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g-bucket,² the g-limiter reduces the positive command g-limit to a value below Nz REF. This reduction
is 1.0g above 20,000 ft and 1.7g below 15,000 ft, but at no time is the symmetrical command limit
reduced below +4.5g. For instance, if Nz REF is +7.5 g (at or below 42,097 lb GW), the g-limiter only
allows +5.8 g to be commanded while ²in the g-bucket.² FSR limits are also reduced in the g-bucket to
80% of (Nz REF minus the reduction).
The Mach numbers at which the g-bucket is entered are dependent on external stores configuration.
The g-bucket is entered at 0.905 Mach accelerating (with wing tanks or A/G stores) or at 0.941M
accelerating (clean or with A/A stores). Regardless of stores loading, the g-bucket is entered at 1.045M
decelerating and is exited at 0.875M decelerating. So, if the pilot wants to have maximum-g available
during a turning maneuver (e.g., the merge), Mach in the HUD should be 0.90 or less (with wing tanks
or A/G stores) or 0.93 or less (clean or with A/A stores) to keep out of the g-bucket.
2.9.7.5 G-Limiter Override. A g-limiter override feature can be enabled to allow a 33% increase in
the command g-limit for emergency use (allows a 10g command at 7.5g NzREF). G-limiter override is
selected by momentarily pressing the paddle switch when the stick is near the full aft limit. When
g-limiter override is selected, a G-LIM OVRD caution is set along with a 927 MSP code. Override is not
disengaged until the stick is returned to near the neutral position.
2.9.7.6 Roll Rate Limiting. Roll rate limiting is enabled in R CAS when external wing tanks or A/G
stores are mounted on wing pylons (hooks closed). If any A/G store indicates HUNG, a R-LIM OFF
caution is set, and roll rate limiting is removed. In this case, higher than normal roll rates are possible
and may exceed the structural limitations of the airframe/pylons if pilot-imposed lateral stick limits
are not applied.
2.9.8 Air Data Function. The air data function is provided by the FCCs and not a separate computer.
The FCCs receive input from pitot-static sensors, total temperature sensors, the angle of attack probes,
the standby altimeter barometric setting, and the mission computers. The FCC air data function
applies appropriate source error corrections to the air data sensor inputs and calculates accurate true
altitude, airspeed, Mach number, AOA, and outside air temperature (OAT). Computed air data is used
internally by the FCC control augmentation system (CAS) and is also supplied to the MCs for IFF
altitude reporting, weapon system calculations, and landing gear wheels warning; to the FADECs for
engine control; and to the ECS controller for ECS scheduling and fuel tank pressurization and vent.
A1-F18EA-NFM-000
I-2-67 ORIGINAL
2.9.8.1 Pitot-Static/Total Temperature Probes. Two combined pitot-static/total temperature
probes are mounted on the left and right forward fuselage. Each probe contains one pitot pressure
source, two static pressure sources, and a total temperature sensor. One of the static pressure sources
from each probe is connected together and pneumatically averaged. This average static source is
provided to the left and right pressure transmitter sets along with the corresponding pitot pressure
source. The left pressure transmitter set provides pitot-static input to FCC CH 1 and 4 with the right
providing input to FCC CH 2 and 3. The FCC air data function corrects sensed pitot and static
pressures for position error to provide accurate true air data for FCC calculations, MC calculations, and
display in the HUD. The pitot pressure source and the second static pressure source from the left probe
are used to drive the standby flight instruments (altitude, airspeed, and VSI). The second static
pressure source from the right probe is unused.
Each pitot-static probe also contains an integral total temperature sensor. Each total temperature
sensor converts sensed temperature to an electrical signal. The output of the left total temperature
sensor is sent to FCC CH 2, with the right to FCC CH 4. The FCCs use total temperature to calculate
OAT. Each pitot-static/total temperature probe is electrically heated to prevent icing.
2.9.8.2 AOA Probes. Two AOA probes are mounted on the left and right forward fuselage. Each
probe mechanically measures local AOA by aligning with the airstream. An integral AOA transmitter
set converts the mechanical input to a 2-channel electrical signal which is sent to the FCCs. The left
AOA transmitter set provides input to FCC CH 1 and 4 with the right to FCC CH 2 and 3. The FCC
air data function corrects the sensed local AOA to a true AOA and provides the output to the MC for
display on the HUD. FCS CH 4 supplies the AOA signal which drives the AOA indexer lights and the
　
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本文鏈接地址：NATOPS Flight Manual 飛行手冊 1(65)