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Service Instruction Number SIN2348 Revision K

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2. dno E1 L86Z2d0yS N r 539 79 F dAl SNOLLODMISNI NOILVTIVISNI HLIM 3ONVOHOOOV NI LAN 3nOHOL 69 drin 2 NMOHS SH3HSVM T VISNI C 10N BSN 9 0 MESZ 2 H3HSVM 916 O96NV g T 1709 J c Re INSQ S ONILLIJ ONI LJVHS3AIMO p V E1 pLEZdOMS O _ 0 Z SNS Jr pu x N T pE 2 FF d CO x E ZW L4VHSSAING 101 8 240 5 1 x 9594 NOISSIWSNVYL WOldAl SNOT LONYLSNI TIVLSNI LHe HLIM i JONVOUHOOOV NI 3anOHOL gt TIYLSNI NMOHS SV 9 LAN HlOG 484 ASSY L4VHS 1HE JI WSO O9NIISIX3 3Sf 3WH dno 1 962 6 earn Sd I NI 04 05 OL 3010401 SVM RIZ d 2 62 02 OL LON 3nouol ev 0311 17 wsIO EI Z96Zd9yS e 1 02 1 27 S1 22 1 ASIQ SI 2962ed0MS LAN 5 C IvOLZSW 3hoHOl 031210395 039 193 g 1708 vG ENV 03151 9395 W3O Q3QOV 20 S1 0 d Il dme V cO Sc 20 W M lI VILYSANI 0300 E GQ31LINI 1 0300 GI 29624393S G3GGV 42d VA3H FFZEdOMSNX3 12V 1S30N M KAMATIC
3. am s ewe a s s c 8 4 5 P fh E N OA ONLLSIXS HLIM NOLLVTIV LSNI HOJVW 38 SLuvd SSSHL 310N TIVMEUld LL ZZ8 LOSS aav d 5 13 ASSY 6 S06 L90 902 ASSY 2 MO 1 06 190 90z 7 7S9NV 61 106 290 902 3NOO 21 106 290 902 ASSV 6 106 290 90 3015 QUVOSNI DNINOO1 auf lt O an s em e s s gt A I S 9661 QALYQ NOYLX3L 1 0 7739 ONY IN3A33H9V NOIIVAHOJNI H3idOJOI 3H 138 Q3L1LIWSNVHL 51 NOILVHOdHOO SOILIVAVX OL AHVlJHdOHd Q3H3GlSNO2 SI NI3H3H Q3NIVINOO LVAHOANI 39IL1ON AHV1d3IHdOHd VI23dS SOILVANVH HLIM 2395 0 SSSINN YSASLYHM ANY H04 QO3HH3JNOO HO SI NOSYSHL NMOHS NOILVAHOJ3NI 1V21INHO3L HO N9IS3d HO JO3H3HL H3LIVA 1937905 HO SLNALNOO AHL HO S9NI VHO SIHL 1 NI HO JTOH NI HO
4. amp D ELG0ZSW ZL usn 35138 01 i TIY NOILIGNOS Sunsa emad Bb E 6 OL NOLL0VO 400g 80 106 90 902 6 i 9 SHANALSVS ONILSIX3 TIVISNI3H J8A02 emalda 281 dOMS J8A07 GE ZZEL 42 8 ASSY ISA09 6 JO 508 180 802 Asay 19 9 10 208 190 902 64 106 200 0027 9005 106 90 902 z Assy BUDD 06 280 802 c am TE E KAMATICSRWG Engineered Performance hc KAMATICSRWG Engineered Performance 3 Firewall Driveshaft Door Rework Continued d Remove cone Figure 2 Item 2 and angle Figure 2 3 from driveshaft door CAUTION Inspect driveshaft door for cracks damage and corrosion Figure 1 Item 5 If these conditions exist replace driveshaft door before proceeding e Align firewall cover Figure 2 Item 6 and secure with two screws Figure 2 Item 8 Note Ensure firewall cover Figure 2 Item 6 is installed on the aft side of the driveshaft door Figure 2 Item 9 with the lip facing forward f Locate and mark seven rivet holes Figure 2 Items 11 amp 12 on driveshaft door Figure 2 Item 9 Remove firewall cover Figure 2 Item 6 from driveshaft door Figure 2 Item 9 and d
5. SHL sii d 1 14159530 HO ON ON ONIASILNSCNI 24902 VTONSWON 3009 HO 1 8302 LIM VILYSNI 9902 LIM VILYANI E 1 o GSLIWI4 CI P2OG62d9948 v9Oc ON S I4dO0WN SH3LOOI ISH 1199 ONIMOT1IOS SHEL OdA AOHddV SI LIM VILYSNI SIH Z dno ET L962do s 32 SiS 1 05 Oi 1708 V p Q3Q33N SI trzZEdOMS N d LIM VILH3NI SOILVNVM SIHL i4dvHOHIV SHL NO GSTIVLSNI 43d c 072996 ESTE 1108 VE EINV 8 ONIMOO 4785 LAN lcvOTc9SN 8 ECEN alg 1 902 1188 SGHL dolos NIMO I lO4 SHEL SO ANY 4I 71 H3HSVM OT O9S6NV gi 91 SALON 5 GI 2962d0 S J 434 1 9624915 484 ASSY 5 SNI Lavesaarua ev Case El pLECdJIAS 31 1 ASIQ ASIA ASSY 5
6. FLIGHT MANUAL SUPPLEMENT FOR BELL 206 2068 KAFLEX ROTOR DRIVESHAFT INSTALLATION DESCRIPTION The KAflex Driveshaft Installation replaces an existing Beil main rotor gear driveshaft with SECTION 1 Operating Limitations Waicht C 3 Limitations Actual weight and CG change with K Aflex driveshaft is negligible SECTION 2 0 perating Procedu res Prefiieht In 1 KAflex Main Rotor Driveshatt a General Condition CHECK for broken loose and missing hardware Flex Frame and Mount Bolt Torque Stripes FAA APPROVED REVISED CAUTION DO NOT ATTEMPT TORE bE TIGHTEN FLEX FRAME BOLTS OR NUTS IF LOOSE REMOVE FROM ROTORCRAFT AND RETURN TO KAMATICS CORPORATION JUN 28 2008 DI KAMATICSRWG KAMAN naine D Specialty Bearings amp Engineered Products COMPONENT NAME PART NUMBER SERIAL NUMBER PAGE OF KAFLEX DRIVESHAFT HISTORICAL SERVICE RECORD INSTALLATION DATA A C HOURS REMOVAL DATA SCH FOR O H DATE INSTALLED BY INSTALLED COMP HRS RETIRE REMOVED AT COMP HRS HRS REASON FOR Bolen NS NeW SINCE Om Janey NL NEW SINCEOH REMOVAL TECHNICAL DIRECTIVES AND HISTORY OF OVERHAUL DIRECTIVE NUMBER TIME DATE COMPLIANCE IF APPLICABLE EFFECTIVITY BY ACTIVITY DATE 1 500 HOURS INSPECTION 6 000 HOURS INSPECTION AND ANY OTHER REP
7. Feels of gt September 12 1988 Bale ro a June 11 1990 Grate of issuance 4 1990 amended june 1 2001 Any alteration ef this certificate punishable by a fine exceeding 51 000 or Imprisonment exceeding 3 years or both FAR Fora 8110 2110 68 Page 1 of 1 This certificate may be rransferred accordance with FAR 21 47 KAMATICSRWG Engineered Performance gt SUPPLEMENTAL TYPE CERTIFICATE 10052951 This Supplementa Type Certificate is issued by EASA acting in accordance with Regulation EC No 216 2008 on behalf of the European Community its Member States and of the European third countries that participate in the activities of EASA under Article 66 of that Regulation and in accordance with Commission Regulation EU No 748 2012 to KAMATICS CORPORATION 1330 BLUE HILLS AVENUE BLOOMFIELD 06002 USA and certifies that the change in the type design for the product listed below with the mitetions and conditions specified meets the applicable Type Certification Basis and environmenta protection requirements when operated within the conditions and limitations specified below Original Type Certificate Number EASA IM R 512 Type Certificate Holder BELL HELICOPTER TEXTRON CANADA Type Design Model 206A 2068 Original STC Number FAA STC SH7767SW Description of Desian Change Installation of KAMATICS KAflex Main Rotor Driveshaft Kit
8. 35072510 asn OL 35 43217 HO 1 1 ON NOILVHOdHOOS S231 1VAVM 30 AlH3dOHd SI NISYSH GSNIVLNOD NOILVAHOJNI pem SLHOIY AHVIJIHdOHd JO 321 10N 2 a __ ON _________ NOI 18142530 Noz 91915 SNOISIA3H 031 5 3SIMH3HIO SS3 NO S3LON lS 5314021 902 GOO IOI 6 ES OEO 902 N d I1Hg INNOW NOI LV IOSI AHHVH 901 901 JO HOM3H 3ONVN3INIVA 3H1 NI SNOILOQHISNI Hd H3ldOOI 3H LNNOWN NOIIVJOSI 3AOW3H 1 WAHL NO 3lV d 3AVN SAVH 17115 AVA SINDQON 3010 WSHL NO 5 3AVN 3AVH AYN 101 HO 500 625 020 302 L1HVd ILHE SLNNOW NOILV IOS OML Q3OHJ3A SVH AMYVG 32415 310N ea E 3una g20Hd V AJY EI 84 902 NILATING 4V2INO3L OL 83338 53903 duvHS a 5 5 0 53903 dHVHS 031319395 5 NMOHS SV 101 HO S00 6b EG OEO 902 N d LNNOW NOILVIOSI AHHVG JO H3AOO 901 JHL ASICGOW 1356 4 55 19 III AdAL ZOI Zvr6 662 lH 5 H3JAOO 31V ld SHL N33M13g LNIOC 1735 3i1V d L1NOHJ SHL NI 105 5317139 4 060 G
9. Figure 4 a b Install firewall cover Figure 2 Item 7 using 4 screws Figure 2 Item 8 Install driveshaft door Figure 2 Item 5 and gasket Figure 2 Item 4 using 11 screws Figure 2 Item 8 and remaining 2 screws Figure 2 Item 8 c Turn KAflex Driveshaft by hand to ensure proper operation and clearance Check clearance between the driveshaft and firewall covers Figure 2 Items 6 amp 7 at four positions 3 o clock 6 o clock 9 o clock and 12 o clock Minimum clearance must be 0 450 If the clearance is less than 0 450 it can be adjusted by loosening 4 screws Figure 2 Item 8 and sliding firewall cover Item 7 or by loosening 11 screws 14 and sliding driveshaft door Item 5 within the clearance of the screw hole and then re tightening the screws CAUTION Ensure aircraft rotors are free to turn and will not strike any surface d Carefully check all electrical lines fuel lines hydraulic lines and bleed air lines for interference or looseness Houte and secure all lines in accordance with AC43 13 1A chapters 10 amp 11 Close engine cowling and install transmission fairing Connect battery Ground run aircraft Complete Historical Service Record and applicable logbook entries should be updated and all the required entries made any time a service or inspection is performed on the driveshaft Page 13 KAMATICSRWG Engineered Performance 1 SECTION 2 KAflex DRIVESH
10. Kamatics rotor brake kit P N 2975 is needed to complete the KAflex installation Note For KAflex inertia kit P N SKCP3244 or rotor brake installation kit P N SKCP2975 please contact Kamatics Corporation Purpose This document provides instruction for retrofit of the SKCP2348 101 KAflex Driveshaft on the Bell 206A and 206B series helicopters The SKCP2348 101 driveshaft is manufactured by Kamatics Corporation Bloomfield CT Additional copies of this document may be obtained by contacting Kamatics Corporation 1330 Blue Hills Ave Bloomfield CT 06002 860 243 9704 4 KAMATICSRWG Engineered Performance SECTION 1 KAflex DRIVESHAFT RETROFIT 1 Preparation and General Notes a Disconnect battery b Remove transmission fairing and open engine cowling to gain access to main driveshaft 2 Removal of Driveshaft Figure 1 P N 206 040 100 or 206 040 015 a From right side of helicopter remove two screws ltem 6 securing driveshaft cover Item 8 and cone assembly Item 18 b Remove eleven screws Item 14 securing driveshaft door Item 5 to aft side of forward firewall Item 15 Remove driveshaft door Item 5 and gasket Item 4 from aircraft c Remove four bolts Item 3 eight washers Item 2 and four nuts Item 1 attaching forward driveshaft coupling to input adapter on transmission d Remove four bolts Item 9 eight washers Item 10 and four nuts Item 11 attaching aft driveshaft co
11. firewall covers Figure 2 Items 6 amp 7 at four positions 3 o clock 6 o clock 9 o clock and 12 o clock Minimum clearance must be 0 450 f the clearance is less than 0 450 it can be adjusted by loosening 4 screws Figure 2 Item 8 and sliding firewall cover Figure 4 Item 7 or by loosening 11 screws Figure 4 Item 14 and sliding driveshaft door Figure 4 Item 5 within the clearance of the screw hole and then re tightening the Screws CAUTION Ensure aircraft rotors are free to turn and will not strike any surface d Carefully check all electrical lines fuel lines hydraulic lines and bleed air lines for interference or looseness Route and secure all lines in accordance with AC43 13 1A chapters 10 amp 11 Close engine cowling and install transmission fairing Connect battery Ground run aircraft Complete Historical Service Record and applicable logbook entries should be updated and all the required entries made any time a service or inspection is performed on the driveshaft Page 16 KAMAN KAMATICSRWG Engineered Performance KAMAN SECTION 3 INSPECTION OF KAflex DRIVESHAFT 1 Inspection DAILY INSPECTION BEFORE FIRST FLIGHT OF THE DAY 1 Check general condition of KAflex Driveshaft a Check for loose and missing hardware bolts nuts washers If loose or missing hardware is found return driveshaft to Kamatics Corporation 1330 Blue Hills Ave Bloomfield CT 06002 Include descr
12. in accordance with drawing SKCP2782 EASA Certification Basis The Certification Basis CB for the origina product remains applicable to this certificate approval The requirements for environmental protection and the associated certified ncise and or emissions levels of the original product are unchanged and remain applicabie to this certificate approval See Continuation Sheet s For the European Aviation Safety Agency Date of issue 14 April 2015 Massimo MAZZOLETTI E Head of Rotgrcraft Department Note The following numbers are listed on the certificate EASA current Project Number 0010034301 001 SUPPLEMENTAL TYPE CERTIFICATE 10052951 KAMATICS CORPORATION TE STC 00091 003 Copyright European Aviation Safety All rights reserved 12 Page 27 KAMATICSRWG Engineered Performance EASA pam Associated Technical Documentation Flight Manual Supplement for Bell 206A 206B KAflex Main Rotor Driveshaft Installation Revision N C dated June 28 2006 or later revisions of the above listed documents approved by EASA in accordance with EASA ED Decision 2004 04 CF or subsequent revisions of this decision and or the Technical Implementation Procedures of EU USA Bilateral Agreement Service Instruction Number SIN2348 Revision K Installation Drawing SKCP2782 Revision F Installation Drawing SKCP3244 Revision C Limitations Conditions 206 rotorcraft with tail rotor drive shaft part num
13. the KAflex Driveshaft and inspect the top of the isolation mount P N 206 030 539 003 101 or 005 if installed If contact has occurred refer to Section 5 Page 20 KAMATICSRWG Engineered Performance 5 After Lightning Strike a Lightning damage can show as burn marks heat discoloration arc marks or as small weld marks where the metal has melted and became solid again b If evidence of lightning damage is found on the driveshaft as described in Item a above attach a tag to the driveshaft and write THIS DRIVESHAFT WAS REMOVED FROM SERVICE BECAUSE OF A LIGHTNING STRIKE Return the driveshaft to Kamatics Corporation for evaluation 6 Compressor Stall Surge a Remove and examine the engine to transmission driveshaft for condition b If any damage suspected to be related to the compressor stall or surge is found make an entry on the Historical Service Record and attach a tag on the driveshaft and write THIS COMPONENT WAS REMOVED FROM SERVICE BECAUSE OF A COMPRESSOR STALL SURGE Return the driveshaft to Kamatics Corporation for factory inspection c no defects were detected return the engine to transmission driveshaft to service 7 Pylon Whirl a Pylon Whirl is an elliptical motion of the pylon which occurs after blade flapping and mast bumping Pylon Whirl inspection will follow the following conditions i An abnormal landing Excessive slope landing Helicopter was operated in se
14. AFT REMOVAL AND INSTALLATION KAflex Driveshaft Removal Figure 4 a b Disconnect battery Hemove transmission fairing and open engine cowling to gain access to KAflex Driveshaft From right side of the helicopter remove 15 screws Figure 4 Item 14 securing firewall cover Figure 2 Item 7 and driveshaft door Figure 2 Item 9 to firewall Remove firewall cover Figure 4 Item 7 driveshaft door Figure 4 Item 5 and gasket Figure 4 Item 4 from aircraft Hemove 4 nuts Figure 4 Item 1 8 washers Figure 4 Item 2 and 4 bolts Figure 4 Item 3 securing the forward portion of the KAflex Driveshaft Remove 4 nuts Figure 4 Item 11 8 washers Figure 4 Item 10 and 4 bolts Figure 4 Item 9 securing the aft portion of the KAflex Driveshaft Install workaid per Figure 3 on KAflex Driveshaft by installing workaid collars over driveshaft and attach tightening screws with nuts Compress forward frames Position lugs of the two tightening screws over nut attaching end fitting to the flex frame at aft end of KAflex Driveshaft The KAflex Driveshaft will be reinstalled with the serial number aft to facilitate future maintenance and inspections Orientation does not affect function of the KAflex Driveshaft Compress KAflex Flex Frames by tightening the workaid nuts approximately Remove KAflex Driveshaft from aircraft Page 14 KAMATICSRWG Engineered Performance KAMAN 2 KAflex Driveshaft
15. AIRS MAINTENANCE PERFORMED ON THE DRIVESHAFT MUST BE RECORDED ON THIS HISTORICAL DATA CARD P O o DIG KAMAN PW r2 Specialty Bearings 8 Engineered Products SCHEDULED INSTALLATION DATA REMO REMOVAL DATA ACCULULATED TIME ON ACCUMULATED TIME ON ASSEMBLY OR PART ASSEMBY OR PART SERIAL NUMBERS DATE SINCE SINCE COMPONENT ii OVERHAUL ES packed OVERHAUL HOURS HRS HRS ORIGINALLY PLACED IN COMPONENT NAME SERVICE PART NUMBER 5 2 5 5 8 5 8 5 8 5 2 5 2 5 I 9 8 5 5 qe qe ee lt ie qe die lt qp dee lt qe te e
16. Installation Figure 4 a Install workaid per Figure 3 on KAflex Driveshaft by installing workaid collar s over driveshaft and attach tightening screws with nuts Position lugs of the two tightening screws over nut attaching end fitting to flex frame of KAflex Driveshaft Figure 3 The KAflex Driveshaft will be installed with the serial number aft to facilitate future maintenance and inspections Orientation does not affect function of the KAflex Driveshaft CAUTION If the lugs on the tightening screws are installed incorrectly over the nut attaching flex frame to flex frame the flex frames can be over compressed and the flex frames are likely to be damaged b Compress KAflex Flex frames approximately 74 by tightening the workaid nuts c Install KAflex Driveshaft in the aircraft with serial number facing aft d Loosen workaid nuts and allow KAflex Driveshaft to extend aligning pilots on KAflex Driveshaft to Quill Adapter and Freewheeling Adapter Remove workaid Install four bolts Figure 4 3 at the forward portion of the KAflex Driveshaft ensuring bolt heads face aft Do not put washers under bolt heads f Install eight washers Figure 4 Item 2 and four nuts Figure 4 Item 1 on the four bolts Do not put washers under bolt heads g Install four bolts Figure 4 Item 9 at the aft portion of the KAflex Driveshaft ensuring bolt heads face forward Do not put washers under bolt heads h Install ei
17. KAMATICSRWG Service Instruction Number SIN2348 Revision K Installation Maintenance and Repair of the KAflex Driveshaft for the Bell 206A 206B Helicopter KAMAN Specialty Bearings amp Engineered Products KAMATICSRWG Engineered Performance KAMAN KAMATICS CORPORATION SERVICE INSTRUCTION NUMBER 2348 This Service Instruction consists of the following sections The KAflex pex o rc s Il KAflex Driveshaft Retrofit KAflex Driveshaft Removal and Installation KAflex Driveshaft Inspection KAflex Driveshaft Maintenance KAflex Driveshaft Repair Supplemental Type Certificate 2782 Installation Drawing Weight and Balance Driveshaft Installation Kit in accordance with drawing SKCP2782 contains the following parts please check parts before continuing 1 KAflex Driveshaft P N SKCP2348 101 2 Firewall Cover kit SKCP1322 3 3 12 MS20613 3C Universal Head CRES Rivets 6 required Included in SKCP1322 3 Firewall Cover 2 520427 Flush Monel Rivet 1 required Included in SKCP 1322 3 Firewall Cover 5 Certificate of Compliance 6 Kamatics Corporation Service Instruction Number 2348 7 Historical Service Record in back pocket of Service Instruction The following tools will be required to complete Section 1 of this Service Instruction p os xe c 3 32 or 093 drill bit Electric or air drill motor Rivet gun with 3 32 set 0 100 in lb torque wrench Worka
18. LINI 1 S BbrECdOMS IOI BPECdOXS 335 AJ1S8W3SSV HOS i quem 14 Q31V20 ATIVYLNAD 5043 IZ I O C E g Nea V V NOI 1935 ENS Wins HN pes Wa IN CSS ASANO YAY s L N N N N N LN N SQN3 dAl 2 SOILVAVM HLIM IN3A33HOV 5 Ad X04 Q3dlAOHd SSAINN H3A31vHM ANY GSYYaANOD HO 51 NOSYSH L NMOHS NOTLVAYOSNI IVOINHO3I HO 1530 HO JOSYSHL 1030816 HO SLNSLNOD JHL SIHL 1 NI HO NI HO 35073510 361 OL 35 43017 HO NI ON NOILVYOdHOD SOILVAVM JO AlH3dOHd JHL SI NI3H3H GANIVLNOD NOILIVAHO ANI SIH9I H AHVI3IHdOHd JO 32110N HLONSAT 3334 SpO O 028 11 9661 Se 031 0 d 1 IH 7739 ONY 560 IN3A33HOV NOILIVAHOJNI AHVlIZIHdOHd NOHLIX31 HdldOO2I 3H 1196 01 GALLINSNVYL SI ONY NOILVHOdHOD SOILVAV Ol AHVlI3HdOHd Q3H3O0ISNOO SI Q3NIVLINOO NOILIVAHO JNI SDILON AHVI3IHdOHd 12346 weena 0 ZEZ Yad 5 8 28 24095 SONSYSSHSLNI WOISAHd 40 5 GSATIVLSNI 90 4 902 L vEO 90 902
19. OS WYN OT LWHOdHOD S2 LLVIAVM Ecc oe SONNOd HONI OZ OL OG SLOAN pJ H3ldVOV 3noMOL ONISN SLOAN ONY Lb 2288015 SHdJHSVM LHOIS IE 51708 YNOS TIVISNI 1708 LNSWHOVLLY 137 NOIDA SONNOd HOINI 04 OL OS SLON ANOYOL 1 H3ldVOV 1 ONISN 428 SIN NOS 82 SHdHSVM LHOIS OE 51708 YNOS TIVISNI S3TOH 1708 LNSWHOVLLY SNI Id OS QHvMHOd NO9I IV JO LASHS 335 SSYNLVNOIS 51709 JO JHL YSONN SH3HSVM TIWLISNI LON OG NMOHS SV SLOAN YSONN SH3HSVM TIVLSNI 0315412345 ASIMYAHLO SSAINN S310N IvH3N39 LAN PE 1 1 NIVA 32 HdHSVM l34MSV9 ATENASSY H3JAO2 LINN SNI 3uHM33H4 MgHOS vc 1708 YSHSVM 1708 OE QHVMHOJ 22 M3ldvOv 77100 62 l3MSV9 3lV Td 3475070 JZ HJHSVM BZ IAN M3HOS 61 3015 DNDIOO1 N M OO0 SZL WLS 1Y LEAS A gt __ ___ ____ 5 ff 7 a j 7 j X b 7 1 Y t H 5 W x g Du QN th 4 E 6 Y A D EN D M P LI D p T
20. QO3TIViSNI 14 H3AOO L1NOHJ JHL 3AY31NE 20080 NNOD Q T3 AOO 1 amp 8 ANYdAOO v o o 1 WINS IETA SI3AIH dOL JOOH ONY LNDOWLAHHVO GHOT N33M130 SISIX3 39N3H33H31NI Jl 1 902 AVOINHOSL ILAG OL H3J3H JOOH NIGVO ONY INNON adya HO WIS A E SAIHS GSZIMOHLAVYNN ASN OQ TNVHYSAO ONY SONVN3INIVA SONVGYOIDV NI LINNON 11 61 N39 3215 9015 HO HO 1 INNON NOI LV IOSI NOISSIWSNVHL ONY 101 24 5 LJvHS3AIHO X314v4 3ON3H3JH3INI JO ALITIG VaOud OL MHON3H HOJ NOSV3H RN DEL RENE UU V V NOILOSS 434 529 1 EL J3H 1d 901 1 m 1 o 1 OLNI SON31X3 I I S lt lt E 438 20 E g Q 11235 LIN3A33H9V 3 5 H04 SS3 INn H3A31VHA 3SO0dMHnd QO3HH3JNOO HO Q31NVHO9 51 NOSYSHL NMOHS 9661 S2 qalvq AN O ALV1d H3AOD2 LNOYS OSc v 1 I 434 NOILVAHOJ3NI 1VOINHO3L1 HO N9IS3GQ HO JO3H3Hl 1 31 31 0 TH 1138 ONY SOIL
21. SOI 90 902 G90 1189 1139 EOI 0 90 902 907 902 SHJHADN iHVd 7738 HOLOH JHL HLIM 38 A IN3SSV LSAVHSSATYCQ X3 14V 3 NOILIVTIVISNI 9902 902 S I300WN H3ldO2I TSH 1138 NO SIHL 40 NOIIVTIVISNI ONIMvHO SIHI HLIM 3O9NVQHOOOV NI ATISNSSSY LAVHSSAINO SOILVNWVM Y JO NOILYTIVLSNI S3 lAOHd 0661 11 ANAT NO 0316561 MSZ944HS YSAEGNNN NOIIVOIJILH3O AdAL ZVIN3A3 dd S NOILVHISINIAOV NOIIVIAV Wdasds4 Z SNY Yad TOL 9NINOISN3AIO 9 3HvMQOHvH HO HO SHAEWNN LlHVd HOJ 9902 HO 3GOA SLYVd 031 415 IIHS 335 9 61 SM3HOS 22 YivM3HI QHvMHOd 40 3015 134 NO amp c L345V9 3lV 1d 3H09S019 LAVHSSATYO TIVLSNI OI Q1S JIN H3d SS3NHOnOH 32V 3Hn5 O6 0E E A3INId O10 F 32v d SlvWiO3Q ZCELdODMS OEO S5 O 53903 dHVHS 18 61 Navan 031512395 3SIMYSHLO 533 101 dO 1511 NOI 141 80530 ON ONIASILNAGI V IH3LVN WIHALVA 3215 2015 MO HO lHVd 20080 07131 J3AOO 18 ANN
22. SRWG Engineered Performance SECTION 8 WEIGHT amp BALANCE The KAflex Main retrofit has negligible effect on weight and balance of the helicopter Page 34 Kamatics Corporation 1330 Blue Hills Avenue Bloomfield CT 06002 USA 1 850 243 9704 KAMATICSRWG Engineered FLIGHT MANUAL SUPPLEMENT FOR BELL 206A 206B KAFLEX DRIVESHAFT INSTALLATION This supplement shall be attached to the flight manual for the 206A 206B with SKCP2348 101 KAflex Driveshaft Installation in accordance with S T C No SH7767SW The information contained herein supplements the information of the basic flight manual For limitations procedures and performance data not contained in this supplement consuit the basic flight manual Approved 1 acres Office ANE 150 JUN 28 2 FAA APPROVED OF3 Kamatics Corporation K AM ATICS RWG 1330 Blue Hills Avenue Bloomfield CT 06002 USA engineered Performance 1 860 243 9704 ROTORCRAFT FLIGHT MANUAL SUPPLEMENT FOR BELL 206A 206B KAFLEX DRIVESHAFT INSTALLATION LOG OF REVISIONS REVISION PAGES NO REVISED REMARKS DATE APPROVED NIC 1234 Pages ca Boston Aircraft Certification Office 150 JUN 2 8 2005 FAA APPROVED REVISED 2 0 3 Kamatics Corporation KAMATICS R WG 1330 Blue Hills Avenue Bloomfield CT 06002 USA engineered 1 860 243 9704 ROTORCRAFT
23. VAVM N33M138 1937815 HO SLIN31NOO JHL HO 9NIMvHO SIHL M IN3A33HO9V 39NVHOX3 NOILYWHOSNI ANMVISIMdOMd 1 NI HO 33 0H NI 32naGOHd3H HO 35072510 asn NOHIX31 H3ldO2I3H 7738 OL GSLLIWSNVYL OL 35 3217 HO ON NOlLVHOdHOO SOI IVWNVM SI SOILVAVX OL AHVIJ3HdOHd JO AlH3dOHd SHL SI NI3H3H Q3NIVINOO NOI LVABOJNI 5 51 NI3H3H GANIVLNOD NOIIVAHOJNI M on oa SIHOIM JO 32110N 30110 1 1 1 6 s 2 BL 4 B NS obse INSNV NO 0951 ASSV LX3N TIVLSNI LIM VILYSNI J4VM 90 5 9 m 3 QE NOI LVOI Sew SNO T TOUS gt Ol leroy HLIM oio de OKI a dar JjONVOIHOOOV NI S3NI 0 235 ANY 31008 SSJ3N43S00 HO d3ONdMddJdHdlNI 504 CUTS SSNI7 HIV 593 1 OIUAVYGAH S3NI 1309 S3NIT 1v2OIHLOS13 VW MO3HO A ri43HV2O 031319395 2 V INN M nr AREE ETE Sar i LIM VILYSNI HLIM IOI 8v amp cdOMS LAVHSSATYGCG TIVLSNI OL SYSH NMOHS
24. bers 206 040 383 101 206 040 383 105 206 040 387 103 206 040 387 105 and 206 040 387 107 must have the Kamatics Inertia Kit drawing SKCP3244 Revision C or later installed Prior to installation of this design change it must be determined that the interrelationship between this design change and any other previously installed design change and or repair will introduce no adverse effect upon the airworthiness of the product end Note The following numbers are listed on the certificate EASA current Project Number 0010034301 001 SUPPLEMENTAL TYPE CERTIFICATE 10052951 KAMATICS CORPORATION TE STC 00001 003 Copyright European Aviation Safety Agency rights reserved 2 2 Page 28 KAMATICSRWG Engineered Performance SECTION 7 INSTALLATION DRAWING Following are copies of the installation drawing in the STC 7767SW 2782 1 2 244 1 29 10 40 902 AV 11041 s HOV 01 1 ___ 2 BB ___ O6 0E E E 28 24075 AJY 31150990 HSVQ NMOHS HSvG 000 Od3H 9902 7739 n MEN AHnHW3SSv LJVHS3AIHQ X3 VM ONIMVYO NOILVTIVISNI S 5 GSI d1oadS 3SIMMSHIO SES NA 0090 NNOD 21 Aa NO LVHOdHOD SOTLVANVM S39NVYH3 IOL euge ene ree aan i Saar SEEREN exco
25. e stripes to 4 aft KAflex mounting bolts and nuts k Torque four nuts at the forward portion of the KAflex Driveshaft Figure 4 Item 1 in accordance with OEM installation instructions ensuring pilot is engaged and KAflex Driveshaft end fitting flanges are flat against the Quill Adapter I Apply torque stripes to 4 forward KAflex mounting bolts and nuts Page 10 2 4 5 B1 B2 B3 B4 B5 Driveshaft Forward Fitting Looking Aft Main Driveshaft B5 anaa aana KAMAN View A A Driveshaft Aft Fitting Looking Forward Main Driveshaft Workaid Collars Workaid Brackets 2PL Wing Nut KAflex Driveshaft Flex Frame Nut Serial Number Installation Tools SKSP1321 or SKSP1375 Yoke Foot Brackets 2PL Hex Nut 2PL KAflex Driveshaft Flex Frame Nut Installation Tool SKSP1404 View B B wa B3 B2 FIGURE 3 Installation of Workaid Installation Tool SKSP1321 SKSP1375 or SKSP1404 Page 11 KAMATICSRWG Engineered Performance yeuseAn OU 22198 Suasana J USBAA 108 x9nv 7 38913 12295 11 2261 dONS 19 88114 dOWS HAND GEM9J J yeyseayg ocg jexsec yog JOSE AA IN an QD r Page 12 KAMATICSRWG Engineered Performance 6 Driveshaft Door Installation
26. ease oil or dirt is covering suspected area or any doubt exists as to whether actual fretting has occurred clean suspected areas thoroughly and recheck in conjunction with next daily inspection If fretting is apparent return Driveshaft to Kamatics Corporation Include description of reason for return and copy of historical record card with the driveshaft e Inspect KAflex Driveshaft for sign of contact rubbing and or chafing OUT OF AIRCRAFT INSPECTION Note This inspection is to be done at 1500 hour intervals coinciding with removal and inspection of freewheeling clutch This inspection reads like the 100 hour inspection but will be more comprehensive with the driveshaft out of the aircraft 1 Check general condition of KAflex Driveshaft a Check for broken loose or missing hardware bolts buts washers loose or missing hardware is found return driveshaft to Kamatics Corporation Include description of reason for return and copy of historical record card with the driveshaft b Inspect flex frame bolt torque stripes for evidence of slippage If the torque stripes have faded touch up using F 925 Skydrol resistant seal equivalent available from Organic Products Co at 972 438 7321 If the torque stripes are yellow contact Henkel North America http www henkelna com to obtain a touch up kit Loctite E 20HP Hysol Epoxy Adhesive Fast Setting WARNING DO NOT disturb or tighten flex frame nuts or bol
27. emove the transmission mount per service instructions b Modify the Lord Barry Isolation Mount in accordance with SKCP2782 Sheet 3 Section 7 c Reinstall the mount according to the BHT Maintenance Manual Note Do not use unauthorized shims adhesives or sealants between the Lord Barry Mount and the cabin roof Refer to BHTI Technical Bulletin 206 77 14 if interference exists between the Lord Barry Mount and roof top rivets 5 KAflex Driveshaft Installation Figures 3 and 4 Note Inspect KAflex Driveshaft in accordance with Section 3 KAflex Driveshaft Inspection and Section 5 Repair of KAflex Driveshaft before proceeding with the installation a Install Workaid on KAflex Driveshaft by installing Workaid collars over driveshaft and attach tightening screws with nuts Figure 3 Compress forward frames Position lugs of the two tightening screws over attaching end fitting to flex frame of KAflex Driveshaft Figure 3 The KAflex Driveshaft will be installed with the serial number aft to facilitate future maintenance and inspections Orientation does not affect function of the KAflex Driveshaft CAUTION If the lugs of the tightening screws are installed over the nut attaching flex frame to flex frame the flex frames can be over compressed and the flex frames are likely to be damaged Page 9 KAMATICSRWG Engineered 5 KAflex Driveshaft Installation continued b Co
28. ght washers Figure 4 10 and four nuts Figure 4 11 on the four bolts Do not put washers under bolt heads Note If a riveted TRDS is installed in the aircraft an inertia kit SKCP3244 is required with this KAflex Driveshaft see Section 1 Page 4 In that case use the hardware bolts nuts washers supplied with the inertia kit for the aft portion of the driveshaft Install the inertia kit as shown on the drawing SKCP3244 enclosed in Section 7 Page 15 KAMATICSRWG Engineered Performance a Torque four nuts Figure 4 Item 11 in accordance with OEM installation d instructions ensuring pilot is engaged and KAflex Driveshaft end fitting flanges are flat against the Freewheeling Adapter Apply torque stripes to 4 aft KAflex mounting bolts and nuts Torque four nuts at the forward portion of the KAflex Driveshaft Figure 4 Item 1 in accordance with OEM installation instructions ensuring pilot is engaged and KAflex Driveshaft end fitting flanges are flat against the Quill Adapter Apply torque stripes to 4 forward KAflex mounting bolts and nuts 3 Driveshaft Door Installation Figure 4 a b C Install firewall cover Figure 4 Item 7 using 4 screws Figure 4 Item 8 Install driveshaft door Figure 4 Item 5 and gasket Figure 4 Item 4 using 11 screws Figure 4 Item 8 Turn KAflex Driveshaft by hand to ensure proper operation and clearance Check clearance between the driveshaft and
29. id KAflex Frame Compressor P N SKSP1321 SKSP1375 OR SKSP1404 Machine shop facilities if aircraft is equipped with a BHTI P N 206 030 539 101 or 005 Lord Barry Transmission Isolation Mount Page 1 KAMATICSRWG Engineered Performance LOG OF REVISIONS TO KAMATICS CORPORATION SERVICE INSTRUCTION NUMBER 2348 Reason Prepared By Preparation of basic manual J Miller Added changes for Lord Barry Mount Modification J Miller Remove requirement for annual removal inspection J Miller Change inspection intervals to agree with those of other nearby drivetrain components added alternate work aid correct callout J Miller for number of fasteners Changed firewall cover to have pre drilled holes Improved FS Instructions in general Changed driveshaft dash number to 101 J Parekh Added weight and balance section Increased inspection interval from 4500 hours to 6000 hours J Parekh Added inertia kit SKCP3244 to be installed with riveted TRDS J Parekh Included 370 max installation compression limit install tool Added Inspection Criteria for Compressor Stall Surge and Pylon J Parekh Whirl Installation Drawing SKCP2782 now at Revision F added corrosion protection coating note Updated workaid illustrations Revised to account for possible change in OEM hardware due to A Zink EASA SIB No 2012 0682 Additional revisions related to EASA SIB 2012 06R2 Kamatics supplied MS21042 nuts removed fr
30. iption of reason for return and copy of historical record card with driveshaft b Inspect flex frame and mount bolt torque stripes for evidence of slippage WARNING DO NOT disturb or tighten flex frame nuts or bolts Evidence of turning fasteners by wrench or other means is cause for rejection 100 HOUR INSPECTION 1 Check general condition of KAflex Driveshaft a Check for loose and missing hardware bolts nuts washers If loose or missing hardware is found return driveshaft to Kamatics Corporation Include description of reason for return and copy of historical record card with driveshaft b Inspect flex frame and mount bolt torque stripes red for evidence of slippage If the torque stripes have faded touch up using F 925 Skydrol resistant seal or equivalent available from Organic Products Co at 972 438 7321 If the torque stripes are yellow contact Henkel North America http www henkelna com to obtain a touch up kit Loctite E 20HP Hysol Epoxy Adhesive Fast Setting WARNING DO NOT disturb or tighten flex frame nuts or bolts Evidence of turning fasteners by wrench or other means is cause for rejection Page 17 KAMATICSRWG Engineered Performance KAMAN 100 HOUR INSPECTION continued c Inspect KAflex Driveshaft for damage and corrosion Refer to Figure 5 for damage and repair limits d Inspect KAflex Driveshaft flex frame joints for fretting dust which will show up as red metallic residue If gr
31. m Praxair Surface Technologies 1550 Polco St Indianapolis In 46222 Zinc Chromate primer color T even though it does not blend cosmetically with Sermetel coating can be used if Sermetel touch up products are unavailable 8 If damage results from contact with transmission isolation mount proceed as 9 follows a If contact with Lord Barry mount P N 206 030 539 303 occurs return driveshaft to Kamatics for evaluation b If contact with Lord Barry mount P N 206 030 539 101 or 005 occurs during unusual and severe condition and depth of damage to top cover does not exceed 025 lightly stone smeared aluminum ceramic coating on corners of flex frames end fittings and interconnect ears to remove raised material and sharp edges Restore coating per Note 6 as necessary If damage to top cover exceeds 025 return driveshaft to Kamatics for evaluation If damage exceeds limit specified in this section return driveshaft to Kamatics Corporation Include description of reason for return and copy of Historical Record Card with the driveshaft Page 24 KAMATICSRWG Engineered Performance SECTION 6 TYPE CERTIFICATE Following is a copy of 1 FAA Supplemental Type Certificate Number SH7767SW 2 EASA Supplemental Type Certificate 10052951 Page 25 ee KAMAN States Of America Wepartment of Transportation Afiation Administration Supplemental Type Mertificate Naber sunasw This Co
32. mpress KAflex Flex frames approximately 2 by tightening the workaid nuts c Install KAflex Driveshaft in the aircraft with serial number facing aft d Loosen workaid nuts and allow KAflex Driveshaft to extend aligning pilots on KAflex Driveshaft to Quill Adapter and Freewheeling Adapter Remove workaid e Install four bolts Figure 4 Item 3 at the forward portion of the KAflex Driveshaft ensuring bolt heads face aft Do not put washers under bolt heads f Install eight washers Figure 4 Item 2 and four nuts Figure 4 Item 1 on the four bolts Do not put washers under bolt heads g Install four bolts figure 4 9 at the aft portion of the KAflex Driveshaft ensuring bolt heads face forward Do not put washers under bolt heads h Install eight washers Figure 4 Item 10 and four nuts Figure 4 Item 11 on the four bolts Do not put washers under bolt heads Note If a riveted TRDS is installed in the aircraft an inertia kit SKCP3244 is required with this KAflex Driveshaft see Section 1 Page 4 In that case use the hardware bolts nuts washers supplied with the inertia kit for the aft portion of the driveshaft Install the inertia kit as shown on the drawing SKCP3244 enclosed in Section 7 i Torque four nuts Figure 4 Item 11 in accordance with OEM installation instructions ensuring pilot is engaged and KAflex Driveshaft end fitting flanges are flat against the freewheeling adapter Apply torqu
33. om locations A Zink connecting the Kaflex driveshaft to the helicopter G Added more caution and warning notes to emphasize daily 100 I Pareki hours and 1500 hour inspection and record in historical data card F J K Page 2 KAMATICSRWG Engineered Performance LOG OF REVISIONS TO KAMATICS CORPORATION SERVICE INSTRUCTION NUMBER 2348 Affected Pages DER Approval w Letter Date Sections Approval ee lab 7 eur AS NITE WIRE naa EIN ela os urpi eee Ree some a 2 E 071620131 57 254 wmms ww EN K f ss ss Note Only Sections 1 and 5 require DER approval Page 3 RW KAMAN KAMATICS CORPORATION SERVICE INSTRUCTIONS Subject KAflex Main Driveshaft Retrofit in accordance with Supplemental Type Certification Number SH7767SW Installation Notes If riveted Tail Rotor Drive Shaft TRDS Bell part number 206 040 383 101 206 040 383 105 206 040 38 103 206 040 38 105 206 040 387 107 is installed on aircraft Kamatics inertia P N 3244 is needed to complete the KAflex installation rotor brake assembly Bell part number 206 706 034 3 206 706 034 7 206 706 034 101 206 706 034 103 206 706 034 105 is installed the aircraft
34. on Note The following inspections detail special inspection instructions applicable to KAflex Driveshaft Refer to appropriate Bell and Allison maintenance manuals for airframe and engine special inspection instructions 1 Overtorque a 110 120 overtorque perform a daily inspection on KAflex Driveshaft b 120 overtorque perform 100 hour inspection on KAflex Driveshaft 2 Overspeed a 114 overspeed no KAflex Driveshaft inspection necessary 3 Sudden Stoppage a Perform a 100 hour inspection on the KAflex Driveshaft Inspect freewheeling clutch assembly for evidence of overtorque If clutch sprags are chipped or broken if there is evidence of static brinelling of clutch races or other evidence of torsional overload return driveshaft to Kamatics Corporation with information described in the Section on 6 000 hour inspection 4 Hard Landing a lf any of the following components do not pass their respective inspection criteria as detailed in chapter 5 Inspections of the Bell 206A B Maintenance Manual the KAflex Driveshaft must be returned to Kamatics as described in the Section of this manual on inspection after 6 000 hours i Main Rotor Hub Main Rotor Mast ii Main Transmission Main Transmission Mounts Drag Pin Drag Plate iv Freewheeling Clutch Assembly v Engine or Engine Mounts b Even if none of the items in Item a above show the effects of the hard landing perform a 100 hour inspection on
35. rdsfecate Kemetics Corporation 1330 Blue Hill Avenue Bloomfield Connecticut 06002 that like change in the type design for the following product with the and conditions therefor as hereon meets the reputrements of Fert 6 of ihe Civil Air Type Namter Bell 206A 2064 1 2068 2068 1 Doserijulion Design Change Installation of a Kamatics Kaflex Drive Sh Shaft Assembly in accordance with Kamatics Corporation Dwg SKCP 2782 Revision A dated March 30 1990 or iater FAA approved revision For Bell aircraft incorporating the tai rotor drive shafts identified below Kamatics Kaflex Incrtia Kit Dwg SKCP 3244 original dated May 5 2001 or later FAA approved revisions must installed and Condations 1 Bell 206 aircraft with Tail Rotor Drive Shaft Part Numbers 206 040 383 101 206 040 383 105 206 040 387 103 206 040 387 105 and 206 040 387 107 must have the Kamatics Kaflex Inertia Kit Dwg SACP 3244 installed 2 Compatibility of this modification with previously instalied equipment must be determined by the installer The STC holder will provide cach person it permits to use this certificate to alter the product written evidence of the agrecment in a ard to the Administrator pr aretha 5 Pet alpina reader of the Federal Avdmnan siratior
36. rill firewall cover using a 3 32 or 093 drill Dimple upper rivet hole for rivet Figure 2 Item 11 to clear dimple on door Rivet in this location must be flush to allow driveshaft door Figure 2 Item 9 to fit flush on firewall Figure 2 Item 10 Install firewall cover Figure 2 Item 6 on driveshaft door Figure 2 Item 9 and secure with two screws Figure 2 Item 8 Cut six MS20613 3C 3 32 Univ Head CRES rivets Figure 2 12 to length install and rivet firewall cover Figure 2 Item 6 to driveshaft door Figure 2 Item 9 Do not install these rivets in top dimpled rivet hole Cut one 520427 3 3 32 flush Monel rivet Figure 2 Item 11 to length install in dimpled hole and rivet firewall cover Figure 2 6 to driveshaft door Figure 2 Item 9 Page 8 KAMATICSRWG Engineered Performance KAMAN 4 Modification to Lord Barry Transmission Isolation Mount P N 206 030 539 101 or 005 Note Modification is necessary only with the Lord Barry Transmission Isolation Mount BHTI P N 206 030 539 101 or 005 the mount with aluminum cover plates The Lord Transmission Isolation Mount P N 206 030 539 003 with black elastometric cover has additional clearance and modification is not necessary Since Barry has merged with Lord the transmission isolation mounts with aluminum covers may have Lord name plate on them Older mounts may still have Barry name plate on them a R
37. s 2 The KAflex Driveshaft is not field overhauled The KAflex Driveshaft can only be disassembled for inspection at Kamatics Corporation 3 The KAflex Driveshaft is to be removed at 6 000 hours and sent to Kamatics Corporation for complete factory overhaul and inspection as required Page 22 KAMATICSRWG Engineered Performance f r k __ INIM k M UM n N N tm DAMAGE LOCATION SYMBOLS Type of Damage Maximum Damage and Repair Depth MECHANICAL 0 001 before 0 005 before 0 005 before 0 015 before and after repair and after repair and after repair and after repair CORROSION 0 005 before 0 005 before 0 010 before ourface no pits and after repair and after repair and after repair MAXIMUM AREA PER FULL 0 05 in 0 10 in 0 25 in 0 25 in DEPTH REPAIR NUMBER OF EDGE DENTS NICKS 0 001 in 0 010 in 0 010 in 0 025 in FIGURE 5 Damage Limits KAflex Driveshaft Page 23 KAMATICSRWG Engineered Performance NOTES a iw xe x 7 Sides and corners of flex frames to be treated as No cracks are permitted Repairs must be no less than 1 000 inch apart Repairs not to be within 0 500 inches of bolt hole Faying surfaces must be free of any raised metal areas All repairs to be smooth at maximum depth and smoothly blended with surrounding surface Exposed bare metal may be touched up with Sermetel Product 1122 or 196 available fro
38. ts Evidence of turning fasteners by wrench or other means is cause for rejection Page 18 KAMATICSRWG KAMAN Engineered Performance LS OUT OF AIRCRAFT INSPECTION continued c Inspect KAflex Driveshaft for damage and corrosion Refer to Figure 5 for damage and repair limits d Inspect KAflex Driveshaft flex frame joints for fretting dust This will show up as red metallic residue If grease oil or dirt is covering a suspected area or any doubt exists as to whether actual fretting has occurred clean suspected areas thoroughly and recheck If fretting is apparent return driveshaft to Kamatics Corporation Include description of reason for return and copy of historical record card with the driveshaft e Inspect KAflex Driveshaft for sign of contact rubbing and or chafing f Enter the 1500 hour inspection record in the historical data card enclosed with this service manual 6 000 HOUR INSPECTION Hemove KAflex Driveshaft for factory inspection Return to Kamatics Corporation Include description of reason for return and copy of historical log with driveshaft WARNING Package driveshaft carefully to ensure safe arrival at Kamatics Corporation Assuming driveshaft is returned to the user for further service inspections between 6 000 and 12 000 hours or multiples thereof will be the same as between new and 6 000 hours Page 19 KAMATICSRWG Engineered Performance 2 KAflex Driveshaft Conditional Inspecti
39. upling to freewheeling adapter flange CAUTION Compress couplings with Kamatics installation tool Figure 3 just enough to release them from mating adapter flange If couplings are compressed beyond 0 370 damage to coupling may occur e Push aft on forward coupling to compress flex frames in couplings and obtain clearance between forward driveshaft coupling and input adapter flange Move forward end of driveshaft outboard to clear input adapter flange Move driveshaft assembly aft passing forward coupling through opening and remove from helicopter 3 Firewall Driveshaft Door Rework Figures 1 and 2 a Gain access to driveshaft door Figure 2 Item 9 b Remove both halves of cone assembly Figure 1 Item 18 c Remove driveshaft cover assembly Figure 1 Items 8 Page 5 KAMATICSRWG Engineered Performance 61 001 0 902 N d 9 0 hs 8 1 wey 4 yeuse pg Bt Meus 8 PUEMIOS St 90 106 c90 00 mag bh 1900 5 50715 Bupunopy 9xeg 193689 wog k Page 6 z 7 9 g JEsJeAjur se o
40. vere turbulence iv Low rotor RPM during flight v Application of extreme and rapid cyclic control input vi Main Driveshaft Coupling has contacted the Isolation Mount b Examine Isolation Mount for damage caused by contact from Main Driveshaft c the Isolation Mount is damaged follow Repair Instructions in Section 5 Repair of KAflex Driveshaft Note 8 Page 21 KAMATICSRWG Engineered Performance SECTION 4 MAINTENANCE OF KAflex DRIVESHAFT 1 There is no periodic maintenance requirement for the KAflex Driveshaft 2 The following maintenance practices will be incorporated as follows a The KAflex Driveshaft is not field overhauled The KAflex Driveshaft can only be disassembled for inspections at Kamatics Corporation b Any time the KAflex Driveshaft is transferred from one aircraft to another the KAflex Driveshaft does not require a complete disassembly and inspection The KAflex Driveshaft does require a 100 hour inspection at this time and then at each aircraft 100 hour inspection c The KAflex Driveshaft is to be removed at 6 000 hours and sent to Kamatics Corporation for complete factory inspection and overhaul as required The KAflex Driveshaft is not field overhauled Refer to the Section on 6 000 hour inspection for return instructions SECTION 5 REPAIR OF KAflex DRIVESHAFT 1 Refer to Figure 5 for repair criteria All blends shall be smooth at maximum depth and smoothly blended with surrounding surface

Service Instruction Number SIN2348 Revision K

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