| AD Number | 80-19-06 | Status | Active |
| Effective Date | September 17, 1980 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-3891 |
| 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) | A300 B2-1A A300 B2-1C A300 B2-203 A300 B2K-3C A300 B4-103 A300 B4-203 A300 B4-2C |
80-19-06 GROUPEMENT d'INTERET ECONOMIQUE (AIRBUS INDUSTRIE): Amendment 39-3891. Applies to Type A300 airplanes, all models, certificated in all categories, not incorporating AI Modification No. 1909/AI Service Bulletin No. A300-57-065, dated December 15, 1977.
Compliance required as indicated, unless already accomplished.
To prevent in-flight loss of wing slat closing plates, accomplish the following:
(a) Within the next 20 flights after the effective date of this AD, or prior to accumulation of 800 flights since new, whichever occurs later, and at intervals thereafter not exceeding 1,400 flights, except as provided in paragraph (b) of this AD, since the previous inspection, until modified in accordance with AI Service Bulletin No. A300-57-065, dated December 15, 1977, or an FAA-approved equivalent, visually inspect No. 1 L.H. and R.H. wing slat closing plate assemblies for cracks in the piano hinges, for failure of rivets, and for cracks or distortion at spring strutattachment lugs, in accordance with Accomplishment Instructions, subparagraph 2.A., Inspection, of AI Alert Service Bulletin No. A300-57-063, Revision No. 1, dated September 5, 1977, or an FAA-approved equivalent.
(b) If, during any inspection required by paragraph (a) of this AD, piano hinge cracks of less than 2.0 inches in length are found, verify that the pin of the piano hinge is complete and correctly installed and repeat the inspection required by paragraph (a) of this AD, within the next 800 flights and at intervals thereafter not exceeding 800 flights since the previous inspection, or, alternatively, proceed as prescribed in paragraph (c) of this AD.
(c) If, during any inspection required by this AD, hinge rivet failures, piano hinge cracks of 2.0 inches in length or greater, or cracks or distortion of the spring strut attachment brackets are found, before further flight, except that the airplane may be flown in accordance with FAR Sections 21.197 and 21.199 to a place where the work can be performed, accomplish the following:
(1) Incorporate the modification specified in AI Service Bulletin No. A300- 57-065, dated December 15, 1977, or an FAA-approved equivalent;
(2) For hinge rivet failures, and for hinge cracks of or greater than 2.0 inches in length, replace rivets or replace hinge, as appropriate, in accordance with subparagraph 2.C., Replacement of Cracked Hinges, of AI Service Bulletin No. A300-57-063, Revision No. 1, dated September 5, 1977, or an FAA-approved equivalent; and
(3) For cracks or distortion of the spring strut attachment brackets, replace the closing plate with a serviceable plate of the same part number in accordance with applicable portions of paragraph 2, Accomplishment Instructions, of AI Alert Service Bulletin No. A300-57- 063, Revision 1, dated September 5, 1977, or an FAA-approved equivalent.
(d) For purposes of this AD, one flight is one takeoff and landing cycle.
(e) For purposes of thisAD, an FAA-approved equivalent may be approved by the Chief, Aircraft Certification Staff, AEU-100, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium.
This amendment becomes effective September 17, 1980.