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100ft/min.
(6) Compare the test-equipment altimeter and
the airplane altimeter.
The indication error must be less than
shown in Table 1 below.
Table 1 Altimeter Indication Error
Altitude Allowable Error
Sea level ±20 ft
4,000 ft ±35 ft
8,000 ft ±60 ft
12,000 ft ±90 ft
16,000 ft ±110 ft
20,000 ft ±130 ft
Navigation
DA20-C1 AMM
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24 Oct 2001 34-10-00 Doc # DA 201-C1
Rev. 8
D. Pitot Test
Detail Steps/Work Items Key Items
(1) Obey the precautions at the beginning of this
subject.
(2) Connect the pitot-static leak-tester to the
pitot-static probe.
(3) Apply a pressure to the pitot port equal to
150 kts.
(4) Let the pressure stabilize.
(5) Monitor the system pressure. The leak rate must not be more than
10 kts/min
(6) Compare the test-equipment altimeter and
the airplane altimeter.
The indication error must be less than
shown in Table 1 below.
Table 1 ASI Indication Error
Airspeed Allowable Error
160 kts ±4 kts
100 kts ±4 kts
40 kts ±1.7 kts
DA20-C1 AMM
Navigation
Doc # DA 201-C1
Rev. 9 34-20-00 Page 1
29 Apr 2004
CHAPTER 34-20
ATTITUDE AND DIRECTION
1. General
This Section tells you about the equipment which shows attitude and flight direction. Figures 1, 2
and 3 show the equipment locations. The DA20-C1 has these attitude and direction indicators:
− Attitude:
− Attitude indicator (vacuum, or electrical).
− Turn coordinator (electrical).
− Stall warning horn.
− Direction:
− Magnetic compass.
− Directional gyro (vacuum, or electrical).
Some aircraft have different direction indicators as customer options. For example, a slaved
compass system. See the manufacturer’s manuals for data about these instruments.
2. Description and Operation
A. Attitude Indicator
The attitude indicator uses a gyro as an attitude reference. The indicator shows pitch and roll
data. Some aircraft use vacuum to operate the gauges. It operates only when the engine is
running. The vacuum necessary to operate the attitude indicator is 4.5 to 5.2 in.Hg. The flow
rate is 2.1 ft3/min. Optionally an electrically driven gyro may be installed
The display shows a blue area for the sky and a brown area for the ground. A small bar shows
the airplanes wings. Where the blue and brown touch shows the horizon. Horizontal markings
above and below the horizon show pitch up and down. Each graduation is 5°.
The roll display has markings around the circumference of the instrument. The markings are at
10, 20, 30, 60 and 90 degrees of roll.
Navigation
DA20-C1 AMM
Page 2
19 Dec 1997 34-20-00 Doc # DA 201-C1
Rev. 0
Figure 1: Instrument Panel Locations
DA20-C1 AMM
Navigation
Doc # DA 201-C1
Rev. 0 34-20-00 Page 3
19 Dec 1997
B. Turn Coordinator
The turn coordinator is an electrically-powered gyroscopic instrument. It operates when the
main bus is powered and the turn coordinator circuit-breaker is closed. A warning flag shows
when there is no power to the unit. The warning flag goes out of view when the turn coordinator
has the correct power.
The turn coordinator has a slip indicator. A ball in a curved tube filled with fluid shows when the
airplane is slipping or skidding. When the ball is in the center, the turn is correctly coordinated.
The turn coordinator shows the rate of rotation of the airplane about the vertical axis. The turn
coordinator has markings for rate 1 and rate 2 turns.
C. Stall Warning
A stall warning horn is located on the left side of the instrument panel. Air pressure operates the
horn. A hole in the leading edge of the left wing connects to the horn. When the angle of attack
is just less than the stall angle, the airflow through the hole operates the horn.
D. Magnetic Compass
The magnetic compass shows the heading of the airplane related to magnetic north. Fluid in the
compass bowl gives damping. Each graduation on the compass is 5°.
A compass deviation card attaches to the compass. Compensating magnets for compass
adjustment are behind the deviation card holder. The compass lighting comes on when the
DIM/BRIGHT switch is set to DIM.
You must do a test for correct operation of the compass (compass swing):
− After replacing a major component.
− After replacing the compass.
− After modification to the airplane.
Navigation
DA20-C1 AMM
Page 4
19 Dec 1997 34-20-00 Doc # DA 201-C1
Rev. 0
Figure 2: Attitude and Direction Component Locations
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