Standby Data - Altitude and Airspeed - Electrical Circuit
 Figure 003

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 Standby Data - Altitude and Airspeed - Electrical Circuit
 Figure 003A

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 Standby Data - Altitude and Airspeed - Data Indication
 Figure 004

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 Standby Data - Altitude and Airspeed - Data Indication
 Figure 004A

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 -the baro correction (2) is displayed on a counter graduated in hecto Pascal
 -a knob (1) located at the L corner of the indicator enables the display of the reference baro correction in the range of 750 to 1050 hPa.
 -four manually adjustable white bugs (3) are provided for manual altitude setting. To improve accuracy, 28VDC supplies the internal vibrator of the standby altimeter through a landing gear relay. In straight and level flight, with the internal vibrator operating, the standby altimeter gives the following accuracy: plus or minus 20 ft. at sea level plus or minus 40 ft. at 6000 ft. plus or minus 80 ft. at 10,000 ft. plus or minus 130 ft. at 20,000 ft. plus or minus 205 ft. at 35,000 ft.
 NOTE : On the ground, with the internal vibrator not supplied, the above
____ figures may be plus or minus 300ft. Integral lighting supplied with external 5VAC is provided to illuminate the presentation.
 B. Standby Airspeed Indicator The standby airspeed indicator contains a capsule-operated mechanism which measures the pitot/static pressure differential from the standby air data system and provides airspeed indication in terms of knots with the following accuracy:
 -
plus or minus 3 kts for VC < 200 kts

 -
plus or minus 4 kts for 200 kts < VC < 300 kts

 -
plus or minus 5 kts for 300 kts < VC < 450 kts.
 The airspeed indication is displayed by means of:

 -a pointer (9) which moves on a dial (7) graduated between 60 kts and 450 kts. The scale is linear from 60 kts to 250 kts with 5 kts graduations and from 250 kts to 450 kts with 10 kts graduations.
 -four manually adjustable white bugs (8) provided for manual speed
 setting. Integral lighting supplied with external 5VAC is provided to illuminate the presentation.

R **ON A/C 001-049, 051-099, 101-105,
 C. Metric Altimeter The metric altimeter is supplied with static pressure by the standby air data system to indicate the barometric altitude of the aircraft in meters with the following accuracy: plus or minus 15 m at the sea level plus or minus 20 m at 2000 m
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 -
a pointer (10) performing one revolution of the dial for 1000 meters.

 -
a display counter (11) made up of two drums displaying respectively the tens of thousands, and the thousands of meters.

 -
the altitude dial (12) is calibrated from 0 to 1000 meters with 50 meters graduations.

 -
the baro correction (14) is displayed on a counter graduated in hecto Pascal.

 -a knob (13) located at the L corner of the indicator enables the display of the reference baro correction in the range of 870 to 1050 hPa. Integral lighting supplied with external 5VAC is provided to illuminate the presentation.
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______________________________________________________
 TASK 34-21-00-790-001
 Low range leak test of standby pneumatic circuits
 WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
 YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

 CAUTION : OBEY THESE PRECAUTIONS WHEN YOU DO THE TEST TO PREVENT DAMAGE TO
_______
 INSTRUMENTS:

 -PRESSURE SET MUST NOT BE MORE THAN 1050 hPa (31 in Hg) OR LESS THAN 115 hPa (3.39 in Hg)
 -CHANGES IN PRESSURE MUST NOT BE MORE THAN 6000 FEET/MINUTE
 -DO NOT SUDDENLY OPEN LINES TO AMBIENT AIR WHILE THE PRESSURE GENERATOR IS CONNECTED.
 CAUTION : THE TOTAL PRESSURE IN THE PITOT SYSTEM MUST NEVER BE LESS THAN THE
_______ STATIC PRESSURE. THE DIFFERENCE BETWEEN THE PITOT AND THE STATIC PRESSURE CIRCUITS MUST NEVER BE MORE THAN 368 hPa (10.86 in Hg).
　
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