MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

CHAPTER

36
PNEUMATIC
 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

CHAPTER 36 PNEUMATIC
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CHAPTER 36 PNEUMATIC
TABLE OF CONTENTS

SUBJECT CH-SE-SU PAGE EFF

PNEUMATIC 36-00-00
General 1 ALL
System Description 1 ALL
DISTRIBUTION 36-10-00
General 1 ALL
System Description 1 ALL
ENGINE BLEED SYSTEM 36-11-00
General 1 ALL
System Description 1 ALL
Component Description 2 ALL
Control and Indication 3 ALL
System Operation 3 ALL
APU BLEED AND CROSSBLEED SYSTEM 36-12-00
General 1 ALL
System Description 1 ALL
Component Description 2 ALL
Control and Indication 2 ALL
System Operation 2 ALL

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 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

PNEUMATIC

1. General

The pneumatic system controls and supplies the bleed air that comes from the engine or the
auxiliary power unit (APU). It supplies it to the aircraft systems that use air.

2. System Description
The pneumatic system consists of the distribution system. Ref. 36-10-00.

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DISTRIBUTION

1. General

The distribution system controls and supplies the high pressure and high temperature bleed
air that comes from:
- The high and low stages of the engine
- The Auxiliary Power Unit (APU)
The distribution system supplies it to the aircraft systems that use air.

2. System Description
The distribution system includes:
- The engine bleed system. Ref. 36-11-00.
- The APU bleed and cross-bleed system. Ref. 36-12-00.
Ref. Fig. 001 for the schematic diagram of the distribution system.

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Hydraulic Tank APU Hydraulic Tank

Pressurization 7 To 接手动开关
Pressurization
液压油箱增压系统
System To接手动开关
Manual Cock Manual Cock 接手动开关
To Manual Cock System
液压油箱增压系统
8
8 10
1 2 9 8 1
S
P
2 S
P
3 3
6 6
R
右 接手动开关
To L左
发动机 10 Manual 发动机
Eng Cock Eng
4 5 5 4

Pneumatic
气动除冰系统 右侧空调系统
Right Air 左侧空调系统
Left Air 气动除冰系统
Pneumatic
De-icing Conditioning Conditioning De-icing
System System System System

Figure 001 Distribution system - Schematic diagram

1. High-pressure Temperature Switch; 2. High-pressure Bleed Valve; 3. High-pressure Bleed

Duct Compensator; 4. Low-pressure Bleed Check Valve; 5. Low-pressure Bleed Duct
Compensator; 6. Bleed Over-temperature Switch; 7. Load Control Valve; 8. APU Bleed Duct
Compensator; 9. APU Bleed Check Valve; 10. Cross-feed Valve.

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ENGINE BLEED SYSTEM

1. General

The engine bleed system has a left bleed system and a right bleed system. They control and
supply the high-temperature and high-pressure air that comes from the high and low stages of
the left and right engines. The engine bleed system supplies air to the aircraft systems that
use air.

2. System Description
Ref. Table 001 for the location of the components of the engine bleed system.
Ref.Table 002 the power supply of the engine bleed system.
Table 001 Engine bleed system - Component location
Ref. Component Type Q.ty Location Zone /Access
Engine high-stage
High pressure Bleed bleed port between FR
1 785804-3 2 433, 434
Valve 9 and FR 10 in left and
right engine nacelles
Engine high-stage
High pressure bleed port between FR
2 750659-14 2 433, 434
Temperature Switch 9 and FR 10 in left and
right engine nacelles
Bleed air Left and right engine
3 Over-temperature 750659-10 2 nacelles between FR 433, 434
Switch 10 and FR 11
Left and right engine
High pressure bleed
4 QWB-17 2 nacelles between FR 433, 434
duct compensator
10 and FR 11
Left and right engine
Low pressure bleed
5 QWB-18 2 nacelles between FR 433, 434
duct compensator
10 and FR 11

Table 002 Engine bleed system - Power supply (circuit breakers)

Component Location
Left Engine
High pressure Bleed Valve and Indicating light LH DC C/B PNL
Right Engine
High pressure Bleed Valve and Indicating light RH DC C/B PNL

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3. Component Description
The engine bleed system is divided into a left engine bleed system and a right engine bleed
system. It has these components:
- High pressure bleed valves
- High pressure temperature switches
- Bleed air over temperature switches
- High pressure bleed duct compensator
-Low pressure bleed duct compensator
- Duct accessories.

A. High Pressure Bleed Valve

The high pressure bleed valve is installed in the air conditioning duct at the high-stage
bleed ports of the left and right engines. It supplies or stops the flow of high-pressure
bleed air.
The high pressure bleed valve is a pneumatic solenoid valve. It opens or closes
automatically in relation to the specified output pressure value. The specified outlet
pressure value is P=1.36 Pa+276 kPa. It changes in relation to the atmospheric pressure.
If the pressure of the high pressure bleed air is more than the specified value, the valve
will close automatically. Thus the bleed system will use bleed air from the engine
low-stage. When the pressure of the high pressure bleed air is less than the specified
value, the valve will open automatically. Thus the system will use the high-stage bleed air
again.
The micro-switch sends a 28 VDC close/not-close signal when the valve opens or closes.
B. High Pressure Temperature Switch
The high pressure temperature switch is installed upstream of the high pressure bleed
valve. When the bleed air temperature is more than 274°C±2.8°C(525.2°F±37.04°F), the
high pressure temperature switch and the high pressure bleed valve will close. When the
bleed temperature decreases, the high pressure bleed valve will open automatically.
C. Bleed Air Over temperature Switch
The bleed air over temperature switch is installed downstream of the high-pressure bleed
valve. When the bleed temperature is more than 288°C±5.6°C(550.4°F ±42.08°F), the
bleed air over temperature switch and the high pressure bleed valve will close. If it is
necessary to open the high-pressure bleed valve again:
- Close the manual switch of the high pressure bleed air valve manually
- Open the valve.
D. High Pressure Bleed Duct Compensator
The high pressure bleed duct compensator is installed in the duct of the high-stage bleed
port of the left and right engines. It adjusts for the duct deformations and displacements
that the engine vibrations can cause. It also adjusts for the axial displacements that the
changes in the duct temperature can cause.

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E. Low pressure Bleed Duct Compensator

The low pressure bleed duct compensator is installed in the duct of the low-stage bleed
port of the left and right engines. It adjusts for the duct deformations and displacements
that the engine vibrations can cause. It also adjusts for the axial displacements that the
changes in the duct temperature can cause.

4. Control and Indication

Ref. Fig.001.
The control switch and the indicating light of the engine bleed system are installed on the
environmental control panel on the top of the Flight Compartment.
The “HIGH PRESS” switch on the environmental control panel controls the engine high
pressure bleed air. The amber “CLOSED” indicating light on the switch comes on or goes off
to show the closed or open condition of the high pressure bleed air valve.

5. System Operation
The bleed air for the air conditioning system usually comes from the engine low-stage (P2.5).
When the engine is at idle and the low-stage bleed pressure is not sufficient, the high
pressure bleed valve will open automatically. The check valve of the low-stage bleed port will
close because of the force of the high pressure bleed air. Thus the system will operate to use
the bleed air from the high-stage (P3.0). When the engine bleed-air temperature is more than
274°C±2.8°C(525.2°F±37.04°F), this will occur:
- The high pressure temperature switch upstream of the high-pressure bleed valve will close
- The high-pressure bleed valve will close.
When the bleed air temperature decreases, the high pressure bleed valve will open
automatically.
When the bleed-air temperature is more than 288°C±5.6°C(550.4°F±42.08°F), this will occur:
- The bleed air over-temperature switch downstream of the high pressure bleed valve will
close
- The high pressure bleed valve will close.
If it is necessary to open the high pressure bleed valve again, close the switch of the
high-pressure bleed valve manually and then open the valve.
The high pressure bleed air valve automatically controls the pressure value of the
high-pressure bleed air. The outlet pressure value is calculated as P=1.36 Pa+276 kPa. It
changes in relation to the atmospheric pressure (Pa). If the outlet pressure of the
high-pressure bleed valve is more than the specified value, the valve will close automatically.
The bleed system will thus use bleed air from the engine low-stage. When the outlet pressure
of the valve is less

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Figure 001 Environmental Control panel

(See the NOTE on next page )

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NOTE:
1. Flight Compartment high-pressure over-temperature fully-closed indicating light; 2. Flight
Compartment over-temperature fully-closed indicating light; 3. Cross-feed fully-open
indicating light; 4. Cabin high pressure over-temperature fully-closed indicating light; 5. Cabin
over-temperature fully-closed indicating light; 6. Flight Compartment high-pressure switch; 7.
Cockpit bleed trip off switch; 8. Cross-feed switch; 9. Cabin high-pressure bleed switch; 10.
Cabin bleed trip off switch; 11. Flight Compartment over-pressure fully-closed indicating light;
12. Cabin over-pressure fully-closed indicating light; 13. Left cross-feed indicating light; 14.
Left cross-feed switch; 15. Flight Compartment pressure-regulation switch; 16. Cockpit
economic flow switch; 17. Flight Compartment maximum flow switch; 18. Cabin pressure
regulation switch; 19. Cabin economic flow switch; 20. Cabin maximum flow switch; 21. Flight
Compartment heat indicating light; 22.Cockpit cool indicating light; 23. Cabin heat indicating
light; 24. Cabin cool indicating light; 25. Flight Compartment Zone Temperature Control
AUTO/MANUAL switch; 26. Flight Compartment zone temperature control HEAT/COOL
switch; 27. Flight Compartment recirculation fan switch; 28. Cabin Zone Temperature Control
AUTO/MANUAL switch; 29. Cabin Zone Temperature Control HEAT/COOL Switch; 30. Cabin
Recirculation fan switch; 31. Flight Compartment temperature selection knob; 32. Cabin
temperature selection knob.

than the specified value, the valve will open automatically. The system will thus use the
high-stage bleed air again.
When the electrical power is supplied to the system, the amber “CLOSED” indicating lights
(related to the left and right “HIGH PRESS” switches) on the Environmental control panel will
come on. When the engine is started and the power is less than idle but pneumatic air is
necessary to operate the downstream systems, this will occur:
- The high pressure bleed valve will open
- The amber CLOSED indicating light will go off.
When the engine power is more than idle, this will occur:
- The high pressure bleed valve will close automatically
- The amber CLOSED indicating light will come on.
- The system will use bleed air from the engine low-stage.

Disconnect the HIGH PRESS switches of the left and right engine bleed systems. The amber
CLOSED indicating lights will come on.

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APU BLEED AND CROSSBLEED SYSTEM

1. General

The APU bleed and crossbleed system can supply bleed air on the ground or during flight to
these systems:
- The air conditioning system
- The pneumatic anti-ice system.

2. System Description
Ref. Table 001 for the location of the components of the APU bleed and crossbleed system.
Ref. Table 002 for the power supply of the APU bleed and crossbleed system.
Table 001 APU bleed and crossbleed system - Component location
Zone
Ref. Component Type Q.ty Location
/Access
Right engine nacelle
APU bleed check
1 778696-1 1 between FR 14 and 434
valve
FR 15
Right engine nacelle
between FR 19 and
APU bleed duct 442, 512,
2 QWB-21 3 FR 20 of left/right
compensator 612
center wing leading
edge
In left top cowling
between FR 15 and
FR 17 of the fuselage
3 Crossfeed Valve 790420-2 2 273, 434
and right engine
nacelle between
FR 12 and FR 13

Table 002. APU bleed and cross-bleed system - Power supply (circuit breakers)
Component Location
Left Engine
Left crossfeed valve and indicator light LH DC C/B PNL
Right Engine
Right crossfeed valve and indicator
RH DC C/B PNL
light

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3. Component Description
A. APU bleed check valve
The APU bleed check valve is installed at the APU bleed inlet to prevent a change in the
direction of the engine bleed-air flow.
B. APU bleed duct compensator
The APU bleed duct compensators are installed as follows:
- In the APU bleed ducts in the right nacelle
- In the air conditioning bleed duct at the left and right center wing leading-edges.
They adjust for the duct deformation and displacement that the engine vibrations can
cause. They also adjust for the axial displacements that the changes in the duct
temperature can cause.
C. Crossfeed Valve
The crossfeed valve is a pneumatic solenoid valve. It operates when the APU supplies air
or when there is the failure of one engine. The operation mode is as follows:
- When the electrical power is supplied, the crossfeed valve will open because of the
force of the engine or APU bleed air pressure.
- When the electrical power is removed, the crossfeed valve will close.
The micro-switch sends a 28 VDC close/not-close signal when the valve opens or closes.

4. Control and Indication

The location of the APU bleed switch is on the APU start control panel on the top of the Flight
Compartment. When the APU bleed switch is set to “ON”, this will occur:
- The load control valve at the APU bleed outlet will open.
- The related green signal light will come on.
The location of the left and right crossfeed switches and indicator lights is on the ECS control
panel on the top of the cockpit. When the crossfeed switch is set to “ON”, this will occur:
- The related crossfeed valve will open.
- The related green “OPEN” signal light will come on.

5. System Operation
If the failure of one engine occurs on the ground or during flight, the APU will supply the bleed
air for the air conditioning system.
The left and right crossfeed valves connect the left and right engine bleed systems. Usually,
these valves are closed. The applicable crossfeed valve will open when:
- The APU supplies air to the two refrigeration components on the ground.
- One engine supplies air to the two refrigeration components.

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- The APU supplies air to one refrigeration component because one engine becomes
unserviceable during flight.
The APU can supply bleed air to the air conditioning system and the pneumatic anti-ice
system on the ground or during flight.
When you start the APU and open the APU bleed switch and the left/right crossfeed switches:
- The left/right crossfeed valves will open.
- The APU bleed air will flow into the left/right air conditioning systems and the left/right
pneumatic anti-ice systems.

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