81-21-51 R1 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-4329 as amended by Amendment 39-4533. Applies to Lockheed Model L-1011-385 series airplanes, certificated in all categories.
To alert the flight crew to conditions which may precede engine failure, perform the following, unless previously accomplished:
A. Within 25 hours time in service after the receipt of this AD or within 3 calendar days, whichever occurs later, revise the Lockheed L-1011 FAA approved Airplane Flight Manual LR-25925 to add the following and provide to flight crews:
NOTE: FAA approved Lockheed L-1011 Airplane Flight Manual revision dated September 29, 1981, is considered an acceptable means of compliance for paragraph A.
SECTION 1 - LIMITATIONS
POWERPLANT LIMITATIONS
Airborne Vibration Monitor (AVM) System
o At least one channel (A or B) (FAN or TURB) of the AVM System must be operative for each engine for all flight operations.
o The operative AVM channel (A or B) (FAN orTURB) must be the same for all engines and must be latched in.
o When both channels of the AVM System are operative, channel A or FAN must be latched in. If this channel becomes inoperative (indication goes to zero) inflight, select B or TURB.
o For single or dual channel operation, the AVM filter selector must be set to the NORM position.
SECTION 2 - EMERGENCIES
ENGINE ABNORMAL VIBRATION INDICATION.
During steady running conditions, if an Airborne Vibration Monitor (AVM) System channel indicates a sudden increase of 1 unit or more, or exceeds 2.5 units (warning light setting) for more than 2 seconds, even if the indication returns to normal:
IMMEDIATE ACTION
THROTTLE
Close
FUEL AND IGNITION SWITCH
Off
NOTE
During takeoff roll, a momentary fluctuation of the AVM indication with no other indication of engine malfunction is not cause for engine shutdown.
REFERENCE
HYDRAULIC POWER
Check
ELECTRICAL LOADS
Monitor
AC ESSENTIALPOWER
Check
Do not attempt a relight unless a greater emergency exists.
NOTE
When holding or descending in heavy icing conditions, the AVM indication may gradually increase to above 2.5 units (warning light setting). No action is required unless other indications of engine malfunction are observed. This condition can be alleviated by increasing N1 to 90 percent for 5 seconds when ice accumulation (gradual vibration increase) is first detected.
SECTION 2 - EMERGENCIES
ENGINE OIL FILTER PRESSURE LIGHT ILLUMINATED
If the engine oil FILTER PRESSURE light illuminates steadily:
IMMEDIATE ACTION
THROTTLE
Close
FUEL AND IGNITION SWITCH
Off
REFERENCE
HYDRAULIC POWER
Check
ELECTRICAL LOADS
Monitor
AC ESSENTIAL POWER
Check
Do not attempt a relight unless a greater emergency exists.
B. Within 25 hours time in service after the receipt of this AD, reactivate the AVM input to the ENG/APU STATUS light in accordance with the Accomplishment Instructions in Lockheed L-1011 Alert Service Bulletin 093-77-A044, Revision 2, dated September 29, 1981, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA Northwest Mountain Region.
C. Within 75 days calendar time after receipt of this AD, comply with paragraphs A and B (Parts I and II) of the Accomplishment Instructions in Lockheed L-1011 Alert Service Bulletin 093-77-A049 dated September 29, 1981, or Revision 1, dated October 13, 1981, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA Northwest Mountain Region.
D. When the indications specified in paragraph A above occur, engines must undergo the following appropriate maintenance actions prior to further engine operation for flight:
1. Rolls Royce Alert Service Bulletin RB.211-77-A6422 dated September 4, 1981, paragraph D.(3) for oil pressure and/or AVM indications.
2. Lockheed L-1011 Maintenance Manual Chapter 71-91-00, High Indicated Vibration.
E. For aircraft incorporating engines which are in compliance with AD 82-12-05, Amendment 39-4398, and which have engine indicating systems modified in accordance with the Accomplishment Instructions in Lockheed L-1011 Service Bulletin 093-77-052, dated December 17, 1982, the Powerplant Limitations and Emergency Procedures contained in FAA approved Lockheed L-1011 Airplane Flight Manual No. LR-25925 revision dated December 20, 1982, may be used in lieu of those specified in paragraph A. above.
F. Special flight permits for a two-engine ferry flight may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.
G. Alternate methods of compliance with this AD which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA Northwest Mountain Region.
The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1).
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 Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California.
Amendment 39-4329 became effective March 11, 1982, to all persons, except those to whom it was made immediately effective by Telegraphic AD T81-21-51, dated October 1, 1981.
This Amendment 39-4533 becomes effective January 17, 1983.