Garmin | GNS 430W | Garmin GNS 430W 400W Series Instructions for Continued Airworthiness

Garmin GNS 430W 400W Series Instructions for Continued Airworthiness
400W Series
Instructions for Continued Airworthiness
Document Number 190-00356-65 Rev. D
Garmin International, Inc.
1200 E. 151st Street
Olathe, Kansas 66062 USA
Record of Revision
Rev.
Date
1
10-19-06
Initial Release
Description of Change
A
B
C
11-03-06
07-30-09
02-28-13
D
11-20-14
Revision for STC Issuance
Add the “-D” to STC number when reissued under ODA
Revise to support software version 5.02. Clarify inspections. Add
electrical bonding check.
Revise to support software version 5.20 with Flight Stream 210.
Table of Contents
1. INTRODUCTION................................................................................................................... 3
1.1 PURPOSE ............................................................................................................ 3
1.2 Scope .................................................................................................................... 3
1.3 Document Control ................................................................................................. 3
1.4 Airworthiness Limitations Section ......................................................................... 3
1.5 Permission to Use Certain Documents................................................................. 3
1.6 Definitions ............................................................................................................. 4
2. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS .................................................... 4
2.1 Introduction ........................................................................................................... 4
2.2 Description of Alteration........................................................................................ 5
2.3 Control, Operating Information ............................................................................. 5
2.4 Servicing Information ............................................................................................ 5
2.5 Periodic Maintenance Instructions........................................................................ 5
2.6 Troubleshooting Information ................................................................................. 7
2.7 Removal and Replacement Information ............................................................... 8
2.8 Diagrams .............................................................................................................. 11
2.9 Special Inspection Requirements ......................................................................... 11
2.10 Application of Protective Treatments .................................................................... 11
2.11 Data Relative to Structural Fasteners................................................................... 12
2.12 Special Tools ........................................................................................................ 12
2.13 Additional Instructions........................................................................................... 12
2.14 Overhaul Period .................................................................................................... 12
2.15 ICA Revision and Distribution ............................................................................... 12
2.16 Assistance ............................................................................................................ 12
2.17 Implementation and Record Keeping ................................................................... 12
400W Series
Instructions for Continued Airworthiness
P/N 190-00356-65 Rev. D
Page 2 of 12
1.6
Definitions
The following terminology is used within this document:
1)
2)
3)
4)
5)
6)
7)
8)
9)
10)
11)
12)
13)
14)
15)
16)
17)
AC: Advisory Circular
ACO: Aircraft Certification Office
AEG: Aircraft Evaluation Group
BIT: Built in Test
CFR: Code of Federal Regulations
DER: Designated Engineering Representative
FAA: Federal Aviation Administration
IAW: In Accordance With
ICA: Instructions for Continued Airworthiness
MFD: Multi-Function Display unit
ODA: Organization Designation Authorization
PED: Portable Electronic Device
PMI: Primary Manufacturing Inspector
POI: Primary Operations Inspector
STC: Supplemental Type Certificate
TC: Type Certification or Type Certificate
TSO: Technical Standard Order
2. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
2.1
Introduction
Content, Scope, Purpose and Arrangement:
This document identifies the Instructions for
Continued Airworthiness for the modification of the
aircraft by installation of the Garmin Models 400W
Series GPS/WAAS Nav/Com.
Applicability:
Applies to aircraft altered by installation of the
Garmin Model 400W Series GPS/WAAS Nav/Com.
Definition of Abbreviations:
See Section 1.6
Precautions:
None
Units of measurement:
None
Referenced publications:
190-00356-02 Rev. K 400W Series Installation
Manual or later revision
005-C0221-00 Rev. J 400W Series STC Master
Data List or later revision
Retention:
400W Series
Instructions for Continued Airworthiness
This document, or the information contained within,
will be included in the aircraft’s permanent records.
P/N 190-00356-65 Rev. D
Page 4 of 12
2.2
Description of Alteration
The Garmin Model 400W Series GPS/WAAS Nav/Com unit is a 6 ¼ inch wide panel mounted unit with
all the interface connections behind the instrument panel. Installation of the Garmin Model 400W Series
GPS/WAAS Nav/Com system interfaces, specific for the aircraft installation, is documented in the
GNS 400W Series Post-Installation Checkout Log that is retained as part of the aircraft’s permanent
records. The 400W Series units combine a large number of easily acceptable controls to use the color
multi-function display, Nav and Com transceiver, GPS/WAAS navigator in a single unit.
The Flight Stream 210 brings Bluetooth connectivity to the cockpit, allowing portable electronics to
stream data to and from the installed avionics.
The Flight Stream 210 interfaces to the GNS 400W via RS-232. The Flight Stream 210 may also
interface to the GDL 88 through RS-422 and the GDL 69 through RS-232. The Flight Stream unit is a
remote mount LRU that may be located in a variety of places around the aircraft. The suggested
locations are in the cabin/cockpit area, or in the forward or aft avionics bay. See Section 3.10 in the
400W Series Installation Manual, 190-00356-02 for suggested locations and mounting information.
2.3
Control, Operating Information
See the 400W Series Installation Manual, listed under the reference documentation in paragraph 2.1 of
this document, for system operation and self-test information.
2.4
Servicing Information
None. In the event of system failure, return the unit to the manufacturer or an approved Garmin repair
station.
2.5
Periodic Maintenance Instructions
The 400W Series units are designed to detect internal failure. A thorough self-test is executed
automatically upon application of power to the units, and built-in test is continuously executed. Detected
errors are indicated on the equipment via failure annunciations and maintenance is on-condition.
Operation of the 400W Series unit is not permitted unless an inspection as described in this section has
been completed within the preceding 12 calendar months. Conduct a visual inspection on the 400W
series unit, its wire harness, and the Flight Stream 210 (if installed) to insure installation integrity:
1. Inspect the 400W and Flight Stream units for security of attachment. If the Flight Stream 210 is
installed and screws are not securely attached, tighten any loose Flight Stream 210 mounting
screws as necessary to snug plus ¼ turn. If required, re-torque bonding strap hardware to 12-15
in-lbs.
CAUTION
Care should be taken when tightening the mounting screws of the
Flight Stream 210. Excessive tightening may damage the mounting flange.
2. Inspect for signs of corrosion.
3. Inspect all knobs and buttons for legibility.
4. Inspect condition of wiring, shield terminations, routing and attachment/clamping.
400W Series
Instructions for Continued Airworthiness
P/N 190-00356-65 Rev. D
Page 5 of 12
5. Inspect electrical bonding components. Perform bonding check, if due (see Section 2.5.4).
2.5.1 Cleaning the Front Panel
The front bezel, keypad, and display can be cleaned with a soft cotton cloth dampened with clean water.
DO NOT use any chemical-cleaning agents. Care should be taken to avoid scratching the surface of the
display.
2.5.2 Display Backlight
The display backlight lamp is rated by the manufacturer as having a usable life of 20,000 hours. This life
may be more or less than the rated time depending on the operating conditions of the 400W series unit.
Over time, the backlight lamp may dim and the display may not perform as well in direct sunlight
conditions. The user must determine by observation when the display brightness is not suitable for its
intended use. Contact the Garmin factory repair station when the backlight lamp requires service.
2.5.3 Battery Replacement
The 400W series has an internal keep-alive battery that will last about 10 years. The battery is used for
GPS system information. Regular planned replacement is not necessary. The 400W series will display a
‘low battery’ message when replacement is required. Once the low battery message is displayed, the
battery should be replaced within 1 to 2 months.
If the battery is not replaced and becomes totally discharged, the 400W series unit will remain fully
operational, but the GPS signal acquisition time may be increased. This acquisition time can be reduced
by entering a new seed position each time the unit is powered on. There is no loss of function or
accuracy of the 400W series unit with a dead battery.
The battery must be replaced by the Garmin factory repair station or factory authorized repair station.
2.5.4 Bonding Check (IFR-certified aircraft only)
Every 2000 flight hours or ten (10) years, whichever is first, perform an electrical bonding check on the
GNS 400W Series Unit and if installed, the Flight Stream 210. If a bonding check was not done during
the initial installation, it must be done to support electromagnetic interference and lightning compliance.
2.5.4.1 GNS 400W Series Unit in Metallic or Tube/Fabric Aircraft
Perform an electrical bonding check as follows:
1. Remove the 400W unit from the mounting rack.
2. Remove the backplate assembly from the rack.
3. Measure the resistance between the mounting rack and nearby exposed portion of aircraft
metallic structure and verify it is less than 10 milliohms.
In the event of bonding test failure, remove the 400W rack and clean the attachment points with
a bonding brush at both the 400W rack and the aircraft and reattach the rack to the rails in the
panel. Verify the resistance between the mounting rack and nearby exposed portion of aircraft
metallic structure is less than 2.5 milliohms.
4. Reinstall the backplate assembly and reinstall the 400W in the mounting rack.
400W Series
Instructions for Continued Airworthiness
P/N 190-00356-65 Rev. D
Page 6 of 12
2.5.4.2 GNS 400W Series Unit in Composite Aircraft
Perform an electrical bonding check as follows:
1. Remove the 400W unit from the mounting rack.
2. Remove the backplate assembly from the rack.
3. Measure the resistance between the mounting rack and the instrument panel, verify it is less
than 10 milliohms.
In the event of bonding test failure, remove the 400W rack and clean the attachment points with
a bonding brush at both the 400W rack and the aircraft and reattach the rack to the rails in the
panel. Verify the resistance between the mounting rack and the instrument panel is less than 5
milliohms.
4. Reinstall the backplate assembly and reinstall the 400W in the mounting rack.
2.5.4.3 Flight Stream 210 in Metallic or Tube/Fabric Aircraft
1. Disconnect the shield terminations from the Flight Stream 210 connector backshell.
2. Measure the resistance between the connector and nearby exposed portion of aircraft metallic
structure and verify that it is less than or equal to 20 milliohms.
In the event of bonding test failure, remove the Flight Stream 210 connector bonding strap from
the aircraft ground plane and clean the attachment point with a bonding brush. Re-attach the
bonding strap to the aircraft ground plane, torque to 12-15 in-lbs. Verify the resistance between
the Flight Stream 210 connector and aircraft structure is less than or equal to 10 milliohms. If
cleaning the far side of the strap is not enough, remove, clean, and re-attach the
Flight Stream 210 side.
3. Connect the shield terminations to the Flight Stream 210 connector backshell.
2.5.4.4 Flight Stream 210 in Composite Aircraft
1. Disconnect the shield terminations from the Flight Stream 210 connector backshell.
2. Measure the resistance between the connector and instrument panel (or other aircraft ground)
and verify that it is less than or equal to 20 milliohms.
In the event of a bonding test failure, remove the Flight Stream 210 connector bonding strap
from the aircraft ground plane and clean the attachment point with a bonding brush. Re-attach
the bonding strap to the aircraft ground plane, torque to 12-15 in-lbs. Verify the resistance
between the Flight Stream 210 connector and aircraft ground is less than or equal to 10
milliohms. If cleaning the far side of the strap is not enough, remove, clean, and re-attach on the
Flight Stream 210 side.
3. Connect the shield terminations to the Flight Stream 210 connector backshell.
2.6
Troubleshooting Information
If error indications are displayed on the 400W series unit, consult the Troubleshooting section contained
in the 400W Series Installation Manual, listed under reference documentation in paragraph 2.1 of this
document. The same troubleshooting section also contains troubleshooting information for the
Flight Stream 210. The 400W Series Post-Installation Checkout Log’ in the aircraft permanent records
includes the configuration information for the installation. (See Section 5 in the 400W Series Installation
Manual for a sample Log).
400W Series
Instructions for Continued Airworthiness
P/N 190-00356-65 Rev. D
Page 7 of 12
2.7
2.7.1
Removal and Replacement Information
GNS 400W
If the 400W series unit is removed and reinstalled, verify that the 400W series unit power-up self-test
sequence is successfully completed and no failure messages are annunciated.
If the 400W series unit is removed for repair and reinstalled, or if the 400W unit is removed and replaced
with a different 400W series unit, then follow ‘Post Installation Configuration & Checkout Procedures’
contained in the 400W Series Installation Manual listed in Section 2.1 of this document, and verify the
400W unit power-up self-test sequence is successfully completed and no failure messages are
annunciated.
If any work has been done on the aircraft that could affect the system wiring, antenna cable, or any
interconnected equipment, verify the 400W series unit power-up self-test sequence is successfully
completed and no failure messages are annunciated.
To remove the 400W series unit from the mounting rack, insert a 3/32-inch hex drive tool into the access
hole at the bottom of the unit face. Rotate the hex tool counterclockwise until the unit is forced out about
3/8 inches and can be freely pulled from the rack.
The 400W unit is installed in the rack by sliding it straight in until it stops, about 1 inch short of the final
position. Insert the hex drive tool into the access hole at the bottom of the unit face. Rotate the hex tool
clockwise while pressing on the left side of the bezel until the unit is firmly seated in the rack.
Note: There are no special handling requirements for the 400W series units.
400W Series
Instructions for Continued Airworthiness
P/N 190-00356-65 Rev. D
Page 8 of 12
2.7.2 Flight Stream 210 (If Installed)
See Figure 1 when performing the following steps:
Removal
1. Locate and open the BT Link circuit breaker.
2. Unscrew the two jackscrews on the Flight Stream 210 connector. Remove connector.
3. Remove the four #6 mounting screws to remove the Flight Stream 210.
Reinstallation
1. Check that the BT Link circuit breaker is open.
2. Reinstall the Flight Stream 210 using the four previously removed #6 mounting screws.
3. Tighten fasteners until snug, plus an additional 1/4 turn.
Note: Ensure that the Flight Stream 210 is mounted with the arrow pointing in the direction of flight.
4. Attach the connector, tightening the two jackscrews.
5. Close the B/T Link circuit breaker.
6. Complete the interface checkout procedures contained in Section 5.5.7 of the 400W Series
Installation Manual.
Figure 1. Flight Stream 210 Assembly Overview (Bonding Strap Not Shown)
400W Series
Instructions for Continued Airworthiness
P/N 190-00356-65 Rev. D
Page 9 of 12
2.7.3 Flight Stream 210 Bonding Strap
The following removal and replacement steps are provided as guidance for replacing the
Flight Stream 210 bonding strap. The bonding strap assembly drawing is shown in Figure 2.
Note: Aircraft structure side of bonding strap may be mounted using a nut in lieu of a nut plate. If a nut
was used in lieu of a nut plate, further disassembly of the aircraft may be required to gain access to the
nut.
Removal
1. Disconnect one end of the bonding strap from the aircraft ground location.
2. Disconnect the other end of the bonding strap from the shield block on the Flight Stream 210
connector backshell.
3. Remove the bonding strap.
Replacement
Note: The Flight Stream 210 bonding strap should be as short as practical. When installed, the bonding
strap must not loop back on itself.
1. Construct a bonding strap no longer than 20” by attaching clean terminal lugs to both ends of
clean braid (See Table 1 for parts required).
2. Clean the attachment locations with a bonding brush.
3. Secure each end of the bonding strap to the previously installed locations. Ensure that the strap
does not loop back on itself and that the hardware is as shown in Figure 2. The washers must
seat fully against the aircraft metallic structure without overhang or interference with other
hardware.
4. Using a milliohm meter, verify that the resistance between the connected structure is less than
10 milliohms.
In the event of a bonding test failure, remove the bonding strap from the aircraft ground point
and clean the attachment points with a bonding brush. Re-install the bonding strap and perform
the electrical bonding test in accordance with Section 2.5.4.
5. Replace any damaged hardware, otherwise hardware may be reused.
400W Series
Instructions for Continued Airworthiness
P/N 190-00356-65 Rev. D
Page 10 of 12
Figure 2. Flight Stream 210 Bonding
Table 1. Flight Stream 210 Bonding Hardware
See Figure 2
1
2
3
4
5
6
2.8
Hardware
Screw
Lock Washer
Flat Washer
#8 Ring Terminal
Screw
Braid
P/N
MS35206 (AN515) #8 Pan Head Screw
MS35338-42 #8 Lock Washer
NAS1149FN832P (AN960-8) #8 Washer
MS25036 #8 Ring Terminal
MS51957-42 #6 Screw
QQB575R36T0250 or larger
Diagrams
Refer to the 400W Series Installation Manual (listed under reference documentation in section 2.1 of this
document) for drawings applicable to this installation. Point to point wiring diagrams are in Appendix H of
the 400W Series Installation Manual. Refer to the GNS 400W Series Post-Installation Checkout Log
retained in the aircraft permanent records for a list of the interfaced equipment. The antenna cables are
routed between the 400W series unit and the antenna with disconnects at each unit. The antenna cable
typically is routed behind interior panels in the fuselage.
2.9
Special Inspection Requirements
None, N/A.
2.10 Application of Protective Treatments
None, N/A.
400W Series
Instructions for Continued Airworthiness
P/N 190-00356-65 Rev. D
Page 11 of 12
2.11 Data Relative to Structural Fasteners
None, N/A.
2.12 Special Tools
A milliohm meter with an accuracy of +/- 0.1 milliohms ohms (or better) is required to measure the
electrical bonding between the 400W system components and aircraft ground.
No special tools are required for system checkout. See 400W Series Installation Manual listed in
reference documentation in section 2.1 of this document.
2.13 Additional Instructions
None.
2.14 Overhaul Period
The system does not require overhaul at a specific time period. Power on self-test and continuous BIT
will monitor the health of the 400W series unit. If the unit indicates an internal failure, the unit may be
removed and replaced. See troubleshooting section contained in the 400W Series Installation Manual,
listed under reference documentation in paragraph 2.1 of this document.
2.15 ICA Revision and Distribution
To revise this ICA, Garmin will follow the Garmin ODA Procedures Manual SOP-0055/ACP-0016 for
Instructions for Continued Airworthiness. The latest revision of this ICA document is available on the
Garmin website (www.garmin.com). A Garmin Service Bulletin describing ICA revision will be sent to
Garmin dealers if a revision is determined to be significant.
2.16 Assistance
Flight Standards Inspectors or the certificate holder’s PMI have the required resources to respond to
questions regarding this ICA. In addition, the customer may refer questions regarding this equipment
and its installation to the manufacturer, Garmin. Garmin customer assistance may be contacted during
normal business hours via telephone 913-397-8200 or email from the Garmin web site at
www.garmin.com.
2.17 Implementation and Record Keeping
Modification of an aircraft by this Supplemental Type Certificate obligates the aircraft operator to include
the maintenance information provided by this document in the operator’s aircraft maintenance manual
and/or the operator’s aircraft scheduled maintenance program.
400W Series
Instructions for Continued Airworthiness
P/N 190-00356-65 Rev. D
Page 12 of 12
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