# TCDS E-270: Curtiss-Wright/Marquette Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Curtiss-Wright/Marquette Inc.
- Revision: 5
- Revised: December 28, 1983
- Product: Engine
- Data sheet PDF: https://openairdocs.org/files/sha256/ca/e6/cae640e56ecd267e3b6ca19c8f64c4c10caa8a4aaa388af1481d977e6cc12794
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/54C0B90EBF2F1BE08525670B006C8762.0001
- Page: https://openairdocs.org/tcds/E-270

## Models (2)

As the data sheet lists them.

- Double Row Cyclone 975C18CB1
- Double Row Cyclone 956C18CA1

## What the data sheet says

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

```text
Page No. 1 2
Rev No. 5 5
Reformatted 12/93.
DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
E-270
Revision 5
WRIGHT
Double Row Cyclone
956C18CA1
975C18CB1
December 28, 1983
TYPE CERTIFICATE DATA SHEET NO. E-270
Engines of models described herein conforming with this specification and approved data on file with the Civil Aeronautics
Administration and Federal Aviation Administration are rated as airworthy for use in certificated aircraft in accordance with
pertinent aircraft specifications and the manufacturer's installation, operation, repair and overhaul instructions.
Manufacturer Curtiss Wright/Marquette Inc.
Fountain Inn, S.C.
Model    Double Row Cyclone 956C18CA1 975C18CB1
Type     18RA 16:7 Reduction gearing -  -
Rating
  (with low impeller gear ratio) 6.46:1 -  -
    Max. continuous, hp, rpm, in.Hg., at:
      Critical altitude (ft.) 2300-2600-45.5-6300 2400-2600-46.0-5300
      Sea level pressure altitude 2300-2600-47.0-S. L. 2400-2600-47.5-S. L.
    Take-off (5 min.), hp, rpm, in.Hg., at:
       Critical altitude (ft.) 2700-2900-52.5-5100 2800-2900-52.5-4500
       Sea level pressure altitude 2700-2900-54.0-S. L. 2800-2900-54.0-S. L.
    (With high impeller gear ratio) 8.67:1 -  -
    Max. continuous, hp, rpm, in.Hg., at:
      Critical altitude (ft.) 2000-2600-46.5-15,800 2000-2600-46.0-16,000
      Low critical pressure altitude (ft.) 2000-2600-48.0-10,700 2000-2600-47.5-10,800
  Fuel (Minimum grade aviation gasoline) 115/145 115/145 (See NOTE 6 for 100/130)
  Bore and stroke, in. 6.125 X 6.312 -  -
  Displacement, cu. in. 3350 -  -
  Compression ratio 6.70:1 -  -
  Weight (dry), lbs. 2945 3065
  C.G. location (dry)
    From crankcase mounting pad counterbore, in. 13.50 -  -
    From thrust nut face, in. 30.64 -  -
    Above propeller shaft, in.  0.2 -  -
  Propeller shaft, SAE No. 60 -  -
  Fuel injection model Bendix Stromberg PR-58-P3 Bendix Stromberg PR-58-S2
  master control with two   or PR-58-P3 master control
  direct injection pumps   with two direct injection pumps
Ignition, Dual Scintilla, DLN-9 magneto -  -
  Timing, °BTC   25 (35 in cruising) -  -
NOTES 1, 2, 3, 4, 5 1, 2, 3, 4, 5, 6
"-  -" indicates "same as preceding model"
"" indicates "does not apply"
Certification basis Type Certificate No. 270
Production basis Production Certificate No. 8

E-270, Rev 5
Page 2
NOTE 1.    Maximum permissible temperatures are as follows:
Head (Well Type Thermocouple) Barrel Oil Inlet
475° (500° for T.O. only) 350° 220°
NOTE 2. Fuel and oil pressure limits:
  Oil pressure (psi) Rear Pump 70 ± 5
  Fuel pressure (psi) 25 ± 1
NOTE 3. The following accessory drives are provided:
Rotation* Speed*
Maximum Torque
(lbs. in.)
Maximum Bending
Moment (in. lbs.)
Continuous Static
Starter C 1.000 - 36000 350
Generator and accessory (2) C 3.110 1500 6600 400
Fuel pump (2) CC 1.000 25 450 15
Hydraulic pump C 1.400 600 2700 350
Vacuum pump (2) C 1.400 250 1650 75
Tachometer (2) 1C 0.500 22 50 15
1CC
Propeller governor C 0.857 125 825 30
*"C" - Clockwise viewing drive pad
  "CC" - Counter clockwise
  Speed - Times crankshaft rpm
NOTE 4. These engines incorporate torquemeters, provisions for crankcase mounting and double-acting hydraulic
propeller provisions.
NOTE 5. The ratings of these engines are based on standard conditions of temperature and barometric pressure
(60°F and 29.92 in.Hg. at sea level) and 80% relative humidity.  If corrected to dry standard air conditions,
the rated powers would be increased approximately 2.5% at sea level to 0.4% at 15,000 feet for equal
manifold pressure settings.
NOTE 6. The 97C18CB1 engine is eligible for use with grade 100/130 fuel at the following ratings:
With low impeller rear ratio:
  Max. continuous, hp, rpm, in.Hg., at:
    Critical altitude (ft.) - 2150-2600-40.5-8700
    Sea level - 2150-2600-43.0-S. L.
Take-off (5 min.), hp, rpm, in.Hg. at:
    Critical altitude (ft.) - 2350-2600-45.0-5900
    Sea level - 2350-2600-46.5-S. L.
With high impeller gear ratio:
  Max. continuous, hp, rpm, in.Hg., at:
    Critical altitude (ft.) - 1800-2600-41.0-18,800
    Low critical pressure
      altitude (ft.) - 1800-2600-42.0-14,000
....END....
```

## ADs (2, in force first)

- [AD 54-25-02](https://openairdocs.org/ad/54-25-02): Cam Drive Gear · Curtiss-Wright/Marquette Double Row Cyclone 975C18CB1, Double Row Turbo Cyclone 972TC18DA1 (R-3350-34, -91) and Double Row Turbo Cyclone 972TC18DA2
- [AD 57-06-04](https://openairdocs.org/ad/57-06-04): Engine Front Section · Curtiss-Wright/Marquette Double Row Cyclone 956C18CA1, Double Row Cyclone 975C18CB1, Double Row Turbo Cyclone 972TC18DA1 (R-3350-34, -91) and 10 more

## STCs approved under this data sheet (1)

- [STC SE01966WI](https://openairdocs.org/stc/SE01966WI): Use of GAMI G100UL High Octane Unleaded Avgas in spark ignition piston aircraft engines. General Aviation Modifications Inc.

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