Midcontinent MD41-1817 Technical Document

INSTALLATION MANUAL AND
OPERATING INSTRUCTIONS
MD41-1817
Annunciation Control Unit
For Lithium Ion Battery Systems
MD41-1817 28vdc Horizontal Mount
Mid-Continent Instruments and Avionics Manual Number 9018252
9400 E. 34th Street N., Wichita, KS 67226 USA Rev. D January 27, 2020
Phone [phone]  Fax [phone]

Rev. D January 27, 2020 2 Manual Number 9018252
FOREWORD
This manual provides information intended for use by persons who, in accordance with current regulatory
requirements, are qualified to install this equipment. If further information is required, please contact:
Mid-Continent Instruments and Avionics
Attn: Customer Service Dept.
9400 E. 34th ST North
Wichita, KS 67226 USA
Phone [phone] Fax [phone]
We welcome your comments concerning this manual. Although every effort has been made to keep it
free of errors, some may occur. When reporting a specific problem, please describe it briefly and include
the manual part number, the paragraph/figure/table number, and the page number. Send your
comments to:
Mid-Continent Instruments and Avionics
Attn: Technical Publications
9400 E. 34th ST North
Wichita, KS 67226 USA
Phone [phone], Fax [phone]
[email protected]
www.mcico.com
 Copyright 2016
Mid-Continent Instruments and Avionics

Rev. D January 27, 2020 3 Manual Number 9018252
REVISION DETAIL
Rev. Date Detail
A 09/29/14 Initial Release.
B 07/29/15 Added Environmental Qualification Form.
C 04/25/16 Revised graphics and text to change annunciation text from STANDBY to
CHARGING and FAIL to TEMP. Minor modifications to Sections 3 and 4.
Added DO-160 section 22 qualification test.
D 01/24/20 Added wiring diagrams for 6430017-2 battery connections.

Rev. D January 27, 2020 4 Manual Number 9018252
TABLE OF CONTENTS
SECTION 1 GENERAL DESCRIPTION 5
1.1 INTRODUCTION 5
1.2 TECHNICAL SPECIFICATIONS 5
1.2.1 MODELS 5
1.2.2 PHYSICAL ATTRIBUTES 5
1.2.3 PERFORMANCE 5
SECTION 2 INSTALLATION CONSIDERATIONS 6
2.1 COOLING 6
2.2 EQUIPMENT LOCATION 6
2.3 ROUTING OF CABLES 6
2.4 LIMITATIONS 6
2.5 TECHNICAL SPECIFICATIONS 6
SECTION 3 INSTALLATION PROCEDURE 7
3.1 GENERAL INFORMATION 7
3.2 UNPACKING AND INSPECTING 7
3.2.1 INCLUDED PARTS 7
3.2.2 AVAILABLE PARTS 7
3.3 CABLE HARNESS 7
3.3.1 LIGHTING CONTROLS 11
3.3.2 POWER AND SIGNALS 12
3.3.3 HARNESS VERIFICATION 12
3.4 MOUNTING 13
SECTION 4 OPERATION 14
4.1 FRONT PANEL CONTROLS AND ANNUNCIATIONS 14
4.1.1 CONTROLS 14
4.1.2 ANNUNCIATIONS 14
SECTION 5 CONFORMANCE 15
5.1 CONTINUED AIRWORTHINESS STATEMENT 15
APPENDIX 1 16
NUMBER LIST OF TABLES AND FIGURES
TABLE 1 MODELS 5
TABLE 2 PHYSICAL ATTRIBUTES 5
TABLE 3 PERFORMANCE 5
FIGURE 1 25 PIN D-SHELL REAR VIEW CONNECTOR PINOUT 7
TABLE 4 SCHEMATIC PINOUT 8
FIGURE 2 WIRING DIAGRAM – TWO TB17 (6430017-1) BATTERIES 8
FIGURE 3 WIRING DIAGRAM – ONE TB17 (6430017-1) BATTERY 9
FIGURE 4 WIRING DIAGRAM – TWO TB17 (6430017-2) BATTERIES 10
FIGURE 5 WIRING DIAGRAM – ONE TB17 (6430017-2) BATTERY 11
FIGURE 6 OUTLINE DRAWING 13
FITURE 7 FRONT PANEL 14

Rev. D January 27, 2020 5 Manual Number 9018252
SECTION 1 GENERAL DESCRIPTION
1.1 INTRODUCTION
The MD41-1817 products are compact, self-contained Annunciation and Control Units (ACUs). The fully
integrated control unit provides annunciation for Mid-Continent Instruments and Avionics TB17 battery
systems. It combines the necessary functions and annunciations required to interface with an approved
system.
Highlighted features include long-life LEDs used for all lighting, internally backlit selection switch, dead-
front inactive annunciations, and the installation option for manual or automatic dimming. An external
annunciation dimming adjustment is provided for balancing low-level light conditions.
1.2 TECHNICAL SPECIFICATIONS
1.2.1 MODEL
MD41-1817
Orientation Horizontal
Power Input 28VDC
Lighting Input 28VDC
TABLE 1
MODEL
1.2.2 PHYSICAL ATTRIBUTES
Characteristics:
Weight: 0.26 pounds
Dimensions:
(not including connector or mate)
3.2 inches long
2.75 inches wide
0.8 inches high
Mating Connector: Positronic RD25F10JVL0 or equivalent (MCI P/N 7014517)
Instrument Panel Mounting: Rear mount
TABLE 2
PHYSICAL ATTRIBUTES
1.2.3 PERFORMANCE
Specifications:
Power Requirement: 0.20 A max
TABLE 3
PERFORMANCE

Rev. D January 27, 2020 6 Manual Number 9018252
SECTION 2 PRE-INSTALLATION CONSIDERATIONS
2.1 COOLING
No direct cooling is required. As with any electronic equipment, overall reliability may be increased if the
unit is not located near a high heat source or crowded next to other equipment. Means of providing some
airflow is considered beneficial.
2.2 EQUIPMENT LOCATION
The MD41-1817 ACU must be mounted as close to the pilot’s field of view as possible. The unit depth,
with connector attached, must also be taken into consideration when selecting an appropriate location.
Allow at least 3 inches of space behind the unit for connector attachment and removal.
2.3 ROUTING OF CABLES
Care must be taken not to bundle the MD41 series ACU logic and low level signal lines with any high
energy sources. Examples of these sources include 400 Hz AC, Comm, DME, HF and transponder
transmitter coaxial cables. Always use shielded wire when shown on the installation print.
Avoid sharp bends in cabling and routing near aircraft control cables. Also avoid proximity and contact
with aircraft structures, avionics equipment, or other obstructions that could chafe wires during flight and
cause undesirable effects.
2.4 LIMITATIONS
Note that this product is part of an incomplete system. It is designed to be installed with other applicable
equipment to provide functionality for main battery systems.
2.5 TECHNICAL SPECIFICATIONS
The MD41-1817 complies with the manufacturers’ specifications and has been verified and approved for
use with the following systems:
Mid-Continent Instruments and Avionics
Model Number(s):
Designed for use with
Battery System:
MD41-1817 Manufacturer: Mid-Continent
Instruments and Avionics
Model(s): TB17

Rev. D January 27, 2020 7 Manual Number 9018252
SECTION 3 INSTALLATION PROCEDURES
3.1 GENERAL INFORMATION
This section contains interconnect diagrams, mounting dimensions and other information pertaining to
the installation of the MD41 series ACU. After installation of cabling and before installation of the
equipment, ensure that power is applied only to the pins specified in the interconnect diagram.
3.2 UNPACKING AND INSPECTING EQUIPMENT
When unpacking this equipment, make a visual inspection for evidence of any damage that may have
incurred during shipment.
3.2.1 INCLUDED PARTS
A. Main Battery ACU – MCIA P/N MD41-1817 series
B. Installation Manual – MCIA P/N 9018252
3.2.2 AVAILABLE PARTS
A. J1 Connector Kit (25 pin) – MCIA P/N 7014517
B. 7-pin Cylindrical TB17 Signal Connector – MCIA P/N 9017889-1
C. Annunciator Cutout Template – MCIA P/N 8014474
3.3 CABLE HARNESS
The MD41 cable harness should be made using 24 AWG wire or larger for all connections. Construct the
cable harness with regards to the instructions below and using the Connector Pinout of Figure 1,
Schematic Pinout of Table 4, and Wiring Diagram of Figures 2 and 3.
FIGURE 1
REAR VIEW OF 25-PIN D-SUB CONNECTOR (J1)

Rev. D January 27, 2020 8 Manual Number 9018252
Connector Pinout
Pin # Description Pin # Description
1 CHARGING, Battery 1 14 Reserved
2 HEATING, Battery 1 15 Pin 2 of RTD 1, Battery 2
3 FAIL/FAULT, Battery 1 16 Pin 1 of RTD 1, Battery 2
4 HEATING, Battery 2 17 Panel Lighting Input, 28VDC
5 CHARGING, Battery 2 18 Pin 1 of RTD2, Battery 2
6 FAIL/FAULT, Battery 2 19 Output to Pin 1 of RTD 1, Battery 2
7 Pin 2 of RTD 1, Battery 1 20 Input from Pin 1 of RTD 2, Battery 1
8 Pin 1 of RTD 1, Battery 1 21 Input from Pin 1 of RTD 2, Battery 2
9 Pin 1 of RTD 2, Battery 1 22 Pin 1 of Over Temperature Warning
10 Output to Pin 1 of RTD 1, Battery 1 23 Pin 2 of Over Temperature Warning
11 28 VDC, Battery 1 24 GROUND
12 28 VDC, Battery 2 25 GROUND
13 28 VDC, Aircraft Power
TABLE 4
SCHEMATIC PINOUT
CHARGING ANNUN, BATT 1
USE 2A CIRCUIT BREAKER
FROM LIGHTING BUS
HEATING ANNUN, BATT 2
OUTPUT TO RTD1/PIN1, BATT 2
RTD1/PIN1, BATT 2
CHARGING ANNUN, BATT 2
20
7
9
2
8
10
1
24
3
11
13
J1
17
28 VDC AIRCRAFT PWR
OVER-TEMP WARN, PIN 1
OVER-TEMP WARN, PIN 2
BATTERY 2, 28 VDC
FAIL/FAULT ANNUN, BATT 2
HEATING ANNUN, BATT 1
RTD1/PIN1, BATT 1
OUTPUT TO RTD1/PIN1, BATT 1
FAIL/FAULT ANNUN, BATT 1
BATTERY 1, GROUND
BATTERY 1, 28 VDC 2A
28VDC
BATTERY 1
RESERVED
BATTERY 2, GROUND
NOTES:
1) ALL WIRING SHALL BE 24 AWG UNLESS OTHERWISE NOTED.
5
18
15
19
21
16
6
4
12
25
14
22
23
BATTERY 2
G
F
A
C
D
B
RTD1/PIN2, BATT 1
INPUT FROM RTD2/PIN1, BATT 1
RTD2/PIN1, BATT 1
E
G
F
A
C
D
B
RTD1/PIN2, BATT 2
INPUT FROM RTD2/PIN1, BATT 2
RTD2/PIN1, BATT 2
E
FIGURE 2
WIRING DIAGRAM - TWO TB17 (6430017-1) BATTERIES

Rev. D January 27, 2020 9 Manual Number 9018252
USE 2A CIRCUIT BREAKER
FROM LIGHTING BUS
20
7
9
2
8
10
1
24
3
11
13
J1
17
28 VDC AIRCRAFT PWR
OVER-TEMP WARN, PIN 1
OVER-TEMP WARN, PIN 2
HEATING ANNUN, BATT 1
RTD1/PIN1, BATT 1
OUTPUT TO RTD1/PIN1, BATT 1
CHARGING ANNUN, BATT 1
FAIL/FAULT ANNUN, BATT 1
BATTERY 1, GROUND
BATTERY 1, 28 VDC 2A
28VDC
BATTERY 1
RESERVED
NOTES:
1) ALL WIRING SHALL BE 24 AWG UNLESS OTHERWISE NOTED.
5
18
21
16
15
19
6
4
12
25
14
22
23
G
F
A
C
D
B
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RTD1/PIN2, BATT 1
INPUT FROM RTD2/PIN1, BATT 1
RTD2/PIN1, BATT 1
E
FIGURE 3
WIRING DIAGRAM - ONE TB17 (6430017-1) BATTERY

Rev. D January 27, 2020 10 Manual Number 9018252
USE 2A CIRCUIT BREAKER
FROM LIGHTING BUS
HEATING ANNUN, BATT 2
OUTPUT TO RTD1/PIN1, BATT 2
RTD1/PIN1, BATT 2
CHARGING ANNUN, BATT 2
20
7
9
2
8
10
1
24
3
11
13
J1
17
28 VDC AIRCRAFT PWR
OVER-TEMP WARN, PIN 1
OVER-TEMP WARN, PIN 2
BATTERY 2, 28 VDC
FAIL/FAULT ANNUN, BATT 2
HEATING ANNUN, BATT 1
RTD1/PIN1, BATT 1
OUTPUT TO RTD1/PIN1, BATT 1
CHARGING ANNUN, BATT 1
FAIL/FAULT ANNUN, BATT 1
BATTERY 1, GROUND
BATTERY 1, 28 VDC 2A
28VDC
BATTERY 1
RESERVED
BATTERY 2, GROUND
NOTES:
1) ALL WIRING SHALL BE 24 AWG UNLESS OTHERWISE NOTED.
5
18
15
19
21
16
6
4
12
25
14
22
23
BATTERY 2
G
F
A
C
D
B
RTD1/PIN2, BATT 1
INPUT FROM RTD2/PIN1, BATT 1
RTD2/PIN1, BATT 1
E
G
F
A
C
D
B
RTD1/PIN2, BATT 2
INPUT FROM RTD2/PIN1, BATT 2
RTD2/PIN1, BATT 2
E
FIGURE 4
WIRING DIAGRAM - TWO TB17 (6430017-2) BATTERIES
105W, 1/4W
105W, 1/4W

Rev. D January 27, 2020 11 Manual Number 9018252
USE 2A CIRCUIT BREAKER
FROM LIGHTING BUS
20
7
9
2
8
10
1
24
3
11
13
J1
17
28 VDC AIRCRAFT PWR
OVER-TEMP WARN, PIN 1
OVER-TEMP WARN, PIN 2
HEATING ANNUN, BATT 1
RTD1/PIN1, BATT 1
OUTPUT TO RTD1/PIN1, BATT 1
CHARGING ANNUN, BATT 1
FAIL/FAULT ANNUN, BATT 1
BATTERY 1, GROUND
BATTERY 1, 28 VDC 2A
28VDC
BATTERY 1
RESERVED
NOTES:
1) ALL WIRING SHALL BE 24 AWG UNLESS OTHERWISE NOTED.
5
18
21
16
15
19
6
4
12
25
14
22
23
G
F
A
C
D
B
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RTD1/PIN2, BATT 1
INPUT FROM RTD2/PIN1, BATT 1
RTD2/PIN1, BATT 1
E
FIGURE 5
WIRING DIAGRAM - ONE TB17 (6430017-2) BATTERY
Refer to Section 2: Pre-Installation Considerations in regards to routing precautions.
3.3.1 LIGHTING CONTROL
Button backlighting (pin 17) is powered (28 VDC) from the aircraft’s panel lighting bus.
All annunciation and button backlight brightness will be automatically controlled by the
internal photocell and the dimming circuit.
105W, 1/4W

Rev. D January 27, 2020 12 Manual Number 9018252
3.3.2 POWER AND SIGNALS
Wire aircraft power and aircraft ground according to the associated ACU pins in the Pinout
Diagram. Annunciation signals should be wired from the appropriate system inputs and
outputs to the associated ACU pins in the Pinout Diagram.
If an over temperature condition exists, pins 22 and 23 will be tied together with a 100Ω
series resistance. This output signal can be utilized as a battery over temperature indicator
to other systems in the aircraft. The TEMP annunciation will be lit in this condition.
3.3.3 HARNESS VERIFICATION
With the MD41 ACU disconnected, turn on the avionics master switch and use a volt-meter
(multimeter) to verify that aircraft power and panel lighting bus power is on the appropriate
pin(s) with appropriate voltage. Also verify that aircraft ground is applied to the appropriate
pins.

Rev. D January 27, 2020 13 Manual Number 9018252
3.4 MOUNTING
Refer to Section 2: Pre-Installation Considerations in regards to equipment location.
The MD41 ACU is designed for rear panel mounting only. A cutout should be made in the panel in
accordance with Figure 4 for the unit bezel and two mounting holes. A cutout template is available from
Mid-Continent Instruments and Avionics (reference p/n 8014474) upon request.
Prior to completing the mounting of the unit in the aircraft, make sure to set the Annunciator Dim
Adjustment if automatic dimming is configured for the annunciations. Ideally this procedure is best
performed in a dark cockpit to simulate low-light/night time conditions. Connect the unit to the cable
harness and turn on master power to the instrument panel and lighting bus. Use a small flat-bladed
screwdriver to access the adjustment screw inside the hole on the bottom of the unit (see Figure 4).
Adjust the screw to increase or decrease the annunciator lighting brightness to a level appropriate with
the rest of the panel instrument lighting.
Secure the indicator to the panel with two #4-40 x 3/8 flat head phillips screws.
2.75
2.25
0.80
R0.16 typ.
2.50
3.00
0.13
Text Direction
2X 4-40 UNC-2B
3/8" max thread depth
Momentary Switch
FIGURE 6
OUTLINE DRAWING MD41-1817

Rev. D January 27, 2020 14 Manual Number 9018252
SECTION 4 OPERATION
4.1 FRONT PANEL CONTROLS AND ANNUNCIATIONS
4.1.1 CONTROLS
BATT/HEAT There are 2 different TB17 battery modes of operation that will determine
actions when the BATT/HEAT momentary switch is depressed (see Manual
Number 9018047, section 4.3 that describes Sleep and Active mode of
TB17):
 When the TB17 battery is in
sleep mode , pressing the BATT/HEAT
momentary switch lights all annunciations as depicted in Figure 5, which
includes MAIN BATTERY, TEMP, FAULT, BATT/HEAT button, CHARGING
and HEATING for at least 3 seconds or until the button is released
 When the TB17 battery is in
active mode , pressing the BATT/HEAT
momentary switch lights all annunciations as depicted in Figure 5, which
includes MAIN BATTERY, TEMP, FAULT, BATT/HEAT button, CHARGING
and HEATING until the button is released
BATT/HEAT button is white backlit. Refer to the installation manual and operating
instructions of the TB17 for additional operational and functional interface details.
4.1.2 ANNUNCIATIONS
MAIN BATTERY (WHITE) Lit when any of the annunciations are ON.
TEMP (RED) Lit when over temperature sensed on battery. Land as
soon as practical and present the battery for
maintenance evaluation.
FAULT (AMBER) Blinking - when battery has experienced a recoverable
fault. Steady - when battery has experienced a non-
recoverable fault. For steady light, present battery for
maintenance evaluation upon landing.
CHARGING (WHITE) Lit when battery is charging. If battery is used as an
emergency power source, it is recommended flight not
be initiated until CHARGING is no longer displayed,
indicating a state of charge greater than 95%.
BATT/HEAT (WHITE) Lit when panel lighting input is high (pin 17) and unit is
connected to Battery 1 (pin 11), Battery 2 (pin 12),
and/or aircraft power (pin 13).
HEATING (WHITE) Lit when battery heater is activated due to unit
temperature below 10°C and battery is in active state. It
is recommended that an engine start not occur until the
HEATING annunciation turns off.
FIGURE 7
FRONT PANEL

Rev. D January 27, 2020 15 Manual Number 9018252
SECTION 5 CONFORMANCE
5.1 CONTINUED AIRWORTHINESS STATEMENT
No periodic scheduled maintenance or calibration is necessary for continued airworthiness of the MD41
series ACU. If the unit fails to perform to specifications, the unit must be removed and serviced by Mid-
Continent Instruments and Avionics or their authorized designee.

Rev. D January 27, 2020 16 Manual Number 9018252
Appendix 1
DO-160 Environmental Qualification Form
MODEL NUMBER: MD41-() PART NUMBER: MD41-1817
NOMENCLATURE: MD41-() Battery Annunciation Control Unit
TSO APPROVALS: N/A
MANUFACTURER: Mid-Continent Instrument Co., Inc.
ADDRESS: 9400 E. 34th St. North, Wichita, KS 67226, USA.
MANUFACTURERS SPECIFICATIONS:
Minimum Performance Specifications: TS360, TDS360
Qualification Test Reports: QTR2104 – QTR2108; QTR2115 – QTR 2118
RTCA DO-160: Rev G, dtd 12/08/10 DATES TESTED: 4/2015-5/2015
CONDITIONS SECTION DESCRIPTION OF TEST
Temperature and Altitude
Low Temperature
High Temperature
Altitude
4
4.5.1
4.5.2
4.5.3
4.5.4
4.6.1
Category F2
Survival and Short Operating Low Temp = -55C
Normal Operating Low Temp = -55C
Survival High Temp = +85C
Short and Normal Operating High Temp = +70C
Altitude = 55,000 ft
Temperature Variation 5 Category S2
Humidity 6 Category B
Operational Shock and Crash
Safety
7 Category B
Vibration 8 Category R Curves B&B1, Category U Curve G
Explosion 9 Category X
Waterproofness 10 Category X
Fluids 11 Category X
Sand and Dust 12 Category X
Fungus 13 Category X
Salt Fog 14 Category X
Magnetic Effect 15 Category Y
Power Input 16 Category Z(XX)
Voltage Spike 17 Category A
Audio Freq Conducted
Susceptibility
18 Category Z
Induced Signal Susceptibility 19 Category ZC(X)
Radio Frequency Susceptibility 20 Category T (conducted)
Category T (radiated)
[TT]
Emission of Radio Freq Energy 21 Category M
Lightning Induced Transient
Susceptibility
22 Category A3 (pin injection)
Category G3L3 (cable bundle)
[A3G3L3]
Lightning Direct Effects 23 Category X
Icing 24 Category X
ESD 25 Category A
Fire, Flammability 26 Category X