AD 98-13-26

This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11 200 and 400 series airplanes, that requires repetitive detailed visual inspections to detect cracking in the trunnion fittings located in the nose landing gear (NLG) bay of the forward fuselage; and repair, if necessary. 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 detect and correct cracking in the trunnion fittings of the NLG, which could lead to collapse of the NLG during takeoff and landing, and possible injury to the flight crew and passengers.

Final rule

98-13-26 BRITISH AEROSPACE AIRBUS LIMITED (Formerly British Aerospace Commercial Aircraft Limited, British Aerospace Aircraft Group): Amendment 39-10617. Docket 98-NM-51-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 (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 actionsto address it.

Compliance: Required as indicated, unless accomplished previously.

To detect and correct cracking in the trunnion fittings of the nose landing gear (NLG), which could lead to collapse of the NLG during takeoff and landing, and possible injury to the flight crew and passengers, accomplish the following:

(a) Perform a detailed visual inspection for cracking on the left- and right-hand trunnion fittings of the NLG, in the area of the trunnion cap attachment holes, in accordance with British Aerospace Alert Service Bulletin 53-A-PM6035, Revision 1, dated March 7, 1996; at the time specified in paragraph (a)(1) or (a)(2) of this AD, as applicable.

(1) For airplanes on which British Aerospace Modification PM5308 has not been accomplished: Perform the inspection within 6 years after the effective date of this AD, or within 11 years after the last inspection accomplished in accordance with the alert service bulletin, whichever occurs later. Repeat the inspection thereafter at intervals not to exceed 11 years.

(2) For airplanes on which British Aerospace Modification PM5308 has been accomplished: Perform the inspection within 30 months after the effective date of this AD, or within 5 years after the last inspection accomplished in accordance with the alert service bulletin, whichever occurs later. Repeat the inspection thereafter at intervals not to exceed 6 years.

(b) If any crack is found during any inspection required by paragraph (a) of this AD, prior to further flight, repair the crack in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate.

(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. 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.

(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.

(e) The inspections shall be done in accordance with British Aerospace Alert Service Bulletin 53-A-PM6035, Revision 1, dated March 7, 1996. 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 004-03-96, dated April 26, 1996.

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

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 April 21, 1998 (63 FR 19682). That action proposed to require repetitive detailed visual inspections to detect cracking in the trunnion fittings located in the nose landing gear (NLG) bay of the forward fuselage; and repair, if necessary.

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 approximately1 work hour per airplane 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 inspection required by this AD on U.S. operators is estimated to be $2,520, or $60 per airplane, per inspection cycle.

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 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: