1、Licensed by Information Handling ServicesMIL-A-bOb72 13 79797Ob 0340355 1 9 1-60692 (bu) 3. REQU1P;EMENTS ?.1 General.- Materials. Darts and assemblies shall comlv with the requirements specified on the applicable drawings and referenced specifications. 3.2 Breakaway torque.- All threaded joints of
2、the assembled Actuator shall withstand a breakaway torque application of 200 inch pounds without loosening or deformation. 3.3 Residual magnetism.- The Actuator shall not deflect the indicator of the approved compass more than 3 degrees in either direction when passed in front of the compass at a di
3、stance of 6 inches. 3.4 of the ball screw assembly so that the strap drum component is not free to rotate. Initial lock security.- The lock pin shall secure the piston component 3.5 Functional. 3.5.1 The actuator shall not fail to fire. 3.5.2 The actuator shall function without mechanical failure (S
4、ee 6.1). 3.5.3 Initiation.- The actuator shall be fired by a source delivering an output equal to that of an MX1 Initiator at the end of i5 feet of aircraft hose, Size 4, Standard MS-28741, at TO0 - 3. ?OF. 3.5.4 Ballistics. - The Actuator loaded with an accepted cartridge and temperature conditione
5、d, when fired, shall separate and eject a 400 pound load from the approved aircrafi seat within an operating time of ,150 seconds minimum and 500 seconds maximum, and function within the performance limits specified in Table I. Table I Temperature Pressure (psi) 65 to 75OF 2000 to 4800 Acceleration
6、(g) 0.85 to 3.0 3.6 W0rkmanshi.p.- The requirements for w0rkmanzA-p are as specified on the applicable drawings, referenced specifications and the following: Metal defects.- All components shall be free from cracks, splits, 3.6.1 cold shuts, inclusions, porosity or any similar defects. Licensed by I
7、nformation Handling ServicesLicensed by Information Handling ServicesMIL-A-bob92 13 9999906 0340957 5 MIL-A-60692 (MU) 4.2.2 (Contd) Table II Major Minor Lot Size Sample Size Accept Rej ect Accept Reject i - 300 10% Examination - - I - 301 - 800 50 O 1 1 2 801 - 1,800 90 1 2 2 3 i801 - 10,ooo 200 2
8、3 3 4 4.2.2.1 Cartridge Assembly, Drawing 5000.1 covering a detail of Drawing 1000- 27. Defect Method of Inspection CRITICAL 1. Mixed cartridges Vi sual 2. Metal defective Vi sual 3. Closure cap missing, damaged or improperly sealed Vi sual 4. Marking missing, incorrect or illegible Vi sual MAJOR 10
9、1. Foreign matter Vi sual MINOR 201. 202. Case scratched, wrinkled, bulged or dented Protective finish, missing or inadequate Vi sual Vi sual 4.2.2.2 Assembly, Drawing 1000-27 with end Closure A #lOOO-l32) removed. CRITICAL 1. Lock pin loose 2. 3. Blowout plug loose Be.11 screw and piston assembly l
10、oose 4 Manual/Vi sual Manual Manual/Vi sual Licensed by Information Handling Services4.2.2.2 (Contd) Defect MAJOR Method of Inspection 101. Thread damaged 102, Foreign matter Vi sual Visual MINOR None defined 4.2.2 3 Assembly Drawing 1000-27 with Breech Assembly (Drawing #1022) and back up washer (D
11、rawing #lOl7) removed. CRITICAL 1. Cartridge loose 2. Cartridge Retainer loose 3. Foreign matter in gas port Manual/Vi sual ManualIVi sual Visual MAJOR 101. Thread damaged Vi sual MINOR None defined 4.2.2.4 Assembly Drawing 1000-27. CFUTICAL 1. 2. MAJOR 101. 102 * 104. 105 o 103. 106. Any part missi
12、ng except as otherwise classified Marking missing, incorrect or illegible Length overall Length of strap exbended Length of strap retracted Shear studs loose Cap screw loose Threads damaged Visual Visual Gage Gage Gage Visual temper- ature conditioning chamber at the same time as the actuator sample
13、s. The con- ditioning time shall be a minimum of one hour longer than the time necessary to bring the element contained in the dummy cartridge to the required tempera- ture. 4.3.4.1.1 Upon completion of the required temperature conditioning, each actuator sample shall be ballistically tested within
14、5 minutes after removal from the conditioning chamber. is exceeded. Samples shall be reconditioned if this time 4.3.4.2 Method of testing.- The actuator tested under the conditions speci- fied herein shall be mounted on an aircraft seat in the proper position. In- stall a fixture on the aircraft sea
15、t. The fixture shall be designed to cover at least 8% of the area comprising the bottom and back of the aircraft seat. Removable weights may be incorporated in the fixture so that the weight of the ejected mass can be adjusted from 100 to 400 pounds. Mount an accelerometer on the fixture to record a
16、cceleration of the ejected mass on a line which bisects the angle between the seat bottom and the seat back. A recording system shall be used to determine the amount of time required to eject the mass after actua- tion of the actuator under load conditions. 4.3.4.3 Ballistic test.- Utilize the test
17、fixture specified in 4.3.4.2. Pressure sensitive devices shall be used to measure the pressure The weights shall be installed in the fixture and secured to prevent shifting. An M3A1 initiator or simulated method shall be used to actuate the actuator under test. exerted to actuate the actuator and to
18、 measure the amount of ballistic gas pressure in the actuator during operation. A pressure port shall be installed in the actuator end closure assembly for recording the ballistic gas pressure. 8 4 3.4.1 Temperature conditioning. - Prior to conducting the ballistic test specified in h.3.4.3, the act
19、uator samples shall be subjected to the temperature condition specified in 3.5.4. A simulated actuator loaded with a dum- cart- Licensed by Information Handling ServicesArmy - MU Army - IUIIT Project No. 1377-Al-90 9 Licensed by Information Handling ServicesMIL-A-bOb72 13 m 7777706 03L10763 O m G! E! O N H x % 3 Pi G2 O k w O fz 4 %I m uz a 9 o u 4 h - E 25 2 I O O 3 n *US. GOVERNMENT PRINTING OFFICE: 1967-251-519/6375 10 5 H e w w 2; Pi O Licensed by Information Handling Services
