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 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.
3

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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.

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Figure 1
AGFCI Dimensions
AGFCI Dimensions
AGFCI Dimensions
AGFCI
AGFCI
6

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Figure
Figure
2
AGFCI Envelope Dimensions
AGFCI Envelope Dimensions
AGFCI Envelope Dimensions
AGFCI
AGFCI
7

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2.8 ELECTRICAL INSTALLATION
2.8.1 General Information
The installing agency will supply and fabricate all external cables. Typically required accessories
such as circuit breakers and switch/annunciators are listed in "Table 2 Accessories Not
Supplied". The required unit electrical connectors are listed in "Table 3 Installation Kit". The
installation kit is supplied with the unit.
The length and routing of the external cables must be carefully planned before attempting the
actual installation. Avoid sharp bends or locations near aircraft control cables or fuel lines. All
cables should be well secured to prevent cable movement.
Do not route 60Hz cables near transmitter or receiver coaxes, video cables, data bus cables, and
audio cables. In general, all 60 Hz cables should be routed away from all other cables in the
aircraft with as much separation as practical.
Prior to installing the AGFCI unit itself, a point-to-point continuity check of the wiring harness
should be performed to verify proper wiring. The aircraft power inputs to the unit should be
also verified to insure that power is applied to only the specified power pin(s).
2.8.2 Functional Pinout Descriptions
This section gives a brief description of the inputs and outputs of the AGFCI unit. It is provided
so the installer can determine what specific wiring needs are to be performed to the aircraft in
which the unit is to be installed. Unless otherwise specified, pins not used, i.e. marked N/C, are
to be left un-terminated. See "Figure 5 Interconnect Diagram" for typical interconnection
diagram.
2.8.3 P1 PINOUT DESCRIPTIONS
The P1 connector is utilized for the 120VAC, 60Hz input and output connections. The electrical
contacts will accommodate 12 or 14 AWG wire. The AGFCI input 120VAC input power cables
must be circuit breaker or fuse protected. The maximum 120VAC current rating for the unit is
15 amps. Shielded wire is recommended with the shield terminated to aircraft ground at the
inverter source. Crimp tooling required is M22520/1-01 Crimp Tool (Daniels Mfg. AF8) with
M22520/1-04 Turret Head (Daniels Mfg. TH163). See "Figure 3 AGFCI Unit J1 Connector
Layout".
Refer to "Table 4 Connector J1 Pin Function List" and "Figure 5 Interconnect Diagram" for
specific connections for the 120VAC power inputs and outputs.

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2.8.4
The P
2 connector is utilized for unit power, ground, switch logic, and annunciator logic inputs
and outputs. The electrical contacts will accommodate 20 or 24 AWG wire.
Crimp tooling required is M22520/2
(Daniels Mfg.). Refer to "
Refer to "
specific
connections for the P
The +28VDC input
Power for the unit should be
galley bus.
The p
ower ground
close as practical to the unit connector.
The Fault
load and may be utilized for annunciation or relay switching.
The
Fault
control annunciator
color and Green
cockpit mounted status annunciators ensure that appropriate isolation techniques are
employed.
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2.8.4
P
2 PINOUT
2 connector is utilized for unit power, ground, switch logic, and annunciator logic inputs
and outputs. The electrical contacts will accommodate 20 or 24 AWG wire.
Crimp tooling required is M22520/2
(Daniels Mfg.). Refer to "
Refer to "
Table 5
Connector J
connections for the P
The +28VDC input
(pin 1)
Power for the unit should be
galley bus.
ower ground
(pin 2) and signal ground (pin 11)
close as practical to the unit connector.
The Fault
Hi (pin 5) and Norm Hi (pin
load and may be utilized for annunciation or relay switching.
Fault
GND (pin 4)
control annunciator
monitoring
color and Green
for
the Norm annunciator color.
cockpit mounted status annunciators ensure that appropriate isolation techniques are
employed.
The annunc
Figure
2 PINOUT
DESCRIPTIONS
2 connector is utilized for unit power, ground, switch logic, and annunciator logic inputs
and outputs. The electrical contacts will accommodate 20 or 24 AWG wire.
Crimp tooling required is M22520/2
(Daniels Mfg.). Refer to "
Figure
4
Connector J
2 Pin Function List
connections for the P
2 connector
(pin 1)
must be circuit breaker protected by a 1 amp rated circuit breaker.
Power for the unit should be
supplied by a non
(pin 2) and signal ground (pin 11)
close as practical to the unit connector.
Hi (pin 5) and Norm Hi (pin
load and may be utilized for annunciation or relay switching.
GND (pin 4)
and Norm GND
monitoring
circuits.
the Norm annunciator color.
cockpit mounted status annunciators ensure that appropriate isolation techniques are
The annunc
iators may be mounted in the cockpit for flight crew monitoring of
**Mating face view of pin
P1 Connector
Figure
3
AGFCI Unit
DESCRIPTIONS
2 connector is utilized for unit power, ground, switch logic, and annunciator logic inputs
and outputs. The electrical contacts will accommodate 20 or 24 AWG wire.
Crimp tooling required is M22520/2
-
01 Crimp Tool (Daniels Mfg.) with M2252
4
AGFCI Unit J
2 Pin Function List
2 connector
.
must be circuit breaker protected by a 1 amp rated circuit breaker.
supplied by a non
(pin 2) and signal ground (pin 11)
close as practical to the unit connector.
Hi (pin 5) and Norm Hi (pin
6) +28VDC
load and may be utilized for annunciation or relay switching.
and Norm GND
(pin 3)
circuits.
Typical installations use
the Norm annunciator color.
cockpit mounted status annunciators ensure that appropriate isolation techniques are
iators may be mounted in the cockpit for flight crew monitoring of
**Mating face view of pin
P1 Connector
Wire Side Layout Is Opposite
AGFCI Unit
J
1 Connector Layout
DESCRIPTIONS
2 connector is utilized for unit power, ground, switch logic, and annunciator logic inputs
and outputs. The electrical contacts will accommodate 20 or 24 AWG wire.
01 Crimp Tool (Daniels Mfg.) with M2252
AGFCI Unit J
2 Connector Layout
2 Pin Function List
, and "
Figure
must be circuit breaker protected by a 1 amp rated circuit breaker.
supplied by a non
-
essential aircraft bus or a non
(pin 2) and signal ground (pin 11)
should be connected to airframe ground as
6) +28VDC
outputs are
load and may be utilized for annunciation or relay switching.
(pin 3)
outputs are Ground/Open logics
Typical installations use
the Norm annunciator color.
In the case of interfacing these outputs with
cockpit mounted status annunciators ensure that appropriate isolation techniques are
iators may be mounted in the cockpit for flight crew monitoring of
**Mating face view of pin
layout** Aircraft
Wire Side Layout Is Opposite
1 Connector Layout
2 connector is utilized for unit power, ground, switch logic, and annunciator logic inputs
and outputs. The electrical contacts will accommodate 20 or 24 AWG wire.
01 Crimp Tool (Daniels Mfg.) with M2252
2 Connector Layout
" for details.
Figure
5
Interconnect D
must be circuit breaker protected by a 1 amp rated circuit breaker.
essential aircraft bus or a non
should be connected to airframe ground as
outputs are
rated at 400 m
load and may be utilized for annunciation or relay switching.
outputs are Ground/Open logics
Typical installations use
White
In the case of interfacing these outputs with
cockpit mounted status annunciators ensure that appropriate isolation techniques are
iators may be mounted in the cockpit for flight crew monitoring of
layout** Aircraft
Wire Side Layout Is Opposite
1 Connector Layout
2 connector is utilized for unit power, ground, switch logic, and annunciator logic inputs
and outputs. The electrical contacts will accommodate 20 or 24 AWG wire.
01 Crimp Tool (Daniels Mfg.) with M2252
0/
" for details.
Interconnect D
iagram
must be circuit breaker protected by a 1 amp rated circuit breaker.
essential aircraft bus or a non
-
essential cabin or
should be connected to airframe ground as
rated at 400 m
illia
mp
outputs are Ground/Open logics
that are used to
White
as the Fault annunciator
In the case of interfacing these outputs with
cockpit mounted status annunciators ensure that appropriate isolation techniques are
iators may be mounted in the cockpit for flight crew monitoring of
layout** Aircraft
Wire Side Layout Is Opposite
AGFCI
2 connector is utilized for unit power, ground, switch logic, and annunciator logic inputs
0/
2-08
Positioner
iagram
" for
must be circuit breaker protected by a 1 amp rated circuit breaker.
essential cabin or
should be connected to airframe ground as
mp
maximum
that are used to
as the Fault annunciator
In the case of interfacing these outputs with
cockpit mounted status annunciators ensure that appropriate isolation techniques are
iators may be mounted in the cockpit for flight crew monitoring of
AGFCI
9
2 connector is utilized for unit power, ground, switch logic, and annunciator logic inputs
Positioner
must be circuit breaker protected by a 1 amp rated circuit breaker.
essential cabin or
should be connected to airframe ground as
maximum
that are used to
as the Fault annunciator
In the case of interfacing these outputs with

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system status or in a galley/passenger service area for use by the cabin attendant depending on
the particular aircraft installation and regulatory requirements.
The Remote Test (pin 7) and Remote Reset (pin 8) switch inputs to the unit must be supplied by
normally open, momentary switches. The switches may be mounted in the cockpit for flight
crew use or in a galley/passenger service area for use by the cabin attendant depending on the
particular aircraft installation and regulatory requirements.
The Remote Switch Ground (pins 9 & 10) shall be utilized for the ground side of the momentary
switches.
Figure 4 AGFCI Unit J2 Connector Layout
NOTE: "Figure 6 Typical Annunciator Switch Interconnect" illustrates a possible interface
utilizing the Vivisun LED series switches. For additional information or other configurations
contact Aerospace Optics, Inc. at 1-888-VIVISUN (817-451-1141). Recommended part numbers
are listed in "Table 2 Accessories Not Supplied".
**Mating face view of
socket
layout** Aircraft P
2
Connector Wire Side Layout Is Opposite

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Table 4 Connector J1 Pin Function List
Table 5 Connector J2 Pin Function List
Pin
#
I/O Function
AI 120 VAC Input (LINE)
BI 120 VAC Input (NEUTRAL)
CI RETURN (GND)
DO 120 VAC Output (LINE)
EO 120 VAC Output (NEUTRAL)
FO RETURN (GND)
Pin # I/O Function Pin # I/O Function
1I +28VDC Input 9 O Remote Switch Ground
2I Power Ground 10 O Remote Switch Ground
3O NORM GND (ground out =
Normal)
11 I Signal Ground
4O FAULT GND (ground out =
Faulted)
12 N/C
5O FAULT HI (+28VDC out = Faulted) 13 N/C
6O NORM HI (+28VDC out= Normal) 14 N/C
7I TEST Remote (Switch momentary
ground input = TEST mode)
15 N/C
8I RESET Remote (Switch
momentary ground input = RESET
mode)

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Figure 5
Interconnect D
Interconnect D
Interconnect D
iagram
AGFCI
AGFCI
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Figure 6
Typical Annunciator Switch Interconnect
Typical Annunciator Switch Interconnect
Typical Annunciator Switch Interconnect
Typical Annunciator Switch Interconnect
Typical Annunciator Switch Interconnect
AGFCI
AGFCI
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3 POST-INSTALLATION
3.1 SYSTEM INSPECTION AND CHECKS
The post-installation test is used to apply power and functionally check the system. Successful
completion of the post-installation test verifies the proper operation of the AGFCI system.
3.1.1 INSPECTION
Table 6 is a visual inspection/check procedure that should be performed after system
installation as part of a system checkout.
EQUIPMENT INSPECTION/CHECK PROCEDURE
AGFCI Unit A. Inspect external surface, switches, LEDs, and connectors for
damage.
B. Ensure that the unit is securely installed.
C. Ensure that all connections to the mounting structure are
properly mounted and secure.
D. Ensure that the D-Sub connector P2 back-shell is secure and
that the retention screws are tightened.
E. Ensure that the MS cannon plug P1 back-shell is installed and
secure.
Remote Switches A. Inspect switches for damage.
B. Ensure that switches are properly mounted, labeled, and
secure.
Remote
Annunciators
A. Inspect annunciators for damage.
B. Ensure that annunciators are properly mounted, labeled, and
secure.
Circuit Breakers A. Inspect circuit breakers for damage.
B. Ensure circuit breakers are properly mounted, labeled, and
secure.
C. Ensure wire connections to circuit breakers are secure.
D. Inspect circuit breaker and bus bar areas for loose items that
could cause arcing or short circuits.
Ground Connections A. Inspect ground connections for damage.
B. Ensure that ground connections are secure.
Table 6 Inspection/Check Procedure

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Perform the following inspection on the overall system:
1) Check that cables do not interfere with aircraft controls or other equipment.
2) Check cabling for proper routing and check security of tie-down points. Inspect and
adjust cable runs to ensure that cables are not strained, kinked, or severely twisted and
not exposed to rough or sharp surfaces.
3.1.2 POST-INSTALLATION CHECKS
3.1.2.1 General
Installation of the AGFCI system requires the following stages of testing to ensure the
proper operation. Initially, prior to the installation of the AGFCI unit, a system
interwiring check should be performed. This check verifies that the aircraft and all AGFCI
interconnections are correct before the power is applied. After the units are installed a
visual inspection of the equipment and connections are made.
3.1.2.2 System Interwiring Check
To check the aircraft and AGFCI system interconnects as follows:
a) Check that all cables and interwiring are installed in accordance with the
interwiring and cable harness fabrication instructions.
b) Using the applicable interconnect information check all system wiring for proper
connections, opens, and shorted circuits.
3.1.2.3 AGFCI System Testing
a) Apply 28 VDC aircraft power.
b) Apply 120VAC, 60 HZ power from the inverter system.
c) On the AGFCI unit momentarily press and release the black "RESET" switch and
verify that the "NORM" LED on the unit illuminates and is green in color.
d) On the AGFCI unit momentarily press and release the red "TEST" switch and
verify that the "FAULT" LED on the unit illuminates and is amber in color.
e) Using the appropriate multi-meter set to the AC voltage function check the
aircraft cabin AC outlets and verify that 120VAC is NOT present at the outlets.
f) On the AGFCI unit momentarily press and release the black "RESET" switch and
verify that the "NORM LED has illuminated and is green in color.
g) Using the multi-meter set to the AC voltage function check the aircraft cabin AC
outlets and verify that the 120VAC is available at the outlets.

CURRENTECH AGFCI
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REVISION: B
h) At the remote mounted switches and annunciators momentarily press and
release the "REMOTE TEST" switch and verify that the "REMOTE FAULT"
annunciator is illuminated.
i) On the AGFCI unit verify that the amber "FAULT" LED is illuminated.
j) Using the multi-meter set to the AC voltage function check the AC outlets and
verify that the 120VAC is NOT present at the outlets.
k) At the remote mounted switches and annunciators momentarily press and
release the "REMOTE RESET" switch and verify that the "REMOTE NORM"
annunciator is illuminated.
l) On the AGFCI unit verify that the green "NORM LED is illuminated.
m) Using the multi-meter set to the AC voltage function check the AC outlets and
verify that the 120VAC is available at the outlets.
n) Dependent on the installation documentation, other interfaces may be utilized in
the design documents. The method used to verify any of these additional
interfaces should be coordinated with the design engineering department.
o) At conclusion of testing, secure power to aircraft systems.
3.1.2.4 PERIODIC SYSTEM TESTING
Provisions should be made for the performance of a periodic inspection and test of the system
as described in the previous section "AGFCI System Testing", steps a) through o) in order to
verify continued operation of the system, fault protection to the cabin environment, and
Continued Airworthiness of the system.