AD 93-21-03
final rule
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 TH-55A Series Helicopters |
| aircraft | Schweizer Aircraft Corporation | 269A-1 | Airworthiness Directives; SCHWEIZER AIRCRAFT CORPORATION AND HUGHES HELICOPTERS, INC. Model 269A, 269A-1, 269B, and TH-55A Series Helicopters |
| aircraft | Schweizer Aircraft Corporation | 269B | Airworthiness Directives; SCHWEIZER AIRCRAFT CORPORATION AND HUGHES HELICOPTERS, INC. Model 269A, 269A-1, 269B, and TH-55A Series Helicopters |
Unsafe Condition
Fatigue failure of the magnesium tailboom center attachment [saddle] fitting could result in loss of the tailboom and subsequent loss of control of the helicopter.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Visually inspect the magnesium fitting and tailboom assembly for fretting, corrosion, and cracks using a 10-power or higher magnifying glass. Inspect the magnesium fitting for cracks using a dye penetrant inspection. Replace unairworthy magnesium fittings with an airworthy aluminum fitting, P/N 269A2324-13 (undrilled).
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Compliance Time
Required as indicated, unless accomplished previously.
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Affected Aircraft
Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B, and TH-55A series helicopters, certificated in any category.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Magnesium Tailboom Fitting
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_93-21-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 93-21-03 Document Type: AD Final Rules Docket Number: 91-ASW-11 Subject Heading: Airworthiness Directives; SCHWEIZER AIRCRAFT CORPORATION AND HUGHES HELICOPTERS, INC. Model 269A, 26...Show more Subject: Magnesium Tailboom Fitting Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 12/17/1993 Make: Schweizer Aircraft Corporation Model: 269A | 269A-1 | 269B Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 93-21-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 91-ASW-11 AMENDMENT: 39-8718 AD NUMBER: 93-21-03 SUBJECT HEADING: Airworthiness Directives; SCHWEIZER AIRCRAFT CORPORATION AND HUGHES HELICOPTERS, INC. Model 269A, 269A-1, 269B, and TH-55A Series Helicopters ACTION: SUMMARY: DATES: Effective December 17, 1993. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 93-21-03 SCHWEIZER AIRCRAFT CORPORATION AND HUGHES HELICOPTERS, INC.: Amendment 39-8718. Docket Number 91-ASW-11. Supersedes AD 80-05-05, Amendment 39-3707, Docket Number 80-WE-3-AD. Applicability: Model 269A, 269A-1, 269B, and TH-55A series helicopters, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent fatigue failure of the magnesium tailboom center attachment [saddle] fitting (fitting) that could result in loss of the tailboom and subsequent loss of control of the helicopter, accomplish the following: (a) For each helicopter with a magnesium fitting, part number (P/N) 269A2324 (BSC) or 269A2324-7, with 4,000 or less hours' time-in-service on the effective date of this AD, perform the following in accordance with the 269 Series Basic Handbook of Maintenance Information, as revised by Temporary Revision No. R-42, dated October 8, 1990 (HMI): (1) Prior to further flight and thereafter at intervals not to exceed 50 hours' time-in-service from the last inspection, visually inspect the magnesium fitting and tailboom assembly for fretting, corrosion, and cracks using a 10-power or higher magnifying glass. (2) Within the next 25 hours' time-in-service after the effective date of this AD and thereafter at intervals not to exceed 100 hours' time-in-service from the last inspection, inspect the magnesium fitting for cracks using a dye penetrant inspection. (3) If the magnesium fitting, P/N 269A2324 (BSC) or 269A2324-7, is found unairworthy by the inspections required by this paragraph, before further flight, remove and replace it with an airworthy aluminum fitting, P/N 269A2324-13 (undrilled). (4) Prior to accumulating 4,100 hours' time-in-service, replace the magnesium fitting, P/N 269A2324 (BSC) or P/N 269A2324-7, with an airworthy aluminum fitting, P/N 269A2324-13 (undrilled). (b) For each helicopter with a magnesium fitting, P/N 269A2324 (BSC) or P/N 269A2324-7, with more than 4,000 hours' time-in-service on the effective date of the AD, perform the following in accordance with the HMI: (1) Before the first flight of each day, visually inspect the magnesium fitting and tailboom assembly for fretting, corrosion and cracks using a 10-power or higher magnifying glass. (2) Prior to further flight after the effective date of this AD and thereafter at an interval not to exceed 50 hours' time-in-service from the last inspection, inspect the magnesium fitting for cracks using a dye penetrant inspection. (3) If the magnesium fitting, P/N 269A2324 (BSC) or 269A2324-7, is found unairworthy by the inspections required by this paragraph, before further flight, remove and replace it with an airworthy aluminum fitting, P/N 269A2324-13 (undrilled). (4) Within the next 100 hours' time-in-service, replace the magnesium fitting, P/N 269A2324 (BSC) or 269A2324-7, with an airworthy aluminum fitting, P/N 269A2324-13 (undrilled). (c) Installation of an aluminum fitting, P/N 269A2324-13 (undrilled), constitutes terminating action for the requirements of this AD. NOTE: Schweizer Aircraft Corporation Service Bulletin B-238.1, dated November 7, 1991, pertains to this AD. (d) 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 S. Franklin Avenue, Room 202, Valley Stream, New York 11581-1145. 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 airworthiness directive, if any, may be obtained from the Manager, New York Aircraft Certification Office. (e) 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. (f) This amendment becomes effective December 17, 1993. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_93-21-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 93-21-03 Document Type: AD Final Rules Docket Number: 91-ASW-11 Subject Heading: Airworthiness Directives; SCHWEIZER AIRCRAFT CORPORATION AND HUGHES HELICOPTERS, INC. Model 269A, 26...Show more Subject: Magnesium Tailboom Fitting Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 12/17/1993 Make: Schweizer Aircraft Corporation Model: 269A | 269A-1 | 269B 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: 93-21-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 91-ASW-11 AMENDMENT: 39-8718 AD NUMBER: 93-21-03 SUBJECT HEADING: Airworthiness Directives; SCHWEIZER AIRCRAFT CORPORATION AND HUGHES HELICOPTERS, INC. Model 269A, 269A-1, 269B, and TH-55A Series Helicopters ACTION: SUMMARY: DATES: Effective December 17, 1993. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 93-21-03 SCHWEIZER AIRCRAFT CORPORATION AND HUGHES HELICOPTERS, INC.: Amendment 39-8718. Docket Number 91-ASW-11. Supersedes AD 80-05-05, Amendment 39-3707, Docket Number 80-WE-3-AD. Applicability: Model 269A, 269A-1, 269B, and TH-55A series helicopters, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent fatigue failure of the magnesium tailboom center attachment [saddle] fitting (fitting) that could result in loss of the tailboom and subsequent loss of control of the helicopter, accomplish the following: (a) For each helicopter with a magnesium fitting, part number (P/N) 269A2324 (BSC) or 269A2324-7, with 4,000 or less hours' time-in-service on the effective date of this AD, perform the following in accordance with the 269 Series Basic Handbook of Maintenance Information, as revised by Temporary Revision No. R-42, dated October 8, 1990 (HMI): (1) Prior to further flight and thereafter at intervals not to exceed 50 hours' time-in-service from the last inspection, visually inspect the magnesium fitting and tailboom assembly for fretting, corrosion, and cracks using a 10-power or higher magnifying glass. (2) Within the next 25 hours' time-in-service after the effective date of this AD and thereafter at intervals not to exceed 100 hours' time-in-service from the last inspection, inspect the magnesium fitting for cracks using a dye penetrant inspection. (3) If the magnesium fitting, P/N 269A2324 (BSC) or 269A2324-7, is found unairworthy by the inspections required by this paragraph, before further flight, remove and replace it with an airworthy aluminum fitting, P/N 269A2324-13 (undrilled). (4) Prior to accumulating 4,100 hours' time-in-service, replace the magnesium fitting, P/N 269A2324 (BSC) or P/N 269A2324-7, with an airworthy aluminum fitting, P/N 269A2324-13 (undrilled). (b) For each helicopter with a magnesium fitting, P/N 269A2324 (BSC) or P/N 269A2324-7, with more than 4,000 hours' time-in-service on the effective date of the AD, perform the following in accordance with the HMI: (1) Before the first flight of each day, visually inspect the magnesium fitting and tailboom assembly for fretting, corrosion and cracks using a 10-power or higher magnifying glass. (2) Prior to further flight after the effective date of this AD and thereafter at an interval not to exceed 50 hours' time-in-service from the last inspection, inspect the magnesium fitting for cracks using a dye penetrant inspection. (3) If the magnesium fitting, P/N 269A2324 (BSC) or 269A2324-7, is found unairworthy by the inspections required by this paragraph, before further flight, remove and replace it with an airworthy aluminum fitting, P/N 269A2324-13 (undrilled). (4) Within the next 100 hours' time-in-service, replace the magnesium fitting, P/N 269A2324 (BSC) or 269A2324-7, with an airworthy aluminum fitting, P/N 269A2324-13 (undrilled). (c) Installation of an aluminum fitting, P/N 269A2324-13 (undrilled), constitutes terminating action for the requirements of this AD. NOTE: Schweizer Aircraft Corporation Service Bulletin B-238.1, dated November 7, 1991, pertains to this AD. (d) 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 S. Franklin Avenue, Room 202, Valley Stream, New York 11581-1145. 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 airworthiness directive, if any, may be obtained from the Manager, New York Aircraft Certification Office. (e) 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. (f) This amendment becomes effective December 17, 1993. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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