1、Y 4. MIL-C-46395 13 = 7997906 0464260 5 I MIL-(;r-p6395(Mu) 5 MARCH 1964 SUPERSEDING 28 DECEMBER 1960 FA-PD-MI-2387, REV. 1 MILITARY SPECIFICATION CATAPULT, AIRCRAFT EJECTION SEAT, M9 ASSEMBLY 1. SCOPE 1.1 This specification covers Catapult, Air- craft Ejection Seat, M9, Assembly for use in conjunct
2、ion with other propellant actuated devices in aircrew emergency escape systems. 2. APPLICABLE DOCUMENTS 2.1 The following documents of the issue in effect on date of invitation for bids or re- quest for proposal, form a part of the specifi- cation to the extent specified herein; SPECIFICATIONS MILIT
3、ARY MIL-A-2550 -Ammunition and Special Weapons, General Specification for. MILI45208 -Inspection System Re- quirement s. STANDARDS MILITARY MIL-STD-105 -Sampling Procedures and Tables for In- spection by Attri- butes. MIMTD-109 -Quality A s s u r a n c e Terms and Defini- tions. -H o s e Assembly-De
4、- tachable End Fit- ting, Medium Pres- sure, MS-28741 DRAWINGS MUNITIONS COMMAND F8596866 -Catapult, Aircraft Ejec- tion Seat, M9, Assem- bIy. C8826679 -Container, Ammunition, Fiber, M424 for Cata- pult, M9. C8826680 -Box, Packing, Arnmuni- tion, for Catapult, M9 in Fber . Container, M424. IEL-85968
5、86 -Index o f I n s p e c ti o n Equipment List for Catapult, Aircraft Ejection Seat, M9, Assembly. (Copies of specifications, standards and drawings required by suppliers in connection with specific procurement functions should be obtained from the procuring activity or as directed by the contracti
6、ng officer.) 3. REQUIREMENTS 3.1 General. Materials, parts and assemblies shali comply with the requirements specified on the applicable drawings, referenced speci- fications and the following: 3.2 Torque. Torque shall be as specified in Table I. No loosening or deformation shall oc- cur upon applic
7、ation of the breakaway torque. 3.3 Residual magnetism. The assembled catapult shall not deflect the indicator of the compass more than 3 degrees in either direc- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Y 7u MIL-C-4b395 13 W 997770b 04b42bL 7
8、I . I,. , ti . , NIGC-46395 (MU) . ;t. , : . . ?, Components Seating or bottoming (inch-pounds) Breakaway (inch-pounds) (minimum) - . Breech, Launcher and Tube, Launcher. 500+50. 400 Trunnion and Tube, Launcher 400+50 200 (Applied between trunnion and motor tube head.) Temperature -65“ to -70“ F 65“
9、 to 76“ F. 160“ to 166“ F. - Temperature -66“ to -70“ F 66“ to 76“ F. 160“ to 166“ F. Acceleration maximum 20.0g. . I . . I . . a . * 20.0g. 2o.og. TABLE II. Booster section Rate of change of Acceleration-time Catapult ignition acceleration maximum Launch time maximum integral minimum delay maximum
10、(see 63) (see 6.4) (see 6.5) (see 6.2) 300 g/sec . 240 Millisec . 0.8 g. sec . 60 Millisec. 300 g/sec. 190 Millisec . 1.0 g. sec 60 Millisec. 300 g/sec., . 170 Millisec 1.2 g. sec 60 Millisec. TABLE III. Rockst section Pressure-time Rocket ignition Pressure maxlmum Pressurization rate Action time ma
11、ximum integral. minimum delay maximum (pi) maximum (see 6.7) (see 6.8) (see 6.9) (see 6.6) 4600 100 psi/Millisec 400 Millisec 560 psi. sec . 50 Millisec. 4600. . 100 psi/Millisec 360 Millisec . 560 psi, sec., . 12 Millisec, 4600 100 psi/Millisec 300 Millisec . 560 psi. sec . 12 Millisec. tion when p
12、assed in front of the compass at a distance of 6 inches. 3.4 Functional. 3.4.1 Ballistics. The catapult, loaded with acceptable explosive components, shall func- tion without mechanical failure (see 6.1). 3.4.1.1 Booster section. The booster section shall propel a 360 pound mass and shall com- ply w
13、ith the requirements of table II. 3.4.1.2 Rocket section. The rocket section shall comply with the requirements of table III. 3.5 Workmanship. The requirements for workmanship are as specified on the applica- ble drawings, referenced specifications and the following: 3.5.1 Metal defects. All compone
14、nts shall be free from cracks, splits, cold shuts, inclusions, porosity or any similar defect. 3.5.2 Buw. No part shall have a burr which might interfere with the assembly or func- tion of the item or which might be injurious to personnel handling the item. 3.5.3 Foreign matter. No part or assembly
15、shall contain chips, dirt, grease, rust, corro- sion or other foreign matter. 4, QUALITY ASSURANCE PROVISIONS 4.1 Responsibility for inspection. Unless otherwise specified in the contract or pur- chase order, the supplier is responsible for the performance of all inspection requirements as specified
16、 herein. Except as otherwise speci- fied, the supplier may utilize his own facilities or any commercial laboratory acceptable to the Government, The Government reserves the right to perform any of the inspections set forth in the specification where such inspec- tions are deemed necessary to assure
17、supplies I - 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-and services conform to prescribed require- ments. 4.1.1 Quality assurunce terms and de%:. .Visual. 4. Voids in wrapping .Visual. 101, Foreign matter . .Visual. Defeat Metho of inspection
18、 Major: Minor: None defined. 4.2.2.5 Assembly, Dwg. F8596866, less all Dwgs. except F8596873, F8596902, and Stad- ars MS-16997-80, MS-28513-19, and M Dlog. F8596866, less a# Dwgs, exaept F8596878, D85M87.4, F8596893, F86$6901;:E8596902, C8596903, B8596908, 08596916, C8597864,4859792?4, F10524201 am$
19、. StanahTds MS-1 SSgl-iiSO, MS-1 6997430, .MS-29518-1 9, MS-29518-228 and MS-353.97-42. Critical: :. Major: : I. Defect . Meulod of insmctiot, I,# improper assembiy . .I . I., i .visuai. 2. Any part missing . .Visual. . :. 101. +. Gngth from. face,of cylinder ta face of gr except F8596905, and Stan
20、“O“ ring missing i . .Visual. 3. Major: i 101; Burr . ;. .:. . .i .: . .Visual. Minor: None defined. 4 .- Nozzle cups missing or loose ; ManuaVVisu+ . . 102. Foreign matter . i. . , . .Visuai. . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I J I M
21、IL-C-Yb375 13 m 777770b 0964264 2 m MIIcC46395 (MU) 4.2.2.8 Assembly, Dwg. F8596866, less all Dwgs. except 38596873, D85968?4, F10524201, F8596893, F8596901, F8596902, C8596903, F8596905, B8596908, 0859691 6, F8596917, D- 8596919, 138597584, F8597595, C8597664, A8597934, F8597935, F8597936 and Stan
22、Length. from centerline of mounting hole to centerline of lugs . .Gage. 103: . Lead seal and wire assembly missing or improperly assembled . .Visual. 201. Location of labels, incorrect . .Visual. 2U2, . Varnish missing or inadequate .Visual. 1. Improper assembly . Visual. Major : Mi&!,*. . 4.2.2.12
23、Contaiwq Ammunition, Fiber, M424 for Catapt&, M9, Dwg. (38836679. Critical: None defined. Major: None defined. Minor : 201. Gap between body and cover, maximum . .Manual. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I - MIL-C-46395 13 797990b 04b4
24、2b5 4 7 O MIL446395 (MU) Defect Method of inspection 202. Contents loose .Manual. 203. Metal ends loose or distorted . .Manual. 204. Cut or damaged through all impregnated layers . .Visual. 205. Marking. missing, incorrect or illegible .Visual. 206. Tape incomplete or badly wrinkled .Visual. 207, Le
25、ngth of tear tab, minimum .Visual. 208. Color of tape incorrect .Visual. 4.2.2.13 Box, Packing, Ammunton, for Catupult, M9 in Fiber Container, M42.4, Dwg. C- 8826680. Critical: None defined. Major: None defined. Minor: Defect Method of iwpectioit 201. Contents loose .Manual. 202. Hardware missing, l
26、oose, broken or improperly engaged . .Visuai/Manual. 203. Strapping missing, loose, broken or improperly assembled . .Visual/Manual. 204. Contents of box exposed .Visual. 205. Box damaged . .Visual. 206. Marking missing, incorrect or illegible .Visual. 207. Number of units incorrect .Visual. 208. Ca
27、r seal missing, unsealed or improperly positioned .Visual. 4.2.3 Iwpectzon testing. The following tests shall be performed in accordance with 4.3, except as provided in Specification MIL-I- 46208. 4.2.3.1 Breakaway torque. A breakaway torque shall be applied to each catapult threaded joint in 3.2. F
28、ailure of any catapult to comply with the requirement of 3.2, table I shall be cause for rejection of the catapult. 4.2.3.2 “O” fing secuhtg. Each subassem- bly consisting of valve shear pins (8696901), slider valve piston (8696902), slider vdve cylinder and booster tube assembly (8596893), loaded s
29、trip holder assembly (8696873), “O” rings (MS-29613-19), cap screws (MS-16997- 30) and washers (MS-35337-42) shall be sub- jected to the nitrogen gas test to determine that the “O” rings are properly installed and undamaged. Any subassembly showing evi- dence of leakage shall be cause for rejection
30、of the subassembly. 4,2.3*3 Re& magrteth. Each catapult shall be tested for excessive residual magne- tism. Failure of any catapult to comply with the requirements of 3.3 shall be cause for re- jection of the catapult. 4.2.3.4 Functional. The following tests shall be performed by the Government: 4.2
31、.3.4.1 BaWistZcs. Twenty-one units shall be tested to determine compliance with the requirements of 3.4. The units shall be tem- perature conditioned as provided in table V and 4.3.4.1.1. Failure of any unit to cornply with 3.4 and tables II and III shall be cause for rejection of the lot. 4.2.4 Ins
32、pection equipment. The examina- tion and tests shall be made using equipment listed on IEL-8596886, except as provided in Specification MILI-45208. 4.3 Test methods and procedures. 4.3J Breakaway torque, A torque wrench set at the torque requirements specified in 3.2, table I shall be used to determ
33、ine the ade- quacy of the joints. The assembly shall be se- cured in the fixture prior to application of the torque. 4.3.2 “O” ring secur& The subassembly shall be mounted in the device, using the fix- ture for properly sealing all openings. Nitro- geh gas shall be injected to a gressure of 200 psi,
34、 minimum, and held for i6 seconds, mini- mum, to determine security of the “O” ring seals. 4.3.3 Residual magnetkm. The catapult. shall be tested or excesshe residual mag- ./- - 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- * MIL-C-4b395 13 7799
35、9Ob 04b42bb b Temperature -65” to -70” F. 65” to 75” F. l” to 165” F. TABIE V. Sample sire 7 7 7 netism in an area free of local magnetic ef- fects by placing the catapult 6 inches from, and at the same height as, the compass in a north-south horizontal position with the com- pass set in an east-wes
36、t heading as shown in figure 1. The catapult shall be moved slowly past the compass in a longitudinal direction for its entire length, rotated 180 degrees in the horizontal position and moved slowly back past the compass. 4.3.4 Fumtonul. 4.3.4.1 Ballistics. The test sample shall be rigidly supported
37、 in the fixture. The sample shall be tested within 10 minutes after re- moval from the temperature conditioning chamber. When this test limit is exceeded, the sample units shall be reconditioned at the original temperatures. 4.3.4.1.1 Temperature conditioning. A standard M9 Catapult, loaded with dum
38、my explosive elements, shall be placed in the con- ditioning chamber at the same time as the samples. The conditioning time shall be a min- imum of one hour longer than the time neces- sary to bring the element contained in the dummy explosive components to the required temperature. 4.3.42 Method of
39、 testag. The catapult shall be fired by an M3A1 Initiator connected to the catapult with 10 feet of aircraft hose, size 4, Standard MS-28741 to determine com- pliance with 3.4 and tables II and III. The head of the catapult shall be statically sup- ported, and the weight shall be attached to the mou
40、nting lugs of the launcher and al- lowed to move freely. A 30 cps accelerometer shall be mounted on the mass to obtain the performance curve of the booster section. The head shall be fitted with a pressure cell to obtain the performance curve of the rock- et section. MIGC-46395 (MU) 5. PREPARATION F
41、OR DELIVERY 5.1 Packing and marking, (Level A) Pack- ing and marking shall be in accordance with Drawings C8826679 and C8826680. 5.2 Data cards. Data card information shall be as specified in Specification MIL-A-2550. 6. NOTES 6.1 A “mechanical failure” is defined as any deformation or breakage of a
42、 part, the occur- rence of which is other than a design func- tion. 6.2 “Catapult ignition delay” is defined as the time that elapses between the firing of the catapult primer (to) and the beginning of the continuous rise (ti) on the acceleration time record (see fig 2). 6.3 “Rate of change of accel
43、eration” is de- fined as the maximum positive slope of the acceleration-time record measured over any 30 milliseconds between the continuous rise (ti) and the maximum acceleration on the ac- celeration-time record (see fig 2). 6.4 “Launch time” is defined as the time between the beginning of the con
44、tinuous rise (tl) and the sudden drop (b) on the accelera- tion-time record (see fig. 2). 6.5 “Acceleration-time integral” is defined as the area under the acceleration-time record bounded by the launch time” limits (see fig. 2) 6.6 “Rocket ignition delay” is defined as the time between the sudden d
45、rop (h) on the acceleration-time record of the booster sec- tion and the point at which the pressure-time record of the rocket section reaches 500 psi (ta) (see fig. 2). 6.7 “Pressurization rate” is defined as a maximum positive slope of the pressure-time record measured over any 30 milliseconds be-
46、 tween the point at which the pressure reaches 500 psi and the maximum pressure (see fig. 2) 6.8 “Action time” is defined as the time be- tween the points where the pressure reaches 500 psi (t3) at the start of burning and the Provided by IHSNot for ResaleNo reproduction or networking permitted with
47、out license from IHS-,-,-?- MIL-C-46375 13 W 9999906 0464267 .s MICM6395 (RIIT) point where the pressure fails below 1000 psi 6.9 “Pressure-time integral” is defined as (t4) at the end of burning on the pressure- the area under the pressure-time record time record (see fig. 2). bounded by the action
48、 time limits (see fig. 2). Custodian: Army-MU Preparing activity: Arm y-MU Project No. 1375-A604 . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2 .- 3. , ?. . . I_ a Q). O a o- k: 3. -. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-u MIL-C-4b375 13 m 779 3 s tli U 2 E 7 2 O N a I a io a I l Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
