EASA AD No.: 20 12

- 0 068

E ASA Form 110 Page 1 / 2 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 12

- 0 068

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 Eur opean 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, P art 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 :

S a ab AB, Aero nautics Type/Model designation(s) :

2000 aeroplanes

TCDS Num ber : EASA. A.069

F oreign AD : N ot applic able

Supersedure : N one



### ATA 53 Fuselage

– Cent r e Bottom Panel

– Inspection

Manufacturer(s): Saab AB, Aeronautics (former ly Saab Aerosystems ).

Applicability: Model 2000

, all serial numbers.

Reason: On t wo SAAB 2000 aeroplanes, signs of chafing hav e 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 c hafing is caused by certain Hi Lok fastener s , installed as a repair during production, through the upper win g skin panel.
This condition, if not detected and corrected, could affect the structural integrity of the affected wing

- to

- fuselage conn ection

. To address this potential unsafe condition , SAAB issued Service Bulletin (SB) 2000

- 53

- 057 to provide instruction s 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 L ok fasteners installed with the collar up. For the reasons described above, this AD requires a one

- time in spection 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: 0 9 Ma y 2012EASA AD No.: 20 12

- 0 068

E ASA Form 110 Page 2 / 2 Required A ction(s) and Compliance Time(s) : Required as indicated, u nless a ccomplished 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 a nd the centre bottom panel

, in accordance with the instructions of SAAB SB 20 00

- 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, befor e next flight, record the affected Hi L ok locations and /or

o the r findings in accordance with the instructions of SAAB SB 20 00

- 5 3

- 057

, contact SAAB for a pproved 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, r eport all findings (including none) to SAAB

, in accordance with the instructions of SAAB SB 20 00

- 53

- 057

.

Ref. Public ations: SAAB SB 2000

- 5 3

- 057 original issue dated 22 November 201 1

. The use of later approved revisions of th i s document is acceptable for compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately substantiated, EASA can approve Altern ative Methods of Compliance for this AD.

2. This AD was posted on 26 March 2012 as PAD 12

- 023 for consultation until 23 April 201 2

. No comments were received during the consultation period.

3. Enquiries regarding this A D should be referred to the Safety Informat ion 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 Linköp ing, Sweden Fax: +46 13 184874 E

- mail: saab2000.techsupport@saabgroup.com

.