Instruments for monitoring engine operation are on the pilot left knee panel (Figure 225). Engine operating parame
ters are displayed on the engine instrument group which is a single WRA with LCD readouts. The display provides white readout segments and scales on a dark background and is red backlighted for night operations. Left and right engine com
pressor speed (rpm), EGT, and fuel flow are displayed on the EIG. Adjacent to the EIG are circular instruments for both engines’ oil pressure and nozzle position. Takeoff checks at military (MIL) thrust should display evenly matched tapes on corresponding vertical scale instruments and all pointers on the circular instruments should be at the 9−o’clock position.
Data on engine operating limits are provided in Chapter 4.
2.11.1 Engine RPM Indicator
The RPM indicators (Figure 225) have a range of 0 to 110 percent. The tape display steps in 5−percent increments and the upper segment flashes to indicate rpm increasing at more than 0.4 percent per second from 0 to 60−percent rpm.
The tape steps in 1−percent increments when greater than 60−percent rpm. Nominal indications are 62 to 78 percent at idle and 95 to 104 percent at military and above. At 107.7 percent and above, the affected engine’s exceeded portions of the chevrons will flash at a rate of 2 to 3 flashes per second.
At 20−percent rpm a horizontal segment will illuminate giving an indication of proper motoring speed to start the engine. There is an rpm reading for each engine.
Note
An overspeed condition in excess of 110 percent will result in momentary loss of rpm indication until N2 rpm falls below 110 ± 0.5 percent. EGT and fuel flow indicators will continue to function normally.
2.11.2 Exhaust Gas Temperature Indicator
The EGT indicators (Figure 225) provide a nonlinear vertical scale with a range of 0 to 1,100° C. The compressed lower portion has a range of 0 to 600° C. The expanded upper portion of the scale has a range of 600 to 1,100° C.
The display moves in 50° increments in the compressed portion and 10° increments in the expanded portion of the
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Figure 225.Engine Instruments (F110−GE−400)
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display. The normal indications are 350 to 650° C at idle and 780 to 935° C at MIL and above. Above 940° C, the affected engine’s exceeded portions of the chevrons flash. With a reading of 940° C, the stall warning light and the aural warning tone will be activated signifying an engine over
temperature condition. The tone is present for a maximum of 10 seconds unless the fault clears sooner. There is an EGT reading for each engine.
2.11.3 Fuel Flow Indicator
The fuel flow indicators have a nonlinear vertical scale, with a range of 0 to 17,000 pph. The expanded lower portion of the scale has a range of 0 to 5,000 pph. The compressed upper portion of the scale ranges from 5,000 to 17,000 pph.
The display moves in 100 pph increments in the expanded portion and in 500 pph increments in the compressed portion of the display. Normal indications on deck are 350 pph starting, 950 to 1,400 pph at idle, and approximately 10,100 pph at military and above. The fuel flow reading for each engine indicates only basic engine consumption and does not indicate AB fuel flow.
2.11.4 Engine Instrument Group BIT
A degraded mode of EIG operation is indicated if the BIT segment on the top left side of the EGT indicator illumi
nates. This means that either the primary or backup micro
processors, or the primary or backup power supply channels (internal to the EIG), have failed. An automatic switch to the operative microprocessor/channel takes place if a failure is detected. The instrument still monitors engine operation and accurately reflects rpm, EGT, and fuel flow. If the input processing circuit fails, the affected scale reading goes to zero.
2.11.5 Engine Instrument Group Self−Test
EIG self−test is selected by the MASTER TEST switch in INST. When master test is selected, all display segments illuminate, scales drive to maximum readings, and warning chevrons (stripes) flash for 5 seconds. BIT segment on the top left side of EGT indicator illuminates. L and R STALL warning acronyms appear on the HUD and MFD and stall warning/overtemp tone is present in pilot earphones for 10 seconds. After 5 seconds, all EIG scales decrease to pre
determined values of equal height that correspond to an EGT reading of 950 ± 10° C. If BIT segment remains illuminated, EIG has failed self−test and BIT remains illuminated until self−test is reinitiated. Total self−test time is 15 seconds. If master test is deactivated prior to this, EIG returns to normal mode after the 15−second test. If the MASTER TEST switch remains in INST for more than 15 seconds, the EIG retains equal height readings until master test is deselected.
2.11.6 Engine Oil Pressure Indicator
The engine oil pressure indicators display oil pressure from 0 to 100 psi. Normal oil pressure is 25 to 65 psi and increases in proportion to engine rpm within the pressure limit range. Stabilized idle oil pressure may be a minimum of 15 psi. The OIL PRESS caution light illuminates at 11 psi with decreasing oil pressure and extinguishes at 14 psi with increasing oil pressure. Maximum allowable oil pressure fluctuation is ±5 psi.
2.11.7 Exhaust Nozzle Position Indicator
The nozzle position indicators (Figure 225) have a range of 0 to 100−percent open. Normal indications (Figure 213) are l00 percent at idle with WOW and vary in flight: 3 to 10 percent at MIL thrust, 5 to 12 percent at MIN AB, and 60 to 90 percent at MAX AB.
Note
When operating engine in SEC mode, the nozzle position indicator is inoperative and indicates below zero. No nozzle position indication is available in SEC mode.
2.11.8 Engine Monitor Display Format
A display of engine parameters (Figure 226) can be selected on the MFD by pressing the pushbutton adjacent to the ENG legend on the own−aircraft menu. The display pre
sents N1 (fan speed), TBT (turbine blade temperature), FF/M (fuel flow main engine) or FF/T (fuel flow total, main engine and AB), and NP (exhaust nozzle position). FF/M scale indi
cates main engine fuel flow and is similar to the fuel flow displayed on the EIG. NP is the same as the nozzle position indicators. Numerical readouts below the N1 and TBT verti
cal scales digitize the indicated value. The TIME readout below the FF/M vertical scale indicates time in hours and minutes that fuel will last based on current consumption rates. Directly below the TIME readout, engine faults are displayed based on current engine operating conditions of both engines processed by FEMS. If more than three faults exist at the same time, the acronyms will continuously scroll upward. The ten possible acronyms and their definitions are:
1. L MACH # or R MACH # Mach number signal to designated engine has failed.
2. L LO THR or R LO THR Designated engine may be producing less than expected thrust.
3. L A/ICE or R A/ICE Designated engine anti−ice is on or anti−ice valve has failed opposite com
manded position.
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Figure 226.MFD Engine Monitor Display 4. L OIL LO or R OIL LO Designated engine oil
level is approximately two quarts low. Postflight, engine at idle.
5. L AUG or R AUG Designated AB control system has failed. AB is not available.
Refer to Chapter 12, WARNING/CAUTION/
ADVISORY LIGHTS/DISPLAY LEGENDS for the appropriate pilot/RIO response.
2.11.9 MFD Engine Caution Legends
In addition to the engine caution lights on the pilot CAUTION/ADVISORY panel, illumination of the READ MFD caution light indicates that one or more of the following caution legends on the upper left quadrant of the MFD is activated:
1. L N2 OSP or R N2 OSP Designated engine N2
overspeed condition.
2. L N1 OSP or R N1 OSP Designated engine N1
overspeed condition.
3. L TBT OT or R TBT OT Designated engine turbine blade overtemperature.
4. L FLMOUT or R FLMOUT Designated engine flameout.
5. L IGV SD or R IGV SD Designated engine inlet guide vane off schedule.
6. L STALL or R STALL Designated engine stall detected (also on HUD).
7. L FIRE or R FIRE Designated engine fire/
overheat condition in engine nacelle (also on HUD).
Refer to Chapter 12, WARNING/CAUTION/
ADVISORY LIGHTS/DISPLAY LEGENDS for the ap
propriate pilot/RIO response.
2.11.10 Engine Stall/Overtemperature Warning An engine stall detection circuit in FEMS monitors each engine. When a stall condition is detected, a L or R STALL warning legend is displayed on the HUD and MFD until the condition is cleared. In addition, an aural warning tone is activated through the pilot ICS for up to 10 seconds.
There is no pilot check of the FEMS engine stall detection system.
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Note
In SEC mode, FEMS and, therefore, the engine stall detection circuit, is inoperative. However, overtemperature warning is still available and will activate both the STALL warning legends and aural warning tone.
When an overtemperature condition occurs, the EGT display rises above 940° C, the warning chevrons begin to flash, and a signal from the EGT indicator activates the STALL warning legend and the aural tone. The overtempera
ture warning system is checked by the pilot during prestart as part of the MASTER TEST check in INST test.