Potez-Heinkel CM.191 — Twin-Jet Executive & Liaison Aircraft
Franco-German Experimental Programme · 1961–1963
The Potez-Heinkel CM.191 was a four-seat, twin-turbojet executive and liaison aircraft jointly developed in 1961 by Établissements Henry Potez (Paris, France) and Ernst Heinkel Flugzeugbau GmbH (Speyer, West Germany). Derived directly from the celebrated Fouga CM.170 Magister military jet trainer, the CM.191 represented an ambitious attempt to translate the Magister's proven aerodynamic pedigree into a high-performance civil and military liaison platform. Only two prototypes were constructed before the programme was closed.
Document Archive — Manifest
This archival edition brings together the surviving primary-source factory documentation for the CM.191 programme:
- Verkaufsbroschüre (Sales Brochure) — 6 pages · German language · Ernst Heinkel Flugzeugbau GmbH, Speyer · Covers general description, airframe, equipment, avionics, powerplant, and performance data
- Flughandbuch (Flight Manual) — Illustrations Volume · Airframe diagrams and system schematics
- Flughandbuch (Flight Manual) — Text Volume · Operational procedures and systems description
- Technische Daten / Specifications Sheets — 7 pages · Detailed dimensional, structural, aerodynamic, and performance data tables
- Anlage 1 — UHF-Anlage Type AN/ARC-34 · Sender-Empfänger RT-263/ARC-34 · 225.0–399.9 MHz · 1,750 channels · 10 W output
- Anlage 2 — Funkkompaß-Anlage Type ADF-102 · Lear ADF-102 radio compass · Fully transistorised · 5 pre-selectable frequencies · 535–1600 kHz
- Anlage 3 — Bord-Eigenverständigungs-Anlage IV T 3 Serie 01 · Intercom system by TEAM, Paris · Licensed manufacture by Bauknecht-GEA, Fellbach · 4.63 kg
Total documents in this archive: 15 unique primary-source pages and plates.
Airframe & Design
- Configuration: All-metal mid-wing monoplane with twin turbojets mounted aft of the wing roots, side-by-side four-seat cabin
- Fuselage: Conventional semi-monocoque shell construction using oval frames and four longerons; pressurised and climate-controlled cabin with full-vision Plexiglas canopy
- Wing: Trapezoidal single-spar structure, aspect ratio 7.67, slight leading-edge sweep (15°), NACA Series 64 profile — 19% thickness at root, 12% at tip; hydraulically actuated Fowler-type flaps, Frise ailerons, retractable spoilers
- Empennage: Iconic V-tail (butterfly tail) inherited from the Fouga Magister — combined pitch/yaw control via differential rudder deflection and servo trim tabs
- Undercarriage: Tricycle, wide-track main gear (4.41 m), hydraulic retraction — nose gear retracts forward to the nose, main gear folds into the wing roots
Powerplant — Turbomeca Marboré VI
- Type: Single-stage centrifugal compressor / single-stage axial turbine / annular combustion chamber with centrifugal fuel injection
- Exhaust: Constant-area nozzle
- Max diameter: 0.567 m · Length: 1.416 m · Weight: 146 kg
- Quantity: 2 × Marboré VI, mounted on either side of the rear fuselage beneath removable fairings
Avionics Suite
- UHF Transceiver: AN/ARC-34 (RT-263/ARC-34) — 225.0–399.9 MHz, 1,750 channels at 1/10 MHz steps, 20 pre-selectable channels, 10 W output, 27 kg total installation
- Radio Compass: Lear ADF-102 — fully transistorised, 5 pre-selectable frequencies, 535–1,600 kHz, Gonio antenna and Gonio coupler, indicator ID 91
- Intercom: Bauknecht-GEA IV T 3 Serie 01 — normal and emergency modes, UHF monitoring capability, pilot priority on transmit
Key Performance Data (Factory Specification)
| Parameter | Value |
|---|---|
| Wingspan | 12.02 m |
| Length | 9.93 m |
| Height | 3.20 m |
| Wing area | 18.83 m² |
| Aspect ratio | 7.67 |
| Max take-off weight | 4,437 kg |
| Max speed (Gm, no tip tanks) | 710 km/h at 21,500 rpm |
| Cruise ceiling (Gm) | 12.1 km |
| Climb rate at sea level (GA, 1 engine) | 3.83 m/s |
| Range at 9,000 m (no climb/descent) | 1,270 km |
| Range at 9,000 m (with climb/descent) | 1,570 km |
| Endurance at 9,000 m | 3.2 h |
| Max speed (with large tip tanks) | 660 km/h |
| Range (large tip tanks, no climb/descent) | 1,800 km |
| Max endurance (large tip tanks) | 4.42 h |
| 2-seat ferry range (additional tank) | up to 2,630 km / ~5 h |
Programme History
- Origin: Developed jointly by Potez-Air Fouga (Paris), Ernst Heinkel Flugzeugbau GmbH (Speyer), and Fouga — derived from the Fouga CM.170 Magister
- First flight: 19 March 1962, Toulouse — test pilots Jacques Grangette and Pierre Caneille
- Intended roles: Civil — business transport, fast feeder, sport aircraft; Military — jet conversion trainer, instrument/night flying, liaison and courier, reconnaissance
- Programme closure: Competition from the Morane-Saulnier MS.760 Paris prevented serial production
- Prototype 1 (N8015Q): Exported to the United States
- Prototype 2: Preserved at Technik Museum Speyer, Germany
This is an archival, static-copy edition fixed at its original publication date. Intended for historical reference, flight simulation, museum restoration, and educational use only. Not approved for active airworthiness maintenance under FAA 14 CFR § 43.13, EASA Part-M, or equivalent international regulations. Operators of active aircraft must use current, revision-controlled publications from the Type Certificate holder or an authorized distributor.
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