Continental Motors O-200-D, Инструкция по установке и эксплуатации

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O-200-D & X Series Engine Installation and Operation Manual 2-5
3 January 2017
Engine Description
2-2.3.4. Manifold Air Pressure
A 0.125-27 NPTF threaded boss is provided on the 2-4 side of the induction manifold to
measure manifold air pressure.
2-2.4. Engine Instrumentation
The aircraft manufacturer is responsible for all engine instrumentation such as RPM, oil
pressure and temperature, fuel pressure, etc.
2-2.5. Fuel System
The airframe manufacturer must ensure the design of the aircraft fuel system, which
supplies fuel to the carburetor, adequately suppresses fuel vapor formation for all aircraft
operating conditions. Examples of aircraft fuel system design practices to satisfy this
requirement include:
•
Installed fuel line size capable of flowing 150% above maximum fuel flow values
•
Minimize fuel line lengths to decrease residence time of the fuel
•
Minimize elevation changes
•
Minimize the number of bends and fittings.
•
Route fuel lines away from heat generating components
•
Install radiation shields and insulation on fuel lines
•
Direct airflow through the engine nacelle to minimize temperatures of fuel system
components
•
Provide auxiliary aircraft operated fuel pumps when necessary
•
Avoid low points where contaminants or water may collect
Table 2-1. Recommended Instrument Range Markings
Instrument Range
Accuracy/
Transient
Response
Time
Red Line Green Arc Yellow Arc Red Line
Minimum Normal Caution Maximum
Tachometer (0-3500 RPM)
±25 RPM/
<5 seconds
---- 0-2750 ---- >2750
Cylinder Head Temp. (CHT)
(spark plug thermocouple)
(200-500°F)
± 10°F
10 seconds
---- 240-420°F 420-480°F >480°F
Oil Temperature (50-265°F)
± 5°F
< 10 seconds
---- 75-220°F
<75°F
221-240°F
>240°F
Oil Pressure (0-100 psig)
± 2 psig
< 10 seconds
10 psig
(idle)
30-60 psig 10-29 psig
61-100 psig
100 psig
(cold)