AD 82-18-06
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Bombardier Inc. | CL-600-1A11 (CL-600) | Airworthiness Directives; CANADAIR Model CL-600-1A11 Aircraft |
Unsafe Condition
The blade lock release shaft of the air-driven generator (Part Number 728315) may have incorrect thread engagement, and chafing of the strut by the cable assembly (Part Number 59431) during deployment could occur.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Measure the exposed thread length on plunger assembly Part Number 726969 within the next 50 hours time in service and after each disassembly/reassembly. Replace control cable assembly Part Number 59431 with 5903301 if exposed thread exceeds 0.520 inches or within 600 hours time in service. Allow alternate means approved by the FAA and issue special flight permits as per FAR 21.197/199.
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 and subsequent to each disassembly/reassembly, or within the next 600 hours time in service.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Bombardier Inc. Model CL-600-1A11 (CL-600) aircraft Serial Numbers 1005 through 1008, 1010 through 1012, and 1014 through 1017.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Control Cable Assembly
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_82-18-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 82-18-06 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; CANADAIR Model CL-600-1A11 Aircraft Subject: Control Cable Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 09/07/1982 Make: Bombardier Inc. Model: CL-600-1A11 (CL-600) Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 82-18-06 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4447 AD NUMBER: 82-18-06 SUBJECT HEADING: Airworthiness Directives; CANADAIR Model CL-600-1A11 Aircraft ACTION: SUMMARY: DATES: Effective September 7, 1982. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 82-18-06 CANADAIR: Amendment 39-4447. Applies to Canadair Model CL-600-1A11 aircraft Serial Numbers 1005 through 1008, 1010 through 1012, and 1014 through 1017, certificated in all categories. Compliance required as indicated to ensure that the blade lock release shaft of the air- driven generator (Part Number 728315) has the correct thread engagement, and to prevent chafing of the strut by the cable assembly during deployment, accomplish the following in accordance with the instructions contained in Canadair Alert Service Bulletin A600-0063, Revision 1, dated October 28, 1981, unless already accomplished: 1. Within the next 50 hours time in service and subsequent to each disassembly/reassembly of control cable assembly Part Number 59431, measure the length of the exposed thread on plunger assembly Part Number 726969. If the length of exposed thread is greater than 0.520 inches, replace the control cable assembly Part Number 59431 with control cable assembly 5903301 in accordance with paragraph 2B of Alert Service Bulletin A600-0063, prior to further flight. 2. Within the next 600 hours time in service, replace the control cable assembly Part Number 59431 with control cable assembly 5903301 in accordance with paragraph 2B of the service bulletin. 3. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 4. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). This amendment becomes effective September 7, 1982. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_82-18-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 82-18-06 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; CANADAIR Model CL-600-1A11 Aircraft Subject: Control Cable Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 09/07/1982 Make: Bombardier Inc. Model: CL-600-1A11 (CL-600) 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: 82-18-06 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4447 AD NUMBER: 82-18-06 SUBJECT HEADING: Airworthiness Directives; CANADAIR Model CL-600-1A11 Aircraft ACTION: SUMMARY: DATES: Effective September 7, 1982. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 82-18-06 CANADAIR: Amendment 39-4447. Applies to Canadair Model CL-600-1A11 aircraft Serial Numbers 1005 through 1008, 1010 through 1012, and 1014 through 1017, certificated in all categories. Compliance required as indicated to ensure that the blade lock release shaft of the air- driven generator (Part Number 728315) has the correct thread engagement, and to prevent chafing of the strut by the cable assembly during deployment, accomplish the following in accordance with the instructions contained in Canadair Alert Service Bulletin A600-0063, Revision 1, dated October 28, 1981, unless already accomplished: 1. Within the next 50 hours time in service and subsequent to each disassembly/reassembly of control cable assembly Part Number 59431, measure the length of the exposed thread on plunger assembly Part Number 726969. If the length of exposed thread is greater than 0.520 inches, replace the control cable assembly Part Number 59431 with control cable assembly 5903301 in accordance with paragraph 2B of Alert Service Bulletin A600-0063, prior to further flight. 2. Within the next 600 hours time in service, replace the control cable assembly Part Number 59431 with control cable assembly 5903301 in accordance with paragraph 2B of the service bulletin. 3. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 4. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). This amendment becomes effective September 7, 1982. 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.