| AD Number | 93-21-09 | Status | Active |
| Effective Date | December 13, 1993 | Issue Date | Not specified |
| Docket Number | 93-NM-62-AD | Amendment | 39-8723 |
| 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) | A320-111 |
93-21-09 AIRBUS INDUSTRIE: Amendment 39-8723. Docket 93-NM-62-AD.
Applicability: Model A320-111 series airplanes, serial numbers 005 through 012 inclusive, on which Modification 20774, as described in Airbus Industrie Service Bulletin A320- 53-1004, Revision 1, dated July 30, 1992, has not been accomplished; certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent loss of structural integrity of the fuselage, accomplish the following:
(a) Prior to the accumulation of 10,000 total landings, or within the next 60 days after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 6,000 landings, perform an external detailed visual inspection to detect breakage of the rivet heads at the junction between frame 15 and the skin on the left and right side, between stops 3 and 7, in accordance with Airbus Industrie Service Bulletin A320-53 -1069, dated August 17, 1991.
(1) Ifno breakage is detected on any rivet head: Prior to the accumulation of 22,000 total landings, or within 180 days after the effective date of this AD, whichever occurs later, replace all of the currently installed rivets with new or serviceable high-strength titanium Hilite bolts in accordance with Airbus Industrie Service Bulletin A320-53-1004, Revision 1, dated July 30, 1992, as revised by Change Notice 1.A., dated October 12, 1992.
(2) If breakage is detected on fewer than 2 rivet heads on each side: Within the next 100 landings after discovery of breakage, replace all of the currently installed rivets with new or serviceable high-strength titanium Hilite bolts in accordance with Airbus Industrie Service Bulletin A320-53-1004, Revision 1, dated July 30, 1992, as revised by Change Notice 1.A., dated October 12, 1992.
(3) If breakage is detected on 2 or more rivet heads on either side: Prior to further flight, replace all of the currently installed rivets with new or serviceable high-strength titanium Hilite bolts in accordance with Airbus Industrie Service Bulletin A320-53-1004, Revision 1, dated July 30, 1992, as revised by Change Notice 1.A., dated October 12, 1992.
(b) Replacement of all of the currently installed rivets with new or serviceable high- strength titanium Hilite bolts in accordance with Airbus Industrie Service Bulletin A320-53-1004, Revision 1, dated July 30, 1992, as revised by Change Notice 1.A., dated October 12, 1992, constitutes terminating action for the repetitive inspection requirements of this AD.
(c) 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.
(d) 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.
(e) The inspection and replacement shall be done in accordance with Airbus Industrie Service Bulletin A320-53-1069, dated August 17, 1991; Airbus Industrie Service Bulletin A320-53-1004, Revision 1, dated July 30, 1992; and Service Bulletin Change Notice 1.A., dated October 12, 1992, for Airbus Industrie Service Bulletin A320-53-1004, Revision 1, dated July 30, 1992. Revision 1 of Airbus Industrie Service Bulletin A320-53-1004 contains the following list of effective pages:
Page Number
Revision Level
Shown on Page
Date
Shown on Page
1-4, 6-8
1
July 30, 1992
5, 9-11
Original
April 5, 1989
This incorporation by reference wasapproved 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.
(f) This amendment becomes effective on December 13, 1993.