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The aircraft is equipped with a fluid ice protection system for wings, stabilizers, propeller and windshield. This
system is supplied with deicing fluid from a tank located below the floor of the baggage compartment. The deicing system consists of :
- the tank,
- the pumps,
- the metering assemblies,
- the spraying bars for windshield,
- the L.H. wing leading edge lighting spot,
- the porous panels,
- the control panel - refer to 30-00-00,
- the propeller deicing - refer to 30-60-00.
2. LOCATION
COMPONENT QTY AREA ACCESS DOOR REFERENCE
Tank 1 220 244L 30-10-00
Pump 2 220 / 30-10-00
Metering assembly 2 220 / 30-10-00
Spraying bar for windshield 2 200 / 30-10-00
L.H. wing leading edge lighting spot 1 100 131 33-40-00
Porous panels 9 or 10 300, 500,
600 / 30-10-00
3. DESCRIPTION A. Tank
The tank is serviced through a filler located on the L.H. side of the fuselage, to the rear of the baggage compartment door. The filler orifice is attached to the inside of a door and moves outwards with the door as it is opened. Special containers are not required to accomplish filling.
Tank capacity is 7.8 US Gal (29.6 litres). The unusable volume is 0.1 US Gal (0.4 litre) with the aircraft in the level attitude, increasing to 1.45 US Gal (5.5 litres) in the climb attitude (measured at 10.5° nose up). Therefore the usable quantities are 7.7 and 6.35 US Gal (29.2 and 24.1 litres) respectively.
Fluid quantity is measured by a float operated sensor wich transmits an electrical signal to the indicator located on the ice protection control panel.
Ity : With ice protection - TKS system Validity Validity 10-00Page 1
(BA) JUN 04
If the system must be used, a minimum of 2.5 US Gal (9.4 litres) should be present in the tank before take-off. This is represented by an indicator reading of 1.7 US Gal (6.4 litres).
A drain provided beneath the right fuselage slightly aft of the wing leading edge is used for priming of the feed pipeline in addition to tank drainage.
The contents indicator reads the approximate fluid quantity in the tank in U.S. Gallons. This display has automatic dimming for night operations.
B. Pump
The fluid supply to the porous panels and propeller is provided by a two-speed electric pump. Propeller, wings and stabilizers protection system cannot be operated independently.
The windshield supply is provided by a separate intermittently rated pump (maximum 5 seconds of operation, each interval of 5 seconds min).
4. OPERATION
Deicing fluid from the pump passes through a filter, then through a spring loaded check valve which prevents flow when the pump does not operate.
A system of plastic tubing carries the fluid to proportioning units, one located under cabin floor, the other one located in rear fuselage. The proportioning units divide the flow into the requirements of the individual regions fed from each proportioning unit outlet.
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本文链接地址：TB20 MAINTENANCE MANUAL 30 防冰和排雨 TB20飞机维护手册(5)
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