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2. More than 60 seconds after WoffW or a waveoff:
a. Floor Altitude - less than 90 feet AGL and greater than 200 KCAS.
b. Check Gear - less than 150 feet AGL, less than 200 KCAS, descending, and landing gear not
down.
c. Landing Sink Rate - less than 150 feet AGL, less than 200 KCAS, landing gear down, and an
excessive sink rate. The allowable sink schedule varies from a maximum of 2,040 fpm to a
minimum of 1,488 fpm based on altitude and GW.
d. Bank Angle - less than 150 feet AGL, less than 200 KCAS, greater than 45° AOB for one
second.
Below 150 feet AGL, GPWS does not directly account for the recovery
capabilities of the aircraft. Therefore, recovery may not be possible
following a warning under extreme flight conditions.
2.16.4.4 GPWS Warning Cues. GPWS provides distinctive, clear, unambiguous and directive visual
and aural cues to the aircrew for each potential CFIT condition.
2.16.4.4.1 GPWS HUD Recovery Arrow. The GPWS visual warning cue is a steady arrow located in
the center of the HUD. See figure 2-37. The HUD recovery arrow is always perpendicular to the horizon
and points in the direction of pull required for recovery. The HUD recovery cue is displayed
simultaneously with all voice warnings except CHECK GEAR. The HUD recovery arrow remains
displayed until GPWS calculates that a CFIT condition no longer exists.
2.16.4.4.2 GPWS Voice Commands. Refer to figure 2-38 for GPWS aural warning cues.
A1-F18EA-NFM-000
I-2-122 ORIGINAL
GPWS Warning
Condition Aural Cue Repetition Rate
Excessive bank angle ²ROLL LEFT (RIGHT), ROLL LEFT (RIGHT)² 2 seconds
Excessive take-off
sink rate
²POWER, POWER² 2 seconds
Excessive landing
sink rate
²POWER, POWER² 2 seconds
Gear-up landing ²CHECK GEAR² 8 seconds
ALDR or floor
altitude
²POWER, POWER² for airspeed <210 KCAS and
AOB £45°
²ROLL LEFT (RIGHT), ROLL LEFT (RIGHT)²
for AOB >45°
²PULL UP, PULL UP² for all other flight
conditions
2 seconds
2 seconds
2 seconds
Figure 2-38. GPWS Aural Cues
Figure 2-37. GPWS HUD Roll Warning Cues
A1-F18EA-NFM-000
I-2-123 ORIGINAL
Voice commands automatically transition to the appropriate command for the current stage of
recovery (e.g., ROLL OUT transitions to PULL UP when AOB becomes less than 45°). The voice
commands are terminated when the appropriate recovery maneuver is initiated (e.g., a PULL UP is
initiated within ½ g of the GPWS calculated target-g).
GPWS voice warnings are inhibited during RALT warnings or other voice aural warnings/cautions.
In addition to following the voice commands, additional pilot action may
be required to avoid an unrecoverable situation (e.g., aft stick with a
POWER call or power addition/subtraction with a PULL UP call.)
2.16.4.5 Areas of Limited CFIT Protection. Areas where CFIT protection is considered limited are
as follows:
1. In the COAST mode (5 to 120 seconds outside the valid RALT envelope).
2. Over rising terrain of greater than 2° slope (GPWS is inhibited to prevent nuisance warnings).
3. Within the GPWS LAT envelope where allowable pilot reaction times have been reduced (+/30°
AOB, 0 to 30° dive, 450 to 560 KCAS).
4. Below 150 feet AGL in the landing phase (less than 200 KCAS) where warnings are designed only
to prevent hard landings.
At certain high speed, high gross weight conditions, overriding the
g-limiter may be required for recovery from dives greater than 50° and
will likely be required for dives between 10 and 25°.
2.16.4.6 Areas of No CFIT Protection. Areas of no protection are as follows:
1. Loss of air data or RALT, INS, or MC1 failed or OFF.
2. Less than 6 seconds after WonW.
3. Less than 5 seconds or greater than 120 seconds outside the valid RALT envelope.
4. Transonic flight (0.95 to 1.04M) outside the valid RALT envelope.
5. For 1.5 seconds after a break X is displayed.
6. After a waveoff until exceeding 1,000 fpm for five seconds.
7. Dives greater than 50° after 2 minutes above 5,000 feet AGL.
A1-F18EA-NFM-000
I-2-124 ORIGINAL
2.17 INSTRUMENTS
Refer to foldout section for cockpit instrument panel illustration. For instruments that are an
integral part of an aircraft system, refer to that system description in this section.
2.17.1 Standby Attitude Reference Indicator. The standby attitude reference indicator is a selfcontained
electrically driven gyro-horizon type instrument. It is normally powered by the right 115
volts ac bus. If this power fails it is automatically powered by an inverter operating off the essential 28
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NATOPS Flight Manual 飞行手册 1(95)
