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1、NOTICE OF INACTIVATION FOR NEW DESIGN INCH-POUND MIL-S-85510(AS) NOTICE 1 18 September 1996 MILITARY SPECIFICATION SEATS, HELICOPTER CABIN, CRASHWORTHY, GENERAL SPECIFICATION FOR This notice should be filed in front of MIL-S-85510(AS), dated 19 November 1981. MIL-S-85510(AS) is inactive for new desi
2、gn and is no longer used, except for replacement purposes. Preparing activity: Navy - AS AMSC N/AFSC 1680 DISTRIBUTION STATEMENT A. Approved for public release; distribution is unlimited. MIL-S-85510(AS) 19 November 1981 1. 1.1 Scope. This specification established the design requirements for two ty
3、pes, use by 1.2 SCOPE three classes MILITARY SPECIFICATION SEATS, HELICOPTER CABIN, CRASHWORTHY, GENERAL SPECIFICATION FOR This specification is approved for use by the Naval Air Systems Command, De- partment of the Navy, and is available for use by all Departments and Agencies of the Department of
4、Defense. and four sizes of lightweight,folding, crashworthy seats for troops/passengers in helicopters. Classification.Seats shall be of the following types, classes and sizes, as specified (see 6.2.1): Type I -Passenger Type II -Troop Class A -Forward-facing Class B -Aft-facing class c - Side-facin
5、g Size 1 -One-man seat Size 2 -Two-man seat Size 3 - Three-man seat Size 4 -Four-man seat 2. APPLICABLE DOCUMENTS 2.1 Government documents. 2.1.1 Specifications, standards, and handbooks. Unless otherwise specified, the following specifications, standards, and handbooks of the issue listed in that i
6、ssue of the Department of Defense Index of Specifications and Standards (DoDISS) specified in the solicitation form a part of this specification to the extent specified herein. Beneficial comments (recommendations, additions, deletions) and any pertinent data which may be of use in improving this do
7、cument should be addressed to: Engineering Specifications and Standards Department (Code 93), Naval Air Engineering Center, Lakehurst, NJ 08733, by using the self-addressed Standardization Document Improve- ment Proposal (DD Form 1426) appearing at the end of this document or by letter. FSC 1680 MIL
8、-S-8551O(AS) SPECIFICATIONS F E D E R A L V-T-295 QQ-C-320 QQ-P-416 QQ-Z-325 TT-E-489 TT-P-1757 PPP-B-601 PPP-B-621 PPP-B-636 MILITARY MIL-P-116 DoD-D-1000 MIL-M-3171 MIL-C-6021 MIL-H-6088 MIL-W-6873 MIL-H-6875 MIL-R-8236 MIL-I-8500 MIL-W-8604 MIL-A-8625 MIL-W-25361 MIL-W-45205 MIL-C-45662 Thread, N
9、ylon. Chromium Plating Plating, Cadmium (Electrodeposit). (Electrodeposited). Zinc Coating, Electrodeposited, Requirements for. Enamel, Alkyd, Gloss (for Exterior and Interior Surfaces). Primer Coating, Zinc Chromate, Low Moisture Sensitivity. Boxes, Wood, Cleated-Plywood, Box, Wood, Nailed and Lock
10、-Corner. Boxes,Shipping, Fiberboard. Preservation-Packaging, Methods of. Drawings, Engineering and Associated Lists. Magnesium Alloy, Processes for Pretreatment and Prevention of Corrosion on. Casting, Classification and Inspection of. Heat Treatment of Aluminum Alloys. Welding, Flash, Carbon and Al
11、loy Steel. Heat Treatment of Steels (Aircraft Practice), Process for. Reel, Shoulder Harness, Inertia Lock. Interchangeability and Replaceability of Component Parts for Aircraft and Missiles. Welding of Aluminum Alloys: Process for. Anodic Coatings, for Aluminum and Aluminum Alloys. Webbing, Textile
12、, Polyester, Low Elongation. Welding, Gas Metal-Arc and Gas Tungsten-Arc, Aluminum Alloys, Readily Weldable for Structures, Excluding Armor. Calibration System Requirement. (See supplement 1 for applicable specification sheets.) STANDARDS FEDERAL FED-STD-751 - MILITARY MIL-STD-22 - MIL-STD-105 - MIL
13、-STD-129 - MIL-STD-130 - Stitches, Seams and Stitchings. Welded Joint Design. Sampling Procedures and Tables for Inspection by Attributes. Marking for Shipment and Storage. Identification Marking of Military Property. 2 MIL-S-8551O(AS) MIL-STD-143 MIL-STD-785 MIL-STD-810 MIL-STD-831 MIL-STD-882 MIL-
14、STD-889 MIL-STD-1186 MIL-STD-1261 Standards and Specifications, Order of Precedence for the Selection of. Reliability Program for Systems and Equipment Development and Production. Environmental Test Methods. Test Reports, Preparation of. System Safety Program Requirements. Dissimilar Metals. Cushion
15、ing, Anchoring, Bracing, Blocking, and Waterproofing, with Appropriate Test Methods. Welding Procedures for Constructional Steels. HANDBOOKS MILITARY MIL-HDBK-5 -Metallic Materials and Elements for Aerospace Vehicle Structures. 2.1.2 Other Government documents, drawings, and publications The followi
16、ng other Government documents form a part of this specification to the extent specified herein. CODE OF FEDERAL REGULATIONS CFR Title 14, Chapter 1, - Compartment Interiors. Part 25, Section 853 CFR Title 49, Chapter 5, - Anthropomorphic Test Dummy. Part 572 (Application for copies should be address
17、ed to the Superintendent of Documents, Government Printing Office, Washington, DC 20402.) APPLIED TECHNOLOGY LABORATORY of the US ARMY RESEARCH and TECHNOLOGY LABORATORIES (AVRADCOM) TR 79-22, Volumes A through E - Crash Survival (Application for copies should be addressed to the Laboratory, Fort Eu
18、stis, VA 23604.) Design Guide. Commander, Applied Technology US ARMY NATICK RESEARCH TR 72-51 -The Body (Application for copies AND DEVELOPMENT LABORATORIES Size of Soldiers. should be addressed to the Commander, US Army Natick Research and Development Laboratories, Natick, MA 01760.) (Copies of spe
19、cifications, standards, handbooks, drawings, and publications required by manufacturers in connection with specific acquisition functions should be obtained from the contracting activity or as directed by the contracting officer. 3 MIL-S-8551O(AS) 2.2 Other publications. The following document forms
20、 a part of this specifi- cation to the extent specified herein. The issues of the documents which ar in- dicated as DoD adopted shall be the issue listed in the current DoDISS and the sup- plement thereto, if applicable. SOCIETY OF AUTOMOTIVE ENGINEERS, INC. (SAE) (Aerospace Material Specifications)
21、 1979 SAE Handbook, Part 2 -Recommended Practice. Section J211b -Instrumentation for Impact Test. (Application for copies should be addressed to the Society of Automotive Engineers, Inc.,400 Commonwealth Drive, Warrendale PA 15096.) (Industry association specifications and standards are generally av
22、ailable for reference from libraries.They are also distributed among technical groups and using Federal agencies.) 2.3 Order of precedence. In the event of a conflict between the text of this specification and the references cited herein, the text of this specification shall take precedence. 3.REQUI
23、REMENTS 3.1 Specification sheets.The individual item requirements shall be as specified herein and in accordance with the applicable specification sheets. In the event of any conflict between requirements of this specification and the specification sheet, the latter shall govern. 3.2 First article.W
24、hen specified, a sample shall be sujected to first article inspection (see 4.4 and 6.3). 3.3 Design characteristics. In general, the “Crash Survival Design Guide“. TR-79- 22, volumes A through E, shall be used as a design guide for the seat systems furnished under this specification.The seat shall a
25、ccommodate the specified type of occupant in the quantities identified for each respective size and orientation (see 1.2).The size I seat is the preferred configuration in order to avoid situations where the energy absorbers of a multi-unit seat are rendered ineffective due to less than full occupan
26、cy.To the maximum extent practical, seat classes (see 1.2) shall be interchangeable to enhance standardization. Seating should be aft-facing whenever operational requirements permit. Forward-facing is the next preference. Seating shall not be side-facing unless absolutely necessary for operational c
27、onsiderations. It is desirable that all seats face in the same direction so that the seat backs protect occupants from loose equipment which can become flying projectiles during crash impact.Fabric, netting or a headrest shall be provided for occupant head/ neck whiplash protection.The seat system s
28、hall incorporate an anti-rebound device (snubber unit) designed to minimize any seat/occupant rebound which may result from the elasticity within the seat system and the resulting lack of structural rigidity due to the stroking process.In the event of a hard landing or rough handling of the seat sys
29、tem, some visual indication of energy absorber stroking, which may have resulted, shall be provided to alert maintenance personnel. 4 MIL-S-8551O(AS) 3.3.1 Seating surface. The seat bottom and back shall be designed for comfort and durability. Seat bottoms made of fabric shall be provided with means
30、 of tighten- ing to compensate for sagging in use. Sufficient clearance between fabric backs and bottoms shall be provided to preclude body contact with structure when subjected to the specified loads (see 3.6).Fabric tensile strength characteristics shall be sufficient to preclude tearing or comple
31、te structural failure when dynamically loaded by the occupant inertial forces resulting from the dynamic test requirements of figure 3.To accommodate back and butt packs that troops may be wearing, the backs of type II seats shall be convertible without tools to provide the recess shown in figure 1.
32、Maximum time to convert either way shall not exceed 10 seconds, and both back supports shall meet the strength requirements. 3.3.2 Crash resistance.The seat shall prevent the 5th through 95th-percentile occupants (see 6.4.1) from experiencing vertical decelerations in excess of human tolerance (see
33、figure 2) during crash pulses of the severity shown in figure 3 and not experience structural failure.Energy shall be absorbed in the vertical axis by load-limiting devices.The energy-absorption stroke shall be the maximum attainable in the space between the seat bottom and the aircraft floor.In any
34、 case, not less than 14 inches of vertical stroking distance shall be provided when measured at the occupants center of gravity.The seat and restraint shall minimize occupant subma- rining (see 6.4.5) and dynamic overshoot (see 6.4.6). 3.3.3 Seat attachment.Acceptable means of attaching seats to the
35、 cabin interior are listed below in order of desirability: a. b. c. d. e. Suspended from the ceiling with attenuators, and wall stabilized. Suspended from the ceiling with attenuators, and floor stabilized. Ceiling and floor mounted (vertical energy attenuators above and below seat). Wall mounted wi
36、th attenuators. Floor mounted with attenuators. 3.3.3.1 Attachment distortion.Seat attachments shall be capable of accommo- dating crash induced cabin distortion consisting of a four (4) inch vertical dis- placement and a 10misalignment of any attachment as shown in figure 15 for the floor warpage c
37、ondition.Figure 16 defines the requirements for the bulkhead at- tachment condition. 3.3.4 Seat folding and stowing. Seats shall be so designed that they may be quickly removed or folded and secured. Tools shall not be required .3.3.4.1 Seat disconnect time. The time for sidconnecting each size 1 se
38、at (one- man seat) by one man shall not exceed 20 seconds. The time for disconnecting multi- unit seats by one man shall not exceed 20 seconds multiplied by the seat size number. 5 MIL-S-85510(AS) 3.3.4.2 Folding and stowage.Each seat shall be capable of being folded, stowed and secured or unstowed
39、quickly and easily by one man in a period not to exceed 20 seconds multiplied by the seat size number. 3.3.5 Obstructions.Seat suspension or mounting shall not interfere with rapid ingress or egress. Braces, legs, cables, straps and other structures shall be de- signed to prevent snagging or trippin
40、g. Loops shall not be formed when the re- straint system is in the unbuckled position. 3.3.6 Occupant restraint. The seats shall have an integral restraint system with lap belt and shoulder harness for each seating position. The restraint shall be comfortable, light in weight, and easy for the occup
41、ant to put on and remove. Reduction in support of the occupant shall not occur due to stroking of the energy absorbers or deformation of the seat. 3.3.6.1 Lap belt.The lap belt anchorage geometry shall be as shown on figure 4.The lap belt anchor fittings shall be attached to the stroking portion of
42、the seat and shall be capable of displacing plus or minus 30 degrees vertically. These fittings shall also be capable of withstanding lateral loads when the webbing is pulling at an angle of plus or minus 60 degrees to the normal plane of the fitting. Lap belt retractors may be used in lieu of adjus
43、tors. In any event, lap belts shall be prevented from falling behind or below the seat. Flexible stand-ups shall be provided at the lap belt anchor points to project the lap belt upward and for- ward 5 inches for each reach.Retractors or adjustors shall not be located over hard points of the occupan
44、ts skeletal structure.The force required to adjust the webbing length shall not exceed 15 pounds and it shall be possible for the seated occupant to easily adjust with either hand.If retractors are used, they shall not pull with more than 15 pounds force, and shall ratchet in increments not to excee
45、d 0.5 inch. 3.3.6.2 Shoulder straps.Seats shall be provided with shoulder straps. Either the configuration shown in figure 5 or that shown in figure 6 shall be used. The figure 5 configuration is preferred.Shoulder harness anchorage geometry shall conform to figure 7.The anchorage or guide at the to
46、p of the seat shall not permit more than 0.5 inch lateral movement of the strap at this point. Distance between the inner edges of the shoulder straps at the seat back shall be within 3 to 5 inches.Flexible guides shall be provided on the seat back as shown on figure 7 to project the shoulder strap
47、fittings up and forward of the seat back for easy reach. 3.3.6.3 Inertia reel.Unless otherwise specified, provision of inertia reel or reels shall be optional.Shoulder strap inertia reel or reels, when specified by mission requirements (such as, a gunners seat installation), shall pull with not more
48、 than 3 pounds force and fully retract the shoulder strap or straps to shoulder height in the guides described above.The reel shall be of a type which remains locked after it locks up initially, and must be manually reset. It is preferred that the reel be designed to lock in an identical manner to t
49、he requirements stated in MIL-R-8236, except that the manual control handle shall not be required. After locking,relocking of the reel shall be accomplished by turning or pushing a simple reset device.The reel shall be located close to the shoulder strap guide point at the back of the seat to minimize strap elongation. 6 MIL-S-85510(AS) 3.3.6.4 Restraint buckle.The restraint harness buckle shall be of the quick- release type and shall require intentional motion by the occupant to activate it. The buckle shall be capable of being operated with a gloved hand, as well as with one finger of eith