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FOLLOWED BY TWENTY (20) MINUTE COOL DOWN PERIOD.
THEN, THREE (3) ADDITIONAL START ATTEMPTS MAY BE MADE,
AFTER WHICH A ONE (1) HOUR COOL DOWN PERIOD MUST BE
OBSERVED.
When APU is up to speed (100% +3%):
6. Electric Master Auxiliary Power ..................................................ON
7. Auxiliary Power Loadings ...............................................OBSERVE
See the limitations at end of this procedure.
NOTE: If flight is continued above 30,000 ft., the following steps must
be accomplished to ensure continuous APU operation.
If the Left Converter / Alternator is inoperative, complete Steps 8
thru 12.
8. Electric Master RIGHT Power ....................................................ON
9. Left AC Main APU / EXT ...................... ON (MANUALLY SELECT)
10. Right AC Main RIGHT .......................... ON (MANUALLY SELECT)
11. Left DC Main TRU / EXT...................... ON (MANUALLY SELECT)
12. Right DC Main RIGHT.......................... ON (MANUALLY SELECT)
Continued on next page →
Quick Reference Handbook
ABNORMAL / EMERGENCY PROCEDURES REVISION 7
Page EA - 30 May 30/02
APU Inflight Operation - ELWS (Loadmeter) / ASC 420
Procedures, ctd… AFM 3-04-30
If Right Converter / Alternator is inoperative, complete Steps 13
thru 17.
13. Electric Master LEFT Power .................ON (MANUALLY SELECT)
14. Left AC Main LEFT................................ON (MANUALLY SELECT)
15. Right AC Main APU / EXT.....................ON (MANUALLY SELECT)
16. Left DC Main LEFT ...............................ON (MANUALLY SELECT)
17. Right DC Main TRU / EXT ....................ON (MANUALLY SELECT)
For either Converter / Alternator inoperative, continue:
18. Essential AC AUTO.................................................................... ON
19. Essential DC AUTO ................................................................... ON
20. Electrical Loadmeter (If Installed)............................................... ON
21. Electrical Loadmeter (If Installed) Green Arc ...................... CHECK
For airplanes SN 1430 and subs, and airplanes with ASC 420:
22. Windshield Heat......................................................AS REQUIRED
A. Left Converter Failed ......................................... RF/LS – OFF
B. Right Converter Failed ....................................... LF/RS – OFF
APU Operating Envelope (SN 1156 and subs; SN 1000 through
1155 with APU Loadmeter installed (or removed by ASC 420), SN
1430 and subs:
Starting: 15,000 ft and below / 250 KCAS maximum
Running: 35,000 ft and below / VMO/MMO maximum
Load: Sea Level to 30,000 ft: 100% (30 KVa)
30,000 to 35,000 ft: linear decrease to 67% (20 KVa)
END
Quick Reference Handbook
REVISION 7 ABNORMAL / EMERGENCY PROCEDURES
May 30/02 Page EA - 31
APU Alternator Failure AFM 3-04-40
An APU alternator failure (as indicated by lack of AUX PWR on
Electrical Master Panel and / or AUX AC POWER FAIL amber caution
message on CAS) will have no effect as long as both engine driven
Alternator / Converters continue to function. Backup power for
Alternator / Converter failures, however, has been lost.
1. Auxiliary Power Switch ..............................CYCLE OFF, THEN ON
If condition remains same:
2. Auxiliary Power Switch ............................................................. OFF
END
Display Unit Failure AFM 3-18-10
For SPZ 8000 equipped airplanes:
1. NORM - Normal presentation.
2. PFD XFER - Display of PFD info. on DU normally used as ND.
3. ND OFF - Blanks the ND.
EICAS switching options are:
1. NORM - Normal presentation.
2. TOP CMPT - "Compacted" display of both engine instrumentation
and flight crew alerting messages on DU 3.
3. BOT CMPT - "Compacted" display of both engine instrumentation
and flight crew alerting messages on DU 4.
For SPZ 8400 equipped airplanes:
PILOT DISPLAY (PFD and ND):
1. NORM - Normal presentation.
2. PFD - Display of PFD information on DU 2.
3. ENG / EICAS:
- With DU 3 failed, engine data is displayed on DU 2.
- With both DU 3 and 4 inop, compact display of engine
instruments and CAS messages is displayed on DU 2.
Continued on next page →
Quick Reference Handbook
ABNORMAL / EMERGENCY PROCEDURES REVISION 7
Page EA - 32 May 30/02
Display Unit Failure, ctd… AFM 3-18-10
COPILOT DISPLAY (PFD and ND):
1. NORM - Normal presentation.
2. PFD - Display of PFD information on DU 5.
3. CAS / EICAS:
- With DU 4 inop, normal CAS display is displayed on DU 5.
- With both DU 3 and 4 inop, compact display of engine
　
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