Piper Cherokee Arrow II Pilots Operating Manual page 21

ARROW I1
ENGINE AND PROPELLER
The Cherokee Arrow I1 incorporates a Lycoming 10-360-ClC** or 10-360-ClC6***
four-cylinder, direct drive, horizontally opposed fuel injected engine rated at 200 horsepower at
2700 RPM. It is furnished with a starter, 60 ampere 14-volt alternator, shielded ignition,
vacuum pump drive, fuel pump, propeller governor and a dry automotive type induction air
filter. A recommended overhaul period of 1400 hours is based on Lycoming service experience.
Operation beyond the recommended time is the decision of the operator. Since Lycoming from
time to time revises the recommended overhaul period, the owner should check the latest
Lycoming Service Instruction at his Piper dealer for the latest recommended overhaul period
and for any additional information.
The aircraft is equipped with a constant speed, controllable pitch propeller. The propeller
control is located on the power quadrant between the throttle and mixture controls. A mixture
control lock* is provided to prevent activation of the mixture control instead of the pitch
control.
The exhaust system is a crossover type, which reduces back pressure and improves
performance. It is constructed entirely of stainless steel and is equipped with dual mufflers.
Cabin heat and windshield defrosting are provided by a heater shroud around the muffler.
An oil cooler is located on the forward lower right side of the firewall, with the air inlet for
the cooler located on the right side of the bottom cowling. A winterization plate is provided to
restrict air during winter operation. (See Winterization in Handling and Servicing.)
The induction system incorporates a Bendix RSA-SAD1 type fuel injector. The injector is
based on the principle of differential pressure, which balances air pressure against fuel pressure.
The regulated fuel pressure established by the servo valve when applied across a fuel control
(jetting system) makes the fuel flow proportional to airflow. Fuel pressure regulation by the
servo valve causes a minimal drop in fuel pressure throughout the metering system. Metering
pressure is maintained above most vapor forming conditions while fuel inlet pressure is low
enough to allow use of a diaphragm pump. The servo system feature also checks vapor lock and
associated starting problems.
The servo regulation meters fuel flow proportionally with airflow and maintains the
mixture as manually set for all engine speeds. The fuel flow divider receives metered fuel and
distributes fuel to each cylinder fuel nozzle. The fuel flow portion of the manifold fuel flow
gauge is connected to the flow divider and monitors fuel pressure. This instrument converts fuel
pressure to an indication of fuel flow in gallons per hour and percentage of rated horsepower.
The alternate air source of the induction system contains a door that functions
automatically or manually. If the primary source is obstructed, the door will open
automatically. It may be opened manually by moving the selector on the right side of the
quadrant. The primary source should always be used for take-off.
The pilot should read and follow the procedures recommended in the Lycoming Operator's
Manual for this engine, in order to obtain maximum engine efficiency and time between engine
overhauls.
*
Serial nos. 28R-7535001 and up
**
Serial nos. 28R-7435001 through 28R-76355 16
***
Serial nos. 28R-7635517 and up
AIRPLANE AND SYSTEMS
REVISED: FEBRUARY 28,1977