RFMS
RFMS 1135-RFMS-1 EUROCOPTER EC135 P2, P2+ EASA APPROVED ROTORCRAFT FLIGHT MANUAL SUPPLEMENT for the EUROCOPTER EC135 P2, P2+ HELICOPTER EQUIPPED WITH FDC/aerofilter INLET BARRIER FILTER SYSTEM REG. NO. SERIAL NO. This supplement must be attached to the EASA Approved Rotorcraft Flight Manual (RFM), when the FDC/aerofilter Inlet Barrier Filter System is installed in accordance with EASA Supplemental Type Certificate (STC) 10038920. The information contained herein supplements information of the basic Flight Manual. For Limitations, Normal and Emergency Procedures, and Performance information not contained in this supplement, consult the basic Rotorcraft Flight Manual. Page 1 of 14 Revision B RFMS EUROCOPTER EC135 P2, P2+ 1135-RFMS-1 RECORD OF REVISIONS When updated, this document is revised in its entirety. APPROVED BY FAA ON BEHALF OF EASA: 15-APR-2014 Page 2 of 14 Revision B RFMS EUROCOPTER EC135 P2, P2+ 1135-RFMS-1 TABLE OF CONTENTS SECTION 1 - GENERAL .......................................................................................... 4 SECTION 2 - LIMITATIONS ..................................................................................... 5 2.1 - FILTER ELEMENT (GROUND AND FLIGHT) .............................................. 5 2.2 - FLIGHT LIMITS ............................................................................................ 5 2.3 - AMBIENT AIR TEMPERATURE LIMITATIONS ........................................... 5 2.4 - TAKEOFF ..................................................................................................... 5 SECTION 3 - EMERGENCY PROCEDURES ........................................................... 6 3.1 - LOW INLET PRESSURE ............................................................................. 6 3.2 - SNSR or MAINT ANNUNCIATION ON FHM IS ILLUMINATED ................... 7 SECTION 4 - NORMAL PROCEDURES .................................................................. 8 4.1 - EXTERIOR CHECK...................................................................................... 8 4.2 - ENGINE PRESTART CHECK ...................................................................... 9 SECTION 5 - PERFORMANCE .............................................................................. 10 SECTION 6 - MASS AND BALANCE .................................................................... 12 SECTION 7 - SYSTEM DESCRIPTION .................................................................. 12 APPROVED BY FAA ON BEHALF OF EASA: 15-APR-2014 Page 3 of 14 Revision B RFMS 1135-RFMS-1 EUROCOPTER EC135 P2, P2+ SECTION 1 - GENERAL This supplement provides the changes in the operating limitations, normal and emergency procedures and performance information unique to the Eurocopter EC135 P2, P2+ rotorcraft, equipped with the FDC/aerofilter Engine Inlet Barrier Filter System. This supplement must be attached to the applicable approved EASA Rotorcraft Flight Manual. For limitations, procedures, and performance information not contained in the supplement, consult the applicable Rotorcraft Flight Manual or Supplement. Noise Levels Noise levels (corrected values) when equipped with the Engine Inlet Barrier Filter System are presented below. Model (gross mass) Flight Phase Measurements according to 14CFR Part 36 Appendix J and ICAO Annex 16 Chapter 11 (dB) Limits according to 14CFR Part 36 Appendix J at given gross mass (dB) Limits according to ICAO Annex 16 at given gross mass (dB) EC135 P2+ (2910 kg) Flyover 83.4 87.7 85.1 EC135 P2 (2835 kg) Flyover 83.4 87.5 85.0 APPROVED BY FAA ON BEHALF OF EASA: 15-APR-2014 Page 4 of 14 Revision B RFMS EUROCOPTER EC135 P2, P2+ 1135-RFMS-1 SECTION 2 - LIMITATIONS 2.1 - FILTER ELEMENT (GROUND AND FLIGHT) Engine operations without the filter elements installed are PROHIBITED. 2.2 - FLIGHT LIMITS The limitations of the basic flight manual remain applicable. NOTE: Operations in falling and/or blowing snow have been demonstrated in onequarter mile or greater visibility conditions when equipped with the Engine Inlet Barrier Filter System. Minimize exposure time in ground and IGE hover operations. Snow accumulations on airframe and filter are more probable in these conditions. Exercise caution when operating in snow. Maintain visual contact with ground and any obstacles at all times. 2.3 - AMBIENT AIR TEMPERATURE LIMITATIONS To maintain the engine oil temperatures within limits, observe the following environmental operating condition during flight planning: Maximum air temperature is …………………………………. ISA + 37.0 C (max. + 48 C) 2.4 - TAKEOFF Takeoff is PROHIBITED when: (a) One or more amber bar-graph segments illuminated on the FHM, and/or (b) CAUT annunciation illuminated on the FHM, and/or (c) LOW INLET PRESSURE annunciation illuminated on IBF ALT AIR Switches. NOTE: Takeoff is permitted if amber bar-graph segments extinguish with activation of IBF ALT AIR Switches. CAUT and LOW INLET PRESSURE annunciations will not extinguish until reset. Reset the FHM (Push and Hold FHM RESET button for 5 seconds) and monitor engine instruments to ensure engine parameters remain within limits (Red Lines). Service the filter system prior to next flight. If engine parameters cannot be maintained within limits, land as soon as possible and conduct applicable maintenance prior to next flight. APPROVED BY FAA ON BEHALF OF EASA: 15-APR-2014 Page 5 of 14 Revision B RFMS 1135-RFMS-1 EUROCOPTER EC135 P2, P2+ SECTION 3 - EMERGENCY PROCEDURES 3.1 - LOW INLET PRESSURE SYMPTOM: One or more amber bar-graph segment(s) illuminated on the FHM, and/or LOW INLET PRESSURE annunciation illuminated on the IBF ALT AIR Switches (Instrument Panel), and/or CAUT annunciation illuminated on the FHM and/or Unexplained increase in engine TOT. or PROBABLE FAULT: Filter blockage has reached the maximum allowable level. ACTION: Both IBF ALT AIR Switches – Push BYP DOOR OPEN annunciation will illuminate on both switches. CAUT and LOW INLET PRESSURE annunciations will not extinguish. Amber bar-graph segments on FHM will extinguish. a. Verify that all amber bar-graph segments on the FHM extinguish, then press and hold RESET on the FHM to clear the CAUT and LOW INLET PRESSURE annunciations. BYP DOOR OPEN annunciation will remain illuminated. Continue mission and monitor engine instruments to ensure engine parameters remain within limits (Red Lines). If engine parameters cannot be maintained within limits, land as soon as possible. b. If any amber bar-graph segments on the FHM remain illuminated, monitor engine instruments and land as soon as practicable. If engine parameters cannot be maintained within limits, land as soon as possible. Remaining amber bar-graph segment(s) on the FHM likely indicates a malfunction of one or both bypass doors. c. If operating in falling and/or blowing snow, monitor engine instruments and land as soon as practicable. If engine parameters cannot be maintained within limits, land as soon as possible. Perform applicable maintenance and conduct a power check prior to next flight. APPROVED BY FAA ON BEHALF OF EASA: 15-APR-2014 Page 6 of 14 Revision B RFMS 1135-RFMS-1 EUROCOPTER EC135 P2, P2+ 3.2 - SNSR or MAINT ANNUNCIATION ON FHM IS ILLUMINATED SYMPTOM: SNSR or MAINT annunciation is illuminated, regardless of illumination of bargraph segments. or PROBABLE FAULT: Differential Pressure Transducer(s) disconnected or failed. ACTION: Verify engine parameters are within limits (Red Lines). If engine parameters are not maintained within limits, open both Bypass Doors by pushing both IBF ALT AIR Switches and monitor engine parameters. If engine parameters cannot be maintained within limits, land as soon as possible. Refer to Inlet Barrier Filter System Instructions for Continued Airworthiness, 1135-SERIES-ICA-5, to determine maintenance action. Only maintenance action can reset the SNSR or MAINT annunciation. APPROVED BY FAA ON BEHALF OF EASA: 15-APR-2014 Page 7 of 14 Revision B RFMS 1135-RFMS-1 EUROCOPTER EC135 P2, P2+ SECTION 4 - NORMAL PROCEDURES 4.1 - EXTERIOR CHECK Perform the following checks prior to the first flight of the day or each flight if snow or freezing rain has fallen: Cabin Top: Filter Elements – Check for damage and security. Verify filter material is in good condition. Filter Element Surfaces and surrounding areas – Must be free of accumulated debris, snow, ice, slush, etc before each flight. Bypass Doors – Check for damage and security. Verify doors are closed. No ice around door edges. Overhead Panel: IBF circuit breakers (2) – In Instrument Panel: BAT MSTR switch – ON IBF ALT AIR Switches – Push both to open Bypass doors. – Check BYP DOOR OPEN annunciation and visually check that doors open fully. Transmission oil filter clogging indicator pin – Check in IBF ALT AIR Switches – Push both to close Bypass doors. – Check that annunciation extinguishes and visually check that doors close fully. APPROVED BY FAA ON BEHALF OF EASA: 15-APR-2014 Page 8 of 14 Revision B RFMS 1135-RFMS-1 EUROCOPTER EC135 P2, P2+ 4.2 - ENGINE PRESTART CHECK Perform the following checks prior to each flight: Overhead Panel: IBF circuit breakers (2) – In Instrument Panel: BAT MSTR switch – ON Filter Health Monitor – Push and Hold TEST button. Verify all monitor bar-graph segments and annunciations illuminate. – Release TEST button – Push and Hold (5 seconds) RESET button. Verify all monitor bar-graph segments and annunciations extinguish. – Release RESET button NOTES: For any malfunction of the FHM, refer to Instructions for Continued Airworthiness 1135-SERIES-ICA-5 to determine maintenance action. APPROVED BY FAA ON BEHALF OF EASA: 15-APR-2014 Page 9 of 14 Revision B RFMS 1135-RFMS-1 EUROCOPTER EC135 P2, P2+ SECTION 5 - PERFORMANCE Engine performance is slightly reduced when the FDC/aerofilter Inlet Barrier Filter is installed and may decrease further as the filter becomes contaminated. It is the responsibility of the pilot/operator to conduct power checks to determine if the engine, as equipped with the IBF, meets published power check criteria and performance. Conduct power checks in accordance with appropriate approved Rotorcraft Flight Manual (RFM) and/or Rotorcraft Flight Manual Supplement (RFMS). Recorded TOT and N1 readings are to be corrected as noted below prior to comparison to the maximum TOT and N1 corresponding to the prevailing ambient conditions. Additional power checks are at the discretion of the pilot/operator and based on the operating environments. Except as noted below, ground and inflight power check procedures and criteria are unchanged from the basic RFM. Performance for the basic engine air inlet published in the RFM and/or appropriate RFMS is assured if power checks result in N1 and TOT margins that are at least zero. Ground Power Check: Increase indicated TOT by +5C and increase indicated N1 by 0.3% prior to comparison with maximum TOT and N1, corresponding to the prevailing ambient conditions. Example: Indicated TOT engine 1 ..................................... 750C Corrected indicated TOT engine 1..................... 755C TOT Margin engine 1 = Power Check Chart maximum TOT – Corrected Indicated TOT engine 1 Indicated N1 engine 1........................................ 92.0% Corrected indicated N1 engine 1 ....................... 92.3% N1 Margin engine 1 = Power Check Chart maximum N1 – Corrected Indicated N1 engine 1 If results meet basic RFM ground power check criteria: Operate aircraft in accordance with basic RFM performance data. APPROVED BY FAA ON BEHALF OF EASA: 15-APR-2014 Page 10 of 14 Revision B RFMS EUROCOPTER EC135 P2, P2+ 1135-RFMS-1 Ground Power Check (continued): If results do not meet basic RFM ground power check criteria: Refer to appropriate maintenance manual to determine cause of power loss and perform new power check. If results still do not meet basic RFM power check criteria: o It is recommended that the filter element be serviced and a new power check be performed. Inflight Power Check: Inflight power check procedures and criteria are unchanged from the basic RFM. Hover No change to approved hover ceiling with respect to basic helicopter performance data. Climb No change to approved climb performance with respect to basic helicopter performance data. APPROVED BY FAA ON BEHALF OF EASA: 15-APR-2014 Page 11 of 14 Revision B RFMS 1135-RFMS-1 EUROCOPTER EC135 P2, P2+ SECTION 6 - MASS AND BALANCE Refer to Equipment List entries in Section 6 of the basic Flight Manual. SECTION 7 - SYSTEM DESCRIPTION The FDC/aerofilter Engine Inlet Barrier Filter System consists of two filter elements installed in front of the engine intakes. The elements consist of porous media treated with oil to enhance filtration performance. Differential pressure sensors located behind each element, measure the differential pressure across the filters and hence the level of blockage. Blockage level is displayed as bar-graph segments to the pilot on the Filter Health Monitor (FHM). The FHM also alerts the pilot when filter element servicing is required and when unrestricted bypass air is needed. Two different FHM models are approved for use with this filter system. Some annunciations and display elements differ between the two models. FHM annunciations are as follows: An amber SNSR or MAINT annunciation (depending on installed FHM model) indicates a maintenance condition exists. This annunciation will remain illuminated until extinguished by corrective maintenance action and cannot be reset by pilot action. An amber CAUT annunciation indicates when the filter elements have exceeded the maximum allowable blockage level. When activated, this annunciation is magnetically latched and will be retained, even without electrical power, until reset in flight or on the ground by pressing RESET on the face of the unit. Simultaneously, the LOW INLET PRESSURE annunciations illuminate on the IBF ALT AIR switches installed on the instrument panel. The FHM and bypass alerts are independent of other aircraft systems – no Master Warning/Caution annunciations will illuminate. The TEST button on the FHM checks all aspects of the unit. Depressing the TEST button will illuminate all bar-graph segments and FHM annunciations, as well as the amber LOW INLET PRESSURE annunciations on the IBF ALT AIR switches. All annunciations illuminated indicate a successful test result. Releasing the TEST button will clear all bar-graph segments but not the CAUT and LOW INLET PRESSURE annunciations, which can only be cleared by pressing and holding the RESET button on the FHM for 5 seconds. Power for the system is provided by two (2) dedicated 28VDC, 1 Amp circuit breakers, labeled IBF #1 and IBF #2, on both left and right Essential or left and right Avionics Essential busses. APPROVED BY FAA ON BEHALF OF EASA: 15-APR-2014 Page 12 of 14 Revision B RFMS 1135-RFMS-1 EUROCOPTER EC135 P2, P2+ Filter Health Monitor (FHM) Both models of FHM are shown below with all display elements illuminated for reference. PN FHM200-1135-3 PN FHM200-1135-1 Annunciations, Locations, and Actions IBF ALT AIR SWITCH FILTER HEALTH MONITOR Annunciation Condition for (Color) Illumination (1) (2) Pilot Action Required In Flight Reset? Maintenance Action Service Filter Elements Before Next Flight Service Filter Monitoring System Before Next Flight CAUT (Amber) High Filter Blockage See section 3.1 Possible SNSR(1) or MAINT (2) (Amber) FHM/System Fault See section 3.2 No Bar-graph Segments 1 - 9(1) or 1 - 5(2) (Green) Normal Condition None No None Bar-graph Segments 10(1) or 6 - 10(2) (Amber) High Filter Blockage No Service Filter Elements Before Next Flight LOW INLET PRESSURE (Amber) High Filter Blockage See section 3.1 Possible Service Filter Elements Before Next Flight BYP DOOR OPEN (Amber) Switch is activated None No None See section 3.1 PN FHM200-1135-3 PN FHM200-1135-1 APPROVED BY FAA ON BEHALF OF EASA: 15-APR-2014 Page 13 of 14 Revision B RFMS 1135-RFMS-1 EUROCOPTER EC135 P2, P2+ FHM Bar-graph Segment and Annunciation Description: Green = (Bar-graph Segments 1 - 9; or 1 - 5, depending on FHM model) Low to moderate filter blockage. Amber = (Bar-graph Segments 10; or 6 - 10, depending on FHM model) Filter Elements have exceeded maximum allowable blockage level. CAUT annunciation on FHM will illuminate. LOW INLET PRESSURE annunciation on IBF ALT AIR switches will illuminate. Pilot Action: See section 3.1. Maintenance Action: Clean and/or replace filter elements per ICA. SNSR or MAINT annunciation, depending on FHM model, will illuminate when one or both pressure sensors have become disconnected and cannot be reset by the pilot. Maintenance is required. Pilot Action: See section 3.2. Maintenance Action: Refer to Inlet Barrier Filter System Instructions for Continued Airworthiness, 1135-SERIES-ICA-5, to determine maintenance action. IBF ALT AIR Switches Two (2) IBF ALT AIR Switches, labeled IBF ALT AIR #1 and IBF ALT AIR #2, are located on the Instrument Panel. Pressing the IBF ALT AIR switches opens and closes the doors. LOW INLET PRESSURE Filter Elements have exceeded maximum allowable blockage level, pilot action and maintenance required. CAUT annunciation on FHM will illuminate. LOW INLET PRESSURE annunciation on IBF ALT AIR switches will illuminate. Pilot Action: See section 3.1. Maintenance Action: Clean and/or replace filter elements per ICA. BYP DOOR OPEN This annunciation indicates that the IBF ALT AIR switch has been activated. APPROVED BY FAA ON BEHALF OF EASA: 15-APR-2014 Page 14 of 14 Revision B
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