MT-Propeller E-3760 Specification sheet

EASA DE.21G.0008
EASA.21J.020
(E-3760)
ATA 61-07-60
OPERATION- and
INSTALLATION MANUAL
ELECTRIC DE-ICE CONTROLLER
Original Issue: July 1st, 2021
The technical content of this document is approved under authority of DOA No. EASA.21J.020.

ATA 61-07-60
WARNING
People who fly should recognize that various types of risks are involved; and they should take all
precautions to minimize them, since they cannot be eliminated entirely.
Before a MT Electric De-Ice Controller is certified as being safe to operate on an airplane, an
adequate margin of safety must be demonstrated. Even though every precaution is taken in the
design and manufacture of a propeller, history has revealed rare instances of failures.
It is essential that the MT Electric De-Ice Controller be properly maintained according to the
recommended service procedures and a close watch be exercised to detect impending problems
before they become serious. Unusual operation characteristics should be investigated and repaired
as it could be a warning that something serious is wrong.
As a fellow pilot, I urge you to read this Manual thoroughly.
It contains a wealth of information about your new propeller.
Thank you for choosing a MT-Propeller Eletric De-Ice Controller. Properly maintained it will give
you many years of reliable service.
Gerd R. Mühlbauer
President
MT-Propeller Entwicklung GmbH
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TABLE OF CONTENTS
Page
Warning Remark 0-1
Table of Contents 1
List of Revisions 2
Table of valid pages 3
MT-Propeller Airworthiness Information 4
1. General 5
2. Applicable and referenced documents 5
3. System Overview 7
4. Technical Specifications 8
5. System Interconnections 9
6. Installation 10
7. Operation 11
8. Drawings 13
9. Qualification 14
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LIST OF REVISIONS
No.
Date of Revision
Page
Short Description
Original Issue
2021-07-01
All Pages
Initial Issue
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TABLE OF VALID PAGES
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MT-PROPELLER AIRWORTHINESS INFORMATION
Every owner should stay in close contact with his MT-Propeller dealer or distributor and Authorized MT-
Propeller Service Shop to obtain the latest information pertaining to his Electrical De-Ice Controller and
its installation. MT-Propeller takes a continuing interest in having the owner get the most efficient use of
his De-Ice Controller and keeping it in the best operational condition. Consequently, MT-Propeller from
time to time issues Service Bulletins, Service Letters and Manuals relating to the propeller and its
installation. Service Bulletins are of special importance and should be complied with promptly. These are
sent to dealers, distributors and latest registered owners. Service Letters deal with products improvements
and service hints pertaining to the propeller and its installation. These are sent to dealers, distributors and
occasionally (at the factory`s discretion) to latest registered owners.
If any changes to this manual have been made, the appropriate list of revisions will be revised according
to Revision List in Page 2 of this Manual.
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1. GENERAL
1.1 STATEMENT OF PURPOSE
This operation and installation manual provides instructions on how to install and operate the EDC. It also
provides a system overview including principles of operation.
1.2 SCOPE
This manual is only applicable for installation and operation of the EDC with part number P6DC-( ) / ( ).
1.3 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
1.3.1 Periodic Maintenance
Regular functional checks as described in Chapter 7 have to be made
in accordance with Aircraft Maintenance Manual Schedule
or
100 flight hours:
For Piston Engine Applications, if no time schedule is available;
150 flight hours:
For turboprop application, if no time schedule is available.
1.3.2 Overhaul Period
No additional overhaul time limitations.
1.3.3 Airworthiness Limitation Section
N/A
2. REFERENCED DOCUMENTS AND ABBREVIATIONS
2.1 REFERENCED DOCUMENTS
Identifier
Doc. N°
Doc title; Revision
/DO-160G/
RTCA DO-160G
Environmental Conditions and
Test Procedures for Airborne
Equipment, Issue G, 2010-12-08
/DO-254/
RTCA DO-254
Design Assurance Guidance for
Airborne Electronic Hardware,
Issue B, 2000-04-19
Table 1: Referenced Documents
For MT-Propeller service literature contact:
MT-Propeller Entwicklung GmbH
Propellerplatz 1
94348 Atting / Germany
Tel.: [phone]
Fax: [phone]
E-Mail: [e-mail]
Internet: www.mt-propeller.com
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2.2 ABBREVIATIONS
DO, Doc.
Document
EDC
Electrical De-Ice Controller
EMI
Electromagnetic Interference
GND
Ground
IMA
Installation Manual
MDL
Master Documents List
MT
MT Propeller Entwicklung GmbH
P/N
Part Number
OAT
Outside Air Temperature
RF
Radio Frequency
RTCA
Radio Technical Commission for Aeronautics, RTCA, Inc.
VDC
Volts Direct Current
WoW
Weight on Wheels
Table 2: Abbreviations
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3. SYSTEM OVERVIEW
3.1 GENERAL DESCRIPTION
The Electrical De-Ice Controller (EDC) is a control device which provides a timed control sequence in a
repetitive cycle for operation of propeller De-Icers in an electrical propeller de-icing system.
There are two main Types, the first type of EDC is made to replace old existing De-Ice Timers and delivers
basic functions, the second type is for new installations and delivers advanced functions.
Generally, the EDC provides following main features:
•Supply power to propeller De-Ice boots or other electrically heated airframe parts (heaters).
•Sequencing single and / or multiple heaters or De-Ice boots
•Control, status, and supervisory input / output signals for advanced models
•“Plug&Play” replacement of outdated propeller De-Ice timer devices from third party
manufacturers.
Up to four (depending on model) power outputs can be used to supply electrical De-Ice boots or other
heaters. The EDC is available with different timing sequences. These define the time and order in which
the outputs are enabled.
For control via external systems advanced EDC models accepts discrete input signals e.g. “heater
enable”, “self-test” or “weight-on-wheels”.
To provide functional safety the advanced EDC is equipped with in-device supervisory features:
•Self-test capability
•Over- & undercurrent detection
•Warning & status outputs
These features enable a wide range of applicability especially for modern type aircraft and avionics
systems where additional control and status capability is required.
However, the EDC is also available for retrofit(basic) application where minimum installation effort is
desired. With its formfactor and connector pinout, direct replacement of outdated controllers in many
aircraft is possible.
3.2 MODEL DESIGNATION
P-6 DC –1 / 3E1964-20
1 2 3 4 5
Legend:
1 P = Propeller accessory
2 6 = Manufactured for MT-Propeller by Avionik Straubing Entwicklungs GmbH
3 DC = De-Ice controller
4 1 = Internal Design Version
5 3E1964-20 = Application Number similar to other available Deice Timers (see Table 3)
S/No. 20 DC 003 –F
a b c d
a= Year of Manufacture
b= Electrical De-Ice Timer
c= Consecutive Number
d= Modification Status
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Figure 1: System Block Diagram for advanced EDC
Figure 2: System Block Diagram for basic EDC (Retrofit)
3.3 BLOCK DIAGRAMS
3.4 DESCRIPTION OF THE BLOCK DIAGRAM
The simplified block diagram in figure 2 shows a basic EDC system environment.
Connector J1 provides input for supply power and system ground. Furthermore, up to four power supply
output channels are provided by J1 (depends on actual device configuration, see Table 3). J2 exists but
is disabled in this configuration.
For application with additional features, connector J2 in figure 1 provides status, warning, and control
signals.
For information regarding connectors and pinout see chapter 5.
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4. AVAILABLE MODELS
Table 3: Electrical Attributes of available models
4.1 TECHNICAL SPECIFICATIONS
Physical Attributes
Weight
800 g max.
Dimensions
101.6 mm length x 95.30 mm width x 71.00 height
40.0 inch length x 3.75 inch width x 2.8 inch height
Mounting
Base Mount, orientation not critical
Device may heat, keep distance of ventilation.
Table 4: Physical Attributes
Refer to figure 3 for further information including weight, dimensions and mating connectors.
Qualifications Overview
Hardware Qualification
DO-254, DAL-C
Software Qualification
Not applicable
Environmental Qualification
DO-160G
Altitude
Up to 50.000 ft
Operating Temperature
-40°C to +70°C
Table 5: Qualifications Overview
Refer to chapter 9 for further qualification information.
Electrical Attributes of available models
P/N
System
Voltage
Output
Current
Max. current/
Min. current
Usage
Control
Self-Test/
WoW
Output
Sequence
Total
Cycle
P6DC-1/
3E1964-20
28 VDC
(18,5-33 V)
12A
16 A / 9 A
Threshold
Advanced /
New install
Heater
enable J2
Yes/Yes
C,E
(60s)
120s
P-6DC-3/
3E1964-3
28 VDC
(18,5-33 V)
10A
12.75 A / 7.5 A
Threshold
Advanced /
New install
Heater
enable J2
Yes/Yes
C,break
(90s)
180s
P-6DC-2/
3E1964-20
28 VDC
(18,5-33 V)
13A
19 A / 9 A
Threshold
Advanced /
New install
Heater
enable J2
Yes/Yes
C,E
(60s)
120s
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5. SYSTEM INTERCONNECTIONS
5.1 DEVICE CONNECTORS
Pin connections for the power connector J1 are shown in table 6.
Pin connections for control and status signals on connector J2 are shown in table 7.*
Connector J1
Pin***
Designation
Description
Connection to, if
I/O
used
unused
A
power supply return
GND
GND
-
Input
B
power supply input
supply voltage
28 VDC
-
Input
C
supply power to heater
power output
28 VDC
Open
Output
D
supply power to heater
power output
28 VDC
Open
Output
E
supply power to heater
power output
28 VDC
Open
Output
F
supply power to heater
power output
28 VDC
Open
Output
G
power supply return
GND
GND
-
Input
Table 6: Pin Assignment of J1
Connector J2
Pin***
Designation
Description
Connection to, if
I/O
used
unused
1
Reserved for future use
Reserved for future use
-
-
-
2
Reserved for future use
Reserved for future use
-
-
-
3
Reserved for future use
Reserved for future use
-
-
-
4
Reserved for future use
Reserved for future use
-
-
-
5
Heater enable
Open / GND
GND
-
Input
6
Self-test
Open / GND
GND
Open
Input
7
Reserved for future use
Reserved for future use
-
-
-
8
Warning**
Open / GND (normally open)
GND
Open
Output
9
Reserved for future use
Reserved for future use
-
-
-
10
Shield
Is connected to case
User needed
application
Open
-
11
Reserved for future use
Reserved for future use
-
-
-
12
Reserved for future use
Reserved for future use
-
-
-
13
Reserved for future use
Reserved for future use
-
-
-
14
Reserved for future use
Reserved for future use
-
-
-
15
Reserved for future use
Reserved for future use
-
-
-
16
Reserved for future use
Reserved for future use
-
-
-
17
Reserved for future use
Reserved for future use
-
-
-
18
Reserved for future use
Reserved for future use
-
-
-
19
Reserved for future use
Reserved for future use
-
-
-
20
Shield
Is connected to case
User needed
application
Open
-
21
Reserved for future use
Reserved for future use
-
-
-
22
WOW - weight on wheels
Open / GND -
GND
Open
Input
23
Reserved for future use
Reserved for future use
-
-
-
24
Reserved for future use
Reserved for future use
-
-
-
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Pin***
Designation
Description
Connection to
I/O
used
unused
25
Reserved for future use
Reserved for future use
-
-
-
26
Reserved for future use
Reserved for future use
-
-
-
27
Reserved for future use
Reserved for future use
-
-
-
28
Reserved for future use
Reserved for future use
-
-
-
29
Reserved for future use
Reserved for future use
-
-
-
30
Reserved for future use
Reserved for future use
-
-
-
31
GND
Ground
GND
-
Input
32
Reserved for future use
Reserved for future use
-
-
-
33
Warning**
Open / GND
(normally closed)
GND
Open
Output
34
Reserved for future use
Reserved for future use
-
-
-
35
Reserved for future use
Reserved for future use
-
-
-
36
Reserved for future use
Reserved for future use
-
-
-
37
Reserved for future use
Reserved for future use
-
-
-
Table 7: Pin Assignment of J2
Notes:
* Leave unused pins open.
** Warning signals on pins 8 and 33 have same source. Different output switch configurations
(normally open or normally closed) can be selected by wiring the correspondent pin.
Explanation: Normally closed configuration is enabled while power off.
*** The pin numbers are matching the pin layouts in chapter 5.2 .
5.2 MATING CONNECTORS
To interface the device, the following connectors can be used for production of wiring harness.
Connector J1: P/N: MS3106A20-15S connected to MS3102A20-15P at EDC.
(MIL-DTL-5015) (MIL-DTL-5015)
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Connector J2: P/N: D38999/26WD35SN connected to D38999/20WD35PN at EDC
(MIL-DTL-38999) (MIL-DTL-38999)
6. INSTALLATION
6.1 RETROFIT / BASIC SETUP
For retrofit plug & play exchange no wiring should be necessary. The device can directly replace the old
device (check the output sequence in Table 3, Pins have to match the old Deice Timer). Mounting holes
and connector J1 should match with the existing parts.
WARNING:
Missmatch of pins may damage the device or aircraft parts.
NOTE:
THE BASIC SETUP COULD ALSO BE USED FOR A NEW INSTALLION.FOR THIS CASE REFER TO CHAPTER 6.2.1-
6.2.4 (J1) AND LET J2 OPEN.
WARNING:
Do not wire connector J2! It is connected to the internal eletronic and damage is possible if
connected.
6.2 NEW INSTALLATION / ADVANCED SETUP
J1 AND J2 have to be connected and used!
6.2.1 Installation Considerations
Fabrication of a wiring harness is required. Some mechanical and electrical methods and practices are
required for installation of the EDC. Ensure that routing of the wiring does not expose to sources of heat,
RF or EMI interference. Make sure that there is space for the cabling and mating connectors.
Avoid sharp bends in cabling and routing near aircraft control cables.
For input protection, a trip-free circuit breaker shall be installed. Tripping current depends on actual
heating device connected. Refer to heating device supplier data for circuit breaker requirements.
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6.2.2 Location of Installation
The EDC housing may heat up under high ambient temperatures, enduring operation, or high output
current configurations. Make sure that sufficient ventilation is provided to the mounting location and avoid
close contact to devises sensitive to heat.
Orientation of the EDC is not critical.
6.2.3 Wiring Harness
Allow adequate space for installation of cables and connectors. The installer shall supply and fabricate all
the cables. Electrical connections are made through connectors for unit connector types as described in
section 5.
6.2.4 Wiring/Connection
J1 has to be connected according to Table 6. It is possible to connect only one Ground Pin (Pin A or G).
The detailed pins for the heating sequence are to be extracted from table 3 under Output Sequence.
The Pin numbers in Table 6 match the pin layout in chapter 5.2.
J2 has to be connected according to Table 7. Heater Enable (Pin 5) and Ground (Pin 31) have to be
wired and connected.
The usage and wiring of Self-test (Pin 6), weight on wheels (Pin 22) and Warning (Pin 8+33) is optional.
Both warning output pins (Pin 8 normally open, Pin 33 normally closed) can be used and will trigger on
the same conditions.
The Pin numbers in Table 6 match the pin layout in chapter 5.2
7. OPERATION
7.1 GENERAL OPERATION INFORMATION
As the EDC is designed for use as retrofit replacement but also for new installations, there are two main
operation “modes” depending on model type. The Basic/Retrofit models and the Advanced models.
NOTE:
OPERATION MODE DEPENDS ON ACTUAL CONFIGURATION,REFER TO TABLE 3FOR AVAILABLE CONFIGURATIONS.
7.2 RETROFIT/BASIC OPERATION (J1 WIRED, J2 NOT WIRED)
For retrofit use the EDC is operated without any additional input and output signals.
In this configuration the EDC is unsupplied in its in off-state. To enable heater operation, supply power
must be applied to the EDC. The heater sequence from Table 3 starts immediately after power is supplied
to the EDC. After power supply off, the sequence is reset.
7.2.1 Functional Checks referring to 1.3.1
Lock brakes and operate engine at about 75% of max. RPM. Activate de-icing system and read on
ammeter. The needle should rest inside within the shaded area during the cycle. The ammeter flickers
during the switch to another cycle. The cycle time (ammeter flicker to ammeter flicker) should be
checked against the specification in table 3.
This procedure could be performed at any time the propeller is operating and OAT is low enough to
avoid overheating damage of the Deice-Boots.
The Pilot is free to perform this procedure anytime, but has to observe the OAT to avoid damage to the
Deice-Boots during high OATs.
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7.3 ADVANCED/NEW INSTALL OPERATION WITH I/O FEATURES (J1 WIRED, J2 WIRED)
This mode makes use of additional features like external heater-enable, Self-test activation or weight-on-
wheels deactivation. An overview of this features follows in table 8.
For this mode power of J1 has to be supplied. After power supply the EDC will perform a Self-test to check
the correct function of the De-Icing and the EDC for up to 7 seconds. After that the heating sequence can
be started by “Heater-Enable”
Function
Description
Heater-Enable
Activates heater outputs if Heater-Enable is activated (pulled to ground).
Self-Test
Triggers the device Self-test if activated (connected to ground). The
usage is optional.
WoW
Deactivates heater outputs if WoW signal active (connected to ground).
The usage is optional.
Warning Output
(normally closed)
Indicates device failures,failure of Deice-System (Deice Boots, Wires,
etc…) and status as described in 7.3.5. Normally closed (connected to
ground) switch is active if EDC is unsupplied. Can be used to detect loss
of supply power. The usage is optional.
Warning Output
(normally open)
Indicates device failures, failure of Deice-System (Deice Boots, Wires,
etc…) and status as described. Normally open (not connected to ground)
switch is open if EDC is unpowered. The usage is optional.
Table 8: Special Functions
7.3.1 Functional checks referring to 1.3.1
The Self-test described under 7.3.3 covers all needed checks. It could be performed anytime the De-Icing
is not operating.
If the Warning Output is inactive after a Self-test, the EDC is in an airworthy condition.
7.3.2 Heater-Enable
To use this input, the EDC must be supplied permanently with supply voltage. The heating sequence will
then be activated by the heater-enable signal. After disable the heating sequence will be reset.
7.3.3 Self-Test
The advanced EDC includes a Self-test function which checks functionality of internal control logic,
warning output and output loads.
The Self-test is executed at every power up (power supply J1-P). During Self-test, the warning output is
active for 3-7 sec., allowing a lamp test of the connected warning lamps. After the Self-test was run
successful, the EDC is ready for normal operation, indicated by an inactive warning output. If the Self-test
was not successful, the warning output remain active.
The Self-test procedure can be triggered any time if the device has power supply but output sequence is
not active. The Self-test input can be connected to a push button or switch. Be aware when using a switch
that the device remains in Self-test mode if the switch state is active.
Important:
The Self-test with propeller inoperating could fail sometime and the warning will be active due to
not sufficient electrical contact of the brush blocks.
Repeat the Self-test with engine running, the warning will be reset if the current is inside the
operational range.
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7.3.4 Weight on Wheels –WoW
The advanced EDC includes an input for a WoW signal. This allows automatic deactivation of the heating
outputs if the aircraft is on ground to prevent the heating elements of overheating.
If the WoW input is active (connected to ground), the heater outputs are disabled. This mode is indicated
by an active warning output.
If the De-Icing is disabled the WoW will not activate the warning output.
The WoW input gets overridden by the Self-test input, which means self-test can be triggered even if the
outputs are deactivated by WoW. This allows Self-test execution while aircraft is on ground.
7.3.5 Warning Outputs
There are two usable warning output pins (1 normally open, 1 normally closed). The warning outputs will
trigger at the same conditions and are indicating following errors and status of the EDC:
•If a Self-test is active or failed
•If WoW is active AND Heater enable is active → Heating disabled
•Internal device failure
•If Over- & undercurrent situation, caused by Deice-Boots, Wires, Brush blocks or Slip-ring
failure (Thresholds depending on P/N, see table 3) → Heating not disabled
Additionally, the normally closed warning output can be used to indicate loss of supply power.
7.3.6 Logical Behavior
Inputs
Outputs
Heater
enable
Self-
test
WoW
Warning
Self-test
active
Normal operation
(heater sequence
running, outputs active)
Use
Case
0
0
0
0
0
0
#1
0
0
1
0
0
0
#2.2
0
1
0
1
1
0
#3.1
0
1
1
1
1
0
#3.2
1
0
0
0
0
1
#4.1
1
0
1
1
0
0
#2.1
1
1
0
0
0
1
#4.2
1
1
1
1
1
0
#3.3
Table 9: Logical Behavior
Legend:
•1 = signal / output active
•0 = signal / output inactive
Explanation:
Use Case
#
Description
#1
Device off.
#2.1
Active WoW overrides Heater-Enable input. This prevents De-Ice boots to be burned while aircraft on ground
/ engine not running
#2.2
#3.1
Self-Test normal operation. While Self-Test is running, the warning outputs are active
#3.2
Self-Test overrides WoW input. Self-Test can be enabled when aircraft on ground.
#3.3
Self-Test is performed while aircraft on ground (WoW) and heater enable is active
#4.1
Heater in normal operation
#4.2
Heater Enable overrides Self-Test input. While deicing is operative this is not interrupted by the self-test
routine.
Table 10: Description Use Case for Logical Behavior
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Figure 3: Installation Drawing
8. DRAWINGS
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9. QUALIFICATION
Environmental qualification according RTCA DO-160G:
Section
Purpose
Category
Description
4.5.1, 4.5.2
Low temperature
C4
-55°C ground survival (non-operating),
-40°C operating low,
-40°C short time operating low
4.5.3, 4.5.4
High temperature
C4
+85°C ground survival (non-operating),
+70°C operating high,
+70°C short time operating high
4.5.5
In-flight loss of cooling
X
N/A, not tested
4.6.1
Altitude
D2
50000 ft, non-pressurized, non-controlled temperature
4.6.2
Decompression
X
N/A, not tested
4.6.3
Overpressure
X
N/A, not tested
5.3.1
Temperature variation
A
10°C/minute, combined testing
6.2
Humidity
C*
*Design assurance only; not demonstrated
7.2.1, 7.3.1
Operational shock and
crash safety
B
6 g operational,
20 g crash safety non-operational
8.8.3
Vibration
S
Test curves T (10 g PK)
9.7
Explosive atmosphere
X
N/A, not tested
10.3.1
Waterproofness
X
N/A, not tested
11.4.1
Fluids susceptibility
X
N/A, not tested
12.4
Sand and dust
X
N/A, not tested
13.0
Fungus
X
N/A, not tested
14.3.6.6
Salt fog
X
N/A, not tested
15.3
Magnetic effect
X
N/A, not tested
16.6.1,
16.6.2
Power input
BX
Normal operation, abnormal operation
DC current ripple test not performed
17.4
Voltage spike
A
600 Volts spikes
18.3.1
Audio frequency
conducted susceptibility
B
19.3
Induced signal
susceptibility
20.4, 20.5
Radio frequency
susceptibility
21.4, 21.5
Emission of radio
frequency
22.5
Lightning induced
transient susceptibility
A3E3X
23.0
Lightning direct effects
X
N/A, not tested
24.0
Icing
X
N/A, not tested
25.5
Electrostatic discharge
A
26.0
Fire, flammability
X
N/A, not tested
Environmental qualification category code:
[C4C4XC4XX]ACBSXXXXXXX(BX)AB(ZCX)WB(A3E3X)XXAX
Table 11: DO-160G Environmental Qualification
Page 17 Original Issue 2021-07-01