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KEY OWNER/USER BENEFITS
Reduced flight crew workload Passenger comfort Low-wire count due to digital interfaces and resource sharing
in IAPS High reliability from reduced parts count and a controlled
environment in IAPS Category II approach performance RVSM compatible altitude tracking performance Operational flexibility with a variety of flight director
modes available to meet customer requirements Reduced maintenance crew workload through an extensive diagnostics
mode Numerous certifications of this family of autopilot systems
and a skilled team of certification engineers Growth potential to provide 21st century
functionality
OVERVIEW
The APS-3000 Autopilot System is an integrated autopilot and flight
director system designed to take full advantage of the benefits of the Pro
Line 21 integrated avionics system. The system provides dual independent flight
directors and a three-axis fail-passive autopilot with automatic pitch trim
control signals. The APS-3000 has a highly monitored architecture that provides a fail-passive
response to internal failures. This means that the system is extremely safe
for the crew and passengers. Most failures are detected and annunciated and
an autopilot disconnect imposed if appropriate, without a control response.
Failures of external sensors that are not detectable will not cause a maneuver
that is more aggressive than normal handling. The APS-3000 is another step in the evolution of digital automatic flight
control systems at Rockwell Collins. The APS-3000 shares power supply, input/output,
signal conditioning and environmental control with other functions residing
in the Integrated Avionics Processing System (IAPS). This resource sharing
reduces wiring and installation complexity and improves reliability. The system is highly flexible and can be tailored to meet the airplane's
mission with relative ease. This is due in part to the fact that most of the
system functionality is implemented with software. This software has a legacy
of numerous Pro Line 4 and Pro Line 21 applications. In addition, the system has a variety of mode select panels and autopilot
engage panels available to match the system functionality and the flight deck
operational philosophy. Also, a number of servo motor and servo mount options
are available to interface with the airplane's flight control system. System performance is superior to previous autopilot systems, because
the APS-3000 has benefited through the experience of the Collins flight control
design and certification experts as well as data gathered through advanced
modeling techniques and onboard test equipment. Installation is eased by the integration of the Flight Guidance Computer
(FGC) into the IAPS. Rockwell Collins mechanical engineering staff is prepared
to assist with the more difficult aspects of installation such as servo motor
and mount location as well as review the physical sensor installation for
optimum performance with respect to autoflight. Federal Aviation Regulation/Joint Airworthiness Requirement Part 23
or Part 25 certification is eased by a Rockwell Collins team of experts who
calibrate the system on a test vehicle in such a way as to account for all
expected deviations in the production airframes and over the life of the airplane.
These certifications are typically approved for Category II all weather operations.
Rockwell Collins has developed relationships with certification authorities
worldwide.
DESCRIPTION
The Collins APS-3000 is a fully digital, dual channel, fail-soft or
fail-passive autopilot system that provides exceptional autoflight capability
in the Pro Line 21 avionics systems. The system benefits
from integration into Pro Line 21 in terms of reliability and weight. The
system typically consists of two FGC-3000, one FGP-300X Flight Guidance Panel
and three SVO-3000/SMT-65 servo motor/mounts. The APS-3000 drives the aircraft Pitch Trim System through a highly
monitored relay system. Direct drive of a pitch trim servo motor is also available. The heart of the system is a digital flight control computer that is
implemented via two Line Replaceable Modules (LRMs), each with two microprocessors.
This computation power provides for unsurpassed flight precision and operational
flexibility on two independent flight director channels. The FGP offers a single point for either crew member to make lateral
and vertical mode selections as well as reference adjustments. Optional Mode
Select Panel(s) (MSPs) may be installed when there are space limitations. The servo interface with the airplane flight control system is through
lightweight, high reliability servo motors. The primary servo motors have
dual monitoring tachometers to ensure that faults at the servo will be detected
and isolated quickly. The servo is connected to the primary flight control
system through a slip clutch mechanism which is provides an override capability
in the unlikely event of a servo motor jam.
OPERATION AND PERFORMANCE
Each of the APS-3000 flight guidance channels sends commands to the
attitude director indicator and to the autopilot function. The selected mode
can be flown manually or automatically. The typical modes and functionality
are provided in the following tables.
Available Lateral Modes
Roll Hold | Hold roll attitude. Typical
roll limit - 32°. Holds
heading when engaged below 5° bank. | Selected
Heading | Provides roll guidance to capture and track the selected
heading (HSI bug) Typical roll limit - 27° | Track Hold | Provides roll guidance to
capture and track the ground . Track provided by an IRS or FMS. | Half
Bank | Provides reduced roll limit, typically 15° Manually selectable or automatic at altitude. | Navigation | Provides guidance relative
to the Source selected on the PFD: VOR - Capture and track of the selected Course LOC - Capture and track of the Localizer FMS - Follows lateral commands provided by the FMS | Approach | Provides
guidance relative to the Source selected on the PFD: | Backcourse | Provides guidance to the
backcourse of the selected Localizer. Automatic backcourse with approach is
also available. | Go
Around | Holds wings level at selection of Go Around. | Rudder Boost | Provides rudder pedal force
assistance in the event of engine failure. |
Available Vertical Modes
Pitch Hold | Hold pitch attitude Typical
roll limit - +20°and -15°. | Vertical
Speed | Pitches to and tracks the Vertical Speed reference
(VS bug). | Altitude Hold | Holds the Pressure Altitude
when the mode is selected. | Altitude
Select | Captures and tracks the Preselected Altitude. | Flight Level Change | Provides climb or descent
guidance towards the preselected altitude. Capable of using pre-programmed
reference speeds, or capturing and tracking the speed bug. | Speed
Hold | Provides pitch guidance to capture and track the IAS/MACH
reference (IAS/MACH bug). | Automatic IAS/MACH
Transition | Provides
automatic transition between the IAS reference and MACH reference at a predetermined
altitude. | Approach | Provides
capture and track of the glideslope for the Localizer selected on the PFD. | Go Around | FD guidance only to a fixed
pitch attitude at selection of Go Around. Value determined by OEM, typically 10°. | Takeoff | Provides
pitch commands for takeoff guidance. Capable of an automatic alternate angle
for single engine operation. | VNAV | Enables vertical functionality
of FMS as determined by the installation. | Overspeed | Automatically
asserts Speed Mode with a reference below Vmo/Mmo when Vmo/Mmo is exceeded. | Turbulence Mode | Softens the control responses
to improve ride comfort in turbulent conditions. |
FGC-300X Flight Guidance Computer
The FGC-300X is a line replaceable module that resides in the IAPS.
The APS-3000 requires two of these modules. Each FGC provides an independent
flight director function. Either one is selected by a switch on the mode panel
to provide FD guidance on both crew displays. Independent guidance is only
provided for precision approach, such as Glideslope track. The flight director
operates in the mode selected by the crew and performs the guidance computations
that result in commands that are provided to the flight crew displays via V-bars
or crosshairs and to the autopilot function.
The FGCs operate together to provide the autopilot function. Each FGC
computes its own servo command to drive the servo motors. These commands are
routed through a midvalue voter. The analog commands are also torque limited.
Servo rate is used as feedback of servo movement to close the servo loop. The FGCs also operate together to provide the automatic pitch trim function.
The FGCs sense torque on the primary pitch servo and generate arm and command
signals to drive the pitch trim servo or external trim control system. Discrete
signals are received from the trim system for feedback of trim system response
to commands as well as for monitoring of unexpected trim system operation.
FGP-300X Flight Guidance Panel
The FGP-300X provides crew interface with most flight director and autopilot
functions. It contains a pushbutton for each mode selection available. The
FGP transmits button presses to the FGC for mode selection. A capability is
available to have Light Emitting Diode (LED) annunciators for each button
to indicate the FGC has accepted the mode request. Annunciation of the current
mode of operation is provided on the Primary Flight Display.
Various versions of the FGP are possible to accommodate the application.
Variations include available mode selections, panel color and lighting power.
The choices are identified in the Selection Guide. The FGP-300X also provides the crew interface with the autopilot and
yaw damper. it contains the autopilot and yaw damper engage, flight director
transfer and turbulence mode pushbuttons. The FGP provides system engage requests to the FGC and provides clutch
engage power to the servos when the FGC acknowledges the engagement. The FGP is typically mounted in the glareshield and occasionally in
the pedestal. For installations that have space limitations, the MSP-85 and
APP-85 series panels may be used. See the APS-85 Section Guide for available
choices.
SVO-3000 Servo Motor
The SVO-3000 is a DC servo motor with dual rate feedback tachometers.
The motor is mechanically coupled to the servo pinion output through a magnetic
engage clutch. The SVO-3000 is based on the SVO-65( ) series servo motors
that have a long history of installations. Three versions of servo provide
three levels of available torque to meet the requirements of the control system
installation. See the Selection Guide for details.
SMT-65( ) Servo Mount
The servo attaches to the SMT-65( ) Servo Mount where the pinion is
geared to a capstan output. This is the mechanical tie into the primary control
system. The mount includes a friction slip clutch that allows continued use
of the primary controls in the extremely unlikely event of a servo jam. Various
load ranges and output configurations of the SMT-65 are available. See the
APS-65 Selection Guide for available choices.
APS-3000 System Certifications
Bombardier Challenger 300 Cessna Citation CJ1+/CJ2+ Cessna Citation CJ3 Cessna Citation Encore+ Cessna Citation XLS+ Gulfstream G150 Hawker Beechcraft C90Gti/B200GT/350 Hawker Beechcraft Premier IA Hawker Beechcraft Hawker 800XP/850XP/750/900XP Piaggio Avanti II
APS-3000 SYSTEM CERTIFICATIONS
Cessna Citation CJ1,
CJ2 and CJ3 | FGC-3000 | TC FAA | Raytheon
Premier I | FGC-3000 | TC FAA | Raytheon Hawker 800XP | FGC-3000 | TC FAA |
TYPICAL SYSTEM
FGC-3000 | 2 | Flight Guidance Computer | Varies with Application | FGP-3000 | 1 | Flight Guidance Panel | Varies with Application | SVO-3000 | 3 | Servo Motor | Varies with Application | SMT-65 | 3 | Servo Mount | Varies with Application |
Note(s): | See Installation Hardware table for mounts and connectors
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SPECIFICATIONS
FAA TSO | C52b (Flight Director) C9c
(Autopilot) | C20(Flight Director) C52b C9c
(Autopilot) | Environmental | DO-160D With
Heater[(A2)(F2)Y]BBB[(TCC1R) (SLM)EXXXXSZ[BZ]AZZ [WWP]H[Z3Z4]XAA Without
Heater[(A2)(C4)(F1)Y]BBB[(TCC1R) (SLM)]EXXXXSZ[BZ]AZZ [WWP]H[Z3Z4]XAA | DO-160D [A2F1]XBBB[SBM]
EXXXXXZ[BZ]AZC [WWP]H[Z3Z3]XXA | EUROCAE | | |
Height | 222
mm (8.73 in) | Varies with Application | Width | 151 mm (5.95 in) | Varies
with Application | Length | 53
mm (2.07 in) | Varies with Application | Weight | 1.04 kg (2.3 lb) | Varies
with Application | Mounting Information | Mounts in Collins ICC No
special hardware required | Varies
with Application |
Temperature | -55 to 70°C | -20 to 70°C | Altitude | 55,000 ft | 55,000 ft |
Primary | 28
V DC, 25 W (internal dissipation supplied
by ICC) | 28
V DC, 4 W total internal dissipation | Lighting | N/A | 5 V AC/DC, 13 W | | | | 28 V DC, 13 W |
FAA TSO | C9c (Autopilot) | -C9C | Environmental | DO-160D | DO-160A | | | [(A2)(F2)X]BBB[TDDIP] E2RFXXXA[BZ]AZZ[WWP] H[Z3Z3]XBA | F2A2/B/JY/XXXXXXXXXXX |
EUROCAE | ED-14B | ED-14A |
Height | 95.3
mm (3.75 in) | 90.47
mm (3.56 in) | Width | 90.5 mm (3.56 in) | 95.25 mm (3.75 in) | Length | 150
mm (5.91 in) | 50.8
mm (2.0 in) | Weight | 1.0 kg (2.3 lb) | 0.64 kg (2.0 lb) | Mounting Information | Mounts to Collins SMT-65 using standard
aircraft quality hardware | Flange |
Temperature | -55 to 70°C | -55 to 70°C | Altitude | 55,000 ft | 55,000
ft |
| Primary | 28 V
DC, 77 W | N/A | | Lighting | (56 W max torque 21
W clutch) | (56 W max torque 21
W clutch supplied by FCP) |
SELECTION GUIDE
FGC-300X | N/A, Part of Pro Line 21
integrated system | | FGP-300X | N/A,
Part of Pro Line 21 integrated system | | | | | |
SVO-3000 | 20-60
in lb torque | 822-1168-001 | | | 50-95 in lb torque | 822-1168-002 | | | 80-150
in lb torque | 822-1168-003 | | | 20-50 in torque, special HIRF, see Note 1 | 822-1168-021 | | | 50-95
in lb torque, special HIRF, See Note 1 | 822-1168-022 | | | 80-150 in lb torque, special HIRF, see Note 1 | 822-1168-023 | Note(s): | Qualified for better
HIRF protection with improved EMI grounding characteristics. Requires mating
with SMT-65-10X series part numbers. |
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SMT-65 | 20 to 78 in lb | 2
in capstan | 0.062 in | 622-5735-001 | | | 20
to 177 in lb | 2 in capstan | 0.062 in | 622-5735-002 | | | 20 to 78 in lb | 2
in capstan | 0.093 in | 622-5735-003 | | | 20
to 177 in lb | 2 in capstan | 0.093 in | 622-5735-004 | | | 20 to 78 in lb | 2
in capstan | 0.062 in | 622-5735-101 | | | 20
to 177 in lb | 2 in capstan | 0.062 in | 622-5735-102 | | | 20 to 78 in lb | 2
in capstan | 0.093 in | 622-5735-103 | | | 20
to 177 in lb | 2 in capstan | 0.093 in | 622-5735-104 | SMT-65B | 20 to 177 in lb | Sprocket | N/A | 622-6140-002 | Note(s): | SMT-65-10X mount series part numbers have improved HIRF characteristics
for use with SVO-3000. Requires mating with SVO-3000 series -021, -022 and
-023. |
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INSTALLATION HARDWARE
| | 2 | Connector | Varies with application |
| | 1 | (-001) aircraft mating connector | 371-6458-000 | | | | or | | | | 1 | (-001) aircraft mating connector | 359-0301-230 | | | 1 | (-002) aircraft mating connector | 371-6459-000 | | | | or | | | | 1 | (-002) aircraft mating connector | 359-0301-240 | | | 1 | (-003) aircraft mating connector | 371-6460-000 | | | | or | | | | 1 | (-003) aircraft mating connector | 359-0301-250 | | | 1 | (-021) aircraft mating connector | 359-0680-630 | | | 1 | (-022) connector | 359-0680-620 | | | 1 | (-023) connector | 359-0680-610 | Note(s): | The 371-
connectors use solder cup connections; the 359- connectors use crimp connections. |
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