Supplemental Type Certificate

2t0R, T2l0F, T2t0G, T2l0H, T2 I 0J, T2 lOK, T2t0L, T2 I 0M, T2l0N. T2l0R. P2t0N. P2l0R Cessna Aircraft Company 206,206H,P206,P206A, P2068, P20 6C, P20 6D, P20 6F,, u206, u206 A, U2068, U206C, u206D, U206F,, U206F, U296G, T2O6H, TP2O6A, TP2O6B, TP2O6C, TP2O6D, TP2O6E, TU2O6A, TU2O6B, TU2O6C, TU2O6D, TU2O6E, TU2O6F, TU2O6G A4CE CAR 3 Cessna Aircraft Comnanr 207.2071'.T207.T2074 AI6CE FAR 23 Cessna Aircraft Company t52. At52 3Al9 CAR 3 Cessna Aircraft Comoanv F152. FAl52 AI3EU CAR 3 Cessna Aircraft Comnanv I72RG 3Al7 CAR 3 Cessna Aircraft Company 310, 3104, 310B, 310c, 310D, 3 10E, 3 10F, 3 10G, 3 10H, 3 10r, 3 r0J, 3 10K, 310L, 310M, 3 10N, 3 10P, 3 10Q, 83 10H, E3l0K 3At0 CAR 3 Cessna Aircraft Company 320. 320-t. 320A. 3208. 320C 3r'.25 CAR 3 Cimrs Desien Corporation SR2O A00009cH FAR 23 CPAC, Incorporated tt2,lt4,7t2TC, ttzB, I 12TCA. I l4A. ll4B. I t4TC AI2SO FAR 23 Cub Crafters cc18-180. CClS-1804 400006sE FAR 23 Diamond Aircraft Industries GmbH DA 40, DA 40 F A47CE JAR 23 The Enstrom Helicopter Corporation F28, F-284, F-28C, F-28C-2, F- 28C, F-28C-2R, F-28F, F-28F- R. 280.280C- 280F. 280FX HICE CAR 6 Extra Flugzeugproduktions EA-300, EA-300/S, EA-300/L, EA-300/200 A67EU FAR 23 Hawker Beechcraft Corporation l9A, B19, M19A,23, A23-19, 423 -24, 823, C23, /.24, 1'24F., 824R. C24R AlCE CAR 3 Fred Garcia 480 21.2 CAR 3 Hawker Beechcraft Corporation 35-33, 35-433, 35-833, 35-C33, E33, F33, G33, H35, J35, K35, M35, N35, P35, 535, V35, v35A 3Al5 CAR 3 Hawker Beechcraft Corooration 60.460.860 AI2CE FAR 23 Hawker Beechcraft Corpo¡ation 76 A29CE FAR 23 Hawker Beechcraft Corporation 77 A3OCE FAR 23 Hawker Beechcraft Corporation 95,895, 95-55, 95-A55, B95A, D954, 895, 95-855, 95-855A, 95-8558. 56TC. A56TC 3Al6 CAR 3 Lavia A¡eentina S.A. P A-25, P A-25 -23 5, P A-25 -260 2^t0 cAR 8.lOlb) Maule Aerospace Technology, Incorporated M-4-180V, M-5-180C, M-5- 200, M-5-2l0TC, M-5-235C, M- 6-180, M-7 -235, M-7-23 54, M- 7 -23 58, Ì|/4-7 -23 5 C, l/f-7 -260, i|'f-7 -260C, M-8-23 5, M-9-23 5, MT -7 -23 5, MT -7 -260, MX-7 - 160, N,D(-7-160C, MX-7-l 80, MX-7- 1 804. I\,D(-7- I 804C. 3/.23 CAR 3 MX-7-l 808, MX-7-l 80C, MX- 7 -23 5, MXT -7- I 60, MXT-7- 180. MXT-7-1804 Mooney Airplane Company, Incorporated MzO,M2OA, M2OB, M2OC, M2OD, M2OE, M2OF, M2OG, M2OJ. M2OM 2A3 CAR 3 Piper Aircraft, Incorporated P A-23, P A-23 - I 60, P A-23 -23 5, PA-23-250.P1.-823-250 lAl0 CAR 3 Piper Aircraft, Incorporated P A-24 - 1 80, P A-24 -250, P A-24- 260.P1.-24-300 lAl5 CAR 3 Piper Aircraft, Incorporated PA-28-140, PA-28-t 50, PA-28- l5 l, PA-28-160, PA-28-16t, PA-28- I 80, PA-28-20 I T, PA- 28-23 5, P A-28 -23 6, PA-2 8R- l 80, PA-28R-200, PA-28RT- 20t, PA-28S-160, PA-28S- I 80 2At3 CAR 3 Piper Aircraft, Incorporated PA-3l, PA-3 r-300, PA-31-32s, PA-31-350 ASEA CAR 3 Piper Aircraft , Incorporated P A-32-260 PA-32R-3 0 I (SP), PA-32-300 PA-32R-301 (HP), PA-32S-300, PA-32R-30 l r, PA-32R-300, PA-32-301, PA- 32RT-300, PA-32-30 I T, PA- 32RT-300T, PA-32-301 FT, PA- 32-30lXT A3SO CAR 3 Piper Aircraft. Incoroorated PA-34-200 ATSO FAR 23 Pioer Aircraft. Incoroorated PA-44-180 AI9SO FAR 23 Piper Aircraft , Incorporated PA-46-3 l0P, PA-46-350P, PA- 46-500TP, PA-46R-350 A25SO FAR 23 Revo, Incorporated LAKELA-4-200, LAKE MODEL 250 lAl3 CAR 3 Robinson Helicopter Company R22,R22 Alpha, R22 Beta, R22 Mariner HIOWE FAR 27 Robinson Helicopter Company R44. R44II HIINM FAR 27 SOCATA Rallye 150T, Rallye 15051 , Rallye 235C, Rallye 235E, MS 8924-150, MS 892E-150, MS 8934, MS 893E, MS 8944, MS 894E 7Al4 CAR IO CAR 3 SOCATA TB9, TBIO, TB2O, T821, TB2OO A5IEU FAR 23 SOCATA GA-7 AITSO FAR 23 Sierra Hotel Aero. Incomorated Navion D. E. F. G. H A-782 CAR 3 Sikorsþ Aircraft Corporation 269 A, 269 A- t, 2698, 269 L, 269C-1 4H12 CAR 6 True Flisht Holdinss LLC AA-1. AA-IA. AA-IB. AA-IC AIIEA FAR 23 True Flisht Holdinss LLC AA-5. AA-54. AA-58. AG-5B A16EA FAR 23 Twin Commander Aircraft LLC 500. 5008. 500-s 6Al CAR 3 Twin Commander Aircraft LLC 700 Al2SW FAR 23 Vulcanair, S.p.A P68, P 68B, P 68C, P 68C-TC, P68 "Observer", P68TC "Observer". P68 "Observer 2" A3IEU FAR 23 Hartzell Engine Technologies LLC Aircraft Engine Alternator Parts List DRAWING NO. 17-0000 Rev. D Created: 11/24/2011 Last Revised: 10/5/2016 Rev. Date By Revisions JH BRJ BRJ CMB Rev* Description ALT-FLX-1 ALT-FLX-2 ALT-FLX-3 ALT-FLX-4 ALT-FLX-5 ALT-FLX-6 ALT-FLX-7 ALT-FLX-8 ALT-FLX-9 17-1001 D INSTALLATION INSTRUCTIONS X X X X X X X X X 17-2000-1 C ALTERNATOR ASSEMBLY X 17-2000-2 C ALTERNATOR ASSEMBLY X X 17-2000-3 C ALTERNATOR ASSEMBLY X X X X 17-2000-4 C ALTERNATOR ASSEMBLY X 17-2000-5 C ALTERNATOR ASSEMBLY X 17-9099 A ALT-FLX CMI MOUNTING KIT X X 17-1089 A ALT-FLX MOUNTING KIT LYC X X 17-1099 A ALT-FLX MOUNTING KIT LYC X X X R1224B L VOLTAGE REGULATOR X X X 10/5/2016 1) UPDATED STRUCTURE TO NEW SCHEME, REPLACED SINGLE ALT- FLX WITH ALT-FLX-1 THRU -9; 2) ADDED MOUNTING KIT SECTION, REMOVED REDUNDANT PART NUMBERS D A B Nov. 12, 2012 10/16/2013 UPDATED 17-1001 REV B * OR LATER APPROVED REVISION 1) FIRST RELEASE TO HET DESIGN DATA. 2) HEADING WAS "PLANE POWER LDT." 3) DRAWING 17-1001 UPDATED TO REV C Part No. C 9/12/2014 INSTALLATION INSTRUCTIONS ALTERNATOR ASSEMBLY MOUNTING KIT REGULATOR 17-1001 Rev. D Page 1 of 5 Drawing No.: 17-1001 ALT-FLX INSTALLATION INSTRUCTIONS READ AND THOROUGHLY UNDERSTAND ALL OF THE INSTRUCTIONS BEFORE BEGINNING INSTALLATION. If a FORD DOFF-series (Cessna 611501, 611502, etc. Grumman American DOFF-10300, etc.) Alternator is being replaced; the ALT-FLX will fit using all existing brackets, belt and hardware. Use ALT-FLX-1. If a Prestolite, Chrysler, Delco or other alternator or a generator is being replaced; new brackets, tension arm and mounting hardware are required, see 17-0000. If desired, the original alternator regulator may be replaced with a R1224 or R1224B regulator. If a generator is being replaced, the generator regulator must be replaced with a R1224 or R1224B regulator (the R1224B mounts using the same holes as most generator regulators). Remove the original regulator and install the R1224 or R1224B in the same location using the R1224 installation and wiring instructions. For Generator Conversions, wire the R1224 per the GENERATOR CONVERSION section of this document. Ensure that the R1224 or R1224B is set for the voltage matching that of the aircraft’s electrical system. MULTI-ENGINE INSTALLATIONS: For proper load-balancing operation, R1224 or R1224B regulators must be installed for each alternator and wired per the R1224 Installation Instructions (12-1001). INSTALLING THE ALT-FLX: NOTE Reference applicable aircraft/engine maintenance manual and FAA AC43-13-1B for guidance on standard methods and practices for electrical, mechanical, and structural work on the aircraft. Follow all WARNINGS and CAUTIONS noted in the aircraft documentation related to the working being accomplished. NOTE Electrical lug and splice sizes are given as a reference. Confirm on aircraft actual wire gauge and associated lug or splice before terminating wires. 1. Gain access to the location where the work is to be accomplished. 2. Label then remove wiring from the existing alternator or generator. Remove the alternator. 3. Cut the ring lug off of the wire removed from the F or F1 terminal (Field) of the original alternator or generator. Connect the wire to EITHER white wire from the supplied 15-5050 Wire Harness/Plug using an M7928/5-4 environmental splice. 4. If a second field wire (F2) was removed, connect it to the other white wire from the supplied 15-5050 Wire Harness/Plug using an M7928/5-4 environmental splice. If no separate field wire (F2) was removed, 17-1001 Rev. D Page 2 of 5 connect the remaining white wire from the supplied 15-5050 Wire Harness/Plug to the elevated post (ground) on the rear of the ALT-FLX using an M7928/1-42 lug and torque 20-35 in-lbs. 5. If an AUX wire was removed from the original alternator (generators will not have one) connect it to AUX terminal of the ALT-FLX with an M7928/1-43 ring lug. Hold the AUX post with a wrench and torque the AUX post nut to 20-35 in-lbs. If an R1224 or R1224B regulator is being installed and there was not an AUX wire, connect a new wire (minimum 20AWG per MIL-W-22759/16) to the ALT-FLX AUX terminal using a ring lug. Route this wire to the location that the regulator is being installed. 6. If a separate ground wire (- or GND) was removed from the original alternator or generator, reconnect it to the elevated post (ground) on the rear of the ALT-FLX. Hold the ground post with a wrench and torque the ground post nut to 20-35 in-lbs. If it is needed to terminate the wire due to lug size, remove existing lug, and terminate with M7928/1-42 lug. 7. Place the ring lug of the “+” wire (large output wire), and any other wires removed from the output (+) terminal of the original alternator or generator on the M8 output bolt of the ALT-FLX. Torque the M8 nut to 45-50 in-lbs. If currently installed ring lug is not sized for a M8 stud, remove existing lug and terminate with an M7928/1-44 lug. Similarly modify all other existing wires attached to the “+” post of the original alternator or generator. 8. Tension the belt and torque the adjusting bolt to 200 in-lbs and safety with stainless steel 0.032” diameter safety wire. Refer to appropriate engine and airframe service manuals for belt tension and other torque values. Safety wire other drilled mounting bolts. 9. Start the aircraft and check the alternator output for proper operation. 10. Recheck and inspect the entire installation. Complete FAA Form 337, make the appropriate log book entry, update the aircraft equipment list and revise the weight and balance if necessary. 17-1001 Rev. D Page 3 of 5 Generator Conversion NOTE: IF AIRCRAFT DOES NOT HAVE A CIRCUIT BREAKER OR CURRENT LIMITING DEVICE IN THE OUTPUT AND REGULATOR INPUT CIRCUIT THEY MUST BE INSTALLED. NOTE Reference applicable aircraft/engine maintenance manual and FAA AC43-13-1B for guidance on standard methods and practices for electrical, mechanical, and structural work on the aircraft. Follow all WARNINGS and CAUTIONS noted in the aircraft documentation related to the working being accomplished. NOTE Electrical lug and splice sizes are given as a reference. Confirm on aircraft actual wire gauge and associated lug or splice before terminating wires. WIRING THE R1224 1) If not already in place, install and label an alternator Field switch and a 5 amp fuse or circuit breaker in the panel. Connect the input of the circuit breaker to the positive bus and the output to the ENABLE terminal of the R1224. 2) Wire the system as follows, following the R1224 Installation Instructions for additional information: a. Install a R1224 or R1224B alternator voltage regulator in the same location from which the generator regulator is removed. Ensure regulator voltage setting matches airframe electrical system. b. Connect the field terminal on the voltage regulator to EITHER white wire from the supplied 15-5050 Wire Harness/Plug using a connector per M7928/1. c. Connect the other white wire from the supplied 15-5050 Wire Harness/Plug to the elevated post (ground) on the rear of the ALT-FLX using a ring lug per M7928/1. d. Hold the ground post with a wrench and torque the ground post nut to 20-35 in-lbs. e. If the aircraft has a “Generator Inoperative” indicator lamp rated at 100mA or less, it may be used. If a lamp is not currently installed or is not compatible, install an appropriate lamp per MS18235 in the panel with placards in view of the pilot. Wire one lead of the lamp to the positive bus and the other to the R1224 LAMP terminal. Use minimum 20AWG wire per MIL-W-22759/16. f. Connect the AUX terminal of the ALT-FLX to the regulator AUX terminal. Use minimum 20AWG wire per MIL-W-22759/16. g. Connect the GND terminal of the regulator to aircraft ground. Use minimum 18AWG wire per MIL-W-22759/16. h. Jumper the regulator SENSE and ENABLE terminals. i. For multi-engine installations, refer to the R1224 Installation Instructions (12-1001) for additional wiring. 17-1001 Rev. D Page 4 of 5 g. Place the ring lug of the “+” wire (large output wire) on the M8 output bolt of the alternator. Torque the M8 nut to 45-50 in-lbs. If currently installed ring lug is not sized for a M8 stud, replace with M8 ring lug per AS7928. h. Start the aircraft and check the alternator output for proper operation. i. Recheck and inspect the entire installation. Complete FAA Form 337, make a log book entry, update aircraft equipment list, and revise the weight and balance as necessary. 17-1001 Rev. D Page 5 of 5 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS Annual / 100 hour inspections: 1. Remove drive belt and turn alternator rotor to check condition of bearings for abnormal noise or roughness. 2. Return to HET if problem is detected. 5 year or 1,000 hour intervals: 1. Repeat: Annual / 100 hour inspection. 2. Remove field brush assembly and inspect brushes for excess wear. Replace brush assembly if brushes extend less than .250” from edge of brush holder case.