AD 2000-05-07

This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300 and A300-600 series airplanes, that currently requires repetitive inspections to detect cracks in Gear Rib 5 of the main landing gear (MLG) attachment fittings at the lower flange, and repair, if necessary. That AD also requires modification of Gear Rib 5 of the MLG attachment fittings, which constitutes terminating action for the repetitive inspections. This amendment expands the current inspection area for certain airplanes. 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 fatigue cracking of the MLG attachment fittings, which could result in reduced structural integrity of the airplane.

Final rule

2000-05-07 AIRBUS INDUSTRIE: Amendment 39-11616. Docket 99-NM-337-AD. Supersedes AD 99-19-26, Amendment 39-11313.

Applicability: Model A300 series airplanes, as listed in Airbus Service Bulletin A300-57-0234, Revision 01, dated March 11, 1998; and Model A300-600 series airplanes, as listed in Airbus Service Bulletin A300-57-6087, Revision 01, dated March 11, 1998; except airplanes on which Airbus Modification 11912 has been installed in production, or on which Airbus Modification 11932 has been accomplished; 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 (d)(1) 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 fatigue cracking of the main landing gear (MLG) attachment fittings, which could result in reduced structural integrity of the airplane, accomplish the following:

Repetitive Inspections
(a) Perform a detailed visual and a high frequency eddy current (HFEC) inspection to detect cracks in Gear Rib 5 of the MLG attachment fittings at the lower flange, in accordance with Airbus Service Bulletin A300-57-6087, Revision 01, dated March 11, 1998 (for Model A300-600 series airplanes); or A300-57-0234, Revision 01, dated March 11, 1998 (for Model A300 series airplanes); as applicable; at the time specified in paragraph (a)(1) or (a)(2) of this AD, as applicable. After the effective date of this AD, only Airbus Service Bulletin A300-57A0234, Revision 02, dated June 24, 1999, or Revision 03, including Appendix 01, dated September 2, 1999 (for Model A300 series airplanes); or A300-57A6087, Revision 02, including Appendix 01, dated June 24, 1999 (for Model A300-600 series airplanes); as applicable; shall be used. Repeat the inspections thereafter at intervals not to exceed 1,500 flight cycles.

Detailed Visual Inspection
NOTE 2: For the purposes of this AD, a detailed visual inspection is defined as: "An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required."

(1) For airplanes that have accumulated 20,000 or more total flight cycles as of March 9, 1998: Inspect within 500 flight cycles after March 9, 1998.

(2) For airplanes that have accumulated less than 20,000 total flight cycles as of March 9, 1998: Inspect prior to the accumulation of 18,000 total flight cycles, or within 1,500 flight cycles after March 9, 1998, whichever occurs later.

NOTE 3: Accomplishment of the initial detailed visual and HFEC inspections in accordance with Airbus Service Bulletin A300-57A0234 or A300-57A6057, both dated August 1, 1997, as applicable, is considered acceptable for compliance with the initial inspections required by paragraph (a) of this AD.

Repair
(b) If any crack is detected during any inspection required by this AD, prior to further flight, accomplish the requirements of paragraphs (b)(1) or (b)(2) of this AD, as applicable.

(1) If a crack is detected at one hole only, and the crackdoes not extend out of the spotface of the hole, repair in accordance with Airbus Service Bulletin A300-57A0234, Revision 02, dated June 24, 1999, or Revision 03, including Appendix 01, dated September 2, 1999 (for Model A300 series airplanes); or A300-57A6087, Revision 02, including Appendix 01, dated June 24, 1999 (for Model A300-600 series airplanes); as applicable.

(2) If a crack is detected at more than one hole, or if any crack at any hole extends out of the spotface of the hole, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or the Direction G n rale de l'Aviation Civile (or its delegated agent).

Terminating Modification
(c) Prior to the accumulation of 21,000 total flight cycles, or within 2 years after October 20, 1999 (the effective date of AD 99-19-26, amendment 39-11313), whichever occurs later: Modify Gear Rib 5 of the MLG attachment fittings at the lower flange in accordance with Airbus Service Bulletin A300-57-6088, Revision 01, including Appendix 01 (for Model A300-600 series airplanes), or A300-57-0235, Revision 01, including Appendix 01 (for Model A300 series airplanes), all dated February 1, 1999, as applicable. Accomplishment of this modification constitutes terminating action for the repetitive inspection requirements of this AD.

NOTE 4: Accomplishment of the modification required by paragraph (d) of this AD prior to the effective date of this AD in accordance with Airbus Service Bulletin A300-57-6088 or A300-57-0235, both dated August 1, 1998; as applicable; is acceptable for compliance with the requirements of that paragraph.

Alternative Methods of Compliance
(d) (1) 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 anappropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116.

(2) Alternative methods of compliance, approved previously in accordance with AD 99-19-26, amendment 39-11313, are approved as alternative methods of compliance with this AD.

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
(e) 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
(f) Except as provided by paragraph (b)(2) of this AD, the actions shall be done in accordance with Airbus Service Bulletin A300-57-6087, Revision 01, dated March 11, 1998; Airbus Service Bulletin A300-57A6087, Revision 02, including Appendix 01, dated June 24, 1999; Airbus Service Bulletin A300-57-0234, Revision 01, dated March 11, 1998; Airbus Service Bulletin A300-57A0234, Revision 02, dated June 24, 1999; Airbus Service Bulletin A300-57A0234, Revision 03, including Appendix 01, dated September 2, 1999; Airbus Service Bulletin A300-57-6088, Revision 01, including Appendix 01, dated February 1, 1999; and Airbus Service Bulletin A300-57-0235, Revision 01, including Appendix 01, dated February 1, 1999; as applicable.

(1) The incorporation by reference of Airbus Service Bulletin A300-57A6087, Revision 02, including Appendix 01, dated June 24, 1999; Airbus Service Bulletin A300-57A0234, Revision 02, dated June 24, 1999; and Airbus Service Bulletin A300-57A0234, Revision 03, including Appendix 01, dated September 2, 1999; is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.

(2) The incorporation by reference of Airbus Service Bulletin A300-57-6087, Revision 01, dated March 11, 1998; Airbus Service Bulletin A300-57-0234, Revision 01, dated March 11, 1998; Airbus Service Bulletin A300-57-6088, Revision 01, including Appendix 01, dated February 1, 1999; and Airbus Service Bulletin A300-57-0235, Revision 01, including Appendix 01, dated February 1, 1999; was approved previously by the Director of the Federal Register as of October 20, 1999 (64 FR 49966, September 15, 1999).

(3) 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 1998-151-247(B), dated June 16, 1999.

(g) This amendment becomes effective on April 12, 2000.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) by superseding AD 99-19-26, amendment 39-11313 (64 FR 49966, September 15, 1999), which is applicable to certain Airbus Model A300 and A300-600 series airplanes, was published in the Federal Register on December 30, 1999 (64 FR 73439). The action proposed to continue to require repetitive inspections to detect cracks in Gear Rib 5 of the main landing gear (MLG) attachment fittings at the lower flange, and repair, if necessary; and modification of Gear Rib 5 of the MLG attachment fittings, which would constitute terminating action for the repetitive inspections. That action also proposed to expand the current inspection area for certain airplanes.

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
There are approximately 164 airplanes of U.S. registry that will be affected by this AD.

The modification that is currently required by AD 99-19-26, and retained in this AD, takes approximately 62 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Required parts cost approximately $10,270 per airplane. Based on these figures, the cost impact of the currently required inspections on U.S. operators is estimated to be $2,294,360, or $13,990 per airplane.

The new expanded inspections that are required in this AD action will take approximately 6 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the requirements of this AD on U.S. operators is estimated to be $59,040, or $360 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 no operator would accomplish those actions in the future if this AD were not adopted.

Regulatory Impact
The regulations adopted herein will not have a substantial direct effect 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, it is determined that this final rule does not have federalism implications under Executive Order 13132.

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 RegulatoryFlexibility 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 removing amendment 39-11313 (64 FR 49966, September 15, 1999), and by adding a new airworthiness directive (AD), amendment 39-11616, to read as follows: