AD 85-22-13

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AD Number:
85-22-13
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
LOCKHEED-CALIFORNIA COMPANY Model L-1011 Series Airplanes
Subject:
Pitch Control
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
11/12/1985
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Superseded AD: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Superseded By: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: 85-22-13
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5160

AD NUMBER:   85-22-13

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

ACTION:  

SUMMARY:  

DATES:   Effective November 12, 1985.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
85-22-13 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-5160. Applies to Lockheed Model L-1011 series airplanes, certificated in any category. Compliance required as indicated unless previously accomplished.

To prevent loss of pitch control as a result of loss of both pitch-system series trim-input bellcranks due to stress corrosion, accomplish the following:

A. Within 30 days after the effective date of this AD, visually inspect both pitch- system series trim-input bellcranks in accordance with Lockheed Service Bulletin 093-27-290 dated September 23, 1985, or later FAA-approved revision:

1. If no cracks are found, reinspect in accordance with paragraph A., above, at intervals not to exceed 8 months.

2. If only one bellcrank is cracked, the airplane may remain in service if:

a. There is no obvious damage or cracks outside the inspection area, as defined by Figure 1, Sheet 2 of Lockheed Service Bulletin 093-27-290, dated September 23, 1985, or later FAA-approved revision; and

b. At intervals not to exceed 10 days, both bellcranks are reinspected in accordance with paragraph A., above; and

c. Within 90 days after discovery of the cracked bellcrank, the torque-tube assembly is replaced.

3. If all of the conditions set forth in paragraph A.2., above, cannot be met, replace the torque-tube assembly prior to further flight.

4. If both bellcranks are cracked, replace the torque-tube assembly prior to further flight.

B. The repetitive inspections required by paragraph A.1., above, may be discontinued after the torque-tube assembly is replaced by an assembly modified in accordance with Lockheed Service Bulletin 093-27-290, dated September 23, 1985, or later FAA-approved revision.

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

D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a base for accomplishment of the inspections or modifications required by this AD.

All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Support Contracts, Dept. 63-11, U-33, B-1. These documents also 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 November 12, 1985.

FOOTER: