CESSNA 336/337 AIRCRAFT "STRUCTURAL" SERVICE DIFFICULTY REPORTS (SDRS)
(Complete Draft, Rev. 3, Sept. 11, 2009)

In response to the FAA’s National Aging Aircraft Program, aircraft manufacturers are considering development of Supplemental Inspection Documents (SIDs) specifying inspections and/or modifications to maintain the airworthiness of aging aircraft. One of the aircraft models that may come under an SID program is the Cessna 336/337 (Skymaster) aircraft.

The data below has been prepared by ConsultResearch Inc.1 in connection with any such SIDs. The work was done primarily by Ernie Martin2. The data was extracted from approximately 1,000,000 Service Difficulty Reports furnished to the FAA since the early 1970's. Filtering was used to gather those involving only Cessna 336/337 aircraft. The data was then analyzed and only those related to structural aspects or aging effects were retained. We erred on the side of inclusion, so that a report where the decision could go either way was retained.

The retained reports for the Model 337 were then organized by area of the aircraft. Within most areas, those reports we deemed more relevant to possible SIDs appear first, and those we judged less relevant then follow; the reports appear in reverse calendar order, starting with the most recent within each group. Those reports that deal with two adjacent areas appear twice, because in the table they are shown in both areas. The figures (which come from the Illustrated Parts Catalog) were added by us for convenience, so that part numbers in the reports are quickly identified.

The retained reports for the Model 336 were so few that they appear in a separate table at the bottom, unarranged by group, newest first.

The number at the start of each row is for internal reference and is not relevant.

RELATES TO FUSELAGE (excluding door mechanism and pedal area)
RowDate Of ReportOperator Control NumberSegmentDate Of OccurrenceAircraft RegistrationOperation TypeDescriptive Name Of PartDefective Location On AircraftFailed Part ConditionPart Total TimePart Total Time Since OverhaulComponent ManufacturerComponent Manufacturer ModelComponent Manufacturer NumberStage Of OperationSeverity FactorAircraft ManufacturerAircraft Manufacturer ModelAircraft Manufacturer NumberPrecautionary ProceduresNature Of ConditionzxcvbRemarkszxcvb
462003-05-15CH1A200393049AIRFRAME2003-04-24293ASTRINGERFUSELAGECRACKED           INSP/MAINT   CESSNAT337GP3370226NONEOTHERSTRINGER 26R CRACKED AT BS 46.
222001-08-08AUS20010417AIRFRAME2001-05-04   GFRAMEFUSELAGECORRODED           INSP/MAINT   CESSNA337   NONEOTHER(AUS) RT ROOF SUPPORT FORMER LOWER EDGE CONTAINED INTERGRANNULARCORROSION.
312000-04-2520000417SH010AIRFRAME2000-03-2153522GSKINFUSELAGECORRODED           INSP/MAINT   CESSNA337G33701680NONEOTHERDURING A 100-HOUR INSPECTION, A SECTION OF MATERIAL USED FOR DAMPING ''OIL CANNING'' WAS REMOVED FROM THE INTERIOR FUSELAGE SKIN BELOW THE AFT SIDE WINDOW. HEAVY CORROSION WAS FOUND ACROSS THE ENTIRE AREA COVERED BY THE MATERIAL. THIS MATERIAL IS USED EXTENSIVELY THROUGHOUT THE AIRFRAME AT MANUFACTURE. (X)
261989-09-12NM018995643AIRFRAME1989-08-266297FGCABIN ROOFFS 135.45CORRODED 0 0       INSP/MAINTUNCOMMONCESSNA337A3370297NONEOTHERTHE CABIN ROOF INTERIOR FROM FS 135.45 TO 165.09 AND LBL 13.75 TO RBL 13.75 WAS CORRODED UNDER THE INSULATION TO THE EXTENT THAT THE SKIN REQUIRED REPLACEMENT. THREE OF THE STIFFENERS WERE LYING LOOSE ON THE INSULATION. APPROXIMATELY 40 PERCENT OF THE SKIN RIVETS WERE HELD BY THE EXTERIOR PAINT ONLY. SUBMITTER RECOMMENDS THAT THIS AREA BE MADE A REQUIRED AREA FOR INSPECTION.
281978-04-14Z197810400035AIRFRAME   861CP   SKINCABIN OVERHEADCORRODED 0 0       INSP/MAINTOVER 24 MOCESSNA3373371060NONEOTHEREXTENSIVE CORROSION BETWEEN CABIN TOP SKIN AND SOUND DEADENING MATERIAL
111977-08-16Z197722800036AIRFRAME   53480     INTERNAL BAFFLECORRODED 425 425       INSP/MAINTOVER 24 MOCESSNA337G33701651NONEOTHERCORROSION DEVELOPED UNDER INTERNAL BAFFLE
41977-07-26Z197720700027AIRFRAME   2FOR   SPARFUSELAGECRACKED-BUCKLED 900 900       INSP/MAINTOVER 24 MOCESSNA337GP3370029NONEOTHERTHE CARRY-THRU SPAR ASSEMBLY CRACKED AND BUCKLED.
241975-10-08Z197528100052AIRFRAME   2629S   LINETOP REAR CABINHOLES 789 789       INSP/MAINTOVER 24 MOCESSNA3373370929NONEFLUID LOSSMOISTURE IN HEADLINER CAUSING CORROSION & LEAKING OF FUEL LINE.NEEDS RUBBER SLEE VE OR PAINT.ALSO TOP SKIN LAP SEALD
(Less significant items below)
271994-07-1994ZZZX4012AIRFRAME1994-07-0192GDGFIREWALLAFT ENGINERIVETS PULLED 5,096 0       INSP/MAINTNEVERCESSNAP337HP3370343NONEOTHERUPON C/W 100-HOUR ANNUAL INSPECTION, FOUND SEVERAL RIVETS SECURING REAR FIREWALL WERE BROKEN AND PULLED THROUGH FIREWALL. ALSO NOTED ENGINE MOUNT BOLTS DID NOT HAVE CORRECT HARDWARE AND WAS NOT TORQUED PROPERLY WHICH CAUSED A VIBRATION WHICH COULD HAVE CAUSED RIVET FAILURE. ENGINE BAFFLES CRACKED AND DAMAGED.
361988-03-22CE658876325AIRFRAME   88HGSIDE WINDOW   UNBONDED 4,677 4,677       INSP/MAINTNEVERCESSNAT337H1947NONEOTHER, UNKNOWNFOUND WINDOWS HAD COME UNBONDED FROM FUSELAGE PREDOMINANTLY AROUND CORNERS OF WINDOWS. THIS ALLOWED RAIN WATER OR WASH WATER TO LEAK IN AROUND WINDOWS AND SOAK UNDERLYING INSULATION CAUSING CORROSION OF FUSELAGE STRUCTURE. NOTE - THESE WINDOWS ARE ONLY GLUED IN WITH PRC TYPE MATERIAL. THE SEALANT DOES NOT SEEM TO ADHERE WELL TO THE SMOOTH SURFACE OF THE WINDOW.
271983-07-15SW99198381529AIRFRAME   86106GOUTER DOOR SKINCABIN DOORCORROSION 2,205 2,205       INSP/MAINTNEVERCESSNA337D1083NONEOTHERFOUND CORROSION ON INNER SURFACE OF OUTER DOOR SKIN, CAUSED BY WATER ABSORBING INTO FIBERBOARD BACKING.

RELATES TO WING (including strut, but excluding aileron)
RowDate Of ReportOperator Control NumberSegmentDate Of OccurrenceAircraft RegistrationOperation TypeDescriptive Name Of PartDefective Location On AircraftFailed Part ConditionPart Total TimePart Total Time Since OverhaulComponent ManufacturerComponent Manufacturer ModelComponent Manufacturer NumberStage Of OperationSeverity FactorAircraft ManufacturerAircraft Manufacturer ModelAircraft Manufacturer NumberPrecautionary ProceduresNature Of ConditionzxcvbRemarkszxcvb
212005-02-01CA040930002AIRFRAME2004-09-29   GSKINLT WINGCRACKED           INSP/MAINT   CESSNAT337G   NONEOTHER(CAN) DURING INSPECTION, CRACKS WERE DISCOVERED AT THE IB END OF THE LT AND RT UPPER OB WING SKINS WHERE THEY UNDERLAP THE FUEL TANK BAY COVERS. THE CRACKS ARE LOCATED IN THE RADIUS OF CUTOUT AREAS IN THE SKINS WHERE THE STINGERS JOIN AT WING STATION 150.0. THE AIRCRAFT IS EQUIPPED WITH FLINT WING TIP FUEL TANKS THAT WERE INSTALLED APPROXIMATELY 800 HOURS AGO. IT IS NOT KNOWN IF THIS IS A CONTRIBUTING FACTOR.
361982-07-26GL10198281597AIRFRAME   5426SGDOUBLERREAR WING SPARCRACKER 5,342 5,342       INSP/MAINTCOMMONCESSNA337B3370526NONEOTHERREAR WING SPAR DOUBLER FOUND CRACKED DURING INSPECTION.
191979-08-07Z197921900078AIRFRAME   1347L   ANGLEREAR SPARCRACKED 137 137       INSP/MAINTCOMMONCESSNAT337H33701839NONEOTHERTHE ANGLE THAT ATTACHES ROOT RIB TO REAR SPAR OF RT WING CRACKED.
101979-07-23Z197920400044AIRFRAME   475DF   SPAR CAPLT WINGCRACKED 3,579 3,579       INSP/MAINTCOMMONCESSNAM337B3370343NONEOTHERCW AD 78-09-05 FOUND LT WING FRONT LOWER SPAR CAP CRACKED FWD & AFT FASTENERS
141976-05-05Z197612600042AIRFRAME   2FOR   SPAR ATTACHMENTRT REAR WINGFAILED 570 570       CRUISEOVER 24 MOCESSNA337G33701633OTHEROTHERSTRUCTURE FAILURE IN FLIGHT.RT REAR WING SPAR ATTACHMENT TO FUSELAGE IN WING.FAI LURE PARTIALLY HIDDEN BY INBD RIB
471975-11-24Z197532800037AIRFRAME   2FOR   SKINSREWS AT TANKCRACKED-DEFORM 1,319 1,319       INSP/MAINTOVER 24 MOCESSNASTC3373370502NONEOTHERROBERTSON STOL CONVERSION PER STC NO SA 1627 WE, WING SURFACE PAINT PEELED, CRA CKED AND DEFORMED AT WING STRUT.
461975-11-24Z197532800036AIRFRAME   2FOR   SKINSCREWS AT TANKCRACKED-DEFORM 1,481 1,481       INSP/MAINTOVER 24 MOCESSNASTC3373370683NONEOTHERROBERTSON STOL CONVERSION PER STC NO SA 1627 WE, WING SURFACE PAINT PEELED,CRACK ED AND DEFORMED AT WING STRUT
311975-06-23Z197517400035AIRFRAME   86530   SPARREAR CARRY TDRUCRACK&KINK 820 820       INSP/MAINTOVER 24 MOCESSNA337E33701224OTDEROTDERDURING AUTOPILOT INSTL AT REPAIR STA FOUND CRACK & KINK IN CARRY TDROUGH WING CE NTER SECTION REAR SPAR
(Less significant items below)
192001-08-08AUS20010414AIRFRAME2001-05-04   GRIVETWINGLOOSE           INSP/MAINT   CESSNA337   NONEOTHER(AUS) LT WING STRUT ATTACHMENT RIB TO OUTBOARD TIP RIVETS LOOSE AND MISSING. LEADING EDGE HAD BEEN REPLACED IN 1972.
432001-03-05CA001228030AIRFRAME2000-11-15   AFUEL TANKRT WINGCRACKED 2,900         INSP/MAINT   CESSNA337H   NONEFLUID LOSS(CAN) WHILE BEING STORED IN A HANGAR RIGHT WING WAS DISCOVERED TO BE LEAKING FUEL. UPON FURTHER INSPECTION NR3 FUEL TANKP/N 1516132-16 HAD A CRACK ON TOP NEAR THE TRAILING EDGE. FUEL TANK WAS THEN REMOVED, REPAIRED AND REINSTALLED.
281994-07-1994ZZZX4022AIRFRAME1994-07-0592GDGRIVETLT WS 66SHEARED 5,096 0       INSP/MAINTCOMMONCESSNAP337HP3370343NONEUNKNOWNTWO RIVETS FAILED AT LT WS 66, ON UPPER FORWARD SPAR CAP. THIS A/C HAS HAD THE ROBERTON STOL CONVERSION AND THE OUTBOARD RIVET FOUND UPSET BETWEEN THE RIB AND SPAR CAP. FAILURE ATTRIBUTED TO IMPROPER INSTALLATION.
261994-07-1194ZZZX3806AIRFRAME1994-05-20285GFUEL TANKRT INBDCRACKED 2,219 0       INSP/MAINTFREQUENTCESSNAT337GP3370228NONEFLUID LOSSFUEL STAIN ON RT FUSELAGE AND ON GROUND AFTER TOPPING OFF FUEL TANKS THE NIGHT BEFORE. REMOVED INBOARD TANK COVER, FOUND .75 INCH LONG CRACK ACROSS A PREVIOUS WELD REPAIR. THIS IS SECOND CRACK IN TOP OF SKYMASTER TANK FOUND IN 6 MONTHS. IN THIS CASE, CRACK WAS AT AREA WHERE FORMED STIFFENING AREAS TRANSITIONED INTO FLAT SURFACE. SUBMITTER SUGGESTED POSSIBLE CAUSE WAS VIBRATION. WELDED REPAIRS ARE NOT SPECIFIED IN SERVICE MANUAL.
251981-03-13NM66198175760AIRFRAME   2QVGTANKR/H INBDLEAKING 650 650       INSP/MAINTFREQUENTCESSNAP337HP3370294NONEFLUID LOSSTANK CORRODED + LEAKING R/H INBD
131981-02-24NM41198173839AIRFRAME   42WAGCELL   LEAKING 0 0       INSP/MAINTFREQUENTCESSNAT337GP3370205NONEFLUID LOSSFOUND FUEL STAINS ON BOTTOM OF RT WING NEAR QUICK DRAIN.FOUND FUEL CELL LEAKING ON BOTTOM ALONG WELDED BAFFLE.
441978-08-22Z197823400060AIRFRAME   2488S   BOOM SUMP TANKTOWER WELDCRACKED 1,450 1,450       INSP/MAINTOVER 24 MOCESSNA3370788NONEOTHERDURING INSP FOUND WELD AREA AROUND TOWERS CRACKED
121977-08-17Z197722900072AIRFRAME   72241   FUEL TNKLFT INBCRACKED 0 0       UNKNOWNOVER 24 MOCESSNA337G33701545OTHEROTHERLFT INB FUEL TNK HAD FATIGUE CRK. CRK OCCURED AT STIFFENER.
111977-04-04Z197709400044AIRFRAME   53511     TOP OF TANKCRACKED 780 780   151613317   INSP/MAINTOVER 24 MOCESSNA33733701671NONEOTHERFOUND 1.5 INCH LONG CRACK ON TOP OF TANK. LEFT INBOARD.
141976-07-21Z197620300056AIRFRAME   326     BOTTOM REARCRACKED 85 85   151613326   CRUISEOVER 24 MOCESSNAT337GP3370238NONEOTHERFUEL LEAKING FROM RT TANK TRACED TO THREE INCH CRACK IN BOTTOM OF TANK AT REAR BULKHEAD.
331976-06-08Z197616000081AIRFRAME   111LK   FAIRINGLEFT STRUTCRACKED 570 570       INSP/MAINTOVER 24 MOCESSNA337G1503NONEOTHERLEFT STRUT FAIRING FOUND CRACKED THRU ALL MOUNTING HOLES TOP AND BOTTOM.
211975-10-02Z197527500046AIRFRAME   8CF     RT WINGCRACKED 497 497   151612016   INSP/MAINTOVER 24 MOCESSNAT337GP3370043NONEOTHERDURING INSP FOUND 1.50 IN CRACK IN TOP OF RT WING CENTER TANK
151975-09-24Z197526700052AIRFRAME   10MM     LT WG INBD TKLEAKING 1,668 1,668   142600337   INSP/MAINTOVER 24 MOCESSNA337D0986NONEOTHERTANK LEAKING AT WELDS. TANK HAD OTHER WELDS TO POROUS TO REPAIR.
291975-04-09Z197509900083AIRFRAME   79N     RT WING INBDCRACKED 1,388 1,388   142600516   INSP/MAINTOVER 24 MOCESSNA3373370726NONEOTHERRT AUX FUEL TANK DEVELOPED CRACKED ON TOP SIDE INBOARD AFT CORNER AREA. CRACK CA USED BY FLEXING OF TANK.
281974-07-22Z197420300037AIRFRAME   1872M     LT BOTTOMCRACKED 484 484   15160571   INSP/MAINTOVER 24 MOCESSNA337G33701472NONEFLUID LOSSFUEL UNDER SIDE LT WING.LT INBD TANK CRACKED AT INNER TANK BAFFLE WELD LOWER SID E
161974-06-21Z197417200066AIRFRAME   83C   FAIRING ASSYRT WING-STRUTCRACKED 95 95       INSP/MAINTOVER 24 MOCESSNA3370241OTHEROTHERUPPER RT WING STRUT FAIRING CRACKED AT ATTACHING SCREW

RELATES TO AILERON
RowDate Of ReportOperator Control NumberSegmentDate Of OccurrenceAircraft RegistrationOperation TypeDescriptive Name Of PartDefective Location On AircraftFailed Part ConditionPart Total TimePart Total Time Since OverhaulComponent ManufacturerComponent Manufacturer ModelComponent Manufacturer NumberStage Of OperationSeverity FactorAircraft ManufacturerAircraft Manufacturer ModelAircraft Manufacturer NumberPrecautionary ProceduresNature Of ConditionzxcvbRemarkszxcvb
421980-06-19CE64198072856AIRFRAME   53475GCONTROL RODEND TO RIVETCRACKED 490 490       INSP/MAINTOCCASIONALCESSNA33733701649NONEOTHERLT AIL PUSH-PULL TUBE CRACKED FROM END OF TUBE TO LAST RIVET HOLE THAT ATTACHES ROD END BEARING.
211987-08-04SO638783469AIRFRAME1987-06-292111XGPUSH PULL RODR/H AILSEVERE RUST 0 0       INSP/MAINTOCCASIONALCESSNA3373370011NONEOTHERLAST FOUR INCHES OF LT AND RT AILERON PUSH RODS SEVERELY RUSTED PROBABLE CAUSE WAS EXPOSURE TO OUTSIDE ELEMENTS. PUSHRODS WERE REPLACED. SUBMITTER RECOMMENDS EXTRA ATTENTION DURING SCHEDULED INSPECTIONS.
201987-08-04SO638783468AIRFRAME1987-06-292111XGPUSH PULL RODL/H AILSEVERE RUST 0 0       INSP/MAINTOCCASIONALCESSNA3373370011NONEOTHERLAST FOUR INCHES OF LT AND RT AILERON PUSH RODS SEVERELY RUSTED PROBABLE CAUSE WAS EXPOSURE TO OUTSIDE ELEMENTS. PUSHRODS WERE REPLACED. SUBMITTER RECOMMENDS EXTRA ATTENTION DURING SCHEDULED INSPECTIONS.
(Less significant items below)
391986-02-24SW998672908AIRFRAME1986-02-03465DFGAILERON CABLEBELLY PULLEYFRAYED 5,642 5,642       INSP/MAINTOCCASIONALCESSNAM337B337M0266NONEOTHERALL CABLES WERE REMOVED DUE TO HIGH AIRFRAME TIME. ALL CABLES HAD A MINIMUM OF ONE STRAND BROKEN. NONE OF THE DAMAGE COULD BE FOUND WITHOUT REMOVING CABLE ASSY.
81977-03-22Z197708100027AIRFRAME   72036   BRACKETINBD CORNERFAILED 730 730       INSP/MAINTOVER 24 MOCESSNA337G33701510OTHEROTHERWHILE TENSIONING CABLES AFTER A-P INST,LT AILERON PULLEY BKT FAILED AT INBD ATCH HOLE,APPEARS BKT OUT OF LINE
231976-12-14Z197634900053AIRFRAME   86513   SCREWSRT AIL BAL WTLOOSE 1,439 1,439       UNKNOWNOVER 24 MOCESSNA337E33701216OTHEROTHER3 SCREWS LOOSE ON RT AILERON BALANCE WT

RELATES TO HORIZONTAL STABILIZER (excluding elevator)
RowDate Of ReportOperator Control NumberSegmentDate Of OccurrenceAircraft RegistrationOperation TypeDescriptive Name Of PartDefective Location On AircraftFailed Part ConditionPart Total TimePart Total Time Since OverhaulComponent ManufacturerComponent Manufacturer ModelComponent Manufacturer NumberStage Of OperationSeverity FactorAircraft ManufacturerAircraft Manufacturer ModelAircraft Manufacturer NumberPrecautionary ProceduresNature Of ConditionzxcvbRemarkszxcvb
311994-08-1594ZZZX4488AIRFRAME1994-07-017CPGRIBHORIZ STAB LECRACKED 2,655 0       INSP/MAINTUNCOMMONCESSNAT337GP3370016NONEOTHERDURING ANNUAL INSPECTION, A SMALL CRACK WAS FOUND NEAR THE RIVET LINE ON THE UNDERSIDE OF THE LEADING EDGE SKIN JUST AFT OF THE DE-ICE BOOT OR THE HORIZONTAL STABILIZER. UPON FURTHER INSPECTION AND REMOVAL OF THE DE-ICER BOOT, NUMEROUS HOLES AND CRACKS WERE FOUND ALONG THE LEADING EDGE SKIN DUE TO RIVETS WHICH HAD PULLED THROUGH THE SKIN. REMOVAL OF THE HORIZONTAL LEADING EDGE SKIN REVEALED SIX LEADING EDGE RIBS AND THREE CENTER SECTION RIBS WHICH WERE CRACKED.
301994-08-1594ZZZX4487AIRFRAME1994-07-017CPGSKINHORIZONTAL STABCORRODED 2,655 0       INSP/MAINTUNCOMMONCESSNAT337GP3370016NONEOTHERDURING ANNUAL INSPECTION, A SMALL CRACK WAS FOUND NEAR THE RIVET LINE ON THE UNDERSIDE OF THE LEADING EDGE SKIN JUST AFT OF THE DE-ICE BOOT OR THE HORIZONTAL STABILIZER. UPON FURTHER INSPECTION AND REMOVAL OF THE DE-ICER BOOT, NUMEROUS HOLES AND CRACKS WERE FOUND ALONG THE LEADING EDGE SKIN DUE TO RIVETS WHICH HAD PULLED THROUGH THE SKIN. REMOVAL OF THE HORIZONTAL LEADING EDGE SKIN REVEALED SIX LEADING EDGE RIBS AND THREE CENTER SECTION RIBS WHICH WERE CRACKED.
481986-06-11SW688679326AIRFRAME1986-04-17140VEGSTABR/H VERT FINBOLT SHEARED 3,650 3,650       INSP/MAINTUNCOMMONCESSNA337H33701945NONEUNKNOWNDURING ANNUAL INSP HORIZ STAB FOUND LOOSE AT FWD ATTACH POINT TO R/H VERTICAL FIN. FURTHER INVESTIGATION REVEALED BOTTOMATTACH BOLT MISSING HEAD AND UPPER BOLT LOOSE DUE TO WEAR OF DOUBLER AFT OF SPAR. UPPER HOLE FOUND ELONGATED TO 1/2 INC H. BOTTOM OF SPAR WEB DAMAGED BY CHAFING ON NON-STRUCTURAL SKIN OF VERTICAL FIN. DAMAGE TO VERTICAL FIN SPAR WEB ON LEFTAND RIGHT SIDE WAS NOTED IN THE FORM OF SLIGHT ELONGATION OF 1/4 INCH BOLT HOLES. PROBABLE CAUSE NOT READILY APPARENT, ALTHOUGH REAR ENGINE VIBRATION MAY HAVE AGRAVATED SOME DAMAGE NOT NOTICED AFTER GEAR-UP LANDING IN 1984. ANNUAL INSPECTION OF PREVIOUS YEAR SHOWED NO APPARENT PROBLEM IN THIS AREA. RECOMMEND MORE STRINGENT ANNUAL INSP REQUIRED.
171976-01-13Z197601300034AIRFRAME   2107X   SPARFRONT STABCHAFED 2,186 2,186       INSP/MAINTOVER 24 MOCESSNA3373370007NONEOTHERDURING INSP,HORIZ STAB WAS FOUND TO HAVE DAMAGE ON BOTH ENDS.FUSELAGE SKIN HAD C HAFED THE SPAR WEB & RADIUS-SPAR CP

RELATES TO ELEVATOR
RowDate Of ReportOperator Control NumberSegmentDate Of OccurrenceAircraft RegistrationOperation TypeDescriptive Name Of PartDefective Location On AircraftFailed Part ConditionPart Total TimePart Total Time Since OverhaulComponent ManufacturerComponent Manufacturer ModelComponent Manufacturer NumberStage Of OperationSeverity FactorAircraft ManufacturerAircraft Manufacturer ModelAircraft Manufacturer NumberPrecautionary ProceduresNature Of ConditionzxcvbRemarkszxcvb
381995-04-2195ZZZX1909AIRFRAME1995-03-162284XGRIBELEV END RIB LTCRACKED 1,060         INSP/MAINT   CESSNA3373370184NONEOTHEREND RIB WHERE PN 1532009-203 (part 36 in fig. below) ATTACHES, BADLY CORRODED AND CRACKED. ELEVATOR ACTUATING ARM HAS STEEL BRACKET, WAS BADLY RUSTED AND RIVETS SHEARED.
421990-05-23WP119085510AIRFRAME1990-03-1586488GBALANCE ARMELEV TORQUE TUBEHOLES ELONGATED 2,050 2,050       INSP/MAINTUNCOMMONCESSNAT337T33701208NONEFLT CONT AFFECTEDOWNER COMPLAINED ABOUT BOOM BOUNCE IN CRUISE. FOUND HOLES ELONGATED IN ELEVATOR BALANCE WEIGHT ARM TORQUE TUBE ASSEMBLY ALLOWING MOVEMENT BETWEEN ARM AND TORQUE TUBE WHICH ALLOWS ELEVATOR TO FLUTTER.
101986-11-05SW618687818AIRFRAME1986-09-155KRGBELLCRANKELEV TRIMELONGATED HOLES 0 0       INSP/MAINTUNCOMMONCESSNAP337HP3370335NONEOTHERON 100 HR INSP, SEVERE UP AND DOWN TRAVEL OF ELEVATOR TRIM TAB IN A STATIC CONDITION WAS DISCOVERED. FURTHER INVESTIGAT ION REVEALED ELONGATED HOLES IN BOTH (2 EA) NR 1432023-1 BELLCRANK LINKS (part 21 in fi. below). THESE LINKS ARE APPROX .030 INCH THICKNESS EA CH. NEW LINKS WERE MANUFACTURED IN HOUSE OF .060 INCH THICKNESS ALUMINUM AND INSTALLED. ADDITIONAL EFFECTS OF THIS PAR T FAILURE INCLUDE IMPENDING FAILURE OF THE ELEVATOR TRIM TAB HINGES. PART NR 1432010-30 AND NR 1432010-32. NOTE - NO CONTROL VIBRATIONS WERE NOTED BY OPERATORS.
221985-07-03EU51198580252AIRFRAME   19MCGLINKBOLT HOLEWORN 0 0       NOT REPORTEDUNCOMMONCESSNA337GP3370015NONEFLT CONT AFFECTED, VIBRATION/BUFFETBOLT HOLE IN ELEV TAB ACTUATOR LINK WORN CAUSING TAB TO VIBR AND FLUTTER.
11985-03-28EU51198574609AIRFRAME   2FORGELEV ACT ARMPIN BORECRACKED 890 890       INSP/MAINTUNCOMMONCESSNAT337GP3370288NONEOTHERDURING 200 HR INSP, FOUND LH + RH ELEV ACT ARMS CRKD AT INNER FACE OF ATTACH.CRKS START AT LARGE SIDE OF PIN BORE. ENTRDAS 2 RPTS.
501985-03-28EU51198574608AIRFRAME   2FORGELEV ACT ARMPIN BORECRACKED 890 890       INSP/MAINTUNCOMMONCESSNAT337GP3370288NONEOTHERDURING 200 HR INSP, FOUND LH + RH ELEV ACT ARMS CRKD AT INNER FACE OF ATTACH.CRKS START AT LARGE SIDE OF PIN BORE.ENTRD AS 2 RPTS.
121984-05-25WP08198478208AIRFRAME   2424SGARMFWD ATT BOLTBROKE 1,217 1,217       INSP/MAINTUNCOMMONCESSNA337B3370724NONEOTHERELEV TRIM TAB ARM BROKE AT FWD ATTACH BOLT.
371980-12-02GL03198082475AIRFRAME   60EGSKIN-RIBSLEADG EDGECRACKED 0 0       INSP/MAINTUNCOMMONCESSNAP337HP3370124NONEOTHERRIBS CRACKED AND REPLACED SKIN AND PART NOS. 1432018-51, 1432018-51 AND 1432018-52 (parts 4, 13, 14 in fig. below).
321980-10-29CE64198080898AIRFRAME   3666XGROD END   BROKE 2,193 2,193       CRUISEUNCOMMONCESSNA337A3370496NONEFLT CONT AFFECTEDELEV LOWER CONTROL ROD END BROKE DURING FLT SEPARATING ELEV FROM ELEV CONTROL SY STEM.BREAK WAS IN THREADED AERA
451978-08-22Z197823400063AIRFRAME   2488S   WEIGHT ARMTAPER PIN HOLECRACKED 1,450 1,450       INSP/MAINTOVER 24 MOCESSNA3370788NONEOTHERDURING INSP FOUND WEIGHT ARM CRACKED AT POINT WHERE TAPER PINS ATTACH TO TORQUE TUBE
331976-09-01Z197624500108AIRFRAME   5317S   RODAT THREADSBROKEN 2,300 2,300       CRUISEOVER 24 MOCESSNA337A3370147OTHER, UNSCHED LANDINGOTHERELEV TRIM TAB CONTROL ROD BROKE AT THREADS DURING FLIGHT
(Less significant items below)
171991-09-0591ZZZX10161AIRFRAME1991-07-18   GCABLERT TAIL BOOMWRAPPED AROUND 0 226       INSP/MAINTUNCOMMONCESSNAP337H   NONEOTHERDURING ANNUAL INSPECTION FOUND ELEVATOR TRIM CABLE WRAPPED AROUND RUBBER CABLE AND THEN WRAPPED AROUND ITSELF INSIDE THE RIGHT TAIL BOOM FRONT SECTION. SUGGEST CLOSE INSPECTION IN THIS AREA WITH A BRIGHT LIGHT AS THIS AREA IS CLOSE AND HARD TO SEE.
91988-12-15NM078898142AIRFRAME1988-11-023000TGCABLEUP ELEVABRAIDED 2,091 2,091       INSP/MAINTUNCOMMONCESSNAT337BT3370600NONEOTHERDURING ANNUAL INSPECTION OF CONTROL CABLES IN LEFT TAIL BOOM FOUND THE UP ELEV CABLE (P/N 1460100-12) BADLY ABRAIDED BY THE LOWER EDGE OF THE PULLEY BRACKET ASSY (P/N 1470066-12) LOCATED IMMEDIATELY AFT OF THE AUTOPILOT PITCH ACTUATOR. IT APPEARS THAT PULLEY BRACKET ASSY WAS MOUNTED TOO LOW IN THE TAIL BOOM THUS CAUSING INTERFERENCE WITH THE CABLE.
471986-06-11EA038679315AIRFRAME1986-04-174DUGACTUATING ARMLT ELEVCRACKED 624 624       INSP/MAINTUNCOMMONCESSNAP337HP3370311NONEOTHERDURING ANNUAL INSPECTION FOUND LEFT ELEVATOR ACTUATING ARM CRACKED. CRACK STARTS AT INBOARD TAPPER PIN HOLE AND RUNS FOR.25 INCH. CAUSE--MAY BE AIRCRAFT BEING IN WIND WITHOUT CONTROL LOCK BEING INSTALLED. BALANCE WEIGHT FOR ELEVATOR IS MOU NTED ON END OF THIS ARM. INSTALLATION OF ELEVATOR CONTROL LOCK AT ALL TIMES AND INSPECTION OF ARM AT TAPPERED PIN HOLES.
401984-12-05GL08198488623AIRFRAME   4KPGSPROCKETHORIZONTAL STABLOST PINS 0 0       NOT REPORTEDUNCOMMONCESSNAT337GP3370255OTHEROTHER, WARNING INDICATIONBOTH PINS HOLDING ELEVATOR TRIM CHAIN TO SPROCKET FELL OUT.
271980-10-17WP01198080312AIRFRAME   2144XGBUMPER BLOCKRT FIN FOR ELEVBROKEN 3,350 3,350       INSP/MAINTUNCOMMONCESSNA3373370044NONEOTHERVERTICAL FIN INSTALLATION-ELEVATOR DOWN BUMPER BLOCK BRACKET BROKEN
401975-05-02Z197512200031AIRFRAME   5325S   STOPSVERT FIN AREASEPARTED 0 0       CRUISEOVER 24 MOCESSNA337A3370425UNSCHED LANDINGFLT CONT AFFECTEDELEV CONTROLS JAMMED IN NEUTRAL POS.FOUND STOP BOLT & NUT IN VERT FIN SEPARATED FROM STRUCTURE,OVERTRVL BENT CTL RD
           

RELATES TO VERTICAL STABILIZER (excluding rudder)
RowDate Of ReportOperator Control NumberSegmentDate Of OccurrenceAircraft RegistrationOperation TypeDescriptive Name Of PartDefective Location On AircraftFailed Part ConditionPart Total TimePart Total Time Since OverhaulComponent ManufacturerComponent Manufacturer ModelComponent Manufacturer NumberStage Of OperationSeverity FactorAircraft ManufacturerAircraft Manufacturer ModelAircraft Manufacturer NumberPrecautionary ProceduresNature Of ConditionzxcvbRemarkszxcvb
291994-08-0194ZZZX4286AIRFRAME1994-07-2192GDGRIBVERTICAL FINCRACKED 5,096 0       INSP/MAINTUNCOMMONCESSNAP337HP3370343NONEOTHERDURING AN ANNUAL INSPECTION, A RIB IN THE VERTICAL FIN WAS FOUND CRACKED APPROXIMATELY .3750 INCH LONG INITIATING AT THE AFT INBOARD BEND RADIUS. THE SAME CONDITION WAS FOUND IN BOTH THE LT AND RT VERTICAL FINS. CESSNA WAS CONTACTED TO DETERMINE THE PART NUMBER SINCE IT IS NOT SHOWN IN THE I.P.C. NO DIRECT CAUSE FOR THE CRACK COULD BE DETERMINED.
221991-10-3091ZZZX1705AIRFRAME1991-08-192181XGFITTINGFIN ATTACHMENTCORRODED 0 0       INSP/MAINTUNCOMMONCESSNA3373370081NONEOTHERCORROSION. DURING ANNUAL INSPECTION RIGHT VERTICAL TAIL FIN ATTACHMENT TO RIGHT REAR HORIZONTAL STABILIZER ATTACH FITTING, P/N 1431003-36 (part 35 in fig. below). CORRODED TO CONDITION OF EXFOLIATION. TOTAL TIME AIRCRAFT 3450.0 HOURS.
391988-03-23CE658876348AIRFRAME   88NGRIBR/H VERT STABCRACKED 4,677 4,677       INSP/MAINTUNCOMMONCESSNAT337H1947NONEOTHERON ANNUAL INSPECTION, FOUND RIB CRACKED IN AFT INBOARD CORNER NEAR ELEVATOR STOP BOLT BRACKET IN BOTH VERTICAL STAB ASSEMBLIES.
381988-03-23CE658876347AIRFRAME   88NGRIBL/H VERT STABCRACKED 4,677 4,677       INSP/MAINTUNCOMMONCESSNAT337H1947NONEOTHERON ANNUAL INSPECTION, FOUND RIB CRACKED IN AFT INBOARD CORNER NEAR ELEVATOR STOP BOLT BRACKET IN BOTH VERTICAL STAB ASSEMBLIES.
481986-06-11SW688679326AIRFRAME1986-04-17140VEGSTABR/H VERT FINBOLT SHEARED 3,650 3,650       INSP/MAINTUNCOMMONCESSNA337H33701945NONEUNKNOWNDURING ANNUAL INSP HORIZ STAB FOUND LOOSE AT FWD ATTACH POINT TO R/H VERTICAL FIN. FURTHER INVESTIGATION REVEALED BOTTOMATTACH BOLT MISSING HEAD AND UPPER BOLT LOOSE DUE TO WEAR OF DOUBLER AFT OF SPAR. UPPER HOLE FOUND ELONGATED TO 1/2 INC H. BOTTOM OF SPAR WEB DAMAGED BY CHAFING ON NON-STRUCTURAL SKIN OF VERTICAL FIN. DAMAGE TO VERTICAL FIN SPAR WEB ON LEFTAND RIGHT SIDE WAS NOTED IN THE FORM OF SLIGHT ELONGATION OF 1/4 INCH BOLT HOLES. PROBABLE CAUSE NOT READILY APPARENT, ALTHOUGH REAR ENGINE VIBRATION MAY HAVE AGRAVATED SOME DAMAGE NOT NOTICED AFTER GEAR-UP LANDING IN 1984. ANNUAL INSPECTION OF PREVIOUS YEAR SHOWED NO APPARENT PROBLEM IN THIS AREA. RECOMMEND MORE STRINGENT ANNUAL INSP REQUIRED.
271980-10-17WP01198080312AIRFRAME   2144XGBUMPER BLOCKRT FIN FOR ELEVBROKEN 3,350 3,350       INSP/MAINTUNCOMMONCESSNA3373370044NONEOTHERVERTICAL FIN INSTALLATION-ELEVATOR DOWN BUMPER BLOCK BRACKET BROKEN
401975-05-02Z197512200031AIRFRAME   5325S   STOPSVERT FIN AREASEPARTED 0 0       CRUISEOVER 24 MOCESSNA337A3370425UNSCHED LANDINGFLT CONT AFFECTEDELEV CONTROLS JAMMED IN NEUTRAL POS.FOUND STOP BOLT & NUT IN VERT FIN SEPARATED FROM STRUCTURE,OVERTRVL BENT CTL RD
231974-07-09Z197419000088AIRFRAME   75BB   RIBVERT STABLCRACKED 4,786 4,786       INSP/MAINTOVER 24 MOCESSNA3373370834NONEOTHERSEVERELY CRACKED RIB IN VERTICAL STABILIZER.

RELATES TO RUDDER
RowDate Of ReportOperator Control NumberSegmentDate Of OccurrenceAircraft RegistrationOperation TypeDescriptive Name Of PartDefective Location On AircraftFailed Part ConditionPart Total TimePart Total Time Since OverhaulComponent ManufacturerComponent Manufacturer ModelComponent Manufacturer NumberStage Of OperationSeverity FactorAircraft ManufacturerAircraft Manufacturer ModelAircraft Manufacturer NumberPrecautionary ProceduresNature Of ConditionzxcvbRemarkszxcvb
231999-02-12CA981230030AIRFRAME1998-12-30   GRIBRUDDERCRACKED 6,447     143100088   INSP/MAINT   CESSNA337G   NONEOTHER(CAN) .75 INCH CRACK FOUND ON RIGHT RUDDER UPPER RIB WHERE THE MASS BALANCE WEIGHT ATTACHES. REPLACEMENT RIB FABRICATEDPER SRM AND AC43.13 GUIDELINES.
411995-09-0895ZZZX4474AIRFRAME1995-08-0972086GSPARRUDDERBROKEN 2,875     143100058   INSP/MAINT   CESSNA337G33701518NONEOTHERAT ANNUAL, FOUND RIGHT RUDDER SPAR BROKEN AT BALANCE WEIGHT RIB ATTACH.
141991-04-24GL199184063AIRFRAME1990-10-0140ZGRIBLEFT RUDDER TIPCRACKED 1,128 1,128       INSP/MAINTUNCOMMONCESSNAP337HP3370313NONEOTHERWHILE REPLACING THE LEFT RUDDER TIP FOR CRACKS THE BALANCE WEIGHT SUPPORT RIB WAS FOUND CRACKED ON BOTH SIDES BETWEEN THE 2 CENTER NUTPLATES. THIS RIB IS SECURED BY 4 SCREWS ON EACH SIDE, 2 GO TO THE LAST RIB IN THE RUDDER AND 2 ARE SECURED ONLY TO THE PLASTIC RUDDER TIP. THE RUDDER TIP WAS CRACKED AT THE SCREW HOLES ON BOTH SIDES ALLOWING THE RIB TO TAKE ALL THE LOAD FROM THE BALANCE WEIGHT.
251985-07-29WP02198581713AIRFRAME   1385LGRIB ASSYRH RUDDER TIPCRACKED 1,398 1,398       INSP/MAINTUNCOMMONCESSNAT337H33701877NONEOTHERRUDDER TIP RIB CRACKED AND ALLOWED WEIGHT TO DROOP AND SCRAPE TOP OF STABILIZER.
441984-12-26WP07198489653AIRFRAME   86230GCHANNELCENTER SUPTBROKEN 1,946 1,946       INSP/MAINTUNCOMMONCESSNA337D3371119NONEOTHERRUDDER BALANCE BAR ATTACH CHANNEL BROKEN.
231982-03-29WP12198275178AIRFRAME   1326SGRIBRUDDERCRACKED 345 345       INSP/MAINTUNCOMMONCESSNAT337H33701904NONEOTHERON REMOVAL OF RUDDER TIP CAP TOP RIB ASSY PART 143100215 (part 6 in fig. below) CRACKED BETWEEN SECOND AND THIRD SCREW HOLES FOR CAP.
251977-01-05Z197700500030AIRFRAME   1VF   FAIRINGTOP RT RUDDERBROKEN 796 796       INSP/MAINTOVER 24 MOCESSNAT337G330098OTHEROTHERROYALITE FAIRING AT TOP OF RT RUDDER TIP SUPPORTS FWD 7 IN OF RIB WHICH CONTAINS 3LB LEAD WT.4 SCREW HOLES CR OUT
(Less significant items below)
111988-12-15NM078898190AIRFRAME1988-08-263000TGCABLERUDDER AT BOOMWORN 2,091 2,091       INSP/MAINTUNCOMMONCESSNAT337B3370600NONEOTHERROUTINE ANNUAL INSPECTION OF CABLES IN RIGHT TAIL BOOM REVEALED THAT THE RIGHT RUDDER CABLE WAS BADLY WORN AT THE GUIDE ASSEMBLY (P/N 1560100-22) ON THE ELECTRIC PITCH TRIM SERVO AT APPROX STA 110. THE CABLE GUIDE GROMMET (P/N S-1291-6) WAS MISSING FROM THE GUIDE ASSEMBLY ALLOWING THE CABLE TO WEAR DIRECTLY ON THE METAL GUIDE.
381986-02-24SW998672907AIRFRAME1986-02-03470DFGRUDDER CABLETHRU BOOM GUIDEFRAYED 4,688 4,688       INSP/MAINTUNCOMMONCESSNAM337B337M0254NONEOTHERALL CABLES WERE REMOVED DUE TO HIGH AIRFRAME TIME. ALL CABLES HAD A MINIMUM OF ONE STRAND BROKEN. NONE OF THE DAMAGE COULD BE FOUND WITHOUT REMOVING CABLE ASSY.

RELATES TO TAIL BOOM
RowDate Of ReportOperator Control NumberSegmentDate Of OccurrenceAircraft RegistrationOperation TypeDescriptive Name Of PartDefective Location On AircraftFailed Part ConditionPart Total TimePart Total Time Since OverhaulComponent ManufacturerComponent Manufacturer ModelComponent Manufacturer NumberStage Of OperationSeverity FactorAircraft ManufacturerAircraft Manufacturer ModelAircraft Manufacturer NumberPrecautionary ProceduresNature Of ConditionzxcvbRemarkszxcvb
502003-10-20AUS20030912AIRFRAME2003-09-08   GSTRUCTURETAILBOOMCORRODED           INSP/MAINT   CESSNA337G   NONEOTHER(AUS) LT TAILBOOM LOWER STRUCTURE CORRODED IN AREA OF ATTACHMENT TO WING STRUCTURE. CORROSION IS BOTH INTERNAL AND EXTERNAL. RT TAILBOOM CONTAINED INTERNAL CORROSION ONLY.
411988-03-23EA218876366AIRFRAME1988-02-0674LGSCREWSTAIL BOOMLOOSE 3,524 3,524       INSP/MAINTUNCOMMONCESSNA337G33701814NONEOTHERDURING ANNUAL, CHECKED TAIL BOOM ATTACHING SCREWS AND FOUND ABOUT 40 PERCENT OF THE SCREWS LOOSE. THIS IS THE SECOND OCCURENCE OF THIS CONDITION FOUND ON THIS AIRCRAFT. THE FIRST OCCURRENCE WAS AT 2186 HOURS. SUBMITTER RECOMMENDS THAT THESE SCREWS BE RETORQUED AT THE ANNUAL INSPECTION. SUBMITTER RECOMMENDS TORQUE IS 90-95 INCH POUNDS. FOUND SOME SCREWS AS LOW AS 35 INCH POUNDS.
401988-03-23EA218876365AIRFRAME1988-02-1674LGSCREWSTAIL BOOMLOOSE 3,524 3,524       INSP/MAINTUNCOMMONCESSNA337G33701814NONEOTHERDURING ANNUAL, CHECKED TAIL BOOM ATTACHING SCREW AND FOUND ABOUT 40 PERCENT OF THE SCREWS LOOSE. THIS IS THE SECOND OCCURRENCE OF THIS CONDITION FOUND ON THIS AIRCRAFT. THE FIRST OCCURRENCE WAS AT 2186 HOURS. SUBMITTER RECOMMENDS THAT THESE SCREWS BE RETORQUED AT THE ANNUAL INSPECTION. SUBMITTER RECOMMENDS TORQUE IS 90-95 INCH POUNDS. FOUND SOME SCREWS AS LOW AS 35 INCH POUNDS.
441978-08-22Z197823400060AIRFRAME   2488S   BOOM SUMP TANKTOWER WELDCRACKED 1,450 1,450       INSP/MAINTOVER 24 MOCESSNA3370788NONEOTHERDURING INSP FOUND WELD AREA AROUND TOWERS CRACKED

RELATES TO FLAP CABLES
RowDate Of ReportOperator Control NumberSegmentDate Of OccurrenceAircraft RegistrationOperation TypeDescriptive Name Of PartDefective Location On AircraftFailed Part ConditionPart Total TimePart Total Time Since OverhaulComponent ManufacturerComponent Manufacturer ModelComponent Manufacturer NumberStage Of OperationSeverity FactorAircraft ManufacturerAircraft Manufacturer ModelAircraft Manufacturer NumberPrecautionary ProceduresNature Of ConditionzxcvbRemarkszxcvb
142004-03-30CA040122003AIRFRAME2004-01-21   GCONTROL CABLETE FLAPSFRAYED           INSP/MAINT   CESSNAT337G   NONEOTHER(CAN) DURING INSPECTION IT WAS DISCOVERED THAT THESE CABLES (2EA. 1 LEFT AND 1 RIGHT) WERE FRAYED WHERE THE CABLE BENDSAROUND THE FLAP CABLE QUADRANT LOCATED IN THE WING TRAILING EDGE.
132004-03-30CA040122002AIRFRAME2004-01-21   GCONTROL CABLETE FLAPSFRAYED           INSP/MAINT   CESSNAT337G   NONEOTHER(CAN) DURING INSPECTION IT WAS DICOVERED THAT THESE CABLES (2EA. 1 LT AND 1 RT) WERE FRAYED WHERE THE CABLE BENDS AROUNDTHE FLAP CABLE QUADRANT LOCATED IN THE WING TRAILING EDGE.
122004-03-29AUS20031318AIRFRAME2003-11-28   GCONTROL CABLETE FLAPSFRAYED           INSP/MAINT   CESSNA337H   NONEOTHER(AUS) IB FLAP CABLE CONTAINED BROKEN WIRES LOCATED AT TIGHT BEND AROUND THE BELLCRANK. APPROXIMATELY 50 PERCENT OF THEWIRES WERE BROKEN. INSPECTION CARRIED OUT IN RESPONSE TO MFG ALERT.
92004-03-25CA040225011AIRFRAME2004-02-24   GCONTROL CABLETE FLAPSFRAYED           INSP/MAINT   CESSNA337A   NONEOTHER(CAN) FLAP CABLES REMOVED FOR INSPECTION DUE TO SERVICE DIFFICULTY ALERT AL-2003-05. LT AND RT OUTBOARD FLAP CABLES FOUND TO BE FREYED AT THE INBOARD BELLCRANK, APPROXIMATELY 1 INCH FROM THE SWAGGED TERMINAL. BOTH CABLES ARE ORIGINAL CESSNAFLAP CABLES AND WERE REPLACED WITH NEW CESSNA FLAP CABLES. ALSO, THE RT, INBOARD FLAP CABLE WAS FREYED AT THE INBOARD BELLCRANK, APPROXIMATELY 1 INCH FROM THE SWAGGED TERMINAL.
52004-01-08AUS20031143AIRFRAME2003-10-16   GCONTROL CABLETE FLAPFRAYED           INSP/MAINT   CESSNAT337G   NONEOTHER(AUS) LT AND RT FLAP DOWN CABLES PN 1460100-7 AND PN 1460100-8 FRAYED WITH BROKEN STRANDS AROUND BELLCRANK ACTUATOR.
22003-10-21CA031001010AIRFRAME2003-09-23   GCONTROL CABLETE FLAPSDAMAGED           INSP/MAINT   CESSNA337G   NONEOTHER(CAN) A SPECIAL INSPECTION WAS INITIATED TO COMPLY WITH REMOVAL AND INSPECTION OF FLAP CONTROL CABLES THAT ARE CONNECTEDTO THE INBOARD FLAP BELLCRANK. CABLE PN 14601007 AND 14601008 WERE BOTH FOUND TO HAVE SEVERAL BROKEN STRANDS AND REQUIRED REPLACEMENT SERVICE DIFFICULTY ALERT AL 2003-05 REFERS TO THIS PROBLEM.
12003-10-21CA031001009AIRFRAME2003-09-23   GCONTROL CABLETE FLAPSDAMAGED           INSP/MAINT   CESSNA337G   NONEOTHER(CAN) A SPECIAL INSPECTION WAS INITIATED TO COMPLY WITH REMOVAL AND INSPECTION OF FLAP CONTROL CABLES THAT ARE CONNECTEDTO THE INBOARD FLAP BELLCRANK. CABLE P/N 1460 100-7 AND 1460100-8 WERE BOTH FOUND TO HAVE SEVERAL BROKEN STRANDS AND REQUIRED REPLACEMENT. SERVICE DIFFICULTY ALERT AL2003-05 REFERS TO THIS PROBLEM.
492003-07-03CA030602001AIRFRAME2003-05-30   GCONTROL CABLEFLAP ACTUATORDAMAGED           INSP/MAINT   CESSNA337G   NONEOTHER(CAN) AFTER RECEIVING SDR ALERT AL-2003-05 AN INSPECTION WAS CARRIED OUT ON OUR 337G. TWO CABLES ON BOTH SIDES WERE FOUND DAMAGED. THE DAMAGE WAS LOCATED EXACTLY IN THE SAME LOCATION AS MENTION IN THE ALERT IE AROUND THE SHARP BEND OF THE BELLCRANK. ALL CABLES HAD TO BE REMOVED TO SEE THE DAMAGE.HAD THEY NOT THE DAMAGE WOULD OF WENT UNNOTICED. BOTH SETS OF CABLES WERE REPLACED WITH SERVICEABLE UNITS.
482003-07-02CA030606010AIRFRAME2003-06-06   GCONTROL CABLETE FLAPFRAYED           NOT REPORTED   CESSNA337A   ACTIVATE FIRE EXT.FLT CONT AFFECTED(CAN) INSPECTION OF FLAP CABLES IAW SERVICE DIFFICULTY ALERT NR AL-2003-05, FOUND THREE FRAYED CABLE ENDS, ONE AT OUTBOARD BELLCRANK.
472003-06-17AUS20030479AIRFRAME2003-03-09   GCONTROL CABLETE FLAPSFRAYED           INSP/MAINT   CESSNAM337B   NONEOTHER(AUS) LH TRAILING EDGE FLAP CONTROL CABLE CONTAINED BROKEN STRANDS IN AREA APPROXIMATELY 25.4MM (1IN) FROM SWAGE AT BELLCRANK END.
422003-05-07AUS20030355AIRFRAME2003-02-27   ACONTROL CABLETE FLAPSFRAYED           INSP/MAINT   CESSNA337B   NONEOTHER(AUS) RT INBOARD FLAP CABLE CONTAINED BROKEN STRANDS LOCATED IN AREA APPROXIMATELY 25.4MM TO 38.1MM (1IN TO 1.5IN) FROMTHE INBOARD BELLCRANK TURNBUCKLE.
412003-04-29AUS20030264AIRFRAME2003-03-03   GCONTROL CABLETE FLAPCORRODED           INSP/MAINT   CESSNA337A   NONEOTHER(AUS) FLAP CONTROL CABLES PN 14601007 AND PNO 14601008 CORRODED AND FRAYED.
402003-04-14CA030227005AIRFRAME2003-02-27   GCONTROL CABLETE FLAPSFRAYED           NOT REPORTED   CESSNA337G   OTHEROTHER(CAN) DURING 100 HR INSPECTION THE INBOARD RIGHT HAND FLAP CABLE WAS INSPECTED FOR WEAR IN THE AREA OF THE INBOARD FLAPBELLCRANK. CABLE WAS FOUND FRAYED APPROX. 1 INCH FROM CABLE END ATTACH FITTING.CABLE R EPLACED.
211999-01-2299ZZZX297AIRFRAME1998-11-092655SGCONTROL CABLETE FLAPSEVERED           APPROACH   CESSNA337C3370955ABORTED APPROACHFLT CONT AFFECTEDTHE LEFT FLAP CONTROL CABLE WAS FOUND BADLY FRAYED AND SEVERED AT THE LEFT INBOARD BELLCRANK. PHOTOS AT THE SCENE SHOWRT FLAPS FULL DOWN AND LOCKED. LT FLAPS ARE NOT EXTENDED. A FULL POWER 'GO AROUND' ATTEMPT RESULTED IN A 'NO CONTROL'SITUATION CAUSED BY A SPLIT FLAT CONDITION KNOWN AS ASYMMETRICAL FLAP HAZARD. SUBMITTER STATED THE ANNUAL INSPECTION HAD BEEN COMPLETED A FEW DAYS PRIOR. AIRCRAFT WAS DESTROYED.
81975-09-04Z197524700054AIRFRAME   2479S   BELLCRANKINBD FLAP-RTBROKEN 621 621       INSP/MAINTOVER 24 MOCESSNA337C3370779NONEOTHERQUANDRANT & BELLCRANK ASSY INBD RIGHT FLAP FAILED,RESULTING IN SPLIT FLAP. CAUGHT BY PILOT ON PREFLT.
(Less significant items below)
471977-10-21Z197729400142AIRFRAME   2321S   CABLERH BELLCRANKFRAYED 855 855       INSP/MAINTOVER 24 MOCESSNA337B3370621NONEOTHERBOTH INNER & OUTER WERE IN SAME GROOVE ON THE RH INNER FLAP BELLCRANK CAUSING FR AYING

RELATES TO ENGINE MOUNT
RowDate Of ReportOperator Control NumberSegmentDate Of OccurrenceAircraft RegistrationOperation TypeDescriptive Name Of PartDefective Location On AircraftFailed Part ConditionPart Total TimePart Total Time Since OverhaulComponent ManufacturerComponent Manufacturer ModelComponent Manufacturer NumberStage Of OperationSeverity FactorAircraft ManufacturerAircraft Manufacturer ModelAircraft Manufacturer NumberPrecautionary ProceduresNature Of ConditionzxcvbRemarkszxcvb
461998-04-02CA970812010AIRFRAME1997-07-23   GTUBEENGINE MOUNTBROKEN 4,165   CONTIO360C60071CRINSP/MAINT   CESSNA337   NONEOTHER(CAN) DURING ANNUAL INSPECTION, IT WAS FOUND THAT A REAR ENGINE MOUNT WAS BROKEN. LOWER RIGHT HAND TUBE 1.5 INCHES BELOW THE WEB. CRACKED THROUGH THE ENTIRE DIAMETER.
321994-09-3094ZZZX5662AIRFRAME1994-06-3083CGCHANNELFWD ENG MOUNTCRACKED 2,164 0       INSP/MAINTUNCOMMONCESSNAT337GP3370114NONEOTDERCRACK FOUND IN RADIUS OF BEND IN CHANNEL THAT MAKES UP THE AFT SIDE OF THE AFT RT ENGINE MOUNT BOX STRUCTURE. TWO OTHER AIRCRAFT WITH ABOUT THE SAME TOTAL HOURS HAD CRACKS IN THE SAME AREA. THE CRACK WAS DISCOVERED DURING ENGINE REMOVAL. THE CRACKS COULD HAVE GONE UNNOTICED IN THE OTHER AIRCRAFT. WITH ENGINES INSTALLED, IT IS A DIFFICULT AREA TO SEE. SUBMITTER SUGGESTS POSSIBLE INCREASED STRESS IN THAT AREA CAUSED CRACKS.
451990-08-02NM079091928AIRFRAME1990-06-1537EGMOUNTREAR ENGINECRACKED 1,701 1,701       INSP/MAINTUNCOMMONCESSNA337GP3370127NONEOTHERREMOVED REAR ENGINE TO REPAIR CASE CRACK. CRACK NOT SEEN IN ENGINE MOUNT DURING INITIAL INSPECTION. AFTER STRIPPING MOUNT FOR OTHER REPAIRS AND PAINTING, CRACK BECAME VISIBLE. SUBMITTER RECOMMENDS THAT AT ANY ENGINE REMOVAL, THE ENGINE MOUNT BE CLEANED AND STRIPPED TO INSPECT FOR CRACKS.
251983-05-16SW63198379642AIRFRAME   86529GMT BRACKETNO 2 ENGCRACKED 2,335 2,335       INSP/MAINTUNCOMMONCESSNAT337/T33701223NONEOTHERPREFLIGHT INSP REVEALED LT REAR ENG MT BRACKET CRACKED APPROX 1.50 INCHES LONG.BRACKET BOLTS TO ENG CASE.
471982-10-22SW63198286179AIRFRAME   86529GMOUNTNO 2 ENG LF MTCRACKED 2,257 2,257       INSP/MAINTUNCOMMONCESSNAT337ET33701223NONEOTHERINSP FOUND NO 2 ENG HAD THE LF ENG MT CRACKED IN CASTING APPEARED TO BE ALMOST TO THE POINT OF COMPLETE SEPARATION.
461980-07-14WP04198074252AIRFRAME   4CTGBRACKETENG MOUNTBROKEN 971 971       INSP/MAINTUNCOMMONCESSNAT337GP3370004NONEVIBRATION/BUFFETFOUND RT REAR ENG MOUNT BRACKET BROKEN
361979-10-10Z197928300046AIRFRAME   4BU   MOUNT LEGAT FIREWALLBROKEN 468 468       INSP/MAINTUNCOMMONCESSNAP337HP33770304NONEOTHERREAR ENGINE MOUNT LEG BROKEN WHERE IT ATTACHES TO THE FIREWALL.
411979-05-11Z197913100038AIRFRAME   2FOR   V BRACEREAR ENGBROKEN 2,160 2,160       INSP/MAINTUNCOMMONCESSNA337A3370258NONEOTHERRT V BRACE BROKEN BETWEEN ENG MT MEMBERS REAR ENG
401979-05-07Z197912700028AIRFRAME   1ZG   MOUNTCROSS MEMBERBROKEN 504 504       INSP/MAINTUNCOMMONCESSNAT337GP3370265NONEOTHERON PREFLIGHT INSP.PILOT FOUND CROSS MEMBER AT REAR OF MOUNT BROKEN LOOSE AT 1 EN D & CRACKED AT OTHER END.REPAIRED
161978-04-03Z197809300048AIRFRAME   1748M   TUBEADJ CLUSTER WELDCRACKED 2,500 2,500       INSP/MAINTOVER 24 MOCESSNA337F33701348NONEOTHERRT LOWER HORIZONTAL ENGINE MOUNT TUBE CRACKED AND BROKE ONE INCH FROM CLUSTER WE LD.
451977-02-07Z197703800045AIRFRAME   1293M   MOUNT BRACKETREAR ENGCRACKED 22 22       INSP/MAINTOVER 24 MOCESSNAT337/01293NONEOTHERBRACKET FOUND CRACKED DURING 25 HR INSP ON REAR ENG ATTACHING WEB & ENG MOUNT BOLT.RECOMMEND RETORQUE ALL MT TO ENG
51976-10-27Z197630100033AIRFRAME   2623S   MOUNT BRACKETREAR ENGINECRACKED 1,276 1,276       INSP/MAINTOVER 24 MOCESSNA337T3370923NONEOTHERENG MOUNT BRACKET ON REAR ENG FOUND CRACKED DURING ANNUAL INSP.REAR ENG MOUNT BRACKET HAD BEEN REPLACED ONCE
421976-06-21Z197617300043AIRFRAME   2623S   MOUNTLEFT REARCRACKED 1,235 100       INSP/MAINTOVER 24 MOCESSNA3373370923NONENO WARNING INDICATION, OTHERRT FRONT ENG MOUNT LEG CRACKED TWO THIRDS OF CIRCUMF.THIS MOUNT PUSHER POSN.CRACKED 100 HRS OUT OF OVERHAUL
131976-04-30Z197612100064AIRFRAME   5311Q   BRACKET   CRACKED 0 0       UNKNOWNOVER 24 MOCESSNAT337D1093OTHEROTHERENG MOUNT BRACKED CRACKED BTWN ENG MOUNT BOLTS
411975-11-13Z197531700059AIRFRAME   6269F   MOUNTENG LWR RTCRACKED 0 0       UNKNOWNOVER 24 MOCESSNA337A3370269OTHEROTHERREAR ENG MOUNT CROSS MEMBER CRACKED,LWR RT,RPRD PER AC 43.13.1A
111975-09-16Z197525900038AIRFRAME   1843M   MOUNTLWR LT CLUSTERBROKEN 0 0       INSP/MAINTOVER 24 MOCESSNA33733701443NONEOTHERREAR ENGINE MOUNT BRACE BROKEN AT LOWER LT CLUSTER
141975-05-28Z197514800064AIRFRAME   6243F   MOUNTUPR SUPP TUBEBROKEN 1,125 1,125       INSP/MAINTOVER 24 MOCESSNA3373370243NONEOTHER  
401975-02-13Z197504400048AIRFRAME   11RA   BRACKETREAR ENGINEBROKEN 0 107       INSP/MAINTOVER 24 MOCESSNAT337DT3371143NONEOTHERRT FRNT ENG MOUNT BROKE.
371975-02-05Z197503600049AIRFRAME   11AR   SUPPORT LEGLT SIDE ENGBROKEN 0 0       INSP/MAINTOVER 24 MOCESSNAT337D3371143NONEOTHERAFT ENG REAR LT SUPPORT LEG CRANKCASE TO DYNAFOCAL MOUNT LEG BROKEN.ENG HAD 107 HRS SINCE REMANUFACTURE.TURBO MT BK
331974-11-14Z197431800073AIRFRAME   2429S   MOUNTRT FWD LEGBROKEN 1,146 1,146       INSP/MAINTOVER 24 MOCESSNAT337/3370729NONEOTHERRIGHT FORWARD ENGINE MOUNT LEG BROKE AT THE MID POINT OF THE LEG.
431974-09-03Z197424600032AIRFRAME   8922M   MOUNTLWR FWD CROSSBROKEN 750 750       INSP/MAINTOVER 24 MOCESSNA337F33701322NONEOTHERREAR ENGINE MOUNT BROKEN AT WELD ATTACHING RT END AND LWR FWD CROSSMEMBER TO RES T OF MOUNT.
71974-06-11Z197416200060AIRFRAME   689CP   REAR ENG MOUNT   CRACKED 0 0       INSP/MAINTOVER 24 MOCESSNA3370330NONEOTHERLT MLG BRACKET ASSY CRACKED AND MFG DEFECT.
(Less significant items below)
11982-12-09WP02198288135AIRFRAME   9CMGMOUNTSFRONT ENGSAGGING 35 35       APPROACHUNCOMMONCESSNAT337GP3370034NONEFLUID LOSS, UNKNOWNSAGGING ENG MNTS CAUSED OIL FILTER TO BE CHAFED BY NOSE WHEEL WELL STRUCTURE RESULTED IN OIL LOSS.
291974-11-08Z197431200031AIRFRAME   1840M   ENGINE MOUNTLWR RT CLUSTERCRACKED 409 409       INSP/MAINTOVER 24 MOCESSNA33733701440NONEOTHERREAR ENG MOUNT CRACKED AT LOWER RT CLUSTER.FOUND DURING 100 HR INSP

RELATES TO NOSE GEAR
RowDate Of ReportOperator Control NumberSegmentDate Of OccurrenceAircraft RegistrationOperation TypeDescriptive Name Of PartDefective Location On AircraftFailed Part ConditionPart Total TimePart Total Time Since OverhaulComponent ManufacturerComponent Manufacturer ModelComponent Manufacturer NumberStage Of OperationSeverity FactorAircraft ManufacturerAircraft Manufacturer ModelAircraft Manufacturer NumberPrecautionary ProceduresNature Of ConditionzxcvbRemarkszxcvb
401992-08-1092ZZZX7528AIRFRAME1992-07-0862NAGBOLTNLG TORQUE LINKBROKEN 0 0       INSP/MAINTFREQUENTCESSNAT337GP3370269NONEOTHERDURING ROUTINE MAINTENANCE, FOUND NOSE GEAR STRUT TORQUE LINK BOLT BROKEN OFF AT THE HEAD, AND BOLT HAD WORKED ITS WAY HALF OUT OF THE TORQUE LINK. THIS PART IS HARD TO SEE ON PREFLIGHT.
221984-07-23SW61198481731AIRFRAME   86452GBOLTNOSE AXLEBROKEN 1,294 1,294       INSP/MAINTNEVERCESSNAT337E33701199NONEOTHERNLG AXLE BOLT BROKEN 1/4 INCH FROM HEAD.
201979-08-10Z197922200033AIRFRAME   444HR   BOLTNLG WHEEL WELLSHEARED 16 16       INSP/MAINTUNCOMMONCESSNAT337H33701900NONEOTHERNLG WOULD NOT FULLY EXTEND DURING RETRACT CHECK.FOUND UPPER TORQUE LINK BOLT SHE ARED & LOWER BOLT ALMOST SHEARED
281976-02-17Z197604800042AIRFRAME   2MIL   BOLTNLG UPLOCKBROKEN 3,000 3,000       APPROACHOVER 24 MOCESSNA337B6810853NONEOTHERNOSE LANDING GEAR UPLOCK BOLT SHEARED. APPEARED TO HAVE PREVIOUS CRACKED.
(Less significant items below; large number of them because many deal with a plastic spring guide later changed to steel)
22009-03-172009FA0000191AIRFRAME2009-03-08302AGCYLINDER HEADMLG STRUTCRACKED 3,600 800       INSP/MAINT   CESSNAM337BM3370331NONEFLUID LOSSWHILE INVESTIGATING A HYD FLUID LEAK IN THE NOSE WHEEL WELL, LOCATED CRACK IN THE RETRACT CYLINDER HEAD BETWEEN THE ATTACH BOLT/BUSHING BOSS AND THE BARREL THREADS, IN THE UPPER RADIUS. THERE WERE NO TOOL MARKS TO CREATE A STRESS RISER, AND NO HARD LANDINGS NOTED. THIS WAS NOT VISIBLE, WITHOUT REMOVING THE RETRACT CYLINDER, AS IT WAS HIDDEN BY THE ATTACH STRUCTURE IN THE WHEEL WELL. APPROX 800 FLIGHT HOURS AND 19 YEARS SINCE LAST CYLINDER REMOVAL/RE-SEAL.
232001-08-08AUS20010418AIRFRAME2001-05-04   GRIVETFUSELAGEDAMAGED           INSP/MAINT   CESSNA337   NONEOTHER(AUS) NOSE LANDING GEAR WHEEL PAN/FIREWALL STRUCTURE RIVETS PULLED. FAILED RIVETS LOCATED IN THE AFT LT TOP CORNER.
241994-07-0594ZZZX3620AIRFRAME1993-01-04470DFGROD ENDBUNGEE ASSYBENT 0 0       INSP/MAINTOCCASIONALCESSNAM337B337M0254NONEOTHERBENT ROD END ON STEERING BUNGEE ASSY. SUBMITTER SUSPECTS CAUSED BY EXCESSIVE PEDAL PRESSURE AT THE TURN LIMIT OF NOSE WHEEL ASSY.
321985-12-05WP08198588533AIRFRAME1985-07-185475SGSPRINGNLG DWN LOCKBROKEN 0 0       LANDINGFREQUENTCESSNA337B3370575NONEOTHER, VIBRATION/BUFFETNOSE WHEEL COLLAPSED ON LANDING. FOUND NLG DWN LOCK SPIRNG GUIDE-PLASTIC-BRKN. ME84-1 HAS STEEL REPLACEMENT.
371984-11-16EA22198487608AIRFRAME   556NAGROD END   DEFECTIVE 0 0       INSP/MAINTOCCASIONALCESSNAT337B3370705NONEOTHERNOSE LANDING GEAR STEERING ROD END DEFECTIVE.
351984-10-15NM64198486025AIRFRAME   1425MGGUIDENG DOWNLOCKBROKEN 886 886       APPROACHUNCOMMONCESSNAT337GP3370162OTHERWARNING INDICATIONNO NLG DOWN + LOCK INDICATION. FOUND NLG DOWNLOCK SPRING GUIDE BROKEN.
151984-06-20NM03198479624AIRFRAME   86255GSPRING GUIDENLG ACTUBROKEN 0 0       INSP/MAINTFREQUENTCESSNAT337D1130NONEOTHERNLG SRING GUIDE EAR BROKEN.
471984-01-04NM61198470106AIRFRAME   42WAGRODNWSBENT 2,750 2,750       TAKEOFFOCCASIONALCESSNAT337GP3370205OTHERWARNING INDICATIONNLG FAILED TO RETRACT. FOUND NWS ROD BENT PREVENTING STRUT FROM CENTERING.
121981-07-15WP09198184135AIRFRAME   740MGGUIDE SPRINGDOWN LOCKBROKEN 2,370 2,370       LANDINGFREQUENTCESSNA3373370160NONENO WARNING INDICATIONNOSE GEAR COLLAPSED ON LANDING ROLL. THE NLG DOWN LOCK SPRING GUIDE HAD BROKEN + A POSITIVE DWN + LOCK WAS NOT MADE .
451981-05-15NM67198180467AIRFRAME   53405GSPRING GUIDENLG DN LOCKBROKEN 2,891 2,891       INSP/MAINTFREQUENTCESSNA337G01602NONEOTHERNO TEXT.
151981-02-25SW99198173966AIRFRAME   72382GGUIDENLG DN LK SPGBROKEN 2,271 2,271       INSP/MAINTFREQUENTCESSNA337G01572NONEOTHERNOSE GEAR WOULD NOT STAY UP AND LOCKED.
461981-01-23EA11198171274AIRFRAME   85869GPISTON RODNLG DOORACTUBROKE 1,411 1,41112805135128051351108INSP/MAINTUNCOMMONCESSNA337D3371005NONEOTHERNLG DOOR ACTU ROD BROKE OFF APPROX 2 THREADS INSIDE ROD END
161980-09-12WP09198078445AIRFRAME   1280MGSPRING GUIDENLG LOCKINGBROKEN 1,550 1,550       INSP/MAINTFREQUENTCESSNAT337ET3371280NONEOTHERPLASTIC SPRING GUIDE BROKE ON ONE SIDE.
301979-09-11Z197925400007AIRFRAME   1397L   GUIDENLG DWNLOCKBROKEN EARS 71 71       UNKNOWNFREQUENTCESSNA337H33701889NONEOTHERNLG DOWNLOCK GUIDE EARS BROKEN
131979-08-02Z197921400037AIRFRAME   2435S   BRACENLGBENT 458 458       LANDINGFREQUENTCESSNAT337B3370745OTHEROTHERNLG DOWN STOP PLATE BENT
21979-06-28Z197917900064AIRFRAME   9LF   BRACKETNLGCRACKED 863 863       INSP/MAINTOCCASIONALCESSNA337F33701327NONEOTHERFOUND NOSE STEERING BRACKET CRACKED FROM LIGHTENING HOLE TO FWD EDGE
421979-05-15Z197913500042AIRFRAME   1293M   BRACKETNLG UPLOCKBROKEN 4,140 4,140       INSP/MAINTFREQUENTCESSNAT337E01293NONEOTHERFOUND NLG UPLOCK BRACKET BROKEN AFT END CAUSE WEAK BRACKET
171979-02-08Z197903900066AIRFRAME   7CT   GUIDE SPRINGNLG DN LOCKBROKEN 0 1,300       INSP/MAINTFREQUENTCESSNAT337GP3370008NONEOTHERPLASTIC SPRING GUIDE BROKE LETTING NLG COLLAPSE CAUSING DAMAGE TO PROP.
481978-12-14Z197834800043AIRFRAME   2717X   BRACKETNLGBROKE 0 0       TAXI/GRND HDLOCCASIONALCESSNA3373370117NONEOTHERNOSE STEERING BRACKET FAILED UNDER NORMAL SERVICE CAUSING LOSS OF NOSE STEERING WHILE TAXING.
321978-07-31Z197821200104AIRFRAME   25905   SPRINGNLG CENTERINGSTRETCHED 2,017 2,017       TAXI/GRND HDLOVER 24 MOCESSNA3373370890NONEOTHERNLG COLLAPSED AFTER LANDING.FOUND NLG CENTERING SPRING STRETCHED.
211978-04-06Z197809600085AIRFRAME   32DM   ROD ASSYSTEERINGBENT 2,969 2,969       INSP/MAINTOVER 24 MOCESSNA3370049NONEOTHER  
191978-04-06Z197809600083AIRFRAME   32DB   BUNGEE ASSYROD ENDBROKEN 0 0       INSP/MAINTOVER 24 MOCESSNA3370049NONEOTHER  
401976-03-11Z197607100054AIRFRAME   86513   EYEBOLTRT FRT NLG DOORBROKEN 1,289 1,289       INSP/MAINTOVER 24 MOCESSNA337E33701216NONEOTHERBOLT ATTACHMENT TO DOOR HINGE BROKE OFF. DURING PREFLT PILOT NOTICED DOOR HANGIN G DOWN.
141975-12-30Z197536400043AIRFRAME   2310S   NLG BUMPERNLG WELLBENT 1,840 1,840       INSP/MAINTOVER 24 MOCESSNAT337B0610NONEOTHERNLG BUMPER BENT & DEFORMED AFT CAUSING NOSE GEAR TO MOVE AS RUDDER PRESSURE APPL IED AFTER LIFT OFF.

RELATES TO RUDDER/BRAKE PEDALS AREA
RowDate Of ReportOperator Control NumberSegmentDate Of OccurrenceAircraft RegistrationOperation TypeDescriptive Name Of PartDefective Location On AircraftFailed Part ConditionPart Total TimePart Total Time Since OverhaulComponent ManufacturerComponent Manufacturer ModelComponent Manufacturer NumberStage Of OperationSeverity FactorAircraft ManufacturerAircraft Manufacturer ModelAircraft Manufacturer NumberPrecautionary ProceduresNature Of ConditionzxcvbRemarkszxcvb
392003-01-14CA021125010AIRFRAME2002-11-21   GBRACKETRUDDERCRACKED           INSP/MAINT   CESSNA337A   NONEOTHER(CAN) CRACK FOUND ON BOTH INBOARD RUDDER TORQUE TUBE MOUNTING BRACKETS. THE CRACK BEGAN AT THE AFT END OF THE BRACKET, EXTENDING FORWARD APPROXIMATELY 3-4 INCHES ON THE LT BRACKET AND 1/2 INCH FORWARD ON THE RT BRACKET. THE CRACK OCCURRED AT THE BEND RADIUS ON THE OUTER PIECE OF THE BRACKET.
242001-08-08AUS20010419AIRFRAME2001-05-04   GTORQUE TUBERUDDER CONTROLDAMAGED           INSP/MAINT   CESSNA337   NONEOTHER(AUS) RUDDER PEDAL TORQUE TUBE CLAMP SUPPORT STRUCTURE CRACKED ANDWORKING. LOOSE RIVETS AND DAMAGE CAUSED BY BELLCRANK.
112001-05-15CA010504017AIRFRAME2001-04-16   ASUPPORT BRACKETRUDDER PEDALCRACKED 7,253   CESSNA337C3370895INSP/MAINT   CESSNA337C   NONEOTHER(CAN) DURING A 100 HOUR INSPECTION IT WAS OBSERVED THERE WA A CRACK IN THE ABOVE MENTIONED BRACKET. A NEW BRACKET WAS INSTALLED AND AIRCRAFT RELEASED FOR RETURN TO SERVICE.
401998-01-0898ZZZX154AIRFRAME1997-12-269739DGSUPPORT ASSYRUDDER BARCRACKED           INSP/MAINT   CESSNA337A3370466NONEOTHERPILOT COMPLAINED OF INCONSISTENT RUDDER TRIM INPUTS TO MAINTAIN COORDINATED FLIGHT AND 'FUNNY' RUDDER CONTROL INPUTS. INSPECTION REVEALED BOTH CENTER RUDDER BAR SUPPORTS CRACKED ALLOWING RUDDER BAR TO WANDER WHEREVER IT WANTED TO GO. AIRCRAFT HAS HISTORY OF LANDING ACCIDENTS WHEN REGISTERED IN A FOREIGN COUNTRY, BUT THIS IS A NEW DISCREPANCY WITH NO PREVIOUS CONTROL SYSTEM PROBLEMS.
391998-01-0898ZZZX153AIRFRAME1997-12-269739DGSUPPORT ASSYRUDDER BARCRACKED           INSP/MAINT   CESSNA337A3370466NONEOTHERPILOT COMPLAINED OF INCONSISTENT RUDDER TRIM INPUTS TO MAINTAIN COORDINATED FLIGHT AND 'FUNNY' RUDDER CONTROL INPUTS. INSPECTION REVEALED BOTH CENTER RUDDER BAR SUPPORTS CRACKED ALLOWING RUDDER BAR TO WANDER WHEREVER IT WANTED TO GO. AIRCRAFT HAS HISTORY OF LANDING ACCIDENTS WHEN REGISTERED IN A FOREIGN COUNTRY, BUT THIS IS A NEW DISCREPANCY WITH NO PREVIOUS CONTROL SYSTEM PROBLEMS.
421995-10-2095ZZZX5770AIRFRAME1995-08-07471DFGSUPPORT ASSYINBD RUD BARCRACKED   384       INSP/MAINT   CESSNAT337B337M0246NONEOTHERDURING NR 2 PROGRESSIVE INSPECTION, THE MOUNT WAS NOTICED FLEXING DURING RUDDER APPLICATION. THIS BRACKET HAD BEEN REPLACED FOR THE SAME REASON DURING THE ANNUAL ON 5-94. THIS HAS BEEN AN ONGOING PROBLEM WITH ACFT, APPROXIMATELY 6 CHANGES, 13 ACFT IN THE FLEET.
251994-07-1194ZZZX3788AIRFRAME1993-12-22470DFGSUPPORT ASSYRUDDER PEDALCRACKED 6,200 0       INSP/MAINTUNCOMMONCESSNAM337B337M0254NONEOTHERRUDDER PEDAL SUPPORT BRACKETS WERE CRACKED AT FLANGE RADII OF FLANGE TO FIRE WALL STRUCTURE ATTACHMENT - CAUSE IS BELIEVED TO BE TOO MUCH PEDAL PRESSURE WITH FLEXING OF THE STRUCTURE DURING BRAKING AND TURNS. THE CRACK IS APPROXIMATELY ONE-HALF THE LENGTH OF THE FLANGE. THREE A/C THIS YEAR HAVE BEEN CRACKED, ONE LAST YEAR. ALL FOUND DURING ANNUAL. RECOMMEND ONE-TIME INSPECTION OF ALL 337 TYPE A/C.
231994-07-0594ZZZX3619AIRFRAME1993-01-04470DFGSUPPORT ASSYRUDDER BARCRACKED 6,171 0       INSP/MAINTUNCOMMONCESSNAM337B337M0254NONEOTHERBOTH LT AND RT RUDDER BAR SUPPORT BRACKETS ON THIS AIRCRAFT HAVE CRACKED AND WERE LOCALLY REPAIRED. IN ALL CASES, THE CRACKS HAVE BEEN IN THE SAME LOCATIONS. THIS HAS BEEN THE SIXTH A/C OVERALL IN WHICH REPAIRS WERE MADE SO FAR.
221994-07-0594ZZZX3615AIRFRAME1993-12-22473DFGSUPPORT ASSYBRAKE PEDALCRACKED 7,044 0       INSP/MAINTFREQUENTCESSNA337B337M0296NONEOTHERDURING ANNUAL INSPECTION OF THE AIRFRAME, STRUCTURE NOTICED TO MOVE WHEN PEDALS WERE POSITIONED TO THE FULL TRAVEL. SUPPORT BRACKET CRACKED IN THE RADII OF THE MOUNTING FLANGE TO FIREWALL.
211994-07-0594ZZZX3614AIRFRAME1993-12-22467DFGSUPPORT ASSYBRAKE PEDALCRACKED 5,801 0       INSP/MAINTFREQUENTCESSNA337B337M0290NONEOTHERDURING ANNUAL INSPECTION OF THE AIRFRAME, NOTICED STRUCTURE MOVED WHEN PEDALS WERE POSITIONED TO THE FULL TRAVEL. SUPPORT BRACKET WAS CRACKED IN THE RADII OF MOUNTING FLANGE AT THE FIREWALL.
121985-05-09CE65198577004AIRFRAME   59NGSUPPT BRACKETRH RUDDER PEDALBROKEN/CRACKED 2,520 2,520       INSP/MAINTUNCOMMONCESSNAT337H33701854NONEOTHERBOTH INBOARD RUDDER PEDAL BEARING SUPPORT BRACKETS BROKEN AND CRACKED. TWO SDRS.
111985-05-09CE65198577003AIRFRAME   59NGSUPPORT BRACKETLH RUDDER PEDALBROKEN/CRACKED 2,520 2,520       INSP/MAINTUNCOMMONCESSNAT337H33701854NONEOTHERBOTH INBOARD RUDDER PEDAL BEARING SUPPORT BRACKETS BROKEN AND CRACKED. TWO SDRS.
81985-05-02CE65198576610AIRFRAME   88NGSUPPORT BRACKETLEFT INBOARDCRACKED 2,361 2,361       INSP/MAINTUNCOMMONCESSNAT337H33701947NONEOTHERLEFT INBOARD RUDDER PEDAL BEARING SUPPORT CRACKED.
31985-04-05SW64198575034AIRFRAME   714GGSUPPORT BRACKETLT I/B MNT FLNGCRACKED 5,689 5,689       INSP/MAINTUNCOMMONCESSNA337G33701728NONEOTHERBOTH LEFT AND RIGHT SUPPORTS WERE CRACKED ALONG RADIUS OF I/B MNTNG FLANGE + AT BRNG BLOCK MNT PLATES. CRACKS ABOUT 2 INCHES LONG.
21985-04-05SW64198575033AIRFRAME   714GGSUPPORT BRACKETRT I/B MNT FLNGCRACKED 5,689 5,689       INSP/MAINTUNCOMMONCESSNA337G33701728NONEOTHERBOTH LEFT AND RIGHT SUPPORTS WERE CRACKED ALONG RADIUS OF I/B MNTNG FLANGE + AT BRNG BLOCK MNT PLATES. CRACKS ABOUT 2 INCHES LONG.
471985-01-16SO64198570822AIRFRAME   86285GBRACKETCONTR RUD BARCRACKED 3,839 3,839       INSP/MAINTUNCOMMONCESSNA337D3371142NONEOTHERCENTER RUDDER BAR SUPT BRCKTS CRACKED.
81981-12-17GL65198193638AIRFRAME   5302SGBAR SUPPORTPILOTS RT EDALCRACKED 2,200 2,200       NOT REPORTEDUNCOMMONCESSNA3373370402NONEOTHERTHE RUDDER TORQUE TUBE SUPPORT RACKED T PILOTS RH PEDAL.
391981-04-29EA03198179364AIRFRAME   2278XGSUPPORTL-R RUD BARCRACKED 2,251 2,251       INSP/MAINTUNCOMMONCESSNA3373370178NONEOTHERSUSPECT CRACKING CAUSED BY METAL FATIGUE.
281980-10-17WP01198080313AIRFRAME   2144XGSUPPORTPEDAL TORQ TUBESCRACKED 3,350 3,350       INSP/MAINTUNCOMMONCESSNA3373370044NONEOTHERSUPPORTS MOUNTED ON THE FIREWALL AND WHICH HOLDS THE RUDDER PEDAL TORQUE TUBES C RACKED.
181978-04-06Z197809600082AIRFRAME   32DB   RUDDER BARFIREWALL ASSYCRACKED 2,969 2,969       INSP/MAINTOVER 24 MOCESSNA3370049NONEOTHER  
121978-03-29Z197808800043AIRFRAME       SUPPORT ASSYFIRE WALLCRACKED 2,118 2,118       INSP/MAINTOVER 24 MOCESSNA3370379NONEOTHERBOTH INBOARD RUDDER BAR SUPPORT ASSY FOUND CRACKED APPROX 2 INCHES
131977-12-27Z197736100030AIRFRAME   2217X   SUPPORTRUDDER BARSCRACKED 2,590 2,590       UNKNOWNOVER 24 MOCESSNA3373370117NONEUNKNOWNPART BADLYCRACK,MAY FAIL,CAUSING LOSS OF USE OF RUDDER,AND NOSE STEARING.
281977-09-15Z197725800079AIRFRAME   86395   PEDAL SUPPORTCOCKPITBROKEN 1,000 1,000       INSP/MAINTOVER 24 MOCESSNA337D3371171NONEOTHERCUSTOMER COMPLAINED RUDDER TRIM NOT FUNCTIONING PROPERLY. FOUND RUDDER PEDAL SUP PORT.
401974-11-22Z197432600088AIRFRAME   5367S   SUPPORTRUDDER BARCRACKED 2,003 2,003       UNKNOWNOVER 24 MOCESSNA337A3370467NONEOTHERBOTH SUPPOORT ASSYS CRACKED AT CNTR RUDDER BAR BEARING ATCH, LT 1513500-13, RT 1 51300-14
(Less significant items below)
381980-05-22SO65198070830AIRFRAME   1443SGPINFIREWALLHANGS 100 100       DESCENTFREQUENTCESSNA337H33701918NONEUNKNOWNDURING DESCENT IN STEEP RT SPIRAL RUDDER PEDAL HUNG IN FULL FWD POSITION.CLEVIS PIN THAT ATTACHES BRAKE LINK TO RUD

RELATES TO CABIN DOOR
RowDate Of ReportOperator Control NumberSegmentDate Of OccurrenceAircraft RegistrationOperation TypeDescriptive Name Of PartDefective Location On AircraftFailed Part ConditionPart Total TimePart Total Time Since OverhaulComponent ManufacturerComponent Manufacturer ModelComponent Manufacturer NumberStage Of OperationSeverity FactorAircraft ManufacturerAircraft Manufacturer ModelAircraft Manufacturer NumberPrecautionary ProceduresNature Of ConditionzxcvbRemarkszxcvb
471990-08-30WP099095341AIRFRAME1990-05-22772HGROD ASSEMBLYFWD TORQUE TUBEBENT/BROKE 0 0       INSP/MAINTNEVERCESSNAT337GP3370265NONEOTHERTHIS LINK BROKE, IT WOULD NOT ALLOW THE TORQUE TUBE TO ROTATE AND UNLATCH THE ENTRY DOOR. THE PILOT WAS TRAPPED IN THE AIRCRAFT FOR 2.5 HOURS BEFORE A SUCCESSFUL EGRESS COULD BE EXECUTED.
501984-01-23GL14198471491AIRFRAME   12GGDOOR LOCKUPR CAB DOORWIRE BROKEN 1,058 1,058       INSP/MAINTNEVERCESSNAT337GP3370265NONEOTHERAFT CABIN DOOR LOCK WIRE BROKEN OFF INSIDE OF DOOR.
271983-07-15SW99198381529AIRFRAME   86106GOUTER DOOR SKINCABIN DOORCORROSION 2,205 2,205       INSP/MAINTNEVERCESSNA337D1083NONEOTHERFOUND CORROSION ON INNER SURFACE OF OUTER DOOR SKIN, CAUSED BY WATER ABSORBING INTO FIBERBOARD BACKING.
361981-04-22CE64198178906AIRFRAME   4KPGLOCK PINUPR DR LATCHMISSING 1,409 1,409       INSP/MAINTNEVERCESSNAT337GP3370255NONEOTHERCOULD NOT OPEN UPPER CABIN DOOR-FOUND SPRING CLIP AND BALL MISSING FROM LOWER FW D UPPER DOOR LATCH LOCK MECHANISM.
331980-05-15SW66198070281AIRFRAME   255GCASINGCABIN DOORSLIPPED 784 784       NOT REPORTEDNEVERCESSNAT337GP3370213NONEOTHERUNABLE TO OPEN CABIN DOOR BECAUSE SPIRAL CASING WORKED DN THRU CLAMP INTO SLEEVE P/N1517120-13 + ACTUATES LOCK PIN.
31979-06-28Z197917900085AIRFRAME   912JF   ROD END   BENT 127 127   151140048   INSP/MAINTNEVERCESSNAP337H3370315NONEOTHERUNABLE TO OPEN UPPER CABIN DOOR.FOUND ROD END TO UPPER LATCH BENT WHERE FALURE O CCURRED.
311978-11-03Z197830700104AIRFRAME   4BZ   LATCH LINK EYECABIN DOORBROKEN 0 0       INSP/MAINTNEVERCESSNAP337HP3370308NONEOTHERCABIN DOOR COULD NOT BE OPENED FROM INSIDE DUE TO DOOR LATCH LINKAGE EYE BROKE O FF.
221978-10-12Z197828500029AIRFRAME   4BX   EYECABIN DOORBROKEN 82 82       TAXI/GRND HDLNEVERCESSNAP337HP3370307NONEOTHERCREW UNABLE TO DEPART AC,REQUIRED OUTSIDE ASSISTANCE TO DISASSEMBLE DOOR.FOUND U PPER CABIN DOOR FWD LATCH EYE BROKE
61978-03-22Z197808100028AIRFRAME   15UC   UPPER DOORCABINSEPARATED 520 520       CLIMBOVER 24 MOCESSNAT337GP3370216UNSCHED LANDINGINFLIGHT SEPARATIONUPPER DOOR BLEW OPEN AND DEPARTED AIRCRAFT AT 8800 FT ALTITUDE.DOOR HAS NOT BEEN LOCATED
181977-04-18Z197710800049AIRFRAME   255   HOUSINGCABIN DOORSLIPPED 312 312       TAXI/GRND HDLOVER 24 MOCESSNA337P3370213OTHEROTHERCABIN DOOR FRONT CONTROL LOCK CABLE HOUSING SLIPPED DN & LOCK LINKS WOULD NOT DISENGAGE & OPEN DOOR
161974-10-01Z197427400034AIRFRAME   9CT   SHAFT,JOINTDRILLED HOLEFAILED 275 275       INSP/MAINTOVER 24 MOCESSNAT337GP3370011NONEOTHERUNABLE TO OPEN CABIN DOOR FROM INSIDE OR OUTSIDE. HAD TO REMOVE UPHOLSTERY PANEL S AND PRYED LATCHES OPEN.

RELATES TO MISCELLANEOUS AREAS
RowDate Of ReportOperator Control NumberSegmentDate Of OccurrenceAircraft RegistrationOperation TypeDescriptive Name Of PartDefective Location On AircraftFailed Part ConditionPart Total TimePart Total Time Since OverhaulComponent ManufacturerComponent Manufacturer ModelComponent Manufacturer NumberStage Of OperationSeverity FactorAircraft ManufacturerAircraft Manufacturer ModelAircraft Manufacturer NumberPrecautionary ProceduresNature Of ConditionzxcvbRemarkszxcvb
291988-01-06SO648870412AIRFRAME1987-09-2553670GPULLEY BRKTUNDER PILOT FLRBROKEN 1,303 1,303       NOT REPORTEDOCCASIONALCESSNA337G33701769NONEOTHERBRACKET HAD OUTBOARD CORNER WHERE ATTACH BOLT GOES THROUGH BROKEN OFF. PULLEY WAS FORCED SIDEWAYS BY CABLE TENSION. THE PULLEY WAS STILL TURNING, BUT AT EITHER EXTREME RIGHT OR LEFT CONTROL WHEEL MOVEMENT, THE CABLE WOULD START TO WALK OFF PULLEY. SUBMITTER SUGGEST STRONGER BRACKET, ESPECIALLY AT 90 DEGREE CABLE TURNS.
421986-04-24CE628676242AIRFRAME1986-04-0172446GPULLEY BRACKETUNDER PILOT FLRBROKEN 255 255       INSP/MAINTOCCASIONALCESSNA337G33701587NONEOTHEROWNER REPORTED THAT AILERONS WERE OUT OF RIG. INVESTIGATION SHOWED THAT PULLEY BRACKET BELOW PILOTS FEET. WAS BROKEN, WHICH ALLOWED TENSION TO SLACKEN. CESSNA MULTI-ENGINE SERVICE LETTER ME 76-21 W/REV NR 1 CALLED FOR AN INSPECTION AND POSSIBLE REPLACEMENT OF THE BRACKET WITH NEW P/N 1513883-1. ME-74-5 ALSO MENTIONED THIS PROBLEM. NEITHER SERVICE LETTER APPLIES TO THIS S/N.
231978-10-23Z197829600031AIRFRAME   53606   PULLEY BRACKETUNDER FLOORBROKEN 470 470       APPROACHOCCASIONALCESSNA337E33701735NONEFLT CONT AFFECTEDDURING LANDING PILOT HEARD LOUD BANG & BOTH AILERONS DROOPED.INSP FOUND AILERON PULLEY BRACKET BROKEN.

RELATES TO UNIDENTIFIED AREAS
RowDate Of ReportOperator Control NumberSegmentDate Of OccurrenceAircraft RegistrationOperation TypeDescriptive Name Of PartDefective Location On AircraftFailed Part ConditionPart Total TimePart Total Time Since OverhaulComponent ManufacturerComponent Manufacturer ModelComponent Manufacturer NumberStage Of OperationSeverity FactorAircraft ManufacturerAircraft Manufacturer ModelAircraft Manufacturer NumberPrecautionary ProceduresNature Of ConditionzxcvbRemarkszxcvb
432007-11-02UIEA200700462AIRFRAME2007-10-24424ASKINNR 4 NACELLECRACKED           INSP/MAINT   CESSNAT337GP3370259NONEOTHERNR 4 PYLON LT SKIN WAS FOUND CRACK AT 483AL ACCESS PANEL CUTOUT LOWER AFT CORNER.
151985-05-24WP08198578015AIRFRAME   5CUGBELLCRANK ASSY   TORN LOOSE 1,618 1,618       INSP/MAINTOCCASIONALCESSNAT337GP3370066NONEOTHERDURING ANNUAL INSPECTION FOUND BELLCRANK ASSEMBLY TORN LOOSE FROMSTRUCTURE AND ROD ASSEMBLY BENT.
141985-05-24WP08198578014AIRFRAME   5CUGROD ASSY   BENT 1,618 1,618       INSP/MAINTOCCASIONALCESSNAT337GP3370066NONEOTHERDURING ANNUAL INSPECTION FOUND BELLCRANK ASSEMBLY TORN LOOSE FROMSTRUCTURE AND ROD ASSEMBLY BENT.
301981-04-06CE64198177405AIRFRAME   159NGBRACKETLEFTBROKEN 4,179 4,179       INSP/MAINTOCCASIONALCESSNA337G33701668NONEOTHERBRACKET AT FIREWALL + FLOOR-INBOARD EAR BROKE OFF AT BOLT HOLE.
311980-10-27WP04198080745AIRFRAME   463DFGHALE OUTERBEADED AREACRACKED 0 0       INSP/MAINTFREQUENTCESSNA337B337M0325NONEOTHERSIX INCH RADIAL CRACK FOUND INSIDE THE BEADED AREA.
11980-07-28EA62198075252AIRFRAME   1346LGBRACKET ASSYOTBD LWR BELLCRKBROKEN 0 0       INSP/MAINTCOMMONCESSNAT337H33701838NONEOTHERDAMAGED IN WIND STORM.
281979-04-03Z197909300062AIRFRAME   1342L   SKINTAIL SECTIONCORRODED 107 107       INSP/MAINTUNCOMMONCESSNA3373371834NONEOTHERC-W AD79-05-02 AND FOLLOWING REMOVAL OF ELT LITHIUM BATTERY-FOUND CONSIDERABLE C ORROSION IN ELT MOUNTING AREA.
461978-12-04Z197833800104AIRFRAME   53606   BRACKETPULLEY-FIREWLBROKEN 470 470       INSP/MAINTOCCASIONALCESSNA33701735NONEOTHERBOTH EARS OF PULLEY BRACKET BROKEN OFF.
501978-08-28Z197824000112AIRFRAME   53475     RT SIDE PANELBLOWN OUT 0 0       INSP/MAINTOVER 24 MOCESSNA33733701649NONEOTHERRT SIDE PANEL CRACKED ALL AROUND COLLECTOR INLET
201978-04-06Z197809600084AIRFRAME   32DB   CHANNEL ASSYBOLT HOLEWORN 2,969 2,969       INSP/MAINTOVER 24 MOCESSNA3370049NONEOTHER  
351977-10-05Z197727800038AIRFRAME   72247     RH OUTBDCRACKED 0 0       INSP/MAINTOVER 24 MOCESSNA337G33701545NONEOTHERCRACK OCCURRED AT DENT & APPARENTLY CAUSED BY VIBRATION
381977-01-20Z197702000068COMPONENT   1752M   CABLETURNBUCKLE ENDFRAYED 1,066 1,066       INSP/MAINTOVER 24 MOCESSNA33733701352NONEOTHERCOULD HEAR AIL CABLE STRANS RUBBING ON PULLEY BRACKET.INSP REVEALED CABLE HAD FRAYED FROM RUBBING PULLEY BKT
181974-10-08Z197428100050AIRFRAME   9CT   LATCH DRIVETHRU HOLEFAILED 0 0       INSP/MAINTOVER 24 MOCESSNA337   NONEOTHEREND OF LATCH DRIVE SHEARED WHERE ENGAGED BY AFT TORQUE TUBE. HOLE DRILLED IN DRI VE WEAKEN SAME.
81974-09-13Z197425600050AIRFRAME   5499S   BACKPLATEMT FLANGECRACKED 1,779 1,779       INSP/MAINTOVER 24 MOCESSNA3373370599NONEOTHERCRACKED AROUND MOUNTING FLANGE-BACKPLATE
71974-09-13Z197425600049AIRFRAME   5499S   TORQUE PLATEOUTER FLANGECRACKED 1,741 1,741       INSP/MAINTOVER 24 MOCESSNA3373370599NONEOTHERCRACKED FROM OUTER FLANGE TO HOLE.

ALL CESSNA 336 "STRUCTURAL" SDRs SHOWN BELOW (not grouped by aircraft area, newest first)
RowDate Of ReportOperator Control NumberSegmentDate Of OccurrenceAircraft RegistrationOperation TypeDescriptive Name Of PartDefective Location On AircraftFailed Part ConditionPart Total TimePart Total Time Since OverhaulComponent ManufacturerComponent Manufacturer ModelComponent Manufacturer NumberStage Of OperationSeverity FactorAircraft ManufacturerAircraft Manufacturer ModelAircraft Manufacturer NumberPrecautionary ProceduresNature Of ConditionzxcvbRemarkszxcvb
362003-04-14CA030227004AIRFRAME2003-02-25   ACONTROL CABLETE FLAPSFAILED           NOT REPORTED   CESSNA336   OTHEROTHER(CAN) OPERATOR EXPERIENCED A ASYMMETRIC FLAP CONDITION DURING LANDING CAUSED BY THE FAILURE OF A FLAP CABLE. THE INBOARDRIGHT HAND FLAP CABLE FAILED AT A POINT WHERE THE CABLE STARTS TO BEND AROUND THE INBOARD RIGHT HAND FLAP BELLCRANK. THIS AREA OF THE CABLE CAN ONLY BE INSPECTED WITH THE REMOVAL OF THECABLE AND/OR BELLCRANK
352002-04-252002FA0000525AIRFRAME2002-04-01108RJGCABLERT BELLCRANKBROKEN 2,892         APPROACH   CESSNA3363360067OTHERFLT CONT AFFECTEDON FINAL APPROACH, AIRCRAFT EXPERIENCED A SPLIT FLAP CONDITION, CAUSED BY BROKEN CABLE ASSEMBLY. FLAP ACTUATOR INBOARD(PN 14601007). CABLE HAD BROKEN ON RIGHT SIDE, 1 INCH FROM CABLE END, AT BELLCRANK ENTRY POINT. INSPECTION OF LEFT SIDE FLAP CABLE ASSEMBLY WITH A MIRROR, REVEALED NO NOTICEABLE DAMAGE. ALL CABLES FOR RIGHT AND LEFT FLAP SYSTEM WERE REMOVED AND INSPECTED. LEFT CABLE ASSEMBLY. FLAP ACTUATOR INBOARD, WAS FRAYED AT SAME CONTACT POINT AS RIGHT, (NOT DETECTED BY MIRROR INSPECTION). DUE TO AREA OF BREAKAGE, HAVING LIMITED POSSIBLY FOR VISUAL INSPECTION, RECOMMEND SET TIME PERIOD FOR CABLES TO BE REMOVED FOR INSPECTION OR TIME IN SERVICE REQUIREMENTS SET FOR REMOVAL.
332000-04-0620000331SH019AIRFRAME2000-03-033856UGSHOCK MOUNTFIREWALLFAILED 1,841         TAXI/GRND HDL   CESSNA33633610156OTHEROTHERDIFFICULT TO INSPECT. PILOT HEARD AND NOTICED COWL RUBBING PROPELER SPINNER DURING SHUT DOWN AT FUEL PIT AT MADERA AIRPORT. (X)
301984-12-19NE65198489369AIRFRAME   3823UGCABLELT WINGFRAYED 26,000 26,000       INSP/MAINTUNCOMMONCESSNA3363360123NONEOTHERLEFT FLAP CABLE STRANDS BROKEN. APPROXIMATELY 75 PERCENT OF STRANDS BROKEN.
291984-12-19NE65198489368AIRFRAME   3823UGCABLERT WINGBROKEN 26,000 26,000       APPROACHUNCOMMONCESSNA3363360123OTHERFLT CONT AFFECTEDRIGHT FLAP FAILED TO FULLY EXTEND. FOUND INBOARD CABLE BROKEN AT 90 DEGREE BEND AT INBOARD BELLCRANK.
271981-09-09WP02198188042AIRFRAME   1797ZGMOUNTLT FRNT MOUNTCRACKED 1,818 1,818       INSP/MAINTUNCOMMONCESSNA3363360097NONEOTHERNO TEXT
241979-10-03Z197927600055AIRFRAME   3850U   HORIZ FIREWALLUNDER EXHCRACKED 0 0       UNKNOWNNEVERCESSNA3363360150NONEOTHERHORIZONTAL FIREWALL ASSY CRACKED ALONG ANGLE BRACKET DIRECTLY UNDER EXHAUST-REAR ENGINE.
201977-03-02Z197706100026AIRFRAME   3844U   MOUNTREAR ENGCRACKED 748 748       INSP/MAINTOVER 24 MOCESSNA3363360144NONEOTHERDURING ANNUAL INSP FOUND RT FRONT ENG MOUNT BROKEN & RT REAR ENG MOUNT CRACKED
191977-03-02Z197706100024AIRFRAME   3844U   BRACKETFORWARD ENGBROKEN 748 748       INSP/MAINTOVER 24 MOCESSNA3363360144NONEOTHERDURING ANNUAL INSP RT FRONT ENG MOUNT BROKEN & RT REAR ENG MOUNT CRACKED
161976-09-27Z197627100035AIRFRAME   1702Z   TANK ASSY SUMPLEFT TAIL BOOMHOLE CHAFED 2,191 2,191       INSP/MAINTOVER 24 MOCESSNA3363360002NONEOTHERELEVATOR CONTROL CABLES CHAFED THRU TOP OF SUMP TANK
61975-01-23Z197502300072AIRFRAME   336JL   MT LEGRT LEGBROKEN 1,386 1,386       UNKNOWNOVER 24 MOCESSNA3360181NONEOTHERRT REAR ENG MOUNT LEG BROKEN

1. ConsultResearch Inc. is a 9-year-old Delaware corporation based in South Florida. Its principal business is providing consulting and research services to high-tech firms.

2. Ernie Martin has an MS degree in Mechanical Engineering from Caltech, over 30 years experience in aerospace and aviation, has consulted for various companies (including GE), and has served as an advisor to several government agencies in the U.S.and abroad. In addition, Mr. Martin has piloted and owned 337 Cessna (Skymaster) aircraft for over 10 years (he is on his second one), has participated in all maintenance of said aircraft (including annual inspections), has a Website dedicated to engineering, maintenance and operational aspects of the aircraft at www.SkymasterUS.com, and is a Webmaster of www.337Skymaster.com, which has an active Message Board giving Skymaster owners the opportunity to discuss any aicraft related issue.

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