AD 65-13-05

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AD Number:
65-13-05
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
LOCKHEED Model 1329 Aircraft
Subject:
Elevator Counterweight Attach Bolts
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
06/13/1965
Make:
Lockheed Martin Corporation
Model:
1329-23A | 1329-23D
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Superseded AD: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Superseded By: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: 65-13-05
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-87

AD NUMBER:   65-13-05

SUBJECT HEADING:   LOCKHEED Model 1329 Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated June 13, 1965.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
65-13-05 LOCKHEED: Amdt. 39-87 Part 39 Federal Register June 22, 1965. Applies to Model 1329 Aircraft Serial Numbers 5001 through 5058.

Compliance required before further flight except that one flight may be made in accordance with the provisions of FAR 21.197 for the purpose of obtaining inspection and rework.

To prevent loss of elevator inboard counterweights accomplish the following:

(a) Remove empennage trailing edge fairing installation P/N JE114 to gain access to inboard elevator counterweights and their attach bolts P/N AN 174H10A.

(b) Remove aft outboard and two inboard attach bolts one at a time and measure shank length. Replace bolts with AN 174H10A bolt if shank length is less than 1.016 inch. Torque to 70-100 inch-pounds.

(c) Back off forward outboard attach bolt eight turns. If bolt is still engaged, retorque to 70-100 inch-pounds. If bolt is not engaged at eight turns, but is engaged at least four turns, retorque to 70-100 inch-pounds. Replace any bolt having less than a four turn engagement with a AN 174H10A bolt. This can be accomplished by disconnecting the vertical push-pull rod from elevator horn on side being worked. Then remove torque tube flange bolt connecting the elevator. This will free elevator assembly so that counterweight can be rotated sufficiently for bolt access. Upon completion reassemble, torque and safety wire bolts.

(d) Inspect two aft adjustment weight attach bolts, if installed, for proper length. Correct length is at least one thread extending through barrel nut. Replace as required with AN 174H()A bolt to obtain proper length. Torque to 70-100 inch-pounds.

(e) Safety wire in pairs with MS20995C40 or equivalent, the attach bolt head of the two outboard, the two inboard and the two aft adjustment weight attach bolts, if installed.

(f) Replace empennage trailing edge fairing.

(g) At the next 100-hour inspection, remove and replace any forward outboard attach bolt found by inspection of (c) to have less than eight turn engagement, with AN 174H10A bolt torqued to 70-100 inch-pounds and safety wired in accordance with (e).

(Lockheed Service Bulletin 329-206 covers this same subject.)

NOTE: It is requested that the results of this inspection be reported to the FAA, Engineering and Manufacturing Branch, Southern Region, P.O. Box 20636, Atlanta, Georgia 30320.

This directive effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated June 13, 1965.

FOOTER: