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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.
Instrument
Tachometer
Cylinder Head Temp. (CHT)
(spark plug thermocouple)
Oil Temperature
Oil Pressure
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
•
O-200-D & X Series Engine Installation and Operation Manual
3 January 2017
Table 2-1. Recommended Instrument Range Markings
Accuracy/
Transient
Response
Range
Time
±25 RPM/
(0-3500 RPM)
<5 seconds
± 10°F
(200-500°F)
10 seconds
± 5°F
(50-265°F)
< 10 seconds
± 2 psig
(0-100 psig)
< 10 seconds
Red Line
Green Arc Yellow Arc
Minimum
Normal
----
0-2750
----
240-420°F 420-480°F
----
75-220°F
10 psig
30-60 psig
(idle)
Engine Description
Red Line
Caution
Maximum
----
>2750
>480°F
<75°F
>240°F
221-240°F
10-29 psig
100 psig
61-100 psig
(cold)
2-5
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