JUPITER AVIONICS JA74-410 USB A and USB C Charger User Manual

JUPITER AVIONICS JA74-410 USB A and USB C Charger

SECTION 1 – DESCRIPTION

System Overview
The JA74-410 USB-A and USB-C Charger allows the aircraft owner/operator to use an unused portion of the instrument panel (3 Dzus high) for charging two devices simultaneously.

Features Overview
One USB 2.0 Type A receptacle is provided to supply 5 Vdc power up to 2.1 Amps. One USB 2.0 Type C receptacle is provided to supply up to 45 Watts.

Inputs and Outputs
Refer to the JA74-410 connector map for the mating connector designators and contact assignments for the input and bi-directional signals.

Specifications

Electrical Specifications

Power Input

USB-A Output Performance

• Output rated current ≤ 2.1 A
• Output rated voltage +5 Vdc ± 10 %
• Ripple ≤ 5 mVpp
• Short circuit ≥ 1 min

USB-C Output Performance

• Output rated current 2.25 A for +20 V output 3.00 A for all other voltages

• Output rated voltage +5 Vdc ± 5 %
  +9 Vdc ± 5 %
  +12 Vdc ± 5 %
  +15 Vdc ± 5 %
  +20 Vdc ± 5 %

• Ripple
  ≤ 5 mVpp for +5 V output
  ≤ 9 mVpp for +9 V output
  ≤ 12 mVpp for +12 V output
  ≤ 15 mVpp for +15 V output
  ≤ 20 mVpp for +20 V output

• Short circuit ≥ 1 min for all voltages

SECTION 2 – INSTALLATION

Introduction
This section contains unpacking and inspection procedures, installation information, and post-installation checks.

Continued Airworthiness
Maintenance of the JA74-410 is on condition only. Scheduled inspection and/or periodic maintenance of this unit is not required.

Unpacking and Inspecting Equipment
Unpack the equipment carefully. Check for shipping damage and report any problems to the relevant carrier. Confirm that the Authorized Release Certificate or Certificate of Conformance is included. Complete the on-line warranty card from the Jupiter Avionics Corporation (JAC) website – www.jupiteravionics.com/warranty.

Warranty
All products manufactured by JAC are warranted to be free of defects in workmanship or performance for 2 years from the date of installation by an approved JAC dealer or agency. This warranty covers the cost of all materials and labour to repair or replace the unit, but does not include the cost of transporting the defective unit to and from JAC or its designated warranty repair centre, or of removing and replacing the defective unit in the aircraft. This warranty does not cover failures due to abuse, misuse, accident, or unauthorized alteration or repairs.
THIS WARRANTY IS VOID IF THE PRODUCT IS NOT INSTALLED BY AN AUTHORIZED JAC DEALER. If the on-line warranty card is not completed, the product will be warranted from the date of manufacture.
Contact JAC for return authorization, and for any questions regarding this warranty and how it applies to your unit(s). JAC is the final arbiter concerning warranty issues.

Installation Procedures
CAUTION: The power input circuitry of the unit may be damaged if the installation does not conform to the wiring instructions in this manual.

Installation Limitations
Those installing the JA74, on or in a specific type or class of aircraft, must determine that the aircraft installation conditions meet standards. The JA74 may be installed only by following the applicable airworthiness requirements.

Cabling and Wiring
All wire shall be selected in accordance with the original aircraft manufacturer’s maintenance instructions, or AC43.13-1B Change 1, Paragraphs 11-76 through 11-78. Follow the Connector Map in Appendix A of this manual.
Note that this unit has a ‘clamshell’ hood that is installed after the wiring is complete.
Maintain wire segregation and route wiring in accordance with the original aircraft manufacturer’s maintenance instructions.
Unless otherwise noted, all wiring shall be a minimum of 20 AWG. Refer to the Interconnect drawing for additional specifications.

Mechanical Installation
The JA74-410 can be mounted in any attitude and location with adequate space for the front panel and sufficient clearance for the connector and wiring harness. It requires no direct cooling.

Post Installation Checks
Voltage/Resistance checks
Do not attach this unit until the following conditions are met:

• Check P1 pin 1 for +28 Vdc relative to ground.
• Check P1 pin 6 (power ground) for continuity to ground (less than 0.5 Ω).
• Check P1 pin 7 (chassis ground) for continuity to ground (less than 0.5 Ω).
• Check all pins for shorts to ground or adjacent pins.

Power on Checks
Power up the aircraft’s systems and confirm normal operation of all functions of the JA74. Refer to
Section 3 (Operation) for specific operational details.
When all performance checks are satisfied, complete the necessary regulatory documentation before releasing the aircraft for service. Refer to Appendix B.

Installation Kit
The kit required to install this unit is not included with the unit. The installation kit (Part # INST-JA74) consists of the following:

Recommended Crimp tools

Standard D-Sub Crimp Tool Chart

Tool Type| Hand crimping tool| Positioner| Insertion/extractor tool
POSITRONIC| 9507-0-0-0| 9502-5-0-0| 4711-2-0-0
DANIELS| AFM 8| K13-1| 91067-2
MIL-SPEC| M22520/2-01| M22520/2-08| M81969/1-02

Installation Drawings
The drawings and documents required for Installation can be found in Appendix A of this manual.

SECTION 3 – OPERATION

Introduction
This section contains the operating instructions for the JA74-410. The JA74-410 provides charging for two phones or other devices.

Front Panel Connectors
The JA74-410 has one front panel USB-A Power output connector and one front panel USB-C Power output connector.

USB-C Power Output
This Power Output is a USB Type C connector.
This connector has a USB PD Type C receptacle with an auto-adjustable supply which can deliver +5 Vdc @ 3 A, +9 Vdc @ 3 A, +12 Vdc @ 3 A, +15 Vdc @ 3 A, or +20 Vdc @ 2.25 A for charging cell phones and similar devices.

USB-A Power Output
This Power Output is a USB Type A connector.
Note: The USB-A port is not designed to be used for data transfer. This connector is provided to supply +5 Vdc up to 2.1 Amps for charging cell phones and similar devices.

Compatibility

CAUTION: Attempting to connect an incompatible plug or device could damage the JA74, the attached device, or both.
If in doubt regarding compatibility of a specific item, contact Jupiter Avionics (www.jupiteravionics.com).

Installation and Operating Manual

Appendix A – Installation Drawings

Introduction
The drawings necessary for installation and troubleshooting of the JA74-410 USB-A and USB-C Charger are in this Appendix, as listed below.

Installation Drawings

JA74-410 INTERCONNECT WIRING NOTES

NOTES

1. ALL WIRE SIZE SHOULD BE 22 AWG MIN UNLESS OTHERWISE SPECIFIED. UNSHIELDED WIRE SHOULD BE SELECTED PER FAA AC43.13-1B CHANGE 1 PARA 11-76 TO 11-78. WIRE TYPES SHOULD BE IN ACCORDANCE WITH MIL-W-22759 AS DESCRIBED IN FAA AC43.13-1B CHANGE 1 PARA 11-85 AND 11-86 AND LISTED IN TABLE 11-11 OR 11-12. ALL SHIELDED CABLE SHOULD BE IN ACCORDANCE WITH MIL-DTL-27500 (REVISION H OR LATER).
2. CONNECTION TO AIRFRAME GROUND SHOULD BE MADE WITH 22 AWG WIRE. LENGTH NOT TO EXCEED 3 FT (0.91 M).
3. CABLE LENGTH NOT TO EXCEED 6 FT (1.82 M).

Appendix B – Installation Documents

Airworthiness

Airworthiness approval of the JA74-410 may require completion of a TCCA Major Modification Report per CAR STD (AWM) 571 Appendix L, or a FAA Form 337. The sample wording for a description of the work is provided to assist the Installing Agency in preparing Instructions for Continued Airworthiness (ICA) when installing a Jupiter Avionics JA74-410 USB-A and USB-C Charger. This sample may be modified appropriately for new installations. It is the installer’s responsibility to determine the applicability of the method used. Installations performed outside Canada must follow the applicable aviation authority’s regulations.

Sample Wording:
Installed the Jupiter Avionics JA74-410 USB-A and USB-C Charger [aircraft location].
Installed in accordance with the JA74-410 Installation Manual, Revision [ ], and AC 43.13-2, Chapters 2, and 3.
The JA74-410 Installation Manual provides detailed installation instructions and wiring diagrams (Section 2, and Appendices A and B).
Power is supplied to the JA74-410 through a 4-Amp circuit breaker.
Aircraft equipment list, weights and balance amended. Compass compensation checked and found to conform to applicable regulations.

Instructions for Continued Airworthiness
Maintenance of the JA74-410 USB-A and USB-C Charger is “on condition” only. Periodic maintenance of the JA74-410 is not required.
The following sample Instructions for Continued Airworthiness (ICA) provides assistance in preparing ICA for the Jupiter Avionics JA74-410 unit installation as part of a Type Certificate (TC) or Supplemental Type Certificate
(STC) project to comply with CAR STD (AWM) 523/527/525/529.1529 or FAR 23/25/27/29.1529 “Instructions for Continued Airworthiness”.
Items that may vary by aircraft make and model are shown in brackets (“[ ]”) and should be filled in as appropriate. Some of the checklist items do not apply, in which case they should be marked “N/A” (Not Applicable).

Instructions for Continued Airworthiness, Jupiter Avionics JA74-410 USB-A
and USB-C Charger in an [Aircraft Make and Model]

1. Introduction
   [Aircraft that has been altered: Registration number, Make, Model and Serial Number] Content, Scope, Purpose and Arrangement: This document identifies the Instructions for Continued Airworthiness for a Jupiter Avionics JA74-410 installed in an [aircraft make and model]. Applicability: Applies to a Jupiter Avionics JA74-410 installed in an [aircraft make and model]. Definitions/Abbreviations: None, N/A.
   Precautions: None, N/A.
   Units of Measurement: None, N/A.
   Referenced Publications: JA74-410 Installation and Operating Manual
   JA74-410 Maintenance Manual
   STC/TC # [applicable STC/TC number for the specific aircraft installation] Distribution: This document should be a permanent aircraft record.

2. Description of the System/Alteration
   Jupiter Avionics JA74-410 USB-A and USB-C Charger. Refer to Appendix A of this manual for interconnect information. Refer to aircraft manufacturer approved interconnect for actual installation.

3. Control, Operation Information
   Refer to section 3 of this manual.

4. Servicing Information
   N/A

5. Maintenance Instructions
   Maintenance of the JA74-410 is ‘on condition’ only. Periodic maintenance is not required. Refer to the JA74-410 Maintenance Manual.

6. Troubleshooting Information
   Refer to the JA74-410 Maintenance Manual.

7. Removal and Replacement Information
   Refer to Section 2 of this manual – the JA74-410 Installation and Operating Manual. If the unit is removed and reinstalled, a functional check of the equipment should be conducted.

8. Diagrams
   Refer to Appendix A of this manual – the JA74-410 Installation and Operating Manual – for installation drawings and interconnect examples.

9. Special Inspection Requirements
   N/A

10. Application of Protective Treatments
    N/A

11. Data: Relative to Structural Fasteners
    JA74-410 and appropriate mounting hardware installation, removal and replacement should be in accordance with applicable provisions of AC 43.13-1B and AC 43.13-2A.

12. Special Tools
    N/A

13. This Section is for Commuter Category Aircraft Only

    • Electrical loads: Refer to Section 1 of the JA74-410 Installation and Operating Manual.
    • Methods of balancing flight controls: N/A.
    • Identification of primary and secondary structures: N/A.
    • Special repair methods applicable to the airplane: N/A.

14. Overhaul Period
    No additional overhaul time limitations.

15. Airworthiness Limitation Section
    N/A

References

• Jupiter Avionics Corporation - Avionics design manufacturer

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