1、MIL-S-7852B Lb q797706 0386225 Li MILITARY SPECIFICATION MIL- S - 7 85 2B 1Apri1 1968 SUPERSEDING MIL-S-7852A 18 June 1958 SEAT, AIRCREW, ADJUSTABLE SWIVEL, TYPE E-1 This specification is mandatory for use by all Departments and Agencies of the Department of Defense. 1. SCOPE 1.1 swivel seats for us
2、e by crew memebers other than pilot and copilot. 2. APPLICABLE DOCUMENTS This specification establishes the requirements for standard, adjustable, * 2.1 The following documents of the issue in effect on date of invitation for bids or request for proposal, form a part of the-specification to the exte
3、nt specified herein. SPECIFICATIONS Federal QQ-P-416 QQ-2-325 PPP-B-60 1 PPP-B- 62 1 . PPP-B-636 Military MIL-P- 1 16 MIL-D-1000 MIL-M-3 17 1 MIL-R-5001 MIL-(2-7219 MIL-E-77 29 MIL-R-8236 MIL-P-8585 MIL-A-8625 Plating, Cadmium (Electrodeposited) Zinc Coating, Electrodeposited Require- ments For Boxe
4、s, Wood, Cleated-Plywood Boxes, Wood, Nailed And Lock-Corner Box, Fiberboard Preservation, Methods Of Drawings,Engineering And Associated Lists Magnesium Alloy, Processes For Pretreat- ment And Prevention Of Corrosion On Rubber Cellular Sheet, Molded And Hand Built Shapes; Latex Foam Cloth, Duck, Ny
5、lon, Parachute Packs Enamel, Gloss For Aircraft Application Reels, Shoulder Harness, Inertia Lock Primer Coating, Zinc Chromate, Low- Moicture-Sensitivity Anodic Coatings, For Aluminun And Aluminum Alloys I I FSC 1680 Licensed by Information Handling ServicesProvided by IHSNot for ResaleNo reproduct
6、ion or networking permitted without license from IHS-,-,-I VIL-S-78526 16 7797706 0386226 6 MIL-S-7852B STANDARDS Federal FED-STD-595 Military MIL-STD-129 MIL-STD-130 MIL-STD-143 MIL-STD-831 - MIL- STD- 1 18 6 MS33586 DRAWINGS Air Force 53D20961 . 54H19650 _, 54H 1965 1 Colors Marking For Shipment A
7、nd 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; With Appropriate Test Met hod s Metals, Definition Of Dissimilar Harness, Aircra
8、ft Safety, Shoulder, Adjustable, Type MB-2 Belt, Aircraft Safety, Lap, Type MD-1 Belt, Aircraft Safety, Lap, Type MD-2 (Copies of specifications, standards, drawings, and publications required by suppliers in connection with specific procurement functions should be obtained from the procuring activi
9、ty or as directed by the contracting officer.) 3. REQUIREMENTS 3.1 Preproduction testing. This specification makes provision for preproduc- tion testing. J; 3.2 Selection of specifications and standards. Specifications and standards for necessary comhodities and services not specified herein.shal1 b
10、e selected in accordance with MIL-STD-143 except as provided in 3.3.1 and 3.3.2. 3.2.1 Commercial parts. Comercial 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,
11、nuts, cotter pins, having suitable properties may be used provided: a. They can be replaced .by .t,he standard parts (MS or AN) without alter- ation. b. The corresponding standard part numbers are referenced in the parts list and, if practical, on the contractors drawings. . 2 I Provided by IHSNot f
12、or ResaleNo reproduction or networking permitted without license from IHS-,-,-1 MIL-S-7852B 3b m 7777706 O386227 8 m MIL-S-7852B 3.2.2 Standard parts. shall be used where they suit the purpose. With the exception in 3.2.1, MS and AN standard parts They shall be identified on the drawings by their pa
13、rt numbers. 3.3 Materials. 3.3.1 Fungus-proof materials. Materials that are nutrients for fungi shall not be used where it is practical to avoid them. Where used and not hermet- ically sealed, they shall be treated with a fungicidal agent acceptable to the procuring activity. inclosure, fungicidal t
14、reatment will not be necessary. 3.3.2 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 or normal service. However, if they will be used in a hermetically sealed 3.3.2.1 Diss
15、imilar metals. - Unless suitably protected against electrolytic corrosion, dissimilar metals shall not be used in intimate contact with each other. Dissimilar metals are defined in MS33586. 3.4 Design. The seat shall be designed for maximum comfort, ease of adjust- ment, and minimum weight. 3.4.1 Di
16、mensions. The critical dimensions of the seat shall be as specified in Figures 1 through 4. Unless otherwise specified, a tolerance of 1/16 inch will be allowed on the over-all dimensions. 3.4.2 Adjustments. The seat shall be adjustable as follows 3.4.2.1 Vertical adjustments. The seat shall be prov
17、ided with a 5-inch vertical adjustment as indicated in Figure 1. The seat shall be adjustable in increments of 112 inch within the 5-inch adjustment range. shall incorporate a loaded mechanical device which shall raise the seat as the occupants weight is removed. This load shall not exceed 150 pound
18、s when the seat is in the lowest position nor be less than 30 pounds when the seat is in the highest position. This adjustment 3.4.2.2 Swivel adjustment. The seat shall be capable of being rotated on its base through any number of complete revolutions in either the clockwise or counterclockwise dire
19、ctions. The swivel adjustment shall contain at least 8 locking positions equally speaced through 360 degrees and shall be capable of being swiveled freely, when unlocked, while carrying a load of 250 pounds on the seat bottom. 3.4.2.3 Horizontal adjustment. The seat shall be adjustable along the tra
20、cks for a distance of not less than 6 inches in increments of not more than 1 inch. 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-S-7852B 36 7777906 0386228 T MIL-S- 7852B SEAT SHOWN IN NEUTRAL POSITION SECTION A-A SEAT REFERENCE POINT ADJUST
21、MENT DIMENSIONS IN INCHES FIGURE I. SIDE VIEW OF SEAT 12.50 O b 4 I -. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-S-7852B Lb 77777Ob OLBb227 L -+- L7-4 HORIZONTAL ADJUSTMENT CONTROL AREA BOTH SIDES I/ t 7 -+ 3 DIA. It 1 DIMENSION IN INCHES F
22、IGURE 2. SIDE VIEW OF SEAT SHOWING LOCATION OF CONTROL -. AREAS FOR SEAT ADJUSTMENTS. MIL-S-7852B ,VERTICAL ADJUSTMENT CONTROL AREA RIGHT- HAND SIZE. I DIA. CONTROL KNOB SHAPE SWIVEL I CONTROL AREAS SWIVEL ADJUSTMENT RIGHT-HAND SIDE. INERTIA REEL LEFT- HAND II I II 4 - 5 - - I Provided by IHSNot for
23、 ResaleNo reproduction or networking permitted without license from IHS-,-,-. c MIL-S-7852B 16 7999906 0386230 B MIL-S-7852B 14*75 “7 BACK PARACHUTE SPACE REQUIREMENTS . SURVIVAL KIT SPACE REQUIREMENTS DIMENSIONS IN INCHES FIGURE 3. BACK VIEW OF SEAT IL 6 I Provided by IHSNot for ResaleNo reproducti
24、on or networking permitted without license from IHS-,-,-.MIL- S - 7 85 2B - ._ 23 MAX- I DIMENSIONS IN INCHES FIGURE 4. SPACE REQUIREMENTS 7 o Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-S-7852B 16 9999906 0386232 1 MIL-S-7852B . 3.4.3 Lockin
25、g mechanism. The control levers for operating the swivel and vertical adjustments shall be located on the right hand side of the seat within the circular areas indicated in Figure 2. operating the shoulder harness inertia reel shall be located on the left hand side of the seat within the circular ar
26、ea indicated in Figure 2. The relative location with respect to the occupant of the control levers for the swivel and vertical adjustment and the inertia reel shall not change when the seat is adjusted horizontally or swiveled. operating the horizontal adjustment along the tracks. be located on each
27、 side of the seat when the seat is faced parallel to the tracks. The control levers shall be located within the circular areas indicated in Figure 2. Figure 2, and there shall be a minimum of 1 1/2 inches c1,earance between the seat adjustment control knobs and the seat structure. shall be released
28、by an upward movement of the levers and the angular movement of the levers shall not exceed 50 degrees. to the locking mechanisms to insure that the mechanisms will automatically lock when the levers are released. The control lever for Two control levers shall be provided for One control lever shall
29、 The seat adjustment control knobs shall be shaped as shown in The locking mechanisms Special attention shall be given 3.4.4 Arm rests. approximate location indicated in Figure 1. The arm rests shall fold into a position where they will not interfere with the egress or ingress of the occupant. Ann r
30、ests shall be provided on each side of the seat at the 3.4.5 Headrest. location indicated in Figures 1 and 3. and installed as to not interfere with the egress or ingress of the parachute pack. 3.4.6 Shoulder harness reel. The seat shall incorporate a shoulder harness take-up inertia lock reel, conf
31、orming to MIL-R-8236. The reel shall be located in such a manner that the centerline of the shoulder harness attachment bolt is 20 inches below the top of the seat back over which the shoulder harness will slide. plane which includes the longitudinal (fore and aft) centerline of the seat. The seat s
32、hall incorporate a headrest at the approximate The headrest shall be so designed It shall be so located that the cable pulls off the reel in a 3.4.7 Shoulder harness roller and guide. A shoulder harness roller and guide shall be provided on the seat back. The dimensions and location of the roller an
33、d guide shall be as shown on Figures 2 and 3. imum diameter of 1 inch. The roller shall have a min- 3.4.8 Safety belt and shoulder harness. Provisions shall be made for the use of the Type MD-1 safety belt conforming to Drawing 54H19650 or the Type MD-2 safety belt conforming to Drawing 54H19651, th
34、e belt to be attached with 1/4 inch diameter aircrft bolts. which will place the attachment bolt in double shear. to the seat shall be so located that when the belt is inclined upward and forward with the plane of the belt at an angle of 40 degrees to the plane of the floor, the centerline of the be
35、lt will pass through the reference point. Provisions shall also be made for the use of the Type MB-2 shoulder harness conforming to Drawing 53D20961, the belt to be attached to the take-up mechanism with a 10-32 aircraft bolt. The attachment fitting shall be of the fork type The point of attachment
36、. 8 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-S-7852B 16 9999306 0186233 3 MIL-S-7852B * 3.4.9 Headrest and arm rests upholstery. The covering material on the head- rest and arm rests shall be 7 1/4 ounce nylon cloth conforming to MIL-C-721
37、9,- type III. It shall be vat dyed maroon (red) conforming to color number 21136 of FED-STD-595. -The headrest cushioning material shall be resilient, curable, comfortable, and shall not pack due to use. The top surface of the arm rests shall be cushioned with a 314 inch thickness of foam rubber, co
38、nforming to MIL-R-5001, type II, class medium. 3.4.10 Parachute support bulkhead. bulkhead permanently fastened within the seat and located as shown in Figures 1 and 3. The seat shall be provided with a metal 3.4.11 Drain holes. Drain holes shall be provided to drain the seat with the bottom in any
39、position into which it might be placed by the normal ground position of the airplane. 3.4.12 Tracks. The tracks which permit horizontal adjustment of the seat shall be provided with holes for attachment to the floor. These holes shall be drilled size “GI (0.261) for 1/4 inch bolts. The holes shall b
40、e arranged in two rows on each track. The two rows shall be symmetrical about the center- line of the track (not in staggered rows) and 2 112 inches apart. The longi- tudinal spacing of the holes in both rows shall be 5 1/2 inches between centers, starting with a set of holes directly below the refe
41、rence point when the seat is adjusted to a position midway of the fore-and-aft travel. on the distance between the centerline of any two holes on one track shall be +1/64 inch. The tolerance 3.5 Construction. 3.5.1 Basic structure. The basic structure of the seat shall be fabricated of metal. or fun
42、gus shall be used in the basic structure. No wood or other materials which are subject to attack by mildew 3.5.2 Methods. Riveting or welding may be used for assembly of component parts fabricated of metals which are suitable for this type of construction. Fittings and joints which will require disa
43、ssembly for installation or removal of the seat from the airplane or for disassembly of the component parts of the seat shall be bolted. 3.5.3 Projections. The inside surfaces of the seat shall be free from pro- jections which could catch or damage by abrasion the parachute pack or the clothing of t
44、he occupant. The exterior surfaces of the seat shall be free from sharp edges or any projections which might scratch the hands or clothing of the occupant as he moves his arms about the sides of the seat to handle equipment within his reach to the rear and to the sides. 3.5.4 Strength requirements.
45、The seat shall have sufficient strength to carry the following loads. 9 . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-S-7852B - . 3.5.4.1 Seat bottom. A down load of 4,000 pounds ultimate, 2,665 pounds proof, distributed over the seat bottom
46、with the load center of gravity (cg) located as shown in Figure 1. and adjusted to the maximum up position. 3.5.4.2 Seat back. An aftload of 4,000 pounds ultimate, 2,665 pounds proof, distributed over the seat back with the load cg located as shown in Figure 1. The seat shall be adjusted to the maxi
47、mum up position. This aft load shall be applied under three separate conditions; directly aft, 20 degrees to the right, and 20 degrees to the left of aft. 3.5.4.3 Headrest. An aft load of 200 pounds ultimate, 135 pounds proof, uniformly distributed over the headrest. The seat shall be mounted facing
48、 parallel to the tracks 3.5.4.4 Arm rests. A down load of 300 pounds ultimate, 200 pounds proof, applied at the center of each arm rest. A side load of 100 pounds ultimate, 67 pounds proof, applied outward or inward perpendicular to each arm rest in a horizontal plane. The load shall be applied at t
49、he center of the ann rest. It is notrequired that these loads be applied simultaneously. * 3.5.4.5 Safety belts. A load of 2,880 pounds ultimate, 1,920 pounds proof, applied to the lap safety belt mountings (equally distributed between the two) on the side of the seat in a direction forward and inclined 40 degrees up from the floor line; and a load of 1,800 pounds ultimate 1,200 pounds proof, a
