Cessna USAF Series, T-41C 1990, T-41D 1991, T-41C 1991, T-41D 1990 Flight Manual

T.O.

1T-41C-1

FLIGHT

USAF

T-41

CID

MANUAL

SERIES

AIRCRAFT

AND

BASIC

DISTRIBUTION

OoO

US.

requests

Other
WARNING

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1SiZg,

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are

laws

HANDUNG
statement
reconslruction

COMMANDERS

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CHANGES

ALL

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shall

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amended

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ANDjE_STRUqTION

destroy

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TO

PUBLISHED

91

/

HAVE

only,

ref erred

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document

(Title 22,

Act

(Title

severe

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document.

ARE

THE ATTENTION

UNDER

865

F34601-90-D-031

MERGED

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MAKE

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FOR

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et seo.)or

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disclosure

THIS PUBLICATION

PERSONNEL.

OF THE

AIR

PUBLICATION'

of Delense

Seplember

ol lhese exporl

wilh lhe distribulion

and

199o.

by lhe

ol the contenls or

FORCE

SEPTEMBER

1

15 APRIL

1990

1991

TO" 1T-41C-1

LIST

,

EFFECTIVE

OF

-

Dates

ol issue

Original

Change

TOTAL NUMBER

Page

No.

for original and

...0 ..15 Sep90

...1 ...15Apr91

.

PAGES

OF

*Change

PAGES

-

IN THIS PUBLICATION IS

No.

INSERT

INOTE: Theportionofthetextaffectedbythechangesisindicatedby

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No.

LATEST CHANGED PAGES.

a vertical line in

illustrations

Changes to wiring

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CONSISTING

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OF

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FOLLOWING:

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to

hands.

areas.

No.

A

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in

'Zero

1

this

column

indicates

an original

page.

T"O.

1T-41C-1

Tech

Co

nf ig

n ical

ratio n

u

Orde r

Status Record

lEq

ipment

u

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Blank)

T.O.

I

1T-41C-1

Flight

and

This page
Manual
Manuals,

you

Ollicer

Manual,

Operational

published

is

Change

Flight Crew

are missing

and

or revision.

any

get

your

Checklist,

publications

copy. Changes in

FLIGHTMANUAL

T.O.

1T-41C-1

FLIGHT

T.O.

CREW

CHECKLIST

1T-41C-1CL-1

Saf ety

Supplement,

Supplement

with

each Safety and Operational

provides

lt

Salety Supplements,

listed

-

a comprehensive

on this

preparation

T

page,

are

Status

Supplement,

listing

and Operalional

your

see

shown

DATE

1Aug90

DATE

1 Aug

ol the

Publications

parentheses

in

I

90

and

each Flight

current Flight

Supplements.

Distribution

(

).

lf

TCHANGET

-

1

15Apr91

CHANGET

-

1

15 Apr

91

Change t i

T.O. 1T-41C-1

Flight Manual,

Saf ety

and Operational

CUNREruT

Number

SUPPLEMENIS

Date Short Title

Supplement,

Supplement

Status

Flight

Pages

Manual

Affected

REP

Number Date Disposition

LAC

E D/RESCIN

D

ED S U

P

LEM

P

E/VIS

-

ii

T.O.

1T-41C-1

SECTION

I

ll

lll

IV

V

VI

vil

TABLE

OF

Description

Normal

Procgdures

Emergency

Crew

Opgrating

Flight

All

Duties

Limitations

Characteristics

Wgathgr

CONTENTS

TITLE

and

Procedures

(Not

Operation

Operation

! .'

.,

Applieable)

...,,,..

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r r . r

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'3-'l

GLOSSARY

APPENDIX-

Alphabgtical

r r.

r

rr

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Performancg

r.,

i.

INDEX

,

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r.

Data

r,.

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ill

T.O"

1T-41

C-1

Figure

1-1

1-2

1-3

1-4

1-5
1-6
1-7

1-B

1-9

1-'t0

1-11

2-1

z-z
2-3

3-1

3-2

5-1
co

J'L

5-3

5-4

5-5
5-6

5-7

6-1

6-2

A1-1

A1-2

A1-3

A1-4
A1-5
A1-6

A1-7

A1-8

41-9

A1-10

A1-1

A1-12

A1-13

A1-14

A1-15

A1-16

A1-17

A1-18

LIST OF

LLUSTRAT

Title

I

The T-41 C

Prinicpal

Lelt Lower

Right
Cockpit
Oil System

Syslem Schemalic

Fuel

FuelQuanlity

Electrical Syslem

VHF Radio
VOR Receiver . .
Transponder

Exterior

Wind Direction
Maximum Glide .

Typical Forced

Airspeed

Aircraft

Dimensions

Switch

Lower Switch

Forward

lnspection

Limitations Gauge

View .

Schematic

Dala

Schematic

. .

Landing

Panel

Panel

(U.S.

Gallons) . . .

Pattern

ONS

Page

ix

1-2

1-3

1_3

1-4

1-8

"l

-o

1-1

1-12

1-18

1-18

-19

1

1-J

2-7

2-11Tralfic Patlern

3-4

3-7

5-1

1

OilTemperaturecauge... 5-2

Pressure Gauge

Oil

Tachomeler

Flow lndicator

Fuel

Fuel Quantitylndicator....

Suction
Stalling
Stalling
Airspeed
Airspeed Correction
T-41C
Weight and
Center

Loading Graph

Takeof

Airspeed correction

I and

Take-Olf

Maximum Rate-of-Climb

....

Gauge

Speeds
Speeds

Conversion

of

Gravity

(2200
(2500

Balance Chart

Moment

Landing Crosswind

Data

Pounds Gross
Pounds

Gross

Chart

Table

Chart

Envelope

Data

Weight
Weight)

Chart

OplimumCruisePerformance....

'1

Cruise
Landing

Take-Off

Maximum

Cruise

Cruise
Cruise
Cruise

Range

&

Distance

Dala,

Performance
Perlormance
Performance
Perlormance

Perlormance

Data .

T-41D Model

Rate-ol-Climb

(2500
(5000
(7500

(10,000 feet) .

Data

T-41D Model

Data,

feet)

f eet)

leet)

5-2

5-2

5-3

5-3
5-3

6-1
6-1

A-2
A-3
A-3

A-4
A-5
A-5

4-6

A-7

A-7

A-7
A-B
A-B

A-9
A-9
A-10

A-11

A-12

A-13

iv

T.O.

1T-41C-I

l

Cod

ing

and Se

lndicales

AIRQRAFT

information

CODTNG

rializatio

that applies

"D"

MODEL

to

"D"

n

modified

airplanes,

69-7755
69-7756

i

All

other

airplanris are standard

l
l

1

1

I

"C"

models,

I
t

I

I

I

t,

i

1

I

I

I
,

I

I

t'

I

I

I

I

i

I

T.O, 1T-41C-1

IMPORTANT!

FLIGHT

Looseleal
use

purchase procedures

Schedule

with

items. Due
ers be used

MANUAL

with

your

binders

your

(FSC

supply

to the size of

BINDERS.
and sectionalized

manual. They

and are

Group 75, Ollice

personnellor

section I it is

al the beginning

are obtained

listed in the Federal

assistance in

ol each system

Read these

scoPE.

manual

The inlormation
plane,

its characteristics,

dures. Your

avoided. This

circumslances,
sound

circumslances

tabs are

Supplies,

suggesied thal

judgemenl.

adverse w€ather,

procedure(s)

available

through

Part 1).

procuring

description.

in lhe

experience

llying

manual

but ars a

lerrain,

may require

presenled

lor

local

Supply

Check

these

divid-

provide-s

Multiple

pages

provides

specific normal

and

is recognized;

lhe

poor

subslitule

emergencies,

or extenuating

modilication

this manual.

in

carefully

you

possible operating instruclion

best

lor

of the

general

a

with

emergency operaling

and

lherelore,

basic flight

3

I

./j

knowledge of lhe

procs-

principles

under mosl

/.\

air-

are

PERMISSIBLE OPERATIONS.

takes

only what

which

prohibited,

by HQ USAF

constantly

T.O. 0-1-1-3

stales

must

or

Manual

are

remain

supplement

checklists

The Flight

mally
conliguralions

lhis manual

unless authorized

HOW TO BE ASSURED

You

ol

supplements.
manual
manuals,

"positive approach"

a

you

can do.

excesd the

except

OF HAVING LATEST

aware

stalus

and supplements.

Usually operalions

limitations

actual emergencies,

in

ACADEMY/CWO.

of the latest manual,

(supplemenled

provide

page

and

as

specif

DATA.

monthly)

a listing

nor-

or

ied in

. .

checklists

and lhe

ol lhe

lalest

current

ARRANGEMENT.

This

simplily
manual.
subsections,
systems.
struclions
characlerislics

lions ll,

dures

tion Vlll.

and stalus

llight
llight

manual

reading

For

You

in section

and

lll,

in seclions

divided into

is

straight

it

convenience,

describing

be lamiliar

must

the limitations

l,

in section

lV. ln adverse

ll and lll

t)

(.,r[

t-J

'

Yr,

seven interdependent

through or using
section I has

syslems

maior

with the systsm operating

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weather conditions, the

shall be

\f4

re:

been divided into 20

or

in

section

the

modilied

sections to

it as a relersnce

groups

ol relaled

V and the llight

procedures

proce-

as

shown in sec-

sec-

in-

vi

CHECKLISTS.

T.O. 1T41C-1

The Flighl
been issued as s€parate

current applicable checklists.

lor

are arranged

Manualcontains

in

same

lhe

lhe

amplilied

technical

order.

lf aulhorized

orders.

Line

Supplement that aflects a checklist,
lected
page,

old

the

checklist

lile the

page (in

page.

page

case lhe

HOW

Each llight crew

Manual,

Checklists.

need lhem to

Manuals

Basically,

lion Requirements

and

00-5-2

publications.

these

SAFETY
Safety supplements

about hazardous

conlain
salely

of

lransmitting

issued by leletype (interim)

supplements

a new

supplemenls
around

printed

ll a

in f;ont

supplement

ol the exisling

supplement

TO GET PEBSONAL

member

Salety

personnel -

publicalions

AND OPEBATIONAL

operating

modilications.

Supplemenls,

The required quantilies

assure

you

give

Make sure

their

it is their

must order

Table

detailed

lo the

are a

condilions

inslructions,

Operational

inlormation

are eilher

number) or by a quick

are

identilied

the borders

of the

checklists.

see the

items in lhe

write

checklist page,

is

cancelled).

COPIES.

is entitled

prompt

job

the required

(T.O.

inlormation

asystem

llight crews

rapid

or saf ety

not

or as

replaced

by red

pages.

Abbreviated

latest supplemenl

Flight Manual

by

an

interim

in the applicable

contains

lo

Salety or

a replacemenl

personalcopies

Operational

to

should

receipl.

tulf ill

your

be

Check

Technical

quantities

0-1-1-3).

is established

TechnicalOrders

properly

lor

at

immediately

SUPPLEMENTS.

means ol

lransmitting

problems.

or restrictions

supplements

involving

printed

by

change

letters "SS"or

{formal)

a lormal

salety.

printed

to lhe

checklists

slalus

and

checklists

operational

change on

checklisl

but do

not lhrow

of

th€

Supplements,

ordered

with

Order

on

belore

your

the

requests.

publica-

ordering

your

base

to deliver

upon

receipt.

inlormation

These

supplements

that affect

are

safely

a rapid

Supplements

supplements.

supplement (wilh

manual.

by

black

letters',OS"

have

page

the af-

out

Flight

and
you

Flight

O0-5-1

these

or

m€ans

are

lnterim

Formal

All supplements

has the letters

the letter

plied

each

i and ii)

These
information checkthe

and the

on supplements.
lalest on top,
or safety

"S'in

with.

printed

to show the

pages

title

supplemenl.

ars

'SS

the number.

A safety

supplemenl

are

only currenl

blockof

File supplements

regardless

numbered

lhe

'in

and operational

current

index,

each

supplement
ol

in sequence.

number.

All currenl

and each

slatus

when

T.O. o-'l

whether

salety

A

An operalional

supplements

supplemenl

change

of suppiements

prepared.

-1

show

in lront

il

-3.

is an

The

the

operational

to lhis manual

To be

page

title

ect

eff

of the

supplement

supplement

must

be com-

page

status

and

checklists.

sure ol lhe

of

lhis

of each

manual,

with the

supplement

has

is

(pages

latest

manual

change

in

vii

T.O_ 1T-41

C-1

CHANGE SYMBOL

The following def

t\/AEINING

initions apply to the

The

lhis

Changes
WARNINGS,

The

found through

Operaling

injury

Operating

equipmenl

to

operaling

An

to emphasize.

tial

"shall,"

words

change

symbol,

paragraph,

to illustrations are

CAUTIONS, AND NOTES.

following

or loss

de{initions

the

procedures,

ol

procedures,

il

procedure,lechnique,

"will," "should,"

as illustrated by

indicates texl changes

indicated

apply to

manual.

"Warnings,"

WARNING

techniques, etc.,

lile if not caref ully

lollowed.

ii:r'.::3

lechniques, etc.,

not caref ully lollowed.

NOTE

etc., which

"may':

and

lhe black

made to

with

a miniature

"Cautions,"

which

which

line

in the

lhe current

hand.

can

resull in

can

result

is

considered

margin of

revision.

"Notes"

and

personal

in damage

essen-

and

express

847

to

express

and shall be

shallbe

possibilily

personnel

of the latest data

this manual

should be

Oklahoma

Used to

Used to express a non-mandatory

complishment

Used lo express an acceptable

ment
to

YOUR RESPONSIBILITY

ellort is made to keep the

Every
with operating
assure inclusion
an error

unless we know

tions regarding

welcomed. These

AF Form

5990.

SHALL or WILL

lhat the requiremenls

SHOULD

desire

construed as

MAY

or suggested

conslrued as a

non-mandatory

("might').

_

TO

LET US KNOW.

Flight Manual

and

a constant review

in

the manual.

of its existence.

or any

lorwarded

City ALC/TISDTM Tinker

phase

Comments,

of lhe

through

are binding

or

a non-mandatory

currenl.

of accident

However,

and

prelerred

means

provision.

Reviewconlerences

and

we

correclions

Flight

Manual

your

major

AFB,

Oklahoma

mandatory.

method

provision.

ol

accomplish-

Not

llight

cannot

and

program

command

of ac-

used

reports
correct

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are

on

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Figure

1 . The

T-41C

Aircraft

ix/(x

Blank)

T.O. 1T-41C-1

SECTION

Aircrafl

The

Engine

lnject

Fuel
Propeller
Engine lnstrumenls

Oilsystem

Fuel

System
Electrical
Nosewheel
Brake System

Wing Flap

Flighl

ControlSystem

Stall Warning Horn

lnstruments
Commun
Lighting
Cabin Heating
Cabin Doors

Seal Operation

Bells

Seat

I

ion/Air

System

Steering

System

ications/Navigalion

and

and Shoulder Harnesses

lnduction

System

Ventilation

System

Equipmenl

System

Table

DESCRIPTION

of Contents

AND

OPERATION

1-1
1-1

1-2

1-5
1-6
1-7
1-7

1-10

1-13
1-13
1-13

1-14
1-14
1-14

1-16
1-17
1-19

1-20

1-24

1-20

THE

AIRCRAFT

The T-41C,

Aircrafl Company, is

strul-balanced,

guishable

engine

lixed

and

metal, fixed

all

Aircralt
side-by-side

sion

lo
T-41D has
The T-41D has a variable

improves

designed

leatures

placed

lorward on

tricycle

pitch,

generally

are

seals

lour-place

the

performance.

and manufactured

all melal,

an

high wing

of

landing

with

seating.

same

aircraft

the

lhe

gear.

and designed for

conligured

lhe capability

On T-41D

characterislics as T-41C.

pitch propeller

single-engine,

monoplane.

are

fuselage centerline

propeller

The

best climb.

with

two

of

aircrafl, lhe

Dimensions

The overall

lows:

WingSpan

dimensions

(Figure

1-1)

ol the

aircralt are as

......36'2"

Height .8'9112"
Length . . .25'11"

Wheel

Base ......7'2"

Propeller . . .6'6"

Cessna

by

Dislin-

its single

lorward

conver-

which

fol-

Gross

This aircralt is FAA-certified

and

are as

is

Reler

tional

Weight

utilily

categories.

lollows:

Normal
Utility

[lNormal
lluritiry

Seclion V, Weight

to

inlormation.

in

Maximum

......2,500

Limitations,

both

the

gross

weights

.2,200 lbs

...2,550tbs

.....2,250

for

normal

lbs

tbs

addi-

ENGINE

The

aircraft

fuel-injected,

360-D engine,

inlernal

an
propeller

in

air

and air

trolled by the ignition

air
spheric

and lhe

in

the six cylinders. Spark

is

ignited

cockpit.

the

powered

is

six-cylinder

rated

at

combustion

is derived lrom

provided

in ihe cylinders

pressure

posilion

by

(see

of

the throttle

horizontally-opposed,

by a

Continental Model

210

bhp

engine,

2,800 RPM.

at

power

lhe ignition

to

two magnetos

switch.

The

ratio

is determined

engine-driven

and mixture knobs

to

ol

ignite

and is

ol

luel

l0­As

turn the

luel

and

lhe luel

con-

luel

and

by atmo-

pump)

Change

1

1-1

T"O. 1T-41C-1

lgnition

Anytime the engine is

by two

its

to

los are engine-driven

are independent

and ol each

as oullined

lgnition

The

panel,

The swilch is labeled

in

a

are for

gency purposes

switch determines which

are operating.

System

lurning,

magnetos. Each

associated set ol

and

ol

the aircralt electrical system

other. Magnelo

in

Section ll, Belore Takeoll

Switch

ignition

clockwise direction. The

swilch, located

conlrols

checking

ignition

the

OFF, R,
magneto

the

only. The

ignition

magneto

spark

plugs.

self-contained.

operation

on the

system

L,

R

system

position

portions

is

supplies

The

is

lelt

lower switch

(figure

BOTH,

L

and

ol

the

of

the system

supplied

power

magne-

They

checked

Check.

1-2).

START,

positions

or emer-

ignition

Starting System

Electrical

supplied by the aircrafl ballery

power

to the spring-loaded

master switch ON)
allowing

cranking the engine.
automalically

Mixture

power

source.

lor

When

energizing

the ignition switch is

START

slarter

the

voltage

relurns

Release

lires.
propeller

starter molor more lhan

onds

start

cranking, allow a 3 minute
belore

the starter

Never engage

is

al one time.

within

reengaging

llow

to

lo the

As

lhe switch is released, it

to lhe

soon

as

lhe starter

turning.

Do

ll

lhe engine fails

30 seconds

the slarter.

BOTH

a tolalol30

Control

the starter may

position

nol operate

ol cumulative

cooling

or an external

turned

(with

solenoid closes

starter

position.

as the engine

while

molor,

the
lhe

sec-

to

period

be

the

PRINCIPAL

DIMENSIONS-

Figure 1-1. Principal

rMrxlmum

norr

wlh

Dimensions

h.lghl ol ri.plmr

g.rl

dlpr.trad.

The

mixlure control

throttle

push

silver

control knob lorward

is

accomplished

toward lull

lean. ll large or rapid

press

position

the

is identilied

and

button

rich or

lock bution on

controllorward

the

knob

is

to the right

by a red knob with

lock in

or alt

by rotating

counlerclockwise

changes are required,

cenler.

the

to adjust the mixlure

the

the conlrol knob

or alt as

knob

required.

Moving

clockwise

toward lull

Throttle

Engine

is identilied by its smoolh, round while

throttle

in

the alt

FUEL INJECTION/AIR INDUCTION

TEM

Fuel and air arrive

tion

air

the

pump.

mixture with

also

mixture conlrol knob.

power
is

lorward

lhe

position

separately, via

induction

aneroid in

The

is conlrolled

operated in the

position

it is

manilold. Fuel flow is

the engine-driven rotary vane

aneroid automatically

altitude changes. The

meters luel based

by

the throttle

convenlional manner

the lhrottle is open,

closed.

at the

the

cylinders

luel injection

the

position

on

knob.

lor

syslem
metered

changes

mixlure

ol the

a

the

de-

and

which

The

-

and in

SYS.

combus-

and

by

luel

lhe

unit

ol the

1-2

T.O. 1T-41 C-1

FUEL STRAINIER

1.

2. MASTER SWITCH

AUXILIARY

3.

4. STROBE

PITOT HEAT

5.

NAVIGATION

6.

7. LANDING/TAXI

FUEL

LIGHT

SWITCH

LIGHT

LIGHT

KNOB

PUMP SWITCH

SWITCH

SWITCH

SWITCH

Figure

B, MANUAL

IGNITION

9.

10. FUEL

11. PARKING

12. FLAP

13.

CIRCUIT

1-2. Lelt Lower Switch Panel

PRIMER

SWITCH

SHUTOFF

BRAKE

CIRCUIT

BREAKERS

KNOB

KNOB

BREAKER

1.

THROTTLE

2.

FUEL

CABIN

3.

MIXTURE

KNOB

AIR

KNOB

Figure

Right Lower

1-3.

4.

FLAP SWITCH

5. CABIN HEAT

Switch

Panel

KNOB

1-3

T.O. 1T-41C-1

1.

MrKE BUTTON

2.

CLOCK

ALTIMETER

3.

4.

AIRSPEED INDICATOR
TURN

5.

DIRECTIONAL

6.

7.

VERTICAL VELOCITY

& BANK

INDICATOR

(ON

YOr(E)

INDICATOR

INDICATOF

8. ATTITUDE INDICATOR

(NAV)

voR

e.

8@

10.

TRAhISPONDER

MAGNETIC COMPASS

11.

FREQUENCY PLACARD

12.
CARBON MONOXIDE

13.

DETECTOR

RADIO

14.

FLAP INDICATOR

15.

FUEL FLOW INDICATOR

16.

FUEL OUANTITY

17.

INDICATOR

18. TACHOMETER

19.

AMMETEB

20.

SUCTION

2'1.

OIL TEMPERATURE

INDICATOR

22.

OIL PRESSURE

INDICATOR

23. AUXILIARY

24.

TRIM

GAUGE

MIKE

TAB

JACK

1-4

Figure

1-4. Cockpit

Forward

View

From

lhe mixlure

air

conlrol unit. Air

lrom

the

becomes

a

spring-loaded

lrom

the engine

The

lhrotlle

air

valves

the

correcl ralio

into

air

distributor,

lhrough

induction

litl-er.

air

clogged,

simultaneously

in lhe fuel-air

the air induction

luel is

the luel injection

manifold

the intake valves.

intake valves

cylinders. Drain

of

lhe intake

accumulale

are installed

ports

during

Propeller

fn"

[l

two-bladed,

propeller.

means

chanically

governor

lhe

maintained,

of

governing
peller
the blades

pressure

centrilugal

twisls

The

the blade

lor mosl

lakeofl, when
quired,

propeller
keeps

respecl
allows lhe

air

gine

mum

time.
for,

is

small,

many,

the low

aircralt

conslanl-speed,

Propeller

propeller

of

a

linked

on

the engine. A

governor

engine

hub.

establishes

and the

oil, boosted

pump,

Oilpressure
toward high

lrom

lhe

lorce,

the blades

constant-speed

angle

conditions

adjusted

maximum

the conslant-speed

blade

angle

the

angle

to the

per

revolulion.

turn

lo

amount of tuel

The

although

the

airplane

relative wind.

propeller

at high RPM

high

RPM

the mass

number

the

slipstream velocily

speed, tlre

unil luel llows

enters

the f uel-air

lo the

Alternalively, if

suclion from the

permitting

door,

compartment

air to be drawn

inlo the

controls

control unit

of luel

lo the fuel

manifold.

evenly distributed

nozzles. Air lrom

enlers

Fuel injection

lines

lo drain

engine

is

equipped wirh

operation

lhe cylinders

nozzles

on

the lop side of

are inslalled

any

shutdown

governor

is

luel which

controllable

control knob which is

to the engine-driven

setting inlroduced

the engine

governor

to high

lrom

to or

acting

pitch

governor

assisted

loward low

propeller

encountered in

power

pitch.

or

ol attack

handle

to

This light

and

into heat

also

creales

of

air

then controls

pressure

piston

the

on the

(low

RPM). When

piston

to

the

by

lor

small and eflicient

internal

an

pitch

(high

automatically

maximum

and

propeller

The

low

At

lhe same

a smaller mass

load

allows

to convert

energy

maximum

handled

ol revolutions

is

high,

lhrust is maximum.

fuel

and

control unit

the air

engine opens

the

distributor and

At

the cylinders

lo

on

lhe boilom

or

an

speed to

lilter

system.

luel

and

delivering

fuel

the

the

lhrough

and the

the

may

priming.

ail metat,

regulated

me-

propeller

inlo

be

llow

by

by the

in

piston

is

pro-

the

lwists

oil

relieved,

spring,

RPM).

keeps

efficiency

llight. During

thrusl are

is

blade

re-

at a low

angle

with

lime,

ol

lhe en-

the maxi-

given

in

a

thrust;

per

revolulion

per

minule

and wilh

is

T.O.

1T-41C-1

After

lift-ofl,

lhe conslant-speed

to a higher

blade

elficient
higher

handled per
gine

RPM,

wear,

After

reduces

power

and

then

RPM.

Al

cruising

llight

and less power

lakeofl

power

increasing

Again,

the reduced
of

air handled per

than

ollsel

and

an increase

is

still

increased

The T-41C

one

main

lhe

setting

amount

[lUanitotd

On

the

speed

the

throttle
controls
rectly

propeller

The

propeller

indicated

it

(manifold

ol

the

lhrough

This

increase

increases

RPM

remains

throttle

pitch

lhe

matically

pitch

decreases

that

the

as

lhe speed

angle

angle

and

the

by reducing

keeps

wilh

blade

reducing

keeps

takeolt

power

the

by lirst

increasing

altilude,

or

climb,

lhe

provides

this

engine

by

small

wilh

respect

angle

revolution.

decreasing

blade

a

because

an

with

power

ot

the

power

of

pressure

other

hand,

propeller

and

the

the

engine's power

indicated

control

blades

on

lhe

lachometer.

pressure)

propeller

the

seiling

RPM

blades

action

in

the

air load

constanl.

(manilold

angle

decreased.

remains

propeller

(or

the

to

increases

luel

lhrust

climb

output

the

when

is

pilot

lhe

the

manifold pressure

angle

a

lorque

power;

revotulion

decrease

in

airspeed.

the

increase

its

lixed-pitch

control

throtile

and

the

the

has

lwo

propeller

on

lhe

manilold pressure

changes

governs

and

is increased,

is

of

the

propeller

on

of

the

This

the

air

constant.

ol

the

airplane

automalically

pitch).

angle

Again,

of

attack

the relative

lhe

This

decreases

consumption

at

a maximum.

is

established

of

the

engine

lhe manilold

blade

required

-

the

propeller

T-41D

propeller

the
pressure)

propeiler

load

angle

lhe

airplane

than

again

blade

reduces

lo

decrease

requirement

lor

although

greater,

is

in

slipstream

The

angle

in

airspeed.

propeller

throttle.

wilt

control

or

&

Engine

with

power

main

conlrol.

output

the

the

As

lhe

lhe

automalically

goveinor

pitch

proportionalely

propeilei

Conversely,

blades

decrease

on

lhe

increases,

the

wind.

mass

and

lo

is

is

angle

has

ln

lhat

engine

RpM

its

constant_

controls

The

which

pitch

RpM

throille

pitch

increased

so that

when

ii

decreased,

in

propelier

changes

higher

small

and

The

ol

the

en_

engine

pilot

the

to

climb

pressure

lower

lhe

in level

used

engine

and

lhen

the

RpM.

lo malch

the mass

it

is

more

velocity

ol

attaci<

been

has

onty

case,

both

the

BpM.

throlile

is

indi_

gauge.

ot

ine

which

sefling

angli

syslem.

the

lhe

is

auto-

propeller

so

air

in

-

is

1-5

T_O.

1T-41C-1

For

lhat

amount

RPM,
engine

stress

undue

nenls

ure.

ln

overstress
awareness

cially

pressure).

throttle

When

be

changed

avoid

lhe

decreased,

given

any

should

of manilold

the maximum

cylinders

on

lhem. lf

slress

and

eventually

order

to avoid

when

the

increasing

The

selting (mani{old

Except

CREASE

go-arounds,

sure

proper

during

to exceed

both

manifold pressure

signif icantly,

overstress

order.

reduce

When power

verse

the order

pre

ssu re.

lf

RPM

is

sure, manilold

increase

manufacturer's

RPM,

nol

lhere

be

exceeded.

pressure

allowable

could

be exceeded, placing

repealed

could weaken

cause

conditions

cylinders

ol

the

tachomeler

lhe

combination

WARNING

fuil

throtile/prop

operations

never

engine

by

making

When poweF

manifold pressure

settings

-

increase

reduced

and

are

cAuiloN

before

pressure

possibly

lolerances.

is

manifold pressure

a

lf

an

is

carried

pressure

too frequenily,

the

cylinder

engine

structural f

that would

there

must

be a constant

indication,

throtile

setting

to avoid

pressure)

such

allow

RpM.

pilot

lhe

power

being increased,

RpM

will

and low

FULL

as takeolfs

manifold pres-

and RpM

can

adjustments

settings

be{ore

f irsl,

then manifold

manifold

aulomalically

exceed

excessive

lor

a

within

compo-

possibly

(manilold

is

a

lN-

and

need

further

are

pres-

the

given

the

undue

lhis

ail-

espe-

high

RpM.

to

help

in

being

RpM.

re-

Fuel

Flow

Fuel

llow

is indicaled

indicating

lhe

gauge,

Bg lorl

!31.

settings,

mixture

ll

luel

panet.

calibrated

Fuel.f

but

conlrol

the luel

lumes

inslrument

lt is

of tuet

low

Cylinder

The

cylinder

the

right

number

Fa.hrenheit.
cal-resistance

power

ils

head

side

3 cylinder

The gauge

f rom

[leropetter

Control
eralion

throtlle.

decreases

RPM

gressively

and

knob

plished

RPM
large.or
lock

control

Tachometer

of

engine

ol

lhe

Ptacing

lhe

setting.

increases

decreases

forward

by rotaling

or

counler-clockwise

rapid

butlon

on

lorward

lndicator

located

a direct

to indicate

being

wiil

vary

cruise

luel

knob.

WABNING

gauge

llow

may

enler

Head

of

type

lhe

Controt

propeller

the knob

blade

Moving

engine

or

changes

lhe

or

Temperature

temperalure

the

instrumeni

head

lemperature

aircrafl

RpM

angle

the

the

aft

to

the

knob

control

aft

as required.

by

llie

right

on

reading

approximate

metered

wilh

throtile

llow

can

malfunctions,

the

cockpit.

gauge

temperaiure

is

conlrolled

bulb

electrical

Knob

is

accomplished

conlrol

in

and

RpM.

adjust

are

knob

lhe

fullforward

provides

conlrol

propeller

Moving

RpM,

clockwise

lo

decrease

required,

knob

and

half

of

the

righl

fuei pressure

gallons

to

the

engine.

propeiler

and

be

set with

luel

located

panet

in

by

an eleclri_

which

system.

indicates

degrees

receives

by

next

position

the

highest

knob

aft

blade

the

control

is

accom_

lo

increase

RpM.

depress
position

dual

a

side

or

op_

to

lhe

pro_

angle

the

lhe

of

the

on

ll

ENGINE

INSTRUMENTS

[lManifotd

The

left

half

cated

induction

cury.

1-6

on

the right

air

Manifold pressure

Pressure

of

a dual

side

manifold pressure

Gauge

indicating

of

the

is

controlled

instrument

panel

in inches

by

the throtile.

lo-

indicates

ol mer-

The

lachomeler

by

a llexibte

shalt.

The

RPM

X

100

Oil

Temperature

The

oil

temperalure

side

or

the

is

a mechanical

shafi

connected

iachomeler

(e.9.,

12

=

Gauge

gauge

inslrument

indicales

1200

RpM)

is

located

panel

indicator

to

lhe

engine

.

(figure

on

1_

driven

pump

oil

speed

the

Heat

).

in

righl

T.O.

1T-41C-l

from engine oil
necting

The

expansion.

Oil

A
psi.

gauge

the

gauge

Pressure Gauge

direct-reading

lt is located adjacent lo

on the

causes the

oil system and lhe

is direct

right

reading

gauge

instrumenl

displays

WARNING

pressure

Should the

abnormal

reason,

tion in

gauge.

correct

for other signs ol engine

any case, declare an emergency

as

soon as

OIL SYSTEM

Oil lor engine

wet

by a

syslem.
Oil is drawn lrom the sump

lilter

The

screen

pressure

automalically

psi.

75

the

From

sure screen lo
lhermostat
cooler
lhe lhermostal
through
controlling engine oil

When

sump reducing the oil

the

when

radialor

culaled lo

and returned to the sump by
The engine uses

ensure better engine

to

period,

in

A while oil

oil.

mineral

oil, a

oil

in cold

the

the

Turning

problem.

lhe

weather for no apparent

problem

line lrom

the cabin

practical.

lubricalion

sump

pressure

capacity

inlo

the

of the sump

reliel valve

regulates

valve opens it

this

pump,

opens

the

various

lhe

is lorced through

oil

a thermoslat

and

is

oil

closes causing the

passages

temperalure.

engine

mineral

mineraloil

liller

cap

yellow

liller cap

may be

the

However,

and cooling

through a

engine-driven

in line

pressure

pressure

allows oil to bypass

cold.

oil

break

replaced

is

identifies

liquid in the

gauge

and

oil

oil

the

panel

indication become

system to the

heal olf

be watchlul

line con-

expand.

to

measures lhis

pressure

lemperature

(ligure

condensa-

may

problems.

land

and

is supplied

splash

in

When

in the oil

parts

gravity

lor

gravity

is 10 US

lrom

lhe

belween 30 and

ports

in the

the oil

the

oil to

Oil is then cir-

lor

f low.

lirst 100

the

After this

in.

with detergent

an engine

indicates detergent

quarts.

pressure

low

pump.

oil

oil

oil back to

syslem.

high

a

cooler.

oil

be

cooler, lhus

lubrication

in

1-4).

ln

relurn

pump

pres-

The

the oil

is hot,

lorced

hours

break

with

oil.

An oil liller

the

engine. The

side

of the engine

the liller

the

FUEL

Fuel

cap and

oil access

SYSTEM

is

supplied

lanks, one

by

LEFT,

gravity

llows

labeled

to a luel reservoir

luel

shutoll valve.

PUSH

ON

cap

oil dipstick

the dipstick

door

to

in each

to

BOTH,

operates

is located

on

is located

just

above

on he

lhe engine

wing.

a three-position

and RIGHT.

tank

push-putt

A

the

shutoll

lhe oil

are

accessible

engine

lrom

Fuel

and a manually

knob tabeled

valve

the

top side

on

cooler.

cowling.

two 26-gallon

from

each

selector

Fuelthen

operaled

(ligure

of

the lefi

Both

lhrough

lank

valve,

ilows

FUEL,

1-2).

im

prevent

To

and lo

ol the luel

valve

lion, except

shuldowns.

passing

Alter

luel

is routed

the nosewheelcomparlment,

check

A

luel

The

syslem

any

tem. Any

by

lefl

be drained

forward

the use

lo the engine-driven

From

lhe luel

tion manifold.

engine-driven

turned

llow

lank is not

during

are unusable (ligure

valve

pump),

luel

slrainer

and is

water

collected

pulling

lower

swilch

luselage

ol a luel

there, luel

and

to the luel

and luel

maneuvering

wear

prevenl

shutoll

should

lhrough

lhrough

in

the

when

provided

that may

the luel

panel.

lhrough

air

throttle

Vapor

luel
line

usable

of the

partially

a

be lelt

during

cable

valve,

in

the PUSH

emergency

the luel

fuel

a

and

electric

the

is

the

have

water

strainer

luel

pump

lowest

as

a means

accumulated

willbe

knob

Additionalwater

lour valves (two

and

one

on each wing

sample

is

placemenl,

during

cup. Fuel

pump

luel

distributed

unit

and

pump

reservoir

and mixlure

slraight

flight,

1-7).

3

and

excess

lank.

assembly,

closed

lhe luel

ON

shutolf

strainer,

lhrough

pump

is not

porlion

drained

located

is

and

to

the engine via

fuel

the

fuel

Due

gallon

1/2

and level

gallons

position

shutoff

posi-

engine

valve,
located

a bypass

(auxiliary

being

of

used.

ol

the

collecting

in

lhe sys-

overboard

on the

may

also

beneath

root) with

then rouled

mixture

unit.

distribu-

lrom

unil

are

gravity

lo

in

each

flight;

in

each

tank

lhe

in

luel

the

the

re-

1-7

T.O. 1T-41C-1

PROPELLER

orL
olPsTrcK

OIL TEMPERATURE

GAGE

orL

COOLER

THERMOSTAT

OIL PRESSURE

RELIEF VALVE

ENGINE

ACCESSOBY

BEARINGS

AND

ENGINE

OIL

PUMP

FILTER

SCREEN

{PBESSURE)

E

orL

CAP

OIt

SUMP

ORAIN

PLUG

1,8

Figure 1-5.

FILTER SREEN

(sucTroN)

OilSystem

Schematic

T.O. 1T-41C-1

FUEL

OR^IN

pUGL

lffil
er-rE(C€s8

*At{ovAPoR

M€CIIANICAL

-

-

--

lrxloE

ELCSIBCAT

-

--

IANK

PLUG

Suppt

FU€L

SUMP

IBEFI

FIJEL

THFOrILE

y

ANO

AIB

UNII

FUEL

PLUG

NOZZLES

Figure 1-6. FuelSyslem

Schemalic

1-9

T.O. 1T-41 C-1

NOTE

o Wilh the

total usable

gallons,

46

lons.

luel

seleclor

fuel

and

model aircraft, lhe.

valve on

for

llight conditions

all

in level llight

knob is in-!he. erigine

ment and is.adidessible lhrouoh

t\**":-

a*gesrd6-ir

o

1968 model aircralt,

On
knob is

in

located

lhe lower

lelt

on the

corner.

BOTH, lhe

is 51

Juel-.sffdiff6r

compart-

fuel

the

inslrurnenl

strainer

the

panel

gal-

oil

preventing

thus

periods

ing

switch to lhe allernate flow

is

ol

approximately 2100

the auxiliary luel
erates the

position

purging
ternate engine

should malfunction. The

to OFF lrom
be held in

is

during

an excessively

low

of

pump

engine

pump

at its highest

used lor

hot

weather

operalion if

HIGH

the

HIGH when

rich

mixture

speed.

rate

rpm.

switch, labeled

at a

The

The

throtile

up

rale.

engine

posiiion

used.

NOTE

priming,

operations,

the engine-driven pump

swilch

is

spring-loaded

and

must

dur-

pump

setting

position

HIGH,

The

HIGH

for vapor

lor

or

therelore

will

of

op-

al-

Engine-Driven

The

engine-driven luel

provides

conditions.

lure

particularly

The mixture unit

engine-driven
through a

control

aulomatic

lt

control

at

mechanical

knob.

Fuel Pump

luel

provides

throughoul the

low

and

is

fuel

ir':Y"'i"%3

Should the aneroid

pump

luel

position
on LOW accompanied by

may be

Auxiliary

An electric

lor

starting and

lailure

vapor

(figure

is

The

pump

on lhrottle

setting

LOW

cruise

luel

the

causes

ol the engine-driven

purging.

1-2),located

guarded,

a

down

al one ol

and the auxiliary

position,

llight

pump.

idle

the auxiliary

lail, it willfailto

use of

and

required

Fuel

auxiliary

lor

The

three-position, center-ofl

position,

two

position.

suff

operation with

When

position,

Pump

icient luel f low is

the throttle

a

pump

has an aneroid

mixture for existing ambient

a more

desirable

luel

operalional range,

power

idle

also an

pump

settings.

integral

controlling

part

fuel llow

linkage from the

in

the engine-driven

LEAN

FULL

lhe

auxiliary

lhe

.

pump

luel

engine

auxiliary

on the

lelt lower switch

labeled

possible

With

the

fuel

a

microswitch

pump

luel

luelpump

manual

supplies

operalion

luel

{uel

LOW,

speeds

leaning

luel

following

pump

pump

operates lhe

depending

lhroltle al a cruise

pump

lailed

switch

provided

engine-driven

is moved

is

tripped

low raie

f

towards

lo

which

mix-

of the

mixture

flow

and for

switch

panel,

switch.

in

the

lor

which

reduce,

lf

the auxiliary

turned

engine

knob

ports

The

auxiliary

engine
the auxiliary
pump
air ralio will

is running

bolh functioning,

Manual

A

manual

panel

the engine.

engine induction manilolds

Fuel

The

tors

(f

(figure

Quantity

two electrically

are located

igure

1-4).

with

on

stopped,

not

at

will llood

luel

luel

result.

Primer

primer,

1-2), is

lt

sprays

The instruments

the tanks lrom

ters. The

level
master

indicators

lransmitters in

switch is ON.

quantity

Fuel
in

stabilized straight

ELECTRICAL

Electrical

current

driven

energy is

syslem

alternator. A 12-volt

pump

fuel

the master

and

FULL

LEAN,

luelwill

and

pump

during

pump

located

luel

lndicator

operated

on

lhe right

empty

receive

each wing

NOTE

indicators

SYSTEM

supplied

powered

and

an excessively

provided

to lull

and levetllight.

by

switch

is

switch

accidenily

the mixture

the cylinder

drain

overboard.

is

not

used

normal

on the left

operations.

the

engine-driven

to

into

the

lor

improved

aid in

elbows

fuelquantity

instrument

indicate

graduated

their inputs

lank

are accurate

by

14-voll,

a

a 60-ampere,

bafiery, located

ON,

control

intake

while

rich luel-

lower

starts.

the

from luel

any

time the

only

the

the

With

luel

switch

slarting

ol

lhe

indica-

panel

fuel

quar-

in

direct

engine-

alt of

in

1-10

T.0.

1T-41

C-1

USABLE

TANK NO.

LEFT WING
RIGHT

lhe

cal

nate

nator
Power is

a splil

conlains

WING

rear cabin

power

lor starting.

source ol electrical

regulalor lailure.

or

supplied

bar

bus

lhe

1

1

bulkhead,

(figure 1-8). The

strobe

ALL
CONDITIONS

lt

lo all electricalcircuits through

lighls,

ceiver, transponder, and

primary

The

tem circuils.

sides ol

when

nected,

power

a

circuit to

lronic

damaging the

equipment.

bus

contains

the

With

bus are

masler switch ON, both

the

normally

either an exlernal

ignition

lhe

or

contactor automatically

electronic bus.

the

circuils

prevents

semiconductors

switch

QUANTTY

FUEL

FUEL

FLIGHT

gal.

23

gal.

23

Figure 1-7. Fuei

is

used to supply

also serves as

power

in

case

eleclronic

VHF radio, VOR re-

pitot

lhe

all olher

power

is turned to START,

heal

electrical sys-

powered.

source

However,

deactivates lhe

lsolaiing the

lransient

vollages

in

the

electronic

ADDITIONAL

USABLE

(LEVEL

Quantity

electri-

an alter-

ol alter-

bus

circuits.

is con-

elec-

lrom

DATA

2.5

2.5

(U.S.

FUEL

FLTGHT)

gal.
gal.

Dala

Ammeler

All

indicates

or lrom
tween

inslrument

meler

the alternator

tery is in

or discharge

tions ol

GALLONS)

(U.S.

aircralt

lhe amount

the

the luel

will

a normal

an electrical

A weak

period

This

is normal;

untilthe
o[ 0

to +2

UNUSABLE

(LEVEL

Gallons)

are

equipped

battery.

quantity

panel

remain

is

operating

rates

battery

may

cause a high

ammeler

needle

FUEL

FLIcHT)

gal.

0.5
gal.

0.5

ol current

The

(ligure

within

state

of charge.

lor

system

NOTE

or

however,

is within

widths.

TOTAL

with

an ammeter

llowing

ammeter

indicators

1-4).

Normally,

0 to

+2 needle widths

properly

Extreme

any

duration

mallunction.

prolonged

a

ammeter reading.

not

do

the normalrange

FUEL

VOLUME

EACH

gal.

26.0
gal.

26.0

either

is

located

on

the right

the am-

and the

are indica-

starting

take

that

to

be-

il

bat-

charge

oll

Master

The master

the

crall, the

on

1969

piece

switch during

Switch

switch controls electrical

aircraft electrical syslem. On

push-pull

switch

lell

the

model

split switch

is

a

lower switch

aircrafl, the master switch

which

normal operations.

NOTE

On 1969 model aircrafl, the

switch may be benelicial

siluations. The lelt

connecl
disconnects the

the alternator

switch

battery.

1968 model

lype and

panel

(ligure

should be

split

during abnormal

serves

while

lhe

power

air-

is located

1-2).

On

is a two-

used as one

master

to dis-

right

side

to

External

ground

A

permit
cold

on

behind

be ON

lhe use

wealher

lower

the

an

belore

Belore

power

nal
personnel

danger

Power

service

of

slarting.

lell

access

connecling

starting

source,

are

area.

Receptacle

plug

receptacle

an exlernal

The

receptacle

side

ol

the

engine

plate.

The

masler

an external

WARNING

the

engine

be

sure

well

clear

is inslalted

power

compartment,

power

using

thal all

of

the

source

is located

swilch

source.

an exter-

ground

propeller

to

lor

should

1-1 1

T.O. 1T-41C-1

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SYSTEM

lo

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TO

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1-12

Figure

1

-8.

Electrical

System Schemalic

T.O. 1T-41C-1

Use

ol other lhan a 12-volt

may

damage eleclrical

ground
corporales

service

lhe external source

service

properly.

plug

plug

polarity

is

connected

receplacle circuit

protection.

will llow only

Circuit Breakers and

The majority ol electrical circuils

protected

on

the

tions are lhe external
circuit

the battery.

lf

resel once il

lions exist.
alter being

it

again.

as soon as conditions

"push

by

lell lower

which

circuit breaker

a

lo

switch

prolecled

are

no

ll

the

reset, do not attempt lo

Terminale

resel"

panel

power

pops

other eleclrical

circuit breaker

the

power

systems.

Power

lo lhe

Fuses

in

the aircralt

circuil

permit.

breakers

(ligure

circuit and

by luses

oul,

mission and

source

if

aircralt

1-2). Excep-

the clock

located near

it may be

mallunc-

pops

reset

NOSEWHEEL STEERING SYSTEM

Nosewheel

ol the

up

to approximately

lral, aller

maximum
center when dilf

damper

BRAKE

hydraulic

The

individually operaled

are

sure

to the upper

pedals.

cylinders,

main landing

tached

transmits hydraulic

wheel

right

steering

rudder

pedals.

which it

delleclion

erential

provided

is

SYSTEM

disc

Depressing the

resulting in a braking

gear

to each of lhe

brake cylinder,

seat brake

is accomplished

The nosewheel

10

degrees each

becomes

lree wheeling to

ol 30 degrees

braking is

minimize nosewheelshimmy.

to

brakes on the

by applying

portion

pedals

wheels. A masler cylinder at-

pressure

thus

pedals

either set

of

activates

lelt

seal

the respective

to

applying brakes.

are connected

through

is sleerable

side ol

right

A shimmy

used.

main

toe

ol

the

aclion on lhe

(pilot)

The

in-

lrom

the

located

out

land

lelt ol

or

wheels

rudder

brake

pedals

by

are

use

neu-

pres-

main

The

me-

chanical

pressure
mitted

Parking

The
left

set

nism

master

bolh master

locks

is.lurned

the
position.

handle

position

a

position.

WING

The
controlled

lower

loaded

motor

cables and

lrom

located

cally-operated

in

degrees

grees.

linkage

applied

mechanically

ll

sharper

a

made

mechanism,

the

turn

rolling.

on a locked

wheel,

dangerous

be apparenl.

wheel

with

rate

of

in

this manner,

Any

lire or

rolls,

mittently.

evenly,

and

Brake

parking

lower

the

is

lhe handle

parking

brake

switch

brakes. The

connected

cylinders.

cylinder

and released.

handle

To release

90

degrees

and let it return

FLAP

wing llaps

by

a three-position

switch

panel

to the

raises

that

push-pull

shorts

on

and

the

ol

to

to

lurn

the

use

pilot's

lhe

the

right

to

lhe

is

desired

rudder

lhe

brakes

lurn desired.

keep

attempt

inside

because

To

release

Apply

cautiously

panel

Pulling

in

to

wheel

strut.

This

the

make

the inside

the

handle

(ligure

handle-and-rachet

by

a

cable

out

piston

position

this

To

out

and

parking

the

clockwise

to

SYSTEM

are

electrically

(figure

olf

or lowers

1-3).

position,

rods.

overheal

circuit

llap

llap

breaker

posilion

extension

brake

pedals

seat

masler

cylinders.

than can be

pedal

steering

to establish

While

lhe inside wheel

pivot

may

damage

sure

brakes

at

all

is located

lhe

damage

particularly

ii

that

the inside

brake

smoothly,

limes.

1-2)

and is

making

may

beneath

to linkage

lhe handle

rods

and

until

set

the

brakes,

turn il

to the

brake, rotate

to the

the

original

operafed

switch on

This

swilch,

controls

the llaps

The

by

panel.

indicator

by means

motor is

a circuit

is calibrated

lrom

0

pedals,

is

trans-

a

aircrall

lhe
nol

inter-

used
mecha-

at

depresses

the rachel

handte

lhe

6 o'clock

9 o'clock

retracted

and are

the

spring-

an

eleclric

protected

breaker

The

electri-

40 de-

to

and

the

lo

the

pull

the

right

of

1-13