AIRCRAFT GENERAL - Minimum taxi strip width for a 180º turn: - Based on maximum nose wheel deflection (80º): 62 ft - This dimension is critical to avoid wingtip or tail strikes with ground obstacles during tight maneuvers. - Selecting MASTER LIGHTING CONTROL knob to OFF: - Sets cockpit lighting for daylight conditions (panel backlights off, switchlights full bright) - Opening Cabin Door from the inside: 1. Engine and APU bleeds off and verify cabin is unpressurized. 2. Lift secondary latch release handle (cherry handle) and hold it. 3. Using the palm of an open hand, push primary handle up and outward. 4. Let go of both, and the door will open. - Opening Baggage Compartment Door from the inside: 1. Rotate door handle up and aft to unlock door. 2. Using hand grips, pull door inward and slide upward on tracks. - Crew and passenger oxygen masks not approved for use above: - 40,000’ cabin altitude. - Tire speed limitation exceeded: - Touchdown in excess of 195 knots groundspeed. - Total number of aircraft occupants shall not exceed: - 22. - Maximum Ramp weight: - 91,400 lbs. - Potable water tank servicing: - Can be serviced internally and externally to 30 US gallons. - Missing items from the aircraft on pre-flight: - Refer to CDL (Configuration Deviation List), which outlines permissible missing or inoperative non-essential equipment. - Windshear is active: - During take-off until 1500’ AGL. - During approach from 1500’ to 10’ AGL. - During missed approach until 1500’ AGL. - Windshear Amber message on PFD during take-off: - Indicates increasing performance. - Windshear Red message on PFD during take-off: - Indicates decreasing performance. - Honeywell Planeview CMF (Communication Management Function): - Communicates via land-based ACARS VHF network or Satellite. - CMF message transmission period: - Attempts to send messages through all available channels for six minutes. - Access Planeview CMF displays: - Push the DLK (datalink) function key on the MCDU. - ATC will forward a PDC (Pre-Departure Clearance): - To GDC for storage approximately 20 minutes prior to the filed departure time. - TOLD (Takeoff and Landing data) MCDU (FMS) performance: - Evaluated by the FAA for accuracy and is acceptable for use per AFM (Aircraft Flight Manual) limitations. - Maximum runway slope approved for take-off and landing operations: - $+2$% (uphill) and $-2$% (downhill). - Caution when maneuvering in tight spaces: - Swept wing growth. - Maximum Take-Off Weight: - 91,000 lbs. - Maximum Zero Fuel Weight (ZFW): - 54,500 lbs (52,000 - JAA). - Max Landing Weight: - 75,300 lbs. - Minimum Control Speed Air: - 112 KCAS. - Additional evacuation trained crew member required when: - 10 or more passengers are onboard. ## PLANEVIEW - Observing ON BAT on the IRS switch: - Indicates IRS is not on its primary electrical source. - In-Flight IRS Alignment requirement: - GPS required. - GPS antenna power source: - MAU via GPS MAU card. - Making in-flight alignment faster: - Make turns, accelerate/decelerate. - Number of GPS needed for alignment: - One valid GPS. - Polar Navigation approved provided: - True heading is selected prior to N73º and S60º Latitude. - Finding RAIM check menu: - NAV menu / pos sensors / GPS / LSK 6. - Default display on DU2: - MAP, PRIMARY ENGINE INSTRUMENTS, SECONDARY ENGINE INSTRUMENTS. - Change DU2 to ECS/PRESS: - Use Display Controller / 2/3 / DU2 Main / Next / ECS Press or CCD Menu ECS/PRESS. - Access CHK LST on DU3 Lower: - Use DISP Controller / Push CHK LST button or CCD Menu CHECKLIST. - Change DU1 lower to TRAFFIC: - Use Display Controller / 1/6 / DU1 Lower {2L} / Traffic or CCD – DU1 - Menu TRAFFIC. - Power sources for MAUs: - Check MAU Function / Failure Matrix in QRH. - Power sources for each MAU: - Each MAU has four (4) power sources. - Circuit Breakers (CBs) for each MAU: - Four (4) CBs. - DU1 failure consequence: - DU2 switches to PFD Display. - DU2 and DU3 failure consequence: - PFD on DU1 and DU4. - DU2 and DU3 failure MAP operation on DU1 or DU4: - Hold 2/3 button for 3 seconds, push MAP on respective Disp Controller. - Red vs Black Circuit Breakers: - Red - ESS DC bus power; Black - MAIN DC bus power. - Power Source for DU1/DU4: - L ESS (DU1); R ESS (DU4). - Power source for DU2 and DU3: - DU2 is (L MAIN / L ESS); DU3 is (R MAIN / R ESS). ## PLANEVIEW (RNP, EPU, LPV, TEMPERATURE COMPENSATION) - Place CHECKLIST on DU1 Lower: - On Disp Cont push 1/6 / select DU1 Lower / Next / Checklist {3} or CCD - DU1 - Menu – CHECKLIST. - Default display for WX RADAR/TERRAIN: - MAP. - Select WX / TER on PFD / HSI: - Display Controller / PFD / Box WX or TER. - Using CCD for WX / TER on PFD: - No. - Items boxed by default on MAP on power-up: - TERRAIN / OBSTACLES / TRAFFIC / WEATHER. - MAP display increases Pilot’s: - Situational Awareness. - Displaying runway LOCALIZER feathers: - Select AIRPORTS on MAP DATA & scroll down the range until feathers appear. - FMS active leg displayed on MAP: - Magenta line. - Current aircraft position not on map: - Aircraft symbol changes to magenta and is placed on the edge of the map. - Auto speeds (V1, VR, V2) display up to: - 1500 feet. - F/D CMD bar on T/O pitch: - FMS calculates nose-up angle based on V2+10 kts speed (two engine); single-engine based on V2 to V2+10 kts. - Auto throttles on take-off “HOLD” appearance on PFD at speed: - 60 knots. - Pilot Not Flying callout at 60 knots: - “Power Set” or “EPR low, increase power.” - Auto throttles (power levers) stay in HOLD mode up to: - 400 feet. - Changing range on HSI: - YES. - Max in WX / 300 (WX boxed); Max in TERRAIN / 500 (TER boxed). - Abnormal of DU1 and DU4 in PFD mode with DU2 & DU3 blank: - Capt cannot select MAP on DU1 after Co-Pilot has selected MAP on DU4. - If down to only one DU, it displays: - PFD or EICAS (Alternate Primary Engine Inst + CAS). - Changing to MAP with only one DU: - No. - Pilot-controlled DU’s: - DU’s 1, 2 & 3. - Co-Pilot controlled DU’s: - DU’s 2, 3 & 4. - Check Charts date location: - MAP / CHARTS / TOP WORLD CHARTS (upper left). - Chart date in CMC: - YES (CMC / DB CONFIG / NEXT). - Take-off speeds calculated check: - MCDU / FPL / Page 1 for T/O SPD and Vertical Performance numbers. - AUTO VSPD 1 vs AUTO VSPD 2: - AUTO VSPD1 indicates auto speeds from FMS 1; AUTO VSPD2 indicates auto speeds from FMS 2. - Amber VSPD on speed tape and speed unboxed indicates: - Comparator problem on ground. - When FMS auto speeds change after take-off: - When flap position is changed or a new vertical mode (i.e., FLCH, ASEL) is selected. - AGM failure indication: - Red “X” on any Display Unit. - Take-off checks on Guidance Panel / PFD: 1. GUIDANCE PANEL 2. ALTITUDE SET 3. LATERAL MODE (HDG, LNAV, etc.) 4. V2 SPEED 5. MAN HEADING / LNAV (After selecting TOGA for direction control) 6. PFD CMD-L (for left seat take-off). - Good time to switch to Electronic Checklist: - BEFORE STARTING ENGINES CHECKLIST (Available after APU start with AC power). - Deferred items in the Electronic Checklist: - YES (option at bottom of checklist synoptic). - Recalling Electronic Checklist deferred items: - Recall. - Undo a checklist item: - YES. - Override a checklist: - Select CHECKLIST, go to bottom, select CHECKLIST FUNCTION, select OVERRIDE. - Checking charts up to date: - CHARTS (far left drop-down menu) / REVISION INFO or CMC / DB CONFIG. - Heading information to the SFD (Standby Flight Display): - Magnetometer. - Normal order of heading source information for the EBDI: - IRS1 / IRS2 / Magnetometer. - STBY instruments called: - SFD and EBDI. - Power source for STBY instruments: - EMER FLT INST BUS (E-BATTS). - “ooo” presentation on STBY INST menus: - SUBMENUS for that item. - HDG Mode on EBDI: - HDG 1 / AUTO. - NAV radios sending info to EBDI: - NAV 1 / NAV 2. - Take-off with red flag on EBDI: - Check MEL. - Radio tuning performed at: - MCDU’s / RADIO button / PROGRESS button (optional for some VHF NAV frequencies). ## AUTO SPEED SCHEDULE - 200 kts – ATA (Airport Traffic Area). - 250 kts > ATA ## ELECTRICAL - HMG (Hydraulic Motor Generator) provides: - AC Power to AUX TRU (Auxiliary Transformer Rectifier Unit) and Standby AC Buses. A TRU converts AC power to DC power. - Normal AC power source for AUX TRU and ESS AC bus: - L MAIN AC bus. - If L MAIN AC bus unpowered, AUX TRU and ESS AC bus switch: - YES (to R MAIN AC bus). - DEAD BUS power logic for AUX TRU: - ESS bus before MAIN; LEFT side before RIGHT side. - E-inverter purpose: - Provides AC Power for ESS AC bus (Essential Alternating Current bus) if it loses power. - Normal position of E INV switch: - AUTO. - Wait duration between selections of L ESS and R ESS when using HMG: - 10 seconds. - 60Hz converter use: - Power outlets in galley and passenger cabin. - L MAIN AC BUS loss action: - AUX TRU transfers to R MAIN AC BUS; AUX TRU Powers L ESS DC Bus; ESS AC bus transfers to R MAIN AC bus. - Power L MAIN DC BUS in above situation: - Use L TRU switch, observe RAC (switch capsule). - ESS DC buses’ simultaneous power sources: - L/R Main batteries; AUX TRU (when powered by HMG). - When RESET switch is pushed: - CAS MSG / CHECKLIST says to push. - MAIN BATTERY switches illuminate ON when: - Powering ESS buses (batteries being used); APU starting; AUX pump operating. - BREAK POWER TRANSFER: - Momentary interruption of power to one or several buses. - Automatic power transfers will be NBPTs (Non-Break Power Transfers) except between: - External AC power and APU generator. This means other transfers happen without power interruption. - BUS TIE ISLN SWITCH function: - Prevents/allows alternate power sources to power failed bus side; allows you to isolate buses. - GEN switch color when generator off: - Black – Grey. - GEN switch appearance if GEN FAILED: - Amber “OFF.” - GND SVC Bus powered on the ground: - R MAIN DC BUS when available; R battery or directly from external DC power receptacle when using one of three switches. - GND SVC BUS powered check: - Beacon illuminated. - Look at Electrical Panel to tell if GND SVC BUS is powered: - GND SVC BUS capsule shows “ON”. - GND SVC BUS in flight powered by: - YES (by R MAIN DC bus). - GND SVC BUS switches location: - 3 switches: Forward External Switch Panel Access Door; Tail compartment; Remote Refuel Panel behind Captain seat in cockpit. - Generator failure indication on synoptic: - GEN outlined in Amber. - GND SVC BUS turn off condition: - Yes, when main cabin door, forward external switch panel access door, and tail compartment door all closed. - Number of E-Batts: - Four (4). - E-Batts purpose: - Avionics Power (2); Emergency Lighting (2). - Avionics E-Batts Power: - These two batteries power critical cockpit displays and controls such as Clocks; STBY INST Panel (SFD/EBDI); Gear Handle and Indicator; MCDUs 1 & 3; CAPT Audio Panel. - Emergency Batteries (E-Batts) activate when: - An ESS DC bus power drops below twenty volts. - E-Batts on displays: - MCDU 1 – STBY ENG INST & FUEL; MCDU 3 – BACK UP RADIOS (VHF 1 COM/NAV) and ATC 1. - Emergency battery mode MCDU tuning limit: - Only tune COM 1 / NAV 1 / ATC 1 on MCDU 3. - Cockpit speakers availability in emergency battery mode: - Not available. - ACP on E BATTS illuminated: - Captain – COM 1 / SPKR ICS + Phone + MIC. - Can plug in AC & DC External Power at the same time?: - Yes. - Priority external power source: - AC. - Remove AC external power to auto switch to DC external power: - No, must deselect EXT PWR switch and RESELECT for DC EXT PWR. - Reason to use DC EXT PWR: - Start APU with low battery voltage. ## APU - Lights/items appear during APU fire test: - Eight (8): 2 OVERHEAD / 4 MASTER CAUTION PANEL / 2 CAS. - Guaranteed APU start altitude: - At or below 39,000’ (may start up to 43,000’). This limit is due to decreasing air density at higher altitudes, which affects combustion and turbine performance. - Max operating altitude of the APU: - 45,000’. - APU generator activation: - Comes on when it reaches 99% after 2 seconds. - After APU start and selecting APU bleed air, isolation valve opens automatically: - Load control valve inhibited OFF for one minute after APU online unless EGT > 150º, no delay when airborne. - Difference between ESSENTIAL and NON-ESSENTIAL APU mode: - ESSENTIAL: Air; NON-ESSENTIAL: Ground (15 minutes after landing); not all AUTO shutdowns active in ESSENTIAL mode. - APU start in flight mode: - ESSENTIAL mode. - APU remains in ESSENTIAL mode after landing for: - 15 minutes. - APU ESSENTIAL CAS message indicates: - APU operating in Essential mode; a Non-Essential Shutdown signal sensed. - APU operating in essential mode while airborne: - Stays in ESSENTIAL mode for 15 minutes after landing. - CAS message not displayed after APU Fire Test: - Fire Bottle Discharged. - APU Surge Control Valve operates at what altitude: - 16,500” and above to prevent high altitude compressor stall, which is a disruption of airflow within the compressor that can lead to engine damage. - APU Bleed Air Augmentation Valve (BAAV) operates at: - 35,000’ and higher – allows 400ºF air into APU intake for starting. This hot air is required to maintain the proper temperature for ignition and stable combustion at cold, high altitude conditions. - APU BAAV delay: - 15 seconds to allow APU to warm before starting at altitude. - Temperature range for APU oil tank to be heated: - $+21$ºC to $+43$ºC regardless of APU use. - Depressing APU STOP switch causes APU to: - Shutdown simulating an overspeed. - Performing an immediate APU shutdown: - Push Master Switch. - Emergency condition requiring operation on main batteries only at 41,000’: - If APU available, descend to APU start envelope altitude (39,000’ or below). - APU starter limitations using aircraft batteries: - 3 (three) start attempts; 1 (one) hour cool down period. This cool down period protects the starter motor from overheating. - APU starter limitations using DC external power: - 3 (three) start attempts; 15-minute cool down period between attempts, followed by 1-hour cool down to protect wiring from excessive heat buildup. ## POWERPLANT - Engine tailwind start limit: - 20 knots. - Ignitors used for normal engine ground start: - One (1). - Ignitors used with Continuous Ignition Switch: - Two (2). - FADEC stands for: - Full Authority Digital Electronic Engine Control. - FADEC power channels: - 2 (Channel A and Channel B). - FADEC power sources during engine start before generator use: - Channel A – L ESS; Channel B – R ESS. - FADEC powered by: - Dedicated generator on accessory gearbox. - FADEC channels per engine: - Two (2) – A/B. - If FADEC detects an anomaly during start: - Start aborted. - FADEC failure prevention in primary Engine Pressure Ratio (EPR) control mode: - Soft reversion to Alternate (LP) control mode (AMBER ALT). - Engine Idle Settings: - Yes, LO/HI. - LO idle active: - Flaps ## FIRE PROTECTION - Procedure for a Fire Detect Loop A Fault on Right engine: - Disable (turn off) LOOP A on right engine; Perform RIGHT ENGINE FIRE TEST to verify remaining LOOP B functionality. - Pilot alert for single activated fire loop: - LOOP switch segment illuminated red on Fire Test Switch + red ENGINE FIRE LOOP ALERT message on CAS. - Items for a Fire Test: - Eight (8). - Items for Fire Detection Fault Test: - Eight (8). - APU Fire bottle: - Left (##2) FIRE BOTTLE. - Fire Bottle 1 usage: - To save No 2 FIRE BOTTLE for possible APU FIRE. - Fire detected in APU enclosure automatic actions: - FUEL is automatically shut off at APU fuel control and fuel tank. - Fire detected in APU enclosure fire bottle automatic discharge: - NO, crew must discharge fire bottle using APU discharge switch on APU Control Panel. - Pulling ENG FIRE HANDLE shuts off: - FUEL, HYDRAULICS, ELECTRICS (ENG IDG Generator). - Red “RED PYLON HOT” CAS message indicates: - Bleed Air Leak, 250º F. - Amber “HOT” CAS message indicates: - Electrical Overheat, 150º F. - Control for evacuating smoke from baggage compartment: - EMERGENCY SMOKE EVACUATION valve. - Rotating EMERGENCY SMOKE EVACUATION valve to EVAC smoke position action: - Deflates baggage door seal for smoke to exit around the baggage door. - Extinguisher most effective against electrical fires: - Halon extinguisher, due to its non-conductive properties and ability to suppress fire without leaving residue. - Baggage door seal reinflation after smoke evacuation: - YES, by rotating handle to NORMAL OPS position. - Lavatory fire protection: - Integrated fire detector and extinguisher unit over lavatory trash bins; container with extinguishing agent and discharge tubes capped with fusible alloy. - Fusible alloy characteristics: - Discharge tube caps melt at $170 - 177$°F, directing extinguishing agent into trash bin. This temperature range is selected to activate quickly enough in a fire scenario while minimizing false activations. ## FUEL - Hopper with APU fuel supply line: - Left. - Hopper with fuel tank temperature sensor: - Both for HFRS. - Fuel quantity system test results: - $7000 / 7000 / 14000$ in amber inverse video on all synoptic pages displaying fuel information and amber “L – R FUEL LEVEL LOW” CAS message. - Presetting quantity of fuel added to aircraft: - Remote Fuel Panel cockpit, set total desired fuel load. - Electrical power loss to fuel pumps consequence: - Suction Feed available below 20,000’. Suction feed relies on gravity and engine fuel pumps drawing fuel directly from the tanks. - Check for automatic refueling: - Auto refuel switch on Remote Refueling Panel is selected off since last flight. - Fuel quantity determination on emergency batteries (E-BATTS): - MCDU 1 (Multi Function Display Unit No.1). - Remote Fuel Panel usage: - Set desired fuel quantity; select AUTO; asterisk ($*$) displays next amount to be added. - Manual describing FUELING PROCEDURES: - AOM Chapter 9 Handling & Servicing Procedures 09-02-10 Fuel Servicing. - Transferring fuel from tank to tank method: - Use Inter Tank Valve. - Fuel balancing via INTER TANK VALVE: - Rotate Rudder Trim in direction of HEAVY WING, resulting in ½ trapezoid displacement, then open INTER TANK VALVE. - Pressure refueling and FQSC operation: - Monitors intertank quantities; imbalance of 500 lbs. / 226 Kg interrupts fueling to heavy wing until imbalances reduced to 100 lbs. / 45 kg. - “FUEL LEVEL LOW” CAS message fuel level: - 650 lbs. / 295 kg. - Fuel Hopper capacity: - 190 US gallons / 1283 lbs. Fuel hoppers are designed to ensure a constant supply of fuel to the engine pumps, even during maneuvers or low fuel conditions. - CAS message during fuel balancing when opening X-FLOW Valve: - Blue “FUEL X-FLOW VALVE OPEN”; changes to AMBER “FUEL X-FLOW VALVE OPEN” after 5 minutes. - Fuel out of balance notification in flight: - Blue “FUEL IMBALANCE” CAS. - Fuel imbalance limits: - Ground - 1,000 lbs., In Flight - 2,000 lbs. - Maximum fuel load at normal fuel density: - 41,300 lbs. - HFRS operation temperature: - Opens at 0º C and stops at $+10$º C; FADEC monitoring includes APU switches at AUTO, engine conditions, and electrical power availability. - Electrical power sources for Fuel Pumps: - L MAIN – Left ESS DC; L ALTERNATE – Left MAIN DC; R MAIN – Right ESS DC; R ALTERNATE – Right MAIN DC. ## HYDRAULICS - HYDRAULICS 2/3 Synoptic components power: - GEAR – L / PTU / EMERGENCY BOTTLE; BRAKES – L / PTU / AUX / BRAKE ACCUMULATOR; FLAPS – L / PTU / AUX; NOSE STEERING – L / PTU / AUX; GROUND SPOILERS – L / R; GROUND SPOILER Pop Up – L / PTU / AUX. - PTU automatic operation when armed: - L HYD pressure drops below 1500 psi; assumes loss of left hydraulic system pressure. - Pressurized power transfer unit (PTU) motor side: - Driven by right hydraulic system pressure. - AUX pump automatic operation when armed: - L HYD and PTU pressure below 1500 psi and brake pedals pressed more than 10º (pump locks on). - Brake Accumulator pre-charge: - 1200 psi. - L HYD SYSTEM fluid depletion but AUX fluid remains: - AUX Pump can provide braking. - GEAR EMERGENCY BLOWDOWN accumulator pressure charge: - 3100 psi. - Turning off L/R Hydraulic system to get zero pressure: - Pull L/R Fire handle. - Pulling Engine Fire Handle shuts off: - Fuel, Hydraulic pressure, Engine Generator (IDG). - Fluid quantities of the L/R Hydraulic system reservoirs: - Left – 4.8 gallons; Right – 1.6 gallons. - Loss of Left Hydraulic system consequences: - Left Thrust Reverser lost. - No other means of pressurizing LEFT HYD system where AUX pump provides pressure for: - Flaps, Brakes, and Nose Wheel Steering. ## LANDING GEAR - Pins removed before flight from landing gear and door system: - Six (6) pins; three (3) Gear; three (3) Gear Door. - Do not lower landing gear using alternate system at speeds in excess: - 175 knots. - Gear Extension Speeds: - Gear – 225 (extension); 250 KCAS once down. - Preflight action if gear uplock is closed: - Pin the gear door valve OPEN; Turn on external battery switch at Left Front Access panel; Actuate AUX pump until gear door and uplocks open; Remove gear door pin; Actuate AUX pump again until gear door closes; Turn off external battery switch. - If landing gear fails to retract: - Do NOT RETARD throttles to IDLE in flight; UNARM the Ground Spoilers. - Emergency landing gear extension procedure: - YES, using Emergency Landing Gear Handle (EMERGENCY BLOWDOWN). - Emergency Landing Gear Nitrogen Bottle Pressure: - 3100 PSI. - Illuminated GEAR HANDLE light during gear retraction: - Landing Gear and/or Gear Doors are NOT retracted (up and locked). - GEAR HANDLE light extinguish condition during gear extension: - When the landing gear is down and locked (gear door position not considered). - Landing Gear Warning HORN sound conditions: - Anytime Flaps selected > 22º; Aircraft Altitude ## BRAKES - ANTI SKID braking availability: - L HYD SYS / PTU/ AUX SYS. - ANTI SKID protection availability with PARK/EMER BRAKE: - NO. - Minimum accumulator pressure to set PARKING brake: - 1700 PSI; recommended to pressurized to 3000 PSI. - Maximum brake pressure using PARK/EMER BRAKE or during NO ANTISKID BRAKING: - 400 PSI. - BRAKE PRESSURE display change when ANTI SKID selected OFF: - PRESSURE scale changes to MAX 800 PSI and begins appearing at 400 PSI. - Valid BRAKE WEAR INDICATION requirement: - PARKING BRAKE MUST be SET. - DACU supplies wheel speed input of knots to which items for operation: - GROUND SPOILERS AND THRUST REVERSER. ## NOSEWHEEL STEERING - Proper position of OVERTRAVEL indicator on Nose Strut during PRE-FLIGHT: - FLUSH with steering collar. - TILLER STEERING below 18 knots ground speed: - 80º left and right. - RUDDER PEDAL STEERING normally provides: - 7º left and right; if TILLER STEERING FAIL CAS message is displayed, rudder pedal authority increases to 16°. ## WEIGHT ON WHEELS - AMBER WOW FAULT message during flight: - SELECT GROUND SPOILER SWITCH OFF and refer to CHECKLIST. - AMBER WOW FAULT message indication during flight: - BOTH MAIN GEAR WOW switches in GROUND mode. - BLUE WOW FAULT message during flight: - REFER to BLUE WOW FAULT message. - Required combined WOW for AIR mode: - ONE MAIN GEAR WOW in AIR mode. - GEAR HANDLE not moving UP after takeoff: - SELECT GROUND SPOILER SWITCH OFF, REFER TO QRH CHECKLIST for LANDING GEAR FAILURE TO RETRACT. - Conditions triggering landing gear warning horn: - Aircraft on ground; ADS indicates ## FLIGHT CONTROLS - Amber “X” on a flight control on Flight Control Synoptic Page indicates: - Flight control RVDT has failed. - LATERAL HOPS occur consequence: - Hydraulic power turned off to both Ailerons. - Jammed Aileron response: - Pull disconnect handle for aileron. - Jammed Elevator response: - Pull disconnect handle for elevators. - Speed Brakes maximum deflection: - Maximum deflection is 30º. - Ground Spoilers maximum deflection: - 55º; control pressure from Left, PTU or AUX system. - Standby Rudder usage loss of Left/Right systems: - Uses AUX pump to YD1; may need to select FGC1; works only while airborne (WOW in FLIGHT). - Flaps controlled: - Electrically requested and hydraulically powered by Left, PTU or AUX pressure; controlled in Flap/Stab computer DC. - Aileron HOPS reset method: - Use QRH and PULL / RESET CBs. - HOPS consequences: - Aileron HOPS shuts off both actuators; elevators and rudder shut down only the affected actuator. - Mechanical trim wheel use requirement: - Select PITCH TRIM switch light to OFF. - BLUE SINGLE RUDDER CAS message indicates: - Rudder power down to one hydraulic power source. - GRD SPOILER FLAP OVERRIDE switch ON behavior: - Flaps > 22º; GROUND SPOILERS deploy automatically with Wheel Speed Spin up. - GPWS/GND SPLR ORIDE switch ON during landing with flaps < 22º: - Prevent nuisance TOO LOW FLAPS aural alert; deploy ground spoilers with wheel spin up. - RED GROUND SPOILER CAS message means: - Failed Ground Spoiler component OR deployed Ground Spoiler Panel. - Loss of one hydraulic system effect on spoilers: - Will not affect spoiler activation. - Horizontal stabilizer remains operative in EMER STAB ARM mode, positioning: - With Yoke Trim Switches. - Selecting EMER STAB switch ON (ARM): - Illuminates ARM in switch; enables EMER STAB mode; stabilizer positioned using YOKE electric pitch trim wheels. - Selecting EMER STAB switch OFF consequence: - Switch dark, EMER STAB mode disabled, stabilizer moves to flap position. - Selecting STALL BARR switch OFF action: - OFF illuminates in switch; STALL BARRIER CAS displays; stick pusher disabled; stall warning stick shaker functionality continues. - STALL BARR switch ON requirement: - Must be on during all flight operations unless malfunction or procedural reasons exist for selection to OFF. - PITCH TRIM ENG/DISENG switch to ENG behavior: - Diseng (AMBER) extinguished; pitch trim engaged, YOKE pitch trim switch active. - PITCH TRIM ENG/DISENG switch to DISENG behavior: - Diseng (AMBER) illuminated; YOKE pitch trim disengaged; manual trim wheel must be used. - YAW DAMP ENG/DISENG switch to ENG behavior: - Diseng (AMBER) extinguished; yaw dampers engaged. - YAW DAMP ENG/DISENG switch to DISENG behavior: - Diseng (AMBER) illuminated; yaw dampers disengaged. - Selecting GPWS/GND SPLR switch to ON: - ON (AMBER) legend illuminated; automatic ground spoiler deployment occurs with flaps <22º and wheel speed spin up; GPWS voice alarm “TOO LOW FLAPS” inhibited. - Selecting GPWS/GND SPLR switch to OFF: - ON (AMBER) legend extinguished; automatic ground spoiler deployment occurs with flaps <22º only when Weight On Wheels has occurred; GPWS voice alarm “TOO LOW FLAPS” not inhibited. - Selecting GND SPLR switch to OFF state: - OFF (AMBER) illuminated; Ground Spoiler System not armed to operate; Gear Down blue “Ground Spoiler Unarm” CAS message appears. - Ground spoiler deployment requirements with flaps > 22 degrees: - Select GND SPLR switch to ARMED (BLUE); both throttles at idle; wheel spin up or WOW ground on each main gear strut. - Operational parameters for NO GND SPLRS red switch lights on center windscreen post: - If operational parameters are satisfied; GND SPLR switch selected to ARMED (BLUE); Left wing, right wing or both wing ground spoilers not deployed. - Flight controls GUST LOCK purpose: - Secures aircraft moveable surfaces in stabilized positions; prevents damage to surfaces and control linkages from high winds or jet blast; effective in winds up to 60 knots. - Depleting hydraulic pressure before engaging GUST LOCK: - Cycle flight controls with control column, yoke, and rudder pedals. ## AIR CONDITIONING, PRESSURIZATION, PNEUMATICS, & ICE & RAIN - Ways to OPEN Bleed Air Isolation Valve: - CRANK MASTER Switch; START MASTER Switch; APU BLEED AIR Switch; MANUALLY. - APU Bleed Switch Isolation Valve opening circumstance: - 60 seconds after APU reaches 100%. - Selecting 8th stage bleed air ON capability: - Cannot be selected, opened automatically by Bleed Air Controller (BAC). - 14 psi, 24 psi, and 35 psi trigger values in the BAC: - 14 psi normal; 24 psi (low power settings: descent/holding); 35 psi (single pack operation). - Minimum pack pressure for single pack operation: - 35 psi. - ¨C269C: - APU & ENGINE BLEED AIR selected simultaneously; ISOLATION VALVE OPEN with BOTH ENGINE BLEED AIR switches ON. - ¨C270C: - 60º - 90ºF. - ¨C271C: - 35º - 230ºF. - ¨C272C: - Reflects actual temperature in supply ducts to air conditioned areas. - ¨C273C: - Both AC packs turn off; A/C depressurizes at cabin leak rate. - ¨C274C: - AUTO, SEMI, and MANUAL. - ¨C275C: - Inhibited below 1,500 feet AGL and above 35,000’. - ¨C276C: - From 35,000’ to landing. - ¨C277C: - 130ºF. - ¨C278C: - Illuminates OFF (BLUE). - ¨C279C: - Two (2) minutes until it turns off or when temperature exceeds 14ºC. - ¨C280C: - Prior to takeoff, engine should be accelerated to 40% LP RPM for 10 seconds and every hour thereafter. - ¨C281C: - Three (3) total: 2 for Automatic and 1 for manual operation. - ¨C282C: - Two (2) A/C (AUTO/SEMI); one (1) D/C (MANUAL). - ¨C283C: - Comes from MCDU. - ¨C284C: - 0.3 psi. - ¨C285C: - Cabin Differential 10.28 Amber CAS; Cabin Differential 10.48 Red CAS; Negative differential pressure relief at $-0.25$ psi. - ¨C286C: - Taxi speed $\ge$ 8 knots; power levers advanced 15 degrees (15º) forward. - ¨C287C: - 8000’ - Landing Field Elevation (LFE) - ¨C288C: - Aircraft turns left 90º, descends to 15,000’, flies at 340 KCAS (MAN), transitions to 250 KCAS (MAN) at 15,000’. - ¨C289C: - AIRCRAFT ALTITUDE > 40,000’; AUTOPILOT ENGAGED. - Guidance Panel speed on EDM mode: - 340 KCAS (MAN); 250 KCAS (MAN) past 15,000’. - Guidance Panel heading change during EDM mode: - NO. - AUTO ANTI-ICE protection termination sequence: - After 1 minute – ICE DETECTED L/R CAS message removed; after 3 minutes – COWL ANTI-ICE valves close; after 5 minutes – WING ANTI-ICE valves close. - APU operating when ICE DET test button pushed actions: - Ensure WING ANTI-ICE switches selected OFF; open WING Anti-Ice valve will increase APU bleed air output. - ICE DET button push outcomes: - CAS messages ICE DETECT FAIL, L/R; ICE DETECTED, L/R appear. - Anti-ice selected ON for take-off requirement: - Must be selected in MCDU on TAKEOFF INIT page 4/5 to box V Speeds. - CABIN WDO HT switch ON during pre-flight condition check: - OFF (BLUE) legend should illuminate; if not, switch to OFF, check CABIN WDW HTRS GROUND BYPASS at Observer Seat panel to OFF. - WSHL BLWR operational conditions: - Ground only (WOW).