AD 95-19-12 ACTIVE

This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11 200 and 400 series airplanes, that requires various repetitive inspections to detect cracks in certain panels of the lower skin of the wing, and in certain fixed ribs of the leading edge of the wing. This amendment also requires repair or replacement of cracked parts, which would terminate certain repetitive inspections. This amendment is prompted by reports of cracking in certain panels of the lower skin of the wing, and in certain fixed ribs of the leading edge of the wing due to fatigue-related stress. The actions specified by this AD are intended to ensure the structural integrity of the wing by detecting fatigue-related cracking in a timely manner in the panels of the lower skin of the wing or in the fixed ribs of the leading edge of the wing.

Final rule

95-19-12 BRITISH AEROSPACE AIRBUS LIMITED (Formerly British Aerospace Commercial Aircraft Limited, British Aerospace Aircraft Group): Amendment 39-9374. Docket 94-NM-184-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 changedconfiguration 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 ensure the structural integrity of the wing, accomplish the following:

(a) Prior to the accumulation of 12,000 total landings or within 1,500 landings after the effective date of this AD, whichever occurs later, perform a close visual and dye penetrant inspection to detect cracks in panel number 1 at rib 6 and in panel number 2 at rib 10 of the lower skin of the wing, in accordance with British Aerospace Alert Service Bulletin 57-A-PM5992, Issue 1, dated October 14, 1992.

(1) If no crack is detected, repeat the inspections thereafter at intervals not to exceed 8,000 landings.

(2) If any crack is detected at rib 6, prior to further flight, repair panel number 1 in accordance with the alert service bulletin. Accomplishment of this repair constitutes terminating action for the repetitive inspections of panel number 1 as required by this paragraph.

(3) If any crack is detected at rib 10, prior to further flight, repair panel number 2 in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.

(b) Prior to the accumulation of 30,000 total landings or within 1,500 landings after the effective date of this AD, whichever occurs later, perform an eddy current inspection to detect cracks in the rebate radius of panel number 2 at the joint between panels 1 and 2 of the lower skin of the wing, in accordance with British Aerospace Alert Service Bulletin 57-A-PM5992, Issue 1, dated October 14, 1992.

(1) If no crack is detected, repeat the inspection thereafter at intervals not to exceed 8,000 landings.

(2) If any crack is detected, prior to further flight, repair panel number 2 in accordance with the alert service bulletin. Accomplishment of this repair constitutes terminating action for the repetitive inspections of panel number 2 as required by this paragraph.

(c) Prior to the accumulation of 30,000 total landings or within 1,500 landings after the effective date of this AD, whichever occurs later, perform a close visual inspection to detect cracks in the top and bottom flanges of fixed ribs 6, 10, and 14 of the leading edge of the wing, in accordance with British Aerospace Alert Service Bulletin 57-A-PM5992, Issue 1, dated October 14, 1992.

(1) If no crack is detected, repeat the inspection thereafter at intervals not to exceed 8,000 landings.

(2) If any crack is detected, prior to further flight, replace the cracked rib with a new rib, in accordance with the alert service bulletin. Prior to the accumulation of 30,000 total landings on the newly installed rib, perform a close visual inspection to detect cracks on the newly installed rib in accordance with the servicebulletin. Repeat the inspection thereafter at intervals not to exceed 8,000 landings.

(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, certain repairs, and replacement shall be done in accordance with British Aerospace Alert Service Bulletin 57-A-PM5992, Issue 1, dated October 14, 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 October 20, 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 June 9, 1995 (60 FR 30474). That action proposed to require various repetitive inspections to detect cracks in panel number 1 at rib 6 and in panel number 2 at rib 10 of the lower skin of the wing, in the rebate radius of panel number 2 at the joint between panels 1 and 2 of the lower skin of the wing, and in the top and bottom flanges of fixed ribs 6, 10, and 14 of the leading edge of the wing. That action also proposed to require repair or replacement of cracked parts, which constitutes terminating action for certain repetitive inspection requirements.

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

The commenter supports the proposed rule.

After careful review of the available data, including the comment noted above, 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 14 work hours per airplane to accomplish the required 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 $26,040, or $840 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 USC 106(g), 40101, 40113, 44701.

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

The service information referenced in this AD may be obtained from British Aerospace, Airbus Limited, P.O. Box 77, Bristol BS99 7AR, England. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

William Schroeder, Aerospace Engineer, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 227-2148; fax (206) 227-1149.