Systems Flashcards
How is the Cabin Ventilated?
Ambient air flows into cabin directly from duct on right wing
Flight controls
Dual primary flying controls, operate the aileron and elevator via control rods
Rudder is operated by control cables
Elevator is fitted to the horizontal, stabilizer and is equipped with adjustable trim tab
Rudder trim is operated via control, cables and located on the lower part of the Rudder
Elevator trim systems
Elevator trim is operated by two components
1. Control stick mounted switch.
2. Servo motor connected to the elevator trim wheel.
Stick limiter
Full elevator upwards deflection is normally 15.5° but it is reduced to 13° in certain circumstances using an electronically actuated control stop.
System senses, the position of the power levers, and the flap selector switch whenever both engines exceeded 20% power the flaps are set to LDG. The stick limit is applied.
Stick limiter test
Test procedure
Pull control column, fully aft and hold
Set flap to LDG
Set both engines to max
Noticed the control column move forward slightly
Set power to idle and check to ensure full deflection
Flaps
Operated by control rods moved by an electric actuator
Three positions
1. Cruise (up) - 0°
2. Approach (app) - 20°
3. Landing (LDG) - 42°
Velocity flaps extended speed
1. VFE APP - 137 Kias
2. VFE LDG - 111 KIAS
Aileron and hinge checks
Ailerons are mounted using a series of hinges
Hinges are secured with roll pins
Nuts and bolts of control rods are covered with varnish
Fire detection system
And overheat detector is in each engine bay
Activated if compartment temp increases over 480°
Fire detection system
And overheat detector is in each engine bay
Activated if compartment temp increases over 480°
Describe the fuel tanks
Uses jet A1 fuel
Stored in aluminum tanks, located in each wing
Each tank has three interconnected chambers
Fuel filler point located on the upper surface of each wing and directly feed into the outer chamber.
Tanks are ventilated to the atmosphere by check and pressure relief valves located on the under side of the wing
Auxiliary fuel tanks are located on each engine nacelle
Main tank capacity is 25 gallons of useful fuel
Auxiliary tank capacity is 13 gallons of useful fuel
Fuel system indications
Two fuel sensors located in each tank and low level sensor located on the inter chamber
Low level switch activates when there is 3 to 4 gallons remaining
Max fuel temperature is 167°F or 75°C
Fuel system limitations
When one engine is an operative fuel selector valve to off
Do not operate with both fuel selectors in the CrossFeed position
Do not take off with either fuel selector in the CrossFeed position
Do not shut down the engine by moving the fuel selector to off - this will damage the high-pressure fuel pump
Describe the landing gear system
Retractable tricycle gear with conventional pneumatic struts and a stable nose wheel
The gear is retracted and extended hydraulically
Hydraulic pressure is provided by an electric pump
Gear extension normally takes 6 to 10 seconds
Gear extension and locking is assisted by springs
Hydraulic pressure on the actuators keep the landing gear retracted
The event of a pump failure gear can be extended by the use of gravity
Three green lights indicate the gear is down and locked
Red gear unite illuminates if any gear leg is neither down or locked or still up
Wheels have hydraulic disc brakes operated by pedals on the top of the Rutter pedals
Nose wheel steering
Using the rudder pedal as the nose can be turned up to 30° either side of the center
A larger deflection of up to 52° can be achieved using differential breaking
On retraction the nose, automatically centered, and the steering linkage disengaged to reduce Rutter pedal loads
