AD 80-08-13
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Viking Air Limited | DHC-7-1 | Airworthiness Directives; DeHavilland Model DHC-7 Airplanes |
| aircraft | Viking Air Limited | DHC-7-100 | Airworthiness Directives; DeHavilland Model DHC-7 Airplanes |
| aircraft | Viking Air Limited | DHC-7-101 | Airworthiness Directives; DeHavilland Model DHC-7 Airplanes |
| aircraft | Viking Air Limited | DHC-7-102 | Airworthiness Directives; DeHavilland Model DHC-7 Airplanes |
| aircraft | Viking Air Limited | DHC-7-103 | Airworthiness Directives; DeHavilland Model DHC-7 Airplanes |
Unsafe Condition
Failure of the main landing gear due to cracking in the upper drag strut.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Visually inspect the lower lug end of the upper drag strut assembly daily and prior to next flight. Conduct Eddy Current inspections within 200 hours in service or 250 landings, whichever comes first. Replace the upper drag strut assembly before further flight if cracks are found.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Prior to next flight, daily thereafter, and within 200 hours in service or 250 landings, whichever occurs first, after the effective date of this AD.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
DeHavilland Model DHC-7 airplanes, Serial Numbers 1 thru 18.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Main Landing Gear Upper Drag Strut
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_80-08-13.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 80-08-13 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; DeHavilland Model DHC-7 Airplanes Subject: Main Landing Gear Upper Drag Strut Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 04/16/1980 Make: Viking Air Limited Model: DHC-7-1 | DHC-7-100 | DHC-7-101 | DHC-7-102 | DHC-7-103 Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 80-08-13 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3747 AD NUMBER: 80-08-13 SUBJECT HEADING: Airworthiness Directives; DeHavilland Model DHC-7 Airplanes ACTION: SUMMARY: DATES: Effective April 16, 1980. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 80-08-13 DeHAVILLAND: Amendment 39-3747. Applies to DHC-7 model airplanes, Serial Numbers 1 thru 18, certificated in all categories. To prevent possible failure of the main landing gear due to cracking in the upper drag strut, accomplish the following: 1. Prior to next flight, and daily thereafter, visually inspect the lower lug end of the upper drag strut sub=assembly on the main landing gear for cracks, in accordance with ACCOMPLISHMENT INSTRUCTIONS in DeHavilland Alert Service Bulletin A7-32-18, paragraphs 1. and 2., dated February 6, 1980, or equivalent. 2. At intervals of 40 hours in service or 50 landings, whichever occurs first, after the effective date of this AD, with gear partially retracted, inspect lugs for cracks in accordance with paragraph 3. of the above DeHavilland service bulletin ACCOMPLISHMENT INSTRUCTIONS or equivalent. 3. If cracks are found, the upper drag strut assembly must be replaced before further flight by parts with the same part numbers or equivalent, inspected and found serviceable in accordance with the above DeHavilland service bulletin or equivalent. 4. Within 200 hours in service or 250 landings, whichever occurs first, after the effective date of this AD, inspect the upper drag strut lower lug ends by Eddy Current methods in accordance with paragraph 4. of the ACCOMPLISHMENT INSTRUCTIONS in the above DeHavilland service bulletin or equivalent. 5. When inspection in paragraph 4. is accomplished the inspections in paragraphs 1. and 2. are no longer required. 6. Report positive findings, including crack length, from any inspection, to the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, within 10 days of inspection. (Reporting approved by Office of Management and Budget under OMB No. 04-R0174.) 7. Equivalent parts and inspections must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 8. Compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, upon receipt of substantiating data submitted through an FAA Maintenance Inspector. This amendment is effective April 16, 1980. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_80-08-13.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 80-08-13 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; DeHavilland Model DHC-7 Airplanes Subject: Main Landing Gear Upper Drag Strut Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 04/16/1980 Make: Viking Air Limited Model: DHC-7-1 | DHC-7-100 | DHC-7-101 | DHC-7-102 | DHC-7-103 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: 80-08-13 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3747 AD NUMBER: 80-08-13 SUBJECT HEADING: Airworthiness Directives; DeHavilland Model DHC-7 Airplanes ACTION: SUMMARY: DATES: Effective April 16, 1980. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 80-08-13 DeHAVILLAND: Amendment 39-3747. Applies to DHC-7 model airplanes, Serial Numbers 1 thru 18, certificated in all categories. To prevent possible failure of the main landing gear due to cracking in the upper drag strut, accomplish the following: 1. Prior to next flight, and daily thereafter, visually inspect the lower lug end of the upper drag strut sub=assembly on the main landing gear for cracks, in accordance with ACCOMPLISHMENT INSTRUCTIONS in DeHavilland Alert Service Bulletin A7-32-18, paragraphs 1. and 2., dated February 6, 1980, or equivalent. 2. At intervals of 40 hours in service or 50 landings, whichever occurs first, after the effective date of this AD, with gear partially retracted, inspect lugs for cracks in accordance with paragraph 3. of the above DeHavilland service bulletin ACCOMPLISHMENT INSTRUCTIONS or equivalent. 3. If cracks are found, the upper drag strut assembly must be replaced before further flight by parts with the same part numbers or equivalent, inspected and found serviceable in accordance with the above DeHavilland service bulletin or equivalent. 4. Within 200 hours in service or 250 landings, whichever occurs first, after the effective date of this AD, inspect the upper drag strut lower lug ends by Eddy Current methods in accordance with paragraph 4. of the ACCOMPLISHMENT INSTRUCTIONS in the above DeHavilland service bulletin or equivalent. 5. When inspection in paragraph 4. is accomplished the inspections in paragraphs 1. and 2. are no longer required. 6. Report positive findings, including crack length, from any inspection, to the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, within 10 days of inspection. (Reporting approved by Office of Management and Budget under OMB No. 04-R0174.) 7. Equivalent parts and inspections must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 8. Compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, upon receipt of substantiating data submitted through an FAA Maintenance Inspector. This amendment is effective April 16, 1980. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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