Mis. Flashcards
FUEL SYSTEM consists of
consists of two interchangeable crashworthy tanks, self sealing fuel lines, firewall mounted selector valves, prime boots pump and fuel tanks, engine drive pumps, quantity gauging and low level warning system
Fuel travel path
Pumps Fuel Filter HMU Liquid to Liquid cooler ODV Nozzels
How much fuel is unusable
360 lbs gravity
359 pressure
356 closed circuit
fueling psi limits
gravity - none
pressure 300 gpm, 55 psi
closed circuit 110 gpm, 15 psi
when does fuel low come on
172 lbs of fuel
What does the LDI do
negative pressure
pump or lines
fuel boost can isolate leak or make it worse
MMU - collective to pitch
compensates for rotor downwash
collective increases provides fwd input
aft input if collective decreases
MMU - collective to roll
compensates for translating tendency
left lateral input when collective increases
right lateral input when collective decreases
MMU - collective to yaw
compensates for changes in torque effect
increases tail pitch as collective increases
decreases tail pitch as collective decreases
MMU - Yaw to Pitch
compensates for vertical thrust
aft input as tail rotor pitch increases
fwd input as tail rotor decreases
Collective / airspeed to yaw (electronic coupling)
Compensates for torque effect function of SAS/FPS computer
decreases tail pitch as airspeed increases - and opposite
tail rotor pitch change is proportional to airspeed
0-40 maximum mixing
40-100 mixing decreases
100+ no mixing
TORQUE COMPENSATION
MMU
Electronic Coupling
Cambered Fin
changes to nominal pitch setting in tail rotor from 7.5 to 10
wind, PA, temp not considered
CAMBERED FIN
helps streamline fuselage as airspeed increases
tapers off as airspeed increases
AFCS
SAS 1 & 2, TRIM, FPS, Stabilator
provides oscillation dampening (dynamic)
maintains desired attitude, speed, and handling (static)
SAS
enhances dynamic stability by providing short term rate damping in the pitch
SAS 1 - analog
SAS 2 - digital
Both have 5% control if one fails remaining sas will double its gain and the control authority of SAS is reduced by one half
TRIM
maintain position of cyclic and tail rotor.
requires boost to be on
FPS - Flight Path Stabilization
FPS enhances static stability - long term rate damping
will not function without TRIM
Basic Auto Pilot Functions
<60 kts
Attitude hold - pitch, roll / hdg hold - yaw
> 60 kts
airspeed & attitude hold - pitch
attitude hold - roll
heading hold / turn coordination - yaw
Stabilator manual slew
is possible with battery only
Pneumatic system
bleed air furnished by the main engines, the APU, or an external pneumatic power source
drives the starter, heating system operation, external extended range tank fuel transfer
anti ice on - lose 18% torque
heater on lose 4%
Powertrain system - input module
freewheeling unit allows engine disengagement during autorotation, accessory module will continue to be driven by main rotor
Powertrain system - accessory module
electrical generator, and hydraulic pump
rotor speed sensor mounted on the right accessory module
Powertrain system - main module
provides reduction in speed for the input module
Intermediate gear box
mounted on tail pylon, can run 30 minutes at cruise with loss of all oil
tail gear box
may run at cruise flight for 30 minutes with loss of all oil
Main Rotor system
fully articulated, main rotor blades, hub, flight controls, and bifilar vibration absorbers
elastomeric bearing permits flap, lead, and lag
damper supplied with pressurized hydraulic fluid
BIM - nitrogen filled blades, red bad
tail rotor system
canted 20 degrees upward, provides 2.5 % of lift at hover
What if APU generator is sole source of ac power
backup pump and windshield anti ice cannot be used simultaneously
emergency power is provided by the
APU generator
can also supply blade deice if one main generator fails
if second fails blade deice load will drop
Primary source of power is DC or AC
Alternating Current
When only battery power is available the battery life is
38 minutes day, 24 minutes night for 80% battery
