AD 93-07-02
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus | A310-203 | Airworthiness Directives; AIRBUS INDUSTRIE Model A310 Series Airplanes |
| aircraft | Airbus | A310-221 | Airworthiness Directives; AIRBUS INDUSTRIE Model A310 Series Airplanes |
| aircraft | Airbus | A310-222 | Airworthiness Directives; AIRBUS INDUSTRIE Model A310 Series Airplanes |
| aircraft | Airbus | A310-304 | Airworthiness Directives; AIRBUS INDUSTRIE Model A310 Series Airplanes |
| aircraft | Airbus | A310-322 | Airworthiness Directives; AIRBUS INDUSTRIE Model A310 Series Airplanes |
| aircraft | Airbus | A310-324 | Airworthiness Directives; AIRBUS INDUSTRIE Model A310 Series Airplanes |
| aircraft | Airbus | A310-325 | Airworthiness Directives; AIRBUS INDUSTRIE Model A310 Series Airplanes |
Unsafe Condition
Wing tip brake valve failure, which could lead to reduced controllability of the airplane.
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Required Actions
Conduct an integrity test to detect corrosion of the wing tip brake solenoids within 350 flight hours after the effective date. Repeat the test at intervals not exceeding 350 flight hours. Replace corroded solenoids with part number 500A00003-03 before further flight. Install Modification 6725 as terminating action.
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Compliance Time
Within 350 flight hours after the effective date of this AD
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Affected Aircraft
AIRBUS INDUSTRIE Model A310 series airplanes on which Modification 6725 has not been accomplished, including models A310-203, A310-221, A310-222, A310-304, A310-322, A310-324, A310-325.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Wing Tip Brake Solenoids
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_93-07-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 93-07-02 Document Type: AD Final Rules Docket Number: 92-NM-101-AD Subject Heading: Airworthiness Directives; AIRBUS INDUSTRIE Model A310 Series Airplanes Subject: Wing Tip Brake Solenoids Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/10/1993 Make: Airbus Model: A310-203 | A310-221 | A310-222 | A310-304 | A310-322 | A310-324 | A310-325 Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 93-07-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 92-NM-101-AD AMENDMENT: 39-8534 AD NUMBER: 93-07-02 SUBJECT HEADING: Airworthiness Directives; AIRBUS INDUSTRIE Model A310 Series Airplanes ACTION: SUMMARY: DATES: Effective May 10, 1993. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 93-07-02 AIRBUS INDUSTRIE: Amendment 39-8534. Docket 92-NM-101-AD. Applicability: Model A310 series airplanes on which Modification 6725 has not been accomplished; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent wing tip brake valve failure, which could lead to reduced controllability of the airplane, accomplish the following: (a) Within 350 flight hours after the effective date of this AD, conduct an integrity test to detect corrosion of the wing tip brake solenoids, in accordance with Airbus Industrie Service Bulletin A310-27-2042, Revision 1, dated December 11, 1986. Thereafter, repeat the integrity test at intervals not to exceed 350 flight hours. (b) If corrosion in any wing tip brake solenoid is detected as a result of any integrity test required by paragraph (a) of this AD, prior to further flight, replace the corroded solenoid with a modified one having part number 500A00003-03. After such replacement, continue to perform integrity tests on all 8 solenoids at intervals not to exceed 350 flight hours until all 8 solenoids have been replaced with modified solenoids. (c) Installation of Modification 6725 in accordance with Airbus Industrie Service Bulletin A310-27-2046, Revision 1, dated November 24, 1989, which involves the installation of modified solenoids on all 8 solenoid valves in the wing tip brake, constitutes terminating action for the integrity testing required by paragraphs (a) and (b) of this AD. (d) 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: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The integrity test and modification shall be done in accordance with the following Airbus Industrie service bulletins, which contain the specified effective pages: Service Bulletin Referenced and Date Page Number Revision Level Shown on Page Date Shown on Page A310-27-2042 Revision No. 1 December 11, 1986 1-2, 5-6 3-4 1 Original December 11, 1986 June 20, 1986 A310-27-2046 Revision No. 1 November 24, 1989 1 -2 3-4 1 Original November 24, 1989 February 2, 1987 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, Airbus Support Division, 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. (g) This amendment becomes effective on May 10, 1993. FOOTER:
Document Text
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AD Final Rules - DRS_93-07-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 93-07-02 Document Type: AD Final Rules Docket Number: 92-NM-101-AD Subject Heading: Airworthiness Directives; AIRBUS INDUSTRIE Model A310 Series Airplanes Subject: Wing Tip Brake Solenoids Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/10/1993 Make: Airbus Model: A310-203 | A310-221 | A310-222 | A310-304 | A310-322 | A310-324 | A310-325 Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 93-07-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 92-NM-101-AD AMENDMENT: 39-8534 AD NUMBER: 93-07-02 SUBJECT HEADING: Airworthiness Directives; AIRBUS INDUSTRIE Model A310 Series Airplanes ACTION: SUMMARY: DATES: Effective May 10, 1993. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 93-07-02 AIRBUS INDUSTRIE: Amendment 39-8534. Docket 92-NM-101-AD. Applicability: Model A310 series airplanes on which Modification 6725 has not been accomplished; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent wing tip brake valve failure, which could lead to reduced controllability of the airplane, accomplish the following: (a) Within 350 flight hours after the effective date of this AD, conduct an integrity test to detect corrosion of the wing tip brake solenoids, in accordance with Airbus Industrie Service Bulletin A310-27-2042, Revision 1, dated December 11, 1986. Thereafter, repeat the integrity test at intervals not to exceed 350 flight hours. (b) If corrosion in any wing tip brake solenoid is detected as a result of any integrity test required by paragraph (a) of this AD, prior to further flight, replace the corroded solenoid with a modified one having part number 500A00003-03. After such replacement, continue to perform integrity tests on all 8 solenoids at intervals not to exceed 350 flight hours until all 8 solenoids have been replaced with modified solenoids. (c) Installation of Modification 6725 in accordance with Airbus Industrie Service Bulletin A310-27-2046, Revision 1, dated November 24, 1989, which involves the installation of modified solenoids on all 8 solenoid valves in the wing tip brake, constitutes terminating action for the integrity testing required by paragraphs (a) and (b) of this AD. (d) 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: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The integrity test and modification shall be done in accordance with the following Airbus Industrie service bulletins, which contain the specified effective pages: Service Bulletin Referenced and Date Page Number Revision Level Shown on Page Date Shown on Page A310-27-2042 Revision No. 1 December 11, 1986 1-2, 5-6 3-4 1 Original December 11, 1986 June 20, 1986 A310-27-2046 Revision No. 1 November 24, 1989 1 -2 3-4 1 Original November 24, 1989 February 2, 1987 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, Airbus Support Division, 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. (g) This amendment becomes effective on May 10, 1993. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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