AD 95-14-03

This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11-200 and -400 series airplanes, that requires repetitive radiographic inspections to detect corrosion of the center torque shaft of the wing spoiler, and replacement, if necessary. This amendment is prompted by a report of the wing spoiler failing to retract fully after deployment, which caused the wing to drop significantly. Subsequent investigation revealed that the torque shaft assembly of the wing spoiler had failed due to severe corrosion. The actions specified by this AD are intended to prevent such failures, which can result in an adverse effect on controllability of the airplane.

Final rule

95-14-03 BRITISH AEROSPACE AIRBUS LIMITED (Formerly British Aerospace Commercial Aircraft Limited, British Aerospace Aircraft Group): Amendment 39-9295. Docket 94-NM-161-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 use the authority provided in paragraph (d) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD.

Compliance: Required as indicated, unless accomplished previously.

To prevent failure of the center torque shaft of the spoiler on the left and right wing, accomplish the following:

(a) Perform a radiographic inspection to detect internal corrosion of the center torque shaft on the left and right wing spoilers, in accordance with the Accomplishment Instructions of British Aerospace BAC 1-11 Alert Service Bulletin 27-A-PM6007, Issue 1, dated April 10, 1992, at the time specified in paragraph (a)(1) or (a)(2) of this AD, as applicable. If the date of installation of a center torque shaft cannot be determined, the radiographic inspection of that shaft must be accomplished within 9 months after the effective date of this AD.

(1) For the center torque shaft on the left wing spoiler: Inspect within 10 years after the date of installation of that center torque shaft, or within 9 months after the effective date of this AD, whichever occurs later.

(2) For the center torque shaft on the right wing spoiler: Inspect within 10 years after the date of installation of that center torque shaft, or within 9 months after the effective date of this AD, whichever occurs later.

(b) If no internal corrosion is detected, repeat the radiographic inspection required by paragraph (a) of this AD thereafter at intervals not to exceed 4 years.

(c) If any internal surface corrosion is detected, prior to further flight, replace that shaft assembly with either a used serviceable assembly or a new assembly, in accordance with British Aerospace Alert Service Bulletin 27-A-PM6007, Issue 1, dated April 10, 1992. Perform the radiographic inspection in accordance with that service bulletin at the applicable time specified in paragraph (c)(1) or (c)(2) of this AD.

(1)If a new shaft assembly is installed: Perform the inspection within 10 years after installation. Thereafter, repeat the inspection at intervals not to exceed 4 years.

(2) If a used serviceable shaft is installed: Prior to installation, perform an initial radiographic inspection of that shaft in accordance with the service bulletin. Thereafter, repeat the inspection at intervals not to exceed 4 years.

(d) 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.

(e) 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.

(f) The inspections and replacement shall be done in accordance with British Aerospace Alert Service Bulletin 27-A-PM6007, Issue 1, dated April 10, 1992. 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, 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.

(g) This amendment becomes effective on August 7, 1995.

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 26, 1995 (60 FR 20461). That action proposed to require repetitive radiographic inspections to detect corrosion of the center torque shaft of the wing spoiler, and replacement of the torque shaft assembly, if necessary.

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

The FAA estimates that 31 airplanes of U.S. registry will be affected by this AD, that it will take approximately 40 work hours per airplane to accomplish therequired actions, and that the average labor rate is $60 per work hour. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $74,400, or $2,400 per airplane.

Should an operator be required to accomplish the replacement of the torque shaft assembly, it will take approximately 40 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Required parts will cost approximately $2,950 per airplane. Based on these figures, the total cost impact of any necessary replacement action is estimated to be $5,350 per airplane.

The total 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.

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. App. 1354(a), 1421 and 1423; 49 U.S.C. 106(g); and 14 CFR 11.89.

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