-
install the textile-floor covering (Ref. TASK 25-28-41-400-001).
-
install the passenger seats (Ref. TASK 25-21-41-400-001).
(3)
FOR 333DW
-install the partitions 131PW, (Ref. TASK 25-54-12-400-001).
-set the CARGO COMP LT switch 6LU to OFF.
-close the FWD cargo-compartment door (Ref. TASK 52-30-00-860-002).
Subtask 30-73-55-862-050
C. Make sure that the ground service network is energized
(Ref. TASK 24-42-00-862-001).
DETECTION - DESCRIPTION AND OPERATION
_____________________________________
1. General
_______ The ice detection system is composed of two detectors directly installed on the skin of the aircraft. Each detector is a single unit composed of one heated probe and one electronic part inside the skin of the aircraft. The ice detection system operates permanently during all the flight phases in which the aircraft is supplied with electrical power. The purpose of the ice detector is:
-
to detect with certainty outside icing conditions in the whole aircraft operating envelope
-
to transmit the corresponding signals to the Electronic Instrument System (EIS).
-
to enable cutting off of the anti ice system when the latter is no longer necessary.
ICE DETECTION - DESCRIPTION AND OPERATION_________________________________________
1. General_______
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 301-399,
A lighted icing indicator is installed in lieu of one windshield center
panel retainer bolt. It is visible by both pilots. Its illumination is
R controlled by a switch (INT LT/ICE IND & STBY COMPASS) located on the panel
R 25VU.
The indicator body is made of titanium. The end of the indicator is made of
titanium, with openings for lighting.
R **ON A/C 401-499,
R The ice detection system sends warning messages to the crew when icing
R conditions and heavy icing are detected.
R
R It also indicates the end of the icing conditions.
R
R This system is inhibited on ground.
R
R The system has two main functions:
R
R - better detection of icing conditions
R
R - cutting off of the anti ice system when the latter is no longer necessary
R (fuel saving).
R
R A lighted icing indicator is installed in lieu of one windshield center
R panel retainer bolt. It is visible by both pilots. Its illumination is
R controlled by a switch (INT LT/ICE IND & STBY COMPASS) located on the
R panel 25VU.
R The indicator body is made of titanium. The end of the indicator is made
R of titanium, with openings for lighting.
R **ON A/C ALL
2. Component Location__________________
R **ON A/C 401-499,
R
R (Ref. Fig. 001, 002)
R **ON A/C ALL
R (Ref. Fig. 003, 004)
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 301-399,
A lighted icing indicator is installed on the center panel retainer between the two windshield panels to appreciate the icing conditions.
-------------------------------------------------------------------------------FIN FUNCTIONAL DESIGNATION PANEL ZONE ACCESS ATA DOOR REF. -------------------------------------------------------------------------------16DD INDICATOR-LIGHTED, ICING 30-81-00
R **ON A/C 401-499,
R R The two ice detectors are located on the fuselage forward nose. R R A lighted icing indicator is installed on the center panel retainer between R the two windshield panels to appreciate the icing conditions.
R -------------------------------------------------------------------------------R FIN FUNCTIONAL DESIGNATION PANEL ZONE ACCESS ATA R DOOR REF. R -------------------------------------------------------------------------------R 2DD1 DET-ICE, L 121 30-81-00 R 2DD2 DET-ICE, R 121 30-81-00 R 16DD INDICATOR-LIGHTED, ICING 30-81-00
R **ON A/C ALL
3. System Description
__________________
R Ice Detector - Component Location
R Figure 001
R 1EFF : 401-499, 1 30-81-00 Page 3
1 1 Aug 01/05
1 1
1CES 1
R ANTI ICE Section on the Panel 25VU - Compoment Location R Figure 002
R 1EFF : 401-499, 1 30-81-00Page 4 1 1 Aug 01/05 1 1 1CES 1
