Mooney M20M Referenzhandbuch

alrg~

SUBJECI:

MOONEY

VOLT

AIRCRAFT

ELECTRICAL

WIRING

MODIFICATION,

(Revision

applicable

M20J

and

M20K

aircraft

only

and

still

effect

for

those

model

aircraft.

Revision

applicable

M20M

only--).

MODEUS/N

AFFECTED:

MOONEY

MODEL:

M20M

S/N

27-0001

THRU

27-0052

TIME

COMPLIANCE:

NDCT

SCHEDULED

MAINTENANCE

INTRODUCTION:

THE

VOLT

ELECTRICAL

SYSTEM

WIRED

MANNER

THAT

RENDERS

THE

OVERVOLTAGE

WARNING

LIGHT

THE

ANNUNCIATOR

PANEL

ASSEMBLY

INOPERATIVE

SHOULD

ALTERNATOR

OVERVOLTAGE

OCCUR.

THIS

PROVIDES

INSTRUCTIONS

REWIRE

PORTION

THE

CIRCUTT

ENABLE

THIS

WARNING

LIGHT.

INSTRUCTIONS:

Disconnect

voltage

regulator

(for

Altemator

#1)

iocated

under

the

instrument

panel

the

co-pilot’s

side.

Locate

existino

~Mre

number

M-PA13A18;

push

wire

out

regulator

main

harness

receptacle.

Cut

from

wire,

M-PA13A18;

cap

wire

end

using

AMP

324485

wire

cap

(included

kit).

Remove

Glareshield

per

instructions

the

appropn’ate

manual,

Section

39-10-01.

Insert

wire

number

M-PA13B18

(included

-1B

kit)

into

voltage

regulator

receptacle

and

reconnect

regulator.

Route

wire

number

M-PA13B18

along

existing

wire

bundle

annunciator

panel

connector

(M-WT103A).

Secure

with

lacing

cord

TyRaps.

Locate

wire

number

M-WT02A20

connected

annunciator

panel

connector,

M-WT103A,

and

cut

M-V1~02C\20

wire

inches

back

from

connector.

Use

AMP

320559

wire

splice

re-connect

wire

number

M-WT02A20

and

tile

unconnected

end

new

wire

M-PA13B18

(SEE

nGUREM20-245-1B).

For

No.

Altemator:

repeat

Steps

through

with

regulator

but

wire

numbers

M-PA33A18

(Steps

and

M-PA33B18

(Step

5);

Route

unconnected

end

wire

number

M-PA33B18

vacuum

switch

back

Artifical

Horhon

and

connect

"white"

terminal.

10.

Remove

the

amp

Annunciator

C/B

and

replace

with

the

amp

C/B,

included

-1B

kit.

Functionally

check

operation

altemator(s)

per

POH/AFM,

Section

IV,

Normal

Procedures,

Before

Takeoff

12.

Enter

compliance

note

aircraft

logbook

and

return

aircraft

service.

WARRANIY:

This

kit

should

ordered

from

the

Mooney

Service

Center

your

area.

Normal

warranty

billing

policies

will

affect

for

this

kit.

MooneyAircraft

Corporation

will

allow

2.0

hourslabor

accomplish

this

modification

completed

Warranty

Claim

received

within

180

days

from

the

date

this

SeM’ce

Bulletin.

REFERENCE

DATA:

N/A

PARTS

LIST:

KIT

P/N

SB-M20-245-1B

(M20M

only)

DESCRIPTION

.QK

M-PA~3B18

WIRE

ASSEMBLY

M-PA33B18

WIRE

ASSEMBLY

324485

WIRE

CAP

(AMP)

320559

WIRE

SPLICE

(AMP)

7277-2-2

C/B,

ANNUNCIATOR

AMP)

GURESI

TABLES:

SPUCE

-I

FIGURE

M20-24518

(M20M

only)

THIS

SERVICE

BULLETIN

FAA

APPROVED

FOR

ENGINEERING

DESIGN.

SUBJECT:

MOONEY

TLS,

M20M.

INCREASED

TAKEOFF

WEIGHT

RETROFIT

MODEL

S/N

AFFECTED:

MOONEY

MODEL

M20M.

SIN

27-0001

THRU

27-0052

TIME

COMPLIANCE.

OWNERS

DISCRETION

BUT

MANDATORY

AIRCRAFT

FLOWN

TAKEOFF

WEIGHT

ABOVE

3200

POUNDS.

INTRODUCTION:

Some

aircraft

owners

have

expressed

desire

increase

the

useful

load

the

M20M

aircraft.

Mooney

Aircraft

Corporation

offering

the

retrofit

procedures

this

Service

Bulletin

accomplish

this.

There

are

several

areas

that

will

modified

order

for

the

aircraft

flown

the

increased

takeoff

weight

3368

pounds.

recommended

that

the

aircraft

brought

back

Mooney

Aircraft

Corporation

for-the

retrofit.

Scheduling

the

retrofrt

action

will

co-ordinated

the

Product

Support

Department,

telephone

(512)

896-6000.

INSTRUCTIONS:

Remove

and

replace

the

Main

Landing

retraction

truss

assembly,

P/N

520024501

(UH)

and

-502

(R/H)

per

M20M

Service

and

Maintenance

Manual

No.

150,

Section

32-10-00.

The

new

truss

will

identified

"A-2"

metal

stamp

the

fork

lover

center

link)

and

ink

stamp

"A-2"

after

paint.

Check

for

proper

operation

and

rigging

landing

gear

retraction

system

after

replacement

retraction

truss

assembly

per

No.

150.

Section

32-30-00.

Remove

the

ABS

flap

hinge

fairings.

each

wing)

drilling

out

the

rivets

fairing

flanges

and

the

side

rivet

each

outboard

fairing.

The

two

inboard

fairings

have

screws

attaching

them

the

fuselage

belly

fairing

and

one

screw

(inboard

side)

attaching

ABS

fairing

the

inboard

wing

flap

hinge

arm

aluminum

fairing.

All

ABS

flap

hinge

fairings

will

modified

pn~or

re-installation.

(See

Step

below)

Remove

flap

gap

seals,

P/N

210374-001

pc)

-003

pcs),

from

left

wing

and

P/N

210374-002

pc)

-004

pcs),

from

right

wing

by:

(1)

Dn’ll

out

the

lower

forward

row

rivets

holding

forward

edge

aluminum

gap

seal

on.

(2)

Lowerfiaps,

drill

out

row

rivets

holding

aluminum

channels,

P/N

210375-1

pc)

and

-003

pcs)

from

each

wing

(Reference

Figure

M20-248-1).

Remove

the

flap

gap

seals

with

the

channels

still

attached.

The

AVEX

1601-0401

rivets

being

drilled

out

will

leave

portions

the

rivet

inside

the

wing.

THESE

NEED

REMOVED.

Enlarge

the

existing

No.

hole

outboard

each

aft

rib

(rib

rivet

line

can

seen

wing

skins)

.250

hole

holes

each

wing).

Forcefully

use

hand

rubber

malletto

hit

wing

skin

area

(DO

NOT

DAMAGE

SKINS)

and

magnet

move

rivet

residue

toward

.250

hole

and

remove

all

pieces,

with

magnet,

through

hole.

This

should

done

between

each

rib

bay.

After

all

drilled

rivet

residue

removed.

Install

A10-80

R’Nnuts

each

enlarged

hole.

(16

places)

Trim

ABS

flap

hinge

fairings.

P/N

210398-005

(LH)

-006

(RH)

each

side)

inboard,

P/N

210379-009

(LH)

-010

(RH)

each

side)

mid,

and

P/N

210379-011

-012

each

side)

outboard,

per

Figures

M20-248-2A

28.

new

hole

will

required

outboard

’side

wall"

each

middle

ABS

fairing,

now

identified

P/N

210379-013

(LH)(2

ea)

074

(RH)(2

ea)

match

tooling

hole

the

two

middle

wing

flap

hinge

arm

aluminum

fairings,

P/N

210106,

wing).

Reference

Figure

M20-248-3

for

basic

instructions

drill

holes.

NOTE:

Outboard

hole

middle

inboard

iairings

will

require

enlarging

to.189

(No.

hole)

M835207-263

screw

can

used

the

A10-80

rivnut

secure

fairing

fiange.

Re-install

each

modified

fairing

using

appropriate

existing

rivet

holes

wing

skins

that

match

remaining

hole

flange

each

ABS

hinge

fairing

and

new

hole

match

tooling

hole

wing

flap

hinge

arm

fairings.

Use

AVM

1601-0410

(or

equivalent)

blind

rivets

and

MS35207-263

screws

attach

ABS

fairings.

M20-248

DATE

Page

10.

Use

AVD:

601-0410

rivets

(59

each

row,

minus

ABS

fairing

attach

holes

and

enlarged

holes

for

rivnuts))

fill

remaining

holes

wing

skins

drilled

out

dun’ng

removal

gap

seals

and

channels.

Reference

Figure

M20-248-1.

install

MS35207-263

screws

all

other

enlarged

holes

seal

wing

skin

area.

CTotal

(16)

MS35207-263

screws

are

required

for

all

enlarged

holes.)

12.

Repainting

the

now

exposed

wing

flap

gap

area

will

required.

Contact

Mooney

Service

Parts

Department

for

paint

color

for

aircraft

Sen~al

Number.

13.

Remove

existing

airspeed

indicator,

P/N

820308-527,

and

replace

with

new

airspeed

indicator,

P/N

820308-531,

included

inthis

kit;

incoporates

new

airspeed

markings

for

the

increased

weight

performance.

14.

After

airspeed

indicator

has

been

replaced

and

all

lines

secured,

perform

pitot/static

check

for

leaks.

15.

Remove

the

OPERATING

UMITATIONS

placard

from

pilot’s

side

panel

and

replace

with

new

OPERATING

UNIITAIIONS

placard,

P/N

150080-980,

included

kit.

16.

Enter

compliance

note

AVC

log

book,

insert

AFM

Supplement

into

POH/AFM

and

return

aircraft

service.

WARRANTY:

Mooney

Aircraft

Corporation

will

perforn

all

retrofit

action

the

factory

service

facility.

Aircraft

owners

will

need

contact

the

Product

Support

Department,

(512)

896-6000

make

arrangements

for

scheduling

aircraft.

REFERENCE

DATA:

N/A

PARTS

LIST:

KITPARTNUMGER

M20-248-1

ITEM

P/N

DESCRIPTION

QT/.

520024-501

(A-2)

RETRACT

TRUSS

ASSY,

520024-502

(A-2)

RETRACT

TRUSS

ASSY,

820308-531

AIRSPEED

INDICATOR

150080-980

PLACARD

1601-0410

RIVET.

AVEX

240

0-80

RIVNUT

.16

MS35207-263

SCREWS

.16

NIA

AFM

SUPPLEMENT

M20-248

FIGURES/

TABLES:

See

Figures

pages.

M20-248

DATE3-20-90

Page

MS20600AD4

(67

PLCS)

REPLACE

WITH

16019410

AVEX

RIVETS

DRILL

THIS

ROW

RIVETS

OUT.

240014

FLAP

ASSY

210375

CHANNELS

MS20470AD4

(61

PLCS)

~210374

NOT

DRILL

THESE

RIVETS

OUT.

MS20600AD4

FLAP

GAP

SEALS

(61

PLCS)

EXTEND

FLAPS

AND

DRILL

OUT

UPPER

ROW

RIVETS

REPLACE

WITH

1601-0410

AVEX

RIVETS

HOLDING

CHANNELS

ON.

DRILL

MIS

ROW

RIVETS

OUT.

FIGURE

M20-248-1

TRIM

EXISTING

ABS

FAIRINGS

DIMENSIONS

SHOWN.

DOTrrD

LINES

INDleArr

UNTRIMMED

CONFIGURAT;IPH

3-CS

~.Z5

\.2J

-009

(SHOWN)

210379

FAIRINGS

’------I

-011

(SHOWN)

-olo

(092)

-012

(OPP)

OFa\n\NC~>

NEW

CONFKiURATION

PIK

FA\RI~G

OPP

FIGURE

M20-248-2A

M20-248

DATE

Page

FAIRING

Slu2-I

210398-005(SHOWN)

-006

(gpp)

0-~

o~c;

NEW

CONFIGURATION

PIK

FIGURE

M20-248-28

~VLX

160~-M\D

(J)

,*L~C

4P~C

I I

klS35207-263

1´•11

C.12~

DI~

Z1010CI

’~b

Wow

hv~x

-14

OCe

16019410

Rtvrr.

-F

I~-ts

-I~

-\4´•

orr

U.L

--IcO~o

*LI

~LI-

Izcn~

COD~\huo

UP)

~De

FIGURE

M20-248-3

SUBJECT:

MOONC/

M20M

ENGINE

MOUNT

HEAT

SHIELD

MODEU

SIN

AFFECTED:

27-0001

THRU

27-0129

TIME

COMPLIANCE:

WITHIN

NMT

OPERATING

HOURS

INTRODUCTION:

There

have

been

occasions

that

the

engine

mount,

the

vicinity

the

turbocharger,

has

had

paint

scorched

missing

due

exhaust

temperatures.

The

steel

tubing

may

show

evidence

heat

and

need

maintenance

action.

The

heat

shidd

and

associated

components

this

kit

will

reduce

this

temperature

action.

INSTRUCTIONS:

Remove

upper

and

lower

ccwling

per

M20M

Section

71-10-00.

Locate

the

area

the

engine

mount

shown.

(See

Figure

M20-251-1

for

location)

Inspect

all

engine

mount

tubes

dose

proximity

the

for

evidence

heat

damage.

Re~iir

any

damage

per

appropriate

AC43-13

procedures

M20M

manual,

Chapter

51.

Lightly

sand,

and

repaint

with

high

temperature

paint,

any

tubes

showing

evidence

heat.

Install

630071-001

shield

using

two

each

630071-003

damp

assemblies

and

appropriate

attaching

hardware.

(Reference

Figure

MM251-1

for

proper

location

and

orientation

the

engine

mount

tube.

Re-install

lower

and

upper

cowling

per

M20M

Section

71-11-00.

Enter

compliance

statement

Aimame

log

book

and

retum

aircraft

service.

WARRANP~

Mooney

Aircraft

Corporation

will

allow

0.7

hours

labor

install

the

components

this

kit

The

kit

can

ordered

through

the

nearest

Mooney

Service

Center.

Warranty

credit

will

allowed

forthe

kit

necessary

paperwork

received

Service

Parts

within

180

days

the

date

this

Service

Bulletin

REFERENCE

DATA

N/A

PARTS

USTr

KIT

PART

NUMBER

-SB

M20-251-1

ITEM

P/N,,....

DESCRIPTION

.QTY

630071-001

SHIELD

630071~03

CLAMP

ASSY

AN3-6A

BOLT

AN960-10

.WASHER

MS21

042-3

NUT

FIGURESI

TABLES:

REFER

FlGURE

M20-251-1

~-ci.

-T

SERVICE

BULLETIN

M20-251

DATE:

4-10-92

Page

i´•/´•l~

590048

ENGINE

NOUNT

CUUP

ASSY.

530071-003

REOWRED)~

0.00

SHIELD

MM1M2-3

HUI

AN950-10

WASHER

/-530071-001

SHIEU)

TOP

VIEW

630371-003

Ifi~

590048

PICINE

.UOUNI

REaVatEO)

-~3

sylml-atn

4lmo

AN3-6A

BOLT

AN860-10

WASHER

MS21042-3

NLIF

SECTION

A-A

ROTATED

550

PUIEIE

~GINE

LIDUNI

TUBE

ii~----_,

~iRREWW.

(RD)

630135

PIPE

-i

~Jm

´•ti

SIDEVIEW

FIGURE

M20-251-1

SUBJECT:

M20M

LANDING

GEAR

RIGG)NG

INSPECTION

AND

MODIFICATION.

MODEU

S/N

AFFECTED:

M20M

S/N

27-0107

THRU

27-0147

(S/N’s

27-0115,

27-0123,

27-0127,

27~131,

27-0137,

27-0142,

27-0144,

27-0150

HAVE

HAD

INSTRUCTIONS

ACCOMPLISHED).

TIME

COMPLIANCE:

WlTHlN

NMT

FLIGHT

HOURS

NDCT

SCHEDULED

MAINTENANCE.

Some

aircraft

within

the

above

S/N

block

have

experienced

landing

gear

inner-door

malfunc-

.tions.

This

has

not

caused

difficulty

with

the

retraction/extension

cycle

any

the

cases.

Maintenance

inspec-

tions

have

found

that

some

the

mechanism

components

have

gone

beyond

normal

tolerance.

Replacement

some

ofthe

components

recommended.

eliminate

the

possibility

exceeding

tolerances,

mechani-

cal

stop

has

been

developed

installed

the

wheelwells.

The

instructions

this

Service

Bulletin

and

components

Kit

wilt

allow

field

personnel

retrofit

applicable

aircraft.

INSTRU~TIONS:

Raise

aircraft

jacks

per

Service

and

Maintenance

h;l)

manual,

Section

71-10-00.

Remove

composite

belly

skins

per

manual,

Section

53-30-00.

Perform

Landing

Gear

dperational

Inspection

per

manual,~Section

32-30-01,

revised

March,

1993.

main

landing

gear,

replace

bearings

(B-47)

and

bushings

(914020-161)

bellcrank

(2).

Replace

rods

(5),

(6),

attaching

pins

and

hardware.

Inspect

press

fit

pins

bellcranks

replace

worn.

Re-n’g

entire

landing

gear

system

per

manual,

Section

32-30-02,

revised

March,

1993

Operational

In-

spections

showany

discrepancies.

NOTE

Instructions

this

Service

Bulletin

are

used

conjunction

with

M20M

Service

and

Maintenance

Manual,

No.

150

Chapter

32,

revised,

March,

1993.

When

landing

gear

system

has

been

n’gged

and

preload

correctly

set,

the

inboard

landing

gear

door

have

mechanical

stop

incorporated

into

the

system

per

the

following

instructions:

Aircraft

still

jacks.

Landing

gear

down

and

locked.

Locate

the

two

rivets

whedwells

that

are

just

forward

the

inboard

gear

door

hinge

(9)

attaching

rivets

(Ref.

Fig

M20-254-1).

This

the

location

for

the

550075-501

stops

(7)

installed.

Disconnect

Inboard

Gear

doors.

Carefully

drill

off

the

two

rivet

heads

sides;

punch

rivets

out.

NOTE

550075501

stop

(7)

has

two

#40

pilot

holes

flange.

some

instances,

doe

manofacturing

toleran-

ces,

the

pilot

holes

may

not

align

exactly

with

both

drilled

holes

wing

rib.

this

the

case,

determine

which

ofthe

two

holes

stop

fiange

viill

create

the

better

alignment

the

stop

bolt

head

(8)

with

the

bellcrank

(4)

arm.

Use

this

hole

the

’primary"

attachment

hole,

Drill

"primary"

attachment

hole

size

(i5~20

dn’ll)

each

stop.

Cleco

stops

(7)

place,

"primary"

attach

hole

only,

head

bolt

(8)

stop

aligns

with

arm

inboard

gear

door

bellcrank

(4)

that

spring

(1)

attached

to.

NOTE

acceptable

chamfer

rear

edge

Range,

stop,

that

rests

against

wing

rib

bucked

heads

rivets

interfere

with

proper

alignment

stop

bolt

head

and

bellcrank

arm.

Chamfer

only

required

clearrivet.

10.

When

stop

(7)

decoed

proper

position,

drill

second

attach

hole

stop

Range

size

(#20

drill),

back

drilling

through

e>dsting

"non-primary"

rivet

hole.

Deburr

hole

Range

and

cieco

position.

Make

sure

head

bolt

(8)

stop

aligns

(directly

centered)

with

arm

bellcrank

(4).

SERVICE

BULLETIN

M20-254

DATE:

4-1-93

Page

lNSTRUCTIONS:

(con’t)

11.

Rivet

stops

t/),

P/N

550075-501,

each

wheelwell

the

location

descn’bed

steps

above

using

rivets

included

this

kit.

Re-attach

Inboard

Gear

doors

before

cycling

landing

gear

for

following

steps.

Leave

spring

(1)

attached

clevis

inboard

door

bellcrank

(4).

Bolt

head

(8)

should

screwed

all

the

way

in.

NOTE

Two

mechanics

(personnel)

may

required

for

the

several

steps.

One

under

the

aircraft

and

the

other

inside

the

aircraft

operating

the

landing

gear

switch.

13.

Retract

landing

gear

using

safety

by-pass

switch

(See

Section

32-30-01,

steps

5, 6,

until

inboard

gear

door

has

traveled

far

willgo

during

its

retraction

cycle.

this

position,

the

pivot

points

bellcrank

(3)

center

line

rod

-(5)

will

straight

line

(Reference

Figure

M20-254-2).

Components

(2),

(5)

(6)

should

now

loaded

condition

and

feel

very

tight.

14.

Adjust

stop

bolt

head

(8)

OUT

until

rests

bellcrank

(4)

arm.

Continue

adjust

bolt

head

OUT

until

rods

(5)

(6)

become

loose

(no

load

felt

either

rod).

Bellcrank

(2)

will

also

become

loose

when

bolt

head

(8)

correct

position.

Tighten

jam

nut

bolt

(8)

against

tube

stop

(7).

15.

Repeat

installation

stop

(7)

(Steps

thru

11)

and

adjustment

procedures

(Steps

thru

14)

other

whedwdl.

16.

Cycle

landing

gear

through

five

complete

retraction/extension

cycles;

inspect

all

components

during

and

after

cycles

for

any

interference,

binding

improper

operation.

Reference

Operational

Inspection

done

Step

No.

17~

Ccmplete

lag

boole

entry

and

retum

aircraft

service.

WARRANP~

Mooney

Aircraft

Corporation

will

allow

3.0

hours

labor

comply

with

this

Service

Bulletin.

Parts

Kit

will

ordered

through

Mooney

Service

Centers

and

credit

will

issued

upon

receipt

warranty

forms

within

180

days

the

issue

date

this

Service

Bulletin.

REFERENCE

DATA:

N/A

PARTS

UST:

KIT

PART

NUMBER

SBM20-254-1

lTEM

.P/N

DESCRIPTION

QTY

~550075601

STOP

ASSY.

.550082-503

ROD,

LOWER

.550082-505

ROD,

UPPER

.91

4020-1

BUSHING

.8-47

BEARING

.MS20392-2C7

PIN,

CLNIS

(PRESS

FIT:BELLCRANK

.MS20392-2C9

PIN,

CLNIS

(PRESS

FIT-BELLCRANK

.MS20392-2C17

PIN,

CLEVIS

.AN381-2-6

PIN,

COTTER

10.

.AN470AD5-13

RIVET

11.

M20M

Chapter

32,

kevised

3-93’

some

later

date

the

complete

will

revised

and

Chapter

32,

revised

March,

1993,

will

available

the

field

and

may

not

included

this

Service

Bulletin

kit.

FlGUREl

TABLES:

SEE

NDCT

PAGES

FOR

FlGURES

SBM20-254-1

AND

SBM20-254-2

SERVICE

BULLETIN

M20-254

DATE:

4-1-93

Page

p’’

spi~P

dp"‘’

\~4

~\o

--~21

I,I

L.9

SBM20-25

4´•-1

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