AD 93-14-17
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | ATR - GIE Avions de Transport R gional | ATR72-101 | Airworthiness Directives; AEROSPATIALE Model ATR72-100 and -200 Series Airplanes |
| aircraft | ATR - GIE Avions de Transport R gional | ATR72-102 | Airworthiness Directives; AEROSPATIALE Model ATR72-100 and -200 Series Airplanes |
| aircraft | ATR - GIE Avions de Transport R gional | ATR72-201 | Airworthiness Directives; AEROSPATIALE Model ATR72-100 and -200 Series Airplanes |
| aircraft | ATR - GIE Avions de Transport R gional | ATR72-202 | Airworthiness Directives; AEROSPATIALE Model ATR72-100 and -200 Series Airplanes |
| aircraft | ATR - GIE Avions de Transport R gional | ATR72-211 | Airworthiness Directives; AEROSPATIALE Model ATR72-100 and -200 Series Airplanes |
| aircraft | ATR - GIE Avions de Transport R gional | ATR72-212 | Airworthiness Directives; AEROSPATIALE Model ATR72-100 and -200 Series Airplanes |
| aircraft | ATR - GIE Avions de Transport R gional | ATR72-212A | Airworthiness Directives; AEROSPATIALE Model ATR72-100 and -200 Series Airplanes |
Unsafe Condition
Reduced structural integrity of the wing spar fittings due to potential peening or cracks in the fastener holes.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Perform a one-time detailed visual inspection of the fastener holes on the front and rear wing spar fittings to ensure spotfacing has been accomplished. If not, conduct a general visual inspection for peening or cracks, then install a shim and replace nuts with self-aligning nuts. If cracks or peening are found, repair using an approved method.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 12 months after the effective date of this AD
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
AEROSPATIALE Model ATR72-100 and -200 series airplanes on which Modification 3196 has not been installed
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Wing Spar Fittings
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_93-14-17.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 93-14-17 Document Type: AD Final Rules Docket Number: 93-NM-15-AD Subject Heading: Airworthiness Directives; AEROSPATIALE Model ATR72-100 and -200 Series Airplanes Subject: Wing Spar Fittings Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 09/16/1993 Make: ATR - GIE Avions de Transport R gional Model: ATR72-101 | ATR72-102 | ATR72-201 | ATR72-202 | ATR72-211 | ATR72-212 | ATR72-212A 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: 93-14-17 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 93-NM-15-AD AMENDMENT: 39-8641 AD NUMBER: 93-14-17 SUBJECT HEADING: Airworthiness Directives; AEROSPATIALE Model ATR72-100 and -200 Series Airplanes ACTION: SUMMARY: DATES: Effective September 16, 1993. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 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. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_93-14-17.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 93-14-17 Document Type: AD Final Rules Docket Number: 93-NM-15-AD Subject Heading: Airworthiness Directives; AEROSPATIALE Model ATR72-100 and -200 Series Airplanes Subject: Wing Spar Fittings Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 09/16/1993 Make: ATR - GIE Avions de Transport R gional Model: ATR72-101 | ATR72-102 | ATR72-201 | ATR72-202 | ATR72-211 | ATR72-212 | ATR72-212A 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: 93-14-17 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 93-NM-15-AD AMENDMENT: 39-8641 AD NUMBER: 93-14-17 SUBJECT HEADING: Airworthiness Directives; AEROSPATIALE Model ATR72-100 and -200 Series Airplanes ACTION: SUMMARY: DATES: Effective September 16, 1993. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 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. FOOTER:
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Retrieved: Apr 8, 2026
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