AIR FORCE MIL-S-25073 A-1970 SEAT AIRCRAFT《飞机座》.pdf

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1、7 MAY 1970- . SUFERSEDIG MIL-S-25073 (USAF) 4 November 1954 MILITARY. SF%CIFICATION SEAT, AIRCRAFT . 1. SCOPE I 1.1 This specification cov pilot S seats. I * 1.2 Classification. Pilot the following types. ers two types of adjustable, long range aircraft seats covered by this specification shall be o

2、f Type I - For use in long-range helicopters. lhe II - For use in cargo, transport, and multi-engine trainer aircraft. 2. APPLICABLE: DOCUMKNTS * 2.1 The following documents, of the issue in effect on date of invitation for bids 01 request for proposal, form a part of the specification to the extent

3、 specified herein. SPECIFICATIOMS Federal G,Q-P-416 89-2-325 TT-L-20 PFP-BO PPP-B-G PPP-B-b36 bilitary Plating, Cadmium (Electrodeposited) Zinc Coating, Electrodeposited Requirements For Lacquer Camouflage Bmes, Wood, Cleated-Plywood Baxes , Wood, Nailed And Lock-Corner Box, Fiberboard MIL-P-116 Pre

4、servation, Methods Of MIL-D-1000 Drawings, Engineering And Associated 1414j-3171 MagnesiGm Alloy, Processes For Lists Pretreatment And Prevention Of Corrosion On Hand Built Shapes; Latex Foam And Associated Equipment, General Specification For MIL-R-5001 Rubber Cellular Sheet, Molded And 11-5;272 En

5、vironmental Testing, Aeronautical NIL-H-O Heat Treatment Of Aluminum Alloys THIS DOCUMENT CONTAINS D-STD-595 hlilitary ldIL-STD-129 LiIL-STD-130 KIL-STD-143 MIL-STD-831 KIL-STD-838 MIL-STD-1186 E33586 Air Force Heat Treatment Of Steels (Aircraft Practice, Processes For) Cloth, Duck, IYylon, Parachut

6、e Packs Screw Threads, Standard , Optimum Selected Series , General Specification For Reels , Shoulder I!arness , Inertia-Lock Support Equipment, Aeronautical, Special, General Specification For Design Of Frimer Coating, Zinc Chromate, Low-doisture-Sensitivity Anodic Coatings, For Aluminum And Alumi

7、num Alloys Colors Marking For Shipment And Storage Identification j4arkine; Of US Military Property Specifications And Standards, Order Of Precedence For The Selection Of Test Reports Preparation Of Lubrication Of Military Equipment Cushioning, Anchoring, Bracing, Blocking, And Waterproofing; With A

8、ppropriate Test Methods Metals, Definition Of Dissimilar Belt, Aircraft Safety Lan, me XD-1 Gelt , Aircraft Safety Lap, Type PD-2 Harness, Aircraft Safety Shoulder, Adjustable , me MB-2A (Copies of specifications, standards, drawings, and publications required by suppliers in connection with specifi

9、c procurement functions should be obtained from the procuring activity or as directed by th2 contracting officer.) 3. REQUIREXENTS * 3.1 Preproduction testing. This specification makes provision for preproduc- tion testing. * 3.2 election of specifications aKd standards. Specifications and standards

10、 for necessary commodities and services not specified herein shall be selected in accordance with NIL-STD-143. “- 2 .i_. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-S-25073A(USAF) * 3.2.1 Standard parts. Standard parts (MS , AN, or JAN ) shal

11、l be used wherever they are suitable for the purpose, and shall be identified on the drawing by their part numbers. Commercial utility parts such as screws, bolts, nuts, cotter pins, et cetera, may be used, provided they possess suitable properties and are replaceable by the standard parts (MS, AN,

12、or JAN) without alteration, and provided the corresponding standard part rtumbers are referenced in the parts list and on the Contractors drawings. In the event there is no suitable corresponding standard part in effect, on date of invitation for bids, commercial parts may be used provided they con-

13、 form to all applicable requirements of this specification. 3.3 Materials. * 3.3.1 Protective treatment. When materials are used in the construction of the seat that are subject to corrosion in salt air or other atmospheric con- dition likely to occur during service usage, they shall be protected ag

14、ainst such corrosion in a manner that will in no way prevent compliance with the performance requirements of this specification. The use of any protective coating that will crack, chip, or scale with age or extremes of atmospheric conditions shall be avoided. * 3.3.2 Metals. Metals shall be of the c

15、orrosion-resistant type or suitably treated to resist corrosion due to fuels, salt spray, or atmospheric condi- tions likely to be met in storage or normal service. * 3.3.3 Heat treat. Materials which require heat treatment in order to satisfactorily accomplish theii. desigfi shall be heat treated i

16、n accordance with MIL-fi-6875 for steels and IFIIL-H-GOB for aluminum. * 3.3.4 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 IB33586. 3.4 Desim. The seat shall b

17、e designed for maximum comfort and ease of adjustment. The area above and to each side of the seat bottom pan should be left as open as possible to aid ingress, .egress, and freedom of movement for the seat occupant. 3.4.1 Dimension. The critical dimensions of the seat shall be as specified in Figur

18、es 1 throus otherwise specified by the procuring agency. * 3.4.4 headrest. The seat shall incorporate a headrest in the approximate location shown in Figures 1 and 2. The headrest shall be so designed and installed as not to interfere with the egress OP ingress of the occupant wearing a back-type pa

19、rachute. The headrest cushioning material shall be resilient, durable, confortable, and shall not pack due to use. The covering material shall be 7-1/4 ounce nylon cloth conforming to MIL-C-7219, lype III. The color shall be maroon red conforming to color Ilo. 21136 of FED-STD-595, unless otherwise

20、specified by the procuring agency. 3.4.5 Shoulder harness reel. The seat shall incorporate a shoulder harness take up, inertia lock reel in accordance with MIL-R-8236, I-e bfA-2 for the Type I seat and Ty-pe PIA-1 for the Type II seat. The reel shall be located so that the center line of the shoulde

21、r harness attaching bolt is 20 inches below the top of the shoulder harness roller. It shall be located so that the cable pulls off the reel in a plane which includes the longitudinal (fore-and-aft) and vertical centerlines of the seat. The angle between the mounting plane of the reel and the floor

22、plane of the seat shall not be less than 75 degrees when the seat back is reclined at tne 13-1/2 degree position. 3.4.6 Shoulder harness roller and guide. A shoulder harness roller and guide shall be provided on the seat back. The dimensions and location of I 4 Provided by IHSNot for ResaleNo reprod

23、uction or networking permitted without license from IHS-,-,-EIL-S-25073A(USAF) I the roller and guide shall be as shown on Figures 2 and 3. The roller shall have a minimum diameter of 1 inch. * 3.4.7 Safety belt anci shoulder harness. Provisions shall be made for the use of eitherTme XD-1 or ND-2 sa

24、fety belt conforming to drawing 541119650 and 5bN.9651, respectively, the belt to be attached with l/h-inch diameter aircraft bolts. The attachment fitting shall be of the fork type which will place the attachment bolt in double shear. The point of attachment of the belt to the seat shall be as indi

25、cated in Figure 3. Provisions shall also be made for the use of the Q-pe M13-2A shoulder harness (depicted on drawing 57D677). 3.4.8 Parachute support bulkhe and a load of 900 pounds ultimate, 600 pounds proof, applied to the shoulder harness take-up reel in a forward direction parallel to the floor

26、 plane as indicated in 4.5.2. These loads shall be applied simultaneously and under the following separate conditions: directly forward, 20 degrees to the right of forward and 20 degrees to the left of forward. If the structure is shown to be symmetrical, the yaw load need only be applied to one sid

27、e. d. Lap safety belt mountings: An up load of 1500 pounds ulti- mate, 1000 pounds proof, applied to the lap belt mountings (equally distributed between the two) on the side of the seat, and parallel to the seat back. Type II only: a. Seat bottom: A down load of 4000 pounds ultimate, 2665 pounds pro

28、of, distributed over the seat bottom with the load center of gravity located as shown in Figure 1. The seat shall be adjusted to the maximum up position during this test. b. Seat back: An aft load of 1500 pounds ultimate, 1000 pounds proof, distributed over the area of the seat back with the load ce

29、nter of gravity located as shown in Figure 1. The seat shall be adjusted to the maximum up position, and the seat back shall be inclined to the 13-1/2-degree position during the test. 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-S-25073A Lb

30、m 99979Ob OL93Z83 9 W c. Safety belt mountings: A load of 2880 pounds ultimate, 1920 pounds proof, applied to the lap safety belt mounting (equally distributed between the two) on the side of the seat in- a direction forward and inclined 40 degrees up from the floor plane, and a load of 1000 pounds

31、ultimate, 1200 pounds proof, applied to the shoulder harness take-up reel in a forward direction parallel to tile floor plane, as indicated in 4.5.2. These loads shall be applied simultaneously and under the following separate conditions: directly forward, 20 degrees to the right of forward, and 20

32、degrees to the left of forward. If the structure is shown to be symmetrical, the yaw load need only be applied to one side. * 3.6 Environmental exposure. The seat shall be capable of conforKing all i requirements specified herein after exposure to the following environmental conditions : a. humidity

33、 of 100 percent. b. Fungus growth as may be encountered in .trofiical climates. c. Salt spray as may be encountered in salt-sea atmosphere. d. Sand and dust as clay be encountered in tropical climates. e. Sunshine. f. Vibration. * 3.7 Interchangeability_. All. parts having the same manufacturers par

34、t number shall be directly and completely interchangeable with each other with respect to installation and performance. Changes in manufacturers part numbers shall be governed by the drawing number requirements of MIL-D-1000. * 3.8 Weight. The complete seat, including all parts, inertia reel, adequa

35、te finish coating and tracks which permit a 6 inch fore-and-aft adjustment shall not exceed a total weight of 45 pounds for the Type II seat and 30 pounds for the me I seat. The seat bottom and seat back cushions are not considered a part of the seat for the purpose of this specification. * 3.9 Colo

36、r. The color of the seat structure shall be medium gray conform- ing to color Bo. 36231 of FED-STD-595, unless otherwise specified by the procuring agency. * 3.10 Finish. Aluminum alloy parts shall be anodically treated in accordance with MIL-A-8625. hagnesium-alloy parts shall be treated in accorda

37、nce with MIL-“3171. Noncorrosion-resisting steel parts shall be cadmium-plated in accordance with QQ-P-416, or zinc-plated in accordance with QQ-Z-325. The seat shall have a paint finish consisting of one think coat of zinc-chromate primer conforming to MIL-P-8585, followed by two coats of aircraft

38、lacquer conforming to TT-L-20, except that anodized aluminum alloy parts need not be painted if colored-anodized. * 3.11 Identification of produc?. 3.11.1 Identification of product. Equipment, assemblies and parts shall be mrked for identification in accordance with MIL-STD-130. Provided by IHSNot f

39、or ResaleNo reproduction or networking permitted without license from IHS-,-,-* 3.11.2 Use of . PEEPARAION FOR DELIVLRY * 5-1.1 Level “- A. Each seat shall be preserved and packaged Method III of i-IL-P-116 .in a weather resistant unit container conforming to PPP-B-63f;. 10 Provided by IHSNot for Re

40、saleNo reproduction or networking permitted without license from IHS-,-,-* 5.1.2 Level C. Preservation and packaging that will afford adequate pro- tection against corrosion, deterioration and physical damace durinp: shinment from supply source to the first receiving activity for imnlediate use. Thi

41、s level 1a.y conforr, to the suppliers commercial practice, provided the latter meets the requiremnts of this level. * 5.2 Facking. Facking shall be Level Ay B or C as specified (see 6.2). * 5.2.1 AVgl-4. Seats preserved and packaged as specified in 5.1.1 shall be packed in overseas type shipping co

42、ntainers conforming to PPP-13-601 or PFP-3-621. As far as practicable, shipping containers shall be of uniforn shape and size, of mininun cube and tare consistent with the protection required, and contain identical quantities. The gross weiGht of each con- tainer shall not exceed the weight limitati

43、on of the specification. Con- tainers shall be closed and strapped in accordance with the specification and appendix thereto. 5.2.2 “- Level B. Seats preserved and packaged as specified in 5.1.1 shall not be overboxed for domestic shipments. The unit container, closed and strapped in accordance with

44、 the applicable appendix of the container specification shall be the shipping container. * 5.2.3 Level C. Packing that will afford adequate protection at the lowest -“ rate against damage during direct domestic shipment from the supaly source to the first receiving activity for immediate use. This l

45、evel shall conform to applicable carrier rules and regulations and may be the suppliers commercial practice, provided the latter meets the requirements of this level. * 5.3 Physical protection. Cushioning, blocking and bracing shall be in accordance with XIL-STD-1166, except that for domestic shipme

46、nts y water- proofing requirements for cushioning materials and containers shall be waived. Dro? tests of I-IIL-STD-1186 shall be waived when preservation, packaging and packing of the item is for immediate use or when drop tests of i.r1-116 are applicable. * 5.4 *king of shipmCnJt Interior packages

47、 and exterior shipping con- tainers shall be marked in accordance with IIIL-STD-129. 6. iiOTES 6.1 Intended use. The tme I seats are intended for use by the pilot and Co-pilot of long range helicopters. The type II seats are intended for use by the pilot an Co-pilot of long range cargo and transport

48、 aircraft, and in multi-engine trainers. “II * 6.2 Ordering data. The procurement document should specify the following: a. Title, number and date of this specification. b. Preproduction test conditions (see 4.7). . 11 Provided by IHSNot for ResaleNo reproduction or networking permitted without lice

49、nse from IHS-,-,-* 6.3 The Eargins of this specification are marked with an asterisk to indicate where changes (additions, modifications, corrections, deletions) from the previous issue were made. This was done as a convenience only and the Government assumes no liability whatsoever for any inaccuracies in these notations. Bidders and contractors are cautioned to evaluate the require- ments of this docunent based on the entir