EASA AD No.: 2013-0253

TE.CAP.00113-003 © 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.: 2013-0253

Date: 18 October 2013

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 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 accordan ce with the requirements of that AD, unless otherwi se 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, A rticle 14(4) exemption]. 

### Design Approval Holder’s Name: SAAB AB, Aeronautics Type/Model designation(s): 340B aeroplanes

TCDS Number: EASA.A.068

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2012-0256 d ated 03 December 2012.



### ATA 27 Flight Controls – Stall Warning/Identification Syst em Stick Pusher Rigging – Inspection / Adjustment

Manufacturer(s): Saab AB, Aeronautics (formerly Saa b Aerosystems)

Applicability: Model 340B aeroplanes, all serial nu mbers

Reason: The standard stick pusher maximum elevator position of a SAAB 340B, prior to delivery, is set at 7.5 degrees trailing edge down. It was recently discovered that this value has been incorrectly referenced in the SAAB 340B Aircraft Maintenance Manual (AMM), which quotes an elevator position of 4 degrees trailing edge down for all aeroplanes, which is the correct value for SAAB SF340A aeroplanes only. If a SAAB 340B aeroplane has been re-rigged in acco rdance with current AMM procedure, there is a possibility that the deflecti on of the elevator will be less than intended. This condition, if not corrected, will affect the s tall characteristics on the outer part of the envelope at maximum flap setting and af t centre of gravity (CG) configuration, possibly resulting in reduced contro l of the aeroplane. To address this potential unsafe condition, SAAB AB Aeronautics issued Service Bulletin (SB) 340-27-105 to reduce the prob ability of a negative effect on the handling quality during stall. Consequently, EASA issued AD 2012-0256 to require a one-time inspection of the stick pushe r rigging and, depending on findings, adjustment to the correct setting. Since that AD was issued, it has been reported that on some aeroplanes, during implementation of SB 340-27-105, the trunnio n at the lower part of theEASA AD No.: 2013-0253

TE.CAP.00113-003 © 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. control column was incorrectly installed. This prev ents proper inspection of the stick pusher rigging. Prompted by this finding, SAAB issued SB 340-27-115 with instructions for all aeroplanes, regardless whether SB 340-27-105 has be en accomplished or not. For the reasons described above, this AD retains th e requirements of EASA AD 2012-0256, which is superseded, but requires the us e of the improved and expanded instructions specified in SAAB SB 340-27-1 15.

Effective Date: 01 November 2013

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Within 24 months after the effective date of th is AD, inspect the installation of the trunnion at the lower part of the control co lumn and the stick pusher rigging in accordance with the instructions of SAAB SB 340-27-115. (2) If, during the inspection as required by paragr aph (1) of this AD, an incorrect setting of the stick pusher maximum eleva tor position is found, or the trunnion at the lower part of the control colum n is incorrectly installed, before next flight, accomplish the applicable corre ctive action(s) in accordance with the instructions of SAAB SB 340-27- 115. (3) Within 30 days after the corrective action as r equired by paragraph (2) of this AD, record the incorrect rigging value that wa s detected and report to SAAB in accordance with the instructions of SAAB SB 340-27-115.
Ref. Publications: SAAB SB 340-27-115 original issu e dated 19 July 2013. 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 19 September 2013 as PAD 1 3-145 for consultation until 17 October 2013. No comments were received du ring 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: Saab AB, Support and Services SE-581 88 Linköping, Sweden Fax: +46 13 184874 E-mail: saab340.techsupport@saabgroup.com

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