[Federal Register Volume 63, Number 76 (Tuesday, April 21, 1998)] [Proposed Rules] [Pages 19678-19680] From the Federal Register Online via the Government Publishing Office [www.gpo.gov] [FR Doc No: 98-10476] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 98-NM-75-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Model A319 and A321-100 Series Airplanes AGENCY: Federal Aviation Administration, DOT. [[Page 19679]] ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: This document proposes the adoption of a new airworthiness directive (AD) that is applicable to certain Airbus Model A319 and A321-100 series airplanes. This proposal would 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. This proposal is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by the proposed 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. DATES: Comments must be received by May 21, 1998. ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 98-NM-75-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056. Comments may be inspected at this location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal holidays. The service information referenced in the proposed rule may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. This information may be examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2110; fax (425) 227-1149. SUPPLEMENTARY INFORMATION: Comments Invited Interested persons are invited to participate in the making of the proposed rule by submitting such written data, views, or arguments as they may desire. Communications shall identify the Rules Docket number and be submitted in triplicate to the address specified above. All communications received on or before the closing date for comments, specified above, will be considered before taking action on the proposed rule. The proposals contained in this notice may be changed in light of the comments received. Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the proposed rule. All comments submitted will be available, both before and after the closing date for comments, in the Rules Docket for examination by interested persons. A report summarizing each FAA-public contact concerned with the substance of this proposal will be filed in the Rules Docket. Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this notice must submit a self-addressed, stamped postcard on which the following statement is made: ``Comments to Docket Number 98-NM-75-AD.'' The postcard will be date stamped and returned to the commenter. Availability of NPRMs Any person may obtain a copy of this NPRM by submitting a request to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 98-NM-75-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056. Discussion The Direction Generale de l'Aviation Civile (DGAC), which is the airworthiness authority for France, notified the FAA that an unsafe condition may exist on certain Airbus Model A319 and A321-100 series airplanes. The DGAC advises that certain Airbus Model A319 and A321-100 series airplanes were manufactured with the free-fall control mechanism for the landing gear rigged incorrectly. The landing gear unlocked-stop screw of the reduction gear box was not adjusted properly. Such improper adjustment of the landing gear unlocked-stop screw could lead to damage to the cut-out valve and rupture of the four shear pins in the free-fall mechanism during a free-fall extension. This condition, if not corrected, could result in non-extension of one or more landing gears, consequent damage to the airplane structure, and possible injury to passengers and crewmembers. Explanation of Relevant Service Information The manufacturer has issued Airbus Industrie A319/A321 All Operator Telex (AOT) 32-15, dated July 1, 1997, which describes procedures for 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 visual inspection of the main landing gear cut-out valve to detect discrepancies (rupture, distortion, and angular position); an operational test of the uplock mechanical control system; and follow-on corrective actions, if necessary. The corrective actions include replacing the cut-out valve with a new or serviceable part and performing functional tests of the normal extension and retraction of the landing gear and of the free-fall extension system. Accomplishment of the actions specified in the AOT is intended to adequately address the identified unsafe condition. The DGAC classified this AOT as mandatory and issued French airworthiness directive 97-177-101(B), dated August 13, 1997, in order to assure the continued airworthiness of these airplanes in France. FAA's Conclusions These airplane models are manufactured in France and are type certificated for operation in the United States under the provisions of Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the DGAC has kept the FAA informed of the situation described above. The FAA has examined the findings of the DGAC, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States. Explanation of Requirements of Proposed Rule Since an unsafe condition has been identified that is likely to exist or develop on other airplanes of the same type design registered in the United States, the proposed AD would require accomplishment of the actions specified in the AOT described previously. Cost Impact The FAA estimates that 2 airplanes of U.S. registry would be affected by this proposed AD, that it would take approximately 20 work hours per airplane to accomplish the proposed actions, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the proposed 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 proposed requirements of this AD action, and that no operator would [[Page 19680]] accomplish those actions in the future if this AD were not adopted. Regulatory Impact The regulations proposed herein would 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 proposal would not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. For the reasons discussed above, I certify that this proposed regulation (1) is not a ``significant regulatory action'' under Executive Order 12866; (2) is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) if promulgated, 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 copy of the draft regulatory evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 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. Sec. 39.13 [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive: Airbus Industrie: 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 Secs. 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. Note 3: The subject of this AD is addressed in French airworthiness directive 97-177-101(B), dated August 13, 1997. Issued in Renton, Washington, on April 15, 1998. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-10476 Filed 4-20-98; 8:45 am] BILLING CODE 4910-13-U