AD 65-16-01

AD Final Rules - DRS_65-16-01.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
65-16-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
LOCKHEED Models 188A and 188C Series Aircraft
Subject:
Nose Landing Gear Support Link
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/30/1965
Make:
Lockheed Martin Corporation
Model:
188A | 188C
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Superseded AD: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Superseded By: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: 65-16-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-101

AD NUMBER:   65-16-01

SUBJECT HEADING:   LOCKHEED Models 188A and 188C Series Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective July 30, 1965.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
65-16-01 LOCKHEED: Amdt. 39-101 Part 39 Federal Register June 30, 1965. Applies to Models 188A and 188C Series Aircraft.

Compliance required as indicated.

As a result of cracks, substandard heat treat, and failure of the nose landing gear actuator support link, LAC P/N 750645-3 manufactured by Acor, Inc., under Acor P/N N07011, accomplish the following:

(a) Unless already accomplished within the last 1,700 landings prior to the effective date of this AD, within the next 300 landings after the effective date of this AD, comply with all requirements of (b) (except, that if a hardness check in accordance with (b) was accomplished at any time prior to the effective date of the AD, it need not be reaccomplished), and thereafter at intervals not to exceed 2,000 landings, comply with those requirements of (b) that pertain to crack inspection and replacement of cracked links.

(b) Inspect all Acor, Inc., links for cracks in the necked down area of the link using magnetic particle technique or an FAA-approved equivalent and check the hardness of the Acor, Inc., link flats midway between the bearings. Replace any cracked links and any link on which the heat treat is less than 140,000 p.s.i. before further flight with a new LAC P/N 750645-3 link. If an Acor link is to be installed, its hardness must be checked prior to installation, and its heat treat must be 140,000 p.s.i. or greater. Accomplish this replacement in accordance with sections 2.B(6) through 2.B(10) of Lockheed Service Bulletin 88/SB-612.

(c) The inspections of (b) may be discontinued when LAC P/N 750645-3 link manufactured by Acor, Inc., under Acor P/N N07011 is replaced by a new LAC P/N 750645-3 link manufactured by other than Acor, Inc.

NOTE: LAC P/N 750645-3 link manufactured by Acor, Inc., under Acor P/N N07011 may be identified by its center body thickness which is greater than 0.400 inch.

(d) For the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each aircraft's hours' time in service by the operator's fleet average time from takeoff to landing for the aircraft type.

(e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator.

(Lockheed Service Bulletin 88/SB-612 dated February 14, 1964, covers this same subject).

This directive effective July 30, 1965.

FOOTER: