AD 93-07-04
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | BAE Systems (Operations) Limited | ATP | Airworthiness Directives; British Aerospace Model ATP Series Airplanes |
Unsafe Condition
Possible loss of integrity and security of the flap drive system due to missing split pins on the four bolt and nut assemblies of the right gearbox drive at station 0.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Perform a one-time general visual inspection of the primary flap drive torque tubes to check for split pins. If split pins are missing, check tighten bolts to 8 to 10 foot pounds torque prior to further flight and repeat every 14 days. Within 6 months, install split pins as per ATP-27-55. Installation of split pins terminates the requirements.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 14 days after the effective date of this AD (May 10, 1993) for the initial inspection. Missing split pins require check tightening prior to further flight and repeat every 14 days, with installation within 6 months after the effective date.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
British Aerospace Model ATP series airplanes, serial numbers 2001 through 2049, inclusive.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Inspect Primary Flap Drive Torque Tubes
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_93-07-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 93-07-04 Document Type: AD Final Rules Docket Number: 92-NM-189-AD Subject Heading: Airworthiness Directives; British Aerospace Model ATP Series Airplanes Subject: Inspect Primary Flap Drive Torque Tubes Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/10/1993 Make: BAE Systems (Operations) Limited Model: ATP Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 93-07-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 92-NM-189-AD AMENDMENT: 39-8536 AD NUMBER: 93-07-04 SUBJECT HEADING: Airworthiness Directives; British Aerospace Model ATP Series Airplanes ACTION: SUMMARY: DATES: Effective on May 10, 1993. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 93-07-04 BRITISH AEROSPACE: Amendment 39-8536. Docket 92-NM-189-AD. Applicability: Model ATP series airplanes; serial numbers 2001 through 2049, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent possible loss of integrity and security of the flap drive system, accomplish the following: (a) Within 14 days after the effective date of this AD, perform a one-time general visual inspection of the primary flap drive torque tubes to ensure that the four bolt and nut assemblies on the splined flanged-coupling assembly on the right gearbox drive at station 0 have split pins installed, in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 1992. (1) If split pins are installed, no further action is necessary. (2) If any split pin is missing, accomplish the requirements of both paragraphs (a)(2)(i) and (a)(2)(ii) of this AD: (i) Prior to further flight, check tighten each of the four bolts to 8 to 10 foot pounds torque. Repeat this check tightening thereafter at intervals not to exceed 14 days. (ii) Within 6 months after the effective date of this AD, install split pins in the bolt and nut assemblies in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 1992. Installation of these split pins constitutes terminating action for the inspections and check tightening requirements of this paragraph. (b) Installation of split pins in the bolt and nut assemblies in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 1992, constitutes terminating action for the requirements of paragraph (a) 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. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, 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 installation shall be done in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 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 Jetstream Aircraft, Inc., Librarian for Service Bulletins, P.O. Box 16029, Dulles International Airport, Washington, DC 20041-6029. 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 May 10, 1993. FOOTER:
Document Text
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AD Final Rules - DRS_93-07-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 93-07-04 Document Type: AD Final Rules Docket Number: 92-NM-189-AD Subject Heading: Airworthiness Directives; British Aerospace Model ATP Series Airplanes Subject: Inspect Primary Flap Drive Torque Tubes Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/10/1993 Make: BAE Systems (Operations) Limited Model: ATP 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: 93-07-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 92-NM-189-AD AMENDMENT: 39-8536 AD NUMBER: 93-07-04 SUBJECT HEADING: Airworthiness Directives; British Aerospace Model ATP Series Airplanes ACTION: SUMMARY: DATES: Effective on May 10, 1993. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 93-07-04 BRITISH AEROSPACE: Amendment 39-8536. Docket 92-NM-189-AD. Applicability: Model ATP series airplanes; serial numbers 2001 through 2049, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent possible loss of integrity and security of the flap drive system, accomplish the following: (a) Within 14 days after the effective date of this AD, perform a one-time general visual inspection of the primary flap drive torque tubes to ensure that the four bolt and nut assemblies on the splined flanged-coupling assembly on the right gearbox drive at station 0 have split pins installed, in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 1992. (1) If split pins are installed, no further action is necessary. (2) If any split pin is missing, accomplish the requirements of both paragraphs (a)(2)(i) and (a)(2)(ii) of this AD: (i) Prior to further flight, check tighten each of the four bolts to 8 to 10 foot pounds torque. Repeat this check tightening thereafter at intervals not to exceed 14 days. (ii) Within 6 months after the effective date of this AD, install split pins in the bolt and nut assemblies in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 1992. Installation of these split pins constitutes terminating action for the inspections and check tightening requirements of this paragraph. (b) Installation of split pins in the bolt and nut assemblies in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 1992, constitutes terminating action for the requirements of paragraph (a) 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. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, 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 installation shall be done in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 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 Jetstream Aircraft, Inc., Librarian for Service Bulletins, P.O. Box 16029, Dulles International Airport, Washington, DC 20041-6029. 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 May 10, 1993. FOOTER:
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Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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