AD 84-13-51 R1

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AD Number:
84-13-51 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
LOCKHEED-CALIFORNIA COMPANY Models L-1011 Series Airplanes
Subject:
Fuel System Limitations
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
11/14/1984
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Superseded AD: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Superseded By: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: 84-13-51 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4947

AD NUMBER:   84-13-51 R1

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

ACTION:  

SUMMARY:  

DATES:   Effective November 14, 1984.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
84-13-51 R1 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-4947. Applies to Lockheed Models L-1011 series airplanes, certificated in all categories. Compliance required as indicated unless previously accomplished.

A. Unless the inspection requirements of paragraph B., below, have been accomplished within the previous 2,000 flight hours or 1,000 landings, whichever came first, revise the Lockheed L-1011 FAA approved airplane flight manual (AFM) LR-25925 within 5 calendar days after receipt of this airworthiness directive (AD), to add the following and provide to flight crews:

SECTION 1 - LIMITATIONS

Fuel System

1. In addition to normal fuel reserve requirements, flight planning must be predicated on the following:

A) A fuel fitting failure, occurs to engine No. 1 or 3 at any time during the flight;

B) 10,000 pounds of fuel will be lost overboard while the flight crew recognizes and reacts to a fuel line failure;

C) At the time of fuel line failure, the respective No. 1 or 3 engine is considered to become inoperative; and

D) At the time of failure, the flight can be continued to a suitable airport.

2. Cockpit fuel totalizer and fuel quantity indicating systems for tanks 1 and 3 must be operational prior to takeoff. Aircraft equipped with tanks 1A and 3A, when fueled, must have the respective cockpit fuel quantity indicating systems operational prior to takeoff.

3. The fuel quantity must be closely monitored and compared with total fuel used at 5 minute maximum intervals during flight.

SECTION 2 - EMERGENCIES

Rapidly Decreasing Fuel Quantity Indication

Reference.

If fuel quantity indication decreases at an abnormally high rate, assume a leak in the fuel line to engine No. 1 or 3 and proceed as follows:

1. All fuel crossfeed valves close

2. All fuel quantity indicators monitor

3A. If fuel quantity indication in tanks 1 and 3 decrease at a normal rate, resume normal operation.

3B. If fuel quantity indication continues to decrease abnormally in tanks 1 or 3:

1.) Fuel tank pumps (in affected tank) off

2.) Affected engine shut down

3.) Affected tank valve close

4.) Fuel quantity indicators (Tank 1 and 3) monitor

5.) Aircraft range check

6.) With tank valve closed, remaining fuel in affected tank is available to the other engines by use of crossfeed procedures.

B. Within 1,000 hours time in service, or ninety (90) days after the effective date of this amendment, whichever occurs first, inspect and replace, if necessary, P/N 741266-101 fuel line fittings as specified in Paragraph 2, Accomplishment Instructions of Lockheed L-1011 Service Bulletin 093-28-072, dated July 23, 1984; or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. Repetitive inspections of P/N 741266-101 fuel line fittings are required at 1000 landing intervals using visual inspections, or 1500 landing intervals using eddy current inspections, until P/N 741266-105 fuel line fittings are installed.

NOTE: Installation of P/N 741266-105 fuel line fittings is terminating action for this AD.

C. A copy of this AD inserted in the FAA approved AFM may be considered as an acceptable means of compliance with required AFM revisions.

D. 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.

E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the repair requirements of 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 14, 1984, and was effective earlier to those recipients of telegraphic AD T84-13-51, dated June 21, 1984.

FOOTER: