/nao-1~7SVBJECT: INSTALLATION OF OPERATION PW\CARO P/N 150010-111

MODELS EFFECTED: M20 and IM22 Series Aircraft

TIME OF COMPLIIINCE: On or before neX, 100 iiour Inspection

INTRODIICTION: P/N 150010-111 is a placard that is to be adhered to an

area on the flight panel (ret’erence shefches shown below)in full view of the pilot.

INSTRL[CTIONS: NOTE -1. Sketch 1- depicts hlZO series flight panel2. Sketch 2 depicts M22 series flight panel

All placards are self-adhering (pressure sensitive)

M20 Series Aircraft

(1) Location A (Shounn on Sketch 1) order Kit No. 1

This is the location far adhering placard 150010-111on aircraft: M20C S/Nls 2121 thru h?013L

#200 S/N’E i. 101 thru 2hO

EZ20E S/M’s 101 to h80001

E70F 9/N’´• hi´•0002 thru h70~85Placard F/I 1:00:9-b3 (Gear Ooum) is to be adhered as

sho~a on Sketch 1 if placard 150010-111 is adhered perthis recommended 1A’ location.

(2) YIILI-V´•II YI Y (Sho~ on Sketch 1)Locationl B C

Locaiions B and C (optional) are for other ’120 aircraft

not feasible on location A.

If thi´• placard cannot be installed on recommended locations

A, R, or C, then it is to be adhered to ;te left of line A-A

(shorn~ on Sketch 1) an the flieht panel--;r full view of pilot.

(L) AdilerP rticker’’ to outside of front coier of ?I?O Series Aircraft

Oxners Manual.

M22 Series iiircraSt

(1) Adhere P/I 150010-111 placard on M22 S/hi’s C.70001 and ~70002

as shorn~ an Sketch 2.

(2) Adhere sticker" to outside of front cover of ~22 Series Aircraf~

Ouiner; Manual.

SERVICE BIILLETIN KIT NO. 1

150010-111 Placard lane)li0019-h3 Placard (or,p)

Stic~eri’(ons

SZRTIICE BlJLLFTIN KIT NO. 2

,,,,,,.,,I

it Sticker is made of paper and has same size, desian, and wording

as P/N 150010-111 placard.

I oFa

i ~k, o09

a ‘B ´•I(´•01*1.):

oh

:-I

onaet lilt Il´•Ulrl ONLI-O´•II´• I´•UI´•l

M IN´• ~I´• II~ I´• U1

o hr~un *lh rlili´• L Ua~ III*

Ihllil~lll´•l´•l´•li´•( Il´•l´•LI´•lllillb li´•il´•li´•l.

PJN 150010-111 Plpep~

To be Lnsta~led an 1I1 M-20 esrisa ~ar locPLLon ’A’

drcralt in Lull vie. alpllot. ONI.Y

P/N 150038-45 PLpeard

BYLTCB 1 nm aERIE8 PLI(IIP~ PANEL)

sBO o

6’ O Q90~

Q

oPrlnrs THS I1RCRl\lr ONLY- Oall,~ raalingawara manull 8 with awnsr manuai an bpard O

8 ear vau all st v a und,l.,nl all ol

´•00

P/N 150010--111 Placard

To be installed on all M-22 series

aircraft in full view of pilot.

SKETCH 2 (M-22 SERIES FLIGRI~ PANEL) ofa

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 670446P122, S/N 670001 and 670002

This Bulletin will also apply to any other Mooneyairpla3le for which a Trleston-Garwin Model 22-374aftimeter was purchased between July i, 1966 and

August 2, 1967.

~E OF COMPLIANCE: Immedia’;ely, this Service Bulletin is mandatory.

INTRODUCTION= Evidence has been found that an accumulation of tolerances

in some Weston-Garwin Model 22-374 altimeters can cause a

malfunction of the instrument. Since this condition is

li~ely to exist in all airplanes which are equipped with

Model 22-374 altimeters, this Service Bulletin is beingissued to require testing of the altimeter and replacement,if necessary, on several models of Mooney airplanes.

II~STfLUCTIONS: To determine if the Weston-Gar~Jin Model 22-374 altimeters

are operating properly, accomplish the following:

1) Set barometric scale or" altimeter to coincide with appropriatefield. pressure and check altimeter reading. It should

agree with field elevation allowing for a tolerance of

plus or minus 100 feet.

2) Set barometric scale of altimeter to 29.92 inches of hg(1013.3 mi77;hars) and observe the altimeter reading.

3) Turn the bare mechanism so as to move the scale to

the low end stop. During this movement, exert slightpressure forward and aft alternately in order to see if

it is possible to cause the internal mechanism to become

disen,oa,Ped. The disengagement will be obvious if the

pointer hand fails to rotate as the knob is turned.

4) Turn the knob for bare scale so as to move the scale to

the high end stop. During this motion, again exert

pressure by alternately pushing and pulling slightly and

watch for needle slippage.

INSTRUCTIONS: 5) Turn the barometric scale back to 24.42 inches of hg(1013,3 and compare this altimet;er readingwith the reading obtained in Step 2. The readingsshould be the same. If the pointers do not, at all times,move in direct relation with the bare scale, or if the

reading of Step 2 does not agree with the final reading,or if the reading in Step 1 is not within tolerances,then the altimeter is not working properly, and ii; should

be replaced or repaired at an approved facility. Aircraft

with defective altimeters shall fly VFR only in visual

contact with the ground until the altimeter is replacedor repaired.

The check required by this Service Bulletin may be per-formed by the pilot.

~ZI´•

OON R~C;SA-9

i"dOX Zlrz 36

´•1.

SUB;IECT: Fuel Filler Caps (Shaw Aero), Inspection and Adjustment

MODUS/ MZ0C S/N 2623 and ON, M20D S/N 201 gr ON, ALL M20E, M20F, M20G, M20J, M20K

S/N AFFECTED: and M22 Aircraft

TIME OF

COMPLIANCE: Within next 25 night hours, and every 100 hour/annual inspection thereafter.

INTRODUCTION: Exposure to weather. fuel fumes, fuel and possibly other elements have a deterioratingeffect on O’ring packings and seals. The two O’rings on the Shaw Aero fuel filler cap

assembly have been reported to lose their resilience and sealing characteristics after a

period oftime when exposed to these elements. This S.B. is intended to describe inspectionprocedures for this deterioration.

INSTRUCTIONS: Fuel fillerport cap assemblies should be checked periodically for proper sealing and should

be serviced occasionally to prevent hard to open or close conditions.

I Refer to Figure S.B. M20-229-1 andthe following procedures for these inspections and

adjustments:

i. TheO’ring real (1) amur.d the cap assembb should be kept clean and free of dirt orgritthat might cause abrasive action on seal or mating nange. Occasional lubrication with

petroleum jelly or Tri-Flow will keep the O’ring soft and pliable.

2. The shaft (2) running through the center of the cap housing, that actuated the rotatinglock plate (3) should be lubricated occasionally with Tri-Flow, or equivalent, to prevent

I binding while opening or closing the cap assembly. This should also lubricate the O’ring;(4) that seals this shaft.

WARNING

Water can enter the fuel tank through a loose

fitting or damaged cap. This should be

corrected as soon as possible.

3. The sealing capability ofeach cap assembly should be checked periodically. This can be

accomplished per the following procedures:

A. Remove cap assembly form wing filler port and inspect O’ring (1) for any damage or

brittleness. Remove and replace if needed.

B. Adjust tension of shaft (2) and rotating lock plate (3) by removing cotter pin (5) from

nut (6) on threaded portion ofshaft t2). Tighten nut (6) so cap assembly handle (7) can

be opened, turned and shut with hand pressure and still provide the necessary seal of

cap assembly to keep water from entering fuel tank.

C. Fuel selector should be in the OFF position prior to pressurizing the fuel tanks.

D. Connect rubber hose to each tank’s vent line. Apply only one-half pound (1/2 psi) air

pressure. Check for fuel cap leaks by soaping circumference of ftlIer cap assemblyand observing bubbles. Replace O’rings if bubbles are observed and adjustment of

the nut does not stop the leak.

’’CAUTION"

Use only one-half pou nd (0.5 psi) ofair pressurein 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 in kit order if needed).

Part Number Description Qty. Required

MS29513-010 O’Ring tcenter) 1

MS29513-338 O’Ring touter) (for 431-9R and 1

531-001 cap)

Page 2 of 2

SE. M20-229A2-12-86

FIGURES/TABLES:

I’ I

FIGURE

S.B. M20-229-1

g

b;L

MOONEY L\1RCRAFt?i~OR NLIMBER-r-

-´•r r

bdX rj‘´• KERRYILLE, rrXAS 76026

gi-i;i´•;; .":rtnSeuLLETIN IS FA* APPROVED~;-i

.-_-I-

SUBJECT: Inspection of 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 ON and M20K: S~25-0855 ON ONLY IF FUEL

TANK HAS BEEN RESEALED BY FIELD PERSONNEL.

TIME OF COMPLIANCE: Within next 50 flight hours or at next scheduled inspection.

INTRODUCTION: Reports have been received that fuel and water have been found trapped between ribs due

to one d~more rib drain holes being sealed over during tank sealing; particularly in tanks

that have been resealed.

INSTRUCTIONS: General Inspect to ensure all required rib holes are open to allow fuel (or any water) to

move to the lowest area of the tank.

Refer to Figures M20-230-1 thru -7 for areas to check for specified holes to be open and NOT

filled with sealant compound.

i. Position airplanes in an approximate level attitude tall axis) on its landing gear. Drain

fuel per instructions in applicable Service and Maintenance Manual.

2. Carefully remove fuel tank access covers on top ofwing as indicated below for a particularmodel (reference Figure MZO-uO-l).

NOTE

In lieu of access cover removal optional methods of inspection are acceptable.

f However, the method MUST be demonstrated to the local FAA inspector that a

poshi~e determination can be made that all holes are open and the intent of this

Service Bulletin has been complied with.

A. MZOB, M20C. MZOD. MZOE and MZOG Models:

Access Cover No.O required. Fuel TransmitterO optional.

B. AIZOF and hIZOJ Models:

Access Cover NoOrequ~red, NoO~plional.C. MZO~ Xlodel:

Access Cover No~ndO required. No. O 8( O optional

D h122 h~lodel:

Access Cover No.O andO required, NaO. 06rOoplional.

3. Inspect each tank bay outboard of each rib station for trapped fuel (or an~ liquid) that has not

drained through the passage holes at each rib station to the fuel tank sump drain area.

4. Inspect each rib station (refer to Figure M20-230-2 thro -7) to determine that all fuel

passage holes are open to allow fuel to drain from outboard of rib stations to the fuel tank

sump area.

5. There should be no fuel (or any liquid) trapped outboard of any rib station. If a positivedetermination cannot be made that fuel is not trapped and/or that all holes are open, the

access covers marked "Opticlnal" in paragraph 2. A thru D above, should be removed to

complete the inspection.

6. Ifinspcction determines all holes are OPEN in the appropriate ribs as shown in figuresM20-230-2 thru -7 this portion of inspection is completed. Proceed to Step 8.

i 7. Ifinspcction dctersines 311 holes are NOT DPEN in Ihe apprapriale ribs as shou~n in

Figure M20-230-2 thru -7 proceed as follows:

A. Determine csact position of rib holc)s) that are sealed over.

B. U\ing pointed csacto knife clear hole of sealant; be careful not to cut sealant from

rib flangc.

S.B. M20-230A

.Date: 1-16-86

Page 2 of 7

C. if after clearing hole it appears that fuel can get under adjoining sealant carefully i’carefully reseal area without covering hole. use PRI422BM or B2 sealant.

D. Proceed to Step 8

8. INtall all removed access covers per Service and Maintenance Manual and Figure M-20-230-8. IUse PR1403-G-B2 or equivalent sealant as specified in S gr M Manual, noting cure time

(PR14UB-1/2 or B-2 may be used if necessary)

"CAUTION"

Use ofAN507 screffs longer than 7/16 inch

will puncture acorn anchor nut in access plate.

REFEHENCE DATA: N/A

PARTS LIST: NIA

FIGURES/TABLES: See Figure M20-UO-1 thru M20-230-7.

C

f"

Seal afl stringer 9E rib

flungcs, top and bottom

of tank

FUEL’I’I1N‘K RIBS AFFECTED

r~n M20F

M20K m20J hll nircrnlt

M22 M22 M20KM22

Witlg Lcnditlg Edgef~-t

r---rll-r~r´• tl´•ti~ ti

tjsj?zirrr*r Trulk Vent Assyt;

I, I,

oQo O 2 :t it (I:ti

I* i: cc*

S~t Ti:)’f=C,1 s,?l ,I´•t,c, t~; c ´•tl r- ’F i~Lli j

,I

´•r´• i+~ tlci I ii- I’

I; rl ,L *b Lbl-.-"-:Y_ I

it

c .´•,-----,.~,.,..er.’."-f~

t:’ 5

,c, c

.i: i,,l’i

tl,tIt. I,I I! i?l :C:;1 ,i

;t, i 5’

-1-

--r Cib

C~´•I

ft\t´• c.~ ´•c*c

-*-t-LL

C C* CI

B~DTank W.S. W

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 on 3,

will vary this

with a/e BCCBSS Drain holes thru stringers onmodels cover

bottom side of wing to be open.

(4PLCS)

FIGURE M20-230-1IVIIIW I nnKlhlC. n~Whl DRnM TnT, ~C Wl~r.\

Seal rib as shown (this side only), ’iSeal all rivets, nut plates St natljies(ALL MODEtS).

´•t´•i "i:

111 \\t´•Seal bath side

Seel both sides´•r;iF;´•

:i of rib -1- TopWing

Witlg Topof rib c~

-t´• -I- -t

i-t- \t-

3´•-t’ jI__~__

1 r,

i- -~-11751

t r´•´•´•-;´•_-1-_ -t-

~nti-slosllvalves

(h120K) (2 ca.)

I~

G vent holes thru L’rib to remain openafter sealing.

Ileopcn aftcP (alI models) -1-

scaling1 Iiole (M?OK)8 holes (All i\ ´•t-oLlicr aircraft)

1.’, de Fuel pickupI::

strainer

r.&linger

s~ tdrn

W,S. 43.50 Inboard fuel qty.transmitter attach

aoint

7Tr, o\

W,S. 24.50

FIGURE. M20-230-3 FIGURE M20-230-2

fl

Willg ’I.op JI! Wing Top1 -1- :-1-

,Il!´•i;: ´•1´• 1 i

I~ ----r*- I O Seal both sitlcs of rib B´•:i.´•i´• (M20K St M2) (All uroutld)

i’i- ´•-i- Scalthi~ side only~’M2oF. M201)

Seal all rivets, flenges i´•’C Ilolcs.

t -C ´•´•1-´•~ tf-’Scnl both sidesof rib as showtl,

~31 t

t-’ -I-12 holes thru rib It~-";

j.to rcmnin open

-hI´•’fl (M20F, M20J, M20K, M22)

---´•t~1-

7 Ides thru ribE. /Lto rernain open

1-

Vent

(7 plcs) i Reopen nftcr holes

holes Vent ‘´•-\’"20" 6;M22)

seali~!g (3 ptcs)~1 (M20F. M20J, M201(

~!f /’Reopen after;I 6iM22).i sealing (M20K St M22)jIIl’-r------- -1:

11 j r--~l-i--iiii.NOTE: This is a tank t;- w.s. 74.90~-W.S. 59.25 close out rib on M20B, M20C, M20D,M20E M20Gand should be sealed on

inboard side only, SealFIGUKE M20-230-4 all rivets, flanges holes, FIGURE M20-230-5 09 I~ td

Vetlt holes3 -CI n (8 plcs)

Close out ribotl M20K- Seal -c+

inboard side ´•I~-I c

otlly, Seal all ´•1- f irivets, flnngcscSt holes. 15 holes to

be reopened~II Scnl inboard rtftcr se:lling

side only 1: (M22 otlly)seal all rivets,nnngcs J~ holes.

i Witll:

;i;Top

Wing Too

W.S. 103-5

(M22 Only) (M22 Only)

FIGURE M20-230-7o\

FIGURE M20-230-6

"F

~7

r‘

Faysurface seal nnngeWing Top Stlrface wet install screws on

nll access covers

Do not use screws

longer than 7/16"

Iii

´•’J~i

ii

Seal inside surface of allaccess covers sealing all rivets

View looking up nutplates as shown

from inside tank (REF. S M Manual) ~tlvl

FIGURE M20-230-8

THIS SERVICE BULLETIN IS FAAAPPROMD FOR ENGINEERING DESIGN

SERVICE BULLETIN M20-ZB1ISSVEDATE: 1 December. 1996

SUBJECT: BENDIXKIND SERVICE BULLETIN No. SE KT 7BA-7, JULY/96 (or later revision(s)),KT 76A ATC TRANSPONDER.

MODELSISINAFFECTED: ALL MODELS OF MOONEY AIRCRAFT MANUFACTURED SINCE 1975 (INCLUDES M20C,

MME. M20F, MZOJ, M20K MZOC M2OM, AND M20FO AND ANY MODEL MAT MAY HAM

HAD A KT 7BA TRANSPONDER RETROFITTED SINCE 1875 (INCLUDES MZO, M20A.M20B, M20D, M20G, OR M22) (APPLIES TO ALL S/N’s)

TIME OFCOMPLIANCE: REFER TO BENDIXKING SE KT 70A-7. DATED JULY/SE (or later revision(s)

INTRODUCTION:

1. Bendix-King SeNice Bulletin No. KT 70A-7 provides information that indicates the integrated cir-

cult (IC) of the KT 78A, P/N 0Bg1082-00/1~02, SIN’s from 83,000 to 109,000, may possess, or

progress to. an electronic breakdown within the IC that causes either or both of the followingmalfunctions:

1) The unit may incorrectly interpret the output of the encoding altimeter.

or

2) 7he unit may transmit a code other than what is set land shown) on the face of the

transponderunl

2. The subject Bendix-King SE pro\i~es the compliance, relrofl, warranty and parts list information

necessary for the relront procedures to be accomplished by apprapiiately rated Bendlx-KingServ ice Centers.Service

INSTRUCTIONS: REFER TO BENDIX-KINO SE KT 78A-7. DATED JULYlSE tar later revision(s)

VII~RRANPI: REFER TO BENDIX-KINO 58 KT 7BA-7. DATED JULY/SE (or later revision(s)

REFERENCEDATA: REFER TO BENDIX-KINO SE KT 7BA-7. DATED JULYISE (or later revision(s)

PARTS LIST:REFER TO BENDIX-KING SE KT 7BA-7, DATED JULY/96 (or later revision(s)

FIGURES/TABLES. REFER TO BENDIX-KINO 58 KT 7BA-7. DATED JULYIS6 (or later revision(s)

MOONEY "-~i" SERVICEINSTRUCJlOr\l

S.I. No. M20-40

Date: 12-2-76

SERVICE INSTRUCTION

SUBJECT: BAGGAGE COMPARTMENT TIE DOWN STRAP

ASSEMBLY REPLACEMENT

MODELS

AFFECTED: Model Serial Effectivity

M20F 680001 thru 22-1362, 22-1364, 22-1365,22-1367, 22-1368, 22-1369, 22-1371 thru

22-1376, 22-1378 thru 22-1381, 22-1385,22-1386, 22-1388 thru 22-1394, 22-1396,22-1399 thru 22-1407

~1120E 680001 thru 21-1180

M20C 680001 thru 20-1196, 20-1198, 20-1199,20-1202, 20-1204 and 20-1205

M20G 680001 thru 700006

M22 680001 thru 700006

TIME OF

COMPLIANCE: At next scheduled inspection or sooner at owner’s

discretion.

INTRODUCTION: On the aircraft noted above the material used for the

baggage compartment tie down rings was found to be of

an incorrect type. Therefore, it is recommended that

the entire tie down strap assemblies be replaced.

INSTRUCTIONS: Remove existing baggage compartment tie down strapassemblies and replace with the new assemblies called

for by the parts list.

SERVICE INSTRUCTION Qty. Part No. Part Name

ICIT S.I- M20-40-1:

2 010003-505 Baggage Strap Assy2 010003-507 Baggage Strap Rssy

S.I. M20-40 Compliance Card

COMPIJANCE: Make Log Bogk entry, fill out and return Compliance Care

MOONEY SERVICEINSTRUCTION

NUMBER: S.I. M20-62

DATE: 10-13-82

SUBJECT: REPLACEMENT of COLERERSEE, STARTER SOLENOID 7iIH CUTLER-HAMMER, P/N 6041H105A

MODELS Mooney Model M20g S/N 25-0681 thru 25-0719 and any M20 series aircraft that have had a

Cole-Hersee solenoid installed in plan of the original PrestoLite.

TIME OF COMPLIANCE: At the nut scheduled maintenance or sooner at owners discretion.

INTRODUCIlON: There have beenreports ofthe contacts sticlring closed on CoIe-Hersee starter solenoids on MooneyM20g airplmes. This causes power transmission to the_starter when the master switch is turned on. The propeller

will rotatebat the engine will not start ifmagneto switch is off. It is recommended that the Cole-Hefiee solenoid be

replaced with the improved solenoid.

INSTRUCTIONS: iC*UllIlNlCAUTION

Exetcise ertreme caution in the area of the propeller when energizing the electrical system.a) Pull AUX. BUS and IGN-TACR, CIG LTR circuit brea~ers, or disconnect battery.b) Disconnect electrical wiring from the fear (4) terminals of the Coie-Hersee solenoid. The solenoid is located on the

coc~lpit side offirewalI forrvard of the co-pilot seat on M20g and h1205. Earlier model aircraft have solenoid located

on engine side of ~ewaI1, ontboard side of pilots footwell.

c) Remove solenoid from the firewalIby unscrewing (2) AN3-3A bolts or MS35206-263 screws from nut plates.d) Retain ground wire (21PS10~8) to use with new solenoid.

e) Drill oat rivets attaching upper nut plate, see drawing 940020, and remove nut plate. Clean up bum and debris.

a Enlarge rivet hole per drawing 940020 for mounting new solenoid.

h) Plug the lower told) mounting hole with AN3-3Abolt and AN960-10 washer per drawing no. 940020.

i) Secure solenoid, P/N 6041H105A, with (2) AN3-3A bolts, (1) AN970-4 washer, (4) AN960-10 washer and (2)AN365-1032 nuts in the new location pet drawing no. 940020.

NOTE: man ground wire, 21PS10A18, under bolt head per 940020 drawing.j) Seal any holes or openings in firewall with Proseal 700 sealant per drawing 940020.

L) Ream holes in wire terminals to acwpt 3/8" posts on solenoid.

1) Connect the electrical wires to terminal posts on new solenoid per drawing 940020. Relative position of wires will

change very little from replacement of the old solenoid with the new solenoid.

m) Verify thatno interference is present between new wiring location and any other components or structure.

n) Chac~ system for normal operation and return aircraft to service.

O) Enter compliance note into log boot

REFERENCE DATA.. Drawing 940020, Cutler-IIammer Solenoid Retrofit

PARTS I;IST: Order 940020-501 git.

FIGURE/TABLES: See Drawing 940020.

NIOONEY SERVICEINSTRUCTIO

Page 1

SI M20-70

DATE: 1-1-84

SUBJECT: FUEL IDENTIFICATION DECAL.

MODEL/SERIAL NUMBERS AFFECTED: Mooney Aircraft, all models.

NOTE: M20g 25-0613 and on, M20J 24-1327 and on aircraft have these decals factory installed.

TIME OF COMPLIANCE: At owners earliest convenience.

INTRODUCTION: Mooney M20 Series aircraft have a decal applied to each fuel filler cap to indentify the typeand quantity of fuel as required by regulation for the proper operation of the engine installed in the aircraft.

To further identify the proper type of fuel required in aircraft the General Aviation Manufacturers

Association (GAMA), in a joint effort with its members, has developed a color-coded decai that can be placed

adjacent to the fuel filler openings on all aircraft. The purpose of this decal is to aid ground personnel in

selecting the proper fuel when refueling the aircraft. There have been instances of the wrong type of fuel used

to refuel some piston engine aircrafts.

INSTRUCTIONS: To obtain and apply the decals for your Mooney the following procedures should be followed.

i. Show aircraft model and serial number on the order form to your Mooney Marketing or Service

Center. Decals are 1.00 each (net).

2. When the decals are received select the desired location to apply the decals. (A recommended location

is as shown in Figure 1.) This should be so the ground servicing personnel can read the decal while

removing the fuel cap and filling the fuel tank, (normally from the leading edge side of the wing).3. Clean the area selected with a solution of water and mild aircraft detergent. Rinse thoroughly with

clean water and dry with a clean cloth.

4. Peel backing paper from decal and apply smoothly. Work out all bubbies during application. Be sure the

edges of the decal are securely stuck to aircraft surface. Peel cover mask from face of decal.

5. Follow the same procedure for selected locations adjacent to all fuel tank filler openings.6. Release aircraft to service.

REFERENCE DATA:NIA

PARTS I;IST:

QTY PART NO. DESCRlPTION

2 150080-167 Decal, Gas GradeAVGAS ONLY

FIGURES/TABLES: Figure 1. s~’GRADE GRADE

IoOLL 100

AFT

4.0 in.APPX. CO/BDFUEL FILLER CAP.

VIEW LOOKING DOWN LEFT WING

F1GURE 1

lanooNEv ~p SERVICEINSTRUCTION

Page 1

S.r. M20-73

4-24-85

SUBJECT: Mooney Aircraft Fuel Tank Repair by Field Personnel

MODELS/

S/N AFFECTED: M20B, M20C, M20D, M20E, M20F, ~v120G. M20J, M20K and M22, All Serial Numbers

TIME OF

COMPLIANCE: At every fuel tank resealing maintenance or repair.

INTRODUCTION: Reports havebeen received that fuel and water have been found trapped between ribs due

to one or more rib drain holes sealed over during resealing procedures. Service Bulletin

M20-230 has been prepared for a one-time inspection of fuel tanks.

The intent ofthis S.I. is to assure that all fuel tanks resealed by field personnel subsequentto the one-time inspection is done in accordance with S.B. M20-UO and current Mooney

procedures.

INSTRUCTIONS: Refer to the appropriate section ofyour Mooney Service and Maintenance manual, and to

Mooney Service Bulletin S.B. M20-230 land subsequent revisions) when any fuel tank

reseding is to be accomplished on any of the above listed Mooney aircraft models.

Particular attention should be shown to assure that all holes required for fuel movement

between fuel bays are open and clear of sealant.

REFERENCE I)ATAr (1) Mooney Service Bulletin M20-230 land subsequent revisions)

(2) Mooney Service Maintenance Manual (applicable to speciftc aircraft model being

repaired).

TARTS LISTr N/A

FIGURE/

TABLE: N/A

C

MOONEYSERVICE INSTRUCTION

DATE: 1-15-92

SUBJECT: REPLACEMENT OF TORSION SPRING IN DRIVE CLUTCH ASSEMBLY OF GEC (PLESSCI)LANDING GEAR ACTUATORS, MOONN P/N 880037-505 AND 880037-507.

SEE GEC (UK) AEROSPACE INC., SERVICE INSTRUCTION No. SI-ll, DATED 12/17/91or SUBSEQUENT REVISION.

MODELS/ S/N’S MOONEY M20J, S/N 24-0001 THRU 24-TEA (WTTH GEC [PLESSC~ ACTUATOR INSTALLED)AFFECTED: MOONN M20K. S/N 25-0001 THRU 25-TEA (WITH GEC[PLESSEY] ACTUATOR INSTALLED)

MOONEY M20M, S/N 27-0001 THRU 27-TEA (WTTH GEC [PLESSC/I ACTUATOR INSTALLED)MOONN M20L, S/N 26-0001 THRU 26-TEA (WITH GEC [PLESSC~ ACTUATOR INSTALLED)AND AL, M20 SERIES AIRCRAFT RETROFITTED WITH SUBJECT ACTUATORS.

TIME OFCOMPLIANCE AT 1000 FLIGHT HOURS OR SCHEDULED MAINTENANCE JUST PRIOR TO REACHING 1,000

FLIGHT HOURS.

INTRODUCTION: There have been 2 reports of a malfunction of the torsion spring at 1200 and 1500 Right hoursin GEC (Plessey) Model No. R5329M12-1 or R5329M24-1 (Mooney P/N 880037-505 and -507)landing gear actuators dun’ng operation in Mooney aircraft.This Mooney SeM’ce Instruction is to notify field maintenance personnel of the GEC (UK)Service Instruction, No S:-ll, dated 12-17-91 which requires torsion spring replacement at

1,000 Right hours.

INSTRUCTIONS:REFERENCE SEE GEC SERVICE INSTRUCTION S1-ll, DATED 12/17/91 or SUBSEQUENT REVISION.

DATA: SEE GEC SERVICE INSTRUCT(ON SI-ll, DATED 12/17/91 or SUBSEQUENT REVISION.

PARTS LIST: SEE GEC SERVICE INSTRUCTION SI-Il, DATED 12/17/91 or SUBSEQUENT REVISION.

FIGURESITABLES: SEE GEC SERVICE INSTRUCTlOl\i S1-ll, DATED 12/17/91 or SUBSEQUENT REVISION.

GEC SeM’ce Instruction Sf-ll and spring replacement kit am available from GEC (UK) Aerospace Inc.,110 Algonquin Parkway, Whippany, NJ 07981-1640, Telephone (201) 428-9898, FAX (201) 884-2277,Product Support Direct Telephone, (201) 428-8787

85-24-03 MOONEY AIRCRA~r CORPORATION: Amendment

39-5173. Applies to Models M20B, M20C, M20D, M20E, M20F, M20G, M20J, M20K, and M22

tall Sen’al Numbers (S/N~ airplanes certificated in any category.

Compliance: Within 100 hours time-in-service after the effective date of this AD or at

the next annual inspection, whichever occurs first, unless already accomplished.

To preclude fuel contarnination and water entrapment in the fuel tanks accomplish the

foElo\nring:

(a) For Models M20B, M20C, M20D,~ M20E, M20F, M20G tall S/N), M20J (S/N24-0001 through 24-1498), M20K(S/N 25-0001 through 25-0854) and M22 tall S/N) airplanes,visually inspect all fuel tank bays and rib stations in accordance with the instructions contained

in Mooney S/B M20-230, dated Apn’l 10, 1985. Repair all discrepancies found prior to further

flight.

(b) For Models M20C (S/N 2623 through 20-1258), M20D (S/N 201 through 260),M20E, M20F, M20G, M20J, M20K and M22 tall S/N) airplanes, visually inspect the fuel tank

filler cap assemblies in accordance with the instructions contained in Mooney S/B M20-229,dated Apn’l 10, 1985. Repair all discrepancies found prior to further flight.

(c) For Models M20J (S/N 24-1499 and on) and 20K (S/N 20-0855 and on) airplanesthat have had any fuel tank reseaied after initial installation at the factory, visually inspect all

fuel tank bays and db stations in accordance with the instructions contained in Mooney S/B

M20-230 dated April 10, 1985. Repair all discrepancies found prior to further flight.

(d) Airplanes may be flown in accordance with FAR 21.1 97 to a location where this

AD may be accomplished.

(e) An equivalent method of compliance with this AD, if used, must be approved bythe Manager, Airplane Certification Branch, ASW-150, Federal Aviation Administration,Southwest Region, Post Offi~ Box 1689, Fort Worth, Texas 76101.

All persons affected by this directive may obtain copies of the documents referred to

herein upon request to Mooney Aircraft Corporation, Post Office Box 72, Kenville, Texas

78028-0072 or FAA, Office of Regional Counsel, Room 1558, 601 East 12th Street, Kansas

City, Missouri 64106.

This amendment becomes effective on January 6, 1986.

CaRPORA nON