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System Description Flashcards

(84 cards)

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1
Q

Flight controls

A

Elevator
Aileron
Rudder
Differential spoilers
Flaps

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2
Q

Aileron trim

A

Trim able to servo on right aileron

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3
Q

Elevator trim

A

2 trim tabs on elevator T.E.

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4
Q

Rudder trim

A

Through nose wheel steering bungee

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5
Q

Red annunciators (9)

A

Engine Fire: High temp in engine compartment

Oil pressure low: <38 PSI

Generator off: Gen not connected to BUS (Generator contactor denergized)

Emergency pwr lever: Not stowed in normal position

Voltage low: Power coming from battery

Vacuum low: suction < 3.0 InHg

Reservoir fuel low: Fuel in reservoir tank less than half

Fuel select off: One or both fuel selectors are off
*Will also be on with both swtiches on IF fuel select warn or start cont CB are pulled

Door warning: Upper cargo door or Upper pax door is unlatched

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6
Q

Yellow annunciators (7)

A

Aux fuel pump on: pump is on

Fuel press low: < 4.75 PSI

Starter energized: Starter/Generator operating in starter mode

Left/Right fuel low: <25 gal remaining

Stby elect pwr on: Alternator is supplying power to bus

Chip detector: Metal chips detected in AGB or RGB

Stby elect pwr inop: Electrical power is not available from the alternator

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7
Q

Green annunciators (3)

A

Ignition on: electrical pwr being supplied to the engine ignition system

Windshield anti-ice: Electrical pwr being supplied to windshield anti-ice power relay

De-ice pressure: pressure in the de-ice system has reached ~15 PSI

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8
Q

Lamp test

A

All lights
Both fuel select horns

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9
Q

Turn radius

A

65’ - 4 7/8’’ required width for 180 deg turn (??)

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10
Q

Wing flaps

A

T.E. angle and L.E. Vortex Generators reduce stall speed and enhance lat stability
Wing flap motor protected by Flap motor CB

Overhead switch:
- NORM : Pedestal switch controls
- STBY: Stby motor and disables dynamic braking of primary motor. No limit swtiches on stby motor

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11
Q

Engine informations (10)

A

Compression ratio: 7:1

Nozzles: 14 simplex (10 primary)

Spark igniters: 2

Max HP: 675 (only available above 1800 RPM)

100% Ng: 37500 RPM

Max RPM: 101.6% = 38100 RPM

Prop ratio: 0.0576:1
1900 RPM = 33 000 N1

Oil tank capacity: 9.5 US quarts

Total oil system capacity: 14 US quarts

RGB type: 2 stage planetary

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12
Q

AGB accessories (8)

A

Oil pump: bottom of oil tank

External scavenge pumps: back of AGB

Internal scavenge pumps

FOHE (Fuel Oil Heat Exchanger): Top rear

Oil filter: Right side of oil tank

Starter gen: Top

Fuel pump: 2 O’Clock

Ng tachometer generator: 5 O’Clock

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13
Q

RGB Accessories (4)

A

Prop tachometer generator: right side

Torque meter: Inside first stage

Prop governor: 12 o’clock front case

Prop overspeed governor: 10 o’clock front case

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14
Q

Engine controls

A

Power lvr
Emergency pwr lvr
Prop control
Condition lvr

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15
Q

Power lever

A

Do not move pwr lvr into beta if prop is feathered
Pneumatic FCU failure - power goes to min idle = 48%

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16
Q

Prop lever

A

Max governs to 1900 RPM

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17
Q

Condition lever

A

Low idle: 52% Ng
High idle: 65% Ng

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18
Q

Torque gauge

A

Converts pressure difference btw engine torque pressure and RGB pressure

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19
Q

Prop RPM gauge

A

Electrically operated
Signal gas gen tach generator

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20
Q

Oil system

A

Oil tank at back of AGB
Pressure pump at bottom of tank
2 scav pumps mounted on back of AGB
2 internal scav pumps inside AGB
Oil filter on right side of tank
ACOC (Air Cooled Oil Cooler) on front right of engine
CSV (??)
Dipstick indicates US quarts low
Tank capacity 9.5 quarts
System capacity 14 quarts

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21
Q

Ignition

A

2 igniters
Exciter on right side of engine mount

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22
Q

Ignition switch

A

NORM: arms system to igniters work when starter on

ON: turns on continuous ignition.
Turn on for air start, water/slush on rwy, icing, fuel exhaustion

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23
Q

Starter switch

A

OFF: shuts off ignition system
Normal position

START: Energizes ignition system if ignition switch is NORM

MOTOR: Motors engine

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24
Q

Inertial separator

A

Bybass : OAT <4°C and visible moisture

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25
Fuel system
Fuel tank Fuel SOV (2/wing) *Gravity Reservoir Jet pump or aux pump Firewall fuel SOV Fuel filter *bypass FOHE HP pump FCU *(back to jet pump or aux pump) Flow divider Manifold Nozzles (10 primary, 4 secondary)
26
Fuel tank vents
Check valves and one line per tank to wing tip T.E. Fuel reservoir vented to both tanks
27
Fuel tank selectors
Two valves per tank Ensure high wing tank is off on ground
28
Fuel shutoff warning system
Powered through START CONT C.B. Warning horn when: - Both valves off and battery on - Starter in START or MOTOR and one fuel shut-off OFF - One fuel shut-off OFF and < 25 gal remaining (in red): FUEL SELECT OFF will be on with both switches ON if Fuel select warn OR start cont C.B.'s pulled
29
Aux boost pump
OFF NORM: pump comes on when manifold pressure < 4.75 PSI ON: operates continuously. Pump to be ON for start to ensure lubrification of FCU
30
Fuel flow indicator
Flow measured downstream of FCU before flow divider Needle stowed in OFF when pwr is removed Powered through fuel flow CB
31
Fuel qty indicators
8 senders - 4 per wing Calibrated for standard day Fuel low annun when < 25 gal
32
Fuel drain can
Drain min once per 6 shutdowns
33
Fuel pump drain
Collects oil from fuel pump drive coupling Check if fuel is leaking past fuel pump seal Drain min once per 6 shutdowns Max 3 CC of oil, 2 CC of fuel per hour
34
Power turbine governor
Limits fuel in overspeed conditions Controlled by governor in reverse
35
Starter generator
28V, 200 Amp Motors to 46% Ng Start cycle auto terminates at 46% Ng Cooled by integral fan and ram air duct in right intake Motoring: Gas gen is rotated with ignition deenergized Switch is spring loaded to off Interlocked with ignition switch. Ignition must be NORMAL to motor
36
ITT temp sensors
twin leads 2 bus bars 8 thermocouples in parallel
37
Prop governor
Located at 12 o'clock on RGB Maintains constant prop speed by adjusting blade pitch
38
Prop overspeed governor
Located at 10 o'clock on RGB Governs Ng by bleeding P3 to move fuel metering valve closed
39
Fire detect
Consists of heat sensor, warning light and warning horn Heat sensor: 3 closed loops detect heat and activate warning Section 1 > 425°C Section 2 > 625°C Section 3 > 450°C
40
Breather
Drain can located on right side tower engine mount truss Collects from AGB pads, alternator drive pulley, starter gen, A/C compressor and prop shaft seal 14 cc max per hour for aircraft with a/c 11 cc max per hour for aircraft without a/c
41
Propeller
Oil pressure opposes force of springs and counterweights Oil drives blades to low pitch (High RPM) Oil from engine is boosted by governor gear pump to hub through flange Prop FAILS FEATHERED
42
Brakes
Single disc hydraulic Master cylinder on each pilots rudder pedals
43
Parking brake
Hold brakes and pull T-handle to set Push in T-handle to release
44
Electrical system
28V DC 24V lead acid battery 300 amp starter generator 2 general busses 2 avionics busses 1 battery bus
45
Battery bus
Always on Feeds memory keep alive, clock, cabin lights
46
General bus (2) abd avionics bus (2)
General: Powered when battery switch ON through general distribution bus Avionics: Powered when battery switch ON and avionics switches ON. All DC power is on when general and avionics busses ON
47
Standby system (electrical)
Powered by engine driven alternator Separate busses
48
GCU (Generator Control Unit)
Provides electrical control functions necessary for the operation of the starter-generator In cabin on fwd fuse sidewall Controls: - Starter/generator - Auto starter cut > 46%Ng - Switches operation to generator when > 46%Ng and starter switch OFF - Generator auto disconnect - Generator contactor Provides voltage regulation, high voltage protection and reverse current protection Connectec generator to airplane bus
49
Ground power monitor
Inside electric power controller on left hand side of firewall in engine compartment Closes external power contactor when external power is within limits (24-28V, 800-1700 amp) Monitors airplane bus voltage and lights VOLTAGE LOW when bus voltage drops to battery voltage
50
Battery Switch
ON: Battery power supplied to 2 gen busses OFF: Power supplied to battery bus only
51
Generator switch
ON: GCU control generator line contactor RESET: Restores generator power TRIP: Shuts off generator system
52
Avionics bus switches
Ensure OFF when: - Turning battery on or off - Starting engine - Applying external power Can be used in place of individual avionics switches
53
Avionics bus tie
2 position guarded toggle switch Connects 2 avionics busses together Each avionics bus is supplied by its own current limiter Using bus tie may require load reduction due to increased load through current limiter
54
External power switch
OFF: Power to main bus and starter/generator circuit External power can not be applied to main bus Generator power to GCU STARTER: External power to starter circuit only Battery power to main bus No generator power available BUS: External power to main bus No power to starter circuit Battery connected to main bus and external power via battery switch Battery must be monitored to prevent overcharge
55
Circuit breakers
Reset only after 3 min cooling period
56
Volt ammeter
GEN: Generator current ALT: Stby alternator current BATT: charge or discharge of battery VOLT: system voltage
57
Ground service plus receptacle
Allows external power to be applied for start etc Control circuitry prevents external power and battery from being connected during start Has polarity reversal and over voltage protection No power will flow if plug is installed backwards or external voltage is too high
58
External lighning
3 nav lights (2 wing, 1 tail) 2 landing lights (wing L.E. outboard) 2 taxi lights (wing L.E. inboard) 2 strobe (wing tips) Beacon 2 courtesy lights (under wing)
59
Cabin heating
Compressor outlet air Flow control valve Mixer muffler (mixes with cabin return air or air from compressor bleed valve)
60
Ventilation
2 inlets on forward side of fuselage 2 ram air ducts at top of struts
61
Bleed air heat switch
ON: opens flow control valve allowing compressor bleed air into cabin heat system OFF: Shuts off hot bleed air to heating system
62
Temperature selector know
Modulates open and closing of flow control valve Clockwise = more mass flow = increased temp High idle or mix air heat control to GND for increased heat on ground Temp sensor located in mexer/muffle outlet duct detects high temp
63
Mix air control
GND: Compressor bleed valve air mixed with hot compressor outlet air Power must be <92% Ng FLT: Cabin return air mixed with compressor outlet air Can be used on the ground BOV (Blowoff valve?) air is dumped overboard at <92% Ng Must be set to FLT at high power to prevent over temp in mixer/muffler outlet duct
64
Aft/fwd push pull
AFT: Heat directed to floor vents in sidewall of pax cabin FWD: Heat to forward cabin to 4 outlets behind instrument panel and/or 2 windshield defrost outlets
65
Defrost/forward push pull
DEFROST: heat directed to 2 defrost outlets FWD: Heat to 4 outlets in forward cabin
66
Cabin heat firewall shut off
Closes 2 firewall shut off valves: 1. bleed air supply into cabin heat system 2. cabin return air line Must not be in OFF position with mix air heat control in GND - Compressor stall can occus at low power - Engine must be shut down to relieve back pressure on valves
67
Vent air control knobs
Located on overhead console Control shutoff valves in each wing CLOSE: wing shut off valves are closed OPEN: progressively opens valves. Full open turns on fans
68
Pitot static system
Static pressure alternate source below icing switch panel Static pressure is from inside the cabin Pressure will vary with vent position Drain valve on left sidewall beneath instrument panel
69
Airspeed pressure switch
Activates horn when airspeed > 175 KIAS
70
Airspeed indicator
Pressure altitude is determined with altimeter set to 29.92
71
Vacuum system
Left hand attitude indicator (right hand electric) Right hand directional indicator (left hand electric) Vacuum created from compressor bleed air routed through vacuum ejector on forward left side of firewall
71
Suction gauge
< 15 KFT : 4.5 - 5.5 15 - 20 KFT: 4.0 - 5.5 > 20 KFT: 3.5 - 5.5
71
Stall warning system
Heated vane in left wing L.E. Horn 5-10 kts above stall in all configurations Will activate on ground with battery ON unless stall warning disconnect switch ON AND Elevator or forward stop
72
Avionics cooling fan
Operates when battery switch and avionics 2 switches are ON
73
Static wicks
Integrity of wicks to be checked annually by qualified technician Wicks to be replaces biannually
74
Icing equipment
Boots: - L.E. of wings, inboard and outboard - Wing struts - Main gear legs - Cargo pod nose cap - Horizontal and vertical stabilizer L.E. Fed via pressure line from bleed air system pressure regulator to vacuum ejector 3 flow control valves and pressure switches, timer and system switch
75
Boot pressure switch
AUTO: - Will activate 1 deice cycle - Must be activate and release when cycle desired MANUAL: - Blows all boots at once
76
Boot inflation sequence
1. 6 sec - Horz + vert stab boots 2. 6 sec - IB wing, main gear and cargo pod nose cap 3. 6 sec - OB wing L.E. and strut boots Total time for sequence : 18 sec
77
De-ice pressure annunciator
Should come on 3 sec after starting cycle and stay on for 3 sec after cycle is complete Shoudl turn on for all pressurization sequences If annunciator does not come on, insufficient pressure (<~15 PSI)
78
Prop anti-ice
Monitor operation with prop anti-ice ammeter on left side of instrument panel AUTO: - Cycles power for prop heat 90 sec ON, 90 sec OFF - Resets sequence when turned off MANUAL: - Provides continuous power for prop heat - Must manually cycle
79
Standby power system **More info in the doc
Alternator, alternator control unit, stby alternator contactor assembly, 2 system control switches, 2 30 or 40 amp C.B., field excitation to alt control unit blablabla, alt on volt/ammeter STBY ELECT PWR ON: alt is supplying pwr to bus STBY ELECT PWR INOP: Electrical pwr is not available from alternator Operation: - When stby electrical system is on stby: power is automatically supplied to main busses if system voltage drops - AVIONICS STBY PWR and AVIONICS BUS TIE switches must be on to use full 75 amp capacity - AVIONICS PWR 1 and AVIONICS PWR 2 must be OFF to avoid feeding a possible fault to the primary pwr system when stby pwr is operatings - The primary pwr supply system can be completely isolated by pulling the 6-30 amp bus feeder C.B.s in the event of a fault in the primary pwr relay box
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SGL
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