United States Department of Transportation / Federal Aviation Administration logo

AFS-600 Regulatory Support Division logo

 

ADVISORY CIRCULAR

43-16A

 

 

AVIATION MAINTENANCE ALERTS

 

 

flag of the United States of America

 

ALERT

NUMBER

385

bald eagle watching over three eggs

AUGUST

2010

 


CONTENTS

AIRPLANES

BEECHCRAFT............................................................................................................................ 1

BELLANCA................................................................................................................................. 2

CESSNA...................................................................................................................................... 7

 

HELICOPTERS

SCHWEIZER............................................................................................................................. 12

POWERPLANTS

CONTINENTAL....................................................................................................................... 16

LYCOMING.............................................................................................................................. 17

ACCESSORIES

AERO CLASSIC OIL COOLER............................................................................................... 18

AIR NOTES

INTERNET SERVICE DIFFICULTY REPORTING (iSDR) WEB SITE................................... 19

IF YOU WANT TO CONTACT US......................................................................................... 20

AVIATION SERVICE DIFFICULTY REPORTS...................................................................... 20

 


U.S. DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
WASHINGTON, DC 20590

AVIATION MAINTENANCE ALERTS

The Aviation Maintenance Alerts provides the aviation community with an economical means to exchange service experiences and to assist the FAA in improving aeronautical product durability, reliability, and safety.  We prepare this publication from information operators and maintenance personnel who maintain civil aeronautical products pertaining to significant events or items of interest.  At the time we prepared this document, we have not fully evaluated the material.  As we identify additional facts such as cause and corrective action, we may publish additional data in subsequent issues of the Alerts.  This procedure gives Alerts’ readers prompt notice of conditions reported to the FAA Service Difficulty Reporting System (SDRS).  We welcome your participation, comments, and suggestions for improvement.  Send to:  FAA; ATTN: Aviation Data Systems Branch (AFS-620); P.O. Box 25082; Oklahoma City, OK 73125-5029.

(Editor’s notes are provided for editorial clarification and enhancement within an article. They will always be recognized as italicized words bordered by parentheses.)

 

AIRPLANES

Beechcraft:  58; Instrument Air Water Contamination; ATA 3710

An unidentified submitter states, "Water is entering the instrument air system and causing corrosion of the system components.  A higher than acceptable gyroscope failure rate has prompted our maintenance staff to probe into the causes of this issue.  Upon opening the instrument air, pressure regulator and manifold check valve assembly for inspection, heavy corrosion of the ferrous components were noted.  Large particles of rust are breaking loose from the fittings and other steel pieces in the system, contaminating instruments.  We recommend Beechcraft develop a Service Bulletin or kit to allow for an inline filter to be installed after the instrument air regulator, but before the air enters the instruments."

Part(s) Total Time:  5,243 hours

 

Beechcraft:  58; Failed Landing Light Switch; ATA 3340

"The aircraft landing light was observed to be hot and emitting smoke," says an unknown writer.  "This switch is post AD (Airworthiness Directive) 2008-13-17.  Basically these switches are the same as the original switch with the addition of an insulator.  (This) prevents a failed 'open' switch from conducting current through the point's 'hold-open' spring that (otherwise) begins to overheat and burn.  Apparently, this failed switch (P/N 35380132103) had a manufacturing defect which allowed current to flow through this spring.  An internal inspection of this switch was inconclusive as to the installation or placement of the insulator pads due to the damage sustained during the overheat event.

"In a ten month period, a fleet of twelve aircraft has required replacement of twenty-one of these switches.  The failures have been limited to the landing and taxi light circuits.  Fortunately, all except this one have failed in the open condition with no indication of smoke or burning.  All switches that have been opened for inspection fail where the copper braid from the points is attached to the switch frame.  Tyco lists this switch as being rated for 10,000 mechanical cycles, but even accounting for unusually heavy fleet usage, the failure rate seems to be no more the 4,000 cycles.


"Much had been made of the overkill of AD 2008-13-17, but until you are flying IFR (instrument flight rules) with a circuit that is overheating and burning with no means other than the master switch to shut it down—(then) suddenly a glowing hot switch becomes much more than an inconvenience.  Final resolution of this issue appears to still be elusive."

(Good Job—we appreciate your submissions to the SDRS database.  The listed manufacturer's name is Potter.  See the first Cessna article below for a similar report and photo describing what may be a very similar switch—Ed.)

Part Total Time:  1,486 hours

 

Bellanca:  1730A; Failed Nose Landing Gear; ATA 3230

"During touchdown on runway 36L," says the submitter, "the nose landing gear failed and partially collapsed upon contact with the runway.  It appears (from our investigation) the nose gear linkage bearing rod-end (P/N 198001-2) to the gear extension assembly experienced a fatigue failure.  Based on the fracture signature, the failure appears to be a mild to high stress concentration (from a...) one-way bending load.  The rod-end failed at a point where (its) threads and nut meet, shearing even with the nut face (AN316-4R).  (These) threads were stretched and bent at a fifteen degree angle with about one-half inch of thread showing.  The rod-end bearing movement was satisfactory.

"When the NLG tire contacted the runway, the over-center extension assembly (to the forward and aft drag struts) failed at the rod-end.  (This allowed...) both struts to travel beyond their proper horizontal positions...allowing the nose wheel to move aft at touchdown.  (This) forced the aft drag strut to pin the forward strut against the wheel cylinder, (preventing) nose wheel steering with the rudder pedals.  The wheel went slightly to the left at contact with the runway and jammed.  The aircraft veered sharply left and (moved) off the runway, across the grass, on to and across the left taxi-way (and its grass), and into a ravine where it came to rest."  (The extension assembly/component number is:  P/N 194317.)


PHOTO OF THE NOSE GEAR STUCK IN MUD AND GRASS.


CLOSEUP PHOTO OF THE NOSE GEAR STRUT.


CLOSEUP PHOTO OF THE NOSE GEAR STRUT WITH BROKEN ROD-END.


CLOSEUP PHOTO OF THE BROKEN ROD-END.


CLOSEUP PHOTO OF THE BROKEN ROD-END (OPPOSITE).

 

(The photos drive the point home quite dramatically—thanks!)

Part Total Time:  2,751 hours

 

Cessna:  425; Failed Avionics Master Switch; ATA 2460

This defect report states, "The avionics master switch (P/N CM358950) was found inoperative upon a functional check.  The part has been red-tagged and replaced with a new switch.  The (failed switch) was disassembled, and upon further inspection it appears to have a manufacturer's defect."  (The manufacturer's name is Potter.  This P/N is reflected ninety times in the SDRS database!  Note the similarities in the failed switch description in the second Beechcraft article to the following photo.)


CLOSEUP PHOTO OF THE SWITCH WITH ITS HOUSING OPENED.

Aircraft Total Time:  4,679 hours

 

Cessna:  525B; Main Landing Gear Corrosion; ATA 3213

"Corrosion was found at the left side, aft main landing gear Trunnion pin's bore and face while performing the Cessna 48 month/2,400 inspection.  A mixture of ferrous and non-ferrous parts are used in the effected areas," says this submitter.  "Lubrication of this area is performed at 12-month intervals.  The lubrication process is to apply WC-393 to the forward and aft pivot points with a squeeze bottle."   (Trunnion P/N:  63413211.)


CLOSEUP PHOTO OF THE LANDING GEAR TRUNNION CORROSION.

 

Part Total Time:  1,333 hours

 

Cessna:  560XL; Broken Aileron Control Lock Arm; ATA 2770

A writer says, "I found the control lock system partially inoperative on post-flight inspection.  Further investigation determined the left aileron lock arm was broken at the lock feature contact area.  The cause of the part failure is unknown (P/N 666102127).  The part appears to have suffered overloading at the contact point, resulting in a crack and (leading) to the failure of the lock arm."


CLOSEUP PHOTO OF THE BROKEN LOCK ARM.


FLOOR VIEW OF THE AILERON LOCK ARM MECHANISM.

SECOND FLOOR VIEW OF THE AILERON LOCK ARM MECHANISM.

Part Total Time:  658 hours

 


HELICOPTERS

Schweizer:  269C; Chafed Fuel Tank; ATA 2810

A technician states, "During a 200 hour inspection, wear marks were found on the bottom of the fuel tank.  (These chafe areas were...) caused by the attach pin (P/N MS20392-2C47) used on the strap assembly (P/N 269A8329-23).  A detailed inspection found the wear (occurred) because of insufficient pad material installed on the strap, allowing contact between the pin and the fuel tank skin.  Wear depth at one point was enough to require replacement of the tank.  Inspection of a (second aircraft) found the beginning of similar wear marks."(Note the total part time:  194.0 hours!)


CLOSEUP PHOTO OF THE STRAP PIN.


CLOSEUP PHOTO OF THE CHAFED TANK HOLE.


PARTS CATALOG DRAWING.

Part Total Time:  194.0 hours

 


POWERPLANTS

Continental:  IO550N; Chafed Fuel Injector Line; ATA 7310

(The following report pertains to a Cirrus SR22 airplane.)

"An aircraft owner requested we clean his fuel injectors—which we did," says an aircraft mechanic.  "I was nearly completed with the task—tightening the nut for the number one cylinder fuel injection line.  I noticed the line was very loose.  Upon further inspection I found the retaining clip (designed) to secure the line to an engine bracket was falling out (apart?) and not doing its job.  I also noticed black staining on an adjacent engine structure.  When I removed the line, I found approximately one inch of the tubing had been worn away to half its thickness and was leaking fuel over the top of the engine.  I inspected the other fuel lines and found the number two cylinder fuel injection line on the opposite side of the engine also had damage, but this was caused by ignition leads rubbing against (it).  This (damaged line) was less severe (and not leaking), but it was not serviceable.  New lines were ordered and installed.  The number one line was secured with a heavier type Adel clamp, and all ignition leads were secured to prevent further chafing.  This customer is new to our operation; it is unknown how long this condition has existed."  (The fuel line P/N is 646421.  Nice catch!  I hope the owner bought you lunch.  See also the chafed Schweizer fuel tank hole under helicopters—Ed.)

 

CLOSEUP PHOTO OF CHAFED INJECTOR LINE.

Part Total Time:  (unknown)

 


Lycoming:  TIO540J2BD; Cam-follower Pitting; ATA 8520

(The following report combines and references two different, same model engines on two different Piper PA31350 aircraft from the same submitter..)

A submitter states, "Excessive cam lobe wear is causing power loss and early removal of several of our Chieftain Lycoming engines.  This engine was removed at 1,650.2 hours TTSO (total time since overhaul), with 549.8 hours remaining on our 2,200 hour overhaul interval.  I have been in contact with Lycoming Technical Support for an extended period of time, now, and have yet to find a solution.  It seems for some reason one cam follower will (usually) become pitted and begin to accelerate wear on the lobe that it rides on.  (I have) no idea what is causing the pitting or how to prevent it.  We use only Lycoming factory remanufactured engines in our entire fleet."

 

CLOSEUP PHOTO OF THE PITTED CAM FOLLOWER.

 


(This second engine had 1,455 hours total, with  745 hours time remaining.)

 

CLOSEUP PHOTO OF ANOTHER ENGINE'S PITTED CAM FOLLOWER.

(Terrific report!  It would have been better with...part numbers?)

Part Total Time:  1,650 and 1,455 hours (respectively)

 

ACCESSORIES

Aero Classic Oil Cooler:  P/N 80000741; Failed/leaking; ATA 7921

"The first (oil cooler) unit that failed was an overhauled cooler...(P/N 8000074) installed on a factory rebuilt, zero-time Lycoming O-540 engine," says the submitter.  "This unit failed after 23.6 flight hours.  The second, new oil cooler (same part number) failed after a total time of 53 hours.  This (issue) is urgent...."  (Good reporting; but please note these are the first two entries for this P/N in the SDRS database.)

Part Total Time(s):  23.6 and 53 hours (respectively)

 


AIR NOTES

INTERNET SERVICE DIFFICULTY REPORTING (iSDR) WEB SITE

The Federal Aviation Administration (FAA) Internet Service Difficulty Reporting (iSDR) web site is the front-end for the Service Difficulty Reporting System (SDRS) database that is maintained by the Aviation Data Systems Branch, AFS-620, in Oklahoma City, Oklahoma. The iSDR web site supports the Flight Standards Service (AFS), Service Difficulty Program by providing the aviation community with a voluntary and electronic means to conveniently submit in-service reports of failures, malfunctions, or defects on aeronautical products. The objective of the Service Difficulty Program is to achieve prompt correction of conditions adversely affecting continued airworthiness of aeronautical products. To accomplish this, Malfunction or Defect Reports (M or Ds) or Service Difficulty Reports (SDRs) as they are commonly called, are collected, converted into a common SDR format, stored, and made available to the appropriate segments of the FAA, the aviation community, and the general public for review and analysis. SDR data is accessible through the “Query SDR data” feature on the iSDR web site at: http://av-info.faa.gov/sdrx/Query.aspx.

In the past, the last two pages of the Alerts contained a paper copy of FAA Form 8010-4, Malfunction or Defect Report. To meet the requirements of *Section 508, this form will no longer be published in the Alerts; however, the form is available on the Internet at: http://forms.faa.gov/forms/faa8010‑4.pdf. You can still download and complete the form as you have in the past.

*Section 508 was enacted to eliminate barriers in information technology, to make available new opportunities for people with disabilities, and to encourage development of technologies that will help achieve these goals.

A report should be filed whenever a system, component, or part of an aircraft, powerplant, propeller, or appliance fails to function in a normal or usual manner. In addition, if a system, component, or part of an aircraft, powerplant, propeller, or appliance has a flaw or imperfection, which impairs or may impair its future function, it is considered defective and should be reported under the Service Difficulty Program.

The collection, collation, analysis of data, and the rapid dissemination of mechanical discrepancies, alerts, and trend information to the appropriate segments of the FAA and the aviation community provides an effective and economical method of ensuring future aviation safety.

The FAA analyzes SDR data for safety implications and reviews the data to identify possible trends that may not be apparent regionally or to individual operators. As a result, the FAA may disseminate safety information to a particular section of the aviation community. The FAA also may adopt new regulations or issue airworthiness directives (ADs) to address a specific problem.

The iSDR web site provides an electronic means for the general aviation community to voluntarily submit reports, and may serve as an alternative means for operators and air agencies to comply with the reporting requirements of 14 Title of the Code of Federal Regulations (CFR) Section 121.703, 125.409, 135.415, and 145.221, if accepted by their certificate-holding district office. FAA Aviation Safety Inspectors may also report service difficulty information when they conduct routine aircraft maintenance surveillance as well as accident and incident investigations.

The SDRS database contains records dating back to 1974. At the current time, we are receiving approximately 40,000 records per year. Reports may be submitted to the iSDR web site on active data entry form or submitted hardcopy to the address below.


The SDRS and iSDR web site point of contact is:

Pennie Thompson
Service Difficulty Reporting System, Program Manager
Aviation Data Systems Branch, AFS-620
P.O. Box 25082
Oklahoma City, OK 73125
Telephone: (405) 954-5313
SDRS Program Manager e-mail address: 9‑AMC‑SDR‑ProgMgr@faa.gov

 

IF YOU WANT TO CONTACT US

We welcome your comments, suggestions, and questions. You may use any of the following means of communication to submit reports concerning aviation-related occurrences.

Editor:  Daniel Roller (405) 954-3646
FAX:    (405) 954-4570 or (405) 954-4655

E-mail address:   Daniel.Roller@faa.gov

Mailing address: FAA, ATTN: AFS-620 ALERTS, P.O. Box 25082 , Oklahoma City, OK 73125-5029

You can access current and back issues of this publication from the internet at:
http://av‑info.faa.gov/. Select the General Aviation Airworthiness Alerts heading.

 

AVIATION SERVICE DIFFICULTY REPORTS

The following are abbreviated reports processed for the previous month, which have been entered into the FAA Service Difficulty Reporting System (SDRS) database. This is not an all-inclusive listing of Service Difficulty Reports. For more information, contact the FAA, Regulatory Support Division, Aviation Data Systems Branch, AFS-620, located in Oklahoma City, Oklahoma. The mailing address is:

FAA
Aviation Data Systems Branch, AFS-620
PO Box 25082
Oklahoma City, OK 73125

To retrieve the complete report, click on the Control Number located in each report. These reports contain raw data that has not been edited. Also, because these reports contain raw data, the pages containing the raw data are not numbered.

If you require further detail please contact AFS-620 at the address above.


 

Federal Aviation Administration

Service Difficulty Report Data

 

Sorted by aircraft make and model then engine make and model. This report derives from unverified information submitted by the aviation community without FAA review for accuracy.

Control Number

Aircraft Make

Engine Make

Component Make

Part Name

Part Condition

Difficulty Date

Aircraft Model

Engine Model

Component Model

Part Number

Part Location

2010FA0000537

 

 

 

IMPULSE COUPLING

DAMAGED

5/21/2010

 

 

 

 

MAGNETO

((2NCR)) THE MAGNETO WAS ORDERED AS A REPLACEMENT UNIT. PRIOR TO INSTALLATION, IT WAS NOTED THAT ONLY 2 PINS EXISTED FOR THE IMPULSE COUPLING WHEN 4 ARE REQUIRED FOR A 6 CYLINDER ENGINE. PN ON DATA TAG WAS CORRECT IAW 6 CYLINDER APPLICATION. PART WAS REJECTED FOR INSTALLATION.

2010FA0000683

 

 

 

CAMSHAFT

MISOVERHAULED

5/18/2010

 

 

 

SL18840

ENGINE

(WS9R) CAMSHAFT LOBES HAVE BLAST MEDIA THAT WAS NOT CLEANED OFF PROPERLY AND HAS LEFT THE MEDIA IMBEDDED IN THE LOBES OF THE CAMSHAFT. THIS WAS A NEW OUT-OF-BOX COMPONENT.

2010FA0000684

 

 

 

CAMSHAFT

MISOVERHAULED

5/18/2010

 

 

 

SL18840

ENGINE

(WS9R) CAMSHAFT LOBES HAVE BLAST MEDIA THAT WAS NOT CLEANED OFF PROPERLY AND HAS LEFT THE MEDIA IMBEDDED IN THE LOBES OF THE CAMSHAFT. THIS WAS A NEW OUT-OF-BOX COMPONENT.

2010FA0000689

 

 

 

CYLINDER

MISOVERHAULED

6/7/2010

 

 

 

ECL240CA

ENGINE

(WS9R) UPON INSPECTION OF CYLINDER, THE HEAD IS NOT COMPLETELY SCREW ONTO THE BARREL.

2010FA0000681

 

 

 

CAMSHAFT

MISOVERHAULED

5/18/2010

 

 

 

SL18840

ENGINE

(WS9R) CAMSHAFT LOBES HAVE BLAST MEDIA THAT WAS NOT CLEANED OFF PROPERLY AND HAS LEFT THE MEDIA IMBEDDED IN THE LOBES OF THE CAMSHAFT. THIS WAS A NEW OUT-OF-BOX COMPONENT.

2010FA0000685

 

 

 

CAMSHAFT

MISOVERHAULED

5/18/2010

 

 

 

SL18840

ENGINE

(WS9R) CAMSHAFT LOBES HAVE BLAST MEDIA THAT WAS NOT CLEANED OFF PROPERLY AND HAS LEFT THE MEDIA IMBEDDED IN THE LOBES OF THE CAMSHAFT. THIS WAS A NEW OUT-OF-BOX COMPONENT.

2010FA0000686

 

 

 

CAMSHAFT

MISOVERHAULED

5/18/2010

 

 

 

SL18840

ENGINE

(WS9R) CAMSHAFT LOBES HAVE BLAST MEDIA THAT WAS NOT CLEANED OFF PROPERLY AND HAS LEFT THE MEDIA IMBEDDED IN THE LOBES OF THE CAMSHAFT. THIS WAS A NEW OUT-OF-BOX COMPONENT.

2010FA0000682

 

 

 

CAMSHAFT

MISOVERHAULED

5/18/2010

 

 

 

SL18840

ENGINE

(WS9R) CAMSHAFT LOBES HAVE BLAST MEDIA THAT WAS NOT CLEANED OFF PROPERLY AND HAS LEFT THE MEDIA IMBEDDED IN THE LOBES OF THE CAMSHAFT. THIS WAS A NEW OUT-OF-BOX COMPONENT.

2010FA0000588

 

 

 

ROTOR

LOOSE

6/3/2010

 

 

 

6431000

GEN STATOR

(( HZ3R)) NR 2 AC GENERATOR CAUTION LIGHT DURING T/O ROLL. STATOR DAMAGED CAUSED BY LOOSE ROTOR BAND. ROTOR DAMAGED DUE TO BAND SEPARATION. OPEN

2010FA0000687

 

 

 

THROTTLE BODY

DAMAGED

5/24/2010

 

 

 

6431751

 

(WS9R) DAMAGED THREADS TO THROTTLE BODY.

2010FA0000714

 

 

 

GENERATOR

FAILED

6/29/2010

 

 

 

11522185

 

( HZ3R) FOUND AC CHIP DETECTION TRIGGERED IN CDS. DURING REMOVAL OF NR 1 AC GEN. FOUND A HOLE IN AC GEN MOUNTING SURFACE CAUSING A CONTAMINATION IN OIL SYS. CAUTION DURING T/O. THE ROTOR BAND FAILED AS A RESULT OF LACK OF PENETRATION OF WELD. THE ROTOR BAND FAILURE CAUSED ALL OTHER DAMAGE SEEN. PENDING COMPLETION OF ENGINEERING INVESTIGATION.

EVGR062910

 

CONT

 

COLLAR

BENT

3/22/2010

 

TSIO520*

 

626739M010

TRANSFER COLLAR

(EVGR) PN 626739M010 TRANSFER COLLAR. THE COLLAR SEEMS TO HAVE BEEN DAMAGED AFTER IT WAS GROUND. ON ONE SIDE THE SPLIT LINE DOES NOT LINE UP, YOU CAN CATCH A FINGERNAIL ON IT. WHEN INSTALLED IT IS TIGHT AND RUBS AT THAT POINT AS SHOWN BY THE MAGIC MARKER RUBBED OFF (PICTURES AVAILABLE ON REQUEST). WHEN THE DIAMETER IS MEASURED WITH BORE GAGE ON EACH SIDE OF THE SPLIT, THERE IS A DIFFERENCE OF .0033. THE MAX CLEARANCE ON THE SHAFT IS .0018. THE PART WAS RETURNED TO THE VENDOR FOR WARRANTY REPLACEMENT.

2010FA0000594

 

GARRTT

 

BEARING

MISSING

5/27/2010

 

TPE33111U

 

31015002

DIAPHRAGM ASSY

ENGINE WAS REMOVED FROM ACFT FOR POSSIBLE OVERTEMP OPERATION. CUSTOMER REQUESTED TEST RUN TO NOTE CONDITION PRIOR TO DISASSEMBLY. HIGHT VIBRATION WAS NOTED FROM GEARBOX THAT INDICATED THE HIGH SPEED PINION. ENGINE GEAR BOX WAS DISASSEMBLED AND HIGH SPEED PINION WAS FOUND TO HAVE 1 ROLLER MISSING FROM THE BEARING. THE DIAPHRAGM ASSY INCLUDING THE HIGH SPEED PINION WAS ASSEMBLED BY REPAIR STATION. ON W/O 810230001 DATED 09/17/2002. THE DIAPHRAGM WAS INSTALLED BY ANOTHER REPAIR STATION ON W/O 147640, DATED 11/22/2002.

2010FA0000641

 

IAE  

 

ROTOR

CRACKED

5/12/2010

 

V2527A5

 

2A5001

ENGINE

((ANZY)) THIS ENGINE, IS UNDERGOING MX. DURING ROUTINE FPI, LINEAR INDICATIONS WERE DETECTED ON THE FIR TREE ROOT PRESSURE FACES, CONSISTENT WITH CRACKING, WHICH APPEARS TO BE ASSOCIATED WITH CORROSION PITTING. THIS ISSUE HAS BEEN DETECTED ON OTHER HUBS AT THIS FACILITY. THE ITEM HAS BEEN REMOVED FROM SERVICE AND MFG HAF BEEN CONTACTED FOR FURTHER INSTRUCTIONS REGARDING CAUSE INVESTIGATION.

2010FA0000640

 

IAE  

 

ROTOR

CRACKED

5/12/2010

 

V2527A5

 

2A5001

ENGINE

((ANZY)) THIS ENGINE IS UNDERGOING MX. DURING ROUTINE FPI, QTY 45 LINEAR INDICATIONS WERE DETECTED ON THE FIR TREE ROOT PRESSURE FACES, WHICH APPEAR TO BE ASSOCIATED WITH CORROSION PITTING. THIS ISSUE HAS BEEN DETECTED ON OTHER HUBS AT THIS FACILITY, HOWEVER, IN THIS CASE THERE ARE NO INDICATIONS OF CRACKING. THE ITEM HAS BEEN REMOVED FROM SERVICE AND MFG HAVE BEEN CONTACTED FOR FURTHER INSTRUCTIONS REGARDING CAUSE INVESTIGATION.

2010FA0000690

 

LYC  

 

SPRING

BROKEN

6/7/2010

 

O320E2D

 

AE66112

PUSHROD

(WS9R) PUSH ROD RETAINING SPRING BROKE DURING ENGINE TEST CELL RUN. OBSERVED THAT THE PUSH ROD TUBE SEALS BEGAN LEAKING OIL, UPON REMOVAL OF THE ROCKER COVERS, DISCOVERED THAT (3) OUT OF (4) RETAINING SPRINGS WERE BROKEN. VERIFIED THAT THEY WERE INSTALLED CORRECTLY IAW THE O/H MANUAL. REPLACED ALL RETAINING SPRINGS, COMPLETED TEST CELL RUN WITH NO OTHER PROBLEMS.

LM1RRA0159

 

PWA  

 

TRANSFER TUBE

MISALIGNED

6/28/2010

 

PT6A68

 

3007867

AGB 

PRIOR TO INSTALLATION, CUSTOMER REPORTED STATIC OIL LEAK FROM ENGINE INLET. AGB REMOVED REVEALING A CUT O-RING AND DISTORTED PACKING GROOVE ON THE NR1 BEARING TRANSFER TUBE JOINING THE AGB DIAPHRAM AND AIR INLET HSG. LIKELY CAUSE WAS MISALIGNMENT OF TRANSFER TUBE DURING AGB MATING TO INLET ASSEMBLY. SDR SUBMITTED TO RAISE AWARENESS TO TECH ON POTENTIAL FOR MISALIGNMENT OF THE OIL TRANSFER TUBES DURING MATING PROCESS OF AGB AND AIR INLET SECTIONS, AND FOR OPERATORS TO RECOGNIZE THE SYMPTOMS THIS TYPE OF INTERNAL OIL LEAK.

2010F00138

AEROSP

 

 

SKIN

DENTED

6/28/2010

ATR72

 

 

S53571303204

ZONE 200

DENT BEYOND ALLOWABLE LIMITS. REGISTRATION,RESERVED AND IS PENDING, A/C PREVIOUSLY OPERATED UNDER N637AS BY ASA.

2010F00139

AEROSP

 

 

KEELBEAM

CORRODED

6/29/2010

ATR72212

 

 

S53574002210

ZONE 100

KEELBEAM LOWER PLATE/ SKIN HAS CORROSION ON BOTTOM BETWEEN SPECIAL STRINGERS. LEVEL II CORROSION, ORIGINAL MATERIAL .063", REMAINING MATERIAL IS 048", 21 PERCENT TOTAL MATERIAL LOSS.

2010F00140

AEROSP

 

 

ANGLE

CRACKED

6/30/2010

ATR72212

 

 

S53573203210

ZONE 200

INTERIOR FUSELAGE, LT WING PRESSURE DECK RE-ENFORCEMENT ANGLE AT STRINGER 4L IS CRACKED AFT OF FRAME 27. NOTE AC N807FX IS RESERVED REGISTRATION, AC FORMERLY N673AS.

2010FA0000665

AEROSP

 

 

ANGLE

CRACKED

6/30/2010

ATR72212

 

 

S53573203211

ZONE 200

INTERIOR FUSELAGE, RT WING PRESSURE DECK RE-ENFORCEMENT ANGLE AT STRINGER 4R IS CRACKED AFT OF FRAME 27. NOTE: AC N807FX IS IN RESERVED REGISTRATION, PREVIOUSLY N637AS.

2010F00147

AEROSP

 

 

CREASE BEAM

CORRODED

7/7/2010

ATR72212

 

 

S53575110209

ZONE 100

RT CREASE BEAM INNER CHORD AT FR 23A, CORRODED BEYOND SRM LIMITS. (LEVEL II)

2010FA0000702

AEROSP

 

 

SKIN PANEL

CORRODED

7/6/2010

ATR72212

 

 

 

ZONE 100

SKIN FWD OF FRAME 12 AT BL 0 RT SIDE OF BUTT SPLICE HAS CORROSION OUTSIDE OF SRM LIMITS. (LEVEL II)

2010FA0000703

AEROSP

 

 

FRAME

CORRODED

7/6/2010

ATR72212

 

 

S53575110201

ZONE 100

PITTING CORROSION ON RT CREASE BEAM WEB FRAME 23-23A. LEVEL II CORROSION.

2010F00144

AEROSP

 

 

CREASE BEAM

CORRODED

7/6/2010

ATR72212

 

 

S5307020820251

ZONE 100

LT CREASE BEAM INNER CORD AT FR 23 HAS CORROSION. (LEVEL II) PART NOT LISTED IN SRM. SRKM SHOWS PN S5307020820251 FOR RT SIDE ONLY. THERE IS NOT A SYMMETRICAL PART IN THE MANUALS FOR THE LT SIDE, BUT AC HAS ONE INSTALLED.

2010F00142

AEROSP

 

 

SEAT TRACK

CORRODED

7/6/2010

ATR72212

 

 

S53570203202

ZONE 100

RT OTBD SEAT TRACK BETWEEN FRAMES 23 AND 29 HAS LEVEL II CORROSION BEYOND ALLOWABLE SRM LIMITS.

2010F00146

AEROSP

 

 

SKIN

CORRODED

7/7/2010

ATR72212

 

 

11S53172202

ZONE 100

LONGITUDINAL BUTT SPLICE AT BL-0 FWD OF FRAME 13 HAS CORROSION OUT OF SRM LIMITS. (LEVEL II)

2010F00143

AEROSP

 

 

SEAT TRACK

CORRODED

7/6/2010

ATR72212

 

 

S53570203202

ZONE 100

LT OTBD SEAT TRACK BETWEEN FRAME 23 AND 29 HAS LEVEL II CORROSION BEYOND SRM LIMITS.

2010F00153

AEROSP

 

 

STRINGER

CORRODED

7/8/2010

ATR72212

 

 

S53571502206

ZONE 100

CORROSION FOUND ON STRINGER 19 LT BETWEEN FR 24- FR 25 BEYOND SRM LIMITS. (LEVEL II)

2010F00150

AEROSP

 

 

DOUBLER

CORRODED

7/8/2010

ATR72212

 

 

S53671400404

FUSELAGE SKIN

FUSELAGE SKIN (FACTORY DOUBLER) UNDER TAIL BUMPER AFT SEAL IS CORRODED. LEVEL II.

2010F00151

AEROSP

 

 

SKIN PANEL

CORRODED

7/8/2010

ATR72212

 

 

S57112322200

ZONE 600

REMOVABLE PANEL CUTOUT FOR PANEL 522CT IS CORRODED BEYOND SRM LIMITS. (LEVEL II)

2010FA0000707

AEROSP

 

 

CREASE BEAM

CORRODED

7/7/2010

ATR72212

 

 

S53373001200

ZONE 100

(COER) RT CREASE BEAM WEB BETWEEN FRAMES 22 AND 23 CORROSION OUTSIDE SRM LIMITS (LEVEL II).

2010FA0000708

AEROSP

 

 

CREASE BEAM

CORRODED

7/7/2010

ATR72212

 

 

S5307020820202

ZONE 100

(COER) RT CREASE BEAM INNER CHORD SPLICE (JOINT) CORROSION BEYOND SRM LIMITS (LEVEL II).

2010F00148

AEROSP

 

 

CREASE BEAM

CORRODED

7/7/2010

ATR72212

 

 

S53373000212

ZONE 100

RT INNER CREASE BEAM CORD BETWEEN FR 16-17 HAS CORROSION OUTSIDE SRM LIMITS. (LEVEL II)

2010F00149

AEROSP

 

 

STRINGER

CORRODED

7/7/2010

ATR72212

 

 

S53571502206

ZONE 100

(COER) CORROSION FOUND ON STRINGER 20LT BETWEEN FR 24- FR 25 BEYOND SRM LIMITS. (LEVEL II)

2010FA0000711

AEROSP

PWA  

 

SKIN PANEL

CORRODED

7/8/2010

ATR72212

PW120

 

S57112322200

ZONE 500

REMOVABLE PANEL CUTOUT FOR PANEL 521CT IS CORRODED BEYOND SRM LIMITS. (LEVEL II)

2010F00152

AEROSP

PWA  

 

SKIN

CORRODED

7/8/2010

ATR72212

PW120

 

S57112322201

ZONE 500

REMOVABLE PANEL CUTOUT FOR PANEL 622CT IS CORRODED BEYOND SRM LIMITS. (LEVEL II)

2010F00145

AEROSP

PWA  

 

SKIN PANEL

CORRODED

7/7/2010

ATR72212

PW120

 

S53571202200

ZONE 200

FUSELAGE SKIN UNDER UPPER ADF ANTENNA AT BL0 BETWEEN FR 28B AND 28C HAS AREAS OF CORROSION. (LEVEL II)

2010FA0000575

AIRBAU

ROTAX

 

OIL CAP

CRACKED

6/16/2010

XTC582

ROTAX582UL

 

 

ENGINE OIL

OIL INJECTION CAP CONTINUES TO CRACK AND LEAK OIL, MFG STATES THAT WE ARE PUTTING TO MUCH FORCE ON THE CAP WHILE INSTALLING. WE HAVE RUN ARE OWN TEST AND VERFIED THAT WE ARE NOT. IF WE INSTALL THE CAP WHERE MFG WOULD LIKE US TO, THEN IT WILL VIBRATE LOOSE IN FLIGHT. WHEN THE CAP CRACKS, IT DOES LEAK OIL. THE TANK SITS ABOVE THE EXHAUST MANIFOLD. THIS PROBLEM WILL CAUSE A FIRE ONE OF THESE DAYS ON THESE TYPES OF ACFT.

2010FA0000570

AIRBUS

 

 

PROFILE

CORRODED

6/15/2010

A320232

 

 

D5347047720600

FUSELAGE

CORROSION ON AFT CARGO COMPARTMENT LEFT SIDE PROFILE CORNER FR56-59. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R PROFILE CORNER IAW SRM 51-42-11. PROFILE CORNER IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000571

AIRBUS

 

 

PROFILE

CORRODED

6/15/2010

A320232

 

 

D5397467800700

FR47 STR 37-38 L

CORROSION ON AFT CARGO COMPARTMENT LT SIDE PROFILE FR47 STRINGER 37-38 LT. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000542

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/12/2010

A320232

 

 

D5311281300251

FUSELAGE

CORROSION ON FORWARD LAV FLOOR SUPPORT FR16 LBL33. CORROSION WAS FOUND TO BE OUT OF LIMITS IAW SRM 53-00-14 FIG 102. R & R SUPPORT IAW SRM 51-42-11. FLOOR SUPPORT IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000541

AIRBUS

 

 

FLOOR PANEL

CORRODED

6/12/2010

A320232

 

 

D5367303801000

ZONE 100

AFT CARGO COMPARTMENT FLOOR PANEL 161BF HAS SURFACE CORROSION. NO CORROSION REMOVAL LIMITS FOUND IN SRM. REPAIRED PANEL IAW SRM 53-02-00 FIG 207. FLOOR PANEL IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000543

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/12/2010

A320232

 

 

D11282600200

FUSELAGE

CORROSION ON FWD LAV FLOOR SUPPORT FR16 LBL22. CORROSION WAS FOUND TO BE OUT OF LIMITS IAW SRM 53-00-14 FIG. 102. R & R FLOOR SUPPORT IAW SRM 51-42-11. FLOOR SUPPORT IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000544

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/12/2010

A320232

 

 

D5347219820600

FUSELAGE

CORROSION ON LT AFT LAV FLOOR SUPPORT FR66 LBL37. CORROSION WAS FOUND TO BE OUT OF LIMITS IAW SRM 53-00-14 FIG. 102. R & R FLOOR SUPPORT IAW SRM 51-42-11. FLOOR SUPPORT IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000557

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/12/2010

A320232

 

 

D5347218320000

FUSELAGE

CORROSION ON RT CABIN FLOOR SUPPORT FR61 RBL35. CORROSION IS OUT OF LIMITS IAW SRM 53-00-14 FIG. 102. R & R FLOOR SUPPORT IAW SRM 51-42-11. FLOOR SUPPORT IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000556

AIRBUS

 

 

PROFILE

CORRODED

6/12/2010

A320232

 

 

D347048220001

FUSELAGE

CORROSION ON AFT CARGO COMPARTMENT RT SIDE PROFILE AT FR 58. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000558

AIRBUS

 

 

THRESHOLD

CORRODED

6/12/2010

A320232

 

 

D5347557520800

FUSELAGE

CORROSION ON THRESHOLD SHEET AFT CARGO DOOR CUTOUT AT FR54. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R THRESHOLD SHEET IAW SRM 51-42-11. THRESHOLD SHEET IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000617

AIRBUS

 

 

PROFILE

CORRODED

6/22/2010

A320232

 

 

D5397470600600

FUSELAGE

AFT CARGO COMPARTMENT FLOOR SUPPORT PROFILE HAS CORROSION SEVERAL AREAS FR56 RBL13 TO LBL27. NO CORROSION REMOVAL LIMITS FOUND IN SRM. REMOVED AND REPLACED PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000603

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/22/2010

A320232

 

 

D5347047400390

FUSELAGE

AFT CARGO COMPARTMENT FLOOR SUPPORT PROFILE HAS CORROSION FR47 - 48 RBL28. NO CORROSION LIMITS FOUND IN SRM. R & R PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000604

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/22/2010

A320232

 

 

D5347048112000

FUSELAGE

AFT CARGO COMPARTMENT FLOOR SUPPORT PROFILE HAS CORROSION FR48 - 52, RBL28. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000605

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/22/2010

A320232

 

 

D539747055000

FUSELAGE

AFT CARGO COMPARTMENT FLOOR SUPPORT PROFILE HAS CORROSION FR50 RBL48 TO LBL28. NO CORROSION REMOVAL LIMITS AVAILABLE IN SRM. R & R PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000618

AIRBUS

 

 

PLATE

CORRODED

6/22/2010

A320232

 

 

D5367009926000

FLOOR PANEL

CORROSION ON CABIN FLOOR PANEL CONNECTING PLATE FR66 LBL1. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R PLATE IAW AMM 20-21-11. PLATE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000619

AIRBUS

 

 

PLATE

CORRODED

6/22/2010

A320232

 

 

D5367009923600

FLOOR PANEL

CORROSION ON CABIN FLOOR PANEL CONNECTING PLATE FR68 RBL20. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R PLATE IAW AMM 20-21-11. PLATE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000607

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/22/2010

A320232

 

 

D5347048320200

FUSELAGE

AFT CARGO COMPARTMENT FLOOR SUPPORT PROFILE HAS CORROSION FR58 - 60 RBL28. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000608

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/22/2010

A320232

 

 

D5397470400300

FUSELAGE

AFT CARGO COMPARTMENT FLOOR SUPPORT PROFILE FR59 BL0 TO RBL28 HAS CORROSION. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000609

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/22/2010

A320232

 

 

D5397469110000

FUSELAGE

AFT CARGO COMPARTMENT FLOOR SUPPORT PROFILE FR58 RBL28 - LBL28 HAS CORROSION NO CORROSION LIMITS FOUND IN SRM. R & R PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000611

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/22/2010

A320232

 

 

D5347047520001

FUSELAGE

AFT CARGO COMPARTMENT FLOOR SUPPORT PROFILE HAS CORROSION NUMEROUS AREAS FR48 - 52 LBL28. NO CORROSION REMOVAL LIMITS IN SRM. R & R PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000610

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/22/2010

A320232

 

 

D5347047400290

FUSELAGE

AFT CARGO COMPARTMENT FLOOR SUPPORT PROFILE HAS FOUR AREAS OF CORROSION FR47- 48 LBL28. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000612

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/22/2010

A320232

 

 

D5347047720000

FUSELAGE

AFT CARGO COMPARTMENT FLOOR SUPPORT PROFILE HAS CORROSION FR56 - 58 LBL28 NUMEROUS AREAS. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000613

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/22/2010

A320232

 

 

D5347047820200

FUSELAGE

AFT CARGO COMPARTMENT FLOOR SUPPORT PROFILE HAS CORROSION NUMEROUS AREAS FR58 - 59 LBL28. NO CORROSION REMOVAL LIMITS FOUND IN SRM. REMOVED AND REPLACED PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000614

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/22/2010

A320232

 

 

D5347047920001

FUSELAGE

AFT CARGO COMPARTMENT FLOOR SUPPORT PROFILE HAS CORROSION NUMEROUS AREAS FR59 - 63 LBL28. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000615

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/22/2010

A320232

 

 

D5397470400200

FUSELAGE

AFT CARGO COMPARTMENT FLOOR SUPPORT PROFILE HAS CORROSION SEVERAL AREAS FR59 LBL2 - LBL27. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000616

AIRBUS

 

 

SUPPORT ANGLE

CRACKED

6/22/2010

A320232

 

 

D5323028120040

FUSELAGE

LT FORWARD WING TO BODY FAIRING SUPPORT ANGLE CRACKED FR34 LBL62. R & R ANGLE IAW SRM 51-42-11. ANGLE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000600

AIRBUS

 

 

SUPPORT ANGLE

CRACKED

6/22/2010

A320232

 

 

D5323028120300

FUSELAGE

RT FWD WING TO BODY FAIRING SUPPORT ANGLE CRACKED FR34 RBL62. R & R ANGLE IAW SRM 51-42-11.

2010FA0000560

AIRBUS

 

 

SHEAR PLATE

CORRODED

6/14/2010

A320232

 

 

D5347112420000

FUSELAGE

CORROSION ON CABIN FLOOR SHEAR PLATE BETWEEN FR69 AND FR70 LT SIDE. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R SHEAR PLATE IAW SRM 51-42-11. SHEAR PLATE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000559

AIRBUS

 

 

SHEAR PLATE

CORRODED

6/14/2010

A320232

 

 

D534711240100

FUSELAGE

CORROSION ON SHEAR PLATE BETWEEN FR69 AND FR70 RT SIDE CABIN FLOOR BELOW GALLEY. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R SHEAR PLATE IAW SRM 51-42-11. SHEAR PLATE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000561

AIRBUS

 

 

PLATE

CORRODED

6/14/2010

A320232

 

 

D5391160420000

FUSELAGE

FWD CARGO COMPARTMENT LOWER LT PROFILE PLATE CRACKED AT NUTPLATE HOLE FR29. R & R PROFILE PLATE IAW SRM 51-42-11. PROFILE PLATE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000562

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/14/2010

A320232

 

 

D5397747000600

FUSELAGE

CORROSION ON AFT CARGO COMPARTMENT FLOOR SUPPORT FITTING AT FR56 ABOVE STRINGER 44 LT. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R FITTING IAW SRM 51-42-11. FITTING IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000563

AIRBUS

 

 

PROFILE

CORRODED

6/14/2010

A320232

 

 

D5347047820200

FUSELAGE

CORROSION ON AFT CARGO COMPARTMENT LT SIDE PROFILE FR59+3" FWD END OF PROFILE. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000564

AIRBUS

 

 

PROFILE

CORRODED

6/14/2010

A320232

 

 

D5347047920001

FUSELAGE

CORROSION ON AFT CARGO COMPARTMENT LT SIDE PROFILE FR59+3" AFT END OF PROFILE. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000565

AIRBUS

 

 

FLOORBEAM

CORRODED

6/14/2010

A320232

 

 

D5347219320000

FUSELAGE

CORROSION ON AFT GALLEY FLOOR SUPPORT FR67 RBL31. CORROSION REMOVAL WAS OUT OF LIMITS IAW SRM 53-00-14, FIG 102. R & R FLOOR SUPPORT IAW SRM 51-42-11. FLOOR SUPPORT IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000566

AIRBUS

 

 

PROFILE

CORRODED

6/14/2010

A320232

 

 

D5397484000200

FUSELAGE

CORROSION ON AFT CARGO COMPARTMENT JOINT PROFILE TOP SURFACE AT FR56 LBL3 TO LBL24. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R PROFILE IAW SRM 51-72-11, 51-42-11, AND 51-49-00.

2010FA0000567

AIRBUS

 

 

SUPPORT

CRACKED

6/14/2010

A320232

 

 

D53230226200

FUSELAGE

RT FORWARD WING TO BODY FAIRING SUPPORT PLATE CRACKED APPROX .5" LONG AT FR34. R & R PLATE IAW SRM 53-25-11 AND 51-42-11. PLATE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000568

AIRBUS

 

 

PLATE

CRACKED

6/14/2010

A320232

 

 

D5323022620000

FUSELAGE

LT FWD WING TO BODY FAIRING SUPPORT PLATE CRACKED APPROX .5" AT FR34. R & R PLATE IAW SRM 51-72-11 AND 51-42-11. PLATE LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000539

AIRBUS

 

 

FLOOR PANEL

CORRODED

6/12/2010

A320232

 

 

D5367320300000

ZONE 100

AFT CARGO COMPARTMENT FLOOR PANEL 131HF HAS CORROSION ON SEVERAL AREAS. NO CORROSION REMOVAL LIMITS FOUND IN SRM. REPAIRED AFT CARGO COMPARTMENT FLOOR PANEL 131HF IAW SRM 53-02-00, FIG 207. PANEL IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000540

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/12/2010

A320232

 

 

D5311281300251

FUSELAGE

CORROSION ON FWD LAV FLOOR SUPPORT FR16 LBL54. CORROSION FOUND TO BE OUT OF LIMITS IAW SRM 53-11-14, FIG 102. R & R FORWARD LAV FLOOR SUPPORT IAW SRM 51-42-11. FLOOR SUPPORT IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000545

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/12/2010

A320232

 

 

D5347219420800

FUSELAGE

CORROSION ON LT AFT LAV FLOOR SUPPORT FR66 LBL21. CORROSION WAS FOUND TO BE OUT OF LIMITS IAW SRM 53-00-14 FIG 102. R & R FLOOR SUPPORT IAW SRM 51-42-11. FLOOR SUPPORT IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000546

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/12/2010

A320232

 

 

D5347209001100

FUSELAGE

CORROSION ON RT AFT LAV FLOOR SUPPORT FR66 RBL50. CORROSION WAS FOUND TO BE OUT OF LIMITS IAW SRM 53-00-14 FIG. 102. R & R FLOOR SUPPORT IAW SRM 51-42-11. FLOOR SUPPORT IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000547

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/12/2010

A320232

 

 

D53472196620000

FUSELAGE

CORROSION ON CABIN FLOOR SUPPORT FR66 LBL10. CORROSION WAS FOUND TO BE OUT OF LIMITS IAW SRM 53-00-14 FIG 102. R & R FLOOR SUPPORT IAW SRM 51-42-11. FLOOR SUPPORT IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000548

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/12/2010

A320232

 

 

D5347217220390

FUSELAGE

CORROSION ON CABIN FLOOR SUPPORT FR66+6" RBL50. CORROSION WAS FOUND TO BE OUT OF LIMITS IAW SRM 53-00-14, FIG 102. RT FLOOR SUPPORT IAW SRM 51-42-11. FLOOR SUPPORT IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000549

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/12/2010

A320232

 

 

D5347217320000

FUSELAGE

CORROSION ON AFT GALLEY FLOOR SUPPORT FR68+9" LBL6. CORROSION WAS FOUND TO BE OUT OF LIMITS IAW SRM 53-00-14 FIG. 102. REMOVED AND REPLACED FLOOR SUPPORT IAW SRM 51-42-11. FLOOR SUPPORT IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000550

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/12/2010

A320232

 

 

D5347219220000

FUSELAGE

CORROSION ON AFT GALLEY FLOOR SUPPORT FR68 LBL30. CORROSION WAS FOUND TO BE OUT OF LIMITS IAW SRM 53-00-14, FIG 102. R & R FLOOR SUPPORT IAW SRM 51-42-11. FLOOR SUPPORT IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000551

AIRBUS

 

 

PROFILE

CORRODED

6/12/2010

A320232

 

 

D5367468100000

FUSELAGE

CORROSION ON AFT CARGO COMPARTMENT FWD PROFILE BOTH CORNERS AT FR47. NO CORROSION REMOVAL LIMITS WERE FOUND IN SRM. R & R PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000552

AIRBUS

 

 

PROFILE

CORRODED

6/12/2010

A320232

 

 

D5347047520001

FUSELAGE

CORROSION ON AFT CARGO COMPARTMENT LT SIDE PROFILE FR48 TO FR52. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000553

AIRBUS

 

 

PROFILE

CORRODED

6/12/2010

A320232

 

 

D5347047400290

FUSELAGE

CORROSION ON AFT CARGO COMPARTMENT RT SIDE PROFILE FR48 TO FR52. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000554

AIRBUS

 

 

PROFILE

CORRODED

6/12/2010

A320232

 

 

D5347047400390

FUSELAGE

CORROSION ON AFT CARGO COMPARTMENT RT SIDE PROFILE AT FR47 TO FR48. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000555

AIRBUS

 

 

PROFILE

CORRODED

6/12/2010

A320232

 

 

D5347047620000

FUSELAGE

CORROSION ON AFT CARGO COMPARTMENT LT SIDE PROFILE FR52 TO FR56. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000656

AIRBUS

 

 

FLOOR PANEL

CORRODED

6/29/2010

A320232

 

 

D5367320400000

ZONE 100

AFT CARGO COMPARTMENT FLOOR PANEL 151AF HAS SEVERAL AREAS OF CORROSION ON UPPER SURFACE. NO CORROSION REMOVAL LIMITS FOUND IN SRM. PANEL IS LISTED AS PRIMARY STRUCTURE. FABRICATED NEW PANEL IAW SRM 53-02-00, FIG 209 AND MM MCG IRM 9701, REV F.

2010FA0000657

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/29/2010

A320232

 

 

D53470482200

CARGO BAY  

AFT CARGO COMPARTMENT FLOOR SUPPORT PROFILE HAS CORROSION FR56 - 58 RBL28. NO CORROSION REMOVAL LIMITS FOUND IN SRM. PROFILE IS LISTED AS PRIMARY STRUCTURE. REMOVED AND REPLACED PROFILE IAW A320 SRM 51-42-11.

2010FA0000658

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/29/2010

A320232

 

 

D5347047620000

CARGO BAY  

CORROSION ON AFT CARGO COMPARTMENT FLOOR SUPPORT PROFILE SEVERAL AREAS FR56 LBL28. NO CORROSION REMOVAL LIMITS FOUND IN SRM. PROFILE IS LISTED AS PRIMARY STRUCTURE. R & R PROFILE IAW SRM 51-42-11.

2010FA0000659

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/29/2010

A320232

 

 

D5397470600400

CAGO BAY  

AFT CARGO COMPARTMENT FLOOR SUPPORT PROFILE HAS CORROSION FR53, RBL28 TO LBL28. NO CORROSION REMOVAL LIMITS FOUND IN SRM. PROFILE IS LISTED AS PRIMARY STRUCTURE. R & R PROFILE IAW SRM 51-42-11.

2010FA0000660

AIRBUS

 

 

FLOOR PANEL

CORRODED

6/29/2010

A320232

 

 

D5367301900000

ZONE 100

AFT CARGO COMPARTMENT FLOOR PANEL 151BF CORRODED WITH DELAMINATION OF UPPER SKIN. PANEL IS LISTED AS PRIMARY STRUCTURE. FABRICATED REPLACEMENT FLOOR PANEL IAW SRM 53-02-00 FIG 209 AND MM MCG IRM 9701 REV F.

2010FA0000647

AIRBUS

 

 

FLOOR PANEL

DELAMINATED

6/29/2010

A320232

 

 

D5367303500100

ZONE 100

AFT CARGO COMPARTMENT FLOOR PANEL 152QF UPPER SKIN DELAMINATED. PANEL IS LISTED AS PRIMARY STRUCTURE. REPAIRED PANEL IAW SRM 53-02-00 FIG 207.

2010FA0000648

AIRBUS

 

 

FLOOR PANEL

CORRODED

6/29/2010

A320232

 

 

D5367303800800

ZONE 100

AFT CARGO COMPARTMENT FLOOR PANEL 162KF UPPER SURFACES CORRODED. NO CORROSION REMOVAL LIMITS FOUND IN SRM. PANEL IS LISTED AS PRIMARY STRUCTURE. REPAIRED PANEL IAW SRM 53-02-00 FIG 207.

2010FA0000655

AIRBUS

 

 

PROFILE

CRACKED

6/29/2010

A320232

 

 

D5391160020300

FUSELAGE

CRACKED PROFILE IN FWD CARGO COMPARTMENT AT FR31 - 33 RBL28 WAS R & R IAW SRM 51-42-11.

2010FA0000649

AIRBUS

 

 

PROFILE

CORRODED

6/29/2010

A320232

 

 

D5397468100000

FUSELAGE

CORROSION ON AFT CARGO COMPARTMENT PROFILE FR 47-4" STR 38, RT TO 38 LT. NO CORROSION REMOVAL LIMITS FOUND IN SRM. PROFILE IS LISTED AS PRIMARY STRUCTURE. R & R PROFILE IAW SRM 51-42-11.

2010FA0000653

AIRBUS

 

 

PROFILE

CRACKED

6/29/2010

A320232

 

 

D5391160020300

FUSELAGE

FWD CARGO COMPARTMENT RT SIDE PROFILE AT FR31 TO FR33 RBL28 CRACKED AT FASTENER HOLES. PROFILE IS LISTED AS PRIMARY STRUCTURE.

2010FA0000654

AIRBUS

 

 

PROFILE

CRACKED

6/29/2010

A320232

 

 

D5391160320000

FUSELAGE

FWD CARGO COMPARTMENT RT SIDE PROFILE CRACKED AT FR31 RBL28. PROFILE IS PRIMARY STRUCTURE. R & R PROFILE IAW SRM 51-42-11.

2010FA0000650

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/29/2010

A320232

 

 

D5347213220000

FUSELAGE

CORROSION ON UPPER SURFACE OF CABIN FLOOR SUPPORT FR67 - 68 LBL28. NO CORROSION REMOVAL LIMITS FOUND IN SRM. SUPPORT IS LISTED AS PRIMARY STRUCTURE. R & R SUPPORT IAW SRM 51-42-11.

2010FA0000645

AIRBUS

 

AIRBUS

PANEL

CRACKED

6/28/2010

A320232

 

 

D5757118

LT WING TE FLAP

LT WING OUTBD FLAP L/E PANEL NR 5 CRACKED 1.3" LONG, .300 " WIDE FROM EDGE TO DRAINHOLE. REPAIRED PANEL IAW EO REO - M0570.

2010FA0000651

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

6/29/2010

A320232

 

 

D5347219320000

FUSELAGE

CORROSION ON UPPER SURFACE OF CABIN FLOOR SUPPORT FR68 RBL28. NO CORROSION REMOVAL LIMITS FOUND IN SRM. SUPPORT IS LISTED AS PRIMARY STRUCTURE. R & R SUPPORT IAW SRM 51-42-11.

2010FA0000652

AIRBUS

 

 

WEB  

CORRODED

6/29/2010

A320232

 

 

D5347556521000

FUSELAGE

CORROSION ON AFT CARGO DOOR CUTOUT SILL WEB FR52 - 53. NO CORROSION REMOVAL LIMITS FOUND IN SRM. WEB IS LISTED AS PRIMARY STRUCTURE. R & R WEB IAW SRM 51-42-11.

2010FA0000622

AIRBUS

 

 

STRAP

CRACKED

6/23/2010

A320232

 

 

D5347081120200

FUSELAGE

AFT CARGO COMPARTMENT FLOOR STRUCTURE REINFORCING STRAP (CLIP) CRACKED FR57 LBL26 - 30. REMOVED, FABRICATED, AND INSTALLED CLIP IAW A320 SRM 51-42-11 AND DWG D53470811. CLIP IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000620

AIRBUS

 

 

SILL

CORRODED

6/23/2010

A320232

 

 

D5367213920000

ZONE 100

CORROSION ON AFT CARGO DOOR CUTOUT SILL PLATE. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R PLATE IAW SRM 51-42-11. PLATE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000602

AIRBUS

 

 

WEB  

CORRODED

6/22/2010

A320232

 

 

D534711242000

FUSELAGE

CORROSION ON CREASE WEB (SHEAR PLATE) FR69 - 70 LBL49. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R WEB IAW SRM 51-42-11. WEB IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000569

AIRBUS

 

 

PROFILE

CORRODED

6/15/2010

A320232

 

 

D5347047400290

FUSELAGE

CORROSION ON AFT CARGO COMPARTMENT LT SIDE PROFILE FR47-48. NO CORROSION REMOVAL LIMITS FOUND IN SRM. R & R PROFILE IAW SRM 51-42-11. PROFILE IS LISTED AS PRIMARY STRUCTURE BY THE MFG.

2010FA0000720

AIRBUS

 

 

FLOOR PANEL

DELAMINATED

7/12/2010

A320232

 

 

D5367175900000

AFT CABIN

AFT CABIN FLOOR PANEL 261EF UPPER SKIN DELAMINATED. INSTALLED NEW FLOOR PANEL PN D5367175900000. PANEL IS LISTED AS PRIMARY STRUCTURE.

2010FA0000713

AIRTRC

WALTER

 

ANGLE

CRACKED

6/17/2010

AT401

M601E11

 

 

 

THE CRACK DEVELOPED FROM THE TOP DOWN IN THE CORNER OF THE ANGLE FOR APPROX 1 INCH. IT HAS FLOWN FOR 91 HRS SINCE THE LAST INSP AT WHICH TIME NO CRACK WAS APPARENT. THE ACFT FLIES OUT OF A SMOOTH PAVED RUNWAY AND IS USED MOSTLY FRO GRANULAR FERTILIZER APPLICATION. THERE HASN`T BEEN ANY REPORT OF A HARD LANDING OR INCIDENT SO THE PROBABLE CAUSE IS FATIGUE. THE ACFT HAS BEEN CONVERTED TO THE TURBINE ENGINE WHICH HAS 751 SHP SO POSSIBLY THE EXTRA HORSE POWER HAS IMPOSED SOME STRESS. BELIEVE CRACK HAS BEEN CAUSED BY FATIGUE ONLY YET THE RATE AT WHICH IT PROGRESSED IS A CONCERN.

2010FA0000710

AMD  

GARRTT

 

WHEEL

BENT

7/8/2010

FALCON10

TFE73121C

 

50004042

NLG 

NOSE WHEEL AND TIRE SEPARATED FROM ACFT AFTER ROTATION AT APPROX 20 FEET IN AIR. PILOT HEARD A "THUD" AT ROTATION AND SUSPECT ENCOUNTER WITH FOD. WHEEL BENT ON ONE SIDE AND TIRE SIDEWALL HAD CORD SEPARATION DUE TO TIRE COMPRESSION.

2010F00124

AMD  

PWC  

 

PIN  

LOOSE

4/26/2010

FALCON2000

PW308C

 

PCB406JE

PUMP CONNECTOR

((JGVR)) INFORMED BY API OF AN INCIDENT REPORTED TO THEM BY THE ACFT OPERATOR. THE REPORT TELLS OF A LOOSE PIN IN THE CONNECTOR THAT RESULTED IN AN INTERMITTENT FAULT INDICATION FOR THE NR 1 HYD PUMP SYS. IT APPEARS THE NR 11 PIN HAD PUSHED BACK EVEN THOUGH IT WAS INSTALLED BY AN EXPERIENCED TECH USING CORRECT DWGS, TOOLS AND INSTRUCTIONS. THIS REPAIR STATION WILL ADD ADDITIONAL INSP, AND TRAINING TO ENSURE TECHS ARE AWARE OF THIS VULNERABLE SITUATION WITH "D SERIES" CONNECTORS.

2010FA0000531

AMTR

 

SNSNCH

ATTACH BOLT

SHEARED

6/11/2010

CUB  

 

 

AN8H53AS

PROP MOUNT

6 PROP BOLTS FAILED IN FLIGHT. PROPELLER SEPARATED FROM ACFT. ACFT WAS LANDED SAFELY.

2010FA0000722

AMTR

LYC  

 

AIR BOX

DEFECTIVE

7/12/2010

HATZVAN

O320*

 

 

AIR INTAKE

A MODIFIED BRACKET AIR FILTER ELEMENT DELAMINATED AND WAS SUCKED INTO THE CARBURATOR, BLOCKING THE AIR FLOW. THE AIR BOX HOLDING THE MODIFIED AIR FILTER ELEMENT DID NOT HAVE A SCREEN GUARDING THE ENTRANCE TO THE CARBURATOR AIR INTAKE DUCT AS IS COMMON ON CERTIFIED ACFT. THE ACFT OWNER MODIFIED THE DESIGN TO INCORPORATE A SCREEN TO PREVENT A REOCCURANCE AND INFORMED THE BIPLANE ASSOCIATION OF HIS FINDINGS AND RECOMENDATIONS.

2010FA0000695

AYRES

GARRTT

 

FCU  

WRONG PART

5/19/2010

S2RRESTD

TPE3311151A

 

 

ENGINE

(IZ2R) FUEL CONTROL UNIT FOUND INSTALLED (PN 893561-10, SN 1479489) IS INCORRECT FOR THIS ENGINE MODEL IAW MFG ILLUSTRATED PARTS CATALOG 72-00-91, REV 16.

2010FA0000696

AYRES

GARRTT

 

GOVERNOR

WRONG PART

5/19/2010

S2RRESTD

TPE3311151A

 

89361512

PROPELLER

(IZ2R) PROPELLER GOVERNOR FOUND INSTALLED IS INCORRECT FOR THIS ENGINE MODEL IAW MFG ILLUSTRATED PARTS CATALOG 72-00-91, REV 16.

2010FA0000698

AYRES

GARRTT

 

CONTROLLER

WRONG PART

5/19/2010

S2RRESTD

TPE3311151A

 

86913017

PROP PITCH

PROPELLER PITCH CONTROL FOUND INSTALLED IS INCORRECT FOR THIS ENGINE MODEL IAW MFG ILLUSTRATED PART CATALOG 72-00-91, REV 16.

2010FA0000697

AYRES

GARRTT

 

PLENUM

WRONG PART

5/19/2010

S2RRESTD

TPE3311151A

 

8939735

ENGINE

PLENUM CHAMBER FOUND INSTALLED IS INCORRECT FOR THIS ENGINE MODEL IAW MFG ILLUSTRATED PART CATALOG 72-00-91, REV 16.

2010FA0000699

AYRES

GARRTT

 

CAM  

MISMARKED

5/19/2010

S2RRESTD

TPE3311151A

 

86555815

PROP PITCH

(IZ2R) CAM ASSY FOUND INSTALLED IN THE PROPELLER PITCH CONTROL IS NOT MARKED CORRECTLY AS IT IS A "30 DEGREE" CAM AND NOT A "40 DEGREE" CAM AS THE PN WOULD INDICATE, ADDITIONALLY IT APPEARS TO HAVE BEEN "LOCALLY" MANUFACTURED.

2010FA0000723

BBAVIA

 

 

STRUT

DAMAGED

7/13/2010

7ECA

 

 

3665 

ZONE 700

DURING LANDING THE RT OLEO PN 3-665 SPRING AND SHAFT POPPED AND CAUSED OLEO TO OVSR EXTEND AND BEND REARWARD. THIS ALLOWED THE WHEEL AND BRACE TO COLLAPSE.

2010FA0000593

BEECH

PWA  

 

CIRCUIT BREAKER

TRIPPED

6/4/2010

200BEECH

PT6A41

 

507250101

NR 2 BUSS

((Q3ER)) NR 2 BUS FEEDER BREAKERS POPPED CAUSING LOSS OF GEAR DOWN AND LOCKED INDICATION. PILOT CHOSE TO MANUALLY EXTEND THE LANDING GEAR AND DECLARED EMERGENCY.

2010FA0000704

BEECH

 

 

STRINGER

CRACKED

7/7/2010

300BEECH

 

 

5044001410

ZONE 100

DURING COMPLIANCE WITH AD 2005-01-18/ SB 53-2472 R4 INSPECTION OF THE AFT STRINGER CRACKED. RT AND LT SIDE STRINGERS NR 8, 9 AND 10 WERE CRACKED. ORDERED KITS 101-4064-1S, 101-4064-2S, 101-4064-3S, 101-4064-4S, 101-4064-5S, AND 101-4064-11S TO MODIFY STRINGERS NR 5 TO NR 11 ON BOTH SIDES.

2010FA0000700

BEECH

 

 

DISPLAY

DEFECTIVE

7/3/2010

36BEECH

 

 

G500 

ZONE 100

THE MAGNETOMETER FAILED ON THE G500 PFD. THE ONLY RESULT WAS LOSS OF SYNTHETIC VISION AND WIND DIRECTION AND VELOCITY.

2010FA0000691

BEECH

CONT

 

ELECTRONIC UNIT

FAILED

4/25/2010

36BEECH

IO550A

 

EDM930

COCKPIT

IN APRIL TOOK DELIVERY OF MY ACFT WHICH HAD JUST UNDERGONE EXTENSIVE UPGRADES INCLUDING NEW O/H ENGINE, 3 BLADE PROP, TURBO NORMALIZING SYS, AND GLASS PANEL WITH G500 AND EDM 930. FOLLOWING NORMAL INDICATIONS AT RUNUP, ON TAKEOFF THE RPM INDICATION ON THE EDM 930 WAS OBSERVED TO GO BLANK ALTHOUGH NO CHANGE IN ENGINE PERFORMANCE HAD OCCURRED. SHORTLY AFTER CLIMBOUT, THE DISPLAY RETURNED TO NORMAL WITHOUT OTHER ACTIONS. ON 2 SUBSEQUENT OCCASIONS AFTER STARTING THE ENGINE, THE RPM DISPLAY WAS AGAIN BLANK FOR A MINUTE OR 2 WHILE THE REST OF THE INDICATIONS WERE NORMAL. CONNECTION TO THE MAGS WERE CHECKED AND NO DISCREPANCIES FOUND.

2010FA0000581

BEECH

CONT

BEECH

RIB  

CRACKED

5/17/2010

58  

IO520*

 

3516505084

LT WING

((OF1R)) DURING AN INSP, PRIOR TO PURCHASE, THE LT FLAP NOSE RIB WAS FOUND CRACKED THROUGH THE L/E RELIEF CUTOUT, IN THE UPPER FLANGE BEND RADIUS, AND THROUGH THE ACTUATOR ATTACH BRACKET NUTPLATE RIVET HOLES. THIS IS A VERY DIFFICULT AREA TO ACCESS AND INSPECT. AN ADDITIONAL SWALL OPENING IN THE BOTTOM FLAP SKIN WOULD BE ADVISABLE FOR INSPECTING THIS AREA. SUSPECT THIS SITUATION IS CAUSED BY FLAPS BEING EXTENDED AT HIGHER THAN DESIGNED AIRSPEEDS OR INCORRECT UP STOP BUMPER RIGGING. RESEARCHED AND FOUND NO MFG SERVICE INFO ADDRESSING THIS FOR SUCH A COMMON FAILURE ITEM.

2010FA0000709

BEECH

CONT

 

GYRO

CONTAMINATED

7/8/2010

58  

IO550*

 

 

INSTRUMENT PNL

WATER IS ENTERING THE INSTRUMENT AIR SYS AND CAUSING CORROSION OF THE SYS COMPONENTS. A HIGHER THAN ACCEPTABLE GYRO FAILURE HAS PROMPTED OUR MX STAFF TO PROBE INTO THE CAUSES OF THIS ISSUE. UPON OPENING THE INSTRUMENT AIR PRESSURE REGULATOR, AND MANIFOLD/CHECK VALVE ASSY FOR INSP, HEAVY CORROSION OF FERROUS COMPONENTS WAS NOTED. LARGE PARTICLES OF RUST ARE BREAKING LOOSE FROM THE FITTINGS AND OTHER STEAL PIECES IN THE SYS AND CONTAMINATING INSTRUMENTS. RECOMMEND THAT MFG DEVELOPE A SB OR KIT TO ALLOW FOR AN INLINE FILTER TO BE INSTALLED AFTER THE INSTRUMENT AIR REGULATOR BUT BEFORE THE AIR ENTERS INSTRUMENTS.

2010FA0000750

BEECH

CONT

 

TUBE

CHAFED

6/25/2010

58  

IO550C

 

6494061

DIPSTICK

DURING ROUTINE OIL CHANGE, A PUDDLE OF OIL WAS OBSERVED IN BOTTOM OF COWLING. NO OIL SPILLED WHILE FILLING CRANKCASE & HAVING SEEN THIS PROBLEM SEVERAL TIMES, MECH IMMEDIATELY LOOKED AT DIPSTICK TUBE IN CHAFED AREA. ALL PREVIOUS SITUATIONS, HOLE IS LOCATED AT FIRST INSIDE BEND BELOW FILLER OPENING. OEM SAYS THEY ARE NOT AWARE OF THE PROBLEM, MOST OF OUR IN-SERVICE ENGINES SHOW SOME SIGN OF CHAFING WHICH CAN BE OBSERVED BY LOOKING DOWN THE OIL FILL OPENING ON THE CRANKCASE SIDE OF TUBE. ONCE THE DIPSTICK IS IN PLACE, IT TENDS TO FILL THE CHAFED OPENING AND VERY LITTLE OIL CAN ESCAPE THROUGH THE HOLE. OEM COULD RESOLVE THIS ISSUE BY USING A ROUND DIPSTICK OR BREAKING THE SHARP EDGE ON CURRENT PRODUCTION UNIT.

2010FA0000590

BEECH

CONT

 

LIFTER

SPALLED

5/11/2010

58  

IO550C

 

653877BW

NR 1 CYLINDER

AFTER REMOVING NR 2 CYL FOR REPAIR, INSPECTED VISIBLE INTERNAL ENGINE COMPONENTS FOR CONDITION. FOUND VISIBLE DAMAGE ON FACE OF NR 1 CYL EXHAUST LIFTER. NO DAMAGE TO CAMSHAFT WAS NOTED.

2010FA0000580

BEECH

CONT

 

RIB  

CRACKED

5/17/2010

A36  

IO520BA

 

3516505084

RT WING

((OF1R)) DURING AN ANNUAL INSP, 1 RT FLAP NOSE RIB WAS FOUND CRACKED. IT IS THE RIB LOCATED DIRECTLY BENEATH THE ACTUATOR ATTACH BRACKET. IT WAS CRACKED IN THE RELIEF CUTOUT FOR THE FLANGES AND THROUGH THE MOST FWD NUTPLATE RIVET HOLES. VERY INACCESSABLE AREA TO INSPECT. YOU MUST BE LOOKING AT THIS RIB WITH THE FLANGES FACING YU TO DETECT CRACKS UNTIL THEY BECOME VERY LARGE. RECOMMEND MAKING AN ADDITIONAL ACCESS HOLE OR USING A BOROSCOPE FOR THIS INSPECTION.

2010FA0000538

BEECH

CONT

BEECH

RIB  

CRACKED

5/17/2010

A36  

IO520BA

 

3516505084

FLAP NOSE RIB

DURING AN ANNUAL INSP, (1) NOSE RIB WAS FOUND CRACKED IN THE RT FLAP. IT IS THE RIB LOCATED DIRECTLY BENEATH THE ATTACH BRACKET MOUNTED ON THE SKIN.

2010FA0000582

BEECH

CONT

 

RIB  

CRACKED

5/17/2010

A36  

IO520BB

 

3516505084

RT WING

((OF1R)) DURING AN ANNUAL INSP, THE RT FLAP RIB WAS FOUND CRACKED THROUGH THE L/E RELIEF CUTOUT, IN THE UPPER FANGE BEND RADIUS, AND THROUGH THE ACTUATOR ATTACH BRACKET NUTPLATE RIVET HOLES. THIS COULD ONLY BE VIEWED THROUGH THE INBD ROLLER BOLT ACCESS HOLE. THE CRACKS HAD ALMOST INTERSECTED EACH OTHER, WHICH WOULD LEAVE THE ATTACH BRACKET BEING LEFT ONLY HELD ON BY THE SCREWS THRUGH THE TOP FLAP SKIN. FAILURE WHILE BOARDING ACT OR SPLIT FLAP SITUATION IN FLIGHT WAS IMMENENT. SUSPECT THIS SITUATION IS CAUSED BY FLAPS BEING EXTENDED IN HIGHER THAN DESIGN AIRLOADS, INCORRECT UP STOP BUMPER RIGGING AND STEPPING ON FLAP WHILE BOARDING, ALTHOUGH LT FLAPS CRACKED ALSO.

2010FA0000637

BEECH

CONT

 

HOSE

LEAKING

6/24/2010

A36  

IO550*

 

330995F40060

FUEL SYSTEM

DURING ANNUAL INSPECTION, NOTICED A POSSIBLE FLASH FIRE IN ENGINE COMPARTMENT. AFTER FURTHER INSP, FOUND FUEL HOSE (330995F-0060 FROM FUEL FLOW SENSOR TO FUEL SPIDER HAD BEEN LEAKING. REMOVED FUEL HOSE AND PRESSURIZED LINE WITH AIR AND FOUND HOSE LEAKING THROUGH OUT ENTIRE HOSE LENGTH. THE FUEL HOSE SHOULD BE INSPECTED AT ANNUAL AND 100 HOURS INSP.

2010FA0000715

BEECH

CONT

 

CYLINDER

LEAKING

6/15/2010

A36  

IO550B

 

SA52006A23P

ENGINE

DURING A ROUTINE 100 HR INSP, A CYLINDER COMPRESSION TEST WAS PERFORMED ON THE ENGINE USING SOAP SOLUTION FOR VISUAL INSPECTION AND DURING THAT CHECK IT WAS FOUND THAT THE NR 4 CYLINDER (SN 4857) AND NR 6 CYLINDER (SN 4864) WERE LEAKING OUT OF THE SIDES OF THE CYLINDER HEADS BETWEEN FINS ON THE EXHAUST SIDE. THE ENGINE WAS APPROACHING TBO AND INSTEAD OF CHANGING CYLINDERS IT WAS DECIDED THAT IT WOULD MAKE MOST SENSE TO CHANGE ENGINE. BOTH NR4 AND NR6 CYLINDERS, PN SA52006-A23P.

2010FA0000717

BEECH

LYC  

 

KEELBEAM

CRACKED

6/14/2010

B19  

O320*

 

169400005471

FUSELAGE

( EL8S) THE RT INBD KEEL PN 169-40005-471 IS CRACKED BETWEEN FUSELAGE STATIONS 68 AND 94 AT THE POINT WHERE THE AFT ATTACHMENT BOLT FOR THE RT INBD RUDDER BAR SUPPORT PENETRATES THE FLANGE OF THE KEEL. THIS LOCATION IS JUST ABOVE THE ELECTREIC FUEL PUMP. THIS IS THE 4TH ACFT IN OUR FLEET FOUND WITH THIS CONDITION. TT ON THE ACFT RANGED FROM 13,702 HRS TO 14,506 HRS.

HSRR13038

BEECH

PWA  

 

TUBE

SPLIT  

6/25/2010

B200

PT6A42

 

132538A19

BLEED AIR

BLEED AIR FAIL WARNING LIGHT CAME ON IN FLIGHT. FOUND BLEED TUBE SPLIT.

2010FA0000601

BEECH

 

 

RELAY

INTERMITTENT

6/16/2010

B300

 

 

SM50D07

TE FLAPS

OWNER REPORTED THE FLAP SYS TO BE INTERMITTENT WHEN THE FLAPS SELECTED TO DOWN POSITION. OPERATED THE FLAP SYS IN THE HANGER AND VERIFIED THE INTERMITTENT FLAPS. FOUND THE FLAP MOTOR CONTROL RELAY TO BE CAUSING THE INTERMITTENT PROBLEM. AFTER REMOVAL OF THE FLAP RELAY FOR REPLACEMENT, NOTICED THE RELAY WIRE CONTENTIONS WERE JUST CRIMPED THROUGH THE EYES AND NOT SOLDERED. NOTE: PART TOTAL TIME NOT PROVIDED BY CUSTOMER.

2010FA0000724

BEECH

 

 

FLEX HOSE

BROKEN

7/13/2010

C90  

 

 

9091010017

RT ENG ANTI ICE

RIGHT ENGINE INLET ANTI/DE-ICE FLEX HOSE AT RT MANIFOLD WAS BROKEN AT FLANGE FITTING.

2010FA0000644

BEECH

CONT

 

RELAY

FAILED

6/27/2010

F33A

IO520BB

 

SM50D7

MLG 

PILOT REPORTED AFTER PUTTING THE GEAR SELECTOR IN THE DOWN POSITION THE GEAR WOULDN’T EXTEND, PILOT CRANKED THE GEAR DOWN AND RETURNED TO BASE. ON TROUBLESHOOTING THE MECHANIC FOUND RELAY FAILED INTERNALLY, 384 FLIGHT HOURS, ESTIMATED CYCLES 1536. PROBABLE CAUSE AT THIS TIME UNKNOWN.

2010FA0000577

BEECH

CONT

 

CYLINDER

CRACKED

6/17/2010

F33A

IO550B

 

655469A8

ENGINE

THE NR 6 CYLINDER BARREL CRACKED 2.5 INCHES UP THE BARREL FROM THE FACE OF THE MOUNTING FLANGE. CRACKED EXTENDED APPROX 330 DEG AROUND THE CIRCUMFERENCE OF THE BARREL. BARREL EXHIBITS HEAT DAMAGE ON THE BARREL IN LINE WITH THE PISTON PIN AND THE PISTON PIN HAS SEVER WEAR ON THE PIN PLUGS. ROD BUSHING WAS BEYOND LIMITS ON THE PISTON PIN. INDICATIONS STARTED AS AN OIL LEAK AND THE PILOT WAS ABLE TO LAND ON AN AIRPORT SAFELY UNDER POWER.

2010FA0000661

BEECH

CONT

CONT

GASKET

FAILED

5/17/2010

P35  

IO470N

 

649964

OIL COOLER

OIL COOLER GASKET FAILED.

2010FA0000638

BEECH

 

 

WIRE

SHORTED

6/24/2010

V35B

 

 

P64A18

ALTERNATOR

ACFT LOST ELECTRICAL POWER IN FLIGHT AND COULD NOT RESET THE ALTERNATOR SWITCH. AFTER INSPECTION, FOUND ALTERNATOR FIELD WIRE TO THE VOLTAGE REGULATOR (P64A18) HAD CRACKED IN SEVERAL LOCATIONS IN THE ENGINE COMPARTMENT AND THE SHIELDING SHORTED OUT THE VOLTAGE REGULATOR. ALTERNATOR WIRES SHOULD BE INSPECTED CLOSELY AT ANNUAL OR 100 HR INSPECTIONS.

2010FA0000639

BELL  

 

 

SPAR

UNSERVICEABLE

6/15/2010

206B

 

 

 

M/R BLADE

((QR9R)) MAIN ROTOR BLADE MID SPAR WEIGHT CAME LOOSE DURING OPERATION CAUSING THE WEIGHT TO BLOW OUT THE END CAP. DEFECT WAS NOTICED ON POST FLIGHT INSP. PILOT DID NOT REPORT ANY UNUSUAL VIBRATIONS. THIS IS NOT THE FIRST BLADE THAT THE MID WEIGHT HAS COME LOOSE AT THIS FACILITY. THE REMAINING TIME LEFT ON THIS BLADE WAS 764 HOURS BEFORE REPLACEMENT WAS DUE. MFG HAS REQUESTED THAT THE ARMY SEND THE BLADE TO THEM FOR EVALUATION.

2010F00136

BELL  

ALLSN

 

GEARBOX

FAILED

6/28/2010

206L1

250C30P

 

23053349

ENGINE

DURING CRUISE FLIGHT TO OFFSHORE PLATFORM, PILOT NOTICED TORQUE INDICATOR FLUCTUATIONS, WITH NO ASSOCIATED ENGINE SURGING OR FLUCTUATIONS. LANDING TO PLATFORM WAS NORMAL. TROUBLESHOOTING REVEALED TORQUE OUTPUT WITHIN ENGINE GEARBOX HAD FAILED. ENGINE GEARBOX WAS CHANGED AT PLATFORM LOCATION. ALL ENGINE PARAMETERS WERE NORMAL AFTER GEARBOX CHANGE. ACFT WAS RETURNED TO SERVICE.

2010F00141

BELL  

ALLSN

 

BLADE

DEBONDED

7/4/2010

407  

250C47B

 

407015001117FM1

MAIN ROTOR

LOWER MAIN ROTOR BLADES SKIN DELAMINATION FROM BLADE STATION 196 TO BLADE STATION 210.

CHIR06112010001

BOEING

 

 

QUILL SHAFT

CRACKED

6/11/2010

107*

 

 

107D20671

M/R TRANSMISSION

(CHIR) DURING COMPLIANCE WITH SB 107-63-1005, FOUND THAT THE QUILL SHAFT HAD A VERY SMALL CRACK COMING FROM THE AREA AROUND THE PIN HOLE. THE QUILL SHAFT HAS A TT OF 325.6 HRS. THE SN IS KA0369 AND IT IS ON WO 126921. THE AD NR THAT IS ESTABLISHED FOR THIS PART IS 2005-24-05. THE CRACK WAS FOUND DURING THE PRELIMINARY INSPECTION PROCESS AND THEN VERIFIED BY THE NDT SHOP.

EE4Y100235

BOEING

 

 

FRAME

CRACKED

7/1/2010

7372X6C

 

 

 

ZONE 200

UPPER FUSELAGE MAIN CARGO CABIN AT BS 986.5 BETWEEN STR 2L AND 3L, FUSELAGE FRAME WITH CRACK.

EE4Y100233

BOEING

 

 

SKIN

GOUGED

6/18/2010

7372X6C

 

 

 

ZONE 100

LOWER AFT FUSELAGE INTERNAL SECTION AT BS 1003 BETWEEN STRINGERS 20 AND 21 RT FUSELAGE SKIN WITH GOUGE.

EE4Y100232

BOEING

 

 

SKIN

BULGED

6/17/2010

7372X6C

 

 

 

RT WING

RT WING TRAILING EDGE SECTION NR 6 FLAP TRACK FAIRING O/B LATERAL STEEL STRAP WITH BULGED SKIN AND WEAR.

EE4Y100236

BOEING

 

 

STRINGER

CORRODED

7/1/2010

7372X6C

 

 

 

ZONE 100

LOWER FUSELAGE E&E COMPARTMENT FROM BS 344 TO BS 360 STR 25LT WITH CORROSION.

EE4Y100237

BOEING

 

 

STRINGER

CORRODED

7/1/2010

7372X6C

 

 

 

ZONE 100

LOWER FUSELAGE AFT SECTION AT BS 977 STR 20LT WITH CORROSION.

EE4Y100238

BOEING

 

 

BEAM

CORRODED

7/1/2010

7372X6C

 

 

 

HORIZONTAL STAB

EMPENNAGE RT HORIZONTAL STABILIZER UPPER T/E BEAM WITH CORROSION AT ELEV STA 94.27, 213.32.

WGFY2010FA0000496

BOEING

 

 

STRINGER

CORRODED

6/30/2010

7472F6B

 

 

BAC1498147

ZONE 100

STRINGER 43 LT WAS CORROSION STA 960-1000 AT BELOW FWD CARGO AREA. REPAIR CLASSIFICATION FOR SRM REPAIR: CAT 'B', REPETITIVE INSP SRM 53-10-03 FIG 1, SHEET 6, TABLE IV. SRM 51-10-06, 51-21-00, 53-10-03 FIG 1, 51-10-02. REPAIR REPETITIVE INSPECTION REQUIREMENT IAW SRM 53-10-03 FIG 1 SHEET 6 TABLE IV , EXT VISUAL 3000 FC, INT : 6000 FC.

WGFY2010FA0000494

BOEING

 

 

STIFFENER

CRACKED

6/30/2010

7472F6B

 

 

65B941004

ZONE 400

PYLON NR1 STIFFENER NR3 BETWEEN NAC STA 234-259 WAS CRACK +/- 25MM. PERFORMED A DETAIL VISUAL REPEAT INSPECTION OF SUBJECT REPAIR AREA AT THE INSPECTION INTERVAL SPECIFICATION IN THE SB 747-54-2223 TO ENSURE ABSENCE OF ANY ADDITIONAL HEAT DAMAGE, LOOSE FASTENER, CORROSION AND CRACKS.

WGFY2010FA0000493

BOEING

 

 

SKIN

CORRODED

6/30/2010

7472F6B

 

 

 

NR 3 PYLON

PYLON NR 3 UPPER DSB LOWER WING SKIN WAS CORROSION LEVEL 2.

WGFY2010FA0000489

BOEING

 

 

SKIN

CORRODED

6/30/2010

7472F6B

 

 

 

ZONE 600

(WGFY) PYLON NR 4 UPPER DSB LOWER WING SKIN WAS CORROSION LEVEL 2, REFER TO JOB CARDS NR 54-812-01-04. MFG MESSAGE: YDK-SOF-10-0011-04B/18 MAY 2010, YDK-SOF-10-0011-09B/03 JUNE 2010, YDK-SOF-10-0011-11B/05JUNE 2010. PERFORM REPEAT DVI INSPECTION OF THE SUBJECT AREA IAW SB 747 54A2182 R2, REQUIREMENT AT 1200 FC INTERVAL NOT TO EXCEED 24 MONTHS.

WGFY2010FA0000488

BOEING

GE  

 

SKIN

CORRODED

6/29/2010

7472F6B

CF650*

 

 

LT WING

PYLON NR2 LT WING LOWER FRONT SPAR LOWER WING SKIN WBL 470 WAS CORRODED LEVEL 2,

2010FA0000606

BOEING

GE  

 

FLAP SYSTEM

SEPARATED

5/17/2010

74747UF

CF680

 

65B02025134G

TE FLAPS

((F8ER)) ON APPROACH, THE RT INBD, FORE FLAP, OTBD SECTION SEPARATED FROM THE ACFT, STRIKING THE RT SIDE OF FUSELAGE AND PUNCTURING SEVERAL AREAS OF EXTERIOR SKIN CAUSING DAMAGE TO SEVERAL FUSELAGE FRAMES AND STRINGERS IN FUSELAGE SECTIOON 46 WITH DAMAGE BEING CONTAINED WITHIN THE APPROX AREAS OF B.S.1640 TO 1660 BETWEEN STRINGERS R19 AND R28. CAUSE OF INCIDENT IS UNKNOWN AND IS CURRENTLY UNDER INVESTIGATION. ACFT LANDED SAFELY WITHOUT FURTHER INCIDENT.

Z6WR0032010

BOEING

 

BOEING

SKIN

DAMAGED

6/15/2010

777268

 

 

315W117625

THRUST REVERSER

THE 315W1176-25 AFT COWL SKIN HAS AN AREA OF DISCOLORATION, POSSIBLE OVERHEAT CENTERED 5.0 INCHES FROM THE AFT EDGE OF THE SKIN AND 4.25 INCHES FROM THE LOWER EDGE OF THE SKIN. THE DISCOLORATION MEASURES 2.5" X 1.5". HEAT DAMAGE ANALYSIS PER SRM 51-20-03 REVEALED THE FOLLOWING, DEFECT: CONDUCTIVITY AND HARDNESS OUT OF RANGE. MATERIAL: 2024-T62 ALUMINUM. ACTUAL CONDUCTIVITY (MAX OF 35 READINGS): 42.3 % IACS (17" FROM AFT EOP; 19" FROM UPPER EOP). IDEAL CONDUCTIVITY: 36.0--40.0 % IACS. ACTUAL HARDNESS (MAX OF 5 READINGS): 66.0 HRB (2 INCHES FROM THE AFT EOP; 18.5 INCHES FROM UPPER EOP). IDEAL HARDNESS: 72.0--86.0 HRB. LOCATION: ENTIRE AFT COWL SKIN. TOTAL MEASUREMENTS: 35 CONDUCTIVITY READINGS; MAX, 42.3 % IACS; MIN, 40.3 % IACS; MEDIAN, 41.00 % IACS; MODE, 40.90 % IACS; MEAN, 41.28 % IACS; STD DEV, 0.86 % IACS.

2010FA0000694

BOEING

GE  

 

SEAL

UNSERVICEABLE

6/7/2010

777268

GE9090B

 

1847M94P03

HP TURBINE

(QEMY) DURING DISASSEMBLY OF THE HP TURBINE MODULE, THE HPT FORWARD ROTATING SEAL WAS FOUND WITH LONG CRACK RUNNING RADIALLY ACROSS FRONT FACE OF SEAL. CRACK APPROX (5")LONG. OEM HAS BEEN INFORMED.

2010FA0000693

BOEING

GE  

 

SEAL

CRACKED

6/7/2010

777268

GE9090B

 

1847M94P03

HPT 

(QEMY) DURING O/H OF THE HPT FORWARD SEAL, 2OF CRACKS NOTED ON WEBB SECTION. BOTH CRACKS RUN IN A RADIAL DIRECTION. THE LONGEST OF THE TWO CRACKS IS 0.350" LONG AND HAD PENETRATED FULL WALL SECTION. THE OTHER CRACK WAS 0.125" LONG, AND HAD NOT PENETRATED THE WALL SECTION. OEM HAS BEEN INFORMED.

AMCR201006

BOMBDR

 

 

TIRE

BULGED

6/21/2010

BD1001A10

 

 

269K431

ZONE 700

(AMCR) AFTER LANDING AT DESTINATION, CREW PERFORMED PRECAUTIONARY CHECK ON TIRES AND FOUND THE NR 3 TIRE BULGED IN (2) SPOTS. BULGES WERE ON SAME SIDE OF TIRE AND IN SAME POSITION, WHICH WAS ON SIDEWALL JUST BELOW THE TREAD CAP. BULGES WERE ABOUT 150 DEG APART. ONE WAS LARGE, ABOUT SIZE OF AN EGG, AND THE OTHER WAS MUCH SMALLER, ABOUT SIZE OF A MARBLE. THIS ACFT JUST EXPERIENCED A BULGED TIRE 2 WEEKS PRIOR ON THE NR2 POSITION. REMOVING ALL PN 269K43-1 AND UPGRADING TO THE -2'S.

2010FA0000729

CASA

 

 

ATTACH FITTING

CRACKED

7/15/2010

C212CC

 

 

2122415XX

HORIZONTAL STAB

3 EA, FUSELAGE SIDE, HORIZ STABILIZER ATTACH FITTINGS WERE FOUND TO BE CRACKED AND 3 OTHERS WERE FOUND WITH INTERGRANULAR CORROSION. 6 OF THE 8 ARE BEYOND LIMITS. ONE OF THE FITTINGS THAT SHOWED NO SIGNS OF CRACKS OR CORROSION WAS REMOVED AND FOUND TO BE BADLY CRACKED.

2010FA0000712

CESSNA

 

 

TRANSMITTER

BROKEN

6/25/2010

152  

 

 

C6680020301

FUEL SYSTEM

(LW5R) RT FUEL TRANSMITTER WAS INSTALLED 11/5/1997 AS AN O/H REPLACEMENT UNIT. ACFT TT 4434.1 HRS. RT FUEL TRANSMITTER CEASED OPERATION IN FLIGHT AND INDICATED ZERO FUEL IN EARLY JUNE 2010 AT AN ACFT TT OF 9319.8 HRS. TRANSMITTER WAS REMOVED AFTER LANDING AND WAS FOUND TO BE MISSING IT`S FLOAT. THE FOAM TYPE FLOAT WAS RECOVERED FROM THE RT FUEL TANK AND APPEARED TO HAVE BROKEN IN HALF ALLOWING THE TRANSMITTER ARM TO FALL FREE OF THE FLOAT AND SINK. THE LT TRANSMITTER WAS ALSO REMOVED AND SHOWED DETERIORATION AROUND THE EDGES OF THE FOAM FLOAT. BOTH UNITS WERE SUBSEQUENTLY REPLACED WITH O/H UIT PN C668002-0301.

ZB0R201000004

CESSNA

 

 

CALIPER

CRACKED

6/23/2010

152  

 

 

06114100

MLG 

DURING 100 HOUR INSPECTION, FOUND BOTH BRAKE CALIPERS CRACKED AT TOP MOUNT BOLT HOLE. SUSPECT BOLT OVER-TORQUE AS CAUSE.

W59R30027

CESSNA

LYC  

 

PROPELLER

CRACKED

7/1/2010

152  

O235L2C

 

1A103TCM

 

(W59R) PROPELLER SUBMITTED FOR INSPECTION AND COMPLIANCE WITH AD 10-04-05. PROPELLER WAS CRACKED ALONG L/E BOLT HOLES BEYOND REPAIR LIMITS.

2010FA0000662

CESSNA

LYC  

 

CRANKSHAFT

BROKEN

6/29/2010

152  

O235L2C

 

 

ENGINE

CRANKSHAFT BROKEN IN HALF IN FLIGHT , LARGE HOLE BROKEN IN CASE. NR 4 CYCLE THROWN AFT ABOUT 1 INCH. CYLINDER BASE STUDS STILL ON NR 4 CYL. O/H W/O 31830.

ZB0R201000003

CESSNA

LYC  

 

STARTER

BURNED OUT

6/16/2010

152  

O235N2C

 

122NL

ENGINE

DURING ENGINE START, PILOT NOTICED STARTER WOULD NOT ENGAGE FLYWHEEL. ACFT REPORTED TO MX WHERE IT WAS DISCOVERED THE STARTER MOTOR WAS INOPERATIVE. STARTER WAS REMOVED AND INSPECTION REVEALED THE MOTOR AREA HAS 2 SPOTS BURNED THROUGH THE CASING. THIS IS THE 2ND OCCURANCE OF THIS PROBLEM IN THE PAST 12 MONTHS DISCOVERED BY THIS MX SHOP. THE STARTER WAS REPLACED AND OPS CK OK.

2010FA0000584

CESSNA

LYC  

 

MOUNT

DAMAGED

4/19/2010

172K

O320E2D

 

05510171

LT ENGINE

UPON ROUTINE INSP, CRACK WAS FOUND ON LOWER LT ENGINE MOUNT BRACE. THERE IS NO DAMAGE HISTORY ON THE ACFT. THE MOUNT DOES NOT HAVE RELIEF HOLES FOR WELDING, AND THUS CAN`T ACHIEVE FULL PENETRATION ON THE WELDS THERE. COMBINED WITH FATIGUE AND VIBRATION, THIS COULD CAUSE THE MOUNT TO CRACK. ON NEWER ACFT, MFG HAS GUSSET PLATES INSTALLED, AND THE COMPANY THAT PERFORMED THE REPAIR ALSO INSTALLS GUSSET PLATES IN THIS AREA. RECOMMENDATION IS FOR VER CLOSE VISUAL INSP OF THIS PARTICULAR AREA AT 100 HR INTERVALS UNTIL GUSSET PLATES ARE INSTALLED, OR NEW STYLE MOUNT IS INSTALLED.

2010FA0000667

CESSNA

LYC  

 

MOUNT

CRACKED

7/2/2010

172M

O320E2D

 

05510171

ENGINE

DURING ROUTINE MX, A CRACK WAS FOUND ON LOWER LT ENGINE MOUNT BRACE. THERE IS NO DAMAGE HISTORY ON THE ACFT. THE MOUNT DOES NOT HAVE RELIEF HOLES FOR WELDING, AND THUS CAN`T ACHIEVE FULL PENETRATION ON THE WELDS THERE. COMBINED WITH FATIGUE AND VIBRATION, THIS COULD HAVE CAUSED THE MOUT TO CRACK. ON NEWER ACFT, MFG HAS GUSSET PLATES INSTALLED IN THE WEAK AREAS OF THE MOUNT. RECOMMENDATION IS FOR VERY CLOSE VISUAL INSP OF THIS PARTICULAR AREA AT 100 HR INTERVALS UNTIL GUSSET PLATES ARE INSTALLED, OR NEW STYLE MOUNT IS INSTALLED.

ZB0R201000005

CESSNA

 

 

STARTER

BINDS

6/23/2010

172S

 

 

149NL

ENGINE

WHILE ATTEMPTING TO START THE ENGINE, THE PILOT REPORTED THE STARTER WOULD NOT ROTATE THE ENGINE. PLANE TAKEN TO MAINTENANCE WHERE IT WAS DISCOVERED THE STARTER WAS FROZEN. REPLACED WITH REPAIRED LIKE PART AND OPS CHECK OK. THIS IS THE SECOND OCCURRENCE OF THIS PART NUMBER STARTER IN LESS THAN 1 YEAR AND 3RD OCCURRENCE OF THIS TYPE. A FEW DAYS EARLIER A C152 EXPERIENCED THE SAME PROBLEM (CONTROL #ZB0R201000004).

2010FA0000586

CESSNA

PWA  

 

SPRING

BROKEN

5/27/2010

208B

PT6A114A

 

26430623

NLG 

PILOT FELT VIBRATION ON THE NOSE GEAR WHEEL. IT BOUNCES ABOUT 3 TIMES AND THE NOSE GEAR COLLAPSE. AFTER TOUCH DOWN, PILOT FELT VIBRATION ON NOSE WHEEL FOLLOWED BY 3 BOUNCES AFTER THAT NOSE GEAR ASSY DISPLACED FWD CAUSING THE PROPELLER TO HIT OR STRIKE THE NOSE WHEEL. UPON INSP, FOUND NOSE TIRE BLOWN OUT AND NOSE GEAR SPRING BROKEN.

FCPR201000230

CESSNA

 

 

SHUTOFF VALVE

LEAKING

7/1/2010

525A

 

 

99124004

HYD SYSTEM

(FCPR) LT HYD SHUTOFF VALVE LEAKING STATIC AND UNDER PRESSURE. OUTLET PORT FLANGE DEFORMED WITH EXTRUDED O-RING.

AMCR201007

CESSNA

WILINT

 

SENSOR

MELTED

6/23/2010

525B

FJ443A

 

2423579646

LT ENGINE

(AMCR) DURING OTHER MX, TECH DISCOVERED A "T2 HEATER FAIL" ANNUNCIATOR. INVESTIGATION DISCOVERED A DEFECTIVE P2T2 SENSOR ON THE LT ENGINE. PROBE TIP SHOWED SIGNS OF SOLDER FLOW FROM VARIOUS PLACES.

EWCRN560CK20702

CESSNA

PWA  

 

FUEL CONTROL

FAULTED

6/14/2010

560CESSNA

JT15D5

 

32448517

RT ENGINE

ACFT WAS AT 21,000 FT. AND APPROVED FOR HIGHER ALTITUDE. POWER WAS APPLIED AND RT ENGINE HAD NO RESPONSE. ACFT WAS RETURNED TO DEPARTURE POINT GSO. POWER CONTROL WAS EFFECTIVE BELOW 10,000 FT. ACFT WAS TURNED OVER TO SERVICE CENTER FOR REPAIRS NEEDED.

CWQR.2010.03

CESSNA

 

 

TORQUE TUBE

CORRODED

6/15/2010

560XL

 

 

6634002966340021

ELEVATORS

THIS IS GENERAL INFORMATION REGARDING SURFACE CORROISION ON ELEVATOR TORQUE TUBES.THE TORQUE TUBES ARE A WELDED STEEL ASSY, AND IS NOT UNCOMMON TO FIND SOME CORRISION WHERE IT IS EXPOSED. HAVE FOUND ABOUT 10 ELEVATOR TORQUE TUBES WITH SURFACE CORRISION. OF THOSE ABUT 25 PERCENT HAD CORRODED ENOUGH TO REPLACE THE TORQUE TUBE. HAVE BEEN ABLE TO EVALUATE AND REPAIR THE ELEVATOR TORQUE TUBES USING THE SRM, BUT BELIEVE A SB IS NEEDED TO EVALUATE AND CORRECT THIS PROBLEM. A SERVICE CONDITION REPORT HAS BEEN SUBMITTED TO MFG UNDER NR516422.

2010F00126

CESSNA

PWC  

 

DIFFUSER

CRACKED

6/17/2010

680CE

PW306C

 

692252054

WING HEATED L/E

((JGVR)) FOUND THESE WING BLEED AIR HEATED L/E DIFFUSERS CRACKED OR DEFORMED ON NUMEROUS ACFT. THIS DISCREPANCY WAS FOUND WHILE PERFORMING A301001 WING/ HORIZ STABILIZER BLEED AIR ANTI-ICE SYS DETAIL INSP. TASK 30-10-00-220 AS PART OF INSP DOCUMENT 9. THE DOCUMENT 9 IS A 48 MONTH INSPECTION. THIS DISCREPANCY WAS LIKELY CAUSED BY THERMAL EXPANSION AND IN FLIGHT VIBRATION OF THE WING L/E ANTI-ICE PICCOLLO TUBE. THE PICCOLLO TUBE IS HARD MOUNTED TO THE DIFFUSER WITN NO VIBRATION DAMPNERS OR MEANS TO COMPENSATE FOR THE THERMAL EXPANSION. THE MATERIAL FOR THE DIFFUSERS IS THIN AND BENDS EASILY. HAVE ALSO FOUND THE PICCOLLO TUBES CHAFING ON THE DIFFUSERS. RECOMMEND THAT THE DIFFUSERS BE BUILT WITH A HEAVIER MATERIAL AND THE PICCOLLO TUBE MOUNTING BE REDESIGNED. THE OCCURRENCE WAS CORRECTED BY REPLACEMENT OF AFFECTED PARTS.

2010F00127

CESSNA

PWC  

 

DIFFUSER

CRACKED

6/17/2010

680CE

PW306C

 

692252055

WING HEATED L/E

((JGVR)) FOUND THE WING BLEED AIR HEATED L/E DIFFUSERS CRACKED OR DEFORMED ON NUMEROUS ACFT. THIS DISCREPANCY WAS FOUND WHILE PERFORMING A301001 WING/ HORIZ STABILIZER BLEED AIR ANTI-ICE SYS DETAIL INSP. TASK 30-10-00-220 AS PART OF INSP DOCUMENT 9. THE DOCUMENT 9 IS A 48 MONTH INSPECTION. THIS DISCREPANCY WAS LIKELY CAUSED BY THERMAL EXPANSION AND IN FLIGHT VIBRATION OF THE WING L/E ANTI-ICE PICCOLLO TUBE. THE PICCOLLO TUBE IS HARD MOUNTED TO THE DIFFUSER WITN NO VIBRATION DAMPNERS OR MEANS TO COMPENSATE FOR THE THERMAL EXPANSION. THE MATERIAL FOR THE DIFFUSERS IS THIN AND BENDS EASILY. HAVE ALSO FOUND THE PICCOLLO TUBES CHAFING ON THE DIFFUSERS. RECOMMEND THAT THE DIFFUSERS BE BUILT WITH A HEAVIER MATERIAL AND THE PICCOLLO TUBE MOUNTING BE REDESIGNED. THE OCCURRENCE WAS CORRECTED BY REPLACEMENT OF AFFECTED PARTS.

2010F00125

CESSNA

PWC  

 

DIFFUSER

CRACKED

6/17/2010

680CE

PW306C

 

692252053

WING HEATED L/E

((JGVR)) FOUND THE WING BLEED AIR HEATED L/E DIFFUSERS CRACKED OR DEFORMED ON NUMEROUS ACFT. THIS DISCREPANCY WAS FOUND WHILE PERFORMING A301001 WING/ HORIZ STABILIZER BLEED AIR ANTI-ICE SYS DETAIL INSP. TASK 30-10-00-220 AS PART OF INSP DOCUMENT 9. THE DOCUMENT 9 IS A 48 MONTH INSP. THIS DISCREPANCY WAS LIKELY CAUSED BY THERMAL EXPANSION AND IN FLIGHT VIBRATION OF THE WING L/E ANTI-ICE PICCOLLO TUBE. THE PICCOLLO TUBE IS HARD MOUNTED TO THE DIFFUSER WITN NO VIBRATION DAMPNERS OR MEANS TO COMPENSATE FOR THE THERMAL EXPANSION. THE MATERIAL FOR THE DIFFUSERS IS THIN AND BENDS EASILY. HAVE ALSO FOUND THE PICCOLLO TUBES CHAFING ON THE DIFFUSERS. RECOMMEND THAT THE DIFFUSERS BE BUILT WITH A HEAVIER MATERIAL AND THE PICCOLLO TUBE MOUNTING BE REDESIGNED. THE OCCURRENCE WAS CORRECTED BY REPLACEMENT OF AFFECTED PARTS.

2010F00128

CESSNA

PWC  

 

DIFFUSER

CRACKED

6/17/2010

680CE

PW306C

 

69225056

 

((JGVR)) FOUND THE WING BLEED AIR HEATED L/E DIFFUSERS CRACKED OR DEFORMED ON NUMEROUS ACFT. THIS DISCREPANCY WAS FOUND WHILE PERFORMING A301001 WING/ HORIZ STABILIZER BLEED AIR ANTI-ICE SYS DETAIL INSP. TASK 30-10-00-220 AS PART OF INSP DOCUMENT 9. THE DOCUMENT 9 IS A 48 MONTH INSPECTION. THIS DISCREPANCY WAS LIKELY CAUSED BY THERMAL EXPANSION AND IN FLIGHT VIBRATION OF THE WING L/E ANTI-ICE PICCOLLO TUBE. THE PICCOLLO TUBE IS HARD MOUNTED TO THE DIFFUSER WITN NO VIBRATION DAMPNERS OR MEANS TO COMPENSATE FOR THE THERMAL EXPANSION. THE MATERIAL FOR THE DIFFUSERS IS THIN AND BENDS EASILY. HAVE ALSO FOUND THE PICCOLLO TUBES CHAFING ON THE DIFFUSERS. RECOMMEND THAT THE DIFFUSERS BE BUILT WITH A HEAVIER MATERIAL AND THE PICCOLLO TUBE MOUNTING BE REDESIGNED. THE OCCURRENCE WAS CORRECTED BY REPLACEMENT OF AFFECTED PARTS.

2010FA0000535

CESSNA

 

 

HINGE

MISINSTALLED

6/10/2010

750  

 

 

 

AILERON

((EBVR)) DURING THE REMOVAL OF THE RT AILERON FOR PAINT, IT WAS FOUND THAT THE OTBD HINGE BUSHING WAS NOT FULLY INSTALLED (PN 67240121). THE BUSHING WAS NOT INSTALLED ENOUGH WHERE THE RETAINING CLIP COULD ENGAGE IN THE GROOVE. AFTER REMOVING THE AILERON IT WAS ALSO FOUND THAT THE OTBD HAT INSERT WAS MISSING (PN NAS75-6-004).

2010FA0000631

CESSNA

ALLSN

 

FRAME

CRACKED

5/25/2010

750  

AE3007C

 

67507434

WING CTR SECTION

((CNQR)) THE PN 6750743-4 FRAME IS PART OF THE AILERON POWER CONTROL UNIT SUPPORT ASSY AND IS APPLICABLE TO ACFT. DURING SCHEDULED INSP, THE FRAME WAS FOUND TO BE BADLY FATIGUE CRACKED AND APPROACHING FAILURE. FAILURE OF THIS FRAME COULD CAUSE LOSS OF AILERON ROLL CONTROL AND/OR A LOCKED AILERON SYS. THE PART WAS REPLACED. AN AILERON FORCE FLIGHT CHECK WAS DONE IAW MM TASK 27-10-00-760 WITH SATISFACTORY RESULTS. NDT WAS ACCOMPLISHED ON ALL FASTENERS COMMON BETWEEN THIS FRAME PIECE AND ALL ADJOINING FRAME PARTS WITH SATISFACTORY RESULTS. MFG ENGINEERING IS INVOLVED WITH THE ISSUE AND THE INVESTIGATION AS TO CAUSE IS ON-GOING.

2010F00132

CESSNA

ALLSN

 

BUSHING

MISINSTALLED

6/25/2010

750  

AE3007C

 

 

AILERON HINGE

((EBVR)) DURING THE REMOVAL OF THE RT AILERON FOR PAINT, IT WAS FOUND THAT THE OTBD HINGE BUSHING WAS NOT FULLY INSTALLED (PN 6724012-1). THE BUSHING WAS NOT INSTALLED ENOUGH WHERE THE RETAINING CLIP COULD ENGAGE IN THE GROOVE. AFTER REMOVING THE AILERON IT WAS ALSO FOUND THAT THE OTBD HAT INSERT WAS MISSING ( PN NAS 75-6-004).

2010FA0000589

CESSNA

LYC  

 

HOUSING

FAILED

6/4/2010

T206H

TIO540AJ1A

 

 

STARTER

HAD FAILURES OF THE HOUSING THAT CONTAINS THE STARTER DRIVE GEAR WITHIN A PERIOD OF 4 DAYS ON 2 SEPAATE ACFT. THE HOUSING THAT SURRROUNDS THE DRIVE GEAR CRACKED AND CAUSED THE DRIVE GEAR TO SHIFT AWAY FROM THE RING GEAR ON THE PROP TO WHERE THE GEARS WERE UNABLE TO MESH. CONTACTED THE MFG AND THEY SAID IMPROVEMENTS HAVE BEEN MADE ON NEWER STARTERS TO BEEF THEM UP.

2010FA0000587

CESSNA

LYC  

 

HOUSING

CRACKED

6/4/2010

T206H

TIO540AJ1A

 

 

STARTER

HAD FAILURES OF THE HOUSING THAT CONTAINS THE STARTER DRIVE GEAR WITHIN A PERIOD OF 4 DAYS ON 2 SEPARATE ACFT. THE HOUSING THAT SURROUNDS THE DRIVE GEAR CRACKED AND CAUSED THE DRIVE GEAR TO SHIFT AWAY FROM THE RING GEAR ON THE PROP TO WHERE THE GEARS WHERE UNABLE TO MESH. CONTACTED THE MFG AND THEY SAID IMPROVEMENT HAVE BEEN MADE ON NEWER STARTERS TO BEEF THEM UP.

2010FA0000719

CESSNA

 

 

STATOR

FAILED

7/10/2010

T210N

 

 

 

ALTERNATOR

STATOR POST ON ALTERNATOR FELL OUT IN FLIGHT, ALTERNATOR FAILED AFTER 44 HOURS SINCE O/H.

2010FA0000630

CESSNA

 

 

STRUCTURE

DAMAGED

5/25/2010

T337G

 

 

 

WING 

((Z4AR)) ACFT WAS BROUGHT IN FOR INSP IAW SAID CE10-20 AND ANNUAL INSP. ACFT IS EQUIPED WITH EXTENDED RANGE FUEL STC AND WING TIP STC. ACFT IS ALSO EQUIPED WITH STALL FENCES STC AND BOOM TO VERTICAL FAIRINGS. AN INSP IS IAW SAIB WAS PERFORMED. COMPRESSION BULGES OF THE INTERNAL STR UPPER SURFACE WAS NOTED ON BOTH WINGS BETWEEN WS 192 AND WS 177. AT THE INSTALLATION POINT OF THE LONG RANGE FUEL TANK OF WS 222, APPROX 50 PERCENT OF ALL 8/32 SCREWS, NO NUTS OR WASHERS WERE INSTALLED. THE STRUCTURE LOOKS TO HAVE BEEN TAPPED FOR THREADS. WING SKINS LT UPPER SURFACE BETWEEN WS 177 AND WS 192 SMOKING RIVETS, COMPRESSION EVIDENT IN THE SKIN. RT WING BETWEEN WS 177 AND WS 192 COMPRESSION BULGING, SMOKING RIVETS EVIDENT WITH CRACKS IN THE SKIN AT WS 177. WS 222.0 END RIB AT 2 INCH SECTION OF THE LOWER PART OF THE RIB WAS CUT DOWN FORM LIGHTENING HOLE IN AN UNACCEPTABLE FASHION IN BOTH WINGS. RT WING AT WS 55.0 JUST OTBD OF THE BOOM COMPRESSION BUCKLE IN UPPER SURFACE WING SKIN. THE STALL FENCES AT THE TIME OF REMOVAL WERE INSTALLED AT WS 132. IT WAS NOTED THE STALL FENCES HAD BEEN PREVIOUSLY LOCATED AT (3) OTHER AREAS IN EACH WING. AT WS 120, WS 90 AND WS 81 THE ATTACHMENT OF THE STALL FENCES AT EACH LOCATION WAS 8/32 MACHINE SCREW HOLE DRILLED AND TAPPED THROUGH FWD AND REAR SPAR CAPS, FOR A TOTAL OF 16 ADDITIONAL HOLES IN EACH WING UPPER SPAR CAP. RT WING, WS 121 AFT UPPER SPAR CAP HAS (1) HOLE WITH NO EDGE DISTANCE BROKEN THROUGH THE EDGE OF THE SPAR CAP. ADDITIONALLY AND UNEXPLAINED IN THE SAME SPAR CAP 10 OVER COUNTER-SUNK HOLES FOR NR 30 RIVETS APPARENTLY HAND COUNTER SUNK AND OBLONGED, VERY DEEP. THE REST OF THE ACFT SHOWS NO EVIDENCE OF STRUCTURAL OVERSTRESS. THE CHIEF INSPECTOR HAS BEEN INVOLVED IN HUNDREDS OF THESE ACFT. STRESS OF SKYMASTER WINGS, THIS STRESS APPEARS IN THE UPPER L/E SKIN JUST FWD OF THE TANK TOP AT A 45 DEGREE ANGLE PATTERN RELEVANT TO THE L/E. WS 66 AND WS 79.60 SOMETIMES EXTENDING TO WS 93.6. ADDITIONALLY IN THE FUEL TANK TOP COVERS THE COUNTER-SUNK 10-32 SCREWS OFTEN TIMES PULLED THROUGH THE OUTER SKIN AND IN CASES OF REPETITIVE STRESS WITH HIGH TT CRACKS GENERALLY APPEAR AT THE TANK TOP COVER SCREW LOCATIONS.

2010FA0000595

CESSNA

CONT

 

BOLT

WORN

5/19/2010

U206G

IO520*

 

NAS464P5A42

NOSE GEAR

DURING A 100 HR INSP, FOUND NOSE GEAR HAD FORE AND AFT MOVEMENT WHERE THERE SHOULD BE NONE. REMOVED AFT DRAG LINK BOLT TO INVESTIGATE AND FOUND IT TO BE WORN AND DEFORMED AS IF GETTING READY TO SHEAR. THIS IS THE THIRD OR FOURTH FOUND. THE OTHER ACFT THAT WERE FOUND HAD SHEARED THE BOLT AND LUCKILY DIDN`T COLAPSE THE GEAR. RECOMEND EITHER A MODIFICATION TO A LARGER BOLT OR 1000 HR TIME REPLACEMENT ESCECIALLY IF THE ACFT IS BEING USED ON ROUGH, UNIMPROVED RUNWAYS. PART IS NR 6 ON FIG 38 IN MFG SRM. THIS ACFT HAS HAD A LANDING DOSE FORK INSTALLED SINCE 12/9/04 AND HAS 1384.2 HRS SINCE IT WAS INSTALLED.

2010FA0000642

CIRRUS

CONT

 

PUMP

ERRATIC

6/9/2010

SR22

IO550N

 

ETISR22212

FUEL EDP

TURBO NORMALIZER EQUIPMENT INSTALLED IAW STC SA10588SC (AIRFRAME), AND STC SE 10589SC. ENGINE DRIVE FUEL PUMP ETI-SR22-2-12 IS REQUIRED UNDER STC FOR TURBO NORMALIZER EQUIPMENT. THIS FUEL-PUMP FEATURES AN ANEROID COMPENSATOR TO REGULATE MIXTURE FOR TURBONORMALIZATION AND REPLACES THE OEM IO550, NON-TURBO PUMP. FUEL MIXTURE CAM PROFILE WAS ERRONEOUS. FUEL FLOW RATE INCREASES NORMALLY FROM IDLE CUT-OFF TO APPROX 80 PERCENT OF MIXTURE-LEVER RANGE OF MOTION WHERE FUEL FLOW IS AT MAXIMUM. THEN FUEL RATIO BEGINS TO DECREASE AS LEVER CONTINUES TOWARD MAXIMUM POSITION. 80 PERCENT MIXTURE PROVIDES 37.5 GPH, 100 PERCENT MIXTURE POSITION PROVIDES 35.5 GPH.

2010FA0000591

CIRRUS

CONT

 

CAMSHAFT

WORN

6/1/2010

SR22

IO550N

 

654084

ENGINE

((5CSR)) DURING A CYLINDER CHANGE JOB PROMOTED BY LOW CYLINDER COMPRESSION AND HIGH IRON CONTENT IN OIL, IT WAS NOTED AN ABNORMAL AND UNSAFE AMOUNT OF WEAR ON THE CAM SHAFT LOBES. IT WAS DIRECTLY CAUSED BY LIFTERS THAT HAD EXCESSIVE AMOUNTS OF SPALLING. IT IS UNCLEAR AS TO WHAT MAY HAVE CAUSED THE INITIAL BREAK DOWN OF THE SURFACE METALS, BUT ONCE BEGAN THE BREAKDOWN ESCALATED. IT IS PROBABLE THA POOR METAL QUALITY OR IMPROPER HEAT TREATING OF THE COMPONENTS COULD BE THE CAUSE AND COULD BE REMEDIED BY BETTER QUALITY CONTROL DURING MFG PROCESSES.

2010FA0000599

CIRRUS

CONT

 

ATTACH FITTING

FRACTURED

6/21/2010

SR22

IO550N

 

 

HEATED AIR TUBE

ENGINE HAD CEASED TO OPERATE AT 10,000 FT, BOOST PUMP TURNED ON, ENG RE-STARTED, PILOT UNABLE TO ADVANCE THROTTLE BEYOND "1ST DETENT" WITHOUT ENG VIBRATION. ACFT RETURNED TO BASE. MX GROUND RUN, MAG DROPS & FUEL SYS PARAMETERS WITHIN LIMITS UNTIL FULL POWER ATTEMPTED. ABOVE 2000 RPM, ENG HAD SERIOUS VIBRATION. VARIOUS CYLINDERS SHOWED DROP IN CHT & EGT. GROUND CHECK DISCONTINUED. COMPRESSION CHECK REVEALED NR 4 CYLINDER AT 28 PSI, OTHER 5 WERE ABOVE LIMITS. REMOVED NR 4 CYLINDER, LEAK AT INTAKE VALVE TO SEAT. FOUND EXCESSIVE WRIST PIN TO CONNECTING ROD CLEARANCE DUE TO ROD BUSHING & PIN WEAR. CLEARANCE APPROX .005 TO .007, .0015 TO .0017 IS CALLED FOR. REMOVED REMAINING CYLINDERS TO INSPECT FOR WRIST PIN WEAR & POSSIBLE ANSWER TO WHY ENGINE SHUTDOWN. FOUND 2 PIECES OF METAL APPROX .2500 BY .3750. 1 PIECE AT INDUCTION SIDE OF NR 1 CYL. OTHER IN NR 6. DAMAGE OCCURRED TO PISTONS NR 2 & NR 5, ALSO, CYLINDER HEAD NR 2 & NR 5 HAD BEEN MARKED BY THE METAL HAVING BEEN IN COMBUSTION CHAMBERS. 2 PIECES OF METAL MIGRATED, 1 PIECE OF METAL HAD HELD NR 4 INTAKE OPEN RESULTING IN PRESSURIZATION OF INTAKE MANIFOLD & CORRESPONDING REDUCTION OF FUEL FLOW. AS ENGINE CONTINUED TO WINDMILL PIECE DISLODGED & FUEL FLOW RE-ESTABLISHED ALONG WITH SUBSEQUENT ENG RESTART. INSP OF INDUCTION SYS REVEALED NO BROKEN COMPONENTS OTHER THAN HEATED AIR SUPPORT TUBE, MISSING 1 ATTACH LEG. LEG HAD BROKEN AT CLAMP THEN BROKE AGAIN NEAR WELD. IT SEEMS DIFFICULT TO THINK THAT THIS BROKEN PIECE MIGRATED UP A 2 PLUS INCH SCAT HOSE, PASSED THROUGH THE ALTERNATE AIR DOOR AND INTO THE INDUCTION SYS, (ALTERNATE AIR DOOR WAS MIS-RIGGED AND REMAINED ALWAYS OPEN ROUGHLY .3750 OF AN INCH), BUT THE METAL FOUND IS SIMILAR IN WIDTH AND THICKNESS TO THE BROKEN MATERIAL OF THE ADAPTER PN 18293-001. CIRRUS “TECH REP” WAS CONTACTED AND AT HIS SUGGESTION THE MATERIAL WILL BE SUBMITTED FOR FACTORY FOR LABORATORY ANALYSIS IN ORDER TO ARRIVE AT A DEFINITIVE SOURCE DETERMINATION. IF THE SUSPECTED MIGRATION OCCURRED, A PROTECTIVE SCREEN SHOULD BE ADDED TO EITHER ONE END OR THE OTHER OF THE HEATED AIR TUBE, P/N 50206-250 TO PREVENT A SIMILAR INCIDENT.

2010FA0000592

CIRRUS

CONT

 

LIFTER

WORN

6/1/2010

SR22

IO550N

 

653888

ENGINE

((5CSR)) DURING A CYLINDER CHANGE JOB PROMPTED BY LOW CYLINDER COMPRESSION AND HIGH IRON CONTENT IN OIL IT WAS NOTED AN ABNORMAL AND UNSAFE AMOUNT OF WEAR AND SPALLING ON THE LIFTER FACE. THIS DIRECTLY CAUSED EXCESSIVE AND UNSAFE WEAR ON THE CAM SHAFT LOBES. IT IS UNCLEAR AS TO WHAT MAY HAVE CAUSED THE INITIAL BREAK DOWN OF THE SURFACE METALS, BUT ONCE BEGAN THE BREAKDOWN RAPIDLY ESCALATED. IT IS PROBABLE THAT POOR METAL QUALITY OR IMPROPER HEAT TREATING OF THE COMPONENTS COULD BE THE CAUSE AND COULD BE REMEDIED BY BETTER QUALITY CONTRL DURING MFG PROCESSES.

2010FA0000716

CIRRUS

CONT

 

SUPPRESSOR

BURNED

6/28/2010

SR22

IO550N

 

12980001

 

ITEM APPARENTLY OVERHEATED CAUSING EXCESSIVE SMOKE IN COCKPIT. THE CASE OF THE TVS IS BURNED AND THE SURROUNDING AREA ON BACK OF THE CIRCUIT BREAKER PANEL IS DISCOLORED FROM THE SMOKE.

2010FA0000634

CIRRUS

CONT

 

ROTOR

SPLIT  

6/11/2010

SR22

IO550N

 

 

MAGNETO

DURING MAG CHECK ON RUN-UP, RT MAGNETO WAS INOPERATIVE. REMOVED MAG AND FOUND ROTOR SPLIT AT KEY WAY LOCATION. 120 HRS SINCE NEW.

2010FA0000624

CNDAIR

 

 

ANTENNA

UNKNOWN

5/4/2010

CL6002B16

 

 

S414222

GLIDE SLOPE

CREW REPORTED THAT ON APPROACH, GLIDE SLOPE DEVIATED UP AND DOWN TO RUNWAY 18L. AUTOPILOT WAS ENGAGED AND COUPLED TO BOTH OF THE NAVIGATION RECEIVERS, WHICH CAUSED THE AIRPLANE TO PORPOISE UP AND DOWN. A/P DISCONNECTED BY CREW AND LANDING CONTINUED ON VISUALLY. MX CHECKS FOUND NO SIGN OF FAILURE AND SYS, OPS CHECKED OK ON GROUND. REPLACED GLIDE SLOPE ANTENNA AS PRECAUTION AND FLIGHT CREW FLEW SAME APPROACH A COUPLE DAYS LATER AND REPORTED THAT ALL SYS WORKED CORRECTLY.

2010FA0000574

CNDAIR

 

 

TEE FITTING

CRACKED

6/1/2010

CL6002B16

 

 

MS21905D6

HYD SYSTEM

FOUND NR 3 HYD SYS PRESSURE LINE PN 600-75239-788 COMING FROM MANIFOLD LEAKING AT LINE "B" NUT FITTING PN MS21905D6 CRACKED. ALSO NOTED LINE CONNECTION TO TEE FITTING WAS IN A BIND. FAILURE WAS UNDER NORMAL OPERATIONS, SYS PRESSURE AT 3,000 PSI. RECOMMENDATION TO PREVENT REOCCURRENCE WOULD BE TO CONSIDER CHANGING TEE FITTING TO STEEL AND INSURE PRESSURE LINE IS ALIGNED WITH NO BINDING AND PROPERLY TORQUED.

2010FA0000534

CNDAIR

 

 

SENSOR

UNSECURE

5/20/2010

CL604

 

 

25147A77

AOA 

((JGVR)) RECEIVED UNIT, AS A REPAIRED UNIT. SENSOR HSG FOUND, NOT SECURED. SENSOR COULD BE ROTATED (RECLOCKED) GIVING IMPROPER READINGS. DISCOVERED WHEN TECH ATTACHED MOUNTING BRACKETS, TEMPORARILY INSTALLED SENSOR IN ACFT, ROTATED SENSOR TO CLOCK POSITION AND HSG ROTATED. APPEARS TO NEED HSG GASKET AND SCREWS REPLACED AND SAFETIED. NOTE: THIS FORM IS BEING SUBMITTED FOR WORK BEING PERFORMED ON A FOREIGH REGISTERED ACFT.

V0XR201006140001

DHAV

 

 

FLAP TRACK

CRACKED

6/14/2010

DHC3

 

 

85780185103

ZONE 100

(V0XR) CRACK ON LT NR 1 FLAP TRACK. R & R FLAP TRACK. W/C 5038

V0XR201006140002

DHAV

 

 

FLAP TRACK

CRACKED

6/14/2010

DHC3

 

 

85780044113

ZONE 100

(V0XR) CRACK ON LT NR 2 FLAP TRACK. R & R FLAP TRACK. W/C 5042

V0XR201006140003

DHAV

 

 

SEAT TRACK

CRACKED

6/14/2010

DHC8102

 

 

85320490133SP

ZONE 100

(V0XR) LT SEAT TRACK HAS CORROSION. R & R SEAT TRACK. W/C 2252

V0XR201006150006

DHAV

 

 

SEAT TRACK

CORRODED

6/15/2010

DHC8102

 

 

85330164117SP

BS 425-531

(V0XR) RT SEAT TRACK FROM STA 425.0 - 531.0 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 1122.

V0XR201006210002

DHAV

 

 

SEAT TRACK

CORRODED

6/21/2010

DHC8102

 

 

85330164119

ZONE 100

(V0XR) LT SEAT TRACK HAS CORROSION INBD FROM STA 425.82 - 531.0. R & R LT SEAT TRACK. W/C 4007

V0XR201006210003

DHAV

 

 

SEAT TRACK

CORRODED

6/21/2010

DHC8102

 

 

85330164119

ZONE 100

(V0XR) LT SEAT TRACK HAS CORROSION INBD FROM STA 425.82 - 531.0. R & R LT SEAT TRACK. W/C 1123

V0XR201006210004

DHAV

 

 

SEAT TRACK

CORRODED

6/21/2010

DHC8102

 

 

85330217007

ZONE 100

(V0XR) LT SEAT TRACK HAS CORROSION INBD FROM STA 531.0 - 600.0. R & R LT SEAT TRACK. W/C 1124

V0XR201006150005

DHAV

 

 

SEAT TRACK

CORRODED

6/15/2010

DHC8102

 

 

85330469001SP

BS 531-600

(V0XR) RT SEAT TRACK FROM STA 531.0 - 600.0 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 1121.

V0XR201006110001

DHAV

 

 

SEAT TRACK

CORRODED

6/11/2010

DHC8102

 

 

85320490135SP

BS 180-455

(V0XR) FLOOR SEAT TRACK X180.00 - X455.00 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 1005

V0XR201006100001

DHAV

 

 

SUPPORT BRACKET

CRACKED

6/10/2010

DHC8311

 

 

8255014003

ZONE 100

(V0XR) SIDE WALL SUPPORT BRACKET CRACKED AT STA X642 Z-20. R & R BRACKET. W/C 2051.

V0XR201006100002

DHAV

 

 

ANGLE

CRACKED

6/10/2010

DHC8311

 

 

238111

ZONE 500

(V0XR) LT ANGLE ON LT FINGERNAIL CRACKED IN 2 PLACES UNDER RIVET HEADS. R & R ANGLE. W/C 4040

V0XR201006150003

DHAV

 

 

ATTACH BRACKET

CRACKED

6/15/2010

DHC8311

 

 

2024T3

LT NACELLE

(V0XR) LT NACELLE INBD ATTACHMENT BRACKET IS CRACKED. R & R BRACKET. W/C 4071.

V0XR201006150004

DHAV

 

 

BRACKET

CRACKED

6/15/2010

DHC8311

 

 

2024T3

RT NACELLE

(V0XR) RT NACELLE INBD ATTACHMENT BRACKET IS CRACKED. R & R BRACKET. W/C 4072.

V0XR20100701002

DHAV

 

 

ANGLE

CRACKED

7/1/2010

DHC8311

 

 

85300011111SP

ZONE 600

(V0XR) FWD WING SPAR TO FUSELAGE (CLOSING ANGLES). R & R FWD WING SPAR TO FUSELAGE, CLOSING ANGLES. W/C 2094

V0XR20100701001

DHAV

 

 

ANGLE

CRACKED

7/1/2010

DHC8311

 

 

85300016121SP

ZONE 600

(V0XR) FWD WING SPAR TO FUSELAGE (CLOSING ANGLES) AT 4R-6R CRACKED. REMOVED AND REPLACED FWD WING SPAR TO FUSELAGE, CLOSING ANGLES. W/C 2093

V0XR20100701004

DHAV

 

 

BRACKET

CRACKED

7/1/2010

DHC8311

 

 

2024T3063

FUSELAGE

(V0XR) BRACKET OF FWD SIDE OF OTBD INTERCOSTAL IS CRACKED. REMOVED AND FABRICATED NEW BRACKET. W/C 4085

V0XR201006150001

DHAV

PWA  

 

SKIN

CRACKED

6/15/2010

DHC8311

PW123

 

 

RT ELEVATOR

(V0XR) RT ELEVATOR CTR HINGE AREA BOTTOM L/E INBD SKIN IS CRACKED. BLENDED HINGE AREA, W/C 3032.

V0XR201006150002

DHAV

PWA  

 

SKIN

DAMAGED

6/15/2010

DHC8311

PW123

 

85520001001

LT ELEVATOR

(V0XR) LT ELEVATOR INBD UPPER SKIN IS DAMAGED. BLENDED UPPER SKIN AREA, W/C 3034.

V0XR201006210001

DHAV

PWA  

 

SHROUD

CRACKED

6/21/2010

DHC8311

PW123

 

A238063

ZONE 600

(V0XR) LARGE CRACK ON FINGERNAIL SHROUD/ EXHAUST OUTLET LOOKING AFT AT 10 O'CLOCK POSITION AND SMALL CRACK AT RIVET ROW 6. REPLACED FINGERNAIL SHROUD. W/C 4007

2010FA0000536

DIAMON

CONT

 

TUBE

WORN

5/27/2010

DA20C1

IO240A

 

2227271100

RUDDER PEDAL

PILOT RUDDER PEDAL "S" TUBE WORN THROUGH.

U43R2010AF0000191

DIAMON

LYC  

 

STARTER

SLOW

6/18/2010

DA40

IO360M1A

 

31B22105

ENGINE

(U43R) WHILE ATTEMPTING TO START THE AIRPLANE, THE STARTER TURNED THE ENGINE VERY SLOWLY. THIS WAS TO BE THE 2ND FLIGHT OF THE DAY, THE AIRPLANE HAD THE PROPER VOLTAGE SUPPLIED TO THE STARTER. R & R THE STARTER, ACFT WAS RETURNED TO SERVICE.

U43R2010AF0000190

DIAMON

LYC  

 

VALVE

STRIPPED

6/11/2010

DA40

IO360M1A

 

D4171662030

ENGINE AIR INTAK

(U43R) DURING SCHEDULED INSP, A&P MECHANIC FOUND THAT THE ALTERNATE AIR VALVE CONTROL LINE WAS LOOSE. FURTHER INSP FOUND THAT THE "EYE" BOLT HAD STRIPPED THE THREADS IN THE VALVE BODY HSG. THE BODY HSG IS MADE FROM ALUMINUM, THE "EYE" BOLT FROM STEEL. THE "EYE" BOLT CANNOT BE TIGHTENED COMPLETELY BECAUSE THE OPENING WILL FACE THE WRONG WAY, NOT ALLOWING INSTALLATION OF THE CONTROL CABLE. WITH THE VIBRATION FROM THE ENGINE, THIS CAUSES THE "EYE" BOLT TO WEAR ON/IN THE VALVE BODY HSG.

U43R2010AF0000193

DIAMON

LYC  

 

HEAT EXCHANGER

BROKEN

6/30/2010

DA40

IO360M1A

 

41303

EXHAUST SYSTEM

IAW POWER FLOW SYS "CONTINUED AIRWORTHINESS INSTRUCTIONS" (DATED 07/22/2008) PARAGRAPH 7.0 STATES "THE EXHAUST SYS MUST BE THOROUGHLY INSPECTED, ESPECIALLY WITHIN THE HEAT EXCHANGER SECTION" DURING A 100 HR INSP OF THIS AIRPLANE A CRACK WAS FOUND IN THE CHAIN WELD AT THE EXHAUST EXIT BALL AND THE HEAT EXCHANGER COVER. THE CRACKS START AT THE FINISH POINT OF THE WELD AND CONTINUE THROUGH THE CTR OF THE WELD TO THE START POINT OF THE WELD SEGMENT. PARAGRAPH 5.4.1 "MAXIMIZING SERVICE LIFE" STATES, "DYNAMICALLY BALANCE YOUR PROPELLER TO BELOW 0.2 IPS EVERY 2 YEARS OR 1000 HRS (WHICHEVER OCCURS FIRST)."

U43R2010AF0000192

DIAMON

LYC  

 

STARTER

FAILED

6/24/2010

DA40

IO360M1A

 

31B22105

ENGINE

AIRPLANE HAD FLOWN 3 TIMES ON THIS DAY, ON THE 4TH FLIGHT STARTER FAILED TO START. A CLICK NOISE COULD BE HEARD WHEN TURNING KEY FROM BOTH TO START. FLIGHT WAS ABORTED.

NX4R00001

DIAMON

LYC  

 

FUEL TANK

CRACKED

4/27/2010

DA42

IO360M1A

 

D6028141100

ZONE 500

DURING A ROUTINE INSP, A FUEL STAIN WAS NOTICED IN THE LT AUX TANK AREA. THE TANK WAS REMOVED AND INSPECTED. THERE WERE CRACKS FOUND AT SEVERAL OF THE WELD POINTS WHERE AN INTERNAL BAFFLE IS WELDED TO THE BOTTOM PANEL OF THE TANK. A NEW TANK (PN-D60-2814-11-00) WAS INSTALLED.

2010FA0000530

DIAMON

THIELT

 

CLUTCH

BLOWN

6/11/2010

DA42

TAE1250299

 

057211K006002

ENGINE

DURING CRUISE FLIGHT THE PILOT SAID THE LT ENGINE LOST POWER THEN IT OVERSPEED. ENGINE SHUTDOWN.

2010FA0000670

DOUG

 

 

SKIN

CRACKED

6/1/2010

DC873F

 

 

 

NLG DOOR

NLG - LT AFT DOOR EXTERNAL SKIN CRACKED 1" AND WITH INTERIM REPAIR.

2010FA0000679

DOUG

 

 

LONGERON

CORRODED

6/1/2010

DC873F

 

 

 

BS 1700 L34L

(SPUY) AFT ACCY COMPT L-34L CORRODED AT STA 1700.000 (CORRECTING SOURCE DOCUMENT: CPCP 5600-0551).

2010FA0000675

DOUG

 

 

VANE

DAMAGED

6/1/2010

DC873F

 

 

 

LWS 247

(SPUY) LT WING - INBD VANE SLOT WITH ELONGATED HOLES AT STA XS 247.000.

2010FA0000680

DOUG

 

 

SKIN

DENTED

6/1/2010

DC873F

 

 

 

RT WING TE FLAP

(SPUY) RT OTBD FLAP T/E PANEL UPPER SKIN WITH (02 EA) DENTS AT STA XF 310.000 AND 320.000.

2010FA0000668

DOUG

 

 

FITTING

CORRODED

6/1/2010

DC873F

 

 

 

LT MLG WW

(SPUY) LT MLG WW - L-24L, JOINT FITTING LWR PART CORRODED AT STA 940.000.

2010FA0000678

DOUG

 

 

CARGO TRACK

BROKEN

6/1/2010

DC873F

 

 

 

BS 140-160

(SPUY) MAIN CARGO COMPT - NR 4 SEAT TRACK LUG PLUG BROKEN (STA 140.000- 160.000).

2010FA0000669

DOUG

 

 

FITTING

CRACKED

6/1/2010

DC873F

 

 

 

LT MLG WW

(SPUY) LT MLG WW, LT 24L, JOINT FITTNG LWR PART CRACKED .5" AT STA 879.000.

2010FA0000676

DOUG

 

 

CARGO TRACK

CORRODED

6/1/2010

DC873F

 

 

 

BS 857-880

(SPUY) MAIN CARGO COMPT - NR 2 SEAT TRACK LUGS WORN AND CORRODED (STA 857.000- 880.000).

2010FA0000674

DOUG

 

 

SKIN

CORRODED

6/1/2010

DC873F

 

 

 

RUDDER

(SPUY) RUDDER LT SIDE PLATING CORRODED AT STA ZR 140.000.

2010FA0000671

DOUG

 

 

ACCESS DOOR

CRACKED

6/1/2010

DC873F

 

 

 

LT WING

(SPUY) LT WING - NR505F ACCESS DOOR PLATING SURFACE UPPER PART CRACKED 1".

2010FA0000672

DOUG

 

 

SKIN

DENTED

6/1/2010

DC873F

 

 

 

LT ELEVATOR

(SPUY) LT HORIZ STAB - ELEVATOR UPPER PLATING DENTED 6" AT STA XE 90.000.

2010FA0000673

DOUG

 

 

CARGO TRACK

WORN

6/1/2010

DC873F

 

 

 

CARGO BAY  

(SPUY) MAIN CARGO COMPT - NR 2 SEAT TRACK (03 EA) LUGS WORN AT STA 280.000.

2010FA0000677

DOUG

 

 

ACCESS DOOR

CRACKED

6/1/2010

DC873F

 

 

 

CENTER WING

(SPUY) CTR WING AUX TANK RT SIDE - NR 516 ACCESS DOOR FLANGE WITH (02 EA) CRACKS AROUND STA XCW 23000, S57 AND S58.

ABXR201006250009

DOUG

 

 

SKIN

CORRODED

4/28/2010

MD88

 

 

593600419

ZONE 100

DURING A HEAVY MX EVENT, FOUND THE MID LOWER CARGO STA 610, BETWEEN L29R AND L30 HAD CORROSION ON THE SKIN. MID LOWER CARGO LOWER SKIN REMOVED AND A NEW SKIN INSTALLED. SKIN STATION 590-760, LONGERON 26L-26R.

ABXR201006250010

DOUG

 

 

FRAME

CORRODED

5/5/2010

MD88

 

 

27779306

ZONE 100

DURING A HEAVY MX EVENT, FOUND CORROSION AT FS 1322, L28L TO L28R ON FRAME AND FRAME LOWER LEG. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS. REPAIRED FRAME IAW SRM. REMOVED DAMAGED SECTION OF FRAME FROM L29R TO L29L AND INSTALLED NEW SECTION OF FRAME IAW SRM. FABRICATED REPAIR PARTS USING 7075-0.071 AMD 7075 T-6 .071 IAW SRM. HEAT TREATED REPAIR PARTS IAW 7075 T-6 IAW MD-80 SRM. TESTED GOOD.

ABXR201006250011

DOUG

 

 

SKIN

CORRODED

5/10/2010

MD88

 

 

593600419

ZONE 100

DURING A HEAVY MX EVENT, FOUND THE SKIN INTERIOR SURFACE CORRODED AT FS 685, L30. REMOVED CORRODED EXTERIOR SKIN STA. 541-769, L26R - 26L AS WELL AS CORRODED INTERIOR DOUBLER FOR REPLACEMENT. INSTALLED NEW LOWER SKIN USING 2024-T3 .071 MATERIAL AND NEW INTERNAL DOUBLER USING 2024 T-3 .071 MATERIAL IAW REA D953-60141. NOTE: REGISTRATION NUMBER PENDING CHANGE TO "880DA".

ABXR201006250008

DOUG

 

 

SKIN

CORRODED

4/28/2010

MD88

 

 

593600419

ZONE 100

DURING A HEAVY MX EVENT, FOUND THE MID LOWER CARGO LT SIDE OF L30, STA. 614, CORROSION ON SKIN. BLENDED AREA OF CORROSION AND TREATED IAW SRM. SKIN WAS FOUND TO BE OUT OF LIMITS AND WAS REPLACED.

ABXR201006250006

DOUG

PWA  

 

SKIN

CRACKED

4/21/2010

MD88

JT8D219

 

59359669

LT WING TE FLAP

DURING A HEAVY MX, THE LT WING INBD FLAP T/E OTBD END FOUND CRACKED. REPAIRED T/E SRM 57-03. FIG 9, ITEM RETURNED TO SERVICE.

ABXR20100625007

DOUG

PWA  

 

RIB  

CRACKED

4/23/2010

MD88

JT8D219

 

993750834

ZONE 600

(ABXR) DURING A HEAVY MX, THE RT WING L/E RIB, UPPER AFT END WAS FOUND CRACKED IN SEVERAL PLACES. APPROX XRS 290. REPAIRED RIB STA. XRS 290 IAW SRM.

2010FA0000721

EMB  

 

 

ACTUATOR

FAILED

7/12/2010

EMB500

 

 

0110083100

MLG 

NUMEROUS SYS FAILURES WERE INDICATED AT THE SAME TIME. THE SYS CONTINUED TO OPERATE NORMALLY. THE PILOT DIVERTED FOR REPAIR. THE PILOT DECLARED AN EMERGENCY DUE TO AN UNSAFE RT LANDING GEAR INDICATION. THE ACFT LANDED AND TAXIED TO THE SERVICE CENTER SAFELY. TECH OBSERVED THE FOLLOWING FAULT INDICATIONS: FUEL 1 LOW LEVEL, NR 2 FUEL STANDBY PUMP CONTINUOUSLY OPERATING WITH THE ENGINE SHUTDOWN AND THE SWITCH IN THE AUTO POSITION, RT MLG INDICATION RED AND LANDING GEAR DISAGREE MESSAGE, AND GEA 2 FAIL MESSAGE. REPLACEMENT OF GEA 2 CLEARED ALL MESSAGES AND RESTORED NORMAL OPERATION.

2010FA0000701

GULSTM

 

 

PLACARD

MISSING

7/6/2010

200  

 

 

 

CABIN

NO PLACARD INSTALLED MEETING FAR 25.1547 LOCATED IN OR ON THE ACFT .

2010FA0000643

GULSTM

 

 

ROLL PIN

BACKED OUT

5/28/2010

690A

 

 

 

MLG 

MLG DID NOT EXTEND TIL 4TH ATTEMPT. JACKED ACFT AND CONFIRMED PROBLEM. ALSO NOTED VERY ERRATIC HYD PRESSURE INDICATIONS. AFTER EXTENSIVE TROUBLESHOOTING NOTED THE ROLL PIN HAD BACKED OUT OF PN 540113-1 ARM (FIG 2-12 INDEX 117, 690A PARTS CATALOG PN M690002-4 REV 22 JULY 1994) WHERE IT ATTACHES TO THE LANDING GEAR CONTROL ASSY PN 540084-501 (FIG 2-12 INDEX 101). PART CATALOG DOES NOT SHOW ROLL PIN AT THIS LOCATION, BUT GEAR CONTROL SHAFT HAS A SLOT IN THE END TO ACCEPT A ROLL PIN THROUGH THE ARM (PN 540113-1) AND CONTROL ASSY (PN 540084-501). LOOKED AT ANOTHER 690A IN THE SHOP AND CONFIRMED A ROLL PIN WAS INSTALLED AND HAD SAFETY WIRE THROUGH IT AND WRAPPED AROUND THE ARM AND TWISTED ( HOLDING THE ROLL PIN IN POSITION) ON ACFT, SN 11309. WE FOUND NO INDICATION OF SAFETY WIRE. IF ROLL PIN HAD COME ALL THE WAY OUT IT POSSIBLY COULD RENDERED THE GEAR CONTROL VALVE INOPERATIVE ( OUT OF THE SYS). EMERGENCY EXTEND WOULD ALSO NOT WORK DUE TO THE GEAR CONTROL VALVE MUST MOVE FOR MLG EXTENSTION. RECOMMEND DURING LANDING GEAR INSPECTION OF NEXT SCHEDULED 150 HR OR PHASE INSP THAT THIS AREA BE GIVEN SPECIAL ATTENTION. TECH SUPPORT CONFIRMED PROPER PN FOR THIS ROLL PIN IS: PN MS171528. DURING INITIAL TROUBLESHOOTING, THAT NOSE GEAR EXTENDED AND LOCKED DOWN WHEN BOTH MAINS STAYED UP IN THE WELL.

2010FA0000627

GULSTM

GARRTT

 

WINDSHIELD

CRACKED

6/14/2010

G100

TFE73140

 

164300104

COCKPIT

RT WINDSHIELD OUTSIDE CRACK FOUND WHEN ACFT DESCENT FROM FL430 TO FL250 ,AND THEN TURNOFF THE WINDSHIELD HEATER, NO-PERSSURE LOSS, AND SAFE LANDING BACK HOME.THE SIGN SHOWS AND DOES NOT STRIKE AS THE SUFFERING EXTERNAL FORCE.

2010FA0000633

GULSTM

 

 

BRAKE ASSY

WORN

5/12/2010

G150

 

 

50065751

NR 2 

NR 2 BRAKE ASSY WORN BEYOND LIMITS AFTER ONLY 19.1 HRS AND 10 CYCLES SINCE O/H UNDER W/O RC1997713.1 DATED 3/22/10. INSTALLED O/H BRAKE ASSY PN 5006575-1, SN MAR03-59, O/H UNDER W.O WP194532/1 DATED APR 13, 2010. OPS CK SATISFACTORY.

2010FA0000632

GULSTM

GARRTT

 

BRAKE

WORN

5/12/2010

G150

TFE73140

 

50065751

NR 1 

NR 1 BRAKE ASSY WORN BEYOND LIMITS AFTER ONLY 19.1 HRS AND 10 CYCLES SINCE O/H UNDER W/O RC1997713.1 DATED 3/22/10. INSTALLED O/H BRAKE ASSY PN 5006575-1, SN MAR03-59, O/H UNDER W.O WP194532/1 DATED APR 13, 2010. OPS CK SATISFACTORY.

2010FA0000579

GULSTM

GARRTT

 

HYDRAULIC SYSTEM

FLUID LOSS

6/16/2010

G150

TFE73140

 

 

MAIN  

LOSS OF MAIN HYD SYSTEM FLUID AND LT GEN.

2010FA0000578

HUGHES

ALLSN

 

ENGINE

MAKING METAL

6/17/2010

369E

250C20B

 

6887190

 

PILOT DEPARTED THE AIRPORT FOR A TOUR FLIGHT AND AN ENGINE CHIP WARNING LIGHT CAME ON. THE PILOT RETURNED TO THE AIRPORT. MX PULLED THE UPPER AND LOWER CHIP PLUGS AND FOUND A SMALL AMOUNT OF MATERIAL ON THE UPPER PLUG .79MM OR LESS IN SIZE. AFTER A 30 MINUTE PENALTY RUN THE SAME AMOUNT OF MATERIAL WAS FOUND ON THE UPPER PLUG. THE ENGINE OILS WERE DRAINED, FLUSHED, SEVICED AND THE FILTERS WERE CLEANED. A SECOND 30 MINUTE RUN WAS PERFORMED. MATERIAL WAS AGAIN FOUND ON THE UPPER PLUG. THE ENGINE WAS REMOVED FROM THE ACFT FOR INSP.

2010FA0000718

LEAR

GARRTT

 

PUMP

FAILED

7/8/2010

35LEAR

TFE73122B

 

307194912

ENGINE OIL SYS

ON ENGINE START LT ENGINE DID NOT SHOW INDICATION OF OIL PRESSURE. ENGINE WAS SHUTDOWN IMMEDIATELY. OIL PUMP WAS REPLACED WITH O/H UNIT

2010F00135

LEAR

GARRTT

 

VALVE

STICKING

6/4/2010

35LEAR

TFE7312B

 

223355

WING HEAT

RT BLEED LIGHT ACTIVATED, CREW RAN AFM CHECKLIST AND DECIDED TO RETURN FOR LANDING. WHILE RETURNING FOR LANDING SOME LIGHT SMOKE WAS BEING EMITTED BY AFT DIVAN. ACFT LANDED WITHOUT INCIDENT. MECHANIC TROUBLESHOT SYS AND DETERMINED THAT THE WING HEAT VALVE FAILED IN THE FULL ON POSITION, WHICH ALLOWED UNREGULATED RAW BLEED AIR FROM ENGINE BLEED AIR MANIFOLD TO THE WINGS. THIS CAUSED SOME SINGING OF THE CARPET AT THE AFT DIVAN WHERE THE DUCTING ENTERS THE CABIN. WING HEAT VALVE WAS REPLACED WITH AN O/H VALVE & FUNCTIONALLY CHECKED. CARPET IS SCHEDULED TO BE REPLACED IN AFT DIVAN AREA.

2010FA0000625

LEAR

 

 

CONTROL BOX

INOPERATIVE

6/18/2010

45LEAR

 

 

C1444863300

TE FLAPS

FLAPS FAIL CAS MESSAGE IN FLIGHT.

2010FA0000626

LEAR

 

 

RVDT

FAULTY

6/19/2010

45LEAR

 

 

6627503000019

TE FLAPS

FLAPS FAIL AMBER CAS INFLIGHT.

2010FA0000623

LEAR

 

 

FLAP

OUT OF RIG

6/16/2010

45LEAR

 

 

6627503000019

TE 

FLAPS FAIL AMBER CAS MESSAGE CAME ON IN LEVEL FLIGHT. CREW COULD NOT RESET.

2010FA0000646

LET  

 

 

CABLE

FRAYED

6/28/2010

L23SUPERBLAN

 

 

A740255N

RUDDER

FRAYED RUDDER CABLES FOUND DURING 100 HR, 4 INSP. 330.9 SHOULD LAST 1000 HOURS IAW MFG MM. CHRONIC PROBLEM.

2010FA0000666

MAULE

LYC  

 

BULKHEAD

CRACKED

7/2/2010

MX7180A

O360C4F

 

C2367

PROP SPINNER

FWD SPINNER BULKHEAD AND SPINNER DOME FOUND CRACKED. THIS WAS THE NEW DESIGN MFG FWD SPINNER BULKHEAD PN C2367 WITH THE MFG ADAPTER PLATE PN A1235 INSTALLED. SEVERAL CRACKS WERE FOUND AROUND THE ATTACH HOLES ON THE BULKHEAD PANEL. TOTAL TIME ON SPINNER DOME AND FWD SPINNER BULKHEAD WERE 95.3 HOURS SINCE THEY WERE INSTALLED NEW. THIS PROBLEM IS CONTINUOUS WITH THE 5 OF THESE ACFT WE OPERATE AND CHANGE FWD SPINNER BULKHEADS REGULARLY DURING INSPECTIONS.

2010FA0000663

MOONEY

CONT

MOONEY

HOSE

DETERIORATED

6/30/2010

M20R

IO550*

 

HP008

VACUUM SYSTEM

PILOT NOTICED A LOW VAC WARNING OF THE ENGINE DRIVEN VACCUME PUMP. TURN THE SWITCH ON FOR THE STANDBY VAC SYS AND THE CIRCUIT BREAKER POPPED. FOUND THE CAUSE OF THE STANDBY VAC PUMP CIRCUIT BREAKER POPPING WAS A FROZEN VAC PUMP. INVESTIGATION REVEALED THAT THE SUPPLY HOSE, THAT IS MADE OF RUBBER WAS BREAKING DOWN INSIDE AND FILLING THE PUMP UP WITH CONTAMINANTS.

2010FA0000572

NAVION

 

 

SUPPORT

CRACKED

6/15/2010

STCNAVION

 

 

C4383

SPINNER

SPINNER SUPPORT, MANY CRACKS AROUND HUB MOUNT.

2010FA0000573

NAVION

CONT

 

SUPPORT

CRACKED

6/15/2010

STCNAVION

E185*

 

C4383

SPINNER

SPINNER SUPPORT, MANY CRACKS AROUND AREA OF PROPELLER HUB MOUNT.

2010FA0000706

PIPER

LYC  

 

DRAG LINK

BROKEN

6/21/2010

PA28R201

IO360A1A

 

7642603

NLG 

DURING A TRAINING FLIGHT, THE LANDING GEAR WAS EXTENDED. UPON GEAR EXTENSION ONLY THE MAIN GEAR DOWN LIGHTS ILLUMINATED. THE NOSE GEAR DOWN LIGHT REMAINED EXTINGUISHED AND THE GEAR UNSAFE LIGHT REMAINED ILLUMINATED. AFTER EXHAUSTING ALL EFFORTS TO LOCK THE NOSE GEAR DOWN IN FLIGHT THE PLANE LANDED UNEVENTFULLY. AFTER INSP OF THE NOSE GEAR WAS PERFORMED IT WAS DISCOVERED THAT THE ATTACH POINT ON THE DRAG LINK FOR THE NOSE GEAR DOWN LOCK FAILED AND SEPARATED CAUSING THE NOSE GEAR DOWN LIGHT TO REMAIN EXTINGUISHED, THE GEAR UNSAFE LIGHT ILLUMINATED, AND THE NOSE GEAR UNRELIABLE DOWN. NO DAMAGE WAS SUSTAINED BY THE AIRPLANE OTHER THAN THE FAILED NOSE GEAR PARTS PREVIOUSLY MENTIONED.

2010FA0000533

PIPER

LYC  

 

ENGINE

FAILED

6/2/2010

PA31350

TIO540J2BD

 

TIO540J2BD

LEFT 

(( MZ2R)) AFTER NORMAL RUN-UP, THE ACFT PROCEEDED TO TAKEOFF, ON ROLLOUT SMOKE WAS NOTED. THE PILOT WAS COMMITTED TO TAKEOFF, THE ENGINE WAS STILL GENERATING POWER AT THAT TIME, THE ENGINE/PROPELLER WERE SHUTDOWN/ FEATHERED. A NORMAL LANDING OCCURRED. AFTER UNCOWLING THE LT ENGINE, A HOLE WAS NOTED ABOVE NR 4 CYLINDER IN THE ENGINE CASE. NR 4 PISTON CONNECTING ROD WAS NOTED BROKEN IN HALF. THE ENGINE HAS NOT BEEN REMOVED FROM THE ACFT AS OF YET FOR FURTHER INVESTIGATION.

2010FA0000583

PIPER

LYC  

 

BLADE

FAILED

5/14/2010

PA32R301

IO540K1G5

 

F7663DR

PROPELLER

((ZY2R)) LOSS OF BLADE TIP IN-FLIGHT. IN FLIGHT, PILOT EXPERIENCED SUDDEN VIBRATION. AS HE WAS OVER AN AIRPORT, IMMEDATELY POWERED BACK AND LANDED THE ACFT APPROX 9 MINUTES LATER. AFTER GO AROUND ACFT INSP PILOT DISCOVERED 1 TIP MISSING FROM THE 3-BLADED PROP. ROCK, STONE OR OTHER FOD AT THE L/E OF THE BLADE, CAUSING STRESS RISER, BENDING AND TWISTING AND LOADS IN THIS AREA LEADING TO BLADE FAILURE.

2010FA0000596

PIPER

LYC  

SLICK

MECHANISM

BURNED

6/8/2010

PA32R301T

TIO540AH1A

 

 

LT MAGNETO

PILOT REPORTED ROUGH RUNNING ENGINE. AFTER INSPECTION OF BOTH MAGNETOS, IT WAS FOUND THAT THE INTERNAL PARTS WERE BURNED AND DETERIORATED. THIS CONDITION WAS FOUND AT 225 HRS AFTER THE 500 HR INSP. BOTH MAGNETOS DID OT REACH THE 500 HR INTERVAL.

2010FA0000597

PIPER

LYC  

 

MAGNETO

BURNED

6/8/2010

PA32R301T

TIO540AH1A

 

6360 

ENGINE

PILOT REPORTED ROUGH RUNNING ENGINE. AFTER INSPECTION OF BOTH MAGNETOS, IT WAS FOUND THAT THE INTERNAL PARTS WERE BURNED AND DETERIORATED. THIS CONDITION WAS FOUND AT 225 HRS AFTER THE 500 HR INSP. BOTH MAGNETOS DID OT REACH THE 500 HR INTERVAL.

2010FA0000705

PIPER

 

 

CONTROL CABLE

BROKEN

6/9/2010

PA34220T

 

 

62701129

ZONE 300

STABILATOR CONTROL CABLE, PN62701-129, FAILED IN FLIGHT. THE CABLE SEPARATED ON LANDING. THE PILOT WAS UNABLE TO FLARE RESULTING IN A HARD LANDING IN A NOSE LOW CONDITION. THERE WAS SUBSTANTIAL DAMAGE TO THE ACFT. THERE WAS NO CORROSION ON THE CABLE EITHER EXTERNALLY OR INTERNALLY. NO EVIDENCE OF CHAFING OR CABLE MISROUTING WAS EVIDENT. THE CABLE WAS SENT TO THE NTSB FOR LABORATORY ANALYSIS.

2010FA0000629

PIPER

LYC  

 

BOLT

BENT

2/15/2010

PA44180

O360*

 

 

DOWNLOCK HOOK

NLG DOWNLOCK HOOK BOLT, BENT.

2010FA0000635

QUEST

PWA  

 

STRUT

LEAKING

6/16/2010

KODIAK100

PT6A34

 

1004100100

NLG 

AFTER APPROX 65 HOURS SINCE THE NOSE STRUT WAS LAST RESEALED, IT WAS LEAKING BADLY AND NEEDED TO BE RESEALED AGAIN. HYD FLUID WAS COMING FROM THE LOWER GLAND OF THE TRUNNION SUGGESTING THAT THE BOTTOM POLY PACK SEAL WAS LEAKING. AFTER IT WAS DISASSEMBLED, THE SEAL WAS INSPECTED FOR DAMAGE, BUT THERE WAS NOTHING APPARENTLY WRONG. ON THE CHAMFERED EDGE OF THE BARREL, THERE WAS SOME BALL LIKE SUBSTANCE ALMOST LIKE IT WAS RESIDUAL MATERIAL THAT HAD ADHERED TO THE EDGE FROM THE CHROME-ING PROCESS. IT IS HARD TO TELL IF THE VERY SMALL BALLS OF CHROME COULD SCAR THE SEAL ENOUGH THAT IT STARTS TO LEAK AFTER BEING IN SERVICE FOR APPROX 50 HOURS. AFTER CLEANING UP THE BARREL AND LUBING, THE STRUT WAS REASSEMBLED AND SERVICED WITHOUT ANY FURTHER DEFECTS FOUND.

E81R_JW30282_3

RAYTHN

WILINT

 

CONTROL CABLE

SEIZED

6/14/2010

390  

FJ442A

 

1606450003

THROTTLE

(E81R) DURING REPLACEMENT OF RT ENG FWD POWER CONTROL CABLE ASSY FOR EXCESSIVE LEAKAGE IN CONJUNCTION WITH COMPLIANCE WITH SB 76-3907 FOUND NEW REPLACEMENT CABLE ASSY. SEIZED DURING INITIAL POST-INSTALLATION RIGGING CHECKS. REPLACED 1ST REPLACEMENT CABLE ASSY WITH 2ND REPLACEMENT CABLE ASSY. OPERATIONS AND RIGGING CHECKS NORMAL. CABLE ASSY BEING RETURNED TO AIRFRAME MFG FOR WARRRANTY EVALUATION. CABLE ASSY PN 390-389006-0015. MFG JANUARY, 2010.

2010FA0000628

RKWELL

PWA  

 

SKIN

CORRODED

6/15/2010

NA265

JT12A6

 

 

PAX DOOR

((KI2R)) IN THE PROCESS OF ACCOMPLISHING A PRE-FLIGHT INSPECTION, THE TECH FOUND CRACKING AS THE RESULT OF INNER-GRANULAR CORROSION ON THE DOOR IN THE AREA OTBD OF THE LWR DOOR STOP. PROBABLE CAUSE IS ACFT AGE AND NR OF LANDINGS. RECOMMEND DETAILED INTERNAL AND EXTERNAL VISUAL INSP OF THE ENTIRE AREA AT EACH 150 HR INSP, LOOKING FOR PAINT CONDITION AND ANY EVIDENCE OF SKIN DEFORMATION OR BULGING, ESPECIALLY AROUND RIVETS. SHOULD BE MADE AWARE TO LOOK THIS AREA OVER CAREFULLY WHEN THEY ACCOMPLISH THEIR PRE-FLIGHT INSPECTIONS.

2010FA0000636

ROBSIN

 

 

NUT PLATE

CORRODED

6/18/2010

R44RAVENII

 

 

MS21086L4

EMPENAGE

DURING ANNUAL INSPECTION NOTED WHAT APEARED TO BE RUST LOCATED NEAR THE UPPER VERTICAL STABILIZER ATTACH POINT. REMOVED UPPER STAB AND FOUND AFT LT NUTPLATE (MS 21086L4) SPLIT IN TWO. REPLACED SAME WITH PART FROM MFG. ALSO, REMOVED LOWER STAB AND INSPECTED REMAINING UPPER AND LOWER NUTPLATES. REPLACED ALL BOLTS AND SPACERS PRECAUTIONARY. MAY BE ISOLATED FAILURE. REF IPC FIG 2-9 WHERE NUTPLATE IS NOT LISTED BUT BOLT ITEM NR 4 WITH SPACER ITEM NR 3 WOULD SCREW INTO NUTPLATE.

2010F00156

SKRSKY

GE  

 

FIRE LOOP

FALSE ACTIVATION

7/10/2010

S61N

CT581402

 

3536200575

NR 1 NACELLE

THE NR 1ENGINE FIRE LIGHT ILLUMINATED UPON LANDING. ACFT COMPLETED ITS NORMAL LANDING WITH NO SECONDARY INDICATIONS, SHUTDOWN AND NOTIFIED MX. MX INSPECTED ACFT NOTING NO DAMAGE TO SYS. DURING TROUBLESHOOTING REPLACED DENTED FIRE LOOP, TESTED FIRE DETECTION SYS WHICH INDICATED PROPER WORKING CONDITION.

2010F00154

SNIAS

TMECA

 

CROSSTUBE

CRACKED

7/9/2010

AS350B2

ARRIEL1D1

 

350A41108702

MLG 

DURING ROUTINE 100 HR INSPECTION, FOUND MULTIPLE CRACKS IN THE AFT CROSSTUBE: RT SADDLE ATTACHING THE RT SKID TUBE. THE ACFT HAS NO HISTORY OR REPORTED INCIDENT THAT WOULD/COULD OF SUBJECTED THE CROSSTUBE TO DAMAGE.

2010FA0000585

SOCATA

PWA  

 

SHUTOFF VALVE

INTERMITTENT

11/6/2009

TBM700

PT6A66

 

4429B000001

CABIN PRESSURE

((X1IR)) ACFT OWNER COMPLAINED OF PRESSURIZATION PROBLEM AT FL 290 WHERE THE CABIN PRESSURE WOULD INTERMITTENTLY DROP FROM 6.2 TO 4.0 UPON INVESTIGATION, FOUND THE ACFT DID NOT SWITCH FROM 3.0 TO 2.5 BLEED AIR. CAUSE IS DETERMINED, DUE TO THE SHUTOFF VALVE HAVING A METALLURGICAL PROBLEM WHERE THE INTERNAL SHUTTLE VALVE SEPARATED, WHICH MADE THE PART NOT OPERATE PROPERLY. THIS PART OPERATES AUTOMATICALLY AND REQUIRES NO INPUT FROM THE ACFT OPERATOR.

2010FA0000532

STBROS

PWA  

 

LEVER

CRACKED

5/20/2010

SD360V200

PW530A

 

201116001

MLG 

DURING MX VISIT, A LARGE CRACK WAS DISCOVERED ON RT MLG LEVER. ISOLATED INCIDENT.

2010FA0000664

WACO  

 

 

FITTING

BROKEN

6/30/2010

YMF  

 

 

AN66534

VERTICAL STAB

HORIZONTAL AND VERTICAL STABILIZER FLYING WIRE TIE ROD BROKEN.