Ice & Rain Protection¶
Ice & Rain Protection: 1 DESCRIPTION¶
Ice & Rain Protection: 1.1 Description¶
The ice and rain protection systems permit aircraft operation in various environmental conditions, in particular, in icing situations. An ice detector, connected to the FWS, monitors ice accretion. In addition, an icing evidence probe is installed to indicate visually an ice accretion. In parallel, an Aircraft Performance Monitoring (APM) system triggers some alerts when the performances are degraded due to ice accretion on the airframe. Aircraft ice protection is provided by: - A pneumatic system operating on areas of the airframe: o Outer, center, and inner wing leading edges o Horizontal tailplane leading edges o Engine air intakes and gas paths. - Electrical heating of: o Propeller blades o Windshields o Probes o Flight control horns. For the pneumatic system, the engines supply bleed air through the LH and RH deice valves (also called Pressure Regulator and Shutoff Valves, PRSOV) regardless of the engine bleed valves position. For electrical heating, the power is supplied primarily by AC wild current. Windshield wipers enable rain removal from the front windshields. Note Refer to IN FLIGHT ICING CONDITIONS for icing conditions definitions.
Ice & Rain Protection: 2 SCHEMATICS¶
Ice & Rain Protection: 2.1 General¶
ICING EVIDENCE PROBE ELECTRICAL HEATING WINDSHIELDS PROBES PROPELLERS HORNS ICE DETECTOR PNEUMATIC SYSTEM GAS PATH ENGINE AIR INTAKES HORIZONTAL TAILPLANE LEADING EDGE OUTER AND CENTER WING AND INNER LEADING EDGE TAT PROBES
Ice & Rain Protection: 1 DESCRIPTION¶
Ice & Rain Protection: 1.1 General¶
An Anti-ice Advisory System (AAS) is installed. The AAS system includes: - An ice detector - An Icing Evidence Probe (IEP) - ICING AOA (green) light on central panel - ICING (amber) label on FMA - Some labels on memo panel display. This system is designed to alert the flight crew on the correct procedures to be applied when flying in icing conditions (Refer to Flight Procedures In Icing Conditions): - IEP (Icing Evidence Probe) and Ice Detector are advisory means of ice accretion detection, - ICING AOA light indicates that stall warning and stick shaker use icing condition thresholds, - IEP is used to visually verify that aircraft is clear of ice in flight.
Ice & Rain Protection: 1.2 Ice Detector¶
The ice detector, under the left wing, alerts the flight crew as soon as and as long as ice accretion is sensed by the probe. When the ice detector detects ice accretion: - Alert is generated by the amber ICING message on FMA - If FMS is in normal condition (ICING AOA label off), FMS automatically switches from NORMAL conditions speeds to ICING conditions speeds (for example, with Flaps 0, the Vmin OPS increases to ICING bug). The system is self tested constantly, and any failure generates a FAULT light with single chime. Detection of ice accretion and associated alert are performed under following cycle:
ICE ACCRETION ON DETECTION PROBE 0.5 mm (0.02 in) 7 s 7 s BEGINNING OF ICE ACCRETION ICING LIGHT ILLUMINATION AND BEGINNING OF PROBE HEATING END OF ICE ACCRETION ICING LIGHT EXTINGUISHING 60 s TIME BEGINNING OF A NEW DETECTION CYCLE
CAUTION The ice detector indicates that ice accretion is building up on the aircraft. Therefore, the amber icing light turning off must be regarded as an end of ice accretion and not as an absence of ice on the aircraft. Therefore, a visual check of IEP must be performed to ensure aircraft is cleared of ice after having encountered ice accretion conditions. Ice accretion on the aircraft under certain circumstances may sublimate. If the ice accretion rate is low, the balance accretion / sublimation may tend to be low or NIL. Under those circumstances, the ice detector may not detect ice accretion (sublimation is much faster on the ice detector than on the airframe). Freezing rain is a precipitation composed of large super cooled water droplets which may be transformed into clear ice when impacting the skin of the aircraft in negative temperature condition. However, if the SAT is slightly negative, these large droplets may not freeze immediately when impacting: clear ice builds up behind the leading edge. The ice detector may become inefficient. The ice detector is not designed to detect ice accretion on ground. During taxi, rainy conditions without being in icing conditions can trigger a spurious ice detection: - This spurious ice detection alert may modify the FMS T/O speeds (NL or manually inserted) without crew alerting (T/O DATA can remain confirmed). Note o FMS T/O speeds are not modified when ICING CONDITIONS are ticked on the VCP or speeds manually inserted in accordance with icing conditions takeoff performance. o Spurious ice detection alert may disappear by modifying the airflow dynamics surrounding the ice detector probe (for example, change in wind direction or slight increase of power below FI with parking brake engaged as close as possible to takeoff). o After the last spurious ice detection, the alert remains active for 60 s.
Ice & Rain Protection: 1.3 Icing Evidence Probe¶
(Applies: 1054-1124;1237-1283) The Icing Evidence Probe (IEP) is under the left side cockpit window and visible by both flight crew. It enables the flight crew to visually monitor the beginning of ice accretion, before ice builds up in other parts of aircraft airframe. After ice accretion, the IEP is used to visually verify that aircraft is clear of ice. An integrated light is provided to help ice accretion monitoring at night using the NAV sw light.
(Applies: 1126-1160) The Icing Evidence Probe (IEP) is under the left side cockpit window and visible by both flight crew. It enables to visually detect the beginning of ice accretion, before ice builds up in other parts of aircraft airframe. After ice accretion, the IEP is used to visually verify that aircraft is clear of ice. An integrated light is provided to help ice accretion monitoring at night using the NAV sw light on “ON” position (on “BAT” position, integrated light turns off).
Ice & Rain Protection: 2 CONTROLS¶
Ice & Rain Protection: 2.1 Ice Detector Panel¶
FAULT OFF ICING A O A TEST TEST APM ICE PUSHER STICK 1 2
FAULT OFF
1 ICING AOA pb ICING AOA comes on green as soon as one horns ANTI ICING pushbutton is selected ON to remind the flight crew that the stall alarm threshold is lower in icing conditions. ICING AOA green label is displayed on FMA. ICING AOA pb can only be turned off manually by pressing it, provided that both horns ANTI ICING are selected OFF. In this case, the stall alarm threshold recovers the values defined for flight in normal conditions. ICING AOA is set to OFF only when aircraft is clear of ice.
PFD
ICING ICING AOA 3 2 ICE Test pb The push to test pushbutton is used to check the ice detector correct operation. Press and hold test button for 3 s. - ICING amber label is displayed flashing on FMA (with associated warning) if system works correctly - A-ICING DETECT alert is displayed with associated procedure on EWD. Master caution light and single chime are activated. 3 ICING Indicator on the FMA ICING comes on amber when ice accretion is detected, provided that both horns ANTI ICING and airframe DE ICING are selected ON. ICING flashes amber when ice accretion is detected and horns ANTI ICING and/or airframe DE ICING are not selected ON.
CAUTION When takeoff speeds (V1, VR and V2) are manually set: - An Ice test performed on ground can trigger a reversion of manual takeoff speeds to non-limiting runway takeoff speeds. - When it happens, it is necessary to re-enter and validate takeoff speeds.
Ice & Rain Protection: 2.2 De Icing Indicator¶
MFD
ANTI ICING DE ICING 1 PROP 2 SIDE WINDOWS 1 HORN 2 1 ENG 2 AIRFRAME
ANTI ICING message When an anti-ice system is selected ON and is not failed, a cyan specific message is displayed, corresponding to the involved anti-ice system. If the selected system is failed, an amber message is displayed. DE ICING message When a deicing system is selected ON and is not failed, a cyan specific message is displayed, corresponding to the involved deicing system (AIRFRAME, ENG 1, or ENG 2). For AIRFRAME - AIRFRAME cyan message is displayed steady when the airframe deicing system is selected ON - AIRFRAME message flashes when the airframe deicing system is still selected ON 5 min after last ice accretion detection - AIRFRAME message is displayed steady amber in case of deicing system failure. The flight crew must disregard AIRFRAME blue message flashing on memo panel and keep the DE ICING and ANTI ICING systems ON until leaving the icing conditions.
Ice & Rain Protection: 3 ELECTRICAL SUPPLY¶
Ice & Rain Protection: 3.1 Electrical Supply¶
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) ICE detector NIL ACW BUS 2 (on lateral panel C/B ICE DET PWR SPLY) ICING AOA light DC EMER BUS (on lateral panel C/B DE ICING-AAS/ C/B BOOTS A AND B IND) NIL
Ice & Rain Protection: 4 SYSTEM MONITORING¶
Ice & Rain Protection: 4.1 ICE DETECT FAULT-Alert¶
CONDITION VISUAL AURAL Ice detector failure - MC light flashing amber - A-ICING DETECT amber message on EWD SC
Ice & Rain Protection: 1 DESCRIPTION¶
Ice & Rain Protection: 1.1 General¶
The operating principle is to sequentially inflate the boots in order to remove ice. The deice valves control the delivery pressure to 20.3 psi. 7 distribution valves control air supply to the boots: - Valve (1) to LH engine air intake and separation chamber - Valve (2) to RH engine air intake and separation chamber - Valve (3) to LH outer wing leading edge - Valve (4) to LH center wing leading edge and LH internal wing leading edge - Valve (5) to RH outer wing leading edge - Valve (6) to RH center wing leading edge and RH internal wing leading edge - Valve (7) to horizontal tailplane leading edge. Each of these distribution valves has one input and two outputs A and B, each controlled by the MFC. For more details, Refer to Engine and Wing Protection General Schematics.
Two types of boots are used: - Transversal boots for the leading edges and the gas paths
BOOTS A BOOTS B A B B A - Fig. 1 : Chordwise Boots - - Annular boots for the engine intakes
ENG GAS PATH AIR OUTLET ENGINE AIR INTAKE - Fig. 1 : Annular Boots - When deflated, the boots are held to the structure thanks to a venturi supplied by bleed air.
Note The system is designed to remain operative with one engine inoperative through a common air manifold, except icing protection of the inoperative engine which is lost. CAUTION With this type of boots, there is no need to wait for ice accretion on airframe before selecting it ON. This system MUST be selected ON as soon as and as long as ice accretion develops on airframe. 2 Time Sequence Diagram Normal Mode ENGINES AIR INTAKES AND SEPARATION CHAMBER WINGS HORIZONTAL STABILIZER OUTER BOOTS (1 AND 2) INNER BOOTS INFLATED BOOTS BOOTS A ENG 1 BOOTS B ENG 1 BOOTS A BOOTS A BOOTS A BOOTS A ENG 2 BOOTS B ENG 2 BOOTS B BOOTS B BOOTS B TIME CYCLE 0 to 5 s 5 s to 10 s 10 s to 15 s 15 s to 20 s 20 s to 25 s 25 s to 30 s 30 s to 35 s 35 s to 40 s Beginning of the following sequence at: - FAST MODE (SAT > -20 °C): 60 s - SLOW MODE (SAT < -20 °C): 180 s OVRD Mode ENGINE 1 AIR INTAKES AND SEPARATION CHAMBER WINGS ENGINE 2 AIR INTAKES AND SEPARATION CHAMBER HORIZONTAL STABILIZER OUTER BOOTS (1 AND 2) INNER BOOTS INFLATED BOOTS BOOTS A ENG 1 BOOTS B ENG 1 L BOOTS A R BOOTS A L BOOTS A R BOOTS A BOOTS A ENG 2 BOOTS B ENG 2 R BOOTS B L BOOTS B R BOOTS B L BOOTS B BOOTS A BOOTS B TIME CYCLE 0 to 5 s 5 s to 10 s 10 s to 15 s 15 s to 20 s 20 s to 25 s 25 s to 30 s 30 s to 35 s 35 s to 40 s 40 s to 45 s Beginning of the following sequence at 60 s (FAST MODE). Note When DE ICING OVRD mode is selected, boots inflate according to a separate timer and MFC is totally bypassed.
Ice & Rain Protection: 2 CONTROLS¶
Ice & Rain Protection: 2.1 Engine-Wing De Icing Panel¶
DE ICING ENG 2 ENG 1 1 ENG 2 AIR FRAME SLOW F A S T N O R M MODE SEL FAULT OVRD AFR AIR BLEED FAULT MAN MODE SEL AUTO FAULT ON FAULT ON FAULT ON FAULT OFF 1 2 3 4 5 6
1 AFR AIR BLEED pb Controls both deice and isolation valves. Pb pressed in Normal operation Both DEICE and ISOLATION VALVES are open. OFF (Pb released) OFF light comes on white. Both DEICE and isolation valves are closed. However, engine deicing can be used (engine DE ICING selected ON will open deice valve). But airframe deicing is not available. FAULT The light comes on amber and the FWS is activated when: - Air pressure downstream of the deice valves stays below 14 psi - Air temperature upstream of the deice valves exceeds 230 °C. A-ICING BLEED alert is displayed with associated procedure on EWD. Master Caution light and Single Chime are activated. The alert is inhibited when pb is released.
2 AIRFRAME pb Controls the outputs A and B of both wings and stabilizers distribution valves. ON (Pb pressed in) Signal is sent to the MFC in order to initiate a deicing cycle depending on DE ICING SAT < -20°C pb. ON light comes on blue. Pb released Normal operation. Associated boots stay deflated. FAULT The light comes on amber and the FWS is activated when inflation sequencing of airframe boots A and B is not correct. - Associated distribution valve output has been controlled open but no downstream pressure has been detected, or - Associated distribution valve output has been controlled closed but a downstream pressure is detected. A-ICING FRAME alert is displayed with associated procedure on EWD. Master Caution light and Single Chime are activated. “AIRFRAME” amber label is displayed on the memo panel display of MFD. When AIRFRAME deicing is ON, “AIRFRAME” cyan label is displayed on the memo panel display:
MFD ANTI ICING DE ICING AIRFRAME
3 ENGINE pbs Control deice valves, as well as the outputs A and B of respective engine distribution valves. ON (Pb pressed in) Deice valve is controlled open even if AFR AIR BLEED pb is not selected ON, and a signal is sent to the MFC in order to initiate a deicing cycle depending on DE ICING SAT < -20°C pb. ON light comes on blue. ENG cyan label is displayed on the memo panel display of MFD. Pb released Associated boots stay deflated. Also controls associated deice valve in closed position, after AFR AIR BLEED pb FAULT and ENG FAULT. FAULT The light comes on amber and the FWS is activated when: - Associated distribution valve output has been controlled open but no downstream pressure has been detected, or - Associated distribution valve output has been controlled closed but a downstream pressure is detected - AFR AIR BLEED pb selected OFF and air temperature upstream of the deice valve exceeds 230 °C - Inflation sequencing of engine boots A or B is not correct. A-ICING ENG alert is displayed with associated procedure on EWD. Master Caution light and Single Chime are activated. ENG amber label is displayed on the temporary selections window of MFD. When at least one ENGINE deicing is ON, “ENG” cyan label is displayed on the memo panel display
MFD ANTI ICING DE ICING 1 ENG 2
4 DE ICING SAT < -20 °C pb To be used when SAT < -20 °C Controls the selection of wings/engines boots inflation cycles when MAN is selected on MODE SEL AUTO pb . FAST (Pb released) Timing cycle = 60 s. SLOW (Pb pressed in) timing cycle = 180 s - SLOW light comes on blue. 5 DE ICING MODE SEL guarded pushbutton Controls the emergency deicing operation. The control panel enables control of all double valves (ENG and AIRFRAME). NORM (Pb released) Normal operation. OVRD (Pb pressed in) The emergency deicing activation is selected (timing cycle = 60 s), the light comes on blue and all deicing lights turn off. This position is used when the associated FAULT light comes on. FAULT The light comes on amber when both MFC modules associated with air intake boots control fail. A-ICING SEL alert is displayed with associated procedure on EWD. Master Caution light and Single Chime are activated.
6 DE-ANTI ICING MODE SEL AUTO pb Pb released Normal operation (automatic operating mode). The DE ICING MODE SEL pb is inoperative. The cycle selection is provided by ADC data computation through CAC and MFC. FAULT Comes on amber and the FWS is activated when MFC (1B or 2B) and/or ADC, or CPM, or IOM failure occurs. The DE ICING MODE SEL pb is inoperative. In this case the FAST mode is automatically activated. MAN The flight crew must select the appropriate timing cycle depending on SAT using ANTI ICING MODE SEL SAT < -10 °C and DE ICING SAT < -20 °C pb. MAN comes on blue.
TEMPERATURE SENSOR ADC 1 RIGHT TEMPERATURE SENSOR ADC 2 MFC 1B FAULT MAN CAC 1 CAC 2 MFC 1A MFC 2A MFC 2B MFC ARINC BUS
Ice & Rain Protection: 2.2 Horns Anti Icing Panel¶
FAULT ON FAULT ON HORNS ELEV L RUD & AIL & R ELEV ANTI ICING 1 ANTI ICING HORNS pushbuttons Controls activation of following units: - RUD & L ELEV: Rudder and left elevator horns anti-ice - AIL & R ELEV: Ailerons and right elevator horns anti-ice. ON (Pb pressed in): Associated anti-ice units are activated. ON light comes on cyan. HORN cyan label is displayed on the memo panel display of MFD. As soon as a HORN is selected ON, ICING AOA light is displayed on the Ice Detector panel. (Refer to CONTROLS) OFF (Pb released): Associated anti-ice units are deactivated. FAULT The light comes on amber and the FWS is activated when electrical power is lost on one of the associated units. HORN amber label is displayed on the memo panel display of MFD. Note As soon as at least one of the ANTI ICING HORNS pb is selected ON, stall alert threshold is reduced (Refer to DSC.31.12.3.2.3 Stall Alert). Horns heating are inhibited on ground.
1) Memo Display Panel
MFD
ANTI ICING DE ICING 1 HORN 2
Ice & Rain Protection: 3 ELECTRICAL SUPPLY¶
Ice & Rain Protection: 3.1 Electrical Supply¶
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) Deice valves DC BUS 2 (on lateral panel C/B SO and REG VALVE 1 and 2) NIL Isolation valves DC ESS BUS (on lateral panel C/B ISOL VALVE 1 and 2) NIL Distribution valves (Boots A + ENG 1) DC EMER BUS (on lateral panel C/B ENG 1 and C/B AFR-BOOTS A SPLY) NIL Distribution valves (Boots B + ENG 2) DC BUS 2 (on lateral panel C/B ENG 2 and C/B AFR-BOOTS B NORM SPLY) and DC EMER BUS (BACK UP) (on lateral panel C/B ENG 2 and C/B AFR-BOOTS B EMER SPLY) NIL Controls and alerts DC EMER (on lateral panel C/B CTL and C/B CAUTION) NIL Left elevator and rudder horns anti-ice NIL 115 VAC wild BUS 1 (on lateral panel C/B L ELEV RUD) Left elevator and rudder horns anti-ice control DC EMER BUS (on lateral panel C/B L ELEV and C/B RUD) NIL Right elevator and ailerons horns anti-ice NIL 115 VAC wild BUS 2 (on lateral panel C/B R ELEV R AIL L AIL) Right elevator and ailerons horns anti-ice control DC EMER BUS (on lateral panel C/B R ELEV and C/B AIL) NIL
Ice & Rain Protection: 4 SYSTEM MONITORING¶
Ice & Rain Protection: 4.1 ANTI ICING HORNS 1(2) FAULT-Alert¶
CONDITION VISUAL AURAL Power loss on a horn anti ice unit. - MC light flashing amber - A-ICING HORNS 1(2) amber message on EWD - HORN 1(2) amber message on Memo Panel - Associated FAULT amber light on overhead panel SC
Ice & Rain Protection: 4.2 AIRFRAME AIR BLEED FAULT (DE ICING)-Alert¶
CONDITION VISUAL AURAL Low pressure in deicing common air manifold (P<14 psi) - OR - Overtemperature (T>230 °C) upstream pressure regulating valve - MC light flashing amber - A-ICING BLEED amber message on EWD - AFR AIR BLEED FAULT amber light on overhead panel SC
Ice & Rain Protection: 4.3 DE ICING AIRFRAME FAULT-Alert¶
CONDITION VISUAL AURAL Distribution valve output controlled open but no downstream pressure detected - OR - Distribution valve output controlled closed but downstream pressure detected - MC light flashing amber - A-ICING FRAME amber message on EWD - AIRFRAME amber message on Memo Panel - AIRFRAME FAULT amber light on overhead panel SC
Ice & Rain Protection: 4.4 DE ICING MODE SEL FAULT-Alert¶
CONDITION VISUAL AURAL Incorrect deicing cycles schedule - MC light flashing amber - A-ICING SEL amber message on EWD - AIRFRAME amber message on Memo Panel - ENG 1 amber message on Memo Panel - ENG 2 amber message on Memo Panel - DE ICING MODE SEL FAULT amber light on overhead panel SC
Ice & Rain Protection: 4.5 DE-ANTI ICING MODE SEL AUTO FAULT-Alert¶
CONDITION VISUAL AURAL MFC 1B or 2B and/or ADC failure - OR - Outputs not in accordance - MC light flashing amber - A-ICING AUTO amber message on EWD - DE-ANTI ICING MODE SEL AUTO FAULT amber light on overhead panel SC
Ice & Rain Protection: 4.6 DE ICING ENG 1(2) FAULT-Alert¶
DE ICING ENG 1(2) FAULT-Alert CONDITION VISUAL AURAL Distribution valve output controlled open but no downstream pressure detected - OR - Distribution valve output controlled closed but downstream pressure detected - OR - AFR AIRBLEED pb selected OFF and air temperature upstream of the de icing valve exceeds 230 °C - OR - Inflation sequencing of engine boots A or B is not correct - MC light flashing amber - A-ICING ENG 1(2) amber message on EWD - ENG 1(2) amber message on Memo Panel - Associated FAULT amber light on overhead panel SC
Ice & Rain Protection: 5 SCHEMATICS¶
Ice & Rain Protection: 5.1 General¶
FUNCTIONAL ABSTRACTION - pneumatic engine/wing de-icing
ENGINE 1 BLEED -> isolation/regulation valves -> ENG 1 intake boots
|
+--> LH outboard-wing boot groups A/B
ENGINE 2 BLEED -> isolation/regulation valves -> ENG 2 intake boots
|
+--> RH outboard-wing boot groups A/B
[DE-ICING CONTROL COMPUTER]
| timing / sequencing |
+--> engine boot valves
+--> wing boot distributors
+--> horizontal-stabilizer boot groups
Pressure/position feedback returns from the distribution paths to monitoring.
Ice & Rain Protection: 5.2 Engine Nacelle Protection System¶
LOWER AIR INTAKE BOOTS AIR INTAKE BOOTS UPPER BOOTS RADIATOR UPPER DUCT BOOTS
Ice & Rain Protection: 1 DESCRIPTION¶
Ice & Rain Protection: 1.1 General¶
Propeller anti-ice is performed by resistors installed near the surface of the inboard sections of the blade leading edges. On each propeller, the heating elements are electrically connected in three blades (every other blade). The system is supplied with 115 V ACW. Two modes are available: - AUTO: MODE SEL AUTO pb released Automatic operating mode. - MAN: MODE SEL AUTO pb pressed in MODE SEL is operative and available depending on the temperature. When selected on, the propeller anti-ice system starts to heat the blades only when NP is sensed above 63 %. Two modes are available: o NORMAL: To be used when SAT is between -10 °C (14 °F) and 0 °C (32 °F). o ON: To be used when SAT is between -30 °C (-22 °F) and -10 °C (14 °F). Note Below -30 °C (-22 °F) icing problems should not be present (no supercooled water). 2 Time Sequence Diagram Normal Operation (pb Out) Anti-ice Propeller Blades Supplied Propeller 1 Blades 1-3-5 Propeller 1 Blades 2-4-6 Propeller 2 Blades 1-3-5 Propeller 2 Blades 2-4-6 Propeller 1 Blades 1-3-5 Time Cycle 0 to 10 s 10 s to 20 s 20 s to 30 s 30 s to 40 s 40 s to 50 s 50 s...
On (pb In) Anti-ice Propeller Blades Supplied Propeller 1 Blades 1-3-5 Propeller 1 Blades 2-4-6 Propeller 2 Blades 1-3-5 Propeller 2 Blades 2-4-6 Propeller 1 Blades 1-3-5 Time Cycle 0 to 20 s 20 s to 40 s 40 s to 60 s 60 s to 80 s 80 s...
Ice & Rain Protection: 2 CONTROLS¶
Ice & Rain Protection: 2.1 Propeller Anti Icing Panel¶
1 1 2 FAULT ON FAULT ON MODE SEL 1 PROP 2 ON SAT< -10° C HORNS ELEV L RUD & AIL & R ELEV ANTI ICING 24VU SIDE WINDOWS FAULT MAN MODE SEL AUTO FAULT ON FAULT ON FAULT ON 3
1 PROP pb Controls the respective propeller heating elements. ON (Pb pressed in) The heating units are supplied. The ON light comes on cyan. PROP cyan label is displayed on the memo panel display of MFD. Pb released The heating elements are not supplied. FAULT The light comes on amber to indicate that at least one blade is not electrically supplied. A-ICING PROP alert is displayed with associated procedure on EWD. Master Caution light and Single Chime are activated. 2 MODE SEL pb (to be used when SAT < –10°C) Controls the duration of propeller anti-ice cycles when MAN is selected on MODE SEL AUTO pb . Pb released LOW POWER cycle is selected. ON (Pb pressed in) HIGH POWER cycle is selected. The ON light comes on cyan. Note - Low Power (pb OUT) for temperature greater than -10 °C (14 °F) - High Power (pb IN) temperature between -10 °C (14 °F) and -30 °C (-22 °F) - Below -30 °C (-22 °F) icing problems should not be present (no supercooled water). 3 MODE SEL AUTO pb Pb released Normal operation (automatic operating mode). The ANTI ICING MODE SEL pb The cycle selection is provided ADC 1, MFC 1B, ADC 2, and MFC 2B. FAULT Comes on amber and the FWS is activated when MFC (1B or 2B) and/or ADC failure occurs. The ANTI ICING MODE SEL pb is inoperative. In this case the HIGH POWER CYCLE is automatically activated. MAN (Pb pressed in) The ANTI ICING MODE SEL pb is operative and enables the flight crew to select the appropriate timing cycle depending on SAT. MAN comes on white.
Memo Panel Display
MFD
ANTI ICING DE ICING 1 PROP 2
Ice & Rain Protection: 3 ELECTRICAL SUPPLY¶
Ice & Rain Protection: 3.1 Electrical Supply¶
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) Propeller 1 ANTI ICING PWR NIL ACW BUS 1 (on lateral panel C/B PROP 1 ANTI ICING PWR SPLY) Propeller 2 ANTI ICING PWR NIL ACW BUS 2 (on lateral panel C/B PROP 2 ANTI ICING PWR SPLY) PROP ANTI ICING CTL and IND DC EMER BUS (on lateral panel C/B PROP CTL and C/B IND) NIL Note Propeller anti icing is inhibited when NP is below 63%.
Ice & Rain Protection: 4 SYSTEM MONITORING¶
Ice & Rain Protection: 4.1 ANTI ICING PROP 1(2) FAULT-Alert¶
CONDITION VISUAL AURAL One or more blade anti icing inoperative - MC light flashing amber - A-ICING PROP 1(2) amber message on EWD - PROP 1(2) amber message on Memo Panel - Associated FAULT amber light on overhead panel SC
Ice & Rain Protection: 5 LATERAL MAINTENANCE PANEL¶
Ice & Rain Protection: 5.1 Propeller Anti-Icing Test Pushbutton¶
CAUTION PROP A /ICING PUSH ONLY PROP RUNNING PTT This guarded pb is used to check the propeller anti-ice system functioning. It must only be operated on ground, with propellers above 63 % NP. Test procedure: - Aircraft on ground, propellers > 63 %NP - Mode select (overhead panel): NORM - Push test button - The system performs a short anti-ice cycle.
Ice & Rain Protection: 1 DESCRIPTION¶
Ice & Rain Protection: 1.1 General¶
The cockpit windows are electrically heated : - The front windshields for ice protection and defogging - The side windows for defogging only. The front windshields are protected against ice formation by an electrically heated transparent film incorporated between two plies of glass. It is supplied with 200 V ACW, and temperature is controlled by an electronic controller which keeps the outer windshield temperature over 2 °C (35 °F). The inner surface remains above 21 °C (70 °F) to prevent mist formation. The side windows are protected by an electrically heated system consisting of small wires embedded between two plies of glass. It is supplied with 28 V DC and keeps the inner temperature over 21 °C (70 °F).
Ice & Rain Protection: 2 CONTROLS¶
Ice & Rain Protection: 2.1 Controls¶
R L WINDSHIELD HTG 24VU ANTI ICING SIDE WINDOWS FAULT ON FAULT ON ELEV L RUD & AIL & R ELEV HORNS FAULT ON FAULT ON 1 PROP 2 MODE SEL ON SAT< -10° C FAULT MODE SEL AUTO 1 1 2 FAULT ON FAULT OFF FAULT OFF 1 WINDSHIELD HTG L or R pb Controls activation of window heat systems. Pb pressed in Power is supplied to the associated window heat system. OFF (Pb released) Window heat system is deactivated. The OFF light comes on white. FAULT The light comes on amber and the FWS is activated when there is a power loss. The light also comes on during MFC test. 2 SIDE WINDOWS pb Controls activation of side window heat systems ON (pb pressed in) Power is supplied to both side windows heat systems. ON light comes on blue SIDE WINDOW cyan label is displayed on the temporary selections window of MFD. Pb released Side windows heat systems are deactivated. FAULT The light comes on amber and the FWS is activated when there is a power loss. SIDE WINDOW amber label is displayed on the temporary selections window of MFD.
Memo Panel Display
MFD
ANTI ICING DE ICING SIDE WINDOWS
Ice & Rain Protection: 3 ELECTRICAL SUPPLY¶
Ice & Rain Protection: 3.1 Electrical Supply¶
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) LH Front windshield supply NIL ACW BUS 1 (on lateral panel C/B L FRONT WINDOW HTG) Front windshield control NIL ACW BUS 1 (on lateral panel C/B FRONT CTL and C/B CAUTION) Front windshield alert DC BUS 2 (on lateral panel C/B WDSHLD IND L ) NIL Side window supply and control DC BUS 1 (on lateral panel C/B SIDE WDO L CTL ) NIL RH Front windshield supply NIL ACW BUS 2 (on lateral panel C/B R FRONT WINDOW HTG) Front windshield control NIL ACW BUS 2 (on lateral panel C/B FRONT CTL and C/B CAUTION) Front windshield alert DC BUS 1 (on lateral panel C/B WDSHLD IND R ) NIL Side window supply and control DC BUS 2 (on lateral panel C/B SIDE WDO R CTL ) NIL Side windows alert DC ESS BUS (on lateral panel side window C/B CAUTION ) NIL
Ice & Rain Protection: 4 SYSTEM MONITORING¶
Ice & Rain Protection: 4.1 SIDE WINDOW HTG FAULT-Alert¶
CONDITION VISUAL AURAL Loss of side window heating - MC light flashing amber - A-ICING WINDOWS amber message on EWD - SIDE WINDOWS amber message on Memo Panel - SIDE WINDOWS FAULT amber light on overhead panel SC
Ice & Rain Protection: 4.2 WINDSHIELD HTG FAULT-Alert¶
CONDITION VISUAL AURAL Loss of windshield heating - MC light flashing amber - A-ICING L(R) WSHLD amber message on EWD - Associated WINDSHIELD HTG FAULT amber light on overhead panel SC
Ice & Rain Protection: 5 LATERAL MAINTENANCE PANEL¶
Ice & Rain Protection: 5.1 Windshield Heat Test Pushbutton¶
WSHLD HTG
T E S T Test pb Is used to check the windshield heat controller functioning. Test procedure: - Press and hold test button for 3 s - The BITE executes a programmed check of the controllers, ending with de- energization of both overheat power relays - MFC magnetic indicator comes on on the RH maintenance panel when a failure has been detected during the windshield heating cycle.
Ice & Rain Protection: 1 DESCRIPTION¶
Ice & Rain Protection: 1.1 General¶
To prevent icing on air data sensors, electrical heating is provided for: - CAPT, F/O, STBY pitot tubes - CAPT, F/O, STBY left and right static ports - CAPT, F/O alpha (angle of attack) probes - CAPT, F/O TAT probes. The probes are heated both on ground and in flight, except TAT sensors heating which are inhibited on ground.
Ice & Rain Protection: 2 CONTROLS¶
Ice & Rain Protection: 2.1 Probe Heat Panel¶
OFF OFF OFF F/O STBY CAPT PROBES HTG 1 2 3 4 2 1 4 4 1 3 3 PITOT STAT PITOT STAT ALPHA TAT ALPHA TAT PITOT STAT 1 PITOT lights Come on amber and the FWS is activated if the associated pitot is not heated, in flight or on ground. . 2 ALPHA, TAT lights Come on amber and the FWS is activated when the respective probe is not heated. 3 STAT lights Come on amber and the FWS is activated when the respective probe is not heated. In flight, static ports are not monitored by FWS. 4 CAPT STBY F/O pushbuttons Control the activation of probe heating of their respective circuits. Pb pressed in Probe heating is activated. OFF (Pb released) Probe heating is deactivated. OFF light comes on white. Respective PROBE HEAT light comes on amber. CAUTION Even if probes are not heated, the F/O probes light (PITOT, ALPHA, STAT and TAT) remains OFF in case of: - DC BUS 1 OFF, and - DC BUS 2 OFF, and - ACW BUS 1 OFF, and - ACW BUS 2 OFF.
Ice & Rain Protection: 3 ELECTRICAL SUPPLY¶
Ice & Rain Protection: 3.1 Electrical Supply¶
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) CAPT Pitot tubes NIL ACW BUS 1 (on lateral panelC/B PITOT) Alpha probe NIL ACW BUS 1 (on lateral panel C/B ALPHA) Static ports DC BUS 1 (on lateral panel ) NIL Alerts DC ESS BUS (on lateral alert C/B CAUTION ) NIL TAT probe NIL ACW BUS 1 (on lateral panel C/B CPT TAT) F/O Pitot tubes NIL ACW BUS 2 (on lateral panelC/B PITOT) Alpha probe NIL ACW BUS 2 (on lateral panel C/B ALPHA) Static ports DC BUS 2 (on lateral panel ) NIL Alerts DC BUS 2 (on lateral panel C/B CAUTION ) NIL TAT probe NIL ACW BUS 2 (on lateral panel C/B F/O TAT) STBY Pitot tube NIL ACW BUS 1 and 115 VAC STBY BUS (back up) (on lateral panelC/B STBY PITOT NORM SPLY and C/B EMER SPLY)
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) Static ports DC BUS 1 (on lateral panel C/B LEFT, RIGHT ) NIL Alerts DC ESS BUS (on lateral panel C/B CAUTION ) NIL
Ice & Rain Protection: 4 SYSTEM MONITORING¶
Ice & Rain Protection: 4.1 PROBES HTG FAILURE-Alert¶
CONDITION VISUAL AURAL Power loss on a probe anti-ice unit. - MC light flashing amber - A-ICING ALPHA/ALPHAs amber message on EWD - A-ICING PIT CPT(F/O)(SBY) amber message on EWD - A-ICING TAT CPT(F/O) amber message on EWD - Associated ALPHA, TAT or PITOT amber lights on overhead panel SC
Ice & Rain Protection: 1 DESCRIPTION¶
Ice & Rain Protection: 1.1 General¶
Rain removal from front windshields is provided by two wipers: Each wiper is driven by a two speed electric motor. They are controlled by two WIPER selectors on the overhead panel: One for the captain, and one for the F/O. Maximum speed to operate the wipers is 160 kt.
Ice & Rain Protection: 2 CONTROLS¶
Ice & Rain Protection: 2.1 Controls¶
FAST SLOW OFF CAPT WIPER FAST SLOW OFF F/O WIPER WIPER rotary selector Controls the windshield wiper on the associated side. FAST Wiper operates at 130 cycles/min SLOW Wiper operates at 80 cycles/min OFF Wiper operation stops at the end-of-travel (parking) position.
Ice & Rain Protection: 3 ELECTRICAL SUPPLY¶
Ice & Rain Protection: 3.1 Electrical Supply¶
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) Captain wiper DC ESS BUS (on lateral panel C/B CAPT) NIL F/O wiper DC BUS 2 (on lateral panel C/B F/O) NIL
Ice & Rain Protection: 1 DESCRIPTION¶
Ice & Rain Protection: 1.1 General¶
The Aircraft Performance Monitoring (APM) system monitors aircraft in-flight performance in order to enhance flight crew awareness about any degradation of performance and especially in icing conditions. The APM system is hosted by the MPC. The APM system compares the aircraft theoretical drag with the current drag and alerts the flight crew if reduction of aircraft performance occurs. If drag and/or speed decay exceed predefined threshold values, the corresponding messages or alerts (cautions and/or warnings) are triggered. A permanent background monitoring is performed as ice accretion is not the single cause of speed decay or drag increase. Other causes can significantly degrade the aircraft performance: mountain waves / wind gradients, aircraft aerodynamic altered (CDL or aircraft skin altered, excessive flight controls deflections …).
Ice & Rain Protection: 1.2 APM Principle¶
The APM compares the in-flight drag computed with measured parameters available in the FDAU with the aircraft theoretical drag. Parameters are smoothed to avoid noise and errors, therefore alarms may trigger up to 60 s after the performance degradation. The APM also conducts monitoring of the current IAS compared to: - Theoretical cruise IAS with engines running at CRZ power - ICING BUG (VmLB0 ICING) + 10 kts. Depending on drag computation and speed monitoring different messages or alerts (cautions and/or warnings) are provided to the crew. The APM inputs include : - Pressure altitude - SAT - IAS - Engine torque - Propeller rotation speed - Landing gear and flaps sensor inputs - Aircraft weight taken from FMS entry and Fuel Flow. - Longitudinal acceleration (for takeoff weight computation if not set in FMS) - Altitude hold mode
Ice & Rain Protection: 1.3 APM conditions for monitoring and triggering¶
Aircraft performance monitoring starts after landing gear and flap retraction and continues during the flight in clean configuration (flaps 0 and landing gear up) and as long as both engines are operating. The messages or alerts (cautions and/or warnings) can be triggered if SAT is below 10 °C and one or several of the following conditions are met: - ICING AOA illuminated - DE ICING AIRFRAME pb selected ON - Ice accretion detected (at least once during the flight).
Ice & Rain Protection: 1.4 APM Flight phases determination¶
The messages or alerts (cautions and/or warnings) triggering conditions depend on the flight phase. Therefore, the APM must determine the current flight phase: “CRUISE”, “DESCENT”, or “CLIMB”. The different flight phases are: CRUISE: ALT mode engaged or vertical speed below +/-200 ft/min for more than 2 min. CLIMB/DESCENT: Out of cruise conditions.
Ice & Rain Protection: 1.5 APM triggering thresholds¶
Depending on the flight phase, if drag and speed degradation exceed predefined threshold values, messages and/or alerts are triggered. They are organized on three levels of alerting depending on aircraft performance degradation: - CRUISE SPEED LOW message indicates a limited performance degradation (around 10 % of drag increase compared to theoretical drag in the same conditions) with a speed decay at least 10 kt below the expected cruise speed. This message is available in CRUISE phase only. - DEGRADED PERF alert indicates a significant performance degradation (around 22 % or 28 % of drag increase). In climb, the alert is triggered by an increase of drag that generates a severe reduction of rate of climb. In cruise, the alert is triggered by an increase of drag that generates an IAS decrease (15 kt to 20 kt below the expected cruise speed). In descent, the alert is triggered by an increase of drag. - INCREASE SPEED alert is triggered by a severe performance degradation generating an IAS decrease below ICING BUG +10 kt. The alert indicates that the conditions for DEGRADED PERF are met and that the speed is below ICING BUG +10 kt. All messages or alerts (cautions and/or warnings) are triggered after a confirmation time of 60 s. However, they can be immediately triggered based on drag gradients to alert the crew when high rates of drag degradation are calculated.
CRUISE SPEED LOW message and DEGRADED PERF alert turn off when the triggering conditions are no more met. Examples : - In the case of a CRUISE SPEED LOW, considering that the aircraft begins the descent, CRUISE SPEED LOW message will disappear as soon as the flight phase is no more CRUISE, even if the degradation of drag remains above 10 %. - In the case of a DEGRADED PERF triggering in CRUISE, considering that the aircraft begins the descent and accelerates above ICING BUG + 30 kt, the DEGRADED PERF message will remain as long as the degradation of drag remains above 22 %. Triggering thresholds and associated messages summary:
X-Y- 00000-T-FB429-000 - -01-N X 3 50 B +10 DRAG IAS -20 +1 % 0 +22% -15 CRZ -10 +28% INCREASE SPEED CRUISE SPEED LOW Nominal Drag and IAS +10 DRAG +28% DEGRADED Cruise flight phase THEORETICAL Climb or Descent flight phase IAS PERF INCREASE ICING BUG SPEED ICING BUG DEGRADED PERF
Ice & Rain Protection: 2 CONTROLS¶
Ice & Rain Protection: 2.1 APM Indications¶
PFD
CRZ SPD LO amber message This attention getter is generated only in Cruise mode to inform the flight crew that the aircraft speed is 10 kt below the theoretical maximum cruise speed and that there is a small drag increase. No aural alert
-B-01-N 5 HOLD ROLL LO CRZ SPD LO CAT1 AP FD DUAL CHECK NAV SRC PITCH HOLD FD SINGLE CH VOR ALT SEL HLD TCS SPD DGD PERF amber message This caution is generated in the case of a significant performance degradation that could be due to the severe icing conditions. Visual and aural alerts are: - MC light flashing amber - DGD PERF amber message on FMA - DEGRADED PERF amber message on EWD - Single Chime aural alert.
HOLD ROLL LO DGD PERF CAT1 AP FD DUAL CHECK NAV SRC PITCH HOLD FD SINGLE CH VOR ALT SEL HLD TCS SPD INCREASE SPEED flashing amber message This caution is generated in the case of a severe performance degradation and the aircraft speed is below ICING BUG + 10 kt. Visual and aural alerts are: - MC light flashing amber - INCREASE SPEED flashing amber message on FMA - INCREASE SPEED amber message on EWD - Single Chime aural alert.
HOLD ROLL LO SPEED CAT1 AP FD DUAL CHECK NAV SRC PITCH HOLD FD SINGLE CH VOR ALT SEL HLD TCS SPD INCREASE
Ice & Rain Protection: 2.2 APM Control Panel¶
FAULT OFF FAULT OFF ICING A O A TEST TEST APM DET ICE PUSHER STICK 2 1
1 APM TEST pb The APM TEST pb is used to test the APM function. The flight crew must perform this test daily, to determine whether the APM components are operational or not. 2 APM pb The APM pb controls the activation of the APM. If the FAULT light comes on, the APM must be selected OFF. OFF APM function in OFF position (comes on white) FAULT Comes on amber in case of APM FAULT (APM FAULT alert is triggered by FWS). The APM FAULT is inhibited on ground. The APM FAULT will be triggered by the MPC in case of internal failure or invalid aircraft parameters.
Ice & Rain Protection: 3 ELECTRICAL SUPPLY¶
Ice & Rain Protection: 3.1 Electrical Supply¶
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) MPC DC ESS BUS NIL CAC 1 CPM 1 & IOM-S 1 DC EMER BUS (Upper panel CAC / CPM 1 / IOM-S 1) NIL CAC 2 CPM 2 & IOM-S 2 DC ESS BUS (Upper panel CAC / CPM 2 / IOM-S 2) DC STBY BUS (Upper panel CAC / CPM 2 / IOM-S 2) NIL APM FAULT DC ESS BUS NIL
Ice & Rain Protection: 4 SYSTEM MONITORING¶
Ice & Rain Protection: 4.1 APM FAULT-Alert¶
CONDITION VISUAL AURAL APM failure - OR - Invalid aircraft parameters - MC light flashing amber - APM FAULT amber message on EWD - APM indicator pb FAULT amber light on center panel SC
Ice & Rain Protection: 4.2 DEGRADED PERF-Alert¶
CONDITION VISUAL AURAL In level flight: Drag abnormally high AND IAS significant decrease compared to max cruise speed - OR - In climb: Drag abnormally high resulting in a loss of rate of climb - OR - In descent: Drag abnormally high - MC light flashing amber - DEGRADED PERF amber message on EWD - DGD PERF amber message on FMA SC
Ice & Rain Protection: 4.3 INCREASE SPEED-Alert¶
CONDITION VISUAL AURAL In level flight: Drag abnormally high AND IAS below ICING BUG +10 kt - OR - In climb: Drag abnormally high resulting in a loss of rate of climb AND IAS below ICING BUG +10 kt - OR - In descent: Drag abnormally high AND IAS below ICING BUG + 10 kt - MC light flashing amber - INCREASE SPEED amber message on EWD - INCREASE SPEED amber message flashing on FMA SC
Ice & Rain Protection: 5 SCHEMATICS¶
Ice & Rain Protection: 5.1 Schematics¶
FMS 1/2 --+
ADC 1/2 --+
EEC 1/2 --+--> A429 inputs --> [MPC / APM FUNCTION] --> A429 broadcast --> CAC 1/2
FCU 1/2 --+ | |
CAC ------+ +--> analog/discrete inputs +--> EWD / PFD
+--> APM indications