AD 2003-26-02

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:

(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.

(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.

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

(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.

(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.

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