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2.68 TURN RATE INDICATING SYSTEM.
A 4-minute turn rate (turn and slip) indicator is at the bottom center of each VSI (Figure 2-8). The pilot’s and copilot’s indicators operate independent of each other through TURN RATE switches on the MODE SEL pan-els. Each system consists of a rate gyro, a turn slip indicator and a select switch. The VSI contains a moving turn rate needle and a .xed turn rate scale for indicating rate and direction of turn. During straight .ight the needle is posi-tioned at the center of the scale. When the helicopter turns, the rate-of-turn signal from the rate gyroscope de.ects the needle in the proper direction to indicate the turn. Amount of de.ection is proportional to the rate-of-turn. A one-needle width de.ection represents a turn of 1.5° per second. The VSI also contains a slip indicator that shows uncoor-dinated turns. If a power failure or unbalance occurs in the pilot’s or copilot’s rate gyroscope, the associated VSI sig-nal will be lost. To restore rate-of-turn information to the indicator, the pilot or copilot will press the TURN RATE switch on his MODE SEL panel so that ALTR appears in the switch window. This applies alternate rate gyroscope signals from the operating gyroscope to the indicator. Power to operate the pilot’s turn rate system is provided from the dc essential bus through a circuit breaker, marked PILOT TURN DETR. The copilot’s system is powered from the No. 1 dc primary bus through a circuit breaker, marked CPLT TURN RATE GYRO. Refer to Chapter 3 for a description of the TURN RATE select switch.
2.69 AIRSPEED INDICATOR.
Two airspeed indicators (Figure 2-8), are installed on the instrument panel, one each for the pilot and copilot. The indicators are differential pressure instruments, measuring the difference between impact pressure and static pressure. Instrument range markings and limitations are contained in Chapter 5, Section II, System Limits.
2.70 ALTIMETER/ENCODER AAU-32A.
Two altimeters are installed on the instrument panel (Figures 2-8 and 2-20). The altimeter encoder functions as a barometric altimeter for the pilot and a barometric alti-tude sensor for the AN/APX-100 transponder in mode C. The copilot’s functions only as a barometric altimeter. The system is equipped with a continuously operating vibrator to improve altitude measuring accuracy. The altimeter’s op-erating range is from -1000 feet to 50,000 feet. The face of the instrument has a marked scale from zero to nine in 50-foot units. The operating indicators and controls are a 100-foot pointer, 100-foot drum, 1,000-foot drum, 10,000-foot drum, barometric pressure set knob, barometric pres-sure scale window and warning .ag. The warning .ag is only used in conjunction with the encoder. A counter win-dow next to the sweep hand contains the three digital drums
Change 2 2-67
ENCODER WARNING 100.FOOT FLAG INDICATOR ALTITUDE NEEDLE
1000.FOOT
ALTITUDE
COUNTER
100.FOOT
ALTITUDE
COUNTER
BAROMETER PRESSUREBAROMETRIC
SCALE
SCALE SET KNOB AA0520
SA
that rotate to indicate the altitude of the helicopter. Another window in the upper left section of the instrument face indicates the normal code operation. When the system fails to transmit signals to the transponder, a .ag marked CODE OFF will appear in the window. A window on the lower right section of the instrument face indicates barometric pressure setting. The barometric pressure set knob is on the lower left corner of the indicator bezel. Power to operate the encoder system is provided by the No. 2 dc primary bus through a circuit breaker, marked PILOT ALTM.
2.71 VERTICAL SPEED INDICATOR.
Two indicators are installed, one each in front of the pilot and copilot (Figure 2-8), to indicate rate of climb or descent.
2.72 STANDBY MAGNETIC COMPASS.
A magnetic compass is installed above the instrument panel on the right center windshield frame (Figure 2-4). The compass is used as a standby instrument for heading references. A compass correction card with deviation errors is installed on the right side of the upper console.
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