INSTRUCTIONS FOR CONTINUED AIRWORTHINESS EASA / FAA EASA PROJECT:

Transcription

1 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS EASA / FAA EASA PROJECT: [applicability for AS350 models B BA B1 B2] 1030 Avenue JR Guillibert Gauthier de la Lauzière AIX EN PROVENCE FRANCE Tel: (0) Fax: (0) Mail: contact@isei.info This document must be attached to the Aircraft Instructions for Continued Airworthiness (Maintenance Manuals). The information contained herein supplements the basic instructions for Continued Airworthiness only in those areas listed, when the aircraft is modified in accordance with EASA STC No including the FAA validation of this STC. For limitations and procedures not contained in this document, consult the basic Aircraft Instruction for Continued Airworthiness (Maintenance Manuals). The inspections specified in this document are EASA accepted. If applicable, the identified airworthiness limitations in Chapter 4 are EASA approved. The Airworthiness Limitations Section is FAA approved and specifies maintenance required under Secs and of the Federal Aviation Regulations unless an alternative program has been FAA approved. Revision 12 page 1

2 SECTION 1: GENERAL RECORD OF REVISIONS No. REVISION INSERTED DATE INSERTED BY 00 Initial release 03/07/2014 T.ATTLAN (Original) 01 Change of the index for the technical documentation 01/09/2014 JC.MARCELLET 02 Change of the index for the technical documentation 23/09/2014 JC.MARCELLET 03 Adding the system HELICOM V2+ ANA 24/11/2014 JC.MARCELLET 04 Adding the statement of compliance with the CP 09/12/2014 JC.MARCELLET 05 Update - index of associated technical documentation 16/12/2014 JC.MARCELLET 06 Update of the associated technical documentation (.3.1) 14/01/2015 JC.MARCELLET 07 Update of the associated technical documentation (.3.1) 21/01/2015 JC.MARCELLET 08 Update of the associated technical documentation (.3.1) 22/01/2015 JC.MARCELLET 09 Adding clarifications requested by FAA manager concerning Airworthiness limitations section, weight and balance section 29/04/2015 JC.MARCELLET 10 Clarifications provided about the lipo battery 21/09/2015 JC.MARCELLET 11 Clarifications provided in the frontpage 15/10/2015 JC.MARCELLET 12 Adding new location for the main device 20/10/2015 JC.MARCELLET Revision 12 page 2

3 LIST OF AFFECTED PAGES PAGE DATE REVISION Cover 20 th October th October th October th October th October th October th October th October th October th October th October th October th October th October th October th October th October th October th October th October th October th October th October th October th October th October th October th October th October th October th October Revision 12 page 3

4 PAGE DATE REVISION th October th October th October th October Revision 12 page 4

5 MONITORING OF DOCUMENT This document is followed by Assurance Quality Service of ISEI. Thank you kindly upon receipt, return to ISEI, by fax or by mail to the attention of service quality, the current page, after having completed /updated informations missing/incorrect. The contact person identified will be in charge of destroying the old version and associated internal diffusions (if any) and to follow the internal diffusions of the new version. File identification: Change Installation of HELICOM V2 ANA system or HELICOM V2+ ANA system TC number TCDS EASA R.008 TCDS FAA H9EU Aircraft AS350 Models B, BA, BB, B1, B2 Note: BB model is not approved by FAA File title Instructions for Continued Airworthiness Project EASA Project No File identification N8-AS350 B BA BB B1 B2-HV2-E-C-05 Issue number EASA approval number Rev.03 Recipient company Identification: Company Address 1 Address 2 Postal code Town Country Phone Fax E mail Contact and support date: Name First name Support date Signature of the contact Revision 12 page 5

6 Identification Title Page SECTION 1: GENERAL RECORD OF REVISION 2 LIST OF AFFECTED PAGES 3 MONITORING OF DOCUMENT 5 SECTION 2: INTRODUCTION Purpose of the document Applicable documents Scope Permission to use certain documents Certification basis Statement of Compliance 8 2.7Definitions 8 SECTION 3: INSTRUCTION FOR CONTINUED AIRWORTHINESS Introduction Description of alteration Control, Operating and Testing Information Servicing information Periodic Maintenance Instructions Troubleshooting information Removal and replacement information Diagrams Special Inspection Requirements Application of protective treatments Specials tools Additional Instructions Overhaul Period ICA Revision and Distribution Assistance Implementation and Record keeping 28 SECTION 4: AIRWORTHINESS LIMITATIONS SECTION AIRWORTHINESS LIMITATIONS INFORMATION 29 ATTACHMENT 1 Chapter APPENDIX A 31 Revision 12 page 6

7 2 SECTION 2: INTRODUCTION 2.1 PURPOSE OF THE DOCUMENT This document is designed for use by the installing of one of the two systems called HELICOM V2 ANA or HELICOM V2+ ANA as Instructions for Continued Airworthiness in response to Federal Aviation regulation (FAR/JAR) Part and Part 27 Appendix A. The ICA includes information required by the operator to adequately maintain the HELICOM V2 ANA or HELICOM V2+ ANA system installed under Approval Model List STC delivered by EASA (see reference on page 5). 2.2 APPLICABLE DOCUMENTS - EASA STC approval (see page 5). - Associated Technical Documentation mentioned on STC certificate (see paragraph 2.1 below) 2.3 SCOPE This document provides the Instructions for Continued Airworthiness of Airbus Helicopters AS 350 B, BA, BB, B1 & B2 rotorcraft, modified by the installation of the system HELICOM V2 ANA or HELICOM V2+ ANA, a system for tracking a set of flight and system parameters during operation of the rotorcraft, according to AML STC. Warning: It is reminded that HELICOM V2 ANA or HELICOM V2+ ANA system is a tool which is not relevant for the flight safety and might be inoperative during the flight (refer to IR/OPS). 2.4 PERMISSION TO USE CERTAIN DOCUMENTS Permission is granted to any corporation or person applying for approval of a HELIOM V2 ANA or HELICOM V2+ ANA - Airbus Helicopters AS 350 B, BA, BB, B1, B2 models to use and reference appropriate STC documents to accomplish the Instructions for Continued Airworthiness and show compliance with STC engineering data. The permission does not construe suitability of the documents. It is the responsibility of the applicant to determine the suitability of the documents for the ICA. Revision 12 page 7

8 2.5 CERTIFICATION BASIS Title File identification Version Edit Rev Date FAR Part 27 CRI for Special Conditions for Lipo battery CRI F-01_Lithium Battery 2.6 STATEMENT OF COMPLIANCE Issue 3 23 th September 2014 The aim of this document is to substantiate the compliance of the change dealing with the installation of the FDMS HELICOM V2 ANA or HELICOM V2+ ANA with the following requirements of the Certification Program, file N2-AS350 B BA BB B1 B2. Regulation substantiated FAR Part Substantiation following certification program «N2-AS350 B BB BA B1 B2» Instructions for Continued Airworthiness are prepared in accordance with Appendix A to FAR Part 27. I declare that this document provides the proof of compliance for which it has been created. 2.7 DEFINITIONS The following terminology is used within this document: ACO : Aircraft Certification Office AEG : Aircraft Evaluation Group EASA : European Aviation Safety Agency FAA : Federal Aviation Agency ICA : Instruction for Continued Airworthiness ISEI : International Services Electronique Informatique STC : Supplemental Type Certificate Revision 12 page 8

9 3 SECTION 3: INSTRUCTION FOR CONTINUED AIRWORTHINESS 3.1. Introduction Content, Scope, Purpose and Arrangement : This document identifies the Instructions for Continued Airworthiness for the modification of the AS350 B BA BB B1 B2 by installation of HELICOM V2 ANA or HELICOM V2+ ANA System. Important: For US H/Cs, BB model is excluded because this Type is not validated by FAA (refer to FAA TCDS) Applicability : Applies to aircraft altered by installation of HELICOM V2 ANA / HELICOM V2+ ANA Definition of See section 1.4 Abbreviations : Precautions : None Unit of measurement : None Referenced publications : STC approval (see page 5): Installation of HELICOM V2 ANA or HELICOM V2+ ANA system on HC type AS350 B BA BB B1 B2. Associated technical documentation (designed by ISEI and accepted by EASA) : - Approval change document File N2-AS350 B BA BB B1 B2-E-C-05 dated 12 th October Installation document File N6-AS350 B BA BB B1 B2-E- C-05 dated 12 th October Rotorcraft Flight Manual Supplement File N8-AS350 B BA BB B1 B2-E-C-03 Revision 06 dated 12 th October Maintenance Manual: MM-PN47XX-E-A-03 and later revisions Retention : This document or the information contained within, will be included in the aircraft s permanent records. Revision 12 page 9

10 3.2 Description of Alteration HELICOM V2 ANA or HELICOM V2+ ANA system is a Flight Data Monitoring and Transmitting system (FDMT) on the market. It is an all in one Recorder/Transmitter. Designed from the last innovative technologies, HELICOM V2 ANA or HELICOM V2+ ANA enables automatic data storage, transmission, analysis and alarm at then end of every flight. Once set up, the system works alone. HELICOM V2 ANA allows acquisition of 48 parameters and up to 64 for HELICOM V2+ ANA, plus other data (like pilot name, mission type, taking off area, landing area, and so on) and different analysis: - Data from GPS (not included in the 48 parameters) - Differential pressure (IAS) - Static pressure - Load factor - Time, cycles, landing, alerts, mission type, and so on (for e-log book) - Fleet localization - Curves of chosen parameters - Maintenance management - Trajectory - Route from GPS HELICOM V2 ANA (VARIANT 1) and HELICOM V2+ ANA (VARIANT 2) have the following capabilities: - Satellite (Irridium) communication - WiFi communication - GSM/GPRS communication - Bluetooth communication - Removable SD Card, Windows compatible - Rugged memory, shocks and high temperature resistant (800 C), with a capacity of 4 hours. - Display on the front panel. The system uses a common web service which is named HELIWEB: it offers different services from ISEI Server (UMS++, HOMP, FOQA, fleet management, E-LOG book, thresholds, alarms pre-alarms, trajectory, localization, display of parameters, curves, trending and so on.). HELISAFE systems fully comply with the EASA OPS 3 requirements and ED155. Revision 12 page 10

11 3.3 Control, Operating Information Parameters set up and main device installation A tool kit reference TKAMWS is provided by ISEI in order to control the correct running of the change. It is a test computer with specific software connected to the equipment by an USB link. The user manual TKAMWS is available on the website space subscriber, and support section. The tool allows: - Step 1: to record in ISEI database the H/C number, the application number, the part and serial numbers installed - Step 2: to download the setup of PN4720, E, F, P-xx / PN4730E, F, P-xx - Step 3: to transfer the set up in PN4720,E, F, P-xx / PN4730E,F,P-xx - Step 4: to perform a functional control - Step 5, 6 and 7: to record the results of airworthiness controls. For more details, refer to Installation manual, file referenced N6, listed under the reference documentation in paragraph 3.1 of this document, for system operation and self-test operation Controls after installation Preliminary controls Test assembly - Check the proper fixing of the rack - Check the proper connections of connectors - Check the proper fixing wires Functional controls These controls are done to check that the system installed runs properly; there is no-interference with equipments already installed. They are done in 5 phases: HELICOM V2/V2+ ANA inspection, engine stopped Non interference controls engine stopped HELICOM V2/V2+ ANA inspection, on ground engine running Non interference controls on ground, engine running Non interference controls in flight Controls conditions Controls described above are conducted at the end of the installation of the approved change. Revision 12 page 11

12 Prerequisites for performing the inspections Controls are performed by an Authorized workshop by using the toolkit provided by ISEI, procedures or methods if equipments can not be controlled by tools or devices Controls results The results are entered by the installer using the tool kit. At the end of the control, data and results are sent to servers located in ISEI. The minutes of the controls are posted on the website Note: Functions to control are mentioned on Installation document, file referenced N6, listed under the reference documentation in paragraph 3.1 of this document, for system operation and self-test operation. 3.4 Servicing Information None. In the event of system failure, troubleshoot the equipment in accordance with the Maintenance Manual PN47XX listed under.3.1 and available on the website space subscriber, support section. Revision 12 page 12

13 3.5 Periodic Maintenance Instructions Periodic inspections are desirable to maintain the airworthiness of the change and reduce the probability of failure Commons actions Action Severity Periodicity Associated file Checking the Circuit Breaker Desirable Daily MM-PN47XX Upgrading firmware Desirable On request MM-PN47XX Basic control Desirable Weekly MM-PN47XX Checking SIM card contacts, PN2802 Desirable Annual MM-PN47XX Charging the spare battery type LPP S-3 (PN4002 / PN4002P) Mandatory Quarterly MM-PN47XX Charging the installed battery (if it was not used anyway) type LPP S-3 Mandatory Quarterly MM-PN47XX (PN4002 / PN4002P) Changing the operated battery type LPP S-3 (PN4002 / PN4002P) Mandatory Two years MM-PN47XX Overhaul main device PN4720-xx / PN4720E-xx / PN4720F-xx / PN4720P-xx / PN4730-xx / PN4730E-xx / PN4730Fxx / PN4730P-xx Mandatory Six years MM-PN47XX Visual inspection - antennas (GPS, GSM, SAT) only if antennas are installed by this STC Desirable In the event of Lightning strike Airbus Helicopters Standard Practices Manual Actions with tube PN installed Action Severity Periodicity Associated file Monitoring of telemetry curves IAS and ground speed Checking Total pressure circuits Mandatory Annual Actions with tube PN installed Mandatory Weekly HELISAFE curves AIRBUS HELICOPTERS process Action Severity Periodicity Associated file Checking Static pressure circuits Mandatory Annual AIRBUS HELICOPTERS process Revision 12 page 13

14 Note: See details on Maintenance Manual MM-PN47XX listed under.3.1 and available on the website space subscriber, support section. The equipment doesn t belong to equipments required for safety of flights. 3.6 Troubleshooting information Troubleshooting information are described within the Maintenance Manual MM-PN47XX listed under.3.1 and available on the website space subscriber, support section. It is strictly forbidden for the user to open the device for performing repair action. In the event of system failure, return the equipment to ISEI (manufacturer). ISEI Company is authorized to perform maintenance action on the system under PART 145 regulation (ISEI approval FR ). 3.7 Removal and replacement information Box extraction If the device HELICOM V2 ANA or HELICOM V2+ ANA is installed, it must be verified that the unit power-up self test sequence is successfully completed and no failure messages are annunciated (see details in the maintenance manual listed above). If the device is removed for repair and reinstalled, then follow installation procedures contained in the Installation document, file N6 listed in paragraph 3.1 of this document, and verify the device power-up self test sequence is successfully completed and no failure messages are annunciated. To remove the main device from the mounting rack, insert Allen keys (3 mm diameter) in the holes located in the front of it. Unscrew the box, symmetrically left and right to disconnect the box to its rack. Device HELICOM V2 ANA PN4720-xx PN4720E-xx PN4720F-xx PN4730-xx PN4730E-xx PN4730F-xx Device HELICOM V2+ ANA PN4720P-xx PN4730P-xx Revision 12 page 14

15 (N7-AS350 B BA BB B1 B2-ICA-E-C-05) Battery extraction When the main device is extracted, turn it upside down to access the battery door screw located underneath the device. The cover must be removed (4 screws 2,5x4 TF to undo with 5x100mm TH1 screwdriver) and the connector removed by pulling it gently before removing the battery Box insertion To insert the main device in the rack it doesn t require particular strength. Screw the box with two Allen keys (3 mm diameter), symmetrically left and right. Device HELICOM V2 ANA PN4720-xx PN4720E-xx PN4720F-xx PN4730-xx PN4730E-xx PN4730F-xx Device HELICOM V2+ ANA PN4720P-xx PN4730P-xx If the box forces during the insertion it is because the rack was installed too tight, so it must be adjusted to facilitate insertion of the box. Box is slide to the bottom of the rack. Screw the box with tow Allen keys (3 mm diameter) symmetrically left and right. Note that the display will flash (approaching the stop). Continue to screw and note resistance to screwing (in lock) Stop screwing, the box is correctly inserted into its rack. Note: for more details, refer to maintenance manual listed above Revision 12 page 15

16 3.7.4 Battery insertion When the main device is extracted, turn it upside down to access the battery door screw located underneath the device. the cover must be removed (4 screws 2,5x4 TF to undo with 5x100mm TH1 screwdriver) the battery must be first connected to the device connector, then the battery must be inserted in its housing with taking care not to pinch the wire when refitting the cover. Note: The date of manufacture ( produced on AAAA/MM ) of the battery on the label must be recorded Battery charging instruction The battery charging is provided as soon as the energy is established in the aircraft. In the event of prolonged storage of the aircraft (more than 3 months), it is necessary to recharge the battery by putting power on the system and let the charge for four hours. The battery charging is automatic, the load current is determined by the integrated controller which ensures that the charge will be made under ideal conditions without temperature rise. For batteries in spare, the frequency is the same (charging every three months for four hours). WARNING USE ONLY BATTERY TYPE LPP S-3 (PN4002 / PN4002P) Handle the batteries with care. Do not use external charger. Do not put in short circuit, do not open, do not drill, do not throw them into the fire. Do not expose them to extreme temperatures (-20 C< < 60 C). When replacing the battery, send back used battery at ISEI. This requires putting in place the battery in the equipment according to the procedure of Revision 12 page 16

17 3.7.6 Equipment Location and Access Table 01 provides the list of Part Numbers which consist of HELICOM System in reference to figures 01 until figure 05. Table 02 provides the characteristics of P/Ns listed in the table 01. Table 03 provides general information Figure 01 below depicts the proposed locations for the main device HELICOM. Figure 02 below depicts the proposed locations for the external display (option) in case of the main device is not installed on the instrument panel. Figure 03 below depicts the proposed locations for antennas GSM, GPS, SAT Figure 04 below depicts the proposed locations for sensors (temperature and air/ground sensor) Figure 05 below depicts the location for the dedicated breaker 1AMP Helicom on the Circuit Breaker panel Revision 12 page 17

18 Table 01. Part Number of the change Rack for main device HELICOM Main device HELICOM Battery for main device SIM Card for main device PN4770-xx / PN4770P-xx PN4720-xx / PN4720E-xx / PN4720F-xx / PN4720P-xx / PN4730-xx / PN4730E-xx PN4730F-xx / PN4730P-xx PN4002 / PN4002P PN2802 Air Ground sensor GSM Antenna GPS Antenna SAT Antenna PN4212 PN4208 PN4205 PN4206 External display Temperature sensor PN4300 / PN4300P PN4208 Revision 12 page 18

19 Table 02. Technical Characteristics Weight Equipment Main device HELICOM V2 ANA (PN4720,E,F-xx / PN4730,E,F-xx) Main device HELICOM V2+ ANA (PN4720P-xx / PN4730P-xx) Rack for main device HELICOM V2/V2+ ANA (PN4770 / PN4770P-xx) External display (PN4300/PN4300P) Antennas Cables and connectors Weight 850 g < 975 g 300 g 350 g 350 g 300 g Power supply Equipment Consumption Supply voltage Main device HELICOM V2 ANA (PN4720,E,F-xx / PN4730,E,F-xx) 2 W +15V, +35 V Main device HELICOM V2+ ANA (PN4720P-xx / PN4730P-xx) 2 W +15V, +35 V Rack for main device HELICOM V2/V2+ ANA (PN4770 / PN4770P-xx) 0,5 W +15V, +35 V External display (PN4300/PN4300P) 0,5 W +15V, +35 V Antennas 0,5 W +15V, +35 V Cables and connectors Operating temperature Equipment Main device HELICOM V2 ANA (PN4720,E,F-xx / PN4730,E,F-xx) Main device HELICOM V2+ ANA (PN4720P-xx / PN4730P-xx) Rack for main device HELICOM V2/V2+ ANA (PN4770 / PN4770P-xx) External display (PN4300/PN4300P) Antennas Cables and connectors Storage temperature Equipment Main device HELICOM V2 ANA (PN4720,E,F-xx / PN4730,E,F-xx) Main device HELICOM V2+ ANA (PN4720P-xx / PN4730P-xx) Rack for main device HELICOM V2/V2+ ANA (PN4770 / PN4770P-xx) External display (PN4300/PN4300P) Antennas Cables and connectors Temperature -40 C, +70 C -40 C, +70 C -40 C, +70 C -15 C, +55 C for PN C, +70 C for PN4300P -40 C, +70 C -40 C, +70 C Temperature -55 C, +85 C -55 C, +85 C -55 C, +85 C -30 C, +70 C for PN C, +85 C for PN4300P -55 C, +85 C -55 C, +85 C Revision 12 page 19

20 Main device with its installation kit (rack) External display (optional) Table 03. General information Parts Location Description Located on the panel or in the under floor bay or in the left side cargo bay On the panel - GSM antenna: located behind the cabin using a dedicated bracket or under the cabin Rack is fixed with a dedicated bracket using screws M3 Device is fixed using 4 quarter turn fasteners A dedicated antenna bracket is used: - GSM antenna is fixed using a nut and washer (nut is tightened with a torque 2.2 danm) and thread lock Antennas (GSM, SAT, GPS) Sensor (Air Ground, OAT) - GPS antenna: located behind the cabin using a dedicated bracket or on the top panel located behind the main rotor - SAT antenna: located behind the cabin using a dedicated bracket or on the top panel located behind the main rotor Fixed under the cabin - GPS antenna is fixed using a nut and washer (nut is tightened with a torque of 2.2daNm). - SAT antenna is fixed using 4 screws M4 and thread lock If installed on the top panel, the SAT antenna is fixed using a flange and rivets. Fixed with nut and washer (a reinforcement plate can be used) Revision 12 page 20

21 Figure 01. Installation of the main device Location 1-1 Location Location 1-3 Revision 12 page 21

22 Figure 02. Installation of the external display (option) Revision 12 page 22

23 Figure 03. Installation of antennas Figure 03 Location 3-1 Location 3-2 / 3-4 Location 3-3 Revision 12 page 23

24 Figure 04. Installation of sensors (temperature, Air/Ground) Location 4-1 Revision 12 page 24

25 Figure 05. Installation of the dedicated breaker 1AMP HELICOM Figure 04 Fuse panel 31 Aplha Or C/B panel 16 Alpha The fuse/breaker 1AMP labeled Helicom is installed in a spare position on the C/B or fuse panel. Revision 12 page 25

26 Remark: In some H/Cs configuration, depending on the availability of the fuse spare position, the fuse 1AMP can be installed close to the electric core 1 Alpha located at the back (which is located close to left side cargo bay). Revision 12 page 26

27 3.7.7 Weight and Balance The mass of the recorder HELICOM is less than 1kg (and less than 2.5kg for the full kit); the empty weight of the aircraft is approximately kg and maximum take-off mass of kg. There is negligible weight change associated with the installation of the HELICOM (0.2% regarding empty weight ratio). 3.8 Diagrams Wiring diagrams are contained in Appendix A of this document. HELICOM system parts locations are described in Section 3.7 of this document. 3.9 Special Inspection Requirements In case of GPS and SAT antennas are installed on the top panel. If an antenna is replaced under this STC, an antenna visual inspection must be performed if there is suspected lighting strike on the aircraft. In the event of a suspected or actual lightning strike to the aircraft, antenna and its associated installation shall be inspected. If thee antenna was struck by lightning then the antenna and the surrounding installation shall be inspected to ensure that there is no structural damage around the areas where lightning may have struck. Execute the system checkout procedure for the GPS/SAT link using antenna, to ensure the system is operating correctly. No action is required for hard landing inspections Application of protective Treatments None, N/A 3.11 Special tools A toolkit TKAMWS is required for maintenance (inspections/tests) and control the correct running of the system. Refer to the user manual, file referenced UM-TKAMWS V2-E-A-01 available on the website function column > communication section > support menu Additional Instructions None. N/A Revision 12 page 27

28 3.13 Overhaul Period The system requires overhaul at a specific time period (6 years) as mentioned above on However power on self-test and continuous built in test monitor the health of the HELICOM. If a message is displayed by the device HELICOM, the unit may be tested and/or removed if relevant failure on device HELICOM has been identified; Any replacement will be performed as described above on.3.7. Refer to section 3.6 for Troubleshooting information ICA Revision and Distribution Changes or corrections made to ICA after Authority acceptance of ICA are considered to be a revision. ISEI uses means to indicate changes to the ICA: any change on line, paragraph, complete page, is indicated by red color and by a vertical bar in the left margin next to the line. To access manuals, you may contact ISEI Company via telephone 0033 (0) or by using the following address support@isei.info. A ISEI Service Bulletin describing ICA revision will be sent to ISEI dealers if a revision is determined to be significant Assistance The customer may refer questions regarding to this ICA, the equipment HELICOM V2 ANA or HELICOM V2+ ANA and its installation to the manufacturer, ISEI. ISEI customer assistance may be contacted via telephone 0033 (0) or contact@isei.info, support@isei.info 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 operator s rotorcraft scheduled maintenance program. Revision 12 page 28

29 SECTION 4: AIRWORTHINESS LIMITATIONS SECTION 4.1. AIRWORTHINESS LIMITATIONS INFORMATION There are no airworthiness limitations associated with this type of design change. For US aircraft: The Airworthiness Limitations section is FAA approved and specifies inspections and other maintenance required under 14CFR and of the Federal Aviation Regulations unless an alternative program has been FAA approved. There are no additional Airworthiness Limitations as defined in 14 CFR 27, Appendix A, A27.4 that result from this modification. Revision 12 page 29

30 ATTACHMENT 1 ATA CHAPTER LISTINGS Listed below are the ATA chapters and their titles concerned by the change. AIRFRAME SYSTEMS Chapter 31 Indicating and Recording Revision 12 page 30

31 APPENDIX A WIRING DIAGRAM HELICOM V2/V2+ PN4770-xx (Variant 1) and PN4770P-xx (Variant 2) REAR VIEW Revision 12 page 31

32 DATA 1 connector: basis and alternatives Revision 12 page 32

33 DATA 1 connector: new equipments, options and alternatives Revision 12 page 33

34 RF connectors Note: A bulkhead connector can be used for conneting SAT antenna (if applicable). See below the diagram. Revision 12 page 34

35 DATA 2 connector Revision 12 page 35