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ATP Grid Index to Manufacturers Publications:

Enstrom HelicopterModel F-28F

Operator Manual and FAA Approved Rotorcraft Flight Manual

Section Topic_ _

General Information

Title PageRecord of RevisionsRecord of Temporary RevisionsLog of SupplementsList of Effective Pages

Section 1 GeneralGeneral

Section 2 Operating Limitations

Section 3 Emergency and Malfunction Procedures

Section 4 Normal Procedures

Section 5 Performance

Section 6 Weight and BalanceWeight and Balance

Loding ChartWeight SheetHelicopter Weight and C.G. CalculationEnstrom F28F Optional Equipment ListEnstrom 280FX, F28F Optional Equipment List

Section 7 Aircraft and Systems Description

Section 8 Inspection Maintenace Servicing Storage Handlingl

02/22/2008 Copyright Aircraft Technical Publishers Page 1 of 2

EN 0141 FM)

Section Topic

Section 9 Operational Information (Reserved)

Section 10 SupplementsSupplement No. 1 Wet/Dry Dispersal SystemSupplement No. 2 Float Landing GearSupplement No. 3 External LoadsSupplement No. 4 SnowshoeSupplement No. 5 ReservedSupplement No. 6 R H Side Pilot ConfiguratioSupplement No. 7 Electric Clutch ActuatorSupplement No. 8 Emergency Float Landing GearSupplement No. 9 ReservedSupplement No. 10 Rotor BrakeSupplement No. 11 Auxiliary Fuel TankSupplement No. 12 Engine Exhaust Muffler

jr*jl End of Index .i~kk

02/22/2008 Copyright Aircraft Technical Publishers Page 2 of 2

(EN 0141 FM)

MFG.

INTRO

ENSTROM F-28F

OPERATORMANUAL

AN D

F.A.A. APPROVED

ROI-ORCRAFT FLIGHT MANUAL

REPORT NO. 28-AC-018

TYPE CERTIFICATE NO. H1CE

HELICOPTER SERIAL NO.

HELICOPTER REGISTRATION NO.

THIS MANUAL MUST BE CARRIED IN THE HELICOPTER AT ALLTIMES. SECTIONS 2,3,4, AND 5 ARE F.A.A. APPROVED.SECTION 10 INCLUDES SUPPLEMENTSTO THE TYPECERTIFICATE WHICH ARE F.A.A. APPROVED IS SO DESIGNATED.

F.A.A. APPROVED BY: iFOR MANAGERCHICAGO AIRCRAFT CERTIFICATION OFFICECENTRAL REGIONFEDERAL AVIATION ADMINISTRATION

DATE: DEC.31, 1980

I

RECORD OF REVISIONS

MFG REVNO DESCRIPTION ISSUEDATE ATPREVDATE INSERTEDBY

?0 Library Addition 6/7/07 3/5/08 ATP/PC

2/22/2008

Q ENsl nOM PAGE viHEUCOPTER CORPORAT~ON F-28F REPORTNO. 28-AC-0~82209 22nd STREFF P.O. BOX 49f)~ MENOMINEE. MICHIGANIsese-azeo U.6.A DATE 1 1-17-80

LOG OF REVISIONS

Rev. Pages Description Approval F.A.A. Approved*No. Date

7 i, vi, 1.4.1, 4.7, 4.8, 4.9, Added pages and figures and 1-8-1986 Gary S. Louser6.5.1, 7.4, 7.5, 7.7, 7.8 revised text

8 I, ii, iv, v, vi, 1.3, 2.3, Added pages, added blade 12-14-1988 Pat Moe2.4, 3.2, 3.3, 3.9, 4.9, tape and 28 volt system. Minor4.12, 4.14, 5.3, 7.5, 7.6, corrections.7.7, 8.6, 8.12

9 2.4 Added previously approved 4-3-1990 Pat Moedeletions

10 ii, vi, 2.6, 2.7, 2.8, 2.9, Added 120"F column to VNE 6-8-2007 Joseph Miess3.7, 3.7.1, 8.17, 10.1.2, placards. Added emergency10.1.2.1, 10.2.3, procedures for main rotor and10.2.3.1, 10.8.3 tail rotor gearbox chip

indications. Added proceduresfor removing and reinstallingmain rotor and tail rotor

gearbox chip detectors.

APPROVED FOR MANAGER CHICAGO AIRCRAFT CERTIFICATION OFFICECENTRAL REGIONFEDERAL AVIATION ADMINISTRATION

NOTE

Revisions are indicated by an black vertical line in margin.

Rev. ?O I JUN 7107

Tlln ENSTHOM HE1.ICOllgI~ PAGEiii

GO; F-28FREPORT NO. 28--AC-018TW1N COUNTY AIAPORT P.O. BOX 211. MENOMINEE. M1CHIGAN ~9858

bATC: 11-17-80

LOG OF PAGES AND REVISIONS

REV. NO. PAGES DESCRIPTION I DASE F.A.A.

~:FPI~up Rcvisfd Pl.oaT

I I to hdd /26/t31.eiiru Res I: ric ccd Cat~egory10.2.6 Enve~.ol,e

TaRc, i, tlan\lal.. for Increasad !/4/S1FM over I~cviscd Baoic Fligl~i:

ii, 11.1, Alt:tude Capabilityill Horil Nurmal andI?cstricired Categories

2.0 rhru

2.5, 3.0,3.1, 3.2,.0, 4.4,.5, 4.6,.9 ehru.14, 5.0

thru 5.8

\a~-iurul,

.0, 7.0,

.2 thru

.5, 8.i3,

.0, 10.0,0;1.2

thru0.1.10,

10,2.2,10.2.3,0.2.4,0.2.6,

~0.2.7,0

..2.9,0.3.%!Iru

13.3.6,0..4.1,0.4.6,0.5.1,0.6.1,0.7.1,0.j.2.

*APPROVED BY CHIEF; ENGINEERING AND MANUFACTURING BRANCH,FLIGHT STANDARDS DIVISION,

41 GREAT LAKES REGIONFEDERAL AVIATION AGENCY

NOTE: ~evised text is indicaeed by a vercic;il b.l.ac!~ iiMe ~louE u~argin.

THE.: ENSTRO~ HELICOPTEA CORPORATION PACE ivF-28F RE PORT NO. 2 S-AC-O 1 8

TWIN CCUNTY AIRPORTP.O. BOX 277. HENOMINEE, MICH. 49858DATE: 11-17-80

LOG .OF PAGES AND R~VISIONS

REV. NO. PAGES DESCRIPTIOP1 DATE F.A.A. AP$ROVED

3 F~i cover ~rinor chang9s and/1/52page, ii, additions

1.3, 2.4,2.5, 3.4,4.1, 4~.6,4.7,4.14, 6.6thru 6.14

5.4 thru8.6, 8.9,10.1.2,10.2.2,10.3.6,10.2.9,10.3.2,10.8.6,10.10.1,10.10.3,10.10.3

4 3.9 Page added. 12/30/82.I Cover %c~,f~linor changes and

age, iv, corrections.1.3,2.5

.4, 4.7,4.9, ~4.104.14, 5 .46.2, 6.6,6.8, 6.9,ii.11,7.3,5.2, 8.3,8.4 ,S.10!0.1.2,10.3.i,10.2.9,10.3.1,10.3.3

m APPROVED BY CHIEF, CHICP~GO AIRCRAFT CERTIFICATION OFFICE,c~,ll CEldTRALREGIONa% FESERAL AV IAflON ADM)NISTRATION

NOTE: Kevised tex~ is indicnted by a veitical black line along margin.

TnE ENSTROM HELICOPTER CORPORATION PaGE VF-28F REPORTNO. 28-AC-018

TWIN COUNTY AIRPORTP.O. BOX 277. MENOMINEE MICH. 49858DaTE: 11/17/80

LOG OF PAGES AND REVISIONS

REV. NO. PAGES I DESCRIPTION I DATE FA.A. APPROVED5 i,ii,l.3,)Allows increased gross j

or S/N732 1.5,2.1 eight to 2600 Ibs insub. Not 2.7,5.1 the Normal Category

pplicable lthru 5.121for S/N 732 and Subseq~entelow S/N or if the helicopter32 unless meets the requirementsn conformilty of Enstrom Spec. Drawinith Enstrot-n 1#28-100015,pec Drawi 6.1,IRenumbered pages and28-100015 6.2,6.8,10.1.5, deleted figures 10.11.1 7/1/84 ii;6.11, and 10.11.2.

10.1.7,1_0.1.8,1.0.2.2thru10.2.11,10.3.2,10.3.3,10.11.2thru10.11.7

2.7 Added placard i AL16

6 1 Added pagesv Revised

2.3 Added instruction2.5 Changed mph ~24

4.7 Revised7.3 Added paragraph8.14 Added autorotation rpm8.15 Added figure8.16 Added figure

APPROVED FOR MANAGER CHICAGO AIRCRAFT CERTIFICATION OFFICE(nl CENTRAL REGIONoJ FEDERAL AVIATION ADMINISTRATION

All changes are indicated by a black vertical line along right margin.

RECORD OF TEMPORARY REVISIONS

TEMP ATP REV INSERT DATE REV REMOVEREV NO DESCRIPTION ISSUE DATE DATE BY REMOVED INCOR BY

2/22/2008

THE ENSTHOM COHPORATIONPAGE vii

TWIN COVNTY PIIRPORT PO BOX 117. MENOMINEE. MICHIG~N 14858F28F REPORINO 28-AC-018

DATE: 11/17/30

LOG OF SUPPLEMENTS

SUPF! PAGES DESCRIPTION DATE F.A.A. APPROVED"NO.

.WET/ DRY 1231-80 /~naBD(SPERSAL SYSTEMFLOAT

2 1231-80LANDING GEAREXTERNAL LOADS

3 12-31-80SUPPLEMENTSSNOWSHOE

p~4 12-31-80SUPPLEMENT5 RESERVED

6 RIGHT SIDE P I LOT L~;ELECTRIC CLUTCH

7 ACTUATOREMERGENCY FLOAT

LANDING GEAR

g RESERVED

10 ROTOR BRAKE 2- 5-82

AUXILIARY FUEL 9-23-83TANK

12 ENG~NUEFFELXEHRnUsT rz,

"APP~IOVED FOR CtIICAGO AIRCRAFT CERTIFICAIION OFFICECENTRAL REGIO~FEDERAL AVIATION ADiiIi\JISliTWTIO~

8 ENSTTZQM PAGEHELICOPTER CORPORATION F-28F REPORTNO. 28-AC-0182208 22md STREET~ P.O. BOX OSO~MENOMINEE, MICHIGAN P985~90 U.S.A. DATE 1 1-17-80

TABLE OF CONTENTSAND

LIST OF EFFECTIVE PAGES

SECTION PAGE

Manual Cover Dated 31 December, 1980

Table of Contents andlistofEffective Pages i thru ii

Log of Pages and Revisions iii thru vi

I Lag of Supplements vii1 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 3.9

4 NormalProcedures FAAApproved 4.0 thru 4.14

5 Performance FAA Approved 5.0 thru 5.12

6 Weight and Balance 6.0 thru 6.16

7 Aircraft andSystems Descriptions 7.0 thru 7.8

8 Inspections, Maintenance, Servicing, Storage, and Handling 8.0 thnu 8.17

9 Operational Information 9.0

10 Supplements 10.0

Supplement 1 Wet/Dry DispersalSystem 10.1.1 thru 10.1.13

Supplement2 Float LandingGear 10.2.1 thru 10.2.11

Supplement 3 ExtemalLoads 10.3.1 thru 10.3.6

Supplement4- Snowshoe 10.4.1

Rev. 10/JUN 7/07

Tne ENm~oM HEI.ICOI~TEK COHPOHATION PAGE iiF-28F REPORT NO. 28-AC-018

TWIN COUNTY AIRPORT PO. BOX 277. MENOM(NEE. MICHIGAN 49858DATE: 11-17-80

SECTION PAGE

Supplement No. 5 10.5.1Reserved

Supplement No. 6 10.6.1Right Side Pilot Configuration

Supplement No. 7 10.7.1 thru 10.7.3Experimental Clutch Actuator

Supplement No. 8 10.8.1 thru 10.8.9Emergency Float Landing Gear

Supplement No. 9 10.9.1Reserved

Supplement No. 10 10.10.1 thru 10.10.4Rotor Brake

Supplement No. 11 10.11.1 thru 10.11.7Auxiliary Fuel Tank

Supplement No. 12 10.12.1Engine Exhaust Muffler

pt FAA Approved: 1/4/82~I Revised: 12/14/88

THE ENSTHOhl HEI,ICOI~EH CORPORAT1ONPAGE 1.0

F-28F REPORT NO. 28-AC-018TWIN COUNTY A)RPORT PD BOX 277. MENOMINEE. MICH1OAN 49858

DATE: 11-17-80

SECTION 1

GENERAL

~I Issued: 1/4/82

THE: ENSTHOM HEI,ICOIJTER COHPORATION PAGE 1.I

F-28F REPoRTNo. 28-AC-018TWIN COUNTY AIRPORT PO BOX 277. MENOMINEE. MICHIGAN 49858DATE: 11-17-80

SECTION 1 GENERAL

I I~TRc7DUCTION

This manual contains the operating instructions, procedures andlimitations for the Enstrom F-28Fhelicopter. The manual is dividedinto two basic parts, the FAA approved Rotorcraft Flight Manual(RFM) and Supplemental Data Provided by TheEnstrom Helicopter Cor-poration. Sections 2 through 5 and the portions of Section 10 sodesignated make up the FAA approved RFM. It is required by FederalRegulations that this manual be carried in thehelicopter at all times.

II OWNER RESPONSIBILITIES

Maintaining the helicopter in an airworthy:condition is the respansi-bility of the owner. (See Section 8 for required inspections.) Toaid the owner in this task The Enstrom Helicopter Corporation has anetwork of Distributors, Dealers and Service Centers. In addition tothis Operators Manual The Enstrom Helicopter Corporation has the followingtechnical publications available for your helicopter:

A. F-28F Maintenance Manual Supplement

B. F-28F Parts Manual Supplement

C. Service Information Letters

D. Service Directive Bulletins

Information regarding Dealer locations, Technical Publications andRevisions can be obtained by contacting:

Customer Service DivisionThe Enstrom Helicopter CorporationTwin County AirportP.O. Box 277

Menominee, Michigan 49858

o, 12/31/80Issued:~I Revised: 1/4/82

THE: ENS1HOM COHI~OHATION PAGE 1.2

F-28F REPORT NO 28-AC-018TWIN COVNTY AIRPORT P.O BOX 277. MENOMINEE. MICHIGAN 49858DATE: 11-17-80

III PILOT RESPONSIBILITIES

The pilot in command is responsible for determining that thehelicopter is safe for flight and for operating within the limita-tions specified-in Section 2. Thepilot should familiarize himselfwith the entiremanual prior to receiving competent flight instruc-tion.

IV WARNING, CAUTIONS, AND NOTES

The use of WARNING, CAUTIONS, and NOTES to.emphasize important andcritical instructions is defined as follows:

A. WARNING

An operating practice or procedurewhich, if not correctly followed,could result in personal injury orloss of life.

B. CAUTION

An operating practice or procedurewhich, if not correctly followed,could result in damage to, or dis-truction of, equipment.

C. N O T. E

An operating practice or procedurewhich is essential and requiresadditional information.

V SPECIFICATIONS

A. Principal dimensions of F-28F helicopter:

Width overall 28 ft. 2 in.Rotor diameter 32 ft.Height overall 9 ft.Length overall 29 ft. 4 in.Cabin width at seat 61 in.Baggage Box dimensions 16 in. x 18 in. x 31 in.Tread landing gear 7 ft. 4 in.

v, 12/31/80Issued:Revised: 1/4/82

b THE ENsT~o,n COHPOHATIOF:REPORTNO. ii3rAC-018PAGE 1 3

F-28FTWIN COUNTY AIRPOAT P O. BOX 277. MENOMINEE. MICHIGAN 49858

DATE: 11-17-80

V. SPECIFICATIONS CONTD

B. Power Plant

Type Lycoming OpposedDesignation HI0-360-F1ADCylinders 4Horsepower 225 hp (sea level to 12,000 ft)RPM 3050SFC (full rich) .69 Ib/hp-hrWeight 325 IbsOil 10 qts (8 qts minimum for flight)

C. Ratios

Lower drive pulley to 1.213:1 (3050-2514 rpm)upper pulley

Upper pulley to 7.154:1 (2514-351 rpm)main rotor shaft

Engine to main rotor 8.678:1 (3050-351 rpm)Tail rotor input shaft to 1:1

output shaft

D. Rotor Systems

Number of blades, main rotor 3Chord, main rotor blade 9.5 in.Disk area, main rotor 804 sq. ft.Number of blades, tail rotor 2Chord, tail rotor blade 4.4 in.Di~k area, tai~ rotor 17.1 ,q. ft. i

E. Weight (see Figure 6.1)Designed gross weight 2600 Ibs.Empty weight 1550 IbsUseful load 1050 Ibs.C.G. travel 96.3 in. to 98.0 in, at 2600 Ibs

92.0 in, to 98.8 in. at 2350 Ibs92.0 in to 100.0 in. at 2000 Ibs

NOTE: Four gross weight-c.g. envelopes apply to this helicopter,see Figure Each envelope is associated with adifferent maximum ceiling and a different VNE limitation,see Figure 5.1.

NOTE: This helicopter must meet the requirements of EnstromSpecification Drawing 28-100015. See Limitations Section.

~I Issued: 12/31/80Revised: 12/14/88

REVISIONS:

H 8 ~3m

jj zB ii;

Po

ow

r 54.5" mo ;jC~ L.---

x

9o

e j,X

O

336" (28.0)

219" (18;25)RADIUS

192" (16.0)

3.0

20" STATIC DROOPj I 48.7" MAX. FMD. C. G.108" (9.0)8.0"

23" STATIC

Y

1 56" 14.7)DIA.2.0"

~OC> 73.1.. 16.125.) 93.75~ 17.813) m72" (6.0) MIN. DROOP hj_UL~ MAX. AFT C. G. I I I I om nmB

4.O"~l96" (8.0)

I

(6.55)-~ 337" (28.08!C,.o

351.6"(29.3) 03c88" (7.333)

r

000

FIG. I.1 I

REVISIONS:

H

v, I -iV) C\ 1 5r I z

~Da 8~c rZ m

P

B -1i Ic g

Co g631

o, I a03I I I I E

s

m O5

e336" (28.0) z

219" (18.25

RADIUS192" (16.0)

-3.0"

i I 48.7" 20" STATIC DROOPMAX. C. G.23" STATIC

108" (9.0)

18.0"1 56" (4.7)DIA.

2.0" 1

73.5" (6.125) I I i 1 93.75" (7.813) 172" (6.0) MIN. DROOP r~

MAX. AFT C. G. Os

4.0..tl)i 1 96.(8.01) 1 I OP o1-C78.63.. 16.55.)j m X m337" (28351.6" (29.3) O

(7.333)rPJPrOD~

P

~OrFIG. 1.1

cooOr

Os

THF- ENSII1CI. HELICOr?elPIGE 1~5

1) F-28F REPORTNO. 28-AC-018TWIN COVNTY AIRPORT PO BOX 217. MENOMINEE. MICHIGAN 49858

DATE 11/17/80

VI. PERFORMANCE (All altitudes are density altitude andperformance based on a2350 Ib gross weight unless otherwise noted.)A. Maximum speed (see Figure 5.1)

VNE power on 112 mph IAS from SL to 3000 ft Hd.See Figure 5.1

VNE power off 85 mph IAS from SL to 8200 ft Hd.See Figure 5.1

NOTE: Four (liffererlt maximum ceiling/VNE enve7opes apply to thishelicopter, see Figure 5.1. Each envelope corresponds to agrossweight/c.g. envelope, see Figure 6.1.

NOTE: This helicopter must meet the requirements of EnstromS~pecification Drawing #28-100015. See Helicopter Logbookfor verification that this helicopter meets theserequirements.

B. Cruise speed 75% power~ 101 mph IAS at sea level

C. Maximum cruise speed 110 mph TAS at sea level115 mph TAS at 3000 ft Hd

D. Maximum range speed 85 mph IAS at sea level

E. Fuel consumption at 14.7 gal/hr75% power

F. Maximum endurance, no reserve 3.5 hrs

G. Fuel capacity 42 gal (40 gal usable)157 mph IAS at sea level

H. Maximum R/C at sea level 1450 ft/min

I. Hover ceiling IGE 13,600 ft (see Item K)J. Hover ceiling OGE 8700 ft

K. Maximum approved operatingaltitude 12,000 ft, see Figure 5.1 i

-I Issued: 12/31/80Revised: 7/1/84

TI1E ENSTHOM HEL,ICOI~TEH CORPOHATIONPAGE 2.0

F-28F REPORTNO. 28-AC-018TWIN COUNTY AIRPORT PO BOX 277. MENOMINEE. MICHIGAN 49BJB

DATE: 11-17-80

SECTION 2

OPERATLNG LIMITATIONS

~9 Issued: 1/4/82

()4 TIIE ENSI.D. HLI.ICOTrr~R CORPOII*710N nr;s 2.1F-28F REPORTNO. 28-AC-018

TWIN COVNTY AIRPORT PO BOX 277. MENOMINEE. MICHIGAN 49858DATE: 11/17/80

SECTION 2 OPERATING LIMITATIONS

I. TYPE OF OPERATION

A. This helicopter is approved for operation under day and night VFRnon-icing conditions.

NOTE: Night operation authorized under visual flight rules only.Orientation must be maintained by ground light or adequatecelestial illumination.

B. Operation with doors removed is approved.

II. WEIGHT

A. The maximum gross weight of this helicopter is 2600 pounds. SeeFigure 6.1.

III. CENTER OF GRAVITY (All airspeedsare IAS unlessotherwise noted.)A. The longitudinal datum is 100.0 inches forward of the center line of

the main rotor head.

B. There are four gross weight/c.g. envelopes for this helicopter. SeeFigure 6.1. Each envelope corresponds to one of four VNE/altitudeenvelopes as described in paragraph IV. Also, see Figure 5.1.

NOTE: This helicopter must meet the requirements of EnstromSpecification Drawing #28-100015, See Helicopter Logbookfor verification that this helicopter meets theserequirements. If the helicopter does not meet theserequirements, it must be operated within the limits ofEnvelope A.

C. Envelope A is the lightest weight envelope with a \INE Of 112 mph atsea level. The c.g. and gross weight limits vary as follows:

1. Upper weight limit is 2350 Ibs.

2. Forward limit at 92.0 inches.

3. Aft 1 imi t varies linearly from 94.6 inches at 2350 Ibs to100.0 inches at 2000 Ibs. Aft limit at 100.0 inches below2000 Ibs.

D. Envelope B is the next heavier envelope. It has a VNE at sea level of101 mph. The c.g. and gross weight limits vary as follows:

~I 1. Upper weight limit is 2450 Ibs.

~I FAA Approved: 12/31/80~1 Revised: 7/1/84

f~ Tns ENsl~n HEl.lcalr~a Conposnrlorr PL~GE 2.2F-28F REPORTNO. 28-AC-018

TWIN COUNTY AIRPORT P O. 8OX 177. MENOMINEE. MICHIGAN 49858

DATE: 11/17/80

2. Forward limit varies linearly from 93.8 inches at 2450 Ibs to92.0 inches at 2350 Ibs.

3. Aft limit varies linearly from 96.0 inches at 2450 Ibs to99.2 inches at 2240 pounds and 100.0 inches at 2000 Ibs.

4. The lower limit correspo?ds to the upper forward and aft limits ofEnvelope A.

E. Envelope C has a VNE at sea level of 90 mph. The c.g. and grossweight limits vary as follows:

i. Upper weight limit is 2550 Ibs.

2. Forward limit varies linearly from 95.5 inches at 2550 Ibs to93.8 inches at 2450 Ibs.

3. Aft limit varies linearly from 97.3 inches at 2550 Ibs to98.4 inches at 2470 Ibs and then to 99.2 inches at 2240 Ibs.

4. Lower limit corresponds to the upper forwardand aft limits ofEnvelope B.

F. Envelope D is the heaviest envelope. It has a VNE at sea level of85 mph. The c.g.and gross weight limits vary as follows:

1. Upper weight limit is 2600 Ibs.

2. Forward limit varies from 96.3 inches at 2600 Ibs to 95.5 inchesat 2550 Ibs.

3. Aft limit varies linearly from 98.0 inches at 2600 Ibs to98.4 inches at 2470 Ibs.

4. Lower limit corresponds to the upper forward and aft limits ofEnvelope C.

G. The lateral datum line is the centerline of the helicopter. Lateralmoment arms are positive right and negative left.

H. Lateral offset moment limits vary with weight. See Figure 6.2.

i. From 2025 Ibs to 2600 Ibs, limits are -3250 in-lbs and+3700 in-lbs.

2. Below 2025 Ibs, see Figure 6.2.

FAA Approved: 12/31/80~I Revised: 7/1/84

THE ENSTH(OM HEI.ICOIIEH CORIORATION PAGE 2.3~5 F-28F REPORTNO 28-AC-018

TWIN COUNTY AIRPORT PO BOX 277. MENOMINEE. MICHIGAN 49858DATE. 11-17-80

IV. AIRSPEED

Never exceed speed (V 112 mph, IAS, sea level to 3000 ft densityaltitude. See Fi.gwre 1 for variations above 3000 ft and for variationswith gross weightjc.g.NOTE: There are four V ~altitude enwelopes:with apply to this

envel ope co rres ponds to one of four grosshelicopter. Eacweight/c.g. envelopes. See Figure 5.1.

NOTE: This helicopter must meet the requirements:of EnstromSpeci fi cati on Drawi ng #28-1 0001 5.. See Hel icopter Logbook forverfication that this helicopter meets these requirements. Ifthe helicopter does not meet these requ i rements it must beoperated within the limits of Envelope A.

V. ALTITUDE

Maximum approved operating altitude 12,000 ft density altitude at 2350Ibs. For variations of altitudewith gross weight, see Figure 5.1.

NOTE: Takeoffsand landings at 2600 Ibs grossweightwere demonstratedto 7000 ft density altitude in all wind conditions up to 20 mph.DO NOT EXCEED ENGINE LIMITATIONS.

Takeoffs and landings at 2350 Ibs gross weight were demonstratedto 10,000 ft density altitude in all wind conditions up to 15 mph.

Operators should use appropriate caution above 10,000 itdensityaltitude and in winds greater than 15 mph to insure safe takeoffsand landings.

VI. ROTOR RPM

A. Flight limitations power on:

Minimum: 334 rpmMaximum: 351 rpm

B. Flight limitations power off:

Minimum: 334 rpmMaximum: 385 rpm

See Section 8 for adjustment procedures.NOTE: During transient maneuvers, such as simulated power failure during

pilot training, the rotor RPM may fall below 334. These maneuvershave been demonstrated with rotor RPM dropping briefly to 280,however, sufficient time and altitude must be available to regainRPM.

1~1 FAA Approved: 12/31/80Revised: 12/14/88

THE ENSTROM HELICOPTER CORPORATION F-28FPAGE 2.4REPORTNO. 28-AC-018

TWIN COVNTY AIAPORT P.O BOX 277. MENOMINEE. MICHIGAN 49858DATE: 1/11/85

VII. POWER PLANT LIMITATIONS LYCOMING HIO-360-F1AD

Engine modified per Enstrom Turbocharger Kit LW-14460

A. Maximum continuous power: 225 hp, 3050 rpm, 39.0 in. MP, sea level to12,000 ft.

8. Engine operating rpm:

Minimum: 2900Maximum: 3050 rpm

C. Engine idle rpm clutch disengaged

Minimum: 1450 rpmMaximum: 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. Fue~: 100/130 aviation grade gasoline (green)100LL aviation grade gasoline (blue)

H. Fuel mixture setting:

1. 29 in. MP or below

a. Maximum fuel flow full rich

b. Minimum fuel flow leaned to 16500F rich side of peak

2. 29 in. MP to 39.0 in. MP (full rich)I. Oil temperature: 245" maximum

J. Oil pressure:

100 psi maximum starting and warm up60-90 psi normal operating

28 psi minimum idling

VIII. TRANSMISSION LIMITATIONS

Transmission oil temperature: 2250F maximum

IX. RESTRICTIONS

A. Instrument flight prohibited.B. No aerobatic maneuvers permitted.C. Hovering IGE above 10,000 ft density altitude is limited to five

ol minutes.FaA Approupd::,

a Revised: APR

THE ENSTROM HELICOPI~ER CORPOR~TIONPAGE 2.5

TWIN COUNIY ~IRPORT P.O. 80X 2r1. MENOM(hlEE. MICHIGAN n9858F-28F REPORT NO. 28-AC-018

DATE: 11-17-80

X. MINIMUM CREW

A. One pilot.8. Solo from left seatonly. (See Supplement No. 6)

XI. IMSTRUMEMT MARKINGS

A. Rotor tachometer

i. 334 rpm red line2. 334-385 rpm green are3. 385 rpm red line

B. Engine tachometeri. 2900 rpm red line2. 2900-3050 rpm green are3. 3050 rpm red line

C. Maximum airspeedi. 85 mph2. 112 mph Power off) blue linepower on)

D. Manifold pressurel0 in. to 39 in. green are

2. 39.0 in. Hg red line3. Overboost light illuminates at 39 in. manifold pressure

E. Engine oil temperaturei. 245" red line2. 120" 245"F green line3. 60" 120"F yellow are

F. Engine oil pressurei. 100 psi red line2. 60-100 psi green are3. 25-60 psi yellow are4. 25 psi red line

G. Cylinder head temperaturei. 500"F red line2. 200" 500"F green ard

H. EGT

1650"F red line

FAA Approved: 12/31/802 Revised: 8/29/85

ENSTROM PAGE 2.6HEUCOPtER CORPORAT1ON F-28F REPORTNO. 28-AC-018ZM9 22nd STREE~T P.D. BOX 490 MENOMINEE. MICHIGAN 498580dD0 U.S.A. DATE 1 1-17-80

I. Transmission oil temperature

i. 225"F red line2. 0" 225" F green are

XII. PLACARDS

A. Placards that are required to be placed in view of the pilot are:

1. THIS HELICOPTER MUST BE OPERATED INCOMPLIANCE WITH THE OPERATING LIMITATIONSSPECIFIED IN THE FAA APPROVED ROTORCRAFTFLIGHT MANUAL

2. PLACARDS FOR F-28F V,, (located overhead above center windshield):

I a. The following VNE placards are used on all F-28F helicopters up to serialnumber819.

2990 v,,- IAS ~MPH) FOR ENVELOPE AB C g

D

AL~TUDE -;10 O 40 60 80 100 Bc

2400SEA LEVEL 112 112 1 112 1 112 1 112 1 112 1 112

2200 2000 112 112 112 112 112 109 1054000 112 112 112 105 100 91

Q "000 sooo 112 ill 1 106 100 90181 738000 107 102 64 55BO~f 1 94 84 t4 65 5598 iOD 2&180052-1112000 76 65 56

CG-lnches

~e v,,-rAS (MPH) FOR ENVELOPE B

Dd c~

_20 9 20 40 59 80 100SEA LEVEL ~01 101 101 101 101 M 101 B96

A 4000 101 101 101 99 96 81 82

B 2000 8000 101 100 96 92 82 73 658000 91 93 83 73 64 56

BO~ 1 86 75 85 56 28;1&00536194 99 99 100 10,800 78 63 57

CG-lnches

ORIGINALAs Received By

FAA Approved: June 8, 2007 ATP Rev. 10 JUN 7/07

E3N5;rROM PAGE 2.7HEUCOPTER CORPORAtlON F-28F REPORTNO. 28-AC-0182209 22nd STAEFT P.O. sox 490 MENOM1NEE. MICMIGAN ~9858-0490 V.S.A. DATE 1 1-17-80

2. PLACARDS FOR F-28F V,,

a.(continued)

2600 v,- IAS (MPH) FOR ENVELOPEC~Lcl)

2400 ALTITUM -20 O 20 48 so so looSEA LEML 90 so 90 90 90 90 99

2000 90 90 90 90 90 88 86

A 4000 90 90 90 88 86 82 736000 90 89 86 82 73 64 55 C8000 87 84 14 64 55

88 t(X)9600 80 70 80 28-1 80054-1 1

CG-lnches

260(] v,- IAS (MPH) FOR ENVELOPE DD/L 1 C\

PRESSURE-20 0 20 40 60 80 100

_ fj~ f SEALEIIEL 85 1 85 85 85 1 85 84 83D 2000 85 1 85 85 84 83 82 81

A 4000 85 846000 83 82 81 79 89 59

o 8000 81 80 10 60 281 8004811

os iM)9000 80 60 a

b. The following VNE placards are used on all F-28F helicopters serialnumber 820 and subsequent. F-28F helicopters up to serial number 819may also use the following placards.

2600 v,,- IAS (MPH) FOR ENVELOPE A/L/- ~eD APRESSURE TUREFd c~-20 O 20 40 60 80 1M) 1202400 ALTITUDE

SEA LEVEL 112 112 212 112 112 112 112 112g2000 112 112 112 112 112 109 105 101y 22004000 112 112 112 110 105 100 91 82

2000 6000 112 111 106 100 90 81 73 65(2 8000 107 102 92 82 73 64 55

isOO9~ ~0,000 94 84 74 g5 5594 96 68 lao 28-1 80052-1312,000 76 65 56CG-lnches

ORIGINALAs Received By

FAA Approved: June 8, 2007 ATP Rev. 10 i JUN 7/07

Q ENS;rRQM PAGE 2.8HEUCOPTER CORPORATION F-28F REPORTNO. 28-AC-0182209 22nd STREFI P.D. BOX 490~MENOMINEE, MICHIGAN 49ess-o4eo U.S.A. DATE 1 1-17-80

2. PLACARDS FOR F-28F V,,

b.(continued)

~Lr ;r~C D VNE- IAS (MPH) FOR ENVELOPE IBI2600c~ PRESSURE

2400 ALTITUDE -20 0 20 40 60 80 100 120SEA LEVEL 101 101 101 101 1M 101 101 101 B2200 2000 101 101 101 101 101 99 96 93

v, A 4000 101 101 101 99 96 91 82 73 -3o" 2000 6000 101 100 96 92 82 73 65 57

8000 97 93 83 73 64 56

1B00g: 10,000 86 75 65 56 281 80053-1394 96 98 100 10,800 78 1 63 57CG-lnches

2600c-~- O VN,-IAS (MPH) FOR ENMLOPE C

PRESSURE

ct 2400 ALTITUDE -20 0 20 40 60 80 100 120Z SEA LEVEL 90 90 90 90 90 90 90 90

2200 2000 90 90 90 90 90 88 86 84VJ A 4000 90 90 90 88 88 82 73 64

2a001 6000 90 89 86 82 73 64 55 C8000 87 84 74 64 558C9~ 9800 80 70 60 28-1 80054-1394 96 98 100

CG-lnches

2600 VNE- IAS(MPH) FOR ENVELOPE DPRESSURE 7 OUfSIDE PJRTEMPERATURE

2400 ALTITUDE -20 0 20 40 60 80 100 120SEA LEVEL 85 85 85 85 85 84 83 82

22001 1 2000 185 1 85 1 85 1 84 83 I 82 81 1 80v, A 4000 85 84 83 82 81 78 69 60

20001 6000 83 82 81 79 69 59g

1 8000 81 80 70 60 28-180048-13iso~

CG-lnches

9000 80 71 60 D94 96 98 100

3. NO SMOMNG

(This placard not required when approved ash~ray is installed.)

ORIGINALFAA Approved: June 8, 2007 As Received By Rev. 10 IJUN 7107

ATP

ENStROM PAGE 2.9HELICOPTER CORPORATION F-28F REPORTNO. 28-AC-018pOB 22nd P.O. BOX 49()~ MENOMINEE. MICHIGAN dSBSBMBD U.S.A. DATE 1 1-17-80

4. THIS HELICOPTER IS APPROVED FOR OPERATIONUNDER DAY AND NIGHT VFR NON-ICINGCONDITIONS ONLY

5. COLLECTIVE FRICTION TO BE USED FOR GROUNDOPERATION ONLY

(This placard to be placed adjacent to the collective friction device.)

B. A placard to be placed in the baggage compartment is as follows:

NIAXIMUM WEIGHT IN THIS COMPARTMENT IS 108 LBS.OBSERVE C.G. AND GROSS WEIGHT LIMITATIONS

C. STOW FLAT ON FLOOR BEFORE FLIGHT

(This placard to be placed on clutch handle.)

FAA Approved: June 8, 2007 Rev. 10 JUN 7107

4 T~lr: ENSTKOM HEI.ICO~IEI( PAGE 3.0F-28F REPORT NO 28-AC-018

TWIN COUNTY AIRPORT PO BOX 217 MENOMINEE MICHIGAN agS58DATE: 11/17/80

SE%TFON 3

EMERGENCY AND MALFUNCTION PROCEDURES

Lssued: 1/4/82

TII~: ENsrrco.n PnGE 3.1

F-28F REponr No 28-AC-018TWIN COVNTY AIRPORT PO BOX 2?: MENOMINEE MICHIGAN 49858DATE: 11-17-80

SECTION 3 EMERGENCY AND MALFUNCTION PROCEDURES

I. GENERAL

This section describes the system failures and malfunctions that mayreasonably be expected to occur andestablishes the emergency proceduresused to maintain control and get the helicopter safely on;the ground.

II. ENGINE FAILURE

The indications of an engine failure, either partial or complete powerloss are; a left yaw and a drop inengine and main rotor rpm. Whenthese conditions are encountered the procedures to be followed aredetermined by the altitude and airspeed available to establish anautorotative glide, control the helicopter and maintain sufficientrotor rpm for a successful landing.

A. Engine Failure Altitude above 375 ft. AGL. When engine failureoccurs proceed as follows:

i. Enter autorotation (collective full down, throttle to idleand right pedal to trim helicopter).

2. Stabilize at 55 mph glide. (Best rate of descent speed.)

CAUTION

Due to high rates of descent, sustainedautorotatioa speed is limited to 85 mphto 8200 ft., above 8200 ft. see Fig. 5.1.Maximum glide distance in autarotationis attained at 80 mph and 334 rotor rpm.Reduce collecti~ire to build rpm prior totouchdown.

3. Check engine and rotor rpm. Adjust collective to keep rotorin green are. If engine is stopped, turn OFF fuel boost pumpand place mixture control in ICO position. If altitude andtime permit, see Air Restart Procedure, Section 3.2.

4. Select landing site.

NOTE

If engine is running and suitable landingsite is not within glide distance, thepilot should attempt to fly the helicopterat reduced power settings to a favorable

irjl landing area. The pilot should be preparedfor a complete loss of power at any time

Jjl under these conditions.

FAA Approved: 12/31/80 Revised: 1/4/82

f~ T.F ERJTHb* HBI.ICOIPHI CDHI.UIL*1.I(IN P*GE 32F-28F AEPORTNO 28-AC-018

TWIN COUN~Y AIRPORT PO BOY 277 MENOMINEE. MICHIGAN 49858

DATE: 11-17-80

5. At approximately 50 ft. AGL apply aft cyclic to reduce speed.

6. Level helicopter with forward cyclic at an.altitude sufficientto provide tail rotor clearance. As helicopter settles towardground, apply up coillective to cushion landing.

7. Maximum recommended ground c.ontact speed on prepared surfaces is 1Reduce speed on rough surfaces.CAUTION

Helicopter control is primary concernafter entering autorotation, DO MOTattempt air restart if control will bejeopardized.00 NOT ATTEMPT AIR RESTART WHEN BECOW3000 feet AGL.

1. Adjust collective as required to maintain rotor RPM in green areand establish 58 MPH autorotative glide.

2. Select landing site.

3. Grip cyclic between knees, turn fuel boost pump OFF and pullmixture control to ICO.

4. Rotate throttle to start position. (start index up)5. Engage starter.

6. When engine fires, mixture full rich and boost pump ON.

7. Slowly increase throttle until engine and rotor tach needles joinin green are.

C. Engine Failure Altitude above 10 feet and below 375 ft. AGL.When an engine failure occurs at low altitude and low airspeed,sufficient altitude may not be available to increase rotor RPM. Thecollective must be adjusted for the conditions in order to reach thetouchdown point without excessive rotor droop. The collective re-duction will vary from no reduction at zero airspeed at 10 feet tofull down collective at higher altitudes and airspeeds. When enginefailure occurs proceed as follows:

1. Adjust collective to maintain rotor RPM, throttle to idle positionand right pedal to trim helicopter.

O FAA Approved: 12/31/80Revised: 12/1$/68

THE ENSTROM CORPOHATION PAGE 3.3F-28F REPORTNO. 28-AC-018

TWIN COUNTY AIRPORT PO BOX 277. MENOMINEE. MICHIGAN 49858

DATE: 11-17-80

2. Adjust cyclic for autorotative glide.NOTE

At higher altitudes and low airspeed useforward cyclic to increase forward speedto approximately 58 mph. At low altitudesand higher airspeed aft cyclic will berequired to reduce speed prior togroundcontact.

3. At altitude of approximately 50 ft. use .aft cyclic to reduceforward speed.

4. Level helicopter with forward cyclic at an altitude sufficient toprovide tail rotor clearance.

5. As helicopter settles toward the groundapply up collective tocushion landing.

6. Maximum recommended ground contact speed on prepared surfaces is35 mph. Reduce speed on rough surfaces.

CAUTION

Avoid rapid lowering of collective oruse of aft cyclic after ground contactor during ground slide.

D. Engine Failure at Hover. Engine failure at a hover is indicated bya sudden yawing of the helicopter to the left. Avoid sideward orrearward movement after engine failure and proceed as follows:

i. Apply right pedal to prevent yawing and align skids in directionof motion.

2. DO NOT reduce collective.

3. As helicopter settles to the ground add up collective to cushionlanding.

III. DITCHING WITHOUT POWER

If engine failure occurs over water, accomplish engine failure emergencyprocedure and proceed as follows:

A. Unlatch doors.

O FAA Approved: 12/31/802 Revised: 12/14/88

E,vsrHow Hel.lcollF:r~ PAGE 3.4

REPORTNO 28-8C-018TWIN COUNTY AIRPOAT P O BOY 277 MENOMINEE MICHIGAN 49858 F- 28FoaTE: 11-17-80

B. Land. Complete normal autorotational landing in water.

C. As collective reaches full up positionand helicopter settlesin water apply full lateral cyclic in direction helicopter tendsto roll.

D. Piler and passengers exit helicopter when main rotor stops.

WARNING

Clear helicopter as quickly as possible.

IV. DITCHING WITH POWER

If ditching is unavoidable without other recourse, proceed as follows:

A. Descend to low hovering altitude over water.

B. Unlatch both doors.

C. Exit passengers.

D. Hover clear of passengers.

E. Turn off master and alternator.

F. Close throttle and complete hovering autorotation.

G. As collective reaches full up position and helicopter settlesinto water, apply full right lateral cyclic.

H. Exit helicopter when rotor stops.

WARNING

Clear helicopter as quickly as possible.

V. TURBOCHARGER OR WASTEGATE FAILURE

Turbocharger or wastegate seizure will be evidenced by loss of mani-fold pressure, if operating at manifold pressures above ambientpressure. It should be possible to maintain level flight at reducedairspeeds and altitudes as the engine should be capable of maintainingmanifold pressure equal to ambient pressure. If the turbochargerseizes or the wastegate seizes in the full bypass condition, proceedas follows:

~I A. Perform a power check to confirm power available for landing.

~I B. Land as soon as practicable, using running landing (see Page 4.13).Irl FAA Approved: 12/31/80 Revised: 7/1/52

f )Ill~li ENS.II~OM H~I.ICOII.EI( CORPOHA.TION PAGE 3.5REPORTNO 28-AC-018TWIN COUNTY AIRPORT PO BOX 277 MENOMINEE MICHIGPN 49858 F-28FDATE 11-17-80

VI. LOW ENGINE OIL PRESSURE

A. Low Oil Pressure and Normal Oil Temperature

If low oil pressure is accompanied by normal oil temperaturethere is a possibility the oil pressure gauge or relief valveis malfunctioning. This is not necessarily cause for an im-mediate precautionary landing. ~Proceed as follows:

i. Land at the nearest suitable landing area.

2. Inspect for and correct this source of trouble beforecontinuing flight.

B. Total Loss of Oil Pressure

If a total loss of oil pressure is accompanied by a rise in oiltemperature this is a good indication that the engine failureis imminent. Proceed as follows:

i. Reduce engine power immediately.

2. Select a suitable forced landing field and land with power.

VIF. TAIL ROTOR MALFUNCTIONS

Because of the many different malfunctions that can occur, successin coping with tail rotor malfunctions depends upon immediate re-cognition of the condition and use of the proper emergency procedure.The following is a description of the three basic types of malfuncrionsand the appropriate emergencyprocedures to follow:

A. Complete Loss of Tail Rotor Thrust

This condition can be caused by a failure of the tail rotordrive system or a failure of the control system which would allowthe blades to assume a neutral pitch condition.

i. Hovering Flight

When tail rotor thrust is lost in hovering flight the heli-copter will rotate rapidly to the right, even with fullapplication of left pedal. Proceed as follows:

a. Roll throttle off to full idle positibn. Relicopterwill slow down or stop rotation.

b. As helicopter settles to ground, cushion landing withup collective (throttle off).

Irl FIV\ Approved: 12/31/80

TI(E ENSIRI)M HI~I.I(OIIEH COI~IJOl(r\llON PAGE 3.6

F-28F RtPORNO 28-AC-018TWIN COUNTY AIRPOAT PO BOX 277 MENOMINEE MICHIGAN 48858oaTE 11-17-80

2. During Flight Near Suitable Landing Area

Helicopter will rotate to right with full application ofleft pedal. Proceed as follows:

a. Roll throttle full off to idle and enter autorotation.

b. Complete autorotational landing.

3. During Flight

If suitable landing area not available within autorotativeglide distance, pilot should proceed as follows afterestablishing autorotation at 60 mph or above.

a. Increase collective pitch and power gradually, maintaining60 to 80 mph until yan to the right reaches a maximumof 450

b. Continue flight in this fashion using cyclic stick fordirectional control until suitable autorotational

landing site is reached.

c. Complete autorotational landing.

B. Fixed Pitch Setting

This is a malfunction involving loss of control resulting in afixed pitch setting. Whether the nose will rotate left or rightdepends upon the setting of the pedals when the controls werejammed or locked.

i. Fixed Right ~edal

If the tail rotor pitch becomes fixed during an approach orlow power setting the nose will turn to the right when poweris 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 onapproach at 50 mph.

d. Adjust throttle and collective pitch so the helicoptertouches down straight ahead at an airspeed of 0-10 mph.Reduce throttle and collective cautiously as skids con-tact surface.

~I F;2A Approved: 12/31/80

rllllllllllllll~1~ ENSIRQM PAGE 3.7

I ~ISTHELICOPTER CORPORATION F-28F REPORT NO. 28-AC-01822M) 2lnd STREFT P.O. BOX 460 MMOMINEE, MICHIBAN 498680480 U.S.A. DATE 1 1-17-80

I IDO NOT abort the emergency landing after airspeed hasdia;-d;dbiirMmI1

2. Fixed Left Pedal

If the tail rotor pitch becomes fixed during cruise or high power settings thehelicopter will yaw to the left when power is reduced below 23" manifoldpressure. Power settings above 23" manifold pressure will produce nearnormal flight conditions at airspeeds above 60 mph. Proceed as follows:

pressure and 60 mph or above.

b Ii c. Adjust throttle and collective pitch so that the helicopter touches down

straight ahead at an airspeed of O to 10 mph.

surface.

I Application of power to settings greater than 23 inchesmanifold pressure will make the helicopter morecontrollable. Therefore, landing attempt may be abortedand new approach initiated if required.

I IC. Loss of Tail Rotor or Components

weight is lost the situation would be similar to a loss of thrust situation. If a largeamount of weight is lost and there is a drastic forward shift in C.G. immediate autorotation is the only emergency procedure available.

VIII. MAIN ROTOR GEARBOX AND TAIL ROTOR GEARBOX

A. Main Rotor Transmission Temperature

I --------------I- LIf the main rotor transmission temperature exceeds red line, reduce power. If theFAA Approved: June 8, 2007 Rev. 10 1 JUN 7/07C

r II~ IIENZSTROM PAGE 3.7.1aEuaMEacaapoamoH

ia II

a~n. main ra, uaosrminion EIP IlgN fames on i"iUBn~ aad m~ lulsrm~iionfemperatu.e is below the r.d line, mon~itor the temperatue end lend as soon asI prartnable onlandog ~emoue sndin.pest(he shi~ derectol (see NOIE)If the main rotor transmission chip light is accompanied by high transmission

C, Tail Rotor Transmission Chip Light (If Equipped)

I i- ",~iI New or recently overhauled gearboxes generallygenerate a ferrous "fuzz" which will collect around the

chip detector as a gray sludge, This type ofcontamination is normal and may be cleaned off with asoft cloth, and the chip detector may be reinstalled andthe flight continued. Any metallic chip greater than 1/16inch in diameter or cross section, or chip lightaccompanied by high transmission temperature is causefor discontinuation of normal flight, In the event offinding large chips, please contact your nearest EnstromService Center or the Enstrom factory. Specific instruc-tions in removal, checking and reinstallation of the chipdetector may be found in Section 8, paragraph V (M),

II i

I iFAA Approved: June 8, 2007 Rev. 10 i JUN 7/07C L

THE ENSIHO~ PAGE 3.8

REPORTNO 28-AC-019TWIN COUNTY AIRPORT PO BOX 277 MENOMINEE MICHIGAN J985R F-28FDATE: 11/17/80

IX FIRE IN FLIGHT

If fire, smoke or the odor of smoke is detected in flight, proceed asfollows:

A. Land immediately using power on approach.

B. Turn the master and alternator switch to the off position.

C. If smoke obstructs vision unlatch doors and let them trail open.

D. Shut off engine as soon as helicopter is on the ground.E. Fuel valve OFF.

F. Pil.ot and passengers clear the helicopter immediately.

X FIRE ON TKE GROUND

If fire, smoke or the odor of smoke is detected proceed as follows:

A. Shut off engine and all switches

B. Shut fuel. valve OFF.

C. Pilot and passenger clear the helicopter immediately.

Xi ALTERNATOR MALFUNCTION

A mal~unction of the alternator will be indicated by zero charge rateor constant discharge on the ammeter. To put the alternator back onthe Pine, proceed as follows:

A. Alternator circuit breaker in.

B. Alternator excite circuit breaker in.

C. Cycle alternator switch.

D. If alternator is not restored or goes off the line again, turnoff all nonessential electrical equipment and land as soon aspracticable.

XII ELECTRIC BOOST PUMP FAILURE

Failure of the electric fuel boost pump will ~e indicated by illumina-tion of red, low boost warning light. The engine will continue tofunction. If the low boost warning light comes on, land as soon aspracticable.

FAA Approved: 12/31/80

TIIE ENBTHUM HEI_IC(IIIYR CnKI.I)R*TI(IN p4GE 3~9F-28F REPORTNO 28-AC-018

TWIN COUNTY AIRPORT PO BOX 277 MENOMINEE. MICH)GAN 44858DATE: 11-11-80

XIII CLUTCH DISENGAGEMENT LIGHT ON

Should the manual clutch become disengaged during flight, it will resultin an instantaneous engine overspeed and severe left yaw at manifoldpressures much above idle. These indications will be instantaneous andthe pilot should immediately enter autorotation. An i ndi cati on of aclutch disengagement without engine overspeed or severe yaw may mean thata clutch disengagement is probable or that the microswitch or electricalcircuit has malfunctioned. The pilot should proceed as follows:

1. Clutch Disengagement Light on with Motion Cues

a. Enter autorotation and reduce power to idle.

b. Perform autorotative landing.

c. Inspect for and correct the source of trouble before continuingflight.

2. Clutch Disengagement Light on without Motion Cues

a. Reduce power and beprepared for sudden clutch disengagement.

b. Land at nearest suitable landing area.

CAUTIONBe prepared for autorotationshould clutch become disengaged.

c. Inspect for and correct the source 05 trouble before continuingflight.

XIV. ABNORMAL VIBRATIONS

Vibrations in this helicopter can usually be classified as either lowfrequency or high frequency. Low frequency vibrations are generallycaused by the main rotor system while the high frequency vibrationsusually originate from the engine, drive system, or tail rotor. Anyabnormal vibrations are an indication that something is not correct andshould be referred to a mechanic before further flight. If a vibrationsuddenly appears during a flight, it is an indication that something hassuddenly changed. The helicopter should be landed as soon as practicaland inspected to find the cause of the vibration. After the cause of thevibration has been identified, the pilot and the mechanic can determinewhether the helicopter can be safely flown or should be repaired on thespot. An abnormal vibration is reason to get the aircraft down as soon aspossible, but the pilot must also use caution and select the safestpossible i andi ng si te worki ng around wi res people, and other ob-structions.

FAA Approved: 12/30/82~1 Revised: 12/14/88

THI EN6THd~ H13I.ICOY~F:H COHPOHATION PAGE 40TWIN COUNTY A1RPORT PO BOX 277 MENOMINEE. MICHIGAN 49858 F-28F

REPORTNO 28-AC-018DATE: 11-17-80

SECTION 4

NORMAL PROCEDURES

~II Issued: 1/4/82

1 THE ENSTHOM HEI,ICOI1E:H COHPORATION PAGE 4.1F-28F nEponT No 28-AC-018TWIN COUNTY AIRPORT PO BOX 277. MENOMINEE. MICHIGAN 49858

DnrE: 11-17-80

SECTION 4 NORMAL PROCEDURES

I PREFLIGHT PLANNING

A. Review and be familiar with Section 2 "Operating Limitations"

B. Calculate weight and balance and review loading information inSection 6 "Weight and Balance"

C. Obtain weatjler briefing and file flight plan.

D. Refer to Section 5 "Performance" to determine if helicopter is withinlimitations for planned loads, winds, temperatures and pressurealtitudes.

NOTE

Pilot experience and training is anotherfactor to consider prior to conductingcertain flights even if helicopter is with-in its operating envelope.

E. Check helicopter and engine log books to determine if helicopteris airworthy.

II. PREFLIGHT INSPECTION

This check list is designed to be used as a guide while performingthe Preflight Inspection. Thoroughly familiarize yourself with theMaintenance Manual before utilizing this checklist.

A. Cabin Prior to starting the exterior inspection check the cabinfor the following items:

i. Standard Airworthiness Certificate, FAA Form 8L00-2.

2. Certificate of Aircraft Registration, AC Form 8050-3.

3. If communications radio installed Aircraft Radio StationLicense FCC Form 556.

4. Flight Manual for helicopter to be flown. Check forms F-1GSAand F-168A in Section 6 for actual weight and balanceof helicopter to be flown. The serial number of the heli-copter to be flown should appear on these forms.

FAA Approved: 12/31/80 Revis ed 7/1/82

THF: ENS(ROM HEI,ICOIIIZH CO)~POHATION PAGE 4.2

F-28F REPoRT No 28-AC-018TWIN COUNTY AIRPORT PO BOX 271. MENOMINEE. MICHIGAN 49858DATE: 11-17-80

NOTE

The above items are to be carried in the

helicopter at all times. Owners andoperators of exported helicopters shouldcheck with their own Aviation Officialsto determine documents required.

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. Pitot Tube unobstructed.

5. Landing light check condition.

6. Right door check condition, security and latch operation.

7. Right oleo struts check extension and security.

8. Right landing gear check condition and security. Checkground handling wheel in up position and secured.

9. Right side engine compartmenta. Electrical wiring condition and terminals tight.b. Lnduction system no obstructions, filter secure, induction

hose and lines secure and backfire and alternate air doorsfree.

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.f. Exhaust no cracks or signs of leakage.g. Cowl door secure.

n( FAA Approved: 12/31/80

I THE ENSTHOM HEI,ICOIIEH COHPOHATION PAGE 4.3F-28F RtPORNO 28-AC-018TWIN COUNTY AIAPORT PO BOX 277 MENOMINEE MICHIGAN 49858

DATE: 11-17-80

10. Upper inspection door

a. Fuel tank drain drain sample into jar.b. Swash plate and control rods check condition and security.c. Fuel tank and lines check for leaks and lines and fitting

secure.

d. Fire curtain condition.

11. Kick in step door

a. Belt drive system check security and condition of idlerpulley, main drive belt.

b. Tail rotor drive shaft check condition of flex coupling.c. Rotor tach drive check condition.d. Cooling fan condition.

12. Right fuel tank check for leaks, fuel quantity and cap secured.

13. From steps

a. Check M/R gearbox filler cap closed.b. Check area between fuel tanks for leaks and obstruction to air

flow.c. Main rotor shaft check condition.d. Main rotor blades security and condition of leading edge

blade tape, no bond seperations, cracks or corrosion. Mainrotor retention pins secured.

e. Check M/R hub for security of all fasteners, no cracks orobvious damage.

f. M/R pitch links check for binding or looseness.g. M/R dampers check for security and no leakage.

14. Baggage box

a. Check contents secured. Observe weight limitations.b. Open inspection door check main rotor transmission sight

gauge. Normal level is half way mark on sight gauge.c. Door secured.

15. Right static port check unobstructed.

16. Tail cone check condition.

17. Tail rotor drive shaft condition and security of drive shaft,hangar bearings and flex couplings.

18. Horizontal stabilizer condition and security.

19. Position lights security

FAA Approved: 12/31/80

THe ENSTROM CORIOHATION PAGE 4.4

F-28F REPoRTNa 28-AC-018TWIN COUNTY AIRPORT PO BOX 277 MENOMINEE. MICHIGAN 49858DATE: 11-17-80

20. Tail rotor

a. Control cables check condition and security.b. Tail rotor transmission check for oil leakage and check

oil quantity. Check for security of attachment.c. Tail rotor guard check for security and evidence of strike

damage.d. Pitch change mechanism check condition and operation.

Check pitch links for binding or looseness.e. T/R hub check security. Check condition of teeter stop

bumpers.f. Tail rotor blades check security. Check for cracks or

bond seperations. Check strike tabs for evidence of strike.

21. Left static port unobstructed.

22. Inspection door

a. Belt drive system engage manual clutch and check belt

tensioning system for proper rigging. Disengage manualclutch.

b. Cooling fan check condition.

23. Left fuel tank check for leaks, fuel quantity and cap secured.

24. Upper inspection door

a. Check engine oil quantity -10 qts full,flight. 8 qts minimum forb. Fuel tank drain drain sample into jar.c. Swash plate and control rods check condition and security.d. Fuel tank and lines check for leaks, lines and fittings

secure.

e. Fire curtain condition.

25. Left engine compartment

a. Turbocharger check condition and security. Check conditionof thermal cover and check area around turbocharger forevidence of heat damage.

b. Exhaust system and waste gate check for security and evidenceof leakage. Wastegate linkage should be in detent, throttlemotion should be free and unrestricted with associated waste-

gate motion.c. Cowl door secure.

26. Left oleo struts check extension and security.

27. Left landing gear check condition and security. Ground handlingwheel in up position and secured.

28. Check operation of all lights for nighs flight.

i?l FAA Approved: 12/31/8021 Revised: 12/30/82

THF: ENSTHOM HF:l.l(Ollf~H COKPORATION PAGE 4.5

F-28F REPORT NO 28-AC-018TWIN COUNTY AIRPORT PO BOX 277 MENOMINEE. MICHIGAN 49858

DnTE: 11-17-80

III BEFORE STARTING ENGINE

A. Adjust pedals.

B. Seat belts fastened and doors latched.

C. Flight controls check for full travel. Center cyclic and pedal.

D. Throttle OFF

E. Collective full down and locked.

F. Fuel valve ON tin).

G. Heater as desired tin for off).

H. Rotor clutch disengaged.

CAUTION

Starting helicopter with clutch engagedwill not damage rotor system but willseverely overload the starter motor.

I. Mixture control in idle cutoff position.

J. Check magnetic compass.

K. Altimeter set to field elevation.

L. Radio(s) off, frequencies set.

M. All switches off and circuit breakers set.

IV STARTING ENGINE

A. Collective down and locked.

B. Master switch ON.

C. Alternator switch on (off for APU start).

D. Starter relay C.B. ON.

E. Trim motor C.B. ON.

-I FAA Approved: 12/31/80rrl Revised: 1/4/82

THF: ENSTROM HEI.ICOISER COHPOHATTON PAGE46

~L)1 F-28F REPORTNO. 28-AC-018TWIN COUNTY AIRPORT PO BOX 277 MENOMINEE. MICHIGAN 49858

DATE: 11-17-80

IV STARTING ENGINE CONTD

F. Throttle open (full).

G. Mixture control full rich.

H. Boost pump switched ON (5-8 seconds).

I. Boost pump switched OFF.

J. Ignition switch ON to both.

K. Throttle closed. Then open to start position (i.e., index up)(see Section 7).

CAUTION

Excessive throttle opening on startingwill result in an engine overspeed whichproduces severe engine damage.

L. Mixture control to idle cutoff (ICO).

M. Engage starter button. When engine fires, release starter button andpush mixture control to full rich.

NOTE

If engine fails to start within 2 to 3seconds, release starter button, primeengine using steps F through K.

N. Turn fuel boost pump ON.

O. Check engine oil pressure off "0" mark within 30 seconds.

P. Disconnect APU.

4. Alternator ON.

R. Check engine idle speed, should be 1450 to 1500 rpm.

NOTE

Idle mixture and rpm must be adjustedfor change in base altitude.

FAA Approved: 12/31/80Revised: 7/1/82

THE ENSTROM HELICOP~ER CORPORATION PAGE 4.7F-28F REPORTNO. 28-AC-018

TWIN COUNTY AIRPORT PO BOX 277. MENOMINEE. MICHIGAN 49858

onTE: 11-17-80

S. When engine oil pressure is above 25 psj and engine runningsmoothly, rotor may be engaged.

V STARTING HOT OR FLOODED ENGINE

A. Hot engine prime engine 3-5 seconds. Proceed with normal startingprocedure, steps J through M.

NOTE

If engine fails to start after 2-3 seconds, slowlymove mixture control to full rich position whilecranking engine. DO NOT engage starter for morethan 5 seconds in fu~l rich position.

B. Flooded engine Ignition switch in OFF position, throttle full openand mixture control in ICO. Press starter and crank engine for3-5 seconds. Throttle closed, then cracked open to start index upposition. Ignition switch ON and proceed with normal startingsequence.

VI ROTOR ENGAGEMENT

A. Check collective down and locked.

CAUTION

Heavy spring capsule forces are present with zeroor low rotor rpm, and damage to the helicopter andengine can resu~t if the collective is to rise.

Collective friction is to be used for ground operation only.

B. Check pedals in neutral position.

C. Center cyclic with trim motors.

D. Check area for personnel and obstructions.

E. Maintain throttle in idle position 1450-1500 rpm and slowly engageclutch until engine rpm drops to 1100-1200 rpm.

F. When rotor rpm reaches 100 rpm, fully engage clutch.

NOTE

Clutch disengage warning light will go out and, onaircraft so equipped, rotor rpm warning light willcome on when clutch is fully engaged.

~I FAA Approved: 12/31/80rl Revised: 1/8186

THF~ EASTHOM HI:I.ICO~I:R C~HrOH*TIONP*GE 4.8

F-28F REPOAT NO 28-AC-018TWIN COUNTY AIRPORT PO BOX 277. MENOM1NEE. MICHIGAN 49858

DnTE: 11-17-80

G. Place clutch handle in stowed position.WARNING

Severe engine damage and complete loss of powerto rotor system will result of manual clutch isdisengaged under any condition other than throttleat idle position.

VII OPERAT~ONAL CHECKS

A. Advance throttle to 1800 rpm and wait for cylinder head temperatureto reach 200"F.

B. After reaching 200"F cylinder head temperature, slowly advancethrottle to 2300 rpm and wait until oil temperature reads 80"F.

C. Advance throttle to 3050 rpm.

D. Check manifold pressure 16-18 inches.

E. Check fuel flow 50-65 Ibs/hr..

F. Move i gn i ti on swi tch to left position. Maximum 125 rpm dropallowable in 5 seconds and maximum of 1OO"F rise in EGT. Returnswitch to BOTH position and let rpm stabilize. Move switch to rightposition, maximum 125 rpm drop and maximum 100"F EGT rise allowable.Return switch to BOTH position.

NOTE

Engine should not run rough when operating on one magneto.

G. Check engine driven fuel pump by turning off boost pump and no changein engine operation. On aircraft equipped with a green fuel pressurelight observe green fuel pressure light out and red fuel pressurelight on. On aircraft equipped with only a red fuel pressure lightobserve red pressure light on.

iii. Gently close throttle to split tachometer needles to check properoperation of overrunning c lutch. When needles ~oin, return tooperating rpm.

VIII BEFORE TAKEOFF

Check following items for proper position or indication:A. Seatbelts and doors latched.

8. Fuel valve ON tin).C. An~meter

D. Main rotor gearbox temperature.FAA Approved: 1?/31/80Revised: 1/8/86

THE ENSTHOM COHPORATIONPAGE 4.9

F-28F REPORT NO 28-HC-018TWIN COVNTY AIRPORT PO BOX 277 MENOMINEE. MICHIGAN 49858

DATE: 11-17-80

E. Fuel quantity.F. Cylinder head temperature.G. Engine oil temperature.H. Engine oil pressure.I. Mixture control full rich.

J. Boost pump ON and green light ON.K. Anti-collision and other lights ON, as required.L. Clutch

.warning light press to test red light goes out whenreleased.

M. Throttle friction.

N. Release collective lock.

WARNING

Keep hand on collective and maintain down positionwhen lock is disengaged.

IX TAKEOFF TO MOVER

A. Cyclic in neutral position.B. Set engine rpm to 2300 rpm with collective full down.C. Slowly and smoothly increase collective pitch, until helicopter is

light on skids.

NOTE

On helicopters equipped with a low rotor rpm system,as the collective pitch lever is increased fromthe full down position, the low rotor rpm warninghorn will sound until rotor reaches 334 rpm.

D. Adjust throttle as required to maintain rpm in the green are beforeraising collective to lift helicopter off the ground.

NOTE

This helicopter is equipped with a mechanicalthrottle correlation device. The correlatorwill compensate for changes in collective pitchwhen manifold pressure is above 25 in. Hg and willmaintain rpm within the normal operating rangefor normai hover maneuvering.

NOTE

Hovering IGE above 10,000 ft density altitudeis limited to five minutes.

CAUTION~I Avoid maneuvers which require full pedal travel~I or rapid pedal reversals.

~I FAU Approved: :2/31/80

THE ENSTHOM HELI(:O)Y~EH COHI~OHATION PAGE 410

F-28F REPORTNO. 28-AC-018TWIN COUNTY AIRPORT PO BOX 277. MENOMINEE. MICHIGAN 49858DATE: 11/17/80

X NORMAL TAKEOFF

A. Align helicopter with desired takeoff course at astabilized hoverheight of approximately 2 feet.

B. Check power required to hover.

C. Smoothly apply forward cyclic to begin acceleration into effectivetranslational lift.

D. As the helicopter begins forward movement, maintain altitude byincreasing collective pitch.

NOTE

Adjust acceleration rate so approximately1-2 inches of manifold pressure over hover

power is required. Maintain 2 foot hoveraltitude or lower altitude if permitted bysafe obstacle or terrain clearance.

E; When effective translational lift has been attained, adjust throttleas necessary to maintain rpm within the normal operation range.Establish a rate of climb. See Height-Velocity Diagram, Figure 5.5,for recommended takeoff profile.

XI MAXIMUM PERFORMANCE TAKEOFF

A. Stabilize at hover of 2 feet aligned with desired takeoff course.Check hover power.

B. Smoothly apply forward cyclic to begin acceleration into effectivetranslational lift.

C. As the helicopter begins forward movement, increase collective pitchto maintain 2-5 feet skid height and 3050 rpm.

CAUTION

Do not exceed 39.0 inches of manifold pressure.

NOTE

Since the F-28F is equipped with a full-timeturbocharger, the turbocharged engine is equippedwith an overboost warning light on the instrumentpanel to warn the pilot of an overboost condition.Transient overboost conditions which may trigger thewarning light may not show as overboost conditions onthe manifold pressure gauge. The manifold pressuregauge red line is the determining factorin ascertairiingthe magnitude of an overboost condition. Subjectoverboost conditions must be logged in the engine logand inspections performed per Lycoming Bulletin 369F.

FAA Approved: 12/31/80Revised: 12/30/82

THI~ ENSTHOM HEI.ICOITEH COHPORA1.ION PAGE 4.11

F-28F REPORT NO. 28-AC-018TWIN COUNTY AIAPORT PO BOX 277 MENOMINEE. MICnlGAN 49858

DATE: 11-17-80

XI MAXIMUM PERFORMANCE TAKEOFF CONTD

D. After attaining translational lift adjust throttle as necessary tomaintain RPM at 3050 RPM. Continue level acceleration to 35 MPH,then apply aft cyclic to allow the helicopter to climb and accelerateto best rate of climb speed. Maintain constant airspeed. Climb atbest climb speed to clear barriers.

XII MAXIMUM PERFORMANCE TAKEOFF IN CONFINED AREA

A. Stabilize at 2 foot hover aligned with desired takeoff course.Check power required to hover.

B. Smoothly apply forward cyclic and increase collective to obtainmaximum manifold pressure (not to exceed red line) and 3050 rpmwhile accelerating to effective translational lift.

NOTE

If distance to barriers precludes level accelerationto translational lift, use a coordinated climb andacceleration.

C. When effective translational lift is reached, apply aft cyclic tomaintain best angle of climb speed (35 mph) to clear barriers.

XIII CRUISE

A. Maintain 3050 rpm and 29 in. manifold pressure, or less, in levelflight.

B. Set cyclic trim.

C. Lean fuel mixture to approximately 90 Ib/hr at 29 in. manifoldpressure.

D. Monitor EGT temperature.

NOTE

Allow a few minutes for temperature tostabilize. DO NOT exceed 16500F EGT.Make fine adjustments to attain desiredfuel flow and cross check cylinder head

~I temperature and oil temperature. If temp-ol eratures are too high, enrich mixture invll F~A Approved: 12/31/80 250F increments until temperatures remain~1 Revised: 1/4/82 in green are.

THE ENSTHOM HE:I.ICOIIEH COHPOHATIONPAGE 4.12

TWIN COUNTY AIRPORT PO BOX 277 MENOMINEE MICHIGAN 49858F28F REPORT NO 28-AC-018

DATE: 11-17-80

XIII CRUISE CONTD

E. Any increase in power setting above 29" should be accompanied bysetting the mixture to full rich.

CAUTION

Avoid maneuvers which require full pedaltravel or rapid pedal reversals.

XIV PRACTICE AUTOROTATIONS

A. Assure that helicopter is in a position to reach a suitable landingarea in autorotative glide.

B. Airspeed between 50 and 80 mph.

C. Lower collective to full down position and needle will split (i.e., DONOT adjust throttle). In the event a power recovery is desired, raisecollective to flight condition. RPM will return to original setting.

D. Monitor rotor tachometer and adjust collective as required to maintainrotor speed in green are.

E. If touchdown au torotat i on is des i red roll off throttle to idleposition for landing before raising collective.

CAUTIOPI

AVOID throttle chops to full idle ataltitudes 7,000 ft above base altitudewhere engine idle was adjusted. Engineidle speeds at altitude will be lessthan those set at base altitude con-ditions and engine stoppage is possible.

F. Level aircraft and cushion landing by raising collective. NOT E Ifpower recovery is desired, throttle must be added.

CAUTION

When making a power recovery avoidrapid throttle movements until therotor and engine tachometer needlesare joined to prevent damage to thefree wheeling clutch.

XV LANDING

A. Mixture control full rich.

~I B. Maintain rpm within normal operating range as collective is reduced.FAA Approved: 12/31/80

~I Revised: 12/14/88

TWE ENSTHOM HRI.ICOPIEH CORPORATIONPAGE 4.13

~5 F-28F REPORT NO. 28-AC-018TWIN COUNTY AIRPORT PO BOX 277. MENOMINEE. MICHIGAN 49858

DATE: 11-17-80

XV LANDING CONTD

C. Landing light ON, if required.

NOTE

The nose landing light is operated by a.switchon the cyclic and can be adjustedby the pilot in flight, The adjustmenthandle is on the cabin floor to he left

.of the cyclic. The bottom landing light(ifsd~equipped) is operated by a switchon the switch panel and is fixed for bestautorotative glide path.

D. Adjust collective and altitude to establish 80 to 100 gpproach angle.Adjust airspeed to 60 mph.

E. As the landing area is approached, reduce the airspeed and rate ofdescent until a zero ground speed hovering altitude of 2-5 feet isattained.

NOTE

Hovering LGE above 10,000 ft densityaltitude is limited to 5 minutes.

XVI RUNNING L~NDING

A. Use a shallow approach angle.

B. Maximum recommended ground contact speed on smooth surface is 35 mph.Reduce speed on rough surfaces.

CAUTION

Avoid rapid lowering of collective pitchafter ground contact, as rapid decelerationand nose down pitching may result.

XVII AFTER LANDING

A. Collective down and locked.

B. Landing lights OFF.

C. Radio(s) OFF.

D. Reduce throttle to 2000 rpm for one minute.

~g FAA Approved: 12/31/80Revised: 1/4/82

f THE ENSldOM H~I,I(:OIIEH COHPOHATION PAGE 4.14TWIN COUNTY AIRPOAT PO BOX 277 MENOMINEE M CHIGAN 49858

F28F REPORT NO 28-AC-018oATE: 11-17-80

XVII AFTER LANDING CONTD

E. Throttle to idle (1500 rpm).F. Clutch disengaged.

CAUTION

Clutch disengagement with throttleopen will result in engine overspeed.Clutch disengagement is signaled by ared warning light on the instrumentconsole.

G. Idle engine at 1600 rpm for 2 minutes, or until cylinder head tempera-ture cools to 300"F.

H. Boost pump OFF.

I. Mixture control to idle cutoff position.

J. Ignition switch OFF.

K. Master and all other switches OFF.

L. Fuel valve OFF tout).XVII GENERAL OPERATING PROCEDURES

Throughout the flight envelope, avoid maneuvers which require full tailrotor pedal input or rapid tail rotor reversals. Although this type of

~pedal input may be necessary in some normal operations such as hoveringdownwind or hovering in~gusty conditions, the pilot should avoid excessivepedal movement except as necessary for normal flight operations.

FAA Approved: 12/31/80Revised: 12/24/88

THE ENSTH;M COHPOHAIION PAGE 5.0~ilS F-28F REPORT NO. 28-AC-018

TWIN COUNTY AIRPORI PO BOX 277. MENOMINEE. MICHIGAN 49858

DATE: 11/17/80

SECTION 5

PERFORMANCE

Issued: 1/4/82

T1tE ENSTHOM CORPOHATION PAGE 5.1~5 F-28F REPORT NO 28-AC-018

TWIN COUNTY *IRPORT PO BOX 277 MENOMINEE MICHIGAN 49858

DATE 11/17/80

2600 /---3t/D The solid VNE/altitude curve shownbelow applies bnlyto operation with5 C

g 2400 thkc.g. within the shaded area sl-~own:B aL:left (Envelope A).: For operat.ion2200 \I with ehe -c.g... in otherareas, see the

apprqpr,iate VI\IE envelope"w 2000.~s EXASPCE::": Helicopter c,g. ,is 96.0inches

lt300I I II at 2000 Ibs, i;ANE

:H!licapter c.g. :is 96.5 ii :Bi~ 2300lbs, uSe Eiiv~l ope i B VNE.Y////////////~/////////

_._. 1.. :j-----:;::_:-~:-i I Fi 5.9B:i....l .I..-il da 9:6 ]._ 190 .:1

..i i_--

i:..__.._. I.-_j CH"ES. 4FI:IO:E.. ..9DA7Uj~T. USe Figu~7e-l6.-1: to.determine:_-

i_ :j I: I actuallloca~ :i on jol cjg.:i MAXII\1UM CEILING I

:-i_ I\iOTE: i This helicopter Imust meet: theL.J. _i..relu~irements of-iEnstrom

.:_._:... .:i.l---:. i SpecifSecat~ibn Ci~at ""nls:-~ngi---i 1:::I

1OOo:il-a i :::i I i :I i

_

I:.;_._~. i._lil.._l~_ _.i_.l_..C__ 1__1._-1-1:_j .---.:-_:.l.i-

I 1 j

;pooll ._:I I I ;II --1-~ELt]-:~ \j

i I: i

iT:iI..._

I_._.~.i.__:_:.._-i- :---i---:i:: t--

i _.I_,____L -...i.... I-I i ._--F~

.j.:I. i i 1 I. i~ 1 I I_i:;_ i _ _i

Oooi L.....11.-l .~....--j.:_ I\ j il_:. i_-_.i.. I

~1 i

i I_:. ..1.1. i.. I I~ _ .I... i...2, i)OO II~ I

I~ ISea Level

0 1 20 40 60 80 100 1 120

INDICATEU AIRSPEED MPH

FIGUnE 5.1A

V~dEVariation with Density Altitude for Envelope A

ORIGINALEAA Approved: lll,iU4 as Received By

ATP

h TIIE ENSTHO.n HEI.ICOYTtSK CORPOHATION PAGE 5.2F-28F REPORTNO 28-AC-018

TW1N COVNTY AIRPORT PO BOX 217 MENOMIEIEE MICHIGAN ~9858

DATE 11/17/80

2600v, 1 The solid VNE/altitude curve showna

240OC below appl~es onlj/to operation with

a the c.g. within the shaded area shownat left(Envelope B). Foroperation

2200 with the c.g. in other areas, see theL J appropriate V~E envelope.W 20O0 1

1 I E Xn~4P L E Helicopter c.y. is35.0 inchesv, at 2400 Ibs, use Envelope B VNE1800 I

I I: i i I I-le:licopter c.g. is 98.i) inches.isoo at: 2400 Ibs, use EnvelI!.ope cv i\lE

:..i...l:::j~ --9~4:J6:i9b 100:1 (Figure 5.1C)1

.G.::- -II\IC~IES AFT OF DATUM i- Use Figure 6;-1 Lo de~en.ninei

j.location of c.lg.

~12:,000 NOTE: Th~is helicopter must.meet therequirements of:EnstromSpec~ fi cat~ oniDrai;J7ng #281 100015

:i i I :i:-.._i. _:...:~_!_._._I.: Sde-Limitations jSection.

000 :L_.:_I^_LLI~.1ti:l::i: j

..1 t ji I I

II ;4 Co

w ;o

~i/c!u I i i io

I-~3: I:I~:r-._._, _.~__._._: _..__

.1. .It;: i----;--::-I i

ii

I 12,000 \I o~I

Sea Level0 20 40 60 80 100 120

INDICATED AIRSPEED MPH

FIGURE 5.1Bm Vh!E Variation with Densit.y Altitude for Envelope B

FAA Approved: 7/1/84 ORIGINALAs Received By

ATP

PAGE 5.3CORPORATION

F-28F REPoRTNo 28-AC-018TWIN COUNTY AIRPORT PO BOX 277 MENOMINEE. MICHIGAN 49858

DATE 11/17/80

e6oaT; D The solid VNE/altitude curve shownbelow applies- only. ~to operation with I

g 24001----

-ithe c.g.iwithin the shaded area shownB at left (Enve~opeC). For operation

2200 with the.:c.g. in.other.-areas, sec.the ..._.I appropriate VNE envelope.2000 i. EXF\~IPLE: Welicopter c.g~.is 93,6 inche

.F~ i"800I at 2300 ii: bs~L!use Enve 1Ol)elL VNEi-be C V;i 1 1.1 I

,.,i,,,., 93.0 in~hesri 1 i i :dt 2350 :~bs :useSe...~nve ~\EnveoDe A VNE1~

:9 ::94 100 i_-. gure :15..~A). i :II I II d,G. INC~IES AFT;OF D~TUM i:: i NPTE: :1I--i: Use. Fi gurei ti.l to I determi n~

:1-_II 1-,actua!, location of c.g. i

I

NOP E iis iiiust riieet ttie.._i--::i.~.:-- I i-

requirementsi;of EnstrdmSpeci-f-icatior Ordwi ng-l-----:I-:-:..i~_..-- ..L..li.~..:: i#28-100015. i-See I imi.ta+~, nnc

..i:j- i- ":1YIJ i-ij:~,.-i-r..-:s"~""""/

-----i--ii--~ i-:i----__il~oii o.i 1II I

~n i- -:-..:-1-- I--r

I i ?ol\ i

-l-.i----:-- i I---- -..--.-:i---.--- i -1... :---._-.:_I i i i iiii

I- i._..:ll.__.i..:.1-i..._..:~_.._ c._li__._l_. I ___1..~. ~.L_.:. ~1 .:i~.. Ij i1

.1 __._~

I..:..;..L.. i I 111.__.1..-j ___1_1I_!_

I:i:::II i j:: :Ii...-:i.:

-.-__!. _.-......_:, _..n .i-..

__i--..i_!1.i :::1-i:_-:._ ..1:_I I

~I-4-; 00

I II: I

Sea

Level2,0I0 20 40 60 130 100 120

INDICA~iEU AIRSPEED ~PH

FIeURE 5.10

VNE Variation with Density Altitude for Envelooe C

ORIGINALFAA Approved. 7/1/84 As Received By

ATP

Q ENS.THOM HE1.ICO~TEH COHPOHATION PaGE 5.4F-28F REPORTNO 28-AC-018

TWIN COUNTY AIRPORT PO BOX 27i MENOMINEE MICHIGAN 49858onTE 11/17/80

2600:The solid VNE/altitude curve shown

z

-i-belowapplies onlyto operation ~ith

a f-- Lhec.~g. withintheshaded area shown-::at le-6t (Envelope D). For operationi 2id0-I iwith:the c.g.in other areas, see the

3 aappropriate VNE envelope.w 2000 1 Helicopter c.g. is 97.0 inches~E EXAMPLE:

~j-1800 jat 2560 Ibs, use Envelope O VNE-I i: ~Clelicopter c.g. Is 96.0 inches

i i at 2550 lb;s, use Envelope C: VNE9.2 94 1 96 ;-9 :160- :I:i (Fi gur:e5;1C )I

I

:--;----j:--l:---C; G;i--IWHCSAFT DFI Figure:6.1 to :determineactual location:of c.g)

1: :12 i0 00 I\IOTE: i :I This helicopter must meet theI I i:~: Irequirements~oT Enstrom

ification Drawing I#28-100015. ISee ~imitations

~--l0,ooo-----l-1-r--l--:--- i--il-./

I j I;Z;

~it; i i~__i

i MAXIMUPI CEILIH(; j :_(~,\: i\;~o, Th~w: 8,000 i...-~ 8-li

I$ \ILil ji-\

w

-i I: i,

4:

000 i I i.._ -j j..-_~___il----- i\v, i i iZYQ

i2,000 zo I

Sea Level0 20 40 60 80 100 120

INDICATED AIRSPEED MPH

FIGURE 5.10

VNE Variation with Density Altitude for Envelope D

FAA Approved: 7/l/t~4 ORIGINALAs Received By

ATP

i THE ENSTHO;M HI~LICOPTEH COHIOHATION PAGE 5.5F-28F REPORT NO 28-AC-018

TWIN COUNTY AIAPORT PO BOX 217. MENOMINEE. MICHIGAN 49858

GATE: 11-17-80

AIRSPEED CALIBRATION

120

ioo

i80

ow

wa

~2 so

ow

40aao

j0 20

0 20 40 60 80 100

INDICATED AIR SPEED -M.P. H.

NOTE: INDICATED SPEEDS BELOW 20 M.P.H. ARE NOT

FIG. 5.2

cn 12/31/80FAA Approved:Revised: 7/1/84

ENSTROM H(ECICOPTES CORPORATIONPAGE NO. 56

F-28F REPORT NO. 28-AC-01~MCNOMINeE COUNTI *IRPORT P O. BOX P77. HLNOH1NEC. HICHIO*N 408B8

DATE 11/17/80

ENSTROM F-2t3F

MOVER CEILING IN-GROUND EFFECT

2 FT SKID HEIGHT

350 ROTOR RPM

14,000MAXIMUMGROSS WEIGHT

STANDARD

!o, DAY10,000

eOo

fi

6,000

2,000

SL2200 2400 2600 2800

GROSS WEIGHT ru LBS

FIGURE 5.3

FAA Approved: 12/31/80Revised: 7/1/84

REVISED

R1E ENSTROM HELICOPTER CORPOKATION PAGE NO. 5.7F-28F REPORT NO. 2il-AC-018HENOHINCE ~OUHTI*IRPORT P O. BOX 277. HLNOHINCL. HICHIOAN 48858

DATE 11/17/80

ENSTROM F-28F

MOVER CEILING OUT-OF-GROUND EFFECT

40 FT SKID HEIGHT

3050 ROTOR RPM

14,000

MAXIMUMGROSS WEIGHT

STANDARDDAY

10,000

600w

w d~ \x\LL I I\ I \VO

w

3

6,000w

v,

v,

LLIo~

a

2,000

SL2000 2200 2400 2t00

GROSS WEIGHTS (Ibs)

FIGURE 5.4

FAA Approved: 12/31/80Revised: 7/1/84

~GE 5.8F-28F ~E:3Ri vo 28-AC-018

CLTE 11/17/80

HEIGHT VELOCITY DIAGRAM2358 LBS GROSS WEIGHTORIGINAL

As Received ByATP

(TESTS CONDUCIED ON PREPARED SURFACES)700

B

60

PoI~h

LL 500

bP

iOo%400 c O RECOMMENDED

10 TAKEOFF PROFILEW s Po

m

r

t. 30I(3wI

200

10

O 20 40 60 80INDICAVED AIRSPEED-M.P.H.

FIG. 5.5

FAA Approved: 1/4/8?Revised: 7/1/84

THE ENSTROM HELICOYTEH CORPORATIONPAGE 5.9

~IS F-28F REPORTNO 28-AC-018TWIN COUNTY AIRPORT PO BOX 277. MENOMINEE. MICHIGAN 49858

DATE: 11/17/80

EFFECT OF LOADING ONCHOICE OF H-V ENVELOPE

The H-V curves presented in Figure 5.5 are valid for operations at 2350 Ib grossweight for the specific density altitude conditions presented. For operation atother than 2350 Ib gross weight, determine the proper H-V curve to be ,used forthe intended gross weight and density altitude for the flight from the curvespresented in Figure 5.6 below. For operations above 2500 Ib gross weight, usethe H-V curves presented in Figure 5.7 in place of Figures 5.6 and 5.5.Example: (1) A gross weight of 2000 Ibs and 3900 ft Hd would allow the use of

the sea level envelope.(2) A gross weight of 2200 Ibs and 4500 ft Hd would require a 2800 ft

curve. to be conservative, use the next higher curve, 4000 ft,12,000

10,0006:o,

\irl8,000 tz~

JO o ow O noO ma3

6,000

Ix

Ln 2c

a 4,000

r

2,000

1600 1800 2000 2200 2450 2600

2350GROSS WEIGHT (Ibs)

~I FIGURE 5.6

FAA Approved: 12/31/80Revised: 7/1/84

THF: ENSTIIOM HELICOPTEI~ CORI~OHATION PAGE 5.10F-28F AEPORI NO. 28-AC-018

TWIN COUNTY AIRPORT PO 80Y 177. MENCUINEE. MICHIGAN IggS8

DATE 11/17/80

HEIGHT VELOCITY DIAGRAM

2600 LBS GROSS WEIGHT ORIGINALAs Received By

ATP

700lII i AVOID OPERATION IN THIS AREA

600

SAFE OPERATINGI AREA500

LLs

400

o

~o 300I/ /1 A Pi TaKeoi! Froii!e

;_ T///y/p, na u i

Vss C;?L!C?7 ?~e;avoic: i3

!Fvare v:i:n Scu:?d100

/Yi/A ,1i:l

O 20 40 ~O 80 E5 100

Indicated Ai:szed MPII

FIGURE 5.7

NOTE: Altitude operations may also be limited by VNE and OGE hover. Crosscheck Figures 5.1 and 5.4 for intended operations when using this figure.

~1 FAA Approved: 7/1/84

THE ENSTHOM WEI.ICOI~TEW CORPOHATIONPAGE 5.11

F-28F REPORTNO 28-AC-018TWIN COUNTY AIRPORT PO BOX 277 MENOMINEE. MICHIGAN 99858

DATE: 11-17-80

DENSITY ALTITUDE CHART

SET ALTIMETER TO 29.921N. HG.WHEN READING PRESSURE ALTITUDE

15,000oO~

14,000) /~jOO;

13,000221 1~

L\2 P

11,000

w P9000 ~D

",iidP~w Y I Vbo 8000 d

oOoT-f+-t-~SP 2

u,7000Z 6000

5000

O0~

4000

3000

2000b~

r

1000

S.Li ;I--20 -10 0 10"C 20 30 40 50

4t-rtrtr+?TtsrttJ-ll"-jl0 tb 20 30 40 50 60 70 80 90 100110120

"F

OUTSIDE AIR TEMPERATURE

(ijl FIGURE 5.8FAA Approved: 12/31/80Revised: 7/1/84

f~ THE gh.iil.H~,u HI-I.II:III.IYH 01HIlOK*11011 ract 5.12F-28F REPORTNO 28-AC-018

TWIN COVNTY AIRPORT PO BOX 27) MENOMINEE MICWIGAN 49858DATE: 11-17-80

RATE OF CLIMBIDENSITY ALTITUDE2350 LBS. GROSS WEIGHT

Best rate of climb speed varies with altitude:

57 MPH at sea level decreasing to48 MPH IAS at 12,000 feet Hd

12000

10000

w

wu_

8000

w

sooo

_I

4000rr,

Zw

D

2000

400 600 800 1000 1200 1400

RATE OF CLIMB. FT. PER MIN.

FIGURE 5.9

FAA Approved: 1/4/82~I Revised: 7/1/84

.I-ltE ENSTnnn HEI.ICOITI.I( CO*PDRlll.lnn ~aoE6.0

F-28F REPORTNO 28-AC-018TWIN COVNTY AIRPORT PO BOX 277. MENOMINEE. MICHIGAN 49858

DATE: 11-17-80

SECTION 6

WEIGHT AND BALANCE

~I Lssued: 1/4/82

THE: ENSTHOM HEI,ICOPTER COKI~ORATIONPAGE 6.1

~1 F-28F REPOATNO. 28-AC-O18TWIN COUNTY AIRPORT PO BOX 277. MENOMINEE. MICHIGAN 49858

DATE: 11/17/80

SECTION 6 WEIGHT AND BALANCE

I. GENERAL

This helicopter must be flown within the weight and center of gravitylimits stated in Section 2, Operating Limitations. This helicopter mustmeet the requirements of Enstrom Specification Drawing #28-100015 (seeLi mi tati on Secti on) The helicopter empty weight, empty weight c.g.,total basic weight and basic weight c.g. are found on Form F-168A.Removal or.installation of approved optional equipment will change thehelicopter weight and c.g. These changes shall be recorded on FormF-165A, and a running basic total weight, arm, and moment will bemaintained. The pilotwill use this running basic total when performingcalculations to insure the helicopter is loaded properly.

II. APPROVED CENTER OF GRAVITY ENVELOPES

A. Longitudinal C.G.1. Station zero located 100.0 inches forward of centerline of main

rotor hub.

2. Longitudinal c.g. range variable with gross wei ght from92.0 inches to 100.0 inches (see chart, Figure 6.1).

I LONGITUDINAL CG ENVELOPES2600

2 30 O t WEL1DPE-"C

2400 ELOPEi-8

2300

72200

ENVr 2100

2000

1900

1800

1700

isoo96 97 98 99 16092 93 94 95

ojl LONGITUDINAL CG (INCHES AFT OF DATUM)~I FIGLj?E 6.:-I Issued: 12/31/80~I Revised: 7/1/84

THE ENSTHOM HELICOPTER CORPORATIONPAGE 6.2

~tS F-28F REPORTNO. 28-AC-018TWIN COUNTY AIRPORT PO BOX 277. MENOMINEE. M1CHIGAN 49858

DATE: 11/17/80

B. Lateral Offset Moment

i. Centerline of helicopter is O inch lateral moment arm. Lookingforward, moment arms left of centerline are negative.

2. Lateral c.g. locations:

a. Two people on board:(1) Left seat (pilot) -13.5(2) Right seat (co-pilot) t13.5

b. Three people on board:(1) Left seat (pilot) -13.5(2) Center passenger 3.0(3) Right passenger +20.5

3. Approved lateral offset moments vary with gross weight from-3250 in-lb to +3700 in-lb (see chart, Figure 6.2). Lateraloffset is the same for all VNE envelopes.

LATERAL OFFSET MOMENT ENVELOPE

260~3 iT -r-rT-r- -I-1~jj2400

C32L300

0 2000I i i j

1 I j j i/!8110

I

!600-40i30 -2Ci-,C; C) r,:;Cc)LEFT RIGHT

IATERAL OFFSET MOMENT (IN-LSS)

~I Figure 6.2

Issued: 12/31/80~I Revised: 7/1/84

T)IE ENSIHOM CORPOHATION PAGE 6.3F-28F

nEPORTNO 28-AC-018TWIN COUNTY AIRPORT PO BOX 277.MENOMINEE. MICHIGAN 49858DATE: 11-17-80

III. WEIGHING THE F-28F HELICOPTER

A. Tools and Equipment

i. Tape measure2. Two scales 1000 Ib. capacity3. Scale 100 Ib. capacity4. Bubble level5. Work stand

B. Procedure

i. Clean helicopter remove rags, charts, etc.2. Drain fuel, check all other operating fluids full.3. Move helicopter inside closed building.4. Check for proper installation of accessory items.5. Close and secure both doors.6. Align one main rotor blade over tail cone.7. Hoist or jack helicopter to a height to clear scales.8. Position a pipe nipplein the center of left and

right 1000 Ib. capacity scales. Place scales underlanding skids so nipples will contact skid gear ata point 17.7 inches aft of forward 3 inch diameter

r I cross tube (Sta. 93.4).

NOTE

See Pig. 6.3 for locating fulcrumby using T-la94. This tool may bepurchased from Enstrom CustomerService Department.

9. Locate the 100 Ib. capacity scale at the center line ofthe tail rotor output shaft. (See Fig. 6.4)

10. Adjust height of tail to level helicopter. Level checkedat left lower pylon tube. Lateral level checked at lowerforward pylon tube.

11. When helicopter is level read the scales and enter weightson Weight Chart, Pig. 6;.7

CAUTION

Weight and measurement readings arecritical. Double check results.

12. Remove helicopter from scales.

NOTE

DO NOT remove curbing, nipples, blocks,etc. from scales. Weigh these items and

01 enter weights in tare column on Fig. 6.7

~I Issued: 12/31/80

THI~ ENSTHOM HEI.ICOI~IEH COHPOHATION PAGE 6.4

F-2&F REPORT NO 28-AC-018TWIN COVNTY AIAPORT PO BOX 277. MENOMINEE MICHIGAN 49858DATE: 11/17/80

WEIGHT AND BALANCE

TOOL POSITIONING

17.7"

T-1794 TOOL

3FULCRUM

FIGURE 6.3

"s Issued: 12/31/80

REVISIONS:

8m

E

100.0

G_ROTORHuB___ I

P j,

LCG SW1 EL TANK119.7Sa

O 02.0 93:446 IjS.O 320.0CABIN FWD. BAGGAGE AFfSEATS WEIGHING BOX WEIGHING

STATION STATION

WL WR WT h,m

o ~o

o\

FIG. 6.4

Issued: 12/31/80 I03

REVISIONS:

H

v,

v,

r 8 c3n,n IE3

m

a z

0" 9I~g

303o,

o m

q190.0 I K

aGROTOR HUB

O

_-rh_~_

r ~s

96.0 FUELTANK I

LCG119.75

i jl!i~ ii i i...i

-rl

r~

03-n

0 62.0 93.446 135.0 320.0 bDCABIN FWD. BAGGAGE AFI B 4;1SEATS WEIGHING BOX WEIGHINGSTATION STATION I zW, WR WT I o

r03Cn

FIG. 6.4 1 t;~ecooOr

CD

THE ENSTHOM HEI,ICOIYI~E:H COKPOHA1ION PAGE 6.6

TWIN COUNTY AIRPORT PO BOX 277. MENOMINEE. MICHIGAN 49858 F-28F REPoRT NO 28-AC-018DATE: 11-17-80

III WEIGHING THE F-28F HELICOPTER CONTD

13. Subtract tare from scale readings and enter net weights.14. Enter arms and multiply by weights to get moments.15. Total weights and moments.16. Using formula on bottom of Fig. 6.7, calculate C.G.17. Transfer weight, C.G. or arm and moment to top of form

F-168A.18. On Form F-168A enter all optional and surplus equipment in

the helicopter at weigh-in. Then enter allstandard equip-ment not installed on the helicopter at weigh-in.

19. Total weights and moments.20. Find total empty weight and moment of standard helicopter.21. Add to this figure optional equipment to obtain

total basic weight and moment.22. Transfer these figures to Form F-165A, Basic Weight and

Balance Record.

NOTE

Any changes to the helicopter such asstructural repairs, or modifications,installation of optional equipment orremoval of optional equipment, will re-quire an entry on Form F-165A.

~I Issued: 12/31/80 Revised: 12/30/82

THF: ENSTHOM HE:I.ICOPIE:H CORPORATION PAGE 6.7

F-28F REPORT NO 28-AC-018TWIN COUNTY AIRPORT PO BOX 277. MENOMINEE. MICHIGAN 49858DATE: 11/17/80

III LON)ING INFORMATION

A. It is the responsibility of the helicopter pilot to insure thatthe helicopter is loaded properly. Using the basic weight andmoment from Form F-165A (Fig. 6,8) and the Loading Chart, (Fig 6.5)the pilot can obtain the total weight and moment for various load-ing conditions. The pilot should first calculate the total weightand moment for zero usable fiiel as this will show the.C.G. shiftwith fuel burn-off. If the C.G. is within limits, add the plannedfuel