120-083-00 - Onboard Systems International
Contents
1. 1 4 The primary elements of the Cargo Hook are the load beam the internal mechanism and a DC solenoid The load beam supports the load and is latched through the internal mechanism The DC solenoid and an external manual release cable provide the means for unlatching the load beam The load beam is normally held in the open position by a spring loaded detent The load is attached to the load beam by passing the load 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 load ring slides off the load beam The load beam then remains in the open position awaiting the next load A load release can be initiated by three different methods Normal release is achieved by pilot actuation of the push button switch in the cockpit When the push button switch is pressed it energizes the DC solenoid in the Cargo Hook and the solenoid opens the latch in the internal mechanism In an emergency release can be achieved by operating a mechanical release pedal A manual release cable attached to the pedal operates the internal mechanism of the Cargo Hook to unlatch the load beam The load can also be releas2. om For ysTEMS BOARDS K WEB SITE AT wn THIS M ANU AL ASE CHECK MY ce REVISIO PLEASE C ap LATEST yn TALON MC KEEPERLESS CARGO HOOK KIT for the 204 205 212 amp 412 Series Helicopters Part Number 200 246 00 Owner s Manual Owner s Manual Number 120 083 00 Revision 10 March 27 2015 Z ONBOARD 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 Revision RECORD OF REVISIONS Page s Reason for Revision Section 4 Removed overhaul instructions from Section 4 and moved information to the new Service Manual 122 004 00 2 5 02 1 1 2 3 and 4 1 Added 528 020 02 Cargo Hook configuration 9 17 02 Title 4 3 Factory address change 8 7 03 1 1 2 5 3 1 4 1 and 4 2 Added 528 020 04 and 06 Cargo Hook configuration Moved RFMS to document 121 020 00 8 15 05 Section 3 Section 4 Added Cargo Hook Loading section Removed maintenance information from section 4 and replaced with reference to service manual 122 004 00 all the information was duplicated 09 19 07 TOC Section 1 2 4 amp Section 3 Added explanation of warnings cautions and notes to general information section Updated warnings cautions and notes throughout 05 15 12 1 3 2 3 Section 3 4 1
3. 13 99 1 19 01 1 13 03 3 15 05 5 30 13 By dlireetgon of her Wed Sigiamie 7 Acting Manager Seattle Aircraft Certification Office Title Any alteration af this certificate is punishable Ay 2 fine al not exceeding 7 000 ar imprisonment nat excreting 3 vers or hoch This certificate may be tetasterred in accorde with FAR 27 47 FA amp Far 8110 2010 63 PAGE 1 OF 7 PAGES Certification Approved Model List jo ebeg Qanssi3M ELOZ Oc ABW 668L OL Jequuo oN Q30N3NYvV BOIL ORBEA aD jeJ24rv ammess Jebeueyy Sugoy vov 7 p paAo1ddy vy fi uoisi s pancuddy Wy 1818 10 UOmeuJojul jguomnppe JO MSPH SASL 88S 2 62 pue LOZ 9 Wey 67 Siuaupuaurg pejep UOISIABY pue c9 L z peyep J92 ir d3Zire ELOZ Ot Aew LZ UOISIADH OC Z90 S51 ELOZ FL AI 00 DZO LCL 6Z VEd v J Zhe cc 138 B obag p 2 uBnou L 4 ELOZ 92 JEN Siusuupueulvg pajep L ucrsi e pue gs L g L vSoz LOZ os Aew LZ uosa OO ZPO SSL LOZ FL ACN OO OZO LZL pap J WO WS02 arc 1138 t uorsiney Bumed Pawg qumN A1N3aW3alddfs TV nNVMN NOILVMH31TV YSSWNnN alva isn SNIMVHG 1H9 13 13V342HO103 HOd SISSY 21 T3GON SV l4420103 AJA TAY aa1vas daaAOHddV vv4 aaAosddv vv NOILV2I3ILN32 TVNIOPHO 13V32330103 6664 21 Aew 31va INSSI LA MOOH O9YYI 00 97 007 TAGOW SWILSAS QHVOBNO JO NOILYTIYLSNI ONY NOLLVOINBY J04 38669004S IW LSI1 1300 Q3AOYddY YY4 NOLLVHISININWQY NOI
4. FAA approved revision of supporting documentation referenced in the subject STC are accepted and a revision of the subject STC is not required If you have any questions please do not hesitate to contact the undersigned at 604 666 5597 Yours truly Henry Wong Regional Engineer Aircraft Certification c c Dorenda D Baker Acting Manager Seattle ACO 1601 Lind Avenue S W 3960 Paramount Boulevard Renton Washington 98055 4056 your reference 190S 01 152 Canada m 5 4 Certification
5. rigged and load beam is latched If adjustment is made to the stop bolt in order to obtain proper clearance recheck adjustment of control cable and conduit With the cargo hook release pedal against the FORWARD stop check for the following conditions e Ensure that the spring assembly 204 070 998 does not bottom If the spring assembly should bottom return the cargo hook pedal to the aft stop and check control cable tension Cable tension should be 20 to 24 pounds e Check the operation of the mechanical release with at least 20 pounds load on the cargo hook load beam e Ensure the swing arm is full up Ensure lever is not stopped by the bottom end of the control cable outer housing e Ensure cargo hook load beam unlocks e Release the cargo hook pedal and ensure that both the upper and lower manual release cables return to the locking position e See the Bell Helicopter service instructions that cover the original cargo hook suspension system for additional instructions Installation Instructions Suspension System Electrical Release Installation Connect the electrical release cable to the connector located on the right underside of the lift beam and safety wire Table 2 1 Cargo Hook Connector PIN FUNCTION B Power C Ground Suspension System Installation Check Out After installation of the Suspension System perform the following functional checks Follow the Bell Helicopter instructions for the
6. the lower manual release cable between the swing arm and the cargo hook manual release provisions in the same manner as it was installed on the old hook Inspect the cable to insure that it is serviceable Install the cotter pins Connect the cargo hook electrical connector located on the Cargo Hook between the two cargo hook retaining bolts Safety wire the connector Position the Suspension System with the manual release control cable on the left and the clevis aligned in the Bell hard point 205 030 107 or 204 030 841 at waterline 38 87 Install the bolt washer and nut removed previously See the appropriate Bell service instructions for the correct installation torque values and maintenance Route the free end of the manual release cable aft and to the right looking aft of the hard point fitting See the Suspension System Manual Release Arrangement section of this manual Engage ball terminal into the cable connector 204 070 995 and secure with the cotter pin MS24665 155 Place the outer housing conduit of control cable assembly into clamp 204 070 996 1 and secure with screw AN520 1 or 12 and washer AN960PD10L into nut plate in existing structure The conduit end should measure approximately 0 42 inches from clamp 204 070 996 1 Installation Instructions Suspension System Manual Release Arrangement Figure 2 3 Suspension System Manual Release Arrangement 204 070 996 1 CLAMP AN520 1 OR 12 SCREW AN960PD10L WASHER
7. 204 070 998 SPRING iN MS24665 155 LIFT BEAM REF BL PIN 9 80 A 3 em 42 INCH APPROX 204 070 995 CONNECTOR REF FITTING REF MANUAL RELEASE CABLE VIEW LOOKING AFT UPPER MANUAL RELEASE CABLE SWING ARM LOWER RELEASE CABLE 12 TO 18 STOP BOLT MANUAL RELEASE LEVER 00 AND 02 HOOKS ONLY REF Installation Instructions 2 5 Suspension System Manual Release Cable Adjustment 2 6 Manual release cable adjustment must be done with the cargo hook in the closed and locked position Adjust the conduit of the manual release cable to obtain 0 03 to 0 08 inch dimension shown in the previous section and secure clamp shown in detail A of the Suspension System Detail section Adjust connector 204 070 995 shown in the previous section to obtain 0 10 inch over travel in the control cable as shown in the previous section The stop bolt of the swing arm should be in contact with the top of the cargo hook case and the swing arm should be parallel to the plane of the main hook attachment bolts when the 0 10 inch measurement is taken By grasping the top of the lower control cable apply tension until all the backlash is taken out Measure the clearance of the lower control cable ball terminal to the swing arm as shown in Figure 2 2 This measurement shall be 0 12 to 0 18 inches when system is
8. Added cargo hook P N 528 020 10 Updated format of Section 3 Updated instructions for returning a system to the factory Removed Functional Check Before Installation section 02 15 13 1 1 2 3 2 4 3 1 Removed reference to suspension system P Ns for clarity Added Figure 2 2 Updated Figure 3 1 03 27 15 1 1 2 6 Updated list of eligible cargo hook to replace to match STC added caution stating cargo hook must be closed when adjusting manual release system 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 ii This page intentionally left blank CONTENTS Section 1 Section 2 Section 3 Section 4 Section 5 General Information Introduction 1 1 Safety Labels 1 2 Bill of Materials 1 3 Inspection 1 3 Specifications 1 3 Theory of Operation 1 4 Installation Instructions Suspension System Removal 2 1 Cargo Hook Removal 2 1 Suspension System Detail Illustration 2 2 Functio
9. LYIAY 1v33034 Certification 5 2 Canadian STC i amp Transport Canada Transports Canada Department of Transport Supplemental Type Certificate This approval is issued to Number SH99 217 Onboard Systems Issue No 1 11212 NW St Helens Road Approval Date September 20 1999 Portland OREGON Issue Date September 20 1999 97231 UNITED STATES OF AMERICA Responsible Office Pacific Aircraft Engine Type or Model Bell 204B 205A 205A 1 212 412 and 412EP Canadian Type Certificate or Equivalent FAA Type Certificate HISW Bell 204B 205A 205A 1 Canadian Type Certificate H 86 Bell 212 412 412EP Description of Type Design Change Installation of Onboard Systems Model 528 020 00 Cargo Hook per FAA STC SR00699SE Installation Operating Data Required Equipment and Limitations Installation of Onboard Systems Model 528 020 00 cargo hook is to be carried out in accordance with FAA approved Onboard Systems Owner s Manual No 120 083 00 dated March 10 1999 This cargo hook is to be fabricated in accordance with FAA approved Onboard Systems Master Drawing List No 155 047 00 dated April 6 1999 Inspect this cargo hook in accordance with Section 4 of Onboard Systems Owner s Manual No 120 083 00 dated March 10 1999 Approval of this change in type design applies to Bell 204B 205A 205A 1 212 412 and 412EP rotorcraft which were previously equipped with an FAA approved installation of the following cargo ho
10. am 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 See following illustration Figure 3 4 Example of Recommended Cargo Hook Rigging Secondary Ring or Shackle Suspension System Operation Instructions Section 4 Maintenance Refer to the Cargo Hook Component Maintenance Manual CMM 122 004 00 for maintenance of the cargo hook 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 NOTICE 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 OnboardS ystems 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 R
11. ed by the manual actuation of the cable mechanism located above the Cargo Hook on the suspension On 00 02 and 10 cargo hook configurations the load can also be released during ground operations by the actuation of a lever located on the side of the Cargo Hook General Information Section 2 Installation Instructions Suspension System Removal The Suspension System interfaces with several helicopter components such as the cargo hook manual and electrical release provisions Before removing the Cargo Hook Suspension System have available and be familiar with the Bell Service Instructions 204 3 212 5 or later bulletins See the Suspension System Detail Illustration located on the following page of this manual Remove the cargo hook manual release cable at the 204 070 995 Connector Loosen the 204 070 996 1 Clamp to allow the cable to slide through it The Connector and the Clamp are located at approximately WL 39 87 and between BL 9 80 and BL 0 00 near the upper end of the suspension system Disconnect the suspension system electrical connector located between the suspension system and airframe Remove the Bell load bolt located at BL 0 00 WL 38 87 and Station 137 55 this will allow the suspension system to be removed through the bottom of the aircraft Cargo Hook Removal Installation Instructions To remove the Cargo Hook from the suspension system disconnect the lower manual release cable from the swing arm by re
12. eturn the components freight cartage insurance and customs prepaid to Onboard Systems 13915 NW 3rd Court Vancouver Washington 98685 USA Phone 360 546 3072 Maintenance 4 1 This page intentionally left blank Section 5 Certification FAA STC Thi totos i Ameren Bexvtnent of Grzuepurtatum Meral Aviation Administration Supplemental Cope Certificate Nuuinber SRO0699SE This ceakifivate issen to Onboard Systems 13915 NW 3rd Court Vancouver WA 98685 certifies that the change in the tye design for the following predict wilh the imitations and conditions hevefove ad specified ereen meeli ike auro PEGHIIEIRENLS Of Hot ofthe Fegulakions iginal Product Type Eewtifirate Mambor See attached Federal Aviation Administration FAA Make Approved Model List AML SROOS99SE for approved Model aircraft models and applicable airworthiness regulations Beseription of the Type Design Change Fabrication of Onboard Systems Model 200 246 00 cargo hook kit in accordance with Onboard Systems Master Drawing List No 155 047 00 Revision 21 dated March 26 2013 or later FAA approved revision and installation of these hooks in accordance with Onboard Systems Owner s Manual Na 120 083 00 Revision 9 dated February 15 2013 or later FAA approved revision Inspection of these hooks in accordance with Section 4 of Onboard Systems Service Manual No 122 004 00 Revision 21 dated January 8 2013 or later FAA approved revision SLin
13. itetions and Condivons Approval of this change in type design applies only to the Bell rotorcraft models listed on AML No SROOS99SE revised May 30 2013 or later FAA approved revision which were previously equipped with an FAA approved installation of the following cargo hooks Bell P N 204 072 924 1 or 7 or Breeze Eastern P N SP7109 1 11 12 62 or 93 This approval shauld 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 by this STC must be operated in accordance with a copy of FAA approved Rotorcraft Flight Manual Supplement RFMS No 121 020 00 Revision 1 dated May 14 2013 or later FAA approved revision If the holder agrees to permit another person to use this certificate to aller the product the holder shall give the other parson written evidence of that permission ias covlifecnte aud the supporting dale which is the basis for approval alt remain in offect until surrendered segeended wwooked or a termination date otherwise cstablishud L lhe bera dre on DA the Federal tiation atre Mover Sale of application April 13 1999 Beale reissued Rate of aree May 17 1999 Date amended 110 89 12
14. itial installation This procedure may vary in different countries Make the appropriate aircraft log book entry Installation Instructions Section 3 Operation Instructions Cargo Hook Operating Procedures Prior to a flight involving external load operations perform the following Operation Instructions 1 Before operating the Suspension System be completely familiar with the Rotorcraft Flight Manual Supplement for External Cargo Operation for your helicopter Cargo is released electrically by use of the cyclic CARGO RELEASE button Refer to the applicable RFM Supplement for each helicopter for switch settings and sequence Activate the electrical system and press the release button to ensure the cargo hook electrical release is operating correctly The cargo hook must release The solenoid in the hook is not rated for continuous duty Continuous power to the solenoid for longer than 30 seconds will damage the solenoid Depress the manual release foot pedal in the cockpit to test the cargo hook manual release mechanism Manually close the hook After each release the cargo hook must be manually closed When the hook is closed verify that the hook locked indicators are aligned Do not use the hook unless the indicators are aligned If marks are not aligned the hook may not be fully locked Figure 3 1 Hook Locked Indication Engraved lines must be aligned as shown 3 1 Suspen
15. moving the cotter pin located in the out board end of the swing arm Remove the cargo hook electrical connector located on the Cargo Hook between the two cargo hook retaining bolts Remove the two cargo hook retaining bolts and separate the Cargo Hook from the suspension system Remove the two bumper ring retaining bolts and separate the bumper ring from the Cargo Hook 2 1 Suspension System Detail Illustration Figure 2 1 Suspension System Detail Illustration 204 070 996 1 CLAMP DETAIL A 204 070 998 SPRING REF LIFT BEAM REF CABLE CLAMP e na MANUAL RELEASE CABLE 204 070 995 MANUAL RELEASE CABLE ECTOR REF BELL 205 030 107 OR 204 030 841 HARD POINT BELL HELICOPTER LOAD BOLT ELECTRICAL RELEASE CONNECTOR VIEW LOOKING AFT STOP BOLT SWING ARM AN COTTER PIN N CARGO HOOK RETAINING BOLT 3 ij LOWER MANUAL f RELEASE CABLE BUMPER RING RETAINING BOLT UMPER RING BUMPER RING RETAINING BOLT CARGO HOOK CARGO HOOK LOAD BEAM 2 2 Installation Instructions Cargo Hook Installation Ensure the Cargo Hook removed is on the list in section 1 of this manual Inspect the suspension system to insure that all components are in serviceable condition before installing the new Carg
16. nal Check Before Installation 2 3 Cargo Hook Installation 2 3 Suspension System Installation 2 4 Suspension System Manual Release Arrangement 2 5 Suspension System Manual Release Adjustment 2 6 Suspension System Electrical Release Installation 2 7 Suspension System Installation Check Out 2 7 Component Weights 2 8 Paper Work 2 8 Operation Instructions Cargo Hook Operating Procedures 3 1 Cargo Hook Loading 3 2 Cargo Hook Rigging 3 3 Maintenance Instructions for Returning a System to the Factory 4 1 Certification FAA STC 5 1 Approved Model List 5 2 Canadian STC 5 3 iii This page intentionally left blank Section 1 General Information Introduction The 200 246 00 Cargo Hook Kit is approved as a replacement for the following cargo hooks on Cargo Hook Suspension Systems on Bell 204B 205A 205A 1 212 412 and 412EP models Bell Cargo Hook Equivalent Breeze Eastern Part Number Cargo Hook Part Number 204 072 924 1 SP7109 1 11 204 072 924 7 SP7109 62 SP7109 12 SP7109 93 General Information 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 R avoided will result in death or serious injury Indicates a hazardous situation which if not avoided could result in death or serious injury Indicates a hazardous situation which if not avoided could result in minor or moderate injury Draws
17. o Hook to the suspension system and returning the system to service The kit is normally shipped with the Bumper Ring installed onto the cargo hook If installing a kit that is not assembled refer to the instructions in the following paragraph for assembly Install the P N 220 040 00 Bumper Ring to the Cargo Hook using the two P N 510 314 00 Cap Screws four P N 290 210 01 Spacers and P N 510 104 00 Nuts Insert a Cap Screw with a Spacer into one of the Bumper Ring mount holes See Figure 2 1 for mount hole locations Place the second Spacer into the other side of the Bumper and secure with the Nut Repeat this for the second Cap Screw installation Torque Cap Screw and Nuts to 120 160 in lbs Figure 2 2 Cargo Hook Bumper Assembly Spacer P N 290 210 01 Qty 4 Nut P N 510 104 00 Bolt P N 510 314 00 Qty 2 Bumper P N 220 040 00 Cargo Hook P N 528 020 10 shown Install the new Cargo Hook and Bumper Ring assembly to the suspension system in the same manner as the old hook was installed using the hardware that was removed See the appropriate Bell service instructions for the correct installation torque values Inspect the hardware to insure that it is serviceable Orient the hook to the suspension system such that the cargo hook load beam points in the same direction as the swing arm See Figure 2 1 Installation Instructions 2 3 Suspension System Installation 2 4 Connect
18. ok Bell P N 204 072 924 1 or 7 or Breeze Eastern P N SP7109 1 11 or 62 Modified rotorcraft must be operated in accordance with an FAA approved copy of Onboard Rotorcraft Flight Manual Supplement No 120 083 00 dated May 17 1999 Basis of Certification as defined in the applicable Type Certificate Data Sheets or later FAA approved revisions End Conditions This approval is only applicable to the type model of aeronautical product specified therein Prior to incorporating this modification the installer shall establish that the interrelationship between this change and any other modification s incorporated will not adversely affect the airworthiness of the modified product craft C rtification For Minister of Transport isl Canada Certification 5 3 iwi Transport Transports Canada Canada Aviation Aviation Aircraft Certification Branch 620 800 Burrard Street Vancouver BC V6Z 2J8 Your file Votre r f rence Our file Notre r f rence 5009 02 May 1 2001 Onboard Systems 11212 NW St Helens Road Portland OR 97231 Attention Mr Ron Pritle Subject Amendment of Canadian STC SH99 217 Issue 1 dated September 20 1999 Dear Sir Madam This is in response to your letters to FAA Seattle ACO dated February 23 2001 requesting a revision of the subject STC Having reviewed the subject STC and FAA STC SR00699SE Date Amended January 19 2001 we would like to inform you that the later
19. sion System Operating Procedures continued 4 Cargo hook P N 528 020 10 has a lever for opening the cargo hook from the ground With no load on the hook rotate the lever counterclockwise CCW until the load beam opens The hook may be flown in the open position to facilitate loading Figure 3 2 Ground Release Lever Rotate lever CCW to open cargo hook Release Lever for ground crew operation 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 3 3 until an internal latch engages the load beam and latches it in the closed position 3 2 Operation Instructions Cargo Hook Loading continued Figure 3 3 Cargo Hook Loading Cargo Hook Rigging Extreme care must be exercised in rigging a load to the Cargo Hook Steel load rings are recommended to provide consistent release performance and resistance to fouling Refer to Figure 3 4 for the recommended rigging The example shown is not intended to represent all rigging possibilities It is the responsibility of the operator to assure the hook will function properly with the rigging Suspension System Operation Instructions 3 3 Cargo Hook Rigging continued 3 4 Nylon Type Straps or Rope Nylon type straps or similar material or rope must not be used directly on the cargo hook load be
20. specific helicopter Direct an assistant to observe the Cargo Hook and reset the cargo hook load beam to the closed position as required Installation Instructions l Ensure that the manual release cable assembly and the electrical release cable have enough slack to allow full swing of the suspension assembly without straining or damaging the cables Close the cargo hook release circuit breaker and position the battery switch to the ON position Depress the cargo hook switch The Cargo Hook should release Rotate the suspension system 90 degrees close the cargo hook and repeat step 3 Rotate the suspension system another 90 degrees close the cargo hook and repeat step 3 Repeat this procedure until the suspension system is back at its original position To prevent burning out the solenoid do not hold the switch for more than 5 seconds in any 30 second period With the cargo hook closed depress the foot operated cargo hook mechanical release in the cockpit the Cargo Hook should release See the Bell Helicopter service instructions that cover the original cargo hook suspension system for additional instructions 2 7 Component Weights Paper Work 2 8 The weight of the 200 246 00 Cargo Hook kit is 17 5 pounds This is approximately the same weight as the Cargo Hook and Bumper it replaced Place the Rotorcraft Flight Manual Supplement 121 020 00 into the Rotorcraft Flight Manual In the US fill in FAA form 337 for the in
21. the reader s attention to important or N O C E unusual information not directly related to safety Used to address practices not related to personal injury 1 2 General Information Bill of Materials Inspection Specifications General Information The following items are included with the 200 246 00 Cargo Hook Kit if shortages are found contact the company from whom the system was purchased 528 020 10 Cargo Hook 220 040 00 Bumper Ring 510 314 00 Cap Screw l Optional cargo hook part number is 528 020 06 These part numbers are interchangeable Cargo hook part number 528 020 10 incorporates a ground crew release lever Inspect the Cargo Hook for evidence of damage corrosion and security of lock wire and fasteners If damage is evident do not use the unit until it has been repaired Table 1 1 Specifications Design load 6 000 Ib 2 721 kg Design ultimate strength 27 000 Ib 12 247 kg Electrical release capacity 15 000 Ib 6 804 kg Mechanical release capacity 15 000 Ib 6 804 kg Force required for mechanical 18 Ib Max 400 travel release at 6 000 Ib Electrical requirements 22 28 VDC 9 amps Minimum release load Unit weight 11 75 pounds 5 33 kg Mating electrical connector MS3106F16S 5S Load capacities given are for the equipment described only Loading limits for your particular helicopter model still apply Consult your flight manual 1 3 Theory of Operation
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