AD 98-25-07

This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300-600 series airplanes, that requires repetitive inspections to detect cracks in the angle fitting at frame 40 of the center wing box, and corrective actions, if necessary; and eventual modification of that angle fitting, which terminates 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 cracks in the center wing box angle fitting, which could result in the failure of the center wing box at frame 40, and consequent reduced structural integrity of the airplane.

Final rule.

98-25-07 AIRBUS: Amendment 39-10933. Docket 97-NM-153-AD.

Applicability: Model A300-600 series airplanes on which Airbus Modification 10453 has 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 (e) 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 prevent cracks in the center wing box angle fitting, which could result in the failure of the center wing box at frame 40, and consequent reduced structural integrity of the airplane, accomplish the following:

(a) Prior to the accumulation of the threshold specified in Table 1 of this AD, as applicable, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later: Perform a detailed visual, eddy current, or liquid penetrant inspection to detect cracking in the angle fitting of frame 40 (both left and right), with the nut removed, in accordance with Airbus Service Bulletin A300-57-6052, Revision 1, dated July 22, 1996. Thereafter, repeat the inspections at the interval specified in Table 1 of this AD, as applicable, until the actions required by paragraph (c) of this AD have been accomplished.

Table 1.

Average flight time
(AFT):
Flight Hours/
Flight Cycles

Threshold
(Flight Cycles)

Visual
Inspection
Interval
(Flight Cycles)
Eddy Current/
Liquid Penetrant
Inspection
Interval
(Flight Cycles)
2.10-2.49
5,900
4,700
5,300
2.50-2.99
5,600
4,400
4,900
3.00-3.49
5,200
4,100
4,600
3.50-3.99
4,800
3,800
4,200
4.00-4.49
4,400
3,500
3,900
4.50-4.99
4,000
3,200
3,500
5.00-5.49
3,600
2,800
3,200
5.50-5.99
3,200
2,500
2,800
6.00-6.50
2,800
2,200
2,500

(b) Except as provided by paragraph (d) of this AD, if any crack is found during an inspection required by paragraph (a) of this AD, prior to further flight, accomplish follow-on corrective actions in accordance with the procedures specified in Airbus Service Bulletin A300-57-6052, Revision 1, dated July 22, 1996.

(c) Within 4 years after the effective date of this AD, modify the angle fitting at frame 40 (both left and right) in accordance with Airbus Service Bulletin A300-57-6053, Revision 1, dated October 31, 1995. Accomplishment of the modification constitutes terminating action for the repetitive inspections required by paragraph (a) of this AD.

(d) If any crack is found during an inspection required by paragraph (a) of 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.

(e) 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.

(f) Special flightpermits 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.

(g) Except as provided by paragraph (d) of this AD, the actions shall be done in accordance with Airbus Service Bulletin A300-57-6052, Revision 1, dated July 22, 1996; and Airbus Service Bulletin A300-57-6053, Revision 1, dated October 31, 1995, which contains the following list of effective pages:

Page Number
Revision Level
Shown on Page
Date
Shown on Page
1, 7-9, 11-15,
19-24, 35, 36,
41, 42, 45-47
1
October 31, 1995
2-6, 10, 16-18,
25-34, 37-40,
43, 44
Original
February 21, 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. Copiesmay 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 (CN) 95-111-181(B) R1, dated October 23, 1996.

(h) This amendment becomes effective on January 14, 1999.

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 A300-600 series airplanes was published as a supplemental notice of proposed rulemaking (NPRM) in the Federal Register on October 14, 1998 (63 FR 55063). That action proposed to require repetitive inspections to detect cracks in the angle fitting at frame 40 of the center wing box, and corrective actions, if necessary; and eventual modification of that angle fitting, which would terminate 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 single comment received. The commenter supports the proposed rule.

Conclusion
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.

Cost Impact
The FAA estimates that 54 Model A300-600 series airplanes of U.S. registry will be affected by this AD.

It will take approximately 36 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 $116,640, or $2,160 per airplane, per inspection cycle.

It will take approximately 754 work hours per airplane to accomplish the required modification, at an average labor rate of $60 per work hour. Required parts will cost approximately $11,605 per airplane. Based on these figures, the cost impact of the modification required by this AD on U.S. operators is estimated to be $3,069,630, or $56,845 per airplane.

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