EASA AD No.: 2015

- 0065

- E

TE. CAP.0011 1

- 00 4 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No

. : 2015

- 00 65

- E

Date: 2 4 April 2015

Note: This Emergency 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 E U 748/2012 , Part 2 1

. A.3B. In accordance with EU 1321/2014 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may ope rate an aircraft to which an AD applies, except in accordance with the requirements of that AD

, unless otherwise specified by the Agency [ EU 1321/2014 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:

SLINGSBY ADVANCED COMPOSITES Ltd Type/Model designation(s):

T67 a eroplanes

TCDS Number: EASA.A.390

F oreign AD: Not applicable

Supersedure: None



### ATA 27 Flight Controls

– Brake Master Cylinder Pivot Pin s
– Inspection / Replacement

Manufacturer(s): Slingsby Advanced Composites Ltd ( trading as Marshall Aerospace and Defence Group) , formerly Slingsby Aviation Ltd.

Applicability: T67B, T67C, T67M, T67M

- MkII, T67M200 and T67M260 aeroplanes, all serial numbers

.

Reason: An occurrence was reported where p ivot p in Part N umber (P/N) T67M

- 45

- 539

, of rudder pedal assembly #4

, installed on the right hand (RH) side of the aeroplane (RH seat
, RH pedal) failed during taxi. This caused the rudder pedal mechanism to detach from the brake master cylinder

. This condition, if not detected and corrected, could c ause the rudder linkages to rotate out of their normal orientation , possibly resulting in jammed rudder controls and consequent loss of control of the aeroplane

. To address this potential unsafe condition, Slingsby Advanced Composites Ltd

, trading as Marshall Aerospace and Defence Group (hereafter called ‘ Marshall’ in this AD ) issued Service Bulletin (SB) SBM200 to provide inspection instructions.
For the reason described above, this A D requires repetitive inspections of the brake master cylinder pivot pins of rudder pedal assemblies #1 and #4 and, depending on findings, replacement of the affected pivot pin (s)

.

Effective Date: 28 April 2015EASA AD No.: 2015

- 0065

- E

TE. CAP.0011 1

- 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Required A ction(s) and Compliance Time(s) : Required as indicated

, unless accomplished previously : (1) Before next flight after the effective date of this AD (see Note)

, and

, thereafter

, at intervals not to exceed 300 flight hours

, or during each annual inspection , whichever occurs first, inspect the brake master cylinder pivot pins P/N T67M

- 45

- 539

, install ed on rudder pedal assemblies #1 and #4

, in accordance with the instructions of Marshall SBM200

. Note: A single ferry flight is allowed to bring the aeroplane to a location where the initial inspection can be accomplished. (2) If, during any inspection as required by paragraph (1) of this AD, any crack or distortion to a brake master cylinder pivot pin is discovered

, or a pivot pin fails the dimensional check, before next flight, replace the affected pivot pin with a serviceable part in accordance with the instructions of Marshall SBM200. (3) Replacement of pivot pins on an aeroplane, as required by paragraph (2) of this AD

, does not constitute terminating action for the repetitive inspections as required by paragraph (1) of this AD for that aeroplane.

Ref. Public ations: Marshall Aerospace and Defence Group SBM200

, original issue dated March 2015, or Revision 1 dated April 2015. 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. The results of the safety assessment have indicated the need for immediate publication and notification, without the full public consultation process

. 3. Enquiries regarding this A D should be referred to the Safety Information Section, Certification Directorate , EASA. E

- mail : ADs@easa.europa.eu

. 4. For any question concerning the technical content of the requirem ents in this AD, please contact: Technical Support Group, Marshall Aerospace and Defence Group, The Airport, Newmarket Road, Cambridge, CB5 8RX, U nited Kingdom

, Telephone +44 (0) 1223 399856, E mail: SS.TSG@marshalladg.com

.