120-092-00 - Onboard Systems International
Contents
1. Cargo Hook Suspension System Removal 2 1 Cargo Hook Suspension System Installation 2 1 Load Weigh System Installation 2 11 Internal Harness Installation 2 11 C 39 Cockpit Indicator Installation 2 11 Indicator Internal Back Light 2 11 Indicator Hook Open Warning 2 12 Remote Analog Meter 2 12 Electrical Connections 2 12 Installation Check Out 2 13 Component Weights 2 13 Suspension System Location 2 14 Paper Work 2 14 Load Weigh Systems Operation Instructions Indicator Front Panel 3 1 The Run Mode 3 2 To Zero or Tare the Display 3 3 To Un Zero the Display 3 3 Error Codes 3 4 The Setup Mode 3 5 Indicator Dampening 3 7 To look at or change the dampening level 3 7 Indicator Calibration 3 7 To look at or change the calibration code 3 8 Installation Zero 3 9 To run the installation zero routine 3 9 Calibration by Lifting a Known Weight 3 9 To run calibration by known weight routine 3 10 Setting the Scale on a Remote Analog Meter 3 11 To look at or change the scale 3 11 Select KG or LB Units 3 12 To look at or change the units 3 12 Indicator Version 3 13 iii CONTENTS 9 continued iv Section 4 Section 5 Section 6 Cargo Hook Suspension System Operation Instructions Operating Procedures 4 1 Cargo Hook Loading 4 2 Cargo Hook Rigging 4 3 Maintenance Instructions for Returning a System to the Factory 5 1 Certification FAA STC 6 1 Canadian Approval 6 2 EASA Approval 6 3 Bra2. MINISTERIO DA DEFESA COMANDO DA AERONAUTICA DEPARTAMENTO DE PESQUISAS E DESENVOLVIMENTO CENTRO T CNICO AEROESPACIAL INSTITUTO DE FOMENTO E COORDENACAO INDUSTRIAL CERTIFICADO DE HOMOLOGA O SUPLEMENTAR DE TIPO Supplemental Type Certificate N MERO 2006S01 24 Number Este certificado emitido com base na Lei n 7565 C digo Brasileiro de Aeron utica de 19 de dezembro de 1986 This certificate issued in the basis of the Law No 7565 C digo Brasileiro de Aeron utica dated 19 December 1986 conferido ao Onboard Systems te granted to 13915 NW 3rd Court Vancouver WA 98685 USA por ter a modifica o ao projeto de tipo do produto abaixo citado observadas as limita es e condi es for having the change to the type design of the product mentioned below with the limitations and conditions therefor as especificadas satisfeito aos requisitos de aeronavegabilidade aplic veis specified hereon met the applicable airworthiness requirements Produto Original Numero do Certificado de Tipo 9603 CTA Original roduct Type Certificate N Fabricante Bell Manufacturer Modelo s 407 Model s DESCRI O DA MODIFICA O AO PROJETO DE TIPO Description of Type Design Change Installation of Onboard Systems Model 200 258 00 without load weigh 200 259 00 with load weigh or 200 259 01 with load weigh and 5V Lighting Cargo Hook Suspension System in accordance with Master Drawi
3. into the Rotorcraft Flight Manual Installation Instructions 2 15 This page intentionally left blank Section 3 Load Weigh System Operation Instructions Indicator Front Panel The C 39 Indicator front panel includes the following features e The four 7 segment LCD digits show the weight on the Cargo Hook and displays various Setup information e The Legends clarify the digital display i e when the LB Legend is turned on the display will be pounds etc e The Right button is used to Zero the display in the Run Mode and select the digit to be changed in the Setup Mode e The Left button is used to Un Zero the display in the Run Mode and scroll the selected digit in the Setup Mode Figure 3 1 Front Panel Calibration amp Zero amp Un Zero Legend lt Hook Logd Dampening Unit Legend Left Button Load Weigh System Operation Instructions 3 1 The Run Mode 3 2 The C 39 Indicator has two operating modes Run and Setup The Run Mode is used to display the cargo hook weight and the Setup Mode is used to setup or configure the Indicator to the helicopter and to the Load Cell When powered up the Indicator always comes to life in the Run Mode After the Indicator has been correctly installed power it up by activating the Load Weigh Circuit Breaker The Indicator will go through a self diagnostic routine During this routine the display will display all of the digits and legend
4. with Onboard Master Drawing List No 155 058 00 Rev 8 dated September 16 2008 or later FAA approved revision and installation and inspection of these Onboard cargo hook systems in accordance with FAA approved Onboard Systems Instructions for Continued Airworthiness Document 123 007 00 Rev 5 dated April 17 2007 Cargo Hook Owner s Manual Document 120 092 00 Rev 8 dated September 15 2008 and Cargo Hook Service Manual Document 122 005 00 Rev 1 dated November 9 2000 or later FAA approved revisions Limitations and Conditions Approval of this change in type design applies only to those Bell model rotorcraft listed above which are equipped with an FAA approved installation of a Bell Auxiliary Equipment Kit Cargo Hook Provisions P N s 206 706 341 7 9 103 111 113 117 123 or 125 only This approval should not be extended to other rotorcraft of these models on which other previously approved modifications are incorporated unless it is determined by the installer that the relationship between this change and any of those other previously approved modifications including changes in type design will introduce no adverse effect upon the airworthiness of that rotorcraft This modification has been approved by the FAA for Class B and C Rotorcraft Load Combinations Non human External Cargo only Modified rotorcraft must be operated in accordance with FAA approved Onboard Rotorcraft Flight Manual Supplement RFMS No 121 003 00 Rev
5. 2 dated August 2 2007 or later FAA approved revision A copy of this certificate and FAA approved RFMS must be maintained as part of the permanent records for the modified rotorcraft If the holder agrees to permit another person to use this certificate to alter the product the holder shall give the other person written evidence of that permission rendered suspended revoked or a termination date s otherwise established by the Administrator of the Soderal Aviation Administrate Date of application September 22 2000 Date reissued 7 March 26 2001 Date amended January 13 2003 October 9 2008 Signature Acting Manager Seattle Aircraft Certification Office Title Any alteration of this certificate is punishable by a fine of not exceeding 1 000 or imprisonment not exceeding 3 years or both This certificate may be transferred in accordance with FAR 21 47 FAA Form 8110 2 10 88 Certification 6 1 Canadian Approval E EF Transport Canada Transports Canada Department of Transport Supplemental Type Certificate This approval is issued to Number SH05 33 Onboard Systems Issue No 1 13915 NW 3rd Court Approval Date July 04 2005 Vancouver Washington Issue Date July 04 2005 United States of America 98685 Responsible Office Pacific Aircraft Engine Type or Model BELL 206L 206L 1 206L 3 206L 4 407 Canadian Type Certificate or Equivalent H 92 Description of Type Design Change Installation of Onboar
6. cable and a manual release lever provide the means for unlatching the load beam The load is attached to the load beam by passing the cargo sling ring into the throat of the load beam and pushing the ring against the upper portion of the load beam throat which will initiate the hook to close In the closed position a latch engages the load beam and latches it in this position To release the load the latch is disengaged from the load beam With the latch disengaged the weight of the load causes the load beam to swing to its open position and the cargo sling slides off the load beam The load beam then remains in the open position awaiting the next load A load release can be initiated by three different methods Normal release is achieved by pilot actuation of the push button switch in the cockpit When the push button switch is pressed it energizes the DC solenoid in the Cargo Hook and the solenoid opens the latch in the internal mechanism In an emergency release can be achieved by operating a mechanical release cable The release cable operates the internal mechanism of the Cargo Hook to unlatch the load beam The load can also be released by the actuation of a lever located on the side of the Cargo Hook 1 5 This page intentionally left blank Section 2 Installation Instructions These procedures are provided for the benefit of experienced aircraft maintenance facilities capable of carrying out the procedures They must not be
7. in the shop or on the helicopter The accuracy of the procedure is directly related to the weight of the known load If for example the procedure was done with a 1 000 pound load that was assumed to weigh only 900 pounds all subsequent lifts would be displayed 10 light Be sure to include the weight of everything between the Cargo Hook and the load i e the cable net dirt etc The closer the known load approaches the lifting capacity of the helicopter the more accurate the calculated Calibration Code will be Load Weigh System Operation Instructions 3 9 The Setup Mode continued 3 10 To Run the Calibration by Lifting a Known Weight Routine With the Indicator powered up and in the Run Mode press both buttons at the same time to go to Setup Scroll through the menu until the word LOAD is displayed then press the Right button The display should look like this Figure 3 7 Running CAL Routine Hook Load x 10 CAL OOO SETUP UN ZERD ZERO The CAL legend is turned on and the first digit is blinking The previous load is not displayed At this point if you wish to return to the Run Mode without changing the Calibration Code power cycle the Indicator At this point it is not possible to return to the Run Mode without changing the Calibration Code by using the buttons on the Indicator front panel To proceed with the procedure use the Right button to select the digit to be changed then use the Left button to sc
8. is fitted with a bulkhead connector Hardware is provided to attach the bulkhead connector to the Quick Disconnect Bracket P N 235 035 00 Attach the Quick Disconnect Bracket to the bracket that holds the manual and electrical release fittings on the skin of the aircraft at the cargo hook area Another cable is marked POWER and is connected to the aircraft electrical power Another cable is marked LIGHT refer to the Indicator Internal Back Light section for installation instructions The last cable is marked DATA and can be connected to the optional Data Recorder or Analog Slave Meter These optional items are not included under this STC NOTICE The data cable may or may not be terminated with a connector depending on part number and manufacture date Route the cables in the most convenient manner Secure the cables to the existing wiring bundles with the Ty wraps Secure the cables clear of flight control rods C 39 Cockpit Indicator Installation The Indicator P N 210 095 00 or P N 210 177 00 should be mounted in a position that is convenient accessible and visible to the pilot It can be mounted in a standard 214 instrument hole Connect the Indicator to its Internal Harness refer to Internal Harness Installation Indicator Internal Back Light Installation Instructions The Indicator is equipped with an Internal Back Lighting System that can be connected to the aircraft 28 VDC light dimming circuit Us
9. rear looking forward Tighten nut 510 170 00 on bolt 290 332 00 to finger tight then rotate to next castellation to install and secure cotter pin 510 178 00 Installation Instructions Cargo Hook Suspension System Installation continued Installation Instructions Remove the manual release cover from the new cargo hook Thread the manual release adapter P N 290 331 00 into the new cargo hook manual release boss on the hook sideplate Connect the manual release cable to the adapter Place the cable ball end fitting into the hook manual release fork fitting as illustrated in Figure 2 7 Move the manual release lever in the clockwise direction until it is against the cam stop this is felt as the lever moves relatively easily for several degrees before hitting the cam stop Measure the cable ball end free play with the manual release handle in the cockpit in the non release position Adjust the manual release cable system to allow a minimum of 125 of free play at the fork fitting as shown in Figure 2 7 Manual release cable rigging must be done with the cargo hook in the closed and locked position Figure 2 7 Manual Release Cable Rigging manual release lever fork Manual Release Adapter cable ball end release cable Load beam must be closed and locked when rigging Route the Manual and the Electrical Release cables as illustrated in Figures 2 8 and 2 9 Connect the cargo hook electrical release
10. To obtain an RMA please use one of the listed methods e Contact Technical Support by phone or e mail Techhelp OnboardSystems com e Generate an RMA number at our website http www onboardsystems com rma php After you have obtained the RMA number please be sure to e Package the component carefully to ensure safe transit e Write the RMA number on the outside of the box or on the mailing label e Include the RMA number and reason for the return on your purchase or work order e Include your name address phone and fax number and email as applicable Return the components freight cartage insurance and customs prepaid to Onboard Systems 13915 NW 3rd Court Vancouver Washington 98685 USA Phone 360 546 3072 5 1 This page intentionally left blank Section 6 Certification FAA STC Woited Seetes of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number SR00898SE This certificate issued to Onboard Systems 13915 NW 3rd Court Vancouver WA 98685 Uarefore as specified hereon meets the airworthiness reguirements of Part 6 ofthe Civil Air Regulations Original Product Type Certificate Number H2SW Maka Bell Model 206L 206L 1 206L 3 206L 4 and 407 of the Type Design Change Fabrication of Onboard Model 200 258 00 without load weigh 200 259 00 with load weigh or 200 259 01 with load weigh and 5V Lighting cargo hook system in accordance
11. ard Systems Model 200 258 00 without load weigh 200 259 00 with load weigh or 200 259 01 with load weigh and 5V Lighting Cargo Hook Suspension System in accordance with Master Drawing List N 155 058 00 Rev 4 dated 17 Jun 2005 or later approved revision This CHST validates in Brazil the STC SROO898SE issued by FAA USA LIMITAGOES E CONDI ES Limitations and Conditions See continuation sheet for applicable data DATAS Dates of Do Requerimento 02 Nov 2005 Da emiss o 31 Jan 2006 Da reemiss o Application Issue Reissue GERALDO CURCIO NETO Ten Cel Av LUIZ ALB RTO C MUNARETTO Cel Av Chefe da Divis o de Certifica o de Avia a o Civil Diretor do Instituto de Fomento e Coordena o Industrial hief Divis o de Certifica o de Avia o Civil Director Instituto de Fomento e Coordena o Industrial F 400 01B 08 04 FI 01 de 02 H 02 2515 0 Sheet of Certification 6 5 Brazilian Approvals continued LIMITA L tLimita MINIST RIO DA DEFESA COMANDO DA AERON UTICA DEPARTAMENTO DE PESQUISAS E DESENVOLVIMENTO CENTRO T CNICO AEROESPACIAL INSTITUTO DE FOMENTO E COORDENA O INDUSTRIAL Folha de Continua o ao Co Sheet to ntinuation CERTIFICADO DE HOMOLOGA O SUPLEMENTAR DE TIPO Supplemental Type Certificate N MERO 2006S01 23 Number ES E CONDI ES ons and Conditions The approval of this type design change should not be exte
12. attempted by those lacking the necessary expertise Cargo Hook Suspension System Installation If installing the cargo hook suspension system on a helicopter that has a Bell P N 206 706 341 125 Fixed Provisions Kit installed the pillow blocks included with this kit must be removed Retain the forward pairs of screws and nuts for each pillow block the aft pairs of fasteners will not be re used The cargo hook suspension systems must be installed with the supplied 232 030 02 Pillow Blocks These systems are not compatible with Pillow Blocks supplied by Bell Attach the two P N 232 030 02 Pillow Block Assemblies as illustrated below Use sealant on the faying surfaces At the forward pair of holes at each pillow block re use the screws and washers provided with the Bell Helicopter provisions kit At the aft pairs of fasteners at each pillow block torque the 510 234 00 nuts and 510 235 00 bolts to 100 130 in lbs NOTICE The 232 030 02 Pillow Blocks install exactly as the Bell pillow blocks with the exception of the P N 510 235 00 bolts These bolts are a shorter grip length than those used with the Bell pillow blocks and they are installed with the heads down to give clearance for the beam when it rotates Figure 2 1 Pillow Block Installation BELL FITTINGS 206 072 927 3 206 072 943 1 206 072 943 101 NUT P N 510 234 00 _ MS21084L04 7 Re use Be
13. b 1360 kg Design ultimate strength 13 500 lb 6120 kg Unit weight P N 200 258 00 12 pounds 5 44 kg Unit weight P N 200 259 00 13 pounds 5 90 kg Table 1 2 P N 528 023 01 Cargo Hook Specifications release at 3 500 lb Inspection Inspect the kit items for evidence of damage corrosion and security of lock wire and fasteners If damage is evident do not use the items until they are repaired General Information 1 3 Bill of Materials The following items are included with the Suspension System if shortages are found contact the company from whom the system was purchased The Bell Helicopter provisions kit is required to complete the installation 200 258 00 200 259 00 200 259 01 200 245 00 Part No Description Quantity Quantity Quantity Quantity 1 pa The 210 177 00 Indicator is equipped with a 5 Volt back lighting system It is an optional indicator that can be ordered in place of the 210 095 00 Indicator P N 200 245 00 is a load weigh kit that can be purchased separately to upgrade the 200 258 00 kit to a 200 259 00 kit P N 210 179 01 supersedes P N 210 179 00 These assemblies are interchangeable 1 4 General Information Theory of Operation General Information The primary elements of the Cargo Hook are the load beam the internal mechanism and a DC solenoid The load beam supports the load and is latched through the internal mechanism The DC solenoid an external manual release
14. cable connector to the Cargo Hook Listed below is the pin out for the cargo hook connector Table 2 1 Cargo Hook Connector Pe sive 2 7 Cargo Hook Suspension System Installation continued Earlier versions of the cargo hook were equipped with a suppression diode that will be damaged if the cargo hook electrical connection is reversed Do not attach the electrical connector until polarity of the aircraft connector is determined to be compatible with the Cargo Hook connector listed in Table 2 1 Figure 2 8 Manual and Electrical Release Cable Routing without Load Weigh Manual Release Cable to cockpit Manual Release Cable from Cargo Hook Electrical Release Cable from Cargo Hook Electrical Release Cable to cockpit View looking from the bottom Beam Assembly Carriage Cargo Hook Electrical Release Cable Manual Release Cable Installation Instructions Cargo Hook Suspension System Installation continued Figure 2 9 Manual and Electrical Release Cable Routing with Load Weigh Manual Release Cable to cockpit 4 Manual Release Cable Irom Cargo Hook Electrical Release Cable from Cargo Hook Electrical Release Cable to cockpit View looking from the bottom Secure the 235 035 00 QD Bracket and the Internal Harness bulkhead connector with the 510 028 00 Screw 510 029 00 Nut and 510 062 00 Washer ut ani ASHEL QD Bracket ra Load Weigh Internal Harness Load Cell Connector Beam A
15. d System Model 200 258 00 200 259 00 or 200 259 01 Hook System per FAA STC SR00898SE Installation Operating Data Required Equipment and Limitations Installation and Inspection of Onboard Systems Model 200 258 00 without load weigh or 200 259 00 with load weigh or 200 259 01 with load weigh and 5V Lighting cargo hook system is to be carried out in accordance with Onboard Systems Instructions for Continued Airworthiness Document 123 007 00 Revision 3 dated May 9 2005 FAA approved Onboard Systems Cargo Hook Owner s Manual Document 120 092 00 dated January 23 2001 and Cargo Hook Service Manual Document 122 005 00 Revision 1 dated November 9 2000 This cargo hook suspension system is to be fabricated in accordance with FAA approved Onboard Systems Master Drawing List No 155 058 00 dated January 24 2001 This modification has been approved by the FAA for Class B and C Rotorcraft Load Combinations Non human External Cargo only Approval of this change in type design applies to Bell model rotorcraft listed above which were previously equipped with an FAA approved installation of Bell Auxiliary Equipment Kit Cargo Hook Provisions P N 206 706 341 7 9 103 111 or 113 only Modified rotorcraft must be operated in accordance with an FAA approved copy of Onboard Rotorcraft Flight Manual Supplement No 121 003 00 dated March 26 2001 End Conditions This approval is only applicable to the type model of aeronautical p
16. e a 22 gauge twisted pair shielded cable to connect the aircraft dimming circuit to the Internal Harness Connect the cable shield wire to airframe ground at the light dimmer end of the cable ONLY 2 11 Indicator Hook Open Warning The Indicator is equipped with a Hook Open Warning feature that can be connected to a cargo hook equipped with a hook open switch Depending on the capabilities of the cargo hook switch the Indicator will flash HOOK OPEN when the cargo hook load beam is open The cargo hook switch must be normally open when the cargo hook load beam is in the closed position When the load beam is open one side of the switch must be grounded and the other side of the switch is to be connected to the Indicator Use a 22 gauge shielded wire to connect the cargo hook switch to the Indicator Disassemble the Indicator mating connector and carefully solder the wire from the cargo hook switch to pin H Connect the cable shield wire to airframe ground as close to the cargo hook as possible at the cargo hook end of the cable ONLY Remote Analog Meter The Indicator is equipped with an Analog drive circuit that can be connected to a remote analog meter Use a 22 gauge twisted pair shielded cable to connect the Remote Analog Meter to the Indicator Disassemble the Indicator mating connector and carefully solder the positive wire from the analog meter to pin G and the common wire to pin F Connect the cable shield wire to airframe
17. e current display and the Un zero legend is turned on If the Left button is again pressed before the zero button is pressed the display blinks in response to the button closure Un Zero is only available in the Run Mode Load Weigh System Operation Instructions 3 3 The Run Mode continued 3 4 Error Codes Error Codes are the result of difficulties discovered during the Indicator diagnostic tests Diagnostic tests occur at power up and during the execution of certain routines Listed below is a matrix of the Error Code displays their meaning and possible corrective action Pressing either button will usually bypass the error code however the displayed information may be suspect Table 3 1 Indicator Error Codes POSSIBLE DISPLAY CAUSE CORRECTIVE ACTION A D or D A circuit failure NV Ram failure NV Ram write failure NV Ram busy failure Potential short in the optional analog meter cable Clear short and power cycle the Indicator by turning the power to the Indicator off for a few moments If Error Code continues return the Indicator to the factory Power cycle the Indicator if Error Code continues return the Indicator to the factory Re enter data if Error Code continues return the Indicator to the factory Power cycle the Indicator if Error Code continues return the Indicator to the factory Load Weigh System Operation Instructions The Setup Mode The C 39 Indicator can be used with a wide rang
18. e of helicopters and load cells The Setup Mode on the Indicator matches the Indicator to the Load Cell and to the helicopter This is done by entering data into the Indicator Entered data includes the load cell Calibration Code the units that the Indicator should read out pounds or kilograms and several other items The Indicator has a group of Setup routines arranged in menu form that are used to configure the Indicator Shown on the next page is a matrix of the Setup routines and a brief discussion of their function and how they are programmed A complete discussion of each setup item is presented later in this section To enter the Setup Mode press both the Right and Left buttons at the same time while the Indicator is powered up and in the Run Mode To exit the Setup Mode and return to the Run Mode press both the buttons at the same time If you are in a Setup routine and have started to change an entry but you change your mind before completing the procedure power cycle the Indicator to exit the Setup Mode and then go to the Run Mode without changing the item The Indicator is power cycled by turning the Indicator power off for a few moments Load Weigh System Operation Instructions 3 5 The Setup Mode continued Table 3 2 Indicator Setup Routines MENU FUNCTION DISPLAY Press the Right button to view or change the To return to the Run Mode press both the scroll through the menu menu item Right and Left buttons at the same
19. etup Mode continued Installation Zero Installation zero is a routine that matches the Indicator to the INSTALLED Load Cell It adjusts the Indicator reading to compensate for the weight of the Cargo Hook on the Load Cell and whatever zero offset is built into the Load Cell The Installation Zero procedure is not mandatory If done the Indicator will read zero when the Un Zero button is pressed and there is no weight on the Cargo Hook If the Installation Zero is not done the Indicator will show the weight of the Cargo Hook plus the value of the Load Cell zero offset To Run the Installation Zero Routine With the Indicator powered up and in the Run Mode press both buttons at the same time to go to Setup Scroll through the menu until the symbol 0 in is displayed then press the Right button The CAL legend will be turned on and the current weight on the Cargo Hook will be displayed and blinking Remove any weight that is not to be zeroed out and press either button to complete the procedure and return to the Run Mode Calibration by Lifting a Known Weight Calibration by lifting a known weight is a Setup routine that calculates the Calibration Code for the Load Cell attached to the Indicator It is useful if the load cell Calibration Code is not known or as a cross check to the accuracy of a known Calibration Code The procedure is done by entering the known weight into the Indicator and then lifting the weight This procedure can be done
20. g utilized with the C 20 or C 30 Data Recorder a 5 amp circuit breaker should be used Install the placard 215 010 00 ELECTRONIC WEIGHING SYSTEM next to the power switch and circuit breaker Install the placard 215 012 00 TURN THE WEIGHING SYSTEM OFF WHEN NAVIGATION EQUIPMENT IN USE NO AIRCRAFT OPERATION SHOULD BE PREDICATED ON THE READING OF THE ONBOARD WEIGHING SYSTEM next to the Indicator 2 13 Installation Instructions Installation Check Out After installation of the Cargo Hook Suspension System perform the following functional checks 1 Swing the installed Cargo Hook on the beam to its full extremes to ensure that the manual release cable assembly and the electrical release cable have enough slack to allow full swing of the suspension assembly without straining or damaging the cables The cables must not be the stops that prevent the Cargo Hook from swinging freely in all directions 2 With no load on the cargo hook load beam pull the handle operated cargo hook mechanical release the Cargo Hook should release Reset the cargo hook load beam 3 Close the cargo hook release circuit breaker and position the battery switch to the ON position With no load on the cargo hook load beam depress the cargo hook electrical release button the Cargo Hook should release Reset the cargo hook load beam 4 See the Bell Helicopter service instructions for your specific helicopter model for additional installati
21. ground as close to the Analog Meter as possible at the Analog Meter end of the cable ONLY The 210 095 00 Indicator can be connected to Onboard Systems Analog Slave Meter P N 210 180 00 through the DATA cable This meter gives solid weight indications without needle bounce The Analog Slave Meter may be mounted in any convenient location in a standard 3 instrument hole Attach connector P N 410 130 00 to data line per pin out Figure 2 11 to connect the Analog Slave Meter to the Internal Harness DATA cable If a data connector is present on the data line use cable P N 270 059 00 to connect to Analog Slave Meter Electrical Connections 2 12 Connect the Internal Harness to the Indicator and route the other end to a convenient location for the Indicator power switch part number 400 048 00 The cable is supplied extra long cut off the excess cable and use as needed to connect the switch and circuit breaker Connect the white red wire if wire harness P N 270 048 00 is installed wire in the power cable to one side of the power switch connect another piece of suitable wire to the other side of the switch and then to an available 1 or 2 amp circuit breaker Connect the white blue black if wire harness P N 270 048 00 is installed wire to the ground bus The bare wire present on P N 270 048 00 harness only should be cut off as it is not needed at this end of the cable Installation Instructions Figure 2 11 Wiring A
22. hay W Schulze Marmeling Head of Programmes Certification STC EASA IM R S 00595 Onboard Systems 6 4 Certification Brazilian Approvals MINIST RIO DA DEFESA COMANDO DA AERONAUTICA DEPARTAMENTO DE PESQUISAS E DESENVOLVIMENTO CENTRO T CNICO AEROESPACIAL INSTITUTO DE FOMENTO E COORDENA O INDUSTRIAL CERTIFICADO DE HOMOLOGA O SUPLEMENTAR DE TIPO Supplemental Type Certificate N MERO 2006S01 23 Number Este certificado emitido com base na Lei n 7565 Codigo Brasileiro de Aeron utica de 19 de dezembro de 1986 This certificate issued in the basis of the Law No 565 C digo Brasileiro de Aeron utica dated 19 December 1986 conferido ao Onboard Systems le granted to 13915 NW 3rd Court Vancouver WA 98685 USA por ter a modifica o ao projeto de tipo do produto abaixo citado observadas as limita es e condi es or having the change to the type design of the product mentioned below with the limitations and conditions therefor as especificadas satisfeito aos requisitos de aeronavegabilidade aplic veis specified hereon met the applicable airworthiness requirements Produto Original N mero do Certificado de Tipo H2SW FAA Original roduct Type Certificate No Fabricante Bell Manufacturer Modelo s 206L 206L 1 206L 3 and 206L 4 Model DESCRI O DA MODIFICA O AO PROJBTO DE TIPO Description of Type Design Change Installation of Onbo
23. in the Run Mode press both buttons at the same time to go to Setup Scroll through the menu using the Left button until the word DAMP is displayed To look at or change the Dampening Level press the Right button The display should look like this Figure 3 5 Changing Dampening Level Hook Load J CAL DAMP SETUP UN ZERD ZERD The CAL and the DAMP legend is turned on and the previously set dampening level is displayed To return to Run without changing the current dampening level press both the Right and Left buttons at the same time To change the dampening number use the Left button to scroll the blinking digit to the desired number After the selection has been made press both the Right and Left buttons at the same time to return to Run Indicator Calibration The Calibration Code or CAL code is a mandatory input The Indicator will not accurately display the load without the correct Calibration Code The Calibration Code scales the signal from the Load Cell If the C 39 Indicator was supplied as part of a Load Weigh System the Calibration Code will have been entered into the Indicator by the factory however it should be confirmed If the Indicator is to be mated to a different Load Cell it must be calibrated before use Calibration can be done by entering a known Calibration Code or by lifting a known load and having the Indicator calibrate itself Both options are discussed below Load Weigh System Operation Ins
24. ions for Continued Airworthiness No 123 007 00 Revision 2 dated 10 October 2003 Service Manual Document No 122 005 00 Revision 7 dated 10 October 2003 Master Drawing List No 155 058 00 Revision 2 dated 10 October 2003 Rotorcraft Flight Manual Supplement No 121 003 00 dated 26 March 2001 Limitations and Conditions I This Cargo Hook System P N 200 258 00 without load weight 200 259 00 with load weigt or 200 259 01 with load weigh and 5V lighting are to be fabricated in accordance with FAA approved Onboard Systems Master Drawing List No 155 058 00 dated 24 January 2001 PA Approval of this change in Type Design applies to Bell 206L 206L1 206L3 206L4 and 407 rotorcraft which were previously equipped with an FAA approved installation of the Bell Auxiliary Equipment Kit Cargo Hook Provisions P N 206 706 341 7 9 103 11 and 113 only Modified Rotorcraft must be operated in acordance with an FAA approved Onboard Systems RFMS to 4 Basis of certification as defined in the applicable Type Certificate Data Sheet S This STC is approved only for the product configuration as defined in the approved design data referred to in the paragraph Description Compatibility with other aircraft engine configurations shall be determined by the installer This certificate shall remain valid unless otherwise surrendered or revoked For the European Aviation Safety Agency Date of Issue 1 March 2005 Mb Ue Manut
25. ity as needed 210 167 00 or 210 178 00 Beam Assembly P 290 370 00 Trunnion Pin 2 each The long end of the Carriage must point to the left side of the aircraft Carriage View is from the rear looking forward View is of 210 167 00 Beam Assembly 2 2 Installation Instructions Cargo Hook Suspension System Installation continued Figure 2 3 Beam Assembly Left End Play Adjustment Move the Beam Assembly in this direction with approximately 10 pounds force and then measure the gap between the Thrust Spacers and the Beam Assembly at the locations illustrated Add sufficient Thrust Spacers to make the gap 00 to 060 inches at both locations Thrust Spacers Thrust Spacers a gt lt 00to 060 gap 00 to 060 gap gt Installation Instructions 2 3 Cargo Hook Suspension System Installation continued Figure 2 4 Beam Assembly Right End Play Adjustment Move the Beam Assembly in this direction with approximately 10 pounds force and then measure the gap between the Thrust Spacers and the Beam Assembly at the locations illustrated Add sufficient Thrust Spacers to make the gap 00 to 060 inches a
26. ld reach the 5 VDC output If for example a 5 volt analog meter is used and its full scale reading is 10 000 pounds the number entered into the Indicator Scale routine would be 1000 the number is entered X 10 This number tells the Indicator that it should output the proportional 0 to 5 VDC signal between zero pounds and 10 000 pounds The Scale number does not affect Onboard Slave Meters P N 210 106 00 or 210 180 00 This number only affects user supplied instruments connected to the analog out signal To Look at or Change the Scale With the Indicator powered up and in the Run Mode press both buttons at the same time to go to Setup Scroll through the menu until the word SCALE is displayed then press the Right button The display should look like this Figure 3 9 Changing the Scale Hook Load x 10 CAL IUU Load Weigh System Operation Instructions 3 11 The Setup Mode continued 3 12 To Look at or Change the Scale continued The CAL legend is turned on and the previously set Scale number is displayed To return to Run without changing the Scale press both the Right and Left button at the same time To change the Scale number use the Right button to select a digit to be changed then use the Left button to scroll the blinking digit to the desired number When the complete Scale number has been entered press both the Right and Left button at the same time to return to Run Select KG or LB Units The uni
27. lectrical release cables do not limit the movement of the hook 2 Be completely familiar with this Owner s Manual Cargo Hook Component Maintenance Manual 122 005 00 and the ICA Maintenance Manual 123 007 00 3 Activate the electrical system and press the Cargo Hook release button to ensure the cargo hook electrical release is operating correctly The Cargo Hook must release Reset the hook by hand after release If the hook does not release or re latch do not use the unit until the difficulty is resolved The release solenoid is intended to be energized only intermittently Depressing the electrical release button continuously in excess of 20 seconds will cause the release solenoid to overheat possibly causing permanent damage resolved 4 1 Activate the manual release lever to test the cargo hook manual release mechanism The mechanism should operate smoothly and the Cargo Hook must release Reset the hook by hand after release If the hook does not release or re latch do not use the unit until the difficulty is Cargo Hook Loading 4 2 The cargo hook can easily be loaded with one hand A load is attached to the hook by pushing the ring upward against the upper portion of the load beam throat as illustrated in Figure 4 1 until an internal latch engages the load beam and latches it in the closed position Figure 4 1 Cargo Hook Loading Operation Instructions Cargo Hook Rigging Extreme care must be exercised
28. ll fasteners O N at fwd pairs of holes BOLT P N 510 235 00 PILLOW BLOCK ASSEMBLY SIDE VIEW MS21250 18 232 030 02 Installation Instructions 2 1 Cargo Hook Suspension System Installation continued Attach the Beam Assembly P N 210 167 00 or 210 178 00 to the Pillow Blocks as illustrated The long end of the Carriage must point to the left side of the aircraft as illustrated below Position the Thrust Spacers P N 290 374 00 on both sides of the Pillow Blocks to center the Beam Assembly between the Pillow Blocks and allow 000 060 lateral movement of the beam assembly The thrust spacers must be positioned on both sides of the pillow block so that when a lateral load is applied the beam will not rub directly metal to metal against the pillow block In addition to the above the thrust spacers must be positioned so that when a lateral load is applied it will be distributed to both pillow blocks To check this apply approximately 10 pounds to the beam in the lateral direction There should be a maximum of 060 gap when measured as shown in the Figures 2 3 and 2 4 Figure 2 2 Cargo Hook Suspension Assembly Installation S 290 374 00 Thrust Spacers j To help installation the Thrust Spacers can be D stacked and tied together with a length of safety wire or string Remove the a safety wire after installation wy Install the Thrust Spacers on EA both sides of each Pillow Block N quant
29. nded to other rotorcraft of this model on which other previously approved modifications are incorporated unless it is determined by the installer that the relationship between this change and any of those other previously approved modifications including changes in Type Design will introduce no adverse effect upon the airworthiness of that rotorcraft If the holder agrees to permit another person to use this certificate to alter the product the holder shall give the other person written evidence of that permission Installation of this modification must be performed according to the Owners Manual Document N 120 092 00 Rev 3 dated 17 Jun 2005 including the placard of Onboard System N 215 190 00 IR dated 30 Jan 2006 Operation must be performed in accordance with FAA Approved Rotorcraft Flight Manual Supplement document No 121 003 00 Rev 1 dated 09 Sep 2004 or later approved revision Maintenance of this installation must be performed in accordance with Instructions for Continued Airworthiness document N 123 007 00 Rev 3 dated 09 May 2005 and Service Manual document N 122 005 00 Rev 8 dated 30 Jun 2005 or later approved revisions A copy of this Certificate and the Supplement referred on item IV above shall be maintained as part of the permanent records of the modified rotorcraft F 400 01B 08 04 Fl 02 de 02 H 02 2515 0 Sheet of 6 6 Certification Brazilian Approvals continued
30. nding instructions 08 11 09 1 3 2 7 Added caution note and revised figure 2 7 Changed P N 268 004 00 to 268 004 01 for improved service life 12 18 09 2 11 to 2 14 Updated manual to reflect new load weigh harness configuration Updated EMI note in installation check out section 12 22 09 1 1 Added P N 200 328 00 as an eligible fixed provisions kit for the 407 model 03 12 15 Section 1 2 1 2 2 2 7 2 8 2 10 2 11 2 13 2 14 3 8 3 9 3 12 4 1 4 3 5 1 Updated safety labels to ANSI format throughout added load cell P N 210 179 01 updated cargo hook load rigging section Register Your Products for Automatic Notifications Onboard Systems offers a free notification service via fax or email for product alerts and documentation updates By registering your Onboard Systems products at our website we will be able to contact you if a service bulletin is issued or if the documentation is updated You can choose to receive notices on an immediate weekly or monthly schedule via fax email or both methods There is no charge for this service Please visit our website at www onboardsystems com notify php to get started This page intentionally left blank CONTENTS Section 1 Section 2 Section 3 General Information Introduction 1 1 Safety Labels 1 2 Specifications 1 3 Inspection 1 3 Bill of Materials 1 4 Theory of Operation 1 5 Installation Instructions
31. ng List N 155 058 00 Rev 4 dated 17 Jun 2005 or later approved revision This CHST validates in Brazil the STC SROO898SE issued by FAA USA LIMITA ES E CONDI ES Limitations and Conditions See continuation sheet for applicable data DATAS Dates of Do Requerimento 02 Nov 2005 Da emiss o 31 Jan 2006 Da reemiss o Application Issue Reissue l Fa Di E F A a Cree y f GERA DO CURCIO NETO Ten Cel Av LUIZ ALBERTO C MUNARETTO Cel Av Chefe da Divis de Certifica o de Avia o Civil Diretor do Instituto de Fomento e Coordena o Industrial Chief Divis o Ye Certifica o de Avia o Civil Director Instituto de Fomento e Coordena o Industrial F 400 01B 08 04 Fi 01 de 02 H 02 2516 0 Sheet of Certification 6 7 Brazilian Approvals continued MINISTERIO DA DEFESA COMANDO DA AERONAUTICA DEPARTAMENTO DE PESQUISAS E DESENVOLVIMENTO CENTRO TECNICO AEROESPACIAL INSTITUTO DE FOMENTO E COORDENA O INDUSTRIAL Folra de Continua o ao ontinuation Sheet to CERTIFICADO DE HOMOLOGA O SUPLEMENTAR DE TIPO Supplemental Type Certificate N MERO 2006S01 24 Number LIMITA ES E CONDI ES Limitations and Conditions l The approval of this type design change should not be extended to other rotorcraft of this model on which other previously approved modifications are incorporated unless it is determined by the installer that the relationship bet
32. om FOR appsySTEMs CO BOARDSY shaded THIS MANUAL TEATW HECK WEB SI E REVISION PLEASE CHECK ares Cargo Hook Suspension System For the Bell 206L amp 407 Series With Talon LC Keeperless Cargo Hook System Part Numbers 200 258 00 W O Load Weigh 200 259 00 W Load Weigh 200 259 01 W Load Weigh and 5V Lighting Owner s Manual Number 120 092 00 Revision 12 03 12 15 ZY lt CONBOARD SYSTEMS INTERNATIONAL 13915 NW 3 Court Vancouver Washington 98685 USA Phone 360 546 3072 Fax 360 546 3073 Toll Free 800 275 0883 www OnboardSystems com This page intentionally left blank Revision Date Record of Revisions Page s Reason for Revision 04 28 06 2 7 Added electrical connection caution statement 09 07 06 1 2 2 11 2 12 Updated manual to allow the installation of wire harness 270 048 04 04 16 07 Section 1 2 2 2 7 2 10 2 12 3 9 amp 3 1 Section 4 Changed P N 232 030 01 to 232 030 02 per Service Bulletin 159 020 00 Updated warnings cautions and notes to current format 07 10 08 1 3 2 1 2 6 2 7 Added kit P N 200 245 00 to BOM added note regarding forward pair of pillow block fasteners updated torque instructions for nut 510 170 00 and clarified release cable rigging dimension 09 15 08 1 1 2 1 Added P Ns 206 706 34 1 117 123 and 125 as compatible Bell provisions kits Clarified Figure 2 1 and correspo
33. on instructions 5 Perform an EMI ground test per AC 43 13 lb section 11 107 For equipment that can only be checked in flight an EMI flight test may be required NOTICE The cargo hook and load cell are of a class of equipment not known to have a high potential for interference This class of equipment does not require special EMI installation testing i e FADEC as required in paragraphs 7 and 8 of FAA policy memorandum ASW 2001 01 6 Power on the Indicator and allow to warm up for 5 minutes with no load on the hook Press both Indicator buttons at the same time to go to the Setup Mode Scroll through the menu until the symbol 0 in is displayed then press the right button Remove any weight that is not to be zeroed out and press either button to complete the procedure 2 14 Installation Instructions Component Weights The weight of the Cargo Hook Suspension System components are listed below Table 2 2 Component Weights Suspension System W hook W O Load Cell 12 0 Ibs 5 5 kgs Suspension System W hook W Load Cell 12 5 lbs 5 7 kgs Indicator and Wire Hamess 0 5 Ibs 23 kgs Suspension System Location Table 2 3 Suspension System Location Fuselage Station 121 0 Paper Work In the US fill in FAA form 337 for the initial installation This procedure may vary in different countries Make the appropriate aircraft log book entry Insert the Rotorcraft Flight Manual Supplement document no 121 003 00
34. roduct specified therein Prior to incorporating this modification the installer shall establish that the interrelationship between this change and any other modification s incorporated will not adversely affect the airworthiness of the modified product yw T Henry Wong For Minister of Transport Canada 6 2 Certification EASA Approval European Aviation Safety Agency SUPPLEMENTAL TYPE CERTIFICATE EASA IM R S 00595 This certificate established in accordance with Regulations EC No 1592 2002 and EC No 1702 2003 and issued to Onboard Systems 13915 NW 3rd Court Vancouver WA 98685 USA certifies that the change in the type design for the product listed below with the limitations and conditions specified meets the applicable type certification basis and environmental protection requirements when operated within the conditions and limitations specified below Original Product Type Certificate number FAA TC No H2SW Manufacturer Bell Helicopter Model Bell Model 206L 206L1 206L3 206L4 and 407 Description of Design Change Fabrication Installation and Inspection on Onboard Systems Model 200 258 00 without load weigh or Model 200 259 00 with load weigh Cargo Hook System per FAA STC SR00898SE Certification 6 3 EASA Approval continued European Aviation Safety Agency Associated Technical Documentation Owner s Manual No 120 092 00 Revision 2 dated 10 October 2001 Instruct
35. roll the blinking digit to the desired number Note that the known weight is entered X 10 a 1000 pound load is entered as 100 When the known load has been entered press both the Right and Left button at the same time The display will look like this Figure 3 8 Entering Load in CAL Routine Hook Load x 10 CAL Load Weigh System Operation Instructions The Setup Mode continued Calibration by Lifting a Known Weight continued The CAL legend and the digits will be blinking Again at this point if you wish to return to the Run Mode without changing the Calibration Code power cycle the Indicator It is not possible to return to the Run Mode by using the buttons on the Indicator front panel without changing the Calibration Code If you wish to proceed lift the known load and when it is stabilized press either button to complete the procedure The Indicator will display the load This ends the procedure The Indicator is now calibrated to the Load Cell It is a good practice to go to the Code routine and record the new Calibration code for later reference Setting the Scale for a remote analog meter The Scale routine is used when a user supplied analog meter is connected to the Indicator It is used to match or calibrate the analog meter to the Indicator The Indicator outputs a 0 to 5 VDC analog signal which is proportional to the Load Cell load The Scale number tells the Indicator at what point in pounds or kilograms it shou
36. rrangement 1 AMP CIRCUIT BREAKER OPERATOR SUPPLIED POWER SWITCH SUPPLIED CUT OFF THE BARE WIRE DO NOT CONNECT IT TO GROUND White Red TO 28 VDC ni gt TO AIRFRAME GROUND White Blue Black POWER CABLE BACK LIGHT POTENTIOMETER OPERATOR SUPPLIED Wiee INTERNAL HARNESS ASSEMBLY TO 28 VDC ite Red LIGHT CABLE WITH OPTIONAL CABLE INSTALLED TO AIRFRAME GROUND L White Blue Black 5 DATA RECORDER ANALOG METER CABLE TO OPTIONAL EQUIPMENT O DEPENDING ON MFG DATE OR DASH NUMBER THIS CABLE MAY TERMINATE INA CONNECTOR OPTIONAL EQUIPMENT CONNECTORS 19 TO LOAD CELL ES IO ED i E He co E DATA RECORDER CONNECTOR Ho P N 410 130 00 410 057 00 amp 410 020 00 ANALOG METER CONNECTOR PIN LOR FUNCTION P N 410 130 00 GOLO ASIS MFG ANY MFG P N MS3126F10 6P 1 WH BL Black Ground PIN COLOR FUNCTION 3 WH Red Power A WH Red Power 5 Shield Shield B WH GN Green Clock 7 WH GN Green Clock Signal C WH OR White Data 9 WH OR White Data Signal D WH BL Black Ground 4 Red Flight Switch E Shield Shield 2 Purple Cap Switch Optional NOTICE If the C 23 Printer is bein
37. s If a problem is found during the routine an Error Code will be displayed For an explanation of Error Codes see the section Error Codes After the diagnostic routine the display should look like this Figure 3 2 After Dia nostic Routine Hook Load x 10 CAL UN ZERD The illustration is of the Indicator in the Run Mode with no load on the hook Note the LB legend displayed Figure 3 3 LB Legend Displayed Hook Load x 10 LB The illustration is a typical hook load reading The display is 3 500 pounds note the last digit is not displayed Load Weigh System Operation Instructions To Zero or Tare the Display The zero feature is used to zero or tare the weight on the Cargo Hook that is not wanted such as the weight of a cargo net or long line The Right button is used to zero the Indicator reading When the Right button is pressed the display is zeroed The zero legend is turned on and the zeroed number is stored in memory If the Right button is pressed again before the Un zero button is pressed the display blinks in response to the button closure Zero is only available in the Run Mode Figure 3 4 Zeroing the Display Hook Load Zero Legend x 10 7 Un Zero Legend To Un Zero the Display The Left button is used to add the zeroed value back into the current Indicator reading or Un zero the display When the Left button is pressed the number previously zeroed is added to th
38. s previously entered number To Scale Indicator to an optional remote analog meter change the number use the Right button to select a digit use the Left button to scroll the digit to the desired number Entry is times 10 LB KG Units selects the Indicator units pounds or Display is previously selected unit To kilograms change the unit use the Left button XX V Version is the revision level of the Indicator Version is for information only it cannot hardware and software be changed 3 6 Load Weigh System Operation Instructions The Setup Mode continued Indicator Dampening The Damp or dampening routine allows the pilot to adjust the Indicator dampening level to his preference The dampening routine is a program that stabilizes the Indicator reading It offers a trade off between Indicator responsiveness and stability Ten dampening levels are available from O through 9 At level O the display responds to the slightest change in weight However if the load bounced even slightly the display digits would respond instantly making the display look unstable With a dampening level of 9 the display would be stable under the most turbulent conditions however it would take several seconds for the display to respond to a change in weight The ideal dampening level will depend on the flying conditions A mid range setting of 5 or 6 is usually adequate To Look at or Change the Dampening Level With the Indicator powered up and
39. ssembly Carriage Load Cell Cargo Hook Electrical Release Cable Manual Release Cable Installation Instructions 2 9 Cargo Hook Suspension System Installation continued Un commanded cargo hook release will happen if the manual release cable is improperly restrained The cables must not be the stops that prevent the Cargo Hook from swinging freely in all directions If the Cargo Hook loads cause the hook to strain against the manual release cable the swaged end of the cable may separate allowing the inner cable to activate the cargo hook manual release mechanism The result is an un commanded release Ensure that no combination of cyclic stick or Cargo Hook position is restrained by the manual release cable Figure 2 10 Un commanded Release From Incorrectly Secured Cable _ Hook rotates and strains against the manual release cable conduit The strain on the conduit exceeds the pull off force between the swaged fitting and the conduit _ The load ring falls free in an un commanded load release The swaged joint fails and allows the inner cable to activate the hooks mechanical release mechanism and the hook opens 2 10 Installation Instructions Load Weigh System Installation Instructions Internal Harness Installation The Internal Harness is made up of four cables terminated to one large connector The connector is plugged into the back of the Indicator One of the cables is marked LOAD CELL and
40. t both locations itam la Thrust Spacers Thrust Spacers lt 00 to 060 gap 00 to 060 gap gt Installation Instruction Cargo Hook Suspension System Installation continued Secure the two Trunnion Pins P N 290 370 00 with fasteners as illustrated Torque the 510 230 00 bolts and 510 114 00 nuts to 56 79 in lbs Torque the 510 229 00 bolts and 510 102 00 nuts to 20 25 in lbs Figure 2 5 Trunnion Pin Fasteners 510 230 00 Bolt 510 100 00 Washer amp 510 114 00 Nut 2 each 510 229 00 Bolt 510 095 00 Washer amp 510 102 Nut 2 each Installation Instructions 2 5 Cargo Hook Suspension System Installation continued 2 6 Attach the Cargo Hook P N 528 023 01 to the Suspension Assembly as illustrated The Cargo Hook load beam must point to the right Figure 2 6 Cargo Hook to Carriage Installation 290 332 00 Bolt 510 144 00 Washer The Cargo Hook Load Beam must point to the right 510 144 00 Washer 510 174 00 Washer 510 170 00 Nut amp 510 178 00 Cotter Pin View is from the
41. time Dampening Level sets the pilots preference Blinking display is previously entered DAMP for display dampening Dampening Level Select the desired dampening level by pressing the Left button Calibration Code matches the Indicator to the Display is previously entered CAL Code CODE Load Cell The Code is changed by selecting the digit to be changed with the Right button The selected digit will blink Change the blinking digit by pressing the Left button Installation ZERO matches the Indicator to Display is a combination of load on the Oin the installed Load Cell and to the helicopter Load Cell and normal load cell zero After this procedure the display will be zero offset Remove all weight from the henno eco SCCO installed Load Cell except the Cargo X 8 Hook and press any button to complete the procedure and return to the Run Mode Load is used to calibrate the system by lifting No previous display is shown Enter the LOAD a known load known load using the Right button to select the digit to be changed and Left button to enter the number Known load is entered X 10 ie 5000 kilograms is entered as 500 After the known load is entered press both buttons at the same time and lift the known load When the load is stabilized press either button A new Calibration Code will be calculated and the known load will be displayed This completes the procedure Scale matches the analog output of the Display i
42. tructions 3 7 The Setup Mode continued 3 8 To Look at or Change the Calibration Code With the Indicator powered up and in the Run Mode press both buttons at the same time to go to Setup Scroll through the menu until the word CODE is displayed then press the Right button The display should look like this Figure 3 6 Changing the CAL Code Hook Load x 10 CAL j SETUP The CAL legend is turned on and the previously entered or computed Calibration Code is displayed To return to Run without changing the CAL Code press both the Right and Left buttons at the same time To change the Calibration Code use the Right button to select the digit to be changed then use the Left button to scroll the blinking digit to the desired number When the Calibration Code has been entered press both the Right and Left button at the same time to return to Run NOTICE Depending on the type of Load Cell the Calibration code could be a 3 or 4 digit number If the Calibration Code is a 3 digit number a leading zero 0 must be used For example if a Load Cell had a CAL Code of 395 it would be entered as 0395 If the load cell Calibration Code is not known or as a cross check the Indicator can generate the Calibration Code This is done by entering the weight of a known load into the Indicator LOAD routine and then lifting the load See the section Calibration by Lifting a Known Load Load Weigh System Operation Instructions The S
43. ts routine sets the display to read in pounds LB or kilograms KG To look at or change the Units With the Indicator powered up and in the Run Mode press both buttons at the same time to go to Setup Scroll through the menu until the word LB or KG is displayed then press the Right button The display should look like this Figure 3 10 Changing the Units Hook Load x 10 CAL LB KG The CAL legend is turned on and the previously set unit is displayed To return to Run without changing the units press both the Right and Left button at the same time To change the units press the Left button When the selection has been made press both the Right and Left button at the same time to return to Run The selected units are displayed when in the Run Mode Load Weigh System Operation Instructions The Setup Mode continued Indicator Version The Version routine displays the Indicator s hardware and software revision levels Version is set at the factory and cannot be changed Figure 3 11 Looking at Indicator Version Hook Load x 10 CAL LB KG SETUP UN ZERD ZERO Load Weigh System Operation Instructions 3 13 This page intentionally left blank Section 4 Operation Instructions Operating Procedures Operation Instructions Prior to a flight involving external load operations perform the following 1 Ensure that the Cargo Hook Kit has been properly installed and that the manual and e
44. ween this change and any of those other previously approved modifications including changes in Type Design will introduce no adverse effect upon the airworthiness of that rotorcraft II If the holder agrees to permit another person to use this certificate to alter the product the holder shall give the other person written evidence of that permission Wl Installation of this modification must be performed according to the Owners Manual Document N 120 092 00 Rev 3 dated 17 Jun 2005 including the placard of Onboard System n 215 190 00 IR dated 30 Jan 2006 IV Operation must be performed in accordance with FAA Approved Rotorcraft Flight Manual Supplement document No 121 003 00 Rev 1 dated 09 Sep 2004 or later approved revision V Maintenance of this installation must be performed in accordance with Instructions for Continued Airworthiness document N 123 007 00 Rev 3 dated 09 May 2005 and Service Manual document N 122 005 00 Rev 8 dated 30 Jun 2005 or later approved revisions j VI A copy of this Certificate and the Supplement referred on item IV above shall be maintained as part of the permanent records of the modified rotorcraft F 400 01B 08 04 Fl 02 de 02 H 02 2516 0 Sheet of 6 8 Certification
45. when rigging a load to the Cargo Hook Steel load rings are recommended to provide consistent release performance and resistance to fouling Figure 4 2 shows the recommended rigging and rigging to avoid but is not intended to represent all rigging possibilities It is the responsibility of the operator to ensure the cargo hook will function properly with each rigging Nylon type straps or similar material or rope must not be used directly on the cargo hook load beam If nylon straps or rope must be used they should be first attached to a steel primary ring Verify that the ring will freely slide off the load beam when it is opened Only the primary ring should be in contact with the cargo hook load beam Figure 4 2 Examples of Cargo Hook Rigging Recommended Avoid Primary Ring Long Line Operation Instructions 4 3 This page intentionally left blank Section 5 Maintenance Refer to the Instructions for Continued Airworthiness ICA manual 123 007 00 for maintenance of the cargo hook suspension system For maintenance of the cargo hook refer to Cargo Hook Service Manual 122 005 00 Instructions for Returning Equipment to the Factory Maintenance If an Onboard Systems product must be returned to the factory for any reason including returns service repairs overhaul etc obtain an RMA number before shipping your return NOTICE An RMA number is required for all equipment returns
46. zilian Approvals 6 5 Section 1 General Information Introduction The 200 258 00 200 259 00 and 200 259 01 Cargo Hook Suspension Systems are approved for installation on the following Bell helicopters Model Serial Numbers 206L 45001 45153 206L 1 45154 and on 206L 3 51001 and on 206L 4 52001 and on 407 All The system replaces the Bell kit part numbers 206 706 341 101 105 and 109 Auxiliary Equipment Kit Cargo Hook It must be installed with the Bell part number 206 706 341 7 9 103 111 113 117 123 or 125 Auxiliary Equipment Kit Cargo Hook Provisions or Onboard Systems P N 200 328 00 Fixed Provisions Kit The 200 328 00 fixed provisions kit is approved for the 407 model under Onboard Systems STC SRO1943SE 1 1 General Information Safety Labels The following definitions apply to safety labels used in this manual Indicates a hazardous situation which if not 1 D AN G F R avoided will result in death or serious injury Indicates a hazardous situation which if not avoided could result in death or serious injury Indicates a hazardous situation which if not avoided could result in minor or moderate injury Draws the reader s attention to important or N O C f unusual information not directly related to safety Used to address practices not related to personal injury 1 2 General Information Specifications Table 1 1 Suspension System Specifications Design load 3 000 I
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