AD 64-12-05

AD Final Rules - DRS_64-12-05.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
64-12-05
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
LOCKHEED Models 188A and 188C Aircraft
Subject:
Landing Gear Cam Follower
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/28/1965
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Superseded AD: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Superseded By: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: 64-12-05
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   64-12-05

SUBJECT HEADING:   LOCKHEED Models 188A and 188C Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective September 28, 1965.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
64-12-05 LOCKHEED: Amdt. 744 Part 507 Federal Register June 9, 1964. Applies to All Models 188A and 188C Aircraft.

Compliance required as indicated.

As a result of failures of the landing gear cam follower P/N NAS 562-3-7A and of worn and bent landing gear lever detent plate P/N 827127-3 or -5, accomplish the following unless already accomplished:

(a) Correct Lockheed Service Information Letter 84 dated May 6, 1964, by changing in item 6 (A) the word "pilot's" to "co-pilot's" and by changing item 6 (F) to read "Perform steps 6 (A), (B) and (D) on pilot's landing gear control lever".

(b) Within the next 40 hours' time in service after the effective date of this AD and at periods not to exceed 4,000 hours' time in service from the last inspection, accomplish the following:

(1) Accomplish items 1 through 8 of the section entitled "Description" of Lockheed Service Information Letter No. 84 dated May 6, 1964, as corrected.

(2) If during accomplishment of item 6 (B) of Service Information Letter 84, the force required to unseat cam follower is less than 5 pounds, before further flight replace the control lever handle return spring with a new return spring.

(3) If during accomplishment of items 6(A), (C), (D), (E), and (F) of Service Information Letter 84, the cam follower is unseated from the detent, before further flight replace the cam follower P/N NAS 562-3-7A, with a new cam follower P/N NAS 562-3-7A and inspect the landing gear lever detent plate, P/N 827127-3 or -5, for deformation and for wear or cracks in the detents. If the landing gear lever detent plate exhibits wear beyond the wear limits recommended by the manufacturer or exhibits deformation or cracks, replace the detent plate, P/N 827127-3 or -5, with a new detent plate P/N 827127-3 or -5. The detent plates P/N 827127-3 or - 5 are interchangeable.

(4) If any parts are replaced in accordance with (b) (1) and (b)(3), before further flight rig the system in accordance with the Electra Maintenance Manual, Section 32-1-0 and reaccomplish items 1 through 8 of the section entitled "Description" of Lockheed Service Information Letter No. 84 dated May 6, 1964.

This directive effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated May 22, 1964.

Revised September 28, 1965.

FOOTER: