1、MIL-E-O05007E(AS) 1 September 1983 Used in lieu of 15 October 1973 and Superseding 16 January 1979 MIL-E-5007D(?2 jo/iI NAPC-P-79002 NAVY NAVY NAVY NAVY NAVY NAVY NAVY NAVY NAVY MILITARY SPECIFICATION ENGINES, AIRCRAFT, TURBOJET AND TURBOFAN, GENERAL SPECIFICATION FOR This specification is approved
2、for use within . the Department of the Navy only. N A v Y N A v Y NAVY NAVY NAVY NAVY NAVY NAVY NAVY NAVY NAVY NOTE: 1. This limited coordination military specification has been prepared by the Naval Air Propulsion Center (PE21) for the Naval Air Systems Command (AIR-5360D) and is based upon current
3、ly available technical information but it has.not been approved for promulgation as a coordinated revision of MIL-E-5007D. It is subject to modification. However, pending its promulgation as a coordinated military specification, it may be used in acquistion. 2. This limited Coordination military spe
4、cification also supersedes NAPC-P-79002, with Ahendment 1 (Revision 1) which was a previous technical revision of MIL-E-5OO7D and which also was prepared by the Naval Air Propulsion Center. 3. . Numbers in the right margin of this specification are for reference purposes only. THIS DOCUMENT CONTAINS
5、 PAGES r- ? L- ? _.,- . _ L “i“*.“ 1. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-E-005007E 28 m 9999906 OL83590 L m I MIL-E-O05007E( AS) 1 September 1983 Used in lieu of 15 October 1973 and Superseding 16 January 1979 MILkE-5007D NAPC-P-7900
6、2 NAVY NAVY NAVY NAVY NAVY NAVY NAVY NAVY NAVY MILITARY SPECIFICATION ENGINES, AIRCRAFT, TURBOJET AND TURBOFAN, GENERAL SPECIFICATION FOR This specification is approved for use within the Department of the Navy only. NAVY NAVY NAVY NAVY NAVY NAVY NAVY NAVY NAVY NOTE: 1. This limited coordination mil
7、itary specification has been prepared by the Naval Air Propulsion Center (PE211 for the Naval Air Systems Command (AIR-5360D) and is based upon currently available technical information but it has not been approved for promulgation as a coordinated revision of MIL-E-5007D. It is subject to modificat
8、ion. However, pending its promulgation as a coordinated military specification, it may be used in acquistion. 2. This limited coordination military specification also supersedes NAPC-P-79002, with Amendment 1 (Revision 1) which was a previous technical revision of MIL-E-5007D and which also was prep
9、ared by the Naval Air Propulsion Center. 3. Numbers in the right margin of this specification are for reference purposes only. 14 15 16 17 18 19 20 21 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 42 43 45 46 47 48 49 52 53 55 55 58 58 Provided by IHSNot for ResaleNo reproduction or networking permit
10、ted without license from IHS-,-,-SECTION 1 . SCOPE . SECTION 2 . APPLICABLE DOCUMENTS SECTION 3 . REQUIREMENTS SECTION 4 . QUALITY ASSURANCE PROVISIONS SECTION 5 . PREPARATION FOR DELIVERY SECTION 6 . NOTES . TABLES . I to XIV . FIGURES . 1 to 24 . APPENDIX A . REQUIREMENTS FOR PFR APPENDIX B . REQU
11、IREMENTS FOR PR INDEX OF TABLES . INDEX OF FIGURES AND APPENDICES . NLJMERICAL INDEX . ALPHABETICAL INDEX flIL-E-005007E 28 m 999790b 0183591 3 m MIL-E-O05007E(AS) TABLE OF CONTENTS Px 1 1 11 135 145 145 165 187 209 . 213 219 220 222 237 12482 12492 12495 124-98 12500 12502 12504 12506 12508 12510 1
12、2512 12514 12516 12518 12520 12522 12524 i 12490 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NIL-E-005007E28 m 7777706 0143572 5 m MIL-E-O05007E(AS) 5 i 1. SCOPE 1.1 Scope. This specification establishes the performance, operating characteristics
13、, design features, detailed interface configuration definitions and installation envelopes f.or turbojet and turbofan engines. It 2lso establishes the demonstrations, tests, reports, inspection procedures, and other data required for satisfactory completion and acceptance, by the Using Service, of t
14、he Preliminary Flight Rating (PFR) ar?d the Production Release (PR) for the engines. Further, this specification identifies the tests, procedures and data required for satisfactory completion of the Acceptance Test (AT) of production units of either model engine. Notwithstanding the requirements for
15、 test verification of individual points of performance or operating characteristics of the engines covered by this specification for purposes of PFR, PR or AT, the engine manufacturer/contractor shall continue to be fully responsible for all features, characteristics and performance of the engine th
16、roughout the environmental conditions and operating envelope, to the extent required by the applicable contract. This specification also establishes the content and format to be used by the engine contractor for the preparation of the engine specification in accordance with 6.5. 2. APPLICABLE DOCUME
17、NTS 63 i 66 67 69 70 71 72 74 75 77 78 79 80 82 83 85 86 87 89 2.1 Documents. The following documents of the exact issue shown form a part 92 of this specification to the extent specified herein. Each document listed 94 shall be supplemented by only those documents listed within the lower tier of 95
18、 each document and shall apply only to the extent specified in the higher tier 96 document. In the event of conflict between the documents referenced herein 97 0 and the contents of this specification, the contents of this specification 98 shall be considered a superseding requirement. 99 SPECIFICAT
19、IONS FEDERAL TT-S-735 Amendment 2 Standard Test Fluids; Hydrocarbon Ref.-3.7.3.3.6 W-G-1690C MILITARY MIL-G-3056D-2 MIL-E-5007D Amendment 2 Gasoline, Automotive Leaded or Unleaded Ref.-3.7.3.2.3 Gasoline, Automotive, Combat Ref.-3.7.3.2.3 Engines, Aircraft Turbojet and Turbofan, General Specificatio
20、n for Ref.-Cover page note 103 105 107 108 1 o9 112 113 114 117 119 120 121 124 125 126 127 1 12 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I MIL-B-5087B MIL-T-5544B-1 Notice 2 MIL-G-5572F-1 MIL-E-5607F MIL-T-5624L-1 MIL-C-7024C-2 MIL-S-7742B-1
21、Notice 2 MIL-L-7808J MIL-S-8879A-1 Notice 2 MIL-E-O05007E(AS) Bonding, Electrical and Lightning Protection, For Aerospace Systems Ref.-3.7.4.5 Thread Compound, Antiseize, Graphite-Petrolatum Ref.-4.6.2.3.10.1 Gasoline, Aviation: Grades 80/87, 100/130, 115/145 Ref.-3.7.3.2.3 Engine, Gas Turbine, Prep
22、aration for Storage and Shipment of, Process for Ref. -5.1 Turbine Fuel, Aviation, Grades D-4 and JP-5 Ref.-3.2.5.1, 3.2.5.8.1, 3.2.5.8.2, 3.7.3.2.1, 3.7.3.3.3, 37.3.3.4, 4.3.4.3, 4.5.1.2.3, 4.5.1.3.2, 4.5.2.3, 4.5.3, 4.6.1.1.2.3, 4.6.1.1.3.2, 4.6.1.2.2.3, 4.6.1.2.3.2, 4.6.2.2.8, 4.6.2.2.9, 4.6.3, 4
23、.6.3.1.1, 4.6.4.1.2, 4.6.5.3, 4.6.5.4 Calibrating Fluid, Aircraft Fuel System Components Ref.-3.7.3.3.1 Screw Threads, Standard, Optimum Selected Series; General Specification for Ref.-3.3.1.2.6 Lubricating Oil, Aircraft Turbine Engine, Synthetic Base Ref.-3.7.7.2.1; 4.6.3 Screw Threads, Controlled
24、Radius Root with Increased Minor Diameter; General Specification for Ref.-3.3.1.2.6 2 130 131 132 133 136 137 138 141 142 143 146 147 148 149 152 153 154 155 156 157 158 159 160 161 162 163 166 167 168 171 172 173 174 177 178 179 180 183 184 185 186 187 2 9 Provided by IHSNot for ResaleNo reproducti
25、on or networking permitted without license from IHS-,-,-MIL-F-17874B MIL-L-23699C-1 MIL-B-23964C MIL-H-25579D MIL-G-26611C . MIL-H-27267A-3 MIL-I-27686E-2 MIL-C-38373B-1 MIL-C-38999H Supplement 1 MIL-T-83133A Amendment 1 MIL-E-O05007E(AS) Fuel System: Aircraft Installation and Test of Ref.-3.7.3.3.8
26、, 4.6.4.1.3 Lubricating Oil, Aircraft Turbine Engine, Synthetic Base Ref.-3.7.7.2.1, 4.5.1.2.3, 4.5.1.3.2, 4.5.3, 4.6.1.1.2.3, 4.6.1.1.3.2, 4.6.1.2.2.3, 4.6.1.2.3.2, 4.6.3, 4.6.3.1.1, 4.7.2.1.1 Bolt, Self-Retaining, m Positive Locking Ref.-3.3.1.2.1 Hose Assembly, Tetrafluoroethylene, High Temperatu
27、re, Medium Pressure Ref.-3.3.1.1.5 Generator, Tachometer GEU-7/A, Miniature Ref.-3.7.6.6 Hose, Tetrafluoroethylene, High Temperature, Medium Pressure Ref.-3.3.1.1.5 Inhibitor, Fuel System Icing Ref.-3.7.3.2.2, 4.6.4.1.2 Cap, Fluid Tank Filler Ref.-3.7.7.4.1.2 . Connectors, Electrical, Circular, Mini
28、ature, High Density Quick Disconnect (Bayonet, Threaded and Breech Coupling), Environment Resistant, Removable Crimp and Hermetic Solder Contacts, General Specification For Ref.-3.7.4.3.2 Turbine Fuel, Aviation, Kerosene Type, Grade JP-8 Ref.-3.7.3.2.1, 3.7.3.3.3, 3.7.3.3.4, 4.3.4.3 3 5 190 191 192
29、195 196 197 198 199 200 201 202 205 206 207 210 21 1 212 213 2 14 217 218 219 222 223 224 225 228 229 232 233 236 237 238 239 240 241 242 243 244 245 248 249 250 251 12 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NAPC-P-79002 Amendment 1 Revision
30、 1 STANDARDS MILITARY MIL-STD- ,130F MIL-STD-210A . MIL-STD-21 OB MIL-STD-461B MIL-STD-462 Notice 1,2 and Interim Notice 4 MIL-STD-704D MIL-STD-721C MIL-STD-810C Notice 1 Engines, Aircraft Turbojet and Turbofan, General Specification for Ref.-Cover page note, 4.4 Ident ification Marking o U.$. Milit
31、ary Property Ref.-3.3.3.1 f Climatic Extremes for Military Equipment (NOTE-This standard is onlv applicable to Tropical Day Atmosphere on Figure 24). Ref.-Fig. 24 limatic Extremes for Military Equipment Ref.-Fig. 24 Electromagnetic Interference Characteristics, Requirements for Equipment Ref.-3.3.2.
32、1 Electromegnetic Interference Characteristics, Measurement of Ref.-3.3.2.1, 4.5.12.1, 4.6.12.1 Aircraft Electric Power Characteristics Ref.-3.7.4.2, 3.7.4.3.1, 4.5.2.2, 4.6.2.3.2 Definition of Effectiveness Terms for Reliability, Maintainability, Human Factors and Safety Ref.-3.2.4.1 Environmental
33、Test Methods Ref.-4.5.2.2, 4.6.2.3.3 through 4.6.2.3.9 4 2 254 255 256 257 260 262 264 265 266 269 270 271 272 273 274 277 278 279 282 283 284 285 288 289 290 291 292 295 296 297 298 301 302 303 304 305 308 309 31 O 9 Provided by IHSNot for ResaleNo reproduction or networking permitted without licen
34、se from IHS-,-,-MIL-STD-838B MIL-STD-879A MIL-STD-882A MIL-STD-889B Notice 1 MIL-STD-1553B DOD-STD-1686 MIL-STD-1757 MS3325 MS3326 MS3327A MIL-E-O05007E(AS) Lubrication of Military Eqaipmen t Ref“3.7.7.2 Designation of Aircraft Propulsion Gas Turbine - Engines Ref.-6.2.1.63 System Safety Program for
35、 Systems and Associated Subsystems and Equipment, Requirements for Ref.-3.3.6 Dissimilar Metals Ref.-3.3.1.1 Aircraft Internal Time Division Command Response Multiplex Dat.a Bus Ref.-3.7.6.1.2 Electrostatic Discharge Control Program for Protection of Electrical and Electronic Parts, Assemblies and E
36、quipment (Excluding Electrically Initiated Explosive Devices) Ref.-3.7.2 Lightning Qualification Test Techniques for Aerospace Vehicles and Hardware Ref.-3.3.2.3, 4.5.12.3, 4.6.12.3 Drive Pad-Accessory, 2.653 BC Square, Design Standard for Ref.-3.1.2.7 Drive Pad-Accessory; 5.000 BC Square, Design St
37、andard for Ref.-3.1.2.7 Drive Pad-Accessory, 5.000 BC Round, Design Standard for Ref.-3.1.2.7 5 313 314 315 318 319 320 32 1 324 325 326 327 328 331 332 335 336 337 338 34 1 342 343 .344 345 346 347 348 351 352 353 354 355 358 359 360 361 364 365 366 367 370 37 1 372 373 5 12 i Provided by IHSNot fo
38、r ResaleNo reproduction or networking permitted without license from IHS-,-,-2 MS3328A Drive Pad-Accessory, 8.000 BC Round, Design Standard for Ref.-3.1.2.7 379 MS3329A Drive Pad-Accessory, 10.000 BC Round, Design Standard for Ref.-3.1.2.7 382 383 384 385 Recesses-Cross, Low Torque Drive, Dimensions
39、 and Gage Dimensions for Ref:-3.3.1.2.4 388 389 390 391 MS9006C Circular Spline and Adapter Details Engine Driven Accessories Ref.-3.1.2.7 394 395 396 MS14169C MS14184A MS18069A Nonmetallic Shaft-Coupling Details Engine Driven Accessories Ref.-3.1.2.7 399 400 401 Compounds, Adhesive, Aircraft Design
40、 Limitation of Ref.-3.3.1.2.2 435 436 437 438 6 9 -1 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MS33602 MS33649A MS3366C MS33668B MS33750F MS33787C AND20005 Rev. 4 Bolts, Self-Retaining, Aircraft Reliability and Maintainability Design and Usage
41、Requirements for Ref.-3.3.1.2.1 Bosses, Fluid Connection- Internal Straight Thread Ref.-3.7.6.3 Packing, Preformed- Aeronautical Elastomeric, Range of Sizes Ref.-3.3.1.1.3 Packing, Preformed, Elastomeric, Tube Fitting, Range of Sizes Ref.-3.3.1.1.3 Recess-Hi-Torque, Dimensions of Recess, Gage and Dr
42、iver for Ref.-3.3.1.2.4 Wrenching Element, External Spline, Dimensions for Ref.-3.3.1.2.7 Drive-Type XV Engine Accessory Ref.-3.1.2.7 HANDBOOKS MILITARY MIL-HDBX-263 Electrostatic Discharge Control Handbook For Protection of Electrical and Electronic Parts Assemblies and Equipment (Excluding Electri
43、cally Initiated Explosive Devices). Ref.-3.7.2 PUPLICATIONS AIR FORCE-NAVY AERONAUTICAL BULLETIN 441 442 443 444 445 448 449 450 453 454 455 456 459 460 461 462 465 466 467 468 47 1 472 473 476 477 478 480 483 485 486 487 488 489 490 49 1 49 2 495 497 NOT APPLICABLE 7 , 499 12 Provided by IHSNot for
44、 ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-E-005007E 28 m 7777906 0183577 B W NAVAL OPERATION INSTRUCTIONS OPNAVINST The Naval Aviation Maintenance 4790.2B Program Ref.-3.2.4.1 (Copies of specifications, standards, drawings, and publications required by contracto
45、rs in connection with specific procurement functions should be obtained from the procuring activity or as directed by the contracting officer . ) 2.2 Other Publications. The following documents of the exact issue shown form a part of this specification to the extent specified herein. In the event of
46、 conflict between the documents referenced herein and the contents of this specification, the contents of this specification shall be considered a superseding requirement. SOCIETY OF AUTOMOTIVE ENGINEERS AEROSPACE STANDARDS AS 681D Gas Turbine Engine Steady State Performance Presentation for Digital
47、 Computer Programs Ref.-3.2.1.2.1 AS 848 Attachment Points, Engine, Remote Trimming Main Fuel Control Ref.-3.7.2.3.1 AS 870C Wrenching Configuration, Double Hexagon (12- Point), for Threaded Fasteners Ref.-3.3.1.2.7 AS 1132C Bolts and Screws-External Wrenching Unified Threaded Inch Series-Design Par
48、ameters for Ref.-3.3.1.2.7 AEROSPACE RECOMMENDED PRACTICES ARP 492B Aircraft Engine Fuel Pump Cavitation Endurance Test Ref.-4.5.2.3, 4.6.2.2.8 ARP 755A Gas Turbine Engine Performance Station Identification and Nomenclature Ref.-3.2.1.2.1, 6.2.2 2 502 504 a 505 506 51 1 512 513 513 516 518 519 520 5
49、20 523 525 528 530 531 535 536 0 538 542 543 545 549 551 553 556 559 559 561 565 566 568 8 9 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AS 1055B Fire Resistance, Fire Test, and Performance Requirements for Flexible Hose and Rigid Tube Assemblies Ref.-4.5.2.5, 4.6.2.4.5 ARP 1179 Aircraft Gas Turbi
