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

379

bald eagle watching over three eggs

FEBRUARY

2010

 


CONTENTS

AIRPLANES

BOEING...................................................................................................................................... 1

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

CONVAIR................................................................................................................................. 16

DIAMOND................................................................................................................................ 18

EMBRAER................................................................................................................................. 19

PILATUS................................................................................................................................... 22

ROCKWELL............................................................................................................................. 23

POWERPLANTS

LYCOMING.............................................................................................................................. 26

AIR NOTES

INTERNET SERVICE DIFFICULTY REPORTING (iSDR) WEB SITE................................... 27

IF YOU WANT TO CONTACT US......................................................................................... 28

AVIATION SERVICE DIFFICULTY REPORTS...................................................................... 28

 


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

AVIATION MAINTENANCE ALERTS

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

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

 

AIRPLANES

Boeing:  A75N1; Broken Engine Mount Bolts; ATA 7120

A mechanic states, "During inspection of the engine installation on this aircraft, it was determined that one of the four high strength NAS-148 bolts that hold the engine mount to the fuselage was fractured completely through -- under the head of the bolt.  This bolt has 100 hours total time in service.  After informing the STC (supplemental type certificate) holder of the failure, we were informed we should have re-torqued these bolts after 25 hours of operation.  This information was not included in the STC.  According to the STC holder (this data) was referenced in the original aircraft maintenance manual where it states the original engine mount 'studs' should be re-torqued to 450 to 500 inch-pounds after the first 25 hours.  These original engine mount studs are not installed in the STC aircraft as they have been removed, and the entire assembly was replaced with a different mount and hardware assembly.  The replacement bolts are NAS 148 (internal wrenching) and are oversize from the original studs.  The original (maintenance) manual torque values would not be sufficient, and no further instructions (were) given.

"These bolts are hidden and it would require the removal of the engine to re-torque them.  We believe a critical safety issue exists, as the failure of these bolts will result in a catastrophic (accident).  (See accident report CA18/2/3/8321  where the failure of an identical bolt in a similar STC caused the separation of the engine and a fatality accident.)  (This) STC is inadequate in its description for maintenance to ensure continued airworthiness."


 

PHOTO OF FORWARD FUSELAGE, ENGINE MOUNT, AND ENGINE.


 

CLOSEUP VIEW OF BROKEN BOLT.

 

(That is a dramatic shot!  Thanks for the photo effort—Ed.)

Part Total Time:  100.0 hours

 

Cessna:  170B; Failed Tail Wheel Assembly; ATA 3220

"During an annual inspection, it was noted that the tail wheel could not be steered," says this mechanic.  "The tail wheel had been painted in the past (as) the top grease fitting was completely (covered).  The aircraft owner stated (a previous mechanic) who had worked on the aircraft in the past told him not to grease the tail wheel, and to tighten the nut on the bottom of the steering bolt as tight as possible.  Disassembly revealed all parts inside the tail wheel unit were extremely worn.  The pins that should have been attached to the thrust plate were missing.  Additionally, the axle for the tail wheel had been damaged previously, and the end of the axle was partially ground off—(extending)  through the hole for the cotter pin (used) to secure the nut on the end of the axle.  The entire tail wheel was beyond repair and was replaced with a serviceable (unit)."  (Part name and number:  Scott 3200.)


FULL PAGE OF NIN CLOSEUP VIEWS OF THE THRUST WASHER, BELL CRANK, AND AXLE BOLT.


FULL PAGE OF NIN CLOSEUP VIEWS SHOWING VARIOUS INTERNAL WHEEL PARTS.


 

FULL PAGE OF FIVE CLOSEUP VIEWS SHOWING VARIOUS INTERNAL WHEEL PARTS.

Part Total Time:  (unknown)

 

Cessna:  182S; Cracked Battery Mount Structure; ATA 2571

An unidentified mechanic writes, "During an annual inspection, both aircraft battery-shelf support brackets were found cracked in their forward and aft ends (four cracks total).  Each crack started at the end of the support in the 90-degree bend radius, propagating toward the center of (the part).  Cracks (measure) from 0.25 to 0.75 inches long.  This is the fourth 182S/T model we have found to be cracked in this manner, (each requiring) replacement supports (P/N 0712059-1).  One previously repaired aircraft has already cracked the replacement parts, requiring yet another set to be installed.  These support brackets are not (sufficiently) thick to withstand both the weight of the 24V battery and normal airframe vibration.  (I) recommend close (observation) at every annual and 100-hour inspection with a small mirror.  The area in question is not readily visible.  I recommend the manufacturer improve the design (by using) thicker supports—and offer (this new) design as replacement parts."


 

PHOTO OF THE BATTERY AND ITS MOUNT STRUCTURE IN THE AIRCRAFT.


 

CLOSEUP OF THE CRACKED SUPPORT; END VIEW 1.


 

CLOSEUP OF THE CRACKED SUPPORT; BOTTOM VIEW.


 

CLOSEUP OF THE CRACKED SUPPORT; END VIEW 2.

 

(While you are waiting for the "new & improved" thicker metal, I see two issues that will buy you a lot more time.  In the second and third pictures both the inside and outside edges of the part's radius are clearly sharp and ragged—as are almost all factory produced parts.  Five bucks argues you will never replace another set if you would feather both inside and outside radius edges of new parts with 220-grit paper, then polish the same with Scotch-Brite until glass smooth—takes 2 minutes per end, plus recoating.  In picture four, the washer impression can be seen encroaching into the radius—the telltale edge "gleam" is very apparent in the bottom view.  Under torque, that washer's edge is not only cutting/chafing a stressed area of the metal, but may also be transferring load into the radius if not sitting perfectly flat.  Consider chamfering the edge of that washer if it is even close, and/or flipping the sharp edge of the washer to face the nut during installation.  If they still crack, scream at Cessna and come beat lunch out of me—Ed.)

 


Cessna: Corvalis Models (see list); Failed Empennage Structure; ATA 5500

(The Wichita Certification Office provides the following safety article referencing Cessna Corvalis model aircraft, including:  300 [LC40-550FG], 350 [LC42-550FG], and 400 [LC41-550FG], all serial numbers. Contact information follows the discussion.)

"The FAA has four reports dating back to 2006 of structural damage being sustained to the empennage after extreme braking (see tire skid marks in first photograph below).  The second and third photos indicate the range of observed structural damage.  Extensive damage in the second photo is obvious—this failure opens up the structure.  Another failure example is shown in the last picture.  De-bonding of the composite fuselage can be seen just forward of the horizontal stabilizer (see arrows).  Although this failure does not open up the structure, the damage is quite apparent.

"These extreme braking maneuvers consist of prolonged periods of heavy braking and tire skidding, resulting in large oscillatory motions known as gear walk.  These conditions can be avoided by operating the airplane in accordance with the applicable POH (Pilot's Operating Handbook).

"Cessna is proposing a Service Newsletter that communicates important safety information about the proper use of brakes as noted in the POH.  Additionally, this Newsletter will provide notification that TRs (Temporary Revisions) to the POH and the Airplane Maintenance Manuals are available and should be inserted into the appropriate manual upon receipt."

 

PROFILE DRAWING OF THIS AIRCRAFT.


 

PHOTO OF SKID MARKS ON RUNWAY.


 

PHOTO OF CRACKED EMPENNAGE STRUCTURE.


 

PHOTO OF DAMAGED EMPENNAGE STRUCTURE ON DIFFERENT AIRPLANE.


(For further information contact Aerospace Engineer Gary Park;  Wichita Aircraft Certification Office, 1801 Airport Road, Room 100;  Wichita, Kansas; 67209; phone:  316-946-4123)

Part Total Time:  (n/a)

 


Convair:  340/440 (580); Fuel Cross-feed Advisory; ATA (N/A)

(Transport Canada provides the following admonition.)

 

TRANSPORT CANADA SERVICE DIFFICULTY ADVISORY.


 

TRANSPORT CANADA SERVICE DIFFICULTY ADVISORY.


 

TRANSPORT CANADA SERVICE DIFFICULTY ADVISORY.

 

Part Total Time:  (N/A)

 

Diamond:  DA40; Failed Alternate Air Control Valve; ATA 7160

"We maintain a fleet of 20 Diamond DA-40 aircraft...", writes the submitter.  "All aircraft arrived a year ago straight from the Diamond factory with 10 hours average total time since new (TTSN).  (This defect first appeared...) after 147 hours (time accumulation) and was found during scheduled maintenance.  Mechanics are finding the alternate air valve body control cable (P/N DAI-9076-00-04) loose or completely disconnected and hanging next to the primary/alternate air valve body (P/N D41-7166-20-30).  When they try to reinstall the cable they are finding the threads are stripped out on the alternate air valve body.  This problem has now occurred on 14 different aircraft in our fleet—all between 147 and 350 hours TTSN.  My concern is an operator of the aircraft may not know if the engine is getting filtered or unfiltered air if the cable has become disconnected.  (I suggest) the manufacturer make the valve body thicker (more threads), install a steel Helicoil, or maybe spot-weld a nut on the outside of the valve body."  (The airplane sports a Lycoming IO-360 up front.)


 

CLOSEUP OF THE VALVE HOUSING AND ITS STRIPPED CABLE MOUNT HOLE.

 

 

Embraer:  EMB-135BJ; Cracked O2 Gage Fitting; ATA 3500

A repair station quality engineer writes, "During routine maintenance (I) investigated a 'low oxygen contents' indication for the passenger and crew systems.  A gas leak was identified behind the oxygen-charging panel at station 3900 (R/H) while attempting to charge the system.  Upon removing the ground charging panel assembly, cracks were discovered on two brass fittings (P/N 500189)—part of the gage assembly (P/N 171013) common to both passenger and crew systems.  Oxygen leaks were apparent at these fittings. (Reference IPC 35-11-00 item 1; panel assembly P/N 135-05153-401 item 150; pressure gage P/N 171013 item 50; Capillary Tube item 155; Brass Oxygen fitting P/N 500189).

"Replacement items were ordered from the manufacturer (Embraer) for defect (resolution).  Upon receipt (of a new) replacement gage assembly (P/N 171013), an identical crack was found on fitting (P/N 500189)—the gage was rejected."  "The cause of cracking can not be positively (identified), but it may be due to over-torquing of the fittings to the gage."


 

EXPLODED DRAWING OF THE OXYGEN PANEL ASSEMBLY.


CLOSEUP OF THE CRACKED FITTING; VIEW 1.

CLOSEUP OF THE CRACKED FITTING; VIEW 2.

Part Total Time:  908.0 hours

 


Pilatus:  PC-12-47; Flap Drive Arm Assembly Cracked; ATA 2750

A technician for a repair station states, "(The pilots received a flap warning light...) on rollout after landing.  (I) checked the (CAS: Crew Alert System's) flap errors and found several E211 codes.  I then inspected the left inner resolver installation and found its drive pin pulled from the socket.  Further inspection found the inboard, L/H flap drive arm assembly (P/N 527-52-12-153) cracked in several places.  The cause is unknown.  There are no recorded over-speeds on the CAS system and no signs of impact side loads.  Rigging of the flaps checked okay—no further damage was found."

PHOTO OF THE FLAP DRIVE ARM.

 

CLOSEUP OF THE VIEW OF CRACK.

 

Part Total Time:  330.0 hours

 


Rockwell:  NA265-65; Cracked Fuselage Skin; ATA 5330

(This very short discrepancy report finds a very short crack—but note:  this seemingly sparse story continues into the next report—Ed.)

A repair station submission says, "The fuselage skin (was found) cracked at the lower aft corner of the left, over-wing escape hatch opening."

 

CRACKED SKIN; VIEW 1.


 

CRACKED SKIN; CLOSEUP VIEW.

 

(Cracked skin:  P/N 30631201621; location:  fuselage station 262.  Okay—the tiny crack self-terminates into the rivet hole, but the pressure vessel business is going to require a little engineering/manufacturer guidance.  Guess we are done, right?  See the next entry....)

Part Total Time:  8,000.0 hours at 5,980 cycles

 

Rockwell:  NA265-65; Cracked Fuselage Side Frame; ATA 5311

(Our intrepid inspector from the previous report is still short on words, but very long in the eyeball department.  Now we go inside the airplane—hunting for connections....)

Our submitter writes, "A three-inch crack (was found) in the left fuselage side frame at station 257.65, approximately two-inches above the cabin floor."  (Frame P/N: 265312254031)


CRACKED BELL FRAME; VIEW 1.

 

CRACKED BELL FRAME; VIEW 2.


 

(Wow!  This is a terrific safety catch.  Did the tiny outside crack in the previous report peak your curiosity for an immediate inside inspection, or were the two discoveries incidental to one another?  This will make for an interesting repair—Ed.)

Part Total Time:  8,000.0 hours at 5,980 cycles

 

POWERPLANTS

Lycoming:  TIO540; Cracked Engine Case; ATA 8520

(This engine hangs from the R/H wing of a Piper PA31-350.)

An unidentified repair station technician writes, "The operator requested troubleshooting of low oil pressure on the R/H engine.  Upon removal of the engine cowl, the mechanic discovered oil film on the L/H side of the engine case.  Further inspection revealed what appeared to be a crack on the L/H case half.  Paint was removed and dye penetrant applied, revealing a 1.3-inch crack on the case half at the number four cylinder (forward top stud area).  The penetrant was cleaned (from the surface) and developer applied to the area.  (I) ran the engine to verify the crack (propagated completely...) through the case.  Run-up revealed oil coming from the suspected crack area.  The operator was advised and the aircraft grounded until a repair (is completed)."

CLOSEUP VIEW SHOWING OIL STAIN IN DYE PENETRANT.

Part Total Time:  (unknown)

 


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

2010FA0000013

 

 

 

CONDENSER

FAILED

12/21/2009

 

 

 

1051676

MAGNETO

THIS CONDENSER FAILED WITH 17.1 HOURS TIS. SERIES CIRCUIT OPENED UP INTERNALLY, CAUSING CONTACTS TO BURN AND MAG TO QUIT.

CA091127005

 

 

HARTZL

SCREW

BROKEN

11/26/2009

 

 

 

A0321

BLADE CLAMP

(CAN) DURING DISASSEMBLY OF PROPELLER FOR OVERHAUL THE SAFETY LOCK WIRE ON ONE CLAMP BOLT WAS BEING CUT. AS THE WIRE WAS CUT THE BOLT FELL FROM ITS LOCATION IN THE BLADE CLAMP. IT IS BELIEVED THAT THE BOLT IS NOT A HARTZELL MANUFACTURED PART AS THE PART NUMBER IS NOT ON ITS OUTER CIRCUMFERENCE AS DESCRIBED IN HARTZELL SERVICE BULLETIN 137A. IT WAS ALSO NOTICED THAT THE TWO BLADE CLAMP HALVES WERE MISMATCHED BY SN WHICH IS NOT ACCEPTABLE PRACTICE IAW THE MANUFACTURER. THIS COULD HAVE CONTRIBUTED TO THE BOLT FAILURE (TC NR 20091127005)

2010FA0000004

 

 

 

STARTER GEN

MISOVERHAULED

11/13/2009

 

 

 

23085025

ENGINE

DURING DISASSEMBLY OF THIS STARTER GENERATOR THAT WAS RECEIVED FOR ROUTINE O/H, 3 ITEMS WERE NOTED THAT ARE NOT APPROVED BY THE MFG 23085 SERIES, REV 4, 8/12/2003, 24-30-19 CMM. THE STATOR WAS COATED WITH GLYPTOL PAINT. CMM STATES THAT "THE USE OF GLYPTOL ON EITHER THE ARMATURE OR STATOR WINDINGS IS STRICTLY PROHIBITED. UNITS HAVING GLYPTOL COATING ON EITHER OF THESE PARTS MUST HAVE THESE PARTS REPLACED PRIOR TO RETURNING UNITS TO SERVICE." GLYPTOL WAS ALSO FOUND COATING THE INSIDE OF THE AIR SCOOP. THIS IS NOT APPROVED BY MFG SPD 1002. ANTI-DRIVE END BEARING LINER HAD BEEN STAKED IN 2 PLACES, PRESUMABLY TO HOLD THE BRG IN PLACE. THIS IS NOT AN APPROVED PRACTICE IAW CMM. THE LINER MUST EITHER BE REPLACED OR REPLATED IT THE DIMENSIONS ARE NOT WITHIN TOLERANCES. IT CMM HAD BEEN FOLLOWED AT THE PREVIOUS REPAIR FACILITY, THESE ITEMS WOULD NOT HAVE BEEN AN ISSUE. (K)

2010FA0000012

 

 

 

CONDENSER

FAILED

12/21/2009

 

 

 

1051676

SERIES CIRCUIT

THIS CONDENSER FAILED WITH LESS THAN 10 HOURS TIME-IN-SERVICE. SERIES CIRCUIT OPENED UP INTERNALLY, CAUSING CONTACTS TO BURN AND MAG TO QUIT. SUSPECT MFG DEFECT ON THIS PART. MFG HAS BEEN NOTIFIED OF THIS TREND, AND FAILED CONDENSERS WILL BE RETURNED TO THEM FOR THEIR ANALYSIS. (K)

2010FA0000014

 

 

 

CONDENSER

FAILED

12/21/2009

 

 

 

1051676

MAGNETO

THIS CONDENSER FAILED WITH LESS THAN 10 HOURS TIME-IN SERVICE. SERIES CIRCUIT OPENED UP INTERNALLY, CAUSING CONTACTS TO BURN AND MAG TO QUIT. THIS IS SECOND CONDENSER TO FAIL IN THIS MANNER WITH LOW TIS SINCE NEW. MFG CONTACTED SAID THEY HAVE NOT SEEN A TREND OF BAD CONDENSERS.

2010FA0000061

 

CONT

 

BLADE

CORRODED

1/7/2010

 

IO470*

 

 

PROPELLER

PROPELLER RECENTLY OVERHAULED 10/29/2009 PROPELLER CAME IN FOR REPITCH WITH NO TIME ON SINCE OVERHAULED. 1 BLADE PAINT WAS REMOVED AND LOTS OF CORROSSION LEFT UNDER PAINT NOT REMOVED AS SHOULD BE WITH OVERHAUL. PROPELLER WILL HAVE TO BE REOVERHAULED TO DETERMINE THAT SPECIFICATIONS OF WIDTH AND THICKNESS WILL STILL BE AMPLE AFTER REPAIRS.

CA091124005

 

CONT

 

FUEL CONTROL

MALFUNCTIONED

10/14/2009

 

IO520BB

 

 

ENGINE

(CAN) ENGINE WOULD QUIT ON LANDING WHEN TAXIING OFF OF RUNWAY. FOUND FUEL CONTROL UNIT HAD AREAS OF TRAVEL ON MIXTURE SIDE WAS HARD TO MOVE. HAVE HAD THREE DIFFERENT AIRCRAFT WITH THE SAME PROBLEM ALL WITH LESS THAN 250 HRS TOTAL TIME ON OVERHAULED ENGINES AND LESS THAN 6 MONTHS OF BEING INSTALLED IN THE AIRCRAFT. (TC NR 20091124005)

CA091201003

 

CONT

 

TERMINAL

FAILED

11/30/2009

 

TSIO550C

 

 

PROPELLER DEICE

(CAN) PILOT NOTICED PROPELLER DEICE FAILURE ANNUNCIATION. INVESTIGATION FOUND DEICE BOOT WIRE TERMINALS FAILED. (TC NR 20091201003)

2010FA0000038

 

PWA  

 

PLANETARY GEAR

MISMANUFACTURED

12/22/2009

 

PT6A28

 

E3035030

2ND STAGE

2ND STAGE PLANET GEARS HAVE ON THE INTERNAL BORE A PRESS FIT BUSHING (PN E3035030). THIS BUSHING HAS ITS BORE COATED OR SPRAYED WITH BRONZE MATERIAL INTRODUCED BY SB 1404. DURING OUR INSP WE OBSERVED THAT THIS BRONZE COATING HAD ROTATED FROM ITS ORIGINAL POSITION INDICATING THAT IT IS LOOSE. HAVING SEPARATED FROM THE INTERNAL WALL OF THE BUSHING. THIS SITUATION COULD LEAD TO METAL CONTAMINATION AND GEARBOX FAILURE. THIS IS MFG DEFECT.

CA091124003

AEROSP

PWA  

 

SYMBOL GENERATOR

MALFUNCTIONED

11/22/2009

ATR42300

PW120

 

 

EHSI 

(CAN) ON ENGINE NR 1 START, THE CAPTAINS EHSI WENT UNSERVICEABLE AND C/B POPPED. C/B RESET WITH NO POSITIVE RESULT. ODOR OF SMOKE WAS OBSERVED. EHSI AND SYMBOL GENERATOR REPLACED. SYSTEM FUNCTION CHECKED SERVICEABLE. (TC NR 20091124003)

CA091203003

AIRBUS

GE  

 

DUCT

CRACKED

12/2/2009

A310300

CF680C2A8

 

A4933101500201

APU BOOST PUMP

(CAN) PIREP DEFECT 1037394 - FUEL MIGRATING FROM LT INNER TANK TO CTR TANK. MX FOUND THE APU BOOST PUMP CANNISTER DELIVERY DUCT CRACKED. REPLACED PER MM 49-32-14 AND SERVICEABLE. (TC NR 20091203003)

CA091202002

AIRBUS

GE  

 

BOLT

DIRTY

11/30/2009

A319114

CFM56*

 

 

RUDDER ACTUATOR

(CAN) F/CREW NOTED A LOSS OF YELLOW HYD FLUID DURING FLIGHT MCO TO YYZ. MAINTENANCE IN YYZ NOTED EVIDENCE OF HEAVY BUILD-UP ON THE RUDDER. FURTHER INVESTIGATION FOUND TWO OF THREE ATTACH BOLTS FOR ONE OF THE ACTUATOR RODS SHEARED. BOLTS SHANKS REMAINED BUT HEADS WERE MISSING. SEE ATTACHED PICTURES. (TC NR 20091202002)

2010FA0000042

AMTR

 

 

GROMMET

FAILED

12/22/2009

GREATLAKES

 

 

 

FIRE WALL

FAILURE OF A RUBBER GROMMET ON THE PRIMARY 28 VDC DC POWER CABLE PASSING THROUGH THE FIRE WALL WAS FOUND DURING AN INSPECTION. FAILURE OF THIS GROMMET AND CHAFING THROUGH THE INSULATION WOULD CAUSE SHORTING OF THE BATTERIES AND A FIRE STARTING IN THE FRONT COCKPIT. THE MASTER RELAY WAS INSTALLED FWD OF THE FIREWALL, MEANING THAT THE 28 VDC POWER CABLE THAT PASSES THROUGH THE FIREWALL AND IS "HOT - LIVE", EVEN WITH THE MASTER SWITCH IN THE "OFF" POSITION. THE BATTERIES ARE LOCATED IN THE FRONT COCKPIT, AFT OF THE FIREWALL. A FIRE COULD HAPPEN IN FLIGHT OR EVEN IT THE ACFT WERE IN STORAGE (UNLESS THE BATTERIES ARE DISCONNECTED. THE MASTER RELAY SHOULD BE LOCATED AFT OF THE FIREWALL AND CLOSE TO THE BATTERY BOX, SO THAT WITH THE MASTER RELAY SWITCHED "OFF" ALL CIRCUITS WOULD BE "COLD-DEAD", WITH NO CHANCE OF SHORTING THE BATTERIES. THE FIELD CIRCUIT WIRING SHOULD HAVE GONE THROUGH THE MASTER SWITCH TO CONTROL THE GENERATOR SYS. THIS ACFT WAS FOUND NOT TO HAVE THIS, WHEN THE ENGINE RUNS THE GENERATOR SYS IS "HOT-LIVE", AND THE PILOT HAS NO WAY TO KILL THE GENERATOR, SHOULD THERE BE A SHORT IN THE 28VDC.

2010FA0000015

AMTR

LYC  

LYC  

SHROUD

CRACKED

1/10/2010

RV9A

O320D2J

FRCN040

AEL14995

NR 3 CYLINDER

PN AEL 14995 (SPRING, SHROUD TUBE) WAS FOUND BROKEN ON NR3 CYLINDER. THE TUBE HAD BACKED PARTIALLY OUT LEAKING A SMALL AMOUNT OF OIL.

2010FA0000022

AYRES

WRIGHT

 

SPAR

CRACKED

1/4/2010

S2R  

R182071

 

40261T023

VERTICAL STAB

TOP RUDDER ATTACH BRACKET CRACKED OUT OF REAR SPAR ON THE VERTICAL FIN. NOTICED CRACK AT ANNUAL INSPECTION. POSSIBLY INSTALL A HEAVIER REAR SPAR OR BEEF UPS IN THAT AREA.

CA091118013

BEECH

PWA  

 

DOUBLER

CRACKED

11/15/2009

1900C

PT6A65B

 

 

HORIZOTNAL STAB

(CAN) DURING A SCHEDULED 1200 HOUR INSPECTION, A CRACK WAS FOUND ON A DOUBLER WHERE THE HORIZONTAL STAB MEETS THE VERTICAL STAB ON THE TAIL. MAINTENANCE GROUNDED THE AIRPLANE IMMEDIATELY. UPON FURTHER INVESTIGATION, IT WAS FOUND THAT THE BOLTS THAT HOLDS THE VERTICAL AND HORIZONTAL STAB TOGETHER WERE NOT TIGHT. BELIEVE THAT THIS WAS THE MAIN CAUSE FOR THE CRACK BECAUSE OF THE MOVEMENT/FLEXING OF THE TWO STRUCTURES. PLEASE SEE ATTACHED PHOTOS (TC NR 20091118013)

CA091112004

BEECH

PWA  

 

LEVER

WORN

11/10/2009

1900C

PT6A65B

 

50944078

THROTTLE

(CAN) THE ALUMINUM INPUT LEVER ARM THAT GOES ONTO THE SHAFT FOR THE ENGINE CONTROL CAMBOX, LOCATED ON THE ENGINE, SLIPPED ON THE SHAFT CAUSING A RE-INDEXING OF THE ENGINE RIGGING, PILOTS WERE UNABLE TO REDUCE THE POWER TO IDLE. THIS IS A VERY POOR DESIGN FROM BEECHCRAFT. THE ALUMINUM ARM HAS NO SPLINES AND SLIDES OVER A STEEL SHAFT WITH VERY SMALL SPLINES. THE CLAMPING BOLT (ON THE LEVER) MUST BE EXTREMELY TIGHT (BEYOND STANDARD TORQUE AND NO SPECIAL TORQUE IS LISTED IN THE MAINTENANCE MANUAL) AND SINCE THERE IS NO SPLINES ON THE ARM, IT CAN EASILY SLIP ON THE SHAFT IF THE ARM IS NOT IN PERFECT CONDITION AND THE BOLT IS NOT OVER TIGHT. THIS IS THE MAIN PART USED TO TRANSFER POWER LEVER INPUTS FROM THE COCKPIT TO THE ENGINE. (TC NR 20091112004)

CA091130003

BEECH

PWA  

 

SHAFT

BROKEN

11/18/2009

1900C

PT6A67D

 

1013800002

TE FLAPS

(CAN) NR 3 FLAP FLEX SHAFT (RT INBD) SHEARED CAUSING SPLIT FLAP PROTECTION TO SHUTOFF FLAP SYSTEM. (TC NR 20091130003)

CA091117004

BEECH

PWA  

 

MOUNT

BROKEN

11/16/2009

3NM  

R985AN14B

 

18S9100

ENGINE

(CAN) FOUND ON ANNUAL INSPECTION, FORWARD END OF LOWER RT ENGINE MOUNT TUBE MEMBER BROKEN COMPLETELY AROUND TUBE AT DATA PLATE ATTACH RIVETS LOCATION. FAILURE LOOKS LIKE IT BEGAN AT THE FORWARD END OF THE DATA PLATE ATTACHING RIVETS. MAY HAVE CRACKED FROM RIVET TO RIVET THEN AROUND THE REST OF THE TUBE. (TC NR 20091117004)

2010FA0000001

BEECH

CONT

 

ARM  

CRACKED

1/7/2010

58  

IO550*

 

3582517213

NLG ACTUATOR

NOSE GEAR ACTUATOR ARM FOUND CRACKED IN AREA OF WHERE THE ARM JOINS THE INPUT DRIVE BOSS. 2 OF THE 4 WEBS ATTACHING THE ARM TO THE BOSS WERE CRACKED.

2010FA0000043

BEECH

 

 

TORQUE TUBE

CRACKED

12/11/2009

99A  

 

 

115610015

RT ELEVATOR

WHILE PERFORMING MAGNETIC PARTICLE INSP IAW SB 2145 OF (RT) ELEVATOR TORQUE TUBE FOUND CRACKED ON (RT) TORQUE TUBE, THE PIN HOLE AREA.

CA091202018

BEECH

GARRTT

 

SHUTOFF VALVE

MALFUNCTIONED

11/30/2009

B100

TPE3316252B

 

 

CABIN AIR

(CAN) BOTH FLOW PACKS INSTALLED ON AIRCRAFT CHECKED ON GROUND RUN, VERY SLOW TO PRODUCE PRESSURIZATION ON EITHER SIDE. TESTED BOTH SIDES IN HANGAR IAW MM, FOUND FIRE WALL SHUTOFF VALVE WOULD NOT OPEN AT SPECIFIED PRESSURE. LEFT SIDE REQUIRED 30 PSI AND OVER A MINUTE TO START OPENING AND 40 PSI TO FULLY OPEN. MM SPECIFIES 19 PSI AND MAX 25 SECONDS TO FULLY OPEN. RIGHT SIDE REQUIRES 19 PSI TO START OPENING AND 30 PSI TO FULLY OPEN. (TC NR 20091202018)

CA091126001

BEECH

PWA  

 

GOVERNOR

MALFUNCTIONED

11/23/2009

C90  

PT6A21

 

 

FUEL CONTROL

(CAN) AFTER TAKEOFF THE ENGINE EXPERIENCED AN UNCOMMANDED POWER INCREASE AND WAS SHUT DOWN. INVESTIGATION REVEALED A FAULTY FUEL CONTROL GOVERNOR SECTION. (TC NR 20091126001)

2010FA0000037

BEECH

 

 

TERMINAL

LOOSE

1/15/2010

F33A

 

 

 

SWITCH

CONTACT TERMINALS ARE LOOSE AND CAN BE MOVED BY HAND. SWITCH THROW HANDLE IS ALSO LOOSE AND CAN BE MOVED FROM ANY POSITION.

2010FA0000036

BEECH

 

 

TERMINAL

LOOSE

1/15/2010

F33A

 

 

 

CONTROL PANEL

CONTACT TERMINALS ARE LOOSE AND CAN BE MOVED BY HAND. SWITCH THROW HANDLE IS ALSO LOOSE AND CAN BE MOVED FROM ANY POSITION.

CA091203001

BELL  

ALLSN

 

FRICTION RING

DAMAGED

12/1/2009

407  

250C47B

 

200SGL132Q

STARTER GEN

(CAN) DURING ANNUAL INSPECTION/UNSCHEDULED ENGINE CHANGE, STARTER/GENERATOR WAS REMOVED & INSPECTED BEFORE TRANSFER TO REPLACEMENT ENGINE. AME NOTICED FRICTION RING SPLIT & PROTRUDING FROM SHAFT PLATE. STARTER GENERATOR SENT TO LOCAL REPAIR FACILITY FOR REPAIR. INSPECTION REPORT INDICATES FRICTION RING WAS FOUND TO BE CLAMPED SECURELY BETWEEN SHAFT PLATE & DAMPER PLATE, DUE TO THE SHAFT NUT BEING TIGHTENED DOWN ALL THE WAY. NEW FRICTION RING INSTALLED IAW CMM.

CA091202012

BOEING

RROYCE

 

FAN BLADE

UNKNOWN

12/2/2009

717200

BR700715A130

 

BRH20390

 

(CAN) ENGINES 13372 AND 13338 ARE IN FOR MAINTENANCE. DURING DETAIL INSPECTION OF 1 OFF FAN BLADE FROM ENGINE 13372 BRH20390 S/N RGK14109 IT WAS NOTED FROM INSPECTION RECORD DATABASE THAT SERIAL NUMBER WAS IDENTICAL TO ENGINE 13338 FAN BLADE, BRH20390 S/N RGK14109. THE FAN BLADE ON BR715 ARE CLASSIFIED PART (SENSITIVE COMPONENT) AND SERIAL NUMBER IS UNIQUE FOR TRACEABILITY AND ENGINE LOG BOOK LIFE MONITORING. A SAFETY ALERT HAS BEEN SUBMITTED TO THE OEM (RRD). (TC NR 20091202012)

CA091125005

BOEING

 

 

STRUCTURE

CHAFED

10/1/2009

7377*

 

 

 

INTERIOR

(CAN) WITH REGARDS TO THE EXOTRIM INTERIOR SUPPORT STRUCTURE DAMAGE WAS FOUND. 1. LOCK FASTENERS CHAFING ON THE ALUMINUM STRUCTURE (FROM INITIAL INTERIOR INSTALL) 2. SECURING SCREWS BEING USED WERE TOO LONG CHAFING INTO THE ALUMINUM SUB-STRUCTURE (FROM ORIGINAL INTERIOR INSTALL) (TC NR 20091125005)

CA091202016

BOEING

GE  

BOEING

SCUFF PLATE

DAMAGED

12/1/2009

737800*

CFM56*

 

141A48421

WINDOW

(CAN) AFTER DEPARTURE FROM YEG, CREW REPORTED DIFFICULTY PRESSURIZING THE AIRCRAFT AND THE LT SLIDING WINDOW APPEAR TO BE NOT CLOSED PROPERLY. AIRCRAFT RETURNED TURNED BACK FROM FLIGHT AND LANDED SAFELY IN YEG. ON INVESTIGATION, FOUND THE SCUFF PLATE ON LT CD POST (FWD FRAME OF SLIDING WINDOW CUT-OUT) CRACKED AND SLIGHTLY DISLOCATED FROM ORIGINAL POSITION. THIS PLATE IS INSTALLED ONLY ON POST-MOD AIRCRAFT PER SB B737-56-1024. THIS PRESUMABLY PREVENTED THE LT SLIDING WINDOW FROM CLOSING PROPERLY CAUSING A PRESSURIZATION LEAK. (TC NR 20091202016)

CA091125001

BOEING

GE  

 

BEARING

FAILED

11/18/2009

767333

CF680C2B6F

 

 

MLG WHEEL

(CAN) NR 4 MAIN WHEEL INNER BEARING HAD A COMPLETE FAILURE. MAINTENANCE SPOTTED THE MAIN WHEEL SITTING AT AN ODD ANGLE ON THE GATE AND INVESTIGATED. OUTER BEARING AND THE PIECES LEFT FROM THE INNER BEARING HAVE BEEN HANDED OVER TO BOEING FOR FURTHER INVESTIGATION. THE MAIN WHEELS HAS BEEN SHIPPED TO AVEOS IN YUL FOR LAB TESTING. (TC NR 20091125001)

2010FA0000044

BOEING

 

 

TURBINE WHEEL

CRACKED

7/12/2009

777306ER

 

 

1865M13G03

ENGINE

DURING O/H OF THE STAGE 1 HPT DISK AFTER 18642 HRS AND 3330 CYCLES SINCE NEW. INSP OF THE DISK IAW ATA 72-53-02 INSP 001 REVEALED 5 OFF CRACKS DURING A CLASS G FPI. 4 OFF CRACKS WERE NOTED TO THE EDGE OF THE LOWER PRESSURE FACE AND 1 OFF CRACK NOTED TO THE EDGE OF THE UPPER PRESSURE FACE. ALL CRACKS WERE APPROX 0.5" IN LENGTH. THE OEM HAS BEEN INFORMED.

CA091124001

BOLKMS

LYC  

 

GEARBOX

MAKING METAL

10/9/2009

BK117B2

LTS101750B1

 

1171200501

MAIN ROTOR

(CAN) DURING TRAINING FLIGHT, PILOTS NOTED TRANSMISSION CHIP LIGHT, BURN-OFF ATTEMPTED PER FLM. NOT SUCCESSFUL, RETURNED TO BASE AME INSPECTED CHIP DETECTOR. FUZZ FOUND CLASS C CHAP 11 TABLE 11-2 MM. CLEANED AND GROUND RUN, NO FAULT FOUND. AIRCRAFT RETURNED TO SERVICE. PILOTS RESUMED TRAINING, NOTED TRANSMISSION CHIP LIGHT. BURN-OFF ATTEMPTED PER FLM. NOT SUCCESSFUL, RETURN TO BASE AME INSPECTED CHIP DETECTOR, CHIPS FOUND CLASS D-F CHAP 11 TABLE 11-2 MM. MAIN TRANSMISSION REMOVED FOR REPAIR (TC NR 20091124001)

CA091124002

BOLKMS

LYC  

 

TRANSMISSION

MAKING METAL

10/20/2009

BK117B2

LTS101750B1

 

1171200501

MAIN ROTOR

(CAN) PILOTS NOTED TRANSMISSION CHIP LIGHT IN FLIGHT, RETURNED TO BASE. AME INSPECTED CHIP DETECTOR. METAL FOUND ON CHIP DETECTORS. MAIN TRANSMISSION REMOVED FOR REPAIR (TC NR 20091124002)

CA091120001

BOMBDR

PWC  

 

PROBE

MALFUNCTIONED

11/17/2009

DHC8400

PW150A

 

028069109

FUEL TANK

(CAN) ON CRUISE NR 2 TANK FUEL LOW, CAUTION LIGHT ILLUMINATED, FUEL INDICATOR WAS ERRATIC WITH READING OF DASHES. ON FINAL APPROACH FOR LANDING ABOUT 8 MILES, ENG NR 2 FLAME OUT. MAINTENANCE ACTION, PERFORMED FUNCTIONAL TEST OF THE FUEL CONTROL ELECTRICAL WIRING HARNESS IAW AMM TASK 73-21-11.720.80, OK PERFORMED FUEL QUANTITY CHECK OF LT AND RT FUEL TANKS USING MAGNA STICK IAW AMM TASK 28.40.26.610.801 RESULTS: LT 769 KG. RT NIL PERFORMED FIM TASK NR 28-40.00.810.827 FOUND TANK PROBE NR 9 FAULTY. (TC NR 20091120001)

2010FA0000006

CESSNA

LYC  

 

SHAFT

WORN

12/7/2009

152  

O235L2C

 

 

THROTTLE

PARTIAL POWER LOSS AT 200 FT AGL. ACFT SUCCESSFULLY LANDED OFF AIRPORT WITHOUT DAMAGE. INSP OF CARBURETOR FOUND FUEL STAINS AROUND THROTTLE SHAFT ON BOTH SIDES- ACCELERATOR PUMP END AND THROTTLE ARM END. UNIT DISASSEMBLED. FOUND SHAFT WEAR EXCESSIVE AND CONTACT WEAR ON THROTTLE PLATE. UNIT SENT FOR REPAIR. UNIT RETURNED WITH NEW SHAFT, THROTTLE PLATE WITH SCREWS, BUSHINGS, AND NEWEST COMPLAINT FLOAT KIT. EXTENSIVE GROUND RUN UPS TO FULL POWER ACCOMPLISHED. RELEASED FOR FLIGHT.

2010FA0000018

CESSNA

 

 

CONNECTOR

BURNED

1/13/2010

172P

 

 

S20641

LANDING LIGHTS

LANDING & TAXI LIGHTS INOP ON PRE-FLIGHT. FOUND COWLING CONNECTOR ASSY, COMPRISING PN S1637-3 & -4, PLUS POWER WIRE AND CONNECTOR PINS BURNED AND CONNECTOR MELTED. REPLACED CONNECTOR AND REMOVED BURNED POWER WIRE. OPS CHECK SAT. THIS CONDITION IS CAUSED BY LEAVING LANDING AND TAXI LIGHTS ON IN FLIGHT FOR EXTENDED TIMES AS THE SYS IS NOT CAPABLE OF THIS ELECTRICAL LOAD FOR EXTENDED OPERATION WITH OUT OVERHEATING WIRES, CONNECTORS AND SWITCHES. SEB09-6A ADDRESSED THIS PROBLEM WITH THE LANDING/TAXI LIGHT SWITCHES REQUIRING INITIAL SWITCH REPLACEMENT AND REOCCURRING REPLACEMENT AT 4 YEARS. SWITCH WAS REPLACED PREVIOUSLY DUE TO OVERHEATING. THIS PROBLEM EXISTS WITH THIS MODEL ACFT, 12 AND 24 VOLT SYS, WITH CONTINUOUS OPERATION OF LANDING LIGHT AND OR TAXI LIGHTS. IN A FLIGHT TRAINING OPERATION MORE NUMEROUS TAKEOFF AND LANDINGS ARE CONDUCTED ON A DAILY BASIS CONTRIBUTING TO THIS PROBLEM. A FIRE HAZARD EXISTS IF OVERHEATED COMPONENTS ARE NOT DETECTED.

2010FA0000033

CESSNA

LYC  

 

CONTROL CABLE

DAMAGED

1/8/2010

172S

IO360L2A

 

0510105365

AILERONS

CABIN OVERHEAD CTR PANEL WAS REMOVED FOR PROGRESSIVE INSP. DURING FLAP & AILERON CABLE INSP FLAT SPOTS WERE NOTICED ON 3 AILERON CONTROL CABLES. ROLLED CABLES FOR BETTER VIEW OF CONTACT POINT WITH PULLEYS AND WAS ABLE TO CATCH FRAYED WIRES WITH A RAG AND COULD SEE A SUBSTANTIAL GROOVE IN THE CARRY-THRU CABLE. CABLE TENSIONS WERE WITHIN PROPER SPECS AND AREA WAS CLEAN & FREE OF ANY DIRT/DEBRIS. ALSO PLASTIC PULLEYS WERE INSPECTED, THEY WERE CLEAN AND FREE TO ROLL. THIS PROBLEM SEEMS TO BE HAPPENING DURING NORMAL FLIGHT TRAINING SCHOOL USE AND HAS BEEN NOTICED TO BE HAPPENING WITH OUR OTHER ACFT WITH THE SAME TIMES. CAUSE IS PROBABLY FROM PULLEYS THEMSELVES. THEY ARE MADE FROM A HARD WHITE PLASTIC MATERIAL. THE BRAIDED STEEL CABLES ARE RUBBING AGAINST THE PULLEYS INSTEAD OF ROLLING ON THEM. THAT IS CAUSING THEM TO FLAT SPOT AT FIRST AND THEN GROOVE ONCE WORN INTO THE CABLE DEEP ENUGH. THERE IS ALSO NO NOTICIBLE CABLE DEFLECTION WHERE THE CABLES CONTACT THE PULLEYS, SEEMS LIKE THE PULLEY DIAMETER IS TOO SMALL. REPLACE THE PULLEYS WITH A NORMAL BROWN PHENOLIC TYPE PULLEY USED IN ALL OTHER AREAS OF THE ACFT OR TO ENLARGE THE PULLEY DIAMETER TO INCREASE THE CABLE TO PULLEY CONTACT.

CA091125003

CESSNA

LYC  

 

ALTERNATOR

FAILED

11/22/2009

172S

IO360L2A

 

991059111RX

ENGINE

(CAN) THE AIRCRAFT PFD INDICATED CHARGING SYSTEM FAILURE IN FLIGHT. AIRCRAFT RETURNED TO BASE TROUBLE SHOOTING C/O FOUND ALTERNATOR FAILED, UNIT ONLY HAD 300 HRS SINCE OVERHAUL. MANUFACTURER RECOMENDS 500 HR INTERVAL. (TC NR 20091125003)

CA091126005

CESSNA

LYC  

LYC  

RING GEAR

FAILED

11/23/2009

172S

IO360L2A

 

72566

STARTER

(CAN) ONE TOOTH ON RING GEAR ASSEMBLY WAS MISSING, TOOTH BROKEN AT BASE, NO EVIDENCE OF DAMAGE ON STARTER PINION GEAR FOUND. NO EVIDENCE OF STARTER KICK BACK/ENGINE KICK BACK NOTED. NO OTHER DAMAGE NOTED ON ANY GEAR TEETH. SUSPECT QUALITY CONTROL AT POINT OF MANUFACTURE. (TC NR 20091126005)

2010FA0000003

CESSNA

 

CESSNA

ROD END

BROKEN

12/11/2009

310  

 

 

HM4 

RT MLG

ROD END BROKE WHEN ATTEMPTING TO EXTEND THE LANDING GEAR IN FLIGHT. COULD NOT EXTEND THE GEAR, RESULTING IN A GEAR-UP LANDING. UPON INSPECTION OF THE ROD END, FOUND THAT IT HAD BEEN CRACKED PRIOR TO THE INCIDENT. PROBABLE CAUSE IS FATIGUE FAILURE DUE TO THE AGE OF THE COMPONENT. RECOMMEND TIME CHANGE REQUIREMENT. (K)

2010FA0000005

CESSNA

CONT

 

STUD

DAMAGED

12/18/2009

337G

IO360G

 

6436511

CYLINDER DECK

DURING THE TORQUE SEQUENCE FOR THE ENG O/H FINAL ASSY, FASTENERS ON THE ENG CASE WERE BROUGHT TO HALF THEIR FINAL TORQUE VALUES WITHOUT ISSUE IAW THE CURRENT MM AND PERTINENT SB`S. THEN WHILE ATTEMPTING TO REACH FINAL TORQUE VALUES, NOTED THAT MANY OF THE STUDS SEEMED TO BE PULLING FROM THE CASE RATHER THAN REACHING TORQUE. REMOVED A CYLINDER TO INVESTIGATE, WHERE WE DISCOVERED THE STUDS WERE STRETCHING. THEN REMOVED 2 STUDS TO EXAMINE THE THREADS IN THE CASE, NO DAMAGE WAS FOUND AND THE STUDS CENTER PORTIONS WERE OBVIOUSLY ELONGATED AND NARROWED IN THE CENTER. REQUESTS FOR POSSIBLE CAUSE TO THE MFG AND THE OTHER TECH ADVISORS SEEMED TO SPECULATE THAT THE STUDS MAY HAVE BEEN OVERTORQUED AT SOME POINT BRINGING THEM FROM AN ELASTIC STAT TO PLASTIC. (NOTE: THE STUDS WERE STRETCHING BETWEEN 220-350 IN/LBS OF TORQUE, WELL UNDER FINAL TORQUE VALUE).

2010FA0000029

CESSNA

 

 

CONTROL VALVE

CRACKED

12/9/2009

421C

 

 

99102251

LANDING GEAR

DURING AN ANNUAL INSP, A HAIRLINE CRACK WAS DISCOVERED ON THE BLOCK OF THE LANDING GEAR CONTROL VALVE, PN 9910225-1. THE CRACK WAS ALLOWING HYD FLUID TO LEAK OUT, THE LEAK WAS SMALL. THE PART HAD 16.1 HRS SINCE O/H. THE VALVE WAS SENT BACK TO O/H, WHERE THE BLOCK WAS REPLACED UNDER WARRANTY, NO EXPLANATION WAS GIVEN FOR THE CRACK, THE WARRANTIED PART WAS INSTALLED AND WORKED AS DESIGNED.

CNQ3200902

CESSNA

 

 

DUCT

CHAFED

12/4/2009

560CESSNA

 

 

65155204

ZONE 100

FOUND WIRE BUNDLE THAT ORIGINATES IN THE BOTTOM OF THE AFT J-BOX AND RUNS HORIZONTALLY THROUGH BULKHEAD VERTICLE SUPPORT STRUCTURE FEED-THROUGH HOLE TOWARD ORANGE FRESH AIR DUCT TO BE CHAFING ON THE FRESH AIR DUCT. FOUND MINOR DAMAGE TO THE SHIELDING BUT NOT TO THE CONDUCTORS. PERFORMED CONTINUITY CHECKS, REPAIRED AND INSTALLED PROTECTIVE SLEEVING IAW WIRING DIAGRAM, MM, CHAPTER 20. NOTIFIED MFG PRODUCT SUPPORT OF CONDITION FOUND.

2010FA0000039

CESSNA

PWC  

 

ATTACH BRACKET

CRACKED

11/26/2009

560XL

PW545B

 

662403412

AILERON

DURING ACFT INSP THE RT AILERON ATTACH BRACKET PN 6624034-12 WAS FOUND CRACKED. THE CRACK APPROX 5MM IN LENGTH WAS STARTING FROM FORWARD BOTTOM EDGE TOWARDS THE BOTTOM RIVET. MFG WAS ADVISED ABOUT THE FINDING.

2010F00003

CESSNA

 

 

ACTUATOR

DEFECTIVE

12/31/2009

680CE

 

 

99142574

PITCH TRIM

AS THE ACFT CREW WAS PERFORMING THEIR COCKPIT CHECKLIST, THE SECONDARY PITCH TRIM FUNCTIONAL CHECK FAILED. MX WAS NOTIFIED AND TROUBLESHOT TO DEFECTIVE PITCH TRIM ACTUATOR. INSTALLED OVERHAULED PITCH TRIM ACTUATOR. PERFORMED OPS CHECK WITH NO DEFECTS NOTED.

CNQ3200903

CESSNA

 

 

PLUG

UNDERTORQUED

12/13/2009

750  

 

 

AN8146J

HYD SYSTEM

AIRCRAFT LOST "B HYD PRESSURE IN FLIGHT AS THE RESULT OF HYD FLUID LOSS. FOUND FLUID TO BE LEAKING FROM PN AN814-6J PLUG, O-RING NAS1612-6 (REF. IPC 29-20-00, FIG.1001, PAGE 1, ITEM 17.) PLUG WAS FOUND TO BE AT LESS THAN SPECIFIED TORQUE. THIS PLUG IS INSTALLED ON PN 6707005-7 MANIFOLD ASSY-RUDDER STANDBY (REF.IPC 29-20-00, FIG. 1001, PAGE 1, ITEM 1.) O-RING WAS REPLACED, FILTERS CHECKED FOR DEBRIS, SYSTEM BLED AND OPERATIONALLY CHECKED. ACFT WAS RETURNED TO SERVICE.

CA091128001

CESSNA

ALLSN

 

ACM  

ODOR

11/18/2009

750  

AE3007C

 

73838433

 

(CAN) DURING GROUND OPERATION, FLIGHT CREW OBSERVED AN ODOR IN THE CABIN, FOLLOWED BY HOT AIR BEING CIRCULATED IN THE CABIN. OPERATING THE TEMPERATURE CONTROLS IT WAS NOTED THAT THE COCKPIT ACM DUCT SUPPLY TEMPERATURE WAS RISING, REGARDLESS OF CABIN TEMP SELECTION. SYSTEM WAS DEFERRED AND AIRCRAFT OPERATED BACK TO A MAINTENANCE BASE WITHOUT INCIDENT. INVESTIGATION OF THE COCKPIT ACM FOUND THE UNIT DIFFICULT TO TURN. ONCE REMOVED FOR THE AIRCRAFT A PIECE OF DEBRIS, APPEARING TO BE BEARING CAGE WAS RATTLED FROM THE UNIT. COCKPIT ACM WAS REPLACED AND SERVICE IAW AMM 21, 12. UNIT GROUND CHECKED SERVICEABLE. SYSTEM DEFERRAL CLEARED AND AIRCRAFT RETURNED TO SERVICE. (TC# 20091128001)

2010FA0000031

CESSNA

 

 

SWITCH

CRACKED

12/17/2009

R172K

 

 

S19061

TE FLAPS

OWNER COMPLAINT - WHEN FLAPS "DOWN" WAS SELECTED, SPARKS CAME OUT AROUND HANDLE. FOUND MICROSWITCH PN S1906-1, BROKEN IN HALF, AND SHORTING OUT ON MOUNTING BRACKET. SWITCH BELIEVED TO BE ORIGINAL. REPLACED SWITCH, ALL OPS NORMAL.

2010FA0000030

CESSNA

CONT

 

ADAPTER

BROKEN

12/18/2009

T210N

IO550P

 

642083A2

STARTER

DURING 100HR INSP FOUND GEAR TOOTH IN OIL SUMP DRAIN PLUG. INVESTIGATED, FOUND STARTER DRIVE TOOTH BROKEN AND MATCHED TOOTH TO GEAR. NO FURTHER DAMAGE NOTED.

CA091124006

CESSNA

CONT

 

LANDING GEAR

STUCK

11/23/2009

T310P

TSIO520B

 

 

NOSE 

(CAN) NOSE RETRACTION AFTER TAKEOFF, NLG STUCK IN PARTIALLY RETRACTED POSITION. EMERGENCY EXTENSION ATTEMPTED WITH NO MOVEMENT IN NOSE GEAR. EMERGENCY LANDING CARRIED OUT. GEAR INSPECTION TO BE CARRIED OUT TO DETERMINE CAUSE. (TC NR 20091124006)

CA091202010

CESSNA

CONT

 

SHAFT

BROKEN

11/27/2009

U206F

IO520F

 

 

ELEVATOR TRIM

(CAN) IT APPEARS THE THREADED SHAFT OF THE ELEVATOR TRIM BROKE ON TAKEOFF OR IMMEDIATELY AFTER, CAUSING THE ELEVATOR TO JAM AND CREATING FLUTTER IN THE ELEVATOR CAUSING IT TO BREAK. THIS ALSO CAUSED THE OUTER PORTION OF THE RIGHT HORIZOANTAL STABILZER TO FLUTTER AND BREAK THROUGH FRONT AND REAR SPAR. AIRCRAFT LANDED SAFELY UPDATES: WHEN ELEVATOR TRIM ACTUATOR BOLT BROKE, SOON AFTER THE ELEVATOR WAS JAMMED IN A FULL DOWN POSITION, FORCING THE AIRCRAFT TO PITCH UP. SHORTLY THEREAFTER, THE PILOT HEARD A LOUD NOISE FOLLOWED BY A TAIL SHUTTERING AND THE ELEVATOR PITCH CONTROL WAS REGAINED. THE PILOT WAS NEAR THE AIRFIELD AND WAS FORTUNATELY ABLE TO LAND SAFELY. THE TRIM ACTUATOR THREADED ROD WAS LATER FOUND TO BE BROKEN WHICH CAUSED THE JAM TO OCCUR BETWEEN THE TRIM TAB AND THE ELEVATOR ITSELF. THERE WAS NO EVIDENCE OF CORROSION ON THE FAILED THREADED ROD AND THE LUBRICANT WAS FRESH (NOT CONTAMINATED WITH MOISTURE OR WATER). NEW INFO: SDR SUBMITTER STATED THAT FAILED ACTUATOR ASSY IS AN OLDER PART NUMBER THAT DOES NOT HAVE A GREASE NIPPLE FOR LUBRICATION PURPOSES. (TC NR 20091202010)

WL7R200121109

CNDAIR

 

WINSLOW

CLAMP

IMPROPER PART

12/11/2009

CL6002B16

 

1218FAAVSL

3202 

LIFE RAFT

DURING ROUTINE INSP OF LIFE RAFT, SN 11218 LAST SERVICED, IT WAS DISCOVERED THAT A HAND CLAMP PN 3202 POSSIBLY USED AS A PACKING AID IN THE FOLDING PROCESS WAS NOT REMOVED PRIOR TO RETURN TO SERVICE. IT SHOULD BE NOTED THAT THIS CLAMP IS NOT CALLED OUT FOR IN CMM 25-60-101. FAILURE TO REMOVE THE CLAMP PRIOR TO THE LIFE RAFT BEING INSERTED INTO THE CARRYING CASE (VALISE)COULD HAVE PREVENTED PROPER INFLATION OF THE LIFE RAFT IN THE EVENT OF AN EMERGENCY. THE CLAMP MAY HAVE BEEN ATTACHED TO THE UPPER AND LOWER BUOYANCY TUBE CHAMBERS DURING THE FOLDING PROCESS.

CA091202004

CNDAIR

GE  

 

DETECTION SYS

FAULTED

11/30/2009

CL6002B19

CF343A1

 

8004301

TE FLAP

(CAN) ON APPROACH TO MKE THE FLAPS FAILED AT ZERO DEGREES WHEN SELECTED TO 8 DEGREES. FLAP FAIL CAUTION MESSAGE DISPLAYED. AN UNEVENTFUL FLAP ZERO LANDING WAS CARRIED OUT. THE FLAPS WERE MANUALLY CONFIGURED TO 8 DEGREES BY MTC AND THE A/C FERRIED TO A MTC BASE. FECU CODES RETRIEVED INDICATED THE SKEW DETECTION UNIT. THE SKEW DETECTION UNIT ALSO HAD FAULT LIGHTS ILLUMINATED. THE SKEW DETECTION UNIT WAS REPLACED AND THE SYSTEM TESTED SERVICEABLE. SKEW DETECTION UNIT P/N 80-043-01, S/N A994 WAS REPLACED (TC NR 20091202004)

2010F00001

CNDAIR

 

 

UNKNOWN

ODOR

12/24/2009

CL6002C10

 

 

 

CABIN

AFTER TAKEOFF SMOKE ODOR WITH LITTLE HAZE IN CABIN NEAR ROWS 3 AND 4 IN GALLEY AREA, COFFEEMAKERS WERE NOT ON. ACFT WAS REMOVED FROM SERVICE. PERFORMED GVI OF CABIN AND GALLEY NO DEFECTS NOTED. ALL GALLEY AND CABIN SIDEWALL/CEILING LIGHTS ILLUMINATED. INSPECTED CABIN LIGHT BALLASTS NO DEFECTS NOTED. INSPECTED AVIONICS BAY AND FOUND NO SMOKE ODOR OR EVIDENCE OF BURNING. PERFORMED SEVERAL HIGH POWER ENGINE RUNS IAW GHC WITH BOTH PACKS ON SERVERAL DIFFERENT SETTINGS COULD NOT DUPLICATE. THE ACFT WAS RETURNED TO SERVICE.

CA091201001

CNDAIR

GE  

 

OIL SYSTEM

LOW PRESSURE

11/30/2009

CL604

CF343B

 

 

RT ENGINE

(CAN) DURING THE TAKEOFF ROLL, THE RT ENG LOW OIL PRESS INDICATION CAME ON THE CREW REDUCED ENGINE POWER TO IDLE AND THE ENGINE SHUT DOWN UNCOMMANDED AIRCRAFT RETURNED TO PARKING POSITION. INVESTIGATION ON GOING, FIRST CHECK OF OIL LEVEL SHOWED SUFFICIENT OIL QTY, NO SIGNS OF EXTERNAL OIL LEAKS. (TC NR 20091201001)

CA091201004

CNDAIR

GE  

 

TRANSMITTER

MALFUNCTIONED

11/24/2009

CL604

CF343B

 

 

SPOILERS

(CAN) CADOR 2009C3326 ON TAKEOFF WHEN THE PILOT ADVANCED THE THRUST LEVERS HE GOT A CONFIGURATION SPOILER WARNING MESSAGE. THE TAKEOFF WAS REJECTED AND THE AIRCRAFT RETURNED TO BASE. UPON INVESTIGATION IT WAS FOUND THAT MAINTENANCE WAS PERFORMED ON THE RT FLIGHT SPOILER TRANSMITTER PRIOR TO THE FLIGHT. RIGGING OF THE FLIGHT SPOILER TRANSMITTER REFERS TO THE OPERATIONAL TEST OF THE FLIGHT SPOILER TRANSMITTER. ALL PROCEDURES WERE FOLLOWED FOR ADJUSTMENT AND TESTING OF THE TRANSMITTER AS REQUIRED BY THE MAINTENANCE MANUAL. THE TRANSMITTER ALSO GIVES AN INPUT FOR THE TAKEOFF CONFIGURATION. THERE IS NO REFERENCE TO TEST THE TAKE OFF CONFIGURATION AFTER ADJUSTING THE SPOILER TRANSMITTER IN THE MM. THE TRANSMITTER WAS READJUSTED AND TESTED. A CONFIGURATION CHECK WAS COMPLETED AND AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER SNAGS (TC NR 20091201004)

CA091202015

CNDAIR

GE  

TACTAIR

SOLENOID

OPEN

11/25/2009

CL604

CF343B

 

601R751451

SELECTOR VALVE

(CAN) MLG FAILED TO DEPLOY. QRH PROCEDURES FOLLOWED, ALT EXTENSION CARRIED OUT. T/S DISCOVERED OPEN CIRCUIT ON EXTEND SOLENIOD OF MLG SELECTOR VALVE. VALVE CHANGED AND GEAR SWINGS COMPLETED PER AMM. A/C RETURNED TO SERVICE. (TC NR 20091202015)

CA091130001

CVAC

ALLSN

 

REGULATOR

MALFUNCTIONED

8/20/2009

440  

501D13D

 

6505680

PROPELLER

(CAN) DURING CRUISE AT FL200 RT PROPELLER OVERSPEED WITHOUT DECOUPLING, ENGINE SHUTDOWN, PROPELLER FEATHERED AND LANDED AT CLEVELAND USA. PROPELLER REGULATOR REPLACED DUE INTERNAL FAILURE AND AIRCRAFT RETURNED TO SERVICE REF. AIRCRAFT LOG BOX PAGE 10872 DEFECT NR 1. (TC NR 20091130001)

CA091118010

DHAV

PWA  

 

CONTROL COLUMN

CRACKED

11/17/2009

DHC2MK3

PT6A27

 

C2CF33951

COCKPIT

(CAN) DURING INSTALLATION OF THE DUAL CONTROLS A CRACK WAS FOUND ON THE WELD AT THE BASE OF THE LOWER CONTROL COLUMN. THIS CRACK IS WHERE AWD CF-84-01R1, S/B 2/28 REV B REQUIRES INSPECTION. CRACK WAS INITIALLY NOTICED AS A PAINT CRACK AND UPON FURTHER INSP CONFIRMED WITH NDT AS AN ACTUAL CRACK. (TC NR 20091118010)

CA091203002

DHAV

PWA  

 

CYLINDER HEAD

CRACKED

11/26/2009

DHC2MKI

R985AN14B

 

399355

ENGINE

(CAN) WHILE PERFORMING THE INSPECTION TO COMPLY WITH AD 78-08-07, OIL WAS NOTICED AT THE TOP OF THE CYLINDER BEAD AND ALSO ON AFT SECTION OF ENGINE. UPON FURTHER INSPECTION, A FINE CRACK WAS NOTICED BETWEEN THE COOLING FINS OF THE CYLINDER BEAD. (TC NR 20091203002)

CA091201005

DHAV

PWA  

 

STRUCTURE

CRACKED

11/26/2009

DHC3

PT6A34

 

 

TE FLAP

(CAN) PILOT REPORTED VIBRATION IN LT FLAP AFTER SECOND FLIGHT OF THE DAY. UPON INSPECTION BY MAINTENANCE PERSONNEL, CRACKS WERE FOUND ON THE LT FLAP. THE CRACKS WERE LOCATED ON THE TOP OF THE FLAP TOWARDS THE LEADING EDGE ON BOTH THE RT SIDE OF THE FLAP AND IN THE CENTER OF THE FLAP, RT OF THE HANGER. THE FLAP INSTALLED IN THIS POSITION HAD BEEN CHANGED BY REPLACEMENT TWICE PREVIOUSLY IN THE LAST MONTH FOR A SIMILAR REPORTED DEFECT. UPON FURTHER INSPECTION IT WAS FOUND THAT THE INBOARD FOREFLAP END FUSELAGE FITTING WAS INCORRECTLY POSITIONED. THE SAME RELEASING ENGINEER HAS BEEN IDENTIFIED AS INVOLVED IN THE FIRST TWO OCCURRENCES. (TC NR 20091201005)

CA091126002

DHAV

PWA  

 

TUBE

MISINSTALLED

11/18/2009

DHC7102

PT6A50

 

77900155003

BREATHER SYSTEM

(CAN) DURING FLIGHT, NR 4 ENGINE LOST OIL PSI INDICATION ALONG WITH MASTER CAUTION & OIL PSI LIGHT ILLUMINATED ON ANNUNCIATOR PANEL. ENGINE SHUTDOWN & ACFT LANDED WITHOUT FURTHER INCIDENT. ENGINE INSPECTED & FOUND TO HAVE NO OIL IN OIL TANK. AFTER SERVICING OIL TANK ENGINE RUNS WERE COMPLETED ENGINE DUMPED A LARGE AMOUNT OF OIL OUT BREATHER SYSTEM. DETERMINED THAT DURING FLT OIL HAD FILLED ACCESSORY GEARBOX LEAVING OIL TANK EMPTY & CAUSING LOSS OF OIL PRESSURE DUE TO OIL STARVATION AT PUMP. FOUND LAST SECTION OF BREATHER PIPING IN AFT PART OF THE NACELLE INSTALLED RUNNING IN AN UPHILL MANNER CREATING A GOOSENECK ALLOWING OIL TO POOL. ONCE THE GOOSENECK FILLED WITH OIL IT BLOCKED THE SYSTEM CAUSING THE PRESSURE IN THE ACCESSORY GEARBOX TO BUILD UP, NOT ALLOWING THE OIL TO RETURN TO THE OIL TANK, CAUSING THE OIL PUMP TO RUN OUT OF OIL. THE BREATHER PIPING WAS RE-ALIGNED TO REMOVE THE GOOSENECK AND ALLOW FOR PROPER DRAINAGE, THE LEAKING GARLOCK SEAL WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20091126002)

CA091118012

DHAV

PWA  

 

WIRE

CHAFED

11/13/2009

DHC8102

PW120A

 

 

ELECTRICAL

(CAN) NR 1 SPU POPPING BREAKER, UPON ARRIVAL FOUND WIRING CHAFED AT FAULT AND SUSPECTED BURNING IN THE CENTER WING WIRE BUNDLE, TEMP WIRING REPAIR CARRIED OUT. AC FERRIED FOR FURTHER INVESTIGATION. DURING THE INVESTIGATION, IT WAS FOUND THE SEVERAL WIRES HAD BURN DAMAGE THAT RESULTED FROM THE WIRES CHAFING ON A BRADED WIRE IN THE BUNDLE. 18 WIRES WERE FOUND WITH VARIOUS AMOUNTS OF DAMAGE AS WELL AS BURNT PINS AT THE WING ROOT CONNECTOR. WIRE CHAFED AFTER SHORTING ON NR 1 ENGINE ECU. (TC NR 20091118012)

CA091123003

DHAV

PWA  

 

BONDING JUMPER

DAMAGED

11/18/2009

DHC8102

PW120A

 

MS250837BBX

 

(CAN) WHILE PERFORMING TASKS REQUIRED BY AD CF 2007-32 AND ASSOCIATED DE SERVICE BULLETIN AND FSL IAW AWL 110 FOUND SEVERAL REJECTED BONDING JUMPERS THAT WERE IN THE LIST TO TEST, REFER FSL 170. REPLACED THE FAULTY BONDING JUMPERS BY NEW PARTS. SOME OF THE NEW REPLACEMENT BONDING JUMPERS (2) WERE ALSO FAULTY. THESE WERE REJECTED. (TC NR 20091123003)

CA091201006

DHAV

PWA  

 

BLADE

DAMAGED

11/27/2009

DHC8102

PW120A

 

SFA13MIROAD

PROPELLER

(CAN) FLIGHT 7723 ON NOV 27/09 ENCOUNTERED MULTIPLE BIRDSTRIKE ON APPROACH INTO LONDON (CYXU) AIRPORT. PILOT REPORTED STRIKE TO THE RIGHT WINDSHIELD, RT WING ROOT AND RT NACELLE. MAINTENANCE INSPECTED THE AIRCRAFT IN ACCORDANCE WITH MM 05-50-26, ENGINE MM 05-50-00 AND PROPELLER MM 61-10-00. DAMAGE FOUND ON RT PROPELLER ASSY BLADES NR 1 AND 2. DAMAGE WAS NOT SEVERE BUT WAS BEYOND THE LIMITS SPECIFIED IN THE MMANUAL. BOTH BLADES WERE REPLACED IN ACCORDANCE WITH HAMILTON STANDARD PROPELLER ASSEMBLY MAINTENANCE MANUAL CHAPTER 61-13-02. AIRCRAFT GROUND RUN, FUNCTION CHECKS AND LEAK CHECKS COMPLETED. AIRCRAFT WAS RETURNED TO SERVICE ON NOV 28/09. (TC NR 20091201006)

CA091202001

DHAV

PWA  

 

FITTING

CRACKED

11/27/2009

DHC8102

PW120A

 

85321414111

DOOR FRAME

(CAN) WHILE CARRYING OUT ZONAL INSPECTION OF THE MAIN PASSENGER ENTRANCE DOOR SURROUND STRUCTURE, A CRACK WAS NOTED ON THE TOP FORWARD CORNER MACHINED FITTING. THIS AIRCRAFT WAS IN ON A SCHEDULED HEAVY CHECK "C" VISIT. A NEW FITTING HAS BEEN ORDERED FOR REPLACEMENT BEFORE AIRCRAFT WILL BE RELEASED FROM MAINTENANCE. REFERENCE :- DE HAVILLAND DASH 8 ILLUSTRATED PARTS CATALOG CHAP 53-10-00 FIGURE 35, ITEM 570. PLEASE SEE ATTACHED PHOTO OF THE MACHINED FITTING AND IPC. (TC NR 20091202001)

CA091130005

DHAV

PWA  

 

PUMP

MALFUNCTIONED

11/28/2009

DHC8301

PW123

 

 

HYD SYSTEM

(CAN) NR 1 STBY HYD PUMP NOT COMING ON LINE. (RESOLVED ON W/O: 216586 TASKCARD: NR-00001) FOUND BURNT WIRES ON THE UPPER AFT CORNER OF NR 2 AC CONTACTOR BOX, (CB POPPED AS WELL) WIRES ON TOP OF BOX HAVE ARCED AND BURNED A HOLE IN THE AC CONTACTOR BOX AS WELL AS CHARRING SOME WIRES INSIDE BOX. A NUMBER OF WIRES REQUIRE REPAIR OUTSIDE OF BOX AND WIRES AND COMPONENTS INSIDE BOX REQUIRE FURTHER INSPECTION TO DETERMINE EXTENT OF DAMAGE. RAYCHEM SPLICE CARRIED OUT ON WIRES 10004B18B-1 AND 10006B18C-1. BOX CLEANED UP AND REASSEMBLED. REQUIRES INSTALLATION ON THE AIRCRAFT AND FUNCTION CHECKS. RT AC CONTACTOR BOX BOLTED INTO PLACE. REQUIRES AVIONICS TO RECONNECT ELECTRICALLY. RECONNECTED AND SECURED ALL CONNECTORS ASSOCIATED WITH THE RT AC CONTACTOR BOX, REQUIRES FUNCTION CHECK ON BOTH STANDBY HYDRAULIC PUMPS AND AC VARIABLE FREQUENCY SYSTEMS. PERFORMED OPERATIONAL TEST OF AC VARIABLE SYSTEM IAW AMM 24-21-02 AND STANDBY HYDRAULIC PUMP IAW AMM29-11-17, CHECKED, SERVICEABLE. (TC NR 20091130005)

CA091124004

DIAMON

 

 

BALANCE WEIGHT

UNSECURE

11/18/2009

DA20C1

 

 

2255206002

ELEVATOR

(CAN) ELEVATOR MASS BALANCE WEIGHT FORWARD ATTACH CAP-SCREW FOUND MISSING DURING PRE-FLIGHT INSPECTION, AFT CAP-SCREW IN PLACE BUT NOT TIGHT. DOSS AVIATION REPORTED THAT MASS BALANCE HAD NO PREVIOUS MAINTENANCE CARRIED OUT. REMAINDER OF FLEET (44 AIRCRAFT) INSPECTED FOR MISSING CAP-SCREWS, NONE FOUND. TORQUE CHECK OF CAP-SCREWS IS CARRIED-OUT AS AIRCRAFT CAME IN FOR INSPECTION, NO REMAINING CAP-SCREWS FOUND LOOSE. (TC NR 20091124004)

CA091127004

DIAMON

CONT

 

ROD END

WORN

11/19/2009

DA20C1

IO240B

 

HF3M 

MIXTURE CONTROL

(CAN) DURING SCHEDULED MAINTENANCE IT WAS DISCOVERED THAT THE BUSHINGS RETAINING THE ROD END SWIVEL BALL WERE WORN AND ONE SIDE HAD DISLODGED CAUSING THE SWIVEL BALL TO SEPARATE FROM THE ROD END. MIXTURE CONTROL WAS NOT LOST DUE TO THE LARGE RETAINER WASHER ON THE BOLT SECURING THE ROD END TO THE MIXTURE CONTROL ARM. (TC NR 20091127004)

CA091121001

DIAMON

CONT

 

CABLE

FRAYED

11/1/2009

DA20C1

IO240B

 

A15500550

THROTTLE

(CAN) DURING GROUND OPERATION IT WAS NOTED THAT THE THROTTLE CABLE MOVEMENT WAS ROUGH AND CATCHES HALF WAY. INSPECTION REVEALED THAT THE INNER PART OF THE CABLE WAS STARTING TO FRAY AND CATCHING IN THE AREA WERE IT PASSES THROUGH THE FIREWALL. NEW CABLE INSTALLED. (TC NR 20091121001)

CA091121002

DIAMON

CONT

 

CABLE

BROKEN

11/13/2009

DA20C1

IO240B

 

 

THROTTLE

(CAN) ON START UP, RPM WENT TO 2300 WITH THROTTLE CONTROL AT IDLE. INSPECTION REVEALED THAT INNER THROTTLE CABLE HAD BROKEN. NEW CABLE INSTALLED. (TC NR 20091121002)

CA091119003

DIAMON

 

 

RELEASE MECH

MISINSTALLED

10/22/2009

DA42

 

 

DA452000051

AFT DOOR

(CAN) DURING ROUTINE INSPECTIONS ON THE AIRCRAFT IT WAS DISCOVERED THAT THE AFT DOOR EMERGENCY RELEASE HANDLE WAS NOT ABLE TO BE USED DUE TO EXCESSIVE SILICONE AROUND THE REAR LAMP HOUSING. (TC NR 20091119003)

CA091127002

DIAMON

THIELT

 

CONTROL VALVE

LEAKING

11/20/2009

DA42

TAE1250299

 

057212E002801

PROPELLER

(CAN) IT WAS REPORTED ON NOVEMBER 25, 2009 THAT DURING A TRAINING FLIGHT THE RT ENGINE EXPERIENCED A SEVERE POWER LOSS. JUST PRIOR TO THIS INCIDENT ENGINE WAS NOTICED SURGING BETWEEN 50 AND 70 PERCENT POWER. JUST AFTER THE INITIAL POWER LOSS THE ENGINE INADVERTENTLY RESTARTED BEFORE EXPERIENCING A SECOND SIGNIFICANT POWER LOSS. WITH THE EXCEPTION OF "ALTERNATOR FAILURE", NO OTHER WARNINGS WERE NOTED THROUGHOUT. CREW WAS NOT ABLE TO RESTART ENGINE, DECLARED AN EMERGENCY AND WERE ABLE TO LAND AT DEPARTURE AIRPORT WITHOUT FURTHER INCIDENT. (TC NR 20091127002)

2010FA0000040

DOUG

 

 

VALVE

SEPARATED

1/15/2010

DC1010

 

 

1489951

NR 2 HYD SYS

THIS IS TO REPORT A LOSS OF NR 2 HYD SYS "PRESSURE AND QUANTITY" PRIOR TO TAKE-OFF, ACFT RETURNED TO GATE. INVESTIGATION FOUND VALVE ASY (M1-164) FOR THE 2-1 NON-REVERSIBLE MOTOR PUMP TO BE AT FAULT. REF IPC 29-12-59, FIG 1, PG 9, ITEM 340, PN 148995-1, SN 331. THE VALVE SEPARATED AT THE UNION POINT OF THE MOTOR AND VALVE RESULTING IN COMPLETE LOSS OF FLUID IN NR 2 HYD SYS. THE DISCREPANT VALVE HAS BEEN SENT FOR FAILURE ANALYSIS.

CA091125008

EMB  

GE  

 

CLAMP

BROKEN

11/20/2009

ERJ170200LR

CF348E5

 

17055400401

A/C PACK

(CAN) DURING REMOVAL OF OUR NR 1 PACK ACM FOUND TWO CLAMPS BROKEN OFF AND LAYING IN THE AIR CONDITIONING BAY BOTTOM. INSPECTED THE AREA AND FOUND THEM MISSING FROM THE PACK RAM AIR INLET SCOOPS LT AND RT. ALSO THE RUBBER BOOTS WHERE THE CLAMPS BELONG ARE TORN AND DETERIORATED ON THE UPPER FORWARD EDGES. HAVE SINCE REPLACED THE BOOTS AND CLAMPS WITH NEW PARTS. ATTACHED ARE SOME PICS OF THE WORN PARTS. NOTE: BOTH AIR-CONDITIONING PACKS FUNCTIONED NORMALLY BEFORE AND AFTER THE BOOTS WERE REPLACED. (TC NR 20091125008)

CA091126003

EMB  

GE  

 

ACTUATOR

MALFUNCTIONED

11/25/2009

ERJ190100IGW

CF3410E5A1

 

 

FLAPS

(CAN) DURING THE APPROACH, THE FLIGHT HAD A FLAPS FAILED MESSAGE. THE CREW EXECUTED A GO-AROUND, DECLARED AN EMERGENCY AND LANDED NORMALLY WITH THE FLAPS IN POSITION 1 (TC NR 20091126003)

CA091126004

EMB  

GE  

 

SLAT SYSTEM

MALFUNCTIONED

11/26/2009

ERJ190100IGW

CF3410E5A1

 

 

 

(CAN) EN ROUTE, IN THE BEGINNING OF THE CRUISE STAGE, THE CREW EXPERIENCED A FLAP FAILURE. A DECISION TO RETURN WAS MADE IN CONSULTATION WITH MTC AND SOC. THE FLIGHT RETURNED, DECLARED AN EMERGENCY AND LANDED WITHOUT FURTHER INCIDENT AT THE ZERO FLAP SETTING. THERE WERE NO PASSENGERS ON BOARD. (TC NR 20091126004)

CA091202003

EMB  

GE  

 

STEERING SYS

FAULTED

11/30/2009

ERJ190100IGW

CF3410E5A1

 

 

NLG 

(CAN) LANDING IN SFO CREW EXPERIENCED A NOSE GEAR STEERING FAULT. RESET ATTEMPTED NIL FIX. ALTERNATE BREAKING USED TO GET TO GATE. (TC NR 20091202003)

CA091202005

EMB  

GE  

 

LANDING GEAR

MALFUNCTIONED

11/27/2009

ERJ190100IGW

CF3410E5A1

 

 

LT MLG

(CAN) ON APPROACH TO YYC LEFT MAIN LANDING GEAR DID NOT EXTEND. GO AROUND AND QRH COMPLETED. GEAR RESELECTED ALL INDICATIONS NORMAL. (TC NR 20091202005)

CA091202006

EMB  

GE  

 

FLAP SYSTEM

MALFUNCTIONED

11/26/2009

ERJ190100IGW

CF3410E5A1

 

 

TE FLAPS

(CAN) YYC TO SEA START OF CRUISE FLAP FAILURE CREW RETURNED TO YYC. DECLARED EMERGENCY AND LANDED WITH FLAPS 0 WITHOUT INCIDENT. (TC NR 20091202006)

CA091202007

EMB  

GE  

 

FLAP SYSTEM

WARNING MESSAGE

11/25/2009

ERJ190100IGW

CF3410E5A1

 

 

TE FLAPS

(CAN) YYZ TO SEA ON APPROACH FLAP FAIL MESSAGE, GO AROUND CARRIED OUT AND EMERGENCY DECLARED. NORMAL LANDING FLAPS 1 (TC NR 20091202007)

CA091127003

GROB

LYC  

 

ENGINE

POWER LOSS

11/23/2009

G120A

AEIO540D4D5

 

 

 

(CAN) THE INSTRUCTOR AND STUDENT WERE DEPARTING ON A LOCAL TRAINING FLIGHT AND EXPERIENCED A ROUGH RUNNING ENGINE WHEN THEY REDUCED POWER AFTER T/O. THE INSTRUCTOR ACTIONED THE `ROUGH ENGINE` TASKS OF THE APPROVED CHECKLIST, CONTACTED ATC TO DECLARE AN EMERGENCY AND RETURNED TO THE DEPARTURE AIRPORT WITH OUT FURTHER INCIDENT. AS THE ENGINE RAN SMOOTHLY FOLLOWING POWER REDUCTION, THE INSTRUCTOR TAXIED THE AIRCRAFT BACK TO THE APRON WITH ARFF FOLLOWING THEM IN. A POST SHUTDOWN INSPECTION REVEALED NO DANGER AND THE FIREFIGHTERS ADVISED THE SITUATION AS SECURED. THE INSTRUCTOR JOINED ATTENDING AME TO CONDUCT GROUND RUNS FOLLOWING AN INSPECTION OF THE ENGINE TO DETERMINE IF IT WAS SAFE TO DO SO. THE AIRCRAFT HAD EXPERIENCED ROUGH RUNNING ON A FLIGHT SEVERAL DAYS EARLIER AND COULD NOW BE DUPLICATED INTERMITTENTLY. FURTHER TROUBLESHOOTING SUGGESTED THE ROUGHNESS ORIGINATED WITH STICKING VALVE TRAIN AND THE ENGINE WAS REMOVED AND SENT TO AN OVERHAUL FACILITY AS IT WAS CLOSE TO RECOMMENDED TBO. (TC NR 20091127003)

2010FA0000007

ISRAEL  

GARRTT

 

VANE

BROKEN

12/10/2009

1124A

TFE73131G

 

193058518

RT TE FLAP

RT NR 3 FLAP VANE DEPARTED ACFT IN OR AROUND 12/6/2009. ACFT LANDED AND CREW DISCOVERED THAT THE FLAP VANE BROKE OFF OF THE FLAP AT THE BOLT HEAD OF THE ATTACHING BRACKET.

CA091202013

LEAR

PWA  

 

ACTUATOR

LEAKING

12/2/2009

60LEAR

PW305A

 

2317100017

NLG 

(CAN) DURING A DAILY INSPECTION HYDRAULIC FLUID WAS NOTED ON THE NOSE GEAR TIRE. THE FLUID WAS COMING FROM THE NOSE GEAR ACTUATOR BODY VENT HOLES. A REPLACEMENT ACTUATOR WAS ORDERED. WHEN TRANSFERRING THE DOWN AND LOCKED SWITCH FROM THE LEAKING ACTUATOR TO THE REPLACEMENT METAL WAS FOUND IN THE SWITCH HOUSING. THE LEAKING ACTUATOR WAS DISASSEMBLED IAW THE LEARJET 60 MAINTENANCE MANUAL AND MORE METAL WAS FOUND AS WELL AS WEAR ON THE SHAFT PLATING WHERE THE LOCKING BALLS ENGAGE. THE ACTUATOR WAS BRAND NEW 57 LANDINGS AGO INSTALLED SOMETIME IN JULY OF 2008. THIS AIRCRAFT HAS HAD SEVERAL INCIDENTS WITH NOSE GEAR ACTUATORS. (TC NR 20091202013)

2010F00002

LEAR

PWA  

 

BLEED VALVE

DEFECTIVE

12/31/2009

60LEAR

PW305A

 

31B575601

RT ENGINE

RT ENGINE WOULD NOT SPOOL UP HIGHER THAN 35 PERCENT. TROUBLESHOT TO DEFECTIVE BOV VALVES AND BOV SOLENOID CONTROL VALVES. INSTALLED NEW BOV VALVES AND BOV SOLENOID CONTROL VALVES. PERFORMED ENGINE GROUND RUN WITH NO DEFECTS NOTED. PERFORMED ENGINE OPS CHECK FLIGHT WITH NO DEFECTS NOTED.

2010F00004

PILATS

PWA  

 

NOSE COWL

UNSECURE

12/29/2009

PC1245

PT6*

 

5711012271

LT NACELLE

UPON CLIMBOUT THE PILOTS NOTICED THE LT UPPER NOSE COWLING WAS SLIGHTLY LIFTING FROM ITS MATING SURFACE. THE PILOTS REDUCED POWER DROPPED FLAPS AND GEAR DECLARED AND EMERGENCY AND TURNED BACK FOR THE AIRPORT. THE ACFT LANDED UNEVENTFULLY. UPON SHUTDOWN OUR MX STAFF INSPECTED THE ACFT AND FOUND THE COWLING LATCH WAS NOT LATCHED AT THE LT AFT LATCH. INSPECTED THE COWLING AND FOUND NO DEFECTS. THE ACFT WAS INSPECTED FOR PROPER LATCHING OF THE COWLING AND RETURNED TO SERVICE.

CA091130002

PILATS

PWA  

 

DISPLAY

MALFUNCTIONED

11/27/2009

PC1245

PT6A67B

 

1242102011

AHRU 

(CAN) "ATTITUDE FAIL" FLAG CAME INTO VIEW ON PILOTS NR 1 EADI. UPON SWITCHING TO AHRS NR 2, FLAG WENT AWAY. PILOT SELECTED AHRS NR 1 OVER TO THE CO PILOTS NR 2 , "ATTITUDE FAIL" CAME INTO VIEW ON NR 2 SIDE. UPON RE-SWITCHING, DEFECT WENT AWAY, (INTERMITTENT). PROBLEM RETURNED A WHILE LATER, SAME RESULTS. NR 1 AHRU REPLACED. (TC NR 20091130002)

CA091130004

PILATS

PWA  

 

DEICE SYSTEM

MALFUNCTIONED

11/27/2009

PC1245

PT6A67B

 

 

PROPELLER

(CAN) CREW REPORTED PROP DEICE CAUTION ON A FEW MINUTES AFTER SELECTED. SWITCH RECYCLED A FEW TIMES, CAUTION EVENTUALLY WENT AWAY, NO OTHER CAUTIONS NOTED. PROBLEM COULD NOT BE DUPLICATED AT MAINTENANCE BASE. TESTING OF COMPONENTS DID NOT REVEAL ANY FAULTS. A DIRTY SLIP RING MAY HAVE BEEN THE CAUSE. (TC NR 20091130004)

5APR577Y24

PILATS

PWA  

 

BRAKE DISC

BROKEN

1/9/2010

PC1245

PT6A67B

 

244755

MLG 

DURING A 100 HR INSP, DISCOVERED THE RT BRAKE OTBD DISC WAS BROKEN INTO 2 PIECES. REMOVED AND REPLACED BRAKE ASSY IAW MM INSTRUCTIONS.

5APR577Y25

PILATS

PWA  

 

DRAG LINK

CRACKED

1/9/2010

PC1245

PT6A67B

 

5322012289

NLG DOOR

DURING NDT INSP OF NLG RT DRAG LINK PN 532.20.12.289 IAW AMM 12-A-32-20-06-00A-313A-A AND AD 09-14-13 A CRACK INDICATION WAS DETECTED IN THE PRESCRIBED NDT INSPECTION AREA. REMOVED RT DRAG LINK AND INSTALLED AN UPGRADED DRAG LINK PN 532.20.12.296 IAW SRM AND AD 09-14-13.

5APR577Y23

PILATS

PWA  

 

BRAKE DISC

CRACKED

1/5/2010

PC1247

PT6A67B

 

244755

BRAKE ASSY

DURING A 100 HOUR INSP THE RT BRAKE OTBD DISC WAS DISCOVERED TO BE CRACKED. REMOVED AND REPLACED BRAKE ASSEMBLY IAW MFG MX INSTRUCTIONS.

CA091127007

PIPER

LYC  

 

LEVER

SEPARATED

11/23/2009

PA28140

O320E3D

 

6697900

THROTTLE

(CAN) DURING THE DOWNWIND LEG, PRIOR TO LANDING, THE THROTTLE KNOB UNEXPECTANTLY SEPARATED FROM THE THROTTLE LEVER WHEN THE PILOT SOUGHT TO REDUCE POWER FOR THE DESCENT. THE PILOT WAS ABLE TO CONTINUE THE APPROACH AND LANDING UNEVENTFULLY BY MANIPULATING THE LEVER ARM (WITHOUT THE KNOB). AN EXAMINATION REVEALED THAT THE SCREW THAT ATTACHED THE THROTTLE KNOB TO THE THROTTLE LEVEL BECAME DETACHED, MOST LIKELY DUE TO VIBRATION. THERE IS NO ANCHOR BOLT CALLED FOR IN THE DESIGN. AN INSPECTION OF THE REMAINING FLEET OF THREE CHEROKEES REVEALED TWO WITH LOOSE ATTACHMENT SCREWS. ONE OF THE FOUR CHEROKEES HAD A SECURE ATTACHMENT SCREW. THE AMO PLACE ANCHORING BOLT ON THE ATTACHMENT SCREWS OF ALL AIRCRAFT. HAD SEPARATION OCCURRED ON SHORT FINAL, THE RESULT COULD HAVE BEEN CATASTROPHIC. (TC NR 20091127007)

2010FA0000008

PIPER

 

 

TUBE

CRACKED

12/1/2009

PA28R201

 

 

63547000

RUDDER HORN

INNER PORTION OF RUDDER HORN TUBE (PN 63547-000) CRACKED AT WELD ASSY (PN 63546-000) ON UNDERSIDE OF WELD BEAD. AREA IN QUESTION EXHIBITED SIGNS OF EXCESSIVE WELD PENETRATION ALONG WITH PROJECTING GLOBULES. PROBABLE CAUSE OF CRACK OCCURRED DUE TO WEAKENING OF METAL FROM IMPROPER WELDING TECHNIQUES. TO PREVENT REOCCURRENCE, THE MFG SHOULD RE-EXAMINE THE HEAT RANGE REQUIREMENT IN ORDER TO GAIN PROPER DEPTH OF WELD PENETRATION REQUIRED TO INSURE FISSION OF BASE METAL AND FILLER ROD.

CA091123002

PIPER

LYC  

 

SHAFT

MALFUNCTIONED

11/16/2009

PA31350

LTIO540J2BD

 

40958000

RHEOSTAT

(CAN) AIRCRAFT HAD JUST TAKEN OFF IN THE CLIMB WITH THE AUTOPILOT ON, THE AIRCRAFT PITCHED UP. PILOT DISCONNECTED AUTOPILOT, ELEVATOR TRIM WAS RESTRICTED TO PITCH UP ONLY. THE PILOT DIVERTED TO WINNIPEG WITH REDUCED POWER TO MAINTAIN LEVEL FLIGHT. INSPECTION OF THE TRIM SYSTEM FOUND THE TRIM CABLE DRUM IN THE HORIZ STAB WAS BINDING. THE SHAFT P/N 40958-000 THAT CONNECTS THE ARM P/N 43204-00 FROM THE TRIM DRUM TO THE RHEOSTAT P/N 41229-000 HAD BEEN ALLOWED TO PUSH BACK OUT OF THE ARM AND FALL AND JAM THE TRIM DRUM EXTENDING MORE FOR "UP" TRAVEL ON THE ELEVATOR TRIM. ROOT CAUSE ANALYSIS, ELEVATOR TRIM CABLE WAS REPLACED A FEW MONTHS AGO. THE MECHANISM FROM THE DRUM TO THE RHEOSTAT HAS A TIGHTENING NUT P/N MS20365-832C. THIS NUT WAS FOUND NOT TIGHT ENOUGH TO HOLD THE RHEOSTAT SHAFT IN PLACE, THUS ALLOWING THE SHAFT TO SHIFT SUCH THAT THE ARM MOVED INTO THE TRIM DRUM TRAVEL. REINSTALLED WITH NEW NUT AND NEW RHEOSTAT. (TC 20091123002)

CA091118015

PIPER

PWA  

 

HOUSING

CRACKED

11/17/2009

PA31T2

PT6A135

 

45316003

STRUT

(CAN) DURING THE INSPECTION, WHILE GREASING NOSE LANDING GEAR, MAINTENANCE NOTICED BLISTERING UNDER THE PAINT. MAINTENANCE REMOVED THE BLISTERS, CLEANED-UP THE GREASE AND NOTICED A HAIRLINE FRACTURE ON GEAR STRUT HOUSING ASSY. (TC NR 20091118015)

2010FA0000032

PIPER

LYC  

 

MAGNETO

MISOVERHAULED

11/26/2009

PA32R301

TIO540S1AD

 

D3000

ENGINE

MAGNETO WAS O/H ALONG WITH ENTIRE ENG 150 HRS AGO, 5 YRS CALENDAR TIME. ON A SUCCESSFUL RUN UP, DEPARTING, ENG BEGAN RUNNING VERY ROUGH ABOUT 100 FT ABOVE RUNWAY. ACFT WAS STILL GENERATING ENOUGH CLIMB POWER TO GET UP TO 1,000 FT AND COMPLETE A SAFE LANDING BACK ON THE FIELD. ON LANDING, NOTICED LT MAGNETO DEAD, RT UNEVEN. CALLED SHOP THAT O/H ENG AND MAGNETO, DID NOT KNOW WHY THIS COULD HAVE HAPPENED BUT FELT THE CALENDAR TIME (5 YRS) WAS SIGNIFICANT AND COULD HAVE A FACTOR ON THE BREAKAGE. SHIPPED THE MAGNETO TO FACILITY AND REPLACED A NUMBER OF PARTS, INCLUDING BOTH NYLON DRIVE WHEELS, WHICH HAD SIGNIFICANT TEETH DAMAGE. MECHANIC, WHO HAD SEEN THE INSIDE OF THE MAGNETO, WAS QUITE APPALLED AT THE BURNING OF THE POINTS AND CONDITION OF THE NYLON WHEELS. FELT THE AMOUNT CHARGED AND THE NUMEROUS PARTS THEY REPLACED WAS EXCESSIVE FOR A MAG THAT ONLY HAD 150 HRS ON IT.

2010FA0000002

PIPER

LYC  

LYC  

VERNATHERM

DISTORTED

1/7/2010

PA32RT300

IO540K1G5D

 

53E19600

OIL FILTER ADAPT

AFTER REMOVING THE LT OIL COOLER SUPPLY HOSE AT THE CASE FOR ACCESS TO MAGNETO, IT WAS NOTICED THAT THE NUT OFF THE END OF THE VERNATHERM WAS STUCK IN THE FITTING STICKING OUT OF THE CASE. VERNATHERM WAS REMOVED AND REMAINING PARTS LOCATED. INSPECTED SEAT AREA AND FOUND NO UNUSUAL MARKS. REMOVED AND INSPECTED SUCTION SCREEN AND OIL FILTER ELEMENT. NO UNUSUAL CONTAMINANTS NOTED. THIS HOSE CONNECTION HAD BEEN REMOVED 13 HOURS PREVIOUS FOR OTHER MX AND NO NUT WAS VISIBLE AT THAT TIME. SB 518B APPLIES BY PN, BUT THIS VALVE IS A HIGHER SN THAN THAT SPECIFIED IN THE SB. THIS ENG IS A FACTORY REBUILT 8/27/1994.

E81RJW302236

RAYTHN

 

 

SHUTOFF VALVE

FAILED

1/11/2010

390  

 

 

5188001

RT ANTI-ICE

REPLACED FAILED RT ENG INLET ANTI-ICE SHUTOFF VALVE ASSY WITH "0 TSOH" VALVE. NEWLY O/H VALVE CAUSED VIBRATION FELT THROUGH AIRFRAME, BELIEVED TO BE CAUSED BY RAPID VALVE MODULATION. VALVE O/H WO NR R79693 DATED 10/27/2009. THIS IS THE SECOND RECENTLY O/H VALVE INSTALLED IN LAST MONTH FROM SAME FACILITY THAT HAVE HAD SIMILAR FAILURES UPON INSTALLATION OR SHORTLY THEREAFTER. RECOMMEND MFG O/H FACILITY REVIEW RECORDS TO DETERMINE IF A QUALITY CONTROL/POST-MX TESTING ISSUE, OR IF O/H STANDARDS NEED TO BE REVISED.

2010FA0000000

RAYTHN

GARRTT

 

BEARING

FAILED

12/28/2009

HAWKER800XP

TFE7315BR

 

3587523

TOWER SHAFT

DURING FLIGHT INBOUND, THERE WAS AN IN FLIGHT SHUTDOWN OF THE NR 2 ENGINE. THE ENGINE UNDERWENT A MPI/CZI INSP 80.8 HOURS PRIOR TO THE FAILURE. TEARDOWN INSP REVEALED A FAILURE OF THE UPPER TOWER SHAFT BEARING. THIS WAS AN ORIGINAL BEARING THAT UNDERWENT CZI INSP. BEARING FAILURE CAUSED THE TOWER SHAFT TO SHEAR WHICH THEN CAUSED IT TO DISENGAGE FROM THE TRANSFER GEARBOX. THE LOSS OF ACCESSORY POWER RESULTED IN THE LOSS OF FUEL AND OIL PRESSURE WHICH RESULTED IN ENGINE SHUTDOWN.

2010FA0000010

RAYTHN

 

 

VALVE

MALFUNCTIONED

12/18/2009

HAWKER850XP

 

 

 

HYD SYSTEM

THE ACFT DEPARTED AFTER ROUTINE MX. UPON OPENING THE MAIN AIR VALVES, THE PILOTS NOTICED SMOKE IN THE CABIN, DECLARED AN EMERGENCY AND RETURNED TO THE AIRPORT. INVESTIGATION FOUND HYD FLUID IN THE BLEED AIR DUCTING. DURING SERVICING, HYD FLUID BYPASSED THE NON RETURN VALVE IN THE RT PIPE CONNECTING THE HYD RESERVOIR TO THE BLEED AIR SUPPLY PROVIDING HEAD PRESSURE TOT HE HYD SYSTEM. DURING SUBSEQUENT GROUND RUNS NO SMOKE WAS NOTED. THE ACFT WAS RETURNED TO SERVICE. SITTING OVERNIGHT, THE FLUID MIGRATED INTO THE BLEED AIR SYS. AFTER DEPARTURE, WHEN THE MAV`S WERE OPENED IT ALLOWED THE HOT AIR TO CONTACT THE HYD FLUID AND PRODUCE SMOKE WHICH WAS TRANSFERRED INTO THE CABIN. ALL CONTAMINATED COMPONENTS WERE CLEANED AND REINSTALLED. THE MALFUNCTIONING VALVE WAS REPLACED AS WAS A SERVICING NON RETURN VALVE ON THE RESERVOIR. THE ACFT WAS RETURNED TO SERVICE AND DEPARTED WITHOUT FURTHER INCIDENT.

CA091202014

ROBSIN

LYC  

BENDIX

WIRE

CHAFED

12/1/2009

R44  

O540F1B5

 

 

MAGNETO

(CAN) DURING A FLIGHT THE LOW ROTOR HORN AND LIGHT CAME ON AND THE PILOT LANDED. TROUBLESHOOTING REVEALED FAULTY TACH POINTS. THE MAGNETO WAS REPLACED AND THE DEFECT WAS RECTIFIED. THE MAG WAS INSPECTED AND FOUND A TACH WIRE HAD CHAFED AND SHORTED TO THE OPPOSITE TACH SPADE TERMINAL WHICH WOULD DISRUPT THE RPM SIGNAL TO THE GOVERNOR CONTROLLER. THE WIRING IN THE POINT COMPARTMENT WAS ROUTED IAW TCM SB 663A. (TC NR 20091202014)

CA091202008

ROBSIN

LYC  

 

STARTER

INOPERATIVE

11/15/2009

R44RAVENII

IO540AE1A5

 

14924HTH

ENGINE

(CAN) STARTER WOULD NOT ENGAGE (TC NR 20091202008)

CA091202009

ROBSIN

LYC  

 

PUMP

LEAKING

11/10/2009

R44RAVENII

IO540AE1A5

 

D5001

HYDRAULIC SYS

(CAN) PUMP FOUND LEAKING ON SUCTION SIDE, REPLACED WITH A SERVICABLE PUMP (TC NR 20091202009)

CA091201002

SNIAS

TMECA

 

SWITCH

UNSERVICEABLE

11/30/2009

AS350B2

ARRIEL1D1

 

MS2771923

COLLECTIVE

(CAN) THE HYDRAULIC SYSTEM INCORPORATES A CUT OFF SWITCH ON THE COLLECTIVE, THE HYDRAULIC TEST PUSH BUTTON DID NOT ACTIVATE THE T/R SOLENOID TO CENTER THE T/R PEDALS, THE CIRCUIT BREAKER HAD BLOWN, AND WAS REPLACED, AFTER REPLACEMENT THE CUTOFF COLLECTIVE SWITCH STILL DID NOT WORK, INVESTIGATION SHOWED TO BE A BAD SWITCH, SWITCH WAS REPLACED AND ALL SYSTEMS CHECK AND FOUND NORMAL. (TC NR 20091201002)

CA091202011

SWRNGN

GARRTT

 

RELAY

MALFUNCTIONED

12/1/2009

SA226TC

TPE33110UA

 

6041H205A

GENERATOR

(CAN) CREW ARRIVED AFTER ONE HOUR FLIGHT REPORTING ABNORMAL LT GENERATOR VOLT METER INDICATION. THE GEN FAIL LIGHT FUNCTIONED NORMALLY WITH THE GENERATOR OFF OR ON, HOWEVER, THE GENERATOR WOULD NOT SUPPLY THE BUS, THIS WAS CONFIRMED ON A GROUND RUN CHECK. AFTER SOME INVESTIGATION MAINTENANCE FOUND A BURNT WIRE FROM THE GENERATOR RELAY’S X2 POST (COIL) TO GROUND. THE INSULATION HAD BURNT OFF IT AND ALSO DAMAGED OTHER WIRES IN THE BUNDLE. THE WIRING WAS MODIFIED IN THIS AREA BY AD 97-11-13 AND VARIOUS SERVICE BULLETINS INCORPORATED BY THAT AD. IT WAS DETERMINED THAT THE MOST LIKELY CAUSE WAS THE FAILURE OF THE GENERATOR RELAY, CAUSING THE MAIN CONTACTOR INSIDE TO TOUCH THE GEN FAIL INDICATOR CONNECTIONS ON THE TOP OF THE RELAY. THIS PROVIDED A DIRECT PATH TO GROUND THROUGH THE X2 POST OF THE RELAY AND CAUSED THE BURNT WIRE. THIS RELAY CAN BE REPLACED BY SB 226-24-033, HOWEVER, THAT HAS NOT BEEN ACCOMPLISHED ON THIS AIRFRAME. THE OPERATOR IS ISSUING A NOTICE TO INSPECT ALL AFFECTED AIRFRAMES AT NEXT ACCESS, AND A CAMPAIGN TO REMOVE THE X2 WIRE FROM THE BUNDLE AND ROUTE IT SEPARATELY SO IN THE EVENT OF A FAILURE, THIS WIRE WILL NOT DAMAGE ANY OTHER WIRING. (TC NR 20091202011)

CA091125007

SWRNGN

GARRTT

 

TRUNNION

CORRODED

11/21/2009

SA226TC

TPE33110UA

 

5451001001

NLG 

(CAN) FOUND CORROSION PITTING IN TRUNNION BORES ON BOTH SIDES OF NLG TRUNNION, WHICH HOUSE THE DRAG BRACE PINS. PITTING IS 0.030 INCHES DEEP LONGITUDINALLY IN END OF BORE AND 0.045 INCHES DEEP LATERALLY AT END OF BORE, AROUND THE BORE RADIUS FOR APPROXIMATELY 0.4 INCHES. THERE ARE NO PUBLISHED INSPECTION REQUIREMENTS SPECIFIC TO THIS AREA. (TC NR 20091125007)

CA091125004

SWRNGN

GARRTT

 

TURBINE BLADES

FAILED

11/18/2009

SA227AC

TPE33111U

 

31081251

RT ENGINE

(CAN) A/C CAME IN FOR A ROUTINE FUEL NOZZLE CHANGE ON THE RT ENGINE. THE MECHANIC AT THAT TIME WAS DOING A SCHEDULED BOROSCOPE AND BEFORE PUTTING THE NEW FUEL NOZZLES IN HAD FOUND SOME DISCREPANCIES INSIDE THE ENGINE. THE MECHANIC THEN NOTIFIED THE TURBINE SHOP TO COME AND DO AN EVALUATION ON THE NOTED DAMAGE. THE ENGINE WAS THEN REMOVED AND FORWARDED TO THE ENGINE SHOP FOR REPAIR. THE NOTED DAMAGE WAS FOUND TO BE 3 OF THE 36 TURBINE ROTOR BLADES HAD FAILED AND HAD PIECES OF MATERIAL MISSING FROM THE BLADES. THE FAILED NR 1 TURBINE ROTOR WAS FORWARDED TO A METALLURGICAL LAB FOR EVALUATION ON THE FAILURE. THE METALLURGICAL EVALUATION REPORT WILL BE ADDED TO THIS SDR AT A LATER DATE WHEN RECEIVED. (TC NR 20091125004)

CA091202017

UROCOP

TMECA

 

SPLINE

DISENGAGED

12/1/2009

EC120B

ARRIU2F

 

0319157200

PUMP DRIVE ADAPT

(CAN) FOLLOWING A SCHEDULED ENGINE CHANGE, ENG PRESS WARNING LIGHT CAME ON DURING A TEST FLIGHT. PILOT LANDED WITHOUT INCIDENT. SUBSEQUENT TROUBLESHOOTING REVEALED DISENGAGEMENT OF THE ENGINE OIL PUMP DRIVE ADAPTER FROM PUMP SLINES. DRIVE ADAPTER APPEARS TO HAVE LOST LOCKING FEATURE, HENCE THE DISENGAGEMENT. THE ENGINE ASSEMBLY TSR=0.3 HRS. (TC# 20091202017)

CA091127001

ZLIN

LYC  

 

LINE

BROKEN

11/25/2009

Z242L

AEIO360A1B6

 

Z4253100700

BRAKE

(CAN) THE LEFT BRAKE LINE WAS OBSERVED TO BE BROKEN AT A FLARE END. (TC NR 20091127001)