EASA AD No.: 2010-0035

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2010-0035

Date: 04 March 2010

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 participat e 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 b e ensured by accomplishing any applicable ADs. Cons equently, no person may operate an aircraft to which an Airworthiness D irective applies, except in accordance with the req uirements of that Airworthiness Directive 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, Ar ticle 14(4) exemption].


### Type Approval Holder’s Name :
BAE Systems (Operations) Ltd Type/Model designation(s) :
HS.748 and ATP aeroplanes

TCDS Number : EASA.A.192 and EASA.A.397

Foreign AD : Not applicable

Supersedure : None



### ATA 27 Flight Controls – Aileron and Rudder Tab Hinge Pins –

Inspection

Manufacturer(s): Hawker Siddeley Aviation Ltd, Brit ish Aerospace plc, British Aerospace (Commercial Aircraft) Ltd

Applicability: HS.748 aeroplanes, all models, all s erial numbers. ATP aeroplanes, all serial numbers.

Reason: Early in the life of the ATP (circa 1989), a report was received that a control surface hinge pin had migrated out of posit ion, causing a rubbing contact. BAE Systems responded by issuing SB ATP-2 7-11, describing a one-time inspection of the hinge pins, which was cl assified mandatory by UK CAA AD 006-06-89. Both SB and AD were subsequent ly cancelled in 1990. The HS.748 and the ATP secondary controls are similar in these areas, although no action was taken on the HS.748 f leet at that time. Recently, during a walk round check, an operator fo und an aileron trim tab hinge pin that had migrated sufficiently to cause a rubbing foul on the flap. Other reports indicate that, for the purposes of ex pediency, it has become common practice during maintenance when replacing a control tab, instead of unbolting the forward part of the piano hinge from the primary control surface, the hinge pins are punched out of the hinges. Investigations have concluded that, after reinserti ng the pins after maintenance, the ends of the hinges may not have be en pinched, which is likely to have been the cause of the detected hinge pin migration.EASA AD No.: 2010-0035

EASA Form 110 Page 2/2 This condition, if not detected and corrected, coul d lead to further incidents of migration of a tab hinge pin out of th e hinge, likely resulting in restricted movement of the tab control and conseque nt reduced control of the aeroplane. For the reasons described above, this AD requires t he inspection of aileron and rudder tab piano hinge pins and, depend ing on findings, the necessary corrective actions.

Effective Date: 18 March 2010

Required action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Within the next three (3) months after the effe ctive date of this AD, inspect the aileron and rudder tab piano hinge pins in accordance with the instructions of paragraph 2 of BAE Systems (Ope rations) Ltd Service Bulletin (SB) HS748-27-136 or SB ATP-27-090 , as applicable to aeroplane type. (2) If any incorrectly secured hinge pin is found d uring the inspection as required by paragraph (1) of this AD, before next f light, accomplish the necessary corrective actions in accordance with the instructions of paragraph 2 of BAE Systems (Operations) Ltd SB HS74 8-27-136 or SB ATP-27-090, as applicable to aeroplane type.

Ref. Publications: BAE Systems (Operations) Limited SB HS748-27-136 dated 14 April 2009. BAE Systems (Operations) Limited SB ATP-27-090 date d 14 April 2009. The use of later approved revisions of these docume nts 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 26 January 2010 as PAD 10- 015 for consultation until 23 February 2010. No comments we re received during the consultation period. 3. Enquiries regarding this AD should be referred t o the Airworthiness Directives, Safety Management & Research Section, C ertification 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: BAE Systems (Operations) Ltd, Customer Information Department, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; Telephone +44 1292 675207, Facsimile +44 1 292 675704; E-mail: RApublications@baesystems.com

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