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INDEXCOPYRIGHT 2008
COPYRIGHT IS NOT CLAIMED AS TO ANY PART OF AN ORIGINAL WORKPREPARED BY A UNITED STATES GOVERNMENT OFFICER OR EMPLOYEE APART OF THAT PERSONS OFFICIAL DUTIES OR BY ANY OTHER THIRD PART
OFFICER OR EMPLOYEE AS PART OF THAT PERSONS DUTIES.
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FORM BY ANY MEANS, ELECTRONIC, MECHANICAL, PHOTOCOPYING,RECORDING OR OTHERWISE, WITHOUT PRIOR WRITTEN PERMISSION OF TH
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ATP Grid
Index to
Manufacturer’s
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
Page
1 of 2
EN
0138
FM
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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
of
Index
2/22/2008
Copyright
Arcraft Technical
Publishers
Page
2
of
2
E N
0138
FM
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IVI
FGI
INTRO
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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
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RECORD
OF
REVISIONS
MFG
REV
NO
DESCRIPTION
ISSUEDATE ATPREVDA INSERTED
BY
5
Library
Addition
617/07 ATP/RD
2/22/2008
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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
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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
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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
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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:
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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
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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
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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
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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.
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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
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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
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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
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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
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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
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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
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1/11/85
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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
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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
8/17/2019 Enstrom 280FX Operator Manual and FAA Approved Rotorcraft Flight Manual.pdf
23/158
THE
ESSTROM
HELICOPTER CORPORATION
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
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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
8/17/2019 Enstrom 280FX Operator Manual and FAA Approved Rotorcraft Flight Manual.pdf
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
8/17/2019 Enstrom 280FX Operator Manual and FAA Approved Rotorcraft Flight Manual.pdf
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
8/17/2019 Enstrom 280FX Operator Manual and FAA Approved Rotorcraft Flight Manual.pdf
27/158
8
VSTROM
PAGE
2.8
HELICOPTER CORPORATION
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
8/17/2019 Enstrom 280FX Operator Manual and FAA Approved Rotorcraft Flight Manual.pdf
28/158
8
NSTTZOM
PAGE 2.9
HELICOPTER CORPORATION
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
8/17/2019 Enstrom 280FX Operator Manual and FAA Approved Rotorcraft Flight Manual.pdf
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
8/17/2019 Enstrom 280FX Operator Manual and FAA Approved Rotorcraft Flight Manual.pdf
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
8/17/2019 Enstrom 280FX Operator Manual and FAA Approved Rotorcraft Flight Manual.pdf
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
8/17/2019 Enstrom 280FX Operator Manual and FAA Approved Rotorcraft Flight Manual.pdf
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
8/17/2019 Enstrom 280FX Operator Manual and FAA Approved Rotorcraft Flight Manual.pdf
33/158
8/17/2019 Enstrom 280FX Operator Manual and FAA Approved Rotorcraft Flight Manual.pdf
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.
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Approved:
1/11/85
8/17/2019 Enstrom 280FX Operator Manual and FAA Approved Rotorcraft Flight Manual.pdf
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
8/17/2019 Enstrom 280FX Operator Manual and FAA Approved Rotorcraft Flight Manual.pdf
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
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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
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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
8/17/2019 Enstrom 280FX Operator Manual and FAA Approved Rotorcraft Flight Manual.pdf
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
8/17/2019 Enstrom 280FX Operator Manual and FAA Approved Rotorcraft Flight Manual.pdf
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
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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
8/17/2019 Enstrom 280FX Operator Manual and FAA Approved Rotorcraft Flight Manual.pdf
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
8/17/2019 Enstrom 280FX Operator Manual and FAA Approved Rotorcraft Flight Manual.pdf
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
8/17/2019 Enstrom 280FX Operator Manual and FAA Approved Rotorcraft Flight Manual.pdf
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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