AD 72-07-08

AD Final Rules - DRS_72-07-08.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
72-07-08
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; GRUMMAN Model G-159 Airplanes
Subject:
Main Landing Gear Drag Brace
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/30/1972
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Superseded AD: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Superseded By: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: 72-07-08
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1419

AD NUMBER:   72-07-08

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

ACTION:  

SUMMARY:  

DATES:   Effective March 30, 1972.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   72-07-08 GRUMMAN: Amdt. 39-1419. Applies to all Model G-159 Airplanes certificated in all categories. Compliance required as indicated unless already accomplished.

To prevent jamming of the main landing gear drag brace assembly, P/N 159L10003, accomplish the following:

(a) For airplanes having been inspected and modified, if necessary, in accordance with Grumman Customer Bulletin Number 99 or 217 within the last 50 hours time in service, comply with paragraph (e) below within the next 50 hours time in service after the effective date of this AD.

(b) For all airplanes incorporating a new drag brace lower bearing, P/N 159LM10011-3 or -5, within the last 100 hours time in service, comply with paragraph (e) below within the next 15 hours time in service after the effective date of this AD.

(c) Airplanes having been inspected and modified, if necessary, in accordance with Grumman Customer Bulletin 217A have met the requirements of this AD.

(d) All airplanes that do not meet the requirements set forth in paragraphs (a), (b), or (c) above, must comply with paragraph (e) below within the next 15 hours time in service after the effective date of this AD.

(e) (1) Inspect the following areas of the main landing gear drag brace assembly in accordance with Grumman Customer Bulletin 217A dated February 18, 1972 or later FAA approved revision:

(a) Inner cylinder, P/N 159LM10001, for wear and galling;

(b) The lower bearing, P/N 159LM10011, for wear and proper wall thickness;

(c) The down lock, P/N 159LM10007, for the presence of a .030 + 010 inch radius on the 2.735 inch major diameter.

(2) If bearing wear or improper wall thickness is found, before further flight, replace with a P/N 159LM10011-7 bearing.

(3) If the down lock radius is absent, or if wear or galling of the inner cylinder is noted, before further flight, rework in accordance with Grumman Customer Bulletin 217A.

(f) Airplanes requiring any action under sub-paragraph (e)(2) or (e)(3) above, may be flown with the landing gear in the down and locked position in accordance with FAR 21.197 to a base where the repair or modification can be accomplished.

This amendment becomes effective March 30, 1972.

FOOTER: