maximum continuous operation at sea level with standard atmosphere
conditions. The engine is mounted horizontally on shock mounts within the
center frame section.
The engine transmits power through a belt drive transmission assembly to
the main transmission and tail rotor drive shaft. The lower pulley of the belt
drive receives power from the engine crankshaft and directs the power to the
upper pulley through a matched set of V-belts. An idler pulley running
against the set of belts and connected to a pilot-controlled actuating
mechanism operates as a clutch to engage and disengage the upper pulley
with the lower pulley. The upper pulley attaches to the input shaft of the
main transmission and incorporates an over running clutch that permits the
main rotor to drive during the autorotation without engine power.
The main transmission mounts on the lower end of the nonrotating main
rotor mast and is rigidly fixed in position by support members connected to
the center frame section. The transmission is lubricated by a self-contained
lubrication system and is cooled by airflow around the housing.
The main rotor drive shaft transmits power from the main transmission to the
main rotor hub. A thrust bearing, acting upon a shoulder on the drive shaft,
positions the shaft within the mast.
The three-bladed main rotor system is fully articulated with flapping hinges
and lead-lag hinged blade attachment.
The one-piece tail rotor drive shaft requires no intermediate couplings or
bearings. Excessive oscillation of the drive shaft during acceleration and
deceleration of the drive system is suppressed by the drive shaft damper,
located near the center of the tailboom.
The tail rotor transmission is located at the aft end of the tailboom and has a
self-contained lubricant supply. The tail rotor is mounted on the output shaft
of the tail rotor transmission and consists of two variable-pitch blades. The
blades are interconnected by a high-strength, tension-torsion strap
assembly.
The helicopter main fuel tank has a total capacity of 35.2 or 33.0 U.S. gallons
(133 or 125 liters) depending on aircraft S/N, and is located externally on the
left-hand side of the cabin bulkhead. An auxiliary tank with a total capacity
of 30.0 or 33.0 U.S. Gallons (113 or 125 liters) depending on aircraft S/N
may be attached externally to the right-hand side of the cabin bulkhead.
General
Pilot's Flight Manual
Reissued: 16 Jan 2019 1-7
SCHWEIZER
Model 269C-1 Helicopter
CSP book 2..indd 33 8/4/19 12:53 PM
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