Northwest Airlink Pinnacle Airlines - crjsim · PDF fileRevision 2—June 2004 1-57 Northwest Airlink CANADAIR REGIONAL JET FLIGHT CREW OPERATING MANUAL—Volume 1 Pinnacle Airlines

Revision 2—June 2004

1-57

Northwest AirlinkCANADAIR REGIONAL JET FLIGHT CREW OPERATING MANUAL—Volume 1

Pinnacle Airlines

Overwing Emergency Exits

An overwing emergency exit is on either side of the passenger com-partment adjacent to the wings (Figure 1-32). To open the emergencyexit, remove the handle cover and pull the handle in and up from theinternal side, or push the push plate in from the external side. Handlemovement retracts latch pins from fittings on the adjacent structure.Then the overwing emergency exit is pulled in and down, then liftedoff of the two hinge-support fittings and removed.

To install the emergency exit, the two hinge fittings on the bottom of theoverwing emergency exit are positioned on the hinge-support fittings onthe fuselage. The handle is pulled in and up to retract the latch pins. Theoverwing emergency exit is pushed up and out to the installed position.Replace the handle cover.

HANDGRIP

QUICK-RELEASE

HANDLE(INTERIOR)

LOCKINGPINS

LOCKPLATEANDPROXIMITYSENSOR(DOORCLOSED)

ESCAPEROPE(NOTPLACARDED)

PUSH IN FLAPPUSH DOOR INWARD

EMERGENCYEXIT

TO OPENDOOR

EXIT-PULL

Figure 1-32 Overwing Emergency Exits

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Northwest AirlinkCANADAIR REGIONAL JET

FLIGHT CREW OPERATING MANUAL—Volume 1

Pinnacle Airlines

Aft Equipment Bay Door

The removable aft equipment bay door

(Figure 1-33) mounts onthe bottom of the aft fuselage on the aircraft center line and

opensdownward. With the handle unlocked and the trigger plate pushed,the handle ejects out from its recess in the door. Turning the handle90º clockwise or counterclockwise disengages or engages two lock-pins from sockets on the adjacent fuselage structure. The door ismanually opened or closed. To set the handle in its recess, align itwith the recess then push it in until the push plate engages with thespring-loaded latch.

NO STEP

LATCH PLATEAND PROXIMITY

SENSOR

VENTILATIONLOUVERS

QUICK-RELEASEPIN

EXTERIOR HANDLEAND PROXIMITY

SENSOR(FULLY STOWEDAND LOCKED)

KEYLOCK

PUSHPLATETRIGGER

LATCHPIN

Figure 1-33 Aft Equipment Bay Door



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Cargo Bay Door

The cargo bay door (Figure 1-34) is on the left side of the fuselagebelow the engine pylon. A spring assists the door to open inward andupward on tracks when operating the door handle. Pressing the pushplate extends the door handle for operation. Rotating the handlecounterclockwise (OPEN) or clockwise (CLOSE) disengages orengages latch pins interfacing with the adjacent fuselage. To closethe door, it is manually closed, the handle rotates to the CLOSEDposition, and the handle pushed into its recess for stowage.

OPEN

CLOSEDFWD

BALANCE SPRINGSAND CABLES

LATCH PIN

AFT LATCH PLATE

EXTERIORHANDLE HOUSINGPROXIMITY SENSOR(FULLY STOWEDAND LOCKED)

FORWARDLATCH PLATEPROXIMITY SENSOR(FULLY LATCHED)

EXTERNAL HANDLE

PUSH PLATE(TRIGGER)

KEY LOCK

Figure 1-34 Cargo Bay Door


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Door Warning System

The door warning system provides indications to the crew about thecondition and safety of the following pressurized aircraft doors:

●

Passenger door

●

Galley service door

●

Avionics bay door

●

Overwing emergency exits

●

Cargo bay door

Door warning system components include the following:

●

Proximity sensor electronic unit (PSEU)

●

Proximity sensors (12)

●

Proximity switches (6)

●

Microswitches (2)

The PSEU uses information from the proximity switches, sensors,and microswitches to send signals to the engine indication and crewalerting system (EICAS). Door warning system information dis-played on the EICAS primary page includes warnings and cautionson individual doors that are improperly secured (Figure 1-35).

EICAS Indications

Primary Display—Primary Page (Figure 1-35)

Warning Messages (Red)

PASSENGER DOOR—This red warning message comes on to indi-cate that the passenger door is unsafe. DOOR aural comes on whenengines are running.

Caution Messages (Amber)

SERVICE DOOR Caution—Comes on to indicate that galley/ser-vice door is unlocked/unsafe.

CARGO DOOR Caution—Comes on to indicate that cargo bay dooris unsafe.



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L(R) EMER DOOR Caution—Comes on to indicate that applicableemergency exit is unsafe

AV BAY DOOR Caution—Comes on to indicate that avionics baydoor is unsafe

0.0 0.0

0 0

ITT

0.0 0.0

N2

N1

PASSENGER DOORSERVICE DOORCARGO DOORL EMER DOORR EMER DOORAV BAY DOORPAX DR LATCHPAX DR OUT HNDL

DOORSRELATEDMESSAGES

021°0

018°0

234011140

Figure 1-35 EICAS Primary Display—Primary Page


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PAX DR LATCH Caution—Comes on to indicate that the passengerdoor is not fully latched

PAX DR OUT HNDL Caution—Comes on to indicate that the pas-senger door outer handle is not stowed

NOTE

Half-intensity magenta is displayed when theproximity sensors and weight-on-wheels(WOW) switches cannot agree on door state.

DOORS

EMER

CARGO

EMER

SERVICE

AVIONIC BAY

PASSENGERPAX DR OUT HNDL

Figure 1-36 EICAS Secondary Page—DOORS Page



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The EICAS secondary display DOORS page (Figure 1-36) providesa status display of the doors in the door warning system. Door out-lines on the EICAS synoptic page provide an indication of the doorcondition. Outlines are usually the same color as the messages onthe EICAS display.

WINDOWS

There is a right windshield and a left windshield (Figure 1-37). Eachwindshield mounts at the front of the flight compartment on eitherside of the aircraft center line. Each windshield is a bonded assem-bly and includes a heating-element film to prevent ice andcondensation from forming on it.

There is a left side window and a right side window immediately aftof the left and right windshields. Each side window is a bondedassembly and includes a heating-element film to prevent condensa-tion from forming on it.

WINDSHIELD(RIGHT)

WINDSHIELD(LEFT)

SIDE WINDOW(RIGHT)

SIDE WINDOW(LEFT)

Figure 1-37 Flight Compartment Windows


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The 26-passenger compartment windows include 12 on the left side,11 on the right side, one in each overwing emergency exit door, andone in the galley service door.

NACELLES/PYLONS

Each nacelle (Figure 1-38) forms an aerodynamic, protective struc-ture around an engine. It also provides aerodynamic surfaces todirect air into, through, and out of the structure.

The pylons are aerodynamic fairing containing the engine-mountingstructure and all connections between the aircraft and the powerplant. Pylon elements include the primary and secondary structures.

FWD

UPPER TRANSLATINGCOWL DOOR

UPPER CORECOWL DOOR

SERVICEPYLON

UPPER ACCESSCOWL

NOSE INLETCOWL

TORQUEBOX

FIXED-CORECOWL

EXHAUST NOZZLEFAIRING

LOWER CORECOWL DOOR

LOWER TRANSLATINGCOWL DOOR

LOWER ACCESSCOWL

FORWARD CORECOWL ASSEMBLY

NOSE-COWLSIDE PANEL

Figure 1-38 Cowling Components



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WINGS

The fully-cantilevered, one-piece, sweptback wing (Figure 1-39) isthe primary load-carrying aircraft structure. At the bottom of thefuselage midsection, the wing attaches to the fuselage-keel long-erons and fuselage frames. The wing attaches to the fuselage-keellongerons at the center of the front and rear spars. It also attaches tothe fuselage frames at three locations on each side of the wing cen-ter section and at two locations on the rear spar. Each wing alsoincludes attachments for flight control surfaces as well as integralfuel tanks.

WING-TO-FUSELAGEATTACHMENT

FITTINGS

WING-TO-KEEL LONGERON

ATTACHMENT FITTINGS

WINGLANDING LIGHT

AND TAXI/RECOG LIGHT

ANTI-SLIPSURFACING STRIPS

LEADINGEDGE AILERON

SHROUDS

GROUNDSPOILERSINBOARD

FLAPOUTBOARD FLAP

FLIGHT SPOILER

SPOILERON

AILERON

STATIC DISCHARGERS(TYPICAL)

WINGLET

Figure 1-39 Wings


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STABILIZERS

The stabilizers (Figure 1-40) are aerodynamic structures, which pro-vide stability around the aircraft’s lateral and vertical axis. Thestabilizers make a T-shaped empennage with the horizontal stabilizermounted at the top of the vertical stabilizer. Subassemblies of thestabilizer group includes the following:

●

Horizontal stabilizer

●

Elevators

●

Vertical stabilizer

●

Rudder

ELEVATORHORIZONTALSTABILIZER

RUDDER

FUSELAGE/STABILIZERSECTION

VERTICALSTABILIZER

Figure 1-40 Stabilizers



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AIRPLANE SYSTEMS

GENERAL

The following is a brief introduction to the major aircraft systemsfor the Canadair Regional Jet. Detailed descriptions of the systemsare in individual chapters of this manual.

AIR-CONDITIONING/PRESSURIZATION SYSTEM

The environmental control system (ECS) (Figure 1-41) providestemperature and pressure regulated air for ventilating and pressuriz-ing the cockpit and passenger cabin. The system also providescooling air for the avionics and equipment racks. Exhaust air, fromthe cabin and cockpit areas, is used to ventilate and pressurize the

LEFTPACK

OUTFLOWVALVES (2)

RAM AIR

LP GROUNDCONDITIONED

AIRCONNECTION

RAM AIR INLET

RIGHTBLEED AIR

LEFTBLEED AIR

AFT PRESSUREBULKHEAD

PASSENGERCABIN

FLIGHT COMPARTMENT

RIGHTPACK

FAIL FAIL

Figure 1-41 Environmental Control System


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compartments containing avionics equipment, before beingexhausted through two outflow valves.

During ground operations, pneumatic air to operate the ECS can beobtained from any of the following:

●

Ground power cart connected to the airplane

●

Auxiliary power unit (APU)

●

Either or both engines

During flight, normally the engines supply bleed air (10th stage) for oper-ating the air-conditioning, pressurization, and avionics cooling systems.

ECS warnings and cautions are presented on the EICAS primarydisplay. ECS advisory and status messages are presented on theEICAS secondary display. General views of airplane temperatureand pressure information are presented through synoptic diagramson the EICAS secondary display (after selecting the ECS page onthe EICAS control panel).

AURAL/VISUAL WARNING SYSTEM

The aural and visual warning system provides aural, visual, and/ortactile indications. These indications warn of potentially unsafeoperating conditions or airplane configurations, system malfunctions,and non-normal situations.

Indications can be generated by the following:

●

Crew alerting subsystem within the EICAS

●

Enhanced ground proximity warning system

●

Traffic alert and collision avoidance system

●

Altitude alert portion of the air data computer

● Stick shaker portion of the stall protection system

The crew alerting system portion of the EICAS continually moni-tors all airplane systems. If an operationally significant faultoccurs on a system, the EICAS displays a crew alerting messageon the left (primary) EICAS display unit (Figure 1-42). All crew


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alerting system messages are divided into one of four categories:warnings, cautions, advisories, or status.

WARNINGMESSAGES(RED)

CAUTIONMESSAGES(AMBER)

ADVISORYMESSAGES(GREEN)

STATUSMESSAGES(WHITE)

PRIMARY PAGE

STATUS PAGE

234011140

Figure 1-42 EICAS Crew Alerting Messages


1-70 Revision 2—June 2004



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In addition to the display messages, some crew alerts are also indi-cated by aural tones, voice advisories, and MASTER WARNINGand MASTER CAUTION lights. EICAS can also illuminate theappropriate switchlight on the system control panel to prompt cor-rective crew action. The stall warning system generates the stickshaker indication under certain unsafe flight conditions.

AUTOMATIC FLIGHT CONTROL SYSTEM

The automatic flight control system (AFCS) is an integrated autopi-lot and flight director. The AFCS data is supplied to dualindependent flight directors, two-axis autopilot, and automatic pitchtrim system for speed and altitude correction. The AFCS also con-trols automatic yaw damping. Working in conjunction with theAFCS, the integrated avionics processor system (IAPS) operates asa data concentrator for the avionics system. AFCS controls are onthe flight control panel, YAW DAMPER panel, and each controlwheel (Figure 1-43).

The AFCS has two primary modes of operation:

● Autopilot—Used to automatically control the aircraft flightcontrol surfaces

● Flight director—Provides flight guidance commands, whichthe pilots use to control the aircraft flight control surfaces

The IAPS interfaces with the flight control, flight management, andmaintenance diagnostic computers. Concentrated data is then pro-vided to the avionics system.




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YD 1 YD 2

DISC ENGAGE

YAW DAMPER

NO

SE UP

NOSE

DN

AP

/SP

DISC

SYNC

R/T -OFF -

I/C -

FLIGHT CONTROL PANEL

YAWDAMPERPANEL

CONTROL WHEEL SWITCHES(CAPTAIN’S SWITCHES SHOWN,FIRST OFFICER’S SIMILAR)

Figure 1-43 AFCS Controls





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AUXILIARY POWER UNIT

The auxiliary power unit (APU) is a gas-turbine engine equippedwith a gearbox driving an oil-cooled 30-kVA, AC generator. TheAPU's primary function is to drive the AC electrical generator. TheAPU has an integral bleed port, supplying pneumatic power to drivethe main engine air-turbine starters or the air-cycle machines withinthe air-conditioning packs (Figure 1-44).

The APU is in a fireproof enclosure in the tail of the airplane. AnAPU air-inlet door is on the top of the fuselage. APU exhaust gasespass through a muffler to an outlet beneath the right engine. Oilcooler air exhaust exits through the APU exhaust. Electrical powerfrom the APU battery starts the APU. Fuel from both wing tanks isused to operate the APU. The APU's control circuits are fed from themain battery.

An electronic control unit (ECU) controls the APU. The ECU moni-tors all sensors and switches, sets up the appropriate fuelacceleration and temperature schedules, and relays appropriateoperating data to the EICAS displays. The APU control systemensures electrical load priority by reducing bleed airflow whenexhaust gas temperature limits are approached.

GENERATORON/OFFSIGNAL

CHECKVALVE

LEFTENGINE

AIRTURBINESTARTER LEFT PACK

SHUTOFFVALVE

LEFT 10THSTAGE BLEED

SHUTOFFVALVE

LOADCONTROL

APU VALVE

CHECKVALVE

ISOLATIONVALVE

RIGHT PACKSHUTOFF

VALVE

EICAS

APU

RIGHT 10TH STAGE BLEED

SHUTOFFVALVE

CHECKVALVE

RIGHTENGINE

AIRTURBINESTARTER

STARTERCONTROL

VALVE

Figure 1-44 APU Bleed-Air Distribution




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COMMUNICATIONS

The aircraft communication system provides communicationbetween the crewmembers, crewmembers and passengers, two-waycommunication with ground stations, and communication with otheraircraft or the ground crew. The very high frequency communicationsystem provide speech communication between ground and airradio stations.

A few passenger-related systems provide public addressing func-tions within the aircraft. The audio integrating system ties all theradio functions between the independent systems together for usewithin the aircraft.

A cockpit voice recorder provides two hours (30 minutes for oldermodel aircraft) of continuous recording of radio transmissions andcockpit sounds. The radio tuning unit tunes and changes frequenciesfor the airplane radios. The standby control system functions as abackup to the radio tuning unit.





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ELECTRICAL POWER SYSTEM

The electrical power system has 115-VAC and 28-VDC systems,which generate and distribute power to the electrical components(Figure 1-45). The electrical system operates on airplane-generatedpower, or on external AC or DC power supplied from groundpower equipment.

Two AC, integrated-drive generators (one on each engine) supplyprimary airplane-generated power. The auxiliary AC generation sys-tem consists of an APU in the tail of the aircraft. The emergency ACgeneration system is powered by an air-driven generator (ADG).

DC power is obtained from five 100-amp transformer rectifier units(TRUs), which convert AC power into DC power. The TRUs supplyall aircraft DC buses except the battery-direct buses. Only the batter-ies supply the battery-direct buses.

The battery system includes the main battery, APU battery, and batterybuses. Two battery chargers keep the main and APU batteries charged.

Both AC and DC power is distributed throughout the aircraft by theelectrical power distribution systems. Backup emergency systemssupply power to essential systems as needed in emergency situa-tions. AC and DC power are controlled, distributed, and monitoredthrough separate control panels circuit breakers, busses, and gages.

EMERGENCY EQUIPMENT

Emergency equipment refers to the systems and equipment whichare essential to the safety of passengers and crew during a fire, rapiddecompression, ditching, and emergency evacuation. These includethe following equipment:

● Oxygen equipment (portable and fixed)● Evacuation devices (crash axe, escape path marking system,

emergency lighting and emergency exits)● Fire fighting equipment (portable and fixed)● Over water emergency equipment (life vests and seat cushion

flotation devices)




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AP

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RN

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DC

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EC

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BAT

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IN/A

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DIS

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FIRE PROTECTION SYSTEM

Fire protection includes those fixed and portable components thatidentify fire and overheat conditions, as well as provide warnings offire, overheat, and smoke in the airplane. The fire protection systemalso stores the fire extinguishing agent and applies it to all protectedareas of the airplane when needed.

The fire protection system allows the flight crew to detect and extin-guish a fire in the engine nacelles and in the auxiliary power unit(APU) compartment. Smoke detection and fire extinguishing areprovided in the cargo compartment. An overheat detection system,in each engine jetpipe and pylon, permits the flight crew to monitorany overheat condition in those areas.

The main gear wheel wells have a similar overheat detection system.The airplane is equipped with a lavatory smoke detector and anautomatic built-in fire extinguisher. Both the detection and extin-guishing systems permit the flight crew to test and monitor forpossible system faults.

FLIGHT CONTROL SYSTEM

The flight controls (Figure 1-46) are divided into primary flightcontrols, secondary flight controls, and the stall protection sys-tem. The primary flight controls (aileron, rudder, and elevator) aremanipulated by the flight crew to control the aircraft in the verticaland horizontal planes. The secondary flight controls consist of hori-zontal stabilizer, primary flight control trim systems, ground andflight spoilers, and high lift devices (flaps). The stall prevention sys-tem is an automatic system that warns the crew of dangerously highpitch attitudes and near-stall conditions.

The ailerons and elevator move in response to positioning the cap-tain and first officer control columns and control wheels. The rudderis positioned through the captain and first officer rudder pedals.

The trim systems augment the primary flight controls by compensat-ing for varying aerodynamic forces at different airspeeds and grossweights. For the rudder and aileron, this is done by using trim to




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adjust the neutral position of the primary flight control, whichreduces the force required to move the control surfaces. For the ele-vator, the entire horizontal stabilizer is moved.

SPOILERON

FIRSTOFFICER

CONTROLWHEELFIRST

OFFICERCONTROLCOLUMN

FIRSTOFFICERRUDDERPEDALS

CENTERPEDESTAL

CAPTAINCONTROLWHEEL

CAPTAINCONTROLCOLUMNCAPTAIN

RUDDERPEDALS

OUTBOARDFLAP

INBOARDFLAP

RUDDER

ELEVATORHORIZONTAL

STABILIZER

AUTOPILOTSERVOACTUATOR

AILERONFLIGHT

SPOILERGROUND

SPOILERS

Figure 1-46 Flight Controls





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FLIGHT INSTRUMENTS

The flight instruments (Figure 1-47) includes pitot-static data, airdata, attitude and heading data, and electronic flight instrumentssystem information. This also includes the basic flight instruments(digital/analog) and related components, which provide the follow-ing information to the flight crew:

● Altitude (barometric/radio)

● Airspeed (MACH/KIAS)

● Airspeed trend

● Vertical speed

● Overspeed warning

● True airspeed

● Temperature data

● Airplane attitude

● Heading information

● Navigation information

Each primary flight display (PFD) and multifunction display (MFD)receives altitude, heading, airspeed, and attitude data from the on-sidesensors. Flight crew access to display format and display controls isthrough the display control panels (DCP).

Each integrated display (PFD and MFD) is capable of generating anyof the various display formats as determined by flight crew selectionat the reversionary panels. If a PFD fails, the PFD format may be dis-played on the adjacent MFD by actuation of the reversionary modeswitch (PFD/NORM/EICAS). If an EICAS display fails, the EICASsecondary display may be displayed on the adjacent MFD.




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1

NORM

2

1

AIR DATA

2ATTDHDG

NORM

EICAS

ED 1 ED 2

DSPL CONT

1NORM

2

NORM

PRIMARY FLIGHT DISPLAYSMULTIFUNCTION DISPLAYS

EICAS DISPLAYS

DISPLAYCONTROLPANEL*

SOURCESELECTORPANEL

* CAPTAIN'S PANEL SHOWN, SAME AS FIRST OFFICER'S PANEL

DISPLAYREVERSIONARYPANEL

RDR/TERR TFC

Figure 1-47 Flight Instruments





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Display capability is also maintained when sensor data failureoccurs. Either PFD (or MFD when in PFD format) can be configuredto display data from either attitude and heading source or either airdata source by operating the corresponding reversionary switch.

Display source selector switches (ATT HDG and AIR DATA) routeoutput from the air data computer (ADC), and attitude and headingsource to the flight compartment displays.

FUEL SYSTEM

The aircraft fuel system (Figure 1-48) includes provisions for fuelstorage, distribution, and indicating. The storage system has twomain tanks, a center tank, and collector tanks, which contain andsupply constant fuel flow to the engines. Each fuel tank has over-wing fill ports that permit gravity refueling. A system of air scoops,vent lines, and vent valves control pressure in the fuel tanks. Thissystem also moves fuel between the tanks to maintain aircraft lateralbalance.

The distribution system controls refueling, defueling, and the flowof fuel to the engines and the APU. It supplies motive flow pressureto operate the ejector pumps of the fuel system. The distribution sys-tem supplies standby engine feed in case of a fuel system failure.

The indicating system monitors the fuel level in the fuel system. Thefuel system computer uses this information to display fuel quantityand to control the automatic operation of the fuel system.




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L REFUEL/DEFUELSHUTOFF VALVE

NACAAIR

SCOOP

R REFUEL/DEFUELSHUTOFF VALVE

L GRAVITYFILLER CAP

SCAVENGEEJECTOR

CENTER GRAVITYFILLER CAP

L TANKRELIEFVALVE

L HIGHLEVEL SENSOR

R GRAVITYFILLER CAP

R TANKRELIEFVALVE

R HIGHLEVEL SENSOR

VENT LINEPURGE CHECK

VALVE

CENTER TANKRELIEF VALVE

CENTER TANKHIGH LEVEL

SENSOR

CENTER TANKREFUEL/DEFUEL

SHUTOFFVALVE

FUEL SYSTEMCOMPUTER

FUEL TANK

VENT LINES

LEGEND

Figure 1-48 Fuel System





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HYDRAULIC POWER SYSTEM

The airplane has three separate and independent systems (Figure1-49). These systems supply hydraulic power to operate the flightcontrols, main and nose landing gear, nosewheel steering, andbrakes. The three systems are identified as the No. 1, No. 2, andNo. 3 hydraulic systems.

Each of the three hydraulic systems operate at a nominal pressure of3,000 psi. The systems provide flight compartment indications ofsystem pressure, quantity, temperature, and shutoff valve position.

ICE AND RAIN PROTECTION SYSTEM

The airplane has an anti-icing detection system and related anti-icing equipment that prevents ice from collecting on the airplane.Electrical power and engine bleed air provide the anti-icing capabil-ities. Wiper controls also allow greater visibility during rain.Additional heater elements prevent frozen drain lines duringwaste disposal.

Electric heating element prevent ice formation on the air data sys-tem (ADS) probes and sensors and remove condensation from theflight compartment windshields and side windows. Bleed air pro-vides anti-icing heat for the wing and engine cowl areas.

Anti-ice controls are on the ANTI-ICE control panel in the flightcompartment. Wiper switches are on each captain and first officerside panel. The galley control panel has the switch for controllingdrain line heating. Anti-ice warning, caution, status, and advisorymessages appear on the primary or secondary EICAS displays.




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ELEVATORS

ELEVATORS

ACMP 1B

ACMP 3A

MAIN LANDING GEARAND INBOARD BRAKES

MAIN LANDING GEARAUXILIARY ACTUATOR

NOSE LANDING GEAR,NOSEWHEEL STEERING,AND NOSE DOOR

OUTBOARDBRAKES

AILERON

SPOILERON

FLIGHTSPOILER

OUTBOARDGROUNDSPOILER

INBOARD GROUND SPOILER

ACMP 3B

LH FIREWALL SOV

ENGINE DRIVENPUMP 1A

ENGINE DRIVENPUMP 2A

RH FIREWALL SOV

ACMP 2B

RUDDER

HYDRAULIC SYSTEM NO. 1



LEGEND

HYDRAULIC

OFFAUTO

ONOFFON

OFFAUTO

ONOFF

AUTO

ON

1 3A 3B 2

Figure 1-49 Hydraulic System





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LANDING GEAR

The landing gear system is the retractable, tricycle-type consistingof two main landing gear assemblies and a nose landing gear assem-bly (Figure 1-50). Each assembly has a nitrogen/oil shock strut. Onthe ground, all three landing gear assemblies are secured with gearlocking pins.

The functions and subsystems associated with the landing gear sys-tem are:

● Landing gear and door retraction and extension

● Alternate landing gear extension

● Main landing gear overheat detection

● Brake system

● Brake temperature monitoring system (BTMS)

● Antiskid

● Nose wheel steering system

● Proximity sensing electronic unit (PSEU)

Figure 1-50 Landing Gear

NOSE LANDINGGEAR FORWARDDOORS

NOSELANDING

GEAR NOSE LANDINGGEAR AFT DOOR

RIGHT MAINLANDING GEAR

MAIN LANDINGGEAR BAYS

LEFT MAINLANDING GEAR

LEFT MAIN LANDINGGEAR DOOR




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Normal landing gear retraction or extension initiates through thelanding gear control lever. The retraction or extension signal is sentto the PSEU which monitors various landing gear proximity sensinginputs and weight-on-wheels (WOW) inputs. Landing gear door’sautomatically sequence with landing gear operation.

Should a failure occur in the landing gear control system or in theNo. 3 hydraulic system, landing gear extension is still possible bypulling the landing gear manual release handle.

Each wheel of the main landing gear is equipped with self-adjusting,multi-disc brakes. Pulling the parking brake handle, then rotating90°, while fully depressing both ruder pedals secures the brakes inthe applied position. The BTMS monitors each brake and providestemperature readouts on the EICAS secondary display.

The nose wheel steering system is a steer-by-wire system. Steeringcontrol is initiated by the steering tiller and/or by the rudder pedalsand powered by the No. 3 hydraulic system pressure.

LIGHTING SYSTEM

The major areas of the airplane lighting system are flight compart-ment lighting, passenger cabin lighting, baggage compartment andservice compartment lighting, and exterior lighting.

Flight compartment area lighting is provided by a dome light at theflight compartment door threshold area. CRT display fluorescentflood, integral instrument and instrument panel lights provide instru-ment lighting. Chart and map lights are provided for miscellaneouslighting requirements.





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Controls for the flight compartment lights (Figure 1-51) are on theoverhead panel, left and right side instrument panels, and at the rearof the center pedestal. The intensity of the indicator lights on theoverhead, glareshield, side panels and pedestal panels, are con-trolled by an IND LTs intensity selector on the center pedestal. ALAMP TEST switch is also provided to test the indicator lights.Limited lighting is available from battery power for flight compart-ment instrument panels and floor lighting.

FLOORLIGHT

FLOODLIGHTSINSTRUMENTPANELS

FLOODLIGHTSFIRST OFFICER’SSIDE CONSOLE

FIRST OFFICER’SMAP READINGLIGHT

FLOORLIGHTFLOODLIGHTS

CAPTAIN’S SIDECONSOLE

FLOODLIGHTSINSTRUMENT

PANELS

FLOODLIGHTCAPTAIN’S

SIDE PANEL

CAPTAIN’S MAPREADING LIGHT

ELT SWITCHPOST LIGHT

PASSENGER OXYGENSWITCH POST LIGHT

FLOODLIGHTFIRST OFFICER’SSIDE PANEL

Figure 1-51 Lighting




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NAVIGATION SYSTEM

The navigation system includes those units and components whichprovide the following data to the flight crew:

● Position Systems—Dual VHF navigation systems (providingVOR, LOC, GS, and MB signals), dual ADF systems, dualDME, and ATC transponder systems

● Independent Position Systems—Weather radar, traffic alertand collision avoidance, and enhanced ground proximitywarning systems (with windshear detection)

The navigation receivers are tuned by CRT-based radio tuning units(RTUs) and navigation data is displayed on the PFDs and MFDs.Navigation data is displayed on the two MFDs in a full compassrose format (HSI mode) or 120° compass rose format (navaid sectoror VOR map modes). The partial (120°) compass rose on the PFDsechoes the MFD bearing information for the navigation aid selectedon the DCP and tuned at the RTU. VOR, DME, ADF, and MB audiomonitoring is provided at three audio control panels.

Display control panels are on the captain’s and first officer’s sidepanels. These panels permit control over PFD and MFD format nav-igation source and bearing source display.





Pinnacle Airlines

POWERPLANT

The airplane is equipped with two General Electric CF34-3Bl, high-bypass ratio turbofan engines, which have a normal takeoff thrustrating of 8,729 pounds (Figure 1-52). An automatic performancereserve (APR) system is installed. If an engine fails, the APR sys-tem, when operating, increases thrust on the remaining engine to9,220 pounds (thrust increase equivalent to 169 rpm N1).

The engine is a dual-rotor assembly consisting of a fan rotor (N1)and a compressor rotor (N2). The N1 rotor consists of a single-stagefan connected through a shaft to a 4-stage, low-pressure turbine. TheN2 rotor is a 14-stage, axial-flow compressor connected through ashaft to a 2-stage, high-pressure turbine. Engine airflow passesthrough the single-stage fan and is divided into two airflow systems:core air and bypass air. A thrust reverser system deflects fan dis-charge (bypass) air to assist in airplane braking on the ground.

When at high thrust settings, the engine is controlled by an elec-tronic control unit (ECU) which works in tandem with a fuel controlunit (FCU). The data concentrator units (DCUs) perform engine sig-nal analog/digital conversion, signal processing, and engine systemfailure detection. The DCU monitors all engine parameters duringnormal operation. Engine operating times, conditions, and all limitsare recorded through the DCUs.

WATER/WASTE SYSTEM

The water system supplies potable water to the water dispenser andcoffee maker in the galley, and wash water to the sink in the lava-tory. A waste system drains, rinses, primes, and flushes the toilet.The toilet has a holding tank, which is serviced at an external servic-ing panel. The waste water disposal system empties through heateddrain masts.




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VARIABLEGEOMETRY

SYSTEM

10th STAGEBLEED AIR

14th STAGEBLEED AIR

ENGINESPEED

CONTROL

ENGINE STARTAND IGNITION

SYSTEM

AIR DRIVENSTARTER

DATACONCENTRATOR

UNITS

ENGINEOIL

AUTOMATICPERFORMANCE

RESERVE

ACCESSORIES

OIL PUMPFUEL PUMPGENERATOR & CSDSTARTERHYDRAULIC PUMP

THRUST REVERSERSYSTEM

BLOCKER DOOR

FOURTEEN STAGEAXIAL FLOW

COMPRESSOR

SINGLE STAGEFAN

TWO STAGE HIGH PRESSURE TURBINE

FROMPNEUMATIC

SYSTEM

FOUR STAGE LOW PRESSURE TURBINE

CORE AIR

BYPASS AIR

CASCADE VANES

TORQUE BOXTRANSLATING

COWL

93.0 93.0

750 750

95.0 95.0

ITT

99.0N1

XX XXVIB

C.ALT3100

RATE100

P–7.7

GEAR

DN DN DN

N23000 3000FF

116 OIL TEMP 118

82 82OIL PRESS

(PH)

FLAPS 18

FUEL QTY (LBS)4870 2340 3830

12180TOTAL FUEL

COMBUSTIONCHAMBER

N1

ENGINEFUEL

SYSTEM

Figure 1-52 Powerplant





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A temperature control system, operated from the flight attendant'sgalley panel (Figure 1-53), prevents freeze up of the water system.Heaters and thermoswitches in the tanks, water lines, drain lines,and drain masts prevent ice formation. Two water system servicingpanels are on the exterior lower fuselage. These panels permit fillingand draining of the water system.

MISCELLANEOUS

HAZARD AREAS

Aircraft hazard areas are shown in Figure 1-54 and Figure 1-55.

GALLEYAREA

WATERLEVEL

INDICATOR(GREEN)

WATERSHUTOFF

VALVE

PUMPSWITCHES

WATER SYSTEMCIRCUT BREAKERS

GALLEY LAVATORY

FULL

POWERON

POWERON

OFF OFF

OVHT OVHTEMPTY

PUMP PUMP

CONTL&IND

CONTL&IND

TANKHTR

TANKHTR

LINEHTR

LINEHTR

5

OVEN

15

COFFEE MAKER

10 10

5

5

5

71/271/2

Figure 1-53 Water/Waste System Controls




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IDLETHRUST

MAXIMUMTHRUST

12 FT25 FT

0

10

20

30

40

50 FT

60

70

80

90

100 FT

110

120

130

140

150 FT

160

170

0

10

20

30

40

50 FT

60

70

80

90

100 FT

110

120

130

140

150 FT

160

170

27°C(80°F)

27°C(80°F)

18 FT

IDLETHRUST

20 MPH

68 MPH

34 MPHMAXIMUMTHRUST

18 FT

34 MPH

68 MPH

136 MPH

272 MPH

136 MPH

544 MPH227°C(440°F)

393°C(740°F)

532°C(990°F)

60°C(140°F)

60°C(140°F)

APU EXHAUSTDANGER AREA(15 FEET)

Figure 1-54 Hazard Areas—Engine and APU





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RADAR 25 WATT60 CM (2 FEET)WITH RADOME CLOSED

Figure 1-55 Hazard Area—Radar




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CONVERSION FACTORS

Table 1-5 CONVERSION FACTORS

MULTIPLY BY TO OBTAIN

Centimeters 0.3937 Inches

Centimeter2 0.155 Inches2

Centimeters3 0.061 inches3

Cubic feet3 0.0283 Meters3

Feet 0.3048 Meters

Feet2 0.0929 Meters2

Imperial gallons 1.2014.546

U.S. gallonsLiters

U.S. gallons 3.7850.8327

LitersImperial gallons

Inches 2.54 Centimeters

Inches2 6.452 Centimeters2

Inches3 16.387 Centimeters3

Kilograms 2.205 Pounds

Kilometers 0.62140.54

MilesNautical miles

Kilometers per hour 0.540.6214

KnotsMiles per hour

Knots 1.1511.852

Miles per hourKilometers per hour

Kilopascals 0.145 Pounds per square inch

Liters 0.26420.22

U.S. gallonsImperial gallons

Meters 3.281 Feet





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Meters2 10.76 Feet2

Meters3 35.3115 Feet3

Miles 5,2801.6090.869

FeetKilometersNautical miles

Miles per hour 1.6090.869

Kilometers per hourKnots

Nautical miles 1.1511.852

MilesMeters

Pounds 0.45 Kilograms

Pounds per square inch 6.895 Kilopascals

Table 1-5 CONVERSION FACTORS (Cont)

MULTIPLY BY TO OBTAIN


Revision 3—December 2004 1-95


Pinnacle Airlines

CRJ VARIATIONS

Pinnacle Airlines operates two versions of the CRJ, which includethe 200LR configured for 50 seats and the 440LR configured with44 seats.

The 44-seater has additional underbin wardrobe and storage space inthe forward cabin that contains either of the following configura-tions (Figure 1-56).

1 2 3A

Figure 1-56 Underbin Wardrobe and Storage Space(1 of 2)





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The 44-seater may also include any or all of the following options:

● New flight attendant’s intercom and lighting control panelwith pushbutton switches and a sterile cockpit light (currentlydisabled) (Figure 1-57)

● Two portable oxygen bottles located in the right side forwardoverhead bin, instead of the flight attendant’s forward com-partment (Figure 1-58)

● Updated flight attendant’s forward compartment (Figure 1-59)

● Digital public address/music system (Figure 1-60)

● Flightdeck sterile light system (currently disabled) (Figure1-61)

● Flightcrew/observer single-piece integrated oxygen masks(Figure 1-62)

1 2 3A

Figure 1-56 Underbin Wardrobe and Storage Space(2 of 2)




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ON

OFF

BRT

DIM

ON

OFF

BRT

DIM

ON

OFF

BRT

DIM

ON

OFF

ON

OFF

STERILE LIGHT

DOME

GALLEY

SIDEWALL

CEILING

EMERGLIGHT

ONOFF

ATT EMGFL A

EMERGENCYLIGHTSSWITCH

Figure 1-57 Flight Attendant’s Intercom and LightingControl Panel





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B

B

B

B

B

B

PORTABLEOXYGEN

BOTTLES

RIGHT HAND OVERHEAD BIN

VIEW LOOKING FORWARD

1 2 3 4 5

Figure 1-58 Two Portable Oxygen Bottles—Right Forward Overhead Bin




Pinnacle Airlines

DOORASSIST

BOARDINGLIGHTS

READINGLIGHTS

CALLCANCEL

GALLEYHEATING

APUSERVICE

BUS

ON TEST RESETINOP

HTR

INOP

HTR

BRT

CLOSED ON

OFFFAIL

FAN SYSTEM1 & 2TEST

MESSAGE

LANGUAGE

VOLUME

SELECT

PLAY

PWR

FLIGHT ATTENDANTMISCELLANEOUSSWITCH PANEL

DIGITAL PUBLICADDRESS/MUSICSYSTEM

EMERGENCYMEDICAL KIT

FIREEXTINGUISHER

FLIGHTATTENDANTSINTERCOM ANDCONTROL PANEL

FIRST AID KIT

PROTECTIVEBREATHINGEQUIPMENT

OBSERVERSLIFE VEST

FLIGHTATTENDANTSLIFE VEST

ON

OFF

BRT

DIM

ON

OFF

BRT

DIM

ON

OFF

BRT

DIM

ON

OFF

ON

OFF

STERILE LIGHT

DOME

GALLEY

SIDEWALL

CEILING

EMERGLIGHT

ONOFF

ATT EMGFL A

Figure 1-59 Flight Attendant’s Forward Compartment





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MISC LTSSTBYCOMP

OFFON

DIMOFF

ON DIM BRT

OVHDDOMELIGHT

OFFON

STERILE

Figure 1-60 Flightdeck Sterile Light System

Figure 1-61 Single-Piece Integrated Mask and Goggles




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INTEGRATED STANDBY INSTRUMENT SYSTEM

For aircraft 8891 and subsequent, Bombarier has replaced the exist-ing standby electronic instrument with a new integrated standbyinstrument and improved stall protection computers (Figure 1-62).

The new integrated standby instrument (ISI) provides standby atti-tude, altitude and airspeed information to the flight crew. To retainfull operational capability under emergency conditions the ISI ispowered by the battery bus. The ISI uses inputs from the alternatepitot probe and static ports. The ISI displays the following informa-tion: attitude displays, ILS deviation, altitude display (corrected),VMO display, airspeed display, static source error protection, Machnumber, barometric pressure, and slip-skid indication.

STD

CAGE BARO

10

10

20

12

ILSM.47 1013hPa

900

800

700

600

50029.92in

240

220

200

180

BARO—Used to adjust baro-correction pressurereference. Setting storedin non-volatile memory toprevent loss during power failure.

CAGE—Used to resethorizon line. Use only during stabilized level flight. Will not operate during power up.

BrightnessControls

STD—Used to select eitherstandard pressure reference,1013 hPa (29.92 inHg), or baro-correction pressurereference.

Figure 1-62 Integrated Standby Instrument System


1-102

Revision 3—December 2004



Pinnacle Airlines

FLAP LEVER DEVIATION

On selected aircraft, the flap lever includes an 8° position. (Figure 1-63).

20°

30°

45°

0°

20°

30°

45°

0°

8° 8°

FLAPSFLAP SELECTOR

LEVER

Figure 1-63 Flap Selector Lever



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INTENTIONALLY LEFT BLANK


1-104 Revision 3—December 2004



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Pinnacle Airlines





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Pinnacle Airlines





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ABBREVIATIONS

The following abbreviations may be used by flight compartment dis-plays, radio tuning units, and flight management system, or may befound throughout the manual. Some abbreviations may also appearin lower case letters. Abbreviations having very limited usage areexplained in the systems chapters where they are used.

AA/C Air-conditioningA/G Air/groundA/ICE Anti-iceA/P AutopilotA/S AirspeedA/SKID Anti-skidABS AbsoluteAC Alternating currentACARS Aircraft communications, addressing and

reporting system

ACCEL Acceleration, accelerate(d), accelerometersACM Air-cycle machineACMP Alternating current motor pump/electric

hydraulic pump

ACT ActiveACU Air-conditioning unitADC Air-data computerADDR Address ADF Automatic direction finderADG Air-driven generatorADI Attitude director indicatorADS Air-data systemAFCS Automatic flight control systemAFT Afterward AGL Above ground levelAHC Attitude heading computer





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AHRS Attitude heading reference systemAIL AileronALIGN Aligning, alignmentALPHA Alpha ALT Altitude, altimeter ALT Altitude hold (PFD/FD) ALT CAP Altitude capture (PFD/FD) ALT HOLD Altitude holdALTN Alternate ALTS Selected altitude arm/abort (PFD/FD)AM Amplitude modulation AMB Ambient AMP Amperes ANNUN Annunciator ANT Antenna AOA Angle of attack AP Autopilot APC Auxiliary power control APP Approach APPROX Approximately APR Automatic performance reserve APU Auxiliary power unit ARINC Aeronautical Radio IncorporatedARP Air-data reference panel ASYM Asymmetrical ATA Air Transport Association ATC Air traffic control ATT Attitude ATTD Attitude ATTND Attendant AUTO Automatic AUTO BAL Automatic balance AUTO XFER Automatic transferAUX Auxiliary




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AV AvionicsAVAIL Available AZ Azimuth

BB/AIR Bleed airB/C Back courseB/CRS Back courseB/LEAK Bleed leakBARO BarometricBAT BatteryBATT BatteryBDI Bearing/distance indicatorBFO Beat frequency oscillatorBITE Built-in-test equipmentBK BrakeBLD Bleed BOOM Headset microphone BRG Bearing BRKR(s) Breaker(s) BRT Bright BTL BottleBTMS Brake temperature monitoring systemBTMU Brake temperature monitoring unitBYPS Bypass

CC Center, caution, cabinCAA Civil Aviation Authority (UK)CAL CalibrateCAP CaptureCAPT CaptainCAS Calibrated air speedCAT Category





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CB, C/B Circuit breakerCBP Circuit breaker panelCCW CounterclockwiseCDL Configuration deviation listCDP Compressor discharge pressureCDU Control display unitCFM Cubic feet per minuteCG Center of gravityCH Chapter, channelCHAN ChannelCHGR ChargerCHR ChronographCHRT ChartCK CheckCKPT Cockpit CKT Circuit CLB Climb CLK Clock Cm Centimeters CMD Command CMPS Compass CMPTR Computer CO2 Carbon dioxide COM Communication COMM Communication COMP Compressor, comparator COMPT Compartment COND Condition, continued CONFIG Configuration CONN Connection CONT Control, continuous, contactor, controllerCOOL Cooling CORR Correction CPAM Cabin pressure acquisition module




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CPLT CopilotCRS CourseCRT Cathode-ray tubeCRZ CruiseCSD Constant speed driveCTR Center CVR Cockpit voice recorder CW Clockwise CYL Cylinder

DDA Drift angleDBU Data base unitDC Direct currentDCP Display control panelDCU Data concentrator unitDECEL Decelerate(d)DECR DecreaseDEFL DefuelDEG DegreeDEPR DepressurizeDEPT DepartureDEST DestinationDET DetectorDEV DeviationDFDAU Digital flight data acquisition unitDFDR Digital flight data recorderDG Directional gyro DH Decision height DIFF Differential DIM Dimming DIR Direct DIS Distance (to way point), disconnect DISC Disconnect DISCH Discharge





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DISP Dispatch, display DIST Distance DME Distance measuring equipment DN Down DOT Department of Transport (Canada) DR Door

EEAS Equivalent airspeedECP EICAS control panelECS Environmental control systemECU Electronic control unitED EICAS displayEDP Engine-driven pump, engine primary

hydraulic pump

EFIS Electronic flight instrument systemEGT Exhaust gas temperatureEICAS Engine indication and crew alerting systemEL ElevationELEC ElectricalELEV Elevator, elevation ELT Emergency locator transmitter EMER(G) Emergency ENG Engine EPC External power contactor EQUIP Equipment ERP Eye reference position datum ESS Essential ET Elapsed time ETA Estimated time of arrival EVAC Evacuation EXH Exhaust EXTIN Extinguish(ed)




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FF/CTL Flight controlsFAA Federal Aviation Administration (USA)FAIL FailureFCC Flight control computerFCU Fuel control unitFD, F/D Flight directorFDAU Flight data acquisition unitFDR Flight data recorder (digital)FECU Flaps electronic control unitFECU Fuel electronic control unitFEED FeederFF, F/F Fuel flowFIRE BTL Fire bottleFIREX Fire extinguisherFL CH Flight level change FLD Field FLT Flight FLT DIR Flight director FLUOR Fluorescent FM Fan marker FMS Flight management system FPM Feet per minute FREQ Frequency FT Feet, foot FW Fire wall FWD Forward

GG (+/–) Receiver gainG/S Glide slopeGA Go-aroundGAL GallonGALY GalleyGCS Ground clutter suppression





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GCU Generator control unitGE General ElectricGEN GeneratorGLD Ground lift dumper (ing)GMT Greenwich mean time GND Ground GPM Gallons per minute GPWS Ground proximity warning systemGR Gear GRAV Gravity GS Ground speed GUIDE Guidance GW Gross weight

HHDG HeadingHDG HOLD Heading holdHDG SEL Heading selectHEAT HeaterHF High frequency (3–30 MHz)Hg MercuryHI HighHLDR HolderHOR, HORIZ HorizontalHOT High oil temperatureHP High pressure HPA Hecto pascals HSI Horizontal situation indicator HSTA Horizontal stabilizer trim actuatorHSTCU Horizontal stabilizer trim control unitHTR Heater HUD Heads-up display HYD Hydraulic Hz Hertz




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II/B InboardI/C Intercom, inspection checkIAPS Integrated avionics processor systemIAS Indicated air speedICAO International Civil Aviation OrganizationICS Idle corrected speedID IdentificationIDENT IdentificationIDG Integrated-drive generatorIFR Instrument flight rulesIGN IgnitionILS Instrument landing systemIM ILS inner markerIMC Instrument meteorological conditionsIMP ImperialIN Inch, inchesIN Hg Inches of MercuryINBD InboardINCR IncreaseIND Indication, indicatorINFLT In flightINHIB InhibitINOP InoperativeINPH InterphoneINSP InspectionINST(S) Instrument(s)INST, INSTR InstrumentINT Internal, integral, intersectionINTEG IntegralIRS Inertial reference systemIRU Inertial reference unitISA International standard atmosphereISO International Standard Organization





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ISOL Isolation, isolatedITT Interturbine temperature

J

JAA Joint Airworthiness Authority (Europe)

KK, KT, KTS KnotsKg (s) Kilogram(s)kHz KilohertzKIAS Knots indicated airspeedkW(s) Kilowatt(s)

LL Left, landingL/T Landing/taxiLAV LavatoryLB(s) Pound(s)LCN Load classification numberLCV Load control valveLDG LandingLDG GR Landing gearLDU Lamp driver unit LE Leading edge LG Landing gear LGC Landing gear controller LGW Landing gross weight LH Left hand LIM Limit LK LeakLN Left noseLNAV Lateral navigationLOC ILS localizerLOGO Logo graphicLOM, MM Compass locator at outer markerLOP Low oil pressure




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LP Low pressureLPM Liters per minuteLR Left rear LRC Long range cruise LSB Lower side band LT(s) Light(s) LW Left wing LWD Left wing down LWR Lower

MM Mach numberm MeterMAA Maximum authorized IFR altitudeMAC Mean aerodynamic chordMAG MagneticMAINT MaintenanceMALF MalfunctionMAN ManualMAP Ground map (WXR)MAX MaximumMAZ MLS azimuthMB MillibarsMCA Minimum crossing altitudeMCT Maximum continuous thrustMDA Minimum descent altitudeMEA Minimum enroute IFR altitudeMECH MechanicMED MediumMEL Minimum equipment listMFD Multifunction displayMGP MLS glideslopeMHz MegahertzMI MilesMIC Microphone





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MID AFT Middle afterwardMID FWD Middle forward MILS .001 of an inch MIN Minimum MISC Miscellaneous MKR Marker MLG Main landing gear MLS Microwave landing system MLW Maximum landing weight MM ILS middle marker MMEL Master minimum equipment list MMO Maximum operating speed in Mach number MOCA Minimum obstruction clearance altitudeMOD Module MON Monitor MPH Miles per hour MRA Minimum reception altitude MSG Message MSL Mean sea level MTG Miles to go MTOW Maximum takeoff weight MTW Maximum taxi weight MZFW Maximum zero fuel weight

N

N/A Not applicable

N1 Low pressure rotor

N2 High pressure rotor

NAV Navigation

ND Nose down, navigation display

NDB (ADF) Nondirectional beacon (automatic direction finder)

NEG Negative





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PF Pilot flyingPFD Primary flight displayPLA Power lever angle PLT(s) Pilot(s)PNF Pilot not flyingPNLS(s) Panel(s)PO Outside air pressure POS Position PPH Pounds per hour PRESS Pressure, pressurization PRI Primary PRIM Primary PROC Procedure PROT Protection PROX Proximity PSEU Proximity sensor electronics unitPSI Pounds per square inch PSIG Pounds per square inch gagePSS Proximity sensor systemPSU Passenger service unitPT2 Engine inlet pressure and temperaturePTCT ProtectPTT Push-to-talkPWR Power

QQAR Quick access recorderQEC Quick engine changeQFE Local station pressure QNH Altimeter setting QTY Quantity




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RR RightRA Radio altitudeRAI Registro Aeronautico ltaliano (Italy)RAT Ram-air turbineRCCB Remote controlled circuit breakerRCDR RecorderRCVR ReceiverRDR Radar REC Receiver, recorderRECOG RecognitionREF(s) Reference(s)REFL RefuelREV ReverseRH Right hand RMI Radio magnetic Indicator ROT Rotation RPM Revolutions per minute RT, R/T Receiver-transmitter RTE Route RTE DATA Route data RTO Rejected takeoff RTU Radio tuning unit RUD Rudder RVR Runway visual range RVSR Reverser RW Right wing RWD Right wing down RWY Runway

SS StatusSAT Static air temperatureSCAV ScavengeSEC Second, secondary





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SECS Spoiler electronic control systemSECU Spoiler electronic control unitSEL Select, selectorSELCAL Selective callSENS Sensitivity, sensorSERV, SVCE ServiceSMKG SmokingSOV Shutoff valve SP, SPD Speed SPC Stall protection computer SPKR Speaker SPLR(s) Spoiler(s) SQL Squelch SSB Single side band STA Station STAB Stabilizer STAT Status STBY Standby STEER SteeringSUPPL Supply SW(s) SwitchesSYN SynchronizeSYNC Synchronous SYS, SYST System

T

T/C Top of climb

T/D Top of descent

T/R Thrust reverser

TACAN UHF tactical air navigation aid

TAS True airspeed

TAT Total air temperature

TCAS Traffic alert and collision avoidance system




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TE Trailing edge

VFTO Final Takeoff Speed

TEMP Temperature

TGT Target

TO, T/O Takeoff

TOL Tolerance

TRB, TURB Turbulence

TRK Track

TRM Trim

TRU Transformer rectifier unit

T2 Engine inlet temperature

UUNSCHD UnscheduledUSB Upper side bandUSG United States gallons UTIL utility

VV VoltVA Design maneuvering speedVB Design speed for maximum gust intensityVC Design cruising speedVD Design diving speedVDF/MDF Demonstrated flight diving speedVEF Engine failure speedVF Design flap speedVFC/MFC Maximum speed for stability

characteristics

VFE Maximum flap extended speedVLE Maximum landing gear extended speedVLO Maximum landing gear operating speedVLOF Liftoff speed





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VMC Minimum control speed with the criticalengine inoperative

VMO/MMO Maximum operating limit speedVMU Minimum unstick speed VR Rotation speed on takeoffVS Stalling speed or minimum steady flight speed at

which the airplane is controllable

VSO Stalling speed or the minimum steady flightspeed in the landing configuration

VS1 Stalling speed or minimum steady flightspeed obtained in a specific configuration

VT Final takeoff speed (same as VFTO)V1 Takeoff decision speed (formerly denoted

as critical engine failure speed)

V2 Takeoff safety speed V2 MIN Minimum takeoff safety speed V/S Vertical speed VERT VerticalVFR Visual flight rulesVG Vertical gyroVHF Very high frequency (30–300 MHz)VIB VibrationVMC Visual meteorological conditionsVNAV Vertical navigation VOL Volume VOLT Voltage VOR VHF omnidirectional range stationVORTAC VOR and TACAN co-located VSI Vertical speed indicator

WW WarningW/C Wind componentW/S Wind shearW/W Wheel well




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WARN WarningWF Runway length limited weightWGT WeightWHLS WheelsWIND WindowWOW Weight-on-wheel WPT(s) Waypoint(s) WRN Warning WS Second segment limited weightWSHLD Windshield WX Weather WXR Weather radar

XX Cross transferXFER, XFR TransferXFLOW Cross flowXMIT TransmitXPNDR Transponder XTK Cross track XWC Cross wind component

Y

YD, Y/D Yaw damper

Z

ZFW Zero fuel weight





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Documents

Northwest Airlink Pinnacle Airlines - crjsim · PDF fileRevision 2—June 2004 1-57 Northwest Airlink CANADAIR REGIONAL JET FLIGHT CREW OPERATING MANUAL—Volume 1 Pinnacle Airlines