AD 98-20-13

This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes, that requires repetitive inspections to detect corrosion on the fuselage skin panels that surround the emergency exits immediately aft of the wing; and follow-on corrective actions, 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 corrosion on the fuselage skin panels that surround the emergency exits immediately aft of the wing, which could result in reduced structural integrity of the fuselage pressure vessel.

Final rule.

98-20-13 AIRBUS INDUSTRIE: Amendment 39-10780. Docket 98-NM-169-AD.

Applicability: Model A300 series airplanes, as listed in Airbus Industrie Service Bulletin A300-53-301, Revision 1, dated February 20, 1997; 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 to address it.

Compliance: Required as indicated, unless accomplished previously.

To detect and correct corrosion on the fuselage skin panels that surround the emergency exits immediately aft of the wing, which could result in reduced structural integrity of the fuselage pressure vessel, accomplish the following:

(a) Within 18 months after the effective date of this AD, perform a visual inspection to detect corrosion on the fuselage skin panels that surround the emergency exits immediately aft of the wing, between frames 55 to 58, and from stringers 13 to 31, left and right; in accordance with Airbus Industrie Service Bulletin A300-53-301, dated September 28, 1995, or Revision 1, dated February 20, 1997.

(1) If no corrosion is detected, repeat the inspection thereafter at intervals not to exceed 18 months on all areas on the fuselage skin panels that do not have a doubler installed or areas that have not been partially or completely replaced.

(2) If any corrosion is detected, prior to furtherflight, accomplish rework and perform a residual thickness measurement, in accordance with the service bulletin.

(i) If the measurement does not exceed the allowable limits specified by the Accomplishment Instructions of the service bulletin, repeat the inspection thereafter at intervals not to exceed 18 months.

(ii) If the measurement does exceed the allowable limits specified by the Accomplishment Instructions of the service bulletin, prior to further flight, repair using a doubler, or replace the affected areas of the skin panel the installation of a new skin panel (partially or completely), in accordance with the service bulletin. Accomplishment of either action constitutes terminating action for the repetitive inspections required by this AD for the repaired area or the replaced panel sections only.

NOTE 2: Inspections, repairs, and replacements of the fuselage skin panels that surround the emergency exits immediately aft of the wing that have been accomplished priorto the effective date of this AD, in accordance with Airbus Industrie Service Bulletin A300-53-301, dated September 28, 1995, are considered acceptable for compliance with the applicable action specified in this AD.

(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, 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, International Branch, ANM-116.

NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.

(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 locationwhere the requirements of this AD can be accomplished.

(d) The actions shall be done in accordance with Airbus Industrie Service Bulletin A300-53-301, dated September 28, 1995, or Airbus Industrie Service Bulletin A300-53-301, Revision 1, dated February 20, 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 Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. 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 4: The subject of this AD is addressed in French airworthiness directive 97-357- 231(B), dated November 19, 1997.

(e) This amendment becomes effective on October 27, 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 certain Airbus Model A300 series airplanes was published in the Federal Register on July 31, 1998 (63 FR 40850). That action proposed to require repetitive inspections to detect corrosion on the fuselage skin panels that surround the emergency exits immediately aft of the wing; and follow-on corrective actions, 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 24 airplanes of U.S. registry will be affected by this AD, that it will take approximately 2 work hours 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 $2,880, or $120 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: