DynAero MCR ULC Model Guide
DynAero MCR ULC · Model Guide
Overview
The DynAero MCR ULC is a two-seat, low-wing, single-engine piston ultralight (ULM Class 3 in France) with a carbon wing and an 80 l fuel tank. The flight manual approves Rotax 912 UL, 912 ULS and 912 ULS-FR engines. Day VFR only, no icing, no aerobatics.
- Two seats, low cantilever carbon wing, 8.66 m span, 5.53 m long overall; cabin width 1.12 m.
- Max takeoff weight is 450 kg without a parachute and 472.5 kg with one.
- Approved engines: Rotax 912 UL (80 HP), 912 ULS (100 HP) and 912 ULS-FR.
- Flap-control bronze nut is life-limited to 300 hours or 3 years (mandatory SB BS 13 D 0044).
Summary written by AI from the source document. Check the original before relying on it. See which parts of Sprinkle are written by AI.
Reference only, not for flight. Use the current approved manual for your aircraft. See terms, section 5.
Document
Source
Copy found at sprinkle.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type ·
- Model Guide
- Year ·
- 2026
- File size ·
- 48 KB
- Copy found at ·
- sprinkle.com
Specifications & performance
Extracted from this document.
Specifications
- Height m ·
- 1.53
- Length m ·
- 5.53
- Wingspan m ·
- 8.66
- Wing area m2 ·
- 8.31
- Cabin width m ·
- 1.12
- Usable fuel l ·
- 79
- Fuel capacity l ·
- 80
- Max takeoff weight kg ·
- 450
Performance
- Glide ratio ·
- 16
- Load factor max g ·
- 4
- Load factor min g ·
- -2
- Max speed vne (kt) ·
- 146
- Max cruise vno (kt) ·
- 113
V-speeds
- VA_KTS ·
- 93
- VNE_KTS ·
- 146
- VNO_KTS ·
- 113
- VFE_FLAPS_17_KTS ·
- 76
- GREEN_ARC_START_KTS ·
- 46
- STALL_FLAPS_DOWN_WHITE_ARC_START_KTS ·
- 34
Weight & balance
- Mac mm ·
- 960
- Cg range aft pct mac ·
- 40
- Cg range forward pct mac ·
- 22
- Max landing weight no parachute kg ·
- 450
- Max takeoff weight no parachute kg ·
- 450
- Max landing weight with parachute kg ·
- 472.5
- Max takeoff weight with parachute kg ·
- 472.5
What engines is the DynAero MCR ULC approved for?
The DynAero MCR ULC manual authorises the Rotax 912 UL (80 HP takeoff), 912 ULS (100 HP) and 912 ULS-FR. Check that the installed engine and propeller match an approved combination.
What is the maximum weight of the DynAero MCR ULC?
The DynAero MCR ULC has a maximum takeoff and landing weight of 450 kg without a parachute and 472.5 kg with one, according to the flight manual.
What should I check before buying a DynAero MCR ULC?
For the DynAero MCR ULC, confirm that service bulletin BS 13 D 0044 was done: flap control inspection and bronze nut replacement at 300 hours or 3 years. Also check propeller tightening records and which engine and propeller are fitted.
What is the DynAero MCR ULC Model Guide?
The DynAero MCR ULC Model Guide is a model guide for the DynAero MCR ULC, dated 2026.
What year was the DynAero MCR ULC Model Guide published?
The DynAero MCR ULC Model Guide — the DynAero MCR ULC model guide on file — is dated 2026.
Most owners only have the POH. Here's the essential set for the DynAero MCR ULC.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins on file
- Type Certificate (TCDS)
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In this document
Limits and operations
Day VFR only, outside icing conditions. Aerobatics and spins are prohibited. Load factors are +4 / -2 g. Minimum crew is one pilot, maximum two seats. When flying solo, buckle the harness of the unused seat. Instrument panel weight is capped at 15 kg.
Engines and propellers
Rotax 912 UL gives 80 HP for takeoff and 78 HP continuous. Rotax 912 ULS gives 100 HP and 98.6 HP continuous. Both are limited to 5800 RPM for takeoff and 5500 RPM continuous. Many MT, E-Prop and AUPA propellers are listed. Fixed-pitch props must be retightened before the first flight, after 1 h and after 5 h, then checked every 50 h.
Fuel and flaps
Total fuel is 80 l, of which 79 l is usable; a 150 l wing tank option is mentioned. Flaps travel 0-45°. The 45° notch is for short-field landings on final only, when no go-around is planned. Slips and sideslips are forbidden with full flaps.
Summary written by AI from the source document. Check the original before relying on it. See which parts of Sprinkle are written by AI.
Safety notes
- Service Bulletin BS 13 D 0044 is mandatory: inspect the flap control system before the next flight; replace the bronze nut if the inspection is unsatisfactory.
- Engine failure after takeoff: never try to turn back to the runway. Recommended glide speed is 130 km/h with a glide ratio of 16.
- The manual lists no aerobatic manoeuvres as approved and prohibits spins; for an unintentional spin it gives a recovery procedure.
Summary written by AI from the source document. Check the original before relying on it. See which parts of Sprinkle are written by AI.
Full document text
DynAero MCR ULC Model Guide The DynAero MCR ULC is a two-seat, low-wing, single-engine piston ultralight (ULM Class 3 in France) with a carbon wing and an 80 l fuel tank. The flight manual approves Rotax 912 UL, 912 ULS and 912 ULS-FR engines. Day VFR only, no icing, no aerobatics. • Two seats, low cantilever carbon wing, 8.66 m span, 5.53 m long overall; cabin width 1.12 m. • Max takeoff weight is 450 kg without a parachute and 472.5 kg with one. • Approved engines: Rotax 912 UL (80 HP), 912 ULS (100 HP) and 912 ULS-FR. • Flap-control bronze nut is life-limited to 300 hours or 3 years (mandatory SB BS 13 D 0044). Limits and operations Day VFR only, outside icing conditions. Aerobatics and spins are prohibited. Load factors are +4 / -2 g. Minimum crew is one pilot, maximum two seats. When flying solo, buckle the harness of the unused seat. Instrument panel weight is capped at 15 kg. Engines and propellers Rotax 912 UL gives 80 HP for takeoff and 78 HP continuous. Rotax 912 ULS gives 100 HP and 98.6 HP continuous. Both are limited to 5800 RPM for takeoff and 5500 RPM continuous. Many MT, E-Prop and AUPA propellers are listed. Fixed-pitch props must be retightened before the first flight, after 1 h and after 5 h, then checked every 50 h. Fuel and flaps Total fuel is 80 l, of which 79 l is usable; a 150 l wing tank option is mentioned. Flaps travel 0-45°. The 45° notch is for short-field landings on final only, when no go-around is planned. Slips and sideslips are forbidden with full flaps. Safety notes: • Service Bulletin BS 13 D 0044 is mandatory: inspect the flap control system before the next flight; replace the bronze nut if the inspection is unsatisfactory. • Engine failure after takeoff: never try to turn back to the runway. Recommended glide speed is 130 km/h with a glide ratio of 16. • The manual lists no aerobatic manoeuvres as approved and prohibits spins; for an unintentional spin it gives a recovery procedure.