CE_560 Study Guide Notes

Fire detect malfunction indicator FIRE DET SYS L/R – indicates failure of the respective engine fire warning system. NOTE respective fire warning light will not illuminate in the event of an engine fire LH/RH ENGINE FIRE –pressing switch Arms both fire bottles Closes fuel shutoff valve Closes hydraulic shutoff valve Opens generator field relay Disables thrust reverser through isolation valve Electrical Battery in EMERG position provides 30 minutes power for Emergency Bus Items L/R N1 indication L/R ignition Standby flight display Standby HSI Standby radio control head Standby pitot static heaters Landing gear control and indication Flap control Comm 1 Nav 1 DG 1 RMU 1 Overhead flood lights Pilot’s and copilot’s audio panels Interior entry lights Generator LIMITATIONS On ground 125 amps ground idle NORMAL 225 amps ground idle HIGH Page 4 CE_560_Study_Guide.txt transients of 300 amps permitted up to 4 min In Flight 225 amps at flight idle 300 amps above flight idle 450 amps over load 4 min START LIMITATIONS • Starter/generator – 3 starts in 30 minutes with 90 sec rest • Battery – 3 battery starts per hour • 2nd engine start – before start set ground idle to HIGH and the load on the operating generator should be below 200 amps J-BOX ANNUNCIATORS • AFT J BOX LMT – failure of 225 amp current limiter • AFT J BOX CB – left or right start CB on aft J Box popped BATT Disconnect switch DISC – Disconnects the battery from the electrical system NOTE • Only use as directed by the checklist • Continued use will the drain battery INTERIOR MASTER switch • Interior master switch located on captains left arm rest panel • Shuts off power to the cabin accessory items, refreshment center, and AC outlets Inverters • Avionics switch – select ON, to power both inverters, the AC buses are normally split. • Inverter switch – is normally left the NORM position which powers both inverters simultaneously, each inverter powers two buses (splits bus). • Selecting INV1 or INV2 will allow that inverter to power all four AC buses. FUEL Max fuel capacity 5,440 lbs(806 gal) • Max normal fuel imbalance 200 lbs • Max emergency imbalance 600 lbs • Avgas NO SINGLE POINT REFUELING LIMITATIONS • refueling Minimum 10psi Maximum 50 psi • defueling max -10 psi SINGLE POINT REFUELING pre Check • Pull out precheck lever. • Full flow must slow to 0-6 gpm within 30 sec. • This check ensures that the shutoff valves will close when the tanks are full • Tanks may be individually filled by pulling opposite individual precheck lever BOOST PUMPS ON – continuous operation Page 5 CE_560_Study_Guide.txt OFF – cannot activate NORM – activates for engine start, LO FUEL PRESS, crosssfeed • If the engine is shutdown in flight and windmills for more than 15 minutes without the boost pumps ON, the engine driven fuel pump must be inspected FUEL/OIL HEAT EXCHANGER • Each engine has a fuel oil heat exchanger between LP engine driven fuel pump and HP fuel pump which utilizes warm oil to heat the fuel before entering the fuel filter • The FOHE eliminates the need for premixed, anti-ice inhibitors in the fuel Four ejector pumps in each wing Primary ejector feeds engine driven pump and transfer ejectors 3 transfer ejector pumps move fuel to the sump Motive flow valve closes on side receiving fuel during cross feed LANDING GEAR AND BRAKES Brakes and Anti-skid system • Landing gear is trailing link • Anti-skid does not have to be off for taxi • When selected from OFF to ON aircraft must be stopped and anti-skid test completed for system to be active. Trailing Link Emergency gear extension FLIGHT CONTROLS Flaps • Flaps are hydraulically powered • 7o position added • When selecting flaps to 15o-25o the pitch trim resets to counter pitch changes ICE AND RAIN PROTECTION Wing bleed air heat system When WING/ENGINE ant-ice is selected ON • Stator valve opens, bleed air heats the engine stator vanes • PRSOV opens to heat the engine nacelle inlet lip • Ignition activates • Flight idle increases to 65% • Bleed air is routed to picolo tubes in the wing leading edge • WING ANT-ICE L/R illuminates till wing temp reaches 300o F • ENG ANT-ICE L/R illuminates till the engine inlet temperature exceeds 70o F • Wing ram air inlets at each wing root, allow air to flow through a secondary chamber separating the heated leading edge and the forward wall of the fuel cell. Purge air exhaust through louvers at the bottom of the wing tip ICE AND RAIN PROTECTION Wing bleed air heat system • All anti-ice systems are activated in visible moisture and RAT below +10o C • Before entering icing conditions select WING/ENGINE ON • WING XFLOW switch – for single engine operation or other abnormal conditions ICE AND RAIN PROTECTION Tail de-ice system • Normally operated in AUTO position Page 6 CE_560_Study_Guide.txt • Uses 23 psi air to inflate left and right horizontal stabilizer boots. • 6 sec left boot inflates, 6 sec suction, 6 sec right boot inflates, 3 minute rest • After selecting AUTO, allow boots to cycle for 18 sec before selecting OFF • When utilizing MANUAL mode hold switch down 6 to 8 seconds, both boots inflate simultaneously, repeat every 3 to 5 minutes Tail de-ice system LIMITATION Do not activate the tail deice boots under the following conditions • Airspeeds at or above 150 KIAS and RAT less than or equal to -35o C • Airspeeds below 150 KIAS and RAT less than or equal to -40o C W/S heat control • Windshield ice protection lights – activate when the battery master is selected on • A red spot on the windshield illuminates at night when ice starts to form on the windshield A/I in-flight idle • Inflight selection of engine anti-ice on will reset flight idle to 65.0% N2 • flight idle will reset to 53.9% N2 If engine anti-ice is selected OFF or the landing gear is exteded PNEUMATICS AIR CONDITIONING Vapor cycle air • Compressor automatically shuts down above 18,000 ft • Discharges cold air from forward and aft vents in the dropped aisle • The acm ejector is replaced by a fan PRESSURIZATION Electronic pressurization controller • Normal operation – set landing field elevation • requires No. 2 ADC • Yellow light illuminated – isobaric mode – press FL to set flight level and field Elevation • Red light – system failure – select manual pressurization • EXER – ground test mode only High altitude and auto EMER PRESS modes • Setting an airport elevation greater than 8,000 in the SET ALT window will set the pressurization controller to the high altitude mode. This adjust the climb schedule. Cabin altitude will climb to 7,800 ft during cruise. • EMER PRESS mode selected– bleed air from the left engine directly into cabin. Shuts down both ACM’s • Automatic with ACM O’HEAT or cabin altitude above 14,500 ft PRESSURIZATION Max cabin differential 8.9 psid EMER DUMP toggle switch – opens both out flow valves, at 14,500 emergency pressurization valve opens, drives cabin to 12,000’ Page 7 CE_560_Study_Guide.txt OXYGEN Control • CREW ONLY – O2 is only supplied to the crew mask. passenger mask are blocked. • NORMAL (armed) – if DC power is available passenger mask will drop at cabin altitude 14,500 ft +/- 500 • MANUAL DROP – will manually drop passenger masks if DC power is lost • • Crew mask (EROS) • Settings – EMER – enables pressure breathing – 100% – 100% O2 – NORM – diluter demand breathing • After cold soaking (2 hours or more at -10 Co) cabin temperature must be at or above 0o C for 15 minutes prior to take off to ensure proper deployment of passenger mask OXYGEN • Must be stowed in container to qualify as quick donning AVIONICS • Primus 1000 integrated avionics system – 3 tube EFIS system consisting of pilots and copilots Primary flight displays (PFD) and a central multi function display (MFD) • PFD failure – (black tube) turn the PFD dim knob to OFF on the failed display, PFD information is displayed on the MFD • EFIS or IAC failure – RED X on PFD and/or MFD – turn the MFD mode knob to SG1 or SG2(all 3 displays will be driven by the selected signal generator) • HDG REV – changes heading source on PFD • ATT REV – changes Attitude source on the PFD • ADC REV – changes air data computer source on the PFD LIMITATION • P-1000 system must be verified operational by the preflight test in the normal procedures • Dual PFD SG reversion to the MFD is prohibited UNS1-C Universal FMS AUTOPILOT • BANK LIMIT – engaging limits bank to 14o. Automatically engages climbing through 34,000 ft, disengages at 33,750 ft. • DN/UP – illuminates with sustained request for trim • If the autopilot is engaged and VS selected on flight director panel, the pitch trim wheel can be used to change target vertical speed rate on the PFD Standby instruments Meggitt Standby Flight Display(SFD) • 24V battery in the nose provides 30 min of power to the secondary flight display. • Displays airspeed and altitude from it’s own stand alone source, attitude from solid state inertial sensors and VOR/ILS indication from Nav. 1 • Also powers lighting for ITT, N1 & standby HSI displays. • Must allow 180 sec. for start up. • Standby horizontal situation indicator – powered by the emergency bus Single mode controller • Pressing APR button cycles through Page 8 CE_560_Study_Guide.txt – LOC/GS – BC back course – Non ILS format • Standby gyro system must be preflight tested and operational before takeoff SAFEFLIGHT N1 REMINDER • Indicates approximate N1 for take off, climb, and cruise, with or without anti-ice ON • 888 indicates successful self test • — indicates failed test or no data • Preflight – Select ant-ice – AS REQUIRED – Place switch in the TO/GA position – Set air temperature by depressing switch and turning – Read takeoff power on display Selecting TO/GA below 10,000 will display go around N1 Noise at 16,630 lbs • Takeoff 70.0 • Sideline 89.8 • Approach 90.5 Forced mixer nozzles on the encore reduce noise 1st hour 1,500 lbs 2nd hour 1,100 lbs Climb 247 KIAS/.62 M Page 9