# TCDS TC 5E-14: Wright Aeronautical Division Curtiss-Wright Corporation

- Type: Type certificate data sheet
- Status: Current
- Holder: Wright Aeronautical Division Curtiss-Wright Corporation
- Revision: 0
- Product: Engine
- Data sheet PDF: https://openairdocs.org/files/sha256/c8/e7/c8e7a47a310cda0cc243761a5de7fb4119dbd8bbd1e1936b6389b85c3b6b12da
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/8CEF61E0DB6D2E1C8525676D004A1A31.0001
- Page: https://openairdocs.org/tcds/TC%205E-14

## Models (1)

As the data sheet lists them.

- Military Cyclone R-1300 Series

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
WRIGHT AERONATICAL DIVISION
CURTISS-WRIGHT CORPORATION
MODELS:  Wright Military Cyclone R-1300 Series
T.C.  NUMBER:  5E-14
Model R-1300-1A, -1B R-1300-3, -3A, -3B, -3C, -3D
Type 5.625: 1 reduction gearing Direct drive
Rating (impeller gear ratio):
   Maximum continuous, hp,
rpm,
   in.Hg., at:
     Critical pressure altitude (ft.)
700-2400-37.0-7300 700-2400-38.0-5000
     Sea level pressure
     altitude 700-2400-39.5-S.L. 700-2400-39.5-S.L.
   Take-off (5 minutes), hp, rpm,
   in.Hg., at:
     Critical pressure altitude (ft.) 800-2600-42.5-5500 800-2600-42.5-3500
     Sea level pressure
     altitude 800-2600-43.5-S.L. 800-2600-44.0-S.L.
Fuel (minimum grade aviation
   gasoline) 91/96 - - - -
Bore and stroke, in. 6.125 x 6.312 - - - -
Displacement, cu. in. 1301 - - - -
Compression ratio 6.20: 1 - - - -
Weight (dry), lbs. 1055 1150
C.G. location (dry):
   Forward of mounting pad
   centerline, in. 5.7 5.29
   Above propeller shaft, in. 0.1 0.08
Propeller shaft, SAE No. 40 - - - -
Crankshaft dampers (See
   NOTE 6) 3-1/2 order - front and rear - - - -
Carburetion Bendix Stromberg PD9F1 Bendix Stromberg PD9G1
Ignition, dual Bosch S7LU-2 magnetos - - - -
Timing, degrees BTC 20 - - - -
Spark plugs See NOTE 7 - - - -
NOTES 1, 2, 5, 6. 7 1, 2, 3, 4, 5, 6, 7
NOTE 1.    Maximum permissible temperatures:
     Cylinder head (well type thermocouple) 475 degrees F. (500 degrees for takeoff)
     Cylinder base 340 degrees F. (350 degrees for takeoff)
     Oil inlet 205 degrees F.
NOTE 2.    Fuel and oil pressure limits:
Maximum Minimum
     Fuel pressure limit 23 psi 21 psi
     Oil pressure limit 70 psi 60 psi
NOTE 3.    The ratings and limitations of the R-1300-3 are applicable to helicopter installation and
   operation.

NOTE 4.    The R-1300-3 incorporates special provisions for installation and operation with the propeller
   shaft inclined at an angle of approximately 40 degrees from horizontal, nose up.
NOTE 5.    When incorporated in certificated aircraft, the engine nameplate should be stamped “FAA
   Spec. No. 5E-14.”  If there is no room for this information on the existing nameplate, such information
   may be stamped on a plain thin metal plate and attached beneath the existing plate by at least two of the
   mounting screws.
NOTE 6.  The above models incorporate additional characteristics as follows:
R-1300 Models Characteristics
-1A Similar to certificated Wright 957C7BA1 engines, except has torsional
   crankshaft dampers only.
-1B Similar to -1A except has both torsional and lateral dampers.
-3 Similar to certificated Wright 990C7BA1 engines, except has torsional
   dampers only.
-3A Same as -3 but has 5° roller clutch impeller drive.
-3B Same as -3A but has both torsional and lateral dampers.
-3C Same as -3A but has 3° roller clutch impeller drive.
-3D Same as -3B but has 3° roller clutch impeller drive.
NOTE 7.    The following spark plugs are approved on these engines:
AC 172, 181, 272, 281
BG RB19R-2, RB27R-1, RB39R
Champion R119, R819, REA87N, REB87N, RHA87N,
   RHB87N
```

## ADs (1, in force first)

- [AD 59-12-07](https://openairdocs.org/ad/59-12-07): Crankshafts · Wright Aeronautical Division, Curtiss-Wright Military Cyclone R-1300 Series

## STCs approved under this data sheet (1)

- [STC SE1206GL](https://openairdocs.org/stc/SE1206GL): Installation of a Shadin Company  Fuel Flow Transducer. Shadin Avionics

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