AIR FORCE MIL-S-27174 B-1985 SEAT TROOP VARIABLE SEATING WIDTH《可变座椅宽度的部队座位》.pdf

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1、MIL-S-271748 16 7777706 017LI286 7 Beneficial comments (recommendations , additions, deletions) and any pertinent 1 data which may be of use in improving this document should be addressed to: the Engineering Division, San Antonio Air Logistics Center, Kelly AFB, Texas 78241 by using the self-address

2、ed Standardization Document Improvement V-F-106 V-T-295 TT-L-20 MIL-S-27174B(USAF) SUPERSEDING MIL-S-27174A(USAF) 7 February 1974 .- MILITARY SPECIFICATION SEAT, TROOP, VARIABLE SEATING WIDTH This specification is approved for use by the Department of the Air Force, and is available for use by all D

3、epart- ments, and Agencies of the Department of Defense. 1. SCOPE 1.1 Scope. This specification establishes the requirements for two types 1.2 Classification. of wall-style, lightweight, folding, variable seating width troop seats. Troop seats shall be of the following types as specified : Type I -

4、Twenty-Inch Unit Type II - Forty-Inch Unit 2. APPLICABLE DOCUMENTS 2.1 Government documents. * 2.1.1 Specifications and standards. Unless otherwise specified (see 6.2), the following specifications and standards of the issue listed in that issue of the Department of Defense Index of Specifications a

5、nd Standards (DoDISS) specified in the solicitation, form a part of this specification to the extent specified herein. SPECIFICATIONS FEDERAL Fasteners, Slide, Interlocking Thread, Nylon Lacquer Camouflage ._- THIS DOCUMENT CONTAINS /7 PAGES / Licensed by Information Handling ServicesflIL-S-Z7L7YB L

6、b m 9999906 034Y287 O U MIL-S-27174B(USAF) STANDARDS FEDERAL FED-STD-595 Colors FED-STD-751 Stitches, Seams, And Stitching MIL IT ARY MIL-STD-129 Marking For Shipment And Storage MIL-STD-130 Identification Marking of U.S. Military Property MIL-STD-143 Standards And Specifications, Order Of NIL-STD-8

7、31 Test Reports, Preparation of MIL-STD-889 Dissimilar Metals MiL-STD-118 6 Cushioning, Anchoring, Bracing, Blocking, And Waterproofing; With Appropriate Test Methods . MS27983 Fastener, Snap, Style 4 AIR FORCE -NAVY AERONAUTICAL AN7516 Fitting And Cargo Airplane Tie Down (Copies of specifications a

8、nd standards required by manufacturers in connection with specific acquisition functions should be obtained from the contracting activity or as directed by the contracting officer:.) 2.1.2 Other publications. The following document(s) form a part of this specification to the extent specified herein.

9、 which are indicated as DoD adopted shall be the issue listed in the current: DoDISS and the supplement thereto, if applicable. The issues of the documents AMERICAN SOCIETY FOR TESTING AND MATERIALS (ASTM) * ASTM B-633-78 Zinc On Iron And Steel, Electro-deposited Coating 31 Mar 78 Packaging Commerci

10、al 21 Jan 82 * ASTM D-3951-82 (Application for copies of ASTM publications should be addressed to the American Society for Testing and Materials, 1916 Race Street, Philadelphia, Pennsylvania 19103. ) 2.1.3 Order of precedence. In the event of a conflict between the text of this specification and the

11、 references cited herein, the text of this specification shall take precedence. 3 REQUIREMENTS 3.1 First Article. This specif ication makes provisions for first article testing, Licensed by Information Handling Services3.2 Components. The complete seat assembly shall consist of a metal tubular frame

12、, a fabric bottom, and a back fabricated from webbing. 3.3 Selection of specifications and standards. Specifications and standards or necessary commodities and services not specified herein sha selected according to MIL-STD-143 except as provided in 3.3.1 and 3.3.2. Lbe . 3.3.1 Commercial parts, Com

13、mercial parts having suitable properties may be used where, on the date of invitation for bids there are no suitable standard parts. In any case, commercial utility parts, like screws, bolts, nuts, cotter pins, having suitable properties may be used provided: a. alteration). They can be replaced by

14、the standard parts (MS or-AN without b. The corresponding standard part numbers are referenced in the parts list and, if practical, on the contractors drawings. 3.3.2 Standard parts. With the exception in 3.3.1, MS and AN standard They shall be identified parts shall be used where they suit the purp

15、ose. on the drawings by their part numbers. 3.4 Materials. 3.4.1 Fungus proof materials. Materials that are nutrients for fungi shall not be used where it is practical to avoid them. Where used and not hermetically sealed, they shall be treated with a fungicidal agent acceptable to the procuring act

16、ivity. sealed inclosure, fungicidal treatment will not be necessary. However, if they will be used in a hermetically 3.4.2 Metals. Metals shall be of the corrosion-resistant type or suitably treated to resist corrosion due to fuels, salt spray, or atmospheric conditions likely to be met in storage o

17、r normal service, 3.4.2.1 Dissimilar metals. Unless suitably protected against electrolytic corrosion, dissimilar metals shall not be used in intimate contact with each other. Dissimilar metals are defined in MIL-STD-889. 3.5 Design. The seat shall be designed for installation on the right or left s

18、ide of the airplane in such a manner that the occupants face inboard and, also, be capable of installation in two rows, back to back in the center of the airplane so that the occupants faee outboard. shall provide a variable seat width of 20 to 24 inches per occupant by adjustment of the seat belt a

19、ttachment points. The seat shall provide maximum comfort and ease of releasing for stowing. The installed areas 3.5.1 Folding and stowing. All seats shall be so designed that the leg or legs and seat bottoms may be quickly folded against and lashed to the seat back with the leg or legs in between th

20、e seat bottom and seat back. 3.5.1.1 Folding and unfolding time. The seats shall be designed to permit folding and lashing or unlashing and unfolding quickly and easily without the use of tools or special equipment by one man, in a period not to exceed 10 seconds, Licensed by Information Handling Se

21、rvicesMIL- S-2 71 74B (USAF) 3.5.1.2 Rolled stowage, AL1 seats shall be designed for rolled stowage. They shall be designed in such a manner that the legs and spreaders may be folded and the seat back may be quickly detached from the upper seat support tube which is considered a part of and is attac

22、hed to the airplane to permit the seat to roll up against the sides of the fuselage. shall be provided and attached CO the type I and type II seats, respectively, for the purpose of lashing the seats in the rolled stowed position. One and two straps 3.5.1.3 Stowing and unstwiag time. The seats shall

23、 also be stowable and unstowable quickly and easily by one man, without the use of tools or special equipment in a period not to exceed 2 minutes. be positioned to provide for the tightest possible lashing. Stowage straps shall 3.5.1.4 Size of package. The seat package of the seats shall be held to

24、a maximum size of 6 inches in diameter when in the rolled stowed pos it ion . 3.5.2 Leg supports. The legs of the seats shall be located as shown in Figures 1 and 2. connect with the stud of the tie-down fitting shown in MIL-F-8905 and AN7516. The tie-down fitting shall be installed in the airplane

25、flush with the floor surface and located as shown in Figures 1 and 2. The leg fittings shall be of the quick release type and the release actuating lever on operating control shall be located at the top of each leg in such a manner that they will be easily accessible to the seat occupants without be

26、nding over. attachment fitting shall be so designed that the fittings will automatically open and snap on the floor tie-down stud when a downward force is applied to the seat leg. The seat leg shall be designed to permit attachment to the floor tie-down stud for any position of the floor stud within

27、 a 1-1/2-inch diameter circle, the center of the circle being the true position in the standard 20-inch floor grid pattern. The base of the legs shall contain fittings that will The seat leg 3.5.2.1 Brace for leg supports. The type I seat shall be designed to support the required side load without d

28、iagonal bracing. shall have rigid braces, if any, that are adjustable, and may be connected or disconnected quickly and easily without tools or special equipment. Braces that are not positively locked at both ends shall be subject to approval by the procuring agency. The type II seat 3.5.3 Seat bott

29、om and back. The seat bottom and back shall be fabricated to provide maximum comf Ort and durability, 3.5.3.1 Seat bottom construction. The seat bottom shall be made of one piece with provisions for attachment to the rear support tube which is removable for the installation of the seat, Minimum size

30、 cutouts in the seat bottoms shall be provided for attachment of seat legs and spreaders as required. and number to prevent equipment that is being carried by paratroopers from accidently snagging the seat. All cutouts shall be bound with 1-inch wide tape conforming to MIL-W-4088, type II. Snap fast

31、eners conforming to MS27983 shall be installed in accordance with Figures 3 and 4. Means shall be provided for tightening the seat bottom. Sufficient clearance between seat bottom and spreader shall be provided in order that the seat bottom will not contact the spreader under the specified proof loa

32、ds of 4.4.2.1. The material used for the seat bottom shall be nylon cloth conforming to MIL-C-72199 Type III, continuous support or attachment to prevent failure in service. Every effort shall be made to make the cutouts of a minimum size The nylon cloth shall be attached to the forward seat beam by

33、 some 4 Licensed by Information Handling ServicesMIL-S-2717VB Lb 7777?Ob OL7V270 O SEATBACK - * ADJUSTMENT STRAP SNAP FASTENER (FEMALE) I OF AIRPLANE. 1 IN. O.D. SLIDE FASTENER s: T: SNAP FASTENER (MALE) SEAT BACK SHALL BE ADJUSTABLE TO POSITION SHOWN. TO ACCOMMODATE OCCUPANT WEARING BACK-TYPE PARAC

34、HUTE UPPER SEATSUPPORT TUBE WHICH IS PART REAR SEATSUPPORT TUBE WHICH IS PART DIMENSIONS IN INCHES. (a) 36 TO 40 DIMENSION INDICATES THE PERMISSIBLE VARIATION OF THE LOCATION OF THE U?PER SEAT SUPPORT TUBE. SEAT BACK ADJUSTMENT STRAPS SHALL BE MADE TO ACCOMMODATE THIS VARIATION. - FIGURE I. DIMENSIO

35、NS OF ONE-MAN SEAT 5 Licensed by Information Handling Services. . SLIDE FASTENER SEAT BACK SHALL B& SHOWN TO ACCOMMODATE OCCUPANT WEARINO BACK-TYPE PARACHUTE I TUBE WHICH IS PART. I / L-REAR SEAT SUPPORT TUBE WHICH IS PART OF AIRPLANE. I IN. 0.0. I -2o-r 9&L - . i - SPREADER i +- - 39% - DIMENSIONS

36、IN INCHES. (0) 36 TO 40 DIMENSION INDICATES THE PERMISSIBLE VARIATION OF THE LOCATION OF THE UPPER SEAT SUPPORT TUBE. SEAT BACK ADJUSTMENT STRAPS SHALL BE MADE TO ACCOMODATE THIS VARIATION. FIGURE 2. DIMENSIONS OF TWO-MAN SEAT 6 Licensed by Information Handling ServicesMIL- S- 2 7 17 4B (U SAF ) WAP

37、 FASTEMER7 -a . DOT FORWARD if LUALE) t ,%DIA WELT 1 DIMENSIONS IN INCHES, UNLESS OTHERWISE SPECIFIED, TOLERANCE ON FRACTIONAL DIMENSIONS f FIGURE 3. LOCATION OF FASTENERS ONE-MAN SEAT BOTTOM 7 Licensed by Information Handling ServicesMIL-S-27174B (USA)?) SNAP FASTENER (FEMALE) DOT FORWAR0 r k- - I*

38、 3 i t I , ! 6Y ! , I I II i II I O c -I /- NYLON ZIPPEN OTHE R HALF AT OPPOSITE END OF SEAT ,DIA WELT - OIMLMSIONS IN INCHES. UNLESS OTHERWISE SCLCIFICD, TOLERANCE OF FRACTIONAL DIMENSIONS FIGURE 4, LOCATION OF FASTENERS FORTWO-MAN SEAT BOTTOM 8 O Licensed by Information Handling Services! i ! MIL-

39、S-27L74B Lb W 7977706 019Li294 B W MIL-S-27174B (USAF) 3.5.3.2 Seat panels. Adjacent seat bottoms shall be attached by a slide fastener conforming to the requirements of V-F-106, type IV, size MH, style 7, class A. Seats shall be easily joined and unjoined when the seat bottoms have varying adjusted

40、 cloth tensions in relation to each other. The joint shall not sag but provide a continuous seat bottom. 3.5.3.3 Back support. The tape (webbing) material used for the seat back and seat back adjustment straps shall be 1-114 inches in width, conform- ing to MIL-W-4088, type III. The tapes shall be e

41、qually spaced as shown in Figures 5 and 6 and shall be sewed together at the points where they cross or intersect. Snap fasteners conforming to MS27983-1N and MS27983-2N shall be installed in accordance with Figures 5 and 6. The lower part of the back support shall be nylon cloth, conforming to MIL-

42、C-7219, Type III. The seat back shall be adjustable and shall be quickly detachable from the upper seat support tube. 3.5.3.4 Back support length. The back support, in addition to having material to provide for an adjustment of 36-40 inches, shall have enough material to allow the back support to la

43、y against the seat bottom. Snap fasteners conforming to the requirements of MS27983-1N shall be spaced as shown in Figures 3 and 4 to provide the maximum seating space for para- troopers carrying full equipment. 3.5.4 Front support tube. Each seat shall be so designed that the front support tube, se

44、at bottom and seat back may be joined to the corresponding parts of an adjacent seat in any combination on either the left side or right side of the aircraft. The front support tube shall be easily and quickly connected to or disconnected from the adjoining seat. should have a minimum number of part

45、s as practicable and shall not require lubrication. positive lock for stowing the interlocking portion of the mechanism when not in use. Any two installed adjoining seats shall have a clearance between butting front support tubes not exceeding 1/16 inch. The mating parts shall conform with the dimen

46、sions of Figure 7. The mechanism The mechanism shall lock positively and shall be provided with a 3.5.5 Independent release. It shall be possible to release the legs and front support tubes of adjoining and joined seats in any combination or number and stow them without disturbing the remaining seat

47、s. 3.6 Construction. 3.6.1 Methods. Riveting or welding may be used for assembly of component parts fabricated of metals suitable for this type of construction. Fittings and joints, which require disassembly of the component parts of the seat, shall be bolted. All thread and stitches used for sewing

48、 seat back and. seat bottom shall be in accordance with V-T-295 and FED-STD-751, type 301, respectively. Licensed by Information Handling ServicesMIL-S-27174B (USAF) DIMENSIONS IN INCHES, UNLESS OTHERWISE SPECIFIED, TOLERANCE ON FRACTIONAL DIMENSIONS t & 33P LDOT TO LEFT SECTION A-& FIGURE 5. LOCATI

49、ON OF SNAP FASTENERS ONE-MAN SEAT BACK 10 Licensed by Information Handling Services- ,B v 2a IJ LJ LJ CJ LJ LJ LJ LJ LJ LI .c1 i i 37 4 I DOT TO LEFT SECTION A-A DIMENSIONS IN INCHES, UNLESS OTHERWISE SPECIFIED, TOLERANCE ON FRACTIONAL DIMENSIONS ?,i. FIGURE 6. LOCATION OF SNAP FASTENERS TWO-MAN SEAT BACK 11 Licensed by Information Handling ServicesHIL-S-27374B Lb SSSSIb 0374277 3 MIL-S-27174B (USAF) SLIDING BOLT7 R.H. END OF ADJOINING T- FRONT SEAT TUBE L.H. END OF -I FRONT SEAT TUBE .340 - .I25 -W ,497 DIA DIMENSIONS IN INCHES. UNLESS OTHERWISE SPECIFIED,