AD 64-28-02
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Schweizer Aircraft Corporation | 269A | Airworthiness Directives; Hughes Models 269A, 269A-1, 269A-2 and 269B helicopters. |
| aircraft | Schweizer Aircraft Corporation | 269A-1 | Airworthiness Directives; Hughes Models 269A, 269A-1, 269A-2 and 269B helicopters. |
| aircraft | Schweizer Aircraft Corporation | 269B | Airworthiness Directives; Hughes Models 269A, 269A-1, 269A-2 and 269B helicopters. |
Unsafe Condition
Inadequate lubrication of the main rotor blade flapping hinge bearings can cause binding, resulting in overstressing and failure of one main rotor blade.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect main rotor blade flapping hinge bearings for wear/damage per specified intervals; apply MIL-G-25537 grease at 25-hour intervals and ensure grease exudes from all bearings; remove bearings or blades from service if wear exceeds 0.002 inch limits or cracks are found; follow Hughes Service Information Notices for inspections.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Compliance required as indicated in the AD, with inspections due based on time in service: helicopters with <100 hours must inspect before 110 hours and every 400 hours thereafter; those with ≥100 hours must inspect within 10 hours and every 400 hours thereafter; grease application must occur within 10 hours after AD effective date and every 25 hours thereafter.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Schweizer Aircraft Corporation Models 269A, 269A-1, 269A-2, and 269B helicopters.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Main Rotor Blade Flapping Hinge Bearing
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_64-28-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 64-28-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Hughes Models 269A, 269A-1, 269A-2 and 269B helicopters. Subject: Main Rotor Blade Flapping Hinge Bearing Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 07/06/1968 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: 64-28-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-617 AD NUMBER: 64-28-02 SUBJECT HEADING: Airworthiness Directives; Hughes Models 269A, 269A-1, 269A-2 and 269B helicopters. ACTION: SUMMARY: DATES: Effective on July 6, 1968. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 64-28-02 HUGHES: Amendment 39-617. Applies to Models 269A, 269A-1, 269A-2 and 269B helicopters. Compliance required as indicated. Due to inadequate lubrication of the main rotor blade flapping hinge bearings, binding has occurred, resulting in overstressing and failure of one main rotor blade. To prevent main rotor blade overstressing and failure, accomplish the following: (a) For helicopters having less than 100 hours' time in service on the effective date of this AD inspect the main rotor blade flapping hinge bearings for the condition indicated in (d), prior to the accumulation of 110 hours' time in service, unless already accomplished, and thereafter at periods not to exceed 400 hours' time in service from the last inspection. (b) For helicopters having 100 hours' or more time in service on the effective date of this AD inspect the main rotor blade flapping hinge bearings for the condition indicated in (d), within the next 10 hours' time in service, unless already accomplished within the last 390 hours' time in service, and thereafter at periods not to exceed 400 hours' time in service from the last inspection. (c) Within 10 hours' time in service, after the effective date of this AD, unless already accomplished within the last 15 hours' time in service, and thereafter at periods not to exceed 25 hours' time in service, apply MIL-G-25537 grease through the grease fittings to all main rotor blade flapping hinge bearings and inspect to ascertain that a thorough purging of the bearings has been achieved. If new grease does not exude from all six bearings, inspect the bearings at the location where the grease does not exude, for the condition indicated in (d), before further flight. (d) If bearings are found to be worn or damaged in excess of the limits specified in Hughes Service Information Notice No. 2A-39.1, 2A-1-06.1 or 2B-07-.1, remove from service before further flight. (e) If the inner race of any bearing is found to be brinelled or worn in excess of the 0.002 inch limit specified in Hughes Service Information Notice No. 2A-39.1, 2A-1-06.1 or 2B- 07.1, remove the corresponding main rotor blade from service before further flight, and conspicuously mark it to prevent inadvertent return to service. (f) If the inner race of any bearing is brinelled or worn, but not in excess of the 0.002 inch limit specified in Hughes Service Information Notice No. 2A-39.1, 2A-1-06.1 or 2B- 07.1, inspect the corresponding main rotor blade for skin cracks in the exposed areas adjacent to the edges of the blade root fitting beside the outboard bolt. Inspect both upper and lower surfaces of the blade, using a 4- to 6-power magnifying glass. If any cracks are found remove the blade from service before further flight. (g) Starting with the effective date of this AD, conduct initial and repetitive inspections of all main rotor blades in a manner and at periods specified in Hughes Service Information Notices No. 2A-38 dated September 9, 1964, No. 2A-1-05 dated September 14, 1964, and No. 2B-06 dated September 16, 1964, or later revisions approved by FAA Western Region Aircraft Engineering Division. (h) The following Hughes Service Information Notices or later FAA approved revisions are approved alternatives to those specified in (d), (e), (f) and (g) above: Notice No. N-10.1 dated December 14, 1967, is an approved alternate to Notices 2A-38, 2A-1-05 and 2B-06. Notice No. N-47 dated April 18, 1968, is an approved alternate to Notices 2A-39.1, 2A- 1-06.1 and 2B-07-.1. This amendment becomes effective on July 6, 1968. FOOTER:
Document Text
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AD Final Rules - DRS_64-28-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 64-28-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Hughes Models 269A, 269A-1, 269A-2 and 269B helicopters. Subject: Main Rotor Blade Flapping Hinge Bearing Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 07/06/1968 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: 64-28-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-617 AD NUMBER: 64-28-02 SUBJECT HEADING: Airworthiness Directives; Hughes Models 269A, 269A-1, 269A-2 and 269B helicopters. ACTION: SUMMARY: DATES: Effective on July 6, 1968. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 64-28-02 HUGHES: Amendment 39-617. Applies to Models 269A, 269A-1, 269A-2 and 269B helicopters. Compliance required as indicated. Due to inadequate lubrication of the main rotor blade flapping hinge bearings, binding has occurred, resulting in overstressing and failure of one main rotor blade. To prevent main rotor blade overstressing and failure, accomplish the following: (a) For helicopters having less than 100 hours' time in service on the effective date of this AD inspect the main rotor blade flapping hinge bearings for the condition indicated in (d), prior to the accumulation of 110 hours' time in service, unless already accomplished, and thereafter at periods not to exceed 400 hours' time in service from the last inspection. (b) For helicopters having 100 hours' or more time in service on the effective date of this AD inspect the main rotor blade flapping hinge bearings for the condition indicated in (d), within the next 10 hours' time in service, unless already accomplished within the last 390 hours' time in service, and thereafter at periods not to exceed 400 hours' time in service from the last inspection. (c) Within 10 hours' time in service, after the effective date of this AD, unless already accomplished within the last 15 hours' time in service, and thereafter at periods not to exceed 25 hours' time in service, apply MIL-G-25537 grease through the grease fittings to all main rotor blade flapping hinge bearings and inspect to ascertain that a thorough purging of the bearings has been achieved. If new grease does not exude from all six bearings, inspect the bearings at the location where the grease does not exude, for the condition indicated in (d), before further flight. (d) If bearings are found to be worn or damaged in excess of the limits specified in Hughes Service Information Notice No. 2A-39.1, 2A-1-06.1 or 2B-07-.1, remove from service before further flight. (e) If the inner race of any bearing is found to be brinelled or worn in excess of the 0.002 inch limit specified in Hughes Service Information Notice No. 2A-39.1, 2A-1-06.1 or 2B- 07.1, remove the corresponding main rotor blade from service before further flight, and conspicuously mark it to prevent inadvertent return to service. (f) If the inner race of any bearing is brinelled or worn, but not in excess of the 0.002 inch limit specified in Hughes Service Information Notice No. 2A-39.1, 2A-1-06.1 or 2B- 07.1, inspect the corresponding main rotor blade for skin cracks in the exposed areas adjacent to the edges of the blade root fitting beside the outboard bolt. Inspect both upper and lower surfaces of the blade, using a 4- to 6-power magnifying glass. If any cracks are found remove the blade from service before further flight. (g) Starting with the effective date of this AD, conduct initial and repetitive inspections of all main rotor blades in a manner and at periods specified in Hughes Service Information Notices No. 2A-38 dated September 9, 1964, No. 2A-1-05 dated September 14, 1964, and No. 2B-06 dated September 16, 1964, or later revisions approved by FAA Western Region Aircraft Engineering Division. (h) The following Hughes Service Information Notices or later FAA approved revisions are approved alternatives to those specified in (d), (e), (f) and (g) above: Notice No. N-10.1 dated December 14, 1967, is an approved alternate to Notices 2A-38, 2A-1-05 and 2B-06. Notice No. N-47 dated April 18, 1968, is an approved alternate to Notices 2A-39.1, 2A- 1-06.1 and 2B-07-.1. This amendment becomes effective on July 6, 1968. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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