AD 98-12-05 ACTIVE

This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A320-111 series airplanes. This amendment requires repetitive inspections to detect cracking around the attachment holes for the access panels in the lower skin of the wing; and repair, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect and correct such cracking, which could result in reduced structural integrity of the airplane.

Direct final rule; confirmation of effective date.

98-12-05 AIRBUS INDUSTRIE: Amendment 39-10410. Docket 98-NM-22-AD.

Applicability: Model A320-111 series airplanes, as identified in Airbus Service Bulletin A320-57-1056, Revision 1, dated July 15, 1997, including Appendix 1; 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 actions to address it.

Compliance: Required as indicated, unless accomplished previously.

To detect and correct cracking around the attachment holes for the access panels in the lower skin of the wing, between ribs 13 and 22 (skin panel number 2, left and right sides), which could result in reduced structural integrity of the airplane, accomplish the following:

(a) Prior to the accumulation of 20,000 total flight cycles, or within 60 days after the effective date of this AD, whichever occurs later: Perform a high frequency eddy current inspection to detect cracking around the attachment holes for the access panels in the lower skin of the wing, between ribs 13 and 22; in accordance with Airbus Service Bulletin A320-57-1056, Revision 1, dated July 15, 1997, including Appendix 1. Thereafter, repeat the inspection at intervals not to exceed 15,000 flight cycles.

(b) If any crack is detected during any inspection required by this AD, and the applicable service bulletin specifies to contact the manufacturer for an appropriate action: Prior to further flight, repair 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 actions shall be done in accordance with Airbus Service Bulletin A320-57-1056, Revision 1, dated July 15, 1997, including Appendix 1. 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 97-083-096(B), dated March 12, 1997.

(f) This amendment becomes effective on June 18, 1998.

The FAA published this direct final rule with request for comments in the Federal Register on March 20, 1998 (63 FR 13508). The FAA uses the direct final rulemaking procedure for a non-controversial rule where the FAA anticipates that there will be no adverse public comment. This direct final rule advised the public that no adverse comments were anticipated, and that unless a written adverse comment, or a written notice of intent to submit such an adverse comment, was received within the comment period, the regulation would become effective on June 18, 1998.

Two comments were received. Both commenters support the rule. However, one of the commenters requests clarification of the applicability of the rule, which is stated in the direct final rule as follows:

"Applicability: Model A320-111 series airplanes, as identified in Airbus Service Bulletin A320-57-1056, Revision 1, dated July 15, 1997, including Appendix 1; certificated in any category."The commenter notes that when an operator is not affected by a service bulletin, that operator only receives a copy of the summary section of the service bulletin. The summary of a service bulletin provides a list of affected operators; it does not provide manufacturer s serial numbers for the affected airplanes. This results in difficulty for an operator, a leasing group, or other non-technical group to evaluate any pending or applicable rules against a specific airplane serial number. Therefore, the commenter proposes that the applicability of the rule reference specific serial numbers for affected airplanes, as follows.

"Applicability: Model A320 series airplanes having manufacturer s serial numbers 002 through 008 inclusive; 010 through 014 inclusive; and 016 through 018 inclusive; certificated in any category."

The FAA concurs that this AD applies to the airplanes identified by the commenter. The applicability, as presented in the rule, is equivalent to the applicability suggested by the commenter. Therefore, the FAA finds that no change to the rule is necessary. As the commenter points out, those operators that are affected by the rule will receive the entire service bulletin (not just the summary) and will, therefore, be informed of the specific serial numbers to which this AD applies.

The same commenter also requests clarification of the cost impact information. The commenter notes that this information specifies that there are 118 Model A320-111 airplanes of U.S. registry. The commenter indicates that only 22 Model A320-100 series airplanes were manufactured, and that none of these are on the U.S. Register. The commenter believes that the number 118 reflects all Model A319 and A320 airplanes on the U.S. Register, and not the actual number of Model A320-100 series airplanes. The commenter adds that Model A319-100 series airplanes are being manufactured, and are on the U.S. Register, but are not considered to be Model A320-100 series airplanes.

The FAA concurs with the clarification provided by the commenter. The number of airplanes affected by the direct final rule reflects the FAA s estimation of the total number of Airbus Model A319, A320, and A321 series airplanes currently on the U.S. register. However, no change to the direct final rule is necessary, since it indicates that none of the affected airplanes are on the U.S. Register.

No adverse comments were received, and thus this notice confirms that this final rule will become effective on that date.

Issued in Renton, Washington, on May 27, 1998.

Norman B. Martenson, Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2110; fax (425) 227-1149.