L-3 COMMUNICATIONS FA2100 CVDR ICA Supplement

Transcription

1 CESSNA AIRCRAFT COMPANY AIRCRAFT DIVISION WICHITA, KANSAS L-3 COMMUNICATIONS FA2100 CVDR ICA Supplement MODEL NO: 208/208B SUPPLEMENT NO: ICA SUPPLEMENT DATE: 03/30/2010 PREPARED BY: CHECKED BY: APPROVED BY: APPROVED BY: APPROVED BY: JAR JAR ACW ACW BAM BAM MDM MDM NLC NLC

2 Cessna Aircraft Company Page i REVISIONS Rev Date By Approved By - 03/30/2010 JAR See Title Sheet ECR Section Description L-3 Communications FA2100 CVDR ICA Supplement All Initial Release Rev Date By Approved By A 05/25/2010 JAR ACW ACW BAM MDM NLC BAM MDM NLC ECR Section , 6.1.2, Description Beginning Effectivity in Table 1, 524 was EC Beginning Effectivity in Table 1, 2226 was EC R0X was X.cfg Add recommended maintenance procedures and time intervals. Added the text is non-essential and and Refer to Section 5.1 for recommended practices. to the second paragraph.

3 Cessna Aircraft Company Page ii Rev Date By Approved By B 07/26/2010 JAR ACW BAM MDM NLC ECR Section Description 2.2.1, P/N 165E Rev 4 or later was P/N 165E , P/N 165E Rev 3 or later was P/N 165E , 6.1.2, 6.3 P/N Rev D or later was P/N Added Garmin G1000 Integrated Flight Deck Pilot's Guide for the Cessna Caravan (P/N or later). 6.2 Refer to Section 5.1 of this supplement. was Refer to L-3 Communications FA2100 CVDR Installation and Operation Instruction Manual (P/N 165E ) and Garmin G1000 Integrated Flight Deck Line Maintenance Manual for the Cessna Caravan (P/N ). 6.3 Refer to Garmin G1000 Integrated Flight Deck Pilot's Guide for the Cessna Caravan (P/N or later). was Refer to Garmin G1000 Integrated Flight Deck Line Maintenance Manual for the Cessna Caravan (P/N ).

4 Cessna Aircraft Company Page iii CONTENTS Section / Title Page REVISIONS... i CONTENTS... iii TABLES... v FIGURES... v 1. INTRODUCTION HEADING Purpose APPLICABILITY Effectivity Complete ICA Documents DESCRIPTION AND OPERATION System Description System Operation CVDR System Major Components and Locations CVDR System Major Components CVDR Major Component Locations Aircraft Wiring Avionics and Electrical Wiring System Software Requirement REMOVAL AND INSTALLATION FA2100 Cockpit Voice and Data Recorder Remove the FA2100 Cockpit Voice and Data Recorder Install the FA2100 Cockpit Voice and Data Recorder GSD41 Data Concentrator Unit Remove the GSD41 Data Concentrator Unit Install the GSD41 Data Concentrator Unit Area Microphone Remove the Area Microphone Install the Area Microphone Axis Accelerometer Remove the 3-Axis Accelerometer

5 Cessna Aircraft Company Page iv Install the 3-Axis Accelerometer Impact Switch Remove the Impact Switch Install the Impact Switch Audio Summing Amplifiers Remove the Audio Summing Amplifiers Install the Audio Summing Amplifiers Flap Potentiometer Remove the Flap Potentiometer Install the Flap Potentiometer MAINTENANCE AND SPECIAL TOOLS Maintenance FA2100 CVDR System Special Tools FA2100 CVDR Test Equipment System Wiring TESTING, RETURN TO SERVICE AND TROUBLESHOOTING Adjustment/Test Adjustment Test Inspection/Check Troubleshooting AIRWORTHINESS LIMITATIONS Limitations and Replacement Intervals Mandatory replacement times Mandatory inspection intervals Mandatory inspection procedures ATTACHMENT 1: Wiring Diagram FA2100 CVDR ATTACHMENT 2: Wiring Diagram GSD41 Data Concentrator Unit ATTACHMENT 3: Configuration Drawing FA2100 CVDR Option ATTACHMENT 4: Configuration Drawing Flap Potentiometer ATTACHMENT 5: FA2100 CVDR / PC (LAPTOP) INTERFACE... 34

6 Cessna Aircraft Company Page v TABLES Table / Title Page Table 1: L-3 Communications FA2100 CVDR Installation ICA Effectivity... 2 Table 2: CVDR Major Components... 6 Table 3: FA2100 CVDR System Test Equipment Table 4: Troubleshooting Symptoms and Recommended Actions FIGURES Figure / Title Page Figure 1: FA2100 CVDR (w/uld)... 3 Figure 2: FA2100 CVDR System Interconnect... 5 Figure 3: Major Component Locations... 6 Figure 4: FA2100 CVDR Installation... 8 Figure 5: Area Microphone Installation Figure 6: 3-Axis Accelerometer Installation Figure 7: Impact Switch Installation Figure 8: Audio Summing Amplifiers Installation Figure 9: Flap Potentiometer Installation... 18

7 Cessna Aircraft Company Page 1 1. INTRODUCTION HEADING 1.1. Purpose The purpose of this Instructions for Continued Airworthiness Supplement is to provide the maintenance technician with the information necessary to ensure the correct functionality and performance of the L-3 Communications FA2100 Cockpit Voice and Data Recorder (CVDR) system on the Cessna Models 208/208B This supplemental document is designed to satisfy CFR Instructions for Continued Airworthiness requirements associated with this installation. This document is a supplement to the Model 208/208B Maintenance Manual and may or may not be incorporated If this information is incorporated into the Model 208/208B Maintenance Manual, the maintenance manual shall take precedence over this supplemental document. Refer to applicable ATA chapter and section of the latest Maintenance Manual for the status of all ICA Supplements applicable to your model. NOTE: This document must be placed with the aircraft operator s Technical Library CD- ROM or Maintenance Manual and incorporated into the operator s scheduled maintenance program.

8 Cessna Aircraft Company Page 2 2. APPLICABILITY 2.1. Effectivity This Instructions for Continued Airworthiness (ICA) supplement is effective for the following aircraft model(s) and serialization where this L-3 Communications FA2100 CVDR System is installed: Model Beginning Effectivity Ending Effectivity and On 208B 2226 and On Table 1: L-3 Communications FA2100 CVDR Installation ICA Effectivity 2.2. Complete ICA Documents The following document(s), in conjunction with this supplement, constitute the Instructions for Continued Airworthiness for the L-3 Communications FA2100 CVDR system. All items must be available to the operator at initial delivery. Garmin G1000 Integrated Flight Deck Cockpit Reference Guide for the Cessna Caravan (P/N or later). On-board requirement for flight. Garmin G1000 Integrated Flight Deck Pilot's Guide for the Cessna Caravan (P/N or later). L-3 Communications FA2100 CVDR Installation and Operation Instruction Manual (P/N 165E ). L-3 Communications Portable Interface (PI) Operator s Manual (P/N 165E Rev 4 or later). L-3 Communications ROSE / RI Software Version 3.0 or Higher Operator s Manual (P/N 165E Rev 3 or later). Garmin GSD41 Data Concentrator Installation Manual (P/N ). Garmin G1000 Integrated Flight Deck Line Maintenance Manual for the Cessna Caravan (P/N Rev D or later). Model 208/208B Maintenance Manual. Model 208/208B Wiring Diagram Manual. Model 208/208B Aircraft Serial Wiring Diagram CD ROM.

9 Cessna Aircraft Company Page 3 3. DESCRIPTION AND OPERATION 3.1. System Description The L-3 Communications FA2100 Cockpit Voice and Data Recorder (CVDR) System as installed in the Cessna models 208/208B consists of one each FA2100 CVDR, area microphone, GSD41 Data Concentrator Unit (DCU), 3-axis accelerometer, 5g impact switch, flap potentiometer, and two audio summing amplifiers. The components are listed in Table 2. The FA2100 CVDR is a single LRU that provides both cockpit voice recorder (CVR) and flight data recorder (FDR) functions. The CVDR is housed in an international orange, ARINC 404A, ½ - ATR short case with two reflective strips and meets the requirements of FAA TSO C123a and C124a. An Underwater Locator Device (ULD), also referred to as an underwater acoustic beacon, is mounted on the front of the CVDR and meets the requirements of FAA TSO C121. The CVDR records 120 minutes of high quality audio on each of four audio channels and 25 hours of flight data at a rate of 64, 128, or 256 words per second. A Ground Support Equipment (GSE) connector is located on the front of the CVDR and is used to download recorded audio and flight data to a readout device (portable interface, computer, laptop, etc.). Reference Figure 1. The accelerometer, summing amplifiers, and CVDR operate from 28Vdc supplied from the aircraft s Electrical bus. Power to the CVDR first passes through the system s impact switch. The impact switch interrupts power to the CVDR and stops the recording of data in the event of a crash to prevent recording over the data recorded prior to the crash. The GSD41 operates from 28Vdc supplied from the aircraft s Avionics Bus 1. Figure 1: FA2100 CVDR (w/uld)

10 Cessna Aircraft Company Page System Operation The L-3 Communications FA2100 Cockpit Voice and Data Recorder (CVDR) System provides dual operational functions; cockpit voice recording (CVR) and flight data recording (FDR). The CVDR contains four designated audio channels that each record 120 minutes of high quality audio. Channel one records all audio coming over the cabin and PA speakers. Channel two records all incoming/outgoing audio from the copilot s headset after being passed through a summing amplifier. Channel three records all incoming/outgoing audio from the pilot s headset and cabin handheld PTT microphone after being passed through a separate summing amplifier from that of the copilot. Channel four records all audio being picked up by the area microphone located on the instrument panel, above the audio panel bezel. Greenwich Mean Time (GMT) is provided to the CVDR via ARINC 429 from GIA1 and recorded simultaneously with audio. Flight data from the G1000 System is provided to the CVDR from the GSD41 Data Concentrator Unit. PFD1 sends flight data, including flap position and accelerometer data from the GEA, via Garmin s proprietary High Speed Data Bus (HSDB), to the GSD41. The data is then converted to ARINC 717 by the GSD41 and sent to the CVDR for recording. The FA2100 CVDR initiates a built-in-test (BIT) function at power up that continuously monitors the unit for fault conditions. In the event that a fault is detected, the CVDR will trigger the annunciation of CAS advisory messages, CVD FAIL and/or FDR FAIL on the G1000 display(s) via separate discrete I/Os dependent on the fault detected. The FA2100 CVDR System interface to the G1000 System is shown in Figure 2. Recorded audio and flight data from the CVDR can be downloaded and analyzed using a laptop. Attachment 5 shows the interface between the CVDR and a laptop containing ROSE software version 3.8 or higher. The latest ROSE aircraft configuration file in accordance to Cessna drawing (file R0X) defines the recorded flight paramaters and is necessary to properly interpret the data.

11 Cessna Aircraft Company Page 5 Figure 2: FA2100 CVDR System Interconnect

12 Cessna Aircraft Company Page CVDR System Major Components and Locations CVDR System Major Components The Cockpit Voice and Data Recorder System consists of the following major components: Component Manufacturer Qty Part Number Location FA2100 Cockpit Voice and Data Recorder (CVDR) w/uld L-3 Communications Top shelf in tailcone Area Microphone L-3 Communications 1 S Instrument panel GSD41 Data Concentrator Unit Garmin International Bottom shelf in tailcone 3-Axis Accelerometer Magnetek Left cabin overhead by wing root. 5-G Impact Switch Aerodyne Controls D-2-X-5-5 Top shelf in tailcone Audio Summing Amplifier Baker Electronics Inc. 2 M1090 Forward side of pedestal Flap Potentiometer Voltronics Inc. 1 V Left cabin overhead, right of accelerometer. Table 2: CVDR Major Components CVDR Major Component Locations Figure 3 below illustrates the aircraft locations of the major components listed in Table 2. Figure 3: Major Component Locations

13 Cessna Aircraft Company Page Aircraft Wiring Avionics and Electrical Wiring Refer to the Model 208/208B Aircraft Serial Wiring Diagram CD ROM provided with each aircraft for a listing and illustration of all Avionics/Electrical system wiring diagrams installed specifically in that aircraft. Reference Attachments 1 and 2 for Avionics/Electrical wiring diagrams and for the CVDR System System Software Requirement. The L-3 Communications FA2100 CVDR System requires G1000 System software version or later.

14 Cessna Aircraft Company Page 8 4. REMOVAL AND INSTALLATION NOTE: The following procedures are for reference only. Make sure that the aircraft is configured for maintenance as defined by the associated system in the maintenance manuals listed in Section 2.2.1, including the removal of electrical power, avionics power, etc., prior to removal or installation of aircraft components. For each installation performed, visually inspect and verify there are no nicks, dents, or scratches on the equipment that might have occurred during installation, and that all connectors are properly installed. Check all cables for proper routing and tiedown and attach points. Especially check that equipment/cables do not interfere with aircraft controls or other equipment. Check that connectors are not strained due to cable routing or tie-down points FA2100 Cockpit Voice and Data Recorder Remove the FA2100 Cockpit Voice and Data Recorder. 1. Remove electrical power from the aircraft. 2. Disengage the CVDR circuit breaker on the electrical circuit breaker panel. 3. Access the FA2100 CVDR, located on the aft top avionics shelf in the tailcone of the aircraft, by removing the rear compartment wall. Reference Chapter Rear Compartment Wall Maintenance Practices in the aircraft maintenance manual. 4. Loosen the knurl nuts and unlatch the locking mechanism located on the front of the FA2100 CVDR mounting tray as shown in Figure 4. Figure 4: FA2100 CVDR Installation

15 Cessna Aircraft Company Page 9 5. Carefully pull the FA2100 CVDR straight forward from its mounting tray and remove it from the aircraft, leaving the connector and wiring attached to the mounting tray Install the FA2100 Cockpit Voice and Data Recorder. 1. Ensure electrical power is removed from the aircraft. 2. Ensure the CVDR circuit breaker on the electrical circuit breaker panel is disengaged. 3. Access the FA21000 CVDR mounting tray, located on the aft top avionics shelf in the tailcone of the aircraft, by removing the rear compartment wall. Reference Chapter Rear Compartment Wall Maintenance Practices in the aircraft maintenance manual. 4. Carefully slide the FA21000 CVDR into its mounting tray until the connector is firmly engaged. 5. Secure the FA2100 CVDR in the mounting tray by latching the locking mechanism and tightening the knurl nuts as shown in Figure Engage the CVDR circuit breaker and restore electrical power to the aircraft. 7. Test the FA2100 CVDR per Section Reinstall rear compartment wall GSD41 Data Concentrator Unit Remove the GSD41 Data Concentrator Unit. 1. Remove electrical power from the aircraft. 2. Disengage the DCU circuit breaker on the avionics circuit breaker panel. 3. Access the GSD41, located on the aft bottom avionics shelf in the tailcone of the aircraft, by removing the rear compartment wall. Reference Chapter Rear Compartment Wall Maintenance Practices in the aircraft maintenance manual. 4. Remove the GSD41 from the aircraft per the Garmin G1000 Line Maintenance Manual referenced in Section Install the GSD41 Data Concentrator Unit. 1. Ensure electrical power is removed from the aircraft. 2. Ensure the DCU circuit breaker on the avionics circuit breaker panel is disengaged.

16 Cessna Aircraft Company Page Access the GSD41 mounting rack, located on the aft bottom avionics shelf in the tailcone of the aircraft, by removing the rear compartment wall. Reference Chapter Rear Compartment Wall Maintenance Practices in the aircraft maintenance manual. 4. Install the GSD41 per the Garmin G1000 Line Maintenance Manual referenced in Section Engage the DCU circuit breaker and restore electrical power to the aircraft. 6. If the GSD41 was returned for service or is a new unit, reload software (v or later) per the Garmin G1000 Line Maintenance Manual referenced in Section Test the GSD41 per Section Reinstall rear compartment wall Area Microphone Remove the Area Microphone. 1. Remove electrical power from the aircraft. 2. Disengage the CVDR circuit breaker on the electrical circuit breaker panel. 3. Access the area microphone located on the forward side of the G1000 Instrument Panel above the GMA1347 Audio Panel. Reference the aircraft maintenance manual in Section for accessibility. 4. Disconnect connector PI527 from JI527. Reference wiring diagram in Attachment Remove the two screws (P/N MS ) that secure the area microphone to the bracket riveted to the instrument panel as shown in Figure 5.

17 Cessna Aircraft Company Page 11 Figure 5: Area Microphone Installation 6. Remove the area microphone from the aircraft Install the Area Microphone. 1. Ensure electrical power is removed from the aircraft. 2. Ensure the CVDR circuit breaker on the electrical circuit breaker panel is disengaged. 3. Access the forward side of the G1000 Instrument Panel and locate the microphone mounting bracket above the GMA1347 Audio Panel. Reference the aircraft maintenance manual in Section for accessibility. 4. Install and secure the area microphone to the bracket using the two screws (P/N MS ) as shown in Figure Connect connector PI527 to JI527. Reference wiring diagram in Attachment Reinstall all parts and equipment removed for accessibility in Step 3 per the aircraft maintenance manual. 7. Engage the CVDR circuit breaker and restore electrical power to the aircraft.

18 Cessna Aircraft Company Page Test the area microphone per Section Axis Accelerometer Remove the 3-Axis Accelerometer. 1. Remove electrical power from the aircraft. 2. Disengage the CVDR circuit breaker on the electrical circuit breaker panel. 3. Access the 3-axis accelerometer, located on the left hand fuselage root rib assembly wing intersection, by removing the hard shell headliner panel. Reference Chapter Cabin Upholstery Maintenance Practices in the aircraft maintenance manual. 4. Disconnect connector PC302 from the 3-axis accelerometer. Reference wiring diagram in Attachment Remove the three screws (P/N MS ) that secure the 3-axis accelerometer to the bracket as shown in Figure 6. Figure 6: 3-Axis Accelerometer Installation 6. Remove the 3-axis accelerometer from the aircraft.

19 Cessna Aircraft Company Page Install the 3-Axis Accelerometer. 1. Ensure electrical power is removed from the aircraft. 2. Ensure the CVDR circuit breaker on the electrical circuit breaker panel is disengaged. 3. Access the accelerometer bracket, located on the left hand fuselage root rib assembly wing intersection, by removing the hard shell headliner panel. Reference Chapter Cabin Upholstery Maintenance Practices in the aircraft maintenance manual. 4. Install and secure the 3-axis accelerometer to the bracket using the three screws (P/N MS ) as shown in Figure Connect connector PC302 to the 3-axis accelerometer. Reference wiring diagram in Attachment Engage the CVDR circuit breaker and restore electrical power to the aircraft. 7. Test the 3-axis accelerometer per Section Reinstall the hard shell headliner panel Impact Switch Remove the Impact Switch. 1. Remove electrical power from the aircraft. 2. Disengage the CVDR circuit breaker on the electrical circuit breaker panel. 3. Access the impact switch, located under the aft top avionics shelf in the tailcone of the aircraft, by removing the rear compartment wall. Reference Chapter Rear Compartment Wall Maintenance Practices in the aircraft maintenance manual. 4. Disconnect connector PT305 from the impact switch. Reference wiring diagram in Attachment Remove the four screws (P/N MS ) and spacers (P/N NAS43DD3-8FC) that secure the impact switch under the aft top avionics shelf as shown in Figure 3.

20 Cessna Aircraft Company Page 14 Figure 7: Impact Switch Installation 6. Remove the impact switch from the aircraft Install the Impact Switch. 1. Ensure electrical power is removed from the aircraft. 2. Ensure the CVDR circuit breaker on the electrical circuit breaker panel is disengaged. 3. Access the aft top avionics shelf, located in the tailcone of the aircraft, by removing the rear compartment wall. Reference Chapter Rear Compartment Wall Maintenance Practices in the aircraft maintenance manual. 4. Install and secure the impact switch under the aft top avionics shelf using the four screws (P/N MS ) and spacers (P/N NAS43DD3-8FC) as shown in Figure Connect connector PT305 to the impact switch. Reference wiring diagram in Attachment Engage the CVDR circuit breaker and restore electrical power to the aircraft. 7. Test the impact switch per Section Reinstall rear compartment wall.

21 Cessna Aircraft Company Page Audio Summing Amplifiers Remove the Audio Summing Amplifiers. 1. Remove electrical power from the aircraft. 2. Disengage the CVDR circuit breaker on the electrical circuit breaker panel. 3. Access the audio summing amplifiers located on the forward side of the pedestal. The pedestal is located between the pilot and co-pilot seats. Reference Chapter Pedestal Description and Operation in the aircraft maintenance manual. 4. Disconnect connector(s) PI528 and/or PI529 as necessary from the audio summing amplifiers. Reference wiring diagram in Attachment 1 and Figure Remove the screws (P/N MS ) and washers (P/N NAS1149FN632P), four per unit. that secure the audio summing amplifier(s) to the bracket on the pedestal as shown in Figure 8.

22 Cessna Aircraft Company Page 16 Figure 8: Audio Summing Amplifiers Installation 6. Remove the audio summing amplifier(s) from the aircraft Install the Audio Summing Amplifiers. 1. Ensure electrical power is removed from the aircraft. 2. Ensure the CVDR circuit breaker on the electrical circuit breaker panel is disengaged. 3. Access the amplifier mounting bracket located on the forward side of the pedestal. The pedestal is located between the Pilot and Co-pilot seats. Reference Chapter Pedestal Description and Operation in the aircraft maintenance manual.

23 Cessna Aircraft Company Page Install and secure the audio summing amplifier(s) to the bracket on the pedestal using the screws (P/N MS ) and washers (P/N NAS1149FN632P), four per unit, as shown in Figure Connect connector(s) PI528 and/or PI529 as necessary to the left and right audio summing amplifiers, respectively. Reference wiring diagram in Attachment 1 and Figure Engage the CVDR circuit breaker and restore electrical power to the aircraft. 7. Test the audio summing amplifiers per Section Flap Potentiometer Remove the Flap Potentiometer. 1. Remove electrical power from the aircraft. 2. Disengage the CVDR circuit breaker on the electrical circuit breaker panel. 3. Access the flap potentiometer, located near the flap interconnect rod assembly between the left and right wings in the overhead compartment, by removing the hard shell headliner panel. Reference Chapters Cabin Upholstery Maintenance Practices and Flap System Maintenance Practices in the aircraft maintenance manual. 4. Disconnect connector JC303 from PC303. Reference wiring diagram in Attachment Loosen the two set screws (P/N AN565D4H3) that attach the lever assembly to the potentiometer shaft as shown in Figure Loosen or remove the three screws (P/N MS ) that hold the potentiometer to the bracket assembly as shown in Figure Turn, if not removed in previous step, the three mount cleats (P/N L3-7) so that the potentiometer can be easily removed from the bottom of the bracket assembly as shown in Figure 9.

24 Cessna Aircraft Company Page 18 Figure 9: Flap Potentiometer Installation 8. Remove the potentiometer from the airplane. Note: The potentiometer lever assembly shown in Figure 9 must be properly secured or removed if the flap system will be used prior to re-installing the potentiometer Install the Flap Potentiometer. 1. Ensure electrical power is removed from the aircraft. 2. Ensure the CVDR circuit breaker on the electrical circuit breaker panel is disengaged. 3. Access the potentiometer bracket assembly, located near the flap interconnect rod assembly between the left and right wings in the overhead compartment, by

25 Cessna Aircraft Company Page 19 removing the hard shell headliner panel. Reference Chapters Cabin Upholstery Maintenance Practices and Flap System Maintenance Practices in the aircraft maintenance manual. 4. Install the potentiometer to the bracket assembly, ensuring the potentiometer shaft is properly fitted in the lever assembly, using the three screws (P/N MS ) and mount cleats (P/N L3-7) as shown in Figure 9. Do not tighten the screws yet. 5. Tighten the two set screws (P/N AN565D4H3) to secure the potentiometer shaft to the lever assembly as shown in Figure Connect connector JC303 to PC303. Reference wiring diagram in Attachment Engage the CVDR circuit breaker and restore electrical power to the aircraft. 8. Configure and test the flap potentiometer per configuration drawing in Attachment 4, ensuring screws and mount cleats referenced in Step 4 have been tightened before continuing. 9. Reinstall the hard shell headliner panel.

26 Cessna Aircraft Company Page MAINTENANCE AND SPECIAL TOOLS 5.1. Maintenance FA2100 CVDR System Preflight: Check that neither FDR FAIL or CVR FAIL messages are displayed on PFD1 and/or PFD2. If either message is displayed, refer to troubleshooting procedures listed in Section 6.3. Every 12 Months: Download and analyze at least one entire flight s data and audio recording. The operator must verify that the recorded values for each parameter being recorded and the quality of the audio are both acceptable with regards to the actual flight characteristics and communications that occurred during the recorded flight. Downloading and testing procedures are listed in Section of this report or in Section 4 of the L-3 Communications FA2100 CVDR Installation and Operation Instruction Manual (P/N 165E ). The latest ROSE aircraft configuration file in accordance to Cessna drawing (file R0X) can be obtained through Propeller Aircraft Customer Service at Every 2 Years: Visually inspect the FA2100 CVDR (and ULD), GSD41, accelerometer, potentiometer, impact switch, summing amplifiers, and area microphone for security of installation, undue deterioration and wear, corrosion or any other form of damage. Check that these components are clean and nameplates are legible. Visually inspect the associated electrical connectors and strain reliefs at the mounting trays. Check for cleanliness, unwarranted looseness, foreign material, properly installed clamp points, wire damage, and bend radius. Visually inspect the associated wiring for signs of wire degradation, evidence of broken, charred or corroded wiring. Look for evidence of: moisture or fluids contamination, wire discoloration due to contamination or heat, wire damage resulting from vibration (under clamps and tie straps), damage due to improper maintenance, and damage due to foreign material. If any wire degradation is detected, identify and eliminate the cause leading to wiring degradation. Repair/replace wiring as required, referring to the aircraft and system wiring Sections 3.4 and 5.3. The ULD and impact switch must also be tested. Refer to Section for ULD and impact switch testing procedures, and this Section, under maintenance interval Every 6 Years, for servicing (battery replacement) the ULD if necessary. Every 5 Years: The flap potentiometer must be adjusted/calibrated every five years or any time maintenance is performed on the aircraft s flap control system. Verification of

27 Cessna Aircraft Company Page 21 flap potentiometer operation is covered in the adjustment/calibration process. Refer to Section for adjustment/calibration procedures of the flap potentiometer. The 3-axis accelerometer is also to be tested for proper operation verification. Verify proper operation of the accelerometer per test procedures in Section Every 6 Years: The ULD is equipped with a battery that has an expected life of 6 years. The ULD is part of the FA2100 CVDR unit and is mounted on the front for easy removal. Refer to the L-3 Communications FA2100 CVDR Installation and Operation Instruction Manual (P/N 165E ) for instructions on servicing the ULD for battery replacement Special Tools FA2100 CVDR Test Equipment Table 3 provides a list of recommended equipment to test the FA2100 CVDR system per the procedures listed in Section 6.1. Similar or equivalent test equipment is permissible to use in place of the listed items. Note: Test equipment must be maintained and inspected periodically to ensure good working condition in accordance to the manufacture s recommendations and/or the Cessna Quality Control Manual (QCM). Equipment / Item Description / Part Number Ground Power Unit (GPU) 28 VDC PC or Laptop Must contain L-3 Read Out Support Equipment (ROSE) software version 3.8 or later installed, P/N 17TES0321. Yokogawa Voltage Tester Model or equivalent. Air Data Tester LAVERSAB Model 6500 or equivalent. Ultrasonic Test Set Dukane Model 42A12D, P/N or equivalent. Inclinometer Readout range of 0 to +35 o. IFR 6000 XPDR/DME Tester IFR 4000 NAV/VOR/GS Tester CAT5E Crossover Cable L-3 P/N or equivalent Portable Interface L-3 P/N 17TES0043 CICC/3 L-3 P/N 17TES0075 Table 3: FA2100 CVDR System Test Equipment 5.3. System Wiring Refer to the Wiring Diagram Manual, Chapter 20, Standard Practices - Airframe, for wiring maintenance requirements and practices. Refer to the Aircraft Serial Wiring Diagram CD ROM provided with the aircraft for all system wiring diagrams specific to that aircraft.

28 Cessna Aircraft Company Page TESTING, RETURN TO SERVICE AND TROUBLESHOOTING 6.1. Adjustment/Test Adjustment FA2100 CVDR System No adjustments to the L-3 FA2100 CVDR system are necessary, except the flap potentiometer. Flap Potentiometer Refer to Cessna configuration drawing in Attachment Test FDR /CVR Option Installed In configuration mode, go to the GDU-Airframe Configuration page on PFD1 and verify FDR / CVR appears in the Airframe window/field using the FMS knob. Reference the Garmin G1000 Integrated Flight Deck Line Maintenance Manual for the Cessna Caravan (P/N Rev D or later) for instructions on placing the G1000 into configuration mode. FA2100 CVDR Built-In-Test (BIT) Verify the absence of annunciated CAS advisory messages CVR FAIL and/or FDR FAIL at power up on PFD1 in normal mode. Pull CVDR circuit breaker on the Electrical circuit breaker panel and verify CVR FAIL and FDR FAIL CAS advisory messages annunciate on PFD1. Engage CVDR circuit breaker and verify both CAS advisory messages extinguish from PFD1. Pull DCU circuit breaker on the Avionics circuit breaker panel and verify FDR FAIL CAS advisory message annunciates on PFD1. Engage DCU circuit breaker and verify CAS advisory message extinguishes from PFD1. FA2100 CVDR System (CVR Operation) Refer to L-3 Communications Portable Interface (PI) Operator s Manual (P/N 165E Rev 4 or later) for instructions on operating the portable interface with the FA2100. Refer to Sub-section, CVR Function in Section 4 in L-3 Communications FA2100 CVDR Installation and Operation Instruction Manual (P/N 165E ) for instructions on testing the FA2100 CVR function with the portable interface.

29 Cessna Aircraft Company Page 23 FA2100 CVDR System (FDR Operation) Refer to L-3 Communications ROSE / RI Software Version 3.0 or Higher Operator s Manual (P/N 165E Rev 3 or later) for instructions on using ROSE software with the FA2100. Obtain latest ROSE aircraft configuration file in accordance to Cessna drawing (file R0X) through Propeller Aircraft Customer Service at Refer to Sub-section, FDR Function in Section 4 in L-3 Communications FA2100 CVDR Installation and Operation Instruction Manual (P/N 165E ) for instructions on testing the FA2100 FDR function using a laptop (or pc) containing ROSE software version 3.8 of later. Attachment 5 illustrates the interface between the FA2100 CVDR and a laptop. Analyze the data for correct operation using the laptop with ROSE software. If the FA2100 CVDR is removed from the aircraft, an additional assembly is required to power the FA2100 CVDR for downloading or directly reviewing recorded data. Underwater Locator Device (ULD) Refer to Appendix F in L-3 Communications FA2100 CVDR Installation and Operation Instruction Manual (P/N 165E ) for instructions on testing the ULD with the Dukane ultrasonic test set. If necessary, remove the four screws that secure the ULD to the FA2100 to remove the ULD and use a metal braid or other flexible conductor to temporarily short the ULD switch. GSD41 Data Concentrator Unit Refer to Garmin G1000 Integrated Flight Deck Line Maintenance Manual for the Cessna Caravan (P/N Rev D or later). 3-Axis Accelerometer In configuration mode with the aircraft sitting on level pavement, go to the GEA Status page on PFD1 and verify the following values. Values in parenthesis are ROSE output values and for reference only. o Analog Channel 2 In = 2.60 ± 0.25 (Longitudinal 0.00g ± 0.10) o Analog Channel 4 In = 2.60 ± 0.25 (Lateral 0.00g ± 0.10) o Analog Channel 6 In = 2.33 ± 0.25 (Vertical 1.00g ± 0.45) Reference the Garmin G1000 Integrated Flight Deck Line Maintenance Manual for the Cessna Caravan (P/N Rev D or later) for instructions on placing the G1000 in configuration mode.

30 Cessna Aircraft Company Page 24 Impact Switch Verify the light on the impact switch is off and no annunciated CAS advisory messages CVR FAIL and FDR FAIL are displayed at power up of PFD1. Trip the impact switch by gently tapping the top aft avionics shelf with a blunt object using a cloth or pad to protect the shelf from being scratched or damaged. Verify the light on the impact switch turns on and both CVR FAIL and FDR FAIL CAS advisory messages annunciate on PFD1. Reset the impact switch by pressing the reset button on the switch. Verify the light on the impact switch turns off and both CVR FAIL and FDR FAIL CAS advisory messages extinguish on PFD1. Area Microphone and Audio Summing Amplifiers Refer to FA2100 CVDR System (CVR Operation) test procedure listed in this section Inspection/Check Refer to Section 5.1 of this supplement Troubleshooting Note: The L-3 Communications FA2100 CVDR System requires G1000 System software version or later. Symptom Only FDR FAIL on PFD. Recommended Action Verify DCU circuit breaker is engaged. Verify operation and discrete input settings of GSD41. Refer to Attachment 2 and Section Check system wiring, connectors, and pins per Attachments 1 and 2. Reload FDR / CVR option per Attachment 3. Refer to Attachment 2. De-pin wire 32PT303-8JT307 at either end and temporarily stow. Apply ground to GSD41 through pin 32 of PT303. If message extinguishes, reconnect wire 32PT303-8JT307 and replace CVDR per Section 4.1.

31 Cessna Aircraft Company Page 25 Symptom Only CVR FAIL on PFD. FDR FAIL and CVR FAIL on PFD. Failed Data Path (Assuming CVDR related) Invalid Recorded Flight Data (Using ROSE) Recommended Action Verify operation and discrete input settings of GIA#1. Refer to Attachment 1 and Garmin G1000 Integrated Flight Deck Line Maintenance Manual for the Cessna Caravan (P/N Rev D or later). Check wiring, connectors, and pins between GIA connector PI507 and PT304 per Attachment 1. Reload FDR / CVR option per Attachment 3. Refer to Attachment 1. De-pin wire 44PI507-23PT304 at either end and temporarily stow. Apply ground to GIA through pin 44 of PI507. If message extinguishes, reconnect wire 44PI507-23PT304 and replace CVDR per Section 4.1. Verify CVDR and DCU circuit breakers are engaged. Verify light on impact switch is off. Reset and test switch if light is on. Refer to Section Verify operation and discrete input settings of GIA#1 and GSD41. Refer to Attachments 1 and 2, and Garmin G1000 Integrated Flight Deck Line Maintenance Manual for the Cessna Caravan (P/N Rev D or later). Check system wiring, connectors, and pins per Attachments 1 and 2. Reload FDR / CVR option per Attachment 3. If messages remain annunciated, replace CVDR per Section 4.1. Verify operation of GSD41 per Section Check GSD41 to PFD1 wiring, connectors, and pins per Attachment 2. Verify FDR / CVR option is installed per Section Verify ROSE software version is 3.8 or higher. Verify ROSE aircraft configuration file in accordance to Cessna drawing (file R0X) is being used. Verify operation of GSD41 per Section Verify validity of data from G1000 utilizing the system s Data Logging feature. Refer to Garmin G1000 Integrated Flight Deck Pilot's Guide for the Cessna Caravan (P/N or later). Check system wiring, connectors, and pins per Attachments 1 and 2.

32 Cessna Aircraft Company Page 26 Symptom Recommended Action Invalid Flap Position Data Verify FDR / CVR option is installed per Section Invalid Acceleration Data -Vertical -Lateral -Longitudinal Noise Present in Audio (Using ROSE and PI) Verify ROSE software version is 3.8 or higher. Verify ROSE aircraft configuration file in accordance to Cessna drawing (file R0X) is being used. Check GEA analog input and flap potentiometer configuration per Attachment 4. Check wiring, connectors, and pins between GEA connector PI002 to PC303 per Attachment 1. Verify resistance between pins 1 and 3 of JC303 is 5KΩ ±5%, and total resistance between pins 1and 2 and 2 and 3 is also 5KΩ ±5%. Refer to Attachment 1. Check wiring from JC303 is properly soldered at potentiometer. Replace potentiometer if necessary per Section 4.7. Verify FDR / CVR option is installed per Section Verify ROSE software version is 3.8 or higher. Verify ROSE aircraft configuration file in accordance to Cessna drawing (file R0X) is being used. Check GEA analog inputs and accelerometer values per Section Disconnect PC302 from accelerometer and verify values on GEA-Status page drop to zero (± 0.05). Check wiring, connectors, and pins between GEA connector PI001 to PC302 and verify 28Vdc at pin A of PC302 per Attachment 1. Replace accelerometer if necessary per Section 4.4. Channel 1 (Cabin and PA Speakers): Check audio quality over cabin speakers. Check audio quality over PA speakers. Check audio (cabin and PA speakers) wiring, connectors, and pins, if necessary. Refer to Section 3.4. Check wiring, connectors, and pins between Channel 1 of connector PT304 to PI500. Refer to Attachment 1. Channel 2 (Copilot): Check audio quality from copilot headset. Recheck with different headset, if necessary. Check audio (copilot headset) wiring, connectors, and pins, if necessary. Refer to Section 3.4.

33 Cessna Aircraft Company Page 27 Symptom Recommended Action Check wiring, connectors, and pins between Channel 2 of connector PT304 to PI529 to PI501. Refer to Attachment 1. Disconnect PI528 and PI529. Connect PI529 to pilot summing amplifier and check copilot headset audio quality over channel 3 with PI. Replace copilot summing amplifier if necessary per Section 4.6 and rewire per Attachment 1. Channel 3 (Pilot and Handheld PTT Mic): Check audio quality from pilot headset and handheld PTT microphone. Recheck with different headset and/or handheld PTT microphone, if necessary. Check audio (pilot headset and handheld mic) wiring, connectors, and pins, if necessary. Refer to Section 3.4. Check wiring, connectors, and pins between Channel 3 of connector PT304 to PI528 to PI501. Refer to Attachment 1. Disconnect PI528 and PI529. Connect PI528 to copilot summing amplifier and check pilot headset and handheld PTT microphone audio quality over channel 2 with PI. Replace pilot summing amplifier if necessary per Section 4.6 and rewire per Attachment 1. Channel 4 (Area Mic): Check wiring, connectors, and pins between Channel 4 of connector PT304 to JI527 to EI008. Refer to Attachment 1. Replace area microphone if necessary per Section 4.3. Table 4: Troubleshooting Symptoms and Recommended Actions

34 Cessna Aircraft Company Page AIRWORTHINESS LIMITATIONS 7.1. Limitations and Replacement Intervals Cessna Aircraft Company Model 208/208B Maintenance Manual, Chapter 4, Airworthiness Limitations, contains the system and airframe limitations for the Model 208/208B. NOTE: The Airworthiness Limitations section is FAA-approved and specifies maintenance required under Section and of Title 14 Code of Federal Regulations, unless an alternative program has been FAA approved. The FA2100 CVDR System is non-essential and has no mandatory replacement time, inspection interval, structural inspection procedures, or impact on the Cessna Aircraft Company Model 208/208B Maintenance Manual, Chapter 4 Airworthiness Limitations. Refer to Section 5.1 for recommended practices Mandatory replacement times. 1. None Mandatory inspection intervals. 1. None Mandatory inspection procedures. 1. None.

35 Cessna Aircraft Company Page 29 ATTACHMENT 1: Wiring Diagram FA2100 CVDR.

36 Cessna Aircraft Company Page 30

37 Cessna Aircraft Company Page 31 ATTACHMENT 2: Wiring Diagram GSD41 Data Concentrator Unit.

38 Cessna Aircraft Company Page 32 ATTACHMENT 3: Configuration Drawing FA2100 CVDR Option.

39 Cessna Aircraft Company Page 33 ATTACHMENT 4: Configuration Drawing Flap Potentiometer.

40 Cessna Aircraft Company Page 34 ATTACHMENT 5: FA2100 CVDR / PC (LAPTOP) INTERFACE