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anti-collision light systems installation and service manual

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1. 14 VDC nominal Average Input Current 0 85 Amps Peak Input Current 4 5 Amps 25 Seconds Eg EEE TE PENE EEE EEE EEE 8 y hed 1 5 Ibs Model Number 7090005 Part Number lt 2 220 h c0css0s lt savenwbede docs ekausensesa 01 0770900 05 Operational Voltage 28 VDC nominal Average Input Current 0 425 Amps Peak Input Current 2 25 Amps 25 Seconds ET accese as E gs pegao o 1 5 lbs Operation Equipment Limitations The Model 70900 series LED anti collision light assembly meets the requirements of FAR 23 1401 25 1401 and 91 205 c 3 If certification for night operations is requested the airplane must have an anti collision light system that consists of one or more approved anti collision lights located so that their light will not impair the flight crew members vision or detract from the con spicuity of the position lights Continued Airworthiness The 70900 series LED anti collision light assembly is designed with 10 vertical columns consisting of 3 LEDs each Should any one LED or any vertical column fail the unit must be repaired or replaced Installation Procedures The following information is to assist in the installation of a Whelen LED Flashing Anti collision Light System 1 The installation procedure described in the following text will be confined to a single light installation but is identical for multiple
2. ANTI COLLISION LIGHT SYSTEMS INSTALLATION AND SERVICE MANUAL JANUARY 2007 Approved under STC SA6NE STC SA21NE STC SA615EA STC SA800EA pg Ta s PPH EE EET r MNT TUTUP NI LI SE II Ill TIE III AR z x a ENGINEERING COMPANY INC ROUTE 145 CHESTER CT 06412 0684 PHONE 860 526 9504 FAX 860 526 2009 www whelen com O 2007 Whelen Engineering Company Inc Documen t 05131A WHELEN A IONI GRTINO WHELEN ENGINEERING COMPANY INC ROUTE 145 CHESTER CT 06412 0684 PHONE 860 526 9504 e FAX 860 526 2009 To view our dui qua contact us visit Whelen at www whele 1 or we can be emailed at EP JE com Industrial Whelen manufacturers a full line of Warning Products Table of Contents 2 Page 2 Table of Contents Company Information Page 16 26 Strobe Lighthead Assemblies Page 3 Strobe System Requirements Page 16 17 A470A Series Page 4 Aircraft Not Specifically Mentioned Page 16 17 A450 Series H102 amp H103 Series on the Eligibility List Page 18 19 A650PG PR Series Page 5 Strobe System Wiring Page 20 A610 A612 Series Page 6 Strobe Power Supply Installation Page 21 A625 Series Page 7 9 Strobe Power Supplies Page 22 23 A500A Series Page 7 HDACF Page 24 25 A600 PG PR Series Page 8 A490ATSC Page 26 A650 Series Page 9 A490TCF Page 27 Strobe Power Supply Replacement Cross Page 9 A490TCCF Reference Listing Page 10 13 Self Contained Light Assemblies
3. QTY A625 Strobe Light Assembly The A625 strobe lighthead assembly fits into a 1 1 inch hole The mounting screws are 1 75 inch center to center It protrudes 1 7 inch outside the aircraft s skin and 1 1 inch inside the aircraft When installing an A625 strobe lighthead assembly on the rudder refer to the aircraft s MAINTENANCE and or SERVICE MANUAL for accepted procedures for balancing the rudder before returning the air craft to service Mount the anti collision strobe lighthead assembly as close to the sta bilizer center line as practical to eliminate backscatter as much as possible for the horizontal surface When installing the A625 strobe lighthead assembly in an enclosed area like a Beech enclosed wingtip or tail cone maintain at least 0 060 inch clearance around the lens to the plastic cover The A625 mounts conveniently just behind the forward position light on Cessna s coni cal camber wingtip Make sure that the navigation light pattern is not interrupted when installing the A625 strobe light head on a wingtip The A612 lens is not considered an obstruction A625 INSTALLATION IN CESSNA 300 OR 400 SERIES WINGTIP TANKS The A625 fits just under the navigation light on an adapter plate of 0 032 inch aluminum approximately 2 3 8 inches x 3 1 2 inches Fit this plate between the navigation light and its mounting surface and locate the A625 strobe head below the navigation light Bend and trim the adapte
4. around the aircraft s vertical axis 75 above and below the horizontal plane REF FAR 23 1401 The position lights must be wired independently of anti collision lights GENERAL AVIATION MINIMUM POSITION LIGHTING REQUIREMENTS For compliance to FAR Part 23 1385 through 23 1397 VFR flight rule night requirements on a General Aviation aircraft you must have a TSO d Aviation Red forward position light on the left and an Aviation Green forward position light on the right See Figure 7 page 4 These are normally mounted on the most outward extremity of the airframe so they can project their light directly in front of the aircraft 0 degree to 110 degrees left and right horizontally and 180 degrees up and down vertically unobstructed by any part of the aircraft The tail position light must project its Aviation White light toward the rear of the aircraft 70 degrees horizontally left and right from 0 degree straight back behind the aircraft 180 degrees up and down 0 04 Steradian 131 36 sq degrees interference is allowable reference FAR Part 23 1387 c More than one light is acceptable 2007 Whelen Engineering Company Inc POSITION LIGHTS AND ANTI COLLISION LIGHT DISTRIBUTION PATTERNS REQUIREMENTS 752 An approved anti collision strobe light system must proj ect light or 30 above and below the horizontal plane of the aircraft One or more strobe lights can be used The or 75 projected light is req
5. 68 4250066 30 38 0130090 00 19 170052 009 Description Clamp Ring Assy A626D Optic Lens Red Optic Lens Split Red White ane Optic Lens White ws Taillight Mounting Cup SA402 Taillight Lens Retainer SA406 Retainer Horizontal Mount SA4181 Retainer Vertical Mount W1282 Retainer for A428 Lens W1283 Strobe Tube Assy W1284G Gasket Spacer for A428 Lens W1284R Lens W12852 Lens Radio Shielded W129014 Lens Retainer Assy Radio Shielded W129028 Strobe Tube Assy A430 Series Mounting Adapter Ring Kit 3 Pin Connector amp contacts Kit 3 Socket Connector amp contacts Trigger Jumper Plug for HDACF Kit 2 Pin Connector amp contacts Kit 2 Socket Connector amp contacts Gasket A457A Lens Lens Lens Shielded Lens Retainer Assy Radio Shielded Vertical Mounting Lens Retainer Assy Radio Shielded Horizontal Mounting Strobe Tube Assy non reflective base Strobe Tube Assy Radio Shielded Strobe Tube Assy Radio Shielding Kit for A469A Disc Lamp Socket for A555A Series Strobe Tube Socket Assy For A500A Lamp Socket for A555A Series Halogen Lamp 14V 25 Watt Halogen Lamp 28V 25 Watt Base Plate Assy For A600 Series Retainer for A600 Series Strobe Tube Magnifying Lens for A610 Lens Retainer Assy Radio Shielded used on A600 Series Taillight Lens used on A600 Series Gasket for A615 Taillight Lens Retainer for A650 Series Model Number Part Number 02 0350072 35 07 730068 000 11 230079 000 68 42300
6. like some plastic navigation light detectors and trimmed to shadow the objectionable reflected area is most effective This reflection problem varies from one aircraft to another due to aircraft design and paint color scheme and must be checked on every installation TOP VIEW LEADS ARE 6 00 1 0 LONG Figure 24A CONNECTOR WIRING POS 1 RED ANODE POS 2 BLACK CATHODE Figure 24B POS 3 WHITE TRIGGER Before 2 ss22so005s4 LENS AFICOATED 68 2290005 30 LENS CLEAR A612 01 0770053 13 A650 D STROBE ASSY SHIELDED CLEAR Aiter with Modified Wingtip 01 0770053 00 A650 STROBE ASSY ITEM PART NUMBER DESCRIPTION 2 6 Document 05131A STROBE POWER SUPPLY CROSS REFERENCE REPLACEMENT LISTING Old Part Number Old Model Number Description Current Replacement A413 H5 41 14 A413 HD 14 A413 HD 28 A413 72 14 A413 HD DF 14 A413 HD DF 28 A J w ucx 1_r___ _u A412A HS 14 A412A HS DF 14 A490 TS 14 o rr A490 T 14 A490 T 28 A490 T DF 14 Model HTCF RR _ oa d0u0 o d oa q Jqmd 11 A490 TC DF 14 Model HRCFA LL Specify lens color HR DFA 14 28 Self Contained Strobe DoubleFlash 14 or 28 VDC A402A lens 2007 Whelen Engineering Company Inc Document 05131A 27 CONTINUED AIRWORTHINESS FLOW CHART Inspect Lens Excessive scratches discolorations or cracking Yes Replace
7. 3 The light assembly must be mounted so that the light distribution pattern is not obstructed by any parts of the aircraft A limited amount of obstruction is permitted Ref FAR Part 23 1401 for anti collision lights and PAR 23 1387 for position lights The baseplate must be mounted parallel to the vertical and horizontal centerlines of the aircraft to project the patterns properly These assemblies are interchangeable with the Grimes model A1285 position light Mounting 1 If necessary fabricate the mounting pattern using dimensions found in Figure 16B Note A 1 diameter hole is needed for the connector to pass through 2 Make the necessary wiring connections using 18 gauge wire for the position lights and Whelen 16 gauge 3 c cable for the strobe lights All connections must use FAA approved techniques Remove the 6 32 x 312 retainer mounting screw and retainer Attach the base assembly to the wingtip using 3 6 32 counter sunk screws unit may be sealed around periphery with RTV or equivalent 5 Re attach lens retainer Wiring 1 The strobe connector should plug into the Whelen 16 gauge inter connecting cable or a Whelen strobe power supply Observe the following strobe color coding PIN 1 RED Anode PIN 2 BLACK Cathode PIN 3 WHITE Trigger Caution When pins 1 amp 2 or pins 2 amp 3 are reversed the system will appear to operate normally however this condition will cause pre mature fla
8. 400 PA 28 140 28 150 28 151 28 160 2A13 28 161 28 180 28 235 288 160 28R 180 285 180 28 181 28R 200 28R 201 28R 201T 28RT 201 28RT 201T 28 201T 28 236 PA 30 PA 39 AIEA PA 31P ASEA PA 31 PA 31 300 325 350 A20SO PA 32 260 300 325 300 A3SO NOTES TO ELIGIBILITY LIST i Aircraft as marked require specific attention to proper balancing of the rudder Refer to the Manufacturers Service Manual for balancing instructions 2 Installations on these aircraft require prior or concurrent installation of STC SA4 977 3 The Model HS 24 replaces the Anti Collision beacon supplied in Bell s Night Flying Kit P N 206 706 303 on Models 206A and 206B Any alteration of this certificate is punishable by a fine of not exceeding 1 000 or imprisonment not exceeding 3 years or both FAA Form 8110 2 1 10 69 Page 6 of 6 This certificate may be transferred in accordance with FAR 21 47 Document 05131A 3 a United States Of America Department of Transportation Federal Abiation Administration Supplemental Type Certificate Ne Carlier SA800EA is Certificado issued lo Whelen Engineering Company Inc Route 145 Winthrop Road Chester Connecticut 06412 0684 therefor as specified hereon meets the airworthiness reguirements of Hart 3 6 23 21 of Be Civil Air Federal Aviation Posgutations reginal Product Lyne Certificato Number Sec Attached Eligibility List dated September 8 1
9. 42a NOTE Aircraft whose application for type certificate was made before April 1 1957 may but need not comply with the field of coverage requirements of FAR 23 27 1401 b Compliance with FAR 91 33 c may be shown provided the light installation is in accordance with data approved prior to August 11 1971 and the applicable criteria of Advisory Circular 43 13 2 are met AMENDMENT HISTORY This STC has been previously amended on the following dates 1115 68 7 19 68 11 25 68 1 17 69 2 18 69 4 18 69 3 3 70 12 10 70 4 21 71 9 14 71 5 18 72 9 22 72 11 7 72 7 21 76 10 4 78 3 26 81 8 5 81 8 25 81 5 21 82 7 16 91 6 7 99 6 18 99 6 17 05 Any alteration of this certificate is punishable by a fine of not exceeding 1 000 or imprisonment not exceeding 3 years or both FAA Form 8110 2 1 10 69 Page 2 of 6 This certificate may be transferred in accordance with FAR 21 47 2007 Whelen Engineering Company Inc Document 05131A 35 United States Of America Department of Transportation Federal Aviation Administration Supplemental Tupe Certificate Continuation Sheet A oa SA615EA Date Amended February 22 2007 ELIGIBILITY LIST June 18 1999 AIRCRAFT MANUFACTURER MODEL TYPE CERTIFICATE Aero Commander 100 100 180 1421 111 A11SO 112 A1250 500 500 A 500 B 500 S 500 U GAI 520 560 560A 560E 560F 680 680E F 720 2A4 680FL 680FL P 680T V W 681 690 685 American Aviation AA 1 FA
10. 75 Figure 22A 2 4 Document 405131A Wiring 1 The strobe connector should plug into the Whelen interconnecting cable or a Whelen strobe power supply Observe the following strobe color coding PIN 1 RED Anode PIN 2 BLACK Cathode PIN 3 WHITE Trigger Caution When pins 1 amp 2 or pins 2 amp 3 are reversed the system will appear to operate normally however this condition will cause pre mature flash tube failure 2 Connect the forward position light wires as follows RED 14 or 28 volts depending on aircraft voltage BLACK Ground 3 The tail position light has no polarity as noted by both wires being BLUE Connect one BLUE wire to 14 or 28 volts depending on aircraft voltage Connect the other BLUE wire to ground see fig ure 22B Dimensions TAIL LIGHT WIRES BLUE NO POLARITY POS 3 WHITE TRIGGER POS 2 BLACK CATHODE POS 1 RED ANODE RED 14 or 28VDC BLACK GROUND 1 35 DIA 18 AWG TEFLON LEAD LENGTH 6 00 1 00 Figure 22B A600 Replacement Parts i i I E mb oo NI ITEM Model A600 Installation Figure 23A 2007 Whelen Engineering Company Inc Document 05131A 25 MODEL A650 SERIES INSTALLATION FAA PM A APPROVED Model Number Part Number Description A650 010770053400 EE dele
11. A612D 68 2290005 34 radio shielded clear lens Specifications A612 Lens Weight eos arar eres a tt 0 08 Ibs Operation A610 The Model A610 flash tube and the Model A612 glass lens are used for installing wingtip strobes in single engine Cessna s 1972 and later The existing position light retainer is modified to accommodate the lens and the flash tube is mounted directly behind The unique magnifying design of the A612 lens increases the light intensity by two to three times in the horizontal plane Lenses meet material requirements of MIL C 7989B class B A610 Dimensions POS 1 RED ANODE POS 2 BLACK CATHODE POS 3 WHITE TRIGGER 1 60 APPROX Figure 18A A612 Dimensions ioe MIN INSIDE HEIGHT 375 RAD Figure 18B 2 0 Document 405131A Late Model Single Engine Cessna Wingtip Strobe Light Installation of A610 and A612 After 1 Remove the position light lens retainer being careful not to drop the red or the green lens 2 Establish a center line on the Cessna lens retainer referencing to the lens retainer center mounting screw and position light base plate rear mounting screw Figure 18C CENTERLINE File to fit A612 lens profile 3 Scribe the A612 lens profile as shown in illustration above the object being to have the strobe light centered over the position light base plate Trim or fit an opening
12. E 1 75 OPTIONAL LOCATION LI 1 T 23 67 DIA Model SACF Parts List si 10 N A 6 32 x 1 2 PPHMS MS51957 30 5 HOLES 9 N A 6 INT TOOTH L W MS 35333 71 ef 8 19 130074 100 A440 MOUNTING FLANGE OPTIONAL DA 7 01 0770619 00 POWER SUPPLY HR CF 14 28V IE 00 6 N A 6 32 x 5 16 SS HEX NUT MS35649 264 E v 5 N A 6 32 x 3 8 PPHMS MS51957 28 4 02 0350053 00 SA406 FLASH TUBE ASSEMBLY 3 38 0230946 00 GASKET EN gt Y 2 01 0450685 00 CLAMP RING 1 68 4230044 30 SA402 LENS CLEAR 75 eae 75 5 00 DIA Panni 4 65 DIA B C ITEM PART NUMBER DESCRIPTION Figure 13B l J 18 00 1 00 T SO JF WHITE BLACK GROUND O 2007 Whelen Engineering Company Inc Document 05131A 1 5 STROBE LIGHTHEAD ASSEMBLIES MODEL A470A SERIES FAA PMA APPROVED Model Number Part Number Description A470AR 01 0770019 18 standard assembly Red lens A470AW 01 0770019 19 standard assembly White lens A470AS 01 0770019 20 standard assembly Split Red White lens A470ADR 01 0770019 21 radio shielded assembly Red lens A470ADW 01 0770019 22 radio shielded assembly White lens A470ADS 01 0770019 23 radio shielded assembly Split Red White lens Specifications ET EPER PETE 0 3 Ibs Exposed Height ib san astesskeseahesasrelepadseee eek ete
13. Page 28 Continued Airworthiness Flow Chart Page 10 11 70900 Series Page 29 30 Strobe System Troubleshooting Page 12 13 71055 Series Page 31 32 Parts Breakdown Page 14 15 HRCFA Series Page 33 49 Appendix A Page 14 15 SACFA Series Page 50 Notes Document 05131A INTRODUCTION TO WHELEN ANTI COLLISION STROBE LIGHTING SYSTEMS STC SA800EA STC SA615EA STC SAGNE STC SA21NE Whelen s Anti Collision Strobe Light Systems are approved under STC SA615EA STC SA800EA STC SA6NE and STC SA21NE manufactured under PMA as an approved anti collision light for all aircraft when installation is accomplished in accordance with the following instructions Whelen s Anti Collision Strobe Light Systems are designed and approved specifically for General Aviation Aircraft to comply to FAR 91 205 c 3 visu al flight rule night requirements Whelen s approved Anti Collision Strobe Light Systems can be installed on all aircraft by completing the installation with reference to this Installation and Service Manual and the appropriate technical data listed below ADVISORY CIRCULAR 43 13 1A Chapter 11 Sections 1 2 3 and 7 Electrical Systems ADVISORY CIRCULAR 43 13 2A Chapters 1 and 2 Radio Installations ADVISORY CIRCULAR 43 13 2A Chapter 4 Anti Collision Light Installations ADVISORY CIRCULAR 20 21 12 3 64 Application of Glass Fiber Laminates in Aircraft ANTI COLLISION AND POSITION LIGHT REQUIREMENTS LOCATIONS amp DISTRIBUTION P
14. Product ype Crertificalo Number A3SO Make Piper Model PA 32A Desorsplion of dype Design Change Installation of Whelen A600 PR and A600 PG anti collision strobe with forward and tail position light assemblies as replacements for wing tip lights installed in accordance with STC SA800EA Lerrilel md bone 1 STC SASOOEA must be accomplished prior to or at the same time as this change 2 This approval shall not be incorporated in any aircraft of this specific model on which other approved modifications are incorporated continued on Page 2 of 2 Shia certificate and lhe supporting data which is the baser for approval shall remain infect until sur Date application January 6 1978 Pale reissued Dat tsuance E March L 1978 Pale anended by di 6 ne f Signature LOUIS R MUSACCHIO Chief Engineering amp Manufacturing Branch Title Any alteration of this certificate is punishable by a fine of not exceeding 1 000 or imprisonment not exceeding 3 years or both This certificate may be transferred in accordance with FAR 21 47 FAA Form 8110 2 10 66 48 O 2007 Whelen Engineering Company Inc Document 405131A nited States of America Department of Transportation Federal Aviation Administration Supplemental Tupe Certificate Continvation Sheet Number sum LIMITATIONS AND CONDITIONS continued unless it is determined that the interrelationship between this change and any of thos
15. T210J 210K 210 5 205 210 5A 205A T201K 210L T210L T210M T210N 210N P210N 310 310A B C D E F G H L J 3A10 31071 E310J 310K L N P T310P 310Q T310Q 320 A B C D E F 320 1 340 3A25 336 A2CE 337 337A B C D E F T337D E A6CE F G 401 401A B 402 402A B 411 411A ATCE 421 421A 414 421B DeHavilland of Canada DHC 2 MK I MK IL MK IT A 806 DHC 3 A 815 DHC 6 Models 1 100 110 200 210 ASEA 300 Fairchild Hiller FH 1100 H2WE Hello H 250 H 295 H 391 H 391B H 395 LAS H 395A Hughes 269A 269A 1 269B 269C 4H12 369 A H HM HS HE H3WE Any alteration of this certificate is punishable by a fine of not exceeding 1 000 or imprisonment not exceeding 3 years or both FAA Form 8110 2 1 10 69 Page 5 of 6 This certificate may be transferred in accordance with FAR 21 47 38 2007 Whelen Engineering Company Inc Document 05131A United States Df America Department of Transportation Federal Afiation Administration Supplemental Tupe Certificate Continuation Sheet A Verb or SAGISEA Date Amended February 22 2007 ELIGIBILITY LIST June 18 1999 AIRCRAFT MANUFACTURER MODEL TYPE CERTIFICATE Piper PA 11 A 691 o PA 12 A 780 FDA 14 A 797 PA 15 A 800 PA 16 TAI PA 17 A 805 DA 18 Series PA 19 142 DA 20 144 PA 22 Series 1A6 PA 25 Series 2A8 PA 23 PA 23 160 PA 23 235 1A10 PA 23 250 PA E23 250 PA 24 24 250 24 260 1415 24
16. Weight se dai aerea hier 1 5 Ibs DIAMGIE sasisbadvaseddebend d pilone feci hd dee 3 7 A440 Mounting Adapter The model A440 Mounting Adapter is for fuselage installations for the HRCFA series and the SACF series Model Number Part Number Nes 19 130074 009 Installation The HRCFA amp SACF self contained strobe light assemblies are inter changeable with Rotating Beacons on any aircraft with a 3 75 inch diameter fairing or mounting adapter It is not necessary to change any of the existing wiring or circuit breakers The light assembly must be properly mounted to comply with FAR Part 91 205 c 2 amp c 3 When necessary such as fuselage installation the Whelen model A440 mounting adapter must be used Mounting 1 Remove the existing beacon 2 Make the necessary wiring connections using the existing wiring Positive to the WHITE wire and Ground to the BLACK wires protruding from the light assembly All connec tions must use FAA approved techniques Note It is recommended to ground the unit to the buss bar or the battery Using the airframe as ground may produce EMI RFI interfer ence 3 Remove the three 3 6 32 x 3 8 mounting screws from the light assembly Do not use longer screws damage to the unit may occur Insert light assembly into mounting location and attach using screws as mentioned in step 3 There are two sets of mounting screw locations on the unit for installation versatility unit may
17. a xenon flash tube that refuses to flash WARNING Strobe light power supplies are meant to be used not to remain in an inactive state Use them at all times this will improve their proper functioning Any strobe light power supply that has been out of service for a long period of time is subject to failure because the elec trolytic condenser loses the polarity formation A strobe light power supply not having been used for one year or longer is vulnerable to failure applies to 1993 amp older units If this is the case it is recommended to start operating the system on a voltage that is reduced by 25 percent for 10 to 15 minutes before put ting the power supply into normal service This will prevent overheat ing of the condenser while they reform If the power supply after a long period of non use is operated at full voltage immediately there is an excellent possibility that the condenser will become overheated POWER SUPPLY TEST PROCEDURES THE POWER SUPPLY IS A HIGH VOLTAGE DEVICE LET THE POWER SUPPLY BLEED DOWN FOR 10 MINUTES AFTER TURNING OFF POWER BEFORE HANDLING WARNING Reverse polarity of the input power for just an instant will permanently damage the power supply This dam age is sometimes not immediately apparent but will cause fail ure later on External trigger switching is not provided on the A413A HDA DF Strobe Light Power Supply Reference A413 T3 DF old style strobe light power supply outlet 1 Do not sh
18. be sealed around periphery with RTV or equivalent If the A440 mounting adapter is used attach light assembly to adapter using screws as mentioned in step 3 unit may be sealed around periphery with RTV or equivalent If light assembly is mounted in an inverted position drill a 1 8 diameter hole in lens as indicated on the lens label For the model SACF series remove the RTV plug from the hole in the lens al D 1 4 Document 05131A Description Ke mounting adapter 7 When installing the light assembly in a rudder mount location rudder balance must be checked with reference to the aircraft s service manual The weight and balance should equal the origin al rotating beacon 8 Check all avionics systems for interference from the installation with reference to AC 43 13 2a Chapter 4 paragraph 52 b 9 Label all switches and breakers install pilot warning placard 10 Update aircraft records and complete FAA form 337 Flash Tube Replacement 1 When a flash tube failure occurs remove the 6 Phillips head screw on the clamp ring Be careful not to lose the 6 hex nut Remove the clamp ring Lift the lens assembly amp gasket off the strobe tube Lift the strobe tube and carefully unplug the connector Replace with new strobe tube assembly Attach all parts as required See parts breakdown for replace ment part numbers O 0 GW N Before with Rotating Beacon After
19. closed 1 10 amp rated Jumper inserted into trigger selector outlet STROBE OUTLETS TRIGGER POWER SELECTOR IN OUTLET Figure 7B 2007 Whelen Engineering Company Inc Dimensions POWER INPUT TRIGGER PIN 1 14 28V SELECTION STROBE OUTPUTS 187 DIA 4 PLACES RED 14 28V BLACK GROUND PIN 3 N C 2 37 MAX Figure 7C Mounting 203 DIA 4 PLACES N Aq Suggested Mounting Plan Figure 7D Document 05131A MODEL A490ATSC STROBE POWER SUPPLY FAA PM A APPROVED Specifications Model Number A490ATSC Part Number 01 0770062 03 Position Lights Current Draw 4 0 Amps 14 Volts D C 2 0 Amps 28 Volts D C Weight 1 7 Ibs Length 5 00 Width 3 12 Height 3 06 Operation This power supply will operate ONE strobe lighthead assembly at 34 joules of power It is equipped to flash up to five 5 other like units simultaneously when an 18 gauge wire is connected to outlet 3 on the input power connector OUTPUT 1 Anode 2 Cathode 3 Trigger POS 1 RED POS 2 BLACK POS 3 SYNC Figure 8A Looking at the power supply connectors with the mounting plate flat on a bench the left connector is the strobe outlet The right connector is the power input and synchronization Left Conne
20. light installations 2 Prepare the aircraft for means to secure the LED Flashing Anti collision Light assembly see reference AC 43 13 2A Ch 4 3 14 and 28 VDC and ground leads equipped with an appro priate sized breaker to be supplied to the LED Flashing Anti colli sion Light Assembly System Both leads must be connected by an approved FAA connection Insure that the wire leads and the pressure venting tube are all clear of any obstructions and ty wrap as required The pressure venting tube may be trimmed to minimum length of 1 from base 4 Install the light assembly by securing to aircraft using 46 32 x 3 8 maximum length approved hardware Note Lens mount ing screws installed at 5 7 in Ibs of torque 5 Check all avionics systems for interference from this installation 6 A flight check should be performed by a properly certified pilot 7 All inverted bottom mounted units shall require waterproofing of the unused mounting holes An application of single part sili cone RTV or equivalent applied into mounting holes is recom mended see illustration on page 11 Fig 11A Inverted and or standard mounted units when necessary may require water proofing around any open area where water could get in specifically the lens to the flasher base assembly and the flash er base assembly to the aircraft 8 Update aircraft records complete Form 337 and obtain FAA field approval for installation If not cove
21. model due to paint schemes and colors The Navigation Light Detector will be a source of reflection and should be reduced in size or masked as necessary A small aluminum or plastic plate mounted between the navigation light and the wingtip protruding up or down as required like some plastic navigation light detectors and trimmed to shadow the objectionable reflected area is simple and very effective The solid angle blockage must be reviewed after installing any masking that will disturb the 360 degrees by 75 degrees pattern The afore mentioned type masking used on wingtip lighting seldom interferes with this pattern 4 Document 05131A ESTABLISHING SOLID ANGLE BLOCKAGE WITH REFERENCE TO AC 43 13 2A CHAPTER 4 1 To determine the vertical angles to use with reference to Figure 7 and 8 of the aforementioned chapter 4 attach a long string to the subject light source location 2 Fix a navigational type plotter or protractor to the string with weighted thread fixed to the center of the scale for a plumb bob 3 Level the aircraft or determine the offset angle 4 Pull the string over the point of solid angle blockage Ref Fig 6 page 4 Any angles greater than 75 degrees vertical are not a factor 5 Apply the vertical and horizontal angles to the graph paper Ref Fig 4 8 and instructions in text of paragraph b6 amp c of Chapter 4 A flight test will be performed by properly certified pilot with reference to pa
22. or skip This signifies that the old flash tube is nearing the end of it s serv ice life However to check the questionable flash tube install it in a sys tem and apply a reduced voltage approximately 20 percent to the input to the power supply If the flash tube will operate at this reduced level it still has a great deal of service life in it N O WHELEN S CometFlash CP Strobe Light System consists of four high energy pulses per burst of light 45 bursts of light per light NOTE Whelen Engineering does not recommend attempting to repair their strobe light power supplies in the field It is recommended to take advantage of our 48 hour Repair Service Document 05131A 2 9 R F I and E M Problems Radio Noise Whelen Engineering strobe light power supplies are designed with a low pass filter built in to keep R Fl and E M I down to a minimum however sometimes there will be interference in the radios by the strobe light system Most always this is an installation problem not a strobe light power supply problem The power supply should acquire its power from a low impedance source such as the alternator or generator end of the electrical buss Historically the rotating beacon or strobe light circuit breaker is added on the electrical buss at the opposite end with the radio in between the strobe breaker and the low impedance end of the electrical buss Any noise generated by the power supply will be tran
23. pins 1 and 3 and pins 2 and 3 of the interconnecting cable NOTE When pins 1 and 2 or pins 2 and 3 are reversed the system will appear to operate normally but these conditions will cause early flash tube failure and void the flash tube warranty XENON FLASH TUBE PROCEDURES 1 A xenon flash tube can be very photosensitive One will flash nor mally when exposed to an external light source but may become hard to fire when subjected to darkness They will become hard firing with age or when exposed to a very high temperature A hard firing tube will sometimes operate with the engine running but will fail when operated on a low battery They can develop a leak through eggshelling of the glass or a leak can develop around the seal of the wire to the glass This is caused by hot and cold cycling of normal operating of the system 4 They can go into self ionization continuously glow a light blue thus rendering the entire system non operational until flash tube is replaced This most likely occurs when the input voltage is highest This can be checked by turning the system off When turning the system back on it generally will operate normally for a few flashes before going back into self ionization ANY OF THE ABOVE MENTIONED CONDITIONS ARE REASONS FOR REPLACEM ENT OF THE XENON FLASH TUBE NOTE Installing one new flash tube in any multi head strobe light sys tem will sometimes cause the remaining old flash tube to misfire
24. to the scribe line to fit the A612 lens Due to the uneven surface of the Cessna lens retainer the A612 will con tact only the front and rear radius Place the sponge rubber pad supplied under the A610 flash tube to firm the assembly RTV is recommended to secure lens in the mod ified retainer 6 The flash tube interconnecting cable is routed through square holes in the rear bulkhead of the position light area 7 Install the modified position light lens retainer A610 flash tube and A612 lens using original hardware J al MODEL A625 SERIES INSTALLATION FAA PM A APPROVED Model Number Part Number Description A625 01 0770058 03 standard unit clear lens A625D 01 0770058 13 radio shielded clear lens Specifications Weight EEE EE EE EE NN nee aa 0 2 Ibs Exposed CI RE EE EJ bode estes eee eee pee ae 1 7 Dimensions 5 50 50 LEAD LENGTH CONNECTOR WIRING POS 1 RED ANODE POS 2 BLACK CATHODE POS 3 WHITE TRIGGER Figure 19A Spare 1 Parts 68 2290005 34 LENS RFI COATED N A 4 40 HEX NUT BRASS 68 2290005 30 LENS CLEAR RETAINER LENS N A 4 40 X 1 2 PPHMS MS51957 17 01 0770058 13 STROBE LIGHT ASSY MODEL A625D 01 0770058 03 STROBE LIGHT ASSY MODEL A625 ITEM PART NUMBER DESCRIPTION 2007 Whelen Engineering Company Inc 1 1 N N IN OO O O OO
25. with an adapter for testing Grimes and Hoskins strobe light systems Model Number Part Number Description 6542600 01 0765246 00 Strobe System Tester Please Order Part Number 01 0765246 00 Photos Show Typical Installations 3 0 Document 05131A When the speaker head phone and microphone use the aircraft s ground for return to the radios one will always experience some inter ference The amount of interference depends upon how much potential difference there is between the two ground points Isolating the audio grounds from the airplane ground at the speaker head phone and microphone junctions and grounding the aforementioned with the radio at one central ground point will eliminate the majority of all ground inducted radio noise Do not parallel any audio leads with any power lead supplying energy to a noise generator i e alternator electric motor or DC choppers such as inverters and strobe light power supplies The interconnecting cable between the power supply and the remote strobe lighthead assembly radiate very little for the output circuit of the power supply is very low impedance They can radiate RF like an anten na if the shield is not terminated to ground The radiation of RF energy is reduced to a minimum by properly terminating the shield at one end or the other generally the power supply end but which ever proves the quietest ground Do not terminate both ends When installing a strobe light syst
26. 10 2 na W1290 A427 3 A508 A441 A615 A600 PR A650 PR A650 W1285 PR A600 PG A650 PG W1285 PG 32 Document 05131A APPENDIX A PIONEERS INSAFETY SIGNALS WHELEN ENGINEERING COMPANY INC AVIATION DIVISION Effective November 1 2006 Subject Whelen STC Permission Statement To Whom It May Concern Whelen Engineering Company hereby authorizes qualified aviation installers to use the following STC installation data to modify aircraft for installation of Whelen Anti Collision lighting systems SAG6ISEA SA800EA SAGNE SA21NE Jim Olson Vice President Aviation Lighting Products 2007 Whelen Engineering Company Inc Document 05131A 33 United States Of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Vilar SA615EA Whelen Engineering Company Inc Route 145 Winthrop Road Chester Connecticut 06412 0684 es Cartifecate issued bo ceri bes fat lhe change in the hyre design for the following product with the lionitatione and conditions Barber as specified hereon meets the atnoorthaness requirements of Part 3 6 23 27 ofthe Civil Air Federal Aviation Bepuletions Creginal Product Tipo Certificate ambar See Attached Eligibility List dated June 18 1999 Model Installation of Whelen Anti Collision Strobe Light Systems Part Number 01 0770006 01 0770028 01 0770029 01 0770062 01 0770900 and 01 0771055 as replacemen
27. 21 47 Document 05131A United States Of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Continuation Sheet Nam Z SABO0 A Date Amended June 17 2005 ELIGIBILITY LIST September 8 1999 AIRCRAFT MANUFACTURER MODEL TYPE CERTIFICATE Cessna Cont d 170 170A 170B A 799 172 172A B C D E F G 3A12 H I K L M N P 175 175A B D P172D 3A17 172RG 177 177A B A13CE 177RG A20CE 180 180A B C D E F G 5A6 H J K 182 182A B C D E F G 3A13 H J K L M N P Q R T182 R182 TR182 185 185A B C D E 3A24 A185E A185F 188 188A B A188 A188A A9CE 188B T188C 190 195 195A B A 790 206 P206 P206A B C D E A4CE TU206A B C D E F G TP206A B C D E U206 U206A B C D E F G 207 207A T207 T207A A16CE 210 210A 210B 210C 210D 3A21 210E 210F T210F 210G T210G 210H T210H 2103 T210J 210K 210 5 205 210 5A 205A T210K 210L T210L T210M T210N 210N P210N Aro A ESAS Sf dii gle TET EGET Any alteration of this certificate is punishable by a fine of not exceeding 1 000 or imprisonment not exceeding 3 years or both FAA Form 8110 2 1 10 69 Page 6 of Document 05131A This certificate may be transferred in accordance with FAR 21 47 45 United States Of America Department of Transportation Federal Abiation Administration Supplemental Type Certificate Continuation Sheet Z
28. 23 PA 23 160 PA 23 235 1A10 PA 23 250 PA E23 250 PA 24 24 250 24 260 24 400 1A15 PA 28 140 28 150 28 151 28 160 2A13 28 161 28 180 28 235 28S 160 28R 180 285 180 28 181 28R 200 28R 201 28R 201T 28RT 201 28RT 201T 28 201T 28 236 PA 30 PA 39 ALEA PA 31P ASEA PA 31 PA 31 300 325 350 A20SO PA 32 260 PA 32 300 A3SO 325 300 Mooney M20B C D E F G 2A3 Mitsubishi MU 2B MU 2B 10 15 20 30 A2PC Univair Stinson 108 108 1 2 3 5 A 767 NOTES TO ELIGIBILITY LIST 1 Aircraft as marked require specific attention to proper balancing of the rudder Refer to the Manufacturer s Service Manual for balancing instructions 2 Installations on these aircraft require prior or concurrent installation of STC SA4 977 Ante ST b Seats An LF Fe SLR fa iii Lal SLE LD PR ee ee Any alteration of this certificate is punishable by a fine of not exceeding 1 000 or imprisonment not exceeding 3 years or both eee 57 ee FAA Form 8110 2 1 10 69 Page 8 of 8 This certificate may be transferred in accordance with FAR 21 47 Document 05131A 47 nited States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Member sar Spis certificate issued to Whelen Engineering Company Incorporated Deep River Connecticut 06417 Mherefor av apecsf d hereon meets the acrorlhimess reguirement cf Bard 3 of lhe Civil Air Regulations Original
29. 44 30 02 0350053 00 38 0230104 00 19 150002 009 38 0230021 00 68 4230020 40 68 4230020 50 02 0350003 01 34 0414020 65 34 0428020 65 Description Lens Retainer Assy for A650 Series Radio Shielded Mounting Adapter for A470A Series Mounting Adapter for A470A Series 3 3 4 dia mounting pattern Lens Clear for SACF amp A450 Series Strobe Tube for SACF amp A450 Series Gasket for SA402 Lens Lens Retainer for W1285 Series Gasket for W1284 Lens Position Light Lens Green Position Light Lens Red Base Plate Assy Position Light Lamp 14V Position Light Lamp 28V A copy of the Whelen warranty regarding products described on these pages may be obtained free of charge from the Whelen Engineering Company Inc Chester Connecticut 06412 2007 Whelen Engineering Company Inc Document 05131A 31 PARTS BREAKDOWN AIRCRAFT STROBE BEACONS FP A628 mi F A425A lt gt A457B D A628 D OPTIONAL OPTIONAL Co A457A ss A457A QI 01 0450685 00 1 i 4 A455 DI NZ heng NS 2 lt 01 0450685 00 SE lt A504 Q SA406 A424 A A444 A441 1 A625 A441 er naag A450 A470A When ordering models A500A and A555A or lens assembly part number A457B D make sure to SPECIFY HORIZONTAL OR VERTICAL W1282 606 A626 A626 A612 D A626 D A626 D OPTIONAL a OPTIONAL OPTIONAL ae W1284 W1284 OMO LG NU Z IMPORTANT NOTE gt a ho A612 W1283 W1283 A6
30. 6136 LED Module Assembly P N 28V 01 0271057 01 P N 14V 01 0271057 00 4 x 46 32 MTG holes equally spaced on a 1 625 bolt circle 4 x 46 32 MTG holes equally spaced on a 1 250 bolt circle CI 6 32 Flat Head 100 Countersink typ DJ O Adapter Plate P N 07 771051 100 Suggested Mounting Hole Pattern AAA O Y 14VDC Red 18 Ga or 28VDC White 18 Ga eo TEFLON WIRE 12 1 LG lt Q QI gt Ti Document 05131A 1 3 MODEL HRCFA SELF CONTAINED STROBE ANTI COLLISION LIGHT ASSEM BLY FAA PM A APPROVED Model Number Part Number Description HRCFAR 01 0770029 29 standard assembly Red lens HRCFAW 01 0770029 30 standard assembly White lens HRCFAS 01 0770029 31 standard assembly Split Red White lens HRCFADR 01 0770029 32 radio shielded Red lens HRCFADW M0 0020238 usss dra radio shielded White lens HRCFADS 01 0770029 34 radio shielded Split Red White lens MODEL SACF SELF CONTAINED STROBE ANTI COLLISION LIGHT ASSEM BLY FAA PMA APPROVED Model Number Part Number SACF 01 0770030 01 Specifications both models Description A A Aviation White lens Input Voltage r a 1 14 to 28 Volts D C Current Draw 1 tenes 3 2 Amps 14 Volts D C 1 6 Amps 28 Volts D C
31. 999 Model Installation of Whelen Anti Collision Strobe Light System Part Numbers 01 0770019 01 0770024 01 0770030 01 0770031 01 0770032 01 0770053 01 07700544 and 01 0770058 and applicable associated power supplies in accordance with Whelen Anti Collision Light Systems Installation and Service Manual May 2005 Document No 05131 Rev or later FAA approved revision Limitationi and Conditions See continuation sheet 2 of 8 The STC holder will provide each person it permits to use this certificate to alter the product written evidence of the agreement in a form acceptable to the Administrator Late of application May 2 1969 Date retsseed Date of is e nee November 14 1969 Leto amended June 17 2005 See page 3 for amendment history Z VAL LOL Signature Richard B Noll Manager Boston Aircraft Certification Office Title au TELGE SE FRS ELLEN NNN eee mm bk LLL rense O medi al A MA Any alteration of this certificate is punishable by a fine of not exceeding 1 000 or imprisonment not exceeding 3 years or both FAA Form 8110 2 10 68 Page 1 of 8 This certificate may be transferred in accordance with FAR 21 47 40 2007 Whelen Engineering Company Inc Document 05131A United States Of America Department of Transportation Federal Abtation Administration Supplemental Type Certificate Continuation Sheet Nam Z SA8OOEA Date Amended J
32. A 1A A lEA AA 5 A16EA Beech 23 A23 A23A A23 19 24 19A AICE B19 M19A B23 C23 A24 A24R 5 A33 B33530353 D35 E35 P35 A 777 G35 35R H35 J35 K35 M35 N35 P35 35 3A15 V35 V35A V35B 35 33 35 A33 35 B33 35 C33 35 C33A 36 A36 E33 E33A E33C F33 F33A F33C 50 L 23A BSO L 23B C50 SA4 D50 L 23E D50A D50B D50C DSOE E50 L 23D RL 23D F50 G50 H50 J50 95 55 95 A55 95 B55 95 BS5B T 42A 3A16 95 B55D 95C55 95 B95 B9SA D95A E95 D55 D55A E55 ESSA 56TC ASGTC 58 65 L23F A65 A65 8200 65 8200 65 80 3A20 65 A80 8800 65 B80 65 88 B90 C90 65 90 65 A90 65 A90 1 U 21A RU 21A RU 21D 65 A90 2 RU 21B 65 A90 3 RU 21C 70 Any alteration of this certificate is punishable by a fine of not exceeding 1 000 or imprisonment not exceeding 3 years or both sn EEES FAA Form 8110 2 1 10 69 Page 3 of 6 This certificate may be transferred in accordance with FAR 21 47 36 O 2007 Whelen Engineering Company Inc Document 405131A United States Of America Department of Transportation Federal Afriation Administration Supplemental Tupe Certificate Continuation Sheet Pe Veglie SA615EA Date Amended February 22 2007 ELIGIBILITY LIST June 18 1999 AIRCRAFT MANUFACTURER MODEL TYPE CERTIFICATE Beech Cont d 60 A60 ARCE 99 99A 100 A14CE Bellanca 14 19 3A 17 30 17 30A 17 31A 1A3 17 31ATC TEC TECA 7FC 7GC 7GCA 7GCAA A 759 7GCB 7GCBA 7GCBC 7H
33. ATTERNS All aircraft must have an approved anti collision light and position light system for nighttime operations The position lights consist of an Aviation Red on the left side an Aviation Green on the right and an Aviation White taillight REF FAR 23 1389 The anti collision lighting system is required under FAR PART 91 205 c 3 There are different requirements affecting different aircraft These aircraft are categorized by the date of application for type certificate Home built aircraft are determined by the date of issuance of the Experimental Operating Limitations The different categories are as follows Aircraft for which type certificate was applied for after April 1 1957 to August 10 1971 These anti collision systems must produce a minimum of 100 effective candela in Aviation Red or White REF FAR 23 1397 360 around the aircraft s vertical axis 30 above and below the horizontal plane REF FAR 23 1401 Aircraft for which type certificate was applied for after August 11 1971 to July 18 1977 These anti collision systems must produce a minimum of 400 effective candela in Aviation Red or White REF FAR 23 1397 360 around the aircraft s vertical axis 30 above and below the horizontal plane REF FAR 23 1401 Aircraft for which type certificate was applied for after July 18 1977 These anti collision systems must produce a minimum of 400 effective candela in Aviation Red or White REF FAR 23 1397 360
34. C 7JC 7KCAB Bell 206A 206B H2SW 206L 206L 1 206L 3 206L 4 407 47B B3 D DI E G G 2 H 1 H 1 47G 2A 2A 1 3 3B 3B 1 3B 27 2H3 A AA 25 SA 47J K J 2 J2A 2H1 Britten Norman BND DA DAD TAA DA AITEU BN 2A MK IM A29EU Cessna 150 150A B C D E F G H J K 3A19 L M A150K A150L A150M 152 A152 172 172A B C D E F G B LK 3A12 L M N P 175 175A B D P172D 172RG 3A17 177 177A B A13CE 177RG A20CE 180 180A B C D E F G H J K SA6 182 182A B C D E F G H J 3A13 K L M N P Q R T182 R182 TR182 185 185A B C D E A185E A185F 3424 188 1884 B A188 A188A A188B T188C A9CE Aro A TT i zLF1rr_e Any alteration of this certificate is punishable by a fine of not exceeding 1 000 or imprisonment not exceeding 3 years or both FAA Form 8110 2 1 10 69 Document 05131A This certificate may be transferred in accordance with FAR 21 47 37 Hrited States Of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Continuation Sheet n Vilar SA615EA Date Amended February 22 2007 ELIGIBILITY LIST June 18 1999 AIRCRAFT MANUFACTURER MODEL TYPE CERTIFICATE Cessna Cont d 206 P206 P206A B C D E AACE TU206A B C D E F G TP206A B C D E U206 U206A B C D E F G 207 207A T207 T207A A16CE 210 210A 210B 210C 210D 210E 3A21 210F T210F 210G T210G 210H T210H 2103
35. CTOR SHIELDED CABLE 1 STROBE SUPPLY 2 2 TUBE END 3 3 END X SHIELD WIRE CUT AND TAPE SHIELD WIRE AT STROBE TUBE END GROUND SHIELD WIRE AT POWER SUPPLY END ONLY M ODEL HDACF STROBE POWER SUPPLY ASSEM BLY _ e FAA PM A APPROVED Specifications Model Number HDACF Part Number 01 0770028 05 Current Draw 7 0 Amps 14 Volts D C 3 5 Amps 28 Volts D C Weight 2 1 Ibs Length 5 50 Height 201 Operation This power supply will operate up to 3 strobe lighthead assemblies When operating two lights in the alternating mode 42 joules of power are produced for each light While in simultaneous mode power to each light is 21 joules When operating 3 lights strobe outlet 1 pro duces 42 joules of power and alternates with strobe outlets 2 amp 3 pro ducing 21 joules each that flash simultaneously see Figure 7B Jumper to be inserted in trigger selector outlet 1 2 3 N C da er Connector for input power cable OEE ds STROBE HOOK UP PIN 1 RED ANODE PIN 2 BLACK CATHODE Figure 7A PIN 3 WHITE TRIGGER Trigger Function Jumping pins 1 and 2 on the trigger plug will provide an alternating flash pattern between strobe outlet 1 and strobe outlet s 2 and or 3 Installing a switch in series with the jumper will allow strobe outlets 2 amp 3 to be turned off while strobe outlet 1 remains on see Figure 7B Switch normally
36. ELIGIBILITY LIST ANTI COLLISION LIGHT INSTALLATION PROCEDURES STC SA800EA STC SA615EA STC SA21NE The following information is to assist in the installation of a custom Whelen anti collision strobe light system on any aircraft and how to return the aircraft back to service with compliance to FAR Part 91 205 c 3 1 Choose the anti collision light system which is most applicable to the aircraft N With reference to the STC s Limitation and Conditions for field of coverage requirements Check the field of coverage of the pro posed location oo These STC s document that Whelen s anti collision strobe lights meet the requirements as specified in AC 43 13 2A Chapter 4 PAR 51 a and b 1 STC SA615EA covers replacement of original equipment STC SA800EA and STC SA21NE cover installation of new anti collision light systems A Vertical fin mounted anti collision strobe beacons will conform to the FAR 23 1401 0 5 steradian 1642 sq degrees maximum solid angle blockage requirements on most standard configurations CAM 3 and FAR Part 23 high or low wing type aircraft An aver age solid angle blockage for an installation of this type is 1324 sq degrees Fuselage mounted anti collision light systems require two 2 anti collision strobe beacons to get the 75 degrees required Two lights mounted in this manner exceed the steradian requirements of 21 600 sq degrees total coverage al O F
37. IS MOUNTED IN AN INVERTED POSITION NA 6 32X 5 16 SS HEX NUT MS35649 264 68 4230044 30 LENS CLEAR 4 01 0450685 00 CLAMP RING 50 8 NA 632X1 2 PHILLIPS PHMS MS51957 30 GASKET LENS 046 THK 1 02 0350053 00 FLASHTUBEASSV 1 p mm 01 0770032 00 A450 STROBE LIGHT HEAD ASSEMBLY E PART NO DESCRIPTION Figure 15B 2007 Whelen Engineering Company Inc Document 05131A 17 MODEL A650PG PR SERIES WINGTIP STROBE ANTI COLLISION POSITION LIGHT ASSEM BLY FAA PM A APPROVED Model Number Part Number Description A650PG14 01 0770054 00 position green 14 volt A650PG28 01 0770054 01 position green 28 volt A650PR14 01 0770054 02 accord enna eet position red 14 volt A650PR28 01 0770054 03 suino position red 28 volt A650PGD1 01 0770054 04 position green 14 volt radio shielded A650PGD2 01 0770054 05 position green 28 volt radio shielded A650PRD1 01 0770054 06 position red 14 volt radio shielded A650PRD2 01 0770054 07 position red 28 volt radio shielded Specifications Position Lights Current DraW 2 0 Amps 14 Volts D C 1 0 Amps 28 Volts D C Wed s cee spiny eter va dda eds ponti 6 lbs A ET ade ATI 3 84 Installation The A650 Series must be properly mounted to comply with FAR Part 91 205 c 2 amp c
38. Lens No Check Lens Mounting Loose or missing hardware Yes Tighten or Replace No Check Operation Improper Operation Yes Check wiring and connections Refer to trouble shooting procedures for strobe lights No 2 8 Document 05131A STROBE SYSTEM TROUBLE SHOOTING TROUBLE SHOOTING PROCEDURES FOR AVIATION ANTI COLLISION STROBE LIGHT SYSTEMS WHEN REPAIRING WHELEN ANTI COLLISION STROBE LIGHT SYS TEMS USE ONLY WHELEN FAA APPROVED HARDWARE BE CAREFUL OF STROBE LIGHT PARTS THAT ARE SIMILAR IN APPEARANCE The Whelen Aviation Strobe Light is a condenser discharge strobe light system A condenser is charged to approximately 450 volts DC then discharged across a xenon flash tube at controlled intervals The con denser is parallel across the xenon flash tube that is designed to hold off the 450 volts DC applied until the flash tube is triggered by an external pulse This pulse is generated by a solid state timing circuit in the power supply When trouble shooting a strobe light system first determine if the trouble is with the flash tube or the power supply This can be accom plished by replacing the flash tube assembly with a good operating flash tube or with the use of a Whelen Strobe Check unit Whelen s power supplies are protected against a short or open circuit on the output In either case the power supplies will effectively turn themselves off when subjected to a shorted output of
39. MU 2B 10 20 15 30 Wing Tip and Tail Strobe Light Installation Procedure dated 19 February 1971 is required in addition to the Anti Collision Light Systems Installation and Service Manual Document 05131 Rev or later FAA approved revision 7 This approval should not be incorporated in any aircraft for these specific models on which other approved modifications are incorporated unless it is determined that the interrelationship between this change and any of those previously incorporated approved modifications will not introduce any adverse effect upon the airworthiness of the aircraft This determination should include a night flight check as specified in AC 43 13 2 Chapter 4 Paragraph 42A NOTE Aircraft whose application for type certification was made before April 1 1957 may but need not comply with the field of coverage requirements of FAR 23 27 1401 b Compliance with FAR 91 33 c may be shown provided the light installation is in accordance with data approved prior to August 11 1971 and applicable criteria of Advisory Circular 43 13 2 are met AMENDMENT HISTORY This STC has been previously amended on the following dates 11 20 69 4 23 70 12 10 70 5 26 71 9 14 71 5 18 72 9 22 72 11 7 72 7 21 76 7 30 76 12 30 77 2 21 78 10 4 78 5 17 79 3 26 81 8 5 81 8 25 81 5 21 82 7 16 91 11 22 93 6 7 99 6 18 99 9 8 99 Any alteration of this certificate is punishable by a fine of not exceeding 1 000 or im
40. Modified Wingtip EN 7 Drill the third mounting screw hole for the navigation light and complete the installation reference the enclosed information Replacement Parts O 2007 Whelen Engineering Company Inc 14 02 0250276 03 FLASH TUBE ASSEMBLY MOLEX CONNECTOR 13 02 0250276 00 FLASH TUBE ASSEMBLY A610 12 68 2290005 30 LENS FLASHTUBE A612 11 19 170052 009 RETAINER LENS A626 10 N A 46 32 X 5 16 PHILLIPS FHMS MS51959 27 8 02 0350003 01 BASE PLATE ASSEMBLY W1285 2 7 38 0130106 00 GASKET FLASHTUBE A427 3 6 38 0230021 00 GASKET LENS W1283 5 34 0414020 65 LAMP 14V W129014 4 34 0428020 65 LAMP 28V W1290 28 3 68 4230020 40 LENS GREEN W1284G 2 68 4230020 50 LENS RED W1284R 1 02 0350072 35 LENS CLEAR A626D 68 2290005 34 LENS RFI COATED ITEM PART NUMBER DESCRIPTION Document 05131A 1 9 INSTALLATION OF MODEL A610 Model Number Part Number Description AA 02 0250270 00 AE standard unit 6 leads Specifications A610 Flash Tube Weight a da 0 09 Ibs Model Number Part Number Description A6G12 68 2290005 30 standard clear lens
41. T ASSY A500A V D 14 01 0770024 03 TAIL POS amp STROBE LT ASSY A500A H 28 Dal 01 0770024 02 TAIL POS amp STROBE LT ASSY A500A H 14 01 0770024 01 TAIL POS amp STROBE LT ASSY A500A V 28 ITEM PART NUMBER DESCRIPTION Model A500A Installation 2007 Whelen Engineering Company Inc Document 05131A 23 MODEL A600 PG PR SERIES INSTALLATION FAA PMA APPROVED Model Number Part Number Description A600PG14 01 0790006 00 position green 14 volt A600PG28 01 0790006 01 position green 28 volt A600PR14 01 0790006 02 position red 14 volt A600PR28 01 0790006 03 position red 28 volt A600PGD1 01 0790006 04 position green 14 volt radio shielded A600PGD2 01 0790006 05 position green 28 volt radio shielded AGOOPRD1 01 0790006 06 position red 14 volt radio shielded A600PRD2 01 0790006 07 position red 28 volt radio shielded Specifications Position Lamps Power Consumption Total 4 0 Amps 14 VDC EE EE a Li 2 0 Amps 28 VDC LEN EE EE ad apa 0 8 Ibs e AU o be 5 63 Width eo soe suas needs oe ed des a oe oe eae eee Ge eee 1 7 2 ON 2 4 Operation Wingtip anti collision forward position and tail position lights all in one compact unit Tail position lig
42. able cut the shield wire and WIRE it to a good ground DO NOT CUT THE BLACK WIRE 3 This must be done for each strobe light connection See Figure 6A 6 Document 05131A Wiring WARNING STROBE LIGHT POWER SUPPLIES ARE POLARITY SENSITIVE REVERSING THE INPUT POLARITY WILL CAUSE SEVERE DAMAGE TO THE POWER SUPPLY Steps below Ref AC 43 13 1B Chapter 11 Sections 1 2 3 amp 7 1 Choosing wire size of A input lead refer to Paragraph 444 Electric Wire Chart Figure 11 7 amp 11 7A with reference to Strobe Light Model Current requirement chart on page 6 amp 11 and Wire and Circuit Protection Chart Figure 11 1 2 Shielded wire is not generally necessary but has proven effective in reducing the possibility of radio interference 3 The power supply shall acquire its power from a low imped ance source such as the alternator or generator end of the electrical buss as close to the battery as possible Do not ground power supply to airframe This can attenuate emi rfi noise to airframe causing it to act as an antennae for inter ference in aircraft audio amp electrical systems 4 For penetrating pressure hull refer to the aircraft service manual 5 Checkall avionics systems for interference FI A igure 6A BIN 1 RED ANODE PIN 2 BLACK CATHODE PIN 3 WHITE TRIGGER SHIELD RFI DRAIN TO GROUND 3 POS PIN HSG 3 POS SOCKET HSG POWER 1 3 CONDU
43. ae SA800EA Date Amended June 17 2005 ELIGIBILITY LIST September 8 1999 AIRCRAFT MANUFACTURER MODEL TYPE CERTIFICATE Cessna Cont d 310 310A B C D E F G 3A10 H L J 3103 1 E310J 310K L N P T310P 310Q T310Q 320 A B C D E F 320 1 3A25 340 340A 336 A2CE 337 337A B C D T337D A6CE 337E T337E 337F T337F T337G 401 401A B 402A B ATCE 411 411A 421 421A 414 421B DeHavilland of DHC 2 MK L MK IL MK II A 806 Canada DHC 3 A 815 DHC 6 Models 1 100 110 ASEA 200 210 300 Fairchild Hiller FH 1100 H2WE Grumman G 164 G 164A G 164B 1A16 Helio H 250 H 295 H 391 H 391B 1A8 H 395 H 395A Hughes 269A 269A 1 269B 269C 4H12 Piper PA 11 A 691 PA 12 A 780 PA 14 A 797 PA 15 A 800 Any alteration of this certificate is punishable by a fine of not exceeding 1 000 or imprisonment not exceeding 3 years or both FAA Form 8110 2 1 10 69 Page 7 of 8 This certificate may be transferred in accordance with FAR 21 47 46 2007 Whelen Engineering Company Inc Document 05131A United States Of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Continuation Sheet Number SA800EA Date Amended June 17 2005 ELIGIBILITY LIST September 8 1999 AIRCRAFT MANUFACTURER MODEL TYPE CERTIFICATE Piper Cont d PA 16 1A1 PA 17 A 805 PA 18 Series PA 19 1A2 PA 20 144 PA 22 Series 1A6 PA 25 Series 2A8 PA
44. coverage It is a direct replacement for the standard tail position light Available in a radio shielded version Voltage 14 or 28 and mounting horizontal or vertical must be specified when ordering Dimensions WIRE EXIT REF Figure 20A CONNECTING WIRING OF THE A500A TO THE A441 AMP 3 POSITION PIN CONNECTOR HOUSING AND THE A444 AMP 2 POSITION PIN HOUSING CONNECTOR Anode Cathode Trigger Position Light A Position Light Ground 2 2 Document 405131A RED wire BLACK wire WHITE wire BLUE wire BLUE wire Pin 1 of A441 Pin 2 of A441 Pin 3 of A441 Pin 1 of A444 Pin 2 of A444 Installation 1 Remove the Model S tail position light by removing the two 2 retainer ring screws 2 This unit fits directly in place of the Grimes Model S tail position light It is however sometimes necessary to open the mounting hole in the aircraft fairing to 1 10 inch to clear the body of the A500A The body protrudes 1 40 inch into the tail fairing 3 Establish the proper light pattern of the A500A tail position light The retainer shield must be located so that the bottoms of the V notches are vertical parallel to the rudder to shadow the light so it will produce a horizontal light pattern of 70 degrees left and right of straight back of aircraft 1 75 HORIZONTAL VERTICAL FIG 20B MOUNTING SURFACE A500A Spare Par
45. ctor Power Output Pin 1 Top RED wire anode Pin 2 Center BLACK wire cathode Pin 3 Bottom WHITE wire trigger Right Connector Power Input Pin 1 Top RED wire 13 to 30 volt positive input Pin 2 Center BLACK wire ground Pin 3 Bottom Synchronization pin If synchronization is desired connect an 18 gauge wire between pin 3 on each power supply 8 Document 05131A CHESTER CONNECTICUT 00412 0884 OUTPUT POWER 1 ANODE 1 2 CATHODE 3 TRIGGER Mounting 1 600 938 MTG MTG 187 DIA 8 MOUNTING HOLES Figure 8C MODEL A490TCF STROBE POWER SUPPLY FAA PM A APPROVED Model Number A490TCF Part Number 01 0770006 08 MODEL A490TCCF STROBE POWER SUPPLY FAA PMA APPROVED Model Number A490TCCF Part Number 01 0770006 09 Specifications Both Models Current Draw 1 7 Amps 14 Volts D C 0 85 Amps 28 Volts D C Weight 1 2 lbs Length 5 00 Width 3 12 Height 2 38 Operation MODEL A490TCF This model operates one strobe lighthead It is our most compact unit and can be mounted in the wingtip and or the tail i adjacent to the lighthead It produces an accumulated 19 joules of power It will only meet 400 ECP when used with the A470A W This unit can not be synchronized This power supply operates gt from 10 to 30 volts DC 4 Not appr
46. e continued from the location of the previous box flasher or power supply to the location of the new LED beacon The following information is to assist in the installation of a Whelen LED Flashing Anti collision Light System 1 The installation procedure described in the following text will be confined to a single light installation but is identical for multiple light installations 2 Using the suggested mounting hole pattern prepare the aircraft for means to secure the LED Flashing Anti collision Light assembly Remove any existing mounting adapters 3 14 28 VDC and ground leads equipped with an appropri ate sized breaker to be supplied to the LED Flashing Anti collision Light Assembly System Both leads must be connected by an approved FAA connection Insure that the wire leads and the pressure venting tube are all clear of any obstructions and ty wrap as required 4 Install the light assembly by first removing the lens Remove the adapter plate Attach the adapter plate to the aircraft mounting holes Refer to page 2 Reinstall the light assembly and lens 5 Check all avionics systems for interference from this installation 6 A flight check should be performed by a properly certified pilot 7 All inverted bottom mounted units shall require waterproofing of the flasher base assembly to the aircraft Note Drill a 1 8 hole in the center of the lens for bottom mount units 8 Update aircraft records c
47. e eee mene t 3 75 A eri 2 5 MODEL A450 SERIES FANPMA APPROVED Model Number Part Number Description A450 01 0770032 00 standard assembly Clear lens Specifications Wahi esa areena a as gawawus kanaa pusa NEEE A 0 3 Ibs EXpOSGd A E rina 2 25 DIaMeler y uuu 5 OES Lesere bw EES ear ee yea 25 MODEL H102 amp H103 SERIES Model Number Part Number Description H102 07 730068 000 flush mount adapter H103 11 230079 000 rotating beacon mount adapter Before with Quartz Light After with Remote Strobe Light The A450 and A470A remote anti collision strobe lighthead assemblies Model A470A Installation are direct replacement for the quartz type flasher using the orig inal or the H102 B mounting adapter The H102 B mounting adapter is mounted in the aircraft s structure Figure 14 with four 4 MS 20470 AD4 rivets or four 4 6 32 screws and self 102 Mounting Adapter 8X 0 136 150 locking nuts Drill out the center hole in the skin to allow access to the strobe head connector Z1 00 NI 2 485 Y 11 625 1 250 BOLT CIRCLE BOLT CIRCLE 1 6 Document 05131A FIG 15D A Vertical Fin and Rudder Mounting of Anti Collision Strobe Lights Rudder mounted anti collision lights should be located top center of the rudder hinge center line or rudder balance must be establ
48. e may be transferred in accordance with FAR 21 47 43 United States BE America Department of Transportation Federal Abtation Administration Supplemental Type Certificate AIRCRAFT MANUFACTURER Beech Cont d Bellanca Bell Britten Norman Cessna Continuation Sheet Nam fE SA800FA Date Amended June 17 2005 ELIGIBILITY LIST September 8 1999 MODEL 65 L 23F A65 A65 8200 65 80 65 A80 65 A80 8800 65 B80 65 88 B90 C90 65 90 65 A90 65 A90 1 U 21A RU 21A RU 21D 65 A90 2 RU 21B 65 A90 3 RU 21C 70 60 A60 99 99A 100 14 19 3A 17 30 17 30A _ 17 31A 17 31ATC TEC TECA TFC 7GC 7GCA TGCAA 7GCB 7GCBA 7GCBC THC 7JC TKCAB 206A 206B 206L 206L 1 206L 3 206L4 407 47B B3 D DI E C C 2 H 1 47G 2A 2A 1 3 3B 3B 1 3B 27 4 4A 5 5A 474 K J 2 J 2A BN 2 2A 2A 2 2A 6 2A 8 BN 2A MK II 120 140 140A 150 150A B C D E F G H J K L M A150K A150L A150M 152 A152 TYPE CERTIFICATE 3A20 A12CE A14CE 1A3 A 759 H2SW 2H3 2H1 A17EU A29EU A 768 SAI 3A19 rr EEE SE AN EEE EEE EEE 55 25 5557 EE 55252 ES FI Any alteration of this certificate is punishable by a fine of not exceeding 1 000 or imprisonment not exceeding 3 years or both FAA Form 8110 2 1 10 69 Page 5 of 44 2007 Whelen Engineering Company Inc This certificate may be transferred in accordance with FAR
49. e previously incorporated approved modifications will not introduce any adverse effect upon the airworthiness of the aircraft 3 The minimum effective intensity requirements of FAR 23 1401 f effective August 11 1971 will be met when the A600 PR and A600 PG are used with power supplies producing a minimum of 20 joules per flash se END sa l Any alteration of this certificate is punishable by a fine of not exceeding 1 000 or imprisonment not exceeding 3 years or both FAA FORM 8110 2 1 10 69 This certificate may be transferred in accordance with FAR 21 47 PAGE OF PAGES FAA AC 72 4435 Document 05131A 49 NOTES 50 Document 05131A WA EDEN ENGINEERING DENDERSHIP IN JO EP ED AV AAN PL IU IT IU The Latest Technology in Strobe and LED Aviation Lighting Visit us on the web at www whelen com O 2007 Whelen Engineering Company Inc Documen t 05131A 51 WARRANTY AND SERVICE REPAIR STATIONS UNITED STATES Whelen Engineering Company Inc Route 145 Winthrop Rd Chester CT 06412 0684 Tel 860 526 9504 Fax 860 526 2009 www whelen com aviation whelen com CANADA Wright Instruments Ltd 2762 Slough Street Mississauga Ontario Canada L4T 163 Tel 905 677 7161 Fax 905 677 2188 OVERSEAS AAR Allen Group International Kruisweg 705 P O Box 52 Hoofddorp Netherlands 2130 AB Tel 31 20 6552213 Fax 31 20 6533991 Aviatec JAR 145 RAI 059 str del Cascinotto 163 10156 Torino I
50. em provide a good ground and a low impedance source to the strobe light power supply Eliminate ground loops in audio circuits by using a centrally located ground point for all audio grounds Whelen Engineering has available RF shielded flash tubes and strobe lighthead assemblies to suppress the trigger pulse or clicking some times heard in the radios If noise problems persist and the procedures described have not cleared them up please contact the Whelen Engineering Company for assistance PARTS BREAKDOWN AIRCRAFT STROBE BEACONS Model Number Part Number 5068500 A402AR A402AS A402AW A424 A425 A425AH A425AV A426 A427 A427 4 A428 A428C A428D A435 A440 A441 A442 A443 A444 A446 A455 A457A A457AD A457BDH A457BDV A469A A469B A469D A469DK A504 A506 A507 A50814 A50828 A605 A606 A610 A612 A612D A615 A616 A626 01 0450685 00 68 2170504 50 68 2170504 60 68 2170504 30 11 430005 100 19 130000 100 19 0150350 01 19 0150350 02 19 190000 009 02 0250274 00 38 0130107 00 68 4290001 30 02 0350033 00 02 0350057 00 02 0350054 00 19 130074 009 01 0430011 00 01 0410823 00 02 0230081 00 02 0230007 00 02 0230085 00 38 0230002 00 68 4270002 30 02 0350038 35 02 0350038 37 02 0350038 36 01 0770044 00 01 0770044 02 01 0770044 01 01 0710834 00 06 150058 001 02 0350034 00 02 0350260 00 34 0412070 63 34 0428070 64 02 0350259 00 19 170049 009 02 0250276 00 68 2290005 30 02 0350071 35
51. gation light with an A650 head assembly installed or an A650 PR or PG and place it in position on the wingtip Mark around the navigation light base plate to get an outline of the navigation light profile on the wingtip 3 File or trim away the excess wingtip material to allow the naviga tion light and the A650 strobe light assembly to fit neatly in place Allow at least 0 060 inch clearance around the A650 strobe head assembly and the wingtip 4 To fill in the hole in the wingtip made by this trimming and to pro vide a platform for the navigation and strobe light assembly mount the navigational light base plate on the wingtip using the two 2 for ward screws with a sheet of polyvinyl between the wingtip and the base plate for a parting agent Tape the polyvinyl back over the wingtip to form a seal so it is possible to apply a polyester resin putty or epoxy putty like Bondo on the inside of the tip Build up the trimmed area with this putty as to have about 1 4 inch of mat N erial under and in back of the base plate Prepare the surface and the putty material in accordance with the putty manufacturer s instructions to assure a good bond to the wingtip 5 Remove the navigation light base plate and parting agent 6 To improve the appearance of this installation fill the indentation on the outside of the wingtip with the aforementioned putty and file the excess material to a clean profile before painting After With
52. hode flash tube ground PIN 3 WHITE Trigger SHIELD Ground at the power supply end only Caution When pins 1 and 2 or pins 2 and 3 are reversed the system will appear to operate normally however this condition will cause pre mature flash tube failure CLIP SHIELD Figure 5A A441 PINS POWER SUPPLY END RED A442 SOCKETS FLASH TUBE END Observe Color and Pin Numbers The retaining clip on the side of each pin or socket of the A441 and A442 connector assemblies must be bent out Reference illustration Figure 5A shown above so that they positively snap into the AMP 3 position socket nylon connector housing If it is not possible to get a good grip it is recommended that the pins and sockets be soldered to prevent burning of the wires INSTALLATION CABLE KITS Intermixing Strobe Light System Equipment Observe Color and Pin Numbers Cables Connecting Strobe Lights MUST BE Connected Correctly Whelen Engineering and Aero flash wiring between light assemblies and remote power supplies are identical as pictured below in Figure 5B CLIP SHIELD Figure 5B Grimes and SDI Hoskins wiring between light assemblies and remote power supplies are identical as pictured below in Figure 5C CLIP SHIELD Figure 5C Both Grimes and SDI sometimes use MS Cannon Type connectors Position A RED Anode Position B White or Blue Trigger Position C Cathode Black or Yellow All Kits include requi
53. ht eliminates the need for a tail mounted position light Available in 14 or 28 volts and in a radio shielded version The forward position lamp is 26 watts and the taillight lamp is 25 watts Installation The A600 Series must be properly mounted to comply with FAR Part 91 205 c 2 amp c 3 The light assembly must be mounted so that the light distribution pattern is not obstructed by any parts of the aircraft A limited amount of obstruction is permitted Ref FAR Part 23 1401 for anti collision lights and PAR 23 1387 for position lights The convergence of the two wingtip tail position must occur within 1200 feet directly behind the aircraft to comply with field of coverage requirements The baseplate must be mounted parallel to the vertical amp horizontal centerlines of the aircraft to project the patterns properly Mounting 1 If necessary fabricate the mounting pattern using dimensions found in figure 22A 2 Make the necessary wiring connections using 18 gauge wire for the position lights and Whelen 16 gauge 3 c cable for the strobe lights All connections must use FAA approved techniques 3 Remove the two 6 32 x 312 retainer mounting screws and retainer 4 Attach the base assembly to the wingtip using 3 6 32 counter sunk screws unit may be sealed around periphery with RTV or equivalent Re attach lens retainer see figure 23A OT 140 DIA 3 MOUNTING HOLES FOR 6 32 SCREWS 1
54. ished N after installation Refer to AC 43 13 2A Chapter 4 Paragraph 55 e Rudder Installation The rudder or fin cap is excellent for shadowing the prop and cabin area if the light is mounted far enough back e tee Round or streamline tubing cut to fit Metal bracket shaped to fit the vertical fin or rudder or vertical fin welded to 2 12 OD rudder with 2 1 2 OD 040 thick disc riveted 40 thick disc Reference AC 43 13 1B in place Reference AC 43 13 1B Chapter 2 Chapter 2 Section 2 Fabrication and installation of these mounting brackets are referenced in this approved installation manual and AC 43 13 1B and 2A Documentation of structural integrity of the fabricated installation must NOTE Mounting an A450 or A470A strobe lighthead assembly on a Pe approved by an IA or other representative of the FAA Conformity vertical fin or rudder can be accomplished by fabricating a mounting inspections will be performed with reference to approved techniques adapter similar to the ones shown in illustrations and procedures specified in this manual see page 3 Dimensions 7 5 2 i 3 50 EM i ej MAS EEG E MEM EN 01 0770019 20 STROBE ASSY RED WHITE A470A R W 01 0770019 19 STROBE ASSY WHITE A470A W 01 0770019 18 STROBE ASSY RED A470A R ITEM PART NUMBER DESCRIPTION Tea afila gt BG NN Lun AAA ene ness O lt Figure 15A REMOVE RTV WHEN UNIT
55. nts prior to 9 14 71 need only be checked for obstructed visibility to meet anti collision light requirements 3 Install the following placard Whelen Part No A421 1 or other FAA approved equivalent in view of the pilot WARNING TURN OFF STROBE LIGHTS WHEN TAXING IN VICINITY OF OTHER AIRCRAFT OR DURING FLIGHT THROUGH CLOUDS FOG OR HAZE STANDARD POSITION LIGHTS TO BE ON FOR ALL NIGHT OPERATIONS 4 On all helicopter installations install the following placard in view of the pilot THE WHITE STROBE LIGHT MUST BE TURNED OFF DURING ALL NIGHT TAKEOFFS AND LANDINGS 5 The modifications approved by this STC can be installed in conjunction with those approved by STC SA615EA or STC SA738EA as delineated in the Anti Collision Light Systems Installation and Service Manual Document 05131 Rev or later FAA approved revision See continuation sheet 3 of 8 A A O 77 7775 7 7 Any alteration of this certificate is punishable by a fine of not exceeding 1 000 or imprisonment not exceeding 3 years or both FAA Form 8110 2 1 10 69 Page 2 of 8 This certificate may be transferred in accordance with FAR 21 47 Document 05131A 4 1 United States Of America Department of Transportation Federal Atiation Administration Supplemental Type Certificate Continuation Sheet Naper SA800EA Date Amended June 14 2005 Limitelions and Conditions Continued 6 On Mitsubishi MU 2B MU 2B 10 20 15 30 aircraft Whelen s Mitsubishi
56. omplete Form 337 and obtain FAA field approval for installation If not covered under STC eligibility list 1 2 Document 05131A TSO C96a CLASS III APPROVED TSO C96a CLASS Ill APPROVED The conditions and tests required for TSO approval of this article are mini mum performance standards It is the responsibility of those installing this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards TSO articles must have separate approval for installation in aircraft The article may be installed only if performed under 14 CFR part 43 or the applicable airworthiness requirements i a 2 19 32 Dimensions i 3 3 32 79mm Adapter Plate No MFG Label YGROUND Black 18Ga Teflon Wire 12 1 LG Ny Sam 14VDC Red 18 Ga or 28VDC White 18 Ga TEFLON WIRE 12 1 LG Figure 12A Figure 13A GROUND Black 18 Ga TEFLON WIRE 12 1 LG O SII S O 2007 Whelen Engineering Company Inc Screw 4 40 X 5 16 PPHMS MS51957 14 P N 14 0050505 14 Washer 4 Lock Spring MS35338 135 P N 16 0050506135 Lens Retainer P N 19 171047 100 Lens P N 68 4971046 30 Lens Gasket P N 38 0250885 00 Screw 6 32 X 3 8 PPHMS MS51957 28 P N 14 0050503 28 Washer 6 Lock Spring MS35338 136 P N 16 005050
57. onal Voltage 14 VDC Average Input Current 1 2 Amps Peak Input Current 6 Amps 0 25 Seconds ET ET EEE nda oo is na 0 55 Ibs Model Number 7105501 Patt NUMDEr 2 riore elet peas 01 0771055 01 Operational Voltage r 28 VDC Average Input Current 0 6 Amps Peak Input Current 3 Amps 0 25 Seconds Te ssaa a RENATE 0 52 Ibs Operation Equipment Limitations The Model 71055 Series LED anti collision light assembly meets or exceeds the requirements of FAR 23 1401 and FAR 91 205 c 3 Continued Airworthiness The 71055 Series LED anti collision light assembly is designed with 6 vertical columns consisting of 2 LED s each Should any one LED or any vertical column fail the unit must be repaired or replaced Periodically inspect the lens and replace if there is excessive scratching discoloration or cracking Installation Procedures The Model 71055 is a self contained flash ing beacon that requires no external flasher or power supply In some installations it may be necessary to remove several existing compo nents When replacing flashing halogen beacon assemblies the flasher box and ballast resistor if present and associated wiring need to be removed When replacing strobe light assemblies the strobe power supply must be removed In both cases 18 gage DC voltage wires A amp Ground must b
58. or combined red white lens those effective on or prior to August 10 1971 b With the white lens those effective on August 11 1971 2 Install the following placard Whelen Part No A421 or other FAA approved equivalent WARNING TO AVOID OPTICAL ILLUSION AND SEVERE VERTIGO TURN ANTI COLLISION LIGHTS OFF UPON ENTERING CLOUDS FOG OR HAZE 3 The aircraft listed on the Eligibility List are those which have had both the physical installation of the lights substantiated and the field of coverage checked including the 20 mask Aircraft not included in the list can use these lights when the physical installation and field of coverage is substantiated as indicated in the Whelen Anti Collision Light Systems Installation and Service Manual May 2005 Document No 05131 Rev or later FA A approved revision section titled Aircraft Not Specifically Mentioned on the Eligibility List 4 The approval of this change in type design applies basically to aircraft listed on the attached eligibility list This approval should not be extended to other aircraft of these models on which other previously approved modifications are incorporated unless it is determined by the installer that the interrelationship between this change and any of those other previously approved modifications will introduce no adverse effect upon the airworthiness of the aircraft This determination should Include a night flight check as specified in AC 43 13 2 Chapter 4 Paragraph
59. ort out high volt age for extended length of time it will cause overheating of the output diodes and cause possible failure A normal operating power supply emits an audible tone If there is no sound emitted investigate 1 Determine that there is a proper input voltage at the power supply If this test is positive go to step 2 2 Clear all possible shorts at the power supply by disconnecting the output cables from the power supply outlets and connect an oper ating strobe lighthead assembly or a Strobe Check unit directly to the power supply outlet then apply the required voltage to the power supply input If this application proves positive the power supply is in working condition and the problem may be with the interconnecting cables 2007 Whelen Engineering Company Inc CABLE CONTINUITY CHECK PROCEDURES If pins 1 and 3 are reversed or if there is a short between pins 1 and 2 of the interconnecting cable the power supply will be rendered non operable until the short is cleared A short of this type will not cause any permanent damage to the power supply However a discharge of the condenser across pin 1 and pin 3 will destroy the trigger circuit in the power supply 1 Check for continuity between the connectors of each interconnect ing cable Pin 1 to pin 1 red wire anode Pin 2 to pin 2 black wire flash tube ground Pin 3 to pin 3 white wire trigger 2 Check for shorts between pins 1 and 2
60. oved for use with red strobe light RED ANODE POSITION 1 BLACK CATHODE POSITION 2 WHITE TRIGGER POSITION 3 WATE 14 28 VDC BLACK GROUND Dimensions Id 20 00 2 00 OUTPUT CABLE 20 00 2 00 INPUT CABLE WHITE 14 28V BLACK GROUND 3 12 Figure 9A 080 6 18 Mountin x 5 562 191 DIA g 4 PLACES 938 F SUGGESTED MOUNTING PLAN i STANDARD Figure 9B 2007 Whelen Engineering Company Inc Operation MODEL A490TCCF SERIES This model is the same as the A490TCF but has amounting plate with additional Z holes that directly replaces a factory installed systems on single engine Cessna s Aero Commanders and Grumman Americans RED ANODE POSITION 1 WHITE 414 28 VDC BLACK CATHODE POSITION 2 BLACK GROUND WHITE TRIGGER POSITION 3 Dimensions A490TC UNITS PLATE BOTTOM VIEW per OUTPUT CABLE INPUT CABLE MOUNTING HOLES 187 DIA 4 PLACES Figure 9C Mounting 500 P E D ed AN OA E P 3 250 iii ai DS Z 87 DIA 4 PLACES SUGGESTED MOUNTING PLAN FOR OPTIONAL BASE Figure 9D Document 05131A 9 SELF CONTAINED LIGHT ASSEMBLIES MODEL 70900 SERIES FLASHING ANTI COLLISION LIGHT ASSEMBLY Specifications Model Number 24 0200 ncrencedocce ane e meta mee dana 7090004 Part NumDBF_ _ sa de eek ds fa n eni 01 0770900 04 Operational Voltage
61. prisonment not exceeding 3 years or both FAA Form 8110 2 1 10 69 Page 3 of 8 This certificate may be transferred in accordance with FAR 21 47 42 2007 Whelen Engineering Company Inc Document 05131A Hrrited States Of America Department of Transportation Federal Abtation Administration Supplemental Type Certificate Continuation Sheet Nam Z SAS00EA Date Amended June 17 2005 ELIGIBILITY LIST September 8 1999 AIRCRAFT MANUFACTURER MODEL TYPE CERTIFICATE Aero Commander 100 100 180 1A21 111 A11SO 112 A12SO 500 500A 500B 500 S 6A1 500 U 520 560 560A 560E 560F 680 680E F 720 2A4 680FL 680FL P 680T V W 681 690 685 American Aviation AA 1 AA 1A AIIEA AA 5 A16EA Beech 23 A23 A23A A23 19 24 AICE 19A B19 M19A B23 C23 A24 A24R 35 A35 B35 C35 D35 E35 A TTI F35 G35 35R H35 J35 K35 M35 N35 P35 3A15 S35 V35 V35A V35B 35 33 35 A33 35 B33 35 C33 35 C33A 36 A36 E33 E33A E33C F33 F33A F33C 50 L 23A B50 L 23B C50 5A4 D50 L 23E D50A D50B D50C DSOE E50 L 23D RL 23D F50 G50 H50 J50 95 55 95 A55 95 B55 3A16 95 B55B T 42A 95 B55D 95C55 95 B95 B95A D95A E95 D55 D55A E55 ESSA S6TC AS6TC 58 Gio S TES gs os A A ET NNN S A Tl Any alteration of this certificate is punishable by a fine of not exceeding 1 000 or imprisonment not exceeding 3 years or both FAA Form 8110 2 1 10 69 Page 4 of Document 05131A This certificat
62. r plate as necessary so that the A625 clears the transparent window that covers the navigation light area 0 060 inch minimum The conduit for the navigation light wire is very small To get the nec essary wires to operate the strobe light and the navigation light through this conduit use a 20 gauge wire with less that 0 060 inch OD It has been found that the Belden 8502 or 8308 has an 0 058 inch OD Document 05131A 21 MODEL A500A SERIES INSTALLATION FAA PM A APPROVED Model Number Part Number Description A500AV14 01 0770024 00 vertical mount 14 volt A500AV28 D1 0770024 01 vertical mount 28 volt A500AH14 01 0770024 02 horizontal mount 14 volt A500AH28 01 0770024 03 horizontal mount 28 volt A500AVDI 01 0770024 04 vertical mount 14 volt radio shielded A500AVD2 01 0770024 05 vertical mount 28 volt radio shielded A500AHD1 01 0770024 06 horizontal mount 14 volt radio shielded A500AHD2 01 0770024 07 horizontal mount 28 volt radio shielded Specifications WEI qe us mitral DEN aa 0 3 lbs Exposed Height EE EE ee 1 7 DAN eee ea 1 5 Operation VERTICAL HORIZONTAL MOUNTING MOUNTING Combination Strobe Tail Navigation Light used when the wingtip anti collision lights are mounted in an enclosure and can t provide 360 of strobe
63. ragraph 52 a b of Chapter 4 COMPLETING THE ANTI COLLISION LIGHT INSTALLATION 1 Check all avionics systems for interference from this installation reference AC 43 13 2A Chapter 4 Paragraph 52 b 2 A flight check will be performed by a properly certificated pilot with reference to AC 43 13 2A Paragraph 52 a and b 3 If a solid angle blockage document must be established it should be performed after all masking has been installed and all flight test ing is completed See page 3 of this manual 4 WATERPROOFING OF STROBE LIGHT INSTALLATIONS When necessary to waterproof the installation of a strobe light mounting to the aircraft apply GE silicone rubber RTV 102 or equivalent around the open area where water could get in 5 Label all switches and breakers install Pilot Warning Placard 6 Up date aircraft records and complete form 337 STROBE SYSTEM WIRING Interconnecting Cable 1 The Whelen interconnecting cable shall be secured in place with approved aviation techniques 2 The cable shall not parallel ADF Gyro or Flux Gate compass leads closer than 12 inches 3 Reference should be made to AC 43 13 1B Chapter 11 Sections 3 and 7 when routing and fishing the interconnecting cable 4 Leave a service loop at the strobe lighthead end to allow access to the connector for flash tube replacement without having to dis assemble the aircraft 5 CABLE COLORING CODE PIN 1 RED Anode PIN 2 BLACK Cat
64. red connectors for hooking up the strobe light to the power supply only warning placards and the Installation Service Manual Cable is 16 gauge 3 c shielded The cable diameter is 275 The weight is 050 Ibs per linear foot Kits do not include switches or breakers In order to maintain the integrity of the installation one of the following installation kits must be used If the installer chooses to use different cable it must have the same or better electrical characteristics En Model Number Part Number Description b W HS5 01 0750215 00 5 Cable Kit A HT10 01 0750218 00 10 Cable Kit HS30 01 0750214 00 30 Cable Kit HD60 01 0750206 00 60 Cable Kit HDT390 01 0750205 00 90 Cable Kit HT 01 0750216 00 Install Kit Only No Cable x REPLACEMENT CONNECTORS Model Number Part Number Description A441 01 0430011 00 3 Position Male Connector with Pins A442 01 0410823 00 3 Position Female Connector with Sockets A444 02 0230007 00 2 Position Male Connector with Pins A446 02 0230085 00 2 Position Female Connector with Sockets 2007 Whelen Engineering Company Inc Document 05131A 5 STROBE POWER SUPPLY INSTALLATION INSTALLATION PROCEDURES Location 1 Consider areas or locations designated by the aircraft man ufacturer Do not mount the
65. red under STC eligibility list 1 0 Document 05131A TSO C96a CLASS III APPROVED Models 7090004 amp 7090005 are designed to replace existing light assemblies with the 3 3 4 Dia mounting pattern Ref Whelen HRCFA series 90081 Series and the old style rotating beacons It has the same mounting hole pattern No modification to the aircraft is required Dimensions En AN BA DOOK NOME DOE i a 4 04 06 14VDC Red 18GA Teflon Wire 18 LG Or 28VDC White 18GA Teflon Wire 18 LG Ground Black 18GA Teflon Wire 18 LG MFG Label Teflon Tube 18GA Pressure Venting Figure 10A Figure 11A Lens P N 68 4990257 30 Screw P N 14 062216 05M Gasket S P N 38 0250843 00 LED Module P N 14V 01 0270918 01 P N 28V 01 0270918 03 RTV required after hardware installation for inverted bottom mounted units A IS ZA N PZ I kap s Model 70900 series LED installation 1 00 Clearance for wires Typical Mounting Hole Pattern O 2007 Whelen Engineering Company Inc Figure 11B 3 46 32 x 3 8 Thread Document 05131A 1 1 SELF CONTAINED LIGHT ASSEMBLIES MODEL 71055 SERIES ANTI COLLISION LIGHT ASSEM BLY Specifications Model Number ia 7105500 PartNumber lena ea 01 0771055 00 Operati
66. sh tube failure 2 Connect the forward position light wires as follows using 18 gauge approved aviation wire or cable OQ RED 14 or 28 volts depending on aircraft voltage BLACK Ground 1 8 Document 405131A Dimensions m 3 84 ih G D y i lll HI il vil N y 1 35 1 79 Hi I Pin 1 RED Anode Pin 2 BLACK Cathode Pin 3 WHITE Trigger E ice Figure 16A Mounting Diagram BOTTOM VIEW 85 88 m 1 75 AN Z el ae a i J 280 DIA X 100 DIMPLE 140 DIA 3 MTG HOLES OPP SIDE Figure 16B Figure 17A Before A650 Wingtip Strobe Light Installation on Later Model Cessna Wingtips with Shortened Light Base Because Cessna has modified the Type E Series Wingtip Navigation Light by cutting off the back 1 3 inch and designed their wingtip to fit in closer to the light it will be necessary to do a little fiberglass work when completing this installation The A650 can be installed on these Cessnas in the manner below and instructions above 1 Remove the wingtip and the navigation light assembly 2 Take a complete Model W1285 navi
67. smitted into the radio through the A input lead to the radio Most of the new radio equip ment manufactured today has inadequate input filtering and any noise on the electrical buss is amplified in the radio and produced through the speaker and or head phones loud and clear Two things can be done to alleviate the problem 1 Connect the strobe light circuit breaker to the low impedance end of the electrical buss using a 16 gauge jumper as close to the battery as possible 2 Install additional filtering in the radio A line or provide an iso lated A source for the radios by installing a filter choke in series with the radio input power lead and a filter adapter to ground and reference all radios to their filter This will also improve the radio system from other line noises REF 2200 mfd 50V Capacitor Frequently the noise is not on the A lead but is conducted through the ground circuit Alternator electrical motor fuel pumps and strobe light power supplies draw heavy current through the ground circuit of the aircraft s frame Any voltage drop in the ground circuit between the bat tery ground and the radio ground can look like a signal to the radios STROBE SYSTEM TESTER Description A strobe system tester designed to determine the reason the strobe light system is not working properly This kit contains an instruction sheet and a trouble shooting procedure sheet Test power supplies and interconnecting cables It also comes
68. standard unit A650D 01 0770053 13 ss docks aan gee eee hake a dae radio shielded Specifications Werni EEE noes an eee aes Ab aces eee eee aeree 0 2 Ibs Exposed Height EE eh ogee pa Ge eee as 2 4 A650 Operation Dimensions 1 66 Converts existing Whelen W1285 position lights into a position anti collision light system by removing the existing retainer and replacing it with the A650 assembly Available in a radio shielded version A650 Wingtip Strobe Light To install the Whelen A650 strobe lighthead assembly on the aircraft proceed with the following instructions 1 Remove the wingtip navigation light and wingtip when necessary 2 Install the nylon three position AMP pin connectors A441 on the end of the flash tube wires RED in pin 1 BLAGK in pin 2 and WHITE in pin 3 3 Assemble the navigation light assembly on the wingtip using the A650 strobe light assembly as the navigation light lens retainer a Install the rubber pad supplied in kit on the position light base plate under the A610 flash tube if necessary to make the lens firm in its mounting 4 In some installations it will be necessary to mask the A650 strobe A650 Spare Parts light to reduce pilot annoyance The Navigation Light Detector will be a source of reflection and should be reduced in size or masked as necessary A small aluminum or plastic plate mounted between the navigation light and the wingtip protruding up or down as required
69. strobe power supply closer than three 3 feet of the ADF loop 2 For alternate locations consider areas such as the cabin baggage compartment the floor under the seat nonstruc tural bulkheads firewalls etc 3 If necessary fabricate support brackets or shelves and attach them to the aircraft structure to provide a mounting surface that will withstand the inertia forces stipulated in chapters 1 amp 3 of AC 43 13 2A 4 An IA or other representative of the FAA must approve documentation of structural integrity of the fabricated instal lation 5 When installing the strobe light power supply in an inverted position drill a 3 16 diameter hole in the lowest corner of the cover to provide for moisture drainage Care must be taken not to let the drill protrude into the power supply for it will inflict damage to the electronic components 6 Specifically call out the location of the strobe light power supply on FAA form 337 Important Note Your new strobe power supply has an additional circuit built in to prevent self ionization steady glowing of the strobe tubes In some cases when replacing older power supplies the bare shield wire in the existing harness is pinned together at each end with the black wire The following modification must be made to ensure proper operation 1 At the strobe tube end of the cable cut the shield wire and tape it off DO NOT CUT THE BLACK WIRE 2 At the power supply end of the c
70. t for originally installed anti collision lights when installed in accordance with Whelen Anti Collision Light Systems Installation and Service Manual dated January 2007 or later FAA approved revision See continuation sheet 2 of 6 The STC holder will provide each person it permits to use this certificate to alter the product written evidence of the agreement in a form acceptable to the Administrator revoked or a larnination date a otherwise estalbsfied ty the Administrator of he Federol Aviation Administration Yale of application February 19 1968 O Dato resse Lute ofusseeance May 14 1968 Hate amended February 22 2007 See page 2 for amendment history By direction of the Adninisvaton Signature Robert G Mann Manager Boston Aircraft Certification Office Title Any alteration of this certificate is punishable by a fine of not exceeding 1 000 or imprisonment not exceeding 3 years or both Tia Tn a m VrI H O 1 1 FAA Form 8110 2 10 68 Page 1 of 6 This certificate may be transferred in accordance with FAR 21 47 34 Document 05131A Huited States Of America Department of Transportation Federal Abiation Administration Supplemental Tupe Certificate Continuation Sheet Virb or SAGISEA Date Amended February 22 2007 Linitationa and Conditions Continued 1 These lights comply with the anti collision light standards of the FARs as follows a With the red
71. taly Tel 39 0 11 223 9904 Fax 39 0 11 223 9915 ENGINEERING COMPANY INC ROUTE 145 CHESTER CT 06412 0684 PHONE 860 526 9504 FAX 860 526 2009 www whelen com 2007 Whelen Engineering Company Inc 11051D 022207 REV 1 Document 05131A
72. ts A500A V D 14 A500A V D 28 A500A H D 14 A500A H D 28 A500A V D M 14 A500A V D M 28 A500A H D M 14 A500A H D M 28 BONDING BRAID S 12 00 1 00 LEADS Ez 6 00 1 00 A500A V 14 A500A V 28 A500A H 14 J2 CONNECTOR WIRING J1 CONNECTOR WIRING _H POS 1 RED ANODE POS 1 BLUE o ii POS 2 BLACK CATHODE POS 2 BLUE GROUND POS 3 WHITE TRIGGER Figure 21A gt 19 02 0350375 01 FLASHTUBE AND SOCKET ASSY A506DM 1 1 1 15 68 4270002 34 LENS RFI COATED 1 1 1 14 02 0350375 00 FLASH TUBE AND SOCKET ASSY A506D _ 1 1 1 1 12 02 0350034 00 FLASH TUBE AND SOCKET ASSY A506 2 2 2 2 2 2 2 8 e NA HEXNUT 4 40X 1 4 A F BRASS 1 1 1 7 34 0428070 64 LAMP ESG HALOGEN 28 VOLT A508 28 f 1 1 1 61 34 0412070 63 LAMPERG HALOGEN 14 VOLT A508 14 GASKET A455 1 1 1 1 4 68 4270002 30 CLEARGLASS PLAINDOME A457A 1 1 3 19 0150350 02 RETAINER MASK VERTICAL 1 1 2 19 0150350 01 RETAINER MASK HORIZONTAL 14 40 X 1 2 PHILLIPS PHMS MS51957 17 it Pt Te jJ j pp LITT 01 0770024 07 TAIL POS amp STROBE LT ASSY A500A H D 28 7 01 0770024 06 TAIL POS 8 STROBE LT ASSY A500A H D 14 01 0770024 05 TAIL POS 8 STROBE LT ASSY A500A V D 28 te 01 0770024 04 TAIL POS amp STROBE L
73. uired since July 18 1977 An approved anti collision strobe light system must proj ect light 360 around the air craft s vertical axis One or more strobe lights can be used Approved light pattern in the horizontal plane The anti collision wingtip mounted lights must converge within 1200 feet directly in front and rear of the aircraft on center line If the wingtip strobe light convergence is greater than 1200 ft in back of the aircraft a 3rd light is necessary LOCATIONS ON THE AIRCRAFT FOR ANTI COLLISION STROBE LIGHTS TO COMPLY TO THE LIGHT PATTERN REQUIREMENTS VERTICAL FIN One anti collision strobe light mounted on the vertical fin will meet the minimum require ments on most aircraft A half red and half white lens is re commended WINGTIP Two wingtip strobe lights that protrude beyond the wingtip their light converging in front and back of the aircraft within 1200 ft is an approved anti collision strobe light system ENCLOSED WINGTIP Enclosed wingtip anti collision strobe lights require a third strobe light on the tail or verti cal fin to fill in the required light envelope This is an approved anti collision system FUSELAGE In a fuselage mounted anti collision strobe light system a minimum of two strobe lights are necessary to get the required vertical coverage This is an approved anti colli sion system Document 05131A 3 AIRCRAFT NOT SPECIFICALLY MENTIONED ON THE
74. une 17 2005 Limitations and Conditions Continued 1 The Anti Collision Lights listed under Description of Type Design Change meet the requirements of FAR 23 and the similarly numbered sections of FAR 27 as follows a 23 1397 0 23 1401 c d e effective August 11 1971 b 23 1401 f in effect on August 10 1971 c Part numbers 01 0770019 19 and 01 0770019 22 with power supplies IRE under STC SA615EA meet FAR 23 1401 f effective August 11 1971 d Part numbers 01 0770054 00 through 01 0770054 07 01 0770058 03 and 01 0770058 13 with power supplies producing a minimum of 20 joules per flash meet FAR 23 1401 f effective August 11 1971 2 To complete the approval of these lights as anti collision light systems the installations on individual aircraft must be checked to show compliance with FAR 23 1401 b Field of Coverage unless the Anti Collision Light Systems Installation and Service Manual Document 05131 Rev or later FAA approved revision specifically indicates that a particular installation has been checked for compliance with the aforementioned sub section NOTE The aforementioned installation and Service Manual contains an acceptable method for checking the adequacy of coverage when using two lights wing tips or three lights wing tips and tail lights For some other acceptable methods see Advisory Circular AC 43 13 2 Chapter 4 Paragraph 46b 2 Installations made in accordance with STC SA800EA Amendme
75. uselage mounted anti collision lights should be located on the fuselage center line to reduce reflection on the wings as much as possible They should be mounted near the trailing edge of the wing to reduce cockpit reflection APPROVED METHOD OF DETERMINING ADEQUATE COVERAGE OF WING AND TAIL STROBE LIGHT INSTALLATIONS The most practical system is the approved wingtip anti collision strobe light system These systems consist of two or more lights to complete the anti collision light requirement There is no question as to their complying to the field of coverage when the installation is completed Reference to the following instructions The acceptable distance for the two wingtip anti collision strobe lights to converge in front and back of the aircraft on center line is 1200 feet If both wingtip anti collision strobe lights can be seen at 1200 feet or less directly in front and back of the aircraft it is considered a point of light source therefore a third light is not necessary The wingtip anti collision light must be located in such a way that it will project light 75 degrees above and below the horizontal axis of the aircraft and the summation of the 2 or 3 lights will project light 360 degrees around the vertical axis PILOT AND CREW INTERFERENCE In some installations it will be nec essary to mask the strobe lighthead assembly to reduce pilot annoy ance This interference problem varies from one aircraft to another of the same
76. with Strobe Light Dimensions 2 33 DIA NOTE ALIGN REFLECTORS AS SHOWN OPTIONAL MOUNTING ADAPTER POSITIONS Model HRCFA Parts List 1 75 a 16 19 130074 100 A440 MOUNTING FLANGE OPTIONAL I 15 N A 6 INT TOOTH LW MS35333 71 f 14 N A 6 32x3 8 PPHMS MS51957 28 13 01 0770619 00 POWER SUPPLY ASSEMBLY RL 12 01 0770044 02 A469B FLASH TUBE ASSY 11 38 0250429 00 RFI GASKET i 10 38 0230840 00 GASKET Mounting ia 6 32 X 5 16 SS HEX NUT MS35649 2 5 HOLES N A MS35649 264 8 01 0450685 00 CLAMP RING AN A SN i N A 6 32x1 2 PPHMS MS51957 30 Sy me 6 68 2170504R60 LENS A402ADS u 75 5 68 2170504R30 LENS A402ADW H OO J 4 68 2170504R50 LENS A402ADR D T lad 4 3 68 2170504 60 LENS A402AS E T J x Y i 7 2 68 2170504 30 LENS A402AW sl 1 u il en i 68 2170504 50 LENS A402AR 5 00 ee 4 65 DIA B C I ITEM PART NUMBER DESCRIPTION BLACK GROUND Figure 13A WHITE 14 28V Dimensions 1 I SHOWN ROTATED FOR 8 ILLUSTRATION OF PARTS 5 50 Ga I Es om 2 97

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