Single Engine
Service Bulletin
February 25, 1994 SEB94-3
TITLE
RUDDER SPAR INSPECTION/REPLACEMENT
EFFECTIVITY
Model Series Year Serial Numbers
150 1975 thru 1977 15075782 thru 15079405
A150 1975 thru 1977 A1500524 thru A1500734
F150 1975 thru 1977 F15001144 thru F15001428
FRA150 1975 thru 1977 FRA1500262 thru FRA1500336
152 1978 thru 1985 15279406 thru 15286033
A152 1978 thru 1985 A1520735 thru A1521049
F152 1978 thru 1986 F15201429 thru F15201980
FA152 1978 thru 1986 FA1520337 thru FA1520425
PURPOSE
Service experience indicates the possibility of cracks/buckles developing in the area of a one inch hole
located near the rudder upper hinge brackets. An inspection for cracks/buckles in this area should be
conducted. If a crack or buckle is found, the rudder spar should be replaced. To assist in preventing this
condition from occurring, new strengthened replacement rudder spars are available without a hole located
near the upper rudder hinge brackets. Non-compliance with this Service Bulletin may result in loss of rudder
control.
COMPLIANCE
Recommended:
A. Initial Inspection:
Should be inspected within the next 100 hours of operation or 12 months, whichever occurs first.
B. Repetitive Inspections:
Accomplish every 100 hours of operation or 12 months after the initial inspection until installation of a
part number 0433010-6 rudder spar that does not have an access hole located near the rudder upper
hinge attach brackets.
Page 1 of 3
To obtain satisfactory results, procedures specified in this publication must be accomplished in accordance with accepted methods and
prevailing government regulations. The Cessna Aircraft Company cannot be responsible for the quality of work performed in
accomplishing the requirements of this publication.
APPROVAL
FAA approval has been obtained on technical data in this publication that affects airplane type design.
For Reims Aviation airplanes, DGAC approval has been obtained on technical data in this publication that
affects airplane type design.
MAN-HOURS
Approximately 0.5 man-hours to inspect upper rudder hinge attach area of the rudder spar.
Approximately 13.0 man-hours per airplane to remove and replace the rudder spar.
MATERIAL
The following parts are available from Cessna Parts Distribution thru an appropriate Cessna Service
Station for the suggested list price shown.
Part Number Description Qtv./Airplane Price
0433010-6 Spar, Rudder 1 $ 46.40 (S) ea.
If Required
CR763-4-4 Rivet 10 $ 0.80 (PS) ea.
If Required
MS20470AD3-2.5 Rivet 80 $ 49.20 (PS) lb.
If Required
MS20470AD3-3 Rivet 80 $ 30.70 (PS) lb.
If Required
MS20470AD3-3.5 Rivet 80 $ 24.10 (PS) lb.
If Required
MS20470AD4-3 Rivet 10 $ 25.60 (PS) lb.
If Required
NAS1738B4-1 Rivet 10 $ 0.78 (PS) ea.
If Required
NOTE: 0433010-6 rudder spars shipped from Cessna Parts Distribution after December 1, 1993 do not
have a one inch hole located near the upper rudder hinge bracket area.
ALL PRICES SUBJECT TO CHANGE WITHOUT NOTICE
ACCOMPLISHMENT INSTRUCTIONS
Rudder Spar Inspection/Replacement Accomplishment Instructions are attached.
CREDIT
Not applicable.
SEB94-3
Page 2 February 25, 1994
OWNER NOTIFICATION
On March 11, 1994 the following Owner Advisory message will be sent to applicable owners of record in
SEB94-3A.
Dear Cessna Owner:
Service experience indicates the possibility of cracks/buckles developing in the area of a one inch hole
located near the rudder upper hinge brackets. An inspection for cracks/buckles in this area should be
conducted. If a crack or buckle is found, the rudder spar should be replaced. To assist in preventing this
condition from occurring, new strengthened replacement rudder spars are available without a hole located
near the upper rudder hinge brackets. Non-compliance with this Service Bulletin may result in loss of
rudder control.
Compliance is recommended;
A. Initial Inspection:
Should be inspected within the next 100 hours of operation or 12 months, whichever occurs first.
B. Repetitive Inspections:
Accomplish every 100 hours of operation or 12 months after the initial inspection until installation of a
part number 0433010-6 rudder spar that does not have an access hole located near the rudder
upper hinge attach brackets
Please contact a Cessna Single Engine Service Station for detailed information regarding the
accomplishment of this Service Bulletin on your airplane.
SEB94-3
February 25, 1994 Page 3
ACCOMPLISHMENT
Single-Engine INSTRUCTIONS
SEB94-3
TITLE RUDDER SPAR INSPECTION/REPLACEMENT
EFFECTIVITY
MODEL(S) SERIAL NUMBERS
150 15075782 thru 15079405
A150 A1500524 thru A1500734
F150 F15001144 thru F15001428
FRA150 FRA1500262 thru FRA1500336
152 15279406 thru 15286033
A152 A1520735 thru A1521049
F152 F15201429 thru F15201965
FA152 FA1520337 thru FA1520415
DESCRIPTION
To inspect the rudder spar at the upper hinge bracket location around the one inch diameter hole for
wrinkles or cracks.
APPROVAL
FAA approval has been obtained on technical data in this publication that affects airplane type design.
For Reims Aviation airplanes: DGAC approval has been obtained on technical data in this publication
that affects airplane type design.
REFERENCE
SEB94-3
CHANGE IN WEIGHT AND BALANCE
WEIGHT INCREASE ............ Negligible
February 25, 1994 Page 1 of 5
To obtain satisfactory results, procedures specified in this publication must be accomplished in accordance with accepted methods and
prevailing government regulations. The Cessna Aircraft Company cannot be responsible for the quality of work performed in
accomplishing the requirements of this publication.
The Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277, U.S.A. (316) 941-7550, Facsimile (316) 942-9006
COPYRIGHT 1994
ACCOMPLISHMENT
INSTRUCTIONS
SEB94-3
MATERIAL INFORMATION
NOTE: If cracking of the rudder spar or evidences of side buckling is present,
the following parts will be required to replace the rudder spar:
PART NUMBER QUANTITY DESCRIPTION
0433010-6 1 Spar-Rudder
CR763-4-4 10 Rivet-Rudder Cap
Assembly Attach
MS20470AD3-2.5 80 Rivet-Skin Attach
MS20470AD3-3 10 Rivet-Skin Attach
MS20470AD3-3.5 34 Rivet-Skin Attach
and Hinge Half Attach
MS20470AD4-3 10 Rivet-Hinge Attach
NAS1738B4-1 10 Rivet-Clip Attach
ACCOMPLISHMENT INSTRUCTIONS
1. Ensure a maintenance tag is displayed in full view in the cabin stating:
WARNING: DO NOT OPERATE AIRPLANE - MAINTENANCE IN PROGRESS
2. (Refer to Figure 1, Sheet 1, Detail A, and Sheet 2, Detail B and View C-C.) Inspection of the rudder
spar:
A. Position the rudder in the neutral (centerline) position. Visually inspect the outer surface of the
rudder skins around the area of the upper attach hinges for cracks in the skins or wrinkles. If
skins are wrinkled, remove and replace using appropriate parts listed in the Model 150 or Model
152 Illustrated Parts Catalog.
B. Position the rudder full left to reveal the right side of the rudder spar. The rudder spar is formed
from 0.020 inch aluminum clad sheet, and has a one-inch hole in the spar web located just below
the upper hinge bracket. Using a flashlight look through the spar below the upper rudder attach
hinges at the hole. Look specifically for cracks radiating from the one-inch hole.
C. Position the rudder full right to reveal the left side of the rudder spar. Again look through the
spar below the upper rudder attach hinges for cracks radiating from the one-inch hole. Proceed
to step 3.
3. If cracks are found, replace the rudder spar using the part numbers listed in the Material Information
section of these instructions.
NOTE: The replacement spar does NOT have the one-inch hole in the spar web below the upper
hinge brackets. This reduces access to this area to buck rivets, therefore, sufficient rivets
will need to be drilled out to allow one side of the rudder skin to be raised to gain access to
buck the rivets common to the hinge brackets and ribs. Pull-type rivets are NOT to be
used common with the hinge brackets.
Page 2
ACCOMPLISHMENT
INSTRUCTIONS
SEB94-3
A. Install the replacement rivets beginning with those common to the hinge brackets and spar web,
then working down from the upper hinge area, bucking those common to the ribs, spar and skin.
B. Install the replacement rivets above the upper hinge working forward and up, finishing with those
rivets at the balance weight attach area.
NOTE: It is permissible to install one rivet size larger providing a minimum edge distance of
1.5 rivet diameter is maintained.
4. Make an entry in the airplane logbook stating compliance with this service bulletin and method of
compliance.
Page 3
ACCOMPLISHMENT
INSTRUCTIONS
SEB94-3
CR763-4-4 RIVET
TO BUCK RIVETS COMMON
TO HINGE BRACKETS AND-
SPAR WEB
DETAIL A
Figure 1. Rudder Inspection/Replacement (Sheet 1 of 2)
Page 4
ACCOMPLISHMENT
INSTRUCTIONS
SEB94-3
EXISTING EXISTING
RUDDER SPAR RUDDER SPAR
(REFERENCE (REFERENCE)
EXISTING
1.0 INCH
HOLE
(REFERENCE)
UPPER ATTACH
HINGES
CRITICAL (REFERENCE)
INSPECTION
AREA
EXISTING
NOTE: THE
0534126-6 REPLACEMENT
CLIP SPAR DOES NOT
(REFERENCE) _ HAVE THIS ONE-
DETAIL B NAS1738B4-1 INCH HOLE
RIVET
(10 REQUIRED)
VIEW C-C
(VIEW LOOKING FORWARD AT
AFT SURFACE OF RUDDER SPAR)
Figure 1. Rudder Inspection/Replacement (Sheet 2)
Page 5
