AD 92-18-05
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | ATR - GIE Avions de Transport R gional | ATR42-300 | Airworthiness Directives; AEROSPATIALE Model ATR42-300 and ATR42-320 Series Airplanes |
| aircraft | ATR - GIE Avions de Transport R gional | ATR42-320 | Airworthiness Directives; AEROSPATIALE Model ATR42-300 and ATR42-320 Series Airplanes |
Unsafe Condition
Collapse of the main landing gear due to fatigue cracks in the fastener holes and insufficient reinforcement of the MLG structure.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Install a new machined reinforcement fitting (Modification 1281) on both sides of the main landing gear, perform a one-time eddy current inspection of the fastener holes to detect fatigue cracks, install doublers on Stringer 15 at Frame 25 on the reinforcement plate, and perform cold working procedures on two fastener holes on both sides of the MLG. Repairs must be done before further flight if cracks are found.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Prior to the accumulation of 10,000 landings since new, or within 30 days after the effective date of this AD (October 13, 1992), whichever occurs later.
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Affected Aircraft
AEROSPATIALE Model ATR42-300 and ATR42-320 series airplanes listed in Service Bulletin ATR42-53-0043, Revision 4, dated April 30, 1991.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Main Landing Gear
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_92-18-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 92-18-05 Document Type: AD Final Rules Docket Number: 91-NM-165-AD Subject Heading: Airworthiness Directives; AEROSPATIALE Model ATR42-300 and ATR42-320 Series Airplanes Subject: Main Landing Gear Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/13/1992 Make: ATR - GIE Avions de Transport R gional Model: ATR42-300 | ATR42-320 Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 92-18-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 91-NM-165-AD AMENDMENT: 39-8349 AD NUMBER: 92-18-05 SUBJECT HEADING: Airworthiness Directives; AEROSPATIALE Model ATR42-300 and ATR42-320 Series Airplanes ACTION: SUMMARY: DATES: Effective October 13, 1992. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 92-18-05 AEROSPATIALE: Amendment 39-8349. Docket 91-NM-165-AD. Applicability: Model ATR42-300 and ATR42-320 series airplanes; as listed in Aerospatiale Service Bulletin ATR42-53-0043, Revision 4, dated April 30, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the collapse of the main landing gear, accomplish the following: (a) Prior to the accumulation of 10,000 landings since new, or within 30 days after the effective date of this AD, whichever occurs later, accomplish the following in accordance with Aerospatiale Service Bulletin ATR42-53-0043, Revision 4, dated April 30, 1991: (1) Install a new machined reinforcement fitting (Modification 1281) on the left and right sides of the main landing gear (MLG) in accordance with the service bulletin. (2) Perform a one-time eddy current inspection of the fastener holes on the left and right sides of the MLG to detect fatigue cracks in accordance with the service bulletin. If any cracks are found, prior to further flight, repair in accordance with the service bulletin. (3) Install doublers on Stringer 15 at Frame 25 on the reinforcement plate in accordance with the service bulletin. NOTE: Previous editions of this service bulletin erroneously referred to Stringer 15 as Stringer 14. The doubler can only be installed at Stringer 15. (4) Perform cold working procedures of two fastener holes on the left and right sides of the MLG in accordance with the service bulletin. (b) Airplanes modified prior to the effective date of this AD in accordance with earlier versions of Aerospatiale Service Bulletin ATR42-53-0043 issued prior to Revision 4 need not be inspected or modified further. (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. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (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 installation, inspection, and cold working shall be done in accordance with Aerospatiale Service Bulletin ATR42-53-0043, Revision 4, dated April 30, 1991, which includes the following list of effective pages: Page Number Revision Level Date 1-2, 29 4 April 30, 1991 3-6, 10-28, 30-32 3 October 30, 1990 7-9 Original April 21, 1989 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. (f) This amendment becomes effective on October 13, 1992. FOOTER:
Document Text
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AD Final Rules - DRS_92-18-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 92-18-05 Document Type: AD Final Rules Docket Number: 91-NM-165-AD Subject Heading: Airworthiness Directives; AEROSPATIALE Model ATR42-300 and ATR42-320 Series Airplanes Subject: Main Landing Gear Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/13/1992 Make: ATR - GIE Avions de Transport R gional Model: ATR42-300 | ATR42-320 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: 92-18-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 91-NM-165-AD AMENDMENT: 39-8349 AD NUMBER: 92-18-05 SUBJECT HEADING: Airworthiness Directives; AEROSPATIALE Model ATR42-300 and ATR42-320 Series Airplanes ACTION: SUMMARY: DATES: Effective October 13, 1992. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 92-18-05 AEROSPATIALE: Amendment 39-8349. Docket 91-NM-165-AD. Applicability: Model ATR42-300 and ATR42-320 series airplanes; as listed in Aerospatiale Service Bulletin ATR42-53-0043, Revision 4, dated April 30, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the collapse of the main landing gear, accomplish the following: (a) Prior to the accumulation of 10,000 landings since new, or within 30 days after the effective date of this AD, whichever occurs later, accomplish the following in accordance with Aerospatiale Service Bulletin ATR42-53-0043, Revision 4, dated April 30, 1991: (1) Install a new machined reinforcement fitting (Modification 1281) on the left and right sides of the main landing gear (MLG) in accordance with the service bulletin. (2) Perform a one-time eddy current inspection of the fastener holes on the left and right sides of the MLG to detect fatigue cracks in accordance with the service bulletin. If any cracks are found, prior to further flight, repair in accordance with the service bulletin. (3) Install doublers on Stringer 15 at Frame 25 on the reinforcement plate in accordance with the service bulletin. NOTE: Previous editions of this service bulletin erroneously referred to Stringer 15 as Stringer 14. The doubler can only be installed at Stringer 15. (4) Perform cold working procedures of two fastener holes on the left and right sides of the MLG in accordance with the service bulletin. (b) Airplanes modified prior to the effective date of this AD in accordance with earlier versions of Aerospatiale Service Bulletin ATR42-53-0043 issued prior to Revision 4 need not be inspected or modified further. (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. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (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 installation, inspection, and cold working shall be done in accordance with Aerospatiale Service Bulletin ATR42-53-0043, Revision 4, dated April 30, 1991, which includes the following list of effective pages: Page Number Revision Level Date 1-2, 29 4 April 30, 1991 3-6, 10-28, 30-32 3 October 30, 1990 7-9 Original April 21, 1989 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. (f) This amendment becomes effective on October 13, 1992. FOOTER:
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Retrieved: Apr 8, 2026
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