AD 98-04-49

This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A320-111, -211, -212, -214, -231, -232, and -233 series airplanes, that requires repetitive ultrasonic inspections to detect fatigue cracking in the wing/fuselage joint cruciform fittings, and 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 fatigue cracks on the wing/fuselage joint cruciform fittings, which could result in reduced structural integrity of the wing/fuselage.

Final rule.

98-04-49 AIRBUS INDUSTRIE: Amendment 39-10360. Docket 97-NM-152-AD.

Applicability: Model A320-111, -211, -212, -214, -231, -232, and -233 series airplanes, all serial numbers, 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, unlessaccomplished previously.

To detect and correct fatigue cracks on the wing/fuselage joint cruciform fittings, which could result in reduced structural integrity of the wing/fuselage, accomplish the following:

(a) Prior to the accumulation of 28,000 total landings, or within 60 days after the effective date of this AD, whichever occurs later, perform an ultrasonic inspection to detect fatigue cracking in the wing/fuselage joint cruciform fittings, in accordance with Airbus Service Bulletin A320-57-1051, Revision 01, dated March 21, 1996.

(1) If no cracking is detected, repeat the inspection thereafter at intervals not to exceed 20,000 landings.

(2) If any crack is detected, prior to further flight, repair it in accordance with the service bulletin. Thereafter, repeat the inspection at the times specified in paragraph (a)(2)(i) or (a)(2)(ii) of this AD, as applicable.

(i) If the crack that was detected and repaired was greater than 2.5 mm: Repeat the inspection priorto the accumulation of 32,000 landings since accomplishment of the repair; and thereafter at intervals not to exceed 32,000 landings.

(ii) If the crack that was detected and repaired was less than or equal to 2.5 mm: Repeat the inspection prior to the accumulation of 28,000 landings since accomplishment of the repair; and thereafter at intervals not to exceed 20,000 landings.

(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 request 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) The actions shall be done in accordance with Airbus Service Bulletin A320-57- 1051, Revision 01, dated March 21, 1996, which contains the specified effective pages:

Page Number
Revision Level
Shown on Page
Date
Shown on Page
1-29, 31-37, 39-40
1
March 21, 1996
30, 38
Original
March 30, 1993

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 96-299- 094(B), dated December 18, 1996.

(e) This amendment becomes effective on April 3, 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 all Airbus Model A320-111, -211, -212, -214, -231, -232, and -233 series airplanes was published in the Federal Register on December 1, 1997 (62 FR 63476). That action proposed to require repetitive ultrasonic inspections to detect fatigue cracking in the wing/fuselage joint cruciform fittings, and corrective actions, if necessary.

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

All of 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 132 airplanes of U.S. registry will be affected by this AD, that it will take approximately 8 work hours per airplane to accomplish the required inspection, at an average labor rate of $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 $63,360, or $480 per airplane.

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: