| AD Number | 93-07-02 | Status | Active |
| Effective Date | May 10, 1993 | Issue Date | Not specified |
| Docket Number | 92-NM-101-AD | Amendment | 39-8534 |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Airbus |
| Model(s) | A310-203 A310-221 A310-222 A310-304 A310-322 A310-324 A310-325 |
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. Aftersuch 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.