A319/A320/A321
TECHNICAL TRAINING MANUAL
SA Family to A319/A320/A321 CFM LEAP - T1+T2
30-ICE AND RAIN PROTECTION
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CEO to NEO T1+T2
SA Family to A319/A320/A321 CFM LEAP - T1+T2
CFM LEAP
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL TP REV 1
System Presentation (NEO)...............................................................2
Engine Air Intake Ice Protection System Description (CFM
LEA....................................................................................................4
Ice and Rain Protection System Line Maintenance.........................12
TABLE OF CONTENTS Page 1
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
ENGINE AIR INTAKE ICE PROTECTION SYSTEM PRESENTATION
MEMO. The EEC monitors the valve position through transducers and
USERS processes them to generate necessary indications and warning through
the Flight Warning System (FWS). The FAULT indication in the PB
The Nacelle Anti-Ice (NAI) System is designed to prevent ice formation
S/W is activated by the PCS.
on the engine inlet which could affect the engine operation. The engine
air intake is heated during icing conditions using its related bleed air. The
hot air is then discharged overboard.
SOURCE
Hot air for the Nacelle anti-ice system is supplied by a dedicated HP
Compressor (HPC) bleed:
- on the CFM-LEAP, 7th stage,
- on the PW1000G, 6th stage.
VALVE
The NAI System is controlled and monitored by the Propulsion Control
System (PCS) (EEC and EIU). Each engine NAI System consists of two
electrically controlled, pneumatically operated Pressure Regulating and
Shut-Off Valves (PRSOV).
The EEC energizes the solenoid to CLOSE the PRSOV. Therefore, in
case of loss of electrical power supply, the valves will go fully open
provided the engine bleed air supply pressure is high enough. In the
absence of air pressure, the valve is spring-loaded to the closed position.
CONTROLS
When the ENG ANTI ICE P/BSW is selected ON, signals are sent to
EEC for controlling the valves and to the EIU to calculate the bleed
decrements.
ECAM PAGE
If at least one of the two engine air intake anti-ice protection systems is
selected ON, a message appears in green on the upper ECAM right
UM30P1000000004_001 - System Presentation (NEO) Page 2
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
USERS ... ECAM PAGE
UM30P1000000004_001 - System Presentation (NEO) Page 3
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
ENGINE AIR INTAKE ICE PROTECTION SYSTEM DESCRIPTION/OPERATION
NAI SYSTEM
Each engine air intake has its own independent Nacelle Anti-Ice (NAI)
protection system and control.
NAI System uses the hot bleed air from the 7th stage High Pressure
Compressor (HPC).
The air is sent through ducts, 2 Pressure Regulated Shut-Off Valves
(PRSOVs) located in Core Zone and is then discharged into the air intake
lip.
The EEC monitors the system operability with two
P
ressure Transducers (PTs) and Fan temperature sensor.
AIR INLET
The airflow exits the D-duct by a single exhaust grid at the bottom of
the nacelle outside the fan. Ducts are insulated in the fan compartment,
in order to keep duct surface temperature below 200°C, to protect
from duct burst and to minimize the risk of flammable fluids ignition.
UM30F2000000004_001 - Engine Air Intake Ice Protection System Description (CFM LEA Page 4
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
NAI SYSTEM - AIR INLET
UM30F2000000004_001 - Engine Air Intake Ice Protection System Description (CFM LEA Page 5
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
ENGINE AIR INTAKE ICE PROTECTION SYSTEM DESCRIPTION/OPERATION
PRSOV CONTROL AND OPERATION
The NAI system is controlled and monitored by the Propulsion Control
System (PCS): Electronic Engine Control (EEC) and Engine Interface
Unit (EIU).The EECs control the PRSOV's operation by
energizing/de-energizing the solenoids.
PRSOV 1 is controlled by EEC A and PRSOV 2 is controlled by EEC
B. Each PRSOV pneumatically regulates the downstream air pressure.
When the NAI PB S/W is selected to 'ON' position, the EECs de-energize
the 2 solenoids and the PRSOVs go to a regulating or open position.
The PRSOV 1 regulates the upstream pressure at 88 psig then in cascade
PRSOV 2 the downstream pressure at 68 psig.
MONITORING
The EECs do a detailed monitoring of the PRSOVs with two PTs (PT
1 & PT 2) located downstream each PRSOV.
PT1 is located in between the PRSOVs in the AFT side of the fan
case. It gives the feedback to channel B only and use for trouble
shooting.
PT2 is located downstream of PRSOV 2 near where the air is
delivered. It gives the feedback to both the EEC channels for
monitoring function in case of single failure of EEC channel.
Two temperature sensors located in the fan case bottom and top,
provide the 2 EEC (channels) with the fan compartment temperature
measurement for NAI leakage detection.
When the engine is running and a "Hot Air Leakage" event is detected,
the EEC energizes PRSOVs solenoids, which provide insulation
function.
UM30F2000000004_001 - Engine Air Intake Ice Protection System Description (CFM LEA Page 6
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
PRSOV CONTROL AND OPERATION - MONITORING
UM30F2000000004_001 - Engine Air Intake Ice Protection System Description (CFM LEA Page 7
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
ENGINE AIR INTAKE ICE PROTECTION SYSTEM DESCRIPTION/OPERATION
They remain latched until the engine is shutdown (N2<20% and Master
ENGINE ANTI ICE P/BSW Lever in Off position) and the A/C is on the ground.
The P/B SW sends a discrete signal to the 2 EEC channels to operate the
PRSOVs. The 2 EECs check valid signal through the Cross Channel Data
Link (CCDL).
The P/B SW position and the opposite engine P/B SW position are
monitored by the EIU for computing the bleed decrements.
The "FAULT" light is triggered by the EIU based on the input from EEC.
It appears when the engine is running and NAI is failed in OPEN or
CLOSED. It also appears in case of monitoring fault.
PCS (EEC and EIU)
The EEC controls the PRSOV to open when the P/B SW is set to ON.
The EEC monitors the position of the PRSOV by the two NAI
transducers to trigger associated fault messages.
Failure messages are computed by the EEC and sent by the EIU to
the FWS and CFDIU.
FAILURE CONDITION
The fail safe position of the valves in case of EEC dual channel failure
is OPEN.
In case of a single valve failure, the corresponding valve being failed
open, the anti-ice function is still available.
Per Master Minimum Equipment List (MMEL) a PRSOV can be
manually locked open or closed.
The two pressure Transducers (PT1 for core zone and PT2 for fan
zone) monitors leak or burst scenarios and a dual fan case
thermocouple helps in identifying over temperature conditions due to
leaks or burst. The EEC monitors the same and generates warning
messages to the FWS.
The Upstream and Downstream PRSOVs are commanded and latched
to OFF if a burst duct is detected ignoring the NAI Command
Selection.
UM30F2000000004_001 - Engine Air Intake Ice Protection System Description (CFM LEA Page 8
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
ENGINE ANTI ICE P/BSW - PCS (EEC AND EIU) & FAILURE CONDITION
UM30F2000000004_001 - Engine Air Intake Ice Protection System Description (CFM LEA Page 9
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
ENGINE AIR INTAKE ICE PROTECTION SYSTEM DESCRIPTION/OPERATION
NAI OPERATION SUMMARY
The PRSOVs operation and functionality depend on the valve inlet
pressure.
In normal mode, when the NAI P/B is selected the PRSOVs regulate, the
FWS computes and displays the ENG A.ICE memo on the ECAM.
Here are the cockpit effects of the possible failures.
UM30F2000000004_001 - Engine Air Intake Ice Protection System Description (CFM LEA Page 10
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
NAI OPERATION SUMMARY
UM30F2000000004_001 - Engine Air Intake Ice Protection System Description (CFM LEA Page 11
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
ICE AND RAIN PROTECTION SYSTEM LINE MAINTENANCE
MEL/DEACTIVATION
WING ICE PROTECTION
In case of failure, the aircraft may be dispatched per Minimum
Equipment List with the RH WING anti-ice valve deactivated in the
OPEN position or either valve in the CLOSED position. If the valve
is deactivated OPEN, the associated engine bleed switch must be
selected OFF until after takeoff. A flight manual performance penalty
is applied (fuel consumption is increased by 1%). If the valve is
deactivated CLOSED, the aircraft may not be flown into icing
conditions.
Procedure:
- Install zero-locking tool on slat/flap lever to prevent movement,
- Depressurize bleed air system,
- Remove access panel on wing lower surface,
- Move the valve indicator to the required position and install the
locking screw OR,
- Move the valve indicator to the required position and install the
locking plate.
UM30BA000000003_001 - Ice and Rain Protection System Line Maintenance Page 12
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
MEL/DEACTIVATION - WING ICE PROTECTION
UM30BA000000003_001 - Ice and Rain Protection System Line Maintenance Page 13
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
ICE AND RAIN PROTECTION SYSTEM LINE MAINTENANCE
MEL/DEACTIVATION (continued)
ENGINE AIR INTAKE ICE PROTECTION - CEO
In case of failure, the aircraft may be dispatched per Minimum
Equipment List with one ENGINE anti-ice valve deactivated in the
OPEN or CLOSED position. If the valve is deactivated OPEN, a Flight
Manual performance penalty must be applied. Based on temperature
and altitude, the maximum weight, takeoff speeds and fuel
consumption will be adjusted. If the valve is deactivated CLOSED,
the aircraft may not be flown into icing conditions.
Procedure:
- Full Authority Digital Engine Control (FADEC) ground power OFF,
- open RH fan cowl,
- move the manual override to the required position.
Lock in place with the locking pin, for CFM and V2500 engines. For
PW6000 engines, the air intake anti-ice valve is locked manually with
the locking lever in the OPEN position or the CLOSED position.
UM30BA000000003_001 - Ice and Rain Protection System Line Maintenance Page 14
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
MEL/DEACTIVATION - ENGINE AIR INTAKE ICE PROTECTION - CEO
UM30BA000000003_001 - Ice and Rain Protection System Line Maintenance Page 15
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
ICE AND RAIN PROTECTION SYSTEM LINE MAINTENANCE
MEL/DEACTIVATION (continued)
ENGINE AIR INTAKE ICE PROTECTION - NEO PW
The Engine Air Intake Valve is controlled and monitored by the Engine
Electronic Control (EEC).
In case of failure, the Aircraft may be dispatched as per Master
Minimum Equipment List (MMEL) with one ENGINE anti-ice valve
deactivated in the OPEN position through the Manual Override
mechanism on the Pressure Regulating Shut-Off Valve (PRSOV).
NOTE: Dispatch with 2 PRSOVs locked in open position is not
allowed for air inlet stress reason.
No PRSOV can be set in locked closed position.
UM30BA000000003_001 - Ice and Rain Protection System Line Maintenance Page 16
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
MEL/DEACTIVATION - ENGINE AIR INTAKE ICE PROTECTION - NEO PW
UM30BA000000003_001 - Ice and Rain Protection System Line Maintenance Page 17
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
ICE AND RAIN PROTECTION SYSTEM LINE MAINTENANCE
MEL/DEACTIVATION (continued)
ENGINE AIR INTAKE ICE PROTECTION - NEO CFM
LEAP
The Engine Air Intake Anti-ice system is controlled and monitored
by the Propulsion Control System (PCS).
In case of failure, the Aircraft may be dispatched as per Master
Minimum Equipment List (MMEL) with one ENGINE anti-ice valve
deactivated in the OPEN position through the Manual Override
mechanism on the valve itself or via the EEC CFDS Special Functions
menu.
This function has protection to avoid having both Nacelle Anti-Ice
(NAI) valves locked in the open position: overpressure risk.
One or 2 PRSOVs can be set in locked closed position and the Aircraft
not operated in Icing conditions, no ETOPS conducted.
UM30BA000000003_001 - Ice and Rain Protection System Line Maintenance Page 18
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
MEL/DEACTIVATION - ENGINE AIR INTAKE ICE PROTECTION - NEO CFM LEAP
UM30BA000000003_001 - Ice and Rain Protection System Line Maintenance Page 19
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
ICE AND RAIN PROTECTION SYSTEM LINE MAINTENANCE
MEL/DEACTIVATION (continued)
DRAIN MAST ICE PROTECTION
In case of a failure of a drain mast heater, the fault will be displayed
on the Flight Attendant Panel (FAP) of the Cabin Intercommunication
Data System (CIDS). The aircraft may be dispatched per Minimum
Equipment List with the drain mast heater inoperative. The water
supply to the LAVatory(ies) (LAV(s)) and galley which use the failed
drain mast must be shut off. As a result, the LAV(s) will not be usable
and must be secured closed and locked.
UM30BA000000003_001 - Ice and Rain Protection System Line Maintenance Page 20
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
MEL/DEACTIVATION - DRAIN MAST ICE PROTECTION
UM30BA000000003_001 - Ice and Rain Protection System Line Maintenance Page 21
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
ICE AND RAIN PROTECTION SYSTEM LINE MAINTENANCE
MAINTENANCE TIPS
When the aircraft is parked, it is recommended to install protective covers
on the air data probes (static ports, pitot probes, AOA probes, TAT
probes). The protective covers help protect the probes from contamination.
The covers should be marked with REMOVE BEFORE FLIGHT. Ground
personnel must insure that the covers are removed before flight or before
power is applied to the probes (engine start or ground test).
The probe heat system operates automatically to power the air data probe
heaters when at least one engine is running. It is also designed to operate
automatically when the aircraft is in flight. During the troubleshooting
and the on ground operations, observe the following precautions:
- if the Probe Heat Computer (PHC) power supply C/B is pulled, the
PHC internal relay will relax and the related probes will be heated. Make
sure to pull ALL of the associated probe heat C/B's (Static supply
(28VDC), AOA supply, Pitot supply & TAT supply (all 115 VAC)).
- if the Engine Interface Unit (EIU) power supply C/B is pulled, the PHC
will sense an "engine running" condition and the probes will be heated.
Make sure to pull ALL of the probe heat C/B's (Static supply (28VDC),
AOA supply, Pitot supply & TAT supply (all 115 VAC)).
- if the C/B of the LGCIU is pulled, it simulates FLIGHT situation. So
the probe heating is also switched ON.
UM30BA000000003_001 - Ice and Rain Protection System Line Maintenance Page 22
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
SA Family to A319/A320/A321 CFM LEAP - T1+T2
TP REV 1
A319/A320/A321 30-ICE AND RAIN PROTECTION
TECHNICAL TRAINING MANUAL
MAINTENANCE TIPS
UM30BA000000003_001 - Ice and Rain Protection System Line Maintenance Page 23
© AIRBUS SAS 2014 All rights reserved. Confidential and proprietary document.
© AIRBUS SAS 2015. All rights reserved.
Confidential and proprietary document.
This document and all information contained herein is the sole property of
AIRBUS SAS. No intellectual property rights are granted by the delivery of
this document or the disclosure of its content. This document shall not be
reproduced or disclosed to a third party without the express written consent
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are expressed in good faith. Where the supporting grounds for these
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thereof.
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