AD 95-10-12

This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, and -212 series airplanes, that requires modification of the junction box and connector backshells of a certain electrical harness assembly. This amendment is prompted by a report indicating that traces of fungus and corrosion have been found on the electrical harness junction box of the thrust reverser. The actions specified by this AD are intended to prevent such corrosion, which could result in multiple faults in the thrust reverser position indication, and subsequent uncontrolled reduction of engine power.

Final rule.

95-10-12 AIRBUS INDUSTRIE: Amendment 39-9229. Docket 94-NM-146-AD.

Applicability: Model A320-111, -211, and -212 series airplanes powered by CFM 56-5A engines equipped with an electrical harness assembly having part number (P/N) 238W0908-513; on which Airbus Modification 23693 (reference Airbus Service Bulletin A320-71-1011) has not 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 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 use the authority provided in paragraph (b) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafecondition 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.

Compliance: Required as indicated, unless accomplished previously.

To prevent multiple faults in the thrust reverser position indication, and subsequent uncontrolled reduction of engine power, accomplish the following:

(a) Within 3,000 flight hours after the effective date of this AD, modify the junction box, connector backshells, and the electrical harness assembly of the thrust reverser, in accordance with Airbus Service Bulletin A320-71-1011, dated November 17, 1993, or Revision 1, dated June 27, 1994.

(b) 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, Standardization Branch, ANM-113, 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, Standardization Branch, ANM-113.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.

(c) 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.

(d) The modification shall be done in accordance with Airbus Service Bulletin A320-71-1011, dated November 17, 1993; or in accordance with Airbus Service Bulletin A320-71-1011, Revision 1, dated June 27, 1994, which contains the following list of effective pages:

Page Number
Revision Level
Shown on Page
Date
Shownon Page
1, 4-6
1
June 27, 1994
2, 3, 7-11
Original
November 17, 1993

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.

(e) This amendment becomes effective on June 21, 1995.

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 A320-111, -211, and -212 series airplanes was published in the Federal Register on December 27, 1994 (59 FR 66493). That action proposed to require modification of the junction box and connector backshells of the electrical harness assembly of the thrust reverser.

Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the two comments received.

Both commenters support the proposed rule.

Since issuance of the notice, Airbus has issued Service Bulletin A320-71-1011, Revision 1, dated June 27, 1994. This service bulletin is essentially identical to the original issue, but contains certain editoral changes. The FAA has revised the final rule to include reference to this revision of the service bulletin as an alternative source of service information.

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 with the change previously described. The FAA has determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD.

The FAA estimates that 50 airplanes of U.S. registry will be affected by this AD, that it will take approximately 24 work hours per airplane to accomplish the required actions, and that the average labor rate is $60 per work hour. Required parts will be supplied by ROHR, Inc. (the manufacturer of the junction box, connector backshells, and the electrical harness assembly) at no cost to the operators. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $72,000, or $1,440 per airplane.

The total cost impact figure discussed above is based onassumptions 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.

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. App. 1354(a), 1421 and 1423; 49 U.S.C. 106(g); and 14 CFR 11.89.
39.13 - [Amended]
2. Section 39.13 is amended by adding the following new airworthiness directive: