COMPLIANCE RECORD. Document Reference: S21.COMP-0811 Issue 2. Introduction. Description

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Myles Barnett
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3 Introduction This design change will install and activate the Spectralux Dlink + ACARS Display Unit (DU) into the wiring provisions installed under STC Twenty One Change S , at the Operators request. The certification basis for this design change is detailed in Certification Programme S21.PROG-0811, and compliance with the certification requirements is detailed in Compliance Checklist S21.CCL-0811 Description Installation The Dlink + DU (Display Unit) has been installed in the P8 Electronics Panel, an annunciator has been installed in the Pilots P1-3 Instrument Panel and a Data Loader Ethernet connector installed on the rear face of the P8 Aft pedestal. Wiring provisions which were installed under S have been connected at various locations with in the EE Bay, the P18-2 panel and at the third VHF COMM Antenna. The 28 VDC power for the system is derived from the Boeing build provisions for the third VHF transceiver. Mechanical The Dlink + DU (Display Unit) has been installed on to the Dzus rails in the centre of the P8 Electrical Panel, an annunciator (ATC/ACARS) has been installed on the P1-3 instrument panel and an RJ field connector installed at the rear of the P8 Aft pedestal. Electrical Avionic Wiring has been added to the P1-3 instrument panel to connect the ATC/ACARS annunciator to the Master Dim and Test circuits and the Dlink + DU (Display Unit). The wiring to the E1-2, E2-1, E2-2 and E2-4 shelves installed previously as provisions under S has been connected and where necessary, existing wires capped and stowed. The antenna feeder has been terminated at both ends and connected to the No 3 VHF COMM Antenna, and to the Dlink + DU (Display Unit). The 28VDC connection has been made at the P18-2 disconnect panel, the existing 10 Amp circuit breaker labelled VHF COMM 3 is re-used and re-labelled ACARS. All wire splicing and terminations have been carried out in accordance with Boeing Standard Wiring Manual ATA Chapter 20. The wire used in this design change meets with Specification M22759/34 for single core wires, M27500 for screened cables and MIL-C-17 for coaxial cable and is approved for installation in the Boeing B737 aircraft. Ethernet cable meets with ARINC 664P2-2 and SAE AS New wiring is routed as per the instructions on the wiring diagram applicable to the aircraft msn and follows existing raceways segregated from existing wire harnesses carrying high power or fuel system wiring. Where not practical to do this, harnesses have been supported using p-clips and spacers as per Boeing Standard Practices; refer to drawing EASA Approval EASA.21J.198 Form Number: S REP.006 The copyrights of this document are reserved by. It is issued on the condition that it is not Form Issue: 10 copied, reproduced or disclosed either wholly or in part, without the consent, in writing, of Date: 31 October 2007 Page 3 of 5

4 Substantiation Reports A safety analysis of the installation of the Dlink+ is detailed in Technical Report S21.TREP No structural substantiation has been performed; the equipment installations have been passed by inspection. The introduction of the Dlink+ DU, together with the wiring has a negligible effect on aircraft basic weight and centre of gravity. The Dlink+ DU weighs 6 lbs and is located at approximately STA 190. A coax cable weighing 4lb is uniformly distributed between the flight deck and the No 3 VHF COMM antenna. The remainder of the wiring installation, approximately 12lb, is uniformly distributed between the flight deck and the EE bay. The Electrical Load will be increased by maximum of 5.5 Amps (transmit) and normal 1.0 Amp. This is less than the load provisioned for the third VHF COMM and is within the load capability of the supply circuits. No separate Electrical Load Analysis has been performed for this change. Master Document List All approved data associated with design change S is contained in Master Document List S21.MDL Testing Requirements A post installation ground test has been carried out in accordance with Ground Test S21.TR or S21.TR-0203, dependent on configuration (refer to S21.MDL-0811), and an EMI Test performed in accordance with EMI Test S21.EMI Equipment Approval The Spectralux Dlink + Display Unit (DU) has been accepted under STC Twenty One Limited equipment approval procurers S21.EAF-0315 refers. Environmental Protection There is no effect on compliance with existing Noise & Emissions Certification requirements as a result of embodying this change. Limitations None EASA Approval EASA.21J.198 Form Number: S REP.006 The copyrights of this document are reserved by. It is issued on the condition that it is not Form Issue: 10 copied, reproduced or disclosed either wholly or in part, without the consent, in writing, of Date: 31 October 2007 Page 4 of 5

5 Manuals Enter N/A for documents not generated as part of this design change/repair. Document Type (See note below) Aeroplane Flight Manual Supplement Master Minimum Equipment List Supplement Document Reference N/A N/A Mass & Balance Report See page 4 Electrical Load Analysis Report See page 4 Maintenance Programme (Instructions for Continued Airworthiness) Maintenance Manual Wiring/Schematic Manual Illustrated Parts Catalogue S21.TEC-0274 IMPORTANT NOTE: It is the responsibility of the operator to ensure that documents specified above are incorporated in or appended to the applicable manual relevant to the aircraft being modified IAW this design change/repair. Approval The technical content of this document is approved under the authority of DOA nr. EASA.21J.198. EASA Approval EASA.21J.198 Form Number: S REP.006 The copyrights of this document are reserved by. It is issued on the condition that it is not Form Issue: 10 copied, reproduced or disclosed either wholly or in part, without the consent, in writing, of Date: 31 October 2007 Page 5 of 5

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