03-31271. Airworthiness Directives; Airbus Model A319-113 and -114 Series Airplanes; and Model A320-111, -211, and -212 Series Airplanes

AGENCY:

Federal Aviation Administration, DOT.

ACTION:

Final rule.

SUMMARY:

This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A319-113 and -114 series airplanes; and Model A320-111, -211, and -212 series airplanes; that requires either a review of airplane maintenance or delivery records, or one-time inspection of the hydraulic actuators located in the pivot doors of both thrust reversers to identify the part number, and eventual replacement of certain actuators with modified or new actuators. This action is necessary to prevent jamming of a thrust reverser door during operation, or inadvertent deployment of a thrust reverser door in-flight, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.

DATES:

Effective January 27, 2004.

The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of January 27, 2004.

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, 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:

Tim Dulin, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone [phone]; fax [phone].

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 A319-113 and -114 series airplanes; and Model A320-111, -211, and -212 series airplanes; was published in the Federal Register on October 2, 2003 (68 FR 56792). That action proposed to require either a review of airplane maintenance or delivery records, or one-time inspection of the hydraulic actuators located in the pivot doors of both thrust reversers to identify the part number, and eventual replacement of certain actuators with modified or new actuators.

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

The FAA estimates that 108 airplanes of U.S. registry will be affected by this AD, that it will take approximately 8 work hours per airplane to accomplish the required actions, and that the average labor rate is $65 per work hour. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $56,160, or $520 per airplane.

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. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions.

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 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:

2003-26-02 Airbus: Amendment 39-13398. Docket 2002-NM-61-AD.

Applicability: All Model A319-113 and -114 series airplanes; and Model A320-111, -211, and -212 series airplanes; certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent jamming of a thrust reverser door during operation or inadvertent deployment of a thrust reverser door in-flight, which could result in reduced controllability of the airplane, accomplish the following:

Inspection and Follow-on Actions

(a) Within 500 airplane flight cycles after the effective date of this AD: Do a detailed inspection of the eight hydraulic actuators located in the pivot doors of the thrust reversers (one actuator per pivot door, four pivot doors per thrust reverser, two thrust reversers per airplane) to identify the part number (P/N) of each actuator, in accordance with Airbus Service Bulletin A320-78-1020, excluding Appendix 01, dated March 28, 2001. Instead of a detailed inspection of the hydraulic actuators, a review of airplane maintenance and delivery records is acceptable if the P/N of each actuator installed on the airplane can be positively determined from that review.

Note 1:

For the purposes of this AD, a detailed 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 any actuator having P/Ns D23090000-1, D23090000-2, D23090000-3, or D23090000-4: Prior to the accumulation of 20,000 total actuator flight cycles, or within 250 airplane flight cycles after accomplishment of the detailed inspection or airplane records review required by paragraph (a) of this AD, whichever occurs later, replace the actuator with a modified or new actuator having part number D23090000-5 or D23090000-6, in accordance with the service bulletin.

(2) For any actuator having P/N D23090000-5: Prior to the accumulation of 30,000 total actuator flight cycles, or within 250 airplane flight cycles after the detailed inspection or airplane records review required by paragraph (a) of this AD, whichever occurs later, replace the actuator with a modified or new actuator having P/N D23090000-6, in accordance with the service bulletin.

(3) For any actuator having P/N D23090000-6: No further action is required by this paragraph.

Note 2:

Airbus Service Bulletin A320-78-1020 references Rohr CFM56-5A Service Bulletin RA32078-106, dated November 16, 2000, as an additional source of service information for modification of the actuators.

(b) Once all of the actuators located in the pivot doors of the thrust reversers have P/N D23090000-6, no further action is required by paragraph (a) of this AD.

(c) For operators that do not track actuator flight cycles, or do not have a means of obtaining information regarding actuator flight cycles, engine flight cycles must be used instead of actuator flight cycles.

Parts Installation

(d) As of the effective date of this AD, no person may install an actuator having P/N D23090000-1, D23090000-2, D23090000-3, or D23090000-4 on any airplane.

Submission of Inspection Results to Manufacturer Not Required

(e) Although the service bulletin referenced in this AD specifies to submit information to the manufacturer, this AD does not include such a requirement.

Alternative Methods of Compliance

(f) In accordance with 14 CFR 39.19, the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, is authorized to approve alternative methods of compliance for this AD.

Incorporation by Reference

(g) The actions must be done in accordance with Airbus Service Bulletin A320-78-1020, excluding Appendix 01, dated March 28, 2001. 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 2001-361(B) R1, dated September 3, 2003.

Effective Date

(h) This amendment becomes effective on January 27, 2004.

Issued in Renton, Washington on December 12, 2003.

Kevin M. Mullin,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.