STC SA03708AT AeroDesigns Oleo Strut Housings PA24-0100-01

United

States

of

Anericx

Bepartment

of

Transportation

--

Hederal

Adiation

Administration

Supplemental

Type

Aertificate

széle

SA03708AT

Thes

cerdificato

issuecd

fo

The

Aeronautical

Design

Scrvice

Pty

Ltd

P.

O.

Box

307

Woombye,

Queensiand

Australia,

cerlifoes

that

o

chango

i

o

bypo

dessgn

for

(s

fottsuwing

prodicct

will

the

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and

condilions

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Pocdscs

-

-

Ygpren

Centificato

Nienber

-

1A15

&

AIEA

Mbake

.

Piper

AModet

:

PA-24,

PA-24--250,

PA-24

260,

PA-24

-400,

PA-30,

PA-39

%chyz/ﬁbn

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-%/Pﬂ

%yn

%fym

This

design

approval

is

based

on

Australian

Civil

Aviation

Safety

Authority

Supplemental

Type

Certificate

Number

SVA510

for

replacement

of

the

Main Landing

Gear

Housing

and

the

exisling

Bilateral

Aviation

Safety

Agreement

Implementation

Procedures

for

Airworthiness

between

the

United

States

and

Australia.

Ernitations

and

Gondeteons.:

This

approval

should

not

be

extended

to

other

aircraft

of

this

model

on

which

other

previously

approved

modifications

are

incorporated,

unless

it

is

determine

by

the

installer

that

the

interrelationship

between

this

change

and

any

other

previously

approved

modificalions

will

produce

no

adverse

effect

upon

the

airworthiness

of

that

airplanc.

If

the

holder

agrees

to

permit

another

person

to

use

this

certificate

to

alter

the

product,

the

holder

shall

give

the

other

person

written

evidence

of

that

permission.

7

l;ﬂw/’ffm&a

andd

ta

degpporting

dale

coftick

i3

Mo

bases

,4/'

(ylﬂ/'o(/a/

Sall

remadn

in

%&/

wnlel

Secrvendered,

suspendedd,

recofied

on

w

lerminaltion

duts

£

ortemeodso

oslalblosfed

fy

e

Atlorincstmatior

of

Ha

Federal

AAviation

AAdiinistration.

Diato

of

ayylicatson

-

October

4,

2008

Dt

recsscced

.

Dirte

of

sswance

.

Junc

2,

2009

Dialo

anendted

.

Ty

clrection

of

)

bbnincstrator

(Signature)

Rick

Jones

Associate

Manager,

ACE-119A

Atlanta

Aircraft

Certification

Office

(Title)

Any

alteration

of

this

certificate

is

punishable

by

a

fine

of

not

exceeding

$1,000,

or

imprisonment

not

cxcecding

1

yeara,

or

both.

PAA

FORE

B110-2(10-6B}

PAGE

1

of

1

FPARBEY

This

certiffcate

may

be

transferred

in

accordance

with

FAR

21.47.

&

Australian

Government

s

iy

é

295"

Civil

Aviation

Safety

Authority

Supplemental

Type

Certificate

Number:

SVAS510

This

certificate

issued

fo:

The

Aeronautical

Design

Service

Pty

Ltd

PO

Box

5250

Bundaberg

West

g

QLD,

5670

Australia

certifies

that

the

change

in

the

type

design

for

the

following

product

with

the

limitations

and

conditions

as

specified

hergin

meets

the

airworthiness

requirements

of

CAR

3,

Amdt

3-6.

Original

Product:

Type

Acceptance

Certificates

A230

and

A231

FAA

Type

Certificates:

1A15

&

A1EA

Make:

Piper

Modeis:

PA-24

Series,

PA-30,

PA-39.

Description

of

Type

Design

Change:

Replacement

Main

Landing

Gear

Housing

in

accordance

with

.

Aeronautical

Design

Service

(ADS)

Report

#

890100-MDL,

Revision

1,

dated 26™

September

2006,

Limitations

and

Conditions:

This

approval

is

issued

on

the

basis

of

a

standard

aircraft

compliant

with

the

referenced

type

certification

and

should

not

be

extended

to

other

aircraft

of

this

mode!

on

which

other

previously

approved

modifications

are

incorporated

unless

it

is

determined

by

the

installer

that

the

-

interrelationship

between

this

change

and

any

of

those

previously

approved

modifications

will

produce

no

adverse

effect

upon

the

airworthiness

of

that

aircraft.

'

If

the

holder

agrees

to

permit

another

person

to

use

this

certificate

to

alter

the

product,

the

holder

shall

give

the

other

person

written

evidence

of

that

permission.

Instructions

for

Continued

Airworthiness

for

the

modified

main

landing

gear

are

contained

in

ADS

Report

#

990100-SMS,

Revision

1,

dated

3™

October

20086

or

later

revision

issued

by

ADS.

This

certificate

and

the

supporting

data,

which

is

the

basis

for

approval,

shall

remain

in

effect

until

suspended,

cancelled

or

a

termination

date

is

otherwise

established

by

the

Civil

Aviation

Safety

Authority.

.

Date

of

application:

20"

July

2006

Date

of

issuance:

3"

October

2006

This

certificate

is

issued

pursuant

to

Part

21.113A

of

the

Civil

Aviation

Safety

Regulations

&

7

Dinh

Nguyen

&,

Delegate

of

the

Authority

______

A3

S

This

certificale

may

be

transferred

in

accordance

with

CASR

21.047.

Page

1

0f

1

401

{Rev

12/03;

AERONAUTICAL

DESIGN

SERVICE

REPORT

REPORT

NO

PROJECT

990100

PA24-990100-7

Installation

Instructions

AeroDesigns

PA24-0100-01

Oleo

Housings

On

Piper

Comanche

Aircraft

Alan

Kerr

REVISION

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AERONAUTICAL

DESIGN

SERVICE

REPORT

PROJECT

990100

1.

PREAMBLE

REPORT

NO

PA24-990100-7

The

Aeronautical

Designs

PA24-0100

Olec

Housing

has

been

designed

as

a

replacement

component

for

the

Main

Landing

Gear

Oleo

Housing

fitted

to

the

Comanche

Series

of

Aircraft.

Added

strength,

and

different

manufacturing

techniques

have

generated

the

distinctively

different

shape

of

the

housing.

Even

with

this

shape

and

its

increased

bulk,

the

AeroDesigns

component

is

a

direct

replacement

item

for

MLG

Assemblies.

Two

micro-switch

brackets

are

included

in

the

kit

to

accommodate

the

two

different

kinds

of

switches

which

are

used

on

the

aircraft.

The

replacement

housing

operates

in

exactly

the

same

mode,

and

is

serviced

in

exactly

the

same

manner

as

the

original

housing.

Installation

in

the

aircraft

is

essentially

the

same

except

that

bracket

attachment

and

orientation

is

slightly

different.

These

differences

are

highlighted

in

this

set

of

instructions.

This

set

of

installation

instructions

is

supplementary

to

the

instructions

provided

in

the

PIPER

COMANCHIE

SERVICE

MANUAL

for

servicing

the

Main

Landing

Gear.

These

instructions

deal

only

with

the

operations

required

to

install

the

oleo

housing

and

adjust

the

safety

switch.

S

Approval

Approval

for

this

installation

is

provided

under

CASA

STC

Serial

Number

SVA510

and

FAA

STC

SAQ03708AT.

3.

Parts

Break-Down

Figure

#1

shows

the

Oleo

Housing

and

parts

that

are

supplied

in

the

installation

kit.

Figure

#2

is

a

view

of

the

Safety

Switch

Bracket,

used

on

the

LHS

Main

Landing

Gear

and

replaces

the

existing

switch

bracket.

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PAGE

2

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Bungea

Arm

Pin

PA24-100-8

Qty2

Required

Svatch

Bracket

PA24-100-2

Applicable

LHS

Only

3MBUNC

X

1/2"

/

UNBRAKO

SHCS

A

Qy4

P

Bungss

Spring

Bracket

TR

<

___

PA24100-5

Ry

{

A

S

/

!

/

;"

.

f

\

7

/

\

J

<

|

O

A

J

V

}

3MBUNC

X

172"

“

UNERAKO

SHCS

Qty

2

Required

LHS

only

AN4-5A

Qty

1

Required

N\

Lwyg

&

:E«“cl,

)

N

Crown

Washer

T

__PA24-100-3

Figure

1

Oleo

Assembly

PAGE3

OF

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REVISION

AERONAUTICAL

DESIGN

SERVICE

REPORT

REPORT

NO

PROJECT

990100

PA24-990100-7

&

S

e

f’!/‘

—

‘/‘

/

’

/

/’

/

/

bt

/

/,«"

(

///

//"

\\.

AN

I

i

e

,»:’:

SWitch

Lever

P/No

PA24-100-4

Qty

1

Required

“~~—__

LHS

ONLY

.

['IFigure

2

Safety

Switch

Bracket

Table

#1

a

of

Oleo

PA24-100-0L

PA24-100-0R

Bungee

Spring

PA24-100-5

|

PA24-100-5

Bracket

Switch

Bracket

PA24-100-2

Not

Arm

Pin

PA24-100-8

PA24-100-8

Crown

Washer

PA24-100-5

PA24-100-5

Cap

Screw

3/16UNC-|

3/16UNC-|

éﬂg

:3

Screw

AN4-5A

AN4-5A

1

Figure

3

is

a

view

of

the

assembled

Main

Landing

Gear

System

with

the

replacement

Oleo

Housing

Installed.

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AERONAUTICAL

DESIGN

SERVICE

REPORT

REPORT

NO

PROJECT

990100

PA24-990100-7

3.1.

Consumables

required

but

not

issued

with

the

kit

Faying

Surface

Sealant

"HYLOMAR"

or

equivalent

Lock-Wire

0.014"

(Spec

MS20995C41)

Hydraulic

Fluid

MIL-H-5606

Nitrogen

Gas

Installation

Instructions

41.

General

Installation

of

the

AeroDesigns

PA24-0100

Oleo

housing

will

require

the

existing

housing

to

be

removed

and

disassembled.

Some

hardware

items,

and

components

fitted

to

the

existing

housing

will

be

used

on

the

replacement

housing.

4.2.

Remove

the

Main

Landing

Gear

From

the

Aircraft

Remove

the

Main

Landing

Gear From

the

aircraft

using

the

procedures

given

in

Section

6-31

of

the

Piper

Service

Manual

4.3.

Disassemble

the

Main

Landing

Gear

Disassemble

the

main

landing

gear

using

the

procedures

contained

in

paragraph

6-9

of

the

PIPER

COMANCHIE

SERVICE

MANUAL.

Identify

and

retain

the

following

components

for

fitment

to

the

replacement

housing.

e

The

complete

Piston

Tube

Assembly

Upper

and

Lower

Torque

Link

assemblies,

complete

with

bolts

washers,

and

spacers.

The

complete

orifice

Tube

Assembly

The

Bungee

Arm,

associated

retaining

bolt

and

Barrel

Nut

All

installation

shims

and

washers.

Remove

and

retain

the

following

items

from

the

oleo

housing

e

The

two

Torque

Link

Pivot

Bushes

e

The

Lower

Drag

Link

Bush

e

Strut Filler

Valve

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AERONAUTICAL

DESIGN

SERVICE

REPORT

REPORT

NO

PROJECT

990100

PA24-990100-7

*

Torque

Link

Bolt

Grease

Nipple

4.4.

Service

all

Retained

Components

Service

all

of

the

retained

components

in

accordance

with

Secticn

6-32

of

the

PIPER

COMANCHIE

SERVICE

MANUAL.

4.5.

Preparation

of

the

Replacement

Oleo

Housing

Assembly

Visually

inspect

the

oleo

housing

to

ensure

that

it

has

not

been

damaged

by

handiing

or

in

transit.

4.5.1.

Painting

The

surface

of

the

oleo

housing

has

been

treated

with

a

conversion

coating

to

help

prevent

corrosion,

and

improve

paint

adherence.

Solvent

degreasing

of

the

surface

is

the

only

preparation

required

for

painting.

Paint

as

required.

4.5.2.

Install

Torque

Link

Bushes

If

the

torque

link

bushes

removed

from

the

original

housing

were

declared serviceable

after

inspection,

coat

the

external

surfaces

with

"HYLOMAR"

or

an

equivalent

barium

chromate

paste,

and

install

these

in

the

replacement

housing.

Use

new

bushes

if

the

original

one’s

were

declared

unserviceable.

4.5.3.

Install

Drag

Link

Bush

If

the

drag

link

bush

removed

from

the

original

housing

was

declared

serviceable

after

inspection,

coat

the

external

surface

with

“HYLOMAR"

or

an

equivalent

barium

chromate

paste,

and

install

these

in

the

replacement

housing.

Use

a

new

bush

if

the

original

one

was

declared

unserviceable.

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AERONAUTICAL

DESIGN

SERVICE

REPORT

REPORT

NO

PROJECT

990100

PA24-990100-7

Main

Gear

Door

Bolt

Assembly

Attachment

Bolt

Bungee

Pulley

Bungee

Chord

Bungee

Pulley

Bracket

Fitting

Attachment

Bolt

10

Bungee

Am

11

Strut

Support

Fitting

-

Rear

-

O

|IND

O

bW

12

Shims

13

Bungee

Arm

Pin

14

Crown

Washer

15 Strut

Housing

186

Strut

Filler

Valve

17

Shims

18

Strut

Support

Fitting

Front

18

Assist

Spring

20

Bolt

Assembly

21

Push

Pull

Cable

22

Side

Brace

Support

Bracket

23

Pivot

Bolt

24

Upper

Drag

Link

25

Down

Limit

Switch

26

Pivot

Bolt

27

Lower

Drag

Link

28

Safety

Switch

Late

Model

29

Docr

Retract

Rod

30

Upper

Torgue

Link

31

Shim

Washers

32

Lower

Torque

Link

33

Brake

line

34

Fork

Assembly

35

Brake

Cylinder

Assembly

36

Wheel

37

Tyre

38

Safety

Switch

Bracket

[IFigure

3

Main

Landing

Gear

Installation

Diagram

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AERONAUTICAL

DESIGN

SERVICE

REPORT

REPORT

NO

PROJECT

990100

PA24-990100-7

4.5.4.

Install

the

Spring

Bracket

The

spring

bracket

is

a

new

item

P/N

PA24-100-5

supplied

with

the

oleo

housing.

This

is

inslalled

using

Qty

4

3/16UNC

X

%2”

Cap

Screws.

Coat

the

threads,

and

faying

surfaces

liberally

with

HYLOMAR

before

assembly.

4.5.5.

Install

the

Switch

Bracket

(LHS

Housing

Only)

The

switch

bracket

is

a

new

item

P/N

PA24-100-2

supplied

with

the

oleo

housing.

This

is

installed

using

Qty

2

3/16UNC

X

2"

Cap

Screws.

Coat

the

threads,

and

faying

surfaces

liberally

with

HYLOMAR

before

assembly.

4.6.

Assembly

of

the

Main

Landing

Gear

Oleo

Note

Assembly

of

the

Main

Landing

Gear

Oleo

is

the

same

as

that

described

in

the

PIPER

COMANCHIE

SERVICE

Manual

except

that the

new

Crown

Washer

P/N

PA24-100-3

replaces

the

washer

(13)

removed

from

the

original

installation,

Ascertain

that

all

of

the

parts

removed

from

the

original

assembly

are

cleaned

and

inspected

and

determined

to

be

serviceable.

Re-insert

the

piston

tube

plug

(21}

using

procedures

contained

in

paragraph

6-30(b)

of

the

PIPER

COMANCHIE

SERVICE

MANUAL

Assemble

the

components

of

the

orifice

tube

(19)

using

procedure

contained

in

paragraph

6-30(d)

of

the

PIPER

COMANCHIE

SERVICE

MANUAL

Trial

fit

the

orifice

tube

in

the

oleo

housing

(7)

to

verify

correct

crush

on

the

o-ring

by

inserting

the

tube

up

through

the

housing.

With

the

end

of

the

tube

exposed

through

the

top

of

the

housing,

install

the

"O”

ring

(15),

back-up

ring

(14),

and

Crown

Washer

(New

Part

JABIRU

PA24-100-

3.

Verify

that

at

least

1-mm

of

crush

is

available

before

fitting,

and

locknut

(12).

Tighten

only

finger

tight.

Assemble

the

piston

tube

assembly

using

the

procedure

in

paragraph

6-30(f)

of

the

PIPER

COMANCHIE

SERVICE

MANUAL.

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AERONAUTICAL

DESIGN

SERVICE

REPORT

REPORT

NO

PROJECT

990100

PA24-990100-7

Lubricate

the

wall

of

the

oleo

housing

(7),

and

piston

tube

(8),

and

carefully

insert

the

tube

assembly

into

the

housing,

guiding

the

orifice

tube

(19)

into

the

piston

tube

until

the

snap

ring

(29)

can

be

installed

in

the

annular

slot

at

the

lower

end

of

the

housing.

Tighten

the

orifice

tube

lock

nut

(12)

at

the

top

of

the

housing.

Verify

full

and

free

travel

of

the

piston

tube

assembly

by

gently

moving

the

tube

into

the

housing

until

it

bottoms.

Gently

withdraw

the

tube

after

bottoming

until

it

reaches

its

full

travel.

Install

the

wiper

strip

(27),

slide

the

washer

(28)

into

position

and

secure

the

assembly

with

the

snap

ring

(29).

Ascertain

that

the

bushings

are

installed

in

the

upper

and

lower

torque

links

(5

and

12).

When

assembling

the

LHS

main

landing

gear.

Trial

fit

the

upper

torque

link

boit

with

the

switch

lever

(New

JABIRU

PART

PA24-1004).

Adjust

the

deformable

tabs

on

the

base

of

the

switch

lever

so

that

the

face

sits

snuggly

against

the

milled

face

of

the

torque

link

when

the

bolt

is

installed.

Verify

the

installation

by

checking

that

the

switch

lever

will

not rotate.

Install

the

links.

Use

the

same

thickness

of

spacer

washer

(3)

between

the

two

links

as

those

removed

1o

maintain

the

correct

wheel

alignment.

Tighten

the

bolts

only

tight

enough

to

allow

no

side-play

on the

links,

yet

free

enough

to

rotate.

Lubricate

the

landing

gear

assembly.

(Refer

to

Lubrication

Chart,

Section

Il

in

the

PIPER

COMANCHIE

SERVICE

MANUAL.

4.7.

Installation

of

the

Main

Landing

Gear

Note

When

assembling

components

of

the

landing

gear,

lubricate

bearings,

bushings

and

friction

surfaces

with

proper

lubricant

as

described

in

Section

Il

of

the

PIPER

COMANCHE

SERVICE MANUAL.

Check

the

landing

gear

support

bearings

(43

and

48) are

clean

and

secure

Install

the

landing

gear

housing

in

the

wheel

well

of

the

wing

Place

a

spacer

washer

(17),

0.035,

P/No

19513-10,

or

criginal

number

of

washers

and

then

the

forward support

fitting

(18)

on the

forward

support

arm

of

the

housing.

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AERONAUTICAL

DESIGN

SERVICE

REPORT

REPORT

NO

PROJECT

990100

PA24-990100-7

Clean

the

threads

of

the

forward-support

attaching

bolt

(AN4-5A)

Item

49,

and

in

the

forward

support

am

of

the

strut

housing

with

a

suitable

solvent.

(This

is

a

new

item

either

supplied

with

the

oleo

housing

or

obtained

from

local

stock)

Apply

LOCTITE

620

to

the

threads

of

the

forward-support

attaching

bolt

using

the

procedures

recommended

by

LOCTITE.

Install

the

forward-support

attaching

bolt

with

the

washer

removed

and

retained

from

the

original

assembly.

Tighten

the

bolt

and

check

the

support

for

freedom

of

rotation.

Check

that

the

head

of

the

bolt

does

not

extend

beyond

the

surface

of

the

forward

surface

fitting.

Secure

the

aft

support

fitting

(11)

to

the

rear

spar

web

with

the

attaching

bolts,

washers,

and

nuts

that

were

removed

from

the

original

installation.

Position

the

main

landing

gear

strut

assembly

in

the

wheel

well

and

attach

the

front

support

filting

to

the

main

spar

web

with the

attaching

bolts

washers

and

nuts

removed

from

the

original

installation.

Using

the

access

hole

behind

the

rear

spar,

insert

the

bungee

tube

(10)

with

washer

(44)

(0.125,

P/N

14843-20)

through

the

rear

support

fitting

and

into

the

rear

strut

arm

using

enough

shim

washers

(12)

between

the

rear

support

fitting

and

the

strut

arm

to

diminish

end

play

of

the

strut

housing.

Position

the

side

brace

support

bracket

(22)

on

the

main

spar

web

and

secure

with

the

attaching

bolts,

and

washers

removed

from

the

original

installation.

Assemble

the

Upper

and

Lower

Drag

Links

(24

and

27)

with

the

pivot

bolt

removed

from

the

original

assembly.

Adjust

the

lower

drag

link

to

a

dimension

6.125

inches

from

the

center

of

the

middle

pivot

bolt

to

the

center

of

the rod

end

bearing.

(Refer

Figure

6-10

of

the

PIPER

COMANCHE

SERVICE

MANUAL)

Install

the

landing

gear

door

retraction

arm

on

the

strut

housing

and

secure

with

the

bolt,

washers,

and

nut

removed

from

the

original

installation.

Attach

the

upper

drag

link

to

the

support

bracket

with

the

clevis

bolt,

washer,

nut

and

cotter

pin

removed

from

the

original

installation.

Attach

the

lower

drag

link

to

the

strut

housing

with

the

bolt,

washers

at

each

side

of

the

bearing,

and

nut

that

were

removed

from

the

original

installation.

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AERONAUTICAL

DESIGN

SERVICE

REPORT

REPORT

NO

PROJECT

9980100

PA24-990100-7

Check

for

clearance

between

the

drag

link

middie

pivot

drag

link

bolt

(26)

and

the

main

landing

gear

cap

strip,

and

for

binding

of

the

lower

drag

link

and bearing

by

retracting

and

extending

the

landing

gear

by

hand.

If

clearance

is

less

than

0.062

inches

between

the

pivot

head

bolt

and

the

spar

cap

strip,

additional

shims

(17)

must

be

added

between

the

strut

arm

and

the

front

support

bracket.

Install

the

Bungee

Arm

Pins

(Qty

2

{New

Item

P/N

PA24-100-8})

in

the

rear

strut

arm

and

safety

with

minimum

0.041

(spec.

MS20995C41)

lock-wire.

(13)

Install

barrel

nut

(46)

in

rear

strut

arm

and

insert

bolt

(9)

with

washer

through

the

bungee

tube

and

tighten.

Check

landing

gear

strut

arm

support

bearings

for

freedom

of

rotation

by

retracting

and

extending

the

landing

gear

by

hand.

Install

attaching

bolt,

and

bungee

chord

roller

in

roller

bracket

(7)

Install

roller

(B)

in

bracket

and

secure

with

pin,

washer

and

cotter

pin.

Install

the

inboard

pulley

(4)

and

bungee

chord

assembly

on

bungee

tool

(P/N

752

998).

Secure

outboard

bungee

chord

bracket

to

its

fitting

aft

of

the

rear

spar.

Place

the

main

landing

gear

in

the

up

position

and

secure

the

inboard

bungee

pulley

to

the

bungee

arm

(10)

with

washers

and

bolt.

Extend

the

landing

gear

and

remove

the

bungee

tool.

Connect

the

retraction

push

pull

cable

(21)

to

the

upper

drag

link

with

attaching

bolt

and

adjust.

(Refer

to

paragraph

6-55

of

the

PIPER

COMANCHIE

SERVICE

MANUAL

for

adjustment

of

the

push

pull

control

cables)

Install

the

assist

spring

(19)

between

the

Bungee

Spring

Bracket

(Jabiru

New

Part

PA24-100-5)

and

the

upper

drag

link.

Install

the

main

landing

gear

down

limit

switch

(25)

and

adjust.

(Refer

to

paragraph

6-53

of

the

PIPER

COMANCHIE

SERVICE

MANUAL

for

adjustment

of

the

landing

gear

down

limit

switches.)

Install

the

landing

gear

safety

switch

(28)

(left

Landing

Gear

Only)

and

adjust.

(Refer

to

paragraph

6-52

of

the

PIPER

COMANCHIE

SERVICE

MANUAL

for

adjustment

of

the

safety

switch.

Connect

the

landing

gear door

retraction

rod

to

the

bracket

on

the

main

landing

gear

strut

housing.

Service

the

oleo

strut

with

fluid

and

nitrogen

(Refer

Oleo

Struts,

Section

|l

of

the

PIPER

COMANCHIE

SERVICE

MANUAL)

REVISION

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AERONAUTICAL

DESIGN

SERVICE

REPORT

REPORT

NO

PROJECT

990100

PA24-990100-7

Cycle

the

undercarriage

up

and

down.

Verify

correct

operation.

Verify

correct

security

and

adequate

clearance

for

the

electrical

leads

and

brake

hoses.

Check

the

main

landing

gear

alignment.

(Refer

to

paragraph

6-35

of

the

PIPER

COMANCHIE

SERVICE

MANUAL

for

instructions

on

checking

the

alignment).

Remove

the

aircraft

from

jacks.

REVISION

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REPORT

NO

AERONAUTICAL

DESIGN

SERVICE

REPORT

990100-SMS

Service

Manual

Supplement

For

Piper

Comanche

Service

Manual

Revisions

Notes

This

report

at

its

latest

revision

status

superseded

all

previous

revisions.

Only

a

total

reprint

of

the

report

promulgates

revisions.

All

ages

bear

the

same

revisions/dale

status

Rev

Revision

Date

|

Details

of

Change

No.

0

20

Sept

06

Original

Issue

1

30ct086

Format

changed

to

include

date

and

revised

footer

format.

1.

Preamble

This

Service

Manual

Supplement

has

been

raised

to

specify

the

servicing

and

maintenance

activities

for

Comanche

Main

Landing

Gear

assemblies

which

are

fitted

with

the

AeroDesigns

PA24-100-00

replacement

Oleo

Housings.

This

supplement

only

contains

information

which

is

associated

with

the

AeroDesigns

Housings

and

needs

to

be

read

in

conjunction

with

the

PIPER

Comanche

Service

Manual

which

contains

instructions

for

all

other

features

of

the

aircraft.

This

supplement

is

to

be

inserted

into

the

Piper

Service

Manual

at

the

beginning

of

Section

6,

when

replacement

Oleo

Housings

are

installed

on

the

aircraft.

Where

the

information

in

this

manual

is

contradictory

with

information

contained

in

the

Piper

Service

Manual

the

Piper

Manual

will

take

precedence

over

all

things

except

those

which

are

explicitly

stated

for

the

Oleo

Housing.

In

those

instances,

this

manual

should

take

precedence.

2.

Description

and

Operation

The

Aeronautical

Designs

PA24-0100

Oleo

Housing

has

been

designed

as

a

replacement

component

for

the

Main

Landing

Gear

Oleo

Housings

identifies

in

Table

#1.

Added

strength

and

different

manufacturing

techniques

have

generated

the

distinctively

different

shape

of

this

housing.

Even

with

this

shape

and

its

increased

bulk,

the

Aero

Designs

component

is

a

direct

replacement

item

on

all

of

the

identified

MLG

Assemblies.

Table

1

Aircraft

Serial

Nos

Piper

Part

No

Applicable

Aero

Designs

P/No

Description

24-1

to0

24-3999

24-4000

to

24-4782

24-4784

to

244803

24-4783

24-4804

and

Up

26-2

and

Up

30-2

and

Up

39-1to

39-135

39-136

and

Up

20752-12

Undercarriage

Housing

PA24-100-01L

—

Main

Gear

-

Port

20752-08

2705300

PA24-100-01R

Undercarriage

Housing

—

Main

Gear

-

Starboard

2079805

24-1

10

24-3999

20752-13

24-4000

to

244782

24-4784

to

244803

20752-09

244783

24-4804

and

Up

26-2

and

Up

30-2

and

Up

39-1

to

39-135

PAGE

1

OF

12

REPORT

NO

AERONAUTICAL

DESIGN

SERVICE

REPORT

990100-SMS

[ |

27053-01

|

39-136

and Up

|

Two

micro-switch

brackets

are

included

in

the

installation

kit

to

accommodate

the

two

different

kinds

of

safety

switches

that

have

been

used

on

different

aircraft.

The

replacement

housing operates

in

exactly

the

same

mode,

and

is

serviced

in

exactly

the

same

manner

as

the

original

housing.

Installation

in

the

aircraft

is

essentially

the

same

except

that

swat

switch

bracket

attachment

and

orientation

are

slightly

different.

The

complete

MLG

assembly

is

shown

in

Figure

#1.

"IFigure

1

Legend

for

Table

#1

PAGE

2

OF

12

]

REPORT

NO

AERONAUTICAL

DESIGN

SERVICE

REPORT

990100-SMS

Item

Description

ltem

Description

1

Main

Gear

Door

20

Bolt

Assembly

2

Bolt

Assembly

21

Push

Pull

Cable

3

Attachment

Bolt

22

Side

Brace

Support

Bracket

4

Bungee

Pulley

23 Pivot

Bolt

5

Bungee

Chord

24

Upper

Drag

Link

6

Bungee

Pulley

25

Down

Limit

Switch

7

Bracket

26 Pivot

Bolt

8

Fitting

27

Lower

Drag

Link

9

Attachment

Bolt

28

Safety

Switch

Late

Model

10

Bungee

Am

29

Door

Retract

Rod

11

Strut

Support

Fitting

-

Rear

30

Upper

Torque

Link

12

Shims

31

Shim

Washers

13

Bungee

Am

Anti-Rotation

Bolts

32

Lower

Torgue

Link

14

Crown

Washer

33

Brake

line

15

Strut

Housing

34

Fork

Assembly

16

Strut

Filler

Valve

35

Brake

Cylinder

Assembly

17

Shims

36

Wheel

18

Strut

Support

Fitting

Front

37

Tyre

19

Assist

Spring

38

Safety

Switch

Bracket

3.

Servicing

Servicing

procedures

specified

in

the

Piper

Comanche

Service

Manual

continue

to

apply

when

this

AeroDesigns

Oleo

Housing

is

fitted

however

additional

inspections

are

required

to

check

features

which

are

unique

to

this

housing

assembly.

The

additional

inspections

specified

in

Figure

2

and

Figure

3

are

to

be

completed

at

each

100-hourly

inspection

of

the

aircraft.

W,

Attachment

Bolts

Visual

Inspection

(Look

for

evidence

of

Movement

«

Look

for

evidence

of

corrosion

&

:

Steel

Pivot

Pin

s

.

\\

=

Visual

Inspection

-

=

2

Look

for

evidence

of

Movement

4

-

»

Look

for

evidence

of

corrosion

Roll

Pin

Visual

Inspection

*

Look

for

evidence

of

Movement

*

Look

for

evidence

of

corrosion

[

IFigure

2

When

evidence

of

movement

is

detected

at

the

bolts

attaching

the

forward

of

aft

pivot

bearing

housings

to

the

airframe

structure

(Figure

#2

refers),

it

is

permissible

to

retension

the

bolts

to

the

following

recommended

limits

in

inch-pounds

(

AN4

50

min, 70

max;

AN5

100

min

,

140

max),

and

note

these

items

for

a

repeat

inspection

at

the

next

100

hourly

inspection.

If

the

bolts

are

loose

on

the

second

inspection

contact

Mr.

Alan

Kerr

at

AeroDesigns

for

evaluation

and

corrective

action.

The

Steel

Pivot

Pin

is

a

shrink

fit

into

the

Oleo

housing.

The

Roll

Pin

functions

as

a

positive

backup

to

lock

the

pivot

pin.

No

movement

of

the

pivot

pin

or

the

roll

pin

relative

to

the

housing

is

permitted.

If

movement

of

PAGE

3

OF

12

]

REPORT

NO

AERONAUTICAL

DESIGN

SERVICE

REPORT

990100.SMS

the

pivot

or

the

roll

pins

in

the

housing

is

detected

then

contact

Mr

Alan

Kerr

at

AeroDesigns

for

an

evaluation

and

corrective

action.

Housing

Visual

Inspection

General

Condition

No

Leaks

No

Cracks

Bolts

(

2

Places)

Check

Security

Lockwire

Intact

Pivot

Move

Wheel

For/Aft

Check

for

Movement

in

Bearing

Figure

3

Movement

of

the

pivots

in

the

bearing

housing

is

checked

by

pushing

and

pulling

on

the

fork

assembly

when

the

aircraft

is

on

jacks

and

the

undercarriage

is

fully

extended.

An

allowable

movement

of

3-mm

measured

at

the

wheel

axle

when

the

gear

is

fully

extended

is

permitted.

|f

more

than

this

amount

of

movement

is

measured,

contact

Mr.

Alan

Kerr

at

Aero

Designs

for

evaluation

and

corrective

action.

4.

Removal

and

Installation

Instructions

Removal

of

the

main

landing

Refer

Figure

4

a)

b)

c)

e)

gear

Oleo

Housing

from

the

aircraft

Place

the

airplane

on

jacks

Disconnect

the

retraction

mechanism

by

pulling

up on

the

release

lever

Retract

the

landing

gear

until

it

hangs

in

the

neutral

position,

by

using

the

emergency

extension

lever

d)

The

5|de

brace

link

assembly

may

be

removed

by

the

following

procedure

iii.

iv.

V.

Disconnect

the

assist

spring,

(This

may

be

accomplished

while

disconnecting

the

push-pull

cable

as

described

in

the

next

step)

Disconnect

the

push-pull

cable

from

the

upper

drag

link

by

removing

attaching

nut,

washer

and

bolt

with

swivel

assembly

(20)

Disconnect

the

gear

down

limit

switch

(25)

by

removing

the

switch

attaching

nut.

Remove

the

side

brace

links

by

removing

the

pivot

bolts

(23)

are

each

end

Remove

side

brace

support

bracket

(22)

from

the

front

spar

by

removing

attaching

bolts

Remove

main

gear

strut

housing

with

components

using

the

following

procedure

.

iv.

V.

Disconnect

the

gear

door

retraction

rod

(29)

from

the

strut

housing

Disconnect

the

brake

line

(33)

and cap

it

to

prevent

dripping

and

contamination

Remove

the

access

panel

aft

of

the

rear

spar

by

removing

the

attaching

screws

Swing

the

landing

gear

enough

to

allow

insertion

of

a

bungee

tool,

P/No

752

998,

between

the

inboard

(4)

and

outboard

(6)

bungee

pulleys

With

tension

relieved

from

the

bungee,

remove

the

inboard

pulley

attaching

bolt

(3)

and

remove

the

bungee

assembly

by

unscrewing

the

outboard

pulley

bracket

(7)

from

its

fitting.

PAGE

4

OF

12

REPORT

NO

AERONAUTICAL

DESIGN

SERVICE

REPORT

990100-SMS

Fork

Assembly

Torque

link

Lower

Spacer

Washers

Bolt

Assembly

Torque

Link

Upper

Piston

Tube

Housing:

Oleo

Strut

Piston

Tube

Bolt

Assembly

alelm

N

o

o

[Alw

N

(=

Bolt

Assembly

11

|

Axle

Nut

12

|

Nut:

Orifice

Tube

13

|

Washers

Back-Up

Ring,

Orifice

Tube

“O"-Ring

15

|

Orifice

Tube

Ring,

Orifice

16

|

Tube

(PA

24-400)

17

|

Orifice

Plate

18

|

Snap

Ring

19

|

Orifice

Tube

‘0"

Ring,

20

|

Piston

Tube

Plug

Plug,

Piston

=

Tube

22

Bearing,

Upper

Piston

Tube

23

|

Pin,

Retaining

24

Bearing,

Lower

Piston

Tube

|

[Figure

4

vi.

Remove

the

bolt

(9)

holding

the

bungee

arm

(10)

to

the

rear

support

fitting

(11)

vii.

Remove

the

two

bungee

arm

anti-rotation

bolts

(13)

viii.

Slide

the

bungee

tube

out

of

the

rear

support

fitting

and

rear

strut

arm

[

PAGE

5

OF

12

AERONAUTICAL

DESIGN

SERVICE

REPORT

REPORT

NO

990100-SMS

ix.

X,

5.

Remove

the

gear

assembly

from

the

wheel

well

by

removing

the

attaching

bolts

holding

the

front

support

fitting

(18)

to

the

front

spar

web.

Remove

the

rear

support

fitting

by

gaining

access

to

the

attaching

nuts

through

the

access

hole

behind

the

rear

spar

and

remove

nuts,

washers

and

bolts.

Cleaning,

Inspection

of

Main

Gear

Oleo

Refer

to

Figure

4.

a)

Clean

all

parts

with

a

suitable

dry

type

cleaning

agent

b)

Inspect

the

main

landing

gear

oleo

assembly

component

for

the

following

Bearings

and

bushing

for

excessive wear

The

Piper

Service

Manual

provides

no

guidance

for

allowable

wear

on

any

of

the

bushings

or

plain

bearings

that

are

used

in

the

MLG

assembly.

The

following

is

provided

for

guidance:

Allowable

Tolerance

|

Allowable

tolerance

tole':\a!l?\(\;?glr?

the

Reference

|

on

Bore

Diameter

of

on

external

internal

Diameter

Mating

Hole

in

the

diameter

of

the

diameter

of

the

housing

bush

b

ush

Ya

0.003

oversize

0.002

undersize

0.003

oversize

5/16

0.003

oversize

0.002

undersize

0.003

oversize

3/8

0.004 oversize

0.003

undersize

0.004

oversize

7116

0.004

oversize

0.003

undersize

0.004

oversize

Ve

0.005

oversize

0.004

undersize

0.005

oversize

vi.

Retaining

Pins

for

wear

and

damage

The

retaining

pins

prevent

the

bungee

arm

from

rotating.

The

machined

tip

of

the

retaining

pins,

fits

into

a

hole

in

the

bungee

arm

and

the

associated

wear

will

be

evident

on

the

machined

tip

of

the

pin

as

shown

in

the

figure

below.

Wear

and

Indentation

on

this

Face

)

=

et

et

.\

_

An

allowable

wear

depth

is

0.020

inches.

Clean

the

face

with

abrasive

paper

to

ensure

that

the

edges

of

any

wear

pattern

are

free

from

burs.

Lock

Rings

for

cracks

and

burrs

This

is

a

visual

inspection

of

the

Lock

Rings

(Circlips),

replace

Lock

ring

is

cracks

or

burs

are

observed.

Cylinder

and

Orifice

Tube

for

corrosion,

scratches,

nicks

and

excess

wear

Allowable

damage

not

to

exceed

0.005

inches

after

damage

has

been

blended.

Orifice

plate

for

hole

restriction

Check

that

the

hole

is

clear

and

free

from

any

debris.

Fork

tube

for

corrosion,

scratches

nicks,

dents,

and

misalignment

No

cracking

which

is

visually

detected

is

allowable.

Scratches

nicks

and

dent

are

acceptable

provided

that

the

depth

of

damage

does

not

exceed

0.005

inches

after

blending.

PAGE

6

OF

12

REPORT

NO

AERONAUTICAL

DESIGN

SERVICE

REPORT

990100-SMS

vii.

Air

Valve

general

condition

Check

that

the

air

valve

is

free

from

corrosion

or

debris

and

that

the

seat

is

free

from

cracks.

Replace

valve

is

defects

are

observed.

6.

Approved

Repairs

Oleo

Housing

FZoneiBiE

:

e

i

Scissor

Link

Bushing

~

Zone

C

Support

~Side

Brace

Attachment

Support

™

,’{

-

N\

:

Zone

A

|

e

N\

-

Consists

of

and

Outside

\J

face

of

flange

and

all

faces

N

of

the

machined

pocket

‘

<

‘

/

\

!

|

,”

;

,?I‘v

/]

.

/

b

L=

7

\

|

Zone

D

A\

o

Pivot

e

Supports

6.1.

Extemal

surface

Zone

A

Zone

A

consists

of

the

material

in

the

flange

and

the

faces

of

the

machined

pockets

on

either

side

of

the

flange.

If

cracking

is

observed,

contact

Mr

Alan

Kerr

at

Aero

Designs

far

an

evaluation and

a

repair

scheme.

Scratches,

nicks,

and

corrosion,

if

present,

can

be

repaired

by

blending

,

provided

that

the

depth

after

bending

does

no

exceed

0.010

inches.

There

is

no

limitation

on

the

surface

area

of

a

blend.

6.2.

Extemal

Surface

Zone

B

and

Zone

C

Zone

B

consists

of

the

material

in

the

boss

into

which

the

scissor

link

bushings

are

inserted,

Zone

C

consists

of

the

material

in

the

boss

into

which

the

side

brace

rod

end

is

inserted.

Cracking

may

be

repaired

by

blending,

provided

that

the

depth

after

blending

does

not

exceed

0.020

inches.

Blending

within

the

bore

must

not

exceed

more

than

25%

of

the

circumference

at

any

one

location.

6.3.

Extemnal

Surface

Zone

D

Zone

D

consists

of

the

housing

material

which

forms

the

boss

which

supports

the

steel

pivot

which

is

located

with

an

interference

fit

into

the

housing.

PAGE

7

OF

12

ﬂ

REPORT

NO

AERONAUTICAL

DESIGN

SERVICE

REPORT

990100-SMS

Cracking

and

corrosion

are

not

permitted

in

this

area.

If

cracks

or

corrosion

is

found

contact

Mr.

Alan

Kerr

at

AeroDesigns

for

evaluation

and

a

repair

scheme.

Nicks

and

scratches

can

be

repaired

by

blending

provided

the

maximum

depth

after

blending

is

less

than

0.020

inches.

6.4.

Intemal

Bore

Likely

damage

to

the

internal

bore

is

expected

to

be

scratches,

gouging,

and/or

corrosion.

Damage

if

this

kind

can

be

repaired

by

smoothing

and

blending

provided

that

the

maximum

depth

of

the

damage

does

not

exceed

0.010

inches,

and

does

nct

extend

more

than

20%

of

the

circumference

of

the

bore

at

any

one

locations.

6.5.

Replacement

of

Wiper

Strips

Individua!

replacement

of

wiper

strips

may

be

accomplished

using

the

instructions

given

in

Section

#5

below

7.

Assembly

of

the

Main

Oleo

Refer

to

Figure

1

a)

Ascertain

that

all

parts

are

cleaned

and

inspected

b)

To

install

the

piston

tube

plug

(21),

first

lubricate

the

plug “O"

Ring

(20)

with

hydraulic

fluid,

(MIL-H-

5606)

and

install

it

on

the

plug.

Lubricate

the

inside

wall

of

the

piston

tube

(8).

Insert

the

plug

into

the

top

of

the

tube,

and

push

it

to

the

fork

end.

Align

the

bolt

holes

as

a

guide.

Drill

a

pilot

hole

and

ream

to

0.250/0.252

inches

through

each

side

of

the

tube

wall.

Remove

burs

from

the

inside

of

the

tube

and

flush

the

tube

with

a

suitable

solvent

to

remove

all

metal

particles.

¢)

If

desired

bond

a

cork

in

the

hole

in

the

bottom

of

the

fork

body

to

prevent

dirt

from

entering

between

the fork

and

the

tube

d)

To

assemble

the

components

of

the

orifice

tube

(19),

insert

the

orifice

plate

(17)

into

the

bottom

of

the

tube

and

secure

with

a

snap

ring,

(18).

Install

ring

(16)

(PA24-400)

only

on

the

lower

end

of

the

tube.

e)

Trial

fit

the

orifice

tube

in

the

oleo

housing

(7)

to

verify

correct

crush

on

the

o-ring

by

inserting

the

tube

up

through

the

housing.

With

the

end

of

the

tube

exposed

through

the

top

of

the

housing,

install

the

“O"

ring

(15),

back-up

ring

(14),

and

Crown

Washer

(New

Part

AeroDesigns

PA24-100-3.

Verify

that

at

least

1-mm

of

crush

is

available

before

fitting,

and

locknut

(12).

Tighten

only

finger

tight.

f)

Toinstall

the

orifice

tube

in

the

oleo

housing

(7),

insert

the

tube

up

through

the

housing.

With

the

end

of

the

tube

exposed

through

the top

of

the

housing,

install

the

"O”

Ring

(15),

backup

ring

(14)

washer

(13)

and locknut

(12).

Tighten

locknut

only

finger

tight

at

this

time.

g)

Assemble

the

components

of

the

piston

tube

(8)

on

the

tube

by

placing,

in

order,

the

snap

ring

(29),

washer

(28),

lower

bearing

(24)

with

the

outer

and

inner

“O"

Rings

(26

and

25)

and

upper

bearing

(22).

Align

the

lock

pin

hole

of

the

upper

bearing

with

the

pin

holes

in

the

tube

and

install

pins

(23)

h)

Lubricate

the

wall

of

the

cylinder

oleo

housing

(7)

and

piston

tube

(8),

and

carefully

insert

the

tube

assembly

into

the

housing,

guiding

the

orifice

tube

(19}

into

the

piston

tube

until

the

snap

ring

(29)

can

be

installed

in

the

annular

slot

at

the

lower

end

of

the

housing.

i)

Atthe

top

of

the

housing,

tighten

the

orifice

tube

locknut

(12).

(Should

it

be an

impossibility

to

tighten

the

locknut

due

to

the

orifice

tube

rotating

with

the

nut,

withdraw

the

piston

tube

assembly

from

the

cylinder

and,

while

tightening

the

nut,

secure

the

orifice

tube

with

the

use

of

a

1-1/2

x

3/16

inch

drag

link

socket

held

in

the

slot

at

the

lower

end.

Check

that

the

orifice

tube

is

centered

in

the

cylinder

and

then

reinstall the

piston

tube

assembly.

i)

Install

the

wiper

strip

(27),

slide

the

washer

(28)

into

position

and

secure

the

assembly

with

snap

ring

(29)

k)

Ascertain

that

the

bushings

are

installed

in

the

upper

and

lower

torque

links

(

&

and

2)

and

then

install

the

links.

The

torque

link

bolt

assemblies

(6

and

10)

should

be

lubricated

and

installed

with the

flat

of

the

bolt

head

hex

adjacent

to

the

milled

stop

of

the

wide

end

of

the

link.

(

Use

same

thickness

of

spacer

washer

(3)

between

the

two

links

as

those

removed

to

maintain

correct

wheel

alignment.)

Tighten

the

bolts

only

tight

enough

to

allow

no

side

play

in

the

links,

yet

be

free

to

rotate

I)

Lubricate

the

gear

assembly

per

lubrication

chart

in

Section

|l

of

the

Piper

Comanche

Maintenance

Manual.

PAGE

8

OF

12

REPORT

NO

AERONAUTICAL

DESIGN

SERVICE

REPORT

990100-.SMS

a)

c)

d)

Compress

and

extend

the

strut

several

times

to

ascertain

that

the

strut

will

fall

freely.

The

weight

of

the

gear

wheel

and

fork

should

allow

the

strut

to

extend.

Service

the

oleo

with

fluid

and

air

using

the

procedures

given

in

Section

Il

of

the

Piper

Comanche

Maintenance

Manual

Check

the

main

gear

alignment

using

the

procedure

given

in

paragraph

6.35

of

the

Piper

Maintenance

Manual.

Remove

the

airplane

from

jacks

Installing

the

Main

Landing

Gear

into

the

Aircraft

Note

When

assembling

components

of

the

landing

gear,

lubricate

bearings,

bushings

and

friction

surfaces

with

proper

lubricant

as

described

in

Section

Il

of

the

PIPER

COMANCHE

SERVICE MANUAL.

Check

the

landing

gear

support

bearings

(43

and

48) are

clean

and

secure

Install

the

landing

gear

housing

in

the

wheel

well

of

the

wing

Place

a

spacer

washer

(17),

0.035,

P/No

19513-10,

or

ecriginal

number

of

washers

and

then

the

forward

support

fitting

(18)

on

the

forward

support

arm

of

the

housing.

Clean

the

threads

of

the

forward-support

attaching

bolt

(AN4-5A)

ltem

49,

and

in

the

forward

support

arm

of

the

strut

housing

with

a

suitable

solvent.

(This

is

a

new

item

either

supplied

with

the

oleo

housing

or

obtained

from

local

stock)

Apply

LOCTITE

620

to

the

threads

of

the

forward-support

attaching

bolt

using

the

procedures

recommended

by

LOCTITE.

Install

the

forward-support

attaching

bolt

with

the

washer

removed

and

retained

from

the

original

assembly.

Tighten

the

bolt

and

check

the

support

for

freedom

of

rotation.

Check

that

the

head

of

the

bolt

does

not

extend

beyond

the

surface

of

the

forward

surface

fitting.

Secure

the

aft

support

fitting

(11)

to

the

rear

spar

web

with

the

attaching

bolts,

washers,

and

nuts

that

were

removed

from

the

original

installation.

Position

the

main

landing

gear

strut

assembly

in

the

whee!

well

and

attach

the

front

support

fitting

to

the

main

spar

web

with

the

attaching

bolts

washers

and

nuts

removed

from

the

original

installation.

Using

the

access

hole

behind

the

rear

spar,

insert

the

bungee

tube

(10)

with

washer

(44)

(0.125,

P/N

14843-20)

through

the

rear

support

fitting

and

into

the

rear

strut

arm

using

enough

shim

washers

(12)

between

the

rear

support

fitting

and

the

strut

arm

to

diminish

end

play

of

the

strut

housing.

Position

the

side

brace

support

bracket

(22)

on

the

main

spar

web

and

secure

with

the

attaching

bolts,

and

washers

removed

from

the

original

installation.

Assemble

the

Upper

and

Lower

Drag

Links

(24

and

27)

with

the

pivot

bolt

removed

from

the

original

assembly.

Adjust

the

lower

drag

link

to

a

dimension

6.125

inches

from

the

centre

of

the

middle

pivot

bolt

to

the

centre

of

the

rod

end

bearing.

(Refer Figure

6-10

of

the

PIPER

COMANCHE

SERVICE

MANUAL)

Install

the

landing

gear

door

retraction

arm

on

the

strut

housing

and

secure

with

the

bolt,

washers,

and

nut

removed

from

the

original

installation.

Attach

the

upper

drag

link

to

the

support

bracket

with

the

clevis

bolt,

washer,

nut

and

cotter

pin

removed

from

the

original

installation.

Attach

the

lower

drag

link

to

the

strut

housing

with

the

bolt,

washers

at

each

side

of

the

bearing,

and

nut

that

were

removed

from

the

original

installation.

Check

for

clearance

between

the

drag

link

middle

pivot

drag

link

bolt

(26)

and

the

main

landing

gear

cap

strip,

and

for

binding

of

the

lower

drag

link

and

bearing

by

retracting

and

extending

the

landing

gear

by

hand.

If

clearance

is

less

than

0.062

inches

between

the

pivot

head

bolt

and

the

spar

cap

strip,

additional

shims

(17)

must

be

added between

the

strut

arm

and

the

front

support

bracket.

Install

the

Bungee

Arm

Pins

(Qty

2

{New

ltem

P/N

PA24-100-8})

in

the

rear

strut

arm

and

safety

with

minimum

0.041

(spec.

MS20995C41)

lock-wire.

(13)

Install

barrel

nut

(48)

in

rear

strut

arm

and

insert

bolt

(S)

with

washer

through

the

bungee

tube

and

tighten.

Check

landing

gear

strut

arm

support

bearings

for

freedom

of

rotation

by

retracting

and

extending

the

landing

gear

by

hand.

Install

attaching

bolt,

and

bungee

chord

roller

in

roller

bracket

(7)

PAGE

9

OF

12

]

REPORT

NO

AERONAUTICAL

DESIGN

SERVICE

REPORT

990100-SMS

w)

Install roller

(6)

in

bracket

and

secure

with

pin,

washer

and

cotter

pin.

x)

Install

the

inboard

pulley

(4)

and

bungee

chord

assembly

on

bungee

tool

(P/N

752

998).

y)

Secure

outboard

bungee

chord

bracket

to

its

fitting

aft

of

the

rear

spar.

z)

Place

the

main

landing

gear

in

the

up

position

and

secure

the

inboard

bungee

pulley

to

the

bungee

arm

(10)

with

washers

and

bolt.

aa)

Extend

the

landing

gear

and

remove

the

bungee

tool.

bb)

Connect

the

retraction

push

pull

cable

(21)

to

the

upper

drag

link

with

attaching

bolt

and

adjust.

(Refer

to

paragraph

6-55

of

the

PIPER

COMANCHIE

SERVICE

MANUAL

for

adjustment

of

the

push

pull

control

cables)

cc)

Install

the

assist

spring

(19)

between

the

Bungee

Spring

Bracket

(AeroDesigns

New

Part

PA24-100-

5)

and

the

upper

drag

link.

dd)

Install

the

main

landing

gear

down

limit

switch

(25)

and

adjust.

(Refer

to

paragraph

6-53

of

the

PIPER

COMANCHIE

SERVICE

MANUAL

for

adjustment

of

the

landing

gear

down

limit

switches.)

ee)

Install

the

landing

gear

safety

switch

(28)

(left

Landing

Gear

Only)

and

adjust.

(Refer

to

paragraph

6-

52

of

the

PIPER

COMANCHIE

SERVICE

MANUAL

for

adjustment

of

the

safety

switch.

ff)

Connect

the

landing

gear

door

retraction

rod

to

the

bracket

on

the

main

landing

gear

strut

housing.

gg)

Service

the

oleo

strut

with

fluid

and

nitrogen

(Refer

Oleo

Struts,

Section

Il

of

the

PIPER

COMANCHIE

SERVICE

MANUAL)

hh)

Cycle

the

undercarriage

up

and

down.

Verify

correct

operation.

Verify

correct

security

and

adequate

clearance

for

the

electrical

leads

and

brake

hoses.

i)

Check

the

main

landing

gear

alignment.

(Refer

to

paragraph

6-35

of

the

PIPER

COMANCHE

SERVICE

MANUAL

for

instructions

on

checking

the

alignment).

i}

Remove

the

airplane

from

jacks.

9.

Replacement

of

Wiper

Strip

on

Landing

Gear

Struts

a)

Place

aircraft

on

jacks

b)

Jack

the

airplane

only

high

enough

to

take

weight

off

the

gear

¢)

Release

the

air

pressure

from

the

strut

by

depressing

the

valve

core

pin

until

the

pressure

has

diminished.

d)

Using

snap

ring

pliers,

disengage

the

snap

ring

from

the

annular

slot

in

the

oleo

housing,

and

allow

it

to

lay

at

the

lower

end

of

the

piston

tube

along

with

the

wiper

strip

retainer

washer

e)

Remove

the

old

wiper

strip

from

the

housing,

and

clean

and

inspect

the

housing

to

determine

that

no

pieces

remain

in

it

f)

Wipe

the

piston

tube

and

check

for

any

abrasions

which

may

damage

the

new

part.

Polish

the

tube

to

remove

any

abrasions

found.

g)

A

new

wiper

strip

should

be

cut

straight

across

and

a

little

longer

than

is

needed

to

circle

the

piston

tube

h)

Insert

eh

new

wiper

strip

up

into

the

oleo

housing

with

the

tapered

edge

down.

Slide

the

retainer

washer

and

snap

ring

up

the

piston

tube

and

insert

them

into

the

oleo

housing. Using

snap

ring

pliers

to

compress

the

snap

ring,

install

it

into

the

annular

slot

in

the

oleo

housing.

i)

Inflate

the

oleo

strut

in

accordance

with

the

instructions given

in

Section

Il

of

the

Piper

Servicing

Manual,

and

remove

the

airplane

from

jacks.

10.

Adjustment

of

Landing

Gear

Safety

Switch

Adjustment

of

the

landing

gear

safety

switch

when

the

AeroDesigns

Housing

is

installed

uses

the

same

procedures

as

was

used

for

the

original

Piper

Housing.

Refer

Paragraph

6.52

of

the

Piper

Comanche

Service

manual

11.

Adjustment

of

the

Gear

Down

Limit

Switch

Adjustment

of

the

landing

gear

safety

switch

when

the

AeroDesigns

Housing

is

installed

uses

the

same

procedures

as

was

used

for

the

original

Piper

Housing.

Refer

Paragraph

6.53

of

the

Piper

Comanche

Service

manual

PAGE

10

OF

12

REPORT

NO

AERONAUTICAL

DESIGN

SERVICE

REPORT

990100.SMS

Annex

A

Figure

#A-1shows

the

Oleo

Housing

and

associated

components.

Figure

#A-2

is

a

view

of

the

Safety

Switch

Bracket,

used

on

the

LHS

Main

Landing

Gear

and

replaces

the

existing

switch bracket.

AIBNE

X

127

7

e

©

snc.f:

/

Switch

Brackst

X4/

S

PA24.100-2

Bungee

Sprng

Brackst

¥

&

|

Appicatie

LMS

Criy

PAZes00-5

.

|

J/TBUNC

X

1127

/'

UNBRAKO

SHCS

/

7

Oy

2Rl

Uity

&

Y\

\

\

‘\

AN4-SA

.

\_

Qly

1

Required

\

\

\

Crerwn

Wesher

\_LHS

SRS

—

.

PA21O03

Figure

A-1

Oleo

Assembly

N

/

\),\'

-

j’,’,’_.'f:"’S/\)’vitch

Lever

-

P/No

PA24-100-4

Qty

1

Required

T~

_

LHSONLY

Figure

A-2

Safety

Switch

Bracket

Table

#1

provides

a

Listing

of

parts

Shown

in

Figure

A-1

l

PAGE

11

OF

12

REPORT

NO

AERONAUTICAL

DESIGN

SERVICE

REPORT

990100-SMS

PA24-100-0R

1

Oleo

Housing

PA24-100-0L

Bungee

Spring

e

-100-

Bracket

PA24-100-5 PA24-100-5

1

Switch

Bracket

PA24-100-2

Not

Required

1

(LHS)

Alternate

Switch

.

"

PA24-100-12

Not

Required

1

(LHS)

Bungee

Arm

Pin

PA24-100-8 PA24-100-8

2

Crown

Washer

PA24-100-5

PA24-100-5

1

LHS

-6

Cap

Screw

3/16UNC-|

3/16UNC-

|

RHS

—4

Screw

AN4-5A

AN4-5A

1

Micro

SWICh

TP

|

pA24-1004

|

NotRequired

|

1(LHS)

PAGE

12

OF

12