| AD Number | 90-03-15 | Status | Active |
| Effective Date | March 05, 1990 | Issue Date | Not specified |
| Docket Number | 89-NM-170-AD | Amendment | 39-6494 |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Lockheed Martin Corporation |
| Model(s) | L-1011-385-1 L-1011-385-1-14 L-1011-385-1-15 L-1011-385-3 |
90-03-15 LOCKHEED AERONAUTICAL SYSTEMS COMPANY: Amendment 39-6494. Docket No. 89-NM-170-AD.
Applicability: Model L-1011 series airplanes, certificated in any category.
Compliance: Required as indicated, unless previously accomplished.
To prevent the failure of No. 3 flap vane outboard carriage link assembly, accomplish the following:
A. Prior to the accumulation of 6,000 landings or 15,000 flight hours, whichever occurs first, or within 30 days after the effective date of this AD, whichever occurs later, conduct the following in accordance with Section 2, "Accomplishment Instructions," of Lockheed Service Bulletin 093-57-209, dated August 10, 1989:
1. Inspect the left and right No. 3 flap vane outboard carriage link assembly for cracks, using the eddy-current procedure as described in the Service Bulletin.
2. If no cracks are found, conduct repetitive eddy current inspections in accordance with the Service Bulletin at intervals not to exceed 1,000 landings.
3. If a crack is found, replace the link assembly with a new link assembly, P/N 1562426-101/-105, or with a titanium No. 3 flap vane outboard carriage link assembly, P/N 1562426-109.
4. If not previously accomplished, remove existing rub strips on the lower surface of spoilers No. 3 through No. 6 in accordance with the procedure described in the Service Bulletin. Then conduct a No. 3 flap vane-to-flap contact check, rigging check, and adjustment in accordance with L-1011 Maintenance Manual, Section 27-51-00. Check the vane-to-spoiler clearance to ensure that a minimum clearance of 0.20 inch is maintained.
5. If rub strips were previously removed, check the vane-to-spoiler clearance as described in the L-1011 Maintenance Manual, Section 27-51-00.
B. Installation of the titanium link assembly, P/N 1562426-109, constitutes terminating action for the repetitive inspections required by paragraph A.2., above.
C. Within 2 1/2 years after the effective date of this AD, replace all aluminum fittings with titanium fittings.
D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.
NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office.
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 Aeronautical Systems 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, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California.
This amendment (39-6494, AD 90-03-15) becomes effective on March 5, 1990.