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volts dc bus. An OFF flag appears if both power sources fail or the gyro is caged. During caging the gyro
initially cages to 4° pitch and 0° roll regardless of aircraft attitude. After 3 to 5 minutes, the indicator
reads 0° pitch and 0° roll. Power should be applied for at least 1 minute before caging. The indicator
displays roll through 360°. Pitch display is limited by mechanical stops at approximately 90° climb and
80° dive. As the aircraft reaches either stop, the gyro tumbles 180° in roll. A needle and ball are at the
bottom of the instrument. A one needle width turn is 90° per minute.
2.17.2 Standby Airspeed Indicator. The standby airspeed indicator displays airspeed from 60 to 850
KIAS. It operates directly from left pitot and static pressure.
2.17.3 Standby Altimeter. The standby altimeter is a counter-pointer type. The counter drum
indicates altitude in thousands of feet from 00 to 99. The long pointer indicates altitude in 50-foot
increments with one full revolution each 1,000 feet. A knob and window permit setting the altimeter
to the desired barometric setting. This setting is also used by the flight control computers. The standby
altimeter operates directly from left static pressure.
2.17.4 Standby Rate of Climb Indicator. The standby rate of climb indicator displays vertical speed
on a scale from 0 to ±6,000 fpm and operates directly from left static pressure.
2.17.5 Standby Magnetic Compass. A conventional aircraft magnetic compass is mounted on the
right windshield arch.
2.17.6 Angle Of Attack Indexer. The angle of attack indexer is mounted to the left of the HUD. It
displays approach angle of attack (AOA) with lighted symbols; corresponding AOA indications are
shown on the HUD (see figure 2-39). The indexer operates with the landing gear down and weight off
the gear. The lighted symbol(s) flash if the arresting hook is up and the hook bypass switch, on the left
vertical panel, is in CARRIER. The symbols will not flash with the arresting hook up and the hook
bypass switch in FIELD. The switch is solenoid held to FIELD and automatically goes to CARRIER
when the arresting hook is lowered or aircraft power is removed. The AOA indexer knob on the HUD
controls dimming of the symbols. All symbols light when the lights test switch on the interior lights
control panel is held to TEST.
2.18 AVIONICS SUBSYSTEM
The avionics subsystem combines the integration and automation needed for operability with the
redundancy required to ensure flight safety and mission success. Key features of the system include
highly integrated controls and displays, inertial navigation set with carrier alignment capability, and
extensive built in test capability. The avionics subsystems operate under the control of two mission
computers with primary data transfer between the mission computers and the other avionics
equipment via the mux buses.
2.18.1 Mission Computer System. The mission computer system consists of two digital computers
(MC1 and MC2) which are high speed, stored program, programmable, general purpose computers
with core memory. Computer de-selection is made with the MC switch on the MC/HYD ISOL panel.
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I-2-125 ORIGINAL
The two mission computers interconnect with the primary avionics equipment on the avionics
multiplex (mux) buses. MC1, referred to as the navigation computer, performs processing for
navigation, control/display management, aircraft built in test (BIT), status monitoring operations and
backup for MC 2. MC2, referred to as the weapon delivery computer, performs processing for air-to-air
combat, air-to-ground attack, and tactical control/display.
There are six avionics mux bus channels with redundant paths (X and Y) for each channel.
The mission computer:
1. Computes and controls the data sent to the cockpit displays,
2. Computes missile launch and weapon release commands,
3. Provides mode control and options for various avionics systems,
4. Generates BIT initiate signals to and equipment operational status from various avionics
systems.
The computers receive inputs for navigational data and steering command computations from the
inertial navigation system, electronic flight control system, multipurpose display group, TACAN, and
Figure 2-39. Angle of Attack Indexer
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I-2-126 ORIGINAL
backup attitude and the navigation system. The computers control display symbology and information
presented to the pilot by the multipurpose display group.
2.18.1.1 MC Switch. The MC switch, located on the outboard edge of the aft left console, is used to
manually turn OFF either of the two mission computers, MC1 or MC2.
1 OFF Removes power to MC1.
NORM Both MC1 and MC2 are powered with ac electrical power available.
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本文链接地址：
NATOPS Flight Manual 飞行手册 1(96)
