DA40 a/c systems
Terms in this set (29)
operated by steel pushrods
on elevator; operated by Bowden cable
manually operated thru control rods; absense of rollpin can lead to the loss of the hinge pin and resultant loss of control; 4 hinges each
controlled by cables attached to the rudder pedals
electronically operated; plain; 6 hinges each
main ldg gear of spring steel struts and a free-castering nose wheel which is strung by an elastomer package; directional control (steering) on the ground is accomplished via differential breaking and use of rudder; stopping and slowing is accomplished by hyrdaulically-actuated, single-disk, main ldg gear wheel breaks; breaks individually operated by toe pedals
mast under left wing providing ram air pressure to the ASI; static ports on the same probe provide static press. to the altimeter, vsi and asi; static press. is measured at 2 orifices at lower and rear edges of the probe' pitot hear and alternate static if ice blockage
da40 doesn't have this; instead a standby electric attitude indicator is powered by either the ess. bus or the emer battery
cabin heat and ventilation
Cabin heat and canopy defrost is provided by air ducted through the exhaust shroud and into
the cabin and is controlled by a lever on the center console below the instrument panel; four air vents
LHANDI, 360 cubic inch, IO-360-M1-A ____, 4 cylinder; 180 HP at 2700 RPM at sea level; ignition provided by 2 mags which provide spark to 8 spark plugs (2 per cylinder); ____-driven fuel pump and back-up electric fuel pump; ____ has an 8 quart oil sump; alternate ____ air source if loss of manifold press. because of icing or blocking
engine drives a Hartzell, 74-inch, all metal, hydraulically actuated, constant speed, non-feathering ___; ___ pitch and RPM is controlled by center lever with blue handle; engine oil from the governor increases the pitch of the blade resulting in lower RPM; centrifugal and aerodynamic pitching moments decrease the blade pitch; if catastrophic loss of engine oil, the ___ will go to low pitch, high RPM setting;
Lever forward = high RPM/low pitch. Lever rear = low RPM/high pitch
Avoiding Engine Over-Heating
The engine cowl openings for engine cooling are relatively small in the DA-40; Keep the MFD engine gauges page open during critical times; Whenever possible (preferably always) point the aircraft nose into the wind during run-up and while attempting to reduce engine temp............... pg 6
The right lever with a RED handle is used to control the fuel-to-air ratio or mixture. Lever forward = higher fuel-to-air ratio. Lever rear (engine cut off) = zero fuel going to the engine.
the fuel system consists of two tanks in the wings with a total fuel capacity of 41.1 gallons (40.1 gallons usable); three fuel sumps - one under each wing and one under the engine cowling; one fuel vent is located under each wing; fuel is drawn from wing tanks to the fuel selector valve, through an electric boost pump, to the engine driven mechanical fuel pump, and then to the fuel distributor where it is metered and passed to a manifold where it is distributed to each cylinder; the auxiliary fuel pump is used for engine priming during all engine starts, takeoff, landing, and when switching fuel selector valve
airplane is equipped with a 28-volt DC electrical system and a 24 volt, 35 amp hour battery that is located in the engine compartment; electrical energy is supplied by a 70-amp alternator located on the front of the engine; An external power receptacle is located on the right side of engine cowl; electrical power is distributed through electrical buses and over-amperage protection is provided by push-pull type circuit breakers
GPS / NAV 1
Back-Up Attitude Indicator
Flood (under glare shield) light
Engine instruments Transponder
the essential bus powers
Flood light (under the glare shield) Back-Up Attitude Indicator
the emergency battery powers
if an electrical problem arises, always check these; Circuits that are essential for flight may be reset only once in flight if: 1) there is no smoke or burning smell 2) the affected system/equipment is needed for the operational environment. Do not reset any non-essential circuit breakers in flight.
Charging System (alternator) Failure
DA-40's battery good for 30 minutes with ESS BUS powered Less time with lights/pitot heat on
essential bus, emergency switch
The DA-40 is an all-electric airplane; it has no vacuum system to operate the back-up attitude indicator. Gyro instrument redundancy is handled in two ways:
essential bus (ESS BUS)
One navcom radio, some lights, back-up electric attitude indicator, engine instruments, annunciator panel, pitot heat, flaps.
emergency switch (Horizon)
Secondary to the Essential Bus, final back-up for the crucial instruments and lights, power provided by a sealed battery pack (non-rechargeable), activated by the guarded "Emergency" switch. The Emergency switch powers only the back-up attitude indicator and under glare shield "flood" lights (for at least 1 hour)
Main Unserviceable Systems (with Ess Bus On)
Avionic / CDU fan
Position light, strobe lights, taxi light
Instrument lights, map light
Avionics Bus (COM2, NAV/GPS2, intercom audio, auto pilot)
No. Noteably, if the Battery Master is OFF and ESS BUS switch ON, the engine starter will not work
What happens if Essential Bus switch is switched ON during normal operation? Will the battery be discharged?
emergency battery switch (non-rechargable battery)
Power supplied for 1.5 hours
Only powers "flood" lights (under glair shield) and back-up attitude indicator
A pneumatic type stall warning system consists of an inlet on the leading edge of the left wing, which is ducted to a horn behind the instrument panel. As the aircraft approaches stalling speed, the lower pressure on top of the wing shifts forward drawing air through a horn resulting in an audible warning. The audible warning will become louder as stalling speed approaches 1.1 times stalling speed.
consists of navigation lights and a white strobe light on each wing tip. A landing light (inboard) and taxi light (outboard) is located on the left wing leading edge.
DA-40 is equipped with a "standard" baggage compartment (not "extended" and no baggage tube) with a limitation of 66 lbs
Canopy, Rear Door, and Emergency Exit
The front canopy has three positions, full open, cooling gap (Position 1), and closed (Position 2). The canopy and rear door are locked closed by means of a red handle and steel bolts that lock into mating holes. The rear door serves as an emergency exit and must not be locked with a key when the aircraft is occupied.
In case of roll-over on the ground, the rear door may be used as an egress point. Pulling the red handle located above and behind the center of the front seats will release the rear door front hinge. Always be sure to visually AND physically verify the rear door and canopy are closed prior to flight.
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