EASA AD No.: 2015-0099

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0099

Date: 03 June 2015

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EU 748/2012, P art 21.A.3B. In accordance with EU 1321/2014 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 accordan ce with the requirements of that AD, unless otherwi se 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, A rticle 14(4) exemption].


### Design Approval Holder’s Name: BAE SYSTEMS (OPERATIONS) Ltd Type/Model designation(s): Jetstream 4100 aeroplanes

TCDS Number: EASA.A.189

Foreign AD: Not applicable

Supersedure: None



### ATA 27 Flight Controls – Elevator Trim Circuit – In spection / Modification

Manufacturer(s): British Aerospace plc, British Aer ospace (Commercial Aircraft) Ltd, British Aerospace Regional Aircraft Ltd, Jetstream Aircraft Ltd and British Aerospace (Operations) Ltd.

Applicability: Jetstream 4100 aeroplanes, all model s, all serial numbers.

Reason: An in-service event was reported of the Pit ch Trim jammed in the fully down position. During the event, the trim circuit was ad justed fully nose down and the swaged stop on the trim cable passed beyond the sto p plates. With gear down and the autopilot disconnected, the aeroplane pitch ed nose down and, even with the control column pulled fully back, the pilo t was unable to prevent descent. The trim circuit was freed and control res tored by the combined efforts of both pilots turning the trim handwheels, which f orced the swaged stop on the trim cable back past the broken stop plates. The re sults of the technical investigation revealed that the pitch trim servo mo tor travel stops were incorrectly adjusted, allowing the servo motor to f orce contact of the swaged stop on the trim cable with the stop plates, and pa rts of the stop plates breaking off.
This condition, if not detected and corrected, coul d lead to loss of control of the elevator trim, possibly resulting in reduced contro l of the aeroplane. To address this unsafe condition, BAE Systems (Oper ations) Ltd issued Inspection Service Bulletin (ISB) 27-068 to provide instructions to inspect and correct pitch trim servo motor travel stop adjustme nt and to install new stop plates made of improved (more robust) material. For the reasons described above, this AD requires a one-time inspection toEASA AD No.: 2015-0099

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. correct adjustment of the pitch trim servo motor tr avel stops to prevent the jam condition and, if damage is found, replacement of t he stop arms and plates.

Effective Date: 17 June 2015

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Within 30 days after the effective date of this AD accomplish a one-time inspection of the pitch trim travel stops in accord ance with the instructions of BAE Systems (Operations) Ltd SB J41-27-068. (2) If, during the inspection as required by paragr aph (1) of this AD, any damage is found to the stop arms, before next fligh t, replace the stop arms and install new stop plates in accordance with the instructions of the BAE Systems (Operations) Ltd SB J41-27-068.

Ref. Publications: BAE Systems (Operations) Ltd, IS B J41-27-068 original issue dated 21 January 2014. 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 29 April 2015 as PAD 15-05 5 for consultation until 27 May 2015. No comments were received during the c onsultation period. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Certification 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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