Pinnacle Airlines Crj-200 Overhead Panel

Front 1

ELECTRICAL POWER PANEL

DC SERVICE SWITCH

Back 1

Used by Mx and Gnd Personnel
Operates Nav, Lav, and Dome
Powers DC Sevice Bus

Front 2

ELECTRICAL POWER PANEL

BATTERY MASTER switch

Back 2

2 Batteries
Main 17 Amps
APU 43 Amps
5 minute limit due to CRTs
NICAD
Batteries 24v
DC System 28v
22v Min for Engine Start

Front 3

ELECTRICAL POWER PANEL

EXT DC power switchlight

Back 3

AVAIL: Correct voltage and polarity

Front 4

ELECTRICAL POWER PANEL

EXT AC power switchlight

Back 4

AVAIL: Correct Phase-3, Frequency-400Hz, Voltage-115v

Front 5

ELECTRICAL POWER PANEL

IDG 1 and IDG 2 switchlights

Back 5

Press when directed by QRH
Cannot be reset in flight
Reset by Mx personnel on ground
FAULT: HOTLOP
High Oil Temp
Low Oil Press
DISC: OO
Over-Temp
Over-Torque

Front 6

ELECTRICAL POWER PANEL

AC ESS XFER

Back 6

AC Ess Bus 1 is not powered by normal source (when illuminated)

Normally powered by AC Bus 1 Auto and Manual

Press when directed by QRH

Front 7

ELECTRICAL POWER PANEL

GEN 1, GEN 2, GEN 3

Back 7

All Generators 12,000 RPM

APU Generator by APU(APU ECU)

GEN 1 and GEN 2 by CSD

Front 8

ELECTRICAL POWER PANEL

AUTO XFER switchlights

Back 8

"OFF" = "Inhibit"
Inhibits Auto Transfer (Priority Logic)

FAIL: Generator Over-Current or Bus Fault

Auto and Manual
Press when directed by QRH

Front 9

ELECTRICAL POWER PANEL

TIE 1 (TIE 2) switchlights

Back 9

TRUs 100 Amp, can only power 2 busses

If illuminated:
TRU 1(2) has failed
DC Service TRU is powering Buss 1(2)
Utility Buss 1(2) is shed
Request DC Synoptic Page
Auto and Manual
Press when directed by QRH

Front 10

ELECTRICAL POWER PANEL

ESS TIE switchlight

Back 10

Request DC Synoptic Page
Manual Only
Press when directed by QRH
Decision Tie-"After referencing the QRH, the decision will be made to press or not press"

Ties Service TRU to DC Essential buss when ESS TRU 1 and ESS TRU 2 fail (can only power L or R side)

Front 11

EXTERNAL LIGHTS PANEL

BEACON

Back 11

If not turned on within 5 minutes of both engines started:
FDR (Flight Data Recorder) Fail Status Message

Front 12

LANDING/TAXI LIGHTS PANEL

LANDING LTS
RECOG TAXI LTS

Back 12

Landing lights no known limit

Recog taxi lights 10 minutes max when stationary

Front 13

PASSENGER SIGNS PANEL

SEAT BELTS

Back 13

AUTO:
Landing Gear Extended
Flaps out of 0 degrees
Cabin Alt exceeds 10,000' (CPAM)

Front 14

EMERGENCY LIGHTS PANEL

EMERGENCY LIGHTS

Back 14

ARM: Int and Ext emergency lights illuminate if DC ESS power fails
Turned on by overhead panel and Flt Attendants station.

Front 15

FIRE DETECTION PANEL

When is Fire Protection/Detection available and what parts of the aircraft have fire/overheat detection?

Back 15

Fire Protection is ALWAYS available.
Fire Detection is available with Batt Master ON

Parts of aircraft w/fire/overheat detection:
Engine
Jet Pipe
Pylon
MLG bay

Front 16

FIRE DETECTION PANEL

fire TEST WARN

Back 16

1. Simulates Fire (APU bottle blows if selected with failed APU loop)
2. by, grounding loops
3. to, check continuity of loops

Front 17

FIRE DETECTION PANEL

fire TEST FAIL

Back 17

Checks for shorts in system
1. Simulates Overheat
2. by, grounding loops
3. to, check continuity

Front 18

FIRE DETECTION PANEL

fire bottle TEST

Back 18

1. Checks continuity of squibs
2. Checks bottle pressure

Front 19

FIRE DETECTION PANEL

cargo bottle TEST

Back 19

1. Checks continuity of squibs
2. Checks bottle pressure
3. Checks respective smoke detector

Front 20

Glareshield

FIRE Pushbutton (switchlight)

Back 20

Closes Fuel SOV
Closes Hydraulic SOV
Closes Bleed Air Valve (10th)
Turns off Generator
Arms Squibs (squibs will fire if Either PRESS TO DISCHARGE button is pressed

Front 21

CABIN PRESSURIZATION PANEL

EMER DEPRESS

Back 21

1. Press when directed by QRH
2. Opens both outflow valves
3. Maintains cabin pressure at 14,250' +/- 750'

Front 22

CABIN PRESSURIZATION PANEL

Fault Light

Back 22

Both cabin pressure controllers failed.

Front 23

CABIN PRESSURIZATION PANEL

Cabin pressure controllers switch when:

Back 23

1. Weight on wheels + 3 minutes
2. One cabin pressure controller fails

Front 24

CABIN PRESSURIZATION PANEL

MAN ALT switch

Back 24

Modulates outflow valves

Front 25

CABIN PRESSURIZATION PANEL

MAN RATE

Back 25

Select approximately, 500fpm up, 300fpm down

Front 26

CABIN PRESSURIZATION PANEL

PRESS CONT switchlight

Back 26

1. Press once to enter manual mode
2. Press twice to change pressure controllers

Front 27

CABIN PRESSURIZATION PANEL

CPAM Messages

Back 27

Cabin Alt Caution-10,000'
Cabin Alt Warning-14,000'(Pax O2 masks deploy)

Front 28

AIR CONDITIONING PANEL

Limits

Back 28

One Pack-25,000'
Positive-8.7psi
Negative--0.5psi
Taxi,T/O,Lnd-0.1psi

Front 29

AIR CONDITIONING PANEL

Pack Fault light

Back 29

Overpressure or over temperature

Left Pack 70%cockpit/30%cabin
Right Pack 30%cockpit/70%cabin

Front 30

AIR CONDITIONING PANEL

RAM AIR switch

Back 30

Press when directed by QRH or due to operational necessity
Operational necessity is dictated by MEL or CDL
Example of CFM operational necessity is unpressurized takeoffs and landings
Primary purpose is avionics cooling

Front 31

AIR CONDITIONING PANEL

Cabin switch

Back 31

OFF- Off
FAN- Adds air from cabin
COND- Adds heat

Front 32

ANTI-ICE PANEL

Windshield Heat Test

Back 32

Mx function
Probe heat turns ON with weight off wheels

Front 33

BLEED AIR PANEL

DUCT MON

DUCT TEST

Back 33

Duct Mon checks continuity of loops

Duct test simulates duct failure

Front 34

ENGINE START PANEL

When is ignition A used and when is B used?

Back 34

Ignition A on odd days, ignition B on even days.

Ignition B has static inverter (can start on battery only, no AC power required) Starter cuts out at 55%

Front 35

FUEL PANEL

FAIL

Back 35

valve is in uncommanded position

Front 36

FUEL PANEL

BOOST PUMP INOP

Back 36

1. Boost pump not on
2. Low pressure
3. Boost pump failed

Front 37

FUEL PANEL

When is auto fuel transfer

Back 37

At 200# imbalance, fills to +50#

Front 38

FUEL PANEL

Fuel Capacity

Back 38

Gravity refuel: 13,906#
Mains: 4488#
Center: 4930#
Pressure refuel: 14,518#
Mains: 4760#
Center: 4998#

Front 39

FUEL PANEL

When is fuel transfered from center tank to main tanks?

Back 39

When main tanks reach 94%(4474#ea,8984#total)fuel is transferred from center tank to main tanks until mains reach 97% (4617#ea, 9234# total)

Front 40

FUEL PANEL

Fuel Flow

Back 40

1. From center tank to main tanks via transfer ejectors
2. From main tanks to collector tanks (always full, hold 10gals) via scavenger ejectors
3. From collector tanks to engines via main ejectors
Ejectors assist w/motive flow

Front 41

HYDRAULIC PANEL (3 systems)

System #3

Back 41

Largest reservoir
Serviced and located in right main wheel well
Cooled via a fuel heat exchanger in right wing (Lt wing contains bulk fuel temperature probes)

Front 42

HYDRAULIC PANEL

Systems #1 and #2

Back 42

Located and service in aft equipment bay
Cooled by RAM air in flight thru RAM air inlet
Cooled by fans on ground thru RAM air inlet

Front 43

HYDRAULIC PANEL

Describe Pumps

Back 43

2 Engine driven pumps (1A,2A)
4AC Motor Pumps (1B,2B,3A,3B)
3A always on
3B also powered by ADG
all pumps are on when flaps are out of 0 (critical phase of flight)

Front 44

HYDRAULIC PANEL

Which pumps are lose during engine failure?

Back 44

Lost left engine, lose 1A & 2B
Lose Right engine, lose 2A & 1B

Front 45

HYDRAULIC PANEL

Normal ops:

Back 45

45-85% system quantity

1800-3200PSI

Front 46

HYDRAULIC PANEL

What are the systems used for?

Back 46

Systems #2 & #3 used for braking
#2 Outboard brakes
#3 Inboard brakes
Outboard brakes "bleed out" first
6 Brake applications from accumulator after loss of hydraulics (ANTI-SKID off)