AD 68-10-08
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Bombardier Inc. | CL-44D4 | CANADAIR CL-44 Airplanes |
| aircraft | Bombardier Inc. | CL-44J | CANADAIR CL-44 Airplanes |
Unsafe Condition
Cracks in the main landing gear actuator attachment brackets, P/N 44-87571-2, due to accumulated time in service.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Visually inspect upper and lower lugs of the four main landing gear actuator attachment brackets before each flight. Remove brackets and inspect with dye penetrant or equivalent at intervals not exceeding 250 hours' time in service. Install spacers P/N 44-87639 or equivalent per Canadair Service Bulletin CL44-474. Replace cracked parts before further flight except under FAR 21.197.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 50 hours' time in service after the effective date (May 21, 1968) for dye penetrant inspections, and within 500 hours' time in service for spacer installation. Intervals thereafter not to exceed 250 hours' time in service for inspections.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Bombardier Inc. CL-44D4 and CL-44J models with main landing gear actuator attachment brackets P/N 44-87571-2 that have accumulated 14,500 or more hours' time in service as of May 21, 1968.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Main Landing Gear Actuator Attach
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_68-10-08.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 68-10-08 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: CANADAIR CL-44 Airplanes Subject: Main Landing Gear Actuator Attach Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/21/1968 Make: Bombardier Inc. Model: CL-44D4 | CL-44J Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 68-10-08 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-601 AD NUMBER: 68-10-08 SUBJECT HEADING: CANADAIR CL-44 Airplanes ACTION: SUMMARY: DATES: Effective May 21, 1968. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 68-10-08 CANADAIR: Amendment 39-601. Applies to CL-44 Type airplanes. Compliance required as indicated. To detect cracks in the main landing gear actuator attachment brackets, P/N 44-87571-2, which have accumulated 14,500 or more hours' time in service as of the effective date of this AD, accomplish the following: (a) Prior to each flight after the effective date of this AD visually inspect for cracks the upper and lower lugs of the four main landing gear actuator attachment brackets. (b) Within the next 50 hours' time in service after the effective date of this AD unless accomplished within the last 200 hours' time in service and at intervals thereafter not to exceed 250 hours' time in service from the last inspection, remove the four brackets and inspect the upper and lower lugs for cracks using dye penetrant and a glass of at least 10-power or an FAA-approved equivalent inspection. (c) Within the next 500 hours' time in service after the effective date of this AD unless already accomplished, install spacers, P/N 44-87639 or an FAA-approved equivalent part in accordance with Canadair Service Bulletin No. CL44-474 dated April 8, 1968 or later revisions approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region or perform an equivalent installation approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (d) Replace cracked parts with a part of the same part number or an FAA-approved equivalent part before further flight except that the airplane may be flown in accordance with FAR 21.197 to a base where the replacement part can be installed, provided the main landing gear remains in the down and locked position with the landing gear lock pins installed. (e) The compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, upon receipt of substantiating data through an FAA Maintenance Inspector. (f) Equivalent parts and inspections must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (Canadair Ltd. Service Information Circular No. 370-CL44 dated April 8, 1968, pertains to this subject.) This amendment is effective May 21, 1968. FOOTER:
Document Text
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AD Final Rules - DRS_68-10-08.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 68-10-08 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: CANADAIR CL-44 Airplanes Subject: Main Landing Gear Actuator Attach Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/21/1968 Make: Bombardier Inc. Model: CL-44D4 | CL-44J 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: 68-10-08 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-601 AD NUMBER: 68-10-08 SUBJECT HEADING: CANADAIR CL-44 Airplanes ACTION: SUMMARY: DATES: Effective May 21, 1968. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 68-10-08 CANADAIR: Amendment 39-601. Applies to CL-44 Type airplanes. Compliance required as indicated. To detect cracks in the main landing gear actuator attachment brackets, P/N 44-87571-2, which have accumulated 14,500 or more hours' time in service as of the effective date of this AD, accomplish the following: (a) Prior to each flight after the effective date of this AD visually inspect for cracks the upper and lower lugs of the four main landing gear actuator attachment brackets. (b) Within the next 50 hours' time in service after the effective date of this AD unless accomplished within the last 200 hours' time in service and at intervals thereafter not to exceed 250 hours' time in service from the last inspection, remove the four brackets and inspect the upper and lower lugs for cracks using dye penetrant and a glass of at least 10-power or an FAA-approved equivalent inspection. (c) Within the next 500 hours' time in service after the effective date of this AD unless already accomplished, install spacers, P/N 44-87639 or an FAA-approved equivalent part in accordance with Canadair Service Bulletin No. CL44-474 dated April 8, 1968 or later revisions approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region or perform an equivalent installation approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (d) Replace cracked parts with a part of the same part number or an FAA-approved equivalent part before further flight except that the airplane may be flown in accordance with FAR 21.197 to a base where the replacement part can be installed, provided the main landing gear remains in the down and locked position with the landing gear lock pins installed. (e) The compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, upon receipt of substantiating data through an FAA Maintenance Inspector. (f) Equivalent parts and inspections must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (Canadair Ltd. Service Information Circular No. 370-CL44 dated April 8, 1968, pertains to this subject.) This amendment is effective May 21, 1968. FOOTER:
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Retrieved: Apr 8, 2026
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