1、DETAIL SPECIFICATIONHOOK, HELICOPTER EXTERNAL CARGO, 20,000 POUND CAPACITY, TYPE CThis specification is approved for use by all Departments and Agenci es of the Department ofDefense.1. SCOPE1.1 Scope . This specification establishes the requirements for a 20,000 pound capacityhelicopter external car
2、go hook, type C.2. APPLICABLE DOCUMENTS2.1 General . The documents listed in this section are specified in sections 3 and 4 of thisspecification. This section does not include documents cited in other sections of this specificationor recommended for additional information or as examples. While every
3、 effort has been made toensure the completeness of this list, document users are cautioned that they must meet allspecified requirements documents cited in sections 3 and 4 of this specification, whether or notthey are listed.AMSC N/A FSC 1670DISTRIBUTION STATEMENT A . Approved for public release; d
4、istribution is unlimited.INCH-POUNDMIL-DTL-81014B2 February 2001SUPERSEDINGMIL-H-81014A(WEP)19 March 1965Beneficial comments (recommendations, additions, deletions) and any pertinent data which maybe of use in improving this document should be addressed to: Commander, Naval Air WarfareCenter Aircraf
5、t Division, Code 414100B120-3, Highway 547, Lakehurst, NJ 08733-5100, byusing the Standardization Document Improvement Proposal (DD Form 1426) appearing at theend of this document or by letter.INACTIVE FOR NEW DESIGN AFTER 28 AUGUST 1996Provided by IHSNot for ResaleNo reproduction or networking perm
6、itted without license from IHS-,-,-MIL-DTL-81014B22.2 Government documents .2.2.1 Specifications and standards . The following specifications and standards form a partof this document to the extent specified herein. Unless otherwise specified, the issues of thesedocuments are those listed in the iss
7、ue of the Department of Defense Index of Specifications andStandards (DoDISS) and supplement thereto, cited in the solicitation (see 6.2).SPECIFICATIONSFEDERALQQ-C-320 - Chromium Plating (Electrodeposited)QQ-P-416 - Plating, Cadmium (Electrodeposited)DEPARTMENT OF DEFENSEMIL-S-4040 - Solenoid, Elect
8、rical, Generals Specification for (Inactive forNew Design)MIL-W-6873 - Welding; Flash, Carbon and Alloys Steel (Inactive forNew Design)MIL-P-6906 - Plates, Identification, Aircraft (Inactive for New Design)MIL-S-7742 - Screw Threads, Sta ndard, Optimum Selected Series:General Specification for (Inac
9、tive for New Design)MIL-L-7961 - Lights, Indicators, Press to TestMIL-A-8625 - Anodic Coatings for Aluminum and Aluminum AlloysAFGS-87242 - Flight Control System General Spec ification forSTANDARDSDEPARTMENT OF DEFENSEMIL-STD-100 - Engineering DrawingsMIL-STD-704 - Aircraft Electric Power Characteri
10、sticsMIL-STD-810 - Environmental Engineering Considerations and LaboratoryTestsMIL-STD-889 - Dissimil ar MetalsMS3102 - Connector, Receptacle, Electric, Box Mounting, SolderContacts, AN Type (Inactive for New Design)MS3106 - Connector, Plug, Electric, Straight, Solder Contacts,AN Type (Inactive for
11、New Design)Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-81014B3(Unless otherwise indi cated, copies of the above specifications and standards are availablefrom the Standardization Document Order Desk, 700 Robbins Avenue, Building 4D, Phila
12、delphia,PA 19111-5094.)2.3 Non-Government publications . The following documents form a part of this documentto the extent specified herein. Unless otherwise specified, the issues of the documents which areDoD adopted are those listed in the issue of the DoDISS cited in the solicitation. Unlessother
13、wise specified, the issues of documents not listed in the DoDISS are the issues of thedocuments cited in the solicitation (see 6.2).AMERICAN SOCIETY FOR TESTING AND MATERIALS (ASTM)ASTM-B117 - Salt Spray (Fog) Apparatus Operating, Standard Practice for.(DoD adopted)(Application for cop ies should be
14、 addressed to the American Society for Testing andMaterials, 100 Barr Harbor Drive, West Conshohocken, PA 19428-2959.)SOCIETY OF AUTOMOTIVE ENGINEERS, INC. (SAE)SAE-AMS-STD-2219 - Fusion Welding for Aerospace Applications.(DoD adopted)SAE-AMS-W-6858 - Welding, Resistance: Spot and Seam. (DoD adopted
15、)(Application for copies should be addressed to the Society of Automotive Engineers, Inc.,400 Commonwealth Drive, Warrendale, PA 15096-0001.)2.4 Order of precedence . In the event of a conflict between the text of this document andthe references cited herein, the text of this document takes preceden
16、ce. Nothing in this document,however, supersedes applicable laws and regulations unless a specific exemption has beenobtained.3. REQUIREMENTS3.1 First article . When specified (see 6.2), a sample shall be subjected to first articleinspection in accordance with 4.2.3.2 Materials . Materials used in t
17、he manufacture of the cargo hook shall meet therequirements of this specification.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-81014B43.2.1 Metals . All metals used in the construction of the cargo hook shall be of the corrosionresistant t
18、ype or shall be treated to resist corrosion in accordance with MIL-A-8625,QQ-C-320 or QQ-P-416. Dissimilar metals shall not be used in accordance with MIL-STD-889.3.3 Design and construction . The hook shall be automatic (see 6.3.1) or semiautomatic(see 6.3.3) cargo pickup.3.4 Screw threads . All sc
19、rew threads shall be in accordance with MIL -S -7742.3.5 Threaded parts . All threaded parts shall use aircraft locking methods. Lock washersshall not be used for locking.3.6 Welding . Welding, where used, shall be in accordance with SAE-AMS-6858 andSAE-AMS-STD-2219.3.7 Interchangeability . All part
20、s having the same manufacturers part number shall bedirectly and completely interchangeable with each other with respect to installation andperformance. Change in manufacturers part numbers shall be in accordance with MIL-STD-100.3.8 Operating condition . The cargo hook shall operate under the follo
21、wing environmentalconditions:3.8.1 Altitude . The hook shall operate at any altitude between sea level to 20,000 feet(see 4.5.2.14).3.8.2 Temperature . The hook shall operate at any ambient temperature between 65 F to+160 F (see 4.5.2.10 and 4.5.2.11).3.8.3 Vibration . The hook shall withstand the h
22、elicopter vibrational environment(see 4.5.2.9).3.8.4 Sand . The hook shall withstand the blowing sand environment (see 4.5.2.13).3.8.5 Salt spray . The hook shall withstand the salt spray environment (see 4.5.2.12).3.8.6 Shock . The hook shall withstand the functional shock environment (see 4.5.2.17
23、).3.8.7 Water immersion . The hook shall withstand salt water immersion without permanentdamage or operational impairment (see 4.5.2.15).3.8.8 Fungus . The hook shall withstand the fungus environment (see 4.5.2.16).Provided by IHSNot for ResaleNo reproduction or networking permitted without license
24、from IHS-,-,-MIL-DTL-81014B53.9 Detailed requirements .3.9.1 General . The hook shall be of the open -throat type. The load sling adapter ring orother pickup device may be introduced into the load bearing portion of the hook automatically orin any event it shall not require personal contact with the
25、 hook. There shall be no protuberancesor other obstacles to prevent or hinder engagement with the load sling adapter ring or otherpickup device. The open -throat shall face forward when installed on an aircraft.3.9.1.1 Throat . The throat (see 6.3.5) configuration shall facilitate engagement with th
26、e loadsling adapter or other pickup device. The throat shall accept any of the following sling adapterrings or pickup devices or their equivalents:a. Nylon strap ring 2.75-inch wide and 0.875-inch thick.b. A steel ring made of 1.5-inch diameter stock.c. Two 1.5-inch diamet er ropes.3.9.1.2 Housing .
27、 The hook housing shall be constructed to support and enclose thecomponents and to protect them from environmental conditions. Components subject to waterdamage shall be enclosed within a completely waterproof housing or other protective device.3.9.1.3 Load beam . The load beam shall support all loa
28、ds under all operational conditions.The load beam shall be mounted in the hook housing by a pivot near its aft end such that uponrelease the front end will swing downward and aft. The configuration of the load beam shall assistthe load sling adapter ring to position itself in the hook while presenti
29、ng minimum resistance todisengagement on release.3.9.1.4 Keeper . A keeper shall be used in the hook throat to positively retain the load slingadapter ring in the desired position in the hook under all operational flight conditions until release.The keeper shall permit engagement of pickup devices c
30、onsisting of more than one part or ring,each engaged separately without personal contact with any part of the hook.3.9.1.5 Attachment . The hook shall have two attachment holes on its upper portion; onenear the forward end and one near the aft end as shown on figure 1, such that the point at whichth
31、e cargo load is applied is midway between them. The suspension holes shall attach to asemi -rigid mounting structure (see 6.3.4) beneath the aircraft and shall permit removal of the hookwhen desired.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL
32、-DTL-81014B6NOTES: 1. All dimensions marked with an asterisk (*) must be held.2. All other dimensions define maximum envelope size except as noted.3. All dimensions are in inches.FIGURE 1. Envelope dimensions .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from
33、IHS-,-,-MIL-DTL-81014B73.9.1.6 Release mechanism . The internal release mechanism in the hook shall providepositive retention of the load beam in its load carrying position until the release mechanism isactuated by one of the modes of release specified in 3.9.6.1. Upon actuation, the releasemechanis
34、m shall react so as to remove all restraint from the load beam. The load beam shall thenopen and completely release the load. Components of the release mechanism which rely on awiping or rolling action between members shall be self -cleaning to prevent contamination andfouling.3.9.2 Weight . The max
35、imum weight of the hook shall be not greater than 40 pounds.3.9.3 Envelope . The overall hook dimensions shall be not greater than those shown onfigure 1.3.9.4 Capacity . The hook shall have a 20,000-pound design 1oad rating. The hook shalloperate under loads specified herein, at attitudes from hori
36、zontal to a 30-degree nose pitch -up.Application of a torsional moment to the hook while under rated load, as specified herein, shallnot damage the hook.3.9.5 Design load factors . The hook shall withstand a design limit load (static) of 60,000pounds with no yield or damage to working parts, and a d
37、esign ultimate load (static) of 90,000pounds.3.9.6 Operating features.3.9.6.1 Hook release . The hook shall release the cargo by the following methods.Actuation of any of the releases for a continuous period of 30 seconds shall not damage the hookor its components.3.9.6.1.1 Normal release . The norm
38、al release shall be actuated when the required aircraftvoltage is applied. The hook release device shall release all loads between seven to 6,000 poundsin not greater than 0.5-second from initiation to release. The device may be an electrical solenoidin accordance with MIL-S-4040 or an electrical ac
39、tuator in accordance with AFGS-87262.3.9.6.1.2 Automatic touchdown release . Automatic touchdown release shall be actuatedwhen the required aircraft voltage is applied and the load is reduced to 150 25 pounds byground contact. The hook shall release all loads greater than seven pounds. The hook shal
40、lremain in the released condition until the circuit is deactivated. The normal release mode shall notbe deactivated when the automatic touchdown mode is used.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-81014B83.9.6.1.3 Manual release . Th
41、e manual release shall be actuated when a link or cable from thehelicopter to the hook is pulled. The release shall release all loads from seven pounds to the60,000-pound design limit. The hook need not be operable after release of loads between therated capacity and the design limit load but shall
42、return to full operating condition with only minorrepairs or replacement of minor parts. The hook and its components shall incur no damage fromreleases of loads up to rated capacity in this mode. The stroke through which the actuatinglinkage must travel to execute a complete release of the hook shal
43、l be not less than 0.5-inch norgreater than 1.25 inches including any pretravel. The amount of pretravel shall be not greaterthan the actuating travel. The point at which the actuating force is applied to the mechanism shallbe so located that the mechanism shall release when a connection is made bet
44、ween it and avertically arising point located four inches above the mounting holes, two inches to starboard ofthe fore -and -aft hook centerline, and not more than two inches forward or a ft of the midpointbetween the mounting holes. The configuration of the manual release attachment point shallacco
45、mmodate a standard AN or MS terminal at the end of a 0.0625-inch diameter cable. Theforce required to actuate this release under various load conditions shall be not greater than thefollowing:LOAD FORCENone 15 lbs20,000 lbs 50 lbs60,000 lbs 80 lbsThe release mechanism shall provide a force of 9 1 po
46、unds at the point of attachment of theactuating linkage in a direction which will retain the aircraft linkage in its de -actuated position.This force is included in the release forces specified above.3.9.6.1.4 Ground release . The ground release shall actuate when a link or cable from groundpersonne
47、l to the hook is pulled. The force required to actuate the release mechanism of the hookby this method shall be not greater than 15 pounds under no -load condition. The releasemechanism shall not be actuated by falling or stringing objects, such as cables or heavy weights.3.9. 6.2 Relatch . After re
48、lease of any load up to rated capacity, the hook load beam shallautomatically relatch into its load carrying condition within five seconds after the release controlshave returned to the non-release position. In the event the load beam does not relatch afterrelease of a load, reactuation of either th
49、e normal or manual release shall cause the load beam torelatch.3.9.6.3 Indication of unlatched load beam . There shall be a means on the hook to indicatewhen the load beam is in an unlatched condition. The device shall complete the circuit when thiscondition occurs, illuminating an aircraft light in accordance with MIL-L-7961.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,
