ELECTRICAL LOAD DISTRIBUTION

ELECTRICAL LOAD DISTRIBUTION
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
ELECTRICAL LOAD DISTRIBUTION
1. DESCRIPTION
A. Power Distribution - Serials 1005 thru 1267
The power distribution system consists of the main electrical power bus, the essential and non-essential power buses, and the associated fuses, circuit breakers and switches. The main power bus
receives power from the power generation system through a series of bus fuses (single alternator system) or circuit breakers (dual alternator system). The main power bus provides power to the essential
and nonessential power buses through a network of bus fuses or bus circuit breakers.
During normal operation, the essential and non-essential buses operate in parallel, but during power
system failures, the non-essential bus can be disconnected to provide load shedding of non-essential
equipment loads. This load shedding is designed to increase emergency operating power capacity and
to decrease pilot work-load during emergency situations by providing the capability to remove all nonessential loads in a single action. Essential aircraft loads can be powered with a failure of either the
alternator or battery. Either power source can be disconnected from the primary bus in the event of a
failure. In addition, the secondary batteries (three 9-volt batteries) can be manually selected to power
the turn coordinator in the event of primary electrical power failure. The secondary batteries are
mounted to the inner side of the bolster switch panel (just above the pilot’s kneecaps).
The airplane has a specially designed bus architecture that allows power to be routed to the essential
circuitry if any one of the main power wires fails. Each bus and circuit are labeled on the circuit breaker
panel. The clock bus is fused within the MCU and is the only bus not connected to the master switch
arrangement. The clock is continuously powered through a 5-amp fuse connected to the primary bus
in the MCU.
Individual circuit load charts and bus schematics showing system current flow during normal and failure modes are provided in the Wiring Manual.
B. Power Distribution - Serials 1268 thru 2015 w/o single alternator SRV, 2016 & subs w/o single
alternator SRV and w/o Perspective Avionics
The power distribution system consists of the main distribution bus and the essential distribution bus in
the MCU along with the associated buses in the circuit breaker panel and their associated circuit
breakers and switches. Each bus and circuit are labeled on the circuit breaker panel. The clock bus is
fused within the MCU and is the only bus not connected to the master switch arrangement. The clock,
if installed, is continuously powered through a 5-amp fuse connected to the primary bus in the MCU.
This airplane has four ways of obtaining electrical power for the essential bus. The essential bus can
obtain electrical power from BAT 1, BAT 2, ALT 1, or ALT 2. In an emergency, as long as one of the
four power sources remain functional, the essential bus will continue to supply electrical power to all of
the flight critical instruments. The essential power bus normally receives electrical power from the ALT
2 and BAT 2 electrical systems.
The main power bus receives power from the BAT 1 system (ALT 1 and/or BAT 1). The main power
bus provides power to the essential and nonessential power buses through a network of bus fuses or
bus circuit breakers.
For normal operation, the Essential Buses in the circuit breaker panel are powered from the essential
distribution bus in the MCU through 25-amp circuit breakers. BAT 2 is connected directly to the Essential Bus in the circuit breaker panel and will power the bus should the voltage coming from the MCU
distribution buses drop below the battery voltage. Additionally, in the event of an ALT 2 failure, the circuit breaker panel Essential Bus will be powered from ALT 1 through the main distribution and essential distribution buses in the MCU. Main Bus 1, Main Bus 2, and the equipment Non-Essential Bus in
the circuit breaker panel are powered from ALT 1 through the main distribution bus in the MCU. The
Avionics Non-Essential Bus in the circuit breaker panel is powered from circuit breaker panel Main Bus
1.
EFFECTIVITY:
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CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
Individual circuit load charts and bus schematics showing system current flow during normal and failure modes are provided in the Wiring Manual.
C. Power Distribution - Serials 2016 & subs w/ Perspective Avionics
The power distribution system for this airplane consists of the Main Distribution Bus 1, Main Distribution Bus 2, and the Essential Distribution Bus in the MCU along with the associated buses in the circuit
breaker panel. The circuit breaker panel is located on the left side of the console next to the pilots right
knee. Each bus and circuit is labeled on the circuit breaker panel.
The Essential Distribution Bus receives electrical power from both Main Distribution Bus 1 and Main
Distribution Bus 2 in the MCU through two 50-amp fuses. The Essential Power Bus powers circuit
breaker buses ESS BUS 1 and ESS BUS 2 through 30-amp fuses located in the MCU.
The Main Power Bus 1 receives power from ALT 1 through a 100-amp fuse. The Main Power Bus 1
provides directly powers the landing light through a 7.5-amp fuse, and circuit breaker buses A/C BUS
1, A/C BUS 2, and MAIN BUS 3 through 30-amp fuses located in the MCU.
The Main Power Bus 2 receives power from ALT 2 through a 80-amp fuse. The Main Power Bus 1
powers circuit breaker buses NON ESS BUS, MAIN BUS 1, and MAIN BUS 2 through 30-amp fuses
located in the MCU.
The airplane can obtain electrical power for the Essential Bus from BAT 1, BAT 2, ALT 1, or ALT 2. In
an emergency, as long as one of the four power sources remain functional, the Essential Bus will continue to supply electrical power to all of the flight critical instruments.
(1)
Essential Buses
The circuit breaker panel ESS BUS 1 is powered by ALT 1 and ALT 2 from the MCU Essential
Distribution Bus through the 20-amp ESSENTIAL POWER circuit breaker and from BAT 2
through the 20-amp BAT 2 circuit breaker.
The circuit breaker panel ESS BUS 2 is powered directly from the MCU Essential Distribution
Bus through the 30-amp fuse inside the MCU. Power from the 10-amp AVIONICS circuit breaker
is controlled through the AVIONICS master switch on the bolster switch panel.
In the event of ALT 1 or ALT 2 failure, the Essential Buses in the circuit breaker panel will be
powered by the remaining alternator through the Main Distribution Bus 1 or Main Distribution
Bus 2 in the MCU. In the case of both alternators failing, BAT 1 is connected directly to the
Essential Distribution Bus in the MCU and will power ESS BUS 1 and ESS BUS 2. In the event
of both alternators and BAT 1 failing, BAT 2 is connected directly to ESS BUS 1.
(2)
Main Buses
The circuit breaker panel MAIN BUS 1 and MAIN BUS 2 are powered by ALT 2 from the MCU
Main Distribution Bus 2 and - in the event of ALT 2 failure - by ALT 1 and BAT 1 from the Main
Distribution Bus 2 via the diode interconnecting the MCU distribution buses through 30-amp
fuses inside the MCU. The 10-amp AVIONICS circuit breaker on MAIN BUS 1 powers all loads
on the AVIONICS BUS.
The circuit breaker panel MAIN BUS 3 is powered by ALT 1 and BAT 1 from the MCU Main Distribution Bus 1 through a 30-amp fuse inside the MCU. In the event of ALT 1 failure, BAT 1 will
power MAIN BUS 3. ALT 2 is prevented from powering MAIN BUS 3 by the isolation diode interconnecting the MCU Distribution Buses 1 and 2.
(3)
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Non-Essential Buses
The circuit breaker panel NON ESS BUS is powered by ALT 2 from the MCU Main Distribution
Bus 2 and - in the event of ALT 2 failure - by ALT 1 and BAT 1 from the Main Distribution Bus 2
via the diode interconnecting the MCU distribution buses through 30-amp fuses inside the MCU.
The Avionics Non-Essential Bus is powered through the 10-amp AVIONICS circuit breaker on
MAIN BUS 1.
EFFECTIVITY:
Serials 2016 & subs w/ Perspective Avionics
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
The circuit breaker panel A/C BUS 1 and A/C BUS 2, is powered by ALT 1 and BAT 1 from the
MCU Main Distribution Bus 1 through a 30-amp fuse inside the MCU. In the event of ALT 1 failure, BAT 1 will power A/C BUS 1 and A/C BUS 2. ALT 2 is prevented from powering A/C BUS 1
and A/C BUS 2 by the isolation diode interconnecting the MCU Distribution Buses 1 and 2.
Individual circuit load charts and bus schematics showing system current flow during normal and
failure modes are provided in the Wiring Manual.
D. Power Distribution - Serials 1337 & subs w/ single alternator SRV
The power distribution system consists of the main distribution bus and the essential distribution bus in
the MCU along with the associated buses in the circuit breaker panel and their associated circuit
breakers and switches. Each bus and circuit are labeled on the circuit breaker panel. The clock bus is
fused within the MCU and is the only bus not connected to the master switch arrangement.
This airplane has three ways of obtaining electrical power for the essential bus. The essential bus can
obtain electrical power from BAT 1, BAT 2, or ALT 1. In an emergency, as long as one of the three
power sources remain functional, the essential bus will continue to supply electrical power to all of the
flight critical instruments.
The main power bus receives power from the BAT 1 system (ALT 1 and/or BAT 1). The main power
bus provides power to the essential and nonessential power buses through a network of bus fuses or
bus circuit breakers.
For normal operation, the Essential Buses in the circuit breaker panel are powered from the essential
distribution bus in the MCU through 25-amp circuit breakers. BAT 2 is connected directly to the Essential Bus in the circuit breaker panel and will power the bus should the voltage coming from the MCU
distribution buses drop below the battery voltage. Main Bus 1, Main Bus 2, and the equipment NonEssential Bus in the circuit breaker panel are powered from ALT 1 through the main distribution bus in
the MCU. The Avionics Non-Essential Bus in the circuit breaker panel is powered from circuit breaker
panel Main Bus 1.
Individual circuit load charts and bus schematics showing system current flow during normal and failure modes are provided in the Wiring Manual.
E. Circuit Protection Devices (See Figure 24-501)
(1)
Circuit Breakers
The electrical system in this airplane is protected by using circuit breakers and fuses. A circuit
breaker panel is located near the pilot's right leg, and is labeled as to each circuit's identity. The
circuit breaker panel contains all circuit protection devices re-settable in flight. The circuit breakers have their rated values identified on the top of the shaft. The circuit breakers only have two
positions, open and closed. In the open position the circuit is disconnected and in the closed
position the circuit breaker will automatically open the circuit if an overload or circuit fault occurs.
Each circuit breaker requires a manual reset by the operator.
Serials 1005 thru 1267: The airplane Essential bus is supplied from the Main Buses through the
20-amp ESSENTIAL 1 and ESSENTIAL 2 circuit breakers. Avionics loads on the Non-essential
Avionics Bus and Essential Avionics Bus are protected by 15-amp AVIONICS circuit breakers
connected to the respective bus through relays energized by the AVIONICS switch.
In addition to the individual circuit breakers, 25-amp fuses located on the primary bus in the
Master Control Unit (MCU) protect the Main Bus 1, Main Bus 2, and the Non-Essential Bus in the
single alternator system. Additionally, the single alternator system uses 15-amp fuses located in
the MCU to protect the landing light and standby vacuum pump circuits. The dual alternator system uses circuit breakers instead of fuses for the aforementioned circuits.
Serials 1268 thru 2015, 2016 & subs w/o Perspective: Avionics loads on the NON-ESSENTIAL
Avionics Bus and ESSENTIAL Avionics Bus are protected by 15-amp AVIONICS circuit breakers
connected to the respective bus through relays energized by the AVIONICS switch.
EFFECTIVITY:
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CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
In addition to the individual circuit breakers, 25-amp circuit breakers located in the Master Control Unit (MCU) protect the Main Distribution Bus and the Essential Distribution Bus. Additionally
a 15-amp circuit breaker is located in the MCU to protect the landing light circuit.
Serials 2016 & subs w/ Perspective Avionics: Avionics loads on the Avionics Bus are protected
by a 10-amp AVIONICS circuit breaker connected to the Main Bus 1 through relays energized by
the AVIONICS switch.
In addition to the individual circuit breakers, 30-amp circuit breakers located in the Master Control Unit (MCU) protect the Main Distribution Bus 1, Main Distribution Bus 2, and the Essential
Distribution Bus. Additionally a 7.5-amp circuit breaker is located in the MCU to protect the landing light circuit.
(2)
Transient Voltage Suppressors (TVS)
Transient Voltage Suppressors (TVS) are installed in key areas of the electrical system to protect the system from lightning strikes. During lightning strikes, enormous energy spikes can be
induced within the aircraft electrical system. In the absence of any transient protection, this
unwanted energy would typically be dissipated in the form of high-voltage discharge across the
avionics and electrical systems of the aircraft. By adding a high power TVS at key power entry
points on the electrical busses, unwanted energy from electrical transients is allowed to dissipate through a semi-conducting pathway to ground.
Serials 1005 thru 1336, 1337 thru 1422 w/o PFD: One TVS is installed on the circuit breaker
panel and one TVS is installed on the wire loom behind the attitude indicator.
Serials 1337 thru 1422 w/ PFD, 1423 thru 2015, 2016 & subs w/o Perspective Avionics: Three
TVS are installed on the circuit breaker panel and one is installed on the wire loom behind the
attitude indicator.
Serials 2016 & subs w/ Perspective Avionics: Two TVS are installed on the RH side of the center
console. Eight TVS are integral to wire harnesses and located at the following locations: AHRS 1
connector, air data computer connector, GIA 63W integrated avionics unit 1 connector, attitude
indicator connector, two on the PFD connector, and two near the circuit breaker panel.
F.
Switches (See Figure 24-504)
Serials 1005 thru 1267: The Battery (BAT) and Alternator (ALT) master switches are side by side and
directly in front of the pilot on the bolster panel. The battery switch disconnects the battery from the primary bus, and the alternator switch disconnects the alternator from the primary bus, thereby disconnecting the aircraft from the power sources. If both switches are turned on (BAT and ALT), the hour
meter becomes activated.
Serials 1268 & subs w/o single alternator SRV: BAT 1, BAT 2, ALT 1, and ALT 2 master switches are
side by side and directly in front of the pilot on the bolster panel. The BAT 1 switch disconnects battery
1 from the main bus in the MCU. The alternator 1 switch disconnects the forward alternator (ALT 1)
from the main bus. If BAT 1 and ALT 1 switches are in the off position the flight critical instruments will
remain powered from ALT 2 or BAT 2. If BAT 1 and either ALT 1 or ALT 2 switches are turned on, the
hour meter becomes activated.
Serials 1337 & subs w/ single alternator SRV: BAT 1, BAT 2, and ALT 1 master switches are side by
side and directly in front of the pilot on the bolster panel. The BAT 1 switch disconnects battery 1 from
the main bus in the MCU. The alternator 1 switch disconnects the alternator (ALT 1) from the main bus.
If BAT 1 and ALT 1 switches are in the off position the flight critical instruments will remain powered
from BAT 2. If BAT 1 and ALT 1 switches are turned on, the hour meter becomes activated.
(1)
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BAT & ALT Master Switches
Serials 1005 thru 1267: The rocker type electrical system MASTER switches are ON in the up
position and off in the down position. The right switch, labeled BAT, controls all electrical power
to the airplane. The left switch, labeled ALT, controls the alternator.
EFFECTIVITY:
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CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
Normally, both master switches will be on. However, the BAT switch can be turned on separately
to check equipment while on the ground. To check or use avionics equipment or radios while on
the ground, the avionics power switch must also be turned on. Positioning the ALT switch to the
off position isolates the alternator from the electrical system and the entire electrical load is
placed on the battery.
Note:
Continued operation with the alternator switch off will reduce battery power low
enough to open the battery relay, remove power from the alternator field, and prevent alternator restart.
Serials 1268 & subs w/o single alternator SRV: The rocker type electrical system MASTER
switches are ON in the up position and off in the down position. The left battery switches, labeled
BAT 1 and BAT 2, control all electrical power to the airplane. The right switches, labeled ALT 1
and ALT 2, control the corresponding alternator.
Note:
Prior to engine start-up, the pilot must activate only the BAT 2 switch to verify that
BAT 2 properly energizes the electrical loads powered by the ESSENTIAL Bus
and that BAT 2 has proper voltage. The voltage reading must be taken from the
combination Volt and Ampere meter mounted on the right instrument panel.
Serials 1268 thru 1581: The voltage is displayed by the combination Volt / Amp
meter mounted on the RH instrument panel.
Serials 1582 & subs: The voltage is displayed by the MFD and PFD.
Use BAT 1 for suppling electrical power to the avionics system when performing
general servicing tests.
Normally, all master switches will be on. However, the BAT 1 switch can be turned on separately
to check equipment while on the ground. To check or use avionics equipment or radios while on
the ground, the avionics power switch must also be turned on. Positioning the ALT 1 and ALT 2
switch to the off position isolates the alternators from the electrical system and the entire electrical load is placed on the batteries.
Note:
Continued operation with the alternator switch off will reduce battery power low
enough to open the battery relay, remove power from the alternator field control,
and prevent alternator restart.
Serials 1337 & subs w/ single alternator SRV: The rocker type electrical system MASTER
switches are ON in the up position and off in the down position. The left battery switches, labeled
BAT 1 and BAT 2, control all electrical power to the airplane. The right switch, labeled ALT 1,
controls the alternator.
Note:
Prior to engine start-up, the pilot must activate only the BAT 2 switch to verify that
BAT 2 properly energizes the electrical loads powered by the ESSENTIAL Bus
and that BAT 2 has proper voltage. The voltage reading must be taken from the
combination Volt and Ampere meter mounted on the right instrument panel.
Serials 1337 thru 1581: The voltage is displayed by the combination Volt / Amp
meter mounted on the RH instrument panel.
Serials 1582 & subs: The voltage is displayed by the MFD and PFD.
Use BAT 1 for suppling electrical power to the avionics system when performing
general servicing tests.
EFFECTIVITY:
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CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
Normally, all master switches will be on. However, the BAT 1 switch can be turned on separately
to check equipment while on the ground. To check or use avionics equipment or radios while on
the ground, the avionics power switch must also be turned on. Positioning the ALT 1 switch to
the off position isolates the alternator from the electrical system and the entire electrical load is
placed on the batteries.
Note:
(2)
Continued operation with the alternator switch off will reduce battery power
low enough to open the battery relay, remove power from the alternator field
control, and prevent alternator restart.
Avionics Power Switch
Serials 1005 thru 1267: A rocker switch, labeled AVIONICS POWER, controls electrical power
from the airplane primary bus to the avionics bus. The switch is located next to the ALT and BAT
Master switches and is ON in the up position and off in the down position. Typically, the switch is
used to energize or de-energize all avionics on the Avionics Non-essential and Avionics Essential buses simultaneously. With the switch in the off position, no electrical power will be applied to
the avionics equipment, regardless of the position of the master switch or the individual equipment switches. The AVIONICS POWER switch should be placed in the off position prior to turning the master switch ON or off, starting the engine, or applying an external power source.
The airplane has two different types of circuit protection devices. Each circuit has an electrical
protective device, with the exception of the starter motor. Fuses are located in the MCU and the
push-pull type circuit breakers are all located in the cabin area. The fuses are not replaceable
during flight.
Serials 1268 & subs w/o single alternator SRV: A rocker switch, labeled AVIONICS, controls
electrical power from the airplane primary bus to the avionics bus. The switch is located next to
the ALT 1, ALT 2, BAT 1, and BAT 2 Master switches and is ON in the up position and OFF in the
down position. Typically, the Avionics Power Switch is used to energize or de-energize all avionics on the Avionics Non-essential and Avionics Essential buses simultaneously. With the switch
in the OFF position, no electrical power will be applied to the avionics equipment, regardless of
the position of the master switch or the individual equipment switches. The AVIONICS switch
should be placed in the OFF position prior to turning the master switch ON or OFF, starting the
engine, or applying an external power source.
The airplane has two different types of circuit protection devices. Each circuit has an electrical
protective device, with the exception of the starter motor. A 5-amp clock fuse is located in the
MCU and the push-pull type circuit breakers are all located in the cabin area. The fuses are not
replaceable during flight.
Serials 1337 & subs w/ single alternator SRV: A rocker switch, labeled AVIONICS, controls electrical power from the airplane primary bus to the avionics bus. The switch is located next to the
ALT 1, BAT 1, and BAT 2 Master switches and is ON in the up position and OFF in the down
position. Typically, the Avionics Power Switch is used to energize or de-energize all avionics on
the Avionics Non-essential and Avionics Essential buses simultaneously. With the switch in the
OFF position, no electrical power will be applied to the avionics equipment, regardless of the
position of the master switch or the individual equipment switches. The AVIONICS switch should
be placed in the OFF position prior to turning the master switch ON or OFF, starting the engine,
or applying an external power source.
The airplane has two different types of circuit protection devices. Each circuit has an electrical
protective device, with the exception of the starter motor. A 5-amp clock fuse is located in the
MCU and the push-pull type circuit breakers are all located in the cabin area. The fuses are not
replaceable during flight.
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EFFECTIVITY:
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CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
G. Transmission Wire
Power is routed throughout most of the aircraft with MIL-W-22759/16 teflon coated wires. These wires
have a 150° C rating. Joints made in wires are covered with polyolefin heat shrink material, or are
joined using a solder sleeve. In the engine compartment, all power wire terminal ring ends are covered
with a silicon boot. Rubber, nylon, or teflon grommets protect the wires from chafing where the wires
pass through materials that could cause wear.
H. Transmission Wire
Power is routed throughout most of the aircraft with MIL-W-22759/16 teflon coated wires. These wires
have a 150° C rating. Joints made in wires are covered with polyolefin heat shrink material, or are
I.
Convenience Power
The aircraft contains a 12 VDC convenience power outlet to power auxiliary equipment. The convenience outlet is located in the center console arm rest. Regulated 12 VDC power is supplied to the outlet through the convenience power circuit card.
Power for Active Noise Reduction (ANR) headsets is also provided through the convenience power circuit card. The ANR power can be set to 9 VDC, 17 VDC, or 28 VDC through a switch on the assembly.
(Refer to 23-50)
Serials 2273 & subs: The aircraft contains two dual-port USB power outlets to power auxiliary equipment. One outlet is located near the convenience outlet for use by the pilot and forward passenger,
and the other is located on the aft portion of the center console for the rear passengers. 28 VDC for the
USB power outlets is supplied through the 5-amp 12V DC OUTLET circuit breaker on MAIN BUS 3.
Serials 1005 thru 1267: 28 VDC for the convenience power circuit card is supplied through the 5-amp
CONVENIENCE POWER 12VDC circuit breaker on NON-ESSENTIAL.
Serials 1268 & subs w/o Perspective: 28 VDC for the convenience power circuit card is supplied
through the 3-amp 12V/ANR circuit breaker on NON-ESSENTIAL.
Serials w/ Perspective: 28 VDC for the convenience power circuit card is supplied through the 5-amp
12V DC OUTLET circuit breaker on MAIN BUS 3.
J. Level Sensor Power Circuit Card - Serials 2156 thru 2292
The aircraft is equipped with a digital fuel quantity system. The fuel quantity level sensors operate on
12 VDC which is provided through the Level Sensor Power Circuit Card. 28 VDC for the Level Sensor
Power Circuit Card is provided through the 3-amp FUEL QTY circuit breaker on MAIN BUS 1. The
Level Sensor Power Circuit Card provides two regulated 12 VDC outputs for the right wing fuel and left
wing fuel quantity systems. Resistors located within the wire harness set the output voltage to 12 VDC.
For information pertaining to the fuel quantity sensors, see Chapter 28, Section 40 - Indicating. (Refer
to 28-40)
K. Convenience System Controller - Serials 2303 & subs w/ Convenience Lighting
The aircraft is equipped with a convenience system controller providing the means to power on ground
lights for several minutes of convenience illumination when aircraft power is off. LED lights controlled
by the convenience system controller include the cabin dome light, flight compartment interior footwell
lights, passenger compartment interior footwell lights, entry step lights, and baggage lights. The convenience system controller is installed on the fuselage skin below the RH passenger seat. Power is activated via wireless keyfob or cabin light switch located on the cabin headliner.
28 VDC for the convenience system controller is supplied through the 3-amp CONV LIGHTS circuit
breaker on CONS bus.
For information regarding convenience lighting, see Lights. (Refer to 33-00)
EFFECTIVITY:
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AIRPLANE MAINTENANCE MANUAL
MODEL SR20
2. MAINTENANCE PRACTICES
A. Circuit Breakers (See Figure 24-501)
(1)
Removal - Circuit Breakers
(a) Verify ignition switch is in OFF position and remove the key.
(b) Disconnect battery 1. (Refer to 24-30)
(c)
Disconnect battery 2. (Refer to 24-30)
(d) Serials 1005 thru 2015, 2016 & subs w/o Perspective Avionics: Remove aft screws securing circuit breaker panel to center console. Swing circuit breaker panel open.
(e) Serials 2016 & subs w/ Perspective Avionics: Rotate turn studs securing circuit breaker
panel to center console. Swing circuit breaker panel open.
(f)
Identify and disconnect all wires to circuit breaker and/or bus.
Note:
It may be necessary to loosen more than one circuit breaker and/or bus bar
to remove the selected breaker and/or bus bar.
(g)
(2)
(3)
Remove nut, washer, and tab washer securing circuit breaker to panel. Remove circuit
breaker from airplane.
Installation - Circuit Breakers
(a) Position tab washer on circuit breaker stud.
(b) Position circuit breaker to panel, ensuring washer tab inserts into small hole on panel.
(c)
Install washer and nut securing circuit breaker to panel.
(d) Identify and connect all wires to circuit breaker.
(e) Serials 1005 thru 2015, 2016 & subs w/o Perspective Avionics: Position circuit breaker
panel to center console and secure with screws.
(f)
Serials 2016 & subs w/ Perspective Avionics: Position circuit breaker panel to center console and secure with turn studs.
(g) Connect battery 2. (Refer to 24-30)
(h) Connect battery 1. (Refer to 24-30)
Functional Check - Redundant Circuit Breakers - Serials 1005 thru 1267
28 VDC for the essential bus is supplied through redundant circuit breakers on the main bus 1
and main bus 2. The following functional check ensures both circuit breakers are operating properly with no disturbance of power to the essential bus.
(a)
(b)
(c)
(4)
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Set BAT 1 switch to ON position.
Pull ESSENTIAL 1 circuit breaker.
Verify no disruption of power to essential bus by confirming annunciator OIL light is illuminated.
(d) Reset ESSENTIAL 1 circuit breaker.
(e) Pull ESSENTIAL 2 circuit breaker.
(f)
Verify no disruption of power to essential bus by confirming annunciator OIL light is illuminated.
(g) Reset ESSENTIAL 2 circuit breaker.
(h) Set BAT 1 switch to OFF position.
Functional Check - Redundant Circuit Breakers - Serials 1268 & subs w/o SRV
28 VDC for the HSI or PFD, turn coordinator, and attitude indicator is supplied through redundant circuit breakers on the Essential Bus and Main Bus 2. The following functional check
ensures both circuit breakers are operating properly with no disturbance of power to the equipment.
(a)
(b)
Set BAT 1 switch to ON position.
Serials 1005 thru 1885: Test HSI/PFD circuit breakers.
EFFECTIVITY:
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CIRRUS
(c)
(d)
(e)
(f)
(g)
(h)
EFFECTIVITY:
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AIRPLANE MAINTENANCE MANUAL
MODEL SR20
1
Pull HSI/PFD #1 circuit breaker.
2
Verify no disruption of power to HSI or PFD.
3
Reset HSI/PFD #1 circuit breaker.
4
Pull HSI/PFD #2 circuit breaker.
5
Verify no disruption of power to HSI or PFD.
6
Reset HSI/PFD #2 circuit breaker.
Serials 1886 & subs: Test PFD circuit breakers.
1
Pull PFD #1 circuit breaker.
2
Verify no disruption of power to PFD.
3
Reset PFD #1 circuit breaker.
4
Pull PFD #2 circuit breaker.
5
Verify no disruption of power to PFD.
6
Reset PFD #2 circuit breaker.
Serials 1005 thru 1885: Test TURN COORD circuit breakers.
1
Pull TURN COORD #1 circuit breaker.
2
Verify no disruption of power to turn coordinator.
3
Reset TURN COORD #1 circuit breaker.
4
Pull TURN COORD #2 circuit breaker.
5
Verify no disruption of power to turn coordinator.
6
Reset TURN COORD #2 circuit breaker.
Serials 1886 & subs w/ System 55X Autopilot: Test TRN CRD circuit breakers.
1
Pull TRN CRD #1 circuit breaker.
2
Verify no disruption of power to turn coordinator.
3
Reset TRN CRD #1 circuit breaker.
4
Pull TRN CRD #2 circuit breaker.
5
Verify no disruption of power to turn coordinator.
6
Reset TRN CRD #2 circuit breaker.
Serials 1005 thru 2015, 2016 & subs w/o Perspective Avionics: Test ATTITUDE circuit
breakers.
1
Pull ATTITUDE #1 circuit breaker.
2
Verify no disruption of power to attitude indicator.
3
Reset ATTITUDE #1 circuit breaker.
4
Pull ATTITUDE #2 circuit breaker.
5
Verify no disruption of power to attitude indicator.
6
Reset ATTITUDE #2 circuit breaker.
Serials 2016 & subs w/ Perspective Avionics: Test ATTITUDE circuit breakers.
1
Pull STDBY ATTD #1 circuit breaker.
2
Verify no disruption of power to attitude indicator.
3
Reset STDBY ATTD #1 circuit breaker.
4
Pull STDBY ATTD #2 circuit breaker.
5
Verify no disruption of power to attitude indicator.
6
Reset STDBY ATTD #2 circuit breaker.
Serials 2016 & subs w/ Perspective Avionics: Test MFD circuit breakers.
1
Pull MFD #1 circuit breaker.
2
Verify no disruption of power to MFD.
3
Reset MFD #1 circuit breaker.
4
Pull MFD #2 circuit breaker.
24-50
Page 9
15 Jun 2010
CIRRUS
(5)
(c)
(d)
(e)
Page 10
15 Jun 2010
MODEL SR20
5
Verify no disruption of power to MFD.
6
Reset MFD #2 circuit breaker.
(i)
Set BAT 1 switch to OFF position.
Functional Check - Redundant Circuit Breakers - Serials 1337 & subs w/ SRV
28 VDC for the PFD and turn coordinator is supplied through redundant circuit breakers on the
essential bus and main bus 2. The following functional check ensures both circuit breakers are
operating properly with no disturbance of power to the equipment.
(a)
(b)
24-50
AIRPLANE MAINTENANCE MANUAL
Set BAT 1 switch to ON position.
Test PFD circuit breakers.
1
Pull PFD #1 circuit breaker.
2
Verify no disruption of power to PFD.
3
Reset PFD #1 circuit breaker.
4
Pull PFD #2 circuit breaker.
5
Verify no disruption of power to PFD.
6
Reset PFD #2 circuit breaker.
Serials 1005 thru 1885: Test TURN COORD circuit breakers.
1
Pull TURN COORD #1 circuit breaker.
2
Verify no disruption of power to turn coordinator.
3
Reset TURN COORD #1 circuit breaker.
4
Pull TURN COORD #2 circuit breaker.
5
Verify no disruption of power to turn coordinator.
6
Reset TURN COORD #2 circuit breaker.
Serials 1886 & subs: Test TRN CRD circuit breakers.
1
Pull TRN CRD #1 circuit breaker.
2
Verify no disruption of power to turn coordinator.
3
Reset TRN CRD #1 circuit breaker.
4
Pull TRN CRD #2 circuit breaker.
5
Verify no disruption of power to turn coordinator.
6
Reset TRN CRD #2 circuit breaker.
Set BAT 1 switch to OFF position.
EFFECTIVITY:
All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
5
7
8
9
3
5
4
1
4
2
6
Serials 1005 thru 1267.
11
CENTER CONSOLE
(REF)
2
12
10
1
2
7
13
4
LEGEND
1. Screw
2. Circuit Breaker Panel
3. Terminal Ring
4. Washer
5. Nut
7. Star Washer
8. Circuit Breaker
9. Bus Bar
10. Piano Hinge
11. Hinge Pin
12. Relay
13. Relay Socket
5
SR20_MM24_1598C
Figure 24-501
Circuit Breaker Panel - Serials 1005 thru 2015, 2016 & subs w/o Perspective Avionics (Sheet 1 of 2)
EFFECTIVITY:
Serials 1005 thru 2015, 2016 & subs w/o Perspective
Avionics
24-50
Page 11
15 Jun 2010
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
12
4
5
13
4
4
5
CENTER CONSOLE
(REF)
1
1
17
1
8
16
2
LEGEND
1. Screw
2. Circuit Breaker Panel
3. Terminal Ring
4. Washer
5. Nut
7. Star Washer
8. Circuit Breaker
9. Bus Bar
10. Piano Hinge
11. Hinge Pin
12. Relay
13. Relay Socket
16. Turn Stud
17. Retainer
7
5
Serials 2016 & subs w/ Perspective Avionics.
SR20_MM24_2910
Figure 24-501
Circuit Breaker Panel - Serials 2016 & subs w/ Perspective Avionics (Sheet 2 of 2)
24-50
Page 12
15 Jun 2010
EFFECTIVITY:
Serials 2016 & subs w/ Perspective Avionics
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
B. Transient Voltage Suppressor (TVS) - Serials 1005 thru 2015, 2016 & subs w/o Perspective Avionics (See Figure 24-502)
(1)
(2)
Removal - Transient Voltage Suppressor
(a) Verify ignition switch is in OFF position and remove the key.
(b) Disconnect battery 1. (Refer to 24-30)
(c)
Disconnect battery 2. (Refer to 24-30)
(d) Remove TVS located on circuit breaker panel.
1
Remove aft screws securing circuit breaker panel to center console. Swing circuit
breaker panel open.
2
Remove screws and washers securing TVS terminal rings to COM 1, PFD #1, and
PFD #2 circuit breakers.
3
Remove screws, washers, and nuts securing TVS and terminal rings to circuit
breaker panel.
(e) Remove TVS located on attitude indicator wire harness.
1
Remove LH kick Plate. (Refer to 25-10)
2
Remove screw and washer securing TVS terminal ring to console.
3
Remove cable tie securing TVS and fuse to attitude indicator wire harness.
4
Cut wire between attitude indicator and TVS fuse holder.
Installation - Transient Voltage Suppressor
(a) Install TVS located on circuit breaker panel.
CAUTION:
Verify TVS polarity prior to installation.
1
(b)
Position TVS and terminal rings to circuit breaker panel and secure with screws,
washers, and nuts.
2
Position TVS terminal rings to COM 1, PFD #1, and PFD #2 circuit breakers and
secure with screws and washers.
3
Position circuit breaker panel to center console and secure with screws.
Install TVS located on attitude indicator wire harness.
CAUTION:
(3)
Verify TVS polarity prior to installation.
1
Splice new TVS and fuse holder to wire from attitude indicator.
2
Position TVS terminal ring to console and secure with screw and washer.
3
Position TVS and fuse to wire harness and secure with cable tie.
4
Install LH kick plate. (Refer to 25-10)
(c)
Connect battery 2. (Refer to 24-30)
(d) Connect battery 1. (Refer to 24-30)
Inspection/Check - Transient Voltage Suppressor
(a) Verify ignition switch is in OFF position and remove the key.
(b) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.
(c)
Remove LH kick Plate. (Refer to 25-10)
(d) Remove aft screws securing circuit breaker panel to center console. Swing circuit breaker
panel open.
Note:
(e)
If a circuit breaker repeatedly opens and cannot be reset, the power TVS
may be damaged.
Reset circuit breakers.
EFFECTIVITY:
Serials 1005 thru 2015, 2016 & subs w/o Perspective
Avionics
24-50
Page 13
15 Jun 2010
CIRRUS
(f)
(g)
(h)
(i)
(j)
(k)
24-50
Page 14
01 Jan 2012
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
Visually inspect power TVS for charring, cracking, pieces broken off or missing, or other
signs of physical damage. If necessary, replace power TVS. (Refer to 24-50)
Serials 1268 thru 2015, 2016 & subs w/o Perspective Avionics: Visually inspect fuse
between attitude indicator and TVS. If fuse is blown, replace fuse and corresponding TVS.
(Refer to 24-50)
Serials 1268 thru 1422 w/o PFD: Visually inspect fuse between TVS and COM 1 circuit
breaker. If fuse is blown, replace fuse and TVS. (Refer to 24-50)
Serials 1337 thru 1422 w/ PFD, 1423 thru 2015, 2016 & subs w/o Perspective Avionics:
Visually inspect fuses between TVS and PFD #1 and PFD #2 circuit breakers. If fuse is
blown, replace fuse and corresponding TVS. (Refer to 24-50)
Position circuit breaker panel to center console and secure with screws.
Install LH kick plate. (Refer to 25-10)
EFFECTIVITY:
Serials 1005 thru 2015, 2016 & subs w/o Perspective
Avionics
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
2
3
5
WIRE LOOM
(REF)
1
6
6
6
2
CIRCUIT BREAKER
PANEL (REF)
5
6
3
Serials 1337 thru 1422
w/ PFD, 1423 & subs.
2
CIRCUIT BREAKER
PANEL (REF)
5
1
3
4
3
Serials 1268 thru 1336,
1337 thru 1422 w/o PFD.
1
3
LEGEND
1. TVS
2. Screw
3. Washer
4. Nut
5. Terminal Ring
6. Fuse Holder
4
NOTE
Serials 1268 thru 1944 after SB 2X-24-09,
1945 & subs.
SR20_MM24_2770A
Figure 24-502
Transient Voltage Suppressor Installation - Serials 1005 thru 2015, 2016 & subs w/o Perspective Avionics
EFFECTIVITY:
Serials 1005 thru 2015, 2016 & subs w/o Perspective
Avionics
24-50
Page 15
01 Jan 2012
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
C. Transient Voltage Suppressor (TVS) - Serials 2016 & subs w/ Perspective Avionics (See Figure
24-502)
(1)
(2)
(3)
Removal - Transient Voltage Suppressor
(a) Verify ignition switch is in OFF position and remove the key.
(b) Disconnect battery 1. (Refer to 24-30)
(c)
Disconnect battery 2. (Refer to 24-30)
(d) Remove right mid console trim. (Refer to 25-10)
(e) Remove screw, washer, and nut securing ground wire to console.
(f)
Remove screw securing terminal rings to positive terminal of TVS.
(g) Remove washers and nuts securing TVS to console. Remove TVS from airplane.
Installation - Transient Voltage Suppressor
(a) Position TVS to console and secure with washers and nuts.
(b) Position ground wire to console and secure with screw, washer, and nut.
(c)
Position terminal rings to positive terminal of TVS and secure with screw.
(d) Install right mid console trim. (Refer to 25-10)
(e) Connect battery 2. (Refer to 24-30)
(f)
Connect battery 1. (Refer to 24-30)
Inspection/Check - Transient Voltage Suppressor
(a) Verify ignition switch is in OFF position and remove the key.
(b) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.
Note:
(c)
(d)
(e)
24-50
Page 16
15 Jun 2010
There are ten TVS with associated fuses in the Perspective Avionics system. Eight of the TVS are integral to wire harnesses and covered by heat
shrink. It is not necessary to remove the heat shrink for the visual inspection.
Visually inspect attitude indicator TVS.
1
Remove LH kick plate. (Refer to 25-10)
2
Visually inspect TVS for signs of overheating or damage.
3
Visually inspect fuse between attitude indicator and TVS. If fuse is blown, replace
fuse and corresponding TVS. (Refer to 24-50)
4
Install LH kick plate. (Refer to 25-10)
Visually inspect center console and circuit breaker panel TVS.
1
Remove turn studs securing circuit breaker panel to center console. Swing circuit
breaker panel open.
2
On RH side of center console, visually inspect TVS for charring, cracking, pieces
broken off or missing, or other signs of physical damage. If necessary, replace TVS.
(Refer to 24-50)
3
On circuit breaker panel, visually inspect TVS for signs of overheating or damage.
4
Visually inspect each TVS fuse. If fuse is blown, replace fuse and corresponding
TVS. (Refer to 24-50)
5
Close circuit breaker panel and secure with turn studs.
Visually inspect TVS on the following connectors: PFD, AHRS 1, air data computer, and
integrated avionics unit 1.
1
Remove PFD. (Refer to 31-60)
2
Remove MFD. (Refer to 31-60)
3
Remove glareshield. (Refer to 25-10)
4
Remove EMI shielding. (Refer to 25-10)
5
Remove AHRS 1. (Refer to 34-20)
EFFECTIVITY:
Serials 2016 & subs w/ Perspective Avionics
CIRRUS
AIRPLANE MAINTENANCE MANUAL
6
7
8
9
10
11
12
MODEL SR20
Visually inspect TVS for signs of overheating or damage.
Visually inspect each TVS fuse. If fuse is blown, replace fuse and corresponding
TVS. (Refer to 24-50)
Install AHRS 1. (Refer to 34-20)
Install EMI shielding. (Refer to 25-10)
Install glareshield. (Refer to 25-10)
Install MFD. (Refer to 31-60)
Install PFD. (Refer to 31-60)
EFFECTIVITY:
Serials 2016 & subs w/ Perspective Avionics
24-50
Page 17
15 Jun 2010
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
2
4
3
SIDE PANEL
RIGHT MID CONSOLE
(REF)
5
2
3
5
6
5
2
3 5
4
3
4
1
7
5
6
4
3
1
5
3
2
1.
2.
3.
4.
5.
6.
7.
LEGEND
TVS
Screw
Washer
Nut
Terminal Ring
Fuse Holder
Cable Tie
SR20_MM24_2908
Figure 24-503
Transient Voltage Suppressor Installation - Serials 2016 & subs w/ Perspective Avionics
24-50
Page 18
15 Jun 2010
EFFECTIVITY:
Serials 2016 & subs w/ Perspective Avionics
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
D. Bolster Panel Switches - Serials 1005 thru 1183 (See Figure 24-504)
(1)
(2)
Removal - Bolster Panel Switches
(a) Verify ignition switch is in OFF position and remove key.
(b) Disconnect batteries. (Refer to 24-30)
(c)
Remove kick plate. (Refer to 25-10)
(d) Remove screws and washers securing bolster panel to console.
(e) Identify and disconnect all wires to the selected switch.
(f)
Compress retainers on selected switch and push up to remove.
Installation - Bolster Panel Switches
(a) Compress retainers on selected switch and push down into position.
(b) Identify and connect all wires to selected switch.
(c)
Secure bolster panel to console with screws and washers.
(d) Install kick plate. (Refer to 25-10)
(e) Connect batteries. (Refer to 24-30)
E. Bolster Panel Switches - Serials 1184 & subs
The bolster panel switches are integral to the bolster panel. For maintenance practices pertinent to the
bolster panel, see Instrument and Control Panels. (Refer to 31-10)
EFFECTIVITY:
All
24-50
Page 19
01 Jan 2016
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
BOLSTER PANEL
(REF)
1
2
3
4
10
6
8
5
9
7
LEGEND
1. Knob
2. Nut
3. Washer, Star
4. Switch
5. Potentiometer
6. Socket Relay
7. Relay
8. Washer
9. Screw
10. Switch Panel, Forward Console
Serials 1005 thru 1183.
Figure 24-504
Bolster Panel Switch Installation - Serials 1005 thru 1183
24-50
Page 20
15 Jun 2010
EFFECTIVITY:
Serials 1005 thru 1183
SR20_MM24_1572B
CIRRUS
F.
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
Convenience Power Circuit Card (See Figure 24-505)
(1)
(2)
(3)
Removal - Convenience Power Circuit Card
(a) Remove pilot’s seat. (Refer to 25-10)
(b) Remove left aft console trim. (Refer to 25-10)
(c)
Disconnect wiring harnesses from connectors on convenience power circuit card.
(d) Remove screws and washers securing convenience power circuit card to bracket.
Installation - Convenience Power Circuit Card
(a) Install screws and washers securing convenience power circuit card to bracket.
(b) Connect wiring harnesses to connectors on convenience power circuit card.
(c)
Perform Functional Test - Convenience Power Circuit Card. (Refer to 24-50)
(d) Install left aft console trim. (Refer to 25-10)
(e) Install pilot’s seat. (Refer to 25-10)
Functional Test - Convenience Power Circuit Card
(a)
Acquire necessary tools, equipment, and supplies.
Description
Voltmeter
(b)
(c)
(d)
(e)
(f)
(g)
(h)
(i)
(j)
(k)
(l)
(m)
(n)
(o)
(p)
(q)
(r)
(s)
(t)
EFFECTIVITY:
All
P/N or Spec.
-
Supplier
Any Source
Purpose
Measure voltage.
Ensure flap switch is set in current flap position.
Ensure that all flight controls and propeller area are clear.
Pull Starter Relay and Fuel Pump Relay circuit breakers.
Connect 28 ±1 VDC external power to external power receptacle.
Set BAT 2 switch to ON position.
Use voltmeter to ensure voltage measures 22-26 VDC.
Ensure Flap circuit breaker is in.
Ensure Flap Position lights are not on.
Set BAT 1 switch to ON position.
Set BAT 2 switch to OFF position.
Ensure OIL, ALT1, and ALT2 annunciator lights indicate power.
Use voltmeter to ensure voltage at convenience power outlet measures 13 ±1 VDC with
positive pin (+) to center contact and negative pin (-) to outside of jack.
On convenience power circuit card, set headset power switch S520 to 9 VDC.
Ensure voltage at all four ANR jacks measures 9 ±1 VDC with positive (+) to center contact and negative (-) to ground.
On convenience power circuit card, set headset power switch S520 to 17 VDC.
Ensure voltage at all four ANR jacks measures 17 ±1 VDC with positive (+) to center contact and negative (-) to ground.
On convenience power circuit card, set headset power switch S520 to 28 VDC.
Ensure voltage at all four ANR jacks measures 1 VDC with positive (+) to center contact
and negative (-) to ground.
Leave power switch set at 28 VDC.
24-50
Page 21
15 Jun 2010
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
G. Voltage Converter - Serials w/ GNC 250 XL (See Figure 24-505)
(1)
(2)
24-50
Page 22
15 Jun 2010
Removal - Voltage Converter
(a) Remove pilot’s seat. (Refer to 25-10)
(b) Remove left aft console trim. (Refer to 25-10)
(c)
Open circuit breaker panel to gain access to voltage converter.
(d) Disconnect wiring harnesses from connectors on voltage converter.
(e) Remove screws, washers, and nuts securing voltage converter to center console.
Installation - Voltage Converter
(a) Install screws, washers, and nuts securing voltage converter to center console.
(b) Connect wiring harnesses to connectors on voltage converter.
(c)
Close and secure circuit breaker panel.
(d) Install left aft console trim. (Refer to 25-10)
(e) Install pilot’s seat. (Refer to 25-10)
EFFECTIVITY:
Serials w/ GNC 250 XL
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
SEAT RAIL
(REF)
SPAR COVER
(REF)
SEAT RAIL
(REF)
1
2
3
4
3
2
5
3
1
5
4
8
1
6
5
9
J537
R529
R528
8
R526
R527
4
PCB 11519CCA 12016-
8
C531
POSITION 2
HEADSET
POWER = 17V
REV
REV
C529
CR525
C528
5
1
CR524
R525
C530
4
POSITION 1
HEADSET
POWER
SYSTEM VOLTAGE
(28V)
S520
U525
5
U524
1
8
CIRRUS
DESIGN
CORP.
4
POSITION 3
HEADSET
POWER = 9V
5
1
CONVENIENCE POWER CIRCUIT CARD ASSEMBLY
LEGEND
1. Heat Sink
2. Screw
3. Washer
4. Bracket
5. Nut
S520 SWITCH POSITION
DETAIL
SR20_MM24_2619
Figure 24-505
Convenience Power Circuit Card Installation (Sheet 1 of 2)
EFFECTIVITY:
All
24-50
Page 23
15 Jun 2010
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
CENTER CONSOLE
(REF)
3
6
5
2
Serials w/ GNC 250 XL.
LEGEND
2. Screw
3. Washer
5. Nut
6. Voltage Converter
SR20_PC24_2620
Figure 24-505
Convenience Power Circuit Card Installation (Sheet 2 of 2)
24-50
Page 24
15 Jun 2010
EFFECTIVITY:
All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
H. Level Sensor Power Circuit Card - Serials 2156 thru 2292 (See Figure 24-506)
(1)
(2)
(3)
Removal - Level Sensor Power Circuit Card
(a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.
(b) Pull FUEL QTY circuit breaker.
(c)
Remove RH crew seat. (Refer to 25-10)
(d) Remove RH kick plate. (Refer to 25-10)
(e) Disconnect wiring harness from Level Sensor Power Circuit Card.
(f)
Remove screws securing Level Sensor Power Circuit Card to console rib. Remove Level
Sensor Power Circuit Card from airplane.
Installation - Level Sensor Power Circuit Card
(a) Position Level Sensor Power Circuit Card to console rib and secure with screws.
(b) Connect wiring harness to Level Sensor Power Circuit Card.
(c)
Install RH kick plate. (Refer to 25-10)
(d) Install RH crew seat. (Refer to 25-10)
(e) Reset FUEL QTY circuit breaker.
(f)
Perform Functional Test - Level Sensor Power Circuit Card. (Refer to 24-50)
Functional Test - Level Sensor Power Circuit Card
(a)
Acquire necessary tools, equipment, and supplies.
Description
Voltmeter
(b)
(c)
(d)
(e)
(f)
P/N or Spec.
-
Supplier
Any Source
Purpose
Measure voltage.
Remove wing access panels LW5 and RW5. (Refer to 06-00)
Disconnect sensor connectors P350 and P450 from LH and RH inboard fuel level sensors.
Ensure voltage at connectors P350 and P450 measures 12 ±1 VDC with positive (+) to
socket 1 and negative (-) to socket 3. (Refer to 28-40)
Connect sensor connectors P350 and P450 to sensors.
Install wing access panels LW5 and RW5. (Refer to 06-00)
EFFECTIVITY:
Serials 2156 thru 2292
24-50
Page 25
01 Jan 2016
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
CONSOLE RIB
(REF)
1
2
LEGEND
1. Level Sensor Power Circuit Card
2. Screw
Serials 2156 thru 2292.
Figure 24-506
Level Sensor Power Circuit Card - Serials 2156 thru 2292
24-50
Page 26
01 Jan 2016
EFFECTIVITY:
Serials 2156 thru 2292
SR20_MM24_3528
CIRRUS
I.
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
Convenience Power Outlet (See Figure 24-507)
(1)
(2)
Removal - Convenience Power Outlet
(a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.
(b) Pull 12V DC OUTLET circuit breaker.
(c)
Open center console armrest and remove glove box. (Refer to 25-10)
(d) Remove aft console rear cover. (Refer to 25-10)
(e) Disconnect electrical terminals.
(f)
Loosen outlet housing from outlet.
(g) Remove outlet and outlet housing from airplane.
Installation - Convenience Power Outlet
(a) Install retaining ring of outlet cover to outlet.
(b) Position outlet through hole in center console with threaded end pointing aft.
Note:
Serials 1005 thru 2272: Ensure terminals and outlet cover cap point down
when outlet is snug against center console.
Serials 2273 & subs: Ensure terminals point down and outlet cover cap is
positioned horizontally as shown when outlet is snug against center console.
(c)
(d)
(e)
(f)
(g)
EFFECTIVITY:
All
Install outlet housing to outlet and tighten until snug against center console.
Connect electrical terminals.
Install aft console rear cover. (Refer to 25-10)
Insert glove box. (Refer to 25-10)
Reset 12V DC OUTLET circuit breaker.
24-50
Page 27
15 Dec 2014
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
J. USB Power Outlets - Serials 2273 & subs (See Figure 24-507)
(1)
Removal - USB Power Outlet
(a)
Acquire necessary tools, equipment, and supplies.
Description
Utility Knife
(b)
(c)
(d)
(e)
(f)
(g)
(h)
-
1
2
3
4
Cut template.
Using utility knife, cut out template on dashed line.
Using utility knife, cut out shaded area within template, making sure to stay inside of
dark line.
Align template over USB outlet.
Using cross-hatches on template, locate center of screws.
Remove smallest area of overlay as possible to expose entire diameter of screw heads.
5
Using utility knife, remove audio panel overlay to expose screw heads.
(i)
Remove screws securing outlet to center console. Discard screws.
(j)
Remove outlet from airplane.
Installation - USB Power Outlet
(a)
Acquire necessary tools, equipment, and supplies.
Description
(b)
(c)
(d)
(e)
(f)
(g)
Page 28
15 Dec 2014
Any Source
Purpose
Verify template is printed to scale.
Note:
24-50
Supplier
Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.
Pull 12V DC OUTLET circuit breaker.
Open center console armrest and remove glove box. (Refer to 25-10)
Remove aft console rear cover. (Refer to 25-10)
For Cockpit USB Power Outlet: Disconnect connector P1520.
For Passenger USB Power Outlet: Disconnect connector P1521.
Using template, remove audio panel overlay covering existing countersunk screws.
Note:
(2)
P/N or Spec.
P/N or Spec.
Supplier
Purpose
Screw, #4-40 x .3125”, Qty. 24676
2
Fastenal
Winona, MN
55987
507-454-5374
Secure outlet.
Flat Washer, Nylon, .115”
ID, .032” Thk, Qty. 2
Fastenal
Winona, MN
55987
507-454-5374
Secure outlet.
11513272
Position outlet to center console and secure with washers and screws.
For Cockpit USB Power Outlet: Connect connector P1520.
For Passenger USB Power Outlet: Connect connector P1521
Install aft console rear cover. (Refer to 25-10)
Insert glove box. (Refer to 25-10)
Reset 12V DC OUTLET circuit breaker.
EFFECTIVITY:
Serials 2273 & subs
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
3
4
A
2
1
4
Serials 1005 thru 2272.
7
A1
5
6
5
7
4
6
3
1
Serials 2273 & subs.
4
A1
VIEW A1
2
Serials 2273 & subs.
DETAIL A
Scale (inches)
0
1/4
1/2
3/4
UP
1
Scale (cm)
0
1
2
2.54
NOTE
1
Verify template is printed to scale.
2
Using utility knife, cut out template on dashed line.
3
Using utility knife, cut out shaded area within
template, making sure to stay inside of dark line.
TEMPLATE
1
2
3
LEGEND
1. Convenience Power Outlet
2. Outlet Cover
3. Outlet Housing
4. Electrical Terminal
5. USB Power Outlet
6. Connector
7. Screw
SR20_MM24_3687
Figure 24-507
Convenience Power Outlet and USB Power Outlet Installation
EFFECTIVITY:
All
24-50
Page 29
15 Dec 2014
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
K. Convenience System Controller - Serials 2303 & subs w/ Convenience Lighting (See Figure 24508)
(1)
(2)
(3)
24-50
Page 30
01 Jan 2016
Removal - Convenience System Controller
(a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.
(b) Pull CONV LIGHTS circuit breaker.
(c)
Remove access panel CF4R.
(d) Disconnect wire harness connector from convenience system controller.
(e) Remove washers and screws securing convenience system controller to standoffs and
remove from airplane.
Installation - Convenience System Controller
(a) Position convenience system controller to standoffs with connector facing inboard. Secure
with screws and washers.
(b) Connect wire harness connector to convenience system controller.
(c)
Install access panel CF4R.
(d) Reset CONV LIGHTS circuit breaker.
(e) Perform Operational Test - Convenience System Controller. (Refer to 24-50)
Operational Test - Convenience System Controller
(a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.
(b) Press unlock button on wireless keyfob.
(c)
Verify doors unlock and step lights illuminate.
(d) Set cabin light switch to ON position.
(e) Verify interior footwell lights illuminate.
(f)
Set cabin light switch to OFF position.
(g) Verify interior footwell lights turn off.
(h) Set cabin light switch to AUTO position.
(i)
Open baggage door.
(j)
Verify baggage lights illuminate.
EFFECTIVITY:
Serials 2303 & subs w/ Convenience Lighting
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
2
1
3
WIRE HARNESS
CONNECTOR
(REF)
A
STANDOFFS
(REF)
LEGEND
1. Convenience System
Controller
2. Screw
3. Washer
DETAIL A
Serials 2303 & subs w/ Convenience Lighting.
SR20_MM24_4238
Figure 24-508
Convenience System Controller Installation - Serials 2303 & subs w/ Convenience Lighting
EFFECTIVITY:
Serials 2303 & subs w/ Convenience Lighting
24-50
Page 31
01 Jan 2016
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
Intentionally Left Blank
24-50
Page 32
01 Jan 2016
EFFECTIVITY:
Serials 2303 & subs w/ Convenience Lighting
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