MD Helicopters 369E, Руководство по летной эксплуатации вертолетов

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General
ROTORCRAFT FLIGHT MANUAL
MD 500E
(Model 369E)
CSP − E − 1
Revision 14 1 − 10
Limiting the maximum power to less than the maximum rated power pro-
vides a higher engine critical altitude. The power turbine governor provides
automatic constant speed control of rotor RPM.
Drive System:
The overrunning clutch transmits power from the engine to the main drive
shaft. The clutch has no external controls and disengages automatically dur-
ing autorotation and engine shutdown. The main drive shaft connects to the
main rotor transmission input shaft. The engine oil cooler blower is belt
driven off the main drive shaft. The oil cooler blower draws cooling air from
the air inlet fairing to supply ambient air to the engine and transmission
oil coolers and to the engine compartment.
The main rotor transmission is mounted on the basic airframe structure
above the passenger/cargo compartment. The transmission is lubricated by
its own air cooled lubrication system.
The main rotor static mast is non−rotating and is rigidly mounted to the
mast support structure. The rotor hub is supported by the rotor mast.
Torque is transmitted independently to the rotor through the main rotor
drive shaft. Lifting loads are prevented from being imposed onto the main
transmission eliminating thrust loading of transmission parts.
The tail rotor transmission is mounted on the aft end of the tailboom and
has a self−contained lubricant system. The tail rotor is mounted on the out-
put shaft of the transmission and consists of two variable−pitch blades.
Main rotor system:
The helicopter utilizes a five bladed, fully articulated main rotor assembly
with unique features. While contemporary helicopters use torsion tension
straps in lieu of thrust bearing stacks to contain blade centrifugal loading
and allow feathering, the MDHI strap pack arrangement goes three steps
further. First, the strap configuration (while secured firmly to the hub) ac-
tually allows the centrifugal load exerted by one blade to be countered by
the force exerted by the opposite two blades. Thus, very light centrifugal
loads are sensed by the hub. Second, the V−legs of the strap pack rotate as
driving members to turn the blades. Finally the straps are configured to al-
low feathering and flapping of the blades. The main rotor blades are se-
cured to the hub with quick release lever type pins.
Flight controls:
Cyclic, collective, and adjustable pedal controls are provided at the left crew
position (right position, military only). Adjustable friction devices, which
may be varied to suit the individual pilot, are incorporated in the cyclic, col-
lective and throttle controls. In addition, electrical cyclic trim actuators al-
low flight loads to be trimmed out. Since stick control forces are low, a hy-
draulic boost system is unnecessary. An optional dual control system may be
easily removed to provide room for passengers or cargo.