AGUSTA A109E Flight Manual

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A109E

ROTORCRAFT

FLIGHT MANUAL

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Page 1 UNMAINTAINED COPY A109E A109E ROTORCRAFT ROTORCRAFT FLIGHT MANUAL FLIGHT MANUAL...
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Page 3 ROTORCRAFT FLIGHT MANUAL AGUSTA A109E Approved by REGISTRO AERONAUTICO ITALIANO Copy assigned to helicopter S/N ......... .
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Page 5 UNMAINTAINED COPY RFM A109E This publication contains information proprietary to the Agusta Company. Reproduction and/or resale of the information or illustrations contained herein is not permitted without the written approval of Technical Publications Department - Logistic Engineering. Additional copies of this publication and/or change service may be obtained from: AGUSTA S.p.A.
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Page 7 UNMAINTAINED COPY RFM A109E LIST OF REVISED PAGES Revision Subject R.A.I. Approved — Issue Letter No. 96/2277/MAE dated 31-5-1996 — Issue Letter No. 96/3153/MAE (Supersedes issue dated 31-5-1996) dated 25-7-1996 — Issue Letter No. 97/3147/MAE (Supersedes issue dated 25-7-1996) dated 30-7-1997 Revised pages A-1/A-2, B-1/B-2, 1-33 and Letter No.
Page 8 UNMAINTAINED COPY RFM A109E (Cont.) Revision Subject R.A.I. Approved Revised pages A-1, B-1, B-2, B-3/B-4, Letter No. 98/2201/MAE 5-2, Appendix 7 page 4 of 5. dated 8-5-1998 Added page A-2, Appendix 17, 18 and 19. Revised pages A-2, B-1, B-2, B-3/B-4, Letter No.
Page 9 UNMAINTAINED COPY RFM A109E (Cont.) Revision Subject R.A.I. Approved Revised pages A-2, B-1 thru B-4, 1-42, 4-32 Letter No. 99-8181-TMI/C thru 4-34, Appendix 10 page 1 to 9 of 9. dated 27-7-1999 Added pages A-3/A-4. Deleted pages 4-35 and 4-36.
Page 10 UNMAINTAINED COPY RFM A109E (Cont.) Revision Subject R.A.I. Approved Revised pages A-3, A-4, B-1 thru B-5/B-6 Letter No. 00-5638-TMI/C and 5-3/5-4. dated 31 March 2000 Added Appendix 31. Revised pages A-4, B-1 thru B-5/B-6, Letter No. 00-6654-TMI/C 1-42, 2-14, 2-24, 4-6 and 5-3/5-4.
Page 11 UNMAINTAINED COPY RFM A109E (Cont.) Revision Subject E.N.A.C. Approved Revised pages B-1 thru B-6, Appendix 25 Letter No.02/171289/SPA pages 1, 2 and 4 thru 8 of 8. dated 22 May 2002 Added pages A-5/A-6. Revised pages A-5/A-6, B-1 thru B-6, 2-11 Letter No.02/171525/SPA...
Page 12 UNMAINTAINED COPY RFM A109E (Cont.) Revision Subject E.A.S.A. Approved Revised pages A-6, B-1 thru B-6 and Approval N° 2004-5763 Appendix 10. dated 2 June 2004 Revised pages A-6, B-1 thru B-6, 5-6, Approval N° 2004-7476 Appendix 7 pages 2 thru 5 of 5, Appendix...
Page 13 UNMAINTAINED COPY RFM A109E (Cont.) Revision Subject E.A.S.A. Approved Revised pages B-1 thru B-7, 5-6, Appen- Approved under the dix 10 (pages 4, 11, 12 of 15), Appendix 31 Authority of DOA (pages 3, 7 of 8), Appendix 41 (pages 2, 7 N°...
Page 14 UNMAINTAINED COPY RFM A109E (Cont.) Revision Subject E.A.S.A. Approved Revised pages A-8, B-1 thru B-7, Appen- Approval EASA.R.A.01446 dix 2 (pages 1 thru 9 of 9). dated 3 March 2008 Revised pages A-8, B-1 thru B-7 and 5-8. Approval EASA.R.C.02849, EASA.R.C.02850 and...
Page 15 UNMAINTAINED COPY RFM A109E NOTE: Revised text is indicated by a black vertical line in the outer margin of the page and the approval revision number is printed in the lower margin. LOG OF PAGES Page Revision No. Page Revision No.
Page 16 UNMAINTAINED COPY RFM A109E LOG OF PAGES (Contd.) Page Revision No. Page Revision No. 2-i and 2-ii 2-39 2-1 and 2-2 2-40 2-41 2-4 and 2-5 2-42 2-6 and 2-7 2-42A 2-8 and 2-9 2-42B blank 2-10 2-43 and 2-44...
Page 17 UNMAINTAINED COPY RFM A109E LOG OF PAGES (Contd.) Page Revision No. Page Revision No. 3-27 3-28 3-29 thru 3-35 5-5 and 5-6 3-36 and 3-37 3-38 thru 3-44 3-45 thru 3-48 Appendix 1 3-48A thru 3-48C 1 and 2 of 5...
Page 18 UNMAINTAINED COPY RFM A109E LOG OF PAGES (Contd.) Page Revision No. Page Revision No. 2 of 15 30 thru 32 of 88 3 of 15 33 and 34 of 88 4 of 15 34A and 34B of 88 5 of 15...
Page 19 UNMAINTAINED COPY RFM A109E LOG OF PAGES (Contd.) Page Revision No. Page Revision No. 2 thru 5 of 12 Appendix 24 6 of 12 1 and 2 of 28 7 of 12 3 of 28 8 of 12 4 thru 7 of 28...
Page 20 UNMAINTAINED COPY RFM A109E LOG OF PAGES (Contd.) Page Revision No. Page Revision No. 3 of 8 7 of 8 4 thru 6 of 8 8 of 8 7 of 8 Appendix 42 8 of 8 1 thru 16 of 16...
Page 21 UNMAINTAINED COPY RFM A109E LOG OF PAGES (Contd.) Page Revision No. Page Revision No. Appendix 49 Appendix 50 8-10 blank PART II - MANUFACTURER’S DATA 9-ii blank 9-1 thru 9-22 6-ii blank 6-5 and 6-6, 6-6A and 6-6B 11 6-7 thru 6-10...
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Page 23: Table Of Contents
UNMAINTAINED COPY RFM A109E TABLE OF CONTENTS INTRODUCTION ........... . .iii PART I - R.A.I.
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Page 25: Introduction
UNMAINTAINED COPY RFM A109E INTRODUCTION GENERAL It is responsibility of the flight crew to be familiar with the contents of the RFM including all revisions and any temporary revision and supplement which are applicable at the time of flight. The contents of this copy shall correspond with the revisions which are shown on the Log of Pages.
Page 26 UNMAINTAINED COPY RFM A109E USE OF PROCEDURAL WORDS The concept of procedural word usage and intended meaning which has been adhered to in preparing this RFM is as follows: ″Shall″ or ″Must″ have been used only when application of a procedure is mandatory.
Page 27 UNMAINTAINED COPY RFM A109E – CAS : Calibrated Airspeed – CVDR : Cockpit Voice Data Recorder – CVR : Cockpit Voice Recorder – DAU : Data Acquisition Unit – d.c. : Direct current – EAPS : Engine Air Particle Separator –...
Page 28 UNMAINTAINED COPY RFM A109E – OAT : Outside Air Temperature – OEI : One Engine Inoperative – PAX : Passenger(s) – PLA : Power Lever Angle (alias En- gine Power Lever) – PMS : Power Management Switch (alias engine mode switch) –...
Page 29 UNMAINTAINED COPY RFM A109E Helicopter - Three Views. vii/(viii blank) Rev. 6...
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Page 31 UNMAINTAINED COPY RFM A109E LIST OF REVISED PAGES Revision Subject F.A.A. Approved — Issue 26-8-1996 — Issue 30-7-1997 (Supersedes issue dated 26-8-1996) Revised pages A-1/A-2, B-1, B-2, 1-33 21-5-1998 and 5-1/5-2. Added Appendices 10 and 11. Revised pages A-1/A-2, B-1, B-2, v, vi,...
Page 32 UNMAINTAINED COPY RFM A109E Revision Subject F.A.A. Approved Revised pages B-1, B-2, B-3/B-4, vii/viii 15-7-1998 and Appendix 15 page 4 of 11. Added page A-2. Revised pages A-2, B-1, B-2, B-3/B-4, vi, 13-1-1999 5-2, Appendix 15 page 1, 2, 4 and 5 of 11.
Page 33 UNMAINTAINED COPY RFM A109E (Cont.) Revision Subject F.A.A. Approved Revised pages B-1, B-2, B-3, B-4, 1-42, 16-12-1999 4-32 thru 4-34, Appendix 10 page 1 to 9 of 9. Added pages A-3/A-4. Deleted pages 4-35 and 4-36. Revised pages A-3/A-4, B-1, B-2, B-3,...
Page 34 UNMAINTAINED COPY RFM A109E (Cont.) Revision Subject F.A.A. Approved Revised pages A-3, A-4, B-1 thru B-5/B-6, 27-03-2000 2-21, 2-25, 3-48A thru 3-48E, 3-48J, 3-48M, 5-2 and 5-3/5-4, Appendix 15 page 1 of 11, Appendix 29 pages 4 and 5 of 15.
Page 35 UNMAINTAINED COPY RFM A109E (Cont.) Revision Subject F.A.A. Approved Revised pages B-1 thru B-6, 5-3 and 7-03-2002 5-5/5-6. Added page A-5/A-6 and Appendix 38. Revised pages A-5/A-6, B-1 thru B-6, 14-06-2002 Appendix 25 pages 1 thru 8 of 8 and Appendix 37 pages 1 thru 4 of 4.
Page 36 UNMAINTAINED COPY RFM A109E (Cont.) Revision Subject F.A.A. Approved Revised pages A-6, B-1 thru B-6 and 27-6-2005 Appendix 10. Revised pages A-6, B-1 thru B-6, 5-6, 27-6-2005 Appendix 7 pages 2 thru 5 of 5, Appendix 10 pages 2, 4, 5, 11, 13 and 14 of 15, Appendix 42 pages 1 and 2 of 14.
Page 37 UNMAINTAINED COPY RFM A109E (Cont.) Revision Subject F.A.A. Approved Revised pages B-1 thru B-7, 5-6, Appen- Not F.A.A. approved dix 10 (pages 4, 11, 12 of 15), Appendix 31 (pages 3, 7 of 8), Appendix 41 (pages 2, 7 of 8).
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Page 39: Part I - R.a.i. Approved
LOG OF PAGES NOTE: The yellow pages apply to F.A.A. registered A109E helicopters only and supersede the corresponding pages of the Rotorcraft Flight Manual. The holders of the Rotorcraft Flight Manual who are affected shall place the attached pages in front of the corresponding pages of the basic Rotorcraft Flight Manual.
Page 40 UNMAINTAINED COPY RFM A109E LOG OF PAGES (Contd.) Page Revision No. Page Revision No. 1-34B blank 2-28 1-35 thru 1-37 2-29 1-38 2-30 and 2-31 1-39 and 1-40 2-32 1-41 2-33 1-42 2-34 1-43 2-35 1-44 blank 2-36 2-i and 2-ii...
Page 41 UNMAINTAINED COPY RFM A109E LOG OF PAGES (Contd.) Page Revision No. Page Revision No. 3-15 4-7 thru 4-10 3-16 4-11 and 4-12 3-17 4-13 3-18 4-14 and 4-15 3-19 thru 3-21 4-16 3-22 4-17 and 4-18 3-23 4-19 3-24 4-20 thru 4-31...
Page 42 UNMAINTAINED COPY RFM A109E LOG OF PAGES (Contd.) Page Revision No. Page Revision No. 7 and 8 of 18 15 thru 18 of 88 9 thru 18 of 18 18A and 18B of 88 Appendix 7 19 of 88 1 of 5...
Page 43 UNMAINTAINED COPY RFM A109E LOG OF PAGES (Contd.) Page Revision No. Page Revision No. 69 of 88 Appendix 21 70 of 88 1 and 2 of 12 70A of 88 3 of 12 70B blank of 88 4 of 12...
Page 44 UNMAINTAINED COPY RFM A109E LOG OF PAGES (Contd.) Page Revision No. Page Revision No. Appendix 27 3 of 5 Appendix 28 4 and 5 of 5 1 of 108 Appendix 36 2 of 108 Appendix 37 3 thru 7 of 108...
Page 45 UNMAINTAINED COPY RFM A109E LOG OF PAGES (Contd.) Page Revision No. Page Revision No. 8 thru 13 of 90 6-14 blank 14 of 90 15 thru 18 of 90 7-ii and 7-iii 19 of 90 7-iv blank 20 thru 44 of 90...
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Page 47 UNMAINTAINED COPY RFM A109E IFR OPERATION REQUIRED EQUIPMENT FOR IFR FLIGHT SINGLE PILOT In addition to that required for VFR day and night flight, the following items must be operational before IFR flight is initiated. — SAS1, SAS2, ATTD HOLD —...
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Page 49 UNMAINTAINED COPY RFM A109E NOISE CHARACTERISTICS The following noise levels comply with ICAO Annex 16, Chapter 8 ’’Noise requirements’’ and FAR part 36 Appendix H. Model:A109E Engine: Pratt & Whitney 206C Gross Weight: 2850 Kg Configuration Level flyover Takeoff Approach...
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Page 51 UNMAINTAINED COPY RFM A109E PART I R.A.I. Approved...
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Page 53 UNMAINTAINED COPY RFM A109E SECTION 1 LIMITATION TABLE OF CONTENTS Page GENERAL 1–1 BASIS OF CERTIFICATION 1–1 TYPE OF OPERATION 1–1 VFR OPERATION 1–1 FLIGHT WITH DOORS REMOVED 1–1 IFR OPERATION 1–2 REQUIRED EQUIPMENT FOR IFR FLIGHT SINGLE PILOT 1–2...
Page 54 UNMAINTAINED COPY RFM A109E List of illustrations (Contd.) Page TAIL ROTOR GEARBOX LUBRICANT LIMITATIONS 1–16B ENGINE STARTER LIMITATIONS 1–16B GENERATOR LIMITATIONS 1–16B CROSS START OPERATION 1–16B MAIN HYDRAULIC SYSTEM LIMITATIONS 1–17 FLUID PRESSURE 1–17 UTILITY HYDRAULIC SYSTEM LIMITATIONS 1–17 NORMAL SYSTEM FLUID PRESSURE 1–17...
Page 55 UNMAINTAINED COPY RFM A109E List of illustrations (Contd.) Page Figure 1-19. EDU 1 - TORQUE (AEO) 1–28 Figure 1-20. EDU 1 - TORQUE (OEI) 1–29 Figure 1-21. EDU 1 - ROTOR POWER TURBINE SPEED (AEO) 1–30 Figure 1-22. EDU 1 - ROTOR SPEED (Power off) 1–31...
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Page 57: Limitations
UNMAINTAINED COPY RFM A109E SECTION 1 LIMITATIONS GENERAL COMPLIANCE WITH THE OPERATING LIMITATIONS IN SECTION 1 OF THIS MANUAL IS MANDATORY. THE HELICOPTER MUST ALSO BE OPERATED IN ACCORDANCE WITH THE APPROPRIATE OPERATING RULES. BASIS OF CERTIFICATION The helicopter is certified under FAR Part 27 with the exemption to para 27.1(a) for maximum gross weight increase to 2850 kg (6283 lb).
Page 58 UNMAINTAINED COPY RFM A109E IFR OPERATION REQUIRED EQUIPMENT FOR IFR FLIGHT SINGLE PILOT In addition to that required for VFR day and night flight, the following items must be operational before IFR flight is initiated. — SAS1, SAS2, ATTD HOLD —...
Page 59 UNMAINTAINED COPY RFM A109E OPTIONAL EQUIPMENT Refer to Section 5 and to pertinent Appendices for additional limitations, procedures and performance data with optional equipment installed. FLIGHT CREW The minimum flight crew consists of one pilot who shall operate the helicopter from the right crew seat.
Page 60 UNMAINTAINED COPY RFM A109E AIRSPEED LIMITATION - VNE (POWER ON) 20000 19000 18000 17000 16000 15000 14000 13000 12000 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 OAT - ˚C -1000 INDICATED AIRSPEED (PILOT) - KNOTS ABHD079C TR 109-60-114/II REV C Fig.
Page 61 UNMAINTAINED COPY RFM A109E AIRSPEED LIMITATION - VNE (POWER OFF/OEI) 20000 19000 18000 17000 16000 15000 14000 13000 12000 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 OAT - ˚C -1000 INDICATED AIRSPEED (PILOT) - KNOTS ABHD080C TR 109-60-114/II REV C Fig.
Page 62 UNMAINTAINED COPY RFM A109E GROUND SPEED LIMITATIONS On concrete even surfaces: Maximum speed for running takeoff and landing : 40 Kts Maximum taxiing speed (nose wheel unlocked) - straight : 20 Kts - turn : 10 Kts On unprepared or uneven surfaces:...
Page 63 UNMAINTAINED COPY RFM A109E NOTE Longitudinal Station ″0″ is 1835 mm forward of the front jack point. Fig. 1-3 (sheet 1 of 2). Longitudinal CG limits (metric). R.A.I. Approved...
Page 64 UNMAINTAINED COPY RFM A109E NOTE Longitudinal Station ″0″ is 72.2 in. forward of the front jack point. Fig. 1-3 (sheet 2 of 2). Longitudinal CG limits (english). R.A.I. Approved...
Page 65 UNMAINTAINED COPY RFM A109E NOTE The lateral station ″0″ is 450 mm inboard from each main jack point and coincides with the helicopter longitudinal plane of symmetry. Fig. 1-4 (sheet 1 of 2). Lateral CG limits (metric). R.A.I. Approved 1-8A...
Page 66 UNMAINTAINED COPY RFM A109E NOTE The lateral station ″0″ is 17.7 in. inboard from each main jack point and coincides with the helicopter longitudinal plane of symmetry. Fig. 1-4 (sheet 2 of 2). Lateral CG limits (english). 1-8B R.A.I. Approved...
Page 67 UNMAINTAINED COPY RFM A109E BAGGAGE COMPARTMENT LIMITATIONS Maximum load : 150 kg (330 lb) NOTE Refer to Section 6, Weight and Balance, for load distribution. Maximum unit load : 500 kg/m (102 lbs/sq ft) R.A.I. Approved 1-8C/(1-8D blank) Rev. 11...
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Page 69 UNMAINTAINED COPY RFM A109E ALTITUDE LIMITATIONS Maximum pressure altitude for takeoff and landing: : 15000 ft (4572 m) Maximum operating pressure altitude: : 20000 ft (6096m) AMBIENT AIR TEMPERATURE LIMITATIONS The minimum ambient air temperature for operation is -25°C (-13°F).
Page 70 UNMAINTAINED COPY RFM A109E One engine inoperative (OEI) Continuous operation : 50 to 100.4% Maximum continuous : 100.4% 2.5 minute range : 100.4 to 102.4% Maximum : 102.4% Transient (20 sec) : 103.4% POWER TURBINE (N2) RPM NOTE 100% N2 corresponds to 6000 RPM output shaft speed and to 39807 RPM power turbine speed.
Page 71 UNMAINTAINED COPY RFM A109E TURBINE OUTLET TEMPERATURE (TOT) All engines operative (AEO) Maximum continuous : 820°C Takeoff (5 min) range : 820°C to 863°C Maximum : 863°C One engine inoperative (OEI) Maximum continuous : 885°C 2.5 min range : 885°C to 930°C Maximum : 930°C...
Page 72 UNMAINTAINED COPY RFM A109E Power On (OEI) Minimum : 90% Takeoff and landing : 90 to 99% Continuous operation : 99 to 101% Takeoff and landing (below 60 KIAS and 1000 ft AGL) : 101 to 102% NOTE During an instrumental approach procedure the use of 102% NR is allowed up to 120 KIAS.
Page 73 UNMAINTAINED COPY RFM A109E One engine inoperative (OEI) Maximum continuous : 124% 2.5 min : 142% Transient (6 sec) : 156% NOTE The One Engine Inoperative (OEI) rating use is intended for emergency use, when one engine becomes inoperative due to an actual malfunction.
Page 74 UNMAINTAINED COPY RFM A109E Military Specification (Reference only) Type Specification JP-4 (*) MIL-T-5624 JP-5 (*) MIL-T-5624 JP-8 (*) MIL-T-83133 (*) Contains fuel system icing inhibitor (FSII). (for JP-8, MIL-T-83133C allows two grades. The grade meeting NATO code F-34 has FSII while the grade meeting code F-35 has no FSII without prior agreement).
Page 75 UNMAINTAINED COPY RFM A109E ENGINE LUBRICATION SYSTEM LIMITATIONS Oil pressure The oil pressure limits vary as function of the gas generator speed according to figure 1-5. These oil pressure limits must be respected when engine oil temperature is between 71 - 120°C.
Page 76 UNMAINTAINED COPY RFM A109E Fig. 1-5. Engine oil pressure limits 1-16 R.A.I. Approved...
Page 77 UNMAINTAINED COPY RFM A109E MAIN TRANSMISSION LUBRICATION SYSTEM LIMITATIONS Oil pressure Minimum : 30 psi Normal range : 30 to 50 psi Cautionary range : 50 to 70 psi Maximum : 70 psi Oil temperature Maximum : 115 °C Approved lubricating oils...
Page 78: Tail Rotor Gearbox Lubricant Limitations
UNMAINTAINED COPY RFM A109E TAIL ROTOR GEARBOX LUBRICANT LIMITATIONS Approved lubricating oils DESIGNATION SPECIFICATION BP Turbo Oil 2380 / EXXON Turbo Oil 2380 MIL-PRF-23699 BP Turbo Oil 2197 MIL-PRF-23699 Mobil Oil Jet II MIL-PRF-23699 Mobil Oil Jet 254 MIL-PRF-23699 AeroShell Turbine Oil 500...
Page 79 UNMAINTAINED COPY RFM A109E Maximum : 160 A Transient (20 seconds) : 200 A Helicopter not equipped with emergency bus: For each generator Continuous operation : 0 to 130 A Maximum : 130 A Transient (20 seconds) : 160 A E.A.S.A.
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Page 81: Main Hydraulic System Limitations Fluid Pressure
UNMAINTAINED COPY RFM A109E MAIN HYDRAULIC SYSTEM LIMITATIONS FLUID PRESSURE Minimum : 1200 psi Cautionary range : 1200 to 1400 psi Normal range : 1400 to 1550 psi Maximum : 1550 psi Approved fluids Hydraulic fluid MIL-H-5606 WARNING Operation of each hydraulic system must be checked before each flight in accordance with Section 2 of this manual.
Page 82: Instrument Markings
UNMAINTAINED COPY RFM A109E INSTRUMENT MARKINGS Fig. 1-6. Airspeed indicator 1-18 R.A.I. Approved...
Page 83: Electronic Display Unit Formats
UNMAINTAINED COPY RFM A109E ELECTRONIC DISPLAY UNIT FORMATS The EDUs present the following information: EDU 1 EDU 2 - Engine oil pressure - N1 - Engine oil temperature - NR/N2 - Transmission oil pressure - TOT - Transmission oil temperature...
Page 84 UNMAINTAINED COPY RFM A109E Fig. 1-7. EDU 1 - START Mode (AEO) The START mode is displayed when selected by the START key on EDU 1. Fig. 1-8. EDU 1 - CRUISE Mode (AEO) The CRUISE mode is displayed upon IDS initialization and/or when selected by the CRUISE key or automatically at the end of the start sequence.
Page 85 UNMAINTAINED COPY RFM A109E Fig. 1-9. EDU 1 - OEI Mode The OEI mode is a subset of CRUISE mode and is automatically selected if one engine becomes inoperative. The OEI format is presented also in REVERSIONARY mode. Fig. 1-10. EDU 1 - AUTOROTATION Mode The AUTOROTATION mode is automatically selected when both engines fail or run at idle, both engine torque inputs are at zero or in presence of NR/N2 split.
Page 86 UNMAINTAINED COPY RFM A109E Intentionally blank Fig. 1-11. Blank Fig. 1-12. EDU 2 - MAIN Mode The MAIN mode is displayed upon IDS initialization and/or when selected by the MAIN key on EDU 2. 1-22 R.A.I. Approved...
Page 87 UNMAINTAINED COPY RFM A109E Fig. 1-13. EDU 2 - AUXILIARY Mode The AUXILIARY mode can be displayed by selecting the AUX key on EDU 2. The AUXILIARY page reverts automatically to the MAIN page when any caution/warning message occurs. Fig. 1-14. EDU 1 and/or EDU 2 - REVERSIONARY Mode...
Page 88 UNMAINTAINED COPY RFM A109E Fig. 1-15. EDU 1 - GAS GENERATOR SPEED (AEO) 1-24 R.A.I. Approved Rev. 2...
Page 89 UNMAINTAINED COPY RFM A109E Fig. 1-16. EDU 1 - GAS GENERATOR SPEED (OEI) R.A.I. Approved 1-25...
Page 90 UNMAINTAINED COPY RFM A109E Fig. 1-17. EDU 1 - TURBINE OUTLET TEMPERATURE (AEO) 1-26 R.A.I. Approved...
Page 91 UNMAINTAINED COPY RFM A109E Fig. 1-18. EDU 1 - TURBINE OUTLET TEMPERATURE (OEI) R.A.I. Approved 1-27 Rev. 11...
Page 92 UNMAINTAINED COPY RFM A109E Fig. 1-19. EDU 1 - TORQUE (AEO) 1-28 R.A.I. Approved...
Page 93 UNMAINTAINED COPY RFM A109E Fig. 1-20. EDU 1 - TORQUE (OEI) R.A.I. Approved 1-29 Rev. 11...
Page 94 UNMAINTAINED COPY RFM A109E Fig. 1-21. EDU 1 - ROTOR POWER TURBINE SPEED (AEO) 1-30 R.A.I. Approved...
Page 95 UNMAINTAINED COPY RFM A109E Fig. 1-22. EDU 1 - ROTOR SPEED (Power off) R.A.I. Approved 1-31...
Page 96 UNMAINTAINED COPY RFM A109E Fig. 1-23. EDU 1 - ROTOR POWER TURBINE SPEED (OEI) 1-32 R.A.I. Approved Rev. 2...
Page 97 UNMAINTAINED COPY RFM A109E Fig. 1-24. EDU 2 (MAIN) - ENGINE OIL PRESSURE R.A.I. Approved 1-33 Rev. 1...
Page 98 UNMAINTAINED COPY RFM A109E Fig. 1-25. EDU 2 (MAIN) - ENGINE OIL TEMPERATURE 1-34 R.A.I. Approved...
Page 99 UNMAINTAINED COPY RFM A109E (Helicopters equipped with EDU P/N 109-0900-42-2A08 or later) Figure 1-25A. EDU 2 (MAIN) - ENGINE OIL TEMPERATURE. E.A.S.A. Approved 1-34A/(1-34B blank) Rev. 42...
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Page 101 UNMAINTAINED COPY RFM A109E Fig. 1-26. EDU 2 (MAIN) - TRANSMISSION OIL (PRESSURE AND TEMPERATURE) R.A.I. Approved 1-35...
Page 102 UNMAINTAINED COPY RFM A109E Fig. 1-27. EDU 2 (MAIN/AUXILIARY) - MAIN HYDRAULIC SYSTEM PRESSURE 1-36 R.A.I. Approved...
Page 103 UNMAINTAINED COPY RFM A109E Fig. 1-28. EDU 2 (MAIN) - FUEL PRESSURE R.A.I. Approved 1-37...
Page 104 UNMAINTAINED COPY RFM A109E Fig. 1-29. EDU 2 (AUXILIARY) - AMMETER. 1-38 E.A.S.A. Approved Rev. 39...
Page 105 UNMAINTAINED COPY RFM A109E Fig. 1-30. EDU 2 (AUXILIARY) - UTILITY HYDRAULIC SYSTEM PRESSURE (NORMAL) R.A.I. Approved 1-39 Rev. 2...
Page 106 UNMAINTAINED COPY RFM A109E Fig. 1-31. EDU 2 (AUXILIARY) - UTILITY HYDRAULIC SYSTEM PRESSURE (EMERGENCY) 1-40 R.A.I. Approved Rev. 2...
Page 107 UNMAINTAINED COPY RFM A109E PLACARDS THE MARKINGS AND PLACARDS INSTALLED ON THIS HELICOPTER CONTAIN OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS HELICOPTER. OTHER OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS HELICOPTER ARE CONTAINED IN THE R.A.I.
Page 108 UNMAINTAINED COPY RFM A109E IN ALTN POSITION CLOSE VENTS AND TURN HEATER/ECS OFF In clear view of the pilot IN ALTN POSN MAINTAIN INST ACCURACY BY CLOSING WINDOWS VENTS AND TURNING HEATER OFF In clear view of the pilot, only with sliding windows P/N 109-0822-68 installed ALT.
Page 109 UNMAINTAINED COPY RFM A109E MAXIMUM ALLOWABLE BAGGAGE LOAD ZONE MAX UNIT FLOOR LOADING 500 KG/M (102 LB/SQ.FT.) Baggage compartment ALL CARGO MUST BE SECURED MAX LOAD PER TIE DOWN RlNG 91 KG (200 LB) Baggage compartment R.A.I. Approved 1-43/(1-44 blank)
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Page 111: Normal Procedures
UNMAINTAINED COPY RFM A109E SECTION 2 NORMAL PROCEDURES TABLE OF CONTENTS Page INTRODUCTION 2–1 FLIGHT PLANNING 2–1 TAKE-OFF AND LANDING DATA 2–2 WEIGHT AND BALANCE DATA 2–2 PREFLIGHT CHECKS 2–2 PILOT’S DAILY PREFLIGHT CHECK 2–3 PILOT’S PREFLIGHT CHECK 2–14 ENGINE PRE-START CHECK 2–15...
Page 112 UNMAINTAINED COPY RFM A109E LIST OF ILLUSTRATIONS Page Figure 2-1. Preflight check sequence 2–4 2-ii E.A.S.A. Approved Rev. 42...
Page 113 UNMAINTAINED COPY RFM A109E SECTION 2 NORMAL PROCEDURES INTRODUCTION This section contains instructions and procedures for operating the helicopter from the planning stage, through actual flight conditions, to securing the helicopter after landing. Normal and standard conditions are assumed in these procedures. Pertinent data in other sections is referenced when applicable.
Page 114 UNMAINTAINED COPY RFM A109E TAKE-OFF AND LANDING DATA Refer to Section 1 - LIMITATIONS and Section 4 - PERFORMANCE . WEIGHT AND BALANCE DATA Ascertain proper weight and balance of the helicopter as follows: — Consult Section 6 - Weight and Balance.
Page 115 UNMAINTAINED COPY RFM A109E PILOT’S DAILY PREFLIGHT CHECK (First flight of the day) The following procedure outlines the pilot walk-around and interior checks (Figure 2-1). Main and tail rotor tie-down (if present) : Removed. AREA N° 1 (Helicopter nose) Nose exterior : Condition.
Page 116 UNMAINTAINED COPY RFM A109E AREA No. 1 : Helicopter nose AREA No. 2 : Fuselage - RH side AREA No. 3 : Tail boom - RH side AREA No. 4 : Fins, 90° gearbox, tail rotor, tail skid AREA No. 5 : Tail boom - LH side AREA No.
Page 117 UNMAINTAINED COPY RFM A109E AREA N° 2 (Fuselage - rh side) Windshield and roof transparent panel : Condition and cleanliness. Pitot tube : Cover removed, condition and obstructions. IDS external air temperature probe : Condition, free of obstructions. Fuselage exterior : Condition.
Page 118 UNMAINTAINED COPY RFM A109E Main rotor pitch change links : Condition and security. Upper anticollision light : Condition. Servo actuator : Condition and leaks. Main transmission and accessories (visible area) : Condition and leaks. Transmission oil cooler : Free of obstructions.
Page 119 UNMAINTAINED COPY RFM A109E Engine cowling : Condition, secured. Fuel filler cap : Secured. Main landing gear : Condition, shock strut exten- sion, leaks, tire pressure. Drain and vent lines : Free of obstructions. Lower anticollision light : Condition. Antenna(s) (if installed) : Condition.
Page 120 UNMAINTAINED COPY RFM A109E Access door : Secured. Tail navigation light : Condition. Tail rotor hub and blades : Condition, cleanliness and freedom of flapping. Tail rotor pitch change mechanism : Condition and security. Area n° 5 (tail boom - lh side) Tail boom exterior : Condition.
Page 121 UNMAINTAINED COPY RFM A109E NOTE The above mentioned circuit breakers are accessible from bag- gage compartment through an inspection door. Baggage door : Secured. Lower avionic bay access door : Secured. Tail rotor middle drive shaft bearings : Check condition verifying no mark slippage.
Page 122 UNMAINTAINED COPY RFM A109E Upper anticollision light : Condition. Swashplate and driving scissors : Condition and security. Main transmission and accessories (visible area) : Condition and leaks. Transmission : Filler cap secured. Transmission oil : Check correct level. Door se- cured.
Page 123 UNMAINTAINED COPY RFM A109E Passenger cabin door : Condition, cleanliness, window secured. Cowling and fairings : Condition and security. Copilot cabin door : Condition, cleanliness, window secured. Antenna(s) : Condition. Pitot tube : Cover removed, condition and obstructions. Windshield and roof transparent panel : Condition and cleanliness.
Page 124 UNMAINTAINED COPY RFM A109E Copilot flight controls (if installed) : Condition and security. Landing gear lever lock : Check in NORMAL position and lockwired. Lower and lateral transparent panels : Cleanliness and integrity. Copilot door : Security. Sliding window closed, if installed.
Page 125 UNMAINTAINED COPY RFM A109E Pilot seat : Security. Pilot flight controls : Condition and security. Lower and lateral transparent panels : Cleanliness and integrity. Instruments, panels and breakers : Condition and legibility. ELT switch on instrument panel (if installed) : Check in ARM position.
Page 126 UNMAINTAINED COPY RFM A109E RH airframe (A/F) fuel filter : Gently drain while respective fuel pump is operating. Check for by-pass indication, # 2 A/F F FLTR caution mes- sage on EDU 1, by pushing red button on filter. NOTE Fuel is pressurized, therefore drainage should be carried out by gently pushing red button.
Page 127 UNMAINTAINED COPY RFM A109E Stabilizers : Condition and security. Nose and main landing gear : Check. Access doors nose compartment, tail rotor gearbox, baggage compartment, lower avionic bay : Security. Cowlings, fairings and relevant access doors : Condition and security, check for evidence of oil.
Page 128 UNMAINTAINED COPY RFM A109E Cabin interior and baggage compart- ment : Security of equipment and cargo. Main and tail rotor blades : Check. 2-14B E.A.S.A. Approved Rev. 41...
Page 129 UNMAINTAINED COPY RFM A109E Air intakes : Free of obstructions. Covers re- moved. Engine exhausts : Check. Covers removed. Fuel filler cap : Secured. Crew safety belts and inertia reels : Condition, belt fastened. Tail rotor gearbox : Check oil level, check for leaks and for filler cap secured.
Page 130 UNMAINTAINED COPY RFM A109E Collective lever : Full down and friction adjusted. Circuit breakers : All engaged. Engine power levers : OFF (full aft). ENG 1 and 2 MODE switches : OFF (fully counterclockwise). LD-SH (Load share) switch : As required.
Page 131 UNMAINTAINED COPY RFM A109E NOTE (Only for helicopters equipped with emergency bus). The battery is automatically disconnect when an external power source is connected to the helicopter. Check that BATT OFF caution message is displayed on EDU 1 if the external power is used.
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Page 133 UNMAINTAINED COPY RFM A109E GEN BUS 1 and 2 : ON. GEN 1 and 2 : ON Force trim : ON. Electronic Display Units (EDU 1 and EDU 2) : Check on. NOTE Both EDUs are automatically activated when the helicopter is electrically powered: EDU 1 in CRUISE mode and EDU 2 in MAIN mode.
Page 134 UNMAINTAINED COPY RFM A109E NOTE It is possible to listen to only one of the ENG FIRE messages due to the short length of the EDU TEST. The ENG FIRE message of the second engine can be heard, even during the test sequence, by pushing the MASTER WARNING RESET pushbutton.
Page 135 UNMAINTAINED COPY RFM A109E NOTE In case of different result of TEST sequence refer to pertinent paragraph in Section 3. EDU 1 and EDU 2 : After 10 seconds automatically return to previous selected for- mats. EDU 1 : Select MENU and enter page 2.
Page 136 UNMAINTAINED COPY RFM A109E ADI stand-by : Flag retracted, erect (operate ″PULL TO CAGE″ knob, if necessary). Fuel quantity : Check. RPM switch (on collective control) : Set 100%. Engine power levers : Set gently to FLIGHT position. CAUTION Avoid rapid movement of engine power levers in order to not damage the internal mechanism.
Page 137 UNMAINTAINED COPY RFM A109E FUEL PUMP 1 switch : ON - FUEL PUMP 1 caution message out, check pressure. ENG 2 FUEL switch : ON - Fuel valve indicator ver- tical. FUEL PUMP 2 switch : ON - FUEL PUMP 2 caution message out, check pressure.
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Page 139 UNMAINTAINED COPY RFM A109E NOTE It is recommended the normal engine starts be made using the auto mode. For starting procedure in manual mode refer to Section 3. Collective control : Flat pitch, check. Rotor brake (if installed) : Disengaged (lever full forward).
Page 140 UNMAINTAINED COPY RFM A109E CAUTION Following aborted start shutdown perform the following proce- dure before restarting: - Allow 30 seconds fuel drain period - Perform a 30 seconds DRY MOTORING RUN. Refer to Section 1 for engine starter limitations and to DRY MOTORING RUN procedure in this Section.
Page 141 UNMAINTAINED COPY RFM A109E Hydraulic utility system (normal and emergency) : When accumulators are dis- charged, as main rotor begins to rotate, check pressure rise in both systems and note the acti- vation of MAIN UTIL CHRG and EMER UTIL CHRG cau- tion messages.
Page 142 UNMAINTAINED COPY RFM A109E NOTE In the starting phase it is suggested to select FLIGHT mode as soon as possible in order to speed up the engine oil heating. ENGINE 2 START Repeat above procedure to start engine N°2. CAUTION Ensure that the second engine engages as the N2 reaches FLIGHT condition.
Page 143 UNMAINTAINED COPY RFM A109E Engine parameters : Check within limits. External power : Disconnect (if used). Check BATT OFF caution message (only helicopters equipped with emergency bus). INV 1 and 2 switches : ON. RAD- MSTR switch : ON. Clock : Set.
Page 144 UNMAINTAINED COPY RFM A109E CAUTION Avoid to operate the ENG MODE switches simultaneously. Gas producer (N1) : Note increasing and START legend vertically displayed. Engine Temperature (TOT) : Note increasing and IGN leg- end vertically displayed. CAUTION Monitor engine start and if any of the following occurs:...
Page 145 UNMAINTAINED COPY RFM A109E NOTE During cold starting conditions the engine oil pressure can rise up to a transient of 200 PSI. The pressure decreases as oil tempera- ture rises. The oil pressure limits in Section 1, Fig. 1-5 must be respected when main oil temperature is 71°C - 120°C.
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Page 147 UNMAINTAINED COPY RFM A109E CAUTION Do not apply power until engine oil temperature reaches 10°C. WARNING If the main rotor has not begun to rotate when gas producer (N1) reaches 40%, abort the start by setting the ENG MODE switch to OFF.
Page 148 UNMAINTAINED COPY RFM A109E Engine power turbine speed (N2) : Check both stabilized to Flight speed, 100%. NOTE Avoid any cyclic movement except to prevent hitting blade stops below 85% rotor RPM. Engine and transmission parameters : Check within limits.
Page 149 UNMAINTAINED COPY RFM A109E NOTE When STARTER GEN IGN circuit breaker is out, the pertinent ignition system is deactivated even though the Engine Control Unit will provide the IGN message to the EDU. Starter pushbutton (on engine power lever) : Push and hold as necessary.
Page 150 UNMAINTAINED COPY RFM A109E Set 2 OFF. SERVO 2 caution message displayed on EDU 1. Check operation of system N°1 with same cyclic, collective and pedal movements. Pressure drop should not ex- ceed 70 psi and there should be no force increase, discontinuity or cyclic/collective coupling.
Page 151 UNMAINTAINED COPY RFM A109E FUEL PUMP 1 : ON. FUEL PUMP 1 caution message out and crossfeed valve automatically closed (bar vertical) and XFEED advisory message suppressed. FUEL PUMP 2 : OFF. Note fall in fuel pressure, activation of FUEL PUMP 2...
Page 152 UNMAINTAINED COPY RFM A109E INVerter 1 : ON. Check INV 1 caution goes out. INVerter 2 : OFF. Check INV 2 caution message displayed. Check for proper reading (115 V) on both AC systems on EDU 2 AUX display. INVerter 2 : ON.
Page 153 UNMAINTAINED COPY RFM A109E Flight director (if installed): SBY button : Press and check - SBY pushbutton: illuminated - ALL mode controller lights: on - GA and DH lights on ADI: on. - FD flag on ADI: in view. GA button : Press and check - Pushbutton (ON): illuminated.
Page 154 UNMAINTAINED COPY RFM A109E HELIPILOT system: SAS 2 switch : SAS 2: - SAS 2 OFF caution message out. - ATTD OFF caution message out. Cyclic stick motion must not cause HELIPILOT indicator motion. SAS 2 switch : OFF: - SAS 2 OFF caution message displayed.
Page 155 UNMAINTAINED COPY RFM A109E COUPLED/DECOUPLED switch (if installed) : As desired. Autotrim (if installed): AUTOTRIM switch : AUTOTRIM. HELIPILOT indicators : Check centered. Ammeters : Within limits and sharing load. Voltmeters : Within limits. Cockpit lights : As required. External lights : Check and leave as required.
Page 156 UNMAINTAINED COPY RFM A109E TAXIING Nose wheel lock : OFF. Collective and cyclic : Increase slowly the collective then move the cyclic stick forward moderately to start movement. Pedal brakes : Check operation. Pedal control : As required to select the direc- tion.
Page 157 UNMAINTAINED COPY RFM A109E Tail rotor pitch : Apply as necessary to maintain direction. Flight instruments : Check. Engine instruments : Within limits. Main hydraulic system instruments : Within limits. Utility hydraulic system instruments : Within limits. NOTE In hover the helicopter has a slight inclination to the left. During lift-off correct as necessary.
Page 158 UNMAINTAINED COPY RFM A109E FTR pushbutton (cyclic) : Trim as desired for attitude ref- erence changes during hover and climb out. RPM switch : Set 100%. NOTE RPM shall be set to 102% during take-off and landing in the airspeed range from 0 knot to 60 knots and in hovering conditions.
Page 159 UNMAINTAINED COPY RFM A109E CAUTION Do not operate landing gear at speeds above 120 knots. Do not fly with landing gear extended at speeds above 120 knots. MAIN UTIL CHRG caution message : Displayed during landing gear operation. Out after the landing gear is locked.
Page 160 UNMAINTAINED COPY RFM A109E Pitot heat : As required. CAUTION Turn Pitot heat on for flight in visible moisture and in rain regardless of ambient temperature. Altitude : As desired. NOTE Refer to applicable operating rules for high altitude oxygen requirements.
Page 161 UNMAINTAINED COPY RFM A109E When flying decoupled, the pilot flies the helicopter to satisfy Flight Director Commands as programmed on the Flight Director Control Panel. When in this mode, the pilot should either center the commands or go to standby on his mode controller.
Page 162 UNMAINTAINED COPY RFM A109E GO-AROUND MODE CAUTION When operating in GO-AROUND mode, use caution to avoid exceeding engine power limits when satisfying the collective command bar. Missed approach - attitude hold mode Apply power to approximately maximum continuous power. For approach speeds below 80 KIAS no initial pitch-up attitude adjustment is required.
Page 163 UNMAINTAINED COPY RFM A109E NR/N2 speed : 102% stabilized, check. Landing gear lever : DOWN. Check light sequence: - Red light on (extension) - Red light off - Green lights on (extended and locked). LANDING GEAR caution message suppressed, if previ- ously activated.
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Page 165 UNMAINTAINED COPY RFM A109E NOTE When descending below 150 feet AGL vocal message ″ONE FIFTY FEET″ is active regardless landing gear status. This message is suppressed if AWG switch is set to REGRADE. CAUTION Check the lever to be correctly engaged in the DOWN position to avoid inadvertent retraction of the landing gear.
Page 166 UNMAINTAINED COPY RFM A109E After reaching a hover, descend slowly to the surface. After ground contact lower the collective lever to the bottom stop, unless taxiing is desired, in which case maintain to con- trol the helicopter. CAUTION The helicopter is free of ground resonance.
Page 167 UNMAINTAINED COPY RFM A109E NOTE Do not apply collective in this phase and during subsequent rotor deceleration, particularly in windy conditions. Avoid any cyclic movement except to prevent hitting blade stops below 85% rotor RPM. ENG 1 and 2 MODE switches : Set to IDLE then to OFF.
Page 168 UNMAINTAINED COPY RFM A109E Cockpit lights : OFF. External lights : OFF. Landing light : OFF, if used. Miscellaneous switches : OFF. RAD-MSTR (Radio Master) switch : OFF. Power levers : OFF (full aft). NOTE Move both engine power levers to OFF before turning off the electrical power in order to avoid fuel spillage on the ground.
Page 169 UNMAINTAINED COPY RFM A109E FLIGHT HANDLING CHARACTERISTICS STEEP APPROACHES AND VERTICAL DESCENT MANOEUVRES Low speed steep approaches (up to 20 kts) and vertical descent manoeuvres should be performed with a rate of descent not exceeding 900 ft/min. E.A.S.A. Approved 2-47/(2-48 blank)
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Page 171: Emergency And Malfunction Procedures
UNMAINTAINED COPY RFM A109E SECTION 3 EMERGENCY AND MALFUNCTION PROCEDURES TABLE OF CONTENTS Page INTRODUCTION 3–1 DEFINITIONS 3–1 WARNING SYSTEM 3–2 MASTER CAUTION AND MASTER WARNING LIGHTS 3–5 WARNING CAUTION AND AURAL MESSAGES 3–6 WARNING MESSAGES (RED) 3–7 CAUTION MESSAGES (YELLOW) 3–9...
Page 172 UNMAINTAINED COPY RFM A109E Table of Contents (Cont.) ELECTRICAL POWER FAILURE (HELICOPTERS EQUIPPED WITH EMERGENCY BUS) 3–45 RAD-MSTR (RADIO MASTER) SWITCH FAILURE 3–48V HELIPILOT MALFUNCTION 3–48V AUTOTRIM MALFUNCTION 3–50 INTERCOMMUNICATION SYSTEM FAILURE 3–50 INTEGRATED DISPLAY SYSTEM FAILURE 3–51 FIRE 3–56 ENGINE FIRE 3–56...
Page 173 UNMAINTAINED COPY RFM A109E SECTION 3 EMERGENCY AND MALFUNCTION PROCEDURES INTRODUCTION The following procedures contain the indications of equipment or system failure or malfunction, the use of emergency features of primary and backup systems, and appropriate warnings and explanatory notes.
Page 174 UNMAINTAINED COPY RFM A109E LAND AS SOON AS PRACTICAL : The duration of the flight and landing site are at the discretion of the pilot. Extended flight beyond the nearest approved landing area is not recommended. WARNING SYSTEM Many of the malfunctions described in this Section are indicated through the display of red warning messages or yellow caution messages on the EDU 1.
Page 175 UNMAINTAINED COPY RFM A109E Warning and Caution messages remain presented until the causative condition has been corrected. Advisory messages have precedence over status annunciations and remain presented until the causative condition no longer exists. The exceedances requiring the pilot’s attention (i.e. Transmission overtorque, Engine overspeed) are displayed as cautions on EDU 1.
Page 176 UNMAINTAINED COPY RFM A109E Figure 3-1 - Cockpit Layout of the Warning and Caution System. R.A.I. Approved...
Page 177 UNMAINTAINED COPY RFM A109E MASTER CAUTION AND MASTER WARNING LIGHTS Panel wording Fault condition Corrective action MASTER CAUTION See caution message Reset after malfunc- on EDU 1. tion acknowledgment and relative action. MASTER WARNING See warning message Reset after malfunc- on EDU 1.
Page 178 UNMAINTAINED COPY RFM A109E WARNING CAUTION AND AURAL MESSAGES NOTE Warning, caution and aural messages are generally accompanied by specific written messages on EDU 1. Refer to warning and caution message list for fault description and corrective action. Vocal alarm...
Page 179 UNMAINTAINED COPY RFM A109E WARNING MESSAGES (RED) EDU message Fault condition Corrective action ROTOR LOW Rotor RPM low. Use collective to adjust Rotor between RPM. 80% and 95.5% (power on) or 80% and 89.5% (power off). ROTOR HIGH Rotor RPM high.
Page 180 UNMAINTAINED COPY RFM A109E EDU message Fault condition Corrective action ENG 1 (2) FIRE Fire in engine compart- Shutdown affected en- ment. gine. Land as soon as possible. (See the perti- nent paragraphs of this Section). XMSN OIL PRES Transmission oil pres- Reduce power.
Page 181 UNMAINTAINED COPY RFM A109E EDU message Fault condition Corrective action BATT HOT Battery temperature Switch battery off. Land exceeding limits. as soon as possible. # 1 (# 2) ECU FAIL Critical hardware failure Automatic reversion to of the engine control manual mode of the unit.
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Page 183 UNMAINTAINED COPY RFM A109E CAUTION MESSAGES (YELLOW) EDU message Fault condition Corrective action # 1 (# 2) OIL HOT Engine oil tempera- Check the oil tempera- ture above maxi- ture indication, if above mum. the maximum shut down the engine and proceed as per paragraph ″FAIL-...
Page 184 UNMAINTAINED COPY RFM A109E EDU message Fault condition Corrective action TGB OIL CHIP Metal particles in the Reduce power. Land as tail rotor gearbox oil. soon as possible. FUEL PUMP 1 (2) Fuel pumps 1 (2) Affected fuel pump OFF.
Page 185 UNMAINTAINED COPY RFM A109E EDU message Fault condition Corrective action # 1 (# 2) FUEL FLTR Engine fuel filter Proceed with flight. Cor- partially clogged. rect trouble before next flight. FUEL DRAIN 1 (2) Fuel drain valve 1 Close the valve before re- (2) open.
Page 186 UNMAINTAINED COPY RFM A109E EDU message Fault condition Corrective action # 1 (# 2) OVSPD N2 overspeed con- Check the engine instru- trol system in opera- ments and warning de- tion. vices. If RPM drops, shut down the affected engine and proceed as per paragraph ″FAILURE OF ONE EN-...
Page 187 UNMAINTAINED COPY RFM A109E EDU message Fault condition Corrective action # 1 (# 2) OVSP DET Failure of the over- Proceed with flight. speed protection Make corrective action system in the ECU. before next flight. MAIN UTIL PRES Failure of the main...
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Page 189 UNMAINTAINED COPY RFM A109E EDU message Fault condition Corrective action EMER UTIL CHRG Solenoid valve Proceed with flight. locked open. The Correct trouble before emergency utility next flight. system is operative. NOTE MAIN UTIL CHRG and EMER UTIL CHRG do not activate the Master Caution Light.
Page 190 UNMAINTAINED COPY RFM A109E EDU message Fault condition Corrective action SAS 2 OFF No power to the Check SAS 2 engage system. switch, breakers and VG 2 caution message. VG 1 Gyro not erected, Check breaker, refer to loss of power to stand-by attitude indica- gyro.
Page 191 UNMAINTAINED COPY RFM A109E EDU message Fault condition Corrective action # 1 (# 2) DCU Data Collection Unit Correct trouble before failure: TOT and flight. torque trim values for engine calibra- tion not available. Fault message active only on ground be- fore engine starting.
Page 192 UNMAINTAINED COPY RFM A109E EDU message Fault condition Corrective action #1 (#2) PLA MOTOR Engine power lever Proceed with flight. If remote control inop- manual mode operation erative. is required, move engine power lever manually, paying attention to en- gine response.
Page 193 UNMAINTAINED COPY RFM A109E EDU message Fault condition Corrective action # 1 (# 2) TOT TOT limiter function Verify that LD-SH switch LIMITER of Engine Control is set to TORQUE. Unit not operative If TOT reading is still and failure in thermo-...
Page 194 UNMAINTAINED COPY RFM A109E EDU message Fault condition Corrective action Failure of the Inte- Try to identify the faulty grated Display System. information and take the Possible degradation pertinent corrective ac- in system function. tion. Refer to paragraph ″IN- TEGRATED DISPLAY SYSTEM FAILURE″...
Page 195 UNMAINTAINED COPY RFM A109E ENGINE FAILURES FAILURE OF ONE ENGINE INDICATIONS: EDU1 : ENG OUT warning message displayed and vocal alarm «ENGINE OUT» activated when N1 below 35% and/or N1 decreasing more than 20% per second. Engine power turbine speed (N2) : Rapidly decreasing.
Page 196 UNMAINTAINED COPY RFM A109E ENG FUEL switch (affected engine) : OFF. Fuel valve indicator hori- zontal. Fuel pump (affected engine) : OFF. FUEL PUMP caution message displayed. CROSS FEED switch : CLOSED: Crossfeed indicator vertical. GEN switch (affected engine) : OFF. Check load on operating generator (See AUXILIARY page on EDU 2).
Page 197 UNMAINTAINED COPY RFM A109E Engine power turbine speed (N2) : Rapidly decreasing (both en- gines). Torque : Rapidly decreasing (both en- gines) Engine temperature (TOT) : Rapidly decreasing (both en- gines). PROCEDURE Collective : Reduce as required. Establish autorotation at 70 to 75 Kts speed.
Page 198 UNMAINTAINED COPY RFM A109E – CROSS FEED switch : CLOSED. Crossfeed indicator vertical. – GEN 1 and GEN 2 switches : OFF. Perform an autorotative landing. NOTE At approximately 100 ft to 70 ft above the ground depending on weight, initiate a flare to reduce the rate of descent and the forward speed;...
Page 199 UNMAINTAINED COPY RFM A109E ENG FUEL switch : OFF. CROSS FEED switch : CLOSED. Perform a DRY MOTORING RUN as described in Section 2. ENGINE RESTART IN FLIGHT Each engine may be started using either the auto or manual mode. It is recommended that normal engine starts be made using the auto mode.
Page 200 UNMAINTAINED COPY RFM A109E GEN switches : Both ON. CAUTION The pilot shall engage the starter and the ignition only when N1 is below 20%. ENG MODE switch (inoperative en- gine) : IDLE. NOTE It is recommended to start the engine to IDLE, neverthless, if necessary, it is possible to start to FLIGHT by setting the ENG MODE switch directly to FLT.
Page 201 UNMAINTAINED COPY RFM A109E CAUTION Monitor engine start and if any of the following occurs: - lightup is not obtained within 10 seconds of fuel on - abnormal noises are heard - TOT increases beyond start limit - N1 or N2 increases beyond engine limits...
Page 202 UNMAINTAINED COPY RFM A109E Engine power lever (inoperative en- gine) : OFF, check. ENG GOV switch : MANUAL. NOTE In presence of an ECU failure the engine control system reverts and operates in manual mode independently from the ENG GOV switch position.
Page 203 UNMAINTAINED COPY RFM A109E Engine power lever (inoperative en- gine) : Move to FLIGHT. Starting button : Push and hold. START and IGN legends verti- cally displayed beside N1 and TOT scales on the EDU panel. Gas producer (N1) : Note increasing.
Page 204 UNMAINTAINED COPY RFM A109E Engine power control : Set the power as required by using either the engine power lever or the ENG TRIM toggle switch on the collective control. Engine oil pressure : Check. CROSS FEED switch : NORM (bar vertical) ENGINE CONTROL UNIT MALFUNCTIONS There are two levels of control system malfunctions: ″non-critical″...
Page 205 UNMAINTAINED COPY RFM A109E NOTE On ground it may be necessary to cycle the ENG GOV switch twice to clear the ECU malfunctions. If the failure message (i.e. #1 PMS, #1 ECU MAINT, etc. caution messages, or #1 ECU FAIL warning message) is still present proceed as follows: Non critical malfunction.
Page 206 UNMAINTAINED COPY RFM A109E CAUTION Be sure that PLA caution message is not displayed before selecting MANUAL mode. NOTE PLA caution message is active only when operating in AUTO mode. The MANUAL mode condition is indicated to the pilot by the activation of MAN legend on EDU 1.
Page 207 UNMAINTAINED COPY RFM A109E Both engines in MANUAL mode WARNING Training with both engines in MANUAL mode should be avoided. In case of critical malfunction of both ECUs (double failure), the pilot shall control both engines in MANUAL mode. Each FMM tracking system will fix the N1 speed at the last commanded value.
Page 208 UNMAINTAINED COPY RFM A109E CAUTION Take care of N2 response when lowering the collective in order to avoid engine overspeed. APPROACH AND LANDING Landing gear lever : DOWN. Utility hydraulic system : Pressure within limits, check. Nose wheel lock : ON (lever up).
Page 209 UNMAINTAINED COPY RFM A109E After the touchdown simulta- neously lower the collective and reduce both engines to IDLE. CAUTION Take care of N2 response when lowering the collective in order to avoid engine overspeed. Apply toe brakes. : Refer to paragraph ″ENGINE...
Page 210 UNMAINTAINED COPY RFM A109E Engine power lever : FLIGHT, check. PLA caution message not dis- played. NOTE If AUTO mode was selected when engine power lever was not in FLIGHT position, set the power lever correctly as soon as possible.
Page 211 UNMAINTAINED COPY RFM A109E EDU 1 : Select START page. ENG MODE switch (inoperative en- gine) : IDLE. Engine power lever (inoperative en- gine) : FLIGHT, check. Starting button : Push and hold. START and IGN legends verti- cally displayed beside N1 and TOT scales on the EDU.
Page 212 UNMAINTAINED COPY RFM A109E Starting button : Release when gas producer (N1) reaches 50%. START and IGN legends sup- pressed. Engine power control : Set the power as required by using either the engine power lever or the ENG TRIM toggle switch on the collective control.
Page 213 UNMAINTAINED COPY RFM A109E Engine power lever : Set to OFF. NOTE If necessary the engine may be shutdown directly from FLT. ENG MODE switch : OFF (full counterclockwise) Fuel pump : OFF. FUEL PUMP caution message displayed. CAUTION During shutdown check that the N1 speed decelerates freely. Note any abnormal noise or rapid rundown and take corrective action as required per Maintenance Manual.
Page 214 UNMAINTAINED COPY RFM A109E NOTE In case of NR/N2 switch locked at 102% the pilot can complete the flight provided that the airspeed is limited to 130 KIAS. Correct trouble before next flight. DRIVE SYSTEM FAILURES TAIL ROTOR FAILURE A tail rotor drive failure results in a loss of yaw control with a consequent yaw to the right, which is the more rapid, the less the forward speed is and the more the torque level is.
Page 215 UNMAINTAINED COPY RFM A109E If the check confirms the tail rotor failure, proceed as per the paragraph ″COMPLETE LOSS OF TAIL ROTOR IN CRUISE″, otherwise carry out the following further check: Airspeed : Maintain 60 KIAS. Collective : Slowly raise, to increase the...
Page 216 UNMAINTAINED COPY RFM A109E Collective : As necessary to cushion the touchdown. NOTE A slight rotation can be expected on touchdown. COMPLETE LOSS OF TAIL ROTOR IN CRUISE PROCEDURE Collective : Lower as necessary to eliminate yaw to the right.
Page 217 UNMAINTAINED COPY RFM A109E Engine power levers : OFF. Fuel pumps : OFF. ENG FUEL switches : OFF. CROSS FEED switch : CLOSED. GENerators 1 and 2 : OFF. BATTery : OFF (except as needed in night flight). Perform an autorotative landing, into wind, maintaining forward speed if terrain permits.
Page 218 UNMAINTAINED COPY RFM A109E Pedals : They tend to move to tail rotor traction zero position (right pedal about three centimeters more forward than left pedal). NOTE The pedal movement is plus or minus evident depending from flight condition. It increases the quicker the pressure drops and more left pedal movement is required.
Page 219 UNMAINTAINED COPY RFM A109E WARNING Following the pressure loss in N.1 main hydraulic system avoid landing and/or operating in conditions which require a high degree or maneuverability (i.e. avoid operating in enclosed areas, helicopter heading not windward, in particular with wind from the right).
Page 220 UNMAINTAINED COPY RFM A109E The jamming of a servo valve of main rotor servo actuators cannot be detected when both main hydraulic systems are functioning as the second hydraulic system will guarantee the full efficiency of the actuators. Such kind of failure can be noticed only during the system check on ground before takeoff (refer to Section 2).
Page 221 UNMAINTAINED COPY RFM A109E Landing gear lever : DOWN EMERG (full down) Check light sequence: - Red light on (extension) - Red light off - Green light on (extended and locked) LANDING GEAR caution message suppressed, if previ- ously activated.
Page 222 UNMAINTAINED COPY RFM A109E EDU message Fault condition Refer to para. GEN BUS # 1 switch FAILURE OF # GEN- ERATOR 2 AND GEN- ERATOR BUS # 1 d.c. gen and bus tie # 1 # 2 DC GEN, BUS TIE, INV1 (2), SAS1 malfunction.
Page 223 UNMAINTAINED COPY RFM A109E PROCEDURE GEN 1 (2) : Reset, then ON. If generator does not remain ON, set switch to OFF. Power is supplied to all loads by the remaining genera- tor. GEN BUS 1 (2) : ON, check.
Page 224 UNMAINTAINED COPY RFM A109E GEN BUS 1 and 2 : ON, check. If failure confirmed, no loads are lost. NOTE Following a failure of both Generator Busses the battery will continue to supply the following loads: DAU ch A, EDU Primary, ICS PLT.
Page 225 UNMAINTAINED COPY RFM A109E After switching off the GEN BUS 1 the following message will be indicated: INV 1, SAS 1 OFF. NOTE Following a failure of both Generator Busses the battery will comntinue to supply the following loads: DAU ch A, EDU Primary, ICS PLT.
Page 226 UNMAINTAINED COPY RFM A109E After switching off the GEN BUS 2 the following message will be indicated: INV 2, SAS 2 OFF. NOTE Following a failure of both Generator Busses the battery will continue to supply the following loads: DAU ch A, EDU Primary, ICS PLT and VHF1 (if radio master switch incorporates the ground position GND).
Page 227 UNMAINTAINED COPY RFM A109E PROCEDURE GEN 1 (2) : Reset, then ON. - If #1 (#2) DC GEN caution light remain ON, select switch to OFF (loss of generator). GEN BUS (1 and/or 2) : ON. If engagement of one...
Page 228 UNMAINTAINED COPY RFM A109E WARNING After both generators failure the battery will carry the electrical loads, for the basic configuration, for approximately 10 minutes. The battery operating time can be extended by selectively reducing system load. Flight duration can be extended to 30 minutes provided that only...
Page 229 UNMAINTAINED COPY RFM A109E PROCEDURE GEN 1 and 2 : Reset, then ON. GEN BUS 1 and 2 : ON, check generators still op- erative. If both generators and generator busses are inoperative, continue flight on battery. Land as soon as possible.
Page 230 UNMAINTAINED COPY RFM A109E Failed inverter : OFF. SAS (1 or 2) switch : ON. Failure of an a.c. bus system - 115V and 26V (Helicopter not equipped with emergency bus) The failure of an a.c. bus system (115V and 26V) is indicated by the simultaneous activation of: SAS 1 OFF - VG 1 message: for a.c.
Page 231 UNMAINTAINED COPY RFM A109E ELECTRICAL POWER FAILURE (Helicopters equipped with emergency bus) EDU message Fault condition Refer to para. #1 (#2) DC GEN cau- d.c. generator failure FAILURE OF A GEN- tion ERATOR BUS TIE caution Bus tie malfunction. Check:...
Page 232 UNMAINTAINED COPY RFM A109E EDU message Fault condition Refer to para. BUS TIE, INV 2, SAS1 Failure of both gen- FAILURE BOTH OFF, SAS 2 OFF cau- erators and both gen- GENERATORS tion messages erators busses. BOTH GENERATORS ELECTRICAL BUSSES...
Page 233 UNMAINTAINED COPY RFM A109E CAUTION Check ammeter does not exceed limit. Failure of generator bus #1 or #2 (Helicopter equipped with emergency bus) This failure is indicated by the BUS TIE caution message and after few seconds, if the battery discharge control box is installed, by BATT DISCH warning message on EDU 1.
Page 234 UNMAINTAINED COPY RFM A109E Failure of both generator busses (Helicopter equipped with emergency bus) This failure is indicated by the BUS TIE caution message and after few seconds, if the battery discharge control box is installed, by BATT DISCH warning message on EDU 1.
Page 235 UNMAINTAINED COPY RFM A109E PROCEDURE GEN 1 : Reset, then ON. GEN BUS 2 : ON, check. If failure is confirmed, proceed as follows: Pilot ICS panel switch : Select FAIL position BATTery switch : OFF. All loads of Generator Bus #1 and Emergency Bus #1 are lost.
Page 236 UNMAINTAINED COPY RFM A109E GEN BUS 1 : ON, check. If failure is confirmed, proceed as follows: Pilot ICS panel switch : Select FAIL position BATTery switch : OFF. All loads of Generator Bus #2 and Emergency Bus #2 are lost. All loads of Essential Bus #2 are retained.
Page 237 UNMAINTAINED COPY RFM A109E The failure of Generator 2 and # 2 DC BUS is indicated by #2 DC GEN, BUS TIE, INV2, SAS2 OFF caution messages on EDU 1. All loads of Generator Bus #2 and pilot EHSI (if installed) are lost. All loads of Essential Bus #2 and Emergency Bus #2 are retained.
Page 238 UNMAINTAINED COPY RFM A109E Failure of both generators (Helicopter equipped with emergency bus) This failure is indicated by ELECTRICAL warning message and, if the helicopter is equipped with battery discharge control box, by BATT DISCH warning message on EDU 1.
Page 239 UNMAINTAINED COPY RFM A109E EMERGENCY BUS N°1 - Fuel quantity N° 1 - Fuel pump N° 1 - Fuel shut-off valve N° 1 - Fuel crossfeed - Engine 1 fire detector system - N° 1 engine compartment fire extinguisher system...
Page 240 UNMAINTAINED COPY RFM A109E NOTE The pilot is allowed to operate the VHF N° 2 system for a period of 15 minutes reception and 3 minutes transmission during the next 25 minutes, commencing from the expiration of the first 5 minutes.
Page 241 UNMAINTAINED COPY RFM A109E NOTE During the load shedding procedure all SAS will be lost until SAS 1 is reselected ON. It is recommended that prior to load shedding, speed is reduced to between 100 and 120 Kts in order to reduce pilot work load.
Page 242 UNMAINTAINED COPY RFM A109E - SAS 1 system - ADI pilot (EHSI-74 version) - HSI standby (EHSI-74 version) - Landing gear position indicator - Landing light(s) - Emergency floats - Inverter #1 EMERGENCY BUS N° 2 - Fuel quantity N° 2 - Fuel pump N°...
Page 243 UNMAINTAINED COPY RFM A109E If conditions require and the Generator Busses have been intentionally disconnected, other system such as windshield wipers can be energized by switching related Generator Bus to ON. In this event, the battery operating time will be reduced due to the greater loads imposed.
Page 244 UNMAINTAINED COPY RFM A109E WARNING In the event of N° 1 a.c. bus system failure the following instruments and equipment will continue to operate: - VOR/ILS N°2 - ADF - VG 2 - SAS 2 WARNING In the event of N°2 a.c. bus system failure the following instruments and equipment will continue to operate: - VOR/ILS N°1...
Page 245 UNMAINTAINED COPY RFM A109E NOTE HELIPILOT indicators normally refer to SAS 1. Turning SAS 1 off. HELIPILOT indicators will automatically switch to SAS 2. NOTE The attitude beep-trim on the cyclic is inoperative when flying coupled in the relative axis or when one of the two SAS is inoperative.
Page 246 UNMAINTAINED COPY RFM A109E Identify the affected axis and helipilot by observing HELIPILOT indicators (API), helicopter attitudes/rates and ADIs (normal and STBY). Switch off the affected SAS. If SAS disengagement eliminates the oscillation, leave it off. If oscillation persists, re-engage both SAS and switch off the other SAS.
Page 247 UNMAINTAINED COPY RFM A109E INTEGRATED DISPLAY SYSTEM FAILURE The internal IDS failures may differ according to the following cases: EDU failure INDICATIONS: Affected EDU : Blank or unusable Healthy EDU : Automatically set to REVER- SIONARY mode. IDS caution message displayed.
Page 248 UNMAINTAINED COPY RFM A109E Failure of both EDUs INDICATIONS: EDU 1 and 2 : Blank or unusable. PROCEDURE EDU 1 and 2 : OFF. CAUTION Primary and secondary parameters, caution and warning mes- sages no more available except: - MASTER CAUTION and MASTER WARNING lights.
Page 249 UNMAINTAINED COPY RFM A109E In case of loss of TOT: EDU 1 : #1 (#2) TOT LIMITER caution message displayed. PROCEDURE EDU 1 : Check correctness backup indication. If the affected ECU has reverted to manual mode, proceed as per paragraph ENGINE OPERATION in MANUAL MODE.
Page 250 UNMAINTAINED COPY RFM A109E PROCEDURE EDU 1 : Access MENU 2/3 page to verify DAU channels status. Select the DAU channel indi- cated by yellow legend and check for data discrepancy. Deselect the channel to return to normal mode operation.
Page 251 UNMAINTAINED COPY RFM A109E PROCEDURE EDU 2 : Access MENU 2/3 page to verify DAU channels status. The failed DAU channel is in- dicated by yellow legend. Check for correctness of sec- ondary parameters. Proceed with flight ignoring the failed DAU channel.
Page 252 UNMAINTAINED COPY RFM A109E FIRE ENGINE FIRE INDICATIONS: EDU 1 : ENG 1 (2) FIRE warning mes- sage displayed and ENGINE ONE (TWO) FIRE aural mes- sage activated. Engine power grip (affected engine) : Illuminated. MASTER WARNING light : Illuminated.
Page 253 UNMAINTAINED COPY RFM A109E ENGINE FIRE IN FLIGHT PROCEDURE Initiate immediately an emergency descent . Collective : Decrease until torque is less than 50%. Shutdown the affected engine as follows: ENG MODE switch : OFF (full counterclockwise). Power lever : OFF.
Page 254 UNMAINTAINED COPY RFM A109E CAUTION Do not attempt to restart the engine. SMOKE IN CABIN, TOXIC FUMES, ETC. In case of smoke, toxic fumes, etc., proceed as follows: VENT CKPT switch : HIGH. VENT CAB switch (if installed) : HIGH.
Page 255 UNMAINTAINED COPY RFM A109E STATIC PORT OBSTRUCTION When operating in adverse weather conditions (rain, snow, etc.), if erratic readings from the airspeed indicator and altimeter occur, with the STATIC source switch in NORMAL position, proceed as follows: Sliding window (if installed) and vents : Closed.
Page 256 UNMAINTAINED COPY RFM A109E CAUTION Avoid to perform extreme manoeuvers. Land as soon as practical. EMERGENCY PROCEDURE FOR LIMIT OVERRIDE PUSHBUTTON OPERATION The engine is protected from limits exceeding through the engine limit governing. The engine limit governing is responsible for limiting measured engine parameters.
Page 257 UNMAINTAINED COPY RFM A109E EDU 1 : OEI transient torque marking (red triangle) displayed, if in OEI mode. Collective : Apply as necessary respecting following transients: Torque OEI 180% Torque AEO 166% 980C° 103.4% paying attention return within the operating limits in no...
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Page 259 UNMAINTAINED COPY RFM A109E SECTION 4 PERFORMANCE DATA TABLE OF CONTENTS Page INTRODUCTION 4–1 POWER ASSURANCE CHECKS 4–1 DENSITY ALTITUDE 4–5 CONVERSION CHART 4–7 OPERATION VS ALLOWABLE WIND 4–8 HOVERING CEILING IGE 4–10 HOVERING CEILING OGE 4–13 HEIGHT - VELOCITY DIAGRAM 4–16...
Page 260 UNMAINTAINED COPY RFM A109E List of illustrations (Contd.) Page Figure 4-13. Rate of climb - all engines - take-off power - 2850 kg. 4–22 Figure 4-14. Rate of climb - all engines - maximum continuous power - 2050 kg. 4–23 Figure 4-15.
Page 261 UNMAINTAINED COPY RFM A109E SECTION 4 PERFORMANCE DATA INTRODUCTION The performance data presented herein is derived from the engine manufac- turer’s specification power for the engine less installation losses. This data is applicable to the basic helicopter without any optional equipment which would appreciably affect lift, drag, or power available.
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Page 263 UNMAINTAINED COPY RFM A109E POWER ASSURANCE CHECK HOVER * HEATER / E.C.S. OFF. * TEST ENGINE MODE SWITCH - FLIGHT. * GENERATOR LOAD TO MINIMUM (< 28 A). * OTHER ENGINE MODE SWITCH - IDLE. * SET NR TO 102%.
Page 264 UNMAINTAINED COPY RFM A109E POWER ASSURANCE CHECK IN FLIGHT * HEATER / E.C.S. OFF. * ESTABILISH LEVEL FLIGHT ABOVE 1000 ft. AGL. * TEST ENGINE - SET ENG. GOV. SWITCH TO MANUAL * GENERATOR LOAD TO MINIMUM (< 28 A).
Page 265 UNMAINTAINED COPY RFM A109E DENSITY ALTITUDE A Density Altitude Chart is provided to aid in calculation of performance and limitations. Density altitude (Hd) is an expression of the density of the air on terms of height above sea level; therefore, the less dense the air, the higher the density altitude.
Page 266 UNMAINTAINED COPY RFM A109E DENSITY ALTITUDE CHART OUTSIDE AIR TEMPERATURE - ˚F 26000 1.52 1.50 1.48 24000 1.46 1.44 1.42 22000 1.40 1.38 20000 1.36 1.34 18000 1.32 1.30 16000 1.28 1.26 14000 1.24 1.22 12000 1.20 1.18 10000 1.16 1.14...
Page 267 UNMAINTAINED COPY RFM A109E CONVERSION CHART A Conversion Chart is also provided for altitude, weight, temperature, airspeed, rate of climb and capacity. Figure 4-4. Conversion chart. R.A.I. Approved...
Page 268 UNMAINTAINED COPY RFM A109E OPERATION VS ALLOWABLE WIND Satisfactory stability and control in rearward and sideward flight has been demonstrated, at all loading conditions for hover in ground effect up to takeoff power, from -1000 ft to 8000 ft Hd, in the following wind/ground speed azimuth envelope: Figure 4-5 (Sheet 1 of 2).
Page 269 UNMAINTAINED COPY RFM A109E Figure 4-5 (Sheet 2 of 2). Wind/ground speed azimuth envelope. R.A.I. Approved...
Page 270 UNMAINTAINED COPY RFM A109E HOVERING CEILING IGE The Hovering Ceiling In Ground Effect charts provide the maximum gross weight for hovering IGE (3 ft above ground level) at all pressure altitudes and outside air temperatures, with main rotor speed at 102% and zero wind condition.
Page 271 UNMAINTAINED COPY RFM A109E HOVERING CEILING IN GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % ZERO WIND WHEEL HEIGHT: 3 ft ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 OAT - ˚C...
Page 272 UNMAINTAINED COPY RFM A109E HOVERING CEILING IN GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % WHEEL HEIGHT: 3 ft ZERO WIND ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 OAT - ˚C...
Page 273 UNMAINTAINED COPY RFM A109E HOVERING CEILING OGE The Hovering Ceiling Out of Ground Effect charts provide the maximum gross weight for hovering OGE (60 ft above ground level) at all pressure altitudes and outside air temperatures, with main rotor speed at 102% and zero wind condition.
Page 274 UNMAINTAINED COPY RFM A109E HOVERING CEILING OUT OF GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % ZERO WIND ELECTRICAL LOAD: 150 A TOTAL CAUTION:OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V LIMITATIONS. GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 OAT - ˚C...
Page 275 UNMAINTAINED COPY RFM A109E HOVERING CEILING OUT OF GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % ZERO WIND ELECTRICAL LOAD: 150 A TOTAL CAUTION:OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V LIMITATIONS. GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 OAT - ˚C...
Page 276 UNMAINTAINED COPY RFM A109E HEIGHT - VELOCITY DIAGRAM The Height - Velocity diagram enable to establish if, in the event of a single engine failure during takeoff, landing or other operation near the surface, a combination of airspeed and height above ground exists from which a safe single engine landing on a smooth, level and hard surface cannot be assured (dangerous zone).
Page 277 UNMAINTAINED COPY RFM A109E HEIGHT-VELOCITY DIAGRAM ONE ENGINE INOPERATIVE CHART "A" SHOWS THE WEIGHT VALUES AT/BELOW WHICH THERE IS NO H-V LIMITATION FOR HEAVIER WEIGHTS, REFER TO CHART "B". CHART A GROSS WEIGHT - POUNDS x 100 OAT - ˚C...
Page 278 UNMAINTAINED COPY RFM A109E HEIGHT-VELOCITY DIAGRAM ONE ENGINE INOPERATIVE FOR SMOOTH, LEVEL, HARD SURFACES CHART B AVOID OPERATION IN SHADED AREA INDICATED AIRSPEED - KNOTS TR 109-60-99/II REV C ABHD078E Figure 4-10 (sheet 2 of 2). Height - velocity diagram.
Page 279 UNMAINTAINED COPY RFM A109E RATE OF CLIMB The Rate of Climb charts are provided with all engines operative and with one engine inoperative. The rate of climb AEO charts are presented for takeoff power rating and for maximum continuous power rating, both with main rotor speed at 100%, and they refer to the best rate of climb speed of 60 Kts IAS.The...
Page 280 UNMAINTAINED COPY RFM A109E RATE OF CLIMB ALL ENGINES TAKE-OFF POWER ROTOR: 100 % 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2050 kg ( 4519 lb ) OAT - ˚C 8 10 12 14 16 18 20 22 24 26 28 30 32 34...
Page 281 UNMAINTAINED COPY RFM A109E Figure 4-12. Rate of climb - all engines - take-off power - 2450 kg. R.A.I. Approved 4-21 Rev. 23...
Page 282 UNMAINTAINED COPY RFM A109E Figure 4-13. Rate of climb - all engines - take-off power - 2850 kg. 4-22 R.A.I. Approved Rev. 23...
Page 283 UNMAINTAINED COPY RFM A109E RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2050 kg ( 4519 lb ) OAT - ˚C 8 10 12 14 16 18 20 22 24 26 28 30 32 34...
Page 284 UNMAINTAINED COPY RFM A109E RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2450 kg ( 5401 lb ) OAT - ˚C 8 10 12 14 16 18 20 22 24 26 28 30 32...
Page 285 UNMAINTAINED COPY RFM A109E RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2850 kg ( 6283 lb ) OAT - ˚C 8 10 12 14 16 18 20 22 24 26 28 30 32...
Page 286 UNMAINTAINED COPY RFM A109E RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 100 % 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2050 kg ( 4519 lb ) OAT - ˚C...
Page 287 UNMAINTAINED COPY RFM A109E RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 100 % 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2450 kg ( 5401 lb ) OAT - ˚C...
Page 288 UNMAINTAINED COPY RFM A109E RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 100 % 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2850 kg ( 6283 lb ) OAT - ˚C...
Page 289 UNMAINTAINED COPY RFM A109E RATE OF CLIMB ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2050 kg ( 4519 lb ) OAT - ˚C...
Page 290 UNMAINTAINED COPY RFM A109E RATE OF CLIMB ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2450 kg ( 5401 lb ) OAT - ˚C...
Page 291 UNMAINTAINED COPY RFM A109E RATE OF CLIMB ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2850 kg ( 6283 lb ) OAT - ˚C...
Page 292 UNMAINTAINED COPY RFM A109E AIRSPEED CALIBRATION The Airspeed Calibration charts provide calibrated airspeed in forward flight for pilot and copilot airspeed systems. 4-32 R.A.I. Approved Rev. 12...
Page 293 UNMAINTAINED COPY RFM A109E AIRSPEED CALIBRATION CURVE PILOT (FORWARD FLIGHT) 10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 INDICATED AIRSPEED - KTS RPT 109-60-99/II REV A ABHD033A Figure 4-23. Airspeed calibration curve pilot (forward flight).
Page 294 UNMAINTAINED COPY RFM A109E AIRSPEED CALIBRATION CURVE COPILOT (FORWARD FLIGHT) 10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 INDICATED AIRSPEED - KTS RPT 109-60-99/II REV A ABHD034A Figure 4-24. Airspeed calibration curve copilot (forward flight).
Page 295: Optional Equipment
UNMAINTAINED COPY RFM A109E SECTION 5 OPTIONAL EQUIPMENT LIST OF APPENDICES Appendix No. Name of equipment Rotor brake 109-0810-63 Engine compartment fire 109-0811-39 extinguishers Weather radar - RDR 2000 Bendix 109-0811-47 King Pulsed chip detector 109-0811-48 Environmental control system (air con-...
Page 296 UNMAINTAINED COPY RFM A109E List of Appendices (Contd.) Appendix No. Name of equipment Battery 22 Ah 109-0812-04 EFIS (Electronic Flight Instrument 109-0900-57- System) -101/-103/-105 /-107 Global Position System Garmin 165 109-0811-53 Nightsun searchlight SX-16 109-0811-33 109-0813-46 Snow skid 109-0811-99 Global Position System Trimble 2101 109-0811-53 and...
Page 297 UNMAINTAINED COPY RFM A109E List of Appendices (Contd.) Appendix No. Name of equipment E.M.T. (Emergency Medical Trans- 109-0812-64 portation) HF System - Type HF950 109-0812-25 Cargo hook 109-0810-31 Cargo hook 109-0811-75 and V extension up to 140 KIAS — Supplementary fuel tanks...
Page 298 UNMAINTAINED COPY RFM A109E OPTIONAL EQUIPMENT INCOMPATIBILITY The following table shows the incompatibility of one or more optional equipment when installed on board the helicopter. Table 5-1. Optional equipment incompatibility Appendix Name of equipment Incompatibility (Appendix No.) Rotor brake None...
Page 299 UNMAINTAINED COPY RFM A109E Appendix Name of equipment Incompatibility (Appendix No.) Equivalent category ″A″ operations 13 and 45 training procedure External hoist 27 and 38 Skywatch Traffic Advisory System 10 (oxygen system SKY 497 109-0811-76) and 32 Moving Map System Skyforce Ob-...
Page 300 UNMAINTAINED COPY RFM A109E Appendix Name of equipment Incompatibility (Appendix No.) Searchlight HF System type KHF1050 Weather Radar PRIMUS 700 None Satcom Aircell E.A.S.A. Approved Rev. 56...
Page 301 UNMAINTAINED COPY RFM A109E LIST OF SUPPLEMENTS Helicopter Supplement Subject Applicability Electrical Provision 109-0742-74-103 11201 Observation System EOST-51 11201 Reserved — Reserved — Reserved — Reserved — FLIR LEO II A-3 System 11211/11212 Homing DF931-05 11211/11212 Rappelling Installation 11211/11212 Reserved —...
Page 302 UNMAINTAINED COPY RFM A109E Helicopter Supplement Subject Applicability 11647/11649/ 11700/11704 Moving Map 11647/11649 SEA FLIR II 11647/11649 Deleted — TELIT GSM/SAT550 Telephone System 11654/11685 Reserved — Reserved — Reserved — Reserved — Reserved — Reserved — Reserved — Reserved —...
Page 303 UNMAINTAINED COPY RFM A109E APPENDIX 1 R.A.I. Approval Letter 97/3147/MAE dated 30 July 1997 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 304: Placards
UNMAINTAINED COPY RFM A109E APPENDIX 1 TABLE OF CONTENTS Page PART I - R.A.I. APPROVED SECTION 1 - LIMITATIONS CENTER OF GRAVITY LIMITATIONS 3 of 5 PLACARDS 3 of 5 SECTION 2 - NORMAL PROCEDURES PILOT’S DAILY PREFLIGHT CHECK 3 of 5 PILOT’S PREFLIGHT CHECK...
Page 305 UNMAINTAINED COPY RFM A109E APPENDIX 1 SECTION 1 - LIMITATIONS CENTER OF GRAVITY LIMITATIONS After rotor brake installation the new empty weight and C.G. location must be determined. PLACARDS DO NOT APPLY ROTOR BRAKE ABOVE 40% ROTOR RPM In clear view of the pilot SECTION 2 - NORMAL PROCEDURES PILOT’S DAILY PREFLIGHT CHECK...
Page 306 UNMAINTAINED COPY RFM A109E APPENDIX 1 AREA N.7 (Cabin Interior) Rotor brake lever : Freedom of movement. Leave disengaged (full for- ward). PILOT’S PREFLIGHT CHECK (Every flight) Rotor brake lever : Freedom of movement. Leave disengaged (full for- ward). Transmision oil : Check correct oil level.
Page 307 UNMAINTAINED COPY RFM A109E APPENDIX 1 SHUTDOWN CAUTION The rotor brake must be disengaged whenever the engines are running. Rotor brake : Apply below 40% rotor RPM. POST FLIGHT CHECK Rotor brake lever : Disengaged (full forward) SECTION 3 - EMERGENCY AND MALFUNCTION...
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Page 309 UNMAINTAINED COPY RFM A109E APPENDIX 2 R.A.I. Approval Letter 97/3147/MAE dated 30 July 1997 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 310 UNMAINTAINED COPY RFM A109E APPENDIX 2 TABLE OF CONTENTS Page PART I - E.A.S.A. APPROVED SECTION 1 - LIMITATIONS CENTER OF GRAVITY LIMITATIONS 3 of 9 SECTION 2 - NORMAL PROCEDURES PREFLIGHT CHECKS 3 of 9 PILOT’S DAILY PREFLIGHT CHECK 3 of 9 PILOT’S PREFLIGHT CHECK...
Page 311 UNMAINTAINED COPY RFM A109E APPENDIX 2 SECTION 1 - LIMITATIONS CENTER OF GRAVITY LIMITATIONS After engine compartment fire extinguishers installation the new empty weight and C.G. location must be determined. SECTION 2 - NORMAL PROCEDURES PREFLIGHT CHECKS PILOT’S DAILY PREFLIGHT CHECK (First flight of the day) AREA N°2 (Fuselage - RH side)
Page 312 UNMAINTAINED COPY RFM A109E APPENDIX 2 Indicator disc : Red, check. NOTE If the indicator disc is not in position, it means that the relative bottle has already been discharged and it needs to be replaced. Extinguishing system nozzles (inside the engine bay) : Free of obstructions.
Page 313 UNMAINTAINED COPY RFM A109E APPENDIX 2 SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES WARNING SYSTEM Figure 3-1A. Control panel on the overhead console (Applicable up to S/N 11674). Figure 3-1B. Control panel on the overhead console (Applicable from S/N 11675 and subs).
Page 314 UNMAINTAINED COPY RFM A109E APPENDIX 2 WARNING MESSAGES (RED) EDU Message Fault condition Corrective action ENG 1 (2) FIRE Fire in engine compart- Shut down the affected en- ment. gine. Operate the engine fire ex- tinguisher. Land as soon as possible.
Page 315 UNMAINTAINED COPY RFM A109E APPENDIX 2 Power lever : OFF. S/OFF FIRE pushbutton : Raise the guard and press. S/OFF wording illuminated. WARNING Press button once only to close the fuel shut-off valve and arm the fire extinguishers system. A further operation of the pushbutton re-opens the fuel shut-off valve and disables the system.
Page 316 UNMAINTAINED COPY RFM A109E APPENDIX 2 ENGINE FIRE IN FLIGHT PROCEDURE Collective : Decrease until torque is less than 50%. To extinguish fire proceed as follows with the affected engine. ENG MODE switch : OFF (full counterclockwise). Power lever : OFF.
Page 317 UNMAINTAINED COPY RFM A109E APPENDIX 2 If fire warning message does not extinguish: FIRE EXTING selector switch : Set to BTL 2 to cause the dis- charge of bottle n°2 of the ex- tinguishing agent. If the fire is extinguished proceed to a suitable area and land.
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Page 319 UNMAINTAINED COPY RFM A109E APPENDIX 3 R.A.I. Approval Letter 97/3147/MAE dated 30 July 1997 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 320 UNMAINTAINED COPY RFM A109E APPENDIX 3 TABLE OF CONTENTS Page PART I - R.A.I. APPROVED SECTION 1 - LIMITATIONS CENTER OF GRAVITY LIMITATIONS 3 of 4 SECTION 2 - NORMAL PROCEDURES WEATHER RADAR OPERATION 3 of 4 SECTION 3 - EMERGENCY AND MALFUNCTION...
Page 321 UNMAINTAINED COPY RFM A109E APPENDIX 3 SECTION 1 - LIMITATIONS CENTER OF GRAVITY LIMITATIONS After Weather Radar RDR 2000 installation the new empty weight and C.G. location must be determined. SECTION 2 - NORMAL PROCEDURES WARNING The weather radar must not be used for obstacle or terrain avoidance.
Page 322 UNMAINTAINED COPY RFM A109E APPENDIX 3 NOTE When SBY or TEST mode is selected the radar does not radiate. As a precaution it is nevertheless convenient to operate as follows: - Direct nose of helicopter such that antenna scan sector is free of large metallic objects such as hangars or other aircraft for a distance of 30 m (100 ft) and tilt antenna fully upwards.
Page 323 UNMAINTAINED COPY RFM A109E APPENDIX 4 E.N.A.C. Approval Letter 97/3147/MAE dated 30 July 1997 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 324 UNMAINTAINED COPY RFM A109E APPENDIX 4 TABLE OF CONTENTS Page PART I - E.N.A.C. APPROVED SECTION 1 - LIMITATIONS 3 of 5 SECTION 2 - NORMAL PROCEDURES 3 of 5 SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES CAUTION MESSAGES (YELLOW)
Page 325 UNMAINTAINED COPY RFM A109E APPENDIX 4 SECTION 1 - LIMITATIONS No change. SECTION 2 - NORMAL PROCEDURES No change. SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES CAUTION MESSAGES (YELLOW) EDU message Fault condition Corrective action XSMN OIL CHIP Presence of metal particles...
Page 326 UNMAINTAINED COPY RFM A109E APPENDIX 4 EDU message Fault condition Corrective action NOTE Terminated a cycle of 50 hours with not more than two message activations, the new 50 hour cycle begins from the last message activation. Make an appropriate log book entry stating beginning of new 50 hour cycle.
Page 327 UNMAINTAINED COPY RFM A109E APPENDIX 4 EDU message Fault condition Corrective action # 1 (# 2) OIL CHIP Presence of metal particles Activate CHIP BURNER in the engine oil. switch momentarily and re- lease. If the message is not sup-...
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Page 329 UNMAINTAINED COPY RFM A109E APPENDIX 5 R.A.I. Approval Letter 97/3147/MAE dated 30 July 1997 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 330 UNMAINTAINED COPY RFM A109E APPENDIX 5 TABLE OF CONTENTS Page PART I - E.A.S.A. APPROVED SECTION 1 - LIMITATIONS ECS OPERATION 4 of 23 CENTER OF GRAVITY LIMITATIONS 4 of 23 MISCELLANEOUS LIMITATIONS 4 of 23 SECTION 2 - NORMAL PROCEDURES...
Page 331 UNMAINTAINED COPY RFM A109E APPENDIX 5 LIST OF ILLUSTRATIONS Page Figure 4-1. Height-Velocity diagram - basic with ECS ON. 10 of 23 Figure 4-2. Height-Velocity diagram - EAPS OFF with ECS ON. 11 of 23 Figure 4-3. Height-Velocity diagram - EAPS ON with ECS ON.
Page 332 UNMAINTAINED COPY RFM A109E APPENDIX 5 SECTION 1 - LIMITATIONS ECS OPERATION Above 2000 ft pressure altitude (Hp), the ECS shall be OFF during take off and landing and in flight below 200 ft AGL. At any altitude the ECS shall be OFF during single engine operation and in all flight conditions requiring the maximum engine power available.
Page 333 UNMAINTAINED COPY RFM A109E APPENDIX 5 SYSTEMS CHECK ENVIRONMENTAL CONTROL SYSTEM OPERATIONAL CHECK The operational check may be accomplished at this time or at any time that environmental control system is desired. NR/N2 : 100% stabilized, check. ECS switch : ON, observe no air-flow from the outlets.
Page 334 UNMAINTAINED COPY RFM A109E APPENDIX 5 CAUTION Disengage ECS when: 1. The air flow does not shut-off when ECS switch is OFF. Operate the shut-off switches. 2. The ECS switch trips. Operate the shut-off switches. 3. The air flow does not shut-off when SHUT-OFF # 1, # 2 switches are OFF.
Page 335 UNMAINTAINED COPY RFM A109E APPENDIX 5 ECS switch : OFF. SHUT-OFF # 1 and # 2 switches : OFF. SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES ENGINE FAILURES FAILURE OF ONE ENGINE Procedure ECS switch : OFF. SHUT-OFF # 1 and # 2 switches : OFF.
Page 336 UNMAINTAINED COPY RFM A109E APPENDIX 5 SMOKE IN CABIN, TOXIC FUMES, ETC. ECS switch : OFF. SHUT-OFF # 1 and # 2 switches : OFF. ENVIRONMENTAL CONTROL SYSTEM MALFUNCTION If a malfunction in the ECS controls occurs, deactivate the system as follows: ECS switch : OFF.
Page 337 UNMAINTAINED COPY RFM A109E APPENDIX 5 HEIGHT - VELOCITY DIAGRAM (Up to 2000 ft Hp) The Height - Velocity diagram enable to establish if, in the event of a single engine failure during takeoff, landing or other operation near the surface, a...
Page 338 UNMAINTAINED COPY RFM A109E APPENDIX 5 HEIGHT-VELOCITY DIAGRAM ONE ENGINE INOPERATIVE ECS ON CHART "A" SHOWS THE WEIGHT VALUES AT/BELOW WHICH THERE IS NO H-V DIAGRAM FOR HEAVIER WEIGHTS, REFER TO CHART "B". CHART A GROSS WEIGHT - POUNDS x 100 OAT - ˚C...
Page 339 UNMAINTAINED COPY RFM A109E APPENDIX 5 HEIGHT-VELOCITY DIAGRAM ONE ENGINE INOPERATIVE EAPS OFF ECS ON CHART "A" SHOWS THE WEIGHT VALUES AT/BELOW WHICH THERE IS NO H-V DIAGRAM FOR HEAVIER WEIGHTS, REFER TO CHART "B". CHART A GROSS WEIGHT - POUNDS x 100 OAT - ˚C...
Page 340 UNMAINTAINED COPY RFM A109E APPENDIX 5 HEIGHT-VELOCITY DIAGRAM ONE ENGINE INOPERATIVE EAPS ON ECS ON CHART "A" SHOWS THE WEIGHT VALUES AT/BELOW WHICH THERE IS NO H-V DIAGRAM FOR HEAVIER WEIGHTS, REFER TO CHART "B". CHART A GROSS WEIGHT - POUNDS x 100 OAT - ˚C...
Page 341 UNMAINTAINED COPY RFM A109E APPENDIX 5 HEIGHT-VELOCITY DIAGRAM ONE ENGINE INOPERATIVE FOR SMOOTH, LEVEL, HARD SURFACES GROSS WEIGHT: UP TO 3000 kg (6613 lb) ECS ON (UP TO 2000 ft-HP) WITHOUT EAPS AND WITH EAPS OFF/ON CHART B AVOID OPERATION...
Page 342 UNMAINTAINED COPY RFM A109E APPENDIX 5 HOVERING CEILING IN GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % E.C.S. ON ZERO WIND WHEEL HEIGHT: 3 ft ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 OAT - ˚C...
Page 343 UNMAINTAINED COPY RFM A109E APPENDIX 5 HOVERING CEILING IN GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % WHEEL HEIGHT: 3 ft E.C.S. ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 OAT - ˚C...
Page 344 UNMAINTAINED COPY RFM A109E APPENDIX 5 HOVERING CEILING OUT OF GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % E.C.S. ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND CAUTION:OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V LIMITATIONS. GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 OAT - ˚C...
Page 345 UNMAINTAINED COPY RFM A109E APPENDIX 5 RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS E.C.S. ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2450 kg ( 5401 lb ) OAT - ˚C...
Page 346 UNMAINTAINED COPY RFM A109E APPENDIX 5 HOVERING CEILING OUT OF GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % E.C.S. ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND CAUTION:OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V LIMITATIONS. GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 OAT - ˚C...
Page 347 UNMAINTAINED COPY RFM A109E APPENDIX 5 RATE OF CLIMB ALL ENGINES TAKE-OFF POWER ROTOR: 100 % E.C.S. ON 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2050 kg ( 4519 lb ) OAT - ˚C...
Page 348 UNMAINTAINED COPY RFM A109E APPENDIX 5 RATE OF CLIMB ALL ENGINES TAKE-OFF POWER ROTOR: 100 % 60 kts IAS E.C.S. ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2450 kg ( 5401 lb ) OAT - ˚C...
Page 349 UNMAINTAINED COPY RFM A109E APPENDIX 5 RATE OF CLIMB ALL ENGINES TAKE-OFF POWER ROTOR: 100 % 60 kts IAS E.C.S. ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2850 kg ( 6283 lb ) OAT - ˚C...
Page 350 UNMAINTAINED COPY RFM A109E APPENDIX 5 RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS E.C.S. ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2050 kg ( 4519 lb ) OAT - ˚C...
Page 351 UNMAINTAINED COPY RFM A109E APPENDIX 5 RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS E.C.S. ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2850 kg ( 6283 lb ) OAT - ˚C...
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Page 353 UNMAINTAINED COPY RFM A109E APPENDIX 6 R.A.I. Approval Letter 97/3147/MAE dated 30 July 1997 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 354 UNMAINTAINED COPY RFM A109E APPENDIX 6 TABLE OF CONTENTS Page PART I - R.A.I. APPROVED SECTION 1 - LIMITATIONS BLEED AIR OPERATION 3 of 18 CENTER OF GRAVITY LIMITATIONS 3 of 18 PLACARDS 3 of 18 SECTION 2 - NORMAL PROCEDURES...
Page 355 UNMAINTAINED COPY RFM A109E APPENDIX 6 SECTION 1 - LIMITATIONS BLEED AIR OPERATION The bleed-air heater shall be OFF during take off and landing, in flight below 200 ft AGL, during single engine operation and in all flight conditions requiring the maximum engine power available.
Page 356 UNMAINTAINED COPY RFM A109E APPENDIX 6 SYSTEMS CHECK BLEED-AIR HEATER OPERATIONAL CHECK The operational check may be accomplished at this time or at any time the heater operation is desired. NR/N2 : 100% stabilized, check. TEMPerature CONTrol knob : MIN.
Page 357 UNMAINTAINED COPY RFM A109E APPENDIX 6 CAUTION Turn the heater OFF when: 1. The air flow does not shutoff when TEMP CONTrol knob is turned fully counterclockwise (MIN). Operate the shutoff switches. 2. The HTR switch trips. Operate the shutoff switches.
Page 358 UNMAINTAINED COPY RFM A109E APPENDIX 6 SHUT-OFF # 1 and # 2 switches : OFF. MIX switch : OFF. SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES ENGINE FAILURES FAILURE OF ONE ENGINE PROCEDURE HTR switch : OFF. SHUT-OFF # 1 and # 2 switches : OFF.
Page 359 UNMAINTAINED COPY RFM A109E APPENDIX 6 FIRE ENGINE FIRE IN FLIGHT Procedure HTR switch : OFF. SHUT-OFF # 1 and # 2 switches : OFF. MIX switch : OFF: SMOKE IN CABIN, TOXIC FUMES, ETC. HTR switch : OFF. SHUT-OFF # 1 and # 2 switches : OFF.
Page 360 UNMAINTAINED COPY RFM A109E APPENDIX 6 SECTION 4 - PERFORMANCE DATA GENERAL The maximum power available with the Bleed-Air Heater system operating is less than that available with the helicopter in basic configuration. This power loss is caused by the compressor bleed-air used for the heater system.
Page 361 UNMAINTAINED COPY RFM A109E APPENDIX 6 HOVERING CEILING IN GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % HEATER ON ZERO WIND WHEEL HEIGHT: 3 ft ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 OAT - ˚C...
Page 362 UNMAINTAINED COPY RFM A109E APPENDIX 6 HOVERING CEILING IN GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % WHEEL HEIGHT: 3 ft HEATER ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 OAT - ˚C...
Page 363 UNMAINTAINED COPY RFM A109E APPENDIX 6 HOVERING CEILING OUT OF GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % HEATER ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND CAUTION:OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V LIMITATIONS. GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 OAT - ˚C...
Page 364 UNMAINTAINED COPY RFM A109E APPENDIX 6 HOVERING CEILING OUT OF GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % HEATER ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND CAUTION:OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V LIMITATIONS. GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 OAT - ˚C...
Page 365 UNMAINTAINED COPY RFM A109E APPENDIX 6 RATE OF CLIMB ALL ENGINES TAKE-OFF POWER ROTOR: 100 % HEATER ON 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2050 kg ( 4519 lb ) OAT - ˚C...
Page 366 UNMAINTAINED COPY RFM A109E APPENDIX 6 RATE OF CLIMB ALL ENGINES TAKE-OFF POWER ROTOR: 100 % 60 kts IAS HEATER ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2450 kg ( 5401 lb ) OAT - ˚C...
Page 367 UNMAINTAINED COPY RFM A109E APPENDIX 6 RATE OF CLIMB ALL ENGINES TAKE-OFF POWER ROTOR: 100 % 60 kts IAS HEATER ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2850 kg ( 6283 lb ) OAT - ˚C...
Page 368 UNMAINTAINED COPY RFM A109E APPENDIX 6 RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS HEATER ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2050 kg ( 4519 lb ) OAT - ˚C...
Page 369 UNMAINTAINED COPY RFM A109E APPENDIX 6 RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS HEATER ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2450 kg ( 5401 lb ) OAT - ˚C...
Page 370 UNMAINTAINED COPY RFM A109E APPENDIX 6 RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS HEATER ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2850 kg ( 6283 lb ) OAT - ˚C...
Page 371 UNMAINTAINED COPY RFM A109E APPENDIX 7 R.A.I. Approval Letter 97/3147/MAE dated 30 July 1997 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 372 UNMAINTAINED COPY RFM A109E APPENDIX 7 TABLE OF CONTENTS Page PART I - R.A.I. APPROVED SECTION 1 - LIMITATIONS AIRSPEED LIMITATIONS (KIAS) 3 of 5 SEARCHLIGHT INSTALLATION P/N 109-0811-46 (all dashes, other than -115) 3 of 5 SEARCHLIGHT INSTALLATION P/N 109-0811-46-...
Page 373 UNMAINTAINED COPY RFM A109E APPENDIX 7 SECTION 1 - LIMITATIONS AIRSPEED LIMITATIONS (KIAS) SEARCHLIGHT INSTALLATION P/N 109-0811-46 (all dashes, other than -115) Maximum speed for searchlight exten- sion : 120 KIAS Maximum speed with searchlight ex- tended, for orientation and retraction...
Page 374 UNMAINTAINED COPY RFM A109E APPENDIX 7 PILOT’S PREFLIGHT CHECK (Every flight) Searchlight : Condition and cleanliness. ENGINE PRE-START CHECK SRCH-CTL/SRCH-PWR circuit breakers : ON IN FLIGHT NOTE When operating Searchlight, magnetic compass indication is not reliable. SEARCHLIGHT OPERATING PROCEDURE NOTE...
Page 375 UNMAINTAINED COPY RFM A109E APPENDIX 7 NOTE Moving switch to L or R position the searchlight rotates left or right. It is possible to adjust the light in an intermediate position, from stowed to extended, by temporarily moving the switch to EXT or RETR position.
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Page 377 UNMAINTAINED COPY RFM A109E APPENDIX 8 R.A.I. Approval Letter 97/3147/MAE dated 30 July 1997 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 378 UNMAINTAINED COPY RFM A109E APPENDIX 8 TABLE OF CONTENTS Page PART I - R.A.I. APPROVED SECTION 1 - LIMITATIONS CENTER OF GRAVITY LIMITATIONS 3 of 8 SECTION 2 - NORMAL PROCEDURES ENGINE PRE-START CHECK 3 of 8 SECTION 3 - EMERGENCY AND MALFUNCTION...
Page 379 UNMAINTAINED COPY RFM A109E APPENDIX 8 SECTION 1 - LIMITATIONS CENTER OF GRAVITY LIMITATIONS After supplementary fuel tank installation, the new empty weight and C.G. location must be determined. SECTION 2 - NORMAL PROCEDURES ENGINE PRE-START CHECK Fuel quantity : Check.
Page 380 UNMAINTAINED COPY RFM A109E APPENDIX 8 SECTION 6 - WEIGHT AND BALANCE WEIGHTS - ARMS AND MOMENTS LONGITUDINAL MOMENTS USABLE FUEL - MAIN FUEL TANKS PLUS SUPPLEMENTARY TANKS WEIGHT CAPACITY MOMENT (kg) (mm) (kgm) (0.8 kg/l) 3324 66.5 3327 133.1 3329 199.7...
Page 381 UNMAINTAINED COPY RFM A109E APPENDIX 8 (Cont.) USABLE FUEL - MAIN FUEL TANKS PLUS SUPPLEMENTARY TANKS WEIGHT CAPACITY MOMENT (kg) (mm) (kgm) (0.8 kg/l) 3831 1992.1 3838 2072.5 3845 2153.2 3851 2233.6 3857 2314.2 3863 2395.1 3868 2475.5 3873 2556.2 3883 2640.4...
Page 382 UNMAINTAINED COPY RFM A109E APPENDIX 8 (Cont.) USABLE FUEL - MAIN FUEL TANKS PLUS RH SUPPLEMENTARY TANKS ONLY WEIGHT CAPACITY MOMENT (kg) (mm) (kgm) (0.8 kg/l) 3614 867.4 3645 947.7 3671 1027.9 3695 1108.5 3715 1188.8 3733 1269.2 3750 1350.0 3764 1430.3...
Page 383 UNMAINTAINED COPY RFM A109E APPENDIX 8 LATERAL MOMENTS USABLE FUEL - MAIN FUEL TANKS PLUS RH SUPPLEMENTARY TANK ONLY WEIGHT CAPACITY MOMENT (kg) (mm) (kgm) (0.8 kg/l) 12.0 15.7 19.7 23.8 27.7 31.6 33.2 33.0 33.1 33.1 33.0 33.3 32.9 33.0...
Page 384 UNMAINTAINED COPY RFM A109E APPENDIX 8 SECTION 8 - HANDLING AND SERVICING SERVICING Supplementary fuel tanks RH fuel cell LH fuel cell Capacity 105 liters 160 liters Usable 105 liters 160 liters Page 8 of 8 Rev. 11...
Page 385 For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual. ″GREEN AIRCRAFT″ CONFIGURATION The ″Green Aircraft″ configuration, as defined in the current Agusta Report N° 109-06-07, includes the following non-conformities with respect to the General Arrangement Drawing N° 109-9000-01-151: —...
Page 386 UNMAINTAINED COPY RFM A109E APPENDIX 9 TABLE OF CONTENTS Page PART I - R.A.I. APPROVED SECTION 1 - LIMITATIONS FLIGHT CREW 3 of 3 NUMBER OF SEATS 3 of 3 SECTION 2 - NORMAL PROCEDURES 3 of 3 SECTION 3 - EMERGENCY AND MALFUNCTION...
Page 387 UNMAINTAINED COPY RFM A109E APPENDIX 9 SECTION 1 - LIMITATIONS FLIGHT CREW The minimum flight crew consists of one pilot who shall operate the helicopter from the right crew seat. NUMBER OF SEATS One (pilot). SECTION 2 - NORMAL PROCEDURES No change.
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Page 389 UNMAINTAINED COPY RFM A109E APPENDIX 10 R.A.I. Approval Letter 97/5288/MAE dated 17 December 1997 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 390 UNMAINTAINED COPY RFM A109E APPENDIX 10 — -131 consists of an internal arrangement without any litter, eight seats (including the pilot), panels at the upper side of lateral and aft walls for medical devices, lights and a provision for the oxygen system.
Page 391 UNMAINTAINED COPY RFM A109E APPENDIX 10 TABLE OF CONTENTS Page PART I - E.A.S.A. APPROVED SECTION 1 - LIMITATIONS TYPE OF OPERATION 5 of 15 REQUIRED EQUIPMENT 5 of 15 VFR OPERATION 5 of 15 FLIGHT WITH PASSENGER CABIN DOORS OPEN...
Page 392 UNMAINTAINED COPY RFM A109E APPENDIX 10 PART II - MANUFACTURER’S DATA SECTION 6 - WEIGHT AND BALANCE PATIENT ARM ON LITTER (-113/-179, -119/-165, -137/-173, -143 AND -163/-183) 11 of 15 PATIENTS ARM ON LITTER (-127/-171 AND -145) 11 of 15...
Page 393 UNMAINTAINED COPY RFM A109E APPENDIX 10 SECTION 1 - LIMITATIONS TYPE OF OPERATION The helicopter in EMS configuration permits rescue and ambulance operation under day and night VFR and IFR non-icing conditions. REQUIRED EQUIPMENT Sliding doors kit installation is required for EMS installation and operation.
Page 394 UNMAINTAINED COPY RFM A109E APPENDIX 10 BAGGAGE COMPARTMENT LIMITATIONS (When oxygen bottle is installed) Maximum load : 140 kg (309 lb) CENTER OF GRAVITY LIMITATIONS After E.M.S. installation the new empty weight and CG location must be determined. PLACARDS (When oxygen bottle is installed)
Page 395 UNMAINTAINED COPY RFM A109E APPENDIX 10 NOTE The messages UTIL DOOR and OXYGEN CLOSED are respec- tively replaced by caution and advisory lights on the instrument panel when IDS configuration utilizes the EDU software version 06 or lower and DAU software version 05 or lower.
Page 396 UNMAINTAINED COPY RFM A109E APPENDIX 10 NOTE If the OXY H.P. RELIEF green indicator plug is not in position, the oxygen bottle is discharged. Baggage compartment : Check the oxygen bottle fairing is properly secured. Cabin seats and litter(s) : Check for condition and fastened if unoccupied.
Page 397 UNMAINTAINED COPY RFM A109E APPENDIX 10 APPROACH AND LANDING Cabin curtain (if installed) : Open. In case of night flight CAB switch : OFF. LITTER OPERATIONS (All E.M.S. configurations except P/N 109-0811-70-131) LITTER(S) LOADING — Secure patient(s) to the litter using the three straps provided.
Page 398 UNMAINTAINED COPY RFM A109E APPENDIX 10 SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES (E.M.S. P/N 109-0811-70-119/-165, -137/173 and -143) WARNING SYSTEM CAUTION MESSAGES (YELLOW) NOTE The messages UTIL DOOR and OXYGEN CLOSED are respec- tively replaced by caution and advisory lights on the instrument panel when IDS configuration utilizes the EDU software version 06 or lower and DAU software version 05 or lower.
Page 399 UNMAINTAINED COPY RFM A109E APPENDIX 10 SECTION 6 - WEIGHT AND BALANCE PATIENT ARM ON LITTER (-113/-179, -119/-165, -137/-173, -143 AND -163/-183) Longitudinal arm (STA) : 2900 mm (114.2 inches) from STA 0. Lateral arm (BL) : 412 mm (16.2 inches) from the helicopter plane of simmetry.
Page 400 UNMAINTAINED COPY RFM A109E APPENDIX 10 Lateral, outboard attendant arm (BL) : 412 mm (16.2 inches) from the helicopter plane of simmetry. AFT ATTENDANT ARM (-127/-171 AND -145) Longitudinal arm (STA) : 3200 mm (126 inches) from STA 0. AFT ATTENDANTS ARM (-131 ONLY)
Page 401 UNMAINTAINED COPY RFM A109E APPENDIX 10 SECTION 7 - SYSTEMS DESCRIPTION Figure 7-1. (sheet 1 of 2) E.M.S. Interior arrangement. Page 13 of 15 Rev. 37...
Page 402 UNMAINTAINED COPY RFM A109E APPENDIX 10 Figure 7-1. (sheet 2 of 2) E.M.S. Interior arrangement. Page 14 of 15 Rev. 37...
Page 403 UNMAINTAINED COPY RFM A109E APPENDIX 10 (WHEN OXYGEN BOTTLE IS INSTALLED) Figure 7-2. Oxygen manual shut-off handle. Page 15 of 15 Rev. 36...
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Page 405 UNMAINTAINED COPY RFM A109E APPENDIX 11 R.A.I. Approval Letter 97/5288/MAE dated 17 December 1997 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 406 UNMAINTAINED COPY RFM A109E APPENDIX 11 TABLE OF CONTENTS Page PART I - R.A.I. APPROVED SECTION 1 - LIMITATIONS VFR OPERATION 3 of 5 IFR OPERATION 3 of 5 AIRSPEED LIMITATIONS (KIAS) 3 of 5 CENTER OF GRAVITY LIMITATIONS 3 of 5...
Page 407 UNMAINTAINED COPY RFM A109E APPENDIX 11 SECTION 1 - LIMITATIONS VFR OPERATION VFR operation is approved with either one or both doors locked in open position or removed. NOTE Operating limitations are identical for both conditions either with doors locked in open position or removed.
Page 408 UNMAINTAINED COPY RFM A109E APPENDIX 11 CAUTION Opening one or both sliding doors will result in a 13 mm maximum aft displacement change CG location. PLACARDS OPENING/CLOSING DOOR ABOVE 70 Kts IAS IS PROHIBITED Below each sliding door handle SECTION 2 - NORMAL PROCEDURES PILOT’S DAILY PREFLIGHT CHECK...
Page 409 UNMAINTAINED COPY RFM A109E APPENDIX 11 Cabin interior : Operation with passenger slid- ing doors open or removed re- quires removal or correct secur- ing of all cabin equipment, installations and trim panels. IN FLIGHT CAUTION Assure that doors are engaged correctly on stops during operation with doors open.
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Page 411 UNMAINTAINED COPY RFM A109E APPENDIX 12 R.A.I. Approval Letter 98/401/MAE dated 29-1-1998 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 412 UNMAINTAINED COPY RFM A109E APPENDIX 12 TABLE OF CONTENTS Page PART I - R.A.I. APPROVED GENERAL INFORMATION 7 of 88 DEFINITIONS 7 of 88 ABBREVIATIONS 10 of 88 SECTION 1 - LIMITATIONS TYPE OF OPERATION 11 of 88 REQUIRED EQUIPMENT...
Page 413 UNMAINTAINED COPY RFM A109E APPENDIX 12 Table of Contents (Contd.) Page TAKEOFF 30 of 88 TAKEOFF FROM HELIPAD (STANDARD TDP) 30 of 88 MODIFIED TAKEOFF FLIGHT PATH FROM GROUND BASED HELIPAD TO CLEAR HIGH OBSTACLES 34A of 88 (INCREASED TDP)
Page 414 UNMAINTAINED COPY RFM A109E APPENDIX 12 Table of Contents (Contd.) Page ENGINE FAILURE DURING TAKEOFF AT/AFTER THE TAKEOFF DECISION POINT (TDP) 61 of 88 ENGINE FAILURE DURING LANDING PRIOR TO/AT THE LANDING DECISION POINT (LDP) 63 of 88 ENGINE FAILURE DURING LANDING AT/AFTER...
Page 415 UNMAINTAINED COPY RFM A109E APPENDIX 12 Table of Contents (Contd.) Page CLIMB PERFORMANCE 83 of 88 SINGLE ENGINE RATE OF CLIMB AT V (30 KTS IAS) 83 of 88 SINGLE ENGINE RATE OF CLIMB AT V (60 KTS IAS) 83 of 88...
Page 416 UNMAINTAINED COPY RFM A109E APPENDIX 12 List of Illustrations (Contd.) Page Figure 3-7. Balked landing flight path profile (short field). 56 of 88 Figure 3-8. OEI landing flight path profile (short field). 58 of 88 Figure 3-9. Rejected takeoff flight path profile (helipad).
Page 417 UNMAINTAINED COPY RFM A109E APPENDIX 12 INTRODUCTION GENERAL INFORMATION This Appendix provides all information allowing the aircraft to be operated in equivalent Category ″A″ as defined in JAR OPS 3.480. DEFINITIONS – CAT - A take-off : Operation of the helicopter tak-...
Page 418 UNMAINTAINED COPY RFM A109E APPENDIX 12 – Takeoff decision point (TDP) : It is the last point in the take off path at which, as result of power unit failure, a rejected takeoff can be assured, and the first point at which a completed takeoff can be assured.
Page 419 UNMAINTAINED COPY RFM A109E APPENDIX 12 – Landing distance : The horizontal distance from a point where the helicopter is 50 ft (15.2 m) (25 ft for vertical landings) above the landing surface to the point where it is brought to stop on the predeter- mined area with one engine in- operative.
Page 420 UNMAINTAINED COPY RFM A109E APPENDIX 12 – Congested area : A densely populated area sub- stantially used for residential, commercial, recreational purposes without adequate safe forced landing areas. ABBREVIATIONS – AGL : Above Ground Level. – AHE : Above Helipad Elevation.
Page 421 UNMAINTAINED COPY RFM A109E APPENDIX 12 SECTION 1 - LIMITATIONS NOTE The helicopter is certified for ″Equivalent Category A″ operations as defined in JAR OPS 3.480. TYPE OF OPERATION Takeoff and landing procedures from clear area, short field and from ground based or elevated helipads, herein described, are approved under day and night VFR, non-icing conditions.
Page 422 UNMAINTAINED COPY RFM A109E APPENDIX 12 WEIGHT-ALTITUDE-TEMPERATURE LIMITATIONS FOR TAKE OFF AND LANDING CLEAR AREA HEATER OR E.C.S. OFF V2 30 kts IAS GROSS WEIGHT - POUNDS x 100 Hd LIMIT 8000 ft OAT - ˚C GROSS WEIGHT - kg X 100...
Page 423 UNMAINTAINED COPY RFM A109E APPENDIX 12 WEIGHT-ALTITUDE-TEMPERATURE LIMITATIONS FOR TAKE OFF AND LANDING SHORT FIELD (100m) HEATER OR E.C.S. OFF V2 30 kts IAS GROSS WEIGHT - POUNDS x 100 Hd LIMIT 8000 ft OAT - ˚C GROSS WEIGHT - kg X 100...
Page 424 UNMAINTAINED COPY RFM A109E APPENDIX 12 WEIGHT-ALTITUDE-TEMPERATURE LIMITATIONS FOR TAKE OFF AND LANDING GROUND BASED HELIPAD 15m x 15m ELEVATED HELIPAD 20m x 20m V2 30 kts IAS HEATER OR E.C.S. OFF GROSS WEIGHT - POUNDS x 100 Hd LIMIT 8000 ft OAT - ˚C...
Page 425 UNMAINTAINED COPY RFM A109E APPENDIX 12 ALTITUDE LIMITATIONS The maximum altitude for takeoff and landing is: — operation from clear area 8000 ft (2438 m) Hd NOTE The ″soft″ takeoff manoeuvre is applicable up to 3000 ft (914 m) Hd only.
Page 426 UNMAINTAINED COPY RFM A109E APPENDIX 12 SECTION 2 - NORMAL PROCEDURES OPERATION FROM CLEAR AREA GENERAL DATA TAKEOFF DECISION POINT (TDP) : 30 Kts IAS. Wheels height : 15 ft (4.6 m) AGL (Standard manoeuvre). 70 ft (21.3 m) AGL (″Soft″...
Page 427 UNMAINTAINED COPY RFM A109E APPENDIX 12 TAKEOFF There are two different takeoff procedures when operating from clear area: a dynamic takeoff manoeuvre (standard takeoff manoeuvre) which minimizes the takeoff and the rejected takeoff distances and a less dynamic takeoff manoeuvre (″soft″ takeoff manoeuvre) privileging the comfort of passengers against a longer rejected takeoff distance.
Page 428 UNMAINTAINED COPY RFM A109E APPENDIX 12 NOTE When use of search and landing light is required proceed as follows: LDG LT switch : FWD. SCHLT switch : ON, extend and set as necessary. CAUTION Landing light operation shall be limited to the time strictly necessary to carry out takeoff and landing manoeuvres in order to avoid overheating.
Page 429 UNMAINTAINED COPY RFM A109E APPENDIX 12 STANDARD TAKEOFF MANOEUVRE (Fig 2-1) Figure 2-1. Takeoff flight path profile from clear area (Standard takeoff manoeuvre). Collective and cyclic : Apply as necessary to increase torque by 15% ±5% on each engine above that required to hover and set 25 degrees nose down attitude change.
Page 430 UNMAINTAINED COPY RFM A109E APPENDIX 12 ″SOFT″ TAKEOFF MANOEUVRE (Fig 2-1A) Figure 2-1A. Takeoff flight path profile from clear area (″Soft″ takeoff manoeuvre). Collective and cyclic : Apply as necessary to increase torque by 15% ± 5% on each engine above that required to hover and set 15 degrees nose down attitude change.
Page 431 UNMAINTAINED COPY RFM A109E APPENDIX 12 Landing gear : UP (by 200 ft AGL). RPM switch : Set 100%. NR/N2 speed : 100% stabilized, check. Takeoff path : Climb at V to the desired alti- tude. E.A.S.A. Approved Page 19 of 88...
Page 432 UNMAINTAINED COPY RFM A109E APPENDIX 12 APPROACH AND LANDING LANDING ON CLEAR AREA (Fig 2-2) Figure 2-2. Landing flight path profile on clear area. Altimeter : Set the known QFE. : Verifiy for equivalent attitude indication between ADIs. RPM switch : Set 102%.
Page 433 UNMAINTAINED COPY RFM A109E APPENDIX 12 Parking brake : Off. Check PARK BRK ON caution message out. External lights : As required. NOTE When use of search and landing light is required proceed as follows: LDG LT switch : FWD.
Page 434 UNMAINTAINED COPY RFM A109E APPENDIX 12 OPERATION ON SHORT FIELD THE SHORT FIELD PROCEDURE CAN BE USED IN CONGESTED AREA IN ACCORDANCE WITH THE APPROPRIATE OPERATING RULES. GENERAL DATA The minimum size for takeoff and landing area is 100 m (length) x 20 m (width) (328 ft x 66 ft) (figure 2-3).
Page 435 UNMAINTAINED COPY RFM A109E APPENDIX 12 LANDING DECISION POINT (LDP) : 25 Kts IAS. Wheel height : 80 ft (25.4 m) AGL. Rate of descent : 500 ±100 fpm. : 30 Kts IAS. : 60 Kts IAS. NOTE Radio altimeter heights should be used when available.
Page 436 UNMAINTAINED COPY RFM A109E APPENDIX 12 CAUTION The ECS or the bleed-air heater must be off during takeoff. NOTE Takeoff will be initiated with the helicopter positioned, such that the takeoff reference marks are directly opposite the crew doors and the helicopter centered on the runway.
Page 437 UNMAINTAINED COPY RFM A109E APPENDIX 12 CAUTION Landing light operation shall be limited to the time strictly necessary to carry out takeoff and landing manoeuvres in order to avoid overheating. Takeoff area : Check clear. Collective : Slowly increase to hover at ap- proximately 3 ft (1 m) wheels height and note torque.
Page 438 UNMAINTAINED COPY RFM A109E APPENDIX 12 NR/N2 speed : 100% stabilized, check. Takeoff path : Climb at V to the desired alti- tude. APPROACH AND LANDING LANDING ON SHORT FIELD (Fig 2-5) Figure 2-5. Landing profile on short field. Altimeter : Set the known QFE.
Page 439 UNMAINTAINED COPY RFM A109E APPENDIX 12 CAUTION Check the lever to be correctly engaged in the DOWN position to avoid inadvertent retraction of the landing gear. Nose wheel lock : ON (lever up). Parking brake : Off. Check PARK BRK ON caution message out.
Page 440 UNMAINTAINED COPY RFM A109E APPENDIX 12 Approach path : Initiate the approach to pass through the LDP, at 80 ft (25.4 m) above the landing site, at 25 Kts IAS and with a rate of descent not higher than 500 ±100 fpm.
Page 441 UNMAINTAINED COPY RFM A109E APPENDIX 12 HELIPAD OPERATION (GROUND LEVEL OR ELEVATED) GENERAL DATA The minimum helipad sizes demonstrated for OEI landing procedure are: — ground based helipad 15 m x 15m (49 ft x 49 ft) — elevated helipad 20 m x 20 m (66 ft x 66 ft).
Page 442 UNMAINTAINED COPY RFM A109E APPENDIX 12 Rate of descent : 200 ±50 fpm. : 30 Kts IAS. : 60 Kts IAS. NOTE Radio altimeter heights should be used when available if operat- ing over a ground level helipad only. TAKEOFF...
Page 443 UNMAINTAINED COPY RFM A109E APPENDIX 12 Collective : MPOG. Nose wheel lock : ON (lever up). Parking brake : ON. Check PARK BRK ON caution message displayed. Caution and warning messages : Check none. RPM switch : Set 102%. NR/N2 speed : 102% stabilized, check.
Page 444 UNMAINTAINED COPY RFM A109E APPENDIX 12 Altimeter : Set zero pressure altitude. : Adjust (if applicable) the pitch bar to indicate zero. NOTE When taking off in windy conditions, set the ADI and the baro-altimeter on ground allowing for the anticipated attitude and altitude changes.
Page 445 UNMAINTAINED COPY RFM A109E APPENDIX 12 Figure 2-7. Takeoff from helipad - view at 3 ft height. R.A.I. Approved Page 33 of 88 Rev. 11...
Page 446 UNMAINTAINED COPY RFM A109E APPENDIX 12 Figure 2-8. Takeoff from helipad - view at TDP (80 ft). Page 34 of 88 R.A.I. Approved Rev. 11...
Page 447 UNMAINTAINED COPY RFM A109E APPENDIX 12 Takeoff path : Climb at V to the desired alti- tude. NOTE For operations on elevated helipad, when obstacles and weather conditions permit, select a takeoff direction that allows the best use of available external cues, which may ease the possible reject manoeuvre.
Page 448 UNMAINTAINED COPY RFM A109E APPENDIX 12 Procedure Determine the TDP height such that the Minimum Height presented in Table 2-1 is not lower than the obstacle height plus 35 ft of clearance. Perform the takeoff procedure from helipad utilizing the above TDP and taking into account of the increased Backup Distance.
Page 449 UNMAINTAINED COPY RFM A109E APPENDIX 12 Solution: - Add 35 ft of minimum clearance to known obstacle height (50 ft) to obtain the Minimum Height (85 ft) on takeoff path. - Enter table 2-1 with Minimum Height (85 ft) to obtain the...
Page 450 UNMAINTAINED COPY RFM A109E APPENDIX 12 : Verify for equivalent attitude indication between ADIs. RPM switch : Set 102%. NR/N2 speed : 102% stabilized, check. Landing gear : DOWN. CAUTION Check the lever to be correctly engaged in DOWN position to avoid inadvertent retraction of the landing gear.
Page 451 UNMAINTAINED COPY RFM A109E APPENDIX 12 CAUTION The ECS or the bleed-air heater must be off during landing. Approach path : Initiate the approach to pass through the LDP, at 80 ft (25.4 m) above the landing site, with an airspeed up to 20 Kts...
Page 452 UNMAINTAINED COPY RFM A109E APPENDIX 12 Figure 2-10. Landing on helipad - view at LDP (80 ft). Page 38 of 88 R.A.I. Approved Rev. 11...
Page 453 UNMAINTAINED COPY RFM A109E APPENDIX 12 SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES INTRODUCTION The following tables list the EDU messages, the fault conditions, and corrective actions for emergencies and malfunctions that might occur during takeoff prior to TDP, during takeoff after TDP, during landing prior to LDP, and during landing after LDP.
Page 454 UNMAINTAINED COPY RFM A109E APPENDIX 12 EDU message Fault condition Corrective action ROTOR HIGH Rotor RPM high. Use collective to ad- Rotor RPM above or just RPM. equal to 105.5% (power on) or 110.5% (power off). ENG 1 (2) OUT N1 abnormally low, Land immediately.
Page 455 UNMAINTAINED COPY RFM A109E APPENDIX 12 Takeoff (after TDP) EDU message Fault condition Corrective action ROTOR LOW Rotor RPM low. Use collective to ad- Rotor RPM between just RPM. 80% and 95.5% (power If this message occurs on) or 80% and 89.5%...
Page 456 UNMAINTAINED COPY RFM A109E APPENDIX 12 EDU message Fault condition Corrective action XMSN OIL PRES Transmission oil pres- Reach reduce sure below minimum power and land as limit. soon as possible, how- ever not later than 15 minutes. XMSN OIL HOT...
Page 457 UNMAINTAINED COPY RFM A109E APPENDIX 12 Landing (prior to LDP) NOTE The decision to execute a balked landing when flying on one engine should be taken before the helicopter descends below LDP. EDU message Fault condition Corrective action ROTOR LOW Rotor RPM low.
Page 458 UNMAINTAINED COPY RFM A109E APPENDIX 12 EDU message Fault condition Corrective action ENG 1 (2) FIRE Fire in engine com- Reach V and operate partment. the engine fire extin- guisher. (See the perti- nent paragraph of Ap- pendix 2). Shutdown the affected engine.
Page 459 UNMAINTAINED COPY RFM A109E APPENDIX 12 Landing (after LDP) EDU message Fault condition Corrective action ROTOR LOW Rotor RPM low. Use collective to ad- Rotor RPM between just RPM. 95.5% (power on) or 80% and 89.5% (power off). ROTOR HIGH Rotor RPM high.
Page 460 UNMAINTAINED COPY RFM A109E APPENDIX 12 EDU message Fault condition Corrective action XMSN OIL HOT Transmission oil tem- Land immediately. perature above maxi- mum limit. BATT HOT Battery temperature Land immediately. exceeding limits. Switch battery off. #1 (#2) ECU FAIL...
Page 461 UNMAINTAINED COPY RFM A109E APPENDIX 12 EMERGENCY PROCEDURES FOR OPERATION ON CLEAR AREA ENGINE FAILURE DURING TAKEOFF PRIOR TO/AT THE TAKE- OFF DECISION POINT (TDP) (Fig 3-1) Figure 3-1. Rejected takeoff flight path profile (clear area). NOTE During the rejected takeoff manoeuvre, the pilot shall control the rotor speed, disregarding the other ECU controlled engine param- eters.
Page 462 UNMAINTAINED COPY RFM A109E APPENDIX 12 Collective : Level pitch attitude and as the helicopter starts to sink, gradu- ally increase to cushion the touchdown. NOTE During a ″soft″ takeoff manoeuvre anticipate the recovery of normal attitude immediately after the pitch up manoeuvre, by slowly levelling the helicopter and by maintaining the level pitch attitude until touchdown.
Page 463 UNMAINTAINED COPY RFM A109E APPENDIX 12 Collective : Adjust as necessary to drop NR not below 90%. Airspeed : Increase to V using up to 2.5 minute power and start to climb. Continued takeoff manoeuvre : Recover rotor speed and climb at V using 2.5 minute power to...
Page 464 UNMAINTAINED COPY RFM A109E APPENDIX 12 ENGINE FAILURE DURING LANDING PRIOR TO/AT THE LAND- ING DECISION POINT (LDP) (Fig 3-3) Figure 3-3. Balked landing flight path profile (clear area). Balked landing manoeuvre : Reach V by pushing over 15 degrees attitude change and by setting the collective to obtain up to 2.5 minute power and to...
Page 465 UNMAINTAINED COPY RFM A109E APPENDIX 12 Airspeed : Accelerate to V while climbing. RPM switch : Set 100%. NR/N2 speed : 100% stabilized, check. Climb path : Select maximum continuous power OEI and keep on climb- ing at V up to 1000 ft (305 m).
Page 466 UNMAINTAINED COPY RFM A109E APPENDIX 12 Airspeed : Reduce by setting a 20 degrees nose up attitude change when approaching 15 ft. Attitude : Assume landing attitude before touchdown to avoid touching the tail first. Touchdown : As the helicopter starts running on the ground reduce collective and apply toe brakes to stop.
Page 467 UNMAINTAINED COPY RFM A109E APPENDIX 12 EMERGENCY PROCEDURES FOR OPERATION ON SHORT FIELD ENGINE FAILURE DURING TAKEOFF PRIOR TO/AT THE TAKE- OFF DECISION POINT (TDP) (Fig 3-5) Figure 3-5. Rejected takeoff flight path profile (short field). NOTE During the rejected takeoff manoeuvre, the pilot shall control the rotor speed, disregarding the other ECU controlled engine param- eters.
Page 468 UNMAINTAINED COPY RFM A109E APPENDIX 12 Rejected takeoff manoeuvre : If the failure occurs below 50 ft AGL push over slightly to bring the helicopter back to the ground. If the failure occurs at or above 50 ft AGL push over 20 degrees...
Page 469 UNMAINTAINED COPY RFM A109E APPENDIX 12 ENGINE FAILURE DURING TAKEOFF AT/AFTER THE TAKEOFF DECISION POINT (TDP) (Fig 3-6) Figure 3-6. Continued takeoff flight path profile (short field). Continued takeoff manoeuvre : Push over 25 degrees attitude change to reach V Adjust the collective to drop NR not below 90%.
Page 470 UNMAINTAINED COPY RFM A109E APPENDIX 12 RPM switch : Set 100%. NR/N2 speed : 100% stabilized, check. Takeoff path : Select maximum continuous power OEI and keep on climb- ing at V up to 1000 ft (305 m). Affected engine : Perform the complete shutdown procedure.
Page 471 UNMAINTAINED COPY RFM A109E APPENDIX 12 Balked landing manoeuvre : Reach V by pushing over 20 degrees attitude change and by setting the collective to obtain up to 2.5 minute power and to drop NR not below 90%. As the...
Page 472 UNMAINTAINED COPY RFM A109E APPENDIX 12 ENGINE FAILURE DURING LANDING AT/AFTER THE LANDING DECISION POINT (LDP) (Fig 3-8) Figure 3-8. OEI landing flight path profile (short field). Collective : As necessary to maintain rotor RPM. OEI landing manoeuvre : If the failure occurs at or above...
Page 473 UNMAINTAINED COPY RFM A109E APPENDIX 12 Perform a flare and level the helicopter before accomplish- ing a running landing. NOTE Attention should be paid to avoid touching the tail first. Touchdown : As soon as the helicopter touches the ground reduce the collective and apply toe brakes to stop.
Page 474 UNMAINTAINED COPY RFM A109E APPENDIX 12 EMERGENCY PROCEDURES FOR OPERATION ON HE- LIPAD (GROUND LEVEL OR ELEVATED) ENGINE FAILURE DURING TAKEOFF PRIOR TO/AT THE TAKE- OFF DECISION POINT (TDP) (Fig 3-9) Figure 3-9. Rejected takeoff flight path profile (helipad). Collective : As necessary to maintain rotor RPM and OEI limits.
Page 475 UNMAINTAINED COPY RFM A109E APPENDIX 12 Perform a flare and level the helicopter to establish the mini- mum ground speed. Collective : As necessary to cushion landing. NOTE Attention should be paid to avoid touching the tail first. After landing perform normal shutdown procedure.
Page 476 UNMAINTAINED COPY RFM A109E APPENDIX 12 Continued takeoff manoeuvre : Set a nose down attitude of approximately 25 degrees to achieve V by using up to the 2.5 minute power. Adjust col- lective to drop NR not below 90%. As the speed approaches V reduce the nose down attitude.
Page 477 UNMAINTAINED COPY RFM A109E APPENDIX 12 Manoeuvre from ground level helipad with increased TDP Continued takeoff manoeuvre : Set a nose down attitude change of approximately 25 degrees to achieve V by using up to the 2.5 minute power. Adjust collective to drop NR not below 90%.
Page 478 UNMAINTAINED COPY RFM A109E APPENDIX 12 Takeoff path : Select maximum continuous power OEI and keep on climb- ing at V up to 1000 ft (305 m). Affected engine : Perform the complete shutdown procedure. Land as soon as possible.
Page 479 UNMAINTAINED COPY RFM A109E APPENDIX 12 ENGINE FAILURE DURING LANDING PRIOR TO/AT THE LAND- ING DECISION POINT (LDP) (Fig 3-11) Figure 3-11. Balked landing flight path profile (helipad). Balked landing manoeuvre : Reach V by pushing over 15 degrees attitude change and by setting the collective to obtain up to 2.5 minute power and to...
Page 480 UNMAINTAINED COPY RFM A109E APPENDIX 12 Airspeed : Accelerate to V while climbing. RPM switch : Set 100%. NR/N2 speed : 100% stabilized, check. Climb path : Select maximum continuous power OEI and keep on climb- ing at V up to 1000 ft (305 m).
Page 481 UNMAINTAINED COPY RFM A109E APPENDIX 12 Collective : As necessary to maintain rotor RPM. OEI landing manoeuvre : If the failure occurs at or above 50 ft above the helipad, push over 15 degrees attitude change to increase forward speed and approach the landing site.
Page 482 UNMAINTAINED COPY RFM A109E APPENDIX 12 SECTION 4 - PERFORMANCE DATA POWER ASSURANCE CHECK Refer to Section 4 of the basic Rotorcraft Flight Manual to determine if the engine can provide the installed specification power. The hover check shall be performed daily prior to takeoff.
Page 483 UNMAINTAINED COPY RFM A109E APPENDIX 12 Figure 4-1. Wind component chart. R.A.I. Approved Page 67 of 88...
Page 484 UNMAINTAINED COPY RFM A109E APPENDIX 12 OPERATION FROM CLEAR AREA NOTE The distances are applicable to all weights, pressure altitudes and ambient temperatures, when operating at allowed gross weights (see WAT limitations). TAKEOFF DISTANCE The distance from takeoff starting to clear a 35 ft high obstacle at V...
Page 485 UNMAINTAINED COPY RFM A109E APPENDIX 12 OPERATION ON SHORT FIELD NOTE The distances are applicable to all weights, pressure altitudes and ambient temperatures, when operating at allowed gross weights (see WAT limitations). TAKEOFF DISTANCE The distance from takeoff starting to clear a 35 ft high obstacle at V with a positive OEI rate of climb following an engine failure is 460 m.
Page 486 UNMAINTAINED COPY RFM A109E APPENDIX 12 HELIPAD OPERATION (GROUND LEVEL OR ELEVATED) NOTE The distances are applicable to all weights, pressure altitudes and ambient temperatures, when operating at allowed gross weights (see WAT limitations). TAKEOFF DISTANCE (MANOEUVRE WITH STANDARD TDP) The horizontal distance from the start of takeoff to reach a point at least 35 ft (10.6 m) above the helipad at V...
Page 487 UNMAINTAINED COPY RFM A109E APPENDIX 12 TDP HEIGHT BACKUP DISTANCE TAKEOFF DISTANCE (ft) -100 -115 -130 -145 -160 -175 -190 -210 -225 -240 Table 4-1. Distances versus the TDP. LANDING DISTANCE The horizontal distance from a point 25 ft (7.6 m) above the helipad to the landing point is 55 m.
Page 488 UNMAINTAINED COPY...
Page 489 UNMAINTAINED COPY RFM A109E APPENDIX 12 TAKEOFF FLIGHT PATH 1 MEAN HEIGHT GAINED IN 30 M HORIZONTAL DISTANCE The mean height gained in 30 m of horizontal distance travelled during an OEI climb at V after takeoff is shown in figures 4-2 thru 4-6 for various altitudes, temperatures, weights and headwind components.
Page 490 UNMAINTAINED COPY RFM A109E APPENDIX 12 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2050 kg ( 4519 lb ) OAT - ˚C...
Page 491 UNMAINTAINED COPY RFM A109E APPENDIX 12 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2250 kg ( 4960 lb ) OAT - ˚C...
Page 492 UNMAINTAINED COPY RFM A109E APPENDIX 12 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2450 kg ( 5401 lb ) OAT - ˚C...
Page 493 UNMAINTAINED COPY RFM A109E APPENDIX 12 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2650 kg ( 5842 lb ) OAT - ˚C...
Page 494 UNMAINTAINED COPY RFM A109E APPENDIX 12 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2850 kg ( 6283 lb ) OAT - ˚C...
Page 495 UNMAINTAINED COPY RFM A109E APPENDIX 12 TAKEOFF FLIGHT PATH 2 MEAN HEIGHT GAINED IN 30 M HORIZONTAL DISTANCE The mean height gained in 30 m of horizontal distance travelled during an OEI climb at V after takeoff is shown in figures 4-7 thru 4-11 for various altitudes, temperatures, weights and headwind components.
Page 496 UNMAINTAINED COPY RFM A109E APPENDIX 12 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % Vy 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2050 kg ( 4519 lb ) OAT - ˚C...
Page 497 UNMAINTAINED COPY RFM A109E APPENDIX 12 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % Vy 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2250 kg ( 4960 lb ) OAT - ˚C...
Page 498 UNMAINTAINED COPY RFM A109E APPENDIX 12 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % Vy 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2450 kg ( 5401 lb ) OAT - ˚C...
Page 499 UNMAINTAINED COPY RFM A109E APPENDIX 12 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % Vy 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2650 kg ( 5842 lb ) OAT - ˚C...
Page 500 UNMAINTAINED COPY RFM A109E APPENDIX 12 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % Vy 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2850 kg ( 6283 lb ) OAT - ˚C...
Page 501 UNMAINTAINED COPY RFM A109E APPENDIX 12 CLIMB PERFORMANCE SINGLE ENGINE RATE OF CLIMB AT V (30 KTS IAS) The single engine rate of climb, at minimum V and 2.5 minute power, is shown in figures 4-12 thru 4-16 for various altitudes, temperatures and weights.
Page 502 UNMAINTAINED COPY RFM A109E APPENDIX 12 RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2050 kg ( 4519 lb ) OAT - ˚C...
Page 503 UNMAINTAINED COPY RFM A109E APPENDIX 12 RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2250 kg ( 4960 lb ) OAT - ˚C...
Page 504 UNMAINTAINED COPY RFM A109E APPENDIX 12 RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2450 kg ( 5401 lb ) OAT - ˚C...
Page 505 UNMAINTAINED COPY RFM A109E APPENDIX 12 RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2650 kg ( 5842 lb ) OAT - ˚C...
Page 506 UNMAINTAINED COPY RFM A109E APPENDIX 12 RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2850 kg ( 6283 lb ) OAT - ˚C...
Page 507 UNMAINTAINED COPY RFM A109E APPENDIX 13 R.A.I. Approval Letter 98/401/MAE dated 29-1-1998 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 508 UNMAINTAINED COPY RFM A109E APPENDIX 13 TABLE OF CONTENTS Page PART I - R.A.I. APPROVED SECTION 1 - LIMITATIONS TYPE OF OPERATION 3 of 12 POWER PLANT LIMITATIONS 3 of 12 POWER TURBINE (N2) RPM 3 of 12 ROTOR LIMITATIONS...
Page 509 UNMAINTAINED COPY RFM A109E APPENDIX 13 SECTION 1 - LIMITATIONS TYPE OF OPERATION The equivalent Cat. A operations are prohibited. POWER PLANT LIMITATIONS POWER TURBINE (N2) RPM One engine inoperative (OEI) Transient : 90%. Minimum : 99%. Continuous operation : 99 to 101%.
Page 510 UNMAINTAINED COPY RFM A109E APPENDIX 13 Takeoff and landing (below 60 KIAS and 1000 ft AGL) : 101 to 102%. NOTE During an instrumental approach procedure the use of 102% NR is allowed up to 120 KIAS. Maximum : 102%.
Page 511 UNMAINTAINED COPY RFM A109E APPENDIX 13 NOTE Transient must not be used intentionally. Single engine transient may be used only in case of real emergency, when one engine becomes inoperative due to an actual malfunction. INSTRUMENT MARKINGS ELECTRONIC DISPLAY UNIT FORMATS Figure 1-1.
Page 512 UNMAINTAINED COPY RFM A109E APPENDIX 13 Figure 1-2. EDU 1 - TORQUE (OEI). Page 6 of 12 R.A.I. Approved Rev. 11...
Page 513 UNMAINTAINED COPY RFM A109E APPENDIX 13 Figura 1-3. EDU 1 - ROTOR POWER TURBINE SPEED (OEI). R.A.I. Approved Page 7 of 12...
Page 514 UNMAINTAINED COPY RFM A109E APPENDIX 13 SECTION 2 - NORMAL PROCEDURES No change. SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES EMERGENCY PROCEDURE FOR LIMIT OVERRIDE PUSHBUTTON OPERATION The engine is protected from limits exceeding through the engine limit governing. The engine limit governing is responsible for limiting measured engine parameters through the control loop selection logic.
Page 515 UNMAINTAINED COPY RFM A109E APPENDIX 13 EDU 1 : OEI transient torque marking (red triangle) displayed, if in OEI mode. Collective : Apply as necessary paying at- tention since the engine is no more protected from limits overcoming. The operation of LIM OVRD pushbutton must be noted on the helicopter log-book.
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Page 517 UNMAINTAINED COPY RFM A109E APPENDIX 13 POWER ASSURANCE CHECK HOVER * HEATER / E.C.S. OFF. * TEST ENGINE MODE SWITCH - FLIGHT. * GENERATOR LOAD TO MINIMUM (< 28 A). * OTHER ENGINE MODE SWITCH - IDLE. * SET NR TO 102%.
Page 518 UNMAINTAINED COPY RFM A109E APPENDIX 13 POWER ASSURANCE CHECK IN FLIGHT * HEATER / E.C.S. OFF. * ESTABILISH LEVEL FLIGHT ABOVE 1000 ft. AGL. * TEST ENGINE - SET ENG. GOV. SWITCH TO MANUAL * GENERATOR LOAD TO MINIMUM (< 28 A).
Page 519 UNMAINTAINED COPY RFM A109E APPENDIX 14 R.A.I. Approval Letter 98/809/MAE dated 19-2-1998 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 520 UNMAINTAINED COPY RFM A109E APPENDIX 14 TABLE OF CONTENTS Page PART I - R.A.I. APPROVED SECTION 1 - LIMITATIONS 3 of 4 SECTION 2 - NORMAL PROCEDURES 3 of 4 SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES ELECTRICAL POWER FAILURE...
Page 521 UNMAINTAINED COPY RFM A109E APPENDIX 14 SECTION 1 - LIMITATIONS No change. SECTION 2 - NORMAL PROCEDURES No change. SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES ELECTRICAL POWER FAILURE Failure of both generators Gen 1 and 2 : Reset, then ON. If both genera- tors are inoperative continue flight on battery.
Page 522 UNMAINTAINED COPY RFM A109E APPENDIX 14 NOTE Due to automatic load shedding, the following electrical loads will be supplied by the battery: – EDU 1, EDU 2, DAU channel A and B – Inverter 1 – Fuel pumps – Fuel valves –...
Page 523 UNMAINTAINED COPY RFM A109E APPENDIX 15 R.A.I. Approval Letter 98/1385/MAE dated 20-3-98 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 524 UNMAINTAINED COPY RFM A109E APPENDIX 15 TABLE OF CONTENTS Page PART I - E.A.S.A. APPROVED SECTION 1 - LIMITATIONS TYPE OF OPERATION 4 of 16 PLACARDS 4 of 16 SECTION 2 - NORMAL PROCEDURES PREFLIGHT CHECKS 4 of 16 PILOT’S DAILY PREFLIGHT CHECK...
Page 525 UNMAINTAINED COPY RFM A109E APPENDIX 15 Table of Contents (Cont.d) PART II - MANUFACTURER’S DATA SECTION 7 - SYSTEMS DESCRIPTION NAVIGATION SYSTEM 14 of 16 DME OPERATION 14 of 16 FLIGHT DIRECTOR OPERATION 15 of 16 EFIS COMPOSITE MODE 15 of 16 LIST OF ILLUSTRATIONS Figure 7-1.
Page 526 UNMAINTAINED COPY RFM A109E APPENDIX 15 SECTION 1 - LIMITATIONS TYPE OF OPERATION (EFIS P/N 109-0900-57-101 only) Operation is permitted under VFR flight only. PLACARDS (EFIS P/N 109-0900-57-101 only) EFIS OPERATION IN VFR ONLY In clear view of the pilot...
Page 527 UNMAINTAINED COPY RFM A109E APPENDIX 15 NORMAL ENGINE START ENGINE 2 START After RAD-MSTR switch activation: EFIS displays : Adjust brightness as necessary. QUICK ENGINE START After RAD-MSTR switch activation: EFIS displays : Adjust brightness as necessary. SYSTEMS CHECK EADI instrument (Pilot side): ATT flag : Out of view.
Page 528 UNMAINTAINED COPY RFM A109E APPENDIX 15 RA flag on EADI : Out of view. : Set 200 ft. RA TST button : Press and hold. DH caption : In view. Indication : 100 ft (±5 ft). RA TST button : Release.
Page 529 UNMAINTAINED COPY RFM A109E APPENDIX 15 IN FLIGHT FLIGHT DIRECTOR OPERATION (if installed) VOR (or GPS) coupled to NAV mode CAUTION When NAV mode on FD control panel is in CAP condition and a change of navigation source is carried out with the NAV key on...
Page 530 UNMAINTAINED COPY RFM A109E APPENDIX 15 SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES WARNING SYSTEM CAUTION MESSAGES (YELLOW) EDU message Fault condition Corrective action VG 1 Gyro not erected, loss of Check breaker. power to gyro. Refer to stand-by atti- ATT flag displayed on tude indicator.
Page 531 UNMAINTAINED COPY RFM A109E APPENDIX 15 SYSTEM FAILURES EFIS FAILURES The EFIS failures can affect separately or simultaneously each of four displays of the system and performing as EADI and EHSI indicators. The cause can be an internal system failure or a connection system failure.
Page 532 UNMAINTAINED COPY RFM A109E APPENDIX 15 On both displays the message ATT 2 (or ATT 1 if the remaining EADI is the co-pilot’s one) will appear. Proceed with flight in the new system configuration. Failure of both EADIs In the event of a failure of both EADIs, the two EHSIs automatically revert to composite mode and a red MON (″monitoring″) message appears at the same...
Page 533 UNMAINTAINED COPY RFM A109E APPENDIX 15 EADI FAILURES Radio altimeter failure In the event of Radio Altimeter failure, a RA red flag replaces the numerical value; the rising runway and the DH indication (if present) disappear from the screen. Aural messages ″ONE FIFTY FEET ″ and ″LANDING GEAR″ are inhibited while LANDING GEAR caution remains displayed on EDU.
Page 534 UNMAINTAINED COPY RFM A109E APPENDIX 15 EFIS FAULT MESSAGES (Messages replacing the instrument indications). EADI message Fault condition Corrective action Gyro not erected, VG 1 Check breaker. Refer to (2) caution message dis- stand-by attitude indica- played on EDU. tor.
Page 535 UNMAINTAINED COPY RFM A109E APPENDIX 15 EADI message Fault condition Corrective action Pitch and roll attitudes Compare the EADIs data discrepancy between the with the ADI stand-by. gyro data. Select the ATT REV pushbutton on the EADI providing misleading data.
Page 536 UNMAINTAINED COPY RFM A109E APPENDIX 15 SECTION 7 - SYSTEMS DESCRIPTION NAVIGATION SYSTEM DME OPERATION General The following table shows the various combinations of possible DME data visualization on EHSI, depending on the selected navigation source. NAV SELECTION PLT IN CMD...
Page 537 UNMAINTAINED COPY RFM A109E APPENDIX 15 FLIGHT DIRECTOR OPERATION When NAV, VOR APR, ILS or BC mode is active in CAP mode temporarily deselect the mode before performing any course change. Set the new course on the EHSI and intercept heading, then re-arm for capture.
Page 538 UNMAINTAINED COPY RFM A109E APPENDIX 15 Figure 7-1. EFIS Fan (if installed) - Controls and indicators. Page 16 of 16 Rev. 42...
Page 539 UNMAINTAINED COPY RFM A109E APPENDIX 16 R.A.I. Approval Letter 98/1385/MAE dated 20-03-98 The information contained herein supplements the information of the basic Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Flight Manual.
Page 540 UNMAINTAINED COPY RFM A109E APPENDIX 16 TABLE OF CONTENTS Page PART I - R.A.I. APPROVED SECTION 1 - LIMITATIONS TYPE OF OPERATION 3 of 8 PLACARDS 3 of 8 SECTION 2 - NORMAL PROCEDURES SYSTEMS CHECK 3 of 8 IN FLIGHT...
Page 541 UNMAINTAINED COPY RFM A109E APPENDIX 16 SECTION 1 - LIMITATIONS TYPE OF OPERATION The GPS Garmin 165 system can be used in VFR conditions only, for use as a supplemental navigation system. PLACARDS GPS SYSTEM. USE ONLY DURING VFR OPERATION...
Page 542 UNMAINTAINED COPY RFM A109E APPENDIX 16 All GPS data are also displayed in white. NOTE When GPS is selected on the EHSI 74B as navigation source, the navigation data coming from VOR 2 receiver are automatically available on pilot HSI (stand-by).
Page 543 UNMAINTAINED COPY RFM A109E APPENDIX 16 IN FLIGHT GPS coupled to EFIS or EHSI 74B system (if installed) CAUTION When one of F/D navigation modes (NAV-VOR APP-ILS-BC) is in CAP condition and a change of navigation source is carried out on the EHSI, press the relevant button on the F/D mode selector to deselect the mode.
Page 544 UNMAINTAINED COPY RFM A109E APPENDIX 16 CAUTION Flying coupled with F/D can result in a 2 NM overshoot if DTK for next leg requires a heading change greater than 90 deg. In order to prevent the overshoot, the pilot can deselect the NAV mode as soon as the GPS displays the message ″Next dtk xxx°″,...
Page 545 UNMAINTAINED COPY RFM A109E APPENDIX 16 Deselect NAV mode and proceed in HDG mode or in NAV mode with F/D coupled to a VOR receiver (if available). During this time, the GPS system will continue to navigate and track satellites but not display information on the unit’s display until a key is pressed or a knob is turned.
Page 546 UNMAINTAINED COPY RFM A109E APPENDIX 16 SECTION 7 - SYSTEMS DESCRIPTION For GPS automatic navigation operation (Flight Plan mode) perform the following procedure: — On the pilot EHSI select the GPS receiver as navigation source. — Select on GPS receiver the correct CDI scale (1 NM full scale).
Page 547 UNMAINTAINED COPY RFM A109E APPENDIX 17 R.A.I. Approval Letter 98/2201/MAE dated 8 May 1998 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this Supplement, consult the basic Rotorcraft Flight Manual.
Page 548 UNMAINTAINED COPY RFM A109E APPENDIX 17 TABLE OF CONTENTS Page SECTION 1 - LIMITATIONS TYPE OF OPERATION 3 of 10 AIRSPEED LIMITATIONS (IAS) 3 of 10 CENTER OF GRAVITY LIMITATIONS 3 of 10 PLACARDS 4 of 10 SECTION 2 - NORMAL PROCEDURES...
Page 549 UNMAINTAINED COPY RFM A109E APPENDIX 17 SECTION 1 - LIMITATIONS TYPE OF OPERATION Activation of Nightsun Searchlight is prohibited in IFR condition. AIRSPEED LIMITATIONS (KIAS) Nightsun searchlight configured without NVG filter Maximum airspeed (V : 140 KIAS Nightsun searchlight configured with NVG filter...
Page 550 UNMAINTAINED COPY RFM A109E APPENDIX 17 PLACARDS Nightsun searchlight configured without NVG filter CAUTION DO NOT USE SX-16 SUN LT BELOW 50 FT AGL OR FOG CONDITIONS. MONITOR LOADMETER WHEN USING SX-16 SUN LT. MAXIMUM AIRSPEED WITH SX-16 SUN LT 140 KTS IAS.
Page 551 UNMAINTAINED COPY RFM A109E APPENDIX 17 SECTION 2 - NORMAL PROCEDURES PRE-FLIGHT CHECKS PILOT’S DAILY PRE-FLIGHT CHECK (First flight of the day) AREA N°1 (Helicopter nose) Nightsun searchlight : Security and wiring properly connected. Lens and NVG filter, if in- stalled, for cleanliness.
Page 552 UNMAINTAINED COPY RFM A109E APPENDIX 17 IN FLIGHT NOTE When operating Nightsun Searchlight, magnetic compass indica- tion is not reliable. NIGHTSUN SEARCHLIGHT OPERATING PROCEDURE CAUTION Do not operate Nightsun Searchlight after a generator failure. IFCO switch on searchlight remote control panel (if NVG filter is installed) : As desired.
Page 553 UNMAINTAINED COPY RFM A109E APPENDIX 17 CAUTION Do not direct the beam towards other aircraft or vehicles to prevent temporary blinding effect, if NVG filter is not installed or not utilized. NVG FILTER OPERATION (if installed) CAUTION Do not move the filter when the searchlight is on to avoid glare to the pilot.
Page 554 UNMAINTAINED COPY RFM A109E APPENDIX 17 SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES SYSTEM FAILURES ELECTRICAL POWER FAILURE Failure of a generator OFF-ON-START switch on search- light remote control panel : OFF. Refer paragraph ″FAILURE OF A GENERA- TOR″ of basic Rotorcraft Flight Manual.
Page 555 UNMAINTAINED COPY RFM A109E APPENDIX 17 SECTION 7 - SYSTEM DESCRIPTION The Nightsun Searchlight SX-16 is provided for enhancing the searchlight capabilities during night or poor visibility conditions. The searchlight contains an air cooled, high intensity xenon arc lamp which start rapidly and can be operated continuosly or may be stopped and restarted as dictated by opera- tional requirements.
Page 556 UNMAINTAINED COPY RFM A109E APPENDIX 17 1. SUN LT circuit breaker 2. Remote control panel, standard version 3. Remote control panel, IFCO version Figure 7-1. Nightsun searchlight control panel. Page 10 of 10 Rev. 33...
Page 557 UNMAINTAINED COPY RFM A109E APPENDIX 18 R.A.I. Approval Letter 98/2201/MAE dated 8 May 1998 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 558 UNMAINTAINED COPY RFM A109E APPENDIX 18 TABLE OF CONTENTS Page PART I - R.A.I. APPROVED SECTION 1 - LIMITATIONS CENTER OF GRAVITY LIMITATIONS 3 of 5 SECTION 2 - NORMAL PROCEDURES PILOT’S DAILY PREFLIGHT CHECK 3 of 5 PILOT’S PREFLIGHT CHECK...
Page 559 UNMAINTAINED COPY RFM A109E APPENDIX 18 SECTION 1 - LIMITATIONS CENTER OF GRAVITY LIMITATIONS After snow skid installation the new empty weight and C.G. location must be determined. SECTION 2 - NORMAL PROCEDURES PILOT’S DAILY PREFLIGHT CHECK (First flight of the day) AREA N.1 (Helicopter Nose)
Page 560 UNMAINTAINED COPY RFM A109E APPENDIX 18 AREA N°6 (Fuselage - lh side) Snow skid, steel cords, bungee cords and relative supports : Condition and security. NOTE Special attention shall be paid to any permanent deformation to the cable supports (sheet metal parts) on the skids, especially to any sheet metal layer separation in the cable attachment area.
Page 561 UNMAINTAINED COPY RFM A109E APPENDIX 18 SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES If any malfunction of the skids occurs in flight, reduce the speed and land as soon as practical. SECTION 4 - PERFORMANCE DATA No change. R.A.I. Approved...
Page 562 UNMAINTAINED COPY...
Page 563 UNMAINTAINED COPY RFM A109E APPENDIX 19 R.A.I. Approval Letter 98/2201/MAE dated 8-5-1998 The information contained herein supplements the information of the basic Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Flight Manual.
Page 564 UNMAINTAINED COPY RFM A109E APPENDIX 19 TABLE OF CONTENTS Page PART I - R.A.I. APPROVED SECTION 1 - LIMITATIONS TYPE OF OPERATION 3 of 9 STANDARD CONFIGURATION (P/N 109-0811-53) 3 of 9 B-RNAV CONFIGURATION (P/N 109-0822-91) 3 of 9 PLACARDS...
Page 565 UNMAINTAINED COPY RFM A109E APPENDIX 19 SECTION 1 - LIMITATIONS TYPE OF OPERATION STANDARD CONFIGURATION (P/N 109-0811-53) The GPS Trimble 2101 system can be used in VFR conditions only, for use as a supplemental navigation system. The GPS system can not be used in the ″DR″...
Page 566 UNMAINTAINED COPY RFM A109E APPENDIX 19 With GPS Trimble 2101 system in B-RNAV configuration P/N 109-0822-91 only. GPS SYSTEM MUST NOT BE USED FOR APPROACHES In clear view of pilot SECTION 2 - NORMAL PROCEDURES CAUTION The pertinent Trimble GPS 2101 Pilot’s Guide must be available on board: −...
Page 567 UNMAINTAINED COPY RFM A109E APPENDIX 19 GPS coupled with EFIS system (if installed) Select the GPS on the EHSI through ″N″ button. The GPS selection is indicated by a blue GPS legend on the left side of EHSI. All GPS data are also displayed in blue.
Page 568 UNMAINTAINED COPY RFM A109E APPENDIX 19 GPS coupled to EFIS or EHSI 74B system (if installed) CAUTION When one of F/D navigation modes (NAV-VOR APP-ILS-BC) is in CAP condition press the relevant button on the F/D mode selector to deselect the mode before any change of navigation source is carried out on the EHSI.
Page 569 UNMAINTAINED COPY RFM A109E APPENDIX 19 CAUTION Flying with the F/D ″coupled″ can result in a 2 NM overshoot if DTK for next leg requires a heading change greater than 90 deg. In order to prevent the overshoot, the pilot can deselect the NAV mode as soon as the GPS displays the message ″TURN TO...
Page 570 UNMAINTAINED COPY RFM A109E APPENDIX 19 ADS failure (IFR and B-RNAV configuration) In the event of ″PRESSURE ALTITUDE DATA INVALID″ message, press AUX key and check that GPS mode is at least 3D and the RAIM is available in GPS status page in the event of NO RAIM status, the use of GPS for enroute navigation is still approved only if a cross-check with VOR/DME systems is possible.
Page 571 UNMAINTAINED COPY RFM A109E APPENDIX 19 SECTION 7 - SYSTEMS DESCRIPTION For GPS automatic navigation operation perform the following procedure: — On the pilot EHSI select the GPS receiver as navigation source. — Create a route by entering two or more waypoints (max. 40).
Page 572 UNMAINTAINED COPY...
Page 573 UNMAINTAINED COPY RFM A109E APPENDIX 20 R.A.I. Approval Letter 98/5857/MAE dated 26 November 1998 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 574: Figure 1-1. Airspeed Limitations
UNMAINTAINED COPY RFM A109E APPENDIX 20 TABLE OF CONTENTS Page PART I - R.A.I. APPROVED SECTION 1 - LIMITATIONS AIRSPEED LIMITATIONS 3 of 4 CENTER OF GRAVITY LIMITATIONS 3 of 4 SECTION 2 - NORMAL PROCEDURES PREFLIGHT CHECKS 3 of 4 PILOT’S DAILY PREFLIGHT CHECK...
Page 575 UNMAINTAINED COPY RFM A109E APPENDIX 20 SECTION 1 - LIMITATIONS AIRSPEED LIMITATIONS (IAS) NOTE Comply with airspeed limitations with landing gear extended. CENTER OF GRAVITY LIMITATIONS After slump protection pads installation the new empty weight and C.G. location must be determined.
Page 576 UNMAINTAINED COPY RFM A109E APPENDIX 20 NOTE Special attention shall be paid to any permanent deformation to the cable supports (sheet metal parts) on the pad, especially to any sheet metal layer separation in the cable attachment area. AREA N°6 (Fuselage - lh side)
Page 577 UNMAINTAINED COPY RFM A109E APPENDIX 21 R.A.I. Approval Letter 98/6164/MAE dated 17 December 1998 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 578: Figure 1-2. Airspeed Limitations
UNMAINTAINED COPY RFM A109E APPENDIX 21 TABLE OF CONTENTS Page PART I - R.A.I. APPROVED SECTION 1 - LIMITATIONS TYPE OF OPERATION 3 of 12 REQUIRED EQUIPMENT 3 of 12 AIRSPEED LIMITATIONS (IAS) 3 of 12 CENTER OF GRAVITY LIMITATIONS...
Page 579 UNMAINTAINED COPY RFM A109E APPENDIX 21 SECTION 1 - LIMITATIONS TYPE OF OPERATION The emergency floats installation is approved for assistance during emergency ditching. The takeoff after ditching is prohibited. In the event of unintended inflation, a landing must be accomplished at first suitable location (not on water) and system deflated and stowed or fully removed prior to further flight.
Page 580 UNMAINTAINED COPY RFM A109E APPENDIX 21 NOTE Survival equipment installation not compatible with drawer installation P/N 109-0329-21-101 or P/N 109-0709-61-101. AIRSPEED LIMITATIONS (IAS) Stowed floats V : No change. Maximum speed for float inflation : 80 Kts. Inflated floats V : 80 Kts.
Page 581 UNMAINTAINED COPY RFM A109E APPENDIX 21 Near each cylinder pressure gauge. E.N.A.C. Approved Page 5 of 12...
Page 582 UNMAINTAINED COPY RFM A109E APPENDIX 21 SECTION 2 - NORMAL PROCEDURES PREFLIGHT CHECKS PILOT’S DAILY PREFLIGHT CHECK (First flight of the day) Area N° 2 (Fuselage - rh side) Cylinder pressure : Check pressure gauge reading is in accordance with diagram on placard located near gauges.
Page 583 UNMAINTAINED COPY RFM A109E APPENDIX 21 PILOT’S PREFLIGHT CHECK (Every flight) Cylinder pressure : Check pressure gauge reading is in accordance with diagram on placard located near gauges. Electric harness and connector : Visually check for condition and security. Floats : Stowed.
Page 584 UNMAINTAINED COPY RFM A109E APPENDIX 21 NOTE Do not arm the emergency float system when the takeoff is not carried out over water. IN FLIGHT It is allowed to arm the emergency float system only when flying over water below 3000 ft (915 m) AGL and at an airspeed less than 80 Kts IAS.
Page 585 UNMAINTAINED COPY RFM A109E APPENDIX 21 EMER FLOATS circuit breakers : Out. SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES CAUTION MESSAGES (YELLOW) EDU message Fault condition Corrective action FLOATS ARMED Emergency float Continue flight taking system armed. care that the emergency float system is operative.
Page 586 UNMAINTAINED COPY RFM A109E APPENDIX 21 CAUTION The float inflation control system is entirely electrical. Thus, if the helicopter is operating with the battery as sole source of power due to generators failure, it is necessary to inflate the floats prior to complete battery discharge.
Page 587 UNMAINTAINED COPY RFM A109E APPENDIX 21 ENG 1 and 2 MODE switches : OFF. Engine power levers : OFF (full aft). ENG 1 and 2 FUEL switches : OFF. Fuel pumps 1 and 2 : OFF. GEN 1 and 2 switches : OFF.
Page 588 UNMAINTAINED COPY RFM A109E APPENDIX 21 NOTE Representative model tests have indicated that sea states 4 condition with height/length ratios of less than 1:12.5 do not cause the helicopter to capsize. LANDING AFTER AN UNINTENDED INFLATION In event of an unintended inflation in flight a landing must be accomplished at the first suitable location, definitely not on water.
Page 589 UNMAINTAINED COPY RFM A109E APPENDIX 22 R.A.I. Approval Letter 99/1254/MAE dated 1 April 1999 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 590 UNMAINTAINED COPY RFM A109E APPENDIX 22 TABLE OF CONTENTS Page PART I - R.A.I. APPROVED SECTION 1 - LIMITATIONS CENTER OF GRAVITY LIMITATIONS 3 of 6 SECTION 2 - NORMAL PROCEDURES PILOT’S DAILY PREFLIGHT CHECK 3 of 6 PILOT’S PREFLIGHT CHECK...
Page 591 UNMAINTAINED COPY RFM A109E APPENDIX 22 SECTION 1 - LIMITATIONS CENTER OF GRAVITY LIMITATIONS After the wire strike protection system installation the new empty weight and CG location must be determined. SECTION 2 - NORMAL PROCEDURES PILOT’S DAILY PREFLIGHT CHECK (First flight of the day) AREA N°...
Page 592 UNMAINTAINED COPY RFM A109E APPENDIX 22 AREA N° 2 (Fuselage - rh side) Wiper deflectors and window strut bumper : Condition and security. Upper cutter : Condition and security. AREA N° 6 (Fuselage - lh side) Upper cutter : Condition and security.
Page 593 UNMAINTAINED COPY RFM A109E APPENDIX 22 TAKE-OFF CAUTION Excessive nose down attitude during transition to forward flight may cause the lower cutter deflector to hit the ground. APPROACH AND LANDING NOTE Landing on even surfaces it is recommended when the wire strike protection system is installed.
Page 594 UNMAINTAINED COPY RFM A109E APPENDIX 22 SECTION 7 - SYSTEM DESCRIPTION WIRE STRIKE PROTECTION SYSTEM The wire strike protection system is designed to provide a measure of protection in the event of an inadvertent impact against horizontally strung wires. The wire cutting is obtained by means of the converging upper and lower deflectors using the kinetic energy of the flying helicopter.
Page 595 UNMAINTAINED COPY RFM A109E APPENDIX 23 R.A.I. Approval Letter 99/1608/MAE dated 23-4-1999 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 596 UNMAINTAINED COPY RFM A109E APPENDIX 23 TABLE OF CONTENTS Page INTRODUCTION 4 of 30 PART I - R.A.I. APPROVED SECTION 1 - LIMITATIONS TRAINING PROCEDURE OPERATION 5 of 30 REQUIRED EQUIPMENT 5 of 30 FLIGHT LIMITATIONS 5 of 30 FLIGHT CREW...
Page 597 UNMAINTAINED COPY RFM A109E APPENDIX 23 LIST OF ILLUSTRATIONS Page Figure I-1. OEI TRAINING switch. 4 of 30 Figure 1-1. Maximum takeoff and landing weight for alti- tude and temperature (WAT for training on clear area). 6 of 30 Figure 1-2. Maximum takeoff and landing weight for alti- tude and temperature (WAT for training on short field).
Page 598 UNMAINTAINED COPY RFM A109E APPENDIX 23 INTRODUCTION DESCRIPTION The TRAINING mode can be selected through the specific switch (figure I-1) placed on the engine control panel. This is a magnetically latched three position switch. In normal flight condition the switch must be set to neutral position (central).
Page 599 UNMAINTAINED COPY RFM A109E APPENDIX 23 SECTION 1 - LIMITATIONS TRAINING PROCEDURE OPERATION The training activity can be carried out, by day and by night, on clear area, on short field and on ground level helipad. The night-exercise has to be practised only after having gained a good proficiency during the day.
Page 600 UNMAINTAINED COPY RFM A109E APPENDIX 23 WEIGHT-ALTITUDE-TEMPERATURE LIMITATIONS FOR TAKE OFF AND LANDING CLEAR AREA (TRAINING) HEATER OR E.C.S. OFF V2 30 kts IAS GROSS WEIGHT - POUNDS x 100 Hd LIMIT 8000 ft NOTE: PATH 2 PROFILE CAN NOT BE CARRIED OUT IN SHADED AREA OAT - ˚C...
Page 601 UNMAINTAINED COPY RFM A109E APPENDIX 23 WEIGHT-ALTITUDE-TEMPERATURE LIMITATIONS FOR TAKE OFF AND LANDING SHORT FIELD (100 m) (TRAINING) V2 30 kts IAS HEATER OR E.C.S. OFF GROSS WEIGHT - POUNDS x 100 Hd LIMIT 8000 ft NOTE: PATH 2 PROFILE CAN NOT BE CARRIED OUT IN SHADED AREA OAT - ˚C...
Page 602 UNMAINTAINED COPY RFM A109E APPENDIX 23 WEIGHT-ALTITUDE-TEMPERATURE LIMITATIONS FOR TAKEOFF AND LANDING GROUND BASED HELIPAD 15 m x 15 m (TRAINING) V2 30 kts IAS HEATER OR E.C.S. OFF GROSS WEIGHT - POUNDS x 100 Hd LIMIT 8000 ft NOTE:...
Page 603 UNMAINTAINED COPY RFM A109E APPENDIX 23 POWER PLANT LIMITATIONS GAS GENERATOR (N1) RPM Training (OEI) Continuous operation : 50 to 97.4%. Maximum continuous : 97.4%. 2.5 min range : 97.4 to 98.7%. Maximum : 98.7%. POWER TURBINE (N2) RPM Training (OEI) Minimum : 90%.
Page 604 UNMAINTAINED COPY RFM A109E APPENDIX 23 TRANSMISSION LIMITATIONS TORQUE (TRQ%) Training (OEI) Maximum continuous : 102%. 2.5 min : 122%. NOTE The reduced OEI governing limits for training prevents engine and transmission system overstress and leaves the trainee a safety margin.
Page 605 UNMAINTAINED COPY RFM A109E APPENDIX 23 Figure 1-4. EDU 1 - OEI TRAINING mode. NOTE The OEI TRAINING mode can be selected by the pilot at any time but it is automatically reverted to CRUISE mode (either OEI or AEO, as applicable) if a single or dual engine out condition occurs or if the ECUs suppress the training authorization.
Page 606 UNMAINTAINED COPY RFM A109E APPENDIX 23 INTENTIONALLY BLANK Page 12 of 30 R.A.I. Approved...
Page 607 UNMAINTAINED COPY RFM A109E APPENDIX 23 Figure 1-5. EDU 1 - GAS GENERATOR SPEED (OEI). R.A.I. Approved Page 13 of 30...
Page 608 UNMAINTAINED COPY RFM A109E APPENDIX 23 Figure 1-6. EDU 1 - TURBINE OUTLET TEMPERATURE (OEI). Page 14 of 30 R.A.I. Approved...
Page 609 UNMAINTAINED COPY RFM A109E APPENDIX 23 Figure 1-7. EDU 1 - TORQUE (OEI). R.A.I. Approved Page 15 of 30...
Page 610 UNMAINTAINED COPY RFM A109E APPENDIX 23 Figure 1-8. EDU 1 - ROTOR/POWER TURBINE SPEED (OEI). Page 16 of 30 R.A.I. Approved...
Page 611 UNMAINTAINED COPY RFM A109E APPENDIX 23 SECTION 2 - NORMAL PROCEDURES TRAINING PROCEDURES Perform the training activity strictly following the same profiles presented in Section 2 and in Section 3 of Appendix 12. Training procedure can be considered completed at the end of flight path 1 (upon reaching a height of 200 ft above the starting point).
Page 612 UNMAINTAINED COPY RFM A109E APPENDIX 23 SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES EMERGENCY DURING TRAINING At any time during the drill the TRAINING mode can be aborted, automati- cally by the electronic engine control or voluntarily by the pilots in case of critical situations.
Page 613 UNMAINTAINED COPY RFM A109E APPENDIX 23 In TRAINING mode the engine limit governing is set not to overcome the following limits: Torque OEI 122% 863°C 98.7% Once the TRAINING mode is aborted, both engines resume running matched at the pilot requested power and the EDU 1 automatically reverts to CRUISE AEO mode.
Page 614 UNMAINTAINED COPY RFM A109E APPENDIX 23 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER (TRAINING) ROTOR: 102 % V2 30 kts IAS ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2050 kg ( 4519 lb ) OAT - ˚C...
Page 615 UNMAINTAINED COPY RFM A109E APPENDIX 23 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER (TRAINING) V2 30 kts IAS ROTOR: 102 % ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2250 kg ( 4960 lb ) OAT - ˚C...
Page 616 UNMAINTAINED COPY RFM A109E APPENDIX 23 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER (TRAINING) V2 30 kts IAS ROTOR: 102 % ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2450 kg ( 5401 lb ) OAT - ˚C...
Page 617 UNMAINTAINED COPY RFM A109E APPENDIX 23 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER (TRAINING) ROTOR: 102 % V2 30 kts IAS ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2650 kg ( 5842 lb ) OAT - ˚C...
Page 618 UNMAINTAINED COPY RFM A109E APPENDIX 23 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER (TRAINING) V2 30 kts IAS ROTOR: 102 % ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2850 kg ( 6283 lb ) OAT - ˚C...
Page 619 UNMAINTAINED COPY RFM A109E APPENDIX 23 TAKEOFF FLIGHT PATH 2 MEAN HEIGHT GAINED IN 30 M HORIZONTAL DISTANCE The mean height gained in 30 m of horizontal distance travelled during an OEI climb at V after takeoff in training is shown in figures 4-6 thru 4-10 for various altitudes, temperatures, weights and headwind components.
Page 620 UNMAINTAINED COPY RFM A109E APPENDIX 23 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER (TRAINING) ROTOR: 100 % Vy 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2050 kg ( 4519 lb ) OAT - ˚C...
Page 621 UNMAINTAINED COPY RFM A109E APPENDIX 23 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER (TRAINING) Vy 60 kts IAS ROTOR: 100 % ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2250 kg ( 4960 lb ) OAT - ˚C...
Page 622 UNMAINTAINED COPY RFM A109E APPENDIX 23 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER (TRAINING) Vy 60 kts IAS ROTOR: 100 % ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2450 kg ( 5401 lb ) OAT - ˚C...
Page 623 UNMAINTAINED COPY RFM A109E APPENDIX 23 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER (TRAINING) ROTOR: 100 % Vy 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2650 kg ( 5842 lb ) OAT - ˚C...
Page 624 UNMAINTAINED COPY RFM A109E APPENDIX 23 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER (TRAINING) Vy 60 kts IAS ROTOR: 100 % ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2850 kg ( 6283 lb ) OAT - ˚C...
Page 625 UNMAINTAINED COPY RFM A109E APPENDIX 24 E.N.A.C. Approval Letter 99/2951/MAE dated 30 July 1999 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 626 UNMAINTAINED COPY RFM A109E APPENDIX 24 The hoist system is provided with a cable foul protection system that stops the hoist if the cable is not properly stowed on the drum and activates a HOIST CABLE LKD caution message on EDU 1.
Page 627 UNMAINTAINED COPY RFM A109E APPENDIX 24 TABLE OF CONTENTS Page PART I - E.N.A.C. APPROVED SECTION 1 - LIMITATIONS TYPE OF OPERATION 5 of 28 REQUIRED EQUIPMENT 5 of 28 FLIGHT CREW 5 of 28 AIRSPEED LIMITATIONS (IAS) 5 of 28...
Page 628: Figure 1-3 (Sheet 1 Of 2). Longitudinal Cg Limits (Metric)
UNMAINTAINED COPY RFM A109E APPENDIX 24 LIST OF ILLUSTRATIONS Page Figure 1-1. Hoist station and butt line. 7 of 28 Figure 1-2. Hoist loading chart (examples of weight layout). 8 of 28 Figure 1-3 (sheet 1 of 2). Longitudinal CG limits (Metric).
Page 629 UNMAINTAINED COPY RFM A109E APPENDIX 24 SECTION 1 - LIMITATIONS TYPE OF OPERATION Hoist operation is approved in VFR conditions with ground visual contact. Hoist operation is approved also with the right passenger door removed. Normal helicopter operation is approved, with the hoist installed, providing the hoist is not used and the hoist electrical system is deactivated.
Page 630 UNMAINTAINED COPY RFM A109E APPENDIX 24 CAUTION Airspeed with external load is limited by controllability. Caution should be exercised when carrying an external load as the handling characteristics may be affected by the size, weight and shape of the load.
Page 631 UNMAINTAINED COPY RFM A109E APPENDIX 24 CENTER OF GRAVITY LIMITATIONS After hoist installation the new empty weight and CG location must be determined. See figure 1-3 for longitudinal CG limits and figure 1-4 for lateral CG limits. For gross weight greater than 2850 kg (6283 lb), see figure 1-5 for longitudinal CG limits and 1-6 for lateral CG limits.
Page 632 UNMAINTAINED COPY RFM A109E APPENDIX 24 Figure 1-2. Hoist loading chart (examples of weight layout). Page 8 of 28 E.N.A.C. Approved...
Page 633 UNMAINTAINED COPY RFM A109E APPENDIX 24 NOTE Longitudinal station ″0″ is 1835 mm forward of the front jack point. NOTE The diagram shaded area is applicable only during hoist operation. Figure 1-3 (sheet 1 of 2). Longitudinal CG limits (Metric).
Page 634 UNMAINTAINED COPY RFM A109E APPENDIX 24 NOTE Longitudinal station ″0″ is 72.2 in. forward of the front jack point. NOTE The diagram shaded area is applicable only during hoist operation. Figure 1-3 (sheet 2 of 2). Longitudinal CG limits (English).
Page 635: Figure 1-4 (Sheet 1 Of 2). Lateral Cg Limits (Metric)
UNMAINTAINED COPY RFM A109E APPENDIX 24 NOTE The lateral station ″0″ is 450 mm inboard from each main jack point and coincides with the helicopter longitudinal plane of symmetry. NOTE The diagram shaded area is applicable only during hoist operation.
Page 636: Figure 1-4 (Sheet 2 Of 2). Lateral Cg Limits (English)
UNMAINTAINED COPY RFM A109E APPENDIX 24 NOTE The lateral station ″0″ is 17.7 in. inboard from each main jack point and coincides with the helicopter longitudinal plane of symmetry. NOTE The diagram shaded area is applicable only during hoist operation.
Page 637 UNMAINTAINED COPY RFM A109E APPENDIX 24 NOTE Longitudinal station ″0″ is 1835 mm forward of the front jack point. NOTE The diagram shaded area is applicable only during hoist operation. Figure 1-5 (sheet 1 of 2). Longitudinal CG limit (metric).
Page 638 UNMAINTAINED COPY RFM A109E APPENDIX 24 NOTE Longitudinal station ″0″ is 72.2 in. forward of the front jack point. NOTE The diagram shaded area is applicable only during hoist operation. Figure 1-5 (sheet 2 of 2). Longitudinal CG limit (english).
Page 639 UNMAINTAINED COPY RFM A109E APPENDIX 24 NOTE The lateral station ″0″ is 450 mm inboard from each main jack point and coincides with the helicopter longitudinal plane of symmetry. NOTE The diagram shaded area is applicable only during hoist operation.
Page 640 UNMAINTAINED COPY RFM A109E APPENDIX 24 NOTE The lateral station ″0″ is 17.7 in. inboard from each main jack point and coincides with the helicopter longitudinal plane of symmetry. NOTE The diagram shaded area is applicable only during hoist operation.
Page 641 UNMAINTAINED COPY RFM A109E APPENDIX 24 PLACARDS CAUTION If for any reason the hoist stops, during rising or lowering operation, do not attempt to free it by actuating the controller. Continued operation may cause total cable failure. Land as soon as possible.
Page 642 UNMAINTAINED COPY RFM A109E APPENDIX 24 SECTION 2 - NORMAL PROCEDURES PREFLIGHT CHECKS PILOT’S DAILY PREFLIGHT CHECK (First flight of the day) AREA N° 2 (Fuselage - rh side) Hoist : Condition, security, oil leaks and wiring connected. CAUTION Crushable bumper shall be inspected to insure the bumper is not being crushed.
Page 643 UNMAINTAINED COPY RFM A109E APPENDIX 24 For the following checks connect the d.c. electrical supply: Main HOIST switch : ON. HOIST ON advisory mes- sage on EDU 2 displayed. Hoist cable payout display (both pilot and remote control) : Check built-in-test reading is: 88.8.
Page 644 UNMAINTAINED COPY RFM A109E APPENDIX 24 Full-in limit switch : Check for correct operation. Main HOIST switch : OFF. HOIST ON advisory mes- sage on EDU 2 suppressed. Disconnect the d.c. electrical supply. HOIST PWR circuit breaker : Out. ENGINE PRE-START CHECK CABLE CUT switch (on pilot’s cyclic...
Page 645 UNMAINTAINED COPY RFM A109E APPENDIX 24 NOTE When reeling-in the cable with no load, apply tension with gloved hands to ensure smooth and even wrapping. Approximately 9 kg tension is recommended. Hoist hook : Check lowering. Cable payout display : Check for meter counting.
Page 646 UNMAINTAINED COPY RFM A109E APPENDIX 24 IN FLIGHT HOIST OPERATING PROCEDURE Main HOIST switch : ON. HOIST ON advisory mes- sage on EDU 2 displayed. WARNING Hoist operator shall be secured to helicopter with an approved safety harness during hoist operations.
Page 647 UNMAINTAINED COPY RFM A109E APPENDIX 24 Cable speed (operator only) : As desired by means of the HOIST thumbwheel on remote control. NOTE As hook nears the up or down limits, hoist speed automatically slows. CAUTION During hoist operation the cable trail angle must be kept to minimum.
Page 648 UNMAINTAINED COPY RFM A109E APPENDIX 24 ″latched″ in the 272 kg mode and the MOTOR WRN light will continue to flash until the system is reset by switching the load select switch to the 272 kg mode. The high speed mode (113 kg) should not be selected until the present load is removed from the cable.
Page 649 UNMAINTAINED COPY RFM A109E APPENDIX 24 Main hoist switch : OFF. HOIST ON advisory mes- sage on EDU 2 suppressed. NOTE During hoist operation, the operator shall record any shock load to the cable; in this event, the cable must be replaced prior to the next flight.
Page 650 UNMAINTAINED COPY RFM A109E APPENDIX 24 NOTE If litter is suspended too far below hook. litter can not be loaded into helicopter with hoist hook at up limit. CAUTION A loaded litter can rotate around cable during hoisting. Hoist operator may have to grasp litter sling straps to control rotation as litter approaches landing gear.
Page 651 UNMAINTAINED COPY RFM A109E APPENDIX 24 In the event of a hoist system overload when the load selection switch is set to 113 kg mode, the hoist control circuitry automatically shifts and latches the hoist system to operate in the 272 kg mode and consequently to limit cable speed to 30 m per minute.
Page 652 UNMAINTAINED COPY RFM A109E APPENDIX 24 Airspeed : As required for adequate con- trollability, not to exceed 20 KIAS. Once a suitable site has been reached, establish hover, then slowly descend to lay the load on ground. Recover manually the cable on board then proceed to land.
Page 653 UNMAINTAINED COPY RFM A109E APPENDIX 24 Failure of both generator busses This falure is indicated by BUS TIE caution message and after few seconds, if the battery discharge control box is installed, by BATT DISCH warning message on EDU 1. No loads are lost.
Page 654 UNMAINTAINED COPY RFM A109E APPENDIX 24 BATT switch : OFF. ELECTRICAL warning, INV 1, SAS 1 OFF, BATT OFF caution messages displayed. All loads of GENerator BUS # 1 and Emergency Bus # 1 are lost. All loads on Essential Bus # 1 are retained.
Page 655 UNMAINTAINED COPY RFM A109E APPENDIX 24 Failure of both generators and generators busses The failure of both generators followed by either the simultaneous failure of both Generator Busses or their intentional disconnection is indicated by BUS TIE, INV 2, SAS 1 OFF, SAS 2 OFF caution messages by ELECTRICAL warning messsage and, if battery discharge control box is installed, by BATT DISCH warning message on EDU 1.
Page 656 UNMAINTAINED COPY...
Page 657 UNMAINTAINED COPY RFM A109E APPENDIX 24 SECTION 4 - PERFORMANCE DATA OPERATION VS ALLOWABLE WIND Satisfactory stability and control in rearward and sideward flight has been demonstrated, at all loading conditions for hover out of ground effect up to takeoff power, from -1000 ft to 8000 ft Hd, in the following wind/ground speed azimuth envelope: Figure 4-1.
Page 658 UNMAINTAINED COPY RFM A109E APPENDIX 24 SECTION 7 - SYSTEMS DESCRIPTION 1. HOIST CABLE LKD caution message 9. HOIST switch 2. HOIST CUT ARMD caution message 10. Pilot display indicator 3. HOIST-PWR circuit breaker 11. MOTOR WRN light 4. HOIST-CTL circuit breaker 12.
Page 659 UNMAINTAINED COPY RFM A109E APPENDIX 25 E.N.A.C. Approval Letter 99/4800/MAE dated 28 December 1999 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 660 UNMAINTAINED COPY RFM A109E APPENDIX 25 TABLE OF CONTENTS Page PART I - E.N.A.C. APPROVED SECTION 1 - LIMITATIONS TYPE OF OPERATION 3 of 8 REQUIRED EQUIPMENT 3 of 8 COMPATIBILITY 3 of 8 SECTION 2 - NORMAL PROCEDURES PREFLIGHT CHECKS 4 of 8 PILOT’S PREFLIGHT CHECK...
Page 661 UNMAINTAINED COPY RFM A109E APPENDIX 25 SECTION 1 - LIMITATIONS TYPE OF OPERATION The TAS SKY497 can be used in VFR and IFR conditions as an aid to visually acquiring traffic. NOTE The pilot should maneuver the aircraft based only on ATC guidance or positive visual acquisition of the conflicting traffic.
Page 662 UNMAINTAINED COPY RFM A109E APPENDIX 25 SECTION 2 - NORMAL PROCEDURES PREFLIGHT CHECKS PILOT’S PREFLIGHT CHECK (Every flight) SKYWATCH TAS SKY497 Pilot’s Guide : Check on board. SKY497 INTEGRATED WITH KMD 550 KMD 550/850 Multifunction Display Pilot’s Guide : Check on board KMD 550/850 Multifunction Display (TCAS/TAS) Pilot’s Guide Addendum...
Page 663 UNMAINTAINED COPY RFM A109E APPENDIX 25 TAS SKY497 OFF/BRT knob : Turn clockwise to the desired display brightness. After the completion of power on self test, press TEST button and verify that test screen appears while self-test is in process and...
Page 664 UNMAINTAINED COPY RFM A109E APPENDIX 25 audio message ″TRAFFIC AD- VISORY SYSTEM TEST PASSED″ is heard and the dis- play reverts to the standby mode. NOTE If the audio message ″TRAFFIC ADVISORY SYSTEM TEST FAILED″ is heard and the TAS FAIL legend appears in the screen, push the TEST button again.
Page 665 UNMAINTAINED COPY RFM A109E APPENDIX 25 WARNING Do not attempt maneuvers based solely on traffic information shown on SKY 497 display. Information on the display is provided to the flight crew as an aid in visually acquiring traffic; it is not a replacement for ATC and See &...
Page 666 UNMAINTAINED COPY RFM A109E APPENDIX 25 SECTION 7 - SYSTEMS DESCRIPTION The Traffic Advisory (TA) display indicates the relative position of an intruder when it is approximately 30 seconds from the Closest Point of Approch (CPA) or inside a range of 0.55 NM and ± 800 ft from own helicopter.
Page 667 UNMAINTAINED COPY RFM A109E APPENDIX 26 E.N.A.C. Approval Letter 99/4800/MAE dated 28-12-1999 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 668 UNMAINTAINED COPY RFM A109E APPENDIX 26 TABLE OF CONTENTS Page PART I - E.N.A.C. APPROVED SECTION 1 - LIMITATIONS TYPE OF OPERATION 3 of 6 SECTION 2 - NORMAL PROCEDURES ENGINE START (NORMAL OR QUICK) 3 of 6 SYSTEMS CHECK...
Page 669 UNMAINTAINED COPY RFM A109E APPENDIX 26 SECTION 1 - LIMITATIONS TYPE OF OPERATION The navigation can not be based on the SKYFORCE OBSERVER System. COMPATIBILITY The installation of the SKYFORCE OBSERVER System is not physically compatible with the oxygen system P/N 109-0811-76.
Page 670 UNMAINTAINED COPY RFM A109E APPENDIX 26 NOTE The TEMP lamp is red to indicate ″Too Hot″ and amber to indicate ″Heater in Operation″. Verify that, after approximately 100 seconds, the WARNING screen appears. Check the correct software stan- dard. SYSTEMS CHECK...
Page 671 UNMAINTAINED COPY RFM A109E APPENDIX 26 IN FLIGHT SKYFORCE OBSERVER display head : As required. SHUTDOWN (After engines shutdown) SKYFORCE OBSERVER display head : Go to MAIN MENU and select SHUT DOWN. Press the YES key. NOTE The SHUT DOWN key must be used to shut the system software down;...
Page 672 UNMAINTAINED COPY RFM A109E APPENDIX 26 SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES No change. SECTION 4 - PERFORMANCE DATA No change. Page 6 of 6 E.N.A.C. Approved...
Page 673 UNMAINTAINED COPY RFM A109E APPENDIX 27 E.N.A.C. Approval Letter 99/4800/MAE dated 28-12-1999 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 674 UNMAINTAINED COPY RFM A109E APPENDIX 27 TABLE OF CONTENTS Page TABLE OF CONTENTS Page PART I - E.N.A.C. APPROVED SECTION 1 - LIMITATIONS TYPE OF OPERATION 3 of 4 COMPATIBILITY 3 of 4 SECTION 2 - NORMAL PROCEDURES IN FLIGHT...
Page 675 UNMAINTAINED COPY RFM A109E APPENDIX 27 SECTION 1 - LIMITATIONS TYPE OF OPERATION The use in flight of AIRSAT 1 satellite telephone must be authorized by the pilot. The use of AIRSAT 1 satellite telephone during takeoff and landing is prohibited.
Page 676 UNMAINTAINED COPY RFM A109E APPENDIX 27 PILOT/CREW pushbutton : Push to select Phone handset (to use) : Turn the phone on and digit the PIN. Operate the phone as required. CAUTION Do not try to switch the phone control from pilot to crew station...
Page 677 UNMAINTAINED COPY RFM A109E APPENDIX 28 E.N.A.C. Approval Letter N. 00/504/MAE dated 16 February 2000 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 678 UNMAINTAINED COPY RFM A109E APPENDIX 28 TABLE OF CONTENTS Page PART I - R.A.I. APPROVED SECTION 1 - LIMITATIONS TYPE OF OPERATION 8 of 108 REQUIRED EQUIPMENT 8 of 108 WEIGHT LIMITATIONS 8 of 108 CENTER OF GRAVITY LIMITATIONS 8 of 108...
Page 679 UNMAINTAINED COPY RFM A109E APPENDIX 28 Table of Contents (Cont.d) Page INTEGRATED DISPLAY SYSTEM (IDS) 108 of 108 DATA DISPLAY 108 of 108 LIST OF ILLUSTRATIONS Page Figure 1-1. Weight - altitude - temperature limitations for take off and landing (clear area) - EAPS OFF.
Page 680 UNMAINTAINED COPY RFM A109E APPENDIX 28 List of Illustrations (Cont.d) Page Figure 4-6. Hovering ceiling - IGE - maximum continuous power - EAPS OFF. 31 of 108 Figure 4-7. Hovering ceiling - IGE - maximum continuous power - EAPS ON.
Page 681 UNMAINTAINED COPY RFM A109E APPENDIX 28 List of Illustrations (Cont.d) Page Figure 4-21. Rate of climb - OEI - 2.5 minutespower - 2450 kg - EAPS OFF/ON. 48 of 108 Figure 4-22. Rate of climb - OEI - 2.5 minutespower - 2850 kg - EAPS OFF/ON.
Page 682 UNMAINTAINED COPY RFM A109E APPENDIX 28 List of Illustrations (Cont.d) Page Figure 4-37. Takeoff flight path 1 - 2050 kg - EAPS ON. 67 of 108 Figure 4-38. Takeoff flight path 1 - 2250 kg - EAPS OFF. 68 of 108 Figure 4-39.
Page 683 UNMAINTAINED COPY RFM A109E APPENDIX 28 List of Illustrations (Cont.d) Page Figure 4-64. Rate of climb - OEI - 2.5 minutes power - 2850 kg - EAPS OFF. 94 of 108 Figure 4-65. Rate of climb - OEI - 2.5 minutes power - 2850 kg - EAPS ON.
Page 684 UNMAINTAINED COPY RFM A109E APPENDIX 28 SECTION 1 - LIMITATIONS TYPE OF OPERATION Flight in falling and/or blowing snow is prohibited. REQUIRED EQUIPMENT In addition to the basic required equipment the helicopter must be fitted with: — the Integrated Display System composed by EDU P/N 109-0900-42- 2A01 and DAU P/N 109-0900-42-6A01.
Page 685 UNMAINTAINED COPY RFM A109E APPENDIX 28 WEIGHT-ALTITUDE-TEMPERATURE LIMITATIONS FOR TAKE OFF AND LANDING CLEAR AREA EAPS OFF HEATER OR E.C.S. OFF V2 30 kts IAS GROSS WEIGHT - POUNDS x 100 OAT - ˚C GROSS WEIGHT - kg X 100...
Page 686 UNMAINTAINED COPY RFM A109E APPENDIX 28 WEIGHT-ALTITUDE-TEMPERATURE LIMITATIONS FOR TAKE OFF AND LANDING CLEAR AREA EAPS ON V2 30 kts IAS HEATER OR E.C.S. OFF GROSS WEIGHT - POUNDS x 100 OAT - ˚C GROSS WEIGHT - kg X 100...
Page 687 UNMAINTAINED COPY RFM A109E APPENDIX 28 WEIGHT-ALTITUDE-TEMPERATURE LIMITATIONS FOR TAKE OFF AND LANDING SHORT FIELD (100 m ) EAPS OFF V2 30 kts IAS HEATER OR E.C.S. OFF GROSS WEIGHT - POUNDS x 100 OAT - ˚C GROSS WEIGHT - kg X 100...
Page 688 UNMAINTAINED COPY RFM A109E APPENDIX 28 WEIGHT-ALTITUDE-TEMPERATURE LIMITATIONS FOR TAKE OFF AND LANDING SHORT FIELD (100 m) EAPS ON V2 30 kts IAS HEATER OR E.C.S. OFF GROSS WEIGHT - POUNDS x 100 OAT - ˚C GROSS WEIGHT - kg X 100...
Page 689 UNMAINTAINED COPY RFM A109E APPENDIX 28 WEIGHT-ALTITUDE-TEMPERATURE LIMITATIONS FOR TAKE OFF AND LANDING GROUND BASED HELIPAD 15 m x 15 m ELEVATED HELIPAD 20 m x 20 m EAPS OFF V2 30 kts IAS HEATER OR E.C.S. OFF GROSS WEIGHT - POUNDS x 100 OAT - ˚C...
Page 690 UNMAINTAINED COPY RFM A109E APPENDIX 28 WEIGHT-ALTITUDE-TEMPERATURE LIMITATIONS FOR TAKE OFF AND LANDING GROUND BASED HELIPAD 15 m x 15 m ELEVATED HELIPAD 20 m X 20 m V2 30 kts IAS EAPS ON HEATER OR E.C.S. OFF GROSS WEIGHT - POUNDS x 100 OAT - ˚C...
Page 691 UNMAINTAINED COPY RFM A109E APPENDIX 28 WEIGHT-ALTITUDE-TEMPERATURE LIMITATIONS FOR TAKE OFF AND LANDING CLEAR AREA (TRAINING) EAPS OFF HEATER OR E.C.S. OFF V2 30 kts IAS GROSS WEIGHT - POUNDS x 100 NOTE: PATH 2 PROFILE CAN NOT BE CARRIED OUT IN SHADED AREA OAT - ˚C...
Page 692 UNMAINTAINED COPY RFM A109E APPENDIX 28 WEIGHT-ALTITUDE-TEMPERATURE LIMITATIONS FOR TAKE OFF AND LANDING SHORT FIELD (100 m) (TRAINING) EAPS OFF V2 30 kts IAS HEATER OR E.C.S. OFF GROSS WEIGHT - POUNDS x 100 NOTE: PATH 2 PROFILE CAN NOT BE CARRIED OUT IN SHADED AREA OAT - ˚C...
Page 693 UNMAINTAINED COPY RFM A109E APPENDIX 28 WEIGHT-ALTITUDE-TEMPERATURE LIMITATIONS FOR TAKE OFF AND LANDING GROUND BASED HELIPAD 15 m x 15 m (TRAINING) EAPS OFF V2 30 kts IAS HEATER OR E.C.S. OFF GROSS WEIGHT - POUNDS x 100 NOTE: PATH 2 PROFILE...
Page 694 UNMAINTAINED COPY RFM A109E APPENDIX 28 SECTION 2 - NORMAL PROCEDURES PREFLIGHT CHECKS PILOT’S DAILY PREFLIGHT CHECK (First flight of the day) Area N° 2 (Fuselage - rh side) Engine air intake and particle separator screen and ejector : Cover removed; foreign matter, integrity and free of obstruc- tions.
Page 695 UNMAINTAINED COPY RFM A109E APPENDIX 28 ENGINE PRE-START CHECK (at the end of ENGINE PRE-START CHECK sequence) EAPS 1 and 2 switches : ON. Check #1 and #2 EAPS ON advisory messages displayed on EDU 2, and #1 and #2 EAPS PRES caution messages dis- played on EDU 1.
Page 696 UNMAINTAINED COPY RFM A109E APPENDIX 28 SHUTDOWN (Before ENG 1 and 2 MODE switches to OFF) EAPS 1 and 2 switches : OFF (if utilized) and check #1 and #2 EAPS ON advisory messages on EDU 2 out. SECTION 3 - EMERGENCY AND MALFUNCTION...
Page 697 UNMAINTAINED COPY RFM A109E APPENDIX 28 ENGINE RESTART IN FLIGHT Before attempting a restart either in AUTO mode or in MANUAL mode: EAPS switch (affected engine) : OFF, check. ENGINE STARTING IN MANUAL MODE (ON GROUND) EAPS switch (affected engine) : OFF.
Page 698 APPENDIX 28 SECTION 4 - PERFORMANCE DATA PERFORMANCE CHARTS This Section includes the performance data for A109E helicopters equipped with particle separator and related to the following configurations: — helicopters in basic configuration; — helicopters with Bleed Air Heater or E.C.S.;...
Page 699 UNMAINTAINED COPY RFM A109E APPENDIX 28 Helicopters in basic configuration — Figure 4-1. Power assurance check - hover - EAPS OFF. — Figure 4-2. Power assurance check - hover - EAPS ON. — Figure 4-3. Power assurance check - in flight - EAPS OFF.
Page 700 UNMAINTAINED COPY RFM A109E APPENDIX 28 — Figure 4-22. Rate of climb - OEI - 2.5 minutes power - 2850 kg - EAPS OFF/ON. — Figure 4-23. Rate of climb - OEI - maximum continuous power - 2050 kg - EAPS OFF/ON.
Page 701 UNMAINTAINED COPY RFM A109E APPENDIX 28 POWER ASSURANCE CHECK HOVER * EAPS OFF. * HEATER / E.C.S. OFF. * TEST ENGINE MODE SWITCH - FLIGHT. * GENERATOR LOAD TO MINIMUM (< 28 A). * OTHER ENGINE MODE SWITCH - IDLE.
Page 702 UNMAINTAINED COPY RFM A109E APPENDIX 28 POWER ASSURANCE CHECK HOVER * EAPS ON. * HEATER / E.C.S. OFF. * TEST ENGINE MODE SWITCH - FLIGHT. * GENERATOR LOAD TO MINIMUM (< 28 A). * OTHER ENGINE MODE SWITCH - IDLE.
Page 703 UNMAINTAINED COPY RFM A109E APPENDIX 28 POWER ASSURANCE CHECK IN FLIGHT * EAPS OFF * HEATER / E.C.S. OFF. * ESTABLISH LEVEL FLIGHT ABOVE 1000 ft. AGL. * TEST ENGINE - SET ENG. GOV. SWITCH TO MANUAL * GENERATOR LOAD TO MINIMUM (< 28 A).
Page 704 UNMAINTAINED COPY...
Page 705 UNMAINTAINED COPY RFM A109E APPENDIX 28 HOVERING CEILING IN GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % EAPS OFF ZERO WIND WHEEL HEIGHT: 3 ft ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 OAT - ˚C...
Page 706 UNMAINTAINED COPY RFM A109E APPENDIX 28 HOVERING CEILING IN GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % WHEEL HEIGHT: 3 ft EAPS ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 OAT - ˚C...
Page 707 UNMAINTAINED COPY RFM A109E APPENDIX 28 HOVERING CEILING IN GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % WHEEL HEIGHT: 3 ft EAPS OFF ELECTRICAL LOAD: 150 A TOTAL ZERO WIND GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 OAT - ˚C...
Page 708 UNMAINTAINED COPY RFM A109E APPENDIX 28 HOVERING CEILING IN GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % WHEEL HEIGHT: 3 ft EAPS ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 OAT - ˚C...
Page 709 UNMAINTAINED COPY RFM A109E APPENDIX 28 HOVERING CEILING OUT OF GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % EAPS OFF ELECTRICAL LOAD: 150 A TOTAL ZERO WIND CAUTION: OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V LIMITATIONS. GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 OAT - ˚C...
Page 710 UNMAINTAINED COPY RFM A109E APPENDIX 28 HOVERING CEILING OUT OF GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % EAPS ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND CAUTION:OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V LIMITATIONS. GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 OAT - ˚C...
Page 711 UNMAINTAINED COPY RFM A109E APPENDIX 28 HOVERING CEILING OUT OF GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % EAPS OFF ELECTRICAL LOAD: 150 A TOTAL ZERO WIND CAUTION: OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V LIMITATIONS. GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 OAT - ˚C...
Page 712 UNMAINTAINED COPY RFM A109E APPENDIX 28 HOVERING CEILING OUT OF GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % EAPS ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND CAUTION:OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V LIMITATIONS. GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 OAT - ˚C...
Page 713 UNMAINTAINED COPY RFM A109E APPENDIX 28 HEIGHT-VELOCITY DIAGRAM ONE ENGINE INOPERATIVE EAPS OFF CHART "A" SHOWS THE WEIGHT VALUES AT/BELOW WHICH THERE IS NO H-V LIMITATION. FOR HEAVIER WEIGHTS, REFER TO CHART "B". CHART A GROSS WEIGHT - POUNDS x 100 OAT - ˚C...
Page 714 UNMAINTAINED COPY RFM A109E APPENDIX 28 HEIGHT-VELOCITY DIAGRAM ONE ENGINE INOPERATIVE (FOR SMOOTH, LEVEL AND HARD SURFACE) EAPS OFF CHART B AVOID OPERATION IN SHADED AREA INDICATED AIRSPEED - KNOTS TR 109-61-65/II REV A ABHD245A Figure 4-12 (sheet 2 of 2). Height - velocity diagram - EAPS OFF.
Page 715 UNMAINTAINED COPY RFM A109E APPENDIX 28 HEIGHT-VELOCITY DIAGRAM ONE ENGINE INOPERATIVE EAPS ON CHART "A" SHOWS THE WEIGHT VALUES AT/BELOW WHICH THERE IS NO H-V LIMITATION. FOR HEAVIER WEIGHTS, REFER TO CHART "B". CHART A GROSS WEIGHT - POUNDS x 100 OAT - ˚C...
Page 716 UNMAINTAINED COPY RFM A109E APPENDIX 28 HEIGHT-VELOCITY DIAGRAM ONE ENGINE INOPERATIVE (FOR SMOOTH, LEVEL AND HARD SURFACE) EAPS ON CHART B AVOID OPERATION IN SHADED AREA INDICATED AIRSPEED - KNOTS TR 109-61-65/II REV A ABHD247A Figure 4-13 (sheet 2 of 2). Height - velocity diagram - EAPS ON.
Page 717 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ALL ENGINES TAKE-OFF POWER ROTOR: 100 % EAPS OFF 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL WITH EAPS ON: DECREASE RATE OF CLIMB BY 350 ft/min ( 1.78 m/s) RATE OF CLIMB - METERS/SECOND...
Page 718 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ALL ENGINES TAKE-OFF POWER ROTOR: 100 % 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL WITH EAPS ON : DECREASE RATE OF CLIMB BY 300 ft/min (1.52 m/s) RATE OF CLIMB - METERS/SECOND...
Page 719 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ALL ENGINES TAKE-OFF POWER ROTOR: 100 % 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL WITH EAPS ON : DECREASE RATE OF CLIMB BY 250 ft/min (1.27 m/s) RATE OF CLIMB - METERS/SECOND...
Page 720 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL WITH EAPS ON : DECREASE RATE OF CLIMB BY 300 ft/min (1.52 m/s)
Page 721 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL WITH EAPS ON : DECREASE RATE OF CLIMB BY 250 ft/min (1.27 m/s)
Page 722 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL WITH EAPS ON : DECREASE RATE OF CLIMB BY 250 ft/min (1.27 m/s)
Page 723 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 100 % 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL WITH EAPS ON : DECREASE RATE OF CLIMB BY 175 ft/min (0.89 m/s)
Page 724 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 100 % 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL WITH EAPS ON : DECREASE RATE OF CLIMB BY 150 ft/min (0.76 m/s)
Page 725 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 100 % 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL WITH EAPS ON : DECREASE RATE OF CLIMB BY 125 ft/min (0.64 m/s)
Page 726 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL WITH EAPS ON : DECREASE RATE OF CLIMB BY 150 ft/min (0.76 m/s)
Page 727 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL WITH EAPS ON : DECREASE RATE OF CLIMB BY 150 ft/min (0.76 m/s)
Page 728 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL WITH EAPS ON : DECREASE RATE OF CLIMB BY 125 ft/min (0.64 m/s)
Page 729 UNMAINTAINED COPY RFM A109E APPENDIX 28 Helicopters in basic configuration with bleed air heater or ECS (refer also to Appendix 5 or 6) — Figure 4-26. Hovering ceiling - IGE - take off power - EAPS OFF/ON - heater or ECS ON.
Page 730 UNMAINTAINED COPY RFM A109E APPENDIX 28 HOVERING CEILING IN GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % WHEEL HEIGHT: 3 ft EAPS OFF ELECTRICAL LOAD: 150 A TOTAL HEATER OR E.C.S. ON ZERO WIND WITH EAPS ON : DECREASE GROSS WEIGHT BY 40 kg (88 lb)
Page 731 UNMAINTAINED COPY RFM A109E APPENDIX 28 HOVERING CEILING IN GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % WHEEL HEIGHT: 3 ft EAPS OFF ELECTRICAL LOAD: 150 A TOTAL HEATER OR E.C.S. ON ZERO WIND WITH EAPS ON : DECREASE GROSS WEIGHT BY 50 kg (110 lb)
Page 732 UNMAINTAINED COPY RFM A109E APPENDIX 28 HOVERING CEILING OUT OF GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % EAPS OFF ELECTRICAL LOAD: 150 A TOTAL HEATER OR E.C.S. ON ZERO WIND WITH EAPS ON : DECREASE GROSS WEIGHT BY 50 kg (110 lb) CAUTION:OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V LIMITATIONS.
Page 733 UNMAINTAINED COPY RFM A109E APPENDIX 28 HOVERING CEILING OUT OF GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % EAPS OFF ELECTRICAL LOAD: 150 A TOTAL HEATER OR E.C.S. ON ZERO WIND WITH EAPS ON : DECREASE GROSS WEIGHT BY 50 kg (110 lb) CAUTION:OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V LIMITATIONS.
Page 734 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ALL ENGINES TAKE-OFF POWER ROTOR: 100 % 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL HEATER OR E.C.S. ON WITH EAPS ON : DECREASE RATE OF CLIMB BY 100 ft/min (0.51 m/s)
Page 735 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ALL ENGINES TAKE-OFF POWER ROTOR: 100 % 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL HEATER OR E.C.S. ON WITH EAPS ON : DECREASE RATE OF CLIMB BY 50 ft/min (0.25 m/s)
Page 736 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ALL ENGINES TAKE-OFF POWER ROTOR: 100 % 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL HEATER OR E.C.S. ON WITH EAPS ON : DECREASE RATE OF CLIMB BY 50 ft/min (0.25 m/s)
Page 737 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL HEATER OR E.C.S. ON WITH EAPS ON : DECREASE RATE OF CLIMB BY 100 ft/min (0.51 m/s)
Page 738 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL HEATER OR E.C.S. ON WITH EAPS ON : DECREASE RATE OF CLIMB BY 100 ft/min (0.51 m/s)
Page 739 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL HEATER OR E.C.S. ON WITH EAPS ON : DECREASE RATE OF CLIMB BY 50 ft/min (0.25 m/s)
Page 740 UNMAINTAINED COPY RFM A109E APPENDIX 28 Helicopters in basic configuration for Equivalent category ″A″ operations (refer also to Appendix 12) — Figure 4-36. Takeoff flight path 1 - 2050 kg - EAPS OFF. — Figure 4-37. Takeoff flight path 1 - 2050 kg - EAPS ON.
Page 741 UNMAINTAINED COPY RFM A109E APPENDIX 28 — Figure 4-63. Rate of climb - OEI - 2.5 minutes power - 2650 kg - EAPS — Figure 4-64. Rate of climb - OEI - 2.5 minutes power - 2850 kg - EAPS OFF.
Page 742 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % EAPS OFF V2 30 kts IAS ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2050 kg ( 4519 lb ) OAT - ˚C...
Page 743 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS EAPS ON ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2050 kg ( 4519 lb ) OAT - ˚C...
Page 744 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2250 kg ( 4960 lb ) OAT - ˚C...
Page 745 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS EAPS ON ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2250 kg ( 4960 lb ) OAT - ˚C...
Page 746 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2450 kg ( 5401 lb ) OAT - ˚C...
Page 747 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS EAPS ON ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2450 kg ( 5401 lb ) OAT - ˚C...
Page 748 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2650 kg ( 5842 lb ) OAT - ˚C...
Page 749 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS EAPS ON ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2650 kg ( 5842 lb ) OAT - ˚C...
Page 750 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2850 kg ( 6283 lb ) OAT - ˚C...
Page 751 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS EAPS ON ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2850 kg ( 6283 lb ) OAT - ˚C...
Page 752 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % EAPS OFF Vy 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2050 kg ( 4519 lb ) OAT - ˚C...
Page 753 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % Vy 60 kts IAS EAPS ON ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2050 kg ( 4519 lb ) OAT - ˚C...
Page 754 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % Vy 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2250 kg ( 4960 lb ) OAT - ˚C...
Page 755 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % Vy 60 kts IAS EAPS ON ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2250 kg ( 4960 lb ) OAT - ˚C...
Page 756 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % Vy 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2450 kg ( 5401 lb ) OAT - ˚C...
Page 757 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % Vy 60 kts IAS EAPS ON ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2450 kg ( 5401 lb ) OAT - ˚C...
Page 758 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % Vy 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2650 kg ( 5842 lb ) OAT - ˚C...
Page 759 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % Vy 60 kts IAS EAPS ON ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2650 kg ( 5842 lb ) OAT - ˚C...
Page 760 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % Vy 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2850 kg ( 6283 lb ) OAT - ˚C...
Page 761 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % Vy 60 kts IAS EAPS ON ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2850 kg ( 6283 lb ) OAT - ˚C...
Page 762 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % EAPS OFF V2 30 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2050 kg ( 4519 lb ) OAT - ˚C...
Page 763 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS EAPS ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2050 kg ( 4519 lb ) OAT - ˚C...
Page 764 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2250 kg ( 4960 lb ) OAT - ˚C...
Page 765 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS EAPS ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2250 kg ( 4960 lb ) OAT - ˚C...
Page 766 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2450 kg ( 5401 lb ) OAT - ˚C...
Page 767 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS EAPS ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2450 kg ( 5401 lb ) OAT - ˚C...
Page 768 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2650 kg ( 5842 lb ) OAT - ˚C...
Page 769 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS EAPS ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2650 kg ( 5842 lb ) OAT - ˚C...
Page 770 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % V2 30 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2850 kg ( 6283 lb ) OAT - ˚C...
Page 771 UNMAINTAINED COPY RFM A109E APPENDIX 28 RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 102 % 30 KNOTS IAS EAPS ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2850 kg ( 6283 lb ) OAT - ˚C...
Page 772 UNMAINTAINED COPY RFM A109E APPENDIX 28 Helicopters in basic configuration for Equivalent category ″A″ operations - Training procedures (refer also to Appendix 23) — Figure 4-66. Takeoff flight path 1 - 2050 kg - training - EAPS OFF. — Figure 4-67. Takeoff flight path 1 - 2250 kg - training - EAPS OFF.
Page 773 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER (TRAINING) ROTOR: 102 % EAPS OFF V2 30 kts IAS ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2050 kg ( 4519 lb ) OAT - ˚C...
Page 774 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER (TRAINING) ROTOR: 102 % V2 30 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2250 kg ( 4960 lb ) OAT - ˚C...
Page 775 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER (TRAINING) V2 30 kts IAS ROTOR: 102 % ELECTRICAL LOAD: 150 A TOTAL EAPS OFF GROSS WEIGHT 2450 kg ( 5401 lb ) OAT - ˚C...
Page 776 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER (TRAINING) ROTOR: 102 % V2 30 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2650 kg ( 5842 lb ) OAT - ˚C...
Page 777 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 1 ONE ENGINE INOPERATIVE 2.5 MINUTE POWER (TRAINING) ROTOR: 102 % V2 30 kts IAS ELECTRICAL LOAD: 150 A TOTAL EAPS OFF GROSS WEIGHT 2850 kg ( 6283 lb ) OAT - ˚C...
Page 778 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER (TRAINING) ROTOR: 100 % EAPS OFF Vy 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2050 kg ( 4519 lb ) OAT - ˚C...
Page 779 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER (TRAINING) ROTOR: 100 % Vy 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2250 kg ( 4960 lb ) OAT - ˚C...
Page 780 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER (TRAINING) ROTOR: 100 % Vy 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2450 kg ( 5401 lb ) OAT - ˚C...
Page 781 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER (TRAINING) ROTOR: 100 % Vy 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL EAPS OFF GROSS WEIGHT 2650 kg ( 5842 lb ) OAT - ˚C...
Page 782 UNMAINTAINED COPY RFM A109E APPENDIX 28 TAKE OFF FLIGHT PATH 2 ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER (TRAINING) ROTOR: 100 % Vy 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT 2850 kg ( 6283 lb ) OAT - ˚C...
Page 783 UNMAINTAINED COPY RFM A109E APPENDIX 28 SECTION 7 - SYSTEM DESCRIPTION INSTRUMENT PANEL AND CONSOLE 1. EAPS 1 switch 2. EAPS 2 switch Figure 7-1. Overhead panel (partial). Page 107 of 108...
Page 784 UNMAINTAINED COPY RFM A109E APPENDIX 28 INTEGRATED DISPLAY SYSTEM (IDS) DATA DISPLAY Display of Advisory/Status Messages Advisory Message Description #1 (#2) EAPS ON Engine Air Particle Separator on Page 108 of 108...
Page 785 UNMAINTAINED COPY RFM A109E APPENDIX 29 E.N.A.C. Approval Letter N. 00/505/MAE dated 16 February 2000 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 786 UNMAINTAINED COPY RFM A109E APPENDIX 29 TABLE OF CONTENTS Page PART I - E.N.A.C. APPROVED SECTION 1 - LIMITATIONS CROSS START OPERATION 4 of 15 SECTION 2 - NORMAL PROCEDURES 4 of 15 ENGINE PRE-START CHECK 4 of 15 NORMAL ENGINE START...
Page 787 UNMAINTAINED COPY RFM A109E APPENDIX 29 PART I E.N.A.C. APPROVED E.N.A.C. Approved Page 3 of 15...
Page 788: Cross Start Operation
UNMAINTAINED COPY RFM A109E APPENDIX 29 SECTION 1 - LIMITATIONS CROSS START OPERATION Any generator-assisted start of the second engine (cross start operation) is prohibited. PLACARDS ENGINE CROSS START IS PROHIBITED In clear view of the pilot. SECTION 2 - NORMAL PROCEDURES...
Page 789 UNMAINTAINED COPY RFM A109E APPENDIX 29 Rotor brake (if installed) : Disengaged (lever full forward) EDU 1 : Select START page. ENGINE 1 START ENG 1 MODE switch : IDLE NOTE It is recommended to start the engine to IDLE, nevertheless, if necessary, it is possible to start to FLIGHT by setting the ENG MODE switch directly to FLT.
Page 790 UNMAINTAINED COPY RFM A109E APPENDIX 29 CAUTION Following aborted start shutdown perform the following proce- dure before restarting: − Allow 30 seconds fuel drain period. − Perform a 30 seconds DRY MOTORING RUN. Refer to Section 1 for engine starter limitations and to DRY MOTORING RUN procedure in this Section.
Page 791 UNMAINTAINED COPY RFM A109E APPENDIX 29 Hydraulic utility system (normal and emergency) : When accumulators are dis- charged, as main rotor begins to rotate, check pressure rise in both systems and note the acti- vation of MAIN UTIL CHRG and EMER UTIL CHRG cau- tion messages.
Page 792 UNMAINTAINED COPY RFM A109E APPENDIX 29 NOTE In the starting phase it is suggested to select FLIGHT mode as soon as possible in order to speed up the engine oil heating. BEFORE ENGINE 2 START (ON BATTERY) During starting on battery, when battery is not fully charged, before proceeding...
Page 793 UNMAINTAINED COPY RFM A109E APPENDIX 29 Engine parameters : Check within limits. External power : Disconnect (if used) GEN 1 and 2 : ON. INV 1 and 2 switches : ON. RAD MSTR switch : ON. Clock : Set. Rotor speed (NR) : 100% check.
Page 794 UNMAINTAINED COPY RFM A109E APPENDIX 29 SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES ENGINE RESTART IN FLIGHT Each engine may be started using either the auto or manual mode It is recommended that normal engine starts be made using the auto mode.
Page 795 UNMAINTAINED COPY RFM A109E APPENDIX 29 GEN switches : Both OFF. CAUTION Cross starting using battery and starter-generator to start the opposite engine can cause starter-generator shaft shearing. CAUTION The pilot shall engage the starter and the ignition only when N1 is below 20%.
Page 796 UNMAINTAINED COPY RFM A109E APPENDIX 29 CAUTION Monitor engine start and if any of the following occurs: - lightup is not obtained within 10 seconds of fuel on - abnormal noises are heard - TOT increases beyond start limit - N1 or N2 increases beyond engine limits...
Page 797 UNMAINTAINED COPY RFM A109E APPENDIX 29 Engine power lever (inoperative en- gine) : OFF, check. ENG GOV switch : MANUAL. NOTE In presence of an ECU failure the engine control system reverts and operates in manual mode independently from the ENG GOV switch position.
Page 798 UNMAINTAINED COPY RFM A109E APPENDIX 29 Engine power lever (inoperative en- gine) : Move to FLIGHT. Starting button : Push and hold. START and IGN legends verti- cally displayed beside N1 and TOT scales on the EDU panel. Gas producer (N1) : Note increasing.
Page 799 UNMAINTAINED COPY RFM A109E APPENDIX 29 Engine power control : Set the power as required by using either the engine power lever or the ENG TRIM toggle switch on the collective control. GEN switches : Both ON. Engine oil pressure : Check.
Page 800 UNMAINTAINED COPY...
Page 801 UNMAINTAINED COPY RFM A109E APPENDIX 30 E.N.A.C. Approval Letter N. 00/851/MAE dated 16 March 2000 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 802 UNMAINTAINED COPY RFM A109E APPENDIX 30 TABLE OF CONTENTS Page SECTION 1 - LIMITATIONS CENTER OF GRAVITY LIMITATIONS 3 of 5 SECTION 2 - NORMAL PROCEDURES PREFLIGHT CHECKS 3 of 5 PILOT’S DAILY PREFLIGHT CHECK 3 of 5 IN FLIGHT...
Page 803 UNMAINTAINED COPY RFM A109E APPENDIX 30 SECTION 1 - LIMITATIONS CENTER OF GRAVITY LIMITATIONS After external loudspeakers installaion the new empty weight and CG location must be determined. SECTION 2 - NORMAL PROCEDURES PREFLIGHT CHECKS PILOT’S DAILY PREFLIGHT CHECK (First flight of the day) AREA N°2 (Fuselage - rh side)
Page 804 UNMAINTAINED COPY RFM A109E APPENDIX 30 IN FLIGHT WARNING Avoid loudspeakers operation when on ground as this may cause injury to personnel. Ground support personnel in vicinity of helicopter should wear protective hearing devices. PUBLIC ADDRESS OPERATION POWER switch : ON. Check POWER ON light illuminated.
Page 805 UNMAINTAINED COPY RFM A109E APPENDIX 30 When system operation is no longer required: SIREN switch : OFF POWER switch : OFF SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES No change. SECTION 4 - PERFORMANCE DATA No change SECTION 7 - SYSTEM DESCRIPTION Figure 7-1.
Page 806 UNMAINTAINED COPY...
Page 807 UNMAINTAINED COPY RFM A109E APPENDIX 31 E.N.A.C. Approval Letter No. 00-5638-TMI/C dated 31 March 2000 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 808 UNMAINTAINED COPY RFM A109E APPENDIX 31 TABLE OF CONTENTS Page PART I - R.A.I. APPROVED SECTION 1 - LIMITATIONS TYPE OF OPERATION 4 of 8 REQUIRED EQUIPMENT 4 of 8 VFR OPERATION 4 of 8 FLIGHT WITH PASSENGER CABIN DOORS OPEN...
Page 809 UNMAINTAINED COPY RFM A109E APPENDIX 31 Page PART II - MANUFACTURER’S DATA SECTION 6 - WEIGHT AND BALANCE PATIENT ARM ON LITTER 7 of 8 FORWARD ATTENDANT ARM 7 of 8 AFT ATTENDANT ARM 7 of 8 SECTION 7 - SYSTEMS DESCRIPTION...
Page 810 UNMAINTAINED COPY RFM A109E APPENDIX 31 SECTION 1 - LIMITATIONS TYPE OF OPERATION The helicopter in EMT configuration permits rescue and transportation of injured people under day and night VFR and IFR non-icing conditions. REQUIRED EQUIPMENT Sliding doors kit installation is required for E.M.T. installation and operation.
Page 811 UNMAINTAINED COPY RFM A109E APPENDIX 31 SECTION 2 - NORMAL PROCEDURES PREFLIGHT CHECKS PILOT’S DAILY PREFLIGHT CHECK (First flight of the day) AREA N°7 (Cabin interior) E.M.T. interior : Check for condition. Cabin seats and litter : Check for condition and fas- tened if unoccupied.
Page 812 UNMAINTAINED COPY RFM A109E APPENDIX 31 SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES EVACUATION THROUGH EMERGENCY EXITS Unstrap the patient and evacuate either through the LH or RH emergency exits. SECTION 4 - PERFORMANCE DATA No change. Page 6 of 8...
Page 813 UNMAINTAINED COPY RFM A109E APPENDIX 31 SECTION 6 - WEIGHT AND BALANCE PATIENT ARM ON LITTER Longitudinal arm (STA) : 2900 mm (114.2 inches) from STA 0. Lateral arm (BL) (left) : -412 mm (16.2 inches) from the helicopter plane of symmetry.
Page 814 UNMAINTAINED COPY RFM A109E APPENDIX 31 SECTION 7 - SYSTEM DESCRIPTION Figure 7-1. E.M.T. Interior arrangment Page 8 of 8...
Page 815 UNMAINTAINED COPY RFM A109E APPENDIX 32 R.A.I. Approval Letter N. 00-6654 TMI/C dated 24 May 2000 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 816 UNMAINTAINED COPY RFM A109E APPENDIX 32 TABLE OF CONTENTS Page PART I - E.N.A.C. APPROVED SECTION 1 - LIMITATIONS SECTION 2 - NORMAL PROCEDURES IN FLIGHT 3 of 3 SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES SECTION 4 - PERFORMANCE DATA...
Page 817 UNMAINTAINED COPY RFM A109E APPENDIX 32 SECTION 1 - LIMITATIONS No change. SECTION 2 - NORMAL PROCEDURES IN FLIGHT CAUTION While transmitting with the HF950, the bearing indications of ADF system are not reliable. SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES No change.
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Page 819 UNMAINTAINED COPY RFM A109E APPENDIX 33 E.N.A.C. Approval Letter 00/2775/MAE dated 27 September 2000 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 820 UNMAINTAINED COPY RFM A109E APPENDIX 33 TABLE OF CONTENTS Page PART I - E.N.A.C. APPROVED SECTION 1 - LIMITATIONS 4 of 34 CARGO HOOK OPERATION 4 of 34 FLIGHT CREW 4 of 34 AIRSPEED LIMITATIONS (IAS) 4 of 34 WEIGHT LIMITATIONS...
Page 821 UNMAINTAINED COPY RFM A109E APPENDIX 33 LIST OF ILLUSTRATIONS Page Figure 1-1 (sheet 1 of 2). Longitudinal CG limits (metric). 6 of 34 Figure 1-1 (sheet 2 of 2). Longitudinal CG limits (english). 7 of 34 Figure 1-2 (sheet 1 of 2). Lateral CG limits (metric).
Page 822 UNMAINTAINED COPY RFM A109E APPENDIX 33 SECTION 1 - LIMITATIONS CARGO HOOK OPERATION The cargo hook is authorized only as ″Class B rotorcraft-load combination″ as follows: ″Class B rotorcraft-load combination means one in which the external load is jettisonable and is lifted free of land or water during the rotorcraft operation″.
Page 823 UNMAINTAINED COPY RFM A109E APPENDIX 33 WEIGHT LIMITATIONS Maximum Gross Weight with external loads attached to cargo hook : 3000 kg (6613 lb) NOTE For maximum takeoff and landing weight refer to Section 1 of the basic Rotorcraft Flight Manual.
Page 824 UNMAINTAINED COPY RFM A109E APPENDIX 33 NOTE Longitudinal station ″0″ is 1835 mm forward of the front jack point. Figure 1-1 (sheet 1 of 2). Longitudinal CG limits (metric). Page 6 of 34 E.N.A.C. Approved...
Page 825 UNMAINTAINED COPY RFM A109E APPENDIX 33 NOTE Longitudinal station ″0″ is 72.2 in. forward of the front jack point. Figure 1-1 (sheet 2 of 2). Longitudinal CG limits (english). E.N.A.C. Approved Page 7 of 34...
Page 826 UNMAINTAINED COPY RFM A109E APPENDIX 33 NOTE The lateral station ″0″ is 450 mm inboard from each main jack point and coincides with the helicopter longitudinal plane of symmetry. Figure 1-2 (sheet 1 of 2). Lateral CG limits (metric). Page 8 of 34...
Page 827 UNMAINTAINED COPY RFM A109E APPENDIX 33 NOTE The lateral station ″0″ is 17.7 in. inboard from each main jack point and coincides with the helicopter longitudinal plane of symmetry. Figure 1-2 (sheet 2 of 2). Lateral CG limits (english). E.N.A.C. Approved...
Page 828 UNMAINTAINED COPY RFM A109E APPENDIX 33 SECTION 2 - NORMAL PROCEDURES PREFLIGHT CHECKS PILOT’S DAILY PREFLIGHT CHECK (First flight of the day) AREA N°1 (Helicopter nose) Rearview mirror : Condition, cleanliness and se- curity. AREA N°2 (Fuselage - rh side) Cargo hook : Condition and security.
Page 829 UNMAINTAINED COPY RFM A109E APPENDIX 33 CARGO HOOK pushbutton on pilot cyclic stick : Push. Verify the opening of the cargo hook and HOOK OPEN caution message on EDU 1 dis- played. Release the switch and verify that the cargo hook re-...
Page 830 UNMAINTAINED COPY RFM A109E APPENDIX 33 PILOT’S PREFLIGHT CHECK (Every flight) Rearview mirror : Condition, cleanliness and se- curity. Cargo hook : Condition and security. SYSTEMS CHECK Hook load indicator : Set to zero. NOTE Adjust the hook load indicator after a 5 minutes warm up with no load on the hook.
Page 831 UNMAINTAINED COPY RFM A109E APPENDIX 33 WARNING Discharge helicopter static electricity, before attaching cargo, by touching the airframe with a ground wire or if a metal sling is used, the hook-up ring can be struck against the cargo hook. If contact has been lost after initial grounding of the helicopter, it should be electrically regrounded and, if possible, contact main- tained until hook-up is completed.
Page 832 UNMAINTAINED COPY RFM A109E APPENDIX 33 EDU 1 : HOOK ARMED caution mes- sage displayed. Perform the approach to the cargo release area with care and at low speed. Stabilize hover above release point, then slowly descend until cargo lies down on ground.
Page 833 UNMAINTAINED COPY RFM A109E APPENDIX 33 SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES WARNING SYSTEM CAUTION MESSAGES (AMBER) EDU message Fault condition Corrective action HOOK ARMED Cargo release system No corrective action is re- armed. quired. Take care to avoid...
Page 834 UNMAINTAINED COPY RFM A109E APPENDIX 33 SECTION 4 - PERFORMANCE DATA List of Performance Data Charts: — Figure 4-1. Wind/ground speed azimuth envelope. — Figure 4-2. Hovering ceiling - OGE - take-off power. — Figure 4-3. Hovering ceiling - OGE - take-off power- heater ON.
Page 835 UNMAINTAINED COPY RFM A109E APPENDIX 33 OPERATION VS ALLOWABLE WIND Satisfactory stability and control in rearward and sideward flight has been demonstrated, at all loading conditions for hover out of ground effect up to takeoff power, from -1000 ft to 8000 ft Hd, in the following wind/ground speed azimuth envelope: Figure 4-1 (sheet 1 of 2).
Page 836 UNMAINTAINED COPY RFM A109E APPENDIX 33 Figure 4-1 (sheet 2 of 2). Wind/ground speed azimuth envelope. Page 18 of 34 E.N.A.C. Approved...
Page 837 UNMAINTAINED COPY RFM A109E APPENDIX 33 HOVERING CEILING OUT OF GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % ZERO WIND ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 838 UNMAINTAINED COPY RFM A109E APPENDIX 33 Figure 4-3. Hovering ceiling - OGE - take-off power - heater ON. Page 20 of 34 E.N.A.C. Approved...
Page 839 UNMAINTAINED COPY RFM A109E APPENDIX 33 HOVERING CEILING OUT OF GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % E.C.S. ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 840 UNMAINTAINED COPY RFM A109E APPENDIX 33 HOVERING CEILING OUT OF GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % ZERO WIND ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 841 UNMAINTAINED COPY RFM A109E APPENDIX 33 HOVERING CEILING OUT OF GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % HEATER ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 842 UNMAINTAINED COPY RFM A109E APPENDIX 33 HOVERING CEILING OUT OF GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % E.C.S. ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 843 UNMAINTAINED COPY RFM A109E APPENDIX 33 RATE OF CLIMB ALL ENGINES TAKE-OFF POWER ROTOR: 100 % 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 3000 kg ( 6613 lb ) OAT - ˚C...
Page 844 UNMAINTAINED COPY RFM A109E APPENDIX 33 RATE OF CLIMB ALL ENGINES TAKE-OFF POWER ROTOR: 100 % 60 kts IAS HEATER ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 3000 kg ( 6613 lb ) OAT - ˚C...
Page 845 UNMAINTAINED COPY RFM A109E APPENDIX 33 RATE OF CLIMB ALL ENGINES TAKE-OFF POWER ROTOR: 100 % 60 kts IAS ECS ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 3000 kg ( 6613 lb ) OAT - ˚C...
Page 846 UNMAINTAINED COPY RFM A109E APPENDIX 33 RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 3000 kg ( 6613 lb ) OAT - ˚C...
Page 847 UNMAINTAINED COPY RFM A109E APPENDIX 33 RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS HEATER ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 3000 kg ( 6613 lb ) OAT - ˚C...
Page 848 UNMAINTAINED COPY RFM A109E APPENDIX 33 RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS ECS ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 3000 kg ( 6613 lb ) OAT - ˚C...
Page 849 UNMAINTAINED COPY RFM A109E APPENDIX 33 RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 100 % 60 kts IAS ELECTRICAL LOAD: 150 A RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 3000 kg ( 6613 lb ) OAT - ˚C...
Page 850 UNMAINTAINED COPY RFM A109E APPENDIX 33 RATE OF CLIMB ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS ELECTRICAL LOAD: 150 A RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 3000 kg ( 6613 lb ) OAT - ˚C...
Page 851 UNMAINTAINED COPY RFM A109E APPENDIX 33 SECTION 6 - WEIGHT AND BALANCE DATUM LINE LOCATIONS Figure 6-1 presents the cargo hook station data to aid in weight and balance computations. Figure 6-1. Cargo hook station diagram. Page 33 of 34...
Page 852 UNMAINTAINED COPY RFM A109E APPENDIX 33 SECTION 7 - SYSTEMS DESCRIPTION 1. CARGO HOOK PRI circuit breaker 2. HOOK ARMED and HOOK OPEN caution messages 3. Cargo release toggle switch 4. Cargo release handle 5. Locking plate, landing gear 6. Hook load indicator Figure 7-1.
Page 853 UNMAINTAINED COPY RFM A109E APPENDIX 34 E.N.A.C. Approval Letter 00/2775/MAE dated 27 September 2000 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 854 UNMAINTAINED COPY RFM A109E APPENDIX 34 TABLE OF CONTENTS Page PART I - E.N.A.C. APPROVED SECTION 1 - LIMITATIONS CARGO HOOKS OPERATION 4 of 14 5 of 14 WEIGHT LIMITATIONS CARGO HOOK LOADING LIMITATIONS 5 of 14 SECTION 2 - NORMAL PROCEDURES...
Page 855 UNMAINTAINED COPY RFM A109E APPENDIX 34 LIST OF ILLUSTRATIONS Page Figure 6-1. Primary and secondary cargo hooks stations diagram. 12 of 14 Figure 7-1. External load rigging. 13 of 14 Figure 7-2. Secondary cargo hook controls and indicators. 14 of 14 E.N.A.C.
Page 856 UNMAINTAINED COPY RFM A109E APPENDIX 34 SECTION 1 - LIMITATIONS CARGO HOOKS OPERATION The cargo hooks may be used only as ″Class B rotorcraft-load combination″ as follows: ″Class B rotorcraft-load combination means one in which the external load is jettisonable and is lifted free of land or water during the rotorcraft operation″.
Page 857 UNMAINTAINED COPY RFM A109E APPENDIX 34 WEIGHT LIMITATIONS Maximum Gross Weight with external loads attached to cargo hook : 3000 kg (6613 lb) NOTE For maximum takeoff and landing weight refer to Section 1 of the basic Rotorcraft Flight Manual.
Page 858 UNMAINTAINED COPY RFM A109E APPENDIX 34 PILOT’S DAILY PREFLIGHT CHECK (First flight of the day) Suspension safety cable and harnesses : Condition and security. AREA N°2 (Fuselage - rh side) Cargo hooks : Condition and security. AREA N°7 (Cabin interior) For the following checks connect the d.c.
Page 859 UNMAINTAINED COPY RFM A109E APPENDIX 34 NOTE Both cargo hooks are provided with a spring which keeps them permanently in closed position even when the opening system releases the lock-device. A force of approximately 5 kg must be applied to each cargo hook to overcome the spring-force and to verify the hook opening.
Page 860 UNMAINTAINED COPY RFM A109E APPENDIX 34 SYSTEMS CHECK Hook load indicator (primary hook only) : Set to zero. NOTE Adjust the look load indicator after a 5 minutes warm up with no load on the hook. TAKE-OFF CARGO ATTACHMENT Take off and stabilize in hovering at sufficient height to allow crew member to discharge helicopter static electricity and to attach cargo sling to the cargo hook.
Page 861 UNMAINTAINED COPY RFM A109E APPENDIX 34 WARNING Discharge helicopter static electricity, before attaching cargo, by touching the airframe with a ground wire or if a metal sling is used, the hook-up ring can be struck against the cargo hook. If contact has been lost after initial grounding of the helicopter, it should be electrically regrounded and, if possible, contact main- tained until hook-up is completed.
Page 862 UNMAINTAINED COPY RFM A109E APPENDIX 34 EDU 1 : HOOK ARMED caution mes- sage displayed. Perform the approach to the cargo release area with care and at low speed. Stabilize hover above release point, then slowly descend until cargo lies down on ground.
Page 863 UNMAINTAINED COPY RFM A109E APPENDIX 34 SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES WARNING SYSTEM CAUTION MESSAGES (AMBER) EDU message Fault condition Corrective action HOOK ARMED Cargo release system No corrective action is armed. required. Take care to avoid accidental release of cargo.
Page 864 UNMAINTAINED COPY RFM A109E APPENDIX 34 SECTION 6 - WEIGHT AND BALANCE DATUM LINE LOCATIONS Figure 6-1 presents the primary and secondary cargo hooks stations data to aid in weight and balance computations. Figure 6-1. Primary and secondary cargo hooks stations diagram.
Page 865 UNMAINTAINED COPY RFM A109E APPENDIX 34 SECTION 7 - SYSTEMS DESCRIPTION Figure 7-1. External load rigging. Page 13 of 14...
Page 866 UNMAINTAINED COPY RFM A109E APPENDIX 34 1. CARGO HOOK PRI circuit breaker 5. Secondary hook, cargo release handle 2. CARGO HOOK SEC circuit breaker 6. Primary hook, cargo release handle 3. HOOK ARMED and HOOK OPEN 7. Locking plate, landing gear caution messages 4.
Page 867 UNMAINTAINED COPY RFM A109E APPENDIX 35 E.N.A.C. Approval Letter 171035/SPA dated 11 July 2001 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 868 UNMAINTAINED COPY RFM A109E APPENDIX 35 TABLE OF CONTENTS Page PART I - E.N.A.C. APPROVED SECTION 1 - LIMITATIONS REQUIRED EQUIPMENT 3 of 5 AIRSPEED LIMITATIONS (KIAS) 3 of 5 PLACARDS 3 of 5 SECTION 2 - NORMAL PROCEDURES TAKE-OFF...
Page 869 UNMAINTAINED COPY RFM A109E APPENDIX 35 SECTION 1 - LIMITATIONS REQUIRED EQUIPMENT In addition to the basic required equipment the helicopter must be fitted with forward landing gear door P/N 109-0313-88-101. AIRSPEED LIMITATIONS (KIAS) Maximum landing gear operating speed V 140 KIAS.
Page 870 UNMAINTAINED COPY RFM A109E APPENDIX 35 SECTION 2 - NORMAL PROCEDURES TAKE-OFF HOVER TAKE-OFF CAUTION Do not operate landing gear at speeds above 140 KIAS. Do not fly with landing gear extended at speeds above 140 KIAS. ROLLING TAKE-OFF CAUTION Do not operate landing gear at speeds above 140 KIAS.
Page 871 UNMAINTAINED COPY RFM A109E APPENDIX 35 APPROACH AND LANDING CAUTION Do not operate landing gear at speeds above 140 KIAS. Do not fly with landing gear extended at speeds above 140 KIAS. SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES No change.
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Page 873 UNMAINTAINED COPY RFM A109E APPENDIX 36 E.N.A.C. Approval Letter 171300/SPA dated 30 November 2001 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 874 UNMAINTAINED COPY RFM A109E APPENDIX 36 TABLE OF CONTENTS Page PART I - E.N.A.C. APPROVED SECTION 1 - LIMITATIONS CENTER OF GRAVITY LIMITATIONS 3 of 8 SECTION 2 - NORMAL PROCEDURES ENGINE PRE-START CHECK 3 of 8 SECTION 3 - EMERGENCY AND MALFUNCTION...
Page 875 UNMAINTAINED COPY RFM A109E APPENDIX 36 SECTION 1 - LIMITATIONS CENTER OF GRAVITY LIMITATIONS After supplementary fuel tank installation, the new empty weight and C.G. location must be determined. SECTION 2 - NORMAL PROCEDURES ENGINE PRE-START CHECK Fuel quantity : Check.
Page 876 UNMAINTAINED COPY RFM A109E APPENDIX 36 SECTION 6 - WEIGHT AND BALANCE WEIGHTS - ARMS AND MOMENTS LONGITUDINAL MOMENTS USABLE FUEL - MAIN FUEL TANKS PLUS SUPPLEMENTARY TANKS WEIGHT CAPACITY MOMENT (kg) (mm) (kgm) (0.8 kg/l) 3324 66.5 3327 133.1 3329 199.7...
Page 877 UNMAINTAINED COPY RFM A109E APPENDIX 36 (Cont.d) USABLE FUEL - MAIN FUEL TANKS PLUS SUPPLEMENTARY TANKS WEIGHT CAPACITY MOMENT (kg) (mm) (kgm) (0.8 kg/l) 3840 1920.0 3847 2000.4 3856 2082.2 3863 2163.3 3872 2245.8 3876 2325.6 3883 2407.5 3890 2489.6 3897 2572.0...
Page 878 UNMAINTAINED COPY RFM A109E APPENDIX 36 (Cont.d) USABLE FUEL - MAIN FUEL TANKS PLUS RH SUPPLEMENTARY TANK ONLY WEIGHT CAPACITY MOMENT (kg) (mm) (kgm) (0.8 kg/l) 3614 867.4 3653 949.8 3687 1032.4 3716 1114.8 3741 1197.1 3764 1279.8 3784 1362.2 3802 1444.8...
Page 879 UNMAINTAINED COPY RFM A109E APPENDIX 36 LATERAL MOMENTS USABLE FUEL - MAIN FUEL TANKS PLUS RH SUPPLEMENTARY TANK ONLY WEIGHT CAPACITY MOMENT (kg) (mm) (kgm) (0.8 kg/l) 10.2 12.2 14.4 16.8 18.9 21.1 23.9 26.4 28.0 29.6 31.3 32.0 Page 7 of 8...
Page 880 UNMAINTAINED COPY RFM A109E APPENDIX 36 SECTION 8 - HANDLING AND SERVICING SERVICING Supplementary fuel tanks RH fuel cell LH fuel cell Capacity 94 liters 136 liters Usable 94 liters 136 liters Page 8 of 8...
Page 881 UNMAINTAINED COPY RFM A109E APPENDIX 37 E.N.A.C. Approval Letter 171350/SPA dated 19 December 2001 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 882 UNMAINTAINED COPY RFM A109E APPENDIX 37 TABLE OF CONTENTS Page PART I - E.N.A.C. APPROVED SECTION 1 - LIMITATIONS TYPE OF OPERATION 3 of 4 SECTION 2 - NORMAL PROCEDURES SYSTEMS CHECK 3 of 4 IN FLIGHT 4 of 4...
Page 883 UNMAINTAINED COPY RFM A109E APPENDIX 37 SECTION 1 - LIMITATIONS TYPE OF OPERATION The KMD 550 system can be used in VFR conditions only as a supplemental navigation system. The navigation must not be based on the KMD 550 system only.
Page 884 UNMAINTAINED COPY RFM A109E APPENDIX 37 KMD 550 : Turn the OFF/ON knob to ON position and adjust brightness. At the end of self-test, select MAP function key and check for valid GPS fix data. NO EXTERNAL GPS DATA advi- sory should not be shown in the middle of the display.
Page 885 UNMAINTAINED COPY RFM A109E APPENDIX 38 E.N.A.C. Approval Letter 171301/SPA dated 30 November 2001 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 886 UNMAINTAINED COPY RFM A109E APPENDIX 38 TABLE OF CONTENTS Page PART I - E.N.A.C. APPROVED SECTION 1 - LIMITATIONS REQUIRED EQUIPMENT 3 of 3 CENTER OF GRAVITY LIMITATIONS 3 of 3 COMPATIBILITY 3 of 3 SECTION 2 - NORMAL PROCEDURES...
Page 887 UNMAINTAINED COPY RFM A109E APPENDIX 38 SECTION 1 - LIMITATIONS REQUIRED EQUIPMENT Operations at gross weight greater than 2850 kg up to 3000 kg are permitted provided that the following assembly is installed: — Tail rotor installation P/N 109-0136-02-103. CENTER GRAVITY LIMITATIONS After installation of main transmission gear box vibration isolator struts, the new empty weight and CG location must be determined.
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Page 889 UNMAINTAINED COPY RFM A109E APPENDIX 39 E.N.A.C. Approval Letter No. 02/171602/SPA dated 12 November 2002 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 890 UNMAINTAINED COPY RFM A109E APPENDIX 39 TABLE OF CONTENTS Page PART I - E.N.A.C. APPROVED SECTION 1 - LIMITATIONS MAIN TRANSMISSION LUBRICATION SYSTEM LIMI- TATIONS 3 of 5 SECTION 2 - NORMAL PROCEDURES 5 of 5 SECTION 3 - EMERGENCY AND MALFUNCTION...
Page 891 UNMAINTAINED COPY RFM A109E APPENDIX 39 SECTION 1 - LIMITATIONS MAIN TRANSMISSION LUBRICATION SYSTEM LIMITATIONS Oil pressure No change. Oil temperature Maximum : 120°C E.N.A.C. Approved Page 3 of 5...
Page 892 UNMAINTAINED COPY RFM A109E APPENDIX 39 Fig. 1-1. EDU 2 (MAIN) - TRANSMISSION OIL (PRESSURE AND TEMPERATURE) Page 4 of 5 E.N.A.C. Approved...
Page 893 UNMAINTAINED COPY RFM A109E APPENDIX 39 SECTION 2 - NORMAL PROCEDURES No change. SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES No change. SECTION 4 - PERFORMANCE DATA No change. E.N.A.C. Approved Page 5 of 5...
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Page 895 UNMAINTAINED COPY RFM A109E APPENDIX 40 E.N.A.C. Approval Letter 03/171104/SPA dated 11 March 2003 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 896 UNMAINTAINED COPY RFM A109E APPENDIX 40 TABLE OF CONTENTS Page PART I - R.A.I. APPROVED SECTION 1 - LIMITATIONS SEARCHLIGHT LIMITATIONS 3 of 5 AIRSPEED LIMITATIONS (KIAS) 3 of 5 CENTER OF GRAVITY LIMITATIONS 3 of 5 SECTION 2 - NORMAL PROCEDURES...
Page 897 UNMAINTAINED COPY RFM A109E APPENDIX 40 SECTION 1 - LIMITATIONS SEARCHLIGHT LIMITATIONS The operation of searchlight P/N 109-0812-83 by the pilot during takeoff and landing is prohibited. During takeoff and landing the searchlight P/N 109-0812-83 may be operated only by the co-pilot.
Page 898 UNMAINTAINED COPY RFM A109E APPENDIX 40 PILOT’S PREFLIGHT CHECK (Every flight) Searchlight : Condition and cleanliness. ENGINE PRE-START CHECK SCHLT 2 CLT/SCHLT 2 PWR circuit breakers : ON SYSTEMS CHECK Searchlight ON/OFF/STOW switch on central console : OFF, check. IN FLIGHT...
Page 899 UNMAINTAINED COPY RFM A109E APPENDIX 40 ON/OFF/STOW switch on central console : ON. NOTE With the switch in OFF position the light remains extinguished in the position where it has been left. EXT/RETR/L/R switch on central console : Set as necessary.
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Page 901 UNMAINTAINED COPY RFM A109E APPENDIX 41 E.N.A.C. Approval Letter 03/171177/SPA dated 2 May 2003 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 902 UNMAINTAINED COPY RFM A109E APPENDIX 41 TABLE OF CONTENTS Page PART I - E.N.A.C. APPROVED SECTION 1 - LIMITATIONS TYPE OF OPERATION 3 of 8 REQUIRED EQUIPMENT 3 of 8 VFR OPERATION 4 of 8 FLIGHT WITH PASSENGER CABIN DOORS OPEN...
Page 903 UNMAINTAINED COPY RFM A109E APPENDIX 41 SECTION 1 - LIMITATIONS TYPE OF OPERATION The helicopter in E.M.T. configuration permits transportation of injured people under day and night VFR and IFR not icing conditions. REQUIRED EQUIPMENT The E.M.T. is a development of a VIP Utility configuration. The helicopter...
Page 904 UNMAINTAINED COPY RFM A109E APPENDIX 41 VFR OPERATION FLIGHT WITH PASSENGER CABIN DOORS OPEN OR REMOVED Operation with passenger cabin doors open or removed is prohibited when patient is on board. FLIGHT CREW The minimum flight crew consists of one pilot and an attendant; both of whom shall be trained in and capable of assisting in litter patient emergency evacuation procedures.
Page 905 UNMAINTAINED COPY RFM A109E APPENDIX 41 PILOT’S PREFLIGHT CHECK (Every flight) E.M.T. interior : Check for condition. Cabin seats and litter : Check for condition and straps fastened if unoccupied. TAKE-OFF Cabin curtain (if installed) : Open. In case of night flight: CAB switch : OFF.
Page 906 UNMAINTAINED COPY RFM A109E APPENDIX 41 LITTER OPERATIONS LITTER(S) LOADING — Secure patient(s) to the litter(s) using the three straps provided; — remove seat cushion of the central aft seat; — unlock and lower the back of the central aft seat;...
Page 907 UNMAINTAINED COPY RFM A109E APPENDIX 41 SECTION 6 - WEIGHT AND BALANCE PATIENT ARM ON LITTER Longitudinal arm (STA) : 2900 mm (114.2 inches) from STA 0. Lateral arm (BL) (left and/or right) : 412 mm (16.2 inches) from the helicopter plane of symmetry.
Page 908 UNMAINTAINED COPY RFM A109E APPENDIX 41 SECTION 7 - SYSTEM DESCRIPTION Figure 7-1. E.M.T. kit. Page 8 of 8 Rev. 41...
Page 909 UNMAINTAINED COPY RFM A109E APPENDIX 42 E.N.A.C. Approval Letter 03/171177/SPA dated 2 May 2003 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 910: List Of Illustrations
UNMAINTAINED COPY RFM A109E APPENDIX 42 TABLE OF CONTENTS Page PART I - E.A.S.A. APPROVED SECTION 1 - LIMITATIONS 3 of 16 SECTION 2 - NORMAL PROCEDURES PREFLIGHT CHECKS 3 of 16 ENGINE PRE-START CHECKS 3 of 16 NORMAL ENGINE START...
Page 911 UNMAINTAINED COPY RFM A109E APPENDIX 42 SECTION 1 - LIMITATIONS No change. SECTION 2 - NORMAL PROCEDURES PREFLIGHT CHECKS Pilot’s Daily preflight check (First flight of the day) Area N.7 (Cabin interior) BATT RELAY circuit breaker : In. Door secured.
Page 912 UNMAINTAINED COPY RFM A109E APPENDIX 42 SYSTEMS CHECK EADI instrument: ATT FAIL flag : Out of view. : Verify for consistency with the ADI stand-by ATT REV pushbutton : Press - Check pushbutton illuminated - Check ADI revertion to oppo-...
Page 913 UNMAINTAINED COPY RFM A109E APPENDIX 42 F/D STBY button (on FD control panel) : Press and hold FD FAIL flag : Check, in view F/D STBY button : Release EHSI instrument: Compass HDG FAIL message : Out of view Compass heading : Consistent with magnetic com- pass reading.
Page 914 UNMAINTAINED COPY RFM A109E APPENDIX 42 IN FLIGHT FLIGHT DIRECTOR OPERATION (if installed) VOR (or GPS) coupled to NAV (or LNAV) mode CAUTION When NAV mode on FD control panel is in CAP condition and a change of navigation source is carried out with the NAV key on...
Page 915 UNMAINTAINED COPY RFM A109E APPENDIX 42 STORMSCOPE WX 1000 OPERATION (if installed) After Stormscope activation (pushbutton LX set to ON), data can be displayed on EHSI in MAP mode (both center or arc format) by pressing the WX/LX pushbutton. The selection of STORMSCOPE overlay page is annunciated by ″LX″ blue legend in the bottom-right side of display.
Page 916 UNMAINTAINED COPY RFM A109E APPENDIX 42 SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES WARNING MESSAGES (RED) EADI message Fault condition Corrective action ATT FAIL Gyro not erected, loss of Check breaker. Refer to power to gyro, loss of stand-by attitude indica- Roll or Pitch data on tor.
Page 917 UNMAINTAINED COPY RFM A109E APPENDIX 42 EDU message Fault condition Corrective action VG 2 Gyro not erected, loss of Check breaker. power to gyro Copilot: revert to VG 1 through ATT REV push- button. EFIS MISCOMPARE MESSAGES (Messages displayed beside the instrument indications).
Page 918 UNMAINTAINED COPY RFM A109E APPENDIX 42 EADI message Fault condition Corrective action Excessive discrepancy Verify that both receiv- between the two local- ers are tuned on the izer data same frequency. If this is confirmed abort the ILS approach. Excessive...
Page 919 UNMAINTAINED COPY RFM A109E APPENDIX 42 Failure of one EADI. In case of failure of pilot’s (or co-pilot’s) EADI, the pilot’s (or co-pilot’s) EHSI automatically reverts to composite mode and a yellow MON DGRD (″moni- toring degraded″) message appears at the same time on all three displays to point out the degradation of the comparison monitor function in the system.
Page 920 UNMAINTAINED COPY RFM A109E APPENDIX 42 Failure of both EADIs. In the event of a failure of both EADIs, the two EHSIs automatically revert to composite mode and a yellow MON DGRD (″monitoring degraded″) message appears at the same time on both displays to point out the degradation of the comparison monitor function in the system.
Page 921 UNMAINTAINED COPY RFM A109E APPENDIX 42 EADI FAILURES Radio altimeter failure In the event of Radio Altimeter failure, an amber caution RA FAIL replaces the numerical value; the rising runway and the DH indication (if present) disappear from the screen.
Page 922 UNMAINTAINED COPY RFM A109E APPENDIX 42 SECTION 7 - SYSTEMS DESCRIPTION DME OPERATION When on EHSI ″IN COMMAND″ the LNAV 1 (or 2) is selected as navigator, the DME is automatically set on CH 2 (VOR 2). If the pilot needs to use CH 1 (VOR 1), he must select VOR 1 as navigator then select DME HOLD function and reselect the previous LNAV sensor (1 at 2).
Page 923 UNMAINTAINED COPY RFM A109E APPENDIX 42 Rotation of the course knob in NAV, VOR APR, ILS or BC modes while FD system is in CAP condition, can falsely trigger the over station sensor and gives a degraded performance in the system.
Page 924 UNMAINTAINED COPY RFM A109E APPENDIX 42 Figure 7-1. EFIS Fan (if installed) - Controls and Indicators. Page 16 of 16 Rev. 42...
Page 925 UNMAINTAINED COPY RFM A109E APPENDIX 43 E.A.S.A. Approval N° 2004-1960 dated 3 March 2004 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 926 UNMAINTAINED COPY RFM A109E APPENDIX 43 TABLE OF CONTENTS Page PART I - E.A.S.A. APPROVED SECTION 1 - LIMITATIONS TYPE OF OPERATION 3 of 10 AIRSPEED LIMITATIONS (KIAS) 3 of 10 CENTER OF GRAVITY LIMITATIONS 3 of 10 ALTITUDE LIMITATIONS...
Page 927 UNMAINTAINED COPY RFM A109E APPENDIX 43 SECTION 1 - LIMITATIONS TYPE OF OPERATION Activation of Nightsun Searchlight SX-5 in IFR condition is prohibited. AIRSPEED LIMITATIONS (KIAS) Maximum airspeed (V : 140 KIAS. CENTER OF GRAVITY LIMITATIONS After Nightsun Searchlight SX-5 installation the new empty weight and C.G.
Page 928 UNMAINTAINED COPY RFM A109E APPENDIX 43 PLACARDS Page 4 of 10 E.A.S.A. Approved...
Page 929 UNMAINTAINED COPY RFM A109E APPENDIX 43 SECTION 2 - NORMAL PROCEDURES PREFLIGHT CHECKS PILOT’S DAILY PREFLIGHT CHECK (First flight of the day) AREA N° 1 (Helicopter nose) Nightsun Searchlight SX-5 : Condition and security. Wiring properly connected. Lens for cleanliness.
Page 930 UNMAINTAINED COPY RFM A109E APPENDIX 43 NIGHTSUN SEARCHLIGHT OPERATING PROCEDURE CAUTION Do not operate the Nightsun Searchlight SX-5 after a generator failure. SUN LT switch : Hold in START position ap- proximately 5 seconds or until the ignition has occured.
Page 931 UNMAINTAINED COPY RFM A109E APPENDIX 43 SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES SYSTEM FAILURES ELECTRICAL POWER FAILURE (Helicopters not equipped with emergency bus) Failure of a generator (Helicopters not equipped with emergency bus) : OFF. Refer to paragraph ″Fail- SUN LT switch ure of a generator″...
Page 932 UNMAINTAINED COPY RFM A109E APPENDIX 43 Failure of generator 1 or 2 and generator bus #1 or #2 (Helicopters equipped with emergency bus) : OFF. Refer to paragraph ″Fail- SUN LT switch ure of generator 1 or 2 and generator bus #1 or #2″ of basic Rotorcraft Flight Manual.
Page 933 UNMAINTAINED COPY RFM A109E APPENDIX 43 SECTION 7 - SYSTEMS DESCRIPTION The Nightsun Searchlight SX-5 is provided for enhancing the searchlight capabilities during night or poor visibility conditions. The searchlight SX-5 contains an air cooled, high intensity xenon arc lamp which start rapidly and can be operated continuously or may be stopped and restarted as dictated by operational requirements.
Page 934 UNMAINTAINED COPY RFM A109E APPENDIX 43 1. SUN LT circuit breaker 2. Remote control panel Figure 7-1. Nightsun Searchlight SX-5 control panel. Page 10 of 10...
Page 935 UNMAINTAINED COPY RFM A109E APPENDIX 44 E.A.S.A. Approval N° 2004-1960 dated 3 March 2004 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 936 UNMAINTAINED COPY RFM A109E APPENDIX 44 TABLE OF CONTENTS Page PART I - E.A.S.A. APPROVED SECTION 1 - LIMITATIONS TYPE OF OPERATION 3 of 5 PLACARDS 3 of 5 SECTION 2 - NORMAL PROCEDURES SYSTEMS CHECK 3 of 5 IN FLIGHT...
Page 937 UNMAINTAINED COPY RFM A109E APPENDIX 44 SECTION 1 - LIMITATIONS TYPE OF OPERATION Use of the Skyforce Observer System is permitted only during VFR operations with visual contact of the ground. The navigation can not be based on the Skyforce Observer System.
Page 938 UNMAINTAINED COPY RFM A109E APPENDIX 44 Skyforce Observer display : Carry out the the power-up se- quence until the MAIN MENU page displays. Select MAP key. NOTE The message NO FIX POSSIBLE appears if the GPS has no fix valid data.
Page 939 UNMAINTAINED COPY RFM A109E APPENDIX 44 Skyforce Observer Control Unit : Select OFF. Check that LEDs extinguish. SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES No change. SECTION 4 - PERFORMANCE DATA No change. E.A.S.A. Approved Page 5 of 5 Rev. 47...
Page 940 UNMAINTAINED COPY...
Page 941 UNMAINTAINED COPY RFM A109E APPENDIX 45 E.A.S.A. Approval N° 2005-2351 dated 14 March 2005 The information contained herein supplements the information of the basic Rotorcraft Flight Manual. For limitations, procedures and performance data not contained in this appendix, consult the basic Rotorcraft Flight Manual.
Page 942 UNMAINTAINED COPY RFM A109E APPENDIX 45 TABLE OF CONTENTS PART I - E.A.S.A. APPROVED Page SECTION 1 - LIMITATIONS REQUIRED EQUIPMENT 7 of 90 VFR OPERATION 7 of 90 FLIGHT WITH ONE OF THE TWO HELIPILOTS INOPERATIVE 7 of 90...
Page 943 UNMAINTAINED COPY RFM A109E APPENDIX 45 List of Illustrations (Cont.d) Page Figure 4-3. Hovering ceiling - in ground effect - maximum continuous power. 22 of 90 Figure 4-4. Hovering ceiling - out of ground effect - take-off power. 23 of 90 Figure 4-5.
Page 944 UNMAINTAINED COPY RFM A109E APPENDIX 45 List of Illustrations (Cont.d) Page Figure 4-23. Hovering ceiling - in ground effect - take-off power - EAPS off. 46 of 90 Figure 4-24. Hovering ceiling - in ground effect - take-off power - EAPS on.
Page 945 UNMAINTAINED COPY RFM A109E APPENDIX 45 PART II - MANUFACTURER’S DATA SECTION 6 - WEIGHT AND BALANCE 66 of 90 SECTION 7 - SYSTEM DESCRIPTION 66 of 90 SECTION 8 - HANDLING AND SERVICING 66 of 90 SECTION 9 - SUPPLEMENTAL PERFORMANCE...
Page 946 UNMAINTAINED COPY RFM A109E APPENDIX 45 List of Illustrations (Cont.d) Page Figure 9-20. Cruise - Pressure Altitude 15000 ft - ISA. 86 of 90 Figure 9-21. Cruise - Pressure Altitude 15000 ft - ISA +20°C. 87 of 90 Figure 9-22. Hovering ceiling - IGE - OEI - 2.5 minute power.
Page 947 UNMAINTAINED COPY RFM A109E APPENDIX 45 SECTION 1 - LIMITATIONS REQUIRED EQUIPMENT Operations at gross weight greater than 2850 kg up to 3000 kg are permitted provided that the following assembly is installed: — Tail rotor hub and blade assy P/N 109-8131-02-157 —...
Page 948 UNMAINTAINED COPY RFM A109E APPENDIX 45 AIRSPEED LIMITATION - VNE (POWER ON) 15000 14000 13000 12000 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 OAT - ˚C -1000 INDICATED AIRSPEED (PILOT) - KNOTS 109G0040A003 REV B ABHD475B Figure 1-1.
Page 949 UNMAINTAINED COPY RFM A109E APPENDIX 45 WEIGHT LIMITATIONS Maximum gross weight for takeoff and landing : 3000 kg (6613 lbs) NOTE The maximum takeoff and landing weight may be limited by performance data contained in Section 4. CENTER OF GRAVITY LIMITATIONS.
Page 950 UNMAINTAINED COPY RFM A109E APPENDIX 45 Figure 1-2 (sheet 1 of 2). Longitudinal CG limit (metric). Page 10 of 90 E.A.S.A. Approved...
Page 951 UNMAINTAINED COPY RFM A109E APPENDIX 45 Figure 1-2 (sheet 2 of 2). Longitudinal CG limit (english). E.A.S.A. Approved Page 11 of 90...
Page 952 UNMAINTAINED COPY RFM A109E APPENDIX 45 Figure 1-3 (sheet 1 of 2). Lateral CG limit (metric). Page 12 of 90 E.A.S.A. Approved...
Page 953 UNMAINTAINED COPY RFM A109E APPENDIX 45 Figure 1-3 (sheet 2 of 2). Lateral CG limit (english). E.A.S.A. Approved Page 13 of 90...
Page 954 UNMAINTAINED COPY RFM A109E APPENDIX 45 ALTITUDE LIMITATIONS Maximum pressure altitude for takeoff and landing : 10000 ft (3048m) Maximum operating pressure altitude : 15000 ft (4572 m) AMBIENT AIR TEMPERATURE LIMITATIONS The maximum sea level ambient air temperature is +45 °C (+113 degree °F) and decreases with pressure altitude at the standard lapse rate of 2 °C (3.6 °F)
Page 955 UNMAINTAINED COPY RFM A109E APPENDIX 45 PLACARDS FOR GROSS WEIGHT IN EXCESS OF 2850 kg UP TO 3000 kg. − MAXIMUM AIRSPEED AEO: THE LESSER OF 140 KIAS AND Vne − AUTOROTATION OR OEI Vne: SAME AS UP TO 2850 kg −...
Page 956 UNMAINTAINED COPY RFM A109E APPENDIX 45 SECTION 2 - NORMAL PROCEDURES No change. SECTION 3 - EMERGENCY AND MALFUNCTION PROCEDURES No change. Page 16 of 90 E.A.S.A. Approved...
Page 957 UNMAINTAINED COPY RFM A109E APPENDIX 45 SECTION 4 - PERFORMANCE DATA OPERATION VS ALLOWABLE WIND Satisfactory stability and control in rearward and sideward flight has been demonstrated, at all loading conditions for hover in ground effect up to take-off power, from -1000 ft to 7000 ft Hd, in the following wind/ground speed azimuth envelope: Figure 4-1 (Sheet 1 of 2).
Page 958 UNMAINTAINED COPY RFM A109E APPENDIX 45 Figure 4-1 (Sheet 2 of 2). Wind/ground speed azimuth envelope. Page 18 of 90 E.A.S.A. Approved...
Page 959 UNMAINTAINED COPY RFM A109E APPENDIX 45 PERFORMANCE CHARTS This Section includes the performance data for A109E in the following configuration: — helicopter in basic configuration; — helicopter with Heater; — helicopter with Environmental Control System (ECS); — helicopter with Engine Air Particle Separator (EAPS) ON or OFF;...
Page 960 UNMAINTAINED COPY RFM A109E APPENDIX 45 Helicopter in basic configuration — Figure 4-2. Hovering ceiling - in ground effect - take-off power. — Figure 4-3. Hovering ceiling - in ground effect - maximum continuous power. — Figure 4-4. Hovering ceiling - out ground effect - take-off power.
Page 961 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING IN GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % ZERO WIND WHEEL HEIGHT: 3 ft ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 962 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING IN GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % WHEEL HEIGHT: 3 ft ZERO WIND ELECTRICAL LOAD: 150 A TOTAL GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 963 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING OUT OF GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % ZERO WIND ELECTRICAL LOAD: 150 A TOTAL CAUTION: OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V. GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 964 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING OUT OF GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % ZERO WIND ELECTRICAL LOAD: 150 A TOTAL CAUTION: OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V. GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 965 UNMAINTAINED COPY RFM A109E APPENDIX 45 HEIGHT-VELOCITY DIAGRAM The Height - Velocity diagram is to identify the region where, in the event of a single engine failure during take-off, landing or operation near the ground, a combination of airspeed and height above ground exists from which a safe single engine landing on a smooth, level and hard surface cannot be assured (dangerous zone).
Page 966 UNMAINTAINED COPY RFM A109E APPENDIX 45 HEIGHT-VELOCITY DIAGRAM ONE ENGINE INOPERATIVE FOR SMOOTH, LEVEL, HARD SURFACES GROSS WEIGHT: ABOVE 2850 kg (6283 lb) UP TO 3000 kg (6613 lb) DENSITY ALTITUDE: UP TO 7000 ft WITHOUT EAPS AND WITH EAPS OFF/ON...
Page 967 UNMAINTAINED COPY RFM A109E APPENDIX 45 RATE OF CLIMB ALL ENGINES TAKE-OFF POWER ROTOR: 100 % 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2851 to 3000 kg ( 6285 to 6613 lb ) OAT - ˚C...
Page 968 UNMAINTAINED COPY RFM A109E APPENDIX 45 RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2851 to 3000 kg ( 6285 to 6613 lb ) OAT - ˚C...
Page 969 UNMAINTAINED COPY RFM A109E APPENDIX 45 RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 100 % 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2851 to 3000 kg ( 6285 to 6613 lb ) OAT - ˚C...
Page 970 UNMAINTAINED COPY RFM A109E APPENDIX 45 RATE OF CLIMB ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2851 to 3000 kg ( 6285 to 6613 lb ) OAT - ˚C...
Page 971 UNMAINTAINED COPY RFM A109E APPENDIX 45 Helicopter with heater — Figure 4-11. Hovering ceiling - in ground effect - take-off power - heater — Figure 4-12. Hovering ceiling - in ground effect - maximum continuous power - heater on. — Figure 4-13. Hovering ceiling - out of ground effect - take-off power - heater on.
Page 972 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING IN GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % WHEEL HEIGHT: 3 ft HEATER: ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 973 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING IN GROUND EFFECT HOVERING CEILING IN GROUND EFFECT MAXIMUM CONTINUOUS POWER MAXIMUM CONTINUOUS POWER ROTOR: 102 % ROTOR: 102 % WHEEL HEIGHT: 3 ft WHEEL HEIGHT: 3 ft HEATER: ON HEATER: ON...
Page 974 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING OUT OF GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % HEATER: ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND CAUTION: OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V. GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 975 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING OUT OF GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % HEATER: ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND CAUTION: OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V. GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 976 UNMAINTAINED COPY RFM A109E APPENDIX 45 RATE OF CLIMB ALL ENGINES TAKE-OFF POWER ROTOR: 100 % 60 kts IAS ELECTRICAL LOAD: 150 A TOTAL HEATER: ON RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2851 to 3000 kg ( 6285 to 6613 lb ) OAT - ˚C...
Page 977 UNMAINTAINED COPY RFM A109E APPENDIX 45 RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS HEATER: ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2851 to 3000 kg ( 6285 to 6613 lb ) OAT - ˚C...
Page 978 UNMAINTAINED COPY RFM A109E APPENDIX 45 Helicopter with Environmental Control System (ECS) — Figure 4-17. Hovering ceiling - in ground effect - take-off power - ECS — Figure 4-18. Hovering ceiling - in ground effect - maximum continuous power - ECS on.
Page 979 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING IN GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % WHEEL HEIGHT: 3 ft E.C.S.: ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 980 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING IN GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % WHEEL HEIGHT: 3 ft E.C.S.: ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 981 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING OUT OF GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % E.C.S.: ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND CAUTION: OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V. GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 982 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING OUT OF GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % E.C.S.: ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND CAUTION: OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V. GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 983 UNMAINTAINED COPY RFM A109E APPENDIX 45 RATE OF CLIMB ALL ENGINES TAKE-OFF POWER ROTOR: 100 % 60 kts IAS E.C.S.: ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2851 to 3000 kg ( 6285 to 6613 lb ) OAT - ˚C...
Page 984 UNMAINTAINED COPY RFM A109E APPENDIX 45 RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS E.C.S.: ON ELECTRICAL LOAD: 150 A TOTAL RATE OF CLIMB - METERS/SECOND GROSS WEIGHT 2851 to 3000 kg ( 6285 to 6613 lb ) OAT - ˚C...
Page 985 UNMAINTAINED COPY RFM A109E APPENDIX 45 Helicopter with Engine Air Particle Separator (EAPS) OFF or ON — Figure 4-23. Hovering ceiling - in ground effect - take-off power - EAPS off. — Figure 4-24. Hovering ceiling - in ground effect - take-off power - EAPS —...
Page 986 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING IN GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % WHEEL HEIGHT: 3 ft EAPS OFF ELECTRICAL LOAD: 150 A TOTAL ZERO WIND GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 987 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING IN GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % WHEEL HEIGHT: 3 ft EAPS ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 988 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING IN GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % WHEEL HEIGHT: 3 ft EAPS OFF ELECTRICAL LOAD: 150 A TOTAL ZERO WIND GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 989 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING IN GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % WHEEL HEIGHT: 3 ft EAPS ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 990 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING OUT OF GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % EAPS OFF ELECTRICAL LOAD: 150 A TOTAL ZERO WIND CAUTION: OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V. GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 991 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING OUT OF GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % EAPS ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND CAUTION: OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V. GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 992 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING OUT OF GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % EAPS OFF ELECTRICAL LOAD: 150 A TOTAL ZERO WIND CAUTION: OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V. GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 993 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING OUT OF GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % EAPS ON ELECTRICAL LOAD: 150 A TOTAL ZERO WIND CAUTION: OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V. GROSS WEIGHT - POUNDS x 100 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 OAT - ˚C...
Page 994 UNMAINTAINED COPY RFM A109E APPENDIX 45 RATE OF CLIMB ALL ENGINES TAKE-OFF POWER ROTOR: 100 % 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL WITH EAPS ON: DECREASE RATE OF CLIMB BY 250 ft/min (1,27m/s) RATE OF CLIMB - METERS/SECOND...
Page 995 UNMAINTAINED COPY RFM A109E APPENDIX 45 RATE OF CLIMB ALL ENGINES MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL WITH EAPS ON: DECREASE RATE OF CLIMB BY 200 ft/min (1,02 m/s) RATE OF CLIMB - METERS/SECOND...
Page 996 UNMAINTAINED COPY RFM A109E APPENDIX 45 RATE OF CLIMB ONE ENGINE INOPERATIVE 2.5 MINUTE POWER ROTOR: 100 % 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL WITH EAPS ON: DECREASE RATE OF CLIMB BY 100 ft/min (0,51 m/s)
Page 997 UNMAINTAINED COPY RFM A109E APPENDIX 45 RATE OF CLIMB ONE ENGINE INOPERATIVE MAXIMUM CONTINUOUS POWER ROTOR: 100 % 60 kts IAS EAPS OFF ELECTRICAL LOAD: 150 A TOTAL WITH EAPS ON: DECREASE RATE OF CLIMB BY 100 ft/min (0,51 m/s)
Page 998 UNMAINTAINED COPY RFM A109E APPENDIX 45 Helicopter with Engine Air Particle Separator (EAPS) and Heater or Environmental Control System (ECS). — Figure 4-35. Hovering ceiling - in ground effect - take-off power - EAPS off/on - Heater or ECS on.
Page 999 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING IN GROUND EFFECT TAKE-OFF POWER ROTOR: 102 % WHEEL HEIGHT: 3 ft EAPS OFF ELECTRICAL LOAD: 150 A TOTAL ZERO WIND HEATER OR E.C.S. ON WITH EAPS ON: DECREASE GROSS WEIGHT BY 40 kg (88 lb)
Page 1000 UNMAINTAINED COPY RFM A109E APPENDIX 45 HOVERING CEILING IN GROUND EFFECT MAXIMUM CONTINUOUS POWER ROTOR: 102 % WHEEL HEIGHT: 3 ft EAPS OFF ELECTRICAL LOAD: 150 A TOTAL ZERO WIND HEATER OR E.C.S. ON WITH EAPS ON: DECREASE GROSS WEIGHT BY 50 kg (110 lb)

AGUSTA A109E Flight Manual

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