120-047-00 - Onboard Systems International
Contents
1. OR syst s4s cOM I www 7 ONBOARDSY i p i core 7 i i NISTON or THIS MAI HE LATES SASK CHE Owner s Manual Cargo Hook Kit for the MD Helicopter s 369 Series and 500N Helicopters Part Number 200 187 00 Owner s Manual Number 120 047 00 Revision 12 April 29 2008 Z CONBOARD SYSTEMS I N TERNATIONAL 13915 N W 3rd Court Vancouver Washington 98685 USA Phone 360 546 3072 Fax 360 546 3073 Toll Free 800 275 0883 www OnboardSystems com This page intentionally left blank Revision Date RECORD OF REVISIONS Page s Reason for Revision 10 10 00 Section 4 Removed overhaul instructions from Section 4 and moved information to the new Service Manual 122 001 00 5 31 01 3 5 RFMS Pg 5 2 1 2 4 Replaced old hook no 528 010 00 with current rev 9 11 02 Title 4 3 Factory address change 9 26 05 2 3 2 5 Section 4 Clarified manual release cable rigging instructions added CAUTION note for electrical connector added kg equivalents to Table 2 1 Added reference to Cargo Hook Service Manual 122 001 00 in Section 4 and removed duplicate information from this manual 02 07 07 1 1 2 2 3 1 4 1 Changed cargo hook part number from 528 010 00 to 528 010 04 per Service Bulletin 159 017 00 Added reference to service manual on page 3 1 and removed reference to troubleshooting table 09 12 07 Sections 1 2 and 3 Listed RFMS 122. pd ELECTRICAL RELEASE CABLE zx Ozer i C 280050 HoN MANUAL RELEASE CABLE ae Installation Instructions Installation Check Out After installation of the Cargo Hook perform the following functional checks 1 Swing the installed Cargo Hook and ensure that the manual release cable assembly and the electrical release cable have enough slack to allow full swing of the suspension assembly without straining or damaging the cables The cables must not be the stops that prevent the Cargo Hook from swinging freely in all directions 2 Apply 10 20 pounds to the cargo hook load beam and squeeze the lever operated cargo hook mechanical release the cargo hook should release 3 Close the cargo hook release circuit breaker and position the battery switch to the ON position Apply 10 20 pounds to the cargo hook load beam and depress the cargo hook electrical release button the cargo hook should release 4 See the MDHC service instructions for your specific helicopter model for additional installation instructions Component Weights The weight of the cargo hook components are listed in Table 2 1 Table 2 1 Component Weights Ibs kgs Cargo Hook Manual Release Cable Electrical Release Cable 0 5 0 23 Bumper Pads 0 2 0 09 Travel Limit Bumper 0 1 0 05 Paper W
3. end is the cable adjuster and thread this end of the manual release cable all the way into the hook and tighten against the hook see Figure 2 4 Place the cable ball end fitting into the fork of the manual release lever as illustrated in Figure 2 4 Adjust the manual release cable system for a minimum of 125 inches of free play at the fork as shown with the manual release handle in the cockpit in the non release position Figure 2 4 Manual Release Cable Rigging Manual Release Lever Manual Release Cable sO Zp 4 Ball End Fitting a J e Min free play Route the manual release cable and rig the cyclic stick release lever assembly following the MDHC Installation and Maintenance Instructions Publication No CSP 005 or later approved source Replace the cargo hook manual release cover and safety wire Connect the Cargo Hook electrical release cable connector to the belly mounted bulkhead receptacle and safety wire the connector Listed below is the pin out for the cargo hook and the bulkhead connector The Cargo Hook is equipped with a suppression diode that will be damaged if the Cargo Hook electrical connections are reversed Do not attach the electrical connector until the polarity of the aircraft connector is determined to be compatible with the Cargo Hook connector listed below Cargo Hook Connector Bulkhead Connector B Power BCI Ground 2 3 Secure the Release Cables Installation Overview 2
4. 4 Secure the cargo hook manual and electrical release cables following the MDHC Installation and Maintenance Instructions Publication No CSP 005 or later approved source The first clamp used to secure the manual release to the A C skin should not be less than 23 inches from the hook Un commanded cargo hook release will happen if the manual and electrical release cables are improperly restrained The cables must not be the stops that prevent the Cargo Hook from swinging freely in all directions If the Cargo Hook loads cause the hook to strain against the manual release cable the swaged end of the cable may separate allowing the inner cable to activate the cargo hook manual release mechanism The result is an un commanded release Ensure that no combination of cyclic stick or Cargo Hook position is restrained by the manual or electrical release cables Figure 2 5 Un commanded Release From Incorrectly Secured Cable Hook rotates and strains against the manual release conduit __ a gt N The strain on the conduit exceeds the _ Ds O p pull off force between the swaged lt VY fitting and the conduit The swaged joint fails and allows the inner cable to activate the hook s mechanical release mechanism and the hook opens The load ring falls free in an un commanded release Figure 2 6 Installation Overview AIRFRAME TO HOOK MOUNTING BRACKET __ TRAVEL LIMIT BUMPER aN LOAD BOLT CARGO HOOK
5. Bumper Installation TRAVEL LIMIT BUMPER TRAVEL LIMIT BUMPER ban w vial INSTALLED Install the new Cargo Hook to the existing MDHC airframe mounting bracket using the load bolt nut and cotter pin supplied with the new hook as illustrated in Figure 2 2 The cargo hook load beam is to point aft 2 1 Cargo Hook Installation continued Figure 2 2 Attach Hardware Installation AIRFRAME TO HOOK MOUNTING BRACKET WASHER P N 510 183 00 WASHER P N 510 183 00 AN960 816L AN960 816L WASHER P N 510 174 00 o NAS1149F 0663P ey COTTER PIN P N 510 178 00 MS24665 302 ay uw U P N 510 170 00 AN320 C6 ATTACH BOLT n 290 332 00 CARGO HOOK Remove any existing hook bumper pads that may be attached to the A C skin Install the P N 290 361 00 Bumper Pads to the airframe skin in the location illustrated in Figure 2 3 with 3M trim cement Figure 2 3 Bumper Pads BUMPER PAD P N 290 361 00 QTY 2 CARGO HOOK MOUNTING BRACKET VIEW LOOKING UP FROM BELOW AIRCRAFT 2 2 Installation Instructions Cargo Hook Installation continued Installation Instructions Connect the manual release cable to the Cargo Hook per the following Remove the cargo hook manual release cover Locate the swaged end of the manual release cable assembly the other
6. Onboard Systems Owner s Manual No 120 047 00 Revision 12 dated April 29 2008 and Cargo Hook Service Manual No 122 001 00 Revision 0 dated June 13 2000 or later FAA approved revision Limitations and Conditions Approval of this change in type design applies to only those McDonnell Douglas model rotorcraft listed above which were previously equipped with an FAA approved installation of McDonnell Douglas cargo hook suspension systems and cargo hooks shown in the table on Continuation Sheet Page 3 This approval should not be extended to 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 Modified rotorcraft must be operated in accordance with an FAA approved copy of Onboard Rotorcraft Flight Manual Supplement RFMS No 121 043 00 Revison 0 dated October 1 2007 or later FAA approved revision This certificate issued to See Continuation Sheet Page 3 This certificate and the supporting data whioh is the Basis for approval hall remain in foot until sur ventared suspended revoked or a termination date is otherwise established by the Administrator off the Federal Aviation Administration Date of application November 10 1996 Date of issuance Ja
7. 1 043 00 in Bill of Materials removed RFMS from back of manual Added Warnings Cautions and Notes section and re formatted these items where applicable Updated Figure 2 3 02 21 08 Removed MD Helicopter kit p n 369H90072 503 from the list of approved installations 04 29 08 Clarified part numbers and applicability in Introduction section Register Your Products for Automatic Notifications Onboard Systems offers a free notification service via fax or email for product alerts and documentation updates By registering your Onboard Systems products at our website we will be able to contact you if a service bulletin is issued or if the documentation is updated You can choose to receive notices on an immediate weekly or monthly schedule via fax email or both methods There is no charge for this service Please visit our website at www onboardsystems com notify php to get started This page intentionally left blank CONTENTS Section 1 Section 2 Section 3 Section 4 Section 5 General Information Introduction 1 1 Warnings Cautions and Notes 1 1 Bill of Materials 1 2 Inspection 1 2 Specifications 1 2 Theory of Operation 1 3 Installation Instructions Cargo Hook Removal 2 1 Cargo Hook Installation 2 1 Secure the Release Cables 2 4 Installation Overview 2 4 Installation Check Out 2 5 Component Weights 2 5 Paper Work 2 5 Operation Instructions Operating Procedur
8. Same Bade it Page 2 of 2 Canada Certification EASA STC X European Aviation Safety Agency X SUPPLEMENTAL TYPE CERTIFICATE EASA IM R S 01396 This certificate established in accordance with Regulations EC No 1592 2002 and EC No 1702 2003 and issued to Onboard Systems 13915 NW 3rd Court Vancouver WA 98685 United States certifies that the change in the type design for the product listed below with the limitations and conditions specified meets the applicable type certification basis and environmental protection requirements when operated within the conditions and limitations specified below Original Product Type Certificate number FAA H3WE Manufacturer MDHI Model 369D 369E 369FF 369HE 369HM 369HS 500N Original STC Number FAA STC SR00407SE Description of Design Change Onboard Systems Model 200 187 00 cargo hook on helicopters 369D 369E 369FF 369HE 369HM 369HS 500N Associated Technical Documentation 1 Onboard Systems Master Drawing List No 155 030 00 Revision 13 dated 6 May 2008 or later approved revisions Onboard Systems Owner s Manual No 120 047 00 Revision 12 dated 29 April 2008 or later approved revisions Cargo Hook Service Manual No 122 001 00 Revision 0 dated June 13 2000 or later approved revisions Onboard Rotorcraft Flight Manual Supplement RFMS No 121 043 00 Revision 1 dated February 22 2008 or later approved revisions Certification EASA STC contin
9. ble and manual release cable in the MD Helicopters 369H92105 501 cargo hook assembly Warnings Cautions and Notes The following definitions apply to Warnings Cautions and Notes used in this manual Means that if this information is not observed serious injury death or immediate loss of flight safety could occur Means that there is a risk of injury or degradation in performance of equipment if this information is not observed NOTE Draws the reader s attention to information which may not be directly related to safety but which is important or unusual General Information 1 1 Bill of Materials The following items are included with the Cargo Hook Kit if shortages are found contact the company from whom the system was purchased Part Number Description Quantity 528 010 04 Cargo Hook l 270 073 00 Electrical Release Cable 1 268 005 01 Manual Release Cable 1 290 360 01 Travel Limit Bumper 1 290 361 00 Bumper Pads 2 120 047 00 Owner s Manual 1 121 043 00 RFMS 1 122 001 00 Talon LC Hook Service Manual 1 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 Specifications Table 1 1 Specifications 7 pounds Mating electrical connector Force required for mechanical 8 lb Max 400 travel release at 3 500 Ib 1 2 General Information Theory of Operation General Informa
10. ce with FAR 21 47 FAA FORM 8110 2 1 10 69 PAGE 3 OF 3 PAGES 5 2 Certification STA i i Transport Canada Transports Canada Department of Transport Supplemental Type Certificate This approval is issued to Number SH97 30 Onboard Systems lssue No 3 11212 NW St Helens Road Approval Date May 15 1997 Portland OREGON Issue Date July 30 2001 97231 UNITED STATES OF AMERICA Responsible Office Pacific Aircraft Engine Type or Model HUGHES 369D 369E 369F 369FF 369HE 369HM 369HS 500N Canadian Type Certificate or Equivatent H 95 SOON only and FAA H3WE Description of Type Design Change Installation of Onboard Systems Model 200 187 00 Cargo Hook Kit per FAA STC SRO0407SE Installation Operating Data l Required Equipment and Limitations Fabrication of Onboard Systems Model 200 187 00 Cargo Hook Kit in accordance with FAA approved Onboard Systems Master Drawing List No 155 030 00 Revision 4 dated October 31 2000 Installation of this replacement cargo hook in accordance with FAA approved Onboard Systems Owner s Manual No 120 047 00 Revision 5 dated October 10 2000 Inspect Cargo Hook in accordance with Onboard Systems Owner s Manual No 120 047 00 Revision 5 dated October 10 2000 and Cargo Hook Service Manual No 122 001 00 Revision 0 dated June 13 2000 i Basis of Certification as defined in the applicable Type Certificate Data Sheets See Required Equipment and Limitations in Conti
11. es 3 1 Cargo Hook Rigging 3 2 Cargo Hook Rigging Illustrations 3 3 Maintenance Inspection 4 1 Instructions for Returning a System to the Factory 4 2 Certification STC 5 1 STA 5 3 EASA STC 5 5 CONTENT S continued ii Figures Tables 2 1 2 2 2 3 2 4 2 5 2 6 3 1 3 2 3 3 3 4 3 5 1 1 2 1 4 1 Travel Limit Bumper Installation 2 1 Attach Hardware Installation 2 2 Bumper Pads 2 2 Manual Release Cable Rig 2 3 Un commanded Release From Incorrectly Secured Cable 2 4 Installation Overview 2 4 Examples of Correct and Incorrect Cargo Hook Rigging 3 3 Un commanded Release Due to Large Load Ring 3 4 Load Hang Up Too Small or Multiple Load Rings 3 5 Un Commanded Release Due to Nylon Straps 3 6 Un Commanded Release Due to Cable or Rope Straps 3 7 Specifications 1 2 Component Weights 2 5 Inspection 4 1 Section I General Information Introduction The 200 187 00 cargo hook kit is approved for installation with the following MD Helicopters cargo hook kits which use the 369H92105 501 cargo hook assembly 369H90072 501 369H90072 515 369H90072 505 369H90072 517 369H90072 507 369H90072 519 369H90072 511 369H90072 523 The 528 010 04 Cargo Hook 270 073 00 Electrical Release Cable and 268 005 01 Manual Release Cable included in this 200 187 00 cargo hook kit are suitable as replacements for the cargo hook Breeze Eastern P N 17149 4 electrical release ca
12. lip the keeper up and then fall free Only correctly sized load rings must be used See examples below Figure 3 2 Un Commanded Release Due to Too Large of a Load Ring Load Ring flips over the Load Beam and gyrates The flip over often occurs with long line operations during landings and take offs Load Ring moves inward and bears against the keeper The Keeper is forced to rotate allowing the Ring to slip off 3 4 Operation Instructions Load Hang Up Due to Too Small of a Load Ring or Multiple Load Rings Load rings that are too small or multiple load rings will hang on the load beam when the load is released Only correctly sized load rings must be used See examples below Figure 3 3 Load Hang Up Due to Too Small a Load Ring or Multiple Load Rings oad Hang Up Due to L Multiple Rings on Load Beam Sling Load Operation Instructions 3 5 Un Commanded Release Due to Nylon Type Straps Nylon type straps or similar material must not be used directly on the cargo hook load beam as they have a tendency to creep under the keeper and fall free If nylon straps must be used they should be first attached to a correctly sized primary ring Only the primary ring should be in contact with the cargo hook load beam See examples below Figure 3 4 Un Commanded Release Due to Nylon Type Straps Nylon type strap on the Load Beam As the load swings the strap fibers work their way under the keeper The stra
13. load can also be released by the actuation of a lever located on the side of the cargo hook 1 3 This page intentionally left blank Section 2 Installation Instructions These procedures are provided for the benefit of experienced aircraft maintenance facilities capable of carrying out the procedures They must not be attempted by those lacking the necessary expertise Cargo Hook Removal Remove the MD Helicopters supplied Cargo Hook from the aircraft by disconnecting the electrical release cable from the belly mounted bulk head type connector Disconnect the manual release cable from the cyclic stick release lever assembly and attaching clamps Remove the single bolt used to attach the Cargo Hook to the airframe mounting bracket and separate the Cargo Hook from the aircraft Cargo Hook Installation Installation Instructions Verify that the part number of the cargo hook removed is a Breeze Eastern 2A20B P N 17149 4 If it is not do not attempt to use the new cargo hook unless compatibility is determined Inspect the airframe to cargo hook mounting bracket and its hardware to ensure that all components are in serviceable condition Install the P N 290 360 01 travel limit bumper to the Cargo Hook as illustrated in Figure 2 1 The Travel Limit Bumper helps protect the aircraft skin and the release cables from excessive hook movement Do not use the hook without the travel limit bumper in place Figure 2 1 Travel Limit
14. n 270 073 00 Visually check the electrical connectors for Same as daily check Electrical damage and security Release Cable Visually check the cable for damage and chafing Cycle the electrical release system to ensure proper cargo hook operation 290 360 01 Visually check for damage cracks and Same as daily check Travel Limit security of attachment Bumper 290 361 00 Visually check for damage cracks and Same as daily check Bumper Pad security of attachment Refer to Service Manual 122 001 00 for overhaul interval for the Cargo Hook inspect other kit items per Table 4 1 at the cargo hook interval Refer to MD Helicopters maintenance documentation that covers the original Cargo Hook installation for additional instructions Maintenance 4 1 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 Contact Technical Support by phone or e mail Techhelp OnboardSystems com Generate an RMA number at our website http Awww onboardsystems com rma php e After you have obtained the RMA number please be sure to 4 2 Package the component carefully to ensure safe transit Write the RMA number on the ou
15. nuary 17 1997 Date reissued Date amended 7 8 1997 6 3 1998 5 4 2001 1 13 2003 10 2 2007 5 14 2008 By Signature Acting Manager Seattle Aircraft Certification Office Y14008 a Any alteration of this certificate is punishable by a fine of not exceeding 1 000 or imprisonment not exceeding 3 years or both This certificate may be transferred in accordance with FAR 21 47 FAA Form 8110 2 10 68 Certification STC continued Tinite Sertes of America Tepartment of Cransportstion Federal Aviation Administration Supplemental Cope Certificate Continuation Sheet Numler SR00407SE Onboard Systems Reissued Amended 7 8 1997 6 3 1998 5 4 2001 1 13 2003 10 2 2007 5 14 2008 Limitations and Conditions continued A copy of this Certificate and the RFMS must be maintained as part of the permanent records of the modified rotorcraft 369H90072 501 505 507 amp 515 369D 369H90072 505 amp 517 369E _ ____ Same 369H90072 505 369H90072 505 amp 511 369H90072 519 amp 523 500N___ Same 369H90072 501 369H90072 501 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 ee 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 accordan
16. nuation Sheet Conditions This approval is only applicable to the type mode of aeronautical product specified therein Prior to incorporating this modification the installer shail establish that the interrelationship between this change and any other meodification s incorporated will not adversely affect the airworthiness of the modified product John Nehera Regional Manager Aircraft Certification For Minister of Transport isi Canad 5 3 Certification Continuation Sheet Number H97 30 Issue 3 NOTE THIS ADDENOUM SHALL REMAIN PART OF THE CERTIFICATE REFERRED TO THEREIN a TE o Required Equipment Modified rotorcraft must be operated in accordance with an FAA approved copy of Onboard Rotorcraft Flight Manual Supplement RFMS No 120 047 00 dated October 2 1998 or later FAA approved revisions Limitations Approval of this changes in type design applies to only those McDonnell Douglas model rotorcraft listed on the front page which were previously equipped with a FAA approved installation of McDonnell Douglas cargo hook Suspension systems and Breeze Eastern cargo hooks shown on the table below Cargo Hook Kit Helicopters Model Cargo Hook 369H90072 501 505 507 amp 515 369D 369H92105 501 369H90072 505 amp 517 369E Same 369H90072 505 369F i Same 369H90072 505 amp 511 369FF Same 369H90072 519 amp 523 SOON Same 369H90072 501 369HE Same 369H90072 501 369HM Same 369H90072 501 369HS
17. ork Insert the Rotorcraft Flight Manual Supplement document number 121 043 00 into the Rotorcraft Flight Manual 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 Installation Instructions 2 5 This page intentionally left blank Section 3 Operation Instructions Operating Procedures Operation Instructions Prior to each job perform the following 1 Ensure that the Cargo Hook has been properly installed and that the manual and electrical release cables do not limit the movement of the hook Be completely familiar with this manual particularly the Cargo Hook rigging section Be completely familiar with all MDHC cargo hook operating instructions Activate the electrical system and press the release button to ensure the cargo hook electrical release is operating correctly The mechanism should operate smoothly and the Cargo Hook must re latch after release If the hook does not re latch 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 Activate the release lever assembly located on the cyclic stick to test the cargo hook manual release mechanism The mechanism should ope
18. p works its way Off of the load beam 3 6 Operation Instructions Un Commanded Release Due to Cable or Rope Type Straps Cable or rope type straps must not be used directly on the cargo hook load beam Their braided eyes will work around the end of the load beam and fall free If cable or rope is used they should be first attached to a correctly sized primary ring Only the primary ring should be in contact with the cargo hook load beam See example below Figure 3 5 Un Commanded Release Due to Cable or Rope Type Straps Cable or rope type line flips over the Load Beam The flip over often Occurs with long line operations during landings and take offs Load Ring moves inward and bears against the keeper The Keeper rotates allowing the Ring to slip off Operation Instructions 3 7 This page intentionally left blank Section 4 Maintenance Refer to Cargo Hook Service Manual 122 001 00 for maintenance of the cargo hook Inspection The inspection of the Cargo Hook Kit shall be in accordance with the table 4 1 shown below Table 4 1 Inspection Part Number Daily Check At Overhaul Interval 528 010 04 Refer to Service Manual 122 001 00 Refer to Service Manual 122 001 00 Cargo Hook 268 005 01 Visually check the end fittings for damage Same as daily check Manual and security Release Cable Visually check the cable for damage Cycle the manual release system to ensure proper cargo hook operatio
19. rate smoothly and the Cargo Hook must relatch after release If the hook does not relatch do not use the unit until the difficulty is resolved See the Cargo Hook Service Manual 122 001 00 and the MD Helicopters service instructions that cover the original Cargo Hook installation for additional instructions 3 1 Cargo Hook Rigging 3 2 Extreme care must be exercised in rigging a load to the Cargo Hook If the load ring is too big it may work its way around the end of the load beam and be supported for a time on the keeper and then fall free If the load ring is too small it may jam itself against the load beam during an attempted release The following illustrations show recommended configurations and potential difficulties that must be avoided The examples shown are not intended to represent all problem possibilities It is the responsibility of the operator to assure the hook will function properly with the rigging Operation Instructions Cargo Hook Rigging continued Figure 3 1 Examples of Correct and Incorrect Cargo Hook Rigging Correct Rigging A 1 50 Primary Ring I D A Secondary Ring or Shackle Incorrect Rigging Multiple Rings Multiple Rings a ie on Primary Ring on Load Beam Operation Instructions 3 3 Un Commanded Release Due to Too Large of a Load Ring Load rings that are too large will cause an un commanded release The ring will flip over the end of the load beam and f
20. tion 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 returned to its closed position after release of the load by a spring in the internal mechanism In the closed position a latch engages the load beam and latches it in this position The load is attached to the load beam by passing the cargo sling ring into the throat of the load beam past a spring loaded keeper which secures the load To release the load the latch is disengaged from the load beam With the latch disengaged the weight of the load causes the load beam to swing to its open position and the cargo sling slides off the load beam A spring in the internal mechanism then drives the load beam back to its closed and latched position 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 lever A manual release cable attached to the lever operates the internal mechanism of the Cargo Hook to unlatch the load beam The
21. tside of the box or on the mailing label Include the RMA number and reason for the return on your purchase or work order Include your name address phone and fax number and email as applicable Return the components freight cartage insurance and customs prepaid to Onboard Systems 13915 NW 3rd Court Vancouver Washington 98685 USA Phone 360 546 3072 Maintenance Section 5 Certification STC Hnit Sterten of America Bepartnent of Transportation Feeral Aviation Administration Supplemental Type Certificate Number SR00407SE Onboard Systems 13915 NW 3rd Court Vancouver WA 98685 certifies that the change in the type dasiga for the following product with the limitations and conditions therefor as specified hereon meets the airworthiness reguivements of Part ofthe Civil Air Regulations Original Product Type Certificate Number H3WE Make McDonnell Douglas Helicopters Company Models 369D 369E 369F 369FF 369HE 369HM 369HS and 500N Desorption of the Type Design Change Fabrication of Onboard Systems Model 200 187 00 cargo hook kit in accordance with FAA Approved Onboard Systems Master Drawing List No 155 030 00 Revision 13 dated May 6 2008 or later FAA approved revision and installation of this replacement cargo hook in accordance with FAA approved Onboard Systems Owner s Manual No 120 047 00 Revision 12 dated April 29 2008 or later FAA approved revisions Inspect cargo hook in accordance with
22. ued K European Aviation Safety Agency X 5 FAA letter 130S GA 08 27 dated 3 March 2008 6 FAA letter 130S GA 08 82 dated 14 May 2008 Limitations and Conditions 1 This cargo hook is not approved for human external load 2 Approval of this change in type design applies to only those McDonnell Douglas model rotorcraft listed above which were previously equipped with an approved McDonnell Douglas cargo hook 369H92105 0501 and cargo hook suspension systems kits shown in the following table 369H90072 501 505 507 amp 369D 515 69HS ame 3 Prior to installation of this modification the installer must determine that the interrelationship between this modification and any other previously installed modification will introduce no adverse effect upon the airworthiness of the product This certificate shall remain valid unless otherwise surrendered or revoked For the European Aviation Safety Agency Date of Issue 08 07 2008 Xe Massimo MAZZOLETTI Certification Manager Rotorcraft Balloons Airships STC EASA IM R S 01396 Onboard Systems International 5 6 Certification
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