AD 98-13-31

This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires repetitive visual inspections to detect discrepancies of the bushing installation of the aileron actuation fitting, and eventual installation of staked bushings in the fitting. Accomplishment of such installation terminates the repetitive inspections. This amendment also provides for an optional temporary preventive action, which, if accomplished, would allow the repetitive inspection intervals to be extended until the terminating action is accomplished. 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 failure of the fitting lugs due to vibration caused by loose bushings in the fittings, and consequent reduced controllability of the airplane.

Final rule

98-13-31 SAAB AIRCRAFT: Amendment 39-10622. Docket 97-NM-145-AD.
Applicability: Model SAAB 2000 series airplanes having serial numbers -002 through -023 inclusive, 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 (e) 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 failure of the fitting lugs, due to vibration caused by loose bushings in the aileron actuation fittings, which could result in reduced controllability of the airplane; accomplish the following:

(a) Within 100 flight hours after the effective date of this AD, inspect the bushing installations of the left-hand and right-hand aileron actuation fittings to detect any discrepancies, in accordance with Saab Service Bulletin 2000-57-014, Revision 02, dated February 11, 1997.

(1) If no discrepancy is found, repeat the inspection thereafter at intervals not to exceed 300 flight hours until the requirements of paragraph (b) of this AD have been accomplished. Accomplishment of the temporary preventive action specified in paragraph 2.E. of the Accomplishment Instructions of the service bulletin allows the repetitive inspections to be accomplished at intervals of 600 flight hours until the requirements of paragraph (b) of this AD have been accomplished.(2) If any discrepancy is found, prior to further flight, accomplish the requirements of either paragraph (a)(2)(i) or (a)(2)(ii) of this AD in accordance with the service bulletin.

(i) Except as specified in paragraph (c), accomplish the installation required by paragraph (b) of this AD. Accomplishment of this installation constitutes terminating action for the requirements of this AD. Or

(ii) Accomplish the temporary preventive action specified in paragraph 2.E. of the Accomplishment Instructions of the service bulletin. Thereafter, repeat the inspection required by paragraph (a) of this AD at intervals not to exceed 600 flight hours until the requirements of paragraph (b) of this AD have been accomplished.

(b) Except as specified in paragraph (c) of this AD, within 3,000 flight hours after the effective date of this AD, install the new staked bushings in the aileron actuation fitting in accordance with Saab Service Bulletin 2000-57-014, Revision 02, datedFebruary 11, 1997. Accomplishment of this installation terminates the requirements of this AD.

(c) If, during the accomplishment of the installation required by paragraph (a)(2)(i) or paragraph (b) of this AD, the diameter of the small hole of the fitting lug is found to be outside the limits specified in Saab Service Bulletin 2000-57-014, Revision 02, dated February 11, 1997, prior to further flight, repair it in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or the Luftfartsverket (or its delegated agent).

(d) As of the effective date of this AD, no person shall install on any airplane an aileron having part number, 7357995-843 (left-hand) or 7357995-844 (right-hand), unless it has been modified in accordance with paragraph (b) of this AD.

(e) 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. 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.

(f) 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.

(g) Except as provided in paragraph (c) of this AD, the actions shall be done in accordance with Saab Service Bulletin 2000-57-014, Revision 02, dated February 11, 1997. 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) No. 1-102R1, dated November 8, 1996.

(h) This amendment becomes effective on July 30, 1998.

FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager, International Branch, ANM-116, FAA, 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 December 11, 1997 (62 FR 65231). That action proposed to require repetitive visual inspections to detect discrepancies of the bushing installation of the aileron actuation fitting, and eventual installation of staked bushings in the fitting. Accomplishment of such installation terminates the repetitive inspections. That action also proposed to provide for an optional temporary preventive action, which, if accomplished, allows the repetitive inspection intervals to be extended until the terminating action is accomplished.

Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the comments received.

One commenter supports the proposedrule.

One commenter, the manufacturer, requests that the repair specified in paragraph (c) of the proposed rule be accomplished in accordance with Saab Service Bulletin 2000-57-014 or the commenter's Repair Statements. The commenter states that its Repair Statements are approved based on privileges granted by Luftfartsverket (LFV), which is the airworthiness authority for Sweden, as part of the production certificate for Model SAAB 2000 series airplanes.

The FAA concurs partially. The FAA does concur that it is appropriate to allow repairs in accordance with the service bulletin, since no repair is specified in the service bulletin for the condition specified in paragraph (c) of this AD. However, in light of the type of repair that would be required to address the identified unsafe condition, and in consonance with existing bilateral airworthiness agreements, the FAA has determined that a repair approved by the FAA, the LFV, or the LFV's delegated agent is acceptable for compliance with the AD.

Additionally, the FAA has included the phrase "prior to further flight" in paragraph (c) of the final rule. This phrase was omitted inadvertently from the proposal.

Conclusion
After careful review of the available data, including the comments noted above, the FAA has determined that air safety and the public interest require the adoption of the rule with the change previously described. The FAA has determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD.

Cost Impact
The FAA estimates that 1 airplane of U.S. registry will be affected by this AD.

The FAA estimates that it will take approximately 1 work hour to accomplish the required inspection, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the required inspection on the single U.S. operator is estimated to be $60 per airplane, per inspection cycle.

The FAA estimates that it will take approximately 4 work hours to accomplish the required installation, and that the average labor rate is $60 per work hour. Required parts will be provided by the manufacturer at no cost to the operator. Based on these figures, the cost impact of the required installation on the single U.S. operator is estimated to be $240 per airplane.

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

Should an operator elect to accomplish the optional temporary preventive action provided by this AD, it would take approximately 1 work hour to accomplish it, at an average labor rate of $60 per work hour. Required parts would be provided by the manufacturer at no cost to the operator. Based on these figures, the cost impact of the optional temporary preventive action would be $60 perairplane.

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 a Federalism 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: