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