AD 99-19-38

This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires repetitive high frequency eddy current inspections to detect fatigue cracking at the hole in the lower web of the inner and outer attachment fittings of the number 3 wing spoilers; and corrective actions, if necessary. This amendment also provides for an optional modification, 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 detect and correct fatigue cracking and eventual failure of the attachment fittings of the number 3 wing spoilers.

Final rule.

99-19-38 AIRBUS INDUSTRIE: Amendment 39-11325. Docket 99-NM-91-AD.

Applicability: Model A310 series airplanes, on which Airbus Industrie Modification 04117 or 04799 has been installed in production; except those airplanes on which Airbus Industrie Modification 11929 (reference Airbus Industrie Service Bulletin A310-57-2079, dated July 21, 1998, or Revision 01, dated January 11, 1999) has 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 detect and correct fatigue cracking and eventual failure of the attachment fittings of the number 3 wing spoilers, which, if left undetected, could lead to fuel leaks and loss of various hydraulic and electrical systems, accomplish the following:

Inspection
(a) At the applicable compliance time specified in paragraph (a)(1), (a)(2), or (a)(3) of this AD, perform a high frequency eddy current inspection to detect fatigue cracking at the hole in the lower web of the inner and outer attachment fittings of the number 3 wing spoilers, in accordance with Airbus Industrie Service Bulletin A310-57-2078, Revision 01, dated January 11, 1999. Repeat the inspection thereafter at intervals not to exceed 1,200 flight cycles.

(1) For airplanes that have accumulated 14,200 or fewer total flight cycles as of the effective date of this AD, accomplish the inspection required by paragraph (a) of this AD prior to the accumulation 10,800 total flight cycles or within 800 flight cycles after the effective date of this AD, whichever occurs later.

(2) For airplanes that have accumulated more than 14,200 total flight cycles but fewer than 15,400 total flight cycles as of the effective date of this AD, accomplish the inspection required by paragraph (a) of this AD within 400 flight cycles after the effective date of this AD.

(3) For airplanes that have accumulated 15,400 or more total flight cycles as of the effective date of this AD, accomplish the inspection required by paragraph (a) of this AD within 200 flight cycles after the effective date of this AD.

NOTE 2: Inspection of the attachment fittings of the number 3 wing spoilers accomplished prior to the effective date of this AD in accordance with the original issue of Airbus Industrie Service Bulletin A310-57-2078, dated July 21, 1998, is considered acceptable for compliance with the inspection required by paragraph (a) of this AD.

Replacement
(b) If any crack is found during any inspection required by paragraph (a) of this AD, at the applicable compliance time specified in paragraph (b)(1), (b)(2), or (b)(3) of this AD, perform a high frequency eddy current inspection for fatigue cracking of the holes in the wing structure; ream and cold work those holes; and replace the cracked aluminum wing spoiler number 3 actuator attachment fitting with a new steel fitting; in accordance with Airbus Industrie Service Bulletin A310-57-2079, Revision 01, dated January 11, 1999. Accomplishment of the replacement constitutes terminating action for the repetitive inspection requirements of paragraph (a) of this AD for the replaced fitting.

(1) If the crack is less than 0.078 inches (2.0 mm) in length, inspect, ream, cold work, andreplace within 100 flight cycles after accomplishment of the inspection.

(2) If the crack is 0.078 inches (2.0 mm) in length or greater and less than 0.118 inches (5.0 mm) in length, inspect, ream, cold work, and replace within 50 flight cycles after accomplishment of the inspection.

(3) If the crack is greater than 0.118 inches (5.0 mm) in length, inspect, ream, cold work, and replace prior to further flight.

Optional Terminating Modification
(c) Accomplishment of the high frequency eddy current inspection for fatigue cracking of the holes in the wing structure; reaming and cold working of those holes; and replacement of all aluminum wing spoiler number 3 actuator attachment fittings with new steel fittings; in accordance with Airbus Industrie Service Bulletin A310-57-2079, Revision 01, dated January 11, 1999; constitutes terminating action for the repetitive inspection requirements of paragraph (a) of this AD.

NOTE 3: Replacement of aluminum attachment fittings ofthe number 3 wing spoilers with steel fittings accomplished prior to the effective date of this AD in accordance with the original issue of Airbus Industrie Service Bulletin A310-57-2079, dated July 21, 1998, is considered acceptable for compliance with the applicable fitting replacement specified in paragraphs (b) and (c) of this AD.

Wing Repair
(d) If any crack is found in the wing structure during any inspection required by paragraph (b) or specified in paragraph (c) of this AD, prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction G n rale de l'Aviation Civile (DGAC) (or its delegated agent). For a repair method to be approved by the Manager, International Branch, ANM-116, as required by this paragraph, the Manager's approval letter must specifically reference this AD.

NOTE 4: For paragraph (d) of this AD, the wing spoiler number 3 actuator attachment fittings are not considered part of the wing structure.

Alternative Methods of Compliance
(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 5: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.

Special Flight Permits
(f) 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.

Incorporation by Reference
(g) Except as provided by paragraph (d) of this AD, the actions shall be done in accordance with Airbus Industrie Service Bulletin A310-57-2078, Revision 01, dated January 11, 1999; or Airbus Industrie Service Bulletin A310-57-2079, Revision 01, dated January 11, 1999; as applicable. 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 6: The subject of this AD is addressed in French airworthiness directive 98-483- 271(B) R1, dated June 2, 1999.

(h) This amendment becomes effective on October 27, 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 A310 series airplanes was published in the Federal Register on July 23, 1999 (64 FR 39946). That action proposed to require repetitive high frequency eddy current inspections to detect fatigue cracking at the hole in the lower web of the inner and outer attachment fittings of the number 3 wing spoilers; and corrective actions, if necessary. That action also provides for an optional modification, which would terminate the repetitive inspections.

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.

Conclusion
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 44 airplanes of U.S. registry will be affected by this AD, that it will take approximately 2 work hours per airplane to accomplish the required inspection, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the required AD on U.S. operators is estimated to be $5,280, or $120 per airplane, per inspection cycle.

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.

Should an operator elect to accomplish the optional terminating action rather than continue the repetitive inspections, it would take approximately 110 work hours per airplane to accomplish the modification, at an average labor rate of $60 per work hour. Required parts will cost approximately $13,280 per airplane. Based on these figures, the cost impact of this optional terminating action is estimated to be $19,880 per airplane.

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: