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- the airframe de-icing system bleed (option),
- the landing gear hydraulic system bleed and drain.
2. LOCATION
COMPONENT QTY AREA ACCESS DOOR REFERENCE
Fuel tank bleed and drain 2 500 / 600 / 12-11-02
Fuel filter bleed 1 210 / 100 / 12-00-02
Engine oil system drain 1 100 131 or 133 (option) 12-12-02
Braking system bleed 2 730 / 740 / 12-13-01
Static system bleed 1 210 / 12-00-02
Oxygen system bleed (option) 1 210 / 12-00-02
Airframe de-icing system bleed (option) 1 210 / 12-00-02
Landing gear hydraulic system bleed 2 100 / 210 121 / 131
218A 12-13-03
Landing gear hydraulic system drain 4 100 / 210 121 / 131
218A
738 / 748 12-13-04

3. DESCRIPTION (Figure 1)
A. Fuel tank bleed and drain
The bleeding point of the fuel tank (1 per wing) consists of a clapper valve which allows to eliminate contamination and especially condensation water caused by air humidity and temperature variations. It also allows to drain the fuel tank entirely. It is located on the lower surface of the wing, at the lowest point of the tank, near inspection doors 513 [613] in the vicinity of the main landing gear.
 
B. Fuel filter bleed
The bleeding point of the fuel filter is a clapper valve which allows to eliminate contamination deposits having passed through the filter and especially condensation water from the fuel tanks.
S / N 1 - 730
The clapper valve is located beneath the fuel filter in the engine compartment against the firewall. It is accessible through an opening made into the lower cowling 131.
S / N 731 - 9999
The clapper valve is located beneath the fuselage, on the R.H. side of the fuel filter and is accessible through an opening made into the cowling under hull 218F.
S / N 731 - 9999 with OPTION A888
The clapper valve is located beneath the fuselage, on the L.H. side of the fuel filter and is accessible through an opening made into the cowling under hull 218F.
C. Engine oil system drain
The engine oil drain valve is located on the engine lower casing and is accessible through inspection door 133, or after removal of lower engine cowling 131.
D. Braking system bleed
The bleeding points of the braking system (1 per brake unit) allow to eliminate the air trapped into the system
during the replacement or the malfunctioning of a component. They are located on the brake units.
E. Static system bleed
The bleeding point of the static system allows to remove condensation water from the lines. It is plugged with a seal-fitted plug. This bleeding point is located beneath the fuselage in the area of the wing splicing, and is accessible through an opening made into the cowling under hull 218F.
　
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本文鏈接地址：TB20 MAINTENANCE MANUAL 12 SERVICING TB20飛機維護手冊 12 保養(12)