Supplemental Type Certificate

Hawker Beechcraft Co. Beech Travelair 95. B95. 8954. D954. E95 3At6 CAR 3 Twin Commander Aircraft Corporation 500, 5008, 500u 6Ar CAR 3 FAA Appro Date: July 17,2014 Manager, Aircraft Certifrcation Offi ce Southwest Region RE\ Date ny Kevtstons F 9/l 8/08 SJK JPDATED DWG. ,I2-1001 REV. F G 11119109 BRJ Updated 14-2001 Rev C, 14-300'l Rev B, 14-4001 Rev B, 14-5001 Rev B, 14-600 Rev C, Removed Airplane Make and Model Eligibility, 12-1010,12-1001, Added R1224 H 9t11t14 BRJ 1)FIRST RELEASE OF DRAWINGS INTO HARTZELL DESIGN DATA 2)UPDATED 14-2001 REV D, 14-3001 REV C, 14-4001 REV C, 14-5001 REV C, 14-6001 REV D AND ADDED 10.1031 3) HEADING WAS "PLANE POWER LTD " J 5129115 CMB 1)ADDED 10-8099-1;2)ADDED MISSING PARTS TO BOMS; 3)CHANGED BOM OF 10-5051; 4) REMOVED LABEL AND LAMP LINES; 5)ADDED 12-102't LtNE Hartzell Engine Technologies l.¿C Belt Driven Aircraft Engine Alternator Conversion Parts List MDL DRAWING I4.OOOO REV. J Created: 3126107 Last Revised:5/29l15 MOUNTING KITS 10-8099 H 5113115 Mountinq Kit 2 1 1 0-8099-1 \E\A 5t2Sh5 Mountino Kit 2 10-1012 F 10t24t14 TENSION ARM 1 1 0-1 009 F 10t3t14 PIVOT HOLE SPACER BUSHING 1 1 0-8003 H 10124114 BRACKET.LYC. 1 1 0-1 002 G 1013114 STARTER STRAP 1 1 0-1 003 E 1013114 U BRACKET 1 14-1011 NE\A 4t14t't5 28V ALTERNATOR INOPERATIVE LAMP I 1 0-1 033 \E\A 2t2t15 TERMINAL, RING I AN5H-5A BOLT I 4N960-516 /VASHER 1 AN7.42A BOLT 1 4N960-716 /VASHER 1 4N363-720 NUT 1 m 1 0-90994 B 2t18t15 lVlountinq Kit 2 I 0-90044 A 9t8t14 ]ONTINENTAL TENSION ARM 1 1 0-90054 A 9t8t14 SPACER 3 1 0-90058 A 918114 SPACER 1 AN7-1OA 3OLT 1 MS35338-47 -OCKWASHER 2 4N960-516 /YASHER 2 AN5H-74 3OLT 1 MS20074-05-1 2 BOLT 1 AN7-434 BOLT 1 M521045-6 NUT 1 4N960-616 WASHER 2 AN6-41A BOLT 1 MS35338-45 LOCKWASHER 1 4N960-8161 WASHER 1 1 0-1 009 F 10t3t14 PIVOT HOLE SPACER BUSHING 1 10-3012 E 10t10t14 SPACER 1 1 0-9006 B 10t24t14 SUPPORT BRACKET 1 1 0-3009 G 10t10t14 PIVOT HOLE REAR SPACER BUSHING 1 I 0-301 0 F 10110114 PIVOT HOLE FRONT SPACER 1 Part No. Rev Date Descri o l\ +N J L o l\ N J L o F- çN J L o È- N J olr N J ALLA '14-2001 D 9t08t14 T AL24-7 0C lnstallation lnstructions 1 14-3001 c 9t10t14 TAL12-70 lnstallation Instructions 1 14-4001 c 9110114 T AL24-7 0 lnstallation lnstructions 1 14-5001 c 9110114 SALl 2-70 lnstallation lnstructions 1 14-6001 D 9110114 SALí 2-70C lnstallation lnstructions 1 User is responsible for verification of current revision before using this document. Document considered "reference only" if not the current revision. 1 0-9003 K 10127114 ]RACKET TCM 1 4N363-624 !UT 1 14-1011 NE\A 4t14t15 28V ALTERNATOR INOPERATIVE LAMP 1 1 0-1 033 NE\A 2t2t15 TERMINAL, RING I 1 0-9007 6/1 0/08 BRACKET ASSEMBLY (AS REQUIRED) 2 1 0-90074 6/'10/08 BRACKET (AIR INDUCTION) 1 1 0-90078 6/l 0/08 BRACKET (ENGINE) 1 1 0-9007c 6/1 0/08 BRACKET 1 AN3-64 BOLT 4 AN3-54 BOLT 3 4N960-'10 WASHER 14 M521045-3 NUT 7 ALTERNATORS 1 0-1 050c E 3t31t't5 Alternator Assy. 12 Volt / 3" DIA 3/8" V-BELT Pullev 1 1 0-1 051 F 1129115 Aternator Assembly, 12Yoll I 112" V-Belt Pulley 2 1 r0-5050c D 2t18t15 Aternator Assy. 24 Volt / 3" DIA 3/8" V-BELT Pullev 2 1 0-5051 c 5126115 Aternator Assembly, 24Yolt I 112" V-Belt Pullev 2 1 0-5006 A 10110114 24V ALTERNATOR ASSEMBLY 1 10-1032 NE\^ 2t2t15 NUT. M5X.8 1 1 0-2005 F 11t3t14 1/2'V-BELT PULLEY 1 '10-1031 \EVl 915114 LABEL c10-221 \E\A 2t2t15 SAFETY WIRE AR PLACARDS 14-1012 A 10t28t14 SINGLE ENGINE PLACARDS 1 14-10't3 A 918114 TWIN ENGINE PLACARDS 1 1 1 AFMS AFMS OO1 1102107 AIRPLANE FLIGHT MANUAL SUPPLEMENT 1 1 AFMS OO2 1t02t07 AfRPLANE FLIGHT MANUAL SUPPLEMENT 1 1 1 FOR INSTATTATIONS WITH TCM BRACKET 628004 (GENERATOR BRACKET MOUNTS BEHTND MOTOR MOUNT AN9ó0-5tó AN5H-ZA INSTALL USING THIS HOLE ì 0-90044 I 0-900ó I 0-5050c I 0-r 009 r 0-90058 MS35338-47 ì 0-9005A @ \ AN7-434 INSTALL USING THIS HOLE FI TERMINAL r 0-9005A MS35338-47 EXISTING TCM BRACKET 628004 (NOT SUPPLTED) óMM OUTPUT TERMINAL AUX TERMINAL FOR INSTATTATIONS WITHOUT (GENERATOR BRACKET MOU NTS TCM BRACKET 628004 ABOVE MOTOR MOUNT AN9ó0-5ìó INSTALL USING THIS HOLE AN5H-ZA r 0-900ó ì 0-9004A 9ó0-51ó MS35338 45 MS20074-05-12 LOCATION OF FAA PMA NAMEPLATE I 0-5050c 1 0-3009 ANó-4IA I0-30t0 AN9ó0-ót ó INSTALL USING THIS HOLE NOTES: 1. TCM# 539547-32.00 V-BELT REQUIRED (PURCHASE SEPERATELY) 2. FOR INSTALLATIONS ON CESSNA 3IOC - 3IOF WITH AIR INDUCIION BOX SUPPORT CESSNA# O85Oó04-ó ORDER PLANE-POWER SUPPORT KIT# ] 0-9007 Wr FAA PMA HARTZELL ENG¡NE EEIUUET D4.YWWSN nEIIilGÐ z¿ AN9ó0-81óL r 0-9003 DESCRIPTION FIRST RELEASE INTO HET DESIGN DAÏA PAGE 3 TO PAGE ì . 2) ADDED HET TITLEBLOCK 3) HARTZELL ENGINE TECHNOLOGIES WAS PLANE POWER, L CALTOUT TO DATA TAG. 5) WAS TAL24-70C. ó)REMOVE AND/OR REPLACED WITH ''HET' "PER DRAWING ON 2900 Selmo H¡9hwoy Monlgomery, AL 3ó100 UNLESS OTHERWISE SPECIFIED GEOMETRIC SYMBOLS PER ANSI YI4.5 DIMENSIONS ARE IN INCHES AND APPLY AFTER HEAT TREAT AND PLATING .X = r.0ì5 .XX=t.0ì0 ANGLESTì' .XXX = 1.005 BREAK ALL EDGES AND MACHINE ALL INSIDE CORNER FILLEIS OI5 MAX t2s/ suRFACE n¡lrsu V Z FTA]NESS SI RA IGHI N ESS O RouNDNEss ø cYuNDRcrrY ô ppor¡te ,L PERPENDTcuLARTTY + PosroN O coNcEMRcrrY = SYMMÊIRY -Z ANGULARIY // PAR^ttELrsM ,/ crRcuLAR RUNoul S P ECIFICATIO N CLASS IFICATION I AL24-7OC I NSTALLATIO N INSTRUCTIONS MATERIAL SEE INDIVIDUAL PARTS THIS DRAWING CONIAINS INFORMATION THAf IS CONIIDENTIAL AND PROPRIEIARY IO HARIZELL ENG¡NE TECHNOLOGIES -IHIS DRAWING IS FURNISHED ON-IHE UNDERSIANDING THAT THE DRAWING AND THE INFORMATION IT CONTAINS WILT NOÌ BE COPIED OR DISCLOSED TO OÌHERS EXCEPT WITH THE WRIITEN CONSENI OT HARIZELL ENGINE TECHNOLOGIES, WILL NOT BE USED TO THE DEIRIMENT OF HARTZELL ENGINE TECHNOLOGIES, AND WILL BE REIURNED UPON REOUEST BY HARIZELT ENGINE IECHNOLOGIES DRAWING NO. 14-2001 CODE ID ó5PYI (XX XX) Parts List: Qtv Part No. Description 2 1 0-5050c Alternator , 24 Volt, with 3.0" Diameter 3/8" V-Belt Pulley. 2 1 0-9099A Mountinq kit for Continental Enqine. 2 R1224 Alternator Controller (Voltaqe Reoulator) and data sheet 12-1001 1 ALP-1002 Placard, LEFT ALT INOP (Part of Drawinq 14-1013) 1 ALP-1003 Placard, RIGHT ALT INOP (Part of Drawinq 14-1013\ 1 ALP-1004 Placard, LEFT ALT FIELD (Part of Drawinq 14-1013\ 1 ALP-1005 Placard, RIGHT ALT FIELD (Part of Drawinq 14-1013) 1 14-2001 lnstallation lnstructions (This document) 2 14-1011 Alternator lnoperative Lamp (28 Volt) 14-2001 Rev. D Page 2of 4 READ AND THOROUGHLY UNDERSTAND ALL OF THE INSTALLATION INSTRUCTIONS BEFORE BEGINNING INSTALLATION OF THIS KIT. NOTE: IF AIRCRAFT DOES NOT HAVE A CIRCUIT BREAKER OR CURRENT LIMITING DEVICE IN EACH GENERATOR'S OUTPUT AND REGULATOR'S INPUT CIRCUIT THEY MUST BE INSTALLED. Part 1, lnstallation of Alternator and Regulator 1. Disconnect aircraft battery. 2. Remove Generators and voltage regulators. 3. lnstall Alternators per drawing on page 1. Tension the belts and torque the AN5H-74 adjusting bolts to 100 - 140 in/lb and safety wire with 0.032" diameter safety wire. Torque the AN7-43A mounting bolts to 450 - 500 in/lb or torque the AN6-41A mounting bolts to 160 - 190 in/lb. 4. operation (See regulator instructions for location of jumpers). 5. lf original output circuit breakers are rated at less than 70-amps and you wish to be able to utilize the increased capacity of the alternators, remove the breakers and replace with suitable breakers up to 70amp maximum size. Ensure wire size from alternator output terminal to output circuit breakers and from Note: lf aircraft has been equipped with an Amp Meter, ensure that it is of adequate size to handle the increased output capability before increasing the output wire and breaker. 14-2001 Rev. D Page 3 of 4 6. Wire the system as follows: a. For regulator wiring instructions view the regulator installation instructions. b. Connect the GRND terminal of each regulator to the common aircraft ground. c. Leave the ground jumper installed on the F2 terminal of the alternator. d. Connect the existing generator output wires to each alternator's 6mm OUTPUT TERMINAL (or install a new wire in accordance with 4C43.13-1B) using a MS25171-25 terminal nipple for insulation (Not Supplied). Torque to 50 in/lb. e. Use the original generator field wire or install a new wire, minimum 18AWG, from each alternator F1 terminal to the FLD terminal of the corresponding regulator. Torque the alternator's F1 terminal nut to 20 in/lb. f. lnstall, in view of the pilot, placard ALP-1004 (LEFT ALT FIELD) adjacent to the field switch for the left alternator and placard ALP-1005 (RIGHT ALT FIELD) adjacent to the switch for the right alternator. g. Ensure that each of the FIELD breakers are connected to the aircraft positive bus. h. If the aircraft has "Generator lnoperative" indicator lamps, they may be used in this step. lf lamps are not currently installed or are not compatible use the supplied lamps Pln 14-1011 Alternator lnoperative Lamp (28 Volt) and install them in pilots clear field of view. i. lnstall, in view of the pilot, placard ALP-1002 (LEFT ALT INOP) adjacent to the lamp for the left alternator and placard ALP-1003 (RIGHT ALT INOP) adjacent to the lamp for the right alternator. Also run a new wire, minimum 18AWG, from the AUX terminal of each alternator to the AUX terminal of the corresponding regulator. 7. Adjust and Test the system: a. Set both FIELD switches to OFF. b. Turn on MASTER switch and start the engines. Ensure that both ALT INOP indicators are illuminated. c. Turn on the LEFT FIELD switch. Check proper charging indication. Check left ALT INOP indicator is off. Check aircraft maintenance manualfor proper bus voltage (typically 28.0V t 0.3V). Adjust the left (Master) regulator to the desired bus voltage at 1200 engine RPM. d. Turn off the LEFT FIELD switch and turn on the RIGHT FIELD switch. Check proper charging indication. Check right ALT INOP indicator is off. At 1200 engine RPM Adjust the right (Slave) regulator to the same bus voltage as left alternator. e. Turn on the LEFT FIELD switch. f. Check proper charging indication. Check bus voltage. g. Recheck and inspect the entire installation. Complete FAA form 337, make log book entry, update aircraft equipment list, and weight and balance. Mountinq Kit Parts List 10.9099A MOUNTING KIT COMPONENTS QTY P/N DESCRIPTION QTY P/N DESCRIPTION QTY P/N DESCRIPTION 1 1 0-9003 MOUNTING BRACKET 3 r0-90054 SPACER 2 MS35338-47 LOCK WASHER 1 10-90044 TENSION ARM 1 1 0-90058 SPACER 1 MS35338-45 LOCK WASHER 1 1 0-9006 SUPPORT BRACKET 1 AN6-414 THRU BOLT 2 4N960-516 WASHER 1 1 0-1 009 SPACER 1 AN7-434 rHRU BOLT 2 4N960-616 WASHER 1 I 0-3009 SPACER 1 AN5H-74 3OLT 1 4N960-81 6L WASHER 1 10-3010 SPACER 1 AN7-1OA 3OLT 1 M521045-6 NUÏ 1 10-3012 SPACER I M520074-05-12 SOLT 14-2001 Rev. D Parl2, Preparation of FAA Form 337 Page 4of 4 1. lnstalled Alternators in accordance with Supplemental Type Certificate No. SA10682SC. Updated Airplane Flight Manual with HET Airplane Flight Manual Supplement 002 (or later revision). Weight changed (compute weight and balance as necessary). Checked size of wire from Alternator output terminals to alternator circuit breakers and from Alternator circuit breakers to bus and size of Alternator circuit breakers with 4C43.13-1B. (Note: use this statement as applicable. lf wire and circuit breaker sizes are satisfactory, so state. lf not satisfactory, state wire and/or circuit breaker size installed to conform with 4C43.13-18.) 2. Modified aircraft equipment list by removal of generators listed and adding Model TAL24-70C Alternator Kit. Weight and Balance Removed two generator installations: Weight Arm (Refer to Aircraft Equipment List) Removed two regulator installations: Weight Arm (Refer to Aircraft Equipment List) I nstalled'l AL24-7 0C alternator consisting of: (2) 1 0-5050C alternators (2) 10-9099A mounting kits: With TCM Bracket 628004 OR With Plane-Power Bracket 10-9003 (2) R1 224 V oltage Regulators (1 ) ALP-1002 Placard (1) ALP-1003 Placard (1) ALP-1004 Placard (1 ) ALP-1005 Placard (2) 14-1011 Lamps kit wgt. 20.01bs. 2.2lbs. 3.2 lbs. 0.6 lbs. Neqliqible Nesliqible Neolioible Neqliqible Neqliqible Part 3, lnstructions for Continued Airworthiness PERIODIC MAINTENANCE: 1 . lt is recommended that the operation of the TAL2 4-70C alternator be checked every 100 hour inspection or every annual inspection which ever comes first. 2. ANNUAL/1OO HOUR INSPECTION: a. Remove drive belt and turn alternator rotor to check condition of bearings for abnormal noise or roughness. b. Each annual/100 hour inspection, the alternator and its associated wiring should be checked for secure electrical connections and physical connection to the airframe. The belt drive tension should be re-set to the aircraft manufacturer's specification. 3. 5 YEAR OR lOOO HOUR INSPECTION a. Repeat the Annual/'100 hour inspection. b. Remove field brush assembly and inspect brushes for excess wear. Replace brush assembly if brushes extend less then 0.250 inches from edge of holder case. AI RWORTHINESS LI MITATIONS There are no mandatory replacement limits. There are no mandatory structural inspection intervals. THE AIRWORTHINESS LIMITATIONS SECTION IS FAA APPROVED AND SPECIFIES MAINTENANCE REQUIRED UNDER SEC. 43.16 AND 91.403 OF THE FEDERAL AVIATION REGULATIONS UNLESS AN ALTERNATIVE PROGRAM HAS BEEN FAA APPROVED t0-t0t2 AN9ó0-5tó AN5H-54 LOCATION OF FAA PMA NAMEPLATE F2 TERMINAL (GROUND) FI TERMINAL I 0-ì 051 AN3ó3-720 AUX TERMINAL óMM OUTPUT TERMINAL AN9ó0-Zró sMM STUD (3) AN7-42A I 0-8003 (CASE MOUNT BRACKET) IO-IOO3 AS REQUIRED (BOSS MOUNT BRACKET) NOTES: l. NOTE: FOR STANDARD /.5" DIAMETER RING GEAR SUPPORT PULLEY usE PTPER V-BELT p/N 452-541 (GATES 9335X1). NOT SUppLtED. Wsr FAA PMA HARTZELL ENGINE l0-1051 EEIIEITÐ C2.YWWSN M¡TIiñGril tZ FIRST RELEASE INTO HET DESIGN DATA 9/10/14 PAGE 3 TO PAGE r. 2) ADDED HET TTTLEBLOCK 3) HARTZELL ENGINE TECHNOLOGIES WAS PLANE POWER, LTD. 4) ADDED ì0-t03t CALLOUTTO DATA TAG.5) MODEL NO. ì0-ì05r WAS TALr2-l0. ó)REMOVED ''PLANE POWER LDT." AND/OR REPLACED wrTH "HEI' WHERE APPLTCABLE.,Tf PtR, DRAWING ON 9/to/14 2900 Selmo Highwoy Monlgomery, At 36108 UNLESS OTHERWISE SPECIFIED GEOMETRIC SYMBOLS PER ANSI Y]4.5 DIMENSIONS ARE IN INCHES AND APPLY AFIER HEAT TREAT AND PLATING .X = t.015 .XX = 1.010 ANGLES 1l ' XXX = 1.005 BREAK ALL EDGES AND MACHINE ALL ¡NSIDE CORNER FILLEIS ,Oì5 MAX. - SIRA|GHINÊSS O RouNDNEss H cYLTNDRcnY ô pnortLt l_ PERPENDcuTARTTY + PosroN O coNcENlRrc[Y .:- SYMMEIRY .2. ANGULARTIY // PARALLET.sM ,/ crRcurAR RUNorrr SP ECIFICATION CLASSI FICATION TAL I 2-70 INSTALLATION INSTRUCTIONS IHIS DRAWING CONTAINS INFORMATION IHAT IS . CONFIDENTIAL AND PROPRIíARY IO HARÌZELL ENGINETECHNOLOGIES THIS DRAWING IS FURNISHED ON THE UNDERSTANDING THAI THE DRAWING AND IHE INFORMAIION fT CONTAINS WILL NOT BE COPIED OR DISCLOSEDÌO OÌHERS EXCEPT WITH THE WRIITEN CONSENT OF HARIZELL ENGINE IECHNOTOGIES, WItL NOÌ BE USED IO THE DETRIMENT OF HAR'IZETL ENGINE IECHNOLOGIES, AND WILL BE REIURNED UPON REQUEST BY HARTZELT ENGINE IECHNOLOGIES MATERIAL SEE INDIVIDUAL PARTS fxx xxl DRAWING NO. r 4-300 r Parts List: Qty Part No. Description 2 10-1051 Alternator, 12 Volt, with 112" V-Belt Pulley. 2 10-8099 Mountinq kit for Lvcominq Enqine. 2 R1224 Alternator Controller (Voltaqe Requlator) and data sheet 12-1001 1 ALP-1002 Placard, LEFT ALT INOP (Part of Drawinq 14-1013) 1 ALP-1003 Placard, RIGHT ALT INOP (Part of Drawinq 14-1013) 1 ALP-1004 Placard, LEFT ALT FIELD (Part of Drawins 14-1013\ 1 ALP-1005 Placard, RIGHT ALT FIELD (Part of Drawinq 14-1013\ 1 14-3001 lnstallation lnstructions (This document) 2 14-1010 Alternator lnoperative Lamo (14 Volt) 14-3001 Rev. C Page 2 of 4 READ AND THOROUGHLY UNDERSTAND ALL OF THE INSTALLATION INSTRUCTIONS BEFORE BEGINNING INSTALLATION OF THIS KIT. NOTE: IF AIRGRAFT DOES NOT HAVE A CIRCUIT BREAKER OR CURRENT LIMITING DEVICE IN EACH GENERATOR'S OUTPUT AND REGULATOR'S INPUT CIRCUIT THEY MUST BE INST Part 1, lnstallation of Alternator and Regulator 1. Disconnect aircraft battery. 2. Remove Generators and voltage regulators. 3. lnstall Alternators per drawing on page 1. Tension the belts and torque the AN5H-54 adjusting bolts to 200 in/lb and safety wire with 0.032' diameter safety wire. Torque the AN7-424 mounting bolts to 425 inllb. 4. operation (See regulator instructions for location of jumpers). 5. lf original output circuit breakers are rated at less than 70-amps and you wish to be able to utilize the increased capacity of the alternators, remove the breakers and replace with suitable breakers up to 70amp maximum size. Ensure wire size from alternator output terminal to output circuit breakers and from Note: lf aircraft has been equipped with an Amp Meter, ensure that it is of adequate size to handle the increased output capability before increasing the output wire and breaker. 14-3001 Rev. C Page 3 of 4 6. Wire the system as follows: f. For regulator wiring instructions view the regulator installation instructions Connect the GRND terminal of each regulator to the common aircraft ground. Leave the ground jumper installed on the F2 terminal of the alternator. Connect the existing generator output wires to each alternator's 6mm OUTPUT TERMINAL (or install a new wire in accordance with AC43.13-1 B) using a MS25171-25 terminal nipple for insulation (Not Supplied). Torque to 50 in/lb. Use the original generator field wire or install a new wire, minimum 18AWG, from each alternator F'l terminal to the FLD terminal of the corresponding regulator. Torque the alternator's F1 terminal nut to 20 in/lb. lnstall, in view of the pilot, placard ALP-1004 (LEFT ALT FIELD) adjacent to the field switch for the left alternator and placard ALP-1005 (RIGHT ALT FIELD) adjacent to the switch for the right alternator. Ensure that each of the FIELD breakers are connected to the aircraft positive bus. lf the aircraft has "Generator lnoperative" indicator lamps, they may be used in this step. lf lamps are not currently installed or are not compatible use the supplied lamps Pln 14-1010 Alternator lnoperative Lamp ('14 Volt) and install them in pilots clear field of view. lnstall, in view of the pilot, placard ALP-1002 (LEFT ALT INOP) adjacent to the lamp for the left alternator and placard ALP-1003 (RIGHT ALT INOP) adjacent to the lamp for the right alternator. Also run a new wire, minimum '18AWG, from the AUX terminal of each alternator to the AUX terminal of the corresponding regulator. 7. Adjust and Test the system: Set both FIELD switches to OFF. Turn on MASTER switch and start the engines. Ensure that both ALT INOP indicators are illuminated. Turn on the LEFT FIELD switch. Check proper charging indication. Check left ALT INOP indicator is off. Check aircraft maintenance manualfor proper bus voltage (typically 14.0V f 0.3V). Adjust the left (Master) regulator to the desired bus voltage at 1200 engine RPM. Turn off the LEFT FIELD switch and turn on the RIGHT FIELD switch. Check proper charging indication. Check right ALT INOP indicator is off. At 1200 engine RPM Adjust the right (Slave) regulator to the same bus voltage as left alternator. Turn on the LEFT FIELD switch. Check proper charging indication. Check bus voltage. Recheck and inspect the entire installation. Complete FAA form 337, make log book entry, update aircraft equipment list, and weight and balance. Alþfnator anO lt¡ountinq 10-8099 MOUNTING KIT COMPONENTS QTY P/N DESCRIPTION OTY P/N DESCRIPTION 1 AN5H.5A BOLT 1 10-1012 TENSION ARM I 4N960-516 WASHER 1 1 0-1 009 SPACER BUSHING 1 AN7-42A BOLT 1 10-1002 STARTER STRAP 1 4N960-716 WASHER 1 10-8003 CASE MOUNT BRACKET 1 4N363-720 NUT 1 10-'1003 BOSS MOUNT BRACKET c. d. e a. b. g. h. c. d. e. f. g. a b 14-3001 Rev. C Page 4of 4 Parl2, Preparation of FAA Form 337 1. lnstalled Alternators in accordance with Supplemental Type Certificate No. SAl0682SC. Updated Airplane Flight Manual with HET Airplane Flight Manual Supplement 002 (or later revision). Weight changed (compute weight and balance as necessary). Checked size of wire from Alternator output terminals to alternator circuit breakers and from Alternator circuit breakers to bus and size of Alternator circuit breakers with AC43.13-18. (Note: use this statement as applicable. lf wire and circuit breaker sizes are satisfactory, so state. lf not satisfactory, state wire and/or circuit breaker size installed to conform with 4C43.13-1 B.) 2. Modified aircraft equipment list by removal of generators listed and adding Model TAL12-70 Alternator Kit. Weight and Balance Removed two generator installations: Weight Arm (Refer to Aircraft Equipment List) Removed two regulator installations: Weight Arm (Refer to Aircraft Equipment List) lnstalled TAL12-7O alternator kit consisting of: wgt. (2) 10-1051 alternators 20.01bs. (2) 10-8099 mounting kits. 2.0 lbs. (2) R1224Voltage Regulators 0.6 lbs. (1 ) ALP-1002 Placard Neqliqible (1 ) ALP-1003 Placard Neqliqible (1) ALP-1004 Placard Neqlisible (1) ALP-1005 Placard Neqliqible (2) 14-1010 Lamps Neoliqible Part 3, Instructions for Continued Airworthiness PERIODIC MAINTENANCE: 1. lt is recommended that the operation of the TAL12-70 alternator be checked every 100 hour inspection or every annual inspection which ever comes first. 2. ANNUAL/1OO HOUR INSPECTION: a. Remove drive belt and turn alternator rotor to check condition of bearings for abnormal noise or roughness. b. Each annual/100 hour inspection, the alternator and its associated wiring should be checked for secure electrical connections and physical connection to the airframe. The belt drive tension should be re-set to the aircraft manufacturer's specification. 3. 5 YEAR OR lOOO HOUR INSPECTION a. Repeat the Annual/100 hour inspection. b. Remove field brush assembly and inspect brushes for excess wear. Replace brush assembly if brushes extend less then 0.250 inches from edge of holder case. AI RWORTH INESS LIM ITATIONS There are no mandatory replacement limits. There are no mandatory structural inspection intervals. THE AIRWORTHINESS LIMITATIONS SECTION IS FAA APPROVED AND SPECIFIES MAINTENANCE REQUIRED UNDER SEC. 43.16 AND 91.403 OF THE FEDERAL AVIATION REGULATIONS UNLESS AN ALTERNATIVE PROGRAM HAS BEEN FAA APPROVED. r0-t0t2 AN9ó0-51ó AN5H-5A OF FAA PMA NAMEPLATE F2 TERMINAL (GROUND) FI TERMINAL AN363-720 AUX TERMINAL óMM OUTPUT TERMINAL AN9ó0-Zró sMM STUD (3) AN7-424 r0-r03r I 0-8003 (CASE MOUNT BRACKET) ]O-]OO3 AS REQUIRED (BOSS MOUNT BRACKET) NOTES: l. NOTE: FOR STANDARD 7.5" DIAMETER usE PTPER V-BELT p/N 452-541 (GATES RING GEAR SUPPORT PULLEY 9335X1). NOT SUPPLTED. FWer FAA PMA HARTZELL ENGINE 10-5051 EEIIEUET E2.YWWSN NEITilGil z¿ FIRST RELEASE INTO HET DESIGN DATA 9 l\ol1 4 PAGE 3 TO PAGE I. 2) ADDED HET TITLEBLOCK 3) HARTZELL ENGINE TECHNOLOGIES WAS PLANE POWER, LTD. 4) ADDED t0-r03.l CALLOUTTO DATA TAG. 5) MODEL NO. r0-505r WAS TAL24-70. ó)REMOVED "PLANE POWER LDT." AND/OR REPLACED WITH ''HET'WHERE APPLICABLE. 7) '.PER DRAWING ON 9 /tolt 4 2900 Selmo HÌghwoy Monlgomery, At 3ó108 UNLESS OTHERWISE SPECIFIED GEOMETRIC SYMBOLS PER ANSIYI4.5 DIMENSIONS ARE IN INCHES AND APPLY AFIER HEAT TREAT AND PLATING .X = !.015 .XX = 1.010 ANGLES 1ì ' .XXX = 1.005 BREAK ALL EDGES AND MACHINE ALL INSIDE CORNER FILLETS .OI5 MAX. tzs/ SURFACE rl¡.tlSH V z Fh.TNESS S] RA IGHT N ESS O RouNDNÊss Þ cYuNDRcrY ô PRoF|LE I PERPENDTcuLARnY + PosroN O coNcENTRrc[Y = SYMMETRY Z ANGUIARÍTY // PARALLEuSM ,/ crRcur.AR RuNouT SPECIFICATION CLASSIFICATION T AI24-70 INSTALLATION INSTRUCTIONS THIS DRAWING CONTAINS INIORMATION THAT 15 CONF¡DENTIAL AND PROPRIETARY IO HAR-TZELL ENGINE TECHNOLOGIES'TH15 DRAWING IS TURNISHED ON IHE UNDERSÌANDING THAT THE DRAWING AND THE INFORMATION IT CONIAINS WILL NOI BE COPIED OR DISCIOSED TO OIHERS EXCEPT WITH THE WRITTEN CONSENT OT HARTZELL ENGINE TECHNOLOGIES, WILT NOT BE USED TO THE DEIRIMENT OF HARTZELL ENGINE TECHNOLOGIES, AND WILL BE REIURNED UPON REOUEST BY HAR'IZELL ENGINE -IECHNOLOGIES MATERIAL SEE INDIVIDUAL PARTS DRAWING NO. 14-4001 CODE ID ósPYI SCALE NTS Parts List: Qtv Part No. Descriotion 2 10-5051 Alternator,24Volt, with 1 12" V-Belt Pulley. 2 1 0-8099 Mountino kit for Lvcominq Enqine. 2 R1224 Alternator Controller (Voltaqe Requlator) and data sheet 12-1001 1 ALP-1002 Placard, LEFT ALT INOP (Part of Drawing 14-1013) 1 ALP-1003 Placard, RIGHT ALT INOP (Part of Drawinq 14-1013) 1 ALP-r004 Placard, LEFT ALT FIELD (Part of Drawins 14-1013) 1 ALP-1005 Placard, RIGHT ALT FIELD (Part of Drawinq 14-1013) 1 14-4001 lnstallation lnstructions (This document) 2 14-1011 Alternator lnoperative Lamp (28 Volt) 14-4001 Rev. C Page 2of 4 READ AND THOROUGHLY UNDERSTAND ALL OF THE INSTALLATION INSTRUCTIONS BEFORE BEGINNING INSTALLATION OF TH¡S KIT. NOTE: IF AIRCRAFT DOES NOT HAVE A CIRCUIT BREAKER OR GURRENT LIMITING DEVICE IN EACH GENERATOR'S OUTPUT AND REGULATOR'S INPUT CIRCUIT THEY MUST BE INSTALLED. Part 1, lnstallation of Alternator and Regulator 1. Disconnect aircraft battery. 2. Remove Generators and voltage regulators. 3. lnstall Alternators per drawing on page 1. Tension the belts and torque the AN5H-54 adjusting bolts to 200 in/lb and safety wire with 0.032' diameter safety wire. Torque the AN7-424 mounting bolts to 425 inllb. 4. operation (See regulator instructions for location of jumpers). 5. lf original output circuit breakers are rated at less than 70-amps and you wish to be able to utilize the increased capacity of the alternators, remove the breakers and replace with suitable breakers up to 70amp maximum size. Ensure wire size from alternat Note: lf aircraft has been equipped with an Amp Meter, ensure that it is of adequate size to handle the increased output capability before increasing the output wire and breaker. 14-4001 Rev. C Page 3 of 4 6. Wire the system as follows: a. For regulator wiring instructions view the regulator installation instructions. b. Connect the GRND terminal of each regulator to the common aircraft ground. c. Leave the ground jumper installed on the F2 terminal of the alternator. d. Connect the existing generator output wires to each alternator's 6mm OUTPUT TERMINAL (or install a new wire in accordance with 4C43.13-1 B) using a MS251 71-25 terminal nipple for insulation (Not Supplied). Torque to 50 in/lb. e. Use the original generator field wire or install a new wire, minimum 18AWG, from each alternator F1 terminal to the FLD terminal of the corresponding regulator. Torque the alternator's F'1 terminal nut to 20 in/lb. f. lnstall, in view of the pilot, placard ALP-1004 (LEFT ALT FIELD) adjacent to the field switch for the left alternator and placard ALP-1005 (RIGHT ALT FIELD) adjacent to the switch for the right alternator. g. Ensure that each of the FIELD breakers are connected to the aircraft positive bus. h. lf the aircraft has "Generator lnoperative" indicator lamps, they may be used in this step. lf lamps are not currently installed or are not compatible use the supplied lamps Pln 14-101'1 Alternator lnoperative Lamp (28 Volt) and install them in pilots clear field of view. i. lnstall, in view of the pilot, placard ALP-1002 (LEFT ALT INOP) adjacent to the lamp for the left alternator and placard ALP-1003 (RIGHT ALT INOP)adjacent to the lamp for the right alternator. Also run a new wire, minimum 18AWG, from the AUX terminal of each alternator to the AUX terminal of the corresponding regulator. 7. Adjust and Test the system: a. Set both FIELD switches to OFF. b. Turn on MASTER switch and start the engines. Ensure that both ALT INOP indicators are illuminated. c. Turn on the LEFT FIELD switch. Check proper charging indication. Check left ALT INOP indicator is off. Check aircraft maintenance manualfor proper bus voltage (typically 28.0V t 0.3V). Adjust the left (Master) regulator to the desired bus voltage at 1200 engine RPM. d. Turn off the LEFT FIELD switch and turn on the RIGHT FIELD switch. Check proper charging indication. Check right ALT INOP indicator is off. At 1200 engine RPM Adjust the right (Slave) regulator to the same bus voltage as left alternator. e. Turn on the LEFT FIELD switch. f. Check proper charging indication. Check bus voltage. g. Recheck and inspect the entire installation. Complete FAA form 337, make log book entry, update aircraft equipment list, and weight and balance. Mountinq Kit Pafts List 10-8099 MOUNTING KIT COMPONENTS QTY P/N DESCRIPTION QTY P/N DESCRIPTION 1 ANSH-54 BOLT 1 10-1012 TENSION ARM 1 4N960-516 WASHER 1 1 0-1 009 SPACER BUSHING 1 AN7-424 BOLT 1 1 0-1 002 STARTER STRAP 1 4N960-716 r¡úASHER 1 10-8003 CASE MOUNT BRACKET 1 4N363-720 NUT 1 10-'1003 BOSS MOUNT BRACKET 14-4001 Rev. C Parl2, Preparation of FAA Form 337 Page 4 of 4 1. lnstalled Alternators in accordance with Supplemental Type Certificate No. SA10682SC. Updated Airplane Flight Manual with HET Airplane Flight Manual Supplement 002 (or later revision). Weight changed (compute weight and balance as necessary). Checked size of wire from Alternator output terminals to alternator circuit breakers and from Alternator circuit breakers to bus and size of Alternator circuit breakers with 4C43.13-'18. (Note: use this statement as applicable. lf wire and circuit breaker sizes are satisfactory, so state. lf not satisfactory, state wire and/or circuit breaker size installed to conform with AC43.13-18.) 2. Modified aircraft equipment list by removal of generators listed and adding Model f AL24-70 Alternator Kit. Weight and Balance Removed two generator installations: Weight Arm (Refer to Aircraft Equipment List) Removed two regulator installations: Weight Arm (Refer to Aircraft Equipment List) lnstalled TAL 24-70 alternator kit consisting of: (2) 10-5051 alternators (2) 10-8099 mounting kits. (2) R1 224 V oltage Regulators (1) ALP-1002 Placard (1 ) ALP-1003 Placard (1) ALP-1004 Placard (1 ) ALP-1005 Placard (2) 14-1011 Lamps wgt. 20.01bs. 2.0 lbs. 0.6 lbs. Neqliqible Neqlisible Neqliqible Neqlisible Neqliqible Part 3, lnstructions for Continued Airworthiness PERIODIC MAINTENANCE: 1. lt is recommended that the operation of the TAL24-70 alternator be checked every 100 hour inspection or every annual inspection which ever comes first. 2. ANNUAL/1OO HOUR INSPECTION: a. Remove drive belt and turn alternator rotor to check condition of bearings for abnormal noise or roughness. b. Each annual/100 hour inspection, the alternator and its associated wiring should be checked for secure electrical connections and physical connection to the airframe. The belt drive tension should be re-set to the aircraft manufacturer's specification. 3. 5 YEAR OR lOOO HOUR INSPECTION a. Repeat the Annual/100 hour inspection. b. Remove field brush assembly and inspect brushes for excess wear. Replace brush assembly if brushes extend less then 0.250 inches from edge of holder case. AI RWORTHINESS LI M ITATIONS There are no mandatory replacement limits. There are no mandatory structural inspection intervals. THE AIRWORTHINESS LIMITATIONS SECTION IS FAA APPROVED AND SPECIFIES MAINTENANCE REQUIRED UNDER SEC. 43.16 AND 91.403 OF THE FEDERAL AVIATION REGULATIONS UNLESS AN ALTERNATIVE PROGRAM HAS BEEN FAA APPROVED. ì0-ì012 AN9ó0-5tó AN5H-5A FAA PMA NAMEPLATE F2 TERMINAL (GROUND) FI TERMINAL AN3ó3-720 AUX TERMINAL óMM OUTPUT TERMINAL AN9ó0-71ó sMM STUD (s) AN7-42A r 0-8003 (cASE MOUNT BRACKET) IO-IOO3 AS REQUIRED lBoss MoUNT BRACKET) NOTES: I. FOR STANDARD 7.5 DIAMETER RING GEAR SUPPORT PULLEY usE PtpER V-BELT plN 452-541 (GATES 9335X1). NOT SUppLtED FWer FAA PMA HÀRTZELL ENGINE 10-1051 EEIIEITET B2-YVVWSN NEIIilGEI Tz FIRST RELEASE INTO HET DESIGN DATA 9110/14 PAGE 3 TO PAGE r . 2) ADDED HET TTTLEBLOCK 3) HARTZELL ENGINE TECHNOLOGIES WAS PLANE powER, LfD. 4) ADDED t0-t031 CALLOUTTO DAïA TAG. 5) MODEL NO. l0-.l05ì WAS SALI2-/0. ó)REMOVED ''PLANE POWER LDT." AND/OR REPLACED WITH ''HE]"'WHERE APPLICABLE. 7) ''PER DRAWING ON 9110114 GEOMETRIC SYMBOLS PER ANSIYI4.5 UNLESS OTHERWISE SPECIFIED DIMENSIONS ARE IN INCHES AND APPLY AFIER HEAT TREAT AND PLATING .X = t.015 .XX = i.010 ANGLES 1l' .XXX = 1 005 BREAK ALL EDGES AND MACHINE ALL INSIDE CORNER FILLETS .Oì5 MAX. 12s/ suRFAcE nNtsH V CHECKED ã FLATNESS STRAIGHINESS Q nounoress H cYuNDRcrrY ô PRoFTLÊ A PERPENDTcuLARTTY + PosrroN O coNcEMRrc[Y = SYMMEfRY -Z ANcULARffY // PARALLELTsM ,/ crRcuLAR RUNou S P ECIFICATIO N CLASSIFICATION SAL I 2-70 INSTALLATION INSTRUCTIONS MATERIAL SEE INDIVIDUAL PARTS THIS DRAWING CONTAINS INFORMAIION-THAI IS CONFIDENTIAL AND PROPRIEIARY TO HARTZELL ENGINETECHNOLOGIES THIS DRAWING IS FURNISHED ON'IHE UNDERSIANDING THAI THE DRAWING AND THE INFORMATION IT CONTAINS WILL NOT BE COPIED OR DISCLOSED TO OTHERS EXCEPT WfTH THE WRTTTEN CONSENT OT HARTZELL ENGINETECHNOLOGIES, WILL NOT BE USED IO THE DEIRIMENI OF HARÍZELL ENGINE TECHNOLOGIES, AND WILL BE RETURNED UPON REQUEST BY HARTZETL ENGINE'TECHNOLOGIES. fxx xxl DRAWING NO. r 4-5001 (XX XX) Parts List: Qtv Part No. Description 1 1 0-1 051 Alternator, 12 Volt, with 1/2" V-Belt Pulley. 1 10-8099 Mountino kit for Lvcomino Enoine. 1 R1224 Alternator Controller (Voltaoe Reoulator) and data sheet 12-1001 1 ALP-1001 Placard, ALT FIELD (Part of Drawing 14-1012) 1 ALP-1006 Placard, ALT INOP (Part of Drawing 14-1012\ 1 14-5001 lnstallation lnstructions ffhis document) 1 14-1010 Alternator Inoperative Lamp (14 Volt) Dwg. 14-5001 Rev. C READ AND THOROUGHLY INSTRUCTIONS BEFORE Page 2of 4 UNDERSTAND ALL OF THE INSTALLATION BEGINNING INSTALLATION OF THIS KIT. NOTE: lF AIRCRAFT IT BREAKER O LIMITING DEVICE IN THE GENERATOR'S OUTPUT AND REGULATOR'S INPUT CIRCUIT THEY MUST BE INSTALLED. Part l, lnstallation of Alternator and Regulator 1. Disconnect aircraft battery. 2. Remove Generator and voltage regulator. 3. lnstall Alternator per drawing on page 1. Tension the belt and torque the ANSH-5A adjusting bolts to 200 in/lb and safety wire with 0.032" diameter safety wire. Torque the AN7-424 mounting bolts to 425 inllb. 4. operation (See regulator instructions for location of jumpers). 5. lf original output circuit breaker is rated at less than 70-amps and you wish to be able to utilize the increased capacity of the alternator, remove the breaker and replace with suitable breaker up to 70amp maximum size. Ensure wire size from alternator output terminal to output circuit breaker and from Note: lf aircraft has been equipped with an Amp Meter, ensure that it is of adequate size to handle the increased output capability before increasing the output wire and breaker. Dwg. 14-5001 Rev. C Page 3 of 4 6. Wire the system as follows: a. For regulator wiring instructions view the regulator installation instructions. b. Connect the GRND terminal of the regulator to the common aircraft ground. c. Leave the ground jumper installed on the F2 terminal of the alternator. d. Connect the existing generator output wire to the alternator's 6mm OUTPUT TERMINAL (or install a new wire in accordance with AC43.13-1 B) using a MS25171-25 terminal nipple for insulation (Not Supplied). Torque to 50 in/lb. e. Use the original generator field wire or install a new wire, minimum 18AWG, from the alternator F1 terminal to the FLD terminal of the regulator. Torque the alternator's F1 terminal nut to 20 in/lb. f. lnstall, in view of the pilot, placard ALP-1001 (ALT FIELD) adjacent to the field switch for the alternator. g. Ensure that the FIELD switch/breaker is connected to the aircraft positive bus. h. lf the aircraft has a "Generator lnoperative" indicator lamp, it may be used in this step. lf the lamp is not currently installed or is not compatible use the supplied lamp P/n 14-1010 Alternator lnoperative Lamp (14 Volt) and install it in pilots clear field of view. i. lnstall, in view of the pilot, placard ALP-1006 (ALT INOP) adjacent to the indicator for the alternator. Also run a new wire, minimum 18AWG, from the AUX terminal of the alternator to the AUX terminal of the regulator. 7. Adjust and Test the system: a. Set FIELD switch to OFF. b. Turn on MASTER switch and start the engine. With FIELD switch in OFF position ensure that ALT INOP indicator is illuminated. c. Turn on the FIELD switch. Check proper charging indication. Check ALT INOP indicator is off. Check aircraft maintenance manualfor proper bus voltage (typically 14.0V t 0.3V). Adjust the regulator to the desired bus voltage at 1200 engine RPM. d. Recheck and inspect the entire installation. Complete FAA form 337, make log book entry, update aircraft equipment list, and weight and balance. Mountinq Kit Parts List 10-8099 MOUNTING KIT COMPONENTS QTY P/N DESCRIPTION QTY P/N DESCRIPTION 1 AN5H-5A BOLT 1 10-1012 TENSION ARM 1 4N960-516 WASHER 1 1 0-r 009 SPACER BUSHING 1 AN7-42A BOLT 1 10-1002 STARTER STRAP 1 4N960-716 /VASHER 1 I 0-8003 CASE MOUNT BRACKET 1 4N363-720 NUT 1 1 0-1 003 BOSS MOUNT BRACKET Dwg. 14-5001 Rev. C Page 4 of 4 Parl2, Preparation of FAA Form 337 1 . lnstalled Alternator in accordance with Supplemental Type Certificate No. S410682SC. Updated Airplane Flight Manual with HET Airplane Flight Manual Supplement 001 (or later revision). Weight changed (compute weight and balance as necessary). Checked size of wire from Alternator output terminal to alternator circuit breaker and from Alternator circuit breaker to bus and size of Alternator circuit breaker with 4C43.13-18. (Note: use this statement as applicable. lf wire and circuit breaker sizes are satisfactory, so state. lf not satisfactory, state wire and/or circuit breaker size installed to conform with 4C43.13-18.) 2. Modified aircraft equipment list by removal of generator listed and adding Model SAL12-70 Alternator Kit. Weight and Balance Removed generator installation : Weight Arm (Refer to Aircraft Equipment List) Removed regulator installation : Weight Arm (Refer to Aircraft Equipment List) lnstalled SAL 12-70 alternator kit consisting of: (1 (1 (1 (1 (1 (1 10-1051 alternator 10-8099 mounting kits. R1 224 Voltage Regulator ALP-1001 Placard ALP-1006 Placard 14-1010 Lamp Part 3, lnstructions for Gontinued Ainryorthiness PERIODIC MAINTENANCE: 1. lt is recommended that the operation of the SALI 2 -70 allernator be checked every 100 hour inspection or every annual inspection which ever comes first. 2. ANNUAL/1OO HOUR INSPECTION: a. Remove drive belt and turn alternator rotor to check condition of bearings for abnormal noise or roughness. b. Each annual/100 hour inspection, the alternator and its associated wiring should be checked for secure electrical connections and physical connection to the airframe. The belt drive tension should be re-set to the aircraft manufacturer's specification. 3. 5 YEAR OR lOOO HOUR INSPECTION a. Repeat the Annual/100 hour inspection. b. Remove field brush assembly and inspect brushes for excess wear. Replace brush assembly if brushes extend less then 0.250 inches from edge of holder case. AIRWORTHINESS LI MITATIONS There are no mandatory replacement limits. There are no mandatory structural inspection intervals. THE AIRWORTHINESS LIMITATIONS SECTION IS FAA APPROVED AND SPECIFIES MAINTENANCE REQUIRED UNDER SEC. 43.16 AND 91.403 OF THE FEDERAL AVIATION REGULATIONS UNLESS AN ALTERNATIVE PROGRAM HAS BEEN FAA APPROVED. r0-30r2 AN9ó0-5ìó I 0-900ó F2 TERMINAL (GRouND) ì 0-9004 9ó0-5 ì ó MS35338- 5 MS20074-05-r2 FI TERMINAL (INTERAV REGULATOR F TERMINAL) r 0-3009 ANó-4IA AUX TERMINAL (NOT USED) óMM OUTPUT TERMINAL BATTERY WIRE INTERNAL REG+WIRE AN9ó0-ó1ó 3X sMM STUD r0-3010 INSTALL USING THIS HOLE LOCATION OF FAA PMA NAMEPLATE AN9ó0-8trr---- ô NOTES: LTCM# s39547-31 .19 V-BELT REQUTRED (pURCHASE SEPERATELY) ffig¡ FAA PMA HARTZELL ENCfNE 10-1050c EEIUEE A2.YVVWSN IlõrIilGril 12 FIRST RELEASE INTO HET DESIGN DATA I /toll 4 PAGE 3 TO PAGE ì . 2) ADDED HET TIILEBLOCK 3) HARÏZELL ENGINE TECHNOLOGIES WAS PLANE POWER, LTD. 4) ADDED l0-t03t CALLOUTTO DATA TAG. 5) MODEL NO. 10-ì050C WAS SALt 2-70C. ó)REMOVED "PLANE POWER LDT." AND/OR REPLACED wtTH "HEI'WHERE APPLTCABLE. /) "PER DRAWING ON I /to/t 4 GEOMETRIC SYMBOLS PER ANSIYI4.5 UNLESS OTHERWISE SPECIFIED ARE IN INCHES AND APPLY AFTER HEAT TREAT AND PLAIING .X = 1.015 .XX = t.010 ANGLES tl' .XXX = t.005 BREAK ALL EDGES AND MACHINE ALL INSIDE CORNER FILLETS.O]5 MAX. 12s/ sURFACE ¡r¡r¡sH V STRA6HTNESS O RouNDNEss ø cYLTNDRcnY ô enorlre I PERPENDTcuhRnY + PosnoN O coNcEMRrc[Y = SYMMETRY Z ANGUURÍIY // PARATTEuSM ,/ crRcuLAR RUNour SP ECIFICATION CLASSI FICATION SAL I 2-7 OC I NSTALLATION INSTRUCTIONS MATERIAL SEE INDIVIDUAL PARTS THIS DRAWING CONIAINS INfORMATION THAI 15 CONFIDENTIAL AND PROPRIETARY IO HARTZELL ENGINE TECHNOLOGIES THIS DRAWING IS FURNISHED ON THE UNDERS'IANDING THAT THE DRAWING AND IHE INFORMAÌION IT CONIAINS WILL NOT BE COPIED OR DISCLOSED TO OTHERS EXCEPT WITH'IHE WRIITEN CONSENT OF HARTZELL ENGINE TECHNOLOGIES, WILL NOI BE USED TO IHE DETRIMENI OF HAR'IZELL ENGINE IECHNOLOGIES, AND WILL BE REIURNED UPON REQUEST BY HARTZETL ENGINE TECHNOTOGIES [XX XX] DRAWING NO, I 4-ó001 CODE ID ósPY1 SCALE NTS Parts List: Qtv Part No. Description 1 1 0-1 050c Alternator, 12 Volt, with 3.0" Diameter 3/8" V-Belt Pulley. 1 10-9099 Mountinq kit for Continental Enqine. 1 R1224 Alternator Controller (Voltaqe Requlator) and data sheet 12-1001 1 ALP-1001 Placard, ALT FIELD (Part of Drawinq 14-1012\ 1 ALP-1006 Placard, ALT INOP (Part of Drawinq 14-1012) 1 14-6001 lnstallation lnstructions (This document) 1 14-1010 Alternator lnoperative Lamp (14 Volt) 14-6001 Rev. D Page 2 of 4 READ AND THOROUGHLY UNDERSTAND ALL OF THE INSTALLATION INSTRUCTIONS BEFORE BEGINNING INSTALLATION OF THIS KIT. NOTE: IF AIRCRAFT DOES NOT HAVE A CIRCUIT BREAKER OR CURRENT LIMITING DEVICE IN THE GENERATOR'S OUTPUT AND REGULATOR'S INPUT CIRCUIT THEY MUST BE INSTALLED. Part l, lnstallation of Alternator and Regulator 1. Disconnect aircraft battery. 2. Remove Generator and voltage regulator. 3. lnstall Alternator per drawing on page 1 . Tension the belt and torque the ANSH-74 adjusting bolts to 100 - 140 in/lb and safety wire with 0.032' diameter safety wire. Torque the AN6-414 mounting bolts to 160 - 190 in/lb. 4. operation (See regulator instructions for location of jumpers). 5. lf original output circuit breaker is rated at less than 70-amps and you wish to be able to utilize the increased capacity of the alternator, remove the breaker and replace with suitable breaker up to 70amp maximum size. Ensure wire size from alternator output terminal to output circuit breaker and from Note: lf aircraft has been equipped with an Amp Meter, ensure that it is of adequate size to handle the increased output capability before increasing the output wire and breaker. 14-6001 Rev. D Page 3 of 4 6. Wire the system as follows: a. For regulator wiring instructions view the regulator installation instructions. b. Connect the GRND terminal of the regulator to the common aircraft ground. c. Leave the ground jumper installed on the F2 terminal of the alternator. d. Connect the existing generator output wire to the alternator's 6mm OUTPUT TERMINAL (or install . a new wire in accordance with 4C43.13-18) using a MS25171-25 terminal nipple for insulation (Not Supplied). Torque to 50 in/lb. e. Use the original generator field wire or install a new wire, minimum 18AWG, from the alternator F1 terminal to the FLD terminal of the regulator. Torque the alternator's F1 terminal nut to 20 inllb. f. lnstall, in view of the pilot, placard ALP-1001 (ALT FIELD) adjacent to the field switch for the alternator. g. Ensure that the other end of the FIELD switch/breaker is connected to the aircraft positive bus. h. lf the aircraft has a "Generator lnoperative" indicator lamp, it may be used in this step. lf the lamp is not currently installed or is not compatible use the supplied lamp P/n 14-1010 Alternator lnoperative Lamp (14 Volt) and install it in pilots clear field of view. i. lnstall, in view of the pilot, placard ALP-1006 (ALT INOP) adjacent to the indicator for the alternator. Also run a new wire, minimum 18AWG, from the AUX terminal of the alternator to the AUX terminal of the regulator. 7. Adjust and Test the system: a. Set FIELD switch to OFF. b. Turn on MASTER switch and start the engine. With FIELD switch in OFF position ensure that ALT INOP indicator is illuminated. c. Turn on the FIELD switch. Check proper charging indication. Check ALT INOP indicator is off. Check aircraft maintenance manual for proper bus voltage (typically 14.0V t 0.3V). Adjust the regulator to the desired bus voltage al12OO engine RPM. d. Recheck and inspect the entire installation. Complete FAA form 337, make log book entry, update aircraft equipment list, and weight and balance Mountinq Kit Parts List 1U-9U99 MOUN I ING KI I CJOMPONEN I S QTY P/N UESL;I-{IP I ION QIY P/N DESCRIP I ION ì U.3UUV SPAL;EI-{ BUSHING 4N960-E1ttL WASHER 1U-3U1U SPACER 2 4N960-6'l 6 WASHER I U-i't.t I Z SPAL;tt-( 2 4N960-51 6 WASHER I t.,-v(rtr.1 UON I INEN tAL BRACKET 1 MIs20074-05-1 2 BOLT Itr-vtrU¿t IENSION ARM f\NbH-/A BOLT -vUt trr SUPPORT BRACKET qNb-414 BOLT rvrs3533E-45 -OCK WASHER ,l vt5z1u45-b NU 14-6001 Rev. D Page 4of 4 Part 2, Preparation of FAA Form 337 1. lnstalled Alternator in accordance with Supplemental Type Certificate No. SA10682SC. Updated Airplane Flight Manual with HET Airplane Flight Manual Supplement 001 (or later revision). Weight changed (compute weight and balance as necessary). Checked size of wire from Alternator output terminal to alternator circuit breaker and from Alternator circuit breaker to bus and size of Alternator circuit breaker with 4C43.13-l B. (Note: use this statement as applicable. lf wire and circuit breaker sizes are satisfactory, so state. lf not satisfactory, state wire and/or circuit breaker size installed to conform with 4C43.13-18.) 2. Modified aircraft equipment list by removal of generator listed and adding Model SALI2-70C Alternator Kit. Weight and Balance Removed generator installation : Weight Arm (Refer to nircraft equipment List) Removed regulator installation : Weight Arm (Refer to Aircraft Equipment List) f nstalled SAL 12-70C alternator consisting of: (1 ) 1 0-1 050C alternator (1) 10-9099 mounting kit. (1 ) R1 224 Voltage Regulator (1) ALP-1001 Placard (1 ) ALP-1006 Placard (1) 14-1010 Lamp kit wgt. 10.01bs. 1.4 lbs. 0.3 lbs. Neqliqible Neqliqible Neqliqible Part 3, lnstructions for Continued Ainvorthiness PERIODIC MAINTENANCE: 1 . lt is recommended that the operation of the SALI2-70C alternator be checked every 100 hour inspection or every annual inspection which ever comes first. 2. ANNUAL/1OO HOUR INSPECTION: a. Remove drive belt and turn alternator rotor to check condition of bearings for abnormal noise or roughness. b. Each annual/100 hour inspection, the alternator and its associated wiring should be checked for secure electrical connections and physical connection to the airframe. The belt drive tension should be re-set to the aircraft manufacturer's specification. 3. 5 YEAR OR ,1OOO HOUR INSPECTION a. Repeat the Annual/100 hour inspection. b. Remove field brush assembly and inspect brushes for excess wear. Replace brush assembly if brushes extend less then 0.250 inches from edge of holder case. AIRWORTHINESS LIMITATIONS There are no mandatory replacement limits. There are no mandatory structural inspection íntervals. THE AIRWORTHINESS LIMITATIONS SECTION IS FAA APPROVED AND SPECIFIES MAINTENANCE REQUIRED UNDER SEC. 43.16 AND 91.403 OF THE FEDERAL AVIATION REGULATIONS UNLESS AN ALTERNATIVE PROGRAM HAS BEEN FAA APPROVED.