AD 83-04-05
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Viking Air Limited | DHC-3 | Airworthiness Directives; DeHavilland Model DHC-3 Series Airplanes |
Unsafe Condition
Fracture of the control column lower weld assembly could cause loss of primary flight controls.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Visually inspect the control column lower weld assembly (P/N C3CF 39-15 or C3CF 39-13) within 25 hours time-in-service after the effective date, and every 100 hours thereafter. Replace or repair assemblies with cracks as specified in Service Bulletin 3/39, using approved parts or methods. Discontinue inspections after installing P/N C3CF 39-21.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 25 hours time-in-service after the effective date of this AD, unless already accomplished within the last 75 hours, and at each 100 hours time-in-service thereafter
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
DeHavilland Model DHC-3 (U-1A) airplanes certificated in any category.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Control Column Lower Assembly
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_83-04-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 83-04-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; DeHavilland Model DHC-3 Series Airplanes Subject: Control Column Lower Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 03/01/1983 Make: Viking Air Limited Model: DHC-3 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 83-04-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4568 AD NUMBER: 83-04-05 SUBJECT HEADING: Airworthiness Directives; DeHavilland Model DHC-3 Series Airplanes ACTION: SUMMARY: DATES: Effective March 1, 1983. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 83-04-05 DeHAVILLAND: Amendment 39-4568. Applies to Model DHC-3 (U-1A) airplanes certificated in any category. COMPLIANCE: As prescribed in the body of the AD. To prevent loss of primary flight controls due to fracture of the control column lower weld assembly, accomplish the following: a. Within the next 25 hours time-in-service after the effective date of this AD, unless already accomplished within the last 75 hours, and at each 100 hours time-in-service thereafter, visually inspect the control column lower weld assembly, P/N C3CF 39-15 or C3CF 39-13 for cracks in accordance with the Accomplishment Section of DeHavilland Service Bulletin S/B No. 3/39 dated October 1, 1982. b. If no cracks are found, return the airplane to service and repeat the inspections required by paragraph a of this AD. c. If cracks are found in control column lower assembly P/N C3CF 39-13, replace the assembly prior to further flight with a serviceable assembly P/N C3CF 39-15 or P/N C3CF 39-21 (Modification 3/930) as specified in the Replacement Section of said Service Bulletin. d. If cracks longer than 1 inch are found in control column lower assembly P/N C3CF 39-15, repair or replace the assembly prior to further flight as instructed in the Accomplishment Instructions Section of said Service Bulletin. e. If cracks 1 inch or less in length are found in control column lower assembly P/N C3CF 39-15, repair or replacement may be delayed for a period of 150 hours time-in-service provided the inspection prescribed in paragraph a above is accomplished at 25-hour intervals. f. The repetitive inspections of paragraph a of this AD may be discontinued when control column lower assembly P/N C3CF 39-21 (Modification 3/930) is installed. g. The airplane may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. h. An equivalent method of compliance with this AD may be used if approved by the Manager, New York Aircraft Certification Office, ANE-170, Federal Aviation Administration, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581; telephone (516) 791-6680. This amendment becomes effective on March 1, 1983. FOOTER:
Document Text
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AD Final Rules - DRS_83-04-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 83-04-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; DeHavilland Model DHC-3 Series Airplanes Subject: Control Column Lower Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 03/01/1983 Make: Viking Air Limited Model: DHC-3 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: 83-04-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4568 AD NUMBER: 83-04-05 SUBJECT HEADING: Airworthiness Directives; DeHavilland Model DHC-3 Series Airplanes ACTION: SUMMARY: DATES: Effective March 1, 1983. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 83-04-05 DeHAVILLAND: Amendment 39-4568. Applies to Model DHC-3 (U-1A) airplanes certificated in any category. COMPLIANCE: As prescribed in the body of the AD. To prevent loss of primary flight controls due to fracture of the control column lower weld assembly, accomplish the following: a. Within the next 25 hours time-in-service after the effective date of this AD, unless already accomplished within the last 75 hours, and at each 100 hours time-in-service thereafter, visually inspect the control column lower weld assembly, P/N C3CF 39-15 or C3CF 39-13 for cracks in accordance with the Accomplishment Section of DeHavilland Service Bulletin S/B No. 3/39 dated October 1, 1982. b. If no cracks are found, return the airplane to service and repeat the inspections required by paragraph a of this AD. c. If cracks are found in control column lower assembly P/N C3CF 39-13, replace the assembly prior to further flight with a serviceable assembly P/N C3CF 39-15 or P/N C3CF 39-21 (Modification 3/930) as specified in the Replacement Section of said Service Bulletin. d. If cracks longer than 1 inch are found in control column lower assembly P/N C3CF 39-15, repair or replace the assembly prior to further flight as instructed in the Accomplishment Instructions Section of said Service Bulletin. e. If cracks 1 inch or less in length are found in control column lower assembly P/N C3CF 39-15, repair or replacement may be delayed for a period of 150 hours time-in-service provided the inspection prescribed in paragraph a above is accomplished at 25-hour intervals. f. The repetitive inspections of paragraph a of this AD may be discontinued when control column lower assembly P/N C3CF 39-21 (Modification 3/930) is installed. g. The airplane may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. h. An equivalent method of compliance with this AD may be used if approved by the Manager, New York Aircraft Certification Office, ANE-170, Federal Aviation Administration, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581; telephone (516) 791-6680. This amendment becomes effective on March 1, 1983. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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