AD 72-21-05
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Bombardier Inc. | CL-44D4 | Airworthiness Directives; CANADAIR Model Canadair CL-44 |
| aircraft | Bombardier Inc. | CL-44J | Airworthiness Directives; CANADAIR Model Canadair CL-44 |
Unsafe Condition
Cracks in the horizontal stabilizer rear spar to fuselage attachment fittings, part numbers 44A45022A and B, could result in structural failure.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the horizontal stabilizer rear spar to fuselage attachment fittings for cracks using Canadair Service Information Circular No. 379-CL44 or approved equivalent. Replace cracked parts with same part number or FAA-approved equivalents before further flight.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 100 hours in service after the effective date of this Airworthiness Directive, unless already accomplished within the last 1900 hours in service and at intervals not exceeding 2000 hours in service from the last inspection.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Bombardier Inc. Canadair CL-44D4 and CL-44J models, all serial numbers.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Horizontal Stabilizer
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_72-21-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 72-21-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; CANADAIR Model Canadair CL-44 Subject: Horizontal Stabilizer Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/17/1972 Make: Bombardier Inc. Model: CL-44D4 | CL-44J Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 72-21-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1536 AD NUMBER: 72-21-05 SUBJECT HEADING: Airworthiness Directives; CANADAIR Model Canadair CL-44 ACTION: SUMMARY: DATES: Effective October 17, 1972. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 72-21-05 CANADAIR: Amendment 39-1536. Applies to all Canadair CL-44 type aircraft certificated in all categories. Compliance required as indicated. Within the next 100 hours in service after the effective date of this Airworthiness Directive, unless already accomplished within the last 1900 hours in service and at intervals not exceeding 2000 hours in service from the last inspection accomplish the following: 1. Inspect the horizontal stabilizer rear spar to fuselage attachment fittings, P/N 44A45022A and B, for cracks in accordance with Paragraph 3.4 of Canadair Service Information Circular No. 379-CL44, dated 7 July 1971, or equivalent inspection approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 2. Replace cracked parts before further flight with parts of the same part number or FAA-approved equivalent parts approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed. Upon request, with substantiating data submitted through an FAA maintenance inspector, the replacement intervals specified herein may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective October 17, 1972. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_72-21-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 72-21-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; CANADAIR Model Canadair CL-44 Subject: Horizontal Stabilizer Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/17/1972 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: 72-21-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1536 AD NUMBER: 72-21-05 SUBJECT HEADING: Airworthiness Directives; CANADAIR Model Canadair CL-44 ACTION: SUMMARY: DATES: Effective October 17, 1972. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 72-21-05 CANADAIR: Amendment 39-1536. Applies to all Canadair CL-44 type aircraft certificated in all categories. Compliance required as indicated. Within the next 100 hours in service after the effective date of this Airworthiness Directive, unless already accomplished within the last 1900 hours in service and at intervals not exceeding 2000 hours in service from the last inspection accomplish the following: 1. Inspect the horizontal stabilizer rear spar to fuselage attachment fittings, P/N 44A45022A and B, for cracks in accordance with Paragraph 3.4 of Canadair Service Information Circular No. 379-CL44, dated 7 July 1971, or equivalent inspection approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 2. Replace cracked parts before further flight with parts of the same part number or FAA-approved equivalent parts approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed. Upon request, with substantiating data submitted through an FAA maintenance inspector, the replacement intervals specified herein may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective October 17, 1972. 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.