SERVICE INFORMATION LETTER

Transcription

1 SERVICE INFORMATION LETTER Document Number: 0001 Release Date: January 24, 2003 Revision: A PRODUCTS AFFECTED Corporation Aircraft Data Acquisition System (ADAS) and Corporation Aircraft Data Acquisition System Plus Upgrade (ADAS+ Upgrade) SUBJECT This describes the multi-day installation of the ADAS/ADAS+ Upgrade monitoring systems. The ADAS/ADAS+ Upgrade is approved by Supplemental Type Certificate # SA00095BO in accordance with the Corporation Installation Manual, Doc. No. TWIN-I Revision J, dated November 8, 2002, or later FAA approved revisions AIRCRAFT OR ENGINE(S) AFFECTED For Raytheon (Beech) Aircraft Series 1900, 1900C, 1900D, 200, 200T, 200C, 200CT, A200, A200C, A200CT, B200, B200C, B200CT, 300, 300LW, B300, B300C IMPLEMENTATION AND COMPLIANCE Implementation date: N/A Compliance: N/A SUMMARY DESCRIPTION The Aircraft Data Acquisition System has been approved for installation following a phased approach. This method will allow the operator to install the system in standard 8-hour maintenance shifts using two people. After each phase (installation shift) the installed hardware can be secured and the aircraft approved to fly in its standard operating environment. The purpose of the multi-day installation method is to allow operators to maintain flight capability of their aircraft while installing the ADAS. The maximum time to complete the multi-day installation should not exceed 90 days. The FAA Boston ACO finds the phased approach incorporated in this to be acceptable and consistent with the approved installation instructions established for the complete installation. It is an installation technique and does not change the system function. The installer should coordinate the phase installation with the local Principal Maintenance Inspector (PMI), or otherwise as required. Page 1 of 5

2 IMPLEMENTATION INSTRUCTIONS There are two separate Installation Schedules. One is for installations that do not require torque transducers and the other is for those installations that do require the torque transducers. Please ensure that you follow the appropriate schedule for your aircraft. At the completion of each phase of the multi-day installation a standard aircraft logbook entry should be completed stating the phase completed with reference to the STC and installation manual. Weight and Balance for the aircraft should be modified after the installation of all hardware. Compatibility of this design with previously approved modifications must be determined by the installer. 1 Installation Schedule Not Requiring Torque Transducers 1.1 Phase One In phase one of the multi-day installation the installer will mount the system processor, pitot and static transducers with plumbing, OAT probe, and the vertical accelerometer. Weight and Balance should be modified based on the installed components. A pitot/static leak check must be done before returning the aircraft to service. Using the TWIN-K-010 ADAS/ADAS+ Upgrade Installation Manual Revision J, Manual # TWIN-I-010-1, perform the following steps: Mounting The System Processor Outside Air Temperature Probe Pitot & Static Pressure Transducers Vertical Accelerometer NOTE: A Pitot/Static Leak Check must be done before returning the aircraft to service 1.2 Phase Two In phase two of the multi-day installation the installer will mount the cockpit download port and trend switches. The wiring harness should also be installed at this time and routed to the appropriate sensors. Weight and Balance should be modified based on the installed components and electrical harnesses Pressure Bulkhead Fitting Trend Switches and Download Port J1 Harness (Power / Sensor) J2 Harness (Engine 1) J3 Harness (Engine 2) Comm Harness (Trend Switches / Download Port) NOTE: All unconnected sensor wires and spare wires will be properly terminated and secured 4.5 Final Assembly (Pot and Seal Pressure Bulkhead Fitting) 1.3 Phase Three In phase three of the multi-day installation final wiring is completed to all sensors and electrical power. Once all wiring is complete a ground run should be accomplished to verify that the system does not interfere with any aircraft electrical component. Aircraft ground test is referenced in Section 4.1 of the TWIN-K-010 ADAS/ADAS+ Upgrade Installation Page 2 of 5

3 2.5.5 Engine 1 & 2 Pre-Existing Torque Sensor Engine N1 Speed Signals Engine N2 Speed Signals Voltage to Frequency Converter (if needed) Engine Fuel Flow Signals Engine ITT Signals Engine Bleed Signals Ice Vane Signals Flap Position Signals Weight On Wheels Signal Gear Extended Signals Pitot And Static Sensors Outside Air Temperature Sensor Power and Ground Connections NOTE: All spare wires will be properly terminated and secured NOTE: Disable the ADAS/ADAS+ Upgrade processor by pulling the 1 Amp circuit breakers. 1.4 Phase Four In phase four of the multi-day installation final calibration and aircraft check out will be performed. Once the system has been calibrated and the aircraft flown, all paperwork can be completed. At this stage the multi-day installation is complete. 2.7 Initial Processor Test 3 System Configuration and Calibration 4.2 Aircraft Flight Test 4.4 Test Data Download And Review 4.6 Documentation 2 Installation Schedule Requiring Torque Transducers 2.1 Phase One In phase one of the multi-day installation the installer will mount the system processor, pitot and static transducers with plumbing, OAT probe, and the vertical accelerometer. Weight and Balance should be modified based on the installed components. A pitot/static leak check must be done before returning the aircraft to service. Using the TWIN-K-010 ADAS/ADAS+ Upgrade Installation Manual Revision J, Manual # TWIN-I-010-1, perform the following steps: Mounting the System Processor Outside Air Temperature Probe Pitot & Static Pressure Transducers Vertical Accelerometer NOTE: A Pitot/Static Leak Check must be done before returning the aircraft to service Page 3 of 5

4 2.2 Phase Two In phase two of the multi-day installation the installer will mount the cockpit download port and trend switches. The wiring harness should also be installed at this time and routed to the appropriate sensors. Final wiring of the wing root torque wires and vertical accelerometer should also be installed so the aircraft interior can be closed. Weight and Balance should be modified based on the installed components and electrical harnesses Pressure Bulkhead Fitting Trend Switches and Download Port J1 Harness (Power / Sensor) J2 Harness (Engine 1) J3 Harness (Engine 2) Comm Harness (Trend Switches / Download Port) NOTE: All unconnected sensor wires and spare wires will be properly terminated and secured. Ensure that torque wires are connected at inboard wing root and are identified on the outboard side 4.5 Final Assembly (Pot and Seal Pressure Bulkhead Fitting) 2.3 Phase Three In phase three of the multi-day installation the torque transmitters should be installed and wired into the aircraft pressure vessel. A ground run should be accomplished to perform a standard leak check after the Altair supplied torque transducers are installed. Aircraft leak check is referenced in Section 4.1 of the TWIN-K-010 ADAS/ADAS+ Upgrade Installation Engine 1 & 2 Altair-Supplied Torque Sensor NOTE: Ensure that torque wires are connected at outboard wing root 4.1 Aircraft Ground Test (Leak Check Only) 2.4 Phase Four In phase four of the multi-day installation final wiring is completed to all sensors and electrical power. Once all wiring is complete a ground run should be accomplished to verify that the system does not interfere with any aircraft electrical component. Aircraft ground test is referenced in Section 4.1 of the TWIN-K-010 ADAS/ADAS+ Upgrade Installation Engine N1 Speed Signals Engine N2 Speed Signals Voltage to Frequency Converter (if required) Engine Fuel Flow Signals Engine ITT Signals Engine Bleed Signals Ice Vane Signals Flap Position Signals Weight On Wheels Signal Gear Extended Signals Pitot And Static Sensors Outside Air Temperature Sensor Power and Ground Connections NOTE: All spare wires will be properly terminated and secured Page 4 of 5

5 NOTE: Disable the ADAS/ADAS+ Upgrade processor by pulling the 1 Amp circuit breakers. 2.5 Phase Five In phase five of the multi-day installation final calibration and aircraft check out will be performed. Once the system has been calibrated and the aircraft flown, all paperwork can be completed. At this stage the multi-day installation is complete. 2.7 Initial Processor Test 3 System Configuration and Calibration 4.2 Aircraft Flight Test 4.4 Test Data Download and Review 4.6 Documentation COMPLIANCE It is the installer s responsibility to ensure compatibility of the STC on the aircraft when using this installation process. REFERENCES TWIN-K-010 ADAS/ADAS+ Upgrade Installation Manual Revision J, Manual # TWIN-I CONTACT INFORMATION Corporation Help Desk 63 Nahatan Street, Suite 300 Norwood, MA Tel. (781) , ext. 113 Fax (781) support@altairavionics.aero Page 5 of 5