Rockwell Commander 112 - ENGINE CONTROLS

Rockwell Commander 112

293 pages

Save Page as PDF

To Next Page

To Next Page

To Previous Page

To Previous Page

Loading...

ROCKWELL

COMMANDER

112/B/TC/TCA

MAINTENANCE MANUAL

SECTION

IV

POWER PLANT

AND

PROPELLER

EXHAUST

SYSTEM

MODELS

112/B.

The

exhaust

system

consists

of

four

exhaust

stacks.

Each

exhaust

stack

is

attached

to

the

exhaust

port

of

each

cylinder

and extends down and

attached

to the

muffler

assembly.

Each

exhaust

stack

is

attached

to the

muffler

by

special

clamps

that

allow

for

expansion and

contraction

of the

entire

installation.

Nuts and lock

washers

are

used

to

secure

each

exhaust

stack

to

the

cylinders.

Inspect

the

exhaust

stacks

at

prescribed

intervals

for

evidence of

leakage,

cracks

and

looseness

of mounting

nuts

(see

Figure

4-7).

MODELS

112TC/TCA.

The

exhaust

system

for

each

engine

consists

of

six

segments.

These

segments

at-

tach

to

the

exhaust

ports

of

the

right

and

left

banks of

cylinders

and extend

across

and

aft

to

where

they

at-

tach

to the

turbine

section

of the

turbocharger.

The

segments

of the exhaust

system

utilize

slip

joints

that

allow

for

expansion and

contraction

of the

entire

as-

sembly.

Nuts and

lockwashers

are

used

to

secure

the

exhaust

system

to

the

exhaust

ports

of

each

cylinder.

Inspect

the

exhaust

system

at

prescribed

intervals

for

evidence of

leakage,

cracks

and

looseness

of mount-

ing nuts (see

Figure

4-7).

EXHAUST

SYSTEM

REPAIR

Components of the

exhaust

system

which

fail

must

be

replaced,

however,

certain

components may

be

re-

paired

in

accordance

with FAA Advisory

Circular

No.

AC

43. 13-1. Consult

this

source

for

repair

guideline

s.

Never

use

lead

pencils,

grease

pencils,

etc.,

to

mark

exhaust

system

components.

Carbon deposited by

these

items

will

eventually

cause

cracks

due to heat con-

centration

and

carbonization

of the

metal.

Use chalk,

prussion

blue

or

India

ink

when

necessary

to

mark

components.

COOLING

SYSTEM

Cooling

air

enters

the engine cowling

compartment

through openings

located

in the

center

of cowling

near

the

propeller.

Engine

baffles

(Figure

4-8)

direct

air

flow

around

the cooling

fins

of

each

cyliriner. Adjust-

able

cowl

flaps,

located

in

the

lower

cowl,

are

pro-

vided to

regulate

engine

temperature.

To

assure

proper

airflow

around

the engine, baffle

seals

and

cowling

must

be

maintained

in

a

serviceable

condition.

Baffle

seals

which

do

not block the airflow

at

the

seal

location

cause

improper

distribution

of

the

cooling

air

and may

result

in

hot

spots

on the

cylinders.

Ground ope

rate

engine with cowl

flaps

open to

prevent

overheating

of engine.

BAFFLE

REMOVAL,

REPAIR

AND

INSTALLATION

Removal and

installation

on the

various

baffles

can

be made with the engine cowling removed.

Insure

that

any

replaced

baffles

and

seals

are

installed

cor-

rectly

and

that

they

seal

properly

to

direct

the cool-

ing

air

in

the

proper

direction.

Baffles should

be

replaced

if damaged

or

cracked.

However,

small

plate

reinforcements

riveted

to

the

baffle will often

prove

satisfactory

both to the

strength

and cooling

requirements

of the unit.

ENGINE

CONTROLS

MODELS

112/B.

The

engine

control

levers

(Figure

4-9)

are

located

on

the

engine

control

quadrant

and

control

the

throttle,

propeller

pitch,

fuel

mixture

and

alternate

air.

Cables

and

push-pull

rods

connect

the

engine

control

levers

to

the power

plant.

Cover

plates

on the

quadrant

pedestal

may

be

removed

for

inspection

and maintenance of

control

cables

and

other

equipment

enclosed

in

the

pedestal.

Additionally,

the complete

pedestal

may

be

removed

for maintenance

purposes.

A

friction

lock

is

installed

on the

right

side

of

the

quadrant

to

secure

the

control

levers

in

the

desired

pOSition,

or

place the

desired

amount of

friction

on

the

engine

control

levers.

Engine

control

cables

are

routed

through the

firewall

and to the

en-

gine.

The individual

controls

are

attached

to the

servo

regulator

(throttle and fuel

mixture),

propeller

governor

(propeller

pitch) and induction

air

box

(alter-

nate

air).

Cable

adjustments

for

the engine

controls

are

made

at

the

ball

joints

and

clevises.

Push-pull

rods,

ball

joints

and

clevises

should

be

checked

for

loose

checknuts,

nuts,

freedom

of

operation

and

ex-

cessive

wear.

Routing of

the

control

cables

should

be

checked

to

see

that

cable

clamps

are

in

place

and

cables

do

not

rub

structure

or

accessories.

MODELS 112TC/TCA. The engine

control

levers

(Figure

4-9)

are

located

on

the

engine

control

quad-

rant

and

control

the

throttle,

propeller

pitch,

fuel

mixblre,

turbocharger

wastegate,

and

alternate

air.

Cables

and

push-pull

rods

connect

the

engine

control

levers

to

the

power

plant.

Cover

plates

on the quad-

rant

pedestal

may

be

removed

for

inspection

and

maintenance of

control

cables

and

other

equipment

enclosed

in

the

pedestal.

Additionally, the

complete

pedestal

may

be

removed

for

maintenance

purposes.

A

friction

lock

is

installed

on

each

side

of the quad-

rant

to

secure

the

control

levers

in

the

desired

posi-

tion,

or

place

the

desired

amount

of

friction

on the

engine

control

levers.

Engine

control

cables

are

routed

through

the

firewall

to

the

engine. The

indi-

4-13

Copyright Commander Owners Group 2013 All Rights Reserved

**unofficial copy**

Table of Contents