AD 98-13-14

This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires repetitive rotating probe inspections of fastener holes and/or the adjacent tooling hole of a former junction of the aft fuselage, and corrective action, if necessary. This amendment also provides for optional terminating action for the repetitive inspections. 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 reduced structural integrity of the aft fuselage caused by fatigue cracking of the former junction at frame 68.

Final rule.

98-13-14 AIRBUS INDUSTRIE: Amendment 39-10602. Docket 97-NM-250-AD.

Applicability: Model A320 series airplanes, as listed in Airbus Service Bulletins A320-53-1089 and A320-53-1090, both dated November 22, 1995; on which Airbus Modifications 21780 and 21781 (reference Airbus Service Bulletin A320-53-1090) have not been installed; certificated in any category.

NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise 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 fatigue cracking of the former junction at frame 68, which could result in reduced structural integrity of the aft fuselage, accomplish the following:

(a) Prior to the accumulation of 20,000 total flight cycles, or within 500 flight cycles after the effective date of this AD, whichever occurs later, perform a rotating probe inspection for fatigue cracking of the fastener holes and/or the adjacent tooling hole, as applicable, of the right- and left-hand former junctions at frame 68, in accordance with Airbus Service Bulletin A320-53-1089, dated November 22, 1995.

(1) If no crack is detected, accomplish either paragraph (a)(1)(i) or (a)(1)(ii) of this AD.

(i) Repeat the inspection thereafter at intervals not to exceed 20,000 flight cycles. Or

(ii) Prior to further flight following the accomplishment of the inspection required by paragraph (a) of this AD, cold work the fastener holes and/or the adjacent tooling hole of the right- and left-hand former junctions at frame 68, as applicable, in accordance with Airbus Service Bulletin A320-53-1090, dated November 22, 1995. Accomplishment of this cold working constitutes terminating action for the repetitive inspections required by this AD.

(2) If any crack is detected, prior to further flight, repair it in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate.

(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.

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.

(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.

(d) Except as provided by paragraph (a)(2) of this AD, the actions shall be done in accordance with Airbus Service Bulletin A320-53-1089, dated November 22, 1995 and Airbus Service Bulletin A320-53-1090, dated November 22, 1995. 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 3: The subject of this AD is addressed in French airworthiness directive 96-298-093(B)R1, dated January 29, 1997.

(e) 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 certain Airbus Model A320 series airplanes was published in the Federal Register on April 20, 1998 (63 FR 19421). That action proposed to require repetitive rotating probe inspections of fastener holes and/or the adjacent tooling hole of a former junction of the aft fuselage, and corrective action, if necessary. That action also provided for optional terminating action for the repetitive inspections.

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

The commenters support the proposed rule. Conclusion

After careful review of the available data, including the comments noted above, 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 10 Airbus Model A320 series airplanes of U.S. registry will be affected by this AD.

Should an operator be required to accomplish the inspection of the fastener holes and the adjacent tooling hole, it will take approximately 8 work hours per airplane to accomplish this inspection, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of this inspection required by this AD on U.S. operators is estimated to be $480 per airplane, per inspection cycle.

Should an operator be required to accomplish the inspection of only the tooling hole, it will take approximately 3 work hours per airplane to accomplish this inspection, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of this inspection required by this AD on U.S. operators is estimated to be $180 per airplane, per inspection cycle.

The cost impact figures discussed above are 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.

Should an operator elect to accomplish the optional terminating action specified in this AD, it would take approximately 9 work hours to cold work the fastener holes and tooling hole, or 3 work hours to cold work (only) the tooling hole. The average labor rate is $60 per work hour. Based on these figures, the cost impact of the optional terminating action would be $540 per airplane for cold working the fastener hole and tooling holes, or $180 per airplane for cold working (only) the tooling hole. 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, itis 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: