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F. Fuel Cooled Oil Cooler:
(See Figure 3.)
Oil from the pressure pump passes into the rear of the oil cooler. It flows
around the outside of the tubes and is directed by the baffle plates to pass
numerous times through the matrix assembly. On reaching the forward end
of the cooler, the oil passes to the pressure oil filter for distribution
throughout the system. The fuel, which flows through the tubes, is of a
moderately low temperature and extracts a proportion of the heat from the
oil.
At low temperatures, the viscosity of the oil is high, restricting its flow
around the tubes. When the pressure drop reaches 50 PSI, the bypass
valve opens to allow oil to pass directly to the outlet connection. This
ensures adequate oil supply for engine lubrication.
G. Engine Oil Remote Replenishing System:
(See Figure 1.)
The engine oil can be replenished from a self-contained engine oil
reservoir located in the aft equipment bay on the left side. The system
consists of a 16 pint reservoir, oil pump, left and right solenoid valves and
associated plumbing.
The replenishing pump receives electrical power from the 28V DC
essential bus through the ENGINE OILER circuit breaker. The pump is also
controlled by the tail compartment door switch, an engine oiler switch
located near the reservoir and an engine oiler switch located on each
engine. The switches on each engine are spring-loaded to OFF. When
selected ON, each switch activates the replenishing pump and opens the
solenoid valve for its respective engine.
OPERATING MANUAL
2A-79-00 PRODUCTION AIRCRAFT SYSTEMS
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May 31/01
Revision 4
3. Controls and Indications:
NOTE:
A detailed description of the Engine Instruments and
Crew Alerting System (EICAS) can be found in Section
5 of Honeywell’s SPZ-8000 (or SPZ-8400) Digital
Automatic Flight Control System Pilot’s Manual for the
Gulfstream IV.
A. Circuit Breakers (CBs):
The engine oil system is protected by the following circuit breakers:
Circuit Breaker Name: CB Panel: Location: Power Source:
ENGINE OILER P L-9 or G-10 (1) ESS DC Bus
L ENG OIL PRESS CP A-12 ESS AC Bus
R ENG OIL PRESS CP B-12 ESS AC Bus
NOTE(S):
(1) Depending on effectivity.
B. Crew Alerting System (CAS) Messages:
Warning (Red) Messages:
CAS Message: SWLP Indication: Cause or Meaning:
L-R OIL PRESS LOW L-R OIL PRESS Indicated oil pressure below 16 PSI
Advisory (Blue) Messages:
CAS Message: Cause or Meaning
L-R OIL FILT BPASS Engine oil filter has clogged
4. Limitations:
A. Flight Manual Limitations:
(1) Oil Inlet Temperature:
• Maximum: 105°C (Oil temperature up to 120°C for maximum
of fifteen (15) minutes is permissible)
• Minimum for Starting: -40°C
• Minimum for opening power lever: -30°C
NOTE:
External heating will be required to raise oil
temperature to -40°C for cold weather starting. If oil
temperature is less than -30°C, the engine should be
idled until at least -30°C temperature is reached.
(2) Oil Pressure:
• Minimum at Idle: 16 PSI
• Minimum acceptable for takeoff (at takeoff power): 30 PSI
Minimum to complete flight:
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-79-00
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May 31/01
Revision 4
• At maximum continuous (97.5% HP): 25 PSI
• 92% HP RPM: 22 PSI
• 84% HP RPM: 19 PSI
• 76% HP RPM or lower: 16 PSI
Engine Oil Remote Replenishing System Simplified Diagram
Figure 1
OPERATING MANUAL
2A-79-00 PRODUCTION AIRCRAFT SYSTEMS
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Engine Oil Tank and Associated Components
Figure 2
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-79-00
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Fuel Cooled Oil Cooler
Figure 3
OPERATING MANUAL
2A-79-00 PRODUCTION AIRCRAFT SYSTEMS
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Oil Pump Assembly
Figure 4
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OPERATING MANUAL
THIS PAGE IS INTENTIONALLY LEFT BLANK.
2A-79-00 PRODUCTION AIRCRAFT SYSTEMS
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ENGINE STARTING
2A-80-10: Engine Starting System
1. General:
A. Description:
The engine starting system can receive pneumatic starting air from any of
the following sources:
• Auxiliary Power Unit (APU)
• An already running engine (crossbleed)
• An external air source (i.e., engine start cart)
Engine starting can be accomplished on the ground (ground starts) or in
　
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