1、MIL-T-bO24b 13 = 777770b 0432785 T I - * r MIL-T- 60246 (MU) u; U a 21 September 1965 SUPERSEDING c 8 November 1960 C FA-PD-MI-2410, Rev. 1 c 4 +i MILITARY SPECIFICATION THRUSTER, CARTRIDGE ACTUATED, M18, ASSEMBLY 1. SCOPE 1.1 This specification is the applicable detail specification for Thruster, C
2、artridge Actuated, M18, Assembly, loaded with Cartridge, Thruster, M43 for use in conjunction with other cartridge actuated devices in aircrew emergency escape systems. 2. APPLICABLE DOCUMENTS 2.1 tion for bids or request for proposal, form a part of this to the extent specified herein: The followin
3、g documents of the issue in effect on date of invita- specification SPECIFICATION Military MIL-A-2550 - Ammunition and Special Weapons, General Specification For STANDARDS Mil it ary MIL-STD-105 MIL-STD-109 MIL-STD-129 MS-28741 - Sampling Procedures and Tables for Inspec- - Quality Assurance Tem and
4、 Definitions - Marking for Shipment and Storage - Hose Assembly - Detachable End Fitting, tion by Attributes Medium Pressure DRAWINGS Munitions Command F8597514 - Thruster, Cartridge Actuated, M18, Assembly F8597515 - Thruster, Cartridge Actuated, M18, Metal Parts Assembly C8848865 - Container, Ammu
5、nition, Fiber M365 for Thruster, Cartridge Actuated, M18, with Cartridge M43 (see 5.1) C8848864 - Box, Packing, Ammunition for Thruster, Cartridge Actuated, Mi8, with Cartridge M43 in Fiber Container M365 (see 5.1) Cartridge Actuated, Mi.8, Assembly IEL-8597514 - Inspection Equipment List for Thrust
6、er 1-j Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- - NIL-T-60246 13 W 7977706 04327b 1 I 4 MIL-T- 60246 (MU) %- 2.1 (cont.) (Copies of specifications, standards and drawings required by contractors in connection with specific procurement functio
7、ns should be obtained from the procuring activity or as directed by the contracting officer.) 3. REQUIREMENTS 3.1 General.- Material, parts and assemblies shall comply with the requirements specified in the applicable drawings and specifications. 3.2 Torque.- Torque requirements shall be as specifie
8、d in Table I. No movement shall occur upon application of the breakaway torque. Table I Components Seating or Bottoming , (inch pounds) Breakaway (inch pounds ) Head and Body 600 2 20 400 t 20 3.3 Residual magnetism.- The thruster shall not deflect the indica- . tor of a compass more than 3 degrees
9、in either direction when passed in front of the compass at a distance of 6 inches. 3.4 Functional. 3.4.1 The thruster shall not fail to fire. 3.4.2 The thruster shall function without mechanical failure (see 6.1). 3.4.3 The thruster fired in a “locked shut“ condition shall show no mechanical failure
10、 (see 6.1 and 6.2). 3.4.4 The thruster fired with “no load“ on the piston shall function without mechanical failure (see 6.1 and 6.3). The piston shall complete its stroke of 9 1/2 plus or minus 1/16 inches, minimum, and shall not separate from the body of the thruster. 3.4.5 The thruster fired unde
11、r “load“ shall perform as follows: (See 6.4.) 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-T-60246 13 W 7977706 02432787 3 I MIL-T-60246 (MU) 3.4.5.1 The thruster shall be capable of moving a 350-lb. weight horizontally through a distance of
12、 9 1/2 plus or minus 1/16 inches, when fired against a 1 1/2 g resistive force. 3.4.5.2 Ve1ocitv.- The thruster when fired under load shall impart to the weight a velocity that does not exceed 12 ft/sec. 3*4*5*3 Acceleration- The thruster when fired under load shall impart to the weight an accelerat
13、ion that does not exceed 5 g/sec. 3.4.5.3.1 Rate of channe.- The thruster when fired under load shall impart to the weight an acceleration where the rate of change of accelera- tion does not exceed 60 g/sec. 3.4.6 Temperature.- The thruster shall comply with all the ballistic requirements throughout
14、 the temperature range of minus 65 degrees to plus 160 degrees F. 3.4.7 Initiation.- The thrustershall be initiated with an M3A1 Initiator connected to the thruster with 15 feet of aircraft hose, size 4, Standard MS-28741. 3.5 Workmanship.- The requirements for workmanship are as specified on the ap
15、plicable drawings, referenced specifications and the following: 3.5.1 Metal defects.- All components shall be free from cracks, splits, cold shuts, inclusions, pormity or other metal defects. 3.5.2 Burr.- No part shall have a burr which might interfere with the assembly or function of the item or wh
16、ich might be injurious to personnel handling the item. 3.5.3 Foreign matter,- No part or assembly shall contain chips, dirt, grease, rust, corrosion or other foreign matter. 4. QUALITY ASSURANCE PROVISIONS 4.1 Responsibility for inspection.- Unless otherwise specified in the contract or purchase ord
17、er, the supplier is responsible for the perform- ance of all inspection requirements as specified herein. otherwise specified, 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 se
18、t forth in the specification where such inspections are deemed necessary to assure supplies and services conform to prescribed requirements. Except as 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1 MIL-T-bO2LIb 13 m 7779706 OLI32788 5 I MIL-T-60
19、246 (MU) 4.1.1 Quality assurance terms and definitions.- Reference shall be made to MIL-STD-109 to define the quality assurance terms used. 4*1.2 Inspection.- Inspection shall be in accordance with MIL-A-2550, except as specified herein. 4.2 Inspection provisions. 4.2.1 Lot. 4.2.1.1 Submission of pr
20、oduct.- The product shall be submitted in accordance with MIL-STD-105. 4.2.1.2 Size of lot.- A lot shall consist of an identificable group of assembled units containing metal parts assemblies produced by a homogene- ous process and loaded with a single lot of cartridges. 4.2.2 Examination.- One hund
21、red percent examination shall be performed for all critical defects. be performed on a defect basis in accordance with the classification of defects contained herein, using the sampling plan and associated criteria in Table II. The total number of allowable defects per class for either the major or
22、minor classification shall not exceed the acceptance number of Table II. All nonconforming material shall be rejected. Four power (4X) . magnification may be used in performing visual examination for such defects as burr and foreign matter. Examination for major and minor defects shall Table II Majo
23、r Minor Lot Size Sample Size Accept Reject Accept Reject 1 - 300 100% Examination 301 - 800 50 O 1 801 - 1800 90 1 2 1 2 2 3 4.2.2.1 Cartridge, Thruster, M43, Drawing D8593275 covering a detail of Dwg. F8597514, Defect CRITICAL 1. Mixed cartridges 2. Metal defective 3. Marking missing, incorrect or
24、illegible MAJOR 101. Foreign matter 4 Method of Inspection Visual Visual Visual Visual Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-T-602Ll6 13 7777706 0432787 7 MIL-T-60246 (Mu) 4.2.2.1 (Cont.) Defect MINOR 201. Case scratched, wrinkled, bulg
25、ed or 202. Varnish missing or inadequate dented Method of Inspection Visual Visual 4.2.2.2 Head Subassembly, consists of: Head F8597503, Firing Pin C8597504, Shear Pin B8597505, O-Ring MS-28775-012 and Screw MS-51017-33 covering a detail of Dwg. F8597515. CRITICAL None defined. M4 JOR 101. Thread da
26、maged 102. Burr 103. Foreign matter Visual Visual Visual MINOR 201. “0“ ring not lubricated Visual Visual 202. Set screw not filled with sealing compound 4.2.2.3 Assembly, Drawing F8597514 less Cartridge D8593275 and Head F8597503. CRITICAL 1. Evidence of fluid leakage MAJOR 101. Burr 102. Foreign m
27、atter MINOR 201. Varnish missing or inadequate Visual Visual Visual Visual 4.2.2.4 Assembly, Drawing F8597514, less Shipping Cap B8593297, CRITICAL 1. 2. Mixed cartridges Shear pin not engaged in firing pin MAJOR 101. Total length 102. Thread damaged 103. Burr 104. Foreign matter Gage Visual Gage Vi
28、sual Visual Visual 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-T-60246 13 W 7777706 0432770 3 W MIL-T- 60246 (MU) 4.2.2.4 (Cont.) Defect MINOR 201. Protective finish inadequate or 202. Set screws above flush defective 4.2.2.5 Assembly, Draw
29、ing F8597514. CRITICAL 1. Improper assembly 2. MAJOR Any missing part as detected by x-ray 101. Thread damaged 102. Marking missing, incorrect or illegible 103. Foreign matter MINOR 201. Shipping cap missing 202. Protective finish inadequate or defective 203. Varnish or marking missing 4.2.2.6 Fiber
30、 Container, Drawing C8848865. CRITIC AL None defined. MAJOR None defined. MINOR 201. 202. 203. 204. 205. 206. 207. 208. Cap between body and cover, max. Contents loose Metal ends loose or distorted Cut or damaged through all impregnated Marking missing, incorrect or illegible Tape incomplete or badl
31、y wrinkled Length of tear tab, min. Color of tape incorrect layers 4,2.2.7 Box, Packing, Drawing C8848864. CRITICAL None defined. Method of Inspection Visual Visua 1 X- Ray X-Ray Visual Visual Visual Visual Visual Visual Manua 1 Manual Manual Visual Visual Visual Visual Visual MAJOR None defined, 6
32、Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-T-6024b 13 777770b OL13277L 5 M D 4.2.2.7 MINOR 201. 202. 203. 204. 205. 206. 207. 208. (Cont. ) Contents loose Hardware missing, loose, broken or improperly engaged Strapping missing, loose, broken
33、 or improperly assembled Contents of box exposed Box damaged Marking misleading or unidentifiable Number of units incorrect Car seal missing, unsealed or improperly pos it ioned MIL-T-60246 (MU) Method of Inspection Manual Visual and Manual Visual and Manual Visual Visual Visual Visual Visual 4.2.3
34、Inspection testing.- The following tests shall be performed in accordance with 4.3: 4.2.3.1 Breakaway torque.- Each head and body assembly shall be subjected to a breakaway torque application. comply with the requirements of 3.2 and Table I shall be cause for rejection of the assembly. Failure of an
35、y assembly to 4.2.3.2 Residual magnetism.- Each thruster shall be subjected t the test for excessive residual magnetism. with the requirement of 3.3 shall be cause for rejection of the thruster. Failure of any thruster to comply 4.2.3.3 Functional tests.- The following tests shall be performed by th
36、e Government : 4.2.3.3.1 Ballistics.- Twenty-three units shall be tested in accordance with Table III to determine compliance with the requirements of 3.4.1 through 3.4.7. The units shall be temperature conditioned as provided in 4.3.3.1. for rejection of the lot. Failure of any unit to comply with
37、the requirements shall be cause Table III Sample Size Method (weight, wt . ) Temperature 7- Load with 350 lb. wt. and 525 lb. had with 350 lb. wt. and 525 lb. 7- restraining force (see 3.4.5.1) 160“ to 165F. Load with 350 lb. wt. and 525 lb. 7- restraining force (see 3.4.5.1) 65“ to 75F. restraining
38、 force (see 3.4.5.1) -65“ to -70F. 1- 1- No load Locked shut 160“ to 165F. 160“ to 165F. 7 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-T-602q6 13 = 9999706 0432972 7 ? MIL-T-60246 (MU) 4.2.4 Inspection equipment.- The examination and tests sh
39、all be made using equipment listed on BL-8597514. 4.3 Test methods andprocedures. 4.3.2 Residual magnetism.- The thruster shall be tested for excessive residual magnetism in an area free of local magnetic effects by placing the thruster 6 inches from and at the same height as the compass, in a north
40、-south horizontal position (cap end at south) with the compass set in an east-west heading as shown in Figure 1. The thruster shall be moved slowly past the compass in a longitudinal direction for its entire length, rotated 90 degrees in the horizontal position about its longitudinal axis and moved
41、slowly back past the compass. This procedure shall be repeated for each 90-degree rotation of the thruster. 4.3.3 Functional tests. 4.3.3.1 Ballistics.- The sample shall be temperature conditioned in accordance with Table III and the following: 4.3.3.1.1 Upon completion of the required temperature c
42、onditioning, the sample shall be ballistically tested within 10 minutes after removal from the conditioning chamber. time is exceeded. When reconditioning thrusters at minus 65 degrees F., all condensation shall be removed from the interior surfaces before returri- ing the thruster to the conditioni
43、ng chamber. Samples shall be reconditioned if this #- 4.3.3.1.2 Temperature conditioning time.- A simulated thruster and cartridge with a temperature sensitive element inserted in the dummy cartridge shall be placed in the temperature conditioning chamber at the same time as the thruster. one hour l
44、onger than the time necessary to bring the element contained in the dummy cartridge to the required temperature. The conditioning time shall be a minimum of 4.3.4 Method of testing.- The thruster tested under the conditions as specified herein. shall be mounted so that the weight will be propelled h
45、orizontally when fired, and supported rigidly so that the entire thrust will be borne by the thruster mounting points. recording system shall be used the moving weight in the ballistic testing of any thruster under “load“ condition. A velocity and acceleration to determine velocity and acceleration
46、of 4.3.4.1 The following method for determining ballistic performance of thrusters has proven satisfactory. The thruster is clamped in a test fixture with piston end mounted against a horizontal carriage on wheels. The carriage is guided along and impact energy of moving carriage is absorbed by a sh
47、ock absorbing device mounted at end of track. measurements are taken with an electrically wired board to record a travel- time relationship by means of breaking carbon contacts. measurements are taken by means of an accelerometer. Velocity Acceleration 8 Provided by IHSNot for ResaleNo reproduction
48、or networking permitted without license from IHS-,-,-MIL-T-60246 13 m 7977706 0432773 7 m * * MIL-T-60246 (MU) 4.3.4.2 Upon completion of ballistic tests, any thruster fired under “locked shut“ condition, shall be disassembled at the cartridge end of the thruster and examined to determine that the c
49、artridge has functioned properly. 5. PREPARATION FOR DELIVERY 5.1 Packing and marking - Level A.- Packing and marking shall be in accordance with Drawings C8848864 and C8848865. Data cards.- Data card information shall be as specified in 5.2 MIL-A-2550. 6. NOTES 6.1 A “mechanical failure“ is defined as any deformation or breakage of a part, the occurrence of which is other than a design function. 6.2 %ocked shut“
