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1.
D
The Safe Flight Instrument Corporation Enhanced Autopower Auto Throttle System (ATS) incorporates
dual-servo control of the thrust levers to enable thrust and speed control for takeoff, climb, cruise,
descent, landing, and go-around modes of operation. The ATS is available in Automatic Flight Control
System (AFCS) coupled (autopilot or flight director modes), as well as AFCS-disengaged flight. In
addition, the enhanced system includes automatic full-time N1 engine synchronization with
pilot-selectable N2 engine synchronization available in cruise.
The ATS is interfaced with the Precision Plus update of the Collins FMS 6000 (Challenger Service
Bulletin SB604-34-031) and is capable of controlling engine thrust from takeoff to touchdown in
conjunction with AFCS vertical modes and Vertical Navigation (VNAV) plan speeds. The system uses
the Flight Management System (FMS) thrust management table-based N1 limit and target calculations
as displayed on the primary Engine Instrument Control And Indication System (EICAS) N1 fan speed
displays. It is operational through all phases of flight, allowing the system to control engine thrust.
Installation of the ATS includes a dual servo clutch pack, an ATS computer, dual Mode Status Displays
(MSD), and an ATS Control Panel (CP). In addition, the original thrust lever quadrant is replaced with a
quadrant that includes ATS disconnect switches on both thrust levers. The thrust lever friction control is
deactivated, and proper thrust lever friction is maintained by the ATS clutch system. Circuit breaker
CBP1 G-7, AUTO THROTTLE, provides circuit protection for this system. Circuit breaker CBP2 P-8,
AUX ANNUN, provides circuit protection for the ATS MSD.
The ATS consists of the components listed in
ARINC 429 data bus to the Air Data Computer (ADC), Inertial Reference Unit (IRU) 1, left Input/Output
Concentrator (IOC), and ground proximity warning computer. The engine N1 speeds are picked up at the
left engine control amplifier, A1KH; and the right engine control amplifier, A2KH. The ATS computer is
also interfaced to the flap control lever, which supplies a ground from the flaps in the 0, 20, 30, and 45
degree positions. Weight-on-Wheels (WOW) logic is also interfaced to the ATS computer.
NOTE: Refer to Safe Flight Repair Procedure Document No. R-2830 (included as an attachment) for
2.
L
OCATION
The main components of the ATS and their locations are listed in the following table and figure.
EFFECTIVITY:
A1.0
AUTO THROTTLE SYSTEM
AUTO THROTTLE SYSTEM - DESCRIPTION/OPERATION
ESCRIPTION
additional information pertaining to installation, repair and part replacement.
Component
ATS computer
Dual servo clutch actuator assembly
ATS mode status display
Control panel with engage switch (ATS),
green LED engaged mode annunciators,
and N2 synchronization selector (N2 SYNC)
TE-22305001-SMM-2
CL-604 SUPPLEMENTAL MAINTENANCE MANUAL
Prepared by DAS-605786-NM
Table
Forward avionics bay, FS244.4, LBL19.75, WL59.35
Forward avionics bay, FS250, BL 0.00, WL76.5
Pilot's and copilot's glareshield
Pilot's glareshield
ATS COMPONENTS AND LOCATIONS
TABLE 1
1. The ATS computer is interfaced through an
Location
22-30-00
Page 1
Dec 3/03
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