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SW820-AP-MMI-010 - Public Intelligence

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1. QU n ees 212 4 8 1 Submarine Combat System SCS 2 2 212 4 8 2 Combat Systems Electronic Space CSES 212 4 8 3 N viga on System ier ore was ER Nes A 212 4 8 4 Weapon Launch Systemi a este dad 212 4 8 4 1 Missile Tube Assembly Ihn o s 212 4 8 4 2 Hydraulic System esu epe teda xx ve RR FR ENS ER a YE Rue NM nd 213 4 8 4 3 Pressurization Vent System 213 10 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 4 8 4 4 Flood and Drain System 2 emen 213 4 8 4 5 Missile Tube Control System 213 4 ONLOAD AND OPREOAD san E 213 4 9 OD POE BA 213 4 9 1 1 Prepare Missile Tube and Ship Systems 214 4 9 1 2 Install Loading Equipment 4 eat HERE a e ads 214 AON Prepare Weapon 215 4 9 1 4 Load Weapon in Missile Tube 2022 215 4 9 1 5 Remove Loading Equipment 2 200 01 005 215 ue 215 4 9 1 7 SSGN Onload Overview 216 4 9 1 8 AUR Onload Sequence
2. 2 277 Status Panel cede RN RS Po VIE cu de esu e ERR OR 278 Mk 14 VLS Canister PHS amp T 2 279 Secure Canister to Mk 23 Tilt Fixture 280 Upright Mk 14 VLS Canister to Vertical Position 281 RGM 109 4 Land Attack TCM Operational Sequence 15 Sheets 282 Multiple All Up Round Canister Fully 297 c Tilt Fixture Mk 23 Mod 0 with Kat B ea vL e 298 Multiple All Up Round Canister MTEL Orientation 299 Cover Viewed in MG us 300 15 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 LIST OF TABLES Table 1 1 Support Equipment 3 104 Table 1 2 Shipboard Equipment Used for TOMAHAWK 5 123 Table 1 3 Reference 2 22 eee ee eee 124 Table 1 4 Abbreviations and Acronyms eh dia VERA ERE TE RADO 133 Table 1 5 Summary of Reports eo astra tana SUA 147 Table 1 6 Common Descriptive Data ere e aa eo tin on e C a a qe 150 Table 1 7 Variant Unique Descriptive Data ss eec osea 154
3. 66 Block IV Tactical TOMAHAWK Missile General Arrangement 67 TACTOM Forward Body ovd re E EX 68 MK 106 Rocket Sao e E 69 Rocket Motoru usus 70 Underwater Protection Devices sie ee OX e EN UR IN 71 Recovery Exercise Module 72 Midbody Section ciosa DR EAR ERE SNR 73 Range Safety System 109 sss teo eh RN RERO RAN a 74 Range Safety System 109D J stes S hr able evite So dia 75 Typical Land Attack Pre landfall Flyout 76 Terrain Contour Matching TERCOM Process 27 TACTOM Aftbody and Tailcone 2 78 Typical Mission Profile 109A C sss 79 Typical Mission Profile 109D 80 CLS Missile Tube Loading and Handling Trainer Assembly 81 Typical Parachute Recovery of REM Equipped Missile 82 TTL Capsules 2 806 te ed TN ES taU eA 83 Electrical and Pneumatic Umbilicals 85 CNU 308 E Shipping 86 Capsule Launching System CLS Mk 45
4. 87 Capsule Launching System CLS 88 All Up Round Simulator AURS Volumetric 89 All Up Round Electronic Simulator AURES Mk 101 90 AURBS AURS Interface 9 Missile Tube Ballast Cal usunta eb pibe ete Pow S Ped eias dad 92 Shipping and Storage Skid Mk 30 93 AUR Simulator Shipping 6 2 2 94 MK AMIS eti et pie eR VES er LADO aede 95 Mk M Ganister 2 Sheets 96 Shipping and Storage Skid 34 2 0 0 07000 98 CLS Submarine Missile Tube Trainer 99 SMET Training Shape te dee ere en dee n T 100 CLS ME 45 Mod 2 Aft Cover nes M avalos 101 CLS Mk 45 Mod 2 Capsule Closure 2 102 SSGN Prototype Multiple All Up Round Canister 103 Explosive Safety Quantity Distance ESQD Arc Restrictions Typical 172 14 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 Figure 2 2 Figure 3 1 Figure 3 2 Figure 3 3 Figure 4 1 Figure 4 2 Figure 4 3 Figure 4 4 F
5. 46 119 PCO ux etait aet utet e im 46 Teen MERC 46 I 2 RECORD BOOKS BEAT SAU us taa 46 1 20 1 PEO W PUB 4440 Record Book for Tomahawk Cruise Missile 47 1 20 2 CMP PUB 4440 2 Record Book for TOMAHAWK Test Missile TOTEM 47 1 21 WEIGHTS AND CENTERS OF 0 72 47 SECTION V CAPSULE LAUNCHING SYSTEM CONFIGURATION 48 1522 AURIDENTIFICATION 35 dux Gp aa aysa 48 1 23 CAPSULE LAUNCHING SYSTEM MK 45 48 MID lk deese om teretes suada wakay aka att ov puedan 48 1 23 Sr tsi 48 1 23 1 2 Capsule Closure Assembly 49 1 23 1 35 98 DOG RI ve ERE ERU IANUE ERO PERPE ER UE ERR e d 50 1 23214 Lateral Support 22 rhet eiie do obere da tere E 50 1 23 1 5 batinclv Seals o ci mu he t De ae MEER DR aues 50 23 0 S paratiom NUTS uay educa o 51 1 23 1 7 Vertical Support Assembly VSA 51 1 23 1 8 Capsule Ex tensions sia ety as 51 1 23 Aft Closure Assembly 51 1235 Cras Generator
6. 26 LII 2 ba d Attack ic ee e 26 1 11 2 1 Forward Body Guidance Section 2 0 0 0 0 0 27 1 11 2 2 Forward Body Payload Section 22 27 27 1 11 3 1 Forward Body Guidance Section 2 00002 28 1 11 3 2 Forward Body Payload Section 28 1 11 4 Block IV Tactical TOMAHAWK 0 29 1 11 4 1 Forward Body Section 2 de 29 1 11 4 2 Midbody Section ie ex UNE 29 1 11 4 3 Aftbody and Tatlcone Section 30 1 11 4 3 1 Air Data Module ADM 3l 1 11 4 3 2 Alternator Voltage Control Converter AVCC 31 1 11 4 3 3 Anti Jam Global Positioning System Antenna 31 1 11 4 3 4 Anti Jam Global Positioning System Receiver AGR 31 1 11 4 3 5 Cruise Missile Airframe CMA Battery 31 1 11 4 3 6 Digital Scene Matching Area Correlator Processor Subsystem 32 1 11 4 3 7 Digital Scene Matching Area Correlator Sensor Assembly 32 1114 38 Fin Control Syst m esa 32 1 11 4 3 9 Guidance Electronic
7. 188 3 1 2 Simulator Present a kant aad oat it 188 3 1 3 Booster Safe Monitor v ro d uae utet E AS 188 3 7 4 Booster Armed Monitor 188 3 7 5 Warhead Safe Monitor 109A only 0 00 188 3 7 6 Warhead Prearmed Monitor 109A only 0002 188 31 7 Missile Bus Monitor ulula Plot etn es dt exuta du e vas ced 188 3 7 8 Missile Enabled uns es o rv v eer oce OR PRAE EE Red da ed 188 3 7 9 Differential Pressure TTL only 2 2 2 2 0 188 SECTION II TORPEDO TUBE LAUNCH 189 CIS UM 189 3 9 MISSILE CAPSULE AND TORPEDO TUBE PHYSICAL INTERFACES 189 3 0 1 Mechanical Interfaces isa Ob NS 189 3 9 2 Electrical and Pneumatic Interfaces 2 189 3 9 2 Umbilical titers oi a o wise akan NE vado Re 189 229222 Pneumatie teslis dan 189 3 10 PRESSURIZATION VENT CONTROL 189 MILSEGCURIDYSSYS TENIS S U RR AA Co reda bad 190 3 12 NAVIGATION SYSTEM 190 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 3 12 1 Navigation Equipment
8. Goran M ei 51 1 23 EE Aft ci Late ate 51 1 23 1 12 Aft Fairing o aso er Ya espe Maya etae 51 1 23 1 13 Instrumentation and Controls 2 2 02 2 22 22 1123 2 C ES MES Mod pan pet ua E stay kusa 52 123 2 Capsule u u tt del ia be di idola bee ya 52 1 23 2 2 Capsule Closure Assembly 53 1232 3 Lateral Support Groups 39 1 23 2 Ac Launch Seals ese oua e S qu a i db ne 59 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 1 23 2 5 Separation Nuts us I pv Fe Ix 54 1 23 2 6 Vertical Support Assembly VSA 54 1 292 Capsule Extensi n ous coto teo o De 54 1 23 2 8 Closure Assembly usay er p EE Leda 54 123 292 Gas Generator esau 54 12352 VVA c daos cise race td ated asd Ca eda 54 525 TT Aft Fairing DEVICE osse mti tert 55 1 23 2 12 Instrumentation and Controls 55 F 234 INERDP MARIANTS zz orbs n umn aya a oa Ne Sedes uda 55 1 24 1 All Up Round Simulator AURS Volumetric Shape 56 1 24 2 CLS Loading and Handling Training Shape Mk 3 Mod 0 56 1 24 3 Balla
9. NE 19 1 122 Chapter 22 S aun tad ductus DV LS Su d 19 Chapter 3 aa e 19 el A Chapterak ees p au SU q up ata d vt e 19 SECTION II TOMAHAWK WEAPON 20 1 2 TWS DESCRIPTION 3 qaqapasqa a hp debida pon 20 1 3 MISSION do x ed d EA epu E OA ares Ltda eos 20 LJA r UP ROUN D dedo e uas betta 20 I4 T Tactical AURS d eva odis 20 142 Exercise AURS a u uA Ee 21 1 5 MISSILE IDENTIFICATION SYSTEM 21 1 6 SUPPORT EQUIPMENT ana akaqa aula 21 1 7 LOADING AND HANDLING TRAINING EQUIPMENT 21 LS DOCUMENTATION 22 IS Record FCR XAR ua 22 1 8 2 Procedural Documentation 22 IK EIU 22 18 222 EVOMIMONS aed 22 1 8 3 Procedural Documentation Terminology 0 0 20 23 1 8 3 1 Procedural Guides oid oa aate n waa m au eda ats 23 1 5 3 2 Operdt ng PrOPed tes 23 18 3 3 Inspectio
10. 7 8 CELL SYSTEM MODULE 276 SS a eR a SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 27 Remote Launch Enable Panel RLEP E LAUNCH ENABLE PANEL gt FWD 277 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 28 Status Panel OPERATION LAUNCH ENABLE BLOWN FUSE INDICATORS 115v 3060 HZ GHTEwP H 3 LOWTEMP SPRINKLER SYSTEM MAGAZINE LOW DELUGE 1 Low DELUGE PRESSURE GAS E HAZARD a 278 4 REVISION 15 27 2009 SW820 AP MMI 010 Figure 4 29 Mk 14 VLS Canister PHS amp T Equipment VERTICAL LIFT LUGS 2 FWD PROTECTIVE COVER SHOCK ISOLATION SKID MK 5 MOD 0 AFT PROTECTIVE COVER MK 17 MOD 0 CANISTER STACKING FRAME 279 MK 27 MOD O SHOCK ISOLATION SKID FORKLIFT POCKET MK 161 MOD 0 SKID eM LASS L SHOCK ISOLATION SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 30 Secure Canister to Mk 23 Tilt Fixture TOP BOTTOM COLLAR QUICK RELEASE PINS 2 VERTICAL POSITION QUICK RELEASE PINS NOTE THE MK 23 TILT FIXTURE SHOWN DOES HAVE ORDALT 16226 INSTALLED
11. sucia ia e RR da 229 2 16 1 5 Postaboadout cerd e ER tte as tetas teta d ds 230 2 16 2 Oc n or e DP e E RC RO 230 416 2 1 Prepare Launcher 230 4 16 2 2 Prepare Grane 230 4 162 3 Remove Weapon SE ae 230 4 16 3 Crossdeck Weapons 231 4 17 OPERATIONAL 231 4 17 Weapon seeds Qa TER Ran RU RO M GU a tat 231 4 17 2 Weapon Avallabilify 35 dest he e de an Rep E os ae wees 231 4 18 LAND ATTACK TCM OPERATIONAL 231 4 18 1 Prelaunch Reprogramming 232 2 18 2 Missile Selection Cac Vlt tus ex ied ete v tutis ins 232 ANS Seletti nen san 232 Cell Missile Preparations 2s olore beoe o ye as edel es boe 232 4 18 5 Select Response Evaluation 232 4 18 6 Mission Assignment 20 uus eese e ere uns er xo ro ree rara e VERS RAN 233 dS os Cono ted mona tu M EE 233 12 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 e e e OO ON E NU A OO E OO e 233 TIS Rocket tO E e
12. 186 3 4 6 Launch Sequence Command 186 3 5 DIGITAL DATA RESPONSES FROM A LAND ATTACK 186 Good Data Word au hole e utu pha h t naska E de 186 3 5 2 Missile Status Word ecc ea pusqa 186 3 6 DISCRETE COMMANDS 0 00 0 186 3 6 1 Booster ale Commande uluya sls veta d ved abes 187 3 6 1 1 Mk 106 Rocket Motor 187 3 6 1 2 Mk 111 Rocket Motor 187 36 2 Booster Armi Command ost teo Pe Re a 187 3 6 2 1 Mk 106 Rocket Motor 187 3 6 2 2 Mk 111 Rocket Motor 187 3 6 3 Warhead Safe Control Command 109A only 187 3 6 4 Warhead Prearm Control Command 109A only 187 3 6 5 Reprogram Command Land Attack only 187 3 6 6 Fire Command or Intent to Launch 0 00 20 187 3 6 7 REM Abort Command 188 3 7 DISCRETE SIGNALS SENT FROM 2 188 S LT Weapon Identificati n
13. 219 4 10 2 Alert Messages and Interloeksz 219 4 11 LAND ATTACK TCM OPERATIONAL SEQUENCE 220 4 11 1 Weapon Preparation 220 4 11 2 Weapon Power Up and Make Ready 2 220 4 11 3 Mission Assignment te sssi e Ra 221 d ILS ysam ara ee mua mama a a ues 221 2 11 3 2 eyed ine ted eds 221 4 11 4 Rocket Motor Capsule Prearm 221 AWS TUDE Ready uy assum anna ankuy ahay A su aaa skay atus 221 2 11 6 Weapon sos gusts ced a da edel es boe 222 4 IIS 222 a E 222 4 11 7 Multiple Launch Salvo Fire 222 11 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 4 12 POSTLAUNCH OPERATIONS E a e ex 222 4 13 LAND ATTACK TCM CASUALTY 22 0 00 222 4 14 BLOCK IV TACTOM OPERATIONAL 223 4 14 T Prelaunch Sequence 223 4 14 2 Launch Sequences e ehe FER ERE RS VS aba s 224 4 14 3 Submarine Weapon System Interfaces 2 2
14. 2 2 4 2 Transfer Navy activities apply wire seals to shipping containers when transferring 5 out of Navy custody Additionally activities apply tamper resistant tape seals to a 109A variant without warhead and its shipping container prior to shipment to the depot or to another intermediate maintenance activity Seal serial numbers identifying data are recorded in the record book 2 3 SAFETY Operations associated with the Weapons System TWS present a number of safety considerations at all levels The TCM contains a number of hazardous components Handling evolutions involve moving heavy weights using dollies or hoists where free wheeling or pendulum effects can occur Operations may have to be performed under adverse conditions where weather or sea state can impact safety During TCM or related equipment maintenance processes personnel may be exposed to various hazardous materials which may require the use of protective equipment or employing special procedures To maximize safety only qualified ordnance certified personnel as specified in NAVSEA OP 4 and OP 5 and NAVSEAINSTS 8020 9 and 8023 2 shall be used to perform TWS evolutions Additionally procedural volumes of this document contain the general safety summary Table 2 1 General Safety Summary as well as generic and specific warnings and cautions to identify potential hazards to personnel equipment These warnings and or cautions appear prior to the
15. 249 SSN 688 Class Submarine Missile Tube 1 251 SSN 688 Class Submarine Hydraulic 252 SSN 688 Class Submarine Pressurization Vent System 253 SSN 688 Class Submarine Flood and Drain 254 SSN 688 Class Submarine Missile Tube Control System 253 Loading Platform Installed cista otio ea pent ea 256 SSN 688 Class Submarine Missile Tube 251 CES Weapon Onload issu ts b itt e IT SER 258 CLS Weapon Seating in Missile Tube 259 Secure CLS Weapon in Missile 42 260 UGM 109 2 Land Attack TCM Operational Sequence 10 Sheets 261 Lifting Adapter and Extension 271 Vertical Launching System Mk 41 40 2 272 Vertical Launching System Mk 41 1 0 273 Vertical Launching System Mk 41 42 0 274 Launch Control Unit CU eher 275 Vertical Launching System Launcher 276 Remote Launch Enable Panel
16. SELECT ARRAY TEA ENGAGE PLAN SUMMARY DISPLAY TEA PLAN ORDER MK RDY SEL STAT DISP AREA MSL SELECTION MAN OR AUTO 286 SW820 AP MMI 010 PLAN ID NUMBER KEYBOARD SELECT MANUAL MSL THEN PLAN P TEA ENTRY ACCEPTED ENTRY VERIF AREA MAN AUTO MAN SEL STAT DISP AREA REVISION 15 27 MARCH 2009 CHAPTER 4 INITIATE ALERT ACK FFK BLW lt 50 MIN CLEAR ALERT AREA INITIATE ALERT ACK FFK MANUAL MISSILE SELECTION REQUIRED P ALERT AREA 287 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 MANUAL MSL SELECT CLEAR CMD LABEL AREA RECOMMEND MANUAL MISSILE SELECT P PROMPT AREA PROMPT AREA SELECT ENTER MANUAL AND SYSTEM MISSILE SELECT CONTROL NUMBER DISPLAY KEYBOARD THEN ARRAY TEA ENTER SELECT PLAN ID ENTER ENTER NUMBER COMMAND TEA PLAN ID KEYBOARD NUMBER KEYBOARD SELECT E MANUAL ENTRY ACCEPTED MSL ENTRY VERIF AREA RECOMMEND SELECT TEA MISSILES DISPLAY PLAN 288 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 IS THIS A BLOCK Ili MISSILE NO RECOMMEND ENTER CURRENT GPS CRYPTO KEY ALERT AREA DATA BEEN PREVIOUSLY INITIATE ALERT ACK FFK CLEAR ALERT AREA INITIATE A
17. 4 8 2 Combat Systems Electronic Space CSES The CSES equipment is shared by both the SCS and the navigation system Computer software programs which include the operational flight program preplanned land attack mission targeting data generated at a shore based Theater Mission Planning System TMPS installation and provided to the submarine prior to deployment platform alignment data and sequential control commands are stored on disks in the CSES The data are loaded into computer memory and sent to the missile on command Missile responses and status are evaluated by the CSES to provide data for displays on TCM status Built In Test BIT checksums and launch countdown 4 8 3 Navigation System SSN VLS capable submarines are equipped with the Electrically Suspended Gyro Navigator ESGN AN WSN 3A V 2 The system consists of two Inertial Measuring Units IMUs and one dual channel Navigation Control Console NCC Velocity and attitude data are generated in raw form by the IMUs and transmitted to the CSES the NCC The raw data are processed by the CSES computers to obtain velocity attitude and position data and then transmitted to the various ship user subsystems 4 8 4 Weapon Launch System The weapon launch system consists of the missile tube assembly and the various ship systems which operate the missile tube assembly during stowage and launch operations The following paragraphs describe the components of the weapon launch system
18. Fuze Booster Assembly Type Type NOTES 27 MARCH 2009 109C FMU 138 B Electropneu matic armed im pact detonated FMU 148 B Electropneu matic armed programmable detonated a Variant with Mk 106 Mod 0 Rocket Motor b Variant with Mk 111 Mod 0 Rocket Motor 155 CHAPTER 1 109D 109E BBU 47 B Elec tropneumatic armed pro grammable deto nated SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Table 1 8 Container Weights and Dimensions ITEM CNU 308 E SHIPPING CONTAINER MK 30 SHIPPING AND STORAGE SKID AUR SIMULATOR SHIPPING SKID MK 14 VLS CANISTER w PHS amp T CNU 308 E SHIPPING CONTAINER MK 30 SHIPPING AND STORAGE SKID AUR SIMULATOR SHIPPING SKID MK 14 VLS CANISTER w PHS amp T WEIGHT empty pounds 1709 2650 2700 3241 kilograms 775 1202 1225 1470 156 LENGTH WIDTH HEIGHT inches inches inches 265 00 34 00 35 00 312 63 40 00 44 00 321 19 39 12 49 88 280 40 34 43 45 centimeters centimeters centimeters 673 86 89 794 102 112 816 99 127 711 102 110 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Table 1 9 Weights of TTL Variants and Related Material ITEM HANDLING WEIGHT LBS Pounds Kilograms Ibs kg TACTICAL AUR UGM 109A 1 4273 1938 UGM 109C 1 4548 2063 UGM 109D 1 439 1992 UGM 109E 1 4510 2046 EXERCISE AUR JUGM 109A 1 4245 1926 JUGM 109A 1 QAST we Tu JUGM 109C 1 4483 2033 JUGM 109D 1 43
19. measuring 248 17 inches long including the nose cover and loading button by 20 97 inches in diameter Capsule components are described in the following paragraphs 1 16 1 1 Nose Cover The capsule nose cover which is made of forged aluminum alloy or a fabric reinforced composite material protects the capsule nose diaphragm and the nose of the missile during stowage and handling Each cover measures 14 48 inches long by 20 95 inches in diameter The aluminum nose cover weighs about 27 pounds and the composite cover weighs about 13 5 pounds Attachment to the capsule barrel is provided by seven screws The cover uppermost screw hole is stencilled TOP to indicate the proper position for installation The nose cover must be removed prior to launch The TCM must be fully depressurized prior to removing or installing the cover 1 16 1 2 Nose Diaphragm The nose diaphragm consists of a neoprene impregnated nylon cloth diaphragm a capsule to diaphragm seal four leashes and a steel attachment ring The nose diaphragm 15 shaped to match the contour of the missile The diaphragm attaches to the capsule barrel with 24 screws 1 16 1 3 Capsule Barrel The capsule barrel is a seamless corrosion resistant steel tube 232 88 inches long by 20 97 inches in diameter Four rows of 12 flow slots each are located at about three quarters of the length of the barrel to permit the entry of torpedo tube launch pulse pressure Another single row of nine flow slots is
20. 216 4 9 1 9 Organizational Level Preparations 20 20 0 21202 216 4 9 1 10 Installing Loading Equipment 216 49 1 11 Uprighting and Inserting opere erro er rre x er unns 216 4 9 1 12 Removing Loading Equipment 221 00 216 4 9 1 13 Organizational Level Closeout Operations 217 ASD 217 4 9 2 1 Prepare Missile Tube and Ship Systems 217 4 9 2 2 Prepare Spent CLS for Offload eter re e n e ees 217 4 9 2 3 Prepare Weapon for Offload 1 218 4 9 2 4 Install Offload Equipment 218 4 9 2 5 Remove Weapon from Missile Tube 74 0 218 4 9 2 6 Remove Offload Equipment oe erar er ato pa T ea red in ded 218 4 9 2 7 Secure Missile Tube and Ship Systems after Weapon Offload 218 4 9 2 8 Post Launch P V Refurbishment after Spent CLS Offload 219 4 9 2 9 Post Launch Missile Tube Refurbishment after Spent CLS Offload 219 4 9 2 10 SSGN Offload Overview 2 219 4 10 OPERATIONAL 219 Weapon NM DO ceed
21. 233 4 15 5 MISSHe ACtIVatI0n cete euh epa petu pe UAR Iu aper HUE 233 4 18 9 Rocket Motor Ignition and Missile Release 233 2 15 1 Cell Saling e unu ea i m nbn BOE TER HORSE XI RE RENE S UN Hd 234 4 19 POST EAUNCH ou ue tu aqu REY RS a AAA Q ua E E E 234 4 20 LAND ATTACK CASUALTY 2 234 13 SW820 AP MMI 010 Figure 1 1 Figure 1 2 Figure 1 3 Figure 1 4 Figure 1 5 Figure 1 6 Figure 1 7 Figure 1 8 Figure 1 9 Figure 1 10 Figure 1 11 Figure 1 12 Figure 1 13 Figure 1 14 Figure 1 15 Figure 1 16 Figure 1 17 Figure 1 18 Figure 1 19 Figure 1 20 Figure 1 21 Figure 1 22 Figure 1 23 Figure 1 24 Figure 1 25 Figure 1 26 Figure 1 27 Figure 1 28 Figure 1 29 Figure 1 30 Figure 1 31 Figure 1 32 Figure 1 33 Figure 1 34 Figure 1 35 Figure 1 36 Figure 1 37 Figure 1 38 Figure 1 39 Figure 1 40 Figure 1 41 Figure 2 1 REVISION 15 27 MARCH 2009 LIST OF FIGURES Dati Atta Ck caue 61 Cruise Missile Guidance Set CMGS 62 Land Attack 63 Digital Scene Matching Correlation 5 64 Eand Attack 4 2 55 46 525 uam EE Uu esa 65 Land Attack 1090 Payload Section
22. 4 224 4 14 4 TOMAHAWK Strike Network In Flight Communications 225 414 5 GPS Missile Interface 225 SECTION IV VERTICAL LAUNCHING 2 227 LAUNCH PLATEORMIS EE RR ER II Mead 227 415 4 bautien Control Unit ivi eu c aH a sta 227 fe vua 227 4 13 2 1 B Cell Module iu sorde terea b a dat 224 4 15 2 2 8 Gell System Module 2 227 4 15 2 3 5 Cell Strikedown Module 7 0 0 2000 402 228 4 15 3 Remote Launch Enable Panel RLEP 2 2 2202 228 ASA Status Panel nn eO Nr chan px e Ex e Fe E 220 4 15 5 TOMAHAWK Weapon Control System TWCS 228 4 15 52 Track Control Group TCG 228 4 15 5 2 Launch Control Group LCG 228 4 16 ONLOAD OFFLOAD AND CROSSDECK 228 416 1 MONO AR e toe i anon eas 228 A T6 1 l Prepare Jaune biet SRM 229 416 12 Prepare 229 4 16 1 3 Prepare Weapon Ex oa REX E eA a ES 229 2 16 L4 Dodd Weapon a
23. 4 5 LAND ATTACK OPERATIONAL SEQUENCE 207 4 5 1 Weapon Preparation and Tube Loading 207 JS sha unta Ro Sa 207 se ho de M 207 4 5 2 Weapon Power Up and Make Ready 208 LITUANIE 208 452 2 HE 208 DE De ida 208 2 5 3 Mission Assignment xut zc osi es det vea e e Oe A VE ER NER 208 doo ddl dtr 3 209 DW cp 209 AS A Tube READY us a u astay akaw yq rb blu unguis 209 4 5 5 Rocket Motor Arming erre a x ph EI 209 4 5 6 Warhead Prearming UGM 109A only 2 2 2 209 4 5 7 Weapon naan tede d iu EE MR 209 4 6 POST LAUNCH OPERATIONS 22 210 2 6 1 Tube RESET uuu una poto nteger putre Ros edi Vater tob Pte qon dud 210 2 62 Capsule Ejection Dese e ie p D i b Tis 210 210 210 4 6 3 Capsule Return to Stowage 2 22 210 4 7 LAND ATTACK CASUALTY 0 0 211 SECTION III CAPSULE 6 8 2 2 212 5 LAUNCH
24. FTCTU GEU GFE GN GPS GPSS GS GSM H amp S HEPA HERO Hg HPU HRA HTML HYD IAW UO IC ID IFF 27 MARCH 2009 CHAPTER 1 DEFINITION Extend Extraction Fleet Ballistic Missile Fleet Calibration Activity Fire Control System Federal Logistics Data Forward Flange Installation and Removal Tool Firing Interlocks Closed Frequency Modulation Flash Point Fleet Training Center Training Unit Guidance Electronics Unit Government Furnished Equipment Gaseous Nitrogen Global Positioning System Global Positioning System Subsystem Guidance System Guidance Set Mockup Health and Status Helium High Efficiency Particulate Air Hazards of Electromagnetic Radiation to Ordnance Mercury Hydraulic Power Unit Hydraulic Ram Assembly HyperText Markup Language Hydraulic In Accordance With Initial Outfitting Input Output Interlocks Closed Inside Diameter Identification Identification Friend or Foe 137 SW820 AP MMI 010 REVISION 15 ABBREVIATION ACRONYM ILSP IMA IMMM IMU InHg INS INST INSTL IP IPB IRTU ISEA ITL IW ER JRS JTA KB KW LA LCG LCM LCU LFS LLCE Lo temp LOG LOGAIR LP LSEQ LTP MAC 27 MARCH 2009 CHAPTER 1 DEFINITION Integrated Logistics Support Plan Intermediate Maintenance Activity In Flight Mission Modification Messages Inertial Measuring Unit Inches of Mercury Insertion Inertial Navigation Set Installation Instruction Installation Inspection Point Illustr
25. UGM 109A C D Routing 0008 199 SW820 AP MMI 010 REVISION 15 Electrical Umbilical Attached to A Y Connector Port Tube Pneumatic Umbilical Lanyard Secured to Retention Fixture Looking Forward UGM 108E Routing 27 MARCH 2009 CHAPTER 3 Pneumatic Connector Attached to Capsule Electrical Connector Keyway at Bottom Electrical Connector Keyway at Bottom Attached to AUR Umbilical Attached to A Y Connector Starboard Tube Looking Forward 200 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 3 Figure 3 2 CLS Electrical Umbilical Routing P1008 MAIN P1304 UMBILICAL MISSILE UMBILICAL TABLE CABLE CONNECTOR UMBILICAL CABLE CLS EXTERNAL SURFACE LAUNCH CONTROL SPARES INTERCONNECTING Pina LIQUID LEVEL SENSOR 3 132 105 6 LIQUID LEVEL SENSOR 107 4107 1078 MISSILE d MISSILE AWAY SWITCH AWAY E SWITCH Um CONTROL CABLE 11 J110 P110B MISSILE P111 P114 i SEPARATION NUT INITIATOR 3124 P124 SEPARATION 120 1 4120 P1208 SEPARATION INTERCONNECTION CABLE SEPARATION NUT PRESSURE ACTUATED SWITCH P117 SEPARATION NUT INTIATOR ELS VERTICAL piis CLS CLOSURE SUPPORT i ASSEMBLY SEPARATION INTIATOR CLS 45 CAPSULE 201 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 3 Fig
26. UGM 109A with W80 Warhead Rocket Motor Mk 106 Mod 0 and Liquid Sustainer Engine Land Attack UGM 109A w o W80 Warhead Rocket Motor Mk 106 Mod 0 and Liquid Sustainer Engine Land Attack JUGM 109A M S w or w o Inert W80 Warhead REM or RSS Rocket Motor Mk 106 Mod 0 and Liquid Sustainer Engine Land Attack Exercise JRGM JUGM 109C M S w Inert Warhead REM or RSS Rocket Motor Mk 106 Mod 0 Mk 111 Mod 0 and Liquid Sustainer Engine Land Attack Conventional Exercise JRGM JUGM 109D w Inert Submunitions or Functional Indicator BLU 97 B Payload Kit 003 RSS Rocket Motor Mk 106 Mod 0 Mk 111 Mod 0 and Liquid Sustainer Engine Land Attack Conventional Submunitions Exercise JRGM JUGM 109E w Inert Warhead REM or RSS Rocket Motor Mk 135 Mod 0 and Liquid Sustainer Engine Land Attack Conventional Exercise 178 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 2 Table 2 3 Pyrotechnic and Hazardous Materials Data ITEM ROCKET MOTOR CONVENTIONAL WARHEAD PAYLOAD MODULE FUEL JP 10 CLS SEPARATION NUT INITIATORS 4 CLS GAS GENERATOR CLS IGNITER CLS GAS GENERATOR EBW INITIATOR GN BOTTLES He BOTTLES HYDRAULIC RESERVOIR AC CUMULATOR BLEED AIR VALVE FUEL SYSTEM ISOLATION VALVE BOOSTER IGNITER BOOSTER SEPARATION RING SHROUD EXPLOSIVE BOLT CABLE CUTTER INLET COVER THRUSTER HAZARD Mk 106 0 304 Ib propellant Mk 111 0 349 Ib propellant Mk 135 0 322 Ib propellant WDU 25 B 378 Ib explosi
27. launchable inert test vehicle having the same general configuration as a tactical TTL AUR that when used with the Digital Missile Simulator Mk 75 is able to simulate the launch sequence of any TTL TCM variant The electrical umbilical issued with the TOTEM may be a used AUR electrical umbilical or the TOTEM Umbilical Cable Assembly P N 1553 5120 The pneumatic umbilical will be a used tactical umbilical Use of unused tactical umbilicals with TOTEM 15 not authorized Used tactical umbilicals are readily identified by an orange identification band 1 18 2 Encapsulated No Launch No Wet TOTEM NL NL TOTEM is a modified non launchable TOTEM that is used to train submarine crews in TTL operations and to verify operability of the TTL pressure vent system aboard the submarine The electrical umbilical issued with the NL TOTEM may be a used AUR electrical umbilical or the TOTEM Umbilical Cable Assembly P N1553A8120 The pneumatic umbilical will be a used tactical umbilical Use of unused tactical umbilicals with NL TOTEM is not authorized Used tactical umbilicals are readily identified by an orange identification band 1 18 3 Crew Training Shape CTS UTM 109 1A The CTS is a modified non launchable TOTEM used to train and certify submarine crews in TTL loading and handling procedures for the UGM 109A 1 variant At Type Commander discretion the CTS may be used aboard submarine tenders and at shore bases to train personnel in
28. 20 W20 WARHEAD 109A 21 DSMAC WINDOW COVER THRUSTERS 109 0 22 GUIDANCE SET THERMAL BATTERY 109A C D 23 PARACHUTE COMPARTMENT COVER 2 REM 24 MAIN PARACHUTE REEFING CUTTERS 2 REM gt 25 DRAG PARACHUTE REEFING CUTTERS 2 REM 26 BATTERY 2 REM 27 PARACHUTE RISER COMPARTMENT COVER THRUSTER REM 728 MAIN PARACHUTE GROUND DISCONNECT CARTRIDGE REM 33 29 RISER SWING ARM RELEASE CARTRIDGES 2 REM 30 FLOTATION SYSTEM GN2SUPPLY VALVES 2 REM 3 31 RSS THERMAL BATTERY 109 32 SEPARATION NUT INITIATOR 4 33 CLS GAS GENERATOR 45 ARMING FIRING DEVICE AND IGNITER ASSEMBLY MK 111 Rooker MOTOR 46 GAS GENERATOR AND HYDRAULIC RESERVOIR ACCUMULATO 47 SPECIAL INSTRUMENT LITHIUM ACTIVE BATTERY Wwe 48 RECOVERY BEACON LITHIUM ACTIVE BATTERY 6008 REM 34 EBW INITIATOR 173 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 2 RSS THERMAL BATTERY 306 1090 SHIELDED MILD DETONATOR CORD AND TRANSFER TIPS JUGM UGM 108D SUBMUNITION PACK SEPARATOR ASSEMBLY JUGM UGM 1090 INITIATOR MANIFOLD JUGM UGM 103D RSS THERMAL BATTERY JUGM 109D FUEL MODULE 2 JUGM UGM 109D BLU 87 B SUBMUNITION JUGM UGM 189D BLU S7 T 1 B SUBMUNITIONS JUGM 109D SUBMUNITION PACK EJECTOR ASSEMBLY JUGM UGM 1090 PAYLOAD COVER JETTISON SYSTEM JUGM UGM 10901 174 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 2 Table 2 1 General Safety summary G
29. 3 16 PRESSURIZATION VENT P V SYSTEM The P V system features automatic independent missile tube controls to replenish internal AUR pressure during stowage in the missile tube and to pressurize vent the space below the capsule closure assembly within a specified range of positive pressure over the underhatch volume pressure prior to TCM launch A differential pressure transducer in the missile tube monitors pressure above the capsule closure assembly and sends a continuous signal to the Vertical Launch Console VLC When the underhatch volume pressure is not within prescribed limits the signal causes a pressurization vent control valve to activate to permit pressurizing venting of the 193 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 3 AUR to occur in order to maintain pressure within band When underhatch volume pressure is not equal to sea ambient pressure or AUR pressure is not within prescribed limits the system inhibits launch until required pressurization venting has occurred and the PRESSURE IN BAND indication is restored Immediately prior to TCM launch the P V control valve is closed to terminate pressurization venting and to prevent reflood water or missile launch by products from entering the ship 3 17 MISSILE TUBE CONTROL SYSTEM The Missile Tube Control System monitors the status of the missile tubes and supports launch The system provides all the interfaces between the ship systems and the submarine fire control syste
30. 57 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 SECTION VI VERTICAL LAUNCHING SYSTEM CONFIGURATION 1 28 AUR IDENTIFICATION Each tactical and exercise AUR is identified by a unique numeric six digit serial number The serial number for all configurations is located on a nameplate in the wing slot but is inaccessible to activities below depot level At the depot the AUR configuration and serial number are printed in the upper right hand corner of the Record Book for TOMAHAWK Cruise Missile TRB PEO W PUB 4440 which accompanies each AUR Additionally an MIS data plate is placed on the AUR and a matching data plate is placed in the TRB Activities below depot level verify AUR identity by comparing TRB data with data contained on an identification plate and an MIS data plate on the aft end of the Mk 10 Canister prior to encanisterization of the RGM 109 2 variant into the Mk 14 Canister A detachable MIS data plate is removed from the TRB and placed on the bottom of the Mk 14 Canister near the deluge connector after encanisterization to identify the VLS configured RGM 109 4 variant RGM 109C 2 RGM 109D 2 and RGM 109E 2 as well as their corresponding exercise variants are employed in VLS configurations after encanisterization in the Mk 14 Canister 1 29 CANISTERS 1 29 1 Mk 10 Canister The Mk 10 Canister Figure 1 34 Mk 10 Canister is used to encanister RGM 109 2 variants and measures 253 5 inches long and 21 2 inches in di
31. HOLDBACK ASSEMBLY ACCESS 2 14 ANCHOR PIN ASSY 15 PHEUMATIC COUPLING PROTECTIVE COVER 16 ELECTRICAL CONNECTOR ACCESS PROTECTIVE COVER 17 LATCH 18 PIP PIN 2 1 Capsule 1 83 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 UM SS Differential Pressure Transducer Barrel closure Lanyard attachment access Holdback assembly access 2 Pneumatic coupling A Retention Fixture Latch Locking Hole Pneumatic coupling protective cover 16 Electrical connector access protective cover M Capsule Mk 3 Mod 0 Nose Cover Diaphragm Slide Strips Barrel Guide stud 2 Forward Slot cover Forward flow slot 12 Aft slot cover Aft flow slot 12 84 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 24 Electrical and Pneumatic Umbilicals PIP MATES WITH CAPSULE PNEUMATIC COUPLING MJ LANYARD HOSE 272 x Fg ma B PNEUMATIC UMBILICAL ASSEMBLY POLARIZATION JAND PULL LANYARD INDICATOR BREECH DOOR CLAMP LOCATION BAND O RING MATES WITH BREECH DOOR Y CONNECTOR ELECTRICAL UMBILICAL ASSEMBLY SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 25 CNU 308 E Shipping Container FORWARD COVER AFT COVER QUARTER TURN FASTENER LIFTING TIE DOWN RING ATTACHMENT PAD EYE AND RUB PLATE FITTING HANDLIFT TRUCK 45 86 SW820 AP MMI 010 REVISION 15 27
32. LOADS PIRE ORDERED 267 4 REVISION 15 27 2009 SW820 AP MMI 010 268 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 269 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 270 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 4 21 Adapter ae 271 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 22 Vertical Launching System Mk 41 Mod 0 61 CELL MISSILE LAUNCHER Sees 52 Dm SZ SD CANISTER ADAPTER PLENUM CELL COVER 272 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 23 Vertical Launching System Mk 41 Mod 1 273 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 24 Vertical Launching System Mk 41 Mod 2 COMBAT SYSTEM EQUIPMENT ROOM NO 1 LAUNCH CONTROL UNIT 2 MK 211 MOD 1 STRIKEDOWN MODULE 2 4 THELCUs ARE LOCATED IN COMBAT SYSTEM EQUIPMENT ROOMS NO 1 AND NO 3 274 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 25 Launch Control Unit LCU DATA TERMINAL GROUP OL 267 V UYK DATA CONTROL MULTIPLEXER 275 4 27 2009 REVISION 15 SW820 AP MMI 010 Figure 4 26 Vertical Launching System Launcher 8 CELL STANDARD MODULES URES Wm 5 CELL STRIKEDOWN MODULE AS
33. SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 5 Land Attack 109D FIGURE 1 6 27 24 8 99 80 PAYLOAD SECTION P ati STA 18 35 7 GUIDANCE SECTION 1 GUIDANCE SET 16 FIN SERVOACTUATOR 3 2 OSMAC OR DSMAC 1 A SET 17 ROCKET MOTOR 3 AVIONICS THROUGH ACCESS COVER 18 FIN 4 4 PAYLOAD COVER 2 19 ENGINE INLET 5 WING 20 PITOT HEAD 8 WING ACTUATOR 21 FUEL EXPANSION BLADDER 7 STANDARD MISSION COVER 22 FUEL DEFUEL PANEL 8 LATERAL THROUGH SLOT 23 FUEL HOPPER 8 DOOR ACTUA 24 COOLANT PUMP GUIDANCE SET 10 AIR DATA PACKAGE 26 DSMAC ILLUMINATOR UNIT REFLECTOR 11 MISSION CONTROL MODULE 12 PNEUMATIC STORAGE BOTTLE HOUSING 13 DC GENERATOR REGULATOR 14 SUSTAINER ENGINE 15 FIN POWER SWITCHING AMPLIFIER 65 26 ILLUMINATOR UNIT ELECTRONIC ASSEMBLY 27 RADAR ALTIMETER ANTENNA 2 28 SENSOR WINDOW COVER amp THAUSTER 29 NOSE FAIRING 30 GPSS RECEIVER PROCESSOR UNIT 31 GPSS ANTENNA MODULE SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 6 Land Attack 109D Payload Section FUEL MODULE 2 SUBMUNITION PACK 24 TACTICAL PAYLOAD COVER REMOVED PAYLOAD SECTION PAYLOAD COVER REMOVED EXERCISE MISSILE B 66 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 7 Block IV Tactical TOMAHAWK Missile General Arrangement 2 Upper Shroud a Rocket Motor GPS
34. Submarine Tenders A telescoping tug bar is used with the dolly dollies are modified with the Adapter Dolly P N SK5711 735 Seals the bottom of a launcher cell to permit launch gases to be vented through the uptake into the atmosphere Seal the Mk 14 Canister in the launch cell to divert launch gases to the atmosphere via the plenum cell 123 ILLUSTRATION SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Table 1 3 Reference Documentation DOCUMENT NUMBER 0348 LP 078 1000 0924 LP 066 6010 6020 0967 LP 529 6010 0978 LP 040 0910 ASME ANSI B30 5 1989 ASME ANSI B30 8 1988 CINCLANTFLTINST 8010 4 CINCPACFLTINST 8010 12 CMP PUB 4440 2 CMP PUB PMA 280 1203 CMP PUB PMA 280 1207 CMP PUB ULSS 4105 D CMP PUB ULSS PMA 280 1205 CMPINST 5102 1 Code of Federal Regulations Title 46 TITLE Record Book All Up Round AUR Volumetric Shape Record Book Missile Tube Ballast Can MTBC Technical Manual for Magazine Sprinkler System Electrically Suspended Gyro Navigator ESGN AN WSN 3A V 2 Dual Miniature Inertial Navigation System DMINS AN WSN 1 V 2 Weapon Delivery Systems Equipments Manual for SSN 688 Class Submarines Safety Standards for Mobile and Locomotive Cranes Safety Standards for Floating Cranes and Floating Devices Atlantic Fleet Conventional Ordnance Management Manual Pacific Fleet Ammunition Requisitioning and Reporting Guide Record Book for TOMAHAWK Test Missil
35. VSA and capsule extension as well as handling and support equipment The upper flange has penetrations for the pressure vent port the annular space vent line and a slot which allows the flat umbilical cable to pass through the flange There are two lip seal grooves around the circumference of the upper flange to provide a seal at the upper end of the missile tube or AUR cell There are two alignment slots located at 53 and 233 azimuth which engage pins at the upper end of the tube cell The alignment slots serve to align the AUR in the tube cell as it is seated When installed in the tube cell the AUR 15 supported and secured by eight retention segments on its upper flange Three of the retention segments provide mounting for cable clamps The segments secure the capsule by exerting downward pressure on the upper closure ring while exerting upward pressure in a groove on the inside surface of the tube cell upper flange 52 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 The aft closure is located below the VSA and capsule extension The aft closure assembly encloses the lower end of the capsule and provides a mounting surface for the gas generator mechanism and electrical components The umbilical cable attaches to a through connector which is installed in the aft closure assembly The cable is unbonded 6 1 inches forward of the aft end of the composite capsule The capsule has a stripe at the expended capsule CG location 1 23
36. a Rate Gyro Accelerometer Package RGAP a Missile Radar Altimeter MRA an Analog Filter Assembly AFA a Warhead Interface Unit WIU a DC DC Converter Module DCM and a Battery Power Unit BPU The CMGS attaches to the payload section via a mechanical hinge and link assembly using five mounting bolts This arrangement permits the CMGS to be swung aside after positive retention nose cone removal in order to install and remove the warhead without having to break electrical connections between the airframe and CMGS The DSMAC or DSMAC set mounts aft of the CMGS The GPSS Receiver Processor Unit RPU mounts aft of the RMUC A window for the DSMAC lens is provided on the bottom centerline along with a pyrotechnically jettisoned cover Shields protect the DSMAC set from electromagnetic interference EMI The illuminator assembly strobe which lights the scenes for night flights also mounts on the bottom centerline Two fuel lines run through the section for CMGS cooling A fuel tank is also provided 1 11 3 2 Forward Body Payload Section The unique payload section Figure 1 6 Land Attack 1090 Payload gt extending from station 18 35 to station 99 80 houses four submunition dispenser modules 24 submunition packs two fuel modules electrical harnesses pyrotechnic transfer lines initiators and detonators Each submunition pack consists of an ejection system and a separator assembly Two submunition packs conta
37. a maximum of two other conventional TOMAHAWK AURs in their launch configuration off loaded from combatant may be placed in a nose to tail configuration in specially positioned chocks or shipping containers on the pier All four missiles must be in a nose to tail configuration in groups of two and each group of two must be positioned no closer than 10 feet side to side or 5 feet nose to tail Figure 2 1 Explosive Safety Quantity Distance ESQD Arc Restrictions Typical 2 3 1 3 The use of these procedures will prevent sympathetic detonation and maintain an of one conventional TOMAHAWK AUR If ESQD restrictions are less than 600 feet to inhabited buildings these procedures will not provide relief and the requirements of NAVSEA OP 4 or OP 5 prevail Conversely where ESQD arcs to inhabited buildings are well beyond 600 ft arc the ordnance handling activity may utilize the procedure to reduce thus enhance the effect of the available ESQD arc These procedures are not applicable in magazines bunkers workshops or inside ships 2 3 0 Hazardous Components hazardous components range from the nonexplosive combustible JP 10 fuel used by the TCM to cruise to the target comparatively low explosive electro explosive devices EED used to separate the TCM from its launching device to the highly destructive high explosive warhead Also included in the general category of explosives are the solid propellant rocket motor and
38. systems for launch from torpedo tubes Prime consideration for selecting a specific weapon for launch should be the time required to prepare and launch a single TCM or in the case of salvo fire the time required to prepare and launch multiple TCMs 4 10 2 Alert Messages and Interlocks Various alert messages and firing interlocks are used to warn operators or inhibit launch when conditions exist that could impact missile performance endanger the submarine or result in the launch of a dud missile Firing interlocks may be either software or hardware interlocks Prior to permitting activation of the FIRE switch the fire control system must receive an indication that the following interlocks are closed 219 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 a OPERATIONAL FLIGHT PROGRAM TRANSFERRED Indicates that the flight program has been successfully transferred to the missile b MISSILE ALIGNED Indicates that the CMGS inertial platform relative to the submarine s inertial reference system has been aligned c MISSION DATA TRANSFERRED Indicates that all data relative to the mission have been transferred to the missile d WITHIN LIMITS Indicates that speed and depth of the submarine are within limits e INPUTS MATCHED Indicates that the CMGS has responded with good MISSILE STATUS missile presetting is complete and launch constraints are satisfied f TUBE IN ACTIVE FIRING SEQUENCE Indicates that the proper tube has been s
39. 2 3 Cruise Electrical Power After the sustainer engine has started and comes up to speed a dual output generator regulator assumes airframe and CMGS electrical loads Output 1 is dedicated to the CMGS and airframe equipment Output 2 serves the fin servoactuator system Load transients occurring on Output 2 have no influence on Output 1 184 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 3 3 2 4 RSS Thermal Battery Activation In the event that an RSS equipped loses cruise electrical power the RSS thermal battery is activated to provide electrical power to close the throttle and initiate fin flip thus aborting the mission 3 3 DIGITAL DATA LINK Communications between the TCM and the launching platform is performed via the digital data lines The lines consist of four pairs of twisted wires 1 true and 1 complement per pair Also provided are shield carry through and a digital 1 power supply return The lines are connected when the launch operator selects the designated missile and disconnected prior to launch The digital data link utilizes serial 17 bit 16 data and 1 odd parity data words The least significant bit is sent first and the parity bit is sent last The first word is always the same in every data block and is used to initialize the CMGS launch platform system interface software The second word is always a control word to request status or identify the data block and the number of data words within the d
40. 2 Mk 10 Variants and Related Material and 1 14 Centers of Gravity for RGM 109 2 Variants respectively Weights of VLS variants are contained in Table 1 15 Weights of VLS Variants 60 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 1 Land Attack 109A FWD BODY 99 80 FUEL SECTION 2 FWD BODY STA eo PAYLOAD section 52 45 se ot STA aw 18 35 1 GUIDANCE SET 2 W80 WARHEAD 3 FUEL EXPANSION BLADDER 4 CMA THERMAL BATTERY DRY WELL RH SIDE 5 WING 6 WING ACTUATOR 7 STANDARD MISSION COVER B LATERAL THROUGH SLOT 3 0008 ACTUATOR 10 AIR DATA PACKAGE 11 MISSION CONTROL MODULE 12 PNEUMATIC STORAGE BOTTLE HOUSING 13 DC GENERATOR REGULATOR 14 SUSTAINER ENGINE 61 MIDBODY d STA 243 33 um m STA 1520 15 POWER SWITCHING AMPLIFIER 18 FIN SERVOACTUATOR 3 17 FIN 4 18 ROCKET MOTOR 19 ENGINE INLET 20 INLET ACTUATOR 21 PITOT HEAD 22 FUEL EXPANSION BLADDER 23 FUEL DEFUEL PANEL 24 FUEL HOPPER 25 COOLANT PUMP GUIDANCE SET 28 RADAR ALTIMETER ANTENNA 2 27 NOSE CONE KIT OR NOSE FAIRING SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 2 Cruise Missile Guidance Set CMGS REFERENCE MEASURING UNIT AND COMPUTER RMUC CHASSIS POWER SUPPLY DC DC CONVERTER MODULE 0 MISSILE RADAR ALTIMETER ANALOG FILTER ASSEMBLY RATE GYRO BATTERY POWER
41. 23 1 12 Aft Fairing Device The aft fairing 15 a cylindrical urethane elastomer which attaches to the aft end of the CLS capsule by eight bolts The aft fairing protects the aft end ofthe AUR during installation into the missile tube Because of its tapered shape the fairing also serves to guide the AUR into the missile tube 51 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 1 23 1 13 Instrumentation and Controls The main electrical umbilical cable runs from a through connector at a penetration in the upper missile tube wall through a slot in the capsule upper flange down the outside of the capsule wall to another through connector in the aft closure The umbilical cable is a flat low profile cable which is bonded to the outside surface of the capsule Three cables are installed within the capsule one cable from the missile one cable from the two separation nuts and one cable from the departure switches The three cables pass through the VSA and connect to three penetration connectors in the aft closure There are three additional cables on the aft side of the aft closure one cable connects the firing unit to the gas generator one cable connects the firing unit to the separation nuts and one cable connects the umbilical cable to the firing unit the missile cable the departure switches liquid sensors and the interconnecting box 1 23 2 CLS Mk 45 Mod 2 The CLS Mk 45 Mod 2 incorporated new designs to successfully integrate
42. 4 Figure 4 10 SSN 688 Class Submarine Missile Tube Assembly HATCH mae FAIRING et BW p aa 2 T BAR ASSEMBLY LATCHING NM E A DEVICE LS LOS T BAR LATCHING DEVICES ARE USED 3 ACTUATOR 558719 AND 55720 MISSILE ae LINKAGE TUBE ASSEMBLIES ONLY LATER SHIPS DIFFERENTIAL NV WILL HAVE ALTERNATE DESIGN PRESSURE PENETRATION HATCH FAIRING PRESSURIZATION ACTUATOR VENT LINE UNDERHATCH VOLUME AUR SENSING SENSING LINES MISSILE TUBE MATCH ELECTRICAL UMBILICAL PENETRATION FLY THROUGH DIAPHRAGM FLOOD AND DRAIN CONNECTION ENVIRONMENTAL SEGMENTED MONITORING RETENTION SENSOR RING CIRCUMFERENTIAL UP SEALS SHOCK PADS 251 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 11 SSN 688 Class Submarine Hydraulic PORT ACCUMULATOR PORT VLS HYD SUPPLY EXT HYD sYs STBD VLS HYDRAULIC supply CONTROL VALVE MANIFOLD TO SHIP SERV HYD SYS RETURN PORT ACCUMULATOR HYD TO EXT HYD 575 potare STBD VLS 71 HYDRAULIC HYD SUPPLY CONTROL VALVE MARIFOLD sup SUPPLY SERV HYD 515 RETURN SUPPLY System AIR FLASK HATCH AND FLOOD amp DRAIN VALVE CONTROL VALVE FLOOD amp DRAIN ISOLATION BACKUP VALVE ACTUATOR FLOOD amp DRAIN EQUALIZATION HULL VALVE ACTUATOR HATCH AND FLOOD amp FLOOD amp DRAIN ISOLATION BACKUP VALVE ACTUATOR FLOOD amp D
43. Alignment 2 2 4 0 0 0 0 190 3 12 2 Velocity and Position Computation irs sce 190 3 12 3 Reset ComputationS uu tau ER vp IR tec 190 3 12 4 Status and Performance Monitoring 190 SECTION IV CAPSULE LAUNCHING SYSTEM 2 2 192 JC ISSGENBRADE 2 edd a HA E NT d VET 192 3 14 CLS UNIQUE ELECTRICAL 192 3 14 1 CLS Unique Prelaunch Electrical Power Requirements 192 CLS Unique ex rx e D ROT e ERN CIT ELT 192 3 14 3 CLS Unique Discrete Responses 192 3 15 MISSILE CAPSULE AND MISSILE TUBE PHYSICAL INTERFACES 193 3 15 1 Mechanical Interfaces coe dada ee a P Fuer dr e drea i praed Dr ta ata 193 2 Electrical Interfaces 5 uu aa sert esce yaa Supa b Eo gor dili das 193 3 16 PRESSURIZATION VENT P V SYSTEM 193 3 17 MISSILE TUBE CONTROL 5 8 2 2 0 2 194 3 17 1 Missile Tube Control Panel 194 3 17 2 Differential Pressure Transducers 194 3 17 3 Environmental Monitoring Sensor 194 3 174 D
44. Antenna RSS Antennas E Fin Deployment Mechanism Turhojet Engine GEU Assembly AGR MCP SPU DCP DSP ADM DSMAC Camera illuminator Converter WDU 36 B Warhead Shroud 67 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 8 TACTOM Forward Body Section 68 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 9 Mk 106 Rocket Motor SAFE AND ARM IGNITER ASSEMBLY 2 gt lt SEPARATION RING ASSEMBLY T MISSILE HOLOBACK ELECTRICAL CONNECTOR 129 LANYARD AND PULL SWITCH HOUSING THRUST VECTOR CONTROL 5 N0ZZLE PLUG MISSILE HOLDBACK ASSEMBLY 69 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 10 Mk 111 Rocket Motor ARMING FIRING DEVICE AND IGNITER ASSEMBLY SEPARATION RING ASSEMBLY MISSILE HOLDBACK ROCKET MOTOR IDENTIFICATION PLATE PNEUMATIC COUPLING ELECTRICAL CONNECTOR Y 1 NOZZLE j o f PLUG k AUR IDENTIFICATION WASHER COVER PLATE 52 ow NOZZLE SEAL PLUG LANYARD amp PULL SWITCH HOUSING MISSILE HOLDBACK ASSEMBLY 70 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 11 Underwater Protection Devices WING SLOT PLUG ORIFICE A WING SLOT PLUGS POSITION OF CONTINUITY SHROUD WHEN INSTALLED SHROUD SEPARATIDN CHARGE ASSEMBLY 2 COVER VENT HOLES MEM VIEW LOOKINGUP PRESSURE RELIEF VALVE B ENGINE INLET COVER CONTINUITY
45. CHAPTER 1 PURPOSE OF REPORT Report receipt of defective AURS or material Report shipping and packaging discrepancies For use by Organizational Level Activities under the cognizance of the Submarine Type Commanders to report damaged faulty or failed equipment ineffective documentation routine requests for technical assistance corrective maintenance and or results of PMS accomplishment for UGM 109C D E AURs and related equipment Report errors omissions or discrepancies or recommend changes to basic manuals Report accident or incident with material loss or damage to any variant creating hazard potential hazard SW820 AP MMI 010 WEAPON SYSTEM RGM 109 4 RGM 109 4 REVISION 15 REPORT CANISTER SHORE AC TIVITY MAIN TENANCE DATA SUM MARY CANISTER MISSILE CON FIGURATION SUMMARY SHORE AC TIVITY MAIN TENANCE DATA SUM MARY 27 MARCH 2009 MEDIA OP NAVINST Form 4790 5 2A NAVSEA Form 4790 5 2B GOVERNING DIRECTIVE NAVSEAINST 4790 6 NAVSEAINST 4790 6 149 CHAPTER 1 PURPOSE OF REPORT Report Mk 14 Canister preventive and unscheduled maintenance and defects Report Mk 14 Canister configuration changes to include encan decan SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Table 1 6 Common Descriptive Data ITEM Engine Designation Type Thrust Rocket Motor Assembly a Designation Type Propellant Control
46. MARCH 2009 CHAPTER 1 Anti Jam Global Positioning System Antenna Anti Jam Global Positioning System Receiver AGR Cruise Missile Airframe CMA Battery Digital Scene Matching Area Correlator Processor Subsystem Digital Scene Matching Area Correlator Sensor Assembly Fin Control System Guidance Electronics Unit GEU Mission Control Input Output MCIO Mission Control Processor MCP Navigation Processor NP Power Filter Unit PFU Pyro and Power Control Assembly PPCA Radar Altimeter RA Satellite Data Link SDL Antenna Satellite Communications SATCOM Data Link Terminal Secondary Power Unit SPU 1 11 4 3 1 Data Module ADM The ADM is used to determine altitude and air temperature using two pressure sensors Analog data is converted to a digital format which compensates for sensor characteristics The ADM provides the Mission Control Input Output MCIO with pressure and temperature data as requested This unit resides in the GEU 1 11 4 3 2 Alternator Voltage Control Converter AVCC The AVCC converts alternator high frequency AC power into two DC voltage outputs used by the missile electrical system during cruise and terminal flight The DC power is filtered by the Power Filter Unit PFU before distribution to missile components 1 11 4 3 3 Anti Jam Global Positioning System Antenna The Anti Jam GPS Antenna is tuned for reception at 1227 MHz and 1575 MHz for military GPS sign
47. MARCH 2009 CHAPTER 1 Figure 1 26 Capsule Launching System CLS Mk 45 LOADING GUARD MAIN UMBILICAL CABLE DECAL 8 1 ELECTRICAL UMBILICAL CABLE 2 CLOSURE PROTECTIVE COVER CAPSULE LOADING COVER 3 UMBILICAL SUPPORT RING 4 CAP COVER 5 CLOSURE PROTECTIVE COVER ASSEMBLY CLOSURE PRESSURE HOSE ASSEMBLY 7 CAPSULE CLOSURE ASSEMBLY 8 MOISTURE AND DUST PLUG 3 CLS IDENTIFICATION PLATE 10 AUR IDENTIFICATION PLATE 2 11 AFT ASSEMBLIES 12 CAPSULE 13 MIS DATA PLATE 2 14 EXPENDED CAPSULE CG SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 27 Capsule Launching System CLS Components ELECTRICAL UMBILICAL CABLE CLS UPPER END COMPONENTS CAPSULE CLOSURE ASSEMBLY LIP SEAL RETENTION SEGMENTS 8 cls MISSILE TUBE MISSILE TUBE SHOCK LAND CLS INTERFACE SUPPORT PAD MISSILE AWAY SWITCHES 2 SEPARATION NUT GAS GENERATOR GAS DEFLECTOR HOLDDOWN STUD VERTICAL SHOCK AND VIBRATION MITIGATION DEVICE VERTICAL SUPPORT ASSEMBLY LATERAL SUPPORT PADS BELLOWS CAPSULE EXTENSION GAS GENERATOR AFT CLOSURE ASSEMBLY INTEGRATED FIRING UNIT EXPLOSIVE BRIDGE WIRE INITIATOR MISSILE TUBE AFT COVER CLS LOWER END COMPONENTS 88 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 28 All Up Round Simulator AURS Volumetric Shape 89 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 29 All Up Ro
48. MISSION PROFILE eem pus 39 Pala pL Prelaunch Phase uuu tad 39 14 2 Launch Phase 39 L 14 3 Boost Phases coded etx E UN UA NIE ER Ese 39 1 14 4 Transition to Cruise Flight 40 ed 40 1 14 6 Terminal Phase 109 40 LET Target Attack Phase 109D ulula vue teda da es 40 1 14 8 Block IV Terminal Phase 41 1 14 9 Recovery Phase REM equipped variants 41 SECTION TORPEDO TUBE LAUNCH CONFIGURATION 42 1HS AUR IDENTIFICATION sau tis ea o E ee AX UE SUVS 42 VAG CAPSULES eti deemed 42 1 16 1 Capsule Mk 1 Mod ecco eur e DEDE re E E eec ens 42 e ca teet ee a A Se ats 42 1 16 1 2 Nose Diaphragm au tert aw A eaa 42 110613 Capsule Barrel eec ero e oa cag C EE CENE eR 42 1 16 1 4 Alignment and Retention Provisions 2 2 43 codem e pn EMI IM M M 43 16 1 6 Barrel Clos eoe p Lech rat ELO 43 1 2615 esse eere M o PO IST Ge Ee DEA 43 1 16 1 5 Protective Ge
49. Midbody Section The midbody section Figure 1 13 Midbody Section extends from Sta 74 0 to Sta 148 0 and contains four access doors tactical mission cover RSS mission cover wing plugs and wing doors three fuel tanks and other electrical components The midbody section structure is a machined A357 T6 casting The skin of this missile is thicker than that of Block III TOMAHAWK The Block IV TACTOM wings are slightly larger than previous generations of TOMAHAWK and measure approximately 40 in in length and 14 in in width The midbody section contains three fuel tanks The lower midbody tank is the largest with a capability of 357 165 and is actually built into the structure of midbody The gravity tank which is a sealed part of the midbody structure similar to the lower midbody tank contains 64 lbs of fuel The hopper tank is the smallest with a capacity of 15 lbs The midbody section houses a fuel metering pump used to send the fuel to the engine and a ullage bladder filled with air that is submerged in the fuel connected to a relief line that passes through the exterior of the missile This system allows for expansion and contraction of fuels and other components The midbody section also houses the following three electrical components for the missile the Inertial Monitoring Unit IMU the DSMAC Illuminator Unit DIU and the radar altimeter antennas 29 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPT
50. N 6510902 Sling Lifting and Tilting Lifting Adapter MTEL Mk 157 Mod 1 P N JCM 14748 002 Sling Pendant Mk 165 Mod 0 P N 6213009 or Mk 165 Mod 1 P N 6213750 Sling Weapon Handling Mk 153 Mod 0 P N 5167582 FUNCTION Handle uncontainerized CLS weapons Remove install AUR Simulator Shipping Skid covers Handle AUR Simulator Shipping Skid Transition the Lifting Adapter and MTEL between vertical and horizontal Interface between lifting device and load Handle Mk 30 AUR Shipping and Storage Skid or Mk 34 AUR Simulator Shipping and Storage Skid 116 ILLUSTRATION SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 EQUIPMENT FUNCTION ILLUSTRATION Socket Special 3 8 inch Remove install Moisture and Dust Plug P N JCM 16654 Assembly Special Hose Assembly Perform Mk 14 Canister nitrogen line P N 6309846 leak check Consists of Regulator Hose Assembly P N 6309846 1 Digital Pressure Gage Hose Assembly P N 6309846 2 Setra Model 360 Pneumatic Test Adapter P N 6309846 3 Rocket Motor Ident Test Used when performing missile Set Box Assy electrical checks 6557811 Stand Deployment Used to support sections of SSN 688 P N 6510854 Class loading platform Stand Deployment Used to support sections of SSN 774 P N 7066384 A3 Class loading platform 117 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 EQUIPMENT FUNCTION ILLUSTRATION Straps Tie down Special Sec
51. NSPCCINST P8010 12 NTP A 20 7703 OD 44979 OPNAVINST 4790 4 OPNAVINST 5102 1 OPNAVINST 5510 1 OPNAVINST 5530 13 OPNAVINST C8126 1 DOD C 5210 41M OPNAVINST 55513 2 27 MARCH 2009 CHAPTER 1 TITLE US Navy Explosive Safety Policies Requirements and Procedures Department of Navy Explosive Safety Policy Manual Reporting of Unsatisfactory Material MILSTRIP MILSTRAP Desk Guide Military Standard Requisitioning and Issue Procedures MILSTRIP Consolidated Hazardous Items List CHIL Afloat Supply Procedures Preparing Hazardous Materials for Air Shipment Reporting of Non Conforming and Quality Deficient Material Obtained Through the Supply Systems Navy Uniform Source Maintenance and Recoverability Codes Disposition of Used or Damaged Material Military Traffic Management Regulations Supply Management of Ammunition Navy Training Plan NTP UGM 109 TOMAHAWK Cruise Missile Submarine Torpedo Tube Launch TTL and SSN 688 Class Vertical Launch System VLS Capsule Launching System CLS Firing Craft Operating Procedures and Checklists for Weapon Loading and Handling Systems SSN 774 Class Ships Maintenance and Material Management 3M Manual Mishap Investigation and Reporting Department of Navy Information and Personnel Security Program Regulation Physical Security Instructions for Sensitive Conventional Arms Ammunition and Explosives A A amp E Nuclear Weapons Security Manual Cruise Miss
52. RF signals to the ground via the rear RA Antenna and processes return signals received from the forward RA Antenna The updated altitude data is provided to the Mission Control Processor and forwarded to the Navigation Processor The altitude data 15 also used for TERCOM navigation 1 11 4 3 16 Satellite Data Link SDL Antenna The SDL Antenna provides the SDLT the ability to transmit and receive RF signals It is designed around center frequencies of 256 MHz and 296 MHz for 5 kHz and 25 kHz channel SATCOM coverage The conformal antenna is made using multi layer micro strip technology and is comprised of a single crossed slot element dual tuned for transmit and receive frequencies with an integrated frequency selective surface 1 11 4 3 17 Satellite Communications SATCOM Data Link Terminal The SDLT is a UHF SATCOM terminal that operates on DOD Demand Assigned Multiple Access channels It is used for data communications between the missile and missile strike controller via satellite The SDLT uses half duplex encrypted data communications and is interoperable with standardized DOD protocols for UHF SATCOM 1 11 4 3 18 Secondary Power Unit SPU SPU receives 28 power from the and provides 15 VDC 15 VDC 5 VDC and 43 3 VDC power to the GEU and other avionics sub assemblies This unit resides in the GEU 1 11 5 Body Sections Common to 109A C D The midbody aft body and propulsion sections are common to the 10
53. SSN 688 tools water debris etc from entering empty missile tube Cover Counterbore Installed on missile tube aboard P N 7066384 73 SSN 774 class to prevent personnel SSN 774 tools water debris etc from entering empty missile tube Cover Counterbore Inserted into the individual AUR P N 7124611 001 stowage locations supported on the Datum B of SSGN MAC AUR cell It permits inspection of the counterbore area prior to loading and prevents items from falling into the AUR cell 108 SW820 AP MMI 010 EQUIPMENT Cover Missile Tube Muzzle Hatch and Magnet Protective P N 101 5951066 54 SSN 688 Cover Missile Tube Muzzle Hatch and Switch Probe Protective P N 7066384 72 SSN 774 Cover Muzzle Face Protective P N 101 5951066 49 Cover Safety MTEL P N JCM 14566 001 Cover VLS Missile Tube CLS Spent Capsule P N 6510965 Cradle Mk 33 Mod 0 P N 6213118 REVISION 15 27 MARCH 2009 FUNCTION Protect muzzle hatch magnets in hatch opening of submarine Used to prevent damage to muzzle hatch gasket sealing surface in missile tube Installed on MTEL prior to CLS weapon onload after offload Protects MTEL missile tube and MAC cell SSGN Installed over spent CLS to prevent personnel tools debris etc from entering spent capsule Secure and transport TTL and Mk 10 weapons by truck and small boat 109 CHAPTER 1 ILLUSTRATION SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER
54. Safe Arm Igniter Assy Rocket Motor Assembly b Designation Type Propellant Control Safe Arm Igniter Assy Electrical System Shroud Converter Type Input Output Guidance Set Battery Type Output Airframe Battery Type Output 1 Output 2 Engine Generator Regulator Type DESCRIPTION F107 WR 400 a or F107 WR 402 b Turbofan 600 Ib Mk 106 Mod 0 Single chamber fixed nozzle Arcadene 228G solid grain 304 Ib Jet tab thrust vector Electromechanical dual initiator Mk 111 Mod 0 Single chamber omnidirectional nozzle 25201 solid grain 349 Ib Nozzle thrust vector Electromechanical dual initiator AC DC 115 200V 400Hz 3 phase Y 27 5 28 5 Vdc Thermal 23 33 Vdc Thermal dual output 25 32 Vdc 26 44 Vdc Dual output 150 SW820 AP MMI 010 REVISION 15 ITEM Output Output 2 REM Batteries 2 c Type Output RSS Battery d Type Output Fuel Pneumatic System Airframe Supply Bottle Pressure Volume TVC Supply Bottle e Pressure Volume g Volume h REM Flotation Supply Botles 2 c Pressure Volume Hydraulic System f Hydraulic Reservoir Accumulator Pressurization Vent System Transducer g Type Range Pressure Relief Valve g Type Cracking Pressure 27 MARCH 2009 CHAPTER 1 DESCRIPTION 28 1 Vdc regulated 24 40 Vdc semi regulated Silver oxide zinc remotely activated 25 32 Vdc Thermal 23 33 Vdc Propellant high density
55. TOMAHAWK Weapon System planning identified requirements for support test and handling equipment aboard submarines surface ships submarine tenders shore bases and training activities Requirements include equipment already in the Navy inventory as well as peculiar equipment designed and developed for TWS unique application Table 1 1 Support Equipment Description gt consolidates and provides identifying data for equipment required for TWS evolutions at submarine and surface launch operational and support activities Table 1 2 Shipboard Equipment Used for TOMAHAWK Support identifies on board submarine tender and surface ship equipment that is used to support TWS evolutions 1 7 LOADING AND HANDLING TRAINING EQUIPMENT The CLS Missile Tube Loading and Handling Trainer Assembly Figure 1 21 CLS Missile Tube Loading and Handling Trainer Assembly is a facsimile of an SSN 688 1 submarine missile tube that 15 used to train submarine tender and shorebase personnel in all facets of CLS onload and offload evolutions This trainer can be used to simulate the SSN 774 Class platform as well as the SSN 688 I For SSGN 726 class the Submarine Missile Tube Trainer SMTT Assembly Figure 1 37 CLS Submarine Missile Tube Trainer Assembly emulates MAC AUR cells for onload and offload training evolutions Installation of an SSN top plate over SSGN platform transforms the trainer assembly from SSGN to SSN use 21 SW820 AP MMI 0
56. Table 1 8 Container Weights and 00 0 2 2 156 Table 1 9 Weights of TTL Variants and Related Material 157 Table 1 10 Centers of Gravity for TTL Variants 159 Table 1 11 Weights of CLS Variants and Related Material 2 161 Table 1 12 Centers of Gravity for CLS Variants 2 22 164 Table 1 13 Weights of RGM 109 2 Mk 10 Variants and Related Material 165 Table 1 14 Centers of Gravity for RGM 109 2 22 166 Table D 15 Weights OF V LS Variants ou sui oe ded Eee urbes rca e 167 Table 2 1 General Safety Summary 175 Table 2 2 Storage and Hazard Data ap olo e NO aet dx 178 Table 2 3 Pyrotechnic and Hazardous Materials Data 179 Table 3 1 Land Attack CMGS Alignment 203 Table 4 1 Missile Availability Factors 301 16 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 FOREWORD FOREWORD SCOPE This document consists of four volumes which provide information data and procedures for operations and support of the TOMAHAWK Weapon System TWS a Volume 1 SW820 AP MMI 010 TOMAHAWK CRUISE MISSILE SYSTEM DESCRIPTI
57. UGM 109A 1 handling procedures 1 18 4 Warhead Installation Trainer WIT Mk 35 Mod 0 The WIT is an inert non launchable facsimile of the UGM 109A 1 that is used to train and certify designated personnel in all aspects of W80 Warhead installation and removal 45 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 1 18 5 TOMAHAWK Fitment Shape TOMFISH Mk 1 Mod 0 The TOMFISH is an inert non functional ballasted shape that duplicates the physical dimensions weight and center of gravity CG of a TTL AUR The TOMFISH is used by shipyards and Fleet activities to test and certify TTL handling loading and stowage capabilities aboard submarines and submarine tenders 1 18 6 Commercial Off The Shelf TOMAHAWK Test Missile COTS TOTEM The COTS TOTEM is a non launchable assembly comprised of an inert Pressure Vent Test Vehicle PVTV within a capsule The assembly simulates the appearance mechanical interface pressure vent control PVC transducer and PVC ullage characteristics of a Block III AUR It can be used in a dry torpedo tube for flow rate testing or it can be connected as a NL TOTEM with the BBY adapter and Missile Simulator for PVC FCS testing or training in a flooded torpedo tube 1 18 7 Pressure Vent Test Vehicle TOMAHAWK Test Missile PVTV TOTEM The PVTV TOTEM is a non launchable assembly comprised of an inert Pressure Vent Test Vehicle PVTV within a capsule The assembly simulates the appearance mechanical interface press
58. Weapon Shipping Handling and Stowage Equipment SSN 688 Class SHIPPING LINE TOPSIDE SKID SHIPPING HARNESS REMDTE CONTROL STATION PRESSURE HULL TRAY Bm SHIPPING TRUNK RAIL A j 1ST PLATFORM LASHING STRAP SHIPPING TRAY TORPEDO ROOM 239 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 6 UGM 109 1 Land Attack TCM Operational Sequence 7 Sheets LEGEND OPERATOR ACTION TYPICAL EQUIPMENT OPERATION INITIAL CONDITIONS 1 SUBMARINE COMBAT SYSTEM CCS OR CC A POWERED UP 2 PVC SYSTEM OFF NOTES 1 RECYCLE ABORT LAUNCH ARE PERFORMED IN ACCORDANCE WITH NAVSEA OD 44979 2 EVENTS WITH AN ASTERISK 3 DENOTE REM OPERATIONS FOR LAUNCHES WITHOUT REM THE EVENT IS DELETED UGM 109A ONLY THE MISSILE POWER MONITOR RELAY APPLIES WARHEAD SAFE COMMAND WHEN DEENERGIZED AND TUBE IS SELECTED THE WARHEAD SAFE COMMAND IS REMOVED WHEN THE MISSILE AC DC CONVERTER ACTIVATES AND THE MISSILE POWER MONITOR RELAY ENERGIZES IF MISSILE VOLTAGE DROPS TO A SPECIFIED LEVEL DUE TO MISSILE POWER FAILURE THE MISSILE POWER MONITOR RELAY WILL DEENERGIZE AND AUTO SAFE THE SELECTED TUBE UGM 109A ONLY RECYCLE THE WARHEAD SAFE ARM SWITCH TO SAFE IF SAFE INDICATION EXISTS PLACE SAFE ARM SWITCH TO ARM AND PROCEED WITH LAUNCH IF NO INDICATION PERSISTS INITIATE SECURE TUBE PROCEDURES AND ABORT LAUNCH 240 5 UGM 109A ONLY I
59. a firing interlock check and closes final interlocks prior to permitting the impulse fire relay to energize and eject the TCM from the torpedo tube 4 5 LAND ATTACK TCM OPERATIONAL SEQUENCE This paragraph describes typical actions and responses required to launch a land attack TCM Primary coverage is given to a normal launch Abnormal launch conditions and abort procedures are discussed by highlighting only those events that differ from a normal launch Typical launch operations are shown in Figure 4 6 UGM 109 1 Land Attack TCM Operational Sequence 7 Sheets The figure illustrates the orders given by the ship s commanding officer typical actions taken by equipment operators and typical equipment operations status displays and machine decisions The operational sequence is described in the following paragraphs Operating procedures and checklists as well as actions to be taken under abnormal conditions are contained in appropriate volumes and parts of NAVSEA OD 44979 4 5 1 Weapon Preparation and Tube Loading Preparation starts with the authorization to launch a land attack TCM A torpedo tube is made ready for loading For a UGM 109A the 4FZ Security Alarm System is disconnected and the capsule security band unlocked and removed The weapon serial number is reverified The missile is then depressurized and moved to the loadline where the slot covers are removed 4 5 1 1 loading pole is attached between the rammer and capsule lo
60. accomplished hydraulically using the HPU The lifting adapter arm is disconnected from the crane and the MTEL hydraulic cylinders are connected to the lifting adapter insertion pins The hydraulic cylinders are extended using the HPU until the weapon seats in the missile tube 4 9 1 5 Remove Loading Equipment After the AUR has been fully seated in the missile tube the MTEL hydraulic cylinders are disconnected from the lifting adapter insertion pins The insertion pins are inserted into the lifting adapter and the MTEL hydraulic cylinders are then fully retracted The HPU is disconnected from the MTEL and the MTEL unbolted from the muzzle face and removed from the deck The lifting adapter is unbolted and removed from the weapon which signifies completion of the loading sequence and final hookup and testing becomes the responsibility of submarine personnel 4 9 1 6 Post Loadout Post loadout involves connecting the weapon to the ship systems through missile tube interfaces Figure 4 19 Secure CLS Weapon in Missile Tube umbilical cable connector is connected to missile tube umbilical connector Eight retention 215 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 segments are installed to restrain the CLS the missile tube at launch Umbilical cable brackets are connected to the retention segments to restrain the umbilical The SCS missile tube and weapon are then tested to ensure operability The annular space ven
61. alignment data and sequential control commands are stored on disks in the CSES The data are loaded into computer memory and sent to the missile on command Missile responses and status are evaluated by the CSES to provide data for displays on TCM status Built In Test BIT checksums and launch countdown 4 2 3 Navigation Equipment TOMAHAWK capable submarines are equipped with either the Electrically Suspended Gyro Navigator ESGN AN WSN 3A V 2 or the Dual Miniature Inertial Navigation System DMINS AN WSN 1 V 2 Each system consists of two Inertial Measuring Units IMUs and one dual channel Navigation Control Console NCC Velocity and attitude data are generated in raw form by the IMUs and transmitted to the CSES the NCC The raw data are processed by the CSES computers to obtain velocity attitude and position data and then transmitted to various ship user subsystems 4 2 4 Weapon Launch and Pressurization Vent Equipment The SSN 688 Class submarine weapon launch equipment consists of a weapon launch console WLC flanked by two banks of canted torpedo tubes two tubes port and two tubes starboard Also included are four PVC manifolds one for each torpedo tube to control the air which pressurizes the TCM prior to launch Pressurization and torpedo tube pre launch operations are controlled from the WLC Figure 4 3 SSN TTL Pressurization Vent Control System depicts the PVC system 4 2 5 Weapon Shipping Unshipping Equipment Bo
62. and CMGS batteries 3 4 6 Launch Sequence Command The LAUNCH SEQUENCE COMMAND block 15 used to reinitialize the RMUC terminate CMGS alignment zero mission data shut down the CMGS and declassify the CMGS memory When the REINITIALIZE command is sent the CMGS recycles to Mode 0 begins normal operation to transfer mission data and begins a new alignment For an explanation of alignment modes see Table 3 1 Land Attack TCM CMGS Alignment Modes When the TERMINATE ALIGNMENT command is sent the RMUC continues to accept alignment data and switches to the NAVIGATION mode At this time the CMGS becomes an independent navigator The ZERO MISSION DATA command causes the program to zero all memory locations dedicated to mission data The SHUT DOWN CMGS command causes the CMGS to perform a controlled shutdown that includes a gyro despin to preclude gyro damage The DECLASSIFY CMGS MEMORY command is used to declassify the CMGS memory following an abort 3 5 DIGITAL DATA RESPONSES FROM A LAND ATTACK TCM Two types of digital data responses are sent by the missile The first GOOD DATA word is sent after receipt of each data block that passes the parity and checksum tests The second MISSILE STATUS word is sent in response to a status request 3 5 1 Good Data Word As CMGS accepts data each word is checked for odd parity The data words are read stored in a data table and added to form a checksum that is checked against the checksum word
63. at the end of the data list If the word parities are good and checksums agree a GOOD DATA word is sent except in response to a missile status request 3 5 2 Missile Status Word The MISSILE STATUS word sent once every second in response to a status request shows the results of pre launch BIT via a combination of software commanded and hardware continuous tests conducted by the CMGS prior to MISSILE ENABLED It also shows the present mode of the CMGS The CMGS software will decode any BIT failure and transmit the information to the launch platform as a zero bit in the appropriate bit position of the MISSILE STATUS word 3 6 DISCRETE COMMANDS SENT TO A TCM 186 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 3 The following paragraphs discuss discrete commands issued to the TCM by the launch platform Discrete commands unique to CLS are discussed in Section IV 3 6 1 Booster Safe Command The BOOSTER SAFE command is a dc signal that sets the rocket motor in the SAFE position 3 6 1 1 Mk 106 Rocket Motor For the Mk 106 Rocket Motor the BOOSTER SAFE command interrupts the armed holding circuit The command allows the safe arm mechanism to spring return to SAFE thus positioning a physical barrier between the igniter initiators and propellant igniter The signal is applied continuously until the BOOSTER ARM command is received 3 6 1 Mk 111 Rocket Motor For the Mk 111 Rocket Motor the safe arm indicator plate is held in the SAFE
64. attack TCM variants 211 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 SECTION CAPSULE LAUNCHING SYSTEM 4 8 LAUNCH PLATFORM The TWS provides selected SSN 688 Class SSN 774 Class and SSGN 726 Class submarines with the capability to carry target and launch TCMs against enemy land targets TCM launch operations are performed aboard the submarine utilizing equipment located in the Attack Center Combat Systems Electronic Space CSES and Vertical Launch Center General locations of the complexes are shown in Figure 4 8 General Locations of SSN 688 Class Submarine Complexes The following paragraphs describe the major TWS related CLS systems aboard the submarine A simplified interface block diagram of TWS related equipment aboard the submarine is shown in figure 4 9 SSN 688 Class Submarine TWS related Equipment Interfaces 2 Sheets 4 8 1 Submarine Combat System SCS The SCS include the Combat Control System CCS and the AN BSY 1 Combat Control Acoustic Set CC A SSN 688 Class submarines may employ either the CCS or CC A Each SCS supported by the ownship navigation system CSES Over the Horizon targeting OTH T and the appropriate software programs provides the necessary power discretes and data to power up weapons transmit orders process and display data initialize and align the missile guidance set and initiate weapons launch Also included are control and monitoring circuits as well as various firing interlocks
65. available TCMs with no TCM launch that has progressed beyond rocket motor arming c Ifall modules or half modules have the same number of TCMs available that satisfy and b above the module or half module with the lowest designation number is selected If the same number module in both forward and aft launchers can meet the criteria the forward magazine is selected 4 18 3 Cell Selection When the MISSILE SELECT ORDER is received by the launch control unit LCU the LCU determines if the ordered TCM is available confirms missile identification and sends cell identification position and alignment data to the TWCS The LCU also sends a cell select message to the launch sequencer LSEQ and starts a 650 ms timer 4 18 4 Cell Missile Preparation Upon receipt of the cell select order the LSEQ begins to prepare the cell and the missile for launch The LSEQ performs a status check to verify missile selection as well as warhead and rocket motor safed If missile selection is not verified or warhead and or rocket motor safe indications are not received the LSEQ takes no further action until the LCU completes evaluation of the failure With missile selection and warhead and rocket motor safed verified the LSEQ applies OPERATE POWER and if applicable REM HEATER POWER to the missile and starts a 400 ms timer At the end of 400 ms delay the LSEQ sends a select response message to the LCU confirming the type missile and warhead selected The LSEQ
66. be fully depressurized prior to removing or installing the cover 1 16 2 2 Nose Diaphragm The nose diaphragm consists of a neoprene impregnated nylon cloth diaphragm a capsule to diaphragm seal four leashes and a steel attachment ring The nose diaphragm 15 shaped to match the contour of the missile The diaphragm attaches to the capsule barrel with 24 screws 1 16 2 3 Capsule Barrel The capsule barrel is a seamless corrosion resistant steel tube 232 88 inches long by 20 97 inches in diameter A single row of twelve flow slots is provided at about three quarters of the length of the barrel to permit the entry of torpedo tube launch pulse pressure Another single row of twelve flow slots is provided around the aft end of the barrel Bonded to the barrel inside surface are a number of Teflon coated rubber strips to absorb shock and reduce missile drag during ejection Also located inside the barrel is a seal that butts against the missile continuity shroud to provide a water tight seal 1 16 2 4 Alignment and Retention Provisions Capsule alignment and retention provisions consist of two guide studs mounted on the top centerline of the barrel and a capsule retention fixture a separate piece of shipboard equipment The guide studs engage the guide slot in the top of the torpedo tube The forward guide stud 1s engaged by the torpedo tube stop bolt depending on the stop bolt position The capsule retention fixture engages slots in the torpedo tub
67. capsule extension provides a watertight connection between the VSA and the aft closure assembly It also provides attachment for the aft closure assembly 1 23 2 8 Aft Closure Assembly The aft closure assembly has provisions for mounting the gas generator and the electrical cabling and controls It also provides through access for electrical cabling and ensures a watertight barrier at the capsule aft end An aft cover attaches to the aft closure to provide a closed environment for the gas generator and electrical cabling and controls 1 23 2 9 Generator gas generator is contained in a cylindrical steel case approximately 15 inches long and 12 inches in diameter An integral flange at the gas generator s CG attaches to the aft closure with a spigot fit The flange seals the capsule from the upper end of the aft closure The ends of the cylinder are fitted with flat steel plate closures The closures are sealed with O rings and retained in the assembly with threaded rings The forward closure provides mounting for an electrical bridgewire initiator on the outside and an ignitor housing on the inside The gas generator aft closure has a nozzle A polyester resin inhibitor is molded on the outer surface and forward end of the propellant grain to form a propellant cartridge Two circular molded rubber gaskets are bonded to the grain spacer to provide shock isolation for the cartridge Four tapped holes in the aft closure provide attachment
68. fiber materials Mechanical breakdown 1 explosion will also liberate and fragment fibers Such fibers can be spread via air currents for considerable distances Fiber material is highly conductive and can potentially damage electric electronic equipment Combustion by products may consist of carbon monoxide carbon dioxide acrolein phenols amines aldehydes aromatic amines hydrofluoric acid and fluoroboric acid COMMUNICATIONS During a weapon loading handling evolution communications must be established and maintained among all parties e g handling loading supervisor security crane hoist operators handling personnel damage control party throughout the evolution Should communications become lost to any party engaged in an evolution stop the operation and secure the weapon until communications are reestablished HAZARDOUS MATERIALS AND SITUATIONS Procedures involving hazardous materials or situations where there is potential for personnel injury or damage to equipment are preceded by WARNING or CAUTION as appropriate For each hazardous material used a Material Safety Data Sheet MSDS shall be posted and reviewed to determine specific hazards involved protective equipment requirements and appropriate handling and emergency procedures to be utilized NUCLEAR SAFETY PRECAUTIONS All personnel performing technical operations on TOMAHAWK Cruise Missile A variant containing the W80 Warhead must be familiar with the Nucl
69. given the READY TO FLOOD pushbutton at the Vertical Launch Console 221 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 VLC is depressed and the FLOOD DRAIN valve opened The Hatch Control Switch must be in REMOTE FLOOD DRAIN VALVE OPEN and EQUALIZE indicators illuminate and the PRESSURE IN BAND indicator remains illuminated Consoles are continuously monitored to ensure that all systems are operational Any anomaly will be displayed on the WCC as a systems alert or mode message which must be resolved prior to proceeding with the launch 4 11 6 Weapon Firing When the STANDBY ENABLE is displayed the STANDBY switch is activated A STANDBY indicator illuminates at the VLC which directs the closing of the P V valve and unlatching of the missile tube hatch The command is then given to activate the FIRE switch Activation of the FIRE switch activates the HATCH OPEN RELAY which automatically routes all subsequent commands directly to the weapon The FIRE command opens the missile tube hatch arms the rocket motor and CLS and sends the ITL signal to the missile It also sends the coded charge and launch signals to the CLS after the missile batteries are activated and MISSILE ENABLED and FIC signals have been sent to the VLC 4 11 6 1 the FIRE command has been sent operators no longer have the ability to intervene in the launch with the exception of sending an ABORT command An abort can be accomplished any time until the MISSILE ENA
70. in PEO W INST 4440 2 1 8 2 Procedural Documentation To perform TWS handling maintenance and warheading evolutions procedural documentation utilizes Procedural Guides PG Operating Procedures and Standard Inspection Procedures SIP requirements equipment tools material and procedures necessary for the safe and efficient handling maintenance and warheading of weapons are contained in those PGs OPs and SIPs The PGs and OPs are self explanatory and only require personnel be familiar with ship shore base facility weapons systems The SIPs are used by inspection personnel when applicable Inspection steps are indicated in the OPs by the following line IP STOP centered prior to a sequence of IP steps The check line will be marked with on the right edge paragraphs steps and sub steps are of equal standing when determining if there is a sequence break requiring IP stop markings 1 8 2 1 Figures Figures are provided in procedural documents to visually supplement procedural information in the OPs and except for certain assembly sequences provide typical views of events Illustrations are not intended to restrict operations Interpretation of visual depictions of events and variance from these same depictions are within the scope of the Weapons Officer Weapons Repair Officer Civilian Counterpart s authority and should only be governed by standard safety procedures and proper performance of equipment operation be
71. launching devices for TCMs Tactical and exercise AURs are delivered to the launch platform fueled and ready for launch Tactical AURs are warheaded Exercise AURs may be equipped with a depot installed Range Safety System RSS and a live or inert warhead or a depot installed Recovery Exercise Module REM without warhead Tactical and exercise AURs with conventional explosive warheads are classified as Class 1 Division 1 explosives UGM 109A is classified as Class 1 Division 3 AURs with inert or without warheads are classified as Class 1 Division 3 explosives 1 4 1 Tactical AURs Tactical AURs are used for land attack missions to strike high value or heavily defended targets Tactical AURs are configured for either surface launch RGM or submarine launch UGM Anti ship TOMAHAWK is no longer employed Each TCM is equipped with various devices for launch a rocket motor to boost it to a specified altitude after launch a sustaining engine for cruising to the target wings and fins to affect course changes a guidance section and an explosive warhead 20 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 1 4 22 Exercise AURs Exercise variants are classified as either REM or RSS equipped TCMs and provide the capability to launch TCMs for testing or training REM and RSS equipped are identified by a J prefix in the missile designator A REM equipped TCM JUGM 109A JRGM JUGM 109C only has a parachute system that permi
72. means for data to be transmitted from telemetry monitoring equipment to the encanistered TCM 1 29 2 6 Canister Safe Enable Switch CSES Mk 14 Mod 1 Mod 2 The CSES provides two position manual control of the booster ignition circuit for encanistered TCMs in the Mk 14 Mod 1 Mod 2 Canisters The CSES status safe or enable is continuously monitored by the VLS weapon control system 1 29 2 7 Canister Code Plug The canister code plug electrically identifies the type of missile in the canister and the type of payload It is attached to the canister cable assembly near the forward cover when the encanistered 15 placed in the Mk 14 Canister 1 29 2 8 Nitrogen Supply Valve The nitrogen supply valve located near the antenna connector provides a means of pressurizing the Mk 10 Canister via a nitrogen line inside the Mk 14 Canister 1 29 3 Mk 14 Mod 2 Canister The Block IV TACTOM AUR is encanistered in the Mk 14 Mod 2 VLS Canister and interfaces mechanically and electrically with the Mk 41 VLS launcher The Mk 14 Mod 2 Canister serves as the launch tube support for the missile when installed in the Mk 41 VLS and as the Packaging Handling Storage and Transportation PHS amp T container for the Block IV TACTOM AUR when installed with PHS amp T equipment The major difference between the Mk 14 Mod 1 and the Mk 14 Mod 2 canister is the new Mechanical Longitudinal Shock Mitigation Devices Mechanical Springs The Mk 14 Mod 2 canister configu
73. module containing the selected missile to TOMAHAWK launch and activates the circuits necessary for launch The LSEQ removes REM power if applied and prepares the cell for firing The cell and uptake hatches are opened and the plenum drain closed The rocket motor is then armed 4 18 8 Missile Activation After receiving the missile module ready status message from the LCU the TWCS issues a MISSILE FIRE ORDER to the LCU Upon receipt of this order the LCU issues a BATTERY ACTIVATE command to the TCM which causes the CMGS to terminate alignment and activates missile batteries When the batteries are fully operational the TCM sends a MISSILE ENABLE signal to the LSEQ The LSEQ removes power to the TCM and reports the missile enabled The LCU sends a launch status message to the TWCS to report MISSILE ENABLED If the launch sequence is stopped after battery activation the missile is dudded and cannot be recycled for firing 4 18 9 Rocket Motor Ignition and Missile Release After receiving MISSILE ENABLED the TWCS send a BOOSTER IGNITION order to the LCU Upon receipt of this order the LCU checks the status of current launches and waits until launch rate and priority requirements are met before issuing the IGNITION command to the LSEQ The LSEQ applies booster ignition 233 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 voltages to the TCM causing the rocket motor to ignite After rocket motor ignition and receipt of the CLOSURE RUPTU
74. of REM Equipped Missile shows a typical parachute recovery of a REM equipped missile 41 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 SECTION IV TORPEDO TUBE LAUNCH CONFIGURATION 1 15 AUR IDENTIFICATION Each tactical and exercise AUR is identified by a unique numeric six digit serial number The serial number for all configurations is located on a nameplate in the wing slot but is inaccessible to activities below depot level At the depot the AUR configuration and serial number are printed in the upper right hand corner of the Record Book for TOMAHAWK Cruise Missile TRB PEO W PUB 4440 which accompanies each AUR Additionally an MIS data plate is placed on the AUR and a matching data plate is placed in the TRB Activities below depot level verify AUR identity by comparing TRB data with data contained on an identification washer installed on the TCM electrical connector or identification plate placed on the TCM near the electrical connector an identification plate on the capsule aft end and an MIS data plate on the capsule aft end A UGM 109A 1 TCM with W80 Warhead installed will have a warhead identification decal on the capsule aft end to reflect the seven digit W80 Warhead serial number The decal is applied when the warhead is installed and is removed when the warhead is removed 1 16 CAPSULES 1 16 1 Capsule Mk 1 Mod 0 The UGM 109A C D 1 is protected by the Capsule Mk 1 Mod 0 Figure 1 23 TTL Capsules 2 Sheets
75. positioning required handling equipment and ensuring the area is free of unnecessary equipment 4 16 1 2 Prepare Cell Cell preparation may include the requirement to transfer weapons between cells prior to commencing onload of new weapons This may be necessitated by the need for certain missiles to be located in certain cells for accessibility to telemetry connections or the Critical Function Interrupt Switch Transfer of missiles between cells may involve removal and or installation of sill assemblies canister adapters and plenum cell covers Exact requirements for tasks to be performed are dictated by the types of missiles to be transferred between cells 4 16 1 3 Prepare Weapon As the launchers and cells are being prepared for onload shore base personnel prepare the weapon for loading If using a Mk 3 Horizontal Strongback the strongback is installed and secured to the canister A crane hook is attached to the strongback lifting shackle and the canister is raised to remove the packaging handling storage and transport PHS amp T equipment Figure 4 29 Mk 14 VLS Canister PHS amp T Equipment from the canister If a forklift is used the fork tines are inserted into the canister forklift channels the canister 15 raised and all PHS amp T equipment except the forklift channels are removed FWD and AFT protective covers are removed The canister is then moved to and secured on the Tilt Fixture Mk 23 Mod 0 with Kit A Figure 4 30 Secure Can
76. power for Recovery Exercise Module REM heater power and dc power for commands to and responses from the TCM The routing of power in the missile is described in the following paragraphs 3 2 1 4 Converter Operate Power Ship wye power is routed to the TCM ac dc converter The dc output of the converter is connected to the missile REGULATED bus via the POWER BUS control relay For land attack TCMs power is fed to the DSMAC set GPSS 109C and 109D only and the CMGS from the REGULATED bus For all TCMs power is also fed through the normally closed contacts of the BUS ISOLATE relay to power the CMA and MCM buses The CMA bus supplies power to the airframe electrical equipment The MCM bus powers the decoder relay drivers inside the MCM 3 2 1 2 Cruise Missile CM Identification Power The dc CM identification power 15 applied to the TCM when the launch operator selects the missile designated for launch Power is routed back to confirm the identity of the TCM selected and permit it to be prepared for launch or to advise the launch operator that there is a mismatch between the TCM selected and the actual TCM in the launching device In the latter instance further processing is automatically precluded 3 2 1 3 REM Heater Power When the launch operator selects a REM equipped and the identity of the TCM has been confirmed power is applied to the REM battery heaters The heaters warm the battery electrolyte in preparation for REM battery activ
77. provided around the aft end of the barrel Bonded to the barrel inside surface are a number of Teflon coated rubber strips to absorb shock and reduce missile drag during ejection Also located inside the barrel is a seal that butts against the missile continuity shroud to provide a water tight seal 42 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 1 16 1 4 Alignment and Retention Provisions Capsule alignment and retention provisions consist of two guide studs mounted on the top centerline of the barrel and two spring loaded latches located at the aft end of the barrel The guide studs engage the guide slot in the top of the torpedo tube The forward guide stud 15 engaged by the torpedo tube stop bolt depending on the stop bolt position The two spring loaded latches engage slots in the torpedo tube aft circumferential land and are held extended by two spring loaded plungers mounted on the aft end of the capsule sleeve Release of the latches is accomplished either by pneumatically actuating the capsule sleeve to close the flow slots or by manually depressing the spring loaded plungers and raising the latches The latches are held retracted by pins for tube loading unloading The pins must be removed to release the latches and stowed in holes provided in the barrel closure prior to TCM launch 1 16 1 5 Sleeve The capsule sleeve measuring 60 80 inches long by 20 50 inches in diameter consists of a machined corrosion resistant steel s
78. step or series of steps in which potential hazards exist 2 31 Explosives Safety Quantity Distance ESQD Arc Restrictions At some activities other than designated ammunition handling facilities 1 WPNSTA handling of explosives 15 substantially restricted because nonexplosive ordnance activities 1 e inhabited buildings are in close proximity to ordnance handling operations To safely accommodate handling of more than one TOMAHAWK AlI UP Round AUR at these ESQD restricted activities special handling procedures have been developed and approved for the conventional TOMAHAWK AUR 2 3 1 1 concept for these special handling procedures is based on maintaining a Maximum Credible Event MCE of one TOMAHAWK AUR regardless of the number of AURs involved The acknowledged ESQD arc to inhabited buildings for one conventional TOMAHAWK AUR is 600 feet The conventional TOMAHAWK AUR ESQD area is 600 feet 169 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 2 2 3 1 2 A maximum of two conventional TOMAHAWK AURs in their launch configuration either in or out of their shipping containers must be maintained in a nose to tail configuration with respect to each other either horizontally or vertically Other stacking restrictions regarding numbers in stacks on or off transport vehicles still apply This nose to tail configuration is to be maintained on the bed of a truck driven onto a pier in small boats or on the pier itself Additionally
79. the OFF position To avoid casualties always remove power and discharge and ground a circuit prior to touching it SERVICING OR ADJUSTING EQUIPMENT Under no circumstances should the servicing or adjusting of equipment be attempted alone The immediate presence of someone capable of rendering aid is required RESUSCITATION Personnel working with or near high voltages shall be thoroughly instructed in the latest methods of cardiopulmonary resuscitation CPR Should someone be injured by electricity and stop breathing begin resuscitation at once a delay could result in the death of a victim VENTILATION Ensure there is adequate ventilation to vent flammable and harmful vapors Keep away from heat sparks and open flame Avoid prolonged breathing of vapors or repeated contact with the skin Failure to comply may result in injury to personnel RESPIRATORS Personnel shall wear approved respirators when working with toxic cleaning agents adhesives and other toxic materials 175 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 2 FIRST AID An injury no matter how slight shall never remain unattended First aid or medical attention shall be given immediately HAZARDS ASSOCIATED WITH COMPOSITE MATERIAL COMBUSTION BREAK DOWN Composite materials composed of carbon graphite fibers present several hazards when subjected to fire explosion etc The epoxy binder will ignite or decompose at high temperatures possibly releasing
80. the designated tube After approximately 24 to 40 seconds WARHEAD ARMED indicators on the and WLC will advise operators that warhead has been successfully prearmed 4 5 7 Weapon Firing With INTERLOCKS CLOSED indicated and firing status ready the order is given to the ACC operator to position the STANDBY FIRE switch to STANDBY Upon order the switch 15 then positioned to FIRE and held until the FIRE indicator is present Subsequent actions occur automatically The missile batteries activate and missile essential busses are isolated The CMGS performs a status check using battery power and if successful sends a MISSILE ENABLED signal With the closing of final interlocks the impulse fire 209 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 relay energizes the stop bolt rolls the electrical umbilical deadfaces and the tube fires Upon firing TUBE FIRED indicators on the ACC and WLC advise operators that the tube has been successfully fired If indicators reflect that the tube was not successfully fired the launch is aborted in accordance with NAVSEA OD 44979 4 6 POST LAUNCH OPERATIONS The post launch operational sequence begins after the missile has been launched from the torpedo tube Operations consist of those evolutions to either eject the capsule or return the capsule to the stowage racks The operations also include resetting the tube 1f required and securing the torpedo tube A typical post launch sequence is
81. the target The message also specifies where in the preplanned mission the missile shall divert to the new mission data This type of message can also be sent to modify communications parameters or request missile status 4 14 5 GPS To Missile Interface The Block IV TACTOM missile uses the Global Positioning System GPS for navigation aiding throughout its flight GPS signals are received by the Anti jam GPS Receiver AGR via the AGR Antenna These components provide the missile with improved resistance to GPS jamming as compared to Block III As in Block III the Block IV TACTOM missile receives GPS crypto keys and almanac data from the launch platform during missile preparation GPS crypto keys are transferred in a matter that memory locations are zeroed after the key information is transferred 225 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Initial GPS satellite acquisition occurs shortly after launch The missile tries to acquire all satellites that are in view to its antenna up to a total of eight The missile will select to receive data from the best set of four satellites based upon the accuracy of the navigation solution Satellites are tracked first using C A Coarse Tracking code and then using P Y Precision Tracking code First Fix is achieved when P Y measurements are achieved from the best set of four satellites During normal GPS track the AGR will keep track of up to eight satellites to enable faster reacquisit
82. to the CCA during shipping handling loading and prelaunch pressurization activities The sabot consists of two closed cell foam halves attached together with plastic tie wraps The foam material is negatively buoyant due to the inclusion of iron particles within each molded foam half The sabot is coated with a zinc rich primer and a polyurethane top coat to provide a corrosion resistant surface compatible with the CCA and the missile nosecone The sabot assembly weighs approximately 26 pounds When launched the missile nose pushes the sabot against the CCA tear strips As the CCA tears and the missile leaves the launch tube the sabot is broken into several small pieces by the ejection forces These pieces will gradually sink to the bottom away from the launch tube Some pieces may sink to the bottom of the capsule This is an acceptable condition 1 23 1 4 Lateral Support Group The lateral support group is bonded to the inner surface of the capsule The lateral support group has thirteen rows of elastomeric liner pads There are four separate liner pads in each circumferential row Each liner pad consists of an inner and outer wall jointed by chevron shaped struts Teflon is bonded to the inside surface of each pad to reduce friction against the missile surface Dual plateau pads with a corrugated inside surface are incorporated into the lateral support group to further reduce friction during encapsulation and decapsulation of the missile and du
83. to prepare and launch a TCM to include the time required to recycle the torpedo tube and when authorized to eject the capsule 4 4 3 Alert Messages and Interlocks Various alert messages and firing interlocks are used to warn operators or inhibit launch when conditions exist that could impact missile performance endanger the submarine or result in the launch of a dud missile Firing interlocks may be either software or hardware interlocks Prior to permitting activation of the FIRE switch the submarine fire control system must receive an indication that the following interlocks are closed a WPN IDENT Indicates that the designated weapon is loaded in torpedo tube 206 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 b INPUTS MATCHED Indicates that all mission data have been transferred to the missile and the CMGS has responded with appropriate MISSILE STATUS and GOOD DATA words c WITHIN LIMITS Indicates that speed and depth of the submarine are within limits d TUBE READY Indicates that the torpedo tube outer door is open e BOOSTER ARMED Indicates that the rocket motor igniter is armed f WARHEAD PREARMED Indicates that the UGM 109A 1 warhead is in prearmed condition g PRESSURE IN BAND Indicates that missile pressure is between 3 8 7 2 psid Upon activation of the FIRE switch and indication of MISSILE ENABLED 1 batteries activated BIT passed MISSILE STATUS word good the fire control system performs
84. upper tube and muzzle hatch areas are then flushed with fresh water and all residual reflood water is pumped from the spent CLS Remaining residue and by products are cleared from above the CLS in order to attach the lifting adapter Additionally egress of the TCM from the CLS causes the diaphragm to rupture leaving residue which must be removed to permit attachment of the CLC and to secure the umbilical cable to the cover 4 9 2 3 Prepare Weapon for Offload Once the missile tube has been prepared the submarine crew prepares the weapon for offload The CLC is installed The umbilical cable connector is disconnected the connector protective cap installed and the connector is secured to the CLC Umbilical cable clamps retention segments and the annular space vent plug are then removed A protective shield is installed on the umbilical to prevent contact with the missile tube and damage to the umbilical 4 9 2 4 Install Offload Equipment Submarine tender shore base personnel connect the lifting adapter to the weapon The MTEL is positioned and secured over the missile tube The HPU is positioned on the loading platform and connected to the electrical source aboard the submarine and to the MTEL cylinders The lifting adapter insertion pins are installed and the MTEL hydraulic cylinders are connected to the insertion pins 4 9 2 5 Remove Weapon from Missile Tube With the MTEL cylinders attached to the lifting adapter insertion pins the HPU is ener
85. 0 132 127 AUR variant AUR Volumetric Shape AURBb AUR Simulator and CLS Loading and Handling Trainer CGs are measured from datum lower edge of upper flange Missile Tube Ballast Can CG is measured from brass protector ring flat gasket mounting surface AUR Simulator Shipping Skid Trunnion end CG will vary for empty spent capsule depending on amount of residual water remaining in capsule after draining SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Table 1 13 Weights of RGM 109 2 Mk 10 Variants and Related Material HANDLING WEIGHT ITEM Pounds Kilograms TACTICAL AUR RGM 109C 2 3973 1802 RGM 109D 2 3823 1734 RGM 109E 3837 5 1741 EXERCISE AUR JRGM 109C 2 3973 1802 JRGM 109D 2 3823 1734 JRGM 109E 2 3938 1786 TRAINING CERTIFICATION VARIANTS CANISTER TRAINER MK 17 3662 1661 CANISTER CANISTER MK 10 495 225 NOTE AUR handling weights calculated using heaviest components plus a small safety factor 165 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Table 1 14 Centers of Gravity for RGM 109 2 Variants APPROXIMATE FWD MEASUREMENT IN ITEM FROM CANISTER CG TACTICAL AUR RGM 109C 2 11 5 RGM 109D 2 11 5 RGM 109E 2 14 8 EXERCISE AUR JRGM 109C 2 M 11 5 JRGM 109C 2 S W 10 0 JRGM 109D 2 S W 11 5 TRAINERS AND CANISTERS CANISTER TRAINER MK 17 MOD 0 0 0 CANISTER MK 10 Empty 2 0 Measure from center of canister CG stripe AUR calculation is for AUR configured with
86. 010 REVISION 15 ABBREVIATION ACRONYM VDA VDC VLA VLC VLS VLT VLV VSA W H WARHD WB WCC WDC WH INST TRNR WIT WIU WLC WMP WPNSTA WSA 27 MARCH 2009 CHAPTER 1 DEFINITION Variable Dive Attack Maneuver Volts DC Vertical Launch Anti Submarine Rocket Vertical Launch Console Vertical Launch Center Vertical Launching System Vertical Launch TOMAHAWK Valve Vertical Support Assembly Warhead Warhead Work Boat Weapon Control Console Weapon Data Converter TOMAHAWK Warhead Installation Trainer Warhead Installation Trainer Warhead Interface Unit Weapon Launch Console Weapon Monitor Panel Weapons Station Warhead Support Assembly 146 SW820 AP MMI 010 WEAPON SYSTEM UGM 109 1 UGM 109 2 RGM 109 2 RGM 109 4 UGM 109A 1 UGM 109 1 UGM 109 2 RGM 109 2 RGM 109 4 UGM 109 1 UGM 109 2 RGM 109 2 RGM 109 4 REVISION 15 27 MARCH 2009 CHAPTER 1 Table 1 5 Summary of Reports REPORT ELECTRONIC CRUISE MISSILE FIELD REPORT E CMFR NUCLEAR WEAPONS UNSATISFAC TORY INFOR MATION RE PORT UR IR PMS TECHNICAL FEEDBACK REPORT TFBR CONVEN TIONAL AM MUNITION INTEGRATED MANAGE MENT SYS TEM CAIMS MEDIA Web based E CMFR Form lo cated in TOMA HAWK Manage ment In formation System TOMIS database NAVSEA Form 8110 4 NAVSEA Form 4790 7B Ammuni tion Trans action Re port GOVERNING DIRECTIVE SWOP 5 8 OPNAVINST 4790 4
87. 09 CHAPTER 1 MCP in the form of position velocity acceleration and attitude The NP is considered a highly critical item This unit resides in the GEU 1 11 4 3 13 Power Filter Unit PFU The PFU provides DC power filtering and protection features and distributes electrical power throughout the missile It receives power inputs from the surface launch platform prelaunch AC DC Converter pre launch phase submarine only the CMA Battery boost phase and the AVCC cruise phase The PFU will isolate all power until commanded before distribution to missile components during the pre launch phase The PFU will apply launch platform power to the TVC FCS and FMP to perform self tests when commanded The PFU incorporates a deadface to the TVC just prior to booster jettison and incorporates a positive disarming mechanism to isolate launch platform power from the pyro circuits during the prelaunch phase 1 11 4 3 14 Pyro and Power Control Assembly PPCA PPCA consists of three circuit cards located within the GEU It controls and monitors designated missile avionics and pyrotechnic pyro devices PPCA functions are performed under control of the launch platform or the missile Mission Control Processor MCP or both 1 11 4 3 15 Radar Altimeter RA The Radar Altimeter also referred as the Single Card Altimeter SCA resides inside the GEU The RA determines the altitude of the missile in relation to the ground below The RA transmits
88. 1 EQUIPMENT FUNCTION ILLUSTRATION Cradle Mk 34 Mod 0 Secure and transport CLS weapons by P N 6213249 small boat Cradle Undersea Transfer weapons on small boats Weapons Transporting Mk 27 Mod 0 P N 5165994 Device Tie down Secure weapons and containers in small lt P N CGU 1 B boats 5 Dolly Assembly Missile Transport Mk 30 Shipping and Storage Handling Mk 34 Mod 0 Skid P N 5167224 5 Dolly VLS Transport Mk Transport Mk 14 Canister 35 Mod 0 LBP ccm 2 v P N 5167396 S Fixture CLS Capsule Transition CLS weapons between Uprighting Mk 26 ModO vertical and horizontal during onload P N 5917401 and off load VH or Mk 26 Mod 1 X PN P N 6213396 ie Fixture Missile Move the missile about nine inches Positioning MTU 68 E out of into the capsule during P N 76Z3550 30 UGM 109A 1 warheading and dewarheading 110 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 EQUIPMENT FUNCTION ILLUSTRATION Fixture Tilt Mk 23 0 With Kit A transition Mk 14 Canister P N 5167473 between the horizontal and vertical positions With Kit B transition CLS weapon between vertical and horizontal for onload and offload Gauge Load Button Verify any TTL capsule load button P N 7339399 No is not oversized bent or otherwise NSN distorted so as to cause problems during tube loading aboard a submarine Hoist Chain Hand 2 ton Used with Hoisting Sling Mk 157 to 15 ft Lift change position of lifting adapter o
89. 1 covers fore and aft are provided to cover the AUR or capsule during shipment or storage The forward cover contains an access door Pins secure the covers to the outer frame assembly Stacking posts are provided to permit stacking of containers The Mod 1 configuration includes a storage location for the Closure Protective Cover Mk 19 Mod 0 Skid dimensions are provided in Table 1 8 Container Weights and Dimensions 1 25 2 AUR Simulator Shipping Skid The AUR Simulator Shipping Skid Figure 1 33 AUR Simulator Shipping Skid gt is used to handle and transport AURS The skid consists of a steel frame with two aluminum covers secured to the frame with capscrews A cradle and restraining straps are provided to secure the shape in the skid Hardwood skids attached to the bottom of the frame allow lifting straps to be used to move the skid Lifting rings on the covers facilitate use of a sling crane arrangement to remove the covers Skid dimensions are provided in Table 1 8 Container Weights and Dimensions gt 1 25 3 Shipping and Storage Skid Mk 34 The Shipping and Storage Skid Mk 34 Figure 1 36 Shipping and Storage Skid Mk 34 gt is also used to handle store and transport the AURS With the installation of the Uprighting Fixture and Forward Support this skid can be used for uprighting lowering the AURS during loading unloading The main body of the skid is constructed of aluminum and consists of an inner and outer frame asse
90. 10 REVISION 15 27 MARCH 2009 CHAPTER 1 SMTT training shape Figure 1 38 SMTT Training Shape is required to handle and train on the 5 The SMTT training shape is modified version of the CLS capsule shortened to approximately 15 inches The SMTT training shape includes a Capsule Loading Cover 1 8 DOCUMENTATION 1 8 1 Record Books Record books form an integral part of maintaining inventory and historical data on TWS variants Each variant s record book accompanies the variant at all times throughout the logistics cycle and 15 returned to the depot with the variant at the time of recertification or unscheduled maintenance The record book identifies the variant configuration and determines the data necessary for Fleet use provides a log for tracking and recording security seal data provides a history of movement maintenance and significant events between initial acceptance and return to the depot and provides a record of authorized waivers and deviations to technical manual acceptance rejection criteria PEO W PUB 4440 Record Book for TOMAHAWK Cruise Missile is used to record data pertinent to tactical and exercise AURs and specific trainers PEO W PUB 4440 has been structured to accommodate both surface and submarine launched variants Therefore some forms contained in the record book are not applicable to some launch configurations Instructions for use forms completion and disposition are contained in the record book and
91. 10 contains the procedures for shore base personnel to prepare the weapon for onload and to perform weapon onload or offload Technical manual SW394 AF MMO 050 provides a detailed discussion of on board procedures for preparing launchers and cells for onload and offload securing weapons in launch cells preparing weapons canisters for offload and activating launchers upon completion of operations 4 16 1 Onload Ship onload begins when the ship arrives at a designated shore activity to receive a complement of weapons Wind and sea motion which affect the ship s position and movement are factors in determining the feasibility of loading operations The shore base loading supervisor and the ship s commanding officer will determine if conditions are satisfactory prior 228 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 to commencing onload Prior to onload launchers are neutralized and placed in the strikedown mode at the status panel During onload responsibility for operations is shared between the ship s commanding officer and the shore base loading supervisor All actions involving ship system preparation are the responsibility of the ship s commanding officer His permission is required prior to commencing loading operations His designated representative is responsible for weapon handling operations and ensures that a weapon transfer inspection is conducted Upon completion of ship preparation responsibility for loading transfers to t
92. 109A Depot Level Warhead Assembly Test Maintenance and Storage Procedures Shorebase Ship and Sub 131 SW820 AP MMI 010 REVISION 15 DOCUMENT NUMBER SWOP W80 82 9 TO300 AM ORD 10 NAVSEA OD 465743 TWI120 AA PRO 010 TW510 AA PRO 020 TMIS TW510 AA PRO 030 TMIS TWA390 BA GSE 010 ULSS PMA 280 1206 27 MARCH 2009 CHAPTER 1 TITLE Operator and Organizational Maintenance TOMAHAWK Land Attack Missile UGM 109A Weapons and Combat Systems Quality Assurance Requirement for Shore Stations and Engineering Agents Nuclear Weapons Radiological Controls Program Torpedo Management Information System Submarine Organizational Level Maintenance Activity Reporting Instructions for Submarine Fired Weapons Vehicles Torpedo Management Information System Intermediate Level Maintenance Activity Reporting Instructions for Submarine Fired Weapons Vehicles Attack Submarine Vertical Launch System Peculiar Support Equipment Item Management Plan TOMAHAWK Cruise Missiles for Transhipment Activities 132 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Table 1 4 Abbreviations and Acronyms ABBREVIATION ACRONYM AA amp E ACC ACN ACR ADM AE AEL AFA AFIRT AGR ANSI AOE APL APML AS ASDS ASME ATR AUR AURBb AURES AURS AURVS AVCC BDI BDII BIT BPU BR DEFINITION Arms Ammunition and Explosives Attack Control Console Advance Change Notice Anticircular Run Air Data Module Ammunition Ship Allowa
93. 15 1 Launch Control Unit LCUs Figure 4 25 Launch Control Unit LCU designated LCU 1 and LCU 2 maintain control of the launcher sequencer LSEQ in the launchers which in turn monitor launcher conditions and provide the interface to permit weapon launch Each LCU consists of a data processing set which receives orders from the weapon control system selects the weapon to engage the target and issues pre launch and launch commands to the launcher a signal data recorder reproducer set which contains the tapes that control the launch control computer program and record operational history and digital data pertinent to fault isolation and data analysis and a data terminal group which allows manual access to the VLS program and provides hard copy of data received from the data processing set 4 15 2 Launchers Each launcher Figure 4 26 Vertical Launching System Launcher consists of 8 cell modules six each for the Mk 158 Mod 0 Launcher and two each for the Mk 159 Mod 0 Launcher an 8 cell system module and a 5 cell strike down module 4 15 2 1 8 Module Each 8 cell module consists of the following a An upright structure to provide vertical storage space for eight missile canisters b A deck to protect the canisters during stowage with a hatch assembly that opens to permit missile launch c plenum and uptake assembly to capture and vent exhaust gases to the atmosphere d Electronic equipment to monitor stored missile cani
94. 2 2 Capsule Closure Assembly The CCA Figure 1 40 CLS Mk 45 Mod 2 Capsule Closure Assembly is compatible with both the Block and Block IV AUR configurations The is attached to the flange at the upper end of the capsule The closure consists of a nylon cloth reinforced rubber diaphragm with an internal stainless steel band around the outer edge Incorporated within the underside of the diaphragm are four sabots The intent of the sabots is to reduce the stress in the diaphragm at maximum launch pressures Upper and lower retaining rings are utilized for diaphragm assembly A diaphragm bead is clamped between the two retaining rings in a compression fit to form a seal between the rings The rings are bolted together The bolts pass through both rings to attach the closure to the capsule An O ring fits in a groove in the capsule forward flange and provides an air tight seal between the closure assembly and the capsule upper flange while in the AUR cell missile tube The rings also provide mounting for the pressure sensing line The diaphragm membrane is purposely weak along a diametrical line called the tear line Yet it is strong enough to withstand maximum external pressure at launch depth and maximum prelaunch internal over pressure As the capsule is pressurized before launch the nylon cloth in the diaphragm allows diaphragm to stretch and grow slightly 1 23 2 3 Lateral Support Group The lateral support group is bonded to the inner surf
95. 23 Mod 0 with Kit A FWD rest The canister 15 lowered to and locked on the tilt fixture The canister 15 lowered to the horizontal position and the Mk 4 Strongback is removed The Mk 3 Horizontal Strongback or forklift channels forklift are installed the canister is removed from the tilt fixture and PHS amp T equipment is installed 4 16 3 Crossdeck Weapons Crossdecking of weapons is performed similar to onload and offload except weapons may be transferred from one launcher to another aboard the same ship or between different ships without lowering the weapon to the pier into the Mk 23 Tilt Fixture Crossdecking 15 accomplished using the Mk 4 Vertical Strongback and crane hook arrangement to extract transfer and insert weapons between launch cells 4 17 OPERATIONAL CONSTRAINTS RESTRICTIONS Tactical employment of the TCM imposes a number of constraints on the operating parameters of the ship The constraints imposed during tactical launch operations of the TOMAHAWK Cruise Missile are provided in applicable tactical publications Employment also places restrictions on the ship s tactical flexibility which are described in Operating Guidelines tactical employment manuals and operation manuals 4 17 1 Weapon Mix Weapon mix will depend on the particular conditions that exist at the time the decision is made to prepare weapons for launch The TWCS is capable of processing a combination of TOMAHAWK Cruise Missile variants Other weapons control system
96. 4 8 41 Missile Tube Assembly The missile tube assembly Figure 4 10 SSN 688 Class Submarine Missile Tube Assembly houses and physically protects the weapon in the missile tube The assembly consists of the missile tube hatch and linkage gear and interfaces to operate the assembly Ship system interfaces include connections for the flood and drain and 212 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 pressurization vent systems AUR interfaces provide shock mitigation and alignment of the AUR as well as a means to pressurize the AUR 1n the missile tube Missile tubes are topped by hatches that are individually operated by outboard hydraulic rotary actuators and are locked by an over center toggle linkage mechanism with locking further enhanced by a device to assure that hatches do not inadvertently open when adjacent tubes are subjected to launch pressure 4 8 4 2 Hydraulic System The hydraulic system Figure 4 11 SSN 688 Class Submarine Hydraulic System provides power to actuate flood and drain system valves and missile tube hatches Class Submarine Pressurization Vent System replenishes the AUR internal atmosphere during stowage and pressurizes or vents the AUR to maintain internal pressure within a specified range of positive pressure over the underhatch volume pressure prior to launch using 700 psig ship service air 4 8 4 3 Pressurization Vent System The pressurization vent system Figure 4 12 SSN 688 4 8 4 4 Floo
97. 42 4 REVISION 15 27 2009 SW820 AP MMI 010 243 4 REVISION 15 27 2009 SW820 AP MMI 010 244 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 245 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 246 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 7 MTEL With MTEL Adapter Installed 247 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 8 General Locations of SSN 688 Class Submarine Complexes COMBAT SYSTEMS ELECTRONIC SPACE 248 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 9 SSN 688 Class Submarine TWS related Equipment Interfaces 2 Sheets 5 A COMBAT CONTROL SYSTEM MK 1 249 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 ACOUSTIC TARGET DATA DISPLAY AND CONTROL SEGMENT wee NAV DATA DISPLAY AND CONTROL MEC MOD2 MK 23 DIGITAL DATA DISPLAY AND CONTROL WCC GRAPHIC MK 81 PLOTTER MOD 2 SENSOR INPUTS DIGITAL es DISPLAY AND CONTROL DATA sw SPEED MULTIPURPOSE RADIO Po BN CONSOLE BEARI DIGITAL PERIS 41 2 OTH CONSOLE SERIAL DISPLAY DATA AND CONTROL WEAPON CONTROL CABLES CO D AU PPORT STA TUBE PANEL kay Sg TM E HARDWIRE INTERFACE COMBAT CONTROL ACOUSTIC AN BSY 1 250 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER
98. 4307 Attn Code 312 FAX transmissions may be submitted using DSN 296 0726 or commercial 805 228 0726 feedback comments will be thoroughly investigated and originators will be advised of action resulting therefrom TOMAHAWK ALL UP ROUND LOGISTICS AND MAINTENANCE INFORMATION PRODUCT TALMIP DISTRIBUTION CHANGES ADDITIONS OR DELETIONS Direct all requests for TALMIP distribution changes additions or deletions to Program Executive Officer for Unmanned Aviation and Strike Weapons Attn PMA 280713 47123 Buse Road Unit IPT Patuxent River MD 20670 1547 STOCK REPLENISHMENT Request additional copies of TOMAHAWK All Up Round Logistics and Maintenance Information Products TALMIP via normal MILSTRIP procedures from Naval Inventory Control Point Material 700 Robbins Avenue Philadelphia PA 19111 5098 18 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 CHAPTER1 INTRODUCTION SECTION I DOCUMENT ORGANIZATION 1 1 SCOPE This document presents information pertinent to the submarine launched and surface ship launched Tomahawk Weapon System TWS to include physical and functional descriptions of system components safety and security considerations and operations aboard platforms employing the TWS 11 1 Chapter 1 Chapter 1 discusses the TWS mission and physical descriptions of system components and equipment required to support the system identifies the types of documentation and documentation terminology asso
99. 5 56 SWOP 50 2 SWOP 100 4 SWOP DE 2 SWOP H 1 SWOP W80 82 0 SWOP W80 82 1 27 MARCH 2009 CHAPTER 1 TITLE TOMAHAWK Test Vehicles COTS TOTEM Description Operation Maintenance and Repair Parts Breakdown RPB TOMAHAWK Inert Fitment Shape TOMFISH Description Certification Verification Operation Maintenance and Repair Parts Breakdown RPB Submarine and Tender Shorebase TOMAHAWK Warhead Installation Trainer Mk 35 Mod 0 Description Operation and Maintenance with Repair Parts List RPL and Quality Assurance Test and Inspection Procedures QATIP Shorebase Numerical Index to Joint Nuclear Weapons Publications Numerical Index to Joint Nuclear Weapons Publications Navy Supplement Glossary of Nuclear Weapons Material Unsatisfactory Information Report Plutonium Contamination Standards Nuclear Safety Criteria Firefighting with Nuclear Warheads Transport of Nuclear Weapons Material Instructions for Logistical Movement of Nuclear Weapons Includes SAFEPOT Maintenance with IPB and Command Disablement Procedures Procedures for the Use and Control of Logistics Codes for Permissive Action Linked PAL Equipped Weapons Custody Accountability and Control of Nuclear Weapons and Nuclear Material Operator Maintenance Instruction with IPB for Disablement Equipment Navy Nuclear Weapons Handling Equipment Certification Policies and Maintenance Instructions Weapon Summary TOMAHAWK Land Attack Missile UGM
100. 67 1981 TRAINING CERTIFICATION VARIANTS TOMAHAWK TEST MISSILE TOTEM 3550 1610 UTM 109 1 ENCAPSULATED NL TOTEM 3550 1610 COMMERCIAL OFF THE SHELF COTS TOTEM 4050 1837 PRESSURE VENT TEST VEHICLE PVTV 4550 2063 9 TOTEM CREW TRAINING SHAPE CTS UTM 109 1A 3576 1622 WARHEAD INSTALLATION TRAINER WIT MK 4137 1877 35 0 w WARHEAD TOMAHAWK FITMENT SHAPE TOMFISH MK 4250 1928 1 0 VEHICLES AND CAPSULES TOTEM TEST VEHICLE TM 109 1C 2600 1179 CAPSULE MK 1 0 938 425 CAPSULE MK 3 0 1005 456 TOTEM CAPSULE 950 431 157 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 ITEM WIT MK 35 0 CAPSULE w nose and slot covers WIT MK 35 0 CAPSULE w o nose and slot covers WIT MK 35 0 TRAINER w WARHEAD TTL NOSE COVER aluminum lightweight Block IV TTL FWD SLOT COVER metal Kevlar Universal TTL AFT SLOT COVER metal Kevlar Universal SHIPPING CONTAINER CNU 308 E empty NOTES CHAPTER 1 HANDLING WEIGHT LBS Pounds Kilograms Ibs kg 864 392 832 377 3273 1485 27 14 27 12 2 6 4 12 2 4 3 2 1 8 1 4 0 9 1 1 2 0 5 0 5 0 9 1709 775 AUR handling weights calculated using heaviest components plus a small safety factor Weight will vary depending on test requirements Refer to Test and Evaluation Plan for data 158 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Table 1 10 Centers of Gravity for TTL Variants ITEM TACTICAL AUR UGM 109A 1 w W80 Warhead UGM 109A 1 w o W80 Warhead UGM 109C 1 UGM 109D 1 UGM 109E 1 E
101. 9A C D TCM variants and are discussed in the following paragraphs 1 11 5 1 Midbody Section The midbody section extending from station 99 80 to station 155 20 consists of a standard mission cover and an upper and lower fuel tank section separated by a lateral through slot The through slot contains the wings one stowed above the other in scissor 33 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 fashion and the wing pneumatic actuator and associated control valves Two pneumatically actuated doors one on each side of the missile open to permit wing deployment then close again to provide aerodynamic smoothness The midbody lower fuel tank section contains an expansion bladder to accommodate fuel expansion and contraction and to provide the initial fuel pressure for engine start The lower section also contains the fuel hopper that supplies fuel to the sustainer engine The Cruise Missile Airframe CMA thermal battery is located in a dry well on the right side A single point fuel defuel panel is provided on the left side A coolant pump used to circulate missile fuel through the CMGS mounts on the aft side of the forward bulkhead 1 11 5 2 Aft Body Section The aft body section extending from station 155 20 to station 182 50 consists of an integral dry well and a domed housing The upper half also serves as the missile aft fuel tank for the 109C Inside the dry well is the Mission Control Module MCM which interfaces the airfram
102. A Transportation 168 2 22 T papan ge ISO HEN pa a dd e 169 2242 TAINS TA els tuer sea da ewe veda ees ea Vus due 169 ZO AR EIEN asd 169 2 3 1 Explosives Safety Quantity Distance ESQD Arc Restrictions 169 PCM 169 ER 170 170 2 3 2 Hazardous Components 2 170 23 3 Permiso OH 170 2 3 4 Hazards Associated With Composite Material Breakdown Combustion 170 p Mec Em 171 p E 171 253 d pes ese u 171 A ibu usus pusuta 171 2 3 5 CLS Post Launch Waste Water 171 CHAPTER 3 FUNCTIONAL DESCRIPTION 182 SECTION T CHAPTER ORGANIZATION wri a n un iay roa ed we on exi id 182 o P sayana 182 SECTION TlGENERAL wi sive neater 183 32 ELECTRICALPOWER SYSTEM eae eee 183 3 2 1 Prelaunch Electrical POWGE br ete pa 183 3 2 1 1 Converter Operate Power eee 183 3 2 1 2 Cruise Missile CM Identification Powe
103. AG SEL ARE SET FOR DESIRED MAGAZINE S 27 MARCH 2009 CHAPTER 4 INITIALIZE LCG NOTE 2 THE LCG SYSTEM DTD IS ASSUMED TO BE ALREADY INSTALLED NOTE 2 ON WRN 5 EQUIPPED SHIPS iF THE WSN 5 UPDATE SOURCE IS NAVSAT AUTOMATIC UPDATES MUST DISABLED TO PREVENT GYRO RESETS DURING MISSILE ALIGNMENT ON WRN 6 EQUIPPED SHIPS THE WSN 5 IS NOT PLACED IN MANUAL FIX THE TWCS OPERATORS MUST ENSURE THAT THE QMs HAVE PROPERLY CONFIGURED NAVSSI TC USE ONLY WAN G INPUTS AND IC MEN HAVE CONFIGURED WRN 5 TO USE ONLY GPS UPDATES NOTE 3 ACCORDANCE WITH SHIP S DOCTRINE 283 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 EP BUILDS PLAN THROUGH INITIAL PHASE CLEAR ALERT AREA INITIATE ALERT ACK FFK 1 PROMPT AREA RECOMMEND ENTER SN VERF CODE P ALERT AREA RECOMMEND INITIATE ALERT ACK FFK ENGAGEMENT PLAN RECEIVED 284 SW820 AP MMI 010 REVISION 15 ENTER PLAN ID NUMBER KEYBOARD SELECT MSN VERF CODE TEA MSN VERF CODE P 27 MARCH 2009 285 CHAPTER 4 ENTER VERIFICATION CODE KEYBOARD SELECT ENTER COMMAND TEA ENTRY ACCEPTED ENTRY VERIF AREA SW820 AP MMI 010 REVISION 15 CLEAR PROMPT AREA EP SENDS MAKE READY PLAN ORDER NGAGEMENT PLA RECEIVED P 27 MARCH 2009 CHAPTER 4 CLEAR ALERT AREA
104. APSULE ARMED indication exists or there is no condition status indicated the launch is aborted 4 11 3 Mission Assignment The appropriate mission disk pack is removed from secure storage and mounted on the random access storage set RASS The disk pack serial number is entered and the RASS initialized With RASS initialized the Cruise Missile Guidance Set CMGS is ready to accept mission data when BALLISTICS SET and CMGS PROGRAMMED are indicated to the Weapon Control Console WCC operator CMGS flight program has been transferred to the missile and the missile has responded with a valid Missile Status Word The WCC operator changes the submode until Land Attack TOMAHAWK Evaluation is indicated on the WCC THEATER MPS MISSION and VERIFY codes are received from the appropriate authority and entered on the WCC Mission data are then indicated on the WCC Mission data are also transferred to the central computer resident memory The WCC operator enters the target number and the pre established waypoints to that target are displayed on the WCC The WCC operator reviews the mission data and approximate flight path to the target and makes route alterations by introducing or deleting waypoints The WCC operator then assigns the mission to the designated missile tube and a verification that the mission is assigned to the correct tube is performed Once a mission has been assigned no further modifications can be made without resetting the mission and th
105. BLED signal is sent to the SCS Once batteries have been activated and the ABORT command issued the missile is dudded and cannot be recycled for firing 4 1 6 2 Upon receipt of the coded launch signal the gas generator ignites initiating missile launch FIRE PULSE DETECTED signal is received from the CLS and all functions to the missile are terminated At first motion a MISSILE AWAY signal is received from the CLS and all commands are terminated 4 11 7 Multiple Launch Salvo Fire Upon receipt of the multiple launch salvo fire order from the commanding officer and subsequent to selection of the missile tube firing order commands and orders are inputted into each weapon sequentially until FIRE is ordered During multiple launch salvo fire activation of the FIRE switch initiates the salvo fire Interlocks for all weapons programmed for launch must be closed prior to launching the first missile Once the FIRE switch is activated firing 1s automatic and only the loss of HATCH OPEN CAPSULE ARMED or MISSILE ENABLE will inhibit launch automatically The salvo firing sequence may be manually interrupted by pushing the STANDBY or FIRE button a second time Manual interruption will not abort or stop a weapon in process of being fired after ITL has been issued to a missile in the firing sequence The salvo may be restarted by manually pressing the FIRE button again 4 12 POST LAUNCH OPERATIONS After first motion and transmittal of the MISSILE AWAY si
106. CINCLANT FLTINST 8010 4 CINC PACFLTINST 8010 12 NSPC CINST 8010 12 147 PURPOSE OF REPORT An electronic reporting system that replaces the former CMFR system For use by Intermediate Maintenance Activities to report damaged faulty or failed equipment ineffective documentation routine requests for technical assistance corrective maintenance and or results of PMS accomplishment for RGM UGM 109C D E AURs and related equipment Report damaged faulty or failed equipment or ineffective documentation for 109A and related equipment Report PMS documentation deficiencies Report transfer change in condition of items identified in PEO CU INST 8800 1 SW820 AP MMI 010 WEAPON SYSTEM UGM 109 1 UGM 109 2 RGM 109 2 RGM 109 4 UGM 109 1 UGM 109 2 RGM 109 2 RGM 109 4 UGM 109 1 UGM 109 2 UGM 109 1 UGM 109 2 RGM 109 2 RGM 109 4 UGM 109 1 UGM 109 2 RGM 109 2 RGM 109 4 REVISION 15 REPORT PRODUCT QUALITY DEFICIENCY REPORT QDR REPORT OF ITEM DIS CREPANCY ROID SUBMARINE WEAPON FIELD TROUBLE REPORT SWFTR TECHNICAL MANUAL DEFICIENCY EVALUATION REPORT TMDER HAZARDOUS INCIDENT REPORT 27 MARCH 2009 MEDIA Standard Form 368 Standard Form 364 SWFTR Form NAVSEA Form 4160 1 Message GOVERNING DIRECTIVE NAVSEAINST 4855 7 NAVMATINST 4355 7 NAVSEAINST 4160 3 OPNAVINST 5102 1 for Navy CMPINST 5102 1 for contractor 148
107. Coded Launch Signal to discharge the firing capacitor to fire the CLS gas generator 3 14 2 CLS Unique Commands The Coded Charge Signal and Coded Launch Signal unique digital commands and the Capsule Arm Command is a unique discrete command sent by the submarine fire control system to the CLS a Coded Charge Signal A coded signal sent to charge the firing capacitor b Coded Launch Signal A coded signal sent 700 milliseconds after the Coded Charge Signal to discharge the firing capacitor which after separation nut release fires the gas generator to launch the TCM c Capsule Arm Command A command which causes capsule firing circuits to be placed in the armed position 3 14 3 CLS Unique Discrete Responses The following are discrete signals sent by the CLS 192 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 3 a Capsule Safe Monitor A continuity of CLS Monitor Power indicating that the CLS firing circuits are in the SAFE position b Capsule Armed Monitor A continuity of CLS Monitor Power indicating that the CLS firing circuits are in the ARMED position c Liquid in Capsule A signal indicating the presence of liquid in the capsule Capsule Dry A continuity of CLS Monitor Power indicating the absence of liquid in the capsule e Fire Pulse Detected A continuity of CLS Monitor Power indicating that the CLS firing capacitor has discharged 3 15 MISSILE CAPSULE AND MISSILE TUBE PHYSICAL INTERFACES The miss
108. D FOR EACH MISSILE TUBE AND ALL UP ROUND SELECTED FOR LAUNCH SEQUENTIALLY 2 RECYCLE AND ABORT LAUNCH ARE PERFORMED IN ACCORDANCE WITH NAVSEA OD 44979 3 EVENTS WITH AN ASTERISK DENOTE REM OPERATIONS FOR LAUNCHES WITHOUT REM THE EVENT IS DELETED 4 ONCE ITL HAS BEEN SENT OPERATORS NO LONGER HAVE THE ABILITY TO INTERVENE IN LAUNCH WITH THE EXCEPTION OF SENDING AN ABORT COMMAND AN ABORT CAN BE ACCOMPLISHED ANY TIME UP UNTIL THE MISSILE ENABLED SIGNAL IS SENT THIS OCCURS APPROXIMATELY 7 SECONDS AFTER ITL FOR TACTICAL AND RSS VARIANTS AND 36 SECONDS FOR REM VARIANTS ONCE BATTERIES HAVE BEEN ACTIVATED THE MISSILE IS IRREVOCABLY DUDDED AND CANNOT BE RECYCLED FOR FIRING 261 SW820 AP MMI 010 LAUNCH m COMMAND wa RELAY SWITCH ERROR INDICATED WEAPON 262 27 MARCH 2009 TUBE CHAPTER 4 4 REVISION 15 27 2009 SW820 AP MMI 010 263 4 REVISION 15 27 2009 SW820 AP MMI 010 RECYCLE ABORT NOTE 2 SENT MISSILE CAPSULE LE 264 SW820 AP MMI 010 REVISION 15 27 2009 MISSION 265 CHAPTER 4 UMTS MISSION CORRECT 4 REVISION 15 27 2009 SW820 AP MMI 010 266 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 RECYCLE ABORT NOTE 2 CAPSULE ARMED yes BOCSTER ARMED DISCONNECT NONCRITICAL
109. ENERAL Operators and maintenance personnel shall strictly observe all safety precautions applicable to their work or duty station Personnel are to immediately report any unsafe conditions or any equipment that is considered unsafe Carelessness is one of the major causes of injury to personnel Personnel shall be thoroughly and frequently instructed in the general safety precautions associated with the system Should situations arise which are not covered in the safety precautions presented in this or other applicable documents the commanding officer or other authorities may issue orders as deemed necessary For handling or maintenance of ordnance personnel performing operations shall be qualified and ordnance certified LAW NAVSEA OP 4 and OP 5 NAVSEAINST 8020 9 and 8023 2 and other applicable documents Familiarity with safety standards ASME ANSI B30 5 1989 and B30 8 1988 will help ensure safe crane operations The following are general safety precautions not related to any specific procedures and therefore do not appear elsewhere in this publication These are precautions that personnel must understand and apply during many phases of operations and maintenance LIVE CIRCUITS Personnel must observe all safety precautions while working on and around electrical equipment Do not replace components or make adjustments with the high voltage supply turned on Under certain conditions dangerous potentials may exist when the power control is in
110. ENTIFICATION SYSTEM DATA PLATE NITROGEN PRESSURE _ CHARGING PORT DELUGE CONNECTOR TELEMETRY ANTENNA CONNECTOR JUMPER ASSEMBLY BOTTOM VIEW WITHOUT PHS amp T EQUIPMENT B y BOTTOM VIEW CSES SWITCH WITHOUT PHS amp T EQUIPMENT 97 27 2009 010 Figure 1 36 Shipping and Storage Skid Mk 34 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 37 CLS Submarine Missile Tube Trainer Assembly 99 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 38 SMTT Training Shape 100 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 39 CLS Mk 45 Mod 2 Aft Cover 101 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 40 CLS Mk 45 Mod 2 Capsule Closure Assembly 102 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 41 SSGN Prototype Multiple All Up Round Canister MAC 103 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Table 1 1 Support Equipment Description EQUIPMENT Adapter Box Assy P N JCM 17683 Adapter Capsule Pneumatic P N 7324001 01 Adapter Endlift Container Mk 156 Mod 0 P N 5166882 Adapter Hook Mk 91 Mod 0 P N 2643315 Adapter Hook Mk 176 Mod 0 P N 6213621 Adapter Missile Round Pneumatic Test P N 6242918 1 FUNCTION Used with Rocket Motor Ident Test Set Box Assembly for performing CLS missile electrical checks Interface b
111. ER 1 The IMU measures linear acceleration and rotational angular rates to assist in the navigation of the missile to the intended target It uses three gyros and three accelerometers positioned on three axes as sensors All data is output to the Navigation Processor for navigation aiding The DIU provides lighting for the DSMAC IV System for use during night flights The DIU isa camera flash device that is optimized for coverage uniformity and spectral output The unit is designed to produce twice the optical energy of IIA Illuminator used on Block III Missiles There are two identical radar altimeter antennas on each Block IV TACTOM Missile These antennas provide the radar altimeter the ability to transmit rear and receive forward The radar altimeter system transmits RF signals to the ground and receives the reflected signals to determine altitude based on timing The updated altitude data 15 then provided to the Mission Control Processor 1 11 43 Aftbody and Tailcone Section The aft body Figure 1 18 TACTOM Aftbody and Tailcone Section extends from Sta 148 0 to Sta 196 0 and contains cruise engine flush inlet inlet cover and aft body cover The aftbody and tailcone section runs from Sta 194 75 to Sta 219 16 The aftbody and tailcone section structure is machined from A357 T6 castings The aft portion of the tailcone is designed to mate with the rocket motor In the case of the submarine configurations the missile also c
112. IAL FIREFIGHTING EQUIPMENT Scott air packs mine safety apparatus MSA or positive pressure self contained breathing apparatus HAZARDOUS PRODUCTS OF COMBUSTION carbon monoxide carbon dioxide acrolein phenols amines aldehydes aromatic amines and hydrofluoric and fluoroboric acids PERSONNEL PROTECTIVE EQUIPMENT a All personnel Disposable coveralls and shoe covers gloves leather palm preferred b Firefighters Positive pressure self contained breathing apparatus c Clean up personnel Full face respirator safety glasses w side shield 180 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 2 ITEM HAZARD CLEAN UP MATERIALS Polyethylene sheeting and tape for containing debris vacuum cleaner equipped w High Efficiency Particulate Air HEPA filter elements polyethylene bags water emulsion floor wax P W 155C NSN 7930 00 141 5888 HAZARDOUS WASTE DISPOSAL Local solid waste disposal authorities shall be consulted for approved burial sites techniques for composites or composite contaminated materials In addition the local cognizant industrial hygienist or medical department representative should be consulted for detail health hazard control guidance based upon extent of exposure POST LAUNCH WASTE WATER IN SPENT CLS CAPSULES Removal of post launch water from expended CLS capsules involves handling material which may be harmful to personnel and which is not authorized for direct dumping into coastal or inla
113. ISION 15 27 MARCH 2009 CHAPTER 4 297 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 34 Tilt Fixture Mk 23 Mod 0 with Kit B 298 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 35 Multiple All Up Round Canister MTEL Orientation X Denotes MTEL Alignment Pins 299 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 36 AUR Aft Cover Viewed in MAC 300 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Table 4 1 Missile Availability Factors AVAILABILITY FACTOR OVERRIDE Failure in cell Yes Number of firings from cell exceeds eight w o Yes ORDALT 16235 Number of firing counts from cell is will be Yes 10 75 or greater w ORDALT 16235 Missile in cooldown Yes Missile fuel leak Yes Module hazard fault Yes Module BITE faults Yes Launch sequence detected fault Yes Launcher unauthorized by TWCS No Canister or plenum cover not present not No dogged down Module declared unavailable No Restrained missile firing within module No MCP BITE is on but should not be No Module set to an offline status No No missile in cell No Cell and missile already selected for a No launching Fault previously reported in half module No containing the missile Fault previously reported in missile No Launch sequence failure previously reported No Launch operations not enabled in VLS No Cell select relay K1 not energized No 301
114. ISSILE RADAR ALTIMETER DATA TERCOM DIGITAL MAP STORED IN CMGS COMPUTER 77 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 18 TACTOM Aftbody and Tailcone Section PFU 2 Fin Actuators Fin Controller Desiccant NS GEU Assembly AGR SPU DCP DSP RA ADM PPCA 7 DSMAC Camera lt gt Inlet Cover 5 78 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 19 Typical Mission Profile 109A C TERCOM AND GPSS 109C UPDATES TERRAIN FOLLOWING MODE HIGH LOW ALTITUDE OPTIMUM RANGE LOW LOW ALTITUDE OPTIMUM PROTECTION FROM DETECTION TERMINAL MANEUVER TERMINAL CRUISE DSMAC AND DSMAC IlA GPSS UPDATE 109 27 TRANSITION LAUNCH CRUISE PHASE SUBMARINE AND BOOST PHASES LAND 79 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 20 Typical Mission Profile 109D ADDITIONAL NAVIGATION FIXES AND TARGETS TERRAIN FOLLOWING MODE GPSS AIDING TERMINAL PAYLOAD COVER DSMAC JETTISON DSMAC Il A HIGH LOW ALTITUDE TERCOM 05 OPTIMUM RANGE 05 LOW LOW ALTITUDE OPTIMUM PROTECTION FROM DETECTION CRUISE PHASE ae Bie s j LAUNCH L 7 AND TRANSITION ka BOOST CRUISE SUBMARINE LAND 80 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 21 CLS Missile Tube Loading and Handlin
115. IT passes the REM batteries activate and post battery activate BIT is begun 3 2 2 4 Bus Isolation Battery power 15 supplied only to those circuits essential to the launch boost phase For a land attack TCM power up of the BPU is sensed by the CMGS RMUC The RMUC in turn sends a discrete coded word to the From the power is applied to the coil of the BUS ISOLATE relay The relay energizes to isolate the REGULATED bus from the MCM and CMA buses The BUS ISOLATE relay remains energized until the engine driven generator regulator comes on line during the transition to cruise flight 3 2 2 5 First Motion Upon first motion the electrical connection between the and the launch platform is disconnected and deenergizes the FIRST MOTION relay The opening of relay contacts 15 sensed by the CMGS which starts the safe eject test The ARM ENABLE relay energizes and the normally open contacts of the ARM ENABLE relay close applying power to the normally open contacts of the SAFE ARM relay The CMGS confirms safe eject velocity and distance then commands the MCM to energize the SAFE ARM relay This action routes electrical power from the CMA battery to energize the PYRO bus The SAFE EJECT relay energizes completing the circuits that hold the SAFE EJECT relay and the ARM ENABLE relay energized The PYRO bus supplies the power to activate the CMA pyros The PYRO bus remains energized until the completion of transition to cruise flight 3
116. LERT ACK FFK 289 SW820 AP MMI 010 REVISION 15 W 1 PROMPT AREA RECOMMEND ENTER CURRENT GPS CRYPTO KEY PROMPT AREA SELECT ARRAY THEN ARRAY TEA 27 MARCH 2009 SELECT MANUAL SYSTEM CONTROL ARRAY TEA ENTER CURRENT GPS CRYPTO KEY DATA AS REQUIRED KEYBOARD INITIATE ENTR 290 CHAPTER 4 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 ENTER NEXT GPS CRYPTO KEY DATA AS REQUIRED KEYBOARD CLEAR ALERT AREA SELECT ENTER GPS CRYPTO KEY TEA 1 PROMPT AREA ALARM SILENCED RECOMMEND ENTER NEXT GPS CRYPTO KEY ENTRY ACCEPTED ENTRY VERIF AREA ALERT AREA RECOMMEND ENTER NEXT GPS CRYPTO KEY INITIATE ALERT ACK PROMPT AREA 291 SW820 AP MMI 010 REVISION 15 NO BLW 50 MIN MSL BIT PASS DATA LOAD OFP PROG TO OFP COMP TO MSN PROG TO MSN COMP BOOSTER SAFE MSL STAT SEL MSL CLASS UNCLICLASS SEL STAT DISP AREA NOTE 27 MARCH 2009 ALERT AREA 292 CHAPTER 4 NOTE THE MISSION DTD CONTAINS A MORE CURRENT DFS GFS VERSION THE ALERTS DFS LOAD REQUIRED MSL AND OR GFS LOAD REQUIRED MSL WILL BE OBTAINED DATALOAD WILL ALSO INDICATE DFS GFS PROG TO DFS GFS SW820 AP MMI 010 REVISION 15 ALARM SELECT SILENT ALARM INITIATE SHIP S
117. MARCH 2009 CHAPTER 1 1 23 1 6 Separation Nuts Two separation nuts attach to two hold down studs on the missile aft end to position the missile before launch and secure the missile to the VSA Each separation nut has two explosive initiators which when fired just prior to missile launch cause the nut to separate from the hold down stud thus permitting missile egress 1 23 1 7 Vertical Support Assembly VSA The VSA consists of a vertical shock and vibration mitigation device a metal bellows anti rotation device two missile retention devices a gas generator gas deflector two missile away switches and a capsule extension The VSA mitigates shock and vibration to the missile in the axial direction positions the missile vertically and azimuthally in the capsule provides a flow path for gases from the gas generator to the missile during launch and provides for mounting electrical control components 1 23 1 8 Capsule Extension The capsule extension provides a watertight connection between the VSA and the aft closure assembly It also provides attachment for the aft closure assembly 1 23 1 9 Aft Closure Assembly The aft closure assembly has provisions for mounting the gas generator and the electrical cabling and controls It also provides through access for electrical cabling and ensures a watertight barrier at the capsule aft end An aft cover attaches to the aft closure to provide a closed environment for the gas generator and electrical cabl
118. MENT FUNCTION Pin Trunnion Alternate to Mk 174 Trunnion Bearing P N 5768606 Adapter to transition the All Up Round Platform Loading P N 5580126 Platform Loading P N 7066384 A1 Platform MTEL Work P N 7126403 002 Plug Assembly Moisture and Dust JCM 17838 4730 01 346 3387 Pressure Vacuum Distributor H3353 P N 5758382 Simulator and CLS Ballast Can between vertical and horizontal during onload off load Used on SSN 688 Class submarines for access to missile tubes Used on SSN 774 Class submarines for access to missile tubes Allows access to the area above the MTEL during SSGN handling operations Seals pressure vent port on CLS AUR AUR Simulator and CLS Loading and Handling Trainer Purge and backfill warhead cavity and missile during 109A warheading and dewarheading 113 ILLUSTRATION SW820 AP MMI 010 EQUIPMENT Protective Shield Umbilical Cable P N JCM 17873 Pump Submersible 440 Volt with Foot Valve Assembly Retainer Separation Nut Lockring Wrench P N 76L5319 1 Security Band Assembly P N 5979383 Security Cover 4 7 P N 76 2994 1 REVISION 15 27 MARCH 2009 CHAPTER 1 FUNCTION Installed on the CLS AUR and CLS Loading and Handling Training Shape umbilical cable during off load to prevent damage from contact with the missile tube while extracting the weapon from the tube Not required with new design umbilical cable with angled cable flange penetrator o
119. Mk 106 Mod 0 Rocket Motor only f Applicable to variants with Mk 111 Mod 0 Rocket Motor only g Applicable to UGM JUGM 109 1 only h Applicable to UGM JUGM 109 2 only 1 Applicable to JUGM UGM 109E 1 2 only 153 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Table 1 7 Variant Unique Descriptive Data ITEM 109A Guidance Land Attack AN DWS 15 V I Block Warhead Type Weight W80 Mod 0 Non Conventional Warhead Type Weight Fuel Capacity TACTICAL 1121 Ib a REM 1121 1 a RSS Warhead Arming Devices Dual Air Valve 109C Land Attack AN DWS 15 V I Block III w DSMAC or DSMAC IIA and GPSS WDU 25 B Conventional high explosive Picratol H 6 992 b 378 Ib explosive WDU 36 B Conventional high explosive PBXN 107 Type II 690 Ib 265 Ib explosive 350 Ib a 546 Ib b 354 Ib a 558 Ib b 350 Ib a 468 Ib b FZU 43 B Pyrotechnic actuated dual initiator 154 109D Land Attack AN DWS 15 V I Block III w DSMAC or DSMAC and GPSS BLU 97 B Conventional high explosive Cyclotol 70 30 287grams each 527 Ib a 568 Ib b 474 lb a 474 Ib b 109E Land At tack Guid ance Electron ics Unit w DS MAC GPSS and TERCOM WDU 36 B Conventional High Explosive Warhead PBXN 107 Type II 690 Ib 265 Ib explosive 1100 Ib FZU 43 B Pyrotechnic actuated dual initiator SW820 AP MMI 010 REVISION 15 ITEM 109A
120. Mk 111 Rocket Motor Add up to 0 5 inch to measurement for variants with Mk 106 Mod 0 Rocket Motor AUR CG at station 138 0 Mk 17 Trainer Canister CG at station 130 0 166 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Table 1 15 Weights of VLS Variants ITEM HANDLING WEIGHT Pounds Kilograms AUR JRGM RGM 109C 4 7290 3307 JRGM RGM 109D 4 7133 3236 109 2 7154 3245 TRAINER CANISTER TRAINER MK 14 6528 2961 NOTE Handling weights calculated using heaviest components plus a small safety factor 167 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 2 CHAPTER2 SECURITY AND SAFETY 2 1 SCOPE This chapter discusses TOMAHAWK Weapon System TWS security and safety requirements regulations and general policies relating thereto 2 2 SECURITY TOMAHAWK mission criticality high cost and political sensitivity require an adequate level of security be maintained regarding security safeguards and physical protective measures used for commercial government transport OPNAVINST 5530 13 PEO CU INST 4601 1 and NAVSEA SW020 AG SAF 010 contain specific security requirements for transport of TOMAHAWK Cruise Missiles TCM variants over public highways Storage and transport of TCM variants on military installations will be LAW NAVSEA OP 5 NAVSEA OP 4461 and amplifying local directives 2 2 1 Security Classification All TCMs carry a minimum security classification of CONFIDENTIAL OPNAVINST 55513 28 contains spec
121. N THE EVENT OF TUBE RECTIFIER FAILURE POWER IS AVAILABLE THROUGH TORPEDO ROOM SWITCHING TO SAFE THE WARHEAD AND OR ROCKET MOTOR BOOSTER FROM THE ALTERNATE TORPEDO TUBE RECTIFIER I E RECTIFIER 1 CAN SUPPLY TUBE 1 OR TUBE 3 CIRCUITS AND RECTIFIER 3 CAN SUPPLY TUBE 3 OR TUBE 1 CIRCUITS IDENTICAL CIRCUITRY SWITCHING IS AVAILABLE FOR THE PORT RECTIFIERS 6 ONCE ITL HAS BEEN SENT OPERATORS NO LONGER HAVE THE ABILITY TO INTERVENE IN LAUNCH WITH THE EXCEPTION OF SENDING AN ABORT COMMAND AN ABORT CAN BE ACCOMPLISHED ANY TIME UP UNTIL THE MISSILE ENABLED SIGNAL IS SENT THIS OCCURS APPROXIMATELY 7 SECONDS AFTER ITL FOR TACTICAL AND RSS VARIANTS AND 36 SECONDS FOR REM VARIANTS ONCE BATTERIES HAVE BEEN ACTIVATED THE MISSILE IS IRREVOCABLY DUDDED AND CANNOT BE RECYCLED FOR FIRING 7 THE CAPSULE CAN BE EITHER IMPULSE EJECTED OR RETURNED TO TORPEDO ROOM RACKS AFTER MISSILE IS LAUNCHED SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 241 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 om CK SERM OPERATE M FOWER TO CONVERTER OF 9 WEAPON NOTE 1 ves MON TOR RESET POWER MOTOR SAFE ROCKET RELAY MOTOR Yo ExSROIZED sare ROCKET MOTOR APMED areva ABORT BLANK RECYCLE ARNT ves NOTE 1 WARHEAD BAFE 2
122. OMAHAWK CRUISE MISSILE UGM 109 1 WARHEAD INSTALLATION REMOVAL AND AIR VEHICLE MAINTENANCE This volume contains PGs OPs and RPBs to handle and prepare UGM 109A All Up Rounds for installation or removal of the warhead and to perform authorized maintenance on the UGM 109A Air Vehicle PURPOSE This document provides information data and procedures for operations and support of the TOMAHAWK Weapons System TWS TOMAHAWK ALL UP ROUND LOGISTICS AND MAINTENANCE INFORMATION PRODUCT TALMIP DEFICIENCY EVALUATION REPORTING All errors omissions discrepancies and suggestions for improvements to PEO U amp W TALMIPS shall be reported to Naval Surface Warfare Center Division Naval Systems Data Support Activity using NAVSEA SPAWAR Technical Manual Deficiency Evaluation Report NAVSEA Form 4160 1 The preferred reporting method for activities with suitable internet access is the on line TMDER input page at the uniform resource locator URL address https nsdsa2 phdnswc navy mil A copy of NAVSEA Form 4160 1 for local reproduction is included in this TALMIP on the CD s root directory under FORMS as tmderform rev 2003 Extra copies of the form may be requisitioned from Naval Inventory Control Point Cog I 17 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 FOREWORD Material 700 Robbins Avenue Philadelphia PA 19111 5089 Hard copies may be submitted to Commander NAVSURFWARCENDIV NDSDA 4363 Missile Way Port Hueneme CA 93043
123. ON This volume presents information pertinent to the submarine and surface launch TOMAHAWK Weapon System TWS to include physical and functional descriptions of system components safety and security considerations and operations aboard platforms employing the TWS b Volume 2 SW820 AP MMI 020 TOMAHAWK CRUISE MISSILE GENERAL HANDLING PROCEDURES This volume contains Procedural Guides PGs Operating Procedures OPs and Standard Inspection Procedures SIP to permit afloat and ashore activities to perform receipt handling inspection transfer and reconfiguration processes for TOMAHAWK Cruise Missile TCM configurations This volume does not include procedures for combatant onload offload or submarine tender unique on board handling Combatant onload offload procedures are contained in NAVSEA OD 44979 for Torpedo Tube Launch TTL variants in NAVSEA OD 44979 and SW820 AD WHS 010 for Capsule Launching System CLS variants and in SW394 EE PRO 010 for Vertical Launching System VLS variants Processes unique to handling TCM configurations on board submarine tenders are contained in SW820 AA WHM 010 for TTL and in SW820 AD WHS 030 for CLS and VLS on AS 39 Class c Volume 3 SW820 AP MMI 030 TOMAHAWK CRUISE MISSILE MAINTENANCE PROCEDURES This volume contains PGs OPs SIPs and Repair Parts Breakdown RPB to permit afloat and ashore activities to perform authorized maintenance on TCM configurations d Volume 4 SW820 AP MMI 040 T
124. ONTROL SYSTEM ey isa Fea tie Deren Vua do 197 3 23 EXHAUST GAS MANAGEMENT 197 CHAPTER 4 OPERA LIONS Pada haqtay 204 SECTION Tos 204 a 1 SCOPE due 60 2 0 et se fer end 204 SECTION II TORPEDO TUBE LAUNCH uuu sae 205 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 42 LAUNCH PLATEORMS SSL S REP PERO er A eden 205 4 2 1 Submarine Combat System 2553 3534 eno EV NE 205 4 2 2 Combat Systems Electronic Space CSES 205 4 2 3 Navigation Equipment eR Ta qux De d d du os 205 4 2 4 Weapon Launch and Pressurization Vent Equipment 205 4 2 5 Weapon Shipping Unshipping Equipment 2 00 122 205 4 2 6 Weapon Handling and Stowage Equipment 2 206 CS WBAPON ONEOAD b i ders i 206 4 4 OPERATIONAL 8 5 8 2 206 Launch e E FORTIS EOS EON QU TERR TES DAE NAAR 206 44 7 Weapon MIX Eua ox LET Dui edes sam Visa tana tide es 206 4 4 3 Alert Messages and Interlocks 2 00000 206
125. ONYM PFU PG PGA PHS amp T PIP P L PLA PMS PPCA PPM PROM PSA psid psig PTMCR PUB PWD Q D QA QAST QATIP QDR QUICKTRANS RA RASS 27 MARCH 2009 CHAPTER 1 DEFINITION Power Filter Unit Procedural Guide Pneumatic Gauge Assembly Packaging Handling Storage and Transportation Push In Pull Position Launch Plain Language Address Planned Maintenance System Pyro and Power Control Assembly Parts Per Million Programmable Read Only Memory Power Switching Amplifier Pound s Per Square Inch Differential Pound s Per Square Inch Gauge Preliminary Technical Manual Change Request Publication Pressure Vent Pressure Velocity Pressurization Vent Control Pressure Vacuum Distributor Pressure Vent Test Vehicle Pressure Vent Test Vehicle TOMAHAWK Test Missile Programmed Warhead Demolition Quantity Distance Quality Assurance Quality Assurance Service Test Quality Assurance Test and Inspection Procedure Quality Deficiency Report Contractor Operated Logistics Airlift Radar Altimeter Random Access Storage Set 142 SW820 AP MMI 010 REVISION 15 ABBREVIATION ACRONYM RDX REM REPROG RF RFI RGAP RJA RLEP RM RMUC RNS ROID RPB RPL RPU RSC RSEU RSS S amp TE S N SAFEPOT SAMDS SATCOM SATNAV SB SCG SCS SDL SEC SHIPALT 27 MARCH 2009 CHAPTER 1 DEFINITION Cyclonite Recovery Exercise Module Reprogram Radio Frequency Ready For Is
126. R or o ring on an AUR Volumetric Shape Simulator during loading The muzzle face protective cover and the missile tube muzzle hatch and magnet protective cover are installed Figure 4 16 SSN 688 Class Submarine Missile Tube Equipment For the AUR Volumetric Shape Simulator onload mylar O ring protective sleeve assembly is also installed Special procedures like direct tube to tube transfer of AURs on the same submarine or between different submarines may utilize lip seal protective covers fabricated from split garden hose or equivalent or a lip seal protective sleeve fabricated from various sheet materials The counterbore cover is installed to prevent personnel tools water and debris from entering the empty missile tube The Environmental Monitoring Sensor EMS pressure and temperature ambients are checked and a leak test performed SCS circuits are checked using the All Up Round Electronic Simulator AURES The accuracy of the differential pressure transducer is verified and the pressurize vent P V plug is removed and stowed The counterbore cover is removed 4 9 1 2 Install Loading Equipment After the missile tube and ship systems have been prepared for loading submarine tender shore base personnel install the loading equipment aboard the submarine This includes the Installation Guide Assembly Mk 116 Hydraulic Power Unit HPU Mk 8 Missile Tube Extension Loader MTEL Mk 23 and the MTEL Safety Cover The installation guide
127. RAIF EQUALIZATION HULL VALVE ACTUATOR 252 TUBES HATCH ACTUATOR GM PRESSURE RETURN FLOOD amp DRAIN DRAIN VALVE CONTROL VALVE ACTUATOR PRESSURE RETURN SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 12 SSN 688 Class Submarine Pressurization Vent System DIFF PRESS XDUCER P V SUPPLY AND PRESS SWITCH ISOLATION VALVE TO OTHER DEW POINT P V VALVES SENSOR 125 PSIG BACKUP 700 PSIG CONNECTION SERVICE MAIN ISOLATION TO OPPOSITE VALVE BANK P V HULL VALVE 253 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 13 SSN 688 Class Submarine Flood and Drain System 125 PSIG FLOOD amp DRAIN FLOOD amp ca ISOLATION HULL amp B U VALVES DRAIN VALVE CONNECTION Ort FROM EQUAL BANK B U VALVE GRAVITY DRAIN SYSTEM TO BILGE COLLECTING TANK 254 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 14 SSN 688 Class Submarine Missile Tube Control System TUBES 557 TUBES 8 amp 11 TUBES 13 amp 15 HATCH OPEN SWITCH HATCH CLOSED SWITCH FLOOD 8 DRAIN VALVE ENVIRON MON SENSOA DIFF PRESS TRANSDUCER TUBES 10 amp 12 TUBES 14 amp 16 INBD OUTDO POWER 255 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 15 Loading Platform Installed DECK FAIRING PLATE NOTE GRAB RAILS NOT SHOWN FOR CLARITY 256 SW820 AP MMI 010 RE
128. RE signal indicating the aft closure plate has been blown open the LSEQ applies power to detonate the explosive restraining bolts allowing release of the TCM When the canister forward closure is broken the breakwire opens to send a MISSILE AWAY signal to the LSEQ which in turn notifies the LCU of missile away 4 18 10 Cell Safing The cell safing sequence may begin at any time when an unsafe condition is monitored a launch sequence is terminated ABORT command issued interrupted SAFE command issued by the TWCS or when a MISSILE AWAY signal is not sent missile misfire or restrained fire During this sequence the SAFE MISSILE command is sent relays open to disconnect power and data lines to the cell In the case of a restrained fire the deluge system is activated If missile batteries were activated prior to an unsuccessful firing attempt missile inventory is updated to reflect the unavailability of that TCM for launch If batteries were not activated the TCM is placed in a 30 minute cool down period prior to being made available for future launch 4 19 POST LAUNCH When the LSEQ receives the MISSILE AWAY signal the LSEQ disconnects prelaunch cell power and signals from the cell and cancels the missile cell selection After a delay to allow the missile and exhaust gases to clear the launcher cell and uptake hatches are closed The LCU evaluates the launch and updates missile inventory and cell firing count to reflect the change in s
129. RESSURIZATION VENT CONTROL SYSTEM The PVC system features independent four tube controls to regulate internal TCM pressure to withstand sea ambient pressure during pre launch operations With the electrical and pneumatic umbilicals connected to the TCM and the PVC system activated dual differential transducers in the TCM one operator selected and one alternate compare internal free volume 189 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 3 pressure with outside ambient pressure and output signals to PVC system equipment The signals energize deenergize manifold pressure vent block solenoids which permit pressurization or venting to occur in order to maintain TCM internal pressure within prescribed limits When pressure is not within prescribed limits the system inhibits launch until the TCM is pressurized vented and the PRESSURE IN BAND indication is restored Should the selected transducer fail the system automatically vents the TCM and likewise inhibits launch until the operator selects the alternate transducer and the PRESSURE IN BAND indication is restored Should the automatic PVC system fail the PVC system can be operated manually utilizing the TCM pressure relief valve as the backup to prevent TCM overpressurization Just prior to launch the fire control system sends an IMPULSE FIRE mark to terminate pressure vent commands to prevent pressure cycling and a possible out of band condition at launch 3 11 SECURITY SYSTEM Secu
130. SEMBLIES 44 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Separate electrical and pneumatic umbilicals Figure 1 24 Electrical and Pneumatic Umbilicals are supplied to interface with the submarine launch and pressure vent control systems The umbilicals are described in the following paragraphs 1 17 1 Electrical Umbilical The electrical umbilical measures 40 50 inches long and consists of a multiconductor electrical cable with quick release connectors on each end One end connects to the breech door inside Y connector The other end connects to the electrical connector on the aft end of the missile The connector at the missile end of the umbilical has a hand pull lanyard to aid manual release 1 17 2 Pneumatic Umbilical The pneumatic umbilical measures 30 inches long and consists of a hose assembly two pneumatic couplings a lanyard and a shackle and PIP pin One end of the umbilical connects to the breech door penetrator The other end connects to the capsule pneumatic coupling The lanyard secures to an eyebolt on the inside of the breech door via the shackle and PIP pin 1 18 INERT VARIANTS The paragraphs below discuss certification training and other inert variants provided to Fleet and shorebase operational and support activities to conduct TTL training maintain technical proficiency and complete personnel crew and ship certifications 1 18 1 TOMAHAWK Test Missile TOTEM UTM 109 1 The TOTEM is an encapsulated
131. SHROUD 71 1 REVISION 15 27 2009 SW820 AP MMI 010 5 58 5 8 2 iuh 3 8 gt E xus sndddsurs s 5 o i i gt 558 7 5 INW S 2 SN AN de T 5 c 72 6008 REM CONFIGURATION SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 13 TACTOM Midbody Section Note Pyrotechnic components are underlined 73 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 14 Range Safety System 109C 1 DUAL ASC RECEIVER DECODER 2 C BAND TRANSPONDER iP POWER MONITOR UNIT 4 C BAND ANTENNA 2 y 5 MRA ANTENNAS REF 6 RSC TEST OSCILLATOR 7 CODER TIPLEX 9 S BAND TRANSMITTER THERMAL BATTERY SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 ANSPONDER 8 DUAL RSC RECEIVER DECODER 10 THERMAL BATTERY 11 RSC TEST OSCILLATOR 13 POWER MONITOR UNIT SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 16 Typical Land Attack TCM Pre landfall Flyout Route me WAYPOINT SAC SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 17 Terrain Contour Matching TERCOM Process HIN M y irr aut LA W 4 ig 7 CORRELATION PROCESSOR OUTPUT M
132. SW820 AP MMI 010 REVISION 15 27 MARCH 2009 SW820 AP MMI 010 TECHNICAL MANUAL TOMAHAWK CRUISE MISSILE RGM UGM 109 SYSTEM DESCRIPTION REVISION 15 THIS DOCUMENT SUPERSEDES SW820 AP MMI 010 REVISION 14 DATED 15 MARCH 2008 DISTRIBUTION STATEMENT D Distribution authorized to the Department of Defense and U S DOD contractors only administrative or operational use 7 April 1998 Other requests for this document shall be referred to Program Executive Officer for Unmanned Aviation and Strike Weapons PEO U amp W WARNING This document contains technical data whose export is restricted by the Arms Export Control Act Title 22 U S C Sec 2751 et seq or the Export Administration Act of 1979 as amended Title 50 U S C App 2401 et seq Violations of these export laws are subject to severe criminal penalties Disseminate in accordance with provisions of DoD Directive 5230 25 DESTRUCTION NOTICE Destroy by any method that will prevent disclosure of contents or reconstruction of the document PUBLISHED BY DIRECTION OF PROGRAM EXECUTIVE OFFICER FOR UNMANNED AVIATION AND STRIKE WEAPONS 27 March 2009 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 TABLE OF CONTENTS FOREWORD oe 17 CHAPTER 1 INTRODUCTION a uum san unanqa 19 SECTION I DOCUMENT ORGANIZATION 19 JA GU Lr 19 til Chapter
133. T VIEW A REFLECTS ORDALT 16226 IF THE SAME PIN 15 USED FOR EACH POSITION ACCOMPLISHED 280 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 31 Upright Mk 14 VLS Canister to Vertical Position THE SAME PIN 18 USED FOR EACH POSITION 281 SW820 AP MMI 010 Figure 4 32 RGM 109 4 Land Attack TCM Operational Sequence 15 Sheets REVISION 15 27 MARCH 2009 CHAPTER 4 LEGEND TYPICAL OPERATOR EQUIPMENT ACTION DISPLAY n DELAV EQUIPMENT OPERATION INITIAL CONDITIONS 1 WEAPONS CONTROL SYSTEMS POWER UP 2 VERTICAL LAUNCH SYSTEM VLS MK 41 POWER UP NOTES FOR SALVO LAUNCH EVENTS DEPICTED FOR SINGLE LAUNCH WILL BE ACCOMPLISHED FOR EACH MISSILE AND AUR SELECTED FOR LAUNCH SEQUENTIALLY ABORT LAUNCH OPERATIONS PERFORMED IAW OP 3594 VOL DESELECT MISSILES ARE ACCOMPLISHED IAW NAVSEA OP 3594 VOL 9A INOP OF AMISSILE IS MANUALLY ACCOMPLISHED IAW NAVSEA OP 3594 VOL 9A THE SYSTEM PROVIDES SOFTWARE PROGRAMS WHICH AUTOMATICALLY SENDS A CANTCO MESSAGE UNDER CERTAIN CONDITIONS IF AN ENGAGEMENT PLAN 15 UNACHIEVABLE UNDESIRABLE THE LC MAY MANUALLY OUTPUT A CANTCO ORDER TO THE EP 282 SW820 AP MMI 010 REVISION 15 LAUNCH AUTHORIZED CONVENTIONAL LA MISSION DTD INSTALLED NOTE 1 LCG INITIALIZED ORDER AND VERIFY LAUNCH ENABLE AND CSES SET NOTE 3 VERIFY AUTH MAG AND M
134. TH WIRE SEAL ASSEMBLY WIRE SEAL 93 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 33 AUR Simulator Shipping Skid STOWAGE PAD SPACE EYES AFT COVER FWD COVER 8 SHIPPING SHIPPING SKID SKID S N LIFTING STRAP FORK LIFT SLOTS SHIPPING SKID SLOTS LIFTING STRAP SLOTS 94 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 34 Mk 10 Canister FLY THROUGH COVER CANISTER BARREL CANISTER IDENTIFICATION PLATE RUPTURE DISK 3 MJR IDENTIFICATION PLATE LOADING BRACKET CANISTER BASEPLATE ved PHEUMATIC DUICX DISCONNECT COUPLING WASHER 15 12 10 CABLE AND CONDUIT ASSEMBLY CONNECTOR 14 13 11 SEPARATION KUT LOCKING RING 12 PROTECTIVE COVER A 13 SEPARATION NUT 14 WIRE SEAL 10 15 SEPARATION NUT INITIATOR SQUIB 16 SHIELDING CAP 4 17 CABLE ANO CONDUIT ASSEMBLY 18 GROUNDING BOLT 19 PRESSURE GAGE 20 SEPARATION NUT THREAD PROTECTOR 2 21 UMBILICAL CONNECTOR ADAPTER 22 HOISTING BRACKET 21 MISSILE IDENTIFICATION SYSTEM DATA PLATE A to na a 95 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 35 Mk 14 Canister 2 Sheets CANISTER WITH PHS amp T EQUIPMENT HORIZONTAL STRONGBACK ENGAGEMENT HOLE SHOCK ISOLATION SKID gt VERTICAL LIFT LUG AFT END VIEW WITHOUT PHS amp T EQUIPMENT AFT FROTECTIVE COVER 96 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 MISSILE ID
135. UNIT ACCELEROMETER WARHEAD INTERFACE PACKAGE RGAP UNIT ROTATED 90 62 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 3 Land Attack 109C gt 25 FWD BODY GUIDANCE SECTION 2 1 GUIDANCE SET 2 OR DSMAC SET 3 JUNCTION BOX 4 WARHEAD SUPPORT WEDGE 4 5 WING 6 WARHEAD FUZE BOOSTER 7 CMA THERMAL BATTERY DRY WELL SIDE 8 WING ACTUATOR 3 STANDARD MISSION COVER 10 LATERAL THROUGH SLOT 11 OOOR ACTUATOR 12 AIR DATA PACKAGE 13 MISSION CONTROL MODULE 14 PHEUMATIC STORAGE BOTTLE HOUSING 15 DC GENERATOR REGULATOR 16 SUSTAINER ENGINE Td 19 STA 246 06 4 243 33 105 STA propulsion 21846 SECTION 5 17 FIN POWER SWITCHING AMPLIFIER 18 SERVDACTUATOR 3 18 ROCKET MOTOR 20 FIN 4 21 ENGINE INLET 22 HEAD 23 FUEL EXPANSION BLADDER 24 FUEL DEFUEL PANEL 25 FUEL HOPPER 26 COOLANT PUMP GUIDANCE SET 27 DUAL AIR VALVE WARHEAD FUZE PREARM 28 WOU 25 8 OR WDU 36 8 WARHEAD OR TEST PAYLOAD 29 ILLUMINATOR ASSEMBLY 30 RADAR ALTIMETER ANTENNA 2 21 SENSOR WINDOW COVER amp THRUSTER 32 NOSE CONE KIT OR NOSE FAIRING 33 GPSS RECEIVER PROCESSOR UNIT 34 GPSS ANTENNA MODULE 63 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 4 Digital Scene Matching Correlation DSMAC CONTAINER B ILLUMINATOR ASSEMBLY A DSMAC SET 64
136. VENTS CLOSURE REQUIRED P ALERT AREA 27 MARCH 2009 CLEAR ALERT AREA SALVO WARNING AND VENTS CLOSURE SWITCH TO ON 293 CHAPTER 4 ALARM INITIATE ALERT ACK FFK SW820 AP MMI 010 RECOMMEND INITIATE ALERT ACK FFK CLEAR ALERT AREA 1 PROMPT AREA REVISION 15 27 MARCH 2009 INITIATE PROMPT SEQ FFK RECOMMEND CLOSE S EXECUTE PLAN P NN AT TOE 0 00 SELECT ENGAGE PLAN SUMMARY DISPLAY TEA EXEC STATUS RECM EXEC SEL STAT DISP AREA 294 CHAPTER 4 SELECT LA DISPLAY TEA ENTER PLAN ID NUMBER KEYBOARD INITIATE PLN LCH SEL FFK EXECUTE PLAN P CMD LABEL AREA RECOMMEND LIFT EXECUTE SAFETY COVER SW820 AP MMI 010 REVISION 15 INITIATE EXECUTE FFK ENTRY ACCEPTED CMD LABEL AREA 27 MARCH 2009 CHAPTER 4 BOOSTER ARMED ALIGN MODE 8 SEL STAT DISP AREA ALERT AREA 295 SW820 AP MMI 010 REVISION 15 INITIATE ALERT ACK FFK SALVO FIRING COMPLETE P ALERT AREA INITIATE ALERT ACK FFK CLEAR ALERT AREA 27 MARCH 2009 MSL BiT BLANK DATA LOAD BLANK ALIGN MODE MODE 0 BOOSTER UNK MSL STAT EMPTY RECM TOE BLANK SEL STAT DISP AREA SELECT ENGAGE PLAN SUMMARY DISPLAY TEA ALL ELEMENTS ARE BLANK SEL STAT DISP AREA 296 CHAPTER 4 SW820 AP MMI 010 REV
137. VISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 16 SSN 688 Class Submarine Missile Tube Equipment FI Tj Dn COUNTERBORE COVER GAGGING THE MISSILE TUBE HATCH IN THE OPEN POSITION C MISSILE TUBE MUZZLE HATCH AND MAGNET PROTECTIVE COVER PROTECTIVE SLEEVE O RING MUZZLE FACE PROTECTIVE ASSEMBLY COVER 257 4 REVISION 15 27 2009 SW820 AP MMI 010 Figure 4 17 CLS Weapon Onload 3 POSITION AND LOWER AUR INTO MISSILE TUSE 258 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 18 CLS Weapon Seating in Missile Tube MTEL INSERTION PIN AUR SUPPORT QU PLATE AUR LIFTING SEATED B POSITION 1 1 t 259 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 19 Secure CLS Weapon in Missile Tube CABLE CLAMP 1 JACKING SCREW UMBILICAL CABLE CONNECTOR UMRILCAL CABLE 3 MISSILE TUBE UMBILICAL CONNECTOR RETENTION SEGMENT 8 MISSILE RETENTION SEGMENT TUBE CAPSULE CLOSURE ASSEMBLY LIP SEALS P V PORT ANNULAR SPACE VENT 260 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 20 UGM 109 2 Land Attack TCM Operational Sequence 10 Sheets LEGEND INITIAL CONDITIONS 1 COMBAT CONTROL SYSTEM POWERED UP 2 VLS SHIP SYSTEMS OPERATIONAL 3 SHIP MOTION WITHIN LIMITS 4 SUBMARINE IN LAUNCH ENVELOPE NOTES 1 FOR SALVO LAUNCH EVENTS DEPICTED FOR SINGLE LAUNCH WILL BE ACCOMPLISHE
138. Vertical Launching System Umbilical Breakout Box Mk 674 Mod 0 User s Manual for VLS Canister Code Plug Test Set Mk 673 Mod 0 Marking for Shipment and Storage Truckloading Encapsulated TOTEM TOTEM Capsule and Expended Capsule Truckloading CLS Ballast Cans Chocked Truckloading VLS Canisters Mk 13 14 amp 15 and All Mods and Mixed Loads Empty and w o PHS amp T Military Standard Inspection Magnetic Particle Standard Requirements for Soldered Electrical and Electronic Assemblies Nondestructive Testing Personnel Qualification and Certification Military Standard Inspection Liquid Penetrant Operations and I Level Maintenance Instructions with Illustrated Parts Breakdown Weapons Skid Aero 21C Part Number 64A114H 4 Truckload Guided Missile U RGM 109 TOMAHAWK in Shipping and Storage Container CNU 308 E 125 SW820 AP MMI 010 REVISION 15 DOCUMENT NUMBER NAVSEA Dwg 6213982 NAVSEA Dwg 6213983 NAVSEA Dwg 6213987 NAVSEA Dwg 6214071 NAVSEA OD 44979 NAVSEA OD 46574 NAVSEA OD 48845 NAVSEA OD 48854 NAVSEA OP 2239 NAVSEA OP 3206 NAVSEA OP 3221 NAVSEA OP 3347 NAVSEA OP 3565 NAVSEA OP 4 NAVSEA OP 5 Vol I NAVSEA OR 99 Series NAVSEAINST 5511 28 NAVSEAINST 8020 9 NAVSEAINST 8020 13 27 MARCH 2009 CHAPTER 1 TITLE Truckload Guided Missile UGM 109 2 TOMAHAWK CLS in Shipping and Storage Skid Mk 30 Mods 0 1 and 2 Truckload Guided Missile RGM 109 TOMAHAWK in VLS Canister Mk 14 Mo
139. W820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 actions to be taken to resolve any problems associated with the specific Inspection Point The Check Off column allows monitoring the Inspection Table status Three terms are used in the Action column Repair Replace and Reject In the cases of Repair or Replace the prescribed action applies to the Inspection Point only not to the higher assembly For TOMAHAWK AUR processing Reject indicates the Inspection Point discrepancy is neither replaceable nor repairable at the IMA level The Reject action flows up and results in rejecting the AUR unless a waiver is requested and approved Repair indicates the Inspection Point discrepancy can and should be repaired at the IMA level in accordance with procedures contained in SW820 AP MMI 030 or other applicable documentation Replace indicates the Inspection Point discrepancy is a replaceable component at the IMA level however the component is not repairable at the IMA 1 8 3 4 Standard Inspection Procedures The SIPs can be reproduced and used and or retained by QA personnel as records and check sheets They contain each and every IP step from the referenced OP rephrased for QA requirements Warnings cautions notes figures and tables are not repeated in the SIP 1 8 3 5 Supervisors The responsibility of the supervisor 15 to define handling team roles and operational requirements based on appropriate local directives and controls team a
140. XERCISE AUR 109 1 w NTIK amp Inert Warhead JUGM 109A 1w QAST JUGM 109C 1 M JUGM 109C 1 S W JUGM 109D 1 S W TRAINING CERTIFICATION VARIANTS AND CAPSULES TOMAHAWK TEST MISSILE TOTEM UTM 109 1 ENCAPSULATED NL TOTEM COMMERCIAL OFF THE SHELF COTS TOTEM ENCAPSULATED PVTV TOTEM CREW TRAINING SHAPE CTS UTM 109 1A WARHEAD INSTALLATION TRAINER WIT MK 35 0 w W80 WARHEAD INSTALLATION TRAINER WIT MK 35 0 w o W80 TOMAHAWK FITMENT SHAPE TOMFISH MK 1 0 CAPSULE MK 1 0 empty w nose and slot covers CAPSULE MK 1 0 empty w o nose and slot covers CAPSULE 3 0 empty w nose and slot covers CAPSULE 3 0 empty w o nose and slot covers 159 APPROXIMATE FWD MEASUREMENT IN FROM CAPSULE CG 10 0 2 5 12 0 11 5 10 6 10 0 11 5 10 5 11 5 7 5 7 5 7 5 20 6 0 9 5 3 5 0 0 0 0 5 0 0 0 2 39 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 APPROXIMATE FWD MEASUREMENT IN ITEM FROM CAPSULE CG TOTEM CAPSULE empty w nose and slot covers 0 0 TOTEM CAPSULE empty w o nose and slot covers 3 5 WIT CAPSULE empty w nose and slot covers 7 0 WIT CAPSULE empty w o nose and slot covers 2 5 Measure from center of capsule CG stripe AUR CG calculation is for AUR configured with Mk 111 Rocket Motor aluminum nose cover and slot covers installed Add up to 1 0 inch to measurement for variants with Mk 106 Mod 0 Rocket Motor Subtract 0 5 inch from measurement with ligh
141. aboard the submarine These interfaces include missile capsule and missile tube physical interfaces as well as the submarine systems utilized to a Maintain pressure in TCMs during stowage and preparation for launch b Operate missile tubes c Compute TCM attack solutions 3 14 CLS UNIQUE ELECTRICAL INTERRELATIONSHIPS In addition to common electrical interrelationships between the submarine combat system and the TCM discussed in Section II the CLS has unique requirements for pre launch electrical power in order to receive commands and provide responses to those commands Unique power requirements commands and responses for CLS TCMs are discussed in the following paragraphs 3 14 1 CLS Unique Prelaunch Electrical Power Requirements CLS unique pre launch electrical power requirements are a CLS Regulator Power Supplies power to the CLS regulator which in turn provides power to CLS components b CLS Converter Power Supplies power to the CLS Firing Unit Converter c CLS Monitor Power Supplies power to monitor discrete events from CLS prelaunch and launch sensors d CLS Power Return Provides the return path for CLS Regulator Power CLS Converter Power and CLS Monitor Power e Liquid Detector Power Supplies power to the CLS liquid detector f Coded Charge Signal Excitation Initiates dc power to allow the Coded Charge Signal to charge the CLS firing capacitor g Coded Launch Signal Excitation Initiates dc power to allow the
142. ace of the capsule The lateral support group has thirteen rows of elastomeric liner pads There are four separate liner pads in each circumferential row Each liner pad consists of an inner and outer wall jointed by chevron shaped struts Teflon is bonded to the inside surface of each pad to reduce friction against the missile surface Dual plateau pads with a corrugated inside surface are incorporated into the lateral support group to further reduce friction during encapsulation and decapsulation of the missile and during launch The design of the elastomeric pads provides necessary lateral support and protects the missile from shock and vibration In this function the lateral support group acts in concert with the interface support pads which are bonded to the exterior of the capsule and capsule extension The lateral support group also serves to provide guidance for the missile during launch 1 23 2 4 Launch Seals There are six circumferential launch seals adjacent to the bands of liner pads which are bonded to the inner surface of the capsule The seals have a projecting lip which bears against the surface of the missile The surface of the seal lip which contacts the missile surface is coated with Teflon to minimize friction Also the Teflon coating eliminates seal lip inversion Seal lip inversion may result from upward forces acting upon lip from launch gas pressure under the lip and from missile motion against the lip During launch the l
143. actions taken by equipment operators and typical equipment operations status displays and machine decisions The operational sequence is described in the following paragraphs For a full discussion of operating procedures as well as actions to be taken under abnormal conditions refer to SW261 DE MMO 030 231 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 4 18 1 Prelaunch Reprogramming Before Intent to Launch is signalled the TWCS can identify and reprogram land attack Block III TCMs During the reprogramming process TWCS issues a READY ALERT request to the VLS issues a non launch select order and applies power to the missile in the selected cell The TWCS downloads mission information and updates DSMAC and GPSS Flight Software When download is complete the missile is deselected power is removed and the TWCS orders the VLS to STANDBY 4 18 2 Missile Selection Missile selection is controlled by the MISSILE SELECT ORDER issued by the TWCS The TWCS may select a specific missile by launcher module and cell WCS MISSILE SELECTOR ORDER or the TWCS may designate a type missile and allow the VLS to select the specific TCM to be launched VLS MISSILE SELECT ORDER Upon receipt of the VLS MISSILE SELECT ORDER the VLS selects the cell to be used for launch based on the following a cell selected must have the least number of launches of those TCMs available b The TCM must be in a module or half module which contains the most
144. ading button Upon order to load tube the loadline rollers are raised and ramming is commenced The capsule nose cover and lashing straps are removed as they clear the forward loadline rollers Ramming is continued until the capsule forward guide stud contacts the tube stop bolt The stop bolt is then rotated to the LOCK position On a UGM 109A C D 1 the capsule latch pins are pulled to allow the capsule latches to extend and engage the slots in the aft land of the torpedo tube On a UGM 109E 1 the retention fixture is installed in the torpedo tube and secured to the capsule The loading pole 15 removed Two shipping nuts are then removed from the missile holdback assemblies 4 5 1 2 After verifying STOP BOLT LOCKED indication covers are removed and the electrical umbilical is connected between the breech door Y connector and the missile and secured to the inside of breech door The pneumatic umbilical is connected between the breech door penetrator 207 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 and the capsule and secured to the eyebolt on the inside of the breech door The breech door is shut and locked 4 5 2 Weapon Power Up and Make Ready Weapon power up and make ready is initiated by the weapon control console WCC operator in the attack center The WCC operator activates switches to select Land Attack TOMAHAWK mode Land Attack TOMAHAWK Preset Submode and the designated torpedo tube to be used for launch These selections per
145. aint gas generation system umbilical cable connection temperature control humidity control and storage Each SCS provides the Mk 82 digital data link for all command and response message traffic to from the AUR Each SCS also provides power discrete and analog signals to the AUR via the capsule wiring harness that connects to the side of the Mk 45 capsule All commands power application data loads and status requests to the missile are applied by submarine class SCS Once in flight the Block IV TACTOM missile is capable of receiving various directions flex command re targeting BDI request H amp S requests via the use of In Flight Mission Modification Messages transmitted by the Strike Controller via the TOMAHAWK Strike Network TSN It is also capable of acquiring and receiving GPS information directly from the GPS satellite constellation 224 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 4 14 4 TOMAHAWK Strike Network In Flight Communications The TOMAHAWK Strike Network TSN is used to link communications between a Block TACTOM with a strike controller or missile controller during flight The missile sends health and status H amp S messages and receives commands from the controller to modify mission outcome or communication parameters Messages are transmitted via UHF Satellite Communications on 5 KHz and 25 KHz UHF Demand Assigned Multiple Access DAMA channels Message Types From Block IV TACTOM Mi
146. al manual products Technical manual user activities may designate additional steps as Inspection Points to support local safety production management quality assurance or administrative processes as prescribed by local command activity policies and procedures 1 8 4 2 QA Functions and Responsibilities Responsibility for quality and safety 15 not restricted to QA and safety organizations but extends to every person The worker s task assignment is to perform all operations in order displayed or as directed by the supervisor and to honor all IP hold points Verification of significant operations at IP stop points should be performed by personnel qualified and designated by the command QA program 1 8 4 3 IP Stop Points IP stop points are located at the highest level of assembly possible which will allow inspections to be performed These points are preceded by banners IP STOP in the body of the steps Check off lines for affected steps are marked with at the end of the line These indications require QA witness approve signature stamp verbal approval before production personnel may continue The assembler will notify the QA representative whenever such notations are encountered in the course of an operation Upon QA approval of a marked step production will continue with the next step QA representatives will follow the operations by using SIPs and OPs when necessary 1 8 5 Reference Documentation Table 1 3 Reference Document
147. alignment completion During Mode 5 the platform is slued 90 from its previous orientation by torquing the vertical gyro Mode 6 performs the second fine alignment phase and duplicates the Mode 4 alignment Upon passing of mode completion tests the alignment process advances to Mode 7 Mode 7 is used only to indicate that alignment complete tests have been passed The computer program continues to perform the Mode 6 alignment until the CMGS is commanded to terminate alignment When this occurs the computer program advances to Mode 8 Mode 8 signals that the CMGS has terminated alignment and it has become an independent navigator 203 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 4 OPERATIONS 1 4 1 5 This chapter discusses TWS operations aboard various types of launch platforms These discussions include brief descriptions of the launch platforms and on board equipment used to load store and launch weapons typical weapon onload scenarios and typical launch operations Section II discusses TTL launch platforms procedures and operations Section III discusses CLS launch platforms procedures and operations Section IV discusses VLS launch platforms procedures and operations 204 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 SECTION TORPEDO TUBE LAUNCH 4 2 LAUNCH PLATFORMS The TTL TWS is employed aboard SSN 688 SSN 774 and SSN 21 Class submarines TCM l
148. als The antenna is made using multi layer micro strip technology and comprised of five crossed slot elements with integrated frequency selective surface design 1 11 4 3 4 Anti Jam Global Positioning System Receiver AGR The AGR is used to assist in directing the missile to the intended target It is a single channel sequencing dual frequency P Y Code Military GPS Receiver with high anti jam capability The AGR has nulling and beam steering processing using a five element antenna to distinguish the GPS signals from various jamming sources The AGR provides line of sight measurements position velocity and time to aid the Navigation Processor 1 11 4 3 5 Cruise Missile Airframe CMA Battery The CMA Battery provides missile electrical power during mission boost It is a pyro activated lithium thermal battery The pyro activates iron potassium perchlorate heat pellets and melts the ternary electrolyte This process provides an electrical path between the lithium silicon anode and iron disulfide cathode Within 31 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 the battery are two independent cell stacks to power missile CM regulated and unregulated busses The CMA Battery outputs DC power to the PFU before distribution to missile components 1 11 4 3 6 Digital Scene Matching Area Correlator Processor Subsystem The Digital Scene Matching Area Correlator DSMAC Processor Subsystem is part of the DSMAC IV System which also includ
149. ameter Canister components are described in the following paragraphs 1 29 1 1 Canister Fly Through Cover Assembly The canister fly through cover assembly measures about 22 85 inches in diameter and about 0 18 inch thick The assembly consists of eight frangible segments and a flange and attaches to the canister barrel with 36 bolts 1 29 1 2 Canister Barrel The canister barrel is a seamless aluminum tube measuring 247 35 inches long and 21 2 inches in diameter The barrel provides environmental and physical protection for the missile and rocket motor and serves as the launch tube 1 29 1 3 Canister Baseplate Assembly The canister baseplate is machined aluminum alloy plate measuring 21 2 inches in diameter It supports the cable and conduit assembly and its associated connector a nitrogen servicing pneumatic quick disconnect coupling and the umbilical adapter It also contains three rupture disks for thrust augmentation and for the exit of rocket motor exhaust Two loading bracket assemblies can be mounted on the baseplate for alignment of the canister 1 29 2 Mk 14 Mod 1 Mod 2 Canister The Mk 14 Mod 1 and Mod 2 Canisters Figure 1 35 Mk 14 Canister 2 Sheets are thermally lined rectangular shells with 16 lateral supports to allow longitudinal movement of the encanistered TCM for shock isolation The canisters provide environmental protection and structural and alignment support for the encanistered TCM as well as a mounting pla
150. and five tie down rings on each side of the lower shell are used for lifting and tie down The container has integral skids having fittings for use with forklifts Also built into the container are fork pockets and hoisting fittings Small non steerable retractable wheels on the aft end of the container permit limited fore and aft movement An access door on the container aft end permits activities to check for fuel leaks and gain access to the record book The empty container weighs 1709 pounds Container dimensions are provided in Table 1 8 Container Weights and Dimensions 1 20 RECORD BOOKS 46 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 1 20 1 PEO W 4440 Record Book for Tomahawk Cruise Missile PEO W 4440 is utilized to maintain data for tactical and exercise TTL AURs PEO W PUB 4440 is also utilized to maintain data for the Crew Training Shape and Warhead Installation Trainer Mk 35 Mod 0 Instructions for use forms completion and disposition are contained in PEO W INST 4440 2 and the record book 1 20 2 CMP PUB 4440 2 Record Book for TOMAHAWK Test Missile TOTEM PUB 4440 2 is a tailored version of PEO W PUB 4440 that is used to record data pertinent to launchable and non launchable Instructions for use forms completion and disposition are contained in the record book 1 21 WEIGHTS AND CENTERS OF GRAVITY Weights and centers of gravity of TTL variants and related material are co
151. anical Equipment Missile Tube Control and Indication Equipment Weapons Launch Console Transportation and Storage Data for Ammunition Explosives and Related Hazardous Materials Navy Transportation Safety Handbook for Ammunition Explosives and Related Hazardous Materials TOMAHAWK Weapon System Mk 36 and Mk 37 Block TOMAHAWK Weapon System Mk 37 Block IIT Round Electronic Simulator AURES Mk 101 AURES User Manual All Up Round Electronic Simulator AURES Mk 101 Mod 4 AURES User Manual Users Manual For All Up Round Electronic Simulator AURES Mk 112 VLS Systems Manual CCS Mk 1 Mod 0 General Information Manual CCS Mk 1 Mod 0 2 Description Operation and Maintenance SSN 688 Class Vertical Launch System Mk 41 129 SW820 AP MMI 010 REVISION 15 DOCUMENT NUMBER SW394 AG MMA 010 SW394 EE PRO 010 SW395 AA IFM 010 SWIM 010 060 SW820 AA WHM 010 UGM 109 1 SW820 AD WHS 010 UGM 109 2 SW820 AD WHS 030 UGM RGM 109 SW820 AF OMP 010 TOMAHAWK EQUIP SW820 AF OMP 020 VLS SSN SUPP EQUIP SW820 AP MMI 010 SW820 AP MMI 020 SW820 AP MMI 030 SW820 AP MMI 040 SW850 D9 PRO 010 REM MSL RECOVERY SW850 EA MMM 010 SW850 EA MMM 020 CTS SW850 EA MMM 050 EMPLOYMENT 27 MARCH 2009 CHAPTER 1 TITLE Description Operation Installation and Maintenance Instructions for AUR Simulator Vertical Launching System VLS Canister Dockside Handling Procedures Submarine To
152. anner Tighten CLS AUR and CLS Loading P N JCM 17635 and Handling Training Shape umbilical cable connector P130B Wrench Canister Loosen and tighten separation nut Separation Nut Lockring lockring during Mk 10 encanisterization P N 7674738 1 and decanisterization Wrench Spanner Tighten CLS AUR and CLS Loading P N JCM 17635 and Handling Training Shape umbilical cable connector P130B 121 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 EQUIPMENT Wrench Spanner P N 76M0235 1 Wrench Spanner Nose Coupler KMU 467 E P N 7673553 8 FUNCTION Remove install positive retention nose cone during 109A warheading and dewarheading Remove install positive retention nose cone during 109A warheading and dewarheading 122 ILLUSTRATION eom odio 2 r 7 ii lo SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Table 1 2 Shipboard Equipment Used for EQUIPMENT Adapter Dolly P N SK5711 735 Chocks Portable Stowage Rack P N SK5111 738 Decking Small Boat LCM Mk 6 Dolly Stowage Rack Plenum Cell Cover Assembly Sill Assembly TOMAHAWK Support FUNCTION Adapt tender stowage rack dollies to support TTL weapons Adapt stowage rack for TTL stowage on board AS 39 Class submarine tenders Provide a platform to secure weapons in LCM Mk 6 Consists of four deck sections secured together with iron bolts and angle irons Stow TTL weapons on AS 39 Class
153. aps used to maintain the missile on flight path to the target Correlation and position updating parameters include the latitude and longitude of map center map heading centerline length width cell size altitude data and estimated fix accuracy Although maps may overlap the data for each map are stored separately for software efficiency Predetermined waypoints define specific latitude and longitude intersections along the flight path to the target Enroute to target TERCOM is updated upon reaching each waypoint Since distance traveled is measured from the last waypoint not total distance flown terminal accuracy is very high TERCOM is also relatively insensitive to weather season and ground cover 1 13 3 Digital Scene Matching Area Correlation DSMAC Stored digitized images or scenes are used by the 109 109D and Block TACTOM to perform terminal updates A sensor in the DSMAC set takes a visible wavelength image of ground features digitizes the images and compares them with the stored digitized images Since the DSMAC scenes are smaller and contain more detail than TERCOM maps they result in more accurate position updates With Block IV TACTOM DSMAC images of pre planned locations can be obtained and transmitted as part of midcourse Health and Status messages for use as Battle Damage Indication Imagery BDI 1 13 4 Global Positioning System Subsystem GPSS A GPSS is used by 109C 109D and Block IV TACTOM to p
154. asses with side shields for cleanup personnel d Full face respirators for cleanup personnel e Positive pressure self contained breathing apparatus for firefighting personnel 2 3 4 4 Waste materials should be collected with a vacuum cleaner equipped with High Efficiency Particulate Air HEPA filter elements Waste materials should be packaged in polyethylene plastic bags If sheeting or bags are not available fibers shall be contained using an acrylic floor wax 1 e Wax Floor Water Emulsion P W 155C Affected areas shall be decontaminated by washing down and or vacuuming Local solid waste disposal authorities shall be consulted for approved burial sites techniques for composites or composite contaminated materials Local cognizant industrial hygienist or medical department representative shall be consulted for detailed health hazard control guidance based upon extent of exposure 2 3 5 CLS Post Launch Waste Water CLS post launch waste water has a lead Pb concentration consistently averaging between 5 to 10 milligrams per liter mg l particle setting may cause concentrations to range from 1 to 5 mg l at the top and 10 to 30 mg l at the bottom of the capsule and cyanide concentration consistently between 20 to 25 mg l Because Environmental Protection Agency regulations identify lead concentrations equal to or greater than 5 mg l and cyanide in any amount as hazardous CLS post launch waste water is considered hazardous waste HW The int
155. at System Technical Operator Manual CG 59 thru CG 64 Combat System Technical Operator Manual CG 52 thru CG 55 Combat System Technical Operator Manual CG 56 thru CG 58 Combat System Technical Operator Manual for DDG 51 Class Ship Systems Manual for SSN 688 Class Product Quality Deficiency Report Program 128 SW820 AP MMI 010 REVISION 15 DOCUMENT NUMBER SECNAVINST 5000 2 50420 010 50420 010 SG420 BU MMA 050 SG420 C9 MME 010 SG420 CC MME 010 SG420 DG IEM 090 SG420 DG IEM 100 SG420 DG IEM 120 SG420 DG IEM 130 SW020 AC SAF 010 020 030 SW020 AG SAF 010 SW260 DE MMO 000 SW261 PB MMO 000 SW279 AC OMP 010 SW279 AC OMP 020 SW279 AD URM 010 SW281 DO MMM 010 thru 050 SW282 B4 GTP 010 SW282 B4 MMO 010 thru 050 C CCS Mk 1 SW394 AF MMO 010 thru 050 27 MARCH 2009 CHAPTER 1 TITLE Implementation of Defense Acquisition Management Policies Procedures Documentation and Reports NAVSEA Periodic Testing Arrangements for Ordnance Handling Equipment Lift System Strikedown CG 47 Class Ship NAVSEA SSN 688 Class Weapon Delivery System Equipment Manual Volume 5 Vertical Launch System Operation and Maintenance Instruction with Parts List Intermediate and Depot Maintenance Levels Virginia Class Vertical Launch System VLS Loading Platform Vertical Launch System Loading Platform Introduction to Vertical Launch System Mechanical Equipment Vertical Launch System Mech
156. ata block The last word in the data block is a checksum 2 s complement addition of the control word and all following data words Information transferred over the digital data link includes the operational flight program platform alignment data missile status command sequences and mission data land attack The digital data lines used for communication are a DATA ENABLE Lines used to send the DATA ENABLE command a discrete signal to permit the RMUC to accept and transmit data b CLOCK Lines used to send timing signals to synchronize commands and data c DATA UPLINK Lines used to transmit digital data sent to the RMUC d DATA DOWNLINK Lines used to transmit digital data from the RMUC e SHIELD CARRY THROUGH Line used to provide shield continuity on wires carrying digital data The shield is floated at the launch platform and grounded in the missile f DIGITAL I O POWER SUPPLY RETURN Line used to provide a common ground reference for digital input output power to the I O channel power supply and the CMGS 3 4 DIGITAL COMMANDS DATA BLOCKS SENT TO A LAND ATTACK TCM Digital commands and data blocks sent to a land attack TCM over the digital data link discussed in paragraph 3 3 gt are described in the following paragraphs Commands unique to a CLS TCM are discussed in Section IV 3 41 Bootstrap Load Program A BOOTSTRAP LOAD program permits the loading of programs into the RMUC When REPROGRAM discrete is rece
157. ated Parts Breakdown Insulation Resistance Test Unit In Service Engineering Agent Intent to Launch Insensitive Warhead Extended Range Joint Reporting Structure Joint Test Assembly Kilobyte Kilowatt Land Attack Launch Control Group Landing Craft Mechanized Landing Craft Utility Launch Control Unit Launch Capable Flight Software Limited Life Component Exchange Low temperature Logistics Logistics Airlift Low Pressure Launch Sequencer Launch Test Payload Military Airlift Command Multiple All Up Round Canister 138 SW820 AP MMI 010 REVISION 15 ABBREVIATION ACRONYM MCE MCIO MCM MCP MDD MDS MEASURE METRL MIC MIL SPEC MIL STD MILSTAMP MILSTRIP MIP MIS Mk Mod MON MRA MRC MRSS MS MSA MSD MSDDC MSDS MSEM MSL MTB 27 MARCH 2009 CHAPTER 1 DEFINITION Maximum Credible Event Mission Control Input Output Mission Control Module Mission Control Processor Maintenance Due Date Missile Designator Series Metrology Automated System for Uniform Recall and Reporting Metrology Requirements List Missile Interface Console Military Specification Military Standard Military Standard Transportation and Movement Procedures Military Standard Requisitioning and Issue Procedures Maintenance Index Page Missile Identification System Mark Model Modification Monitor Missile Radar Altimeter Maintenance Requirements Card Midbody Range Safety Subsystem Military Specification Mine Safe
158. ation 3 2 1 4 Monitor Reset Power A dc monitor reset voltage is applied to the DC MONITOR RESET POWER bus The DC MONITOR RESET POWER bus powers the submarine launch TCM dual differential pressure transducer the WARHEAD DEADFACE relay 109A and the rocket motor safe arm monitoring circuits The bus also supplies power to energize the POWER BUS CONTROL relay and connects the ac dc converter output to the missile REGULATED bus It supplies power to energize the FIRST MOTION relay via the first motion loop to generate the MISSILE ENABLED mark that is sent prior to missile launch 3 2 1 5 DC Monitor Reset Power Return The DC MONITOR RESET POWER RETURN provides the return leg back for dc monitor reset power 3 2 1 6 Chassis Static Ground A copper ground path is provided to assure that the launch platform and missile are at the same ground potential 3 2 2 Launch Boost Electrical Power Launch boost electrical power is supplied by two remotely activated thermal batteries One battery located in the missile midbody is the CMA battery The second battery is the BPU located in the CMGS 109C D A REM equipped TCM 183 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 3 also has two electrically activated REM batteries The CMA and CMGS batteries supply short duration power about 30 seconds to power the TCM until the engine driven generator regulator can take over The REM batteries power REM subsystems and once activated last about 15 hou
159. ation provides a consolidated list of TWS unique documentation as well as directives instructions and technical and general reference documents applicable to the TWS 1 8 6 Abbreviations and Acronyms Table 1 4 Abbreviations and Acronyms provides a consolidated list of abbreviations and acronyms applicable to the TWS 1 9 REPORTS Table 1 5 Summary of Reports provides a consolidated list of reports applicable to the TWS Requirements for report submission are contained in the applicable submarine and surface ship User s Operational Logistics Support Summary 25 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 SECTION TOMAHAWK CRUISE MISSILE 1 10 GENERAL This section provides a physical description of tactical and exercise TCM variants and presents a typical mission profile for each variant 1 11 TACTICAL VARIANTS The following paragraphs describe the sections and components that make up tactical TCM variants Table 1 6 Common Descriptive Data provides data common to multiple TCM variants Table 1 7 Variant Unique Descriptive Data provides variant unique data common to multiple launch configurations 1 11 1 Land Attack 109A The land attack 109A Figure 1 1 Land Attack 109 gt is long range missile which carries a non conventional W80 Warhead with guidance provided by Terrain Contour Matching TERCOM techniques The missile measures 243 33 inches long by 20 375 inches in diameter The miss
160. aunch operations are performed utilizing equipment located in the Attack Center Combat Systems Electronic Space CSES and Torpedo Room General locations of the complexes are shown in Figure 4 1 General Locations of SSN Complexes The following paragraphs describe major TWS related TTL systems aboard submarine A simplified interface block diagram of submarine TWS related equipment is shown in Figure 4 2 SSN TWS related Equipment TTL Interfaces 4 2 1 Submarine Combat System Submarine Combat Systems SCS include Combat Control System CCS and the AN BSY 1 Combat Control Acoustic Set CC A SSN 688 Class submarines may employ either the CCS or CC A Each SCS supported by the ownship navigation system CSES Over the Horizon OTH targeting and the appropriate software programs provides the necessary power discretes and data to power up weapons transmit orders process and display data initialize and align the missile guidance set and initiate weapons launch Also included are control and monitoring circuits as well as various firing interlocks 4 2 2 Combat Systems Electronic Space CSES The CSES equipment is shared by both the SCS and the navigation system Computer software programs which include the operational flight program preplanned land attack mission targeting data generated at a shore based Theater Mission Planning System TMPS installation and provided to the submarine prior to deployment platform
161. aunch seals minimize gas pressure buildup in the space between the capsule inner wall and the missile skin The seals also enhance eject performance by minimizing gas 53 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 leakage from the volume pressurized by the gas generator By reducing asymmetric pressure forces during the in tube cell travel of the missile the seals serve to reduce launch vibrations Holes spaced around the circumference of the seal lip allow air to flow between the compartments during capsule pressurization 1 23 2 5 Separation Nuts Two separation nuts attach to two hold down studs on the missile aft end to position the missile before launch and secure the missile to the VSA Each separation nut has two explosive initiators which when fired just prior to missile launch cause the nut to separate from the hold down stud thus permitting missile egress 1 23 2 6 Vertical Support Assembly VSA The VSA consists of a vertical shock and vibration mitigation device a metal bellows anti rotation device two missile retention devices a gas generator gas deflector two missile away switches and a capsule extension The VSA mitigates shock and vibration to the missile in the axial direction positions the missile vertically and azimuthally in the capsule provides a flow path for gases from the gas generator to the missile during launch and provides for mounting electrical control components 1 23 2 7 Capsule Extension The
162. briefly described in the following paragraphs Post launch operations are preformed in accordance with NAVSEA OD 44979 4 6 1 Tube Reset If the WLC indicator continues to show TUBE FIRED at the completion of missile launch the WLC operator takes action to reset the tube and close the outer door 4 6 2 Capsule Ejection UGM 109A C D 1 When ordered to eject capsule the WLC operator positions the missile interrupter switch to MANUAL and the tube stop to LOCK The WLC operator then activates the switch to route ship 700 psi air to the capsule Upon application of air pressure the capsule sleeve moves forward unlocking the capsule latches Continued movement of the capsule sleeve retracts the capsule latches and closes the flow slots With the closing of the flow slots the weapon supply switch on the WLC is turned to OFF UGM 109E 1 When ordered to eject capsule the WLC operator shall unload the capsule from the torpedo tube in accordance with NAVSEA OD 44979 The capsule nose cover shall be re installed The AUR will then be loaded back into the torpedo tube 4 6 2 1 When ordered the ACC operator orders OPEN DOOR Responding to the order the WLC operator opens the muzzle door WLC and ACC indicators advise the operators that the tube is ready to eject the capsule On order the tube is fired and the capsule ejected If indicators show that the tube did not fire operators refer to NAVSEA OD 44979 for further guidance 4 6 2 2 Upon receipt o
163. carried The All Up Round Ballast Grade B AURBb is a ballast can which may be carried in cells during SSGN deployment 1 24 4 Missile Tube Bore Gage The Missile Tube Bore Gage is a cast iron facsimile of the CLS AUR that 15 used to verify the proper missile tube clear bore to ensure compatibility with the AUR 1 25 CLS SHIPPING CONTAINERS Reusable stackable shipping containers have been designed to provide protection for the CLS AUR AUR Simulator and empty CLS during handling storage and transportation The basic design functions of the containers are to a Attenuate shock and vibration b Permit handling by forklift handlift truck or sling crane arrangement c Provide a means to stack containers during transport or storage 1 25 1 Shipping and Storage Skid Mk 30 The Shipping and Storage Skid Mk 30 Figure 1 32 Shipping and Storage Skid Mk 30 gt is used to handle store and transport CLS tactical and exercise AURs and to handle and transport CLS Loading and Handling Trainers and spent CLSs The skid is also used for loading CLS weapons aboard submarines and may also be used to perform weapon maintenance by installing the Uprighting Fixture Mk 26 and Forward Support Mk 167 in the skid The main body of the skid is constructed of aluminum and consists of an inner frame assembly saddles restraint straps lifting eyes and forklift slots Lightweight plastic 56 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER
164. ch enable functions within the launcher when the CONTROL key switch is set to REMOTE 4 15 55 TOMAHAWK Weapon Control System TWCS The TWCS is a general purpose computer system that receives track and target data from weapon and sensor systems from own and other ships Targets are selected by operators for engagement by the VLS Missile select commands target related data and launch commands are transmitted to the VLS for launch control The VLS provides the TWCS with missile inventory and equipment availability status The TWCS is comprised of two functional groups Track Control Group and Launch Control Group 4 15 5 1 Track Control Group TCG The TCG performs targeting and track data processing threat evaluation and weapon assignments using an Operator Interactive Display Terminal and TCG Preprocessor Control Center Data Processor Control Center and Data Storage Control Center equipment 4 15 5 2 Launch Control Group LCG The LCG receives engagement plans and launch orders from the TCG to prepare control evaluate and launch TCMs using Operator Interactive Display Terminals and LCG Data Processor Control Center and Data Storage Control Center equipment The LCG also provides direct interface with LCU data processors 4 16 ONLOAD OFFLOAD AND CROSSDECK WEAPONS This paragraph provides general information regarding preparation for and onload and offload of weapons as well as offload of a spent canister Technical manual SW394 EE PRO 0
165. ciated with TWS operations and support describes TOMAHAWK Cruise Missile TCM mission profiles from prelaunch to target engagement and provides TWS reference data Section I of this chapter provides an outline of this document s organization and content Section II provides an overview of the TWS to include a discussion of the TWS mission TCM AII Up Round support equipment and documentation and documentation terminology Section III provides a description of the TCM without regard to launch configuration and discusses targeting and the typical missile profile for each TCM variant Section IV discusses the submarine Torpedo Tube Launch TTL launch configuration and provides information and data unique to the TTL system Section V discusses the submarine Capsule Launching System CLS launch configuration and provides information and data unique to CLS Section VI discusses the surface Vertical Launching System VLS launch configuration and provides information and data unique to VLS 1 1 2 Chapter 2 Chapter 2 discusses TWS security and safety requirements regulations and general policies relating thereto 1 1 3 Chapter 3 Chapter 3 discusses functional descriptions of TWS components and interfaces between the TCM and its launch platforms Section I provides an outline of the organization and content of the chapter Section II discusses the TCM electrical power system and type commands and requests for status issued to the TCM and TCM respon
166. continuously monitors missile functions and sends a failure message to the LCU if monitor functions change to an improper condition 4 18 5 Select Response Evaluation If the LCU receives the select response message prior to the end of the 650 ms delay the LCU starts an 80 second clock and updates the missile availability file This delay is used to ensure that the TWCS remains in communication with the LCU throughout the launch sequence The 80 second delay is reset each time a valid message pertaining to the selected missile 15 received from the TWCS If 80 seconds pass without receiving a message the LCU sends an equipment failure status message and commences the cell safing procedure 232 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 4 18 6 Mission Assignment The appropriate mission disk pack is removed from secure storage and mounted on the random access storage set RASS The disk pack serial number is entered and the RASS initialized With RASS initialized the TWCS is ready to transmit missile and alignment data messages to the missile via the LCU THEATER MPS MISSION and VERIFY codes are received from the appropriate authority and entered Mission data are then indicated and transferred to the central computer resident memory The operator enters the target number and the pre established waypoints to that target are displayed The operator reviews the mission data and approximate flight path to the target and makes route alterat
167. ctions acknowledges all verbal statements of completion from the team members 1 8 3 6 Readers The responsibility of the reader is to ensure the procedure has been verified fj read aloud all warnings cautions and notes as they occur read aloud the complete step verbatim observe the worker s performance as a double check to ensure proper execution of the step when physically possible In some situations it may be more efficient to have a second worker or observer perform this double check observation providing this individual reports satisfactory completion of the step and check off the step when it is completed it is considered completed when reports are received from all workers A verbal acknowledgement shall be made upon completion of each step Ensure all steps are performed in proper sequence and report completion of the procedure by appropriate checkoff in the PG completion of the certification form or by continuation to the next procedure 1 8 3 7 Workers The responsibility of the worker is to verbally acknowledge all warnings cautions and notes after they are read perform step report completion of step using the standard term check 1 8 3 8 Observers The responsibility of the observer is the same as that of the worker except that observer observes step instead of performing step 1 8 4 Quality Assurance QA Within procedural documents certain OPs have procedural check o
168. d and Drain System The flood and drain system Figure 4 13 SSN 688 Class Submarine Flood and Drain System floods and equalizes the missile tube underhatch volume to sea pressure so hatch be opened drains underhatch volume to remove water and allows this volume to be maintained at submarine internal ambient pressure 4 8 4 5 Missile Tube Control System The missile tube control system Figure 4 14 SSN 688 Class Submarine Missile Tube Control System contains the controls indicators and interlock circuitry necessary to ready missile tubes for launch and to monitor missile tube operation The system also provides all of the interfaces between the ship systems and the SCS 4 9 ONLOAD AND OFFLOAD The following paragraphs provide general information regarding preparation for and onload and offload of weapons as well as offload of a spent CLS Various volumes of NAVSEA OD 44979 contain specific procedures to be used by SSN personnel Technical manual SW820 AD WHS 010 UGM 109 2 contains specific procedures for submarine tender and shore based personnel supporting SSNs For SSGN Class procedures refer to NAVSEA OD 64501 and SW820 AD WHS 040 UGM 109 2 4 9 1 Onload Submarine onload begins when the submarine arrives at a designated shore base activity or supporting submarine tender to receive a complement of weapons Wind and sea motion which affect the submarine s position and movement are factors in determini
169. d elastomer loading guard pads as well as the upper flange grooves are greased to facilitate loading the weapon into the missile tube The forward section of the weapon is depressurized and the Closure Protective Cover CPC is replaced with the Capsule Loading Cover CLC The annular space vent plug is removed and stowed Two lip seals are then greased and carefully installed into the upper flange grooves The lifting adapter is then attached to upright the weapon to the vertical position 4 9 1 4 Load Weapon in Missile Tube The weapon is uprighted about the trunnions or trunnion bearing assemblies and lifted off the Mk 23 fixture Figure 4 34 Tilt Fixture Mk 23 Mod 0 with or uprighting skid Figure 4 17 CLS Weapon Onload The trunnions trunnion bearing assemblies are removed and weapon is lifted over the MTEL and aligned for insertion into the missile tube The MTEL safety cover is removed The weapon is lowered into the MTEL until the bellyband and the moisture and dust plug can be sequentially removed The MTEL centering guides are released to allow the flange to pass permitting the weapon to be lowered until the lifting adapter is above the bellmouth The lifting adapter arm is then pinned in the vertical position and the weapon is further lowered until the lifting adapter insertion pins rest the MTEL stop plates Figure 4 18 CLS Weapon Seating in Missile Tube Seating J the weapon in the missile tube is
170. d storage of explosives shall be observed at all times Personnel shall be familiar with the operating procedures and precautions necessary to prevent the spurious initiation of EEDs Areas containing explosives shall be clearly posted with the appropriate warning signs See NAVSEA OP 4 and OP 5 POST LAUNCH WASTE WATER DISPOSAL Removal of post launch waste water from expended capsules involves handling material which is not authorized for direct dumping into coastal or inland waters In many locations disposal of post launch waste water into shore sewage systems is prohibited Contact the local public works department and advise them of detailed disposal considerations to obtain guidance for waste water disposal SAFETY HARNESSES Personnel performing over the side operations or working in or around open hatches missile tubes shall wear safety harnesses with safety lines secured LITHIUM BATTERIES REM equipped TOMAHAWK missiles contain two lithium active battery packs one used to power the recovery beacon and one used to power a special instrumentation electronics package Lithium active batteries can become hazardous if the case is ruptured or the leads are shorted together causing the battery to discharge at a high rate Either situation can cause a violent chemical reaction the venting of potentially hazardous gasses including sulfur dioxide SO hydrochloric acid sulfuric acid 5 and sulfurous acid H SO and p
171. dified version of the Mod 1 configuration The new device accepts the new aft cover and allows for the redesigned umbilical and the umbilical cable clamp The revised aft fairing device will still work on the Mod 1 capsule 1 23 2 12 Instrumentation and Controls The only umbilical cable required for application use in the SSGN is located at the bottom of the MAC cell With the CLS AUR loaded into the MAC cell SSGN personnel remove the P1130 connector from the J1130 and install it in its stowage position The ship s umbilical is then installed in the J1130 Each AUR requires one of these umbilical cables seven umbilical cables for each fully loaded MAC These umbilical cables plug into the ship s control interface cable and to a connector located at the bottom of the AUR Three cables are installed within the capsule one cable from the missile one cable from the two separation nuts and one cable from the departure switches The three cables pass through the VSA and connect to three penetration connectors in the aft closure There are three additional cables on the aft side of the aft closure one cable connects the firing unit to the gas generator one cable connects the firing unit to the separation nuts and one cable connects the umbilical cable to the firing unit the missile cable the departure switches liquid sensors and the interconnecting box The AUR umbilical cables are not used on the SSGN for umbilical cable applications The umb
172. ds 0 and 1 Truckload Guided Missile RGM 109 TOMAHAWK in VLS Canister MK 14 Mods 0 and and Guided Missile U RGM 109 TOMAHAWK in Container CNU 308 E ISO Container Load Shipping and Storage Skid Mk 30 Mods TOMAHAWK in 40 Ft Full Height Open Top ISO Container Firing Craft Operating Procedures and Checklists Weapon and Combat Systems Quality Assurance Requirements for Shore Stations and Engineering Agents Metrology Requirements List Field Calibration Activity Metrology Requirements List Explosive Driver s Handbook Handling and Stowage of Naval Ordnance Aboard Ammunition Ships Loading and Stowage of Military Explosives Aboard Breakbulk Merchant Ships United States Navy Ordnance Safety Precautions Radio Frequency Hazards to Ordnance Personnel and Fuel Ammunition Afloat Ammunition and Explosives Ashore Regulations for Handling Storing Production Renovation and Shipping Intermediate and Depot Maintenance Instructions for Specified Handling and Support Equipment Guided Missiles Security Classification Guide Non Nuclear Ordnance and Explosive Handling Qualification and Certification Program Emergency Response Procedures for Transportation Accidents 126 SW820 AP MMI 010 REVISION 15 DOCUMENT NUMBER NAVSEAINST 8023 2 NAVSEAINST 4855 7 NAVSUP PUB 409 NAVSUP PUB 437 NAVSUP PUB 4500 NAVSUP PUB 485 NAVSUP PUB 505 NAVSUPINST 4400 189 NAVSUPINST 4423 14 NAVSUPINST 4440 120 NAVSUPINST 4600 70
173. e La D Qe 43 Toto 2 Capsule Mk3 Mog 0 43 1 16 21 Nose 43 1 16 2 2 Nese Diaphragm o bee Ores Suay ass 44 1162 3 Capsule Barrel ulat rb 44 1 16 2 4 Alignment and Retention Provisions 2 702 44 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 1 16 Bartel Fer tx eoa see Ee Inge edid 44 TANGOS OVEPS cos QT REX S aa 44 1 16 2 7 Protective P peo ust tec Et I 44 LIT UMBILICAL ASSEMDBLIES ot e ER aka A Rad 44 IET Electrical Umbilical ato oa ve eek Ox Roo TRE YA dd 45 TT 7 2 Pneumatic Umbilical vise ken IE eU Ua Quee un ue e ORA Ee dA 45 DAS INE RO VARIANTS 224 55 ias ie ide i Mapas as Susa 45 1 18 1 TOMAHAWK Test Missile TOTEM UTM 109 1 45 1 18 2 Encapsulated No Launch No Wet TOTEM NL TOTEM 45 1 18 3 Crew Training Shape CTS UTM 109 1A 2 45 1 18 4 Warhead Installation Trainer WIT Mk 35 Mod Q 45 1 18 5 TOMAHAWK Fitment Shape TOMFISH Mk 1 Mod 0 46 1 18 6 Commercial Off The Shelf TOMAHAWK Test Missile COTS TOTEM 46 1 18 7 Pressure Vent Test Vehicle TOMAHAWK Test Missile PVTV TOTEM 46 1 19 CNU 308 E SHIPPING
174. e TOTEM User s Logistics Support Summary ULSS for the TOMAHAWK Cruise Missile UGM 109 1 and TOMAHAWK Cruise Missile UGM 109 2 Integrated Logistics Support Plan ILSP for Sea Launched Cruise Missile SLCM TOMAHAWK All Up Round Advanced TOMAHAWK Weapon Control System AN SWG 4 V Launch Control Group Replacement TL4 Configuration VLS Mk 14 Canisters with TOMAHAWK Cruise Missiles at Intermediate Maintenance Activities and Limited Maintenance Activities Explosive Mishap Reporting Procedures Shipping 124 SW820 AP MMI 010 REVISION 15 DOCUMENT NUMBER Code of Federal Regulations Title 49 DOD Regulation 4500 32 R DOD STD 1686 ILSP 167 P D JCS PUB 6 VOL II Part 4 MD 4790 100 200 MD 55658 MD 56068 MIL STD 129 MIL STD 1320 235 MIL STD 1320 246 MIL STD 1320 264 MIL STD 1949 MIL STD 2000 MIL STD 410 MIL STD 6866 NAVAIR 19 15BC 13 NAVSEA Dwg 6213981 27 MARCH 2009 CHAPTER 1 TITLE Transportation Defense Transportation System Policies and Procedures Electrostatic Discharge Control Program for Protection of Electrical and Electronic Parts Assemblies and Equipment Excluding Electrically Initiated Explosive Devices Integrated Logistics Support Plan ILSP for Vertical Launching System Mk 41 Joint Reporting Structure JRS Volume II Joint Reports Part 4 Nuclear Weapons NUREP Shore Activity Maintenance Data Collection System Checkout Procedures and Inspection Requirements for
175. e RMUC A window for the DSMAC lens is provided on the bottom centerline along with a pyrotechnically jettisoned cover Shields protect the DSMAC set from electromagnetic interference EMI The illuminator assembly strobe which lights the scenes for night flights also mounts on the bottom centerline Two fuel lines run through the section for CMGS cooling A fuel tank is also provided 1 11 2 2 Forward Body Payload Section The forward body payload section extending from station 52 45 to station 99 80 houses the warhead the warhead fuze booster assembly and a pyrotechnically activated dual air valve to arm the warhead On WDU 36 B warhead configurations this section also houses the GPSS Antenna Module and additional fuel for extended flight Warhead support is provided by a series of adjustable wedges and bolts Two fuel tube assemblies run through the section for CMGS cooling Quick disconnect couplings at each end of the tube assemblies permit removal and installation of the payload section without having to defuel the missile For test and exercise flights involving Recovery Exercise Module REM equipped missiles the forward body payload section is replaced by a REM section 1 11 3 Land Attack 1090 The land attack 1090 Figure 1 5 Land Attack 1090 5 is a medium range missile armed with BLU 97 B combined effects bomblets with guidance provided by Terrain Contour Matching techniques and Digital Scene Matching Ar
176. e aft circumferential land and secures the capsule via an access hole on the barrel closure 1 16 2 5 Barrel Closure The barrel closure is a machined corrosion resistant steel plate 20 97 inches in diameter A loading button is installed in the center of the barrel closure to permit torpedo tube loading or unloading of the weapon The barrel closure provides access to the pressure transducer arrangement electrical umbilical connector two missile holdback assemblies retention fixture latch locking hole pneumatic umbilical connector and rocket motor pull switch lanyard attachment 1 16 2 6 Slot Covers Two universal slot covers are installed on the capsule One covers the forward capsule slots and another covers the aft capsule slots The slot covers prevent entry of foreign matter There are two straps on each slot cover for cover retention The covers must be removed prior to tube loading 1 16 2 7 Protective Covers The electrical access protective cover is on the starboard side of the barrel closure The pneumatic coupling protective cover is on the port side These two covers are also referred to as shipping covers Both covers provide protection to a separate missile holdback assembly Additionally the pneumatic coupling protective cover protects the rocket motor pull switch lanyard attachment The transducer protective cover protects the transducer arrangement including the transducer pneumatic and electrical connectors 1 17 UMBILICAL AS
177. e electrical systems with the CMGS Inside the domed housing is the airframe pneumatic storage bottle that 15 used to erect the fins and to deploy the wings and the engine inlet The aft body lower half contains the molded fiberglass epoxy engine inlet and its pneumatic actuator and associated control valve The aft body lower half also contains the pilot static system air data package which provides barometric and differential pressure inputs to the CMGS to determine altitude dynamic pressure and flight Mach number and supplies air pressure to arm the conventional warhead 1 11 5 3 Propulsion Section The propulsion section extending from station 182 50 to station 219 16 includes the tail cone structure the turbofan sustainer engine and four pneumatically erected fiberglass polycarbonate stabilizer fins The lower fin is fixed while the other fins move to provide pitch roll and yaw control An engine driven dc generator regulator three electrically driven servo actuators one for each movable fin and the fin Power Switching Amplifier are also housed within the propulsion section 1 11 6 Rocket Motor Assemblies RGM 109C and RGM 109D variants are configured with the Mk 106 Mod 0 Rocket Motor UGM 1094 variants are also configured with Mk 106 rocket motor assemblies UGM 109C and UGM 109D variants are configured with the Mk 111 Mod 0 Rocket Motor RGM UGM 109E Block IV is configured with the Mk 135 Rocket Motor Assembly Each rock
178. e in the aft portion fuel tank of the guidance section Figure 1 14 Range Safety System 109C The J 109D has the RSS equipment mounted on two shelf assemblies in payload section and an RSS antenna nose cone installed in place of the positive retention nose cone Figure 1 15 Range Safety System 109D RSS instrumentation consists of a dual RSC receiver decoder PCM encoder an FM multiplexer J 109C D an RSC test oscillator power monitor unit thermal battery a C band transponder J 109C D an S band telemetry transmitter and associated antennas J 109C D and a squib activated thermal battery 1 12 3 Midbody Range Safety Subsystem MRSS Block IV TACTOM missiles used for test or exercise flights are equipped with MRSS The MRSS provides the missile with a communications link with test ranges during flight tests This subsystem 15 only present during such exercises and comprises of a Range Safety Electronics Unit RSEU and a Tri Band Antenna The RSS provides telemetry data at a rate of 2 5 megabits per second The communications includes missile instrumentation data range command and control flight termination position tracking and underwater telemetry data transmission submarine launch only Major Subcomponents include Tri band Antenna Command Control Decoder C Band Transponder Flight Termination Battery Flight Termination CCA Flight Termination Receivers 2 Harnessing I O CCA Power Monitoring Un
179. e of the designated tube pressure vent manifold is opened to supply air to the missile When missile pressure stabilizes between 3 8 and 7 2 psid a PRESSURE IN BAND indicator appears on the WLC and the PRESSURIZE indicator goes out PRESSURE IN BAND PRESSURIZE and VENT indicators may cycle on and off during the preparation for launch due to changes in missile pressure 4 5 3 Mission Assignment With RASS initialized the CMGS is ready to accept mission data when BALLISTICS SET and CMGS PROGRAMMED are indicated to the WCC operator CMGS flight program has been transferred to the missile and the missile has responded with a valid Missile Status Word The WCC operator changes the submode until Land Attack TOMAHAWK Evaluation is indicated on the WCC THEATER MPS MISSION and VERIFY codes are received from the appropriate authority and entered on the WCC Mission data are then indicated on the WCC Mission data are also transferred to the central computer resident memory The WCC operator enters the target number and the pre established waypoints to that target are displayed on the WCC The WCC operator reviews the mission data and approximate flight path to the target and makes route alterations by introducing or deleting waypoints The WCC operator then assigns the mission to a designated torpedo tube and a verification that the mission is assigned to the correct tube is performed Once a mission has been assigned no further modifications can be made w
180. ea Correlation DSMAC or DSMAC and Global Positioning System Subsystem GPSS to increase terminal accuracy Time of Arrival TOA and Time on Target TOT software are 27 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 also used to enhance coordination with other strike capabilities The missile has a modular construction aluminum airframe with a diameter of 20 375 inches The length is 243 33 inches with the Mk 106 Mod 0 Rocket Motor or 246 06 inches with the Mk 111 Mod 0 Rocket Motor The unique body sections are the forward body guidance section and the forward body payload section which are described in the following paragraphs 1 11 3 1 Forward Body Guidance Section The forward body guidance section extends from station 0 00 to station 52 45 Major components are the positive retention nose cone the Cruise Missile Guidance Set CMGS Figure 1 2 Cruise Missile Guidance Set CMGS the Digital Scene Matching Area Correlation DSMAC Figure 1 4 Digital Scene Matching Correlation DSMAC or DSMAC and Global Positioning System Subsystem GPSS sets and an illuminator assembly Also included are a junction box in a well on the right side and two radar altimeter antennas on the bottom centerline The positive retention nose cone made of an aluminum alloy threads on to the payload section The CMGS provides missile navigation guidance and control functions and consists of a Reference Measuring Unit and Computer RMUC
181. eals P N JCM 17678 Trailer Munitions Aero Transport containerized and 5 B C D uncontainerized weapons P N 67A314F100 119 SW820 AP MMI 010 REVISION 15 EQUIPMENT Truck Handlift Mk 45 Mod 2 P N 5167104 Truck Pallet Low Lift Trunnion P N JCM 14514 001 Umbilical Breakout Box UBOB Mk 674 Mod 1 P N 7379010 Universal Restraint Stand Mk 121 Mod 0 P N 6146521 Vertical Launch System VLS Canister Code Plug Test Set Mk 673 Mod 0 P N 6375451 Weapons Skid Aero 21C P N 64A114H1 4 or Munitions Transporter MHU 191 M P N 1500AS100 1 27 MARCH 2009 CHAPTER 1 FUNCTION Handle CNU 308 E Shipping Container Handle CNU 308 E Shipping Container Used when lowering the CLS AUR into the Mk 23 Tilt Fixture Can also be used for uprighting the All Up Round Simulator and Ballast Can Perform VLS weapon electrical tests Warhead 109A May be used for maintenance on TTL Mk 10 and VLS weapons Determine VLS canister code plug configuration With Mk 130 Mod 0 Extension Handle Aero 64A 64B Soft Belt Adapters and front and rear Aero 58A 58B Skid Adapters installed transport uncontainerized TTL and Mk 10 weapons 120 ILLUSTRATION SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 EQUIPMENT FUNCTION ILLUSTRATION Wrench Canister Loosen and tighten separation nut Separation Nut Lockring lockring during Mk 10 encanisterization P N 7674738 1 and decanisterization Wrench Sp
182. ear Safety Rules for Operations provided in applicable Type Commander directives and SWOP 20 7 FUEL PRECAUTIONS TOMAHAWK Cruise Missiles are fueled with JP 10 a nonexplosive combustible liquid The flashpoint for JP 10 is 130 degrees F and auto ignition may occur at 474 degrees F Firefighting involving JP 10 is the same as for any other hydrocarbon fuel Carbon dioxide dry chemical and water spray are the methods used to combat fire The probability of fuel leaking from the missile is highly unlikely since the capsule canister also serves as a fuel tight barrier In the event leakage should occur the affected areas should be wrapped in Buna N rubber sheeting and or ordnance tape to provide a fuel tight seal 176 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 2 Do not use organic cartridge respirators or oxygen breathing apparatus to combat fuel associated casualties including cleanup of spills or combustion by products A minimum of two personnel shall be present during operations involving fuel spills No smoking matches or open flames are permitted in the area of a fuel spill EXPLOSIVE HAZARDS The TOMAHAWK Cruise Missile contains a number of explosive components They range from comparatively low explosive electroexplosive devices EED to the highly destructive high explosive warhead Also included in the general category of explosives 15 the solid propellant rocket motor General safety precautions regarding handling an
183. ed to separate the submunition pack after ejection from the payload section The submunition pack combined effects bomblets are armed when exposed to the airstream allowing the primary or secondary firing mechanism to detonate the explosive upon impact 40 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 1 14 8 Block IV TACTOM Terminal Phase The Block IV TACTOM terminal phase begins with Terminal BDI image acquisition and ends with the missile impacting the target The terminal subphase of the Block IV TACTOM mission differs from the Block III mission in several respects If the mission is autonomous strike the Block IV TACTOM will proceed to target after the DSMAC update and function the same as Block III If an alternate target has been designated during enroute navigation or in the loiter pattern the remainder of the navigation will be GPS only The Block IV TACTOM missile will use a pushover maneuver that will induce negative Gs The Block IV TACTOM Missile can be programmed to attack targets with either a Programmed Warhead Demolition PWD maneuver or a Variable Dive Attack Maneuver VDA with a terminal dive angle from five to 85 degrees The PWD attack is the same as that used for the Block TOMAHAWK Land Attack Missile The range of angles available for a VDA is significantly wider than that used in Block III and also serves to replace the Horizontal Attack Maneuver used in Block III The Block IV TACTOM Missile uses an ellipt
184. el for operator evaluations The printer and paper tape provide two means of producing hard copies of output data Reset and control data may be transmitted to either INS as selected by the DLS 3 21 4 Radio Navigation Set RNS The RNS receives Satellite Navigation SATNAV data for updating INS Reset data is transmitted to either INS as selected at the DLS that also interfaces with the DTG 3 21 5 Global Positioning System GPS The GPS is a satellite navigation system which provides continuous worldwide information The information is used to calculate 3 dimensional speed and precise time of data GPS also provides a parallel digital interface for information exchange with the INS 3 22 VLS DAMAGE CONTROL SYSTEM The VLS Damage Control System provides for detection and control of hazardous conditions within launch cells and modules Elements of the damage control system include the damage control monitoring system which utilizes sensors located inside and outside launch cells to monitor conditions deluge system which distributes water over a missile warhead when activated in an emergency and the magazine sprinkler system that provides remote fire fighting capability in missile modules Conditions monitored include the status of the anti icing system deluge system operating module high water level condition one half inch or deeper a continuous launch sequencer LSEQ power off condition and when implemented missile fuel leak In the ev
185. elected and sequenced all controls have been positioned and all indicators are go g TUBE READY Indicates that the underhatch volume has been flooded and the pressurization vent control valve 15 closed h CAPSULE BOOSTER PREARMED Indicated that the capsule and rocket motor are in the prearmed position Upon activation of the FIRE switch and indication of MISSILE ENABLED 1 hatch open booster armed capsule armed batteries activated BIT passed MISSILE STATUS word good the fire control system closes firing interlocks prior to permitting the coded charge and launch signals to be sent to the CLS 4 11 LAND ATTACK TCM OPERATIONAL SEQUENCE This paragraph describes typical actions and responses required to launch a land attack TCM Primary coverage is given to normal launch of a single weapon For salvo launch the operational steps for a single launch are sequentially accomplished for each weapon selected for launch Abnormal launch conditions and abort procedures are discussed by highlighting only those events that differ from a normal launch Typical launch operations are shown in Figure 4 20 UGM 109 2 Land Attack TCM Operational Sequence 10 Sheets The figure illustrates the orders given by ship s commanding officer typical actions taken by equipment operators and typical equipment operations status displays and machine decisions The operational sequence is described in the following paragraphs For a full discussio
186. ell module physical interfaces consist of the mechanical electrical and pneumatic interfaces described in the following paragraphs 3 20 1 Mechanical Interfaces The mechanical interfaces consist of the following a Pyrotechnically activated separation bolts to restrain the missile in the canister until launch b Thermal lined corrugated shell structure for loading in the launch cell 16 lateral supports inside the Mk 14 Canister to provide shock isolation for the TCM in the Mk 10 Canister Deluge connector to connect the ship s deluge system to provide distribution of water on the missile warhead in the event of an emergency e Latches to secure the Mk 14 Canister in the cell Mk 14 Canister and sill assembly interface to direct rocket motor exhaust gas into the module plenum 3 20 2 Electrical Interfaces The electrical interfaces consist of the following a Telemetry monitoring connector to transmit data from a telemetry missile prior to launch b Umbilical connector connects to the MK 14 Canister Cable Assembly which in turn connects the code plug FWD closure breakwire temperature sensor AFT closure breakwire All Up Round AUR cable and conduit assembly and AUR umbilical connector adapter to transmit commands from the fire control system and receive responses from the canister and TCM e Antenna connector to transmit data from telemetry monitoring equipment to the missile d Canister Safe Enable Switch CSES Mk 14 Canist
187. em arming firing device and igniter assembly and aft cover assembly The nozzle comes equipped with an aluminum nozzle seal plug fitted with a flood valve The nozzle plug blows out upon rocket motor ignition The rocket motor aft cover supports the electrical connector and the missile retention devices 1 11 6 3 Mk 135 Rocket Motor Assembly The Mk 135 Rocket Motor Assembly consists of an air melt 4330 steel cadmium plated motor case loaded with 322 pounds of Arcadene 360B HTPB a high performance aluminized composite propellant Arcadene 360B HTPB has been assigned a Department of Defense DOD hazard classification of 1 3C The propellant is cast into and bonded to the insulated steel case Other major subcomponents include the Arm Fire Device AFD and a fixed nozzle to which the TVC is attached The TVC employs electrically actuated jet tabs The rocket motor assembly is approximately 19 9 inches in diameter and 24 5 inches in length The total weight of the assembly is approximately 600 pound 1 11 7 TCM Components Common to 109A C D The following components are common to the 109A C D variants 1 11 7 1 Missile Retention Devices Two retention devices are installed between the rocket motor and capsule or canister to restrain the missile in the capsule canister during storage shipping and handling Each device consists of a stud and nut that releases at launch to permit egress of the missile from the launching device 1 11 7 2 Underwater P
188. en reentering the mission number and verification code After assigning the mission the WCC operator normally selects the Land Attack TOMAHAWK Preset submode for the remainder of the launch in order to monitor tube and missile status and any alerts concerning launch 4 11 3 1 CMGS alignment begins automatically upon completion of a successful upload of the Operational Flight Program OFP A two position alignment technique eliminates the need to perform submarine maneuvers at latitudes below 75 Launches at latitudes above 75 however will require submarine maneuvers to meet the alignment timeline Upon completion of alignment the CMGS will provide an ALIGNMENT COMPLETE message to the WCC operator 4 11 3 2 If CMGS computer built in test BIT is not passed or valid communication can not be established or becomes lost with the CMGS computer an alert message is provided to the WCC operator To establish or restore communications a controlled shutdown of the CMGS 15 performed and missile electrical power recycled The normal start up sequence is then repeated and program load reattempted When program load is accomplished the reprogram command is sent to the CMGS 4 11 4 Rocket Motor Capsule Prearm When proper authorization is given the BOOSTER ARM and CAPSULE ARM switches are activated to prearm the rocket motor and capsule respectively 4 11 5 Tube Ready When WCC display indicates INPUTS MATCHED YES and when proper authorization is
189. ent a sensor reports a hazardous condition the Local Status Panel located at the entrance to magazines displays the hazard and advises the Central Control Station of the hazardous condition The LSEQ which continually monitors cell conditions generates the hazard message to the launch control unit which after analysis of the hazard directs the VLS to act to eliminate or reduce the hazard 3 23 EXHAUST GAS MANAGEMENT SYSTEM The exhaust gas management system Figure 3 3 VLS Exhaust Gas gt directs the gas from the rocket motor to the external atmosphere Exhaust gas from the rocket motor expands downward from the bottom of the canister into the module plenum where is vented through the uptake and open uptake hatch Sealing of the system is particularly critical to ensure that all 197 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 3 exhaust gas is vented to the atmosphere and not into the ship The Mk 14 Canister and the sill assembly installed at the time of loading provide this effective seal against improper venting of gases 198 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 3 Figure 3 1 TTL Electrical and Pneumatic Umbilical Routing 2 Sheets PNEUMATIC LANYARD CONNECTOR inasa LANYARD ELECTRICAL ATTACHED SHACKLED CONNECTOR TO CAPSULE ED TO EYE ATTACHED SULE lt PNEUMATIC UMBILICAL revue men ATTACHED SREECH DOOR
190. er to monitor weapon status safe or enable 3 20 3 Pneumatic Interface The nitrogen supply valve provides a means to pressurize the Mk 10 by way of a nitrogen line inside the Mk 14 Canister 3 21 NAVIGATION SYSTEM The navigational systems provide data on ownship s time position heading velocity pitch angular rate and roll angular rate The data is used for track data management and engagement planning 196 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 3 3 21 1 Inertial Navigation Set INS Most ships have two INSs aboard One is in the forward Gyro Room the other in the aft Gyro Room The INSs are designated FWD and AFT They serve as the primary navigation data source Each set provides ownship heading position speed roll pitch and time These data are provided to the TOMAHAWK Weapons Combat System TWCS by the Launch Data Processing Control Center via an interface with the Digital Linear Switch DLS 3 21 2 Digital Linear Switch DLS The DLS determines if the input to the TWCS is from the FWD or AFT INS unit During a casualty to one when one unit may be inoperable an operator can switch the DLS to the operating unit 3 21 3 Data Terminal Group DTG The DTG also called Input Output Control Console IOCC provides an interface with the INS Data is manually loaded by keyboard and automatically though a paper tape reader The control panel furnishes DTG control and indicators Output is displayed on a pan
191. erform periodic navigational updates A GPSS receiver receives signals from GPS satellites processes the signals and provides navigational data for the missile This GPSS navigational data can be used in lieu of or in combination with TERCOM DSMAC fixes to provide more flexibility and higher reliability in accomplishing mission objectives 1 13 5 Block IV Tactical TOMAHAWK Targeting The Tactical TOMAHAWK Cruise Missile is part of the Block IV upgrade to the TOMAHAWK Weapon System The Block IV upgrade also includes improvements to the planning and launch control systems that coupled with improvements to the Tactical TOMAHAWK Cruise Missile provide increased capabilities to the operational forces The Block IV TACTOM combines the capabilities of the current system with faster response time and more flexibility Multiple outcome missions can be created at shore based planning centers or the Afloat Planning System installed on aircraft carriers Each mission can have up to 15 outcomes The default outcome may be reset prior to launch or via communication with the missile while in flight Mission data for Block IV TACTOM can also be created onboard launch platforms Launch platform planned missions are GPS only with a single outcome During flight the Block IV TACTOM can report Health and Status H amp S at predetermined intervals or when requested by the Strike Controller Near the end of the mission the missile can transmit a Battle Damage Ind
192. ernal volume of an expended CLS contains approximately 700 gallons of HW Tube flushing will produce approximately 300 additional gallons of HW Therefore approximately 1 040 gallons of HW are generated during off load of one expended CLS 171 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 2 Figure 2 1 Explosive Safety Quantity Distance ESQD Arc Restrictions Typical lt PIER T ALSO APPLIES SMALL BOAT 1 ALSO APPLIES TO SMALL BOAT FLATBED TRUCK ETC FLATRED TRUCK ETC gt gt 172 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 2 Figure 2 2 TOMAHAWK Cruise Missile Hazardous Component Locations 2 Sheets 12 13 45 1 N A A RECOVERY EXERCISE MODULE REM 2 WDU 25 B WARHEAD OR WDU 36 8 WARHEAD 109C 3 WARHEAD FUZE BOOSTER ASSEMBLY 109C 4 CMA THERMAL BATTERY 5 WING SLOT PLUG THRUSTERS 2 6 3 WAY VALVE WING EXTEND He VENT CONTROL 7 He 3 WAY VALVE SLOT DOOR CLOSE He VENT CONTROL He 3 WAY VALVE ENGINE INLET DEPLOYS SLOT DOOR OPEN CONTROL 9 He 3 WAY VALVE He SUPPLY FIN DEPLOY CONTROL 10 ENGINE START CARTRIDGE 32 11 CABLE CUTTER 12 ROCKET MOTOR SEPARATION ASSEMBLY 13 SAFE ARM IGNITER SUPPLY 106 ROCKET MOTOR 14 GN SUPPLY VALVE MK 106 ROCKET MOTOR 18 SHROUD SEPARATION ASSEMBLY S NP 17 ENGINE INLET COVER THRUSTER X 22 E 18 FUEL SECTIONS 109A C 1 19 DUAL AIR VALVE 109
193. ers covers the compartment The compartment is vented through two tubes to an orifice plate located on the top of the forward body section 1 12 1 2 Riser Stowage Compartment The parachute Y harness and risers are routed along two shallow channels in the top of the missile midbody Excess harness is stowed in the riser compartment Additionally the compartment contains two pyrotechnically released riser attachment fittings and the attachment fitting for the aft leg of the main parachute Y harness It also contains the recovery beacon antenna and its flotation assembly Rubber impregnated cloth strips held by aluminum retainers cover the riser channels A jettisonable cover held by a single pyrotechnic thruster encloses the riser compartment 1 12 1 3 Flotation Equipment Compartment The flotation equipment compartment houses the flotation equipment used for water recovery The equipment consists of a pneumatically inflated flotation bag two pyrotechnically activated pressure bottles and the tubing and fittings to route pneumatic pressure to the flotation bag The compartment contains lead ballast to compensate for the differences in weight between the REM and the forward body section it replaces Fuel lines for the land attack REM equipped variants are also provided for the transfer of fuel between the CMGS the payload section fuel tank and the midbody 1 2 1 4 Instrumentation Avionics Compartment The instrumentation avionics compartment ma
194. es a Loading button on the capsule barrel closure to load unload the missile capsule from the torpedo tube b Two guide studs on the capsule barrel to align the capsule in the torpedo tube The forward guide stud also engages the tube stop bolt c Two shear holdback assemblies to restrain the missile in the capsule until ejection d Two spring loaded latches at the aft end of the capsule to restrain the capsule in torpedo tube UGM 109A C D 1 e Capsule retention fixture installed on the capsule to restrain the capsule in the torpedo tube The retention fixture also houses a clamp that is removed and installed on the capsule barrel closure in order to secure the eletrical umbilical cable UGM 109E 1 3 0 2 Electrical and Pneumatic Interfaces The electrical and pneumatic interfaces consist of the electrical and pneumatic umbilical discussed below The routing of the umbilicals is shown in Figure 3 1 TTL Electrical and Pneumatic Umbilical Routing 2 Sheets gt 3 9 2 1 Electrical Umbilical The electrical umbilical connects between the breech door and the missile to transfer power commands and status signals between the missile and submarine combat system 3 0 2 2 Pneumatic Umbilical The pneumatic umbilical connects between the breech door and the capsule to connect the PVC system to pressurize the missile and supply pneumatic pressure to close the capsule flow slots in preparation for capsule ejection when authorized 3 10 P
195. es the DSMAC Sensor and the Illuminator There are two processor cards within the subsystem DSMAC Control Processor DCP and DSMAC Signal Processor DSP Both of these cards reside within the Guidance Electronics Unit The DCP provides interfaces to the sensor illuminator Mission Control Subsystem and telemetry The chief function of the DSP is to process the DSMAC video data from the sensor and compares it with the reference maps stored in its memory 1 11 4 3 7 Digital Scene Matching Area Correlator Sensor Assembly The Digital Scene Matching Area Correlator DSMAC Sensor is part of the DSMAC IV System which also includes DSMAC Processors and the Illuminator The Sensor is an optical device camera that captures digital grayscale images for the DSMAC IV System Images are processed in the DSMAC Processor Subsystem against reference images for missile navigation assistance DSMAC Images of pre planned locations can be obtained and transmitted as part of midcourse Health and Status messages for use as Battle Damage Indication Imagery 1 11 4 3 8 Fin Control System The Fin Control System controls all three missile fins right left and vertical located at the rear of the missile The system consists of one controller and three actuators and ballscrew assemblies The FCS is controlled by the MCP and returns feedback and status data to the 1 11 4 3 9 Guidance Electronics Unit The provides centralized housing o
196. et motor assembly is described in the following paragraphs 1 11 6 1 Mk 106 Mod 0 Rocket Motor The Mk 106 Rocket Motor Figure 1 9 Mk 106 Rocket Motor gt is a single chamber fixed nozzle assembly that extends from station 219 16 to station 243 33 The major components are an insulated steel case containing solid grain propellant a safe arm igniter assembly a fixed nozzle pneumatic hydraulic thrust vector control TVC tabs and a pyrotechnic separation assembly The nozzle is fitted with a moisture tight plug that includes a pressure relief valve to prevent rocket motor collapse in the event of a submarine torpedo or missile tube over pressure condition The nozzle plug blows out upon rocket motor ignition The rocket motor aft cover supports the electrical connector and the missile retention devices 1 11 6 2 Mk 111 Mod 0 Rocket Motor The Mk 111 Rocket Motor Figure 1 10 Mk 111 Rocket Motor is mounted on the missile tail cone at station 219 16 through a separation ring and extends to station 246 06 The rocket motor has a pneumatically actuated hydraulically operated movable ball and socket nozzle which directs the rocket motor exhaust and controls the 34 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 directional movement of the missile during the boost phase of the missile flight The rocket motor consists of a heat treated steel case containing solid grain propellant insulation movable nozzle and thrust vector actuator syst
197. etween TTL Capsule TOTEM Capsule pneumatic coupling and pressurization equipment Handle CNU 308 E Shipping Container with pallet truck Use with forklift and sling to handle uncontainerized TTL and Mk 10 weapons Use with forklift and sling to handle uncontainerized CLS weapons Perform VLS weapon pressure check and pressure service 104 ILLUSTRATION SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 EQUIPMENT FUNCTION ILLUSTRATION Adapter Support Cradle Supports forward end of CLS weapon Forward 168 0 when connected to the Mk 26 P N 5917395 Uprighting Fixture Adapter Trunnion Bearing Attaches to CLS weapon to act as pivot Assembly Mk 174 Mod 0 to permit transitioning between vertical P N JCM 17863 and horizontal during onload off load Alignment Guide Nose Aligns nose cover capsule screw holes Cover Attachment to attach nose cover to Capsule Mk 1 P N 7677894 1 Mod 0 Capsule Alignment Guide Nose Aligns nose cover capsule screw holes Cover Attachment to attach nose cover to Capsule Mk 3 P N 7677897 3 Mod Capsule Alignment Tool Guidance Maintain control of the Cruise Missile Set Guidance Set during 109A warheading if P N 6145719 and dewarheading SB A Assembly Chain and Secure weapons and containers in small Adjuster boats i P N MB 1 CGU 4E agamy 105 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 EQUIPMENT FUNCTION ILLUSTRATION A
198. ew Point Monitor assqa qa sgk akaqa sasay aaa kawsas 194 3 17 5 Hatch and Valve Position Sensors civ ccs creer rre hn nnns 194 SIS NAVIGATION SYSTEM ua ete eed 194 3 18 1 Navigation Equipment Alignment 2 00 2 0 0 195 3 18 2 Velocity and Position Computation 0 0 00 7 2 195 3 18 3 Reset ComputallODS vetu vr ooo ci ob eroe Rad bed ud 195 3 18 4 Status and Performance Monitoring 0 1 200200 195 SECTION V VERTICAL LAUNCHING 5 8 196 Dal GENERAL ctetu stati aiat e d ente rA 196 3 20 MISSILE CANISTER AND LAUNCH CELL PHYSICAL INTERFACES 196 3 20 1 Mechanical Interfaces s pida err tte t 196 3 20 2 Electrical Interfaces e Sedet Ea SETS Diae oues 196 3 20 53 Pneumati o 196 32I NAVIGATION SYSTEM eos csi tavernas has GNU ian rU ia crv ean aeree t eds 196 3 21 1 Inertial Navigation Set INS 197 3 21 2 Digital Linear Switch DLS 2523 0 ip reb Tia t 197 3 21 3 Data Terminal Group DTG sie cy re 197 3 21 4 Radio Navigation Set RNS 197 3 21 5 Global Positioning System GPS 2 4 197 322 VLS DAMAGE C
199. f various electronic cards for guidance pyro and power control mission control and secondary power The GEU motherboard provides interconnections among the cards and with the rest of the missile 1 11 4 3 10 Mission Control Input Output MCIO The MCIO provides the interface between the Mission Control Processor and other missile subsystems These subsystems include the Fin Control System Thrust Vector Control Air Data Module Radar Altimeter Satellite Data Link Terminal Engine and Mid body Range Safety System Collectively these interfaces are referred to as Mission Control I O Low Priority MCIOLP This unit resides in the GEU 1 11 4 3 11 Mission Control Processor MCP The MCP is the central executive for the Block IV TACTOM missile during all phases of the mission and functions as the manager of all other elements The MCP provides the computational functions necessary to enable autonomous vehicle flight from launch to mission completion The MCP also provides control of SATCOM Data Link Terminal communications MCP is the hardware host for TACTOM mission control operational flight software This unit resides in the GEU 1 11 4 3 12 Navigation Processor NP The NP is a single board computer that provides a navigation solution to the MCP for directing the missile to the intended target The NP takes in IMU DSMAC Radar Altimeter and TERCOM inputs The outputs are passed to the 32 SW820 AP MMI 010 REVISION 15 27 MARCH 20
200. f indicators that the tube successfully fired the WLC operator closes the muzzle door turns the weapon loaded switch to OFF secures the ship 700 psi air isolation valve to the pressure vent manifold and drains the tube After the tube is drained the breech door 15 opened The umbilicals and inside of the breech door are rinsed with fresh water to remove salt water residue and then dried The umbilicals are then disconnected and removed and the tube is secured using procedures contained in NAVSEA OD 44979 4 6 3 Capsule Return to Stowage Upon order to stow capsule the WLC operator turns the weapon supply and weapon loaded switches to OFF secures the ship 700 psi air isolation valve to the pressure vent manifold and drains the tube The breech door is then opened and the umbilicals the inside of the breech door and the aft face of the capsule are rinsed with fresh water to remove salt water residue and dried The umbilicals are then disconnected and removed The capsule latches are manually retracted by pressing and holding their spring loaded plungers then lifting the latches and securing them with the pins provided The capsule is removed from the tube using 210 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 procedures contained in NAVSEA OD 44979 rinsed with fresh water dried covers installed and the capsule is then moved and secured to a stowage position 4 7 LAND ATTACK TCM CASUALTY MODE There is no casualty mode for land
201. fare Center Division Port Hueneme 140 SW820 AP MMI 010 REVISION 15 ABBREVIATION ACRONYM NTIK NTP NTSP NUREP NUWC NUWCDIV NUWCDIVNPT NWAD NWS OD OFP OLSS OP OPNAV OPNAVINST OR ORDALT OSHA OTH OTL OTLP PAL CD P N PCM PEO CU INST PEO U amp W PEO W PEO W INST 27 MARCH 2009 CHAPTER 1 DEFINITION Non Tactical Instrumentation Kit Navy Training Plan Navy Training System Plan Nuclear Weapons Report Naval Undersea Warfare Center Naval Undersea Warfare Center Division Naval Undersea Warfare Center Division Newport Naval Weapons Assessment Division Naval Weapons Station Ordnance Data Outside Diameter Operational Flight Program Operational Logistics Support Summary Operating Procedure Ordnance Publication Office of Chief of Naval Operations Chief Naval Operations Instruction Ordnance Requirement Ordnance Alteration Occupational Safety and Health Administration Over the Horizon Operational Test Launch Operational Test Launch Payload Permissive Action Link Command Disable Part Number Pulse Code Modulation Program Executive Officer Cruise Missiles and Joint Unmanned Aerial Vehicles Instruction Program Executive Officer for Unmanned Aviation and Strike Weapons Program Executive Office for Strike Weapons and Unmanned Aviation Program Executive Office for Strike Weapons and Unmanned Aviation Instruction 141 SW820 AP MMI 010 REVISION 15 ABBREVIATION ACR
202. ff steps followed by IP These steps are procedures which should be witnessed by QA personnel and are repeated in a modified form for QA use on the SIPs The SIP can be used for record purposes by QA if required 1 8 4 1 Philosophy and Scope The policy and practice of designating steps for inspection verification 15 not intended to provide solutions for training deficiencies operation tempo variations in personnel performance or other hardware system features susceptible 24 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 to procedural error Neither do they cover all facets involved in administering a total QA program Inspection verification points generally create a record that significant operations were accomplished by or in the presence of specific personnel The record may be useful in a failure investigation suggesting candidates for interview and the involvement of a QA function may heighten worker attentiveness at affected steps however the record 15 not a guarantee of compliance Safety of operations and reliability of product are dominated by the training proficiency and professionalism of the personnel accomplishing the tasks In the limit record worthy steps are those which if not performed correctly may create a hidden condition that may in turn cause a post launch mission failure Steps meeting this record worthy criteria from a standpoint of AUR design features are designated as Inspection Points in the technic
203. ffect the ship s position and movement are factors in determining the feasibility of offloading operations The shore base loading supervisor and the ship s commanding officer will determine if conditions are satisfactory prior to commencing offload Prior to offload launchers are neutralized and placed in the strikedown mode at the status panel During offload responsibility for operations is shared between the ship s commanding officer and the shore base loading supervisor actions involving ship system and weapon preparation are the responsibility of the ship s commanding officer His permission 15 required prior to commencing offloading operations His designated representative is responsible for weapon handling operations and ensures that a weapon transfer inspection is conducted Upon completion of ship and weapon preparation responsibility for offload transfers to the shore base loading supervisor The following paragraphs provide a general overview of procedures used during offload operations For purposes of illustration offloading of a generic weapon from one launch cell is discussed For multiple offloads the procedures are the same except that multiple actions may be occurring simultaneously to prepare launch cells and weapons Additionally loading equipment is moved from missile to missile until the full complement of weapons is offloaded from the ship Similarly post offload procedures are accomplished on a cell by cell basis until
204. for REM and applies ac power to the REM battery heaters 3 7 2 Simulator Present SIMULATOR PRESENT is a continuity to DC MONITOR RESET POWER that indicates that a simulator is connected instead of an actual TCM 3 7 3 Booster Safe Monitor The BOOSTER SAFE monitor is a continuity to DC MONITOR RESET POWER that indicates the rocket motor igniter 15 safed 3 7 44 Booster Armed Monitor The BOOSTER ARMED monitor is a continuity to DC MONITOR RESET POWER that indicates the rocket motor igniter is armed 3 7 5 Warhead Safe Monitor 109A only The WARHEAD SAFE monitor is a continuity to DC MONITOR RESET POWER RETURN that indicates the warhead has been safed 3 7 6 Warhead Prearmed Monitor 109A only The WARHEAD PREARMED monitor is a continuity to DC MONITOR RESET POWER RETURN that indicates the warhead has been prearmed 3 7 7 Missile Bus Monitor The MISSILE BUS monitor is a dc signal that monitors the dc output of the ac dc converter Upon loss of voltage prior to MISSILE ENABLED the launch platform automatically safes the warhead 109A only and rocket motor igniter 3 7 8 Missile Enabled MISSILE ENABLED is a continuity to DC MONITOR RESET POWER that indicates the missile batteries have been successfully activated BIT has passed and the MISSILE STATUS word is good The signal is combined in software with other conditions to complete the closing of firing interlocks For a REM RSS equipped missile the MISSILE ENABLED signal is routed thr
205. for the thrust neutralizer The thrust neutralizer is a safety device installed on the gas generator when it 15 not installed on the AUR The gas generator is a component of the AUR rather than the CLS because it is installed during missile encapsulation It is described because of its close physical and functional relationship to major components described above 1 23 2 10 Aft Cover The aft cover Figure 1 39 CLS 45 Mod 2 Aft Cover attaches to the aft closure to provide a closed environment for the gas generator and electrical cabling and controls The Mod 2 aft cover configuration is a one piece design cast from Passivated 316 54 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 stainless steel The aft cover incorporates a pressure test port and also allows for the use of the redesigned P1130 J1130 connector and for stowage of the P1130 connector The design of the aft cover allows for loading and unloading on both the SSN and SSGN platforms An umbilical clamp has been added to provide protection for the umbilical An ordnance ground has been added as well as a vent pressure test port 1 23 2 11 Aft Fairing Device The fairing is cylindrical urethane elastomer which attaches to the aft end of the CLS capsule by eight bolts The device protects the aft end of the missile Because of its tapered shape the aft fairing also serves to guide the AUR into the tube cell The aft fairing device for the Mod 2 is a slightly mo
206. full closeout is accomplished Offload terminates when all weapons scheduled for offload have been removed from the ship 4 16 2 1 Prepare Launcher Launcher preparations include preparing below deck and above deck areas for offload The launcher entry procedure takes the launcher offline puts the launcher in strikedown ensures power is available to strikedown controls and if required performs launcher blowout to ensure residual launch gases are not present in the plenum area In addition the launcher crew performs the prior to use inspection of torque tools to be used to undog and dog the dogdown latches The above deck preparations include positioning required handling equipment and ensuring the area is free of unnecessary equipment 4 16 2 2 Prepare Crane If the offload involves expended Mk 14 Canisters the shipboard strikedown crane may be utilized for offload Preparation of the crane includes bringing the crane up to the 01 level and preparing it for operation 4 16 2 3 Remove Weapon The weapon is disconnected from all VLS electrical circuitry and the deluge system Additionally all devices securing the canister in the cell are removed The 230 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Mk 4 Vertical Strongback is installed on the FWD canister lifting lugs The canister is slowly extracted from the launch cell and swung outboard to the pier The canister is oriented so that the canister bottom faces the Tilt Fixture Mk
207. g Trainer Assembly 81 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 22 Typical Parachute Recovery of REM Equipped Missile PILOT CHUTE NOTE AT WATER IMPACT SALTWATER SWITCH DEPLOYS FLOTATION DISCONNECTS MAIN PARACHUTE AT LAND IMPACT INERTIA SWITCH WATER RECOVERY 1 MISSILE ORIENTED FOR RECOVERY 2 THRUSTERS EJECT COMPARTMENT COVERS PARACHUTE COVER SEPARATION TURN EXTRACTS PILOT CHUTE 3 AERODYNAMICS LOADING EXTRACTS DRAG PARACHUTE FROM 4 DRAG PARACHUTE IS DEPLOYED REEFED PYROTECHNIC CUTTERS DISREEF DRAG PARACHUTE ALLOWING DRAG PARACHUTE TO FULLY OPEN 6 PYROTECHNIC DISCONNECT RELEASES DRAG PARACHUTE DRAG PARACHUTE TURN EXTRACTS MAIN PARACHUTE PACK 7 AERDDYNAMIC LOADING EXTRACTS MAIN PARACHUTE FROM PACK 8 FARACHUTE IS DEPLOYED REEFED PYROTECHNIC CUTTERS DISREEF MAIN PARACHUTE ALLOWING MAIN PARACHUTE FULL Xm OPEN RECOVERY BEACON ACTIVATE Lm E 10 PYROTECHNIC DISCONNECT RELEASES MAIN PARACHUTE RISER ALLOWING MISSILE REPOSITION TO HORIZONTAL ATTITUDE ON Y HARNESS 11 ON IMPACT PYROTECHRIC DISCONNECT RELEASES FITTING BETWEEN MAIN PARACHUTE RISER AND Y HARNESS 82 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 23 TTL Capsules 2 Sheets 1 NOSE COVER 2 DIAPHRAGM 3 1 4 GUIDE STUD 5 FORWARD FLOW SLOT 12 6 FORWARD SLOT COVER 7 FLOW SLOT 9 12 13
208. gized causing the hydraulic cylinders to retract thereby extracting the weapon from its seated position in the missile tube The weapon is positioned on the stop plates and the hydraulic cylinders are detached from the insertion pins A crane hook is attached to the lifting adapter arm to withdraw the weapon As the weapon is raised the insertion pins are retracted the moisture and dust plug is installed and the bellyband and tag lines are attached The weapon is fully extracted from the missile tube lifted clear of the submarine and transferred to the tender or dockside where trunnions or trunnion bearing assemblies are installed The weapon is positioned on the Tilt Fixture Mk 23 Mod 0 with Kit B or on a MK 30 skid rigged with a Mk 26 Uprighting Fixture 4 9 2 6 Remove Offload Equipment After the weapon has been removed from the missile tube the offload equipment is removed from the submarine or moved to another missile tube The MTEL centering guides are disengaged the HPU MTEL connection is severed and the hydraulic cylinders are stowed on the MTEL After detaching the MTEL from the missile tube the MTEL is removed 4 9 2 7 Secure Missile Tube and Ship Systems after Weapon Offload After the offloading equipment has been removed from the missile tube the submarine crew secures the missile tube and ship systems The crew installs the missile tube counterbore cover the P V port plug and the missile tube umbilical security cap The missile t
209. gnal the missile clears the missile tube and missile launched is indicated The order is given to close the missile tube and secure the system after ensuring a HANGFIRE alert is not indicated The Hatch Control Switch is moved from REMOTE to CLOSE and the Weapon Supply Switch turned OFF The Missile Tube Power Switch is moved to MONITOR and Missile Power turned OFF Post launch operations are performed in accordance with NAVSEA OD 44979 4 13 LAND ATTACK TCM CASUALTY MODE 222 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 There is no casualty mode for land attack TCM variants 4 14 BLOCK IV TACTOM OPERATIONAL SEQUENCE The following paragraphs describe typical actions and responses during a Block IV TACTOM launch 4 14 1 Prelaunch Sequence The Block IV TACTOM Missile prelaunch sequence includes checks of missile hardware and software loading of missile flight capable software mission data and strike data and alignment of the inertial measurement unit The prelaunch sequence starts when the application of power is initiated and completes when the missile is ready for launch The missile prelaunch sequence initiates with the application of power from the launch platform The missile s first operation upon power application is to run Built In Tests of the air data module inertial measurement unit mission control processor and navigation processor Once the initial Built In Tests are completed the platform s SCS interroga
210. gnal being sent to the MTCP 3 17 4 Dew Point Monitor The Dew Point Monitor consisting of a sensor in the 700 psig piping and electronics equipment monitors the moisture level of the air being supplied to the TCM by the pressurization vent system 3 17 5 Hatch and Valve Position Sensors Hatch and valve position sensors are magnetic proximity switches that sense the position of missile tube hatches and flood and drain system outboard valves The sensors provide a constant status of hatches and valves and will signal an alarm when conditions are not consistent with operations 3 18 NAVIGATION SYSTEM Navigation and ownship parameter data are used in computing attack control solutions Data include latitude longitude velocity heading pitch roll and depth computations Except for navigation equipment digital data input data are supplied as either synchro or event data and are converted to digital data for use by the submarine computer equipment 194 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 3 3 18 1 Navigation Equipment Alignment Computer equipment through closed loop control maintains true vertical alignment of navigation equipment stable platforms by collecting velocity data from the velocity meters and using these data to provide torquing pulses to the gimbal mounted torquing motors 3 18 2 Velocity and Position Computation True position of the submarine is continuously updated by computer equipment using primarily na
211. he following paragraphs 1 11 2 1 Forward Body Guidance Section The forward body guidance section extends from station 0 00 to station 52 45 Major components are the positive retention nose cone the Cruise Missile Guidance Set CMGS Figure 1 2 Cruise Missile Guidance Set CMGS the Digital Scene Matching Area Correlation DSMAC Figure 1 4 Digital Scene Matching Correlation DSMAC or DSMAC and Global Positioning System Subsystem GPSS sets and an illuminator assembly Also included are a junction box in a well on the right side and two radar altimeter antennas on the bottom centerline The positive retention nose cone made of an aluminum alloy threads on to the payload section The CMGS provides missile navigation guidance and control functions and consists of a Reference Measuring Unit and Computer RMUC a Rate Gyro Accelerometer Package RGAP a Missile Radar Altimeter MRA an Analog Filter Assembly AFA a Warhead Interface Unit WIU a DC DC Converter Module DCM and a Battery Power Unit BPU The CMGS attaches to the payload section via a mechanical hinge and link assembly using five mounting bolts This arrangement permits the CMGS to be swung aside after positive retention nose cone removal in order to install and remove the warhead without having to break electrical connections between the airframe and CMGS The DSMAC or DSMAC IIA set mounts aft of the CMGS The GPSS Receiver Processor Unit RPU mounts aft of th
212. he shore base loading supervisor The ship s crew conducts the final hookup and closeout of the launcher upon disconnect and removal of the loading equipment The following paragraphs provide a general overview of procedures used during loading operations For purposes of illustration loading of a generic weapon into one launcher is discussed For multiple loadings the procedures are the same except that multiple actions may be occurring simultaneously to prepare launch cells and weapons Additionally loading equipment is moved from missile to missile until the full complement of weapons is aboard the ship Similarly post loadout is accomplished on a cell by cell basis until full closeout is accomplished Onload terminates when the ship has received its scheduled complement final hookup has been accomplished all loading equipment has been removed cell hatches are closed and secured and ship system equipment has been activated 4 16 1 1 Prepare Launcher Launcher preparations include preparing below deck and above deck areas for loading The launcher entry procedure takes the launcher offline puts the launcher in strikedown ensures power 15 available to strikedown controls and if required performs launcher blowout to ensure residual launch gases are not present in the plenum area In addition the launcher crew performs the prior to use inspection of torque tools to be used to undog and dog the dogdown latches The above deck preparations include
213. ical steering algorithm to determine its terminal maneuver The ellipse is sized to provide impact at the target with the programmed terminal dive angle Depending on the ingress altitude either a Low Approach Ellipse or High Approach Ellipse is selected For a Low Approach Terminal maneuver the missile executes a pull up maneuver to put it in position to transition to the selected ellipse The ellipse is sized to be the minimum flyable size that meets the terminal dive requirements At the apex of the ellipse the missile executes a pushover and then enters proportional navigation for the terminal dive For a High Approach maneuver the ellipse is sized to intersect with the missiles current trajectory Upon reaching the ellipse the missile executes a pushover and then enters proportional navigation for the terminal dive 1 14 9 Recovery Phase REM equipped variants REM equipped missiles are pre programmed to fly to a designated recovery site Normal recovery is initiated by on board pre programmed signals chase aircraft command or by loss of RF signal a function of range safety The programmed recovery events include initiation of the recovery sequence transfer of telemetry and tracking systems to REM battery power parachute deployment and engine and CMGS shutdown Also included are radio beacon activation flotation bag inflation water recovery only main parachute jettison and REM power shutdown Figure 1 22 Typical Parachute Recovery
214. ication BDI message that contains its estimate of navigation error as it approaches the target In addition the Block IV TACTOM can transmit compressed images taken by the DSMAC Sensor as part of a H amp S message The locations for acquiring BDI images are part of a preplanned mission The Block IV TACTOM can also be redirected in flight The Strike Controller at a Command and Control facility or the Missile Controller on 38 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 a launch platform for a missile launched by the launch platform can command the missile to execute a new preplanned mission outcome The Strike Controller or Missile Controller can also send the missile a newly planned terminal segment to direct the missile to an emerging target Target coordinates are supplied external to the TWS The controller can also send an aimpoint update message to allow the missile to autonomously navigate a direct GPS route to the target The Block IV TACTOM GPS receiver provides increased ESM resistance compared to TLAM Block III The GPS Receiver is tightly coupled with inertial navigation and several other sensors to provide robust navigation performance In the terminal area the Block IV TACTOM is capable of dive angles between five and 85 degrees The expanded range of dive angles removes the need for a Horizontal Attack Mode and provides greater resistance to vertical errors in targeting data 1 14 TYPICAL MISSION PROFILE The ty
215. ific information on the security classification of TCM variants and their components 2 2 2 Maintaining Unwarheaded 109A Certification Prior to during and subsequent to warhead installation the 109A variant receives no missile systems testing at the intermediate level To ensure that the variant retains its certification the following requirements apply to the 109A without warhead installed a The 109A without warhead shall be safeguarded in accordance with the provisions of OPNAVINST 5530 13 and OPNAVINST C8126 1 DOD C 5210 41 M and shall be protected at the same level of security provided Category II Arms Ammunition and Explosives AA amp E b Formal entry and access control shall be maintained in accordance with OPNAVINST 5530 13 after the tamper resistant tape seals are broken on the shipping container c Upon breaking the tamper resistant tape seals on the shipping container the 109A shall be provided two person control which is defined in Special Weapons Ordnance Publication SWOP 4 1 as close surveillance and control of materials at all times by a minimum of two authorized persons each capable of detecting incorrect or unauthorized procedures with respect to the task to be performed and each familiar with established security requirements 2 2 3 Warheaded 109A Warheaded 109A TCMs are secured handled maintained and transported in accordance with applicable SWOPs 2 2 4 Transportation Security All shipping conta
216. igure 4 5 Figure 4 6 Figure 4 7 Figure 4 8 Figure 4 9 Figure 4 10 Figure 4 11 Figure 4 12 Figure 4 13 Figure 4 14 Figure 4 15 Figure 4 16 Figure 4 17 Figure 4 18 Figure 4 19 Figure 4 20 Figure 4 21 Figure 4 22 Figure 4 23 Figure 4 24 Figure 4 25 Figure 4 26 Figure 4 27 Figure 4 28 Figure 4 29 Figure 4 30 Figure 4 31 Figure 4 32 Figure 4 33 Figure 4 34 Figure 4 35 Figure 4 36 TOMAHAWK Cruise Missile Hazardous Component Locations 2 Sheets 173 TTL Electrical and Pneumatic Umbilical Routing 2 Sheets 199 CLS Electrical Umbilical Routing 201 VLS Exhaust Gas Control 202 General Locations of SSN Complexes 2 2 235 SSN TWS related Equipment TTL Interfaces 236 SSN TTL Pressurization Vent Control 4 237 MTEL Work Platforms oss C d 238 TTL Weapon Shipping Handling and Stowage Equipment SSN 688 Class 239 UGM 109 1 Land Attack TCM Operational Sequence 7 Sheets 240 MTEL With MTEL Adapter Installed 247 General Locations of SSN 688 Class Submarine Complexes 248 SSN 688 Class Submarine TWS related Equipment Interfaces 2 Sheets
217. ile Classification Guide 127 SW820 AP MMI 010 REVISION 15 DOCUMENT NUMBER PEO CU INST 4601 1 PEO CU INST 8023 1 PEO CU INST 8800 1 PEO CU letter 5513 Ser PEO CU 142 12 May 1990 PEO CU P1540 1 PEO W PUB 4440 PEO W INST 4440 2 54140 5 010 59086 8 5 010 593 S9086 XG STM 000 CH 613 S9086 XG STM 010 5976 010 S9CG0 B2 CSM 000 59 64 S9CG0 BU CSM 000 CG 52 CG 55 59 5 000 CG 56 CG 58 S9DDG BT CSM 000 SOSSN W4 SSM Series SECNAVINST 4855 5 27 MARCH 2009 CHAPTER 1 TITLE Physical Security Measures for Sea Launched Cruise Missiles During Transportation TOMAHAWK Conventional All Up Round Qualification and Certification TOMAHAWK Missile Nomenclature Security Classification Guidance Capsule Launching System CLS Missile Tube Loading and Handling Trainer Assembly Setup Breakdown and Maintenance Procedures Record Book for TOMAHAWK Cruise Missile TOMAHAWK Cruise Missile Record Book PEO W PUB 4440 Capsule Launching System CLS Submarine Missile Tube Trainer Assembly Setup Breakdown and Maintenance Procedures Naval Ships Technical Manual Chapter 593 Pollution Control Navy Ships Technical Manual Chapter 613 Wire Fiber Rope and Rigging Naval Ships Technical Manual Chapter 700 Shipboard Ammunition Handling and Stowage Instructions for Missile Tube Ballast Can Description Installation Maintenance and Repair Comb
218. ile capsule and missile tube interfaces consist of mechanical and electrical interfaces which are described in the following paragraphs 3 15 1 Mechanical Interfaces The mechanical interfaces consist of the following restraining devices and connections a The lateral support group on the interior of the CLS provides positioning and lateral shock and vibration mitigation for the missile b Sixlaunch seals on the CLS prevent high pressure gases from the ejected missile from contacting the missile surfaces forward of missile station 180 6 c Two holddown studs on the aft end of the missile position and secure the missile to the vertical support assembly inside the CLS d Eight retention segments on the top of the capsule mate with the upper missile tube flange to restrain the CLS in the missile tube e Lateral support pads on the CLS bear against shock lands bolted to the missile tube to position and provide lateral shock support for the CLS in the missile tube f Anumbilical cable bracket is attached to the CLS exterior to provide protection for the umbilical on the outside of the CLS g A differential pressure transducer sensing line connects the CLS to the ship s differential pressure transducer via connections on the CLS and missile tube 3 15 2 Electrical Interfaces electrical interfaces are routed through the electrical umbilical cable The routing of the electrical umbilical is shown in Figure 3 2 CLS Electrical Umbilical Routing
219. ile has a modular construction aluminum airframe The unique body sections are the guidance section forward body payload section and forward body fuel section Each section is described in the following paragraphs 1 11 1 1 Guidance Section The guidance section extending from station 0 00 to station 18 35 includes the positive retention nose cone and the Cruise Missile Guidance Set CMGS Figure 1 2 Cruise Missile Guidance Set CMGS The positive retention nose cone is made of an aluminum alloy and threads onto the missile forward body payload section The CMGS provides missile navigation guidance and control functions and consists of a Reference Measuring Unit and Computer RMUC a Rate Gyro Accelerometer Package RGAP a Missile Radar Altimeter MRA an Analog Filter Assembly AFA a Warhead Interface Unit WIU a DC DC Converter Module and a Battery Power Unit The CMGS attaches to the payload section via a mechanical hinge and link assembly using five mounting bolts This arrangement permits the CMGS to be swung aside after positive retention nose cone removal for access to the warhead cavity in order to install and remove the warhead without having to break electrical connections between the airframe and CMGS 1 11 1 2 Forward Body Payload Section The forward body payload section extending from station 18 35 to station 52 45 houses a W80 Warhead Joint Test Assembly JTA or Launch Test Payload LTP in the REM eq
220. ilical cable at the top of the AUR is strapped to the MAC cell wall and plugged into a dummy connector The long electrical umbilical cable that runs from a through connector at a penetration in the upper MAC cell wall through a slot in the capsule upper flange down the outside of the capsule wall to another through connector in the aft closure This flat low profile umbilical cable is bonded to the outside surface of the capsule and plugs into a dummy connector at the bottom of the AUR Onboard SSN class the umbilical can be connected to the same through connector in the upper missile tube wall as is done with the Mod capsule 1 24 INERT VARIANTS The paragraphs below discuss certification training and other inert variants provided to Fleet and shorebase operational and support activities to conduct CLS training maintain technical proficiency and complete personnel crew and ship certifications 55 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 1 24 1 All Up Round Simulator AURS Volumetric Shape The AURS Figure 1 28 All Up Round Simulator AURS Volumetric 5 gt is an inert non launchable volumetric shape that is used for pre and post delivery test programs crew certification trials and at sea testing Its design permits simulation of the CLS AUR to allow for pressurization venting and flood drain system operations aboard the submarine Its design also provides a watertight pressure proof enclosure for
221. in six combined effects bomblets CEB and the remaining 22 packs contain seven CEBs each for a total of 166 CEBs The payload section incorporates a longitudinal avionics trough on the top centerline for electrical harnesses pyrotechnic transfer lines and pyrotechnic initiators and detonators On GPSS equipped configurations an avionics cover which covers the trough houses the GPSS Antenna and antenna electronics Also housed in the payload section is the DSMAC set a sensor window for the DSMAC lens the DSMAC illuminator unit electronics assembly the DSMAC illuminator unit reflector and two radar altimeter antennas The radar antennas illuminator reflector strobe which lights the DSMAC scenes for night flights and the sensor window with its pyrotechnically jettisoned cover are all mounted on the bottom centerline Two payload covers are installed on the right and left sides of the payload section and are pyrotechnically jettisoned in the target area before the submunitions are ejected 28 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 1 11 4 Block IV Tactical TOMAHAWK The Tactical TOMAHAWK TACTOM Cruise Missile Figure 1 7 Block IV Tactical TOMAHAWK Missile General Arrangement is part of Baseline IV upgrade to the TOMAHAWK Weapon System The Block carries the WDU 36 B warhead The Navigation Processor provides navigation solution updates to the Mission Control Processor MCP using multiple onb
222. iners containing TCM variants are secured by wire seals Shipping containers containing 109A variants without warhead are shipped from the manufacturer to the military first destination with tamper resistant tape seals as well as wire seals applied to the container Additionally the manufacturer places tamper resistant tape seals on the 109A variant prior to shipment Tamper resistant tape seals are serially numbered with the back of the seal coated with a bar pattern release agent that will show the bars if the seal was 168 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 2 removed and re affixed or has been subjected to tampering Serial numbers or seal identifying data are recorded in the Record Book for TOMAHAWK Cruise Missile PEO W PUB 4440 that accompanies each TCM variant Seal locations are illustrated in the record book as well as in applicable volumes of this document addressing removal installation of seals during handling and maintenance processes 2 2 41 Receipt During receipt inspections tamper resistant tape and wire seals are inspected for integrity Additionally seal serial numbers identifying data are compared with the information contained in the record book If seals are missing broken or show evidence of tampering compromise of the variant is suspected and Program Executive Officer for Unmanned Aviation and Strike Weapons PEO U amp W PMA 280714 as well as the applicable In Service Engineering Agent are notified
223. ing Equipment The HPU is transferred and secured to the SSGN work area There are two different MTEL Adapters and each must be used in the appropriate AUR cells The 7124601 003 Adapter is used with MAC cells A C E and G The 7124601 004 Adapter is used with MAC cells B D and F Figure 4 35 Multiple All Up Round Canister MTEL Orientation The prepared MTEL MTEL Adapter is lowered onto the AUR cell and oriented with the large and small alignment pins temporarily placed in the MAC top plate The MTEL MTEL Adapter is secured to the MAC with four bolts The hydraulic hoses from the HPU are connected to the manifold on the MTEL 4 9111 Uprighting and Inserting Procedures to upright the AUR are similar to SSN Class with the exception of installing the lifting adapter extension Inserting the AUR is essentially the same as for the SSN Class as well with the MTEL adapter providing an interface between the existing MTEL design and the MAC top plate The additional height of the MTEL adapter requires the lifting adapter be attached to the AUR with an extension of equal height The MTEL adapter is outfitted with a guide ring The guide ring can be rotated to the open or shut position to engage or disengage the guide shoes The guide shoes perform the same function as the MTEL centering guides which is to assist in keeping the AUR in the center of the cell during loading and offloading operations 4 9 1 12 Removing Loading Equipment The MTEL Adap
224. ing and controls 1 23 1 10 Gas Generator The gas generator is contained in a cylindrical steel case approximately 15 inches long and 12 inches in diameter An integral flange at the gas generator s CG attaches to the aft closure with a spigot fit The flange seals the capsule from the upper end of the aft closure The ends of the cylinder are fitted with flat steel plate closures The closures are sealed with O rings and retained in the assembly with threaded rings The forward closure provides mounting for an electrical bridgewire initiator on the outside and an ignitor housing on the inside The gas generator aft closure has a nozzle A polyester resin inhibitor is molded on the outer surface and forward end of the propellant grain to form a propellant cartridge Two circular molded rubber gaskets are bonded to the grain spacer to provide shock isolation for the cartridge Four tapped holes in the aft closure provide attachment for the thrust neutralizer The thrust neutralizer is a safety device installed on the gas generator when it 15 not installed on AUR The gas generator is a component of the AUR rather than the CLS because it is installed during missile encapsulation It is described because of its close physical and functional relationship to major components described above 1 23 1 11 Aft Cover An aft cover attaches to the aft closure to provide a closed environment for the gas generator and electrical cabling and controls 1
225. ing performed with no degradation of mission weapon effectiveness 1 8 2 2 Evolutions Procedural documents contain only the PGs OPs and SIPs required for the performance of pertinent evolutions The combination of PGs and OPs SIPs provides procedural documentation for an overall task Evolutions are controlled by the PGs which will refer the user to the appropriate OPs or other external references The PGs are presented in order of use and in a general to specific type sequence OPs are arranged in a step by step sequence which allows personnel to read a procedural step perform the work and check off the accomplishment of 22 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 the work in the space provided The procedures stand alone to the extent that referral to other steps procedures or documents is minimized The SIPs are used with their corresponding OPs whenever IP is involved as indicated in the OPs by the IP stops SIPs are numbered to track with the OP with which they are used 1 3 is used with OP 3 There will be gaps in the numbering sequence of the SIPs because every OP does not have a SIP 1 8 3 Procedural Documentation Terminology The following paragraphs discuss terminology used in TWS procedural documentation 1 8 3 1 Procedural Guides PGs are used to coordinate major evolutions Accomplishment of OPs may be prescribed Appropriate steps for the evolution in process should be selected and all non selected step
226. installing the All Up Round Electronic Simulator AURES Figure 1 29 All Up Round Electronic Simulator AURES 101 gt on a hoisting frame This permits AURES to be raised without electrical disconnection so that topside operators have access to the AURES front panel controls and indicators Figure 1 30 AURES AURS Interface The AURES is a testing and training device used to simulate land attack CLS variants thereby permitting submarine launch control system to operate through complete CLS launch cycle in single or salvo launch modes The AURES Mk 101 and Mk 112 are presently in use in the fleet 1 24 2 CLS Loading and Handling Training Shape Mk Mod 0 The CLS Loading and Handling Training Shape Mk 3 Mod 0 is an inert CLS MK 45 containing non launchable ballasted training vehicle that is used by submarine tender and shorebase personnel to train for and maintain proficiency in all facets of CLS AUR handling and submarine onload offload operations 1 24 3 Ballast Can Variants The Missile Tube Ballast Can Figure 1 31 Missile Tube Ballast gt is an inert non launchable enclosed steel cylinder that may be loaded in SSN CLS missile tubes to enhance launch platform buoyancy control when a full complement of CLS AURS is not carried aboard the SSN Missile Tube Ballast Cans may be loaded in SSGN MAC cells to close cells against water intrusion during non deployed underway periods if AURs are not
227. ion The AGR with its Controllable Radiation Pattern Antenna CRPA allows it to vary its pattern to avoid jamming sources 226 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 SECTION IV VERTICAL LAUNCHING SYSTEM 4 15 LAUNCH PLATFORMS The VLS TWS is employed using the VLS Mk 41 aboard CG 47 Class ships CG 52 and up VLS Mk 41 Mod 0 DD 963 Class ships VLS Mk 41 Mod 1 and DDG 51 Class ships VLS Mk 41 Mod 2 The VLS Mk 41 is a multi purpose launching system capable of launching TCMs as well as STANDARD Missiles and the Vertical Launch Anti Submarine Rockets VLA The VLS Mk 4 Mod 0 configuration Figure 4 22 Vertical Launching System Mk 41 Mod 0 consists of two Mk 211 Mod 0 or Mod 1 Launch Control Units LCU two Mk 158 Mod 0 Launchers having 61 cells each one fore and one aft two status panels one fore and one aft and a Remote Launch Enable Panel RLEP The VLS Mk 41 Mod 1 configuration Figure 4 23 Vertical Launching System Mk 41 Mod 1 gt consists of two Mk 211 Mod 0 or Mod 1 LCUs Mk 158 Mod 0 Launcher having 61 cells forward one status panel forward and an RLEP The VLS Mk 41 Mod 2 configuration Figure 4 24 Vertical Launching System Mk 41 Mod 2 consists of two Mk 211 Mod 1 LCUs one Mk 159 Mod 0 Launcher having 29 cells forward one Mk 158 Mod 0 Launcher having 61 cells aft two status panels one fore and one aft and an RLEP Launch control is provided by the TOMAHAWK Weapon Control System 4
228. ion Devices 35 1 11 7 2 Underwater Protection Devices 22 2 35 11 721 Wig Slot PINGS eti aud que ad ta NOE ER 35 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 1 11 7 2 2 Engine Inlet Cover ess pr ee ea SERA 35 1 11 7 2 3 Continuity Shroud 35 112 EXERCISE VARIANTS UE MA 36 1 12 1 Recovery Exercise Module Equipped Missile 36 1 12 1 1 Parachute Compartment et 36 1 12 1 2 Riser Stowage Compartment 36 1 12 1 3 Flotation Equipment Compartment 36 1 12 1 4 Instrumentation Avionics Compartment 2 22 36 1 12 2 Range Safety System Equipped Missile 2 0 37 1 12 3 Midbody Range Safety Subsystem MRSS 37 1 13 LAND ATTACK TARGETING 37 LS Datas ts Pus y a a 37 1 13 2 Terrain Contour Matching 2 37 1 13 3 Digital Scene Matching Area Correlation DSMAC 38 1 13 4 Global Positioning System Subsystem GPSS 38 1 13 5 Block IV Tactical TOMAHAWK Targeting 38 1 14 TYPICAL
229. ions by introducing or deleting waypoints The operator then assigns the mission to the designated cell and a verification that the mission 15 assigned to the correct cell is performed Once a mission has been assigned no further modifications can be made without resetting the mission and then reentering the mission number and verification code 4 18 6 1 CMGS alignment begins automatically upon completion of a successful upload of the Operational Flight Program OFP Alignment data are repeatedly sent about each second during the prelaunch stage A two position alignment technique eliminates the need to perform maneuvers at latitudes below 75 Launches at latitudes above 75 however require maneuvers to meet the alignment timeline Upon completion of alignment the CMGS provides an ALIGNMENT COMPLETE message 4 18 6 2 If CMGS computer built in test BIT is not passed or valid communications can not be established or becomes lost with the CMGS computer an alert message is provided To establish or restore communications a controlled shutdown of the CMGS is performed and missile electrical power recycled The normal start up sequence 15 then repeated and program load reattempted When program load is accomplished the reprogram command is sent to the CMGS 4 18 7 Rocket Motor Arm When all data has been loaded into the CMGS the TWCS orders BOOSTER ARM via the LCU to the LSEQ When this order 15 received by the LCU the LCU dedicates half
230. ipping Loading and Handling Training Shape P N 14843 002 Capsule Closure Assembly during transport and handling Cover Assy Shock Plate Used to cover the AUR bore holes in P N 7124611 002 the middle and lower shock plates Provides a flat non skid surface without raised handles and will prevent items from falling into the MAC cell Cover Assy Top Hat Placed over loaded AURs to protect P N 7124611 004 them from damage after the CLC has been removed during the AUR close out procedure or in the event that an AUR has to be pulled and replaced Provides a level surface strong enough for a worker to stand on Cover Assy Top Plate Used to cover the MAC AUR cells P N 7124611 003 and to provide a flat non skid surface without raised handles It prevents items from falling into the MAC cell 107 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 EQUIPMENT FUNCTION ILLUSTRATION Cover Capsule Loading Used instead of CPC when P N JCM 17759 loading offloading CLS AUR and CLS Loading and Handling Training Shape when working on weapons loaded in missile tube or MAC cell Protects the Capsule Closure Assembly Cover Closure Protective Protects the CLS AUR and CLS Mk 19 and Clamp Loading and Handling Training Shape Ring Capsule Closure Assembly during P N 14865 001 transport and handling Cover Counterbore Installed on missile tube aboard P N 101 5580126 SSN 688 class to prevent personnel 171
231. is installed on the missile tube inner shoulder to assist in centering the MTEL over the missile tube The MTEL is lowered over the missile tube maneuvered to align its guide holes with the missile tube pins and bolted to the muzzle face The installation guide is then removed The MTEL safety cover 15 installed over the MTEL mouth to prevent objects from 214 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 falling into the open missile tube The HPU is positioned on the loading platform and connected to the electrical source aboard the submarine Hoses are connected between the HPU and the MTEL A check is made to insure the centering guides and the insertion pin stop plates are in the correct position on the MTEL 4 9 1 3 Prepare Weapon As the missile tube and ship systems are being prepared for loading and loading equipment 15 being installed submarine tender shore base personnel prepare the weapon for loading After opening the Shipping and Storage Skid Mk 30 two trunnions or trunnion bearing assemblies are installed in the weapon to allow vertical uprighting with either the Tilt Fixture Mk 23 Mod 0 with Kit B or a Shipping and Storage Skid Mk 30 that has been rigged for uprighting The weapon is removed from the skid and placed in the uprighting equipment being used where if not previously performed a pressure check and inspection to include rocket motor safe armed and weapon configuration tests are performed Interface support an
232. ister to Mk 23 Tilt Fixture in the horizontal position The strongback or forklift and forklift channels are removed 4 16 1 4 Load Weapon The Mk 4 Vertical Strongback 15 installed on the FWD canister lifting lugs Pins securing the canister in the horizontal position are removed and the canister is raised to 229 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 the vertical position Figure 4 31 Upright Mk 14 VLS Canister to Vertical Position Pins securing canister to tilt fixture are removed and canister is raised and positioned over the launch cell The canister is oriented so that the umbilical connector will be on the walkway side of the canister when installed in the launch cell The canister is slowly lowered into the launch cell until the bottom of the canister contacts the sill assembly The strongback is removed from the canister and lowered to the pier The canister is secured in the cell and connected to the electronic circuitry of the VLS and the deluge system 4 16 1 5 Post Loadout Post loadout is the reactivation of the launcher This process brings the launcher back on line and able to launch missiles It includes returning power to the launch sequencer and taking the launcher out of strikedown mode at the status panel 4 16 2 Offload Ship offload begins when the ship arrives at a designated shore base activity to discharge a complement of weapons or expended canisters Wind and sea motion which a
233. it Pulse Control Modulation Encoder S Band Transmitter Test Oscillator OTL payload cover 1 13 LAND ATTACK TCM TARGETING The capabilities and special employment considerations of the land attack TCM makes it necessary to limit the access to mission data and displays presented This is accomplished by requiring the use of mission codes to access data Only when the correct code 15 entered can data be displayed and evaluated The evaluation of mission data is generally concerned with the establishment of flyout routes and introducing waypoints which define specific latitude and longitude intersections along the flight path to the target Figure 1 16 Typical Land Attack Pre landfall Flyout gt 1 13 1 Mission Data Route map and target data land attack variants are stored disks Access is gained by entering the disk serial number and correct mission number The data consist of trajectory segment data TERCOM maps DSMAC scenes 109C 109D and 109E only and mission definition data 1 13 2 Terrain Contour Matching TERCOM The guidance system is periodically corrected and updated in flight through TERCOM The process Figure 1 17 Terrain Contour Matching TERCOM Process compares a set of digital maps stored in the with ground 37 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 elevation readings supplied by the missile radar altimeter The digital maps consist of several TERCOM m
234. ithout resetting the mission and then reentering the mission 208 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 number and verification code After assigning the mission the WCC operator normally selects the Land Attack TOMAHAWK Preset submode for the remainder of the launch in order to monitor torpedo tube and missile status and any alerts concerning launch 4 5 3 1 CMGS alignment begins automatically upon completion of a successful upload of the Operational Flight Program OFP The mission data are loaded into the CMGS and a course level is performed followed by the alignment of axis 1 The inertial platform is then slued 90 and alignment of axis 2 15 performed The two position alignment technique eliminates the need to perform submarine maneuvers at latitudes below 75 If the submarine is maneuvering and the CMGS can estimate platform azimuth angle during alignment of axis 1 slue and alignment of axis 2 will be bypassed Launches at latitudes above 75 however will require submarine maneuvers to meet the alignment timeline Upon completion of alignment the CMGS will provide an ALIGNMENT COMPLETE message to the WCC operator 4 5 3 2 If CMGS computer BIT is not passed or valid communications can not be established or becomes lost with the CMGS computer an alert message is provided to the WCC operator To establish or restore communications a controlled shutdown of the CMGS 15 performed and missile electrical power recyc
235. ition 3 6 4 Warhead Prearm Control Command 109A only The WARHEAD PREARM control command is a unique signal placing the warhead in the prearmed condition 3 6 5 Reprogram Command Land Attack only The REPROGRAM command is a dc signal that allows the CMGS to be reprogrammed It zeros the RMUC memory except for calibration coefficients To prevent gyro damage this command is never issued without first performing a controlled shutdown of the CMGS 3 6 6 Fire Command or Intent to Launch The FIRE or ITL command is a dc signal that energizes the ARM BATTERY ACTIVATE BUS relay The CMA battery activates first followed by the CMGS battery about one second later For a REM equipped missile the REM batteries activate first followed by the CMA and CMGS batteries 187 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 3 3 6 7 REM Abort Command The REM ABORT command is a dc signal that disconnects the REM batteries which results in a turnoff of all REM battery powered equipment 3 7 DISCRETE SIGNALS SENT FROM A TCM The following paragraphs discuss the discrete signals transmitted from a TCM to the launch platform Discrete signals unique to CLS are discussed in Section IV 3 7 1 Weapon Identification Electrical identification of the 15 derived from CM identification power Decode circuit defects open on the identification lines not applicable to the identified TCM Weapon identification also allows the launch platform to configure
236. ived by the RMUC it activates the Programmable Read Only Memory and reestablishes the serial data link The program is loaded into computer memory and data transmission begins 3 4 2 Request Status The REQUEST STATUS block is sent once every second to request go no go summary of missile BIT results It is also used to request the present operating mode of the CMGS e g warmup coarse level navigate Table 3 1 Land Attack TCM CMGS Alignment gt 185 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 3 3 4 3 Alignment Data The ALIGNMENT DATA block is sent once every second to send reference data to align the CMGS inertial platform relative to the launch platform inertial reference system Alignment data blocks continue to be sent until the missile is commanded to terminate alignment 3 4 4 Mission Data The MISSION DATA block includes target characteristics waypoints guidance parameters terrain correlation maps and DSMAC scenes 109C 1090 only It also identifies the type missile and the type mission to be flown Each group is sent by a unique data block that is repeatedly sent until all data for that group are transferred to the CMGS 3 4 5 Battery Activate Receipt of the ITL command causes the CMGS to initiate the battery activate sequence For a tactical TCM the CMA battery activates first followed by the CMGS battery For a REM equipped TCM the REM batteries activate first followed by the CMA
237. ization Decapsulate DSMAC Illuminator Unit DSMAC Illuminator Unit Electronics DSMAC Illuminator Unit Reflector Digital Linear Switch Dual Miniature Inertial Navigation System 135 SW820 AP MMI 010 REVISION 15 ABBREVIATION ACRONYM DMS DOD DODIC DOE DOT DPG DRAI DSMAC DSN DSP DTD DTG E CMFR EAB EBW ECP EED EID EMI EMS ENCAN ENCAP EOD EPA EQUIP ESD ESDS ESGN ESM ESQD ESSD 27 MARCH 2009 CHAPTER 1 DEFINITION Digital Missile Simulator Department of Defense Department of Defense Information Code Department of Energy Department of Transportation Digital Pressure Gauge Dead Reckoning Analyzer Indicator Digital Scene Matching Area Correlation Defense Switching Network DSMAC Signal Processor Data Transfer Device Dated Data Terminal Group Electronic Cruise Missile Field Report Emergency Air Breathing Exploding Bridgewire Squib Engineering Change Proposal Electroexplosive Device End Item Description Electromagnetic Interference Environmental Monitoring Sensor Encanisterization Encapsulate Explosive Ordnance Disposal Environmental Protection Agency Equipment Electrostatic Device Electrostatic Discharge Electrostatic Discharge Sensitive Electrically Suspended Gyro Navigator Electronic Support Measures Explosive Safety Quantity Distance Electrostatic Sensitive Devices 136 SW820 AP MMI 010 REVISION 15 ABBREVIATION ACRONYM EXT FBM FCA FCS FEDLOG FFIRT FIC FM FP
238. kes up the aft one third of the REM The equipment mounts on a removable shelf as well as on the REM body structure Equipment mounted on the shelf includes two pyrotechnically activated batteries two lithium active batteries an inertia switch a test control module an auxiliary relay unit a digital delay module a telemetry support package an electronic support package a relay enclosure a dual Range Safety Command RSC receiver decoder a Pulse Code Modulation PCM encoder a recovery beacon transmitter an S band telemetry transmitter a C band transponder a hybrid antenna coupler and an RSC test oscillator REM body mounted equipment includes two RSC antennas two S band antennas and two C band antennas Two 36 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 inertia switches are mounted on the compartment forward bulkhead A saltwater sensor switch is mounted near the bottom centerline Two acoustic pingers one 9 kHz and one 45 kHz are flush mounted on the sides The REM antennas consist of two S band two C band and two RSC antennas The S band antennas are flush mounted on the REM top and bottom centerline The C band and RSC antennas are flush mounted on the sides 1 12 2 Range Safety System Equipped Missile The land attack TCMs used for test and exercise flights with live or inert warheads submunitions are equipped with a depot installed RSS kit The J 109C has the RSS equipment installed primarily on a vertically mounted plat
239. led The normal start up sequence 15 then repeated and program load reattempted When program load is accomplished the reprogram command is sent to the CMGS 4 5 4 Ready The final steps to launch the missile are making the torpedo tube ready and arming the weapon Upon receipt of indications that alignment and mission transfer are complete and that inputs match the ACC operator gives the order to flood the designated torpedo tube Responding to the order the WLC operator floods the tube and when so ordered equalizes tube pressure with ambient sea pressure Indicators advise operators that the tube is flooded and equalized When ordered the ACC operator orders OPEN DOOR for the designated tube Responding to the order the WLC operator opens the muzzle door Indicators advise ACC and WLC operators that the muzzle door is open When ordered the WLC operator turns the launch mode switch to EJECT The ACC operator selects the firing tube and a NEXT indicator appears 4 5 5 Rocket Motor Arming When ordered the booster armed and warhead arm supply key lock UGM 109A only switches are activated by the ACC operator for the designated tube BOOSTER ARMED indicators on the ACC and WLC advise operators of successful arming of the rocket motor If indicators do not reflect that the rocket motor is armed the launch is recycled or aborted 4 5 6 Warhead Prearming UGM 109A only When ordered the warhead arm switch on the ACC is activated for
240. leeve and a sleeve ring The sleeve contains flow slots that match the flow slots in the barrel It also includes a number of Teflon coated rubber strips to absorb missile shock and reduce drag The sleeve ring attaches to the aft end of the sleeve and supports the two spring loaded plungers used to lock the capsule latches 1 16 1 6 Barrel Closure The barrel closure is a machined corrosion resistant steel plate 20 97 inches in diameter It supports the sleeve pneumatic actuator that moves the capsule sleeve to close the flow slots and the pneumatic coupling used to pressurize the TCM and actuate the actuator A loading button is installed in the center of the barrel closure to permit torpedo tube loading or unloading of the weapon On TCM configurations with the Mk 106 Mod 0 Rocket Motor the button supports a nozzle plug retainer to prevent the rocket motor nozzle plug from being dislodged prior to launch Holes are provided in the barrel closure to access the two missile holdback assemblies rocket motor pull switch lanyard and TCM electrical umbilical connector 1 16 1 7 Slot Covers Slot covers are installed over the capsule flow slots to prevent the entry of foreign matter into the flow slots Tension latches are provided for cover retention The covers must be removed prior to tube loading 1 16 1 8 Protective Covers Capsule protective covers consist of two molded polyethylene plates The electric connector access protective cover covers the up
241. ly ecole cei cere ente eo te 59 1 29 22 APT Closure Assembly ero e De kdo ux Toga 59 1 29 2 3 Umbilical Connector Rx EE A USA 59 1 29 24 Deluge zn n yana reb NS Mob e a 59 1252 3 Antenna CODDBOLOL ec soo es 59 1 29 2 6 Canister Safe Enable Switch CSES Mk 14 Mod 1 Mod 2 59 1 292 T Ganister Code Plug ons ssec re Pe Tt Ux Etpe o yea aa 59 1 29 2 8 Nitrogen Supply Valve 2 5 a tn vts te aae i e REO Questa 59 NX SEU DE 59 ESO TINERT VARIANTS tob onore atr dot ae bero da aed as 59 1 30 1 Canister Tramer Mk 17 aasan 60 1 30 2 Mk 14 Canister Trainer sacl ca s eee ex pe a eu ox oet ph o Aa SR 60 131 RECORD BOOK 5 HO QURE VERSA ARN Qus RS 60 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 1 32 WEIGHTS AND CENTERS OF 0 0 02 2 60 CHAPTER 2 SECURITY AND SAFETY erea TRA QR ter 168 utc e DISQUE quu we i d 168 212 SECURLDEY nen UC TR v NI OE es a q ayway a M ids 168 2 2 1 Security Classification ies 168 2 2 2 Maintaining Unwarheaded 109A Certification 168 22 9 Warheaded DUDAS he vr aS ot 168 D D
242. m Monitoring and control occur in the Vertical Launch Center VLC A brief functional description of the components of the missile tube control system is presented in the following paragraphs 3 17 4 Missile Tube Control Panel Missile Tube Control Panels MTCP located in the VLC provide two normal modes of system operation MONITOR and OPERATE When switches are in the MONITOR position command functions are disabled but monitoring functions and displays are operating When a switch is locked in the OPERATE position monitoring and display functions are operating and command functions are enabled for the common functions and for the selected tube The MTCP also has a special SIMULATE mode of operation to support maintenance and trouble shooting 3 17 2 Differential Pressure Transducers Two differential transducers one adjacent to each missile tube sense the differential pressure between the underhatch area and the CLS A pressure switch senses TCM pressure When underhatch differential pressure or AUR pressure is outside the specified pressure range the differential pressure transducer activates the pressure vent system to increase vent pressure as required 3 17 3 Environmental Monitoring Sensor An Environmental Monitoring Sensor is located in the underhatch area of each missile tube to sense underhatch pressure temperature and the presence of fluid Detection of one of these conditions outside the specified range results in an alarm si
243. m the SSGN platform are the location of the umbilical for disconnection by submarine personnel and the requirements for the MTEL work platform MTEL adapter and lifting adapter extension As discussed in the SSGN onload overview there are two MTEL adapters each of which must be used in the appropriate AUR cells The 7124601 003 Adapter is used with MAC cells A C E and G The 7124601 004 Adapter is used with MAC cells B D and F Similar to the MTEL centering guides the guide ring of the MTEL adapter is rotated to the shut position to engage the guide shoes and assist in keeping the AUR in the center of the cell during offload 4 10 OPERATIONAL CONSTRAINTS RESTRICTIONS Tactical employment of the TCM imposes a number of constraints on the operating parameters of the submarine The constraints imposed during tactical launch operations of the TOMAHAWK Cruise Missile are provided in applicable tactical publications Employment also places restrictions on the submarine s tactical flexibility which are described in Operating Guidelines tactical employment manuals and operation manuals 4 10 1 Weapon Mix Weapon mix will depend on the particular conditions that exist at the time the decision is made to prepare weapons for launch The SCS is capable of processing a combination of land attack TCM variants for single or salvo launch from vertical missile tubes as well as a combination of land attack TCM variants Mk 48 Torpedoes and other defensive
244. mbly saddles restraint straps lifting eyes and forklift slots Lightweight plastic covers fore and aft are provided to cover the AURS during shipment or storage Pins secure the covers to the outer frame assembly Stacking posts are provided to permit stacking of containers 1 26 RECORD BOOKS 1 26 1 PEO W 4440 Record Book for TOMAHAWK Cruise Missile PEO W PUB 4440 is used to record data pertinent to the CLS Loading and Handling Trainer Shape Mk 3 Mod 0 as well as tactical and exercise CLS AURs Instructions for use forms completion and disposition are contained in PEO W INST 4440 2 and the record book 1 26 2 Record Book All Up Round AUR Simulator Volumetric Shape The AURS record book is used to record data pertinent to the AURS Data recording requirements are similar as those required for PEO W PUB 4440 Instructions for completing required records are contained in the record book 1 26 3 Record Book Missile Tube Ballast Can MTBC The ballast can record book is used to record data pertinent to the CLS ballast can Data recording requirements are similar as those required for PEO W PUB 4440 Instructions for completing required records are contained in the record book 1 27 WEIGHTS AND CENTERS OF GRAVITY Weights and centers of gravity of CLS variants and related material are contained in Tables 1 11 Weights of CLS Variants and Related Material and 1 12 Centers of Gravity for CLS Variants gt respectively
245. minated tape forms a separation line across the dome which extends between segments and the hemispheres of the polar cap This separates at launch to allow the missile to pass through unimpeded The diaphragm membrane is purposely weak along a diametrical line called the tear line Yet it is strong enough to withstand maximum external pressure at launch depth and maximum prelaunch internal over pressure Perpendicular to the membrane tear strip are two peel strips which initiate the tearing of the membrane to reduce the loads on the missile nose The ends of each peel strip are attached to under side of membrane at apex near tear line and to lower retaining ring Between attachment points two peel strips hang free As capsule is pressurized before launch the nylon cloth in the diaphragm allows diaphragm to stretch and grow slightly The fabric in the peel strips does not stretch because it is kevlar reinforced thus peel strips are 49 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 placed under tension This tension is transmitted to the apex of the tear line When launched the missile nose contacts the tear strips increasing tension until tearing of the membrane is initiated 1 23 1 3 Sabot CLS Mk 45 1 capsules containing UGM 109C D JUGM 109C D variant of the TCM with a Positive Retention Chine Nosecone have a sabot assembly installed between the nosecone and capsule closure assembly CCA The sabot is used to prevent damage
246. mit the WCC operator to monitor the selected tube and any alerts concerning launch The weapon launch control WLC operator in the torpedo room positions the designated tube weapon loaded switch to the assigned missile variant This action initiates alignment of torpedo room equipment to the selected weapon and allows verification in the attack center through displays on equipment indicators that the appropriate weapon is loaded in the tube If such verification can not be obtained the launch 15 recycled or aborted 4 5 2 1 When ordered FIRING ORDER and MAKE READY ORDERED are input by the attack control console ACC operator which permit other operator actions and equipment responses to commence in preparation for launch The mission disk pack is removed from secure storage and mounted on the random access storage set RASS The disk pack serial number 18 entered and the RASS is initialized 4 5 2 2 The WLC operator positions the designated tube weapon supply switch to POWER ON WEAPON READY indicators appear on the WCC ACC and WLC to reflect that the weapon is ready to receive commands A tube status check is again performed to verify readiness If WEAPON READY indicators are not obtained the launch is recycled or aborted 4 5 2 3 Positioning the weapon supply switch to POWER ON applies MONITOR RESET POWER to the PVC system and a PRESSURIZE indicator appears on the WLC Upon receipt of this indicator the ship 700 psi air isolation valv
247. n Table Specifics 23 1 8 3 4 Standard Inspection Procedures 2 0 00 0 24 SUDELVISOLBO T 24 13 3 0 Readetse e S d e b tea Med td a as 24 VET RENE 24 1 8 5 8 ODSet Vers it b eros Ee 24 1 3 c iot u te Tux 24 1 8 4 1 Philosophy and Scope 24 1 8 4 2 QA Functions and Responsibilities 04 440 25 1843 UP Stop POMS 2 usa gun ener a CO P EE D eee 25 1 8 5 Reference Documentation 5 23 1 8 6 Abbreviations and Acronyms 25 149 T 25 SECTION TOMAHAWK CRUISE 2 2 26 LIO GENERAT tite en tms PIA I alid e od Ra ated dtt 26 e Ma Ui da rutas 26 LAT ean Attack 109 A prio apod ihe 26 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 LATA Guidance Section uio ee Re Su ey sees Ee Inge sies 26 1 11 1 2 Forward Body Payload Section 40 0 0 02 26 1 11 1 3 Forward Body Fuel Section
248. n of operating procedures and checklists as well as actions to be taken under abnormal conditions refer to the appropriate volumes and parts of NAVSEA OD 44979 4 11 1 Weapon Preparation Preparation for launch commences with the authorization from the commanding officer He will issue the necessary make ready command for a single or salvo launch Based on that command the MAKE READY command is issued and the appropriate land attack weapon for the mission is selected To verify the correct missile has been selected and to permit weapon power up the Weapon Supply Switch is placed in the IDENT position Should a weapon conflict result from CM IDENT POWER application an ID ERROR will be displayed and all relays to the weapon will remain closed 4 11 2 Weapon Power Up and Make Ready When the correct designator is reflected the Missile Power keyswitch is placed in the ENABLE position and the Weapon Supply Switch is 220 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 moved from IDENT to ON This permits MONITOR RESET POWER and CAPSULE POWER to flow to the missile and CLS respectively so the SCS can transmit commands receive responses and open relay circuitry for missile OPERATE POWER Additionally activation of the switches permits the flow of REM BATTERY HEATER POWER to exercise weapons Weapon responses are monitored to ensure that BOOSTER SAFE and CAPSULE SAFE indicators show that the weapon is in a safe status If a BOOSTER ARMED or C
249. nce Equipage List Analog Filter Assembly Aft Flange Installation and Removal Tool Anti Jam Global Positioning System Receiver American National Standards Institute Fast Combat Support Ship Allowance Parts List Assistant Program Manager Logistics Submarine Tender Advanced Seal Delivery System American Society of Mechanical Engineers Ammunition Transaction Report All Up Round All Up Round Ballast Grade B All Up Round Electronic Simulator All Up Round Simulator All Up Round Volumetric Shape Alternator Voltage Control Converter Battle Damage Information Battle Damage Indication Imagery Built in Test Battery Power Unit Bend Radius 133 SW820 AP MMI 010 REVISION 15 ABBREVIATION ACRONYM BSTR BUS CAGE CAIMS CAL CATMIS CC A CCA CCC CCLS CCN CCS CCW CD CDS CHIL CHT CII CINCLANTFLTINST CINCPACFLTINST CL CLC CLF CLS CMA CMFR CMGS CMP CMP PUB 27 MARCH 2009 CHAPTER 1 DEFINITION Booster Bus Voltage Commercial and Government Entity Conventional Ammunition Integrated Management System Calibration Canister Asset Tracking Management Information System Combat Control Acoustics Set Capsule Closure Assembly Circuit Card Assembly Central Computer Complex Composite Capsule Launching System Certification Control Number Combat Control System Central Control Station Counter Clockwise Command Disable Command Disable System Center of Gravity Guided Missile Cruiser Consolidated Haza
250. nd waters 181 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 3 CHAPTER3 FUNCTIONAL DESCRIPTION SECTION I CHAPTER ORGANIZATION 3 1 SCOPE This chapter discusses functional descriptions of TOMAHAWK Cruise Missile components and systems as well as interfaces between the TCM and its launch platform Section II discusses the TCM electrical power system and type commands and requests for status issued to the TCM by the launch platform systems and TCM responses to those commands and requests for status which are in general common among all irrespective of launch platform Section III discusses unique interfaces between torpedo tube launch TCMs and the submarine Section IV discusses unique interfaces between Capsule Launching System CLS TCMs and the submarine Section V discusses unique interfaces between Vertical Launching System VLS TCMs and the surface ship 182 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 3 SECTION GENERAL 3 2 ELECTRICAL POWER SYSTEM The TCM electrical power system consists of a dc monitor reset power bus regulated bus semi regulated bus and a Cruise Missile Airframe bus a Mission Control Module bus a pyro bus and an arm battery activate bus 3 2 1 Prelaunch Electrical Power The launch platform s electrical power distribution system converts 3 phase 400 Hz delta power to 3 phase wye power to provide operating power for the missile provide single phase wye
251. ng the feasibility of loading operations To prevent damage to the missile ship or equipment it is recommended that weapons not be onloaded or offloaded if roll exceeds 3 degrees or pitch exceeds 1 2 degree and winds exceed 30 knots The submarine tender shore base loading supervisor and the submarine s commanding officer will determine if conditions are satisfactory prior to commencing onload Prior to onload the security system is neutralized for each missile tube to be loaded flood and drain system and pressure vent system operability are verified at the VLC and SCS operability is verified through operator conducted system diagnostics During loading responsibility for all operations 15 shared between the submarine s commanding officer and the submarine tender shore base loading supervisor actions involving ship system 213 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 preparation are the responsibility of the submarine s commanding officer His permission is required prior to commencing loading operations His designated representative is responsible for weapon handling operations and ensures that a weapon transfer inspection is conducted Upon completion of submarine preparation responsibility for loading transfers to the submarine tender shore base loading supervisor The submarine crew conducts the final hookup and closeout of the missile tube upon disconnect and removal of the loading equipment from the submarine The foll
252. nstalled in the upper shroud half to monitor differential pressure between the shroud cavity and the sea A pressure relief valve is installed in the lower shroud half to 35 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 prevent overpressurizing the missile Also installed in the lower shroud is an ac dc converter that converts ship wye power to dc to power the missile during prelaunch operations Linear shaped pyrotechnic charges assisted by leaf springs jettison the shroud halves following broach 1 12 EXERCISE VARIANTS The following paragraphs describe the components of the REM and RSS kit which may be installed for use in test and exercise flights of the TCM 1 12 1 Recovery Exercise Module Equipped Missile TCMs used for test and exercise flights and subsequent recovery reuse are equipped with a depot installed REM Figure 1 12 Recovery Exercise Module The compartmentalized REM body section replaces the 109A forward fuel tank section or the forward body payload section of the 109 TOMAHAWK variant housing assembly replaces the standard mission cover on the upper midbody The various REM compartments and equipment are described in the following paragraphs 1 12 1 1 Parachute Compartment The REM parachute compartment houses the main parachute pack and a drag parachute pack The compartment also contains the forward attachment fitting for the main parachute Y harness A jettisonable cover held by two pyrotechnic thrust
253. ntained in Tables 1 9 Weights of TTL Variants and Related Material and 1 10 Centers of Gravity for TTL Variants respectively 47 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 SECTION V CAPSULE LAUNCHING SYSTEM CONFIGURATION 1 22 AUR IDENTIFICATION Each tactical and exercise AUR is identified by a unique numeric six digit serial number The serial number for all configurations is located on a nameplate in the wing slot but is inaccessible to activities below depot level At the depot the AUR configuration and serial number are printed in the upper right hand corner of the Record Book for TOMAHAWK Cruise Missile TRB PEO W PUB 4440 which accompanies each AUR Additionally an MIS data plate is placed on the AUR and a matching data plate is placed in the TRB Activities below depot level verify AUR identity by comparing TRB data with data contained on two identification plates and two MIS data plates placed inboard and outboard on the upper end of the electrical umbilical 1 23 CAPSULE LAUNCHING SYSTEM MK 45 The Capsule Launching System CLS Mk 45 Figures 1 26 Capsule Launching System CLS Mk 45 and 1 27 Capsule Launching System CLS gt is a pressurizable cylindrical enclosure that encapsulates supports protects and launches a TOMAHAWK Cruise Missile There are two configurations of the CLS the Mk 45 Mod 1 and Mod 2 The Mk 45 Mod 1 is used on SSN class submarines In order to acc
254. o includes those ship systems necessary to stow and launch TCMs 1 3 MISSION The mission of the TWS 15 to provide theater and force commanders with a capability to use surface and sub surface platforms to employ either independently or in coordination with other strike capabilities highly accurate all weather TOMAHAWK Cruise Missiles TCM armed with a variety of highly destructive payloads against land targets at stand off ranges 1 4 ALL UP ROUND An AUR consists of a TCM installed in a capsule or canister configuration For a TTL AUR the separate pneumatic and electrical umbilicals are considered part of the AUR For horizontal submarine launch the depot installs an appropriately configured TCM into a Capsule Mk 1 Mod 0 for UGM 109A C D 1 or a Capsule Mk 3 Mod 0 for UGM 109E 1 For vertical submarine launch the depot installs an appropriately configured TCM into either a Capsule Launching System CLS Mk 45 Mod 1 SSN use only or a CLS Mk 45 Mod 2 CLS Mk 45 Mod 1 assemblies are being converted to the Mod 2 configuration which be used on both SSN and SSGN platforms For surface launch TCMs are encanistered at the depot into the Mk 10 Canister and then subsequently encanistered into the Mk 14 Canister at designated intermediate maintenance activities to permit surface vertical launch The capsules canisters provide protection during handling storage and transportation The capsules and Mk 14 Canister also serve as
255. oard sensors These sensors include the improved DSMAC IV system Radar Altimeter TERCOM System Inertial Measurement Unit Air Data Module GPS Subsystem and Anti Jam GPS Receiver During flight target relocation to alternate land targets may be selected by the Strike Controller through communications with the Satellite Data Link Transceiver The Block IV TACTOM has a loiter function used for post launch Time Of Arrival adjustments to ensure precise timing of diversionary and suppressive strikes In addition the Block IV TACTOM can be re targeted while enroute or in a loiter pattern The MCP is the central executive during all phases of the mission including flight control management and warhead detonation The Block IV TACTOM uses the existing WDU 36 B warhead thermal battery and many of the electro explosive devices used in other TOMAHAWK missiles However the composition of each of the body sections is considerably different from other TOMAHAWK configurations and is described in the following paragraphs 1 11 4 1 Forward Body Section The forward body section Figure 1 8 TACTOM Forward Body Section extends from Sta 0 00 to Sta 74 0 and consists of the nose and payload structure It provides the necessary brackets and configuration to support the WDU 36 B warhead Fuel is distributed throughout the entire missile including the forward section There is approximately 455 Ib of JP 10 fuel located in the forward section 1 11 4 2
256. ommodate the unique requirements of the SSGN launch platform Figure 1 41 SSGN Prototype Multiple All Up Round Canister gt the Mk 45 was redesigned to Mod 2 and will be used interchangeably between SSN SSGN platforms without the requirement for Intermediate Depot Level maintenance or reconfiguration All Mod 1 capsules will eventually be modified to Mod 2 Except for differences in the positioning of handling equipment necessitated by changes in the center of gravity between the two configurations CLS operations are the same for both configurations Paragraphs 1 23 1 through 1 23 1 13 describe the CLS Mk 45 Mod 1 paragraphs 1 23 2 through 1 23 2 12 describe the CLS Mk 45 Mod 2 1 23 1 CLS Mk 45 Mod 1 The CLS Mk 45 Mod 1 uses a filament wound composite capsule with titanium flanges mounted on each end for attaching CLS forward and aft components The CLS accepts a specified amount of reflood water after missile launch to preclude the necessity for a missile compensation system The Mk 45 Mod 1 configuration has a nominal weight of 2 121 pounds 1 23 1 1 Capsule The capsule is a tube 243 inches in length which forms the main structural member of the CLS The capsule increases in diameter from 24 inch at the aft end to 26 61 inches at the upper flange The capsule is sealed on the forward end by the capsule closure assembly and at the aft end by the aft closure assembly Within the capsule shell is mounting space for
257. ontains continuity shrouds The Block IV TACTOM has three fins vice four which are made of foam core sheet composite that deploy 134 degrees in approximately 0 25 seconds The fins are used by the vehicle to provide stability and control The cruise engine is started by means of a single pyrotechnic start cartridge The engine is controlled by an engine control module integrated in the air vehicle s mission control system and an in the loop fuel metering pump An alternator powers direct current sources which are used by the missile during cruise flight The engine is equipped with an Alternating Voltage Control and Converter AVCC The AVCC provides two sources of power and an engine speed signal to the missile The major features of the cruise engine include the Model XF415 WR 400 engine which includes an internal 4 kw alternator a separate power conditioner AVCC a single pyrotechnic start cartridge one ignition cartridge an exhaust extension and an exhaust extension thermal covering Fuel is distributed throughout the entire missile including the aftbody and tailcone section There is approximately 106 Ibs of JP 10 fuel located in the aft body The aftbody and tailcone section houses the majority of the electrical components for the entire missile The components contained within the aftbody and tailcone section are Air Data Module Alternator Voltage Control Converter AVCC 30 SW820 AP MMI 010 REVISION 15 27
258. or a composite material CLS If a CLS made of composite material is subjected to fire additional precautions must be taken as outlined below and summarized in Table 2 3 Pyrotechnic and Hazardous Materials Data 170 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 2 2 3 41 Composite materials composed of carbon graphite fibers present several hazards when subjected to fire explosion etc Carbon graphite fibers can be released into the atmosphere if their epoxy binder burns When subjected to temperatures of approximately 752 F 400 C the epoxy binder will ignite or decompose possibly releasing fiber material Once free the fibers can be transported up to several miles by air currents The fiber material is highly conductive and fibers can potentially damage electric electronic equipment Mechanical agitation especially an explosion can also fragment the composite causing fibers to become airborne 2 3 4 2 Fires should be extinguished with CO dry chemicals AFFF or water Special firefighting equipment such as Scott airpacks MSA s positive pressure self contained breathing apparatuses will be required Hazardous combustion by products may consist of carbon monoxide carbon dioxide acrolein phenols amines aldehydes aromatic amines hydrofluoric acid and fluoroboric acid 2 3 4 3 Personnel should wear protective clothing such as a Disposable coveralls and shoe covers b Gloves preferably with leather palms c Safety gl
259. or the gas generator mechanism and electrical components The umbilical cable attaches to a through connector which is installed in the aft closure assembly The cable is unbonded 24 1 inches forward of the end of the composite capsule The capsule has a stripe at the expended capsule CG location 1 23 1 2 Capsule Closure Assembly The capsule closure assembly is attached to the flange at the upper end of the capsule The closure consists of a nylon cloth reinforced rubber diaphragm with an internal stainless steel band around the outer edge a low permeance mylar dome installed over the diaphragm and an upper and lower retaining ring A diaphragm bead is clamped between the two retaining rings in a compression fit to form a seal between the rings A barrier flange is adhesively bonded to the bottom of the upper closure ring The rings are bolted together Bolts pass through both rings to attach the closure to the capsule An O ring fits in a groove in the capsule forward flange and provides an air tight seal between the closure assembly and the capsule upper flange while in the missile tube The rings also provide mounting for the pressure sensing line The low permeance dome is made up of six triangular sections a flange section and a split polar cap assembled with a foil laminate tape The dome material is a three layer laminate of mylar tin foil and mylar MTM The tin foil makes the dome nearly impermeable to water vapor The foil la
260. ossible explosion This violent reaction can also be caused by water entering the battery through a rupture in the case Extreme care shall be used when disconnecting the active lithium batteries to prevent the leads from shorting Cease all operations and notify Explosive Ordnance Disposal EOD if a ruptured or crushed lithium battery is observed Do not spray water into the REM compartment during missile washdown or decontamination operations 177 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 2 Table 2 2 Storage and Hazard Data Q D CLASS 1 1 DOT HAZARD MARKING ROCKET AMMUNITION W EXPLOSIVE PROJECTILE UN ID No UN0397 RGM UGM 109C w WDU 25 B WDU 36 B Warhead Rocket Motor Mk 106 Mod 0 Mk 111 Mod 0 and Liquid Sustainer Engine Land Attack Conventional JRGM JUGM 109C W w WDU 25 B WDU 36 B Warhead RSS Rocket Motor Mk 106 Mod 0 Mk 111 Mod 0 and Liquid Sustainer Engine Land Attack Conventional Exercise RGM UGM 109D w BLU 97 B Payload Module Kit 001 002 Rocket Motor Mk 106 Mod 0 Mk 111 Mod 0 and Liquid Sustainer Engine Land Attack Conventional Submunition JRGM UGM 109D W w BLU 97 B Payload Module Kit 003 004 RSS Rocket Motor Mk 111 Mod 0 and Liquid Sustainer Engine Land Attack Conventional Submunitions Exercise RGM UGM 109E w WDU 36 B Warhead Rocket Motor Mk 135 Mod 0 and Liquid Sustainer Engine Land Attack Conventional Q D CLASS 1 3 DOT HAZARD MARKING ROCKET MOTOR CLASS B EXPLOSIVE UN ID No all UN0396
261. ough the REM RSS Before the MISSILE ENABLED signal can be sent the REM RSS must first pass all REM RSS BIT s and issue a REM RSS ENABLED to complete the circuit 3 7 9 Differential Pressure TTL only Because encapsulated TTL 5 are subjected to pressure differences when in a flooded torpedo tube prior to launch two dc signals A and B are provided by the missile dual differential pressure transducer to indicate differential pressure between the shroud compartment and ambient outside pressure The redundant signals which are derived from DC MONITOR RESET POWER are used to monitor the missile pressure and provide a PRESSURE IN BAND signal 188 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 3 SECTION III TORPEDO TUBE LAUNCH 3 8 GENERAL This section discusses launch platform and TCM physical and functional interfaces aboard the submarine These interfaces include missile capsule and torpedo tube physical interfaces as well as the submarine systems utilized to a Maintain pressure in TCMs during preparation for launch b Secure and prevent unauthorized launch of the UGM 109A 1 c Compute TCM attack solutions 3 9 MISSILE CAPSULE AND TORPEDO TUBE PHYSICAL INTERFACES The missile capsule and torpedo tube physical interfaces consist of the mechanical electrical and pneumatic interfaces described in the following paragraphs 3 9 1 Mechanical Interfaces The mechanical interfaces consist of the following restraining devic
262. owing paragraphs provide a general overview of procedures used during loading operations For purposes of illustration loading of a generic weapon into one missile tube is discussed There are some minor differences in loading procedures among AURs AUR Simulator Volumetric Shapes and ballast cans which are not discussed For multiple loadings the procedures are the same except that multiple actions may be occurring simultaneously to prepare missile tubes and weapons Additionally loading equipment is moved from missile tube to missile tube until the full complement of weapons is aboard the submarine Similarly post loadout is accomplished on a tube by tube basis until full closeout is accomplished Onload terminates when the submarine has received its scheduled complement final hookup has been accomplished all loading equipment has been removed missile tube hatches are closed and secured and ship system equipment has been activated 4 9 1 1 Prepare Missile Tube and Ship Systems After supporting submarine tender shore base personnel have erected the loading platform Figure 4 15 Loading Platform Installed submarine personnel prepare the missile tube and ship systems for onload The missile tube hatch is opened and gagged Figure 4 16 SSN 688 Class Submarine Missile Tube Equipment and the missile tube is visually inspected to ensure it is free of potential contaminants Contaminants if present will damage the lip seal on an AU
263. per shipping nut the electrical connector access opening and the lanyard attachment on the barrel closure The pneumatic coupling protective cover covers the capsule pneumatic coupling Captive thumbscrews attach the protective covers to the barrel closure The electrical connector access protective cover is replaced with a security plate after loading aboard the submarine UGM 109A 1 only The plate and or cover s must be removed to permit connection of umbilicals to the missile prior to launch 1 16 2 Capsule Mk 3 Mod 0 The UGM 109E 1 is protected by the Capsule Mk 3 Mod 0 Figure 1 23 TTL Capsules 2 Sheets measuring 248 17 inches long including the nose cover and loading button by 20 97 inches in diameter Capsule components are described in the following paragraphs 1 16 2 1 Nose Cover The capsule nose cover which is made of forged aluminum alloy protects the capsule nose diaphragm and the nose of the missile during stowage and handling Each cover measures 14 48 inches long by 20 95 inches in diameter The nose cover weighs about 27 pounds 43 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Attachment to the capsule barrel is provided by seven screws The cover uppermost screw hole is stenciled TOP to indicate the proper position for installation The Mk 3 Mod 0 nose cover has the words BLOCK IV stenciled to distinguish it from the Mk 1 Mod 0 capsule nose cover The nose cover must be removed prior to launch The TCM must
264. perations and is determined by the person in charge of the evolution Illustrations supporting an event are considered typical Deviation from depicted events 15 allowed under the same guidelines used when deviating from procedural text Referral to the OP during the evolution is mandatory and status of steps accomplishment shall be appropriately indicated by a physical checkoff of the OP steps or N A type indication The Reader Worker Method is not mandatory but is recommended When not using Reader Worker Method reading aloud or making oral reports at end of each step is not required The terms as required as necessary etc indicate a choice of action is required within the step usually as a result of actions taken within the step such as test results presence of varying conditions etc 1 8 3 3 Inspection Table Specifics Some OPs contain Inspection Tables to be used as references during the performance of the OP steps These tables list the specific items and features to be inspected describe unacceptable conditions for these items and prescribe a disposition for items which are not acceptable An Inspection Table has four columns with headings of Inspection Point Inspection Criteria Action and Check Off The Inspection Point column identifies the specific item or subassembly being examined Inspection Criteria describes the particular conditions or items to be assessed at the Inspection Point The Action column indicates 23 S
265. pical mission is divided into six phases prelaunch launch boost transition to cruise cruise and either a terminal phase for 109A C Block IV Figure 1 19 Typical Mission Profile 109 gt or a target attack phase for 109D Figure 1 20 Typical Mission Profile 1090 gt A REM equipped missile also includes a seventh or recovery phase in which the REM equipped missile instead of detonating a warhead continues on to a pre determined recovery site Typical mission profiles are described as having either a lo lo and hi lo penetration of the general target area Maximum protection from detection is provided by a lo lo penetration A hi lo penetration provides maximum range The missile is programmed to fly at a specific altitude and speed which may or may not include a terminal maneuver prior to warhead detonation Flight path altitude also depends on the roughness of terrain evasive maneuvers to avoid enemy defenses and climb and dive rates of the missile The various mission phases are described in the following paragraphs 1 14 1 Prelaunch Phase The prelaunch phase begins with the decision to launch a TOMAHAWK Cruise Missile against a predetermined land target It covers preparation of the missile and launching device weapon power up guidance set initialization and alignment and loading target data The prelaunch phase is described in detail in Chapter 4 for each launch configuration 1 14 2 Launch Phase Following the closing of
266. port Safe Working Load Special Weapons Ordnance Publication Test and Evaluation Tactical TOMAHAWK Ammunition Ship Military SEALIFT TOMAHAWK AUR Logistics and Maintenance Technical Information Products Track Control Group TOMAHAWK Cruise Missile Temperature Terrain Contour Matching Technical Feedback Report Target 144 SW820 AP MMI 010 REVISION 15 ABBREVIATION ACRONYM TLAM TMDER TMIS TMPS TNT TOA tol TOMFISH TOMIS TOT TOTEM TR TRB TRNR TRS TRT TSN TTE TVC TWCS TWS TYCOM UBOB UIC ULSS UOC UR IR URL UWARS 27 MARCH 2009 CHAPTER 1 DEFINITION Land Attack TOMAHAWK Missile Technical Manual Deficiency Evaluation Report Torpedo Management Information System Theater Mission Planning System Trinitrotoluene Time of Arrival Tolerance TOMAHAWK Fitment Shape TOMAHAWK Management Information System Time On Target TOMAHAWK Test Missile Trainer 1 Warhead Installation Trainer TR1001 Record Book for TOMAHAWK Cruise Missile PEO W PUB 4440 Trainer Technical Repair Standard Tensioner Rigging Tool TOMAHAWK Strike Network Torpedo Tube Launched Thrust Vector Control TOMAHAWK Weapon Control System TOMAHAWK Weapons System Tactical Weapons Simulator Type Commander Umbilical Breakout Box Unit Identification Code User s Logistics Support Summary Usable on Code Unsatisfactory Information Report Uniform Resource Locator Universal Restraint Stands 145 SW820 AP MMI
267. position by spring tension In the safe position the safe arm indicator plate will not complete the electrical circuit to the bridgewires and ARM monitor which are necessary for rocket motor ignition It also prevents the proper alignment of the barrier slots with the poppet slots and consequently prevents a vent path for the initiator output to reach the igniter and subsequent rocket motor ignition The Mk 111 Rocket Motor will remain in SAFE position until such time as the BOOSTER ARM command is received The Mk 111 Rocket Motor arming firing device cannot be manually safed 3 6 2 Booster Arm Command The BOOSTER ARM command is a dc signal that places the rocket motor in the ARMED position 3 6 2 1 Mk 106 Rocket Motor For the Mk 106 Rocket Motor the BOOSTER ARM command removes the physical barrier between the igniter initiators and propellant igniter to arm the rocket motor 3 6 2 2 Mk 111 Rocket Motor For the Mk 111 Rocket Motor BOOSTER ARM command is sent to the solenoid rotor of the arming firing device The energized rotor causes the safe arm indicator plate to rotate which in turn moves the sweep contacts on the switch plate assembly to complete the electrical circuit to the pyros and aligns the barrier slots to allow initiator output to reach the igniter explosive thereby arming the rocket motor 3 6 3 Warhead Safe Control Command 109A only The WARHEAD SAFE control command is a dc signal that sets the warhead to the safe cond
268. propellant 298 gm Igniter mix IB 43 and Boron potassium nitrate 17 5 gm Zirconium potassium perchlorate 65 mg and Titanium hydride potassium perchlorate 220 mg Zirconium potassium perchlorate 65 mg and Titanium hydride potassium perchlorate 220 mg Hercules Hi Temp Boron Calcium Chlorate Tellurium Dioxide Viton B 285 gm 1 3C Main Charge Talley TAL 11 0g 1526 HTB Enhanced Thiokol 2D 140 mg Pellet Equivalent to MIL P 46994A 11B Pellet Iron sulfide lithium fluoride potassium chloride lithium bromide magnesium oxide Iron powder MH 100 and NH 100 Cab O Sil potassium perchlorate NOTE Refer to SW020 AC SAF 010 020 030 for Net Explosive Weights COMPOSITE CLS HAZARD INFORMATION Composite materials in the Composite CLS are reinforced with carbon graphite fibers to provide stiffness high strength to weight ratio and ease of fabrication Carbon graphite fibers can be released into the atmosphere if their epoxy binder burns approximately 752 degrees F 400 degrees C will cause epoxy binder to ignite or decompose Once free the small lightweight fibers can be transported up to several miles by air currents Because of their high electrical conductivity they can damage unprotected electrical electronic equipment Similarly mechanical agitation especially an explosion can fragment the composite and cause fibers to become airborne EXTINGUISHING AGENTS Carbon dioxide dry chemical AFFF water SPEC
269. r 183 327 3 Heater Power 183 3 2 1 4 Monitor Reset Power 2 21 00 183 3 2 1 5 DC Monitor Reset Power Return 2 0 0 0 183 3 2 1 6 Chassis Std te Ground RR SERES 183 3 2 2 Launch Boost Electrical Power 183 3 2 2 1 CMA Battery u eX oec do Ea eR ai yas SER NR 184 3 2 2 2 CMGS Battery Activation 184 3 2 2 3 REM Battery Activation 184 212 24 Bus Isolation as 184 3 2 2 9 Fits MOLIOD 122215 cte dnd in nek 184 3 2 3 Cruise Electrical Power 184 3 2 4 RSS Thermal Battery Activation 185 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 3 3 DIGITAL DATA LINK rueda e e e o PERDE RR RO edu 185 3 4 DIGITAL COMMANDS DATA BLOCKS SENT TO A LAND ATTACK 185 3 4 1 Bootstrap Load Program 12599 1 etes eet TI ARE 185 3 AD Request Status 185 544 3 Alienment Data ns rt into e GRE Re aee STR S 186 SA Ac MiSSion Data d Vm 186 JAD Battery Activate
270. r P N LHH 2B 15 MTEL Hydraulic Power Unit With MTEL provides insertion and HPU Mk 8 Mod 0 extraction force to seat unseat CLS P N JCM 14899 001 weapons except ballast can into out of the missile tube MAC cell Installation Guide Mk 116 Align MTEL to prevent missile tube Mod 0 damage during MTEL installation and P N JCM 14375 001 removal Kit Pressure Servicing Pressurize TTL and Mk 10 weapons Mk 182 Mod 0 P N 5759440 Kit Pressure Servicing Pressurize CLS AUR and CLS Loading CLS Forward Mk 184 and Handling Training Shape forward Mod 0 section P N 6199900 Consists of 111 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 EQUIPMENT FUNCTION Closure Pressure Hose Pneumatic Adapter P N 6146684 CPC Pneumatic Adapter P N 6199896 Pressurizing Gear Tester T3159 P N 5545882 CLS Pressurizing Hose Assembly FWD P N 6146623 CHAPTER 1 Lifting Adapter Assembly Attaches to CLS weapon except Mk 169 Mod 0 ballast can to upright lift or lower P N JCM 14699 001 CLS weapon during submarine onload off load Missile Tube Aligns and with HPU inserts extracts Extension Loader CLS weapon except ballast can MTEL Mk 23 Mod into out of missile tube MAC cell 1 P N JCM 14455 002 Multi Test Box Mk 71 Verify electrical continuity and isolation Mod 0 of specific wires in the pyro harness P N 6574418 112 ILLUSTRATION SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 EQUIP
271. ration also includes ablative blocks and burn through protection plates that are affixed to the aft end of the canister to protect against canister sidewall burn through during a restrained firing 1 30 INERT VARIANTS The paragraphs below discuss certification training and other inert variants provided to Fleet and shorebase operational and support activities to conduct training maintain technical proficiency and complete personnel crew and ship certifications 59 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 1 30 1 Canister Trainer Mk 17 The Mk 17 Canister is an inert facsimile of the Mk 10 Canister used to train personnel to handle RGM 109 2 variants and the Mk 10 Canister 1 30 2 Mk 14 Canister Trainer The Mk 14 Canister Trainer 15 an inert unit used to train personnel to handle the Mk 14 Mod 1 2 Canister and to encanister and decanister RGM 109 2 variants using the Mk 17 Trainer 1 31 RECORD BOOK PEO W PUB 4440 Record Book for the TOMAHAWK Cruise Missile is used to record data pertinent to the RGM 109 2 variant and the VLS AUR Instructions for use forms completion and disposition are contained in PEO W INST 4440 2 and the record book PEO W PUB 4440 is not used to record data applicable to the Mk 14 Canister without an encanistered RGM 109 2 variant 1 32 WEIGHTS AND CENTERS OF GRAVITY Weights and centers of gravity of RGM 109 2 variants and related material are contained in Tables 1 13 Weights of RGM 109
272. rdous Items List Collection Holding and Transfer Configuration Item Identifier Commander in Chief Atlantic Fleet Instructions Commander in Chief Pacific Fleet Instructions Checklist Capsule Loading Cover Combat Logistics Force Capsule Launching System Cruise Missile Airframe Cruise Missile Feedback Report Cruise Missile Guidance Set Cruise Missile Project Cruise Missiles and Joint Unmanned Aerial Vehicles Publication 134 SW820 AP MMI 010 REVISION 15 ABBREVIATION ACRONYM CMPINST CMTS CNTT COE COSAL COSBAL COTS TOTEM CPC CPSL CRF CRPA CRS CSAS CSES CTS CW DAMA DCASPRO DCM DCP DDG DDS DECAN DECAP DIU DIUE DIUR DLS DMINS 27 MARCH 2009 CHAPTER 1 DEFINITION Cruise Missiles and Joint Unmanned Aerial Vehicles Instruction Combined Missile Test Set Chief Naval Technical Training Certificate of Equivalency Coordinated Shipboard Allowance List Coordinated Shorebase Allowance List Commercial Off The Shelf TOMAHAWK Test Missile Closure Protective Cover Capsule Container Repair Facility Controllable Radiation Pattern Antenna Corrosion Resistant Steel Configuration Status Accounting System Canister Safe Enable Switch Combat System Electronic Space Crew Training Shape Clockwise Demand Assigned Multiple Access Defense Contract Administration Services Procurement Office DC DC Converter Module DSMAC Control Processor Guided Missile Destroyer Dry Dock Shelter Decanister
273. ring launch The design of the elastomeric pads provides necessary lateral support and protects the missile from shock and vibration In this function the lateral support group acts in concert with the interface support pads which are bonded to the exterior of the capsule and capsule extension The lateral support group also serves to provide in tube guidance for the missile during launch 1 23 1 5 Launch Seals There are six circumferential launch seals adjacent to the bands of liner pads which are bonded to the inner surface of the capsule The seals have a projecting lip which bears against the surface of the missile The surface of the seal lip which contacts the missile surface is coated with Teflon to minimize friction Also the Teflon coating eliminates seal lip inversion Seal lip inversion may result from upward forces acting upon lip from launch gas pressure under the lip and from missile motion against the lip During launch the launch seals minimize gas pressure buildup in the space between the capsule inner wall and the missile skin The seals also enhance eject performance by minimizing gas leakage from the volume pressurized by the gas generator By reducing asymmetric pressure forces during the in tube travel of the missile the seals serve to reduce launch vibrations Holes spaced around the circumference of the seal lip allow air to flow between the compartments during capsule pressurization 50 SW820 AP MMI 010 REVISION 15 27
274. rity of the UGM 109A 1 is maintained by connecting the missile to the submarine 4FZ Security Alarm System using a special security plate The security plate is a kidney shaped plate that replaces the electrical connector access protective cover and covers the pull switch lanyard attachment the electrical umbilical connection and the upper holdback assembly on the aft end of the capsule It is held in place by two captive thumbscrews that are lockwired together to provide visual evidence of any tampering A pneumatic coupling is installed in the plate to provide a connection to the 4FZ Security Alarm System The security plate is provided separately and is installed after weapon shipping aboard the submarine and replaced by the electrical connector access protective cover prior to weapon unshipping 3 12 NAVIGATION SYSTEM Navigation and ownship parameter data are used in computing attack control solutions Data include latitude longitude velocity heading pitch roll and depth computations Except for navigation equipment digital data input data are supplied as either synchro or event data and are converted to digital data for use by the submarine computer equipment 3 12 1 Navigation Equipment Alignment Computer equipment through closed loop control maintains true vertical alignment of navigation equipment stable platforms by collecting velocity data from the velocity meters and using these data to provide torquing pulses to the gimbal mounted
275. rotection Devices Submarine launch variants employ underwater protection devices consisting of two wing slot plugs an engine inlet cover and a continuity shroud Figure 1 11 Underwater Protection gt The devices are described in following paragraphs 1 11 7 2 1 Wing Slot Plugs Jettisonable wing slot plugs cover the wing cutouts on each side of the missile to prevent the entry of seawater during underwater launch Each consists of a plug that is shaped to fit the wing cutout an integral vent valve and a pyrotechnic thruster The thruster which also attaches to the wing pivot fitting provides the means to jettison the plug The vent valves prevent possible structural damage due to overpressure by venting the through slot cavity pressure during underwater ascent The wing slot plugs are jettisoned immediately following broach 1 11 7 2 2 Engine Inlet Cover An engine inlet cover is installed on underside of the missile to cover the inlet cavity and prevent the entry of seawater during underwater launch The cover includes seven vent valves and two vent holes to vent the engine inlet and propulsion section cavities during underwater ascent The cover is jettisoned by pyrotechnic thruster immediately following broach 1 11 7 2 3 Continuity Shroud The continuity shroud consists of two shroud halves that bolt together to form a watertight closure around the propulsion section A dual differential pressure transducer is i
276. rpedo Tubes and Weapons Handling Systems Interface Manual TOMAHAWK Cruise Missile UGM 109 1 Intermediate Level Activity Handling and Stowage TOMAHAWK Cruise Missile UGM 109 2 Intermediate Level Activity Handling Loading and Stowage TOMAHAWK Vertical Launch All Up Rounds Handling and Stowage Aboard AS 39 Class TOMAHAWK Support and Test Equipment Description Maintenance and Repair Parts Breakdown RPB TOMAHAWK Support and Test Equipment Description Maintenance and Repair Parts Breakdown RPB Vertical Launch System Submarine Launch VLS SSN Support Equipment TOMAHAWK Cruise Missile System Description TOMAHAWK Cruise Missile General Handling Procedures TOMAHAWK Cruise Missile Maintenance Procedures TOMAHAWK Cruise Missile UGM 109A 1 Warhead Installation Removal and Air Vehicle Maintenance TOMAHAWK Cruise Missile Recovery Procedures Recovery Exercise Module REM Configurations TOMAHAWK Test Vehicles Description Operation Maintenance and Repair Parts Breakdown RPB TOMAHAWK Test Missile TOTEM UTM 109 1 TOMAHAWK Test Vehicles Description Operation Maintenance and Repair Parts Breakdown RPB TOMAHAWK Crew Training Shape CTS UTM 109 1A TOMAHAWK Test Vehicles Employment Procedures 130 SW820 AP MMI 010 REVISION 15 DOCUMENT NUMBER SW850 EA MMM 060 SW850 EB MMM 010 TOMFISH SW850 FA MMM 010 WIT MK 35 SWOP 0 1 SWOP 0 1B SWOP 4 1 SWOP 5 8 SWOP 20 5 SWOP 20 7 SWOP 20 11 SWOP 45 51 SWOP 4
277. rs Activation of batteries is described in the following paragraphs 3 2 2 1 Battery Activation When the launch operator sets the switch to FIRE Intent to Launch ITL DC power is routed to the coil of the ARM BATTERY ACTIVATE BUS relay The relay energizes and applies CMA bus power to the ARM BATTERY ACTIVATE bus Upon CMGS command the CMA BATTERY ACTIVATE relay energizes and fires the battery pyros to activate the battery Output 1 powers the MCM and CMA buses Output 2 powers the SEMI REGULATED bus which in turn supplies power to the fin servoactuators 3 2 2 2 CMGS Battery Activation The battery output 15 sensed by the When the specified voltage is attained CMA BATTERY GO signal is sent to the CMGS Upon CMGS command the CMGS BATTERY ACTIVATE relay energizes and applies power to fire the CMGS battery pyros Battery output 15 applied to the CMGS subsystems and the REGULATED bus 3 2 2 3 REM Battery Activation To allow time to activate the REM batteries and perform REM BIT about 29 seconds are added between ITL and CMA battery activation REM battery activation begins when the REM ACTIVATE command is issued by the CMGS after receipt of ITL BATTERY ACTIVATE power is provided by the ARM BATTERY ACTIVATE bus Upon receipt of REM ACTIVATE the REM performs a pre battery activate BIT If REM BIT fails the REM will not issue the REM ENABLE command and as a result the MISSILE ENABLED signal will not be sent If B
278. s MISCELLANEOUS SABOT Closure Protective Cover CPC Mk 19 Capsule Loading Cover CLC Clamp Ring Forward Capsule Support Adapter Mk 168 CLS Uprighting Fixture Mk 26 Lifting Adapter Mk 169 Lifting Adapter Extension Missile Tube Extension Loader MTEL Mk 23 MTEL Adapter Container Shipping Storage MTEL Adapter Lifting Adapter Extension Loaded Platform Loaded A 162 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 MAX HANDLING MAX HANDLING WEIGHT POUNDS WEIGHT KILOGRAMS SSN 688 Class Loading Platform 5SN 774 Class Loading Pao AUR handling weights calculated using heaviest components plus a small safety factor ncludes approximately 86 gallons 325 liters of water 163 SW820 AP MMI 010 REVISION 15 CHAPTER 1 Table 1 12 Centers of Gravity for CLS Variants ITEM TACTICAL AUR UGM 109C 2 UGM 109D 2 UGM 109E 2 EXERCISE AUR JUGM 109C 2 M JUGM 109C 2 S W JUGM 109D 2 S W JUGM 109E 2 S W CAPSULE LAUNCHER SPENT CLS OTHER AUR SIMULATOR SHIP SKID LOADED AUR SIMULATOR SHIP SKID EMPTY AUR SIMULATOR VOLUMETRIC SHAPE w AURES AUR SIMULATOR VOLUMETRIC SHAPE w o AURES AURBb MISSILE TUBE BALLAST CAN CLS LOADING AND HANDLING TRAINING SHAPE CENTER OF GRAVITY INCHES CLS MK 45 1 2 126 6 127 6 127 6 133 132 132 143 163 6 CENTER OF GRAVITY INCHES 141 160 153 155 122 5 1 0
279. s Unit GEU 32 1 11 4 3 10 Mission Control Input Output 2 0 100 32 1 11 4 3 11 Mission Control Processor 32 1 11 4 3 12 Navigation Processor NP 32 1 11 4 3 13 Power Filter Unit PFU 33 1 11 4 3 14 Pyro and Power Control Assembly PPCA 33 1 11 4 3 15 Radar Altimeter RA 33 1 11 4 3 16 Satellite Data Link SDL Antenna 33 1 11 4 3 17 Satellite Communications SATCOM Data Link Terminal 33 1 11 4 3 18 Secondary Power Unit SPU 33 1 11 5 TCM Body Sections Common to 109A C D 33 1 11 5 1 Midbody 33 ATE BOdY Section be a E S RN SUM 34 1 11 5 3 Propulsion Section 34 1 11 6 Rocket Motor Assemblies tre nn be ree a ax 34 1 11 6 1 Mk 106 Mod 0 Rocket Motor 222 34 1 11 6 2 Mk 111 Mod 0 Rocket Motor 0 00 34 1 11 6 3 Mk 135 Rocket Motor Assembly 21 0 0002 35 1 11 7 Components Common to 109A C D 20 022 35 1 11 1 Missile Retent
280. s are used to launch STANDARD missiles and VLA Prime consideration for selecting a specific weapon for launch should be the time required to prepare and launch a single TCM Additionally the VLS will neither select a TCM in a module with a launch in progress nor suspend a launch in progress in order to support a TCM launch 4 17 2 Weapon Availability Various factors are used by the VLS to verify that a particular TCM is available for selection These factors summarize missile cell and module status conditions A particular missile is available for selection if no availability factor applies If any factor does apply the missile may still be available 1f the factor can be overridden Table 4 1 Missile Availability Factors identifies availability factors and the capability for override 4 18 LAND ATTACK OPERATIONAL SEQUENCE This paragraph describes typical actions and responses required to launch a land attack TCM Primary coverage is given to normal launch of a single weapon For multiple launch the operational steps for a single launch are sequentially accomplished for each weapon selected for launch Abnormal launch conditions and abort procedures are discussed by highlighting only those events that differ from a normal launch Typical launch operations are shown in Figure 4 32 RGM 109 4 Land Attack Operational Sequence 15 Sheets The figure illustrates the orders given by the ship s commanding officer typical
281. s can be disregarded Non selected steps should be appropriately marked i e N A Selected steps should be accomplished in the sequence listed unless a deviation has been authorized by the Weapons Officer Weapons Repair Officer Civilian Counterpart When deviating from the listed sequence and or illustrations the Weapons Officer Weapons Repair Officer Civilian Counterpart must evaluate the broad task to ensure that the deviation is both safe and correct Referral to the PG during the evolution is mandatory and status of steps accomplishment shall be indicated by a physical check off of PG steps or N A type indication The Reader Worker Method is not mandatory but is recommended When not using the Reader Worker Method reading aloud or making oral reports at the end of each step 15 not required terms as required as necessary etc indicate a choice of action is required within the step usually as a result of actions taken within the step such as test results presence of varying conditions etc 1 8 3 2 Operating Procedures OPs are used where the rigid method required for Checklists is not necessary and where specific tasks may be completed in other than the listed sequence OPs may include steps which refer to other procedures and documents when it is not practical to include all the required steps in one procedure Steps may be performed in any correct sequence or concurrently A correct sequence results in safe and reliable o
282. s until Mode 3 aligned is reported At that point the FCS issues the Booster Arm and the Intent to Launch ITL commands Once the ITL is issued responsibility for aborting the launch passes from the FCS to the missile Next the FCS issues a Terminate Alignment to the missile which causes the Mission Control Processor to command the navigation processor into Navigate mode The then initiates the rocket motor thrust vector control and fin control system The cruise missile airframe battery is also enabled 223 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Before the MCP issues the Enable Missile command it performs several initial status checks including a status update from the navigation processor and verification of proper GPS load data 4 14 2 Launch Sequence The Block IV TACTOM Missile launch sequence from application of Intent To Launch ITL to wing deployment includes discrete signals from missile removal of launcher power digital interface deadfacing gas generator ignition first motion booster ignition deployment of fins and wings rocket motor jettison and engine start up The missile launch sequence begins upon transmission of Firing Command ITL by the launch platform to the missile The ITL and subsequent sequence results in missile battery activation transition from platform power to internal missile power execution of missile Built In Test and the subsequent return of Missile Enable
283. ses to those commands and requests for status Section discusses unique interfaces between TTL and the submarine Section IV discusses unique interfaces between CLS and the submarine Section V discusses unique interfaces between VLS and the surface ship 1 1 4 Chapter 4 Chapter 4 discusses TWS operations aboard launch platforms to include a description of the launch platform and on board equipment used to load store and launch TCMs TCM onload scenarios and launch operations Section I provides an outline of the organization and content of the chapter Section II discusses TTL unique operations Section III discusses CLS unique operations Section IV discusses VLS unique operations 19 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 SECTION TOMAHAWK WEAPON SYSTEM 1 2 TWS DESCRIPTION The TWS consists of the submarine TTL system employed aboard SSN 688 SSN 21 and SSN 774 Class submarines the submarine CLS employed aboard selected SSN 688 Class submarines SSN 774 Class submarines and SSGN Class submarines and the surface VLS employed aboard DD 963 Class CG 47 Class and DDG 51 Class ships Each system employs a unique All Up Round AUR configuration to launch In addition to tactical TCM variants each system also includes applicable exercise certification and training variants as well as related support test handling and training equipment Within the broad definition each system als
284. space is accomplished via athwartship transfer mechanisms vertical hoist s pivot mechanisms trays and loading rammers 4 3 WEAPON ONLOAD The supporting submarine tender or shore base removes the weapon from its shipping container and places the weapon on the topside skid SSN 688 Class Subsequent actions to lower the weapon to the torpedo room are depicted in Figure 4 5 TTL Weapon Shipping Handling and Stowage Equipment SSN 688 Class for SSN 688 Class submarines Weapon onload is performed in accordance with applicable volumes and parts of NAVSEA OD 44979 4 4 OPERATIONAL CONSTRAINTS RESTRICTIONS Tactical employment of a TCM may impose constraints on the operating parameters of the submarine and restrictions on the submarine s tactical flexibility The following paragraphs identify the different constraints and methods of alerting the ship s commanding officer to an operational constraint or restriction 4 41 Launch Constraints The launch constraints imposed on the operational parameters of the submarine during employment of tactical and exercise variants are described in the applicable tactical employment manuals 4 4 2 Weapon Mix Weapon mix will depend on the particular conditions that exist at the time the decision is made to load torpedo tubes The SCS is capable of processing a combination of TOMAHAWK variants Mk 48 Torpedoes and other defensive systems Prime consideration for specific weapon mix is the time required
285. ssembly Protective Protect O rings on CLS weapon Sleeve O ring P N 101 5951066 4 5 50 6 SSN 688 P N 7066384 71 SSN 774 Band CLS Used with Taglines Mk 4 Mod 0 to TOMAHAWK Mk 90 maintain control of uncontainerized Mod 0 CLS weapons P N 5167268 Band Mk 87 Mod 0 Used with Taglines Mk 3 Mod 0 to P N 5166711 maintain control of uncontainerized TTL and Mk 10 weapons Beam Hoisting AUR Handle containerized TTL and Mk 10 Container Mk 46 weapons P N 5167804 Beam Lifting MK 44 Handle uncontainerized TTL and Mk Mod 0 10 weapons P N 5167164 Cable Adapter Umbilical Used with Rocket Motor Ident Test Set ASSy Box Assembly for performing TTL P N 3193140 028 missile electrical checks 101 Cable Adapter Umbilical Used with Rocket Motor Ident Test Set ASSy Box Assembly for performing TTL P N 3193140 missile electrical checks 028 102 Conventional Use Only 106 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 EQUIPMENT FUNCTION ILLUSTRATION Cable Assy Used with Rocket Motor Ident Test Set _ P N 3193140 013 Box Assembly for performing missile 82 101 electrical checks Canister Loader VLS Encanister decanister VLS weapons 33 Mod 0 P N 5167196 Cap Faraday Upper Provides electrical shielding for the Umbilical Connector electrical umbilical connector on CLS P N 14339 001 AUR and CLS Loading and Handling Training Shape Container Closure Protects the CLS AUR and CLS Sh
286. ssile H amp S Sent to controller to report missile location current mission outcome and status of selected missile subsystems H amp S messages may be prescheduled triggered by events or in response to a request by the controller Battle Damage Information This is an H amp S message that also contains an estimate of navigation error at the target BDI messages are sent during the terminal portion of the mission Battle Damage Indication Imagery This is an H amp S message that includes a compressed single frame of imagery collected with the DSMAC sensor Collection of images is controlled by mission data From Strike Missile Controller In Flight Mission Modification Preplanned Outcome These messages can be used to select one of up to 16 preplanned mission outcomes The missile will transition to the chosen outcome at a preplanned point in the route This type of message can also be sent to modify communications parameters or request missile status Aimpoint Update This message is used to command the missile to directly transition to a new target location specified by GPS location The message also provides commands for flyout altitude to the target dive angle and warhead fuze delay This type of message can also be sent to modify communications parameters or request missile status Retarget This message also provides a new aim point to the missile but also includes a segment of mission data to guide the missile to
287. st Can Variants os ens a etu Do o eI gea PE ARP Pod e ur da baee 56 1 24 4 Missile Tube Bore Gage ioo etse verge rel os bo ehe MEE id ext deber 56 1 25 GLS SHIPPING CONTAINERS Ie dace oe a aux aet E ADR s deeds shen 56 1 25 1 Shipping and Storage Skid Mk 30 00202 0 56 1 25 2 AUR Simulator Shipping Skid 4 1 42 4 4 57 1 25 3 Shipping and Storage Skid Mk 34 2 0 0 0 0 0 2 57 126 RECORD 57 1 26 1 PEO W PUB 4440 Record Book for TOMAHAWK Cruise Missile 57 1 26 2 Record Book All Up Round AUR Simulator Volumetric Shape 51 1 26 3 Record Book Missile Tube Ballast Can MTBO 57 1 27 WEIGHTS AND CENTERS OF 57 SECTION VERTICAL LAUNCHING SYSTEM CONFIGURATION 58 128 AUR TDENTIEICATION L uu s beue tt eaa Fed hb ied 58 P29 ANISTBRS ete ote a aX 58 58 1 29 1 1 Canister Fly Through Cover Assembly 58 1 29 142 Canister 2 a e ERO ERRARE E POT Rd 58 1 29 1 3 Canister Baseplate Assembly 58 1 29 2 Mk 14 Mod 1 Mod 2 Canister 2646 pee ree OE E ERA 58 1 29 2 1T EWD Closure Assemb
288. sters and module components and to assist in launching missiles 4 15 2 2 8 Cell System Module The 8 cell system module is like the 8 cell module except that equipment is added to serve the entire launcher The 8 cell system module receives and distributes power and control signals from outside the launcher to all modules and collects control and damage control signals from all modules and sends them outside the launcher 227 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 4 15 2 3 5 Cell Strikedown Module The 5 cell strikedown module replaces three cells with a crane on an elevator both hydraulically operated The crane is used for maintenance loading STANDARD Missile 2 BLK II and VLA canisters removing empty canisters and reconfiguring cells The crane is stowed inside the module when not in use 4 15 3 Remote Launch Enable Panel RLEP The RLEP Figure 4 27 Remote Launch Enable Panel RLEP located in the Combat Information Center CIC interfaces directly with status panel and is used to control Remote Launch Enable and Remote Magazine Power Enable signals when the status panel permits remote operation 4 15 4 Status Panel The status panel Figure 4 28 Status gt receives and displays module status and launcher hazard signals from sensors within the launcher forwards such signals to the Central Control Station CCS and receives enable signals from the RLEP to enable launcher enable power and laun
289. submarine tender shore base loading supervisor and the submarine s commanding officer will determine if conditions are satisfactory prior to commencing offload Prior to offload ship systems are neutralized for each missile tube to be offloaded During offload responsibility for all operations is shared between the submarine s commanding officer and the submarine tender shore base loading supervisor All actions involving ship system and weapon preparation are the responsibility of the submarine s commanding officer His permission is required prior to commencing offload operations His designated representative is responsible for weapon handling operations and ensures that a weapon transfer inspection is conducted Upon completion of submarine and weapon preparation responsibility for offload transfers to the submarine tender shore base The following paragraphs provide a general overview of procedures used during offload operations For purposes of illustration offload of a generic weapon from one missile tube is discussed There are some minor differences in offload procedures among AURs AUR Simulator Volumetric Shapes ballast cans and spent CLSs which are not discussed For multiple offloads the procedures are the same except that multiple actions may be occurring simultaneously to prepare missile tubes and weapons Additionally loading equipment is moved from missile tube to missile tube until the full complement of weapons is offloaded from the s
290. sue Rate Gyro Accelerometer Package Relay Junction Assembly Remote Launch Enable Panel Rocket Motor Reference Measuring Unit and Computer Radio Navigation Set Report of Item Discrepancy Repair Parts Breakdown Repair Parts List Receiver Processor Unit Range Safety Command Range Safety Electronics Unit Range Safety System Support and Test Equipment Serial Number Small Arms Fire Enclosure for the Protection of Ordnance Transit Shore Activity Maintenance Data System Satellite Communications Satellite Navigation Shore Base Storage Compatibility Group Submarine Combat System Satellite Data Link Second Ship Alteration 143 SW820 AP MMI 010 REVISION 15 ABBREVIATION ACRONYM SIB SIP SLCM SMDC SMR SMTT SOF SPAWAR SPU SRA SSGN SSN STA START SUBASE SUBROC SWF SWFTR SWL SWOP T amp E TACTOM TAE TALMIP TCG TCM TEMP TERCOM TFBR TGT 27 MARCH 2009 CHAPTER 1 DEFINITION Ship Information Book Standard Inspection Procedure Sea Launched Cruise Missile Shielded Mild Detonating Cord Source Maintenance and Recoverability Submarine Missile Tube Trainer Special Operations Forces Space and Naval Warfare Systems Secondary Power Unit Specialized Repair Activity Submarine Guided Missile Nuclear Propulsion Submarine Nuclear Propulsion Fast Attack Station Strategic Arms Reduction Treaty Submarine Base Submarine Rocket Strategic Weapons Facilities Submarine Weapon Field Trouble Re
291. synthetic hydrocarbon JP 10 MIL P 87107C 6000 psi helium 39 cu in 6000 psi nitrogen 23 cu in 60 cu in 6000 psi nitrogen 60 cu in each 3550 psi Dual differential pressure sensing 0 5 12 5 psid Poppet spring loaded 12 16 psid 151 SW820 AP MMI 010 REVISION 15 ITEM Reseat Pressure Pressure Relief Valve h Type Cracking Pressure Reseat Pressure CLS Electrical System h Type Input Output Engine 1 Designation Type Thrust Rocket Motor Assembly 1 Designation Type Propellant Control Safe Arm Igniter Assy Airframe 1 Type Output 1 Output 2 Alternator i Type Output 27 MARCH 2009 CHAPTER 1 DESCRIPTION 10 8 psid min Poppet spring loaded 3 4 17 0 psid 3 0 psid 24 30 Vdc 4 5 5 5 Vdc 24 30 Vdc Model F415 WR 400 Turbofan 650 Ib Mk 135 Mod 0 Single chamber fixed nozzle Arcadene 360B HTPB high performance aluminized composite propellant 322 Ib Jet tab thrust vector Mk 38 Lithium thermal dual output 28 34 Vdc 40 65 Vdc Engine shaft mounted three phase permanent magnet generator 4 3 max 152 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 ITEM DESCRIPTION Voltage 140 250 Volts NOTES a Applicable to UGM JUGM 109A b Applicable to UGM JUGM 109C D only c Applicable to JRGM JUGM 109A C M only d Applicable to JUGM 109C D S W only e Applicable to variants with
292. t is plugged and the P V sensing line connected to the pressure transducer in the missile tube A leak test at the missile tube hatch opening is conducted and the underhatch area cleaned The CLC 15 removed and the capsule closure is inspected to ensure no damage occurred during loading The missile tube hatch and fairing are then closed and the loading platform removed 4 9 1 7 SSGN Onload Overview The following paragraphs provide a brief description of the unique aspects of onloading the Tomahawk onboard a SSGN 726 Class submarine 4 9 1 8 AUR Onload Sequence An onload sequence begins with staging and preparing the work platform Figure 4 4 MTEL Work Platforms onto the MTEL attaching the MTEL adapter Figure 4 7 MTEL With MTEL Adapter Installed onto the MTEL and attaching the lifting adapter extension Figure 4 21 Lifting Adapter and Extension onto the lifting adapter The MTEL work platform the MTEL adapter and the lifting adapter extension are support equipment unique to SSGN 4 9 1 9 Organizational Level Preparations The submarine crew opens the missile tube hatch providing access to the Multiple All Up Round Canister MAC Figure 4 33 Multiple All Up Round Canister Fully Loaded and its individual AUR cells and tags out the hydraulic system The appropriate AUR cells are inspected for dirt debris or foreign material that will damage lip seals during loading and the area is cleaned as required 4 9 1 10 Installing Load
293. tatus brought about by the launch 4 20 LAND ATTACK TCM CASUALTY MODE There is no casualty mode for land attack TCM variants 234 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 1 General Locations of SSN Complexes WEAPONS SHIPPING HATCH 235 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 2 SSN TWS related Equipment TTL Interfaces NAV REVR TOT AN BOD 5 DATA 0 SYSTEMS SPACE DATA issu 6 CLASS UMBILICALS TUBE DIGITAL DATA ANALOG DATA ees SHIPS AIR mmm REGULATED AIR 236 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 3 SSN TTL Pressurization Vent Control System PRESSURIZATION VENT VALVE MANIFOLD WEAPONS LAUNCH CONSOLE CONTROL POWER 51117 700 PS SERVICE AR PRESS VENT VENT BLOCK DLENDID WITH DETENTED MANUAL OVERRIDE WING WING SLOT PLUG THROUGH VENT PORT 2 SHROUD ACTUATOR ELECTRICAL UMBILICAL ENGINE 1 1 press COVER VENT CHECK 1 PRESSURIZATION VENT CONTROLIS SHOWN 2 AIR ENTERS WING THROUGH SLOT FROM neuer VALVE ADDER TUBE ONLY 15 TYPICAL FOR OUTSIDE MISSILE VALVE ALL FOUR TUBES 237 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 4 MTEL Work Platforms 238 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 Figure 4 5 TTL
294. ter a velocity test is passed the engine inlet and wings are deployed and a pushover command initiated 1 14 4 Transition to Cruise Flight The transition to cruise flight begins about 14 seconds after first motion and coincides with rocket motor thrust decay As the thrust decays the ACR enable is turned off and the nulled The rocket motor 15 then jettisoned and the sustainer engine started As the sustainer engine comes up to speed the engine driven generator regulator comes on line to supply the electrical power needs The transition to cruise flight continues at maximum engine thrust until the missile descends or climbs to the commanded cruise altitude and accelerates to the commanded Mach number 1 14 5 Cruise Phase The cruise phase commences with the descent or climb to cruise altitude and acceleration to cruise speed For a land attack variant it includes pre landfall inertial plus GPSS aiding navigation crossing the initial TERCOM field and making altitude corrections for terrain following overland inertial plus GPSS aiding navigation to the programmed mission waypoints and performing enroute or midcourse position fixes using TERCOM maps plus GPSS aiding For REM or RSS equipped variants radio frequency RF carrier is continually sent by the chase aircraft If the missile loses RF carrier the missile will climb or descend to a predetermined altitude After a prescribed time if the carrier remains lost REM equipped missile
295. ter is unbolted from the MAC top plate and removed The lifting adapter extension is unbolted from the capsule upper flange and removed The HPU is disconnected from the electrical power source and removed 216 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 4 9 1 13 Organizational Level Closeout Operations Topside personnel connect the pressure vent sensing line and install the eight retention segments to secure the AUR in the AUR cell Topside personnel mate the AUR upper umbilical cable connector to the MAC umbilical cable stowage receptacle Inside the MAC the crew connects the AUR ground strap moves the P1130 connector to the stowage position of the aft cover and mates the MAC umbilical cable to the J1130 connector Figure 4 36 AUR Aft Cover Viewed in MAC Each AUR requires one MAC umbilical to be connected to 130 connector A bubble test is performed on installed AUR to check for leaks at the MAC top plate 4 9 2 Offload Submarine offload begins when the submarine arrives at a designated shore base activity or supporting submarine tender to discharge a complement of weapons or spent CLSs Wind and sea motion which affect the submarine s position and movement are factors in determining the feasibility of offload operations To prevent damage to the missile ship or equipment it is recommended that weapons not be offloaded if roll exceeds 3 degrees or pitch exceeds 1 2 degree and winds exceed 30 knots The
296. tes the missile for its ID number tail number OFS cyclic redundancy check status and OFS version ID The SCS also requests version IDs from other missile software components such as the DSMAC flight software and GPS flight software After these checks are passed the SCS loads the Missile Launch Capable Flight Software LFS Once the LFS 15 loaded the Missile Response Status Word reported to the SCS will show the missile to be launch capable After the software loads are completed the Anti Jam GPS Receiver Digital Scene Matching Area Correlator and Satellite Data Link Transceiver are powered up and Built In Tests are performed Next the Thrust Vector Control and Fin Control System Built In Tests are performed Initialization of the Inertial Measurement Unit begins with the transmittal of the missile initialization message from the FCS which contains data from the platform s inertial navigation system This allows the navigation processor to transition from Mode 1 Ready to Align to Mode 2 Aligning Alignment data from the platform is combined with up to 220 KB of mission data and loaded into the missile The Mission Data also includes strike data and communications parameters Mission data loads are verified by checksum tests after download completion The loading of mission data continues with the over water data planned by the launch platform GPS almanac data and GPS keys The FCS continues to monitor the navigation processor statu
297. tform for various command control and safety devices The canisters also serve as shipping and storage containers and launch tubes for TCMs Canister components safety security devices and canister circuits are discussed in the following paragraphs 58 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 1 29 2 1 FWD Closure Assembly FWD Closure Assembly consists of two vertical lift lugs a cover seal that ruptures during TCM egress and a closure with a breakwire to indicate missile away during TCM launch 1 29 2 2 Closure Assembly The Closure Assembly consists of a grid closure closure with breakwire and a support ring that provides an exhaust gas seal 1 29 2 3 Umbilical Connector The umbilical connector is the exterior interface to connect the Mk 14 Canister cable assembly The cable assembly connects the code plug FWD and AFT closure breakwires temperature sensor cable and conduit assembly connector and umbilical connector adapter 1 29 2 4 Deluge Connector The quick disconnect deluge connector provides the means of activating the three piece deluge manifold surrounding the warhead in the canister should a signal be received over the deluge circuit that canister conditions indicate that detonation of a warhead in a canister is imminent The manifold with its 22 equally spaced holes provides an even distribution of water on the warhead area 1 29 2 5 Antenna Connector The antenna connector provides the
298. th SSN 688 and SSN 774 Class submarines use a shipping line to ship and unship weapons On SSN 688 Class submarines the major components are a portable topside deck skid intermediate shipping rails and a shipping 205 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 tray located in the torpedo room The weapons restrained by a shipping harness are lowered or raised along the shipping line aft end down using a chain drive Figure 4 5 TTL Weapon Shipping Handling and Stowage Equipment SSN 688 Class depicts SSN 688 Class submarine shipping handling and stowage equipment On SSN 774 Class submarines the major components are a portable topside deck skid intermediate and shipping trunk mounted shipping rollers and a shipping cradle located in the torpedo room The weapons restrained by a shipping nose piece and shipping cables are lowered or raised along the shipping line forward end down using a pier side crane connected to the shipping cables 4 2 6 Weapon Handling and Stowage Equipment Two level stowage racks are provided aft of the torpedo tubes for stowage of weapons On the SSN 688 Class the weapons are supported by dollies on athwartship tracks and are restrained by lashing straps On the SSN 774 Class the weapons are supported in cradles which in turn are supported at each end by an end truss track and restrained by lashing bands Transfer of weapons to the torpedo tube or to any other stowage position or working
299. the lateral support group and six lip type circumference seals which protect the exterior surface of the missile and constrain eject gases External mounting arrangements are provided for lateral support pads and an umbilical guard and cable The capsule has provisions for attaching the vertical support assembly VSA and capsule extension as well as handling and support equipment 48 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 The upper flange has penetrations for the pressure vent port the annular space vent line and a slot which allows the flat umbilical cable to pass through the flange There are two lip seal grooves around the circumference of the upper flange to provide a seal at the upper end of the missile tube There are two alignment slots located at 53 and 233 azimuth which engage pins at the upper end of the missile tube The alignment slots serve to align the AUR in the missile tube as it is seated When installed in the missile tube the AUR 15 supported and secured by eight retention segments on its upper flange Three of the retention segments provide mounting for cable clamps The segments secure the capsule by exerting downward pressure on the upper closure ring while exerting upward pressure in a groove on the inside surface of the missile tube upper flange The aft closure is located below the VSA and capsule extension The aft closure assembly encloses the lower end of the capsule and provides a mounting surface f
300. the Capsule Launching System gas generator hazardous component locations are illustrated in Figure 2 2 TOMAHAWK Cruise Missile Hazardous Component Locations 2 Sheets All TOMAHAWK AURs are assigned to Storage Compatibility Group J and to DOT Hazard Class IAW SW020 AC SAF 010 020 030 Table 2 2 Storage and Hazard Data summarizes storage and hazard data for all AURs Table 2 3 Pyrotechnic and Hazardous Materials Data provides AUR pyrotechnic and hazard data associated with composite material breakdown combustion and postlaunch waste water in spent CLS capsules 2 3 8 Permits As all TCMs contain some hazardous materials in their shipping configurations current Department of Transportation DOT Exemptions and Certifications of Equivalency COE are required to authorize the movement of these items Copies of the applicable permits must accompany the shipment and any special instructions contained in the permit must be observed The permits have the force and effect of federal law and failure to have a permit or to comply fully with its provisions may result in fine and or imprisonment The fact that a shipment is made by or for the government in no way relieves the shipper from full compliance with permit requirements Five permits have been issued by federal agencies that effect shipment of TCMs 2 3 4 Hazards Associated With Composite Material Breakdown Combustion CLS may be encapsulated in a steel
301. the existing SSN class AUR configuration as cost effectively as possible for use with SSGN The three primary areas of concern in achieving this were 1 at the aft end connection the Multiple All Up Round Canister MAC was unable to connect the existing P130A connector with the umbilical cable installed 2 there was possible interference from the sabot with the hatch closure and there existed the possibility of damage to adjacent AURs due to post launch sabot debris and 3 there was concern over the CCA and umbilical cable performance in the SSGN environment over the AUR life cycle Solutions to these three areas were to install a new CCA umbilical cable and aft end components The major components of the CLS Mk 45 Mod 2 are discussed in the following paragraphs 1 23 2 1 Capsule The capsule is a tube 243 inches in length which forms the main structural member of the CLS The capsule increases in diameter from 24 inch at the aft end to 26 61 inches at the upper flange The capsule is sealed on the forward end by the capsule closure assembly and at the aft end by the aft closure assembly Within the capsule shell is mounting space for the lateral support group and six lip type circumference seals which protect the exterior surface of the missile and constrain eject gases External mounting arrangements are provided for lateral support pads and an umbilical guard and cable The capsule has provisions for attaching the vertical support assembly
302. to the launch platform After receipt of Missile Enable the launch platform s SCS removes launcher power to the missile and the Mission Control Processor MCP issues a Mk 82 deadface command to prevent spurious digital commands Following the deadface command the SCS issues a gas generator ignition command When the missile senses first motion a launcher position and velocity test is initiated When launcher position and velocity is detected the missile disables the booster and waits for a deceleration indication and when the deceleration occurs the booster is ignited and the missile enables ACR monitor TVC control and initiates booster guidance autopilot Missile enable is then turned off When water broach is detected the wing slot plugs are ejected Shroud separation occurs fins are deployed and boost roll control is initiated Regardless of the launch platform the missile then jettisons the inlet cover and deploys the wings When the rocket motor thrust decays the missile jettisons the rocket motor and starts the cruise engine and follows the cruise route to the designated target 4 14 3 Submarine Weapon System Interfaces During the pre launch phase the Block IV TACTOM AUR interfaces directly to the SCS and the Mk 45 Capsule Launching System CLS The Mk 45 Capsule provides for all mechanical and environmental interfaces to the AUR including the longitudinal shock isolation lateral support mounting to Mk 45 canister aft structure restr
303. torquing motors 3 12 2 Velocity and Position Computation True position of the submarine is continuously updated by computer equipment using primarily navigation equipment data and secondarily Dead Reckoning Analyzer Indicator DRAI data The electromagnetic underwater log EM Log which measures ownship speed through the water is used in conjunction with the computers to provide damping to the navigation equipment It also provides ownship speed to the DRAI 3 12 3 Reset Computations Latitude and longitude information is periodically computed the computer equipment from navigation satellite receiver data These data are used to reset navigation equipment position at the direction of the system operator 3 12 4 Status and Performance Monitoring The computer equipment reacts to navigation operator directions concerning mode of operation and requests for data to be displayed on the 190 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 3 Navigation Control Console NCC Navigation software continuously monitors the equipment to provide the navigation operator with equipment failure or misalignment indications 191 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 3 SECTION IV CAPSULE LAUNCHING SYSTEM 3 13 GENERAL This section discusses CLS unique electrical interrelationships between the submarine fire control system and CLS Additionally this section discusses launch platform and TCM physical and functional interfaces
304. ts recovery upon test flight completion REM equipped are identified by an M suffix in the missile designator An RSS equipped TCM JRGM or JUGM 109C or D or MRSS equipped Block IV TACTOM JRGM or JUGM 109E is used for an exercise flight involving a target hit and may have a live warhead or an 5 inert warhead suffix in the missile designator 1 5 MISSILE IDENTIFICATION SYSTEM The Missile Identification System MIS is a method of differentiating between operationally significant features within a weapon type Digital data can be electronically read from TCM variants containing a Programmable Read Only Memory in the Mission Control Module or from data stored in the protected memory of the guidance set The MIS code consists of a series of digital data words followed by a checksum These data are transmitted to the submarine ship launch control system upon request Matching data plates containing the AUR serial number and MIS code are mounted in the Record Book for TOMAHAWK Cruise Missile TRB PEO W PUB 4440 and on the AUR A removable data plate is provided for VLS variants for attachment to the Mk 14 Canister The MIS data plate may also contain canister code plug values which are applicable only to surface launched variants Refer to PEO CU INST 8800 1 for complete identification of AUR nomenclatures National Stock Numbers Navy Ammunition Logistics Codes discriminators and MIS codes 1 6 SUPPORT EQUIPMENT
305. tweight nose cover installed AUR WIT CTS CGs at station 142 1 TOTEM NL TOTEM and COTS TOTEM Capsule CGs at station 144 0 PVTV TOTEM Capsule CG at station 155 0 QAST CG will vary depending on test requirements Refer to Test and Evaluation Plan for data 160 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Table 1 11 Weights of CLS Variants and Related ITEM TACTICAL VARIANTS UGM 109C 2 UGM 109D 2 UGM 109E 2 EXERCISE VARIANTS JUGM 109C 2 JUGM 109D 2 JUGM 109E 2 S W JUGM 109E 2 W CAPSULE Capsule Launching System Mk 45 w CPC Capsule Launching System Mk 45 Spent TRAINING INERT VARIANTS AUR VOLUMETRIC SHAPE AUR SIMULATOR AURES Mk 101 AURES Mk 112 Missile Tube Ballast Can w o additional ballast AURBb Material MAX HANDLING MAX HANDLING WEIGHT POUNDS WEIGHT KILOGRAMS CLS Mk 45 CLS Mk 45 CLS Mk 45 CLS Mk 45 Mod 1 Mod 2 Mod 1 Mod 2 5905 5905 2679 2679 5749 5749 2608 2608 5900 5900 2676 2676 2132 2290 967 2218 2376 1006 1078 MAX HANDLING MAX HANDLING WEIGHT POUNDS WEIGHT KILOGRAMS m 5680 300 2576 136 161 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 MAX HANDLING MAX HANDLING WEIGHT POUNDS WEIGHT KILOGRAMS CLS Loading and Handling Trainer Assembly Mod 1 CLS Loading and Handling Trainer Assembly Mod 2 SHIPPING SKID Shipping and Storage Skid Mk 30 Mod 2 w covers AUR Simulator Shipping Skid w cover
306. ty Apparatus Material Support Date Military Surface Deployment amp Distribution Command Material Safety Data Sheet Maintenance Standard Electronic Module Missile Multi test Box 139 SW820 AP MMI 010 REVISION 15 ABBREVIATION ACRONYM MTBC MTCP MTEL MV NALC NAS NAVICP M NAVMAG NAVMAT NAVMATINST NAVSEA NAVSEAINST NAVSUP NAVSUP PUB NAVSUPINST NAVSURFWARCENDET NC NCC NESIP NL TOTEM No NOTTS NP NSDSA NSN NSSF NSTM NSWC NSWCDET NSWCDIVPH 27 MARCH 2009 CHAPTER 1 DEFINITION Missile Tube Ballast Can Missile Tube Control Panel Missile Tube Extension Loader Millivolts Naval Ammunition Logistics Code Naval Air Station Navy Inventory Control Point Mechanicsburg Naval Magazine Navy Material Command Naval Material Command Instruction Naval Sea Systems Command Naval Sea Systems Command Instruction Naval Supply Systems Command Naval Supply Systems Command Publication Naval Supply Systems Command Instruction Naval Surface Warfare Center Detachment Normally Closed Navigation Control Console Naval Explosive Safety Improvement Plan Encapsulated No Launch No Wet TOMAHAWK Test Missile Number Naval Ordnance Transportation Tracking System Navigation Processor Naval Sea Data Support Activity National Stock Number Naval Submarine Support Facility Naval Ship s Technical Manual Naval Surface Warfare Center Naval Surface Warfare Center Detachment Naval Surface War
307. ube muzzle hatch protective cover muzzle face protective cover fairing cofferdam and counterbore cover are removed The missile tube hatch is ungagged and the hatch is closed Flood and drain pressurization vent and security systems are then energized to return the submarine to normal operations The loading platform is removed 218 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 4 9 2 8 Post Launch P V Refurbishment after Spent CLS Offload After the offload equipment has been removed from the missile tube the submarine crew conducts post launch P V refurbishment The P V valve is disassembled cleaned and reinstalled Differential transducer lines are cleaned and the transducer is checked and tested P V piping is flushed dried and tested for serviceability Upon completion of the refurbishment the P V plug is reinstalled 4 9 2 9 Post Launch Missile Tube Refurbishment after Spent CLS Offload Launching a TCM and exposure to sea water during the launch may cause minor damage to the missile tube necessitating post launch missile tube refurbishment The submarine crew removes the missile tube counterbore cover inspects the interior of the missile tube and performs or arranges for missile tube maintenance depending on the complexity of repairs required 4 9 2 10 SSGN Offload Overview The following paragraphs describe unique aspects of offloading the Tomahawk from a SSGN 726 Class submarine Primary elements unique to offloading fro
308. ubmarine Similarly post offload procedures are accomplished on a tube by tube basis until full closeout is accomplished Offload terminates when all weapons scheduled for offload have been removed from the submarine and all loading equipment has been removed 4 9 21 Prepare Missile Tube and Ship Systems Initially the SCS must be disengaged from those missile tubes containing weapons to be offloaded After the SCS has been disengaged from those missile tubes to be offloaded and the loading platform Figure 4 15 Loading Platform Installed installed by supporting submarine tender shore base personnel the first missile tube hatch is opened and gagged Figure 4 16 SSN 688 Class Submarine Missile Tube Equipment The muzzle face protective cover the missile tube muzzle hatch and magnetic protective cover and the EMS protective cover are installed to protect submarine personnel and equipment while preparing AUR weapons for removal 4 9 2 2 Prepare Spent CLS for Offload In addition to those above tasks to be performed to prepare for weapon offload reflood water and residue must be removed from a spent CLS prior 217 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 4 removing it from the missile tube Submarine tender shore base personnel pump approximately half of the reflood water in the spent CLS into a holding tank using a submersible pump The submarine crew then performs a P V piping blow down to ensure reflood water is removed The
309. uipped missile with the remaining section volume serving as a fuel tank Two flush mounted radar altimeter antennas one a transmitter and the other a receiver are installed on the bottom centerline to provide altitude and terrain inputs to the CMGS 1 11 1 3 Forward Body Fuel Section The forward body fuel section extending from station 52 45 to station 99 80 contains fuel and an expansion bladder to accommodate changes in fuel volume due to fuel expansion and contraction For test and exercise flights the forward body fuel section 15 replaced by a REM section 1 11 2 Land Attack 109C The land attack 109C Figure 1 3 Land Attack 109C is a medium range missile armed with a WDU 25 B or WDU 36 B conventional warhead with guidance provided by Terrain Contour Matching TERCOM techniques and Digital Scene 26 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Matching Area Correlation or DSMAC and a Global Positioning System Subsystem GPSS to increase terminal accuracy Time of Arrival TOA and Time on Target TOT software are also used to enhance coordination with other strike capabilities The missile has a modular construction aluminum airframe with a diameter of 20 375 inches The length is 243 33 inches with the Mk 106 Mod 0 Rocket Motor or 246 06 inches with the Mk 111 Mod 0 Rocket Motor The unique body sections are the forward body guidance section and the forward body payload section which are described in t
310. und Electronic Simulator AURES Mk 101 90 REVISION 15 27 2009 1 Figure 1 30 AURES AURS Interface AUR SIMULATOR UMBILICAL CABLE ASSEMBLY TO MISSILE TUBE HARD CLOSURE UMBILICAL CONNECTOR SW820 AP MMI 010 AUR SIMULATOR AUR ELECTRONIC EX SIMULATOR jT UMBILICAL CABLE 1 Lm ASSEMBLY 1 AUR SIMULATOR UMBILICAL 4 CABLE lt CONNECTOR 5 PLUG PRESSURIZATIOR VENT oa PIPE TUBE lt 2 gt STATIC LOAD 5 4 BANK CONNECTOR AT 4 PLUG f CB ATP IPSA Ae gt 4 AUR ELECTRONIC SIMULATOR di REMOVAL GUIDE TUBES LIFTING PULLEY AUR ELECTRONIC SIMULATOR IN EXTENDED POSITION FROM VOLUMETRIC SHAPE STATIC 1040 BANK CABLE ASSEMBLY A 4 gt 1 PLATE BALLAST STATIC LOAD CIRCULATION FAN AURES IN AUR SIMULATOR ARRANGEMENT 91 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 31 Missile Tube Ballast Can FILL PLUG LIFTING PAD BRASS PROTECTOR O RING GROOVE RING NOT USED FLAT RUBBER GASKET POLYMER PADS TRUNNION BEARING HOLE 2 HOLES 180 APART SHOWN OUT OF POSITION 92 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 Figure 1 32 Shipping and Storage Skid Mk 30 TOP VIEW OF WIRE SEAL LOCATIONS LATCH POST LATCH POST WITH WIRE SEAL FORWARD COVER FORWARD COVER DOOR W WIRE SEALS 2 STACKING POST 4 LATCH POST WI
311. ure 3 3 VLS Exhaust Gas Control CANISTER AFT CLOSURE END VIEW PETALS 4 CANISTER MK 14 MOD 1 2 202 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 3 Table 3 1 Land Attack TCM CMGS Alignment Modes MODE 0 Warmup 1 Standby 2 Course Level 3 Spare 4 Align Axis 1 5 Slue 6 Align Axis 2 7 Alignment Complete 8 Navigate COMMENT Mode 0 performs the first set of BITs and sequences the CMGS inertial platform into gyro control Operations include warmup loading of operational flight program initialization BIT gyro caging and gyro spinup BIT results are contained in the MISSILE STATUS word If all BITs are passed and gyros have spun up the mode number advances to Mode 1 Mode 1 tests availability to present position and checks to see if inertial platform is under gyro control Program will advance to Mode 2 when present position is available and platform is determined to be under gyro control During Mode 2 the inertial platform is torqued to level by computer program torquing commands Mode is complete when the computed tilt angle and mode time tests are passed Not used Mode 4 performs the first fine alignment phase and is completed when a series of mode time computed tilt angle gyro bias change and azimuth angle change tests are satisfied If sufficient maneuvering occurs in this mode to estimate the platform azimuth angle Modes 5 and 6 are bypassed and Mode 7 will be entered at
312. ure vent control PVC transducer characteristics and PVC ullage characteristics of a Block IV AUR It can be used in a dry torpedo tube for flow rate testing or it can be connected as a NL TOTEM with the BBY adapter and Missile Simulator for PVC FCS testing or training in a flooded torpedo tube 1 19 CNU 308 E SHIPPING CONTAINER The CNU 308 E Shipping Container Figure 1 25 CNU 308 E Shipping Container is a reusable stackable container to provide protection for TCMs and capsules during handling storage and transportation The basic design functions of the container are to a Attenuate shock and vibration b Permit handling by forklift handlift truck or sling crane arrangement c Provide a means to stack containers during transport or storage 1 19 1 Function The function of the container is to handle store and transport TTL tactical and exercise AURs and handle and transport TTL certification and training variants post launch REM equipped TCMs and TOTEM test vehicles with an adapter 76Z7908 1 installed and TTL capsules 1 19 2 Description The container consists of a fiberglass lower and upper shell the latter in two sections Thirty two quarter turn fasteners are located around the upper edge of the lower shell with matching slots located on the mating edges of the upper shell Shock mounts integral supports and internal straps attenuate the shipping and handling stresses to safe levels Four handles on each upper shell
313. ure weapons and containers in small Purpose boats P N CBU Strongback Horizontal Handle Mk 14 Mod 1 Canister VLS Mk 3 Mod 0 P N 5598249 9 Strongback Horizontal Handle Mk 14 Mod 1 or Mod 2 Canister VLS Mk 3 Mod 1 P N 72511117 9 Strongback Vertical VLS Onload off load Mk 14 Canister Mk 4 Mod 0 P N 5497606 Support System Mk 8 Support TTL and Mk 10 weapons in Mod 0 storage P N 6213373 Tagline Mk 3 Mod 0 With Mk 87 Mk 90 Band maintain P N 5166715 control of uncontainerized weapons or Mk 4 Mod 0 during handling Maintain control of P N 5166702 containers during handling 118 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 EQUIPMENT FUNCTION ILLUSTRATION Tester Igniter Used for testing the igniters in solid Amptec Model fuel rocket engines detonation circuits 630AN 630BN 641N in warheads explosive separation bolts or any other squib actuated devices Threadsaver Trunnion Used in place of trunnion bearing Bearing assemblies to preserve threads in P N JCM 17679 trunnion bearing holes Tool Kit Nose Diaphragm Remove install nose diaphragm P N 7670667 1 during UGM 109A 1 warheading and dewarheading Tool Kit Special Weapons Set of four tools to align P N 7676333 8 missile capsule detach attach holdback S eS nuts protect holdback assembly and lt remove install booster lanyard nut during 109 1 warheading and dewarheading Tool Lip Seal Used to install lip s
314. various preset firing interlocks and verification of firing status ready Intent to Launch ITL 1s signaled The final firing sequence occurs automatically The missile batteries activate and the essential electrical power buses are isolated A status check is then performed by the CMGS using battery power If the status check 15 go a MISSILE ENABLED signal is sent Upon receipt of this signal launch equipment separate and eject the TCM from its launcher The launch phase is described in detail in Chapter 4 for each launch configuration 1 14 3 Boost Phase After 1 5 to 4 seconds from first motion the rocket motor pull switch actuates With CMGS concurrence of safe eject velocity and distance the CMGS initiates signals that activate the rocket motor TVC system and ignite the rocket motor The CMGS also enables the anti circular run ACR system At the same time that rocket motor ignition occurs a momentary pitchup command is sent to deflect the exhaust causing the missile to pitch up as it begins to accelerate Should the missile deviate from the planned trajectory or the CMGS fail to 39 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 reset the MCM timer the ACR system will automatically terminate the mission by jettisoning the continuity shroud and rocket motor which stops the uncontrolled acceleration of the missile and prevents it from turning back toward the launch platform The fins deploy and active roll control is initiated Af
315. ve WDU 36 B 265 Ib explosive BLU 97 B 106 Ib explosive Flashpoint FP 130 degrees Auto Ignition Temperature 474 degrees F Zirconium Potassium Perchlorate Titanium Hydride Potassium Perchlorate Mixture 295 milligrams Class Pyrotechnic Propellant Grain Material 7 Ib Boron Potassium Nitrate Binder Mixture 100 grams Boron Phosphate Nitrate Superfine RDX Mixture 240 milligrams 6000 psi for Mk 106 0 Rocket Motor thrust vector control 5000 psi for REM flotation system 6000 psi for air frame wing slots wings and inlet deployment jet tab control 3500 psi for Mk 111 0 Rocket Motor thrust vector control Zirconium potassium perchlorate 65 mg and Titanium hydride potassium perchlorate 220 mg Zirconium potassium perchlorate 65 mg and Titanium hydride potassium perchlorate 220 mg BKNO Pellets 107 5 gm FLSC CH6 5 76 gm and Loaded Charge Case HNS 17 gm ZPP 16 mg Lead azide 14 mg and RDX 200 mg Zirconium potassium perchlorate 65 mg and Titanium hydride potassium perchlorate 220 mg Zirconium potassium perchlorate 65 mg and Titanium hydride potassium perchlorate 220 mg 179 SW820 AP MMI 010 REVISION 15 ITEM ENGINE START CARTRIDGE AND IGNITERS WING PLUG THRUSTERS WING DEPLOYMENT PNEUMATIC VALVES FIN CABLE CUTTER FIN DEPLOYMENT SYSTEM PYROTECHNIC LINEAR ACTUATORS UGM 109E CMA BATTERY 27 MARCH 2009 CHAPTER 2 HAZARD Ammonium nitrate based
316. vermold Remove ballast from CLS ballast can Prevent Mk 10 separation nut lockring wrench from backing out of lockring and rounding holes Attaches over nose cover of UGM 109A 1 to prevent unauthorized inadvertent tube load aboard the submarine Replaces electrical connector protective cover on UGM 109A 1 aboard submarine to allow connection of 4FZ security system 114 ILLUSTRATION SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 EQUIPMENT FUNCTION Sling Hoisting Container Handle CNU 308 E Shipping HLU 265 E Container P N 7673525 16 or Mk 152 Mod 0 P N 5167256 Sling Lifting Mk 95 Mod Handle uncontainerized TTL and Mk 0 10 weapons P N 2642629 Sling Lifting Mk 114 Handle uncontainerized TTL and Mk Mod 0 10 weapons in areas where clearance P N 2643810 does not allow use of Mk 95 Sling Sling Lifting Mk 162 Connect lifting apparatus and lifting Mod 0 device Shall not be used to handle P N 1001 6212682 CLS AUR and AURS Sling Lifting Assembly Handle CLS loading platform P N 5580126 271 SSN 688 P N 7066384 A14 SSN 774 Sling Lifting Assembly Used to lift ballast can P N 6510856 SSN 688 P N 7066384 A13 SSN 774 115 ILLUSTRATION SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 1 EQUIPMENT Sling Lifting AUR Mk 154 Mod 0 P N 5167321 Sling Lifting AUR Simulator Shipping Skid Cover P N 5951067 Sling Lifting AUR Simulator Shipping Skid P
317. vigation equipment data and secondarily Dead Reckoning Analyzer Indicator DRAI data The electromagnetic underwater log EM Log which measures ownship speed through the water is used in conjunction with the computers to provide damping to the navigation equipment It also provides ownship speed to the DRAI 3 18 3 Reset Computations Latitude and longitude information is periodically computed by the computer equipment from navigation satellite receiver data These data are used to reset navigation equipment position at the direction of the system operator 3 18 4 Status and Performance Monitoring The computer equipment reacts to navigation operator directions concerning mode of operation and requests for data to be displayed on the Navigation Control Console NCC Navigation software continuously monitors the equipment to provide the navigation operator with equipment failure or misalignment indications 195 SW820 AP MMI 010 REVISION 15 27 MARCH 2009 CHAPTER 3 SECTION V VERTICAL LAUNCHING SYSTEM 3 19 GENERAL This section discusses launch platform and TCM physical and functional interfaces aboard the ship These interfaces include missile canister and launch cell physical interfaces as well as ship systems utilized to a Compute TCM attack solutions b Provide a means of detecting and controlling hazardous conditions in launch cells 3 20 MISSILE CANISTER AND LAUNCH CELL PHYSICAL INTERFACES The missile canister and launch c
318. will initiate recovery a RSS equipped missile will terminate flight throttle is driven off and the vertical fin is driven hard over Additionally if electrical power 15 lost or the CMGS fails in a REM equipped missile a zoom command may be initiated to enhance the probability of missile recovery Emergency flight termination by chase aircraft command is also provided wherein the vertical fin is driven hard over the throttle 15 driven off and the parachute recovery sequence REM equipped missile only is initiated 1 14 6 Terminal Phase 109A C The terminal phase covers the terminal flight events which consist of a final position fix es by TERCOM 109A or DBMAC DSMAC IIA GPSS 109C terrain following warhead arming and determining final target range and bearing These events also include the terminal maneuver and warhead detonation or missile impact The exact sequence of events will depend on the mission data loaded into the CMGS 1 14 7 Target Attack Phase 109D The target attack phase consists of five position fixes by DSMAC or multiple periodic updates by DSMAC IIA GPSS before attacking first target payload cover jettison submunition pack ejection over the first target and additional navigation fixes and submunition pack ejection for subsequent targets As each submunition pack is ejected door assemblies in the dispenser module close allowing the missile to maintain an aerodynamic surface submunition separation system is us

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