AD 98-04-10

This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 and A300-600 series airplanes, that requires repetitive inspections for cracking of the lugs of hinge brackets of inner airbrakes (spoilers) No. 1 and No. 2, and corrective action, if necessary. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent detachment of the spoilers and consequent reduced controllability of the airplane.

Final rule.

98-04-10 AIRBUS INDUSTRIE: Amendment 39-10323. Docket 97-NM-240-AD.

Applicability: All Model A300 and A300-600 series airplanes, 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 of the lugs of hinge brackets of inner airbrakes (spoilers) No. 1 and No. 2 of both wings, which could result in detachment of the spoilers and consequent reduced controllability of the airplane, accomplish the following:

(a) Perform a high frequency eddy current (HFEC) inspection for cracking of the lugs of the center hinge brackets of spoilers No. 1 and No. 2, in accordance with Airbus Service Bulletin A300-57-0229 (for Model A300 series airplanes) or A300-57-6074 (for Model A300-600 series airplanes), both dated October 16, 1996, as applicable. Accomplish the inspection at the time specified in paragraph (a)(1), (a)(2), or (a)(3), as applicable, of this AD. If any discrepancy is found, prior to further flight, perform the follow-on actions specified in the Accomplishment Instructions of the applicable service bulletin. Repeat the HFEC inspection thereafter at intervals not to exceed 8,200 flight cycles.

(1) For airplanes that have accumulated less than 23,200total flight cycles as of the effective date of this AD: Inspect prior to the accumulation of 16,000 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever occurs later.

(2) For airplanes that have accumulated 23,200 total flight cycles or more, but less than 36,500 total flight cycles as of the effective date of this AD: Inspect within 500 flight cycles after the effective date of this AD.

(3) For airplanes that have accumulated 36,500 total flight cycles or more as of the effective date of this AD: Inspect within 50 flight cycles after the effective date of this AD.

(b) Airbus Service Bulletins A300-57-6074 and A300-57-0229, both dated October 16, 1996, specify that the actions required by paragraph (a) of this AD may be accomplished in accordance with a method "left to the operator's discretion." [Operators may use a discretionary method only if that method has been approved as an alternative method of compliance in accordance with paragraph (c) of this AD.] Therefore, this AD requires that the replacement of a bracket as required by paragraph (a) be accomplished in accordance with the procedures specified in British Aerospace Repair Drawings (for Airbus Model A300 and A300- 600 series airplanes) R572-40205, Revision F, dated August 12, 1997 (for a center hinge bracket), and/or R572-40208, Revision B, dated August 12, 1997 (for an inner or outer hinge bracket), as applicable.

(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, 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 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 inspections shall be done in accordance with Airbus Service Bulletin A300-57-0229, dated October 16, 1996, or Airbus Service Bulletin A300-57-6074, dated October 16, 1996; as applicable. The replacement shall be done in accordance with the following British Aerospace Repair, as applicable, which contain the specified list of effective pages:

Repair Drawings
Referenced and Date

Sheet Number
Revision Level
Shown on Sheet
Date
Shown on Sheet
572-40205,
Revision F,
August 12, 1997
1, 8, 13-15

2-7, 9-12
F

A
August 12, 1997

March 6, 1996
572-40208,
Revision B,
August 12, 1997
1, 6, 8-10

2-5, 7
B

A
August 12, 1997

February 21, 1996This 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 97-080-211(B)R1, dated May 21, 1997.

(f) This amendment becomes effective on March 24, 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 A300 and A300-600 series airplanes was published in the Federal Register on November 6, 1997 (62 FR 60047). That action proposed to require repetitive inspections for cracking of the lugs of hinge brackets of inner airbrakes (spoilers) No. 1 and No. 2, and corrective action, 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.

Clarification of Referenced Repair Drawings
The FAA has revised paragraph (b) of this final rule to clarify the referenced repair drawings by adding the company name, the applicable revision level, and the date of the drawings.

Conclusion
After careful review of the available data, including the clarification noted above, the FAA has determined that air safety and the public interest require the adoption of the rule with the changes previously described. The FAA has determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD.

Cost Impact
The FAA estimates that 102 Model A300 and A300-600 series airplanes of U.S. registry will be affected by this AD, that it will take approximately 4 work hours per airplane to accomplish the required actions, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $24,480, or $240 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: