EASA AD No.: 2013-0253

TE.CAP.00113-003 © European Aviation Safety Agency. All rights reserved. 1/2 

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EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2013-0253 

Date: 18 October 2013 

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 Agency [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 

Foreign AD: Not applicable 

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

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: 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 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 effect 

on the handling quality during stall. Consequently, EASA issued AD 2012-0256 

to require a one-time inspection of the stick pusher 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 trunnion at the lower part of the 
EASA AD No.: 2013-0253

TE.CAP.00113-003 © European Aviation Safety Agency. All rights reserved. 2/2 

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

control column was incorrectly installed. This prevents 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 been accomplished or not. 

For the reasons described above, this AD retains the requirements of EASA AD 

2012-0256, which is superseded, but requires the use of the improved and 

expanded instructions specified in SAAB SB 340-27-115. 

Effective Date: 01 November 2013 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within 24 months after the effective date of this AD, inspect the installation 

of the trunnion at the lower part of the control column and the stick pusher 

rigging in accordance with the instructions of SAAB SB 340-27-115. 

(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, or 

the trunnion at the lower part of the control column is incorrectly installed, 

before next flight, accomplish the applicable corrective action(s) in 

accordance with the instructions of SAAB SB 340-27-115. 

(3) Within 30 days after the corrective action as required by paragraph (2) of 

this AD, record the incorrect rigging value that was detected and report to 

SAAB in accordance with the instructions of SAAB SB 340-27-115. 

Ref. Publications: SAAB SB 340-27-115 original issue dated 19 July 2013. 

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 19 September 2013 as PAD 13-145 for consultation 

until 17 October 2013. No comments were received during the consultation 

period. 

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 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.