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parameter computation; and
• Diagnostic functions.
The FMS, when equipped with a current navigation database, provides accurate flight planning
and three-dimensional steering command outputs, to facilitate optimum great-circle, point-to-point
navigation within the limits of the aircraft.
NAVIGATION SYSTEMS
Description
Vol. 2 17−10−1
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
GENERAL (CONT'D)
Associated Components
The following components (based on a standard cockpit configuration) are associated with the
operation of the navigation systems:
• Two display control panels (DCPs)
• Two primary flight displays (PFDs)
• Two multifunction displays (MFDs)
• Two radio tuning units (RTUs)
• Two FMS control display units (RTUs)
• One source selector panel
INERTIAL REFERENCE SYSTEM (IRS)
Description
The IRS installed in the Challenger 604 is the Litton LTN-101 inertial reference unit. It is a fully
independent, self-contained navigation system, which provides attitude, directional, position, and
three-axis rate/acceleration data to the following aircraft systems:
• PFD and MFD displays
• Automatic flight control system (AFCS)
• Weather radar system
• EGPWS
• TCAS
• Fuel system (for fuel quantity indications)
• Flight data recorder (FDR)
• Air data computer (ADC)
• Flight management system (FMS)
The standard installation consists of two IRS systems, IRS 1 and IRS 2 (see Figure 17−10−1). A
dual MSU (mode select unit), installed in the cockpit, provides control functions for the two IRS
systems. An optional third IRS, including a single MSU, may also be installed.
Components and Operation
Inertial Reference Unit (IRU)
Each IRU uses three laser gyros and three linear accelerometers to sense aircraft attitude and
acceleration. After alignment is successfully completed, the IRU outputs the following data for
use by other aircraft systems:
• Attitude (pitch, roll, yaw)
• Heading (true and magnetic)
• Inertial position (latitude and longitude)
• Ground speed
• Wind direction and speed
• Three-axis body rate and acceleration (includes an inertial vertical velocity component to
the VSI)
NAVIGATION SYSTEMS
Description
Vol. 2 17−10−2
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
INERTIAL REFERENCE SYSTEM (IRS) (CONT'D)
• Flight path data
Each IRS receives true airspeed and altitude from the on-side air data system. In the event of a
failure of the on-side air data input, the cross-side input is automatically selected.
Power Supply
Each IRU has two power sources, a 115-volt AC source and a backup 28-volt DC source.
Either source is sufficient for operation, but both are required for initial startup. Inside the IRU,
the battery backup circuit automatically switches to the backup 28-volt DC source when the
normal 115-volt AC source is not available. During startup, the battery backup circuit verifies
that backup power is available by momentarily switching off the 115-volt AC input. The IRS
1(2)(3) ON BATT advisory EICAS message is displayed when an IRU is operating on DC power
only.
115-volt, 400-Hz AC power is also supplied to the IRU cooling fans.
IRU Power Sources
IRU # AC POWER BACKUP DC POWER
1 AC Essential Bus Battery Bus
2 AC Bus 2
DC Essential Bus
Battery Bus
3 AC Bus 1 Battery Bus
Mode Select Unit (MSU)
The mode select unit provides the necessary switches that select the modes of operation of
each IRS. All IRS-related annunciations are displayed as EICAS messages or FMS CDU
scratchpad messages.
Each MSU switch has three positions: OFF, NAV, and ATT. Power is applied to the IRU
whenever the respective switch is selected to the NAV or ATT position.
Figure 17−10−1 illustrates the dual MSU (for IRS 1 and 2) and the single MSU for the optional
third IRU.
Mode Select Unit
Figure 17−10−1
NAVIGATION SYSTEMS
Description
Vol. 2 17−10−3
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
INERTIAL REFERENCE SYSTEM (IRS) (CONT'D)
IRS Reversionary Mode Selectors
IRS reversionary mode selector switches are provided to control IRU outputs to the pilot’s and
copilot’s PFD and MFD displays. In the event of an IRU failure, the selectors can be used to
restore IRU data to the affected side’s displays.
With the reversionary switches at NORM, the PFD and MFD displays normally receive data from
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庞巴迪挑战者604操作手册 Operating Manual 4(61)
