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A109S RFM Section 1
Document N109G0040A013 Table of Contents
EASA Approved 01-06-05 Page 1-i
Rev. 1
SECTION 1
LIMITATIONS
TABLE OF CONTENTS
Page
GENERAL ....................................................................................... 1-1
BASIS OF CERTIFICATION ........................................................... 1-1
TYPES OF OPERATION ................................................................. 1-1
MINIMUM FLIGHT CREW............................................................... 1-1
NUMBER OF SEATS ...................................................................... 1-1
WEIGHT LIMITATIONS................................................................... 1-2
CENTER OF GRAVITY LIMITATIONS ........................................... 1-2
AIRSPEED LIMITATIONS............................................................... 1-7
GROUND SPEED LIMITATIONS.................................................... 1-7
ON CONCRETE OR EVEN SURFACES.................................... 1-7
ON UNPREPARED OR UNEVEN SURFACES.......................... 1-7
WIND SPEED LIMITATIONS FOR ROTOR STARTING AND
STOPPING ...................................................................................... 1-7
ALTITUDE LIMITATIONS ............................................................. 1-10
AMBIENT AIR TEMPERATURE LIMITATIONS ........................... 1-10
SLOPE LIMITATIONS................................................................... 1-10
SLIDING DOORS OPENED OR REMOVED ................................ 1-11
--- For Training Use Only ---
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Section 1 A109S RFM
Table of Contents Document N109G0040A013
Page 1-ii 01-06-05 EASA Approved
Rev. 1
Page
POWER PLANT LIMITATIONS.....................................................1-12
GAS GENERATOR SPEED (N1)..............................................1-12
POWER TURBINE SPEED (N2)...............................................1-12
TURBINE OUTLET TEMPERATURE (TOT) ............................1-13
OIL PRESSURE .......................................................................1-14
OIL TEMPERATURE ...............................................................1-14
ENGINE STARTER LIMITATIONS...........................................1-14
ROTOR LIMITATIONS (NR)..........................................................1-15
POWER-ON (AEO) ...................................................................1-15
POWER-ON (OEI) ....................................................................1-15
POWER-OFF ............................................................................1-15
TRANSMISSION LIMITATIONS....................................................1-16
TORQUE (TRQ)........................................................................1-16
ALL ENGINES OPERATING (AEO) .........................................1-16
ONE ENGINE INOPERATIVE (OEI).........................................1-16
OIL PRESSURE........................................................................1-17
OIL TEMPERATURE ................................................................1-17
FUEL SYSTEM LIMITATIONS ......................................................1-17
FUEL PRESSURE (PSI) ...........................................................1-17
FUEL QUANTITY......................................................................1-17
TOTAL UNUSABLE FUEL........................................................1-17
FUEL TYPES ............................................................................1-18
EMERGENCY FUELS ..............................................................1-19
LUBRICANTS................................................................................1-20
AUTHORIZED ENGINE OILS...................................................1-20
AUTHORIZED TRANSMISSION OILS .....................................1-21
HYDRAULIC SYSTEMS LIMITATIONS........................................1-22
MAIN FLUID PRESSURE ........................................................1-22
UTILITY SYSTEM - NORMAL - FLUID PRESSURE ...............1-22
UTILITY SYSTEM - EMERGENCY - FLUID PRESSURE ..........1-22
APPROVED FLUIDS ................................................................1-22
--- For Training Use Only ---
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A109S RFM Section 1
Document N109G0040A013 Table of Contents
EASA Approved 01-06-05 Page 1-iii
Page
GENERATOR LOAD LIMITATIONS............................................. 1-23
AVIONICS LIMITATIONS.............................................................. 1-23
AUTOMATIC FLIGHT CONTROL SYSTEM LIMITATIONS......... 1-23
FLIGHT WITH ONE HELIPILOT OPERATIVE ONLY .............. 1-23
FLIGHT DIRECTOR LIMITATIONS .............................................. 1-24
ILS APPROACH ....................................................................... 1-24
FLIGHT DIRECTOR MODES MINIMUM USE HEIGHT (MUH)1-24
ROTOR BRAKE LIMITATION (IF INSTALLED) ........................... 1-24
MISCELLANEOUS LIMITATIONS ................................................ 1-24
BAGGAGE COMPARTMENT LIMITATIONS ........................... 1-24
PLACARDS .................................................................................. 1-25
INSTRUMENT MARKINGS ........................................................ 1-28
ELECTRONIC DISPLAY UNIT FORMATS................................... 1-29
--- For Training Use Only ---
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Section 1 A109S RFM
Table of Contents Document N109G0040A013
Page 1-iv 01-06-05 EASA Approved
Rev. 1
LIST OF FIGURES
Figure Page
WEIGHT AND CENTER OF GRAVITY ENVELOPES
Figure 1-1 Weight and Longitudinal CG Envelope.......................1-3
Figure 1-2 Weight and Longitudinal CG Envelope.......................1-4
Figure 1-3 Weight and Lateral CG Envelope ...............................1-5
Figure 1-4 Weight and Lateral CG Envelope ...............................1-6
FLIGHT ENVELOPES
Figure 1-5 Airspeed Limitation Vne (Power-ON)....................... 1-8A
Figure 1-6 Altitude / OAT Envelope .............................................1-9
PLACARDS
Figure 1-7 Cockpit placards (Sheet 1 of 2) ................................1-25
Figure 1-7 Cockpit placards (Sheet 2 of 2) ................................1-26
Figure 1-8 Baggage compartment placards...............................1-27
INSTRUMENTS MARKINGS
Figure 1-9 Airspeed Indicator.....................................................1-28
Figure 1-10 EDU1 - START Mode (AEO) (Typical) .....................1-30
Figure 1-11 EDU1 - CRUISE Mode (AEO) (Typical)....................1-31
Figure 1-12 EDU1 - OEI Mode (Typical) ......................................1-32
Figure 1-13 EDU1 - AUTOROTATION Mode (Typical)................1-33
Figure 1-14 EDU2 - MAIN Mode (Typical) ...................................1-34
Figure 1-15 EDU2 - AUXILIARY Mode (Typical) .........................1-35
Figure 1-16 EDU1 and EDU2 - REVERSIONARY Mode
(Typical) ....................................................................1-36
Figure 1-17 EDU1 - Gas Generator Speed (AEO).......................1-37
Figure 1-18 EDU1 - Gas Generator Speed (OEI) ........................1-38
Figure 1-19 EDU1 - Turbine Outlet Temperature (AEO)..............1-39
Figure 1-20 EDU1 - Turbine Outlet Temperature (OEI) ...............1-40
Figure 1-21 EDU1 - Torque (AEO)...............................................1-41
Figure 1-22 EDU1 - Torque (OEI) ................................................1-42
Figure 1-23 EDU1 - Rotor Power Turbine Speed (AEO) .............1-43
Figure 1-24 EDU1 - Rotor Power Turbine Speed (OEI)...............1-44
Figure 1-25 EDU1 - Rotor Speed (Power-OFF)...........................1-45
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A109S RFM Section 1
Document N109G0040A013 Table of Contents
EASA Approved 01-06-05 Page 1-v
Figure Page
Figure 1-26 EDU2 (MAIN) - Engine Oil Pressure ........................ 1-46
Figure 1-27 EDU2 (MAIN) - Engine Oil Temperature .................. 1-47
Figure 1-28 EDU2 (MAIN) - Transmission Oil Pressure .............. 1-48
Figure 1-29 EDU2 (MAIN) - Transmission Oil Temperature ........ 1-49
Figure 1-30 EDU2 (MAIN/AUXILIARY) - Main Hydraulic
System Pressure ...................................................... 1-50
Figure 1-31 EDU2 (MAIN) - Fuel Pressure .................................. 1-51
Figure 1-32 EDU2 (AUXILIARY) - Ammeter ................................ 1-52
Figure 1-33 EDU2 (AUXILIARY) - Utility Hydraulic System
Pressure (Normal) .................................................... 1-53
Figure 1-34 EDU2 (AUXILIARY) - Utility Hydraulic System
Pressure (Emergency).............................................. 1-54
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Section 1 A109S RFM
Table of Contents Document N109G0040A013
Page 1-vi 01-06-05 EASA Approved
LIST OF TABLES
Table Page
Table 1-1 Authorized Fuels ...........................................................1-18
Table 1-2 Emergency Fuels ..........................................................1-19
Table 1-3 Authorized Lubricating Oils, Type II (5 Centistokes) .....1-20
Table 1-4 Authorized Lubricating Oils ...........................................1-21
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A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-1
SECTION 1
LIMITATIONS
GENERAL
Compliance with Section 1 of this manual is mandatory.
The helicopter must also be operated in accordance with the appropri-
ate operating rules.
BASIS OF CERTIFICATION
The helicopter is certified under JAR / FAR 27 as detailed in the Type
Certificate Data Sheet EASA R005.
TYPES OF OPERATION
The A109S helicopter, in its basic configuration, is approved for Day/
Night VFR / IFR operations in non-icing conditions.
No aerobatic manoeuvres are permitted.
MINIMUM FLIGHT CREW
The minimum required flight crew consists of one pilot who shall oper-
ate the helicopter from the right crew seat.
The left crew seat may be used for an additional pilot when the
approved dual controls and co-pilot instruments are installed.
NUMBER OF SEATS
Eight, including the pilot.
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Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-2 01-06-05 EASA Approved
Rev. 1
WEIGHT LIMITATIONS
Maximum gross weight for
ground taxiing and towing ......................................... 3205 kg (7066 lb)
Maximum take-off gross weight................................. 3175 kg (7000 lb)
Minimum gross weight for flight................................. 2050 kg (4519 lb)
CENTER OF GRAVITY LIMITATIONS
Longitudinal limits........................................... See Figures 1-1 and 1-2
Lateral limits ................................................... See Figures 1-3 and 1-4
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A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-3
Rev. 1
Figure 1-1 Weight and Longitudinal CG Envelope
(metric units)
3330 3430
2050
2970
2050
3249
3225
3415 3520
2910
3175
2370
1600
1800
2000
2200
2400
2600
2800
3000
3200
3400
3200 3250 3300 3350 3400 3450 3500 3550
Longitudinal Station (mm)
Gro
ss W
eig
ht
(kg
)
ICN-0B-A-151000-G-A0126-00032-A-01-1 109G1560A001 REV.A
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Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-4 01-06-05 EASA Approved
Rev. 1
Figure 1-2 Weight and Longitudinal CG Envelope
(imperial units)
138,6134,4 138,6
4519
6548
4519
127,0
127,9
131,1 135,0
5225
6415
7000
3500
4000
4500
5000
5500
6000
6500
7000
7500
126 128 130 132 134 136 138 140
Longitudinal Station (in)
Gro
ss W
eig
ht
(lb
s)
ICN-0B-A-151000-G-A0126-00033-A-01-1 109G1560A001 REV.A
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A109S RFM Section 1
Document N109G0040A013 Limitations
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Rev. 1
Figure 1-3 Weight and Lateral CG Envelope
(metric units)
-80
-80 80
80
-40 40
2450 2450
20502050
3175 3175
1600
1800
2000
2200
2400
2600
2800
3000
3200
3400
-100 -60 -20 20 60 100
Lateral Station (mm)
Gro
ss
We
igh
t (k
g)
C.L
ICN-0B-A-151000-G-A0126-00034-A-01-1 109G1560A001 REV.A
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Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-6 01-06-05 EASA Approved
Rev. 1
Figure 1-4 Weight and Lateral CG Envelope
(imperial units)
-3,1
-3,1
-1,6 1,6
3,1
-3,1 3,1
5401
4519 4519
5401
7000 7000
3500
4000
4500
5000
5500
6000
6500
7000
7500
-4,00 -3,00 -2,00 -1,00 0,00 1,00 2,00 3,00 4,00
Late ral Station (in)
Gro
ss
We
igh
t (l
bs
)
C.L
ICN-0B-A-151000-G-A0126-00035-A-01-1 109G1560A001 REV.A
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A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-7
Rev. 1
AIRSPEED LIMITATIONS
VNE (Power-ON)............................................................ See Figure 1-5
VNE (Power-OFF / OEI)..............................VNE (Power-ON) - 40 KIAS
Vmini (minimum IFR airspeed).................................................55 KIAS
Maximum landing gear operating airspeed (VLO) ..................140 KIAS
Maximum landing gear extended airspeed (VLE) ...................140 KIAS
Minimum airspeed in autorotation
(without close external reference) ............................................60 KIAS
GROUND SPEED LIMITATIONS
ON CONCRETE OR EVEN SURFACES
Maximum speed for running take-off and landing ................... 40 knots
Maximum taxiing speed (nose wheel unlocked)
- Straight.................................................................................. 20 knots
- Turning .................................................................................. 10 knots
ON UNPREPARED OR UNEVEN SURFACES
Maximum speed for running take-off and landing ................... 20 knots
Maximum taxiing speed (nose wheel unlocked)
- Straight.................................................................................. 20 knots
- Turning .................................................................................. 10 knots
WIND SPEED LIMITATIONS FOR ROTOR STARTINGAND STOPPING
The maximum wind speed for rotor starting and stopping is 40 knots.
--- For Training Use Only ---
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Page 1-8 01-06-05 EASA Approved
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A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-9
Rev. 1
Figure 1-6 Altitude / OAT Envelope
--- For Training Use Only ---
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Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-10 01-06-05 EASA Approved
Rev. 1
ALTITUDE LIMITATIONS
Maximum altitude for take-off and landing .....................see Figure 1-6
Maximum operating altitude ...........................................see Figure 1-6
AMBIENT AIR TEMPERATURE LIMITATIONS
Minimum ambient air temperature .................................-25 C (-13 F)
Maximum sea level ambient air temperature .................50 C (122 F)
The maximum ambient air temperature for operation decreases with
pressure altitude at the standard lapse rate of 2 C (3.6 F) every
1,000 ft (305 m) up to 20,000 ft (6,095 m).
SLOPE LIMITATIONS
CAUTION
While operating on slopes, care must be
taken to avoid touching tail.
Slope operations are prohibited on surfaces with a slope angle
(degrees) above the following:
Maximum lateral slope angle ..................................................... 10 deg
Maximum longitudinal slope angle ............................................. 10 deg
--- For Training Use Only ---
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A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-11
SLIDING DOORS OPENED OR REMOVED(Applicable only with passenger door modification
P/N 109-0814-35 installed)
Flight with either one or both sliding doors open or removed is prohib-
ited if passenger door modification P/N 109-0814-35 is not installed.
VNE with one or both doors open or removed ..........................75 KIAS
Maximum airspeed for door opening or closing .......................50 KIAS
Note
When passenger cabin doors are open or
removed, check the helicopter Weight and
Balance.
IFR operation is prohibited with either one or both sliding doors locked
in open position or removed.
--- For Training Use Only ---
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Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-12 01-06-05 EASA Approved
POWER PLANT LIMITATIONS
The helicopter is powered by two (2) Pratt and Whitney PW207C tur-
boshaft engines.
GAS GENERATOR SPEED (N1)
All Engines Operating (AEO)
Continuous Operation ........................................................50 to 97.1%
Take-Off Range (5 minutes) ............................................97.2 to 99.7%
Maximum.....................................................................................99.7%
Transient (20 seconds)..............................................................104.1%
One Engine Inoperative (OEI)
Continuous Operation ........................................................50 to 99.7%
2.5 minutes Range ........................................................99.8 to 103.0%
Maximum...................................................................................103.0%
Transient (20 seconds)..............................................................104.1%
Note
Transient range must not be used intentionally.
POWER TURBINE SPEED (N2)
All Engines Operating (AEO)
Transient ........................................................................................95%
Minimum.........................................................................................99%
Continuous Operation (except takeoff and landing) ............99 to 101%
Take-Off and Landing (below Vy ..................................................102%
Maximum......................................................................................102%
Transient (20 seconds).............................................................. 112.4%
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A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-13
One Engine Inoperative (OEI)
Transient ........................................................................................85%
Minimum.........................................................................................90%
Cautionary Range .................................................................90 to 98%
Continuous Operation (except takeoff and landing) ........... 99 to 101%
Take-Off and Landing (below Vy) .................................................102%
Maximum......................................................................................102%
Transient (20 seconds).............................................................. 112.4%
Note
Transient range must not be used intentionally.
TURBINE OUTLET TEMPERATURE (TOT)
Engine Starting
Maximum at Starting (2 seconds)...............................................875 C
All Engines Operating (AEO)
Maximum Continuous ................................................................840 C
Take-Off Range (5 minutes) ............................................841 to 900 C
Transient (20 seconds).............................................................1000 C
One Engine Inoperative (OEI)
Maximum Continuous ................................................................900 C
2.5 minutes Range ..........................................................901 to 970 C
Transient (20 seconds).............................................................1000 C
Note
Transient range must not be used intentionally.
--- For Training Use Only ---
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Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-14 01-06-05 EASA Approved
Rev. 1
OIL PRESSURE
Note
The oil pressure limits vary as a function of
the gas generator speed.
Minimum for ground idle....................................... Above lower red line
Continuous Operation .......................................... ..............Green band
(variable as a function of N1)
Cautionary Range .............................................. ..............Yellow bands
(variable as a function of N1)
Transient (10 minutes) .............................................................. 200 psi
Maximum during engine starting ............................................... 200 psi
Note
The engine can operate with oil pressure up
to 200 psi after start or if the oil temperature
drops significantly below 71 C. The opera-
tion at an oil pressure up to 200 psi is per-
mitted for a period of 10 minutes. The oil
pressure will decrease as the oil tempera-
ture rises.
OIL TEMPERATURE
Continuous Operation ....................................................... 10 to 125 C
Maximum....................................................................................125 C
ENGINE STARTER LIMITATIONS
The engine starter duty cycle is the following:
- 30 seconds on, 1 minute off;
- 30 seconds on, 1 minute off;
- 30 seconds on, 30 minutes off.
--- For Training Use Only ---
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A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-15
ROTOR LIMITATIONS (NR)
POWER-ON (AEO)
Transient ........................................................................................95%
Minimum.........................................................................................99%
Continuous Operation (except take-off and landing)...........99 to 101%
Take-Off and Landing (below Vy) .................................................102%
Maximum......................................................................................102%
POWER-ON (OEI)
Transient ........................................................................................85%
Minimum ........................................................................................90%
Cautionary Range .................................................................90 to 98%
Continuous Operation (except take-off and landing)...........99 to 101%
Take-Off and Landing (below Vy) .................................................102%
Maximum......................................................................................102%
POWER-OFF
Transient ........................................................................................90%
Minimum.........................................................................................95%
Continuous Operation ......................................................... 95 to 110%
Maximum...................................................................................... 110%
--- For Training Use Only ---
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Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-16 01-06-05 EASA Approved
TRANSMISSION LIMITATIONS
TORQUE (TRQ)
ALL ENGINES OPERATING (AEO)
Maximum Continuous ..................................................................100%
Take-Off Range (5 minutes) ..............................................101 to 107%
Maximum......................................................................................107%
Transient (6 seconds)................................................................... 110%
ONE ENGINE INOPERATIVE (OEI)
Maximum Continuous ..................................................................133%
2.5 minutes Range ............................................................134 to 162%
Maximum......................................................................................162%
Transient (6 seconds)...................................................................173%
Note
The use of the one engine inoperative (OEI)
2.5 minutes range rating is intended for
emergency use only, when one engine
becomes inoperative due to an actual mal-
function.
OEI operations for maintenance or training
purposes shall be limited to the maximum
continuous OEI power rating.
Note
Transient range must not be used intentionally.
--- For Training Use Only ---
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A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-17
Rev. 1
OIL PRESSURE
Minimum...................................................................................... 30 psi
Continuous Operation ........................................................ 30 to 50 psi
Cautionary Range .............................................................. 51 to 70 psi
Maximum..................................................................................... 70 psi
OIL TEMPERATURE
Continuous Operation .........................................................0 to 120 C
Maximum....................................................................................120 C
FUEL SYSTEM LIMITATIONS
FUEL PRESSURE
Cautionary Range .................................................................. 0 to 7 psi
Continuous Operation .......................................................... 8 to 25 psi
Maximum..................................................................................... 25 psi
FUEL QUANTITY
Total............................................................................................ 460 kg
(575 liters at 0.8 kg/liter)
TOTAL UNUSABLE FUEL
In coordinated flight ...................................................................... 10 kg
(12 liters at 0.8 kg/liter)
--- For Training Use Only ---
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Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-18 01-06-05 EASA Approved
Rev. 1
FUEL TYPES
The fuels shown in Table 1-1 have been authorized for use with the
Pratt & Whitney PW207C engines.
Note
Fuel grades marked with an * 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 unless
specifically requested.
Note
For operations below +4C, the use of anti-
ice additive is authorized but not mandatory
since the helicopter is equipped with an air-
frame anti-ice fuel filter.
Note
For additive requirements and blending pro-
cedures refer to the Pratt & Whitney
PW207C engine manual.
Table 1-1 Authorized Fuels
Kerosene
Type
Applicable
Specification
JET A
JET A-1
JP-5 *
JP-8 *
ASTM D1655
ASTM D1655
MIL-T-5624
MIL-T-83133
--- For Training Use Only ---
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A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-19
Rev. 1
EMERGENCY FUELS
Table 1-2 presents a list of fuels approved for emergency use. Emer-
gency fuels should only be used whenever any of the authorized fuels
is not available.
Refer to the Pratt & Whitney PW207C Manual for full details.
Table 1-2 Emergency Fuels
Fuel Type Applicable
Specification
Restrictions
Automotive Diesel
CPW 46
Aviation Gasoline
Grades: 80, 100
and 100 LL
Arctic Grade
Winter Grade
Regular Grade
MIL-G-5572
Do not use below -15 C (5 F) OAT
Do not use below -7 C (20 F) OAT
Do not use below 5 C (40 F) OAT
Do not use for longer than 150
hours during any period between
engine overhauls
--- For Training Use Only ---
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Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-20 01-06-05 EASA Approved
LUBRICANTS
AUTHORIZED ENGINE OILS
The oils shown in Table 1-3 have been authorized for use with the
PW207C engines.
Note
Engine oil tank capacity is 5.12 liters
(1.34 US Gallon).
Note
Mixing of the different brands and types is
prohibited.
Table 1-3 Authorized Lubricating Oils, Type II (5 Centistokes)
Applicable
Specification
Brand Names
(For reference only)
MIL-PRF-23699 Aero-Shell Turbine Oil 500
Aero-Shell Turbine Oil 560
BP Turbo Oil 2380 (formerly Exxon Turbo Oil 2380)
BP Turbo Oil 25 (formerly Exxon Turbo Oil 25)
Castrol 5000
Mobil Jet Oil II
Royco Turbine Oil 500
Royco Turbine Oil 560
Turbonycoil 525-2A
--- For Training Use Only ---
-
A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-21
AUTHORIZED TRANSMISSION OILS
The oils shown in Table 1-4 have been authorized for use with the
main transmission and the tail rotor gearbox lubrication systems.
Oils limited to ambient temperature above -40 C (-40 F).
Note
Mixing of oils of different brands and types is
prohibited.
Table 1-4 Authorized Lubricating Oils
Designation Specification
BP Turbo oil 2380
(formerly EXXON Turbo oil 2380)
MIL-PRF-23699
Mobil Jet Oil II MIL-PRF-23699
Mobil Jet Oil 254 MIL-PRF-23699
Aeroshell Turbine oil 500 MIL-PRF-23699
Aeroshell Turbine oil 555 DOD-PRF-85734
Aeroshell Turbine oil 560 MIL-PRF-23699
Castrol Aero 5000 MIL-PRF-23699
BP Turbo oil 2197 MIL-PRF-23699
--- For Training Use Only ---
-
Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-22 01-06-05 EASA Approved
Rev. 1
HYDRAULIC SYSTEMS LIMITATIONS
MAIN FLUID PRESSURE
Minimum.................................................................................. 1200 psi
Cautionary Range ...................................................... 1200 to 1400 psi
Continuous Operation ................................................ 1401 to 1600 psi
Maximum................................................................................. 1600 psi
UTILITY SYSTEM - NORMAL- FLUID PRESSURE
Minimum.................................................................................... 500 psi
Cautionary Range .........................................................500 to 1140 psi
Continuous Operation .................................................1141 to 1600 psi
Maximum................................................................................. 1600 psi
UTILITY SYSTEM - EMERGENCY- FLUID PRESSURE
Minimum...................................................................................1140 psi
Maximum................................................................................. 1600 psi
APPROVED FLUIDS
The following hydraulic fluids are approved:
MIL-PRF-5606
MIL-PRF-83282.
Note
Mixing of fluids of different brands and types
is prohibited.
--- For Training Use Only ---
-
A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-23
Rev. 1
GENERATOR LOAD LIMITATIONS
For each generator
Continuous operation ............................................................0 to 160 A
Maximum......................................................................................160 A
Transient (20 seconds).................................................................200 A
AVIONICS LIMITATIONS
OBS mode must not be used coupled with EFIS and Flight Direc-
tor system.
GNS430 and GNS530 systems must not be used for GPS
approach.
AUTOMATIC FLIGHT CONTROL SYSTEM LIMITATIONS
Minimum AFCS configuration
for VFR flight .........................................................No helipilot required
Minimum AFCS configuration
to start IFR flight ....................................................... Two helipilots and
ATT Hold mode ON
FLIGHT WITH ONE HELIPILOT OPERATIVE ONLY
VFR Flight
Fly attentive up to 128 KIAS and/or 1,000 ft/min rate of climb, and
above 500 ft AGL.
Fly manually in all other conditions.
IFR Flight
The following limitations apply:
Maximum airspeed.................................................................128 KIAS
Maximum rate of climb ....................................................... 1,000 ft/min
Fly attentive above 500 ft AGL.
Fly manually below 500 ft AGL.
--- For Training Use Only ---
-
Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-24 01-06-05 EASA Approved
FLIGHT DIRECTOR LIMITATIONS
ILS APPROACH
Steepest approach gradient ............................................... 8.4 degrees
FLIGHT DIRECTOR MODES MINIMUM USE HEIGHT (MUH)
All Flight Director modes when
in cruise, climb and descent.................................................500 ft AGL
All Flight Director modes during approach .............................50 ft AGL
ROTOR BRAKE LIMITATION (if installed)
Selection of the rotor brake to the ON position is limited as follows:
Rotor Speed (NR)................................................................ below 40%
MISCELLANEOUS LIMITATIONS
BAGGAGE COMPARTMENT LIMITATIONS
Maximum load............................................................... 120 kg (264 lb)
Maximum Unit Load .......................................... 500 kg/m2 (102 lbs/ft2)
Note
Refer to Section 6, Weight and Balance, for
load distribution.
--- For Training Use Only ---
-
A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-25
Rev. 1
PLACARDS
Figure 1-7 Cockpit placards (Sheet 1 of 2)
--- For Training Use Only ---
-
Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-26 01-06-05 EASA Approved
Rev. 2
IN ALTN POSITIONCLOSE VENTS AND
TURN HEATER/ECS OFF
IN ALTN POSNMAINTAIN INSTACCURACY BY
CLOSINGWINDOWS VENTS
AND TURNINGHEATER OFF
DO NOT APPLY ROTORBRAKE ABOVE 40%
ROTOR RPM
APPROVED TYPES OF OPERATION DAY/NIGHT VFRDAY/NIGHT IFR
ICING PROHIBITED
C
B
D
E
E
ALT. STATICDECREASE ALTIMETER READING BY 80 ft
Only with sliding windows
ICN-0B-A-151000-G-A0126-00002-A-04-1
Figure 1-7 Cockpit placards (Sheet 2 of 2)
--- For Training Use Only ---
-
A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-27
Figure 1-8 Baggage compartment placards
--- For Training Use Only ---
-
Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-28 01-06-05 EASA Approved
Rev. 1
INSTRUMENT MARKINGS
AIRSPEED
KNOTS
20
40
60
80100
150
2000
NE
ICN-0B-A-151000-G-A0126-00005-A-02-1
87;RNG
NORM
STA
TIC
ALTN
NE
Figure 1-9 Airspeed Indicator
--- For Training Use Only ---
-
A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-29
ELECTRONIC DISPLAY UNIT FORMATS
The EDUs present the following information:
EDU1 EDU2
- N1 - Engine 1 oil pressure
- TOT - Engine 1 oil temperature
- TRQ - Transmission oil pressure
- NR - Transmission oil temperature
- N2 - OAT
- Caution, warning and advisory - Engine 2 oil pressure
messages - Engine 2 oil temperature
- Main hydraulic pressure
- Fuel Quantity
- Fuel Pressure
- Utility hydraulic pressure
- DC current
- DC voltage
- AC voltage
- Fuel flow
- Normal utility hydraulic pressure
- Emergency utility hydraulicpressure
- Advisory and status mes-sages
Note
Fuel flow indication should not be used for
flight planning.
--- For Training Use Only ---
-
Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-30 01-06-05 EASA Approved
Rev. 1
The main display formats are:
The START mode of EDU1 is displayed upon initialization and/or
when selected by the START key on EDU1.
EDU1 EDU2
- START
- CRUISE AEO OEI AUTOROTATION
- MAIN
- AUXILIARY
- REVERSIONARY AEOOEIAUTOROTATION
CLR
ON
OFF
ENT
BRT
DIM
M
START
START
IGN
IGN
MAN
MAN
N1 TOT TRQ NR
N2 N2
IDLE
IDLE
#1 OIL PRES
SERVO 1
ROTOR LOW
XMSN OIL PRES
PARK BRK ON
#2 OIL PRES
#2 DC GEN
SERVO 2
63 63 440 440 8 8 65
#1 DC GEN
100
ICN-0B-A-151000-G-A0126-00006-A-02-1
Figure 1-10 EDU1 - START Mode (AEO) (Typical)
--- For Training Use Only ---
-
A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-31
Rev. 1
The CRUISE mode is displayed on EDU1 when selected by the
CRUISE key on EDU1 or automatically when NR exceeds 85% at the
end of the start sequence. The CRUISE mode is displayed on both
EDUs in case of complete loss of secondary data.
The cruise (AEO) format is also presented in the REVERSIONARY
mode.
CLR
ON
OFF
ENT
BRT
DIM
M
N1 TOT TRQ NR
N2 N2
#1 OIL PRES
SERVO 1 PARK BRK ON
#2 OIL PRES
#2 DC GEN
SERVO 2
#1 DC GEN
95.5 95.5 770 770 95 95 100
BATT HOT
XMSN OIL PRES
ICN-0B-A-151000-G-A0126-00007-A-02-1
100
Figure 1-11 EDU1 - CRUISE Mode (AEO) (Typical)
--- For Training Use Only ---
-
Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-32 01-06-05 EASA Approved
Rev. 1
The OEI mode is a subset of the CRUISE mode and is automatically
displayed if one engine becomes inoperative.
The OEI format is also presented in REVERSIONARY mode.
CLR
ON
OFF
ENT
BRT
DIM
M
N1 TOT TRQ NR
N2 N295.5 770 100
ENG 2 OUT
0 0 095
OEI
OEI
OEI
ICN-0B-A-151000-G-A0126-00008-A-02-1
100
Figure 1-12 EDU1 - OEI Mode (Typical)
--- For Training Use Only ---
-
A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-33
Rev. 1
The AUTOROTATION mode is automatically displayed when both
engines fail or run at idle, both engine torque inputs are zero and/or in
presence of a NR/N2 split.
The AUTOROTATION format is also presented in REVERSIONARY
mode.
CLR
ON
OFF
ENT
BRT
DIM
M
N1 TOT TRQ NR
N2 N2
#1 OIL PRES
SERVO 1 PARK BRK ON
#2 OIL PRES
#2 DC GEN
SERVO 2
#1 DC GEN XMSN OIL PRES
ROTOR LOW
67 67 430 430 0 0 108
ICN-0B-A-151000-G-A0126-00009-A-02-1
100
Figure 1-13 EDU1 - AUTOROTATION Mode (Typical)
--- For Training Use Only ---
-
Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-34 01-06-05 EASA Approved
The MAIN mode of EDU2 is displayed upon IDS initialization and/or
when selected by the MAIN key on EDU2 and/or when any caution/
warning message appears.
CLR
ON
OFF
ENT
BRT
DIM
M
TEST
POWER
CHECKEXIT AUX
MENU 1/3
MAIN
55 65 45 68
PSI
1450
ICN-0B-A-151000-G-A0126-00010-A-01-1
PSI
HYD 1
22 23
PSI PSI
1450
PSI
HYD 2225 FUEL
C
OAT
55 65
PSI C
KG KG
OILENG 1 OILXMSNCPSI C
OILENG 2
+15
225
Figure 1-14 EDU2 - MAIN Mode (Typical)
--- For Training Use Only ---
-
A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-35
The AUXILIARY mode of EDU2 is displayed by pressing the AUX key
on EDU2.
The AUXILIARY page reverts automatically to the MAIN page when
any caution/warning message appears.
CLR
ON
OFF
ENT
BRT
DIM
M
TEST
POWER
CHECKEXIT AUX
MENU 1/3
MAIN
HYD 1
PSI
HYD 2
KG
ICN-0B-A-151000-G-A0126-00011-A-01-1
KG/HR
FUEL
VDC
VAC 116
MAIN
HYDRAULICS
PSI
UTIL
NORM EMER
118 AMP 123 100 99
1450 1450
27.3 27.5
115225
14501450
ELECTRICS
225
Figure 1-15 EDU2 - AUXILIARY Mode (Typical)
--- For Training Use Only ---
-
Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-36 01-06-05 EASA Approved
Rev. 1
Any EDU reverts to the REVERSIONARY mode when it is manually
commanded by pressing the ON/OFF switch to OFF on the failed EDU
or automatically when a critical failure occurs and is detected by the
healthy EDU.
CLR
ON
OFF
ENT
BRT
DIM
M
N1 TOT TRQ NR
SERVO 1 IDS
ENG 1 OIL
65 PSI 88 C
PSI
FUEL SYS 1
19 143 KG
65 PSI 88 C 65 PSI 88 CENG 2 OILXMSN OIL
PSI19 143 KGFUEL SYS 2
PSI1053 14731 HYD OIL 2
ICN-0B-A-151000-G-A0126-00012-A-02-1
100
Figure 1-16 EDU1 and EDU2 - REVERSIONARY Mode (Typical)
--- For Training Use Only ---
-
A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-37
Rev. 1
TRANSIENT 104.1%
TAKE-OFF 99.8%
MAX. CONTINUOUS 97.2%
50%
0%
CRUISE format (AEO)AUTOROTATION formatREVERSIONARY format
0%
50%
MAX. CONTINUOUS 97.2%
TRANSIENT 104.1%
TAKE-OFF 99.8%
START format (AEO)
N1 N1
CLR
ON
OFF
ENT
BRT
DIM
M
N1 TOT TRQ NR
N2 N2
#1 OIL PRES
SERVO 1 PARK BRK ON
#2 OIL PRES
#2 DC GEN
SERVO 2
#1 DC GEN
95.5 95.5 770 770 95 95 100
BATT HOT
XMSN OIL PRES
ICN-0B-A-151000-G-A0126-00013-A-02-1
100
Figure 1-17 EDU1 - Gas Generator Speed (AEO)
--- For Training Use Only ---
-
Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-38 01-06-05 EASA Approved
Rev. 1
0%
50%
TRANSIENT 104.1%
OEI formatREVERSIONARY OEI format
MAX. OEI CONTINUOUS 99.8%
MAX. 2.5 MIN 103%
N1
CLR
ON
OFF
ENT
BRT
DIM
M
N1 TOT TRQ NR
N2 N295.5 770 100
ENG 2 OUT
0 0 095
OEI
OEI
OEI
ICN-0B-A-151000-G-A0126-00014-A-02-1
100
Figure 1-18 EDU1 - Gas Generator Speed (OEI)
--- For Training Use Only ---
-
A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-39
Rev. 1
CRUISE format (AEO)AUTOROTATION formatREVERSIONARY format
START format (AEO)
50%
TOT
MAX. CONTINUOUS 840C
TAKE-OFF 900CSTART LIMIT 875C
MAX. CONTINUOUS 840C
TAKE-OFF 900C
TRANSIENT 1000C
TOT
50%
CLR
ON
OFF
ENT
BRT
DIM
M
N1 TOT TRQ NR
N2 N2
#1 OIL PRES
SERVO 1 PARK BRK ON
#2 OIL PRES
#2 DC GEN
SERVO 2
#1 DC GEN
95.5 95.5 770 770 95 95 100
BATT HOT
XMSN OIL PRES
ICN-0B-A-151000-G-A0126-00015-A-02-1
100
Figure 1-19 EDU1 - Turbine Outlet Temperature (AEO)
--- For Training Use Only ---
-
Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-40 01-06-05 EASA Approved
Rev. 1
TOT
50%
OEI formatREVERSIONARY OEI format
TRANSIENT 875C
MAX. CONTINUOUS 900C
TRANSIENT 1000C
MAX. 2.5 MIN 970C
CLR
ON
OFF
ENT
BRT
DIM
M
N1 TOT TRQ NR
N2 N295.5 770 100
ENG 2 OUT
0 0 095
OEI
OEI
OEI
ICN-0B-A-151000-G-A0126-00016-A-02-1
100
Note
The transient value at starting
(half red dot at 875 C) is
displayed on the scale of the
engine being started, during
the restart phase only.
Figure 1-20 EDU1 - Turbine Outlet Temperature (OEI)
--- For Training Use Only ---
-
A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-41
Rev. 1
0%
CRUISE format (AEO)AUTOROTATION formatREVERSIONARY format
0%
START format (AEO)
TRQTRQ
TRANSIENT 110%
TAKE-OFF 107%
MAX. CONTINUOUS 100%
TAKE-OFF 107%
MAX. CONTINUOUS 100%
TRANSIENT 110%
CLR
ON
OFF
ENT
BRT
DIM
M
N1 TOT TRQ NR
N2 N2
#1 OIL PRES
SERVO 1 PARK BRK ON
#2 OIL PRES
#2 DC GEN
SERVO 2
#1 DC GEN
95.5 95.5 770 770 95 95 100
BATT HOT
XMSN OIL PRES
ICN-0B-A-151000-G-A0126-00017-A-02-1
100
Figure 1-21 EDU1 - Torque (AEO)
XMSN OVTRQ
When TRQ1 + TRQ2 > 215%
--- For Training Use Only ---
-
Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-42 01-06-05 EASA Approved
Rev. 3
XMSN OVTRQ
OEI formatREVERSIONARY OEI format
0%
TRQ
MAX. CONTINUOUS 133%
CLR
ON
OFF
ENT
BRT
DIM
M
N1 TOT TRQ NR
N2 N295.5 770 100
ENG 2 OUT
0 0 095
OEI
OEI
OEI
TRANSIENT 173%
MAX. 2.5 MIN 162%
ICN-0B-A-151000-G-A0126-00018-A-02-1
100
When TRQ > 162%
Figure 1-22 EDU1 - Torque (OEI)
XMSN OVTRQ
--- For Training Use Only ---
-
A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-43
Rev. 1
CLR
ON
OFF
ENT
BRT
DIM
M
N1 TOT TRQ NR
N2 N2
#1 OIL PRES
SERVO 1 PARK BRK ON
#2 OIL PRES
#2 DC GEN
SERVO 2
#1 DC GEN
95.5 95.5 770 770 95 95 100
BATT HOT
XMSN OIL PRES
20%
TRANSIENT 112.4%
N2 NR
AND LANDING 102%
MAX TAKE-OFF
START and CRUISE formats (AEO)REVERSIONARY format
CONTINUOUSOPERATION
MAX CONTINUOUS 101%
MINIMUM 99%
TRANSIENT 95%
ICN-0B-A-151000-G-A0126-00019-A-02-1
100
ROTOR LOW
ROTOR HIGH
#1(2) OVSPD
when NR < 95.5%
when NR > 106%
when N2 > 112.4%
+ ROTOR LOW
+ HORN
+ ROTOR HIGH
Figure 1-23 EDU1 - Rotor Power Turbine Speed (AEO)
--- For Training Use Only ---
-
Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-44 01-06-05 EASA Approved
Rev. 1
OEI formatREVERSIONARY OEI format
20%
N2 NR
TRANSIENT 112.4%
102%MAX TAKE-OFFAND LANDING
99%
90%
MAX. CONTINUOUS 101%
CLR
ON
OFF
ENT
BRT
DIM
M
N1 TOT TRQ NR
N2 N295.5 770 100
ENG 2 OUT
0 0 095
OEI
OEI
OEI
CONTINUOUSOPERATION
MINIMUM
TRANSIENT 85%
ICN-0B-A-151000-G-A0126-00021-A-02-1
100
ROTOR LOW
ROTOR HIGH
#1(2) OVSPD
when NR < 95.5%
when NR > 106%
when N2 > 112.4%
+ ROTOR LOW
+ HORN
+ ROTOR HIGH
Figure 1-24 EDU1 - Rotor Power Turbine Speed (OEI)
--- For Training Use Only ---
-
A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-45
Rev. 1
20%
N2 NR
AUTOROTATION formatREVERSIONARY AUTOROTATION format
MAXIMUM 110%
CONTINUOUSOPERATION
MINIMUM 95%
TRANSIENT 90%
CLR
ON
OFF
ENT
BRT
DIM
M
N1 TOT TRQ NR
N2 N2
#1 OIL PRES
SERVO 1 PARK BRK ON
#2 OIL PRES
#2 DC GEN
SERVO 2
#1 DC GEN XMSN OIL PRES
ROTOR LOW
67 67 430 430 0 0 108
ICN-0B-A-151000-G-A0126-00020-A-02-1
100
ROTOR LOW
ROTOR HIGH
when NR < 94.5%
when NR > 111%
+ ROTOR LOW
+ HORN
+ ROTOR HIGH
Figure 1-25 EDU1 - Rotor Speed (Power-OFF)
--- For Training Use Only ---
-
Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-46 01-06-05 EASA Approved
Rev. 1
ICN-0B-A-151000-G-A0126-00022-A-01-1
0 PSI
CAUTIONARY
CONTINUOUSOPERATION
MAXIMUMCAUTIONARY
120 PSI
MINIMUM
ENG OIL
CLR
ON
OFF
ENT
BRT
DIM
M
TEST
POWER
CHECKEXIT AUX
MENU 1/3
MAIN
55 65 45 68 +15
PSI
1450
PSI
HYD 1
22 23
PSI PSI
1450
PSI
HYD 2225 FUEL
C
OAT
55 65
PSI C
KG KG
OILENG 1 OILXMSNCPSI C
OILENG 2
225
#1(2) OIL PRES
When engine oil pressure
is outside limits:
+ WARNING
Figure 1-26 EDU2 (MAIN) - Engine Oil Pressure
--- For Training Use Only ---
-
A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-47
CONTINUOUSOPERATION
ENG OIL
ICN-0B-A-151000-G-A0126-00023-A-01-1
0C
MAXIMUM 125C
10C
130C
CLR
ON
OFF
ENT
BRT
DIM
M
TEST
POWER
CHECKEXIT AUX
MENU 1/3
MAIN
55 65 45 68 +15
PSI
1450
PSI
HYD 1
22 23
PSI PSI
1450
PSI
HYD 2225 FUEL
C
OAT
55 65
PSI C
KG KG
OILENG 1 OILXMSNCPSI C
OILENG 2
225
#1(2) OIL HOT
when engine oil temp. > 125C
Figure 1-27 EDU2 (MAIN) - Engine Oil Temperature
--- For Training Use Only ---
-
Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-48 01-06-05 EASA Approved
0 PSI
CAUTIONARY
ICN-0B-A-151000-G-A0126-00024-A-01-1
XMSN OIL
100 PSI
MAXIMUM 70 PSI
CONTINUOUSOPERATION
MINIMUM 30 PSI
50 PSI
CLR
ON
OFF
ENT
BRT
DIM
M
TEST
POWER
CHECKEXIT AUX
MENU 1/3
MAIN
55 65 45 68 +15
PSI
1450
PSI
HYD 1
22 23
PSI PSI
1450
PSI
HYD 2225 FUEL
C
OAT
55 65
PSI C
KG KG
OILENG 1 OILXMSNCPSI C
OILENG 2
225
XMSN OIL PRES
when transmission oil pressure < 30 psi
+ WARNING
Figure 1-28 EDU2 (MAIN) - Transmission Oil Pressure
--- For Training Use Only ---
-
A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-49
CONTINUOUSOPERATION
0C
130C
ICN-0B-A-151000-G-A0126-00025-A-01-1
XMSN OIL
MAXIMUM 120C
CLR
ON
OFF
ENT
BRT
DIM
M
TEST
POWER
CHECKEXIT AUX
MENU 1/3
MAIN
55 65 45 68 +15
PSI
1450
PSI
HYD 1
22 23
PSI PSI
1450
PSI
HYD 2225 FUEL
C
OAT
55 65
PSI C
KG KG
OILENG 1 OILXMSNCPSI C
OILENG 2
225
XMSN OIL HOT
when transmission oil temp. > 120C
+ WARNING
Figure 1-29 EDU2 (MAIN) - Transmission Oil Temperature
--- For Training Use Only ---
-
Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-50 01-06-05 EASA Approved
CONTINUOUSOPERATION
ICN-0B-A-151000-G-A0126-00026-A-01-1
MINIMUM1200 PSI
MINIMUMCONTINUOUS
1400 PSI
800 PSI
CAUTIONARY
2000 PSI
HYD
CLR
ON
OFF
ENT
BRT
DIM
M
TEST
POWER
CHECKEXIT AUX
MENU 1/3
MAIN
55 65 45 68 +15
PSI
1450PSI
HYD 1
22 23PSI PSI
1450PSI
HYD 2225 FUEL
C
OAT
55 65
PSI C
KG KG
OILENG 1 OILXMSNCPSI C
OILENG 2
CLR
ON
OFF
ENT
BRT
DIM
M
TEST
POWER
CHECKEXIT AUX
MENU 1/3
MAIN
HYD 1
PSI
HYD 2
XFEED
KG
KG/HR
FUEL
VDC
VAC 116
MAIN
HYDRAULICS
PSI
UTIL
NORM EMER
118 AMP 123 100 99
1450 1450
27.3 27.5
115225 227
14501450
EDU2 - AUXILIARY EDU2 - MAIN
ELECTRICS
MAXIMUM1600 PSI
225
Figure 1-30 EDU2 (MAIN/AUXILIARY) - Main Hydraulic System
Pressure
--- For Training Use Only ---
-
A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-51
ICN-0B-A-151000-G-A0126-00027-A-01-1
CAUTIONARYCONTINUOUSOPERATION
MAXIMUM25 PSI
MINIMUM0 PSI
MINIMUMCONTINUOUS
7 PSI
30 PSI
FUEL
CLR
ON
OFF
ENT
BRT
DIM
M
TEST
POWER
CHECKEXIT AUX
MENU 1/3
MAIN
55 65 45 68 +15
PSI
1450
PSI
HYD 1
22 23
PSI PSI
1450
PSI
HYD 2225 FUEL
C
OAT
55 65
PSI C
KG KG
OILENG 1 OILXMSNCPSI C
OILENG 2
225
Figure 1-31 EDU2 (MAIN) - Fuel Pressure
--- For Training Use Only ---
-
Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-52 01-06-05 EASA Approved
CONTINUOUSOPERATION
ICN-0B-A-151000-G-A0126-00028-A-01-1
AMMETER
TRANSIENT200 AMP
0 AMP
MAXIMUM160 AMP
CLR
ON
OFF
ENT
BRT
DIM
M
TEST
POWER
CHECKEXIT AUX
MENU 1/3
MAIN
HYD 1
PSI
HYD 2
KG
KG/HR
FUEL
VDC
VAC 116
MAIN
HYDRAULICS
PSI
UTIL
NORM EMER
118 AMP 123 100 99
1450 1450
27.3 27.5
115225
14501450
ELECTRICS
225
Figure 1-32 EDU2 (AUXILIARY) - Ammeter
--- For Training Use Only ---
-
A109S RFM Section 1
Document N109G0040A013 Limitations
EASA Approved 01-06-05 Page 1-53
CLR
ON
OFF
ENT
BRT
DIM
M
TEST
POWER
CHECKEXIT AUX
MENU 1/3
MAIN
HYD 1
PSI
HYD 2
KG
KG/HR
FUEL
VDC
VAC 116
MAIN
HYDRAULICS
PSI
UTIL
NORM EMER
118 AMP 123 100 99
1450 1450
27.3 27.5
115225
14501450
ICN-0B-A-151000-G-A0126-00029-A-01-1
NORM
300 PSI
MINIMUM500 PSI 1140 PSI
2000 PSI
CONTINUOUSOPERATIONCAUTIONARY
ELECTRICS
MAXIMUM1600 PSI
225
Figure 1-33 EDU2 (AUXILIARY) - Utility Hydraulic System
Pressure (Normal)
--- For Training Use Only ---
-
Section 1 A109S RFM
Limitations Document N109G0040A013
Page 1-54 01-06-05 EASA Approved
CLR
ON
OFF
ENT
BRT
DIM
M
TEST
POWER
CHECKEXIT AUX
MENU 1/3
MAIN
HYD 1
PSI
HYD 2
KG
KG/HR
FUEL
VDC
VAC 116
MAIN
HYDRAULICS
PSI
UTIL
NORM EMER
118 123 100 99
1450 1450
27.3 27.5
115225
14501450
300 PSI
2000 PSI
CONTINUOUSOPERATION
ICN-0B-A-151000-G-A0126-00030-A-01-1
MINIMUM1140 PSI
EMER
ELECTRICS
AMP
MAXIMUM1600 PSI
225
Figure 1-34 EDU2 (AUXILIARY) - Utility Hydraulic System
Pressure (Emergency)
--- For Training Use Only ---
-
A109S RFM Section 2
Document N109G0040A013 Table of Contents
EASA Approved 01-06-05 Page 2-i
SECTION 2
NORMAL PROCEDURES
TABLE OF CONTENTS
Page
GENERAL ....................................................................................... 2-1
FLIGHT PLANNING ........................................................................ 2-2
EXTERNAL PREFLIGHT CHECKS ................................................ 2-2
GENERAL................................................................................... 2-2
PILOTS PREFLIGHT CHECK.................................................... 2-3
ENGINE PRE-START CHECK...................................................... 2-17
ENGINE START ............................................................................ 2-24
NORMAL ENGINE START....................................................... 2-24
QUICK ENGINE START........................................................... 2-29
DRY MOTORING RUN............................................................. 2-33
SYSTEMS CHECK ....................................................................... 2-35
HYDRAULIC SYSTEMS........................................................... 2-35
FUEL SYSTEM......................................................................... 2-36
ELECTRICAL A.C. SYSTEM.................................................... 2-38
MISCELLANEOUS ................................................................... 2-38
HELIPILOT SYSTEM................................................................ 2-40
BEFORE TAKE-OFF CHECKS..................................................... 2-42
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Section 2 A109S RFM
Table of Contents Document N109G0040A013
Page 2-ii 01-06-05 EASA Approved
Page
GROUND TAXIING........................................................................2-43
TAKE-OFF .....................................................................................2-43
HOVER TAKE-OFF...................................................................2-43
ROLLING TAKE-OFF ...............................................................2-45
IN FLIGHT......................................................................................2-47
FLIGHT DIRECTOR OPERATION (IF INSTALLED) ................2-47
APPROACH AND LANDING ........................................................2-48
VERTICAL LANDING................................................................2-49
RUNNING LANDING ................................................................2-49
SHUTDOWN .................................................................................2-50
POST FLIGHT CHECK..................................................................2-51
FLIGHT HANDLING CHARACTERISTICS...................................2-52
ENGINE LIMIT GOVERNING ...................................................2-52
CLIMB SPEED..........................................................................2-53
AUTOROTATIVE DESCENT....................................................2-53
STEEP APPROACHES AND VERTICAL DESCENT
MANOEUVRES.........................................................................2-53
ADVISORY CAPTIONS DEFINITIONS .........................................2-54
--- For Training Use Only ---
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A109S RFM Section 2
Document N109G0040A013 Table of Contents
EASA Approved 01-06-05 Page 2-iii
LIST OF FIGURES
Figure Page
Figure 2-1 Preflight Check Sequence .......................................... 2-3
Figure 2-2 IGN Circuit Breakers Location .................................. 2-34
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Table of Contents Document N109G0040A013
Page 2-iv 01-06-05 EASA Approved
This Page Intentionally Left Blank
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01-06-05 A109S RFM Section 2
Document N109G0040A013 Normal Procedures
EASA Approved 01-06-05 Page 2-1
SECTION 2
NORMAL PROCEDURES
GENERAL
The following procedures are the result of extensive flight tests and
experience with the A109S aircraft. They are intended to ensure that
the level of safety established by the design and certification process
is achieved.
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.
The instructions and procedures contained herein are written for the
purpose of standardization and are not applicable to all situations.
The minimum and maximum limits, and the normal and cautionary
operating ranges for the helicopter and its subsystems are indicated
by instrument markings and placards. Refer to Section 1 for details of
the operating limitations.
Each time an operating limitation is exceeded, a malfunction or an
emergency occurs, an appropriate entry shall be made in the logbook
(airframe, engine, etc.). The entry shall state which limit was
exceeded, the duration of time, the extreme value attained, and any
additional information essential in determining the maintenance action
required. As an aid to this task, the IDS software includes logs of limit
exceedance data, fault data, and caution and warning signals which
are stored in a Non-Volatile Memory for subsequent retrieval.
--- For Training Use Only ---
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Section 2 A109S RFM
Normal Procedures Document N109G0040A013
Page 2-2 01-06-05 EASA Approved
FLIGHT PLANNING
Each flight must be planned adequately to ensure safe operations and
to provide the pilot with the data to be used during the flight.
Essential weight and balance, and performance information should be
compiled as follows:
- Check type of mission to be performed and destination.
- Select appropriate performance charts to be used form Section 4.
- Review the appropriate Supplements of this Rotorcraft Flight Manual
for the optional equipment installed.
Ascertain proper weight and balance of the helicopter as follows:
- Consult Section 6 - Weight and Balance;
- Ascertain weight of fuel, oil, payload, etc;
- Compute take-off and anticipated landing gross weights;
- Check helicopter center of gravity (CG) locations;
- Check that the weight and CG limitations in Section 1 are not
exceeded during the flight.
EXTERNAL PREFLIGHT CHECKS
GENERAL
Preflight checks are intended as those checks to be performed by the
pilot in order to ascertain that the helicopter is flightworthy and ade-
quately equipped.
Note
All checks are to be carried out before the first flight
of the day. Checks in blue may be omitted if the
AIRWORTHINESS CHECK has been performed as
per Maintenance Manual. Furthermore, checks
marked with an are required before each flight.
The inspection commences at the nose and continues clockwise
around the helicopter. During the inspection, check that there are no
leaks from overboard drains, that all vents, air intakes and air outlets are
clear of obstructions, and all access panels and antennas are secure.
--- For Training Use Only ---
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01-06-05 A109S RFM Section 2
Document N109G0040A013 Normal Procedures
EASA Approved 01-06-05 Page 2-3
PILOTS PREFLIGHT CHECK
Figure 2-1 Preflight Check Sequence
AREA N1: Helicopter nose
AREA N2: Fuselage - RH side
AREA N3: Tail boom - RH side
AREA N4: Fins, tail gearbox, tail rotor and skid
AREA N5: Tail boom - LH side
AREA N6: Fuselage - LH side
AREA N7: Cabin interior
--- For Training Use Only ---
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Section 2 A109S RFM
Normal Procedures Document N109G0040A013
Page 2-4 01-06-05 EASA Approved
The following procedure outlines the pilot walk-around and interior
checks (Figure 2-1):
Main and tail rotor tie-downs : Removed.
Area N1 (Helicopter Nose)
Nose exterior : Condition.
Ventilation air intake : Free of obstruction.
Pitot-static tubes (2) : Cover removed, condition and
free of obstruction.
Nose landing gear : Condition, shock strut extension,
leaks, tire condition and pres-
sure.
Landing light : Condition and cleanliness.
Nose compartment access door : Open.
Avionic components : Condition and secured.
Accumulators : Condition and free of leaks.
Nose compartment access
door
: Secured.
Accumulators : Discharge by pressing two rele-
vant red pushbuttons.
CAUTION
The discharge of accumulators causes loss
of parking brakes. Suitable measures
(wheel chocks) should be taken to ensure
helicopter will not move.
Drains and vents : Condition.
--- For Training Use Only ---
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01-06-05 A109S RFM Section 2
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EASA Approved 01-06-05 Page 2-5
Area N2 (Fuselage - RH side)
Windshield and roof transpar-
ent panel
: Condition and cleanliness.
IDS external air temperature sen-
sor
: Condition, free of obstruction.
Fuselage exterior : Condition.
Pilot cabin door and window : Condition, cleanliness, seal
retainer and secured.
Antenna(s) : Condition.
Sliding door : Condition, cleanliness of window
and secured.
Sliding door jettison window : Security and condition of win-
dow, seal retainer and emer-
gency markings.
Cowlings and fairings : Condition and secured.
Middle access door : Open.
Servo hydraulic system valves
and filter group
: Check for leaks and status (Red
button out: filter clogged).
Hydraulic system tanks (2) : Check fluid level and filler cap
for security.
Middle access door : Secured.
Service step : Open, if necessary, to reach
upper part of helicopter.
Main rotor hub and blades : Condition and secured.
Main rotor dampers : Condition and secured.
Check for correct charge indica-
tion.
Main rotor pitch change links : Condition and secured.
--- For Training Use Only ---
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Section 2 A109S RFM
Normal Procedures Document N109G0040A013
Page 2-6 01-06-05 EASA Approved
Upper anti-collision light : Condition.
HYD. SERVOS access door : Open.
Servo actuator
(actuator with yellow decal)
: Condition and leaks.
Main transmission and accesso-
ries (visible area)
: Condition and leaks.
Transmission external oil filter : By-pass indication (red button
out: filter clogged).
HYD. SERVOS access door : Secured.
ENGINE OIL COOLER access door : Open.
Cooler blower air intake : Free of obstruction.
Cooler system belt : Condition and secured.
ENGINE OIL COOLER access
door
: Secured.
Service step : Open.
Airframe (A/F) fuel filter : Condition and leaks.
Service step : Secured.
Engine air intake screen and
chamber
: Covers removed; free of dam-
age and/or obstruction.
Engine access door : Open.
Engine area : Check for fuel and/or oil leaks.
Engine oil : Check gauge for oil level.
Engine-transmission drive shaft : Condition.
Engine supports (visible area) : Condition.
Engine access door : Condition, secured.
Fuel filler cap : Secured.
Igniter access door : Open.
--- For Training Use Only ---
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Document N109G0040A013 Normal Procedures
EASA Approved 01-06-05 Page 2-7
Igniter box : Condition.
Engine fire extinguisher bottle : Condition.
Igniter access door : Secured.
Engine fire extinguisher indicator
disc
: Check in the red position.
Note
If the indicator disc is not in the red posi-
tion, it means that the relevant bottle has
already been discharged and needs to be
replaced.
Engine exhaust : Cover removed, condition and
free of fuel.
Main landing gear : Condition, shock strut extension,
leaks, tire condition and pres-
sure.
Taxi and landing lights : Condition.
Drain and vents lines : Free of obstruction.
Antenna(s) : Condition.
Navigation and position lights : Condition.
External Power door : Secured.
Battery door : Secured.
Area N3 (Tailboom - RH side)
Tailboom exterior : Condition.
Antenna(s) : Condition.
Lower anti-collision light : Condition.
Stabilizer : Condition and secured.
--- For Training Use Only ---
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Section 2 A109S RFM
Normal Procedures Document N109G0040A013
Page 2-8 01-06-05 EASA Approved
Area N4 (Fins, tail gearbox, tail rotor and skid)
Tail fin and skid : Condition.
Tail navigation light : Condition.
Tail rotor gearbox access door : Open.
Tail rotor gearbox : Check no leaks.
Tail rotor pitch link control lever : Condition.
Tail rotor gearbox access door : Secured.
Oil filler cap : Secured.
Tail rotor gearbox : Check oil level. Check for leaks.
Tail rotor hub and blades : Condition, cleanliness and free-
dom of flapping.
Tail rotor pitch change mecha-
nism
: Condition and secured.
Area N5 (Tailboom - LH side)
Tailboom exterior : Condition.
Stabilizer : Condition and secured.
Antenna(s) : Condition.
Tail rotor driveshaft cover : Open.
Tail rotor driveshaft bearings : Condition and secured.
Check for grease leaks.
Tail rotor driveshaft cover : Secured.
--- For Training Use Only ---
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01-06-05 A109S RFM Section 2
Document N109G0040A013 Normal Procedures
EASA Approved 01-06-05 Page 2-9
Area N6 (Fuselage - LH side)
Fuselage exterior : Condition
Engine exhaust : Cover removed, condition and
free of fuel.
Engine fire extinguisher
indicator disc
: Check in the red position.
Note
If the indicator disc is not in the red posi-
tion, it means that the relative bottle has
already been discharged and it needs to be
replaced.
Tail rotor driveshaft support
access door
: Open.
Igniter box : Condition.
Engine fire extinguisher bottle : Condition.
Tail rotor middle drive shaft bearings : Check condition.
Verify no marks of slippage.
Door secured.
Access door : Secured.
Baggage compartment door : Open.
Baggage compartment : Cargo (if on board) properly
secured.
Tail rotor hydraulic servo actuator : Check for oil leaks.
BATT RELAY circuit breaker : In.
Access door closed.
--- For Training Use Only ---
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Section 2 A109S RFM
Normal Procedures Document N109G0040A013
Page 2-10 01-06-05 EASA Approved
Note
The above mentioned circuit breakers are
accessible from baggage compartment
through an inspection door.
Baggage compartment door : Secured.
Engine access door : Open.
Engine area : Check for fuel and/or oil leaks.
Engine oil : Check gauge for oil level.
Engine-transmission drive shaft : Condition.
Engine support (visible area) : Condition.
Engine access door : Condition, secured.
Engine air intake screen and
chamber
: Cover removed; free of damage
and/or obstruction.
ENGINE OIL COOLER ACCESS
door
: Open.
Cooler blower air intake : Free of obstruction.
Cooler system belt : Condition and secured.
ENGINE OIL COOLER
ACCESS door
: Secured.
Service step : Open and use to reach upper
part of helicopter.
Main rotor hub and blades : Condition and secured.
Main rotor dampers : Condition and secured.
Check for correct charge indica-
tion.
Main rotor pitch change links : Condition and secured.
Swashplate and driving scissors : Condition and secured.
--- For Training Use Only ---
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01-06-05 A109S RFM Section 2
Document N109G0040A013 Normal Procedures
EASA Approved 01-06-05 Page 2-11
Rev. 1
Main transmission and accesso-
ries (visible area)
: Condition and leaks.
Transmission oil access door : Open.
Transmission : Filler cap secured.
Transmission oil : Check correct level. Door
secured.
Note
Transmission oil level must be between the
MIN and the MAX markings.
Transmission oil access door : Secured.
HYD. SERVOS ACCESS door : Open.
Servo actuators
(visible ones: actuator with red
decal and one with blue decal)
: Condition and leaks.
HYD. SERVOS ACCESS door : Secured.
Airframe (A/F) fuel filter : Condition and leaks.
Service step : Secured.
Drains and vents lines : Free of obstruction.
Navigation and position lights : Condition.
Main landing gear : Condition, shock strut extension,leaks, tire condition and pres-sure.
Taxi and landing lights : Condition.
Sliding door jettison window : Security and condition of win-dow, seal retainer and emer-gency markings.
Sliding door : Condition, cleanliness, windowsecured.
Cowling and fairings : Condition and secured.
--- For Training Use Only ---
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Section 2 A109S RFM
Normal Procedures Document N109G0040A013
Page 2-12 01-06-05 EASA Approved
Co-pilot cabin door and window : Condition, cleanliness, sealretainer and secured.
Antenna(s) : Condition.
Windshield and roof transpar-
ent panel
: Condition and cleanliness.
Area N7 (Helicopter interior)
Cabin interior
Sliding door jettison windows
(RH and LH)
: Security and condition of seal
retainer and strap.
Sliding doors (RH and LH) : Check correct operation of lock-ing and mechanical stop devices.
Passenger safety belts : Condition
Cabin interior : Check security of equipment.
Check presence of markings.
Note
Operation with passenger sliding doors open
or removed requires removal or correct
securing of all cabin equipment, installations
and trim panels and that passenger safety
belts be fastened if seats are unoccupied.
First aid kit : Check on board and content.
Cabin fire extinguisher : Charged and secured.
Sliding doors (RH and LH) : Secured.
--- For Training Use Only ---
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01-06-05 A109S RFM Section 2
Document N109G0040A013 Normal Procedures
EASA Approved 01-06-05 Page 2-13
Cockpit interior
Co-pilot door jettison handle : Correct position and secured.
Co-pilot safety belt and inertia reel : Condition and belt fastened ifseat is unoccupied.
Co-pilot seat : Secured.
Co-pilot flight controls : Condition and secured.
Lower and lateral transparent panels : Cleanliness and integrity.
Co-pilot door : Secured.
Pilot door jettison handle : Correct position and secured.
Pilot safety belt and inertia reel : Condition.
Pilot seat : Secured.
Pilot flight controls : Condition and secured.
Lower and lateral transparent panels
: Cleanliness and integrity.
Landing gear lever : Check DOWN.
Landing gear lever lock : Check in NORMAL position andwirelocked.
Parking brake : ON (pull out and turn).
Rotor brake lever : Leave disengaged (full forward).
Access door : Secured.
Instruments, panels and breakers : Condition and legibility.
All interior and exterior lights : Check OFF.
PITOT 1 and 2 switches : Check OFF.
--- For Training Use Only ---
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Section 2 A109S RFM
Normal Procedures Document N109G0040A013
Page 2-14 01-06-05 EASA Approved
For the following checks connect the d.c. supply.
Note
The following checks may require a large elec-trical consumption. Beware of possible batterycharge depletion if not using external power.
BAT switch : ON.
GEN BUS 1 and GEN BUS 2 switches
: ON.
External Power : Connect (if required). If external power connected, thebattery is automatically discon-nected. Check BATT OFF cau-tion message is displayed.
Landing gear indications : Check down and locked.Check 3 green lights lit (Nose,RH, LH).
Accumulators (HYDRAULIC
UTILITY NORM / EMER)
: Check for correct pre-charge(427 20 psi).
LH airframe (A/F) fuel filter : Gently drain while respective fuel
pump is operating. Push red but-
ton on filter and check for by-pass
indication and #1 A/F F FLTR
caution message on EDU1.
Note
Fuel is pressurized, therefore drainage
should be carried out by gently pushing red
button. Failure to comply with this advice
could result in some fuel being squirted
around.
--- For Training Use Only ---
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01-06-05 A109S RFM Section 2
Document N109G0040A013 Normal Procedures
EASA Approved 01-06-05 Page 2-15
LH fuel pump : Drain by raising guard and set-ting FUEL DRAIN switch,located in baggage compart-ment, to VALVE 1 ON (lowerposition).Check for fuel dripping from thedrain and verify FUEL DRAIN 1caution message displayed onEDU1.
Set switch to OFF (center posi-tion).Verify no fuel dripping and FUELDRAIN 1 caution message sup-pressed.
RH fuel pump : Drain by setting FUEL DRAINswitch to VALVE 2 ON (upperposition).Check for fuel dripping from thedrain and verify FUEL DRAIN 2caution message displayed onEDU1.
Set switch to OFF (center posi-tion).Verify no fuel dripping and FUELDRAIN 2 caution message sup-pressed.Lower guard.
RH airframe (A/F) fuel filter : Gently drain while respectivefuel pump is operating. Push redbutton on filter and check for by-pass indication and #2 A/F FFLTR caution message onEDU1.
--- For Training Use Only ---
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Section 2 A109S RFM
Normal Procedures Document N109G0040A013
Page 2-16 01-06-05 EASA Approved
Note
Fuel is pressurized, therefore drainage
should be carried out by gently pushing red
button. Failure to comply with this advice
could result in some fuel being squirted
around.
Check following systems for correct operation:
Navigation and anticollision lights.
Landing lights.
Disconnect the d.c. electrical supply.
External Power (if used) : Disconnect.
BAT switch : OFF.
GEN BUS 1 and GEN BUS 2
switches
: Check automatically to OFF.
Pilot door : Secured.
--- For Training Use Only ---
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01-06-05 A109S RFM Section 2
Document N109G0040A013 Normal Procedures
EASA Approved 01-06-05 Page 2-17
Rev. 1
ENGINE PRE-START CHECK
Pedals and seat : Adjust.
Seat belt : Fasten and adjust.
Doors (RH and LH) : Closed and locked.
Jettison mechanism on doors : Check secured.
Landing gear lever : Check DOWN.
Nose wheel lock : ON (lever up).
Parking brake : Check ON.
Cyclic stick : Centered (or positioned to
counter wind) and friction
adjusted.
Collective lever : Fully down and friction adjusted.
Engine Control Panel:
ENG 1 MODE switch : OFF (fully counterclockwise).
ENG 2 MODE switch : OFF (fully counterclockwise).
OEI TNG (OEI training) switch : Off position (centered).
Overhead Panel:
Circuit breakers : All engaged.
BAT switch : ON.
GEN BUS 1 and GEN BUS 2
switches
: ON.
GEN 1 and 2 switches : ON.
External power : Connect (if required).
--- For Training Use Only ---
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Section 2 A109S RFM
Normal Procedures Document N109G0040A013
Page 2-18 01-06-05 EASA Approved
Note
Be sure that external power source sup-
plies not less than 28 V.
Note
The battery is automatically disconnected
when an external power source is con-
nected to the helicopter. Check that BATT
OFF caution message is displayed on
EDU1 if the external power is used.
Engine power levers : Check FLIGHT.
INV 1 and 2 switches : ON.
LD-SH (Load share) switch : As required.
Note
The LD-SH switch allows the pilot to keep
matched engine TORQUE or TOT, as
required.
Altimeter : Set.
STATIC source switch : NORM and protected.
SERVO (Main hydraulic) : BOTH.
SAS 1 and 2 switches : OFF.
AUTOTRIM switch : AUTOTRIM.
F-TRIM switch : ON.
Electronic Display Units
(EDU1 and EDU2)
: Check on.
Note
BOTH EDUs are automatically activated
when the helicopter is electrically powered.
--- For Training Use Only ---
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01-06-05 A109S RFM Section 2
Document N109G0040A013 Normal Procedures
EASA Approved 01-06-05 Page 2-19
Rev. 1
EDU1 : Select MENU, press TEST key
and check the following test
sequences on both EDUs.
Note
The TEST function can also be selected on
EDU2.
EDU1 : The test sequence shall display
the CRUISE format with the fol-
lowing data:
N1 97.4%
TOT 820 C
TRQ 100%
NR / N2 100%
The caution and warning mes-
sages, simulated by the DAU,
shall be presented in the mes-
sage area during the test routine.
Note
During the test, the DAU will activate the
MWL, MCL and the ENG FIRE warning
message; it will also illuminate the engine
power lever grips and the FIRE warning
lights on the engine control panel. If a fail-
ure is detected on engine fire and/or fuel
low detectors, the caution message FIRE
DET and/or F LOW FAIL will appear.
--- For Training Use Only ---
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Section 2 A109S RFM
Normal Procedures Document N109G0040A013
Page 2-20 01-06-05 EASA Approved
Rev. 1
Note
Due to the short length of the EDU Test,
only one of the ENG FIRE messages is
heard. The ENG FIRE message of the sec-
ond engine can be heard by pushing the
MASTER WARNING RESET pushbutton.
EDU2 : The test sequence shall display
the MAIN format with the follow-
ing data:
ENG OIL pressure 50 PSI
ENG OIL temperature 100 C
XMSN OIL pressure 40 PSI
XMSN OIL temperature 100 C
FUEL pressure 20 PSI
Hydraulic oil pressure 1500 PSI
Fuel quantity Decreasing
OAT +25 C
In the advisory area (lower part
of the screen) the test sequence
shall display:
EDU1 and EDU2 software iden-
tification number.
DAU-A and DAU-B software
identification number.
EDU 1 BIT PASS
EDU 2 BIT PASS
top related