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Owner`s Manual Cargo Hook Swing Suspension System Airbus

1. Q IL Item Part Number Description Qty 1 232 151 00 Fixed Quick Disconnect Assembly 1 2 232 150 00 Release Handle Assembly 1 3 232 137 01 Shackle Assembly 4 4 210 095 00 C 39 Indicator Assembly 1 5 290 772 00 Indicator Mount Bracket 1 6 290 780 00 Cable Attach Bracket 1 7 290 783 00 Relay Bracket 1 8 445 005 00 Relay 1 9 290 782 00 Connector Bracket 1 10 500 065 00 Grommet Edging 1 11 270 106 02 Load Weigh Internal Harness 1 12 270 108 00 Electrical Release Internal Harness 1 13 215 165 00 Multiple Sticker Sheet 1 14 270 125 00 Ground Strap 1 15 290 888 00 Retainer 1 16 290 889 01 Guard 1 17 290 893 00 Bracket 1 6 2 System Part Numbers System Part Numbers continued 232 137 01 Shackle Assembly 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 232 150 00 Release Handle Assembly 6 4 Item Part Number Description Qty 1 268 025 00 Fixed Manual Release Cable 1 2 510 215 00 Cover Screws 2 3 290 757 00 Cover 1 4 510 210 00 8 32 Locking Heli Coil 2 5 290 754 00 L
2. i Relay Socket P N 445 004 00 part of 270 108 00 electrical harness Q Install Connector Bracket P N 290 782 00 at fuel tank support frame as illustrated below Q Fasten hook release connector 32M and load cell connector 55M to the Connector Bracket with screws P N 510 481 00 washers P N 510 062 00 and nuts P N 510 029 00 NOTICE 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 Figure 2 4 5 Connector Bracket Installation Load Cell Connector 7 28 in 185 mm Hook Release Connector 55M K Rivets 3 A A Looking Down 1 18 in 30 Connector Bracket P N 290 782 00 View Looking Forward Q Install electrical markers P N 215 165 00 Installation Instructions 2 11 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 Q Remove upper mounting hardware see below for 3N connector bracket and retain Q 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 Q Install ground strap terminal re using hardware remov
3. Installation Instructions f 3N ground Relay Bracket 23M Install per Figure 2 4 3 2 9 2 4 Electrical Wiring Installation continued 2 10 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 a minor modification Cut the MEIE wire off just prior to the butt splice and discard the splice and the 20 ga wires Figure 2 4 2 P N 270 108 00 Harness Modification Cut wire here Q 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 4 3 Figure 2 4 3 Relay Bracket Installation Existing hole Forward Z 2450 0 169 in 4 3 mm 2 pl s 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 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 Installation Instructions 2 4 Electrical Wiring Installation continued Figure 2 4 4 Relay Installation Relay ra P N 445 005 00 Relay Bracket J P N 290 783 00
4. PIV VV Sa 0000 00 00 KXXX XXX XXXI Wr NA XAXA KA KNK KAAI AAYYY YYY PAVVVY YY XXX PONSA I KONOCO RK KXRXY RK RA OONAN Azar maa D 2 Disconnect the electrical cables and the ground strap at the belly of the helicopter 3 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 Figure 4 3 Suspension Removal Shackle Assembly Safety Pin Quick Release Pin 4 2 Operation Instructions Optional Link Assembly An optional Link Assembly P N 232 436 00 may be used in place of the Load Cell Assembly This link assembly does not provide for load weighing It is directly interchangeable with the Load Cell Assembly including using the same hardware Refer to ICA manual for instructions for removal and re installation 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 4 until an internal latch engages the load beam and latches it in the closed position Figure 4 4 Cargo Hook Loading Cargo Hook Rigging Operation Instructions Extreme care must be exercised when rigging a load to the Cargo Hook Steel load rings are recommended to provide consistent relea
5. x 7 R oAR 2psYSTE EMS com I or MANUAL www 0NB T gITE ATW THIS PLEASE CECE LATE gi REVISION OFT sB4 TI D Owner s Manual Cargo Hook Swing Suspension System On the Airbus Helicopters AS350 Series System Part Number 200 280 04 STC SR01164SE Owner s Manual Number 120 104 03 Revision 8 05 09 14 Z CONBOARD SYSTEMS I N TERNATIONAL 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 Record of Revisions Revision Date Reason for Revision 10 12 09 Initial Release 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 drain guard kit Replaced bolt P N 510 505 00 with bolt P N 510 01 21 11 762 00 in swing frame assembly parts list Updated RMA instructions Updated Bill Of Materials to include corrected quantities of P N 510 102 00 510 085 00 amp 510 03 15 11 1 3 to 1 6 amp 2 5 455 00 Added fuel drain guard items to Bill of Materials Updated figure 2 2 6 to show correct P N 510 454 00 to 510 085 00 Added Fuel Drain Warning Placard to System Parts Numbers section under swing hook frame assembly Added Half Clamp Pad EC P N 350A 41 1099
6. Draws the reader s attention to important or N O CI unusual information not directly related to safety General Information Used to address practices not related to personal injury 1 1 Specifications Table 1 1 Suspension System Specifications Design load 3 086 lbs 1 400 kg Design ultimate strength 11 574 lbs 5 250 kg Unit weight Fixed Provisions 5 lbs 2 3 kg Unit weight Removable Provisions 30 lbs 13 6 kg Table 1 2 P N 528 029 00 Cargo Hook Specifications Design load 3 600 Ibs 1 633 kg Design ultimate strength Electrical release capacity Mechanical release capacity 9 000 Ibs 4 082 kg Force required for mechanical release at 3 500 lb Electrical requirements Minimum release load Unit weight 3 0 pounds 1 35 kg Mating electrical connector PCO6A8 2S SR 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 1 2 General Information General Information Bill of Materials The following items are included with the 200 280 04 Swing Suspension System the 210 202 01 fixed provisions kit and the 210 201 03 removable provisions kit If shortages are found contact the company from whom the s
7. Figure 2 5 11 Installation Complete 2 20 Installation Instructions 2 6 Swing Suspension Installation Q Install the cable assemblies onto the swing suspension frame with hardware provided pre assembled onto the cable clevis end 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 the manual release cable is routed to the right side of the helicopter Install the Swing Suspension onto the aircraft by attaching the four clevises at the end of the cables to the INBOARD holes on 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 Figure 2 6 1 Cargo Hook Swing Suspension Assembly Installation Shackle Assembly Safety Pin Installation Instructions Quick Release Pin 2 21 2 7 Removable Manual Release Cable Assembly Installation Connect the manual release cable P N 268 024 02 to the cargo hook per the following instructions o Remove the manual release cover from the cargo hook by removing two screws see below Figure 2 7 1 Manual Release Cover Removal o Thread the fitting at the end
8. 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 Gimbal 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 03 Swing Hook Frame Assembly System Part Numbers 6 10 System Part Numbers continued 232 145 0
9. Washer 4 4 510 095 00 Washer 3 3 510 102 00 Nut 6 6 510 277 00 Screw 2 2 510 278 00 Washer 2 2 510 279 00 Nut 2 2 510 453 00 Bolt 2 2 510 455 00 Bolt 4 4 1 3 Bill of Materials continuea Table 1 3 Onboard Systems Bill of Materials Continued 1 4 Part Description Total Kit Fixed Kit Removable Number 200 280 04 210 202 01 Kit 210 Qty Qty 201 03 Qty 510 457 00 Screw 4 4 510 475 00 Screw 3 3 510 481 00 Screw 8 8 510 526 00 Cotter Pin 2 2 512 024 00 Adel Clamp 2 2 610 024 00 Fuel Valve Seal 1 1 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 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 4 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 NOTICE These items may or may not be installed with a standard aircraft therefore verification recommended before purchasing them Table 1 5 Airbus Helicopters Part Numbers is Airbus Helicopters P N _
10. 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 27 Installation Check Out After installation of the Cargo Hook Swing Suspension System perform the following functional checks 1 Swing the Cargo Hook and the suspension to their full extremes to ensure that the manual release cable assembly and the electrical release cable have enough slack to allow full swing of the cargo hook and suspension without straining or damaging the cables The cables must not be the stops that prevent the Cargo Hook or suspension from swinging freely in all directions 2 With no load on the cargo hook load beam pull the handle operated cargo hook mechanical release the Cargo Hook should release Reset the load beam 3 With no load on the cargo hook load beam depress the cargo hook electrical release button the Cargo Hook should release Reset the load beam 4 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 5 Power on the Indicator and allow it to warm up for 5
11. 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 350 B 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 EASA 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 amdt 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 oe 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 Keeperless Cargo Hook 528 029 00 See Contin
12. 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 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 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 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 5 10 2 19 2 5 Fuel Drain Guard Installation continued Figure 2 5 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 unused sealant Q Add fuel to the tank and check for leakage 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 5 11 for completed installation
13. Installation continued Q 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 8 Installation Instructions 2 4 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 4 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 13 Make the appropriate connections with terminal lugs Secure the C 39 indicator harness P N 270 106 02 along the canopy with clamps and connect to the C 39 indicator Refer to Figure 2 4 7 for electrical schematic The electrical harness includes a line with that can be equipped an accessory connector for use with an Onboard Systems Data Recorder or Analog Meter These items are not included under this STC If the accessory line is not used stow this line of the harness Figure 2 4 1 Electrical Wiring Routing Overview Connector Bracket Install per Figure 2 4 5
14. Manual Release Cable Release Lever Fork Load beam must be closed and locked for rigging 2 24 Installation Instructions 2 7 Removable Manual Release Cable Assembly Installation continued O If necessary adjust the system to obtain the minimum gap of 125 inches at the release lever fork as shown in Figure 2 7 5 the maximum gap is limited by the manual release cover 1 e the release cable must fit within the cover when it is installed The system can be adjusted at the manual release lever on the collective or minor adjustments can be made at the cargo hook by loosening the jam nut and turning the manual release cable in the required direction this requires that the manual release cable be disconnected from the fixed release cable and the quick release clamps on the belly Be sure to maintain full thread engagement between the manual release cable fitting and cargo hook Move hook and swing frame throughout its range of motion while observing free play At no point should the free play be less than 030 Check that the cable housing is not kinked or pulled tight in any hook and swing frame position Re install the manual release cover with the two screws and ensure the manual release cable jam nut is tightened securely against the cargo hook 2 8 External Electrical Release and Load Cell Cable Installation Installation Instructions Q Q Connect the end of the cargo hook electrical release cable to the fixed elec
15. Operation 1 6 Installation Instructions Shackle Assembly Installation 2 1 Fixed Manual Release Cable Assembly Installation 2 2 Cockpit Indicator Installation 2 7 Electrical Wiring Installation 2 9 Fuel Drain Guard Installation 2 15 Swing Suspension Installation 2 21 Removable Manual Release Cable Assembly Installation 2 22 External Electrical Release and Load Cell Cable Installation 2 25 Placard Installation 2 27 Installation Check Out 2 28 Component Weights 2 28 Paper Work 2 28 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 continued Section 4 Section 5 Section 6 Section 7 Operation Instructions Operating Procedures 4 1 Disconnecting Removable Provisions 4 2 Optional Link Assembly 4 3 Cargo Hook Loading 4 3 Cargo Hook Rigging 4 3 Maintenance Instructions for Return
16. Remove and retain spring Airbus Helicopters P N 350A55 1044 21 and Lever Q Remove the cable support bracket Retain the two attachment screws Q Remove the connections from the common ground point on the lever retainer Q Remove the safety wire securing the Fuel Drain Valve Airbus Helicopters P N 350A52 1008 01 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 5 2 Fuel Drain Disassembly Complete iy Q Prepare the Retainer P N 290 888 00 for electrical bonding by removing the anodize from the area shown in Figure 2 5 3 Figure 2 5 3 Prepare Retainer Remove anodize this area Installation Instructions 2 5 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 5 4 Retain unused sealant to ensure proper cure Figure 2 5 4 Apply Sealant Apply sealant to this surface Figure 2 5 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
17. Zero is not done the Indicator will show the weight of the Cargo Hook plus the value of the Load Cell zero offset To Run the Installation Zero Routine With the Indicator powered up and in the Run Mode press both buttons at the same time to go to Setup Scroll through the menu until the symbol 0 in is displayed then press the Right button The CAL legend will be turned on and the current weight on the Cargo Hook will be displayed and blinking Remove any weight that is not to be zeroed out and press either button to complete the procedure and return to the Run Mode Calibration by Lifting a Known Weight Calibration by lifting a known weight is a Setup routine that calculates the Calibration Code for the Load Cell attached to the Indicator It is useful if the load cell Calibration Code is not known or as a cross check to the accuracy of a known Calibration Code The procedure is done by entering the known weight into the Indicator and then lifting the weight This procedure can be done 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 heli
18. computed Calibration Code is displayed To return to Run without changing the CAL Code press both the Right and Left buttons at the same time To change the Calibration Code use the Right button to select the digit to be changed then use the Left button to scroll the blinking digit to the desired number When the Calibration Code has been entered press both the Right and Left button at the same time to return to Run 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 O must be used For example if a Load Cell had a CAL Code of 395 it would be entered as 0395 If the load cell Calibration Code is not known or as a cross check the Indicator can generate the Calibration Code This is done by entering the weight of a known load into the Indicator LOAD routine and then lifting the load See the section Calibration by Lifting a Known Load 3 8 Load Weigh System Operation Instructions The Setup Mode continued Installation Zero Installation zero is a routine that matches the Indicator to the INSTALLED Load Cell It adjusts the Indicator reading to compensate for the weight of the Cargo Hook on the Load Cell and whatever zero offset is built into the Load Cell The Installation Zero procedure is not mandatory If done the Indicator will read zero when the Un Zero button is pressed and there is no weight on the Cargo Hook If the Installation
19. connected to the analog out signal To Look at or Change the Scale With the Indicator powered up and in the Run Mode press both buttons at the same time to go to Setup Scroll through the menu until the word SCALE is displayed then press the Right button The display should look like this Figure 3 9 Changing the Scale Hook Load x 10 CAL or UN ZEI RO 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 displa
20. minutes with no load on the hook Press both Indicator buttons at the same time to go to the Setup Mode Scroll through the menu until the symbol 0 in is displayed then press the right button Remove any weight that is not to be zeroed out and press either button to complete the procedure 6 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 2 Component Weights Weight Removable Provisions 30 0 lbs 13 6 kg 133 in 3375 mm 5 5 Ibs 2 5 kg 110 in 2794 mm Fuel Drain Guard 0 40 Ibs 18 kg 135 in 3430 mm 35 9 lbs 16 3 kg 129 4 in 3288 mm Paper Work In the US fill in FAA form 337 for the initial installation This procedure may vary in different countries Make the appropriate aircraft log book entry Insert the Rotorcraft Flight Manual Supplement P N 121 012 03 in the Rotorcraft Flight Manual 2 28 Installation Instructions Section 3 Load Weigh System Operation Instructions Indicator Front Panel The C 39 Indicator front panel includes the following features The four 7 segment LCD digits show the weight on the Cargo Hook and display various setup information The Legends clarify the digital display i e when the LB Legend is turned on the display will be pounds etc The right button i
21. not install a clamp at the furthest aft NOTICE If your helicopter does not have holes in the honeycomb panel modify it per Airbus Helicopters Service Bulletin No 25 00 04 Figure 2 2 7 Cable Support Clamp Installation Nut _ Washer PIN 510 085 00 A C Centerline Bolt P N 510 455 00 Eurocopter P N A3125 2 H179 A A Rotated 90 _ Fuel Tank Support Centerline View Looking Up oo At Lower Aft Cowling 2 6 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 S Ro RH Door Pillar se C 39 Indicator Bracket P N 290 772 00 View Looking Outbd 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 Installation Instructions 2 7 2 3 Cockpit Indicator
22. of certain routines Listed below is a matrix of the Error Code displays their meaning and possible corrective action Pressing either button will usually bypass the error code however the displayed information may be suspect Table 3 1 Indicator Error Codes POSSIBLE DISPLAY CAUSE CORRECTIVE ACTION A D or D A circuit failure NV Ram failure NV Ram write failure NV Ram busy failure Potential short in the optional analog meter cable Clear short and power cycle the Indicator by turning the power to the Indicator off for a few moments If Error Code continues return the Indicator to the factory Power cycle the Indicator if Error Code continues return the Indicator to the factory Re enter data if Error Code continues return the Indicator to the factory Power cycle the Indicator if Error Code continues return the Indicator to the factory 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
23. release lever to test the cargo hook manual release mechanism The mechanism should operate smoothly and the Cargo Hook must release Reset the load beam by hand after release Verify that the hook lock indicator on the side of the hook returns to the fully locked position If the hook does not release or re latch do not use the unit until the problem is resolved In the fully locked position the hook lock indicator must align with the lines on the manual release cover see Figure 4 1 Figure 4 1 Hook Lock Indicator Cover Lock Indicator Lock Indicator ACCEPTABLE NOT ACCEPTABLE LOCK INDICATOR DIAMOND LOCK INDICATOR DIAMOND IS NOT VISIBLE OR IS IS ALIGNED WITH ENGRAVED VISIBLE BUT IS NOT ALIGNED WITH ENGRAVED LINES ON THE COVER LINES ON THE COVER AS SHOWN ABOVE wa 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 Remove the removable section of the manual release cable by un clipping it from the bracket on the belly of the helicopter disengaging the locking pin and unthreading the Adapter Fitting Unclip the Release Cable Cap see below from the bracket and thread it over the open end of the fixed manual release cable assembly and clip it into the inboard spring clip on the bracket Figure 4 2 Manual Release Cable Removal Release Cable Cap
24. suspension flying vertically due to aerodynamics when ferrying with no load or from recoil effects from releasing large cargo hook loads General Information Section 2 Installation Instructions These procedures are provided for the benefit of experienced aircraft maintenance facilities capable of carrying out the procedures They must not be attempted by those lacking the necessary expertise 2 1 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 1 1 Airbus Helicopters part numbers are shown in italics except at the RH forward hard point install an Attachment Bracket at the inboard side as illustrated in Figure 2 1 2 Note the orientation of the Shackle Assembly Torque the nuts to 100 130 in lbs At the Attachment Bracket fasten an Adel Clamp P N 512 024 00 with hardware as illustrated do not torque nut down until manual release cable is routed through see section 2 2 Figure 2 1 1 Shackle Assembly Installation Inboard Bolt Pa a 13 Nut A vo P N 22201BE120074L I OL O P N ASN5232BH120N Washer Washer i P N 23111AG120LE P N 23111AG120LE Shackle Assembly P N 232
25. the key See figures 2 5 6 and 2 5 7 Installation Instructions 2 17 2 5 Fuel Drain Guard Installation continued Figure 2 5 6 Fuel Tank Key Figure 2 5 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 5 8 Figure 2 5 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 18 Installation Instructions 2 5 Fuel Drain Guard Installation continued Q Secure the Fuel Drain Valve with safety wire using the small hole in the retainer tab Re install the electrical connections to the new Retainer tab per Airbus Helicopters Electrical Bonding Procedure Refer to Airbus Helicopters Standard Practices Manual 20 02 07 Install the Lever by placing it in Retainer slot and rotating upwards Secure with cotter pin P N 510 526 00 See Figure 2 5 9 Figure 2 5 9 Install Lever Installation Instructions
26. 137 01 Figure 2 1 2 RH Forward Shackle Assembly Installation Inboard Attachment Bracket _ a P N 290 780 00 i E ee a Bolt P N 510 453 00 Washer P N 510 042 00 sy Nut P N 510 102 00 Q 1 Adel Clamp e View Looking Fwd P N 512 024 00 Installation Instructions 2 1 2 2 Fixed Manual Release Cable Assembly Installation 2 2 Remove the lower fairings on the helicopter in order to obtain access to cable routing areas The manual release cable installation consists of a fixed section P N 268 025 00 and a removable section The fixed section is routed from the release lever at the collective aft to an external bracket attached to the lower rear fairing at the centerline of the forward fuel tank support frame as shown in Figure 2 2 1 Figure 2 2 1 is an overview of the cable routing and the figures following detail the cable support installations at various points Figure 2 2 1 Fixed Manual Release Cable Installation Overview X 1790 15 AIC Centerline See Figure 2 1 2 Route cable outboard through this hole See Figures 2 2 6 See Figure 2 2 5 and 2 2 7 View Looking Outboard From A C Centerline Installation Instructions 2 2 Fixed Manual Release Cable Assembly Installation continued Q Mount the manual release lever assembly P N 232 138 00 to the collective stick with the Clamp Half P N 290 753 00 and two screws P N 510 390 00 pro
27. 20 to the table of Eurocopter required part numbers 09 01 10 03 21 11 6 10 amp 6 12 05 02 11 1 4 Updated electrical system interface information to include Eurocopter mod 073475 09 09 11 1 5 2 13 2 14 Updated electrical schematic to reflect a c side wiring 02 19 13 1 5 2 13 2 14 interface of post mods 07 4280 and 07 3450 Added note regarding post mod 07 4280 Updated Eurocopter to Airbus Helicopters Replaced load cell P N 210 249 00 with P N 210 249 03 Replaced fuel drain guard P N 290 889 00 with 290 889 01 Updated Figure 4 5 Added note regarding contact P N 410 194 00 on page 1 5 Title 1 1 1 4 1 5 ie Section 2 4 4 6 12 Register Your Products for Automatic Notifications Onboard Systems offers a free notification service via fax or email for product alerts and documentation updates By registering your Onboard Systems products at our website we will be able to contact you if a service bulletin is issued or if the documentation is updated You can choose to receive notices on an immediate weekly or monthly schedule via fax email or both methods There is no charge for this service Please visit our website at www onboardsystems com notify php to get started This page intentionally left blank CONTENTS Section 1 Section 2 Section 3 General Information Introduction 1 1 Specifications 1 2 Inspection 1 2 Bill of Materials 1 3 Theory of
28. 21 012 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 200 280 04 0 121 012 03 Revision 0 dated March 4 2010 ROTORCRAFT FLIGHT MANUAL SUPPLEMENT 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 NNN Any alteration of this certificate is punishable by a fine of not exceeding 1 000 or imprisonment not exceeding 3 years or both This certificate may be transferred in accordance with FAR 21 47 FAA FORM 8110 2 1 10 69 PAGE 3 OF 3 PAGES 7 2 Certification Transport Canada Approval Transport Transports ivi Canada Canada Aviation Aviation Aircraft Certification Branch 620 800 Burrard Street Vancouver BC V6Z 2J8 Your file Votre r f rence 190S 03 169 Our file Notre r f rence March 24 2003 Onboard Systems 13915 NW 3 Court Vancouver WA 98685 USA Attention Mr Ron Pirtle Subject Acceptance of Foreign STCs SR01164SE SR01165SE and SR01166SE Dear Sir This is in response to your letters dated February 25 2003 making application for Canadian approvals of the subject STCs In a
29. 3 Swing Hook Frame Assembly continued GROUND STRAP CONNECTION SEE GROUND STRAP CONNECTION DETAIL System Part Numbers 6 11 System Part Numbers continued 232 145 03 Swing Hook Frame Assembly Item Part Number Description Qty 1 235 117 00 Swing Frame Half 2 2 290 845 00 Foot Right 2 3 510 762 00 Bolt 4 4 510 104 00 Nut 4 5 517 055 00 Spherical Bearing 4 6 510 510 00 Jam Nut 4 7 235 116 00 Frame Strut 2 8 510 440 00 Nut Castellated 1 9 290 843 00 Shaft Cap 2 10 290 842 00 Shaft Pivot 1 11 517 057 00 Bearing 2 12 517 058 00 Bearing 2 13 232 143 01 Loadcell Gimbal Assembly 1 14 290 862 00 Bumper 1 15 510 506 00 Bolt 1 16 290 846 00 Foot Left 2 17 510 443 00 Bolt 1 18 290 740 00 Shaft Retaining Bushing 2 19 290 739 00 Shaft Gimbal 1 20 510 220 00 Washer 1 21 510 178 00 Cotter Pin 3 22 270 107 00 Electrical Release Cable 1 23 510 170 00 Nut 1 24 510 174 00 Washer 1 25 510 183 00 Washer 1 26 510 320 00 Nut Castellated 1 27 528 029 00 3600 Ib Keeperless Cargo Hook 1 28 290 775 00 Long Hook Attach Bolt 1 29 290 774 00 Hook Bumper 1 30 210 249 03 AS350 Swing Load Cell Assembly 1 31 590 008 00 Plastic Tubing Wrap 80 32 215 183 00 Serial Number Plate 1 33 510 429 00 Drive Screw 4 34 270 126 00 Ground Strap 1 35 510 391 00 Screw 1 36 512 011 00 Ty Wrap 2 37 215 271 00
30. Fuel Drain Warning Placard 1 Supersedes 210 249 00 210 199 01 and 210 199 00 These part numbers are interchangeable 6 12 System Part Numbers Section 7 Certification FAA STC Hnit States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Numer SR01164SE This certificate issued ta Onboard Systems International 13915 NW 3 Court Vancouver WA 98685 certifies thal the change tn the Wye design for the following product with the temitations and conditions therefore as yrecified hereon meets the airworthiness reguirenenls of Fiat 27 of the Federal Aviation Kegulations Original Product Type Certificate Number H9EU Make Eurocopter France Medel AS350B AS350B1 AS350B2 AS350B3 AS350BA and AS350D DLeseyrtion of the Type Design 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 approved 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 Man
31. 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 4 7 Electrical Schematic Data line may or may not a connector depending on Existing Airbus Helicopters Wiring post Mod 07 4280 ok aaalp_paeakerpaner j AI 1 a SWING ME1E 1Al Se BUS M 1 10A OPT1 1 23M ae es 2S z ee 2 1 A1 oe 5G AD S1ALP32 BREAKER PANEL x4 1 43 1 ME2E 10 m gi i A 1 2 5A 1 18 24M 32M EEE atl pecan A 5 AIA Alla ME4NE ME10E P pe S B B vest BiB j MESE Q i To CARGO REL cyclic button cic Oo ee j 3N 30M 55M Alla Ilas i 55M Ala WH B B f f 1 ME87E B D _MESTE oN ee 1 i cic WH OR D D 20ALP J1A PIA DD WH BL Elle U CA FLOOR U CA FLOOR l EWE FIF Q fe ee EJE RE alla Existing Airbus Helicopters Wiring 1 a HiH post Mod 07 3450 shown amp 5 kilk 7 c 7 TE Jb BELLY DISCONNECT 1N a M M 2LK71E N N Note D
32. 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 email 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 5 1 This page intentionally left blank Section 6 System Part Numbers 210 201 03 AS 350 Swing Removable Provisions MAX HOOK LOAD 3086 LBS 1400 KGS MAX HOOK LOAD 2557 LBS 1160 KGS Item Part Number Description Q 232 145 003 Hook Frame Assembly 1 232 140 01 Forward Attach Cable Assembly 2 2 1 1 1 232 141 01 Aft Attach Cable Assembly 268 024 02 Manual Release Cable Assembly 215 166 00 Max Hook Load 3086 Decal 215 168 00 Max Hook Load 2557 Decal Ni NB WPN System Part Numbers 6 1 System Part Numbers continued 210 202 01 AS 350 Swing Fixed Provisions
33. RO The illustration is a typical hook load reading The display is 3 500 pounds note the last digit is not displayed Load Weigh System Operation Instructions To Zero or Tare the Display The zero feature is used to zero or tare the weight on the Cargo Hook that is not wanted such as the weight of a cargo net or long line The Right button is used to zero the Indicator reading When the Right button is pressed the display is zeroed The zero legend is turned on and the zeroed number is stored in memory If the Right button is pressed again before the Un zero button is pressed the display blinks in response to the button closure Zero is only available in the Run Mode Figure 3 4 Zeroing the Display Hook Lood Zero Legend x 10 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
34. To return to Run without changing the current dampening level press both the Right and Left buttons at the same time To change the dampening number use the Left button to scroll the blinking digit to the desired number After the selection has been made press both the Right and Left buttons at the same time to return to Run Indicator Calibration The Calibration Code or CAL code is a mandatory input The Indicator will not accurately display the load without the correct Calibration Code The Calibration Code scales the signal from the Load Cell If the C 39 Indicator was supplied as part of a Load Weigh System the Calibration Code will have been entered into the Indicator by the factory however it should be confirmed If the Indicator is to be mated to a different Load Cell it must be calibrated before use Calibration can be done by entering a known Calibration Code or by lifting a known load and having the Indicator calibrate itself Both options are discussed below Load Weigh System Operation Instructions 3 7 The Setup Mode continued To Look at or Change the Calibration Code With the Indicator powered up and in the Run Mode press both buttons at the same time to go to Setup Scroll through the menu until the word CODE is displayed then press the Right button The display should look like this Figure 3 6 Changing the CAL Code Hook Load x 10 CAL he The CAL legend is turned on and the previously entered or
35. _ 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 350A 41 1097 20 Half Clamp Rear 2 350A 41 1099 20 Half Clamp Pad 2 350A86 0020 33 Bracket 1 ASNA0078A403 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 General Information Bill of Materials continuea General Information Table 1 6 Airbus Helicopters Electrical Parts Pre mod 07 3274 Airbus Helicopters 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 Table 1 7 Airbus Helicopters Electrical Parts with Mod 07 3274 Airbus Helicopters P N Description Qty 045004A127A Cargo Hook Sling Switch 1 ECS0744A02A5 Circuit Breaker 2 5A 1 ECS0744B 15A0 Circuit Breaker 15A 1 AS350B2 and B3 ai
36. ata line included with Pee Pye INSTRUMENT alle Load Weigh Harness P N 270 1 06 02 only HANG be terminated with a oes manufacture date Installation Instructions 2 13 2 4 Electrical Wiring Installation continued Figure 2 4 7 Electrical Schematic continued 6 esas 254 Pc Jcourrou H Y ME pe ME10E 20a Cyclic Lever PCB Existing Airbus Helicopters Wiring Post Mod 07 3273 2 14 Installation Instructions 2 5 Fuel Drain Guard Installation Installation Instructions NOTICE If installing the 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 6 In preparation for installing the fuel drain guard Q m D Figure 2 5 1 Removing Control Cable Obtain ProSeal sealant P N PR1422 B 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 350A55 1043 21 To free the control cable remove the Sleeve Airbus Helicopters P N N1 5ALU and Cable Grip Airbus Helicopters P N 58 2 009 See Figure 2 5 1 2 15 2 5 Fuel Drain Guard Installation continued 2 16 Q
37. ator 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 initiate the hook to close In the closed position a latch engages the load beam and latches it in this position To release the load the latch is disengaged from the load beam With the latch disengaged the weight of the load causes the load beam to swing to its open position and the cargo sling ring slides off the load beam The load beam then remains in the open position awaiting the 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
38. ccordance with our current policy associated with the review of foreign STCs some STCs applicable to certain categories of rotorcraft 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 STCs fail within these criteria These STCs 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 STCs by Transport Canada Should you require additional information with regards to this matter or clarification please do not hesitate to contact the undersigned at 604 666 5597 Yours truly H W Wong Senior Engineer Aircraft Certification for Minister of Transport c c Mr Jeffrey E Duven Acting Manager Seattle ACO Canada Certification 7 4 This page intentionally left blank Certification 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
39. copter the more accurate the calculated Calibration Code will be Load Weigh System Operation Instructions 3 9 The Setup Mode 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 d
40. d joint fails and allows un commanded load release the inner cable to activate the hook s mechanical release mechanism and the hook opens Installation Instructions 2 9 Placard Installation Installation Instructions Q Install appropriate load limitation placard P N 215 166 00 3086 Ib 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 The provided load limitation placards P N 215 166 00 and P N 215 168 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
41. ed per above step DP 2 4 6 Ground Strap Installation Location Q 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 Q 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 o Re install lower fairings 2 12 Installation Instructions 2 4 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 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
42. ever Body 1 6 517 049 00 Pulley 1 7 290 759 00 Shaft 1 8 510 450 00 Bolt Handle pivot 1 9 510 449 00 Bolt Pulley Pivot 1 10 290 755 00 Handle 1 11 510 042 00 Washer 1 12 510 082 00 Nut 2 13 510 125 00 Cotter Pin 2 14 510 248 00 10 32 Heli Coil 2 15 290 753 00 Clamp Half 1 16 510 390 00 Screw Mounting Clamp 2 17 510 095 00 Washer 2 System Part Numbers System Part Numbers continued 232 151 00 Quick Disconnect Support Assembly Item Part Number Description Qty 1 290 797 00__ Attach Bracket 1 2 290 791 00 Release Cable Cap 1 3 514 053 00 Spring Clip 1 4 510 102 00 Nut 2 5 510 085 00 AN 970 3 2 6 510 455 00 NAS 6603 13 2 a 514 050 00 Spring Clip 1 8 510 211 00 Button Head Screw 3 9 531 016 00 Crimp Sleeve 2 10 531 015 00 Lanyard 6 System Part Numbers 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 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
43. gure 2 2 1 and Figure 2 2 5 and install Plastic Edging Grommet P N 500 065 00 Figure 2 2 5 Grommet Installation Plastic Edging Grommet P N 500 065 00 Installation Instructions 2 2 Fixed Manual Release Cable Assembly Installation continued Q At the RH forward hard point X2700 secure the cable to the Adel Clamp installed per Figure 2 1 2 Q Install Quick Disconnect Bracket Assembly P N 232 151 00 on the RH rear lower fairing with the fairing removed at a location 400mm 15 7 in to the right of the A C centerline and in line with the fwd fuel tank support reference Figure 2 2 1 utilizing the existing insert holes in the honeycomb panel structure Secure with fasteners provided pre assembled on bracket as illustrated below NOTICE If your helicopter does not have holes in the honeycomb panel modify panel per Airbus Helicopters Service Bulletin No 25 00 62 Figure 2 2 6 QD Bracket Installation P N 510 102 00 e Washer 2 Nut 2 P N 510 085 00 Bolt 2 4 SL K P N 510 455 00 QD Bracket Assembly P N 232 151 00 Installation Instructions 2 5 2 2 Fixed Manual Release Cable Assembly Installation continued Q Install the two clamps Airbus Helicopters P N A3125 2 H179 in the RH rear lower fairing that will support the removable section of the manual release cable The clamps are installed at points 1 and 2 see below using existing inserts in the belly of the helicopter Do
44. he fixed cable adapter fitting and lock in position by engaging a castellation with the Locking Pin P N 514 052 00 o Snap the removable cable Adapter Fitting into the inboard spring clip on the Quick Disconnect Support Assembly 2 23 2 7 Removable Manual Release Cable Assembly Installation continued Fi ure 2 7 4 Manual Release Cable Connection Removable Manual Release Cable Adapter Fitting Fixed Manual Release Cable Adapter Fitting BAAN m 1 94 2 00 gt Locking Pin P N 514 052 00 o At the cargo hook ensure the manual release cable is between the two prongs of the release lever fork as illustrated in Figure 2 7 5 Manual release cable rigging must be done with the cargo hook in the closed and locked position o With the cargo hook closed and locked rotate the release lever in the clockwise direction to remove free play the free play is taken up when the hook lock indicator begins to move this is also felt as the lever rotates relatively easily for several degrees as the free play is taken up and measure the gap between the cable ball end and the release lever fork with the manual release lever in the cockpit in the non release position This gap should be a minimum of 125 inches 3 2 mm as shown in Figure 2 7 5 Figure 2 7 5 Manual Release Cable Rigging Hook Lock Indicator
45. igits will be blinking Again at this point if you wish to return to the Run Mode without changing the Calibration Code power cycle the Indicator It is not possible to return to the Run Mode by using the buttons on the Indicator front panel without changing the Calibration Code If you wish to proceed lift the known load and when it is stabilized press either button to complete the procedure The Indicator will display the load This ends the procedure The Indicator is now calibrated to the Load Cell It is a good practice to go to the Code routine and record the new Calibration code for later reference Setting the Scale for a remote analog meter The Scale routine is used when a user supplied analog meter is connected to the Indicator It is used to match or calibrate the analog meter to the Indicator The Indicator outputs a 0 to 5 VDC analog signal which is proportional to the Load Cell load The Scale number tells the Indicator at what point in pounds or kilograms it 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
46. ing a System to the Factory 5 1 System Part Numbers 210 201 03 AS 350 Swing Removable Provisions 6 1 210 202 01 AS 350 Swing Fixed Provisions 6 2 232 137 01 Shackle Assembly 6 3 232 150 00 Release handle assembly 6 4 232 151 00 Quick Disconnect Support assembly 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 Load Cell Gimbal Assembly 6 9 232 145 03 Swing Hook Frame Assembly 6 10 Certification FAA STC 7 1 Transport Canada Approval 7 3 EASA STC 7 5 Section 1 General Information Introduction Safety Labels The P N 200 280 04 Cargo Hook Swing Suspension System kit consists of fixed provisions P N 210 202 01 and removable provisions P N 210 201 03 The fixed provisions are permanently installed on the aircraft while the removable provisions are easily removed when not required on the helicopter s mission These kits are approved for installation on Airbus Helicopters AS350B AS350BA AS350D AS350B1 AS350B2 and AS350B3 helicopters The following definitions apply to safety labels used in this manual Indicates a hazardous situation which if not D AN G E R avoided will result in death or serious injury Indicates a hazardous situation which if not avoided could result in death or serious injury Indicates a hazardous situation which if not avoided could result in minor or moderate injury
47. ll be determined by the installer 3 Installation and operation of the system on AS350B3 with the modification OP 3369 incorporated is not approved es 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 listed on the certificate EASA old Project Number EASA IM R S 01324 REV 2 SUPPLEMENTAL TYPE CERTIFICATE 10016937 REV 2 ONBOARD SYSTEMS INT EASA Form 91 issue 3 11 11 2009 3 3 Certification
48. nly it cannot hardware and software be changed 3 6 Load Weigh System Operation Instructions The Setup Mode continued Indicator Dampening The Damp or dampening routine allows the pilot to adjust the Indicator dampening level to his preference The dampening routine is a program that stabilizes the Indicator reading It offers a trade off between Indicator responsiveness and stability Ten dampening levels are available from 0 through 9 At level 0 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 f o ook tak LoadN O a a UN ZERO OIE IDA The CAL and the DAMP legend is turned on and the previously set dampening level is displayed
49. of the Setup routines and a brief discussion of their function and how they are programmed A complete discussion of each setup item is presented later in this section To enter the Setup Mode press both the Right and Left buttons at the same time while the Indicator is powered up and in the Run Mode To exit the Setup Mode and return to the Run Mode press both the buttons at the same time If you are in a Setup routine and have started to change an entry but you change your mind before completing the procedure power cycle the Indicator to exit the Setup Mode and then go to the Run Mode without changing the item The Indicator is power cycled by turning the Indicator power off for a few moments Load Weigh System Operation Instructions 3 5 The Setup Mode continued Table 3 2 Indicator Setup Routines MENU FUNCTION DISPLAY Press the Right button to view or change the To return to the Run Mode press both the scroll through the menu menu item Right and Left buttons at the same time Dampening Level sets the pilots preference Blinking display is previously entered DAMP for display dampening Dampening Level Select the desired dampening level by pressing the Left button Calibration Code matches the Indicator to the Display is previously entered CAL Code CODE Load Cell The Code is changed by selecting the digit to be changed with the Right button The selected digit will blink Change the blinking digit by pressing the Left but
50. of the manual release cable into the manual release boss on the cargo hook side plate until the threads protrude approximately 125 inches beyond the boss and secure with jam nut as shown in Figure 2 7 2 Leave the manual release cover off of the cargo hook until the other end of the release cable is connected in order to verify proper setting Figure 2 7 2 Initial Release Cable Adjustment Manual Release Cable Approx 125 in 3 2mm 2 22 Installation Instructions 2 7 Removable Manual Release Cable Assembly Installation continued Q Route the cable from the hook through the aft end of the suspension frame as illustrated below Clip the cable into the clamps at points 1 and 2 installed per section 2 2 Figure 2 7 3 Release Cable Routing Route cable outside of frame Forward Do not route through clamp at this locatio Manual Release Cable View Looking Down Installation Instructions o Connect the other end of the removable cable assembly to the end of the fixed cable by sliding the Adapter Fitting back to expose the swaged cable end fitting and connecting this fitting to the swaged cable end fitting on the fixed cable as shown below NOTICE The pre set compressed spring length is set at the factory to be 1 94 2 00 inches see figure 2 7 4 If necessary minor adjustments can be made at the release handle assembly on the collective o Thread the Adapter Fitting on the removable cable onto t
51. rcraft with modification 07 3475 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 7 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 1 5 Theory of Operation 1 6 The 200 280 04 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 manual 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 stick 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 indic
52. s used to Zero the display in the Run Mode and select the digit to be changed in the Setup Mode 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 ero amp Un Zero Legend Y Hook Logd Dampening Unit Legend Left Button Load Weigh System Operation Instructions 3 1 The Run Mode 3 2 The C 39 Indicator has two operating modes Run and Setup The Run Mode is used to display the cargo hook weight and the Setup Mode is used to setup or configure the Indicator to the helicopter and to the Load Cell When powered up the Indicator always comes 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 Figure 3 2 After Diagnostic Routine Hook Load xX 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 ZE
53. se 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 4 3 Cargo Hook Rigging continued 4 4 Some combinations of small primary rings and large secondary rings could cause fouling during release It is the responsibility of the operator to assure the cargo hook will function properly with each rigging Multiple load rings nylon type straps or similar material or rope must not be used directly on the cargo hook load beam If nylon straps or rope must be used they should be first attached to a steel primary ring Verify that the ring will freely Slide off the load beam when it is opened Only the primary ring should be in contact with the cargo hook load beam Figure 4 5 Cargo Hook Rigging Examples Recommended Primary Ring Long Line Avoid Operation Instructions Section 5 Maintenance Refer to the Instructions for Continued Airworthiness ICA manual 123 011 03 for maintenance of the cargo hook suspension system For maintenance of the cargo hook refer to Cargo Hook Service Manual 122 017 00 Instructions for Returning Equipment to the Factory Maintenance If an Onboard Systems product must be returned to the factory for any reason including returns service repairs overhaul etc obtain an RMA number before shipping your return NOTICE An
54. t exceeding 1 000 or imprisonment not exceeding 3 years or both This certificate may be transferred in accordance with FAR 21 47 FAA FORM 8110 2 10 68 PAGE 1 OF 3 PAGES Certification 7 1 FAA STC continued United States of Amerin Bepartment of Transportation Frderal Aviation Administration Supplemental Type Certificate Continuation Sheet Nunley SR01164SE Onboard Systems International sued January 22 2003 Heissued January 2001 Ano Or Amended October 26 2004 February 04 2005 October 30 2007 Apri 13 2010 Description of the Tyne Design Change continued 7 Yt GF ge INSTRUCTIONS FOR CONTINUED AIRWORTHINESS AND CARGO HOOK SERVICE MANUAL 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 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 SYSTEM PART NUMBER P N OWNER S MANUAL No 200 280 01 200 280 02 200 280 03 200 280 04 Limitations and Conditions continued SYSTEM PART NUMBER 200 280 01 41
55. ton Installation ZERO matches the Indicator to Display is a combination of load on the Oin the installed Load Cell and to the helicopter Load Cell and normal load cell zero After this procedure the display will be zero offset Remove all weight from the henno ead onth Carso Hook installed Load Cell except the Cargo X 8 Hook and press any button to complete the procedure and return to the Run Mode Load is used to calibrate the system by lifting No previous display is shown Enter the LOAD a known load known load using the Right button to select the digit to be changed and Left button to enter the number Known load is entered X 10 ie 5000 kilograms is entered as 500 After the known load is entered press both buttons at the same time and lift the known load When the load is stabilized press either button A new Calibration Code will be calculated and the known load will be displayed This completes the procedure Scale matches the analog output of the Display is previously entered number To Scale Indicator to an optional remote analog meter Change the number use the Right button to select a digit use the Left button to scroll the digit to the desired number Entry is times 10 LB KG Units selects the Indicator units pounds or Display is previously selected unit To kilograms change the unit use the Left button XX V Version is the revision level of the Indicator Version is for information o
56. trical release connector 32M installed per Section 2 4 Connect the ground strap from the hook to the fixed ground strap installed per section 2 4 Connect the end of the load cell cable to the fixed load weigh harness connector 55M installed per Section 2 4 See table 2 1 for connector pin out information Table 2 1 Cargo Hook Connector Function A Ground e Pove 2 25 2 8 External Electrical Release and Load Cell Cable Installation continued 2 26 The cargo hook is equipped with a suppression diode that will be damaged if the cargo hook electrical connection is reversed Un commanded cargo hook release will happen if the manual release cable is improperly restrained The cable must not be the stops that prevent the Cargo Hook from swinging freely in all directions If the Cargo Hook loads cause the hook to strain against the manual release cable the swaged end of the cable may separate allowing the inner cable to activate the cargo hook manual release mechanism The result is an un commanded release Ensure that no combination of cyclic stick or Cargo Hook position is restrained by the manual release cables Figure 2 8 1 Un commanded Release From Incorrectly Secured Cable 1 Cargo hook rotates and strains against the manual release cable conduit 2 The strain on the conduit exceeds the pull off force between the swaged fitting and the conduit 4 The load ring falls free in an 3 The swage
57. ual listed in the table below or later FAA approved revision See Continuation Sheet on Page 3 Limitations 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 modifications 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 the tuyyorling data which is the Cass for approval shall remain n fect until surrendered suena revoked or a termination date tt bherwise established by the Administrator oft the Federal Aviation Administration Date fi application March 29 2002 Date reissued Date of issuance January 22 2003 Zare amended October 26 2004 February 04 2005 October 30 2007 April 13 2010 By daveclton of the Administrator I Signature Acting Manager Seattle Aircraft Certification Office Title Any alteration of this certificate is punishable by a fine of no
58. uation Sheet s For the European Aviation Safety Agency Date of issue 21 06 2010 fp gt Fel Massimo MAZZOLETTI Certification Manager Rotorcraft Balloons Airships Note The following numbers are listed on the certificate EASA old Project Number EASA IM R S 01324 REV 2 SUPPLEMENTAL TYPE CERTIFICATE 10016937 REV 2 ONBOARD SYSTEMS INT EASA Form 91 Issue 3 11 11 2009 1 3 Certification EASA STC continued European Aviation Safety Agency This STC is the validation of FAA STC SRO1164SE issued on January 22 2003 and last amended 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 model 20028002 and 03 Revision 18 dated July 1 2009 approved by FAA 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 1230111 03 for system model 20028004 Rev 0 dated Januar
59. vided pre assembled on the release lever assembly as illustrated below Figure 2 2 2 Manual Release Lever Installation Release Lever Assembly Q Route the cable to underneath the cabin floor through the existing slot by removing the grommet to allow the cable end fitting to be fed through Re install the grommet 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 3 Cabin Floor Hole Detail O25mm Collective Pitch SS Lever Unit A C Centerline 150mm FROM X 1790 15 VIEW LOOKING DOWN Installation Instructions 2 3 2 2 Fixed Manual Release Cable Assembly Installation continued Q Underneath the floor route the manual release cable through an existing hole in the frame immediately aft of the collective Secure the cable at this point with an adel clamp P N 512 024 00 Fasten the adel clamp to the existing bracket Airbus Helicopters P N 350A86 1051 00 with hardware as illustrated below Figure 2 2 4 Cable Routing Through Frame Bolt P N 510 453 00 Washer P N 510 042 00 Nut P N 510 102 00 ouau O V Adel Clamp P N 512 024 00 A View Looking Aft Q Aft of the frame route the cable outboard through the hole in the structural member as shown in Fi
60. y 27 2010 approved by FAA and Onboard Systems Service Manual No 122005 00 or Keeperless Cargo Hook 528 023 01 Rev 17 dated March 9 2010 approved by FAA or be 122 015 00 for Hydraulic Cargo Hook Rev 7 dated January 30 2009 approved by FAA No 122 017 00 for Reeperices Cargo Hook 528 029 00 Rev 8 dated March 10 2010 approved by FAA Operation Onboard Systems RFMS bi 121 012 01 for system model 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 FAA ar No 121 012 03 for system mode 200 280 04 Rev 0 dated March 4 2010 approved by FAA eing numbers are listed on the certificate EASA old Project Number EASA IM R S 01324 REV 2 SUPPLEMENTAL TYPE CERTIFICATE 10016937 REV 2 ONBOARD SYSTEMS INT EASA Form 91 Issue 3 11 14 2009 2 3 7 6 Certification EASA STC continued European Aviation Safety Agency 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 External 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 sha
61. yed To return to Run without changing the units press both the Right and Left button at the same time To change the units press the Left button When the selection has been made press both the Right and Left button at the same time to return to Run 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 xX 10 CAL LB KG UN ZERD 3 12 Load Weigh System Operation Instructions 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 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 relatch do not use the unit until the difficulty is resolved The cargo hook release solenoid is intended to be energized only intermittently Depressing the electrical release button continuously in excess of 20 seconds will cause the release solenoid to overheat possibly causing permanent damage 2 Activate the manual
62. ystem was purchased Table 1 3 Onboard Systems Bill of Materials Part Description Total Kit Fixed Kit Removable Number 200 280 04 210 202 01 Kit 210 Qty Qty 201 03 Qty 120 104 03 Owner s Manual 1 1 1 121 012 03 RFMS 1 1 1 122 017 00 Cargo Hook Service Manual 1 1 123 011 03 ICA 1 1 1 210 095 00 C 39 Indicator 1 1 210 095 04 C 39 Indicator NVG Lights 1 1 215 165 00 AS 350 Multiple Decal Sheet 1 1 215 166 000 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 Forward Attach Cable Assembly 2 2 232 141 01 Aft Attach Cable Assembly 2 2 232 145 03 Hook Frame Assembly 1 1 232 150 00 Release Handle Assembly 1 1 232 151 00 Fixed Quick Disconnect Assembly 1 1 268 024 02 Manual Release Cable 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 1 290 780 00 Attachment Bracket 1 1 290 782 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 1 510 029 00 Nut 8 8 510 042 00 Washer 2 2 510 062 00 Washer 8 8 510 085 00

Owner`s Manual Cargo Hook Swing Suspension System Airbus

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