Aerosoft CRJ-700 Operation Manual Part 2

	Aerosoft – Digital Aviation				AOM PART 2	VOL	5-1-1
	CRJ-700 CRJ-900				Revision Info	5	26-Jul-2017
	Rev #	Date	Author		Change			Version
	001	11-Oct-15	IV		Start of documentation			0.90
	002	31-Dec-16	MK		Updating to new software			0.92
	003	20- Apr-17	MK		Finalizing			1.00
	004	01-May-17	MK		Updating to latest files			1.00

On behalf of Authority

	Aerosoft – Digital Aviation		AOM PART 2		VOL		5-1-2
	CRJ-70 & CRJ-900		Systems Description		5		26-Jul-2017
	TABLE OF CONTENTS
	AUXILLIARY POWER UNIT .....................................................................................................................							5
	AURAL/VISUAL INDICATING & RECORDING ..........................................................................................							6
	EICAS CONTROL PANEL .....................................................................................................................							7
	DISPLAY REVERSION..........................................................................................................................							8
	AURAL WARNINGS / AUDIO SIGNALS		...............................................................................................					9
	MASTER WARNING LIGHT.................................................................................................................							9
	MASTER CAUTION LIGHT ................................................................................................................							10
	CREW ALERTING SYSTEM (CAS) ..................................................................................................							10
	TAKE-OFF WARNING .......................................................................................................................							13
	LANDING CONFIG WARNING ..........................................................................................................							14
	MENU PAGE ....................................................................................................................................							15
	FLIGHT DATA RECORDER.....................................................................................................................							15
	AUTOMATIC FLIGHT CONTROL SYSTEM..............................................................................................							15
	FLIGHT DIRECTOR............................................................................................................................							16
	FLIGHT MODE ANNUNCIATOR – LATERAL MODES..........................................................................							17
	FLIGHT MODE ANNUNCIATOR – VERTICAL MODES ........................................................................							18
	SYNCHRONIZATION.........................................................................................................................							20
	ALTITUDE ALERT SYSTEM....................................................................................................................							20
	AUTOPILOT .........................................................................................................................................							21
	COMMUNICATIONS ............................................................................................................................							22
	AUDIO CONTROL PANEL .................................................................................................................							22
	INTERPHONE AND INTERCOM CONTROL PANEL.............................................................................							23
	RADIO TUNING UNIT (RTU).............................................................................................................							23
	COMS MENU...................................................................................................................................							24
	TCAS MENU.....................................................................................................................................							24
	BACKUP TUNING UNIT ....................................................................................................................							25
	ELECTRICAL .........................................................................................................................................							25
	ALTERNATING CURRENT, AC SYSTEM .............................................................................................							26
	CONTROLS ON OVERHEAD PANEL ..............................................................................................							28
	EICAS SYNOPTIC PAGE – HOW TO OPEN AC & DC ELECTRICAL SYNOPTIC PAGES .......................							29
	EICAS SYNOPTIC PAGE – ELECTRICAL POWER SUPPLIED FROM ENGINES...................................							29
	EICAS SYNOPTIC PAGE – ELECTRICAL POWER SUPPLIED FROM AIR DRIVEN GENERATOR..........							30
	EICAS SYNOPTIC PAGE – ELECTRICAL POWER SUPPLIED FROM EXTERNAL POWER....................							31
	EICAS MESSAGES.............................................................................................................................							31
	DIRECT CURRENT, DC SYSTEM ........................................................................................................							32
	EICAS MESSAGES.........................................................................................................................							33
	ENVIRONMENTAL CONTROL SYSTEM .................................................................................................							36
	AIR CONDITIONING SYSTEM / PACKS..............................................................................................							36
	ECAM MESSAGES ........................................................................................................................							37
	AVIONICS COOLING SYSTEM .......................................................................................................							37
	ECAM MESSAGES ........................................................................................................................							38
	CABIN PRESSURIZATION SYSTEM....................................................................................................							38
	ECAM MESSAGES ........................................................................................................................							38
	PRESSURIZATION MODES – AUTOMATIC MODES.......................................................................							40
	PRESSURIZATION MODES – MANUAL MODES ............................................................................							40
	SAFETY VALVES ...........................................................................................................................							41
	GROUND VALVE ..........................................................................................................................							41
	CABIN ALTITUDE LIMIT................................................................................................................							41
	EMERGENCY DEPRESSURIZATION...............................................................................................							41

Aerosoft – Digital Aviation		AOM PART 2	VOL	5-1-3
CRJ-70 & CRJ-900		Systems Description	5	26-Jul-2017
EMERGENCY EQUIPMENT...................................................................................................................				42
FIRE PROTECTION ...............................................................................................................................				43
ENGINE FIRE CONTROLS & MESSAGES		............................................................................................		43
ECAM MESSAGE..........................................................................................................................				43
APU FIRE CONTROLS & MESSAGES .................................................................................................				46
CARGO COMPARTMENT FIRE CONTROLS & MESSAGES..................................................................				46
ECAM MESSAGES ........................................................................................................................				46
FIRE SYSTEM TEST ...........................................................................................................................				46
MAIN LANDING GEAR OVERHEAT DETECTION................................................................................				47
FLIGHT CONTROLS ..............................................................................................................................				48
AILERONS........................................................................................................................................				49
RUDDER ..........................................................................................................................................				50
ELEVATOR .......................................................................................................................................				51
HORIZONTAL STABILIZER TRIM .......................................................................................................				52
FLAPS AND SLATS............................................................................................................................				53
SPOILERS .........................................................................................................................................				54
STALL PROTECTION SYSTEM ...........................................................................................................				55
FLIGHT INSTRUMENTS ........................................................................................................................				56
ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS) ..........................................................................				57
DISPLAY REVERSION........................................................................................................................				58
DISPLAY CONTROL ..........................................................................................................................				58
AIR DATA SYSTEM ...........................................................................................................................				59
PITOT STATIC SYSTEM .....................................................................................................................				59
AIR DATA.........................................................................................................................................				59
AIR DATA REFERENCE (ARP) PANELS...............................................................................................				60
ALTITUDE ALERTS............................................................................................................................				63
LOW SPEED CUE..............................................................................................................................				63
AIR DATA REVERSION......................................................................................................................				63
RADIO ALTIMETER SYSTEM.............................................................................................................				64
INERTIAL REFERENCE SYSTEM.........................................................................................................				65
DISPLAY REVERSION....................................................................................................................				66
STANDBY INSTRUMENTS AND CLOCKS ...........................................................................................				67
INTEGRATED STANDBY INSTRUMENT .........................................................................................				67
STANDBY COMPASS ....................................................................................................................				68
CLOCKS........................................................................................................................................				69
FUEL SYSTEM ......................................................................................................................................				70
FUEL TANKS / STORAGE ..................................................................................................................				70
FUEL MANAGEMENT (TRANSFER/CROSSFLOW) & DISTRIBUTION..................................................				70
FUEL QUANTITY GAUGING..............................................................................................................				72
HYDRAULIC POWER ............................................................................................................................				74
ICE & RAIN PROTECTION.....................................................................................................................				77
ICE DETECTION SYSTEM ..................................................................................................................				78
WING AND COWL ANTI-ICE SYSTEM ...............................................................................................				79
AIR DATA ANTI-ICE SYSTEM ............................................................................................................				80
WINDSHIELD AND SIDE WINDOW ANTI-ICE SYSTEM ......................................................................				81
WINDSHIELD WIPER SYSTEM ..........................................................................................................				81
LANDING GEAR ...................................................................................................................................				82
BRAKE SYSTEM................................................................................................................................				83
PARKING BRAKE ..........................................................................................................................				83
BRAKE TEMPERATURE MONITORING SYSTEM............................................................................				84
ANTI-SKID....................................................................................................................................				85
NOSE WHEEL STEERING SYSTEM.................................................................................................				86

Aerosoft – Digital Aviation		AOM PART 2	VOL	5-1-4
CRJ-70 & CRJ-900		Systems Description	5	26-Jul-2017
LIGHTING ............................................................................................................................................				87
COCKPIT LIGHTING..........................................................................................................................				87
PASSENGER COMPARTMENT LIGHTING..........................................................................................				88
EXTERNAL LIGHTING .......................................................................................................................				89
EMERGENCY LIGHTING ...................................................................................................................				91
NAVIGATION SYSTEMS........................................................................................................................				91
FLIGHT MANAGEMENT SYSTEM (FMS) ...........................................................................................				92
WHERE TO FIND THE FMS/CDU AND BASIC LAYOUT ......................................................................				92
PREFLIGHT SETUP AND SEQUENCE OF PAGES ................................................................................				96
GLOBAL POSITIONING SYSTEM (GPS)		..............................................................................................		97
VHF NAVIGATION............................................................................................................................				97
AUTOMATIC DIRECTION FINDER (ADF) .........................................................................................				100
DISTANCE MEASURING EQUIPMENT (DME) .................................................................................				101
AIR TRAFFIC CONTROL TRANSPONDER SYSTEM (ACT)..................................................................				103
TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM (TCAS) .......................................................				104
TRAFFIC ADVISORY (TA) ............................................................................................................				106
RESOLUTION ADVISORY (RA) ....................................................................................................				106
AURAL WARNING......................................................................................................................				107
GROUND PROXIMITY WARNING SYSTEM (GPWS) ........................................................................				107
MODE 1 – EXCESSIVE DESCENT RATE........................................................................................				109
MODE 2 – EXCESSIVE TERRAIN CLOSURE RATE.........................................................................				109
MODE 3 – ALTITUDE LOSS AFTER TAKE-OFF .............................................................................				109
MODE 4 – UNSAFE TERRAIN CLEARANCE..................................................................................				110
MODE 5 – BELOW GLIDESLOPE ALERT ......................................................................................				110
MODE 6 – CALLOUTS (DESCENT BELOW MINIMUM, ALTITUDE CALLOUTS AND BANK ANGLE
ALERT).......................................................................................................................................				110
MODE 7 –WINDSHEAR DETECTION AND ALERTING..................................................................				110
TERRAIN / OBSTACLE AWARENESS ALERTING AND DISPLAY ....................................................				112
WEATHER RADAR (WXR)...............................................................................................................				113
POWER PLANT ..................................................................................................................................				114
THRUST CONTROL.........................................................................................................................				115
FULL AUTHORITY DIGITAL ELECTRONIC CONTROL (FADEC) ..........................................................				117
FLEX POWER .................................................................................................................................				118
AUTOMATIC POWER RESERVE (APR) ............................................................................................				118
HIGH POWER SCHEDULE ...........................................................................................................				119
N1 AND N2 SYNCHRONISATION .....................................................................................................				119
ENGINE OVERSPEED PROTECTION ................................................................................................				119
ENGINE N2 INDICATIONS WHEN USING WING ANTI-ICE ...............................................................				119
STARTING AND IGNITION SYSTEM ................................................................................................				119
OIL SYSTEM ...................................................................................................................................				121
FUEL SYSTEM ................................................................................................................................				122
INTERTURBINE TEMPERATURE (ITT) MONITORING ......................................................................				123
VIBRATION MONITORING .............................................................................................................				123
REVERSE THRUST ..........................................................................................................................				124
PNEUMATICS ....................................................................................................................................				125

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-5
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

AUXILLIARY POWER UNIT

The CRJ700 and CRJ900 are both equipped with an Allied Signal RE 220 (RJ) auxiliary power unit (APU). The APU is technically a gas-turbine and it is used to provide electrical power and even more important compressed air.

The APU is basically comprised of three stages: a compressor followed by a combustion chamber and a turbine. The APU is started by an electrical motor which rotates the APUs main shaft until it gained enough speed so that fuel can be injected into the combustion chamber. The fuel burns and hence tries to expand which accelerates the air even further. The turbine on the other hand drives a generator – so the turbine converts the accelerated airflow into electrical power. As you can see the basic principle of an APU and an aircraft engine are technical the same. The major difference is that the APU is not used to produce thrust therefore APUs are also much smaller than aircraft engines.

Apart from electrical power, bleed air is also drawn from the APU to supply the packs or also the engine starters (the aircrafts engines are usually started with pneumatic air).

Thus, it is mainly use during aircraft preparation and engine start. Nevertheless, it may also be used as a backup once an engine failed / was switched off.

The air-inlet-flap of the APU is used to control airflow into the APU. The flaps position is controlled automatically by the built-in electronics.

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-6
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

AURAL/VISUAL INDICATING & RECORDING

All aircraft systems do have sensors to detect abnormal settings or behaviour. All systems – including the engines – report this information to two central processing units: the data concentrator units (1 & 2). The interface to the pilots is the engine indication and crew alerting system (EICAS). Certain messages do also trigger audio signals or trigger the master warning or master caution light.

The EICAS is comprised of two units – called EICAS Display 1 & 2 (ED1 and ED2) – basically the

left and the right EICAS display: The left EICAS is called ED1 and the right EICAS ED2.

Normally ED1 displays the primary page and ED2 displays the status page. The EICAS control panel on the lower pedestal enables the pilots to select if the primary, the secondary or a synoptic page is displayed on either ED. Please us the display reversion control panels to change whether the primary or secondary is displayed on ED1 or ED2 respectively. The EICAS source selector panel allows the pilot to select where all EICAS information is displayed. You may choose between ED1 or ED2 or both (default).

The EICAS primary page displays the following information:

1.Engine compressor and turbine speeds (N1 and N2 rpm)

2.Engine temperature (ITT)

3.Fuel flow (FF)

Oil pressure and temperature Engine vibration data

4.Landing gear position

5.Slat/flap position

6.Fuel tank quantities and total fuel

7.Crew alerting system (CAS) messages in the form of red warning and amber caution messages

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CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

The EICAS status page displays the following information:

1.Flight control trim indications

2.Auxiliary power unit (APU) indications such as APU RPM, exhaust gas temperature (EGT) and APU inlet door status

3.Pressurization data such as cabin altitude, cabin rate of change, cabin pressure differential, and landing field elevation

4.Oxygen system pressure

5.Brake system temperature readouts

6.Crew alerting system (CAS) messages in the form of green advisory and white status messages

•Aircraft systems synoptic pages (via the EICAS control panel)

See next section for more details

•MENU page (via the EICAS control panel) allows reset of the fuel used indicator and displays the engine oil quantity

See respective section of this chapter.

EICAS CONTROL PANEL

The EICAS Control Panel enables you to open the different aircraft system synoptic pages.

The panel itself is found on the upper pedestal. The following pushbuttons, respective system pages are available:

•PRI: Opens Primary Page (normally displayed on ED1) on secondary display (ED2)

•STAT: Displays Status Page. A second push removes all status messages / open further status messages if several pages of status messages exist.

•Synoptic Pages

o ECS: Opens Environmental Control System page o HYD: Opens Hydraulic system page

o ELEC: Opens Electrical system page o FUEL: Opens Fuel system page

o F/CTL: Open Flight Controls system page o A/ICE: Opens Anti-Ice system page

o DOORS: Opens Door system page

oMENU: Opens the menu page

•SEL: Selector – used to activate a selected item. A change in colour will indicate selection

•CAS: Removes caution messages from primary display. Previously invisible messages get displayed

•UP: Controls cursor

•DN: Controls cursor

•STEP: Steps through pages of secondary page if available

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-8
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

DISPLAY REVERSION

In case EICAS display ED1 fails, ED2 will automatically switch to primary page. In case EICAS display ED2 fails, there is no automatic switch. With either display failed, the EICAS control panel is rendered inoperative. Please switch the EICAS selector on the SOURCE SELECTOR PANEL to the operative display (ED1 or ED2). This reenables you to select and display the EICAS information on the selected display.

Furthermore, a revisionary panel is installed on either pilot’s side panel. They offer three positions:

•PFD 1, respective PFD 2

Switches the respective primary flight display (PFD1 = pilot, PFD 2 = co-pilot) to the adjacent MFD.

•NORM

PFD and MFD in normal operation

•EICAS

Shows the EICAS ED1 display on the MFD.

		Aerosoft – Digital Aviation			AOM PART 2		VOL	5-1-9
		CRJ-70 & CRJ-900			Systems Description		5	26-Jul-2017
		AURAL WARNINGS / AUDIO SIGNALS
		The following table shows the available aural warnings / audio signals.
		Sound	Indication
		Warbler	Stall
		Windshear	Windshear
		Whoop – Whoop	GPWS (excessive descent or closure rate)
		Fire bell	Fire warnings
		Clacker	Excessive stabilizer trim Movement
			VMO/MMO exceedance
			Airspeed too high for current flap setting
		Cavalry Charge	Autopilot disconnect
		Horn	Gear warning (not down)
		Triple chime	Warning tone (indicates an aircraft system voice advisory)
		C-chord	Altitude alert
		Single chime	Caution tone (indicates an aircraft system voice advisory)

Faulty aural warnings may result from a defective DCU. There are two guarded pushbuttons on the co-pilots side panel – called the audio warning panel – to switch off the affected DCU. Open the guard and press the pushbutton to deactivate the DCU. Switching a DCU off triggers respective EICAS messages and the pushbutton will illuminate white.

MASTER WARNING LIGHT

There is a master warning light on either side – the pilot’s and the co-pilot’s side. In case a warning is triggered, both lights come on and stay flashing if the warning exists or the warning light is pushed by the pilot or copilot. The aural warning and flashing light stay off until the next warning is triggered.

In the following cases the aural warning may not be muted:

•Stall warbler

•Stabilizer trim clacker

•GPWS/TCAS (voices and aural)

•AP Disconnect cavalry charge

•Overspeed clacker

•Configuration warnings

•Flap clacker

•Gear Horn

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-10
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

MASTER CAUTION LIGHT

Positioned right next to the master warning light is the master caution light. It works the same way the master warning light does.

In the following two cases the master caution may not be muted:

•GPWS and TCAS voice alerts

•Altitude alert (C-chord) aural

CREW ALERTING SYSTEM (CAS)

All warning / caution messages are sorted by priority / urgency and order of occurrence. The CAS works with four categories of messages, with different colour codes and behaviour, indicated in the following table.

In case the triggering condition / fault is removed the message will disappear from the EICAS again. New messages are added on top according their priority / category.

If the number of message exceeds the available lines in the EICAS, the message “PAGE 1/2” appears in red. All further messages are available on the following page(s). Press the CAS button to access the messages on the second side.

When messages are excluded from view by pressing the CAS button a “MSGS” message appears in the EICAS reminding the crew of the excluded messages. Same goes for advisories and status messages on the STAT page.

Category	Aural	Master warning /	Color	Sort order	Displayed	Removeable
	Warning	master caution	code		on ED1 /	from EICAS?
					ED2
Warning	Triple chime	Master warning	Red	top	ED1	No
	Or voice
Caution	Single chime	Master caution	amber	Below	ED1	Yes – CAS
				warnings		button
Advisory	No	No	Green	Top of ED2	ED2	No – unless
						condition is
						removed
Status	No	No	White	Below	ED2	Yes – STAT
				advisory		button

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-11
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

To reduce information during flight phases with high stress level, the DCUs filter information:

Inhibit	Inhibit is enabled when:		Inhibit is removed when:
Initial take-off	•	Left and right engine N1 is greater than	•	Left and right engine N1 is less than
		79%,		67.6%, or
	•	weight-on-wheels, and airspeed is less	•	Airplane is in the final take-off phase
		than 100 knots.
Final take-off	•	Left and right engine N1 is greater	•	Left and right engine N1 is less than
		than 79%, and		67.6%, or
	•	airspeed transitions to greater than	•	Radio altitude is greater than 400 ft
		100 knots.		AGL, or
			•	30 seconds after ground to air
				transition.

	Aircraft System	Warning Message					Aural
		(Inhibited during take-off)					(Inhibited during take-off)
	Environmental Control						CABIN ALT Cabin Pressure
	System
	Flight Controls						Overspeed Clacker
	Landing Gear	•	GEAR DISAGREE				•	Gear Disagree
								Nose Door
		•	NOSE DOOR OPEN				•
Landing	• Radio altitude transitions to less than				•	30 seconds after air to ground
	400 ft AGL, and					transition or
	• landing gear down and locked.				•	Radio altitude transitions from less
						than 400 ft to greater than 400 ft.
	Aircraft System	Warning Message					Aural
		(Inhibited during take-off)					(Inhibited during take-off)
	Auxiliary Power Unit	APU OVERTEMP					APU
	Doors	PASSENGER DOOR					Door
	Environmental Control	•	CABIN ALT				•	Cabin Pressure
	System	•	DIFF PRESS				•	Cabin Pressure
	Ice and Rain Protection	• ANTI-ICE DUCT					•	Anti-Ice Duct
								Anti-Ice Duct
		• L COWL A/I DUCT					•
								Anti-Ice Duct
		• R COWL A/I DUCT					•
								Wing Overheat
		•	WING OVHT				•
	Landing Gear	NOSE DOOR OPEN					Node Door
	Power Plant	• L ENG OIL PRESS					•	Engine Oil
		• R ENG OIL PRESS					•	Engine Oil

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-12
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

In a similar fashion the cautions are inhibited as well. There are several caution messages which are not inhibited though:

Airplane system	Caution message (not inhibited)
Automatic Flight Control System	YAW DAMPER
Auxiliary Power Unit	APU LCV CLSD
Fire Protection	FIRE SYS FAULT
Flight Controls	•	GLD NOT ARMED	•	PITCH FEEL
				RUD LIMITER
	•	GLD UNSAFE	•
				SLATS FAIL
	•	GND SPLR DEPLOY	•
				SPOILERONS ROLL
	•	IB (OB) FLT SPLRS	•
				STAB TRIM
	•	IB (OB) GND SPLRS	•
				STAB TRIM LIMIT
	•	IB (OB) SPOILERONS	•
			•	STALL FAIL
Flight Instruments	EFIS COMP MON
Hydraulic Power	HYD 1 (2) (3) LO PRESS
	•	ICE	• L (R) COWL A/I OPEN
			• L (R) WING A/I
	•	ICE DET FAIL
Landing Gear	•	A/SKID INBD (OUTBD)
	• IB (OB) BRAKE PRESS
	•	PROX SYSTEM
	•	WOW INPUT (OUTPUT)
Pneumatic	• ANTI-ICE DUCT
	• L (R) BLEED DUCT
	• L (R) COWL LOOP
Power Plant	• L (R) ENG FLAMEOUT
	• L (R) ENG SRG CLSD
	•	L (R) FADEC
	• L (R) FADEC OVHT
	• L (R) REV INOP
	• L (R) REV UNLOCKED
	• L (R) REV UNSAFE

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-13
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

TAKE-OFF WARNING

A lot of aircraft do have take-off configuration warning. The actuals aircraft is checked according a pre-defined logic and in case a deviation is recognized, the crew is informed. The CRJ does this automatically as soon as the engines are accelerated beyond 70% N1.

The following systems / conditions are checked:

Condition	Voice Message	EICAS Message
Autopilot engaged	Config autopilot	CONFIG AP
Flaps not in take-off position	Config flaps	CONFIG FLAPS
All spoilers not in take-off position	Config spoilers	CONFIG SPLRS
(down)
Horizontal stabilizer outside take-off	Config trim	CONFIG STAB
range (green band)
Parking brake set	Config Brakes	PARKING BRAKE SET
Rudder trim outside of take-off	Config trim	CONFIG RUDDER
range (trim > ±1 degree)
Aileron trim outside of take-off range	Config trim	CONFIG AILERON
(trim > ±1 degree)

If the aircraft detects a deviation it is considered unsafe for take-off. Aural and warning messages will indicate if such a condition is detected. Furthermore, both MASTER WARNING lights come on.

As soon as the triggering system is corrected, the warning is silenced.

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-14
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

LANDING CONFIG WARNING

Like the take-off configuration the landing configuration is automatically checked, too. A deviation will be indicated by the landing gear horn. Two minutes after lift-off (ground to air transition) the mechanism is armed and will sound if one of the following conditions exists:

•Radio altitude < 500 ft

•Both throttles at less than maximum landing setting OR

•Flaps > 30°

OR

•Both throttles at less than maximum landing setting OR

•Any one throttle is at IDLE with the landing gear warning horn muted

AND

•Airspeed < 170 kts

•Flaps > 30° OR

•Airspeed < 190 kts

•Flats / slats = 0

AND

•Radio altimeter OR throttle is not valid

OR

•Radio altitude is less than 1000 ft AGL

•vertical speed less than -400 ft/min

AND

•No windshear warning or a windshear warning with a windshear monitor failure

OR

•Radio altitude is less than 1000 ft AGL

•vertical speed OR GPWS not valid

The “Too low gear” aural warning is heard if:

•any landing gear is not down and locked

•radio altitude less than 500 ft AGL

•indicated airspeed at less than 190 knots.

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-15
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

MENU PAGE

The MENU page is divided into three sections: menu section, confirmation section and parameter readout. A cursor on the left side of the screen is controlled by the UP/DN buttons on the EICAS control panel (ECP). The SELECT button on the ECP is used to select a line item.

The menu list contains a single FUEL USED RESET line. When the line is selected, the ACCEPT/CANCEL selections in the confirmation section are used to accept or cancel the request to reset to zero the “Fuel Used” indication, on the FUEL synoptic page.

The parameter readouts section contains the engine OIL LEVEL indications.

FLIGHT DATA RECORDER

Real aircraft are equipped with flight data and voice recorders. The CRJ’s flight data recorder saves different information for 25hrs of flight. The FDR automatically starts recording as soon as the BEACON light, STROBE light is switched ON or a take-off-like condition is detected via the wheels. In case the pilots want to mark a certain event, they can push the FDR event button for 2 seconds and a timestamp is saved.

The voice recorder saves the last 120 minutes of cockpit communication and passenger announcements as soon as the aircraft is powered up.

AUTOMATIC FLIGHT CONTROL SYSTEM

The automatic flight control system consists of several systems:

•Flight Director

•Autopilot

•Flight control computers

•Two yaw dampers

•Automatic elevator trim

•Servos / actuators

The flight director computes a flight path which needs to be followed to archive certain pre-set constraints (i.e. climb at a pre-defined speed to a pre-set altitude). The autopilot computes the required flight control’s

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CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

deflections / trim adjustment to archive the commanded flight path. The flight control computers, FCCs, calculation are based on data from the inertial reference system and air data computers.

Further input sources are selections made on the flight control panel, flight management computer outputs and radio system outputs.

FLIGHT DIRECTOR

At this point we like to emphasize the difference between the flight director and the autopilot again. The flight director indicates the needed attitude to archive a pre-set flight path based on selected mode by means of two cross-hair bars or a v-shaped indication on the PFD’s attitude direction indicator. The flight director does not control any actuator, flight controls, engine parameters or such to follow the flight path. It is solely for indication.

The autopilot on the other hand controls the flight control’s servos and actuators to make the aircraft fly along the pre-set flight path in accordance with the programmed modes. Basically, the autopilot will do everything needed to follow the flight director.

Bear in mind that the CRJ has no auto throttle – during take-off, climb and go-around you get help from the FADEC and fixed throttle detents (see later chapters) but especially during descent and levelling off after descent you must monitor speed closely and adjust thrust as necessary.

The programmed / selected modes are split up in lateral and vertical modes and are presented on the PFD on top of the attitude direction indicator. The following section introduces and explains the available modes.

Click the FD pushbutton to activate and deactivate the flight director. Dave allows you to select different types of flight directors as this differs between companies.

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-17
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

FLIGHT MODE ANNUNCIATOR – LATERAL MODES

Mode	Commanded attitude	Annunciation	Select	Cancel
Take-off	On ground: wings level		TOGA button	Synchronize FDs
mode	After lift-off: heading hold		on thrust	Select different
	Bank angle ≤ 5°		lever	lateral mode
Navigation	Capture and follow a track to a	Nav source	NAV button
mode	navigation source	„VOR1/2,
		LOC1/2 or
		FMS1/2“
		illuminates in
		green
Heading	Capture and hold selected heading	Green HDG	Push HDG	Select different
select		message	knob	lateral mode
mode
Back	Capture and hold selected back	Green B/C ½	Push B/C	Push B/C switch
course	course	message	switch	again or selecting
mode				another lateral
				mode
Roll mode	Holds the existing heading. Given	Green ROLL	Roll mode is	Selecting any
	the roll angle upon initiation was	message	selected	other lateral
	not over 5°		automatically	mode
			if no other
			lateral mode
			is active
Half bank	Reduces maximum bank angle by	White ½ BNK	Push ½ BANK	Pushing ½ BANK
mode	50%	message	switch or	again
			climbing
			through
			31,600ft
Lateral go-	Heading Hold command, 5° bank	Green GA	Press of	Selecting
around	limit, clears all other modes, turns	message	TOGA button	Synchronization
mode	on both flight directors and turns		on thrust	or selecting
	off the autopilot		lever	another lateral
				mode
Approach	Commands to capture and track	Green message	Press APPR	Press APPR
mode	the selected navigation source. In	of the used	switch.	switch again,
	case no valid navigation source is	navigation		selecting another
	received, the mode arms but	source: VOR ½,		lateral mode,
	tracking won’t work. Automatically	LOC ½, FMS ½.		changing nav
	selects glideslope mode			source

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-18
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

FLIGHT MODE ANNUNCIATOR – VERTICAL MODES

Mode	Commanded attitude	Annunciation	Select	Cancel
Vertical	Generates a fixed pitch-up	Green TO	Press of TOGA	Press TOGA switch
Take-off	command (pitch angle depends	message	button on thrust	again
mode	on take-off speed and difference		lever	Engage autopilot
	between V2 and VR – loss of an			Select
	engine reduces commanded			synchronization
	pitch)			Select another
	clears all other modes, turns on			active mode
	both flight directors and turns
	off the autopilot
Pitch	Command to maintain pitch	Green PTCH	Pitch mode is	Selecting a vertical
mode	angle at activation.	message	automatically	hold mode
	Reference value may be altered		selected when	Selecting a vertical
	using the VS pitch wheel (1/2-		the flight	mode capture
	degree change per click).		director is
	When preselecting an altitude –		activated.
	altitude preselect mode must be		Rotating the VS
	activated before activating pitch		pitch wheel also
	mode		activates the
			pitch mode
			(unless in
			glideslope
			capture or VS
			mode)
Altitude	Generates commands to	Green ALT	Press ALT switch	Press ALT switch
Hold	capture and hold selected	message		again
mode	altitude.			Selecting a vertical
	When the mode is selected, it			hold mode
	sets the current altitude as			Vertical mode
	reference.			capture
Altitude	Generates commands to	Annunciated	It is	Cleared by
preselect	capture and maintain a	by white ALTS	automatically	glideslope capture
mode	preselected altitude. The	message.	selected as soon	or altitude capture
	preselected value is displayed	Alt capture is	as any vertical	and switching to
	on the PFD.	indicated by	mode (except	altitude hold mode.
	The capture point depends on	green ALT CAP	glideslope
	the closure rate.	message.	capture) is
	In case the altitude is reselected		activated.
	during altitude capture (within
	200ft of the preselected
	altitude), the flight director will
	ignore the new setting and
	capture the preselected
	altitude.
	As soon as altitude is captured,
	the flight director switches to
	altitude hold mode.
Speed	Commands pitch in order to	IAS CLB or IAS	Push the SPEED	Selecting another
mode	capture and maintain and	DES	knob	vertical capture
(CLB, DES,	preselected airspeed.			mode
IAS)	Speed is selected by turning the			Deactivate autopilot
	speed knob.			and flight director.

Aerosoft – Digital Aviation

AOM PART 2

VOL

5-1-19

CRJ-70 & CRJ-900

Systems Description

5

26-Jul-2017

As soon as the autopilot is

Capture of

activated or synchronization is

preselected altitude

activated the current airspeed is

automatically

selected as the reference speed.

deactivates speed

mode.

Vertical

Generates commands to

Green

Push the VS

Push VS switch

speed

maintain and preselected

VS #.# or

switch

again.

mode

vertical speed.

VS #.#

Selecting a different

The selected vertical speed is

The #.# shows

vertical mode

displayed on the PFD and may

the current

Capture of

be selected in a range of ±

vertical speed

preselected altitude

12,000 ft/min using the pitch

in thousands

automatically

wheel.

of feet/minute

deactivates vertical

As soon as the autopilot is

speed mode.

engaged or synchronization

selected, the reference vertical

speed is set to the current

vertical speed.

In case a new altitude is

preselected, the altitude must

be preset before activating VS

mode.

Glideslope

Generates commands to

Green GS

Glideslope mode

Turning outbound

mode

capture and follow a glideslope

message

is activated

or dialling in a

signal. Capture may be

automatically,

different navigation

performed from above and

when APR mode

source, deactivating

below the glideslope.

is active, the

APP mode clears

aircraft is flying

glideslope mode.

towards

(inbound) a

navigation

source with a

valid glideslope

signal.

Vertical

Fixed pitch-up command. The

Green GA

Press TOGA

Engaging the

go-around

commanded pitch angle

message

switch on thrust

autopilot.

mode

depends on if both engines are

lever

Selecting

running or one engine is

synchronization.

inoperative.

Selection /

Activation automatically turns

capturing or

on both flight directors

another active

disengages both autopilots and

mode.

clears all other modes.

The resulting autopilot

disengagement warning sound

may be cancelled by pressing

the TOGA switch again.

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-20
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

SYNCHRONIZATION

Synchronization enables you to synchronize the flight director bars with the current flight attitude.

The Sync switch on the yoke is not simulated (because it is hidden on the backside of the yoke), so you must use the standard key assignment “flight director synchronization”. Please note this standard key is NOT assigned in FS/P3D so you must

assign a key to it before it can be used. We used [control]-[shift]-[s].

It has no effect in case the autopilot is engaged and only certain lateral and vertical modes allow synchronization:

•Lateral

•Bank mode

•Vertical

•IAS mode

•MACH mode

•VS mode

Synchronization is annunciated by an amber SYNC indication on the

PFD. The message disappears after 3 seconds.

ALTITUDE ALERT SYSTEM

The pilots are notified on the PFD in case they are reaching / leaving a preselected or selected altitude. The respective advisories are all displayed on the PFD but in two different places:

•The readouts and bugs change colours and state according the following rules:

•Approx. 1,000ft before reaching a preselected altitude an aural warning for approx. 1 second is sounded, and the readout and bugs flash in magenta for approx. 4 seconds

•Within 200ft of the (pre-)selected altitude the readout and bugs come steady to indicate altitude capture

•In case the aircraft deviates for more than 200ft from the selected altitude after capture, a 1 second tone will sound and the readout and altitude bugs will start to flash amber (and continue if the deviation occurs or the warning is cancelled by pressing the ALT switch or selecting a different altitude)

•In case the aircraft is 200ft below the selected altitude the flashing magenta bugs and readout will cancel

•If the aircraft deviates further (± 1,000ft) from the selected altitude a 1 second tone sounds

•As soon as the aircraft is again within 200ft of the selected altitude the readout and bugs will cease to flash

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-21
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

AUTOPILOT

The installed autopilot is a two-axes, digital, fail-passive autopilot. It commands input to the ailerons, elevators and rudder via the flight control computers, FCCs.

To activate the autopilot the following requirements need to be fulfilled:

•All flight control computers (FCC) are operative

•At least one channel of horizontal trim is available

•At least one yaw damper is engaged

•At least one IRS system is available

•At least one air data computer (ADC) is available

•No significant instability of the aircraft

When flying through turbulent weather autopilot’s corrective signals might reduce passenger comfort. By selecting the turbulence mode, the intensity of signals is reduced to smooth aircraft motion. Turbulence mode is automatically cleared as soon as a localizer is captured. The autopilot is activated with the AP ENG pushbutton and can be deselected by the AP DISC push bar.

The autopilot can also be disengaged by any of the following controls.

1.Push AP/SP DISC switch on control when – this equals the autopilot disengage button / key assignment within FS.

2.Push the AP ENG switch on the flight control panel

3.Lower the AP DISC switch-bar on the right flight control panel

4.Operating the stabilizer trim

5.Pressing the TOGA switch on the thrust levers

6.Disengaging yaw damper by pressing the DISC pushbutton on the yaw damper panel

Disengagement of the autopilot is indicated by an aural warning (cavalry charge) and the AP indications on the PFDs turns red. After two repetitions of the cavalry charge the warning is cancelled automatically.

Automatic disengagement of the autopilot occurs:

•In case both yaw dampers are disengaged or fail

•In case a failure in the FCC monitoring circuit is detected (not simulated)

•In case a stall warning is triggered

•During a windshear and the subsequent clearance procedure.

It automatically disconnects approx. 2 seconds after the windshear warning

In case the autopilot is disengaged automatically, the following warnings (aural and flashing red AP indication on the PFD) may be cancelled by pressing the AP/SP DISC switch or either TOGA switch.

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-22
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

COMMUNICATIONS

Some parts of the communication systems cannot be modelled and are not integrated in this package like the crew / passenger addressing system, boarding music system, external communication panels, attendant headsets or similar. So, the communication system basically consists of the

•Audio control panel

•Interphone panel on the centre pedestal

•Intercom control panel

•The radio tuning units

AUDIO CONTROL PANEL

The audio control panel is part of the audio integrating system. The audio integrating system provides display and control for all incoming and outgoing audio signals of the aircraft’s navigation and communication system.

Three audio control panels are the interface between the crew and the audio integrating system.

1.Transmit Selector: Selects the communication system, only one can be active.

2.Receive pushbuttons: Click to select and deselect.

3.Voice/Both: At voice only the voice transmissions are audible, at both voice and station indentification are audible.

4.DME Ident selector: Press to select

5.ADF Ident selector: Press to select

6.NAV Ident selector: Press to select

7.MKR Ident selector: Press to select

The other functions are not simulated.

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-23
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

INTERPHONE AND INTERCOM CONTROL PANEL

The interphone panel on the centre pedestal is part of the ground crew interphone. The ground crew interphone is used to establish communication between crew inand outside of the aircraft (like during pushback, engine start, aircraft maintenance). Hence there are several

panels in and outside the aircraft to establish communication. The interphone panel on the pedestal is the only one modelled and as the counterparts are missing as outside crew there is no function associated with the ground crew call button which is normally used to establish communication to an outside crew.

The intercom control panel is used for in-airplane- communication and it faces similar limitations like the interphone panel. It is not simulated, on the real plane, it offers four modes of communication:

•PA: Used to address passengers – turns green when activated / pushed

•CHIME: Sounds a chime in the cabin

•CALL: Sounds a chime in the cabin and enables intercom to the flight attendants – turns green when activated / pushed

•EMER: Used for emergency calls from the flight deck to the flight attendants – flashed in amber when activated / pushed

RADIO TUNING UNIT (RTU)

Two VHF (very high frequency) communication systems provide AM (amplitude modulation) voice communication with ground stations and other aircraft. They operate in a range from 118.000 to 136.975 MHz They are tuned by via the radio tuning units in normal operation and in case both RTUs fail a backup tuning unit provides tuning for communication system 1.

The radio tuning units, RTU, are associated with the side they are installed on. Hence the left RTU controls COM 1 and NAV 1 and the right RTU controls COM 2 and NAV 2.

1.FREQUENCY READOUT: The current active frequency is shown in green

2.SELECT KEY: Push once to directly tune the active frequency, push twice to open COM main page

3.TUNING WINDOW: The while box indicates the frequency that can be adjusted

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-24
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

4.PRE /RECALL: PRE-indicates the frequency was changed, RECALL indicates the frequency was swapped with the active frequency

5.PRE-SET FREQUENCY: The Preset frequency (shown in white) can be swapped with the active frequency

6.FREQUENCY SWAP: Push to swap active with Preset

7.ADJUST FREQUENCY: in 25 kHz steps (COM) or 50 kHz steps (NAV)

8.ADJUST FREQUENCY: in 1 MHz steps

9.IDENT: Sends ATC Ident

10.DME-H: Locks frequency for DME measuring.

11.1/2: Swaps COM1/NAV1/ADF1 with COM2/NAV2/ADF2

12.TCAS: Push to open TCAS menu

COMS MENU

The COMS menu can be accessed by double clicking the COM select button (see #2 in previous image). It allows the toggling of Squelch.

TCAS MENU

The TCAS menu can be opened with the TCAS select button (see #12).

1.MODE: switch between Auto, Standby and Traffic Advisory Only

2.ALT: Toggles between relative (difference in altitude between aircraft and target) or absolute altitude display

3.TEST: Runs a test program

4.RETURN: back to main RTU menu

5.TRAFFIC: toggles display of traffic symbols on MDF

6.ABOVE: Shows traffic above altitude (can be selected with BELOW)

7.NORM: Standard display

8.BELOW: Shows traffic below altitude (can be selected with ABOVE)

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-25
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

BACKUP TUNING UNIT

The backup tuning unit provides a spare / backup in case both RTUs fail. Normally the backup tuning unit stays in standby mode the entire flight. As soon as it is switched on it takes control of COM1 and NAV 1.

1.RTU INHIBIT: Disables either RTU

2.FREQUENCY DISPLAY: Shows COM1 (upper) and NAV1) lower, TX is displayed to indicate transmission

3.TUNING SELECTOR: Toggles between tuning COM1 and NAV1

4.FMS TUNE INHIBIT: Stops FMS Autotune function

5.ATC SEL: To select the active transponder

6.MODE SELECTOR:

a.OFF: Display off

b.STB: Displays the frequency shown in RTU1

c.ON: Frequency is controlled by the tuning knob

d.SQ OFF: Squelch selected off

7.TUNING KNOB: To set frequency

ELECTRICAL

The CRJ’s electrical system can be split into an alternating current, AC, subsystem and a direct current, DC, subsystem. The alternating current, AC system is supplied with power from the engine generators (integrated drive generators, IDGs), the auxiliary power unit’s generator or the air driven generator, ADG (which is a backup in case both IDGs fail). The direct current, DC, system is supplied with power from two transformer rectifier units, TRUs, the main battery, or the APU battery. The TRUs convert alternating current to direct current. To reload both batteries, battery chargers are installed as well.

Both subsystems use computers to ensure the proper power distribution to the respective systems. The following table shows the available AC and DC busses.

AC busses		DC busses
•	AC BUS 1	•	DC BUS 1
•	AC BUS 2	•	DC BUS 2
•	AC ESSENTIAL BUS	•	DC ESSENTIAL BUS
•	AC SERVICE BUS	•	DC SERVICE BUS
•	ADG BUS	•	DC BATTERY BUS
		•	DC EMERGENCY BUS
		•	DC UTILITY BUS
		• MAIN BATTERY DIRECT BUS
		• APU BATTERY DIRECT BUS

Furthermore – when on ground – an external power receptacle is available which allows the CRJ to be supplied with ground power. The electrical power panel on the overhead panel is used to control the electrical systems. Error messages, warning or advisories are indicated on the EICAS.

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-26
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

ALTERNATING CURRENT, AC SYSTEM

During normal operation, the IDGs supply alternating current. The APU may be used as a backup in case both IDGs fail. In case even the APU fails, the CRJ is equipped with an Air Driven Generator, ADG, which is basically a propeller which is extended into the airstream. The ADG can provide enough power for the most important aircraft systems to be still able to fly the aircraft.

The IDGs are monitored regarding temperatures, oil pressure and supplied power. In case of exceedances the affected IDG can be disconnected automatically. Nevertheless, there is also a possibility by means of a switch light on the electrical power panel, to disconnect the IDG manually.

Please bear in mind that a disconnected IDG (no matter if disconnected automatically or manually) can only be reconnected on ground. Please open Dave, go to the “Services / Maintenance” page to reconnect the IDG. Disconnected IDGs are displayed in blue. Press on “Reconnect” and “Save” to reconnect.

Before disconnecting you may try to reset the IDG by switching the generator switch on the electrical control panel to OFF/RESET and then back to ON.

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-27
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

The following table shows the power distribution in the AC system for normal operation:

	AC BUS 1		AC BUS 2		AC ESSENTIAL
•	Flight Recorder Power	•	TRU 2	•	Essential TRU 1
•	TRU 1	•	Essential TRU 2	• Display Cooling Fan 1
•	Main Battery Charger	•	Recirculating Fan 2	• Avionics Cooling Fan 1
•	Recirculating Fan 1	•	Galley Exhaust Fan	•	Crossflow Pump
•	Display Cooling Fan 2	•	Galley Heater	•	Left Pitot Heater
•	Lavatory Exhaust Fan	•	Slats and Flaps	•	Standby Pitot Heater
•	Baggage Compartment		Channel 2	•	Left AOA Heater
•	Heater	• Pitch Trim Channel 2		•	Ice Detector 1
•	Slats and Flaps	•	Hydraulic Pumps 3A	•	Left Window Heater
	Channel 1		and 1B	•	Cabin Ceiling Lighting
•	Pitch Trim Channel 1	•	Right Windshield	• CB Panel Integral Lights
•	Hydraulic Pumps 3B		Heaters	• Pilot Panel Integral Lights
	and 2B	•	Right Window Heater	•	Overhead Panel Integral
•	Hydraulic System Fan	•	Ice Detector 2	•	Lights
•	Left Windshield Heater	•	Co-pilot Panel Integral	• Centre Panel Integral Lights
•	TAT Probe Heater		Lights	• Traffic Alert and Collision
•	Right AOA Heater	•	Inertial Reference Unit	•	Avoidance System (TCAS)
•	Right Pitot Heater		Fan	•	Engine Ignition A
•	Enhanced Ground
	Proximity
•	Warning System
	(EGPWS)
•	Engine Vibration
	Monitor
• Avionics Cooling Fan 2
•	ADG Heater

	AC SERVICE BUS		ADG BUS
•	APU Charger	•	Hydraulic Pump 3B
•	Logo Lights	•	Pitch Trim 2
•	Cabin Sidewall Lighting	• Slats and Flaps #1
•	Cabin Ceiling Lighting	• Slats and Flaps #2
•	Toilet
•	Water System

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-28
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

CONTROLS ON OVERHEAD PANEL

1.DC SERVICE: Connects the DC service bus to the APU battery direct bus

2.BATTER MASTER: Used to supply the battery bus with power from the APU or main direct busses. Always ON in flight!

3.AC: External Power toggle

-AVAIL indicates connected source

-IN USE indicates AC busses are connected to external power unit

4.IDG1/2 DISCONNECT: Open guard and press push button to disconnect IDG1 (reconnect on ground only!)

-DISC (white) indicates IDG is disconnected

-FAULT (amber) indicates low oil pressure or high temperature

5.AC ESS XFER: Switches essential bus feed from AC bus 1 to AC bus 2, switches automatic in case of IDG1 failure

-ALTN (white) indicates essential bus is fed from AC bus 2

6.GEN 1: Used to switch generators between AUTO and OFF

7.AUTO XFER: Disables automatic transfer of respective IDG

-OFF indicates autotransfer is deactivated

-FAIL indicates a fault is preventing autotransfer

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-29
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

EICAS SYNOPTIC PAGE – HOW TO OPEN AC & DC ELECTRICAL SYNOPTIC PAGES

The AC and DC electrical synoptic page is opened via the EICAS control panel by pressing the ELEC key (1) once to open the AC electrical synoptic page and twice to open the DC electrical synoptic page.

EICAS SYNOPTIC PAGE – ELECTRICAL POWER SUPPLIED FROM ENGINES

On the EICAS Electrical displays the green flow lines show energized busses, white lines show not energized busses.

EICAS DIGITAL	GREEN	AMBER	WHITE	HALF INTENSITY AMBER	AMBER
READOUT					DASHES
XXX kVA	Generator	Generator	Generator not	Insufficient data	Invalid data
	loaded	overload	loaded
XXX V	Voltage in	-	Voltage not in	Insufficient data	Invalid data
	range		range
XXX HZ	Frequency	-	Frequency not	Insufficient data	Invalid data
	in range		in range

EICAS OUTLINE	GREEN	AMBER	WHITE	HALF	HALF
				INTENSITY	INTENSITY
				AMBER	CYAN
	Bus powered	Bus not	-	Invalid data	-
		powered or
		voltage low
	Generator on	Generator off	Both	Invalid data	-
		with engine /	generator and
		APU running	engine / APU
			are off
	Constant speed	Low oil	Engine is off or	Invalid data	-
	drive on	pressure or	IDG is
		high oil	disconnected
		temperature
	-	-	Engine / APU	Invalid data	Engine / APU
			off		running and
					ready to load

Aerosoft – Digital Aviation	AOM PART 2	VOL	5-1-30
CRJ-70 & CRJ-900	Systems Description	5	26-Jul-2017

EICAS SYNOPTIC PAGE – ELECTRICAL POWER SUPPLIED FROM AIR DRIVEN GENERATOR

EICAS DIGITAL READOUT	GREEN	WHITE	AMBER DASHES
XXX V	Between 108 and 130	Less than 108 or more	Invalid data
	volts	than 130 volts
XXX HZ	Between 360 and 440 Hz	Less than 360 or more	Invalid data
		than 440 Hz

EICAS OUTLINE	GREEN	WHITE
	ADG outline green	ADG outline white
	Voltage and frequency digital	Voltage or frequency digital
	readouts green	readouts white