AD 86-16-12
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Viking Air Limited | DHC-3 | Airworthiness Directives; DeHavilland Model DHC-3 Series Airplanes |
Unsafe Condition
Loss of elevator control and improper operation of the control system due to bending of the elevator pushrod and attachment bolt, cracks in the threaded shank of the elevator pushrod rod ends, and damage or distortion to elevator control system cables and pulleys.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Within 25 hours time-in-service after the effective date, visually inspect the elevator pushrod, attachment bolt for bending, threaded shank for cracks, and cables/pulleys for damage. Replace unserviceable parts with specified parts (C3-CF-633-1 pushrod, NAS1954-24D bolt) prior to further flight. Within 60 days, replace elevator pushrod and rudder pushrod bolts if no damage found. Adjustments require FAA approval.
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Compliance Time
Within 25 hours time-in-service after the effective date of this AD, unless already accomplished. For parts replacement, prior to further flight. Additional requirements within 60 days after the effective date if no damage found.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Viking Air Limited Model DHC-3 (all serial numbers) airplanes certificated in any category.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Elevator Pushrod Inspection
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_86-16-12.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 86-16-12 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; DeHavilland Model DHC-3 Series Airplanes Subject: Elevator Pushrod Inspection Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/15/1986 Make: Viking Air Limited Model: DHC-3 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 86-16-12 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5389 AD NUMBER: 86-16-12 SUBJECT HEADING: Airworthiness Directives; DeHavilland Model DHC-3 Series Airplanes ACTION: SUMMARY: DATES: Effective August 15, 1986. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 86-16-12 DeHAVILLAND: Amendment 39-5389. Applies to Model DHC-3 (all serial numbers) airplanes certificated in any category. Compliance: Required as indicated, after the effective date of this AD, unless already accomplished. To preclude loss of elevator control and to ensure proper operation of the control system, accomplish the following inspections and parts replacement: (a) Within 25 hours time-in-service (TIS), after the effective date of this AD, visually inspect the following parts: (1) The elevator pushrod, and the elevator pushrod to rear quadrant attachment bolt, for bending, in accordance with "ACCOMPLISHMENT INSTRUCTIONS" in DeHavilland Service Bulletins (S/B) No. 3/35, Revision A, dated April 11, 1980, and S/B No. 3/43, dated January 18, 1985. (2) The threaded shank of the elevator pushrod rod ends, for cracks. (3) All elevator control system cables and pulleys for damage or distortion. (b) Replace unserviceable parts, prior to further flight, with serviceable pacts follows: (1) Elevator pushrod with new pushrod Part Number (P/N) C3-CF-633-1, in accordance with "ACCOMPLISHMENT INSTRUCTIONS" in DeHavilland S/B No. 3/35, Revision A, dated April 11, 1980. (2) Elevator pushrod to rear quadrant attachment bolt with a new NAS1954- 24D bolt, in accordance with paragraph (c) of this AD. (3) Elevator control system cables and pulleys in accordance with the applicable section of the aircraft maintenance manual. NOTE: When a parked DHC-3 airplane has been subjected to wind gusts of 60 mph or greater (including helicopter or jet blasts) damage may occur to the elevator control system, and the requirements specified in paragraphs (a) and (b) of this AD should be accomplished again. (c) If the elevator pushrod to rear quadrant attachment bolt is replaced with a NAS1954-24D bolt, replace the associated hardware and in addition, replace the rudder pushrod to rear quadrant attachment bolt with a NAS1954-24D bolt and the associated hardware in accordance with "ACCOMPLISHMENT INSTRUCTIONS" in DeHavilland S/B No. 3/43 dated January 18, 1985. Torque nuts to 65 in-pounds prior to installation of cotter pins. (d) If no damage is found during the inspection as required by paragraph (a) of this AD, within 60 days after the effective date of this AD, unless already accomplished: (1) Replace the elevator pushrod in accordance with paragraph (b)(1) of this AD, and (2) Replace the elevator and rudder pushrod to rear quadrant attachment bolts in accordance with paragraph (c) of this AD. (e) The airplane may be flown in accordance with Federal Aviation Regulations (FAR) 21.197 to a location where the requirements of this AD may be accomplished. (f) An equivalent method of compliance with this AD, if used, must be approved by the Manager, New York Aircraft Certification Office, ANE-170, FAA, New England Region, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. (g) Upon submission of substantiating data by an owner or operator, through an FAA Maintenance Inspector, the Manager, New York Aircraft Certification Office, FAA, New- England Region, may adjust the compliance intervals specified in this AD. All persons affected by this directive may obtain copies of the documents referred to herein upon request to DeHavilland Aircraft of Canada, Ltd., Downsview, Ontario, Canada, M3K 1Y5 or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on August 15, 1986. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_86-16-12.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 86-16-12 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; DeHavilland Model DHC-3 Series Airplanes Subject: Elevator Pushrod Inspection Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/15/1986 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: 86-16-12 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5389 AD NUMBER: 86-16-12 SUBJECT HEADING: Airworthiness Directives; DeHavilland Model DHC-3 Series Airplanes ACTION: SUMMARY: DATES: Effective August 15, 1986. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 86-16-12 DeHAVILLAND: Amendment 39-5389. Applies to Model DHC-3 (all serial numbers) airplanes certificated in any category. Compliance: Required as indicated, after the effective date of this AD, unless already accomplished. To preclude loss of elevator control and to ensure proper operation of the control system, accomplish the following inspections and parts replacement: (a) Within 25 hours time-in-service (TIS), after the effective date of this AD, visually inspect the following parts: (1) The elevator pushrod, and the elevator pushrod to rear quadrant attachment bolt, for bending, in accordance with "ACCOMPLISHMENT INSTRUCTIONS" in DeHavilland Service Bulletins (S/B) No. 3/35, Revision A, dated April 11, 1980, and S/B No. 3/43, dated January 18, 1985. (2) The threaded shank of the elevator pushrod rod ends, for cracks. (3) All elevator control system cables and pulleys for damage or distortion. (b) Replace unserviceable parts, prior to further flight, with serviceable pacts follows: (1) Elevator pushrod with new pushrod Part Number (P/N) C3-CF-633-1, in accordance with "ACCOMPLISHMENT INSTRUCTIONS" in DeHavilland S/B No. 3/35, Revision A, dated April 11, 1980. (2) Elevator pushrod to rear quadrant attachment bolt with a new NAS1954- 24D bolt, in accordance with paragraph (c) of this AD. (3) Elevator control system cables and pulleys in accordance with the applicable section of the aircraft maintenance manual. NOTE: When a parked DHC-3 airplane has been subjected to wind gusts of 60 mph or greater (including helicopter or jet blasts) damage may occur to the elevator control system, and the requirements specified in paragraphs (a) and (b) of this AD should be accomplished again. (c) If the elevator pushrod to rear quadrant attachment bolt is replaced with a NAS1954-24D bolt, replace the associated hardware and in addition, replace the rudder pushrod to rear quadrant attachment bolt with a NAS1954-24D bolt and the associated hardware in accordance with "ACCOMPLISHMENT INSTRUCTIONS" in DeHavilland S/B No. 3/43 dated January 18, 1985. Torque nuts to 65 in-pounds prior to installation of cotter pins. (d) If no damage is found during the inspection as required by paragraph (a) of this AD, within 60 days after the effective date of this AD, unless already accomplished: (1) Replace the elevator pushrod in accordance with paragraph (b)(1) of this AD, and (2) Replace the elevator and rudder pushrod to rear quadrant attachment bolts in accordance with paragraph (c) of this AD. (e) The airplane may be flown in accordance with Federal Aviation Regulations (FAR) 21.197 to a location where the requirements of this AD may be accomplished. (f) An equivalent method of compliance with this AD, if used, must be approved by the Manager, New York Aircraft Certification Office, ANE-170, FAA, New England Region, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. (g) Upon submission of substantiating data by an owner or operator, through an FAA Maintenance Inspector, the Manager, New York Aircraft Certification Office, FAA, New- England Region, may adjust the compliance intervals specified in this AD. All persons affected by this directive may obtain copies of the documents referred to herein upon request to DeHavilland Aircraft of Canada, Ltd., Downsview, Ontario, Canada, M3K 1Y5 or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on August 15, 1986. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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