AD 99-16-01

This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Industrie Model A300-600 series airplanes, that currently requires repetitive high frequency eddy current inspections to detect cracks in bolt holes where parts of the main landing gear are attached to the rear spar, and repair, if necessary. This amendment requires repetitive ultrasonic inspections to detect cracking in certain bolt holes of the rear spar, and repair, 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 cracking of the rear spar of the wing, which could result in reduced structural integrity of the airplane.

Final rule.

99-16-01 AIRBUS INDUSTRIE: Amendment 39-11236. Docket 98-NM-62-AD. Supersedes AD 95-20-02, Amendment 39-9380.

Applicability: Model A300-600 series airplanes, having manufacturer's serial numbers (MSN) 252 through 553 inclusive, certificated in any category; except those airplanes on which Airbus Industrie Production Modification No. 07601 has been accomplished prior to delivery.

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 (h) 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 rear spar of the wing, which could result in reduced structural integrity of the airplane, accomplish the following:

RESTATEMENT OF REQUIREMENTS OF AD 95-20-02:
NOTE 2: Accomplishment of the inspections and repair of cracking in accordance with Airbus Industrie Service Bulletin A300-57-6017, dated November 22, 1993, prior to November 9, 1995 (the effective date of AD 95-20-02, amendment 39-9380), is acceptable for compliance with the applicable action specified in this amendment.

(a) Perform a high frequency eddy current (HFEC) rototest inspection to detect cracks in certain bolt holes where the main landing gear (MLG) forward pick-up fitting and MLG rib 5 aft are attached to the rear spar, in accordance with Airbus Industrie Service Bulletin A300- 57-6017, Revision 1 (includes Appendix 1), dated July 25, 1994.

NOTE 3: This service bulletin also references Airbus Industrie Service Bulletin A300- 57-6020, dated November 22, 1993, as an additional source of service information.

(1) For airplanes that have accumulated 17,300 total landings or less as of November 9, 1995: Inspect prior to the accumulation of 17,300 total landings, or within 1,500 landings after November 9, 1995, whichever occurs later.

(2) For airplanes that have accumulated 17,301 or more total landings, but less than 19,300 total landings as of November 9, 1995: Inspect within 1,500 landings after November 9, 1995.

(3) For airplanes that have accumulated 19,300 or more total landings as of November 9, 1995: Inspect within 750 landings after November 9, 1995.

(b) If no crack is found during the inspection required by paragraph (a) of this AD, repeat that inspection thereafter at the time specified in either paragraph (b)(1) or (b)(2) of this AD, as applicable.

(1) For airplanes on which Airbus Industrie Modification 07716 (as described in Airbus Industrie Service Bulletin A300-57-6020) has not been accomplished, inspect at the time specified in paragraph (b)(1)(i) or (b)(1)(ii) of this AD, as applicable.

(i) For airplanes having MSN 465 through 553 inclusive: Repeat the inspection at intervals not to exceed 13,000 landings, until the inspection required by paragraph (d)(2)(i)(A) has been accomplished.

(ii) For airplanes having MSN 252 through 464 inclusive: Repeat the inspection at intervals not to exceed 8,400 landings, until the inspection required by paragraph (d)(2)(i)(B) has been accomplished.

(2) For airplanes on which Airbus Industrie Modification 07716 has been accomplished, inspect at the time specified in either paragraph (b)(2)(i) or (b)(2)(ii) of this AD, as applicable.

(i) For airplanes having MSN 465 through 553 inclusive: Repeat the inspection at intervals not to exceed 11,800 landings, until the inspection required by paragraph (d)(2)(ii)(A) has been accomplished.

(ii) For airplanes having MSN 252 through 464 inclusive: Repeat the inspection within 10,700 landings following the initial inspection required by paragraph (a) of this AD, and thereafter at intervals not to exceed 7,500 landings, until the inspection required by paragraph (d)(2)(ii)(B) has been accomplished.

(c) If any crack is found during the inspection required by either paragraph (a) or (b) of this AD, prior to further flight, accomplish the requirements of either paragraph (c)(1) or (c)(2) of this AD, as applicable.

(1) For airplanes on which Airbus Industrie Modification 07716 has not been accomplished: Oversize the bolt hole by 1/32 inch and repeat the HFEC inspection required by paragraph (a) of this AD, in accordance with Airbus Industrie Service Bulletin 300-57-6017, Revision 1, dated July 25, 1994. After accomplishing theoversizing and HFEC inspection, repeat the inspection as required by paragraph (b) of this AD at the applicable schedule specified in that paragraph, until the inspection required by paragraph (d)(2)(ii)(A) has been accomplished.

NOTE 4: For the purposes of this AD, airplanes that are repaired in accordance with Airbus Industrie Service Bulletin 300-57-6017, Revision 1, are considered to be subject to repetitive inspections at the same interval as those airplanes on which Airbus Industrie Modification 07716 has been accomplished.

(i) If no cracking is detected, install the second oversize bolt in accordance with the service bulletin.

(ii) If any cracking is detected, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate.

(2) For airplanes on which Airbus Industrie Modification 07716 has been accomplished: Repair in accordance with a method approved by the Manager, International Branch,ANM-116. After repair, repeat the inspections as required by paragraph (b) of this AD at the applicable schedule specified in that paragraph, until the inspection required by paragraph (d)(2)(ii)(B) has been accomplished.

NEW REQUIREMENTS OF THIS AD:

New Initial and Repetitive Inspections
(d) Perform an ultrasonic inspection to detect cracks in certain bolt holes where the MLG forward pick-up fitting and MLG rib 5 aft are attached to the rear spar, in accordance with Airbus Industrie Service Bulletin A300-57-6017, Revision 3, dated November 19, 1997; at the time specified in paragraph (d)(1) or (d)(2) of this AD, as applicable.

NOTE 5: Inspections accomplished prior to the effective date of this AD in accordance with Airbus Industrie Service Bulletin A300-57-6017, Revision 2, dated January 14, 1997, are considered acceptable for compliance with paragraph (d) of this AD.

(1) For airplanes not inspected prior to the effective date of this AD in accordance with Airbus Industrie Service Bulletin A300-57-6017, dated November 22, 1993, or Revision 1 (includes Appendix 1), dated July 25, 1994: Inspect at the time specified in paragraph (d)(1)(i), (d)(1)(ii), or (d)(1)(iii) of this AD, as applicable. Accomplishment of this inspection terminates the requirements of paragraph (a) of this AD.

(i) For airplanes that have accumulated 17,300 total landings or fewer as of the effective date of this AD: Inspect prior to the accumulation of 17,300 total landings, or within 1,500 landings after the effective date of this AD, whichever occurs later.

(ii) For airplanes that have accumulated 17,301 total landings or more but fewer than 19,300 total landings as of the effective date of this AD: Inspect within 1,500 landings after the effective date of this AD.

(iii) For airplanes that have accumulated 19,300 total landings or more as of the effective date of this AD: Inspect within 750 landings after the effective date of this AD.

(2) For airplanes on which an HFEC inspection was performed prior to the effective date of this AD in accordance with paragraph (a) of AD 95-20-02, or in accordance with Airbus Industrie Service Bulletin A300-57-6017, dated November 22, 1993: Inspect at the time specified in paragraph (d)(2)(i) or (d)(2)(ii), as applicable.

(i) If no cracking was detected during any HFEC inspection accomplished prior to the effective date of this AD, and if Airbus Industrie Modification 07716 has not been accomplished: Inspect at the time specified in paragraph (d)(2)(i)(A) or (d)(2)(i)(B) of this AD, as applicable.

(A) For airplanes having MSN 465 through 553 inclusive: Inspect within 13,000 landings after the most recent HFEC inspection, and thereafter at intervals not to exceed 8,900 landings. Accomplishment of this inspection constitutes terminating action for the repetitive inspection requirement of paragraph (b)(1)(i) of this AD.

(B) For airplanes having MSN 252 through 464 inclusive: Inspect within 8,400 landings after the most recent HFEC inspection, and thereafter at intervals not to exceed 5,500 landings. Accomplishment of this inspection constitutes terminating action for the repetitive inspection requirement of paragraph (b)(1)(ii) of this AD.

(ii) If any cracking was detected during any HFEC inspection performed prior to the effective date of this AD, regardless of the method of repair, or if Airbus Industrie Modification 07716 has been accomplished: Inspect at the time specified in paragraph (d)(2)(ii)(A) or (d)(2)(ii)(B) of this AD, as applicable.

(A) For airplanes having MSN 465 through 553 inclusive: Inspect within 11,800 landings after the most recent HFEC inspection, and thereafter at intervals not to exceed 8,200 landings. Accomplishment of this inspection constitutes terminating action for the repetitive inspection requirement of paragraph (c)(1) or (c)(2) of this AD, as applicable.

(B) For airplanes having MSN252 through 464 inclusive: Inspect within 10,700 landings after the initial inspection in accordance with paragraph (a) of AD 95-20-02, or within 7,500 landings after the most recent HFEC inspection, whichever occurs later, and thereafter at intervals not to exceed 4,900 landings. Accomplishment of this inspection
constitutes terminating action for the repetitive inspection requirement of paragraph (c)(1) or (c)(2) of this AD, as applicable.

(e) If no cracking is detected during the ultrasonic inspection required by paragraph (d)(1) of this AD, repeat that inspection thereafter at the time specified in paragraph (e)(1) or (e)(2) of this AD, as applicable.

(1) For airplanes having MSN 465 through 553 inclusive: Repeat the inspection at intervals not to exceed 8,900 landings.

(2) For airplanes having MSN 232 through 464 inclusive: Repeat the inspection at intervals not to exceed 5,500 landings.

Repair
(f) If any cracking is detected during any inspection performed in accordance with paragraph (d) or (e) of this AD: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116; or the Direction G n rale de l'Aviation Civile (or its delegated agent).

Terminating Action
(g) Accomplishment of Airbus Industrie Modification 11440 (Airbus Industrie Service Bulletin A300-57-6073, dated September 30, 1997) constitutes terminating action for the repetitive inspection requirements of paragraphs (d) and (e) of this AD, as applicable.

Alternative Methods of Compliance
(h) 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 6: 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
(i) 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
(j) Except as provided by paragraphs (c)(1)(ii), (c)(2), (f), and (g) of this AD, the actions shall be done in accordance with Airbus Industrie Service Bulletin A300-57-6017, Revision 1 (includes Appendix 1), dated July 25, 1994, and Airbus Industrie Service Bulletin A300-57-6017, Revision 3, dated November 19, 1997. The incorporation by reference of Airbus Industrie Service Bulletin A300-57-6017, Revision 3, dated November 19, 1997 is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. The incorporation by reference of Airbus Industrie Service Bulletin A300-57-6017, Revision 1 (includes Appendix 1), dated July 25, 1994, was approved previously by the Director of the Federal Register as of November 9, 1995 (60 FR 52618, October 10, 1995). 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 7: The subject of this AD is addressed in French airworthiness directive 94-031-155(B)R1, dated May 7, 1997.

(k) This amendment becomes effective on September 1, 1999.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) by superseding AD 95-20-02, amendment 39-9380 (60 FR 52618, October 10, 1995), which is applicable to certain Airbus Industrie Model A300-600 series airplanes, was published in the Federal Register on April 23, 1999 (64 FR 19942). The action proposed to require repetitive ultrasonic inspections to detect cracking in certain bolt holes of the rear spar, and repair, if necessary.

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 54 airplanes of U.S. registry that will be affected by this AD.

The new inspections that are required by this AD will takeapproximately 226 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 new requirements of this AD on U.S. operators is estimated to be $732,240, or $13,560 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.

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 removing amendment 39-9380 (60 FR 52618, October 10, 1995), and by adding a new airworthiness directive (AD), amendment 39-11236, to read as follows: