# Single Engine

# ~ Cessna A Toxtton Com " 

# Service Bulletin 

# I October 3 , 2012

TITLE AILERON HING E BRACK ET INSPECTION EFFECTIVI TYModel Year 190 1948 thru t 953 190 1948 thru 1953 195 1948 thru 1953 195 1948 thru 1953 195A 1948 thru 1953 1 95A 1948 thru 1953 1958 1948 thru 1953 

### 1958 1948 thru 1953
PURPOSE Serial Numbers 7004 thru 7999 16000 thru 16 183 7004 thru 7999 16000 th ru 16183 7004 thru 7999 16000 thru 16183 7004 thru 7999 16000 thru 16183 SE804-1 Revision 1

To inspect the inboard aileron hinge brackets for corrosion and cracks. 

### If corrosion or cracks are found, the h in ge brackets shall be replaced as directed in this Service Bulletin. Non-compliance with this Service Bulle ti n may allow corrosion or cracks to go undetected which could result in less than the designed structural inte g r ity of the aileron hinge brackets. COMPLIANCE Mandatory; shall be accomplished as a part of the next 100 hour or annuaV12 month inspection whichever occurs first and each subsequent 1 00 hour or annua l/ 12 month inspection the reafter except as noted below
. NOT E: Installation of the new 0322709 and 032 2 70 9-1 machined Aluminum h inge brackets 

### will delete the repet itive special inspection requirement. 

# I NOTE: If the aileron hinge brackets have been replaced with Aluminum brackets and if in compliance with SE804-1 Original Issue , compliance with SEB04-1 Revision 1 is not required
. APPROVAL FAA approval has been obtained on techn ical data in this publication that affects airpl ane type design. IOriginal lssu<:!: April 26. 2004 Page 1 of 7

To obtain satisfactory resulls
. proc edures spe: i fi e d in this pubhcauon must be accompl iShed in accordance with accepted methods and preva i llllg govem :n en • regul ati ons C essna Aircraft Com pa ny ca nno t bo responsible for the quality of w ork performed in accompl i shing tile requ:rements o f this publication
.**Cessn~** A ircraft Ccmpany,**~!o mer** **Se rv** **~ct~ .**  P
.O
. Box 7106
. W t chlfa
. K aMu &1277
. U
.S
.A
. (3 16 ) 517-5800. Facsi mile (3 16 )5 17-7271 www c &.ts 1 asup.por t COJn COP Y FI G HT 4:> 2004

### MATERIAL 

# I The f ollow ing are avail able from Cessna Service Parts and Programs through an appropriate Ces s na Author ized Se N i ce Fa cili ty
.



### Part Numbe r Desc r iQti o n**Qt~/Aiq2l ne**  

### 0322709 H i nge Bracket, 1 

### (if required) Left 0322709- 1 H i nge Bracket, 1 

### (if requ ired) Right MS2 1 044N 4 Nut 4 MS21044N3 Nut 1 0 U074093 Alodine 1132 (as requ i red) Marke r K00091 2 Epoxy Primer (as required)

ACCOMPLISHMENT IN STRUCTIONS Change In Weight And Balance

M ode l
. . . . . . . . . . . . . . • . . . • . . . . . . . . • . . 190/195 We i ght C han ge Negligib l e Material I nformat i on 

### T he fo llowin g parts may be n ecessar y : New PIN Quantity Des cripti on 032270 9 1 (as n ecessary} Aileron H i nge Bracket (Left) 0322709 - 1 1 

### (as necessary) Ai leron Hinge Bracket (Ri gh t) 

# I MS2 1 04 4N 4 

### 4 Nut MS21 044N3 10 Nut



# I Page 2 Old PIN Same Same Same Same Dispos it i on D iscard Discard Discard Discard

SEB04 - 1 Revis i on 1 October3, 20 1 2

# I T h e materia ls below , or equivalent may 

### be necessary. NAME NUMBER MANUFACTURER US E To u c h -N-Prep Alodine 1132 Parker Amchem 32100 To apply to bare metal. (c o lor che mica l Stephenson Highway Madison film tre atment) Heights. Michigan 48071 Co rrosion 

### 513 X 

### 419910 X 

### 942 PRC-DeSoto International To apply to bare metal. Resis tant 5430 San Fernando Road P rime r Glendale, CA 91209 1 . ( Re f er to Figure 1. Sheet 1.} Electrically gro und the airplane and turn all switches to the "OFF" position. II external powe r is connected to the airplane, disconnect external power from receptacle , 2
. Remove the batte ry access panel and disconnect the airplane battery. (Refer to the Cessna 190 & 

### 195 Pa rts Catal og. ) 3
. Attach mainte nance warning tags to the banery and external power receptacle with the following in s tru ct io ns: 

### 00 NOT CONNECT ELECTRICAL POWER - MAIN T ENANCE IN PROGRESS. 4
. M e asu re and record the range of up and down travel of both ailerons
. NOT E : The ai l e ron 

### range of travel information will be needed to install the ailerons. NOTE : The spe cified range of up travel is 

### 25 " and the down travel is 

### 25 °
. 5 . Re m ove the ailerons. (Re fer to the Cessna 190-195 Parts Catalog.) A
. D i sconnect th e a i leron pushrod fro m the ai !eron on each wing
. ( 1) l<eep the bolts a nd washers 

### if serviceable
. (2) D i sc ard the nuts. B. Remove t h e aileron attach bolts a n d was n ers from the inboard and outboard aileron brackets on e ac h w in g an d remove the ailerons. ( 1 ) l<e ep the bolts and washers if serviceable. (2) Discard the nuts. 6
.**~efe r**  

### to Fi g ure 1 , Sheet 1.} 

### Remove the inboard 0322709 (left) and inboa rd 0322709-1 (right) Aileron H ing e Bracket s f rom the wing**n~ar** 

### spar. (Refer to the Cessna 190 

### & 195 Parts Cata log. ) A . Keep t1 1e bo l ts and washers 

### if serviceable. B. Disca rd the n uts. 

### CAUTION: DO NOT USE A MECHANICAL METHOD TO REMOVE THE PAINT FROM MAGNESIUM A I LERON H I NGE BRACKETS. 7
. Remove the paint from the 0322709 and 0322709-1 Aileron H ing e Brackets. 8
. Do a v i su a l inspe ction of the 0322709 and 0322709-1 Aile ron Hi nge Brackets for corrosion and cracks. N OTE:**T~e** 

### o rig inal and o:der replacemen t inboard aileron h inge brackets were made of Magnesium which has a greater potenti al to c orrode or crack than al uminum
. A. Lo 'J I\ o n the ai ler on h inge b rackets lor identification as follows: (1) Mag nes i um forged b rackets have a 0822605-497 or a 0322707-2 mark on them. (2 } Alum inu m forged brackets have a 0822605-499 mark on them
. 

# I SEB0 4·1 Revision 1 Octob er 3, 2012 Page 3

# I 

# I 

# I (3} If the brackets have no marks, they are aluminum. B. 

### If corrosion or cracks 

### are found on the 0322709 and/or 0322709-1 Aileron Hinge Bracket, replace the bracket with 

### a new Aluminum aileron hinge bracket as necessary. 

### NOTE: The new repl acement 0322709 and 0322709- 1 Aileron Hinge Brackets 

### are A lumi num. (1 ) Apply Alodine and corrosion resistant primer to the new aileron hinge bracket part and paint to match the airplane finis h. (2) Go to Step 9 to install the new ai l eron h i nge bracket(s). C
. 

### If no corrosion or cracks are found on the 0322709 and 0322709-1 Aileron Hinge Brackets, install th e aileron hi nge brackets back on the wi ngs . (Refer to the Cessna 

### t 90 

### & -195 Parts Catalog.) 

### (1 ) Appl y corrosion resistant primer to the aileron hinge bracket part 

### and paint to match the airpi ane f ini sh. (2} Go to Step 9 to install the aileron hinge brackets. 

### 9. I nstall the a il eron hin ge brackets. (Refer to the Cessna 190 & 

### 195 Parts Catalog.) A. (Refer to Figure 1 , Sheet 2. ) 

### If 

### a new hinge bracket is being installed , the 0322715-1 Aileron Fillet may n eed to be trimmed so the new hinge bracket will 

### lit to the rear wing spar co rrectly
. ( Refer to the Cessna 190 

### 8. 195 Parts Catalog
. } B. Install 

### t he ai le ron hinge bracKets t o the rear wing spar with the kept bolts and new MS20365-1032 Nuts, 

### a nd torque each 

### nu t to 25 inch-pounds. 

### 10. I nstall the ail e ro ns o n the wings . ( Refer to the Cessna 190 

### & 195 Operation Manual. Mai nte nance

- Ailerons. ) 

### A. Insta ll the aileron attach bolts kept in Step 58(1) to the inboard aileron hinge brackets on each wing with new MS20365-428 Nuts and torque to 70 inch-pounds. (Refer to the Cessna 1 90 & 195 Pa rts Catalog
. ) 

### B. Attach the a ileron push rod to each aileron with the bolt and washers kept in Step 5A{1) and with one new MS20 365-1 032 Nut torq ued t o 25 inch-pounds. (Refer to the Cessna 190 & 195 Pa rts Catalog
. ) 11. Check and a dju st each ailero n range of travel as necessary. (Refer to the Cessna 190 & 195 Operation Manual , M ai n te nance· Ailerons.) 

### NOTE: T h e 

### specified up range of travel is 

### 25" and the down range of travel is 25°
. 

### NOTE: R efer to the record of ai l eron travel you recorded in Step 4. 12. Make s ure the tumbuckles are safetie d after adjustments are completed
. 13. Remove maintenance warning tags from the battery and the external power receptacle. 14. Conn ect t he a i rp l ane battery and install the battery access panel. (Refer to the Cessna 190 & 195 Parts C ata l o g.) 

### 15. Make an entry in th e airplane logbook that states compliance and method of compliance of th i s Service Bulletin and 

### if applicabl e , w h en the next inspection of the inboard aileron hinge brackets is due. 

### NOTE: This information shall 

### be considered an amendment to the Cessna Manufacturer's Service/ Maintenance Manual, Operation Manua l 

### or Instruct i ons for co n tinued airworth i ness and must be acc o mplished for ongoing airworthiness compliance as required per 1 4 CFR Part 43
. 13. 

# I Page4 SEB04 - 1 Revision 1 October 3, 2012ll8.'l4

CONTROL PULL EY BRACKET (REFERENCE)



# I SE804- 1 Rev i sion 1 

### October 3 , 2012 BELL CRANK STOP ASSEMBLY (REFERENCE)



### DETAIL 

# A RIGHT WING SHOWN LEFT WING OPPOSITE**Fi~ Jre**  

### 1. (Sheet 1) AILERON BELL CRANK BRACKET (REFERENCE)
WING TR AILING EDGE SPAR (REFERENCE)

0322709 (LEFT) 0322709- 1 (R IGH T ) AILERON HINGE BRACKET (REPLACE AS NECESSARY)

04!0TI001 AD424T1001



### Page 5

### 0.30



### • OU TBD 

# T

A FT W I N G UPPER SP AR CAP (REFE REN C E ) TRIM THE AILERON FILLET AS SHOWN TO AlLOW THE NEW AILERON HIN GE BRACKET TO MATCH FIT THE BRACKET HOLE S
. (NOTE3)


### DETA IL 

# 8 VIEW LOOKI NG UP LEFT WING SHOWN NOTE 

### 1: THE PUSH ROD IS NOT SHOWN FOR CLARITY
. NOT E 

### 2 : ALL D I MENS ION S SHOWN ARE I N INCHES. TH E HASH MARKED AREA SHOWS WHE R E THE AILERON HI NG E BRACKET UPPER MOUNT PAD ATTACHES TO THE UPPER A FT W I NG SPA R CAP.

A I LERON PUSHROD S L OT (REFERENCE) ( NOTE 1)

NOTE 

### 3: VIEW SHOW N IS AFT ER AILERON FILLET HAS BEEN TR IMM ED
. 9G424T1 002 

### Fi gure 1. (Sheet 2) 

# I Page 6 SEB04 · 1 

### Revi sion 1 

### October 3 , 2012

# I SE B0 4 · 1 Revision 1 October 3, 20 1 2 Page 7