EASA AD No : 2011-0130 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0130 

Date: 08 July 2011 

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 EC 1702/2003, Part 21A.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]. 

Type Approval Holder’s Name : 

SOCATA

Type/Model designation(s) : 

TBM700 aeroplanes 

TCDS Number : EASA A.010 

Foreign AD : Not applicable 

Supersedure : None 

ATA 34 Navigation – Standby Compass Lighting – Modification 

Manufacturer(s): SOCATA (formerly EADS SOCATA) 

Applicability: SOCATA TBM700 aeroplanes, variants TBM700 B, TBM700 N, serial 

numbers (S/N) 148; from 434 to 572 inclusive; 574 and 576. 

Reason: A TBM700 operator reported an occurrence where, as a result of handling the 

standby compass lighting bulb cover in flight, both essential bus bars (ESS 

BUS 1 and ESS BUS 2) failed, leading to the loss of a number of instruments 

and navigation systems. 

The technical investigations carried out by SOCATA have shown that the 

cause of this occurrence was that the electrical protection of some TBM 700 

aeroplanes is insufficient to allow in-flight handling of the standby compass 

lighting cover when energized. 

This condition, if not corrected, may compromise the ability of the pilot to 

safely operate the aeroplane under certain flight conditions due to the 

increase of workload. 

To address this unsafe condition, SOCATA have developed a modification 

which consists of installing a protection fuse on the wire at the standby 

compass connector, introduced by SOCATA Service Bulletin (SB) 70-192-34. 

For the reasons described above, this AD requires installation of a protection 

of the electrical wire at the standby compass connector. 

Effective Date: 22 July 2011 
EASA AD No : 2011-0130 

EASA Form 110 Page 2/2 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

Within 6 months after the effective date of this AD, install a protection fuse on 

the wire at the standby compass connector in accordance with the 

accomplishment instructions of SOCATA SB 70-192-34.

Ref. Publications: SOCATA Service Bulletin 70-192-34 original issue dated April 2011. 

The use of later approved revisions of this document 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 06 June 2011 as PAD 11-059 for consultation until 

04 July 2011. 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) 62 41 73 00, Fax : + 33 (0) 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.