Z-42 MU
The revised Zlín Z 42M flew in November 1972, with a revised tail taken from the Z 43, and a Constant speed propeller replacing the variable pitch propellor (where the propellor pitch is controlled by the pilot) of the original Z 42. When early Z 42s were refitted with the new propellor, they were redesignated Z 42 MU.
Technical Characteristics and Operational Limitations
2. Description: The Z 42 MU aircraft is two-seat, low wing, single-engine,
and cantilever monoplane.
4. Dimensions:
Span: 9.11 m
Length: 7.07 m
Height: 2.69 m
Wing Area: 13.15 m
5. Engine:
5.1.1 Model: M – 137 A
5.1.2 Type Certificate: EASA approved (CAA Cz TC No. 69-01) (see Note 4)
5.1.3 Limitations: Max. Take-off power (5 min.)
max. Power 133 kW (180 HP)
max. Engine speed 2 750 RPM
max. Consumption 61 l/h
max. Manifold pressure 100 ± 2 kPa
Max. Continuous power
max. Power 118 kW (160 HP)
max. Engine speed 2 680 RPM
max. Consumption 52 l/h
max. Manifold pressure 95 ± 2 kPa
Z 42 MU TCDS EASA.A.027 Moravan Aviation Page 19 of 45
Issue 6 Z 42 - Series 2 November 2010
EASA Form NR 90 CS-23
Issue 01
Max. Cruising power
max. Power 103 kW (140 HP)
max. Engine speed 2 580 RPM
max. Consumption 43 l/h
max. Manifold pressure 87 kPa
or
5.2.1 Model: M – 137 AZ
5.2.2 Type Certificate: EASA approved (CAA Cz TC No. 69-01) (see Note 4)
5.2.3 Limitations: Max. Take-off power (5 min.)
max. Power 133 kW (180 HP)
max. Engine speed 2 750 RPM
max. Consumption 61 l/h
max. Manifold pressure 100 ± 2 kPa
Max. Continuous power
max. Power 118 kW (160 HP)
max. Engine speed 2 680 RPM
max. Consumption 52 l/h
max. Manifold pressure 95 ± 2 kPa
Max. Cruising power
max. Power 103 kW (140 HP)
max. Engine speed 2 580 RPM
max. Consumption 43 l/h
max. Manifold pressure 87 kPa
6. Load factors: Category U +5.0 g, -3.2 g
Category N +3.8 g, -1.5 g
7. Propeller:
7.1 Model: V 503 A
7.2 Type Certificate: EASA approved (CAA Cz TC No. 69-02) (see Note 5)
7.3 Number of blades: 2
7.4 Diameter: 2 000 mm
7.5 Sense of Rotation: Anticlockwise in flight direction.
8. Fluids:
8.1 Fuel: Non-ethylated aviation gasoline, with min. 72 octanes.
Application of ethylated fuels is only permitted in case the
T.E.L. content does not exceed the value of 0.06% vol.
LBZ 72
LBZ 78
LBE 80
LBE 87
Shell 80
Z 42 MU TCDS EASA.A.027 Moravan Aviation Page 20 of 45
Issue 6 Z 42 - Series 2 November 2010
EASA Form NR 90 CS-23
Issue 01
ESSO 80
AVGAS 100 LL
(DEFENCE STANDARD 91/90, ASTM D910)
8.2 Oil: AERO SHELL 100 (a mineral oil) or equivalent – is
recommended for running-in (max. up to 50 hours).
AERO SHELL W 100 or equivalent – is recommended for
after-running-in operation in temperate climatic area.
AERO SHELL W 120 or equivalent – is recommended for
after-running-in operation in tropical area.
AERO SHELL W 80 or AERO SHELL W 65 or equivalent – is
recommended for after-running-in operation during winter or
in polar area.
8.3 Coolant: None
9. Fluid capacities:
9.1 Fuel: Total: 130 litres
Usable: 127 litres
2 x 65 litres in main tanks
9.2 Oil: Minimum 7 litres – Maximum 12 litres
9.3 Coolant system capacity: None
10. Air Speeds: Never Exceed Speed Limit vNE 315 km/h CAS
Normal Operating Speed
Limit vNO 226 km/h CAS
Design Manoeuvring Speed
Limit vA
Category U 270 km/h
CAS
Category N 220 km/h
CAS
Maximum Flaps Extended
Speed Limit vFE 185 km/h CAS
11. Maximum Operating Altitude: Category U 4 250 m
Category N 3 800 m
12. All-weather Operations Capability: The aircraft is approved for VFR Day flights.
13. Maximum Weights: Max. Take-off and Landing weight:
Category U
920 kg
Category N 970 kg
Max. Variable Load:
Category U, N 200 kg
14. Centre of Gravity Range: 19 % – 27 % MAC
M.A.C. is 1 460 mm; 0 % M.A.C. is 300 mm aft reference TCDS EASA.A.027 Moravan Aviation Page 21 of 45
Issue 6 Z 42 - Series 2 November 2010
EASA Form NR 90 CS-23
Issue 01
datum.
15. Datum: The rear part of firewall; from it are measured, for purpose of
assignation of Gravity Centre, all lateral dimensions.
16. Control surface deflections: Elevator deflection up 34º + 0°, -1º
down 27° + 1°
Rudder deflection right and left 30° ± 2°
Ailerons deflection up 21° ± 1°
down 17° ± 1°
Wing flaps positions retracted 0°
take-off 14° ± 1°
landing 37° ± 1°
17. Levelling Means: Levelling points on left and right side of airplane fuselage to
be levelled. Measurement plane to be min. 600 mm below.
18. Minimum Flight Crew: 1 (Pilot)
19. Maximum Passenger Seating
Capacity:
2 (including crew)
20. (Reserved)
21. Baggage/Cargo Compartments: Max. 20 kg
Notes
Note 1: Model has been approved under original Czech CAA Type Certificate No. 73-06 dated
November 30, 1973, Supplement No. 1 dated February 01, 1974.
Note 2: The Z 42 MU aircraft have been converted by the aircraft manufacturer to the models:
Z 42 M S/N: 0011; 0027
Note 3: For operation of the airplane in other than the Normal Category, compliance with the
applicable parts of Mandatory Service Bulletins Z42/54a, Z42/55a and Z42/56a or later
revision of each is required.
Note 4: The EASA type certification standard includes that of CAA Cz TCDS No. 69-01 based
on individual EU member state acceptance or certification of this standard prior to 28
September 2003. Other standards confirming to TC/TCDS standards certificated by
individual EU member state prior to 28 September 2003 are also acceptable.
Note 5: The EASA type certification standard includes that of CAA Cz TCDS No. 69-02 based
on individual EU member state acceptance or certification of this standard prior to 28
September 2003. Other standards confirming to TC/TCDS standards certificated by
individual EU member state prior to 28 September 2003 are also acceptable.
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