Indicating and Recording Systems Flashcards
INDICATIONS ON E/WD
PACKS/NAI/WAI
PACKS / NAI / WAI displayed on the EWD
PACKS - indicated when take off thrust is set or take-off config test is conducted and the PACKS are selected ON
NAI/WAI - displayed when selected ON
INDICATIONS ON E/WD
T.O SPEEDS NOT INSERTED
T.O V1/VR/V2 DISAGREE
indicated in amber when take off power is set or take-off config test is conducted and speeds are not inserted or do not agree.
G LOAD
The screen displays one of the following items:
‐ Load factor (G LOAD) in amber, when the value is above 1.4 g or below 0.7 g for more
than 2 s.
The G LOAD amber indication remains displayed 5 s after the excessive load occurrence. The display of the load factor is inhibited during flight phases 1, 2, 3, 9 and 10.
‐ “CHECK CAPT (F/O) PFD”, “CHECK CAPT (F/O) ND” or “CHECK SD” all in amber.
DECEL indicated on speed scale
When the autobrake is active, the aircraft decelerates as selected via the AUTO BRK mode selector.
The DECEL message is displayed when the aircraft deceleration is at least 80 % of the selected
deceleration. When the aircraft deceleration is less than 70 % of the selected deceleration, it
disappears.
The BSCU provides the DECEL information.
Linear Deviation (green filled circle) and Latch Symbol (magenta square).
The Linear Deviation symbol appears next to the altitude that corresponds to the theoretical
vertical profile computed by the FMS.
That Linear Deviation appears from the top of descent
down to the MAP altitude. The flight crew read the linear deviation directly from the altitude
scale. The range is ±540 ft.
The Latch symbol appears when the aircraft is near to the vertical profile and FMS provide
priority to the vertical profile: the aircraft is “Latched on the profile”.
Depending on the vertical profile computed by the FMS, the Latch symbol can appear from ±540 ft or less.
When the vertical deviation value exceeds ±540 ft, all the following apply :
‐ The symbol stays at the range limit, but changes to a filled half circle
‐ The value is indicated on the left of the symbol in hundreds of feet
‐ If the aircraft is Latched on the profile, the Latch symbol is displayed
‐ The MCDU PROG page displays the exact value.
F-LOC or LOC Deviation scale and Index
Deviation scales appear as soon as the flight crew pushes an LS pb on the EFIS control panel.
Deviation indexes (double diamond) appear, when the deviations are valid, if deviation scales are displayed.
When a deviation index is out of the displayed range, only half a symbol appears at the
end of the scale.
LOC only approach
When a LOC only approach is selected:
‐ ″LOC″ and ″F-G/S″ (magenta) are displayed above the deviation scales
‐ The LOC deviation index is a single diamond.
Selected Landing Systems information (magenta)
The following information appears on the PFD, when the crew has selected a Non Precision
approach using FLS and pushed the LS p/b
‐ For VOR, VOR/DME, NDB, NDB/DME on RNAV approach:
‐ The FLS anchor point ident:
‐ RWYXXX if anchor point is on the runway
‐ EPXXX if anchor point is not on the runway
‐ The FLS beam slope
‐ The distance to anchor point.
‐ For LOC only or ILS G/S OUT approach:
‐ ILS LOC identification
‐ LOC frequency
‐ DME Distance.
FLS BEAM
The FLS beam of the Non-Precision Approaches (NPA) is indicated with a magenta dotted line.
This FLS beam appears when the flight crew has performed all of the following:
‐ Selected an NPA, in the active flight plan
‐ Pressed the LS p/b on the EFIS CP
‐ Selected an ND range that is less than or equal to:
• 80 NM in ARC, or
• 160 NM in ROSE-NAV mode.
If the anchor point of the FLS beam is not defined at the runway threshold, the anchor point ident
(EPXXX) is displayed.
ND DISPLAY WITH FCU 1+2 FAULT
ARC mode with 20nm displayed.
BACKUP SPEED/ALTITUDE SCALE
BUSS
The Back-Up Speed Scale (BUSS) enables to fly the aircraft when airspeed indications are
unreliable.
When the BUSS is activated:
‐ The BUSS replaces the normal speed
‐ The GPS altitude replaces the barometric altitude scale.
The use of the BUSS is reversible.
The reversible BUSS is activated and deactivated with two BKUP SPD/ALT p/b available on the
main instrument panel:
‐ One on the left of the Captain PFD
‐ One on the right of the F/O PFD.
Each BKUP SPD/ALT pb independently commands the display of the BUSS on its associated
side.
The BUSS information is based on the angle of attack (AOA), and depends on the slat/flap
configuration.
