EASA AD No.: 2012-0068

EASA Form 110 Page 1/2

EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0068

Date: 25 April 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 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 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].

Type Approval Holder’s Name :

Saab AB, Aeronautics

Type/Model designation(s) :

2000 aeroplanes

TCDS Number : EASA.A.069

Foreign AD : Not applicable

Supersedure : None

ATA 53 Fuselage – Centre Bottom Panel – Inspection

Manufacturer(s): Saab AB, Aeronautics (formerly Saab Aerosystems).

Applicability: Model 2000, all serial numbers.

Reason: On two SAAB 2000 aeroplanes, signs of chafing have been found on the 

bottom panel of the centre cabin between fuselage station (STA) 562 and 

STA 622. The investigation results have shown that the chafing is caused by 

certain Hi Lok fasteners, installed as a repair during production, through the 

upper wing skin panel.

This condition, if not detected and corrected, could affect the structural 

integrity of the affected wing-to-fuselage connection.

To address this potential unsafe condition, SAAB issued Service Bulletin 

(SB) 2000-53-057 to provide instructions for a general visual inspection to 

detect chafing in the area between the upper wing skin and the cabin centre

bottom panel and to verify if there are Hi Lok fasteners installed with the 

collar up.

For the reasons described above, this AD requires a one-time inspection of 

the designated area, the accomplishment of corrective action(s), depending 

on findings, and the reporting of all inspection results to SAAB.

This AD is considered an interim action and further AD action may follow.

Effective Date: 09 May 2012
EASA AD No.: 2012-0068

EASA Form 110 Page 2/2

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 12 months after the effective date of this AD, accomplish a 

general visual inspection of the area between the upper part of the wing 

skin and the centre bottom panel, in accordance with the instructions of 

SAAB SB 2000-53-057. 

(2) If, during the inspection as required by paragraph (1) of this AD, Hi Lok 

fasteners are found installed with the collar up and/or signs of chafing 

are found, before next flight, record the affected Hi Lok locations and/or

other findings in accordance with the instructions of SAAB SB 2000-53-

057, contact SAAB for approved repair instructions and accomplish 

those instructions accordingly.

(3) Within 30 days after the inspection as required by paragraph (1) of this 

AD, or within 30 days after the effective date of this AD, whichever 

occurs later, report all findings (including none) to SAAB, in accordance 

with the instructions of SAAB SB 2000-53-057.

Ref. Publications: SAAB SB 2000-53-057 original issue dated 22 November 2011.

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 26 March 2012 as PAD 12-023 for consultation 

until 23 April 2012. 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: saab2000.techsupport@saabgroup.com.