1、MIL-S-58OC 16 m 7777906 0185153 O m 16 August i967 . SUPERSEDING MIL-s-5 eo( AS G) 24 September 1957 MILITARY SPECIFICATION SEAT, AIRCRAFT, TROOP, WALL-STYl3 1. SCOPE 1.1 This specification covers standard, light-weight folding, wall-type seats for use by troops in ca.rgo-type aircraft. 1.2 Classifi
2、cation. Troop seats shall be of the following four types, as specified (see 6 2) : Type SEU-l/A Four-Man Seat me F-2 Three-Man Seat Type F-3 Two-Man Seat Type F-4 Che-Man Seat 2. APPLICABm DOCUMENTS 2.1 The following documents of the issue in effect on date of invitation for -bids or request for pro
3、posal, form a part of the specification to the extent specified herein. SPECIFICATION Federal V-T-295 QQ-P-416 QQ-2-325 PPP-B-601 PPP-B-621 PPP-B-636 Military MIL-P-116 MIL-D-1000 MIL-W-4088 MIL-C-7219 MIL-A-8625 Thread, Nylon Plating, Cadmium (Electrodeposited) Zinc Coating, Electrodeposited, Requi
4、rements For Boxes, Wood, Cleated-Plywood Boxes, Wood, Nailed And Lock-Corner Boxes, Fiberboard Preservation, Methods Of Drawings, Engineering And Associated Lists Webbing, Texbile, Woven, Nylon Cloth, Duck, Nylon, Parachute Packs Anodic Coatings, For Aluminum And Aluminum Alloys A Provided by IHSNot
5、 for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-S-5804C( USAF) MILA-8905 MILA-21165 STANDARDS Federal FED-S TD-5 9 5 FEDSTD-751 Military MILSTD-U9 MIL-STD-130 MILSTD-I43 MILSTD-831 MILSTD-U86 26504 Adapter, Tie Down, Aircraft Floor Adapters, Quick-Disconnect, Pass
6、enger Seat To Floor Colors Stitches, Seams, And Stitchings Marking For Shipment And Storage Identification Marking Of US Military Property Specifications And Standards Order Of Precedence For The Selection Of Test Reports, Preparation Of Cushioning, Anchoring, Bracing, Blocking, And Waterproofing; W
7、ith Appropriate Test Methods Plate-Anchor, Aircraft Troop Seat (Copies of specifications, standards, drawings, and publications required by suppliers in connection with specific procurement functions should be obtained from the procuring activity or as directed by the contracting officer.) 3. REQU=N
8、TS 3.1 Preproduction testing. This specification makes provision for preproduc- tion testing. 3.2 Selection of specification and standards. Specifications and standards for necessary commodities and services not specified herein shall be selected in accordance with MILSTD-143. 3.2.1 Standard parts.
9、Standard parts (MS, AN, or JAN) shall be used wherever they are suitable for the purpose, and shall be identified on the drawing by their part numbers. cotter pins, et cetera, may be used, provided they possess suitable properties and are replaceable by the standard parts (MS, AN, or JAN) without al
10、teration, and provided the corresponding standard part numbers are referenced in the parts list and, if practicable, on the contractors drawings. there is no suitable corresponding standard part in effect on date of invita- tion for bids, commercial parts may be used provided they conform to all req
11、uirements of this specification. Comercial utility parts such as screws, bolts, nuts, In the event 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-S-5804C 26 9999906 0185155 4 MIL-s-5804c( USAFI 3.3 Mat erials. 3.3.1 Basic structure. of metal.
12、The basic structure of the seats shall be fabricated 3.3.2 Protective treatment. When materials, that are subject to corrosion in salt air or other atmospheric conditions likely to occur during service usage, are used in the construction of the seat, they shall be protected against such corrosion in
13、 a manner that will in no way prevent compliance with the perform- ance requirements of this specification. that will crack, chip, or scale with age or extremes of atmospheric conditions, shall be avoided. 3.4 Desian. or left side of th-e airplane in such manner that the occupants Will face inboard.
14、 respective type, sitting side-by-side, and shall provide maximum comfort and ease of releasing and stowing. 3.4.1 Foldina and stowing. 3.4.1.1 All seats shall be so designed that the leg or legs and seat bottom may be quickly folded against and lashed to the seat back with the leg or legs in betwee
15、n seat bottom and seat back. The use of any protective coating The seat shall be designed for installation on either the right The seat shall accommodate the number of persons specified for each 3.4.1.2 rolled stowage. spreaders may be folded and the seat back may be quickly detached from the upper-
16、seat support tube which is considered part of and attached to the airplane, to permit the seat to roll up against the side of the fuselage. Two, three, and four straps shall be provided and attached to the two-man, three-man and four-man seats, respectively, for the purpose of lashing the seats in t
17、he stowed position. The two-man, three-man and four-man seats shall also be designed for They shall be designed in such manner that the legs and 3.4.1.3 Foldina and unfoldine: time. folded and lashed, or unlashed and unfolded, quickly and easily, in a period not to exceed 10 seconds. The seats shall
18、 be capable of being 3.4.1.4 All seats shall also be capable of being stowed or unstowed, quickly, and easily, in a period not to exceed 2 minutes. 3.4.1.5 use of tools or special equipment or the removal of parts. seats must be positive in order that no portion of the seats protrudes into the cargo
19、 compartment, to type II of MILW-4088. 3.4.1.6 Size of package. The seat package of two-man and three-man seats, when it is in the stowed position, shall be held to a max5num size of not more than 6 inches in diameter. All operations ,outlined in 3.4.1.3 and 3.4.1.4 shall not require the All lashing
20、 of All lashing straps shall be 1-inch-wide webbing conforming 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-S-5OYC Lb W 777770b 0385356 b W MILs-5804C( USAI?) 3.4.2 Leg sumorts. Figures 1, 2, 3, and 4. ance with MIL-A-21165, securely to the
21、stud of anchor plate shown in MS26504 and the stud -of the tie- down fitting shown in MILA-8905. installed in the airplane flush with the floor surface, and located as shown in Figures 1, 2, 3, and 4. The release shall be capable of being actuated at the base of the leg. legs shall be capable of a s
22、mallmovi attachment to the rear seat support tube which is removable for the installa- tion of the seat. individual seat to permit attachment of the safety belt fitting to rear seat support tube. ment of seat legs and spreaders, as required. 1-inch-wide tape conforming to MILW-4088, type II. for tig
23、htening 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 specified load. nylon cloth conforming to MILC-7219. forward seat beam by some continuous support or attachment method to prevent failure
24、 in service. The seat bottom shall be made of one piece, with provisions for A 2-1/2 inch cutout shall be provided in between each Additional cutouts in seat bottoms may be provided for attach- All cutouts shall be bound with Means shall be provided The material used for the seat bottom shall be The
25、 nylon cloth shall be attached to the 3.4.3.2 panel, and seat back adjustment straps shall be 1-1/4 inches in width, conform- ing to MILW-4088, type III. Figures 1, 2, 3, and 4, and shall be sewed together at the points where they cross or intersect. in width, conforming to MILC-7219. shall be quick
26、ly detachable from the upper seat support tube. 3.4.3.3 The materials for the seat back and bottom shall be vat-dyed a color selected by the procuring activity. All thread and stitches used for sewing seat back and seat bottom shall be in accordance with V-T-295 and FED-STD-751, type 301, respective
27、ly. The tape (webbing) material used for the center seat back, head rest The tapes shall be equally spaced as shown in The lower seat back panel shall be nylon cloth, 8 inches The seat back shall be adjustable and The color shall conform to FED-STD-595. 3.5 Construction. 3.5.1 Methods. parts fabrica
28、ted of metals suitable for this type of construction, Fittings and joints which require disassembly for installation or removal of the seat from the airplane, or for disassembly of the component parts of the seat, shall be bolted. Riveting or welding may be used for assembly of component 4 /- o Prov
29、ided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-S-5804C 3b m 797770b 0385357 8 m MIL-S-5804C( WAF) SEAT BACK SHALL BE CAPABLE OF BEING ADJUSTED TO POSITION SHOWN TO ACCOMMODATE OCCUPANT WEARING BACK-TYPE PARACHUTE. SECTION A-A SEAT BACK ADJUSTMEN STR
30、AP 8 (TRUE UPPER SEAT SUPPORT TUBE WHICH IS PARTOF AIRPLANE(1 IN.OD). REAR SEAT SUPPORT TUBE WHICH IS PART OF AIRPLANE ( I IN. OD). DIMENSIONS IN INCHES, (a) 36 TO 40 DIMENSION INDICATES THE PERMISSIBLE VARIATION OF THE LOCATION OF THE UPPER SEAT SUPPORT TUBE. SEAT BACK ADJUSTMENT STRAPS SHALL BE MA
31、DE TO ACCOMMODATE THIS VARIATION E I. DIMENSIONS OFONE-MAN SEAT 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-S-58OLIC 3b 7779706 0385358 T MIGS-580l+C( USAF) SEAT BACK SHALL BE CAPABLE OF BEING ADJUSTED TO POSITION OCCUPANT WEARING BACK- TYP
32、E PARACHUTE WHICH IS PART OF AIRPLANE SHOWN TO ACCOMMODATE UPPER SEAT SUPPORT TUBE (I IN.00). SECTION A-A 9$-r740 d. Where the preproduction test sample should be sent, the activity responsible for testing, and instructions concerning the submittal of the test reports (see 4.3.1.2). 6.3 to the previ
33、ous issue, due to the extensiveness of the changes. Asterisks are not used in this revision to identify-chuiges with respect Custodian: Air Force -.82 Review Activity : Air Force - 82 Preparing Activity: Air Force - 82 Project No. 1680-00l+2 *US. GOYERNMm PRINTING OFFICE: 186?-901-510/900 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
