Manual de Voo SA330 SM [PDF]

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EUROCOPTER-FRANCE Edition du : Issue Dated :

SITUATION DES REVISIONS DU MANUEl DE VOl 330Sm FLIGHT MANUAL

05/02/2008

330Sm

REVISIONS STA TUS

This manual must contain the normal revision ( RN ) and rush revisions ( RR ) listed under the relevant issue (EDIT).

1 VOLUME PARTIE REGLEMENTAIRE PRESCRIBED SECTION

PARTIE REGLEMENTAIRE PRESCRIBED SECTION

a

a

SECT.

EDIT

a

1

DATE

RN2

-

07-35

R

RR3A

07-35

R

-

1i4

Ed.1 Ed.1 SLF // 11A FES WB SUP6 SUP3 MC LS PL SUP SUP4 SUPS

II

I

02-38RN.O En RN.O caurs RN.O 02-38 02-38 RN.O RN.O RN.O RN.O RN.O RN.O AD11 RN.O RN. DATE EDIT. A,O,17 JI APPENDIX ANNEXE Pending

SR330Sm MILlTAIRE

I

SECT. a

M

---------

Ed.1

I

1

FLIGHT MANUAL

REVISION 5*RR* 4*RR* 1*RR* 1*RC* 8*RR* 2*RR* 2.1 5*RC* 4*RC* 0.0.P3 0.0.P4 Section 3.2 Pages the List of Effective the acknowledgement card. - Check that the pages inpages. eachor chapter section arefrom thosethespecified •-Return main points of the(added revision. 2.2 3.2 This • page list of affected amended pages modified), may be -filed (apart manual).in the List of Contents and 3.2 PUBLICATION CONCERNED: 330 Srn FLIGHT MANUAL DESCRIPTION OF THE REVISION outline of the revision is given below:

DATE - CODE:

107-451

Page

1/1

SA 330 Sm FLIGHT

REGISTRATION

MANUAL

N°:

SERIAL

IMPORTANT

The

practical

updated.

value

of this manual

The manual's

list of effective

effectivity

depends

W

NOTE

entirely

upon

at the time of the

its being

latest

correctly

revision

is given

in the

pages.

* This manual EUROCOPTER.

covers

the helicopters

All updates provided AEROSPATIALE.

THIS

DOCUMENT

by EUROCOPTER

IS

TO

BE

delivered

follow

CARRIED

by AEROSPATIALE

the same procedures

IN

AIRCRAFT

EUROCOPTER Etablissement Direction Technique Support

and those

as those

AT

ALL

de Marignane - 13725 Marignane

delivered

used

by

by

TIMES

Cedex

. France

0.1

330Sm 02-38

Page 1

FLIGHT MANUAL CONDITIONAL REVISIONS (RC)

This manual assigned to the helicopter mentionned on the title page, contains the following pink pages except those cancelled when the conditions are complied with.

CAUTION IF A NORMAL REVISION (RN) MODIFIES THE PAGE NUMBER FOR ANY INFORMATION CONCERNED BELOW, THE READER WILL HAVE TO CHANGE THE NUMBER OF THE PINK PAGE BY HAND, SO THAT THE INFORMATION REMAINS IN ACCORDANCE WITH THE PARAGRAPH CONCERNED. N°

MOD 07-45 3.2 4 SECTIONPAGE DATE 50727198 before conditions is met: Applicable

O.O.P3

330 Srn

07-45

Page 1

FLIGHT MANUAL CONDITIONAL REVISIONS (RC)

This manual assigned to the helicopter mentionned on the title page, contains the following pink pages except those cancelled when the conditions are complied with.

CAUTION IF A NORMAL REVISION (RN) MODIFIES THE PAGE NUMBER FOR ANY INFORMATION CONCERNED BELOW, THE READER WILL HAVE TO CHANGE THE NUMBER OF THE PINK PAGE BY HAND, SO THAT THE INFORMATION REMAINS IN ACCORDANCE WITH THE PARAGRAPH CONCERNED. SECTION

PAGE

DATE

Applicable before conditions is met:

O.O.P3

330 Srn 02-38

Page 1

2

COMPOSITION OF RUSH REVISIONS (RR) This manual contains the following additional yellow page(s) :

N°

DATEDATE07-45 542 07-45 SECTION 8 1PAGE 0.0.P4PAGE SECTION N°

CODE

O.O.P4

330 Srn

07-45

Page 1

FLIGHT MANUAL COMPOSITION OF RUSH REVISIONS (RR) This manual contains the following additional yellow page(s) : N°

N° PAGEPAGE SECTION SECTION DATE CODE-

O.O.P4

330Sm 02-38

Page 1

FLIGHT MANUAL

RECORD OF REVISIONS

N°sig.sig. INCORPORATED INCORPORATED REVISION dateby date by REVISION

0.2

330 Srn 02-38

Page 1

FLIGHT

MANUAL

LIST OF EFFECTIVE PAGES (1)

Page reV1Slon code - R Revised. to be replaced - N : New. to be inserted 4 7 3 2.3 07-35 5 11 12 07-35 06-15 2.7 2.5 2.4 3 3.2 3.3 RDATE 02-38 02-38 10 8 1 I 2.8 3.2 2 2 6 3.1 1 13 1 2 02-38 2.6 3.3 9 1PAGE 3.1 3P (1) 1SECTION SECTION I 2.4

330

0.3

Srn

07-35

Page 1

FLIGHT MANUAL

4P

2 7 2 1 6 02-38 14 5 3

4.0 4.2 4.5 4.1 4.4 4.3 4P

ISSUE: 1 2 No LATEST NORMALNORMAL REVISION: Date 02-38 07-35 06-15 LIST OF THE 2 1

330

0.3

Srn

07-35

Page 2

FLIGHT MANUAL

TABLE OF RELATED UNITS FRENCH AND ENGLISH

Ib 3,2808 0,0394 TO OBTAIN ftgal inch kt Ib BY CONVERSION 0,00001 FACTORS mm 100000Pa m hPa km/h bar 2,2046 14,5038 0,02953 0,54 25,4 3,7854 0,0689 1,852 0,4536 33,864 0,3048 4,5461 psi UKgal US inHg kg 1 MULTIPLY From metric units to other units MULTIPLY

0.4

330 Srn 02-38

Page 1

FLIGHT MANUAL

LIST OF SYMBOLS AND ABBREVIATIONS USED IN THE MANUAL

SYMBOLS

I French

English Speeds:

Vz Vi Vp Vc Vy VSD V1 VNE Vw

. RlC-RlD IAS . TAS . CAS . Vy . . VTOSS V1 . VNE . Vw .

- Rate of climb or descent.. - Indicated airspeed - True airspeed - Calibrated airspeed - Optimum climbing speed - Take-off safety speed - Critical decision speed - Never exceed speed - Wind velocity Altitudes: -

Take-off or touch-down height Critical decision height.. Pressure altitude Density altitude

h h1 Hp HO'

h h1 lp lO'

Weights: M m MV MVE MOE

Wt . . MTOW EW . EEW . . OEW . AUW

- Weight - Maximum take-off weight.. - Empty weight - Equipped empty weight - Operating empty weight.. - AII-u p we ight

MT

Temperature: -

Outside air temperature, in degrees centigrade

OAT

I

8s

Miscellaneous: - Power - Torq ue - Barometric pressure, in millibars, - Degrees centigrade - Rotor speed - Gas generator speed - Free turbine speed - Exhaust gas temperature - Out of ground effect.. - In ground effect. - Power plant. - Main gearbox - Tail gearbox - Automatic pilot

. . . . . . . . . . . . . .

W C

W Tq Po °C NR

Po °C

NR

Ng

Ng NTL

Nf

t4

t4

OGE IGE ENG MGB TGB AP

HES DES GTM BTP BTA PA

0.5

330 Srn 02-38

Page 1

FLIGHT MANUAL

SECTION 1 LIMITATIONS TABLE OF CONTENTS

1.1

OPERATING LIMITATIONS

1 2 3 1.2

1

1 1 1 2 2 2 5 5 5 5

GAS GENERATOR SPEEDS (Ng) FREE TURBINE RPM (Nf) t4 TEMPERATURE ENGINE LUBRICANTS FUELS FUEL TANK CAPACiTIES

1 2 2 3 4 6

SYSTEM ASSEMBLIES AND HYDRAULIC SYSTEMS

TRANSMISSION SYSTEM ASSEMBLIES HYDRAULIC SySTEMS

1 3

PLACARDS AND INSTRUMENT MARKINGS

1 2

1.7

1

1

RESTRiCTIONS ROTOR SPEED MGB INPUT TORQUE LIMIT COLLECTIVE PiTCH AI RSPEED L1MITS (VNE) ALTITU DES MANOEUVRING LIMITS ROTOR STARTING AND BRAKING L1MITATIONS SLOPE LANDING LAN DIN G GEAR

TRANSMISSION LIMITATIONS 1 2

1.6

WE IG HT CENTER OF GRAVITY LIMITS

POWER PLANT LIMITATIONS 1 2 3 4 5 6

1.5

1 1

FLYING LIMITATIONS

2 3 4 5 6 7 8 9 10

1.4

1

OPERATING CONDITIONS OPERATING ENVELOPE M INIMUM FLIGHT CREW

WEIGHT AND CENTER OF GRAVITY LIMITS 1 2

1.3

Pages

1

INSTRUMENT MARKINGS INSCRIPTIONS AND PLACARDS

3

EQUIPMENT LIMITATIONS

1 2 3 4 5

1

AUTOMATIC PILOT LANDING GEAR WINDSHIELD WIPERS LANDING LIGHT PITOT HEAD

1

1 1 1

1.P

330 Srn 02-38

Page 1

FLIGHT MANUAL

THE "PUMA" 330Sm HELICOPTER IS TO BE OPERATED IN ACCORDANCE LIMITATIONS LAID DOWN IN THIS SECTION.

WITH THE

All airspeeds specified in this section are corrected airspeeds (CAS) unless stated otherwise.

1.1 - OPERATING LIMITATIONS

1 OPERATING CONDITIONS Approved flight conditions: The SA 330Sm helicopter is approved for day and night flying in VFR and IFR conditions when the required equipments are fitted and are serviceable. 2 OPERATING ENVELOPE The altitude limits at take-off and landing are: - 1650 to 13000 ft (- 500 m to + 4000 m). The maximum operating altitude is : + 16500 ft (+ 5000 m). The approved temperature limits are: - 40°C to ISA + 35°C limited to + 50°C. 3 MINIMUM FLIGHT CREW In VFR conditions: one pilot. In IFR conditions: two pilots.

1.1

330 Srn 02-38

Page 1

FLIGHT MANUAL

1.2 - WEIGHT AND CENTER OF GRAVITY LIMITS

1 WEIGHTS

A THE MAXIMUM PERMISSIBLE OPERATING WEIGHT

16300 Ib (7400 kg)

The maximum permissible weight may be limited at a lower figure depending on the external conditions (altitude and temperature).

B MINIMUM PERMISSIBLE WEIGHT

8400 Ib (3800 kg)

2 CENTER OF GRAVITY (CG) LIMITS A LONGTITUDINAL

CG

The origin of the longtitudinal CG is an imaginary plane perpendicular to the aircraft centerline and located 185 in. (4.70 m) forward of the overage CG datum (97.63 in. 2.48 m forward of the cockpit bulkhead). Forward limit

Aft limit

177 in. (4.50 m)

194.7 in. (4.95 m)

.

B LATERAL CG The origin is the symmetry plane of the fuselage. LH limit

RH limit

3.15 in. (0.08 m)

3.55 in. (0.09 m)

1.2

330 Sm 02-38

Page 1

FLI GHT MANUAL 1.3 - FLYING LIMITATIONS

1.

RESTRICTIONS

The following Starting

activities

the engine

are prohibited: with the rotor brake applied,

unless

the wind

strength

is

above 30 kt (54 km/h). Flights in icing conditions. Aerobatics. Steady rearwards

flight, because of exhaust gas return

into the cabin.

Start spinning the rotor in wind speeds above 45 kt (83 km/h). Intentional running landing on soft ground (powdered snow, deep mud). Aircraft Running

nose up attitudes landings

greater than 100 during the final round-out.

above 43 kt (80 km/h).

Flights with doors open above 150 kt (275 km/h). Using emergency power ratings other than in the failure.

case

of

an

actual

engine

Intentional full autorotation landings. Flights with the relative wind from behind when the bleed valve is on NORMAL. NOTE:

With the

For the engine air bleeds,

the autopilot controls

engaged

(cyclic

2.

or disengaged,

stick

pedals when the aircraft conditions.

refer to SECTION

and

height

collective

1.4 paragraph

one of the pilots lever)

and

feet

1.2.

must on

keep

the

hands

yaw

is less than 500 ft (150 m) or when flying

on

control in IFR

MAIN ROTOR SPEED LIMITS

Power-on

flight

Minimum

(transient)

220 rpm

Nomi na 1 ••.•••••••••••••••••••.•••. (NR range: 245-275

265 rpm

rpm)

Max imum

290 rpm

Power-off flight Maximum Minimum

310 rpm

220 rpm if the IAS is lower than 108 kt (200 km/h) 240 rpm if the IAS is above 108 kt (200 km/h). 3. 3.1

3.2

MGB INPUT TORQUE

LIMITS

Sum of the MGB input torque

limits with all engines

-

Maximum

continuous .•.................

-

Maximum ........•.....................

MGB input torque with one engine -

Maximum

operative

(AEO):

156 m.daN

(1300 kw for NR at 265 rpm)

217 m.daN

(1810 kw for NR at 265 rpm)

inoperative

(OEI)

156 m.daN

330

(1300 kw for NR at 265 rpm)

1.3

Srn

02-38

Page 1

FLIGHT

4.

COLLECTIVE

PITCH LIMITS

Hover

16.5° OGE or IGE

Level flight

15.5° for density

altitudes

16° for density altitudes Climbing 5.

AIRSPEED

5.1

Forward

MANUAL

below 3300 ft (1000 m)

above 3300 ft (1000 m)

16.5°

LIMITS

flight

Airspeed

limits depend on the aircraft weight

and density altitude

(see Figure 2). The VNE must be calculated modified Maximum

throughout

take-off

according

Rearward

5.3

Minimum

6.

ALTITUDES

weight,

then

167 kt (310 km/h)

and lateral airspeed

Maximum

to the starting

reduces.

VNE

5.2

-

before

the flight as the weight

flight

30 kt (55 km/h)

in IMC

40 kt (70 km/h)

operating

altitude

Height - velocity

envelope

(see figure

The avoid area is a function The graph

(1) shows

R

20000 ft (6000 m) 1).

of the weight

the envelope

and the external

of the avoi d area

conditions.

of a wei ght of

16300

1b

(7400 kg) at Hp = 2000 ft and for an OAT of + 30°C. Points (B) and conditions. Point weight, The

height and temperature

avoid

temperature Example: For a:

(C) are valid for all weight, (A) is to be calculated from graph

area

does

not

height and temperature (2) as a function of the

conditions.

exist

which give a point

for

those

combinations

(A) height below

Wei ght Press.alL

6500 kg 4000 ft

OAT

+ 20°C

The height of point A is calculated

of weight,

height

and

100 ft (or 30 m).

to be 110 ft (33 m).

330

1.3

Srn

06-15

Page 2

-Y I

FLI GHT

~ ::;;0 0> B

C 50 0 0 20 (kt) 30 10 15 IAS 200- 220 CID OAT ......... + 30 GC

~

CD

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FOR: GROSS WEIGHT .. 7400 kg

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11

MANUAL

w-V ~_

100

200

300

350 (ft)

HEIGHT OF POINT A

16 (Ib x 1000)

WEIGHT

CONDITIONS

HEIGHT VELOCITY ENVELOPE

Figure 1 - Height-velocity

envelope

1.3

330 Srn

06-15

Page 3

I

I

In

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MV.30.0869.01

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~

2000 WEIGHT (Kg)

CONDITIONS L/G down Both engines at take-off Ng or 217rndaN rnax. torque or rnax collective pitch of 16.50 No P2 air bleed

TWIN-ENGINE RATE OF CLIMB AT 45 kt IAS Figure 1

4.2

330 Srn 02-38

Page 2

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1500 WEIGHT (Kg)

CONDITIONS L/G up One engine at max. continuous rating Vy

SINGLE-ENGINE

RATE OF

CLIMB AT Vy (Max. continuous rating) Figure 5

4.2

330 Srn 02-38

Page 6

FLIGHT MANUAL

4.3 - SERVICE CEILINGS

4.3

330 Srn 02-38

Page 1

FLIGHT MANUAL

PRESS.ALT. (x1000Ft)

20

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CONDITIONS One engine at 30 minutes rating RlC 150 ft/mn

SINGLE-ENGINE SERVICE CEILING AT Vy AND 30 MINUTES RATING

Vy

Figure 1

4.3

330 Sm 02-38

Page 2

FLIGHT MANUAL

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6000

(Kg)

CONDITIONS One engine at rnax. continuous rating RlC 150 ftIrnn Vy

SINGLE-ENGINE SERVICE CEILING AT Vy AND MAX. CONT. RATING

Figure 2

4.3

330 Srn 02-38

Page 3

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TWIN-ENGINE

SERVICE

CEILING AT Vy Figure 3

4.3

330 Srn 02-38

Page 4

FLIGHT MANUAL

4.4 - MAXIMUM RANGE IN FULL AUTOROTATION

4.4

330 Srn 02-38

Page 1

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