Cessna 206H Model, Pod Installation Document
Contents
1. G Model T206H Airplane Exhaust Pipe Extension Installation 1 For Model T206H also install exhaust pipe extension as follows a Using Aerocet Part 10 20021 or Cessna Part 1250999 1 Exhaust Extension as a template drill four 4 Number 29 0 136 inch diameter holes in exhaust pipe NOTE Extension must be flush with the exhaust pipe It may be necessary to grind off approximately 1 5 inches of bead on exhaust pipe or reshape exhaust pipe in order to provide tight fit b Attach extension using MS51861 34C Screws REVISION DATER 3 10 2009 8 AUXILIARY FUEL PUMP VENT SEE FIG 5 FOR MODIFICATION 7 COWL FLAP BAFFLES SEE FIG 4 FOR INSTALLATION 6 PANEL ASSEMBLY 7 SEE FIGURE 3 FOR INSTALLATION S REF SCRIBE MARKS ON POD FOR HOLE LOCATIONS 10 20022 PLACARD 206H AND T206H ONLY MOUNTED EXTERNALLY amp IN UNOBSTRUCTED VIEW FIGURE 1 265 Shannon Lane ISSUI PO Box 2119 ae a EROCET 6 07 1994 INCORPORATED Priest River ID E 206 Cargo Pod Installation Manual 83856 1 10 10010 CARGO POD ASSEMBLY 4 10 20017 1 PLACARD 10 20029 PLACARD U206 amp TU206 T206H MODEL ONLY U20602781 amp ON 10 20030 PLACARD LOCATE ON INSIDE 206H MODEL ONLY OF DOOR I 9 of 14 10 NO A 10014 EVISION CAD FILE POD 10 10022 2 LANDING GEAR CUTOUTS 1 8 10 20017 2 PLACARD U206 amp2. LISTING and Page 11 FIGURE 3 illustration UE PO Box 2119 DATE EROCET EEE E 265 Shannon Lane 6 07 1994 INCORPORATED Priest River ID 83856 E NO REVISION DATE 3 10 2009 EVESKONE F 206 Cargo Pod Installation Manual A 10014 CARGO POD C 206 KIT PARTS LIST QUANTITY PART NUMBER PART NAME 1 10 10010 Pod Shell 32 MS27039 1 13 Screw 32 MS35335 32 Washer 32 NAS1149F0332P Washer 20 NAS1329S3K80 Rivnut 7 NAS1329S3K130 Rivnut 4 NAS1329S3K180 Rivnut 10 NAS1329S06K120 Rivnut 20 R860064 Seal 1 10 20017 1 Placard 10 20017 2 Placard 10 20022 Placard 10 20029 Cargo Pack Placard Cessna T206H 10 20030 Cargo Pack Placard Cessna 206H 1213509 1 Cessna Part Baffle Inbd LH thru U20601604 1213509 2 Cessna Part Baffle Inbd RH thru U20601604 1213509 3 Cessna Part Baffle Outbd LH thru U20601604 12 1 1 1 1 1 1 1 1 1213509 4 Cessna Part Baffle Outbd RH thru U20601604 1 10 20010 L Baffle Outbd LH thru 020601605 amp on 1 10 20010 Baffle Outbd RH thru 020601605 amp on 1 10 20012 L Baffle Inbd LH thru U20601605 amp 1 10 20012 R Baffle Inbd RH thru U20601605 amp on 2 10 20015 Link 1 10 20027 Fairing 1 10 20028 Fairing 1 1200641 13 Cess
3. SCALE 1 2 10 10030 2 FORWARD HINGING DOOR ASSEMBLY PART NUMBER DESCRIPTION 10 10031 DOOR PANEL FWD HINGING 10 10032 LATCH HANDLE 10 10034 LATCH BUSHING 10 10035 PANEL LATCH POSITION PLACARD 10 10037 LATCH POST 10 10039 _EPDM FOAM RUBBER SEAL 1 2 D PROFILE 7 1 assy 10 10040 2 HINGE ASSEMBLY AEROCET 206 CARGO POD 8 PART 35 80004 NUT HEX NYLON 1 2 20 THREAD EREA HRDWR LOCTITE 222 THREAD LOCKER 10 HRDWR MS16562 240 SPRING PIN 11 5 MS20426AD4 5 RIVET COUNTERSUNK LENGTH A R 12 HRDWR MS24694C49 MACHINE SCREW FLAT COUNTERSUNK HEAD 100 13 5 HRDWR NAS1149FN432P WASHER FLAT 2 Figure 6 1 7 Parts Listing for 10 10030 2 Forward Hinging Door Assembly End
4. VED WORK ORDERS FROM MDL SHEET 2 10 20 10 10 10 10 EVISED DOCU 10040 10 20015 10 20017 amp 31005 amp 10014 ADDED 10 20021 10 20022 10 20027 10 20029 10 20030 0012 10016 amp ENT 10014 amp 021 MENT 10 10010 ADDED G DRAWING TO MD 016 10 10030 100 10 10035 10 10 10039 0051 10 10053 4 31005 OC SHEET 2 SIZE B SIZE 10 10005 GS 10 10010 35 10 1 j 15 amp UPDATED SIZ 034 040 10033 TO SH REV 1 PREV APPR REV OVED DATE WAS CORRE A SEE SHEET 2 FOR LISTINGS CUSTOMER COPY TOLERANCES EXCEPT WHERE NOTED TOLERANCING AND DIMENSIONING PER ANSI Y14 5M LINEAR X NA XX NA NA ANGULAR NA DEGREE FRACTIONAL NA FINISH REQUIREMENTS NA RMS REMOVE ALL BURRS AND EDGES 010 015 CONCENTRICITY RUNOUT PERPENDICULARITY PARALLELISM INTERNAL CORNER RADII DIMENSIONS IN INCHES DIMENSIONS APPLY BEFORE PLATING DRAWN BY DATE SCALE DWG NO LOCATION APPROVAL DATE DESCRIPTION NGS 10 20010 amp 10 20012 UPDATED 10 10011 10 10012 10 20010 ADDED 10017 AND L 10 10031 10 10037 10 10054 10 10030 F 3 ee i2 REVISED D 0037 T W CORRECTED TYPO FOR CHECKED 206 CARGO POD MASTER DRAWING LIST Priest River Idaho 10 10005 F STC 5 00965
5. 1 EXTENSION KIT AEROCET P N 10 20025 REQUIRED ONLY ON CESSNA MODEL T206H AIRCRAFT 2 CESSNA KIT MK 206 53 01 2 MAY BE USED AS AN ACCEPTABLE ALTERNATE MS51861 34C SCREW TAPPING 4 REQ D DRILL 136 HOLE SIMILAR AS BILL OF MATERIALS FOR 10 20025 EXHAUST EXTENSION KIT SHOWN THROUGH EXHAUST PIECES ITEM ary TYPE PART NUMBER DESCRIPTION 1 1 PART 10 20021 EXHAUST EXTENSION 2 4 HRDWR MS51861 34C SCREW TAPPING FIGURE 6 EXHAUST EXTENSION INSTALLATION EROCET PO Box 2119 265 Shannon Lane 4 20 2006 INCORPORATED Priest River ID 83856 TITLE Supplemental Airplane Flight Manual SUBTITLE Cessna Model 206H Airplanes Equipped with Aerocet 206 Cargo Pack FAA APPROVED SUPPLEMENTAL AIRPLANE FLIGHT MANUAL FOR CESSNA MODEL 206H AIRPLANES EQUIPPED WITH AEROCET 206 CARGO PACK Registration No Serial No The information contained in this document is FAA approved material which must be applied together with the basic FAA approved airplane placards and markings and or FAA approved Airplane Flight Manual This supplemental manual must be carried in the airplane when it is modified by the installation of the Aerocet 206 Cargo Pack in accordance with Supplemental Type Certificate STC No SAQOO96SE The information contained in this document supersedes the basic airplane markings and placards and or Flight Manual covered in the items contained herein For Limitati
6. Figure 1 4 1 Showing side view of Aerocet Cargo Pod on Cessna 206 Aircraft Figure 1 4 2 Showing front view of Aerocet Cargo Pod on Cessna 206 Aircraft EROCET Incorporated 4 20 06 9 of 28 N FILE NO TITLE Service Manual A 10033 REVISION REVISION DATE 3 22 12 SUBTITLE Aerocet 206 Cargo Pack 2 SECTION 2 Cargo Pack Maintenance Corrosion is minimized due to the composite construction The cargo pack should be kept clean with soap and water External stains may be removed using commercially available marine fiberglass stain remover We have used a product called FSR with good success These surfaces may also be waxed to help in the cleaning process Do not use abrasive cleaners or pads these will scratch the white gel coat surface The gel coat color surface should always be maintained on external surfaces for ultraviolet protection Cargo door provides access for inspection to view internal damage and to comply with the maintenance inspections See Table 1 in Section 4 for scheduled maintenance See also Exceptional Inspections Any penetration to the shell structure delamination of the cloth layers or gelcoat having worn through must be repaired according to hull repair Section 3 Significant damage i e damage caused by ground or animal strikes may warrant consultation with Aerocet Inc Significant damage may be categorized as damage that penetrates beyon
7. 1500 1800 1 14 3700 5500 2200 3300 1 1 8 12 5000 7000 3000 4200 1 1 4 12 9000 11 000 5400 6600 Figure 2 2 1 Recommended Torque Values inch pounds From AC43 13 1B Table 7 1 MINIMUM PREVAILING THREAD SIZE TORQUE THREAD SIZE MINIMUM PREVAILING TORQUE Figure 2 2 2 Minimum Prevailing Torque Values for Re used Self Locking Nuts from AC43 13 1B Table 7 2 Self Locking Nuts Self locking nuts when re used must have at least the minimum prevailing torque listed in figure to the left Nuts that are smaller than those listed in the table shall not be used if they can be run up by hand EROCET PAGE 4 20 06 Incorporated 11 of 28 FILE NO TITLE Service Manual and I C A A 10033 REVISION DATE 3 22 12 suBTITLE Aerocet 206 Cargo Pack REVISION 2 WHEN USING A TORQUE WRENCH ADAPTER WHICH CHANGES THE DISTANCE FROM THE TORQUE WRENCH DRIVE TO THE ADAPTER DRIVE APPLY THE FOLLOWING FORMULAS TO OBTAIN THE CORRECTED TORQUE READING Short Open End Adapter TORQUE ADAPTER WRENCH DRIVE HANDGRIP CENTERLINE CENTERLINE PREDETERMINED WRENCH DRIVE 77 CENTERLINE Set Screw Adapter 5 FORMULA LE Y EXAMPLE WITH E AS PLUS DIMENSION T 135 LB IN Y UNKNOWN Hose Clamp Adapter L 10 0 IN E 1 5 IN Y 117 LB IN LEGEN T ACTUAL DESIRED TORQUE Y APPARENT INDICATED TORQUE L EFFECTIVE LENGTH LEVER E EFFECTIVE LENGTH OF
8. 3 22 12 TITLE SUBTITLE EROCET Incorporated Service Manual and Aerocet 206 Cargo Pack This page intentionally left blank PAGE 4 of 28 FILE NO A 10033 REVISION 2 EROCET Incorporated 4 20 06 TITLE Service Manual REVISION DATE 3 22 12 suBTITLE Aerocet 206 Cargo Pack Table of Contents Description PAGE 5 of 28 FILE NO A 10033 REVISION 2 Section Introduction and General Information Cargo Pack Maintenance Repairing Composite Structure Recommended Airworthiness Service Schedule General Practices and Product Listings for Service 1 2 3 A Airworthiness Limitations Illustrated Parts Catalogue 4 20 06 REVISION DATE 3 22 12 TITLE SUBTITLE EROCET Incorporated Service Manual and Aerocet 206 Cargo Pack This page intentionally left blank PAGE 6 of 28 FILE NO A 10033 REVISION 2 EROCET Incorporated FRGS 4 20 06 7 of 28 N FILE NO TITLE Service Manual A 10033 REVISION REVISION DATE 3 22 12 SUBTITLE Aerocet 206 Cargo Pack 2 SECTION 1 Introduction and General Cargo Pack Information This service and maintenance manual is applicable to Aerocet 206 Cargo Pack and its general application to a variety of Ce
9. REVISION DATE 3 22 12 SUBTITLE Aerocet 206 Cargo Pack 2 3 2 3 4 damage has occurred where there is sandwich construction and involving the core then work each layer separately Fix either the outside or inside skins Then cut to fit like core material to replace the damaged core Bond the core onto the repaired skin using the proper resin and thickener A mixture of Hydrex resin and Aerosil 202 thickener should be applied to the bonding surface of the core using a squeegee Torin Corebond alt OK A film of approximately 015 should be used Pressure needs to be applied for the bond to assure proper adhesion to the skin eliminating air voids This pressure can be applied to small area core bonding by weights ex lead shot bags with a release film to keep from sticking to any excess Larger areas require core bonding using a vacuum bag Consult Aerocet Inc for this procedure Fill any seam voids with a resin glass bubble mixture Apply the final laminates accordingly to finish the repair 3 3 Impregnation of Fabric Resin impregnation can be accomplished by laying cloth cut to a suitable pattern on a flat table and applying resin mixture with a squeegee so as to achieve an even impregnation Similarly it may also be done directly on the part with the cloth being applied with either a squeegee or a brush assuring that voids and starved areas are not produced It is very helpful to apply a thin coat of resin to the are
10. any one place The number of laps shall be kept to a minimum 3 6 Surface Coat Application Gel Coat 3 6 1 All surface coats must be applied to a thickness of 10 to 15 mil Use a mil gauge and check often 3 6 2 surface coats must be catalyzed with 2 MEKP 3 6 3 Thinning of surface coats can be done to manufacturers recommendations 4 20 06 REVISION DATE 3 22 12 TITLE SUBTITLE EROCET Incorporated Service Manual and I C A Aerocet 206 Cargo Pack This page intentionally left blank PAGE 16 of 28 FILE NO A 10033 REVISION 2 EROCET ISSUE PAGE 4 20 06 Incorporated 17 of 28 N FILE NO TITLE Service Manual I C A A 10033 REVISION REVISION DATE 3 22 12 SUBTITLE Aerocet 206 Cargo Pack 2 SECTION 4 Recommended Airworthiness Service Schedule General Practices and Product Listings for Service 4 1 Recommended Service Schedule Table 1 TABLE 1 INSPECTION TIME HOURS MONTHS INTERVALS Whichever occurs first 100 200 25 50 12 24 Inspect for damage surface coat gel coat UV Interior Inspect for evidence of damage Inspect seals latches and hinges for proper function corrosion and damage Spray coat protection according to Note 1 Hardware according to Note 2 if desired Inspect for placement amp legibility See installation manual for
11. 0038 TRIM RING AND DOOR INSET 4 3 PART 10 10051 LATCH RAMP 5 2 PART 10 10053 CARGO RAMP 6 12 MS20426AD4 5 RIVET 100 COUNTERSUNK LENGTH 7 6 HRDWR MS21083C3 NUT SELF LOCKING LOW HEIGHT STAINLESS 8 6 HRDWR MS24694C52 MACHINE SCREW FLAT COUNTERSUNK HEAD 100 9 6 HRDWR NAS1149CO363R WASHER FLAT STAINLESS 10 12 HRDWR NAS1149FN432P WASHER FLAT Figure 6 1 4 Parts Listing for 10 10010 2 Door Configuration EROCET Incorporated 4 20 06 26 of 28 FILE NO TITLE Service Manual and I C A A 10033 REVISION REVISION DATE 3 22 12 SUBTITLE Aerocet 206 Cargo Pack 2 INSTALL WITH LOCTITE 222 Luces Naya alge MFG RECOMMENDATION DETAIL A SCALE 1 4 DETAIL B SCALE 1 2 10 10030 1 BOTTOM HINGING DOOR ASSEMBLY ITEM ary TYPE PART NUMBER DESCRIPTION 1 1 PART 10 10031 DOOR PANEL BOTTOM HINGING 2 10 10082 LATCH HANDLE 3 3 PART 10 10034 LATCH BUSHING 4 8 PART 10 10035 PANEL LATCH POSITION PLACARD 5 3 PART 10 10037 LATCH POST 6 1 HRDWR 10 10039 EPDM FOAM RUBBER SEAL 1 2 D PROFILE 7 1 assy 10 10040 1 HINGE ASSEMBLY AEROCET 206 CARGO POD 8 3 PART 35 80004 NUT HEX NYLON 1 2 20 THREAD 9 1 HRDWR LOCTITE 222 THREAD LOCKER 10 HROWR 516562 240 SPRING PIN 11 12 HRDWR MS20426AD4 5 RIVET COUNTERSUNK LENGTH A R 12 3 HRDWR
12. 3 for exploded views and part lists 10 10010 2 New Door design utilizing Aerocet developed rotational latches and a piano hinge along the bottom edge An available option on all new 206 Pod orders Refer to Figures 6 1 4 and 6 1 5 for exploded views and part lists 10 10010 3 New Door design utilizing Aerocet developed rotational latches and a piano hinge along forward edge An available option on all new 206 Pod orders Refer to Figures 6 1 6 and 6 1 7 for exploded views and part lists 10 10010 3 FORWARD HINGING NEW VERSION Figure 6 1 1 206 Cessna Pod Assembly Versions EROCET Incorporated PROS 4 20 06 23 of 28 FILE NO TITLE Service Manual and A 10033 REVISION REVISION DATE 3 22 12 SUBTITLE Aerocet 206 Cargo Pack 2 DETAIL A A SCALE 1 4 CROSS LINKED POLYETHLENE FOAM ADHESIVE BACKED 1 8 X 1 2 PLACED AROUND ENTIRE PERIMETER NOT SHOWN IN PARTS LISTING 10 10010 1 POD ASSEMBLY BOTTOM HINGING DOOR ORIGINAL CONFIGURATION ITEM QTY TYPE PART NUMBER DESCRIPTION 1 1 PART 10 10010 11 AEROCET 206 CARGO POD SHELL 1 OPTIONS 2 1 ASSY 10 10015 DOOR PANEL ASSEMBLY 3 PART 214 16N CAMLOCK END 4 HRWDR 4002 7W STUD CAMLOC P N 5 PART 4002 N GROMMET 6 6 HRDWR MS20426AD4 4 RIVET 100 COUNTERSUNK HEAD LENGTH A R 7 6 HRDWR MS21044c08 SELF LOCKING
13. 524694 49 MACHINE SCREW FLAT COUNTERSUNK HEAD 100 13 12 HRDWR NAS1149FN432P WASHER FLAT Figure 6 1 5 Parts Listing for 10 10030 1 Bottom Hinging Door Assembly EROCET Incorporated en 4 20 06 27 of 28 FILE NO TITLE Service Manual A 10033 REVISION REVISION DATE 3 22 12 SUBTITLE Aerocet 206 Cargo Pack 2 DETAIL A SCALE 1 4 ri 2 PART NUMBER DESCRIPTION 1 1 10 10010 21 AEROCET 206 CARGO POD SHELL 2 amp 3 OPTIONS 1 10 10030 2 DOOR PANEL ASSEMBLY FORWARD HINGING 3 1 10 10038 TRIM RING AND DOOR INSET 4 3 10 10051 LATCH RAMP 5 2 10 10053 CARGO RAMP 6 5 HRDWR MS20426AD4 9 RIVET COUNTERSUNK LENGTH A R 7 6 HRDWR 521083 3 NUT SELF LOCKING LOW HEIGHT STAINLESS 8 6 524694 52 MACHINE SCREW FLAT COUNTERSUNK HEAD 100 9 6 HRDWR NAS1149CO363R WASHER FLAT STAINLESS 10 5 NAS1149FN432P WASHER FLAT Figure 6 1 6 Parts Listing for 10 10010 3 Door Configuration EROCET 4 20 06 Incorporated PROS 28 of 28 TITLE Service Manual FILE NO A 10033 REVISION REVISION DATE 3 22 12 SUBTITLE Aerocet 206 Cargo Pack INSTALL WITH LOCTITE 222 THREAD LOCKER PER MFG RECOMMENDATIONS e Di DETAIL SCALE 1 4 DETAIL B
14. 6 CHECK NUT 7 10 20015 LINK REQUIRED THRU SERIAL U20601604 REQUIRED FOR SERIAL U20601605 amp ON NOT REQUIRED ON TURBO OR 206H AIRCRAFT 77 2 REQ D 7 8 cLEVIS FIGURE 4 COWL FLAPS INSTALLATION et AEROCET PO Box 2119 1 265 Shannon Lane 6 INCORPORATED Priest River ID 83856 F 206 Cargo Pod Installation Manual A 10014 3 10 2009 EVISION CAD FILE POD 10 10023 VENT TUBE DRAIN 1 REQ D 2 aERoQUIP 806 4 HOSE 2 1 4 LONG AIRCRAFT 3 1 4 STAINLESS CLAMPS AN742 10 INBOARD 1 4 00 5052 0 ALUM TUBE 77 GROMMET INTO EXISTING PN 5 INSERT 535489 7 9 16 HOLE IN POD q AIRCRAFT VIEW LOOKING AFT THIS MODIFICATION FOR AIRCRAFT EQUIPPED WITH AUXILIARY FUEL PUMP IN FUSELAGE REMOVE EXISTING VENT TUBE DRAIN AND APPLICABLE TO SERIALS INSTALL DRAIN MODIFICATION AS SHOWN 020601605 THRU 20601618 020601633 amp ON NOT APPLICABLE TO 206H OR T206H FIGURE 5 AUXILIARY PUMP DRAIN MODIFICATION REVISION DATE 3 10 2009 ISSUI DATE EROCET 265 Shannon Lane 6 07 1994 INCORPORATED Priest River ID 83856 PO Box 2119 E 206 Cargo Pod Installation Manual A 10014 EVISION CAD FILE POD 10 20025 FUSELAGE SKIN FUSELAGE SKIN 10 20021 EXHAUST EXTENSION OR CESSNA P N 1250999 1 1 REQ D NOTE
15. 6 Cargo Pack This page intentionally left blank PAGE 20 of 28 FILE NO A 10033 REVISION 2 EROCET ISSUE PAGE 4 20 06 Incorporated 21 of 28 N FILE NO TITLE Service Manual A 10033 REVISION REVISION DATE 3 22 12 SUBTITLE Aerocet 206 Cargo Pack 2 Section 6 Illustrated Parts Catalogue Section 6 contains part listings for the Aerocet 206 Cargo Pod For installation related part listings refer to Aerocet installation manual A 10014 6 1 LIST OF FIGURES Figure 6 1 1 206 Cessna Pod Door Versions Figure 6 1 2 Parts Listing for 10 10010 1 Door Configuration Figure 6 1 3 Parts Listing for 10 10010 1 Door Panel Assembly Figure 6 1 4 Parts Listing for 10 10010 2 Door Configuration Figure 6 1 5 Parts Listing for 10 10010 2 Door Panel Assembly Figure 6 1 6 Parts Listing for 10 10010 3 Door Configuration Figure 6 1 7 Parts Listing for 10 10010 3 Door Panel Assembly EROCET ISSUE PAGE 4 20 06 Incorporated 22 of 28 FILE NO TITLE Service Manual and I C A A 10033 REVISION REVISION DATE 3 22 12 SUBTITLE Aerocet 206 Cargo Pack 2 Cargo Pod Door Versions 10 10010 1 Original Door design utilizing Camloc latches and three bottom positioned door hinges Available for repair and replacement parts only once 2 and 3 versions are available Refer to Figures 6 1 2 and 6 1
16. EXTENSION Open End Wrench TORQUE WRENCH Adapter WRENCH HANDGRIP 2 JE DRIVE CENTERLINE CENTERLINE ADAPTER PREDETERMINED Flare Nut Wrench Adapter TxL FORMULA EXAMPLE WITH E AS MINUS DIMENSION T 135 LB IN Y UNKNOWN Spanner Wrench Adapter L 10 0 IN E 4 5 IN Y 159 LB IN Figure 2 2 3 Torque Wrench with Various Adapters from AC43 13 1B Figure 7 2 EROCET Incorporated 4 20 06 12 of 28 N FILE NO TITLE Service Manual A 10033 REVISION REVISION DATE 3 22 12 SUBTITLE Aerocet 206 Cargo Pack 2 2 3 Fastener Use and Discretion 23 1 Fastener Lengths Rivets Where replacement or repair of rivets is required use rivets of proper specifications only For instance MS203426AD4 xxx Lengths may be determined by measuring the thickness of the material s to be assembled and adding 1 5 X Diameter of the rivet to be used Over sized rivets may be substituted where holes have been drilled out Bolts and screws shall have a minimum of one thread visible through the nuts upon final torque Washers may be rearranged if necessary to accommodate proper fit up to two washers beneath the nut and one beneath the fastener head Typically Aerocet intends to put one thin washer beneath the fastener head and one thicker washer beneath the nut 23 2 Fastener Reuse Fasteners are to be inspected for condition per Section 6 of this manual S
17. FAA APPROVED MODEL LIST AML NO SA00096SE AEROCET INC for AEROCET 206 CARGO PACK INSTALLATION ISSUE DATE June 28 2006 ITEM AIRCRAF AIRCRAFT ORIGINAL CERTIFICATION FAA APPROVED FAA APPROVED MASTER AML T MODEL TYPE BASIS FOR AIRPLANE FLIGHT DRAWING LIST REVISION MAKE CERTIFICATE ALTERATION MANUAL SUPPLEMENT NUMBER 21274208 Number Revision Drawing Revision 1 Cessna 206 P206 A4CE CAR 3 A 10012 Revision 1 10 10005N 1 Revision B P206A E dated 6 19 06 dated 8 5 05 TP206A E U206 U206A G TU206A G 2 Cessna 206H AACE Part 23 A 10016 Revision I R 10 10005N 1 Revision B dated 6 19 06 dated 8 5 05 3 Cessna T206H A4CE Part 23 A 10017 Revision I R 40 10005N 1 Revision B dated 6 19 06 dated 8 5 05 Or later FAA Approved Revision FAA Approved Acting Manager Seattle Aircraft Certification Office Page 1 of 1 PROPRIETARY INFORMATION CONTAINED HEREIN IS PROPRIETARY AND PROPERTY OF AEROCET INC AND IS NOT TO BE COPIED DUPLICATED OR USED AS THE BASIS OF MANUFACTURE OR SALE OF EQUIPMENT WITHOUT PERMISSION WHERE FURNISHED TO A SUBCON TRACTOR II SHALL BE USED SOLELY IN THE PERFORMANCE OF WORK CONTRACTED BY AEROCET INC THIS DOCUMENT IS PRO PRIETARY AND SHALL NOT BE DISCLOSED TO OTHERS WITHOUT THE ROVAL OF AEROCET INC FILE NO POD 10 10005 DATE DESCRIPTION 8 5 05 1 DRAWI REMO E 11 22 10 ED 0 10 10 REVISED D CHANGE lt THIS WAS A E
18. ION CAD FILE POD 10 10020 MODIFIED PANEL 7 ASSEMBLY SEE FIG 2 1200641 14 FAIRING 1 REQ D OR 2 AEROCET P N 10 20027 MAY BE SUBSTITUTED R860064 BULB SEAL AS REQ D 3 10 20020 SEAL 2 REQ D n MS35206 230 SCREW AN526 632R8 OBS 10 REQ D S 1200641 13 FAIRING L H 1 REQ D OR AEROCET P N 10 20028 MAY BE SUBSTITUTED 6 51329506 120 RIVNUT 12 189 HOLE 10 EACH REQ D IN CARGO PACK 7 10 10010 gt CARGO POD ASSEMBLY 8 NAs1329S3K80 1 4 HOLE 20 EACH REQ D IN FUSELAGE SKIN PANEL INSTALLATION 1550 DATE 6 07 1994 REVISION DATE AEROCET PO Box 2119 265 Shannon Lane INCORPORATED Priest River ID 83 3 10 2009 E 206 Cargo Pod Installation Manual 1 1213509 4 77 10 20010 R OUTBOARD COWL FLAP BAFFLE R H 2 1213509 2 5 SS 10 20012 R of 14 856 E NO A 10014 EVISION CAD FILE POD 10 10021 1213509 1 INBOARD 10 20012 L COWL FLAP BAFFLE R H 4 cowL INBOARD COWL FLAP BAFFLE L H FLAP CONTROL 5 1213509 3 77 10 20010 L OUTBOARD COWL FLAP BAFFLE L H 7 6 cowL FLAP 11fANS25 10R6 SCREW 12 REQ Y TITUT 10 521042 3 OR MS21042L3 NUT MS20426AD6 4 RIVETS OR AN363 1032 OBS DRILL NEW HOLES AND USE 12 REQ D MS20470AD4 4 RIVETS AN316 4R 9 CHECK NUT 2 REQ D
19. ITLE Aerocet 206 Cargo Pack 2 LOG OF REVISIONS PAGE REV PAGES DESCRIPTION DATE APPROVED AFFECT o PALL Initial Release 4 2006 Changed Continued Airworthiness to 7 01 10 Recommended Airworthiness Table of Contents Section 4 Added Section 5 Airworthiness Limitations and Section 6 Illustrated Parts Catalogue to Table of Contents Added sub sections 1 1 Availability 1 2 Component Maintenance Manuals 1 3 Installation Manual 1 4 Dimensions Locations and Nomenclature Figures 1 4 1 and 1 4 2 to document Added Sections 2 1 Fastener Torque 2 2 Fastener Torque Values and 2 3 Fastener Use and Discretion to document Added Warnings 3x beginning section 3 4 Resin Mixing Added 2 paragraph Gel times should be assessed Section 3 4 Resin Mixing Added Obsolete use Hydrex 100 33350 not shown at Typical Gel Times Hydrex 33 253 table heading Deleted Warning which was duplicate of 1 of 3 Warnings added previously Changed Section 4 heading Recommended Airworthiness was Continued Airworthiness Added Section 5 Airworthiness Limitations to document Added Section 6 Illustrated Parts Catalogue to document 3 22 12 Rev 2 certification statement New Figure showing washers on rivets for Fig 6 1 3 6 1 4 6 1 5 6 1 6 4 20 06 REVISION DATE
20. Impact Damaged Soft Spots 1 2 Dia or less 3 2 1 1 If necessary sand surfaces to remove gloss 3 2 1 2 Use brush squeegee or hypodermic to work resin into defective area Use same resin as the original laminate 3 2 2 Small Bruises Punctures Less than 1 4 diameter or Surface Voids 3 2 2 1 Sand surface surrounding defect to remove gloss 3 2 2 2 Use same fabric as the original part 3 2 2 3 Cut patches to fit correction area extending a minimum of 1 2 past the damaged area All patch corners must be rounded 3 2 2 4 Apply light brush coat of resin similar to original 3 2 2 5 Place one or more plies on detail covering correction area using impregnation of fabric as described in section 3 3 3 2 3 Cuts Fractures or Punctures 1 4 diameter or Larger 3 2 3 1 Cut back material as required to ascertain extent of damage Trim plies outward to a smooth oval 1 2 per ply generally 3 2 3 2 If the area is large enough supply backing to hold the shape of the original contour Put a parting agent on this backing to assure its release 3 2 3 3 Replace the fabric on a ply for ply basis overlapping 1 2 minimum on each succeeding ply using impregnation of fabric as described in section 3 3 Any smooth areas need to be sanded with 80 grit sandpaper to assure proper bonding EROCET ISSUE PAGE 4 20 06 Incorporated 14 of 28 N FILE NO TITLE Service Manual I C A A 10033 REVISION
21. REGULAR HEIGHT STAINLESS 8 6 HRDWR MS24694C6 MACHINE SCREW FLAT COUNTERSUNK HEAD 100 9 6 HRDWR NAS1149CO332R WASHER FLAT STAINLESS 10 SNAP RING P N Figure 6 1 2 Parts Listing for 10 10010 1 Door Configuration EROCET Incorporated FRGS FILE NO TITLE Service Manual and I C A A 10033 4 20 06 24 of 28 REVISION REVISION DATE 3 22 12 SUBTITLE Aerocet 206 Cargo Pack 2 DETAIL A SCALE 1 4 10 10015 ORIGINAL DOOR ASSEMBLY ATEM QTY TYPE PART NUMBER DESCRIPTION 1 1 PART 10 10016 _ DOOR PANEL 2 9 MS21044C08 NUT SELF LOCKING REGULAR HEIGHT STAINLESS 3 9 524694 6 MACHINE SCREW FLAT COUNTERSUNK HEAD 100 4 9 HRDWR NAS1149CO332R WASHER FLAT STAINLESS 5 3 HRDWR SD 202511 1 DOOR HINGE Figure 6 1 3 Parts Listing for 10 10015 Door Assembly 4 20 06 TITLE REVISION DATE 3 22 12 SUBTITLE EROCET PAGE Incorporated 25 of 28 FILE NO Service Manual A 10033 REVISION Aerocet 206 Cargo Pack 2 DETAIL A SCALE 1 4 10 10010 2 POD ASSEMBLY BOTTOM HINGING DOOR CONFIGURATION LTEM QTY TYPE PART NUMBER DESCRIPTION 1 1 PART 10 10010 21 AEROCET 206 CARGO POD SHELL 2 amp 3 OPTIONS 2 1 ASSY 10 10030 1 DOOR PANEL ASSEMBLY 3 1 PART 10 1
22. ROVAL OF AEROCET INC PRIEST RIVER IDAHO 208 448 0400 A 10 10005 REVISIONS F TEDI POD 1 0 10005 LOCATION B REY ZEEVUTBATE USED ON SHT UE PO Box 2119 DATE EROCET 265 Shannon Lane 1 of 14 Lr 6 07 1994 INCORPORATED Priest River ID 83856 E NO REVISION DA i E E 206 Cargo Pod Installation Manual A 10014 3 10 2009 EVISION INSTALLATION MANUAL FOR AEROCET CARGO PACK ON CESSNA 206 SERIES AIRPLANES This Installation Manual is a necessary part of an FAA Approved data package for STC SA00096SE providing requirements for the acceptable installation of the Aerocet 206 Cargo Pack UE PO Box 2119 E DATE EROCET 265 Shannon Lane 2 of 14 Lr 6 07 1994 INCORPORATED Priest River ID 83856 E NO REVISION DATE 3 10 2009 EVISION E 206 Cargo Pod Installation Manual A 10014 LOG OF REVISIONS PAGE PAGES FAA REV AFFECTED DESCRIPTION APPROVED DATE I R ALL Initial Release 1 ALL Added Cover Page 4 20 2006 Style change to Title Block updated Company address Added Section G Added Figure 6 Updated Parts Listing Updated Figures 1 5 with current hardware and specific model call outs with regard to Models 206H and T206H Changed Rivnut part number 3 10 2009 NAS1329S3K130 was NAS1329S3K140 page 3 PART
23. TU206 U20602781 amp ON LOCATE ON INSIDE OF DOOR CARGO PACK INSTALLATION ISSUI DATE 6 07 1994 REVISION DANEK 3 10 2009 AEROCET PO Box 2119 265 Shannon Lane of 14 INCORPORATED Priest River ID 83856 NO F 206 Cargo Pod Installation Manual A 10014 CUT ALONG THIS LING EXISTING PANELS NOTES 1 2 3 4 5 CUT ORIGINAL NOSE GEAR PANELS 8 7 16 FROM FORWARD END MAKE DOUBLER OUT OF 032 2024 T3 ALCLAD ALUMINUM MATERIAL RIVET DOUBLER ON THE UNPAINTED SIDE OF REAR SECTION OF PANEL WITH MS20470B3 RIVETS AN470 3 OBS RIVET TWO MS21069L3 NUTPLATES EVENLY SPACED WITH MS35207 261 SCREWS AN526 1032R6 OBS THE LEFT REAR PANEL IS MODIFIED THE SAME AS DESCRIBED HERE EXCEPT THE DIMENSION OF THE DOUBLER IS 3 3 4 X 2 FIGURE 2 PANEL MODIFICATION EVISION CAD FILE POD 10 10024 PO Box 2119 PAGE J Sem ERCCET 265 Shannon Lane 11 of 14 DATE 6 07 1994 INCORPORATED Priest River ID 83856 FILE NO REVISION 10014 Ge DAMER 3 10 2009 rt 11 NAS132983K 180 RIVNUT 77 1 4 HOLE 4 REQ D AS SHOWN AAT 10 NAS132993K130 RIVNUT 1 1 4 HOLE NC 7 REQ D AS SHOWN 9 10 193 HOLE 7 MS27039 1 13 SCREW MS35335 32 WASHER NAS1149F0332P WASHER AN960 10L 085 31 EACH REQUIRED FIGURE 3 CARGO PACK AND 206 Cargo Pod Installation Manual 2 EVIS
24. a to be laminated Then lay the cloth down rolling the cloth into the resin Any air in the laminate should be squeegeed or brushed out See section 8 4 regarding resin mixing 3 4 Resin Mixing WARNING Observe all safety regulations and recommendations of the manufacturer according to the Material Safety Data Sheet MSDS and or other instructions for the safe use and handling of all resin related products WARNING Cobalt should never be mixed directly with MEKP catalyst A violent reaction will occur which may result in fire or explosion Cobalt should be stored separately from the catalyst WARNING Be careful with the MEKP catalyst Contact with eyes must be prevented Flush eyes immediately contact a physician immediately Never mix MEKP without eye protection Read recommendations on catalyst supply bottle Gel time or pot life is the time it takes the resin to set up in the container after proper and thorough mixing with accelerators and catalysts Gel times can be adjusted significantly by varying the amounts of these materials Gel times also will vary significantly with the batch size if left in a bucket or with a very thick laminate EROCET ISSUE PAGE 4 20 06 Incorporated 15 of 28 N FILE NO TITLE Service Manual A 10033 REVISION REVISION DATE 3 22 12 SUBTITLE Aerocet 206 Cargo Pack 2 Gel times should be assessed with each new batch or type of resi
25. d the outside laminates to the core and or the inside laminates that is greater than 4 in diameter or that compromises attachment fasteners Latches and seals are to be maintained as needed for proper function If applicable Exhaust Extensions which are required only on Cessna T206H airplane applications should be inspected for stress cracking corrosion damage and condition 2 1 Fastener Torque 2 1 4 Torque Value Conversion To convert in lbs to ft lbs Value ft Ibs x 12 Value in lbs To convert ft Ibs to in Ibs Value in lbs x 0 0833 Value ft Ibs 2 1 2 Tooling Requirements Calibrated torque wrench Adapters that affect the length of the torque wrench will affect the required torque indication and must be calculated according to Figure 2 2 3 2 4 5 Hardware Cleanliness All hardware is to be free of dirt grit and grease All dirty hardware shall be thoroughly cleaned and lubricated with a dry film lubricant such as LPS 1 or Teflon products per manufacturer instructions It is recommended that all stainless hardware be thoroughly lubricated with anti seize lubricant of good quality to prevent galling upon assembly 2 1 4 Torque Procedure Assure that hardware is clean and properly prepared for installation Assemble nuts to bolts measuring the tension required to turn the nut and add this to the required final torque Where possible apply torque to the nut and not to the fastener head Apply a smooth even p
26. esent Owner Present Address Present Phone Number Present Email Address 1 2 Component Maintenance Manuals Certain accessories that are more complex that require additional inspection and maintenance procedures may be described in Component Maintenance Manuals CMM or Maintenance Manuals MM These documents would be provided as part of the documentation provided with your product At the time of this writing no such components are used with Aerocet 206 Cargo Pod This subsection is reserved in the case of such future use 1 3 Installation Manual Installation instructions are provided as a part of the documentation package provided with the original purchase or upon request as detailed above Refer to Aerocet Document Number A 10014 for instructions and installation parts lists EROCET Incorporated 4 20 06 TITLE Service Manual and I C A DATE 3 22 12 SUBTITLE Aerocet 206 Cargo Pack 1 4 Dimensions Locations Nomenclature See A 10014 values are reference here BASIC SPECIFICATIONS CHANGE IN WEIGHT AND BALANCE Maximum Weight 300 lbs Weight Increase 35 0 pounds net change Maximum Load 200 Ibs ft Arm 51 0 inches Internal Volume 16 ft2 Resultant Moment 1785 0 pound inches Overall Length 97 5 8 1 V2 Index 1 632 Opening for Baggage 10 1 x 27 1 Width along 30 of mid section 40 5 Mission Aviation Fellowship Used with permission www maf org
27. fairings 5 and 12 and prime with zinc chromate primer UE PO Box 2119 E DATE EROCET 265 Shannon Lane 7 of 14 6 07 1994 INCORPORATED Priest River ID 83856 E NO REVISION DATE 3 10 2009 EVISION E 206 Cargo Pod Installation Manual A 10014 E Refer to Figure 4 Cowl Flap Modification Models 206 P206 U206 and Stationair NOT APPLICABLE TO 206H AND T206H MODELS 1 Disconnect cowl flap controls 4 and install links 7 and checknuts 9 Retain existing checknuts 6 on cowl flap control as shown Cessna supplied links 1213626 1 can be substituted for 7 2 With cowl flap control in closed position adjust cowl flaps by turning links until cowl flap is 1 05 open at aft end Openings to be measured between centerline of cowl flap at projected aft edge to lower firewall Tighten checknuts 6 and 9 3 Position baffles 1 2 3 amp 5 with forward end of flange resting on flange of existing baffles aft end of baffle aligning with aft end of existing baffle and lower corner of angular cutoff aligning with upper aft corner of existing baffle Use Cessna part 1213509 1 2 3 4 for aircraft serial numbers through U20601604 Use Aerocet part 10 20010 R L and Aerocet part 10 20012 R L for aircraft serial numbers U20601605 and on Cessna baffles 1213687 1 2 3 4 may be substituted for the Aerocet baffle parts 10 20010 and 10 20012 4 Using holes in baffle
28. fall between rivets as shown in Figure 1 When pack assembly 7 is positioned correctly drill thirty one 10 193 holes through pack and fuselage using hole locations scribed into the pack as a guide CAUTION Use a drill stop or some other device to assure that the drill does not go beyond the rivnut depth Remove pack assembly and enlarge 10 holes in fuselage to 1 4 and cut slots as shown use a Rivet key punching tool if available Install Rivets 8 10 and 11 in fuselage skin Apply seal 2 to cargo pack 7 holding in place with masking tape If a sealer caulk is necessary assure that it is non corrosive to aluminum Attach pack assembly to fuselage using screws and washers 9 Use an ice pick to put holes in the seal for the fasteners D Refer to Figure 3 Installation of Seals and Fairings 1 3 4 Cement seals 3 to inboard side of fairings 5 and 12 using contact cement Cut out area in seals should be centered in relation to rectangular openings in fairings with split end of seal aft Split aft ends of fairings to match split ends of seals place fairings over landing gear springs and position so bead at top of fairing matches bead edge of cargo pack Using holes in fairings as a guide drill five 26 147 holes in each side of cargo pack Remove fairings and enlarge 26 holes in cargo pack to 12 189 Install Rivnuts 6 in cargo pack and reattach fairings using screws 4 Clean
29. n Manual A 10014 3 1 0 2009 EVISION CHANGE IN WEIGHT AND BALANCE 1 D A WEIGHT INCREASE 35 0 POUNDS NET CHANGE ARM 51 0 INCHES RESULTANT MOMENT 1785 0 POUND INCHES INDEX 1 632 ESCRIPTION OF INSTALLATION Refer to Figure 1 Installation of this kit consists of 1 Removing two existing nose gear access panel assemblies and modifying them according to Figure 2 2 Modifying auxiliary fuel pump vent if pump installed in fuselage area 3 Positioning cargo pack drilling attaching holes and installing rivnuts in fuselage skin 4 Attaching cargo pack to fuselage with screws 5 Modifying cowl flaps by adding baffles and or extensions some come modified 2 INSTALLATION INSTRUCTIONS A Refer to Figures 1 amp 3 Installation of Nose Gear Access Panel Assemblies 1 Remove existing panel assemblies and modify according to Figure 2 Prime with zinc chromate Using existing screws install modified assemblies according to Figures 1 and 3 NOTE Modified panel assemblies will permit servicing nose gear strut without removing cargo pack Refer to Figure 5 Modification of Auxiliary Fuel Pump Vent Applicable only to serial numbers U20601605 through U20601618 and U20601633 and on when auxiliary fuel pump is located in fuselage NOT APPLICABLE TO 206H AND T206H MODELS 1 Remove existing vent tube drain from aircraft 2 Install tube 1 line 4 and grommet 5 with connecting hose 2 a
30. n system used in the working environment Ambient air and resin temperatures shelf life and catalyst ratios may affect the gel times significantly As previously stated thicker laminates and or resin pots will cure more quickly due to accumulation of heat during gel process Thin laminates such as specified for use in many Aerocet products will often gel in double the amount of time needed to gel a 100g in a 4 in diameter pot Resin catalysis shall not be accomplished in ambient air temperatures of less than 50 F except under extreme circumstances for the purposes of a temporary field repair In no case shall more than 2 catalyst mixture be used and in no case shall less than the recommended 75 catalyst mixture be used TYPICAL GEL TIMES HYDREX 33 253 Obsolete Use Hydrex 100 33350 not shown 100g castings only laminate times typically double 33 7 MEKP Catalyst Resin Qty Note Under no circumstances should more than 2 0 catalyst mixture be used Also do not use less than the recommended minimum amount of catalyst 75 or the resin may never completely cure resulting in a reduction of strength 3 5 Preparation of Fiberglass Materials 3 5 1 Fiberglass shall be trimmed on a clean table to prevent contamination 3 5 2 When laps are necessary lap widths of at least 1 2 shall be maintained for fiberglass pieces in any given ply and no more than one of the component plies shall be lapped at
31. na Part Fairing 1 1200641 14 Cessna Part Fairing 2 10 20020 Seal Not necessary for 206H and T206H Models MK206 53 01 2 is an alternate part number for 10 20025 1200641 13 and 1200641 14 are alternate part numbers for 10 20027 and 10 20028 UE DATE 6 07 1994 REVISION DATE 3 10 2009 Z ERCCET INCORPORATED 265 Shannon Lane Priest River ID F 206 Cargo Pod Installation Manual PO Box 2119 4 of 14 83856 187 A 10014 EVISION CARGO POD C 206 KIT PARTS LIST Cont d QUANTITY PART NUMBER PART NAME 4 MS21069 L3 Nutplate 4 MS35207 261 Screw 12 AN525 1032R6 Screw 10 MS35206 230 Screw 12 MS21042 3 Nut 2 AN316 4R Nut 4 5132953 230 Rivnut 2 14 Stainless AN742 10 Clamp 2 306 4 Aeroquip Low Pressure Hose 7 4 OD 5052 0 Aluminum Tube 1 MS35489 7 Grommet 1 10 20025 Exhaust Extension T206H Kit MK206 53 01 2 Cessna Part Exhaust Extension T206H Kit Not necessary for 206H and T206H Models MK206 53 01 2 is an alternate part number for 10 20025 1200641 13 and 1200641 14 are alternate part numbers for 10 20027 and 10 20028 Ul DATE x 2119 EROCET 265 Shannon Lane 5 of 14 6 0 7 1994 INCORPORATED Priest River ID 83856 E NO REVISION DATE E 206 Cargo Pod Installatio
32. nd clamps 3 C Refer to Figure 3 Installation of Cargo Pack Assembly 1 Determine centerline of pack assembly 7 and mark on outside of pack on the aft end Centerline at forward end is determined by location of nose gear drag brace trough in pack assembly 2 Mark centerline of aircraft on bottom fuselage skin across the station 100 area UE DATE PO Box 2119 265 Shannon Lane 6 of 14 6 07 1994 INCORPORATED Priest River ID 83856 E NO REVISION DATE E 206 Cargo Pod Installation Manual A 10014 3 10 2009 EVISION 3 4 9 Before fitting cargo pack loosen lower wing lift strut fairings and slide them about 12 up lift strut out of the way Place pack assembly 7 under the aircraft and align cutouts 2 Figure 1 with landing gear springs Position drag brace trough under nose gear drag brace While pack assembly is being held in position place a board crosswise under pack 7 and using a jack support the entire pack assembly firmly against fuselage Be careful not to exert enough pressure to deform or spread edges of cargo pack Check centerline of pack assembly 7 with centerline marked on lower fuselage skin Check position of existing holes locations on pod 5 Figure 1 in cargo pack with fuselage skin below the door sills Holes should align with lower rivet line on both sides of aircraft Adjust pack fore and aft so that holes
33. non Lane 4 20 2006 INCORPORATED Priest River ID 83856 TITLE Supplemental Airplane Flight Manual SUBTITLE Cessna Model 206H Airplanes Equipped with Aerocet 206 Cargo Pack NOTE The above fuel sump placard which is required to be located on the cargo pack door refers to the two drains located in the cargo pack In addition as per normal procedures before the first flight of the day and prior to flight following exposure to rain sleet snow or refueling from an unfiltered fuel source Drain and catch a sample from the fuel strainer wing and belly sumps and check for water SECTION 3 EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when the cargo pack is installed SECTION 4 NORMAL PROCEDURES NOTE THESE ITEMS SUPPLEMENT THE CESSNA NORMAL PROCEDURES BE SURE TO FOLLOW THE CESSNA PROCEDURES EXCEPT AS NOTED BELOW a NORMALLY ASPIRATED AIRCRAFT Because of the effect of the cargo pack on climb performance the maximum flap deflection approved for takeoff is 10 whenever the airplane is operated at weights above 3450 pounds When operated at or below this weight up to 20 of flap may be used At takeoff weights above 3450 pounds short field takeoffs with 10 flaps should be conducted using a speed of 68 KIAS at the 50 foot obstacle At weights of 3450 pounds or less the speeds on the Takeoff Distance chart in Section 5 of the Pilots Operating Handbook and 20 flap setting ma
34. nt supplements supercedes the basic manual only in those areas listed herein For limitations procedures and performance information not contained in this manual consult the basic aircraft ICA or Maintenance Manual Aerocet Inc P O Box 2119 265 Shannon Lane Priest River Idaho 83856 Phone 208 448 0400 Fax 208 448 1644 EROCET ISSUE PAGE 4 20 06 Incorporated FILE NO TITLE Service Manual REVISION DATE 3 22 12 SUBTITLE Aerocet 206 Cargo Pack REVISION Rev 0 was approved by FAA without signature sheet STATEMENT OF Rev 1 CERTIFICATION This manual complies with Federal Aviation Association FAA Airworthiness Requirements Part 23 FAA Acceptance LA Date at 5 above certifi o revisions or amendments made after the date of initial certification by other Approved Organizations Revisions or amendments made by other Approved Organizations must be separately certified and recorded on separate record sheets STATEMENT OF Rev 2 CERTIFICATION The changes in revision C are classified as minor and do not affect the FAA approved sections of this manual The changes to the IPC include data that has FAA design data approval EROCET ISSUE PAGE 4 20 06 Incorporated 3 of 28 N FILE NO TITLE Service Manual A 10033 REVISION REVISION DATE 3 22 12 SUBT
35. of 2 REVISIONS EVISION AIRCRAFT APPLICATION DRAWING 10 10010 10011 SERVICE MANUAL AND INSTRUCTIONS FOR CONTINUED ATRWORTHINESS ye Urea A AZAMARA AAAS HAA AAA 10033 3 22 12 PER INSTALLATION DOCUMENT A 10014 10 20017 1 IS NOT APPLICABLE TO H MODEL AIRCRAFT 10 10037 10 10038 10 10053 10 10054 EXOLUDING H MODELS EXCLUDING H MODELS CUSTOMER CO PY 10 20012 10 20015 T206H 206H amp T206H PROPRIETARY DESCRIPTION INFORMATION CONTAINED HEREIN IS TOLERANCES EXCEPT WHERE NOTED TOLERANCING AND DIMENSIONING PER ANSI YI4 5M C06 CARGU PUD PROPRIETARY AND PROPERTY OF LINEAR AEROCET INC AND 15 NOT TO BE E ENA COPIED DUPLICATED OR USED AS _ NA M A lt T E R R A W I N G L S T 1 j THE BASIS OF MANUFACTURE OR SALE ANGULAR N ADECREE OF EQUIPMENT WITHOUT PERMISSION WHERE FURNISHED TO A 5 TRACTOR IT SHALL BE USED SOLELY IN THE PERFORMANCE OF FRACTIONAL FINISH REQUIREMENTS RMS REMOVE ALL BURRS AND EDGES 010 015 CONCENTRICITY N A WORK CONTRACTED BY AEROCET 2 i tin INC THIS DOCUMENT IS PRO PERPENDICULARITY PRIETARY AND SHALL NOT BE PARALLELISM N A DISCLOSED TO OTHERS WITHOUT THE INTERNAL CORNER RADII DIMENSIONS IN INCHES DIMENSIONS APPLY BEFORE PLATING APP
36. ons Procedures and Performance information not contained in this supplement consult the basic airplane markings and placards and or Flight Manual FAA Approved pu fok Manager Seattle Aircraft Certification Office Date 11 Junge 2004 AEROCET PO Box 2119 265 Shannon Lane INCORPORATED Priest River ID 83856 TITLE Supplemental Airplane Flight Manual SUBTITLE Cessna Model 206H Airplanes Equipped with Aerocet 206 Cargo Pack LOG OF REVISIONS PAGE PAGES DESCRIPTION FAA AFFECTED us APPROVED PO Box 2119 EROCET 265 Lane 4 20 2006 INCORPORATED Priest River ID 83856 TITLE Supplemental Airplane Flight Manual SUBTITLE Cessna Model 206H Airplanes Equipped with Aerocet 206 Cargo Pack SECTION 1 GENERAL 206 CARGO PACK The cargo pack provides additional cargo and baggage space The basic shell of the cargo pack including the loading door is fabricated from a fiberglass composite sandwich construction A loading door is located on the left side of the pack and is hinged at the bottom It is secured in the closed position by three quick release fasteners The volume of the cargo pack is 16 cubic feet Dimensions of the pack and its loading door opening are contained in Section 6 of the basic Pil
37. ots Operating Handbook The pack is attached to the bottom of the fuselage with screws and after the initial installation can be readily removed or installed Complete instructions for installation of the cargo pack and required modifications to the nose gear access panels fuel pump vent line and cowl flaps are contained in the Aerocet 206 Cargo Pod Installation Manual Doc A 10014 This supplemental manual applicable to those Cessna Model 206H airplanes equipped with the Aerocet 206 Cargo Pack provides information and limitations not included in the basic FAA approved markings and placards and or Airplane Flight Manual The aircraft is to be operated under the NORMAL CATEGORY only SECTION 2 LIMITATIONS The ADF bearing accuracy may be adversely affected by the type and or arrangement of the cargo pack contents The following information must be presented in the form of a placard located on the inside of the cargo pack door The fuel sump draining information placard is to be located on the outside of the cargo pack door REFER TO WEIGHT amp BALANCE DATA FOR BAGGAGE CARGO LOADING NEVER EXCEED 300 LBS CARGO WEIGHT 10 20030 THE ADF BEARING ACCURACY MAY BE ADVERSELY AFFECTED BY THE TYPE AND OR ARRANGEMENT OF THE CARGO PACK CONTENTS 10 20017 2 FUEL SUMP DRAINS TWO AT STA 23 40 DRAIN BEFORE FIRST FLIGHT OF EACH DAY OR AFTER REFUELING 10 20022 FAA Approved PO Box 2119 EROCET 265 Shan
38. proper locations Inspect for stress cracking and corrosion applicable to Cessna T206H only Cargo Door Hardware Placards Exhaust Extensions Note 1 Spray coat of a migrating corrosion material ACF 50 Boeshield T9 or Corrosion X Note 2 Coat hardware with PUR AL KETONE or LPS 3 4 2 Exceptional Inspections In a variety of circumstances it is necessary to perform prompt inspections for damage Details relating to these investigations are addressed in Sections 2 amp 3 of this manual and Table 1 above It is the responsibility of the pilot to determine the severity of damage and the flightworthiness of the aircraft in the field Inspections and repairs are to be performed as necessary and per practices outlined throughout this manual A list of possible scenarios includes but is not limited to the following 4 2 1 Harsh landings especially when heavy cargo is loaded or has shifted in a significant manner 4 2 2 Impact with an object during taxi take off or landing 4 2 3 Suspected damage incurred during tie down 4 2 4 Visible damage found during normal preflight inspection ISSUE DATE 4 20 06 TITLE REVISION DATE 3 22 12 SUBTITLE 4 3 General Practices EROCET Incorporated Service Manual and Aerocet 206 Cargo Pack PAGE 18 of 28 FILE NO A 10033 REVISION 2 4 3 1 Metal Parts check for co
39. ressure stopping and re torquing if chattering or premature loading occurs This may warrant disassembly and subsequent inspection for burrs or galling Replace any damaged hardware Cross recessed Machine pan head style screws should be torqued only to hand tight the fiberglass should exhibit only mild deformation A portable hand drill could be used provided that the clutch is set properly All other fasteners shall be torqued as shown in this section unless otherwise noted EROCET Incorporated 4 20 06 10 of 28 FILE NO TITLE Service Manual and I C A A 10033 REVISION REVISION DATE 3 22 12 SUBTITLE Aerocet 206 Cargo Pack 2 2 2 Fastener Torque Values Except where otherwise noted CAUTION THE FOLLOWING TORQUE VALUES ARE DERIVED FROM OIL FREE CADMIUM PLATED THREADS TORQUE LIMITS RECOMMENDED FOR INSTAL MAXIMUM ALLOWABLE TIGHTENING LATION BOLTS LOADED PRIMARILY IN SHEAR TORQUE LIMITS Thread Size Tension type nuts Shear type nuts MS20364 Nuts MS20365 and Nuts MS20364 and MS20365 and AN310 and AN320 24 000 psi AN310 90 000 psi in AN320 54 000 psi in 40 000 psi in bolts bolts bolts FINE THREAD SERIES 8 36 12 15 7 9 20 12 10 32 20 25 12 15 1 4 28 50 70 30 40 5 16 24 100 140 60 85 3 8 24 160 190 95 110 7 16 20 450 500 270 300 1 2 20 480 690 290 410 9 16 18 800 1000 480 600 5 8 18 1100 1300 600 780 3 4 16 2300 2500 1300 1500 7 8 14 2500 3000
40. rrosion stress cracks or metal distortion elongation of holes rivet damage 4 3 2 Critical Bolts check for corrosion rust wear torque 4 3 3 Composite Parts check for stress cracks gel coat presence UV protection punctures 4 4 Product Listings our recommendations 4 41 Rust corrosion Protection ACF 50 Corrosion X or Boeing Co Boeshield T9 4 4 2 Bolt Protection PUR AL KETONE Distributed by Lake amp Air LPS Industries LPS 3 Zip Chemical Co Zip D 5029NS 4 4 3 Composite Materials for Hull Repair Contact Aerocet Inc for resin cloth gel coat resin thickeners EROCET ISSUE PAGE 4 20 06 Incorporated 19 of 28 N FILE NO TITLE Service Manual A 10033 REVISION REVISION DATE 3 22 12 SUBTITLE Aerocet 206 Cargo Pack 2 Section 5 Airworthiness Limitations 5 1 GENERAL The Airworthiness Limitations section is FAA approved and specifies inspections and other maintenance required under SS43 16 and 91 403 of the Federal Aviation Regulations unless an alternative program has been FAA approved 5 2 DESCRIPTION 1 TIME LIMITED ITEMS None 2 REQUIRED INSPECTIONS INTERVAL None 3 SCHEDULED MAINTENANCE None for Aerocet recommended Inspection or Replacement refer to Section 4 4 20 06 REVISION DATE 3 22 12 TITLE SUBTITLE EROCET Incorporated Service Manual and Aerocet 20
41. s as a guide drill twelve 10 193 holes in existing baffles Deburr holes and secure new baffles to existing baffles with screws 11 and 10 Options to substitute with rivets as shown in 11 5 Adjust clearance of cowl flap baffles Clearance between baffles and edge of cutout in engine cowl should be 1 8 125 Adjust by hand bending baffles Check for clearance with engine drain tubes 6 Check cowl flap travel Cowl flaps should be 1 05 open when control is in closed position and approximately 6 00 open when control is in open position F Refer to Figure 3 Cowl Flap Modification Model TP206 amp TU206 NOT APPLICABLE TO 206H AND T206H MODELS NOTE Baffles 1 2 3 amp 5 are not required on turbocharged aircraft 1 Disconnect cowl flap controls 4 and install links 7 and checknuts Retain existing checknuts 6 on cowl flap control as shown 2 With cowl flap control in closed position adjust cowl flaps by turning links until cowl flap is 2 50 open at aft end Tighten checknuts 6 and 9 3 Check cowl flap travel Cowl flaps should be 2 50 open when control is in closed position and approximately 8 00 open when control is in open position UE PO Box 2119 DATE EROCET 265 Shannon Lane 8 of 14 6 07 1994 INCORPORATED Priest River ID 83856 E NO REVISION DATE 206 Cargo Pod Installation Manual A 10014 3 10 2009 EVISION
42. ssna Model 206 airplanes The Aerocet 206 Cargo Pack is all composite construction and is mounted to the belly of the aircraft according to the approved installation document Reference the STC document for specific listing At the time of this writing Document A 10014 is applicable to all aircraft models 1 1 Availability One complete hard paper copy of this manual shall be provided with each new 206 Cargo pack Additional copies and minor revisions shall be available via email U S P S mail UPS or FedEx by request Fees and delivery charges may apply Notification of any changes that require service for airworthiness shall be distributed to all applicable Aerocet owners on record with Aerocet Inc In such a case copies of the applicable revised portions of this manual shall be provided Aerocet Inc maintains record of purchasers and or owners collected at the time of purchase in order to comply with the above as well as to maintain a high standard of service If you have moved since your original purchase have purchased a used product or otherwise have reason to believe that the contact information on file is incorrect please provide the following information to Aerocet Inc Aerocet contact information is on the front of this document Cargo Pod Information Cargo Pod S N Aircraft Information Aircraft Make Model Aircraft Registration Aircraft S N Owner Information as applicable Previous Owner Previous Address Pr
43. uch fasteners that are acceptable may be cleaned re lubricated and re installed as determined Self locking nuts shall meet the minimum prevailing torque as listed in Figure 2 2 2 or shall be replaced EROCET ISSUE PAGE 4 20 06 Incorporated 13 of 28 N FILE NO TITLE Service Manual A 10033 REVISION REVISION DATE 3 22 12 SUBTITLE Aerocet 206 Cargo Pack 2 SECTION 3 Repairing Composite Structure 3 1 General Description Composite structure repair done correctly will obtain the strength required to return the cargo pack to normal service and show little or no cosmetic evidence of damage having taken place The materials used for original construction and repair are conventional to the industry Contact Aerocet Inc prior to beginning a repair to obtain correct materials resin resins have shelf lives catalyst cloth gel coat resin thickeners In the field epoxy patch kits may be used in an emergency if the damage is relatively small but the repair must be replaced with correct materials for equal strength status Damage larger than 4 in size requires consulting Aerocet Inc for proper laminate orientation and counts in the damaged area 3 2 Repair Types and Procedures All repaired areas on the exterior must be surface coated gel coated with a minimum of 10 mil thickness to assure UV protection 3 2 1 Resin Starved Areas Exposed Fibers or Small
44. y be used All other speeds remain unchanged from those listed in Section 4 SECTION 5 PERFORMANCE a NORMALLY ASPIRATED AIRCRAFT To obtain takeoff performance of the airplane with a cargo pack installed and using 10 flaps increase both ground roll and total distance over the 50 foot obstacle by 1096 over that found in Section 5 of the Pilots Operating Handbook This procedure is required only when operating at weights above 3450 pounds When operating at or below this weight use 20 flaps and takeoff data in section 5 of the Pilots Operating Handbook The climb performance of the airplane equipped with a cargo pack is approximately 40 ft min less than that shown in the Rate of Climb chart for the standard airplane To obtain speed performance for the airplane equipped with a cargo pack the cruise speeds are approximately 5 KTAS lower than shown in the cruise charts in Section 5 of the Pilots Operating Handbook FAA Approved EROCET Incorporated PROS ISSUE DATE 4 20 06 1 of 28 FILE NO TITLE Service Manual and I C A 10033 REVISION REVISION DATE 3 22 12 SUBTITLE Aerocet 206 Cargo Pack 2 SERVICE MANUAL AND INSTRUCTIONS FOR CONTINUED AIRWORTHINESS FOR AEROCET 206 CARGO PACK This ICA must be followed when the Cargo Pack is installed in accordance with Supplemental Type Certificate STC No SAO096SE _ dated June 7 1994 4 information contained this docume
Download Pdf Manuals
Related Search