AT 354 study guide
AT 354 study guide AT 354
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This 10 page Study Guide was uploaded by Rachel Borsa on Wednesday February 11, 2015. The Study Guide belongs to AT 354 at Purdue University taught by Lisa Lewis in Fall. Since its upload, it has received 168 views. For similar materials see Phenom 100 Ground School in Aerospace Engineering at Purdue University.
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I had to miss class because of a doctors appointment and these notes were a LIFESAVER
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Date Created: 02/11/15
Phenom 100 KNOW limitations and memory items Aircraft General 14 40 41 Min turn radius 55 Wing tip radius 83 8 latching pins on the door 2 microswitches emergency exit third window back on right side 0 opened from inside and outside 2 pilot seats 4 passengers 1 potty seat 1 lap child Flight Controls Primary controls aileron elevator rudder Secondary trim tabs aps All primary ight controls are operated mechanically no hydraulic boost Braking without differential 183 and differential 35 Trim is electrically actuated by the TAS Aileron has one control on center console no backup TAC 1 left wnng Rudder has one control on center console no backup TAC 2 Elevator has autopilot manual backup 0 Masterslave con guration LH commands RH Quick disconnect button turns off all trim yaw damper stick pusher and autopilot lf trim held for more than 3 seconds TRIM aural warning 0 held for more than 7 seconds locked out until startup Flaps are electromechanically operated not mechanically linked Flaps 0 10 26 26 36 0 Both signals have to agree for the aps to move 12 static wicks none can be missing Automatic Flight AP button disengages AP and YD CPL button alternates ight data source YD disengages YD Disengage AP by 0 Pushing the quick disconnect button 0 Pushing the CWS on yoke o Pushing pitch trim switches o Pushing TOGO button on throttles Disengage YD by o Pushing QD button 0 Pushing TOGA button on throttles No airspeed protection in VS mode Use FLC button for ight level change gives speed selection Colors 0 White armed o Flashing green capturing o Steady green active YD ashes yellow when manually disconnected AP ashes red with single AUTOPILOT warning when manually disconnected AP ashes red with repeated AUTOPILOT warning when unintentionally disconnected miss hit quick disconnect button to stop Powerplants and FADEC Pratt and Whitney turbofan engines Two spool high and low compressor high and low turbine 1685 lbs of thrust 1820 with ATR Start knob starts the FADEC to beginning sequence 0 Starter generator rotates engine fuel induced start generator switches to generator at 44 N2 igniters de energize at 54 N2 Thrust levers are electrically actuated Oil system provides lubrication for engine main shaft and accessory gear box 0 2 scavenging units 1 lubricating 0 runs through a lter with poppet valve check on pre ight 0 air to air oil cooler is primary way to cool oil 0 fuel oil heat exchanger is also used 0 oil capacity 411 qt for 10 hours 315 qt for 5 hours Engine fuel system is run by the Fuel management unit 0 Also contains a poppet valve checked on pre ight for lter will get CAS message if popped 0 Use motive ow ejector pumps Engine fuel system emergency shut off if N1 fan and turbine come apart a cable is able to pull a plunger which shuts off the fuel to that engine lgniters are FADEC controlled 0 A is powered by emergency bus B is powerd by Main DC bus Two for air start Two for auto relight One for ignition on ground unless it is less than 0 celsius OOOO Fuel Full Authority Digital Engine Control 0 Provides thrust management and engine limit protection 0 Lose FADEC lose control of engines 0 2 channel FADEC talks and must agree before inputs are added 0 powered by 28VDC but have a permanent magnet alternator which is a self contained power source for the engines 0 provides engine limit protection hot start hung start auto relight cool down protection 0 ATR closes bleed air valve to provide extra thrust to engines Colors 0 White enable 0 Green armed Blue active Engine start lt 0 celsius run engine 3 min at idle after oil temp reaches 14 degrees ldle engines 2 min before shutdown 2 integral tanks 0 Main 0 Collector tanks collect fuel fuel pumps located here 0 Surge tank for over ll and expansion Collector tank should be sumped before rst ight of the day Over wing fueling only 0 Can open the fuel transfer valve if not possible to over wing fuel allow to ll up 60 of the tanks 0 Fuel transfer valve must be closed for takeoffs maneuvers landing turbulence 0 Max fuel imbalance 220 lbs 2 DC electric pumps in collector tank 0 powered by emergency bus 0 used for engine start and low fuel pressure situations 4 ejector pumps 0 2 scavenge o 2 engine feed primary source 0 use motive ow no moving parts Engine re shutoff valves 0 1 per engine 0 pushed in fuel ow to engine is ceased Fire Protection 0 re detection loop powered by emergency bus detects an overheat or a re 0 re test button red lights on re shutoff switches redlight is illuminated until re is extinguished aural re N12 FIRE CAS FIRE indication on l39lT gauge 0 If engine Fire shutoff button is pushed in 0 White light illuminates white 0 Engine re shutoff valve closes o Bleed air valve closes o Extinguishing bottle is armed One halon extinguisher Electrical 0 28 VDC 0 Colors 0 Yellow unintentionally de energized 0 Red loss of parameters 0 White intentionally de energized 0 Green normalenergized 2 starter generators 0 at 44 N2 switch to generators o 1 56 can power whole aircraft 0 GCU provides automatic control for each 56 o 2 24 VDC lead acid batteries 0 connected to Hot Battery Bus battery 2 used to start engines battery charged by GPU or generator battery switch must be on for Battery to charge batteries are an emergency source of electrical power providing 45 min of power 0 DC external power is an option 0 Push in GPU button green in use 0 White available 0 GPU laches to the rst 28 VDC power source selected by crew o 110 VAC inverter 0 powered by shed bus 0 contains sensor pins to allow outlet to be charged 0 Emergency bus 0 Fire detection 0 Engine 1 and 2 fuel shut off 0 PFDAHRSCom 1 o Dome light 0000 o Mag light Hot Battery Bus 0 Engine 1 and 2 re extinguishing 0 Engine 1 and 2 re shut off valves 0 Baggage lights Central bus 0 Hydraulic motor Shed bus 0 Inverter 0 Convenience items ush AC 0 Drops off automatically if one power source or battery power Run by split con guration Electrical emergency button 0 Push in connects the batteries directly to the emergency bus Hydraulics Provides a hydraulic boost for landing gear and brakes Located on right side of nose Hydraulic pump does not operate continuously 0 Normal pressure is 3000 psi 0 Driven by DC motor Electric motor is powered by the central bus shuts down when over temp of 120 celsius and resets when temp lowers Reservoir acts as a storage tank 0 Must be checked each 15 consecutive days or before the next ight whichever is last Manifold and lter 0 Will not receive CAS if clogged poppet valve is visible Accumulator o Keeps constant pressure on the system 0 Uses nitrogen o Dump valve button manually bleed system pressure for pre ight check and re lling o 3250 high pressure relief valve ventilation fan runs automatically if 0 weight on wheels nose gear down and locked and both engines running Brakes Brakes only located on main gear Located in forward wing fairings Brake by wire no mechanical linkage Controlled through BCU lf leak or failure BCU closes the SOV to prevent further impact Emergencyparking brake 0 Provides 6 full brake applications Brake protections 0 Anti skid protection If one wheel is faster than the other reduces pressure to stop skid Engages through 30 knots drops out below 10 knots Locked wheel protection prevents a deep skid 30 difference Touchdown protection prevents brake application until after weight on wheelswheel spin up Spin down control stops wheels from spinning during retraction Nose gear has spin down brake pad in nosewheel Fusible plugs to prevent blowouts Brake wear pins if ush brake must be replaced Landing Gear Main gear retract sideways nose gear forward Always pin gear before towing LG are locked in the down position mechanically LG held up by hydraulic pressure LG will freefall if hydraulic system pressure is lost 2 WOW switches one on each main gear AirGround System 0 Disagreement of more than 3 seconds between left and right WOW sensors results in LG WOW SYS FAIL CAS message Down lock release button push and it mechanically unlocks handle if stuck Warning horn button push to stop LG horn when landing aps are not selected and altitude is less than 700 ft above LFE lf disagreement between any LG and LG handle for more than 20 seconds LG LEVER DISAG Aural LG when LG not down and o Flaps 0 or 1 position silenced with button 0 Flaps 2 cannot be silenced o Flaps 3 or full cannot be silenced Garmin Prodigy Set up General overview 0 NO GPU Before start ow Before start checklist Start both engines Atis clearanceboth admin owcockpit safety inspection included Pilot ying brie ng After start checklist Check MFD status page for 0 Fuel level 0 Oxygen 0 Door annunciations 0 Electrical page Altitude tape 0 On ground within 75 feet of eld elevation o In ight check every hourwithin 200 ft of each other MFD set up 0 Flight plan enter Engine data set OAT LFE set destination eld elevation Radar standby Weight enter OOOO Pressurization 0 Electronic control and monitoring unit is the brains of the system 0 Openscloses the out ow valve Out ow valve located on main pressure bulkhead o Electronically actuated by DC motor 0 Closes when advance to TOGA 0 Cabin pressurizes to 200 ft 150 below eld elevation Automatic mode opens valve in 6 seconds 0 Manual mode pilot controlled opens at 300 fpm Dump button 0 llluminates white light 0 Opens out ow valve 0 Stops recirc fans Dump button 0 Auto limits cabin altitude to 12000 ft 0 Manual limits cabin altitude to 14500 ft 0 Will pressurize to departure elevation if 0 Cruise altitude is less than 6000 ft 0 Aircraft descends 1000 ft from cruise altitude 0 Flight time is less than 10 minutes lf cabin altitude reaches 10000 ft crew is alerted with CABIN ALT Hi If lfe is gt 9600 ft CABIN ALT HI is reset to 14500 Oxygen Designed to provide oxygen from 41000 to 10000 ft or for smoke in cockpit Oxygen cylinder in nose cone no visual indication that the valve is open 0 Pressure read on MFD or analog gauge in FWD baggage Overboard relief port green disc will pop off if overpressured Control cable down oxygen up no oxygen Oxygen switch 0 Pax auto masks deploy automatically at 14700 ft 300 feet 0 Px ovrd manually deploy masks 0 Crew only pass masks do no deploy and oxygen does not go to them 7 passenger masks 2 in lavatory oxygen quits descending through 10000 ft test the masks and must get a yellow star or oxygen is not on crew mask settings 0 normal delivers diluted oxygen with cabin air 100 at 35000 ft 0 100 delivers 100 oxygen on demand 0 emergency delivers 100 oxygen under pressure Mask mic must be manually switched on Lighting Dome light mag compass light and annunciator lights are powered by emergency bus Annunciator lights 0 Cabin dump switch Pusher cutout switch Parking brake light CVDR panel Fuel transfer switch 0 Electrical emergency switch Cabin lights come on automatically in the event of cabin de pressurization Signsoutlets switch 0 Pedbeltsoff seat belts on cabin outlets deenergized o Beltson seat belts on cabin outlets energized o Offon seat belts off outlets energized OOOO 0 Courtesy lights 0 Overhead main entrance air stair cockpit step lights baggage compartments 0 Turned off automatically after 5 min 0 Red beacon turned on automatically when engines are on run 0 Landing light taxi and landing setting same bulb different intensity 0 Inspection light left hand side checks for ice Air Conditioning 0 Environmental control system ECS provides hot and warm air Vapor Cycle System VCS provides the cold air no PACKS Temp modulating valves use an air to air heat exchanger to be warm air some air bypasses and stays hot 0 Auto use knobs manual use temp toggle off turns VCS and ground cooling fan 0 Left bleed air cockpit right bleed air passenger VCS removes heat from cabin air resulting in cold air 0 Operates automatically when in AUTO 0 Contains evaporator recirc fans a condenser a compressor refrigerant Uses ram airground cooling fan to cool the refrigerant o Air ow through evaporators is increase with recirc fans Ice and Rain Protection 0 Wing and Stab Deicing O O O O O O 0 System uses bleeed air from engines to in ate deice boots Vacuum suction is provided to de ate and keep them de ated 6 seconds stab 6 seconds outboard 6 seconds inboard 42 second dwell at least 1 PRSOV valve must be open ejector ow control valves control bleed airvacuum suction tofrom boots bleed air is drawn from the heat exchanger ONOFF will complete one cycle then off 0 Engine ant ice 0 O O Bleed air extracted from each engine through a EAl shutoff valve to heat engine cowl lip Cannot supply bleed air to opposite engine EAl shutoff valves are built to fail to the open position 0 Windshield heat 0 Only forward windshields are heated 0 Two heating mats per window 0 Left and Right are powered by respective main DC busses 0 Left windshield gets priority 0 Turns windshield heat on below 95 and off above 110 0 Rain protection 0 Coated in rain repeant 0 Air Data Heating System 0 AUTO a ADSAOA probes are heated IF at least one engine is running or aircraft is airborne 0 ON all on regardless of WOW status 0 Static ports are heated automatically anytime the aircraft is airborne o ICING CONDITIONS 0 In ight TAT lt 10 degrees and visible moisture is present 0 On ground Same as ight and anytime SATTAT lt10 degrees and snow ice slush standing water on ground Pneumatic system IN NOTES
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