AD 62-27-03
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airlift International, Inc. | Curtiss-Wright Corporation | Flying Tiger Line, Inc. | L. B. Smith Aircraft Corporation | Skyways International Trading and Transport Co. | Tempo Design Corporation | C-46A | CURTISS-WRIGHT Model C-46 Series Aircraft |
| aircraft | Airlift International, Inc. | Curtiss-Wright Corporation | Flying Tiger Line, Inc. | L. B. Smith Aircraft Corporation | Skyways International Trading and Transport Co. | Tempo Design Corporation | C-46D | CURTISS-WRIGHT Model C-46 Series Aircraft |
| aircraft | Airlift International, Inc. | Curtiss-Wright Corporation | Flying Tiger Line, Inc. | L. B. Smith Aircraft Corporation | Skyways International Trading and Transport Co. | Tempo Design Corporation | C-46F | CURTISS-WRIGHT Model C-46 Series Aircraft |
| aircraft | Airlift International, Inc. | Curtiss-Wright Corporation | Flying Tiger Line, Inc. | L. B. Smith Aircraft Corporation | Skyways International Trading and Transport Co. | Tempo Design Corporation | C-46R | CURTISS-WRIGHT Model C-46 Series Aircraft |
| aircraft | Airlift International, Inc. | Curtiss-Wright Corporation | Flying Tiger Line, Inc. | L. B. Smith Aircraft Corporation | Skyways International Trading and Transport Co. | Tempo Design Corporation | C-46E | CURTISS-WRIGHT Model C-46 Series Aircraft |
| aircraft | Airlift International, Inc. | Curtiss-Wright Corporation | Flying Tiger Line, Inc. | L. B. Smith Aircraft Corporation | Skyways International Trading and Transport Co. | Tempo Design Corporation | C-46/CW20-T | CURTISS-WRIGHT Model C-46 Series Aircraft |
| aircraft | Airlift International, Inc. | Curtiss-Wright Corporation | Flying Tiger Line, Inc. | L. B. Smith Aircraft Corporation | Skyways International Trading and Transport Co. | Tempo Design Corporation | Super C-46/CW20-T | CURTISS-WRIGHT Model C-46 Series Aircraft |
Unsafe Condition
Failure of the rudder spring tab rod terminal can cause free flutter of the rudder spring tab and oscillation of the rudder, leading to loss of control of the aircraft.
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Required Actions
Inspect the rod terminal (P/N 20-530-5132-2) for cracks using dye penetrant, magnetic particle, or FAA-approved equivalent inspection with at least 5-power magnification. Replace cracked rod terminals prior to further flight. Inspections must be conducted at specified intervals based on aircraft or part time in service.
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Compliance Time
Compliance required as indicated in the AD, with inspections due before reaching specific time-in-service thresholds (e.g., 10,200 hours for aircraft under 10,000 hours, or within 200 hours after AD effective date for those over 10,000 hours). Repetitive inspections every 400 hours thereafter.
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Affected Aircraft
Curtiss-Wright Model C-46 Series aircraft with rudder assemblies P/N 20-140-5110 installed, including models C-46A, C-46D, C-46F, C-46R, C-46E, C-46/CW20-T, and Super C-46/CW20-T.
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Federal Register Abstract
Rudder Spring Tab
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_62-27-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 62-27-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: CURTISS-WRIGHT Model C-46 Series Aircraft Subject: Rudder Spring Tab Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 01/29/1963 Make: Airlift International, Inc. | Curtiss-Wright Corporation | Flying Tiger Line, Inc. | L. B. Smith Air...Show more Model: C-46A | C-46D | C-46F | C-46R | C-46E | C-46/CW20-T | Super C-46/CW20-T 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: 62-27-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 62-27-03 SUBJECT HEADING: CURTISS-WRIGHT Model C-46 Series Aircraft ACTION: SUMMARY: DATES: Effective January 29, 1963. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 62-27-03 CURTISS-WRIGHT: Amdt. 525 Part 507 Federal Register December 28, 1962. Applies to all C-46 Series aircraft which have rudder assemblies P/N 20-140-5110 installed. Compliance required as indicated. A recent inflight failure of the rudder spring tab rod terminal resulted in the free flutter of the rudder spring tab which forced the rudder to oscillate. To preclude the failure of this rod terminal and the resulting loss of control of the aircraft, the following shall be accomplished: (a) (1) Aircraft with less than 10,000 hours' time in service shall be inspected in accordance with (b) prior to the accumulation of 10,200 hours' time in service and thereafter every 400 hours' time in service. (2) Aircraft with 10,000 or more hours' time in service shall be inspected in accordance with (b) within 200 hours' time in service after the effective date of this AD, unless already accomplished within the last 200 hours' time in service, and thereafter every 400 hours' time in service from the last inspection. (b) (1) Remove the clevis, P/N 20-530-5133-2, and AN 316-5R nut from the rudder spring tab rod assembly, P/N 20-530-5134-1. (2) Inspect for cracks in the shoulder and threaded shank of the rod terminal, P/N 20-530-5132-2, using a dye penetrant, magnetic particle, or an FAA approved equivalent inspection method in conjunction with at least a 5-power magnifying glass. (3) Replace cracked rod terminals, P/N 20-530-5132-2, prior to further flight. (c) Rod terminals, P/N 20-530-5132-2, or rod assembly, P/N 20-530-5134-1, having zero or a known time in service not exceeding 5,000 hours, may be installed in compliance with (b)(3). Such parts shall be inspected and replaced in accordance with the following: (1) Parts having less than 4,800 hours' time in service shall be inspected in accordance with paragraphs (b)(1) and (2) prior to the accumulation of 5,000 hours and thereafter every 400 hours' time in service. (2) Parts having 4,800 or more hours' time in service shall be inspected in accordance with paragraphs (b)(1) and (2) within the next 200 hours' time in service and thereafter every 400 hours' time in service. (3) Cracked parts shall be replaced prior to further flight. (d) The inspection required by paragraph (b) is no longer required when rod assembly, P/N 20530-5134-1, is replaced with a new Component Air, Inc., rod assembly, P/N CAI-46003-1, or with an FAA approved rod terminal and clevis, or a rod assembly incorporating a clevis with 3/8-24 UNF or 7/16-20 UNF threads. (e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Southern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. This directive effective January 29, 1963. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_62-27-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 62-27-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: CURTISS-WRIGHT Model C-46 Series Aircraft Subject: Rudder Spring Tab Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 01/29/1963 Make: Airlift International, Inc. | Curtiss-Wright Corporation | Flying Tiger Line, Inc. | L. B. Smith Air...Show more Model: C-46A | C-46D | C-46F | C-46R | C-46E | C-46/CW20-T | Super C-46/CW20-T 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: 62-27-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 62-27-03 SUBJECT HEADING: CURTISS-WRIGHT Model C-46 Series Aircraft ACTION: SUMMARY: DATES: Effective January 29, 1963. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 62-27-03 CURTISS-WRIGHT: Amdt. 525 Part 507 Federal Register December 28, 1962. Applies to all C-46 Series aircraft which have rudder assemblies P/N 20-140-5110 installed. Compliance required as indicated. A recent inflight failure of the rudder spring tab rod terminal resulted in the free flutter of the rudder spring tab which forced the rudder to oscillate. To preclude the failure of this rod terminal and the resulting loss of control of the aircraft, the following shall be accomplished: (a) (1) Aircraft with less than 10,000 hours' time in service shall be inspected in accordance with (b) prior to the accumulation of 10,200 hours' time in service and thereafter every 400 hours' time in service. (2) Aircraft with 10,000 or more hours' time in service shall be inspected in accordance with (b) within 200 hours' time in service after the effective date of this AD, unless already accomplished within the last 200 hours' time in service, and thereafter every 400 hours' time in service from the last inspection. (b) (1) Remove the clevis, P/N 20-530-5133-2, and AN 316-5R nut from the rudder spring tab rod assembly, P/N 20-530-5134-1. (2) Inspect for cracks in the shoulder and threaded shank of the rod terminal, P/N 20-530-5132-2, using a dye penetrant, magnetic particle, or an FAA approved equivalent inspection method in conjunction with at least a 5-power magnifying glass. (3) Replace cracked rod terminals, P/N 20-530-5132-2, prior to further flight. (c) Rod terminals, P/N 20-530-5132-2, or rod assembly, P/N 20-530-5134-1, having zero or a known time in service not exceeding 5,000 hours, may be installed in compliance with (b)(3). Such parts shall be inspected and replaced in accordance with the following: (1) Parts having less than 4,800 hours' time in service shall be inspected in accordance with paragraphs (b)(1) and (2) prior to the accumulation of 5,000 hours and thereafter every 400 hours' time in service. (2) Parts having 4,800 or more hours' time in service shall be inspected in accordance with paragraphs (b)(1) and (2) within the next 200 hours' time in service and thereafter every 400 hours' time in service. (3) Cracked parts shall be replaced prior to further flight. (d) The inspection required by paragraph (b) is no longer required when rod assembly, P/N 20530-5134-1, is replaced with a new Component Air, Inc., rod assembly, P/N CAI-46003-1, or with an FAA approved rod terminal and clevis, or a rod assembly incorporating a clevis with 3/8-24 UNF or 7/16-20 UNF threads. (e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Southern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. This directive effective January 29, 1963. FOOTER:
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