AD 72-14-04

AD Final Rules - DRS_72-14-04.html
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AD Number:
72-14-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; NORTH AMERICAN ROCKWELL Models NA-265, NA-265-20, NA-265-30, NA-265-40, an...Show more
Subject:
Main Gear Door Torque Tube
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/07/1972
Make:
Sabreliner Corporation
Model:
NA-265 | NA-265-20 | NA-265-30 | NA-265-40 | NA-265-60
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Superseded AD: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Superseded By: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:
Updated RGL applicability to match AD applicability; CAR C-11-185
AIRWORTHINESS DIRECTIVES FINAL RULES: 72-14-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1481

AD NUMBER:   72-14-04

SUBJECT HEADING:   Airworthiness Directives; NORTH AMERICAN ROCKWELL Models NA-265, NA-265-20, NA-265-30, NA-265-40, and NA-265-60

ACTION:  

SUMMARY:  

DATES:   Effective July 7, 1972.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   72-14-04 NORTH AMERICAN ROCKWELL: Amdt. 39-1481. Applies to Models NA-265, NA-265-20, NA-265-30, NA-265-40 (Serial Nos. 282-1 thru 282-105), and NA-265-60 (Serial Nos. 306-1 thru 306-63).

Compliance required as indicated:

To prevent failure of the main landing gear wheel door torque tube assembly, P/N 265- 333338-1, -2, 285-333338-1, -2, -31, -32, as applicable, accomplish the following:

(a) Within 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 50 hours' time in service, and at intervals not to exceed 100 hours' time in service thereafter, perform a dye penetrant inspection of the main landing gear wheel door torque tube in the area 3 inches adjacent to the fore and aft weldments for evidence of cracking, until (c), below, is accomplished.

(b) If evidence of cracking is discovered as a result of any of the inspections of (a), above, replace the torque tube assembly with a new or serviceable assembly prior to further flight. Mark the rejected part to prevent inadvertent return to service (Note: The manufacturer has recommended that operators return parts for rework by them. If returned, and after rework, the mark may be removed, the part re-identified, and returned to service).

(c) Replace main landing gear wheel door torque tube assemblies P/N 265-333338- 1, -2, 285-333338-1, -2, -31, -32 with torque tube assemblies P/N 285-333338-51, -52, 276- 933338-1, -2, -31, -32, -41, -42, -51, -52 as applicable.

This amendment becomes effective July 7, 1972.

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