RULES and REGULATIONS

DEPARTMENT OF TRANSPORTATION 14 CFR Part 39 [Docket No. 95 -NM- 04 -AD; Amendment 39 - 9436; AD 95 -24 -04] Airworthiness Directives; Airbus Model A300 and A300 - 600 Series Airplanes Monday, November 27, 1995 AGENCY: Federal Aviation Administration, DOT. ACTION: Final rule. SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 and A300 - 600 series airplanes, that requires repetitive eddy current inspections to detect cracks at the aft spar web of the wings, and repair, if necessary. This amendment is prompted by reports indicating that cracks have been found in the rear spar web of the wings between ribs 1 and 2 of an in- service airplane and during testing on the fatigue test wing; the cracking occurred due to fatigue -related high shear stress. The actions specified by this AD are intended to prevent such fatigue -related cracking, which could result in reduced structural integrity of the wing. DATES: Effective Decem ber 27, 1995. - The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of December 27, 1995. ADDRESSES: The service information referenced in this AD may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. FOR FURTHER INFORMATION CONTACT: Phil Forde, Aerospace Engineer, Standardization Branch, ANM 113, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055 -4056; telephone (206) 227 -2146; fax (206) 227 - 1149. SUPPLEMENTARY INFORMATION: 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 May 4, 1995 ( 60 FR 22011 ). That action proposed to require repetitive eddy current inspections to detect cracks at the aft spar web of the wings, and repair, if necessary. - 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. - After careful review

o f the available data, including the comment noted above, the FAA has determined that air saf ety and the public interest require the adoption of the rule as proposed. -The FAA estimates that 89 airplanes of U.S. registry will be affected by this AD, that it will take approximately 3

work hours per airplane to accom plish 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 $16, 020, or $180 per airplane. The cost im

pact figure discussed above is based on assumptions that no operator has yet accom plished 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. - 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 p ower 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 thi s 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 im pact, 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

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AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 USC 106(g) , 40101 , 40113 , 44701 . 14 CFR § 39.13 §39.13 [Amended] - 14 CFR § 39.13 2. Section 39.13 is amended by adding the following new airworthiness directive: 95 -24 - 04 Airbus Industrie: Amendment 39 - 9436.Docket 95 -NM -04 -AD. Applicability: All Model A300 and Model 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 mo dified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (f) of this AD to request approval from the FAA. This ap-proval may address either no action, if the current configuration eliminates the unsafe condition; or different actions

necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD. Com pliance: Required as indicated, unless accomplished previously. To prevent fatigue -related cracking in the rear spar web of the wings, which could result in reduced structural inte grity of the wing, accomplish the following: (a) For Model A300 B2 series airplanes: Prior to the accumulation of 18,000 total flight cycles or within 1,400 flight cycles after the effective date of this AD, whichever occurs later, perform a high frequency eddy current (HFEC) inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300 - 57 - 0213, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles. (b) For Model A300 B4 - 103, and B4 -2C series airplanes: Prior to the accumulation of 1 9,000 total flight cycles or within 1,400 flight cycles after the effective date of this AD, whichever occurs later, perform an HFEC inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300 - 57 - 0213, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 6,000 flight cycles. (c) For Model A300 B4 -200 series airplanes: Prior to the accumulation of 1 7,000 total flight cycles or within 1,400 flight cycles after the effective date of this AD, whichever occurs later, perform an HFEC inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300 - 57 - 0213, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles. (d) For Model A300 - 600 B4 - 601, B4 - 603, B4 - 620, B4 - 622, B4 - 605R, B4 - 622R, and F4 - 605R series airplanes: Prior to the accumulation of

2 1,600 flight cycles, perform an HFEC inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300 - 57 - 6059, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 5,700 flight cycles. (e) If any crack is detected during any inspection required by this AD, prior to further flight, repair the crack in accordance with Airbus Service Bulletin A300 - 57 -0213, dated August 12, 1994, or Airbus Service Bulletin A300 - 57 - 6059, dated August 12, 1994, as applicable; or in accordance with a method approved by the Manager, Standardization Branch, ANM - 113, FAA, Transp ort Airplane Directorate. (f) An alternative method of c om pliance or adjustment of

the com pliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM - 113. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then s end it to the Manager, Standardization Branch, ANM - 113. Note 2: Information concerning the existence of approved alternative methods of com pliance with this AD, if any, may be obtained from the Standardization Branch, ANM - 113. (g) Special flight permits may be issued in accordance with sections 21.197 and 21.1 99 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. (h) The inspections and repairs shall be done in accordance with Airbus Service Bulletin A300 - 57 - 0213, dated August 12, 1994, or Airbus Service Bulletin A300 - 57 - 6059, dated August 12, 1994, 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 CFRpart 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. (i) This amendment becomes effective on December 27, 1995. Issued in Renton, Washington, on November 9, 1 995. S. R. Miller, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 95 -28798 Filed 11 -24 - 95; 8:45 am] BILLING CODE 4910 - 13 -U 

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