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5. Beacon Switch ..................................................................................................................... ON
6. APU Air/External Air ......................................................ON/PRESSURE 25 PSI MINIMUM
NOTE: Normal air pressure from APU can vary between 25 to 50 psi. During starting cycle,
APU air pressure drops, but should not fall below approximately 20 psi.
7. Fuel Boost Pumps (One Each Side)........................................................ ON/MESSAGE OUT
8. Electrical Power...................................................................................... CHECK (35% MAX)
NOTE: If using APU, limit APU alternator load (AC AUX PWR) to 35% during Main Engine
Starts. At high elevation airports and/or in high ambient temperature conditions, limit
AUX AC load to 30%.
9. Engine Start Master ............................................................................................................. ON
10. Engine Start Switch ....................................................................................................... PRESS
CAUTION: CONTINUED USE OF THE STARTER IS LIMITED TO THREE (3) CRANK
CYCLES, WITH MAXIMUM OF THIRTY (30) SECONDS PER CYCLE.
DELAY THREE (3) MINUTES BETWEEN START ATTEMPTS. AFTER
THREE (3) CYCLES, DELAY USE OF STARTER FOR AT LEAST FIFTEEN
(15) MINUTES.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 2
NORMAL
PROCEDURES
FAA APPROVED 2-23
30 May 2002
11. Start Valve and Ignition ....................................................................................................... ON
NOTE: If IGN mnemonic is not displayed on EICAS, start may be salvaged by selecting AIR
START IGN-ON prior to opening HP Fuel Cock:
12. Positive LP RPM ..........................................................................................................CHECK
13. HP Fuel Cock.................................................................................OPEN (15% HP Minimum)
NOTE: In high tail wind conditions, direction of rotation of LP may initially be reversed and, if
so, the HP fuel cock should not be selected to OPEN until HP is stabilized. This
ensures that LP rotation is positive. Starts with tailwinds of up to 25 knots have been
demonstrated.
NOTE: Ignition should occur within ten (10) seconds after selecting HP Cock to OPEN.
14. Start Valve and Ignition ......................................................................................................OFF
NOTE: Start valve should close by 44.5% HP RPM. For SPZ 8000 equipped airplanes the SVO
mnemonic changes from blue to amber above 42% (for SPZ 8400 equipped airplanes
44.5%) and starts flashing. Check at ground idle HP RPM, and if not closed (SVO still
illuminated); execute START VALVE FAILURE TO CLOSE abnormal checklist.
15. TGT................................................................................................. MONITOR (700°C MAX)
NOTE: During starting, TGT should not exceed 700°C. If there is any evidence of rapid rising
TGT and it is anticipated that 700°C will be exceeded, select HP Cock to SHUT
immediately. If TGT has not exceeded 700°C, second start may be attempted. If, under
normal starting conditions, TGT exceeds 650°C, this will indicate a fault in the engine
or starting systems.
16. Engine RPM..........................................................................CHECK (46.6% HP MINIMUM)
17. Oil Pressure and Temperature.......................................................................................CHECK
18. EVM. ............................................................................................................................CHECK
NOTE: The EVM system is designed to monitor engine vibrations at idle and above. During
start, the EVM system may occasionally display momentary EVM values above the
ALERT level (0.60) which in turn causes EVM digits to an amber display momentarily
on the CAS (for SPZ 8400 equipped airplanes). This normally occurs on the first start
of the day.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 2
NORMAL
PROCEDURES
2-24 FAA APPROVED
31 May 2000
19. Single Rudder Limit Message.............................................................................................. ON
(right engine only running)
20. Hydraulic Pressure .................................................................................................. CHECKED
21. Flight Data Recorder Fail Message..................................................................... CHECK OUT
22. Second Engine Start............................................................................. Repeat Steps 10 thru 18
23. Single Rudder Limit Message............................................................................................OUT
　
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