sadffdddd Flashcards
Primary flight controls
Ailerons and multi-function roll spoilers
Elevators
Rudder
Secondary flight controls
Horizontal stabilizer
Flaps and slats
Multi-function spoiler when used as speed brakes or GLD
Dedicated ground spoilers
What moves the flight controls?
PCUs Power Control Units
Hydraulic actuators
How are the ailerons moved?
Control cables that run from each control wheel back to a pair of hydro mechanical actuators
Two components of primary flight control electronics
Primary Actuator Control Electronics (P-ACE)
Flight Control Module (FCM)
Pitch trim switch limits
Only half the switch actuated for more than 7s it is auto deactivated
Manual trim inputs limited to 3s
Captain trim has priority over FO
FltCtrl synoptic airplane control surface position status for: RETRACTED
Green line aligned with wings, elevator and rudder
FltCtrl synoptic airplane control surface position status for: DEPLOYED
Green line and the surface with green stripes
White dashed box for deflection 50% or greater
FltCtrl synoptic airplane control surface position status for: FAILED RETRACTED
An amber line, a white dashed box and and amber cross
FltCtrl synoptic airplane control surface position status for: FAILED DEPLOYED
White dashed box, surface with amber stripes and amber cross
FltCtrl synoptic airplane control surface position status for: NOT AVAILABLE WITH NO FAIL INDICATION
White dashed box for surfaces with deflection in one direction
Two white dashed box for surface deflection in two directions
FltCtrl synoptic airplane control surface position status for: NOT AVAILABLE WITH FAILURE INDICATION
White dashed box and an amber cross for surfaces with deflection in one direction
Two white dashed box and two amber crosses for surfaces with deflection in two directions
FltCtrl synoptic airplane control surface position status for: DIRECT MODE
Amber stripes
White dashed box is shown only for surface position greater than 50%
FltCtrl synoptic airplane control surface position status for: FULL DEPLOYED
Solid green box
ACE
Actuator Control Electronics
FCM
Flight Control Module
Flight Control System: NORMAL MODE
Provides software based airspeed gain schedules and control limits to the P-ACE
Flight Control System: NORMAL MODE - High level functions
Elevator control laws scheduling with airspeed
Auto-thrust compensation with elevator
AOA limiting with elevator offset
Rudder airspeed gain scheduling and stroke limiting
Yaw damper and turn coordination via AFCS
Rudder flight authority
Roll spoiler scheduling with airspeed and speedbrake deployment
Configuration change compensation with horizontal stabilizer due to speed brakes actuation
Flight Control System: Direct mode
The FCM is removed from the control loop and the control limits default to values set by hardware in the P-ACE
Flight Control System: Direct mode - extra
Direct mode of ops is primarily the result of loss of data from all FCM or multiple ACE failures
Operation is defaulted to fixed control laws config
Control input provided by captain and FO sensors is sent directly to the surface
PBIT
Power-up Built In Test
Reduces flight control exposition to latent faults ensuring that the system remains operable
PBIT covers what two systems?
Electrical and hydraulic
Last for 50hrs
Electrical PBIT
Detects out of tolerance conditions, and failures in FCMs, P-ACEs and SF-ACEs
Performed once AC power established, takes 3 mins
Hydraulic PBIT
Functional test of flight control actuators
Only performed when all three HYD systems are pressurized
Takes 1 min to complete
