EASA AD No.: 2013-0227

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/3

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0227

Date: 23 September 2013

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation 

(EC) No 216/2008 on behalf of the European Community, its Member States and of the 

European third countries that participate in the activities of EASA under Article 66 of that 

Regulation.

This AD is issued in accordance with EU 748/2012, Part 21.A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the 

continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an 

aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency [EC 

2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].

Design Approval Holder’s Name:

SOCATA

Type/Model designation(s):

TBM 700 aeroplanes

TCDS Number: EASA.A.010

Foreign AD: Not applicable

Supersedure: None

ATA 32 Landing Gears – Nose and Main Landing Gear Actuators –

Inspection / Replacement

Manufacturer(s): SOCATA (formerly EADS SOCATA)

Applicability: SOCATA TBM 700 aeroplanes, all manufacturer serial numbers.

Reason: During maintenance check, possible unscrewing of rod and piston during 

operation was detected on a landing gear actuator. Investigation showed that 

this was likely caused by maintenance operation not conforming with the 

procedure described in the SOCATA maintenance manual.

Moreover, following in-service landing gear collapse, uncrimping of a right hand 

main landing gear (MLG) actuator ball joint was detected. Investigation 

revealed a manufacturing non-conformity of some actuator rod end assemblies. 

These conditions, if not detected and corrected, could lead to MLG or nose 

landing gear (NLG) failure during landing or roll-out and consequent damage to 

the aeroplane and injury to occupants.

To address this potential unsafe condition, SOCATA issued Service Bulletin 

(SB) 70-197-32 to require a one-time inspection of the landing gear actuator 

piston/rod and SB 70-206-32 to require a one-time inspection of the landing 

gear actuator ball joint centering and, depending on findings, accomplishment 

of corrective actions.

SOCATA also developed modification 70-0334-32, embodied in production to 

secure rod/piston assembly through addition of a pin and to reduce retraction/

extension indication failure through improvement of switch kinematics. These 

modified actuators have a new part number (P/N).

For the reasons described above, this AD requires a one-time inspection of the 

landing gear actuators piston/rod and ball joint centering and, depending on 

findings, accomplishment of applicable corrective actions.
EASA AD No.: 2013-0227

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Effective Date: 07 October 2013

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 8 months after the effective date of this AD, for aeroplanes on which

landing gear actuator P/N T700A3230050000 or P/N T700A323005000000 

or P/N T700A323005300000 is installed, accomplish the following actions 

concurrently:

(1.1) Perform a detailed visual inspection (DVI) of pistons/rods of the 

NLG and left hand (LH) and right hand (RH) MLG actuators and 

measure the distance (A) in accordance with the instructions of 

SOCATA SB 70-197-32.

(1.2) Perform a DVI of ball joint centering of NLG and LH and RH MLG

actuators and measure ball joint mismatch in accordance with the 

instructions of SOCATA SB 70-206-32.

Note: For the purpose of this AD, distance (A) is defined in SOCATA

SB 70-197-32.

(2) If, during any inspection as required by paragraph (1.1) or (1.2) of this AD, 

any discrepancy is identified, before next flight, replace the affected 

actuator or rod end assembly, as applicable, with a serviceable part, as 

specified in Appendix 1 of this AD, in accordance with the instructions of 

SOCATA SB 70-197-32 or SB 70-206-32, as applicable.

(3) From the effective date of this AD, installation on an aeroplane of a landing 

gear actuator P/N T700A3230050000 or P/N T700A323005000000 or P/N 

T700A323005300000 is allowed, provided that, following installation, the 

part passes the inspections as specified in paragraph (1) of this AD.

Ref. Publications: SOCATA SB 70-197-32 original issue dated April 2013.

SOCATA SB 70-206-32 original issue dated April 2013.

The use of later approved revisions of these documents is acceptable for 

compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD.

2. This AD was posted on 01 August 2013 as PAD 13-113 for consultation 

until 29 August 2013. No comments were received during the consultation 

period.

3. Enquiries regarding this AD should be referred to the Safety Information 

Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu.

4. For any question concerning the technical content of the requirements in 

this AD, please contact:

SOCATA, Direction des services, 65921 Tarbes Cedex 9, France.

Tel. +33 (0) 5 62 41 73 00, Fax : + 33 (0) 5 62 41 76 54.

or for the U.S.A

SOCATA NORTH AMERICA, North Perry Airport, 7501 South Airport

Road, Pembroke Pines, Florida 33023, The United States of America.

Tel.: +1 (954) 893 1400 Fax: +1 (954) 964 4141.
EASA AD No.: 2013-0227

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Appendix 1 – Corrective Actions

Ball joint mismatch

In accordance with SB 70-206-32

Equal or less than 

0.3 mm (0.012 in)

Greater than 

0.3 mm (0.012 in)

Distance (A)

In accordance with SB 70-197-32

Less than 6 mm (0.236 in) 

if jam nut is 6 mm (0.236 in) 

thick,

or 

less than 4 mm (0.157 in) 

if jam nut is 8 mm (0.315 in) 

thick

Replace the affected actuator 

with a serviceable part in 

accordance with the 

instructions of SOCATA 

SB 70-197-32.

Replace the affected actuator 

with a serviceable part in 

accordance with the 

instructions of SOCATA 

SB 70-197-32.

Equal or greater than 

6 mm (0.236 in) if jam nut is 

6 mm (0.236 in) thick,

or 

equal or greater than 

4 mm (0.157 in) if jam nut is

8 mm (0.315 in) thick

No action required. Replace the affected rod end 

assembly with a serviceable 

part in accordance with the 

instructions of SOCATA 

SB 70-206-32.