AD 99-10-03

This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11 200 and 400 series airplanes, that requires an inspection to detect cracking of the flap control lever and to identify the material from which the lever is made; replacement of the flap control lever with an improved part, if necessary; and repetitive inspections for airplanes having a lever made from certain material. 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 flap control lever, which could result in restricted flap movement and consequent reduced controllability of the airplane.

Final rule

99-10-03 BRITISH AEROSPACE AIRBUS LIMITED (Formerly British Aerospace Commercial Aircraft Limited, British Aerospace Aircraft Group): Amendment 39-11157. Docket 98-NM-307-AD.
Applicability: All Model BAC 1-11 200 and 400 series airplanes, 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 (b) 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 toaddress it.

Compliance: Required as indicated, unless accomplished previously.

To prevent failure of the flap control lever, which could result in restricted flap movement and consequent reduced controllability of the airplane, accomplish the following:

(a) Within 12 months after the effective date of this AD, perform a one-time detailed visual inspection of the flap control lever to detect cracking, and to identify the type of aluminum alloy from which the flap control lever is made, in accordance with British Aerospace Alert Service Bulletin 27-A-PM6041, Issue 1, dated August 21, 1998.

(1) If no crack is detected and the lever is made of L97 or L99 aluminum alloy, no further action is required by this AD.

(2) If no crack is detected, and the lever is made of L53 aluminum alloy or the material of the flap control lever cannot be identified, repeat the inspection thereafterat intervals not to exceed 24 months; or prior to further flight, replace the flap control lever with a flap control lever made of L97 or L99 aluminum alloy, in accordance with the alert service bulletin. Following such replacement, no further action is required by this AD.

(3) If any crack is detected, prior to further flight, replace the flap control lever with a flap control lever made of L97 or L99 aluminum alloy, in accordance with the alert service bulletin. After the replacement, no further action is required by this AD.

Alternative Methods of Compliance

(b) 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.

NOTE2: 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

(c) 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

(d) The inspections and replacement shall be done in accordance with British Aerospace Alert Service Bulletin 27-A-PM6041, Issue 1, dated August 21, 1998. 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 British Aerospace, Service Support, Airbus Limited, P.O. Box 77, Bristol BS99 7AR, England. 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 British airworthiness directive 003-08-98.

(e) This amendment becomes effective on June 9, 1999.

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 all British Aerospace Model BAC 1-11 200 and 400 series airplanes was published in the Federal Register on February 18, 1999 (64 FR 8027). That action proposed to require an inspection to detect cracking of the flap control lever and to identify the material from which the lever is made; replacement of the flap control lever with an improved part, if necessary; and repetitive inspections for airplanes having a lever made from certain material.

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 42 airplanes of U.S. registry will be affected by this AD, that it will take approximately 1 work hour per airplane to accomplish the required actions, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $2,520, or $60 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 towarrant 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: