INSTALLATION MANUAL AND OPERATING INSTRUCTIONS MD41

INSTALLATION MANUAL AND OPERATING INSTRUCTIONS MD41
INSTALLATION MANUAL AND
OPERATING INSTRUCTIONS
MD41-( ) Series GPS Annunciation Control Unit
for Garmin GTN 650/750
MD41-1468A
MD41-1478A
MD41-1464A
MD41-1474A
28vdc
28vdc
14vdc
14vdc
Horizontal Mount
Vertical Mount (shown on page 10)
Horizontal Mount
Vertical Mount (shown on page 10)
Mid-Continent Instruments and Avionics
9400 E. 34th Street N., Wichita, KS 67226 USA
Phone 316-630-0101  Fax 316-630-0723
Manual Number 9010778
REV. A October 28, 2013
Revision Detail
ECO
6051
Rev.
N/R
1
A
REV. A October 28, 2013
Date
05/30/00
11/28/06
10/28/13
Detail
Complete issue
Added (A), (W) and (TAWS) receivers
Updated Technical Specifications to include compatible
Garmin GTN Systems.
2
TABLE OF CONTENTS
SECTION 1
1.1
1.2
1.2.1
1.2.2
1.2.3
1.2.4
1.2.4.1
1.2.4.2
1.2.5
1.2.6
1.2.7
GENERAL DESCRIPTION
INTRODUCTION
SPECIFICATIONS, TECHNICAL
PHYSICAL CHARACTERISTICS
ENVIRONMENTAL CHARACTERISTICS
SPECIFICATIONS, ELECTRICAL
FRONT PANEL CONTROLS AND ANNUNCIATIONS
CONTROLS
ANNUNCIATIONS
INTERFACE
EQUIPMENT LIMITATIONS
MAJOR COMPONENTS
SECTION 2
2.1
2.2
2.3
INSTALLATION CONSIDERATIONS
COOLING
EQUIPMENT LOCATION
ROUTING OF CABLES
SECTION 3
3.1
3.2
3.3
3.4
INSTALLATION PROCEDURE
GENERAL INFORMATION
UNPACKING AND INSPECTING
MOUNTING THE MD41-( )
INSTALLATION LIMITATIONS
SECTION 4
4.1
4.2
POST INSTALLATION CHECKOUT
PRE-INSTALLATION TEST
OPERATING INSTRUCTIONS
FIGURE N0.
3.1
3.2
3.3
LIST OF ILLUSTRATIONS
SCHEMATIC PINOUT, 25 PIN DSUB
OUTLINE DRAWING
WIRING DIAGRAM, MD41-1464A/1474A (14Volt),
MD41-1468A/1478A/1468A(5V)/1478A(5V) (28volt)
APPENDIX
ENVIRONMENTAL QUALIFICATION FORM
REV. A October 28, 2013
3
SECTION 1 GENERAL DESCRIPTION
1.1
INTRODUCTION
The MD41-( ) is a compact, self -contained GPS Annunciation and Control unit. It meets
all requirements for external (remote) mode selection and status annunciation for the
Garmin GNS 430/530 VHF Communication and Navigation Management System.
Features include dual 20,000 hour lamps used for all annunciations, internally lighted
selection switches and automatic photocell dimming. An external annunciation dimming
adjustment is provided for balancing low level light conditions.
1.2
SPECIFICATIONS, TECHNICAL
Mid-Continent Instruments Co., Inc. certifies that the model MD41-( ) series, Annunciation
Control Unit has been tested to and meets or exceeds the functional and environmental
requirements of the following FAA Technical Standard Order (TSO):

FAA/TSO-C151a:
TERRAIN AWARENESS AND WARNING SYSTEM
We also certify we meet the requirements of Part 21, Subpart 0 of the Code of Federal
Regulations.
The MD41-( ) series, Annunciation Control Unit conforms to all pertinent documented
design and internal manufacturing standards. This includes, but is not limited to:
component drawings, specifications, testing criteria, inspection requirements, quality
processes, manufacturing instructions, and handling procedures. It shall be manufactured in
accordance with Mid-Continent Instruments FAA-approved Production Approval HolderQuality System Manual, Revision M, dated April 14, 2011 or later.
The MD41-151X series complies with the manufacturers’ specifications and has been
verified and approved for use with the following systems:
Mid-Continent Instruments and Avionics
Model Number(s):
Designed for use with
GPS System:
MD41-1468A
MD41-1478A
MD41-1464A
MD41-1474A
Manufacturer: Garmin International
Model(s):
650/750
CDI/HIS Annunciators
REV. A October 28, 2013
4
1.2.1 PHYSICAL CHARACTERISTICS
Mounting:
Width:
Height:
Depth:
Weight:
Panel
3.25 Inches
.80 Inches
3.20 Inches
0.50 lbs.
1.2.2 ENVIRONMENTAL CHARACTERISTICS
1.2.3
TSO Compliance:
Applicable Documents:
TSO C129
RTCA DO-160C, DO-208
Operating Temperature Range:
Humidity:
Altitude Range:
Vibration:
-55C to +70C
95% Non-Condensing
0 to 55,000 ft.
Cat. M and N
Operational Shock:
Rigid Mounting, 6 G Operational
15 G Crash Safety
SPECIFICATIONS, ELECTRICAL
Design
All Solid State
MD41-1464A/1474A (14VDC)
0.40 Amps
MD41-1468A/1478A (28VDC)
0.30 Amps
MD41-1468A(5V)/1478A(5V) (28DC)
0.30 Amps
1.2.4 FRONT PANEL CONTROLS AND ANNUNCIATIONS
1.2.4.1 CONTROLS
GPS
OBS
REV. A October 28, 2013
Momentary action switch, when pressed, will select
LOC or GPS presentation on HSI/CDI.
Momentary action switch, when pressed, will select between
automatic waypoint sequencing (AUTO) mode and OBS
mode.
In OBS mode, this will enable OBS selection input from
a remote HSI/CDI indicator.
5
1.2.4.2 ANNUNCIATIONS
VLOC
GPS
MSG
WPT
AUTO
OBS
INTG
TERM
APR
NAV or ILS information presented on the HSI or CDI.
GPS information presented on the HSI or CDI.
On indicates message(s) active.
On indicates reaching the arrival waypoint.
Automatic sequencing of waypoints is active.
On indicates GPS OBS mode of operation.
On indicates GPS receiver detecting a position error.
On indicates aircraft is within 30 miles of departure or arrival
airport.
On indicates the approach is active.
.
1.2.5 INTERFACE
CDI (select)
J1 Pin 4
Provides a momentary low to the
GNS 430/530
VLOC annunciation
J1 Pin 2
Receives ground from GNS 430/530
when in VOR/ILS mode
GPS annunciation
J1 Pin 1
Receives ground from GNS 430/530
when in GPS mode.
OBS (select)
J1 Pin 12
Provides a momentary logic low to the
GNS 430/530 when OBS is selected.
Selects between AUTO and OBS.
OBS annunciation
J1 Pin 24
Requires a logic low to annunciate
TERM annunciation
J1 Pin 3
Requires a logic low to annunciate
APR annunciation
J1 Pin 9
Requires a logic low to annunciate
WPT annunciation
Requires a logic low to annunciate
REV. A October 28, 2013
6
1.2.5 INTERFACE (cont.)
J1 Pin 8
MSG annunciation
J1 Pin 10
Requires a logic low to annunciate
INTG annunciation
J1 Pin 20
Requires a logic low to annunciate
Lamp Test
J1 Pin 7
Receives ground from remote test switch
to light all annunciations. (optional connection)
1.2.6 EQUIPMENT LIMITATIONS
The MD41-( ) series control units contain specific dash numbers to be used with various GPS
receivers or Navigation Management Systems. The installer must match the correct controller
part number with the system being installed.
The conditions and tests required for TSO approval 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 by the
Administrator.
The MD41-1464A/1474A/1468A/1478A/1468A(5V)/1478A(5V) is TSO’D and certified for
use with the Garmin GNS 430/530 system. This includes the (A), (W) and (TAWS) versions.
Any attempts to install the listed units in an installation other than the GNS 430/530 system is
prohibited. This will void the TSO.
NOTE: If the MD41-( ) is disconnected or removed from the aircraft, there will be no effect
in the operation of the GNS 430/530.
1.2.7 MAJOR COMPONENTS
This system is comprised of one major component, the MD41-146XA/147XA series GPS
Annunciation Control Unit.
REV. A October 28, 2013
7
SECTION 2 INSTALLATION CONSIDERATIONS
2.1
COOLING
No direct cooling is required. As with any electronic equipment, overall reliability may be
increased if the MD41-( ) is not located near any high heat source or crowded next to other
equipment. Means of providing a gentle air flow will be a plus.
2.2
EQUIPMENT LOCATION
The MD41-( ) must be mounted as close to the pilot’s field of view as possible. The preferable
location is near the HSI/CDI that will be displaying the GPS/VLOC information. The unit
depth, with connector attached, must also be taken into consideration. Note: Unlike previous
versions of the MD41 Annunciation Control Units (ACU), the transfer relays are not required
as all switching between GPS, VOR and ILS is handled by the GNS 430/530.This has allowed
a for a smaller size ACU which now provides more options for panel mounting.
2.3
ROUTING OF CABLES
Care must be taken not to bundle the MD41-( ) logic and low level signal lines with any high
energy sources. Examples of these sources include 400 HZ AC, Comm, DME, HF and
transponder transmitter coax. Always use shielded wire when shown on the installation print.
Avoid sharp bends in cabling and routing near aircraft control cables.
REV. A October 28, 2013
8
SECTION 3 INSTALLATION PROCEDURES
3.1
GENERAL INFORMATION
This section contains interconnect diagrams, mounting dimensions and other information
pertaining to the installation of the MD41-( ). After installation of cabling and before
installation of the equipment, ensure that power is applied only to the pins specified in the
interconnect diagram.
3.2
UNPACKING AND INSPECTING EQUIPMENT
When unpacking equipment, make a visual inspection for evidence of damage incurred during
shipment. The following parts should be included:
1.
2.
3.
3.3
MD41-1464A (14volt) or MD41-1468A (28 volt) Horiz. Mount
MD41-1474A (14volt) or MD41-1478A (28volt) Vert. Mount
MD41-1468A(5V) (28volt) 5 volt button lighting Horiz. Mount
MD41-1478A(5V) (28volt) 5 volt button lighting Vert. Mount
J1 Connector Kit (25 pin). MCI PN 7014517
Installation Manual. MCI PN 9010778
MOUNTING THE MD41-( )
Plan a location in the aircraft for the MD41-( ) to be mounted as close to the pilot’s field of
view as possible. The preferable location is near the HSI/CDI that will be displaying the GPS
information. Avoid mounting close to heater vents or other high heat sources. Allow a
clearance of at least 3 inches from back of unit for plug removal.
The indicator is secured in place behind the panel since it is designed for rear mount only.
Make a panel cutout as shown in Figure 3-2. Secure the indicator in place with two 4-40 x 3/8
flat head phillips screws.
3.4
INSTALLATION LIMITATIONS
Wire the aircraft harness according to figure 3-3. Use at least 24 AWG wire for all
connections. Avoid sharp bends and routing cable near high energy sources. Care must be
taken to tie the harness away from aircraft controls and cables. Normal installation techniques
should be applied. Also see equipment limitations, section 1.2.6.
REV. A October 28, 2013
9
REAR VIEW OF J1 CONNECTOR
J1
PIN NO.
1 ---------------------------2 ---------------------------3 ---------------------------4 ---------------------------5 ---------------------------6 ---------------------------7 ---------------------------8 ---------------------------9 ---------------------------10 -------------------------11 -------------------------12 -------------------------13 -------------------------14 -------------------------15 -------------------------16 -------------------------17 -------------------------18 -------------------------19 -------------------------20 -------------------------21 -------------------------22 -------------------------23 -------------------------24 -------------------------25 --------------------------
GPS ANNUNCIATION
VLOC ANNNCIATION
TERM ANNUNCIATION
CDI SOURCE SELECT (momentary logic low sent to receiver)
DIMMER IN (from aircraft dimming bus for push-button lighting)
SPARE
LAMP TEST (receives ground from remote test switch)(optional conn.)
WPT ANNUNCIATION
APR ANNUNCIATION
MSG ANNUNCIATION
SPARE
OBS MODE SELECT (momentary logic low sent to the receiver)
14 or 28 VDC UNIT POWER (depends on dash number)
SPARE
SPARE
SPARE
SPARE
SPARE
SPARE
INTG ANNUNCIATION
SPARE
SPARE
SPARE
OBS ANNUNCIATION
POWER GROUND
FIGURE 3-1 SCHEMATIC PINOUT, 25 PIN DSUB
REV. A October 28, 2013
10
Note 1: Use two 4-40 X 3/8” Flat Head Phillips Screws for Mounting
FIGURE 3-2 OUTLINE DRAWING
REV. A October 28, 2013
11
MD41-146XA/147XA SERIES ACU
J1
5
13
25
24
11
12
9
3
8
10
2
1
4
20
6
14
19
22
7
18
23
15
17
16
21
(for pushbutton lighting, see note 4)
TO LIGHTING BUS
5,14 or 28VDC
14 OR 28VDC AIRCRAFT PWR
POWER GND
TO MD41-ACU CIRCUIT BREAKER
2A
7
OBS ANN
SPARE
OBS MODE SELECT
APR ANN
TERM ANN
WPT ANN
MSG ANN
VLOC ANNUNCIATION
GPS ANNUNCIATION
CDI SOURCE SELECT
71
5
4
3
6
1
2
73
INTG ANNUNCIATION
9
SPARE
SPARE
SPARE
SPARE
LAMP TEST
SPARE
P4001
GNS 430
P5001
GNS 530
TEST
(note 3)
SPARE
SPARE
SPARE
SPARE
SPARE
NOTES:
1) REFER TO GARMIN GNS 430/530 INSTALLATION MANUAL FOR ACTUAL
INSTALLATION.
2) ALL WIRING SHALL BE 24 AWG UNLESS OTHERWISE NOTED.
3) MOMENTARY SWITCH FOR TEST. (optional connection)
4) 5 VOLT FOR MD41-1468A(5V)/1478A(5V), 14 VOLT FOR
MD41-1464A/1474A, AND 28 VOLT FOR MD41-1468A/1478A.
FIGURE 3-3 WIRING DIAGRAM, MD41-1468A/1478A/1468A(5V)/1478A(5V)
1464A/1474A
REV. A October 28, 2013
12
GARMIN GNS 430/530
SECTION 4 POST INSTALLATION CHECKOUT
4.1
PRE INSTALLATION TESTS
With the MD41-( ) disconnected, turn on the avionics master switch and verify that aircraft
power is on pin 13 for. Using an ohm meter, verify pin 25 is aircraft ground.
4.2
OPERATING INSTRUCTIONS
Turn off the avionics master switch and connect the mating connector to the MD41-( ). Turn
on the avionics master switch and the MD41-( ) should come on with the following
annunciations.
1.
2.
3.
VLOC or GPS
AUTO
MSG may be flashing depending on the status of the GPS receiver.
Press the lamp test button (if installed), all annunciations should light. Continue pressing the
lamp test button and cover the photocell window located in the center of the front panel. All
annunciations should dim.
Annunciation brightness at the minimum dimming level may be adjusted by rotation of the
dimmer control located on the bottom of the MD41-( ) case. CW rotation lowers the dimming
level.
Refer to section 5.2.7 of the Garmin GNS 430 or GNS 530 installation manual for testing of
external mode select switches and annunciations.
No periodic maintenance or calibration is necessary for continued airworthiness of the
MD41-( ).
REV. A October 28, 2013
13
ENVIRONMENTAL QUALIFICATION FORM
RTCA / DO160C
NOMENCLATURE: MD41-( ) GPS ANNUNCIATION CONTROL UNIT
MODEL NO: MD41-( )
TSO NO: C129
CLASS A1
MANUFACTURER TEST SPECIFICATION:
MANUFACTURER:
Conditions
Temperature and Altitude
Low Temperature
High Temperature
In-Flight Loss of Cooling
Altitude
Decompression
Overpressure
MPS 7015613
Mid-Continent Instruments and Avionics
9400 E. 34th Street N.
Wichita, KS 67226
Phone (316) 630-0101
Section
Description of Conducted Tests
4.0
Equipment tested to Categories A1 & F2 except as noted
4.5.1
4.5.2 & 4.5.3
4.5.4
Cooling air not required
4.6.1
4.6.2
4.6.3
Not Tested
Temperature Variation
5.0
Equipment tested to Category B
Humidity
6.0
Equipment tested to Category A
Shock
Operational
Crash Safety
7.0
7.2
7.3
Equipment tested per DO-160C
Par. 7.2.1
Vibration
8.0
Equipment tested without shockmounts to Categories M
and N
(Table 8-1)
Explosion
9.0
Equipment identified as Category X, no test required
Waterproofness
10.0
Equipment identified as Category X , no test required
Fluids Susceptibility
11.0
Equipment identified as Category X, no test required
REV. A October 28, 2013
14
Environmental Qualification (cont.)
Conditions
Section
Description of Conducted Tests
Sand and Dust
12.0
Equipment identified as Category X, no test required
Fungus
13.0
Equipment identified as Category X, no test required
Salt Spray
14.0
Equipment identified as Category X, no test required
Magnetic Effect
15.0
Equipment tested to Class Z
Power Input
16.0
Equipment tested to Category B
Voltage Spike
17.0
Equipment tested to Category A
Audio Frequency
Susceptibility
Induced Signal Susceptibility
18.0
Equipment tested to Category B
19.0
Equipment tested to Category A
Radio Frequency
Susceptibility
Radio Frequency Emissions
20.0
Equipment tested to Category T
21.0
Equipment tested to Category Z
Lightning Induced Transient
Susceptibility
22.0
Equipment identified as Category X, no tests required
Lightning Direct Effects
23.0
Equipment identified as Category X, no tests required
Icing
24.0
Equipment identified as Category X, no test required
REV. A October 28, 2013
15
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