1、6- 22 JULY 1963 SUPERSEDING SO JUNE 1958 FA-PD-311-2204, REV. 3 . . MILITARY SPECIFICATION .r .CATAPULT, AIRCRAFT EJECTION SEAT, MAI . . METAL PARTS ASSEMBLY 1, SCOPE . 1.1 This specification covers metal parts assembly far Catapult, Aircraft Ejection Seat, MSA1, Assembly will ultimately be loadd an
2、d used in conjunction with other propellant actuated devices in to pei?form any of the STD-105. inspections s6t ?orth in tile specification where such inspections are deemed necessary . to assure supplies and services conform to - 4,3,1.2 Size of lot. The shipping lots of metal parts assemblies shal
3、l consist of 614 catapults, maximum, provided the homogeneity require- ments of inspection lots have been retained. A ? prescribed reqi;ivements. . . 4.1.1 Qscntg msuyance temts a ish Blocks prescribed in MILSTD-639 shall be use as a basis of comparison for surface roughness determination, Four powe
4、r (45) magnification may be used in performing vis- ual esamination for such defects as bur and foreign matter. 8 r- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-tot sire 1- 300 301- 1,3O 1,301- 3,200 3,201- 8,W . 81001-221000 4.3.2.1. Latch, Dwg.
5、 C86 detail of Dwg. F8598687. Criticni Major Dsfmt Nono dofined Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Nethwl of Defect inupectba 190. Protective finish inadequate or *. defective . . Visual 131 Surface finish of small cavity, body I - shoul
6、der and body slots, improper Visual 132. Bur Visual . . 133. Foreign matter Visual Ninor 201, Pitch diameter of thGad, min. Gage 202. Diameter of large cavity Gage 203. Diameter of counterbore, min. Gage 204, Diameter of body shoulder Gage 205. Diameter of flange, ma%. . Gage 206. Diameter- of pin h
7、ole in body . Gage 207, Dionteter of screw hole, min. Gage 208. Depth of Iarge cavity Gage 209. Length from flange to base of large . cavity Gage 210. Length of slot in body Gage Zl. Width of slot in body *_. Gage 212. Location of slot tPCtOl None clefincd 101. Diameter of body Gage 102. Diameter of
8、 shouldel Gage 103. Diameter, inside Gage 104. Total length, min. Gage 101. Total length, min. Gage lob. Thickness af wall variation, max. Gage 106. Straightness Gage 107. Diameter of holes in shoulder Measure 108. Number of holes in shoulder, incorrcct Visual 109. Metal defective Visuai 110. Protec
9、tive finish inadequate or defective Visual 111, Surface finish of shoulder, improper Visual 112. Bur Visual 113, Foreign matter . Visual 201. Total length, mm, Gage 4.3.2.11 Tzibe, Inside, Dzvg,O859365, -97, Minor cottering CL deto21 of Dwg. F8593687. Critical Maior Bfathd of DrfceC inipecfiOn . Non
10、e defined 101, Pitch diameter of thread, min. 102. Major diameter of thread, min. 103. Goiicentricity of pitch diameter of Gage Gage thread with shoulder at datum location Gage 104. Concentricity of pitch diameter of thread with bore at datum location Gage 105. Diameter of shoulders Gage 106, Depth
11、of relief of spiral groove, min. Gage Gage Gage 107. Total length, max. 108, Thickness of wall, min. 109. Length of effective thread, min. Gage 110. Straightness Gage 111. Pellet missing Visual 112, Metal defective Visual 113, Thread (lnrnnned or not full VRunl 114, Protactiva flnlah hadoquate or de
12、fective Visual 116. Surace ._ finish of body at ende, improper Visual 11 Max. Gage 102. Minor diameter of thread, Max. Gage 103. Concentricity of outside diameter with pitch diameter thread Gage 104. Diameter of thread undercut, max. Gage 105. Diameter of body, min. Gage 106. Width of thread undercu
13、t, max. Gage 107. Thickness of base Gage 108. Thread damaged or not full Visual 109. Metal dzfective Visual 110. Protective finish inadequate or defective Visual 111, Bur or sharp corner Visual 112. Foreign matter Visual ; 201. Pitch diameter of thread, min. Minor Gage 4.3.2.13 Tmnnion, DWQ. 0859570
14、0;cover- Eng a detail of Dtug. F859.9687. Critical Major nmhd of Drfect in8pcetion None defined 101, Pitch diameter of sniall thread, ma%. Gage - 102. Minor diameter of small thread, ma. Gage 103. Pitch diameter of large thread, ma. Gage 104. Minor diameter of large thread, mu. Gage 106. Concentrici
15、ty of pitch diameter of large thread with inside diameter Gage 106. Concentricity of inside diameter with pitch diamctsr of smnll thrcud Gago 10% Symmetry of lugs Gage 108. Symmetry of widh across flats at root of lugs with inside diameter Gage 109. True position of lug with inside diameter Gam 110.
16、 Concentricity of luga Gage 7 K- 1 - - -/ Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-118. Length to center of lug Gage 119. Length of effective thread, min, Gage 120. Width across fats at root of lugs Cage 121. Height of lug Measure 122. Thread
17、damaged OF riot full Visual 123, Metal defective Visu:il 124. Prutective finish inadequate os defective Visual 126. Surface finish of inside diameter, improper Visual 126. Bur Visual 127. Foreign inattei. Visual 201. Pitch diameter OP small thread, inin. Gage 202. Pitch diameter of large thread, min
18、. Gage 203. Depth of spiral groove Gage 204. Width of relief of spiral groove Gage 205. Location of groove at small end , Gnge 206, Diameter .of tang hole at spiral groove Me as ur e 207. Length of relief of spiral groove Measure 208. Location of spiral groove . Measure 209. Syminetry of tang hole w
19、ith spiral groove Visual 210. Direction of turn of miral groove, incoriwt Visual 211. Number of turns of spiral groove incorrect Visual 4.3.2.14 Metal Parts A8sernbll.1, Dwu. method of Minor . F8593687. Defect inspectimi Critical Major None deineti 101. Any part missing Visual 102. !mproper assembly
20、 Manualflisual 103. Thread damaged or not full Visual 104. Bur Visual 106. Foreign matter Visual Nono dc9ned Minor 4.3.2.18 Awwniton, Containel., Fibe, Dion. F8707377. Method of Drlect inrpectioic Critical None defined Provided by IHSNot for ResaleNo reproduction or networking permitted without lice
21、nse from IHS-,-,-MILc-3*6943 (MU) jected to the structui.cil strength test. Friilure of any assembly to comply with the require- nmits of 3.7 shall be cause for rejection of the lot. subjected to the specified tension and com- pression loads for determination of compli- ance with the requiremnts of
22、3.7. The test shall be performed as follows: I 4.3.3,5 Brcakcwag torque. A breakaway . torque shall be appiied to each assembly tlireigled joint as listed in table III. Failure of any assembly to. comply with the require- ments af column C table III shall be cause for i*cjcclim of tlic ismrnhly, .i.
23、:l,:Lfi Protective jnsli Tlic number of specimens and acceptance criteria for pro- tcctivs finish tests slinll bo in nccordniicct with tlic nliplicnblc milit:iry stiind:rmi listad on tlic .1,:1,7,7 Itwrlicril nragnct-iwt. E:;ch ;notal pnrts assetnbly siall be tested for excessive residual magnetism.
24、 Failure of any assembly to comply with the requirements of 3.10 shall, be c:itise for rejection of the asseinbly. 4.3.4 Impcction epipntent. The examina- tion and tests shall be made using equipment listed on IEL-8593687, except as provided in MIGI-115208. dn1r iiige. 6 -1.4 Tes iiiethods and proce
25、dures. 4.4,1 Wai.Cl?tcss. Prior to the application of potective finish, ;I Hardness Tester shall be used to deterinine compliance with he liard- ness requirements specified on the detail drawing. 4.4.2 Hgdrosfntic presszcic. Prior to the iipplictition of protective finish, the outside, telcscotring
26、tinct iriside tubes siiall be inouiited in tlie device nnd snbjected to the inteiml liy- . drost:tic pressure, The device used shall in- ter-iiilily seal tlie tube within lvg inches from ench end without applying any axid load other than that applied by the liquid pressure. . (a)-Apply a preload of
27、500 pounds in tension and adjust the dial indica- tor to zero inches. (b) Apply the load in tension so as to move the mounting points away rom ciicii ollier, (e) Reloisc the load in tension to 500 pounds in tension and record the cial indicator rcndivg. Regont (b) :nd (c) . (1) Apply :i pucloiid of
28、500 poiiii(1s in coinpression :irid :idjust tlic .ditil inchtor to zero inclics. (e) Apply the load in compression load so as to move the mounting points toward each other. (f) Release tlie compression load ta 600 pounds in compression and record the dial indicator reading, Repeat (e) and (f), 1.4.5
29、 Protective finish. Test procedures for protective finish shall be in accordance with .the applicriblc military stindnyd referenced on the drawing. 4.4.6 Residual magnetism. The catapult shali be tested for escessive residual magne- tism in an area free of local magnetic effects by placing the catap
30、ult 6 inches from and at th smie height as :in approved compass, in it iortli-soiitk horizoiit;il position (trunnion end at south) with tlie compass set in an east- west heading as shown in Figure 1. The cat- apult shall be moved slowly past the compass in R longitudinal direction for its entire len
31、gth, rotated 180 degrees in the horizontal position aboiit its Iongitudiniil axis and moved - -1A3 Slim?* pz?t styen 5. PREPARATION FOR DELIVERY 6.1 Packing and marking. Packing and marking shall be in accordance with Drawing F8797377 and F8797378. 5.2 Data cards. Data card information shall be as s
32、pecified in MIL-A-2650. - /- o - -. .- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Custodian : Army-MU Preparing activity: Army-MU Project No. 1375-A556 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-u) I 8 C L . p. f =I= 1 i 3- +- I 1 SI . B n- i v1 r( 11 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
