Daher MSB 70-130: Revision 3, text

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A DAHER-SOCATA SOCATA Direction des Services TELEPHONE: 33 (0)5 62.41.73.00 65921 TARBES CEDEX 9 TELEFAX: 33 (0)5 62.41.76.54 FRANCE

TBM AIRCRAFT SERVICE BULLETIN SB 70-130 REVISION 3 32 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 SUBJECT: "MAIN LANDING GEAR INSPECTION"

• EFFECTIVITY: TBM 700/850 aircraft S/N 1 to 638, 687 which main landing gear body P/Ns are different from D68161 or D68161-1 (L.H. landing gear) and D68162 or D68162-1 (R.H. landing gear).

PURPOSE A. PROBLEM Cracks have been evidenced on main forging bodies during an overhaul.

B. ROOT CAUSE Fatigue.

C. SOLUTION Inspections and replacement, if necessary.

PURPOSE OF REVISION 1 :

- Closing of validity range

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

- SB application form deleted

- Note deleted at Compliance Paragraph

- Logo modification PURPOSE OF REVISION 2 :

- Increase of inspection interval from 175 landings to 240 landings PURPOSE OF REVISION 3 :

- Modification of effectivity

- Addition of Terminating Solution paragraph

SUMMARY A. CHECK OF LANDING GEAR BODY P/N B. PREPARATION C. CHECK D. RECONDITIONING E. TERMINATING SOLUTION JAN 06 Page 1 / 6 Rev. 3 - DEC 14

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TBM AIRCRAFT SERVICE BULLETIN SB 70- 130 REVISION 3 32 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 APPLICATION:

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 repeat this inspection without exceeding 240 landings.

For landing gear with landing forging body totalizing 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 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 Z0O.N7323265025 Cotter pin E27487-25-22CAT 2 CONSUMABLE MATERIAL or OTHER PRODUCTS (Local purchase) :

- Alodine 1200 (MIL-C-5541 Class I/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. 7D 1586 + hardener Ref. 7D 1586 ASTRAL-PYROLAC

• Isolating varnish Ref. 43022 AKZO NOBEL + blue colorant Ref. 557506 VIRACOLOR

• or any other equivalent locally approved product.

TOOLS

- Standard aeronautical maintenance station tools

- Eddy current measurement bench

- Tools necessary for dye penetrant inspection or fluorescent penetrant inspection MANPOWER :

- 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 JAN 06 Page 2 / 6 Rev. 3 - DEC 14

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TBM AIRCRAFT SERVICE BULLETIN SB 70-130 REVISION 3 32 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 DESCRIPTION OF ACCOMPLISHMENT INSTRUCTIONS:

NOTE :

Operations required in this Service Bulletin must be accomplished by persons authorized by their Airworthiness Authorities and according to the procedure described hereafter.

A. CHECK OF LANDING GEAR BODY P/N - see Figure 1

1) On embossment (7), note main landing gear body P/N.

a) If P/N is D68161 or D68161-1 for L.H. landing gear and D68162 or D68162-1 for R.H. landing gear, this SB is not applicable to the aircraft.

b) If P/N is different, apply paragraphs B. thru D. on aircraft involved landing gear (S).

B. PREPARATION - see Figure 1

1) Put the aircraft on jacks - refer to Chapter 07-10-00 of the Maintenance Manual.

2) Connect the ground power unit - refer to Chapter 24-40-00 of the Maintenance Manual.

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.

With a second operator, at mid-travel, open "LDG GR" circuit breaker.

6) Set "SOURCE" selector to "OFF".

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.

C. CHECK - see Figure 1 NOTE :

Crack detection can either be performed by Eddy current or by dye penetrant inspection or by fluorescent penetrant inspection.

JAN 06 Page 3 / 6 Rev. 3 - DEC 14

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TBM AIRCRAFT SERVICE BULLETIN SB 70-130 REVISION 3 32 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 Detection by Eddy current

1) On a flat area, close to the described area (6) of Figure 1, calibrate the measurement bench.

2) As per the described area (6) of Figure 1, for about 1.96 in (5 cm) in length, perform the crack detection on the landing gear leg by Eddy current with special emphasis on the 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 cm) in length, perform the crack detection on the landing gear leg by dye penetrant inspection or 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 protect a sed do ine product may be used to facilitate further repetitive dye penetrant inspections or

c) Torque nut (3) - refer to Chapter 32-10-01 of the Maintenance Manual.

d) Install a new cotter pin (4), P/N Z00.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 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) Confirm the presence of the crack with dye penetrant inspection or fluorescent penetrant inspection - refer to Chapter 20-50-01 ofthe Maintenance Manual.

JAN 06 Page 4 / 6 Rev. 3 - DEC 14

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TBM AIRCRAFT SERVICE BULLETIN SB 70-130 REVISION 3 32 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 MATERIAL" 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 original condition.

d) Install landing gear leg - refer to Chapter 32-10-01 of the 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. 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 "LDG 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 07-10-00 of the Maintenance Manual.

6) Make sure all the tools and materials are removed and the work area is clean and free from debris.

E. TERMINATING SOLUTION Installation 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, Revision 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 this SB.

Operators who arbitrarily ignore the compliance statement indicated in this SB do so at their own risk.

JAN 06 Page 5 / 6 Rev. 3 - DEC 14

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TBM AIRCRAFT SERVICE BULLETIN SB 70 - 130 REVISION 3 ATA No. 32

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 - Bonding strap 2 - Attaching lug 3 - Nut 4 - Cotter pin 5 - Bending radius 6 - Area to be inspected 7 - Embossment Figure 1 - Inspection of main landing gears JAN 06 Page 6 / 6 Rev. 3 - DEC 14