[Federal Register Volume 61, Number 177 (Wednesday, September 11, 1996)] [Proposed Rules] [Pages 47835-47838] From the Federal Register Online via the Government Publishing Office [www.gpo.gov] [FR Doc No: 96-23241] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION 14 CFR Part 39 [Docket No. 95-NM-176-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Model A320 Series Airplanes AGENCY: Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: This document proposes the supersedure of an existing airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that currently requires inspections to detect chafing of the wire looms (bundles) in the wing and the horizontal stabilizer; and repair or replacement, protection, and realignment, if necessary. This proposal would require that those actions also be accomplished in certain areas of the main landing gear (MLG) bays. This proposal also would require installation of protective sleeves around the wire bundles, and realignment of bundles that are not guided centrally into the conduit end fittings, which constitutes terminating action for the repetitive inspections. This proposal is prompted by a report that electrical short circuiting could occur in the wire bundles in the MLG bays. The actions specified by the proposed AD are intended to prevent such electrical short circuiting due to chafing of the wire bundles in the wing, horizontal stabilizer, or MLG bays. DATES: Comments must be received by October 21, 1996. ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-103, Attention: Rules Docket No. 95-NM-176-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 [[Page 47836]] the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 227-2797; fax (206) 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 95-NM-176-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-103, Attention: Rules Docket No. 95-NM-176-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056. Discussion On September 30, 1992, the FAA issued AD 92-22-02, amendment 39- 8388 (57 FR 48957, October 29, 1992), applicable to certain Airbus Model A320 series airplanes, to require inspections to detect chafing of the wire looms (bundles) in the wing and the horizontal stabilizer; and repair or replacement, protection, and realignment, if necessary. That action was prompted by an incident in which short circuiting of a wire bundle caused fire extinguishant to discharge and pop the circuit breaker for a brake fan. The requirements of that AD are intended to prevent electrical short circuiting due to chafing of the wire bundles in the wing and the horizontal stabilizer. Actions Since Issuance of Previous Rule Since the issuance of that AD, the Direction Generale de l'Aviation Civile (DGAC), which is the airworthiness authority for France, has advised the FAA that chafing of the wire bundles and subsequent electrical short circuiting also could occur in the main landing gear (MLG) bays. This condition presents the same unsafe condition that was addressed by AD92-22-02. Additionally, the DGAC has advised that protection of the wire bundle is necessary following any repair or replacement of a wire to prevent further wire damage. Explanation of Relevant Service Information Airbus has issued Service Bulletin A320-24-1044, Revision 3, dated March 12, 1993. Although Revision 3 of the service bulletin is essentially the same as Revision 2, it adds procedures for repetitive visual inspections of the wire bundles to detect damage, contact with the end fittings of the protective conduit, and misalignment with conduit end fittings in the MLG bays. The service bulletin recommends that any damaged wire be repaired or replaced in accordance with procedures described in the Aircraft Wiring Manual or the Aircraft Maintenance Manual. Airbus also has issued Service Bulletin A320-24-1045, Revision 3, dated June 10, 1993. Among other things, this service bulletin describes procedures for installation of protective sleeves around the wire bundles, and realignment of bundles that are not guided centrally into the conduit end fittings. Revision 3 of the service bulletin adds procedures for accomplishment of these actions in the MLG bays. Accomplishment of the protection and realignment in accordance with Revision 3 of the service bulletin eliminates the need for the repetitive visual inspections. The DGAC classified these service bulletins as mandatory and issued French airworthiness directive 91-182-020(B)R2, dated December 7, 1994, in order to assure the continued airworthiness of these airplanes in France. FAA's Conclusions This airplane model is manufactured in France and is type certificated for operation in the United States under the provisions of section 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 supersede AD 92-22-02 to continue to require inspections to detect chafing of the wire bundles in the wing and the horizontal stabilizer; and repair or replacement, protection, and realignment, if necessary. The proposed AD also would require that these actions be accomplished in certain areas of the MLG bays. Additionally, the proposed AD would require installation of protective sleeves around the wire bundles, and realignment of bundles that are not guided centrally into the conduit end fittings, which constitutes terminating action for the repetitive inspections. The actions would be required to be accomplished in accordance with the service bulletins described previously. Explanation of Requirement for Terminating Action While the French AD and service bulletins allow flight to continue as long as the wire bundles are inspected repetitively, this proposed AD would require that protection and, if necessary, realignment of the wire bundles be accomplished as terminating action for the repetitive inspections. The FAA has determined that long term continued operational safety will be better assured by modifications or design changes to remove the source of the problem, rather than by repetitive inspections. Long term inspections may not be providing the degree of safety assurance necessary for the transport airplane fleet. This, coupled with a better understanding of the human factors associated with numerous repetitive inspections, has led the FAA to consider placing less emphasis on special procedures and [[Page 47837]] more emphasis on design improvements. The proposed requirement for realignment and protection of the wire bundles is in consonance with these considerations. In developing an appropriate compliance time for the proposed requirement to protect the wire bundles, the FAA's intent is that these actions be accomplished during a regularly scheduled maintenance visit for the majority of the affected fleet, when the airplanes would be located at a base where special equipment and trained personnel would be readily available, if necessary. The FAA finds that 7,000 hours time-in-service corresponds closely to the interval representative of most of the affected operators' normal maintenance schedules. The FAA considers that this interval will provide an acceptable level of safety. Cost Impact There are approximately 30 Model A320 series airplanes of U.S. registry that would be affected by this proposed AD. The actions that are required currently by AD 92-22-02 take approximately 31 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Based on these figures, the cost impact on U.S. operators of the actions currently required is estimated to be $55,800, or $1,860 per airplane. The inspections that are proposed in this AD action would take approximately 31 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Based on these figures, the cost impact on U.S. operators of the proposed inspection is estimated to be $55,800, or $1,860 per airplane. The installation that is proposed in this AD action would take approximately 59 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. The cost for required parts would be negligible. Based on these figures, the cost impact on U.S. operators of the proposed installation is estimated to be $106,200, or $3,540 per airplane. The cost impact figures discussed above are based on assumptions that no operator has yet accomplished any of the current or proposed 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 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 removing amendment 39-8388 (57 FR 48957, October 29, 1992), and by adding a new airworthiness directive (AD), to read as follows: Airbus Industrie: Docket 95-NM-176-AD. Supersedes AD 92-22-02, Amendment 39-8388. Applicability: Model A320 series airplanes on which Airbus Modification No. 22109 (Airbus Service Bulletin A320-24-1045, Revision 3, dated June 10, 1993) has not been accomplished; certificated in any category. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise 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 (h) 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 electrical short circuiting due to chafing of the wire bundles in the wing, horizontal stabilizer, or main landing gear (MLG) bay, accomplish the following: Restatement of Requirements of AD 92-22-02 (a) For airplanes having manufacturer's serial numbers through 169 inclusive: Prior to the accumulation of 450 hours time-in- service after December 3, 1992 (the effective date of AD 92-22-02, amendment 39-8388), inspect the wire bundles in wing zones 574 and 674 through panels 574AB and 674AB to detect chafing or contact with the end fittings of the protective conduit, in accordance with Airbus Service Bulletin A320-24-1044, Revision 2, dated March 3, 1992, or Revision 3, dated March 12, 1993. Thereafter, repeat this inspection at intervals not to exceed 450 hours time-in-service until the inspection required by paragraph (c) of this AD is accomplished. (1) If any chafed or damaged wire is found, prior to further flight, repair or replace it in accordance with the Airplane Maintenance Manual or the Aircraft Wiring Manual. (2) If any wire bundle is found in contact with the edge of the conduit end fitting, or which might come in contact with the edge of the conduit end fitting due to vibration in flight, prior to further flight, realign and protect the bundle in accordance with Airbus Service Bulletin A320-24-1045, Revision 2, dated April 12, 1992, or Revision 3, dated June 10, 1993; or in accordance with the temporary repair described in paragraph 2.B.(2)(b) of Airbus Service Bulletin A320-24-1044, Revision 2, dated March 3, 1992, or Revision 3, dated March 12, 1993. (b) For airplanes having manufacturer's serial numbers through 169 inclusive: Prior to the accumulation of 1,500 hours time-in- service after December 3, 1992, inspect the wire bundles in the wing and horizontal stabilizer, excluding wing zones 574 and 674 through panels 574AB and 674AB, to detect chafing or contact with the ending fittings of the protective conduit, in accordance with Airbus Service Bulletin A320-24-1044, Revision 2, dated March 3, 1992, or Revision 3, dated March 12, 1993. Thereafter, repeat this inspection at intervals not to exceed 3,500 hours time-in-service until the inspection required by paragraph (d) of this AD is accomplished. (1) If any chafed or damaged wire is found, prior to further flight, repair or replace it in accordance with the Airplane Maintenance Manual or the Aircraft Wiring Manual. (2) If any wire bundle is found in contact with the edge of the conduit end fitting, or which might come in contact with the edge of the conduit end fitting due to vibration in flight, prior to further flight, realign and protect the bundle in accordance with Airbus Service Bulletin A320-24-1045, Revision 2, [[Page 47838]] dated April 12, 1992, or Revision 3, dated June 10, 1993; or in accordance with the temporary repair described in paragraph 2.B.(6)(b) of Airbus Service Bulletin A320-24-1044, Revision 2, dated March 3, 1992, or Revision 3, dated March 12, 1993. New Requirements of This AD (c) For all airplanes: Prior to the accumulation of 450 hours time-in-service after the effective date of this AD, inspect the wire bundles in wing zones 574 and 674 through panels 574AB and 674AB to detect damage, contact chafing, or contact with the end fittings of the protective conduit, in accordance with Airbus Service Bulletin A320-24-1044, Revision 2, dated March 3, 1992, or Revision 3, dated March 12, 1993. Thereafter, repeat this inspection at intervals not to exceed 450 hours time-in-service. Accomplishment of this inspection terminates the inspections required by paragraph (a) of this AD. (1) If any chafed or damaged wire is found, prior to further flight, accomplish the requirements of paragraphs (c)(1)(i) and (c)(1)(ii) of this AD. (i) Repair or replace the wire in accordance with the Airplane Maintenance Manual or the Aircraft Wiring Manual. And (ii) Protect the wire bundle in accordance with Airbus Service Bulletin A320-24-1045, Revision 2, dated April 12, 1992, or Revision 3, dated June 10, 1993; or in accordance with the temporary repair described in paragraph 2.B.(2)(b) of Airbus Service Bulletin A320- 24-1044, Revision 2, dated March 3, 1992, or Revision 3, dated March 12, 1993. (2) If any wire bundle is found in contact with the edge of the conduit end fitting, or which might come in contact with the edge of the conduit end fitting due to vibration in flight, prior to further flight, realign and protect the bundle in accordance with Airbus Service Bulletin A320-24-1045, Revision 2, dated April 12, 1992, or Revision 3, dated June 10, 1993; or in accordance with the temporary repair described in paragraph 2.B.(2)(b) of Airbus Service Bulletin A320-24-1044, Revision 2, dated March 3, 1992, or Revision 3, dated March 12, 1993. (d) For all airplanes: Prior to the accumulation of 1,500 hours time-in-service after the effective date of this AD, inspect the wire bundles in the wing and horizontal stabilizer, excluding wing zones 574 and 674 through panels 574AB and 674AB, to detect chafing or contact with the ending fittings of the protective conduit, in accordance with Airbus Service Bulletin A320-24-1044, Revision 2, dated March 3, 1992, or Revision 3, dated March 12, 1993. Thereafter, repeat this inspection at intervals not to exceed 3,500 hours time-in-service. Accomplishment of this paragraph terminates the inspections required by paragraph (b) of this AD. (1) If any chafed or damaged wire is found, prior to further flight, accomplish the requirements of paragraphs (d)(1)(i) and (d)(1)(ii) of this AD. (i) Repair or replace the wire in accordance with the Airplane Maintenance Manual or the Aircraft Wiring Manual. And (ii) Protect the wire bundle in accordance with Airbus Service Bulletin A320-24-1045, Revision 2, dated April 12, 1992, or Revision 3, dated June 10, 1993; or in accordance with the temporary repair described in paragraph 2.B.(6)(b) of Airbus Service Bulletin A320- 24-1044, Revision 2, dated March 3, 1992, or Revision 3, dated March 12, 1993. (2) If any wire bundle is found in contact with the edge of the conduit end fitting, or which might come in contact with the edge of the conduit end fitting due to vibration in flight, prior to further flight, realign and protect the bundle in accordance with Airbus Service Bulletin A320-24-1045, Revision 2, dated April 12, 1992, or Revision 3, dated June 10, 1993; or in accordance with the temporary repair described in paragraph 2.B.(6)(b) of Airbus Service Bulletin A320-24-1044, Revision 2, dated March 3, 1992, or Revision 3, dated March 12, 1993. (e) For all airplanes: Prior to the accumulation of 1,500 hours time-in-service after the effective date of this AD, inspect the wire bundles in the MLG bays to detect chafing or contact with the end fittings of the protective conduit, in accordance with Airbus Service Bulletin A320-24-1044, Revision 3, dated March 12, 1993. Thereafter, repeat this inspection at intervals not to exceed 3,500 hours time-in-service. (1) If any chafed or damaged wire is found, prior to further flight, accomplish the requirements of paragraphs (e)(1)(i) and (e)(1)(ii) of this AD. (i) Repair or replace the wire in accordance with the Airplane Maintenance Manual or the Aircraft Wiring Manual. And (ii) Protect the wire bundle in accordance with Airbus Service Bulletin A320-24-1045, Revision 3, dated June 10, 1993; or in accordance with the temporary repair described in paragraph 2.B.(6)(b) of Airbus Service Bulletin A320-24-1044, Revision 3, dated March 12, 1993. (2) If any wire bundle is found in contact with the edge of the conduit end fitting, or which might come in contact with the edge of the conduit end fitting due to vibration in flight, prior to further flight, realign and protect the bundle in accordance with Airbus Service Bulletin A320-24-1045, Revision 3, dated June 10, 1993; or in accordance with the temporary repair described in paragraph 2.B.(6)(b) of Airbus Service Bulletin A320-24-1044, Revision 3, dated March 12, 1993. (f) If a temporary repair over a damaged length of wire bundle is accomplished in accordance with paragraph (a)(2), (b)(2), (c)(2), (d)(2), or (e)(2) of this AD: Prior to the accumulation of 450 hours time-in-service, replace the temporary repair with a protective sleeve around the wire bundle, and realign the bundle if it is not guided centrally into the conduit end fittings. Accomplish these actions in accordance with Airbus Service Bulletin A320-24-1045, Revision 3, dated June 10, 1993. Accomplishment of these actions terminates the repetitive inspections required by paragraph (c), (d), or (e) of this AD, as applicable. Note 2: Accomplishment of the actions in accordance with Airbus Service Bulletin A320-24-1045, Revision 2, dated April 12, 1992, is acceptable for compliance with the requirements of paragraph (f) of this AD for the areas specified in paragraphs (c) and (d) of this AD. (g) For all airplanes: Prior to the accumulation of 7,000 hours time-in-service after the effective date of this AD, install protective sleeves around the wire bundles, and realign any bundle that is not guided centrally into the conduit end fittings, in wing zones 574 and 674 through panels 574AB and 674AB, in the wing and horizontal stabilizer, excluding wing zones 574 and 674 through panels 574AB and 674AB, and in the MLG bays, in accordance with Airbus Service Bulletin A320-24-1045, Revision 3, dated June 10, 1993. Accomplishment of these actions constitutes terminating action for the repetitive inspections required by this AD. Note 3: Accomplishment of the actions in accordance with Airbus Service Bulletin A320-24-1045, Revision 2, dated April 12, 1992, is acceptable for compliance with the requirements of paragraph (g) of this AD for the areas specified in paragraphs (c) and (d) of this AD. (h) 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 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (i) 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. Issued in Renton, Washington, on September 5, 1996. James V. Devany, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 96-23241 Filed 9-10-96; 8:45 am] BILLING CODE 4910-13-U