(b)  
If the CDS BITE test does not show an EFIS data fault, then continue.

(2)
Replace the engine control module, P2-2.

(a)  If the V1 bug shows on the MASI, then you corrected the fault.
-------------------------END OF TASK ---------------------------
EFFECTIVITY SIL ALL  34-16 TASK 802 
D633A103-SIL BOEING PROPRIETARY -Copyright # Unpublished Work -See title page for details  Page 203 Jun 10/2006 

801.  Integrated Standby Flight Display BITE Procedure
A.  General
(1)  
In this task, you do the BITE procedure for the integrated standby flight display (ISFD) system.

(2)  
The integrated standby flight display is installed in the P2 center instrument panel.

(3)  
Switches used for the self test are on the front panel of the integrated standby flight display.

(4)  
Current faults will show any internal faults that are active for the integrated standby flight display.

B.  BITE Procedure
(1) Do these steps to find any current internal faults for the integrated standby flight display:
(a)  
Push APP and HP/IN, on the face of the ISFD, for approximately two seconds.

(b)  
Push the + select key next to <TESTS.

(c)  
Push the select key next to <FUNCTIONAL TEST (110s).

NOTE: The TEST screen will display IN PROGRESS 110s.
(d)  
If the TEST result displays OK, there are no internal faults for the integrated standby flight display.

(e)  
If the TEST result displays an internal fault message, replace the integrated standby flight display. These are the tasks:

Integrated Standby Flight Display Removal, AMM TASK 34-24-02-000-801, Integrated Standby Flight Display Installation, AMM TASK 34-24-02-400-801.
-------------------------END OF TASK ---------------------------
802.  Procedure To Be Determined -Fault Isolation
A.  Fault Isolation Procedure
(1)  At this time the FIM does not have a procedure for this fault. The FIM will contain a procedure for this fault in the future.
-------------------------END OF TASK ---------------------------
EFFECTIVITY

34-20 TASKS 801-802
SIL ALL; AIRPLANES WITH THE INTEGRATED STANDBY FLIGHT DISPLAY
Page 201 D633A103-SIL Jun 10/2006

801.  ADIRS BITE Procedure
A.  General
(1)  
You do the air data inertial reference system (ADIRS) fault retrieving from the control display unit (CDU). There are two CDUs on the forward electronic panel in the flight compartment.

(2)  
Do one of these items on the ADIRS L BITE or ADIRS R BITE main menu to retrieve the faults:

(a)  
CURRENT STATUS.

(b)  
INFLIGHT FAULTS.

(3)  
CURRENT STATUS

(a)  The CURRENT STATUS display shows mainteneance messages that are currently active. A maintenance message identifies a specific failure which is found by the air data inertial reference unit (ADIRU). The maintenance messages are in English text and have a seven digit number.
NOTE: The CURRENT STATUS messages can be clear on ground.
(4)  INFLIGHT FAULTS
(a)  
The INFLIGHT FAULTS display shows the flight legs during which faults occurred. The ADIRS can display the fault data for LEG 01 through LEG 09. The flight legs are shown with the flight leg that had the most current fault at the top of the first page. Only the flight legs during which faults occurred will show. You can use the PREV PAGE and NEXT PAGE keys to see all the legs. The takeoff time, the takeoff date, and the number of faults in the leg will show under each leg.

(b)  
When you push the line select key next to the prompt for one of the flight legs, you will see this data for each fault in the flight leg: 1) A maintenance message number and the message text 2) The date that the fault occurred 3) The time that the fault occurred
　
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