CURRENTECH AGFCI User manual

REVISION: B
REVISION: B
AIRCRAFT GROUND FAULT CIRCUIT
AIRCRAFT GROUND FAULT CIRCUIT
INTER
PART NUMBER 511
CurrenTech
PO Box 13361
Arlington, Tx. 76094
214
CURRENTECH
AIRCRAFT GROUND FAULT CIRCUIT
INTER
R
UPTER
PART NUMBER 511
CurrenTech
PO Box 13361
Arlington, Tx. 76094
-
214
-693-6751
CURRENTECH
AIRCRAFT GROUND FAULT CIRCUIT
UPTER
(AGFCI)
PART NUMBER 511
-
0361
CURRENTECH
AIRCRAFT GROUND FAULT CIRCUIT
(AGFCI)
PART NUMBER 511
-
92670
AIRCRAFT GROUND FAULT CIRCUIT
(AGFCI)
92670
AIRCRAFT GROUND FAULT CIRCUIT
(AGFCI)
(AGFCI)

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REVISION: B
REVISION HIGHLIGHTS
REVISION DATE DESCRIPTION PAGE
IR 8/21/2011 Initial Release ALL
Revision A 1/9/2012 Incorporate DO-160F Section 15 & 21 environmental
qualifications, reformat entire document, and
correct connector designations.
ALL
Revision B 3/16/2012 Incorporate DO-160F Section 4 & 5 environmental
qualifications.
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Table Of Contents
1 GENERAL INFORMATION......................................................................................................... 1
1.1 INTRODUCTION ................................................................................................................ 1
1.2 EQUIPMENT DESCRIPTION............................................................................................... 1
1.3 TECHNICAL CHARACTERISTICS ......................................................................................... 2
1.4 CERTIFICATION ................................................................................................................. 2
1.5 ENVIRONMENTAL QUALIFICATIONS ................................................................................ 3
2 INSTALLATION.......................................................................................................................... 4
2.1 ACCESSORIES NOT SUPPLIED ........................................................................................... 4
2.2 INSTALLATION KIT (Provided)........................................................................................... 4
2.3 GENERAL INSTALLATION INFORMATION ......................................................................... 4
2.4 UNPACKING AND INSPECTING EQUIPMENT .................................................................... 4
2.5 COOLING REQUIREMENTS ............................................................................................... 5
2.6 EQUIPMENT LOCATION.................................................................................................... 5
2.7 MECHANICAL INSTALLATION ........................................................................................... 5
2.8 ELECTRICAL INSTALLATION .............................................................................................. 8
2.8.1 General Information ................................................................................................. 8
2.8.2 Functional Pinout Descriptions................................................................................. 8
2.8.3 P1 PINOUT DESCRIPTIONS ........................................................................................ 8
2.8.4 P2 PINOUT DESCRIPTIONS ........................................................................................ 9
3 POST-INSTALLATION.............................................................................................................. 14
3.1 SYSTEM INSPECTION AND CHECKS ................................................................................ 14
3.1.1 INSPECTION............................................................................................................. 14
3.1.2 POST-INSTALLATION CHECKS.................................................................................. 15

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Table Of Tables
Table 1 Technical Characteristics.................................................................................................... 2
Table 2 Accessories Not Supplied ................................................................................................... 4
Table 3 Installation Kit .................................................................................................................... 4
Table 4 Connector J1 Pin Function List ......................................................................................... 11
Table 5 Connector J2 Pin Function List ......................................................................................... 11
Table 6 Inspection/Check Procedure............................................................................................ 14
Table Of Figures
Figure 1 AGFCI Dimensions............................................................................................................. 6
Figure 2 AGFCI Envelope Dimensions ............................................................................................. 7
Figure 3 AGFCI Unit J1 Connector Layout ....................................................................................... 9
Figure 4 AGFCI Unit J2 Connector Layout ..................................................................................... 10
Figure 5 Interconnect Diagram ..................................................................................................... 12
Figure 6 Typical Annunciator Switch Interconnect....................................................................... 13

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1 GENERAL INFORMATION
1.1 INTRODUCTION
This manual describes the physical, mechanical, and electrical characteristics for the
CURRENTECH Aircraft Ground Fault Circuit Interrupter (AGFCI) unit part number 511-92670.
General installation procedures for the unit are included.
1.2 EQUIPMENT DESCRIPTION
The AGFCI unit receives high voltage (e.g., 120 volt, 60 HZ AC) from the source unit, typically an
aircraft cabin power inverter system. The AGFCI unit prevents personnel injury and guards
against inadvertent contact with "live" high voltage by providing the 120 volt, 60 HZ output to
the aircraft cabin, galley, and lavatory outlets while continuously monitoring this output for
differential fault current conditions. Fault current is defined as a current that flows from one
conductor to ground or to another conductor due to an abnormal connection (including an arc)
between the two. Differential protection is a technique for protection from short circuits.
When a fault is sensed on the output circuit the AGFCI unit will automatically disconnect the
high voltage output from the aircraft cabin outlets that are protected by the unit in less than 30
milli-seconds while limiting the maximum fault current to 5 mA.
The AGFCI requires aircraft 28VDC power which is utilized for the internal control, monitoring,
and test circuits. The unit provides both switched ground and switched 28VDC output logic
which is utilized for remote indication in the cockpit or galley areas for the system status.
System status is also annunciated on the face of the unit by amber and green LEDs. System test
and reset logics are available for use from remote switches located in the cockpit or galley.
The AGFCI is contained in an all aluminum enclosure (see Figure 1 and 2 for basic dimensions)
and may be mounted in a horizontal or vertical orientation. The electrical connections are
achieved with a 15 pin D-subminiature connector for the 28VDC power, control, monitoring,
test circuits and a 6 pin Mil-Spec connector for the high voltage AC input and output circuits.

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1.3 TECHNICAL CHARACTERISTICS
TECHNICAL CHARACTERISTICS
Physical dimensions 4.85"W x 4.35"H x 7.43"D (12.32cm x 11.04cm x
18.87cm)
Weight 2.2 lbs. (1 kg)
Mounting Remote mounting inside passenger/pilot
envelope or other remote mounted location such
that the environmental conditions specified are
not exceeded.
Cooling requirements None required
Temperature range -5⁰ to +158⁰F (-21⁰ to 70⁰C)
Humidity 0-95% RH, non-condensing
Power inputs DC Input: 22 to 32VDC, 80 ma nominal, 200 ma
maximum
AC Input: 120VAC, 60Hz, 15 amp maximum
continuous.
NOTE: AC input to unit must be protected for
maximum of 15 amps continuous current.
Trip Point fault current 5mA
Average Response time fault 15-27 msec
Max. Allowed Response time fault <30 msec
Isolation voltage 1,500 VAC
Table 1 Technical Characteristics
1.4 CERTIFICATION
The Aircraft Ground Fault Circuit Interrupter (AGFCI) part number 511-92670 was designed to
meet the guidelines specified by Federal Aviation Administration "Policy Statement on
Certification of Power Supply Systems for Portable Electronic Devices on Part 25 Airplanes".
The referenced FAA document establishes criteria that limits maximum fault current to 30
milliamps, activation time in event of a fault to less than or equal to 30 milli-seconds, and in the
event of a circuit failure, output power should be removed automatically, features for
monitoring the health of the detection circuits should be included, and in case a fault is
detected power to the outlet should be removed automatically. Further criteria direct that
automatic reset features should not be permitted.
The Aircraft Ground Fault Circuit Interrupter part number 511-92670 exceeds the criteria
established by the FAA document. While this FAA policy statement provides guidelines for
certification of these items of equipment it remains the responsibility of the installing activity to
coordinate certification efforts with the responsible FAA office.

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1.5 ENVIRONMENTAL QUALIFICATIONS
The Aircraft Ground Fault Circuit Interrupter part number 511-92670 has been tested to the
following categories of RTCA, Inc. DO-160F Environmental Conditions and Test Procedures for
Airborne Equipment.
Environmental Qualification Form
NOMENCLATURE: Aircraft Ground Fault Circuit Interrupter_(AGFCI)______________________________________
TYPE/MODEL/PART NO: 511-92670___________________ TSO NUMBER: N/A_____________________________
MANUFACTURER’S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION: ___________________________
MANUFACTURER: CurrenTech____________________________________________________________________
ADDRESS: P.O. BOX 13361__Arlington,_Texas_76094-0361_____________________________________________
REVISION & CHANGE NUMBER OF DO-160: DO-160F__________ DATE TESTED: 12-28-2011 Section 15 & 21
02-13-2012 Sections 4 & 5____
CONDITIONS
SECTION
DESCRIPTION OF TESTS CONDUCTED
Temperature and Altitude
Low Temperature
High Temperature
In-Flight Loss of Cooling
Altitude
Decompression
Overpressure
4.0
4.5.1 & 4.5.2
4.5.3 & 4.5.4
4.5.5
4.6.1
4.6.2
4.6.3
Category A1
Category A4: Survival -55°C, Low Operating -15°C,
Category A1: Survival +85°C, Short Time +70°C, Operating +55°C.
No Cooling Required.
Equipment is Category A1 to 15,000 feet.
Category A1: 50,000 feet.
Category A1: -15,000 feet.
Temperature Variation 5.0 Category C: 2°C per minute.
Humidity 6.0 Equipment identified as Category X.
Operational Shock and Crash Safety 7.0 Equipment identified as Category X.
Vibration 8.0 Equipment identified as Category X.
Explosive Atmosphere 9.0 Equipment identified as Category X.
Waterproofness 10.0 Equipment identified as Category X.
Fluids Susceptibility 11.0 Equipment identified as Category X.
Sand and Dust 12.0 Equipment identified as Category X.
Fungus 13.0 Equipment identified as Category X.
Salt Fog Test 14.0 Equipment identified as Category X.
Magnetic Effect 15.0 Equipment is Category Z.
Power Input 16.0 Equipment identified as Category X.
Voltage Spike 17.0 Equipment identified as Category X.
Audio Frequency Susceptibility 18.0 Equipment identified as Category X.
Induced Signal Susceptibility 19.0 Equipment identified as Category X.
Radio Frequency Susceptibility 20.0 Equipment identified as Category X.
Radio Frequency Emission 21.0 Equipment tested to Category M.
Lightning Induced Transient Susceptibility 22.0 Equipment identified as Category X.
Lightning Direct Effects 23.0 Equipment identified as Category X.
Icing 24.0 Equipment identified as Category X.
Electrostatic Discharge 25.0 Equipment identified as Category X.
Fire, Flammability 26.0 Equipment identified as Category X.

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2 INSTALLATION
The items listed in “Table 2 Accessories Not Supplied” and “Table 3 Installation Kit” are
recommended in order to maximize the capabilities of the Aircraft Ground Fault Circuit
Interrupter unit. The annunciators listed in “Table 2 Accessories Not Supplied” may be required
for FAA certification of the system and coordination with the certification authority is strongly
suggested. The items listed in “Table 3 Installation Kit” are provided with each unit.
2.1 ACCESSORIES NOT SUPPLIED
ITEM PART NUMBER DESCRIPTION SOURCE QTY
1 * LED-52-12-BB-E0T6E ANNUN/SW. (GFCI RESET/NORM) AEROSPACE OPTICS 1
2* LED-52-12-BB-E0T6D ANNUN/SW. (GFCI TEST/FAULT) AEROSPACE OPTICS 1
3Installation dependent CIRCUIT BREAKER, 1 AMP QPL 1
4Installation dependent CIRCUIT BREAKER, 15 AMP QPL 1
* Recommended part number and supplier
Table 2 Accessories Not Supplied
2.2 INSTALLATION KIT (Provided)
ITEM PART NUMBER DESCRIPTION SOURCE QTY
1MS27467T17B6S CONNECTOR, P1 QPL 1
2M85049/49-2S16W BACKSHELL, P1 QPL 1
3M39029/56-353 SOCKET CONTACT, 12 & 14 AWG QPL 6
4205205-7 RECEPTACLE, D-SUB, 15 CONTACT TYCO 1
5M39029/63-368 SOCKET, CONTACT, 24 TO 20 AWG QPL 15
6207470-1 CABLE CLAMP TYCO 1
75205980-1 SCREW RETAINER, MALE TYCO 2
Table 3 Installation Kit
2.3 GENERAL INSTALLATION INFORMATION
This section contains general suggestions and information to consider before installation of the
AGFCI unit. Close adherence to these suggestions will assure optimum performance from the
equipment.
2.4 UNPACKING AND INSPECTING EQUIPMENT
Exercise extreme care when unpacking the equipment. Make a visual inspection of the unit for
evidence of damage during shipment. If a claim for damage is to be made, save the shipping
container to substantiate the claim. The claim should be promptly filed with the transportation
company. It is advisable to retain the shipping container and packing material after all
equipment has been removed, in the event that equipment storage or reshipment becomes
necessary.

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2.5 COOLING REQUIREMENTS
No forced cooling is required. Maintain clearance from adjacent equipment to allow convective
cooling.
2.6 EQUIPMENT LOCATION
The equipment should be installed in the aircraft in a manner consistent with acceptable
workmanship and engineering practices and in accordance with the instructions set forth in this
publication. To ensure that the system has been properly and safely installed in the aircraft, the
installer should make a thorough visual inspection and conduct an overall operational check of
the system on the ground prior to flight.
The installation should be in accordance with standards established by the customer's installing
agency and existing conditions as to unit location and type of installation.
Care should be exercised to avoid mounting components near other equipment that may be
susceptible to 60 Hz alternating current noise. In general the equipment should be installed in a
location convenient for operation, inspection, and maintenance, and in an area consistent with
the environmental limits. Determine the mounting location for system components following
the guidelines below.
2.7 MECHANICAL INSTALLATION
The AGFCI unit is a remote LRU and shall be mounted inside the passenger/pilot envelope or
other remote location such that the environmental conditions do not exceed the conditions set
forth in "Table 1 Technical Characteristics".
As part of the AGFCI unit mechanical installation, ensure that the unit's connectors, LEDs, and
the "RESET", and "TEST" switches are accessible for post-installation and periodic checkouts.
Refer to "Figure 1 AGFCI Dimensions" and "Figure 2 AGFCI Envelope Dimensions" for additional
installation and mounting information.

CURRENTECH
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Figure 1
AGFCI Dimensions
AGFCI Dimensions
AGFCI Dimensions
AGFCI
AGFCI
6