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GH-3100

Installation & Operation Manual

Page 1-6

General Information

TP-559

March 30, 2017

Revision K

1.3 SPECIFICATIONS

1.3.1 GH-3100

PART NUMBER

501-1860-() (GH-3100)

CERTIFICATION:

USA (FAA) and Europe (EASA)
See paragraph 1.3.1.1 and 1.3.1.2 for information.

RTCA COMPLIANCE:
see environmental qualification
form in Appendix B.

Environmental Category: DO-160D
Software Category: DO-178B, criticality Level B & C
Other: DO-187, DO-189, DO-192, DO-195, DO-196, And DO-208.

EUROCAE COMPLIANCE:
see environmental qualification
form in Appendix B.

ED-14E, ED-22B, ED-46B, ED-47B, ED-54

SIZE:

Case shall be 3 ATI in accordance with ARINC Specification 408A.
Length (with knob): 12.29 inches [31.22 cm]
Bezel Width and Height: 3.30 inches [8.38 cm]

WEIGHT:

4.0 Lbs. (1.81 Kg) maximum.

POWER REQUIREMENTS:

Starting: (warm up) 50.0 watts at +28.0 Vdc, continues for first five minutes of

operation.

Running: (with heaters, fan, and thermal electrical cooler off) shall not exceed 23.5

watts at 28 Vdc input.

Lighting Power: 0.708 watts at 5.0 Vac or Vdc or 0.9 watts at 28.0 Vac or Vdc.

CIRCUIT BREAKER:

3.0A recommended.

CONFIGURATION:

OPERATING TEMPERATURE:

-40

°

to +70

°

C (-40

°

to +158

°

F)

STORAGE TEMPERATURE:

-55

°

to +85

°

C (-67

°

to +185

°

F)

MAXIMUM ALTITUDE:

25,000 ft.

AIR SPEED AND ALTITUDE
MAXIMUM DISPLAY LIMITS:

Mach Range

0.41 to 0.99

Altitude Range

–1,000 to +55,000 feet

Indicated Airspeed Range

0 to 450 knots

OPERATION REQUIREMENTS:

DCM-3100 installed at J2 is required to operate.

CONNECTOR TYPE:

J1 (p/n 563-1113-01)

mates with

MS3116F18-32S

(solder contacts)

or

MS3126F18-32S

(front release crimp contacts)

or

MS3476L18-32S

(rear release crimp contact).

with M85049/52S18W strain relief.

J2 (p/n 563-1013-21)

Interface port to the DCM-3100 and diagnostic port.

Static Pressure Port : IAW MS33649-05

Total Pressure Port: IAW MS33649-04

SCHEDULED MAINTENANCE

No scheduled maintenance interval applicable. Subject to bi-annual requirements of
FAA document

CFR FAR Part 91.411

.

REPAIRABILITY:

Repairs will be performed at the factory

SERVICE LIFE:

The indicator has unlimited service life

CAUTION

Do not use this information for acceptance verification for the GH
indicator. Verification tests are located in the Installation Checkout
section of this manual.

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Summary of Contents for GH-3100

Page 1: ... Operation Manual This manual contains installation and operating information for the GH Electronic Standby Instrument System Information in this manual includes the following products GH 3100 Electronic Standby Indicator with 1 3 1 4 or 3 0 software DCM 3100 Detachable Configuration Module and MAG 3000 MAG 3100 Magnetometer This information is supplemented and kept current by revisions service le...

Page 2: ...manual is distributed with permission by L3 Aviation Products 5353 52PP nd PP Street S E Grand Rapids MI USA 49512 9704 Telephone 800 453 0288 or 616 949 6600 Fax 616 977 6898 Email avionics techpubs L3T 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 in...

Page 3: ... includes periodic maintenance troubleshooting return to service procedures and instructions for the return of defective components APPENDIX A SIGNAL AND CABLE CHARACTERISTICS This appendix defines the electrical characteristics and wiring and label configuration options of all input and output signals APPENDIX B ENVIRONMENTAL QUALIFICATION FORM This appendix provides the environmental qualificati...

Page 4: ...ower ON Self Test Mode SL 186 Service Letter Provide factory generated tolerance settings of altitude accuracy for certified repair stations SL 189 Service Letter 1 Import Export control issues 2 Modification status of models GH 3000 GH 3004 and GH 3100 SL 244 Service Letter To inform customers about the replacement of the GH 3100 with software version 1 3 with the new GH 3100 with software versio...

Page 5: ...Software load 2 2 SB501 1860 18 Service Bulletin To improve attitude performance when configured without heading Maintenance release to address open action items SB501 1860 19 Service Bulletin Provide replacement display due to diminishing source SB501 1860 20 Service Bulletin Software update to correct alignment error at startup as a result of power sequencing This condition only affects units co...

Page 6: ...ges in this publication consists of the following Title page A Page i thru x 1 1 thru 1 12 2 1 thru 2 12 3 1 thru 3 12 4 1 thru 4 6 5 1 thru 5 34 A 1 thru A 10 B 1 thru B 4 REVISION HIGHLIGHTS Revision K is a republication This republication completely replaces the existing manual New and revised material for the GH 3100 Installation Manual has been added These changes include Update company name ...

Page 7: ...iations x SECTION 1 GENERAL INFORMATION 1 1 Introduction 1 1 1 2 Functional description 1 3 1 2 1 Electronic Standby Indicator GH 3100 1 4 1 2 2 Detachable Configuration Module DCM 3100 1 5 1 2 3 Magnetometer MAG 3000 1 5 1 2 4 Magnetometer MAG 3100 1 5 1 3 Specifications 1 6 1 3 1 GH 3100 1 6 1 3 2 DCM 3100 1 8 1 4 Modifications and Software Revisions 1 8 1 4 1 Software Release Summery 1 8 1 5 In...

Page 8: ...2 7 2 3 5 Installation Guidelines for MAG 3100 Magnetometer 2 8 SECTION 3 INSTALLATION CHECKOUT 3 1 Introduction 3 1 3 2 Post Installation Checks Initial System Installation 3 1 3 2 1 Electronic Standby Indicator Check 3 1 3 2 2 Magnetometer Check 3 2 3 2 3 Post Installation Checks Remove and Replace Checkout 3 11 SECTION 4 MAINTENANCE 4 1 Introduction 4 1 4 2 Continued Airworthiness 4 1 4 2 1 Per...

Page 9: ...al Functions 5 25 5 3 1 Power ON Sequence 5 25 5 3 2 Pitch and Roll Attitude Display 5 26 5 3 3 Slip Skid Indicator 5 27 5 3 4 Air Data Display 5 27 5 3 5 NAV Displays 5 28 5 3 6 Magnetic Heading Display Data 5 34 APPENDIX A GH 3100 INTERFACE SIGNAL NAME CABLE CHARACTERISTICS A 1 Introduction A 1 A 2 Digital Interface A 1 A 2 1 ARINC 429 Input BUS A 1 A 2 2 CSDB Input BUS A 2 A 2 3 RS 422 Input BU...

Page 10: ...play 3 6 3 4 DME Display 3 6 3 5 FMS Display 3 7 3 6 TACAN Display 3 8 5 1 Indicator Front Panel 5 1 5 2 Attitude Display with Callouts 5 7 5 3 Chevrons in Excessive Pitch Attitude Display 5 8 5 4 Full Screen Attitude Failure Display 5 10 5 5 Processor Error Screens 5 11 5 6 Attitude Display with Airspeed and Altitude 5 12 5 7 Altitude Displays 5 13 5 8 Invalid Air Data Displays 5 15 5 9 IAS Tape ...

Page 11: ... Configuration 1 3 2 1 GH 3100 Installation Kit P N 504 1895 07 2 2 2 2 Magnetometer Installation Kit P N 504 1895 05 2 7 2 3 Magnetometer Installation Kit P N 504 1895 18 2 7 3 1 Installation Data Record 3 10 4 1 Indicated Airspeed 4 2 4 2 Fault List 4 3 5 1 Menu Item Display Summary 5 4 5 2 NAV Annunciator Colors 5 19 A 1 External Systems BUS Input Options A 3 ...

Page 12: ...on Standard DCM Detachable Configuration Module NVIS Night Vision Imaging System Degree N A Not Applicable DEG Degree OBS Omni Bearing Selector DG Directional Gyro OM Outer Marker DME Distance Measuring Equipment PFD Primary Flight Display DTK Desired Track P N Part Number EASA European Aviation Safety Agency PVOR Pseudo VHF Omnidirectional Range EFIS Electronic Flight Instrument System REF Refere...

Page 13: ...the end of this section is a list of equipment required but not supplied with the system A list of system components is provided in Table 1 1 Installation kits are called out in paragraph 1 6 and described in the installation section Table 1 1 GH 3100 System Components NAME MODEL PART NUMBER Electronic Standby Indicator GH 3100 501 1860 see Table 1 2 Detachable Configuration Module DCM 3100 501 18...

Page 14: ...GH 3100 Installation Operation Manual Page 1 2 General Information TP 559 March 30 2017 Revision K GH 3100 DCM 3100 MAG 3000 MAG 3100 Figure 1 1 GH 3100 Electronic Standby Instrument System ...

Page 15: ...1860 1401 28 V No Black 200 Sec 542 2851 02 501 1860 1501 5 0 V Yes Gray 200 Sec 542 2851 02 501 1860 1601 5 0 V Yes Black 200 Sec 542 2851 02 501 1860 1701 28 V Yes Gray 200 Sec 542 2851 02 501 1860 1801 28 V Yes Black 200 Sec 542 2851 02 501 1860 2101 5 0 V No Brown 100 Sec 542 2851 02 501 1860 2201 28 V No Brown 100 Sec 542 2851 02 501 1860 0103 5 0 V No Gray 100 Sec 9230 10000 01 501 1860 0203...

Page 16: ...tion A bezel mounted light sensor provides automatic display dimming capability with manual offset control achieved through the menu mode The GH 3100 contains the following built in interfaces ARINC 710 711 VHF NAV Receivers ARINC 429 CSDB ARINC 709 VHF DME ARINC 429 CSDB TACAN ARINC 429 Flight Management System Interface ARINC 429 Three axis solid state Magnetometer input for Magnetic Heading RS ...

Page 17: ...tted via an RS 422 bus to the Standby Attitude Indicator GH 3100 The field data is used with the pitch and roll attitude of the Standby Attitude Indicator to compute the magnetic heading of the aircraft NOTE Refer to the MAG 3000 Install manual TP 633 for complete installation information 1 2 4 Magnetometer MAG 3100 The Magnetometer uses a three axis magnetic sensor to sense magnetic fields The fi...

Page 18: ... Vdc or 0 9 watts at 28 0 Vac or Vdc CIRCUIT BREAKER 3 0A recommended CONFIGURATION See Table 1 2 OPERATING TEMPERATURE 40 to 70 C 40 to 158 F STORAGE TEMPERATURE 55 to 85 C 67 to 185 F MAXIMUM ALTITUDE 25 000 ft AIR SPEED AND ALTITUDE MAXIMUM DISPLAY LIMITS Mach Range 0 41 to 0 99 Altitude Range 1 000 to 55 000 feet Indicated Airspeed Range 0 to 450 knots OPERATION REQUIREMENTS DCM 3100 installed...

Page 19: ...to 450 Knots 0 41 to 0 99 Mach Air Data Computer TSO C113 Airborne Multipurpose Electronic Display TSO C115b Airborne Navigation Equipment Using Multi Sensor Inputs 1 3 1 2 ETSO Authorizations ETSO NO ETSO ADDITIONAL MARKING ETSO TITLE ETSO C2d Airspeed Instruments ETSO C4c 28 V dc 50W max Bank and Pitch Instruments ETSO C6d Directional Instruments Magnetic ETSO C8d Vertical Speed Instruments Rate...

Page 20: ...idual units Software revision is shown on the display during the startup phase of the Electronic Standby Indicator 1 4 1 Software Release Summery 1 Software release 1 1 see Service Bulletin SB501 1860 11 added the capability of compensating the IAS with DCM 3100 loaded constants K1 and K2 Superseded by SB501 1860 14 2 Software release 1 2 see Service Bulletin SB501 1860 14 released to improve atti...

Page 21: ...ration Test Box JT 147A has no scheduled maintenance interval MAT 3000A Transmitter Assembly P N 501 1846 01 Test Box Cable P N 501 8552 10 GH 3100 Adapter Cables P N 570 8984 01 and P N 570 8984 02 The MAT 3100 Transmitter P N 9200 21250 01 is used only for the MAG 3100 and is a part of the test set only upon request Circuit Breaker Installer responsible for determining appropriate circuit breake...

Page 22: ...3838 Phone 800 678 0141 Fax 607 563 5157 Or ITT Cannon 1851 E Deere Ave Santa Ana CA 92705 6500 Phone 714 261 5300 Fax 714 575 8324 Digital Level Required for GH 1000 and magnetometer installation Manufacturer SmartTool M D Building Products 92346 or equivalent Installation Kit s Installation Kit P N 504 1895 07 for the GH 3100 Includes the following Mounting Clamp P N 566 1814 04 Mating Connector...

Page 23: ...r TSO approvals of this article are minimum performance standards It is the responsibility of those desiring to install this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards The article may be installed only if further evaluation by the applicant documents an acceptable installation and is approved ...

Page 24: ...GH 3100 Installation Operation Manual Page 1 12 General Information TP 559 March 30 2017 Revision K This page intentionally left blank ...

Page 25: ...re the equipment received with that noted on the packing list Missing items or evidence of damage should be reported to the carrier making the delivery To justify a claim retain the original shipping container and all packing materials Every effort should be made to retain the original shipping containers for storage If the original containers are not available a separate cardboard container shoul...

Page 26: ...ers engine exhausts or heat sources CAUTION Improper installation of the 3 ATI mounting clamp may result in damage to the indicator during operation due to excessive heat build up 4 Compare the space requirements of the indicator with the installation area being considered Refer to Figure 2 2 for dimensional requirements It is recommended that the Mounting Clamp provided in the installation kit se...

Page 27: ...of the wiring harness before installing the indicator into the instrument panel The connection of mating connector may be required before installation of the unit 9 This completes the indicator installation Refer to paragraph 2 3 3 for electrical connections 2 3 2 DCM 3100 Detachable Configuration Module Connect the Detachable Configuration Module to the wiring harness of the GH 3100 via the attac...

Page 28: ...GH 3100 Installation Operation Manual Page 2 4 Installation TP 559 March 30 2017 Revision K Figure 2 2 GH 3100 Outline Dimensions and J1 Pin Assignments Sheet 1 of 2 ...

Page 29: ...GH 3100 Installation Operation Manual TP 559 Installation Page 2 5 Revision K March 30 2017 Figure 2 2 GH 3100 Outline Dimensions and J1 Pin Assignments Sheet 2 of 2 ...

Page 30: ...ise noted Use M22759 or equivalent wire and M27500 or equivalent for twisted shielded wired for installation The length and routing of the external cables must be carefully studied and planned before attempting installation of the equipment Wire marking identification is at the discretion of the installer The GH Indicator and Magnetometer should be placed on separate circuit breakers Use of any ca...

Page 31: ...ed for MAG installations requiring a bulk head mount mating connector NOTE All mounting hardware must be non ferrous materials 1 It is recommended that the magnetometer be mounted directly to the aircraft frame in the fuselage in a location free of magnetic disturbances The magnetometer should be located near the primary flux sensor this will reduce heading differences with the primary flight disp...

Page 32: ...ocated near the primary flux sensor this will reduce heading differences with the primary flight display The location of the Magnetometer should not be near potential magnetic interference such as ferrous metals high current cables or luggage compartments that will affect the accuracy of the system 2 The P1 connector must be at least 6 inches from the magnetometer shell and secured to limit moveme...

Page 33: ...GH 3100 Installation Operation Manual TP 559 Installation Page 2 9 Revision K March 30 2017 Figure 2 4 System Electrical Interface Diagram with MAG 3000 ...

Page 34: ...GH 3100 Installation Operation Manual Page 2 10 Installation TP 559 March 30 2017 Revision K Figure 2 5 System Electrical Interface Diagram with MAG 3100 Sheet 1 of 2 ...

Page 35: ...GH 3100 Installation Operation Manual TP 559 Installation Page 2 11 Revision K March 30 2017 Figure 2 5 System Electrical Interface Diagram with MAG 3100 Sheet 2 to 2 ...

Page 36: ...GH 3100 Installation Operation Manual Page 2 12 Installation TP 559 March 30 2017 Revision K This page intentionally blank ...

Page 37: ...moved for maintenance the DCM 3100 remains with the aircraft via a chain that is attached to the GH 3100 wiring harness It is recommended that a conductive connector dust cover be placed over the connector end of the DCM 3100 1 Apply power to the GH 3100 Electronic Standby Instrument System Allow the indicator to complete Built in Test BIT A normal display is viewed in approximately three minutes ...

Page 38: ...libration Test Box 3 2 2 2 Calibration Procedures 3 2 2 2 1 Attitude Compensation Attitude compensation does not affect the GH 3100 computed pitch display Attitude differences between the GH 3100 and MAG 3000 or MAG 3100 are automatically compensated by the utilization of the MAT 3000A or MAT 3100 Transmitter Assembly refer to JT 147A during steps 1 7 1 Remove input power from the GH 3100 Instrume...

Page 39: ...ing Calibration The following terms are being defined to limit confusion of their meaning during the heading calibration procedure Magnetic Heading Any one of four cardinal or intercardinal headings located on a compass rose Actual Aircraft Heading Direction of the longitudinal axis of the airframe Misalignment The difference between the magnetic and actual aircraft heading NOTE The GH 3100 Indica...

Page 40: ... DCM 3100 When prompted by the message on the Calibration Test Box display remove power from the GH 3100 instrument system 7 Remove the JT 147A from the aircraft returning the GH 3100 and DCM 3100 to a normal installation configuration Figure 3 1 Example of Plane on Compass Rose 3 2 2 2 3 Calibration Check 1 Apply power to the GH 3100 instrument system and wait approximately 3 minutes for the Alig...

Page 41: ...up a valid ILS input to GH 3100 Indicator Figure 3 2 ILS Display 2 Select ILS normal display using the GH 3100 Indicator menu and observe normal indication of the following ILS display data refer to Figure 3 2 ILS Mode Descriptor Selected Course Left Right Deviation Indicator Localizer Indicator Up Down Deviation Indicator Glide Slope Indicator 3 Select ILS BC Back Course using the GH 3100 Indicat...

Page 42: ... display using the GH 3100 Indicator menu and observe normal indication of the following VOR display data refer to Figure 3 3 VOR Mode Descriptor Left Right Deviation Indicator Selected Course To From Ambiguity Indicator 3 Turn off the VOR input and observe that the VOR display data is removed 3 2 2 2 7 DME System Test The following paragraphs apply only to aircraft with a DME installed and the in...

Page 43: ...o aircraft with FMS installed and the indicator configured to display FMS information Multiple FMS display options are available for the GH 3100 and appearance is dependent on FMS option included in configuration 1 Set up a valid FMS input to GH 3100 Indicator Figure 3 5 FMS Display 2 Select FMS normal display using the GH 3100 Indicator menu and observe normal indication of the following FMS disp...

Page 44: ...tation Distance to Station 3 Turn off the TACAN input and observe that the TACAN display data is removed 3 2 2 2 10 Pneumatic Pressure Checks 1 Push in on indicator GH 3100 adjustment knob and observe that the barometric correction window displays STD 29 92 In HG 2 Connect an Air Data Test Set to the aircraft pitot and static ports 3 Adjust pitot and static pressures to provide a vertical velocity...

Page 45: ...E A red VNE bar will extend from the VNE Power On point to the high speed end of the tape Record results in Table 3 1 Test Paragraph T4 Reset the Air Data Test Set to provide airspeed lower than VNE A yellow VNE bar will be drawn from the VNO point to the VNE Power On point Record results in Table 3 1 Test Paragraph T5 Reset the airspeed setting on the Air Data Test Set so that a green bar is draw...

Page 46: ...00 feet 20 000 feet 130 feet 20 000 feet 30 000 feet 180 feet 30 000 feet T2 Airspeed Fixed Wing 0 46M 0 01M Yes No 9 000 feet 260 0 KIAS 2 0K T3 Yes No Vmo Changes to red Airspeed Rotor Wing T4 Yes No Observe red Vne bar T5 Yes No Observe yellow Vno to Vne bar T6 Yes No Observe green Vno bar See CFR FAR PART 91 411 Part 43 Appendix E 3 2 2 2 11 Final Installation Inspection Make certain that indi...

Page 47: ...ttached to the GH 3100 wiring harness 2 Allow the indicator to complete Built in Test BIT A normal display will be viewed in approximately three minutes The display should reflect the attitude of the aircraft as it rests on the ramp 3 Compare results on GH 3100 display with that of primaries a Attitude will be 0 5 b Heading will be 4 0 Only for units configured with heading c Airspeed indication w...

Page 48: ...ate heading The same requirements must apply d Remove power from the GH 3100 instrument system 2 If the Magnetometer does not pass the Calibration Check the unit must undergo the Initial system installation on page 3 1 paragraph 3 2 page 3 1 3 2 3 3 Detachable Configuration Module Check The following instructions are used only after a DCM 3100 is removed for replacement or repair 1 Verify that par...

Page 49: ...defined as that point in time when repair is no longer economical 4 2 1 Periodic Maintenance Regular maintenance of the GH 3100 Electronic Standby Instrument System is not required except as included in this section 1 At regular inspection intervals a Check that mounting hardware is secure b Check that cable connectors are properly mated and secured c Check that connecting cables are not cut or pi...

Page 50: ...r data test set to each of the altitudes listed in CFR FAR Part 91 411 part 43 appendix E up to the service ceiling of the aircraft Observe that the indicator altitude tape moves smoothly and properly displays altitude within the listed tolerances 4 2 2 3 Computed Airspeed Accuracy Check 1 Set the barometric pressure on the display to 29 92 in Hg 2 Set static pressure to ambient atmospheric pressu...

Page 51: ...ntact L3 Aviation Products Customer service before removal Heading between GH 3100 and Primary system greater than 4 1 Check for magnetic interference around magnetometer 2 GH 3100 system may require recalibration Follow the Post Installation checkout procedures in the Installation Checkout section of this manual 3 Replacement of one of the GH 3100 system components may be required Contact L3 Avia...

Page 52: ...ck for valid ARINC 429 data from air data computer If valid contact L3 Aviation Products Customer service If no ARINC 429 data is present check for correct input voltage to the air data computer If air data computer input voltage is ok check continuity between GH indicator and air data computer If air data computer input voltage is missing Check breakers 2 Replacement of air data computer may be r...

Page 53: ...form cannot be used The use of loose crystals may cause unnecessary damage resulting in a cleaning problem a If the GH 3100 is removed for maintenance the DCM 3100 remains with the aircraft via a chain that is attached to the GH 3100 wiring harness a Ensure that conductive covers caps are installed on the exposed terminals of connectors and pitot static lines if applicable b LRU s that are electro...

Page 54: ...omponents to L3 Aviation Products Attn Customer Service 5353 52nd Street S E Grand Rapids MI USA 49512 9704 3 Send a letter along with the defective part and include the following information Your name address and telephone number Description of component A brief description of the difficulty 4 5 3 Magnetometer MAG 3100 and MAG 3000 1 For the MAG 3100 refer to Installation Manual 0040 21200 01 2 F...

Page 55: ...b The adjustment knob is located in the lower right corner of the indicator The knob may be rotated to the right and left as well as pushed in Rotating the adjustment knob clockwise increases values and counter clockwise rotation decreases values The adjustment knob does not pull out 5 2 1 1 1 Barometric Correction The adjustment knob is used to change the baro setting at all times except when in ...

Page 56: ...t In relatively low lighting conditions the brightness offset control will allow the display to be adjusted for minimum brightness output but not to maximum brightness output 5 2 2 Menu Interface The push button key and the adjustment knob are used to view select and change alphanumeric menu items shown on the screen In the menu mode a list of menu items is presented across the lower portion of th...

Page 57: ...unction Initiation When the knob is pressed the highlighted command is activated If the activation is a singular function the menu mode ends If the activation is a sub menu title the sub menu command list occupies the menu area with the adjustment knob used in the same manner as the initial menu If the highlighted menu command is a set command SET BRIGHTNESS OFFSET or SET CRS a set command operati...

Page 58: ...selected course Press the knob when done 000 SOFTWARE VERSION 1 X VOR ILS or TACAN is the active NAV display SOFTWARE VERSION 3 X VOR or TACAN is the active NAV display ILS BC or ILS Normal ILS is the active NAV display Crs Auto Center When VOR or TACAN data is the active NAV display and left right deviation needle is showing Nav Displays List of Possible Sub Menu Items Configuration Dependant If ...

Page 59: ... has already been selected and is active Nav OFF VOR ILSX or ILSX VOR ILSX or VORX FMSX or GPSX or NAVL or NAVR FMSX or GPSX or NAVL or NAVR TACAN1 TACAN2 The sub menu items shown are those configured options that are not the active NAV data being shown Activation of any sub menu item changes the NAV data being shown to that item Activation of that NAV OFF item removes NAV data from the display 5 ...

Page 60: ...ub menus where the items of the list are based on the current operating mode 1 2 3 If in HPA mode If in MB mode If in HG mode MB HPA HPA IN HG IN HG MB Of the three baro types the two that are not shown are shown in the sub menu Activation of a baro type changes the baro display to that type 5 2 2 3 12 IAS Tape Direction The IAS TAPE DIRECTION UP or DOWN menu item is shown when IAS INCREASE TAPE D...

Page 61: ...3 1 Menu Display The menu mode has a black background with dim white menu items commands Highlighted menu items are white with a white symbol preceding the item 5 2 3 2 Attitude Data Attitude data is shown in the form of a pitch ladder a roll pointer a roll scale a slip skid indicator and aircraft reference symbol Refer to full screen display as shown in Figure 5 2 Figure 5 2 Attitude Display with...

Page 62: ...t any attitude A ghost horizon is shown whenever the actual horizon line lies outside of the circular viewing area In this condition the pitch ladder continues to move with the actual pitch but the sky ground boundary remains in view to help the pilot keep his orientation A reduced intensity line marks the ghost horizon boundary 5 2 3 3 3 Background The background on which pitch ladder lines are d...

Page 63: ...k zero refer to Figure 5 2 Additionally there are a series of white lines representing 10 20 30 and 60 roll The lines radiate out from the center of the attitude display area starting on an arc of a circle tangent to the apex of the zero roll triangle The lines for 30 and 60 are longer than the other lines The 45 roll marks are configured to either fixed white lines or filled white equilateral tri...

Page 64: ...s erection cut off for a duration which is long enough for potential attitude errors to develop 2 Units configured for heading display the Extended Maneuver indication whenever heading alignment criteria are not met 3 After appearing the Extended Maneuver indication is removed when any of the following occur Normal erection and heading alignment if configured for heading are restored The attitude ...

Page 65: ...n with instructions are shown if errors are detected in the graphic or host processors as shown in Figure 5 5 Errors attributed to the Graphics Processor automatically generate a graphics processor reboot with little display or information interruption Errors attributed to the Host Processor require the operator to manually reset power to the indicator Figure 5 5 Processor Error Screens ...

Page 66: ... COLOR The following defines more precisely the tape presentation The altitude tape displays a span of 1 100 feet during normal operation The altitude tape displays a span of 800 feet when the menu mode is active The altitude tape current altitude is aligned with the vertical center of the attitude display area The altitude tape scale digit size is medium for the 1 000 and 10 000 foot digits and s...

Page 67: ...ied digits and be capable of displaying altitudes from 1 000 to 55 000 feet with a resolution of 10 feet when ALTITUDE DISPLAY ROLLING DIGITS is configured for OFF Negative numbers are shown with a right justified minus sign The minus sign appears when the altitude is less than 0 feet Leading zeroes in the altitude digital readout is used to provide a minimum of three digits For positive altitudes...

Page 68: ...be capable of displaying altitudes from 305 to 15 240 meters rounded to multiples of 3 meters Negative numbers are shown with a right justified minus sign The minus sign appears when the altitude is less than 0 meters For positive altitudes less than 10 000 meters a hashed box is shown as a place holder in the ten thousands place of the metric altitude digital readout When METRIC ALTITUDE READOUT ...

Page 69: ...ed Digital Readout is shown at the top right of the indicator display below the baro readout window An active Menu Mode will not obscure the roll scale tic marks baro or vertical speed digital readout The vertical speed digital readout is configured in the detachable configuration module The vertical speed window color is black with a white border The digit and arrow color is based on unit configu...

Page 70: ...ertical tape refer to Figure 5 6 The Mach readout is located at the top to the tape IAS tape format is shown in Figure 5 9 A B C D Figure 5 9 IAS Tape Displays The IAS tape displays a span of 100 knots when the menu is not shown from the bottom of the mach box to the bottom of the display The IAS tape span is 72 0 5 knots when the menu is shown from the bottom of the mach box to the top of the men...

Page 71: ...VNE Power Off is less than VNE Power On as shown in Figure 5 9D The striped line appears under the IAS digits and over the IAS tape tic marks and VNE bars 5 2 4 1 7 IAS Digital Readout Format The IAS digital readout consist of three large size right justified digits capable of displaying current IAS from 0 to 450 knots but TSO performance only guaranteed from 50 to 450 knots with a resolution of o...

Page 72: ... display area refer to Figure 5 9B or C The on top state is defined so as the IAS tape and attitude display do not interfere with the mach digital readout When IAS PART 27 29 is configured for OFF and the mach digital readout is OFF and the mach data is greater than or equal to 0 45 mach the mach digital readout shall be turned ON When IAS PART 27 29 is configured for OFF and the mach digital read...

Page 73: ...OR ARINC CSDB ANNUNCIATOR COLOR VOR VOR1 VOR2 VOR3 VOR ILS 1 or AUTO VOR1 Annunciator Color VOR VOR1 VOR2 VOR3 VOR ILS 2 or AUTO VOR2 Annunciator Color ILS ILS1 ILS2 ILS3 VOR ILS 1 or AUTO ILS1 Annunciator Color ILS ILS1 ILS2 ILS3 VOR ILS 2 or AUTO ILS2 Annunciator Color TCN1 TACAN 1 TCN1 Annunciator Color TCN2 TACAN 2 TCN2 Annunciator Color FMS FMS1 FMS2 FMS3 FMS4 FMS GPS 1 FMS GPS 2 FMS Annuncia...

Page 74: ...or Background based on unit configuration and having O Annunciator Color M Annunciator Color and I Annunciator Color respectively based on unit configuration at the second line from the bottom right side of the attitude display area Figure 5 13 FMS Mode The data descriptors NM KTS MIN CRS DTK and BRG is shown in the small character size Each following the digits in the distance ground speed time t...

Page 75: ...ified and located in three consecutive lines ending at the lower left corner of the attitude display area above the area of the optional heading display WP ALRT and WAY PT are mutually exclusive on the same line The background for each of these annunciators is the Message Annunciator Background based on unit configuration The descriptors BC NM KTS MIN CRS DTK BRG NAV TST TO FR DME H and the NAV or...

Page 76: ... up down needle s movement is constrained to 110 of full scale deflection in each direction from the boresight mark 5 2 5 2 4 Up Down Deviation Cross Pointer Format The up down needle has the same format as the right left needle rotated by 90 The up down needle is drawn in front of all other symbology except the left right needle and are drawn such that it does not obscure the black scaling marks ...

Page 77: ...s center A DG descriptor is displayed in the free heading mode in white characters above the index line For roll angles near 180 the DG descriptor is removed when the roll pointer requires that display area occupied by the descriptor When the Menu Mode is active the heading tape is removed from the display Figure 5 15 Heading Tape VOR Mode The heading tape is drawn such that its background color i...

Page 78: ...tapes The heading tape will not extend into the altitude or airspeed tapes The selected course arrow color has the COURSE ARROW COLOR and COURSE ARROW BACKGROUND based on unit configuration Figure 5 18 Heading Invalidity with Box An invalid heading omits the heading tape tic marks heading tape numbers selected course arrow STBY designator and reference triangle When HEADING INVALIDITY TYPE is conf...

Page 79: ... indicator displays an identification screen software identification numbers a software copyright notice total number of operating hours and aircraft effectivity or the result of the power on self tests if a failure is detected NOTE If there has been a failure which affects the display hardware the attempt to display the identification screen may fail The identification mode displays self test res...

Page 80: ... ID screen is shown Then the indicator displays the attitude fail screen as shown in Figure 5 4 with a message indicating that the indicator is aligning shown below the aircraft symbol A counter appears below the message which shows the number of seconds remaining in the alignment process If sensor alignment is unsuccessful the attitude fail screen remains on the display as long as power is applie...

Page 81: ...e Slip Skid Indicator is such that rotating the unit by 8 1 about the roll axis shall result in the slip skid indicator deflecting to its maximum deflection of 2 25 0 25 indicator lengths The operational limit of the slip skid indicator is 8 1 The direction of the deflection of the Slip Skid Indicator shall be right for clockwise rotation of the nit and left for counter clockwise rotation Rotating...

Page 82: ...al speed data is calculated from the altitude data 5 3 4 5 Air Data Invalidity The invalid altitude display as shown in Figure 5 8A or B is shown if any tests of air data hardware detect fault with the altitude data The invalid airspeed display as shown in Figure 5 10A or B is shown if any tests of air data hardware detect fault with the computed airspeed data When IAS PART 27 29 is configured for...

Page 83: ... indicator is configured for ARINC 710 ILS Receiver and an ARINC Input bus is configured for VOR ILS1 this NAV mode is considered ILS mode only If the indicator is configured for ARINC 710 ILS Receiver and an ARINC Input bus is configured for VOR ILS2 this NAV mode is considered VOR mode only 5 3 5 1 1 ILS Descriptor The descriptors are ILS ILS 1 ILS 2 or ILS 3 When in ILS Mode using ARINC 429 inp...

Page 84: ...pointer full scale movement is identical to the ILS mode with the exception that the ILS BC mode left right deviation indicator is mirrored on the other side of the boresight mark When in ILS BC Mode the up down cross pointer is removed from the display 5 3 5 3 Marker Descriptors When the indicator is in VOR Mode or ILS Mode the reception of marker beacon information is annunciated with the charac...

Page 85: ... VOR Data Type NAV receivers transmit VOR data representing either bearing to omnibearing or radial from the station The unit is configurable for the two types of VOR data 5 3 5 5 DME Display Data When in VOR Mode or ILS Mode the indicator displays DME data as defined by configuration The DME data consists of DME Slant Range Distance in Nautical Miles NM a DME Hold annunciator if required and opti...

Page 86: ...reater 5 3 5 6 6 Desired Track Selected Course The display of Desired Track or Selected Course is dependent on the FMS navigator 5 3 5 6 7 Bearing To Waypoint When in FMS Mode Bearing to Waypoint data and a descriptor is shown as the bearing from the present aircraft position to the active waypoint if FMS Bearing On has been chosen in the main menu 5 3 5 6 8 FMS Magnetic True North Reference The D...

Page 87: ...ore than 90 0 1 from the current TACAN omnibearing the appropriate FROM indication is shown When the Selected Course is displaced by less than or equal to plus or minus 90 0 1 from the current TACAN omnibearing the appropriate TO indication is shown 5 3 5 8 5 Course Auto Center Automatic course centering is done using the main menu When the Course Auto Center menu item is selected the Selected Cou...

Page 88: ...on is added to the Pilot s Menu to allow setting correction of the heading value When external heading information becomes valid from an invalid condition an immediate fast slew is initiated followed by the return of the normal slew rate 5 3 6 3 Selected Course Arrow When VOR or TACAN navigation information is shown with heading the selected course heading arrow shows the Selected Course When vali...

Page 89: ...ction of this manual for J1 pin assignment information A 2 1 ARINC 429 Input BUS ARINC 429 Input BUS 1 2 3 4 5 6 can be configured to receive data at high 100 kbps and low 12 0 to 14 5 kbps speeds Each Input BUS complies with ARINC 429 standards and is compatible with ARINC 711 Airborne VOR Receivers including VOR receivers which combine the functions of ARINC 710 Airborne ILS receivers ARINC 702 ...

Page 90: ...eviation BNR Label 147 Magnetic Variation BNR GAMA Label 163 PFD Mode Select Word DSC Non Std Label 251 Distance to Waypoint BNR GAMA Label 251 Distance to Waypoint BNR Non Std Label 272 FMC Mode Word 1 DSC Non Std Label 275 LRN Status Word DSC GAMA Label 326 Lateral Deviation Scale Factor BNR GAMA Label 327 Vertical Scale Factor BNR GAMA The following ARINC 429 label is received at high 100 kbps ...

Page 91: ...X X X X CSDB BUS 1 X X Auto CSDB BUS 2 X DME Dir Freq 1 DME Dir Freq 2 DME Auto NOTE Configuration Information is programmed on the DCM 3100 at the factory A 2 4 1 Configuration Notes 1 When Heading Input is configured for ARINC 429 the ARINC 429 BUS 3 and 4 receive data at high 100 kbps speed 2 When VOR ILS 1 VOR ILS 2 TACAN 1 and TACAN 2 are configured for ARINC 429 the ARINC BUS see Table A 1 f...

Page 92: ...Signal Type Electrical Characteristics Connection No Connection Comments PIN D Signal Name ARINC 429 OUTPUT 2 A Signal Type ARINC 429 Transmit Electrical Characteristics High Speed ARINC 429 100 kbps Connection Not Connected Comments Reserved for factory testing PIN E Signal Name ARINC 429 INPUT 1 A Signal Type ARINC 429 Receive Electrical Characteristics Configuration Option Low Speed ARINC 429 1...

Page 93: ... ARINC 429 12 0 to 14 5 kbps High Speed ARINC 429 100 kbps Connection See Digital Interface information in paragraph A 2 Comments PIN J Signal Name ARINC 429 INPUT 3 A Signal Type ARINC 429 Receive Electrical Characteristics Configuration Option Low Speed ARINC 429 12 0 to 14 5 kbps High Speed ARINC 429 100 kbps Connection See Digital Interface information in paragraph A 2 Comments PIN K Signal Na...

Page 94: ...erface information in paragraph A 2 Comments PIN P Signal Name ARINC 429 INPUT 5 A Signal Type ARINC 429 Receive Electrical Characteristics Configuration Option Low Speed ARINC 429 12 0 to 14 5 kbps High Speed ARINC 429 100 kbps Connection See Digital Interface information in paragraph A 2 Comments PIN R Signal Name ARINC 429 INPUT 5 B Signal Type ARINC 429 Receive Electrical Characteristics Confi...

Page 95: ...Comments Reserved for factory testing PIN V Signal Name 5VAC DC_LOW Signal Type Lighting Power Return Electrical Characteristics Connection Aircraft 5VAC or 5VDC or 28VDC Return BUS Configuration option Comments PIN W Signal Name ARINC 429 OUTPUT 2B Signal Type ARINC 429 Transmit Electrical Characteristics High Speed ARINC 429 100 kbps Connection Not Connected Comments Reserved for factory testing...

Page 96: ... 5 kbps High Speed ARINC 429 100 kbps Connection See Digital Interface information in paragraph A 2 Comments PIN b Signal Name 28V_RETURN Signal Type 28 Vdc Power Return Electrical Characteristics Connection Aircraft 28V Return BUS Comments PIN c Signal Name RS 422_INPUT A Signal Type RS 422 Receive Electrical Characteristics 2 to 6 Vdc Logic 0 6 to 2 Vdc Logic 1 Connection MAG 3000 Pin J1 1 Comme...

Page 97: ...pe Electrical Characteristics Connection No Connection Comments PIN g Signal Name CHASSIS GND SIGNAL TYPE Chassis Ground Electrical Characteristics Connection Airframe Ground Comments PIN h Signal Name SPARE Signal Type Electrical Characteristics Connection No Connection Comments PIN j Signal Name SPARE Signal Type Electrical Characteristics Connection No Connection Comments ...

Page 98: ...GH 3100 Installation Operation Manual Page A 10 Appendix A TP 559 March 30 2017 Revision K This page intentionally left blank ...

Page 99: ...501 1860 1201 501 1860 1301 501 1860 1401 501 1860 1501 501 1860 1601 501 1860 1701 501 1860 1801 501 1860 2101 501 1860 2201 501 1860 0102 501 1860 0103 501 1860 0203 501 1860 0303 501 1860 0403 501 1860 0503 501 1860 0603 501 1860 0703 501 1860 0803 501 1860 1103 501 1860 1203 501 1860 1303 501 1860 1403 501 1860 1503 501 1860 1603 501 1860 1703 501 1860 1803 501 1860 2103 501 1860 2203 MODEL DC...

Page 100: ...nge No 1 used in lieu of Change No 0 Equipment Tested to Category R for fixed Wing Aircraft Random Test only and Category U remarks for helicopters with unknown frequencies Explosion Proofness 9 0 Equipment tested to Category E Waterproofness 10 0 Equipment tested to Category X no test performed Fluids Susceptibility 11 0 Equipment identified as Category X no test performed Sand and Dust 12 0 Equi...

Page 101: ... Category X no test performed Electrostatic Discharge 25 0 Equipment tested to Category A Other Tests None Remarks Tests were conducted at L 3 Avionics Systems Inc Touchstone Systems Services Cessna Aircraft Co and DNB Engineering Inc The In Flight Loss of Cooling test is not relevant because the unit does not require external cooling Unit does contain an internal cooling fan During all temperatur...

Page 102: ...1860 1703 501 1860 1803 501 1860 2103 501 1860 2203 Tested in September 2010 at Environ Laboratories Minneapolis MN See the Test Report Drawing Number 513 1430 for the actual test results Table 1 FREQUENCY CONTINUOUS WAVE SQUARE WAVE MODULATION PULSE MODULATION 100MHz 126MHz 350v m 510v m 200v m 126MHz 400MHz 510v m 510v m 200v m 400MHz 700MHz 200v m 200v m 800v m 700MHz 848MHz 250v m 250v m 1700v...

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