AD 61-21-06

AD Final Rules - DRS_61-21-06.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
61-21-06
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
LOCKHEED Models PV-1 and B-34
Subject:
Landing Gear Lower Drag Strut
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
11/03/1961
Make:
Air Trading Corporation
Model:
Army B-34 | Navy PV-1
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Superseded AD: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Superseded By: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: 61-21-06
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   61-21-06

SUBJECT HEADING:   LOCKHEED Models PV-1 and B-34

ACTION:  

SUMMARY:  

DATES:   Effective November 3, 1961.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
61-21-06 LOCKHEED: Amdt. 343 Part 507 Federal Register October 4, 1961. Applies to All PV-1 and B-34 Type Aircraft Having Main Landing Gear Lower Drag Struts P/N 112004.

Compliance required as indicated.

During investigation of a PV-1 main landing gear failure, the main landing gear lower drag strut, P/N 112004, was found to be understrength because it was not in the specified heat-treated condition. As a result of this service experience, the following is required:

(a) Within the next 50 hours' time in service from the effective date of this directive unless already accomplished, determine by the Brinell, Rockwell, or an equivalent hardness test method whether or not the struts, P/N 112004, are heat-treated to an ultimate tensile strength of 150,000 to 170,000 p.s.i. If the ultimate tensile strength is less than 150,000 p.s.i., the strut must be replaced with a similar part heat-treated to 150,000 to 170,000 p.s.i. or by a strut, P/N 125715 or equivalent, prior to further flight, except for ferry flight in accordance with the provisions of CAR 1.76.

NOTE: Strut, P/N 125715, originally designed for the PV-2 type aircraft is an acceptable alternative for strut, P/N 112004, and a hardness test on this strut is not necessary. If the P/N is missing or obscured, the struts may be identified by the following: The PV-2 strut, P/N 125715, weighs approximately 15.5 pounds and the PV-1 strut, P/N 112004, weighs approximately 10.5 pounds. The PV-2 strut tube has a wall-thickness of 0.25 inch whereas the PV-1 part has a wall- thickness of 0.156 inch. The wall-thickness can be measured by laying a straight edge along the tube and measuring the perpendicular distance between the straight edge and the end fitting.

(b) Spare lower drag struts, P/N 112004, must comply with the hardness test and replacement provisions of (a) prior to installation.

This directive effective November 3, 1961.

FOOTER: