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1. AIR CONDITIONING AIRCRAFT
MAINTENANCE MANUAL
EFFECTIVITY:
ALL
Embraer 190 - SDS 2327
21-00-00
Page 1 of 16
Rev 41 - Jul 26/18
Copyright © by Embraer S.A. All rights reserved - See title page for details.

2. Introduction
The air conditioning system supplies airflow to the cockpit and
passenger cabin for ventilation and pressurization. It also controls the
temperature and humidity of the air.
The air conditioning system contains a BIT (Built-in Test) that
continuously monitors the performance of the system components.
The figure AIR CONDITIONING - OVERVIEW provides further data on
the preceding text. AIRCRAFT
MAINTENANCE MANUAL
EFFECTIVITY:
ALL
Embraer 190 - SDS 2327
21-00-00
Page 2 of 16
Rev 41 - Jul 26/18
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3. AIR CONDITIONING
PACKS
ZONE
191
AMS CONTROLLER
(SPDA 2)
ZONES
147/148
AIR CONDITIONING
CONTROLS AND
INDICATIONS
ZONES
221
222
COCKPIT
DISTRIBUTION
ZONES
123/124
125/126
221/222
223/224
225/226
MAIN CABIN
DISTRIBUTION
ZONES
130/230
140/240
150/250
EM170SDS210121B.DGN AIR CONDITIONING - OVERVIEW
AIRCRAFT
MAINTENANCE MANUAL
EFFECTIVITY:
ALL
Embraer 190 - SDS 2327
21-00-00
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Rev 41 - Jul 26/18
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4. General Description
The AIR CONDITIONING includes these subsystems:
• DISTRIBUTION (AMM SDS 21-20-00/1)• PRESSURIZATION CONTROL (AMM SDS 21-30-00/1)• COOLING (AMM SDS 21-50-00/1)• TEMPERATURE CONTROL (AMM SDS 21-60-00/1)CONTROL PANELS/INDICATING
These control panels and indicators allow the monitoring of the air
conditioning system:
•PRESSURIZATION control panel ( AMM SDS 21-30-00/1) -
Controls the pressurization of the aircraft.
•AIR COND/PNEUMATIC panel ( AIPC 31-17-04) - The air
conditioning portion of this panel controls the overall functions of
the air conditioning system.
•CABIN TEMPERATURE knob - Located on the ATDT (Attendant)
control panel and enabled by the PAX CABIN knob on the cockpit,
it controls the temperature of the cabin when the ENABLE LED is
on.
•EICAS (Engine Indication and Crew Alerting System) display
(AMM SDS 31-11-00/1) - Shows the system failure messages and
the pressurization data.
•MFD (Multi-Function Display) Synoptic Page (AMM SDS
31-11-00/1) - Shows the synoptics of the environmental control
system. Data is provided for the air conditioning, pressurization,
bleed, and oxygen systems.
AIR CONDITIONING - CONTROL PANEL - FUNCTIONS
REF.
CONTROL/INDICA-
TOR
FUNCTION
1PACK 1
Controls the left cooling pack (AUTO/OFF). Selection of
the OFF mode shuts down the left pack. Selection of the
AUTO mode activates the left pack.
2PACK 2
Controls the right cooling pack (AUTO/OFF). Selection of
the OFF mode shuts down the right pack. Selection of
the AUTO mode activates the right pack.
3RECIRC
Controls the recirculation system (AUTO /OFF). Selec-
tion of the OFF mode shuts down both recirculation fan.
4 PAX CABIN KNOB Controls the passenger cabin temperature.5 CKPT KNOB Controls the cockpit temperature.
The figure AIR CONDITIONING - CONTROLS AND INDICATIONS
provides further data on the preceding text. AIRCRAFT
MAINTENANCE MANUAL
EFFECTIVITY:
ALL
Embraer 190 - SDS 2327
21-00-00
Page 4 of 16
Rev 41 - Jul 26/18
Copyright © by Embraer S.A. All rights reserved - See title page for details.

5. FWD
ENTRANCE
FWD GALLEY
AREA
ON/
ARMED
PRESSURIZATION
CONTROL PANEL
RECIRC 1 RECIRC 2
SAFETY VALVE
CABIN ALT
DOWN UP
DOWN UP
B
A
B
DCD
AIR COND/PNEUMATIC PANEL
A
DC
RECIRC
CKPT
C H C H
CABIN
PAX
ATTND
PACK 1 PACK 2
XBLEED
BLEED 1 BLEED 2BLEED APU
WING 1
START 1
WING 2
START 2GND
CONN
2O.7
ATTCS
8O.O 8O.O MTO
N1
2O.7
REV
463
°
463
°
9O.O
1OOO
9O.O
1OOOPPH
ITT
N2
FF
FQLBS9OO 3OOO
FUEL QTY
IGN
A
IGN
A
1
LANDING GEAR
UP
APU
CABIN
TRIMS
TEMP
1O681
PRESS
1112° °
LP HP
VIB °1OO 1O2O% C
ALT
RATE FPM
PSI
LFE 12OO
-5 FT
-5
P -64.6
FT
2
S/F
SPDBRK
S F
ROLL PITCH
UP
YAW
22
CABIN LIGHTING
CABIN TEMPERATURE
HC
ENABLED
GALLEY MASTER
PANEL LIGHTS
ON ON ON
SIDEWALLCEILING
TEMPERATURE SETTING
ON
RESET
OFF
AUTO
TEST
LAVATORY SMOKE TEST
FWD AFT LH AFT RH RESET
PSU
TEST
ATTND CALL
RESET
TEST
BRIGHT
DIM
BRIGHT
DIM
BRIGHT
DIM
EMERGENCY LIGHT COURTESY LIGHT
BRIGHT
DIM
E
EICAS DISPLAY MFD SYNOPTICS PAGE
Map Plan Systems ECS
TCAS ChecklistWeather
25
25
25
25
25
25
SET ACTUAL
CKPT
FWD CAB
AFT CAB
RAM AIR
PACK 1 PACK 2
45
PSI FCV1
APU
FCV2
XBLO
GND CART
OPEN
CLOSED
OFV
FWD
BAY
CARGO
45
PSI
PRESSURIZATION
AUTO
MAN
LFE
CTRL
STOP
MODE
LFE
DUMP
STOP
E
FWD MONUMENT
1
1
A MONUMENT CAN BE A CLOSET OR LAVATORY.
ATTENDANT PANEL
1 2
3
45
EM170SDS210047C.DGN AIR CONDITIONING - CONTROLS AND INDICATIONS
AIRCRAFT
MAINTENANCE MANUAL
EFFECTIVITY:
ALL
Embraer 190 - SDS 2327
21-00-00
Page 5 of 16
Rev 41 - Jul 26/18
Copyright © by Embraer S.A. All rights reserved - See title page for details.

6. AMS CONTROLLER MODULES
The primary electronic control for the environmental control system,
overheat detection, pneumatic bleed system, crew oxygen monitoring,
and slat ice protection is provided by the AMS (Air Management
System) controller cards. The AMS controller cards are eight cards
installed in SPDA (Secondary Power Distribution Assembly) 2 (located
at Middle Electronic Compartment). All cards are Line Replaceable
Module (LRM (Line Replaceable Module)).
The AMS controller architecture consists of two independent control
channels for redundancy (Channel A (1) and Channel B (2)). Each
control channel is identical to the other and is comprised of four
modular electronic cards (a shipset consists of eight cards). The
software of the AMS is the Black Label.
AIR CONDITIONING - AMS CONTROLLER MODULES LOCATION
AMS CONTROLLERSPDA 2 (SLOT)
AMS CTRL CHAN-
NEL
AMS CTRL Microproc-
essor
18
A (1)
AMS CTRL In/Out 19AMS CTRL Motor drive 20AMS CTRL In/out 21AMS CTRL In/out 22
B (2)
AMS CTRL Motor drive 23AMS CTRL In/Out 24AMS CTRL Microproc-
essor
25The AMS controller channels provide all system control and buit-in test
functions. Both channels receive signals and calculate values, but only
the channel in control drives outputs.
After the aircraft power-up, each AMS controller channel starts the
PBIT (Power Up Built in Test).
The automatic transfer of control occurs 30 second after each landing.
The NVM (Non-Volatile Memory) of the AMS stores the channel that
must be in control until the next landing. Then, if a PBIT is executed,
the channel in control (stored in the NVM) will continue in control.
During the AMS operation, if the active channel fails, the control of the
system will be automatically transferred to the other channel, with no
interruption of AMS system functions.
The figure AIR CONDITIONING - AMS CONTROLLER MODULES -
LOCATION provides further data on the preceding text. AIRCRAFT
MAINTENANCE MANUAL
EFFECTIVITY:
ALL
Embraer 190 - SDS 2327
21-00-00
Page 6 of 16
Rev 41 - Jul 26/18
Copyright © by Embraer S.A. All rights reserved - See title page for details.

7. TYPICAL
SPDA 2
ZONES
147
148
EM170SDS210119B.DGN
M18
M19
M20
M21
M22
M23
M24
M25
AMS
CONTROLLER
MODULE
A
B
B
A
C
C AIR CONDITIONING - AMS CONTROLLER MODULES - LOCATION
AIRCRAFT
MAINTENANCE MANUAL
EFFECTIVITY:
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21-00-00
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Rev 41 - Jul 26/18
Copyright © by Embraer S.A. All rights reserved - See title page for details.

8. EFFECTIVITY: ON ACFT WITH AMS SOFTWARE UP TO
BLACK LABEL 8.0
EICAS MESSAGES
The EICAS messages related to the AMS controller are the
following:
AIR CONDITIONING - CAS (Crew Alerting System) MESSAGESMESSAGE TYPE DESCRIPTION
AMS CTRL FAILCaution (amber color)
This message will show when:
•
The two AMS controller channels are
faulty, as the AMS controller senses
it; or
•
There is no valid data on the ASCB
(Avionics Standard-Communication
Bus) from the AMS controller, as the
MAU (Modular Avionics Unit) senses
it; or
•
The two ODS (Overheat Detection
System) cards are faulty, as the AMS
controller senses it.
NOTE:
The ODS cards are installed
directly on the AMS cards.
EFFECTIVITY: ON ACFT WITH AMS SOFTWARE UP TO
BLACK LABEL 8.0 (Continued)
AIR CONDITIONING - CAS (Crew Alerting System) MESSAGES (Con-
tinued)
MESSAGE TYPE DESCRIPTION
AMS CTRL FAULTAdvisory (cyan color)
This message will show when:
•
One of the AMS controller channels is
faulty when the CAS message is
correlated with a CMC (Central
Maintenance Computer) message
that relates to the AMS control
processor module, or
•
The AMS channels have different
software versions.
NOTE:
This message will only be
displayed while the aircraft is
on the ground.

AIRCRAFT
MAINTENANCE MANUAL
EFFECTIVITY:
ALL
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21-00-00
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Rev 41 - Jul 26/18
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9. THIS PAGE INTENTIONALLY LEFT BLANK
AIRCRAFT
MAINTENANCE MANUAL
EFFECTIVITY:
ALL
Embraer 190 - SDS 2327
21-00-00
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Rev 41 - Jul 26/18
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10. EFFECTIVITY: ON ACFT WITH AMS SOFTWARE BLACK
LABEL 9.0 AND ON
EICAS MESSAGES
The EICAS messages related to the AMS controller are the
following:
AIR CONDITIONING - CAS MESSAGESMESSAGE TYPE DESCRIPTION
AMS CTRL FAILCaution (amber color)
This message will show when:
•
The two AMS controller channels are
faulty, as the AMS controller senses
it; or
•
There is no valid data on the ASCB
from the AMS controller, as the MAU
senses it; or
•
The two ODS cards are faulty, as the
AMS controller senses it; or
•
The AMS channels have different
software versions.
NOTE:
The ODS cards are installed
directly on the AMS cards.
AMS CTRL FAULTAdvisory (cyan color)
This message will show when:
•
One of the AMS controller channels is
faulty when the CAS message is
correlated with a CMC message that
relates to the AMS control processor
module.
NOTE:
This message will only be
displayed while the aircraft is
on the ground.

AMS CONTROLLER AND CMC
Through the CMC (AMM TASK 45-45-00-970-805-A/200), it is possible
to:
•Check the AMS channel in control. Most of the AMS CMC
screens show this information (AMM TASK 21-00-00-910-803-A/
200).
•Transfer the AMS channel in control ( AMM TASK
21-00-00-910-801-A/200).
•Check the software part number installed on the AMS controller
microprocessor module (AMM TASK 21-00-00-910-802-A/200).
The AMS also has the initiated BIT, parameters, and status CMC
screens.
The figure AIR CONDITIONING - CONTROLS AND INDICATIONS
provides further data on the preceding text. AIRCRAFT
MAINTENANCE MANUAL
EFFECTIVITY:
ALL
Embraer 190 - SDS 2327
21-00-00
Page 10 of 16
Rev 41 - Jul 26/18
Copyright © by Embraer S.A. All rights reserved - See title page for details.

11. FWD
ENTRANCE
FWD GALLEY
AREA
ON/
ARMED
PRESSURIZATION
CONTROL PANEL
RECIRC 1 RECIRC 2
SAFETY VALVE
CABIN ALT
DOWN UP
DOWN UP
B
A
B
DCD
AIR COND/PNEUMATIC PANEL
A
DC
RECIRC
CKPT
C H C H
CABIN
PAX
ATTND
PACK 1 PACK 2
XBLEED
BLEED 1 BLEED 2BLEED APU
WING 1
START 1
WING 2
START 2GND
CONN
2O.7
ATTCS
8O.O 8O.O MTO
N1
2O.7
REV
463
°
463
°
9O.O
1OOO
9O.O
1OOOPPH
ITT
N2
FF
FQLBS9OO 3OOO
FUEL QTY
IGN
A
IGN
A
1
LANDING GEAR
UP
APU
CABIN
TRIMS
TEMP
1O681
PRESS
1112° °
LP HP
VIB °1OO 1O2O% C
ALT
RATE FPM
PSI
LFE 12OO
-5 FT
-5
P -64.6
FT
2
S/F
SPDBRK
S F
ROLL PITCH
UP
YAW
22
CABIN LIGHTING
CABIN TEMPERATURE
HC
ENABLED
GALLEY MASTER
PANEL LIGHTS
ON ON ON
SIDEWALLCEILING
TEMPERATURE SETTING
ON
RESET
OFF
AUTO
TEST
LAVATORY SMOKE TEST
FWD AFT LH AFT RH RESET
PSU
TEST
ATTND CALL
RESET
TEST
BRIGHT
DIM
BRIGHT
DIM
BRIGHT
DIM
EMERGENCY LIGHT COURTESY LIGHT
BRIGHT
DIM
E
EICAS DISPLAY MFD SYNOPTICS PAGE
Map Plan Systems ECS
TCAS ChecklistWeather
25
25
25
25
25
25
SET ACTUAL
CKPT
FWD CAB
AFT CAB
RAM AIR
PACK 1 PACK 2
45
PSI FCV1
APU
FCV2
XBLO
GND CART
OPEN
CLOSED
OFV
FWD
BAY
CARGO
45
PSI
PRESSURIZATION
AUTO
MAN
LFE
CTRL
STOP
MODE
LFE
DUMP
STOP
E
FWD MONUMENT
1
1
A MONUMENT CAN BE A CLOSET OR LAVATORY.
ATTENDANT PANEL
1 2
3
45
EM170SDS210047C.DGN AIR CONDITIONING - CONTROLS AND INDICATIONS
AIRCRAFT
MAINTENANCE MANUAL
EFFECTIVITY:
ALL
Embraer 190 - SDS 2327
21-00-00
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Rev 41 - Jul 26/18
Copyright © by Embraer S.A. All rights reserved - See title page for details.

12. AMS CONTROLLER COMMUNICATION/INTERFACES
The AMS controller receives and transmits Input/Output signal through
SPDAs and MAUs. The communication between AMS controller and
SPDA is through ARINC 429. The communication between SPDAs is
thought ARINC 429 BUS. The communication between the channels of
the AMS controller is through RS 422.
The figure AIR CONDITIONING - AMS SYSTEM COMMUNICATION -
SCHEMATIC DIAGRAM provides further data on the preceding text. AIRCRAFT
MAINTENANCE MANUAL
EFFECTIVITY:
ALL
Embraer 190 - SDS 2327
21-00-00
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Rev 41 - Jul 26/18
Copyright © by Embraer S.A. All rights reserved - See title page for details.

13. MAU 3
APU
FADEC
10 ASCB COMMS
8 MICRO/COMMS
1 POWER SUPPLY
2 DC POWER
3 DC POWER
4 DC POWER
5 DC POWER
6 DC POWER
7 DC POWER
9 DISCRETE I/O
11 DISCRETE I/O
12 MICRO/COMMS
13 DC POWER
14 SPARE
15 SPARE
16 AC POWER
17 ANALOG I/O
19 DISCRETE I/O
20 POWER SUPPLY
10 ASCB COMMS 8 MICRO/COMMS
1 POWER SUPPLY
2 DC POWER
3 DC POWER
4 DC POWER
5 DC POWER
6 DC POWER
7 DC POWER
9 DISCRETE I/O
11 DISCRETE I/O
12 MICRO/COMMS
13 AC POWER
15 SPARE
14 AC POWER
16 SPARE
26 POWER SUPPLY
SPDA 1SPDA 2
18 ARINC 429
17 ARINC 429
18 AMS PROCESSOR
19 AMS I/O
20 AMS MOTOR DRIVE
21 AMS I/O
22 AMS I/O
23 AMS MOTOR DRIVE
24 AMS I/O
25 AMS PROCESSOR
ASCB BUS
MAU 1 MAU 2 MAU 3
ARINC 429
ARINC 429
ARINC 429
RS 422
ARINC 429
ARINC 429
AMS
CONTROLLER
CHANNEL 1
(CHANNEL A)
AMS
CONTROLLER
CHANNEL 2
(CHANNEL B)
EM170SDS210120B.DGN AIR CONDITIONING - AMS SYSTEM COMMUNICATION - SCHEMATIC DIAGRAM
AIRCRAFT
MAINTENANCE MANUAL
EFFECTIVITY:
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Embraer 190 - SDS 2327
21-00-00
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14. Components
DISTRIBUTION (AMM SDS 21-20-00/1)The distribution system receives airflow from the recirculation fans,
cooling packs, ram air system and ground equipment and distributes
this air to the cockpit, passenger cabin, gaspers, avionics
compartments and forward cargo compartment.
PRESSURIZATION CONTROL ( AMM SDS 21-30-00/1)The aircraft operates at altitudes where the oxygen density is not
sufficient to sustain life. The pressurization control keeps the aircraft
cabin interior at a safe pressure altitude. This protects the passengers
and crew from the effects of hypoxia (oxygen starvation).
COOLING (AMM SDS 21-50-00/1)The cooling system receives hot bleed air from the APU (Auxiliary
Power Unit) or engines (AMM SDS 36-00-00/1 ) and supplies
conditioned air to the distribution system (AMM SDS 21-20-00/1).
TEMPERATURE CONTROL ( AMM SDS 21-60-00/1)The temperature control system provides independent closed loop
temperature control for the cockpit and one or two separate passenger
cabin zones.
The figure AIR CONDITIONING - SCHEMATIC DIAGRAM provides
further data on the preceding text. AIRCRAFT
MAINTENANCE MANUAL
EFFECTIVITY:
ALL
Embraer 190 - SDS 2327
21-00-00
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Rev 41 - Jul 26/18
Copyright © by Embraer S.A. All rights reserved - See title page for details.

15. COMPARTMENT
RECIRCULATION
COMPARTMENT
RECIRCULATION
FILTER
FAN
FAN
FILTER
MF1
T
T
T
F
F
F
F
F
F
F
F
F
FORWARD CABIN
CABIN
F1
MIXER
SAFETY
VALVES
OUTFLOW
VALVES
TO GASPERS
FWD
CARGO
RECIRCULATION
FAN FILTER
RECIRCULATION FAN
RECIRCULATION
FAN FILTER
RECIRCULATION FAN
PRESSURIZED
UNPRESSURIZED
LEFT
ECS
PACK
RIGHT
ECS
PACK
GROUND CONN.
FROM LEFT
BLEED SYS
FROM RIGHT
BLEED SYS
CARGO VENTILATION
CHECK VALVE
CARGO COMPARTMENT
SHUTOFF VALVE
AVIONICS
COMPARTMENT
MID
AVIONICS
COMPARTMENT
FORWARD
COCKPIT
T
AFT CABIN
EM170SDS210085A.DGN AIR CONDITIONING - SCHEMATIC DIAGRAM
AIRCRAFT
MAINTENANCE MANUAL
EFFECTIVITY:
ALL
Embraer 190 - SDS 2327
21-00-00
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16. Training Information PointsCAUTION:THE MODULE OR UNIT CONTAINS ELECTROSTATIC
DISCHARGE SENSITIVE (ESDS) ITEMS. OBEY THE
APPROVED INDUSTRY PRECAUTIONS WHEN YOU
TOUCH, REMOVE, OR INSERT PARTS OR
ASSEMBLIES. DAMAGE CAN OCCUR FROM
ELECTROSTATIC DISCHARGE.
CAUTION:DO NOT TOUCH THE ELECTRICAL PINS OF THE
CONNECTORS. DAMAGE CAN OCCUR TO THE
INTERNAL ESDS COMPONENTS.
The AMS modules must be handled using ESDS (Electrostatic
Discharge Susceptible).
The AMS controller processor modules incorporate a field-loadable
software named Black Label. AIRCRAFT
MAINTENANCE MANUAL
EFFECTIVITY:
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Embraer 190 - SDS 2327
21-00-00
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Copyright © by Embraer S.A. All rights reserved - See title page for details.