AD 99-24-17

This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires modification of the airplane by coldworking fastener holes at the front and rear wing spars and by installing modified support angles for the lower trailing edge panel of the wing. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fatigue cracking in the lower spar cap of the wing rear spar and in the lower skin at the wing front spar, just outside the nacelle, on the left-hand and right-hand side of the airplane, which could result in fuel leakage and consequent fire in or around the wing.

Final rule

99-24-17 SAAB AIRCRAFT AB: Amendment 39-11442. Docket 99-NM-197-AD. Issued November 18, 1999.
Applicability: Model SAAB 2000 series airplanes, as listed in Saab Service Bulletin 2000-57-029, dated June 4, 1999; certificated in any category.

NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance: Required as indicated, unless accomplished previously.

To prevent fatigue cracking in the lower spar cap of the wing rear spar and in the lower skin at the wing front spar, just outside the nacelle, on the left-hand and right-hand side of the airplane, which could result in fuel leakage and consequent fire in or around the wing, accomplish the following:

(a) Prior to the accumulation of 13,000 total flight cycles, or within 500 flight cycles after the effective date of this AD, whichever occurs later, modify the airplane by coldworking the fastener holes at the front and rear wing spar (including all applicable nondestructive test and detailed visual inspections and repairs of holes) and installing modified support angles for the lower trailing edge panel of the wing, in accordance with the instructions of Saab Service Bulletin 2000-57-029, dated June 4, 1999.

(b) Where Saab Service Bulletin 2000-57-029, dated June 4, 1999, specifies that Saab be contacted for repair instructions for certain damage conditions, this AD requires that such damage conditions must be repaired in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Luftfartsverket (LFV) (or its delegated agent). For a repair method to be approved by the Manager, International Branch, ANM-116, as required by this paragraph, the Manager's approval letter must specifically reference this AD.

Alternative Methods of Compliance
(c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, International Branch, ANM-116, FAA. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.

Special Flight Permits
(d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.

Incorporation by Reference
(e) Except as provided by in paragraph (b) of this AD, the actions shall be done in accordance with Saab Service Bulletin 2000-57-029, dated June 4, 1999. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Saab Aircraft AB, SAAB Aircraft Product Support, S-581.88, Linkoping, Sweden. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

NOTE 3: The subject of this AD is addressed in Swedish airworthiness directive SAD 1-142, dated June 4, 1999.

(f) This amendment becomes effective on January 4, 2000.

FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager, International Branch, ANM-116, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2110; fax (425) 227-1149.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Saab Model SAAB 2000 series airplanes was published in the Federal Register on September 23, 1999 (64 FR 51486). That action proposed to require modification of the airplane by coldworking fastener holes at the front and rear wing spars and by installing modified support angles for the lower trailing edge panel of the wing.

Comments
Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were submitted in response to the proposal or the FAA's determination of the cost to the public.

Conclusion
The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

Cost Impact
The FAA estimates that 3 airplanes of U.S. registry will be affected by this AD, that it will take approximately 180 work hours per airplane to accomplish the actions, at an average labor rate of $60 per work hour. The manufacturer states that necessary parts will be provided at no cost to operators. Based on these figures, the cost impact of the this AD on U.S. operators is estimated to be $32,400, or $10,800 per airplane.

The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted.

Regulatory Impact
The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of aFederalism Assessment.

For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES."

List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:PART 39 - AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.

39.13 [Amended]
2. Section 39.13 is amended by adding the following new airworthiness directive: