AD 80-02-11

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AD Number:
80-02-11
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; DeHavilland Model DHC-7 Airplanes
Subject:
Main Landing Gear Frame Bolts
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
01/24/1980
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Superseded AD: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Superseded By: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: 80-02-11
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3672

AD NUMBER:   80-02-11

SUBJECT HEADING:   Airworthiness Directives; DeHavilland Model DHC-7 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective January 24, 1980.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
80-02-11 DeHAVILLAND: Amendment 39-3672. Applies to DHC-7 airplanes, S/N 1 through 13 inclusive, certificated in all categories.

Compliance required as indicated, unless already accomplished.

To prevent possible landing gear support structure failure due to looseness of the main landing gear frame attachment bolts, accomplish the following:

1. Within the next 25 hours in service after the effective date of this AD, unless previously accomplished within the last 295 hours in service, inspect the main landing gear frame bolts, P/N MS21250H10042, for evidence of improper torque.

2. If evidence of improper torque is found at any bolt location,

a. cut an access hole at all four bolt locations as detailed in DeHavilland Service Bulletin No. 7-54-4, ACCOMPLISHMENT INSTRUCTIONS, Page 2, paragraphs 1 and 2. Retorque all bolts to 1400-1650 inch-pounds and cover the access holes with snap hole plug P/N CSP80-20 or equivalent. Mark the end of the bolt, nut and adjacent structure with a red line. Visually inspect the red marking at each location for signs of movement at intervals not to exceed 320 hours in service from last inspection until the modification in paragraph 2.b. is accomplished, or

b. incorporate DeHavilland modification (Ref. S/B 7-54-4).

3. For bolts that are found to be properly torqued, mark and inspect bolts as above in paragraph 2.a. until the modification is accomplished.

4. Incorporate DeHavilland modification in accordance with S/B No. 7-54-4, ACCOMPLISHMENT INSTRUCTIONS, or equivalent, within 1900 hours in service from the initial inspection in paragraph 1.

5. Equivalent parts and modification must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.

This amendment is effective January 24, 1980.

FOOTER: