EASA AD No.: 2015-0065-E

TE.CAP.00111-004 © European Aviation Safety Agency. All rights reserved. 1/2

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EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2015-0065-E

Date: 24 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 EU 748/2012, Part 21.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 operate 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 aeroplanes

TCDS Number: EASA.A.390

Foreign AD: Not applicable

Supersedure: None

ATA 27 Flight Controls – Brake Master Cylinder Pivot Pins – 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 pivot pin Part Number (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 cause 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 AD 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 2015
EASA AD No.: 2015-0065-E

TE.CAP.00111-004 © European Aviation Safety Agency. All rights reserved. 2/2

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

Required Action(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, installed 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. Publications: 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 AD 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 requirements in 

this AD, please contact:

Technical Support Group, Marshall Aerospace and Defence Group,

The Airport, Newmarket Road, Cambridge, CB5 8RX, United Kingdom, 

Telephone +44 (0) 1223 399856,

Email: SS.TSG@marshalladg.com.