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e.g., CRUISE, V/S, VPATH or PITCH HOLD mode.
3. Controls and Indications:
A. Circuit Breakers (CBs):
The engine thrust management system is protected by the following CBs:
Circuit Breaker Name: CB Panel: Location: Power Source:
L SEC LOCK P G-7 ESS DC Bus
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Circuit Breaker Name: CB Panel: Location: Power Source:
R SEC LOCK P H-7 ESS DC Bus
L T/REV CONTROL P I-7 ESS DC Bus
R T/REV CONTROL P J-7 ESS DC Bus
L T/R EMER STOW P K-7 or
L-7 (1) ESS DC Bus
R T/R EMER STOW P K-7 or
L-7 (1) ESS DC Bus
ENG SYNC P K-9 R MAIN DC
Bus
L EPR 115V CP A-9 ESS AC Bus
R EPR 115V CP B-9 ESS AC Bus
A/T SERVO #1 CPO C-9 L MAIN DC
A/T SERVO #2 CPO D-9 R MAIN DC
NOTE(S):
(1) Depending on effectivity.
B. Crew Alerting System (CAS) Messages:
The HP SYNC or LP SYNC annunciator lights are available on the Engine
Instruments Display page (EICAS). Illumination of either annunciator
indicates which tach generators (HP or LP) are currently being used.
Caution (Amber) Messages:
CAS Message: Cause or Meaning:
AT OFF Autothrottle disconnected
Advisory (Blue) Messages:
CAS Message: Cause or Meaning:
AT ENGAGE INHIBIT Attempt is made to engage autothrottle under any of the
following conditions:
• A/T disconnect button active
• A/T not armed on flight guidance control panel
• Both engines not running
• EPR below 1.17
• Isolation valve open
AT 1-2 FAIL Indicated autothrottle has failed, autothrottle will
disconnect.
AT NOT IN HOLD Airplane speed has exceeded 60 KCAS with autothrottle
engaged on takeoff and autothrottle servos are not in hold.
4. Limitations:
A. Flight Manual Limitations:
Engine synchronizer must be OFF for takeoff and landing.
OPERATING MANUAL
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Autothrottle Control
Figure 1
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-76-00
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Engine Sync Control Panel
Figure 2
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ENGINE INDICATION
2A-77-10: Engine Indication System
1. General:
The Engine Indication system generates data from the engines to provide the
flight crew with operating parameter indications and alerts classified as advisory,
caution or warning.
Refer to the system descriptions listed as follows during the study of this section:
• 2A-31-50: Central Display System
• Engine Instruments and Crew Alerting System (EICAS)
NOTE:
A description of the Engine Instruments and Crew
Alerting System (EICAS) with specific information on
displays of the Engine Parametric data and/or Engine
Discrete Status data 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. Subsystems, Units and Components:
The Engine Indication system is composed of the following subsystems:
• Engine Pressure Ratio (EPR) Indication System
• Engine Speed Indicating System
• Turbine Gas Temperature (TGT) Indication System
• Engine Vibration Monitor (EVM) Indication System
• Engine Fuel Indicating System
• Engine Oil Indication System
• Standby Engine Instruments (Digital) Indication System
2. Description of Subsystems, Units and Components:
A. Engine Pressure Ratio (EPR) Indication System:
Engine pressure ratio (EPR) indication is displayed on the center
instrument panel through the Engine Instrument and Crew Alerting System
(EICAS) and the standby engine instruments indicator. These indicators
provide an indication of engine power in the form of ratio of engine fan duct
total pressure to intake total pressure which is commonly known as EPR.
The EPR transmitter has a single pressure transducer to measure engine
fan duct pressure. Each EPR transmitter receives free stream total
pressure via an ARINC 429 data bus from each of the two air data
computers aboard the aircraft. It outputs EPR data, fan duct pressure, flight
line fault codes and shop fault codes on two ARINC 429 buses to the data
acquisition unit for EICAS EPR display and to the standby engine
instruments indicator for EPR digital readout.
B. Engine Speed Indicating System:
(1) Low Pressure (LP) Speed:
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-77-00
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