| AD Number | 93-14-17 | Status | Active |
| Effective Date | September 16, 1993 | Issue Date | Not specified |
| Docket Number | 93-NM-15-AD | Amendment | 39-8641 |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | ATR - GIE Avions de Transport R gional ATR - GIE Avions de Transport R gional ATR - GIE Avions de Transport R gional ATR - GIE Avions de Transport R gional ATR - GIE Avions de Transport R gional ATR - GIE Avions de Transport R gional ATR - GIE Avions de Transport R gional ATR - GIE Avions de Transport R gional ATR - GIE Avions de Transport R gional ATR - GIE Avions de Transport R gional ATR - GIE Avions de Transport R gional ATR - GIE Avions de Transport R gional ATR - GIE Avions de Transport R gional ATR - GIE Avions de Transport R gional ATR - GIE Avions de Transport R gional |
| Model(s) | ATR72-101 ATR72-102 ATR72-201 ATR72-202 ATR72-211 ATR72-212 ATR72-212A |
93-14-17 AEROSPATIALE: Amendment 39-8641. Docket 93-NM-15-AD.
Applicability: Model ATR72-100 and -200 series airplanes on which Modification 3196 has not been installed; certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent reduced structural integrity of the wing spar fittings, accomplish the following:
(a) Within 12 months after the effective date of this AD, perform a one-time detailed visual inspection of the fastener holes on the front and rear wing spar fittings to ensure that spotfacing of the fastener holes has been accomplished, in accordance with Aerospatiale Service Bulletin ATR72-57-1008, dated November 19, 1992.
(1) If spotfacing of the fastener holes has been accomplished, no further action is required by this AD.
(2) If spotfacing of the fastener holes has not been accomplished, prior to further flight, perform a one-time general visual inspection of the fastener holes for peening or cracks, in accordance with the service bulletin.
(i) If no peening or crack is found, prior to further flight, install a shim and replace existing nuts with self-aligning nuts, in accordance with the service bulletin.
(ii) If any peening or crack is found, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.
(b) 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.
(c) 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.
(d) The inspections, installation, replacement, and repair shall be done in accordance with Aerospatiale Service Bulletin ATR72-57-1008, dated November 19, 1992. 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, 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.
(e) This amendment becomes effective on September 16, 1993.