AD 98-13-18

This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319 and A321-100 series airplanes, that requires adjustment of the landing gear unlocked-stop screw; replacement of the shear pins in the reduction gear box and the landing gear pulley assembly with new or serviceable shear pins; a one-time inspection to detect discrepancies of the landing gear cut-out valve; an operational test of the uplock mechanical control system; and follow-on corrective actions, if necessary. 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 prevent non-extension of one or more landing gears, consequent damage to the airplane structure, and possible injury to passengers and crewmembers.

Final rule.

98-13-18 AIRBUS INDUSTRIE: Amendment 39-10606. Docket 98-NM-75-AD.

Applicability: Model A319 series airplanes, manufacturer's serial numbers 578 through 625 inclusive; and Model A321-100 series airplanes, manufacturer's serial numbers 385 through 620 inclusive; 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 (b) 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 prevent non-extension of one or more landing gears, consequent damage to the airplane structure, and possible injury to passengers and crewmembers, accomplish the following:

(a) Within 400 flight hours after the effective date of this AD, accomplish the actions required by paragraphs (a)(1), (a)(2), (a)(3), and (a)(4) of this AD, in accordance with Airbus Industrie A319/A321 All Operator Telex (AOT) 32-15, dated July 1, 1997.

(1) Adjust the landing gear unlocked-stop screw.

(2) Replace the shear pins in the reduction gear box and the landing gear pulley assembly with new or serviceable shear pins.

(3) Inspect the cut-out valve for discrepancies. If any discrepancy to the cut-out valve is detected, accomplish the requirements of paragraphs (a)(3)(i) and (a)(3)(ii) of this AD at the time specified in the AOT.

(i) Replace the cut-out valve with a new or serviceable part within the time specified in the AOT.

(ii) After replacing the cut-out valve, perform a functional test of the normal extension and retraction of the landing gear and of the free-fall extension system. If any discrepancy is detected during the accomplishment of either of the functional tests, prior to further flight, repair in accordance with the AOT.

(4) Perform an operational test of the gear uplock and door uplock mechanical control system. If any discrepancy is detected during the accomplishment of the operational test, prior to further flight, repair in accordance with the AOT.

(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, 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.

(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 actions shall be done in accordance with Airbus Industrie A319/A321 All Operator Telex (AOT) 32-15, dated July 1, 1997. 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 97-177- 101(B), dated August 13, 1997.

(e) This amendment becomes effective on July 30, 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 certain Airbus Model A319 and A321-100 series airplanes was published in the Federal Register on April 21, 1998 (63 FR 19678). That action proposed to require adjustment of the landing gear unlocked-stop screw; replacement of the shear pins in the reduction gear box and the landing gear pulley assembly with new or serviceable shear pins; a one-time inspection to detect discrepancies of the landing gear cut-out valve; an operational test of the uplock mechanical control system; and follow-on corrective actions, if necessary.

Comments
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.

The commenters support the proposed rule.

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 2 airplanes of U.S. registry will be affected by this AD, that it will take approximately 20 work hours per airplane to accomplish 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 $2,400, or $1,200 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.

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 ofgovernment. 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. 106(g), 40113, 44701.
39.13 [Amended]
2. Section 39.13 is amended by adding the following new airworthiness directive: