AD 75-08-01
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Bombardier Inc. | CL-44D4 | Airworthiness Directives; CANADAIR Models CL-44D4 and CL-44J Airplanes |
| aircraft | Bombardier Inc. | CL-44J | Airworthiness Directives; CANADAIR Models CL-44D4 and CL-44J Airplanes |
Unsafe Condition
Cracks emanating from the ends of the slotted hole located at the center of the nose landing gear upper and lower toggle pins P/N 28-86128.
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Required Actions
Inspect the nose landing gear toggle pins P/N 28-86128 for cracks using Magnaflux or FAA-approved equivalent. Repeat inspections at intervals not exceeding 750 hours' time in service. Replace cracked parts prior to further flight with same part number, P/N 28-86128-2, or approved equivalent.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 300 hours' time in service after the effective date of this AD, unless accomplished within the last 450 hours' time in service.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
CANADAIR Models CL-44D4 and CL-44J airplanes with nose landing gear upper and lower toggle pins P/N 28-86128.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Nose Landing Gear
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_75-08-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 75-08-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; CANADAIR Models CL-44D4 and CL-44J Airplanes Subject: Nose Landing Gear Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 04/07/1975 Make: Bombardier Inc. Model: CL-44D4 | CL-44J Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 75-08-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2150 AD NUMBER: 75-08-01 SUBJECT HEADING: Airworthiness Directives; CANADAIR Models CL-44D4 and CL-44J Airplanes ACTION: SUMMARY: DATES: Effective April 7, 1975. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 75-08-01 CANADAIR: Amendment 39-2150. Applies to all CL-44D4 and CL-44J airplanes. Compliance required as indicated. 1. Affects the nose landing gear upper and lower toggle pins P/N 28-86128. a. Within the next 300 hours' time in service after the effective date of this AD, unless accomplished within the last 450 hours' time in service, remove the upper and lower nose landing gear toggle pins P/N 28-86128 and inspect for cracks emanating from the ends of the slotted hole located at the center of the pins using Magnaflux (MIL-I-6868) or an FAA- approved equivalent inspection. b. The inspection specified in "a" above shall be repeated at intervals not to exceed 750 hours' time in service from the last inspection. 2. Cracked parts shall be replaced prior to further flight. a. Replacement parts shall be of the same part number or P/N 28-86128-2 or approved equivalent parts. 3. The inspection specified in (1) is not required if: a. P/N 28-86128-2 pins are installed or; b. P/N 28-86128 pins are reworked, in accordance with Canadair Limited Service Information Circular No. 381-CL44 dated October 23, 1974, to P/N 28-86128-2 configuration. 4. The aircraft may be flown in accordance with FAR 21.197 to a base where the inspections or repairs can be performed. 5. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the inspection intervals specified in this AD. Equivalent parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective April 7, 1975. FOOTER:
Document Text
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AD Final Rules - DRS_75-08-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 75-08-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; CANADAIR Models CL-44D4 and CL-44J Airplanes Subject: Nose Landing Gear Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 04/07/1975 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: 75-08-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2150 AD NUMBER: 75-08-01 SUBJECT HEADING: Airworthiness Directives; CANADAIR Models CL-44D4 and CL-44J Airplanes ACTION: SUMMARY: DATES: Effective April 7, 1975. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 75-08-01 CANADAIR: Amendment 39-2150. Applies to all CL-44D4 and CL-44J airplanes. Compliance required as indicated. 1. Affects the nose landing gear upper and lower toggle pins P/N 28-86128. a. Within the next 300 hours' time in service after the effective date of this AD, unless accomplished within the last 450 hours' time in service, remove the upper and lower nose landing gear toggle pins P/N 28-86128 and inspect for cracks emanating from the ends of the slotted hole located at the center of the pins using Magnaflux (MIL-I-6868) or an FAA- approved equivalent inspection. b. The inspection specified in "a" above shall be repeated at intervals not to exceed 750 hours' time in service from the last inspection. 2. Cracked parts shall be replaced prior to further flight. a. Replacement parts shall be of the same part number or P/N 28-86128-2 or approved equivalent parts. 3. The inspection specified in (1) is not required if: a. P/N 28-86128-2 pins are installed or; b. P/N 28-86128 pins are reworked, in accordance with Canadair Limited Service Information Circular No. 381-CL44 dated October 23, 1974, to P/N 28-86128-2 configuration. 4. The aircraft may be flown in accordance with FAR 21.197 to a base where the inspections or repairs can be performed. 5. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the inspection intervals specified in this AD. Equivalent parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective April 7, 1975. FOOTER:
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Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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