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diverter valve (Item 31).
HIGH All cabin airflow is directed to the windshield defog outlets, providing maximum defog
capability for conditions of very high aircraft descent rates and high humidity. In the
HIGH position, the ECS controller increases the temperature range controlled by the
CABIN TEMP knob.
NORM The NORM range provides a near linear division of air between the cockpit louvers and
the defog outlets. In the NORM range, airflow to the defog outlets is sufficient to provide
windshield defog for most conditions.
LOW All cabin airflow is directed to the cockpit louvers and the foot heater, providing maximum
cockpit cooling capability.
2.12.8 Cabin Pressurization. The cabin is pressurized using airflow from the cockpit heating and
cooling system. Cabin pressurization is controlled by the CABIN PRESS switch and automatic
operation of the cabin pressure regulator. Cabin pressure altitude is displayed on a cabin pressure
altimeter.
Cabin pressure is controlled by the cabin pressure regulator which regulates exit airflow to maintain
a pressure/altitude schedule. The cabin is unpressurized from sea level to an aircraft altitude of 8,000
feet. Between 8,000 and 24,500 feet aircraft altitude, cabin pressure is maintained at a constant 8,000
feet. Above 24,500 feet, cabin pressure decreases slowly to approximately 14,500 feet at 35,000 feet
aircraft altitude and 20,000 feet at 50,000 feet aircraft altitude. A rule of thumb for cabin altitude above
24,500 feet aircraft altitude is aircraft altitude x 0.4.
A cabin safety and dump valve is incorporated to limit cabin pressure if the pressure regulator fails.
When the CABIN PRESS switch is placed to DUMP or RAM/DUMP, the cabin safety and dump valve
opens to release pressure to the cabin pressure regulator, reducing cabin pressure to ambient.
A slowly increasing cabin pressure altimeter may be the only warning of
a gradual loss of cabin pressurization.
2.12.8.1 CABIN PRESS Switch. The CABIN PRESS switch, located on the ECS panel on the right
console, is used to control cabin pressurization. The switch is lever-locked in the NORM position.
NORM Cabin pressurization is automatically controlled to the cabin pressure schedule by the
cabin pressure regulator.
A1-F18EA-NFM-000
I-2-96 ORIGINAL
DUMP Dumps cabin pressurization. Normal ECS airflow to the cockpit and the avionics is not
affected.
RAM/
DUMP
Dumps cabin pressurization. Terminates all ECS airflow to the cockpit by closing the
cabin flow valve (Item 9). Cockpit airflow is provided by the RAM air scoop. Avionics
airflow is provided by a simplified control scheme (a full open avionics flow valve (Item
8) and a modulated ECS flow modulator valve (Item 4)).
2.12.8.2 Cabin Pressure Altimeter. A cabin pressure altimeter, located on the center console in the
front cockpit and the lower left instrument panel in the rear cockpit, displays the current cabin
pressure altitude.
2.12.9 Windshield Anti-ice and Rain Removal. The windshield anti-ice and rain removal systems use
the same air nozzle to direct warm air to the external surface of the windshield to improve forward
visibility in icing/raining conditions. Warm airflow is provided by mixing output from the primary heat
exchanger with engine bleed air. The windshield area affected is approximately 20 inches to the left
and 9 inches to the right of centerline at design eye level and below. System operation is controlled by
the WINDSHIELD switch.
2.12.9.1 WINDSHIELD Switch. The WINDSHIELD switch, located on the right console outboard of
the ECS panel, is used to select either windshield anti-ice or rain removal. The switch is lever-locked
to the OFF position.
ANTI
ICE
Delivers a high flow rate of 290 ±20°F air to the external surface of the windshield.
OFF Terminates anti-ice/rain removal airflow.
RAIN Delivers a low flow rate of 270 ±20°F air to the external surface of the windshield.
2.12.10 Anti-g System. The anti-g system delivers air pressure to the g-suit proportional to sensed
load factor. A button in the anti-g valve allows the aircrew to test system operation by manually
inflating the anti-g suit. The system incorporates a pressure relief valve to prevent over-pressurization.
A1-F18EA-NFM-000
I-2-97 ORIGINAL
2.12.11 ECS RESET and AV COOL Switch.
2.12.11.1 ECS RESET. If the ECS is DEGD, selecting the ECS RESET option from the BIT/
HYDRO-MECH display commands an ECS controller software reset and may restore normal
functionality following a transient fault.
Resetting the ECS controller at mid to high power settings may cause
uncomfortable cockpit pressure surges and ear pain.
Resetting the ECS controller results in the loss of system overtemperature
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本文链接地址：
NATOPS Flight Manual 飞行手册 1(81)
