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120-104-02 - Onboard Systems International

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1. Item Part Number Description Qty 1 517 047 00 Bushing 2 2 290 850 00 Airframe Attach Fitting 1 3 517 016 00 Bushing 1 System Part Numbers 6 3 System Part Numbers continued 232 166 00 232 166 01 Master Cylinder Assembly Os DESCRIPTION EC SSCP Std DS posmorte o a 29081600 fsan Sd 5 osno seen 1 6 fosso Psn TJ 7 200 8130 Spun 1 Cd s 09200 Jreservoir ia OJ Do somo orm 1 Do siso sew OJ 86 32 x 2 Button Head Cap Screw Du sos fu a 15 TJ stox082 00 Nu St id us 50090 we a i fions coer 1 Cd 16 _ 556 048 00 Cosa SCT C seor O Ring 18 51405500 Compression Sprin 1 19 51055200 Washer Pison Step 1 51500800 Sprm ooo a saio heon a id 22 25511800 Master Cylinder Bae JO 25 _ 514 060 00 Compression Spring OJ 24 51053000 4832x 3116 Nylon Tip Set Sew 1 232 166 01 for the B3 collective uses lever P N 290 811 01 PRAHAA System Part Numbers System Part Numbers continued 232 165 00 232 165 01 Master Cylinder Assembly with Plumbing 232 165 01 for the B3 collective uses Master Cylinder Assembly P N 232 166 01 System Part Numbers 6 5 System Part Numbers continued 232 140 01 Forward Attach Cable 6 6 Item Part Number Description Qty 1 232 177 00 Forward Attach Cable 1 2 290 851 00 Quick Release Pin I 3 53
2. 55M 32M Connector Bracket 16 19 mm VIEW LOOKING FORWARD 2 3 2 1 2 4 Electrical Wiring Installation continued Install the Ground Strap P N 270 125 00 terminal at the 3N ground connector bracket at the LH airframe beam at Y400 per the following 0 0 Figure 2 1 6 Ground Strap Installation Location Remove upper mounting hardware see below for 3N connector bracket and retain Prepare the surface for electrical bonding per Airbus Helicopters electrical bonding procedure Refer to section 20 02 07 of the Airbus Helicopters Standard Practices Manual Install ground strap terminal re using hardware removed per above step E o Route the Ground Strap to the load weigh and electrical release harnesses installed previously and route with these harnesses while securing with ty wraps to their termination points at the Connector Bracket Route the Ground Strap around the Connector Bracket and position it such that the disconnect fitting at the end can be routed through the connector access hole and extended below the lower fairing when installed Re install lower fairings if both the electric and hydraulic systems have been installed Installation Instructions 2 1 Electrical Wiring Installation continued The electrical schematic for the electrical release system and the load weigh system is shown below along with the aircraft s interface points Airbus Helicopters modification
3. Q Connect the end of the load cell cable to the fixed load weigh harness connector 55M installed per Section 2 1 Q Connect the hydraulic hose from the hook to the fitting installed at the belly of the helicopter 2 Installation Instructions 2 7 Filling Hydraulic Release System Each hydraulic system is typically shipped dry A label affixed to the Master Cylinder and Slave Cylinder assemblies will state if each hydraulic assembly has been filled and bled Proper bleeding is critical to the operation of the hydraulic release system An improperly bled system will not release the cargo hook mechanism A reservoir seal is installed beneath the reservoir lid This seal serves to prevent hydraulic fluid left over from the testing process from leaking during shipping The reservoir seal is for shipping purposes only and must be removed and discarded before bleeding or installation of the hydraulic release system If there is a need to fill and or bleed the system follow the procedures listed below If you need to remove and repair any items in the hydraulic system refer to 123 011 02 Instruction for Continued Airworthiness Filling and bleeding the hydraulic release system is most easily accomplished on the bench prior to installation on the aircraft This process may also be accomplished after the system is installed Filling and bleeding requires two persons one to inject hydraulic fluid through the system and the other to ob
4. The hydraulic release system installation consists of a fixed section and a removable section The fixed section is routed from the release lever at the collective underneath the cabin floor and aft to meet up with the electrical release harness as shown in Figure 2 2 1 Figure 2 2 1 is an overview of the hose routing and the figures following detail the support installations at various points Figure 2 2 1 Fixed Hydraulic Release System Installation Overview X 1790 15 X 2700 Centerline of fwd CONNECTOR BRACKET P N 290 884 00 View Looking Down See Figure 2 2 2 See Figure 2 2 7 Fuel Tank Support View Looking Outboard From A C Centerline Installation Instructions 2 7 2 2 Fixed Hydraulic Release System Installation continued 2 8 The hydraulic release system is supplied dry It is recommended that the system be filled and bled on the bench before installing on the helicopter Refer to section 2 6 for filling and bleeding instructions Mount the Release Lever Assembly to the collective stick with the Clamp Half P N 290 753 00 and two screws P N 510 390 00 provided pre assembled on the assembly as illustrated below NOTICE An optional clamp half P N 291 523 00 which can be installed in place of clamp half P N 290 753 00 and includes a 10 mm 394 in mounting hole e g for an accessory is available from the factory NOTICE If installing kit P N 200 280 03 for the AS350B3 model a shorter
5. Theory of Operation General Information The Cargo Hook Swing Suspension System is composed of e A suspended pyramid frame that supports the cargo hook e An electrical release system that provides means for release 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 e A hydraulic release system which provides a means of releasing a cargo hook load in the event of an electrical release system failure A lever mounted to the collective actuates it e Ground personnel may also release a load by the actuation of a lever located on the side of the cargo hook e A load weigh system which is comprised of an indicator mounted to the RH door pillar within the cockpit connected to a load cell between the cargo hook and frame A load is attached to the cargo hook by passing a 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 cause 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 ring slides off the load beam The load beam then remains in the open position awaiting th
6. hook the ground strap is installed in the same location as on P N 528 023 01 Apply a suitable conductive chemical surface treatment such as Alodine 1201 to the bare metal Attach the ground strap using the screw removed from previous cargo hook Attach the new electrical release harness P N 270 129 00 onto the cargo hook connector Fit the new Bumper P N 290 839 02 over the cargo hook Align the Bumper and Cargo Hook with the load cell and assemble attach bolt and hardware removed previously and cotter pin P N 510 178 00 refer to ICA 123 011 02 section 25 17 for orientation and hardware Route the load cell harness slave cylinder plumbing ground strap and electrical release harness through the bumper grooves refer to ICA 123 011 02 section 25 17 for routing Connect the electrical connectors ground strap connector and slave cylinder plumbing connector to the mating fittings at the Connector Bracket Bleed the hydraulic system per Section 2 7 Perform installation check out per Section 2 9 Installation Instructions 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 display 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 t
7. on April 13 2010 Associated Technical Documentation Definition and installation Onboard Systems Master Drawing List No 155 086 00 Rev 27 dated October 30 2009 approved by FAA Onboard Systems Owner s Manual No 120 104 01 for system model 20028001 Rev 10 dated October 30 2008 approved by FAA or No 120 104 02 for system mode 20028002 and 03 Revision 18 dated July 1 2009 approved by F or No 120 104 03 for system model 20028004 Revision 0 dated October 12 2009 approved by FAA Inspection and maintenance Onboard Systems Instructions for Continued Airworthiness No 123011 01 for system model 20028001 Rev 3 dated October 29 2007 approved by FAA or No 123011 02 for system model 20028002 and 03 Rev 5 dated January 27 2009 approved by FAA or No 123011 03 for system model 20028004 Rev O dated January 27 2010 approved by FAA and Onboard Systems Service Manual No 122005 00 for Keeperless Cargo Hook 528 023 01 Rev 17 dated March 9 2010 approved by FAA No 122 015 00 for Hydraulic Cargo Hook Rev 7 dated January 30 2009 approved by FAA No 122 017 00 for Keeperless Cargo Hook 528 029 00 Rev 8 dated March 10 2010 approved by ia OR Onboard Systems RFMS No 121 012 01 for system mode 20028001 Rev 2 dated June 12 2007 approved by FAA No 121 012 02 for system model 200 280 02 and 03 Rev 3 dated October 25 2007 approved by or No 121 012 03
8. s 07 4280 and 07 3450 are reflected below Earlier Airbus Helicopters configurations which affected how and where wire numbers MEIE ME2E and MEIOE of the electrical release harness and load weigh harness interface with the helicopter are shown on the following page Refer to the applicable Airbus Helicopters Wiring Diagrams Manual for additional information and for other cargo hook aircraft side wiring configurations that may not be shown For the C 39 Indicator backlighting install wire 2LK71E to an available pin in the instrument panel or console lighting circuit 31L for pre mod 07 4280 at 28 volts the indicator s internal bulb draws 25 mA If existing Airbus Helicopters cargo hook or load weigh wiring is installed and terminated at the locations below remove the wires completely or remove from connectors and cap and stow them Figure 2 1 7 Electrical Schematic 44ALP_ BREAKER PANEL Existing Eurocopter Wiring post Mod 07 4280 Sa Data
9. 1 1 290 772 00 Indicator Mount bracket 1 1 290 884 00 Connector Bracket 1 1 290 783 00 Relay Bracket 1 1 290 888 00 Retainer 1 1 290 889 01 Guard 1 1 290 893 00 Bracket 1 1 291 105 00 Friction Knob 1 1 445 005 00 Relay 1 1 500 065 00 Grommet Edging 1 1 505 014 00 Grommet 1 1 510 029 00 Nut 8 8 510 042 00 Washer 2 2 510 062 00 Washer 8 8 510 095 00 Washer 3 3 510 102 00 Nut 2 2 510 277 00 Screw 2 2 510 278 00 Washer 2 2 510 279 00 Nut 2 2 510 453 00 Bolt 2 2 510 457 00 Screw 4 4 510 475 00 Screw 3 3 510 481 00 Screw 8 8 510 486 00 Rivet 3 3 510 526 00 Cotter Pin 2 2 512 003 00 Ty wrap 5 5 512 005 00 Adel Clamp 4 4 610 024 00 Seal 1 1 Fuel drain guard component included with kits shipped after August 2010 Fuel drain guard P N 290 889 01 supersedes fuel drain guard P N 290 889 00 The 210 095 04 Indicator is equipped with NVG compatible lights It is an optional indicator that can be ordered in place of the 210 095 00 Indicator 1 5 Bill of Materials continued 1 6 The following is needed for installation of the fuel drain guard and is not included with the kit and should be obtained before installation is begun Table 1 5 Needed Supplies Description PR1422 B Sealant To complete the cargo hook installation the following Airbus Helicopters parts may be necessary to obtain these parts are frequently found to be on the aircraft from the factory or are standard Airbus Helicopters parts NO
10. 6 Added Half Clamp Pad EC P N 350A 41 1099 20 to the table of Eurocopter required part numbers 09 09 11 1 7 2 5 2 6 Updated electrical system interface information to include Eurocopter mod 073475 12 19 11 6 14 Replaced Cup Seal P N 556 038 00 with Quad Ring P N 556 097 00 inside Slave Cylinder assembly 02 19 13 1 7 2 5 2 6 Updated electrical schematic to reflect a c side wiring interface of post mods 07 4280 and 07 3450 Added note regarding post mod 07 4280 06 06 13 1 7 1 8 2 34 amp 6 11 Replaced Bumper P N 290 839 01 amp 290 839 00 with P N 290 839 02 05 09 14 Title 1 1 1 4 to 1 6 1 7 1 10 Section 2 4 3 4 3 6 2 amp 6 11 Updated Eurocopter to Airbus Helicopters load cell P N 210 249 00 with P N 210 249 03 Added note regarding contact P N 410 194 00 page 1 7 Replaced fuel drain guard P N 290 889 00 with 290 889 01 Updated load rigging instructions Replaced 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 Plea
11. Figure 4 1 Suspension Removal Shackle Assembly Safety Pin Quick Release Pin Re installing Removable Provisions Re install the removable provisions per the following instructions 1 Wipe off electrical connectors and the hydraulic quick disconnect fitting to remove any debris 2 Connect the electrical connector and the hydraulic quick disconnect fitting to the connector bracket A Operation Instructions Cargo Hook Loading 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 2 until an internal latch engages the load beam and latches it in the closed position Figure 4 2 Cargo Hook Loading Cargo Hook Rigging Extreme care must be exercised when rigging a load to the Cargo Hook Steel load rings are recommended to provide consistent release performance and resistance to fouling The following illustration 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 assure the cargo hook will function properly with each rigging Operation Instructions 43 Cargo Hook Rigging continued Nylon Type Straps and Rope 4 4 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 u
12. 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 scroll through the menu the menu item Right and Left buttons at the same time om Dampening Level sets the pilots Blinking display is previously entered DAMP preference for display dampening Dampening Level Select the desired dampening level by pressing the Left button Calibration Code matches the Indicator to Display is previously entered CAL Code The CODE the Load Cell 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 Display is a combination of load on the Load Oin to the installed Load
13. friction adjustment knob for the collective is required because of interference with the master cylinder assembly reservoir This item is supplied as P N 291 105 00 See below for installation instructions Figure 2 2 2 Release Lever Installation Release Lever Assembly Installation Instructions 2 2 Fixed Hydraulic Release System Installation continued Figure 2 2 3 B3 Collective Friction Knob Q Remove the collective to the extent necessary to remove the friction knob Refer to Airbus Helicopters maintenance manual for removal and re installation instructions Q Replace the OEM friction knob with the friction knob P N 291 105 00 provided O Re install collective per Airbus Helicopters maintenance manual instructions Q Mount the Release Lever Assembly P N 232 165 01 to the collective stick with the Clamp Half P N 290 753 00 and two screws P N 510 390 00 provided pre assembled on the assembly as illustrated below NOTICE Locate the Release Lever Assembly on the collective shaft as close as possible to the throttle twist grip as shown in Figure 2 2 4 Q Adjust the Friction Knob to its outermost position and verify that there is clearance with the reservoir on the release lever assembly 2 10 Installation Instructions 2 2 Fixed Hydraulic Release System Installation continued Figure 2 2 4 AS350B3 Release Lever Installation Release Lever Assembly NOTICE The lever posit
14. 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 3 4 Load Weigh System Operation Instructions The Setup Mode The C 39 Indicator can be used with a wide range 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
15. line may or may not be terminated vvith GEA a connector depending on manufacture date i A i SWING E ME1E mM o Bus 1 10A OPT1 Ja 23M EE 2 ae 1 1 I a i i 1 a xe x1 a2 ne 31ALP32 BREAKER PANEL y 13 ME2E H to KY gl i LJ 2 5A Pa 18 24M 32M ERA SAS N ar 3 i AJA A e ME4NE ME10E 7 Si a ate MESE E a MESE f 9 I o CARGO REL cyclic button SN 30M 55 AJJA 1 46 55M ATA WH B B f A 11 MEB7E 213 aon ire ll i l CHC WH OR DI D 20ALP J1A PIA DID WH BL Elle 1 U CA FLOOR U CAFLOOR JE 2LK72NE oll Bal es ES oa E EN FILE MEGNE alia Existing Eurocopter Wiring i A HIH 8 post Mod 07 3450 shown 1 1 gt E JIJ 3 i 5 K TE 7 L L BELLY DISCONNECT 1N A Y MJIM 2LK71E N ies ad TRI PILP l Note Data line included with NETAMENT SHE Load Weigh Harness P N 270 106 02 only LIGHTING Installation Instructions 2 5 2 1 Electrical Wiring Installation continued Figure 2 1 7 Wiring Schematic continued Y MEZE 4 ME 10E ME10E 20a Cyclic Lever PCB Existing Eurocopter Wiring Post Mod 07 3273 Existing Eurocopter Wiring pre mod 07 3475 Existing Eurocopter Wiring pre mod 07 1737 Existing Eurocopter Wiring post mod 07 1737 2 6 Installation Instructions 2 2 Fixed Hydraulic Release System Installation Remove the lower fairings on the helicopter in order to obtain access to hydraulic hose routing areas
16. 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 ifa Load Cell had a CAL Code of 395 it vvould be entered as 0395 Load Weigh System Operation Instructions The Setup Mode continued 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 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
17. thereby without the written permission of Onboard Systems By accepting this document the recipeint agrees to affix this legend to an duplication of reproduction in whole or part of the document of information disclosed thereby made persuant to such permission For a description of any revisions see document number 150 066 00 11 00 IN 279 MM MAX HOOK LOAD 2557 LBS CARGA MAXIMA NO GANCHO 1160 KGS 38 POINT FONT COLOR TO CONTRAST WITH BACKGROUND TITLE MAX LOAD PLACARD MATERIAL 3M SCOTCHCAL 3650 VINYL OR EQUIVALENT UNLESS OTHERWISE SPECIFIED DEN 1660 LBS DIMENSIONS ARE IN INCHES 04 03 07 MH TAK 215 201 00 SHEET 4 OF 1 0 5 DEG 08 E LINEAR be re REVISED 7 8 Certification Brazilian CHST Required Placards continued Install the following per section 2 7 This document when released outside Onboard Systems is supplied for identification engineering evaluation or inspection purposes only and shall not be duplicated used or disclosed to produce articles and or subject matter covered thereby without the written permission of Onboard Systems By accepting this document the recipeint agrees to affix this legend to any duplication of reproduction in whole or part of the document of information disclosed thereby made persuant to such permission For a description of any revisions see document number 150 066 00 1 88 I
18. 0 View Looking Outbd Installation Instructions 2 15 2 3 Cockpit Indicator Installation continued Q Drill three mounting holes in the RH door pillar to install the nut clips Reuse the electrical bonding screw at the fourth location see below Q After completing electrical bonding install the three nut clips Airbus Helicopters P N SL211M5 1 and fasten Indicator Bracket with three screws P N 510 475 00 and three washers P N 510 095 00 Figure 2 3 2 Indicator Bracket Hardware Electrical Bonding Screw Screw P N 510 475 00 Washer P N 510 095 00 O Install C 39 Indicator P N 210 095 00 or P N 210 095 04 onto bracket with hardware as illustrated below Figure 2 3 3 C 39 Indicator Installation C 39 Indicator Screw P N 510 457 00 4 2 16 Installation Instructions 2 4 Fuel Drain Guard Installation NOTICE If installing the Swing Kit on a helicopter that has NOT been retrofitted with the B 2 style dual fuel pump type tank Airbus Helicopters P N 350A55 1015 0251 the fuel drain guard installation is omitted Skip to section 2 5 In preparation for installing the fuel drain guard Q Obtain ProSeal sealant P N PR1422 B Q Verify that the fuel drain lever has been modified per AD 2005 03 08 requirements Completely drain the fuel from the fuel tank Begin disassembly of the fuel drain assembly by disconnecting the fuel drain control cable from the Lever Airbus Helicopters P N 350
19. 0 mm Go od Q Secure Relay Bracket with two screws P N 510 277 00 two washers P N 510 278 00 and two nuts P N 510 279 00 2 2 Installation Instructions 2 1 Electrical Wiring Installation continued Q Place relay socket part of 270 108 00 electrical harness into relay bracket mounting holes from below and secure to relay and relay bracket with hardware provided with relay as illustrated below Figure 2 1 4 Relay Installation Relay P N 445 005 00 Relay Bracket Val P N 290 783 00 E a i Relay Socket P N 445 004 00 part of 270 108 00 electrical harness Locate Connector Bracket P N 290 884 00 at forward fuel tank support frame as illustrated below Drill out pilot holes in bracket to 0 129 0 132 3 2 3 4 mm diameter and drill fuel tank support to match Secure Connector Bracket to fuel tank support with three rivets P N 510 486 00 The hook release connector 32M and load cell connector 55M will be installed on the Connector Bracket later in the installation The hydraulic connector must be installed prior to installing the connectors Figure 2 1 5 Connector Bracket Installation Load Cell Connector 146 152 mm Hook Release Connector Installation Instructions Hydraulic Connector pe 5 75 6 00 in
20. 01 supersedes fuel drain guard P N 290 889 00 The 210 095 04 Indicator is equipped with NVG compatible lights It is an optional indicator that can be ordered in place of the 210 095 00 Indicator General Information Bill of Materials continued General Information The following items are included with the 200 280 03 Swing Suspension System and the 210 202 03 fixed provisions kit The 200 280 03 system uses the 210 201 02 removable provisions kit see Table 1 3 If shortages are found contact the company from whom the system was purchased Table 1 4 Onboard Systems Bill of Materials 200 280 03 Part No Description 200 280 03 210 202 03 120 104 02 Owner s Manual 1 1 121 012 02 RFMS 1 1 122 015 00 Cargo Hook Service Manual 1 123 011 02 ICA 1 1 210 095 00 C 39 Indicator 1 1 210 095 04 C 39 Indicator NVG Lights 1 1 210 201 02 Removable Provisions Kit 1 215 165 00 AS 350 Multiple Decal Sheet 1 1 215 166 00 Max Hook Load 3086 Decal 1 215 168 00 Max Hook Load 2557 Decal 1 232 137 01 Shackle Assembly 4 4 232 140 01 Forward Attach Cable Assembly 2 232 141 01 Aft Attach Cable Assembly 2 232 145 02 Swing Frame Assembly 1 232 165 01 Master Cylinder Assembly 1 1 270 106 02 LW Internal Harness 1 1 270 108 00 Release Internal Harness 1 1 270 125 00 Ground Strap Fixed
21. 1 015 00 Lanyard Cable 2 4 531 016 00 Crimp Sleeve 2 5 510 464 00 Hitch Pin 1 6 510 438 00 Bolt 1 7 510 221 00 Washer 3 8 510 440 00 3 8 Castellated Nut 2 9 510 178 00 Cotter Pin 2 10 510 439 00 Bolt 1 11 232 142 00 Lower Attach Gimbal Assembly 1 12 290 749 00 Standoff Bushing 2 System Part Numbers System Part Numbers continued 232 141 01 Aft Attach Cable Assembly Item Part Number Description Qty 1 232 178 00 Aft Attach Cable 1 2 290 851 00 Quick Release Pin 1 3 531 015 00 Lanyard Cable 2 4 531 016 00 Crimp Sleeve 2 5 510 464 00 Hitch Pin 1 6 510 438 00 Bolt 1 7 510 221 00 Washer 3 8 510 440 00 3 8 Castellated Nut 2 9 510 178 00 Cotter Pin 2 10 510 439 00 Bolt 1 11 232 142 00 Lower Attach Gimbal Assembly 1 12 290 749 00 Standoff Bushing 2 System Part Numbers 6 7 System Part Numbers continued 232 142 00 Lower Attach Cable Gimbal Assembly 6 8 Item Part Number Description Qty 1 517 048 00 Bushing 2 2 290 746 00 Lower Cable Gimbal 1 3 517 016 00 Bushing 1 System Part Numbers System Part Numbers continued 232 143 01 Loadcell Gimbal Assembly Item Part Number Description Qty 1 517 056 00 Bushing Upper Hook Gimbal 2 2 290 841 00 Gimb
22. 10 202 02 210 201 02 120 104 02 Owner s Manual 1 1 1 121 012 02 RFMS 1 1 1 122 015 00 Cargo Hook Service Manual 1 1 123 011 02 ICA 1 1 1 210 095 00 C 39 Indicator 1 1 210 095 04 C 39 Indicator NVG Lights 215 165 00 AS 350 Multiple Decal Sheet 1 1 215 166 00 Max Hook Load 3086 Decal 1 1 215 168 00 Max Hook Load 2557 Decal 1 1 232 137 01 Shackle Assembly 4 4 232 140 01 Fwd Attach Cable Assembly 2 2 232 141 01 Aft Attach Cable Assembly 2 2 232 145 02 Svving Frame Assembly 1 1 232 165 00 Master Cylinder Assembly 1 1 270 106 02 LW Internal Harness 1 1 270 108 00 Release Internal Harness 1 1 270 125 00 Ground Strap Fixed 1 1 290 772 00 Indicator Mount bracket 1 1 290 884 00 Connector Bracket 1 1 290 783 00 Relay Bracket 1 1 290 888 00 Retainer 1 1 290 889 01 Guard 1 1 290 893 00 Bracket 1 1 445 005 00 Relay 1 1 500 065 00 Grommet Edging 1 1 505 014 00 Grommet 1 1 510 029 00 Nut 8 8 510 042 00 Washer 2 2 510 062 00 Washer 8 8 510 095 00 Washer 3 3 510 102 00 Nut 2 2 510 277 00 Screw 2 2 510 278 00 Washer 2 2 510 279 00 Nut 2 2 510 453 00 Bolt 2 2 510 457 00 Screw 4 4 510 475 00 Screw 3 3 510 481 00 Screw 8 8 510 486 00 Rivet 3 3 510 526 00 Cotter Pin 2 2 512 003 00 Ty wrap 5 5 512 005 00 Adel Clamp 4 4 610 024 00 Seal 1 1 Fuel drain guard component included with kits shipped after August 2010 Fuel drain guard P N 290 889
23. 68 00 feature black letters on a transparent background If being installed on a dark colored helicopter the lettering may not be readily visible In this instance new placards of the same size and with the same text may be fabricated with a different background to provide visibility The lettering must contrast with the background NOTICE If installation is being done under a Brazilian CHST bilingual placards are required The required placards are illustrated in Section 7 fabricate as shown or contact Onboard Systems for price and availability Install appropriate load limitation placard P N 215 200 00 1400 kg max hook load or P N 215 201 00 1160 kg max hook load dependent on the model of AS350 on which the system is being installed Install SOLTA CARGA placard P N 215 202 00 on the manual release lever in the cockpit over or next to the CARGO RELEASE engraving 2 31 2 9 Installation Check Out After installation of the Cargo Hook Swing Suspension System perform the following functional checks Q Swing the installed cargo hook and suspension to their full extremes to ensure that the hydraulic hose and the electrical harnesses have enough slack to allow full swing without straining or damaging the cables The hose or harnesses must not be the stops that prevent the cargo hook and suspension from swinging freely in all directions Q With no load on the cargo hook load beam pull the release lever on
24. 74 P N Description Qty 045004A 127A Cargo Hook Sling Switch 1 1180 01 2 5A Circuit Breaker 2 5A 1 Alt P N ECS0744A02A5 1170 01 15A Circuit Breaker 15A 1 Alt P N ECS0744B 15A0 AS350B2 and B3 aircraft with modification 073475 introduced by Airbus Helicopters Service Bulletin No AS350 25 01 09 incorporated use a 10 amp circuit breaker installed in the 44 ALPHA panel rather than the 15 amp circuit breaker listed in Table 1 8 This 10 amp circuit breaker P N EN2495 10AM may be necessary to obtain For AS350 B2 and B3 aircraft post mod 07 4280 refer to the Airbus Helicopters IPC for Sling switch and circuit breaker P Ns For early B2 models with a Honeywell switch panel to connect the electrical harnesses to the switch panel it will be necessary to obtain two IDC contacts that are not supplied with the kit Amp P N 640632 3 Onboard Systems P N 410 194 00 Kit P N 200 280 01 which uses a cargo hook with a mechanical release cable as the means for secondary release can be converted to Kit P N 200 280 02 using upgrade kit P N 200 306 00 or to Kit P N 200 280 03 using upgrade kit P N 200 306 01 See Section 2 9 for installation instructions Table 1 9 Onboard Systems Bill of Materials Upgrade Kit P N 200 306 00 Part No Description Qty 270 129 00 Electrical Release Harness pa 232 209 00 Cargo Hook Slave Cylinder Assembly 290 839 02 Hook Bumper 232 165 00 Master C
25. A55 1043 20 To free the control cable remove the Sleeve Airbus Helicopters P N N1 SALU and Cable Grip Airbus Helicopters P N 58 2 009 See Figure 2 4 1 Figure 2 4 1 Removing Control Cable Installation Instructions 2 17 2 4 Fuel Drain Guard Installation continued 2 18 Q Remove and retain spring Airbus Helicopters P N 350A55 1044 21 and Lever Remove the cable support bracket Retain the two attachment screws Remove the connections from the common ground point on the lever retainer D oO DO Remove the safety wire securing the Fuel Drain Valve Airbus Helicopters P N A1282Z3 Remove the Fuel Drain Valve and the Retainer from the tank Discard used Fuel Valve Seal Airbus Helicopters P N SD16X 21P Q Remove the residual sealant from the tank taking care to not mar the sealing surface Prepare the area for sealing per Airbus Helicopters Standard Practices Manual Figure 2 4 2 Fuel Drain Disassembly Complete Prepare the Retainer P N 290 888 00 for electrical bonding by removing anodize from the area shown in Figure 2 4 3 Figure 2 4 3 Prepare Retainer Remove anodize this area Installation Instructions 2 4 Fuel Drain Guard Installation continued Q Prepare PR1422 B or equivalent fuel tank sealant per Airbus Helicopters Standard Practices Manual Apply sealant to Retainer as shown in Figure 2 4 4 Retain unused sealant to ensure proper cure Figure 2 4 4 Apply Sealant Apply seal
26. ANGEMENT 4 Remove screws reservoir lid reservoir seal and baffle from the master cylinder reservoir as shown in Figure 2 7 3 the reservoir seal is for shipping purposes only after removal discard or retain for future shipping or storage NOTICE The reservoir seal is for shipping purposes only and must be removed and discarded before bleeding or installation of the hydraulic release system 2 26 Installation Instructions 2 7 Filling Hydraulic Release System continued Figure 2 7 3 Reservoir Disassembly N screw 2 Reservoir Lid Reservoir Seal 5 Remove the screw and stat o seal on the slave cylinder see Figure 2 7 4 Figure 2 7 4 Screw and Stat o seal Removal SLAVE CYLINDER 6 Fill the syringe with approximately 35 cc of MIL H 5606 fluid and purge any remaining air in the syringe and tubing Screw the end of the bleed adapter into the screw hole on the slave cylinder to create a tight seal See Figure 2 7 5 7 While observing the reservoir slowly push on the syringe plunger to force fluid through the slave cylinder hydraulic hose and up to the master cylinder reservoir There will be some resistance during filling this is normal Installation Instructions 2 27 2 7 Filling Hydraulic Release System continued 2 28 Injecting the fluid into the system too rapidly may cause the fluid to spray up and out of the master cylinder reservoir Wear safety glasses when observ
27. ASA TCDS R 008 Issue 04 23 November 2009 The Certification Basis for the original product and the following additional or alternative airworthiness requirements are applicable to this certificate approval Change under Revision 2 complies with FAR 27 at amat 27 39 The requirements for environmental protection and the associated certificated noise and or emissions levels of the original product are unchanged and remain applicable to this certificate approval Description of Design Change External Load Swing Suspension System models 200 280 01 and 04 with Keeperless Cargo Hooks and model 200 280 02 and 03 with Hydraulic Cargo Hooks Revision 1 introduced cargo hook kit 200 280 03 with a collective friction knob and a new release lever to accommodate the AS350B3 style collective configuration Revision 2 introduced cargo hook kit 200 280 04 with Keeperiess Cargo Hook 528 029 00 See Continuation Sheetis For the European Aviation Safety Agency Date of issue 21 06 2010 pre fet Massimo MAZZOLETTI Certification Manager Rotorcraft Balloons Airships Note i The following numbers are tsted on the certificate EASA old Project Number EASA IM R 5 01324 REV 2 SUPPLEMENTAL TYPE CERTIFICATE 10016937 REV 2 ONBOARD SYSTEMS INT 7 10 Certification EASA STC continued European Aviation Safety Agency X This STC is the validation of FAA STC SRO1164SE issued on January 22 2003 and last amended
28. Cell and to the Cell and normal load cell zero offset Remove helicopter After this procedure the all weight from the installed Load Cell except E i the Cargo Hook and press any button to display will be zero when no load is on complete the procedure and return to the Run the Cargo Hook Mode Load is used to calibrate the system by No previous display is shown Enter the LOAD lifting 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 i e 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 is previously entered number To Scale Indicator to an optional remote analog change the number use the Right button to mien 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 Display is previously selected unit To change or kilograms the unit use the Left button XX V Version is the revision level of the Version is for information only it cannot be Indicator hardware and software changed 3 6 Load Weigh System Operation Instructions The Setup Mode c
29. IFICATE 10016937 REV 2 ONBOARD SYSTEMS INT
30. IONAL DE AVIA O CIVIL BRASIL CERTIFICADO DE HOMOLOGA O SUPLEMENTAR DE TIPO Supplemental Type Certificate N MERO 2007S04 12 Numbe emitido com base na Lei n 7565 C digo Brasileiro de Aeron utica de 19 de dezembro Este certificado 1986 This certificate issued in the basis of the Law No 7565 C digo Brasileiro de Aeron utica dated 19 mbro de 1986 6 conferido ao a Onboard Systems va st 13915 NW 3 Court Vancouver WA 98685 USA r 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 roje design of the product mentioned below with the limitations and conditions Patas q as especificadas satisfeito aos requisitos de aeronavegabilidade aplic veis specified hereon met the applicable ai TE iness requirements Produto Original N mero do Certificado de Tipo 8812 ANAC roduct Type Certificate No nte Eurocopter France Fabrica Manufacturer Modelo s AS 350 BA AS 350 B1 AS 350 B2 and AS 350 B3 Model s DESCRI O DA MODIFICA O AO PROJETO DE TIPO Description of Type Design Chan Installation of Onboard Systems Model 200 280 01 or 200 280 02 Cargo Hook Swing Suspension System in accordance with Onboard Systems Owner s Manual No 120 104 01 Rev 5 dated 3 Apr 2007 or Owner s Manual No 120 104 02 Rev 9 dated 3 Apr 2007 or later approved revisions This CHST validate
31. N 48 MM JI 0 28 IN F 7 MM OLTA CARGA 12 POINT FONT BLACK BACKGROUND COLOR WHITE TITLE MATERIAL 3M SCOTCHCAL 3650 VINYL OR EQUIVALENT C NBUARD SYSTEMS CARGO RELEASE PLACARD DIMENSIONS ARE IN INCHES DAN 04 03 07 MH UNLESS OTHERWISE SPECIFIED TOLERANCES ARE CAK 215 202 00 2 03 0 5 DEG 001 REVISED LINEAR ANGLES SHEET 4 OF 1 Certification 7 9 EASA STC European Aviation Safety Agency SUPPLEMENTAL TYPE CERTIFICATE 10016937 REV 2 This Supplemental Type Certificate is issued by EASA acting in accordance with Regulation EC No 216 2008 on behalf of the European Community its Member States and of the European third countries that participate in the activities of EASA under Article 66 of that Regulation and in accordance with Commission Regulation EC No 1702 2003 to ONBOARD SYSTEMS INT 13915 NW 3rd COURT VANCOUVER WA 98685 USA and 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 TC Number EASA R 008 TC Holder EUROCOPTER Model AS 3508 AS 350 B1 Model AS 350 B2 AS 350 B3 Model AS 350 BA AS 350 D Original STC Number FAA STC SR01164SE EASA Certification Basis As per E
32. S350B2 model helicopters The P N 200 280 03 Cargo Hook Swing Suspension System kit is the same as the 02 kit except is includes a different release lever assembly and it includes a friction knob for the collective It is intended for installation on the AS350B3 model Newer Cargo Hook Swing Suspension System kits shipped after August 2010 include a fuel drain guard which is compatible with fuel tanks on AS350 B2 and B3 helicopters and on AS350B B1 BA and D models that have been retrofitted with the B 2 style dual fuel pump type tank The Airbus Helicopters part number for this tank is 350A55 1015 0251 The fuel drain guard is intended for helicopters with their fuel drain levers previously modified per AD 2005 03 08 See Theory of Operation section for description of fuel drain guard 1 1 Safety Labels The following definitions apply to safety labels used in this manual Indicates a hazardous situation which if not T D AN G F 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 CI 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 Specif
33. TICE These items may or may not be installed with a standard aircraft therefore verification is recommended before purchasing them Table 1 6 Airbus Helicopters Part Numbers P N Description Quantity 22201BE120074L Screw 4 23111AG120LE Washer 8 ASN52320BH120N Nut 4 DHS751 160 62 Grommet 1 SL211M5 1 Nut 3 A3125 2 H179 Quick Disconnect Clamp 2 350A41 1097 20 Half Clamp Rear 2 350A 41 1099 20 Half Clamp Pad 2 350A86 0020 33 Bracket 1 ASNAO0078A403 Rivet 3 The cargo hook electrical system interfaces with the aircraft s electrical panel Earlier versions pre mod 07 3274 of the AS350 utilize a fuse type switch panel The following electrical panel components for these versions are typically found to be on the aircraft but may be necessary to obtain Table 1 7 Airbus Helicopters Electrical Parts Pre mod 07 3274 P N Description Qty DHS775 160 42 Indicator Light Body 1 DHS775 240 22 Indicator Light 1 EN2240 6839 Lamp 4 DI 2 5 Fuse 2 5A 1 DA8 16A Fuse 16A 1 AS350B2 and B3 aircraft with modification 07 3274 incorporated utilize a circuit breaker type switch panel The following electrical panel components for these versions are typically found to be on the aircraft but may be necessary to obtain General Information Bill of Materials continued General Information Table 1 8 Airbus Helicopters Electrical Parts with Mod 07 32
34. aixo 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 Motor as especificadas satisfeito aos requisitos de aeronavegabilidade aplic veis ified hereon met pplicable airworthiness requirements Produto Original N mero do Certificado de Tipo 84 FN 157 DGAC France Original roduct pe Certificate Fabricante Eurocopter France Manufacturer Modelo s AS 350 B Model s DESCRI O DA MODIFICA O AO PROJETO DE TIPO Description of Type Design Cha Installation of Onboard Systems Model 200 280 01 or 200 280 02 Cargo Hook Swing Suspension System in accordance with Onboard Systems Owner s Manual No 120 104 01 Rev 5 dated 3 Apr 2007 or Owner s Manual No 120 104 02 Rev 9 dated 3 Apr 2007 or later approved revisions This CHST validates in Brazil the STC SRO1164SE issued by FAA USA LIMITA ES E COND Limitations and ONDI OES See continuation sheet for applicable data Dates of 21 Dec 2006 Da emiss o 13 Apr 2007 Da reemiss o Application Issue Reissue Pa j Gerente Gera Cortica o do Diretor Presidente Coral Aeronautical de Prod iutos Aeron Director President F 400 01C 05 06 7 6 Certification Brazilian CHST continued z gt ANAC ae re re e AG NCIA NACIONAL DE AVIA O CIVIL Folha de Continua o ao Cont
35. al Link 1 3 517 046 00 Bushing Lower Hook Gimbal 2 4 518 003 00 Grease Fitting 1 System Part Numbers 6 9 System Part Numbers continued 232 145 02 Swing Frame Assembly IV LIT AIGWASSV HOd LASHS das System Part Numbers 6 10 System Part Numbers continued 232 145 02 Swing Hook Frame Assembly PART OF ITEM 1 ASSEMBLY GROUND STRAP CONNECTION 15 210 249 03 Swing Load Cell Assembly 16 270 126 00 Item Part Number Description Qty 1 232 145 25 Swing Frame Assembly 1 2 510 443 00 Bolt 1 3 290 740 00 Shaft Retaining Bushing 2 4 290 739 00 Shaft Gimbal 1 5 510 220 00 Washer 1 6 510 178 00 Cotter Pin 1 7 270 129 00 Lower Electrical Release Cable 1 8 510 170 00 Nut 1 9 510 174 00 Washer 1 10 510 183 00 Washer 2 11 510 320 00 Nut Castellated 1 12 528 028 00 Talon LC Hydraulic Cargo Hook 1 13 290 775 00 Long Hook Attach Bolt 1 14 290 839 02 Hook Bumper 1 1 1 Ground Strap Supersedes P N 210 243 00 amp P N 210 199 01 and P N 210 199 00 These assemblies are interchangeable Supersedes 290 839 01 and 290 839 00 These parts are interchangeable System Part Numbers 6 11 System Part Numbers continued 6 12 232 145 02 Swing Hook Frame Assembly continued Item Part Number Descriptio
36. ant to this surface Figure 2 4 5 Position Guard NOTICE On some aircraft the guard may have to be modified to fit the key on the fuel tank In these cases the sides of the clearance slot on the guard should be widened the minimum amount necessary in order to fit over the key See figures 2 4 6 and 2 4 7 Installation Instructions 2 19 2 4 Fuel Drain Guard Installation continued Figure 2 4 6 Fuel Tank Key Figure 2 4 7 Modification of Guard Slot Q Carefully place the Retainer inside the Guard by inserting the tab through the slot in the Guard Press the retainer to the tank firmly and center it about the drain hole See Figure 2 4 8 Figure 2 4 8 Retainer Guard Assembly Q Secure the Guard and Retainer by re installing the Fuel Drain Valve with Fuel Valve Seal P N 610 024 00 Airbus Helicopters P N SD16X 21P Use a flat blade screwdriver to prevent the Retainer from twisting when tightening the Fuel Drain Valve Torque per Airbus Helicopters specifications NOTICE The guard is not intended to fit tightly with the fuel tank When properly installed the guard should have freedom to move slightly 2 20 Installation Instructions 2 4 Fuel Drain Guard Installation continued Q Secure the Fuel Drain Valve with safety wire using the small hole in the retainer tab O Re install the electrical connections to the new Retainer tab per Airbus Helicopters Electrical Bonding Procedure Refer to Air
37. bus Helicopters Standard Practices Manual 20 02 07 Q Install the Lever by placing it in Retainer slot and rotating upwards Secure with cotter pin P N 510 526 00 See Figure 2 4 9 Figure 2 4 9 Install Lever COTTER PIN O Install a second cotter pin through the other holes in the Guard this cotter pin is for valve protection only and is not used for rigging purposes Q Prepare to install Bracket P N 290 893 00 by threading the control cable through the Bracket hole Install Bracket using the two screws removed previously Q Pass the cable through the spring and then the Lever Install the Sleeve and Cable Grip To avoid inadvertent fuel loss Airbus Helicopters P N 58 2 009 Cable Grip must be used with this installation Q Adjust the cable travel by doing the following allow the lever to rest against the cotter pin stop Slide the Cable Grip up to the bottom of the lever and secure See Figure 2 4 10 Installation Instructions 2 21 2 4 Fuel Drain Guard Installation continued Figure 2 4 10 Adjust Cable Travel Q Check the cable adjustment with the release handle on the side of the aircraft There should be a minimum of 25 inch 6mm cable travel before valve opens Adjust the Cable Grip as required Q Trim excess cable to within 25 of cable grip Q Allow the sealant to cure per Airbus Helicopters Standard Practices Manual before adding fuel Verify proper cure of unu
38. cle 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 should 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 bo
39. d 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 O If fuel drain guard was installed pull the handle on the side of the helicopter and verify that fuel is dispensed from the valve Component Weights The weights and cgs of the Cargo Hook Swing Suspension System components are listed below Table 2 3 Component Weights Removable Provisions 30 0 lbs 13 6 kg 133 in 3375 mm 5 9 Ibs 2 7 kg 110 in 2794 mm Fuel Drain Guard 0 4 lbs 18 kg 135 in 3430 mm 36 3 lbs 16 5kg 129 4 in 3288 mm The removable provisions include the swing suspension w hook external manual release cable and external electrical release cable These items are easily removed if they are not needed on the helicopter s mission The fixed provisions are those items of the kit that remain on the aircraft These include the fixed manual release cable internal electrical wire harnesses the load weigh indicator and the miscellaneous brackets that support these items Included with newer kits kits shipped after August 2010 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 Place the Rotorcraf
40. e continued 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 OUT UN ZEI RO 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 scroll 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 3 10 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 cy
41. e 28 MIL G 81322 Fasten the two shorter cable assemblies P N 232 140 01 onto the forward pivot points of the suspension frame and the two longer cable assemblies P N 232 141 01 to the aft pivot points The forward end of the suspension is determined by the orientation of the cargo hook When the suspension is installed the cargo hook load beam must point to the left side of the helicopter Installation Instructions 2 23 2 6 Swing Suspension Installation O Install the Swing Suspension onto the aircraft by attaching the suspension cable clevises to the INBOARD holes of the Shackle Assemblies with the Quick Release Pins P N 290 851 00 as shown in Figure 2 6 1 Install the attached safety pins at each Quick Release Pin Apply grease to quick release pins before installing recommended lubricants are AeroShell 17 MIL G 21164 or Mobilgrease 28 MIL G 81322 Figure 2 6 1 Cargo Hook Swing Suspension Assembly Installation Shackle Assembly Safety Pin Quick Release Pin O Connect the end of the cargo hook electrical release cable to the fixed electrical release connector 32M installed per Section 2 1 See Table 2 2 for pin out information Table 2 2 Cargo Hook Connector Function PA ora E Power TI The cargo hook is equipped with a suppression diode that will be damaged if the cargo hook electrical connection is reversed Q Connect the Ground Strap from the hook to the fixed ground strap installed per Section 2 1
42. e Type Design Change continued SYSTEM INSTRUCTIONS FOR CONTINUED AIRWORTHINESS PART NUMBER PIN AND CARGO HOOK SERVICE MANUAL 200 280 01 120 104 01 Revision 1 dated 123 011 01 Revision 0 dated August 11 2004 September 29 2004 122 005 00 Revision 15 dated April 23 2009 120 104 02 Revision 10 dated 123 011 02 Revision 5 dated January 27 2009 May 23 2007 122 015 00 Revision 7 dated January 30 2009 120 104 02 Revision 10 dated 1 123 011 02 Revision 5 dated January 27 2009 May 23 2007 122 015 00 Revision 7 dated January 30 2009 120 104 03 Revision 0 dated 123 011 03 Revision 0 dated January 27 2010 October 12 2009 122 017 00 Revision 5 dated July 27 2009 Limitations and Conditions continued SYSTEM PART NUMBER ROTORCRAFT FLIGHT MANUAL SUPPLEMENT 200 280 01 121 012 01 Revision 2 dated June 12 2007 200 280 02 121 012 02 Revision 3 dated October 25 2007 200 280 03 121 012 02 Revision 3 dated October 25 2007 121 012 03 Revision 0 dated March 4 2010 A copy of this certificate FAA approved RFMS ICA and Service Manual must be maintained as part of the permanent records of 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 END Any alteration of this certificate is punishable by a fine of not exceeding 1 000 or imprisonment no
43. e next load The Cargo Hook Swing Kit includes a fuel drain guard The fuel drain guard protects the fuel drain valve on the helicopter from accidentally being opened or damaged by the cargo swing The fuel drain valve is located on the bottom of the fuel tank and extends below the belly skin of the helicopter In this position it is vulnerable to damage or uncommanded opening The most common occurrence of the cargo hook swing suspension striking the fuel drain valve happens when the helicopter lands on snow or on uneven terrain The swing has limited ground clearance and when the skid gear sinks into the snow the swing suspension is pushed upward into the fuel drain valve opening it and causing fuel to drain The fuel drain valve can also be opened in flight by the swing suspension flying vertically due to aerodynamics when ferrying with no load or from recoil effects from releasing large cargo hook loads 1 9 Theory of Operation continuea The systems feature several improvements over the original 200 280 00 system 1 10 The swing frame now has an additional gimbal near where the hook attaches and spherical rod ends on the sides This allows the frame to distribute the loads between the four cables more effectively As the swing moves from side to side under the helicopter the four cables all describe their own arcs With a load applied to a rigid swing frame something has to give to accommodate this geometry This can be observed by
44. for system model 200 280 04 Rev 0 dated March 4 2010 approved by FAA Note The following numbers are listed on the certificate EASA old Project Number EASA IM R 5 01324 REV 2 SUPPLEMENTAL TYPE CERTIFICATE 10016937 REV 2 ONBOARD SYSTEMS INT EASA STC continued X European Aviation Safety Agency q n or later revisions of the above listed documents approved by EASA in accordance with EASA ED Decision 2004 04 CF or subsequent revisions of this decision Limitations 1 EASA approved AS350 Flight Manual and lt Extemal Load Transport Cargo Swing gt FM supplement are required 2 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 3 Installation and operation of the system on AS350B3 with the modification OP 3369 incorporated is not approved Conditions Prior to installation of this modification it must be determined that the interrelationship between this modification and any other previously installed modification and or repair will introduce no adverse effect upon the airworthiness of the product This Certificate shall remain valid unless otherwise surrendered or revoked end Note The following numbers are fisted on the certificate EASA old Project Number EASA IM R S 01334 E REV 2 SUPPLEMENTAL TYPE CERT
45. he 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 Load Weigh System Operation Instructions 3 7 The Setup Mode continued 3 8 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 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 x10 CAL u SETUP UN ZERO The CAL legend is turned on and the previously entered or computed Calibration Code is displayed To return to Run vvithout changing the CAL Code press both the Right and Left buttons at the
46. he 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 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 on in the Run Mode After the Indicator has been correctly installed power it up by activating the aircraft electrical system The Indicator will go through a self diagnostic routine During this routine the display will display all of the digits and legends 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 Fi ure 3 2 After Diag nostic Routine Hook Load x 10 CAL I SETUP UN ZERO zi 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 SETUP UN ZERO ZERO The illustration is a ty
47. ications Design load 3 086 lbs 1400 kg Design ultimate strength 11 574 lbs 5250 kg Unit weight Fixed Provisions 5 5 lbs 2 5 kg Unit weight Removable Provisions 30 lbs 13 6 kg Table 1 2 P N 528 028 00 Cargo Hook Specifications Design load Design ultimate strength Electrical release capacity Mechanical release capacity Force required for mechanical 12 Ibs max Master Cylinde release at 3 500 lb Electrical requirements 22 32 VDC 6 9 10 amps Minimum release load Unit weight 3 0 pounds 1 35 kg Mating electrical connector PCOSA8 2S Load capacities given are for the equipment described only Loading limits for your particular helicopter model still apply Consult your flight manual 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 200 280 02 Swing Suspension System the 210 202 02 fixed provisions kit and the 210 201 02 removable provisions kit If shortages are found contact the company from whom the system was purchased See Table 1 4 for kit P N 200 280 03 Table 1 3 Onboard Systems Bill of Materials 200 280 02 Part No Description 200 280 02 2
48. ing fluid reservoir while filling Figure 2 7 5 Injecting Hydraulic Fluid Bleed Adapter Female X Barb Fitting PVC Tubing 8 Continue to force fluid into the master cylinder reservoir until the reservoir is approximately half full NOTICE If bleeding an already filled system you may need to draw fluid from the master cylinder reservoir during this step to prevent overflow 9 Remove the bleed adapter from the screw hole Re install the Stat O Seal P N 510 496 00 and screw P N 510 493 00 see Figure 2 7 6 Installation Instructions 2 7 Filling Hydraulic Release System continued Figure 2 7 6 Screw Re installation 3 Stat O Seal 10 Allow the system to rest for several minutes This will allow any air to rise through the system 11 Very slowly pull the release lever on the master cylinder and watch for bubbles If bubbles are observed rising within the reservoir continue to slowly cycle the lever until there are no more Actuating the lever releases air trapped within the master cylinder Pull the lever very slowly When the reservoir is not baffled and capped a hard pull will cause fluid to erupt over the edge of the reservoir Installation Instructions 2 29 2 7 Filling Hydraulic Release System continued 2 30 12 Check the system for air by actuating the lever firmly until it bottoms out Check the push rod position see Figure 2 7 7 If the green area
49. inuation Sheet to CERTIFICADO DE HOMOLOGA O SUPLEMENTAR DE TIPO Supplemental Type Certificate N MERO 2007S04 11 LIMITA ES E CONDI ES Limitafions and Conditions The approval of this type design change 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 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 Operation must be performed in accordance with FAA approved Rotorcraft Flight Manual Supplement RFMS document No 121 012 001 Rev 0 dated 19 Oct 2004 or Supplement No 121 012 02 Rev 0 dated 2 Feb 2005 or later approved revisions This modification must be inspected and maintained in accordance with section ATA 5 of the Onboard Systems Instructions for Continued Airworthiness document No 123 011 01 Rev 0 dated 11 Aug 2004 or document No 123 011 02 Rev 0 dated 13 Dec 2004 and Service Manual No 122 005 00 Rev 9 dated 3 Jan 2006 or Service Manual No 122 015 00 Rev 4 dated 6 Jul 2006 or later approved revisions A copy of this Certificate Supplement and Mai
50. ion is to be adjusted if necessary at installation check out after the system is filled and bled Q Route the hose to underneath the cabin floor through the existing slot If the slot in floor does not exist create one with dimensions as shown below in the cabin floor 43 mm from the collective pitch lever unit and 150 mm forward of X1790 15 see below and install the grommet Airbus Helicopters P N DG 38 Figure 2 2 5 Cabin Floor Hole Detail 25mm Collective Pitch no Lever Unit SN Fwd A C Centerline 150mm FROM X 1790 15 VIEW LOOKING DOWN 2 10 Installation Instructions 2 2 Fixed Hydraulic Release System Installation continued Q Underneath the floor route the hydraulic hose through an existing hole in the frame immediately aft of the collective Secure the hose at this point with an adel clamp P N 512 005 00 Fasten the adel clamp to the existing bracket Airbus Helicopters P N 350A86 0020 33 with hardware as illustrated below Figure 2 2 6 Hose Routing Through Frame Bolt P N 510 453 00 Washer P N 510 042 00 Nut P N 510 102 00 aurou D V Adel Clamp P N 512 005 00 A View Looking Aft Q Aft of the frame route the hose along the top of the structural member shown below and secure with adel clamp P N 512 005 00 at location shown Figure 2 2 7 Adel Clamp Installation Ng Adel clamp from Figure 2 2 4 is behind this _ Route
51. ith FAA approved Rotorcraft Flight Manual Supplement RFMS document No 121 012 01 Rev O dated 19 Oct 2004 or Supplement No 121 012 02 Rev 0 dated 2 Feb 2005 or later approved revisions This modification must be inspected and maintained in accordance with section ATA 5 of the Onboard Systems Instructions for Continued Airworthiness document No 123 011 01 Rev 0 dated 11 Aug 2004 or document No 123 011 02 Rev 0 dated 13 Dec 2004 and Service Manual No 122 005 00 Rev 9 dated 3 Jan 2006 or Service Manual No 122 015 00 Rev 4 dated 6 Jul 2006 or later approved revisions A copy of this Certificate Supplement and Maintenance Manual referred on items Ill and IV above respectively shall be maintained as part of the permanent records of the modified rotorcraft e 55 a c END F 400 01C 05 06 Certification 7 5 Brazilian CHST continued Y ANAC AG NCIA NACIONAL DE AVIA O CIVIL BRASIL CERTIFICADO DE HOMOLOGA O SUPLEMENTAR DE TIPO Supplemental Type Certificate N MERO 2007S04 11 Number Lei n 7565 C digo Brasiloi Este certificado emitido com base na ro de Aeron utica de 19 de dezembro de 1986 This certificate issued in the mena of the Law r 7565 C digo relato de Aeron utica dated 19 December 1986 conferido ao Onboard Systems ie granted te 13915 NW 3 Court Vancouver WA 98685 USA por ter a modifica o ao projeto de tipo do produto ab
52. l as applicable e Return the components freight cartage insurance and customs prepaid to Onboard Systems 13915 NW 3rd Court Vancouver Washington 98685 USA Phone 360 546 3072 Maintenance 5 1 This page intentionally left blank Section 6 System Part Numbers 210 201 02 AS 350 Swing Removable Provisions lite MAX HOOK LOAD MAX HOOK LOAD 3086 LBS 1400 KGS 2557 LBS 1160 KGS Item Part Number Description Q 232 145 02 Swing Hook Frame Assembly 1 232 140 01 Forward Attach Cable Assembly 2 2 1 1 232 141 01 Aft Attach Cable Assembly 215 166 00 Max Hook Load 3086 Decal 215 168 00 Max Hook Load 2557 Decal WM BY OQ Nd System Part Numbers System Part Numbers continued 210 202 02 AS 350 Swing Fixed Provisions 3 _ 210 095 00 C39 Indicator Assembly 1 4 390 773 007 indicator Mount Bracket 1 5 290778300 Retay Bracket JA 6 445 005 00 Reay 1 7 50006500 Grommet Edging Ja E 2088400 Connector Bracket 1 o _ 270 106 02 Lona Weigh intemal Hames 1 10 270 108 00 Electrical Release Internal Hames 1 ui 215165 0 Multiple Sticker She 1 iz 27012500 Ground Swap Fed i EEC TJ is TJ 290 888 00 Reiner 1 is osso Guara SSS io 290 893 00 Ba Jr alatalalalaltalaltalalalalalm 6 2 System Part Numbers System Part Numbers continued 232 137 01 Shackle Assembly
53. ment Connectors Analog Meter Connector Data Recorder Connector P N 410 130 00 P N 410 011 00 410 057 00 amp 410 020 00 Mfg P N MS3126F10 6P Pin Color Function Pin Color Function A WH Power 1 WH BL Ground B WH GN Clock 3 WH Power C WH OR Data 5 Shield Shield D WH BL Ground 7 WH GN Clock Signal E Shield Shield 9 WH OR Data Signal 4 Red Flight Switch 2 Purple Cap Switch Optional Installation Instructions 2 1 2 1 Electrical Wiring Installation continued Figure 2 1 1 Electrical Wiring Routing Overview Comnector Bracket C 39 Indicator Y400 9400 3N Ground Relay 23M If installing the wire harnesses on a newer AS350B2 or B3 model equipped with a switch panel of circuit breaker design Airbus Helicopters mod 07 3274 incorporated the electrical harness P N 270 108 00 requires modification Cut the MEIE wire off just prior to the butt splice and discard the splice and the 20 ga wires Figure 2 1 2 P N 270 108 00 Harness Modification Cut wire here O In preparation for installing the Relay Bracket P N 290 783 00 create two holes in the LH beam at Y400 as illustrated in Figure 2 1 3 Figure 2 1 3 Relay Bracket Installation 1 30 in 33 mm LH Beam Existing hole Y 400 x lt Forward 7 1 in A 18
54. moving the Onboard Systems gimbaled swing frame side to side under the helicopter and watching the gimbaled joint and the parallelism of the frame tubes The frame flexes to accommodate the paths of the cable ends With a rigid frame such as supplied by Airbus Helicopters swinging side to side with no load one or more of the cables goes slack With a load on the hook the cables don t go slack and the geometry is accommodated by flexure of the swing frame and the airframe The more rigid the swing frame is the more loads get transferred to the airframe It is this principal that lead to the articulated swing frame of the current design This reduces the stresses in both the airframe and the swing frame to a minimum The swing frame supporting cables are now a simplified design with fewer parts and less weight The attach fittings have been redesigned with larger replaceable bushings for longer life and more economical service A ground strap is included to reduce the effects of static discharge Improved routing of electrical cables from the hook to the belly plug Hydraulic Manual Release System e Norigging required e Improved cable routing for increased durability e Inherently safer design than cable General Information Section 2 Installation Instructions These procedures are provided for the benefit of experienced aircraft maintenance facilities capable of carrying out the procedures Those lacking the necessary expertise
55. must not attempt them 2 1 Electrical Wiring Installation Install electrical harnesses P N 270 106 02 and P N 270 108 00 Route them along the existing harnesses reference Figure 2 1 1 while observing the following precautions Pick up existing wire runs by opening existing cable clamps Nylon ties alone may not be used for primary support The distance between supports should not exceed 21 inches Bend radius of wire or harness must not be less than 10 times the wire or harness diameter Inspect and verify that the wire harness may not be manually deflected into a structure with a bend radius of less than 0 13 Make the appropriate connections with terminal lugs Secure the C 39 indicator harness along the canopy with clamps and connect to the C 39 indicator Refer to Figure 2 1 6 for electrical schematic The P N 270 106 02 electrical harness includes a data line for use with an Onboard Systems Data Recorder or Analog Meter These items are not included under this STC Attach connectors to data line per pin out in Table 2 1 1 to connect the Analog Slave Meter or Data Recorder to the electrical harness DATA line If a data connector is present on the data line use harness P N 270 059 00 to connect to Analog Slave Meter If the accessory connector is not used stow this line of the harness NOTICE The data line may or may not be terminated with a data connector depending on manufacture date Table 2 1 1 Optional Equip
56. n Qty 17 510 391 00 Screw 1 18 512 011 00 Ty Wrap 4 19 510 115 00 Cotter Pin 1 20 232 168 00 Slave Cylinder Assembly 1 21 510 531 00 Screw 2 22 420 033 00 Safety Wire AR 23 512 003 00 Ty Wrap 1 24 215 271 00 Fuel Drain Warning Placard 1 System Part Numbers System Part Numbers continued 232 168 00 Slave Cylinder Assembly with Plumbing Item Part Number Description Qty 1 232 169 00 Slave Cylinder Assembly 1 2 232 170 02 Slave Cylinder Plumbing Assy l 3 556 041 00 O Ring 2 4 558 031 00 Banjo Bolt 1 5 560 006 00 Quick Disconnect 1 This item supersedes P N 232 170 00 amp 232 170 01 These parts are fully interchangeable System Part Numbers 6 13 System Part Numbers continued 232 169 00 Slave Cylinder Assembly Item Part Number Description 1 290 803 00 Slave Cylinder 2 290 802 00 Cylinder Cap 3 290 805 00 Piston 4 517 040 00 Bushing 5 6 7 510 496 00 Stat O Seal 510 493 00 Screw 556 097 00 Quad Ring ll O tes 6 14 System Part Numbers Section 7 Certification FAA STC Thid Sites of Amrin Department of Trmsportation Federal Aviation Administration Supplemental Type Certificate Number SRO116ASE This certificate issued fo Onboard Systems International 13915 NW 3 Court Vancouver WA 98685 errtifes that the change in the type desig for the followi
57. ng peroduet weth the Fmitations and conditions therefore as jreciferd hereon meets the airworthiness regimens of Piet 27 of the Federal Aviation Regulations Original Product Type Certificate Number HIEU Hako Eurocopter France Mode AS350B AS350B1 AS35082 AS35083 AS350BA and AS350D Desorption of the Type Designa Change Fabrication of Onboard Systems Model 200 280 01 200 280 02 200 280 03 or 200 280 04 Cargo Hook Swing Suspension System in accordance with FAA approved Onboard Systems Master Drawing List No 155 086 00 Revision 27 dated October 30 2009 or later FAA approved revision Installation of the systems in accordance with FAA approwed Onboard Systems Owner s Manual No listed in the table below or later FAA approved revision This modification must be inspected and maintained in accordance with Section 5 of the FAA approved Onboard Systems Instructions for Continued Airworthiness ICA and Onboard Systems Cargo Hook Service Manual listed in the table below or later FAA approved revision See Continuation Sheet on Page 3 Lm itationi and Conditions Approval of this change in type design applies to the Eurocopter AS350 model rotorcraft listed above 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 modificati
58. ntenance Manual referred on items Ill and IV above respectively shall be maintained as part of the permanent records of the modified rotorcraft END Ips F 400 01C 05 06 Certification 7 7 Required Placards Install one of the following per section 2 7 This document when released outside Onboard Systems is supplied for identification engineering evaluation or inspection purposes only and shall not be duplicated used or disclosed to produce r subject matter covered thereby without the written permission of Onboard Systems By accepting this document t agrees to affix this legend to any duplication of reproduction in whole or part of the document of information disclosed thereby made persuant to such permission For a description of any revisions see document number 150 066 00 11 00 IN 279 MM MAX HOOK LOAD 3086 LBS CARGA MAXIMA NO GANCHO 1400 KGS 38 POINT FONT COLOR TO CONTRAST WITH BACKGROUND TITLE MAX HOOK LOAD MATERIAL 3M SCOTCHCAL 3650 VINYL OR EQUIVALENT yess omenmse crrores a aera PLACARD TOLERANCES ARE vag CHK REF 215 200 00 oa size SHEET 4 OF 1 08 0 5 DEG LINEAR ANGLES 001 HOLES This document when released outside Onboard Systems is supplied for identification engineering evaluation or inspection purposes only and shall not be duplicated used or disclosed to produce articles and or subject matter covered
59. om FOR D psy STE E MS CO MANUAL NBOAR p SITE AT WWW p rais PLEASE CMEC TEST RE PASION OF 1 alia T Di ak Owner s Manual Cargo Hook Svving Suspension System Talon LC Hydraulic Cargo Hook Airbus Helicopters AS350 Series System Part Numbers 200 280 02 200 280 03 Owner s Manual Number 120 104 02 Revision 29 05 09 14 A CBNBOARD 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 Record of Revisions Page s Reason for Revision 07 30 10 Section 1 through 4 Replaced P N 212 014 00 with 212 014 01 and updated hydraulic fluid filling instructions to use new kit Updated warnings cautions and notes section to safety label section Updated safety label format through out document 08 09 10 Section 1 2 amp 4 amp 6 2 Replaced warnings cautions and notes section with safety labels sections Updated safety label format to current format throughout document Added fuel drain guard to kit and associated instructions Updated weight for fixed provisions to included fuel dram guard kit 03 28 11 2 8 2 9 6 10 amp 6 12 Added Fuel Drain Warning Placard to System Parts Numbers section under swing hook frame assembly Added P N 291 523 00 as an optional clamp half that is available 04 20 11 1
60. on the push rod is visible proceed to step 13 If the green on the push rod is not visible with the lever completely pulled the system has too much air in it and needs further bleeding To do this repeat steps 5 11 Figure 2 7 7 Checking System for Air 13 14 15 16 Verify green ring on push rod is still visible After the system is properly bled verify that the reservoir is approximately half full of hydraulic fluid Fluid should be visible above the baffle Re install the baffle and the reservoir lid Check the system for proper operation Fully actuate the release lever The hook must open and the lever must have a firm feel Disassemble and thoroughly clean the hydraulic hook bleed kit with isopropyl alcohol Allow it to dry Not cleaning the kit will render it unusable Reassemble and store for next use Installation Instructions 2 8 Placard Installation Install appropriate load limitation placard P N 215 166 00 3086 lb max hook load or P N 215 168 00 2557 Ib max hook load dependent on the model of AS350 on which the system is being installed Consult the Airbus Helicopters Flight Manual Supplement applicable to your particular helicopter for the external load limitation Locate the placard on the belly of the helicopter visible to the ground operator and near the hook Installation Instructions NOTICE The provided load limitation placards P N 215 166 00 and P N 215 1
61. ons including changes in type design will introduce no adverse effect upon the airworthiness of that rotorcraft Rotorcraft modified in accordance with this STC must be operated in accordance with a copy of a FAA approved Onboard Systems Rotorcraft Flight Manual Supplement RFMS listed in the table below or later FAA approved revision See Continuation Sheet on Page 3 This certificate and tha Aypyorting data which is the basis fer approval Mal remain in offect until surrendered segpende revoked or a termination date 43 otherwise established by the Shninestrator of lhe Federal Seiation Seininistration Date of applications March 29 2002 Date reissued Pate of issuance January 22 2003 Wave amenda October 26 2004 February 04 2005 October 30 2007 April 13 2010 By direction of the Melorinesraler Signature i Aires Offi Tithe 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 Fora BID 10 68 PAGE 1 OF 3 PAGES Certification FAA STC continued Vetted States of Amerin Department of Trmaportation Federal Aviation Administration Supplemental Type Certificate Continuation Sheet Number SRO1164SE Onboard Systems International Jura January 22 2003 Shkenda October 26 2004 February 04 2005 October 30 2007 April 13 2010 Peseryetion of th
62. ontinued 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 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 x 10 CAL DAMP 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 t
63. ose will route outboard of Y400 and follow the electrical release harness installed previously to the connector bracket Q Pass the hydraulic quick disconnect coupling through the load cell electrical connector hole Slide the fitting to the end of the slot and tighten the jamb nut securely against the Connector Bracket Figure 2 2 11 Quick Disconnect Coupling Installation Fixed hydraulic line Connector Bracket Installation Instructions 2 13 2 2 Fixed Hydraulic Release System Installation continued Q Install the hook release connector 32M and load cell connector 55M with screws P N 510 481 00 washers P N 510 062 00 and nuts P N 510 029 00 Install screws with their heads on the bottom side of bracket flange if nuts are installed on bottom side they will interfere with mating connector See figure 2 4 1 for location of each connector O Install electrical markers P N 215 165 00 on the Connector Bracket adjacent to the corresponding connectors 2 14 Installation Instructions 2 3 Cockpit Indicator Installation The Indicator is mounted on the RH door pillar If nut clips are not pre installed in the door pillar install them per the following Q Hold the Indicator Bracket P N 290 772 00 at a location as shown below and transfer its hole pattern to the door pillar Figure 2 3 1 Indicator Bracket Installation Ro RH Door Pillar 39 Indicator Bracket P N 290 772 0
64. ously in excess of 20 seconds will cause the release solenoid to overheat possibly causing permanent damage 4 Activate the manual release lever on the collective to test the cargo hook manual release mechanism 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 5 Swing the installed Cargo Hook and the suspension to ensure that the hydraulic hose electrical harnesses and ground strap have enough slack to allow full swing of each component without straining or damaging the harnesses and hose The hose and or harnesses must not be the stops that prevent the Cargo Hook or the suspension from swinging freely in all directions 6 Visually check for presence and security of fasteners and condition of cables Swing the Cargo Hook and the suspension in fore and aft and side to side directions to check for freedom of rotation at all joints 4 1 Disconnecting Removable Provisions For helicopter missions in which the cargo hook swing suspension system is not needed its removable provisions may be removed per the following instructions 1 Disconnect the electrical cables the ground strap and the hydraulic release hose at the belly of the helicopter 2 Remove the Swing Suspension by removing the safety pins and then the quick release pins that secure the cables to each of Shackle Assemblies at the aircraft hard points
65. pical 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 UN ZEI 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 the 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 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
66. s in Brazil the STC SRO1164SE issued by FAA USA LIMITA ES E CONDI ES LIMITA OE and CONDI ES See continuation sheet for applicable data Dates of Do Requerimento 21 Dec 2006 Da emiss o 13 Apr 2007 Da remiss o Applic ation Issue Reissue ren Al A kre Td hg da CLAUDIO PASSOS SI MILTON ZUAN Gerente Geral Certi os Aeron uticos Manager certifica o cal ge Prod iutos ASTON Director President F 400 01C 05 06 g 1 da 2 7 4 Certification Brazilian CHST continued x ANAC AG NCIA NACIONAL DE AVIA AO CIVIL Folha de Continua o ao Continuation Sheet to CERTIFICADO DE HOMOLOGA O SUPLEMENTAR DE TIPO Supplemental Type Certificate N MERO 2007S04 12 Number LIMITA ES E CONDI ES Limita ions and Conditions The approval of this type design change 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 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 Operation must be performed in accordance w
67. se 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 9 Installation Instructions 2 1 Electrical Wiring Installation 2 1 2 2 Fixed Hydraulic Release System Installation 2 7 2 3 Cockpit Indicator Installation 2 15 2 4 Fuel Drain Guard Installation 2 17 2 5 Shackle Assembly Installation 2 23 2 6 Swing Suspension Installation 2 24 2 1 Filling Hydraulic Release System 2 25 2 8 Placard Installation 2 31 2 9 Installation Check Out 2 32 Component Weights 2 33 Paper Work 2 33 2 10 Upgrade Kit Installation 2 34 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 8 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 CONTENTS 9 con
68. sed sealant Q Add fuel to the tank and check for leakage O Re install aft lower cowling Check for clearance between Guard and cowling If required trim cowling cutout to provide a min of 125 inch 3 5mm clearance between the cowling and guard See Figure 2 4 11 for completed installation Figure 2 4 11 Installation Complete 2 22 Installation Instructions 2 5 Shackle Assembly Installation Airbus Helicopters landing gear fittings P N 350A41 1097 20 are standard on B3 and optional on earlier models If not present install per Airbus Helicopters modification 07 2772 Attach the four Shackle Assemblies P N 232 137 01 to the helicopter landing gear fittings with hardware as illustrated in Figure 2 5 1 Airbus Helicopters part numbers are shown in italics NOTICE The smaller lobe of the shackle must be inboard as shown in the Figure 2 5 1 below Figure 2 5 1 Shackle Assembly Installation INBOARD ej N Bolt 4 A h P N 22201BE120074L A Nur A P NASN5232BHI20N j i N Vasher P N 23111AGI20LE Washer P N 23111AG120LE THIS LOBE MUST BE INBOARD _ Shackle Assembly P N 232 137 01 Q Install the cable assemblies onto the swing suspension frame with hardware provided pre assembled onto the cable clevis end Disassemble hardware from cable clevis end and apply grease to pivot bolts recommended lubricants are AeroShell 17 MIL G 21164 or Mobilgreas
69. sed 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 3 Example of Recommended Cargo Hook Rigging Recommended Primary Ring Long Line Operation Instructions Section 5 Maintenance Refer to the Instructions for Continued Airworthiness ICA manual 123 011 02 for maintenance of the cargo hook suspension system For maintenance of the cargo hook refer to Cargo Hook Service Manual 122 015 00 Instructions for Returning Equipment to the Factory 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 An RMA number is required for all equipment returns e 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 e 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 emai
70. serve the reservoir Bleeding procedure 1 Obtain the hydraulic hook bleed kit 212 014 01 This kit consists of 2 ounces of MIL PRF 5606 fluid a syringe a female barb fitting a length of PVC tubing and a bleed adapter fitting The bleed kit is included in new Hydraulic Hook kits Assemble the bleed kit by press fitting each component together as shown Figure 2 7 1 Hydraulic Hook Bleed Kit Bleed Adapter PVC Tubing Female X Barb Fitting Je Syringe 2 Ifthe system is already installed on the aircraft place an absorbent towel under the master cylinder If the master cylinder is not installed on the aircraft lightly clamp the master cylinder in a vise to hold it in a vertical position and position the slave cylinder so that its level is below the level of the master cylinder Installation Instructions 2 25 2 7 Filling Hydraulic Release System continued NOTICE Use best shop practices to keep foreign material out of the hydraulic system FOD will plug orifices damage seals and or scratch sealing surfaces necessitating system rebuild Use only clean hydraulic fluid from sealed containers 3 Connect the master cylinder assembly to the slave cylinder assembly if not already done If filling or bleeding on the bench as much as possible arrange the hoses uncoiled straight and running uphill as much as possible See figure 2 1 2 Figure 2 7 2 Hose Arrangements GOOD HOSE ARRANGEMENT POOR HOSE ARR
71. t Flight Manual Supplement P N 121 012 02 in the aircraft Flight Manual Installation Instructions 2 33 2 10 Upgrade Kit Installation These instructions are provided for installing upgrade kit P N 200 306 00 or P N 200 306 01 which are used to convert the P N 200 280 01 to the P N 200 280 02 or P N 200 280 03 configuration respectively 2 34 Convert the fixed provisions per the following O O O O O Remove the internal manual release cable and all supporting hardware Remove existing connector bracket at aft fuel tank support frame Install Connector Bracket P N 290 884 00 per Section 2 1 of this manual If installing kit P N 200 306 01 for the B3 model install friction knob P N 291 105 00 per Section 2 2 of this manual Install the hydraulic release lever assembly and plumbing P N 232 165 00 or P N 232 165 01 per Section 2 2 of this manual At the swing frame assembly perform the following O O O Remove the external manual release cable and all supporting hardware Cut ty wraps securing electrical harnesses and ground strap at cargo hook bumper and remove the existing cargo hook P N 528 023 01 and bumper Retain the attach bolt P N 290 775 00 and hardware Remove the ground strap P N 270 126 00 from the existing cargo hook and retain the screw P N 510 391 00 Prepare cargo hook surface for installation of ground strap by lightly removing the anodize layer around the tapped hole on the new cargo
72. t ex ing 3 years or both This certificate may be transferred in accordance wilh FAR 21 47 FAA Format 10 2 1 GOGH Pa 3 or 3 Pages 7 2 Certification Canadian Approval Transport Transports Canada Canada Aviation Aviation Suite 620 Your file Votre r f rence 800 Burrard Street 102S GA 05 98 Vancouver B C VEZ 2J8 P 05 0225 May 26 2005 Mr Mark Hanson Onboard Systems 13915 NW 3 Court Vancouver WA 98685 USA Subject Acceptance of revised FAA STC SR01164SE Dear Mr Hanson This is in response to the FAA Seattle ACO letter dated April 29 2005 requesting Transport Canada approval of the subject STC In accordance with our current policy associated with the review of foreign STCs some STCs applicable to certain categories of aircraft may be accepted solely on the basis of their foreign certification and do not require the issue of a corresponding certificate by Transport Canada The subject STC falls within these criteria This STC will be entered in the national index of STCs that have been reviewed and accepted by Transport Canada for installation on Canadian registered aeronautical products This letter confirms formal acceptance of the referenced STC by Transport Canada Yours truly YO IN a Henry Wong Aircraft Certification Engineer c c Mr Jeffrey E Duven Manager Seattle Aircraft Certification Office Ii Canada Certification 7 3 Brazilian CHST 6 ANAC AG NCIA NAC
73. th 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 Chan ing the Scale Hook Load x 10 CAL 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 units 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 b
74. the collective to operate the cargo hook hydraulic release the Cargo Hook should release Reset the cargo hook load beam Q Actuate the release lever on the collective and observe its range of motion Ensure that it is accessible and that there is no interference throughout its range of motion refer to Figure 2 9 1 If necessary adjust the lever position by loosening the set screw and turning the lever adjustment screw ref Figure 2 9 2 in the required direction Re tighten set screw Figure 2 9 1 Lever Position Adjust lever position to approximately center its range of motion within this area Ensure access and clearance is present at its starting and ending positions Release Lever Assembly Lever Adjustment Screw 2 32 Installation Instructions 2 9 Installation Check Out continued Q 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 Q Perform an EMI ground test per AC 43 13 1b section 11 107 For equipment that can only be checked in flight an EMI flight test may be required NOTICE The cargo hook is 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 02 Q Power on the Indicator and allow it to warm up for 5 minutes with no loa
75. 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 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 Mod
76. the hose to this beam and secure with Adel clamp Drill hole as necessary to fit Adel clamp screw Installation Instructions 2 11 2 2 Fixed Hydraulic Release System Installation continued 2 12 Q Aft of the clamp installed in Figure 2 2 3 route the hose inboard and aft across the airframe centerline to the identical structural member on the left side of the airframe Secure hose to fitting on top of structural member with ty wrap as shown below Ensure the hose is secured so that it does not interfere with the control rods Fi Tie off hose at this fitting Q Route the hose under the airframe support as shown below and secure the hose to the fitting on top of the structural member aft of the airframe support Install grommet edging P N 500 065 00 as necessary to protect hydraulic hose from chafing under Airframe a Cut and install grommet edging in this area to prevent chafing of hydraulic hose Installation Instructions 2 2 Fixed Hydraulic Release System Installation continued Q Route the hose up through the rear cabin bulkhead as shown in Figure 2 2 10 Split and install grommet P N 505 014 00 in hole after hose is routed through Figure 2 2 10 Hose Routing through Rear Cabin Bulkhead Install grommet in this hole View Looking Aft pas Q Aft of the rear cabin bulkhead pick up existing electrical harness runs and secure hydraulic hose using ty wraps The h
77. tinued Section 4 Section 5 Section 6 Section 7 Operation Instructions Operating Procedures 4 1 Disconnecting Removable Provisions 4 2 Re installing Removable Provisions 4 2 Cargo Hook Loading 4 3 Cargo Hook Rigging 4 3 Maintenance Instructions for Returning a System to the Factory 5 1 System Part Numbers 210 201 02 AS 350 Swing Removable Provisions 6 1 210 202 02 AS 350 Swing Fixed Provisions 6 2 232 137 01 Shackle Assembly 6 3 232 166 00 232 166 01 Release Handle Assembly 6 4 232 165 00 232 165 01 Master Cylinder Assembly with Plumbing 6 5 232 140 01 Forward Attach Cable Assembly 6 6 232 141 01 Aft Attach Cable Assembly 6 7 232 142 00 Lower Attach Cable Gimbal Assembly 6 8 232 143 01 Loadcell Gimbal Assembly 6 9 232 145 02 Swing Hook Frame Assembly 6 10 232 168 00 Slave Cylinder Assembly with Plumbing 6 13 232 169 00 Slave Cylinder Assembly 6 14 Certification FAA STC 7 1 Canadian Approval 7 3 Brazilian CHST 7 4 EASA STC 7 10 Section 1 General Information Introduction General Information The P N 200 280 02 and 200 280 03 Cargo Hook Swing Suspension System kits consist of fixed provisions and removable provisions The fixed provisions are permanently installed on the aircraft while the removable provisions are easily removed when not required on the helicopter s mission The 200 280 02 kit is intended for installation on Airbus Helicopters AS350B AS350BA AS350D AS350B1 and A
78. utton When the selection has been made press both the Right and Left button at the same time to return to Run NOTICE 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 LB KG 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 hydraulic hose electrical harnesses and ground strap do not limit the movement of the hook 2 Be completely familiar with this Owner s Manual Cargo Hook Service Manual 122 015 00 and the ICA Manual 123 011 02 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 the 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 continu
79. ylinder Assembly 290 884 00 Connector Bracket 505 014 00 Grommet 212 014 00 Bleed Kit 510 062 00 Washer 510 102 00 Nut 510 178 00 Cotter Pin 510 277 00 Screw 510 278 00 Washer 510 279 00 Nut 510 453 00 Bolt 512 005 00 Adel Clamp 512 003 00 Ty wrap 510 486 00 Cherry Max Rivet 120 104 02 Owner s Manual 121 012 02 RFMS 122 015 00 Cargo Hook Service Manual wlan AININININI i Nl o m m 123 011 02 ICA 1 7 Bill of Materials continued Table 1 10 Onboard Systems Bill of Materials Upgrade Kit P N 200 306 01 Part No Description Qty 270 129 00 Electrical Release Harness 232 209 00 Cargo Hook Slave Cylinder Assembly 290 839 02 Hook Bumper 232 165 01 Master Cylinder Assembly 290 884 00 Connector Bracket 291 105 00 Friction Knob 505 014 00 Grommet 212 014 00 Bleed Kit 510 062 00 Washer 510 102 00 Nut 510 178 00 Cotter Pin 510 277 00 Screw 510 278 00 Washer 510 279 00 Nut 510 453 00 Bolt 512 005 00 Adel Clamp 512 003 00 Ty wrap 510 486 00 Cherry Max Rivet 120 104 02 Owner s Manual 121 012 02 RFMS 122 015 00 Cargo Hook Service Manual 123 011 02 ICA pa Rll WO AInNINININI I Nl o 1 8 General Information

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