MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

CHAPTER

30
ICE AND RAIN
PROTECTION
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CHAPTER 30 ICE AND RAIN PROTECTION

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CHAPTER 30 ICE AND RAIN PROTECTION

TABLE OF CONTENTS

SUBJECT CH-SE-SU PAGE EFF

ICE AND RAIN PROTECTION 30-00-00
General 1 ALL
System Operation 1 ALL
AIRFOIL DEICING 30-10-00
General 1 ALL
System Description 1 ALL
AIRFOIL DEICING CONTROL 30-11-00
General 1 ALL
System Description 1 ALL
System Components 3 ALL
System Operation 5 ALL
WING DEICING 30-12-00
General 1 ALL
CENTER WING LEADING EDGE DEICING 30-12-10
General 1 ALL
System Description 1 ALL
System Operation 1 ALL
INBOARD WING LEADING EDGE DEICING 30-12-20
General 1 ALL
System Description 1 ALL
System Operation 1 ALL
OUTBOARD WING LEADING EDGE DEICING 30-12-30
General 1 ALL
System Description 1 ALL
System Operation 1 ALL
STABILIZER DEICING 30-13-00
General 1 ALL
System Description 1 ALL
System Operation 2 ALL
AIR INTAKE DEICING 30-20-00

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CHAPTER 30 ICE AND RAIN PROTECTION

TABLE OF CONTENTS

SUBJECT CH-SE-SU PAGE EFF

General 1 ALL
System Description 1 ALL
System Components 2 ALL
System Operation 6 ALL
AIR INTAKE DEICING CONTROL 30-21-00
General 1 ALL
System Description 1 ALL
System Operation 2 ALL
SENSOR HEATING 30-30-00
General 1 ALL
PITOT/PITOT PROBE HEATING 30-31-00
General 1 ALL
System Description 1 ALL
Controls and Indicators 2 ALL
System Components 2 ALL
System Operation 2 ALL
TOTAL AIR TEMPERATURE SENSOR 30-32-00
HEATING
General 1 ALL
System Description 1 ALL
Controls and Indicators 2 ALL
System Components 2 ALL
System Operation 3 ALL
AOA SENSOR HEATING 30-33-00
General 1 ALL
System Description 1 ALL
Controls and Indicators 2 ALL
System Operation 2 ALL
WINDOWS, WINDSHIELDS AND DOORS 30-40-00
General 1 ALL

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CHAPTER 30 ICE AND RAIN PROTECTION

TABLE OF CONTENTS

SUBJECT CH-SE-SU PAGE EFF

System Description 1 ALL
System Components 1 ALL
WINDSHIELDS/SIDE WINDOWS HEATING 30-41-20
SYSTEM
General 1 ALL
System Description 1 ALL
System Operation 2 ALL
WINDSHIELD WIPER SYSTEM 30-42-00
General 1 ALL
System Description 1 ALL
System Components 4 ALL
System Operation 6 ALL
PROPELLERS ANTI-ICING 30-60-00
General 1 ALL
System Description 1 ALL
System Components 7 ALL
System Operation 7 ALL
ICING DETECTION 30-80-00
General 1 ALL
System Description 1 ALL
System Components 2 ALL
ICING ANNUNCIATOR 30-81-00
General 1 ALL
System Description 1 ALL
System Components 3 ALL
System Operation 3 ALL
ICING PROBE 30-82-00
General 1 ALL
System Description 1 ALL
System Operation 3 ALL

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ICE AND RAIN PROTECTION

1. General

A. The ice and rain protection system includes:

- Pneumatic deicing systems;
- Electric heating and deicing systems;
- Ice detection systems.
B. The pneumatic deicing systems include:
- Airfoil deicing (Refer to 30-10-00);
- Engine air intake deicing (Refer to 30-20-00).
C. The electric heating systems include:
- Sensors heating (Refer to 30-30-00);
- Windows, windshields and doors (Refer to 30-40-00);
- Propeller anti-icing (Refer to 30-60-00).
D. The ice detection system (Refer to 30-80-00).
E. Ref. Fig. 001 for the main components of the ice protection system.

2. System Operation

A. Operation of Pneumatic Deicing Systems

Ref. Fig 002.

Pneumatic deicing system includes airfoil (wing and stabilizer leading edges) deicing
system and engine intake deicing system. The two systems are not completely
independent. They share three parts of bleed device, pressure regulating device and
water separator, as well as their ducts.
Pneumatic deicing system consists of pneumatic deicing boot, check valve, pressure
regulating relief valve, water separator, ejector flow control valve, pressure switch,
electric heating blanket, deicing timer, etc.
When the engine works and the pneumatic deicing system does not work, the solenoid
valve in ejector flow control valve will stop, and the ejector valve will open to vacuumize
all deicing boots based on the injection principle. Thus the deicing boot will be attached
on airfoil and inner surface of engine intake, keeping the aerodynamic shape and
reducing the flight resistance.
After the icing annunciator BXH-2G sends icing signal, the pilot monitor the icing detector
BTQ-1 and examine icing conditions on wing leading edge, for ice on wing and stabilizer
leading edges and engine intake. At this time, open the deicing control switch. The

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deicing timer will control system working.

The high-pressure hot air from engine compressor will firstly enter check valve and
pressure regulation relief valve, which will regulate the air pressure to a constant value
applicable to working of deicing boot. After entering the wing leading edge through
fire-resistant partitions, the air will be divided into two ways in wing leading edge: one will
flow to leading edge of outboard wing, and the other will flow to the fuselage. The air from
LH and RH engines will combine at the right side of fuselage, enter the cabin through the
skin of fuselage, and then flow to the tail section.
The bleed air from LH and RH engines connect to each other. Thus, when one engine
fails to bleed, bleed air of the other engine can make the wing and stabilizer leading edge
deicing boots and engine intake deicing boot work normally, that is to say, guarantee
normal working of deicing system.
The air flows to outboard wing will be divided into three ways (four ways for LH outboard
wing) after passing through water separator (for drying the air). One way will enter engine
nacelle through fire-resistant partitions, for the deicing system of engine intake. The other
two ways will flow into ejector flow control valve, which controls the deicing boots of
inboard wing leading edge and outboard wing leading edge. For LH inboard wing, there
is another way which will flow into the ejector flow control valve, which controls the
deicing boot of center wing leading edge.
When the pneumatic deicing system works, the solenoid coil in ejector flow control valve
will be energized in the sequence set by airfoil deicing timer. The solenoid valve will be
engaged, thus closing the ejector valve in ejector flow control valve. The air entering
ejector flow control valve will flow into the deicing boot on leading edge. Under the action
of air pressure, the pipes in deicing boot will swell to break the ice on deicing boot. The
broken ice will be removed by the air flow. In this way, the deicing target is realized.
The air, which flows on top of cabin toward the tails section, will also be divided into two
ways after passing through the water separator at FR 40. One way will enter the ejector
flow control valve, which controls the leading edge deicing boot inside horizontal
stabilizer. The other way will enter the ejector flow control valve, which controls the
leading edge deicing boot outside horizontal stabilizer and the vertical stabilizer leading
edge deicing boot. Both the ejector flow control valves, controlled by airfoil deicing timer,
are used to inflate the deicing boots for deicing.
After entering the nacelle through the duct, the air of engine intake deicing system will
flow into the ejector flow control valve of engine intake deicing boot, under the lower
fire-resistant partitions of FR 9 thru FR 10 of nacelle. This ejector flow control valve,
controlled by air intake deicing timer, will inflate the deicing boot to break the ice in engine
intake. Most of the broken ice will be drained into the air along the inertia channel of
engine.
The deicing systems of wing, stabilizer and air intake are equipped with a deicing timer
respectively. In normal conditions, the deicing timers are controlled by the wing and tail
deicing switch and air intake deicing switch on deicing control panel respectively. Wing
and tails section deicing includes two states of low icing and high icing, for which, deicing
will be done with 3 min as a cycle and 1 min as a cycle. Each deicing boot works
one-time for 6 s. Air intake deicing is done with 1 min as a cycle, with each deicing boot
working one-time for 6 s. When the deicing boot is working, the related indicator is ON,
for monitoring whether the deicing boot works normally.
When a deicing timer fails, pneumatic deicing is at emergency state. Deicing of wing and
tail and engine intake is controlled by the normal deicing timer at the same time. Deicing

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will be done with a cycle per 1 min.

Working sequence of deicing boot controlled by deicing timer is as shown in Fig 003.
There are pressure switches installed between ejector flow control valve and related
deicing boot, for examination of deicing boots. When pressure in deicing boot reaches a
certain value (at normal working state), the pressure switch will connect the circuit, and
the indicator on deicing control panel will be ON.
No matter at any working state, the deicing system will complete a working cycle and
stop automatically, if you open the control switch and close it instantaneously.
Deicing system needs air pressure, instead of high temperature, for working. The air
temperature higher than 71℃ (160°F) must be kept away from the deicing boot. Bleed
air of deicing system comes from engine compressor, thus its temperature is high. For
convenience of heat dissipation, no thermal insulation material is wrapped on the pipes of
deicing system.
The deicing boots are controlled by ejector flow control valves at the following nine
locations:
- Right engine inlet and air intake;
- Left engine inlet and air intake;
- Leading edge of center wing;
- Leading edge of left inboard wing;
- Leading edge of right inboard wing;
- Leading edge of left outboard wing;
- Leading edge of right outboard wing;
- Inside horizontal stabilizer leading edge;
- Outside horizontal stabilizer leading edge, vertical stabilizer.
B. Pneumatic Deicing Boot
The aircraft has two types of deicing boot:
- Spanwise pneumatic deicing boots at wing and stabilizer leading edges and inside the
air intake (Ref. Fig 004).
- Circular pneumatic deicing boot at engine inlet (Ref. Fig 005).
C. Technical Data of Pneumatic Deicing System
Rated working pressure of system ............................................145 kPa (21 lbf/in2)
Maximum working pressure of system ......................................165 kPa (24 lbf/in2)
Air flow required for system (non-deicing)
Each ejector flow control valve ...................................... 0.92 L/s (1.95 ft3/min)
Each water separator ....................................................... 0.71 L/s (1.5 ft3/min)
Total flow ........................................................................ 10.5 L/s (22.1 ft3/min)

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Figure 001 Ice and Rain Protection System – Main Components

1. Deicing Boot of Horizontal Stabilizer Leading Edge; 2. Deicing Boot of Vertical Stabilizer
Leading Edge; 3. Deicing Boot of Center Wing Leading Edge; 4. Deicing Boot of Inboard Wing
Leading Edge; 5. Deicing Boot of Outboard Wing Leading Edge; 6. Propeller Blades; 7. Icing
Detector (Icing Probe); 8. Icing Annunciator; 9. Windshield; 10. Engine Air Inlet; 11. Engine Air
Intake; 12. Pneumatic Deicing System; 13. Electric Heating Deicing/Anti-Icing System.

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Figure 002 Schematic Diagram of Pneumatic Deicing System

1. Leading Edge Deicing Boot of Left Center Wing; 2. Leading Edge Deicing Boot of Right
Center Wing; 3. Inside Leading Edge Deicing Boot of Left Inboard Wing; 4. Inside Leading
Edge Deicing Boot of Right Inboard Wing; 5. Outside Leading Edge Deicing Boot of Left
Inboard Wing; 6. Outside Leading Edge Deicing Boot of Right Inboard Wing; 7. Leading Edge
Deicing Boot of Left Outboard Wing; 8. Leading Edge Deicing Boot of Right Outboard Wing; 9.
Inside Leading Edge Deicing Boot of Left Horizontal Stabilizer; 10. Inside Leading Edge
Deicing Boot of Right Horizontal Stabilizer; 11. Outside Leading Edge Deicing Boot of Left
Horizontal Stabilizer; 12. Outside Leading Edge Deicing Boot of Right Horizontal Stabilizer; 13.
Leading Edge Deicing Boot of Vertical Stabilizer; 15. Engine Air Inlet Deicing Boot; 17. Bypass
Duct Deicing Boot of Engine Intake; 19. Rear Bottom Deicing Boot of Engine Intake; 101.
Pressure Switch; 102. Injection Flow Control Valve; 103. Pressure Regulating Relief Valve;
104. Check Valve; 105. Deicing Timer; 106. Emergency Deicing Control Switch; 107. Indicator
Light; 108. Electric Heating Blanket; 109. Water Separator; 110. Icing Annunciator; 111. Icing
Detector; 112. Wing & Tail Deicing Control Switch; 113. Engine Intake Deicing Control Switch.

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Deicing Boots Working Sequence

Figure 003

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Figure 004 Spanwise Pneumatic Deicing Boot

Figure 005 Annular Deicing Boot

1. Engine Inlet; 2. Air Intake; 3. Air Outlet; 4. Engine.

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Maximum flow when deicing system works ............................... 42 L/s (89 ft3/min)
Time for the timer to complete a cycle
Heavy icing ............................................................................................... 60 s
Light icing ................................................................................................ 180 s
NOTE: Each group of deicing boots operates for 6 s.
Maximum working current of system ............................................................... 15 A
Working voltage of system ......................................................................... 28 VDC

D. Controls and Indicators

Ref. Fig 006.

(1) Deicing control panel, installed at the overhead middle location of pilot, is used to
control the operation of deicing system.
(2) Wing and tail deicing switch
It is used to control the operation of wing and stabilizer deicing boots, make them
work at two states of high icing and low icing.
When the switch is at neutral position “HIGH”, the deicing system will work with 1
min as a cycle. Each deicing boot works one-time for 6 s.
When the switch is at “LOW” position, the deicing system will work with 3 min as a
cycle. Each deicing boot works one-time for 6 s.
When the deicing boot is working, the related indicator is ON, for monitoring whether
the deicing boot works normally.
(3) Air intake deicing switch
Used to control the operation air intake deicing boot of engine.
When the switch is at “ON”, the air intake deicing boot will start working with 1 min as
a cycle. Each engine intake deicing boot will work one-time in a cycle for 6 s.
When the deicing boot is working, the related indicator will be ON, for monitoring
whether the deicing boot works normally.
(4) Emergency deicing switch
The emergency deicing switch operates when a timer fails (airfoil timer or air intake
timer). It is used to make the other timer control operation of overall aircraft
pneumatic deicing system.
When the airfoil deicing timer fails, set the emergency deicing switch at “INTAKE
TIMER”. The air intake timer will control working of the overall aircraft pneumatic
deicing system.
When the air intake timer fails, set the emergency deicing switch at “WING & TAIL
TIMER”. The airfoil timer will control working of the overall aircraft pneumatic deicing
system.

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Figure 006 Deicing Control Panel

1. Propeller Check Switch; 2. Propeller Timer Switch; 3. Wing & Tail Deicing Control Switch; 4.
Air Intake Deicing Control Switch; 5. Deicing Indication Light of inside Horizontal Tail; 6.
Deicing Indication Light of outside Horizontal Tail; 7. Emergency Deicing Control Switch of
Wing & Tail Air Intake; 8. Deicing Indication Light Ⅱ of Left Outboard Wing; 9. Deicing
Indication Light Ⅰ of Left Outboard Wing; 10. Deicing Indication Light of Left Air Intake; 11.
Deicing Indication Light of Center Wing; 12. Deicing Indication Light of Right Air Intake; 13.
Deicing Indication Light Ⅰ of Right Outboard Wing; 14. Deicing Indication Light Ⅱ of Right
Outboard Wing; 15. Left Propeller Blade 2 and Blade 4 Heating Indication Light; 16. Left
Propeller Blade 1 and Blade 3 Heating Indication Light; 17. Right Propeller Blade 2 and Blade
4 Heating Indication Light; 18. Right Propeller Blade 1 and Blade 3 Heating Indication Light;
19. Propeller High/Low Icing Heating Switch.

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At both emergency working states above, the overall aircraft deicing boots work with
1 min as a cycle.
At normal working state, the emergency deicing switch is at “NORM” position. The
pneumatic deicing systems are controlled by the other two control switches
respectively.
(5) Indicators
The correct operation of the deicing boots and the propeller heaters is shown on the
deicing control panels with:
- Five indicators for the wing boots;
- Two indicators for the stabilizer boots;
- Two indicators for the engine air-intake boots;
- Four indicators for the propeller heaters.
Each group of deicing boots is installed with an ejector flow control valve and a
pressure switch. When the system is working, the air intake deicing timer will open
related ejector flow control valves according to pre-set program and let the air from
engine compressor reach deicing boots. The pressure switch behind the ejector flow
control valve will be close after sense the air pressure and send signal. The green
indicator on the deicing control panel will be on to indicate that the deicing boots are
properly working.
If the deicing timer fails or the deicing boot is damaged, the related indicator will not
be ON normally, warning the pilot that the deicing system fails.

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AIRFOIL DEICING

1. General

The airfoil deicing system, as part of the pneumatic deicing system, is used for deicing of the
leading edges of wings and stabilizers under the icing condition.

2. System Description

The airfoil deicing system includes the wing deicing system and the stabilizer deicing system.
The airfoil deicing control. Refer to 30-11-00.
The wing deicing. Refer to 30-12-00.
The stabilizer deicing. Refer to 30-13-00.
Ref. Fig 001 for the location of deicing boots of the airfoil deicing.

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Figure 001 Locations of Deicing Boots

1. Leading Edge Deicing Boot of Left Center Wing (29S-7D5237-01); 2. Leading Edge
Deicing Boot of Right Center Wing (29S-7D5237-02); 3. Inboard Leading Edge Deicing Boot
of Left Inboard Wing (29S-7D5237-03); 4. Inboard Leading Edge Deicing Boot of Right
Inboard Wing (29S-7D5237-04); 5. Outboard Leading Edge Deicing Boot of Left Inboard Wing
(29S-7D5237-05); 6. Outboard Leading Edge Deicing Boot of Right Inboard Wing (29S-
7D5237-06); 7. Leading Edge Deicing Boot of Left Outboard Wing (29S-7D5237-07); 8.
Leading Edge Deicing Boot of Right Outboard Wing (29S-7D5237-08); 9. Inboard Leading
Edge Deicing Boot of Left Horizontal Stabilizer (29S-7D5237-09); 10. Inboard Leading Edge
Deicing Boot of Right Horizontal Stabilizer (29S-7D5237-10); 11. Outboard Leading Edge
Deicing Boot of Left Horizontal Stabilizer (29S-7D5237-11); 12. Outboard Leading Edge
Deicing Boot of Right Horizontal Stabilizer (29S-7D5237-12); 13. Leading Edge Deicing Boot
of Vertical Stabilizer (29S-7D5237-13).

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AIRFOIL DEICING CONTROL

1. General

After pressure regulating and the water separation, the air from high pressure and low
pressure bleed ports of the two engines or the APU, the airfoil deicing control system will
provide the air, with pressure and flow under control, to the wing and stabilizer leading edge
deicing boots.

2. System Description

The airfoil deicing control system consists of:

- The pressure switch;
- The deicing control panel;
- The airfoil deicing timer;
- The check valve;
- The pressure regulating relief valve;
- The water separator;
- The ejector flow control valve;
- The electric heating blanket;
- The duct accessory.
Refer to Table 001 for the location of the components of the airfoil deicing control system.
Table 001 Positions and Description for Main Accessories of Airfoil De-Icing Control System

No. Description Type Qty Installation Position Zone/Access

1 Pressure switch 3D3533-01 1 Rib 7a thru Rib 8 of leading 522

edge of left inboard wing
2 Rib 8a thru Rib 9 of leading 522, 622
edges of the right and left
inboard wings
2 Rib 13 thru Rib 14 of left 532, 632
and right outboard wing
leading edges
2 AFT FR 40 at tail of 310
fuselage
2 Deicing control 1 Overhead control panel of 210
panel flight compartment

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Table 001 Positions and Description for Main Accessories of Airfoil De-Icing Control System

No. Description Type Qty Installation Position Zone/Access

3 Airfoil deicing 3D2485-25 1 Under the middle floor 160

timer between FR 25 thru FR 26
of passenger compartment
4 Check valve 3D3511-1 2 FR 10 thru FR 11 of left and 433, 434
right engine nacelles
5 Pressure 4D2095-211 2 FR 11 thru FR 12 of left and 433, 434
regulating relief right engine nacelles
valve
6 Water separator 4D2125-05 3 Front spars of left and right 522, 622, 310
inboard wing leading
edges, AFT FR 40 at tail
section of fuselage
7 Ejector flow 3D3502-63 1 No.5 partition of leading 522
control valve edge of left inboard wing
2 Leading edges of left and 522, 622
right inboard wings
2 Leading edges of left and 532, 632
right outboard wings
2 AFT FR 40 at tail of 310
fuselage
8 Electric heating 2D1798 2 On shell of ejector flow 532, 632
blanket control valves at left and
right outboard wing leading
edges
2 On shell of ejector flow 310
control valve AFT FR 40 at
the tail of fuselage
Refer to Table 002 for the power supply of the components.
Table 002 Power Supply of Component
DC Busbar Power Supply (Circuit
Component
Breaker Panel)

Deicing timer RH normal DC busbar power supply

Pressure switch RH normal DC busbar power supply

Ejector flow control valve RH normal DC busbar power supply

Electric heating blanket RH normal DC busbar power supply

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3. System Components
A. Pressure Switch
The 7 pressure switches are installed on the duct between ejector flow control valve of
airfoil deicing system and air connector of deicing boot. They are used to directly sense
the pressure of flow provided to deicing boots. The air supply pressure for working
deicing boot is far larger than the working pressure of pressure switch. Thus, the working
pressure of pressure switch is the minimum pressure for working deicing boot. When the
air pressure in duct reaches the working pressure of pressure switch, the pressure switch
will engage the power supply, and the related indicator will be ON, indicating the deicing
boot of this part works normally.
Technical data:
Ambient temperature .........................................－54℃ to 121℃(－65℉ to 250℉)

Operating temperature .......................................－54℃ to 204℃(－65℉ to 399℉)

Operating voltage .......................................................................................... 28 VDC

Rated current (28 VDC) ............................................................................... 100 mA

Air pressured with indicator ON ......................104 kPa±6.9 kPa (15 lbf/in2±1 lbf/in2)
Normal operating pressure ....................................................... 145 kPa (21 lbf/in2)
B. Deicing Control Panel
The deicing control panel, located on overhead control panel of flight compartment,
includes a control switch of pneumatic deicing system and propeller deicing system and
indicators. It is used to control and monitor the wing, stabilizer and intake deicing systems,
and propeller deicing system.
C. Airfoil Deicing Timer
The airfoil deicing timer, installed under the middle floor between FR 25 thru FR 26 in
passenger compartment, controls the wing and stabilizer deicing system.
Technical data:
Electrical power supply ............................................................... 18 VDC to 30 VDC
Operating current ...................................... 4 A within 12 ms after the power supply is
applied at 25℃(77°F), and 8 mA at steady state
Load current .............................................................. Maximum output current 4.5 A
D. Check Valve
The two check valves are respectively installed in bleed ducts of pneumatic deicing
systems between FR 9 and FR 10 in left and right engine nacelles. They are used to
prevent the air in pneumatic deicing system flowing back into engines.
E. Pressure Regulating Relief Valve
The two pressure regulating relief valves are respectively installed in the bleed ducts of
pneumatic deicing system between FR 9 thru FR 10 in left and right engine nacelles.

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They are used to regulate the high pressure air from engine to a pressure suitable for
working of pneumatic deicing system. When the pressure regulator fails, the system
pressure will increase. The relief valve in pressure regulating relief valve will work as a
safety valve. It can make the working pressure of deicing system a little higher and keep
it within the safe pressure range. Thus, the deicing system can work normally too.
Technical data:
Ambient temperature .............................................. -54℃ to 121℃(-65℉ to 250℉)

Operating temperature .......................................... -54℃ to 315℃(-65℉ to 599℉)

Inlet air pressure ............................... 275 kPa to 1550 kPa (40 lbf/in2 to 225 lbf/in2)
Pressure after pressure regulator ............. 145 kPa±6.9 kPa (21.0 lbf/in2±1.0 lbf/in2)
Operating pressure of safety valve (when pressure regulator fails) .........................
..............................................................170 kPa ＋6.9 ＋1
0 kPa (24.5 1bf/in2 0 1bf/in2)

Effective flow area ........................................................................... 5.2 cm2 (0.8 in2)

Flow ........................................................ 0.94 L/s to 16.5 L/s(2 ft3/min to 35 ft3/min)
F. Water Separator
The three water separators are installed in ducts before ejector flow control valves at left
and right outboard wing leading edges and after FR 40 at tail of fuselage. The air flow
rotates in water separator shell, thus removing the water by centrifugal force. The water
will be collected at the bottom of shell and drained through the drainage pipe at bottom of
shell. In this way, the air for deicing is dried.
Technical data:
Ambient temperature .............................................. -54℃ to 121℃(-65℉ to 250℉)

Working Temperature ............................................. -54℃ to 232℃(-65℉ to 450℉)

Maximum Working Pressure .................................................... 690 kPa (100 lbf/in2)
Flow (21.1℃ (70℉), inlet pressure of 690 kPa (100 psi)) .......... 33 L/s (70 ft3/min)
Flow area .................................................................................... 0.6 cm2 (0.093 in2)
G. Ejector Flow Control Valve
The 7 ejector flow control valves are installed in the ducts before wing and stabilizer
deicing boots. They are used to deflate and inflate the deicing boots.
In normal conditions (power supply not applied), the ejector flow control valve allows a
small quantity of air at certain pressure travel through the ejector valves in it, so as to
deflate the whole deicing boot, make the deicing boot attach on airfoil closely, maintain
the shape and reduce the resistance.
After the ejector flow control valve receives the command (power supply applied) of
deicing timer, the ejector valve in it will be closed. A large quantity of air at certain
pressure will enter the deicing boot through ejector flow control valve, thus inflating the
deicing boot and realizing the goal of deicing.
Technical data:

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 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

Ambient temperature ............................................. -54℃ to 121℃(-65℉ to 250℉)

Operating temperature ............................................. -54℃ to 90℃(-65℉ to 194℉)

Operating pressure .................................................................... 145 kPa (21 lbf/in2)
Flow area ................................................................................. 40.6 mm2 (0.063 in2)
Flow (21.1℃ (70℉), inlet pressure of 145 kPa (21 psi)) ......... 16.5 L/s (35 ft3/min)
Ejector flow (inlet pressure 145 kPa (21 psi)) ............................ 0.94 L/s (2 ft3/min)
Solenoid coil impedance (25℃ (77℉)) .................................................. 12Ω (min)
Electrical power supply ................................................................. 24 VDC to 32 VDC
Current ..............................................................................................................2.2 A
H. Electric Heating Blanket
The four electric heating blankets are wrapped on shells of ejector flow control valves far
from the engine bleed source at left and right outboard wing leading edges and after FR
40 at tail of fuselage. They are used to heat the valve shells and keep the temperature of
air through valve no lower than 0℃(32℉), so as to prevent icing of water in air and
guarantee normal working of ejector flow control valves.
Technical data:
Ambient temperature ............................................... -54℃ to 93℃(-65℉ to 199℉)
Operating pressure ...................................................................................... 28 VDC
Power (28 VDC) .............................................................................................. 40 W

Engaging temperature of temperature relay ....................... 49℃±2.8℃(120°F±5°F)

Disengaging temperature of temperature relay ................ 65.5℃±2.8℃(150°F±5°F)

4. System Operation
A. General
The airfoil deicing timer is the core of airfoil deicing control system. When the system is
operating, it will open the related ejector flow control valve in sequence according to the
defined procedure. The air from engine compressor will enter each deicing boot in
sequence.
The airfoil deicing system includes 7 groups of deicing boots (i.e. center wing leading
edge, left inboard wing leading edge, right inboard wing leading edge, left outboard wing
leading edge, right outboard wing leading edge, inside horizontal stabilizer leading edge,
outside horizontal stabilizer leading edge, and vertical stabilizer leading edge).
Each group of deicing boots is installed with an ejector flow control valve and a pressure
switch. When the system is operating, the intake deicing timer will open related ejector
flow control valves according to pre-set program and let the air from engine compressor
reach deicing boots.
The pressure switch behind the ejector flow control valve will be close after sense the air
pressure and send signal. The green indicator on the deicing control panel will be ON to

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 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

indicate that the deicing boots are properly working.

B. Normal Operation
In normal operation, the emergency deicing switch is set at “NORM”. The wing, stabilizer
and intake deicing systems are separately controlled by wing and tail deicing switches
and intake deicing switch.
In normal operation, the wing and stabilizer deicing system has two states (sever/slight).
When the wing & tail deicing switches are at “HIGH”, the deicing system will operate 1
min for each cycle. Each deicing boot operates one-time for 6 s.
When the wing & tail deicing switches are at the upper position “LOW”, the deicing
system will operate 3 min for each cycle. Each deicing boot operates one-time for 6 s.
In normal working conditions, for both sever icing and slight icing, the deicing boot of
wing and stabilizer deicing system operate circularly according to the sequence that
follows:
- Deicing boot of center wing leading edge;
- No. 1 outboard wing leading edge deicing boot;
- No. 2 outboard wing deicing boot;
-Inside leading edge deicing boot horizontal stabilizer;
- Outside leading edge deicing boot horizontal stabilizer;
- Vertical tail leading edge deicing boot.
The deicing boots will be inflated in sequence symmetrically during working. Each pair
will be inflated for about 6 s, with the related green indicator on deicing control panel
lightened.
After completion of deicing, set the wing & tail deicing switches at “OFF”. The system will
stop working.
C. Emergency Operation
When the airfoil deicing timer fails, set the emergency deicing switch at “INTAKE TIMER”.
In this condition, the intake deicing timer controls the wing, the stabilizer and the intake
deicing systems at the same time.
Set the wing & tail deicing switches at “OFF”, and intake deicing switch at “ON”, the
overall aircraft deicing boots operates 1 min for a cycle. The operating sequence is as
follows:
- Left engine intake deicing boot;
- Right engine intake deicing boot;
- Center wing leading edge deicing boot;
- No. 1 outboard wing leading edge deicing boot;
- No. 2 outboard wing leading edge deicing boot;
- Horizontal stabilizer leading edge deicing boot;
- Vertical stabilizer leading edge deicing boot.

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The deicing boots will be inflated symmetrically in sequence. Each pair will be inflated for
about 6 s, with the related green indicator on deicing control panel lightened in sequence
as well.

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 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

WING DEICING

1. General

The wing deicing system includes:

- The center wing leading edge deicing system. Refer to 30-12-10.
- The inboard wing leading edge deicing system. Refer to 30-12-20.
- The outboard wing leading edge deicing system. Refer to 30-12-30.

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CENTER WING LEADING EDGE DEICING

1. General

Center wing leading edge deicing is part of wing deicing. The working air, controlled by an
ejector flow control valve installed in LH center wing leading edge, is used to remove the ice
on center wing leading edge.

2. System Description
Ref. Fig 001.
The center wing leading edge deicing boots are symmetrically installed at the removable
center wing leading edge.
For the location of leading edge deicing boot for center wing, Ref. Fig 006 in 30-00-00.
Besides the duct for air supply of center wing leading edge deicing boot, there are also the
total air supply duct of deicing system and the air supply duct for engine intake deicing system
in center wing leading edge.
Center wing leading edge deicing involves LH and RH center wing leading edge deicing boots,
an ejector flow control valve, a pressure switch, ducts and other accessories.
The ejector flow control valve and pressure switch, installed in LH inboard wing leading edge,
are used to control working of center wing leading edge deicing boot. Refer to (16) and (17) in
Fig 001 of 30-12-20.
LH and RH center wing leading edge deicing boot 29S-7D5237-01/02 includes two parts,
installed between Rib 2 thru Rib 5 of wing at center wing leading edge. The center wing
leading edge deicing boot is covered on the removable center wing leading edge. For
convenience of opening, the movable access panel on lower surface of center wing is not
covered by deicing boots.

3. System Operation
Air supply for center wing leading edge deicing boot comes from LH inboard wing leading
edge. Refer to (6) in Fig 001. The air passes through the ejector flow control valve and
pressure switch, which control the center wing leading edge deicing boot (installed on No. 5
partition of LH inboard wing leading edge). It is directly provided to the two center wing
leading edge deicing boots.
In addition, the total air supply duct of whole pneumatic deicing system also comes from LH
and RH engine nacelles. Refer to (3) and (4) in Fig 001. It is divided in center wing leading
edge. One way will be combined at right side of symmetry axis of aircraft, pass through the
fuselage skin, enter the cabin and flow to the tail section. The other way will flow to LH
outboard wing leading edge and RH outboard wing leading edge respectively.
The duct for air supply of engine intake deicing system also comes from outboard wing
leading edge. It enters the engine nacelle through center wing leading edge. Refer to (5) in
Fig 001.

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VIEW A

FWD
MA60 AIRCRAFT MAINTENANCE MANUAL (PART I

Figure 001 Center Wing Leading Edge Deicing System

SDS)

1. Leading Edge Deicing Boot of Left Center Wing (29S-7D5237-01); 2. Leading Edge Deicing Boot of Right Center Wing
(29S-7D5237-02); 3. Total Air Supply Duct from the Left Engine Nacelle; 4. Total Air Supply Duct from the Right Engine
Nacelle; 5. Air Supply Duct to the Engine Intake Deicing System; 6. Air Supply Duct from LH Outboard Wing to Center
Wing Leading Edge Deicing Boot; 7. Air Supply Duct to the Tail Leading Edge De-Icing Boot; 8. Fuselage Outer Skin.

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30-12-10
 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

INBOARD WING LEADING EDGE DEICING

1. General
The inboard wing leading edge deicing is part of wing deicing. The working air, controlled by
the ejector flow control valves installed in LH and RH center wing leading edges, is used to
remove the ice on LH and RH inboard wing leading edge.

2. System Description
LH and RH inboard wing leading edge deicing boots include inner and outer parts respectively.
Both are installed on removable inboard wing leading edge.
For the location of leading edge deicing boot for inboard wing, Ref. Fig 001 in 30-10-00.
Besides the duct for air supply of inboard wing leading edge deicing boot, there are also
ejector flow control valve, which controls working of center wing leading edge deicing boot,
and the duct for air supply of engine intake deicing system, installed in the center wing leading
edge.
Inboard wing leading edge deicing involves deicing boots inside and outside LH and RH
inboard wing leading edge, two water separators, two ejector flow control valves, two
pressure switches, ducts and other accessories.
The two ejector flow control valves control LH and RH inboard wing leading edge deicing
boots respectively. The inside and outside deicing boots are controlled by the same ejector
flow control valve.
The leading edge deicing boot 29S-7D5237-03/04 inside inboard wing covers between No. 1
and No. 13 partitions (Rib 7 thru Rib 10 of wing) on removable inboard wing leading edge.
The stall rod is attached on deicing boot under the leading edge line between No. 8 and No.
11 partition of inboard wing. For convenience of opening the movable access cove on lower
surface of inboard wing leading edge, the deicing boots all have notches at the locations of
access covers, in order to make sure the access covers are not covered by deicing boot.
The leading edge deicing boot outside inboard wing 29S-7D5237-05/06 covers between No.
14 and No. 20 partitions (Rib 10 thru Rib 12 of wing) on removable inboard wing leading edge.
For normal working of landing light on lower surface of inboard wing leading edge and for
convenience of opening the access covers, the deicing boots all have notches at the locations
of landing light and access covers, in order to make sure the landing light and access covers
are not covered by deicing boots.

3. System Operation
Ref. Fig 001 for the installation of the inboard wing leading edge de-icing system.
The air from LH and RH engines is divided into three ways (four ways for LH inboard wing)
after passing through the water separators (10) installed on front spars of LH and RH inboard
wings. One will enter the ejector flow control valve (11) which controls working of inboard wing
leading edge deicing boot. The other will enter the ejector flow control valve (13) which
controls working of inboard wing leading edge deicing boot. The air flow will finally enter LH

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 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

and RH inboard wing leading edge deicing boots (4), (5), (6) and (7) through the ducts.
The third way from water separator will flow to the duct (15) of engine intake deicing system
and enter the nacelle.
Another way of LH inboard wing will enter the ejector flow control valve (16), which is installed
on inboard wing leading edge for controlling the center wing leading edge deicing boot. It will
finally flow to the deicing boots of LH and RH center wing leading edges.
There are pressure switches (12) installed between the ejector flow control valves and deicing
boots of LH and RH inboard wings. They are used to indicate whether the deicing boots work
normally. When the pressure switch sends a signal, the related indicator will be ON.
Additionally, there is an electric heating blanket 2D1798 wrapped on ejector flow control valve
shell of outboard wing deicing boot. When the deicing system works, it will heat the air in
ejector flow control valve shell, so as to prevent icing and blockage of pipe port caused by ice
and make the system work normally.

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Figure 001 Leading Edge Deicer Boots of LH and RH Inboard Wings and Outboard Wings (Sheet 1 of 2)

1. Removable Leading Edge of Inboard Wing; 2. Removable Leading Edge of Outboard Wing; 3. Butt Plate Between Removable
Leading Edge of Inboard Wing and Leading Edge of Outboard Wing; 4. Inside Leading Edge Deicing Boot of Right Inboard Wing
(29S-7D5237- 04); 5. Inside Leading Edge Deicing Boot of Left Inboard Wing (29S-7D5237-03); 6. Outside Leading Edge Deicing
MA60 AIRCRAFT MAINTENANCE MANUAL (PART I

Boot of Right Inboard Wing (29S-7D5237-06); 7. Outside Leading Edge Deicing Boot of Left Inboard Wing (29S- 7D5237-05); 8.
Leading Edge Deicing Boot of Right Outboard Wing (29S-7D5237-08); 9. Leading Edge Deicing Boot of Left Outboard Wing
SDS)

(29S-7D5237-07); 10. Water Separator 4D2125-05; 11. Injection Flow Control Valve 3D3502-63 (Controlling Leading Edge
Deicing Boots of Inboard Wings); 12. Pressure Switch 3D3533-01 (Leading Edge Deicing Boots of Inboard Wings); 13. Injection
Flow Control Valve 3D3502-63 (Controlling Leading Edge Deicing Boots of Outboard Wings); 14. Pressure Switch 3D3533-01
(Leading Edge Deicing Boots of Outboard Wings); 15. Duct to the Engine Intake Deicing System; 16. Injection Flow Control Valve
3D3502-63 (Controlling Leading Edge Deicing Boots of Center Wings); 17. Pressure Switch 3D3533- 01 (Leading Edge Deicing
Boots of Center Wings); 18. Duct to Deicing Boots of Center Wings.

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Front spar axis
Forward
Right inboard wing and outboard wing
MA60 AIRCRAFT MAINTENANCE MANUAL (PART I
SDS)

Figure 001 Leading Edge Deicer Boots of LH and RH Inboard Wings and Outboard Wings (Sheet 2 of 2)

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 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

OUTBOARD WING LEADING EDGE DEICING

1. General

The outboard wing leading edge deicing is part of wing deicing. The working air, controlled by
the ejector flow control valves installed in LH and RH center wing leading edges, is used to
remove the ice on LH and RH outboard wing leading edge.

2. System Description

Outboard wing leading edge deicing boot 29S-7D5237-07/08 is divided into LH and RH parts,
which are installed on removable outboard wing leading edges between Rib 12 thru Rib 23 of
wing.
Ref. Fig 001 in 30-10-00 for positions of the outboard wing leading edge deicing boots.
Outboard wing leading edge deicing involves LH and RH outboard wing leading edge deicing
boots, two ejector flow control valves, two pressure switches, ducts and other accessories.
The two ejector flow control valves control LH and RH outboard wing leading edge deicing
boots respectively.
For convenience of opening the movable access cover on lower surface of outboard wing
leading edge, the deicing boots all have notches at the locations of movable access covers, in
order to make sure the access covers are not covered by deicing boots.

3. System Operation

Ref. Fig 001 in 30-10-00 for the installation of the outboard wing leading edge deicing system.
The air from LH and RH engines is divided into three ways (four ways for LH outboard wing)
after passing through the water separators (10) installed on front spars of LH and RH inboard
wings. One way will enter the ejector flow control valve (13), which controls LH and RH
outboard wing leading edge deicing boots. The air flow will finally enter LH and RH outboard
wing deicing boots (8) and (9) through the ducts.
There are pressure switches (14) installed between the ejector flow control valves and deicing
boots of LH and RH outboard wings. They are used to indicate whether the deicing boots
work normally. When the pressure switch sends a signal, the related indicator will be ON.
Additionally, there is an electric heating blanket wrapped on ejector flow control valve (13)
shell of LH outboard wing and RH outboard wing deicing boot. When the deicing system
works, it will heat the air in ejector flow control valve shell, so as to prevent icing and blockage
of pipe port caused by ice and make the system work normally.

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STABILIZER DEICING

1. General

Stabilizer deicing system includes two parts of horizontal stabilizer leading edge deicing and
vertical stabilizer leading edge deicing.

2. System Description

Stabilizer deicing system consists of stabilizer leading edge deicing boot, pressure switch,
water separator, ejector flow control valve, electric heating blanket, ducts, and so on.
Stabilizer leading edge deicing boot consists of inside leading edge deicing boots of LH and
RH horizontal stabilizers, outside leading edge deicing boots of LH and RH horizontal
stabilizers and vertical stabilizer leading edge deicing boot.
There is an inside leading edge deicing boot of horizontal stabilizer at both left and right sides.
They are between No. 0 and No. 14 partitions of removable horizontal stabilizer leading edge
(Rib 1 thru Rib 8 of horizontal stabilizer).
There is an outside leading edge deicing boot of horizontal stabilizer at both left and right
sides. They are between No. 14 and No. 24 partitions of removable horizontal stabilizer
leading edge (Rib 8 thru Rib 15 of horizontal stabilizer) and are pasted on the same
removable leading edge together with the inside leading edge deicing boot of horizontal
stabilizer.
There is only one vertical stabilizer leading edge deicing boot. It is between No. 1A and No. 16
partitions of removable vertical stabilizer leading edge (Rib 4 thru 14 of vertical stabilizer).
Ref. Table 001 for the locations of the component of the stabilizer deicing system.
Table 001 Positions and Description of Main Accessories of Stabilizer Deicing System
No. Description Type Qty Installation Position Zone/Access

Between No. 0 and

Inside leading edge
29S-7D5237 No. 14 Inside leading
1 deicing boot of 2 332, 342
-09/10 edge deicing boot of
horizontal stabilizer
LH and RH stabilizers
Between No. 14 and
Outside leading
29S-7D5237 No. 24 Outside leading
2 edge deicing boot of 2 332, 342
-11/12 edge deicing boot of
horizontal stabilizer
LH and RH stabilizers
Leading edge Between No. 1A and
29S-7D5237
3 deicing boot for the 2 16 partitions of vertical 323
-13
vertical stabilizer stabilizer leading edge
AFT FR 40 at tail of
4 Pressure switch D3533-01 2 310
fuselage

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Table 001 Positions and Description of Main Accessories of Stabilizer Deicing System
No. Description Type Qty Installation Position Zone/Access

AFT FR 40 at tail of
5 Water separator 4D2125-05 1 310
fuselage
Ejector flow control AFT FR 40 at tail of
6 3D3502-63 2 310
valve fuselage
On shell of ejector flow
Electric heating control valve after FR
7 2D1798 2 310
blanket 40 at the tail of
fuselage
Ref. Fig 001 for the installation of the fuselage-section duct of the stabilizer deicing system.
Ref. Fig 002 for the installation of the horizontal stabilizer leading edge deicing system.
Ref. Fig 003 for the installation of the vertical stabilizer leading edge deicing system.

3. System Operation

Air supply of fuselage deicing system comes from LH and RH engines and enters the
fuselage after converging outside the fuselage. It will flow on top of the cabin to the tail section,
pass through FR 40 and then the water separator from the back of FR 40. The separated
water will flow to the drainage port on bottom skin of fuselage through the duct at the bottom
of water separator, and will be drained out of fuselage through the drainage port.
The air will be divided into two ways after passing through the water separator. They will
respectively enter the ejector flow control valves, which controls working of inside leading
edge deicing boot of horizontal stabilizer, and which controls outside leading edge deicing
boot of horizontal stabilizer and vertical stabilizer leading edge deicing boot. Then, they will
respectively flow to the horizontal stabilizer and vertical stabilizer.
There are pressure switches installed between ejector flow control valves and deicing boots,
for indicating whether the deicing boots work normally.
The inside leading edge deicing boot of LH horizontal stabilizer and the inside leading edge
deicing boot of RH horizontal stabilizer share the same air supply duct. An ejector flow control
valve, which is installed on the section behind the small door of FR 40 in the fuselage, will
provide air to remove the ice on inside leading edge deicing boot of horizontal stabilizer.
LH and RH parts of outside leading edge deicing boot of horizontal stabilizer are connected
together and share the same supply duct with the vertical stabilizer leading edge deicing boot.
An ejector flow control valve, which is installed on the section behind the small door of FR 40
in fuselage, for outside leading edge deicing of horizontal stabilizer and vertical stabilizer
leading edge, will provide air to remove the ice on outside leading edge deicing boot of
horizontal stabilizer.
Vertical stabilizer leading edge deicing boot shares the same supply duct with the outside
leading edge deicing boot of LH and RH horizontal stabilizers. An ejector flow control valve,
which is installed on the section behind the small door of FR 40 in fuselage, for outside
leading edge deicing of horizontal stabilizer and vertical stabilizer leading edge, will provide
air to remove the ice on vertical stabilizer leading edge deicing boot.

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MA60 AIRCRAFT MAINTENANCE MANUAL (PART I
SDS)

Aircraft horizontal axis

Figure 001 Installation of Fuselage-section Deicing System (Sheet 1 of 2)

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 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

A DIRECTION
Only the installation at FR40 is shown.

Fuselage Symmetrical Axis

Figure 001 Installation of Fuselage-section Deicing System (Sheet 2 of 2)

1. Air Supply Duct from Engine; 2. Air Supply Duct to Vertical Stabilizer Leading Edge Deicing
Boot; 3. Pressure Switch 3D3533-01; 4. Air Supply Duct to Outside Leading Edge Deicing
Boot of Horizontal Stabilizer; 5. Air Supply Duct to Inside Leading Edge Deicing Boot of
Horizontal Stabilizer; 6. Pressure Switch 3D3533-01; 7. Ejector Flow Control Valve in Control
of Inside Leading Edge Deicing Boot of Horizontal Stabilizer 3D3502-63; 8. Injection Flow
Control Valve in Control of Leading Edge Deicing Boot of Vertical Stabilizer 3D3502-63; 9.
Water Separator 4D2125-05; 10. Drain Pipe.

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Forward

Partition axis
Front spar axis

Rib axis
MA60 AIRCRAFT MAINTENANCE MANUAL (PART I

Figure 002 Installation of Horizontal Stabilizer Leading Edge Deicing System

1. Inside Leading Edge Deicing Boot of Horizontal Stabilizer; 2. Outside Leading Edge Deicing Boot of Horizontal
SDS)

Stabilizer; 3. Removable Leading Edge of Horizontal Stabilizer; 4. Horizontal Stabilizer; 5. Air Supply Duct to Outside
Leading Edge Deicing Boot of Horizontal Stabilizer; 6. Air Supply Duct to Inside Leading Edge Deicing Boot of
Horizontal Stabilizer.

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 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

Front Spar Axis

Forward

Partition Axis
Rib Axis

Figure 003 Installation of Vertical Stabilizer Leading Edge Deicing System

1. Vertical Stabilizer Leading Edge Deicing Boot; 2. Removable Leading Edge of Vertical
Stabilizer; 3. Air Supply Duct to Vertical Stabilizer Leading Edge Deicing Boot; 4. Vertical
Stabilizer.

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 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

AIR INTAKE DEICING

1. General

The air intake deicing is a pneumatic deicing system. It uses a deicing boot sticking on the air
intake engine where freezing easily takes place. This system is able to deice for the engine air
intake, the engine air intake bypass tube and the base of air intake to ensure the engine
working normally under frozen weather conditions and ensure the flight safety.

2. System Description

Ref. Fig 001 and Fig 002.

The air intake deicing system includes the air intake deicing system of the engine and the
bleed duct of the entire pneumatic deicing system.
The air intake deicing system of engine consists of the air intake deicing control and air intake
deicing boot.
The air intake deicing control system is composed of the air intake deicing timer, pressure
switches, injection flow control valves and duct accessories.
The air intake deicing boots include the deicing boots attached to the following positions: the
leading edge of the engine air intake, the rear bottom of the air intake and the air intake
bypass tube.
The bleed duct of the entire pneumatic deicing system consists of check valve, pressure
regulating relief valve and duct accessories.
Ref. Table 001 for positions and description of main accessories of air intake deicing system.
Table 001 Positions and Description of Main Accessories of Air Intake Deicing System

No. Description Type Qty Installation Position Zone/Access

1 Leading edge 29S-5D5237-15 2 Engine air intake, 411, 412

deicing boot between FR 1 thru FR 5
of nacelle
2 Rear bottom 29S-5D5237-19 2 Between FR 5 thru FR 425, 426
deicing boot 7 at rear bottom of air
intakes of LH and RH
engines
3 Bypass tube 29S-5D5237-17 2 LH and RH engine 425, 426
deicing boot bypass tube internal
sidewall
4 Air intake deicing 3D2485-25 1 Under the middle floor 160
timer between FR 26 thru FR
27 of the cabin
compartment

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Table 001 Positions and Description of Main Accessories of Air Intake Deicing System

No. Description Type Qty Installation Position Zone/Access

5 Pressure switch 3D3533-01 2 On deicing ducts below 431, 432

fire-resistant partitions
in FR 9 thru FR 10 of
engine nacelles
6 Injection flow 3D3502-63 2 On fire-resistant 431, 432
control valve partitions in the lower
sections of FR 9 thru
FR 10 of engine
nacelles
7 Check valve 3D3511-1 2 FR 10 thru FR 11 of LH 433, 434
and RH engine nacelles
8 Pressure 4D2095-211 2 FR 11 thru FR 12 of LH 433, 434
regulating relief and RH engine nacelles
valve

3. System Components

A. Air Intake Deicing Boot

The installation position of the leading edge air intake deicing boot is at the left and right
side of FR 5 from outside of air intake to inside of air intake.
The installation position of the rear bottom air intake deicing boot of the engine is in the
range of FR 5 thru FR 7.
The installation position of the bypass air intake deicing boot of engine is on the sidewall
of engine bypass tube.
B. Ejector Flow Control Valve
The installation position of ejector flow control valve is on the fire-wall in the lower
sections of FR 9 thru FR 10 of engine nacelles.
C. Pressure Switch
The installation poison of pressure switch is on the deicing duct below fire-resistant
partition in FR 9 thru FR 10 of engine nacelle.
D. Check Valve
The installation position of check valve is in the bleed duct of deicing system on the top of
FR 10 thru FR 11 of engine nacelles.
E. Pressure Regulating Relief Valve
The installation position of pressure regulating relief valve is at the engine support on the
right top of FR 11 thru FR 12 of engine nacelles.

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Figure 001. Engine Air Intake Deicing Boot

1. Leading Edge Deicing Boot; 2. Bypass Tube Deicing Boot; 3. Rear Bottom Deicing Boot.

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Heading

ENG axial line

MA60 AIRCRAFT MAINTENANCE MANUAL (PART I
SDS)

Figure 002 Installation of Engine Intake Deicing System (Sheet 1 of 2)

Feb 20/2013
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 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

A DIRECTION
Only air intake is shown

Heading

Throat axial line

Figure 002 Installation of Engine Air Intake Deicing System (Sheet 2)

Ⅰ. Ram Air Inlet; Ⅱ. Air Supply to the Engine; Ⅲ. Air Exhaust through Inertial Passage.
1. Engine Nacelle; 2. Pressure Switch; 3. Injection Flow Control Valve; 4. Pressure Regulating
Relief Valve; 5. Wing Leading Edge; 6. Dry Air Duct from Outboard Wing; 7. Air Duct to the
Outboard Wing Leading Edge; 8. Air Duct to the Tail; 9. Port for Bleed Air from Air Conditioner
Tube to the Pneumatic Deicing System; 10. Bleed Air Duct of Air Conditioning System; 11.
Check Valve; 12. Connecting Hose; 13. Engine Air Intake; 14. Air Supply Duct to Air Intake
Deicing Boots; 15. Rear Bottom Deicing Boot of Engine Air Intake; 16. Engine Air Intake
Deicing Boot; 17. Bypass Tube Deicing Boot of Engine Air Intake; 18. Clearance Between
Engine Air Intake and Nacelle.

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4. System Operation

Ref. Fig 002.

The air supply duct of air intake deicing system for engine comes from leading edge of the
outboard wing. It supplies dry air that comes from water separator. The duct goes through
wing fire-resistant partition into nacelle. In the nacelle, the duct goes through the fire-resistant
partition of FR 11 and then goes through the lower fire-resistant partition between FR 9 thru
FR 10 into the lower section of the nacelle. In the lower section of the nacelle, the duct is
connected with the connect hose (12) at FR 9 through the ejector flow control valve (3) on
fire-resistant partition, then connected with supply ducts of deicing boots (14) through the
hose, and finally reaches to deicing boots.
The function of the connect hose (12) is for compensating. Because the entire air intake is
installed on the engine directly, there is gap between air intake and nacelle. When engine
works, the vibration will cause relative displacement of the air intake and nacelle. Thus, the
connect hose (12) is used to compensate that relative displacement of the dusts on nacelles
and supply dusts for air intake deicing boots.
The bleed air of pneumatic deicing system is taken from the ducts in front of the main control
switch of air conditioning system. There are only two bleed ports at the engine: high pressure
bleed port and low pressure bleed port. During normal flight, the bleed air for air conditioning
and deicing will supplied by the engine low pressure bleed port. However, when the aircraft is
in descent status, engine is at idle speed, the air provided by low pressure bleed port of the
engine will be to low and unable to be used. At this time, the air conditioning system will
switch to high pressure bleed port automatically to satisfy the requirement of air conditioning
and deicing. The bleeding air for the deicing system is not controlled by the switch of air
conditioning system. Once engines work, the bleed air will be available for deicing system .
The pneumatic deicing system receives high pressure air from bleed port (9), the high
pressure air passes through check valve (11) and pressure regulating relief valve (4). The
pressure of the bleeding air will be adjusted to a stable value, and then it goes across wing
fire-resistant partition and will be divided into two flows: one flow goes to the air duct (8) on
leading edge of the tail through the fuselage; the other flow goes to air duct (7) on leading
edge of the outboard wing.

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AIR INTAKE DEICING CONTROL

1. General

The air intake deicing control system will adjust the air pressure and separate water from the
bleed air which is bled from the engine high/low pressure bleed port or the bleed air from APU.
Then controlling the pressure and flow, the air will be supplied in a certain order to air intake
deicing boots at different locations for deicing.

2. System Description

Air intake deicing control consists of air intake deicing timer, pressure switch, ejector flow
control valve and duct accessories.
The core component of air intake deicing control system is the air intake deicing timer. When
the system is working, the air intake deicing timer will open the ejector flow control valves of
left and right air intakes one by one according to pre-set program. The air from engine
compressor will flow into left and right air intake deicing boots in a certain sequence.
The deicing boots of air intake deicing system is divided into two groups: left air intake and
right air intake. Each group of deicing boots is installed with an ejector flow control valve and a
pressure switch. When the system is working, the intake deicing timer will open related ejector
flow control valves according to pre-set program and allows the air flow from engine
compressor to the deicing boots. The pressure switch behind the ejector flow control valve will
be close after sense the air pressure and send signal. The green indicator on the deicing
control panel will be on to indicate that the deicing boots are properly working.
The control switches and indicators of intake deicing system are integrated on the deicing
control panel on the overhead panel in flight compartment and shall be operated by the right
pilot. Ref. Fig 006 of 30-00-00 for the deicing control panel.
Normally, the intake deicing timer will control air intake deicing system alone. The air intake
deicing operation is programmed in one cycle per minute. The operating interval of each
group of deicing boots is 6 s. When each group of deicing boots is working, the corresponding
green indicator will be on and indicates whether deicing boots are working properly.
When there is a fault happens in the air intake deicing timer, the emergency deicing control
switch shall be set to the position of “WING & TAIL TIMER”. At this time, the airfoil deicing
timer controls the wing, stabilizer and air intake deicing system. The working mode of the
airfoil deicing timer is one cycles per minute.
Ref. Table 001 for the power supply of the components.
Table 001 Power Supply of Component
Component DC Busbar Power Supply (Circuit Breaker Panel)

Deicing timer RH normal DC busbar power supply

Pressure switch RH normal DC busbar power supply

Ejector flow control valve RH normal DC busbar power supply

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3. System Operation

A. Normal operation
In the normal working condition, the emergency deicing control switch shall be switched
to the position of “NORM” as neutral position, and the air intake deicing system is
controlled by the air intake deicing control switch alone.
In the normal working condition the air intake deicing system works in cycles and each
cycle lasts 1 min in the sequence of: left engine air intake deicing boots→ right engine air
intake deicing boots. During the working procedure, the air intake deicing boots will bulge
in order. The bulging on each side will lasts 6 s, and the green indicators on deicing
control panel will be on relatively at the same time.
After deicing, set the air intake deicing switch to the position of “OFF”, the system will
stop work.
B. Emergency operation
When there is a fault happens in the air intake deicing timer, the emergency deicing
control switch shall be set to the position of “WING & TAIL TIMER”. At this time, the airfoil
deicing timer controls the wing, stabilizer and air intake deicing system.
Set the air intake deicing switch to “OFF” position, then set wing and tail deicing switch to
the position of “HIGH” or “LOW”. All the deicing boots on the aircraft will work in cycles,
each cycle lasts 1 min in the sequence of: leading edge deicing boot for the center wing
→ No. 1 leading edge deicing boot of outboard wing→ No. 2 leading edge deicing boot
of outboard wing→ inside leading edge deicing boot of horizontal stabilizer→ leading
outside edge deicing boot of horizontal stabilizer, vertical stabilizer leading edge deicing
boot and air intake deicing boots of left engine→ air intake deicing boots of right engine.
Deicing boots will bulge in order. The bulging on each side will lasts 6 s, and the green
indicators on deicing control panel will be on relatively at the same time.

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SENSOR HEATING

1. General

The sensor heating system includes:

- Pitot /pitot probe heating (Refer to 30-31-00);
- Total air temperature sensor heating (Refer to 30-32-00);
- AOA sensor heating (Refer to 30-33-00).

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PITOT/PITOT PROBE HEATING

1. General

Pitot/ pitot probes heating system use the electrical power to heat the probes on the external
surface of the aircraft. That is to prevent from icing caused in flight which will affect sensors
working.

2. System Description

A. Function
The pitot/pitot probe are in the easy-frozen area on the external surface skin of aircraft.
There is electric heating resistance in those sensors to prevent those sensors from icing
failure during flight. The electric heating devices will work continuously to ensure probes
to work normally.

B. Operational Principle

Close the heating circuit breaker and turn on the heating switch and the aircraft power is
supplied to the pitots and the pitot probe through the heating relay. And the energized
resistance wire heats the sensors.

Meanwhile, there are airborne monitoring circuits to monitor the failure of the heating
circuits and to send the heating failure message to the pilot. When a heating circuit fails,
the indicator on the heating control panel comes on.

C. Installation Location

Ref. Table 001 for installation location of pitots and pitot probes.

Table 001 Location of Sensors

No. Name Type Installation Location Zone Access Remark

FR 9 thru FR 10 of
1 Left pitot GKY-10 231
LH fuselage
FR 9 thru FR 10 of
2 Right pitot GKY-10 232
RH fuselage
FR 5 thru FR 6 of LH
3 Pitot probe GKY-7A 213
fuselage

D. Power Supply

Pitot/pitot probe heating circuit breakers are installed on LH and RH DC C/B panels. Ref.
Table 002.
Power supply of left pitot heating is from 28.5 V Emergency/LH DC C/B panel.

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Power supply of right pitot heating is from 28.5 V Emergency/RH DC C/B panel.
Power supply of pitot probe heating is from 28.5 V Emergency/RH DC C/B panel.
Table 002 Pitot/Pitot Probe Heating System Circuit Breaker

Equipment Type Designation Row/Column Location

Left pitot heating BACC18Z10R L PITOT H7 LH DC C/B PNL

Right pitot heating BACC18Z10R R PITOT E2 RH DC C/B PNL

Pitot probe
BACC18Z10R PT STBY A2 RH DC C/B PNL
heating

3. Controls and Indicators

The heating switch for pitots and pitot probes is located on the heating control panel of the
right console.
Depress the “PITOT” and the “PT STBY” heating switch to energize the heating circuits of the
pitots and pitot probes and the applicable amber fault indicator on the switch goes off.
When one (or more than one) fault indicator(s) comes on, the applicable heat circuit is failed.

4. System Components

A. Pitot Heating
Close the “L PITOT” and “R PITOT” circuit breakers. Depress the “PITOT” heating
switches of the heating control panel the heating circuit begins work normally, and the
amber heating fault indicator will be off. At this time, there is electricity in electric heating
resistance in the pitot and the pitot will be heated.
If there are any faults in the heating circuit, related heating fault indicator will be on to
indicate those faults.
B. Pitot Probe Heating
Close the “PT STBY” circuit breaker. Depress the “PT STBY” heating switch in the
heating control panel, the heating circuit begins work normally, and the amber fault
indicator will be off. At this time, there is electricity in electric heating resistance in pitot
probe and the pitot probe will be heated.
If there are any faults in the heating circuit, related heating fault indicator will be on to
indicate those faults.

5. System Operation

CAUTION: THE HEATING SYSTEM SHALL NOT WORK EARLIER THAN 5 MIN BEFORE
THE AIRCRAFT TAKEOFF, AND SHALL BE TURNED OFF WITHIN 3 MIN
AFTER LANDING.

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Close the H7 “L PITOT” circuit breaker on LH DC C/B panel and A2 “PT STBY” circuit breaker
and E2 “R PITOT” circuit breaker on RH DC C/B panel. At this time, three heating fault
indicators (amber) on right console shall be on.
Set the “L PITOT”, “R PITOT” and “PT STBY” heating switches to ON. At this time, three
heating fault indicators on right console shall be off to indicate the heating circuit works
properly.
If there are any faults in the one of the heating circuit, related heating fault indicator will be on
to indicate those faults.
After checking, set all the heating switches off and open all the circuit breakers.

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TOTAL AIR TEMPERATURE SENSOR HEATING

1. General

The total air temperature sensor heating system uses the electrical power to heat the sensors
on the external surface of the aircraft. That is to prevent from icing caused in flight which will
affect sensors working.

2. System Description

A. Function
Total air temperature sensors are in the easy-frozen area on the external surface skin of
aircraft. There is electric heating resistance in the total air temperature sensors to prevent
the total air temperature sensors from icing failure during flight. The electric heating
devices will work continuously to ensure the total air temperature sensors to work
normally.

B. Operational Principle

Close the heating circuit breaker and turn on the heating switch and the aircraft power is
supplied to the total air temperature sensor heating through the heating relay. And the
energized resistance wire heats the sensors.

Meanwhile, there are airborne monitoring circuits to monitor the failure of the heating
circuits and to send the heating failure message to the pilot. When a heating circuit fails,
the indicator comes on.

C. Installation Location
Refer to Table 001 for installation location of the total air temperature sensor.
Table 001 Location of Total Air Temperature Sensor

No. Name Type Installation Location Zone Access Remarks

No. 1 total air FR 6 thru FR 7 of

1 102AU1AF 214
temperature sensor RH fuselage
No. 2 total air FR 6 thru FR 7 of
2 102AU1AF 214
temperature sensor RH fuselage

D. Power Supply

No. 1 TAT sensor is supplied by 28.5 VDC circuit breaker panel.

No. 2 TAT sensor is supplied by 28.5 VDC circuit breaker panel.
Ref. Table 002 for the power supply of TAT sensor heating.

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Table 002 Total Air Temperature Heating System Circuit Breaker

Equipment Type Designation Row/Column Location

No.1 total air temperature ELEC EQPT C/B

BACC18Z15R TAT 1 I1
sensor heating PNL
No.2 total air temperature ELEC EQPT C/B
BACC18Z15R TAT 2 R1
sensor heating PNL

3. Controls and Indicators

“TAT SENSOR” heating switches are on heating control panel on the right console in flight
compartment.
The heating circuit of the total air temperature sensor is controlled by AIR/GND relay. The
AIR/GND relay is controlled by gear landing switch.
CAUTION: THE GROUND HEATING CHECK SHALL BE LESS THAN 1 MIN. THE “TAT
SENSOR” SHALL BE SET OFF ONCE THE TEMPERATURE RISING IS ABLE
TO BE FELT BY HAND.
CAUTION: IF THE “AIR/GRD TRANSFER” CIRCUIT BREAKER IS NOT CLOSED, IT IS
FORBIDDEN TO SET “TAT SENSOR” HEATING SWITCHES ON.
There are heating switch of total air temperature sensor “UP”; heating indicators’ heating
switch of total air temperature sensor “LOW”; and heating indicators on the heating control
panel of right console. When “AIR/GRD TRANSFER” circuit breaker is not closed (same as
the situation of landing gear off-ground), set the heating switch of total temperature sensor on
and then the related heating indicators (amber) will be off. Set the heating switch of total
temperature sensor off, and then the related heating indicators (amber) will be on.

4. System Components

A. No.1 Total Air Temperature Sensor Heating

Close the heating circuit breaker and turn on the heating switch of total air temperature
sensor “UP” on right console. If the heating circuit works normally, the amber heating
indicator of the total air temperature sensor “UP” will be OFF. At this time, the electricity
will go through the electric heating resistance in the total air temperature sensor 1 for
heating the total air temperature sensor 1.
When there are any faults in the heating circuit, the amber indicator of total air
temperature sensor “UP” will be ON.
B. No.2 Total Air Temperature Sensor Heating
Close the heating circuit breaker and turn on the heating switch of total air temperature
sensor “LOW” on right console. If the heating circuit works normally, the amber heating
indicator of the total air temperature sensor “LOW” will be OFF. At this time, electricity will
go through the electric heating resistance in the total air temperature sensor 2 for heating
the total air temperature sensor 2.
When there are any faults in the heating circuit, the amber indicator of total air
temperature sensor “LOW” will be on.

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5. System Operation

CAUTION: THE HEATING SYSTEM SHALL NOT WORK EARLIER THAN 5 min BEFORE
THE AIRCRAFT TAKEOFF, AND SHALL BE TURNED OFF WITHIN 3 min
AFTER LANDING.
Check the heating switch of total air temperature sensor “UP” and “LOW” on the heating
control panel of right console to make sure that the heating switch is off, and “TAT 1” and “TAT
2” circuit breakers shall be pulled out. Make sure that the heating indicators are off.
Close the “TAT 1” and “TAT 2” circuit breakers on the electronic equipment C/B panel on
overhead control panel, the heating indicators of total air temperature sensor “UP” and “LOW”
on the heating control panel of right console shall be ON.
Set the heating switches of total air temperature sensor “UP” and “LOW” ON, the indicators
shall be off; you will feel the heat when touching the total air temperature sensor 1 by hand,.
Set the heating switches of total air temperature sensor “UP” and “LOW” OFF; open the “TAT
1” and “TAT 2” circuit breakers.

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AOA SENSOR HEATING

1. General

The AOA sensor heating system uses the electrical power to heat the AOA sensor on the
external surface of the aircraft. That is to prevent from icing caused in flight which will affect
sensors normal operation.

2. System Description

A. Function
The AOA sensor is in the easy-frozen area on the external surface skin of aircraft. There
is electric heating resistance in AOA sensors to prevent AOA sensors from icing failure
during the flight. The electric heating devices will work continuously to ensure AOA
sensors working normally.

B. Operational Principle

Close the heating circuit breaker and turn on the heating switch and the aircraft power is
supplied to the total air temperature sensor heating through the heating relay. And the
energized resistance wire heats the sensors.

Meanwhile, there are airborne monitoring circuits to monitor the failure of the heating
circuits and to send the heating failure message to the pilot. When a heating circuit fails,
the indicator comes on.

C. Installation Location
Ref. Table 001 for installation location of the AOA sensor.
Table 001 Location of AOA Sensor

No. Name Type Installation Location Zone Access Remarks

1 AOA sensor GGJ-3 FR 3 thru FR 4 of 211

LH fuselage

D. Power Supply

The AOA sensor heating circuit breaker is installed on the electronic equipment C/B
panel.
Ref. Table 002 for the power supply of AOA sensor heating.
Table 002 AOA Sensor Heating System Circuit Breaker

Equipment Type Designation Row/Column Location

AOA sensor BACC18Z15R STALL WS H1 ELEC EQPT C/B

heating PNL

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3. Controls and Indicators

The “AOA SENSOR” heating switch is located on the heating control panel of the flight
compartment overhead control panel.

Depress the “AOA SENSOR” heating switch to energize the heating circuit of AOA sensor and
the amber indicator comes on.

When AOA sensor heating circuit fails, the amber indicator of heating control panel will be on.

4. System Operation

CAUTION: THE HEATING SYSTEM SHALL NOT WORK EARLIER THAN 1 MIN BEFORE
THE AIRCRAFT TAKEOFF, AND SHALL BE TURNED OFF WITHIN 1 MIN
AFTER LANDING. THE INTERNAL UNIT WOULD BE DAMAGED IF GROUND
HEATING IS TOO LONG AND SENSOR OF ANGLE OF ATTACK WOULD BE
MALFUNCTIONED.
Close the H1 “STALL WS” circuit breaker on the electronic equipment C/B panel. Set the
“AOA SENSOR” heating switch on the heating control panel on. The electricity will go through
the electric heating resistance in the AOA sensors and the AOA sensors will be heated.

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 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

WINDOWS, WINDSHIELDS AND DOORS

1. General

During the fight in winter or under complicated weather conditions, when the aircraft is taking
off, landing or climbing, the windows and windshields system shall be able to ensure the
visibility for pilots and flight safety.

2. System Description

The windows and windshields ice and rain protection system includes windshields/side
windows heating system and windshield wiper system.
Ref. Fig. 001 for installation of the window and windshield system.

3. System Components

The windshields/side windows heating system refer to 30-41-00.

The windshield wiper system refer to 30-42-00.

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Figure 001 Installation Diagram of Window and Windshield

1. Right Electric Heating Windshield; 2. Right Electric Windshield Wiper; 3. Left Electric
Windshield Wiper; 4. Left Electric Heating Windshield; 5. Relay Box of Electric Windshield
Wiper; 6. Temperature Control Box; 7. Electric Heating Glass of Left Side Windows; 8. Electric
Heating Glass of Right Side Windows.

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WINDSHIELDS/SIDE WINDOWS HEATING SYSTEM

1. General

The windshields/side windows heating system is used to heat the left and right
windshields/side.

2. System Description

A. Function

In order to provide a good visibility for pilot during taking-off, landing and various flight
conditions and ensure the normal work of pilot under complicated weather conditions, the
electric heating method is adopted for the windshields/side windows to prevent it from
freezing, and ensure flight safety.

B. Components and Installation

Windshield/side windows heating system includes mainly left and right windshields, left
and right side windows, temperature control box WTR-II (4 units), heating glass switch
and indicator.
Ref. Table 001 for components and installation location of the windshields/side windows
heating system.
Table 001 Components and Installation Location of Windshields/Side Windows Heating System
No. Code Name Type Qty Location
1 481H Circuit breaker BACC18Z5R 1 RH DC C/B PNL

2 484H Heat switch MS24524-21 1 Control panel of icing

detector/glass heating/wiper
3 482H Three-phase C/B 4330-001-10 1 VAR FREQ AC C/B PNL

4 483H Three-phase C/B 4330-001-10 1 VAR FREQ AC C/B PNL

5 485H Three-phase C/B 4330-001-10 1 VAR FREQ AC C/B PNL

6 486H Three-phase C/B 4330-001-10 1 VAR FREQ AC C/B PNL

7 487H LH windshield WTR-II 1 Electronic equipment bracket

temperature control box before FR7

8 488H RH windshield WTR-II 1 Electronic equipment bracket

temperature control box before FR7

9 489H LH side windows WTR-II 1 Electronic equipment bracket

temperature control box before FR7

10 490H RH side windows WTR-II 1 Electronic equipment bracket

temperature control box before FR7

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Table 001 Components and Installation Location of Windshields/Side Windows Heating System
No. Code Name Type Qty Location

11 491H Left windshield glass 1 Left windshield

12 492H Right windshield glass 1 Right windshield

13 493H Left side glass 1 Left side window

14 494H Right side glass 1 Right side window

15 499H Indicator MS25041-3 1 Control panel of icing

detector/glass heating/wiper

C. Power Supply

Ref. Table 002 for the power supply of the windshields/side windows heating system.

Table 002 Power Supply

Equipment CB Type CB Designation Bus Bar, Breaker Panel Remarks

Windshield/ BACC18Z5R WSHLD HT Normal bus/28.5 VDC RH DC

side C/B panel
windows
heating 4330-001-10 WSHLD HT 115 VAC VAR FREQ C/B PNL
system
4330-001-10 L SIDE WINDOW 115 VAC VAR FREQ C/B PNL

4330-001-10 WSHLD HT 115 VAC VAR FREQ C/B PNL

4330-001-10 R SIDE WINDOW 115 VAC VAR FREQ C/B PNL

D. Controls and Indications

The controls and indicators of windshield/side windows heating system are located on
the control panel of icing detector/glass heating/wiper at the top of the flight compartment,
Ref. Fig 001.

3. System Operation
Ref. Fig. 002 for the block diagram of the windshield/side windows system
Windshield/side windows system is an automatic heating anti-icing system, and is divided into
two kinds of working conditions, i.e. weak heating and strong heating.
Lower heating working condition should be set first during the normal flight, and is converted
to the strong heating working condition when entering the icing area. The higher heating can
be allowed only after 5 min to 6 min lower heating.
Heating of windshields is automatically controlled by a temperature control box, to ensure that
the circuit is disconnected when the temperature is up to 30℃(86℉), and connected when the
temperature is reduced to 25℃(77℉) so as to ensure the normal heating of glasses.

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When the glass temperature thermistor has a short circuit or open circuit, the “L WSHLD”, “R
WSHLD”, “L WSHLD” and “R WSHLD” orange warning lights on the integrated warning light
box are “ON”.
If a glass thermistor has a short circuit or open circuit fault, the related temperature control
box will stop controlling the heating, and the other temperature control box at the other side
has the capacity to control the heating for two glasses simultaneously, i.e. the temperature
control box has the function to support each other to improve the reliability of system.
The operation principles of the left and right windshield/side windows heating system are the
same.
The example that follows refers to the left windshield:
- Open the T6 “WSHLD HT” 481H on the RH DC C/B panel, and the A1 “WSHLD HT” 482H
and K1 “WSHLD HT” 483H on the frequency conversion AC C/B Panel.
- Set the switch “WSHLD HEAT” 484H on the control panel of icing detector/glass heating
/wiper at the top in “LOW HEAT” position.
- When the temperature of thermistor is below 25℃(77℉), the glass temperature will rise
gradually with the connection of inner temperature control box.
- When rising to 30℃(86℉), its resistance value will be reduced, and the heating circuit in the
temperature control box will be disconnected and stop heating.
- When reducing to 25℃(77℉), the system will be reconnected for heating, and such cycle
will make the glass temperature between 25℃(68℉) to 30℃(86℉).
- When the thermistor has an open circuit or short circuit, the “L WSHLD” orange warning light
on the integrated warning light box is “ON”.
- When the thermistor has an open circuit or short circuit, the logic control circuit within the left
windshield glass (491H) seals off the output signal of its temperature comparator, in this
case, the output signals are connected through the holes ④ and ○ 11 at the left windshield

temperature control box and the holes ○ 11 and ④ at the right windshield temperature
control box (488H).
- The control signal of right windshield temperature control box (488H) is sent to the left
windshield temperature control box (487H). So that the left glass (491H) will continue to
heat (on the contrary, when the right thermistor has an open circuit or short circuit, the signal
of left windshield temperature control box can also make the right glass continuing to heat).

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Figure 001 Control Panel of Icing Detector/ Glass Heating /Wiper

1. Glass Heating Indicator; 2. Glass High/Low Heating Switch.

115 V variable frequency AC power supply

WTR-II left side window

Left side window
temperature control box

115 V variable frequency

AC power supply

Heating indicator
WTR-II left windshield Left windshield
temperature control box

Right normal Glass heating

+28.5 V power switch 115 V variable frequency AC power supply

WTR-II right windshield Right windshield

temperature control box

115 V variable frequency

AC power supply

WTR-II right side window

Left side window
temperature control box

Figure 002 Schematic Diagram of Windshields/Side Windows Heating System

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WINDSHIELD WIPER SYSTEM

1. General

The windshield wiper system is to utilize the DC to operate the wiper blade for left and right
swinging on the windshield so as to remove the rainwater and ice-snow on the windshield,
and keep a good transparency for the front windshield.

2. System Description

A. Location and Description of Main Accessories

Electric windshield wiper system consists of left and right electric windshield wipers and
windshield wiper relay box. Left and right electric windshield wipers are fully symmetrical
and independent.
Left and right electric windshield wipers consist of electric reducer assembly, wiper rod,
wiper blade and knob switch assembly.

Ref. Fig 001 for the appearance and composition of the electric windshield wiper.

Ref. Table 001 for location and description of main accessories of the electric windshield
wiper system.

Table 001 Location and Description of Main Accessories of Windshield wiper system

No. Name Type Qty Installation location Zone Access

Electric
1 4351933 One for each
windshield wiper
Lower edge of left and right
electric reducer 4351897,
2 One for each windshields within the flight 211
assembly 4351881
compartment
4388637,
Lower edge of left and right
4388644/
3 Wiper rod One for each windshields outside the flight 211
4351919,
compartment
4351903
Lower edge of left and right
4 Wiper blade 4351926 2 windshields outside the flight 211
compartment
Control panel of icing
Knob switch detector/ glass heating
5 4353464 2 211
assembly /wiper overhead flight
compartment
Under the right floor of FR 5
Windshield wiper
6 1 thru FR 7 of flight 214
relay box
compartment

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Figure 001 Electric Windshield Wiper System

1. Right Electric Reducer Assembly; 2. Left Electric Reducer Assembly; 3. Right Wiper Rod; 4.
Left Wiper Rod; 5. Wiper Blade Assembly; 6. Knob Switch Assembly; 7, 8. Connector and
Pigtail Holder.

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B. Main Technical Data

Operation height .................................................. 0 m to 10000 m (0 ft to 32808.4 ft)

Ambient temperature ................................................. -65℃ to 71℃(-85℉ to 160℉)

Operation temperature ................................................ -15℃ to 55℃(5℉ to 131℉),

+70℃(158℉) within 3 min is allowable

Operation pressure .................................................................................... 28 VDC

Operation current................ 6 A when the quickness is no larger than 130 times/min

.............................................. 3.5 A when the slowness is no less than 80 times/min

Flight speed during the operation of wiper ......................... Not exceeding 335 km/h

Fly-back angle of wiper

With no aerodynamic loading (maximum) ................................................. 50°

With aerodynamic loading (flight speed is 335 km/h) ........................... 46°－2°

+4°

Rotation angle of wiper arm when the wiper is reset .....................................14°±1°

Pressure of wiper on the glass surface (ground) ..... 35 N±2 N (7.868 lbf±0.450 lbf)

Refer to the following table for the sweep frequency of wiper and the current when the
temperature is 20℃(68℉) and the voltage is 28 VDC±0.5 VDC:

SLOW FAST
Flight speed
km/h (mile/h)
Sweep /min Current(A) Sweep/min Current (A)

0 to 148
83 2.5 130 4
(0 to 91.963)

148 to 230
80 3 125 4.5
(91.963 to 142.915)

230 to 295
75 5 110 6.5
(142.915 to 183.305)

295 to 335
70 6.5 100 9
(183.305 to 208.159)

C. Components

Ref. Table 002 for electrical control elements of windshield wiper and installation location.

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Table 002 Electrical Control Elements of Windshield Wiper and Installation Location

No. Name Type Qty Location

21M Breaker BACC18Z10R 1 100 LH DC C/B panel

22M Breaker BACC18Z10R 1 100 LH DC C/B panel

046 Overhead heating

23M Knob switch 4353464 1
panel
046 Overhead heating
24M Knob switch 4353464 1
panel
Left electric reducer 4351897/21210 FR 1 thru FR 2 under left
25M 1
assembly 1 windshield
Right electric reducer 4351881/21220 FR 1 thru FR 2 under
26M 1
assembly 1 right windshield
27M
Left wiper relay JKB-52B 1 Wiper relay box

28M Left wiper relay JKB-52B 1 Wiper relay box

29M Right wiper relay JKB-52B 1 Wiper relay box

30M Right wiper relay JKB-52B 1 Wiper relay box

D. Controls and Indications

The control switches and indicators of the windshield wiper system are located on the ice
detection/windshield heating/windshield wiper panel of overhead panel in the flight
compartment.
Wiper rotary switch: used to control the corresponding left and right windshield wipers.
FAST: Windshield wiper works according to 130 times/min.
SLOW: Windshield wiper works according to 80 times/min.
RESET: Windshield wiper stops at the final position.

3. System Components
A. Electric Windshield Wiper
Electric windshield wiper wipes the windshield.
When the electric windshield wiper stops the operation, it will stay at the lower frame of
windshield. The view of the pilot does not black out with electric windshield wiper.
B. Relay Box of Electric Windshield Wiper
Electric windshield wiper relay and knob switch assembly are used together to control the

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4 relays are used in the windshield wiper control circuit to control the operating conditions
of windshield wiper. When the two left and right relays (27M and 29M) operate, the left
and right windshield wipers are in the SLOW operating conditions. When 4 relays (27M,
28M, 29M and 30M) operate, the left and right windshield wipers are in the FAST
operating conditions.
Technical data of relay JKB-52B:
Coil voltage ................................................................................................ 27 VDC
Coil current ................................................................................................... 0.22 A
Contact voltage .......................................................................................... 27 VDC
Contact DC ...................................................................................... 10 A (τ≤0.015)
Pull-in voltage ............................................................................................ 18 VDC
Relief voltage ............................................................................................ 6.5 VDC
C. Knob Switch Assembly
CAUTION: KNOB SWITCH CAN ONLY BE ROTATED 240° BACK AND FORTH, AND
THE 360° ROTATION IS NOT ALLOWED, OTHERWISE THE SWITCH
WILL BE DAMAGED.
The knob switch assembly consists of electric rotary switch and knob matching with the
switch. It is the pure electrical element. The knob switch operated at 3 positions –
“RESET”, “SLOW” and “FAST”, to control the operating speed of electric windshield wiper.
3 work positions have a difference of 120° respectively.
D. Mounting Rack of Windshield Wiper
Mounting rack of windshield wiper is used to fix the electric reducer assembly, and
support the whole electric windshield wiper, with the installation surface of mounting rack
required to be parallel with the surface of windshield to ensure the normal work of
windshield wiper.
Mounting rack of windshield wiper is riveted on the inner skin in front of the aircraft nose
FR 2 under the windshield, and the mounting racks of left and right windshield wipers are
installed symmetrically.
E. Seal Assembly
Electric speed reducer assembly is installed inside the air-tight compartment, and the
wiper rod and blade assembly is installed outside the air-tight compartment. Therefore,
the middle is connected and controlled by the output shaft of electric reducer assembly.
Seal assembly is to make the output shaft go across the elliptical hole of aircraft skin for
sealing (depending on the sealant ring in the seal assembly) to ensure the airtightness of
air-tight compartment.
Seal assembly is installed between inner skin opening of air-tight compartment and
mounting rack. It is connected and fixed with screws.
F. Locating Support of Wiper Rod
Locating support of wiper rod is installed on the pressing plate of the lower frame of
windshield, and is taken as the support member when the wiper rod stops.

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4. System Operation
A. Operation Principle
The operation principles of left and right windshield wipers are the same, now taking the
left windshield wiper as an example.
CAUTION: WATER OR ALCOHOL MUST BE SPRINKLED IN CASE OF POWER-ON
INSPECTION AS THE DRY WIPING IS NOT ALLOWED FOR THE
WINDSHIELD WIPER.
Close the V6 “L WSHLD” circuit breaker (21M) on the RH DC C/B panel. When the switch
(23M) rotates to the “SLOW” position anticlockwise, the relay (27M) is turned on, with the
positive electricity entering the electric mechanism through the circuit breaker (21M) →
contact 3·2 of relay (27M) →contact 2·1 of relay (28M) →E-hole of electric reducer
assembly (25M) →F-hole of electric reducer assembly (25M) →contact 5·6 of relay
(27M) →grounded. At this moment, the windshield wiper will wipe slowly on the outer
surface of windshield. Then turn the switch (23M) anticlockwise to the “FAST” position
from the “SLOW” position. At this moment, the relays (27M and 28M) are turned on, the
positive electricity entering the electric mechanism through the circuit breaker (21M) →
contact 3·2 of relay (27M) →contact 2·3 of relay (28M) →D-hole of electric reducer
assembly (25M), and grounded through the F-hole of electric reducer assembly (25M) →
contact 5·6 of relay (27M) →grounded. Windshield wiper will work in the fast state.
Finally, turn the switch (23M) clockwise back to the “RESET” position through the
“SLOW” position
B. Operation Precautions
Knob switch is only allowed to turn to the “SLOW” and then to the “FAST” anticlockwise
from the “RESET”; Then turn to the “SLOW” and then to the “RESET” clockwise from the
“FAST”; Turning to the “FAST” clockwise from the “RESET” or to the “RESET” position
anticlockwise from the “FAST” are not allowed.
When the flight speed exceeds 335 km/h (208.159 mile/h), the electric windshield wiper
is not allowed to be connected.
Electric windshield wiper cannot be used on the dry electric heating glass for the wiper
blade to avoid the anti-static coating of glass surface from wearing.
When the aircraft takes off, lands or flies at low altitude in rainy or snowy day, the electric
windshield wiper system can be used to ensure the clarity of windshield and flight safety.
C. Operation
CAUTION: DRY WIPING NOT ALLOWED IN CASE OF GROUND DEBUGGING, THE
GLASS SURFACE MUST BE WATERED TO KEEP WET.
CAUTION: WHEN THE FLIGHT SPEED EXCEEDS 335 km/h (181 kt), THE
WINDSHIELD WIPER CANNOT BE USED.
When the electric windshield wiper system doesn’t work, the wiper blade of windshield
wiper will stop on the lower frame of windshield. Electric windshield wiper starts to work
as necessary when the knob control switches of left “WSHLD WIPER” and right “WSHLD
WIPER” on the control panel of Icing probe/glass heating /wiper at the top of the flight
compartment are turned to the “SLOW” anticlockwise from the “RESET” position.
If the motor of electric reducer assembly is energized by low voltage, the motor will run in at a low

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speed, through the electric reducer assembly to reduce the speed in one hand , the
rotation is converted to swing the reducer output shaft on the other hand.
Firstly the wiper arm and blade of electric windshield wiper will return slowly on the
windshield after rotating 14°±1° upward from the deck stopping at the lower frame of
+4°
windshield, with the fly-back angle of 46°－2° and speed no larger than 85 cycles/min.

When the knob turns to the “FAST” anticlockwise from the “SLOW”, the windshield wiper
rod and blade return back fast, with the speed no less than 100 cycles/min. If the
windshield has been cleaned, when the “WSHLD WIPER” knob on the control panel of
icing detector/glass heating/wiper is turned to the “SLOW” and then to the “RESET”
position clockwise from the “FAST”, the windshield wiper rod and blade will stop on the
glass for returning, move downwards automatically, and stop on the deck of lower frame
of glass before recovering the work.
D. Power Supply
Refer to Table 003 for power supply.
Table 003 Power Supply

Equipment DC Power Supply Bus

LH windshield wiper RH normal DC busbar power supply

RH windshield wiper RH normal DC busbar power supply

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PROPELLERS ANTI-ICING

1. General

Function of propellers anti-icing system is to prevent the propellers from icing by using the
propellers anti-icing system when the aircraft enters the icing area.

2. System Description

Ref. Fig 001.

Propellers anti-icing system consists of bulkhead and sliding ring, carbon brush sliding block
assembly, dual mode heating timer, oil low pressure sensor, anti-icing heater and contactor,
etc.
The steady current from carbon brush sliding block is transmitted to the resistance heater at
the leading edge of propeller blade by the sliding ring.
There are two propeller heating timers for mutual backup. If a fault happens in a timer, another
timer can be converted by operating the timer selector switch.
When the selector switch is set to the “LOW” position below, the heating timer will control the
resistance heater of each group of blade. Connect 10 s for heating and anti-icing, and
disconnect 60 s for cycle. Corresponding indicator must be ON in case of heating to indicate
the work is normal.
Propellers anti-icing system is interlocked with the engine oil pressure switch and landing
gear touchdown switch , and the heating can be allowed only when the engine oil pressure is
higher than 2.76 MPa±0.0414 MPa (40.03 psi±6.005 psi) and the landing gear off the ground.
Each propeller has 4 blades, each two symmetrical blade heaters is one group, and two pairs
of propellers have totally 4 groups of blade for heating in turn.
Propellers anti-icing system is interconnected with the engine oil system. When the oil
pressure of a certain engine is below the setting value, the propeller anti-icing power on one
corresponding side will be cut off automatically. Power supply required by the propellers
anti-icing system is 115 V and 400 Hz, and the anti-icing current is transmitted onto the
propeller sliding ring and blade anti-icing heater by the carbon brush sliding block. Ref. Fig 002.
There are two optional modes of propeller blade anti-icing, and can be selected according to
the temperature. When the selector switch is set to the “HIGH” position, the heating time will
control the resistance heater of each group of blade. Connect 20 s for heating and anti-icing,
and disconnect 60 s for cycle. Corresponding indicator must be ON in case of heating to
indicate the work is normal.
NOTES:
① "LOW" state must be selected when the temperature is higher than -10℃ (14℉).

② "HIGH" state must be selected when the temperature is lower than -10℃ (14℉).
Time sequence diagram that the heating timer of propeller blade anti-icing system controlling
the blade anti-icing is shown in Fig 003.

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Figure 001 Propellers Anti-icing System

1. Blade Anti-icer; 2. Bulkhead and Slip Ring; 3. Carbon Brush Sliding Block; 4. Heating Timer.

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Figure 002 Carbon Brush Sliding Block

1. Carbon Brush Sliding Block Assembly; 2. Carbon Brush Sliding Block Mount Bracket; 3.
Cable Connector of Carbon Brush Sliding Block; 4. Attaching Bolt of Carbon Brush Sliding
Block.

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Slight icing: (unit: s)

Left

Right

Left

Right

Severe Icing: (unit: s)

Left

Right

Left

Right

NOTE: There is 30 s interval from slight icing to severe icing but no interval from heavy icing
to slight icing.

Figure 003 Diagram of Propeller Blade Anti-icing Sequence

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Ref. Table 001 for the components and installation location of propeller heating system.
Table 001 Components and Installation Location of Propeller Heating System

No. Name Type Qty Location

1H Heater 1 circuit breaker BACC18Z25B 1 Variable frequency AC C/B

panel of FR 6 thru FR 7

2H Heater 2 circuit breaker BACC18Z25B 1 Variable frequency AC C/B

panel of FR 6 thru FR 7

3H Heating interlock circuit BACC18Z1R 1 LH DC circuit breaker

breaker panel of AFT LH FR 5

4H Timer 1 HS774934-1 1 Below the floor of FR 25

thru FR 26

5H Diode 2CZ53D 1 Relay box on the ceiling

behind the FR 26

6H LH engine oil interlocked JKB-22B 1 Relay box on the ceiling

relay behind the FR 26

7H LH oil low pressure XY-15 1 Left lower support rod of

sensor FR 8 thru FR 9 of LH
nacelle

8H Diode 2CZ53D 1 Contactor box on the

ceiling behind the FR 11

9H Contactor 6041H219 1 Contactor box on the

ceiling behind the FR 11

10H Diode 2CZ53D 1 Contactor box on the

ceiling behind the FR 11

11H Contactor 6041H219 1 Contactor box on the

ceiling behind the FR 11

12H LH carbon brush sliding 782689-6 1 LH propeller spinner

block assembly

13H Propellers heating C/B BACC18Z2R 1 LH DC circuit breaker

panel of AFT LH FR 5

14H Propellers heating check MS24524-23 1 Heating control panel

switch

15H Propellers heating timer MS24523-21 1 Heating control panel

selector switch

16H Propellers heating MS24523-23 1 Heating control panel

selector switch

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Table 001 Components and Installation Location of Propeller Heating System

No. Name Type Qty Location

17H Diode IN4003 1 Relay box on the ceiling

behind the FR 26
18H Diode IN4003 1 Relay box on the ceiling
behind the FR 26
19H Timer 2 HS774934-1 1 Below the floor of FR 25
thru FR 26
20H Blade heating indicator MS25041-3(327) 1 Heating control panel

21H RH engine oil interlocked JKB-22B 1 Relay box on the ceiling

relay behind the FR 26
22H Blade heating indicator MS25041-3(327) 1 Heating control panel

23H Blade heating indicator MS25041-3(327) 1 Heating control panel

24H Blade heating indicator MS25041-3(327) 1 Heating control panel

25H Diode 2CZ53D 1 Contactor box

26H Contactor 6041H219 1 Contactor box

27H RH carbon brush sliding 782689-6 1 RH propeller spinner

block assembly
28H Heating interlock circuit BACC18Z1R 1 LH DC circuit breaker
breaker panel of AFT LH FR 5
29H Heater 3 circuit breaker BACC18Z25B 1 Variable frequency AC C/B
panel of FR 6 thru FR 7
30H Heater 4 circuit breaker BACC18Z25B 1 Variable frequency AC C/B
panel of FR 6 thru FR 7
31H Diode 2CZ53D 1 Relay box on the ceiling
behind the FR 26
32H RH engine oil low XY-15 1 Left lower support rod of
pressure sensor FR 8 thru FR 9 of RH
nacelle
33H Diode 2CZ53D 1 Contactor box on the
ceiling behind the FR 11
34H Contactor 6041H219 1 Contactor box on the
ceiling behind the FR 11

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3. System Components

A. Heating Timer
Technical data:
Rated voltage ............................................................................................. 28 VDC
Rated current .................................................................................................... 1 A
B. Carbon Brush Sliding Block Assembly
Technical data:
Rated voltage ............................................................................................ 115 VAC
Frequency ................................................................................................... 400 Hz
Rated power/blade ..................................................................................... 1404 W
Rated power/pair of blade .......................................................................... 2808 W
Pure resistance property
C. Oil Low Pressure Sensor
Technical data:
Rated voltage ........................................................................... 28 VDC±10% VDC
Rated current ............................................................................. No larger than 1 A
Oil pressure higher than 0.276 MPa±0.0414 MPa (40.030 psi±6.005 psi) .... 1-2 ON
Oil pressure lower than 0.276 MPa±0.0414 MPa (40.030 psi±6.005 psi) ..... 1-3 ON

4. System Operation
A. Heating Timer
There are two working modes for the heating timer: heating 20 s, and disconnecting 60 s;
or heating 10 s, and disconnecting 60 s.
When the propellers heating system is turned off, the work timer will recall the
implementation position of heating and circulation. When the propellers heating system is
reconnected, it will continue to implement heating according to the position recalled by
the timer used.
B. Anti-icing Heater
Heat the propellers to prevent it from icing.
C. Oil Low Pressure Sensor
Oil low pressure sensor is interlocked with the propeller to ensure it does not continuous
to heat when the engine shuts down.

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ICEING DETECTION

1. General

Ice detection system is used to forecast the icing of aircraft, and the pilot can select the best
time of deicing according to the signals sent by the system to ensure flight safety.

2. System Description

Ref. Fig 001.

Icing detection system consists of icing annunciator and icing probe (icing probe bar).
Icing annunciator consists of two parts, i.e. sensor and follower. When the aircraft flies in the
icing area, the icing annunciator will send the aircraft icing warning message to alert the A/C
crew that the aircraft has entered the icing area for flight.
Icing probe is installed below the right side-window of outer side fuselage, and the LH pilot
can observe the icing of icing probe bar to determine the best time of operating the pneumatic
deicing system.

Figure 001 Installation Diagram of Icing Detection System

1. Icing Probe BTQ-1; 2. Sensor of Icing Annunciator BXH-2G; 3. Follower of Icing

Annunciator BXH-2G.

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3. System Components

For details of the icing annunciator, refer to 30-81-00.

For details of the icing probe, refer to 30-82-00.

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ICING ANNUNCIATOR

1. General

When the aircraft is flying in icing airspace, the icing annunciator sends icing warning
message to the crew.

2. System Description

A. Location and Description of Main Accessories

Icing annunciator BXH-2G consists of the sensor and the follower. The sensor is used to
sense the ambient temperature and humidity. When the icing condition is sensed, the
follower sends signals to the crew.

The sensor is used in collaboration with the follower. Once the adjustment is completed,
the two devices can not be replaced by others, otherwise readjustment is needed.

Ref. Table 001 for location and description of main accessories of the icing annunciator.

Table 001 Location and Description of Main Accessories of Icing Annunciator

Zone
No. Name Type Qty Installation Location
Access

On the nose outer

Sensor of icing
1 BXH-2G 1 skin, lower right side, 211
annunicator
at FR 1A thru FR 1

Below the right floor

Icing annunciator of the flight
2 BXH-2G 1 214
follower compartment at FR 5
thru FR 7

B. Main Technical Data

Operation height ................................................ 0 m to 18000 m (0 ft to 59055.12 ft)

Ambient temperature .......................................... ﹣55℃ to﹢60℃ (﹣67°F to 140°°F)

Voltage of DC power ........................................................................... 25 V to 30 V

Power consumption

In non-icing condition...........................................................no more than 20 W

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In icing condition ................................................................. no more than 80 W

Temperature range for icing signals ON ....................................................................

........................................................................................ no lower than ﹣1℃ (30℉)

...................................................................................... no higher than ＋2℃ (36℉)

Surface temperature of the sensor end ....................... 30℃ to 45℃ (86℉ to 113℉)

Delay time of icing announciator ............................................................ 40 s to 60 s

Interval between icing operations .................................................................... 7 min

Working state .......................................................................................... continuous

C. Components

Ref. Table 002 for electrical control elements of icing annunciator and installation
location.

Table 002 Electrical Control Elements of Icing Annunciator and Installation Location

No. Name Type Qty Location

On right DC circuit breaker

231H Circuit breaker BACC18Z5R 1
panel

On the icing detection/glass

232H Switch MS24524-21 1 heating/windshield wiper
panel

Icing annunciator On the right floor at FR 5 thru

233H BXH-2G 1
follower FR 7

On the right side of FR 1 thru

Icing annunciator
234H BXH-2G 1 FR 1A outside the flight
sensor
compartment

D. Controls and Indications

The control switches of the icing annunciator are located on the icing detection/glass
heating/windshield wiper panel of overhead panel in the flight compartment. Ref. Fig 002
in 30-41-00.

Set the control switch of icing annunciator to “TEST” location and check the operation of
the icing annunciator on ground. Set the switch to “ON” and the icing annunciator is in
working state.

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3. System Components

A. Icing Annunciator Sensor

The icing annunciator sensor is installed on the outer skin at the lower right side of the
nose at FR1A thru FR1. The sensor end directly aims at the airstream to sense the
ambient temperature and humidity during flight.

The sensor end of icing annunciator is composed of the inner and outer sleeves with
insulation layer between them, respectively connected to the power supply. When the air
contains extremely cold water and the ambient environment reaches a certain low
temperature, the inner and outer sleeves are conductive because of condensation of cold
water. The follower of the icing annunciator sends signals and forecasts the entry into the
icing airspace and the possibility of icing.

The sensor end can automatically be heated to remove the accumulated ice for next use.

B. Icing Annunciator Follower

The follower is installed below the right floor in the flight compartment at FR5 thru FR7.

The follower mainly contains electronic assemblies in its housing. It supplies the power to
the icing annunciator sensor. On the other hand, it amplifies icing signals from the sensor
and the signal light circuit is connected with the signal light on. Meanwhile, the power is
supplied to the heating circuit of the sensor end to remove the ice accumulated on the
end for next use.

4. System Operation

The icing annunciator BXH-2G is based on the conductivity of the ice accumulated on the
sensor end. Close the circuit breaker (231H) and Set the switch (232H) to “ON” location, and
the follower (233H) supplies 20 V to the outer sleeve of the sensor (234H) and the icing
annunciator operates in the follower armed icing state. When the sensor surface temperature
is lower than ＋2℃ (36℉), the RT value of the thermistor increases, and relay J1 in the
follower operates and its contact points engage the icing signal input channel. When ice or
water accumulates on the sensor surface, short circuit occurs to the inner and outer sleeves
in the sensor and the icing signal is sent to the follower. As the follower supplies signal to the
integrated warning light box, warning light come on. During the continuous, send the warning
signal intermittently to the crew, informing the pilot of the aircraft entry into the icing airspace.
Meanwhile, the follower also supplies 28 V power to the heating resistor R in the sensor to
melt its external ice and to heat the thermistor RT. As the resistance value decreases, the
icing signal input channel is cut off. The icing signal display delay time is 50 s±10 s starting
from the icing signal input. When the above conditions appear again, the icing annunciator will
send icing signals. The interval between two icing conditions of the icing annunciator is within
7 min.

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Icing annunciator BXH-2G is used to forecast the icing signal according to the conductivity of
the condensed ice on the sensor end.

Set the icing annunciator control switch to “ON” location and the follower of the icing
annunciator starts to operate in servo state.

Normally, the inner and outer sleeves of the icing annunciator sensor are insulated to each
other. When the ambient air contains a great deal of extremely cold water and the
temperature falls below ﹢2℃ (36°F), the cold water is condensed on the sensor end, leading
to the conductivity between the inner and outer sleeves, and as a result, the relay in the
follower is energized and supplies 27 V voltage to the heating resistor and the annunciator. At
this time, the warning light is ON, informing the pilot of the aircraft entry into the icing airspace.

After power-on, the heating resistor heats the sensor and the ice on the sensor end melts.
The circuit is disconnected and thus the relay is de-energized and the sensor stops heating.
But the annunciator will go off after about 1 min due to the delay circuit, and the indication light
is OFF.

The sensor begins to cool down. When its surface temperature falls to 0℃ (32°F), the ice
accumulates again on the surface between the two sleeves and the procedure mentioned
above will be repeated after 7 min. In this way, the annunciator sends signals at intervals
during continuous icing.

Ref. Table 003 for the power supply of icing annunciator.

Table 003 Power Supply

Equipment DC Power Supply Bus

Icing annunciator RH normal DC busbar power supply

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ICING PROBE

1. General

Icing probe is for the pilot to directly observe the icing visually, providing intuitive signal for
deicing system independently, with the safety and reliability of the system increased.

2. System Description

A. Location and Description

Ref. Fig 001.
Icing probe BTQ-1 (also called icing probe bar) is installed at the place below the
side-window of RH pilot of external aircraft nose and where the bar can be easily seen.
The bar of icing probe is an airfoil profile bar, leaning backward with the airflow. To
facilitate the night observation, a special focus lamp is set to light the bar.

Figure 001 Outside View of Icing Probe

1. Airfoil Profile Bar; 2. Spotlight; 3. Flange; 4. Base.

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B. Icing Probe Main Technical Data

Power supply voltage ......................................................................... 27±10% VDC
＋50
Melting ice consumed power ............................................................ 500 W -100 W

C. Components
Ref. Table 001 for electrical control elements and their installation location of the icing
probe.
Table 001 Electrical Control Elements and Installation Location of Icing Probe

No. Name Type Qty Location

131H Circuit breaker BACC18Z20G 1 RH DC C/B panel

Icing detection/windshield
132H Switch MS24523-22 1 heating/windshield wiper
panel
Icing detection/windshield
133H Switch MS24523-30 1 heating/windshield wiper
panel
Icing detection/windshield
Icing probe heating heating/windshield wiper
134H MS25041-3 1
indicator panel
Icing detection/windshield
Bulb MS25237-327 1 heating/windshield wiper
panel
STR 24 to STR 25, right
135H Icing probe BTQ-1 1 side, before FR4 (outside
the fuselage)

D. Controls and Indicators

Controls of icing probe are located on the control panel for windshield heat/icing
probes/windshield wiper at the top of the flight compartment. Ref. Fig 002 in 30-41-00.
(1) Icing Probe Light Switch
Light switch is generally used when the aircraft enters the icing area in the night
flight. When the switch is ON, the lamp on the icing probe will light up on the bar
directly for observing the icing easily.
(2) Icing Probe Heating Switch and Heating Indicator
When the ice on the icing probe bar gets to a certain thickness after the aircraft
enters the icing area, engage the heal switch, then the bar is heated and the ice on it
is removed. In this case, the heating indicator should be ON to indicate the heating is
normal.

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3. System Operation
Ice layer will be accumulated on the icing detection bar when the aircraft enters the icing area,
and the pilot can clearly see the icing severity on the icing probe through the flight
compartment glass. Connect the “LT ON” switch (132H) during the night flight to make the
illuminator within the icing probe BTQ-1 (135H) being ON, then the icing severity can be seen.
Then put the heating switch (133H) at the “HEAT ON” position, and power on the heating
element on the icing detection bar to remove the ice layer, and make preparations for the icing
detection next time. At the same time, the “HEAT” light (134H) is ON.
When the signal is sent by the icing annunciator after the aircraft enters the icing area, the RH
pilot can judge the icing severity of aircraft and determine the best time of aircraft’ pneumatic
deicing system for deicing by observing the icing severity on the icing probe bar outside the
side-window of flight compartment.
During the operation of deicing system, the RH pilot should set the icing probe switch at the
“HEAT ON” position. In this case, the “HEAT” indicator should be ON, and the bar heating
element should be powered on to remove the ice on the bar. After the ice on the bar is
removed, the heating switch should be set at the “HEAT OFF” position. In this case, the
heating indicator is OFF to stop heating the bar for easily observing the bar icing next time.
When the aircraft enters the icing area in the night flight, the light switch should be pressed,
after which the “LT ON” on the switch is ON, and the focus lamp on the icing probe lights up
on the bar directly for observing the icing easily.
Ref. Table 002 for power supply.
Table 002 Power Supply

Equipment DC Power Supply Bus

RH normal DC busbar power

Icing probe
supply

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