AD 86-23-52 R2

AD Final Rules - DRS_86-23-52_R.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
86-23-52 R2
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
LOCKHEED CALIFORNIA COMPANY Model L-1011-385 Series Airplanes
Subject:
Wing Rear Spar
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
05/01/1987
Make:
Lockheed Martin Corporation
Model:
L-1011-385-1 | L-1011-385-1-14 | L-1011-385-1-15 | L-1011-385-3
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Superseded AD: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Superseded By: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: 86-23-52 R2
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5605

AD NUMBER:   86-23-52 R2

SUBJECT HEADING:   LOCKHEED CALIFORNIA COMPANY Model L-1011-385 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective May 1, 1987.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
86-23-52 R2 LOCKHEED CALIFORNIA COMPANY: Amendment 39-5605. Applies to Model L-1011-385 series airplanes certificated in any category. Compliance required as indicated, unless previously accomplished.

To prevent wing rear spar failure due to fatigue cracking, accomplish the following:

A. Within 40 landings after the effective date of this AD, or prior to accumulation of 6,000 landings, whichever occurs later, unless already accomplished within the last 260 landings, and thereafter at intervals not to exceed 300 landings, inspect the wing rear spar in accordance with the ultrasonic inspection procedures specified in Section 2, Accomplishment Instructions of Lockheed Service Bulletin 093-57-A181, Revision 3, dated December 11, 1986, or later FAA- approved revision. Ultrasonic inspections accomplished in accordance with Lockheed Service Bulletin 093-57-A181, Revision 1, dated November 20, 1986, or Revision 2, dated November 26, 1986, prior to receipt of telegraphic AD T86-23-52 R1, satisfies the initial ultrasonic inspection requirements of this paragraph.

B. If a crack is found, repair before further flight in a manner approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.

C. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.

All persons affected by this directive who have not already received the appropriate service documents from the manufacturer, may obtain copies upon request to Lockheed-California Company, P. O. Box 551, Burbank, California 91520, Attention: Commercial Order Administration, Dept. 65-33, U-33, B-1. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California.

This Amendment becomes effective May 1, 1987, as to all persons, except those persons to whom it was made immediately effective by telegraphic AD T86-23-52-R1, issued December 18, 1986.

FOOTER: