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Page 1 / 9OCT 94 Rev. 3 --- DEC 17 SUBJECT : WING FRONT ATTACHMENTS REFERENCE : REPAIR SHEET No. 20---084 EFFECTIVITY : TB 9, TB 10 and TB 200 aircraft PURPOSE : To ensure integrity of the wing front attachments on wing and fuselage sides by a crack detection inspection.
PURPOSE OF THE REVISION 1 :
Consideration of customers who, before the issue of this Service Bulletin, had already applied kit OPT10908100 concerning side fuselage reinforcement.
PURPOSE OF THE REVISION 2 :
--- Modification of Effectivity.
--- Modification of Application.
--- Integration of the new repair solution of front attachment on wing side.
--- Removal of Figure 1 “Wing front attachment (wing side) --- Inspection / check”.
--- Addition of Figure 2 “Front spar --- Crack permissible criteria”.
--- Removal of SB Supplement pages.
PURPOSE OF THE REVISION 3 :
--- ToreplaceKitOPT10911001withKitOPT10911002(concerningwingfrontattachment).
--- To authorize Eddy current testing as a variant of dye penetrant inspection.
--- To modify application after Kit OPT109110XX installation (see Figure 2).
DESCRIPTION: Pickling,crackdetectionbydyepenetrantinspectionorEddycurrenttesting,possiblerepair and painting of the wing front attachments on fuselage and wing sides.
SERVICE BULLETIN
TB AIRCRAFT
MANDATORY The technical content of this document is approved u nder the authority of DOA No. EASA.21J.013 is the subject of an AD SB 10--081 REVISION 3 57 ATA No.
SOCATA D irection des Services TELEPHONE : 33 (0)5 62.41.73.00 65921 TARBES CEDEX 9 TELEFAX : 33 (0)5 62.41.76.54 FRANCE
SERVICE BULLETIN
TB AIRCRAFT
MANDATORY The technical content of this document is approved u nder the authority of DOA No. EASA.21J.013 is the subject of an AD SB 10--081 REVISION 3 57 ATA No.
Page 2 / 9O CT 94 Rev. 3 --- DEC 17 APPLICATION: Every 3000 landings or 2000 flight hours (whichever occurs first).
A. FRONT ATTACHMENT ON WING SIDE (Perform the operations in accordance with flowcharts hereunder) before KITOPT109110XXinstallation --- see Figure 1 after KITOPT109110XXinstallation --- see Figure 2 Figure 1 --- Before Kit OPT109110XX installation INSTALL KIT OPT10911002 YESNO
IS AIRCRAFT MORE THAN 12000 LANDINGS OR 8000 FLIGHT HOURS (*) ?
YESNO (*)WHICHEVER OCCURS FIRST (**)PENETRANT INSPECTION OR EDDY CURRENT TESTING
IS ANY CRACK
DETECTED ?
CRACK DETECTION (**)EVERY 3000 LANDINGS OR 2000 FLIGHT HOURS (*)
SERVICE BULLETIN
TB AIRCRAFT
MANDATORY The technical content of this document is approved u nder the authority of DOA No. EASA.21J.013 is the subject of an AD SB 10--081 REVISION 3 57 ATA No.
Page 3 / 9O CT 94 Rev. 3 --- DEC 17 Figure 2 --- After Kit OPT109110XX installation (*)WHICHEVER OCCURS FIRST ( **)PENETRANT INSPECTION OR EDDY CURRENT TESTING KIT OPT109110XX INSTALLED
SCHEDULED
INSPECTION
SOLUTION ?
YES KIT REPLACEMENT AT 6000 LANDINGS OR 4000 FLIGHT HOURS (*)BY OPT10911002 1stCRACK DETECTION AT 6000 LANDINGS OR 4000 FLIGHT HOURS (*) NO CRACK
DETECTED ?
YES NOREPLACE KITBY KIT OPT10911002 INSPECT (**)EVERY 3000 LANDINGS OR 2000 FLIGHT HOURS (*) CRACK
DETECTED ?
YES NO
SERVICE BULLETIN
TB AIRCRAFT
MANDATORY The technical content of this document is approved u nder the authority of DOA No. EASA.21J.013 is the subject of an AD SB 10--081 REVISION 3 57 ATA No.
Page 4 / 9O CT 94 Rev. 3 --- DEC 17 B. FRONT ATTACHMENT ON FUSELAGE SIDE NOTE:
OnlyTB9S/N1to9999andTB10S/N1to803,805,806,809to815,820to822aircraft areconcernedbyfrontattachmentonfuselagesidecrackdetection.
1) Perform a crack detection on fuselage side front attachment by dye penetrant inspection --- refer to 20---00---14 of the Maintenance Manual --- or Eddy current testing.
2) Aircraft S/N 1 to 399, 413, SL 10-14/1 notapplied, kit OPT908100 notapplied (Attachments in 25CD4S)
a) When there is no crack :
--- Installation of kit OPT10919800 in accordance with Technical Instruction OPT10---9198---53 Revision 2 or any later at the latest at 6000 landings or 4000 flight hours (whichever occurs first).
--- NewinstallationofkitOPT10919800inaccordancewithTechnicalInstruction OPT10---9198---53 Revision 2 or any later at the latest at 12000 landings or 8000flighthoursafterthelastapplicationofthekit(whicheveroccursfirst).
b) When cracks have been detected during the inspection :
--- Installation of kit OPT10919800 in accordance with Technical Instruction OPT10---9198---53 Revision 2 or any later.
--- NewinstallationofkitOPT10919800inaccordancewithTechnicalInstruction OPT10---9198---53 Revision 2 or any later at the latest at 12000 landings or 8000flighthoursafterthelastapplicationofthekit(whicheveroccursfirst).
3) Aircraft S/N 1 to 399, 413, SL 10-14/1 applied, kit OPT10908100 installed (Attachments in 15CDV6)
a) When there is no crack :
--- Installation of kit OPT10919800 in accordance with Technical Instruction OPT10---9198---53 Revision 2 or any later at the latest at 12000 landings or 8000flighthoursafterthelastapplicationofthekit(whicheveroccursfirst).
b) When cracks have been detected during the inspection :
--- Installation of kit OPT10919800 in accordance with Technical Instruction OPT10---9198---53 Revision 2 or any later.
--- NewinstallationofkitOPT10919800inaccordancewithTechnicalInstruction OPT10---9198---53 Revision 2 or any later at the latest at 12000 landings or 8000flighthoursafterthelastapplicationofthekit(whicheveroccursfirst).
4) TB 9 aircraft S/N 400 to 412, 414 to 9999 (Attachments in 15CDV6) TB 10 aircraft S/N 400 to 412, 414 to 803, 805, 806, 809 to 815, 820 to 822 (Attachments in 15CDV6)
a) When there is no crack :
--- Installation of kit OPT10908100 in accordance with Technical Instruction OPT10---9081---53 Revision 3 or any later at the latest at 12000 landings or 8000 flight hours (whichever occurs first).
SERVICE BULLETIN
TB AIRCRAFT
MANDATORY The technical content of this document is approved u nder the authority of DOA No. EASA.21J.013 is the subject of an AD SB 10--081 REVISION 3 57 ATA No.
Page 5 / 9O CT 94 Rev. 3 --- DEC 17 --- New installation of the kit OPT10908100 in accordance with Technical Instruction OPT10---9081---53 Revision 3 or any later at the latest at 12000 landings or 8000 flight hours after the last application of the kit (whichever occurs first).
b) When cracks have been detected during the inspection :
--- Installation of kit OPT10908100 in accordance with Technical Instruction OPT10---9081---53 Revision 3 or any later.
--- New installation of the kit OPT10908100 in accordance with Technical Instruction OPT10---9081---53 Revision 3 or any later at the latest at 12000 landings or 8000 flight hours after the last application of the kit (whichever occurs first).
PROCURABLE MATERIAL:
--- Parts to be ordered to your TB spare parts distributor, Item Part number Description Qty/aircraft 2 5402453300 Locknut 12 / 5401458300 Locknut 12 / 5402454490 Locknut 2 and if necessary :
A. Aircraft S/N 1 to 9999 Kit OPT10911002 for the front attachment on wing side B. Aircraft S/N 1 to 399, 413 Kit OPT10919800 for front attachment on fuselage side C. TB 9 aircraft S/N 400 to 412, 414 to 9999 TB 10 aircraft S/N 400 to 412, 414 to 803, 805, 806, 809 to 815, 820 to 822 Kit OPT10908100 for front attachment on fuselage side CONSUMABLE MATERIAL or OTHER PRODUCTS(Local purchase) :
--- Paint remover --- Crack detector product (dye penetrant, developer) --- Primer --- Final painting (according to the aircraft range) --- Red paint --- Methyl---Ethyl---Ketone (MEK) TOOLS :
--- Standard aeronautical maintenance station tools --- Wing support --- Fuselage support
SERVICE BULLETIN
TB AIRCRAFT
MANDATORY The technical content of this document is approved u nder the authority of DOA No. EASA.21J.013 is the subject of an AD SB 10--081 REVISION 3 57 ATA No.
Page 6 / 9O CT 94 Rev. 3 --- DEC 17 MANPOWER :
--- 1 mechanic, skilled in crack dye penetrant detection method --- 3 manhours (inspection only) per aircraft --- Application of kit OPT10911002 : 8.50 manhours per aircraft --- Application of kit OPT10908100 : 16 manhours per aircraft --- Application of kit OPT10919800 : 16 manhours per aircraft --- 1 assistant (if application of one of the kits) DESCRIPTION OF ACCOMPLISHMENT INSTRUCTIONS:
NOTE:
The inspectionand thepossible installationofkit(s)OPT10911002 and/orOPT10908100 and/orOPT10919800mustbeaccomplishedinacertifiedaeronauticalmaintenancestation accordingtotheproceduredescribedhereafter.
A. PREPARATION
1) Remove the cowling under hull Nr 218.
2) Remove the L.H. junction fairing Nr 217L and the R.H. junction fairing Nr 217R.
3) Install supports under the R.H. and the L.H. wings and under the fuselage.
4) Remove the front seats --- refer to Chapter 25---11---00 of the Maintenance Manual.
5) Remove the side upholsterings at the frame Nr 1.
6) Remove the circuit---breaker panel.
B. PROCEDURE --- see Figures 3 and 4 NOTE:
TheproceduredescribedhereafteristhesameforL.H.andR.H.wingfrontattachments.
NOTE:
OnlyTB9S/N1to9999andTB10S/N1to803,805,806,809to815,820to822aircraft areconcernedbyfrontattachmentonfuselagesidecrackdetection.
1) Remove wing front attachment --- refer to Chapter 57---20---03 of the Maintenance Manual.
2) Remove and retain screw (5) and washer (1). Discard the locknut (2).
3) Cleanandnakethewingfrontattachmentfittingsonwingandfuselagesides,aswell as small spar below front attachement on wing side. Degrease them.
4) Perform a crack detection by a dye penetrant inspection --- refer to Chapter 20---00---04 of the Maintenance Manual or Eddy current testing.
5) If one crack is detected :
a) On the small spar (Figure 4), apply the proposal for rework described in the Technical Instruction delivered with kit OPT10911002.
b) On the front attachment on fuselage side, apply the proposal for rework described in the Technical Instruction delivered with kit OPT10908100 or kit OPT10919800.
SERVICE BULLETIN
TB AIRCRAFT
MANDATORY The technical content of this document is approved u nder the authority of DOA No. EASA.21J.013 is the subject of an AD SB 10--081 REVISION 3 57 ATA No.
Page 7 / 9O CT 94 Rev. 3 --- DEC 17
c) InaccordancewithMaintenanceManual,onthefrontattachment,onwingside, replace the front attachment.
NOTE:
Ifseveralcracksaredetected,flightisnotauthorized,contactDAHER.
6) If no crack has been detected, proceed to the painting of the fittings --- refer to Chapter 20---00---03 of the Maintenance Manual.
7) Install screw (5), washer (1) and new locknut (2). Torque to 39 lbf.in (4.5 N.m).
8) Install wing front attachment --- refer to Chapter 57---20---03 of the Maintenance Manual.
9) Mark screw (5) and locknut (2) with a red paint line.
C. RECONDITIONING
1) Install the circuit---breaker panel.
2) Install the L.H. and R.H. upholsterings.
3) Install the front seats --- refer to Chapter 25---11---00 of the Maintenance Manual.
4) Install the L.H. junction fairing Nr 217L and the R.H. junction fairing Nr 217R.
5) Install the cowling under hull Nr 218.
6) Remove the wing and fuselage supports.
UPDATING OF THE AIRCRAFT DOCUMENTATION:
Record accomplishment of Service Bulletin Nr SB10---081---57 Revision 3 ”WING FRONT ATTACHMENTS”andthepossibleapplicationofkitsOPT10911002”Reinforcementofwing frontattachment”and/orOPT10908100and/orOPT10919800”Frame1reinforcement,wing attachmentarea”intheaircraftlogbook,Chapter”Aircraftmodificationsembodied”page X or XI.
CAUTION IF THE APPLICATION OF KIT OPT10911002 AND/OR KIT OPT10908100 AND/OR KIT OPT10919800 ONLY AFFECT(S) ONE SIDE OF THE WING, SPECIFY IT ON THE AIRCRAFT LOG BOOK.
WARNING : DAHER considers that it is MANDATORY for operators to comply with the instructions of this SB.
OperatorswhoarbitrarilyignorethecompliancestatementindicatedinthisSBdosoattheir own risk.
TB AIRCRAFT SERVICE BULLETIN SB 10-081 REVISION 3 57 ATA No.
MANDATORY The technical content of this document is approved under the authority of DOA No. EASA.21J.013 is the subject of an AD 1 - Washer 2 - Locknut 3 - Front seat strut 4 - Cabin floor 5 - Screw 6 - Wing front attachment 7 - Shim 0000 5 Revêtement extérieur Outside skin 4570001AAAKYZ4600 Figure 3 - Wing front attachment (fuselage side) - Inspection / check OCT 94 Page 8 / 9 Rev. 3 - DEC 17
TB AIRCRAFT SERVICE BULLETIN SB 10-081 REVISION 3 57 ATA No.
MANDATORY The technical content of this document is approved under the authority of DOA No. EASA.21J.013 is the subject of an AD 20 mm
0.79 in 14570001AAA I·724600 VOIR NOTA
SEE NOTE 10 mm MINI
0.39 in MIN NOTA : LONGUEUR MAXIMALE DE CRIQUE ADMISSIBLE : 20 mm NOTE: MAXIMUM CRACK LENGTH 0.79 in Figure 4 - Front spar - Crack permissible criteria OCT 94 Page 9 / 9 Rev. 3 - DEC 17