Instructions for Continued Airworthiness for G500H in Robinson R44 Series Rotorcraft Reg. No.____________ S/N_______________ STC TBD Dwg. Number: 190-01190-11 Rev. 1 Garmin International, Inc. 1200 E. 151st Street Olathe, Kansas 66062 USA Record of Revision Rev.
1. INTRODUCTION ........................................................................................................................ 3 1.1 Purpose...................................................................................................................... 3 1.2 Scope ......................................................................................................................... 3 1.3 Document Control ......................................................................................
1. INTRODUCTION 1.1 Purpose This document is designed for use by the installing agency of the Garmin G500H PFD/MFD System as Instructions for Continued Airworthiness in response to Title 14 CFR Part 27.1529 and Part 27 Appendix A. This ICA includes information required by the operator to adequately maintain the Garmin G500H system installed under STC TBD. 1.
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 rotorcraft by installation of the Garmin G500H PFD/MFD System. Applicability: Applies to Robinson R44 series rotorcraft altered by installation of the Garmin G500H PFD/MFD System. Definition of Abbreviations: See Section 1.
Garmin 005-W0227-07 Rev. 1 “G500H ROBINSON R44 SERIAL ALTITUDE HARNESS ASSY DWG (OPTL)” or later revision Garmin 005-W0227-08 Rev. 1 “G500H ROBINSON R44 TRAFFIC HARNESS ASSY DWG (OPTL)” or later revision Garmin 005-W0227-09 Rev. 1 “G500H ROBINSON R44 GLARESHIELD HARNESS ASSY (REQD)” or later revision Garmin 190-01190-00, Rev 2, “G500H ROBINSON R44 INSTALLATION DRAWING” or later revision Retention: 2.
The installed G500H equipment can be accessed as described below: 1. 2. 3. 4. 5. GDU 620: FS 30.00, WL 42.5 Access or remove by removing the six screws in the bezel of the GDU 620. GRS 77H: FS 19.25, WL 30.0 Access or remove by tilting the instrument shroud to its open position by removing four glareshield retaining screws. GMU 44: FS 41.5, WL19.75 Access or remove by lifting the pilots seat bottom. GDC 74H: FS 39.25, WL 15.75 Access or remove by lifting the co-pilots seat bottom.
[1] A rotorcraft weight and balance is required after installation of the G500H system. Refer to installation manual P/N 190-01190-06 for additional information, including overall size and center of gravity location of all LRUs. [2] The longitudinal arm is measured in terms of the fuselage station (FS) number. [3] The lateral arm is measured in terms of the butt line (BL). The centerline of the helicopter is BL 0.00.
Item Interval Description/Procedure Coincident with upper console 100 hour inspection per Robinson Model R44 Maintenance Manual, Change 13 October 2006, or later ,page 2.16, perform - Garmin Glareshield Assembly 1. Visual inspection of composite glare shield assembly, Garmin PN 011-02759-00 (28VDC electrical system), or 011-02759-01 (14VDC electrical system) for damage. Inspect for loose rivets indicated by cracks in composite or aluminum components, or paint.
Item Interval Description/Procedure Perform an electrical bonding test for each listed LRU: GDU 620, GRS 77H, GDC 74H, GMU 44, GTP 59 1. Gain access to the LRU (see General Arrangement Drawing for LRU location) 2. Disconnect all harness connectors from the LRU 3. Measure the resistance between the LRU and a nearby exposed portion of aircraft metallic structure. If any resistances are greater than the values below refer to section 3.
Problem Cause Solution Vertical GPS deviation is not displayed on the GDU 620. For 400W/500W Series units, the ARINC 429 vertical deviation labels are not being transmitted. The GPS navigator is not correctly configures as LNAV1/2 or SYS1/2. Enable Labels on the 400W/500W Series unit ARINC 429 configuration page. Unable to control the GPS course when in OBS mode. Data is not being received from an ARINC 429 device.
2.6.2 G500H Alerts The G500H will display a number of alerts on the GDU 620 MFD. These are listed in the following table. Table 2-2. GDU 620 Alert Troubleshooting Guide Alert Text SERVICE Cause Specific LRU should be serviced, where denotes specific LRU. AHRS1 GPS – AHRS 1 using AHRS is using the backup GPS backup GPS source. information AHRS1 GPS - AHRS is not AHRS is not receiving any GPS receiving any GPS information information.
Alert Text DSCRT CONFIG – Discrete output configuration error. Cause A discrete output required by an interfaced system has not been configured. Solution Use the DISCRETE CONFIGURATION page in the SYS page group to configure the discrete outputs to match the installation.
Alert Text GDU (1/2) VOLTAGE Cause GDU supply voltage is below 12 VDC. Solution Increase the voltage above 12VDC. This alert is normal in 14V aircraft that are running on the battery only and should clear once the aircraft engine is started and the alternator/generator is carrying the load. GEO LIMITS GPS(1/2) GPS(1/2) PPS Failure GSR FAIL HDG FAULT Location is too far north/south for GRS 77H magnetic compass. Communication with GPS1 or GPS2 Ensure GPS (1/2) is turned on lost.
Alert Text SW MISMATCH TERRAIN DSP TRAFFIC FAIL TRAFFIC STDBY TRK LOST 2.7 Cause GDU software version strings do not match. Terrain, Airport Terrain, or Obstacle database error. The traffic information system has failed. Solution Verify the correct SW is loaded Update/Reload database The GDU 620 is not receiving traffic information from the traffic sensor. Verify wiring between GDU 620 and traffic sensor.
NOTE The installation configuration settings are stored in the configuration module and will be retained when the GDU 620 is replaced with a new unit. User settings, such as map orientation preferences, are stored internally and will be lost when the GDU 620 is replaced with a new unit. Original GDU 620 is Reinstalled If the original GDU 620 is reinstalled, then no software loading is required.
2. Loosen the four Phillips thumbscrews with a screwdriver. 3. Gently lift the GRS 77H from the mounting plate (if the supports for the mounting plate are removed, the GRS 77H must be recalibrated) 2.7.2.2 Installation 1. Place the GRS 77H on the mounting plate, ensuring the orientation is correct. 2. Fasten the unit to the plate using the Phillips thumbscrews. Recommended torque is 22-25 inch pounds. 3. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair any damage. 4.
Table 2-3. GRS 77H Calibration Criteria Condition Calibrations Required GRS 77H GRS/GMU Pitch/Roll Magnetic Offset Calibration See Section 5 See Section 5 of the G500H STC of the G500H STC Installation Manual Installation Manual GRS 77H AHRS was removed and/or replaced. The mounting tray was NOT removed and the mounting tray bolts were NOT loosened. None Required. GRS 77H AHRS was removed and/or replaced. The mounting tray WAS removed and/or mounting tray bolts WERE loosened.
Return to Service After removing and reinstalling the GMU 44, the following return-to-service checks should be performed. 1. Power up the G500H system with the GDU 620 in normal mode. 2. Verify that the GDU displays valid heading within approximately one minute. Note that heading can remain invalid if the magnetometer is near a large metal structure such as a hangar wall or if the magnetometer is close to a large ground power cart. 3. Verify that no unexpected alerts are present.
2.8 Diagrams Rotorcraft specific LRU locations and wire routing diagrams are contained in the Garmin Reference Publications listed in Section 2.1 of this document. Point to point wiring diagrams are in Appendix D of the G500H STC Installation Manual. Refer to the G500H Post-Installation Checkout Log retained in the rotorcraft permanent records for a list of the interfaced equipment and port configurations. 2.9 Special Inspection Requirements 2.9.
2.12 Special Tools For electrical bonding testing, a milliohm meter is required. 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 G500H system. If any LRU indicates an internal failure, the unit may be removed and replaced. See the troubleshooting section contained in the G500H STC Installation Manual, listed under reference documentation in paragraph 2.
