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Mar 2017

Page 98

DATA ACQUISITION FLIGHT RECORDER Type D51615-202-XXX or D51615-

202-XXX-090 with CCU Type D51616-XXXX and CAM Type D51623-XXXX

Installation and Operating Manual with Illustrated Parts

List

Commercial in Confidence

PIM434-I

means without prior permission in writing from the copyright owner.

4.3 POWER

SUPPLY

The Cockpit Control Unit is designed to be powered from the
CVR Recorder derived Pre Amp supply. This supply is

nom12VDC ±5% or +18VDC ±5% with maximum
current of 100mA.

Summary of Contents for D51615-202 Series

Page 1: ...XX Installation and Operating Manual with Illustrated Parts List PIM434 I March 2017 Penny Giles Aerospace Limited 1 Airfield Road Christchurch Dorset BH23 3TH United Kingdom Tel 44 0 1202 481771 Fax 44 0 1202 484846 Registered Office 1 Airfield Road Christchurch Dorset BH23 3TH United Kingdom Registered in England No 2336358 VAT Registration No GB 806 6586 08 Website www cwc ae com ...

Page 2: ...e or for any other purpose except with the written consent of Penny Giles Aerospace Limited The operating procedures given in this manual have been written on the assumption that personnel performing the procedures have received training of a standard adequate to enable them to do so and are qualified in the appropriate operating techniques Such personnel are deemed also to be competent to act at ...

Page 3: ...ed DS790 Mar 2009 Update to figures and tables reflecting qualified unit standard DS842 Oct 2010 Win 95 changed to Win XP 72 month inspection instructions updated DS872 Oct 2010 CCU and CAM variants added IPL section added DS909 Sep 2011 Addition of note regarding current limiting when powering the recorder with a 28V PSU DS0990 Sep 2013 Clarify the version of PGS required Vision or Analysis in pa...

Page 4: ... XXXX and CAM Type D51623 XXXX Installation and Operating Manual with Illustrated Parts List Commercial in Confidence PIM434 I Penny Giles Aerospace Ltd No part of this work may be reproduced or distributed by any means without prior permission in writing from the copyright owner THIS PAGE IS INTENTIONALLY BLANK ...

Page 5: ... AND SPECIFICATION 3 1 1 DESCRIPTION 3 1 1 1 General 3 1 1 2 Equipment Part Numbering 5 1 1 3 Mechanical Description 6 1 1 4 Electrical Description 6 1 1 5 Interface Description 7 1 2 OPERATION 18 1 2 1 Operational Modes 18 1 3 SPECIFICATION 22 1 3 1 Functional Characteristics Performance 22 1 3 2 Physical and Other Characteristics 30 1 3 3 Environmental Conditions 30 2 STORAGE 34 3 UNPACKING 34 4...

Page 6: ...leaning 47 6 4 2 ULB Battery Test 47 6 4 3 ULB Test 49 6 4 4 ULB Removal and Replacement 30 Day Beacon Battery 50 6 4 5 ULB Removal and Replacement 90 Day Beacon 51 6 5 CVR SYSTEM CHECK 52 6 5 1 Equipment Required 52 6 5 2 Procedure 52 6 6 FDR SYSTEM CHECK 53 6 6 1 Equipment Required 54 6 6 2 Procedure Using Internet Explorer 55 6 6 3 Procedure Using PGS Only 58 6 7 CVR REPLAY 60 6 7 1 Equipment R...

Page 7: ...ION 86 1 1 1 General 86 1 1 2 Mechanical Description 87 1 2 OPERATION 87 1 2 1 Interfaces 87 1 2 2 Installation 90 1 2 3 Equipment Inputs 90 1 2 4 Equipment Outputs 92 1 3 SPECIFICATION 93 1 3 1 Functional Characteristics Performance 93 1 3 2 Physical and Other Characteristics 93 1 3 3 Environmental Characteristics 95 2 STORAGE 96 3 UNPACKING 96 4 INSTALLATION 97 4 1 WIRING 97 4 2 SIGNAL LEVELS 97...

Page 8: ...ISITION FLIGHT RECORDER TYPE D51615 202 XXX 37 FIGURE 10 TYPICAL BEACON LABEL 49 FIGURE 11 TYPICAL STATUS PAGE 69 FIGURE 12 FAULT ISOLATION FLOWCHART SHEET 1 71 FIGURE 13 FAULT ISOLATION FLOWCHART SHEET 2 72 FIGURE 14 DATA ACQUISITION FLIGHT RECORDER TYPE D51615 202 XXX 78 FIGURE 15 DATA ACQUISITION FLIGHT RECORDER TYPE D51615 202 XXX 090 80 FIGURE 16 COCKPIT CONTROL UNIT TYPE D51616 1XXX 86 FIGUR...

Page 9: ...ny means without prior permission in writing from the copyright owner TABLE 7 SPECIAL TO TYPE TEST EQUIPMENT REQUIRED 67 TABLE 8 GENERAL PURPOSE TEST EQUIPMENT REQUIRED 67 TABLE 9 CLEANING MATERIALS 73 TABLE 10 COCKPIT CONTROL UNIT TYPE D51616 1XXX CONNECTOR DETAILS FOR SINGLE DAFR INSTALLATION SUPPORT REMOTE MIC 88 TABLE 11 COCKPIT CONTROL UNIT TYPE D51616 2XXX CONNECTOR DETAILS FOR DUAL DAFR INS...

Page 10: ...623 XXX or Type D51702 XX Who should read this manual Installers operators and maintenance personnel of DAFR equipment should read this manual It introduces the features of DAFR CCU and CAM interfacing and operation that you need to understand to become competent in the use of these products How to use this manual Each chapter in the manual builds on concepts introduced in previous chapters so wor...

Page 11: ...e left mouse button whilst moving the mouse What do I need before I begin Before starting to work with the DAFR and its ground support interface you must have a PC with Internet Explorer 6 installed on the machine as a minimum You also need Penny Giles Replay equipment Type D51620 comprising PGS Vision version 4 0 7 Part No 010000331 or equivalent Ground Aircraft replay leads Part Nos SA109680 and...

Page 12: ...AND SYMBOLS A Amperes AC Alternating Current AF Audio Frequency ARINC Air Radio INCorporated ATA Air Transport of America ATR Air Transport Racking BIT Built In Test BITE Built In Test Equipment BS British Standards CAA Civil Aviation Authority CAM Cockpit Area Microphone CCS Customer Configuration Specification CCU Cockpit Control Unit CFE Customer Furnished Equipment CMM Component Maintenance Ma...

Page 13: ...ead Only Memory EPROM Eraseable Programmable Read Only Memory EUROCAE European Organisation for Civil Aviation Electronics FAA Federal Aviation Administration FDAU Flight Data Acquisition Unit FDR Flight Data Recorder GMT Greenwich Mean Time GND Ground GRE Ground Replay Equipment HDLC High Level Data Link Communication Hz Hertz ISO International Standards Organisation in inches in s inches per sec...

Page 14: ...an Time Between Overhauls MTI Manufacturers Test Interface mtr metre n nano NC Not Connected NOVRAM Non Volatile Random Access Memory OC On Condition OMS Onboard Maintenance System P G Penny Giles Aerospace Limited 1 Airfield Road Christchurch BH23 3TH UK PCB Printed Circuit Board PEC Panel Electronic Circuit PRE Portable Replay Equipment PSU Power Supply Unit PTT Push To Test RAM Random Access Me...

Page 15: ...Illustrated Parts List Commercial in Confidence PIM434 I Penny Giles Aerospace Ltd No part of this work may be reproduced or distributed by any means without prior permission in writing from the copyright owner ULB Underwater Locator Beacon V Volts wps Words per Second º Degree s Temperature µ micro Plus or minus Less than Less than or equal to Greater than Greater than or equal to ...

Page 16: ...6 XXXX and CAM Type D51623 XXXX Installation and Operating Manual with Illustrated Parts List Commercial in Confidence PIM434 I Penny Giles Aerospace Ltd No part of this work may be reproduced or distributed by any means without prior permission in writing from the copyright owner THIS PAGE IS INTENTIONALLY BLANK ...

Page 17: ...ulated crash conditions to enable the subsequent retrieval and decoding by suitable replay equipment following an incident Facilities exist within the DAFR for aircraft in situ data retrieval The DAFR retains as a minimum both the most recent 25 hours of aircraft data and the most recent 120 minutes of four audio sources The DAFR is configurable to support different user applications through a con...

Page 18: ...Cockpit Voice EASA Specifications ETSO C123b and ETSO C124b The Cockpit Control Unit Type D51616 XXXX may be used in conjunction with each variant of the Penny Giles Aerospace Ltd Data Acquisition Flight Recorder and provides features compatible with ARINC 757 Supplement 2 The Cockpit Control Unit provides facilities to monitor and display the operational status of the recorder and also contains t...

Page 19: ...egulations allow the fitting of a combined voice and data recorder The equipment is compatible with interface requirements of ARINC 757 Supplement 2 for CVR functions FDR data acquisition is supported via three high or low speed ARINC 429 interfaces 4 analogue inputs 6 discrete inputs a single rotor tachometer input and an accelerometer input DAFR Type D51615 202 XXX is illustrated in Figure 1 and...

Page 20: ...ns without prior permission in writing from the copyright owner Figure 1 Data Acquisition Flight Recorder Type D51615 202 XXX Figure 2 Data Acquisition Flight Recorder Type D51615 202 XXX 090 Fitted with the 90 Day Beacon Kit The DAFR is capable of downloading stored flight data audio rotor speed and configuration data digitally at high speed across the 10Base T 100Base Tx Fast Ethernet Manufactur...

Page 21: ...y white strips as an aid to its location No external controls are provided on the DAFR as operation is automatic upon the application of power The DAFR Type D51615 202 XXX or Type D51615 202 XXX 090 satisfies the minimum operating requirements for a Cockpit Voice Recorder and Flight Data Recorder as defined by ED112 and ARINC 757 Supplement 2 1 1 2 Equipment Part Numbering The Penny Giles Aerospac...

Page 22: ...tional Orange as an aid to its location Additionally reflective tape is attached to the external surfaces The DAFR is marked with the following warning in black letters FLIGHT RECORDER DO NOT OPEN ENREGISTREUR DE VOL NE PAS OUVRIR Fitted through the case front panel to the Crash Survivable Memory Module CSMM is the ULB and two hold down feet The unit identification label a modification label a Sof...

Page 23: ... PSU MODULE Figure 4 DAFR System Block Diagram 1 1 5 Interface Description General All status outputs and control inputs with the exception of VOICE ERASE and RECORD ON operate with respect to CHASSIS GROUND The DAFR is direct mounted to an aircraft bulkhead equipment shelf NOTE Anti vibration mounting is not required Electrical connection is automatically achieved via the single connector mounted...

Page 24: ...ed equipment are identified in Table 1 Table 1 Aircraft Mating Connector Details EQUIPMENT DAFR DAFR REPLAY CONNECTOR CONNECTOR D38999 26FF35SN D38999 20FB35PN STRAIGHT CABLE CLAMP 1 M85049 38 19A Not required ELBOW CABLE CLAMP 1 M85049 39 19A Not required DUST CAP Not required D38999 33 W 11R CRIMP TOOL M22520 2 01 M22520 2 01 CRIMP TOOL LOCATOR M22520 2 07 M22520 2 09 NOTE 1 The cable clamp is o...

Page 25: ...e D51623 XXXX Installation and Operating Manual with Illustrated Parts List Commercial in Confidence PIM434 I Penny Giles Aerospace Ltd No part of this work may be reproduced or distributed by any means without prior permission in writing from the copyright owner Figure 5 Installation drawing for DAFR Type D51615 202 XXX Part 1 ...

Page 26: ...pe D51623 XXXX Installation and Operating Manual with Illustrated Parts List Commercial in Confidence PIM434 I Penny Giles Aerospace Ltd No part of this work may be reproduced or distributed by any means without prior permission in writing from the copyright owner Figure 6 Installation drawing for DAFR Type D51615 202 XXX Part 2 ...

Page 27: ...ype D51623 XXXX Installation and Operating Manual with Illustrated Parts List Commercial in Confidence PIM434 I Penny Giles Aerospace Ltd No part of this work may be reproduced or distributed by any means without prior permission in writing from the copyright owner Figure 7 Installation drawing for DAFR Type D51615 202 XXX 090 ...

Page 28: ...urable5 7 Pre Amp Power Out GND 24 AWG Configurable5 8 0V Signal1 22 AWG 9 Accelerometer In Lo 22 AWG Configurable5 10 Rotor Speed In Hi 24 AWG S T P Configurable5 11 Rotor Speed In Lo Configurable5 12 28 VDC Power In 22 AWG 13 FDR Fault Out 24 AWG Configurable5 14 CVR Fault Out 24 AWG Configurable5 15 Voice Erase A 24 AWG Configurable5 16 Voice Erase C 24 AWG Configurable5 17 Audio Out Hi 24 AWG ...

Page 29: ... 1 Audio In Lo 24 AWG S T P WITH 27 Configurable5 37 Channel 2 Audio In Lo 24 AWG S T P WITH 28 Configurable5 38 Channel 3 Audio In Lo 24 AWG S T P WITH 29 Configurable5 39 Channel 4 Audio In Lo 24 AWG S T P WITH 30 Configurable5 40 Potentiometer 3 Return Configurable5 41 Potentiometer 2 Return Configurable5 42 Reserved 43 ARINC 429 3 In A Configurable5 44 ARINC 429 3 In B Configurable5 45 Discret...

Page 30: ...ft Pins 4 5 8 and 61 2 Link to be kept as short as possible Pins 59 and 60 3 Category 5 Foil Twisted Pair Pins 20 to 21 and 22 to 23 4 Force IP Address Pin 33 5 Refer to Part 4 Customer Configurations Specifications for details relating to the recorder configuration Equipment Inputs Power Supply The nominal power supply to the DAFR shall be 28VDC with aircraft electrical power characteristics of R...

Page 31: ...TEST A High to Low transition causes the DAFR to reset and commence its power up test sequence During the start up sequence the CVR and FDR Fault outputs are asserted This action also initiates automatic recording iii VOICE ERASE Linking VOICE ERASE A to VOICE ERASE C for greater than two seconds initiates a voice erase for all channels assuming aircraft interlocks are satisfied and the recorder i...

Page 32: ...configuration file uploaded at time of manufacture the source of this data is defined in the appropriate customer configuration specification The acquired data is formatted into a means suitable for download processing and replay in support of an incident CVR Audio Channel Inputs All audio inputs are balanced and have input impedance of 10kΩ at 1kHz nominal Signal characteristics are defined in Au...

Page 33: ...FDR and CVR Fault Output polarity is configurable i FDR FAULT Open circuit until the data recording system is operating satisfactorily at which time it is connected to CHASSIS GROUND When open circuit the FDR Data out signals are clamped to 0v Maximum current 100mA ii CVR FAULT Open circuit until the audio recording system is operating satisfactorily at which time it is connected to CHASSIS GROUND...

Page 34: ...ill operate at either 10 MHz or at a maximum MTI clock rate of 100 MHz The link will auto negotiate to whichever rate is determined at equipment start up Information Protocol The MTI implements TCP IP 1 2 OPERATION 1 2 1 Operational Modes The following are the operational modes for each of the separate recording subsystems The voice recording section can operate completely independently of the dat...

Page 35: ...rounded Data is validated on a read after write basis internal to the recorder only Record CVR Audio Only The Record CVR Audio Only mode is the normal operational mode for the Cockpit Voice Recorder subsystem The states of the control lines to initiate this mode are as follows STOP CVR RECORDING High RECORD ON Jumper fitted PUSH TO TEST High VOICE ERASE A Low or open circuit FDR INHIBIT Don t Care...

Page 36: ...BIT Don t Care OR STOP CVR RECORDING Low PUSH TO TEST High to Low transition VOICE ERASE A Low or open circuit RECORD ON Jumper fitted FDR INHIBIT Don t Care This mode is also entered upon power being applied to the DAFR Audio information is digitized and sequentially written to the crash survivable memory module in a method consistent with the segregation and partitioning requirements of ED112 fo...

Page 37: ...FR is installed within the aircraft Download Off Aircraft The off aircraft Download mode allows the high speed recovery of all recorded aircraft parameter data or audio information via the MTI Download options are provided for the individual files recorded within the CSMM These comprise of files for each input audio channel the combined communications channels the reduced bandwidth CAM channel Fli...

Page 38: ...itable aircraft interlocks FDR INHIBIT Don t Care RECORD ON Jumper fitted During the erase cycle CVR FAULT output will toggle at a frequency of 0 5Hz 1 3 SPECIFICATION 1 3 1 Functional Characteristics Performance Flight Data Characteristics Data Inputs The DAFR acquires FDR data from multiple input sources These collectively comprise ARINC 429 input channels Three ARINC 429 input channels are prov...

Page 39: ...ources Six discrete inputs are available for data acquisition over and above those that are available for recorder control purposes These inputs are typically connected to Push To Transmit or Engine status signals The inputs are sampled and recorded in accordance to the frequency resolution and accuracy of ED112 Enable Standard Ground Disable Standard Open Data Storage Delay The delay between the ...

Page 40: ...iod of 256 seconds Data Retention Following the removal of power from the DAFR the recorded information is retained for at least two years for the stipulated operational and storage environment Except for the overwriting of the oldest data by new information no means for the erasure of the record is provided Audio Characteristics Audio Inputs Four independent balanced inputs are provided Audio Sto...

Page 41: ...Hz iv Audio Channel 4 150Hz to 6 0kHz Noise Level Signal to No Signal A weighted With no signal applied to any input channel the reproduced signal is at least 48dB below the Reference Level when measured in accordance with the method described in EUROCAE ED112 Part I 3 2 5 This performance is also achieved for out of band signals applied to the inputs in accordance with the method described in EUR...

Page 42: ...w the Reference Level Audio Channel Balance With half of the Reference Signal applied to all audio channels the signals recovered differ by no more than 3dB Quality Index The speech transmission index of the audio channels when assessed using the method described in EUROCAE ED112 Part I annex D is at least the values given below i Audio Channel 1 0 75 ii Audio Channel 2 0 75 iii Audio Channel 3 0 ...

Page 43: ...o connected internally to 0V_Signal Pulse frequency range 10 Hz to 900 Hz Sensor source impedance 100 to 130 Ω in series with 33 mH or 1200 to 1500 Ω in series with 360 mH Typical Accuracy Measured to better than 2 Data to Audio Correlation The DAFR records synchronizing information embedded within the digitized audio record such that with appropriate replay equipment the relative time between the...

Page 44: ...til power is removed or a subsequent test is passed satisfactorily Continuous Tests Data During normal operation BIT routines are executed to continuously monitor the following aspects of the data recording system i Data processor program sequence ii Protected memory read after write iii Valid recording of flight data iv Ability to meet statutory minimum storage duration v Interface integrity chec...

Page 45: ...sserted only if its associated tests were failed Power Interruptions Power Interruption 200 milliseconds At normal power level interruptions with duration of 200 milliseconds or less have no effect Power Interruption 200 milliseconds At normal abnormal and emergency power levels interruptions with durations of more than 200 milliseconds may cause a reset condition When power is restored a power up...

Page 46: ... weight of the unit does not exceed 3 3kg 7 3lb This includes the ULB Dimensional Limits 255 L x 120 W x 89 H mm this includes the ULB External Finish To aid location of the DAFR the case is finished in International Orange to BS381C colour number 592 Marking The DAFR is marked with the following warning in black letters 25mm high FLIGHT RECORDER DO NOT OPEN ENREGISTREUR DE VOL NE PAS OUVRIR Refle...

Page 47: ...sceptibility F 2 12 Sand and Dust D 13 Fungus Resistance F 14 Salt Fog S 15 Magnetic Effect Z 16 Power Input A 17 Voltage Spike A 18 AF Conducted Susceptibility Z 19 Induced Signal Susceptibility ZC 20 RF Susceptibility WW 21 Emission of RF Energy M 22 Lightning Induced Transient Susceptibility A2F3X 23 Lightning Direct Effects X 24 Icing A 25 ESD A 26 Fire X Table 3 Non Cockpit Equipment Environm...

Page 48: ...15 Hydraulic Fluids Phosphate Ester Based 70 OX 20 Skydrol Lubricating Oils Synthetic 150 OX 27 Lubricating Oils Synthetic Hydrocarbon 70 Solvents and Cleaning Fluids Denatured Alcohol 23 Solvents and Cleaning Fluids Aircraft Cleaning Compound 23 Ardrox 6092 1 9 mix with water De Icing Fluid Ethylene Glycol 50 De Icing Fluid Propylene Glycol 50 Insecticides Pyrethroid Pesticide 23 Sullage Formalde...

Page 49: ...112 section 1 Chapter 2 4 2 2 Static Crush Subjected to a 22 25 kN 5000 lb static crush on at least four points and all diagonals for a continuous period of 5 minutes each as defined in ED 112 section 1 Chapter 2 4 2 3 High Temperature Fire Subjected to a high temperature fire test of 60 minutes duration producing a minimum thermal flux of 158 kW m2 50 000 Btu ft2 hour and a typical flame temperat...

Page 50: ...nths over the temperature range of 25 C to 40 C with a relative humidity not exceeding 75 NOTE If the DAFR is to be stored at temperatures expected to exceed 71 C then the ULB should be removed and stored separately at a lower temperature To mitigate the risk of an ULB battery fire explosion or burns do not recharge disassemble or heat above 71 C or incinerate Dispose of batteries promptly 3 UNPAC...

Page 51: ...llation will need to comply with the requirements of the relevant Certification Authority The conditions and tests required for TSO approval of this article are minimum performance standards It is the responsibility of those performing the installation of this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO ...

Page 52: ...1623 XXXX Installation and Operating Manual with Illustrated Parts List Commercial in Confidence PIM434 I Penny Giles Aerospace Ltd No part of this work may be reproduced or distributed by any means without prior permission in writing from the copyright owner DATA ACQUISTION FLIGHT RECORDER Figure 8 Typical DAFR System Block Diagram ...

Page 53: ...XX Installation and Operating Manual with Illustrated Parts List Commercial in Confidence PIM434 I Penny Giles Aerospace Ltd No part of this work may be reproduced or distributed by any means without prior permission in writing from the copyright owner Figure 9 Typical Wiring Diagram for Data Acquisition Flight Recorder Type D51615 202 XXX ...

Page 54: ... XXXX and CAM Type D51623 XXXX Installation and Operating Manual with Illustrated Parts List Commercial in Confidence PIM434 I Penny Giles Aerospace Ltd No part of this work may be reproduced or distributed by any means without prior permission in writing from the copyright owner THIS PAGE IS INTENTIONALLY BLANK ...

Page 55: ...he attenuation therefore set accordingly Confirmation of optimum attenuation level should be established by subjective evaluation of recordings made during flight 4 4 WIRING The recommended minimum wiring sizes are shown in Table 2 These sizes are applicable for runs of up to 100 metres For variants with an Internal Preamplifier and remote Area Microphone the limit on cable length to the microphon...

Page 56: ...RECORDING Some Operational Rules require a means of automatically terminating the recording and erasure functions within 10 minutes of an event such as all engines stopped or safe landing A built in timer is provided for this purpose A ground on pin 24 of the rear panel connector STOP CVR RECORDING will stop any recording and erasure within 10 minutes This may be achieved by wiring pin 24 to groun...

Page 57: ...events access to the Cockpit Voice recording The corresponding Flight Data recording is not affected Operating Rules do not mandate a Voice Erase function it is therefore an installation option If implemented it is however mandatory to provide a safety interlock to prevent accidental operation Further guidance is contained in ARINC 757 4 9 RECORDER LOCATION Operating rules give guidance on the rec...

Page 58: ...n the MAINTENACE section 2 Carry out the CVR System Check described in the MAINTENANCE section 3 Carry out the FDR System Check described in the MAINTENANCE section 4 12 FLIGHT TEST Each newly installed DAFR system on each aircraft type will need to be flight tested and for the audio recording evaluated to demonstrate adequate recording quality during all normal regimes of flight In the case of he...

Page 59: ...via the connector CAUTION IT IS NECESSARY TO REMOVE THE DATA ACQUISITION FLIGHT RECORDER TYPE D51615 202 XXX FOR MAINTENANCE POWER MUST BE SWITCHED OFF AT LEAST FIVE SECONDS BEFORE THE UNIT IS DISCONNECTED FROM THE AIRCRAFT 5 2 CONTROLS AND INDICATORS The Cockpit Control Unit Type D51616 XXXX provides two push buttons for TEST and ERASE a biased toggle switch for FDR RCRD ARINC 757 FDR INHIBIT fun...

Page 60: ... for the purpose of FDR subsystem ground test 5 2 4 CVR FAIL Indicator Steady illumination of the CVR FAIL indicator indicates either that a fault in the CVR subsystem has been detected by the DAFR BIT function or that the DAFR has been put into a non recording mode A non recording mode may be enabled when the Record On link is not fitted or within 10 minutes of the assertion of the Stop CVR Recor...

Page 61: ...ving repetitive inspections or tests to determine the condition of an assembly with regard to continued serviceability Corrective action is taken when required by assembly condition Comprehensive Built In Test Equipment BITE is provided within the equipment which identifies any subsystem failures and facilitates fault finding down to module circuit board level The BITE can be interrogated using Po...

Page 62: ... audio side tone interphone public address if recorded and boom microphone including hot mic function of the inhibit logic for bulk erase DAFR FDR System Check 12 months Copy and replay the last 15 minutes of flight recording Check all mandatory parameters are active and are of acceptable quality DAFR CVR Replay 24 months Remove recorder immediately post flight Replay and evaluate the quality of t...

Page 63: ...n extinguish 3 If either of the FAIL indicators remain illuminated the Functional Check has failed and the DAFR must be removed from the aircraft for servicing NOTE The Built In Test function is automatic on the application of power to the DAFR Provided power has been cycled pre flight it is sufficient just to check for a NO FAIL indication 6 4 ULB PERIODIC INSPECTIONS ULB periodic inspections are...

Page 64: ...dance of 10 MΩ not required when using the Dukane TS200 Test Set to perform the procedure make sure the case and water switch are clean and dry prior to testing If in doubt wipe clean using mild detergent and a soft cloth 2 Place the negative lead of the high impedance voltmeter on the water switch pin and the positive lead of the meter on the beacon case or the mounting kit if already installed 3...

Page 65: ...6 Beacon Voltage Code and Minimum Acceptable Voltage 6 4 3 ULB Test At the intervals specified and at any other time considered necessary the ULB is to be tested as follows NOTES 1 The beacon should be tested both prior to and after installation onto the DAFR 2 Alternate test equipment and test procedures may be used 1 Set the switches on the Dukane Ultrasonic Test Set Model 42A12A or equivalent a...

Page 66: ...CARE MUST BE TAKEN TO ENSURE THAT THE PAINT AROUND THE FIXING NUTS IS NOT DAMAGED DURING THIS PROCEDURE 2 THE ULB BRACKETS ARE DIFFERENT THE TOP BRACKET IS SLOTTED TO PREVENT THE BUILT UP OF MOIST TRIGGERING THE ULB AND THUS DRAINING THE ULB BATTERY CARE MUST BE TAKEN WHEN REASSEMBLING THE ULB TO THE DAFR TO ENSURE THAT THE CORRECT BRACKET IS USED IN THE CORRECT POSITION 3 DAFR TYPE D51615 202 XXX...

Page 67: ...S TO BE MADE TO REMOVE THE ADHESIVE FROM THE SKIN WITHOUT SOAP AND WATER DO NOT USE A SOLVENT FOR THIS PURPOSE 6 Assemble the fluorosilicone ring 100 in bottom beacon bracket 60 only Assemble beacon brackets 60 70 on the ULB 50 7 Rotate the ULB 50 so that the battery replacement date can be read easily 8 Attach the beacon brackets 60 and 70 to the main assembly with four M5 cap head socket screws ...

Page 68: ...he procedure detailed in steps 1 to 4 above 6 5 CVR SYSTEM CHECK The CVR System Check is to be carried out at intervals not exceeding six months elapsed time or as agreed with the relevant Regulatory Authority Carry out the Audio System Check as follows 6 5 1 Equipment Required The following equipment is required to carry out the check 1 600 Ω Headphone with 1 4 in mono jack plug 6 5 2 Procedure 1...

Page 69: ...s the use of Portable Replay Equipment PRE Type D51620 to carry out the FDR System Check The PRE available from Penny Giles Aerospace Ltd comprises software and cables In addition to this the hardware required to perform this check includes a portable PC and possible interface card should the PC not provide as standard The software includes Engineering Unit conversion and display functions Consult...

Page 70: ...nalysis prior to Release 5 2 0 the FDR Convert Utility must be used 9 When downloading and replaying using PGS Release 5 2 0 and above the FDR Convert Utility is not required This function has been integrated into the software 6 6 1 Equipment Required The following equipment is required to carry out the check 1 Pentium IV 2 4 GHz PC IBM or compatible with the following minimum specification a 10Ba...

Page 71: ...r aircraft 3 Apply power to the DAFR and the PC NOTE DAFR may take a minute or two after power is applied before responding to commands via the MTI 4 Download is started by either selecting the Internet Explorer icon on the desktop or by selecting the Internet Explorer task bar from the Task menu 5 Enter the recorder IP address of 10 0 0 100 in the address box and click go 6 Internet Explorer atte...

Page 72: ...ile for conversion on to the FDRConvert exe program icon located on the desktop or elsewhere The program will start and output similar to the following 4 The FDRConvert tool will check the validity of the file name and terminate if a The Input File does not exist b The Input File is of the wrong format NOTE If the Output File to be created already exists the existing file is automatically deleted ...

Page 73: ...ther functions within the software highlighting the button 7 From the menu options select the Flight Open Flight option from the drop down menu 8 Select the Files of Type drop down list and select the pcm option to reveal all previously converted PCM files Select the appropriate directory in which the download file is held 9 Select the appropriate file from the list you will then be asked to conve...

Page 74: ...op down menu select the Open Flight option 5 In the Open dialogue box select MPFR Files fdr as the file type and navigate to the appropriate directory in which the downloaded file is held 6 Select the file and when asked to convert the file into PGS flight data format click Yes 7 In the Save As dialogue box that opens select a location for the converted file and rename it if required Click Save 8 ...

Page 75: ...er option 5 Click on the Configuration button and ensure that the default IP address of 10 0 0 100 is specified Click OK to return to the download 6 From the check box options presented within this window select the FDR Data to download either All or Last Only option If Last Only option is selected enter the duration required followed by the Flight data Master System Log Files and Keep Compressed ...

Page 76: ...suitably qualified personnel 2 The applicable Regulatory Authority may require this procedure to be carried out by an approved Replay Centre 3 Confidentiality of the recording must be preserved 4 This procedure has to be performed with the DAFR removed from the aircraft 6 7 1 Equipment Required The following equipment is required to carry out the check 1 Pentium IV 2 4 GHz PC IBM or compatible wit...

Page 77: ... current limiting is disabled before applying power 3 Apply power to the DAFR and the PC 4 Replay is started by either selecting the Internet Explorer icon on the desktop or by selecting the Internet Explorer task bar from the Task menu 5 Enter the recorder IP address of 10 0 0 100 in the address box and click go 6 Internet Explorer attempts to connect to the recorder If successful the Recorder Ho...

Page 78: ...he displayed dialog box click the browse button and locate the DAFR cvr downloaded files from the above web based download 3 Select the 16bit resolution option and click Convert The CVR to WAV file conversion process will be performed 4 Repeat for all downloaded files 5 Quit from the WaveConverter utility 6 7 3 Procedure Using PGS NOTE The following procedure assumes that the PC has been configure...

Page 79: ...cel button to return to the Fleet Management window 6 7 4 CVR Audio Analysis The analysis of the CVR files may be performed on the download PC or on an alternative PC once the files have been copied 1 From the PGS workspace select the Flight Audio Player menu option or click on the Audio Player toolbar button 2 Audio player supports up to four separate audio files at once Select the File Open menu...

Page 80: ... situ or removed from the aircraft 2 If the FDR Check is to be performed in situ the procedure for FDR System check identified above should be performed A lab FDR Replay is identified following 6 8 1 Equipment Required The following equipment is required to carry out the check 1 Pentium IV 2 4 GHz PC IBM or compatible with the following minimum specification a 10Base T 100Base Tx Ethernet Interfac...

Page 81: ...ossible damage to the unit please ensure that any power supply current limiting is disabled before applying power 3 Perform the data download procedure identified in FDR Data Download above 4 Perform the data analysis procedure identified in FDR Data Analysis above 6 9 INSPECTION CAUTION IT IS NECESSARY TO REMOVE THE DATA ACQUISITION FLIGHT RECORDER TYPE D51615 202 XXX FOR 72 MONTHS PERIODIC INSPE...

Page 82: ...artial disassembly and observation of internal indicators and test points These operations shall be carried out with the equipment removed from the aircraft The recording functions of the DAFR cannot be verified directly without special to type test equipment or alternatively fitment in a known good aircraft installation Procedures for verifying the recording functions as part of the installation ...

Page 83: ...100Base Tx Ethernet Interface 1 Gbyte RAM 2 Microsoft Windows XP software 3 Internet Explorer 6 software 4 28VDC 4 Amp regulated power supply 5 Digital Multi Meter 1A DC range Table 8 General Purpose Test Equipment Required 7 2 3 Default Mode of Operation Current Status The DAFR maintains an internal register of the current status of key functions and the results of self tests This register the St...

Page 84: ... page is shown in Figure 11 9 Verify that the Recorder Mode parameter in the General status group reads NOT RECORDING 10 Verify that both the CVR Recorder and FDR Recorder groups show the following Mode PASSIVE Fault INDICATED Fault Count 0 Last Fault Source NO FAULT 11 Verify that all sections of the CRASH PROTECTED MEMORY group display RUNNING 12 Verify that the Manager status in the Built In Te...

Page 85: ...elf Test OK Configuration Checksum Self Test OK Power Supply Self Test OK Last 5 Trace Messages Typical None None None None None Figure 11 Typical Status Page Run Disk Check This function verifies that each disk drive in the crash protected memory area is working correctly The disk check also indicates how much disk space is available in total and how much is currently used To invoke the disk chec...

Page 86: ...n Benchmarking This function is reserved for use by the manufacturer ROM Test This function verifies that a series of test patterns in the program storage area of internal memory can be read correctly RAM Test This function verifies that a series of test patterns can be written to the data storage area of internal memory and that they can be read back correctly Program Checksum Test This function ...

Page 87: ... prior permission in writing from the copyright owner DATA ACQUISITION FLIGHT RECORDER Type D51615 202 XXX or D51615 202 XXX 090 with CCU Type D51616 XXXX and CAM Type D51623 XXXX Installation and Operating Manual with Illustrated Parts List Commercial in Confidence PIM434 I Figure 12 Fault Isolation Flowchart Sheet 1 ...

Page 88: ...XXXX and CAM Type D51623 XXXX Installation and Operating Manual with Illustrated Parts List Commercial in Confidence PIM434 I Figure 13 Fault Isolation Flowchart Sheet 2 FDR MODE NOT RECORDING FDR FAULT INDICATED RETURN TO P G RETURN TO P G CVR2 RUNNING RETURN TO P G RETURN TO P G CVR1 RUNNING YES YES NO NO NO NO YES PREVIOUS PAGE FDR1 RUNNING FDR2 RUNNING RETURN TO P G RETURN TO P G NO NO YES YES...

Page 89: ...r these items DESCRIPTION PART No SPEC VENDOR Soft cloth CFE Mild detergent CFE Table 9 Cleaning Materials 8 2 GENERAL CLEANING General cleaning of the DAFR is restricted to a wipe over the case with a damp not wet cloth 8 3 ULB SWITCH CLEANING CAUTION DIRT ON THE ULB SWITCH CONTACTS CAN CREATE A PATH FOR BATTERY CURRENT DRAIN The ULB inspections are to be carried out at intervals not exceeding si...

Page 90: ...DATA ACQUISITION FLIGHT RECORDER Type D51615 202 XXX or D51615 202 XXX 090 with CCU Type D51616 XXXX and CAM Type D51623 XXXX Installation and Operating Manual with Illustrated Parts List Commercial in Confidence PIM434 I 9 REPAIR NOTE The unit must be returned to Penny Giles Aerospace Limited for repairs Equipment is repaired at second line by the replacement of modules ...

Page 91: ...em number where the part can be found in the Detailed Parts List 10 1 3 Numerical Index when applicable The Numerical Index contains all the part numbers included in the Detailed Parts List together with the total quantity required for each figure and item listing A column has also been provided for the insertion of airline stock numbers Part numbers are arranged in an alphanumeric sequence with a...

Page 92: ...cribed and the unit is broken into its subassemblies and detailed parts Entries in the Nomenclature column are indented to indicate item relationship as follows 1234567 Main Assembly Reference Item Attaching Parts or Installation of Main Assembly Detail Parts for Main Assembly Attaching Parts for Detail Part Sub assembly Attaching Parts for Sub assembly Detail Parts for Sub assembly Attaching Part...

Page 93: ...y shown against each part is the quantity required for that position in the Detailed Parts List It does not preclude the recurrence of the part at other positions in the Detailed Parts List The abbreviation AR is given when the quantity of parts to be used is as required The abbreviation RF is given when the part is listed for reference purposes only Unillustrated Bulk Items List when applicable T...

Page 94: ...23 XXXX Installation and Operating Manual with Illustrated Parts List Commercial in Confidence PIM434 I Page 78 Penny Giles Aerospace Ltd No part of this work may be reproduced or distributed by any means without prior permission in writing from the copyright owner Figure 14 Data Acquisition Flight Recorder Type D51615 202 XXX ...

Page 95: ...d CAM Type D51623 XXXX Installation and Operating Manual with Illustrated Parts List Commercial in Confidence PIM434 I Page 79 Penny Giles Aerospace Ltd No part of this work may be reproduced or distributed by any means without prior permission in writing from the copyright owner THIS PAGE IS INTENTIONALLY BLANK ...

Page 96: ...rating Manual with Illustrated Parts List Commercial in Confidence PIM434 I Page 80 Penny Giles Aerospace Ltd No part of this work may be reproduced or distributed by any means without prior permission in writing from the copyright owner Figure 15 Data Acquisition Flight Recorder Type D51615 202 XXX 090 140 130 120 110 50 100 50 90 60 80 50 40 10 30 20 70 ...

Page 97: ...d CAM Type D51623 XXXX Installation and Operating Manual with Illustrated Parts List Commercial in Confidence PIM434 I Page 81 Penny Giles Aerospace Ltd No part of this work may be reproduced or distributed by any means without prior permission in writing from the copyright owner THIS PAGE IS INTENTIONALLY BLANK ...

Page 98: ...90003 SCREW M5 BUTTON HD SKT SS 2 12mm LG VK7766 30 680150161 WASHER M5 SS VK7766 2 40 250208134 PIN ROLL 1 5mm DIA 8mm LG 2 50 220000040 BEACON UNDERWATER 1 LOCATOR 60 P109552 BRACKET BEACON BOTTOM 1 70 P110318 BRACKET BEACON TOP 1 ATTACHING PARTS 80 435350487 SCREW M5 CAP HD SKT SS 4 45mm LG VK7766 90 680150161 WASHER M5 SS VK7766 4 100 230180180 FLUOROSILICONE 0 070in AR SECTION 110 200000193 L...

Page 99: ...110360 PLATE SPACER 1 230 SA109567 3 PEC MEMORY DAUGHTER BOARD 1 ESD ATTACHING PARTS 240 435750891 SCREW M3 PAN HD SS 4mm LG 4 VK7766 250 480230224 SPACER M3 MALE FEMALE 4 5mm LG 260 P109703 BRACKET CONNECTOR TOP 1 270 P109702 BRACKET CONNECTOR BOTTOM 1 ATTACHING PARTS 280 435450622 SCREW M3 CSK HD SS 6mm LG 4 VK7766 290 SA110592 PEC SYSTEM ESD 1 ATTACHING PARTS 292 435751034 SCREW M2 5 POZI PAN H...

Page 100: ...TTACHING PARTS 380 435886023 SCREW M3 BUTTON HD SKT SS 4 8mm LG VK7766 390 435886025 SCREW M3 BUTTON HD SKT SS 1 10mm LG 400 P109879 RAIL PCB MOUNTING 3 ATTACHING PARTS 410 480230238 SPACER M3 MALE FEMALE 2 7mm LG 420 680130110 WASHER M3 STD SS VK7766 2 440 435886023 SCREW M3 BUTTON HD SKT SS 4 8mm LG VK7766 450 P109701 SUPPORT PCB 2 460 P109878 BRACKET FRONT MOUNTING 1 ATTACHING PARTS 470 4358900...

Page 101: ...F 1B SA112457 BRACKET ASSEMBLY 1 10 P112281 BRACKET BEACON RH 1 P112454 PLATE CONNECTING 1 P112458 PLATE CONNECTING 1 435460630 SCREW M4 x 6mm CSK HD SS 2 20 P112298 FOOT RETENTION RH 1 30 250208135 PIN ROLL 1 5mm DIA x 10mm LG 2 ATTACHING PARTS 40 435890001 SCREW M5 x 10mm BTN HD 2 50 680150161 WASHER M5 PLAIN 6 60 P112304 SCREW RETENTION 2 70 P111197 PLATE RETENTION 1 80 P112305 FOOT RETENTION L...

Page 102: ...ESCRIPTION 1 1 1 General The Cockpit Control Unit Type D51616 XXXX forms part of the aircraft Combined Voice and Flight Data Recording System and is usually installed in the cockpit The unit is a panel mounted enclosure containing the Area Microphone Pre amplifier provision for an integral or externally mounted Area Microphone a Headphone jack socket together with pushbuttons and indicators for th...

Page 103: ...sts of a metal frame to which the printed circuit board and the front panel are fixed The electronics are protected from mechanical damage by a metal dust jacket The front panel assembly consists of a metal support plate to which the front panel assembly is fixed The integral microphone if fitted together with the indicators switches and the headset jack socket are fixed to this combined assembly ...

Page 104: ...IC No 1 SHIELD 5 24 AWG SCREENED TWISTED TRIPLE 1 RESERVED INTERNAL MIC No 1 BIAS 6 N C RESERVED INTERNAL MIC No 1 HI 7 N C RESERVED INTERNAL MIC No 1 HI 8 N C OUTPUT TO CHANNEL 4 LO 9 24 AWG SCREENED TWISTED PAIR 3 OUTPUT TO CHANNEL 4 HI 10 24 AWG SCREENED TWISTED PAIR 3 RESERVED CVR FAULT No 2 11 N C RESERVED FDR FAULT No 2 12 N C CVR FAULT No 1 13 24 AWG FDR FAULT No 1 14 24 AWG RESERVED AUDIO ...

Page 105: ...ntrol Unit Type D51616 2XXX Connector Details for Dual DAFR Installation Support Remote Mic FUNCTION 37 PIN CONN CABLE REQUIREMENTS RESERVED REMOTE MIC No 2 SHIELD 1 N C RESERVED REMOTE MIC No 2 LO 2 N C REMOTE MIC No 1 BIAS 3 24 AWG SCREENED TWISTED TRIPLE 1 REMOTE MIC No 1 HI 4 24 AWG SCREENED TWISTED TRIPLE 1 REMOTE MIC No 1 SHIELD 5 24 AWG SCREENED TWISTED TRIPLE 1 RESERVED INTERNAL MIC No 1 B...

Page 106: ...TCH 24dB 26 24 AWG AUDIO MONITOR INPUT LO 27 24 AWG SCREENED TWISTED PAIR 4 AUDIO MONITOR INPUT HI 28 24 AWG SCREENED TWISTED PAIR 4 AUDIO MONITOR No 2 LO 29 24 AWG SCREENED TWISTED PAIR 2 PUSH TO TEST 30 24 AWG ERASE SWITCH C 31 24 AWG ERASE SWITCH A 32 24 AWG LIGHTING 28V 33 24 AWG RESERVED LIGHTING 34 24 AWG LIGHTING COMMON 35 24 AWG LIGHTING 5V 36 24 AWG FDR INHIBIT B 37 24 AWG 1 2 2 Installat...

Page 107: ...control inputs to give attenuation of between 0dB and 42dB c 24dB ATTENUATION Connect to ATTENUATION COMMON to attenuate microphone input signal by 24dB May be used in addition to the 6dB and 12dB ATTENUATION control inputs to give attenuation of between 0dB and 42dB d ATTENUATION COMMON See a to c above e CVR FAULT High causes the CVR FAIL indicator to be extinguished f FDR FAULT High causes the ...

Page 108: ...Normally connected to aircraft interlocks such that interlocks are open circuit when aircraft can move under its own power and ground when not capable of moving If interlocks or function not implemented leave open circuit 1 2 4 Equipment Outputs Control Outputs a PUSH TO TEST Normally open circuit but is connected to CHASSIS GROUND when TEST pushbutton is depressed b ERASE SWITCH A Normally connec...

Page 109: ... µPa Harmonic Distortion at 1kHz Less than 10 for SPL at 120dB over 20 µPa Polar Response Ratio of front to 60 degrees response less than 6dB range Ratio of front to rear response 10dB Microphone Preamplifier Frequency Response 150Hz to 10kHz 6dB range Continuous decrease in output level outside this range Harmonic Distortion at Maximum Gain over 150Hz to 8kHz Less than 5 for input level equivalen...

Page 110: ...ion Support Figure 18 Cockpit Control Unit Part Number Options DAFR Installation Support Option 1 Single DAFR Option 2 Dual DAFR installation AREA Microphone Option 0 External Cockpit Area Microphone Option 1 Internal Cockpit Area Microphone Front Panel Indicator Options Various indicator options are available as follows Option 1 Yellow Night Vision Goggle compatible to MIL L 85762A Option 2 Yello...

Page 111: ...nel dimensions 28 2mm H x 145 8mm W x 63 0mm D excluding connector Connector DCM37P or equivalent 1 3 3 Environmental Characteristics The CCU and CAM satisfies the requirements of RTCA DO 160D with test categories as shown in Table 12 SECTION REQUIREMENT CCU CAM 4 Temperature Altitude A2 5 Temperature Variation C 6 Humidity A 7 Operational Shock Crash Safety B 8 Vibration U zone 2 curves F F1 S zo...

Page 112: ... an applied sound pressure level of 50 dB above 20 Pa 3 The microphone pre amplifier Signal to Noise ratio may be reduced to 35 dB under this test condition For the CAM the test level for radiated susceptibility shall be 2V m from 30 MHz to 1 215 GHz For the CAM the test level for conducted susceptibility shall be 3 mA 2V m from 500 kHz to 400 MHz and from 500 kHz to 10 kHz shall fall at the rate ...

Page 113: ...TYPE D51616 XXXX TO ENSURE THAT THE UNIT DOES NOT SUFFER UNDUE SHOCK The installation detail for the Control Unit depends on case configuration and is detailed in Figure 19 and Figure 20 4 1 WIRING The recommended minimum wiring sizes are shown in Table 10 for CCU Type D51616 1XXX and Table 11 for CCU Type D51616 2XXX These sizes are applicable for runs of up to 100 metres For variants with an Int...

Page 114: ...ated Parts List Commercial in Confidence PIM434 I Penny Giles Aerospace Ltd No part of this work may be reproduced or distributed by any means without prior permission in writing from the copyright owner 4 3 POWER SUPPLY The Cockpit Control Unit is designed to be powered from the CVR Recorder derived Pre Amp supply This supply is nominally 12VDC 5 or 18VDC 5 with maximum current of 100mA ...

Page 115: ...AM Type D51623 XXXX Installation and Operating Manual with Illustrated Parts List Commercial in Confidence PIM434 I Penny Giles Aerospace Ltd No part of this work may be reproduced or distributed by any means without prior permission in writing from the copyright owner Figure 19 Cockpit Control Unit with Single DAFR Support ...

Page 116: ...CAM Type D51623 XXXX Installation and Operating Manual with Illustrated Parts List Commercial in Confidence PIM434 I Penny Giles Aerospace Ltd No part of this work may be reproduced or distributed by any means without prior permission in writing from the copyright owner Figure 20 Cockpit Control Unit with Dual DAFR support ...

Page 117: ...hout prior permission in writing from the copyright owner 5 MAINTENANCE The concept of on condition maintenance applies to the Cockpit Control Unit 6 REPAIR The Cockpit Control Unit may be repaired at third line 7 FAULT FINDING The unit must be returned to Penny Giles Aerospace Limited for repairs NOTE It is advisable that headphones are not plugged into the Control Unit jack socket during the app...

Page 118: ...ogue voltage signals The active element of the microphone is housed in anti vibration rubber which itself is housed in a two part epoxy body Two bushes are provided on the bottom surface to aide mounting 1 2 OPERATION The Remote Microphone can be mounted in a suitable location in the cockpit as the main audio source 1 3 SPECIFICATION 1 3 1 Functional Characteristics Performance Frequency Response ...

Page 119: ...Termination 001 MIL C38999 Connector fitted If only three digits after D51623 Colour Semi Mat Black To FED STAN 595A 37038 1 Medium Gunship Grey FED STD 595 36118 Figure 21 CAM Part Number Options Figure 22 D51702 Part Number Options 1 4 COMPATIBILITY INTERFACES The Remote Microphone functions in accordance with the performance specification of ED 56A Amendment 1 See ARINC 757 Appendices 1 2 for g...

Page 120: ...HONE TYPE D51623 XXXX OR TYPE D51702 XX TO ENSURE THAT THE UNIT DOES NOT SUFFER UNDUE SHOCK The installation details for the Remote Microphone are detailed in Installation Drawing Figure 23 Outline dimensions and fixing centres for the Remote Microphone are shown in ARINC 757 Attachment 18 2 1 WIRING The recommended minimum wiring sizes are shown in Table 13 for the remote Area Microphone The elec...

Page 121: ...ence PIM434 I Penny Giles Aerospace Ltd No part of this work may be reproduced or distributed by any means without prior permission in writing from the copyright owner 2 3 BONDING Recommended Fit the earth bonding lead to the CAM housing bonding pad with the retaining screw Tighten the retaining screw to the correct loading lbf Carry out an earth bonding test to establish that the bonding is withi...

Page 122: ... CAM Type D51623 XXXX Installation and Operating Manual with Illustrated Parts List Commercial in Confidence PIM434 I Penny Giles Aerospace Ltd No part of this work may be reproduced or distributed by any means without prior permission in writing from the copyright owner Figure 23 Installation Drawing For Remote Microphone ...

Page 123: ...stallation and Operating Manual with Illustrated Parts List Commercial in Confidence PIM434 I Penny Giles Aerospace Ltd No part of this work may be reproduced or distributed by any means without prior permission in writing from the copyright owner Figure 24 Installation Drawing For D51702 XX Remote Microphone Figure 25 Preferred Locations for CAM ...

Page 124: ...buted by any means without prior permission in writing from the copyright owner Figure 26 Microphone Spacing 3 STORAGE The Area Microphone is delivered in a standard Penny Giles Aerospace Ltd trade container unless otherwise negotiated with the Customer and should remain in this container until required for use With the units packaged as received the storage life will be 36 months over the tempera...

Page 125: ...NG CAUTION CARE MUST BE TAKEN WHEN UNPACKING AND HANDLING THE AREA MICROPHONE TYPE D51623 XXXX TO ENSURE THAT THE UNIT NOT SUFFER UNDUE SHOCK The Area Microphone is packed in a Penny Giles standard trade container unless otherwise negotiated with the Customer The unit should not be removed from the packaging until required for use When unpacking the unit care should be taken to ensure that it does...

Page 126: ...6 XXXX and CAM Type D51623 XXXX Installation and Operating Manual with Illustrated Parts List Commercial in Confidence PIM434 I Penny Giles Aerospace Ltd No part of this work may be reproduced or distributed by any means without prior permission in writing from the copyright owner THIS PAGE IS INTENTIONALLY BLANK ...

Page 127: ...nd shall not be responsible for any loss cost or damage including consequential damage caused by decisions based on information in this manual Penny Giles Aerospace Limited is a business unit of Curtiss Wright Controls UK Ltd Penny Giles Aerospace Ltd 1 Airfield Road Christchurch Dorset BH23 3TH United Kingdom Telephone 01202 409409 Fax 01202 484846 ...

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