NSN 5990-00-503-0594
Part Details | CONTROL TRANSFORMER SYNCHRO
5990-00-503-0594 A synchro consisting of a stator and rotor inductively coupled. The electrical output of the rotor is dependent upon both the position of the rotor and the electrical input to the stator from a transmitter synchro or a differential synchro. Does not include variable resistors, goniometers, or variable transformers.
Alternate Parts: 7411398P1, 23231B, 2323-1B, MILS2335TYPE1HCTM, 1CTMK5, 1HCT, MILS2335 TYPE 1HCTM1, MILS2335, 255711, TYPE1HCTMK11, S2407H3229853 PIECE 20, 255711, L2210401, L221040-1, 5990-00-503-0594, 00-503-0594, 5990005030594, 005030594
| Supply Group (FSG) | NSN Assigned | NIIN | Item Name Code (INC) |
|---|---|---|---|
| 59 | JAN 01, 1963 | 00-503-0594 | 15289 ( SYNCHRO, CONTROL TRANSFORMER ) |
REFERENCE DRAWINGS & PICTURES
STANDARD ROUND, REAR MOUNTING FLANGE
1 Y-ROTOR, 1 STATOR
Cross Reference | NSN 5990-00-503-0594
| Part Number | Cage Code | Manufacturer |
|---|---|---|
| 7411398P1 | 24446 | GENERAL ELECTRIC COMPANY |
| 2323-1B | 55972 | HONEYWELL INTL INCDEFENSE AVIONICS SYSTEMS |
| MILS2335TYPE1HCTM | 83149 | JEANNETTE CORP |
| 1CTMK5 | 56232 | LOCKHEED MARTIN CORPORATIONDBA LOCKHEED MARTIN |
| 1HCT | 81349 | MILITARY SPECIFICATIONSPROMULGATED BY MILITARY |
| MILS2335 TYPE 1HCTM1 | 81349 | MILITARY SPECIFICATIONSPROMULGATED BY MILITARY |
| MILS2335 | 81349 | MILITARY SPECIFICATIONSPROMULGATED BY MILITARY |
| 255711 | 10001 | NAVAIR AND NAVSEA MANAGEDORIGINAL DESIGN ACTIVITY DWG NOT |
| TYPE1HCTMK11 | 53711 | NAVAL SEA SYSTEMS COMMAND |
| S2407H3229853 PIECE 20 | 80064 | NAVAL SHIP SYSTEMS COMMAND |
| 255711 | 49956 | RAYTHEON COMPANYDBA RAYTHEON |
| L221040-1 | 06845 | RAYTHEON COMPANYDBA RAYTHEON |
Technical Data | NSN 5990-00-503-0594
| Characteristic | Specifications |
|---|---|
| BODY SIZE | 23 |
| STATOR INPUT VOLTAGE RATING IN VOLTS | 90.0 NOMINAL |
| STATOR INPUT CURRENT RATING | 24.0 MILLIAMPERES NOMINAL |
| STATOR INPUT ELECTRICAL POWER RATING | 58.0 MILLIWATTS NOMINAL |
| FREQUENCY IN HERTZ | 60.0 NOMINAL |
| ZRO RESISTANCE IN OHMS | 596.00 NOMINAL |
| PLUS J ZRO REACTANCE IN OHMS | 1930.00 NOMINAL |
| ZSO RESISTANCE IN OHMS | 1000.00 NOMINAL |
| PLUS J ZSO REACTANCE IN OHMS | 3040.00 NOMINAL |
| ZRS RESISTANCE IN OHMS | 850.00 NOMINAL |
| PLUS J ZRS REACTANCE IN OHMS | 310.00 NOMINAL |
| ROTOR DC RESISTANCE IN OHMS | 435.00 NOMINAL |
| STATOR DC RESISTANCE IN OHMS | 930.00 NOMINAL |
| TRANSFORMATION RATIO | 0.735 ROTOR TO STATOR NOMINAL |
| PHASE SHIFT ANGLE IN DEG | 14.000 OUTPUT TO INPUT NOMINAL |
| MAXIMUM TEMP RISE | 3.0 DEG CELSIUS |
| MAXIMUM TOTAL NULL VOLTAGE OUTPUT IN MILLIVOLTS PER VOLT | 60.00 |
| ELECTRICAL ERROR ANGULAR RANGE IN MINUTES | M18.0/P18.0 |
| BODY STYLE | STANDARD ROUND, REAR MOUNTING FLANGE |
| SHOULDER DIAMETER | 1.2500 INCHES NOMINAL |
| PILOT DIAMETER | 1.0625 INCHES NOMINAL |
| SECOND SHOULDER DIAMETER | 1.9000 INCHES NOMINAL |
| SECOND SHOULDER LENGTH | 0.7000 INCHES NOMINAL |
| OVERALL LENGTH | 3.7330 INCHES MAXIMUM |
| FLANGE DIAMETER | 0.2480 INCHES MINIMUM AND 0.2500 INCHES MAXIMUM |
| FLANGE THICKNESS | 0.2500 INCHES NOMINAL |
| BODY DIAMETER | 0.1950 INCHES NOMINAL |
| PILOT LENGTH | 0.1250 INCHES NOMINAL |
| SHOULDER LENGTH | 0.0550 INCHES NOMINAL |
| SECOND SHOULDER FACE TO REAR FLANGE DISTANCE | 1.7000 INCHES NOMINAL |
| ALIGNMENT HOLE DEPTH | 0.1560 INCHES NOMINAL |
| ALIGNMENT HOLE BOLT CIRCLE DIAMETER | 0.8440 INCHES NOMINAL |
| ALIGNMENT HOLE QUANTITY | 3 |
| TERMINAL TYPE AND QUANTITY | 6 SCREW |
| TERMINAL LOCATION | REAR |
| BODY MATERIAL | ALUMINUM |
| TEST DATA DOCUMENT | 81349-MIL-S-2335 SPECIFICATION (INCLUDES ENGINEERING TYPE BULLETINS, BROCHURES,ETC., THAT REFLECT SPECIFICATION TYPE DATA IN SPECIFICATION FORMAT; EXCLUDES COMMERCIAL CATALOGS, INDUSTRY DIRECTORIES, AND SIMILAR TRADE PUBLICATIONS, REFLECTING GENERAL TYPE DATA ON CERTAIN ENVIRONMENTAL AND PERFORMANCE REQUIREMENTS AND TEST CONDITIONS THAT ARE SHOWN AS "TYPICAL", "AVERAGE", "NOMINAL", ETC.). |
| SHAFT END PLAY | 0.0150 INCHES MAXIMUM |
| SHAFT MAXIMUM RUNOUT | 0.0010 INCHES |
| SCHEMATIC DIAGRAM DESIGNATOR | 1 Y-ROTOR, 1 STATOR |
| FRAGILITY FACTOR | MODERATELY RUGGED |
