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

369

bald eagle watching over three eggs

APRIL

2009

 

 

CONTENTS

AIRPLANES

BEECH......................................................................................................................................... 1

CESSNA...................................................................................................................................... 3

MITSUBISHI............................................................................................................................... 8

PIPER........................................................................................................................................... 9

HELICOPTERS

HILLER........................................................................................................................................ 9

ACCESSORIES

CHAMPION................................................................................................................................ 9

AIR NOTES

INTERNET SERVICE DIFFICULTY REPORTING (iSDR) WEB SITE................................... 10

IF YOU WANT TO CONTACT US......................................................................................... 11

AVIATION SERVICE DIFFICULTY REPORTS...................................................................... 11

 

 

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

AVIATION MAINTENANCE ALERTS

The Aviation Maintenance Alerts provides a common communication channel through which the aviation community can economically interchange service experience, cooperating in the improvement of aeronautical product durability, reliability, and safety. This publication is prepared from information submitted by those who operate and maintain civil aeronautical products. The contents include items that have been reported as significant, but have not been evaluated fully by the time the material went to press. As additional facts such as cause and corrective action are identified, the data will be published in subsequent issues of the Alerts. This procedure gives Alerts’ readers prompt notice of conditions reported via a Malfunction or Defect Report (M or D) or a Service Difficulty Report (SDR). Your comments and suggestions for improvement are always welcome. 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

BEECH

Beech:  A200; Twisted Cabin Door Bellcrank; ATA 5210

A technician for an air taxi operation states, "During a routine, Phase 3 inspection the main cabin door aft up-lock bell crank was found twisted about 10 degrees from (that) of a new bell crank (P/N 50-430031-17).  The up-lock bracket pivot bolt (P/N NAS1103-21D) was also noted to be slightly deformed.  This (condition) was probably caused by the up-lock hook being (improperly) rigged.  All effected parts were replaced and the up-lock hooks were (then) able to be rigged properly."

(Slightly deformed?  Nice comparison photos.)

 

PHOTO DEFECTIVE BELLCRANK IS SHOWN BESIDE A NEW PART IN FOUR DIFFERENT VIEWS--CONFIRMING THE "TWISTED" CONDITION.

Part Total Time:  (unknown).

 

 

Beech:  B65-A80; Sheared Nose Gear Actuator; ATA 3220

"The nose landing gear would not deploy on approach to landing," says an air taxi submitter.  "After nose gear removal it was discovered that the nose gear actuator drive shaft (P/N 50-820218) internal spline was worn and sheared.  (Lubrication maintenance should be consistent...) to reduce wear."

Part Total Time:  4,383.0 hours.

 

Beech:  B200C; Cracked Wing Skin; ATA 5730

A mechanic states, "During a pre-flight inspection, maintenance technicians noted a 3.75 inch long crack in the right wing lower wing skin, just forward of the inboard section of the outboard flap.  Additionally, a support/anchor tab that attaches the lower wing skin to the inboard most flap-well rib of the outboard wing ...was found cracked through (failed).  We believe this tab failure allowed the skin to vibrate, generating rapid crack growth.  This crack is (positioned) directly aft of the lower aft wing bolt.  (It) had just appeared within the past two hours of flight time.  I can pin-point this time frame since the 5 year wing bolt removal and inspection process was completed just 2 flight hours ago.  No wing skin cracks were noted or documented at that time."  (R/H trailing edge lower wing skin P/N:  50-110027-15)

Part Total Time:  8,914.0 hours.

 

CESSNA

Cessna:  208; Chafed Engine Mount; ATA 7120

(This aircraft is being pulled by a Pratt & Whitney PT6A-114A.)

A mechanic writes, "During (this) aircraft's corrosion inspections, it was noticed that the air conditioning condenser duct clamp was cutting into the engine mount on the L/H truss.  The truss was also rubbing against the condenser duct.  There are four cuts measuring as follows (length x depth; respectively):  9/32 inch x .020—2 each; 7/32 inch x .010; 9/16 inch x .032.  I had determined the clamp was correctly installed, and that the part numbers are in accordance with the current Cessna 208 parts catalog.  The clamp, when installed on the engine mount, rubs against the truss and creates damage.  Cessna was notified by e-mail and (they) recommend using aluminum 'speed tape' under the clamp to reduce damage to the truss.  Cessna has not provided an official engineering analysis, and the recommendation was provided by e-mail.  This engine mount assembly was replaced.  We would like to see this clamp replaced by a more suitable clamp to prevent damage to the engine mount truss.  (Operators of...) the Cessna Caravan fleet should be notified of the possible unsafe condition created by the rubbing/cutting of the clamp, possibly causing failure of the engine mount."

(Engine mount P/N:  2651023-19.  A search of the FAA Service Difficulty Reporting System (SDRS) database reflects a second, very similar defect report. Readers should note part total time!)

Part Total Time:  575.2 hours.

 

Cessna:  208B; Burned Flap Motor Wires, ATA 2752

A mechanic writes, " We departed (our base) at approximately 8:30 local time.  The flaps were set at 10 degrees....  Take-off and climb were normal.  After about 10 to 15 minutes into the flight (with the autopilot engaged) we noticed a burning smell and saw a small amount of smoke—lasting for about a second or two.  We disengaged the autopilot and looked at the circuit breakers, noticing the stall warning circuit breaker had popped.  After returning to (base) we found several circuit breakers had popped and that the flaps were inoperative, stuck at 10 degrees.  An avionics shop was contacted to look at the aircraft—they reported back the following (account)."

 

"A hidden damage inspection was performed.  Burned wires were found in the wire bundle running from the main flap motor to the circuit breaker panel and from the main flap motor to the ground block J66.  Insulation of adjacent wires along the same wire bundle were also found melted.  A loose ring terminal was found on the normally open terminal of the up limit switch on the flap actuator assembly.  The flap system was inspected for any defects structurally—none were found.  The flap actuator jackscrew exhibited no abnormal signs of wear—it rotated freely when checked with the primary motor removed.  Upon further investigation, it was found that the primary flap motor had failed, and the 10 amp primary flap circuit breaker had not tripped as it should have, causing the circuit to overload and melt the wire bundle.  The primary flap circuit breaker exhibited signs of overheating on the bottom surface of the plastic casing, and had a burned odor to it.  The primary flap motor looked good physically, but upon further investigation (opening the motor) it exhibited serious signs of overheating/burning inside the unit (this also having a very strong burned odor).  During the investigation to determine the severity of the damage caused by the failed circuit, it is estimated at least 70 to 75 percent of the wire insulation on the power wire to the primary flap motor had been melted/burned off of the wire, leaving a bare exposed wire throughout the cabin headliner.  The wire finally burned itself in half behind the circuit breaker panel about two inches from the J37 connector.  The following components were removed and sent to Cessna for investigation:  Flap actuator (P/N 9910586-3); Flap Circuit breaker (P/N S1232-510); Flap Control Relays K20 and K21 (P/N MS24187D1); and the Flap overhead Normal/Standby power switch (P/N MS25068-23).  We are waiting to hear from Cessna as to what was the root cause of this (defect)."

(This flap actuator/motor finds seven additional entries in the SDRS database.)

Part Total Time:  294.9 hours.

 

Cessna:  441; Secondary Bulkhead Cracks; ATA 5312

"During the SID (shaft inspection device) inspection," says an unknown submitter, "the fuselage bulkhead at the forward opening of the cabin door and secondary bulkhead were found cracked, buckled, and distorted.  (The only reason...) this was found was the SID inspection requires removal of the door bayonet receptacles for inspection, and (also) the removal of the interior sidewall upholstery."

 

 

PHOTO DOOR FRAME (BELL FRAME) MEMBER SHOWING THE PARTICULAR FEMAIL BAYONET SLOT AND ITS TWO POSSIBLE VIEWS: FORWARD OR AFT.

 

PHOTO CLOSEUP OF THE FORWARD SLOT AND ITS OUTSIDE CRACK.

 

A CLOSUP OF THE INSIDE OF THE ABOVE SLOT AND ITS INTERNAL CRACK.

 

AN AFT VIEW OF THE BUCKLED BELL FRAME.

 

AN AFT VIEW OF THE BUCKLED BELL FRAME WITH A MIRROR, SHOWING THE CRACKED MEMBER.

 

 

A CLOSEUP PICTURE OF THE ABOVE PICTURE "e."

 

(Bulkhead P/N 57111434345.  Nice camera/mirror work—Ed.)

Part Total Time:  7,246.0 hours.

 

MITSUBISHI

Mitsubishi:  MU2B25; Cracked Gearbox Housing; ATA 7210

A repair station technician writes, "A pilot reported low and fluctuating oil pressure from the left engine while in flight, and elected to shut the engine down.  An uneventful single engine landing was made (at a landing site).  The engine oil bypass valve was found to be in the 'popped' condition.  The oil filter was then removed—(it was observed) to be black in color, with the forward sealing surface broken in several small pieces.  The reduction gearbox was disassembled and the oil pump removed.  The forward (reduction gearbox) housing (P/N 3102047-4) was cracked approximately three inches radially at the forward detail."

(Oil Pressure pump assembly; Honeywell P/N 3103217-4; engine is TPE331-10AV-511M).

Part Total Time:  82.2 hours.

 

 

PIPER

Piper:  PA31T1; Improperly Manufactured Pneumatic Timer; ATA 3010

An unidentified submitter states, "These Pneumatic Control Timers (Lamar P/N 488-699) were purchased new...and when they were installed in the aircraft it was noted the surface deice boots were inflated (continuously) when the aircraft power was on.  A second timer unit was purchased and the same problem existed when it was installed.  Upon troubleshooting the system and verifying correct installation and wiring, it was found that two of the wires coming out of the unit were switched during manufacture and the boxes were operating opposite as is intended.  There are four wires:  red, black, white, and blue.  The white and blue wires are reversed."

Part Total Time:  0.00 hours.

 

HELICOPTERS

HILLER

Hiller:  UH-12E; Incorrect Transmission Retainer; ATA 6330

"(I) suspect this (defective retainer part) is locally made," says a repair station technician.  The installation word 'up' is not stamped on this part (retainer; P/N 23688) but is etched on by hand.  The thickness of this retainer is .045 inches—the actual part thickness of a new retainer is .051 inches.  (I) found shafts that are shimmed with bad retainers to be shimmed improperly due to (this) retainer thickness—as is required by the Hiller overhaul manual.  The shafts were out of tolerance by .014 to .020 inches."  (Transmission P/N: 23700-23.)

Part Total Time:  3,749.5 hours.

 

ACCESSORIES

CHAMPION

Champion Oil Filter Kit:  CFO100-1; Slipping Gasket; ATA 8550

(This oil filter kit fits a Lycoming O360A1F6D engine nestled under the cowling of a Cessna 177B.)

A private pilot provides the following report.  "During replacement of the canister-type oil filter at the time of oil change, it is tricky to achieve a good seal of the canister against the seat (with) the filter gasket that is supplied with the Champion CFO100-1 filter kit.  This gasket very easily slips inside the canister during tightening of the canister retainer bolt.  Extreme care must be taken to ensure it does not slip inside.  If it does slip, there is a strong oil leak during the run-up check.  This failure of proper gasket sealing has happened—not only to me as a (CFR) Part 91 private pilot changing my own oil, but also to both mechanics in the shop I use.  So far, removal, cleaning, and drying of the gasket has resulted in a good seal during reinstallation.  A better design could save us lost oil, and having to pay the mechanic for extra time and clean-up.  This has been an ongoing issue for at least three years."

(Good evaluation!  The SDRS program can use all the input from private pilots it can get—Ed.)

Part Total Time:  (n/a).

 

 

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 (SDR) System 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

CA090204009

 

 

WOODWARD

DRIVE ASSY

DAMAGED

2/3/2009

 

 

 

210625

OVRSPD GOVERNOR

DURING ENGINE CHANGE THE OVERSPEED GOVERNOR WAS REMOVED AND CHIPPED GEAR TOOTH WAS DISCOVERED. STATUS SHEET INDICATED THE GOVERNOR WAS INSTALLED 2006/05/26 AND HAS ACCUMULATED 2312.2 TIME SINCE OVERHAUL. THE ENGINE, THE GOVERNOR WAS INSTALLED ON, HAS BEEN SENT FOR OVERHAUL AS SCHEDULED AND THE OVERSPEED GOVERNOR HAS BEEN SENT FOR REPAIR.

CA090129002

 

 

 

TIRE

LEAKING

11/13/2008

 

 

 

0283353

MLG 

TIRE WAS FOUND LOW ON PRESSURE UPON DAILY INSPECTION. ATTEMPT TO INFLATE TO PROPER PRESSURE WAS DONE, BUT TIRE FAILED TO MAINTAIN PRESSURE. WHEEL ASSEMBLY REMOVED FROM SERVICE. FURTHER INSPECTION REVEALED THAT TIRE HAS PRESSURE LEAKS FROM AROUND BEADSEAT AREA ON INNER AND OUTER SIDES OF TIRE. ALSO DISCOVERED ON INSPECTION THAT LEAKS WERE DISCOVERED FURTHER UP THE SIDEWALL TO TREAD. ALSO THAT THIS TIRE IS A RECAPPED TIRE IN ITS 1ST SCHEDULED RECAP.

CA090129003

 

 

 

ACTUATOR

MISMANUFACTURED

1/29/2009

 

 

 

215900018

TRIM TAB ROTARY

AFTER THE INSTALLATION ON A CL415, THE ACFT TECH TESTED AND FOUND OUT THAT THE ROTATION WAS IN THE OPPOSITE DIRECTION FOLLOWING THE DEMAND. THEY INSTALLED A OTHER ONE AND EVERYTHING WENT RIGHT.

CA090119002

 

 

 

GEAR

LOOSE

1/8/2009

 

 

4373

K3822

 

THE DISTRIBUTOR FINGER WAS DISCOVERED LOOSE ON THE GEAR ASSEMBLY DURING SCHEDULED INSPECTION.

CA090225007

 

 

 

HEATER

CRACKED

2/24/2009

 

 

 

10585KFGH

FUEL/OIL

IT WAS NOTICED ON A RETURN FLIGHT THAT OUR AIRCRAFT HAD OIL STAINING AND LEAKAGE ON THE LOWER LEFT NACELLE AND LANDING GEAR. WHEN THE AIRCRAFT WAS TROUBLESHOT IT WAS FOUND THAT THE STEWART WARNER FUEL TO OIL HEATER WAS CRACKED ON THE CORNER EDGE RADIUS FOR ROUGHLY AN INCH IN LENGTH. IF YOU OBSERVE THE FOLLOWING PICTURES YOU CAN SEE THE BUBBLING FROM THE LEAK WHEN THE PART WAS PRESSURIZED.

CA090206008

 

 

 

STOP PIN

WORN

2/5/2009

 

 

 

 

MAGNETO

THE MAGNETO WAS REMOVED FOR A SCHEDULED MAINTENANCE CHECK ON THE DISTRIBUTOR BLOCK AND BRUSH ASSEMBLY. THE IMPULSE COUPLING STOP PIN WAS OBSERVED WORN BEYOND MANUFACTURERS LIMITS OF 0.050 INCH. MEASURED WEAR WAS 0.155 INCH MAGNETO HAS LESS THAN 30 HOURS SINCE NEW.

2009FA0000201

 

 

 

UNKNOWN

SMOKE

2/16/2009

 

 

 

 

CABIN & COCKPIT

ACFT ON GROUND RUNNING APU FOR ABOUT 3 HOURS BEFORE DEPARTURE. ON TAKEOFF, SMALL AMOUNT OF SMOKE IN CABIN AND COCKPIT. RETURNED TO AIRPORT AND LANDED. PERFORMED AN INSP OF APU AREA AND FOUND SMALL AMOUNT OF OIL IN AREA. PERFORMED GROUND POWER ENGINE RUNS AND NO SMOKE NOTED. PERFORMED OPS FLIGHT TO CHECK SYS. SYSTEM CHECKED OK. NO SMOKE NOTED. (K)

2009FA0000223

 

 

 

FITTING

DEFECTIVE

3/1/2009

 

 

 

AN9161D

HYDRAULIC SYS

FOUND THESE FITTINGS AN-916 1D TO BE DEFECTIVE. THE FITTINGS WERE BEING USED ON A HYDR SYS WITH A LOW PRESSURE OF 1,100 PSI. WHEN ASSEMBLED ORIGINALLY THE FITTINGS WERE ASSEMBLED WITH A LIGHT COAT OF FUEL LUBE. WHEN FOUND TO LEAK, THE FITTING ASSY WAS REMOVED, TIGHTENED AND REASSEMBLED. ONCE AGAIN, WE HAD A LEAK. STATED TIGHTENING EACH FITTING OF A RUGN AND THEN PLACED ON A HAND PUMP HYD MULE. EACH TIME IT LEAKED. HAD (1) SPARE SET OF FITTINGS, MADE UP THE SAME ASSY AGAIN AND THIS TIME BEGAN TO GO PAST WHAT WAS CONSIDERED A REASONABLE AMOUNT OF TORQUE FOR THE ASSY. USING THE SAME PROCEDURE OF TIGHTENING THE FITTING A TURN AND PUTTING IT BACK ON THE MULE. EACH TIME FLUID STARTED COMING OUT AROUND BOTH SIDES OF THE FITTING AT LESS THAN 200 PSI. BOTH ASSYS WERE MADE USING THE AN-9161D WITH A AN8164D ON ONE SIDE AND AN AN8254D ON THE OTHER. THESE WERE INSTALLED ON THE PLANE WHEN LEAKS WERE DISCOVERED. THE OTHER ASSY WAS MADE UP OF THE SPARE THAT WAS ORDERED USING THE SAME PARTS AS THE FIRST ASSY. ALL 3 FITTING LEAK AROUND BOTH SIDES OF THE AN916-1D. THE LAST FITTING ASSEMBLED WAS OVER TIGHTENED TO SEE IF LEAK WOULD STOP. RAN OUT OF MALE THREADS BEFORE LEAK WOULD STOP. SEEMS LIKE THE PIPE THREAD TAP WAS RUN TOO FAR INTO THE FITTING DURING THE MFG PROCESS OR THERE IS NOT ENOUGH TAPER ON THE THREAD. HAVE LABELED THE FITTINGS 1-3. NR 1 IS THE FITTING ORIGINALLY INSTALLED ON THE PLANE WITH THE AN 816-4D. NR 2 IS THE ONE THAT WAS INSTALLED ON THE PLANE IN A LOWER PRESSURE AREA. NR 3 IS THE ONE ASSEMBLED AFTER AND KEPT TIGHTENING AND TESTING. NR 3 IS THE ONE THAT THE MALE THREADS WERE COMPLETELY RUN INTO ON BOTH ENDS. WAS UNABLE TO REMOVE THE AN-816-4D FROM THE NR 3. DISTRIBUTOR WHO SUPPLIED PARTS INFORMED MECH THAT HAD RECALLED PARTS FROM LOT NR THAT WAS TRYING TO BE PUT ON ACFT. LOT NR ON BAG. (K)

2009FA0000199

 

 

 

POINTS

DAMAGED

3/10/2009

 

 

 

 

MAGANETO

AT THE END OF THE 3 HOUR BENCH RUN FROM OVERHAUL AN INTERNAL INSP OF THE MAGNETO WAS ACCOMPLISHED. THE TIP OF THE TACHOMETER POINTS (10-400507) WAS FOUND IN THE COMPARTMENT. THE CONTACT BROKE OFF THE RIVET ON THE BREAKERS SPRING SIDE. THE CONTACTS WERE NEW WITH DATE STAMP TCM-0750 AND THE ONLY RUN TIME WAS ON THE BENCH. INSPECTION UNDER MAGNIFICATION WOULD INDICATE A JOINT FAILURE OF THE WELD BETWEEN THE RIVET AND SILVER CONTACT..

2009FA0000200

 

 

 

BULB

CORRODED

2/26/2009

 

 

 

4596 

LANDING LIGHT

HAVE FOUND (5) NEW 4596 LANDING LIGHT BULBS WITH CORRODED WIRE ATTACHMENT TERMINALS. CORROSION COLORING WAS EITHER WHITE OR GREEN, FLAKING TYPE POWDER. ALL BULBS WERE NEW IN BOX. TOO MUCH SOLDIER FLUX?

2009FA0000204

 

 

 

MAGNETO

UNSERVICEABLE

2/19/2009

 

 

 

1068255514

 

DATA PLATE INDICATES D-3000 MAGNETO, HOWEVER, MAGNETO HSG HAS BEEN POSITIVELY IDENTIFIED TO BE D-2000. HSG ALSO MODIFIED FOR D-3000 DISTRIBUTOR BLOCK. AD APPLYING TO D-2000 MAGNETO HSG ARE ELIMINATED WITH D-3000 HSG. USING THE D-2000 HSG IS POTENTIALLY DANGEROUS. AD APPLICABLE TO D-2000 HSG: 78-18-06, 80-17-14. THESE AD IF NOT COMPLIED WITH BECAUSE OF MISREPRESENTATION OF DATA PLATE COULD RESULT IN FAILURE OF MAGNETO. (K)

2009FA0000192

 

 

 

DISTRIBUTOR BLK

MISMANUFACTURED

3/9/2009

 

 

S6RN1225

ES10391586ES1034

MAGNETO

WE RECEIVED NEW DISTRIBUTOR BLOCK AND GEAR KIT FOR BENDIX MAG S6RN-1225.UPON ASSEMBLING THE GEAR AND DISTRIBUTOR BLOCK THE HIGH TENSION TERMINAL OF THE GEAR WAS FOUND TO BE RUBBING THE DISTRIBUTOR BLOCK AT THE TIMING MARK LOCATION ON THE BLOCK. THIS HAPPENED ON 4 OF THE 5 SETS OF PARTS WE RECEIVED. PARTS WERE TAGGED AND RETURNED TO VENDOR.

2009FA0000224

 

LYC  

 

NOZZLE

FAILED

3/12/2009

 

LTS101750B1

 

411109002

GP MODULE

ENGINE, SN: LE-45724AEF (REFERENCE WO NR 240967, SVS NR 45724E) WAS RETURNED TO THIS REPAIR STATION. WHILE ENGINE WAS OPERATIONAL THERE WAS A LOUD BANG JUST BEFORE THE ENGINE SHUT DOWN IN FLIGHT. THE AIRFRAME WAS A DUAL ENGINE DESIGN AND PILOT MANAGED TO PERFORM AN UNSCHEDULED LANDING (OEI) WITHOUT INJURIES OR DAMAGE TO THE ACFT. UPON DISASSEMBLY OF THE ENGINE AND SEPARATING THE POWER MODULES WE DISCOVERED THE GAS PRODUCER (GP) NOZZLE (PN 4-111-090-02, SN 972025600047 TSN 6650 HOURS) TO HAVE SEPARATED RADIALLY (ABOUT 270 DEGREES) ON THE CURL PORTION OF THE NOZZLE ASSEMBLY. WE ARE NOT CONCLUDING THIS AS THE CAUSE OF THE INCIDENT. WE ARE JUST REPORTING A PART CONDITION WE HAVE NOT WITNESSED BEFORE. UPON NOTIFYING THE ENGINE DESIGN HOLDER. WE WERE ASKED TO STOP ALL WORK AND TO SEND THE POWER MODULES TO THEM. WE PACKAGED AND SHIPPED THE POWER MODULES FOR FURTHER DISASSEMBLY AND INVESTIGATION.

CA090115009

 

LYC  

 

COUNTERWEIGHT

BROKEN

12/2/2008

 

TIO540J2BD

 

 

CRANKSHAFT

CRANKSHAFT COUNTERWEIGHT EAR FAILED CAUSING COUNTERWEIGHT TO PUNCTURE CRANKCASE.

2009FA0000251

 

PWA  

 

BLADES

CRACKED

3/25/2009

 

PT6A114

 

304574101

COMPRESSOR

DURING HOT SECTION INSP, 2 COMPRESSOR TURBINE BLADES, PN 3045741-01, WERE FOUND TO HAVE CRACKS IN THE T/E OF THE BLADE. THESE CRACKS WERE FOUND ABOUT HALF WAY UP THE T/E. ONE CRACK .3750 INCH IN LENGTH. THE OTHER WAS .1875 INCH IN LENGTH. CRACKS WERE FOUND BY FLUORESCENT PENETRANT INSPECTION. SB1703 WAS GOING TO BE COMPLIED WITH, BUT AFTER CRACKS WERE FOUND, ALL BLADES WERE SCRAPPED. COMPRESSOR TURBINE BLADES TIME SINCE NEW: 6940.1 TIME SINCE OVERHAUL: 1782.9

CA090210001

 

PWA  

 

TURBINE

FAILED

2/10/2009

 

PT6A65B

 

 

ENGINE

EIR PT6A 2009-014 INTERNAL ENGINE FAILURE. (TC NR 20090210001)

CA090219014

 

PWA  

 

WIRE HARNESS

DAMAGED

2/6/2009

 

PW206A

 

 

ENGINE

(CAN) SHORTLY AFTER T/O, THE ENGINE SUFFERED AN UNCOMMANDED DECREASE IN POWER. THE FLIGHT WAS ABORTED AND THE AIRCRAFT RETURNED TO BASE WITHOUT INCIDENT. THE DECREASE IN POWER WAS COMPENSATED BY THE OTHER ENGINE AND AT NO TIME DID THE ENGINE REVERT TO MANUAL NOR WAS THERE ANY FAULT INDICATED ON THE COCKPIT DISPLAY. TROUBLESHOOTING LED TO THE REPLACEMENT OF THE ENGINE HARNESS DUE TO AN ERRATIC TORQUE SIGNAL. POST REPLACEMENT GROUND CHECKS AND TEST FLIGHT WERE ALL NORMAL. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.

2009FA0000232

 

PWA  

 

SEAL

CRACKED

2/13/2009

 

PW4090

 

56H192

COMPRESSOR

SUBJECT ENGINE WAS RECEIVED DUE TO HIGH TIME. DURING DISASSEMBLY AND INSP OF THE HPC THE DIFFUSER AIRSEAL PN 56H192, SN CENCBG1041 WAS FOUND WITH LINEAR CRACKS IN THE BOLT HOLE FLANGE ID, IAW CIR MANUAL PN 51A750 INSP CHECK 02 (NDI) NO CRACKS ARE ALLOWED. ENGINEERING INVESTIGATING. (K)

CA090122008

 

RROYCE

RROYCE

INSERT

PULLED

1/21/2009

 

DART5342

 

KB6831

 

AFTER TAKEOFF AT 200 FT AGL, THE RT ENGINE LOST OIL PRESSURE. THE CREW SHUT DOWN THE ENGINE AND DECLARED AN EMERGENCY AND RETURNED TO THE AIRPORT. UPON INVESTIGATION, MAINTENANCE FOUND THE WHEELCASE SCAVENGE FILTER LYING IN THE BOTTOM OF THE COWL. THE FILTER WAS COMPLETE WITH THE SINGLE ATTACHMENT BOLT. ATTACHED TO THE BOLT WAS THE INSERT THAT CONTAINED THE THREADS TO WHICH THE BOLT THREADS. IN SHORT, THE INSERT PULLED OUT OF THE CASING CAUSING THE FILTER TO COME OUT AND DEPLETING ALL ENGINE OIL. THE INCIDENT WILL BE PUT THROUGH THE COMPANY SMS SYSTEM FOR ACTION.

2009FA0000070

AEROSP

 

 

LANDING GEAR

MALFUNCTIONED

2/7/2009

AS365N2

 

 

 

 

RT LANDING GEAR WOULD NOT LOCK DOWN. PILOT RETURNED TO DEPARTURE WHILE TROUBLESHOOTING ISSUE AND EXECUTING EMERGENCY CHECKLIST. ADDITIONAL TROUBLESHOOTING OVER RADIO WITH PILOT AFTER CONSULTING WITH MX. GEAR WOULD NOT LOCK IN FULL DOWN AND LOCK POSITION. ELECTED TO HAVE SOMEONE TRY TO PULL THE GEAR DOWN WHILE THE PILOT HOVERED. DID EXTENSIVE COORDINATION PRIOR TO THE ATTEMPT AND WAS SUCCESSFUL. GEAR LOCKED DOWN AND ACFT WAS TOWED TO THE HANGAR.

CA090209002

AEROSP

PWA  

 

TAB  

WARPED

1/19/2009

ATR42300

PW120

 

S5547900090010

RUDDER ASSY

WE HAVE BEEN EXPERIENCING A VIBRATION DURING DESCENT. AFTER SUBSTANTIAL INSPECTIONS, TESTING AND CONSULTATION WITH ATR, A CHECK WAS CARRIED OUT TO MEASURE THE SPRING TAB FOR WARPAGE. THE RESULTS WERE SENT TO ATR FOR ANALYSIS. THE WARPAGE LIMITS WERE DEEMED OUT OF LIMITS. THE SPRING TAB WAS REPLACED AND THE VIBRATION CEASED DURING SUBSEQUENT FLIGHTS.

CA090122011

AEROSP

PWA  

AEROSP

FITTING

OVERTORQUED

1/22/2009

ATR42300

PW120

1005383Y00

ER804D060604

 

ON TWO SEPARATE OCCASIONS WHILE PERFORMING UNSCHEDULED MAINTENANCE INVOLVING THE MLG SELECTOR VALVE , TWO ALUMINUM HYDRAULIC FITTINGS HAVE BEEN FOUND DAMAGED OR CRACKED (1) OCT 27, 2008 - WHILE TROUBLESHOOTING A REPORTED HYDRAULIC LEAK UNION P/N MS21902D6 HAD A DAMAGED FLARE. (2) JAN 9, 2009, WHILE REPLACING THE MLG SELECTOR VALVE REDUCER P/N ER804D060604 WAS FOUND CRACKED. SUSPECT THAT THESE FITTING HAVE BEEN OVER TORQUED CAUSING DAMAGE AND STRESS CRACKS.

CA090218004

AEROSP

PWA  

 

TURBINE BLADES

DAMAGED

2/2/2009

ATR72

PW124B

 

 

LT ENGINE

DURING ENGINE RUN-UP AFTER C CHECK CREW HEARD LOUD BANG FROM LT ENGINE. THIS OCCURRED BETWEEN 70 PERCENT AND 60 PERCENT TQ, DURING PL REDUCTION FROM 80 PERCENT TQ TO GI. AFTER SHUT DOWN, VISUAL INSPECTION REVEALED HEAVY DAMAGE ON THE 2ND STAGE POWER TURBINE, IMPACT DAMAGE ON THE EXHAUST PIPE AND PROPELLER COULD NOT BE ROTATED MANUALLY. METAL DEBRIS WAS FOUND APPROX 20M BEHIND THE ENGINE. THE ENGINE WILL BE BOROSCOPE TO ACCESS INTERNAL DISTRESS. P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.

CA090219015

AEROSP

PWA  

 

COMBUST CHAMBER

DAMAGED

2/10/2009

ATR72212

PW127

 

 

ENGINE

(CAN) DURING CRUISE, THE CREW NOTED MAIN OIL PRESSURE FLUCTUATION WHICH WAS SHORTLY FOLLOWED BY A LOUD NOISE AND A LOSS OF POWER. THE ENGINE WAS SHUTDOWN AND THE FLIGHT WAS DIVERTED, WHERE A SINGLE ENGINE LANDING FOLLOWED. POST FLIGHT INSP, FOUND OIL COVERING COWLINGS AND MAJOR METALLIC CONTAMINATION OF THE TURBOMACHINE CHIP DETECTOR. THE ENGINE WILL BE REPLACED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.

2009F00023

AIRBUS

 

 

BEARING

GALLED

2/23/2009

A300*

 

 

 

BOOST PUMP MOTOR

BOOSTER PUMP CIRCUIT BREAKER POPPED, FOUND THAT THE ELECTRICAL MOTOR MAIN SHAFT BRG WORN TO ALLOW IMPELLER TO HIT DIFFUSER CASE, ALLOWING GALLING OF METAL TO METAL, HEATING AND STOPPING PUMP MOTOR. MODIFICATION OF PUMP TO 2052C23 IMPROVES BEARINGS.

2009F00022

AIRBUS

 

INTERTECHNIQ

MOTOR

WORN

1/23/2009

A300*

 

MT1840

MT1840

BOOST PUMP

BOOSTER PUMP CIRCUIT BREAKER POPPED, FOUND THAT THE ELECTRICAL MOTOR MAIN SHAFT BEARING WORN TO ALLOW IMPELLER TO HIT DIFFUSER CASE, ALLOWING GALLING OF METAL TO METAL, HEATING AND STOPPING PUMP MOTOR. MODIFICATION OF PUMP TO 2052C23 IMPROVES BEARINGS.

CA090216004

AIRBUS

CFMINT

 

HOSE

LEAKING

2/13/2009

A320214

CFM565B4P

 

AE7074221

FUEL SYSTEM

(CAN) WHILE TAXING ONTO GATE, MX NOTICED FUEL COMING OUT FROM THE COWLING. CLOSER INSP REVEALED THE OUTER SLEEVE OF THE FLEXIBLE HOSE TO THE LOW PRESSURE PUMP WAS TORN DUE TO AN INTERNAL LEAK BETWEEN THE INNER LINER AND THE STAINLESS STEEL BRAIDING. THIS WAS A PRE SB RA320735 HOSE ASSY. THE HOSE WAS REPLACED.

2009FA0000197

AIRTRC

PWA  

HAMSTD

SHAFT

SHEARED

3/9/2009

AT301

R1340AN1

 

 

COUNTERWEIGHT

AT THE TRANSITION FROM DECENT TO LEVEL FLIGHT ON A SEEDING PASS, PROP RPM WAS INCREASED AND A VIBRATION WAS FELT. AS THE THROTTLE WAS ADVANCED THE VIBRATION INCREASED DRAMATICALLY. THE ACFT WAS FORCED TO LAND AND AT LOW SPEED, FLIPPED OVER AS IT BROKE THROUGH A FOOT OF SNOW. ON SCENE INVESTIGATION REVEALED THAT ONE OF THE COUNTERWEIGHT BEARING SHAFTS HAD SHEARED, AND WAS NO LONGER PENETRATING THE PROPELLER BLADE.

2009FA0000181

AIRTRC

 

AIRTRC

RIB  

CRACKED

3/5/2009

AT802A

 

 

204031

WING ASSY

DURING ANNUAL INSP, NUMEROUS CRACKED L/E RIBS WERE FOUND BETWEEN 66.3750 INCH TO 173.7500 INCH ON THE LT WING AND 86.6250 INCH TO 201 INCHES ON THE RT WING. THESE CRACKS WERE IN THE RIB BODY AND RAN ALONG THE UPPER SKIN ATTACH FLANGE. THE CRACKS STARTED AT THE AFT END OF THE FLANGE. LENGTHS WERE BETWEEN .0625 INCH TO .5 INCH. CORRECTIVE ACTION WILL CONSIST OF INSTALLING P.N 21062-(1 OR 2) AND P.N. 21068-(1 OR 2) DOUBLERS IAW DRAWING 21065 REPAIR - LE RIB - 802 AFTER THE INSTALLATION OF ADDITIONAL INSPECTION HOLES IAW DRAWING 21066 INSTALLATION - ADDITIONAL INSP. PLATE - WING L/E - 802.

2009FA0000231

AMD  

PWC  

 

FEEDER CABLE

SHORTED

3/16/2009

FALCON

PW307A

 

 

NR 2 GENERATOR

ON ACFT, ACCOMPLISHING SB 7X-106 DRAFT 1 TITLED "ELECTRICAL POWER-PRIMARY DC GENERATION SYS INSP OF THE RT MAIN FEEDER GENERATOR 2 INCH. THE BLACK BOOT WHICH SURROUNDS THE FWD FEEDER CABLE FEED THROUGH CONNECTION AT FR46LH SIDE WAS FOUND SLIGHTLY MELTED ON THE TOP SIDE. (PG8 FG 2 OF SB) THE CUSTOMER OF THE ACFT THEN WANTED A FULL INVESTIGATION OF FEEDER CONNECTION AT FR 46 WITH THE ENGINE REMOVED. AFTER THE ENGINE REMOVAL THE MAIN WIRE FEED-THROUGH CONNECTOR AT FR 46 WAS DISSEMBLED. ARCING AND OVERHEATING WAS FOUND UNDER THE FWD LUG CONNECTION AND FEED THROUGH ASSEMBLY. ALL FINDINGS WERE REPORTED TO MFG ENGINEERING. REPAIR/ REPLACEMENT OF THE NR 2 POWER FEEDER CABLE FROM FR41 POWER DISTRIBUTION BOX TO THE FR 46 BULKHEAD CONNECTOR WITH A NEW DESIGNED FR 46 BULKHEAD CONNECTOR WAS ACCOMPLISHED IAW MFG TECH INSTRUCTIONS TI-7X-R0032-M. ALL OF THE ABOVE ACCOMPLISHED AT SERVICE CENTER. DURING AN 1A INSP.

BKEA200902160

AMD  

 

 

WINDSHIELD

FAILED

2/16/2009

FALCON50MYST

 

 

MY20268109

COCKPIT

WHILE FLYING, CO-PILOT`S FWD WINDSHIELD SHATTERED. RETURNED TO DEPARTURE AIRPORT. (K)

2009FA0000121

AMD  

 

 

LIFE RAFT

INOPERATIVE

2/25/2009

FALCON50MYST

 

 

100118305

CABIN

DURING ANNUAL INSPECTION TO TWO 4-MAN LIFE RAFTS, BOTH LIFE RAFTS WERE FOUND TO HAVE THEIR COMPRESSED GAS CYLINDERS DEPLETED OF ALL STORED GAS PRESSURE. NEITHER RAFT WOULD HAVE WORKED IF NEEDED IN AN EMERGENCY. BOTH RAFTS WERE STILL COMPLETELY PACKED AND APPEARED TO BE UNDISTURBED AFTER THEIR LAST MX. (MAY 2008).

2009FA0000068

AYRES

 

 

CHANNEL

CRACKED

2/5/2009

S2RT15NORMAL

 

 

10962T001

ZONE 200

UPON REMOVAL OF THE HORIZONTAL STABILIZER, IT WAS NOTED THE FUSELAGE ATTACH FITTING CHANNEL APPARENTLY HAD BECOME FILLED WITH WATER, FROZE AND BURST. A (3) INCH CRACK ACROSS THE SPAN OF THE ATTACH FITTING SHOWED SIGNS OF BULGING OUTWARD. INSPECTION IN THIS AREA IS LIMITED WITHOUT STABILIZER REMOVAL.

2009FA0000067

AYRES

 

 

ATTACH FITTING

LOOSE

2/5/2009

S2RT660

 

 

952675

VERTICAL STAB

UPON REMOVAL OF VERTICAL FIN FROM HORIZONTAL STABILIZER FOR ROUTINE MX, THE VERTICAL FIN ATTACH BRACKET IN THE STABILIZER WAS FOUND LOOSE AND HAD ELONGATED MOST ALL OF THE MOUNTING HOLES IN THE STABILIZER SPAR. WITH THE TAIL FULLY ASSEMBLED, NO LOOSENESS HAD BEEN NOTED. THIS AREA HAD NEVER BEEN ACCESSED, THE LOOSENESS CAME FROM IMPROPER TORQUE FROM THE FACTORY AT ASSY.

CA090121005

BBAVIA

LYC  

 

CRANKSHAFT

CORRODED

1/19/2009

8GCBC

O360C2A

 

05K22806

ENGINE

(CAN) UPON DESLUGING THE INNER BORE OF THE CRANKSHAFT, IT WAS DISCOVERED THAT THE PID COATING HAD BEGUN TO BUBBLE AND CHIP OFF. THE PID WAS REMOVED AND SURFACE CORROSION WAS DISCOVED UNDER THE PID SIMMILAR TO THAT REFERENCED IN AD 980208 AND SB 505B. IT SHOULD BE NOTED THAT THERE IS ONLY ONE CALANDER YEAR ON THIS ENGINE SINCE OVERHAUL.

CA090223015

BBAVIA

LYC  

 

CRANKSHAFT

CORRODED

2/23/2009

8GCBC

O360C2E

 

13B2712185

ENGINE

UPON REMOVAL OF THE EXPANSION PLUG TO FACILITATE SLUG REMOVAL IT WAS DISCOVERED THAT THEIR WAS BUBBLING IN THE PID. BASED UPON PREVIOUS EXPERIENCE WITH THIS PROBLEM ON OTHER AIRCRAFT THE PID COATING WAS REMOVED AND PITTING SIMILAR TO THAT FOUND IN SERVICE BULLETIN NR 505B WAS FOUND.

CA090209005

BEECH

PWA  

 

FUEL DIVIDER

LEAKING

1/22/2009

100BEECH

PT6A28

 

 

RT NACELLE

AIRCRAFT RETURNED TO BASE NOTING HIGH FUEL CONSUMPTION ON RT ENGINE. AFTER LANDING LARGE AMOUNT OF FUEL NOTED LEAKING FROM RT NACELLE. FUEL LINE WAS RUPTURED FROM FCU TO START CONTROL. REF SDR 20080513005, 20080211006 AND 20080521010. THIS WAS THE FOURTH LINE FAILURE. AIRCRAFT RETURNED TO SERVICE WITH A LINE REMOVED FROM A SPARE ENGINE. AFTER INVESTIGATION FOUND NR 2 BEARING TO HAVE EXCESSIVE MOVEMENT AND NR 2 BEARING SEAL LEAKING. ENGINE WAS REMOVED AND REPLACED WITH OVERHAULED ENGINE. IT IS THOUGHT THE VIBRATION FROM THE NR 2 BEARING CAUSED A VIBRATION THAT RESONATED THROUGH THE LINE CAUSING THE LINE TO FAIL.

CA090220004

BEECH

PWA  

 

TURBINE BLADES

ERODED

1/2/2009

1900C

PT6A65B

 

310830101

GAS GENERATOR

THE TREND MONITORING PROGRAM STARTED TO SHOW SIGNS OF HOT SECTION DISTRESS ON THE GRAPHS. BOROSCOPE INSPECTION REVEALED SOME EROSION AND IMPACT DAMAGE ON THE CT BLADES. AN HOT SECTION INSPECTION WAS CARRIED OUT AND THE COMPONENTS REPLACED. WHEN THE CT BLADES AND STATOR WAS INSPECTED AT THE APPROVED OVERHAUL FACILITY IT WAS DETERMINED THAT THE DAMAGE WAS CONSISTENT WITH EXCESSIVE CARBON ERODING THE TURBINE WITH IMPACT DAMAGE FROM LARGER PIECES OF CARBON WHICH DETACHED FROM THE COMBUSTION LINER. THE COMBUSTION LINER HAD ALSO BEEN REPLACED AT THE HOT SECTION INSPECTION DUE TO EROSION. THE MANUFACTURER HAS NOT SEEN THIS TYPE OF DAMAGE BEFORE ON THIS TYPE OF ENGINE.

2009FA0000250

BEECH

 

 

DOUBLER

CORRODED

3/24/2009

1900D

 

 

 

ZONE 100

DURING SCHEDULED INSP, NOTED CORRODED STEEL DOUBLER INSTALLED UNDER 13R STRINGER AFT OF FS 557.5 AFT PRESSURE BULKHEAD FRAME. STEEL DOUBLERS OR SHIMS NOT TYPICALLY INSTALLED, THIS LOCATION, NOT NOTED IN IPC OR SRM. INSTALLATION INFORMATION NOT AVAILABLE FROM OPERATOR. REMOVED AREA OF STRINGER 13R AS REQUIRED FOR REPAIR ACCESS AND REMOVED STEEL DOUBLER. VISUAL INSP OF AREA FOR CRACKING, EXCESSIVE STRINGER INSTALLATION GAP, ETC. OK. REPAIRED CORROSION AS REQUIRED AND INSTALLED SPRINGER SPLICE REPAIR IAW 1900 SERIES SRM 51-70-01.

CA090216005

BEECH

PWA  

 

BEARING

LACK OF LUBE

1/27/2009

1900D

PT6A67D

 

1368520629

MLG WHEEL

(CAN) RT MLG, INBD MAIN WHEEL ASSY FELL OFF DURING TAKEOFF ROLL. REFER TO CADOR 2009C0229. INITIAL INVESTIGATION DETERMINED BEARING FAILURE, BEARING NOT AVAILABLE TO INSPECT, SUSPECTED CAUSE - BEARING LUBRICATION. MLG ASSY REMOVED AND REPLACED WITH NEW. FAILED MLG AND WHEEL ASSY SENT TO TSB FOR FURTHER INVESTIGATION.

CA090121006

BEECH

PWA  

 

STRINGER

CRACKED

1/19/2009

1900D

PT6A67D

 

11444000033

FUSELAGE

(CAN) DURING 6TH, 200HR INSP, NOTED STRINGER P/N 114-440000-33 CRACKED ON AFT END APPROX. 3 INCHES LONG. THIS STRINGER IS LOCATED IN THE AFT FUSELAGE ASSY. AND SOME OF THE ANCHOR NUTS FOR THE LT STABILON ARE ATTACHED TO THIS STRINGER. THE STRINGER ON THE RT SIDE WAS INSPECTED AND NO FAULTS FOUND. STRINGER REPLACED WITH NEW.

CA090219006

BEECH

PWA  

 

BLEED VALVE

SEIZED

2/17/2009

200BEECH

PT642A

 

312312201

COMPRESSOR

(CAN) WHEN WE REPLACED THE HIGH PRESSURE COMPRESSOR BLEED VALVE FOR TOUBLESHOOTING, THE OVERHAULED UNIT THAT WAS INSTALLED CAUSED THE ENGINE TO HAVE SEVERAL COMPRESSOR STALLS AT IDLE. THE OVER HAULED BLEED VALVE WAS REMOVED FROM THE ENGINE AND EXAMINED. NOTICED THAT THE PISTON IN THE BLEED VALVE WAS SEIZED IN THE CLOSED POSITION, THE HSG WAS ASSEMBLED USING SILICONE SEALER AND SOME OF IT GOT ON TO THE PISTON. THE VALVE HAD BEEN OVERHAULED ON NOV 2005 AND HAD NEVER BEEN INSTALLED.

CA090219007

BEECH

PWA  

 

BLEED VALVE

SEIZED

2/17/2009

200BEECH

PT642A

 

310092302

COMPRESSOR

(CAN) REPLACED THE LOW PRESSURE COMPRESSOR BLEED VALVE FOR TROUBLE SHOOTING, THE OVERHAULED UNIT THAT WAS INSTALLED CAUSED THE ENGINE TO HAVE SEVERAL COMPRESSOR STALLS AT IDLE. THE OVERHAULED BLEED VALVE WAS REMOVED FROM THE ENGINE AND EXAMINED. NOTICED THAT PISTON IN THE BLEED VALVE SEIZED IN THE CLOSED POSITION, THE VALVE HSG WAS ASSEMBLED USING SILICONE SEALER AND THE SPRINGS WERE BROKEN INSIDE. THE VALVE HAD BEEN OVERHAULED ON NOV 2005 AND HAD NEVER BEEN INSTALLED.

2009FA0000239

BEECH

PWA  

 

BEARING

WORN

3/20/2009

200BEECH

PT6A41

 

 

BELLCRANK

THE BUSHING PN 101-521046-5 THAT HOLDS THE BEARING PN4A INSIDE THE RT AILERON BELLCRANK PN 101-521046-3 WAS FOUND LOOSE IN THE BELLCRANK AND INDUCED A LOSS MOTION OF APPROX .75 INCH AT THE T/E WITH THE RIG PINS INSTALLED.

CA090210003

BEECH

PWA  

 

RHEOSTAT

UNSERVICEABLE

2/4/2009

200BEECH

PT6A41

 

CM39569

COCKPIT LIGHTS

THE SIDE PANEL LIGHTING WOULD NOT WORK UNTIL THE RHEOSTAT KNOB WAS PULLED. WHEN THE KNOB WAS WIGGLED A CRACKLING SOUND COULD BE HEARD. THE RHEOSTAT WAS REPLACED AND OPERATED NORMALLY. THE OLD RHEOSTAT HAD BEEN REPLACED FEB 2/09.

2009FA0000079

BEECH

PWA  

 

DUCT

CRACKED

2/3/2009

200CBEECH

PT6A42

 

1019100491112

ZONE 400

DURING REPLACE OF THE RT ENGINE, AFT LOWER COWLING FWD BULKHEAD P/N 101-910038-3, CRACKS WERE DISCOVERED IN THE LT AND RT COWLING AFT DUCTS P/N 101-910049-11 AND 101-910049-12 UPPER MOUNTING FLANGES. THIS AREA IS ONLY ACCESSIBLE BY REMOVING THE PANEL (DOOR) PN 101-910049-47 LOCATED IN THE CTR OF THE AFT COWL DUCT ASSY AND USING A BRIGHT LIGHT AND A MIRROR OR BY USE OF A BORESCOPE. THIS PROBLEM WAS DISCOVERED ON A HIGH TIME ACFT WITH 9010 HOURS TT IN SERVICE, BUT THE CONDITION COULD BE PRESENT ON LOWER TIME ACFT. RECOMMEND THIS AREA BE INSPECTED DURING A 'DETAILED ENGINE INSP' SUCH AS A PHASE 4 OF THE ACFT RECOMMENDED INSP PROGRAM.

CA090209004

BEECH

PWA  

 

WINDSHIELD

CRACKED

2/8/2009

300BEECH

PT6A60A

 

10138402523

COCKPIT

IN CRUISE FLIGHT, THE LT WINDSHIELD CRACKED. THE CREW LOWERED THE CABIN DIFFERENTIAL TO 4 PSI AND CONTINUED TO DESTINATION.

2009FA0000081

BEECH

 

 

CONNECTOR

DIRTY

2/17/2009

400A

 

 

 

 

FOUND RUDDER TRIM INOPERATIVE DURING "A" AND "B" INSPECTION OP CHECKS. FOUND CORROSION ON RUDDER TRIM CONTROL SYS WIRING LINE FILTER, REF. DESIGNATOR C004. CLEANED AND REINSTALLED WIRING CONNECTIONS ON LINE FILTER ASSY. RUDDER TRIM SYS FUNCTIONAL CHECKS NORMAL.

2009FA0000101

BEECH

 

 

MOUNT

DAMAGED

2/24/2009

400A

 

 

 

ENGINE

DURING SCHEDULED INSP, FOUND RT FWD ENGINE MOUNT ATTACH BRACKETS, P/N 45A34361-004 AND P/N 45A34361-006, HAD UPPER PORTIONS CUT INTO BY REPAIR ANGLE INSTALLED ON RT ENGINE UPPER INBD COWL PANEL AND ADJACENT EDGE OF COWL PANEL EDGE CHANNEL. REPAIR ANGLE WAS INSTALLED IAW DER-APPROVED EA NR 01-00176 DATED 11/12/2000. REPAIR HAD BEEN INSTALLED 11/14/2000 AND 3936.4 HRS. PREVIOUSLY. NUMEROUS OTHER SRM AND DER-APPROVED REPAIRS PERFORMED SUBSEQUENT. ACFT HAD BEEN THROUGH NUMEROUS A, B, C, AND D INSPECTIONS AND ENGINE REMOVAL/INSTALLATIONS SINCE REPAIR INSTALLATION. TECHS AND INSPECTORS ARE CAUTIONED TO INSPECT AREAS OF POSSIBLE COWLING INTERFERENCE CLOSELY DURING SCHEDULED INSP AND ENGINE CHANGES WHEN ACCESS IS AFFORDED, ESPECIALLY ON OLDER, EARLIER SN WHICH TEND TO EXHIBIT COWL FIT PROBLEMS. THIS HAS BEEN ADDRESSED BY PREVIOUS MFG INFO, ESPECIALLY COMMUNIQUE NR 69, DATED 9/2004. EXPENSIVE AND TIME-CONSUMING REPAIRS INVOLVED REPLACING THE AFFECTED ENGINE MOUNT BRACKETS AND ENGINE REINSTALLATION, AFTER BLENDING AND RELIEVING THE INTERFERING COWLING AREAS. THIS SAME REPAIR MAY BE FOUND ON OTHER OLDER, EARLIER SN MODELS PREVIOUSLY OPERATED BY FLT OPTIONS.

2009FA0000098

BEECH

 

 

WIRE

MISREPAIRED

2/23/2009

400A

 

 

 

CABIN LIGHTS

DURING TROUBLESHOOTING OF INOPERATIVE CABIN COLD CATHODE ("FLUORESCENT") LIGHTING SYS, FOUND SEVERAL INCORRECT STANDARD BUTT SPLICE TYPE CONNECTORS IN HIGH VOLTAGE WIRING SPLICES. MFG COMMUNIQUÉ NR 28 AND OTHERS REFER TO THIS SUBJECT. HAVE PREVIOUSLY FOUND INCORRECT SPLICES DESIGNED FOR LOW VOLTAGE DC WHEN USED IN SHIELDED HIGH VOLTAGE AC WIRING TO MELT OR OVERHEAT AND CAUSE MINOR FIRES ABOVE THE HEADLINER AREA AND/OR CABIN SMOKE. RECOMMEND MFG ADD SPECIFIC WIRE SPLICE REPAIR INFORMATION TO THE APPLICABLE SECTION OF THE MM AND POSSIBLY ISSUE A ONE-TIME MANDATORY SB TO VERIFY CORRECT WIRING SPLICES INSTALLED IN CABIN LIGHTING HIGH VOLTAGE AC WIRING. INCORRECT REPAIRS SEEM TO OCCUR MORE FREQUENTLY WHEN INTERIOR REFURBISHMENT OR REPAIRS ARE ACCOMPLISHED BY FACILITIES OR PERSONNEL UNFAMILIAR WITH SYS REPAIR WIRING USING COMMON SHOP MATERIALS.

CA090224004

BEECH

PWA  

 

ACTUATOR

FAILED

2/23/2009

65A90

PT6A20

 

5081016418

R MLG

(CAN) DURING A POST MAINTENANCE TEST FLIGHT THE LANDING GEAR WAS SELECTED DOWN, THE NOSE AND LEFT DOWN LIGHTS ILLUMINATED AND THE RIGHT STAYED OUT. TWO MORE GEAR CYCLES WERE PERFORMED, HOWEVER THE RIGHT DOWN AND LOCKED LIGHT FAILED TO COME ON. THE PILOT THEN PERFORMED A FLYPAST THE TOWER TO CONFIRM THE GEAR APPEARED TO BE DOWN PRIOR TO CONDUCTING AN UNEVENTFUL LANDING. A POST FLIGHT GEAR SWING WAS PERFORMED AND A LOUD SQUEALING NOISE WAS NOTED COMING FROM THE RIGHT MAIN GEAR ACTUATOR. THE ACTUATOR WAS EXCHANGED FOR ANOTHER UNIT AND THE AIRCRAFT RETURNED TO SERVICE. INSPECTION OF THE ACTUATOR REVEALED THE LOWER HOUSING BEARING WAS IN CONTACT WITH THE PINION GEAR CAUSING IT TO BIND. AN ADDITIONAL NOTE OF INTEREST IS THE ACTUATOR HOUSING WAS FILLED WITH WHAT APPEARS TO BE AEROSHELL 22 INSTEAD OF THE MOLYBDENUM DISULFIDE (MIL-G 21164) THAT IS CALLED UP IN THE COMPONENT MAINTENANCE MANUAL.

CA090120001

BEECH

PWA  

 

FLAP TRACK

CRACKED

1/15/2009

A100

PT6A28

 

501600183

TE FLAP

PILOT SELECTED FLAPS DOWN THEN NOTICED A ASYMMETRICAL FLAP CONDITION, FLAPS WERE SELECTED UP WHICH RESULTED IN THE CIRCUIT BREAKER POPPING. AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THAT THE LEFT OUTBOARD FLAP, INBOARD TRACK HAD FRACTURED NEAR THE TIP CAUSING THE FLAP ROLLER TO COME OUT OF THE TRACK (SEE ATTACHMENT). TRACK REPLACED AIRCRAFT INSPECTED AND RETURNED TO SERVICE.

CA090120003

BEECH

PWA  

BEECH

SWITCH

FAILED

1/14/2009

A100

PT6A28

EQUIPMENT

MS250261

 

THE AIRCRAFT DEPARTED FROM YAT AND AFTER REACHING CRUISE ALTITUDE, THE CREW NOTICED SMOKE IN THE CABIN. THE CREW ATTEMPTED TO RETURN TO YAT BUT THE FLAPS WOULD NOT EXTEND ON APPROACH. THE CREW DIVERTED TO YMO. THE FLAP CONTROL CIRCUIT BREAKER TRIPPED, THE SMOKE IN THE CABIN DISSIPATED AND THE AIRCRAFT LANDED SAFELY IN YMO WITH THE FLAPS UP. MAINTENANCE FOUND THAT THE RIGHT FLAPS HAD TRAVELED SLIGHTLY HIGHER THAN NORMAL. WHEN THE FLAP MOTOR AND GEARBOX WAS REMOVED SOME OF THE FLAP ACTUATOR DRIVE CABLES WERE FOUND DAMAGED. IT IS SUSPECTED THAT DUE TO THE EXTREME COLD TEMPERATURES OF THAT DAY, THE UPLIMIT MICROSWITCH DID NOT ACTUATE TO STOP THE FLAPS IN THE UP POSITION. THE FLAP MOTOR THEN CONTINUED TO OPERATE UNTIL THE POINT IT OVERHEATED AND CAUSED THE SMOKE IN THE CABIN AND DAMAGE TO THE DRIVE CABLES. ALL AFFECTED COMPONENTS ARE BEING INSPECTED AND REPLACED AS NECESSARY PRIOR TO RETURNING THE AIRCRAFT TO SERVICE.

2009FA0000208

BEECH

 

 

BELLCRANK

CORRODED

2/26/2009

A36  

 

 

355211588

ELEVATOR

WHILE PERFORMING SB 27-3935 ELEVATOR BELLCRANK BRG REPLACEMENT, CORROSION WAS FOUND INSIDE THE BELLCRANK BEARING BOSS. THIS CORROSION IS BETWEEN THE 2 BEARING SEAT AREAS. (K)

2009FA0000145

BEECH

CONT

BEECH

BOLT

WRONG PART

2/26/2009

A36  

IO550B

 

AN2310

ZONE 300

DURING THE COMPLIANCE WITH RECOMMENDED SB 27-3929, BOTH ELEVATOR TORQUE TUBES MOUNT BOLTS (8 TOTAL, 4 PER SIDE) WERE SHANKED OUT AND NOT TIGHT AT THE ATTACH POINTS. THE IPC CALLS FOR BOLTS AN-23-10, AND THE REPLACEMENT BOLTS ARE AN23-9. THIS SHOULD BE A MANDATORY SB SINCE IT INVOLVES THE ATTACHMENT OF PRIMARY FLIGHT CONTROLS.

2009FA0000166

BEECH

 

 

ANTENNA

BROKEN

2/27/2009

B200

 

 

110323

ELT 

ELT ANTENNA BREAKS IN HALF AND LEAVES THE AIRPLANE IN FLIGHT. WE HAVE INSTALLED (2) ELT ANTENNAS P/N 110-323 AND BOTH HAVE BROKEN OFF. WE ARE NOW INSTALLING A THIRD. THEY KNOW THERE IS A PROBLEM WITH THE ANTENNAS, BUT AT THIS TIME, IT IS NOT A PRIORITY TO CORRECT THE ISSUE. ANOTHER ANTENNA TO REPLACE THE CURRENT ANTENNA, THE PAPERWORK TO ALLOW FOR THE NEW ANTENNA TO BE INSTALLED IS NOT A PRIORITY AT THIS TIME.

CA090203002

BEECH

PWA  

 

POWER CABLE

SEIZED

1/29/2009

B200

PT642A

 

11538900123

ENGINE CONTROLS

THE POWER CABLE WAS REPLACED 200 HRS PRIOR DUE TO VERY STIFF OPERATION AND 200 HRS LATER DURING A SCHEDULED INSPECTION. THE SAME CABLE WAS FOUND VERY STIFF AND HAD EXCESSIVE END PLAY. SUSPECT SUB-QUALITY AIRCRAFT PART.

2009F00024

BEECH

PWA  

 

LINE

SEPARATED

3/19/2009

B200

PT6A60A

 

 

HYDRAULIC SYS

LT MLG BEGAN LOWERING OUT OF NACELLE DURING FLIGHT.

CA090123004

BEECH

PWA  

 

TORQUE TUBE

CRACKED

12/29/2008

B99  

PT6A27

 

1155240463

ELEVATOR

(CAN) WHILE ACFT WAS IN FOR MAJOR OVERHAUL AND PAINT, THE ELEVATOR BELLCRANK TORQUE TUBE WAS REMOVED FOR ROUTINE MX. THE BELLCRANK ARMS WERE FOUND LOOSE. AFTER THE ARMS WERE REMOVED THE STEEL TORQUE TUBE WAS NDT INSPECTED. CRACK INDICATIONS WERE FOUND ON TWO (2) OF THE EIGHT (8) TAPER PIN HOLES. THIS WAS A NEW ASSEMBLY LESS THAN A YEAR AGO. THE PREVIOUS ELEVATOR BELLCRANK TORQUE TUBE ASSY WAS REPLACED BECAUSE OF CRACKS IN THE SAME AREA. IMPLEMENTING AN INHOUSE INSP OF THIS ELEVATOR BELLCRANK TORQUE TUBE ASSY ON OUR ACFT.

CA090206007

BEECH

PWA  

 

CASTING

CRACKED

2/6/2009

C90A

PT6A21

 

508103704

MLG 

DURING 72 MONTH INSPECTION IT WAS FOUND THAT THE LOWER CASTING WAS CRACKED AT THE LOWER TORQUE KNEE CONTACT POINT.

2009FA0000220

BEECH

CONT

 

RELAY

INTERMITTENT

2/28/2009

F33A

IO520BB

 

SM50D7

MLG 

PILOT REPORTED AFTER PUTTING THE GEAR SELECTOR IN THE UP POSITION, THE GEAR WOULD NOT RETRACT. ON TROUBLESHOOTING, THE MECHANIC CYCLED GEAR SEVERAL TIMES AND GOT GEAR RETRACTION TO FAIL. REPLACED RELAY WITH NEW IAW DATE CODE MFD RW 0734. NO RECOMMENDATIONS AT THIS TIME. (K)

CA090116001

BELL  

 

 

RING

OUT OF POSITION

1/14/2009

205A1

 

 

 

CARGO NET

WHILE WORKING ON THE AIRCRAFT IN THE HANGAR, IT WAS DISCOVERED THAT THE RT SLIDING DOOR WOULD ONLY OPEN APPROX SIX INCHES. IT WAS FOUND THAT ONE OF THE UPPER "D" RINGS ON THE RIGHT REAR BULKHEAD HAD ROTATED (PROBABLY WHEN THE CARGO NET WAS REMOVED FOR MAINTENANCE) AND IT WAS PREVENTING THE DOOR FROM OPENING FURTHER. THE RING WAS ROTATED TO ITS PROPER ORIENTATION AND THE DOOR NOW OPERATES NORMALLY.

CA090119010

BELL  

HNYWL

BELL  

BEARING

DIRTY

1/19/2009

205A1

T5313BHNYWL

212040003023

212040143103

INNER RACES

INTERMEDIATE GEARBOX RECEIVED TO INVESTIGATE HIGH ROTATIONAL FORCE TO TURN INPUT PINION. MEASURED TO BE 50 INCH POUNDS. THIS GEARBOX WAS INSTALLED ON AIRCRAFT IN 1995 AND UNTIL NOVEMBER OF 2008 HAD NEVER BEEN REMOVED. DISASSEMBLED GEARBOX AND FOUND AND ACCUMULATION OF MUD LIKE DEPOSIT INSIDE GEARBOX. THIS DEPOSIT WAS ON THE GEARS AND ALL THE BEARINGS WERE COVERED WITH IT. ALL COMPONENTS WERE THEN CLEANED IN WHITE MINERAL SPIRITS. VISUALLY UNDER INSPECTION WITH A BEARING SCOPE THE BEARINGS LOOKED GOOD. BUT UNDER PRESSURE THE DUPLEX BEARING HALVES WERE VERY DIFFICULT TO TURN. THE BEARINGS WERE TURNED OVER TO BELL HELICOPTER PRODUCT SUPPORT FOR FURTHER INVESTIGATION. AT THIS TIME I HAVE NO RESPONSE AS TO WHY THE BEARINGS WERE SO TIGHT. THE GEARBOX WAS THEN UPGRADED TO OVERHAUL AND BOTH DUPLEX BEARINGS AND ALL SEALS WERE REPLACED. AFTER REBUILD THE ROTATIONAL FORCE TO TURN PINION WAS 4 INCH POUNDS.

CA090123001

BELL  

ALLSN

 

FAN  

FAILED

1/22/2009

206B

250C20

 

 

OIL COOLER

(CAN) SLIGHT VIBRATION FELT THROUGH ACCELERATION DURING START TO FLIGHT IDLE RPM. OIL COOLER FAN BRGS REPLACED AND FAN BALANCED CHECKED SERVICEABLE. VIBRATION DISAPPEARED BUT WITHIN 30 FLIGHT HOURS BEGAN INCREASING IN FREQUENCY AGAIN DURING THE SPOOL UP THEN STOPPED. ACFT REMOVED FROM SERVICE. OIL COOLING FAN, SHAFT AND BEARING HANGARS REMOVED. CRACK IN SKIN DETECTED BELOW AFT BEARING HANGAR AT BOLT ATTACH POINT.

CA090123002

BELL  

ALLSN

 

DRIVE GEAR

LOOSE

1/16/2009

206B

250C20

 

23065121

GOVERNOR

(CAN) THE EXPOXY HOLDING THE RETAINING CLIP IN PLACE CAME UNBONDED, ALLOWING THE CLIP TO MOVE, THERFORE ALLOWING THE DRIVE GEAR TO DISCONNECT FROM THE SHAFT.

CA090202006

BELL  

ALLSN

 

FRAME

CRACKED

1/23/2009

206B

250C20

 

206031302173S

BS 130

DURING 1200 HR/12 MONTH INSPECTION AFT LEFT FRAME OF ROLLOVER BULKHEAD FOUND CRACKED. CRACK IS 2.5 INCHES LONG AND IS LOCATED AT STA 130, WL 68, AND BL 26.

CA090130009

BELL  

ALLSN

 

CLUTCH

MALFUNCTIONED

11/20/2008

206B

250C20

 

CL422501

FREEWHEEL UNIT

ON RUNDOWN OF HELICOPTER PILOT NOTED N2 AND M/R RPM LOCKED UP. INVESTIGATED AND FOUND CLUTCH ASSY WAS NOT DISENGAGING. REMOVED AND REPLACED WITH FREE WHEEL ASSY PN206-040-270-003 TSN 11046.6 TSO 0.0HRS. CLUTCH CL42250-1 TSN0.0 HRS. SENT DAMAGED ASSEMBLY IN FOR OVERHAUL. OVERHAUL SHOP REPORTED BACK THAT THE BEARINGS WERE GONE.

CA090211003

BELL  

ALLSN

 

SUPPORT

CRACKED

2/2/2009

206B

250C20

 

206031301023

RBL 13 FWD SIDE

SEVERAL CRACKS DISCOVERED WHERE SUPPORT ASSEMBLY, ATTACHES TO THE FORWARD SIDE OF THE CROSS TUBE FUNNEL. ONE CRACK EXTENDS PAST THE STANDARD REPAIR AREA AS STATED IN THE SRM. OTHER CRACKS ARE OUT SIDE THE ALLOWABLE REPAIR AREA ALONG THE 90 DEGREE BEND AT THE BOTTOM OF THE SUPPORT P/N 206-031-301-023. NEW SUPPORTS INSTALLED ON THE AIRCRAFT.

CA090114005

BELL  

ALLSN

 

SKID

UNSERVICEABLE

1/9/2009

206B

250C20B

 

206020110005

TAILBOOM

THE AIRCRAFT WAS BEING POSITIONED IN THE HANGER FOR MAINTENANCE. THE TAIL SKID WAS BEING USED TO STEADY THE HELICOPTER AS IT WAS BEING HOISTED TO HAVE THE LANDING GEAR REMOVED. A PORTION OF THE TAIL SKID BROKE OFF IN THE ENGINEER’S HAND. THE CAUSE OF THE BREAK IS DUE TO CORROSION. A SERVICEABLE UNIT WAS INSTALLED.

CA090121012

BELL  

ALLSN

 

PUMP

UNKNOWN

12/23/2008

206B

250C20B

 

6899253

FUEL SYSTEM

DURING ENGINE TROUBLESHOOTING A STARTING ISSUE, THE FUEL PUMP WAS REPLACED DUE TO UNDETERMINED REASONS.

CA081209002

BELL  

ALLSN

 

CLUTCH

CRACKED

9/14/2008

206B

250C20B

 

CL422501

FREEWHEEL UNIT

(CAN) APPROX 100 HRS PRIOR TO SCHEDULED REMOVAL OF THE FREEWHEEL ASSY, METAL WAS DISCOVERED ON FREEWHEEL CHIP DETECTOR. CREW ORDERED REPLACEMENT ASSY AND MONITORED FURTHER INDICATIONS. UPON DISASSEMBLY AT THE OPERATOR`S OVERHAUL FACILITY, IT WAS NOTED THAT THE CLUTCH CAGE HAS BEEN CRACKED THROUGH FWD AND AFT FACES. THE "DOG BONE" POCKETS EXHIBITED UNUSUAL WEAR ON INNER SIDE AS WELL AS FWD AND AFT SURFACES. THIS O/H SHOP HAS NOTED SEVERAL CASES OF WORN POCKETS (WEAR BEYOND .004 INCH) ON CLUTCHES INSPECTED WITHIN THE LAST YEAR.

CA090122009

BELL  

ALLSN

BELL  

SUPPORT TUBE

CRACKED

12/16/2008

206B

250C20B

206BIII

206031301121

SUPPORT STRUCTUR

DURING A FUEL CELL CHANGE (DUE TO FUEL SEEPAGE), A SMALL CRACK WAS FOUND IN THE AFT CROSSTUBE SUPPORT STRUCTURE, ON THE RT SIDE OF THE AIRCRAFT. THE LOCATION OF THE CRACK WAS AT THE FWD BOTTOM RIVET OF THE CROSSTUBE SUPPORT. THE CRACK WAS APPROXIMATELY 1/4 INCH IN LENGTH. THIS AREA IS SUSCEPTIBLE TO CRACKS BECAUSE OF THE LOADING ON THIS AREA. THE MANUFACTURER HAS INCREASED THE WALL THICKNESS OF THE SUPPORT STRUCTURE IN THIS AREA, WITH THEIR REPLACEMENT PARTS. THE SUPPORT STRUCTURE WAS REPLACED WITH THE NEW BEEFIER PARTS, AND RETURNED TO SERVICE. IT WAS NOTED THAT THE CRACK COULD NOT BE SEEN FROM THE OUTSIDE, AND THAT ANOTHER CRACK WAS ALSO FOUND ON ANOTHER PIECE OF THE STRUCTURE, WHICH COULD NOT BE SEEN AS WELL. IT WAS ONLY WHEN THE FUEL CELL WAS REMOVED, THAT YOU COULD SEE THE CRACK STARTING FROM THE RIVET.

CA090217004

BELL  

ALLSN

 

PUMP

FAILED

2/12/2009

206B

250C20R

 

850500101

HYDRAULIC SYS

(CAN) DURING NORMAL FLAT AND LEVEL CRUISE FLIGHT AT APPROX. 4000` ASL THE PILOT INITIATED A GENTLE RT TURN. UPON MOVING THE CYCLIC CONTROL THE PILOT NOTED ROUGH OPERATION AND FEEDBACK THROUGH THE CYCLIC GRIP. THE PILOT CUT HYD AND RESTORED THEM. THE CYCLIC MOVED SMOOTHLY FOR APPROX. 10 SECONDS AND THEN RESUMED ROUGH OPERATION. THE PILOT ONCE AGAIN CUT AND RESTORED HYD. THE CYCLIC MOVED FREELY FOR APPROX. 5 SECONDS AND THEN RESUMED ROUGH OPERATION. THE PILOT ONCE AGAIN CUT HYD BUT THIS TIME RETURNED TO BASE HYD OFF. UPON INSP, ON THE GROUND IT WAS NOTED THAT THE HYD FILTER`S CLOGGING INDICATOR HAD "POPPED". THE FILTER WAS REMOVED FOR VISUAL INSP AND IT WAS DISCOVERED TO BE COMPLETELY CONTAMINATED WITH WHAT APPEARED TO BE BRASS SHAVINGS. THE SOURCE OF THIS MATERIAL IS KNOWN TO BE THE HYD PUMP. THERE WAS NO CAUTION LIGHT THAT INDICATED FAILURE FOR THIS DEFECT AS THE PUMP WAS STILL FUNCTIONING AS IT FAILED. THE SERVOS WERE ESSENTIALLY STARVED OF HYD FLUID PRESSURE DUE TO THE CLOGGED FILTER. THIS PARTICULAR PUMP ONLY HAD A TSN OF 6.5 HOURS.

CA081223003

BELL  

ALLSN

BELL  

RELEASE CABLE

SEPARATED

12/9/2008

206L

250C20R

 

20803100

CARGO HOOK

(CAN) PILOT REPORTED UN-COMMANDED HOOK RELEASE (LOSS OF LEAD) UPON INSPECTION FOUND FAULTY MANUAL RELEASE CABLE WHEN HOOK PULLED TO FAR END OF SWAGED END SEPARATED CAUSING UNCOMMENDED HOOK RELEASE HOOK END CABLE REMOVED FROM A/C AND NEW CABLE ORDERED ALL OTHER ACFT INSPECTED FOR SAME DEFECT (NO FAULTS FOUND) INSPECTION OF HOOK AND MANUAL RELEASE CABLE ADDED TO DAILY CHECK PROCEDURE MANUAL.

2009FA0000093

BELL  

ALLSN

 

VALVE

FAILED

1/9/2009

206L3

250C30

 

2538877

ENGINE

CUTOFF VALVE ASSY FAILED. THE EPOXY BOND THAT RETAINS THE END CAP IN THE VALVE FAILED. THEN FUEL PRESSURE WAS PRESENT IN THE VALVE ASSY THE PRESSURE WOULD PUSH THE END CAP PARTIALLY OUT OF THE VALVE ASSY. THIS EFFECTIVELY INCREASED THE LENGTH OF THE VALVE. THIS INCREASED LENGTH BLOCKED THE CUTOFF SEAT FOR AN ADDITIONAL 26 THROTTLE DEGREES, CHANGING THE FUEL FLOW CUTOFF ANGLE FROM 8-14 THROTTLE DEGREES TO APPROX 40 THROTTLE DEGREES. THIS ALSO ELIMINATED ALL START FUEL FLOW MODULATION. ENGINE WOULD NOT START. (K)

2009FA0000092

BELL  

ALLSN

 

BEARING

FAILED

11/10/2008

206L4

250C30

 

2544198

INSIDE PTG

SPOOL BEARING ASSY FAILED INTERNALLY. BEARING ASSY NO LONGER ROTATES. THE UPPER BEARING LOWER SHIELD AND RETAINER HAS COME OFF, BEARING BALLS ARE LOOSE. THE LWR BEARING IS INTACT BUT NO LONGER ROTATES. (K)

CA090213002

BELL  

ALLSN

 

FUEL CELL

LEAKING

2/11/2009

206L4

250C30P

 

206064633105

 

(CAN) ACFT PARKED STATIC INSIDE HANGER. FUEL LEAKS THOUGH CELL MATERIAL. REQUIRES REPLACEMENT.

CA090213003

BELL  

ALLSN

 

FUEL CELL

LEAKING

2/11/2009

206L4

250C30P

 

206064633105

 

(CAN) ACFT PARKED STATIC IN HANGER. FUEL LEAKS THOUGH CELL MATERIAL. REQUIRES REPLACEMENT.

CA090105005

BELL  

 

 

RIVET

SHEARED

1/5/2009

212  

 

 

 

ATTACHMENT

ATTACHMENT RIVETS ATTACHING TEE CAP TO OUTBOARD TITAINIUM PANEL P/N 205-030-209-020 UPPER EDGE RIVET P/N MS20470AD4-XX SHEARED.

CA090127013

BELL  

PWA  

BELL  

LONGERON

CORRODED

12/5/2008

212  

PT6T3B

212030100

212030132150B

TAILBOOM BAGGAGE

CORROSION OF LONGERON AND SPLICE UNDER SPLICE. FOUND WHILE PERFORMING INSPECTION REQUIRED FOR ASB212-90-63. CORROSION WAS VERY SEVERE WHEN SIGNS WERE VISIBLE BECAUSE CORROSION WAS BETWEEN LONGERON AND SPAR SPLICE FAYING SURFACES.

CA090120005

BELL  

ALLSN

 

SUPPORT ANGLE

CRACKED

1/13/2009

407  

250C47B

 

407023800127

TAILBOOM

(CAN) SUPPORT ANGLE P/N 407-023-800-127 FOUND CRACKED ON A DAILY INSP. PART HAS BEEN UPGRADED BY A -129 THAT WAS INSTALLED. THIS IS KNOWN TO MFG AND THEY HAVE COME OUT WITH THE -129 THAT IS THINNER MATERIAL AND HAS MORE FLEXABILITY.

CA090205007

BELL  

ALLSN

 

RELEASE CABLE

FRAYED

2/2/2009

407  

250C47B

 

26800400

CARGO HOOK

DURING INSPECTION CABLE TOP END OF MANUAL RELEASE CABLE WAS FOUND TO BE FRAYED AND PULLED OUT OF THE SWAGED END. SDR WAS SUMITTED DEC 09 2008 FOR A SIMILAR DEFECT BUT ON THE BOTTOM END OF CABLE, THAT CASE RESULTED IN A UN-COMMANDED RELEASE OF THE HOOK, BOTH CABLES HAVE BEEN SENT TO THE MANUFACTURE.

CA090107013

BELL  

 

 

BRACKET

BROKEN

1/2/2009

427  

 

 

427044223101

TAIL ROTOR

DURING A DAILY INSPECTION, THE AFT FAN SHAFT HANGAR BEARING SUPPORT BRACKET WAS FOUND TO BE BROKEN. THERE WAS NO DAMAGE TO THE SURROUNDING AREA, AND INSPECTION OF THE FORWARD BRACKET FOUND NO DAMAGE TO IT. A ONE TIME INSPECTION OF THE WHOLE AIRCRAFT WAS ALSO PERFORMED.

CA090121007

BELL  

PWC  

 

BEAM

CHAFED

1/9/2009

427  

PW207D

 

427365281101

NACELLE

DURING ANNUAL INSPECTION, FRETTING RESIDUE WAS NOTED ON BOTTOM OF LEFT HAND PYLON BEAM ASSEMBLY 427-010-201-107. FURTHER INVESTIGATION AND SUBSEQUENT REMOVAL OF THE BEAM REVEALED CHAFING DAMAGE TO PYLON BEAM 427-010-201-107, ADAPTER 427-010-206-101 AND HOSE 427-365-281-101. THE CAUSE OF THE DAMAGE WAS SLEEVE 120-067B.

CA090119013

BNORM

LYC  

LYC  

SLEEVE

LOOSE

1/18/2009

BN2A26

O540E4C5

0540E4C5

71699

NR 5 CYLINDER

ON GROUND RUN IT WAS DISCOVERED THAT CYLINDER NR 5 ON THE RIGHT ENGINE, EGT WAS NOTICABLY HIGHER THAN OTHER CYLINDERS. INDUCTION TUBE WAS REMOVED FROM THE CYLINDER, THE INDUCTION TUBE SLEEVE IN THE OIL SUMP WAS FOUND TO BE LOOSE.

CA090225004

BNORM

LYC  

 

GOVERNOR

MALFUNCTIONED

2/24/2009

BN2B21

IO540K1B5

 

G210659M

PROPELLER

ON GROUND RUN, RT PROP WOULD NOT FEATHER. OTHER PITCH CHANGE FUNCTIONS WORKED NORMALLY. INITIALLY THE PROP WAS REPLACED WITH SIMILAR RESULTS THE GOVERNOR WAS THEN REPLACED WITH A SERVICEABLE UNIT FROM ANOTHER AIRCRAFT AND THE PROP PITCH/FEATHER FUNCTIONED NORMALLY. THE SUSPECT GOVERNOR WILL BE SENT FOR ANALYSIS AND LIKELY OVERHAUL.

CA090223001

BOEING

RROYCE

 

ENGINE

MAKING METAL

2/17/2009

717200

BR700715A130

 

 

 

IFSD, ACFT TURNED BACK INTO ATLANTA DUE TO, HIGH VIB, COMPRESSOR STALL, AND TGT WENT TO 1149 DEG. FOUND METAL NUGGETS IN THE TAIL PIPE, AND HPT CASE BULGED IN LINE WITH HPT1. ENGINE WILL BE INDUCTED TO MANUFACTURER ON MARCH 3 FOR INVESTIGATION. FURTHER INFORMATION WILL BE AVAILABLE FOLLOWING ENGINE DISASSEMBLY.

CA090216007

BOEING

RROYCE

 

COMPRESSOR

STALLED

2/10/2009

717200

BR700715A130

 

 

LT ENGINE

(CAN) SURGE/IFSD/AIR RETURN. DURING CLIMB OUT OF DEPARTURE AIRPORT AT 5000 FEET, LOUD BANG REPORTED ACCOMPANIED BY ACFT YAW AND ENG L COMPRESSOR STALL ALERT. ENGINE AUTO SHUTDOWN. ACFT RETURNED TO DEPARTURE. INITIAL FINDINGS NOT AVAILABLE AS OF THIS WRITING. ENGINE HAD BEEN SCHEDULED FOR REMOVAL TONIGHT (10 FEB) FOR HIGH-TIME LIP5 HP TURBINE BLADES. ENGINE WILL BE INDUCTED AT MFG, FURTHER DETAILS WILL BE SUBMITTED AFTER ENGINE TEAR DOWN.

CA090203004

BOEING

PWA  

 

TURBINE BLADES

FRACTURED

1/31/2009

720023B

JT3D1

 

771104

ENGINE

APPROXIMATELY 3.5 HOURS INTO THE FLIGHT TEST PROFILE, CLIMBING OUT OF FL380 TO FL410 AT CLIMB THRUST, IN SMOOTH AIR CONDITIONS, A SUDDEN YAW AND VIBRATION WAS FELT IN THE AIRPLANE. ENGINE INSTRUMENTATION OF THE ENGINE NR 1 SHOWED EGT WAS IN THE YELLOW AT ABOUT 500 C, N2 WAS 70 PERCENT AND N1 WAS AT 30 PERCENT. FLIGHT CREWMEMBERS DECIDED TO SHUTDOWN THE ENGINE, NOTIFIED ATC AND RETURN TO THE BASE, NO EMERGENCY WAS DECLARED. AFTER LANDING, AN INITIAL INSPECTION OF THE NR 1 ENGINE EXHAUSTS AREA SHOWED MISSING TURBINE TIP BLADES. THE ENGINE IS CURRENTLY BEING REMOVED AND WILL BE SENT FOR INVESTIGATION/REPAIR.

CA090119014

BOEING

PWA  

 

DRUM

FROZEN

1/16/2009

727225

JT8D15

 

652459310

TE FLAP

ON APPROACH INTO YYZ WHEN FLAPS 30 WAS SELECTED NEEDLES REMAINED IN FLAPS 25 POSITION BAND. "TO LOW FLAPS" AURAL WARNING SOUNDED. MISSED APPROACH WAS EXECUTED. RECTIFICATION TROUBLESHOOTING CARRIED OUT AS PER MM 27-51-000-5. UNABLE TO FAULT. SUSPECT FROZEN DRUM AND CABLES. HEAT APPLIED AND LUBED DRUM AND CABLES GROUND CHECKED SERVICEABLE.

CA090204008

BOEING

PWA  

 

LANDING GEAR

MALFUNCTIONED

1/31/2009

737200

JT8D17

 

65737625

NOSE 

DEPARTING YFB FOR YOW ON JAN 31, 2009, THE CREW OBSERVED A NOSE LANDING GEAR FAIL TO LOCK CONDITION AFTER GEAR WAS SELECTED UP. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE SERVICED THE NOSE GEAR AND THE AIRCRAFT WAS RETURNED TO SERVICE AND THE AIRCRAFT RETURNED TO YOW.

CA090203005

BOEING

PWA  

 

SKIN

CORRODED

1/27/2009

737275C

JT8D9A

 

 

BS 460-480

DURING ROUTINE SCHEDULED HEAVY MAINTANANCE VISIT (C3 CHECK), CORROSION WAS FOUND ON A LAP JOINT AT STA 460 TO 480, ON STR 26L. THIS CORROSION IS BELIEVED TO BE CAUSED BY THE BONDING PROCESS AT FACTORY. THE PROCESS (COLD BONDING) WAS ACCOMPLISHED ON THE FIRST 491 B737 AIRCRAFT. THIS AIRCRAFT IS LINE NR 4481. THIS IS A KNOWN FLAW, AND HENCE THE CHANGE TO A NEW PROCESS ON AIRCRAFT LINE NR 492 AND ON. THIS CORROSION WAS CLASSIFIED, AND VERIFIED AS LEVEL 2, IAW THE CPCP DOCUMENT D6-38528, FIGURE 9 LOGIC DIAGRAM, ITEM NR 20. DUE TO THE LINE NR OF THIS AIRCRAFT THE CPCP PROGRAM HAS SOME TASKS DUE AT 18 MONTH INTERVALS INSTEAD OF MOST AIRCRAFT AT 2 YEAR INTERVALS. AN ADDITIONAL INTERNAL DVI INSPECTION WILL BE RAISED AGAINST THIS AIRCRAFT FOR THIS AREA AND ADJACENT AREAS ONLY AT NEXT HEAVY MAINTENANCE VISIT. THIS WILL BE IN ADDITION TO THE 18 MONTH CPCP INSPECTION AND THE ADDITIONAL INSPECTIONS THAT WILL BE REQUIRED DUE TO THE HMV VISIT.

COOSDR080234

BOEING

 

 

STRINGER

CRACKED

11/13/2008

737322

 

 

65458001261

FUSELAGE

UPPER FUSELAGE PAX CABIN AT STA 296.5, S10L CRACKED. (K)

COOSDR080233

BOEING

 

 

INTERCOSTAL

CRACKED

11/13/2008

737322

 

 

651768465

FUSELAGE

UPPER FUSELAGE PAX CABIN AT STA 300 AND ABOVE S10L INTERCOSTAL CRACKED. (K)

COOSDR080231

BOEING

 

 

INTERCOSTAL

CRACKED

11/13/2008

737322

 

 

6517684634

FUSELAGE

UPPER FUSELAGE PAX CABIN BETWEEN STA 294.5 AND STA 303.9 AT S-16L INTERCOSTAL CRACKED. (K)

CA090210008

BOEING

GE  

 

HINGE

LOOSE

2/8/2009

737705

CFM567B24

 

 

L1 DOOR

ON FEBRUARY 8, 2009 LEAVING TORONTO THE AIRCRAFT FAILED TO PRESSURIZE AFTER TAKEOFF THEN RETURNED TO GATE. MAINTENANCE ACTION CONFIRMED THE L1 ENTRY DOOR GUIDE ARM JAM NUT WAS LOOSE CAUSING THE DOOR TO MIGRATE OUT OF RIG. THE GUIDE ARM WAS RE-ADJUSTED. WEST JET CONSIDERS THIS SDR CLOSED.

CA090212001

BOEING

GE  

 

SPAR

FAILED

2/11/2009

767333

CF680C2B6F

 

 

RUDDER ACTUATOR

ON TAXI OUT, R RUDDER TEST FAILED. RUDDER PEDAL APPEARS TO BIND. UNABLE TO ACHIEVE MORE THAN HALF DEFLECTION. INITIAL INSPECTION FOUND CTR PCA (LT HYD SYS) FULLY RETRACTED IN THE LT RUDDER DEFLECTION POSITION, WITH ONLY LT HYD SYS PRESSURIZED, RUDDER APPROX 4 INCHES RIGHT OF NEUTRAL PCA REMAINED FULL LEFT. RIGHT RUDDER PEDAL INPUT APPROX 1/2 TRAVEL, PCA SUDDENLY WENT FULL RIGHT THEN BACK TO FULL LEFT AND REMAINED IN THAT POSITION FOR REMAINDER OF TEST. WITH ALL 3 HYD SYSTEMS PRESSURIZED, FULL RIGHT PEDAL RUDDER MOVED TO THE RIGHT. LEFT RUDDER PEDAL WAS STIFF TO OPERATE AND RUDDER MOVED TO THE LEFT WITH SOUNDS OF BREAKING COMPOSITE. LT HYD SYS PCA JAMMED IN FULL LEFT WITH CTR AND RIGHT SYS PCA`S FIGHTING THE LEFT. ALSO, FOUND INTERFERENCE DAMAGE TO SECONDARY INPUT CONTROL ROD AND REACTION LINK AT CTR PCA POSITION.

CA090211002

BOEING

PWA  

 

DUCT

CRACKED

2/9/2009

767333

PW4060

 

213T412917

AIR CON

DURING THE INSPECTION FOUND AC DUCT CRACK, THE DAMAGE AIR CONDITIONING DUCT RUN`S FROM A TRIM AIR SUPPLY MODULATING VALVE (UNPRESSURIZED AREA) TO THE MIX MANIFOLD OUTLET DUCT (FWD CARGO PRESSURIZE AREA).

CA090210011

BOEING

PWA  

 

DUCT

CRACKED

2/10/2009

767333

PW4060

 

213T412917

AIR CON SYS

DURING INSPECTION FOUND AC DUCT CRACK THE DAMAGE AIR CONDITIONING DUCT RUN’S FROM A TRIM AIR SUPPLY MODULATING VALVE (UNPRESSURIZE AREA) TO THE MIX MANIFOLD OUTLET DUCT (FWD CARGO PRESSURIZE AREA) THR : 60554 TCY : 9972 TLN : 9972.

CA090115004

BOEING

 

 

BEARING

FAILED

1/13/2009

777233LR

 

 

4100941C

COOLING FAN

INFO RECEIVED FROM MX, WHEN MX HAD BOARDED THE ACFT AFTER ARRIVAL, FRONT END CREW HAD DEPARTED THE ACFT. MX REPORTED THE ACFT AND SPECIFICALLY THE FLIGHT DECK WAS FILLED WITH SMOKE. RELATED SBS: HAMILTON STANDARD 4100941-21-4 OCT 24 2008. THIS ONE IS APPLICABLE TO THE GIVEN P/N BOEING SB 777-21-0104 REV.1 OCT 9 2008. THIS ONE IS APPLICABLE TO P/N 4100943/A/B/C, BUT DESCRIBES THE SAME ISSUE. THE ISSUE IS THE ROTOR RUBBING AGAINST THE STATOR.

CA090213001

BOEING

GE  

 

CHECK VALVE

FAILED

2/12/2009

777233LR

GE90110B1

 

8102052

AIR CON

(CAN) UNABLE TO CONTROL CABIN TEMP ZONE B, D AND F. DURING MAINT INSP FOUND THE LT PACK WITH A RUPTURED DUCT CAUSED BY A FAILED LT PACK FAN AIR CHECK VALVE.

CA090204002

BOEING

GE  

 

ENGINE

FAILED

1/30/2009

777333ER

GE90115B

 

 

LEFT 

DURING CRUISE AT FL330, THE LT ENGINE FAILED ABRUPTLY. N1 WINDMILLING AND N2 ZERO. NO RELIGHT ATTEMPT. THE CREW DECLARED AN EMERGENCY AND DIVERTED TO ANC. TGB SUSPECTED. ENGINE SB 72-0263R03 IS RELATED.

CA081204004

BOLKMS

ALLSN

 

HANDLE

DAMAGED

12/3/2008

BO105S

250C20B

10510521

10213193

ROTOR BRAKE

(CAN) DURING CRUISE, THE ROTOR BRAKE HANDLE DOWN WARNING LIGHT TURN ON INTERMITTENTLY. THE WARNING LIGHT SWITCH IS ADJUSTED TO WARN PILOT IF THE HANDLE IS NOT IN ITS NEUTRAL OR DOWN POSITION AND TO VERIFY IF THE REASON IS NOT THE PILOT`S SEAT BELT BEING UNDER THE HANDLE. IAW THE MM, THERE SHOULD BE A CLEARANCE OF 22 TO 28 MM BETWEEN THE HANDLE AND THE FLOOR WHEN NOT ENGAGE. A NEW ROTOR BRAKE HANDLE RUBBER BOOT, P/N: 10.2131.9.3, WAS INSTALLED DURING THE LAST O/H, REPLACING THE LEATHER BOOT, P/N: 105-10551, INITIALLY INSTALLED IN ALL MBB BO-105. THE NEW RUBBER BOOT, BEING MORE RIGID THEN THE LEATHER BOOT, KEEPS THE HANDLE UP AT 34MM CLEARANCE BETWEEN THE HANDLE AND THE FLOOR. DURING THEIR PRE-START CHECK, THE PILOT CHECKS IF THE HANDLE IS ALL THE WAY DOWN. BY DOING SO, THEY FORCE THE HANDLE AGAINST THE WARNING LIGHT MECHANISM ON A GREATER DISTANCE AND GET THE SWITCH OUT OF ADJUSTMENT, MAKING THE CONTACTS CLOSING AND TURNING THE ROTOR BRAKE WARNING LIGHT ON WHEN FLYING IN LIGHT TURBULENCES.

CA090202004

BOMBDR

 

 

OUTFLOW VALVE

MALFUNCTIONED

1/31/2009

BD1001A10

 

 

81141A010302

CABIN PRESSURE

LOSS OF PRESSURIZATION AT ALTITUDE ACFT DEPARTED AT FL410, THE CREW HEARD A LOUD NOISE IN THE BACK OF THE ACFT. PRESSURIZATION RAPIDLY LOST. CREW DECLARED EMERGENCY AND DIVERTED TO FLL. UNEVENTFUL LANDING MADE IN FLL. ACFT AT BAS FLL FACILITY. UPDATE, DEADHEAD TRIP FROM NAPLES TO TULSA, OK. WHEN EVENT OCCURRED, CREW DONNED O2 MASKS, MADE SELECTION ON AUDIO CONTROL PANEL AND INITIATED AN EMERGENCY DESCENT. CABIN ALTITUDE DID REACH 15,000 FT. CREW COMMENTED THEY HAD DIFFICULTY WITH COMMUNICATIONS WITH MASKS ON. ALL CABIN MASKED DEPLOYED. NO FAULTS FOUND IN MDC. REQUEST IASCS NVM TO BE DOWNLOADED. A VISUAL INSPECTION OF SAFETY VALVES IN BAGGAGE COMPARTMENT C/W. NO FOREIGN OBJECT DAMAGE FOUND. VISUAL OF OUTFLOW VALVE DONE, NO DEFECTS NOTED.

CA090212002

BOMBDR

HNYWL

 

CONNECTOR

SHORTED

2/11/2009

BD1001A10

AS90711A

 

A3005P1CONNECT

COFFEEMAKER

C/B A-112 FOUND POPPED DURING AIRCRAFT SERVICING. WIRES CONNECTED TO PLUG A3005P1 FOR HOT LIQUID CONTAINER NR 1 WERE FOUND ROUTED SUCH THAT CONTACT WAS MADE BETWEEN TERMINALS CAUSING A SHORT POPPING THE C/B. THE WIRES WERE REPOSITIONED TO PREVENT CONTACT. ADJACENT CONNECTOR A3006P1 FOR HOT LIQUID CONTAINER NR 2 WAS EXAMINED AS WELL AND THE SAME CONDITION EXISTED. THESE WIRES WERE ALSO REPOSITIONED TO PREVENT SHORTING. REFERENCE NR 8 (B) MANUFACTURE IS IN FACT MAPCO. THIS INFO NOT AVAILABLE IN DROP DOWN.

CA090205004

BOMBDR

HNYWL

 

ENGINE

POWER LOSS

2/3/2009

BD1001A10

AS90711A

 

 

LEFT 

CHIEF PILOT REPORTS DESCENDING BELOW 13000 FT MSL INTO SAN ANTONIO INT`L AIRPORT FROM HOUSTON, THE LEFT ENGINE SHUTTERED, THE HIGH VIB INDICATED ON THE EICAS, THE ITT ROSE TO 700C AND THE OIL PRESSURE DROPPED ABOUT 15 PSI, FROM NORMAL. HE SHUT THE LEFT ENGINE DOWN. THE CREW DECLARED AN EMERGENCY AND LANDED THE AIRCRAFT WITHOUT INCIDENT ON THE RIGHT ENGINE ONLY. ENGINE OIL LEVEL IS REPORTED AS NORMAL, AFTER LANDING. SOME METAL HAS BEEN REPORTED ON THE CHIP DETECTOR OF THE NR 4 AND NR 5 AFT BEARING CASE SUMP RETURN. ALL OTHER CHIP DETECTORS REPORTED TO BE CLEAN OF DEBRIS. ENGINE TO BE REMOVED FOR REPAIR/INVESTIGATION AND LOANER INSTALLED.

CA090126001

BOMBDR

HNYWL

 

APU  

FAILED

1/19/2009

BD1001A10

AS90711A

 

36150BD

 

WHILE DESCENDING THROUGH 12000 FT ALTITUDE THE CREW TRIED TO START THE APU, BUT THEY EXPERIENCED A HUNG START. THEY THEN SHUT THE ENGINE DOWN AND WAITED TWO MINUTES BEFORE ATTEMPTING A 2ND START WHICH PROVED TO BE SUCCESSFUL. ON LANDING, THEY NOTICED THAT THE APU INTAKE HAD EXPERIENCED SOME KIND OF BACKFIRE WHICH MUST HAVE HAD FLAMES BLOWING OUT THE INTAKE, AND AS A RESULT BURNT THE AREA AROUND THE APU INTAKE. THE INLET DUCT HAS ALSO SUSTAINED SUBSTANTIAL DAMAGED, IN THAT THE COATING IN THE DUCT HAS BURNT AWAY, AND THE FIBERGLASS FIRE PROOF MATERIAL IS NOW EXPOSED. A BOROSCOPE INSPECTION OF THE APU FOUND CHUNKS OF CARBON WEDGED INTO THE TURBINE INLET STATOR. THERE IS ALSO MAJOR BUILDUP OF CARBON IN THE COMBUSTION LINER. REPAIRS WILL BE CARRIED OUT BY A MAINTENANCE FACILITY IN SOUTH AFRICA.

CA090130003

BOMBDR

RROYCE

 

BRACKET

LOOSE

1/27/2009

BD7001A10

BR700710A220

 

 

ELEVATOR PULLEY

QUANTITY 2 BOLTS LOOSE ON BRACKET GD417-1579-3 QUANTITY 2 BOLTS INSTALLED BUT NOT SECURED AND TORQUED BOLT ARE NAS 6203-3 THE ELEVATOR BRACKET ASSY IS MOVING UP OR DOWN .375 INCH LOCATION: RT ELEVATOR PULLEY BRACKET ASSY REAR FUSELAGE F/S 955.

CA090130005

BOMBDR

RROYCE

BOMBDR

SUPPORT

LOOSE

1/27/2009

BD7001A10

BR700710A220

 

 

ELEVATOR PULLEY

3 BOLTS NAS6203-3 MISSING ONTO PULLEY SUPPORT GD417-1570-3 AND 3 BOLTS NAS6203-3 MISSING ONTO PULLEY SUPPORT GD417-1573-3. 1 BOLT NAS6203-3 MISSING ONTO CHANNEL GD417-1580-3. HOLES ON CLEAT GD417-1661-1 DO NOT LINE UP WITH PULLEY SUPPORT GD417-1570-3 AND HOLES ONTO CLEAT GD417-1662-1 DO NOT LINE UP WITH HOLES ONTO PULLEY SUPPORT GD417-1573-3. LOCATION: RT ELEVATOR PULLEY BRACKET ASSY REAR FUSELAGE F/S 955.

CA090204004

BOMBDR

 

 

WINDSHIELD

FAILED

2/2/2009

DHC8400

 

 

80260009

COCKPIT

APPROX 15 MINS AFTER TAKEOFF, PASSING 21000 FT, THE PILOT WINDSHIELD SHATTERED. ACFT RETURN TO BASE. WINDSHIELD REPLACED IAW AMM TASKS 56-10-01-000-801, 56-10-01-400-801 AND 30-41-00-710-802.

CA090216001

BOMBDR

PWC  

 

SELECTOR VALVE

FAILED

2/13/2009

DHC8400

PW150A

 

483003

MLG 

(CAN) THE LANDING GEAR FAILED TO EXTEND WHEN GEAR LEVER WAS SELECTED DOWN. A MISSED APPROACH WAS CARRIED OUT. AT A SAFE ALTITUDE (3000 FT) THE QRH CHECKLIST WAS INITIATED. THE ALTERNATE LANDING GEAR SYS WAS USED. LANDING GEAR EXTENDED (3 GREENS) AND A NORMAL APPROACH AND LANDING WAS EXECUTED. LINE MX INVESTIGATION CONFIRMED FAILURE OF THE LANDING GEAR SELECTOR VALVE. VALVE ASSY REPLACED AND LANDING GEAR FUNCTIONALLY TESTED IAW THE ACFT`S MM. ACFT RELEASED BACK TO SERVICE WITHOUT FURTHER INCIDENT.

CA090216002

BOMBDR

PWC  

 

FADEC

FAILED

2/13/2009

DHC8400

PW150A

 

8193007008

NR 2 

(CAN) AFTER TAKEOFF NR 2 FADEC FAIL CAUTION LIGHT ILLUMINATED. FLIGHT CREW SHUTDOWN NR 2 ENGINE AND RETURNED TO DEPARTURE AIRPORT WITHOUT INCIDENT. MX TROUBLESHOOTING DETERMINED FADEC AT FAULT. NR 2 FADEC REMOVED AND REPLACE AND ACFT RETURNED TO SERVICE.

CA090206003

BOMBDR

PWC  

 

POWER UNIT

FAILED

2/2/2009

DHC8400

PW150A

 

4213403

HYD PUMP

DURING TAKEOFF ROLL (40KTS) NR 1 STBY HYD PUMP HOT CAUTION LIGHT ILLUMINATED. TAKEOFF ABORTED AIRCRAFT RETURNED TO GATE. MAINTENANCE REPLACED THE STANDBY POWER UNIT. AIRCRAFT RETURNED TO SERVICE.

CA090223010

BOMBDR

PWC  

 

HOSE

LEAKING

2/21/2009

DHC8400

PW150A

 

115503008

HYDRAULIC SYS

DURING APPROACH AFTER GEAR DOWN SELECTION, THE FLIGHT CREW OBSERVED NR 2 HYDRAULIC ISOLATION VALVE CAUTION LIGHT ILLUMINATED, HYDRAULIC PRESSURE INDICATING 3000 PSI, AND QUANTITY DROPPING. LANDING GEAR CONFIRMED DOWN AND LOCKED. FLIGHT CREW CARRIED OUT EMERGENCY PROCEDURES AND AIRCRAFT LANDED UNEVENTFULLY. MAINTENANCE DISCOVERED HYDRAULIC FLUID LEAK FROM MAIN LANDING GEAR DOWN LOCK RELEASE ACTUATOR. HYDRAULIC LINE REPLACED AND HYDRAULIC SYSTEM FLUSHED. AIRCRAFT RETURNED TO SERVICE. VENDOR FOR FLEX LINE IS GOODRICH.

CA090224003

BOMBDR

PWC  

 

BRACE

MISSING

2/23/2009

DHC8400

PW150A

 

464017

LT MLG

DURING A GROUND MAINTENANCE INSPECTION, THE LT MAIN GEAR STABILIZER BRACE WAS FOUND TO BE MISSING APPROXIMATELY 120 DEGREES OF BRACE BEARING SUPPORT AT THE OUTBOARD HINGE POSITION. PART VENDOR IS GOODRICH.

CA090218001

BOMBDR

PWC  

 

COMPUTER

FAULTED

2/13/2009

DHC8400

PW150A

 

699018002

FUEL CONTROL

(CAN) AIR TURN BACK DUE TO POWERPLANT MESSAGE DURING CLIMB. CREW ELECTED TO RETURN TO DEPARTURE AIRPORT WITH NO FURTHER ISSUES. ON GROUND TROUBLESHOOTING DISCOVERED PEC FAULTS. PEC REPLACED AND ACFT FUNCTION TESTED ON RETURNED TO SERVICE.

CA090219012

BOMBDR

PWC  

 

WINDSHIELD

FAILED

2/18/2009

DHC8400

PW150A

 

80260008

COCKPIT

(CAN) AT 4000 FEET DURING DESCENT, WITH WINDSHIELD HEAT SELECTED ON, THE CO-PILOTS WINDSHIELD SHATTERED. MX REPLACE THE WINDSHIELD AND ACFT RETURNED TO SERVICE.

2009FA0000202

BRAERO

 

 

MODULATOR

FAILED

2/3/2009

BAE125800A

 

 

 

RT MLG BRAKE

RT MLG BRAKE MODULATOR FAILED CAUSING NR 4 BRAKE TO DRAG. THE ACFT PULLED TO THE RT DURING TAKEOFF ROLL. (K)

CA090211001

BRAERO

RROYCE

 

CONE

CRACKED

1/30/2009

HS7482A

DART5342

 

RK37505A

EXHAUST

VISUAL INSPECTION DURING "A-CHECK" (WITH FLASHLIGHT) REVEALED LARGE CRACK IN CIRCUMFERENCE OF EXHAUST UNIT INNER CONE. CLOSER INSPECTION (CRAWLED UP JET-PIPE) INDICATED APPROX, 2/3 OF INNER CONE CIRCUMFERENCE CRACKED. DAMAGED AREA NORMALLY RESTS WITHIN 1/8 - 1/4 INCH OF 3 STAGE TURBINE BLADES/BLADE KEEPERS. ENGINE REMOVED AS A GEL, EXHAUST UNIT REPLACED WITH SERVICEABLE PART, ENGINE REINSTALLED. STATIC AND FUNCTION CHECKS COMPLETED.

CA090213004

BRAERO

RROYCE

 

INDICATOR

LEAKING

2/3/2009

HS7482A

DART5342

 

 

HYD SYSTEM

(CAN) SHORTLY AFTER DEPARTURE, THE CREW OBSERVED A PORT HYD PUMP INDICATION LIGHT WHICH REMAINED ILLUMINATED WITH THE MAIN SYS CYCLING EVERY 5 SECONDS. THE ACFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MX IDENTIFIED THAT THE STARBOARD FLOW INDICATION SWITCH WAS LEAKING. THE UNIT WAS REPLACED AND THE ACFT RETURNED TO SERVICE.

2009FA0000252

CESSNA

LYC  

 

DOWEL PIN

SHEARED

3/17/2009

152  

O235L2C

 

STD1065

CRANKSHAFT

DOWEL SHEARED IN FLIGHT, THE ACFT WAS A TOTAL LOSS, NO INJURIES TO CREW, BUT WAS CLASSIFIED AS AN INCIDENT. NO PROP STRIKES EVER RECORDED, INCLUDING THE NEW DEFINITION. THE INSURANCE COMPANY REQUESTED THE DOWEL FOR METALLURGY TESTS. GIVEN THE TIMES BETWEEN THE O/H. CALENDAR - ALMOST 11 YEARS AND FLIGHT 1881, DIFFICULT TO PROVIDE ANY PREVENTATIVE ACTION FOR THIS TYPE OF OCCURRENCE. HAVE OWNED ACFT SINCE 1988. ENGINE HAS BEEN O/H TWICE IN THIS TIME. (K)

CA090130008

CESSNA

LYC  

 

ATTACH BRACKET

CRACKED

1/30/2009

152  

O235L2C

 

04320049

HORIZONTAL STAB

DURING A ROUTINE 200-HR INSPECTION, CRACKS WERE DETECTED ON THE REAR FIN ATTACH BRACKET THAT IS RIVETED TO THE AFT SPAR OF THE HORIZONTAL STAB. ONE HALF INCH CRACK WAS ALONG THE WELD AT THE TOP FORWARD BOXED AREA AND THE OTHER CRACK WAS PROPAGATING FROM ONE OF THE RIVET HOLES FOR THE FIN ATTACH NUT PLATES. IT SHOULD BE NOTED THAT THE NUT PLATES WERE PREVIOUSLY REMOVED TO COMPLY WITH AD 80-11-04 AND THAT NO RIVETS WERE INSTALLED IN THE RIVET HOLE IN QUESTION. FIN ATTACH BOLTS WERE SECURED WITH NUTS AS PER THE AD. WE OPERATE A LARGE FLEET OF CESSNA 152S AND HAVE REPLACED THIS BRACKET ASSEMBLY ONLY TO FIND IT CRACKING AGAIN IN THE SAME AREA. CESSNA NEEDS TO REDESIGN THE BRACKET AND BEEF IT UP.

2009FA0000205

CESSNA

 

 

FORK

DAMAGED

2/24/2009

172A

 

 

 

NLG 

UPON PULLING THE NOSE WHEEL FAIRING. NOTED THE NOSE FORK HAD A DISTINCT, REARWARD BEND TO IT. THE CENTERLINE OF THE AXLE, RELATIVE TO THE CENTERLINE OF THE CHROME STRUT TUBE WAS APPROX 1.5 INCH AFT. THE NOSE FORK WAS REPLACED IAW MFG SK182-34C, AND ALL THE NOSE GEAR COMPONENTS AND FIREWALL WERE CAREFULLY INSPECTED FOR DAMAGE, BUT AMAZINGLY, NONE WAS FOUND. THE EXCEPTION WAS THE NOSEWHEEL FAIRING, WHICH WAS IN POOR CONDITION, LITERALLY "POP RIVETED" TOGETHER. THE NOSE WHEEL WAS FITTED WITH WHAT APPEARED TO BE A NEW TIRE, BUT NOTHING WAS IN THE RECORDS. THE OWNER OF THE ACFT WAS NOT AWARE OF ANY INCIDENTS, ALTHOUGH HE HAD NOT OWNED THE ACFT FOR VERY LONG. (ABOUT A YEAR) AND HAD NOT FLOWN IT OVER 5 HRS OF SO. THE ACFT IS BASED AT A SMALL, COUNTRY AIRPORT, AND THE OWNER SUSPECTS SOMEONE "BORROWED" IT , DAMAGED IT, AND REPLACED THE NOSE TIRE TO TRY AND HIDE THE DAMAGE. IT WAS A LOCAL AIRPLANE BEFORE THIS OWNER BOUGHT IT, WITH SAME MECH "MAINTAINING" IT FOR SEVERAL YEARS. (K)

2009FA0000249

CESSNA

LYC  

 

MASTER CYLINDER

FAILED

3/24/2009

172I

O320*

 

54113820

RT MLG

COMPLETE RT BRAKE IND SYS FAILURE WHILE TAXING THE ACFT. NO VISIBLE SIGNS OF DAMAGE OR FLUID LEAKAGE, POSSIBLY DEFECTIVE MASTER CYLINDER OR BRAKE CALIPER ASSY.

2009FA0000242

CESSNA

 

 

TUBE

FAILED

3/12/2009

172M

 

 

0923150

LT MLG WHEEL

LT MAIN TUBE FAILED. TUBE SPLIT ON THE OUTSIDE DIAMETER OF TUBE. THIS TUBE INSTALLED 5-8-06. (K)

CA090130006

CESSNA

LYC  

SLICK

ROTOR

LOOSE

1/28/2009

172M

O320E2D

 

 

DISTRIBUTOR

DURING SCHEDULED 500-HR INTERNAL MAGNETO INSPECTION IT WAS DISCOVERED THAT THE ROTOR DISTRIBUTOR PLATE HAD OVERHEATED AND BECOME LOOSE. THE PLASTIC ROTOR BODY WAS MELTED IN THE VICINITY OF THE PLATE DUE TO ARCING CAUSED BY THE LOOSE PLATE. THERE WAS NO OPERATIONAL INDICATION, THE ENGINE RAN NORMALLY WITH NORMAL MAG DROPS.

CA090127007

CESSNA

LYC  

SLICK

BRUSHES

DAMAGED

1/21/2009

172M

O360A4M

 

K3215

MAGNETO

WHILE PERFORMING SB3-08 ON BOTH LEFT AND RIGHT MAGNETOS LT P/N 4370 LT S/N 08010485 LT TSN 64.7 AND RT P/N 4371 RT S/N 07111952 RT TSO 400.6 THERE WAS EVIDENCE OF IMPROPER WEAR OF THE CARBON BRUSH. THE COIL TAB HAD RESIDUE COATING AND UNACCEPTABLE WEAR MARKS. UNDERCUTTING WAS ALSO NOTED ON THE CARBON BRUSH. IT WAS LATER LEARNED THAT BOTH MAGNETOS HAD THE NEW BRUSH REPLACEMENT AND TERMINATING ACTION IMPLEMENTED. THE AFFECTED MAGNETOS WERE SUBSEQUENTLY REPLACED WITH OTHERS AND WERE SENT OUT FOR REPAIR.

2009FA0000245

CESSNA

 

 

TUBE

FAILED

3/12/2009

172N

 

 

XA1AC

NLG TIRE

NOSE TUBE FAILED. TUBE SPLIT ON THE OUTSIDE DIAMETER OF TUBE. THIS TUBE INSTALLED 2-14-08. (K)

CA090209006

CESSNA

LYC  

 

ROLLER

BROKEN

2/6/2009

172N

O320D2J

 

0523921

TE FLAP

LT FLAP OUTBOARD LOWER ROLLER BROKE COMPLETELY UP CAUSING THE FLAP TO SEIZE INTO THE FLAP TRACK DURING THE FLAPS BEING RETRACTED AFTER TAKEOFF. WITH THE FLAP SEIZE THE FLAP MOTOR CONTINUED TO PULL THE SLAVE FLAP UNTIL THE RETRACT CABLE SNAPPED IN FLIGHT. THE FLAP ROLLER HAS BEEN WELL LUBRICATED EVERY 100 HR OF AIRTIME.

CA090209003

CESSNA

LYC  

 

CONTROL CABLE

FAILED

2/6/2009

172N

O320D2J

 

051010594

TE FLAPS

RT FLAP RETRACT CABLE P/N 0510105-94 FAILURE DURING FLAP RETRACTION JUST AFTER TAKEOFF. PILOT DISCOVERED DEFECT DURING FLIGHT VISUALLY AND DID NOT HEAR A FAILURE OF THE CABLE OCCUR IN THE CABIN. CABLE FAILURE CAUSED AIRCRAFT TO ROLL/TURN RIGHT IN FLIGHT DUE TO LT FLAP (SLAVE FLAP) FALLING INTO FULL EXTENDED POSITION AND RT FLAP (MASTER FLAP) FULLY RETRACTING. CONTROL OF THE AIRCRAFT WAS REGAINED ONCE PILOT DISCOVERED THE CAUSE OF THE FLIGHT CONTROL DEFECT. THE U/S CABLE BROKE IN THE AREA WHERE THE CABLE ROLLS OVER THE CENTRAL FLAP PULLEY CLUSTER IN THE MIDDLE OF THE CABIN BEHIND THE HEAD LINER. FURTHER INVESTIGATION IS REQUIRED TO PIN POINT AND EXACT CAUSE OF WHY THIS FAILURE OCCURRED WHICH IS IN PROGRESS. JUDGING FROM MY OWN OPINION IT LOOKS AS IF ONE OF THE 7 OF 19 INTERNAL CABLE BUNDLES HAD FAILED PREVIOUSLY AND THE REST OF THE STANDS LOOK TO HAVE FAILED IN TENSION. THE FAILURE OF THE CABLE DOES NOT OCCUR IN ONLY ONE AREA BUT IN MULTIPLE SPOTS WITHIN APPROX 10 INCH LENGTH. THE AIRCRAFT WILL UNDER GO A FULL ABNORMAL OCCURRENCE INSPECTION AND THE FLAP CONTROL SYSTEM WILL BE DISMANTLED TO INSPECT THE ENTIRE SYSTEM FOR DEFECTS. I WILL KEEP ANY UPDATES POSTED. UPDATE- ONE OF THE LEFT (SLAVE) FLAP ROLLERS FAILED CAUSING THE FLAP TO COMPLETELY SEIZE IN THE FLAP TRACK CAUSING THE MOTOR TO TENSION THE RETRACT CABLE TO THE POINT OF FAILURE. ROLLER P/N 0523921. THE ROLLERS HAVE BEEN LUBRICATED ON THIS ACFT AT THE LEAST EVERY 100 HRS OF AIRTIME AND WE HAVE HAD PAST ISSUES WITH THESE ROLLER FAILING.

2009FA0000246

CESSNA

 

 

TUBE

FAILED

3/12/2009

172R

 

 

302013460

NLG TIRE

NOSE TUBE FAILED. TUBE SPLIT ON THE OUTSIDE DIAMETER OF TUBE. THIS TUBE INSTALLED 2-25-08. (K)

2009FA0000243

CESSNA

 

 

TUBE

FAILED

3/12/2009

172R

 

 

302246401

RT MAIN TIRE

RT MAIN TUBE FAILED. TUBE SPLIT ON THE OUTSIDE DIAMETER OF TUBE. THIS TUBE INSTALLED 5-11-07. (K)

2009FA0000244

CESSNA

 

 

TUBE

FAILED

3/12/2009

172R

 

 

XA1AC

NLG TIRE

NOSE TUBE FAILED. TUBE SPLIT ON THE OUTSIDE DIAMETER OF TUBE. THIS TUBE INSTALLED 6-25-08. (K)

2009FA0000089

CESSNA

LYC  

 

PLUG

LEAKING

2/17/2009

172R

IO360L2A

 

STD1211

CRANKSHAFT

CRANKSHAFT PLUG IMPROPERLY INSTALLED LEAKING OIL.

2009FA0000207

CESSNA

 

 

ACTUATOR

CRACKED

2/24/2009

172RG

 

 

98820

LT MLG

AFTER LANDING GEAR WAS RETRACTED IN, IT WAS NOTED THAT THE LT LANDING GEAR ASSY DID NOT FULLY RETRACT INTO THE WELL. THE PILOT WAS INFORMED AND IMMEDIATELY RETURNED TO THE AIRPORT. DURING THE RETRACT TEST, IT WAS FOUND THAT THE LEFT GEAR HUNG UP AT THE MIDWAY POSITION BUT WAS ABLE TO EXTEND BACK DOWN FULLY. UPON REMOVAL OF THE MLG ACTUATOR IT WAS DISCOVERED THAT THE ACTUATOR HSG HAD CRACKED A THE FWD MOST SECURING BOLT HOLE. AFTER FURTHER INVESTIGATION, IT HAS BEEN DETERMINED THAT THIS OCCURRENCE HAS HAPPENED FREQUENTLY TO MANY ACFT IN SAME LOCATION BUT RESULTING IN A GEAR UP LANDING. THE ACTUATOR ASSY IS THE ORIGINAL ACTUATOR THAT CAME WITH THE ACFT AT MFG AND IS DATED 1980. (K)

2009FA0000157

CESSNA

LYC  

 

PIVOT ASSY

CRACKED

3/2/2009

172RG

O360F1A6

 

244110010

LT MLG

LT MAIN LANDING PIVOT FOUND CRACKED WHEN INSPECTED IAW SEB90-1 REV 3 DURING 100 HOUR INSPECTION.

2009FA0000158

CESSNA

LYC  

 

PIVOT SUPPORT

CRACKED

3/2/2009

172RG

O360F1A6

 

244110010

MLG 

RT MAIN LANDING PIVOT FOUND CRACKED WHEN INSPECTED IAW SEB90-1 REV 3 DURING 100 HOUR INSPECTION.

2009FA0000159

CESSNA

LYC  

 

PIVOT

CRACKED

3/2/2009

172RG

O360F1A6

 

244110010

LT MLG

LEFT MAIN LANDING PIVOT FOUND CRACKED WHEN INSPECTED IAW SEB90-1 REV 3.

2009FA0000063

CESSNA

LYC  

 

PIN  

BROKEN

2/4/2009

172RG

O360F1A6

 

12802091

NLG DOWNLOCK

ONE OF THE NOSE GEAR DOWNLOCK PINS BROKE, AT THE GROOVE MACHINED INTO THE PIN FOR ROLLPIN RETENTION, ALLOWING THE UNSECURED PORTION OF THE PIN TO JAM THE NOSE GEAR DOWNLOCK HOOKS. THIS RESULTED IN A GEAR UNSAFE INDICATION AND SUBSEQUENT NOSE GEAR COLLAPSE ON LANDING.

CA090115007

CESSNA

LYC  

 

GEAR

WORN

1/7/2009

172RG

O360F1A6

 

 

MAGNETO

DURING SCHEDULED 500 HOUR MAGNETO INSPECTION IT WAS NOTED THAT THERE WAS ALOT OF WHITE DUST INSIDE MAGNETO. THEN IT WAS NOTED THAT THE PLASTIC GEAR TEETH WERE PARTIALLY WORN AWAY DUE TO BEING IMPROPERLY MESHED WITH THE PLASTIC DISTRIBUTOR GEAR DUE TO THE GEAR NOT BEING DRIVEN DOWN AND SEATED ON THE MAGNETO SHAFT, BOTH MAGNETOS HAD SAME CONDITION ALTHOUGH ONE WAS FAR WORSE THAN THE OTHER.

2009FA0000241

CESSNA

 

 

TUBE

FAILED

3/12/2009

172S

 

 

0923150

LT MLG TIRE

LT MAIN TUBE FAILED. TUBE SPLIT ON THE OUTSIDE DIAMETER OF TUBE. THIS TUBE INSTALLED 9-24-07. (K)

2009FA0000227

CESSNA

LYC  

 

GUIDE

CHAFED

2/20/2009

172S

IO360L2A

 

 

AILERONS

DURING 100 HR INSP, FOUND LT AND RT AILERON CABLES WORN THROUGH SEVERAL STRANDS AT WING STA 71. THERE IS A CABLE RUB BLOCK INSTALLED ON THE RIB AT THIS STATION. IT IS CAUSING EXCESSIVE WEAR TO THE CABLES. REPLACED BOTH CABLES IN LT AND RT WINGS. P/N 0510105-362, 0510105-364 AND 0510105-365. RECOMMEND INSPECTING THIS AREA CLOSER SINCE IT IS HARD TO SEE AND THERE ARE NO ACCESS PANELS INSTALLED IN THE AREA. INSPECT THE CABLES LOOKING THROUGH THE FLAP PUSHROD HOLE JUST AFT OF THE REAR SPAR. MOVE THE AILERONS TO FULL UP AND FULL DOWN TO SEE THE AREA OF WEAR ON THE CABLE. WE FOUND THIS ON ANOTHER MODEL AS WELL.

CA090130012

CESSNA

LYC  

KELLY

GEAR

FAILED

1/18/2009

172S

IO360L2A

 

MHB6018

STARTER

DURING POST INSPECTION, ENGINE FAILED TO START. INTERMITTENT ENGAGEMENT OF BENDIX. ONCE REMOVED AXIAL MOVEMENT OF INTERNAL PARTS AS COMPARED TO A NEW STARTER SEEMED EXCESSIVE. STARTER WAS REPLACED AND NOT FURTHER ISSUES WERE NOTED.

CA090206001

CESSNA

LYC  

 

CONTROL CABLE

WORN

2/5/2009

172S

IO360L2A

 

0510105364

AILERON BALANCE

FOUND DURING AN INSPECTION THAT THE AILERON BALANCE CONTROL CABLE WAS WORN AT STATION 71.125.

2009FA0000210

CESSNA

LYC  

 

CYLINDER HEAD

BROKEN

2/18/2009

172S

IO360L2A

 

AEL85099

ENGINE

ACFT WAS DOING A STEADY CLIMB AFTER TAKEOFF WHEN HE HEARD A LOUD BANG AND LOST RPM. PILOT LANDED THE PLANE BACK ON THE RUNWAY. FUND THE CYLINDER HEAD ON NR 4 CYLINDER COMPLETELY BLOWN OFF. PROBABLE CAUSE COULD POSSIBLY BE MORE DEFECTIVE CYL ASSY THAN CALLED OUT IN AD 08-19-05. THIS CYL ASSY IS OUTSIDE THE SN RANGE. RECOMMEND INSTALLING CYL ASSY. (K)

2009FA0000085

CESSNA

PWA  

 

HINGE

CORRODED

1/24/2009

208B

PT6*

 

26310461

VERTICAL STAB

DURING THE REMOVAL OF THE RUDDER, LWR STABILIZER HINGE ASSY WAS FOUND WITH HEAVY CORROSION. THIS CORROSION WAS NOT VISIBLE WITHOUT REMOVING THE RUDDER. (K)

CA090127003

CESSNA

PWA  

 

PUMP

FAILED

1/25/2009

208B

PT6A114A

 

025323150

ENGINE FUEL

AME NOTICED FUEL IN THE DRAIN CAN ON A DAILY CHECK. DURING A SUBSEQUENT GROUND RUN HE FEELS THAT THE ENGINE PERFORMANCE FROM LOW TO HIGH IDLE IS NOT AS FAST AS IT SHOULD BE. THE AIRCRAFT IS GROUNDED AND A REPLACEMENT PUMP ASSY AND SUPPORT PARTS HAVE BEEN DISPATCHED.

CA090126009

CESSNA

PWA  

CLEVELANDPNU

TUBE

FAILED

1/23/2009

208B

PT6A114A

40179

302129402

 

TIRE WENT FLAT IN HANGAR AFTER AIRCRAFT WAS PUT IN FOR THE NIGHT. WHEEL ASSEMBLY INSPECTED AND SMALL HOLE FOUND IN TUBE. NOTHING FOUND IN TIRE TO CAUSE HOLE.

CA090122010

CESSNA

PWA  

CESSNA

PLUNGER

OUT OF POSITION

1/19/2009

208B

PT6A114A

261705713

 

 

PILOT REPORT, EN ROUTE TO YQT AT 9000 FEET, THE UPPER HALF OF REAR CARGO DOOR OPENED IN FLIGHT AND DOOR WARNING ANNUNCIATOR ILLUMINATED. LOWERED FLAPS AND SLOWED AIRCRAFT TO 100 KTS AS PER AFM. REQUESTED DIRECT TO NEAREST AIRPORT (YQK) AND LANDED WITH OUT INCIDENT. VISUALLY INSPECTED DOOR FOR DAMAGE AS A RESULT OF FLYING WHILE OPEN. INSPECTED LOCKING MECHANISM WHICH SEEMED TO WORK PROPERLY. SECURED DOOR AND CONTINUES TO YQT WITHOUT FURTHER PROBLEMS. CARGO DOOR (UPPER) HINGE INSPECTED, DOOR SKIN INSPECTED. UPPER DOOR INSIDE PANEL REMOVED AND LATCHING MECHANISM INSPECTED. NO FAULTS FOUND. INSIDE PANEL REINSTALLED USING EXISTING HARDWARE. SUSPECT, PLUNGER P/N K5SN WAS NOT FULLY IN ITS DETENT WHICH ALLOWED THE OUTER DOOR HANDLE P/N 2617094-16 TO ROTATE OPEN IN FLIGHT AIRCRAFT 6233 HOURS TSN.

CA090206010

CESSNA

PWA  

 

TIRE

DEFLATED

2/5/2009

208B

PT6A114A

 

40179

MLG 

AFTER LOADING THE AIRCRAFT THE LEFT MAIN TIRE WAS FOUND TO BE FLAT. THE TIRE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.

CA090206006

CESSNA

PWA  

 

TIRE

DEFLATED

2/4/2009

208B

PT6A114A

 

40179

MLG 

PREFLIGHT INSPECTION SHOWED A FLAT RIGHT TIRE. NO CAUSE FOR THE FLAT HAS BEEN DETERMINED AT THIS TIME.

2009FA0000248

CESSNA

PWA  

 

MOUNT

DEBONDED

3/19/2009

414A

PW545A

 

99124801

NR 1 ENGINE

DURING NR 1 ENGINE REMOVAL FROM ACFT, FOUND NR 1 ENGINE ISOLATOR MOUNT ALIGNMENT PUCK DEBONDED AND SEPARATED FROM THE MAIN BODY OF THE ISOLATOR. (K)

CA090209001

CESSNA

CONT

 

ATTACH BOLT

CRACKED

1/23/2009

421  

GTSIO520D

 

NAS464P10LA32

WING 

THIS BOLT WAS INSPECTED DURING THE ANNUAL INSPECTION OF THIS AIRCRAFT. IT WAS VISUALLY SEEN TO HAVE WHAT LOOKED LIKE A CRACK ON THE HEAD SURFACE OF THE BOLT. THIS COULD BE MISTAKEN AS DAMAGE FROM A DRIFT OR HAMMER DONE DURING INSTALLATION. THE PART WAS REMOVED FROM SERVICE, AND SENT FOR NDT INSPECTION. THE INSPECTOR PERFORMED BOTH MAG PARTICLE AND PENETRANT INSPECTIONS AND DETERMINE WITH BOTH METHODS THAT THE BOLT IS IN FACT CRACKED. THEY ARE GUESSING THE CRACK DEPTH TO BE APPROXIMATELY .020-.030 INCH DEEP. THEY ALSO SUGGESTED THAT THIS COULD HAVE BEEN A MANUFACTURING DEFECT CAUSED DURING ANY HARDENING PROCESS THAT MAY HAVE BEEN PERFORMED. THIS PART IS AVAILABLE FOR FURTHER INSPECTION. THE TIME ON THE PART HAPPENS TO BE THE TOTAL TIME OF THE AIRCRAFT AS THERE IS NO RECORD IN THE LOGS WHICH DATE BACK TO 2001 (THE ONLY LOGS AVAILABLE AT TIME OF REPORT) WHICH INDICATES BOLT HAS BEEN REPLACED.

2009F00016

CESSNA

 

 

GEARBOX

LOCKED

2/24/2009

421B

 

 

 

LT MLG

LANDING GEAR WOULD NOT EXTEND ELECTRICALLY OR BY UTILIZING THE EMERGENCY GEAR EXTENSION SYSTEM. THE ACFT LANDED GEAR UP. POST INCIDENT INVESTIGATION WAS CONDUCTED ON SCENE AND A COMPLETE INSPECTION OF THE LANDING GEAR SYS WAS CONDUCTED WITH NO FINDINGS AS TO THE CAUSE. THE ONLY COMPONENT THAT WAS NOT DISASSEMBLED WAS THE LANDING GEARBOX. SUSPECT THAT FOREIGN MATTER BECAME LODGED IN THE GEARBOX PREVENTING NORMAL OPERATION. HOWEVER, THE GEAR SYSTEM OPERATED NORMALLY BOTH ELECTRICALLY AND MANUALLY AFTER THE INCIDENT. SUSPECT FOREIGN MATTER BECAME DISLODGED DURING INCIDENT FORCES OR SUBSEQUENT HANDLING OF THE AIRCRAFT.

2009FA0000193

CESSNA

 

 

LINE

CUT  

9/2/2008

425  

 

 

 

PNEUMATIC SYS

PREVIOUSLY REPORTED TO MFG, DURING THE SUPPLEMENTAL INSP FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. DURING SUPPLEMENTAL INSP NR 57-10-14 CARRY-THRU FWD SPAR CAP, FOUND MULTIPLE PNEUMATIC LINES SPLICED TOGETHER WITH STANDARD MIL-SPEC HOSE ON LT AND RT WINGS. LINES NOT AVAILABLE FROM MFG. FABRICATED LINES FROM PN R3/4X049-T3, WWT-700/4X.500, WWT-700/4X.625 AND R3/8X035-50. INSTALLED LINES AND UNION BACK TO ORIGINAL IPC 36-10-00 CONFIGURATION.

2009FA0000194

CESSNA

 

 

LINE

CUT  

3/9/2009

425  

 

 

 

ZONE 500

PERFORMED SUPPLEMENTAL INSP FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. DURING SUP INSP NR 57-10-14 CARRY-THRU FWD SPAR CAP, FOUND MULTIPLE PNEUMATIC LINES SPLICED TOGETHER WITH STANDARD MIL-SPEC HOSE ON LT AND RT WINGS. LINES NOT AVAILABLE FROM MFG. FABRICATED LINES FROM PN R3/4X049-T3, WWT-700/4X.500, WWT-700/4X.625 AND R3/8X035-50. INSTALLED LINES AND UNION BACK TO ORIGINAL IPC 36-10-00 CONFIGURATION.

2009FA0000195

CESSNA

 

 

LINE

CUT  

3/9/2009

425  

 

 

 

ZONE 500

PERFORMED SUPPLEMENTAL INSP FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. DURING SUPPLEMENTAL INSP NR 57-10-14 CARRY-THRU FWD SPAR CAP FOUND MULTIPLE PNEUMATIC LINES SPLICED TOGETHER WITH STANDARD MIL-SPEC HOSE ON LT AND RT WINGS. LINES NOT AVAILABLE FROM MFG. FABRICATED LINES FROM PN R3/4X049-T3, WWT-700/4X.500, WWT-700/4X.625 AND R3/8X035-50. INSTALLED LINES AND UNION BACK TO ORIGINAL IPC 36-10-00 CONFIGURATION.

2009FA0000196

CESSNA

 

 

LINE

CUT  

8/4/2008

425  

 

 

 

ZONE 500

PREVIOUSLY REPORTED DURING SUPPLEMENTAL INSP FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. DURING SUP INSP NR 57-10-14 CARRY-THRU FWD SPAR CAP FOUND MULTIPLE PNEUMATIC LINES SPLICED TOGETHER WITH STANDARD MIL-SPEC HOSE ON LT AND RT WINGS. LINES NOT AVAILABLE FROM MFG. FABRICATED LINES FROM PN R3/4X049-T3, WWT-700/4X.500, WWT-700/4X.625 AND R3/8X035-50. INSTALLED LINES AND UNION BACK TO ORIGINAL IPC 36-10-00 CONFIGURATION.

2009FA0000178

CESSNA

 

CESSNA

TORQUE TUBE

CORRODED

3/5/2009

425  

 

 

58330119

ZONE 300

REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN THE SUPPLEMENTAL INSPECTION DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. FOUND RUDDER TORQUE TUBE RUSTED DURING SUPPLEMENTAL INSPECTION 27-20-04. REPLACED TORQUE TUBE PN 5833011-9.

2009FA0000179

CESSNA

 

 

FITTING

CORRODED

3/5/2009

425  

 

 

081135010

ZONE 500

REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN THEIR SUPPLEMENTAL INSPECTION DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. FOUND LT LWR FWD FITTING CORRODED. REPLACED FITTING PN 0811350-10.

2009FA0000180

CESSNA

 

 

FITTING

CORRODED

3/5/2009

425  

 

 

081135010

ZONE 600

REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN THEIR SUPPLEMENTAL INSPECTION DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. FOUND RT LOWER FWD FITTING CORRODED. REPLACED FITTING PN 0811350-10.

2009FA0000148

CESSNA

 

 

TRUSS

CORRODED

2/27/2009

425  

 

 

595105137

RT WING

DURING SUPPLEMENTAL INSP 54-10-02 FOUND LT WING INBD TRUSS ASSLY PN 5951051-37 SEVERELY PITTED. SENT OUT FOR REPAIR.

2009FA0000165

CESSNA

 

 

HINGE

CORRODED

3/3/2009

425  

 

 

51115128

ZONE 800

REPORTED TO MFG DURING SUPPLEMENTAL INSPECTION FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. DURING SUPPLEMENTAL INSPECTION NR 52-10-01 CABIN DOOR RETENTION FOUND HARDWARE UNABLE TO REMOVE FROM UPPER CABIN DOOR DUE TO CORROSION. DRILLED OFF UPPER AND LOWER CABIN DOOR HINGE SUPPORTS TO REMOVE DOOR FOR INSPECTION. INSTALLED TWO NEW HINGE SUPPORTS. REPLACED HARDWARE, BUSHINGS, STAT-O-SEALS, BEARINGS, BOLTS, AND NUTS.

2009FA0000171

CESSNA

 

 

STRUT

SCRATCHED

8/4/2008

425  

 

 

59411302

ZONE 700

PREVIOUSLY REPORTED DURING SUPPLEMENTAL INSPECTION FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. LT MLG PISTON BARREL HAS DEEP SCRATCHES IAW SUPPLEMENTAL INSPECTION NR 32-10-06. REPLACE PISTON BARREL WITH PN 5941132-8.

2009FA0000160

CESSNA

 

 

HINGE

CORRODED

9/2/2008

425  

 

 

51115128

ZONE 800

PREVIOUSLY REPORTED TO MFG DURING SUPPLEMENTAL INSPECTION FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. DURING SUPPLEMENTAL INSP NR 52-10-01 CABIN DOOR RETENTION FOUND HARDWARE UNABLE TO REMOVE FROM UPPER CABIN DOOR DUE TO CORROSION. DRILLED OFF UPPER AND LOWER CABIN DOOR HINGE SUPPORTS TO REMOVE DOOR FOR INSPECTION. INSTALLED TWO NEW HINGE SUPPORTS. REPLACED HARDWARE, BUSHINGS, STAT-O-SEALS, BEARINGS, BOLTS, AND NUTS.

2009FA0000161

CESSNA

 

 

HINGE

CORRODED

12/17/2008

425  

 

 

51115128

ZONE 800

PREVIOUSLY REPORTED TO MFG DURING SUPPLEMENTAL INSP FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. DURING SUPPLEMENTAL INSPECTION NR 52-10-01 CABIN DOOR RETENTION FOUND HARDWARE UNABLE TO REMOVE FROM UPPER CABIN DOOR DUE TO CORROSION. DRILLED OFF UPPER AND LOWER CABIN DOOR HINGE SUPPORTS TO REMOVE DOOR FOR INSPECTION. INSTALLED TWO NEW HINGE SUPPORTS. REPLACED HARDWARE, BUSHINGS, STAT-O-SEALS, BEARINGS, BOLTS, AND NUTS.

2009FA0000162

CESSNA

 

 

HINGE

CORRODED

8/4/2008

425  

 

 

51115128

ZONE 800

PREVIOUSLY REPORTED DURING SUPPLEMENTAL INSPECTION FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. DURING SUPPLEMENTAL INSPECTION NR 52-10-01 CABIN DOOR RETENTION FOUND HARDWARE UNABLE TO REMOVE FROM UPPER CABIN DOOR DUE TO CORROSION. DRILLED OFF UPPER AND LOWER CABIN DOOR HINGE SUPPORTS TO REMOVE DOOR FOR INSPECTION. INSTALLED TWO NEW HINGE SUPPORTS PART NUMBER 5111512-8. REPLACED HARDWARE, BUSHINGS, STAT-O-SEALS, BEARINGS, BOLTS, AND NUTS.

2009FA0000163

CESSNA

 

 

HINGE

CORRODED

3/3/2009

425  

 

 

51115128

ZONE 800

PREVIOUSLY REPORTED TO MFG DURING SUPPLEMENTAL INSPECTION FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. DURING SUPPLEMENTAL INSPECTION NR 52-10-01 CABIN DOOR RETENTION FOUND HARDWARE UNABLE TO REMOVE FROM UPPER CABIN DOOR DUE TO CORROSION. DRILLED OFF UPPER AND LOWER CABIN DOOR HINGE SUPPORTS TO REMOVE DOOR FOR INSPECTION. INSTALLED TWO NEW HINGE SUPPORTS PN 5111512-8. REPLACED HARDWARE, BUSHINGS, STAT-O-SEALS, BEARINGS, BOLTS, AND NUTS.

2009FA0000175

CESSNA

 

 

PISTON

CORRODED

8/4/2008

425  

 

 

59411361

MLG STRUT

PREVIOUSLY REPORTED TO MFG DURING SUPPLEMENTAL INSPECTION FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. DURING DISASSEMBLY AND INSPECTION IAW SUPPLENTAL INSPECTION NR 32-10-06 FOUND DEEP SCRATCHES AND CORROSION ON THE ISOLATION PISTON PN 5941136-1. REPLACED ISOLATION PISTON.

2009FA0000167

CESSNA

 

 

ACTUATOR

CRACKED

8/4/2008

425  

 

 

57151608

ELEVATOR TRIM

PREVIOUSLY REPORTED DURING SUPPLEMENTAL INSPECTIONS FOR CONTINUED AIRWORTHINESS FOR THE AIRPLANE. DURING REASSEMBLE OF ELEVATOR TRIM TAB ACUTATOR IAW MM 27-30-02 FOUND BARREL CRACKED AND VERIFIED BY EDDY CURRENT INSPECTION. REPLACED ACTUATOR WITH PN 5715160-8.

2009FA0000168

CESSNA

 

 

ACTUATOR

CORRODED

3/3/2009

425  

 

 

57151608

ELEVATOR TRIM

REPORTED DURING SUPPLEMENTAL INSPECTIONS FOR CONTINUED AIRWORTHINESS FOR THE AIRPLANE. DURING INSPECTION OF ELEVATOR TRIM TAB ACUTATOR IAW MM 27-30-02 FOUND BARREL CORRODED AND PITTED. REPLACED ACTUATOR WITH PN 5715160-8.

2009FA0000169

CESSNA

 

 

ACTUATOR

CORRODED

3/3/2009

425  

 

 

57151608

ELEVATOR TRIM

REPORTED DURING SUPPLEMENTAL INSPECTIONS FOR CONTINUED AIRWORTHINESS FOR THE AIRPLANE. DURING INSPECTION OF ELEVATOR TRIM TAB ACUTATOR IAW MM 27-30-02 FOUND BARREL CORRODED. REPLACED ACTUATOR WITH PN 5715160-8.

2009FA0000170

CESSNA

 

 

ACTUATOR

CORRODED

3/3/2009

425  

 

 

57151608

ELEVATOR TRIM

REPORTED DURING SUPPLEMENTAL INSPECTIONS FOR CONTINUED AIRWORTHINESS FOR THE AIRPLANE. DURING INSPECTION OF ELEVATOR TRIM TAB ACUTATOR IAW MM 27-30-02 FOUND BARREL CORRODED. REPLACED ACTUATOR WITH PN 5715160-8.

2009FA0000164

CESSNA

 

 

HINGE

CORRODED

3/3/2009

425  

 

 

51115128

ZONE 800

PREVIOUSLY REPORTED TO MFG DURING SUPPLEMENTAL INSPECTION FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. DURING SUPPLEMENTAL INSPECTION NR 52-10-01 CABIN DOOR RETENTION FOUND HARDWARE UNABLE TO REMOVE FROM UPPER CABIN DOOR DUE TO CORROSION. DRILLED OFF UPPER AND LOWER CABIN DOOR HINGE SUPPORTS TO REMOVE DOOR FOR INSPECTION. INSTALLED TWO NEW HINGE SUPPORTS. REPLACED HARDWARE, BUSHINGS, STAT-O-SEALS, BEARINGS, BOLTS, AND NUTS.

2009FA0000172

CESSNA

 

 

STRUT

WORN

2/12/2009

425  

 

 

59411302

LT MAIN GEAR

PREVIOUSLY REPORTED DURING SUPPLEMENTAL INSPECTION FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. LT MLG PISTON BARREL HAS BARE METAL SPOTS FOUND DURING SUPPLEMENTAL INSP NR 32-10-06. REPAIRED PISTON BARREL WITH PROTECTIVE COATING.

2009FA0000177

CESSNA

 

 

STRUT

WORN

2/12/2009

425  

 

 

59411302

ZONE 700

PREVIOUSLY REPORTED DURING SUPPLEMENTAL INSPECTION FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. DURING DIASSEMBLY AND INSPECTION IAW SUPPLENTAL INSPECTION NR 32-10-06 FOUND PROTECTIVE COATING WORN OFF PISTON BARREL PN 5941132-8. REPAIRED PISTON BARREL WITH PROTECTIVE COATING.

2009FA0000149

CESSNA

 

 

TRUSS

CORRODED

2/27/2009

425  

 

 

595105138

RT WING

DURING SUPPLEMENTAL INSPECTION 54-10-02 FOUND RT WING INBD TRUSS ASSY PN 5951051-38 SEVERELY PITTED. SENT OUT FOR REPAIR.

2009FA0000150

CESSNA

 

 

TRUSS

CORRODED

2/27/2009

425  

 

 

595105137

LT WING

DURING SUPPLEMENTAL INSPECTION 54-10-02 FOUND LT WING INBD TRUSS ASSY PN 5951051-37 SEVERELY PITTED. SENT OUT FOR REPAIR.

2009FA0000151

CESSNA

 

 

TRUSS

CORRODED

2/27/2009

425  

 

 

595105138

RT WING

DURING SUPPLEMENTAL INSPECTION 54-10-02 FOUND RT WING INBD TRUSS ASSY PN 5951051-38 SEVERELY PITTED. SENT OUT FOR REPAIR.

2009FA0000152

CESSNA

 

 

TRUSS

CORRODED

2/27/2009

425  

 

 

595105137

LT WING

DURING SUPPLEMENTAL INSPECTION 54-10-02 FOUND LT WING INBD TRUSS ASSY PN 5951051-37 SEVERELY PITTED. SENT OUT FOR REPAIR.

2009FA0000153

CESSNA

 

 

TRUSS

CORRODED

2/27/2009

425  

 

 

595105138

RT WING

DURING SUPPLEMENTAL INSPECTION 54-10-02 FOUND RT WING INBD TRUSS ASSY PN 5951051-38 SEVERELY PITTED. SENT OUT FOR REPAIR.

2009FA0000154

CESSNA

 

 

TRUSS

CORRODED

2/27/2009

425  

 

 

595105135

LT WING

DURING SUPPLEMENTAL INSPECTION 54-10-02 FOUND LT WING OTBD TRUSS ASSY PN 5951051-35 SEVERELY PITTED. SENT OUT FOR REPAIR.

2009FA0000155

CESSNA

 

 

TRUSS

CORRODED

2/27/2009

425  

 

 

595105135

LT WING

DURING SUPPLEMENTAL INSPECTION 54-10-02 FOUND LT WING OTBD TRUSS ASSY PN 5951051-35 SEVERELY PITTED. SENT OUT FOR REPAIR.

2009FA0000128

CESSNA

 

 

MAST

RUSTED

2/25/2009

425  

 

 

58330119

RUDDER

PREVIOUSLY REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN THE SUPPLEMENTAL INSPECTION DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. FOUND RUDDER TORQUE TUBE RUSTED DURING INSPECTION OF SUPPLEMENTAL INSPECTION 27-20-04. REPLACED TORQUE TUBE PN 5833011-9.

2009FA0000140

CESSNA

 

 

BELLCRANK

CRACKED

9/2/2008

425  

 

 

59420011

ZONE 700

PREVIOUSLY REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN SUPPLEMENTAL INSPECTION DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. NOSE GEAR STEERING BELLCRANK PN 5942001-1 FAILED NDT IAW SUPPLEMENTAL INSPECTION 32-50-00. REPLACED BELLCRANK WITH PN 5942001-1.

2009FA0000118

CESSNA

 

 

FITTING

MISREPAIRED

2/25/2009

425  

 

 

082255030

ZONE 600

PREVIOUSLY REPORTED IAW INSTRUCTIONS BY MFG SUPPLEMENTAL INSPECTION DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. THE RT WING UPPER FWD ATTACH FITTING PN 0822550-30 HAD UNAPPROVED STEEL BUSHING UNABLE TO PERFORM NDT INSPECTION. REPLACED WING FITTING.

2009FA0000119

CESSNA

 

 

FITTING

CORRODED

2/25/2009

425  

 

 

081135010

ZONE 600

PREVIOUSLY REPORTED IAW INSTRUCTIONS BY MFG SUPPLEMENTAL INSPECTION DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. THE RT WING LWR FWD ATTACH FITTING PN0811350-10 FAILED NDT INSPECTION. REPLACED WING FITTING.

2009FA0000134

CESSNA

 

 

FORK

CRACKED

12/17/2008

425  

 

 

58420005

NLG 

PREVIOUSLY REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN SUPPLEMENTAL INSPECTION DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. NOSE GEAR FORK FAILED NDT IAW SUPPLEMENTAL INSPECTION 32-20-02. REPLACED NOSE FORK ASSEMBLY PN 5842000-5.

2009FA0000135

CESSNA

PWA  

 

FORK

CRACKED

2/26/2009

425  

PT6*

 

58420005

ZONE 700

PREVIOUSLY REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN SUPPLEMENTAL INSPECTION DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. NOSE GEAR FORK FAILED NDT IAW SUPPLEMENTAL INSPECTION 32-20-02. REPLACED NOSE FORK ASSEMBLY PN 5842000-5.

2009FA0000136

CESSNA

PWA  

 

FORK

CRACKED

2/26/2009

425  

PT6*

 

58420005

ZONE 700

PREVIOUSLY REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN SUPPLEMENTAL INSPECTION DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. NOSE GEAR FORK FAILED NDT IAW SUPPLEMENTAL INSPECTION 32-20-02. REPLACED NOSE FORK ASSEMBLY PN 5842000-5.

2009FA0000137

CESSNA

PWA  

 

FORK

CRACKED

2/26/2009

425  

PT6*

 

58420005

ZONE 700

PREVIOUSLY REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN SUPPLEMENTAL INSPECTION DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. NOSE GEAR FORK FAILED NDT IAW SUPPLEMENTAL INSPECTION 32-20-02. REPLACED NOSE FORK ASSEMBLY PN 5842000-5.

2009FA0000141

CESSNA

PWA  

 

BELLCRANK

CRACKED

8/4/2008

425  

PT6*

 

59420011

NLG STEERING

PREVIOUSLY REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN SUPPLEMENTAL INSPECTION DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. NOSE GEAR STEERING BELLCRANK PN 5942001-1 FAILED VISUAL AND NDT INSPECTION IAW SUPPLEMENTAL INSPECTION 32-50-00. REPLACED BELLCRANK WITH PN 5942001-1.

2009FA0000142

CESSNA

PWA  

 

BELLCRANK

CRACKED

2/26/2009

425  

PT6*

 

59420011

NLG STEERING

PREVIOUSLY REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN SUPPLEMENTAL INSPECTION DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. NOSE GEAR STEERING BELLCRANK PN 5942001-1 FAILED VISUAL AND NDT INSPECTION IAW SUPPLEMENTAL INSPECTION 32-50-00. REPLACED BELLCRANK WITH PN 5942001-1.

2009FA0000143

CESSNA

PWA  

 

BELLCRANK

CRACKED

2/26/2009

425  

PT6*

 

59420011

NLG STEERING

PREVIOUSLY REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN SUPPLEMENTAL INSPECTION DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. NOSE GEAR STEERING BELLCRANK PN 5942001-1 FAILED VISUAL AND NDT INSPECTION IAW SUPPLEMENTAL INSPECTION 32-50-00. REPLACED BELLCRANK WITH PN 5942001-1.

2009FA0000144

CESSNA

PWA  

 

BELLCRANK

CRACKED

2/26/2009

425  

PT6*

 

59420011

NLG STEERING

PREVIOUSLY REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN SUPPLEMENTAL INSPECTION DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. NOSE GEAR STEERING BELLCRANK PN 5942001-1 FAILED VISUAL AND NDT INSPECTION IAW SUPPLEMENTAL INSPECTION 32-50-00. REPLACED BELLCRANK WITH PN 5942001-1.

2009FA0000138

CESSNA

PWA  

 

STRUT

CRACKED

2/26/2009

425  

PT6*

 

5842000230

NLG 

PREVIOUSLY REPORTED TO MFG IAW INSTRUCTIONS STIPULATED IN SUPPLEMENTAL INSPECTION DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. NOSE GEAR FORK FAILED NDT IAW SUPPLEMENTAL INSPECTION 32-20-02. REPLACED NOSE FORK ASSEMBLY PN 5842000-230.

2009FA0000176

CESSNA

PWA  

CESSNA

PISTON

CORRODED

8/4/2008

425  

PT6*

 

59411361

STRUT ASSY

PREVIOUSLY REPORTED DURING SUPPLEMENTAL INSPECTION FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. DURING DIASSEMBLY AND INSPECTION IAW SUPPLENTAL INSPECTION NR 32-10-06 FOUND DEEP SCRATCHES AND CORROSION ON THE ISOLATION PISTON PN 5941136-1. REPLACED ISOLATION PISTON.

2009FA0000139

CESSNA

PWA  

 

FORK

CRACKED

2/26/2009

425  

PT6A60A

 

58420005

NLG 

PREVIOUSLY REPORTED TO MFG INSTRUCTIONS STIPULATED IN SUPPLEMENTAL INSPECTION DOCUMENTS FOR CONTINUED AIRWORTHINESS OF THE AIRPLANE. NOSE GEAR FORK FAILED NDT IAW SUPPLEMENTAL INSPECTION 32-20-02. REPLACED NOSE FORK ASSEMBLY PN 5842000-5.

2009FA0000183

CESSNA

 

 

BEARING

FAILED

3/6/2009

441  

 

 

MS244624

RUDDER

DURING THE SID INSPECTION THE RUDDER WAS REMOVED. VISUALLY DISCOVERED THE TOP RUDDER PIVOT BEARING FALLING APART. THERE IS NO REQUIREMENT TO REMOVE THE RUDDER EXCEPT DURING THE SID INSPECTION CALLED OUT IN THE LATEST MANUAL REVISION 16. COULD NOT BE DETECTED WITHOUT RUDDER REMOVAL.

2009FA0000184

CESSNA

 

 

FRAME

CRACKED

3/6/2009

441  

 

 

511130915

FUSELAGE

DURING THE SID INSPECTION THE INTERIOR UPHOLSTERY WAS REQUIRED TO BE REMOVED. VISUALLY FOUND THE FUSELAGE DOOR FRAME STRUCTURE WHERE THE AFT DOOR SUPPORT CABLE MOUNTS TO BE CRACKED. THERE IS NO REQUIREMENT TO REMOVE THE SIDE WALL TRIM EXCEPT DURING THE SID INSPECTION CALLED OUT IN THE LATEST MANUAL REVISION 16. THIS COULD NOT BE DETECTED WITHOUT UPHOLSTERY REMOVAL.

2009FA0000185

CESSNA

 

CESSNA

HINGE

DAMAGED

3/6/2009

441  

 

 

5233001952330011

RUDDER

DURING THE SID INSPECTION THE RUDDER WAS REMOVED. VISUALLY DISCOVERED THE RUDDER BOTTOM HINGE BRACKET HOLES THAT BOLT TO THE BEARING TO BE EXCESSIVELY ELONGATED.

2009FA0000186

CESSNA

 

 

HINGE

DAMAGED

3/6/2009

441  

 

 

513302037

RUDDER

DURING THE SID INSP THE RUDDER WAS REMOVED. VISUALLY DISCOVERED THE RUDDER TOP HINGE BRACKET HOLES THAT BOLT TO THE BEARING TO BE EXCESSIVELY ELONGATED. THERE IS NO REQUIREMENT TO REMOVE THE RUDDER EXCEPT DURING THE SID INSP CALLED OUT IN THE LATEST MANUAL REVISION 16. THIS WOULD NOT BE DETECTED WITHOUT RUDDER REMOVAL.

2009FA0000187

CESSNA

 

 

MOUNT BRACKET  

CRACKED

3/6/2009

441  

 

 

581304412EA

NLG ACTUATOR

DURING THE SID INSP, THE NLG WAS REMOVED FOR INSPECTION. THE RETRACT ACTUATOR UPPER MOUNT WAS FOUND CRACKED WHICH ALLOWED THE DOWNLOCK OVER-CENTER TENSION TO BE REDUCED. THERE IS NO REQUIREMENT TO REMOVE THE NLG EXCEPT DURING THE SID INSPECTION CALLED OUT IN THE LATEST MANUAL REVISION 16. IT WOULD HAVE BEEN VERY DIFICULT TO FIND THIS PROBLEM WITHOUT REMOVING THE NLG.

2009FA0000188

CESSNA

 

 

DRAG BRACE

LOOSE

3/6/2009

441  

 

 

 

NLG 

DURING THE SID INSP, THE NLG WAS REMOVED FOR INSP. THE DRAG BRACE LT AND RT MOUNT BOLT HOLES WERE ALL FOUND EXCESSIVLY ELONGATED REQUIRING STRUCTURAL REPAIR. SUSPECT DAMAGE WAS CAUSED BY NORMAL TOWING OVER THE 9268 HOURS. THIS WOULD NOT BE DETECTED UNLESS THE NOSE GEAR IS REMOVED AS REQUIRED BY THE SID INSP CALLED OUT IN THE LATEST MANUAL REVISION 16.

2009FA0000190

CESSNA

 

 

HINGE

CORRODED

3/6/2009

441  

 

 

 

PAX DOOR

DURING THE SID INSP, THE UPPER CABIN DOOR WAS REMOVED FOR INSP. THE HINGE PIVOT BOLTS COULD NOT BE REMOVED BECAUSE THE BOLTS, BUSHINGS AND BEARINGS WERE ALL RUSTED SOLID. THIS CAUSED THE BOLTS TO PIVOT IN THE FUSELAGE STRUCTURE INSTEAD OF THE BEARINGS CAUSING EXCESSIVE WEAR OF THE FUSELAGE DOOR MOUNT HOLES. THERE IS NO REQUIREMENT TO REMOVE THE UPPER CABIN DOOR EXCEPT DURING THE SID INSP, CALLED OUT IN THE LATEST MANUAL REVISION 16.

2009FA0000213

CESSNA

 

 

CHANNEL

CRACKED

3/11/2009

441  

 

 

5754429257544302

 

DURING THE SID INSP, THE ENGINES AND TRUSS ASSEMBLIES WERE REMOVED FOR INSPECTION. THE LT ENG INBD TRUSS ATTACH POINT SUPER STRUCTURE AFT OF THE FIREWALL WAS FOUND CRACKED. ACCESS TO AREA IS LIMITED.

2009FA0000214

CESSNA

 

 

CHANNEL

CRACKED

3/11/2009

441  

 

 

57111454

PAX DOOR

DURING THE SID INSP, THE LOWER DOOR WAS REMOVED FOR INSPECTION. FOUND LOWER CABIN DOOR AFT CHANNEL SUPPORTING STEP HINGE CRACKING OUT OF ACCESS HOLES. LOWER CABIN DOOR FRAME DOOR HANDLE PIVOT BOLT HOLE IS WORN OUT. CABIN DOOR FRAME IS CRACKING NEAR THE FWD END OF THE LOWER CABIN DOOR END CAP. FOUND THAT THE CABIN DOOR SKIN IS CRACKED.

2009FA0000215

CESSNA

 

 

SKIN

DEBONDED

3/11/2009

441  

 

 

 

HORIZONTAL STAB

DURING THE SID INSP, FOUND AREA OF DE-BOND IN HORIZONTAL STABILIZER. REPAIRED DE-BOND AREA BETWEEN PN 5732133-2, STRINGERS AND HORIZONTAL STABILIZER LOWER SKIN PANEL PN 5732130-17 AND -18 IAW FORM 8110-3 INSTRUCTIONS. THIS DE-BONDING WOULD NOT HAVE BEEN FOUND WITHOUT DOING THE SID INSPECTION.

2009FA0000216

CESSNA

 

 

HINGE

DAMAGED

3/11/2009

441  

 

 

 

PAX DOOR

DURING THE SID INSP THE UPPER CABIN DOOR WAS REMOVED FOR INSP. THE HINGE PIVOT BOLTS COULD NOT BE REMOVED BECAUSE THE BOLTS, BUSHINGS AND BRGS WERE ALL RUSTED SOLID. THIS CAUSED THE BOLTS TO PIVOT IN THE FUSELAGE STRUCTURE INSTEAD OF THE BEARINGS CAUSING EXCESSIVE WEAR OF THE FUSELAGE DOOR MOUNT HOLES. THERE IS NO REQUIREMENT TO REMOVE THE UPPER DOOR EXCEPT DURING THE SID INSP CALLED OUT IN THE LATEST MANUAL REVISION NR 16.

2009FA0000217

CESSNA

 

 

SKIN

CORRODED

3/11/2009

441  

 

 

 

WING L/E

DURING THE SID INSP THE WING SURFACE DE-ICE BOOTS WERE REQUIRED TO BE REMOVED. AFTER REMOVAL FOUND LARGE AREAS OF MODERATE CORROSION ON THE RT WING INBD AND OTBD SECTIONS. A SMALLER AREA WAS FOUND ON THE LT WING L/E.

2009FA0000259

CESSNA

 

 

BULKHEAD

CRACKED

3/27/2009

441  

 

 

57111434345

FUSELAGE

DURING THE SID INSP, THE FUSELAGE BULKHEAD AT THE FWD OPENING OF THE CABIN DOOR AND THE SECONDARY BULKHEAD WERE FOUND CRACKED, BUCKLED AND DISTORTED. THIS WAS ONLY FOUND BECAUSE THE SID INSP REQUIRES REMOVAL OF THE DOOR BAYONET RECEPTACLES FOR INSP AND THE REMOVAL OF INTERIOR SIDEWALL UPHOLSTERY.

2009FA0000212

CESSNA

GARRTT

 

WINDSHIELD

CRACKED

3/11/2009

441  

TPE331*

 

991100312

COCKPIT

DURING THE SID INSP BOTH WINDSHIELDS WERE INSPECTED USING A PRISM, BOTH WINDSHIELDS WERE FOUND CRACKED. THE CRACK CRITERIA IN THE LATEST MANUAL REVISION IS - NO CRACKS ALLOWED. IF USING THE PREVIOUS MANUAL REVISION (OR OLDER REVISION) THESE CRACKS ARE ACCEPTABLE.

2009FA0000182

CESSNA

GARRTT

 

STRUCTURE

CRACKED

3/6/2009

441  

TPE33110N

 

581201214

HORIZONTAL STAB

DURING THE SID INSP, THE HORIZONTAL STABILIZER WAS REMOVED. VISUALLY DISCOVERED THE SHELF UNDER THE HORIZ STAB WAS CRACKED AT THE AFT END WHERE IT IS RIVETED TO THE AFT HORIZ STAB MOUNT BULKHEAD.

2009FA0000206

CESSNA

PWA  

 

MOTOR

FAILED

2/18/2009

560CESSNA

JT15D5

 

MB38A1

BLOWER

THE BLOWER MOTOR FAILED INTERNALLY SENDING SMOKE INTO THE CABIN. AC WAS AT ALTITUDE WHEN SMOKE CAME OUT OF THE GASPER SYS. ACFT DESCENDED TO A LOWER ALTITUDE AND THE CABIN CLEARED. (K)

2009FA0000173

CESSNA

PWA  

 

MOTOR

BURNED OUT

2/17/2009

560CESSNA

JT15D5

 

MB38A1

OVERHEAD BLOWER

WHILE ENROUTE AT 41000 FT HEAVY ACRID BLACK SMOKE THE INUNDATED CABIN. OXYGEN MASKS WERE DEPLOYED AND AN EMERGENCY DESCENT WAS INITIATED. ACFT WAS LANDED AT THE NEAREST SUITABLE AIRPORT WITHOUT INCIDENT. ON FEB 21ST, MX IDENTIFIED THE MALFUCTION AS A OVERHEAD BLOWER FAN AND REPLACED WITH NEW FAN ASSY. THE ACFT WAS SUBSQUENTLY RETURNED TO ITS HOME BASE FOR CLEANING AND INTERIOR RESTORATION.

2009FA0000077

CESSNA

 

 

AUTOPILOT SYS

FAILED

11/16/2007

650  

 

 

 

 

AUTOPILOT WILL NOT INITIATE, UNABLE TO ENGAGE SYS.

CA090204011

CESSNA

 

 

ACTUATOR

FAILED

1/13/2008

680CE

 

 

 

STAB TRIM

DURING PREFLIGHT, IT WAS DISCOVERED THAT THE HORIZONTAL STABILIZER TRIM POSITION INDICATION DID NOT CHANGE TO WHITE WHEN TRIM WAS IN TAKEOFF POSITION AREA. NO TAKEOFF MESSAGE REMAINED ON IN THE EICAS AND THE RED STAB NO TAKEOFF ANNUNCIATOR ILLUMINATED WHEN THRUST LEVER TAKEOFF POSITION WAS SELECTED. THE HORIZONTAL STABILIZER TRIM ACTUATOR (HSTA) WAS REPLACED BUT THE REPLACEMENT FAILED THE INDICATION TEST AS THE STAB NO TAKEOFF ANNUNCIATOR WOULD NOT ILLUMINATE. ANOTHER HSTA (OVERHAULED) WAS INSTALLED AND TESTED SERVICEABLE.

2009FA0000191

CESSNA

 

 

CYLINDER HEAD

CRACKED

3/8/2009

M337B

 

 

2947171

MLG STRUT

WHILE INVESTIGATING A HYD FLUID LEAK IN THE NOSE WHEEL WELL, LOCATED CRACK IN THE RETRACT CYLINDER HEAD BETWEEN THE ATTACH BOLT/BUSHING BOSS AND THE BARREL THREADS, IN THE UPPER RADIUS. THERE WERE NO TOOL MARKS TO CREATE A STRESS RISER, AND NO HARD LANDINGS NOTED. THIS WAS NOT VISIBLE, WITHOUT REMOVING THE RETRACT CYLINDER, AS IT WAS HIDDEN BY THE ATTACH STRUCTURE IN THE WHEEL WELL. APPROX 800 FLIGHT HOURS AND 19 YEARS SINCE LAST CYLINDER REMOVAL/RE-SEAL.

2009FA0000146

CESSNA

 

 

TORQUE LINK

BENT

2/12/2009

P210N

 

 

12434252

LANDING GEAR

WE ARE FINDING SEVERAL DEFECTIVE UPPER TORQUE LINKS BENT, CRACKED OR BOTH WITH INCREASING POTENTIAL FOR FAILURE. (K)

2009FA0000240

CESSNA

CONT

 

OIL FILTER

LOOSE

3/23/2009

P337H

TSIO360*

 

CH481081

ENGINE

PILOT REPORTED LOW OIL PRESSURE DURING TAKEOFF PHASE OF FLIGHT FOLLOWED BY NO OIL PRESSURE INDICATION SHORTLY AFTER. PILOT THOUGHT THE LOW OIL PRESSURE WAS AN INDICATION PROBLEM. UPON INSPECTION AND FUNCTIONAL CHECK OF PRESSURE GAUGE, THE INDICATOR WAS RULED OUT. A MANUAL GAUGE WAS CONNECTED TO THE ENGINE AND A FUNCTIONAL CHECKED PERFORMED. THE OIL PRESSURE SYS INITIALLY MADE 20 POUNDS PRESSURE FOLLOWED BY A DROP TO AROUND 10 POUNDS WHEN ENGINE RPM WAS SLIGHTLY INCREASED. THE OIL FILTER PN CH48108-1 WAS REMOVED FOR INSPECTION. UPON EXAMINATION THE RELIEF VALVE WAS FOUND DISPLACED AND LOOSE (FLOATING) ABOUT THE FILTER. A NEW FILTER WAS INSTALLED AND A FUNCTIONAL CHECKED PERFORMED AND OIL PRESSURE SYS WAS NORMAL.

2009FA0000156

CESSNA

 

 

PIVOT

SHEARED

3/2/2009

R182

 

 

22411143

RT MLG

DURING SLOW FLIGHT MANEUVERS THE INSTRUCTOR NOTICED THE GREEN GEAR SAFE LIGHT WAS OUT. THE STUDENT OBSERVED THE LEFT GEAR WAS HANGING OUT AND SWINGING. THE GEAR WAS CYCLED BUT THE GEAR REMAINED HANGING. AFTER CONTACTING DISPATCH THE INSTRUCTOR ELECTED TO RETRACT THE RIGHT AND NOSE GEARS AND LAND GEAR UP. MAINTENANCE FOUND THE LEFT GEAR PIVOT HAD SHEARED AT THE SPLINE SHAFT. THE RIGHT GEAR WAS REMOVED AND ZYGLO CHECKED. MAINTENANCE FOUND THE RIGHT PIVOT WAS CRACKED 3/4 AROUND THE SPLINE SHAFT, NEARING COMPLETE FAILURE. THIS CRACK AREA IS NOT NORMALLY ACCESSIBLE DURING REGULAR INSPECTIONS WITHOUT REMOVING THE GEAR ACTUATOR. CESSNA HAS BEEN NOTIFIED OF THE PROBLEM. AT THIS TIME THERE ARE NO REPLACEMENT STEEL PIVOTS AVAILABLE FOR THESE AIRCRAFT.

CA090206005

CESSNA

LYC  

 

CARBURETOR

MALFUNCTIONED

2/5/2009

R182

O540J3C5

 

LW1596070

ENGINE

DURING START AND RUNUP, NR 3 CYLINDER WAS RELUCTANT TO FIRE UNLESS THE MIXTURE WAS LEANED ALMOST TO IDLE CUTOFF. ONCE THE ENGINE WAS WARM IT WOULD RUN NORMALLY. IN FLIGHT THE EGTS WERE UNEVEN, WITH NR 3 AND NR 6 MUCH COOLER THAN THE REST. BOTH OF THESE CYLINDERS FEED OFF THE BOTTOM OF THE PLENUM AND SUSPECT THAT POORLY ATOMIZED FUEL WAS RUNNING DOWN AND ENTERING THEM, MAKING THE MIXTURE DISTRIBUTION VERY UNEVEN. REPLACING THE CARBURETOR ELIMINATED THE PROBLEM ENTIRELY.

2009FA0000226

CESSNA

 

 

RIB  

CRACKED

3/13/2009

S550

 

 

661205061

NACELLE

DURING ACCOMPLISHMENT OF STC NR ST02664CH, INSTALLATION OF ENGINES, THE PYLONS REQUIRE DISASSEMBLY AND MODIFICATION. DURING DISASSEMBLY OF THE LT PYLON, THE AFT PYLON CENTER RIB WAS FOUND CRACKED AT THE LOWER STRINGER CUT-OUT. THE CRACK EMANATES FWD FROM THE STRINGER CUT-OUT. THE LOWER FLANGE OF THE RIB IS ALSO JOGGLED AT THIS AREA.

2009FA0000225

CESSNA

WILINT

 

RIB  

CRACKED

3/13/2009

S550

FJ443A

 

661205061

NACELLE

DURING ACCOMPLISHMENT OF STC ST02661CH, INSTALLATION OF ENGINES, THE PYLON REQUIRES DISASSEMBLY AND MODIFICATION. DURING DISASSEMBLY OF BOTH LT AND RT PYLONS, THE AFT PYLON CENTER RIB WAS FOUND CRACKED AT THE LOWER STRINGER CUT-OUT. THE CRACKS ARE EMANATING FWD FROM THE STRINGER CUT-OUT. THE LOWER FLANGE OF THE RIB IS ALSO JOGGLED IN THIS AREA.

2009FA0000218

CESSNA

 

 

BRACKET

BROKEN

2/16/2009

T206H

 

 

12019951

AUTOPILOT SERVO

DURING A 100 HR/ ANNUAL INSP THE AUTOPILOT PITCH TRIM SERVO BRACKET WAS FOUND TO HAVE BROKEN FREE FROM THE 90 DEGREE SUPPORT BRACKET THAT IT ATTACHES TO. THIS BRACKET IS A FACTORY INSTALLED PART FOR THE AUTOPILOT SYS AND IS RIVETED TO THE EXISTING AIRFRAME. THE PROBABLE CAUSE TO THIS FAILURE IS EXCESSIVE VIBRATION IN THIS AREA. RECOMMENDATIONS TO PREVENT A RECURRENCE WOULD BE TO INSTALL A DOUBLER BRACKET ON THE INBD SIDE OF THE ORIGINAL BRACKET TO HELP SHARE THE LOAD AND INCREASE THE SIZE OF THE MATERIAL LOCATED IN THAT AREA. (K)

2009FA0000082

CESSNA

LYC  

 

STRUCTURE

CRACKED

2/2/2009

T206H

TIO540*

 

07232051

OUTER WING TIP

REMOVED CRACKED LT AND RT WING TIPS AND REPLACED WITH NEW PN`S 0723205-1 AND 0723205-20. REMOVED CRACKED ELEVATOR RT AND LT TIPS AND REPLACED WITH NEW PN`S 1234640-4 AND 1234640-3. REMOVED CRACKED HORIZONTAL STAB PLASTIC TIP ON RT SIDE & REPLACED WITH NEW. ACFT KEPT IN A 50 DEGREE HEATED HANGER. ACFT TAKEN OUTSIDE FOR FLT IN 17 DEGREE TEMP. INFLT TEMPS REACHED -17 DEGREES. UPON LANDING AT DESTINATION, OBSERVED THAT ALL PLASTIC WING, ELEVATOR & HORIZ STABILIZER TIPS SUSTAINED CRACKS. ALL CRACKS WERE OF SEVERITY THAT SEPARATION COULD HAVE RESULTED DURING FLT. ACFT PLACED OUT OF SERVICE UNTIL PARTS COULD BE REPLACED. MFG NOTIFIED. ALL PARTS WERE REPLACED AND THE ACFT WAS PLACED BACK IN SERVICE. (K)

2009FA0000083

CESSNA

LYC  

 

STRUCTURE

CRACKED

2/2/2009

T206H

TIO540*

 

07232052

OUTER WING TIP

REMOVED CRACKED LT AND RT WING TIPS AND REPLACED WITH NEW PN`S 0723205-1 AND 0723205-20. REMOVED CRACKED ELEVATOR RT AND LT TIPS AND REPLACED WITH NEW PN`S 1234640-4 AND 1234640-3. REMOVED CRACKED HORIZONTAL STAB PLASTIC TIP ON RT SIDE & REPLACED WITH NEW. ACFT KEPT IN A 50 DEGREE HEATED HANGER. ACFT TAKEN OUTSIDE FOR FLT IN 17 DEGREE TEMP. INFLT TEMPS REACHED -17 DEGREES. UPON LANDING AT DESTINATION, OBSERVED THAT ALL PLASTIC WING, ELEVATOR & HORIZ STABILIZER TIPS SUSTAINED CRACKS. ALL CRACKS WERE OF SEVERITY THAT SEPARATION COULD HAVE RESULTED DURING FLT. ACFT PLACED OUT OF SERVICE UNTIL PARTS COULD BE REPLACED. MFG NOTIFIED. ALL PARTS WERE REPLACED AND THE ACFT WAS PLACED BACK IN SERVICE. (K)

CA090126007

CESSNA

 

 

HEADER TANK

CRACKED

12/16/2008

T337E

 

 

14260147

FUEL SYSTEM

DURING A ANNUAL INSPECTION, FOUND CRACKS AND CORROSION HOLE IN HEADER AND AUXILIARY FUEL TANK, PARTS WERE REMOVED, REPAIRED AND REINSTALLED.

CA090126008

CESSNA

 

 

SUMP

CORRODED

12/16/2008

T337E

 

 

14260148

RT WING

DURING A ANNUAL INSPECTION, FOUND THE RT WING SUMP TO HAVE CORROSION PIN HOLES IN BOTTOM, REMOVED, REPAIRED AND REINSTALLED SUMP.

2009FA0000198

CESSNA

CONT

 

CYLINDER

CRACKED

3/10/2009

TU206G

TSIO520M

 

FRCN712

ENGINE

NR 4 CYLINDER BARREL CRACKED APPROX. 1INCH FROM THE TOP OF THE BARREL AND ALMOST .7500 INCH OF THE WAY AROUND THE INSIDE CIRCUMFERENCE. THIS WAS A NEW ECI FREEDOM STEEL BARREL CYLINDER. THE CYLINDER HAS TEST CELL AND GROUND RUN TIME ONLY, WHEN THE MECHANIC NOTICED OIL COMING FROM AROUND THE AREA OF THE BOTTOM COOLING FIN OF THE CYLINDER HEAD.

CA090204014

CESSNA

CONT

 

EXHAUST VALVE

STUCK

2/4/2009

U206E

IO520F

 

SA52006A20P

ENGINE

100 HOUR INSPECTION CARRIED OUT AND ENGINE LEAKDOWN CARRIED OUT NORMAL. AFTER ENGINE WAS COOL THE PROPELLER WAS ROTATED TO CHECK MAGNETO TO ENGINE TIMING. A BANG WAS HEARD IN THE FRONT AREA OF THE ENGINE. NR 5 AND NR 6 CYLINDER EXHAUST VALVES WERE STICKING OPEN AND WHEN THE PISTON CONTACTED, THEY WERE JARRED LOOSE AND RETURNED TO THEIR SEATED POSITION WITH VALVE SPRING PRESSURE. ALL CYLINDERS WERE REMOVED AND IT WAS DETERMINED THE EXHAUST VALVE PUSH RODS FOR NR 5 AND NR 1 CYLINDERS WERE BENT, ALONG WITH NR 1, NR 5, AND NR 6 PISTON HEADS HAD SIGNS OF CONTACT WITH THE EXHAUST VALVES. ALL CYLINDERS WERE REPLACED WITH REPAIRED UNITS. NR 1 CYLINDER EXHAUST VALVE WAS REMOVED AND INSPECTED VALVE STEM AND GUIDE. BOTH HAD CARBON DEPOSITS CREATING THE REDUCED CLEARANCE AND STICKING. THE AIRCRAFT HAD BEEN ON SURVEY WORK PRIOR TO INSPECTION WITH REDUCED POWER SETTINGS AND COLD AMBIENT OUTSIDE AIR TEMPERATURES. SUSPECT THIS MAY HAVE CONTRIBUTED SOMEWHAT, BUT THE PILOT REPORTED THAT ENGINE TEMPERATURES WERE NORMAL DURING THIS TIME. THERE WAS NO ROUGH RUNNING ENGINE IN FLIGHT, BUT THE PILOT REPORTED AFTERWARD THAT ONE START-UP ONE MORNING THERE WAS SOME BACKFIRING BUT IT WENT AWAY AND HE ATTRIBUTED IT TO COLD OUTSIDE AIR TEMPERATURES AND POSSIBLE OVER PRIMING.

2009FA0000055

CESSNA

CONT

 

DUCT

DISLODGED

2/3/2009

U206G

IO550*

 

12507351

ENGINE

THE BYPASS DOOR ON THE ENGINE AIR INDUCTION FILTER DUCT TO THE THROTTLE BODY WAS FOUND LAYING IN THE BOTTOM OF THE DUCT, THE DOOR PIN HAD FALLEN OUT AND THE DOOR, THE SPRING, AND THE HINGE PIN WERE FOUND IN THE BOTTOM OF THE DUCT , NO PARTS HAD GONE ANY FURTHER UP THE DUCT. THE BYPASS DUCT DOOR IS LOCATED DOWNSTREAM OF THE FILTER, ALL PARTS WERE ACCOUNTED FOR. THE PIN FELL OUT OF THE HINGE BECAUSE THE HINGE END WAS NOT SUFFICIENTLY STAKED CLOSED.

2009FA0000147

CIRRUS

CONT

 

SPRING

BROKEN

2/20/2009

SR20

IO360ES

 

1051324

IMPULSE COUPLING

IMPULSE COUPLING SPRING BROKE INTO 2 PIECES DISRUPTING MAGNETO TIMING. 12 MONTHS SINCE CERTIFICATION. (K)

CA090210012

CNDAIR

PWA  

 

SKIN

CRACKED

2/9/2009

CL2151A10

CA3  

 

21530023102

FS 389

DURING WINTER MAINTENANCE, A CRACK WAS FOUND AT FUSELAGE STATION 389.0/WING STATION 43 IN THE FUSELAGE SKIN NEAR THE FORWARD LEFT WING/FUSELAGE PICKUP ANGLE ATTACHMENT. THE CRACK IS APPROXIMATELY 2.5 INCH LONG AND RUNS FORE AND AFT ALONG THE BEND RADIUS IN THE FUSELAGE ROOF SKIN.

CA090122007

CNDAIR

 

 

SKIN

CRACKED

1/20/2009

CL2156B11215

 

 

21530027116

FUSELAGE

LT SKIN AT FS 388 IS CRACKED 70 MILLIMETERS LONG AND THE CRACK CONTINUES BELOW THE WING/FUSELAGE SHEAR PANEL 215-30031-1000.

CA090129008

CNDAIR

PWA  

 

TENSIONER

STUCK

1/29/2009

CL2156B11215

PW123

 

S21558500

CONTROL CABLE

DURING AN INSPECTION IN THIS AREA AN A/C ENGINEER FOUND THIS PART COMPLETELY JAMMED. THERE IS NO TASK FOR THAT PART IN THE PSP 495.

CA090125006

CNDAIR

 

 

WIRE

BROKEN

10/24/2008

CL6002B19

 

 

 

HYD CONNECTOR

ACCUMULATOR IS THE ORIGINAL ONE (FLT HRS: 8880.5 AND CYCLES: 6991), THE CREW WAS ONBOARD (NO PASSENGERS) PERFORMING THE PRE FLIGHT AND WHEN SELECTING THE HYDRAULIC THEY HEARD A LOUD BANG. THE EVENT DID HAPPEN AROUND 13:30 AT DETROIT INTERNATIONAL AND THE AIRCRAFT FLEW 3 LEGS BEFORE THE INCIDENT. THE CONNECTOR P3QA INSTALLED ON THE R ENG FUEL SOV (V2QA) WAS HIT AND THE WIRES WERE BROKEN, THEY HAD TO DISCONNECT THE BATTERY SINCE THE WIRES WERE "SPARKING". ONE FUEL FEED LINE DAMAGED, 14TH STAGE BLEED DUCT DAMAGED (PROBABLY BROKEN).

CA090125005

CNDAIR

GE  

 

RUDDER PEDAL

BROKEN

9/23/2008

CL6002B19

CF343A1

 

600902005

COCKPIT

AIRCRAFT TOOK A CREW CANCEL BECAUSE THE FO CALL FATIGUE. THE AIRCRAFT THEN WAS RESCHEDULED TO REPOSITION AT 1000. GOT A CALL THAT THE CAPTAIN’S LEFT RUDDER PEDAL WAS BROKEN. WHEN THE MECHANICS WENT O BOARD THEY FOUND THAT THE CAPTAIN’S RUDDER PEDAL WAS BENT AND TWISTED AND LOOKING DOWN AT THE RUDDER PEDAL TUBE THEY COULD SEE THAT THERE WAS A CRACK.

CA090125002

CNDAIR

GE  

 

TIRE

FAILED

11/13/2008

CL6002B19

CF343B1

 

 

MLG 

AIRCRAFT WAS AOG DUE TO A CUT IN MAIN WHEEL TIRE NR 2. SENT A MECHANIC IN ORDER TO REPLACE THE DAMAGED MAIN WHEEL. AFTER REPLACEMENT OF THE MAIN WHEEL, THE MECHANIC WANTED TO PERFORM A TIRE SERVICING CHECK ON ALL TIRES. DURING THE TIRE CHECK THE RT NOSE WHEEL/TIRE EXPLODED. THE RT NOSE WHEEL WAS TOTALLY DESTROYED, BROKEN DOWN IN SEVERAL PARTS. IT HAS BEEN REPORTED THAT THE TIRE ITSELF IS NOT BURST. THE WHEEL BEARING WAS FOUND IN A DISTANCE OF 6 TO 8 METERS FROM THE NLG. A PRESSURE-MEASURING GAUGE WAS ALSO FOUND IN A DISTANCE OF 6 TO 8 METERS FROM THE NLG. IT IS SUSPECTED, THAT THE EXPLOSION OCCURRED DURING/AFTER THE INFLATION AND OR A PRESSURE CHECK OF THE RT NOSE WHEEL. THE MECHANIC WAS HEAVILY INJURED AND LOST ONE ARM AND ONE FOOT/LEG. THE SITUATION OF THE MECHANIC IS CURRENTLY STABLE. HE IS NOT IN DANGER OF LIFE. THE WHEEL ASSEMBLY WAS ONLY SIX DAYS (SINCE DECEMBER 6) INSTALLED ON ACFT AFTER COMING FROM AERO, A LUFTHANSA TECHNIQUE MAINTENANCE FACILITY. THE WHEEL ASSEMBLY HAS THE P/N 5010598 AND S/N SAPR000065 (LT), OCT 930173 (RT). THE TIRES INSTALLED ON THE NOSE WHEEL ARE FROM VENDOR DUNLOP. THE DESTROYED, RIGHT NOSE WHEEL TIRE WAS NEW. THE LEFT NOSE WHEEL TIRE WAS ONE TIME RETREATED. THE DESTROYED, RIGHT WHEEL ASSEMBLY HAS BEEN OVERHAULED AT AUGUST 28, 2008. THE BRITISH AIR ACCIDENT INVESTIGATION BRANCH (AAIB) HAS QUARANTINED THE AIRCRAFT FOR INVESTIGATION AND PRESERVATION OF EVIDENCE.

CA090125003

CNDAIR

GE  

 

ACTUATOR

MALFUNCTIONED

1/16/2009

CL6002B19

CF343B1

 

852D10021

TE FLAP

ON APPROACH, FLAP FAIL MSG. FLAPS STUCK AT 0 DEG. COMPLIED WITH QRH AND AIRCRAFT DIVERTED AND LANDED WITHOUT FURTHER INCIDENT UNDER NORMAL BRAKING. REMOVED AND REPLACED FLAP ACTUATORS AND OPS CHECKED FLAP SYSTEM. NO FURTHER DEFECTS NOTED. ACTUATOR, INBD (INBD FLAP, LT), OUTBD (INBD FLAP, LT) INBD (OUTBD FLAP, LT), OUTBD, (INBD FLAP, RT), INBD, (OUTBD FLAP, RT) ACTUATOR, OUTBD (OUTBD FLAP, RT) 1) 852D100-21 2) 852D100-21 3) 601R93103-19 4) 852D100-19 5) 853D100-20 6) 854D100-20 1) 4867 2) 6782 3) 3982 4) 4418 5) 2429 6) 3805 HOURS ON ACTUATORS LISTED BELOW 1) 10,780 FH 2) 3,250 FH 3) 3,250 FH 4) 10,350 FH 5) 12,559 FH 6) 3,250 FH (TC NR 20090125003).

CA090205001

CNDAIR

GE  

 

B-NUT

LOOSE

1/26/2009

CL6002B19

CF343B1

 

 

ENGINE OIL SYS

FLT 5542, IAH-MOB, DURING CLIMB, FLT CREW REPORTED RIGHT ENGINE VIBRATION WAS HIGH AND THERE WAS AN INDICATION OF LOW OIL PRESSURE. RIGHT ENGINE SHUT DOWN AND FLIGHT RETURNED TO IAH AND LANDED WITHOUT FURTHER INCIDENT. MAINT INSPECTED ENGINE AND FOUND A LOOSE B-NUT ON LUBE/SCAVENGE PUMP. B-NUT RESECURED AND OIL WAS SERVICED. ENGINE RUNS CARRIED OUT AND NO DEFECTS NOTED. AIRCRAFT RETURNED TO SERVICE.

CA090205002

CNDAIR

GE  

 

WIRE HARNESS

DAMAGED

1/30/2009

CL6002B19

CF343B1

 

601R572201

MLG 

FLT CREW REPORTED THAT ON GEAR RETRACTION, THERE WAS A NOSE LANDING GEAR DISAGREE MSG AND THE NOSE LANDING GEAR DOOR INDICATION RED AND THE NOSE LANDING GEAR INDICATES IN TRANSIT. THE AIRCRAFT CONTINUED ON TO IAH AND LANDED WITHOUT FURTHER INCIDENT. MX PERFORMED GEAR SWINGS AND THE GEAR RETRACTED NORMALLY. BUT THERE WERE NO GREEN LIGHTS FOR THE NOSE GEAR DOORS. A PSEU WAS INSTALLED BUT NIL FIX. THE RIGHT NOSE LANDING GEAR PROX SWITCH HAD DAMAGED PINS ON THE HARNESS. PINS WERE REPLACED BY NIL FIX. NOSE LANDING GEAR UPLOCK PROX SENSOR HARNESS REPLACED AND LANDING GEAR EXTENSION / RETRACTIONS SYSTEM OPS CHECKED SERVICEABLE. AIRCRAFT RETURNED TO SERVICE.

CA090219019

CNDAIR

GE  

 

COWLING

DEPARTED

1/28/2009

CL6002B19

CF343B1

 

22850080802

RT NACELLE

AFTER GEAR UP SELECTION, AND ALREADY IN A RIGHT TURN, TO FOLLOW THE DEPARTURE ROUTE, WE EXPERIENCED AN ABNORMAL YAW TO THE RIGHT FOR 1 SECOND AND THEN BACK TO NORMAL. WE EXPECTED A BIRDSTRIKE. NORMAL FLIGHT AND NORMAL LANDING. AFTER LANDING I PERFORMED AN IMMEDIATE INSPECTION AFTER DISEMBARKING OF THE PAX, AND FOUND THE RT ENGINE UPPER COWLING MISSING. PAX DIDN’T REALIZE ANYTHING. FURTHER FLIGHT WAS CANCELLED.

CA090129009

CNDAIR

GE  

 

CARBON SEAL

WORN

1/28/2009

CL6002B19

CF343B1

 

5018T49P05

ENGINE

FLT IB 8659 FROM SXB TO MAD IN CRUISE. RHE OIL PRESS FLUCTUATIONS OBSERVED BY FLIGHT CREW. FLIGHT CREW DECIDED TO DIVERT TO ZAZ. AIRCRAFT LANDED IN ZAZ. MAINTENANCE FOUND RHE EDP CARBON SEAL WORN. RHE EDP CARBON SEAL REPLACED AS PER AMM 72-60-00-000/400-801. TEST OK. CARBON SEAL 5018T49P05 N/A WORN N/A 17279.12/14586.

CA090129010

CNDAIR

GE  

 

COUPLING

LOOSE

1/27/2009

CL6002B19

CF343B1

 

 

ENG OIL SYS

FLIGHT LT 3606 SCHEDULED FROM STR TO VIE DIVERTED TO MUC BECAUSE DURING CLIMB AT FL 260 ENGINE NR 2 OIL PRESS WARNING CAME ON SEVERAL TIMES. AFTER LEVEL OFF ENG NR 2 WAS REDUCED TO IDLE. OIL PRESSURE BETWEEN 30 AND 35 PSI. WITH INCREASING THRUST PRESSURE STILL BETWEEN 30-35 PSI. ENGINE WAS KEPT IN IDLE FOR THE REMAINDER OF THE FLIGHT. OIL TEMPERATURE WAS DECREASING TO 48 °C. MAINTENANCE INSPECTED ENGINE INSPECTED. ENGINE COVERED WITH OIL. FOUND 2 LOOSE COUPLINGS ON A-SUMP PUMP. COUPLINGS TIGHTENED. FOUND DURING RUN UP OIL ACCUMULATION AROUND OIL LEVEL SENSOR ON OIL TANK. LEVEL SENSOR AND PACKINGS REPLACED, NO HELP. OIL TANK PRESSURIZED. FOUND CRACK IN OIL TANK. OIL TANK REPLACED. AIRCRAFT RETURNED TO SERVICE.

CA090129011

CNDAIR

GE  

 

PSEU

MALFUNCTIONED

1/27/2009

CL6002B19

CF343B1

 

S21558500

MLG 

IN CRUISE, CAUTION MESSAGE PROX SYST CHAN. ON APPROACH, NORMAL LDG EXTENSION INOPERATIVE. ALTERNATE EXTENSION USED. AIRCRAFT LANDED. DURING TAXI, STEERING INOP CAUTION MESSAGE ON ED1. MAINTENANCE REPLACED PSEU AS PER AMM 32-61-01-000-/400-801. THE STEERING INOP MESSAGE WAS THE CONSEQUENCE OF LDG ALTERNATE HANDLE BEING NOT COMPLETELY PULLED IN. PSEU 8-648-08 D865 INOPERATIVE INTERNAL 16756.18/14104.

CA090129012

CNDAIR

GE  

 

PUMP

CRACKED

1/26/2009

CL6002B19

CF343B1

 

887055

HYD SYSTEM

FLT CREW REPORTED HYD 2 LOW QTY (C) MSG WAS POSTED WHILE IN CRUISE. SYNOPTIC PAGE CHECKED AND INDICATED 0 PERCENT AND 2500 PSI. QRH FOLLOWED, AIRCRAFT DIVERTED AND LANDED WITHOUT FURTHER INCIDENT. UPON FURTHER INVESTIGATION BY MAINTENANCE, IT WAS DETERMINED THAT THE NR 2 ENGINE DRIVEN HYD PUMP WAS LEAKING. NR 2 EDP REPLACED AND OPS CHECKED. NO FURTHER LEAKS NOTED. AIRCRAFT RETURNED TO SERVICE. ENGINE DRIVEN HYD PUMP 887055 MX583389 CRACKED RIGHT ENGINE 2196/UNKNOWN/1641 (LRU TIMES).

CA090129013

CNDAIR

GE  

 

VALVE

LEAKING

1/24/2009

CL6002B19

CF343B1

 

750005000

HYD SYSTEM

UPON GEAR RETRACTION, GEAR WOULD INDICATE UP AND LOCKED FOR A FEW SECONDS, THEN THE AMBER HASHED INDICATIONS. THIS REPEATED SEVERAL TIMES ACCOMPANIED BY LOUD THUMPING NOISE. THERE WERE NO OTHER CAUTION, WARNING OR AURAL WARNINGS REPORTED. THE GEAR WAS EXTENDED NORMALLY AND ALL GEAR INDICATED DOWN AND LOCKED. AIRCRAFT RETURNED AND LANDED WITHOUT FURTHER INCIDENT. MX WAS ABLE TO DUPLICATE DEFECT WHILE AIRCRAFT WAS ON JACKS. MAIN LANDING GEAR VALVE DETERMINED TO BE AT FAULT. VALVE REPLACED AND OPS CHECKED SERVICEABLE. VALVE 750005000 0720 LEAKING MLG 15799/12794, AIRFRAME TIMES.

CA090129014

CNDAIR

GE  

 

NOSE COWL

SEPARATED

1/28/2009

CL6002B19

CF343B1

 

22850080802

 

THE OPERATOR HAS REPORTED THE FOLLOWING, DURING TAKEOFF ON A FLIGHT THE NR 2 ENGINE UPPER ENGINE COWL DETACHED. THE CREW NOTED A SLIGHT BUFFET DURING THE EVENT AND CONTINUED TO THE DESTINATION AIRPORT WHERE IT WAS DISCOVERED THAT THE COWL WAS MISSING. THIS WAS THE FIRST FLIGHT AFTER THE AIRCRAFT HAD UNDERGONE AN A CHECK IN MAINTENANCE. THE CRJ TECHNICAL HELP DESK AND ISE ARE SUPPORTING THE OPERATOR. NOW THE ANSWERED QUESTIONS. WHICH SIDE IS THE COWLING IS MISSING. RT SIDE UPPER NOSE ACCESS COWLING , PROVIDE P/N OF THE MISSING COWLING, PN:228-50080-802 SN:SBRJNACC0 1183, ANY OTHER DAMAGES TO THE ACFT. NO DAMAGES, PILOT REPORTED AFTER DETAILED INSPECTION, CAN YOU EXPLAIN WHY THE COWLING DEPARTED THE ACFT. IT IS ASSUMED THAT AN ERROR APPEARED DURING A-CHECK, IT WAS THE FIRST FLIGHT AFTER THE A CHECK, IS SB 601R-71-007 HAS BEEN PERFORMED ON THE ACFT, THIS SB IS NOT APPLICABLE FOR THIS AIRCRAFT. IT SHOULD BE PERFORMED BEFORE DELIVERY. THERE WAS NO ENGINE CHANGE SINCE DELIVERY. ANY REPORT FROM THE PILOTS, HAVE THEY NOTICE BUFFETING OF ABNORMAL CONDITION. THE COWLING WAS LOST DURING TAKEOFF, AND IT IS STILL NOT FOUND ON THE AIRPORT AREA. THE PILOT NOTICED ONLY A LIGHT FORCE IN THE NOSE UP DIRECTION DURING TAKEOFF, LIKE A BIRD STRIKE. HE EXPLAINED THAT THERE WAS NO BUFFETING OR ANY OTHER FORM OF ABNORMAL CONDITION NOTICEABLE DURING THE WHOLE FLIGHT AFTER TAKEOFF. COWLING WAS REPLACED. TFH: 12205/THC: 10091.

CA090203007

CNDAIR

GE  

TACTAIR

BEARING

DAMAGED

2/2/2009

CL6002B19

CF343B1

 

MS276413

CONTROL VALVE

WHILE RIGGING THE PARKING BRAKE CABLE SMALL BALLS WERE FOUND AT THE BOTTOM OF THE COMPARTMENT HOUSING THE BRAKE CONTROL VALVE PN 600-88101-125. UPON FURTHER INVESTIGATION IT WAS DISCOVERED THAT THE TWO FOLLOWER BEARINGS FOR THE PILOT BRAKE PEDAL INPUT TO THE BRAKE CONTROL VALVE WERE DESTROYED. PART CYCLES, TSN AND TSO ARE UNKNOWN ON THE BEARINGS.

CA090212007

CNDAIR

GE  

 

EEC  

MALFUNCTIONED

2/10/2009

CL6002B19

CF343B1

 

 

ENGINE

(CAN) ACFT ON APPROACH, PILOT REPORTED ACFT HIT BY LIGHTNING IN THE NOSE AREA. IMMEDIATELY AFTER LIGHTNING STRIKE, RT ENG FLAMED OUT. PILOT DID NOT TRY TO RE-START RT ENG. ACFT LANDED, MX PRESENTLY INSPECTING THE ACFT. FDR TO BE DOWNLOADED. CUSTOMER CONTACTING MFG. ADDITIONAL INFORMATION 11 FEB 2009: FDR HAS BEEN DOWNLOADED. DOWNLOAD ON ITS WAY . SHOULD BE HERE TODAY AT NOON. ACFT AND ENGINE (EXTERIOR) INSPECTIONS CARRIED OUT. DAMAGES ARE MINOR. FUEL SAMPLES TAKEN. BOTH LT ENG AND RT ENG FUEL FILTERS ARE BEING DRAINED FOR QTY COMPARISON RT ENG CHIP DETECTOR OK. RT ENG BSI TO BE DONE ASAP. IT IS CONFIRMED THAT THE CONT IGN WAS ON PRIOR TO THE EVENT. DFDR CHECK SHARED WITH MFG. RT ENGINE DOES NOT FLAME OUT DURING PERIOD 180.22.23 THRU 180.23.10 BUT DOES ROLL BACK AND ITT INCREASES SIGNIFICANTLY INDICATIVE OF AN HPC STALL. THE ENGINE REMAINS IN STALL AND "ROLLS BACK" ITT INCREASES. AT APPROX 180.23.11 INDICATED FUEL FLOW DROPS TO ZERO, ITT DECLINES RAPIDLY WHICH IS CONSISTENT WITH PILOT ACTION FUEL SHUT OFF IN RESPONSE TO "ROLL BACK" AND LIKELY EICAS LOW OIL PRESSURE INDICATION LOW AND LOP AURAL WARNING. NOTE LIGHTNING APPEARS TO HAVE HIT THE FWD RT FUSELAGE AT THE LOWER PART OF THE SERVICE DOOR "SCUFF PLATE". EICAS INDICATIONS? "LOW OIL PRESS" AURAL AND INDICATION WHEN N2 GOT LOW ENOUGH? YES. YOU CAN SEE WHERE THE LIGHTNING STRUCK AND HOW CLOSE TO THE RT ENGINE INTAKE IT WAS. THE ACFT IS IN MX BUT MX REPORTS ENTRY POINT AROUND SVCE DOOR SCUFF PLATE (RT SIDE). AFTER INSP, MX REPORTS LIGHTNING ENTRY POINT.

CA090218003

CNDAIR

GE  

 

UPLOCK

INOPERATIVE

2/13/2009

CL6002B19

CF343B1

 

16600101

MLG 

(CAN) ACFT TOOK OFF FOR A FLIGHT TEST. THE TEMPERATURE WAS ABOUT -5 DEGREES CELSIUS, CLEAR SKIES AND WINDS FROM THE WEST BETWEEN 5 AND 10 KNOTS DURING THE INITIAL CLIMB, THE LANDING GEARS WERE RETRACTED AND HAD AN INDICATION OF 2 GREEN LIGHTS, HOWEVER THE NLG INDICATED "IN TRANSIT". THE NLG DOORS REMAINED OPENED. THE SYS INDICATED "GEAR DISAGREEMENT". PILOT DECIDED TO EXTEND THE GEARS, 3 GREEN LIGHTS, AND LANDED. MX CHECKED THE (PROXIMITY SENSOR ELECTRONIC-UNIT) PSEU FOR A FAULT CODE AND IT INDICATED A FAULTY (PROXIMITY SENSOR PS3GA) NOSE GEAR UPLOCK. RETRACTIONS OF THE NLG WERE MADE AND MX CONFIRMED THE UPLOCK MECHANISM WAS NOT FUNCTIONING CORRECTLY. FOUND THAT THE (EMERGENCY RELEASE LEVER) WHICH IS PART OF THE UPLOCK ASSY, WAS STIFF, PREVENTING THE TARGET (WHICH IS PART OF THE “MANUAL RELEASE LEVER”) FROM GETTING IN PROPER RANGE WITH THE PROXIMITY SENSOR. IT WOULD APPEAR AS IF THOSE TWO PARTS HAD BEEN ASSEMBLED TOO TIGHTLY TOGETHER. THE (UPLOCK) MECHANISM WAS REPLACED IAW AMM. THE NLG WAS RETRACTED SEVERAL TIMES AND FOUND SERVICEABLE. P/N OFF: 16600-101, S/N OFF: DCL263-96 P/N ON: 1660-103, S/N: NLG/0656/01.

CA090125004

CNDAIR

 

 

WINDOW

FAILED

1/19/2009

CL6002C10

 

 

601R3303321

COCKPIT

CAPTS WINDSHIELD BROKE ON LANDING. TEMP IS +63 DEG/WITH HIGH WINDS 35 MPH GUSTS TO 44 MPH INCH. WINDSHIELD WAS REPLACED PER AMM. WINDSHIELD IS POST MOD.

CA090129001

CNDAIR

GE  

 

CAP  

DISCONNECTED

11/3/2008

CL6002C10

CF348C5B1

 

4117T25P03

ENGINE FAN

RIGHT ENGINE N1 VIB ICON AND THE PILOTS REPORTED THE FAN VIBES REACHING 2.9 MILS. UPON LANDING AT AN OUTSTATION, A MECHANIC WAS SENT TO INVESTIGATE THE ISSUE. AFTER REMOVING THE FORWARD SPINNER IT WAS FOUND THAT THE FORWARD "BLIND" CAP OF THE FAN SHAFT HAD COME LOOSE AND WAS BANGING AROUND THE AFT SPINNER CAUSING THE IMBALANCE. DAMAGE WAS FOUND ON THE FORWARD BLIND CAP, RETAINING RING, AND AFT SPINNER. THE ENGINE FLEW EXACTLY 6 CYCLES BEFORE THE BLIND CAP LIBERATED FROM THE FAN SHAFT. BLIND CAP MOVEMENT IS BELIEVED TO BE DUE TO IMPROPER SEATING OF THE RETAINING RING DURING INSTALLATION, WHICH MIGHT BE A CONSEQUENCE OF RETAINING RING DEFORMATION.

CA090118008

CNDAIR

GE  

GE  

FUEL FILTER

RUPTURED

1/5/2009

CL6002C10

CF348C5B1

GECF348C5B1

7582591

RT ENGINE

"PILOT REPORTED A SNAG "RT ENGINE N1 READING 86 PERCENT, WHILE TARGET N1 WAS 88 PERCENT. RT ENGINE FAILED TO ACHIEVE TARGET N1 AS PER FCOM". POWER ASSURANCE CHECK WAS CARRIED OUT BY THE ENGINEER AND THE CHECK FAILED. THE DATA OF THE POWER ASSURANCE CHECK IS PROVIDED IN THE ATTACHMENT TITLED "ENGINE DATA". ONCE THE POWER ASSURANCE CHECK FAILED, I ASKED THE OPERATOR WHEN WAS THE LAST TIME AN ENGINE PERFORMANCE RECOVERY WASH WAS DONE. THEY SAID THAT IT WAS MORE THAN AN YEAR. I ASKED TO DO A RECOVERY WASH ON THE ENGINE AND AGAIN DO THE POWER ASSURANCE CHECK. THE DATA FOR THE POWER ASSURANCE CHECK DONE AFTER THE WASH ARE GIVEN IN THE ATTACHMENT TITLED "ENGINE DATA 2". THE CHECK FAILED EVEN THEN. THE AIRCRAFT IS FITTED WITH CF348C5-B1 ENGINES. PROPULSION FROM ENGINE GRD RUNS CRJ ISE RECOMMENDED TO CHECK ENGINE FMU MAIN FUEL FILTER AND OTHER CHECKS. N1 CONFIRMED TO BE LOW BUT INDICATED FUEL FLOW ABNORMALLY HIGH. CONFIRMED FUEL FILTER HAD "RUPTURED" AND INDICATION OF FILTER "SPINNING". LOW POWER (N1) AND HIGH FUEL FLOW CONSISTENT WITH FILTER RUPTURE AND AFFECT ON FMU MAIN FUEL METERING VALVE AND METERING VALVE POSITION WHICH IS USED BY FADEC TO COMPUTE AND INDICATE FUEL FLOW IN PPH TO EICAS. GE REFUSED HELP AND SUPPORT TO BOMBARDIER OR ALLIANCE REF "NON GE NON OEM PART INVOLVED". MAIN FUEL FILTERS ARE COMMON PN`S FOR ALL CRJ 100-200 AND 700-900. MAIN ENGINE FUEL FILTER FAA PMA PN 7582591 MFG PMA HOLDER PTI TECHNOLOGIES OXNARD CA USA N/K RUPTURED ALSO "SPINNING" OF FILTER NOTED TSN: 3472 HRS, CSN: 2763 CYCLES.

CA090217005

CNDAIR

GE  

 

RELIEF VALVE

DAMAGED

1/30/2009

CL6002C10

CF348C5B1

 

9752753

MLG 

(CAN) GEAR DISAGREE MSG FOLLOWING T/O. PRIORITY BALANCE RELIEF VALVE WAS CHANGED AND LANDING GEAR RETRACTION SYS OPS, CHECK GOOD. ACFT RETURNED TO SERVICE. PRIORITY BALANCE RELIEF VALVE, 975275-3.

CA090217006

CNDAIR

GE  

 

RELIEF VALVE

MALFUNCTIONED

1/13/2009

CL6002C10

CF348C5B1

 

9752753

MLG 

(CAN) GEAR DISAGREE MSG DURING RETRACTION. ACFT RETURNED TO FIELD. MX CARRIED OUT LANDING GEAR INSPECTIONS WITH NO DEFECTS FOUND. HYD SYS PRESSURE DECAY CHECK CARRIED OUT AND FAILED. HYDR SYS NR3 RESERVIOR CHANGED AND SYS PRESSURE AND DECAY RATE GOOD. CHANGED PRIORITY BALANCE RELIEF VALVE. LANDING GEAR OPS CHECK CARRIED GOOD. PRIORITY BALANCE RELIEF VALVE, 975275-3.

CA090217007

CNDAIR

GE  

 

RELIEF VALVE

MALFUNCTIONED

12/25/2008

CL6002C10

CF348C5B1

 

9752753

MLG 

(CAN) GEAR DISAGREE CAUTION FOLLOWING T/O. LANDING GEAR RETRACTION SYS DEFERRED IAW MEL 32-30-01. ACFT REPOSITIONED FOR MX, WHERE THE PRIORITY BALANCE RELIEF VALVE WAS CHANGED AND LANDING GEAR RETRACTION SYS OPS CHECK GOOD. ACFT RETURNED TO SERVICE.

CA090217008

CNDAIR

GE  

 

PSEU

MALFUNCTIONED

2/1/2009

CL6002C10

CF348C5B1

 

895304

MLG 

(CAN) LANDING GEAR DISAGREE WARNING AFTER GEAR RETRACTION IN THE CLIMB. ALL THREE GEAR INDICATED GREEN WHEN HANDLE WAS IN THE UP POSITION. REMOVED AND REPLACED PSEU IAE MM 32-61-01. C/W POWER UP TEST OF LANDING GEAR PSS IAW MM 32-61-00. C/W LANDING GEAR OPS TEST IAW MM 32-30-00. OPS CHECK GOOD. A REQUEST OF THE PSEU NVM AS BEEN MADE. MUST WAIT UNTIL UNIT IS RECEIVED BY VENDOR TO PERFORM DOWNLOAD. PSEU 8-953-04 D280 10826:08/7737/9068:50

CA090127005

CNDAIR

GE  

 

BUTTERFLY VALVE

BROKEN

1/20/2009

CL604

CF343B

 

9795804

A/C PACK

PILOT REPORTED LEFT AIR CONDITIONING PACK BLOWS HOT AIR REGARDLESS OF TEMPERATURE SELECTION. SYSTEM INTERROGATED AND DETERMINED THE LOW PRESSURE MODULATING AND SHUTOFF VALVE DEFECTIVE. CLOSE INSPECTION OF VALVE PLENUM DETERMINED BUTTERFLY VALVE HAD BEEN EJECTED DOWNSTREAM OF PLUMBING AND WAS RETRIEVED WITH ALL HARDWARE INTACT. THE SHAFT OF THE VALVE THAT CONNECTS THE BUTTERFLY VALVE HAD BROKEN, RENDERING THE VALVE INOPERATIVE REGARDLESS OF TEMPERATURE INPUT. CHALLENGER 604 IPC REFERENCE 21-51-01 FIGURE 1 ITEM NR 10.

CA090202007

CNDAIR

GE  

 

DUCT

DENTED

1/29/2009

CL604

CF343B

 

601970305

APU 

(CAN) WHILE IN SCOTTSDALE, ARIZONA, DURING THE PREFLIGHT CHECK THE CREW NOTICED THE APU INLET WAS DENTED AND APU INLET BELLOWS WAS RIPPED. NO OPERATIONAL ABNORMALITY WERE NOTICED BY THE CREW PRIOR TO THE DISCOVERY. MAINTENANCE TECHNICIAN WAS DISPATCHED AND BOTH PARTS WERE REPLACED WITH NEW AND APU INLET CHECKED FOR HIDDEN DAMAGE AS PER CL605 MM CHAPTER 49-14. BOMBARDIER IS INVESTIGATING THE POSSIBLE CAUSE. I HAVE LISTED THE MANUFACTURER AS CANADAIR BUT THE CORRECT MANUFACTURER NAME IS SENIOR AEROSPACE WHICH IS NOT LISTED ON THIS PROGRAM.

CA090224002

CVAC

ALLSN

 

TUBE

LEAKING

2/12/2009

440  

501D13

 

6878432

ENGINE OIL SYS

ON FEBRUARY 12, 2009 NR 1 ENGINE WAS SHUT DOWN 30 MINUTE BEFORE LANDING DUE TO OIL PRESSURE INDICATION OSCILLATING AND LOW OIL PRESSURE LIGHT ON. 20 LITERS OF OIL ADDED, FOUND OIL SUPPLY TUBE FOR THE TURBINE BEARING WAS LEAKING BADLY, REF. ROLLS-ROYCE PICK 72-50-00 FIG. 2 ITEM 14, AT THE SWIVEL GLEN. THE REAR TURBINE BEARING ASSEMBLY REPLACED, ENGINE TESTED SERVICEABLE.

CA090119009

DHAV

PWA  

DHAV

INTAKE

CORRODED

1/16/2009

DHC2MK3

PT6A27

CT2EC100118

C2TEC100118

MIDDLE

DURING A STRUT REPAIR, THE TECH FOUND SEVERE CORROSION, LEVEL 3, ON 2 LONGERON INTAKE COWLS, PN C2TEC1001-18 AND C2TEC1001-17. BOTH PARTS WERE REPLACED.

CA090211004

DHAV

PWA  

 

LINK

WORN

2/9/2009

DHC2MKI

R985AN14B

 

C2CF347ND

BELLCRANK ASSY

DURING THE REPLACEMENT OF THE BEARING IN THE ELEVATOR BELL CRANK ASSY, THE LINKS AND SPACERS WERE THE ELEVATOR CABLE ATTACHES WERE FOUND WORN, SPACERS WERE WORN RIGHT THROUGH (PN C2CF349ND). THE AN3 BOLT THAT ATTACHES LINK IN PLACE WAS WORN 1/3 THROUGH. SPACERS AND BOLTS WERE REPLACED.

CA090203001

DHAV

PWA  

 

HINGE

CRACKED

2/2/2009

DHC3

PT6A135

 

C3FS4727

HORIZONTAL STAB

ON INSPECTION FOUND LT AND RT TAILPLANE HINGE ASSEMBLIES CRACKED THROUGH RIVIT HOLE ON ATTACHMENT LT P/N C3FS473-7 AND RT P/N C3FS472-7.

CA090130007

DHAV

PWA  

 

GEAR

FAILED

7/29/2008

DHC6100

PT6A20

 

 

RGB 

THEENGINE SUFFERED A COMPLETE LOSS OF POWER DUE TO A FAILURE OF A FIRST STAGE REDUCTION GEARBOX PLANETARY GEAR. FAILURE OF THE PLANETARY GEAR WAS THE RESULT OF INTERGRANULAR AND FATIGUE CRACKING TO THE PLANETARY GEAR BORE. THE BEARING SLEEVE SPUN WITHIN THE BORE DUE TO CONTAMINANTS WITHIN THE LUBRICATING OIL ENTERING THE BEARING SLEEVE AND PLANETARY GEAR SHAFT INTERFACE. CONTAMINANTS WITHIN THE LUBRICATING OIL WERE AS A RESULT OF NORMAL OIL CONTAMINANTS BEING ALLOWED TO BYPASS THE FINGER SCREEN OF THE PLANETARY GEAR. UPON DISASSEMBLY OF THE POWER SECTION IT WAS FOUND THAT THE FINGER SCREEN WAS DEFORMED AND RESULTED IN FRETTING OF THE MAIN O-RING ON THE FINGER SCREEN, AND FRETTING OF THE FINGER SCREEN BODY AND FINGER SCREEN CHAMBER. THE FRETTING GENERATED CONTAMINANTS THAT WERE ALLOWED TO BYPASS THE FINGER SCREEN AND WEAR ON THE O-RING ALSO ALLOWED CONTAMINANTS TO BYPASS THE SCREEN. THE TEFLON PACKING WAS IMPROPERLY POSITIONED DURING THE LAST OVERHAUL OF THE ENGINE. THE IMPROPERLY INSTALLED TEFLON PACKING IMPOSED ABNORMAL STRESSES TO THE FINGER SCREEN AND RESULTED IN THE DEFORMATION OF THE FINGER SCREEN BODY. THE UNFILTERED OIL CAUSED HIGH TEMPERATURES TO THE PLANETARY GEAR RESULTING IN FAILURE OF THE GEAR AND ULTIMATELY FAILURE OF THE POWER SECTION OF THE ENGINE.

CA080924010

DHAV

PWA  

 

LEG ASSY

CRACKED

9/24/2008

DHC6300

PT6A27

 

C6UM11104

MLG 

(CAN) DURING THE 12 MONTH INSPECTION OF THE MLG WHICH CONSISTS OF INSPECTING THE WELDS FOR CRACKS, A CRACK WAS DETECTED ON THE BOTTOM OF THE AFT ATTACH TUBE APPROX 5 INCHES FROM THE AFT GEAR ATTACH FITTING. (TC NR 20080924010)

CA090204007

DHAV

PWA  

 

CONTROL CABLE

SEPARATED

2/2/2009

DHC7*

PT6A50

 

NAS303260852

BRAKES

ON APPLICATION OF BRAKES AFTER LANDING, THE LEFT PEDAL WENT TO THE MAX POSITION WITH NO EFFECT. LT BRAKE CABLE WAS FOUND SEPARATED APPROX 8 INCHES FROM THE VALVE IN THE UPPER FUSELAGE CLOSE TO A SMALL DIAMETER PULLEY. THIS CABLE WAS THE ORIGINAL INSTALLED IN 1981 AT THE FACTORY.

CA090219013

DHAV

PWA  

 

EEC  

FAILED

1/30/2009

DHC8*

PW123

 

 

ENGINE

(CAN) DURING APPROACH, ONE ENG EXPERIENCED (2) UNCOMMANDED POWER ACCELERATIONS. THE CREW REDUCED THE POWER (PLA) AND SHUTDOWN ENGINE. THE ACFT MADE A SINGLE ENGINE LANDING AT PLANNED DESTINATION. THE FUEL CONTROL, FUEL PUMP AND EEC WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.

CA090219016

DHAV

PWA  

 

LINE

FRACTURED

2/4/2009

DHC8*

PW123

 

 

OIL SYSTEM

(CAN) DURING T/O ROLL, THE CREW RECEIVED A FIRE WARNING ON NR 1 ENGINE AND IMMEDIATELY ABORTED T/O. IT IS UNKNOWN IF FIRE BOTTLES WERE DISCHARGED. THE A/C RETURNED TO THE RAMP WHERE INS REVEALED A FRACTURED 6 AND 7 BEARING OIL LINE, FRACTURED 1ST AND 2ND STAGE PT BLADES. HEAT RELATED DAMAGE WAS ALSO FOUND ON ACCESS PANNELS. THE LOCAL AUTHORITIES ARE INVESTIGATING THIS EVENT. MFG HAS OFFERED ASSISTANCE AND WILL FOLLOW UP.

CA090127006

DHAV

PWA  

 

PUMP

FAILED

1/26/2009

DHC8102

PW120

 

570347

HYD SYSTEM

WHEN SPU`S WERE SELECTED OFF, HYDRAULIC PRESSURE WAS LOST ON THE NR 2 HYDRAULIC SYSTEM. ASSOCIATED "RUDDER PRESSURE", "NR 2 RUDDER HYDRAULIC" AND "RUDDER FULL PRESSURE" ILLUMINATED. RECTIFICATION, NR 2 HYDRAULIC ENGINE DRIVEN PUMP REPLACED, GROUND RUNS AND LEAK CHECK SERVICEABLE.

CA090126004

DHAV

PWA  

 

LINK

BROKEN

1/25/2009

DHC8102

PW120

 

 

NLG 

WHILE CARRYING OUT LANDING GEAR RETRACTIONS, IT WAS FOUND THAT THE NOSE LANDING (NLG) WAS HUNG UP AT THE EXTENSION CYCLE. FURTHER INVESTIGATION REVEALED THAT THE NOSE LANDING (NLG) WAS NOT CENTERED AND THIS WAS PROBABLY CAUSED BY THE CENTERING SPRING NOT OVERCOMING THE BINDING FORCE. THIS RESULTED IN THE STEERING ACTUATOR BEING TWISTED UPWARDS AS A RESULT OF THE ADJUSTABLE LINK THAT WAS FOUND TO BE BROKEN. NOSE LANDING GEAR (NLG) ADJUSTABLE LINK ASSEMBLY REPLACED, FUNCTION CHECKED AND FOUND TO BE SERVICEABLE.

CA090205003

DHAV

PWA  

 

TORQUE TUBE

DELAMINATED

2/3/2009

DHC8102

PW120

 

234187B

TE FLAPS

FLAP POWER LIGHT INTERMITTENT. TORQUE TUBE P/N 234187B OF PRIMARY FLAP DRIVE SYSTEM FOUND TO HAVE 300 DEGREES OF ROTATION FREE PLAY. BONDED ENDS (RUBBER) FOUND DISINTEGRATED. TORQUE TUBE REPLACED AND LUBRICATED IAW AMM 27-52-00. ADDITIONAL CHECKS OF INSTALLED PARTS PERFORMED BY APPLYING PRESSURE OF TORQUE TO CHECK INTEGRITY OF BONDED ELASTOMER. SYSTEM CHECK SERVICEABLE.

CA090119005

DHAV

PWA  

VICKERS

BRAKE

LEAKING

1/12/2009

DHC8102

PW120

214665

 

 

LEFT INBOARD BRAKE PACK LEAKING HYDRAULIC FLUID FROM ONE PISTON PUCK.

CA090203003

DHAV

PWA  

 

LINE

LEAKING

2/2/2009

DHC8102

PW120A

 

82970009101

HYDRAULIC SYS

SHORTLY AFTER TAKEOFF, NR 1 HYD SYS WAS LOST, AIR CREEBEC FLIGHT 921 DECLARED AN EMERGENCY AND TURN BACK TO YUL AIRPORT ACFT LANDED SAFELY AND WAS TOWED TO GATE FOR PASSENGER OFFLOAD. AFTER MAINTENANCE INSPECTION THEY FOUND THE NR 1 ENG DRIVEN PUMP CASE DRAIN LINE RUPTURE AT THE FILTER AREA IN THE LT WHEEL WELL LINE AND PUMP WAS REPLACED AND THE ACFT WAS BACK IN SERVICE AROUND 11:00 AM.

CA090204010

DHAV

PWA  

 

LINE

BROKEN

2/2/2009

DHC8102

PW120A

 

82970009101

HYD SYSTEM

SHORTLY AFTER TAKEOFF, THE NR 1 ENG HYD PUMP CAUTION LIGHT ILLUMINATED AND NR 1 HYD QTY GAGE WENT TO ZERO. THE CREW DECLARED AN EMERGENCY AND RETURNED FOR A SAFE FLAPLESS LANDING. MAINTENANCE FOUND IN THE LEFT WHEEL WELL A BROKEN HYDRAULIC LINE. THE LINE IS THE RETURN FROM THE ENGINE DRIVEN HYDRAULIC PUMP TO THE CASE DRAIN FILTER.

CA090210013

DHAV

PWA  

 

INDICATOR

FAILED

1/13/2009

DHC8102

PW120A

 

H321ALM1

STBY ATTITUDE

PIREP, STANDBY ATTITUDE INDICATOR FAILED. MADE GRINDING NOISE THEN TOPPLED. WOULD NOT RE-ERECT. LIGHTS REMAINED POWERED AND FLAG NOT IN VIEW. STANDBY INDICATOR REPLACED AND FUNCTION TEST SERVICEABLE. STRIP REPORT FROM AVIONICS SHOP ON SN 12395 STBY ATT IND, "FOUND THE ROTOR BEARINGS BOUND UP AND FUSE BLOWN. ERECTION AND DRIVE BEARINGS WORN." UNIT HAD 1196.5 HRS ON IT SINCE LAST REPAIR.

CA090210014

DHAV

PWA  

 

INDICATOR

MALFUNCTIONED

1/20/2009

DHC8102

PW120A

 

SELOC8J

FUEL FLOW

PIREP NR 1 ENGINE FUEL FLOW INDICATOR ANALOG FLICKERING FOR APPROX 1 HOUR, WITH DIGITAL READ OUT SHOWING STEADY INDICATION. ACTION, FUEL FLOW GAUGE REPLACED WITH NEW. STRIP REPORT FROM SHOP, "FINDINGS: POINTER AND FDR OUTPUTS OSCILLATING, WORK PERFORMED. REPAIRED CRACKED SOLDER JOINTS ON IC, REF DIGITAL PC BOARD ASSEMBLY. FINAL TESTS, RE-CERTIFIED AND RETURNED TO SERVICE.

CA090210010

DHAV

PWA  

 

METER

FAILED

1/22/2009

DHC8311

PW123

 

67003008010

A/C POWER

PILOT REPORTED, AC POWER METER CIRCUIT BREAKER POPPING. RECTIFICATION AC POWER METER REPLACED, CHECKED SERVICEABLE. AC POWER METER SENT TO VENDOR FOR REPAIR. WILL UPDATE SDR AT RECEIVING OF STRIP REPORT. UPDATE, FEB 10 2009 STRIP REPORT FROM AVIONICS SHOP STATEMENT- "INSPECT T/S FOUND INPUT DC RF FILTER SHORTED TO CASE GRD. REPAIR ALL THREE RF FILTERS ON DC POWER INPUT LINES, ASSEMBLE AND TEST TO MAN SPEC".

CA090216003

DHAV

PWA  

 

STRUT

CRACKED

2/15/2009

DHC8311

PW123

 

881517

NLG 

(CAN) DURING COMPLETION OF A-1 INSP TASK NR3220/51, EXTERNAL GENERAL VISUAL INSP OF THE NLG SHOCK STRUT AND DRAG STRUT, THE ENGINEER DISCOVERED A 9 INCH LONG CRACK ON THE AFT SIDE OF THE SHOCK STRUT CYLINDER. THE CRACK IS LOCATED BETWEEN THE SHOCK STRUT CYLINDER UPPER FLANGE AND THE CASTOR NUT LOCK PIN HOLE. THE NLG ASSY IS BEING REPLACED. THE NLG ASSY COMPLETE S/N IS DCL295/90/00R/00. THE SHOCK STRUT CYLINDER S/N IS DCL-796.

CA090123003

DHAV

PWA  

 

WIRE

BURNED

1/20/2009

DHC8311

PW123

 

 

COMPENSATOR

(CAN) AT BASE, WHEN CAPTAIN TURNED ON THE BATTERY MASTER SWITCH, SUDDENLY GOT A BURNING ODOR WITH C/B POPPING. POPPED THE CAUTION LIGHT NR 2 AND AUTO-PILOT DISENGAGE C/B. FOUND NR1 RNAV (RADIO NAVIGATION) ANNUNCIATOR PANEL P/N : 83461029-003 AT FAULT ONE COMPENSATOR OVERHEATED ON PC BOARD (P/N : 82210023-003) ON THIS ASSY. PANEL REPLACED AND ACFT RETURNED TO SERVICE.

2009FA0000230

DIAMON

CONT

 

PUMP

MALFUNCTIONED

3/16/2009

DA20C1

IO240B

 

5367001

FUEL SYSTEM

PROBLEM WAS FOUND TRYING TO START ACFT, AUX PUMP DOESN'T SUPPLY ENOUGH FUEL PSI TO OPEN MANIFOLD TO PRIME ENGINE FOR STARTING. (2) SPEED AUX/EMERGENCY FUEL PUMP WILL NOT PROVIDE ENGINE WITH SUFFICENT FUEL FLOW OR FUEL PRESSURE TO RUN ENGINE IF ENGINE DRIVEN FUEL BECOMES INOP IN AN EMERGENCY CONDITION. AIRPLANE ENGINE WILL NOT CONTINUE TO OPERATE IN FLIGHT. MFG REP. SAYS THAT IS CORRECT AND IT IS MFG PROBLEM. (ENGINE IS FINE AIRFRAME PROBLEM) MFG REP SAYS THE ACFT IS CERTIFIED. THEY ARE NOT ABLE TO ANWSER VERY MANY QUESTIONS. PROBLEM IS HOW DID THIS BECOME CERTIFIED IT IS AN UNSAFE CONDITION.

CA090210007

DIAMON

CONT

 

FUEL CONTROL

OUT OF ADJUST

2/8/2009

DA20C1

IO240B

 

 

ENGINE

PILOT REPORT, UPON APPLYING POWER ON THE FIFTH TOUCH-AND-GO, WHILE ROLLING ON RUNWAY, THE ENGINE STOPPED RUNNING. ATC WAS IMMEDIATELY ADVISED THE ENGINE HAD QUIT. AFTER A FEW SECONDS WAS ABLE TO PRIME AND RESTART THE ENGINE WITHOUT PROBLEM. ATC WAS ADVISED OF THIS AND TAXIED DOWN RUNWAY AND EXITED RUNWAY ONTO TAXIWAY. THE ENGINE DID NOT GIVE ANY FURTHER TROUBLES AND SHUT DOWN AT THE MAIN BASE WITHOUT INCIDENT. MAINTENANCE RESPONSE, ADJUSTED FUEL PRESSURES AND MIXTURE SETTINGS. AIRCRAFT RUN UP AND LEAK CHECKED. AIRCRAFT RETURNED TO SERVICE SUBJECT TO SATISFACTORY TEST FLIGHT.

CA090129016

DIAMON

CONT

 

UNKNOWN

UNKNOWN

1/27/2009

DA20C1

IO240B

 

 

 

ENGINE SHUT DOWN AFTER TOUCHDOWN. FUEL SET UP PROCEDURE WAS PERFORMED IN ACCORDANCE WITH TCM SID97-3E AND GROUND RUN SATISFACTORY WITH ALL FUEL AND POWER INDICATIONS NORMAL. PAST EXPERIENCE WITH THESE ENGINE TYPES HAVE REVEALED THAT THEY CAN BE SENSITIVE TO AMBIENT TEMPERATURE AND PRESSURE CHANGES. ANOTHER CONTRIBUTING FACTOR MAY BE THE CONDITION OF THE FUEL SYSTEM COMPONENTS AND RELATED FUNCTIONS. THE FUEL SET UP PROCEDURE USUALLY CORRECTS THIS TYPE OF CONDITION.

CA090129004

DIAMON

CONT

DIAMON

TUBE

BLOWN

1/26/2009

DA20C1

IO240B

4078E

302013400

NEAR STEM

LT MAIN TIRE BLOWN ON LANDING. AIRCRAFT REMAINED ON RUNWAY UNTIL MAINTENANCE CREWS WERE ABLE TO REPLACE THE DEFECTIVE WHEEL ASSEMBLY WITH A SERVICEABLE UNIT AND ENABLE THE AIRCRAFT TO TAXI BACK TO THE HANGAR FOR FURTHER INSPECTION.

CA090129005

DIAMON

CONT

 

ENGINE

MALFUNCTIONED

1/26/2009

DA20C1

IO240B

 

IO240B

 

PILOT REPORT, ENGINE FAILED ON RUNWAY FOLLOWING FULL POWER APPLICATION AFTER DOING TOUCH AND GO. ENGINE WAS RESTARTED AFTER SEVERAL ATTEMPTS AND TAXIED OFF. MAINTENANCE RESPONSE, FUEL SET UP PROCEDURE WAS PERFORMED IN ACCORDANCE WITH TCM SID97-3E AND GROUND RUN SATISFACTORY WITH ALL FUEL AND POWER INDICATIONS NORMAL. EXPERIENCE WITH THESE ENGINE TYPES HAVE REVEALED THAT THEY CAN BE SENSITIVE TO AMBIENT TEMPERATURE AND PRESSURE CHANGES. ANOTHER CONTRIBUTING FACTOR IS THE CONDITION OF THE FUEL SYSTEM COMPONENTS AND RELATED FUNCTIONS. THE FUEL SET UP PROCEDURE USUALLY CORRECTS THIS TYPE OF CONDITION.

CA090129006

DIAMON

CONT

DIAMON

TUBE

WORN

1/29/2009

DA20C1

IO240B

EQUIPMENT

2227271100

UPPER S TUBE

INSPECTION OF THE RUDDER PEDAL ASSEMBLY REVEALED EXCESSIVE WEAR ON THE S TUBE CAUSED BY WEAR FROM THE RUDDER CABLE. THE WEAR WAS DETECTED BY VISUALLY CHECKING THE OUTER SURFACE OF THE S TUBE FOR MATERIAL DEFORMATION IN THE AREA(S) WHERE THE CABLE CAUSES THE MOST FRICTION ON THE INSIDE OF THE TUBE. THE AIRCRAFT RUDDER CABLES WERE DUE FOR REPLACEMENT AS MANDATED BY THE MANUFACTURER AT EACH 3000 HOURS TTSN. THIS DEFECT HAS BEEN ADDRESSED IN PREVIOUS REPORTS FROM THIS COMPANY. BASED ON THE NATURE OF THIS DEFECT WE REPLACED ALL RUDDER PEDAL ASSEMBLIES ALONG WITH THE CABLES AND HAVE AMENDED OUR INTERNAL MAINTENANCE TRACKING TO INSPECT/REPLACE AS NECESSARY THE PEDAL ASSEMBLIES AT 2500 HOUR INTERVALS. THIS ISSUE CONTINUES TO BE MONITORED.

CA090203006

DIAMON

CONT

 

RUDDER PEDAL

WORN

1/21/2009

DA20C1

IO240B

 

2227211200

COCKPIT

DURING THE AIRCRAFT PREFLIGHT INSPECTION, THE PILOT REPORTED THAT THE PILOTS SIDE RUDDER PEDAL CABLE WAS STUCK IN THE FULL FORWARD POSITION. CLOSER INSPECTION BY MAINTENANCE REVEALED THAT THE PILOTS SIDE LT RUDDER CABLE HAD WORN THROUGH THE S TUBE THAT FORMS PART OF THE PEDAL ASSEMBLY. THE CABLE WAS EXPOSED THROUGH THE UPPER BEND OF THE S TUBE TO A POINT WHERE IT WAS JAMMED IN ITS WEAR HOLE THUS RESTRICTING THE SLIDE ACTION OF THE PEDAL ASSEMBLY ON THE ADJUSTMENT SLIDE TUBE. THE DEFECTIVE PART WAS REPLACED ALONG WITH THE OTHER PEDALS DUE TO THEIR SUSPECTED CONDITION NEARING THAT OF THE FAILED PART.

CA090123006

DIAMON

CONT

DIAMON

ROLL PIN

MISSING

1/23/2009

DA20C1

IO240B

 

 

FLAP ACTUATOR

PILOT REPORTED THAT THE FLAPS WOULD NOT GO DOWN. INSPECTION REVEALED THAT THE ROLL PIN WHICH IS USED TO LOCK THE ROD END BEARING AT THE END OF THE FLAP ACTUATOR WAS MISSING ALLOWING THE FLAP ACTUATOR ROD TO ROTATE AND ALLOW FOR MIS-ALIGNMENT OF ALL FLAP CONTROL SWITCHES. REPAIRED FLAP ACTUATOR INSTALLED.

2009FA0000071

DIAMON

CONT

 

RELIEF VALVE

STICKING

2/10/2009

DA20C1

IO240B

 

631687

ZONE 400

PILOT CALLED TOWER TO REQUEST PERMISSION FOR PRIORITY APPROACH TO AIRPORT DUE TO A LOW OIL PRESSURE INDICATION. ACFT LANDED WITHOUT INCIDENT. MX PROCEDURES CONSISTING OF CLEANING OIL PRESSURE RELIEF VALVE PERFORMED, WITH A SATISFACTORY OPS RUN-UP CHECK. ACFT APPROVED FOR RETURN TO SERVICE BY AUTHORIZED MX PERSONNEL.

CA081229002

DIAMON

CONT

 

OIL SYSTEM

MALFUNCTIONED

12/29/2008

DA20C1

IO240B

 

 

ENGINE

(CAN) PILOT REPORTED LOW OIL PRESSURE READING (15-20 PSI) WHILE PERFORMING TEST FLIGHT AFTER MAINTENANCE. NO LEAKS WERE DETECTED & ACFT GROUND RUN WITH AN EXTERNAL PRESSURE GAUGE TO VERIFY PRESSURE READINGS ON ACFT GAUGE. OIL PRESSURE RELIEF SPRINGS & PLUNGER REPLACED WITH NEW. OIL PRESSURE INDICATIONS REMAIN SUSPECT WHEN COMPARED TO INFORMATION PROVIDED IN ACFT FLT MANUAL. SECTION 2.5 (TR-1) OF AFM STATES THAT THE OIL PRESSURE SHOULD BE 30-60 PSI IN GREEN NORMAL OPS RANGE FOR TYPE. NORMAL OPERATING RANGE IS STATED AS 700-2800 RPM. BASED ON THIS INFORMATION, OIL PRESSURE SHOULD BE AT LEAST 30 PSI EVEN AT 700 RPM. PREVIOUS EXPERIENCE ON THIS ACFT TYPE HAS PROVEN THAT IT IS NOT UNCOMMON FOR OIL PRESSURE READING TO INDICATE BELOW 30 PSI AT VARIOUS PHASES OF FLT. ENGINE OPS MANUAL SECTION 6-22 STATES "IF OIL PRESSURE DROPS BELOW 30 PSI, AN ENGINE FAILURE SHOULD BE ANTICIPATED." HAVE CONSULTED WITH THE ENGINE MANUFACTURER AND AIRFRAME MANUFACTURER FOR CLARITY ON INTERPRETING THESE OIL PRESSURE INDICATIONS. VARIOUS IDEAS AND TROUBLESHOOTING TIPS HAVE BEEN EXCHANGED AND DOCUMENTED WITH AMO 62-92.

2009FA0000100

DIAMON

 

 

GEAR

CRACKED

2/24/2009

DA40

 

 

 

STARTER GEN

WHILE ATTEMPTING TO START THE ENGINE ON THE GROUND THE ENGINE TURNED OVER SEVERAL TIMES BUT THEN STOPPED. THE STARTER WAS STILL RUNNING AND COULD BE HEARD FROM THE COCKPIT. INVESTIGATION REVEALED THE STARTER BENDIX/GEAR HSG HAD CRACKED AND SEPARATED FROM THE CASTING.

CA090122001

DIAMON

 

 

SHAFT

DAMAGED

1/5/2009

DA42

 

 

D6032338232

NLG 

THE NLG TUBULAR PIVOT ASSEMBLY SHOWS SIGNS OF FAILURE INDICATED BY THE MISALIGNMENT OF THE GUDGEON (D60-3233-82-31) WITHIN THE TUBULAR PIVOT SHAFT (D60-3233-82-32). THE MISALIGNMENT ALWAYS OCCURS ON THE LT GUDGEON AND ALWAYS OPENS TOWARD THE AFT DIRECTION WHEN THE GEAR IS DOWN AND LOCKED. FORCES ON THIS POINT ARE INDUCED BY THE NLG SPRING ASSEMBLY AND THE NLG ACTUATOR OVERDRIVING THE DOWN LOCK. REPEATED FORCES ON THE GUDGEON RESULT IN A BELLING DEFORMATION ON THE TUBULAR PIVOT SHAFT.

CA090122002

DIAMON

 

 

SHAFT

DAMAGED

12/29/2008

DA42

 

 

 

NLG 

THE NLG TUBULAR PIVOT ASSEMBLY SHOWS SIGNS OF FAILURE INDICATED BY THE MISALIGNMENT OF THE GUDGEON (D60-3233-82-31) WITHIN THE TUBULAR PIVOT SHAFT (D60-3233-82-32). THE MISALINGMENT ALWAYS OCCURS ON THE LT GUDGEON AND ALWAYS OPENS TOWARD THE AFT DIRECTION WHEN THE GEAR IS DOWN AND LOCKED. FORCES ON THIS POINT ARE INDUCED BY THE NLG SPRING ASSEMBLY AND THE NLG ACTUATOR OVERDRIVING THE DOWN LOCK. REPEATED FORCES ON THE GRUDGEON RESULT IN A BELLING DEFORMATION ON THE TUBULAR PIVOT SHAFT.

CA090122003

DIAMON

 

 

SHAFT

DAMAGED

12/29/2008

DA42

 

 

D6032338232

NLG 

THE NLG TUBULAR PIVOT ASSEMBLY SHOWS SIGNS OF FAILURE INDICATED BY THE MISALIGNMENT OF THE GUDGEON (D60-3233-82-31) WITHIN THE TUBULAR PIVOT SHAFT (D60-3233-82-32). THE MISALIGNMENT ALWAYS OCCURS ON THE LT GUDGEON AND ALWAYS OPENS TOWARD THE AFT DIRECTION WHEN THE GEAR IS DOWN AND LOCKED. FORCES ON THIS POINT ARE INDUCED BY THE NLG SPRING ASSEMBLY AND THE NLG ACTUATOR OVERDRIVING THE DOWN LOCK. REPEATED FORCES ON THE GRUDGEON RESULT IN A BELLING DEFORMATION ON THE TUBULAR PIVOT SHAFT.

CA090122004

DIAMON

 

 

SHAFT

DAMAGED

12/29/2008

DA42

 

 

D6032338231

NLG PIVOT ASSY

THE NLG PIVOT ASSEMBLY FAILED BY SHEARING OF THE LT GUDGEON WITHIN THE TUBULAR PIVOT SHAFT. THIS FAILURE WAS NOTED UPON INSPECTION DUE TO A NLG INDICATION LIGHT NOT BEING ILLUMINATED DURING TAXI OUT. UPON RETURNING TO HANGAR THE FAILURE WAS NOTED. ALSO DISCOVERED WAS COMPOSITE DAMAGE ON THE LT WALL OF THE WHEEL WELL INFLICTED BY THE NLG COMPONENT DISLOCATION.

CA090122005

DIAMON

 

DIAMON

SHAFT

DAMAGED

12/29/2008

DA42

 

D60323382

D6032338232

END OF SHAFT

THE NLG TUBULAR PIVOT ASSEMBLY SHOWS SIGNS OF FAILURE INDICATED BY THE MISALIGNMENT OF THE GUDGEON (D60-3233-82-31) WITHIN THE TUBULAR PIVOT SHAFT (D60-3233-82-32). THE MISALIGNMENT ALWAYS OCCURS ON THE LT GUDGEON AND ALWAYS OPENS TOWARD THE AFT DIRECTION WHEN THE GEAR IS DOWN AND LOCKED. FORCES ON THIS POINT ARE INDUCED BY THE NLG SPRING ASSEMBLY AND THE NLG ACTUATOR OVERDRIVING THE DOWN LOCK. REPEATED FORCES ON THE GRUDGEON RESULT IN A BELLING DEFORMATION ON THE TUBULAR PIVOT SHAFT.

CA090122006

DIAMON

 

DIAMON

SHAFT

DAMAGED

12/29/2008

DA42

 

D60323382

D6032338232

END OF SHAFT

THE NLG TUBULAR PIVOT ASSEMBLY SHOWS SIGNS OF FAILURE INDICATED BY THE MISALIGNMENT OF THE GUDGEON (D60-3233-82-31) WITHIN THE TUBULAR PIVOT SHAFT (D60-3233-82-32). THE MISALIGNMENT ALWAYS OCCURS ON THE LT GUDGEON AND ALWAYS OPENS TOWARD THE AFT DIRECTION WHEN THE GEAR IS DOWN AND LOCKED. FORCES ON THIS POINT ARE INDUCED BY THE NLG SPRING ASSEMBLY AND THE NLG ACTUATOR OVERDRIVING THE DOWN LOCK. REPEATED FORCES ON THE GUDGEON RESULT IN A BELLING DEFORMATION ON THE TUBULAR PIVOT SHAFT.

2009FA0000234

DIAMON

THIELT

 

TUBE

BENT

3/17/2009

DA42

TAE12501

 

D6032338232

ZONE 700

DURING A PREFLIGHT INSPECTION, THE NLG DRAG BRACE PIVOT WAS FOUND TO BE LOOSE, BENT AND DAMAGED. THE FOLLOWING PARTS NEEDED TO BE CHANGED BECAUSE OF DAMAGE. 1 CAMP BOLT TUBE, 1 BRACE BEARING, 1 NIG BRACKET, 2 GUDGEON AND 2 BEARINGS. INVESTIGATION REVEALED THROUGH AN OPERATION TEST OF THE LANDING GEAR THAT THE NLG ACTUATOR IS PUTTING TO MUCH PRESSURE ON THE CAMP BOLT TUBE WHEN IN THE EXTENDED POSITION. THIS CAUSES THE CAMP BOLT TUBE TO BEND AND OVER TIME CAUSES THE ENDS TO FLARE OUT WHERE THE GUDGEONS AND INSTALLED. IF ALLOWED TO GO ON THE GUDGEONS COULD FALL OUT.

2009FA0000211

DIAMON

THIELT

 

WIRE HARNESS

BURNED

2/26/2009

DA42

TAE1250299

 

057150E000902

FADEC

DURING IMC FLIGHT, THE RT ENGINE EXPERIENCED A RAPID 50 PERCENT POWER EXCURSION DOWNWARD TO 25 PERCENT AND RAPID SURGING THEREAFTER. AN EMERGENCY WAS DECLARED TO ATC, THE FLIGHT COMPLETED SAFELY. INVESTIGATION: ON THE FADEC ENGINE WIRING LOOM, THE PROPELLER CONTROL VALVE CONNECTOR CONTACTS WERE FOUND BURNED FROM ARCING, AND THE CONTACTS WERE MECHANICALLY SPREAD AND NO LONGER ABLE TO MAKE GOOD CONTACT WITH THE PROP CONTROL VALVE SPADE TYPE PINS. IF THIS CONNECTOR LOSES CONDUCTIVITY WITH THE PROPELLER CONTROL VALVE IN FLIGHT, THE PROP "FAIL SAFES" TO FEATHER, SHUTTING THE ENGINE DOWN. THIS OPERATOR HAS HAD SEVERAL PROBLEMS WITH THESES ENGINES DEEP SURGING, INCLUDING ONE IN-FLIGHT. (K)

2009FA0000228

ECLIPS

 

 

ATTACH FITTING

LOOSE

3/14/2009

ECLIPSEEA500

 

 

 

LT WING

LAST YEAR ABOUT THIS TIME WE WERE PERFORMING PERFORMANCE MODS ON THE ACFT. FOUND THE MAIN WING ATTACH POINTS TO HAVE EXCESSIVE PLAY ON BOTH WINGS WHEN ACFT WAS ON JACK. ENGINEERING LOOKED AT THE DATA WE PRESENTED TO THEM AND SAID "THE PLAY WAS WITHIN LIMITS." HAVE WORKED MANY ACFT AND NEVER SEEN THIS CONDITION ACCEPTABLE. IT HAS APPROX .020 TO .030 PLAY AT MAIN WING ATTACH FITTING. WHICH AT THE WING TIPS = OUT TO ABOUT 8 INCH. ENGINEERING DID NOT SPECIFY ANY ADDITIONAL INSP REQUIREMENTS. BELIEVE THIS WAS A COVER UP BY UPPER MANAGEMENT AT THE TIME SO THAT THE PRODUCT WOULD NOT BE DAMAGED. I AM HIGHLY CONCERNED THAT IS AN UNSAFE CONDITION AND NEEDS TO BE LOOKED INTO. THERE ARE MANY OTHER ITEMS ON THIS ACFT THAT NEED TO BE LOOKED INTO AS WELL SUCH AS AVIONICS SYS. FIRE PROTECTION AGENT IS SEVERALLY CORROSIVE WITH IN A DAY IF THE AGENT IS NOT FOUND LEAKING IT EATS STAINLESS STEEL AND ALUMINUM VERY QUICKLY. THE RT ENGINE IS EFFECTED SEVERAL BECAUSE THE IMPENDING BYPASS SWITCH FOR THE FUEL CONTROLLER IS DRIPPED ON BY THE AGENT AND COULD CAUSE AN UNSAFE CONDITION IF THERE IS BLOCKAGE WITH FUEL THE INDICATION MY NOT BE RECORDED. AT THE TIME,DID NOT REPORT IT BECAUSE MFG SCARED EMPLOYEES WITH THERE NONDISCLOSURE AGREEMENT AND TERMINATION IF ANY INFORMATION WAS LEAKED OUT. AC NR SERIAL NR 28 WAS THE AIRCRAFT THAT THE WINGS WERE FOUND LOSS ON.

2009FA0000189

ECLIPS

 

 

WINDSHIELD

DAMAGED

1/22/2009

ECLIPSEEA500

 

 

561035971004

COCKPIT

DURING A POST FLIGHT INSPECTION, IT WAS NOTED THAT THE INNER PANE OF THE PILOTS WINDSHIELD HAD LOCALIZED HAZING IN THE CRITICAL VISION AREA, AS DEFINED BY EA500 AMM 06-117751, CHAPTER 56-00-00, FIG 601; JUST BEHIND THE GLARE SHIELD MOUNTED OPTIONAL ELECTRIC ATTITUDE INDICATOR. ACFT WAS FERRIED TO SERVICE CENTER, UNDER LIMITED ALTITUDE OF NO MORE THAN 12,000 (UNPRESSURIZED) FEET WITH AIRSPEED OF NO MORE THAN 250 KNOTS, FOR THE REPLACEMENT OF PILOTS WINDSHIELD. CONTROL NO. CUXA2009-00001

CA090127001

EMB  

GE  

 

BRAKE ASSY

FAILED

12/13/2008

ERJ170200SU

CF348E5A1

 

900005832PR

 

TRANSCRIPTION OF EMAIL RECEIVED FROM MRO: BRAKE PN 90000583-1PR SN MAR05-0550 AC PO C129RAER006 THIS BRAKE WAS RECEIVED IN PRETTY BAD CONDITION. IT LOOKS LIKE 2 ROTORS AND 1 STATOR FAILED DURING OPERATION. ATTACHED ARE SOME PICTURES OF THE BRAKE AND PIECES OF THE CARBON STACK THAT FELL OUT OF THE BRAKE. WE HAVE NOT DISASSEMBLED YET IN CASE SOMEONE NEEDS TO INVESTIGATE FURTHER. IT ALSO LOOKS LIKE SOME DAMAGE TO THE TORQUE TUBE WHERE WE CAN SEE IN THROUGH THE HOLE BY THE MISSING CARBON DISK.

CA090127004

EMB  

GE  

MEGGITT

DISK

DAMAGED

1/21/2009

ERJ170200SU

CF348E5A1

 

 

BRAKE ASSY

TRANSCRIPTION FROM EMAIL RECEIVED FROM ENGINEERING DEPT, FAILED WITH 2048 LANDINGS SINCE INSTALLATION, MPN: 90000583-1PR WITH SN: APR05-0595 FOUND THE DAMAGE WAS FOUND AFTER REMOVAL OF THE WHEEL TO REPAIR FLAKING PAINT WHICH WAS IDENTIFIED IN THE 14TH OF JANUARY DURING A WTL M/W CHANGE AT THAT POSITION. NO DAMAGE TO THE BRAKE WAS NOTED AT THAT TIME. SO IN MERELY 7 DAYS WE HAD SUFFICIENT DETERIORATION OF THE CARBON CONDITION TO CAUSE FAILURE DESPITE HAVING DONE THE RECOMMENDED INSPECTIONS PER THE SB.

CA090204001

EMB  

GE  

 

WHEEL

FAILED

1/29/2009

ERJ190100IGW

CF3410E5A1

 

90002331

MLG 

THE RIGHT MAIN TIRE WAS BLOWN ON LANDING. THERE WAS TIRE DEBRIS FOUND ON RUNWAY. ENGINEERING BELIEVE THIS TO BE CAUSED BY A FROZEN BRAKE. OTHER P/N (O/B HALF WHEEL) IS 90002318, S/N IS JUL06-0529.

CA090205010

GROB

LYC  

 

ACTUATOR

DAMAGED

1/23/2009

G120A

AEIO540D4D5

 

120A42614262

TE FLAPS

AIRCRAFT ON LOCAL FLIGHT TRAINING MISSION. INSTRUCTOR NOTED FLAPS CIRCUIT BREAKER POPPED WHEN FLAPS SELECTED UP. C/B RESET AS PER CHECKLIST, POPPED WHEN SELECTED UP A SECOND TIME. INSTRUCTOR ADVISED ATC OF FLAP DIFFICULTY AND RETURNED TO LAND WITH FLAPS IN LANDING, FULL DOWN, POSITION. ACFT WAS MET WITH AIRFIELD EMERGENCY RESPONSE, LANDED WITHOUT INCIDENT. MAINTENANCE BROUGHT ACFT INTO WARM HANGAR. FLAPS CYCLED REPEATEDLY WITHOUT FAULT. ACFT RELEASED SERVICEABLE. THE FLAP C/B EVENT IS TYPICAL OF TYPE IN COLD WEATHER (MID -20S C. AND COLDER). THE FLAP ACTUATOR IS AN `ACME` THREAD SCREW JACK DRIVEN BY FLEXIBLE DRIVES FROM THE FLAP MOTOR/TRANSMISSION ASSY. IT IS SUSPECTED THAT THE LUBRICANT IN THE ACTUATOR BECOMES TOO VISCOUS IN COLD WEATHER CAUSING EXCESSIVE RESISTANCE AT THE MOTOR. CONSEQUENTLY THE MOTOR IS SLOWED CAUSING THE HIGHER THAN NORMAL CURRENT DRAW, HENCE THE C/B POPS. OEM IS WORKING WITH OPERATOR TO DELIVER FLAP ACTUATORS WITH AN IMPROVED LUBRICANT THEY BELIEVE WILL IMPROVE THE COLD WEATHER RELIABILITY OF THE FLAP SYSTEM.

CA090129007

GRUMAN

WRIGHT

 

BUSHING

WORN

1/28/2009

TS2ACALFORST

982C9HE2

 

89TM109641

ELEVATOR

DURING VISUAL INSPECTION OF ELEVATOR BELLCRANK IAW SB 00-004R1, WEAR WAS FOUND IN THE BUSHING BOSS PLATE.

CA090129015

GULSTM

LYC  

 

SHAFT

CRACKED

1/26/2009

500S

IO540E1B5

 

7500691

NLG 

ON VISUAL INSPECTION OF THE NOSE LANDING GEAR DRAG BRACE AND BUNGEE SYSTEM, IT WAS FOUND THAT THE SHAFT LINKING THE DRAG BRACE TO THE BUNGEE WAS CRACKED AT THE BOLT HOLES. THE BOLT HOLES WERE FOUND TO ALSO BE ELONGATED. THE SHAFT WAS REMOVED AND THE HIDDEN PART OF THE SHAFT WAS SEVERELY CRACKED. SIX OTHER AERO COMMANDER 500B AND 500S ARE TO BE INSPECTED. TO DATE 2 SHAFTS ARE FOUND CRACKED.

AMCR200901

GULSTM

 

 

EXTINGUISHER

DISCHARGED

3/2/2009

GIVG400

 

 

474276

ZONE 900

DURING ROUTINE INSP, FOUND MINI-EXTINGUISHER (9 CU.IN) FOR WASTE RECEPTACLE IN GALLEY FAILED WEIGHT CHECK. FOUND DISCHARGE TUBE CHAFED FROM CONTACT WITH WASTE RECEPTACLE.

CA090130011

GULSTM

GARRTT

 

ACTUATOR

MALFUNCTIONED

1/23/2009

GULFSTREAMGV

TFE73140

 

3538000000

MLG 

AFTER TAKEOFF THE GEAR LANDING GEAR WAS SELECTED UP. ALL 3 "DOWN AND LOCKED" LIGHTS EXTINGUISHED BUT THE "IN TRANSIT" RED LIGHT REMAINED ILLUMINATED AND THE TOWER REPORTED THAT THE RIGHT MAIN GEAR WAS STILL EXTENDED. THE LANDING GEAR WAS SELECTED DOWN. THE NOSE AND LEFT MAIN GEAR "DOWN AND LOCKED" LIGHTS ILLUMINATED IMMEDIATELY BUT THE RED "IN TRANSIT" LIGHT REMAINED ILLUMINATED. AFTER APPROXIMATELY 30 SECONDS THE RIGHT MAIN GEAR "DOWN AND LOCKED" INDICATOR ILLUMINATED AND THE "IN TRANSIT" LIGHT EXTINGUISHED. THE AIRCRAFT LANDED AND RETURNED TO THE HANGAR. A VISUAL INSPECTION REVEALED NO OBVIOUS DAMAGE OR LEAKAGE. A REPLACEMENT ACTUATOR WAS INSTALLED AND THE AIRCRAFT RETURNED TO SERVICE. NO RECURRENCE HAS BEEN NOTED IN THE FOLLOWING 3 FLIGHTS DURING WHICH THE LANDING GEAR WAS RETRACTED AND EXTENDED NUMEROUS TIMES. THE FAILED ACTUATOR HAS BEEN RETURNED TO THE MANUFACTURER FOR INVESTIGATION.

CA090205005

HOFFLU

ROTAX

 

CRANKCASE

CRACKED

2/4/2009

H36DIMONA

ROTAX914

 

888364

ENGINE

OIL LEAKING FROM UPPER REAR CYLINDER HOLD DOWN STUD. THE OIL WAS FOUND TO RUN DOWN THE STUD AND EXIT ONTO THE CYLINDER FINS. OIL LEAK WAS ONLY NOTICED AT HIGHER TEMPS, AREA WOULD STAY CLEAN AT NORMAL RUN-UP CONDITIONS. THIS LEAK IS UNUSUAL AS THE STUD DOES NOT PROTRUDE INTO THE CASE (SO NO O-RING OR SEALANT IS REQUIRED). CASE WAS DISASSEMBLED AND NDT LOCATED THE CRACK ON THE INSIDE WEBBING OF THE CENTER CRANKSHAFT JOURNAL. CRACK WAS NOT VISUALLY DETECTABLE AND DID NOT CONTINUE TO THE OUTSIDE SURFACE OF THE CRANKCASE. CRANKCASE TO BE REPLACED WITH NEW.

CA090126006

HUGHES

LYC  

 

BOLT

BROKEN

1/26/2009

269C

HIO360D1A

 

269A60923

TAIL ROTOR

OPERATING A SCHWEIZER 269 C MODEL SERIAL NUMBER S1575 TSN 6449.5 THE CONICAL BRGS WERE REPLACE WITH NEW AT 6338.8 AND A NEW BOLT WAS INSTALLED AT THIS TIME P/N 269A6092-3 WHICH WAS PURCHASE NEW FROM SCHWEIZER ON. THE RETORQUE WAS CARRIED OUT AT 6416.1 TSN NO MOVEMENT WAS NOTED AT THIS TIME. THE AIRCRAFT WAS IN FLIGHT AT THE TIME OF THE OCCURRENCE. THE PILOT WAS TURNING SHORT FINAL WHEN HE FELT A VIBRATION SUSPECTED ENGINE PROBLEMS. HE COMPLETED A RUN ON LANDING UNDER POWER WHILE MAINTAINING DIRECTIONAL CONTROL. UPON LANDING THE AIRCRAFT WAS NOT PERFORMING CORRECTLY AND A VIBRATION WAS FELT. THE PILOT SHUT DOWN AND MAINTENANCE WAS BROUGHT OUT TO AIRCRAFT. UPON INSPECTION OF AIRCRAFT IT WAS NOTED THE FLAPPING HINGE BOLT WAS SHEARED AND THE AIRCRAFT WAS THEN GROUND HANDLED TO THE HANGAR FOR FURTHER INSPECTION.

CA090115008

HUGHES

ALLSN

ALLSN

SPRAG ASSY

UNSERVICEABLE

1/15/2009

369D

250C20B

 

369D25351

O/R CLUTCH

SPRAG ASSY FAILED 300 HR INSPECTION DUE TO 2 BROKEN CORNERS OF 2 DIFFERENT TEETH (SPRAGS). NO OTHER DAMAGE WAS FOUND TO THE ASSEMBLY AS A RESULT OF THIS INCIDENT. CLUTCH ASSY WAS WORKING FINE PRIOR TO INSPECTION. NEW SPRAG ASSY INSTALLED AND CLUTCH RETURNED TO SERVICE.

CA090112011

HUGHES

ALLSN

 

BELLCRANK

CRACKED

1/7/2009

369D

250C20B

 

369A7302

FLT CONTROLS

A CRACK WAS FOUND ON THIS FLIGHT CONTROL BELLCRANK DURING ANNUAL INSPECTION.

2009FA0000247

LANCAR

CONT

 

SPEED BRAKE

FAILED

3/2/2009

LC40550FG

IO550N

 

300500031

WING 

THE ACFT USES PRECISE FLIGHT SPEEDBRAKES. 31 AUG 07, FOUND A PROBLEM WITH THE SPEEDBRAKES AND WERE REPLACED. THE SPEEDBRAKES HAVE BEEN OVERHAULED (5) TIMES SINCE. 2 MAR 09, DEPLOYED THE SPEEDBRAKES IN FLIGHT AND THE ACFT YAWED TO THE RIGHT. APPARENTLY ONE SPEEDBRAKE DEPLOYED BEFORE THE OTHER. INSPECTED THE SPEEDBRAKES AND FOUND SEVERAL DISCREPANCIES. THE PROBLEM COULD BE A VERY TIGHT FIT OF THE RT SPEEDBRAKE. SCRAPED AND SANDED THE RT SPEEDBRAKE HOLE. THE SPEEDBRAKES ARE CURRENTLY BEING OVERHAULED. THIS IS A SAFETY OF FLIGHT PROBLEM. WHEN THE POWER WAS REMOVED THE RT SPEEDBRAKE AND WOULD STAY DEPLOYED. (K)

2009FA0000233

LANCAR

CONT

 

CYLINDER HEAD

CRACKED

3/17/2009

LC42550FG

IO550N

 

655465B

NR 4 

DURING INSP, FOUND NR (4) CYLINDER CRACKED FROM FUEL INJECTOR HOLE TOWARDS UPPER SPARK PLUG HOLE.

BHKA10FNFEB252009

LEAR

GARRTT

 

TURBINE BLADES

FAILED

2/25/2009

36LEAR

TFE731*

 

 

ENGINE

WHILE CLIMBING AT 17,000 FT, APPROX 40 MINUTES INTO FLIGHT, HEARD LOUD BANGS COMING FROM THE RT ENG. THE ENGINE SHUTDOWN, AND THE A/C LANDED (UNSCHEDULED) WITHOUT INCIDENT. UPON VISUAL INSPECTION, IT WAS FOUND THERE WAS CONTAINED TURBINE FAILURE, AND BLADES WERE MISSING. THE ENGINE IS BEING REMOVED FOR TEARDOWN ANALYSIS, AND INVESTIGATION BY MAINT.

CA090212004

LEAR

ALIDSG

 

DRIVE UNIT

LEAKING

2/11/2009

45LEAR

TFE7313AR

 

C1444831

TE FLAPS

(CAN) FLAP POWER DRIVE UNIT FOUND LEAKING FROM SOLENOID VALVE, THIS IS THE (4TH) UNIT WE HAVE HAD THE SAME FAULT ON, NO SDR WAS SUBMIITTED ON THE PREVIOUS UNITS. THE FIRST UNIT SN 1385P HAD 1217.9 TT WHEN IT STARTED TO LEAK FROM SOLENOID, REPLACED 2008/04/11, NEXT UNIT SN 1101 WAS ON FOR 29.1 HOURS, REPLACED 2008/05/11, NEXT UNIT SN 1387 WAS ON FOR 99.6 HOURS REPLACE 2009/07/11, UNIT SN 1322 WAS INSTALLED FOR 279.8 HOURS. ACCORDING TO MM NO LEAK RATE FROM THE SOLENOID VALVE IS GIVEN.

CA090121002

LKHEED

ALLSN

 

WINDSCREEN

FAILED

1/19/2009

382G

501D22A

 

3850201

COCKPIT

(CAN) AFTER DEPARTING, THE ACFT SUFFERED A CENTER WINDSHIELD OUTER PANE FAILURE. THE CREW REDUCED CABIN PRESSURE AND THE ACFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MX REPLACED THE CTR WINDSHIELD AND THE ACFT WAS RETURNED TO SERVICE.

CA090210005

LKHEED

ALLSN

HAMSTD

HOUSING

LEAKING

2/6/2009

382G

501D22A

 

582855

VALVE

DEPARTING YZF THE CREW OBSERVED A LOW OIL INDICATION ON NR 3 PROPELLER IN THE CLIMB WITH NORMAL RPM. THE PROPELLER RPM INCREASED TO 103 PERCENT SHORTLY AFTER AND THE CREW SHUT THE NR 3 ENGINE DOWN. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE REPLACED THE NR 3 PROPELLER, AND PROP VALVE HOUSING AND THE AIRCRAFT WAS RETURNED TO SERVICE. MAINTENANCE OBSERVED SOME DAMAGE ON 3 PROPELLER BLADE SEALS AND IT IS UNCONFIRMED THAT THE FLUID LOSS INDUCED A VALVE HOUSING PROBLEM OR IF THE OVER SPEED CONDITION WAS RESULTANT FROM AN ACTUAL PROP VALVE FAILURE. TEARDOWN RESULTS ARE BEING REQUESTED FROM THE VENDOR.

2009FA0000238

LKHEED

 

 

FITTING

CRACKED

3/20/2009

P3A  

 

 

9032201

ZONE 500

DURING PHASE DEPOT INSP THE LWR FWD LT RING FITTING, PN 903220-1 WAS FOUND FRACTURED THRU THE HORIZONTAL BOTTOM FLANGE AT THE FILLET NUT PLATE HOLE AND HAD PROPAGATED ACROSS THE BOTTOM WEB AND UP THE VERTICAL THROUGH TWO FASTENERS; THE FIRST .1875 INCHAND THE SECOND .2500 INCH DIAMETER WHERE THE FRACTURE TERMINATED. THE TOTAL LENGTH IS APPROXIMATELY 2.6250 INCHES.

CA090204005

PIAGIO

PWA  

 

INSULATION

MISINSTALLED

1/22/2009

P180

PT6A66

 

80909115611C

COCKPIT

(CAN) DURING AN AVIONICS SYS MODIFICATION, DIMMING CONTROL RELAY PANEL P/N 8090986-401 WAS REMOVED FROM PILOT`S SIDE OF COCKPIT FOR ACCESS. THE INSULATION BAG, P/N 80-909156-11C WAS OBSERVED TO HAVE (2) TWO BURN HOLES IN IT, APPARENTLY CAUSED BY THE (2) RESISTORS THAT ARE ATTACHED TO THE DIMMING CONTROL RELAY PANEL. UPON FURTHER INVESTIGATION, IT APPEARS THAT THE INSULATION BAG (P/N 80-909156-11C) WAS NOT INSTALLED IN THE PROPER POSITION.

CA090205009

PILATS

PWA  

PILATS

BUSHING

WORN

2/2/2009

PC1245

PT6A67B

 

 

FLAP DRIVE SYS

CREW REPORTS OF INTERMITTENT FLAP OVERSPEED WARNINGS WITH FLAPS UP. SOMETIMES ASSOCIATED WITH FLAP AND PUSHER WARNINGS. NO MAINTENANCE CODES WERE NOTED FROM FCWU. SLOTTED BUSHING IN FLAP DRIVE ARM ASSY WAS FOUND UNBONDED, UPON ROTATION, THE IMPROPER ORIENTATION OF THE SLOT WOULD CAUSE THE ARM TO HAVE EXCESSIVE PLAY. THIS IN TURN WOULD ALLOW THE SWITCH ACTUATOR ARM TO COME OFF THE UPLIMIT SWITCH INTERMITTENTLY IN FLIGHT AND REMOVE THE "FLAPS UP" SIGNAL TO THE FLAP CONTROL AND WARNING UNIT, THE STICK PUSHER COMPUTERS AND THE AIRSPEED WARNING SYSTEMS. BOTH LEFT AND RIGHT ARM ASSYS WERE REPLACED WITH NEW AS RT WAS FOUND WITH UNBONDED BUSHES.

CA090206002

PILATS

PWA  

 

GENERATOR

FAILED

2/5/2009

PC1245

PT6A67B

 

5243212158

NR 2 

ON MORNING GROUND RUN NR 2 GENERATOR WOULD NOT TAKE A LOAD MORE THAN 60 AMPS AS READ OFF EIS. NR 2 GENERATOR WOULD GO OFF AND ON LINE BY IT SELF (FLASHING WARNING) ON ANNUNCIATOR PANEL AND OVERHEAD PANEL. REPLACED GENERATOR WITH SERVICEABLE UNIT, DEFECT GONE.

5APR577Y5

PILATS

PWA  

 

CONTROL UNIT

FALSE INDICATION

3/5/2009

PC1247

PT6A67

 

065001885102

ZONE 100

DURING CLIMB AND CRUISE BOTH PRIMARY FLIGHT DISPLAYS (PFD) INDICATED A 12-20 DEGREE LT TURN WHILE THE ACFT WAS IN A WINGS LEVEL CONDITION, WHICH WAS CONFIRMED BY THE VISUAL METEOROLOGICAL CONDITIONS AND THE ATTITUDE INDICATION ON THE ELECTRONIC STANDBY INSTRUMENT SYSTEM (ESIS). THIS IS BEYOND THE 10 DEGREE ATTITUDE ROLL ATTITUDE OFFSET DESCRIBED IN AD 09-04-14 AND POH TEMPORARY REVISION 9. THIS DISCREPANCY OCCURRED AFTER MFG "BUILD 5" HAD BEEN ACCOMPLISHED ON THIS ACFT. BOTH CHANNELS OF THE ADAHRS UNIT TEST NORMALLY IAW AMM 12-B-34-25-00-00S-903S-S WITH NO DOWNLOADABLE FAULTS.

5APR577Y4

PILATS

PWA  

 

BRAKE DISC

BROKEN

3/2/2009

PC1247

PT6A67B

 

244755

LT MLG

DURING AN ANNUAL INSPECTION THE LT MAIN WHEEL WAS REMOVED TO REPACK THE WHEEL BEARINGS WHEN IT WAS DISCOVERED THAT OTBD BRAKE DISC ON THE LT BRAKE WAS BROKEN INTO SEVERAL PIECES. THE BRAKE ASSY WAS REMOVED AND REPLACED.

CA090212006

PIPER

LYC  

 

GAUGE

FAILED

1/14/2009

PA28140

O320E2A

 

687258

FUEL QTY

(CAN) FUEL GUAGE BECAME INTERMITTENT AND EVENTUALLY FAILED TO FUNCTION. FAULTY GUAGE REMOVED AND REPLACED WITH NEW GUAGE.

2009FA0000174

PIPER

LYC  

PRECISION

BOWL

DEFECTIVE

3/3/2009

PA28161

O320D3G

 

15A21

CARBURETOR

ACFT WAS STARTED AND TAXIED TO ACTIVE RUNWAY FOR DEPARTURE. A NORMAL RUN-UP WAS PREFORMED AND NO PROBLEM WAS NOTED. ON TAKEOFF NORMAL RPM WAS NOTED AND AS THE ACFT BECAME AIRBORNE AND ON INITIAL CLIMB OUT ENGINE ROUGHNESS WAS NOTED AND THEN AS THE PILOT MADE A DECISION TO ENTER A DOWNWIND FOR A RETURN TO THE FIELD A NOTICEABLE ROUGHNESS AND POWER LOSS WAS NOTED AND AN UNEVENTFUL RETURN TO THE FIELD WAS MADE. UPON AN INVESTIGATION OF THE ENGINE COMPARTMENT AND OF THE INDUCTION SYSTEM IT WAS NOTED THAT THE CARBURETOR BOWL COULD BE MOVED. THE (4) FOUR SCREWS HOLDING THE BOWL ON HAD THE LOCKS ATTACHED AND THE SCREWS ARE LOOSE. THIS CAUSED AN UNEVEN FUEL FLOW AND DISRUPTION OF FLOW CAUSING ENGINE ROUGHNESS AND POWER LOSS. THE CARBURETOR HAD BEEN OVERHAULED BY THE COMPANY THAT HAD OVERHAULED THE ENGINE WITH ONLY 125.5 HR T.I.S. IN THIS CASE THE IMPROPER INSTALLATION OF BOWL TO THROTTLE BODY ASSY OR THE USE OF A BOWL ASSY. WITH DEFECTIVE THREADS WAS THE CAUSE OF THE DEFECT.

CA090126002

PIPER

LYC  

 

SPRING

MISINSTALLED

1/24/2009

PA28R201

IO360C1C6

 

 

IMPULSE COUPLING

ENGINE DISPLAYED EXCESSIVE MAG DROP DURING PRE-FLIGHT RUNUP. MAGNETO REMOVED FOR INSPECTION. IMPULSE COUPLING SPRING FOUND INCORRECTLY INSTALLED IN HOUSING RESULTING IN DAMAGE TO HOUSING. IMPULSE COUPLING FAILED MANDATORY INSPECTION REQUIREMENTS IN SERVICE MANUAL L1363D. IMPULSE COUPLING REMOVED FROM SERVICE AND REPLACED WITH NEW UNIT. CARBON BRUSH INSTALLED INCORRECTLY, CARBON BRUSH REMOVED AND REPLACED WITH NEW BRUSH.

CA090220005

PIPER

CONT

 

PLUG

MISSING

2/13/2009

PA28R201T

TSIO360F

 

6295183

ACCESSORY CASE

ON APPROACH TO YBL, THE PILOT DETECTED BURNING OIL AND SAW SMOKE, THE PILOT LANDED THE AIRCRAFT AND NOTICED A LARGE AMOUNT OF OIL ON THE BELLY OF THE AIRCRAFT AND DRIPPING FROM THE COWLS, AFTER THE TECHNICIAN INVESTIGATED THE OIL LEAK HE FOUND A HOLE WHERE A PLUG SHOULD BE IN THE ACCESSORY CASE, AFTER A BRIEF SEARCH FOR THE MISSING PART AND NOT FINDING THE PLUG THE TECH INSTALLED A NEW PLUG (PN AN913-3) AND LOCKWIRED.

CA090212003

PIPER

LYC  

 

TIRE

DEFLATED

2/9/2009

PA31350

LTIO540J2BD

 

40141

NLG 

THE AIRCRAFT LANDED WITH INDICATIONS OF A SOFT NOSE TIRE ON THE ROLL OUT. ON THE TAXI TO THE HANGAR, THE TIRE WENT COMPLETELY FLAT. THE TIRE WAS REPLACED AND THE AIRCRAFT CONTINUED ON IT`S SCHEDULED FLIGHT. WHEN THE TIRE WAS DISASSEMBLED, A "ROUND SHAPED" CUT WAS FOUND IN THE TUBE SIDEWALL. IT WAS THE SHAPE AND DIAMETER OF A AS3209-009 O-RING. AN O-RING OF THIS SIZE WAS FOUND BETWEEN THE TUBE AND THE TIRE WALL. IT IS BELIEVED THAT THE O-RING WAS TRAPPED INSIDE THE TIRE DURING BUILD UP AND THE MOVEMENT OF THE TUBE CAUSED THE CHAFING WHERE THE O-RING WAS TRAPPED. A REVIEW OF PROCEDURES HAS BEEN COMPLETED WITH THE MAINTENANCE SHOP TO AVOID THIS ISSUE AGAIN. IT HAS BEEN SUBMITTED AS AN SMS REPORT.

CA090212005

PIPER

LYC  

 

TUBE

DEFLATED

2/10/2009

PA31350

LTIO540J2BD

 

40141

NLG TIRE

(CAN) WHEN THE ACFT TOUCHED DOWN, A VIBRATION WAS FELT IN THE NOSEGEAR. THE NOSE TIRE WAS COMPLETELY FLAT AFTER THE ACFT STOPPED. THE ACFT WAS TOWED TO THE HANGAR AND THE WHEEL REMOVED. THE VALVE STEM HAD SHEARED OFF AS WELL AS THERE BEING SOME DAMAGE TO THE TUBE. IT WAS BELIEVED THAT MOST OF THE DAMAGED WAS CREATED DURING THE TOWING OF THE ACFT. A NEW TIRE AND TUBE WERE INSTALLED ON THE ACFT.

CA090213005

PIPER

LYC  

 

PUMP

SEIZED

2/11/2009

PA31350

LTIO540J2BD

 

2B663

FUEL BOOST

(CAN) AFTER TAKEOFF THE RT BOOST PUMP CIRCUIT BREAKER POPPED. THE FLIGHT CREW THEN RETURNED TO BASE. UPON INVESTIGATION BY MX IT WAS FOUND THE RT BOOST PUMP HAD SEIZED. THE BOOST PUMP WAS REPLACED AND ACFT RETURNED TO SERVICE.

CA090210009

PIPER

LYC  

 

DRIVE SHAFT

SHEARED

2/4/2009

PA31350

LTIO540J2BD

 

442CW6

VACUUM PUMP

AFTER INSTALLING THE PUMP ON THE AIRCRAFT THE PUMP SEIZED AND THE DRIVE SHEARED. THE PUMP WAS AN OVERHAULED PUMP.

CA090210004

PIPER

LYC  

 

SHAFT

SHEARED

2/3/2009

PA31350

LTIO540J2BD

 

 

VACUUM PUMP

ON TAKEOFF THE RT PNEUMATIC SOURCE LIGHT ILLUMINATED. THE AIRCRAFT REJECTED TAKEOFF AND RETURNED TO BLOCKS. MAINTENANCE DISCOVERED THE DRIVE ON THE PNEUMATIC PUMP SHEARED.

CA090202002

PIPER

LYC  

 

STARTER

CRACKED

1/29/2009

PA31350

LTIO540J2BD

 

149NLR

ENGINE

DURING A ROUTINE INSPECTION IT WAS DISCOVERED THAT THE TAB ON THE STARTER THAT THE BELT TENSIONER PULLEY ATTACHES TO WAS SHEARED AT THE HOUSING. THE PART ONLY HAD 128.4 HOURS ON IT AND WAS RETURNED FOR WARRANTY. THE PART MANUFACTURER IS SKY TEC BUT I COULDN`T ENTER THAT BRAND NAME.

CA090218006

PIPER

LYC  

 

VALVE

FAILED

2/18/2009

PA31350

LTIO540J2BD

 

53E22144

VERNATHERM

(CAN) IN CRUISE, THE PILOT NOTICED THAT THE RT ENGINE OIL TEMP WAS CLIMBING TO THE RED LINE WITH A DECREASE IN OIL PRESSURE. THE PILOT DECIDED TO SHUT DOWN AND SECURE THE ENGINE ONCE THE OIL TEMP REACHED THE RED LINE. THE PILOT RETURNED TO BASE WITHOUT INCIDENT. MX FOUND THAT THE VERNATHERM VALVE SPRING WAS BROKEN AND WAS PROTRUDING OVER THE SEAT WHICH WOULD NOT ALLOW THE VERNATHERM TO DIRECT THE OIL THROUGH THE OIL COOLER. A NEW VERNATHERM VALVE WAS INSTALL AND THE ENGINE OIL TEMP RETURNED TO NORMAL.

CA090225014

PIPER

LYC  

 

SHAFT

SHEARED

11/29/2008

PA31350

TIO540J2BD

 

 

FUEL PUMP

PILOT REPORT ENGINE FUEL PUMP ON APPROACH AND VACUUM PUMP FAILURE. FUEL PUMP AND VACUUM PUMP FOUND BOTH WITH SHAFT BROKEN. BOTH REPLACED, ENGINE DIDN`T START. ENGINE REMOVED AND SENT FOR REPAIR. REPORT FROM REPAIR SHOP RECEIVED WITH INDICATION OF METAL CONTAMINATION AND SEVERE DAMAGED TO ACCESSORIES GEAR MAYBE CAUSE BY FAILURE OF FUEL PUMP. PUMP STILL IN OUR HAND WE WOULD GET AN EXPERTISE ON THE UNIT.

2009FA0000219

PIPER

LYC  

 

BELT

BROKEN

2/20/2009

PA31350

TIO540J2BD

 

LW18129

RT ALTERNATOR

BOTH RT AND LT ALTERNATOR BELTS BROKE IN FLIGHT, POSSIBLE CAUSE WAS BOTH ENGINES MAY HAVE BEEN STARTED WITH NOSE COWL PLUG WOOL BLANKETS INSTALLED, THUS, BINDING UP THE PULLEYS AND/OR BELTS WHILE THE REST OF THE MOVING PARTS SEVERELY CUT INTO THE BELTS. BOTH BELTS HAD LESS THAN 10 HOURS TIME IN SERVICE. (K)

CA090204013

PIPER

PWA  

 

BOLT

LOOSE

1/30/2009

PA31T

PT6A28

 

 

FUEL CELL

AFTER REMOVING THE AIRCRAFT FROM JACKS, I GRABBED ONTO THE RIGHT SIDE WING TIP TANK AND GAVE THE AIRCRAFT A SHAKE IN AN EFFORT TO SETTLE THE OLEO STRUTS. IN DOING SO I NOTICED AN OBVIOUS MOVEMENT BETWEEN THE TIP TANK AND WING STRUCTURE. I REMOVED THE FAIRINGS WHICH COVER THE MOUNTING POINTS FOR THE TIP TANK AND THEN GAVE IT ANOTHER SHAKE. AT THIS POINT IT WAS OBVIOUS THAT THE TIP TANK MOUNTING BOLTS WERE LOOSE. TO BE MORE SPECIFIC, THE TIP TANK IS HELD INTO PLACE BY 6 BOLTS. ONE 4/16 INCH BOLT AT THE FORWARD END, ONE 4/16 INCH BOLT AT THE AFT END AND FOUR 3/16 INCH BOLTS IN THE CENTER WHICH ATTACH TWO (APPROX 4 INCH SQUARE) MOUNTING PLATES. THE MOVEMENT WAS NOTED AS BEING BETWEEN THESE TWO PLATES IN THE CENTER. REMOVED ONE OF THE CENTER BOLTS TO INSPECT FOR WEAR IN THE BOLT HOLE, NO ELONGATION WAS NOTED, AND THE BOLTS WAS RE-INSTALLED. THE SURROUNDING STRUCTURE, BOTH ON THE WING AND ON THE TIP TANK, WAS INSPECTED WITH NO FAULTS FOUND. ALL OF THE MOUNTING BOLTS WERE TORQUED AS PER THE MANUFACTURERS MAINTENANCE MANUAL AND THE FAIRING WAS RE-INSTALLED. I INSPECTED THE LEFT WING TIP TANK AND THERE WAS NO MOVEMENT FOUND. REMOVED THE FAIRING AND TORQUE CHECKED ALL OF THE MOUNTING BOLTS, ALL OF THE CENTRE (FOUR) BOLTS WERE FOUND TO BE UNDER TORQUED, BUT THE FORWARD AND AFT BOLTS WERE TIGHT. I TORQUED THE CENTER BOLTS AND RE-INSTALLED THE FAIRINGS. WE HAVE SCHEDULED A 50 HOUR INSPECTION INTERVAL ON THESE MOUNTING BOLTS AND WILL RE-EVALUATE THE INTERVAL AS TIME GOES ON.

CA090128003

PIPER

PWA  

 

TUBE

PUNCTURED

1/23/2009

PA31T2

PT6A135

 

XA1AK

MLG TIRE

TIRE WAS REPORTED FLAT UPON PRE-FLIGHT INSPECTION. TIRE AND TUBE WERE INSPECTED AND THE TUBE REVEALED A PUNCTURE, CAUSING THE DEFLATION.

CA090202005

PIPER

PWA  

 

TUBE

PUNCTURED

1/23/2009

PA31T2

PT6A135

 

XA1AK

TIRE 

THE LT MAIN TIRE WAS REPORTED LOW BY OUR MAINTENANCE CREW. MAINTENANCE PERSONNEL IMMEDIATELY REPLACED THE WHEEL ASSY AS PREVENTATIVE MAINTENANCE, SINCE 3 TIRE FAILURE INCIDENTS OCCURRED THIS PAST MONTH. THE TIRE AND TUBE WERE INSPECTED AND THE TUBE REVEALED A PUNCTURE MARK, CAUSING A SLOW DEFLATION.

CA090128001

PIPER

PWA  

 

TUBE

PUNCTURED

1/16/2009

PA31T2

PT6A135

0763561

XA1AK

OUTR CIRCMFERNCE

TIRE LOSING AIR AFTER SHUTDOWN. THE TIRE AND TUBE WERE INSPECTED AND NUMEROUS PIN HOLES WERE FOUND ON THE TUBE`S OUTER CIRCUMFERENCE, CAUSING THE DEFLATION.

CA090128002

PIPER

PWA  

 

TUBE

DESTROYED

1/17/2009

PA31T2

PT6A135

0763561

XA1AK

 

THE TIRE WAS DESTROYED ON TOUCHDOWN. UNABLE TO EVALUATE TIRE AND TUBE CONDITION.

2009FA0000253

PIPER

 

 

LINE

CHAFED

3/19/2009

PA34220T

 

 

83744139

HYD PWR PACK

WHILE COMING IN FOR A LANDING, CUSTOMER WENT TO EXTEND LANDING GEAR AND GEAR WOULD NOT EXTEND. USED EMERGENCY GEAR EXTENSION AND LANDED ACFT WITH NO INCIDENT. UPON TROUBLESHOOTING FOUND RETRACTION LINE FROM HYD POWER PACK CHAFED THROUGH. HYDRAULIC LINE WAS CHAFING ON NOSE WHEEL WELL COVER INSIDE FWD BAGGAGE COMPARTMENT. REMOVED AND REPLACED LINE ASSY WITH LOCALLY MFG LINE ASSY AND REPOSITIONED TO PREVENT FURTHER CHAFING ON WHEEL WELL COVER. OPS AND LEAK CHECKED SATISFACTORY. (K)

2009FA0000236

PIPER

 

 

TUBE

FAILED

3/1/2009

PA38112

 

 

500X5

MLG TIRE

IN LAST 6 TO 8 MONTHS, FLEET HAS HAD CRONIC PROBLEMS WITH TUBE FAILURES ON MAIN GEAR ONLY. INVESTIGATION SHOWS NO DAMAGE TO THE CORRESPONDING AREA OF THE TIRE INSIDE OR OUT. THE RUPTURE ON THE TUBES HAS BEEN VERY CONSISTENT. ALWAYS MAIN GEAR, ALWAYS O THE INBD SIDEOF THE TUBE, ALWAYS IN THE AREA WHERE THE TREAD OF THE TIRE TRANSITIONS INTO THE SIDEWALL AND ALWAYS A VERY SMALL SLIT OR PUNCTURE. HAVE EXAMINED INSTALLATION TECHNIQUES , INFLATION PRESSURES, AND LANDING TECHNIQUES AND DO NOT SUSPECT ANY OF THESE BEING THE CAUSE. HAVE BEEN IN CONTACT WITH MFG, THEY HAVE PROVIDED US WITH SOME TUBES MADE WITH A NEW COMPOUND WHICH HAVE FAILED ALSO. (K)

CA090123005

PIPER

LYC  

 

BRACKET

LOOSE

1/22/2009

PA44180

LO360A1H6

 

 

THROTTLE

(CAN) INSP REVEALED THAT THE THROTTLE BRACKET WHICH IS RIVETED TO THE TOP OF THE CARB HEAT BOX WITH BLIND RIVETS HAD WORKED LOOSE AND WAS ALLOWING MIS-ALIGNMENT OF THE THROTTLE CONTROL CABLE AND CAUSING THE THROTTLE TO STICK.

2009FA0000087

QUARTZ

CONT

 

BREATHER TUBE

LEAKING

1/17/2009

11E  

IO360ES

 

 

OIL SYSTEM

AFTER A GROUND RUN UP, THE PILOT HAS NOTICED LARGE AMOUNTS OF OIL UNDER THE ACFT ON THE RAMP. FINDINGS WERE THAT THE OIL HAD COME OUT OF THE ENGINE BREATHER TUBE. UPON FURTHER INVESTIGATION, FOUND THAT THE BREATHER LINE WAS ROUTED SO THAT THERE WAS A "TRAP" IN THE LINE COLLECTING WATER AND FREEZING CAUSING THE CRANKCASE TO PRESSURIZE AND BLOW THE OIL OVERBOARD.

2009FA0000084

QUARTZ

CONT

 

ROD END

LACK OF LUBE

1/16/2009

11E  

IO360ES

 

 

ZONE 500

INSTRUCTOR NOTED ON A PREFLIGHT THAT THE LT AILERON WAS EMITTING A SQUEAKING SOUND . FOUND THAT IT WAS DUE TO A LACK OF LUBRICATION OF THE AILERON ROD END BEARING . NOTING THIS, DUE TO A EARLIER INSTANCE OF ANOTHER SN SAME TYPE ACFT THAT A STIFF AILERON CONTROL IN FLIGHT DUE TO SAME REASONS. LUBRICATION REMEDIED THIS PROBLEM.

2009FA0000086

QUARTZ

CONT

 

LINE

MISROUTED

1/10/2009

11E  

IO360ES

 

 

OIL BREATHER

AFTER A GROUND RUN UP, THE PILOT HAS NOTICED LARGE AMOUNTS OF OIL UNDER THE ACFT ON THE RAMP. FINDINGS WERE THAT THE OIL HAD COME OUT OF THE ENGINE BREATHER TUBE. UPON FURTHER INVESTIGATION, FOUND THAT THE BREATHER LINE WAS ROUTED SO THAT THERE WAS A "TRAP" IN THE LINE, COLLECTING WATER AND FREEZING CAUSING THE CRANKCASE TO PRESSURIZE AND BLOW THE OIL OVERBOARD.

CA090130010

RAYTHN

PWA  

 

TURBINE BLADES

DAMAGED

1/22/2009

400ARAYTHEON

JT15D5

 

 

ENGINE

DURING TAKEOFF ROLL, THE ENGINE ELECTRONIC CONTROL WENT OFF LINE AND THE CREW ABORTED THE TAKEOFF AFTER RETURNING TO THE RAMP, INSPECTION OF THE ENGINE SHOWED POWER TURBINE BLADE DAMAGE. THE ENGINE WILL BE REMOVED AND FORWARDED FOR INVESTIGATION AND REPAIR. P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.

CA090128004

RAYTHN

PWA  

 

RIVET

SHEARED

1/28/2009

B300RAYTHEON

PT6A60A

 

2117T4

ATTACH BRACKET

DURING A PHASE 1A INSPECTION, THE PROPELLER CONTROL BRACKET LOCATED UNDER THE CENTER PEDESTAL WAS FOUND TO HAVE 2 SHEARED OFF RIVETS. IN LIEU OF RIVETS IT WAS FOUND THAT 2 C-CLAMPS WERE HOLDING THIS BRACKET IN PLACE. WHAT IS IMPORTANT TO NOTE IS THAT THIS WAS THE FIRST PHASE INSPECTION DONE AT THIS FACILITY. PRIOR TO THIS THE AIRCRAFT UNDERWENT A FULL PHASE 1 TO 4 INSPECTION AT A BEECHCRAFT REPAIR STATION IMMEDIATELY BEFORE BEING IMPORTED. PLEASE SEE ATTACHED PICTURES AND DOCUMENTS.

CA090302004

RAYTHN

PWA  

 

FUEL CONTROL

FAILED

2/27/2009

B300RAYTHEON

PT6A60A

 

8061330

ENGINE

AIRCRAFT WAS IN CRUISE AT FL210. FIRST OFFICER ATTEMPTED TO ADJUST THE RT POWER LEVER TO BRING THE TORQUE UP TO MATCH THE LT ENGINE. FOUND THE POWER LEVER ALREADY AT THE STOP. CREW THEN NOTICED A GRADUAL LOSS OF POWER (TORQUE, FUEL FLOW AND ITT) TO ABOUT 50 PERCENT TORQUE. THEY DEPLOYED THE ICE DOORS TO TROUBLESHOOT, AND AFTER SOME TIME, THE POWER RECOVERED TO 90 PERCENT. AFTER ABOUT 5 MINUTES, THE POWER BEGAN DECAYING AGAIN. AT 40 PERCENT TORQUE THE CAPTAIN INSTRUCTED THE F/O TO PREPARE FOR AN ENGINE FAILURE. AT APPROX 20 PERCENT TORQUE THE PROP AUTO-FEATHERED AND THE CREW SECURED THE ENGINE. AN UNEVENTFUL LANDING WAS MADE. MAINTENANCE TROUBLESHOT AND FOUND THE MAX FUEL FLOW AVAILABLE WAS APPROX 100 LB/HOUR, NOT ENOUGH TO EVEN GET THE ENGINE STARTED. THE FUEL CONTROL WAS REPLACED AND THE ENGINE GROUND RUN SERVICEABLE. PART IS BEING SENT TO STANDARD AERO FOR REPAIR. WILL ADVISE FURTHER DETAILS WHEN THEY BECOME AVAILABLE.

2009FA0000221

RAYTHN

 

 

WINDOW

CRACKED

2/16/2009

HAWKER750

 

 

258FN35343A

COCKPIT

PILOTS DV WINDOW CRACKED IN FLIGHT DURING CLIMB. FLIGHT WAS ABORTED AND RETURNED TO DEPARTURE. (K)

2009FA0000222

RAYTHN

 

 

WINDOW

CRACKED

2/23/2009

HAWKER750

 

 

258FN35344A

COCKPIT

CO-PILOTS DV WINDOW CRACKED DURING FLIGHT, FLIGHT WAS ABORTED AND RETURNED TO DEPARTURE. (K)

CA090116014

ROBSIN

LYC  

 

ATTACH BRACKET

CRACKED

1/15/2009

R44  

O540F1B5

 

C8303

ELT 

DUE TO PAST ISSUES WITH ELT`S GOING OFF, THE ELT`S WERE FOUND TO BE AT THE INCORRECT CLOCK ANGLE. THE ELT WAS REPOSITIONED TO THE PROPER ANGLE, WHICH WE THINK MAY HAVE CAUSED THE CRACKING OVER TIME. A SMALL CRACK WAS FOUND IN THE BOTTOM ANGLE BRACKET RADIATING FROM THE MIDDLE SCREW HOLE. THE ELT`S ARE NOW BEING REPLACED WITH THE KANNAD 406 ELT WHICH IS SUPPORTED DIFFERENTLY.

CA090117001

ROBSIN

LYC  

WELDON

PUMP

FAILED

1/15/2009

R44RAVENII

IO540AE1A5

C8187B

119066

 

AUX FUEL PUMP FAILURE WITHIN 5.5 HOURS AFTER UNIT INSTALLED. THIS PUMP WAS ORIGINALLY REPAIRED FOR LOW PRESSURE OUTPUT AND HAS AGAIN FAILED TO PRODUCE PRESSURE. POSSIBLE QUALITY CONTROL ISSUE FROM OVERHAUL/REPAIR SHOP.

CA090210006

ROBSIN

LYC  

 

CLUTCH

SLIPPED

1/30/2009

R44RAVENII

IO540AE1A5

 

C0183

MAIN ROTOR

DURING FLIGHT A LOUD BANG WAS HEARD BY THE CREW. THEY RETURNED TO BASE AND MAINTENANCE NOTIFIED. CLUTCH WAS INSPECTED AND REPLACED DUE TO SLIPPAGE.

CA081223006

ROBSIN

LYC  

 

HOUSING

CRACKED

12/4/2008

R44RAVENII

IO540AE1A5

 

14924HT

STARTER GEN

(CAN) STARTER HSG FOUND CRACKED.

CA090121008

ROBSIN

LYC  

 

STARTER GEN

INOPERATIVE

12/21/2008

R44RAVENII

IO540AE1A5

 

H4M440507

ENGINE

STARTER WOULD NOT ENGAGE. STARTER WAS REPLACED AND NO FURTHER ISSUES WERE NOTED.

CA090121009

ROBSIN

LYC  

 

PUMP

UNSERVICEABLE

1/6/2009

R44RAVENII

IO540AE1A5

 

118241

AUX FUEL

DURING START-UP, THE AIRCRAFT FAILED TO START. AUX FUEL PUMP WAS FOUND TO BE UNSERVICEABLE. PUMP WAS REPLACED AND NO FURTHER ISSUES WERE NOTED.

CA090121010

ROBSIN

LYC  

 

PUMP

NOISY

12/21/2008

R44RAVENII

IO540AE1A5

 

118287

AUX FUEL

DURING SHUT DOWN A ROUGH SOUNDING NOISE SEEMED TO BE COMING FROM THE AUX FUEL PUMP. MAINTENANCE INVESTIGATED THE INCIDENT AND PUMP WAS REPLACED. NO FURTHER ISSUES WERE NOTED.

CA090121011

ROBSIN

LYC  

 

SERVO

LEAKING

12/21/2008

R44RAVENII

IO540AE1A5

 

D2121

 

DURING THE REPLACEMENT OF THE AUX FUEL PUMP, IT WAS NOTED THAT THE SERVO LEAKING. SERVO WAS REPLACED AND NO FURTHER ISSUES WERE NOTED.

CA090109007

ROBSIN

LYC  

 

HOUSING

CRACKED

12/20/2008

R44RAVENII

IO540AE1A5

 

F4M460701

STARTER GEN

CRACK FOUND ON THE BENDIX HOUSING.

CA090130013

ROBSIN

LYC  

 

PUMP

FAILED

1/15/2009

R44RAVENII

IO540AE1A5

 

C8181B

FUEL BOOST

DURING ENGINE START, AUX FUEL PRESSURE LIGHT ILLUMINATED. PUMP WAS REPLACED AND NO FURTHER ISSUES WERE NOTED.

CA090130014

ROBSIN

LYC  

 

PUMP

FAILED

1/10/2009

R44RAVENII

IO540AE1A5

 

C8187B

FUEL BOOST

DURING DI, IT WAS NOTED THAT THE AIRCRAFT AUX FUEL PUMP FAILED. PUMP WAS REPLACED AND NO FURTHER ISSUES WERE NOTED.

CA090128005

ROBSIN

LYC  

 

BEARING

WORN

1/28/2009

R44RAVENII

IO540AE1A5

 

22021081806

MAGNETO

MAG WAS RECEIVED FOR AN OVERSPEED INSPECTION (500 HOUR INSPECTION PROCEDURE). BEFORE DISASSEMBLY THE BEARINGS WERE INSPECTED BY TURNING THE ROTATING MAGNET ASSEMBLY. SIDE PLAY WAS NOTED AND THE END PLAY WAS MEASURED AT 0.004 INCH. TCM DOES NOT ALLOW SIDE PLAY AND ONLY ALLOWS 0.0005 TO 0.0015 END PLAY. THE MAG WAS DISASSEMBLED AND THE BEARINGS WERE INSPECTED AND FOUND SERVICEABLE. THE 500 HOUR INSPECTION WAS CARRIED OUT WITH THE BEARINGS SHIMMED TO THE PROPER PRELOAD AND THE MAG WAS RETURNED TO SERVICE. THIS MAG WAS A FACTORY NEW UNIT WITH 412.7 HOURS IN SERVICE.

CA090127002

ROBSIN

LYC  

 

LINE

CHAFED

1/21/2009

R44RAVENII

IO540AE1A5

 

C7411

FUEL SYSTEM

DURING A VISUAL INSPECTION ON A 100 HR, THE MAIN FUEL FEED LINE WAS FOUND SMOKING THOUGH THE AFT FIRE WALL. UPON FURTHER INSPECTION OF FUEL LINE THE SMALL GROMMET/BUSHING WAS FOUND WORN THROUGH CAUSING THE FIRE WALL SUPPORT TO CHAFE INTO THE LINE. THE LINE WAS REMOVED FROM SERVICE AND REPLACED NEW.

CA090116013

ROBSIN

LYC  

 

BRACKET

CRACKED

1/15/2009

R44RAVENII

IO540AE1A5

 

C8303

ELT MOUNT

DUE TO PAST ISSUES WITH ELT`S GOING OFF, THE ELT`S WERE FOUND TO BE AT THE INCORRECT CLOCK ANGLE. THE ELT WAS REPOSITIONED TO THE PROPER ANGLE, WHICH WE THINK MAY HAVE CAUSED THE CRACK OVERTIME. A SMALL CRACK WAS FOUND IN THE BOTTOM ANGLE BRACKET RADIATING FROM THE MIDDLE SCREW HOLE. THE ELT`S ARE NOW BEING REPLACED WITH THE KANNAD 406 ELT WHICH IS SUPPORT DIFFERENTLY.

MALA090025

SAAB

 

 

POWER SUPPLY

INOPERATIVE

2/24/2009

340B

 

 

330151

CABIN

EMERGENCY LIGHT AT SEAT 8A INOP. REMOVED AND REPLACED LIGHT ASSY PN 2LA005115-20 AT COVE 8A IAW AMM 33-50-55. ALSO FOUND POWER SUPPLY 24LN BAD. REMOVED AND REPLACED POWER SUPPLY PN 3301-51, SN ON 1096, S/N OFF 2023. ALL WORK DONE IAW AMM 33-50-10. OPS CHECK GOOD.

2009FA0000235

SCHLER

 

 

SLIP JOINT

CORRODED

3/1/2009

ASK21

 

 

 

CONTROL STICK

CORROSION WAS FOUND AT THE JUNCTION OF THE UPPER AND LOWER BODY OF THE FRONT SEAT CONTROL STICK ASSY. THE UPPER STICK HALF SLIDES INTO THE LOWER STICK HALF AND IS THEN HELD TOGETHER WITH A SINGLE THROUGH BOLT. THE CORROSION WAS DETECTED PROTRUDING FROM THE TOP OF THE JOINT WHERE THE UPPER PIECE SLIDES INTO THE LOWER PIECE OF THE ASSY. THE EXTENT OF THE CORROSION COULD NOT BE DETERMINED WITHOUT REMOVEING AND DISASSEMBLING THE STICK. CORROSION WAS SEVERE ENOUGH THAT SEPARATION OF THE (2) STICK PARTS WAS ACHIEVED ONLY AFTER APPLICATION OF HIGH HEAT FROM A TORCH. THE PROBABLE CAUSE IS PERSPIRATION FROM THE PILOT`S HAND DRIPPING DOWN THE STICK TO WHERE THE PARTS ARE MATED. CORROSION EASILY DEVELOPS WHEN THE MOISTURE CONTACTS THE BARE METAL IN THE JOINT. WHAT IS DISTRUBING IS THAT THE ACFT HAS ONLY BEEN IN SERVICE FOR LESS THAN 2 YEARS SINCE NEW. MFG SHOULD HAVE PROVIDED BETTER CORROSION PREVENTION OR DESIGN. SHOULD CORROSION BE ALLOWED TO CONTINUE, THAT THE CONTROL STICK WILL ULTIMATELY FAIL. INSP OF (2) OTHER ACFT OF THE SAME MAKE, MODEL AND IN-SERVICE TIME REVEALED SIMILAR CONDITIONS. (K)

CA090206009

SKRSKY

ALLSN

 

TRANSMISSION

MAKING METAL

1/29/2009

S76A

250C30S

 

7635109500044

MAIN ROTOR

METAL CONTAMINATION, CHIP LIGHT.

CA090127011

SNIAS

 

 

BRACKET

CRACKED

1/23/2009

AS350B

 

 

417157001

ENG FUEL FILTER

ENGINE HIGH PRESSURE FUEL FILTER BRACKET, TOP HOLE CRACKING DUE TO HARMONIC VIBRATION, KNOWN PROBLEM.

CA090127012

SNIAS

LYC  

HONEYWELL

BRACKET

CRACKED

1/21/2009

AS350B

LTS101*

LTS101700D

417157001

TOP BOLT HOLE

ENGINE HIGH PRESSURE FUEL FILTER BRACKET, CRACKING AT TOP BOLT HOLE DUE TO HARMONIC VIBRATION, KNOWN PROBLEM.

CA090127010

SNIAS

LYC  

HONEYWELL

BRACKET

CRACKED

11/26/2008

AS350B2

LTS101750C1

 

417157001

TOP BOLT HOLE

HIGH PRESSURE ENGINE FUEL FILTER BRACKET CRACKING AT TOP BOLT HOLE DUE TO HARMONIC VIBRATION, KNOWN PROBLEM.

CA090223013

SNIAS

TMECA

 

FRICTION RING

FAILED

1/12/2009

AS350B3

ARRIEL2B

 

 

STARTER GEN

PRIOR TO INSTALLING STARTER GEN SB 80.00.07 PARA 2B2B AND 2B3 WERE APPLIED. THE STARTER WAS THEN INSTALLED AS PER MM AND A GROUND RUN WAS DONE. DURING THE GROUND RUN NO VIBRATION WAS NOTED ON THE STARTER, VOLTAGE AND AMPERAGE WAS NORMAL. I NOTICED A BURNING ODOR SIMILAR TO WHEN THE ROTOR BRAKE WAS APPLIED AND SAW PARTS OF THE FRICTION RING OF THE DAMPER ASSY ON THE ENGINE DECK AGAIN NO ABNORMAL VIBRATION WAS NOTED ON THE STARTER. THE PILOT SHUT DOWN THE ENGINE. REINSTALLED THE OLD STARTER, STILL HAD TIME LEFT TO OH. UPON CLOSER INSPECTION IT WAS NOTED THAT THE FRICTION RING WAS COMPLETELY BROKEN UP. IT WAS SENT BACK TO APC FOR FURTHER INVESTIGATION.

CA090127009

SNIAS

 

 

BRACKET

CRACKED

9/5/2008

AS350BA

 

 

417157001

FUEL FILTER

ENGINE FUEL FILTER BRACKET CRACKING DUE TO HARMONIC VIBRATION.

2009FA0000237

SWRNGN

GARRTT

 

IMPELLER

DAMAGED

12/2/2008

SA227AC

TPE331*

 

 

RT ENGINE

DURING TAKEOFF (ASCENT), ACFT SUFFERED A BIRD STRIKE IN THE RT ENGINE. THE PILOT VERIFIED HIS PARAMETERS AND THEY DID NOT HAVE ANY VIBRATION. HOWEVER, HE SMELLED BURNED BIRD AND DECIDED TO RETURN TO DEPARTURE AIRPORT. DURING THE WALK AROUND INSP, THE PILOT EVIDENCE DAMAGES IN THE RT ENGINE FOR BIRD INGESTION (FIRST IMPELLER DAMAGE). THE ENGINE WAS TO BE SENT TO REPAIR STATION. (K)

CA090202003

SWRNGN

GARRTT

 

WINDSHIELD

CRACKED

2/1/2009

SA227AC

TPE33111U

 

2719442004

COCKPIT

IN CRUISE AT FL230 SOUTHBOUND, A LOUD BANG HEARD BY BOTH CREW AND SAW F/O SIDE WINDSHIELD SHATTER, BUT REMAINED INTACT. NO LOSS OF PRESSURIZATION. FLIGHT DESCENDED TO FL100 AND CREW INFORMED ATC BUT DID NOT DECLARE AN EMERGENCY. LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE IS IN PROCESS OF REPLACING THE WINDSHIELD. BONDING CHECKS WERE PERFORMED ON THE WINDOW PRIOR TO REMOVAL AND WERE FOUND WITHIN ACCEPTABLE RESISTANCE LIMITS IN ACCORDANCE WITH M7 AEROSPACE SB 227-56-010 WHICH WAS ISSUED TO HELP ELIMINATE THIS TYPE OF FAILURE.

CA081218002

UROCOP

TMECA

 

ROTOR HEAD

DAMAGED

12/16/2008

EC120B

ARRIU2F

 

 

MAIN ROTOR

(CAN) DURING PREFLIGHT INSP ON NEWLY DELIVERED ACFT, DISCOVERED A .5 INCH COUNTERSINK RESTING UNDER ACFT TRANSMISSION. NO DAMAGE WAS FOUND BUT THE TOOL IS LARGE ENOUGH TO HAVE CAUSED FLIGHT CONTROL INTERFERENCE OR TO HAVE CONTACTED THE ROTOR BRAKE DISK. TOOL WAS REMOVED. NO FURTHER ACTION TAKEN.

2009FA0000209

UROCOP

TMECA

 

STARTER GEN

WORN

3/10/2009

EC120B

ARRIUS2F

 

160SG140Q

ENGINE

GROWLING OR LOUD HOWLING NOISE COMING FROM ENGINE AREA FLUCTUATING WITH POWER CHANGES. VIBRATION TRANSMITTING THROUGH ACFT.