Systems Flashcards
Construction
Semi monocoque shell structure made from carbon fibre reinforced plastic (CRFP) with glass fibre reinforced plastic bulkeads
Firewall comprising of fire resistant matting separating the engine nacelles from the rest of the structure
Dimensions
Span = 13.42m Length = 8.52m Height = 2.49m
Total fuel quantity
52 US Gal
Max usable fuel
50 US Gal
Max fuel imbalance
5 US Gal
Max Masses]
Min flight mass Max ramp MTOM MZFM MLM
Min flight mass = 1250kg Max ramp = 1793kg MTOM = 1785kg MZFM = 1650kg MLM = 1700kg
Seat construction
Kevlar and GRFP
Fire extinguisher, first aid kit and ELT location
Fire extinguisher, behind the copilots seat
First aid, in the rear baggage compartment
ELT, rear fuselage below the baggage compartment. The aerial is fitted to the top of the fuselage
How long does the ELT transmit for after a crash
It transmits on VHF, UHF and satellite emergency frequencies for 72 hours
Cabin heating system
Air is drawn in from each engine nacelle, passes through the engines heat exchanger allowing the hot coolant that passes through the heat exchanger to heat the air
Different uses for the right/left heat exchangers
Right = canopy demisting Left = cabin heating
Cabin ventilation
Ambient air flows through a NACA duct on the right wing, providing cabin ventilation. This can be controlled by a number of ventilation ducts in the cockpit.
The trim switch is guarded from trim runaway by
A dual pole design, both switches need to be moved to move the trim.
If only one part is moved and held for 3 seconds then the system detects a fault and disconnects
Elevator stick limiter operation and number of degrees
Limits aft stick movement when the power setting on both engines exceed 20% and flaps are set to landing
The elevator goes from 15.5* to 13* max deflection
Flap degrees and Vfe for each stage
Cruise (up) = 0* Green
Approach (APP) = 20* White 137kts
Landing (LDG) 42* White 111kts
White speed tape speed range
56 to 111kts
care must be taken when selecting APP flap as 137 is in the green range
Type of stall warning fitted
Electrical flapper, lift detector vane in the flight manual
Type of engines
Two, four cylinder, liquid cooled, turbo charged Thielert TAE 125 four stroke diesel engines.
Both propellers are controled by a reduction gearbox
The FADEC controls
Engine fuel system, propeller and the turbo charger system
Engine lubrication system and capacity
Wet sump system with an external filter and oil cooler. An engine driven pump provides provides the oil flow
Oil capacity = 6L
Max consumption is about 0.1L
Approved oils
Shell helix ultra 5W40 synthetic and Aero Shell 10w40 Diesel Oil are approved for engine use.
Gearbox = Shell EP 75W90 API GL-4
Oil temp and pressure warnings illuminate when
Pressure = 1.2 bar
Temperature = greater than 140C
Gearbox temp = greater than 120C
Engine cooling system
Liquid cooled. The liquid coolant is pumped around the engine by a belt driven integral pump
The aircraft uses a CSU to control propeller pitch, what moves to coarsen or fine the blade angle
Oil pressure is used to move towards fine ptich
A spring moves it to coarse pitch
Centrifugal twisting moments cause
Act towards fine pitch
while centrifugal twisting mometns of counterweights act in the opposite direction
How is propeller unfeathered
It uses oil stored under pressure in an accumulator charged with nitrogen gas
Min RPM for the propeller to feather
Propeller speed needs to exceed 1300RPM
Centrifugal force acting on the propeller blade counterweights and spring move the blades to the feathered position
If both alternators fail the ECUs will be supplied with battery power for how long
30mins
If an ECU FAIL caption is seen on the PFD, you can try and reset the ECU by
Pressing and holding the ECU test button for 2 secs
ENG Fire warning illuminates when
Compartment temp is above 250*C
