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 b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Europe an Community, its Member States and of the European third countries that participate in th e 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 en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accor dance with the requirements of that AD unless other wise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/200 8, 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 – Modi fication

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 a nd 576.
Reason: A TBM700 operator reported an occurrence wh ere, 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 pr otection of some TBM 700 aeroplanes is insufficient to allow in-flight handl ing of the standby compass lighting cover when energized. This condition, if not corrected, may compromise th e ability of the pilot to safely operate the aeroplane under certain flight c onditions due to the increase of workload. To address this unsafe condition, SOCATA have devel oped a modification which consists of installing a protection fuse on t he wire at the standby compass connector, introduced by SOCATA Service Bul letin (SB) 70-192-34. For the reasons described above, this AD requires i nstallation of a protection of the electrical wire at the standby compass conne ctor.

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

EASA Form 110 Page 2/2 Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly:
Within 6 months after the effective date of this AD , install a protection fuse on the wire at the standby compass connector in accord ance with the accomplishment instructions of SOCATA SB 70-192-34.

Ref. Publications: SOCATA Service Bulletin 70-192-3 4 original issue dated April 2011. The use of later approved revisions of this documen t is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA 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 t o the Safety Information Section, Executive Directorate, EASA. E-mail ADs@easa.europa.eu

. 4. For any question concerning the technical conten t 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 So uth Airport Road, Pembroke Pines, Florida 33023, The United Sta tes of America. Tel.: +1 (954) 893 1400 Fax: +1 (954) 964 4141.