EASA

EASA AD No.: 2010-0115

AIRWORTHINESS DIRECTIVE

AD No.: 2010-0115

Date: 17 June 2010

Note: This ,Airworthiness Directive (AD) is issued by EASA, <'I\..1;ngin accordance with

Regulation (EG) No 216/2008 on behalf of the European Community, its Member Slates and

of the European third countries thai parlitjpate in (he activities of EASA under Article 66 01

thaI Regulation, '

This AD is issued in accordance with EC 170212003, Part 21A.3B. In accordance with EC 2042/2003 Anne~ 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 lhal AD, unless otherwise specified by the Agency

lEG 2042/2003 Annex I, Part MA303] or agreed with the Authority of lhe Stale of Registry [EG 216/2008, Article 14(4) exemplionJ.

Type Approval Holder's Name:

5MB AB, Saab Aerosystems

Type/Model designation(s) :

2000 aeroplanes

TCDS Number'

Foreign AD :

Supersedure:

ATA55

Manufacturer(s):

Applicability:

Reason:

Effective Date:

EASA Form 110

EASAA069

Not applicable

None

Stabilizers - Horizontal Stabilizer Rear Spar Upper Cap & Wiring

Harness - Inspection I Modification

5MB AS, Saab Aerosystems (formerly Saab Aircraft AS).

Model 2000, all serial numbers

Corrosion has been found on the rear spar upper cap of the horizontal

stabilizer of SAAB 2000 aeroplanes. The affected areas are adjacent to the

inboard elevator hinge where the electrical wiring harnesses are located and

wired through the lightening holes. The upper spar cap is a primary

structural eiement and is important to the structural integrity of the horizontal

stabilizer.

Corrosion damage in these areas, if not detected and corrected, can result

in a starting. point for future crack propagation, which would impair the

integrity of the horizontal stabilizer upper spar cap structure.

For the reasons describe above, this AD requires a detailed visual

inspection {DVI} of the LH and RH horizontal stabilizer rear spar adjacent to

the inboard elevator hinge and the harnesses installed in the adjacent

areas, installation of convoluted tubing on the harness, and corrective

actions depending on findings.

01 July 2010

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EASA AD No.: 2010-0115

Required as indicated, unless accomplished previously:

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

of the LH and RH horizontal stabilizer and the harness installed in the

Required Action(s) adjacent area, and install convoluted tubing on the harness, in

and Compliance accordance with the instructions of 5MB SB 2000-55-013,

Time(s): (2) If, during the DVI as required by paragraph (1) of this AD, corrosion is

detected, before next flight, contact SAAB (address indicated in SB) to

obtain approved repair instructions and accomplish those instructions

accordingly.

5MB S8 2000-55-013 original issue dated 06 July 2009.

Ref. Publications: The use of later approved revisions of this document is acceptable for

compliance with the requirements of this AD.

1. [f requested and appropriately substantiated. EASA can approve

Alternative Methods of Compliance for this AD.

2 This AD was posted on 17 May 2010 as PAD 10-045 for consultation

until 14 June 2010. No comments were received during the consultation

period.

3. Enquiries regarding this AD should be referred to the Airworthiness

Remarks: Directives, Safety Management & Research Section, Certification

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 AS, Saab Aerosystems, BrOderna Ugglas gala,

SE-581 88 Unkoping, Sweden

Telephone: +4613 185591, Fax: +4613184874

E-mail: technical. support@sal.saabgroup.com

EASA Form 110 Page 2J2