Mooney Ranger M20C Manuale di riferimento

/nao-1~7

SVBJECT:

INSTALLATION

OPERATION

PW\CARO

P/N

150010-111

MODELS

EFFECTED:

M20

and

IM22

Series

Aircraft

TIME

COMPLIIINCE:

before

neX,

100

iiour

Inspection

INTRODIICTION:

P/N

150010-111

placard

that

adhered

area

the

flight

panel

(ret’erence

shefches

shown

below)

full

view

the

pilot.

INSTRL[CTIONS:

NOTE

-1.

Sketch

depicts

hlZO

series

flight

panel

Sketch

depicts

M22

series

flight

panel

All

placards

are

self-adhering

(pressure

sensitive)

M20

Series

Aircraft

(1)

Location

(Shounn

Sketch

order

Kit

No.

This

the

location

far

adhering

placard

150010-111

aircraft:

M20C

S/Nls

2121

thru

h?013L

#200

S/N’E

101

thru

2hO

EZ20E

S/M’s

101

h80001

E70F

9/N’´•

hi´•0002

thru

h70~85

Placard

F/I

1:00:9-b3

(Gear

Ooum)

adhered

sho~a

Sketch

placard

150010-111

adhered

per

this

recommended

1A’

location.

(2)

YIILI-V´•II

(Sho~

Sketch

Locationl

Locaiions

and

(optional)

are

for

other

’120

aircraft

not

feasible

location

thi´•

placard

cannot

installed

recommended

locations

then

adhered

;te

left

line

A-A

(shorn~

Sketch

the

flieht

panel--;r

full

view

pilot.

(L)

AdilerP

rticker’’

outside

front

coier

?I?O

Series

Aircraft

Oxners

Manual.

M22

Series

iiircraSt

(1)

Adhere

P/I

150010-111

placard

M22

S/hi’s

C.70001

and

~70002

shorn~

Sketch

(2)

Adhere

sticker"

outside

front

cover

~22

Series

Aircraf~

Ouiner;

Manual.

SERVICE

BIILLETIN

KIT

NO.

150010-111

Placard

lane)

li0019-h3

Placard

(or,p)

Stic~eri’(ons

SZRTIICE

BlJLLFTIN

KIT

NO.

,,,,,,.,,I

Sticker

made

paper

and

has

same

size,

desian,

and

wording

P/N

150010-111

placard.

oFa

~k,

‘B

´•I(´•01*1.):

:-I

onaet

lilt

Il´•Ulrl

ONLI-O´•II´•

I´•UI´•l

IN´•

~I´•

II~

I´•

hr~un

*lh

rlili´•

Ua~

III*

Ihllil~lll´•l´•l´•li´•(

Il´•l´•LI´•lllillb

li´•il´•li´•l.

PJN

150010-111

Plpep~

Lnsta~led

1I1

M-20

esrisa

~ar

locPLLon

’A’

drcralt

Lull

vie.

alpllot.

ONI.Y

P/N

150038-45

PLpeard

BYLTCB

aERIE8

PLI(IIP~

PANEL)

6’

90~

oPrlnrs

THS

I1RCRl\lr

ONLY-

Oall,~

raaling

awara

manull

with

awnsr

manuai

bpard

ear

vau

all

und,l.,nl

all

´•00

P/N

150010--111

Placard

installed

all

M-22

series

aircraft

full

view

pilot.

SKETCH

(M-22

SERIES

FLIGRI~

PANEL)

SUBJECT:

ALTIMETER

INSPECTION

MODELSPI~EC1TED:

~zoc,

S/N

670001-670135

~20E,

S/N

1177,

1199,

1217,

1268,

1273,

1277,1281,

1283,

1286

thru

1288,

1290,

1292,

1293,

1295

thru

1308,

670001

thru

670062

~20F,

S/N

660001

ihru

660004,

670001

thru

670446

P122,

S/N

670001

and

670002

This

Bulletin

will

also

apply

any

other

Mooney

airpla3le

for

which

Trleston-Garwin

Model

22-374

aftimeter

was

purchased

between

July

1966

and

August

1967.

COMPLIANCE:

Immedia’;ely,

this

Service

Bulletin

mandatory.

INTRODUCTION=

Evidence

has

been

found

that

accumulation

tolerances

some

Weston-Garwin

Model

22-374

altimeters

can

cause

malfunction

the

instrument.

Since

this

condition

li~ely

exist

all

airplanes

which

are

equipped

with

Model

22-374

altimeters,

this

Service

Bulletin

being

issued

require

testing

the

altimeter

and

replacement,

necessary,

several

models

Mooney

airplanes.

II~STfLUCTIONS:

determine

the

Weston-Gar~Jin

Model

22-374

altimeters

are

operating

properly,

accomplish

the

following:

Set

barometric

scale

or"

altimeter

coincide

with

appropriate

field.

pressure

and

check

altimeter

reading.

should

agree

with

field

elevation

allowing

for

tolerance

plus

minus

100

feet.

Set

barometric

scale

altimeter

29.92

inches

(1013.3

mi77;hars)

and

observe

the

altimeter

reading.

Turn

the

bare

mechanism

move

the

scale

the

low

end

stop.

During

this

movement,

exert

slight

pressure

forward

and

aft

alternately

order

see

possible

cause

the

internal

mechanism

become

disen,oa,Ped.

The

disengagement

will

obvious

the

pointer

hand

fails

rotate

the

knob

turned.

Turn

the

knob

for

bare

scale

soas

move

the

scale

the

high

end

stop.

During

this

motion,

again

exert

pressure

alternately

pushing

and

pulling

slightly

and

watch

for

needle

slippage.

INSTRUCTIONS:

Turn

the

barometric

scale

back

24.42

inches

(1013,3

and

compare

this

altimet;er

reading

with

the

reading

obtained

Step

The

readings

should

the

same.

the

pointers

not,

all

times,

move

direct

relation

with

the

bare

scale,

the

reading

Step

does

not

agree

with

the

final

reading,

the

reading

Step

not

within

tolerances,

then

the

altimeter

not

working

properly,

and

ii;

should

replaced

repaired

approved

facility.

Aircraft

with

defective

altimeters

shall

fly

VFR

only

visual

contact

with

the

ground

until

the

altimeter

replaced

repaired.

The

check

required

this

Service

Bulletin

may

per-

formed

the

pilot.

~ZI´•

OON

R~C;SA

-9

dOX

Zlrz

´•1.

SUB;IECT:

Fuel

Filler

Caps

(Shaw

Aero),

Inspection

and

Adjustment

MODUS/

MZ0C

S/N

2623

and

ON,

M20D

S/N

201

ON,

ALL

M20E,

M20F,

M20G,

M20J,

M20K

S/N

AFFECTED:

and

M22

Aircraft

TIME

COMPLIANCE:

Within

night

hours,

and

every

100

hour/annual

inspection

thereafter.

INTRODUCTION:

Exposure

weather.

fuel

fumes,

fuel

and

possibly

other

elements

have

deteriorating

effect

O’ring

packings

and

seals.

The

two

O’rings

the

Shaw

Aero

fuel

filler

cap

assembly

have

been

reported

lose

their

resilience

and

sealing

characteristics

after

period

oftime

when

exposed

these

elements.

This

S.B.

intended

describe

inspection

procedures

for

this

deterioration.

INSTRUCTIONS:

Fuel

filler

port

cap

assemblies

should

checked

periodically

for

proper

sealing

and

should

serviced

occasionally

prevent

hard

open

conditions.

Refer

Figure

S.B.

M20-229-1

andthe

following

procedures

for

these

inspections

and

adjustments:

TheO’ring

real

(1)

amur.d

the

cap

assembb

should

kept

clean

and

free

dirt

orgrit

that

might

cause

abrasive

action

seal

mating

nange.

Occasional

lubrication

with

petroleum

jelly

Tri-Flow

will

keep

the

O’ring

soft

and

pliable.

The

shaft

(2)

running

through

the

center

the

cap

housing,

that

actuated

the

rotating

lock

plate

(3)

should

lubricated

occasionally

with

Tri-Flow,

equivalent,

prevent

binding

while

opening

closing

the

cap

assembly.

This

should

also

lubricate

the

O’ring

;(4)

that

seals

this

shaft.

WARNING

Water

can

enter

the

fuel

tank

through

loose

fitting

damaged

cap.

This

should

corrected

soon

possible.

The

sealing

capability

each

cap

assembly

should

checked

periodically.

This

can

accomplished

per

the

following

procedures:

Remove

cap

assembly

form

wing

filler

port

and

inspect

O’ring

(1)

for

any

damage

brittleness.

Remove

and

replace

needed.

Adjust

tension

shaft

(2)

and

rotating

lock

plate

(3)

removing

cotter

(5)

from

nut

(6)

threaded

portion

shaft

t2).

Tighten

nut

(6)

cap

assembly

handle

(7)

can

opened,

turned

and

shut

with

hand

pressure

and

still

provide

the

necessary

seal

cap

assembly

keep

water

from

entering

fuel

tank.

Fuel

selector

should

the

OFF

position

prior

pressurizing

the

fuel

tanks.

Connect

rubber

hose

each

tank’s

vent

line.

Apply

only

one-half

pound

(1/2

psi)

air

pressure.

Check

for

fuel

cap

leaks

soaping

circumference

ftlIer

cap

assembly

and

observing

bubbles.

Replace

O’rings

bubbles

are

observed

and

adjustment

the

nut

does

not

stop

the

leak.

’’CAUTION"

Use

only

one-half

pou

(0.5

psi)

air

pressure

tank.

Higher

pressure

ma~

damage

the

fuel

tank.

"NOTE"

MZOI<

aircraft

must

have

the

anti-siphon

valve

inside

filler

port

propped

open

during

this

pressure

testing.

REFERENCE

DATA:

N/A

PARTS

LIST:

(Parts

NOT

included

kit

order

needed).

Part

Number

Description

Qty.

Required

MS29513-010

O’Ring

tcenter)

MS29513-338

O’Ring

touter)

(for

431-9R

and

531-001

cap)

Page

SE.

M20-229A

2-12-86

FIGURES/TABLES:

I’

FIGURE

S.B.

M20-229-1

b;L

MOONEY

L\1RCRAFt?i~OR

NLIMBER

-r-

-´•r

bdX

rj‘´•

KERRYILLE,

rrXAS

76026

i-i;i´•;;

.":rtnSeuLLETIN

FA*

APPROVED~

;-i

.-_-I-

SUBJECT:

Inspection

Fuel

Tank

Sealant

Application

MODELS/

M20B,

M20C,

M20D,

M20E,

M20F,

M20G

M22

ALL

SERIAL

NUMBERS.

S/N

AFFECTED:

M20J:

thru

24-1498;

M20K:

SM25-0001

thru

25-0854.

h120J:

S/N23-1499

and

M20K:

S~25-0855

ONLY

FUEL

TANK

HAS

BEEN

RESEALED

FIELD

PERSONNEL.

TIME

COMPLIANCE:

Within

flight

hours

scheduled

inspection.

INTRODUCTION:

Reports

have

been

received

that

fuel

and

water

have

been

found

trapped

between

ribs

due

one

d~more

rib

drain

holes

being

sealed

over

during

tank

sealing;

particularly

tanks

that

have

been

resealed.

INSTRUCTIONS:

General

Inspect

ensure

all

required

rib

holes

are

open

allow

fuel

(or

any

water)

move

the

lowest

area

the

tank.

Refer

Figures

M20-230-1

thru

-7

for

areas

check

for

specified

holes

open

and

NOT

filled

with

sealant

compound.

Position

airplanes

approximate

level

attitude

tall

axis)

its

landing

gear.

Drain

fuel

per

instructions

applicable

Service

and

Maintenance

Manual.

Carefully

remove

fuel

tank

access

covers

top

ofwing

indicated

below

for

particular

model

(reference

Figure

MZO-uO-l).

NOTE

lieu

access

cover

removal

optional

methods

inspection

are

acceptable.

However,

the

method

MUST

demonstrated

the

local

FAA

inspector

that

poshi~e

determination

can

made

that

all

holes

are

open

and

the

intent

this

Service

Bulletin

has

been

complied

with.

MZOB,

M20C.

MZOD.

MZOE

and

MZOG

Models:

Access

Cover

No.O

required.

Fuel

Transmitter

optional.

AIZOF

and

hIZOJ

Models:

Access

Cover

NoOrequ~red,

NoO~plional.

MZO~

Xlodel:

Access

Cover

No~nd

required.

No.

optional

h122

h~lodel:

Access

Cover

No.O

andO

required,

NaO.

06rOoplional.

Inspect

each

tank

bay

outboard

each

rib

station

for

trapped

fuel

(or

an~

liquid)

that

has

not

drained

through

the

passage

holes

each

rib

station

the

fuel

tank

sump

drain

area.

Inspect

each

rib

station

(refer

Figure

M20-230-2

thro

-7)

determine

that

all

fuel

passage

holes

are

open

allow

fuel

drain

from

outboard

rib

stations

the

fuel

tank

sump

area.

There

should

fuel

(or

any

liquid)

trapped

outboard

any

rib

station.

positive

determination

cannot

made

that

fuel

not

trapped

and/or

that

all

holes

are

open,

the

access

covers

marked

"Opticlnal"

paragraph

thru

above,

should

removed

complete

the

inspection.

Ifinspcction

determines

all

holes

are

OPEN

the

appropriate

ribs

shown

figures

M20-230-2

thru

-7

this

portion

inspection

completed.

Proceed

Step

Ifinspcction

dctersines

311

holes

are

NOT

DPEN

Ihe

apprapriale

ribs

shou~n

Figure

M20-230-2

thru

-7

proceed

follows:

Determine

csact

position

rib

holc)s)

that

are

sealed

over.

U\ing

pointed

csacto

knife

clear

hole

sealant;

careful

not

cut

sealant

from

rib

flangc.

S.B.

M20-230A

.Date:

1-16-86

Page

after

clearing

hole

appears

that

fuel

can

get

under

adjoining

sealant

carefully

i’

carefully

reseal

area

without

covering

hole.

use

PRI422BM

sealant.

Proceed

Step

INtall

all

removed

access

covers

per

Service

and

Maintenance

Manual

and

Figure

M-20-230-8.

Use

PR1403-G-B2

equivalent

sealant

specified

Manual,

noting

cure

time

(PR14UB-1/2

B-2

may

used

necessary)

"CAUTION"

Use

AN507

screffs

longer

than

7/16

inch

will

puncture

acorn

anchor

nut

access

plate.

REFEHENCE

DATA:

N/A

PARTS

LIST:

NIA

FIGURES/TABLES:

See

Figure

M20-UO-1

thru

M20-230-7.

Seal

afl

stringer

rib

flungcs,

top

and

bottom

tank

FUEL’I’I1N‘K

RIBS

AFFECTED

r~n

M20F

M20K

m20J

hll

nircrnlt

M22

M20K

M22

Witlg

Lcnditlg

Edge

f~-t

r---rll-r~r´•

tl´•ti~

tjsj?zirrr*r

Trulk

Vent

Assy

oQo

:ti

cc*

S~t

Ti:)’f=C,1

s,?l

,I´•

t,c,

t~;

´•tl

’F

i~Lli

´•r´•

i+~

ii-

I’

Lbl-.-"-:Y_

.´•,-----,.~,.,..er.’."

-f~

t:’

,c,

.i:

i,,

l’i

tl,t

It.

:C:

;t,

5’

-1-

--r

´•I

ft\

t´•

c.~

´•c*

-*-t

-L

B~D

Tank

W.S.

W,S.

w.s.

w.5.

w.s.

Drain

24.50

103.5

88.75

74.00

59.25 43.50

Fuel

filler

Qty.

gauge

o\o

port

location

optional

will

vary

this

with

a/e

BCCBSS

Drain

holes

thru

stringers

models

cover

bottom

side

wing

open.

(4PLCS)

FIGURE

M20-230-1

IVIIIW

nnKlhlC.

n~Whl

DRnM

TnT,

Wl~r.\

Seal

rib

shown

(this

side

only),

’i

Seal

all

rivets,

nut

plates

natljies

(ALL

MODEtS).

´•t´•

"i:

111

\\t´•

Seal

bath

side

Seel

both

sides

´•r;iF;´•

rib

-1-

Top

Wing

Witlg

Top

rib

-t´•

-I-

-t

-t-

\t-

´•-t’

jI__~__

-~-11751

r´•´•´•-;´•_-1-_

-t-

~nti-slosll

valves

(h120K)

ca.)

vent

holes

thru

L’

rib

remain

open

after

sealing.

Ileopcn

aftcP

(alI

models)

-1-

scaling

Iiole

(M?OK)

holes

(All

´•t-

oLlicr

aircraft)

1.’,

Fuel

pickup

I::

strainer

&linger

W,S.

43.50

Inboard

fuel

qty.

transmitter

attach

aoint

7Tr,

W,S.

24.50

FIGURE.

M20-230-3

FIGURE

M20-230-2

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