APR 13 Page 1 / 7

Amdt. X --- DAT XX

ACTUATORS INSTALLED ON AIRCRAFT S/N 536, 540 to 543, 547 to 557, IF NOT REPLACED SINCE

APPLICATION OF TN 70 -- 13 -- 32 ARE NOT CONCERNED BY THIS SERVICE BULLETIN.

SUBJECT : LANDING GEAR ACTUATOR ROD END ASSEMBLY

EFFECTIVITY : Actuators installed on aircraft from S/N 1 to 9999 and actuators in shop which P/N is :

T700A3230050000 or T700A323005000000 or T700A323005300000.

REASON :

A. PROBLEM

Possible uncrimping of landing gear actuator ball joint that could result in a landing gear

leg collapse.

B. REASON

Occurrences of manufacturing non conformity of some actuator rod end assemblies.

C. SOLUTION

Rod end assembly crimping check. Actuator return to conformity through rod end

assembly replacement, if necessary.

SUMMARY :

A. PREPARATION

B. CHECK OF LANDING GEAR ACTUATOR BALL JOINT CENTERING

C. REMOVAL OF ROD END ASSEMBLY

D. INSTALLATION OF NEW ROD END ASSEMBLY

E. RECONDITIONING

COMPLIANCE : During next scheduled inspection and at the latest before May 31, 2014.

WARRANTY : For aircraft under warranty, parts and manpower are taken under warranty within granted

time limit until May 31, 2014.

Only the rod ends returned to DAHER ---SOCATA will be taken under warranty, until

May 31, 2014.

SERVICE BULLETIN

TBM AIRCRAFT

MANDATORY

The technical content of this document is approved

under the authority of DOA No. EASA.21J.013

is the subject of an AD

SB 70 -- 206

AMENDMENT 1

32

ATA No.

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
SERVICE BULLETIN

TBM AIRCRAFT

MANDATORY

The technical content of this document is approved

under the authority of DOA No. EASA.21J.013

is the subject of an AD

SB 70 -- 206

AMENDMENT 1

32

ATA No.

APR 13 Page 2 / 7

Amdt. X --- DAT XX

PROCURABLE MATERIAL :

--- Parts to be ordered from your TBM spare parts distributor.

Item Part number Description Qty/aircraft

1 7134340003 Rod end assy Up to 3 *

3 7228230573 Lockwasher Up to 3 *

7 7743090220 Lockwasher Up to 3 *

* as per number of related actuators

CONSUMABLE MATERIAL (Local purchase) :

--- Grease AIR 4210B [MIL ---PFR ---23827C (Type II)]

TOOLING :

--- Standard aeronautical maintenance station tools

--- One set of feeler gauges

MANPOWER :

--- 1 aeronautical mechanic

For ball joint centering check on all 3 actuators

--- 1 hour

For rod end assembly replacement

--- 2.5 hours for each main landing gear

3 hours for nose landing gear

TECHNICAL INCIDENCES :

--- None

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.

NOTE :

This SB must be applied on the 3 actuators.

A. PREPARATION

1) Make sure the ”SOURCE” selector is set to ”OFF”.
SERVICE BULLETIN

TBM AIRCRAFT

MANDATORY

The technical content of this document is approved

under the authority of DOA No. EASA.21J.013

is the subject of an AD

SB 70 -- 206

AMENDMENT 1

32

ATA No.

APR 13 Page 3 / 7

Amdt. X --- DAT XX

2) Install the warning sign prohibiting ”SOURCE” selector operation

WARNING

DO NOT OPERATE

MAINTENANCE WORK IN PROGRESS

B. CHECK OF LANDING GEAR ACTUATOR BALL JOINT CENTERING --- see Figure 1

NOTE :

For check , the rod end assembly should not be painted.

1) With a feeler gauge (11), check both sides of rod end, make sure that ball joint

mismatch is lower than or equal to 0.012 in (0.3 mm).

2) If ball joint mismatch is lower than or equal to 0.012 in (0.3 mm), the crimping is

correct --- refer to Paragraph E.

3) If ball joint mismatch is greater than 0.012 in (0.3 mm), the rod end assembly must

be replaced --- refer to Paragraph C.

C. REMOVAL OF ROD END ASSEMBLY --- see Figure 2

1) Jack up the aircraft -- refer to 07--10--00.

2) Unlock landing gear.

3) Open ”LDG GEAR” circuit breaker.

CAUTION

FOR NOSE LANDING GEAR, REMOVAL OF R.H. DOOR 142 IS IMPERATIVE --

REFER TO CHAPTER 52 -- 80 -- 02 OF THE MAINTENANCE MANUAL.

4) Loosen locknut (2) without removing it.

5) Unlock and remove nut (8).

6) Remove and discard lockwasher (7).

7) Remove and retain washer (6).

8) Gradually retract landing gear manually to find the angle enabling to disengage rod

end assy (1) from axle (4).

CAUTION

IN ORDER TO SAVE INTEGRITY OF HYDRAULIC CONNECTIONS, IT IS IMPERATIVE

TO RELIEVE THE ACTUATOR BY SUPPORTING IT WITH A TIE --WRAP OR ANY

OTHER APPROPRIATE MEANS.

9) Identify on the visible face the rod end assy (1) with S/N of aircraft from which it is

removed followed by R :Right, L : Left, N : Nose according to its location (ex : 488 ---R).
SERVICE BULLETIN

TBM AIRCRAFT

MANDATORY

The technical content of this document is approved

under the authority of DOA No. EASA.21J.013

is the subject of an AD

SB 70 -- 206

AMENDMENT 1

32

ATA No.

APR 13 Page 4 / 7

Amdt. X --- DAT XX

10) Remove rod end assy (1) and return it to DAHER ---SOCATA.

Richard ARRIULOU

DAHER SOCATA --- Direction des Services

Aéroport Tarbes ---Lourdes ---Pyrénées

65921 TARBES Cedex 9

FRANCE

Phone : +33 (0)5 62 41 76 74

Fax : +33 (0)5 62 41 76 54

e ---mail : r.arriulou@socata.daher.com

or for the Americas :

Marcel KIM

SOCATA NORTH AMERICA

North Perry Airport

7501 South Airport Rd.

Pembroke Pines, FL 33023

USA

Phone : +1 (954) 893 1418 or 1419

Fax : +1 (954) 964 7092

e ---mail : m.kim@socata.daher.com

D. INSTALLATION OF NEW ROD END ASSY --- see Figure 2

1) Screw without tightening, locknut (2) on the new rod end assy (1).

2) Lubricate internal thread of piston rod.

3) Install, without locking and with a new lockwasher (3), a new rod end assy (1) at the

end of piston rod.

4) Lubricate axle (4) with grease AIR 4210B [MIL ---PFR ---23827C (Type II)].

5) Install washer (5).

6) Gradually retract landing gear manually to find the angle enabling to engage rod end

assy (1) on axle (4).

7) Install washer (6) and lockwasher (7).

8) Screw without tightening nut (8).

9) For nose landing gear, install R.H. door 142 --- refer to Chapter 52 ---80 ---02 of the

Maintenance Manual.

10) Close ”LDG GEAR” circuit breaker.

CAUTION

AFTER REPLACEMENT OF ROD END ASSY, IT IS MANDATORY TO PERFOM

ADJUSTMENT/TEST OPERATIONS AND TORQUE LOCKNUT (2) AND NUT (8) IN

COMPLIANCE WITH MAINTENANCE MANUAL PROCEDURES :

MAIN LANDING GEAR ACTUATOR -- REFER TO CHAPTER 32 -- 30 -- 01 OF THE

MAINTENANCE MANUAL.

NOSE LANDING GEAR ACTUATOR -- REFER TO CHAPTER 32 -- 30 -- 02 OF THE

MAINTENANCE MANUAL.
SERVICE BULLETIN

TBM AIRCRAFT

MANDATORY

The technical content of this document is approved

under the authority of DOA No. EASA.21J.013

is the subject of an AD

SB 70 -- 206

AMENDMENT 1

32

ATA No.

APR 13 Page 5 / 7

Amdt. X --- DAT XX

E. RECONDITIONING

1) Make sure all the tools and materials are removed and the work area is clean and free

from debris.

2) Remove the warning sign prohibiting ”SOURCE” selector operation.

UPDATING OF THE AIRCRAFT DOCUMENTATION :

Upon completion of Service Bulletin No. SB 70 ---206 ---32 ”LANDING GEAR ACTUATOR ROD

END ASSEMBLY”, make an appropriate maintenance record entry.

WARNING : 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.
SERVICE BULLETIN

TBM AIRCRAFT

MANDATORY

The technical content of this document is approved

under the authority of DOA No. EASA.21J.013

is the subject of an AD

SB 70 -- 206

AMENDMENT 1

32

ATA No.

APR 13 Page 6 / 7

Amdt. X --- DAT XX

Figure 1 --- Check of landing gear actuator ball joint centering

11 --- Feeler gauge
SERVICE BULLETIN

TBM AIRCRAFT

MANDATORY

The technical content of this document is approved

under the authority of DOA No. EASA.21J.013

is the subject of an AD

SB 70 -- 206

AMENDMENT 1

32

ATA No.

APR 13 Page 7 / 7

Amdt. X --- DAT XX

Figure 2 --- Removal / installation of rod end assy

1 --- Rod end assy

2 --- Locknut

3 --- Lockwasher

4 --- Axle

5 --- Washer

6 --- Washer

7 --- Lockwasher

8 --- Nut