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 the subject of an AD 

SUBJECT I EFFECTIVITY 

"MAIN LANDING GEAR INSPECTION" 

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.Ianding gear) and D68162 or D68162-1 (R.H.Ianding 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 

I 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 

I E. TERMINATING SOLUTION 

JAN06 

Rev. 3- DEC 14 

Page 1 I 6 
TBM AIRCRAFT 

SERVICE BULLETIN I I SB 70-130 32 

REVISION 3 ATA 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 repeat this inspection without exceeding 240 landings. 

For landing gear with landing forging body totalizing more than 3500 landings sjnce 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-81706) 

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 

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 necessary for dye penetrant inspection or fluorescent penetrant 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 
I 

I 

TBM AIRCRAFT I SERVICE BULLETIN SB 70-130 32 

REVISION 3 ATA No. 

MANDATORY 

The technical content of this 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 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 Rgure 1 

1) On embossment (7), note main landing 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 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. 

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 GW 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). 

1 0) 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. 

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 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 em) 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 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 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. 

Page 4 I 6 
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 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 "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 07-10-00 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. 

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 AIRCRAFT 

REVISION 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 landing gears 

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 

® 

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