AD 98-20-22

This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300, A310, and A300-600 series airplanes, that requires repetitive visual inspections to detect cracked or broken door stop fittings on the fuselage frame of the forward passenger doors, and replacement of any cracked or broken fitting with a new fitting. 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 cracked or broken door stop fittings of the forward passenger doors, which could result in failure of the door stop fittings, consequent reduced structural integrity of the door support structure, and sudden loss of cabin pressure in the passenger compartment.

Final rule.

98-20-22 AIRBUS INDUSTRIE: Amendment 39-10788. Docket 97-NM-307-AD.
Applicability: All Model A300, A310, 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 andcorrect cracked or broken door stop fittings of the forward passenger doors, which could result in failure of the door stop fittings, consequent reduced structural integrity of the door support structure, and sudden loss of cabin pressure in the passenger compartment, accomplish the following:

(a) Prior to the accumulation of the total flight cycles specified in the "Threshold" column of paragraph 1.B.(5) of the Planning Information of Airbus Service Bulletin A300-53-0309 (for Model A300 series airplanes); A310-53-2087 (for Model A310 series airplanes); or A300-53-6060 (for Model A300-600 series airplanes); all dated March 19, 1997; as applicable; or within 200 flight cycles after the effective date of this AD, whichever occurs later; accomplish paragraphs (a)(1) and (a)(2) of this AD.

(1) Perform a visual inspection of the left and right forward passenger door stop fittings to detect cracked or broken door stop fittings, in accordance with the applicable service bulletin.(2) Thereafter, repeat the visual inspection at the intervals specified in the "Intervals" column of paragraph 1.B.(5) of the Planning Information of the applicable service bulletin.

(b) If any cracked or broken door stop fitting is detected during any inspection required by paragraph (a)(1) or (a)(2) of this AD, prior to further flight, replace the door stop fitting with a new fitting in accordance with Airbus Service Bulletin A300-53-0309 (for Model A300 series airplanes); A310-53-2087 (for Model A310 series airplanes); or A300-53-6060 (for Model A300-600 series airplanes); all dated March 19, 1997; as applicable. Thereafter, repeat the visual inspections at the intervals specified in the "Intervals" column of paragraph 1.B.(5) of the Planning Information of the applicable service bulletin.

(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 actions shall be done in accordance with Airbus Service Bulletin A300-53-0309, dated March 19, 1997; Airbus Service Bulletin A310-53-2087, dated March 19, 1997; or Airbus Service Bulletin A300-53-6060, dated March 19, 1997; 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 3: The subject of this AD is addressed in French airworthiness directive 97-124-223(B), dated June 4, 1997.

(f) This amendment becomes effective on October 27, 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, A310, and A300-600 series airplanes was published in the Federal Register on July 7, 1998 (63 FR 36622). That action proposed to require repetitive visual inspections to detect cracked or broken door stop fittings on the fuselage frame of the forward passenger doors, and replacement of any cracked or broken fitting with a new fitting.

Comments Received
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.

Request to Delete Proposed Immediate Replacement Requirement
One commenter requests that the FAA delete the requirement for immediate replacement of cracked or broken fittings [as required by paragraph (b) of the proposed AD]. The commenter states that the Master Minimum Equipment List (MMEL) compliance times referenced in Airbus Service Bulletin A300-53-6060 would be sufficient, since Airbus reports of single findings are rare. The commenter also states that it is not reasonable for the FAA to assume that a large number of fittings are on the verge of failure. The commenter states that allowing aircraft to operate under MMEL compliance times will enable it to schedule repairs in a manner which minimizes operational impact.

The FAA does not concur with the commenter s request to delete the requirement for immediate replacement of any cracked or broken door stop fittings. It is the FAA s policy to require repair of known cracks prior to further flight (except in certain cases of unusual need). This policy is based on the fact that such damaged airplanes do not conform to the FAA certificated type design, and therefore, are not airworthy until a properly approved repair is incorporated. Further, the FAA considers that deferral of the compliance time for accomplishment of repairs, as specified in the MMEL, is not appropriate in this case, since to accomplish the inspection the airplane would already be at a location where such repairs can be made. Therefore, such repairs would be expected to have a minimal impact on operation of the airplane. No change to the final rule is necessary.

Conclusion
After careful review of the available data, including the comments noted above, 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 103 Model A300, A310, and A300-600 series 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 AD on U.S. operators is estimated to be $12,360, or $120 per airplane, per inspection cycle.

The cost impactfigure 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, positiveor 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: