曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
March 2010
7-54 Information Manual
Section 7 Cirrus Design
Airplane and Systems Description SR22
Figure 7-11
Electrical / Lighting Controls and Indicating
LEGEND
1. Essential & Main Bus Voltage
2. Alternator & Battery Current
3. Battery 2
4. Battery 1
5. Alternator 1
6. Alternator 2
Density Alt 8000 Ft
Oat 31°F -1°C (ISA +0°C)
1
3 4 6 7
Electrical System Indication
2
7. Avionics
8. Navigation
9. Strobe
10. Landing Light
11. Instrument Dimmer
12. Panel Dimmer
SR22_FM07_2811A
Electrical and Lighting Controls
5 8 9 10
11
12
March 2010
Cirrus Design Section 7
SR22 Airplane and Systems Description
Information Manual 7-55
Lighting Systems
Exterior Lighting
The airplane is equipped with wing tip navigation lights with integral
anti-collision strobe lights and recognition Lights. The landing light is
located in the lower cowl.
Navigation Lights
The airplane is equipped with standard wing tip navigation lights. The
lights are controlled through the NAV light switch on the instrument
panel bolster.
28 VDC for navigation light operation is supplied through the 5-amp
NAV LIGHTS circuit breaker on the NON ESS BUS.
Strobe Light
Anti-collision strobe lights are installed integral with the standard
navigation lights. Each strobe is flashed by a separate power supply.
The strobe power supplies are controlled through the STROBE light
switch on the instrument panel bolster.
28 VDC for strobe light and control circuits is supplied through the 5-
amp STROBE LIGHTS circuit breaker on the NON ESS BUS.
Landing Light
A High Intensity Discharge (HID) landing light is mounted in the lower
engine cowl. The landing light is controlled through the LAND light
switch on the instrument panel bolster.
Setting the LAND light switch 'on' energizes the landing light control
relay in the Master Control Unit (MCU) completing a 28 VDC circuit
from the airplane Main Distribution Bus 1 to the light's ballast located
on the firewall. The ballast provides boosted voltage to illuminate the
HID lamp.
A 7.5-amp fuse on the Main Distribution Bus 1 in the MCU protects the
circuit.
Recognition Lights
The airplane is equipped with recognition lights on the leading edge of
the wing tips. The lights are controlled through the landing light switch
on the instrument panel bolster.
28 VDC for recognition light operation is supplied through the 5-amp
RECOG LIGHTS circuit breaker on the NON ESS BUS.
March 2010
7-56 Information Manual
Section 7 Cirrus Design
Airplane and Systems Description SR22
Interior Lighting
Interior lighting for the airplane consists of separately controlled
incandescent overhead lights for general cabin lighting, individual
lights for the pilots and passengers, and dimmable panel floodlights.
The flight instrumentation and avionics equipment lights are dimmable.
Instrument Lights
Instrument lighting for the airplane consists of photocell backlighting
technology for the flight displays, bezel, audio panel keys, FMS
keyboard, and optionally installed GMC 705 AFCS Control Unit and
dimmable incandescent lights in the standby instrument bezels.
Components using backlighting technology automatically adjust for
ambient lighting conditions. Manual brightness adjustment for all
instruments can be accomplished through the INSTRUMENT dimmer
control on the instrument panel bolster. The instrument light circuits
operate on 28 VDC supplied through the 5-amp CABIN LIGHTS circuit
breaker on MAIN BUS 1.
Panel Flood Lights
A string of red LEDs mounted under the instrument panel glareshield
provide flood lighting for the instrument panel. The lights are controlled
through the PANEL dimmer control on the instrument panel bolster.
The panel lights operate on 28 VDC supplied through the 5-amp
CABIN LIGHTS circuit breaker on MAIN BUS 1.
Reading Lights
Individual eyeball-type reading lights are installed in the headliner
above each passenger position. Each light is aimed by positioning the
lens in the socket and is controlled by a push-button switch located
next to the light. The pilot and copilot reading lights are also dimmable
through the PANEL lights control on the instrument panel bolster. The
reading lights are powered by 28 VDC supplied through the 5-amp
CABIN LIGHTS circuit breaker on MAIN BUS 1.
Overhead Dome Light
General cabin lighting is provided by a dome light located in the
headliner at the approximate center of the cabin. The dome light is
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
西锐20飞机信息手册 SR22 AIRPLANE INFORMATION MANUAL 2979(70)
