ZLIN AIRCRAFT a.s.
Chapter 7
Z 242 L Flight Manual
Description of the aircraft and its systems
REVISION No. 3
25.2.2017
EASA Approved
7 - 19
7.25.2
Engine oil system
The oil tank is contained engine crankcase (1). The oil quantity in the engine crankcase is
checked of an oil gauge (16) - the maximum filling is 7,6 litres (8 quart).
Oil is transported by the pump (15) to the lubricated parts of the engine via full-flow oil filter (4).
When the oil temperature indicates cca. 85
o
C, the thermostatic valve (13) closes the direct oil
flow through the filter, whereupon oil starts to flow through the oil cooler (5) and is returned back
into the engine through the filter. The oil pressure is controlled by pressure reduction valve (2).
The crankcase is vented into the atmosphere via an oil separator (7), the separator oil is
returned into the engine through the hose. The diagram of the oil system is illustrated in Fig. 7-
10.
On the figure are also shows the system of measuring the oil pressure by means of oil pressure
transducer (9), signalling the oil minimum pressure by means of the minimum pressure switch
(17) and oil temperature by means of the oil temperature transducer (3).
The oil is drained by the drain valve.
Normal flight
Inverted flight
1 - engine crankcase
11 - venting piping
2 - reduction valve of oil pressure
12 - oil sump
3 - oil temperature transducer
13 - thermostatic valve
4 - full-flow oil filter
14 - filter strainer
5 - oil cooler
15 - oil pump
6 - single-direction flap valve
16 - filling neck cap with oil quantity gauge
7 - oil separator
17 - pressure switch
8 - oil pressure indicator (4-pointer engine indicator)
9 - oil pressure transducer
18 - annunciator lights panel
10 - gravitional valve
Fig. 7-11 Diagram of oil system