section 1 limitations - helicopter...

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 ---

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


A109S RFM Section 1


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


Section 1 A109S RFM


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


A109S RFM Section 1


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


Pressure (Emergency).............................................. 1-54


Section 1 A109S RFM


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


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.


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


A109S RFM Section 1



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


Section 1 A109S RFM



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


A109S RFM Section 1



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


Section 1 A109S RFM



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


A109S RFM Section 1



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.


Section 1 A109S RFM



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A109S RFM Section 1



Rev. 1

Figure 1-6 Altitude / OAT Envelope


Section 1 A109S RFM



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


A109S RFM Section 1



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.


Section 1 A109S RFM



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)


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%


A109S RFM Section 1




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


TURBINE OUTLET TEMPERATURE (TOT)

Engine Starting

Maximum at Starting (2 seconds)...............................................875 C


Maximum Continuous ................................................................840 C

Take-Off Range (5 minutes) ............................................841 to 900 C

Transient (20 seconds).............................................................1000 C


Maximum Continuous ................................................................900 C

2.5 minutes Range ..........................................................901 to 970 C

Transient (20 seconds).............................................................1000 C

Note



Section 1 A109S RFM



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.


A109S RFM Section 1



ROTOR LIMITATIONS (NR)

POWER-ON (AEO)

Transient ........................................................................................95%

Minimum.........................................................................................99%

Continuous Operation (except take-off and landing)...........99 to 101%


Maximum......................................................................................102%

POWER-ON (OEI)

Transient ........................................................................................85%

Minimum ........................................................................................90%

Cautionary Range .................................................................90 to 98%

Continuous Operation (except take-off and landing)...........99 to 101%


Maximum......................................................................................102%

POWER-OFF

Transient ........................................................................................90%

Minimum.........................................................................................95%

Continuous Operation ......................................................... 95 to 110%

Maximum...................................................................................... 110%


Section 1 A109S RFM



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



A109S RFM Section 1



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)


Section 1 A109S RFM



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


A109S RFM Section 1



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


Section 1 A109S RFM



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


A109S RFM Section 1



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


Section 1 A109S RFM



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.


A109S RFM Section 1



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.


Section 1 A109S RFM



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.


A109S RFM Section 1



Rev. 1

PLACARDS

Figure 1-7 Cockpit placards (Sheet 1 of 2)


Section 1 A109S RFM



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)


A109S RFM Section 1



Figure 1-8 Baggage compartment placards


Section 1 A109S RFM



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


A109S RFM Section 1



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.


Section 1 A109S RFM



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)


A109S RFM Section 1



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)


Section 1 A109S RFM



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)


A109S RFM Section 1



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)


Section 1 A109S RFM



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)


A109S RFM Section 1



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)


Section 1 A109S RFM



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)


A109S RFM Section 1



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)


Section 1 A109S RFM



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)


A109S RFM Section 1



Rev. 1


START format (AEO)

50%

TOT

MAX. CONTINUOUS 840C

TAKE-OFF 900CSTART LIMIT 875C


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)


Section 1 A109S RFM



Rev. 1

TOT

50%


TRANSIENT 875C


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)


A109S RFM Section 1



Rev. 1

0%


0%

START format (AEO)

TRQTRQ

TRANSIENT 110%

TAKE-OFF 107%

MAX. CONTINUOUS 100%

TAKE-OFF 107%


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%


Section 1 A109S RFM



Rev. 3

XMSN OVTRQ


0%

TRQ


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


A109S RFM Section 1



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)


Section 1 A109S RFM



Rev. 1


20%

N2 NR

TRANSIENT 112.4%

102%MAX TAKE-OFFAND LANDING

99%

90%


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)


A109S RFM Section 1



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)


Section 1 A109S RFM



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 2

225

#1(2) OIL PRES

When engine oil pressure

is outside limits:

+ WARNING

Figure 1-26 EDU2 (MAIN) - Engine Oil Pressure


A109S RFM Section 1



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 2

225

#1(2) OIL HOT

when engine oil temp. > 125C

Figure 1-27 EDU2 (MAIN) - Engine Oil Temperature


Section 1 A109S RFM



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 2

225

XMSN OIL PRES

when transmission oil pressure < 30 psi

+ WARNING

Figure 1-28 EDU2 (MAIN) - Transmission Oil Pressure


A109S RFM Section 1



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 2

225

XMSN OIL HOT

when transmission oil temp. > 120C

+ WARNING

Figure 1-29 EDU2 (MAIN) - Transmission Oil Temperature


Section 1 A109S RFM



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 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


A109S RFM Section 1



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 2

225

Figure 1-31 EDU2 (MAIN) - Fuel Pressure


Section 1 A109S RFM



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


A109S RFM Section 1



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


Pressure (Normal)


Section 1 A109S RFM



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


Pressure (Emergency)


A109S RFM Section 2


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


Section 2 A109S RFM


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


A109S RFM Section 2


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


Section 2 A109S RFM


Page 2-iv 01-06-05 EASA Approved

This Page Intentionally Left Blank


01-06-05 A109S RFM Section 2

Document N109G0040A013 Normal Procedures


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.


Section 2 A109S RFM

Normal Procedures Document N109G0040A013


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.





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


Section 2 A109S RFM



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.





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.


Section 2 A109S RFM



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)


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.





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.


Navigation and position lights : Condition.

External Power door : Secured.

Battery door : Secured.

Area N3 (Tailboom - RH side)

Tailboom exterior : Condition.


Lower anti-collision light : Condition.

Stabilizer : Condition and secured.


Section 2 A109S RFM



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.


Tail rotor driveshaft cover : Open.

Tail rotor driveshaft bearings : Condition and secured.

Check for grease leaks.

Tail rotor driveshaft cover : Secured.





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.


Section 2 A109S RFM



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.





Rev. 1

Main transmission and accesso-

ries (visible area)


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)


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.


Section 2 A109S RFM



Co-pilot cabin door and window : Condition, cleanliness, sealretainer and secured.


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.





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.


Section 2 A109S RFM



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.





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.


Section 2 A109S RFM



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.





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).


Section 2 A109S RFM



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.





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.


Section 2 A109S RFM



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

section 1 limitations - helicopter...

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