# TCDS E-280: Hiller Helicopters

- Type: Type certificate data sheet
- Status: Current
- Holder: Hiller Helicopters
- Revision: 1
- Revised: December 17, 1954
- Product: Engine
- Registered aircraft: 3, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/ad/8c/ad8cd476bc015ad7752a9bf0f3c92aecb953bd38ce3282ec493b5feb279d64f5
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/0C8A5BA2D062E3BE85256784006878B4.0001
- Page: https://openairdocs.org/tcds/E-280

## Models (1)

As the data sheet lists them.

- 8RJ2B

## 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
Rev No. -
Reformatted 1/94.
DEPARTMENT OF COMMERCE
CIVIL AERONAUTICS ADMINISTRATION
E-280-1
HILLER
8RJ2B
December 17, 1954
AIRCRAFT ENGINE SPECIFICATION
Engines of models described herein conforming with this specification and approved data on file with the Civil
Aeronautics 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 Hiller Helicopters
Palo Alto, California
Model 8RJ2B
Type Ramjet
Ratings
  Take-off and Maximum Continuous static
    thrust, lbs., equivalent rotor rpm, at sea level 39-550-S.L.
Fuel Gasoline, Automotive Regular
Grade (Federal Grade 72)
Dimensions 21.2
  Length, in. 8.4 (exclusive of
  Diameter, in.         mounting tab)
Weight, lbs. 13.0
C.G. location On engine axis in line with
   mounting tab holes
Ignition system Champion V21-X1 spark plug with
   aircraft mounted energizer
Certification basis Type Certificate No. 280
NOTE 1. The rated thrust output value is based on static operation on the Hiller 5.5 inch free air jet test
stand operating at 662 ft./second airspeed at sea level standard conditions of 59°F and 29.92 in.Hg.
ambient air and 65 gph (400 lbs. per hr.) fuel flow.  This thrust value is also corrected for the
fuel pumping loss incurred when the engine is operated on a 23 ft. diameter rotor at 550 rpm.
NOTE 2. Fuel inlet pressures of 5 to 40 psi are required for supplying fuel through the rotor head fuel
transfer gland.
NOTE 3. This engine is used tip mounted on the 23 ft. diameter rotor blades in the Hiller HJ-1 helicopter.
It is operated governor controlled at all flight speeds.
...END...
```

## ADs

None name its models.

## Registered aircraft by registry model (OpenAirDocs)

- [Hiller 8RJ2B](https://openairdocs.org/engine/hiller-8rj2b): 3 aircraft (registry code 33501)

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