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 1 to 9999 

A. PROBLEM 

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 

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 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 175 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 175 landings. 

NOTE: 

Before applying this present SB, go online at "www.socata.com" and fill the form in order to 

help you determine the actual number of landings on your forging body since new. You will 

promptly receive a reply with the answer taking into account any landing gear exchange 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 E27 487-25-22CAT 2 

JAN 06 Page 1 I 6 
TBM AIRCRAFT I SERVICE BULLETIN I SB 70-130 

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 

CONSUMABLE MATERIAL (Local purchase) : 

TOOLING 

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. 1318B DUROUX 

Blue isolating varnish Ref. 70 1586 + hardener Ref. 70 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 

ACCOMPLISHMENT INSTRUCTIONS : 

JAN 06 

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. 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 - refer to Chapter 07-1 0-00 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 GR" circuit breaker. 

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

Page 2 I 6 
I TBM AIRCRAFT 

SERVICE BULLETIN I SB 70-130 

JAN 06 

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 

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 1 0) on the other landing gear. 

B. CHECK - see Figure 1 

NOTE: 

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

or by fluorescent penetrant inspection. 

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. 

Page 3 I 6 
I TBM AIRCRAFT 

SERVICE BULLETIN I SB 70-130 

JAN 06 

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 

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 or fluorescent 

penetrant inspection- refer to Chapter 20-50-01 of the 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 

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 C. 

6) If the crack is confirmed, contact EADS SOCATA to coordinate the landing gear repair 

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" 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. 

7) After application of this SB, please return the enclosed form to SOCATA at the 

indicated address. 

Page 4 I 6 
TBM AIRCRAFT I SERVICE BULLETIN I SB 70-130 

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 

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. 

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

own risk. 

Page 5 I 6 
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 

under the authority of DOA No. EASA.21 J.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 I 6 
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 by fluorescent 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