# AD 96-25-04: Wing and horizontal stabilizer wire bundles - Type: Airworthiness directive - Status: Historical - Products: Airbus A320-111, A320-211, A320-212, A320-214, A320-231, A320-232 and A320-233 - Effective: January 27, 1997 - Published: December 19, 1996, 61 FR 66881–66884 - Issued as: Final rule - Superseded by: [AD 2019-22-04](https://openairdocs.org/ad/2019-22-04) - Product type: Aircraft, Large airplane - Amendment: 39-9846 - Docket: 95-NM-176-AD - Registered aircraft: 563 may be affected, by airframe or engine model (OpenAirDocs) - Official PDF: https://openairdocs.org/files/sha256/1e/c7/1ec759ab26ebd3d9f6048dd81e7ede885d7024744e7a320d4a3e4bf48d3958d9 (from https://www.govinfo.gov/content/pkg/FR-1996-12-19/pdf/96-31113.pdf) - Federal Register: https://www.federalregister.gov/documents/1996/12/19/96-31113/airworthiness-directives-airbus-model-a320-series-airplanes - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/A44CED1DFDC7446986256961006F5684.0001 - DRS record last changed: August 7, 2025 - Page: https://openairdocs.org/ad/96-25-04 ## Summary This amendment supersedes 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 amendment requires that those actions also be accomplished in certain areas of the main landing gear (MLG) bays. This amendment also requires 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 amendment is prompted by a report that electrical short circuiting could occur in the wire bundles in the MLG bays. The actions specified by this AD are intended to prevent such electrical short circuiting due to chafing of the wire bundles in the wing, horizontal stabilizer, or MLG bays. ## The airworthiness directive 96-25-04 AIRBUS INDUSTRIE: Amendment 39-9846. 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, 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 thewire 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 tofurther 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 forcompliance 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. (j) The actions shall be done in accordance with the following Airbus Industrie service bulletins, as applicable, which contain the specified list of effective pages: Service Document Referenced and Date Page Number Revision Level Shown on Page Date Shown on Page A320-24-1044 Revision 2 March 3, 1992 1-6, 8, 8A, 8B, 9, 12, 16 7, 10, 11, 13-15, 17-23 2 1 March 3, 1992 August 23, 1991 A320-24-1044 Revision 3 March 12, 1993 1-6, 8A, 13,24 7, 10, 11, 14, 15 17-23 8, 8B, 9, 12, 16 3 1 2 March 12, 1993 August 23, 1991 March 3, 1992 A320-24-1045 Revision 2 April 12, 1992 1, 2, 4-8, 8A, 8B 23 3, 9, 14-16, 10-13 17-22 1 Original August 23, 1991 February 1, 1991 A320-24-1045 Revision 3 June 10, 1993 1-3, 6, 8A, 9 11, 21, 22 4, 5, 7, 8, 8B, 23 10, 12-14, 17-20 15, 16 3 2 Original 1 June 10, 1993 April 12, 1992 February 1, 1991 August 23, 1991 The incorporation by reference of Airbus Service Bulletin A320-24-1044, Revision 2, dated March 3, 1992; and Airbus Service Bulletin A320-24-1045, Revision 2, dated April 12, 1992; was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51 as of December 3, 1992 (57 FR 48957, October 29, 1992). The incorporation by reference of Airbus Service Bulletin A320-24-1044, Revision 3, dated March 12, 1993; and Airbus Service Bulletin A320-24-1045, Revision 3, dated June 10, 1993; 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. (k) This amendment becomes effective on January 27, 1997. ## Rule preamble ### Supplementary information A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) by superseding AD 92-22-02, amendment 39-8388 (57 FR 48957, October 29, 1992), which is applicable to certain Airbus Model A320 series airplanes, was published in the Federal Register on September 11, 1996 (61 FR 47835). The action proposed to 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 action also proposed to require that these actions be accomplished in certain areas of the MLG bays. Additionally, the action proposed to require installation of protective sleeves around the wire bundles, and realignment of bundles that are not guided centrally into the conduit end fittings, which would constitute terminating action for the repetitive inspections. 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. Both 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 There are approximately 30 Model A320 series airplanes of U.S. registry that will be affected by this proposed AD. The actions that are currently required 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 of the actions currently required on U.S. operators is estimated to be $55,800, or $1,860 per airplane. The inspections that are required by this new AD action will 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 of the required inspections on U.S. operators is estimated to be $55,800, or $1,860 per airplane. The installation that is required by this AD action takes approximately 59 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. The cost for required parts is negligible. Based on these figures, the cost impact of the installation on U.S. operators 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 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 of government. 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 removing amendment 39-8388 (57 FR 48957, October 29, 1992), and by adding a new airworthiness directive (AD), amendment 39-9846, to read as follows: ## Affected data sheets (1) (OpenAirDocs) The type certificate data sheets whose models the AD names. - [TCDS A28NM](https://openairdocs.org/tcds/A28NM): Airbus SAS; names 7 of 50 models: A320-111, A320-211, A320-212, A320-214, A320-231, A320-232, A320-233 ## Registered aircraft it may apply to (OpenAirDocs) Matched by airframe and engine model; the AD's applicability may narrow it by serial number, part number or equipment. - Aircraft: 563 (563 by airframe model, 0 by engine model) - Makers: Airbus 377, Airbus Industrie 184, Airbus S A S 2 Models with the most aircraft: - [Airbus A320-232](https://openairdocs.org/model/airbus-a320-232): 189 aircraft (airframe model) - [Airbus A320-214](https://openairdocs.org/model/airbus-a320-214): 160 aircraft (airframe model) - [Airbus Industrie A320-232](https://openairdocs.org/model/airbus-industrie-a320-232): 109 aircraft (airframe model) - [Airbus Industrie A320-212](https://openairdocs.org/model/airbus-industrie-a320-212): 39 aircraft (airframe model) - [Airbus Industrie A320-214](https://openairdocs.org/model/airbus-industrie-a320-214): 26 aircraft (airframe model) - [Airbus A320-233](https://openairdocs.org/model/airbus-a320-233): 21 aircraft (airframe model) - [Airbus Industrie A320-211](https://openairdocs.org/model/airbus-industrie-a320-211): 6 aircraft (airframe model) - [Airbus A320-211](https://openairdocs.org/model/airbus-a320-211): 3 aircraft (airframe model) - [Airbus Industrie A320-231](https://openairdocs.org/model/airbus-industrie-a320-231): 2 aircraft (airframe model) - [Airbus A320-212](https://openairdocs.org/model/airbus-a320-212): 2 aircraft (airframe model) - [Airbus S A S A320-214](https://openairdocs.org/model/airbus-s-a-s-a320-214): 2 aircraft (airframe model) - [Airbus A320-231](https://openairdocs.org/model/airbus-a320-231): 2 aircraft (airframe model) - [Airbus Industrie A320-233](https://openairdocs.org/model/airbus-industrie-a320-233): 1 aircraft (airframe model) - [Airbus Industrie A320-111](https://openairdocs.org/model/airbus-industrie-a320-111): 1 aircraft (airframe model) All 15 models: https://openairdocs.org/ad/96-25-04/models.md Every aircraft: https://openairdocs.org/ad/96-25-04/aircraft.md ## Related documents - [AD 2019-22-04](https://openairdocs.org/ad/2019-22-04): Electrical power · Airbus A320-211, A320-212 and A320-231. Effective Dec 24, 2019. Supersedes this AD - [Proposed rule 95-NM-176-AD](https://openairdocs.org/proposed/95-NM-176-AD): Notice of proposed rulemaking (NPRM), published Sep 11, 1996 Its text cites no advisory circulars or STCs. --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.