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P.O. Box 3707 M/C 20-89
Seattle, WA 98124-2207
USA
Fax: (206) 662-7812
Telex: 32-9430 Station 627
SITA: SEABO7X
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Sect Name Section Name
Operations Manual Bulletin
for
The Boeing Company
Seattle, Washington 98124-2207
International Lease Finance Corp.
Number: ILF2-48(R1)
Date: April 1, 2001
Document Effectivity: D6-30151-425
Subject: VNAV ALTITUDE CAPTURE ANOMALY
Reason: To inform flight crews the airplane may pitch over duringVNAV cruise
altitude capture at high altitude. Revised to add Service Bulletin
THE FOLLOWING PROCEDURE AND/OR INFORMATION IS EFFECTIVE UPON RECEIPT
Information in this bulletin is recommended by The Boeing Company, but may not be FAA approved
at the time of writing. In the event of conflict with the FAA approved Airplane Flight Manual (AFM),
the AFM shall supersede. The Boeing Company regards the information or procedures described
herein as having a direct or indirect bearing on the safe operation of this model airplane.
information.
Background Information
Boeing has received several in-service reports of an anomaly that may occur
during VNAV cruise altitude capture following VNAV climb. If the FMC cruise
altitude is near the FMC maximum altitude, and airplane climb speed is slightly
below FMC command speed when cruise altitude capture occurs, the airplane may
pitch over and descend attempting to accelerate to FMC command airspeed.
Thrust reduction may occur during the descent.
Operating Instructions
This bulletin does not apply to airplanes modified by Boeing Service Bulletin 747-
34A2672 (FMC software load 15).
If this anomaly occurs, disengage the autopilot, disconnect the autothrottle, and
level the airplane at cruise altitude. Once established at cruise altitude with the
AFDS pitch mode VNAV PTH active, the autopilot may be reengaged and
autothrottle reactivated.
Page 2 of 2
Operations Manual Bulletin No. ILF2-48(R1), Dated April 1, 2001 (continued)
Administrative Information
This bulletin replaces bulletin ILF2-48 dated January 14, 2000. Discard Bulletin
ILF2-48. Revise the Bulletin Record to show ILF2-48 CANCELLED (CANC).
Insert this bulletin behind the Operations Manual Bulletin Record page in Volume
1 of your Operations Manual. Amend the Operations Manual Bulletin Record to
show bulletin ILF2-48(R1) IN EFFECT (IE).
This Operations Manual Bulletin will be cancelled after Boeing has been notified
all affected airplanes in your fleet have been modified by SB 747-34A2672. If you
do not plan to modify all your airplanes and would like the contents of this bulletin
incorporated in your Operations Manual, please advise Boeing accordingly.
Please send all correspondence regarding Operations Manual Bulletin status to
one of the following addresses:
Mailing Address:Manager, Flight Technical Publications (747-400)
Boeing Commercial Airplane Group
P.O. Box 3707 M/C 20-89
Seattle, WA 98124-2207
USA
Fax: (206) 662-7812
Telex: 32-9430 Station 627
SITA: SEABO7X
CS3 2786
Page 1 of 2
Sect Name Section Name
Operations Manual Bulletin
for
The Boeing Company
Seattle, Washington 98124-2207
International Lease Finance Corp.
Number: ILF2-49
Date: July 5, 2000
Document Effectivity: D6-30151-425
Subject: ENGINE BLEED AIR SHUTOFF ANOMALY
Reason: To inform flight crews a system fault can result in the shutoff of all
THE FOLLOWING PROCEDURE AND/OR INFORMATION IS EFFECTIVE UPON RECEIPT
Information in this bulletin is recommended by The Boeing Company, but may not be FAA approved
at the time of writing. In the event of conflict with the FAA approved Airplane Flight Manual (AFM),
the AFM shall supersede. The Boeing Company regards the information or procedures described
herein as having a direct or indirect bearing on the safe operation of this model airplane.
engine bleed air.
Background Information
An operator recently reported shutoff of bleed air from all engines during flight.
Investigation revealed a single fault in the Air Supply Control Test Unit (ASCTU)
can result in closure of all engine bleed air valves and illumination of all Engine
Bleed Air OFF lights. In the reported incident the fault was intermittent.When the
fault was removed, low-pressure bleed air became available and all Engine Bleed
Air OFF lights extinguished. Cycling the Engine Bleed Air Switches recovered
normal engine bleed air.
With this fault the BLEED 1, 2, 3 and 4 messages do not display. With bleed air
shut off to all using systems, the following indications will be observed:
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