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crj2 limits, systems

Pinnacle CRJ200 limits, systems, overhead panel

QuestionAnswer
Max pressure alt for t/o and landing 10000ft
Max operating alt 41000ft / company 37000ft
max operating alt with 1/inop pack 25000ft
max ambient air temp for t/o landing ISA +35 C
Min temp for t/o -40 C
Max taxi/ramp weight 53,250 lb
MTOW 53,000 lb
MLW 47,000 lb
MZFW 44,000 lb
min flight weight 30,000 lb
max runway slope +/- 2% gradient
Max tailwind 10kt
max x-wind comp on wet runway 27kt
max x-wind comp on contaminated runway 15kt
max demonstrated x-wind component landing/to? 27kt
What is visible moisture (defined as?) clouds, fog w/ vis <1 mile, rain, snow, sleet, ice crystals
When must cowl anti-ice be used on the ground? OAT below 10C and: visible moisture, runway has snow, ice, water, slush
When must wing anti-ice be used on the ground for takeoff? OAT below 5C and: visible moisture, runway has snow, ice, water, slush
Can SAT or TAT be used before takeoff? No, because the probes may give inaccurate readings on the ground or at low speed.
When must anti-ice be used when type 2/4 anti-icing fluids have been applied? just prior to thrust increase for take-off.
Define icing conditions in flight: TAT 10C or below and visible moisture, unless the temp is -40C or below.
When must Engine cowl anti-ice must be used in flight? Icing conditions, ICE is annunciated
When must wing anti-ice be used in flight? ICE is annunciated, Icing conditions below 230kt
Vle 250kt
Vlo (retract gear) 200kt
Vlo (gear extended) 250kt
Vfe 8* 215kt
Vfe 20* 215kt
Vfe 30* 185kt
Vfe 45* 170kt
Max windshield wiper speed 220 kt
Max tire speed/ground speed 182kt
Target turb air penetration speed 280kt or mach .75 (Whichever is lower)
max speed with STAB or MACH trim INOP 250kt or mach .7 (unless autopilot is engaged)
If you are above 10,000ft, what is the minimum climb speed? 250kt/.7 Mach
What should you do if you cannot maintain 250kt/.7 and 350ft/min climb above 10,000ft? Immediately level off and advise ATC
Minimum enroute cruise speed above 10,000ft .7 Mach or Long Range Cruise Speed (whichever is lower)
Describe the three main gauge colors: Red = max/min limitations, Amber = Caution, Green = Normal
Engine operating limits for start: N2% 20, ITT*C 900 degrees
Engine operating limits for idle: N2% do not accelerate above idle if below 57% N2, N2 split no greater than 2%
Max ITT's Accelerating: 900*C
Max continuous: 874*C
Normal Takeoff ITT max temps: 884 for 5 mins, 900 for 2 mins/5mins
Go-around or APR thrust max ITT temps: 900 for 5 mins, 928 for 2 mins/5mins
What must you do for the first flight of the day if the plane is cold-soaked at a temp -30 or below for +8 hours? motor engines for 60 secs, verify fan rotation, Reverse thrusters must be actuated until the deploy and stow cycles are less than 5 secs
Max oil temp continuous +155*C
Max oil temp permissible +163*C (15 min max)
min oil temp for starting -40*C
oil pres minimum: steady state idle 25 PSI
oil pres minimum: take off 45 PSI
Max cont oil pres 115 PSI
oil pres: max transient after cold start 156 PSI, 130 PSI at idle, 10 min max
when is continuous ignition required? t/o & landing on contaminated runways t/o x-wind +10kt, flight thru moderate/heavy rain, flight thru moderate/heavy turb, flight in vicinity of thunderstorms, flight at or near shaker and pusher settings
When must APR be verified? When takeoff performance is predicated on its use
How long must engines run prior to takeoff or landing? 2 mins
What should you do if ITT rises above 350*C following engine shut-down? carry out an engine motoring cycle to reduce ITT
Starter limits on ground or in-flight cannot be used if N2 >55%
Engine start cycle times 1st try = Max time on 1 min, followed by 10 second off, 2nd try = Max time on 1 min, followed by 10 second off, 3rd try = Max time on 1 min, followed by 5 min off
ITT limits at the initiation of thrust lever movements from SHUT-OFF to IDLE? ITT < 120*C for ground starts, ITT < 90*C for air starts
max fuel imblance? 800lb
Takeoff with fuel in excess of ??? pounds in the center is not allowed unless each wing tank has ???? pounds no more than 500lb center unless the wings are above 4400lb.
Min fuel for go-around 450lb per wing
Minimum engine fuel temp for takeoff? 5C
Min bulk fuel temp prior to flight? -30C
Fuel Cross-flow - what must be off prior to t/o? powered crossflow and gravity crossflow
Minimum temp for starting a cold-soaked APU? -40*C
APU start times on batt 1: max 30 secs on, 2: max 30 secs on, wait 20 min, 3: max 30 secs on, 4: max 30 sec on, wait 40 mins
APU start times using DC ground power 1: max 15 secs on, 2: max 15 secs on, wait 20 min, 3: max 15 secs on, 4: max 15 sec on, wait 40 mins
Bleed air limits: AC in-flight bleed air from APU not permitted above 15000ft
Bleed air limits: engine start - ground no bleed air extraction limit, each engine may be started using APU bleed, If both engines are started via APU, the operating engine cannot exceed 70% N2
Bleed air limits: engine start during flight during single engine ops, APU bleed air for engine start not permitted, during double engine failure, APU bleed permitted at/below 13000ft
If the APU door is open you must: Limit to 300kt, APU must remain in operation
Aircon/Pressurization: max positive dif presure 8.7 psi
Aircon/Pressurization: max negative presure -.5 psi
Aircon/Pressurization: during taxi/to/landing .1 psi
AC and Pres.. Max differential presures: Max Positive Pres? 8.7PSI
AC and Pres.. Max differential presures: Max negative pres? -.5PSI
AC and Pres.. Max differential presures: During takeoff and landing .1PSI
Permissible loads on the AC system (Load limitation in kVA): ALT = 0-FL350 Main Gens = 30kVA, APU Gen = 30 kVA
Permissible loads on the AC system (Load limitation in kVA): ALT = FL350-FL370 Main Gens = 25kVA, APU Gen = 30 kVA
Permissible loads on the AC system (Load limitation in kVA): ALT = above FL370 Main Gens = 25kVA, APU Gen = NA
Max permissible continuous load on each TRU 100 amps
Flaps above XXXXX feet prohibited 15,000FT
Flight spoilers may not be extended below ??? ft AGL 1000 ft AGL
Flight spoilers may not be extended at airspeeds below the recommended approach/maneuvering speeds plus ?? KIAS: + 17 KIAS
Use of spoilers with flaps greater than ?? degrees prohibited: N/A with flaps greater than 30 degrees
At 10,000 ft, or when SAT falls below 0*C, the ailerons must be operated manually every ???? feet until the top of climb: every 5000 feet
Are both stall protection systems required for flight? YES
Are thrust reversers approved for ground use only? YES
Can you attempt a go-around when thrust reversers have been used during landing? NO, TR's only intended for full-stop landings
Can take-off occur with any of the following error messages? TRUST REVERSER UNLK Light, REV icon N1, L/R REV UNLOCK No
Max reverse thrust must stop at what airspeed on the ground? 60 KIAS, TR must be at idle
Taxi lights must be switched off if the plane is stationary for longer than ?? minutes 10 minutes
Normally, the auto pilot use is prohibited at altitudes below ??? ft: 600 FT
Normally, the auto pilot use is prohibited at altitudes below 600 ft AGL, except under what conditions? visual approaches: 400ft AGL, precision approaches: 80ft AGL
If your DH/MDA is 92ft, what number would you dial in with the DH/MDA knob? 100 ft. Knob works in 10' increments
If you receive a TCAS RA, should you deviate from an ATC clearance to comply? YES
If you receive a EGPWS warning, should you deviate from an ATC clearance to comply? YES
What does the FIRE PUSH button do? Arms the Squibs, close fuel feed SOV, close bleed air SOV, close HYD SOV, EDG off
What is the total fuel for pressure refueling, and total usable fuel? 14,518 lbs
Describe the fuel capacities in each tank: Wings can hold 4,760 lbs each, Center tank 4998 lbs
When does the XFO/APU pump come on? +200 lb fuel imbalance
When does the center fuel tank automatically begin transferring fuel to the wing tanks? Anytime the wing tanks are below 94% full
What does the 10th stage bleed air provide? AC Packs, Pressurization, Main engine start
What does the 14th stage bleed air provide? wing/cowl anti-ice, thrust reverse
What are the pressure limits for the Packs? 30PSI if both in use, 41PSI if 1 inop
What causes a PACK FAULT caution? over pressure, over temp
Cabin pressure controllers (CPC) are spring loaded XXXX and modulated XXXX with XXXX pressure from XXXX Cabin pressure controllers (CPC) are spring loaded SHUT and modulated OPEN with VACUUM pressure from 10TH STAGE BLEED
Describe what happens when you press the PRES CONT button: Press 1: manual mode, Press 2: PRES CONT 2, Press 3: manual mode, Press 4: PRES CONT 1
What would cause a PRES CONT FAULT to appear? failure of both CPCs
What happens to the CPC's 3 minutes after landing? The active/inactive CPC's switch
If the aircraft is above 14250ft +/- 750 feet, the plane will maintain what pressure? 14250ft +/- 750 feet
Describe CPAM CABIN ALT messages, and when they occur: ***Cabin Alt *master caution* between 8,500 and 9,999 ft. and master warning *CABIN ALT > 10,000 ft., illumination of fasten seat belts, and no smoking signs automatic when switch is selected to auto. Passenger O2 masks drop automatically at 14,000 ft.
What happens if an APU XFLO pump fails? Negative gravity relief valve supplies fuel from the right tank
How does the APU shutdown? From a simulated overspeed signal
What are the critical altitudes to know concerning the APU? FL370 max opp alt, FL300 max alt to start APU, 13000 engine start with bleed, 15000 ECS operation
Are both batteries required to start the APU? What is the battery minimum voltage? Yes, 22V
What causes an APU shutdown in the air? Fire, Loss of speed signal, ECU failure, DC power loss, overspeed
BITE stands for? Built in test equipment
Describe the AC power system: 115V, 400 HZ, 30 kVA, BUS 1/2, UTIL BUS 1/2, SERV BUS, ESSENTIAL BUS
What is the voltage of the DC power system? 28V via the TRU's
What would cause an IDG fault? Low oil pres, High oil temp
What would cause an IDG DISC message? overtemp, over torque
Describe the APU Battery 43 Amp, 24 Volt, Powers ADG Deploy and APU start, Charged by AC UTIL BUS 2
Describe the main Battery 17 Amp, 24 Volt, Charged by AC UTIL BUS 1, Powers 4 busses: L/R bat busses, main bat bus, APU bat bus, DC emergency bus
Describe the ADG power
T/F The APU bleed air directly feeds the right side of the 10th stage manifold to feed the right pack. FALSE, it supplies the Left pack
In case of failure of both packs, _ _ can be used as the sole source of ventilation. Ram Air
The Left pack primarily supplies the flight compartment _% and supplements the flow to the passenger cabin _%. 70/30
T/F In the Air Conditioning system the dual bypass valves modulate as necessary to blend bypassed hot air with cooled air cycle machine air to achieve the selected temperature. TRUE
Pack Fault Light indicates a(n) _ or _ condition has been detected. Overpressure/Over Temperature
If live cargo is being transported at high ambient temperatures, the cargo switch should be only be set to _ _ after takeoff. COND AIR
T/F The CPKT and CABIN temp control knobs adjust the temp setting for the related compartment. TRUE
Rotation of the V/S pitch wheel changes the pitch reference value by _ degrees per click. 1/2
The vertical takeoff mode generates a _ degree pitch up flight director command. Loss of an engine limits the pitch up command to _ degrees. 15, 10
Go-Around mode generates a _ degree pitch up command. 10
Automatic switchover from IAS to Mach occurs when climbing through _ feet. 31,600 (AFM)
T/F The square HDG push button on the FCP selects or deselects the heading mode. TRUE
When a pilot selects a HDG change > _ degrees, the aircraft will initiate a roll in the direction of the selected heading change. 180
Aircraft limitations prohibit the use of ___ submode during approach (either FD or autopilot coupled). DES
Automatic transition to half-bank mode occurs when climbing above _ feet (PA) or if the airplane is above half-bank transition altitude when the flight director is engaged. 31,600
Half bank mode reduces the maximum command bank angle to _ degrees. 15
The yellow ROLL comparator flag is displayed when a difference of _ degrees (in level flight) or 3 degrees (during approach) is detected between AHRS roll data. ?
Traffic advisories (TA) indicate the relative positions of intruding airplanes that are about _ seconds from the closest point of approach (CPA) and may require a later resolution advisory. 40
The TCAS resolution advisory programs are based on the pilot initiating the RA maneuver within approx _ seconds. 5
Pitch-Limit Indicator (PLI) (yellow)-displayed during windshear warning or alert for a minimum of _ seconds- it displays the maximum pitch attitude that can be made before encountering the stall angle-of-attack. 60
For aircraft equipped with Mach transducers, each Mach transducer supplies primary Mach compensation data to the _ _ computer. Stall Protection
The radio altimeter provides absolute altitude in a range of 0 to _ feet. 2500
The AUTO X FLOW INHIB- EICAS message will remain if the fueler leaves the power switch on the Refuel/Defuel control panel selected ON. TRUE, will be manual & not able to do automatically
The green low speed awareness indicator bar indicates _ times the computed stall speed. 1.27
An _ knot range on the airspeed scale is always in view. 80
_ 100 amp, Transformer Rectifier Units convert the AC supply to 28volts DC, and power the airplane's buses. 5
The ADG (Air Driven Generator) is automatically deployed if there is a complete _ _ failure. AC Power
The ADG is pushed into the airstream, where _ _ turns the turbine. Ram Air
The main generators are _, 115 VAC, three phase, 400Hz, integrated drive generators. 30KVa
Power to the AC service bus is supplied directly from the _ _ _ or the _ _. External Power Receptacle / APU Generator.
The AC service bus is supplies power to those circuits necessary for _ _ _, without having to energize the remainder of the electrical system. Ground Servicing Operations
Bus priority for AC bus #2 is: IDG2 - APU - IDG1 - External Ground Power
The EXT AC PUSH green AVIAL light in the external service panel illuminates when the connected AC power _ voltage and frequency are correct. Phase
During AFCE operation, trim rate is determined by _ movement. Flap
During an aileron mistrim condition, and with the autopilot engaged, the yellow aileron mistrim indicator appears on the _. PFD
Some CRJ 200's have _ flap detent positions, while some CRJ 200's have _. 5/4
There are _ spoiler panels on each wing. 4
Ground flight spoilers are retracted in flight, or deploy to _ degrees after landing. 45
Flight spoilers can be extended from 0 to _ degrees. 50
T/F Operation of the flap system is controlled by HYD system #3. False
T/F The ground lift dump system is fully automated? True
T/F Operations of mobile transceivers in close proximity to the smoke detectors may cause a false alarm. True
Slow metering of the cargo fire ext. system last approx 30 min, but will give protection for _ minutes. 45
The CARGO BTL LO caution message may take up to _ minutes before it extinguishes, as the cargo FIREX bottle gradually discharges. 20
The airplane has _ portable fire extinguishers. 3
T/F The main landing gear overheat detection consists of a dual loop overheat detection? False
The Cargo compartment extinguisher system uses _ firex bottles. 2
_ smoke detector(s) monitor the cargo compartment. 2
_ heat sensitive fusible plugs are in each wheel. 4
The APU receives fuel directly from the _ tanks by the crossover/APU pump. Main
The fuel temperature is continuously monitored by a fuel temp sensor in the _ wing. Left
If one wing fuel quantity is less than _ pounds, that wing's quantity readout turns amber. 450
When left or right wing tank drops below _% full, the fuel system computer activates fuel transfer until the respective tank fuel level is 97/100% of it's capacity. 94
Automatic fuel crossflow is maintained until a fuel imbalance of _ pounds is reached in each tank selected for crossflow ( "low wing" ) +50
The fuel tanks are vented and slightly pressurized by a _ scoop. NACA
T/F Fuel boost pumps, when armed, serve as a backup to the main ejectors. True
Maximum zero fuel weight is _ pounds. 44,000
Each hydraulic system operates at _ PSI. 3,000
Overall length of the CRJ is _'_". 87/10
T/F There is no EICAS caution or warning for the crew escape hatch. True
Maximum landing weight is _ pounds. 47,000
If IDG2 is disconnected, hydraulic pump _ is shed. 1B
The heat exchanger cools hydraulic fluid in the _ and _ hydraulic systems through ram air flow. #1/#2
ACMP 2B provides backup to the right engine driven fuel pump and is supplied power from _ _ _. AC Bus #1
A(n) _ _ augments air flow through the heat exchanger for hydraulics on the ground. Electric fan
AC motor pumps _ and _ do not automatically start during or after and engine failure. 1B/2B
The respective AC hydraulic pump operates in AUTO when _ and associated generator is online. Flaps are out of the 0 degree position
The windshield wiper switch on the pilot and co-pilot side simultaneously controls _ wiper(s). Both
T/F The CRJ has three independent ice detection systems. False
If bleed air is not supplied from one engine, the opposite engine can supply bleed air to both wings by the _ _. ISOL Valve
With the landing gear not in the down and locked position, the warning horn cannot be muted if flaps are selected to _ degrees or more. 30
There are _ brake wear pins on each brake assembly. 2
In the event of a failure of _ or _ hyd systems, accumulators in both hyd systems provide reserve pressure for six brake applications with the anit-skid off. #2/#3
Loss of _ or _ hydraulic systems leaves the aircraft with 50% symmetric braking capability with full anti-skid control to the working brakes. #2/#3
During initial, final takeoff, and landing phases, the _(s) process inhibit logic to minimize distracting warning or caution messages. DCU (Data Concentrator Unit)
Inboard and outboard brake pressure caution message display if the system is less than _ PSI. 1030
There should be a _ minute delay between cranking attempts to allow for cooling of the APU starter and drainage. 2
The recognition/taxi lights illuminate automatically when the associated _ _ is selected on. Landing Lights
If a fire extinguisher is discharged in the _ compartment, all flight crew must wear oxygen masks with the EMER selected to 100%. Flight
The chemical oxygen generator supplies approx _ minutes to each mask. 13
T/F The N2 rotor is a 16 stage axial flow compressor. False
_ _ switches on the thrust reverser panel drive the TR equipment to the stow position, should the automatic system fail. EMER STOW
_ _ gauges replace the oil pressure gauges when oil level is normal. Fan Vib
T/F 18 dual orifice fuel injectors are on each engine. True
IGN-B, on both engines, is powered from a static inverter on the _ _ bus. DC Battery
With the APU armed and engines operating in N1 mode, a drop to _% N1 on either engine causes the APR system to command N1 speed increase on both engines. 67.6
A minimum of _ PSI and 24V DC are required for engine starts. 40
The CPAM automatically deploys the passenger cabin oxygen masks when cabin altitude reaches _ feet, and illumination of the seat belt/no smoking sign when cabin altitude reaches _ feet. 14,000/10,000
If the airplane maintains an altitude of _ feet or less above takeoff airport elevation, and then begins a descent at 1,000FPM or more, the system assumes the landing elevation is the departure airport. 6,000
T/F The pressurization system includes two outflow valves. True
The pressurization system has _ identical and redundant cabin pressure controllers when operating in automatic mode. 2
Cabin altitude rate of change is limited to _ FPM climbing and _ FPM on descent. 500/300
Advisory messages are set in _ at the top of the stack of messages on ED2. Green
T/F Advisory messages can not be removed from view, unless the applicable system or switch has been deselected or deactivated. True
T/F Warning messages can not be removed from view, unless the applicable failure is rectified. True
Caution messages appear in _. Amber
The lavatory wash water system uses a _ gallon water tank. 5
The galley potable water system contains a _ gallon water tank. 8
ELECTRICAL POWER PANEL - DC SERVICE SWITCH Used by Mx and Gnd Personnel, Operates Nav, Lav, and Dome, Powers DC Sevice Bus
ELECTRICAL POWER PANEL - BATTERY MASTER switch 2 Batteries, Main 17 Amps, APU 43 Amps, 5 minute limit due to CRTs, 2 24v NICAD Batteries, 22v Min for Engine Start
ELECTRICAL POWER PANEL - EXT DC power switchlight AVAIL: Correct voltage and polarity
ELECTRICAL POWER PANEL - EXT AC power switchlight AVAIL: Correct Phase-3, Frequency-400Hz, Voltage-115v
ELECTRICAL POWER PANEL - IDG 1 and IDG 2 switchlights Used to disconnect IDG from engine. Cannot be reset in flight, reset by MX personnel on ground. FAULT (amber) light indicates a fault within IDG. HOTLOP (High Oil Temp or Low Oil Press). DISC (white) light indicates selected disconnect is successful Over-
ELECTRICAL POWER PANEL - AC ESS XFER Used to switch essential bus feed from AC bus 1 to AC bus 2. The ALTN (white) light indicates essential bus is fed from AC bus 2. Transfer is automatic during an AC bus 1 failure. Can also be powered from the ADG bus.
ELECTRICAL POWER PANEL - GEN 1, GEN 2, APU GEN ON – Connects generator to associated bus. OFF/RESET – Disconnects generator from associated bus and/or resets the generator control circuit.
ELECTRICAL POWER PANEL - AUTO XFER switchlights OFF (white) light indicates autotransfer is selected off. FAIL (amber) light indicates a fault preventing autotransfer.
ELECTRICAL POWER PANEL - DC POWER TIE 1 + TIE 2 switchlights CLOSED – Illuminates white to indicate the corresponding DC bus has been automatically tied to the service TRU during an abnormal condition, or has been pressed in to manually tie corresponding bus to the service TRU. Indicates the corresponding utility b
ELECTRICAL POWER PANEL - ESS TIE switchlight CLOSED – When pressed in, illuminates white to indicate that ESS Bus has been manually tied to the service TRU during a DC essential TRU failure. ESS TIE Switchlight can only be selected manually.
EXTERNAL LIGHTS PANEL - BEACON If not turned on within 5 minutes of both engines started: FDR (Flight Data Recorder) Fail Status Message
LANDING/TAXI LIGHTS PANEL - LANDING LTS, RECOG TAXI LTS Landing lights no known limit, Recog taxi lights 10 minutes max when stationary
PASSENGER SIGNS PANEL - SEAT BELTS AUTO: Landing Gear Extended, Flaps out of 0 degrees, Cabin Alt exceeds 10,000' (CPAM)
EMERGENCY LIGHTS PANEL - EMERGENCY LIGHTS ARM: Int and Ext emergency lights illuminate if DC ESS power fails, Turned on by overhead panel and Flt Attendants station.
FIRE DETECTION PANEL - When is Fire Protection/Detection available and what parts of the aircraft have fire/overheat detection? 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
FIRE DETECTION PANEL - fire TEST WARN Simulates Fire (APU bottle blows if selected with failed APU loop) by grounding loops to check continuity
FIRE DETECTION PANEL - fire TEST FAIL Checks for shorts in system, Simulates overheat by grounding loops to check continuity
FIRE DETECTION PANEL - fire bottle TEST 1. Checks continuity of squibs, 2. Checks bottle pressure
FIRE DETECTION PANEL - cargo bottle TEST 1. Checks continuity of squibs, 2. Checks bottle pressure, 3. Checks respective smoke detector
GLARESHIELD - FIRE Pushbutton (switchlight) 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
CABIN PRESS PANEL - EMER DEPRESS Press when directed by QRH, Opens both outflow valves, Maintains cabin pressure at 14,250' +/- 750'
CABIN PRESS PANEL - PRESS CONT switchlight 1. Press once to enter manual mode, 2. Press twice to change pressure controllers
CABIN PRESS PANEL - PRESS CONT FAULT Both cabin pressure controllers failed
CABIN PRESS PANEL - PRESS CONT MAN Manual mode selected, removes electrical supply from both outflow valves, locks them in current position and allows manual (pneumatic) operation
CABIN PRESS PANEL - Cabin pressure controllers switch when: 1. Weight on wheels + 3 minutes, 2. One cabin pressure controller fails
CABIN PRESS PANEL - MAN ALT switch Modulates outflow valves, used in manual mode
CABIN PRESS PANEL - MAN RATE Pneumatically adjusts outflow valve rate during manual mode
CABIN PRESS PANEL - CPAM Messages CABIN ALT Caution CABIN ALT Warning CABIN ALT Caution = cabin altitude 8500' to 9999', CABIN ALT Warning = cabin alt > 10000', at 14,000' Pax O2 masks deploy
AIR CONDITIONING PANEL - PACK FAULT light Overpressure or over temperature, Left Pack 70%cockpit/30%cabin, Right Pack 30%cockpit/70%cabin
AIR CONDITIONING PANEL - PACK OFF light Associated pack pressure regulating shutoff valve closes, no airflow into the pack
AIR CONDITIONING PANEL - RAM AIR switch Provides ambient air to left conditioned air supply duct (cockpit). Press when directed by QRH or MEL. Primary purpose is avionics cooling
AIR CONDITIONING PANEL - CARGO switch OFF- Off, FAN- Adds air from cabin, COND AIR- Adds heat
ANTI-ICE PANEL - WING Anti-Ice Switch Controls operation of left and right wing (modulating and shutoff) valves. NORM – Anti-icing controller operates modulating/shutoff valves to maintain a constant wing leading edge temperature of 107 ± 8° C. OFF–Closes modulating/shutoff valves and shuts d
ANTI-ICE PANEL - WING OVHT/DUCT FAIL Switchlight Used to test bleed air leak detection system and to indicate failures/overtemp conditions.
ANTI-ICE PANEL - COWL LH/RH Switches Controls operation of cowl anti-ice shut-off valves.
ANTI-ICE PANEL - DET ICE Switchlight ICE – Lamp illuminates amber to indicate airplane entry into icing conditions with both anti-icing systems not selected on. TEST – When switch is pressed, system is tested simulating an accumulation of ice on the ice detectors. This test also checks the p
ANTI-ICE PANEL - WSHLD LH/RH Switches Used to heat windshields and windows. HI – High temperature heat 41 °C to corresponding windshield (and low level 24 °C to side window). LOW – Low temperature heat 24 °C to corresponding windshield, and side window. RESET/OFF – Windshield and window heat
ANTI-ICE PANEL - WSHLD TEST Switch Used to test windshield anti-ice system; simulates a no-heat condition. MX function.
ANTI-ICE PANEL - PROBES LH/RH Switches OFF – All probe heaters are off when there is no AC power online. ON – With AC power on-line or external power, probe heat is as follows: TAT – OFF, Static and AOA – ON, Pitot and Base – Half power heat, All probe heat turns ON with weight off wheels
BLEED AIR PANEL - DUCT MON Used to check serviceability of detector loops in left and right sections of 10th and 14th stage systems. TEST – Tests 10th/14th stage loops by grounding loop to simulate a duct failure. LOOP A/B – Tests Loop A or B of 10th stage for continuity, to ensure
BLEED AIR PANEL - L/R 14th STAGE Switchlights Controls the 14th stage bleed air shutoff valves. DUCT FAIL – Indicates bleed air leak in applicable duct. Illuminates during duct monitor test. CLOSED – Indicates shutoff valves fully closed.
BLEED AIR PANEL - 14th STAGE ISOL Switchlight OPEN – Indicates isolation valve has been selected open
BLEED AIR PANEL - 10th STAGE L/R Switchlights When pressed in, associated bleed air shutoff valve opens and CLOSED (white) extinguishes. When pressed out, associated bleed air valve closes and CLOSED (white) illuminates. DUCT FAIL (red) – Illuminates if bleed leak detector sensors detect a failure in
BLEED AIR PANEL - APU LCV Switchlight OPEN – APU LCV selected open. FAIL – APU LCV open when commanded by the interlock protection circuit.
BLEED AIR PANEL - 10th STAGE ISOL switchlight When pressed in, bleed air isolation valve opens and OPEN (white) illuminates.
FUEL PANEL - L/R BOOST PUMP Switchlights Pressed in – For engine start, both boost pumps are activated. With both engines running, the pumps remain armed and automatically come on when low fuel pressure is detected in any engine feed line. The switchlights show ON when the pumps are operating. P
FUEL PANEL - GRAVITY/XFLOW Switchlight Pressed in – Opens the balance line SOV, OPEN light illuminates. Pressed out – Closes the balance line SOV, OPEN light extinguishes. FAIL light illuminates to indicate the balance line SOV is not in the commanded position.
FUEL PANEL - L/R XFLOW Switchlights (With AUTO OVERRIDE Switchlight pressed in, manual mode) Pressed in – Respective crossflow SOV opens and crossflow/APU pump goes on, ON light illuminates. Pressed out – Respective crossflow SOV closes and crossflow/APU pump goes off, ON light extinguishes.
FUEL PANEL - L/R XFLOW Switchlights (With AUTO OVERRIDE Switchlight pressed out, automatic mode) ON light illuminates to indicate the respective SOV is open and the crossflow/APU pump is on. FAIL light illuminates to indicate the respective crossflow SOV is not in the commanded position or the crossflow/APU pump fails to go on with the left or right
FUEL PANEL - AUTO OVERRIDE Switchlight Pressed in – XFLOW/APU pump is armed for manual crossflow, automatic crossflow is disabled. MANUAL light goes on. Pressed out – XFLOW/APU pump is disarmed for manual crossflow, automatic crossflow is enabled. MANUAL light goes out.
APU PANEL - PWR FUEL switchlight Used to control APU fuel pump. When pressed in, crossflow/APU pump is energized, APU IN BITE, APU gauges energized, door scheduled to open, and APU fuel shut-off valve opens. PUMP FAIL (amber) light indicates that APU fuel pump has failed. SOV FAIL (amber
APU PANEL - START/STOP switchlight When pressed in, starter motor is energized and START light (white) illuminates. At 50% rpm, START light extinguishes. At 95% rpm, and 4 seconds later, AVAIL light (green) illuminates. When pressed out FCU shut-off valve closes, APU shuts down, and AVAIL
ENG INGNITION PANEL - L/R START switchlights Used to initiate engine start sequence. START (white) light indicates start is selected.
ENG INGNITION PANEL - L/R STOP switchlights Used to stop engine start sequence. STOP (white) light indicates stop is selected.
ENG INGNITION PANEL - IGNITION A and B ARM (green) – Arms respective ignition system on both engines. ON (white) – Indicates the ignition system is activated.
ENG INGNITION PANEL - CONT Used to select continuous ignition of both ignitors on both engines. ON (white) light indicates continuous ignition is selected on.
ENG INGNITION PANEL When is ignition A used and when is B used? What are their power sources? When is starter cutout? Ignition A on odd days, ignition B on even days. Ignition A is AC powered, ignition B is DC powered through a static inverter (can start on battery only, no AC power required). Starter cuts out at 55%
FUEL PANEL - XFLOW FAIL valve is not in commanded position
FUEL PANEL - BOOST PUMP INOP Boost pump not on. Low pressure. Boost pump failed
FUEL PANEL - When is auto fuel transfer At 200# imbalance, fills to +50#
FUEL PANEL - When is fuel transfered from center tank to main tanks? 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)
FUEL PANEL - How does the fuel flow from center tank to engine? 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
HYDRAULIC PANEL (3 systems) System #3 Largest reservoir, Serviced and located in right main wheel well, Cooled via a fuel heat exchanger in right wing (L wing contains bulk fuel temperature probes)
HYDRAULIC PANEL Systems #1 and #2 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
HYDRAULIC PANEL Describe Pumps 2 Engine driven pumps (1A,2A), 4 AC 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)
HYDRAULIC PANEL Which pumps are lost during engine failure? Lost left engine, lose 1A & 2B. Lost Right engine, lose 2A & 1B
HYDRAULIC PANEL Normal ops quantity and pressure: 45-85% system quantity, 1800-3200 PSI
Created by: sketch88