MD Helicopters MD900 with PW206E, Руководство по эксплуатации самолета

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CSP–900RFM206E–1
ROTORCRAFT FLIGHT MANUAL
MD900 With PW 206E
Systems Description
Original
7–40
the failure of another function. These fault monitoring provisions are
implemented using hardware Built−in−Test Equipment (BITE) and soft
ware diagnostics, allowing isolation of failures to at least the internal
module level. In addition, provisions are made to check operation of
the transducers and sensors and provide an appropriate maintenance
alert.
Any sensor that can be checked for proper function and is determined
to have failed causes an IIDS
caution annunciation and a blanking of
the digit display for that parameter. No Fault Log is created.
The following are exceptions to the above:
1. A failure of a sensor for the primary display parameters (EGT,
Torque, N
R
, and N
P
) causes both the vertical scale and digit value
to blank.
2. If the voltage for the fuel probes (Battery Bus voltage input) drops
below the specified operating low limit of 18 volts for more than
40 seconds, the low voltage indication shall be to blank the segments
in the fuel quantity vertical scale. The digit quantity shall remain
active. When the probe voltage goes back above 18 volts for more
than one second, the vertical scales shall be illuminated. A failure
of one of the
fuel probes causes only the digit values to blank whereas
the failure of both probes causes both the vertical scale and digit
value to blank.
3. If the parameters displayed on the alphanumeric display (Pressure/
Density Altitude, L/R engine fuel flow, CLP, and Hydraulic Pressure)
are out−of−range, the display
will read NOT VALD.
The functional architecture of the IIDS to meet these design goals and
the operational requirements of the aircraft is shown in Figure 7−22.
SYSTEM OPERATING PROGRAM: The System Operating Program
provides the programming and functions controlling the data collection,
displays and formatting, key entry functions, date/time clock, cautions
and warnings, exceedance detection, memories and BIT feature.
The integrated display is divided into two separate displays. The prima
ry is on the right side and the secondary is on the left.
The primary display includes the following information.
Power turbine speed: N
P
Rotor speed: N
R
Measured gas temperature: EGT
Engine Torque: TORQUE
N
R
and N
P
are displayed with three vertical bargraphs and a digit
value of N
R
displayed in the center.
System
Software
Architecture
Primary and
Secondary
Displays