ENSTROM 280F Operator's Manual

ENSTROM

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level of the 280F Rotorcraft Flight Manual.

UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

280F

OPERATORS MANUAL

AND

F.A.A. APPROVED

ROTORCRAFT FLIGHT

REPORT NO.

TYPE

CERTIFICATE

HELICOPTER SERIAL

HELICOPTER

THIS MANUAL MUST ALL

TlMES.

SECTION CERTIFICATE

10

REGISTRATION

SECTIONS

INCLUDES SUPPLEMENTS

WHICH

28-AC-019

NO.

NO.------

BE

CARRIED

2,3,4,

ARE

AND 5 ARE

F.

A.A.

MANUAL

HlCE

NO.

____

IN

THE

APPROVED

HELICOPTER

F.

A.A. APPROVED.

TO

THE

IF

_

AT

TYPE

SO

DESIGNATED.

FOR CHICAGO

CENTRAL

MANAGER

AIRCRAFT CERTIFICATION OFFICE

REGION

FEDERAL AVIATION ADMINISTRATION

DATE=

REVISED:

DEC.31,1980

Novernber.

7,1989

Page: i

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level of the 280F Rotorcraft Flight Manual.

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280F

Report No: 28-AC-019 Date: 2/14/17

TABLE OF CONTENTS

AND

LIST OF EFFECTIVE PAGES

SECTION PAGE Manual Cover Dated December 31, 1980

as revised Table of Contents and List of i thru ii

Effective Pages Log of Supplements iii Log of Pages and Revisions iv thru vi

EASA Log of Revisions vii

EASA Log of Supplements viii 1 General 1.0 thru 1.5 2 Operating Limitations – FAA Approved 2.0 thru 2.7 3 Emergency and Malfunction Procedures 3.0 thru 3.11

FAA Approved

4 Normal Procedures 4.0 thru 4.13 5 Performance – FAA Approved 5.0 thru 5.12 6 Weight and Balance 6.0 thru 6.16 7 Aircraft and Systems Description 7.0 thru 7.8 8 Inspections, Maintenance, Servicing, 8.0 thru 8.15

Storage and Handling 9 Operational Information 9.0 10 Supplements 10.0 Supplement 1 10.1.1 thru 10.1.13

Wet/Dry Dispersal System Supplement 2 10.2.1 thru 10.2.10

Float Landing Gear

Page: ii

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level of the 280F Rotorcraft Flight Manual.

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280F

Report No: 28-AC-019 Date: 2/14/17

SECTION PAGE 10 Supplements - Continued Supplement 3 10.3.1 thru 10.3.6

External Loads Supplement 4 10.4.1

Snowshoe Supplement 5 10.5.1

(Reserved) Supplement 6 10.6.1

Right Side Pilot Configuration Supplement 7 10.7.1

(Reserved)

Supplement 8 10.8.1 thru 10.8.9 Emergency Float Landing Gear

Supplement 9 10.9.1 (Reserved)

Supplement 10 10.10.1 (Reserved)

Supplement 11 10.11.1 thru 10.11.11 (Reserved)

Supplement 12 10.12.1 (Reserved)

Page: iii

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level of the 280F Rotorcraft Flight Manual.

UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

280F

Report No: 28-AC-019 Date: 2/14/17

LOG OF SUPPLEMENTS

SUP.

NO

DESCRIPTION DATE FAA APPROVED

1 Wet/Dry Dispersal System 12-31-80 C. E. Arnold 2 Float Landing Gear 12-31-80 C. E. Arnold 3 External Loads 12-31-80 C. E. Arnold 4 Snowshoe 12-31-80 C. E. Arnold 5 (Reserved) 6 Right Side Pilot Configuration 6-26-81 C. E. Arnold 7 (Reserved) 8 Emergency Float Landing Gear 11-20-81 C. E. Arnold

9 (Reserved) 10 (Reserved) 11 Auxiliary Fuel Tank 9-23-83 J. Hannen 12 Engine Exhaust Muffler 7-16-86 P. Moe

APPROVED FOR MANAGER CHICAGO AIRCRAFT CERTIFICATION OFFICE,

CENTRAL REGION

FEDERAL AVIATION ADMINISTRATION

FAA Approved: March 28, 2017

9 THE ENSTROM HELICOPTER CORPORATrON

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level of the 280F Rotorcraft Flight Manual.

UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

TWIN

COUNTY

AIRPORT•P.O.BOX 277. MENOMINEE,

MICH.

4985B

280F

PAGE REPORT

DATE:

NO.

iV

28-AC-019

ll/17/80

REV. NO.

1

2

LOG

PAGES

FM

10-2-1

thru

10-2-6

AlL

OF

PAGES

DESCRIPTION

Revised Supplement

Restricted

Add

Category Envelope

Revised Manual Altitude

in

Both Normal and

Restricted Additional Changes

Changes are black since affected.

for

not

vertical all

Basic

Increased

Capability

Categories.

Minor

and

in

this

indicated

pages

AND

Float

to

Flight

Correction

rev

is

by

line

were

REVISIONS

DATE

6/26/81

1/30/84

io

F.A.A. APPROVED

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~~--------------------------------------------------------~

CENTRAL FEDERAL

NOTE:

All

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::>

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u......,.

o

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changes

i

~ii

,iv,

1.4,1.5,

2.1

thru

2.7,5.1 thru 5.1

6.2,6.8,

6.11'

10.1.5,

10.1.7,

10.1.8,

10.2.2,

10.2.3,

10.2.

FOR

REG I

AVIATION

A

11

ows

weight to

Normal

the

for

SIN

or

if

meets the of

Enstrom

Drawin~

6.1

7'

(continued

MANAGER,

ON

are

indicated

increased gross

2500

Jbs

in

Category

1517 and

the

helicopter

requirement~

Specificati

#28-100015

on

CHICAGO

Subse

uent

n

p. i

v)

At

RCRAFT CERTIFICATION OFFICE,

ADMINISTRATION

by a

black

vertical

7/1/84

line

along

right

margin.

-~

This electronic document is not linked to a subscription for revision control or distribution. Refer to theTechnical

Publications Status link under the Technical Support Page of the Enstrom Helicopter website for the current revision

level of the 280F Rotorcraft Flight Manual.

UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

~

TWIN

THE

ENSTROM

COUNTY

AIRPORT•

HELICOPTER

P.O.

SOX

277, MENOMINEE,

CORPORATION

MICH.

49658

280f

PAGE REPORT NO. DATE:

V

28-AC-019

ll/17/80

REV.

(cont'd)

NO.

3

4

LOG

PAGES

10.2.9,

10.2.10,

10.

3.2'

10.3.3,

10.11.2

ll~h~~

7

i

iv

2.3

2.7

4.6

4.7

7.3

7.4

thru

7.8

8.12

8.13

8.14

OF

lContinued)

Added

Revised

Added

Revised Added

Moved

Added

PAGES

.DESCRIPTION

pages instruction

p 1 instruction

paragraph text

autorotation

figure figure

aca

rd

AND

rpm

REVISIONS

DATE

7/1/84

F.A.A. APPROVED

~

;z.q

flt)G

85

~~

I

-.

V')

z

0

5 .

APPROVED CENTRAL FEDERAL

i

i i

iii

.

v thru vi

1.4

2.3

2.4

2.5

2.6

3.2

3.3

3.g

4.7

4.11

4.13

5.1

thru

;·!

FOR

REGION

MANAGER

AVIATION

Changed/Added

.1\dded

Changed Changed I Added

Minor

Added 11oved Moved Moved

~li

~inor

Added tl.dded Added Added

Figures Redrawn,

rtinor Correction

~~rlnrl

Suppl

Page

Correction

Note

Text Text Text

nor Changes '

Changes

Paragraph Cautions Cautions

Page

Paraoranh

CHICAGO

ADMINISTRATION

Pages

ernent

Pages

AIRCRAFT

'"

~~t.

CERTIFICATION

K

h

OFFICE,

"'

>

w

NOTE:

All changes are

indicated

by

a black

vertical

line

along

right

margin.

Page: vi

This electronic document is not linked to a subscription for revision control or distribution. Refer to theTechnical

Publications Status link under the Technical Support Page of the Enstrom Helicopter website for the current revision

level of the 280F Rotorcraft Flight Manual.

UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

280F

Report No: 28-AC-019 Date: 2/14/17

LOG OF PAGES AND REVISIONS

REV. NO PAGES DESCRIPTION DATE FAA APPROVED

5

(cont’d)

7.6 thru

7.8

8.5

8.15

10.12.1

Moved Text, Added 28-Volt System

Added 28-Volt System Added Page Added Page

Dec 14/88 Pat Moe

6 4.7, 4.9 Corrected Page Numbering Error Nov 7/89 Pat Moe

7

8

i

vi

3.10 thru

3.11

i, ii, iii, vi

vii, viii

4.1, 4.2,

4.3, 4.4

10.7.1

Revised List of Effective Pages FAA Approval Added Lamiflex Bearing Failure

Emergency Procedures

Updated Added EASA Approval Logs Added Fuel Management

Inspection Checklist (Content removed, Reserved)

Jul 9/12

J. Miess

10.10.1

(Content removed, Reserved)

APPROVED FOR MANAGER CHICAGO AIRCRAFT CERTIFICATION OFFICE,

CENTRAL REGION

FEDERAL AVIATION ADMINISTRATION

FAA Approved: March 28, 2017

Page: vii

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level of the 280F Rotorcraft Flight Manual.

UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

280F

Report No: 28-AC-019 Date: 2/14/17

EASA LOG OF REVISIONS

REV.

NO

1 Sep 28/03 Article 3, Commission Regulation (EU) 748/2012 N/A 2 Sep 28/03 Article 3, Commission Regulation (EU) 748/2012 N/A 3 Sep 28/03 Article 3, Commission Regulation (EU) 748/2012 N/A 4 Sep 28/03 Article 3, Commission Regulation (EU) 748/2012 N/A 5 Sep 28/03 Article 3, Commission Regulation (EU) 748/2012 N/A 6 Sep 28/03 Article 3, Commission Regulation (EU) 748/2012 N/A 7 Aug 17/15 FAA/EASA T.I.P.* G. J. Michalik 8 Aug 16/17 FAA/EASA T.I.P.*

DATE EASA APPROVED

FAA APPROVAL ON

BEHALF OF EASA

* Section 3.2 T.I.P.

FAA Approved: March 28, 2017

Page: viii

This electronic document is not linked to a subscription for revision control or distribution. Refer to theTechnical

Publications Status link under the Technical Support Page of the Enstrom Helicopter website for the current revision

level of the 280F Rotorcraft Flight Manual.

UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

280F

Report No: 28-AC-019 Date: 2/14/17

EASA LOG OF SUPPLEMENTS

SUP.

NO

1

2 Float Landing Gear Sep 28/03

3 External Loads Sep 28/03

4 Snowshoe Sep 28/03

DESCRIPTION DATE EASA APPROVED

Wet/Dry Dispersal

System

Sep 28/03

Article 3, Commission

Regulation (EU) 748/2012

Article 3, Commission

Regulation (EU) 748/2012

Article 3, Commission

Regulation (EU) 748/2012

Article 3, Commission

Regulation (EU) 748/2012

5 [Reserved]

6

Right Side Pilot

Configuration

NOT EASA APPROVED

7 [Reserved]

8

Emergency Float

Landing Gear

Sep 28/03

Article 3, Commission

Regulation (EU) 748/2012

FAA APPROVAL ON

BEHALF OF EASA

N/A

9 [Reserved]

10 [Reserved]

11 Auxiliary Fuel Tank Sep 28/03

12 Engine Exhaust Muffler Sep 28/03

Article 3, Commission

Regulation (EU) 748/2012

Article 3, Commission

Regulation (EU) 748/2012

FAA Approved: March 28, 2017

N/A

TWlN

This electronic document is not linked to a subscription for revision control or distribution. Refer to theTechnical

Publications Status link under the Technical Support Page of the Enstrom Helicopter website for the current revision

level of the 280F Rotorcraft Flight Manual.

UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

THE

COIJNN

ESSTROM

AIFIPCIFI7

HEUCOPTER

~

P 0 BOX

:277.

CoRPORATION

MENOMl"'EO:. MJCH'GAN

~&856

280F

PAGE

REPORT NO. DATE·

1.0

28-AC-019

11/17/80

SECTION

1

GENERAL

Vi

z

0

~

~l.

Issued: 12/31/80

..

~R:e:vl~·s~e:d~:~l~/~3~0~/8:4:.

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

...

··-

This electronic document is not linked to a subscription for revision control or distribution. Refer to theTechnical

Publications Status link under the Technical Support Page of the Enstrom Helicopter website for the current revision

level of the 280F Rotorcraft Flight Manual.

UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

THE

ENSTROM

TWit.! CQl.ti\IT'J' AIFIPOR.T • P.O

HEliCOPTER

-BOX

CoRPORATION

:2)'7_

ME.t.JQI,.IINEE.

l.fiC'iiGII.N

~!leU

280F

PAGE

AEPORT

DATE

NO

1.1

28-AC-019 11/17/80

I.

INTRODUCTION

This

1 i

two

Supp 1 ementa 1 Data

Sections 2 through 5

the

manual

II.

OWNER

manu

a 1 contains the operating

mi

tat

ions

basic

FAA

be

for

parts,

approved

carried in the helicopter

RESPONSIBILITIES

the

RFM.

Enstrom

provided

and

Maintaining the helicopter in

this

owner.

task

of the

in Distributors, Operator's

{See Oea 1 ers,

Manu

a 1 ,

The

Section 8

Enstrom

technical publications available

A.

280F

B.

Maintenance

280F

Parts

Manual

Supplement

SECTION

1 -

GENERAL

instructions,

280F

FAA

approved Rotorcra

by

he

1 i copter.

The

Enstrom

the portions of Section

It

is

required

an

airworthy condition is the responsibility

for

required inspections.)

by

at

all times.

Federal Regulations

Helicopter Corporation

and

Enstrom

Service Centers.

He

1 i copter Corporation

for

your helicopter:

Supplement

ft

procedures

The

manu

a 1 is divided into

Fl

i ght

He

1 i copter Corporation.

10

In

Manu

a 1

so

designated

To

aid the

has

a

addition to

has

the

network

(RFM)

make

that

owner

fo

11

owing

and and

up

this

of

this

C.

Service Information Letters

D.

Service Directive Bulletins

Information regarding

revisions

can

be

obtained

Enstrom

The

Enstrom Twin PO

County

Box

Menominee,

III.

PILOT

A.

The

for

B.

The

RESPONSIBILITIES

pilot

is

res

flight.

pilot

is

specified in Section

C.

The

pilot

should familiarize himself

receiving competent

in

z

0

~

>

~

Issued: 12/31/80

Revised: 1/30/84

dea 1 er

by

Helicopter Service

Helicopter Corporation Airport

277

Michigan

pons

i b 1 e for determining

repsonsible

2.

flight

1 ocati ons, techni

contacting:

49858

for

operating within the limitations

with

instruction.

that

the

ca 1 pub

1 i cations

the helicopter

entire

manual

is

prior

and

safe

to

-~

This electronic document is not linked to a subscription for revision control or distribution. Refer to theTechnical

Publications Status link under the Technical Support Page of the Enstrom Helicopter website for the current revision

level of the 280F Rotorcraft Flight Manual.

UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

TWltt

THE

ENSTROM

CO\.INTY AIRPORT •

IV.

WARNINGS, The

HEUCOPTER

PO

use of

critical

A.

WARNING:

B.

CAUTION:

C.

NOTE:

V.

SPECIFICATIONS A.

Principal dimensions of

CORPORATION

SOX;.,;;_ MIENCIMINEE. I,IIICHiiG.W 49858

CAUTIONS

WARNINGS,

instructions

An

AND

NOTES

CAUTIONS,

is

defined as follows:

operating practice or procedure which,

followed, could

An

operating practice or procedure which, followed, could equipment.

An

operating practice or procedure requires additional information.

result

280F

and

NOTES

in personal injury or loss of

result

in

helicopters:

PAGf

280F

REPORT

OAH:·

to emphasize important

if

not correctly

if

not correctly

damage

to,

or destruction

which

is

essenti a 1

NO.

1.2

28-AC-019

11/17/80

and

life.

of,

and

Width Rotor diameter Height overa Length

Cabin Baggage Tread

B.

Power

Type Designation

Cylinders Horsepower RPM SFC

(full

Weight

Oil

C.

Ratios Lower

upper

Upper

rotor Engine Tail

output

overa

11

overall

width

at

box

dimensions

seat

- landing gear

Plant

rich)

drive pulley

pu

11

ey

pulley

to

main

shaft

to

main

rotor

rotor input shaft

to

shaft

to

28ft 32

ft

9ft

29

ft 3 in.

58

in.

16

in. x

7

ft

4 in.

Lycoming HI

0-360-FlAD

4

225

hp

(sea level to

3050

•

69

1 b/hp/hr

357

lbs

10

qts

(8

1.213:1

7.154:1

8.678:1 1:1

18

in.

x

31

Opposed

qts

minimum

(3050 -2514 (2514-

351

{3050 -351

in.

12,000

for

rpm) rpm) rpm)

ft)

flight)

iri

z

0

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~~----------------------------------------------------------------

Issued: 12/31/80

Revised: 1/30/84

..

TWIN

This electronic document is not linked to a subscription for revision control or distribution. Refer to theTechnical

Publications Status link under the Technical Support Page of the Enstrom Helicopter website for the current revision

level of the 280F Rotorcraft Flight Manual.

UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

THE

ENSTROM

COUNTY

AIRPORT • PO_ SOX

HELICOPTER

2n.

1--::--~

CoRPORATION

MENOMINIEE. MICHIGAN-49656

280F

"'

~

·.

a

~

PAGE

-REPORT

DA.

TE:

1.3 28-AC-019

NO.

11/17/80

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This electronic document is not linked to a subscription for revision control or distribution. Refer to theTechnical

Publications Status link under the Technical Support Page of the Enstrom Helicopter website for the current revision

level of the 280F Rotorcraft Flight Manual.

UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

~

THF. ENSTROM

TWIN

COUNl'r'

AIRPORT • P 0

D.

Rotor

HELiCOPTER

80X

'2ll.

Systems

CoRPORATIOK

MENO~INE.E.

Ml{;HIGP.N

'19856

280F

PAGE

·

REPORT

DATE:

1.4

NO

28-AC-019 11/17/80

Chord, Disk

E.

Weight Designed gross weight

Empty

Usefu

C.G.

NOTE:

VI.

PERFORMANCE

A.

Maximum

Number Chord, Disk

area,

Number

area,

weight

1 load

travel

of

blades,

main of

blades,

tail

rotor

main

rotor

tail

main

blade

rotor

tail blade

rotor

3

9.5

804

2

4.4

17.1

in.

sq

in.

sq

ft

(see Figure 6.1)

2600

lbs

1550

lbs

1050

lbs

96.3

in.

to 98.0

92.0

in.

to

92.0

in.

to 100.0

Four gross weight-e.g. envelopes apply see Figure different see

figure

(All

altitudes

2350

lb gross weight unless otherwise noted.)

6.1.

maximum

5.1.

are

density

Each

cei 1 ing

envelope

and

altitude

a

speed

in.

at

98.8

in.

at

in.

at

to

this

is

associated with a

different

and

performance based

\INE 1 imitation,

2600

2350

2000

lbs 1bs

lbs

helicopter,

on

I

a

117

mph

VNE

power

on

See

85

\INE

power

off

mph

See

NOTE:

B.

Cruise speed

c.

Maximum

Four

different

helicopter, gross

This

weight/e.g.

helicopter Specification verification

75%

power

cruise

speed

maximum

ceiHng/\INE envelopes apply to

see Figure 5.1.

envelope, see Figure 5.1. must

Drawing

that

this

meet

#28-10015.

helicopter

101

117

122

0.

Maximum

V)

z

0

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>

UJ

a:

Issued;

Revised:

12/31/80 12/14/88

range speed

85

mph

lAS

Figure 5.1

lAS

from

Figure 5.1

Each

the requirements of

See meets these requirements.

mpn

lAS

at

mph

TAS

at

mph

TAS

at

IAS

at

from

Sl to

Sl

to

3000

8200

ft

Hd.

this

envelope corresponds to a

Enstrom

Helicopter logbook

for

sea level

3000

ft

Hd

sea level

-.-

This electronic document is not linked to a subscription for revision control or distribution. Refer to theTechnical

Publications Status link under the Technical Support Page of the Enstrom Helicopter website for the current revision

level of the 280F Rotorcraft Flight Manual.

UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

TWIN

THE

COUNt'f'

ENSTROM

A~PORT

E.

HELICOPTER

• ? 0

BO:<:

Fue 1 consumption

75%

F.

Maximum

57

G.

Fuel

capacity

H.

Maxi

mum

I.

Hover

J.

Hover

K.

Maximum

CoRPORATION

'l77 M E"t.!OIIINEE. M ICHIGP.N

491!69

at

power endurance,

mph

lAS

R/C

at ceiling ceiling

IGE

OGE

no

at

sea level

sea 1

eve

approved operating

14. 7

ga

reserve 3.5 hrs

42

gal

1

1450

ft/mi n 13,600 8700

ft

12,000

280F

1/hr

(40

gal

usable)

ft

(see

Item

ft,

see Figure 5.1

PAGE REPORT

DATE 11/17/80

K)

NO

}.5

28-AC-019

altitude

Issued: 12/31/80

Revised:

7/l/84

·~

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level of the 280F Rotorcraft Flight Manual.

UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

~

TWIN COUNT'I' ArRF'OFIT •

THE

ENSTROM

HELICOPTER

PO

80X

2n.

CoRPORATION

MENOMINEE.

MICHIGAN

4Q!!5.8

280F

PAGE REPORT NO

om

2.0

28-AC-019

ll/17/80

SECTION

OPERATING

LIMITATIONS

2

<ij

z

0

~

~l.

FAA

Approved: 12/31/80

..

~R:ev:l~·s~e:d~:~l~/~3:0/~8:4~

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

~--------..-

-.~

This electronic document is not linked to a subscription for revision control or distribution. Refer to theTechnical

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level of the 280F Rotorcraft Flight Manual.

UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

TWir..;

TH•

COL-'NT'r

ENSTROM

AlR.F'ORT • PO

HEUCOJ>TER

SOX 2'l1.

CORPORATION

ME:t..O~INEE.

t.tiCHIGAN

..c.9658

280F

PAGE

P.EPOAT

OA1E

NO

2.1 28-AC-019 11/17/80

I.

II.

III.

SECTION

TYPE

OF

OPERATION

A.

This

helicopter

is

non-icing conditions. NOTE:

Ni

gilt operation authorized Orientation celestial

8. Operation with doors WEIGHT

A.

The

maximum

gross weight of tl!i s helicopter is

Figure 6.1.

CENTER

A.

B.

OF

GRAVITY

The

longitudinal

the

main

There

rotor head.

are four gross weight/e.g. envelopes for

Figure 6.1.

(All airspeeds are

datum

Each

2 -

OPERATING

approved

for operation under

LIMITATIONS

under

must

be

rna

i nta i

ned

illumination.

removed

is

approved.

IAS

unless otherwise noted.)

100.0 inches forward of the center

envelope corresponds to

vi

sua 1 flight

by

ground

one

day

and

ni

gilt

rules only.

1 i ght or adequate

2600

pounds.

this

helicopter.

of four

VNE/a

VFR

See

line

of

See

ltitude

-

envelopes as described in paragraph NOTE:

This Spec i fi

for

verification

helicopter

cation

Drawing

requirements.

C.

Envelope A is

sea level.

l.

Upper.weight

2.

Forward

3. Aft

100.0 inches

2000

requirements, Envelope

A.

the 1 ightest weight

The

e.g.

limit

1 imit varies 1 i nearly

at

lbs.

it

and

gross weight limits vary as follows:

is

92.0 inches.

2000

must

meet

#28-100015.

that

If

the helicopter

must

be

envelope

2350

lbs.

from

lbs.

Aft 1 imit

IV.

Also, see Figure 5.1.

the requirements of

See

He

1 i copter

this helicopter

does

not

operated within the

with a

94. 6 inches

at

VNE

at

100.0 inches

meets

meet

of

2350

Enstrom Logbook

· these

limits

117

mph

lbs to

these

of

at

below

z

"'

0

~

X:

FAA

Approved:

12/31/80

Revised: 7/1/84

'~

This electronic document is not linked to a subscription for revision control or distribution. Refer to theTechnical

Publications Status link under the Technical Support Page of the Enstrom Helicopter website for the current revision

level of the 280F Rotorcraft Flight Manual.

UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

TWIN

THE

COUHT't

ENSTROM

AIRPORT

HELICOPTER

...

PO

BO:f

CORPORATION

?ll_

MENOMIN':E.E..

MICHIGAN

49@.5@.

280F

PAGE 2 REPORT

DATE

NO.

..

2

28-AC-019 ll/17

/80

D. Envelope B

The

e.g.

and

I.

Upper

2.

Forward

92.0 inches

3. Aft

99.2 inches

4.

Tile

lower 1 imit corresponds to the upper forward

limits

E.

Envelope C

weight

I.

2.

limits

Upper Forward

93.8 inches

3.

Aft

limit

98.4 inches

is

the next heavier envelope.

gross weight

weight 1

limit

of

has·

imit

varies

at

2350

varies

at

2240

Envelope

a

VNE

vary

as

weight 1 i mit

limit

varies lil'lfarly

at

2450

varies

at

2470

limits

is

2450

linearly

lbs. linearly

pounds

A.

at

sea level

follows:

is

2550

lbs.

linearly

lbs

and

It

has a

vary as follows:

lbs.

from

and

100.0 inches

1 bs.

from

93.8 inches

96.0 inches

of

91

mph.

95.5 inches

97.3 inches

at

then to 99.2 inches

2000

The

at

VNE

at

lbs.

e.g.

at

2240

of

2450

and

2550

lbs.

104

lbs

aft

lbs

mph.

to

gross

to

4.

Lower

Envelope

F.

Envelope D

85

mph.

1.

Upper

2.

Forward 1 imit at

3.

Aft

98.4 inches

4. lower

Envelope

G.

The

lateral

moment

H.

Lateral

1.

From +3700

2.

c;;

z

D

FAA

"'

>

UJ

0:

Approved: 12/31/80

Revised:

7/l/84

Below

limit

The

weight

2550

limit

arms

offset

2025

in-lbs. 2025

corresponds to the upper forward

B.

is

the heaviest envelope.

e.g.

and

gross weight

limit

is

varies

2600

from

limits

lbs.

96.3 inches

lbs.

varies

at

2470

corresponds

linearly

lbs.

to

the

from

uptJer

C.

datum

are

line

positive

moment

lbs

lbs,

see Figure

is

right

limits

to

the

centerline

and

negative

vary with weight.

2600

lbs,

limits

6.2.

It

has a

vary

at

98.0 inches

forward

of

left.

and

VNE

as

follows:

2600

and

the

helicopter.

See

are

aft

limits

at

sea level

of

lbs to 95.5 inches

at

aft

2600

limits

lbs

of

to

lateral

Figure

-3250

6.2.

in-lbs

and

~-

This electronic document is not linked to a subscription for revision control or distribution. Refer to theTechnical

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UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

Til"

TWIN COUI>ff'l

IV.

ENSTROM

oiJAPOF'iT • PO

HELICO

AIRSPEED

E!OX

PTilR

277_

MEt.DI/III\IE.E,

CoRPORATION

MICHIGAN

496Y.I

280F

PAGE

REPORT NO. OATE:

2.3 28-AC-019 11/17/80

Never altitude.

variations NOTE:

NOTE:

V.

ALTITUDE Maximum

2350 Figure

NOTE:

exceed speed

See

(VNE)

-

Figure 5.1

117

for

mph,

lAS,

variations

with gross weight/CG.

There are four helicopter.

weight/CG This

fication

envelopes.

helicopter

Drawing

verification

If

the

helicopter

be

operated within the

Each

must

that

VNE/a

ltitude

envelopes

envelope corresponds to

See

Figure

meet

the requirements of

#28-100015.

this

does

helicopter meets these requirements.

not

meet

limits

of Envelope

approved operating a 1 t itude - 12,000

1 bs. For

5.1.

Takeoffs strated to

20

Takeoffs strated up

to

variations

and

to

7000

mph.

and

to 10,000

15

mph.

landings

ft

DO

NOT

landings

of

at density EXCEED

at

ft

density

altitude

2600

altitude

ENGINE

2350

altitude

sea level to

above

which

5.

1.

3000

ft

apply to

one

of four gross

Enstrom

See

Helicopter

Logbook

these requirements,

A.

ft

density a 1

titude

with gross weight, see

lbs gross weight

in

all

wind

were

conditions

LIMITATIONS.

lbs gross weight

in

all

wind

were

conditions

density

and

for

this

Speci-

for

it

must

demon-

at

up

Operators should use appropriate caution density safe

VI.

ROTOR

A.

RPM

Flight

limitations

Minimum: Maximum:

B.

Flight

limitations

Minimum: Maximum:

NOTE:

During during

maneuvers

to 280, however, to regain

See

;,;

z

0

u;

>

Ill

0:

~------------------------------------------~

FAA

Approved:

Revised:

Section 8

12/31/80

12/14/88

altitude

takeoffs

334

rpm

351

rpm

334

rpm

385

rpm

transient pilot

training,

have RPM.

for

and

in

and

landings.

power

on:

off:

maneuvers, such

the

rotor

been

demonstrated with

sufficient

winds

time

greater

as

RPM

and

Adjustment Procedures.

simulated

may

rotor

altitude

than

fall

power below

RPM

must

above 15

10,000

mph

failure

334.

dropping

be

available

ft

to insure

These

briefly

,_

This electronic document is not linked to a subscription for revision control or distribution. Refer to theTechnical

Publications Status link under the Technical Support Page of the Enstrom Helicopter website for the current revision

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UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

THE

TIM"'

COU-•HV AIR-PORT •

ENSTRO>!

HELICOPTER

PO

BOX

~71

MENOMINE~.

CoRPORATION

MI:::HIGAN

49!58

280F

PAGE

REPORT NO. 28-AC-0

DATE

2~4

11/17/88

19

VII.

POWER Engine modified A.

PLANT

LIMITATIONS -LYCOMING

Maximum

per

continuous power:

level to 12,000

B.

Engine

Minimum:

Maximum:

C.

Engine Minimum:

Maximum:

D.

Manifold

E.

Cylinder head temperature:

F.

EGT:

G.

Fuel: 100/130

operating

2900 3050

id1e

rpm -clutch 1450 1500

pressure:

1650°f

maximum

Enstrom

ft.

rpm: rpm rpm

rpm rpm

39.0

aviation

HI0-360-FlAD

Turbocharger Kit

225

hp,

LW-14460.

3050

rpm,

disengaged

in.

Hg,

sea level to 12,000

500°F

maximum

grade gasoline (green)

39.0

in.

ft

MP,

sea

VIII.

lOOLl

fuel

1.

mixture

29

in .

H.

a. b.

2.

I.

Oil temperature:

J.

Oil 100

in.

29

pressure: psi

60-90 psi

28

psi

TRANSMISSION

Transmission

LIMITATIONS oil

aviation

grade gasoline (olue)

setting:

MP

or

be 1 ow Maximum Minimum

MP

to 39.0

maximum

normal

minimum

flow

fuel fuel

flow-

in.

245°

maximum

starting

operating

id1ing

temperature: 225°F

-

full

rich

leaned to 1650°f

MP

and

(full

rich}

warm

up

maximum

ricn

side

of

peak

in

z

0

~

~------------------------------------------~

FAA

Approved: 12/31/80

Revised: 12/14/88

9

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UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

TWIN

THE

E~STROM

COIJNrY

AIRPORT • PO

IX.

RESTRICTIONS

A.

8.

C.

HELIC<lPfER

BOX

277_

Instrument

No

aerobatic

Hovering

IGE

minutes.

X.

MINIMUM

A.

B.

XI.

INSTRUMENT

A.

CREW

One

pi

lot.

Solo

from

left

MARKINGS

Rotor tachometer

334

1.

rpm

CORPORATIOX

;JENOM•"'i:E. Y C'iiGA."'

f1ight

+911~

prohibited.

maneuvers permitted.

above 10,000

seat

only. (See Supplement

ft

red

density

line

280F

altitude

No.

6}

is

PAGE

REPORT

DATE

limited

2.5

NO

28-AC-019 11/17/80

to

five

2. 334-385

3.

385

B.

Engine tachometer

2900

1.

2.

2900-3050

3.

3050

c.

Maximum

85

mph

117

10

39.0

in.

D.

l.

2.

Manifold

1.

2.

3. Overboost

E.

Engine

I.

2.

oil 245°F 120° -245°F

3. £0° -

rpm

airspeed

(power

mph

(power on) red

off)

pressure

to

39

in.

Hg

light

illuminates

temperature

12:0°F

green arc red

line

red

line

green

red

blue

arc

line

green

red

red green

arc

line

at

line

arc

39

yellow arc

in.

manifold pressure

F.

Engine

1.

2. 60-100

3. 25-60 psi

z

"'

0

>

UJ 0:

FAA

Approved:

Revised:

4.

oil

100

psi

25

j)Si

12/31/80 12:/14/88

pressure

psi

red

line

green

yellow

red

line

arc

,_

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UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

TWiN

THE

COUNTY

EJ<STRO>!

AIRPORT • P

G.

H.

HEliCOPTER

0_

SOY.

CoRPORATION

277.

MENOMINEE.

Cylinder head temperature

1.

500°F

2.

200°

- 500°F green arc

EGT

MICHIGA><

491156

red

line

280F

PAGE

REPORT NO

DATE:

2.6

28-AC-019

11/17/80

1650°F

I.

TransmiSsion oi1 temperature

1.

225°F

oo

XI

I.

PLACARDS

A.

2.

Placards

1.

-

225°F

that

THIS

WITH

are

HELICOPTER

THE

FAA

2.

PLACARDS

2600

~

,e

I

2400

t-

I

~22oo

~2000

3

ffi

/

f?&lA:~

W/111$//#,

1

ono,

/---.

//

~

94

9S

CG

Inche-s

'c

s',

'\

9B

FOR

--

tJ

\

'\

\

1(:0

required

MUST

OPERATING

APPROVED

280F

PRESSURE

ALTITUDE

SEA

LEVEL

2000

4000

6000

8000 10000 12000

ROTORCRAFT

VNE

VNE-IAS

red

line

red

1 ine

green

to

BE

LIMITATIONS

arc

be

placed

OPERATED

SPECIFIED

FLIGHT

in

view

IN

COMPLIANCE

MANUAl

{located overhead above

(MPH)

-zo

117

117 117 IP2

99

81

OUT

FOR

SID

0

117 ll7

U7

116

107

88

70

ENVElOPE

AtR

TEMPERA

20

1!7

li7

117

Ill

96

78 60

40

117

115

105

.87

69

of

the

IN

THE

center

'A'

lURE

50

117

117 110

96

78

59

pilot

are:

windshield):

·~

80

117 117

114

105

87

59

roo

109

S6

2B·IB004

78 60

s-rr·

A

--

2600

I

24oo

iti

z

0

5

~

FAA

Approved: 12/31/SQ

Revised: 12/14/88

PRESSURE TSIDI

AL

SEA

\INE-IAS

TITUOE

LEVEL

2000

4000 6000

8000

IOPOO

10,800

{MPH)

-20 104 104 104 104

104 104 104

100

89 81

FOR

0

104

103

96 78

70

ENVELOPE 'B'

AIR

TEMPERATURE

20

104 104 104 104

99

-68

40

102

95

86

60

76

58

60

!04

99

85

67

Of

80

104 102

94

76

58

100

10'1

98 85 68

B

-

-..-

This electronic document is not linked to a subscription for revision control or distribution. Refer to theTechnical

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UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

THE

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277, M-ENOMiNEE. MICHIGAN 49658

CoRFORAT!ON

280F

PAGE 2. 7

REPDRT DATE:

NO 28-AC-0

ll/17/80

19

2600I

~

12400 L

>-

I

,.2200

w '

;.

.,2000

"'

0

::3

180092

,;2600

::!

I

24oo

~

~2200

"'

~

ii80J

_.,......_

2000

92

.... --...

~0

__

,

8

'

'-

A ' \

94

96

CG-Jncll.u

/~D

....

..:--- c '

_ _

~

.........

',,

A

I

96 98

94

CG

-lnefles

.....

98

, \

'\

\

' \

',\

I

\

'l

:

100

1

I I

I

100

VN£-IAS

PRESSURE

ALTITUDE

SEA

LEVEL

2000 4000

6000

8000

9600

VNE-IAS

PRfSflURt

AL I UO

SEA

LEVEL

2000 4000

6000

8000

9000

(MPH)

OUTSIDE

20

91

91 91

91

88

81

(MPH)

-20 85

85

85 84 83

81

80

0 91

91

90

85

71

OUTSJOE

0

85 85

82 80

71

FOR

ENVELOPE

AIR

TEll/E'ER

20

91

87

75

ENVELOPE

AIR

20

85 85 85 83

81

70 60

40

91 91

61

91 91 90

83

65

TEMPERATURE

40

84 82

79

60

'c'

ATtJRE

60

91

91 87

74 56

'o'

60

85

83

81 69

'F

so

91

89

'f

80

84 82

78 69 59

28-180048-11 D

100

91 87

83 65

28-180047-11 -

74

57

100

83

81

c

-

NO

3.

{This

4.

5.

placard not required

THIS

HELICOPTER

DAY

AND

NIGHT

VFR -NON-ICING

COLLECTIVE

GROUND

{This

"placard to

collective

B.

A placard to

1.

c.

be

pla~ed

MAXIMUM

WEIGHT

OBSERVE

STOW

in the

C.G.

FLAT

IN

AND

(This placard to

z

"'

0

V)

>

w

<r

FAA

Approved:

Revised:

12/31/80

8/29/85

SMOKING

when

IS

APPROVED

approved

fRICTION

OPERATION

be

placed adjacent to the

friction

baggage

THIS

COMPARTMENT

GROSS

ON

FLOOR

be

placed

ashtray

FOR

OPERATION

CONDITIONS

TO

BE

USED

ONLY

device.}

compartment

IS

WEIGHT BEFORE

LIMITATIONS FliGHT

on

clutch handle.)

FOR

is

108

is

installed.)

UNDER ONLY

as

follows:

LBS.

I

THE

This electronic document is not linked to a subscription for revision control or distribution. Refer to theTechnical

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f'WlH COONTY

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.t.IFII='ORl

HELiCOPTER

.. ~ 0

BoO~

2"7f.

CoRPORATION

MfNOWlNEf.

MICHIGAN

4.11151

280f

PAGE:

.REF'OfiT

OA.TE·

NO.

3.0

26-AC~Ol9

ll/17/80

EMERGENCY

AND

SECTION

MALFUNCTION

3

PROCEDURES

iii

z

0

"'

~L.

FAA

Approved:

..

:R:ev:l~s:e:d~:~l~/~3:0/~8=4~------------------------------------------------------

12/31/80

··--

This electronic document is not linked to a subscription for revision control or distribution. Refer to theTechnical

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level of the 280F Rotorcraft Flight Manual.

UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

TWIN

THE

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~TY

A!A.FOfi!T •

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SOli

U1.

l.fE.~i<t>IEE.

lo111CHIG.U.•91:5t

280F

PAGE REPORT NO. OATE:

3.1

28-AC-019

11/17/80

SECTION

I.

GENERAL This

section describes the

and

establishes the

the helicopter safely

II.

ENGINE

llle indications of

loss,

FAILURE

are a

]eft

3 -

EMERGENCY

emergency

on

the ground.

an

engine

yaw

and a drop

ANO

system

procedures

failure,

in engine

conditions are encountered the procedures to

the aHitude

while

ma1ntafntng control of the helicopter

and

airspeed available to establish successful landing. A.

Engine

When

1.

failure-

engine

failure

Altitude.above

occurs proceed as follows:

Enter autorotation (collective full

right

pedal

to

trim helicopter}.

MALFUNCTION

failures

used

eftller

375ft

PROCEDURES

and

malfunctions that to maintain control

partial

and

main

be

followed are determined

and

sufficient

AGL.

down,

may

or

complete

rotor

an

throttle

rpm.

When

autorotative glfde,

rotor

to

rpm

idle

occur

and

power these

for a

get

by

and

Stabilize

2. CAUTION:

3.

Check

green

place mixture control in

at Due

speed Figure attained to

engine arc.

58

mph

glide {best rate of

to

high

is

5.l.

build

and

rotor

If

engine is stopped, turn

rates of descent, sustained autorotation

limited to

Maximum

at

80

rpm

prior

rpm.

mph

85

glide distance in autorotation and to

touchdown.

Adjust collective

ICO

des~ent.speed).

mph

to

8200

334

rotor

position.

permit, see Air Restart Procedure, Section,3.2

4. Select landing NOTE:

site.

If

engine is running

and

suitable landing

wtthin glide distance, the pi1ot should attempt to fly

he

Jf

the

and i ng

1

copter

a rea.

complete loss of

at

The

reduced

pilot

power

shou

at

conditions.

At

5.

iJi

z

0

3

~

FAA

Approved:

Revised: l/30/84

approximately

12/31/80

50

ft

AGL

apply

aft

cyclic to reduce speed.

ft;

rpm.

OFF

fuel boost

If

above Reduce

to

altitude

8200

collective

keep

rotor

pump

and

site

ft

is

and

time

not

sett1ngs to a favorable

1 d

be

prepared for a

any

time

under

these

see

is

in

e

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6.

HELICOPTER

p-0

BOX

Level provide

CoRPORATION

277_

P.IIENQI.IIINEE.

helicopter

tail

ground, apply

MI.CHIGA.'f

~96.58

with forward cyclic

rotor

up

collective

clearance.

280F

at

an

altitude

As

helicopter

to cushion landing.

PAGE REPORT NO.

OATE

sufficient

settles

3~

2

28-AC-019

ll/17/80

to

toward

Maximum

7. 35

mph.

CAUTION:

B.

Air Restart

an

After

will

engine

depend

CAUTION:

1. Adjust and

establish

2. Select landing

3. Grip

OFF

cyclic

and

recommended

Reduce

Avoid

after

failure

on

the

altitude

He

1 i copter centro 1

autorotation.

ground contact speed

speed

on

rough

rapid lowering of

ground contact or during ground

in

flight

and

00

NOT

jeopardized.

00

NOT

attempt

collective

58

air

restart

as required to maintain

mph

autorotative

site.

between knees

and

pull mixture control to

on

prepared surfaces

surfaces.

collective

or use

slide.

the decision to attempt a

potential

is

primary concern

attempt

when

landing areas

air

restart

below

3000

if

ft

rotor

glide.

with

right

hand

turn fuel boost

!CO.

of

aft

available.

after

entering

control will

AGL.

rpm

in green

is

cyclic

restart

be

arc

pump.

1

4. Rotate

5.

Engage

6.

When

7. Slowly increase in green

C.

Engine

When

an sufficient collective

touchdown reduction will vary

full

down

failure

1. Adjust

ifi

z

0

Vi

>

:i!

FAA

Approved:

Revised: 12/14/88

and

throttle

to

start

position

starter.

engine

fires,

throttle

mixture

until

arc.

Failure -

engine

altitude

must

Altitude

failure

may

be

adjusted for the conditions in order to reach the

above

occurs

not

be

point without excessive

from

collective

at

no

reduction

higher

occurs proceed as follows:

collective

right

pedal to

to maintain

trim

helicopter.

12/31/80

(start

full

10

at

rich

engine

feet

low

and

altitude

available to increase

rotor at

zero airspeed

altitudes

rotor

and

rpm,

index up).

boost

pump

rotor

below

375

and

droop.

airspeeds.

throttle

ON.

tach needles

ft

AGL.

low

airspeed,

rotor

The

and

to

rpm.

collective

10

feet

When

idle

position

engine

join

The

to

e

This electronic document is not linked to a subscription for revision control or distribution. Refer to theTechnical

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UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

n

...

IN

THE

COUNT'1

ENSTRO"

AIRPORT

HELICOPTER

•

PO

80:0:271.

Co RP<IRATlON

IJI€NOM1N:EE:.

p.J;ICHIG.I.N

49856

280F

PAGE

REPORT NO DATE

J.J

28-AC-019 ll/17

/80

2. Adjust

3.

4.

5.

6.

0.

Engine

Engine he engine

cyclic

NOTE:

At

for

higher to increase forward speed to approx i low

a

required to reduce speed

At

altitude

of

forward speed.

Level provide

As

helicopter

tail

he

1 i copter

rotor

sett

cushion landing. Maximum

35

mph.

CAUTION:

recommended

Reduce

Avoid after

- Failure failure

at

1 i copter to the 1

failure

and

proceed as follows:

autorotative

altitudes

1t

itudes

and

glide.

and

low

airspeed use forward

higher airspeed

prior

approximately

with forward

50

ft

cyclic

AGL

at

clearance.

1 es toward the ground apply

ground contact speed

speed

rapid lowering of

ground

on

rough surfaces.

contact

or

collective

during

Hover

a hover

eft.

is

Avoid

indicated

by

sideward or rearward

rna

te

ly

aft

cyclic

to ground

use

aft

an

altitude

contact.

eye

up

on

prepared surfaces

or use

ground

a

slide.

sudden

yawing

movement

cyclic

58

mph.

wi

11

At be

1 i c to reduce

sufficient

co

11

ecti

ve

to

isl

of

aft

cyclic

of the

after

l.

Apply

right

peda 1 to prevent

yawing

and

of motion.

2.

DO

NOT

3.

As

helicopter

reduce

collective.

settles

to the ground,

add

landing.

III.

DITCHING

If

engine

procedure

A.

Unlatch doors.

B.

Land.

C.

As

co

water, apply

~ITHOUT

failure

and

Complete

11

ect i ve

PO~ER

occurs over water, accomplish engine

proceed as follows:

normal

reaches

full

autorotational

fu

11

lateral

cyclic

up

landing in water.

position

in

and

direction

roll.

61

z

0

~

~~----R•e.vl.·s.e.d.=

FAA

Approved:

12/31/80

......

1~2/~1.4~/8•8

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

a 1 i

gn

up

collective

he

1 i copter

helicopter

skids in

failure

direction

to cushion

emergency

sett 1 es

tends to

in

~L__

'•"

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UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

TWIN

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AIAPOAT + P 0

D.

Pilot

HELICOPTER

i!IOJC

2U

ME

and

C<>RPORA1'10N

NOMINE£.

6,1!CHIGAN

passengers

<49!51

exit

helicopter

when

280F

main

PAG£

REPORT NO.

O,I.Te:

rotor stops.

3.4 28-AC-019

.11{17

/80

WARNING:

IV.

DITCHING

If

ditching fs unavoidable without other recourse, proceed

A.

Descend

WITH

to

8. Unlatch both doors. C,

Exit passengers.

D. E. F. G.

Hover

Turn

Close

As

clear

off

throttle

collective reaches

water, apply

H.

Exit helicopter

WARNING:

Clear helicopter as quickly as possible. POWER

low

hovering

altitude

over

water.

of passengers.

master

Clear helicopter as quickly

and

full

~en

and

alternator.

complete hovering autorotation.

full

right

rotor

up

lateral

stops.

position

cyclic.

as

and

possible.

helicopter

as

follows:

settles

into

V.

TURBOCHARGER Turbocharger

pressure,

should

be altitudes equal

to

seizes in the A.

Perform a power

B.

Land paragraph

VI.

LOW

A.

a

ENGINE Low

Ofl

If

low

possibility

ing. This

landing. Proceed

in

z

0

~

FAA

Approved:

12/31/80

Revised: 1/30/84

OR

or

if

operating

WASTEGATE

wastegate seizure will

FAILURE

at

manifold pressures

possible to maintain level

as the engine should

ambient pressure.

full

bypass condition,

as

soon

XV

Oil

Pressure

oil

check

as practicable, using

I).

PRESSURE

and

pressure

to confirm

Normal

is

be

capable of maintaining manifold pressure

If

th.e

Oil

accompanied

the oil pressure

fs

not necessarily cause

as

follows:

be

evidenced

above

flight

turbocharger seizes or the wastegate proceed

power

as follows:

available for landing.

running

Temperature

by

normal

gauge

or

for

relief

an

by

loss of manifold

ambient pressure.

at

reduced

airspeeds

landing (see Section 4,

oil

temperature there

valve is malfunction-

i1m1ediate

precautionary

It

and

is

,.,

This electronic document is not linked to a subscription for revision control or distribution. Refer to theTechnical

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level of the 280F Rotorcraft Flight Manual.

UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

TWI'k

THE

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..

1RP'Ofi!T

• P 0

I.

2.

B.

Total

If temperature, imminent.

HELICOPTER

SOX

2n

"t.IE.tf'Qj,j.INEE.

Land

at

Inspect for

flight.

Loss

a

tota

CORPORAT!ON

MICHIG

...

N

~!M!t

nearest suitable landing area.

and

of

Oil

1 1

os

this

Proceed

correct

Pressure

s of oil pressure is

is a

as

follows:

this

good i ndi

source of troub 1 e

catf

PAGE

280F

accompanied

on

that the engine fa i1 ure

REf'ORT

DATE·

be

fore continuing

by a rise

NO

3.5

28-AC-019

11/17/80

in

oil

is

VII.

Reduce

1.

2.

Select a suitable forced landing TAil Because

ROTOR

of the coping with condition

and description emergency

A.

Complete

procedures to follow:

This condition system or a to

assume

I.

Hovering When

will rotate rapidly to the

left

engine

power

immediately.

field

MALFUNCTIONS

many

ta

i 1

use

of

the three basic types of malfunctions

loss of Tail

failure

different

rotor

ma

1 functions

of the proper

Rotor

can

be

caused

of the control

ma

1 functions that

depends

emergency

procedure.

Thrust

by a fa

11

system

a neutral pitch condition.

flight

tail

pedal.

rotor

Proceed

thrust

as follows:

is

lost

right,

in

hovering

even

and

land with

can

upon

recognition of the

and

ure of the

which

would

flight

wfth

fu

power.

occur, success in

The

following is a

the appropriate

tail

rotor drive

allow the blades

the helicopter

11

app

1 i cation of

a.

b.

2.

During He

pedal. Proceed a. b.

<i:i

z

0

~

[i;

FAA

Approved:

Rev

f sed: 1/30/84

12/31/80

Roll slow

As

collective

flight

1 i copter

Roll

Complete

throttle

down

he

lf

copter

off

to

full

or stop rotation.

sett 1 es

(throttle

to

off).

near suitable landing area

wi

11

rotate to

as

throttle

follows:

full

off

right

to

autorotational landing.

idle position. Helicopter will

ground,

with full

idle

and

cushion 1

app

and i ng

1i

cation of 1

with

enter autorotation.

up

eft

280F

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UNCONTROLLED COPY WHEN DOWNLOADED OR PRINTED

PAG.f

REPORT

DATE:

NO

3.6 28-AC-019

11!17/80

3. During

B.

Fixed This

pitch upon locked.

1. Fixed

flight

If

suitable

glide

distance,

autorotation a.

Increase

60

land1ng area

pilot

at

60

collective

to

80

mph

45°.

b.

c.

Continue

directional

site

Complete

Pitch

is

Set~ing

a malfunction involving

setting.

the

setting

right

flight

·control

is

reached.

autorotational

Whether

of

the

pedal

is

should proceed

mph

or

above:

pitch

until

in

yaw

this

until

loss.of

the

nose will

pedals

not

available

as

and

power

to

the

right

fashion using

suitable

landing.

control

rotate

when

the

follows

gradually,

reaches a

within

after

cyclic

autorotative

establishing

maintaining

maximum

stick

auton>tational landing

resulting

left

controls

or

were

in a fixed

right

janmed

of

for

depends

or

If

the

tail

power

setting,

applied. a.

.

b. Maintain c.

Remove

Fly

approach

d. Adjust

touches Reduce

rotor

the nose

Proceed

feet

24

to

suitable

at

throttle

down

throttle

pitch

as

from

becomes

will

follows:

pedals •

fixed during

tum

to

inches manifold pressure

50

mph.

straight

and

a~ea

and

and complete a shallow

collective

ahead

collective

at

cautiously

surface.

CAUTION:

1. Fixed If

settings,

the

left

tail

pedal

the reduced below 23

in.

~

z

0

~

FAA

Approved: 12/31/80

Revised:

l/

30/84

conditions

manifold

at

DO

NOT

abort

has diminished

rotor

pitch

becomes

helicopter

23

in.

manifold pressure.

pressure

airspeeds above

the

will

60

emergency

below

40

mph.

fixed during

yaw

to

produce near

mph.

Proceed as follows:

the

and

pitch

an

airspeed

landing

the

.an

right

50

so the

cruise

left

Power

approach

when

mph.

helicopter

of

as skids

after

or

high

when

settings

normal

or

low

power

0-10

mph.

contact

airspeed

power

above

flight

is

on

is

ENSTROM 280F Operator's Manual

Specifications and Main Features

Frequently Asked Questions

User Manual