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.
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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
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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
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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
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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
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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
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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
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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
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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
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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 +5C 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 ..................................... 750C
Corrected indicated TOT engine 1..................... 755C
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
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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
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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
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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
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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
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