E ASA AD No.: 20 12

- 0256

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 12

- 0256

Date : 0 3 Dec em ber 2012

Note: This 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 EC 2042/2003 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 Age ncy [EC 2042/2003 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:

SAAB AB, Aeronautics Type/Model designation(s):
340B aeroplanes

TCDS Number: EASA.A.068

F oreign AD: Not applicable

Supersedure: None



### ATA 27 Flight Controls

– Stall Warning/Identification System Stick Pusher Rigging

– Inspection / Adjustment

Manufacturer(s): SAAB AB, Aeronautics (formerly SAAB Aerosystems)

Applicability: Model 340B aeroplanes

, all serial numbers

.

Reason: T he standard stick pusher max imum 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 in correctly referenced in the SAAB 340 B 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 accordance with current AMM procedure, there is a possibility that the deflection of the elevator will be less than intended.

This condition, if not corrected, will affect the stall characteristics on the outer part of the envelope at maximum flap setting and aft centre of gravity ( CG ) configuration , possibly resulting in reduced control of the aeroplane

. To address this potential unsafe condition, SAAB AB Aeronautics issued Service Bulletin (SB) 340

- 27

- 105 to reduce the probability of a negative e ffect

on the handling quality dur in g stall.
For the reasons described above, this AD requires a one

- time inspection of the stick pusher rigging and , depending on findings, adjustment t o the correct setting

.

Effective Date: 1 7 December 2012E ASA AD No.: 20 12

- 0256

TE. CAP.0011 0

- 00 3 © 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) Within 24 months after the effective date of this AD , i nspect the stick pusher rigging in accordance with the instructions of SAAB SB 340

- 27

- 105. (2) If , during the inspection as required by paragraph (1) of this AD, an incorrect setting of the stick pusher maximum elevator position is found, before next flight , adjust the stick pusher rigging in accordance with the instructions of SAAB SB 340

- 27

- 105. (3) Within 30 days after th e corrective action as required by paragraph (2) of this AD, r ecord the incorrect rigging value that was detected and report to SAAB in accordance with the instructions of SAAB SB 340

- 27

- 105.

Ref. Public ations: SAAB SB 340

- 27

- 105 original issue dated 12 July 2012

, or Revision 01 dated 31 August 2012.
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. This AD was posted on 0 2 November 2012 as PAD 12

- 1 3 7 for consultation until 30 November 2012

. N o comments were received during the consultation peri o d

. 3. Enquiries regarding this AD should be referred to the Safety Information Section, Executive Directorate, EASA. E

- mail: ADs@easa.europa.eu

. 4. For any question concerning the technical content of the requireme nts 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

.