TCDS.R.508 Issue 01, 15 June, 2010
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European Aviation Safety Agency
EASA TYPE-CERTIFICATE DATA SHEET R.508 EC 120 B
Type Certificate Holder: Eurocopter Aéroport International Marseille – Provence 13725 Marignane cedex France
Manufacturer: Eurocopter Aéroport International Marseille – Provence 13725 Marignane cedex France
Issue 1: 15 June, 2010
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TCDS.R.508 Issue 01, 15 June, 2010
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TABLE OF CONTENTS Section
Page
EC 120 B I II III IV V
General Certification Basis Technical Characteristics and Operational Limitations Operating and Service Instructions Notes
3 3 4 6 6
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EC 120 B I.
General
1.
Data Sheet No:
2.
Type / Variant or Model: (a) (b)
R.508 Corresponding to JAA DATA SHEET N° JAA/27/97/002
Type: Variant or Model:
3.
Airworthiness Category:
4.
Type Certificate Holder: Since December 22, 1997
5.
EC 120 EC 120 B Small Rotorcraft,
Manufacturer:
EUROCOPTER Aéroport International Marseille - Provence 13725 MARIGNANE cedex - FRANCE EUROCOPTER Aéroport International Marseille – Provence 13725 MARIGNANE cedex – France
6. JAA Application Date:
6 May 1994
7. Type Certificate Issuance Date
19 June 1997
II.
Certification Basis
1.
JAA Certification Basis: JAR 27 First Issue dated September 06, 1993 defined in CRI A1
2.
Airworthiness Requirements:
JAR 27
3.
Reversions and Exemptions Granted:
N/A
4.
Equivalent Safety Findings:
- Main gear box oil filter by pass - Powerplant instrument marking
5.
Special Conditions:
HIRF
6.
Environmental Standards including noise: See EASA Type Certificate Data Sheet for Noise - For fuel discharge: Annex 16, volume 2, 2nd part.
III.
Technical Characteristics and Operational Limitations
1.
Type Design Definition:
2.
Description:
Small single-engine helicopter
3.
Equipment:
As per compliance with JAR 27 requirements and included in the original Type Design Standard
4.
Dimensions:
Fuselage:
Basic EC 120 B definition Report DMD C 000A0761 E01 Issue B
Length Width Height
9,60m 1,50m 3,40m
Main Rotor: 3 blades Diameter 10m
TCDS.R.508 Issue 01, 15 June, 2010
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Tail Rotor: 5.
Engines:
5.1
Installed Engine Limits:
Fenestron - 8 blades Diameter
0,75m
1 Turboméca ARRIUS 2F See DGAC-F engine TCDS n° M22
Ratings
Gas generator Speed (NG) (1)
Exhaust gas Temperature (T4) (2)
Max transient (5 s) Max take-off (5 min) Max Continuous
103.6% 101% 99.5%
900°C 870°C 830°C
Notes: (1) 100%: 54 117 rpm (2) Max Continuous during starting: 800°C 5.2
Transmission Torque Limits: Max transient: 110% Max Take off: 103% Max Continuous: 97% Note: 100%: 300 Kw at 406 rpm
6.
Fluids (Fuel/Oil/Hydraulic/Additives):
6.1
Fuel:
as approved in the Flight Manual
6.2
Oil:
as approved in the Flight Manual for engine and gearboxes
6.3
Hydraulic:
as approved in the Flight Manual
6.4
Additives:
as approved in the Flight Manual
7.
Fluid Capacities:
7.1
Fuel:
Total: Usable fuel:
7.2
Oil:
engine: Main Gear Box: Tail Gear Box:
8.
Airspeed Limits:
Vne Power on: 150 kt at sea level less 3 kt/1000ft Vne Power off: 120 kt at sea level less 3 kt/1000 ft Refer to RFM for approved airspeed with doors open or removed
9.
Rotor Speed Limits:
Power on:
Normal range
390 to 415 rpm
Power off:
Maximum Minimum
447 rpm (aural warning: 420 rpm) 340 rpm (aural warning: 370 rpm)
10.
410,5 l (108.4US gal) 406 l (107.2US gal) 3 to 4.9 l (0.79 to 1.29 US gal) 4 l (1.06 US gal) 0,2 l (0.05 US gal)
Maximum Operating Altitude and Temperature:
10.1 Altitude:
Take-off and landing En route
10.2 Temperature:
2000ft / 20.000ft pressure altitude. (See Note[1]) 20.000ft pressure altitude - 30°C to + 50°C
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Operating Limitations: Day VFR Night VFR (See Note [2]) Flights under icing conditions, freezing rain and aerobatic manoeuvres are prohibited
12.
Maximum Certified Weights:
13.
Centre of Gravity:
Take-off and landing:
1715 kg (3777 lb)
Longitudinal:
Lateral:
14.
Datum: Longitudinal: Lateral:
4m (13ft2in) forward of main rotor head aircraft symmetry plane
15.
Levelling Means:
Mechanical floor
16.
Minimum Flight Crew:
1 pilot
17.
Maximum Passenger Seating Capacity:
18.
Passenger Emergency Exits:
One door on each side of the fuselage
19.
Maximum Baggage/Cargo Loads:
-The baggage floor is provided with the structural strength required for a load of 300kg/m2 evenly distributed in cargo configuration
4
-The cockpit floor is provided with the structural strength required for a load of 300kg/m2 evenly distributed in cargo configuration 20.
Rotor Blade and Control Movement: For rigging information, refer to Maintenance Manual
21.
Auxiliary Power Unit:
None
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IV.
Operating and Service Instructions
1.
Rotorcraft Flight Manual, Document No: Flight Manual (original issue approved by DGAC-F 19 June 1997) at issue 2 (Approved by DGAC-F 19 March 1998) or subsequent issues
2.
Maintenance Manual, Document No: EC 120B Aircraft Maintenance Manual - chapter 04 (original issue approved by DGAC-F, 19 June 1997) at issue 1 (approved by DGAC-F, 30 March 1998) EC 120B Master Servicing Manual - chapter 04, original issue approved by DGAC-F, 12 March 1999 or subsequent issues
3.
Service Letters and Service Bulletins:
4.
Required Equipment:
As published by Eurocopter and approved by DGACF or EASA
As per compliance with JAR 27 requirements and included in the original Type Design Standard Note [1]: Max take off and landing Hp= 20.000 ft permitted when change A00075 and SB 32.001 have been embodied to the aircraft (use Flight Manual issue 2 + ITR 3C or subsequent issues) Note [2]: Night VFR operation permitted when SB 34.001 has been embodied to the aircraft (use Flight Manual issue 2 + ITR 3E or FM subsequent issues)
V.
Notes
1.
Eligible serial numbers:
2.
There is no approved Repair Manual
1001 and subsequent, except S/N 1004
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