AD 61-22-02
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Bombardier Inc. | CL-44D4 | Airworthiness Directives; CANADAIR Model CL-44D4 Aircraft |
Unsafe Condition
Failure of the main landing gear rotation lever P/N 4487528 can cause the landing gear to remain in the 'up' position when the lever is operated to lower the gear.
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Required Actions
Conduct dye penetrant inspections within the next 45 hours' time in service (if not done in the past 180 hours) and every 225 hours thereafter. Perform visual inspections between dye penetrant inspections at intervals not exceeding 45 hours' time in service. Replace cracked levers before further flight except for ferry flights under CAR 1.76.
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Compliance Time
Effective November 1, 1961.
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Affected Aircraft
Bombardier Inc. Model CL-44D4 aircraft, all serial numbers.
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Federal Register Abstract
Landing Gear Rotation Lever
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_61-22-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 61-22-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; CANADAIR Model CL-44D4 Aircraft Subject: Landing Gear Rotation Lever Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/01/1961 Make: Bombardier Inc. Model: CL-44D4 Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 61-22-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 61-22-02 SUBJECT HEADING: Airworthiness Directives; CANADAIR Model CL-44D4 Aircraft ACTION: SUMMARY: DATES: Effective November 1, 1961. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 61-22-02 CANADAIR: Amdt. 355 Part 507 Federal Register November 1, 1961. Applies to all CL-44D4 aircraft. Compliance required as indicated. Failures have occurred on the main landing gear rotation lever P/N 4487528 on Model CL-44D4 aircraft. Failure of the lever can cause the landing gear to remain in "up" position when the lever is operated to lower the gear. The following must be accomplished pending the development and installation of a Canadian Department of Transport and FAA approved modification of the affected parts after which no further inspection will be required: (a) Within the next 45 hours' time in service unless already accomplished within the past 180 hours' time in service and at intervals not exceeding 225 hours' time in service thereafter conduct the dye penetrant inspection specified in Canadair Service Information Circular No. 27- CL-44D4 or FAA approved equivalent. Cracked levers must be replaced prior to further flight except for a ferry flight in accordance with the provisions of CAR 1.76. (b) Subsequent to the effective date of this AD, at intermediate intervals between dye penetrant inspections not exceeding each 45 hours' time in service, conduct a visual inspection of the affected part. Cracked levers must be replaced prior to further flight except for a ferry flight in accordance with the provisions of CAR 1.76. (c) Upon request of the operator an FAA maintenance inspector subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern 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 November 1, 1961. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_61-22-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 61-22-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; CANADAIR Model CL-44D4 Aircraft Subject: Landing Gear Rotation Lever Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/01/1961 Make: Bombardier Inc. Model: CL-44D4 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: 61-22-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 61-22-02 SUBJECT HEADING: Airworthiness Directives; CANADAIR Model CL-44D4 Aircraft ACTION: SUMMARY: DATES: Effective November 1, 1961. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 61-22-02 CANADAIR: Amdt. 355 Part 507 Federal Register November 1, 1961. Applies to all CL-44D4 aircraft. Compliance required as indicated. Failures have occurred on the main landing gear rotation lever P/N 4487528 on Model CL-44D4 aircraft. Failure of the lever can cause the landing gear to remain in "up" position when the lever is operated to lower the gear. The following must be accomplished pending the development and installation of a Canadian Department of Transport and FAA approved modification of the affected parts after which no further inspection will be required: (a) Within the next 45 hours' time in service unless already accomplished within the past 180 hours' time in service and at intervals not exceeding 225 hours' time in service thereafter conduct the dye penetrant inspection specified in Canadair Service Information Circular No. 27- CL-44D4 or FAA approved equivalent. Cracked levers must be replaced prior to further flight except for a ferry flight in accordance with the provisions of CAR 1.76. (b) Subsequent to the effective date of this AD, at intermediate intervals between dye penetrant inspections not exceeding each 45 hours' time in service, conduct a visual inspection of the affected part. Cracked levers must be replaced prior to further flight except for a ferry flight in accordance with the provisions of CAR 1.76. (c) Upon request of the operator an FAA maintenance inspector subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern 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 November 1, 1961. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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