Flight Controls Flashcards
The primary flight control system consists of:
(1) Ailerons and the multi function roll spoilers for roll axis control.
(2) Elevators for pitch axis control.
(3) Rudder for yaw axis control.
The secondary flight control system consists of:
(1) Horizontal stabilizer.
(2) Flaps and Slats.
(3) The multi-function spoiler (when used as speed brakes or ground spoilers).
(4) Dedicated ground spoilers.
Hydraulic actuators control the respective flight control surfaces. These are referred to as _____
Power Control Units (PCUs).
_______are controlled electronically using Fly-by-Wire (FBW) technology.
Elevators, rudders, roll spoilers as well as all secondary flight control systems, including the horizontal stabilizer, flaps and slats, ground spoilers and speed
brakes,
The ____ are commanded by conventional control cables that run from each control wheel back to a pair of hydro-mechanical actuators.
ailerons (not FBW)
The primary flight control electronics include two complementary parts:
(1) The Primary Actuator Control Electronics (P-ACE).
2) The Flight Control Module (FCM
Manual pilot trim commands are limited to ____
3 s
Fly-by-wire is an electronic system designed to operate the flight controls replacing the _____ of a conventional airplane.
control cables
The EMBRAER FBW system is composed of a set of ___ Actuator Control Electronics (ACEs) and ___ Flight Control Modules (FCMs):
nine Three Primary-ACEs (P-ACE). Two Slat/Flap ACEs (SF-ACE). One Horizontal Stabilizer ACE (HS-ACE). Three Spoiler ACEs (S-ACE).
four
The ___ provide software-based assistance to the P-ACE and is required for ____-mode operation of the flight controls system.
FCMs
normal
The FCM units are connected to the P-ACE via the _______, providing digital inputs to the P-ACE, which are combined with pilot inputs. This is used to augment pilot inputs for different airspeeds, and provides other high-level functions such as Angle-of-attack (AOA) limiting to the P-ACE units
Controller Area Network Bus (CAN BUS),
The 3 P-ACE units control the
rudder and the elevator surfaces.
MODES OF OPERATION
NORMAL MODE: The Flight Control Module (FCM) provides software based airspeed gain schedules and control limits to the P-ACE, as well as high level functions
DIRECT MODE: The FCM is removed from the control loop (for instance, due to loss of airspeed data) and the control limits default to values set by hardware in
the P-ACE
The following systems provide data to the flight controls system:
A. Smart probes and the Air Data Application (ADA) modules provide air data for various airspeed augmentation commands.
B. The IRS provides airplane attitude and accelerations to the FCMs used for AOA limiting function computation.
C. The Proximity Sensor Electronic Module (PSEM) provides Weight-On-Wheels (WOW) and ground spoiler position data to the FCMs
D. Brake Control Modules (BCM) provide wheel speed signals used for ground spoiler deployment.
E. The FADEC provide Thrust Lever Angle (TLA) to the FCMs used for elevator thrust compensation, and the Automatic Flight Control System (AFCS) provides
autopilot commands.
F. Data is shared for the EICAS to display warnings, cautions, advisory and system status and also provided to the central maintenance computer (CMC) for system
diagnostics
The Controller Area Network BUS (CAN BUS) is the communication link between the FCMs and the P-ACE units while the Avionics Standard Communication Bus (ASCB) provides data exchange between all FCMs, and with other components of the avionic system.
