Document
European Aviation Safety Agency
EASA
TYPE-CERTIFICATE
DATA SHEET
Number : E.030 Issue : 02 Date : 14 August 2007 Type : TURBOMECA TM 333 series engines Variant TM 333 2B2 TM 333 2M2 List of effective Pages Pages 1 2 3 4 5 6 7 8 9 Issue 2 2 2 2 2 2 2 2 2 TCDS E.030 TURBOMECA TM 333 engines page 2/9 Issue 02, 14 August 2007 Variants 2B2, 2M2 intentionally left blank TCDS E.030 TURBOMECA TM 333 engines page 3/9 Issue 02, 14 August 2007 Variants 2B2, 2M2 I - General 1. Type : TM 333 Variant : 2B2, 2M2 2. Type Certificate Holder : TURBOMECA 64511 Bordes Cedex - France DOA-ref: EASA.21J.070 3. Manufacturer : TURBOMECA 4. Date of application : TM 333 2B2:18 November 1999 TM 333 2M2: 11 September 2002 Note: EASA type certification for the TM 333 2B2 was granted in accordance with article 2 paragraph 3(a) of EU Commission Regulation EC 1702/2003 based on the DGAC-France type certification.The Type Certificates for the variants TM 333 1A and TM 333 2B had been surrendered on 19 October 2006.
II - Certification Basis 1. Reference Date for determination of the applicable airworthiness standards: For the TM 333 1A, the reference date was 30 September 1983.
For the TM 333 2B, the certification basis was modified 18 May 1990.
For the TM 333 2B2, the certification basis was modified 20 December 2001.
For the TM 333 2M2, the certification basis was modified 15 June 2007.
2. Certification Date : TM 333 2B2: 21 December 2001 (initially DGAC-France Type Certificate Data Sheet n° M 14) TM 333 2M2: 14 August 2007 3. Certification Basis : a) Airworthiness Standards : TM 333 2B2 DGAC letter No. 2001/05992/SFACT/NME of 20 December 2001.
JAR-E Change 6 of 28 August 1981, completed or modified by paragraphs E20, E25, E40, E50, E60, E150, E170, E515, E690, E730, E740, E820, E830 of JAR -E Change 10.
TM 333 2M2 JAR-E Change 6 dated 28 August 1981, completed or modified by the following paragraphs of JAR-E Change 10: JAR-E20, E25, E40, E60, E150, E170, E510, E680, E690, E730, E740, E820, E830.
JAR-E 515 determination of life limits for the gas generator and free turbines JAR-E 50 for the engine control system (see also AMJ 20X-1) JAR-E 80 (b) for equipments JAR-E 530 (f) for fire precautions (see also AMJ 20X-1) b) Special Conditions : TM 333 2B2 CS1: 30 sec and 2 min OEI (One Engine Inoperative) ratings according to NPA-E 19 of 24 October 2001.
CS2: 30 min HIP/SARM rating (or 30 min AEO).
TCDS E.030 TURBOMECA TM 333 engines page 4/9 Issue 02, 14 August 2007 Variants 2B2, 2M2 CS3: Control system: paragraphs E50, E150(c) and E530(f) of JAR-E Change 10, as interpreted by AMJ 20X-1.
TM 333 2M2 SC-1: CRI-T1 30-min HIP/SARM Rating c) Deviations : TM 333 2B2, 2M2 None.
d) Equivalent Safety Finding : TM 333 2B2, 2M2 JAR-E 25 (b) (2) and E-60 (h) as modified by NPA -E 19 dated 24 September 2001.
e) Environmental Standards : TM 333 2B2, 2M2 None.
III - Technical characteristics 1. Type Design Definition TM 333 2B2 P/N 0 333 00 516 0 TM 333 2M2 P/N 0 333 00 518 0 2. Description The TM 333 engine is a twin spool turboshaft engine of modular design consisting of: - an annular air intake with variable inlet guide vanes - two stage axial compressor, a single stage centrifugal compressor driven by a single stage turbine - an annular reverse flow combustion chamber - a single stage axial power turbine driving a forward mounted reduction gearbox - a control provided by a single channel digital engine control unit The starter-generator and exhaust jet pipe are not part of engine type definition.
3. Equipment Defined in TM 333 2B2 and TM 333 2M2 Installation and Operating Manual.
4. Dimensions: TM 333 2B2, 2M2 TM 333 2B2, 2M2 Length: 1045 mm Height: 754 mm Width: 454 mm 5. Dry weight of the equipped engine TM 333 2B2 166.5 kg TM 333 2M2 162.5 kg Additional weight of residual oil and fuel: 3 kg TCDS E.030 TURBOMECA TM 333 engines page 5/9 Issue 02, 14 August 2007 Variants 2B2, 2M2 6. Power ratings Power (kW) TM 333 2B2 TM 333 2M2 Rating Thermal Power Shaft Power Thermal Power Shaft Power without Torque with Torque without Torque with Torque 1 1 Limitations Limitations ( ) Limitations Limitations ( ) 30 sec OEI 910 808 - - 2 min OEI 841 808 - - 30 min OEI 807 737 - - Take-off / 30-min AEO 825 773 807 456 / 30-min HIP-SARM Maximum continuous 736 684 736 368 ( ) Limitation by the EECU.
The minimum guaranteed power values indicated in the above table are defined under the following conditions: - ISA conditions at sea level (15 °C, 1 013 mbar); - At the engine test bed with hydraulic brake system; - Neither air intake nor exhaust gas pressure drop; - No bleed air; - No power drawn by any accessories other than those required for engine operation; - Fuel Low Heat Value: 43 136 kJ/kg; - Engine equipped with a test bed air intake (6528135060) and primary exhaust pipe (6528135070).
The performance curves are given in the TM333 2B2 and TM 333 2M2 Performance Booklets.
7. Control System The engine is controlled by a Full Authority Digital Engine Control (FADEC).
The FADEC shall be installed in the airframe. The installation conditions are defined in the Installation and Operating Manual.
8. Fluids (Fuel/Oil/Additives): Refer to Installation and Operating Manual 9. Aircraft accessory drive Accessory Direction of Reduction ratio Maximum Maximum Maximum static rotation (1) Nominal speed steady state torque overhung load shaft power daNm (2) kW daNm Starter- CW 0.25446 7.5 4.7 2,50 generator 11 451 rpm NOTE: (1) The direction of rotation is given as viewed from the outside.(CW : clockwise) (2) Load exerted by the weight of the accessory overhung on the drive pad.
TCDS E.030 TURBOMECA TM 333 engines page 6/9 Issue 02, 14 August 2007 Variants 2B2, 2M2 10. Air Bleed extraction For TM 333 2B2 and TM 333 2M2, P3 air bleed extraction for helicopter use.
Maximum air flow corresponding to 100 g/s at take-off rating for sea-level standard conditions.
Limitations on the use of air bleed are defined in the Installation and Operating Manual.
IV - Operational Limitations 1. Temperature limits 1.1 Gas generator exhaust temperature (T45) limits On start-up (for TM 333 2B2 and TM 333 2M2): T45 (°C) For an unlimited duration 790 Maximum over-temperature (<5s) 860 In flight (steady state conditions): T45 (°C) Rating TM 333 2B2 TM 333 2M2 30 sec OEI 985 - 2 min OEI 925 - 30 min OEI 897 - Take-off / 30-min AEO / 30-min HIP-SARM 904 897 Maximum continuous 853 853 1.2 Fuel temperature (TM 333 2B2 and TM 333 2M2) Maximum fuel temperature : Refer to Installation and Operating Manual Minimum temperature for engine starting : Refer to Installation and Operating Manual Additives : use of anti-icing additive for fuel temperature ≤ + 5°C 1.3 Oil temperature (TM 333 2B2 and TM 333 2M2) Minimum oil temperature for engine starting : -30 °C for oil between 3.9 and 5 cSt -40 °C for oil with 3 cSt Minimum oil temperature for power-up : 10 °C for oil between 3.9 and 5 cSt 0 °C for oil with 3 cSt Maximum oil temperature : 115 °C TCDS E.030 TURBOMECA TM 333 engines page 7/9 Issue 02, 14 August 2007 Variants 2B2, 2M2 2. Maximum / Minimum speeds 2.1 Gas generator speed (N1) 100% N1 = 45 000 rpm.
TM 333 2B2 TM 333 2M2 Gas generator speed Gas generator speed Rating % rpm % rpm 30 sec OEI 101.92 45 864 - - 2 min OEI 100.51 45 229 - - 30 min OEI 99.88 44 946 - - Take-off / 30-min AEO / 30-min 100.20 45 088 99.88 44 946 HIP-SARM Minimum stabilized speed 74.60 33 570 74.60 33 570 Maximum continuous 98.58 44 361 98.58 44 361 Maximum overspeed, transient 101 45 450 101 45450 conditions < 5 seconds (excluding 30sec and 2 min OEI) At all ratings, the N1 varies depending on the ambient temperature. The instructions, which apply in the event of this temperature being exceeded, are indicated in the Installation and Operating Manual.
2.2 Power turbine speed (N2) 100%N2 = 37 562 rpm.
The power turbine nominal speed corresponds to 6 000 rpm at the power off-take.
For TM 333 2B2 and TM 333 2M2: Power Turbine Speed % Rpm Maximum speeds No limit on duration 105 39 440 Transient (5 seconds) 107 40 192 Minimum speeds No limit on duration 90 33 805 Transient (5 seconds) 90 33 805 TCDS E.030 TURBOMECA TM 333 engines page 8/9 Issue 02, 14 August 2007 Variants 2B2, 2M2 3. Torque Limits Maximum torque on shaft during operation: Torque (daN.m) Rating TM 333 2B2 TM 333 2M2 30 sec OEI 151.9 - 2 min OEI 151.9 - 30 min OEI 136 - Take-off / 30-min AEO / 123 123 30-min HIP-SARM Maximum continuous 108.8 108.8 Max. overtorque (20 sec.) 136 136 4. Pressure limits 4.1 Oil pressure (TM 333 2B2 and TM 333 2M2) Minimum oil pressure : 1 700 hPa for N1 ≥ 31 950 rpm (71%) Maximum starting oil pressure : 20 000 hPa Normal operating range : 2 500 to 5 000 hPa 4.2 Fuel pressure Refer to TM 333 2B2 and TM 333 2M2 Installation and Operating Manual.
5. Installation Assumptions Refer to TM 333 2B2 and TM 333 2M2 Installation and Operating Manual.
6. Dispatch limitations All engine control systems or equipment must be functional prior to aircraft take-off, except if defined in an approved MMEL.
TCDS E.030 TURBOMECA TM 333 engines page 9/9 Issue 02, 14 August 2007 Variants 2B2, 2M2 V - Operational and Service Instructions Document TM 333 2B2 TM 333 2M2 Installation and Operating Manual X 333 H8 002 2 X 333 H8 005 2 Performance Booklet X 333 H8 004 2 X 333 B2 001 2 Maintenance Manual X 333 H8 450 2 X 333 B2 450 2 Overhaul Manual X 333 H8 500 2 X 333 B2 850 2 Service Letters and Service Bulletins Refer to SL and SB Refer to SL and SB directory directory VI - Notes 1. The TM 333 2B2 engine is approved for use on twin-engine civil helicopters. The TM 333 2M2 engine is approved for use on single engine civil helicopters. Their Operating/Starting envelope is defined in the Installation and Operating Manual.
2. Air intake: - The helicopter air intake design shall be such as to prevent instantaneous ingestion of maximum ice and water quantities, as defined in the Installation and Operating Manual.
- A protective grid as defined in the Installation and Operating Manual shall be installed to limit the ingestion of foreign matters in the engine.
3. On TM 333 2B2 the electronic control system provides a “TRAINING” function for training crews in an engine loss of automatic control system situation. Characteristics are defined in the Installation and Operating Manual.
4. On TM 333 2M2 the electronic control system provides a “TRAINING” function for training crews in an engine failure situation. Characteristics are defined in the Installation and Operating Manual.
5. The electronic control unit must not be installed in a dedicated fire zone. Installation conditions are defined in the Installation and Operating Manual.
6. Protection conditions against lightning and electromagnetic interference are defined in the Installation and Operating Manual.
7. Vibrations are measured by sensor on the rear flange of the turbine casing: refer to Installation and Operating Manual.
8. Overspeed: the engine is equipped with a shut-down device in case of power turbine overspeed.
9. “APU” function: On TM 333 2B2 only, the control system has an “APU” function for on-ground electrical power and hydraulic generation.
10. Life limited Components are defined in the Chapter 5 “Airworthiness Limitations Section” of the Maintenance Manual.
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