# AD 83-04-05: Control Column Lower Assembly

- Type: Airworthiness directive
- Status: Current
- Products: Viking Air DHC-3
- Effective: March 1, 1983
- Superseded by: Nothing supersedes this AD
- Product type: Aircraft, Small airplane
- Amendment: 39-4568
- Registered aircraft: 76 may be affected, by airframe or engine model (OpenAirDocs)
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/EDFDCA98CD9EE05886256A4E00521701.0001
- DRS record last changed: May 30, 2024
- Page: https://openairdocs.org/ad/83-04-05

## The airworthiness directive

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 theManager, 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.

## Affected data sheets (1) (OpenAirDocs)

The type certificate data sheets whose models the AD names.

- [TCDS A-815](https://openairdocs.org/tcds/A-815): De Havilland Aircraft of Canada Limited; names 1 of 1 models: DHC-3

## Registered aircraft it may apply to (OpenAirDocs)

Matched by airframe and engine model; the AD's applicability may narrow it by serial number, part number or equipment.

- Aircraft: 76 (76 by airframe model, 0 by engine model)
- Makers: Dehavilland 67, Dehavilland Canada 8, Dehavilland-Hansen 1

Models with the most aircraft:

- [Dehavilland DHC-3](https://openairdocs.org/model/dehavilland-dhc-3): 67 aircraft (airframe model)
- [Dehavilland Canada DHC-3](https://openairdocs.org/model/dehavilland-canada-dhc-3): 8 aircraft (airframe model)
- [Dehavilland-Hansen DHC-3](https://openairdocs.org/model/dehavilland-hansen-dhc-3): 1 aircraft (airframe model)

All 5 models: https://openairdocs.org/ad/83-04-05/models.md
Every aircraft: https://openairdocs.org/ad/83-04-05/aircraft.md

Its text cites no advisory circulars or STCs.

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