NSN 5990-00-847-3806
Part Details | CONTROL TRANSFORMER SYNCHRO
5990-00-847-3806 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: VCT23366A, VCT23/36-6A, AY240AA 10 A1, A10630, 23CT6, 7406453P4, 23CT6, AS2070894, AS20708/94, 23CT6, 7676357, 5990-00-847-3806, 00-847-3806, 5990008473806, 008473806
| Supply Group (FSG) | NSN Assigned | NIIN | Item Name Code (INC) |
|---|---|---|---|
| 59 | JAN 01, 1962 | 00-847-3806 | 15289 ( SYNCHRO, CONTROL TRANSFORMER ) |
REFERENCE DRAWINGS & PICTURES
STANDARD ROUND D
Cross Reference | NSN 5990-00-847-3806
| Part Number | Cage Code | Manufacturer |
|---|---|---|
| VCT23/36-6A | 10112 | GENERAL DYNAMICS GLOBAL IMAGINGTECHNOLOGIES, INC. |
| AY240AA 10 A1 | 55972 | HONEYWELL INTL INCDEFENSE AVIONICS SYSTEMS |
| A10630 | 28199 | L3 TECHNOLOGIES, INC.DBA L3 HENSCHEL |
| 23CT6 | 28199 | L3 TECHNOLOGIES, INC.DBA L3 HENSCHEL |
| 7406453P4 | 03538 | LOCKHEED MARTIN CORPORATIONDIV RMS |
| 23CT6 | 81349 | MILITARY SPECIFICATIONSPROMULGATED BY MILITARY |
| AS20708/94 | 81343 | SOCIETY OF AUTOMOTIVE ENGINEERS INC |
| 23CT6 | 81343 | SOCIETY OF AUTOMOTIVE ENGINEERS INC |
| 7676357 | 19200 | US ARMY ARDEC RDECOM |
Technical Data | NSN 5990-00-847-3806
| Characteristic | Specifications |
|---|---|
| BODY SIZE | 23 |
| STATOR INPUT VOLTAGE RATING IN VOLTS | 90.0 NOMINAL |
| STATOR INPUT CURRENT RATING | 20.0 MILLIAMPERES NOMINAL |
| STATOR INPUT ELECTRICAL POWER RATING | 500.0 MILLIWATTS NOMINAL |
| FREQUENCY IN HERTZ | 60.0 NOMINAL |
| ZRO RESISTANCE IN OHMS | 1015.00 NOMINAL |
| PLUS J ZRO REACTANCE IN OHMS | 2746.00 NOMINAL |
| ZSO RESISTANCE IN OHMS | 492.00 NOMINAL |
| PLUS J ZSO REACTANCE IN OHMS | 4027.00 NOMINAL |
| ZRS RESISTANCE IN OHMS | 239.00 NOMINAL |
| PLUS J ZRS REACTANCE IN OHMS | 81.00 NOMINAL |
| TRANSFORMATION RATIO | 0.735 ROTOR TO STATOR NOMINAL |
| MAXIMUM TEMP RISE | 45.0 DEG CELSIUS |
| MAXIMUM FUNDAMENTAL NULL VOLTAGE IN MILLIVOLTS PER VOLT | 60.00 OUTPUT |
| MAXIMUM TOTAL NULL VOLTAGE OUTPUT IN MILLIVOLTS PER VOLT | 75.00 |
| ELECTRICAL ERROR ANGULAR RANGE IN MINUTES | M6.0/P6.0 |
| ACTUATOR FRICTION TORQUE AT MINUS 55 DEG CELSIUS | 0.50 INCH-OUNCES MAXIMUM |
| ACTUATOR FRICTION TORQUE AT PLUS 25 DEG CELSIUS | 0.20 INCH-OUNCES MAXIMUM |
| BODY STYLE | STANDARD ROUND D |
| SHOULDER DIAMETER | 1.9850 INCHES MINIMUM AND 1.9900 INCHES MAXIMUM |
| PILOT DIAMETER | 0.5900 INCHES MINIMUM AND 0.6000 INCHES MAXIMUM |
| SECOND SHOULDER DIAMETER | 1.9985 INCHES MINIMUM AND 1.9995 INCHES MAXIMUM |
| SECOND SHOULDER LENGTH | 0.1680 INCHES MINIMUM AND 0.1700 INCHES MAXIMUM |
| OVERALL LENGTH | 4.2940 INCHES NOMINAL |
| FLANGE DIAMETER | 2.2490 INCHES MINIMUM AND 2.2500 INCHES MAXIMUM |
| FLANGE THICKNESS | 0.2480 INCHES MINIMUM AND 0.2500 INCHES MAXIMUM |
| BODY DIAMETER | 1.9850 INCHES MINIMUM AND 1.9900 INCHES MAXIMUM |
| PILOT LENGTH | 0.0360 INCHES MINIMUM AND 0.0460 INCHES MAXIMUM |
| SHOULDER LENGTH | 0.2500 INCHES NOMINAL |
| AFT OF FIRST FLANGE DIAMETER | 1.9985 INCHES MINIMUM AND 1.9995 INCHES MAXIMUM |
| MOUNTING SURFACE TO TERMINAL END DISTANCE | 3.4450 INCHES MAXIMUM |
| ALIGNMENT HOLE DEPTH | 0.1250 INCHES NOMINAL |
| ALIGNMENT HOLE BOLT CIRCLE DIAMETER | 1.6420 INCHES NOMINAL |
| ALIGNMENT HOLE QUANTITY | 3 |
| TERMINAL TYPE AND QUANTITY | 5 SCREW |
| TERMINAL LOCATION | REAR |
| BODY MATERIAL | STEEL, STAINLESS |
| TEST DATA DOCUMENT | 81349-MIL-20708 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.). |
| SPECIFICATION/STANDARD DATA | 81349-MIL--20708 TO 94 GOVERNMENT SPECIFICATION |
| FRAGILITY FACTOR | MODERATELY RUGGED |
