1、-1IL-P-5238C 29 m 9797706 0384564 5 m MIL-P-5238C 12 September 1974 SUPERSEDING 2 February 1961 MI L-P- 5 2 3 8 B MILITARY SPECIFICATION PUMP, CENTRIFUGAL, FUEL BOOSTER, AIRCRAFT, GENERAL SPECIFICATION FOR This specification is approved for use by all Departments and Agencies of the Department of De
2、fense. 1. SCOPE 1.1 mounted centrifugal type, fuel booster pumps, used for engine feed or transfer. This specification covers the general requirements for aircraft tank 2. APPLICABLE DOCUMENTS 2.1 The following documents of the issue in effect on date of invitation for bids or request for proposal,
3、form a part of this specification to the extent specified herein. SPECIFICATIONS Federal QQ- P- 4 16 Mi lit ary MIL- D- 1000 MIL-W-5088 MI L- P- 53 15 MIL-H-5440 MIL- G- 5572 MI L-T- 5624 MI L-C-6021 MIL-E-6051 MI L- R- 6855 MI L- S- 7742 MI L-V- 7899 MIL- F-8615 MIL-T-8879 . . Plating, Cadmium (Ele
4、ctrodeposited) Drawings, Engineering and Associated Lists Wiring, Aircraft, Selection and Installation of Packing, Preformed, Hydrocarbon Fuel Resistant Hydraulic Systems, Aircraft Types I however, if used in a hermetically sealed enclosure, fungicidal treatment will not be necessary. Materials that
5、 are nutrients for fungi shall not be Where used and not hermetically 3.5.2 Metals. treated to resist corrosion due to fuels, salt fog, or atmospheric condi- tions likely to be met in storage or normal service. tive coating that will crack or scale with age or extremes of climatic and environmental
6、conditions shall be avoided. accordance with FED-STD-151. Metals shall be of the corrosion-resistant type or suitably The use of any protec- Metals shall be inspected in 3.5.2.1 Dissimilar metals. Unless suitably protected against electrolytic corrosion, dissimilar metals shall not be used in intima
7、te contact with each other. Dissimilar metals are defined in MIL-STD-889. 3.5.2.2 Magnesium and copper. not be used in contact with fuel. 3.5.2.3 Cadmium. Cadmium shall not be used in contact with fuel. Where plating is used (not in contact with fuel) it shall be in accordance with QQ-P-416, Type II
8、, Class 2. Magnesium and copper or alloys thereof shall 3.5.2.4 Castings. or MIL-A-21180. 3.5.3 Rubber. Rubber materials shall conform to MIL-P-5315, MIL-R-6855 Class I, MIL-R-25988 or MIL-R-83248. Castings shall be in accordance with MIL-C-6021, Class 1 The minimum acceptable elongation shall be 3
9、percent. 3.6 Design 3.6.1 Lubrication. The pump and motor assembly shall not require any lubri- cation or any other maintenance throughout its service life between overhauls. Any lubricated part shall be a replaceable sealed assembly as approved by the procuring activity. 4 .- . -. Provided by IHSNo
10、t for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-P-5238C 27 M 7777706 0384568 2 MI L-P- 52 38C 3.6.2 Electrical. The electrical equipment shall satisfactorily operate on power in accordance with the air vehicle requirements. The minimum require- ments shall be in
11、accordance with MIL-STD-704. 3.6.2.1 Wiring. All wiring shall be fuel resistant, and, other than windings, shall be in accordance with MIL-W-5088. 3.6.2.2 Electrical fault containment. The pump assembly housing shall be completely capable of containing any internal fault without failure of the housi
12、ng. to the outside of the housing or generate an unsafe condition. tection shall be incorporated to assure that the electric pump assembly is maintained within safe temperature limits under all operating or non-operating conditions. due to electrical heating, shall not exceed 390F or as required in
13、the detail specification. In no case shall an electrical short or internal explosion propagate Thermal pro- The peak temperature for any portion of the outside of the assembly 3.6.2.3 Vent. A vent connected to the electrical motor chamber shall not be connected to the seal drain chamber and shall in
14、corporate a flame arrestor. 3.6.2.4 Electrical insulation resistance. The electrical components shall withstand, without damage, breakdown, or excessive leakage current, repeated applications of AC dielectric test voltage in accordance with the test pro- cedure of Section 4. The insulation resistanc
15、e shall not be less than 100 megohms when exposed to 500 volts DC. The dielectric leakage current shall not exceed 2 milliamperes. 3.6.2.5 Electromagnetic. The equipment shall comply with the requirements of the air vehicle and the applicable requirements of MIL-E-6051. 3.6.3 Inlet. than 8 mesh and
16、no finer than 20 mesh. The flow area shall be sufficient to permit maximum flow with 50 percent of the area blocked when operating at maximum altitude. The inlet to the pump shall be enclosed by a screen no coarser 3.6.3.1 Suction feed. shall be in accordance with the detail specification. The rate
17、of flow and pressure drop under suction feed 3.6.4 Pump drain. A chamber, incorporating a drain port, shall be provided between the shaft seals for the motor and the pump to isolate leakage. drain port configuration and the allowable leakage shall be in accordance with the detail specification. shaf
18、t seals are not used this requirement does not apply. The Wherever the motor and pmp are integral and 3.6.5 Threaded connections. Threaded connections shall comply with MIL-T-7742, MIL-S-8879, MS16142 or MS33649 as applicable. 5 Provided by IHSNot for ResaleNo reproduction or networking permitted wi
19、thout license from IHS-,-,-MIL-P-5238C 3.6.5.1 Pipe threads. closures. Pipe threads shall not be used except for permanent 3.6.6 Locking of parts. All threaded parts shall be locked by safety wiring, or cotter pins in conformance with MS33540 or the use of self-locking nuts in conformance with MS335
20、88 or other approved methods. Wherever loosening of the self-locking nut could possibly result in the nut or other parts entering the fuel system, approval of the installation shall be obtained from the procuring activity. The use of cotter pins on studs, or the use of lockwashers or stak- ing is pr
21、ohibited. 3.6.7 Outlet. The outlet fitting shall utilize couplings in accordance with MIL- C- 22263. 3.6.7.1 Check valve. each pumping unit in accordance with the detail specification in order to prevent any reverse flow of fuel through the pump into the tank. valve shall be capable of satisfying al
22、l applicable performance requirements of MIL-V-7899. (or 5cc per minute at the conclusion of the test program) from 4 inches of fuel head up to 60 psig. 3.6.7.2 Proof pressure. The outlet and check valve(s) shall be capable of withstanding an applied pressure of 120 psig (or higher in accordance wit
23、h the detail specification) without failure or permanent distortion. 3.6.8 operated under negative G conditions or during inverted flight. output under these conditions shall be in accordance with the detail specification. 3.6.9 Start-up. start-up shall be stated in the detail specification. or foll
24、owing the climb of 3.2.3, when a non-operating pump is started, it shall develop the required flow and pressure within 5 seconds after power is applied. 3.6.10 Variations in power input. patibility with all the variations in the aircraft power supply system(s), without overspeed, overheating, stoppi
25、ng, or other failure. The minimum requirements are MIL-STD-704, MIL-H-5440, or MIL-i-8891, as applicable. It is not required that 3-phase electric motors must operate on 2 ?hase power. 3.6.11 Leakage. There shall be no external leakage from the pump assembly except from drains provided for that purp
26、ose. For plug-in pump units, the detail specification shall state the maximum allowable fuel loss during removal and reinstallation in a full fuel tank. A check valve shall be incorporated in the outlet of The check Reverse flow leakage shall not exceed lcc per minute initially Negative G and invert
27、ed operation. The pump shall be capable of being The pump The rate of power input, acceleration, and output during At any point during The pump assembly shall demonstrate com- 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I l MIL-P-523BC 29 99999
28、06 0384570 O I MI L-P-5238C 3.6.12 Pump down. The pump shall be capable of maintaining rated flow and I pressure at any altitude when the head of fuel is no greater than 2 inches above the inlet and the fuel temperature is 65F to 95F. ture fuel, the flow rate, pressure, altitude and fuel head shall
29、be in accordance with the detail specification. to each inlet. of the other inlet in either the normal or the inverted position. at less than the above heads shall be in accordance with the detail specification. With higher tempera- For dual inlet pumps, this requirement applies Performance Uncoveri
30、ng of one inlet shall not deteriorate the performance 3.6.13 Reprime. following a period when the inlet is uncovered and then resubmerged in fuel. This capability shall exist up to the maximum operating altitude of the aircraft. The pump output, depth of submersion and fuel temperature shall be in a
31、ccordance with the detail specification, provided that the fuel temperature.shal1 be no less than 12SF, and depth of submersion of the inlet no greater than 10 inches of fuel. The pump shall be capable of self repriming within 5 seconds 3.6.14 Dry operation. dry operation in cycles of 5 hours each.
32、deterioration in performance or other failure, nor shall it cause a hot spot to develop that could ignite the fuel vapors in the tank. that any portion of the housing in contact with fuel is allowed to achieve is 390F or as required in the detail specification, whichever is lower. The pump shall be
33、capable of accumulating 100 hours of The dry run test shall not cause any The peak temperature 3.6.14.1 Automatic dry cut-off. Where an integral automatic dry cut-off feature is required by the detail specification, it shall be capable of 10,000 cycles of operation without failure or causing degrada
34、tion of pump performance. 3.7 Performance. The pumps shall demonstrate satisfactory performance when subjected to the applicable tests of table I. 3.8 Safety, reliability and maintainability 3.8.1 Safety analysis. complete safety analysis, including the impact of each failure mode, shall be made, in
35、 accordance with MIL-STD-882. All possible failure modes shall be examined and a 3.8.1.1 Proof-of-safety tests. analysis. powered pumps, explosion and fault containment tests; for hydraulic power pumps, overspced and dragging impeller tests; and for all pumps, proof and burst pres- sure tests. speci
36、fication and as approved by the procuring agency. MIL-STD-882 will be applied to the verification tests. Tests shall be conducted to verify the safety The minimum proof-of-safety tests requirements are, for electric Additional tests shall be conducted in accordance with the detail The requirements o
37、f 7 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MILP-5238C 27 W 7797906 038q573 2 W 4 -5.2 4.5.20 4.5.3 4.5.5 MI L-P-5238C xxx x x .x xxx xxx TAB1.E I. First Articlc 1nspcct.ioii Program 8 Dry En:-nce 9 ry Cut-Off Endurancc 10 Contamination Fuel
38、O Examination 1 Insulatim Kcsistancc 2 Break-In Run 3 Calibration :i .&L4 4.5.17 X .6.14.1 4.5.17.1 X 3.1.5 4.5.18 . X 5,2, 3.12 3. h. 3.1 3. :! 3.2.2 11 Altitiide Climb Perforiiincc 12 Pump Down 13 Blocked Inlet Screen 3.2.3 4.5.11 X 3.6.12 4.5.7 X 3.6.3 4.5.6 X - -. 4 Leakage 5 Fuel Kcsistancc 6 C
39、orrosion Resistance 4.5.14 7 Endurance 22 Explosion-Proof 23 High Tcmpcrature Dry Kiiii 24 Locked Rotor 25 Overspeed 26 Dragging Impeller 27 Pressure 28 Thermal Protectors 29 Water in Fue1 30 Icing 31 Disassembly and Inspection 3.6.1.1 4.5.23.1 5.8.1.1 4.5.23.2.1 3.8.1.1 4.5.23.2.2 3.6.1.1 4.5.23.3
40、3.8.1.1 4.5.23.4 3.8. I. 1 4.5.23.5 3.6.2.2 4.5.21 3 .-2.5 4.5.24.2 3.2.4, 3.2.5 4.5.24.3 5. 1 4.5.25 -_ - 14 Reprime 15 Neeativc G 3.6.13 4.5.8 I 3.6.8 I 4.5.9 16 Su&io_n Fecd I 5.6.3.1 17 Vibration 18 Shock 3.7 4.5.13 1 I 19 Fungus Resistance I 3.5.1 . 4.5.15 20 Power iipiit I 3,G. 10 I 4.5.19 I x
41、 21 Eectronaonetic ntcrcrcncc 1 3.6.2.5 I 4.5.22 1 X - X X X X X X X X X X X X X X X NOTES: A) Inspections 1, 2, 3 and 4 sliall be repeated at end of test program prior to disasscnibly. Inspections 5 tlim 12 slinll hc nccomplislicd in the order listcd. A 4th test article is option,?l for sharing the
42、 inspections of test article 3. B) C) 8 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-P-523BC 29 999990b 0184572 4 MIL-P-5238C 3.8.2 Reliability. in the detail specification, as required to satisfy system requirements. 3.8.3 Maintainability. T
43、he maintainability plan shall provide an estimate of maintenance manhours, total clock-hours, and special tools needed for intermediate shop and overhaul maintenance of the pump assembly. 3.9 Interchangeability. All component parts shall be interchangeable between units without selection for fit or
44、performance. by the requirements specified in MIL-STD-100 and the contract. The reliability of the pump to perform shall be stated Part numbering shall be governed 3.10 Nameplate. An aluminum or corrosion resistant steel (stamped or etched) metal nameplate, conforming to MIL-P-15024 shall include th
45、e identification requirements of MIL-STD-130 and the following: PUMP, FUEL BOOSTER, AIRCRAFT Specification MIL-P-5238C Manufacturers Part Number Serial Number 3.11 AGE Control. The assembly date marking shall be in accordance with MIL-STD-1523. 3.12 Workmanship. Workmanship shall be in accordance wi
46、th all applicable specifications, drawings, and quality control plans. 4. QUALITY ASSURANCE PROVISIONS 4.1 Responsibility for inspection. Unless otherwise specified in the contract or purchase order, the supplier is responsible for the performance of all inspec- tion requirements as specified herein
47、. suitable facilities unless disapproved by the Government. the right to perform any of the inspections set forth in the specification where such inspections are deemed necessary to assure supplies and services conform to prescribed requirements. The supplier may use his own or other The Government
48、reserves 4.2 Classification of inspections. shall be classified as follows: a. First Article Inspection The inspection and testing of the pump b. Quality Conformance Inspection. 4.3 First article inspection. all inspections and tests herein. with the detail specification and the procurement document
49、. articles and the order of tests shall be in accordance with table I. The first article inspection shall consist of Any additional tests shall be in accordance The number of test 9 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-P- 5238C 4.3.1 Test report. The test report, covering all details of the First Article inspection shall be prepared in accordance with MIL-STD-831. shall include
