AD 69-05-01 R2
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Viking Air Limited | DHC-6-1 | Airworthiness Directives; de Havilland Model DHC-6 Series Airplanes |
| aircraft | Viking Air Limited | DHC-6-100 | Airworthiness Directives; de Havilland Model DHC-6 Series Airplanes |
| aircraft | Viking Air Limited | DHC-6-200 | Airworthiness Directives; de Havilland Model DHC-6 Series Airplanes |
| aircraft | Viking Air Limited | DHC-6-300 | Airworthiness Directives; de Havilland Model DHC-6 Series Airplanes |
Unsafe Condition
Cracks in the control column lower sub-assembly, part number C3CF39-17, could result in loss of control column operation.
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Required Actions
Visually inspect the control column lower sub-assembly (P/N C3CF39-17) for cracks. Replace cracked parts with P/N C3CF39-17 or equivalent approved part. The inspection interval may be increased with FAA approval and replacement with P/N C3CF39-19 (per S/B 6/180) discontinues the inspection requirement.
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Compliance Time
Prior to next flight unless accomplished within the last 50 hours time in service, and at intervals thereafter not to exceed 100 hours time in service from the last inspection.
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Affected Aircraft
Viking Air Limited DHC-6-1, DHC-6-100, DHC-6-200, DHC-6-300 airplanes certificated in all categories.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Control Column Sub-assembly Cracks
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_69-05-01_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 69-05-01 R2 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; de Havilland Model DHC-6 Series Airplanes Subject: Control Column Sub-assembly Cracks Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 07/07/1980 Make: Viking Air Limited Model: DHC-6-1 | DHC-6-100 | DHC-6-200 | DHC-6-300 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 69-05-01 R2 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3824 AD NUMBER: 69-05-01 R2 SUBJECT HEADING: Airworthiness Directives; de Havilland Model DHC-6 Series Airplanes ACTION: SUMMARY: DATES: Effective July 7, 1980. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 69-05-01 R2 DE HAVILLAND: Amendment 39-728 as amended by Amendment 39-1175 is further amended by Amendment 39-3824. Applies to de Havilland DHC-6 airplanes certificated in all categories: (a) Prior to next flight unless accomplished within the last 50 hours time in service, and at intervals thereafter not to exceed 100 hours time in service from the last inspection, visually inspect the control column lower sub-assembly, P/N C3CF39-17 for cracks. Replace cracked parts before further flight with a part of the same part number or with an equivalent part approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (b) The repetitive inspection interval required by (a) may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region upon receipt of substantiating data submitted through an FAA maintenance inspector. (c) Report the results of the initial inspection findings required by this AD to the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region (reporting approved by the Bureau of the Budget under B.O.B. No. 04-R0174). (d) Cracked parts, P/N C3CF39-17, may be replaced with a new sub-assembly, P/N C3CF39-19, in accordance with De Havilland Modification No. 6/1433 in De Havilland Service Bulletin (S/B) No. 6/180, Revision D, dated April 30, 1976, ACCOMPLISHMENT INSTRUCTION No. 5, or with an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (e) The repetitive inspection required by (a) may be discontinued when the lower sub-assembly is replaced by P/N C3CF39-19 in accordance with De Havilland Modification No. 6/1433, or FAA approved equivalent. Amendment 39-728 effective March 5, 1969, and was effective upon receipt for all recipients of the telegram dated January 31, 1969 which contained this amendment. Amendment 39-1175 was effective March 23, 1971. This Amendment 39-3824 becomes effective July 7, 1980. FOOTER:
Document Text
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AD Final Rules - DRS_69-05-01_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 69-05-01 R2 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; de Havilland Model DHC-6 Series Airplanes Subject: Control Column Sub-assembly Cracks Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 07/07/1980 Make: Viking Air Limited Model: DHC-6-1 | DHC-6-100 | DHC-6-200 | DHC-6-300 Product Type: Aircraft Product Subtype: Small 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: 69-05-01 R2 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3824 AD NUMBER: 69-05-01 R2 SUBJECT HEADING: Airworthiness Directives; de Havilland Model DHC-6 Series Airplanes ACTION: SUMMARY: DATES: Effective July 7, 1980. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 69-05-01 R2 DE HAVILLAND: Amendment 39-728 as amended by Amendment 39-1175 is further amended by Amendment 39-3824. Applies to de Havilland DHC-6 airplanes certificated in all categories: (a) Prior to next flight unless accomplished within the last 50 hours time in service, and at intervals thereafter not to exceed 100 hours time in service from the last inspection, visually inspect the control column lower sub-assembly, P/N C3CF39-17 for cracks. Replace cracked parts before further flight with a part of the same part number or with an equivalent part approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (b) The repetitive inspection interval required by (a) may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region upon receipt of substantiating data submitted through an FAA maintenance inspector. (c) Report the results of the initial inspection findings required by this AD to the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region (reporting approved by the Bureau of the Budget under B.O.B. No. 04-R0174). (d) Cracked parts, P/N C3CF39-17, may be replaced with a new sub-assembly, P/N C3CF39-19, in accordance with De Havilland Modification No. 6/1433 in De Havilland Service Bulletin (S/B) No. 6/180, Revision D, dated April 30, 1976, ACCOMPLISHMENT INSTRUCTION No. 5, or with an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (e) The repetitive inspection required by (a) may be discontinued when the lower sub-assembly is replaced by P/N C3CF39-19 in accordance with De Havilland Modification No. 6/1433, or FAA approved equivalent. Amendment 39-728 effective March 5, 1969, and was effective upon receipt for all recipients of the telegram dated January 31, 1969 which contained this amendment. Amendment 39-1175 was effective March 23, 1971. This Amendment 39-3824 becomes effective July 7, 1980. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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