enstrom 280fx operator manual and faa approved rotorcraft flight manual.pdf

8/17/2019 Enstrom 280FX Operator Manual and FAA Approved Rotorcraft Flight Manual.pdf

1/158

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ATP Grid

Index to

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Publications:

Enstrom

Helicopter

Model

280FX

Operator

Manual

and

FA A

Approved

Rotorcraft

Flight

Manual

ToDic

F

General

Information

Ttle

Page

Record

of

Revisions

Record

of

Temporary

Revisions

Table of

Contents

and

Lst

of Effective

Pages

Lo g

of

Pages

and

Revisions

Lo g

of

Supplements

Section

1 General

Section

2

Operating

Limitations

FAA

Aproved

Section

3 Emer

Malfunction

Procedures FAA

Approved

Section

4 Normal

Procedures FAA

Approved

Section

5 Performance

FAA

Approved

Section

6

Weight

and Balance

Section

7 Arcraft

and

System

Description

Section

8

Insp,

Maint,

Servicing,

Storage

and

Handling

Section

9

Operational

Information

(Reserved)

Section

10

Supplements

Wet/Dry

Dispersal

System

Supplement

No. 1

02/22/2008

Copyright

Aircraft

Technica Publishers

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Topic

Float

Landing

Gear

Supplement

No.

2

External

Loads

Supplement

No. 3

Snowshoe

Supplement

No.

4

(Reserved)

Supplement

No.

5

(Reserved)

Supplement

No.

6

(Reserved)

Supplement

No.

7

(Reserved)

Supplement

No. 8

(Reserved)

Supplement

No. 9

Rotor

Brake

Supplement

No.

10

Auxiliary

Fuel

Tank

Supplement

No.

11

Engine

Exhaust

Muffler

Supplement

No.

12

End

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Copyright

Arcraft Technical

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of

2

E N

0138

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4/158

IVI

FGI

INTRO


5/158

ENSTROM

280FX

OPERATOR

MANUAL

AN

D

F.A.A. APPROVED

ROTORCRAFT

FLIG

HT MANUAL

REPORT

NO. 28-AC-020

TYPE

CERTIFICATENO.

H~ CE

MELICOPTER

SERIAL

~LO.

HELICOPTER REGISTRATION

NO.

THIS

MANUAL

MUST

BE

CARRIED

IN

THEHELICOPTER

AT

ALL

TIMES.

SECTIONS

2,3,4,

AND 5 AREF.A.A.

APPROVED.

SECTION

10

INCLUDES

SUPPLEMENTS

TO

THE

TYPE

CERTIFICATEWHICH ARE

F.A.A. APPROVED IS SODESIGNATED.

F.A.A.

APPROVED

BY:

FORMANAGER

CHICAGOAIRCRAFT

CERTIFICATION

OFFICE

CENTRALREGION

FEDERAL

AVIATION

ADMINISTRATION

DATE:

JANUARY

11.

1985

I


6/158

RECORD

OF

REVISIONS

MFG

REV

NO

DESCRIPTION

ISSUEDATE ATPREVDA INSERTED

BY

5

Library

Addition

617/07 ATP/RD

2/22/2008


7/158

RECORD

OF TEMPORARY

REVISIONS

TEMP

ATP

REV INSERT

DATE

REV

REMOVE

REV

NO

DESCRIPTION

ISSUE

DATE DATE BY REMOVED INCOR

BY

2122/2008


8/158

ENST~IOM

PAGE

HEUCOPTER CORPORATION

280FX

REPORTNO. 28-AC-020

rms 22Mf

SFREET •́

P.O. BOX *BD

MENOM)NEE.

MICHLOANt985&0490

U.S.A.

DATE 1-1 1-85

TABLEOF

CONTENTS

AND

LIST OF

EFFECTIVE

PAGES

SECTION

PAGE

Manual Cover

Table of

Contents and

List ofEffective

Pages

i

thru i

LogofSupplements

ii

I

Log

of

Pages

andRevisions

iv thru

v

1 General

1.0 thru

1.5

1

2

Operating

Limitations

FAA

Approved

2.0

thru

2.9

3

Emergency

and

Malfunction

Procedures

FAA

Approved

3.0 thru

3.10

4

Normal

Procedures

FAAApproved

4.0

thru

4.13

5

Performance

FAAApproved

5.0

thru

5.12

6

Weight

and

Balance

6.0

thru

6.16

7 Arcraftand

SystemDescription

7.0

thru7.8

8

Inspections,

Maintenance,

Servicing,

Storage,

and

Handling

8.0 thru

8.14

9

Operational

Information

(Resenred)

9.0

10

Supplements

10.0

Supplement

1

Wet/Dry

Dispersal System i

10.1.1

thru

10.1.13

Supplement

2

Float

Landing

Gear

10.2.1

tluu10.2.10

Supplement

3

ExternalLoads

10.3.1 thru

10.3.6

Rev.

5

IJUN

710


9/158

THE

E NS TROM

HELICOP~ER

CORPORATION

PAGE

TWIN

COVNPI/IPPORT

p

O

80X

277.

MENOMINEE

MICHIGAN

49858

280FX

REPORT

NO

28-AC-O20

DATE:

1/11/85

SECTION

PAGE

10

Supplements

Continued

Supplement

10.4.1

I

Supplement

5

10.5.1

(Reserved)

Supplement

6

10.6.1

(Reserved)

Supplement

7

10.7.1

(Reserved)

ií •

Supplement

8

10.8.1

(Reserved)

Supplement

9

10.9.1

(Reserved)

Supplement

10

10.10.1

thru

10.10.4

Rotor

Brake

Supplement

11

10.11.1

thru

10.11.7

Auxiliary

Fuel Tank

Supplement

12

10.12.1

Muffler

Revised:

h?9 ;1

291389


10/158

iv

fHE

ENS’TROM

HEtlCOPTER

CORPORAflON

PAGE

280FX REPOATNO.

28-AC-020

TWINCOUNTY

AIRPORT´•P.O.

BOX

277, M E N O M I N E E ,

MICH.

49858

oaTE:

1/11/85

LOG

OF

PAGES

AND

REVISIONS

EV.

NO~I

PAGES

DESCRIPTION

DATE

F.A.A.

APPROVED

1

i

Revised

Contents

1

7-12-85

iv

Added

Revision

Log

2.3

1

Added

Note

2.5

Revised

Limits

2.7

Added

Placard

3.1

Added

Note

4.2

Revised

Description

4.7

1

Added

Paragraph

4.9

Added

Note

7.3

Added

2

Paragraphs

8.11

Added

Paragraph

8.12

Added

Page

8.13

Added

Page

8.14

Added

Page

10.2.1

Added

Float

Landing

thru

Gear

Supplement

10.2.10

2

i,ii

Added

Pages´•

~v

Added

Revision

2

1.4

Minor

Correction

2.3

Added

Note

ar

2.4

J

hru

Moved

Text

2.6

3.2,3.3

Minor

Changes

3.9,3.10

Added

Paragraph

4.6

Minor

Correction

4.9,4.11

Added

Cautions

4.13

Added

Paragraph

5.1

thru

Figures

Redrawn,

5.4

Minor

Correction

7.5

Added

Paragraph

7.6

thru

~ioved

Text,

Added

7.8

28

Volt

System

8.5

Added

28

Volt

System

8.9

Minor

Correction

8.12

Added

Paragraph

APPROVED

FOR

MANAGER

CHICAGO

AIRCRAFT

CERTIFICATION

OFFICE,

v;l CENTRAL

REGION

~I

FEDERAL

AVIATION

ADMINISTRATION

v,

Al

revisions are

indicated

by

a

vertical

black

line,

NOTE:

5 L ~ (

FAA

Approved:


11/158

ENSTROM

PAGE

HEUCOPTER CORPORAtTON

280FX

REPORTNO.

28-AC-020

2208

Pnd

STREET.

P.O.

BOX a9D MENOM)NEE,

MICHIGAN

4985B-aUK)

U.S.A

DATE

1-11-85

LOGOF

REVISIONS

Rev.

Pages

Description

Approval

P.A.A.

Approved*

No. Date

3

n,

m,

v,

7.3,

10.4.1

Corrected EGT

System

5-22-1989 Pat

Moe

description,

added

Snowshoe

Supplement

4

i,

m, v,

10.1.1 thru

Added

Wet/Dry Dispersal

1-11-1991 Richard

S.

Adler

10.1.13

System Supplement

5

i,

v,

2.6, 2.7, 2.8,

2.9,

Added

120 F column

to

VNE

6-8-2007

Joseph

Miess

10.1.2,

10.1.2.1, 10.2.3,

placards.

10.2.3.1

APPROVED

FORMANAGER

CHICAGO

AIRCRAFT

CERTIFICATION

OFFICE

CENTRAL

REGION

FEDERAL

AVIATION

ADMINISTRATION

NOTE

Al

revisions

are

indicated

by

an

black

vertical

line.

Rev.

5

1

JUN

718


12/158

f

Trle ENS1’I~ODI HELICOYI’EI( COKPORATION

PAGE

iii

280FX

REPORT

NO.

28-AC-02

TWIN

C,OUNTY

AIRPORT

P.O.

BOX

27~.

MENOMINEE.

MICHIGAN

JBBSB

DATE:

1/11/85

LO G

OF

SUPPLEMENTS

SUPP.

N O .

P A G E S

DESCRIPTION DATE

_FAA APPROVE

WET/DR

Y DISPERSAL

JAN

1

i

1 9 9 ’ 1

SVSTEM

2

:FLOAT.~-tANDING

GEAR

July

12,

1985

3 EXTERNAL

LOADS

JAN

1

1

~985´•

4

S: OWSHOE

IIAY

It

fj~j

5

RESERVED

6

RESERVED

7 RESERVED

8 RES ERV ED

9

RES ERV ED

10

ROTOR

BRAKE

JAN

11

1 9 8 5

~d

11

AUXILIARY

FUEL

TANK

JAH

11

1 3 8 5 ~

12

~1UFFCER

JUL 16

t986

APPROVED

FO R

MANAGER,

CHICAGO

AIRCRAFT

CERTIFICATION

OFFICE,

CENTRAL

REGION

FEDERAL

AVIATION

ADMINISTRATION


13/158

i

THE:

ENSTHOM

HEI.ICOI’TER

COHPORATION

PAGE

1.0

TWIN

COUNTY

AIRPORI

PO

BOX

277.

MENOMINEE

MICHIGAN

49858

280FX

REPOAT

NO

28-AC-020

DATE:

1/11/85

SECTION

1

G E N E R A L


14/158

THE ENSTROM

COHPORAT1ON

PAGE

1.1

~ilS

280FX

REPORT

NO

28-AC-020

TWIN

COUNTY ARPORT

PO

DOX 277.

MENOMINEE MICH1GAN

49858

DATE:

1/11/85

SECTION 1

GENERAL

I.

INTRODUCTION

This

nianual

contains

the

operating

instructions,

procedures

and

limtations for

the

Enstrom

280FX

helicopter.

The manual

is

divided

into

two

basic

parts,

the

FAA

approved

Rotorcraft

Flight

Manual

(RFM)

and

Suppl

ementa

Data

provi

ded

by

The

Enstrom

Hel

i

copter

Corporation.

Sections

2

through

5 and the

portions

of

Section 10

so

designated

make

up

the FAA

approved

RFM. It

is

required

by

Federa

Regulations

that ths

manual be

carried

in the

helicopter

at al

times.

II.

O W N E R

RESPONSIBILITIES

Maintaining

the

helicopterin

an

airworthy

condition

is

the

responsibility

of the

owner.

(See

Section

8

for

required

inspections.)

To aid

the

owner

in

ths

task

The

Enstrom

Helicopter

Corporation

has

a

network

of

Distributors,

Dealers,

and

Service

Centers.

In

addition

to ths

Operator’s

Manual,

The

Enstrom

Helicopter

Corporation

has

the

following

technical

publications

available

for

your

helicopter:

A.

280FX

Maintenance Manual

Supplement

B.

280FX

Parts

Manual

Supplement

C. Service

Information Letters

D.

Service Directive Bulletins

Information

regarding

dealer

locations,

technical

publications

and

revisions

can

be obtained

by

contacting:

Enstrom

Helicopter

Service

The Enstrom

Helicop.ter Corporation

Twin

County

Airport

PO

Box 277

Menominee,

Michigan

49858

III.

PILOT

RESPONSIBILITIES

A.

The

pilot

is

responsible

for

determining

that the

helicopter

is

safe

for

flight.

B.

The

pilot

is

responsible

for

operating

wthn

the

limtations

specified

in

Section

2.

C. The

pilot

should

famliarize

himself with

the enire

manual

prior

to

receiving

competent

flight

instruction.


15/158

THE

ENSTROM

HEI.ICOrTTER

COHPORATION

PAGE

1.2

~1

280FX

REPORT

NO 28-AC-O2O

TWIN

COUNTY ARPORT

PO

BOX

277.

MENOMINEE.

MICHIGAN

49858

DATE:

1/11/85

IV.

WARNINGS,

CAUTIONS AND

N O T E S

The

use

of

WARNINGS

C AU T

IONS,

and

NOTES

to

emphasize

important

and

critica

instructions

is

defined

as

follows:

A.

W A R N I N G ~ :

Ar,

operating

practice

or

procedure

which,

if

not

correctly

followed,

could

result

in

personal injury

or

loss of life.

B. CAUT

ION: An

operating

practice

or

procedure

which,

if

not

correctly

followed,

could

result

in

damage

to,

or

destruction

of,

equipment.

C.

NOTE:

An

operating practice

or

procedure

which

is

essential and

requires

additional

information.

V.

SPECIFICATIONS

A.

Principal

dimensions

of

280FX

helicopters:

Width

overall 28

ft

Rotor diameter

32

ft

Height

overall

9

ft

Length

overall

29

ft

3

in.

Cabin

width

at

seat 58

in.

Baggage

box dimensions 16

in.

x

18

in.

x

31

in.

Tread

landing

gear

7

ft

4

in.

B.

Power

Plant

Type

Lycoming

Opposed

Designation

HIO-36O-F1AD

Cylinders

4

Horsepower

225

h p

(sea

level to

12,000

ft)

RPM

3050

SFC

(full

rich)

.69

Ib/hp/hr

Weight

357

Ibs

Oil

10

qts

(8

qts

minimum

for

flight)

C.

Ratios

Lower drive

pulley

to

1.213:1

(3050

2514

rpm)

upper

pulley

Upper

pulley

to

main

7.154:1

(2514

351

rpm)

rotor shaft

Engine

to

main

rotor

8.678:1

(3050

351

rpm)

Tail

rotor

input

shaft

to

1:1

output

shaft


16/158

REVISIONS:

ij

c

a

o

o

i~

H

I

9

1 I

o

5

I

I I

~s

(,6.0’1

i

zs- Ils.zn

.isz-

cli.o’,

R~DUS

1.0’

u~x F10 0_6_

I

i

20~

IT~TE

DRW

~8.7´•

r

y

i

i i :

I

t o e

Is.o~

I

~ - r l

03

o

i

LU.*FT

C.C.

11’16.0’)

YIH.DRCCP

~1

D

I,

~n

~o

os’lao~

------I

I I

Om

128.666’)

O

rru

rW

Oo

FIGURE

1.1

EI\ ISTROM

280FX

c~o

N

o


17/158

THE

ENSTROM HEL1COPI~ER

CORPORATION

PAGE

1.4

IWIN COUNTI~POT

PO sox

277

MENO)I(INEE

MCHG*N*g~B

280FX

REPORT

NO

28-AC-020

DATE

1/11/85

D,

Rotor

Systems

Number

of

blades,

main

rotor

3

Chord,

main

rotor

blade 9.5

in.

Disk

area,

main rotor

804

so

ft

Number

of

blades,

tal

rotor

2

Chord,

tal

rotor

blade 4.4

in.

Disk

area,

tal

rotor

17.1

so

ft

E.

Weight

(see

Figure

6.1)

Designed

gross

weight

2600

Ibs

Empty

weight

1570 Ibs

Useful

load

1030 Ibs

C.G.

travel

96.3

in.

to

98.0

in.

at

2600

Ibs

92.0

in.

to 98.8

in.

at

2350

Ibs

92.0

in.

to

100.0 in,

at

2000 lhs

NOTE:

Four

gross

weight-c.g.

envelopes

apply

to

ths

helicopter,

see

Figure

6.1.

Each

envelope

is associated

with

a

dfferen

maximum

ceiling

and

a

dfferen

V N E

limitation,

see

Figure

5.1.

VI.

PERFORMANCE

(All

altitudes

are

density

altitude

and

performance

based

on

a

2350

lb

gross

weight

unless

otherwise

noted.)

A.

Maximum

speed

V N E

power

on

117

mph

IAS~from

SL

to

3000

ft

H d .

See

Figure

5.1

V N E

power

off

85

mph

IAS from

SL

to

8200

ft

H

See

Figure

5.1

NOPE: Four

dfferen maximum

cei~ing/VNE

enue~opes

app~y

to

ths

helicopter,

see

Figure

5.1.

Each

envelope

corresponds

to

a

gross

weight/c.g.

envelope,

see

Figure

6.1.

B.

Cruise

speed

75 %

power

110

mph

IAS at

sea

level

C.

Maximum

cruise

speed

117

mph

TAS

at

sea

level

122

mp h

TAS at

3000 ft

H d

D.

Maximum

range

speed

85

mph

IAS

at

sea

level

Issued:

1/11/85

~I

Revi

sed:

12/14/88


18/158

THE

ENSTROM

HELICOI’7’EH

COHPORATION

PAGE

1.5

TWIN COUNTY

AIRPORT

PO

BOX

277.

MENOM1NEE.

MICHIGAN

49858

280FX

REPOAT NO

28-AC-020

DAIE:

1/11/85

E.

Fuel

consumption

at

14.7

gal/hr

75 %

power

F.

Maximum

endurance,

no

reserve

3.5 hrs

57

mph

IAS

at

sea

level

G.

Fuel

capacity

42

gal

(40

gal

usable)

H.

Maximum

R/C

at sea

level

1450

ft/min

I.

Hover

ceiling

IGE

13,600

ft

(see

Item

K)

J.

Hover

ceiling

OG E

8700

ft

K.

Maximum

approved

operating

12,000

ft,

see

Figure

5.1

atitude


19/158

THE ENS’PHOM

HEI.ICOPTEH

COHPORATION

PAGE

2.0

TWIN

COVNTY

AIRPORT

PO.

BOX

277.

MENOMINEE

MICH(GAN

49858

280FX

REPORT NO

28-AC-020

DATE:

1/11/85

SECTION 2

OPERATING

LIMITATIONS

FAA

Approved:

1/11/85


20/158

THE ENSTROM

HELICOPTER

CORI~OHA1’ION

PAGE

2.1

280FX REPOAT

NO. 28-AC-020

TWIN COVNTY AIRPORT

PO BOX

277.

MENOMINEE

M(CHIGAN

49858

DATE

1/11/85

SECTION

2

OPERATING LIMITATIONS

I.

TYPE

O F

OPERATION

A. This

helicopter

is

approved

for

operation

under

day

and

night

VFR

non-icing

conditions.

NOTE:

Night

operation

authorized

under visual

flight

rules

only.

Orientation

must

be

maintained

by ground light

o

adequate

ceestia

illumination.

B.

Operation

with doors

removed is

approved.

II.

WEIGHT

A.

The

maximum

gross

weight

of

ths

helicopter

is

2600

pounds.

See

Figure

6.1.

III.

CENTER

OF

GRAVITY

(All

airspeeds

are

IAS unless

otherwise

noted.)

A. The

longitudinal

datum

is 100.0 inches forward of

the

center

of the

main

rotor

head.

B. There

are

four

gross

weight/c.g.

envelopes

for

this

helicopter.

See

Figure

6.1. Each

envelope

corresopnds

to

one

of

four

VNE/altitude

envelopes

as

described

in

paragraph

IV.

Also,

see

Figure

5.1.

C.

Envelope

A

is the

lightest

weight envelope

with

a

V N E

of

117

mph

at

sea

leve.

The

c.g.

and

gross

weight

limts

vary

as

follows:

1.

Upper weight

limt

is

2350

Ibs.

2.

Forward

limt

at

92.0

inches.

3. At limt

varies

linearly

from 94.6

inches

at

2350

Ibs

to

100.0

inches

at

2000

Ibs.

Aft

limt

at

100.0

inches below

2000

Ibs.

-I

FAA

Approved:

1/11/85


21/158

f~

THI:ENJ.IIIOM ~IRI.ICOPI.EII

CI)KPOH*TION

Pa E

2.2

280FX

REPORT NO

28-AC-020

TWIN

COUNTY

ARPORT

PO

BOX

277.

MENOMINEE

MICHIGAN

49858

DATE:

1/11/85

O.

Envelope

B

is

the

nex

heavier

envelope.

It

has

a

V N E

of

104

mph.

The

c.g.

and

gross

weight

limts

var_v

as

follows:

i.

Upper

weight

limt

is

2450

lbs.

2.

Fo

rwa

rd limt

varies

linearly

from

93.8

inches

at

2450

Ibs

to

92.0 inches

at

2350

Ibs.

3.

Aft

limt

varies

linearly

from

96.0 inches

at

2450

Ibs

to

99.2 inches

at

2240

pounds

and

100.0

inches

at

2000

Ibs.

4.

The lower

limt

corresponds

to the

upper

forward

and

aft

limts

of

Envelope

A.

E.

Envelope

C

has

a

V N E

at

sea

level

of

91

mph.

´•The

c.g.

and

gross

weight

limts

vary

as

follows:

i.

Upper

weight

limtis

2550

Ibs.

2.

Fo

rwa

rd limt

varies

linearly

from 95.5 inches

at

2550

Ibs

to

93.8

inches

at

2450

Ibs.

3. Aft

limt

varies

linearly

from

97.3 inches at 2550

Ibs

to

98.4

inches

at

2470

Ibs

and

then

to 99.2

inches at

2240

Ibs.

4. Lower

limt

correspondes

to the

upper

forward and

aft limts of

Envelope

B.

F.

Envelope

D is

the

heaviest

envelope.

It has

a

V N E

at

sealeve~ of

85

mph.

The

c.g.

and

gross

weight

limts

vary

as

follows:

1.

Upper weight

limt

is 2600

Ibs.

2. Forward limt

varies from

96.3

inches at 2600 Ibs

to

95.5

inches

at

2550

Ibs.

3.

Aft limt

varies

linearly

from

98.0

inches

at

2600

Ibs to

98.4

inches

at

2470

Ibs.

4.

Lower

limt

corresponds

to the

upper

forward

and

aft

limts

of

Envelope

C.

G. The

latera

datum line is

the

centerline

of the

helicopter.

L

a

te

ra

moment

arms

are

positive right

and

negative

left.

H.

Lateral

offset

moment limts

vary

with

weight.

See

Figure

6.2.

i.

From 2025

Ibs

to

2600

Ibs,

limts

are

-3250

in-’lbs and

+3700

in-lbs.

2.

Below

2025

Ibs,

see

Figure

6.2.

FAA

Approved: 1/11/85


22/158

THE

ENSTROM

HELICOPTER CORPORATION

PAGE

2.3

280FX

REPORTNO

28-AC-020

TWIN

COUNTY

ARPORT

P

O

BOX 277.

MENOMINEE

MICHIGAN49858

DATE:

1/11/85

IV.

AIRSPEED

Never

exceed

speed

( Y N E )

117

mph,

IAS,

sea

level

to

3000

ft

density

altitude. See

Figure

5.1

for

variations

above

3000

ft

and for

variations

with

gross

weight/c.g.

NOTE:

There

are

four

VNE/altitude

envelopes

which

apply

to

ths

helicopter.

Each

envelope corresponds

to

one

of four

gross

weight/c.g.

envelopes.

See

Figure

5.1.

V.

ALTITUDE

Maximum

approved

operating

a ti

tude

12,000

ft

density

al

t

tu

de at

2350

lbs. For

variations

of atitudewith

gross

weight,

see

Figure

5.1.

N O T E :

Takeoffs

and

landings

at

2600

Ibs

gross

weight

were

demonstrated

to 7000

ft

density

altitude

in al

wind

conditions

up

to

20

mph.

DO

N OT EXCEED

ENGINE

LIMITATIONS.

Takeoffs

and

landings

at

2350

Ibs

gross

weight

were

demonstrated

to

10,000

ft

density

altitude

in

al

wind

conditions

up

to

15

mph.

Operators

should

use

appropriate

caution

above

10,000

ft

density

atitude

and

in

winds

greater

than

15

mph

to

insure

safe takeoffs

and

landings.

VI.

ROTOR

RP M

A.

Flight

limtations

power

on

Minimum: 334

rpm

Maximum:

351

rpm

B.

Flight

limitations

power

off:

Minimum:

334

rpm

Maximum:

385

rpm

See

Section

8

for

adjustment

procedures.

NOTE:

During

trancient

maneuvers,

such

as

simulated

power

faluredurin

pilot

training,

the

rotor

RP M

may

fal

below

334.

These

maneuvers

have been

demonstrated with

rotor RP M

dropping briefly

to

280,

however,

sufficen

time

and

altitude

must

be

available

to

regain

RPM.

NOTE:

The

helicopter

is

equipped

with

a

low

rpm

warning

device.

Operating

the

helicopter

below

334

rpmwith

the

collective off

the

down

stop

wll

automatically

activate

a

warning

horn.

v,

FAA

Approved: 1/11/85

Revised:

12/14/88


23/158

THE

ESSTROM


PAGE

2.4

,,IN,,,,Y

280FX REPORT

NO

28-AC-020

DATE:

1/11/85

VII.

P O WER

PLANT

LIMITATIONS

L Y C O M I N G

HIO-360-F1AD

Engine

Modified

per

Enstrom

Turbocharger

Kit

LW-14460

A.

Maximum

continuous

power:

22hp,

3050

rpm,

39.0

in.

M P,

sea

level

to

12,000

ft

B.

Engine

operating

rpm:

Minimum:

2900

rpm

Maximum:

3050

rpm

C.

Engine

idle

rpm

clutch

disengaged

Minimum:

1450

rpm

Maximum:

1500

rpm

D.

Manifold

pressure:

39.0

in.

Hg,

sea

level

to

12,000

ft

E.

Cylinder

head

temperature:

500 F

maximum

F.

EGT: 1650 F

maximum

G.

Fuel:

100/130

aviation

grade

gasoline

(green)

100LL

aviation

grade

gasoline

(blue)

H.

Fuel mixture

setting:

1.

29

in. M P

or

below

a.

Maximum

fuel

flow

ful

rich

b.

Minimum

fuel flow

leaned to

1650 F

rich

side

of

peak

2.

29

in.

Mg to

39.0

in.

M P

(full

rich)

Oil

temperature:

2450

maximum

J.

Oil

pressure:

100

psi

maximum

starting

and

warm

up

60-90

psi

normal

operating

28

psi

minimum

idling

VIII.

TRANSMISSION

LIMITATIONS

Transmission

ol

temperature:

225 F

maximum

FAA

Approved:

1/11/85

a Revised:

12/14/88


24/158

THE

ENSTROM

CORPORATION

PAGE

2~5

,,IN

280FX REPORTNO

28-AC-020

DATE:

1/11/85

IX.

RESTRICTIONS

A.

Instrument

flight

prohibited.

B.

N o aerobatic

maneuvers

permitted.

C.

Hovering

IGE

above

10,000

ft

density

altitude

is

limited to five

minutes.

X.

MINIMUM

CREW

A.

One

pil6t.

8.

Solo

from

left

seat

only.

XI.

INSTRUMENT MARKINGS

A.

Rotor

tachometer

i. 334

rpm

red

line

2.

334-385

rpm

green

are

3. 385

rpm

red

line

B.

Engine

tachometer

1. 2900

rpm

red

line

2.

2900-3050

rpm

green

are

3. 3050

rpm

red

line

C.

Maximum

airspeed

1. 85

rriph

(power

off)

blue

line

2. 117

mph

(power

on)

red

line

D.

Manifold

pressure

1.

10

in.

to

39

in.

green

are

2. 39.0

in.

H Q

red

line

3. Overboost

light

illuminates

at

39

in.

manifold

pressure

E.

Engine

ol

temperature

1. 245 F

red

line

2.

120

245 F

green

are

3.

60

120 F

yellow

are

F.

Engine

ol

pressure

1.

100

psi

red

line

2.

60-100

psi green

are

3.

25-50

psi

yellow

are

(ijl

4.

25

psi

red line

0

FAA

Approved:

1/11/85

v,

Revised:

12/14/88


25/158

8

VSTRQM

PAGE

2.6

HELICOPTER

CORPORATION

280FX REPORTNO.

28aC-020

22M)

synd STREET

P.O. BOX 490

MENOMINEE,

MICMGAN

19858-0080

U.S.A.

DATE

1-1 1-85

G.

Cylinder

head

temperature

1.

500 F

red

line

2.

200

500

F

green

are

H. Exhaust

gas

temperature

1.

1650 F Maximum

(digital

readoutwth

placard)

I. Transmission oil

temperature

1.

225 F

red

line

2.

0

225

F

green

are

XII.

PLACARDS

A. Placards

that

are

required

to

be

placed

inview

of the

pilot

are:

1.

THIS

HELICOPTER

MUST

BEOPERATED

IN

COMPLIANCE

WITHTHE

OPERATING

LIMITATIONS

SPECIFIED

INTHE

FAA

APPROVED

ROTORCRAFT

FLIGHT

MANUAL

2,

PLACARDS

FOR280FX

VN E

(located

overhead

above

center

windshield):

I

a.

The

following

V,

placards

are

used

on

all 280FX

helicopters

up

to

serial number

2132.

2699

v~-

IAS

(MPHJ

FOR

ENVECOPE

’A ’

2400

ALTITUDE

-20

O

20

40

60

80

100

A

D

8

PRESSURE

PIR

SEALEVEt

117

117

117

117

117 117

117

3

2000

117

117 117

117

117

114 109

g

2200

4000

117

117

117

115

110 105

96

A

8

2000

6099

117

116

11 1

105 96

87

78

8000

112

107

96

87

78 69

60

t s o 8 S

10,000

99

BE

78

69

59

28-1 80045-11

94

96

98

109

12000

8 1

70

60

CG-lnches

2600

VNE’

IAS

~MPH)

FOR

ENVELOPE

’B’

D

415 TEMPERANRE

F

c i

PRESSURE

c ~

2400

ALnNDE

-20

9

20

40

60

80 iDO

B

SEA

LEVEL

104

104 104

104

104 104

104

B

9 8

~ZMO

2000

104

1(34

104

104

104

102

W

A

4000

104

104 104

102

99

94

85

moo

6000

104

193 99

95

85

76

68

8000

100

96

8 6

76

67

58

lao~

10,000

89

78

68

58

2&1 80046-11

94

96 98

100

1

800

8 1

70

60

CG •́lnches

FAA

Approved:

June

8,

2007

Rev.

5

JUN 710


26/158

ENSTROM

PAGE 2.7

HELICOPTER

CORPORATION

280FX REPORTNO. 28-AC-020

2209

22nd S~FIEET

P.O.

BOX 490~

MENOMINEE.

MICHIGAN*9B5~BDU.SA

DATE

1-1

1-85

2. PLACARDS FOR280FX

V,,

a.(continued)

2600r

VNE’

IAS

(MPH)

FOR

ENVELOPE

’C’

d

PRESSURE

I

OUTSIDEAIR

TEMPERATURE

2400

ALTITUDE

-20

0

20

40 60

80

100

r

B

Y ( c ~

I

SEALEVEL

91

9 1

91 91 91 91 91

2 2 9 9 /

2000

91

91

91

91

1

91

89

1

87

A

4000 91

91

91

90

87

83

74

2000

6000

91

90

87 83

74

65

57

C

8000

88

85 75

65 56

28-1 80047-11

9609

8 1

71

61

94

96

98

100

GO-inches

2600r

771

n

VNE’

IAS

(MPH)

FOR

ENVELOPE

’D ’

PRESSURE

;TURE

’F

-20

0

20

40

60

80

100

2499

ALTITUDE

SEA

LEVEL

85 85 85

85

85 84 83

(3

2000

85 85

85

84 83 82

8 1

L

85

84 83 82

B1

78

69

V)

A

40M)

2090

6000

83

82

8 1

79

69 59

8000

8 1

80 70

60

28-180048-1

i

i

9000

80 71

60

D

4

96

98 inn

CG-lnches

b. The

following

VN E

placards

are

used

on

all

280FX

helicopters

serial

number 2133 and

subsequent.

280FX

helicopters

up

toserial number

2132

may

also

use

the

following

placards.

VNE’

IAS

(MPH)

FOR EN

VELOPE

’Al

ALTINDE

-20

O

20 40

60

80

100

120

A

RESSURE

OUTSIDE

AIR

TEMPERANRE’F

SEA

LEVEL

117 117

117 117

117 117

117

117

2000 117 117 117 117 117 114 109 104

4000

117

117

117 115 110

105

96

87

2000

6000 117

116 1 11

105

96

87

78

69

o

8000

112

107

96 87

78

69 60

1BO~

1 000

99

88 78

69

59

94

96

98 100

2&1 80045-13

12,000

8 1

70

60

CG-lnches

FAA

Approved:

June

8,

2007

Rev. 5 1 JUN7/0


27/158

8

VSTROM

PAGE

2.8


280FX

REPORTNO. 28-AC-020

2209 22nd

s7ReEf

P.a.

BOX

MENOMINEE,

MICHIGAN

498589a90

U.S.A.

DATE

1-1 1-85

2.

PLACARDS

FOR

280FX

V,,

b,

(continued)

/L*r -~L-D

V N E -

(AS

(MPH)

FOR

ENVELOPE

(B1

2600

c~

PRESSURE

2400

-20 0

20 40 60 80

100 120

B

SEA LEML 104

104

104

104

104

104

~04

104

B

g

2200

A

4000

104

104

104

102 99 94

85 76

0

2000

6000 104

103

99 95 85 76

68 60

8000

100 96

86

76 67 58

1 8 0 9 ~

10,000

89 78

68 58

2&1 80046-2

3

94 96

98 198

10,800

8 1

70

60

CG-Inches

2600

c~

D

v,,-

IAS

(MPH)

FOR ENMLOPE’C’

PRESSURE

TURE’F

2400

ALTI

-20

0

20 40

60

80 100

120

t

SEA

LEVEL 91

9 1 9 1

9 1

9 1 91 9 1 9 1

B

2000

9 1 91 91

91

9 1

89

87

85

4000

9 1 91

9 1

90 87 83

74

65

v,

A

C :

sooo

9 1 90

87

83

74 65

28-180047-13

C

7

1

8000

88 85

75

65

56

1

9600

8 1 71

61

92 94 96 98 100

GO-inches

2800 VNE’

IAS

(MPH)

FOR ENVELOPE ’D’

PRESSURE

I

OUTSIDE

AIR

TEMPERATVRE

’F

2400

TINDE

-20

0

20 40 60

80 100

120

SEALEML

85

B5

85

85

65 84 83

82

B

00

2DOO 85

86

85

84

83 82 B1 80

V)

A

4000

85 84

83

82

8 1 78 69

60

8000

83

1

82

8 1

79 69

59

8000

8 1

80 70 60

28-1

8004&13

leoo~i

9000 80 71

60

D

4

96

98

100

CC-Inches

3.

NOSMOKING

(This placard

not

required

when

approved

ashtray

is

installed.)

FAA

Approved:

June

8,

2007

Rev. 5 JUN

710


28/158

8

NSTTZOM

PAGE 2.9


280FX

REPORTNO. 28-AC-020

2208

22nd

STREET́ • P.O.

BOX

460 •́

MENOMINEE,

MICHLGAN

(685&0490

U.S.A

DATE

1-1 1-85

4.

THIS HELICOPTER IS APPROVEDFOROPERATION

UNDERDAYANDNIGHT VFR

NON-ICING

CONDITIONS

ONLY

5. COLLECTIVEFRICTIONTOBEUSED

FOR

GROUND

OPERATIONONLY

(This

placard

tobe

placed

adjacent

to

the collective

friction

device.)

B. A

placard

tobe

placed

in

the

baggage

compartment

is

as

follows:

MAXIMUMWEIGHT

INTHIS COMPARTMENT IS

108

LBS.

OBSERVE

C.G.

AND GROSS WEIGHT

LIMITATIONS

C.

STOWFLAT

ON

FLOOR

BEFORE

FLIGHT

(This

placard

to

be

placed

on

clutch

handle.)

FAA

Approved:

June

8,

2007 Rev. 5 JUN

710


29/158

?‘)(E

ESSTHOM HEI.ICO’rEM

COHPORA~I‘ION

PAGE

3.0

TWIN COUNTY

AIRPORT

PO BOX 271.

MENOM(NEE MICHIGAN

49858

280FX

REPORT

NO.

28-AC-020

DATE:

1/11/85

SECTION 3

EMERGENCY

AND

MALFUNCTION PROCEDURES

v,

FAA

Approved:

1/11/85


30/158

~4

P GE

3~1

´•4´•

280FX

REPORT

NO

28-AC-020

TWIN COUNTY A1RPORT

PO

BOY

271

MENOMINEE MICHIGAN

49858

DnTE:

1/11/85

SECTION 3 EMERGENCY

AND

MALFUNCTION

PROCEDURES

I.

GENERAL

This section

describes

the

system

falures

and

malfunctions

that

may

occur

and establishes the

emergency

procedures

used

to

maintain

control

and

get

the

helicopter

safely

on

the

ground.

II.

ENGINE FAILURE

The

indcations of

an

engine

failure,

ether

partial

or

complete

power

loss,

are

a

left

yaw

and

a

drop

in

engine

and

main rotor

rpm.

NOTE:

Loss of

rotor

rpm

wll

result

in

a

low

rpm

warning

light

and horn.

When these conditions

are

encountered

the

procedures

to be

followed

are

determined

by

the atitude and

airspeed

available

to

establish

an

autorotative

glide,

while

maintaining

control

of

the

helicopter

and

sufficien rotor

rpm

fora

successful

landing.

A.

Engine

Failure

Atitude above

375

ftAGL.

When

engine

falure

occurs

proceed

as

follows:

1.

Enter

autorotation

(collective

ful

down,

throttle to

idle and

right

pedal

to

trim

helicopter).

2. Sablize

a´•t’58

mph

glide

(best

rate

of

descent

speed).

CAUTION:

Due

to

high

rates

of

descent,

sustained

autorotation

speed

is

limted

to

85

mph

to

8200

ft;

above

8200 ft

see

Figure

5.1.

Maximum

glide

distance

in autorotation

is

attained at

80

mph

and

334

rotor

rpm.

Reduce

colective

to

buld

rpm

prior

to

touchdown.

3.

Check

engine

and

rotor

rpm.

Adjust

colective

to

keep

rotor

in

green

are.

If

engine

is

stopped,

turn

OFF

fuel

boost

pump

and

place

mixture

control in

ICO

position.

If

atitude

and

time

permit,

see

Ar

Restart

Procedure,

Page

3.2.

4.

Select

landing

site.

NOTE:

If

engine

is

running

and

suitable

landing

ste

is

not

wthn

glide

distance,

the

pilot

should

attempt

to

fly

the

helicopter

at

reduced

power

settings

to

a

favorable

landing

area.

The

pilot

should

be

prepared

for a

complete

loss

of

power

at

any

time

under

these

conditions.

5.

At

approximately

50

ft

AGL

apply

aft

cyclic

to

reduce

speed.

FAA

Approved:

1/11/85

Revised:

7/12/85


31/158

TI(E

ESSIHI)M

HEI.I(’OI’TEI( COHI’OI(ATI()S

PAGE

3.2

COUNTY

*(F~YORT P

O BOX 2~).

MENOMINEE.

~ltHIGAN a9858

280FX

REPORTNO

28-AC-020

DATE

1/11/85

6. Level

helicopter

with forward

cyclic

at

an

atitudesufficien

to

provide

tal

rotor

clearance.

As

heliCopter

settles toward

ground, apply

up

colective

to

cushion

landing.

7.

Maximum recommended

ground

conact

speed

on

prepared

surfaces

is

35

mph.

Reduce

speed

on

rough

surfaces.

CAUTION: Avoid

rapid

lowering

of

collective

or

use

of aft

cyclic

after

ground

contact

or

during

ground

side.

3.

Ar Restart

After

an

engine

falure

in

flight

the

decision

to

attempt

a

restart

wll

depend

on

the

atitude

and

potentia

landing

areas

available.

C AU T ION:

Helicopter

control

is

primary

concern

after

entering

autorotation.

DO

N OT

attempt

ar

restart

if

control

wll

be

jeopardized.

DONOT

attempt

ar restart

when

below

3000 ft

AGL.

1.

Adjust

colective

as

required

to maintain

rotor

rpm

in

green

are

and establish

58

mph

autorotative

glide.

2.

Select

landing

site.

3.

Grip

cyclic

between

knees

and

wth

right

hand

turn

fue

boost

pump

OFF

and

pull

mixture control

to

ide

cut

off.

4.

Rotate

throttle

to start

position

(start’index

up).

5.

Engage

starter.

6.

When

engine

fires,

mxureful

rich

and

boost

pump

ON.

7.

Slowly

increase

throttleunil

engine

and

rotor

tach

needles

join

in

green

ae

C.

Engine

Failure

Atitudeabove

10

feet

and below

375

ft

AGL.

When

an

engi

ne

falure

occurs

at low

atitude

and

low

airspeed,

sufficien

atitude

may

not

be

available

to

increase

rotor

rpm.

The

colective

must

be

adjusted

for

tile

conditions

in

order

to reach

the

touchdown

point

without

excessive

rotor

droop.

The

collective

reduction

wll

vary

from

no

reduction

at

zero

airspeed

and 10

feet

to

ful

down

colective

at

higher

altitudes

and

airspeeds.

When

engine

falure

occurs

proceed

as

follows:

i.

Adjust

colective

to

maintain rotor

rpm,

throttle

to

ide

position

and

right pedal

to

trim

helicopter,

FAA

Approved:

1/11/85

Revised:

12/14/88


32/158

6~

TI(E

EESTIUI

HBI.ICOI7LN

COHÍ •IIII~Tl(l\i

pact

3.3

´•1)

280FX

REPORTNO

28-AC-020

TWIN

COVNTI

*IRPO(I~

PO BOX

2r3

MENOMINEE MICHIGAN

~9858

DATE:

1/11/85

2.

Adjust

cyclic

for

autorotative

glide.

NOTE:

At

higher

atitudes

and

low

airspeed

use

forward

cyclic

to

increase

forward

speed

to

approximately

58

niph.

At

low

altitudes

and

higher airspeed

aft

cyclic

wll

be

required

to

reduce

speed

prior

to

ground

contact.

3.

At

atitude

of

approximately

50

ft

AGL

use

aft

cyclic

to

reduce

forward

speed.

4.

Level

helicopter

with forward

cyclic

at

an

atitude

sufficen to

provide

tal

rotor

clearance.

5. As

helicopter

settles

toward

the

ground

apply

up

collective

to

cushion

landing.

6.

Maximum

recommended

ground

conact

speed

on

prepared

surfaces

is

I

35

mph.

Reduce

speed

on

rough

surfaces.

CAUTION:

Avoid

rapid

lowering

of

collective

or

use

of

aft

cyclic

after

ground

contact or

during

ground

side.

D.

Engine

Failure at

Hover

in

Ground Effect

Engine

Cai~ure at a

hover is

indicated

by

a

sudden

yawing

of

the

helicopter

to

the

left.

Avoid

sideward

or

rearward

movement

after

engine

falure

and

proceed

as

follows:

i.

Apply right

pedal

to

prevent

yawing

and

aign

s~ids

in drection

of

motion.

2. DO

NOT reduce

colective.

3. As

helicopter

settles

to

the

ground,

add

up

collective

to

cushion

landing.

III.

DITCHING WITHOUT

P O WER

If

engine

falure

occurs

over

water,

accomplish

engine

falure

emergency

procedure

and

proceed

as

follows:

k.

Unlatch

doors.

B.

Land.

Complete

nornia

autorotational

landing

in

water.

C.

As

colective

reaches

ful

up

position

and

helicopter

settles

in

water,

apply

ful latera

cyclic

in

direction

helicopter

tends

to

j j ~ s

FAA

Approved:

iii1/85

~I

Revised:

12114188


33/158


34/158

dP

TIIE

pciGE

3,5

280FX

REPORT

NO

28-AC-020

TWIN

tOVNTY AIRPORT

PO

BOY

21i MENOMINEE

MICHIGAN 19858

DATE: 1/11/85

i. Land

at nearest

suitable

landing

area.

2.

Inspect

for and

correct

this

source

of trouble

before

continuing

flight.

B. Total

Loss

of Oil Pressure

If

a

tota loss of

ol

pressure

is

acconipanied by

a

rise

in

ol

temperature,

ths

is

a

good

indcation

that

the

engine

falure

is

imminent.

Proceed

as

follows:

i.

Reduce

engine

power

immediately.

2.

Select

a

suitable forced

landing

fied

and

land wth

power.

VII.

TAIL

ROTOR MALFUNCTIONS

Because

of the

many

different

malfunctions that

can

occur,

success

in

coping

with tal rotor

malfunctions

depends

upon

recognition

of

the

condition and

use

of

the

proper

emergency

procedure.

The

following

is

a

description

of

the

three

basic

types

of

malfunctions and

the

appropriate

emergency

procedures

to

A.

Complete

Loss

of

Tail Rotor

Thrust

This

condition

can

be

caused

by

a

falure

of

the tal

rotor drive

system

or

a

falure

of

the

contro7

system

which would al7ow

the

blades

to

assume a

neutral

pitch

condition.

i.

Hovering flight

When tal

rotor

thrust

is lost

in

hovering

flight

the

helicopter

wll

rotate

rapidly

to

the

right,

even

with

ful

application

of

left

pedal.

Proceed

as

follows:

a.

Roll

throttle

off.to

ful

ide

position. Helicopter

wll

slow down

or

stop

rotation.

b. As

helicopter

settles to

ground,

cushion

landing

with

up

colective

(throttle off).

2.

During

flight

near

suitable

landing

area

Helicopter

wll

rotate

to

right

with

ful

application

of

left

pedal.

Proceed

as

folows:

a.

Roll

throttle

ful off

to ide and

ener

autcrotation.

b.

Complete

autorotational

landing.

FAA

Approved:

1/11/85


35/158

~9

P*~E

3~6

~Q,

280FX

REPORT

NO

28-AC-020

TWIN

COVNTY ARPORT PO

BOX 2:.

MENOMINEE

MICnlGAN

19858

DnTE:

1/11/85

3.

During

flight

If

sutabe

landing

area

is

not

available wthn

autorotative

glide

distance,

pilot

should

proceed

as

follows

after

establishing

autorotation

at

60

niph

o

above:

a.

Increase

colective

pitch

and

power

gradually,

maintaining

60

to

80

mph

unil

yaw

to

the

right

reaches

a

maximum of

45

b. Conti

nue

f

ight

in

this

fa

s

h

i

on

using cycl

i

c

stick

for

drectiona

control unil

sutabe

autorotational

landing

site

is

reached.

c.

Complete

autorotational

landing.

B.

Fixed Pitch

Setting

This

is

a

malfunction

involving

loss

of

control

resulting

in

a

fixed

pitch

setting.

Whether

the

nose

wll

rotate

left

or

right

depends

upon

the

setting

of

the

pedals

when the

controls

were

jammed

or

locked.

i. Fixed

right

pedal

´•If the

tal

rotor

pitch

becomes

fixed

during

an

approach

or

low

power

setting,

the

nose

wll

turn

to

the

right

when

power

is

applied.

Proceed

as

follows:

a.

Remove

feet

from

pedals.

b. Maintain

24

inches

manifold

pressure

and

50

mph.

c.

Fly

to suitable

area

and

complete

a

shallow

power

on

approach

at

50

mph.

d.

Adjust

throttle

and

colective

pitch

so

the

helicopter

touches

down

straight

ahead

at

an

airspeed

of 0-10

mph.

Reduce

throttle and

colective

cautiously

as

skids

conact

surface.

CAUTION:

DO

NOT

abort

the

emergency

landing

after

airspeed

has diminished

below 40

mph.

i.

Fixed left

pedal

If

the tal

rotor

pitch

becomes

fixed

during

cruise

or

high

power

settings,

the

helicopter

wll

yaw

to

the left

when

power

is

reduced below

23

in,

manifold

pressure.

Power

settings

above

23

in.

manifold

pressure

wll

produce

near

norma

flight

-I

conditions

at

airspeeds

above

60

mph.

Proceed

as

folows.

FAA

Approved:

1/11/85


36/158

l.ilE

ETSTIII)X

HRI.ICI)I?EII COil’llli\.llO~

P GE

3.7

280FX

REPORT

NO

28-AC-020

T~N

COVNTY

AIRPORI PO

BOX 217

MENOMINEE

MICnlGAN n4BSfi

DATE 1/11/85

a.

Fly

to

suitable

landing

area

at

a

power

setting

of

at least

23

in.

manifold

pressure

and 60

mph

o

above.

b.

Complete

a

shallow

power-on

approach

at

60

mph.

CAUTION:

DO

N OT

AUTOROTATE.

c.

Adjust

throttle

and

collective

pitch

so

that

the

helicopter

touches

down

straight

ahead

at

an

airspeed

of

O

to

10

m ph .

d.

Reduce

throttle

and

colective

pitch

cautiously

as

skid

gear

contacts

surface.

NOTE:

Application

of

power

to

settings

greater

than

23

inches

manifold

pressure

wll

make

the hei-

copter

more

controllable.

Therefore,

landing

attempt

may

be

aborted and

new

approach

intiated

if

required.

C.

Loss of

Tal Rotor

o

Components

The amount

of

weight

lost

wll determine

the

helicopter

reaction

If

a

smal

amount

of

weight

is

lost

the

situation would be

similar

to

a

loss

of

thrust stuation.

If

a

large

amount

of

weight

is lost and

there is

a

drastic

forward

shft

in

C.G.,

immediate autorotation

is

the

only

emergency

procedure

avalabe.

VIII.

MAIN

ROTOR

GEARBOX

A.

Transmission

Temperature

If the main rotor

transmission

temperature

exceeds

red

line,

reduce

power.

If

the

temperature

remains

above red

line,

make

a

power-on

landing

as

soon as

possible.

B.

Elain

Rotor

Transmission

Chip

Light

If

the

main rotor

transmission

chip

light

comes

on

in

flight

and

the

transmission

temperature

is

below

the red

line,

monitor

the

tempera-

ture

and

land

as soon

as

practicable.

On

landing,

renove

and

inspect

the

chip

detector

(see

NOTE).

~f the

main rotor

transmission

chip light

is

acconipanied

by

high

transmission

temperatures,

land

as

soon as

possible.

C. Tail

Rotor

Transmission

Chip

Light

If

the

tal rotor

transmission

chip light

comes on

in

flight,

make

a

power-on

landing

as soon as

practicable

and

inspect

the

chip

detector

(see

NOTE).

-I

FAA

Approved:

1/11/85


37/158

B

PAGE

3.8

;QI

1WIN COUN-Y

r\lRPORI

PO

BOX

lil.

MENOUINEE

UICnlGAN ,9858

280

F

X

REPORT

NO

28-AC-020

DATE

1/11/85

NOTE:

New

or

recently

overhauled

gearboxes’

generate

a

ferrous fuzz which

wll

colect around

the

chip

detector

as

a

gray

sludge.

This

type

of

contamination

is

norma

and

may

be

cleaned off

\Jith

a

soft

cloth,

and

the

chip

detector

may

be

renstaled and

the

flight

continued.

A ny

metalic

chip greater

than

1/16

inch

in

diameter

or

cross

section,

o

chip light

accompanied

by

high

transmission

temperature

is

cause

for

discontinuationof

norma

flight.

In

the

event

of

finding

large

chips,

please

cal

your

nearest Enstrom

service

center

or

the

Enstrom

factory. Specific

instruc-

tions

in

removal,

checking

and

renstalation

of

the

chip

detector

may

be

found in Section

8,

paragraph

V

~k),

page

8.11.

IX. FIRE

IN

FLIGHT

If

fire,

smoke,

or

the

odor of smoke

is

detected

in

flight, proceed

as

fol lows:

A.

Land

immediately

using

power-on

approach.

B. Turn the

master

and

aternator

switch to

the

OFF

position.

C.

Ifsmoke

obstructs

vision,

unlatch doors

and

let

them

tral

open.

D.

Shut

off

engine

as

soon

as

helicopter

is

on

the

ground.

E.

Fuel

valve

OFF.

F.

Plot and

passengers

Cleay~_the

helicopter

immediate~y.

X.

FIRE

ON THE GROUND

if

fire,

smoke,

or

the odor of smoke is

detected,

proceed

as

follows.

A. Shut off

engine

and

al

switches.

8.

Shut

fue

valve

OFF.

C.

Plot and

passenger

clear

the

helicopter

immediately.

XT. ALTERNAIOR

MALFUNCTION

A

malfunction

of

the

alternator

wll

be

indicated

by

zero

charge

rate

or

constant

discharge

on

the

ammeter.

To

put

the aternator

back

on

the

line,

proceed

as

follows:

A.

Aternator

circut breaker

in.

B.

Aternator

excte

circut

breaker

in.

~I

C.

Cycle

aternator

switch.

w

FAA

Approved:

1/11/85


38/158

C

THE

ESLi7WOy

HEI.ICOII‘ER

COHI’OHATION

PAGE

3.9

280FX

REPORT

NO

28-AC-020

TWIN

COUNTY

*IR~ORT

PO BOY

277 MENOMINEE

UICHIGAN 198Y)

DATE

1/11/85

D.

If

aternator

is

not

restored

or

goes

off

the

line

again,

turn

off

al

nonessential

eectrica

equipment

and

land

as

soorl

as

practicable.

XII.

ELECTRIC

BOOST

PUMP

FAILURE

Failure

of

the

eectric

fuel

boost

pump

wll

be

indicated

by

illumination

of

red,

low

boost

warning

light.

The

engine

wll

continue to

function.

Ii

the

low

boost

warning

light

comes

on,

land

as soon

as

practicable.

XIII.

CL UTCH

DISENGAGEMENT

LIGHT

ON

Should

the

manual

clutch

become

disengaged

during

flight,

itwll resut

in

an

instantaneous

engine

overspeed

and

severe

left

yaw

if

manifold

pressure

is

much

above

ide.

These

indications

wll

be

instantaneous

and

the

pilot

should

immediately

ener

autorotation.

An

indi

cati

on

of

a

clutch

disengagement

without

engine overspeed

or

severe

yaw

may

mean

that

a

clutch

disengagement

is

probable

or

that

the microswitch

or

eectrica

circut

has

malfunctioned.

The

pilot

should

proceed

as

follows:

A.

Clutch

Disengagement

Light

on

with

Motion

Cues

1. Enter

autorotation

and

reduce

power

to

ide.

2.

Perform

autorotative

landing.

3.

Inspect

for

and correct

the

source

of trouble

before

continuing

flight.

8.

Clutch

Disengagement

Light

on

without

motion

cues

i. Reduce

power

and

be

prepared

for

sudden

clutch

disengagement.

2.

Land at nearest

suitable

landing

area.

CAUTION:

Be

prepared

for

autorotation

should clutch

become

disengaged.

3.

Inspect

for

and

correct

the

source

of

trouble

before

continuing

flight.

XIV.

ABN O RMAL

VIBRATIONS

Vibrations in ths can

usually

be

cassfied

as

ether

low

frequency

or

high frequency.

Low

frequency

vibrations

are

generally

caused

by

the

main

rotor

system

while

the

high frequency

vbrations

usually originate

from

the

engine,

drive

sys

tem,

or

tal

rotor.

Any

abnormal

vbrations are

an

indication

that

something

is

not correct

and

should

be

referred

to

a

mechanic

before

further

flight.

If

a

vbration

suddenly

appears

during

a

flight,

it

is

an

indication

that

something

has

suddenly

changed.

The

helicopter

should

be

landed

as

soon as

practical

FA~

kpproved:

1j /85

Revised:

12/14/88


39/158

6;

THE

ENS1’HOM HELICOPI~F:H

COHPOHA’I’ION

PAGE

3.10

TWIN COUNTY

AIRPDR‘T PO

BOX

277.

MENOMINEE.

MICHIGAN

99858

280FX

REPORT

NO

28-AC-020

DATE:

1/21/85

XIV.

ABN O RMAL

VIBRATIONS

CONT.

and

inspected

to

find

the

cause

of

the

vbration. Ater

the

cause

of

the

vibration has been

indentified,

the

pilot

and

the

mechanic

can

determine

whether

the

helicopter

can

be

safely

flown

or

should

be

repaired

on

the

spot.

An

abnorma

vbration

is

reason

to

get

the

arcraft

down

as

soon as

possible,

but

the

pilot

must

also

use

caution

and

select the safest

possible

landing

s

i

te

working

around

wi

res

people,

and other

obstructions.

FAA

Approved:

12/14/88


40/158

THE

ENSTROM HfSI,ICO~TER

CORPOHA1‘ION

PAGE

4.0

280FX

REPORT

NO.

28-AC-020

TWIN

COUNTY

AIRPORT

PO

BOX

277.

MENOMINEE

MICHIGAN

49858

DATE:

1/11/85

SECTION

4

NORM AL

PROCEDURES

-s

FAA

Approved:

1/11/85


41/158

(Q

TWH RNSTHOM HBI.ITOI~BH

CURPOR*710N

PnoE

4.1

´•1)

TWIN COUNTY

ARPORT PO BOX

27).

MENOMINEE

MICHIGAN

49858

280FX REPORTNO 28-AC-020

DATE:

1/11/85

SECTION

4 N O R M A L

PROCEDURES

T. PREFLIGHT

PLANNING

A.

Review and be

famliar with

Section

2,

Operating

Limitations.

B.

Calculate

weight

and

balance and review

loading

information

in

Section

6,

Weight

and

Balance.

C.

Obtain

weather

briefing

and

file

flightplan.

D.

Refer

to

Section

5,

Perfo

ma

nce

to

determi

ne

if

helicopter

is

within

limitations

for

planned

loads, winds,

temperatures

and

pressure

altitudes.

NOTE: Plot

experience

and

training

is another factor

to

consider

prior

to

conijucting

certain

flights,

even

if

helicopter

is

wthnits

operating

envelope.

E.

Check

helicopter

and

engine log

books

to

determine

if

helicopter

is

airworthy.

II.

PREFLIGHT INSPECTION

This

checklist

is

designed

to

be

used

as

a

guide

while

performing

the

preflight inspection.

Thoroughly

famliarize

yourself

with

the

Maintenance

Manual

before

utilizing

ths checklist.

A.

Cabin

Prior to

starting

the

exterior

inspection,

check

the

cabin

for

the

following

items:

i.

Standard Airworthiness

Certificate,

FAA Form 8100-2.

2. Certificate

of

Arcraft

Registration,

AC

Form

8050-3.

3. If

communications

radio

is

instaled

Arcraft Radio

Stations

License

FC C Form

556.

4.

Flight

Manual

for

helicopter

to

be

flown.

Check

forms

F-165A

and

F-168A

in

Section

6

for

actual

weight

and

balance

of

helicopter

to

be flown.

The

serial

number

of

the

helicopter

to

be

flown should

appear

on

these

forms.

NOTE:

The above

items

are

to

be carried in the

helicopter

at

al

times.

Owners and

operators

of

exported

helicopters

should

check

with

ther

own

Aviation

Oficias

to

determine

documents

required.

~I

FAA

Approved:

1/11/85


42/158

THE

ENSTHOM

COHI’OHATION

PAGE

4.2

280FX REPORTNO

28-AC-020

TWIN COUNTY AIRPORT

PO BOX

277 MENOMINEE

MICHIGAN

49858

DATE:

1/11/85

5.

Master

switch

OFF.

6.

Ignition

switch

OFF.

7. All

other

switches

OFF.

8.

Fuel

valve

ON .

B.

Exterior

Inspection

i.

Remove

covers

and

tie-downs.

2.

Left

door check

condition,

security

and latch

operation.

3.

Windshield

check

condition.

4. Ptot

tube

unobstructed.

5.

Landing light

check

condition.

6.

Kight

door

check

condition,

security

and latch

operation.

7.

Right

oleo

struts

Srut

extension

may

be

checked

with back

side

of fuel

dipstick.

NOTE:

Align

fuel

dipstick

with

centerline

on

fairing

bump.

i

Sight

across

top

of

cross

tube

normal

operating

levels

are

indicated

on

the

stick.

TOP

OF

CROSS

TUBE

BACK

SIDE

OF

FUEL DIP

STICK

CENTERLINE FAIRING BUMP

8.

Right landing

gear

check

condition and

security.

Check

ground

handling

wheel

removed

or

in

up

position

and

secured.

9.

Right

side

engine

compartment.

a.

Eectrica

wiring

condition and

terminals

tight.

b. Induction

system

no

obstructions,

filter

secure,

induction

hose

and

lines

secure

and

backfire

and

alternate

ar

doors

free.

c.

Fuel

filter

secure

and

drain fuel

sample

into

jar.

d. Fuel

lines

secure

and

no

signs

of

leakage.

e.

Oil lines-

secure

and

no

signs

of

leakage.

~jl

f.

Exhaust

no

cracks

or

signs

of

leakage.

g.

Cowl

door

secure.

~s

FAA

Approved:

1/11/85

~I

Revised:

7/12/85


43/158

f~

TnE

ENETROM

HFÍ •ICOIT*-R

CollrOH*TION

P E

4´•3

280FX

REPORT

NO

28-AC-020

TWIN COVNTY

AIRPORT

PO BOX 277.

MENOMINEE

MICHIGAN

49858

DATE:

1/11/85

10.

Upper inspection

door.

a.

Fuel tank

drain drain

sample

into

jar.

b.

Swashplate

and control

rods

check

condition

and

security.

c.

Fuel tank

and

lines

check for leaks

and

lines and

fitting

secure.

d.

Fire

curtain check

condition.

11.

Kick-in

step

door.

a.

Belt

drive

system

check

security

and

condition

of

ider

pulley,

main

drive

belt.

b. Tail

rotor

drive shaft

check

condition

of

flex

coupling.

c.

Rotor tach

drive check

condition.

d.

Cooling

fan check

condition.

12.

Right

fuel

tank.

Check for

leaks,

fuel

quantity

and

cap

secured.

13.

From

steps.

a.

Check main

rotor

gearbox

filler

cap

closed.

b. Check

area

between fuel

tanks

for

leaks

and

obstruction

to

ar

flow.

c.

Main

rotor

shaft check

condition.

d. Main

rotor

blades

security

and

condition of

leading edge

blade

tape,

no

bond

separations,

cracks

or

corrosion.

Main

rotor

retention

pins

secured.

e.

Check main

rotor

hub for

security

of al

fasteners,

no

cracks

or

obvious

damage.

f.

Main

rotor

pitch

links check for

binding

or

looseness.

g.

Main

rotor

dampers

check

for

security

and

no

leakage.

14.

Baggage

box.

a.

Check

contents

secured.

Observe

weight

limtations.

b.

Open inspection

door

check main

rotor

transmission

sight

gauge.

Normal

level

is

halfway

mark

on

sight

gauge.

c.

Door

secured.

15.

Right

static

port

check

unobstructed.

16. Tail

cone

check

condition.

17.

Horizontal and vertica

stablizers

check

condition and

security.

18.

Position

and

ani-colision

lights

check

security.

-I

FAA

Approved:

1/11/85


44/158

dr4

P*GE

4~4

C~

TWIN

COUNTY

AIRPOAT PO 80X1r7. MENOMINEE MICHIGAN

49858

280FX

REPORT

NO 28-AC-020

DATE:

1/11/85

19.

Tail

rotor

a.

Control cables

check

condition

and

security.

b.

Tail

ro

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