TCDS R00004RD

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. R00004RD This data sheet which is a part of Type Certificate No.R00004RD prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder Leonardo S.p.a. Helicopter Division Piazza Monte Grappa, 4 00195 – Rome, Italy Type Certificate Holder Record: AgustaWestland S.p.A. was previous name of TC holder. The company name change history is presented below. Type Certificate Holder Period AgustaWestland S.p.A. Via Giovanni Agusta, 520; 21017 Cascina Costa di Samarate (VA) – Italy 1 June 2011 - 30 July 2014 AgustaWestland S.p.A. Piazza Monte Grappa, 4; 00195 Roma - Italy 31 July 2014 - 31 December 2015 Finmeccanica S.p.A., Helicopter Division Piazza Monte Grappa, 4; 00195 Roma - Italy 1 January 2016 - 14 July 2016 Leonardo S.p.A., Helicopters Piazza Monte Grappa, 4; 00195 Roma - Italy since 15 July 2016 I. Model AW189 (Transport Helicopter: Category A and Category B), Approved 27 February 2015 Engine Two (2) General Electric CT7-2E1 FAA Engine Type Certificate Data Sheet No E8NE Free turbine turboshaft engines with FADEC For Limitations Ref. to GE Operating Instructions No. GEK112766 Auxiliary Power Unit (APU) One (1) Microturbo model e-APU60 model 342 (FAA TSO C77b) • Max. Continuous = 41.9 hp (31.25 kW) at APU gearbox. • See e-APU60 for AW189 Installation Manual No. 0342/09/012, issue /Ed. 06, dated 5/21/14 or later approved issue for detail Fuel JET A, JET A1, JP5, JP8, JP8+100, No. 3 Jet Fuel (for code no. specification and more details refer to approved Rotorcraft Flight Manual) Fuel icing inhibitors are mandatory for ambient temperatures below -15°C See Section I of the approved Rotorcraft Flight Manual for fuel mixture and fuel temperature limitations R00004RD REVISION 6 Leonardo S.p.a. AW189 December 03, 2025 Page No. 1 2 3 4 5 6 7 8 9 10 11 12 Rev. No. 6 5 4 4 4 4 4 6 4 4 4 4 R00004RD 2 Rev. 5 Oil Hydraulics MIL-PRF-83282; MIL-PRF-5606, as alternative in low temperature environments below -20° C (See NOTE 7) Transmissions Engine APU Additives Coolant AEROSHELL TURBO OIL 555 (DoD-L-85734). No different specification or brand is allowed Ref. to GE Operating Instructions No. GEK112766 MIL-PRF-23699, MIL-PRF-7808 MIL-DTL-27686, MIL-DTL-85470, MIL-I-25017, Biobor JF R134a See Section I of the approved Rotorcraft Flight Manual for detailed information Fluid capacities Fuel AW189 equipped with Core Avionics SW Release up to 6.0 Total A/C capacity litres [kg (lb) (*)] Unusable litres [kg (lb) (*)] Two main fuel tanks (LH and RH) 1295 [1036 (2284.0)] 24 [19 (41.9)] Two main fuel tanks (LH and RH) plus Forward Tanks 1533 [1272 (2804.3)] 28 [22 (48.5)] Two main fuel tanks (LH and RH) plus Auxiliary Central Tank 1823 [1458 (3214.316)] 30 [24 (41.9)] Two main fuel tanks (LH and RH) plus Forward Tanks plus Auxiliary Central Tank 2061 [1649 (3635.4)] 34 [27(59.5)] Extended Range (See Note 11) Two main fuel tanks (LH and RH) Plus underbelly tanks 2569 [2055 (4530.0)] 9 [7 (15.4)] (*) Considering a medium density between different fuels of 0.8kg/l AW189 equipped with Core Avionics SW Release 7.0 or later approved Total A/C capacity litres [kg (lb) (*)] Unusable litres [kg (lb) (*)] Two main fuel tanks (LH and RH) 1295 [1036 (2284.0)] 24 [19 (41.9)] Two main fuel tanks (LH and RH) plus Forward Tanks 1533 [1272 (2804.3)] 24 [19 (41.9)] Two main fuel tanks (LH and RH) plus Auxiliary Central Tank 1823 [145876 (3214.3.0)] 24[19 (41.9)] Two main fuel tanks (LH and RH) plus Forward Tanks plus Auxiliary Central Tank 2061 [1649 (3635.4)] 24 [19 (41.9)] Extended Range (See Note 11) Two main fuel tanks (LH and RH) Plus underbelly tanks 2569 [2055 (4530.0)] 9 [7 (15.4)] (*) Considering a medium density between different fuels of 0.8kg/l Oil Quantity litres [kg (lb)] ENGINE (each) minimum 3.6 [3.59 (7.91)] – maximum 5.5 [5.49 (12.10)] MAIN GEARBOX (minimum/maximum) minimum 21.5 [21.46 (47.31)] - maximum 27 [26.95 (59.41)] (24.5 + 2.5 for oil cooler, oil ducts and filter) INTERMEDIATE GEARBOX 1.22 [1.217 (2.683)] TAIL GEARBOX 1.87 [1.866 (4.114)] HYDRAULIC (per each Power Control Module) 3.20 [2.72 (6.00)] Coolant system capacity 2.9kg R00004RD 3 Rev. 5 Installed Engine Limits General Electric CT7-2E1 with EECU SW up to V5.0 Rating Max TQ [Lb-ft] Max ITT [°C (°F)] Max NG [% (rpm)] AEO Take-off 5 min. 515 968 (1774.4) 102.7 (45907) Maximum Continuous 490 942 (1727.6) 102.7 (45907) OEI 30 sec. 575 1078 (1972.4) 105 (46935) 2 min. 575 1078 (1972.4) 105 (46935) Continuous 515 968 (1774.4) 102.7 (45907) General Electric CT7-2E1 with GE EECU SW 6.0 or later: Rating Max TQ [Lb-ft] Max ITT [°C (°F)] Max NG [% (rpm)] Max NF [% (rpm)] AEO Continuous 490 957 (1754,6 ) 102.7 (45 907) 104.7 (22 000) Take-off 5 min. 515 983 (1801.4) 102.7 (45 907) - - - OEI Continuous 515 983 (1801,4) 102.7 (45 907) 104.7 (22 000) 2.5 min. 575 1101 (2013.8) 105 (46 935) - - - Transmission Limits AW189 with GE CT7-2E1 and Core Avionics Phase 3.0 SW Release Rating Max torque % (Lb-ft) Power (SHP) @ 102% NR OEI 30 sec. 1 x 164% (1 x 502.66) 2050.07 2min. 1 x 155% (1 x 475.08) 1937.59 Continuous 1 x 135% (1 x 413.78) 1687.58 AEO 30 min. (below 90 KIAS) 2 x116% (2 x 355.54 ) 1450.05 30min. (above 90 KIAS) 2 x112% (2 x 343.28) 1400.05 Maximum continuous 2 x100% (2 x 306.5 ) 1250.04 AW189 with GE CT7-2E1 and Core Avionics Phase 4.0 SW Release (or later) Rating Max Torque [%] Input Speed [rpm] Input Power [shp] AEO Max continuous 2 x 100 21, 420 2,500 30 min. 2 x 116 (*) 2,907 OEI Max continuous 1 x 142 21, 420 1,775 2.5 min. 1 x 172 (**) 2,150 (*) For airspeeds less than 90 KIAS. For airspeeds greater than 90 KIAS refer to RFM. (**) Between 164% and 175% allowed for 30 sec and once per 2.5 min. event R00004RD 4 Rev. 5 Rotor Limits Air Speed Limits VNE Power On AEO = 169 KIAS VNE Power On OEI = 139 KIAS VNE Power Off = 120 KIAS VLE/VLO (gear extended/gear operating) = 150 KIAS/150 KIAS See approved Rotorcraft Flight Manual for variations with altitude, OAT and weight. POWER ON AEO CONDITION (RPM) (%) Minimum Continuous 284.75 100.0 Maximum Continuous 296.14 104.0 POWER ON OEI CONDITION (RPM) (%) Minimum Cautionary 256.28 90.0 Minimum Continuous 284.75 100.0 Maximum Continuous 296.14 104.0 POWER OFF CONDITION (RPM) (%) Minimum Continuous 270.51 95.0 Maximum Continuous 313.23 110.0 R00004RD Rev. 5 AIRSPEED LIMITATION POWER OFF 140 150 160 PRESSURE ALTITUDE [It X 1000] NE [KIAS] ICN:-89-4-151000-0-A0128-00002-4-02-1 Center of Gravity (C. G.) Range 5.503 г 5.570 m 7100 kc 5.55 8600 - 5400 kg 0.09 m +0.106 m 5.477 ₩ 8400 8300 kg 8300 kg 8200 5.45 8000 7800 7600 7400 7200 · 7000 +0.122 m 6843 kg 6800 -0.097 m 6529 kg 6400 5.15 5.138 m 8300 kg 8200 8000 5.053 m 6425 kg 5800 MAST 5600 5400 -0.026 MAST +0.048 m 5400 kg 5400kg 5200• 5200 -0.12 -0.08 -0.04 BL [m] 0.04 0.08 0.12 189G1560A001 Iss A ICN-89-A-151000-G-A0126-00002-A-01-1 Weight And Longitudinal Cg Envelope Weight And Lateral Cg Envelope R00004RD Rev. 5 Ambient Temperature Limitations AW189 FLIGHT ENVELOPE OAT - [°F] -50-40-30-20-10 0 10 20 30 40 50 60 70 80 100 120 140 10000 3000 Minimum GW 9000 permitted 2800 for area A 6000 kg - 2600 (13228lb) 8000 1MIP 18800 K 2400 2200 7000 HALIMIT 8000 H 2000 6000 Pressure Altitude - [ft] 5000 MINIMUM OAT LIMIT 1600 Pressure Altitude TAKE OFF and 1400 LANDING ENVELOPE 1200 1000 3000 800 2000 600 400 1000 200 -200 -50 -40 -30 -20 • 10 10 20 30 40 50 60 OAT - [°C] 189G1560A001 Rev.C ICN-89-A-151000-G-A0126-00004-A-02-1 Maximum Operating Altitude and Temperature Altitude Maximum operating altitude 10000 ft (pressure/density altitude whichever occurs first) For aircraft equipped with Core Avionics Phase 5.0 SW release (or later) and Altitude Extension Kit P/N 8G0000F00511 the Maximum Operating Altitude is extended to 15 000 ft PA/DA (whichever comes first). Maximum Take-off and Landing altitude 8000 ft (pressure/density altitude whichever occurs first) Temperature -40°C ÷ +55°C (ISA+40°C) For variation of Temperature limitations with altitude, see the approved Rotorcraft FlightManual and applicable supplement R00004RD 7 Rev. 5 Datum Longitudinal Datum (STA 0) is located at 2830 mm forward to the front jack point On the Extended Range configuration (see Note 11) the longitudinal datum line (STA 0) is located at 3009 mm forward to the front jack point. Lateral Datum (BL 0) is located at +/- 275 mm inboard of LH/RH front jack points Leveling Means Plumb line from ceiling reference point to index plate on floor of passenger cabin Maximum weights - Taxi and Towing 8350 kg (See Note 12) - Take-off and Landing 8300 kg (See Note 12) Minimum Crew One (1) for VFR; Two (2) for IFR. (See also “Equipment” and NOTE 5.) For Cat. A operations, two (2) pilots are required if take-off and landing is to be carried out from the left seat. For NVG operations, two (2) pilots or one (1) pilot and one (1) crew member are required. Both pilot and crew member must be equipped with NVGs (see NOTE 10). Number of Seats 21 (2 crew – 19 passengers maximum) Maximum Baggage 300 kg (660 lb) located in the Baggage compartment (See Note 13) Baggage compartment max pressure load 550 kg/m2 (110 lb/sq. ft) Baggage compartment max load height 600 mm (2 ft) (See Note 13) Rotor Blades and Control Movements For rigging information, refer to the AW189 Maintenance Manual. Import Requirements To be considered eligible for operation in the United States, each aircraft manufactured under this Type Certificate must be accompanied by a Certificate of Airworthiness for Export or certifying statement endorsed by the exporting foreign civil airworthiness authority which states the following (in the English language): Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. “The rotorcraft covered by this certificate has been examined, tested and found to conform to the type design approved under FAA Type Certificate No. R00004RD and to be in condition for safe operation.” The only aircraft eligible for import into the United States are those aircraft with the configuration defined in Leonardo S.p.a. Report No. 189G0000P005, “AW189 - FAA Type Design Definition,” dated 26 February 2015 or latest issue.. Certification Basis (1) 14 CFR Part 21.29. (2) 14 CFR Part 29 Amendment 29-1 through 29-52, dated 30 March 2010 (See Note 16) (3) 14 CFR Part 36 Appendix H, Amendment 36-1 through 36-29 dated 11 March 2013. (4) Special Condition: • 30 Minute All Engines Operating (AEO) Power Rating: 14 CFR 29.1049, 29.1305, 29.1521 R00004RD 8 Rev. 5 (5) Equivalent Level of Safety Findings issued against: • 14 CFR § 29.807(c) Passenger emergency exits (documented in ELOS Memo TC4265RD-R-C-01) • 14 CFR § 29.813(c) Passenger access to each emergency exit (documented in ELOS Memo TC4265RD-R-C-02). • 14 CFR § 29.807 (d)(2) & (d)(3) Ditching emergency exits for passengers (documented in ELOS Memo TC4265RD- R-C-04). • 14 CFR § 29.815 Main aisle width (documented in ELOS Memo TC4265RD-R-C-05). • 14 CFR § 29.1545(b) Airspeed indicator (documented in ELOS Memo TC4265RD-R-F-01). • 14CFR §29.1305 and §29.1549 Power Index (documented in ELOS Memo TC4265RD-R-F-03) • 14CFR §29.1505(c) (2) Power-Off VNE (documented in ELOS Memo AT04309RD-R-F-1 • 14CFR §29.1505(c) (2) Power-Off VNE (documented in ELOS Memo AT11392IB-R-F-1 • 14CFR §29.923 and §29.927 Rotor drive system and control mechanism tests: Endurance and additional tests by test rig (documented in ELOS Memo AT19460IB-R-29.923 & 29.927 (6) Core Avionics SW Release Phase 7.0 and later For Core Avionics SW Release 7.0 and later compliance has been shown for the following requirements: • 29.1317 Amdt. 29-52 • Appendix E to Part 29, Amdt 29-52 • 29.610 Amdt. 29-53 • 29.1316 Amdt. 29-53 Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (See Certification Basis) must be installed in the helicopter for certification. The installation of the followings is mandatory for Ditching Operations (see Supplement 6 of the RFM): • Life rafts (life rafts P/N 8G2560F00511 have been approved for use by Leonardo S.p.a. The use of other life raft installations must be in accordance with CS/FAR 29 and must be approved) • Survival type Emergency Locator Transmitter • Life preservers (the following life preservers installations have been approved by Leonardo S.p.a: 8G2560F00611, 8G2560F00711, 8G2560F00811. Different life preserver installations must be in accordance with CS/FAR 29 and must be approved). The installation of the followings is mandatory for Night Vision Goggles Operations (see Supplement 14 of the RFM): • Aviator’s Night Vision Goggles as specified in 189G3360A001 “AW189 NVG Compatibility Reference Handbook” • Helmet with NVG mount suitable for NVG Model being used • Cockpit/Cabin physical separation device as defined in 189G3360A001 “AW189 NVG Compatibility Reference Handbook”. The installation of the following is mandatory for operations in Full Icing Conditions: • Kit Full Ice Protection System P/N 8G3000F00111 with DGCU P/N 8G2420V00351 (see RFM Supplement 44 or 49, according to the relevant aircraft configuration) The aircraft configuration approved for use in full icing condition is described in the Report 189G3000A001”AW189 Icing Compatibility Reference Handbook” Refer to approved Rotorcraft Flight Manual and related supplements for other approved mandatory and optional equipment. Refer to Kit Compatibility Handbook 189G0000A002 for incompatibilities and restrictions between optional equipment. AW189 Software Configuration is managed within the Software Handbook 189G0000X007. R00004RD 9 Rev. 5 Personal Electronic Device (PED)-sensitive equipment, which is under the responsibility of the TC Holder and is declared as NON-PED tolerant, or has PED tolerance limitations, is reported in the document 189G9850A005 “PED Compatibility Reference Handbook”. Service information Leonardo S.p.a. Service bulletins, structural repair manuals, vendor manuals, Rotorcraft Flight Manual, and overhaul and maintenance manuals, which contain a statement that the document is EASA approved, are accepted by the FAA and are considered FAA approved. These approvals pertain to the approved type design only. Flight Manual EASA approved on behalf of FAA Rotorcraft Flight Manual, 189G0290X002, Issue 1 Revision 3 or later approved revision (See NOTE 5). Maintenance Manual Maintenance Planning Information 89-B-AMPI-00-P Maintenance Publication 89-A-AMP-00-X. R00004RD 10 Rev. 5 NOTES NOTE 1 A current weight and balance report, including a list of equipment included in the certificated empty weight, must be provided for each helicopter at the time of original airworthiness certification in accordance with 14 CFR 29.25, 29.27 and 29.29. NOTE 2 All placards required by either FAA Approved Rotorcraft Flight Manual, the applicable operating rules, or the Certification Basis must be installed in the helicopter. NOTE 3 Information essential to the proper maintenance of the helicopter is contained in the Manufacturer’s Maintenance Manual provided with each helicopter. Life limited components and associated retirement times are presented in Chapter 4 and must be replaced accordingly. NOTE 4 The model AW189 rotorcraft employs electronic engine controls, commonly named Full authority Digital Engine Controls (FADEC), that are recognized to be more susceptible to Electromagnetic Interference (EMI) than rotorcraft that have non-electronic controls. (EMI may be the result of radiated or conducted interference.) For this reason modifications that add or change systems that have the potential for EMI, must either be qualified to a standard acceptable to the FAA or tested at the time of installation for interference with the FADEC. This type of testing must employ the particular FADEC diagnostic techniques and external diagnostic techniques. The test procedure must be FAA approved. NOTE 5 The FAA approved Rotorcraft Flight Manual (RFM) is identical to the EASA approved RFM; any exceptions unique for FAA are presented on yellow pages marked “EASA approved on behalf of FAA” or “FAA Approved”. They must be included in the FAA manual to reflect the differences noted below: 1. Section 1, LIMITATIONS, MINIMUM FLIGHT CREW: Requires two pilots for IFR 2. Section 4, Performance Data, NOISE CHARACTERISTICS: Model: AW189 General Electric GE CT7-2E1 Gross Weight 8300 kg Configuration Level Flyover EPNL Take Off EPNL Approach EPNL (EPNdB) (EPNdB) (EPNdB) 102% NR 102% NR 102% NR Clean aircraft No external kits installed 95.2 91.3 99.1 NOTE 6 The Leonardo S.p.a. Model AW189 incorporates an integrated avionics system using software-based line replaceable units (LRU) which share a digital signal transmission bus. The software configuration of the AW189, as delivered from production, is critical to the proper operation of the avionics and cockpit instrumentation system. Modification to the LRU software supplied with the AW189, replacement of an LRU with a different LRU, addition of new LRU, or alteration of an LRU interface could adversely affect the airworthiness of the certified software. No changes to the integrated avionics system should be made without coordination with the FAA Aircraft Certification Office (ACO) having jurisdiction over the modifier. NOTE 7 The hydraulic fluids must conform to MIL-PRF-83282 or MIL-PRF-5606 which is an alternate for low Temperature operation - see LIMITATIONS Section of the approved Rotorcraft Flight Manual. NOTE 8 Any changes to the type design of this helicopter by means of a amended type certificate (TC), supplemental type certificate (STC), or amended STC, requiring instructions for continued airworthiness (ICA's) must be submitted thru the project aircraft certification office (ACO) for review and acceptance by the Fort Worth -Aircraft Evaluation Group (FTW-AEG) Flight Standards District Office (FSDO) prior to the aircraft delivery, or upon issuance of the first standard airworthiness certificate for the affected aircraft, whichever occurs later as prescribed by Title 14 CFR 21.50. Type design changes by means of a field approval that require ICA's must have those ICA's reviewed by the field approving FSDO. NOTE 9 The AW189 name identifies production batches manufactured in conformity with the same Type Design. Applicable serial numbers: • S/N 49007: and subsequent, manufactured by AgustaWestland S.p.A. or Finmeccanica S.p.A., or Leonardo S.p.a. in Italy. • S/N 89001: and subsequent, manufactured by AgustaWestland S.p.A. or Finmeccanica S.p.A., or Leonardo S.p.a. in Italy. (See Note 11) • S/N 91001: and subsequent, manufactured by AgustaWestland S.p.A or Finmeccanica S.p.A., or Leonardo S.p.a. in UK. • S/N 92001 and subsequent, manufactured by AgustaWestland S.p.A. or Finmeccanica S.p.A.,or Leonardo S.p.a. in UK. (See Note 11). It should be noted that S/N 92001 and 92003 have been manufactured by AgustaWestland Ltd in UK. R00004RD 11 Rev. 5 NOTE 10 Night Vision Goggle operations may be granted by the local civil aviation authority if the rotorcraft is operated according to the limitations and procedures of RFM 189G0290X002 Supplement 14. The rotorcraft configuration involving internal and external light emitting and reflecting equipment approved for use with NVGs is described in Report 189G3360A001 “AW189 NVG Compatibility Reference Handbook”. Subsequent modifications and deviations to the NVG helicopter configuration shall be managed in accordance with AgustaWestland document 189G3360E001 “AW189 Helicopter NVG Policy” NOTE 11 Applicable to the extended range configuration when installed in accordance with Drawing 8G0000X00831 and Drawing 8G0000X00931. For detailed information, refer to Supplement 22 of the approved Rotorcraft Flight Manual. NOTE 12 Operation of the aircraft with a maximum weight up to 8600 kg is permitted provided kit P/N 8G0000F00111 is installed, and the limitation and procedures within RFM 189G0290X002 Supplement 21 are adhered to. NOTE 13 The installation of Vertical Cargo Net restrain system P/N 8G2550F00311 permits the maximum load to be carried in the baggage compartment to be increased to 360 Kg, and the maximum cargo height to be extended up to 700 mm (2 ft 3 ins). For detailed information, refer to approved Rotorcraft Flight Manual Section 1 – Baggage Compartment Limitations. The installation of the Heavy Duty Baggage Compartment Kit p/n 8G5010F00411, according to RFM Supplement 46, permits the maximum load in the baggage compartment to be increased to 460 kg. The installation of the Heavy Duty Baggage Compartment Kit p/n 8G5010F00511, according to RFM Supplement 46, permits maximum load in the baggage compartment of 280 kg. NOTE 14 NOTE 15 Removed. Removed NOTE 16 Kit Rescue Hoist and FIPS: For Kit Single Rescue Hoist (P/N 8G2591F00111), Kit Double Rescue Hoist (P/N 8G2591F00311), Kit Foldable Single Hoist (P/N 8G2591F00211) and Kit Full Ice Protection System (P/N 8G3000F00111, 8G3000F00311) design changes compliance to 14 CFR Part 29 Amendment 29-1 through 29-55, dated 31 January 2012 has been provided for the following requirements: • 29.571 Amdt.55 – Fatigue Tolerance Evaluation of Metallic Structure • 29.573 Amdt.54 – Damage Tolerance and Fatigue Evaluation of Composite Rotorcraft Structures. • Appendix A, A 29.4 Amdt.54 – Airworthiness Limitations Section Comparison between 14 CFR Part 29 Amendment 29-1 through 29-55 (dated 31 January 2012) and CS 29 Amdt.3 (dated 11 December 2012) is provided in LH report 189G0274A001. R00004RD 12 Rev. 5 Acronyms and Abbreviations AEO All Engines Operative CS Certification Specification CFR Code of Federal Regulations Doc. Document EASA European Union Aviation Safety Agency FAA Federal Aviation Administration GE General Electric ICAO International Civil Aviation Organisation IFR Instrument Flight Rules ISA International Standard Atmosphere LH Max Left Hand Maximum min. minute No. Number NVG Night Vision Goggle OAT Outside Air Temperature OEI One Engine Inoperative RFM Rotorcraft Flight Manual RH Right Hand sec. second SL Sea Level STA Station VNE Velocity Never Exceed VFR Visual Flight Rules ….END….