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* Inconsistency between radio altitude and pressure altitude.
* Reduction in aerodynamic noise with increasing speed, or increase in aerodynamic noise with decreasing speed.
* Impossibility of extending the landing gear by the normal landing gear control.
To determine the correct ADR, refer to the :
— UNRELIABLE SPEED INDICATION procedure to fly the target pitch and thrust setting (Refer to the QRH 2.15), or
— SEVERE TURBULENCE procedure, if in cruise, to set a thrust and deduce the correct speed indication (Refer to the QRH 5.01).
— FAULTY ADR   OFFA319/A320/A321
0 ccanTri
ABNORMAL PROCEDURE
REV 35
2.15

SEQ 001

Unreliable airspeed indication may be caused by a radome destruction or frozen pitots.
CAUTION  
If the failure is due to radome destruction, the drag will increase and therefore N1 must be increased by 5 %. Fuel flow will increase by about 27 %.IMMEDIATE ACTIONS I
— AP/FD   OFF
— A/THR   OFF
— FLAPS   MAINTAIN CURRENT CONFIG
— SPEEDBRAKES   CHECK RETRACTED
NOTE : If failure is detected while in CONF FULL and go-around is initiated, select CONF 3.
— L/G   UP WHEN AIRBORNE
IMMEDIATE PITCH ATTITUDE AND THRUST GUIDANCE
* With slats extended :
— THRUST LEVER   MCT
— PITCH ATTITUDE   12.5°
* In clean configuration :
— THRUST LEVER   CLB
— PITCH ATTITUDE below FL 100   10°
— PITCH ATTITUDE above FL 100   5°
Respect the Stall warning, if in alternate law.
Ground speed variations can provide valuable short-term information at low altitude.
The FPV is unreliable, if the altitude information is affected. In other cases, it is a valuable aid in establishing a safe flight path.
WHEN FLIGHT PATH IS STABILIZED I
— PROBE WINDOW HEAT   ON
— ATTITUDE/THRUST   ADJUST
Adjust attitude and thrust, according to the table below.

A319/A320/A321
oniatTri
ABNORMAL PROCEDURE
REV 35
2.16

SEQ 030

FLIGHT PHASE
WEIGHT
(1000 kg)
FLT LEVEL
PITCH ATT
N1

below 48 48 to 60 60 to 72 above 72

21° 17° 15° 13°
TO or FLX
CL
TAKEOFF I

 

 

 

 

I ACCELERATION I F

 

 

 

 

and CONF CHANGE S
below 48
48 to
60 to 72
above 72

16° 12° 10° 10°
CL
CLIMB I 250 kt
below 45
above 45
0 to 50
15°
11°
CL

 

 

250 kt
below 45
above 45
50 to 100
13°
10 °

Climb profile : 250 kt
below 45
above 45
100 to 150
 1 90° °

. 250 kt below FL 200
. 275 kt from FL 200 to FL 320 250 kt
M 0.76 above FL 320
.
below 45
above 45
150 to 200
9°
7.5°

275 kt

200 to 250
250 to 320
5°
4°

.76

above 320
3.5°

below 55
from 55 to 75
above 75
0 to 200
1.5°
3°
4.5°

I CRUISE I 250 kt

 

 

 

 

275 kt
below 55
from 55 to 75
above 75
200 to 320
1°
2°
3°

. 76
below 55
from 55 to 75
above 75
above 320
1.5°
2.5°
3°

* In cruise, initially set the pitch attitude and adjust Ni to maintain approximate level flight with the pitch attitude held constant. When time permits, set an accurate Ni from QRH 5.01 "SEVERE TURBULENCE" and adjust attitude to maintain level flight.A319/A320/A321
0 ccanTri
ABNORMAL PROCEDURE
REV 35
2.15

SEQ 001

Unreliable airspeed indication may be caused by a radome destruction or frozen pitots.
CAUTION  
If the failure is due to radome destruction, the drag will increase and therefore N1 must be increased by 5 %. Fuel flow will increase by about 27 %.IMMEDIATE ACTIONS I
— AP/FD   OFF
— A/THR   OFF
— FLAPS   MAINTAIN CURRENT CONFIG
— SPEEDBRAKES   CHECK RETRACTED
NOTE : If failure is detected while in CONF FULL and go-around is initiated, select CONF 3.
— L/G   UP WHEN AIRBORNE
IMMEDIATE PITCH ATTITUDE AND THRUST GUIDANCE
* With slats extended :
— THRUST LEVER   MCT
— PITCH ATTITUDE   12.5°
　
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