Specifications

CESSNA SECTION 7
MODEL 172R NAV III AIRPLANE AND SYSTEM DESCRIPTION
GFC 700 AFCS
U.S.
ENGINE (Continued)
NEW ENGINE BREAK-IN AND OPERATION
The engine run-in was accomplished at the factory and is ready for the
full range of use. It is suggested that cruising be accomplished at 80%
power as much as practicable until a total of 50 hours has accumulated
or oil consumption has stabilized. This will ensure proper seating of the
piston rings.
ENGINE LUBRICATION SYSTEM
The engine utilizes a full pressure, wet sump type lubrication system
with aviation grade oil as the lubricant. The capacity of the engine
sump, located on the bottom of the engine, is eight quarts with one
additional quart contained in the engine oil filter. Oil is drawn from the
sump through a filter screen on the end of a pickup tube to the engine
driven oil pump. Oil from the pump passes through a full-flow oil filter, a
pressure relief valve at the rear of the right oil gallery, and a
thermostatically controlled remote oil cooler. Oil from the remote cooler
is then circulated to the left oil gallery. The engine parts are then
lubricated by oil from the galleries. After lubricating the engine, the oil
returns to the sump by gravity. The filter adapter in the full-flow filter is
equipped with a bypass valve which will cause lubricating oil to bypass
the filter in the event the filter becomes plugged, or the oil temperature
is extremely cold.
An oil dipstick/filler tube is located at the right rear of the engine case.
The oil dipstick/filler tube is accessed through a door located on the
right side of the engine cowling. The engine should not be operated on
less than five quarts of oil. To minimize loss of oil through the breather,
fill to eight quarts for normal flights of less than three hours. For
extended flight, fill to eight quarts (dipstick indication only). For engine
oil grade and specifications, refer to Section 8 of this POH.
(Continued Next Page)
172RPHBUS-00
7-35