AD 65-13-04

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AD Number:
65-13-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; GRUMMAN Model G-159 Aircraft
Subject:
Nose Gear Strut Assembly
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
06/12/1965
Make:
Gulfstream Aerospace Corporation
Model:
G-159
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Superseded AD: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Superseded By: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: 65-13-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-80

AD NUMBER:   65-13-04

SUBJECT HEADING:   Airworthiness Directives; GRUMMAN Model G-159 Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective June 12, 1965.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   65-13-04 GRUMMAN: Amdt. 39-80 Part 39 Federal Register June 12, 1965. Applies to Model G-159 Aircraft Equipped with Bendix Nose Gear Strut Assembly, P/N 1722-40 or 2570890.

Compliance required as indicated.

To prevent failure of the nose gear trunnion, accomplish the following:

(a) Inspect the nose gear trunnion, Bendix P/N 171467 in accordance with (c) within the next 20 hours' time in service after the effective date of this AD unless replaced within the next 20 hours' time in service after the effective date of this AD, or unless already inspected within the last 80 hours' time in service, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection.

(b) Within the next 20 hours' time in service after replacement of a nose gear trunnion, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, inspect the replacement trunnion in accordance with (c).

(c) Inspect the retract shaft attachment lugs on the nose gear trunnion forward flanges for cracks in the radii above and below the area where the retract shaft attachment lugs blend into the trunnion flanges, using the dye penetrant method with a 10 power or greater glass or an FAA-approved equivalent.

(d) Replace cracked trunnions with a trunnion of the same part number or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, before further flight except that the aircraft may be flown in accordance with the provisions of FAR 21.197, after approval by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, to a base where the repair can be made.

This directive effective June 12, 1965.

FOOTER: