air conditioning liebheer

AB 139

LIEBHERR-AEROSPACE Toulouse Dez. 2003 TECHNICAL SERVICES

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This document must be used for training purpose only

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Training on

Ventilation/Forced Ventilation/Heating andAir Conditioning System of the

AB139 Helicopter

It will not be updated

Under no circumstances should this document be used as a reference

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TABLE OF CONTENTS:

Table of ContentsAbbreviationsGeneral description

Ventilation System including Forced Ventilation:- Pilot Interfaces- System Control- Detailed System Operation- Low Pressure Ducting- Component description- Trouble shooting

Heating and Ventilation System including Forced Ventilation: - Pilot Interfaces- System Control- Detailed System Operation- High Pressure Ducts- Component description- Trouble shooting

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TABLE OF CONTENTS (cont'd):

Air Conditioning System:- Pilot Interfaces- System Control- Detailed System Operation - Component description- Trouble shooting

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LIST OF ABBREVIATIONSA/C: AircraftAC Alternative CurrentACCB Air Conditioning Control BoxAFT Cabin zoneBAD: Bleed Air DuctCP: Cockpit PanelCV: Check ValveDTS: Duct Temperature SensorECS: Environmental Control SystemFMEA: Failure Mode And Effect AnalysisFMECA: Failure Mode, Effect and Criticality AnalysisFV: Flapper ValveFWD Cockpit zoneHCB: Heating Control BoxHMV Heating Modulation Valve (see TCV)HTR HeaterJP: Jet PumpLPD: Low Pressure DuctingLTS: LIEBHERR AEROSPACE ToulouseOTS: Over Temperature SwitchSOV: Shut Off ValveTCV Temperature Control Valve

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LIST OF ABBREVIATIONS (cont'd)

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Ventilation

Enter

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Forced Ventilation

Enter

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Ventilation/Heating

Enter

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Forced Ventilation/Heating

Enter

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Ventilation/Heating Air Conditioning

Enter

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General Description

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General descriptionThe Environmental Control System on the AB139 is divided in severalsubsystems which are the Ventilation and the Heating system optimisedby an Air Conditioning System.

- Heating is generated by mixing bleed air from the engine with outsideram air flow in a jet pump and by diffusing it into the helicopter through alow pressure ducting system.

- Fresh air is provided by outside Ram Air flow controlled by FlapperValves and distributed into the helicopter trough a low pressure ductingsystem.

- Cooling is provided by two splitted vapour cycle systems dedicatedrespectively to the cockpit an cabin zones.

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The ECS system has 5 different versions :- The cockpit and cabin ventilation system - P/N 3G2120A00111

- The forced cabin ventilation system - P/N 3G2121F00111

NOTE: Ventilation and Forced Ventilation are discribed in the same chapter.

- The heating* and ventilation system - P/N 3G2140F00111

- The heating* and forced ventilation system - P/N 3G2141F00111

NOTE: Heating withVentilation and Forced Ventilation are discribed in thesame chapter.

- The AIR conditioning* / heating and Ventilation System - P/N3G2150F00111

*High and low pressure ducts are provided for the heating and the airconditioning system.

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Helicopter Ventilation System cut off view

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Ventilation system components:Item Components of the Cockpit ventilation P/N20204A010000 P/N Qty

001

Ventilation COCKPIT CONTROL PANEL 91100A010000

1

Ventilation COCKPIT CONTROL PANEL NVG 91100A010001

002 Ventilation Cockpit FLAPPER VALVE 6034A010001 2

003 Ventilation COCKPIT fan 8013A020000 2

004 Wedges for 6034 mounting 20204-72 2

005 P_CLIP PLENUM DISTRIBUTION COCKPIT 20204-4 2

006 FLEXIBLE between NACA & 6034 9869B010000 2

007 RIGID 6034 -> 8013 right 9871B010000 1

008 RIGID 6034 -> 8013 left 9870B010000 1

009 RIGID 8013 -> PLENUM DISTRIBUTION 9706B010000 2

010 PLENUM COCKPIT right - PART 1 - Fan side 9873B010000 1

011 PLENUM COCKPIT right - PART 2 - GASPER side 9896B010000 1

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Ventilation system main parts:012 PLENUM COCKPIT left - PART 1 - Fan side 9872B010000 1

013 PLENUM COCKPIT left - PART 2 - GASPER side 9897B010000 1

014 COCKPIT LATERAL DIFFUSER - up right 9711B010000 1

015 COCKPIT LATERAL DIFFUSER - up left 9712B010000 1

016 COCKPIT LATERAL DIFFUSER - down right 9713B010000 1

017 COCKPIT LATERAL DIFFUSER - down left 9714B010000 1

018 CENTRAL DIFFUSER right 9895B010000 1

019 CENTRAL DIFFUSER left 9894B010000 1

020 brackets for 8013 20204-68 2

021 Y BRANCH ASSY for GASPERS 9709B010000 2

022 GASPERS 9710B010000 4

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Ventilation system main parts:

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Addional Forced Ventilation system parts:Components of the Cockpit/Cabin Forced ventilation system

P/N 20204B010000 P/N Qty

Forced ventilation COCKPIT CONTROL PANEL 91102A010000

1

Forced ventilation COCKPIT CONTROL PANEL NVG 91102A010001

CABIN fan 8012A010000 1

CABIN fan bracket 20204-21 1

Forced ventilation CABIN CONTROL PANEL 91103A010000 1

Forced ventilation CABIN CONTROL PANEL - NVG 91103A010001 1

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VENTILATION SYSTEM

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VentilationLTS provides two different cockpit and cabin ventilation systems,called Ventilation and Forced ventilation.

Cockpit ventilation system

For the cockpit, two separate systems provide air for pilot and co-pilot. Outside RAM air enters the systems through two air intakeslocated on the nose section.

For cockpit and cabin ventilation the outside ram air flow can beselected by flapper valves, manually controlled by the crew with a 4-position switch on the Cockpit control Panel.

Ventilation

Forced outside air for cockpit ventilation or defogging is provided by2-speed axial fans in each systems. The blowers are manuallycontrolled by the crew in Off, Low Speed, or High Speed.

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Training DOCTR 039Ventilation

The Cockpit Control Panel (P/N 91100A010000) interfaces with:

- the cockpit fans (2 qty)

-the cabin (1 qty) and cockpit (2qty) flapper valves

VENT CREW 4 position switch:OFF- FVs "Closed" and FANs "Off"

ON FVs "Open" and FANs "Off"

LOW - FVs "Open" and FANs "Low speed"

HIGH - FVs "Open" and FANs "High speed"

Ventilation

VENT

OFFON

VENT

91101A010000 or 91101A010001 (NVG)Cabin Control Panel

91100A010000 or 91100A010001 (NVG)Cockpit Control Panel

VENT CTRL

PAX

CREW

VENT

OFF

FANLOW FAN

HIGHON

CREW

ON

PAX

OFF

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Ventilation cont.CONTR 2-position switch control the availability of the passenger controlpanel.

When CREW is selected, the control of the cabin area is done by thecockpit panel.

When PAX is selected, the control of the cabin area is done by thepassenger panel.

The Cabin Control Panel (P/N 91101A010000) interfaceswith:- the cabin flapper valve

The VENT indication light on the Cabin panel is illuminated when PAX hasbeen selected on the Cockpit panel.

OFF - Cabin FV "Closed"

ON Cabin FV "Open"

Ventilation

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The cockpit panel CREW selected, allows the direct control oftwo cockpit fans (off/low/high) and two single cockpit flappervalves, PAX selected the cabin flapper valve is controled via thecabin panel.

VENTILATION SYSTEM CONTROL

Cabin ventilation Cockpit ventilation

Lower Side Window Demister

Upper Side Window Demister

Main winshield Demister

Front face outlets

Fan

Air intake




Front face outlets

Fan

Flapper valve

Air intake

To control panel

Air intake Flapper valve

Plenum

To control panel

Singular gaspers manifold

Side vents manifold


Side vents manifold

Water separation

duct

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Training DOCTR 039VENTILATION

Cockpit ventilation system (cont'd)One 2-speed centrifugal fan on the L/H and one on the R/H side,provides outside/ram air for ventilation or defogging.

They are manually controlled by the crew in Off, Low Speed, or HighSpeed mode.

Cabin ventilation systemFor the cabin, outside ram air enters the system through one air intakein the forward pylon fairing in the cabin roof, the air flow is admitted bya flapper valve.The air is then routed through ducts which are installed above thecabin ceiling panels.

The cabin panel allows the direct control (open/close) of the cabinflapper valve with the VENT switch.

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FORCED VENTILATION

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Forced Ventilation

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The Forced ventilation system provides an additional 2-speedcentrifugal fan for the cabin zone supplying outside/ram air.

The CABIN fan is controlled manually by the crew on the cockpitcontrol panel VENT in OFF, LOW or HIGH speed mode when "CREW"selected or from the cabin panel by the passengers when "PAX"selected.

Nota: For Air conditioning option, the air flow across the cabinevaporators is provided by the cabin fan and a second addional fan.The air conditioning option allows to run the cockpit and cabin fans inrecirculation mode (override of the VENT Switch).

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The COCKPIT panel for Forced Ventilation (P/N 91102A010000) interfaces with:- the cabin fan (1)

- the cockpit fans (2)

- the cabin (1) and cockpit flapper valves (2)

Cockpit Control Panel P/N 91102A010000

The CABIN panel for Forced Ventilation (P/N 91103A010000) interfaces with:- the cabin fan (1)

- the cabin flapper valve (1) Cabin Control Panel P/N 91103A010000

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Forced Ventilation:When VENT CTRL "CREW" selected, the cockpit panel allowsthe direct control of all fans (off/low/high), and flapper valves(open/close) in the cabin and cockpit zone.

When VENT CTRL "PAX" selected, the cabin panel allowsindependently the control of the cabin fan (off/low/high), andflapper valve (open/close).

SYSTEM CONTROL

Cabin ventilation Cockpit ventilation




Front face outlets

Fan

Air intake




Front face outlets

Fan

Flapper valve

Air intake

To control panel


Plenum


Side vents manifold


Side vents manifold

To control panel

AFT Fan

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Training DOCTR 039 Heating system

Ventilation/Forced

Ventilation System Logic :

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Forward Ventilation :

If cockpit fans are operating, then the control panel sends the " ForwardVentilation On " discrete signal to the helicopter general displayer (MAU).

After Ventilation : If cabin fan is operating, and cabin flapper valves are not fully closed; thenthe control panel sends the " After Ventilation On " discrete signal to thehelicopter general displayer (MAU).

Ventilation Failure: If AFT-FAN-FAULT is active or FWD-FAN1-FAULT is active or FWD-FAN2-FAULT is active , then the control panel sends the " Ventilation Failure" discrete signal to the helicopter general displayer.

Heating system

Ventilation and Forced ventilation System Logic :

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Detailed Ventilation System

Operation

And

Component Description

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Training DOCTR 039Cockpit and Cabin Ventilation and Forced Ventilation

Cockpit ventilation system (basic)

For the cockpit, two separate systemsprovide air for pilot and co-pilot. OutsideRAM air enters the systems through two airintakes positioned on the helicopter nosesection.

Air for ventilation or defogging is providedby either ram air and/or (on ground) by two2-speed axial fans installed near to the pilotand co-pilot pedestal (flapper valves open).

Air is then distributed to the different outlets,front faces outlets, main windshield and sidewindows diffusers.

The cockpit and the cabin ventilation systems are two different and separate sub-systems.




Front face outlets

Fan

Air intake




Front face outlets

Fan

Flapper valve

Air intake

To control panel

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Training DOCTR 039Ventilation System

Cabin ventilation system (basic)

For the Cabin, outside ram air enters the system through one air intake inthe forward pylon fairing in the cabin roof. The air is then routed through aduct to the flapper valve.

The outside Ram air flow is supplied by an Open/Close flapper valvecontrolled manually by the crew with a 2 position switch on the cockpitcontrol Panel " VENT PAX or by the cabin panel provided CONTR PAXhas been selected.

Air is then distributed via the plenum to both lateral manifolds, each onebeing separated supplying fresh air via singular gaspers to thepassengers.

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FORCED ventilation for the cabin is provided by an additionel two speed axial fan.

The fan and flapper valve control can be achieved by the crew through the cockpit panel or when VENT CTRL PAX selected by the passengers through the cabin panel.


Plenum


Side vents manifold


Side vents manifold

To control panel

Fan

Water separation

duct

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The demisting outlets are composite diffusers with fins to control the air jetcharacteristics to perform the windscreen bay demisting.

The cockpit gaspers are wide diffusers to provide comfortable diffusingwith large air flow.

The cabin gaspers are standard airplane gaspers.

The cabin and cockpit pedestals are composite outlets to diffuse air tocrew and passengers feet.

Characteristics:

The ventilation distribution system is designed to withstand pressurevariations in a range of 15 mBars and + 150 mBars.

The maximum operating temperatures should be in-between 40 C to +85 C.

Distribution system description:

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Distribution system description

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Training DOCTR 039Ventilation Low Pressure Ducting Cockpit view:

Flapper Valve

Pluged Heating System connections

Fan

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The low pressure ducting LPD system consists of air distribution ducts,manifolds, cabin diffusors, pedestral outlets, window demister, front faceoutlets and a plenum. Depending on the configuration to be installed onthe helicopter, we can distinguish 5 subsystems :

The LPD for Cockpit Ventilation Subsystem (basic)

The LPD for Cabin ventilation Subsystem (basic)

The LPD for Forced Cabin Ventilation Subsystem (kit)

The LPD for Heating Subsystem (kit)

The LPD for Air Conditioning Subsystem (kit)

The ventilation system distribution ducting for cockpit and cabin is thebasic version for the helicopter.

Low Pressure Ducting

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Training DOCTR 039Low Pressure Ducting views (exampels):

Cabin ceiling plenum with diffuser

Cabin diffuser (exampel)

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Ventilation System Main

Component description

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Ram Air Flapper valvesGeneral information:The pilot drives the Flapper Valves from the cockpit panel, to open or shut offthe ram air intakes of cabin and cockpit low pressure distribution system.

Installation:The valves are located after the ram air intakes of the ECS before fans.

They are attached to the structure by metallic brackets and to the ducting withminox clips.

The mounting brackets ensure bonding between the valve and the helicopter.

Pressure drop (valve full open) :

With a nominal Cockpit flow of 125g/s = 0,2 mbar

With a nominal Cabin flow of 350 g/s = 0,3 mbar

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Cockpit FLAPPER valve 6034A010001 (ventilation + heating)

The two flapper valves are derived composed of : a 3cylindrical composite body, a tangential gear box, a shaft which transmits the rotational movement by a tenon-mortise typedrive

brushes direct current motor, one end of travel opening and one end of travel closing position switch, an aluminium flap.

Characteristics: Nominal power supply : 28 Vdc for a limit of 17 Vdc to 32 VdcCurrent consumption at nominal torque of 0.12 mdaN :

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Cockpit Flapper valve pin location :

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Cockpit FLAPPER valve (6034A010001 ventilation + heating) general view:

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Cabin FLAPPER valve 6035A010001:The Ram air cabin valve is a 4 diameter, single cylindrical composite body butterflyvalve.

Inside the valve core an aluminium circular flap, held by 2 half-shafts, perform theshut-off function.

The flapper valve shaft is driven by an electrical actuator.

The electric actuator, consists of an endless screw and an 28Vdc electrical motor.

Two end of travel micro-switches indicates the state of the valve: Open or Close.

Characteristics: Nominal power supply : 28 Vdc for a limit of 17 Vdc to 32 VdcCurrent consumption at nominal torque of 0.12 mdaN :

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Cabin Flapper Valve pin location :

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Cabin FLAPPER valve 6035A010001 general view:

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Cockpit Fan 8013A020000 function (ventilation/heating system only):There are 2 two speed brush less cockpit fans per helicopter on 2 symmetricalventilation systems.

Both fans sucks air from the ram air intake and generates ventilation air flow towardsthe cockpit outlets and are used for ground and flight operation.

They are controlled by the ECS Cockpit panel at high and low speed and are equippedwith a thermal switch and a under speed detection. To reset the fan, select OFF/ON.Fan characteristics:Power supply: 28Vdc

Normal working temperature range: - 40 C to + 70 C

Low speed flow rate at 30 C and at see level: 7350 rpm / 35 g/s

High speed flow rate at 30 C and at see level: 14200 rpm / 6.5 A / 70 g/s

Max. current consumption: 7 A (start up 14 A)

Weight: 0.9 kg

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In On mode, a fault is indicated (Ground) only if the speed is inferior to the under speed limit during 3 to 5s.

With no power supplied the under-speed pin detection shall be Open.

With power supplied and OFF selection the under-speed pin detection shallbe open circuit.

The under-speed detection level is the half off low speed and half off highspeed 15% (in tr/mn).

During the start up phase when ON selection is activated the under-speedpin detection is open circuit during 5 seconds.

An under-speed fault is detected if the under-speed pin detection is groundafter the start up phase. In this case the fan will be stop and a OFF/ONselection is necessary for start again the fan.

Cockpit Fan 8013A020000 under speed detection:

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ON/OFF selection : Under-speed detection :

o Ground ON o Ground Faulto Open Circuit OFF o Open Circuit No fault

High speed / Low speed selection :

o Ground Low speedo Open Circuit High speed

Cockpit Fan 8013A020000 electrical logic:

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Cockpit Fan 8013A020000 Pin Location (idem for FAN 2):

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Cockpit Fan 8013A020000 (ventilation/heating system only) general view:

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Cabin Fan 8012A020000 function (Forced ventilation + heating):In this configuration we will find one 2 speed brush less cabin fan perhelicopter.

The fan sucks air from the ram air intake and generates ventilation air flowtowards the cabin overhead outlets. The cabin fan is used for ground and flightoperation.

It is controlled either by the ECS Cockpit panel or Cabin panel.

Fan characteristics:Power supply: 28 Vdc

Normal working temperature range: - 40 C to max. + 85 C

Low speed flow rate at 30 C and at see level: 8000 rpm / 5A / 110 g/s

High speed flow rate at 30 C and at see level: 12300 rpm / 16A / 210 g/s

Nominal current consumption: 16 A (start up 23 A)

Weight: 1,6 kg

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In On mode, a fault is indicated (Ground) only if the speed is inferior to the under speed limit during 3 to 5s.

With no power supplied the under-speed pin detection shall be Open.

With power supplied and OFF selection the under-speed pin detection shallbe open circuit.

The under-speed detection level will be the half off low speed and half offhigh speed 15% (in tr/mn).

During the start up phase when ON selection is activated the under-speedpin detection is open circuit during 5 seconds.

An under-speed fault is detected if the under-speed pin detection is groundafter the start up phase. In this case the fan will be stop and a OFF/ONselection is necessary for start again the fan.

Cabin Fan 8012A020000 under speed detection:

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ON/OFF selection : Under-speed detection :

o Ground ON o Ground Faulto Open Circuit OFF o Open Circuit No fault

High speed / Low speed selection :

o Ground Low speedo Open Circuit High speed

Cabin Fan 8012A020000 electrical logic:

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Cabin Fan 8012A020000 Pin Location :

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Cabin Fan 8012A020000 (Forced ventilation/heating) general view:

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VENTILATION SYSTEM TROUBLE SHOOTING PROCEDURE

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Ventilation System trouble shooting using break-out box (BOB) -P/N92612A010000 :On the Cockpit panel : Switch VENT CREW Fan in low and high speed mode (both FWD fans).

1a) No air flow, (cockpit gaspers fully open pedestral gaspers fully closed).BOB indication :

- FWD Fan Off selected : FWD Fan-Ctl light Yellow , Fan-On light Off

- FWD Fan Low selected : FWD Fan-Ctl light Green , Fan-On light Green

-FWD Fan High selected : FWD Fan-Ctl light Yellow, Fan-On light Green

IMPORTANT:Loose of FWD FAN-CTL order result automatically into a Fan High speed order!

Note BOB: Fan ON (Jumper-15) and Fan CTL (Jumper-16)

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Training DOCTR 039Ventilation System trouble shooting contd:

NO Red Failure light indication on BOB:- FWD Fan 1 red light Off (to confirm remove Jumper - 35),

- FWD Fan 2 red light Off (to confirm remove Jumper - 44),

- AFT Fan 1 red light Off (to confirm remove Jumper - 50),

- A/C version : AFT Fan 2 red light Off (to confirm remove Jumper 43).

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Training DOCTR 039Ventilation System trouble shooting cont'd:

1b) NO air flow on left or/and right side (both sides are completely independant):

Check power supply to the fan (FWD-FAN-ON [to confirm remove jumper 15 light goes Off ],

if o.k. (fan running) check connections of the distribution ductings,no 28Vdc power supply (BOB FWD-FAN-ON light Off ) check wiring and power supply to the Cockpit Panel

wiring and power supply o.k. replace Cockpit panel

2) Low flow at the cockpit gaspers with fan running

a) Check if left/right Fan is/are running in high speed mode (different noise level use flowmeter)

-If not, check High speed order (BOB: FWD Fan-Ctl light Yellow, Fan-On light Green)

no High speed order replace Cockpit panel

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Ventilation System trouble shooting cont'd:Reminder BOB: Fan On (Jumper-15) + Fan CTL (Jumper-16), to confirm signal remove jumpers.High speed order o.k. check wiring and 28Vdc on fan connectorIf O.K. - replace concerned fan

b) Low flow and Fan running in low and high speed mode- check visually the position indicator on the Flapper valve,

- check power supply order to the flapper valve(s) which should be fully open BOB FWD FV CMD green light On (Jumper-23),

if o.k. and valve still closed - BOB FWD FV Full Close green light "On [Jumper 51], - check wiring and 28Vdc on FV connector,

If wiring and 28Vdc O.K. - replace concerned FV,BOB FWD FV CMD light Off check wiring and 28Vdc power supply to the Cockpit panel between jumper 25 and 32,

If O.K. - replace Cockpit Panel

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Forced Ventilation System trouble shooting:On the Cockpit VENT PAX or on the cabin panel VENT switch fan in low and high speed mode (all 12 cabin gaspers open), select CREW

Note: PAX selected Cabin panel provides order to cockpit panel which controls the cabin Fan.

1) No flow at the cabin outlets:check power supply to the AFT fan, BOB-AFT FAN-ON Green light On (Jumper-8) and FAN CTL Yellow light ON = High Speed order (Jumper-9) ,

if o.k. (fan running) check cabin distribution ducting connection downstream of the plenum,

no 28Vdc power supply check wiring and connectionwiring o.k. check power supply to cockpit and/or cabin panel

Wiring o.k. replace cockpit or cabin panel

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Forced Ventilation System trouble shooting cont'd:

2) "Low" flow at the cabin outlets:

a) Fan not running in high speed mode-check High speed order to the fan, using break out box.

Reminder: Fan-On green light (Jumper-8) and Fan-CTL Yellow light (high speed Jumper-9)

Check wiring and 28Vdc on Fan connector,if o.k. - replace fan, no High speed order Fan CTL Green light ON (low speed) disconnect helicopter wiring from BOB and check if Fan CTL Yellow light comes on (high speed)

check helicopter wiring, if O.K. - replace Cockpit panel,

PAX selected for Cabin panel check wiring and if o.k. - replace cabin panel

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Training DOCTR 039Forced Ventilation System trouble shooting cont'd:

2 b) Low flow and Fan running in low and high speed mode - visually check the Flapper Valve position indicator,

- check power supply to the flapper valve which must be fully open, BOB AFT FV-CMD green light "On"[Jumper-21] and AFT FV Full-close green light Off (Jumper-55),

Check 28Vdc power supply on connector, if o.k. and valve still closed, BOB green light "On"[Jumper-55]) - replace FV

no 28Vdc power supply (BOB between jumper 25 and 32) replace Cockpit panel,

for Cabin panel check wiring and if o.k., replace Cabin panel

c) Fan running in low and high speed mode and FV openAttention: In A/C configuration, FV might be closed

- Look for a leakage located upstream of the plenum in the upper deck zone

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Forced Ventilation System trouble shooting cont'd:

3) Flow misbalance between left and right side, (Fan running in low and high speed mode, Flapper valve open)

- Look for a leakage located either on the plenum connection or on the manifold and Not in the upper deck zone.

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HEATING

AND

VENTILATION SYSTEM

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Helicopter Heating System cut off view

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Training DOCTR 039Low Pressure Ducting (Vent/Heating) Cockpit view:

Flapper Valve

From Heating System

Fan

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Item Heating system Components (ventilation) 20204C010000 P/N Qty

042HEATING COCKPIT CONTROL PANEL 91104A010000

1HEATING COCKPIT CONTROL PANEL - NVG 91104A010001

043 TEMPERATURE CONTROL VALVE 14422A030001 1

044 FACIAL E-SEAL JOINT 3475 4

045 Check Valve clamps 6354-100 2

046 HIGH PRESSURE DUCT Left 12771A010000 1

047 HIGH PRESSURE DUCT Right 12772A010000 1

048 HP Duct 12760A020001 2

049 HP Duct 12761A020001 1

050 1'' HP Check valve 2298A020000 2

051 Composite Jet Pump 428B010000 1

052 Shut off valve 6916A020000 2

053 Heating control box 92177A020000 1

054 Duct Temperature sensor 93260A010000 1

055 OVERHEAT THERMAL SWITCH 92252A010000 1

056 Heating air inlet 9804B010000 1

057 flexible hose between 9804 & JET PUMP 9805B010000 1

058 flexible hose downstream the JET PUMP 9806B010000 1

Helicopter Heating/Ventilation System components:

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059 NOISE ATTENUATOR ASSY 9807B020000 1060 Y BRANCH ASSY between 9807 & 9810 9808B020000 1061 between 9808 & 9810 left 9809B010000 1062 Heating distribution flexible 9810B010000 2063 T Branche to 9892 & 9893 9811B010000 2064 Left Bwd heating diffuser 9893B010000 1065 Right Bwd heating diffuser 9892B010000 1066 Flexible hoses after 9810 9816B010000 2067 T BRANCHE + flexible to SBAND 9922B010000 2

068 FLEXIBLE 9817 to 9891 9818B010000 1

069 FLEXIBLE 9817 to 9890 9819B010000 1

070 Left Fwd heating diffuser 9891B010000 1

071 Right Fwd heating diffuser 9890B010000 1

072 Left RIGID SBAND through wall 9823B020000 1

073 Right RIGID SBAND through wall 9824B020000 1

074 Left right balancing flexible 9825B010000 1075 Y BRANCHE to GASPER or COCKPIT right 9826B020000 1076 Foot GASPER holder right 9827B010000 1077 Y BRANCHE to GASPER or COCKPIT right 9829B020000 1

078 Foot GASPER holder left 9830B010000 1079 Heating arrival in the left cockpit - H&V 9908B010000 1080 Heating arrival in the right cockpit - H&V 9874B010000 1081 Connection of 9826 to COCKPIT right - common 9927B010000 1082 Connection of 9829 to COCKPIT left - common 9875B010000 1083 H&V - flexible between the 9874 and the 9870 & 9871 9924B010000 2084 RIGID 6034 -> 8013 right 9871B010000 1085 RIGID 6034 -> 8013 left 9870B010000 1


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075 Y BRANCHE to GASPER or COCKPIT right 9826B020000 1

076 Foot GASPER holder right 9827B010000 1

077 Y BRANCHE to GASPER or COCKPIT right 9829B020000 1

078 Foot GASPER holder left 9830B010000 1

079 Heating arrival in the left cockpit - H&V 9908B010000 1

080 Heating arrival in the right cockpit - H&V 9874B010000 1

081 Connection of 9826 to COCKPIT right - common 9927B010000 1

082 Connection of 9829 to COCKPIT left - common 9875B010000 1

083 H&V - flexible between the 9874 and the 9870 & 9871 9924B010000 2

084 RIGID 6034 -> 8013 right 9871B010000 1

085 RIGID 6034 -> 8013 left 9870B010000 1


AB 139


Training DOCTR 039


AB 139


Training DOCTR 039

Helicopter Heating/ForcedVentilation Systemcomponents:

Components of the Heating + Cockpit/Cabin Forced ventilation system P/N 20204D010000 P/N Qty

Heating + Forced ventilation COCKPIT CONTROL PANEL 91106A010000

1

Heating + Forced ventilation COCKPIT CONTROL PANEL NVG 91106A010001

CABIN fan 8012A010000 1

CABIN fan bracket 20204-21 1

Forced ventilation CABIN CONTROL PANEL 91103A010000 1

Forced ventilation CABIN CONTROL PANEL - NVG 91103A010001 1

AB 139


Training DOCTR 039

Heating System

The heating system consists of the elements described on thefollowing schematic and a distribution system.

ENG1

ENG2

SOV1 (1)

SOV2 (1)

TCV (4)

JP (5) ADTS (7)

DOTS (8)

HCB (6)

CV2 (2)

CV1 (2)

BAD (3)

AMBIANT AIR

AB 139


Training DOCTR 039

Heating System

Distribution ducting:

Fan

Fan

Pedestral outlets

Front cabin diffusor Rear cabin diffusor

Jet Pump

Pedestral outlets

Front cabin diffusor Rear cabin diffusor

From cockpit ventilation

From cockpit ventilation

AB 139


Training DOCTR 039

The Heating Control Box and the Cockpit Panel controls and monitors the HeatingSystem according to the pilot demand.

An overheat protection is provided to shut off the system if required.

Two modes are basically proposed for the system :

Semi-automatic mode where the control box controls the blowing temperaturein accordance with the selected temperature set by the crew on the cockpitpanel.

Manual mode to insure the safety defogging mode, in case of automatic modefailure

The Cockpit Control Panel for Heating and Ventilation System interfaces with:

- the cockpit fans (2 qty.)

- the cabin (1 qty.) and cockpit flapper valves (2 qty.)

- the Shut Off Valves ( SOV1 & SOV2 )

- the Temperature Control Valve ( TCV ) (1 qty.)

- the Heating Control Box ( HCB ) (1 qty.)

HEATING

AB 139


Training DOCTR 039

The different valves of the Heating system are supplied with hot engineair by HP-ducts which are equipped with insulation jackets in order tokeep the skin temperature below 200 C.

High Pressure Ducts and Insulation Jackets

HP Duct12761A010001

HP Duct12772A010000

HP Duct12760A020001

HP Duct 12771A010000

HEATING

AB 139


Training DOCTR 039

PILOT INTERFACES

HEATING

AB 139


Training DOCTR 039HEATING

"Heating and Ventilation system" Cockpit Control P/N91104A010000 and Cabin Control Panel P/N 91101A010000

CONTR

PAX

CREW

HTR

SOV

NORMAL

CLOSE

OFF

AUTO

VENT

OFF

FANLOW FAN

HIGHON

CREW

ON

PAX

1 potentiometer2 switches

TEMPCONTR

OFF

VENT

OFFON

VENT

91101A010000 or 91101A010001 (NVG)Cabin Control Panel

91104A010000 or 91104A010001 (NVG)Cockpit Control Panel

AUTO

MAN HTR

MIN MAX

AUTO

MAN HTR

MIN MAX

MAN

1 2

HTR

Toggle switch

AB 139



Cockpit Control Panel "Heating and Ventilation system" P/N91104A010000VENT part : please refer to "Ventilation" chapter

HEATER part :

Two 2-positions toggle switches control the SOV 1+2 :

NORMAL the SOV is open or closed.

CLOSE the SOV is closed for safety reason by the crew.

The switch goes back to the NORMAL position when the 28VDC to the controlpanel is switched off.

Enter

AB 139



A 3-positions Off, Man/Demist, Auto switch allows to select thecontrol mode :

OFF selected, the Heating Control Box is switched Off, both SOVs are closed.The pilot can choose ventilation mode.

AUTO selected, the Heating System is in automatic mode. The pilot can chooseventilation mode. Both SOVs are open, the HCB is switched "On", and controlsautomatically the blowing temperature (only if at least one of the SOV is open). Forproper selection, the control panel sends a discrete signal, and the HCB controls theblowing temperature by modulating the TCV according to temperature demand, whichis set by the pilot using the rotary potentiometer. The manual control of the TCV withthe HMV rotary toggle switch is hence inhibited.

MAN selected, the Heating Control Box is switched Off. The pilot can chooseventilation mode. Both SOVs are open, and the control of the Heating System is doneby direct TCV motor command from the TEMP CONTR rotary toggle switch, whichallows to adjust manually the blowing temperature.

AB 139



A Rotary Potentiometer :

When HTR AUTO is selected, the potentiometer controls via the HeatingControl Box the Temperature in cabin and cockpit.When OFF or MAN is selected, the potentiometer has no function.

A TEMP CONTR Rotary Toggle Switch :

When AUTO or OFF is selected, the Rotary Toggle Switch has nofunction.

When MAN is selected, the Rotary Toggle Switch controls directly theTCV, left position (-) for closing and right position (+) for opening.

AB 139



Heating and Forced Ventilation system Cockpit Control P/N 91106A010000 and Cabin Control Panel P/N 91103A010000

CREWCLOSE

AB 139


Training DOCTR 039

Cockpit Control Panel Heating and Forced Cabin Ventilation systemVENT part : please refer to "Ventilation" description

HEATER part : please refer to previous Heating and Ventilation systemdescription

HEATING

Enter

Enter

AB 139


Training DOCTR 039

SYSTEM CONTROL

HEATING

AB 139


Training DOCTR 039

Cockpit panel functions, Ventilation/Heating system:(VENT CTRL "CREW" selected)

Control Cockpit fans (off/low/high),

Control Cockpit and Cabin Flapper Valves*,Control Shut Off Valve SOV 1+2 opening/closing (in Man and Automode),

Control Temp Control Valve TCV opening/closing (in Man mode bythe Temp. Contr. Rotary Toggle Switch),

Control Heating system Control Box HCB on/off,Provides Cockpit/Cabin zone temperature demand signal to the HCB(potentiometer).

*With VENT CTRL "PAX" selected on the cockpit control panel thecabin panel control the cabin flapper valve.

HEATING SYSTEM CONTROL

AB 139


Training DOCTR 039

Cockpit panel functions, Heating and Forced Ventilationsystem: (VENT CTRL "CREW" selected)Control Cockpit and CABIN fans (off/low/high)*,Control Cockpit and Cabin Flapper Valves*,Control Shut Off Valve SOV 1+2 opening/closing,Control Temp Control Valve TCV with toggle switch ("MAN" mode)Control Heating system Control Box HCB On/Off,Provides Cockpit/Cabin zone temperature demand signal to the HCB(potentiometer).

*With VENT CTRL "PAX" selected on the cockpit control panel thecabin panel control the cabin flapper valve and the cabin fan.


AB 139


Training DOCTR 039

Cockpit

panel pin

location:


AB 139


Training DOCTR 039HEATING SYSTEM CONTROL

AB 139


Training DOCTR 039

Heating system Control Box HCB functions:Monitoring of the External Air Temperature Sensor EATS,Monitoring of the Air Duct Temperature Sensor ADTS,Monitoring of the Duct Overheat Thermal Switch DOTS,Monitoring the Shut Off Valves - SOV 1 + 2 which are controlled by theCockpit Panel,

Control of the Temperature Control Valve TCV (in Auto mode)Memorizing the EATS, ADTS, DOTS and the Temp. Control faultmessage,

Triggering HTR-Failure.


AB 139


Training DOCTR 039

Detailed Operation

Heating System

AB 139


Training DOCTR 039Heating system operation:Added to the cockpit and cabin ventilation system, this configuration includes theheating functions which consists of the elements shown here below.

The Heating Control Box and the Cockpit Control Panel control the proper functionof the heating system and provides alarm and overheat protection.

The basic heating system uses bleed air from the compressor discharge port ofeach engine. The bleed flow is limited down to 2% of the total air flow of eachengine by restrictions.

The bleed air is routed from each engine port to a Shut-Off Valve (1). Check valve(2) avoids any back flow from one engine to the opposite engine.

ENG1

ENG2

SOV1 (1)

SOV2 (1)

TCV (4)

JP (5) ADTS (7) DOTS (8)

HCB (6)

CV2 (2)

CV1 (2)

BAD (3)

AMBIANT AIR

AB 139


Training DOCTR 039Heating system cont'dVia the Bleed Air Tubes BAD (3), hot engine air under high pressure isrouted to the Temperature Control Valve (4) which controls the quantity ofbleed air to be mixed in the Jet Pump (5) with the air outside ambient air.

An additional injector which by-pass the TCV enables the heating systemoperation with outside ambient conditions up to 15 C in case of TCVmalfunction .

The mixed airflow is controlled by the Heating Control Box (6) bycomparison between the blowing temperature measured by the Air DuctTemperature Sensor (7) and the selected temperature, given by theCockpit Control Panel potentiometer(9).

In case of overheat non-detected by this sensor, the Duct OverheatTemperature Switch (8) closes directly the shut-off valves.

The Shut-Off Valves and the Temperature Control Valve can also be controlled manually by the pilot via the Cockpit Panel (9).

The mixed air is ducted to the delivery distribution ducts (10).

AB 139


Training DOCTR 039 Heating systemHeating System Architecture:

COCKPIT PANEL

Air Duct Temp Sensor

Duct Overheat Thermal Switch

AFT - FV

FWD - FV

TCV SOV1

SOV2

FWD - FAN1

AFT - FAN2

FWD - FAN2

+28 Vdc2 0 Vdc2

+28 Vdc1 0 Vdc1

+ 5 Vdc DIMMING 0 Vdc DIMMING

HEATING CONTROL

BOX

+28 Vdc1 0 Vdc1

+ 5 Vdc DIMMING 0 Vdc DIMMING

1 Heater Failure

5 Heater on Forward ventilation on After ventilation on Ventilation Failure

ADTS

DOTS

* see acronyms in appendix 1 +28 Vdc2 0 Vdc2

+28 Vdc2

0 Vdc2 Maintenance connector

Ext. Air Temp Sensor

EATS

HELICOPTER

AFT - FAN1

* provision for ECS

configuration

Provision for forced ventilation

*

AB 139



Heating System Architecture:

J01J01

M+

-

TCV

J02J02TEMP. SENSOR 1

TEMP. SENSOR 2

THERMAL SWITCH

M+

-

FV 1

M+

-

FV 2

SOV 2

SOV 1

Hi speed

Low speed

FWD FAN 1Hi speed

Low speed

FWD FAN 2

+28 Vdc

GND +28 Vdc

COCKPIT PANEL

HEATERCONTROL BOX

+28 Vdc

+28 Vdc

+28 Vdc

+28 Vdc

Hi speed

Low speed

AFT FAN

+28 Vdc

+28 Vdc

+28 Vdc

+28 Vdc

A

B 4

3

1

2

A

B

A

B

AB 139


Training DOCTR 039


Temp - CTL1 - SIG

Temp - CTL1 - SUP

Temp - CTL1 - REF

AFT - FAN - CTL

AFT - FAN - ON

FWD - FAN - CTL

FWD - FAN - ON

AFT - FV - CMD - H

AFT - FV - CMD - L

FWD - FV - CMD - H

FWD - FV - CMD - L

A UTO - HTR - SEL

FWD FAN 1

FWD FAN 2

M

A FT FV

M

FWD FV1

HCB

HCB

12

10 11

41

8

9

+ 28 Vdc1

55 15

16 51

21

22

6

23 24

7

11

7

28

12

4 3 5

4 3 5

6

6

48

49

Selection and Speed Control

M F

D

Selection and Speed Control

M D

F

B

E

A

B

E

A

HELICOPTER 43

HTR Failu re

EATS 2 3

3 4

AFT FAN1 Selection and Speed

Control

M A

F

D

B

C

0 Vdc1 TEMP_CONTR

OFF

MAN V PWR2 HTR

AUTO

V PWR1

HIGH LOW ON

OFF HIGH LOW

ON OFF

PAX

V PWR1

HIGH LOW ON

OFF HIGH LOW

ON OFF

CREW

HIGH LOW ON

OFF HIGH

LOW ON

OFF

PAX/CREW V

PWR1

HIGH LOW ON

OFF HIGH

LOW ON

OFF

PAX/CREW V

PWR1

AFT FAN2 Selection and Speed

Control

M A

F

D

B

C

0 Vdc1

HELICOPTER 46 44

+28 Vdc2 0 Vdc2

45

J01

J01

M

FWD FV2 4 3 5 6

AB 139


Training DOCTR 039


V PWR2

H TR

SOV1 - CMD

SOV2 - CMD

AFT - VENTILATION

+ 5 Vdc DIMMING

FWD - VENTILATION

SOV1 - ON

SOV2 - ON

0 - 5v

LAMPS

cc protection

0 Vdc1

+28 Vdc1 V PWR1

SOV 1

SOV 2

V PWR2

LOGICS

0 Vdc DIMMING

FWD - FAN1 - FAULT FWD - FAN2 - FAUL T

VENT - FAILURE

TCV

HCB

A

B

A

B

SOV1

SOV2

C

FWD - FAN1

E

AFT - FAN 1 C

FWD - FAN2

HELICOPTER

3

39

38

2

53

29

54

30

48 34 49 35 44 50

25

32

40

47

15 34

40

14

9 36

DOTS

B

A

3 1 2

5

6

ADTS

37 5

TCV - CMD - OPEN - OUT

TCV - REF

TCV - CMD - CLOSE - OUT

TCV - CMD - OPEN - IN

TCV - CMD - CLOSE - IN

Sp eed option

4

8

TCV - FC 36

CASE GND 33

Heater on 0 Vdc2

31 20

26

+28 Vdc2

V PWR2

SOV1 - ON SOV2 - ON

3

1

2

TCV - FC

TCV - FO

M

CLOSE NORMAL CLOSE NORMAL

HTR AUTO/MAN

O FF AUTO/MAN OFF

SOV1

AUTO/MAN OFF AUTO/MAN OFF

SOV2 CLOSE NORMAL CLOSE NORMAL

+

+

-

- AUTO

AUT O

MAN/OFF

MAN/OFF

AFT - FAN1 - FAULT 43

E

AFT - FAN 2

MAINTENANCE CONNECTOR

8 9 13 7 5 4 6 12

17 18 26 10 37 50 38 39

J01

J01

* Forced ventilation configuration

* ECS configuration

AB 139



HCB - Control Principale:System control is achieved by an analog closed loop.

The loop controls the temperature by comparing a reference which isset by the pilot with the real temperature measured by theTemperature Sensor.

The error thus obtained via un internal logic drives the TemperatureControl Valve, taking care to avoid excessive overheating of theHeating Ducts.

The comfort in the cabin is adjust by the pilot who adapts the blowingtemperature as a function of outside conditions, thermal loads in thecabin, etc...

AB 139



Heating/Ventilation System Logic

AB 139


Training DOCTR 039

Forward Ventilation :

If cockpit fans are operating, then the control panel sends the " ForwardVentilation On " discrete signal to the helicopter general displayer (MAU).

After Ventilation : If cabin fan is operating, and cabin flapper valves are not fully closed; thenthe control panel sends the " After Ventilation On " discrete signal to thehelicopter general displayer (MAU).

Ventilation Failure: If AFT-FAN-FAULT is active or FWD-FAN1-FAULT is active or FWD-FAN2-FAULT is active , then the control panel sends the " Ventilation Failure" discrete signal to the helicopter general displayer.

Heating system

Heating/Ventilation System Logic Description:

AB 139



Heating/Ventilation System Logic Description cont'd: Ventilation Failure: The Cockpit and cabin flapper valves even failed closed are NOT triggering theVentilation failure.

Heater On: If SOV1 open command is active or SOV2 open command is active; then thecontrol panel sends the " Heater On " discrete signal to the helicopter generaldisplayer.

Heater Failure:If DOTS is open ( T 85 C ) , or regulated temperature is incorrect and HTRselected, or others electronic conditions as EATS broken (open circuit) and Temp.Potentiometer defect (open circuit); then the HCB sends the " Heater Failure "discrete signal to the helicopter general displayer.

Nota: Air COND selection is associated to three additional signals (ForwardVentilation On, After Ventilation On and NO Ventilation Failure).

AB 139



HCB Logic Functions:

HEATER-Failuresignal is sent to Modular Avionic Unit(MAU):

if [(SOV1 is open or SOV2 is open) and (Duct Overheat Thermal Switch(DOTS) is active then the " Heater Failure " discrete signal shall be sent tothe helicopter general displayer (MAU).

if { [HTR is selected and (SOV1 is open or SOV2 is open)] and [(Ducttemperature sensor is in open circuit or External temperature sensor is inopen circuit or potentiometer is in open circuit)] } then the " Heater Failure "discrete signal shall be sent to the helicopter general displayer (MAU).

AB 139



HCB - TCV control logic:

- if { [HTR is selected and (SOV1 is open or SOV2 is open)] and [faultconditions are all inactive] then (TCV power stage is controlledaccording to PWM signal and error sign signal) else wise (TCV powerstage is activated at maximum speed to close TCV).

The HCB close Flapper Valves with following logic:

- AFT FV and FWD FV power stages are activated during at least 15seconds to close both Flapper Valves after HTR selection(independently of SOV status)

AB 139



HCB Failure Logic: To memorized following failures for maintenance operation:- Duct Overheat Thermal Switch (DOTS) has been activated more than 8seconds in automatic heater mode.

- External Air Temperature Sensor (EATS) has been during 15 seconds in openstate permanent condition in automatic heater mode.

- Air Duct Temperature Sensor (ADTS) has been during 15 seconds in openstate permanent condition in automatic heater mode.

- Temperature selection potentiometer (CTL1 FAULT) has been during 15seconds in open state permanent condition in automatic heater mode.

NOTA : Memorized fault signals must be read and reseted using SpecialFailure read-out Box 92599A010000.

AB 139


Training DOCTR 039 Heating systemHCB ANALOG FUNCTIONS- To limit maximum duct air temperature to T max : 72.5 C +/- 2.5 C.- To make temperature reference acquisition on 10 K potentiometer with +/- 2%accuracy. Complete potentiometer range is corresponding to -10 C/90 C includingfailure analysis.

- To make temperature acquisition on EATS (-50 C to 50 C) and on ADTS (-10 Cto 90 C) including failure analysis.

-To regulate duct air at selected temperature 5 C in normal automatic conditions,in function of External Air Temperature Sensor ( EATS ) using PWM motor drive onTCV actuator.

Regulation law:

T regulation=T external + alfa(Tselected) + (40 C +/-5 C) if T regulation < T max

- HCB failure detection logic for temperature sensor and potentiometer:

Potentiometer open circuit: temperature reference > 85 C

Sensor open circuit: external temperature > 45 C or duct temperature > 80 C

AB 139



TEMPERATURE CONTROL1

FAULT

MODUL

ADTS

DOTS

TCV OPEN

AUTO-HTR-SEL

HTR-FAILURE

FAULT MEMORY

DOTS FAULT MODUL

ADTS FAULT MODUL

EATSEATS

FAULT MODUL

CTL1 FAULT MODUL

TEMPERATURECONTROL1

SOV1 ON

TCV CLOSE

SOV2 ON OR

AND

+

- 0,5

-ADTS PID PWM

MODUL

TCV-FC

TCVCONTROL

MODUL

FV CONTROL

MODUL

AFT-FV-CLOSE

FWD-FV-CLOSE

FAULT-READFAULT-RESETFAULT-TEST

EATS

AB 139



Heating System

Main Component description

AB 139



92177A020000

AB 139



Heating Control Box 92177A020000:The HCB drives the Heating system. It monitors the sensors and warns thecrew when a fault occurs.

The Electronic Control Box is an analog & logic array card fitted inside ametallic housing.

The following equipments are interfacing with the HCB:- Temperature Sensors ADTS (PT1000) and EATS (PT500 supplied byAugusta) ,

- Potentiometer (Cockpit Panel - 10 K ),

- Thermal Switch DOTS,

- Cockpit Control Panel (ventilation/air-conditioning selected/available),

- Modular Avionic Unit ( MAU for failure triggering),

- Temperature Control Valve control via Cockpit Control Panel .

AB 139



Helicopter harness Maintenance connector using Test box 92599A010000:- memorised failure/s is/are sent on the maintenance bus and can be indicated on the Test Box,

Heating Failure read out box Flow chart Heating Failure read out box cont.

AB 139



Heating Control Box HCB general view:

AB 139


Training DOCTR 039 Heating systemHeating Control Box Pin Location:

AB 139



Heating Control Box Pin Location:

TWO TW From EATS

To

Maintenance

Connector

PIN ITEM TYPE NOM. / MAX CURRENT

WIRE FROM / TO

2 EATS- SIG Analog Input 5 / 10 mA

3 EATS- REF Analog Input 5 / 10 mA SH CORE

17 ADTS-FAULT 5v / OC 2 / 10 mA SINGLE CORE

18 CTL1-FAULT 5v / OC 2 / 10 mA SINGLE CORE

26 TS-FAULT 5v / OC 2 / 10 mA SINGLE CORE

10 EATS-FAULT 5v / OC 2 / 10 mA SINGLE CORE

37 FAULT-RESET 5v / OC 2 / 10 mA SINGLE CORE

50 FAULT-TEST 5v / OC 2 / 10 mA SINGLE CORE

38 FAULT-READ 5v / OC 2 / 10 mA SINGLE CORE

39 ENABLE 5v / OC 2 / 10 mA SINGLE CORE

AB 139



Shut Off Valve SOV 6916A020000:Function:The valve shuts off the engine hot air supply of the high pressure bleed ductingwhen heating is not selected by the pilot or forbidden for safety reasons.

The valve is a fail safe component (in close position).

Description:The shut-off valve is a solenoid operated in-line valve. A piston acting as a valvedisplaces inside a cylinder, machined in a 1 inch diameter body.

The piston is kept at rest against its seat by a spring.

When energized, the solenoid vents air from the valve servo-chamber, thuscausing piston to open. Valve remains open as long as solenoid is energized.

When solenoid is de-energized, puppet valve shuts vent port and opens pressureport, compressed air through a filter pushes piston against the seat to closeposition.

Piston rings avoid too large internal leakages.

AB 139



Shut Off Valve - SOV

Characteristics:Nominal power supply: 28 Vdc

Current consumption: 0,4 A

Opening /closing time 3 s / 4 s

Operating pressure min/max: 0,7 bar/15 bar

Normal operating temperature: 403 C up to max. 436C for a short time

Surrounding temperature: -40C to +150C up to max. 180C

Storage temperature: -55C to + 85C

Weight: 1100 g

AB 139


Training DOCTR 039 Heating systemShut Off Valve - SOV Pin Location (idem for SOV2):

Overall view:

(GND)

AB 139



High Pressure Check Valve 2298A020000:It prevents the potential one engine discharge towards the other in case of strong pressure misbalance (one engine off, lower engine rate) between the 2 engines. The check valve with a 1 inch diameter, is a non return valve connected to the bleed ducting branch close to the engine port. This is a double flap stainless steel check valve.

Similar check valves are already used on Jaguar, Tornado and Eurofighter Aircraft.Characteristics:Normal operating temperature (short time): 231C (270C) up to 403C (436C) max.

Ambient temperature: -40C to +130C

Storage temperature: -55C to + 85C

Weight: 50g

Internal leakage closed in non return position:

AB 139



HP - Check Valve general view:

AB 139



Temperature Control Valve TCV 14422A030001:Function:The temperature control valve is driven either by the pilot in Manual or by theHCB in Auto mode.

It modulates the amount of hot air to be injected in the jet pump to control theheating temperature for the cockpit and cabin zone.

Description:The temperature control valve body, is a cylindrical carbon plug valve with stainless "1" inch steel body.

It is driven by an electric actuator mounted on an insulated base to limit the thermalconduction towards the actuator.

AB 139



Temperature Control Valve TCV:Description cont'd:The valve is composed of : a stainless steel body with machined female ports,

a cylindrical carbon plug,

a shaft which transmits the rotational movement of the plug by a tenon-mortise type drive,

a spring washer which pushes the plug and the shaft onto the seal,

a cap to maintain the spring.

The tightness at the bearing is ensured by a seal.

The tightness on the cap is ensured by the lip which is an integral part of the cap.

An electrical heating muff covers the valve body and is automatically supplied by28Vdc in case of sub-zero temperatures.

Two thermo switches control the electrical supply of the heater.

AB 139



Temperature Control Valve - TCV:Characteristics:Nominal supply voltage : 28 VDC (limit 17 Vdc to 32 Vdc)

Current consumption : < 0.6 Amp (1.8 Amp with heating)

Maximum operating pressure : 12.7 bar

Maximum operating temperature : 436 C

Ambient operation temperature : - 40 C to + 130 C

Opening, closing time : 4 s

Internal leakage under 12 bar rel. pressure: < 12 l/mn

Weight: 700 g

AB 139



Temperature Control Valve 14422A030001 TCV general view:

AB 139



Temperature Control Valve Pin Location :

AB 139



Jet Pump 428B010000:Function:The jet pump is the heating system hot air generator.

It produces a hot air flow using temperature and pressure of engine bleed air.

The expansion of bleed air at high pressure and temperature through the injectorsucks and warms up a large amount of outside fresh air.

The generated hot air flow is therefore a mixture of extremely hot engine bleed airand external fresh air.

Bleed flow

Outside fresh air Mixed air

AB 139



Jet Pump:Description :

A Composite Mixing Unit (a venturi and a mixing chamber in one assy)

A twin stainless steel Injector An insulation plate installed between Mixing unit and Injector

The main components of the Jet Pump are:

The jet pump provides sufficient heat to cockpit and cabin using HP enginebleed air (maximum 2% of each engine).

A tube directly connected to the injector of the Jet Pump, by-passes the TCVif failed closed. This ensures a minimum temperature of 18 C and providescomfort to the cockpit and cabin within the full flight envelop:

Altitude [0-20000ft] , External temperature [-40,+50 C]

The calculated heat power of the jet pump is 13 kW .

AB 139



Jet Pump:Characteristics:Maximum operating pressure - Mixing Unit: 0,1 bar above atmosphere

Maximum operating pressure - Injector: 12.0 bar

Maximum operating temperature - Mixing Unit: 85 C (short time 120 C)

Maximum operating temperature - Injector: 403

Max. short time operation temperature: 436 C

Mixing Unit flow rate: 500 g/s

Injector flow rate: 170 g/s

Ambient operation temperature : - 40 C to + 85 C

Weight: 0,9 Kg

AB 139



Jet Pump general view:

Mixing Unit

Injector

By-pass tube

ADTS location

AB 139



HP Ducts & Insulation Jackets:

- the engine compartment for P/N 12758A010000 and 12759A010000

- the tail rotor compartment for P/N 12760A010001 and 12761A010001

Functions:The high-pressure ducting is used to supply air from the two engines bleedports to the jet pump.

It interfaces with the shut off valves, the check valves and the temperaturecontrol valve.

The ducting crosses the upper deck firewall and 2 different parts of thehelicopter:

AB 139



HP Ducts & Insulation Jackets:Description: P/N 12758A010000 & 12579A010000

Flexible hoses located in the engine compartment. The hose willcompensate engine displacement and vibration.

The duct is connected

- to the engine ports with an orifice plate to limit the bleed flow to 2% ofthe total engine flow

- to the shut off valves

P/N 12760A010001Rigid duct located underneath the engine department connected to the shut offvalves through a SM coupling and including the support flange of the check valve.

AB 139



HP Ducts & Insulation Jackets cont'd:Description: P/N 12761A010001

Rigid duct located underneath the engine compartment including a Teejunction and a flexible hose to compensate thermal growth and pressureloads. The duct is connected to the Temperature control valve andincludes the check valves supporting flanges.Maximum operating condition: 12 bar at 230 C or short time 11,7 bar at436 C

HP Duct12761A010001

HP Duct12758A010000

HP Duct12760A010001

HP Duct 12759A010000

AB 139



HP Ducts & Insulation Jackets:

The ducts located underneath the engine compartment (P/N 12760A01 &12761A01) are insulated to limit their skin temperature at 200 C, underfuel flammability.

The ducting is covered with Velcro fastenings insulation jackets, made of :

Nomex fabric coated on one side with viton Long needled glass fibers Glass fabric impregnated of viton product

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ADTS Air Duct Temperature SensorFunction:

The sensors are providing a temperature information to the HCB (Heating ControlBox):

- The ADTS measures the output temperature of the Jet Pump,- The EATS (supplied by Augusta) measures the external air temperature upstreamfrom the Jet Pump.

The HCB use the temperature information from both sensors and compares it withthe temperature demand coming from the Cockpit Panel potentiometer.

Thus to adjust the TCV flap position to obtain the desired ambient temperature inthe cockpit and cabin zone of the helicopter.

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ADTS Air Duct Temperature Sensor 92260A010000:

Description:Single Sensitive element allowing air to be circulated directly to themeasurement component housing whit an optimum response time andaccuracy. The ADTS is installed on the jet-pump.

CharacteristicsOperating temperature range: - 40 C to + 125 C

Storage temperature range: - 55 C to + 125 C

Type : PT1000

Accuracy: 0 C to +85 C 1 C

Response Time with flow 5 m/s: 15 seconds,

for 50 m/s: 6 seconds.

Weight: 100 g

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ADTS Air Duct Temperature Sensor Pin Location:

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EATS Ext. Air Temperature Sensor Pin Location:The EATS installed upstream of the jet pump and represent the same characteristic than the ADTS.

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DOTS - Duct Overheat Thermal Switch 92252A010000:

Description and operationIt is composed of a housing, a bimetallic thermal switch and an electricalconnector welded on the housing.

The thermal-switch is installed downstream of the jet pump.

In case of duct temperature overheat, the thermal-switch opens thecontact at a preset threshold of 85 C +/- 2 C (close at 70 C +/- 5 C) andclose the shut off-valve.

Characteristic 28Vdc - Single contact switch, normally closed

Nominal current: < 0.7A

Weight: 68 g

Operating range -40 C to +204 C

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DOTS - Duct Overheat Thermal Switch Pin Location:

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Cockpit and Cabin fans, please refer to Ventilation chapter

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Training DOCTR 039

HEATING SYSTEM TROUBLE SHOOTING PROCEDURE

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Training DOCTR 039

Heating System trouble shooting using

Break-out box BOB - P/N92612A010000

and

Heating Test Box - HTB -P/N92599A010000

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Training DOCTR 039

Heating and Ventilation System trouble shooting

Test which should be performed prior to a ground run, in the hangar with 28Vdc power supply (ground cart) and HEATER

OFF mode selected on Cockpit Panel :

Check correct function of the cockpit ventilation refer to Ventilation trouble shooting chapter.

Note 1 : Check cockpit ventilation/distribution system with pedestral cockpit outlets "OPEN" (front face gaspers closed)

Note 2 : The cabin heating distribution system, powered by the jet pump is completely seperated from the CABIN ventilation system.

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Training DOCTR 039

IN HANGAR Heating and Ventilation System trouble shooting:Read out the HCB memorised fault, connect the Heating system test box P/N 92599A010000 to the helicopter harness maintenance connector.

Result :No failure memorised in HCB to confirm correct operation of the heating system continue with a ground run

Control fault, EATS, ADTS and/or DOTS fault memorised interconnect the Break out Box P/N 92612A010000 in-between Cockpit Panel and HCB, for further investigation.

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Training DOCTR 039

Control fault :Select Auto Mode on cockpit panel and check AUTO HTR SEL Break out box green led "On (GND output Jumper - 41), continue trouble shooting during ground run.

Break out box green led "Off", check wiring, connection and 28Vdc power supply (between jumper 25 and 32), to Cockpit Panel,

Check Cockpit panel power supply - if O.K. replace Cockpit panel.Potentiometer check Use Ohmmeter between Jumper 11 and 12:

Potentiometer Min cold position 0

Potentiometer Middle position 5 K

Potentiometer Max warm position 10 K

Switch back to OFF Mode (Auto mode = OFF)

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Training DOCTR 039

External Air Temp. Sensor EATS fault (supplied by Augusta) :Check OAT if higer than 45C - no maintenace action required,Check wiring and connection between HCB and EATS,Check temp. Sensor resistance refer to helicopter maintenance manuel

0C = 500 Ohm + (1.925 Ohm per 1C).

Example for 20C : 500 Ohm + (1.925 Ohm x 20C) = 538,5 Ohm replace if out of range

If temperature sensor O.K. contd. trouble shooting during ground runNote : EATS - Pin connection 3 and 4.

Test procedure:

Disconnect the helicopter wiring from the HCB. Connect the BOB to the helicopter harness which goes to the EATS: Measure the temperature value between jumper 2 and 3.

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Training DOCTR 039

Air Duct Temp Sensor ADTS fault:Check wiring and connection between HCB and ADTS,Check temp. Sensor resistance refer to CMM

0C = 1000 Ohm + (3.85 Ohm per 1C).

Example for 20C : 1000 Ohm + (3.85 Ohm x 20C) = 1077 Ohm replace if out of range

Note :

ADTS - Pin connection A and B.

Test procedure:

Disconnect the helicopter wiring from the HCB. Connect the BOB to the helicopter harness which goes to the ADTS : Measure the temperature value between jumper 5 and 6.

If temperature sensor O.K. contd. trouble shooting during ground run

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Training DOCTR 039Duct Overheat Thermal Switch DOTS fault :Check electrical continuity between HCB and DOTS, using ohmmeter :

a) open circuit - check wiring, connection and switch repair/replace faulty element,

b) close circuit check TCV position (refer to TCV functional check)

Test procedure:

Disconnect the helicopter wiring from the HCB. Connect the BOB to the helicopter harness which goes to the DOTS: Measure prescence of 28Vdc between jumper 36 and 44 or disconnect the wiring/connector from the DOTS and measure the continuity between Pin A and B.

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Training DOCTR 039Functional check of the SOV, prior to ground run (power supplied by ground cart or battery). Note: Interconnect the Break out Box P/N 92612A010000 in-between Cockpit Panel and helicopter harness for further investigation.

Switch to MAN on the Cockpit Control Panel, Check one by one the SOV 1 + SOV 2 opening/closing:

SOV 1 + 2 position "Normal" selected on cockpit panel

a) Check break out box corresponding green leds ON - SOV must open audible click (28Vdc supplied either to SOV 1 Jumper 53, or SOV 2 Jumper 54)

b) If SOV 1 (2) not opens no audible click with green led ON - Check wiring, connection and correct power supply to solenoid valve - replace faulty element or SOV

c) If valve green led is not ON , check wiring, connection and correct power supply to the Cockpit Control Panel, - if O.K, replace Cockpit Panel

SOV 1 + 2 position "Close" selected on cockpit panel

a) SOV 1 (2), Check break out box corresponding green leds goes OFF

b) SOV 1 (2) close - continue trouble shooting during ground run

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Training DOCTR 039Functional check of the TCV prior to ground run (28Vdc supplied by ground cart): HMV on Cockpit panel = TCVCheck the TCV opening/closing:

TCV turn the Temp Contr Rotary toggle switch to (TCV close) on cockpit panel

a) TCV break out box green led remains "OFF" check TCV-CMD yellow led on BOB (Jumper 39), should be illuminated as long as toggle switch activated - check wiring, connection and correct 28Vdc power supply to the valve - replace faulty element

b) Check break out box BOB-TCV Full Close green led "ON" (Jumper-36),

TCV push the toggle switch to + (open) on cockpit panel

a) check TCV-CMD green led on BOB (Jumper 38) + audible TCV motor noise, if not check wiring, connection and correct 28Vdc power supply to valve - replace faulty element

b) TCV open drive it to close position and continue trouble shooting during ground run

REFER TO NEXT PAGE FOR GROUND RUN - SYSTEM OPERATION

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Training DOCTR 039

Heating and Ventilation System operational test during Ground Run (break out and failure read out box connected)

WARNING :

DO NOT OPERATE BLEED AIR HEATING SYSTEM WHEN OUTSIDE AIRTEMPERATURE IS ABOVE 45C.

1)Make sure that Heating Outside Air Intake is not fully or partially blocked by any foreign objects

2)Make sure that the Cockpit Panel is in correct initial selection:HEATER mode OFF (SOVs are closed as long as Heater Mode OFF selected.

Heater mode Man and Auto selected SOVs are Open )

HTR AUTO MINVENT Crew Fan - OFFVENT Pax Fan OFFSOV 1 + SOV 2 CLOSE

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Training DOCTR 039

3)Pedestral cockpit gaspers fully open, front face gaspers fully closed.

4)Start engines and operate them at 75% thrust.

5)Switch to MAN on the Cockpit Control Panel

6)Set SOV 1 to Normal position (BOB [Jumper-53] Green led "ON").

Check Heating "On" advisory legend comes in view on MAU.

SOV 1 does not open (no warm air flow):

Check wiring, connection between Cockpit Panel and SOV 1, repair as necessairy (search for a fase contact), if O.K.

Check correct power supply to Cockpit panel (search for a false contact - if O.K. - replace SOV 1

No power supply to Cockpit panel

Check wiring and connection if O.K. -replace Cockpit panel

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Training DOCTR 039

7) Set the SOV 1 to OFF position and VENT CREW FAN to LOW (warm air flow must stop).

If warm air flow does not stop - replace SOV 1 (stucked open)

8)Repeat above steps with SOV 2.

9)Using HTR MAN Rotary toggle switch, drive TCV to close position (BOB TCV-CMD [Jumper-39] Yellow led "ON and TCV Full Close [Jumper-36] Green led ON ).

Check the TCV closing:

TCV turn the HTR MAN Rotary toggle switch to (close) on cockpit panel

a) TCV break out box green led remains "OFF" check TCV-CMD yellow led on BOB (Jumper 39), should be illuminated as long as toggle switch is activated, if not - check wiring, connection and correct 28Vdc power supply to the valve - replace faulty element

b) Check break out box BOB-TCV Full Close green led "ON" (Jumper-36),

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Training DOCTR 039Contd. 9)

TCV does not close (despite to TCV CMD Yellow ) :

Check wiring, connection between Cockpit panel and TCV, repair as necessairy, if O.K. - replace TCV

TCV does not close (No -TCV CMD)

Check correct power supply to Cockpit panel, if

air conditioning liebheer

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