As Requested (Flight envelope to be expanded as flight hours increase)
I. General
1. Data Sheet No: EASA.R.002
2. Type / Variant or Model: EC 225 LP
3. Airworthiness Category: Large Rotorcraft
4. Type Certificate Holder: EUROCOPTER
Aéroport International Marseille - Provence
13725 MARIGNANE cedex
FRANCE
5. Manufacturer: As above
6. DGAC-F Application Date: 07 November 2000
7. EASA Certification Date: 27 July 2004
8. JAA Recommendation Date: TBA
II. Certification Basis
1. Airworthiness Requirements: JAR 29, Change 1 effective December 1st, 1999,
except for the following :
2. Reversions and Exemptions Granted :
• reversion to FAR 29, Amendment 24 as follows:
- FAR 29.561(b)(3) Emergency landing conditions-general (Reference CRI C-01)
• partial reversions to FAR 29, Amendment 24 as follows:
- FAR 29.571 Fatigue evaluation of structure (Reference CRI C-03)
- FAR 29.785 Seat, berth, safety belts, and harnesses (Reference CRI D-01)
• exemptions from JAR 29, Change 1 as follows:
- JAR 29.562 Emergency dynamic landing conditions (Reference CRI C-02)
- JAR 29.952(a)(c)(d)(e)(f)(g) Fuel system crash resistance (Reference CRI E-01)
- JAR 29.955(b) Fuel transfer (Reference CRI E-05)
• partial exemption from JAR 29, Change 1 as follows:
- JAR 29.963(b) Fuel tanks: general; Puncture resistance (Reference CRI E-02)
3. Equivalent Safety Findings:
- JAR 29.173, 175 Static longitudinal Stability (Reference CRI B-03)
- JAR 29 Apdx B §IV IFR Static longitudinal Stability – Airspeed stability (Reference CRI
B-04)
- JAR 29.571 Fatigue evaluation of structure for changed metallic PSE (Reference CRI C-
04)
- JAR 29.807(c)(1) Passenger emergency exits other than side-of-fuselage (Reference
CRI D-02)
- JAR 29.813(a), 29.815 Emergency exit access - Main aisle width (Reference CRI D-03)
- JAR 29.923(a)(2) Rotor drive system and control mechanism tests (Reference CRI E-
03)
- JAR 29.1303(j) VNE aural warning (Reference CRI F-01)
- JAR 29.1545(b)(4) Airspeed indicators markings (Reference CRI G-01)
- JAR 29.1549(b) Powerplant instruments markings (Reference CRI G-02)
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4. Special Conditions: Minimum in flight experience (Reference CRI B-01)
External loads, JAR 29.865 amdt. 2 (Reference CRI
D-06)
Protection from the effects of High Intensity Radiated
Field (Reference CRI F-02)
5. Environmental Standards including noise:
Noise.
Compliant with ICAO Annex 16, Volume 1, Part II, Chapter
8 and Appendix 4
Engine Emission.
Compliant with ICAO Annex 16 Volume 2, (Fuel Discharge).
III. Technical Characteristics and Operational Limitations
1. Type Design Definition: document ref. 332 A 89 2120, Issue F
2. Description: large twin-engine helicopter designed as a derivative
product of the former type certified model AS 332 L2
3. Equipment: As required by JAR 29 and referenced within approved
Flight Manual
4. Dimensions:
Fuselage Width 3.96m (13ft 00in)
Height 4.97m (16ft 30in)
Main Rotor 5 blades Diameter 16.20m (53ft 14in)
Tail Rotor 4 blades Diameter 3.15m (10ft 33in)
5. Engines: 2 Turboméca Makila 2A
EASA DS No: E.006
5.1 Installed Engine Limits: Refer to approved Flight Manual
5.2 Transmission Torque Limits: Refer to approved Flight Manual
6. Fluids (Fuel/Oil/Hydraulic/Additives):
6.1 Fuel JP-8 (F34), Jet A-1(F35)
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 2588 l (684 US gals)
basic internal fuel tanks and sponsons
7.2 Oil engines 4,92 l
MGB 27 l
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IGB 0,62 l
TGB 1,5 l
7.3 Hydraulic RH system 5,0 l
LH system 9,5 l
8. Airspeed Limits: Vne Power on 175 Kt up to 5.000ft density altitude
and 175kt – 3kt / 1.000ft above 5.000ft
Vne Power off Vne Power on limited to 150 Kt
see Flight Manual for other approved airspeed limits
9. Rotor Speed Limits:
Power on:
Maximum 275 rpm
Minimum 246 rpm
Min transient 220 rpm
Power off:
Max transient 310 rpm (20 sec)
Maximum 290 rpm
Minimum 246 rpm (IAS > 100Kt) 220 rpm ( IAS < 100Kt)
10. Maximum Operating Altitude and Temperature:
10.1 Altitude
Take-off and landing –2.000ft altitude pressure / + 2.000ft density
altitude
En route –2.000ft altitude pressure / + 10.000ft altitude
pressure
10.2 Temperature -15°C to ISA +25°C limited to + 40°C
11. Operating Limitations:
11.1 General Category A and B
VFR day and night
IFR day and night
12. Maximum Certified Weights: Take-off and landing 11,000kg (24,251lb)
13. Centre of Gravity: Refer to approved Flight Manual
14. Datum: 4.67m (183.85in) forward of main rotor centroid
15. Levelling Means: Levelling plate on right side of the fuselage and
graduated plate for plumb line on left side
16. Minimum Flight Crew: Two (2): Pilot and Co-pilot in IFR
One (1): Pilot in VFR
17. Maximum Passenger Seating Capacity: 25
18. Passenger Emergency Exits: one (1) door whose dimensions exceed those of Type II
exit + two (2) Type IV exits on each side
19. Maximum Baggage/Cargo Loads: the cabin floor is provided with the structural strength
required for a load of 800kg/m2 evenly distributed in
cargo configuration
20. Rotor Blade and Control Movement: For rigging information, refer to Maintenance manual
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21. Auxiliary Power Unit: None as basic equipment
22. Wheels and Tyres:
Tyres: nose: 466 x 173-10
main: 615 x 225-10
Wheels: nose: Messier Bugatti C 20525 000
main: Messier Bugatti C 20147 200
IV. Operating and Service Instructions
1. Rotorcraft Flight Manual, Document No: EC 225LP Flight Manual, normal revision RN0,
04-20 approved by EASA on 27 July 2004 or
subsequent
approved issues
2. Maintenance Manual, Document No: Airworthiness Limitations as EC 225LP
Maintenance Servicing Recommendations,
Chapter 05.99, edition 2004.05.31, Rev. 000
approved by EASA on 27 July 2004 or
subsequent approved issues
EC 225LP Maintenance Programme as
- Maintenance Servicing Recommendations
(PRE),
- Aircraft Maintenance Manual (AMM)
3. Service Letters and Service Bulletins: As published by Eurocopter and approved by
EASA
4. Required Equipment:
• As per compliance with JAR 29 requirements and in accordance with the
original Type Design standard.
• Refer to approved Flight Manual and MMEL.
5. Master Minimum Equipment List: None
V. Notes
1. Eligible serial numbers: 2600 and subsequent of EC 225LP version.
2. The certified “optional” installations are each approved independently of the basic helicopter and
an approved Flight Manual Supplement is associated to each optional installation if necessary.
3. Cabin Interior and Seating Configurations must be approved.
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