曝光台 注意防骗
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minimum during a temperature decrease.
NAVAIR 014=14AAQ-1
2.11 ENGINE INSTRUMENTS
Instruments for monitoring engine operation are on
the pilot left knee panel (Figure 2-25). Engine operating
parametersa red isplayedo n the engine instrumentg roup
which is a single WRA with LCD readouts.T he display
provides white readout segments and scales on a dark
background and is red backlighted for night operations.
Left and right engine compressor speed(rpm), EGT, and
FF are displayed on the EIG. Adjacent to the EIG are
circular instruments for both engine’s 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 2-25) have a range of 0 to 110 percent. The
tape display steps in 5-percent increments and the upper
segment flashes to indicate ‘pm increasing at more than
0.4 percentp er second from 0- 106 0-percent‘p m. The
tape steps in l-percent increments when greater than
60-percent ‘pm. 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 overspeedc ondition in excesso f 110p ercent
will result in momentary loss of rpm
indication until Nz rpm falls below 110 M.5
percent. EGT and FF indicators will continue
to function normally.
2.11.2 Exhaust Gas Temperature Indicator. The
EGT indicators (Figure 2-25) 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 display. Tbe normal indications are 350 to
650 “C at idle and 780 to 935 OC at MIL and above.
Above 940 “C, the affectede ngine(s)e xceededp ortions
ofthe chevrons flash. With a reading of 940 “C, the stall
warning light and the aural warning tone will be activated
signifying an engine overtemperature condition.
The tone is present for a maximum of 10 secondsunless
the fault clears sooner. There is an EGT reading for each
engine.
2-35 ORIGINAL
NAVAIR 0%F14AAD-1
Figure 2-25. Engine Instruments (Fl IO-GE-400)
ORIGINAL 2.36
2.11.3 Fuel Flow indicator. TheFFindicatorshave
a nonlinear vertical scale, with a range of 0 to 17,000
pph. The expandedlo wer portion ofthe scaleh asa 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
onthetopleftsideoftheEGTindicatorilluminates. This
means that either the primary or backup microprocessors,
or the primary or backup power supply channels
(internal to the EIG), have failed. An automatic switch
to the operative micropmcessorf takes place if a
failure is detected. The instrument still monitors engine
operation and accurately reflects rpm, EGT, and FF. 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 testi s selected,a ll display segments
illuminate, scales drive to maximum readings, and
warning chevrons (stripes) flash for 5 seconds. BIT seg
ment 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 earphonesfo r 10s econds.A fter 5 seconds,a ll EIG
scalesd ecreaseto predeterminedv alues of equal height
that correspond to an EGT reading of 950 +lO “C. If
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F-14D 飞行手册 Flight Manual 1(74)
