True blue power TA202 Series Technical Document

Revision J • June 30, 2020

1 Manual Number 9017899 • Revision J, June 30, 2020
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:
True Blue Power
c/o Mid-Continent Instrument Co., Inc.
Attn: Customer Service Dept.
9400 E. 34th St. N.
Wichita, KS 67226 USA
Phone [phone]
Fax [phone]
www.truebluepowerusa.com
www.mcico.com
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:
True Blue Power
c/o Mid-Continent Instrument Co., Inc.
Attn: Technical Publications
9400 E. 34
th
St. N.
Wichita, KS 67226 USA
Phone [phone]
Fax [phone]
© Copyright 2018
Mid-Continent Instrument Co., Inc.
Download the current
version of this
installation manual
using your smartphone
or tablet.

2 Manual Number 9017899 • Revision J, June 30, 2020
TABLE OF CONTENTS
SECTION 1GENERAL DESCRIPTION 4
1.1PURPOSE OF EQUIPMENT 4
1.2TECHNICAL SPECIFICATIONS 5
SECTION 2PRE-INSTALLATION CONSIDERATIONS 6
2.1COOLING 6
2.2EQUIPMENT LOCATION 6
2.3ROUTING OF CABLES 6
2.4LIMITATIONS 6
2.5MODIFICATIONS 7
SECTION 3INSTALLATION 8
3.1GENERAL INFORMATION 8
3.2UNPACKING AND INSPECTING EQUIPMENT 8
3.3CABLE HARNESS 8
3.4MOUNTING 9
3.5INSTALLATION COMPLETION 10
SECTION 4OPERATION 14
4.1ELECTRICAL PERFORMANCE 14
4.2PROTECTIVE FEATURES 14
SECTION 5CONFORMANCE 15
5.1INSTRUCTIONAS FOR CONTINUED AIRWORTHINESS 15
5.2ENVIRONMENTAL QUALIFICATON STATEMENT 15

3 Manual Number 9017899 • Revision J, June 30, 2020
REVISION HISTORY
Rev Date Detail Approved
A 03/14/2016 Initial release. BAW
B 04/25/2016 Updated formatting, added AEH statement to table 1.3 CAS
C 05/10/2016 Added single port unit mounting options, removed
configurations table. BAW
D 06/23/2016 Added two screws (1/4”) to include connector kit. ScH
E 01/04/2017 Updated to include new mounting option. Added 1.2.4. BAW
F 05/07/2019 Added single rear mount with cover plate option. VAA
G 06/06/2019 Updated figure 3.9 and added rear mount with circular
cover plate options. VAA
H 05/14/2020
Updated style and brand to meet Marketing and
Engineering guidelines. Update Section 3.2, Optional
Equipment names.
DLR
J 06/30/2020 Updated DO-160 qualifications in Section 5 based on
additional testing. Updated wire length in Section 3.3.1. DLR

4 Manual Number 9017899 • Revision J, June 30, 2020
SECTION 1 GENERAL DESCRIPTION
1.1 PURPOSE OF EQUIPMENT
The TA202 Series High Power USB Charging Port is a certified accessory that converts 10 to 32
volts of DC electrical input from the aircraft to standard 5 volt power for any electronic product that
charges using a USB connector. The TA202 provides one or two Universal Serial Bus-A or C
(USB-A or USB-C) ports and can be rear mounted or front mounted in a variety of locations
throughout the aircraft. The new “Type-C” USB port design is a smaller port that accommodates
the latest consumer electronic devices on the market. Among other features, the Type-C connector
accepts reversible cable plugging with no ‘up’ or ‘down’ requirement for cable orientation. The unit
is certified to FAA TSO C71 and qualified to multiple RTCA DO-160 requirements, providing
confidence and allowing installation in the cockpit or cabin.
This High Power USB Charging Port is designed as a DCP (Dedicated Charging Port) to industry-
standard protocol per the USB Battery Charging 1.2 Compliance Plan. It also complies with the
higher power requirements of USB Power Delivery 2.0. Newer electronics, such as the Apple
iPad®, other tablets and larger devices can accept or may require 2.1 amps or more to charge and
operate. As a high power DCP, the TA202 can provide up to 3.0 amps of power to charge USB
devices, including the higher demand products. Most dual USB chargers typically provide 1.0 amp
on one port and 2.1 amps on the second port, but the TA202 can provide 3.0 amps to both ports
simultaneously (for dual port units). The unit has built-in protections for short circuit, over-current,
and low voltage conditions. It is designed to protect against reverse polarity installation and has
temperature monitoring and shutdown capability, allowing the unit to handle unforeseen conditions
safely.
Small, compact and powerful, with plenty of installation flexibility, the TA202 is an ideal choice as a
highly useful and effective addition to any aircraft.

5 Manual Number 9017899 • Revision J, June 30, 2020
1.2 TECHNICAL SPECIFICATIONS
Electrical Attributes
Input Voltage 10-32 VDC
Input Power 35 watts max; 2.5 amps @ 14 VDC / 1.25 amps @
28 VDC
Output Voltage 5 VDC ±0.25 per port
Output Power 3.0 amps max per port
Efficiency ~90% nominal
Table 1.1
Physical Attributes
Weight 1.3 oz. (38 g) (dual port), 0.8 oz. (23 g) (single port)
Dimensions (Dual Port Units)
(not including connector)
1.50 inches wide X 1.03 inches high X 1.25 inches deep
Dimensions (Single Port Units)
(not including connector)
1.50 inches wide X 0.52 inches high X 1.25 inches deep
Charging Ports Type USB Standard-A or USB Standard-C
Connector Kit MCIA P/N 9017960
Mounting Panel mount; rear or front
Table 1.2
Qualifications
Certification FAA TSO-C71
EASA ETSO-C71
Environmental Qualification RTCA DO-160G Environmental Category
See Section 5.2
Airborne Electronic Hardware RTCA DO-254, Design Assurance Level E
Table 1.3
Configurations
Non Lighted Lighted Power Input
Location USB Connector
Part Numbers
6430202-1 6430202-11 Rear Dual: Type A+Type C
6430202-2 6430202-12 Bottom
6430202-3 6430202-13 Rear Dual: Type C+Type C
6430202-4 6430202-14 Bottom
6430202-5 6430202-15 Rear Dual: Type A+Type A
6430202-6 6430202-16 Bottom
6430202-7 6430202-17 Rear Single: Type C
6430202-8 6430202-18 Bottom
6430202-9 6430202-19 Rear Single: Type A
6430202-10 6430202-20 Bottom
Table 1.4

6 Manual Number 9017899 • Revision J, June 30, 2020
SECTION 2 PRE-INSTALLATION CONSIDERATIONS
2.1 COOLING
No external cooling is required. The unit will become warm when in use. This is normal and within
operational parameters. No special mounting considerations are required; however, mounting to a
metal surface can help dissipate any heat generated and extend the life of the product.
2.2 EQUIPMENT LOCATION
The TA202 High Power USB Charging Port is designed for mounting flexibility, allowing for
installation in the cockpit or in the cabin. It is designed for panel mounting and can be installed in a
rectangular configuration or, with an available installation kit, can be front mounted with a cosmetic
cover plate. An instrument mounting adapter bracket is also available to easily mount the unit in a
standard 2-inch round instrument opening that may already exist in the cockpit panel. There are
two versions to choose from which allow the input connector to be located either on the rear of the
unit or from the bottom.
The unit can be mounted in any orientation. Clearance should be provided for the mating
connector which may require an additional inch beyond the rear of the unit.
2.3 ROUTING OF CABLES
Avoid sharp bends in cabling and routing near aircraft control cables. Avoid close proximity and
contact with aircraft structures, avionics equipment or other obstructions that could chafe wires
during flight and cause undesirable effects.
2.4 LIMITATIONS
Environmental qualifications were verified per RTCA DO-160, Revision G in lieu of those identified
within the minimum performance standards (MPS) of the TSO.
The conditions and tests for TSO approval of this article are minimum performance standards.
Those installing this article, on or in a specific type or class of aircraft, must determine that the
aircraft installation conditions are within the TSO standards, specification of the article and
deviations as listed above. TSO articles must have separate approval for installation in an aircraft.
The article may be installed only according to 14 CFR part 43 or the applicable airworthiness
requirements.
The USB Type-C interface is an exciting new connector for electronic devices. Beyond the physical
format of the Type-C connector, it also allows for a variety of interface options when
communicating with compatible devices. This device-to-charger communication is defined within
the USB 3.1 Specification and Power Delivery 2.0 standards. However, manufacturers of
consumer electronic devices and/or cables may choose to implement proprietary versions or
modifications of the USB standards to operate specifically with their own charging equipment. The
TA202 has been tested with and supports a wide variety of devices now emerging on the open
market. However, compatibility with all devices may not be guaranteed. True Blue Power continues
to be proactive in evaluating new devices and strives to continually improve the product as needed
to serve the vast majority of USB Type-C electronic products.

7 Manual Number 9017899 • Revision J, June 30, 2020
2.5 MODIFICATIONS
This product has a nameplate that identifies the manufacturer, part number, description,
certification(s) and technical specifications of the unit. It also includes the “MOD” or modification
number representing notable changes in the hardware design of the unit.
Modification (MOD) 0 is the initial release of the product and is identified on the nameplate by the
lack of marking on the MOD numbers 1 through 9 (i.e. 1-9 are visible). All subsequent
modifications are identified on the nameplate by the marking/blacking out of that particular MOD
number (i.e. for MOD 1, the number 1 is not visible and 2-9 are visible - see Figure 2.1 for
examples). MODs do not have to be sequentially inclusive and may be applied independent of
each other.
For additional details regarding specific changes associated with each MOD status refer to the
product published Service Bulletins at www.truebluepowerusa.com.
Figure 2.1
Nameplate and MOD Status Example
MOD 0
MOD 1
MOD 1
& MOD 2

8 Manual Number 9017899 • Revision J, June 30, 2020
SECTION 3 INSTALLATION
3.1 GENERAL INFORMATION
This section contains interconnect diagrams, mounting dimensions and other information
pertaining to the installation of the TA202 Single and Dual USB Charger. After installation of
cabling and before installation of the equipment, ensure that power and ground are applied to the
proper pins specified in Section 3.3.2, Pin Assignment Information.
3.2 UNPACKING AND INSPECTING EQUIPMENT
When unpacking this equipment, make a visual inspection for evidence of any damage that may
have occurred during shipment. The following parts should be included:
A. High Power USB Charging Port MCIA P/N 6430202-( )
B. Installation Manual MCIA P/N 9017899
C. Connector Kit MCIA P/N 9017960
i. Mating Connector, 2-pin
ii. Pins (4) (2 required, 2 spares)
iii. Screws, #4-40 x 1/4 flat-head (2)
iv. Screws, #4-40 x 5/16 flat-head (2)
Optional Equipment Available:
A. Dual Port Front Mount Faceplate Kit MCIA P/N 9017897
B. Dual Port Instrument Mount Adapter Kit MCIA P/N 9017947
C. Dual Port Rear Mount Faceplate Kit MCIA P/N 9017958
D. Single Port Rear Mount Faceplate Kit MCIA P/N 9019351-1
E. Dual Port Rear Mount Circular Faceplate MCIA P/N 9019384-4
F. Single Port Rear Mount Circular Faceplate MCIA P/N 9019384-3
Equipment Not Provided:
A. Cable Harness Wire See Section 3.3.1 for specifications
B. Circuit Breaker Recommendation 3 amp (2 amp may be sufficient for 28V aircraft)
3.3 CABLE HARNESS
Construct the cable harness following the instructions outlined below and per Figure 3.1.
Refer to Section 2: Pre-Installation Considerations, for routing precautions.
Wire Gauge Selection
Use of PTFE, ETFE, TFE, Teflon or Tefzel insulated wire is recommended for aircraft use.
The wire harness should utilize 20-24 AWG stranded wire. Refer to table 3.1 below. This
table is provided to aid in the consideration of voltage drop due to harness length. Any
other wiring standards that are applicable to the installation should also be considered. 
Wire Gauge Wire Length
20 AWG stranded wire 24 ft
22 AWG stranded wire 14 ft
24 AWG stranded wire 9 ft
Table 3.1
Wire Gauge and Length

9 Manual Number 9017899 • Revision J, June 30, 2020
Pin Assignment Information
INPUT POWER:
Pin A (keyed) – Positive DC input +10 to 32 VDC power
Pin B – Negative DC input / ground
Note: Pins should be crimped using Molex Hand Crimp Tool
63819-0000 (Preferred), 63811-2800 (obsolete) or 11-01-0200
(obsolete). See the Molex Hand Crimp Tool User Manual for
crimp procedures.
Harness Verification
Note:
The TA202 has built-in reverse polarity protection for the power
connector. If Pins A and B are swapped, the unit will not be
damaged, but will also not function.
Once the cable harness is prepared, prior to connecting the
TA202, activate the aircraft power bus and use a multimeter to
verify that aircraft power and ground is supplied with
appropriate voltage on the proper pins within the mating
harness.
3.4 MOUNTING
The TA202 can be installed in one of five ways:
 rear mount, rectangular
 instrument mount
1 2 3

front mount, decorative faceplate
1 2 4

rear mount, decorative faceplate
1 4

rear mount, circular faceplate
1 3
1
Installation kit required. See Section 3.2, Optional Equipment Available for part
number reference
2
Dual port units only
3
Black anodized
4
Brushed aluminum, bare (appropriate for additional plating/finish)
Prepare the panel cutout as shown in Figures 3.4 thru 3.11 per the selected mounting option.
 Countersinks shown in the panel cutouts for flat head screws are optional. However, flat head
screws are provided for flush appearance. For Rear Mount Cover Plate Installations,
countersinks in the panel are required.
 For Rear Mount Installations:
Mounting screws length MUST be between (PT +0.150”) and (PT +0.210”). [PT = panel thickness]
Mounting screws provided with the unit are 0.24” and 0.31”. (Accommodates 0.030” to 0.160” PT)
For PT greater than 0.125, the USB connector will be below the surface of the panel (below flush).
 For Front Mount Installations: Minimum panel thickness is 0.04”. Maximum panel thickness is 0.20”.
 For Rear Mount Installation with Cover Plate: Panel thickness greater than 0.065 will cause the
USB connector to be below the surface of the Cover Plate (below flush).
Figure 3.1
Pin B
(Bottom input versions)
Pin
A
Pin A
(Rear input versions)
Pin B

10 Manual Number 9017899 • Revision J, June 30, 2020
3.5 INSTALLATION COMPLETION
Prior to operating the unit in the aircraft, it is recommended to verify the output and functionality of
the unit. In order to prevent accidental damage to other systems, it is not recommended to attach
the output to other equipment prior to verification. Verify the output of the unit at the terminating
end of the cable with a multimeter to ensure proper voltage and polarity. Once verified, installation
can be completed and functionality should be checked.
Figure 3.4
Dual Port Rear Mount Installation Kit
Figure 3.2
TA202 Outline Drawing
Figure 3.3
TA202 Outline Drawing
Panel Cutout Detail

11 Manual Number 9017899 • Revision J, June 30, 2020
Figure 3.5
Dual Port Instrument Mount Adapter Kit
Step 1: install
grommets
Step 2: place scre
w
through mounting plate
(x4) with front
recess set to panel thickness
(see Gap set detail view)
Step 3: loosely attach mounting plate to unit
usin
g
screws included with uni
t
Step 4: twist unit through
panel cutout.
Tighten screws (x2)
Step 6: Apply adhesive backing, align pins
on rear of cover plate into holes on
mounting plate and press firmly
Step 5: Insert top and bottom screws
Ga
p
Set Detail
Step 1: attach
ada
p
te
r
Step 2: attach adapte
r
p
late to
p
anel
Figure 3.6
Dual Port Front Mount Installation

12 Manual Number 9017899 • Revision J, June 30, 2020
Step 1: install
grommets
Step 2: place screw through
mounting plate (x4) with front
latches set flush to front of unit
(see detail view)
Latch and front of unit - flush
Flush Detail
Step 3: place unit in panel
cutout and secure
with screws (x2)
Provided with unit
Step 4: place adhesive on
panel (x2) in locations
shown and remove
backing
Step 5: align pins on
rear of cover plate into
holes on panel and
press firmly
Figure 3.8
Dual Port Rear Mount Circular Faceplate
Circular Cover Plate is
Ø1.50
Note: screws provided
with unit
Figure 3.7
Dual Port Rear Mount Faceplate Kit

13 Manual Number 9017899 • Revision J, June 30, 2020
Port
protrusion
toward top
Step 1: Insert grommets
Step 2: Place mounting
plate over port
protrusion
Step 3: place unit in panel
cutout and secure with
screws (x2) provided with
unit
Step 4: place adhesive on
panel (x2) in locations
shown and remove
backing
Step 5: align pins on rear of
cover plate into holes on
panel and press firmly
Figure 3.9
Single Port Rear Mount Installation
Figure 3.10
Single Port Rear Mount Faceplate Kit
Figure 3.11
Single Port Rear Mount Circular Faceplate
Note: screws
p
rovided with unit
Circular Cover Plate is
Ø1.35

14 Manual Number 9017899 • Revision J, June 30, 2020
SECTION 4 OPERATION
4.1 ELECTRICAL PERFORMANCE
The TA202 Series High Power USB Charging Port converts an aircraft (DC) input voltage within
the range specified to a 5V (DC) output. This output power is applied to a single or dual USB-A or
USB-C connector in accordance with the USB Implementers Forum.
The USB D+ and D- data lines communicate with the USB portable device to tell the device it is a
dedicated charging port (DCP), capable of a higher current than a standard USB port. This allows
the USB portable device to draw up to 3.0 Amps.
The unit is designed as a DC-to-DC converter with a series switch on each output to regulate
current applied to that output. Each series switch independently reduces the output current to a
safe level if the USB portable device draws excess current, is shorted or has a fault.
If the temperature of the TA202 becomes elevated due to a fault or excessive load, the device will
seamlessly communicate with the USB portable device to lower the charge current. This allows the
device to continue charging while the unit returns to a temperature within designed limits. When
the temperature returns to a safe level the TA202 will automatically reestablish the higher charge
current level with the device and continue charging.
4.2 PROTECTIVE FEATURES
Short Circuit Protection
The TA202 is capable of surviving a short circuit event without permanent damage. The
unit goes into an over-current condition so that the average current is significantly reduced
and the device is protected.
Over-Current Protection
The TA202 monitors the current draw individually on each port. During an over-current
condition the voltage is reduced. If the voltage falls below 3.8 VDC the output is turned off
for a period of 12 seconds. The output is then checked for continued over-current
conditions every 16 milliseconds. This condition is referred to as a hiccup mode. The
device stays in this mode until the over-current condition is removed, then returns to normal
operation.
Low Input voltage Shutdown
If the input voltage applied to the TA202 drops below 10 VDC the unit will shut down until
the applied voltage returns to a level within range.
Over-Temperature
When the internal temperature of the TA202 exceeds designed thresholds, the unit will shut
down and stop providing power. When the temperature returns to an acceptable level the
unit will automatically begin providing power as required, up to a full charge of 3.0 amps.

15 Manual Number 9017899 • Revision J, June 30, 2020
SECTION 5 CONFORMANCE
5.1 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
No periodic scheduled maintenance or calibration is necessary for continued airworthiness of the
TA202 series Single and Dual USB Charger. 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.
5.2 ENVIRONMENTAL QUALIFICATON STATEMENT
MODEL NUMBER: TA202 Series PART NUMBER: 6430202-( )
DESCRIPTION: Single and Dual USB Charger CERTIFICATION: FAA TSO-C71
MANUFACTURER: True Blue Power, a division of Mid-Continent Instrument Co., Inc.
ADDRESS: 9400 E. 34th St. North, Wichita, KS 67226, USA.
SPECIFICATION: Test Specification (TS) 365 Test Data Sheet (TDS) 365
STANDARD: RTCA DO-160, Rev G, dated 12/08/10; MIL-STD-810E, dated 7/14/1989
CONDITIONS SECTION DESCRIPTION OF TEST
Temperature and Altitude 4 Category F1
Temperature Variation 5 Category S2
Humidity 6 Category B
Operational Shock and Crash Safety 7 Category B
Vibration 8 DO-160: Category R; Curves C, C1
MIL-STD810E: See Remarks
Explosion 9 Category E
Waterproofness 10 Category W
Fluids 11 Category X
Sand and Dust 12 Category S
Fungus 13 Category F
Salt Spray 14 Category S
Magnetic Effect 15 Category Z
Power Input 16 Category B(XX)
Voltage Spike 17 Category B
Audio Frequency Conducted Susceptibility 18 Category R
Induced Signal Susceptibility 19 Category X
Radio Frequency Susceptibility 20 Category X
Emission of Radio Frequency Energy 21 Category H
Lightning Induced Transient Susceptibility 22 Category X
Lightning Direct Effects 23 Category X
Icing 24 Category X
ESD 25 Category A
Fire, Flammability 26 Category C
REMARKS:
Section 4: Category F1 with excursions as declared by the manufacturer:
 4.6.2: Decompression +8,000 to 50,000 feet
Section 7: Crash Safety Impulse: 11ms, 40g Shock Wave
Section 8: Vibration per MIL-STD-810E: Sine-On-Random, Method 514.4, Cat. 4, Procedure 1