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NMI O-2048 NONE xX)(x.X RT to LT
Command course 1 DEG I l-360 1 NONE I XXX I RTtoLT
Notes:
(1) If a sign is not input, the number is assumed positive,
(2) Prompt underscores disappear as numerics are input. Pressing ‘BKSP’ will delete a keyed-in numeric
and the underscore will reappear. Continued backspacing will delete inputs in the reverse order in which
they were input. If the prompt is a single underscore, it disappears upon the first keyed entry. When backspacing,
it will reappear when the first keyed entry has been deleted.
(3) Qualifiers ‘s’. ‘N’, ‘E’. ‘w’, ‘+’ and ‘-’ can be keyed in before, after or during keying of numeric data.
‘BKSP’ will not delete these symbols; however, they can be overwritten. The last keyed symbol will be implemented.
Depression of ‘CLR’ will also reset the total scratchpad.
(4) Trailing zeroes for minutes and seconds will be assumed if not entered from keypad.
(5) ‘b’ implies blank or space: ‘Q’ implies qualifier (S, N, E, W, +, -).
Figure 2-122. Data Entry Parameters
2-235 ORIGINAL
NAVAIR Ol-F14AAD-1
When the radar altimeter drops out of the track mode,
anO FF flag appearsa ndt he pointer is hidden by a mask.
The altimeter remains inoperative until a return signal is
received, at which time the altimeter will again indicate
actual altitude above terrain.
Reliable system operation in the altitude range of 0
to 5,000 feet permits close altitude control at minimum
altitudes. The system will operate normally in bank
angles up to 45O and in climb or dives except when the
reflected signal is too weak.
The system includes a height indicator (altimeter), a
test light on the indicator, a low-altitude warning tone,
a radar receiver-transmitter under the forward cockpit,
andt wo antennas(t ransmit andr eceive)o ne one achs ide
of the IR fairing, in the aircraft skin. During descent,t he
warning tone is heard momentarily when the aircraft
passes through the altitude set on the limit index. When
the aircraft is below this altitude, the red low-altitude
warning light on the indicator stays on.
Note
If radar altitude is unreliable, only the OFF
flag is present.
The radar altimeter receives power from the ac essential
bus No. 1 through the RADAR ALTM circuit
breaker (4B3) and from dc essential bus No. 1 through
the ALT LOW WARN circuit breaker (7B6). The radar
altimeter has a minimum warmup time of 3 minutes.
During this time, failure indications and erroneous readouts
should be disregarded.
2.35.4.1 Radar Altimeter. The radar altimeter (FO-
12) on the pilot instrument panel has the only controls
for the system. The indicator displays radar altitude
above the Earth’s surface on a single-turn dial that is
calibrated from 0 to 5,000 feet in decreasing scale to
provide greater definition at lower altitudes. The control
lmob in the lower right comer of the indicator is a combination
power switch, self-test switch, and positioning
control for the low-altitude limit bug.
2.35.4.2 Altimeter BIT. Depressing and holding
the control knob energizes the self-test circuitry; the
green test light illuminates, the indicator reads 100
+lO feet, and the HUD altitude scale reads approximately
100 feet. If the indicator passes below the altimeter
limit bug setting, the aural and visual warnings
are triggered. Normal operation is resumed by releasing
the control knob.
2.35.4.3 Low-Altitude Aural Warning. A lowaltitude
aural warning alarm provides a 1000 Ha tone,
modulated at two pulses per second, lasting for 5 seconds.
The tone is available to both crewmembers when
the airwail descends below the altitude set on the lowaltitude
limit bug.
2.35.5 Vertical Velocity indicator. The wrtical velocity
indicator on the left side of the pilot and RIO
instmment panel is a sealed case connected to a static
pressure line through a calibrated leak. It’indicates rate
ofclimb or descent.S uddeno r abruptc hangesin attitude
may cause erroneous indications because of the sudden
change of airflow over the static probe.
2.35.6 Standby Compass. A conventional standby
compass is above the pilot instrument panel. It is a semifloat-
type compasss uspendedin compassf luid.
2.35.7 Clock. A mechanical 8&y clock is on the instrument
panel in each cockpit. It incorporatesa l-hour
elapsed-time capability. A winding and setting selector
is in the lower left comer of the instrument face. The
knob is turned in a clockwise direction to wind the clock
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F-14D 飞行手册 Flight Manual 1(172)
