# EADS SOCATA EADSSOCATA Direction des Services 65921 TARBES CEDEX 9 FRANCE TELEPHONE : 33 (0)5 62.41.73.00 TELEFAX : 33 (0)5 62.41.76.54

TELEX : 532 835 F 

## TBM AIRCRAFT 

# I SERVICE BULLETIN 

# I SB 70-130

SUBJECT EFFECTIVITY REASON

SUMMARY

COMPLIANCE: MAIN LANDING GEAR INSPECTION TBM 700/850 aircraft S/N 1to 9999
A. PROBLEM 

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

Cracks have been evidenced on main forging bodies during an overhaul. B. ROOT CAUSE Fatigue. C. SOLUTION Inspections and replacement, if necessary. A. PREPARATION B. CHECK C. RECONDITIONING
For landing gear with forging bodytotalizing more than 1750 landings since new :

- Perform an inspection of forging body within 100 landings once this Service Bulletin is issued, then repeat this inspection without exceeding 175 landings. For landing gear with landing forging bodytotalizing more than 3500 landings since new :

- Perform an inspection of forging body within 25 landings once this Service Bulletin is issued, then repeat this inspection without exceeding 175 landings. NOTE: Before applying thispresent

### SB, go online at "www.socata.com"andfill the form in orderto help you determine the actualnumberoflandings on yourforging bodysince new. You will promptlyreceive areplywith the answertakingintoaccountanylandinggearexchange when applicable. 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
JAN 06 Page 1

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## TBM AIRCRAFT 

# I SERVICE BULLETIN 

# I SB 70-130 MANDATORY The technical content of this document is approved underthe authority of DOA No. EASA.21J.013 is the subject of an AD CONSUMABLE MATERIAL (Local purchase) :

TOOLING

MANPOWER - Alodine 1200 (MIL-C-5541 Class 1/A or MIL-C-81706)

- Primer ISOMAP P23 (BMS 1079) or equivalent

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

- Protective varnish : Green isolating varnish Ref. 1318B DUROUX Blue isolating varnish Ref. 70 1586 + hardener Ref. 70 1586ASTRAL-PYROLAC Isolating varnish Ref. 43022 AKZO NOBEL+ blue colorant Ref. 557506 VIRACOLOR or any other equivalent locally approved product.

- Standard aeronautical maintenance station tools

- Eddy current measurement bench

- Tools necessaryfor dye penetrant inspection orfluorescent penetrant inspection

- 1 aeronautical mechanic

- 1 Eddy current certified operatorfor crack detection, or 1 certified operatorfor dye penetrant inspection orfluorescent penetrant inspection TECHNICAL INCIDENCES :

- None ACCOMPLISHMENT INSTRUCTIONS :

JAN 06 NOTE: Operations requiredin this Service Bulletin mustbeaccomplishedbypersons authorizedby theirAirworthinessAuthorities andaccording to the procedure describedhereafter. A. PREPARATION
- see Figure 1 1) Connect the ground power unit - refer to Chapter 24-40-00 of the Maintenance Manual. 2) Put the aircraft on jacks - referto Chapter 07-10-00 ofthe Maintenance Manual. 3) Disconnect L.H. and R.H. side door links - refer to Chapter 52-80-01 of the Maintenance Manual. 

### WARNING PRIOR TO ANY LANDING GEAR OPERATION, MAKE SURE THE LANDING GEAR AREA IS CLEAR. 4) Retract landing gear. 5) With a second operator, at mid-travel, open "LOG GR" circuit breaker. 6) Set "SOURCE" selectorto "OFF". Page 2 

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# I TBM AIRCRAFT 

# SERVICE BULLETIN 

# I SB 70-130

JAN 06 

## MANDATORY The technical content of this document is approved underthe authority of DOA No. EASA.21J.013 is the subject of an AD 7) Install the warning sign prohibiting "SOURCE" selector operation 

## WARNING DO NOT OPERATE MAINTENANCE WORK IN PROGRESS 8) Remove tie-wraps securing electrical harness and bonding strap (1). 9) Remove and discard cotter pin (4). 10) Without removing it, unscrew nut (3) in order to disengage attaching lug (2) of the bonding strap during crack detection. 11) Perform steps 8) thru 10) on the other landing gear. B. CHECK
- see Figure 1 NOTE: Crackdetection can eitherbeperformedbyEddycurrentorbydyepenetrantinspection orbyfluorescentpenetrantinspection. Detection by Eddy current 1) On aflat area, closetothe described area (6) of Figure 1, calibratethe measurement bench. 2) As perthe 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 Eddy current with special emphasis on the bending radius (5) as perthe described area (6) of Figure 1. Dye penetrant inspection orfluorescent penetrant inspection 1) Perform a chemical etching of the area as perthe described area (6) of Figure 1. 2) As perthe 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 inspectionwith special emphasis onthe 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 productmaybe used to facilitate further repetitive dye penetrantinspections or dye fluorescentinspections. c) Torque nut (3)
- refer to Chapter 32-10-01 of the Maintenance Manual. Page 3 

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# I TBM AIRCRAFT 

# SERVICE BULLETIN 

# I SB 70-130

JAN 06 

## MANDATORY The technical content of this document is approved underthe authority of DOA No. EASA.21J.013 is the subject of an AD 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 Chapter 52-80-01 of the Maintenance Manual. g) Recondition the aircraft
- refer to Paragraph C. 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) Confirm the presence of the crack with dye penetrant inspection orfluorescent penetrant inspection- referto Chapter 20-50-01 ofthe Maintenance Manual. 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 MATERIAL' paragraph or any equivalent locally approved productmaybe used to facilitate further repetitive dye penetrantinspections or dye fluorescentinspections. c) Recondition controlled area in its original condition. d) Install landing gearleg -refertoChapter32-10-01 ofthe MaintenanceManual. e) Recondition the aircraft
- see Paragraph C. 6) Ifthecrack is confirmed, contact EADS SOCATAtocoordinatethe landing gearrepair and then imperatively conform to any instruction stated by EADS SOCATA. C. RECONDITIONING
- see Figure 1 1) Remove the warning 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" selectorto "OFF". 5) Lowerthe aircraftto ground and removethejacks - referto Chapter 07-10-00 ofthe Maintenance Manual. 6) Make sure all thetools and materials are removed and theworkarea is clean and free from debris. 7) After application of this SB, please return the enclosed form to SOCATA at the indicated address. Page 4 

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## TBM AIRCRAFT 

# I SERVICE BULLETIN 

# I SB 70-130 MANDATORY The technical content of this document is approved underthe authority of DOA No. EASA.21J.013 is the subject of an AD UPDATING OF THE AIRCRAFT DOCUMENTATION :
WARNING

JAN 06 Upon completion of Service Bulletin No. SB 70-130-32 MAIN LANDING GEAR INSPECTION , make an appropriate maintenance record entry. SOCATA considers that it is MANDATORY for operators to comply with the instructions of this SB. Operatorswho arbitrarily ignorethe compliancestatement indicated in this SB doso attheir own risk.

Page 5 

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# I SERVICE BULLETIN 

# I TBM AIRCRAFT 

# I 

# SB 70-130 

# I**~~.I** MANDATORY

4 3 6

JAN 06 5 The technical content of this document is approved underthe authority of DOA No. EASA.21J.013 

# j::-: is the subject of an AD 1 - Bonding strap 2 - Attaching lug 3- Nut 4 - Cotter pin 5 - Bending radius 6 - Area to be inspected



# /4 

# ®

# ~~

# 3~~=----**~········** 5 

# II

6 Figure 1 - Inspection of main landing gears Page 6 

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# EADS SOCATA FORM TO BE FILLED AFTER COMPLIANCE WITH SERVICE BULLETIN 

# I SERVICE BULLETIN 

# I TBM AIRCRAFT 

# SB 70-130 32

ATA No. 

## MAIN LANDING GEAR INSPECTION I, the undersigned, that service bulletin No. SB 70-130-32 has been complied with on aircraft.

1.

2.

3.

4.

5. Inspection by Eddy Current Inspection by dye penetrant inspection or byfluorescent penetrant inspection Replacement of R.H. main landing gear

# D Replacement of L.H. main landing gear Aircraft Type: Serial No.: Registered : Flight hours : Number of landings : Owner Name: Phone: Address: E-mail: User (if different from owner) Name: Address: E-mail: Service center Name: Address: E-mail: Approval No. : Remarks

DATE: SIGNED: To be returned to SOCATA at the following address : certify 

# D D D

EADS SOCATA Direction des Services 65921 TARBES CEDEX 9 FRANCE Fax: 33 (0)5 62 41 76 54 Telex : 532 835 F