# l: DAHER-SOCATA

SOCATA Direction des Services 65921 TARBES CEDEX 9 FRANCE 

# SERVICE BULLETIN 

# I TELEPHONE: 33 (0)5 62.41.73 .00 TELEFAX: 33 (0)5 62.41.76 .54 

## TBM AIRCRAFT 

# SB 70-130 32 REVISION 3 ATA No . 

## MANDATORY The technical content of this document is approved under the authority of DOA No . EASA.21J.013 is t he subject of an AD SUBJECT 

# I EFFECTIVITY "MAIN LAND ING GEAR I NSPECTION" TBM 700/850 ai rcraft S/N 1 to 638, 687 which main landing gear body P/Ns are different from D68161 or D68161-1 (l.H.Ianding gear) and D68 162 o r D68162-1 (R.H .I anding gear) . PURPOSE A. PROBLEM Cracks have been evidenced on main forging bodies during an overhaul. B. ROOT CAUSE Fatigue. C . SOLUTION I nspections and replacement, if necessary. PURPOSE OF REVISION 1

- Closing of validity range

- Addition of Pa ragraph A . to check landing gear body P/N

- SB application form deleted

- Note deleted at Compl iance Paragraph

- Logo modification PURPOSE OF REVIS I ON 2

- Increase of inspection interval from 175 landings to 240 landings 

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PURPOSE OF R EVISION 3 :

- Modification of effectivity

- Addition of Terminating Solution paragraph S UMMARY 

### A. CHECK OF LANDING GEAR BODY P/N B. PREPARATION C. CHECK D. RECONDITI ONING 

# I E. TERMINATING SOLUTION JAN06 Rev. 3- DEC 14 Page 1 

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## TBM AIRCRAFT 

# SERVICE BULLETIN 

# I I SB 70-130 32 REVISION 3 A T A No.

APPLICATION : 

## MANDATORY The technical content of this document is approved under the authority of DOA No. EASA.21J . 013 is the subject of an AD For landing gear with forging body totalizing more than 1750 landings since new :

- Perform an inspection of forging body within 100 landings once this Service Bulletin is issued, then r epeat this inspection without exceeding 240 landings. For land i ng gear with landing forging body total izing more than 3500 landings sj nce new :

- Perform an inspection of forging body within 25 landings once this Service Bulletin is issued, then repeat this inspection without exceeding 240 landings. For additional assistance, please go online at www.socata.com PROCURABLE MATERIAL :

- Parts to be ordered from your TBM spare parts distributor. Item Part number Description Qty /aircraft 4 ZOO.N7323265025 Cotter pin E27487 -25-22CAT 2 CONSUMABLE MATERIAL or OTHER PRODUCTS (Local purchase) :

TOOLS

MANPOWER - Alodine 1200 (MIL- C-5541 Class 1/A or MIL-C-81 706) Primer ISOMAP P23 (BMS 1 079) or equivalent

- Finish paint AEROMAP 1000 (MIL - C-83289)

- Protective varnish : Green isolating varnish Ref. 131 88 DUROUX Blue isolating varnish Ref. 7D 1586 + hardener Ref. 7D 1586 ASTRAL-PYROLAC Isolati ng varnish Ref. 43022 AKZO NOBEL + blue colorant Ref. 557506 VIRACOLOR or any other equivalent locally approved product.

- Standard aeronautical maintenance station tools

- Eddy cu rrent measurement bench

- Tools necessary for dye penetrant inspection or fluorescent pe netrant inspection

- 1 aeronautical mechanic

- 1 Eddy current certified operator for crack detection, or 1 certified operator for dye penetrant inspection or fluorescent penetrant inspection TECHNICAL INCIDENCES :

- None

JANOS Page 2/6 Rev. 3 - DEC 14

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# I TBM AIRCRAFT 

# I SERVI CE BULLETIN SB 70-130 32 REVISION 3 ATA No . 

## MANDATORY The techn ical content of th is document is approved under the authority of DOA No. EASA.21 J.013 is the subject of an AD DESCRIPTION OF ACCOMPLISHMENT INSTRUCTIONS :

JAN06 Rev. 

### 3- DEC 14 NOTE: Operations required in this Service Bulletin mustbe accomplished bypersons authorizedby t heirAirworthi ness Authorities and accord i ng to the procedure descr i bed hereafter. A . CHECK OF LANDING GEAR BODY P / N - see Rgure 1 1) On embossment (7), note mai n land i ng gear body P / N. a) If P / N is D68161 or D68161 - 1 for L.H.Ianding gear and D68162 or D68162 - 1 for R.H. landing gear, this SB is not applicabl e to the aircraft. b) If P / N is different, apply paragraphs B. thru D. on ai rcraft i nvolved landing gear (s) . B. PREPARATI ON - see Figure 1 1) Put the aircraft on j acks - refer to Chapter 07-10-00 of the Maintenance Manual. 2) Connect the ground power unit - re fer to Chapter 24-40-00 of the Maintenance Manual. 3) Disconnect L.H. and R.H. s ide door links - refer to Chapter 52-80 - 01 of the Maintenance Manual. 

### WARNING PRIOR TO ANY LAND I NG GEAR OPERATION, MAKE S UR E THE LANDING GEAR AREA IS CLEAR. 4) Retract landing gear . 5) With a second operator, at mid-travel , open " LOG GW circuit breaker. 6) Set "SOURCE" selector to " OFF". 7

) Install the warn ing s ign prohibiting " SOURCE" selector operation 

## WARN I NG DO NOT OPERATE MAINTE NANCE WORK IN PROGRESS 8) Remove tie-wraps securing electrical harness an d bonding strap (1) . 9) Remove and discard cotter p in (4). 1 0) Without removing it , unscrew nut (3) in order to disengage attaching lug 

### (2} of the bonding strap during crack detectio n. 11 ) Perform steps 8) thru 10 ) on the other landing gear. 

### C. CHECK - see Figure 1 NOTE: Crack detection can either be performed by Eddy current or bydye penetrantinspection or by fluorescent penetrant inspection. Page 3 / 6

# I TBM AIRCRAFT 

# SERVICE BULLETIN 

# I SB 70-130 32 REVISION 3 ATA No .



### JAN 06 Rev. 3- DEC 14 

# MANDATORY The technical content of this document is approved under the authority of DOA No. EASA.21J.013 is the subject of an AD Detection by Eddy current 1) On a flat area, close tothe described area (6) of Figure 1, calibrate the measurement ben ch. 2) As pe r the described area (6) of Figure 1, for about 1.96 in (5 em) in length, perform the c rack detection on the landing gear leg by Eddy current with special emphasis on th e bending radius (5) as per the described area (6) of Figure 1. Dye penetrant inspection or fluorescent penetrant inspection 1) Perform a chemical etching of the area as per the described area (6) of Figure 1. 2) As per the described area (6) of Figure 1, for about 1.96 in (5 em) in length , perform the crack detection on the landing gear leg by dye penetrant inspection or fluorescent penetrant inspection with special emphasis on the bending radius (5) as per the described area (6) of Figure 1 - refer to Chapter 20-50-01 of the Maintenance Manual. 

## All 3) If no crack is detected : a) Protect bare metal with Alodine 1200 and a coat of primer paint, as required. b) Perform paint touch - up, as required. NOTE: 

### As an alternative process to protect bare metal, protective varnish as listed in

· coNSUMABLE MATERIAL: paragraph or any equivalent locally approved product may 

### be used to facilitate further repetitive dye penetrant inspections or dye fluorescent inspections. 

### c) Torque nut (3) - refer to Chapter 32-10-01 of the Maintenance Manual. d) Install a new cotter pin (4), P/N ZOO.N7323265025. e) Install tie-wraps securing electrical harness and bonding strap (1). 

### f) Connect L.H . and R.H. side door links - refer to Ch apter 52-80-01 of the Maintenance Manual. g) Recondition the aircraft - refer to Paragraph 

### D. 4) In case a crack is suspected : a) Remove the concerned landing gear leg - refer to Chapter 32-10-01 of the Maintenance Manual. b) Confi rm the presence of the crack with dye penetrant inspection or fluorescent penetrant inspection - refer to Chapter 20-50-01 ofthe Maintenance Manual.

Page 4 

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# I I TBM AIRCRAFT 

# SERVICE BULLETIN 

# I 

# I SB 70-130 32 REVISION 3 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 5) If no crack is found : a) Protect bare metal with Alodine 1200 and a coat of primer paint. b) Perform paint touch - up. NOTE: 

### As an alternative process to protect bare metal, protective varnish as listed in "CONSUMABLE MATERIAe 

### paragraph or any equivalent locally approved product may be used to facilitate further repetitive dye penetrant inspections or dye fluorescent inspections. c) Recondition controlled area in its orig inal condition. d) Install landing gear leg - referto Chapter 32-10-01 ofthe Maintenance Manual. e) Recondition the aircraft - see Paragraph D. 6) If the crack is confirmed, contact DAHER-SOCATA to coordinate the landing gear repair and then imperatively conform to any instruction stated by DAHER - SOCATA. D. RECONDITI ONING - see Figure 1 1 ) Remove the warn ing sign prohibiting " SOURCE" selector operation. 

### WARNING PRIOR TO ANY LANDING GEAR OPERATION, MAKE SURE THE LANDING GEAR AREA IS CLEAR. 2) Close "LOG GR" landing gear breaker. 3) Perform a complete extension/ retraction cycle. 4) Set "SOURCE" selector to "OFF" . 5) Lower the aircraft to ground and remove the jacks - refer to Chapter 07- 1 0-00 of the Maintenance Manual. 6) Make sure all the tools and materials are removed and the work area is clean and free f rom debris. E. TERM I NATING SOLUTION Installa t ion of a L.H. reinforced body D68161 or D68161 -1 and of an R.H. reinforced body D68162 or D68162-1 in compliance with instructions provided in Component Maintenance Manuals 32-11-01 and 32 - 11-02. UPDATING OF THE AIRCRAFT DOCUMENTATION : Upon completion of Service Bulletin No. SB 70 - 130-32 , Revis ion 3 "MAIN LANDING GEAR INSPECTION " , make an appropriate maintenance record entry. WARNING DAHER-SOCATA considers that it is MANDATORY for operators to comply with the instructions of th is SB.

JAN06 Rev. 3- DEC 14 Operators who arbitrarily ignore the compliance statement indicated in this SB do so at their own risk. Page 5 / 6

# I SERVICE BULLETIN 

# I TBM AI RCRAFT
R EV I S ION 3 ATA No . 

# SB 70-130 32 MANDATORY

JAN06 Rev. 3- DEC 14 The technical content of this document is approved under the authority of DOA No. EASA .21J . 013

6 

### Figure 1 - Inspection of main land ing gears is the subjec t of an AD 1 - Bonding strap 2 - Attaching lug 3- Nut 4 - Cotter pin 5 - Bending radius 6 - Area to be inspected 7 - Embossment



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