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R  wings (wing tips). 
R  The SEVERITY signal is reset and its processing is inhibited as long 
R  as the ice detectors receive an input indicating that the wing anti 
R  ice is supplied from the aircraft. 
R 
R  (3) FAULT signal 
R 
R  The ice detector has an internal monitoring to get an appropriate 
R  failure rate. A FAULT signal is sent when a fault is detected. In 
R  this case, the ICE and SEVERITY signals are inhibited. 
R

 

R  F. Lighted Icing Indicator 
R 
R  A lighted icing indicator is installed in lieu of one winshield center 
R  panel retainer bolt. It is visible by both pilots. It provides a visual 
R  indication when icing conditions are encountered. 
R 
R  Its illumination is controlled by a switch INT LT/ICE IND & STBY COMPASS 
R  (2LF) for night visibility. 
R  **ON A/C ALL
 7. Operation/Control and Indicating________________________________ 
R  **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 301-399, 
R  (Ref. Fig. 004) 
R  **ON A/C 401-499, 
R  (Ref. Fig. 004, 008, 011) 
R 
R  A. Operation (monitoring) 
R 
R  When icing conditions are detected a discrete signal is generated by the 
R  ice detector and transmitted to the cockpit, at the following location: 
R 
R  - a message is displayed on the upper ECAM display unit 
R 
R  - MASTER CAUT light comes on. 
R 
R  Then the single chime is activated. 
R  (1) The FAULT signals are sent to the SDAC to provide: 
R 
R  (a) the crew with a caution message (class 1 fault) when both ice 
R  detectors are failed 
R 
R  (b) the maintenance crew with a class 2 fault message indicating that 
R  one ice detector has failed 
R

 

R  Ice Detection System - Indicating 
R  Figure 011 (SHEET 1)
 1EFF :  401-499,  1  30-81-00 Page 22 
1  1  Aug 01/05
 1  1
 1CES  1

 

R  Ice Detection System - Indicating 
R  Figure 011 (SHEET 2)
 1EFF :  401-499,  1  30-81-00 Page 23 
1  1  Aug 01/05
 1  1
 1CES  1

 

R  Ice Detection System - Indicating 
R  Figure 011 (SHEET 3)
 1EFF :  401-499,  1  30-81-00 Page 24 
1  1  Aug 01/05
 1  1
 1CES  1

 

R  (c) illumination of the MASTER CAUT light and activation of the 
R  single chime. 
R  (2) The FAULT signals are also sent to the CFDIU. 
R  (3) In addition to this permanent monitoring, the ice detectors perform a 
R  test initiated either by power up or by the CFDIU (test input). 
R 
R  For the test initiated by the CFDIU, each of the following signals is 
R  activated for two seconds: 
R 
R  - ICE, 
R 
R  - SEVERITY, 
R 
R  - or FAULT. 
R 
R  If a fault is detected, the FAULT signal remains activated. 
R  B. Indicating 
R 
R  The ice detection system is inhibited on the ground in weight-on-wheels 
R  configuration (in relation with the LGCIU) because the ice detectors need 
R  a minimum relative airspeed, and below 1500 ft, which corresponds to FWC 
R  level 2 alerts inhibition phases. 
R  All the above inhibitions originate from the FWC. 
R  The ICE and SEVERITY signals used for the warning messages can be 
R  provided by one ice detector or/and the other. 
R 
R  When respectively icing conditions or heavy icing are detected, following 
R  warning messages are displayed in amber at the bottom part of the upper 
R  ECAM display unit (level 2): 
R 
R  - ICE DETECTED, 
R 
R  - SEVERE ICE DETECTED. 
R  C. Control 
R  (1) When the engine 1(2) anti ice system is not activated, the following 
R  messages are displayed until the corresponding actions are performed: 
　
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