(b)
SPD flag shows on first officer’s EFIS display.
(c)
True airspeed (TAS) data does not show on the first officer’s EFIS display.
B. Possible Causes
(1)
Loose AOA vane ground wire in ground stud
(2)
ADM
(3)
Wiring between the ADIRUs and the DEU 2
EFFECTIVITY
34-21 TASKS 827-828
SIL ALL
Page 257 D633A103-SIL Oct 15/2008
(4)
Right ADIRU, M1752
(5)
DEU 2, M1809
C. Circuit Breakers
(1) These are the primary circuit breakers related to the fault:
CAPT Electrical System Panel, P18-1
Row Col Number Name
E 5 C01009 ADIRU LEFT DC
E 7 C01007 ADIRU LEFT AC
CAPT Electrical System Panel, P18-2
Row Col Number Name
E 8 C00425 ADIRU LEFT EXC
F/O Electrical System Panel, P6-1
Row Col Number Name
C 14 C01008 ADIRU RIGHT AC
C 15 C00426 ADIRU RIGHT EXC
C 17 C01010 ADIRU RIGHT DC
D 9 C01362 DISPLAY DEU 2 HOLDUP
D 11 C01360 DISPLAY DEU 2 PRI
D. Related Data
(1)
(SSM 34-21-11)
(2)
(WDM 34-21-11)
(3)
(WDM 31-62-11)
E. Initial Evaluation
(1) Do these steps to prepare for initial evaluation and fault isolation:
(a)
Make sure the DISPLAY switch on the P5 panel is in the AUTO position.
(b)
Make sure the right ADIRU is aligned and in the NAV mode.
(c)
Make sure the L IRS switch on the mode select unit is in the OFF position.
(d)
Open these circuit breakers and install safety tags:
CAPT Electrical System Panel, P18-1
Row Col Number Name
E 5 C01009 ADIRU LEFT DC
E 7 C01007 ADIRU LEFT AC
CAPT Electrical System Panel, P18-2
Row Col Number Name
E 8 C00425 ADIRU LEFT EXC
(2) If the observed fault shows on the first officer’s EFIS display, then do the Fault Isolation Procedure below.
EFFECTIVITY SIL ALL 34-21 TASK 828
D633A103-SIL BOEING PROPRIETARY -Copyright # Unpublished Work -See title page for details Page 258 Oct 15/2008
(a) Remove the safety tags and close these circuit breakers:
CAPT Electrical System Panel, P18-1
Row Col Number Name
E 5 C01009 ADIRU LEFT DC
E 7 C01007 ADIRU LEFT AC
CAPT Electrical System Panel, P18-2
Row Col Number Name
E 8 C00425 ADIRU LEFT EXC
(3) If the observed fault does not show on the first officer’s EFIS display, then continue.
(a) Remove the safety tags and close these circuit breakers:
CAPT Electrical System Panel, P18-1
Row Col Number Name
E 5 C01009 ADIRU LEFT DC
E 7 C01007 ADIRU LEFT AC
CAPT Electrical System Panel, P18-2
Row Col Number Name
E 8 C00425 ADIRU LEFT EXC
F. Fault Isolation Procedure
(1)
Do the air data inertial reference system self-test in this task: Air Data Inertial Reference System -Operational Test, AMM TASK 34-21-00-710-801.
(a)
If static and/or pitot ADM test is unsatisfactory, then do these steps.
1) Replace the static and/or pitot ADM as appropriate, these are the task: Pitot Air Data Module Removal, AMM TASK 34-21-04-000-801, Pitot Air Data Module Installation, AMM TASK 34-21-04-400-801, Static Air Data Module Removal, AMM TASK 34-21-04-000-802, Static Air Data Module Installation, AMM TASK 34-21-04-400-802. a) If static and/or pitot ADM is satisfactory, then you corrected the fault. b) If the test is unsatisfactory, then continue. 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：737-600/700/800/900 FAULT ISOLATION MANUAL 故障隔离手册 导航(61)
