AD 93-05-11
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Schweizer Aircraft Corporation | 269A | Airworthiness Directives; Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B and 269C Helicopters |
| aircraft | Schweizer Aircraft Corporation | 269A-1 | Airworthiness Directives; Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B and 269C Helicopters |
| aircraft | Schweizer Aircraft Corporation | 269B | Airworthiness Directives; Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B and 269C Helicopters |
| aircraft | Schweizer Aircraft Corporation | 269C | Airworthiness Directives; Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B and 269C Helicopters |
Unsafe Condition
Restriction to the movement of the engine throttle control linkage that could result in loss of control of engine power due to tube assembly interference.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Within 5 hours time in service after the effective date, inspect the tube assembly length and check for security and clearance from the throttle linkage. If issues are found, install improved tube assembly P/N 269A8326-235 with clamp P/N MS21333-98 or secure the existing tube assembly and conduct repetitive checks. Replace the tube assembly within 6 months after the effective date.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 5 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 25 hours time in service from the last check
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A helicopters with fuel injected engines; all Model 269A-1 and 269B helicopters; Model 269C helicopters, serial numbers 0004 through 1480 and 1482 through 1486, equipped with engine-driven fuel pump drain tube assembly P/N 269A8326-95.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Fuel Pump Drain Tube Assembly
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_93-05-11.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 93-05-11 Document Type: AD Final Rules Docket Number: 92-ASW-47 Subject Heading: Airworthiness Directives; Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 26...Show more Subject: Fuel Pump Drain Tube Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/25/1993 Make: Schweizer Aircraft Corporation Model: 269A | 269A-1 | 269B | 269C Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 93-05-11 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 92-ASW-47 AMENDMENT: 39-8515 AD NUMBER: 93-05-11 SUBJECT HEADING: Airworthiness Directives; Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B and 269C Helicopters ACTION: SUMMARY: DATES: Effective May 25, 1993. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 93-05-11 SCHWEIZER AIRCRAFT CORPORATION AND HUGHES HELICOPTERS, INC.: Amendment 39-8515. Docket No. 92-ASW-47. Applicability: Model 269A helicopters with fuel injected engines; all Model 269A-1 and 269B helicopters; and Model 269C helicopters, serial numbers (S/N) 0004 through 1480 and 1482 through 1486; equipped with an engine-driven fuel pump drain tube assembly (tube assembly), part number (P/N) 269A8326-95, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent a restriction to the movement of the engine throttle control linkage that could result in loss of control of engine power due to tube assembly interference, accomplish the following: (a) Within 5 hours time in service after the effective date of this AD, perform a one-time inspection of the length of the tube assembly, P/N 269A8326-95, in accordance with Part I of Schweizer Aircraft Corporation (Schweizer) Service Bulletin B-235.1, dated March 20, 1992 (SSB). If the tube assembly length is less than 7.50 inches, before next flight, install tube assembly, P/N 269A8326-235, with a clamp, P/N MS21333-98, in accordance with Part III of the SSB. (b) Within 5 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 25 hours time in service from the last check, check the tube assembly, P/N 269A8326-95, for security and clearance from the throttle linkage as follows: (1) Move the throttle linkage from fully open to fully closed and verify that the tube assembly is not loose and does not interfere with movement of the throttle linkage. (2) If the tube assembly interferes with movement of the throttle linkage, before next flight-- (i) Install tube assembly, P/N 269A8326-235, with a clamp, P/N MS21333-98, in accordance with Part III of the SSB; or (ii) Secure tube assembly, P/N 269A8326-95, in accordance with Part II b of the SSB and conduct repetitive checks as prescribed by this paragraph. (3) After the initial check, the repetitive check contained in this paragraph may be performed by the pilot and must be recorded in accordance with FAR 43.9. (c) Within 6 months after the effective date of this AD, replace the tube assembly, P/N 269A8326-95, with an improved tube assembly, P/N 269A8326-235, and clamp, P/N MS21333-98, in accordance with Part III of the SSB. (d) Installation of the improved tube assembly, P/N 269A8326-235, and clamp, P/N MS21333-98, constitutes terminating action for the requirements of this AD. (e) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, New York Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Manager, New York Aircraft Certification Office. (f) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished. (g) The inspections and modifications shall be done in accordance with Schweizer Service Bulletin B-235.1, dated March 20, 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 Schweizer Aircraft Corporation, P.O. Box 147, Elmira, New York 14902. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 4400 Blue Mound Road, Bldg. 3B, Room 158, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective May 25, 1993. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_93-05-11.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 93-05-11 Document Type: AD Final Rules Docket Number: 92-ASW-47 Subject Heading: Airworthiness Directives; Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 26...Show more Subject: Fuel Pump Drain Tube Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/25/1993 Make: Schweizer Aircraft Corporation Model: 269A | 269A-1 | 269B | 269C Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 93-05-11 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 92-ASW-47 AMENDMENT: 39-8515 AD NUMBER: 93-05-11 SUBJECT HEADING: Airworthiness Directives; Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B and 269C Helicopters ACTION: SUMMARY: DATES: Effective May 25, 1993. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 93-05-11 SCHWEIZER AIRCRAFT CORPORATION AND HUGHES HELICOPTERS, INC.: Amendment 39-8515. Docket No. 92-ASW-47. Applicability: Model 269A helicopters with fuel injected engines; all Model 269A-1 and 269B helicopters; and Model 269C helicopters, serial numbers (S/N) 0004 through 1480 and 1482 through 1486; equipped with an engine-driven fuel pump drain tube assembly (tube assembly), part number (P/N) 269A8326-95, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent a restriction to the movement of the engine throttle control linkage that could result in loss of control of engine power due to tube assembly interference, accomplish the following: (a) Within 5 hours time in service after the effective date of this AD, perform a one-time inspection of the length of the tube assembly, P/N 269A8326-95, in accordance with Part I of Schweizer Aircraft Corporation (Schweizer) Service Bulletin B-235.1, dated March 20, 1992 (SSB). If the tube assembly length is less than 7.50 inches, before next flight, install tube assembly, P/N 269A8326-235, with a clamp, P/N MS21333-98, in accordance with Part III of the SSB. (b) Within 5 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 25 hours time in service from the last check, check the tube assembly, P/N 269A8326-95, for security and clearance from the throttle linkage as follows: (1) Move the throttle linkage from fully open to fully closed and verify that the tube assembly is not loose and does not interfere with movement of the throttle linkage. (2) If the tube assembly interferes with movement of the throttle linkage, before next flight-- (i) Install tube assembly, P/N 269A8326-235, with a clamp, P/N MS21333-98, in accordance with Part III of the SSB; or (ii) Secure tube assembly, P/N 269A8326-95, in accordance with Part II b of the SSB and conduct repetitive checks as prescribed by this paragraph. (3) After the initial check, the repetitive check contained in this paragraph may be performed by the pilot and must be recorded in accordance with FAR 43.9. (c) Within 6 months after the effective date of this AD, replace the tube assembly, P/N 269A8326-95, with an improved tube assembly, P/N 269A8326-235, and clamp, P/N MS21333-98, in accordance with Part III of the SSB. (d) Installation of the improved tube assembly, P/N 269A8326-235, and clamp, P/N MS21333-98, constitutes terminating action for the requirements of this AD. (e) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, New York Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Manager, New York Aircraft Certification Office. (f) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished. (g) The inspections and modifications shall be done in accordance with Schweizer Service Bulletin B-235.1, dated March 20, 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 Schweizer Aircraft Corporation, P.O. Box 147, Elmira, New York 14902. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 4400 Blue Mound Road, Bldg. 3B, Room 158, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective May 25, 1993. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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