AD 63-21-03
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Hiller Aviation | Siam Hiller Holdings, Inc. | UH-12D | Airworthiness Directives; Hiller Models UH-12D and UH-12E Helicopters |
| aircraft | Hiller Aviation | Siam Hiller Holdings, Inc. | UH-12E | Airworthiness Directives; Hiller Models UH-12D and UH-12E Helicopters |
Unsafe Condition
Fatigue cracking and brazed doubler separation of main rotor blades, Parsons P/N's 2253-1101-02 and 2253-1101-03, near the outboard end of the steel doubler brazed to the leading edge spar.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect top and bottom surfaces of each blade with a 4 to 6-power magnifying glass within 10 hours' time in service from the effective date and daily thereafter. Conduct dye penetrant inspections within 10 hours' time in service after October 15, 1963, and at intervals not exceeding 25 hours (for blades Serial Number 1269 and below) or 100 hours (for blades Serial Number 1270 and above) from the last inspection. Inspect for cracks in the main rotor blade fork bolt hole and adjacent surfaces via dye penetrant if unusual vibration occurs, replace cracked forks before flight. Remove blades with cracks or separation from service before further flight.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Compliance required as indicated.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Hiller Models UH-12D and UH-12E Helicopters with main rotor blades Parsons P/N's 2253-1101-02 and 2253-1101-03.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Main Rotor Blades
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_63-21-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 63-21-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Hiller Models UH-12D and UH-12E Helicopters Subject: Main Rotor Blades Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: Hiller Aviation | Siam Hiller Holdings, Inc. Model: UH-12D | UH-12E Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 63-21-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 63-21-03 SUBJECT HEADING: Airworthiness Directives; Hiller Models UH-12D and UH-12E Helicopters ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 63-21-03 HILLER: Amdt. 631 Part 507 Federal Register October 15, 1963. Applies to Models UH-12D and UH-12E Helicopters. Compliance required as indicated. Due to fatigue cracking and brazed doubler separation of main rotor blade, Parsons P/N's 2253-1101-02 and 2253-1101-03, inspect the top and bottom surfaces of each blade after removing paint in the area adjacent to the outboard end of the steel doubler brazed to the leading edge spar (approximately 27 inches from the blade root end), for doubler separation and for cracks in the leading edge spar near the end of the doubler as follows: (a) For all main rotor blades, conduct a visual inspection of the affected areas with a 4 to 6-power magnifying glass within 10 hours' time in service from the effective date of this AD and daily thereafter. When inspecting for cracks or separation in the lower surface, the blade tip must be supported in a manner to remove all droop from the blade. (b) For all main rotor blades, conduct a dye penetrant inspection of the affected areas within the next 10 hours' time in service after October 15, 1963, and thereafter at intervals not to exceed 25 hours' time in service from the last dye penetrant inspection for blades, Serial Number 1269 and below, and at intervals not to exceed 100 hours' time in service from the last dye penetrant inspection for blades, Serial Number 1270 and above. (c) In the event of any unusual main rotor vibration that cannot be corrected by normal tracking, balancing or rigging procedures, conduct a dye penetrant inspection of the affected areas. In addition, inspect for cracks the bolt hole and adjacent milled surfaces of the main rotor blade fork P/N 52110-3 by means of a dye penetrant inspection or FAA approved equivalent. For this inspection remove nut, washer and pin. Replace cracked forks before further flight. (d) Main rotor blades with cracks or doubler separation must be removed from service before further flight. (e) The repetitive visual and dye penetrant inspections required by this AD may be discontinued after the installation of blades. Parsons P/N 2253-1101-04. (Hiller Service Information Letter No. 3037A covers this subject.) This supersedes AD 60-17-02. This directive effective October 15, 1963. Revised April 8, 1966. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_63-21-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 63-21-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Hiller Models UH-12D and UH-12E Helicopters Subject: Main Rotor Blades Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: Hiller Aviation | Siam Hiller Holdings, Inc. Model: UH-12D | UH-12E 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: 63-21-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 63-21-03 SUBJECT HEADING: Airworthiness Directives; Hiller Models UH-12D and UH-12E Helicopters ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 63-21-03 HILLER: Amdt. 631 Part 507 Federal Register October 15, 1963. Applies to Models UH-12D and UH-12E Helicopters. Compliance required as indicated. Due to fatigue cracking and brazed doubler separation of main rotor blade, Parsons P/N's 2253-1101-02 and 2253-1101-03, inspect the top and bottom surfaces of each blade after removing paint in the area adjacent to the outboard end of the steel doubler brazed to the leading edge spar (approximately 27 inches from the blade root end), for doubler separation and for cracks in the leading edge spar near the end of the doubler as follows: (a) For all main rotor blades, conduct a visual inspection of the affected areas with a 4 to 6-power magnifying glass within 10 hours' time in service from the effective date of this AD and daily thereafter. When inspecting for cracks or separation in the lower surface, the blade tip must be supported in a manner to remove all droop from the blade. (b) For all main rotor blades, conduct a dye penetrant inspection of the affected areas within the next 10 hours' time in service after October 15, 1963, and thereafter at intervals not to exceed 25 hours' time in service from the last dye penetrant inspection for blades, Serial Number 1269 and below, and at intervals not to exceed 100 hours' time in service from the last dye penetrant inspection for blades, Serial Number 1270 and above. (c) In the event of any unusual main rotor vibration that cannot be corrected by normal tracking, balancing or rigging procedures, conduct a dye penetrant inspection of the affected areas. In addition, inspect for cracks the bolt hole and adjacent milled surfaces of the main rotor blade fork P/N 52110-3 by means of a dye penetrant inspection or FAA approved equivalent. For this inspection remove nut, washer and pin. Replace cracked forks before further flight. (d) Main rotor blades with cracks or doubler separation must be removed from service before further flight. (e) The repetitive visual and dye penetrant inspections required by this AD may be discontinued after the installation of blades. Parsons P/N 2253-1101-04. (Hiller Service Information Letter No. 3037A covers this subject.) This supersedes AD 60-17-02. This directive effective October 15, 1963. Revised April 8, 1966. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.