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used as an auxiliary display.
COMPONENT AND OPERATION
The standby compass is installed in a bracket on the center post of the windshield, above the flight guidance panel. The
compass is aligned with the aircraft longitudinal axis.
The standby compass is a self-contained unit that has a transparent and molded bowl and is filled with silicon fluid. In the
fluid is a sphere with a compass dial. Silicone fluid is used to insure free and smooth movement in order to provide an accurate
indication. Metal bellows in the compass let the fluid volume expand and contract to changes in temperature and
altitude.
The standby compass is lighted and uses a special non-magnetic bulb. The light unit is powered by 5 vdc from the integral
light controller.
The compass dial shows markings for the four cardinal heading (N, E, S, W) and has numerals every 30°, with bars every
10°. The last numeral is not shown (for example “24” means “240”). Heading of the aircraft is read against the vertical
lubber line.
To operate correctly, the compass needs installation adjustments and also corrections for heading indication errors caused
by magnetic interference from the aircraft electrical and avionics system. During the adjustment procedure, the heading
reference is supplied by the attitude and heading references system (AHRS).
The standby compass is adjusted in the vertical axis with two adjustment screws that attach the compass to the mounting
bracket through two extended holes. At the top of the compass there is an index error adjustment scale. The center major
index mark on this scale is used as a reference point during the adjustment procedures.
The standby compass has also two compensators (B and C) installed at the top area of the compass. They are used to adjust
the readings for the magnetic interferences.
COMPASS CORRECTION CARD
The standby compass system includes a compass correction card installed on a bracket above the standby compass. The
compass correction card has a STEER row used to write the corrected heading for each of the cardinal headings and for the
30° increments.
FLIGHT INSTRUMENTS
Volume 2 Flight Crew Operating Manual Sep 13/2004
11-01-32 CSP 100-6 REV 1
STANDBY COMPASS (Cont)
CFO1101002_031
N 3
B 10 10 C
33
LIGHT UNIT
COMPASS
DIAL
COMPENSATORS
BRACKET
ADJUSTMENT SCREW
B
C
A
A
B
B
CENTER INDEX MARK
COMPASS
CORRECTION
CARD
STANDBY COMPASS WITH ALL RADIOS ON SWUNG / / BY
TO FLY
STEER
N 30 60 E 120 150 S 210 240 W 300 330
FLIGHT INSTRUMENTS
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 11-01-33
CONTROLS AND INDICATIONS
PRIMARY FLIGHT DISPLAY (PFD)
00
IAS 225
M
.54
.50
.42
.38
4
2
1
1
4
ALTS
20
10
20
10
350 16000
350 00
4
3
100
00
00
352 00
80
20
2
29.92 IN
.68
.68
7
9
UTC
° C
11 : 42
SAT -60
ISA -5 ° C
TAS
GS
385
280
30
HDG 340
TR / WX / LX
TNU
NEBOR
24
W
100
30
33
N
340
3
6
E
12 15
S
21
FMS1
DTK 340
KCID
TTG 15:01
95.0 NM
FMS1
LOC1
FMS2
VOR2
111.30
126.80
NAV
SOURCE
FMS2 180N
FIX
IOW
IA
CID
KCID
ALO MXO
ANOSA
DBQ
CFO1101002_022
ROLL AP YD PITCH
FLIGHT INSTRUMENTS
Volume 2 Flight Crew Operating Manual Sep 13/2004
11-01-34 CSP 100-6 REV 1
CONTROLS AND INDICATIONS (Cont)
MULTIFUNCTION DISPLAYS (MFD)
COM1 NAV1 ATC1/TCAS ADF1 HF1 COM3 COM2
118.000 108.00 1200 1799.5 118.000 118.000
118.000 108.00 STBY 190.0 2.0000 118.000 118.000
ABV
TX 2.0000 AM
25 25
CID
DIRECT 3.0°
10000A
0 : 20 /
18325
12000B
95NM
CID 95 NM
77 NM
0 : 20
IRK
OSH 215 NM 0 : 59
KORD 339 NM 1 : 20
HDG 340
FMS2 340
UTC
° C
11 : 42
SAT -15
ISA -5 ° C
TAS
GS
250
254
30
FMS2 180NM
FIX
MFD
CONTROL
TR / WX / LX
WX
T-1.5A
24
W
30
33
N
3
6
DBQ
ALO
TNU
NEBOR
ANOSA
CID
IOW
IA
MXO
200
KCID
100
270 / 150
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
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