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

382

bald eagle watching over three eggs

MAY

2010

 


CONTENTS

AIRPLANES

AIRTRACTOR............................................................................................................................. 1

BOEING...................................................................................................................................... 2

CESSNA...................................................................................................................................... 8

EMBRAER................................................................................................................................. 14

LEARJET................................................................................................................................... 16

UNIVAR.................................................................................................................................... 17

HELICOPTERS

SCHWEIZER............................................................................................................................. 17

POWERPLANTS

CONTINENTAL....................................................................................................................... 19

AIR NOTES

INTERNET SERVICE DIFFICULTY REPORTING (iSDR) WEB SITE................................... 20

IF YOU WANT TO CONTACT US......................................................................................... 22

AVIATION SERVICE DIFFICULTY REPORTS...................................................................... 22

 


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

Airtractor:  AT301; Cracked Isolator Mounts; ATA 7120

An unidentified submitter writes, "The engine isolator mounts (P/N 22387) were replaced when the aircraft was restored.  At the first Annual Inspection (with approximately 60 hours total time) these mounts showed excessive cracking and deterioration—requiring replacement.  The lower mounts showed the most amount of wear, with the area around the metal engine mount cracked two-thirds way around, (and there were) pieces missing.  (I) was told by the aircraft owner that he had heard the (rubber) mount composition had recently been changed.  I have no recommendations at this time, other than to closely monitor (these mounts)."


 

CLOSEUP OF CRACKED, RUBBER ISOLATOR MOUNTS.

 

Part Total Time:  60.0 hours

 

Boeing: 747-281F; Cracked Door Doubler; ATA 5210

A very short submission from an unknown source writes, "The main entry door's number one upper outer skin doubler (has a) crack 0.35 inches at the upper hinge door (mount)."


PHOTO OF CABIN ENTRY DOOR AND CLOSEUP OF HINGE POINT.


 

PARTS DRAWING OF DOOR DOUBLER.


(No part numbers were provide with this report.)

Part Total Time:  101,362 hours

 

Boeing:  747-281F; Cracked Horz. Stabilizer Hinge Fitting; ATA 5551

The previous submitter provides another discrepancy report stating, "The L/H and R/H horizontal stabilizer hinge fitting had two cracks each:  0.8 and 0.9inches, and 0.85 and 1.1 inches, (respectively)."

PARTS DRAWING OF HORIZONTAL STABILIZER HINGE FITTING.


PHOTO OF L/H HINGE FITTING AND CLOSEUP PHOTO OF L/H HINGE FITTING.


 

CLOSEUP PHOTO OF L/H HINGE FITTING AND CLOSEUP PHOTO OF R/H HINGE FITTING.

(No part numbers were provide with this report.)

Part Total Time:  101,362 hours

 


Cessna:  402C, 414A, 421C; Cracked Main Gear Trunnion; ATA 3213

(The Wichita Aircraft Certification Office provides the following safety admonition.  Contact information follows the discussion.)

The FAA has received a Safety Recommendation (09.385) suggesting an Airworthiness Directive be issued for non-destructive inspections on Cessna landing gear (P/N 5141103), effecting models 402C, 414A, and 421C.  This recommendation stems from a Cessna 402C gear failure in August 2009 (photos attached).

Cessna is working to develop Supplemental Inspection Documents (SID; number 32-10-05) for these specific aircraft.  They have developed a surface eddy current process to inspect for cracks on the main gear (upper barrel), targeting both the actuator and upper torque link attachment fittings (photo 3).  The crack initiating this failure can just be seen in the last picture—an internal view of the gear cylinder where this kind of defect may first be detected.  The Cessna inspection requirement is expected to be available by August, 2011.  It is scheduled to be accomplished at 5,000 landings, and thereafter at each 2,000 landings.

The gear failure depicted below occurred on an airplane estimated to have 30,000 landing cycles during 12,000 hours of flight time.  Search of the FAA's Service Difficulty Reporting System (SDRS) database generated 28 failed gear reports (for these models) in a production fleet of 2,290 airplanes.  Model 402C alone produced 21 of these reports—681 of these aircraft were built between 1979 and 1985.

Photo 1:  Cessna 402C with a collapsed main landing gear.

PHOTO OF THIS AIRCRAFT WITH A COLLAPSED R/H MAIN GEAR STRUT.


Photo 2:  Gear strut removed from airplane (P/N 51401103).

PHOTO OF BROKEN GEAR STRUT.

 


Photo 3:  The same part removed from another airplane, illustrating a crack that may be found during an inspection.

PHOTO OF A SIMILAR, CRACKED GEAR STRUT.

 


Photo 4:  An internal view of the above part showing initial crack development.

PHOTO OF AN INTERNAL VIEW OF A CRACKED GEAR STRUT.

 

(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)

 

Cessna:  680CE; Vertical Stabilizer Spar Corrosion; ATA 5531

An unidentified general aviation technician states, "During replacement of the rudder hinge brackets on the vertical stabilizer's rear spar (P/N 693101222), exfoliation corrosion was found on the 1)  lower bracket (P/N 6931050-10) of the upper rudder hinge point; and 2)  on the lower bracket (P/N 693105012) and upper bracket (P/N 6931050-11) of the middle rudder hinge point.  Exfoliation corrosion was also noted on the vertical stabilizer aft spar stiffener (P/N 65931012-22) at approximate water line WL 190.763.  (This stiffener) required replacement."


 

TWO PHOTO VIEWS IN 1: AREAS OF CORROSION ON STABILIZER SPAR.


 

FIVE PHOTO VIEWS IN 1: AREAS OF CORROSION ON STABILIZER SPAR.

 

FIVE PHOTO VIEWS IN ONE: AREAS OF CORROSION ON STABILIZER SPAR.


 

THREE PHOTO VIEWS IN ONE: AREAS OF CORROSION ON STABILIZER SPAR.

 

Part Total Time:  3,856.0 hours

 

Embraer:  145EP; Broken Bolts in Rudder PCU; ATA 2720

Another unidentified submitter says, "The pilot reported a number two Low Quantity on the EICAS (engine indicating crew alert system) while on the ground.  Maintenance inspected and found the rudder power control unit (PCU) to be leaking.  (This unit) was removed and replaced in accordance with EMB 145 Maintenance Manual 27-22-03.  It operationally and leak checked good.  (We) serviced the number two hydraulic system IAW EMB 145 AMM 12-13-01.  The aircraft was returned to service.  The (defective) rudder PCU was missing (several) bolt (heads)—causing the leakage."  (The SDRS database includes ten of these PC units, none but this one having a reported bolt problem!)


 

PHOTO OF TOP VIEW OF POWER CONTROL UNIT.


 

PHOTO OF SIDE VIEW OF POWER CONTROL UNIT.

 

(The PCU is from Parker-Hannifin.  Great photos; but very scary scenario!  I wish you would have speculated as to why this might have occurred.  For example:  if those steel bolts thread into an aluminum casting, we could probably rule out over-torque as an issue--right?  Or, are there nut plates on the other side? Might the bolts, then, be defective?  Have you seen this before?  Would 24,000 hours indicate an extreme bolt life for this application?  Have the bolts and/or the PCU been flagged for any kind of failure analysis?  Please keep me informed of any similar PCU events via e-mail on the Alerts address page.  Thank-you—Ed.)

Part Total Time:  23,982.0 hours

 

Learjet:  60; Undersized Spoileron Bearings; ATA 2760

A general aviation submitter writes, "New spoileron bearings (P/N AA401-12) that were ordered (for this aircraft) were received with their outside diameter below the tolerance listed in the SRM (structural repair manual)—causing a loose fit when installed.  The SRM (calls for) 0.4400 inch outside diameter, with no tolerance allowed.  All bearings received have measured 0.438 inches."  "Reference Learjet 60 SRM:  51-71-03, page 1 and 2, item 12."

Part Total Time:  7,291 hours (aircraft)

 


Univar:  415-C; Sheared Brake Clevis; ATA 3240

"On landing," says this general aviation technician, "(this aircraft) lost braking action.  An investigation found the brake piston clevis rod—between the brake pedal arm and the master cylinder—had sheared below the lock nut."  (Piston clevis rod P/N:  4008.  Component name and P/N: Brake Arm; 41533458.  See photo below.)

 

CLOSEUP PHOTO OF BROKEN CLEVIS.

 

Part Total Time:  617.0 hours

 

HELICOPTERS

Schweizer:  269C; Cracked Support Strut; ATA 5302

"During unscheduled maintenance," states an unidentified general aviation technician, "the lower drive support strut (P/N 269A5423009) was found to be cracked 90 per cent through the tube—where the upper attach lug is welded.  Upon removal, the lug completely separated from the tube.  If this tube had separated during flight, loss of main rotor torque would have occurred."


 

CLOSEUP PHOTO OF CRACKED STRUT.

 

CLOSEUP PHOTO OF CRACKED STRUT PIECE.

 


(Okay....  That is scary!—Ed.)

Part Total Time:  6,527 hours

 

POWERPLANTS

Continental:  IO-550-N25; Cracked Cylinder Head; ATA 8530

A Chief Inspector for a repair station says, "During an Annual Inspection, (we) found a fuel stain trailing from the fuel injector nozzle port toward the spark plug hole on number three cylinder (P/N 655465).  This cylinder has 980.9 hours since new.  The engine was manufactured in July of 2003.  It was installed in this Lancair 550FG in August 2003 by the Lancair company."

 

CLOSEUP PHOTO (1) OF CRACKED CYLINDER HEAD.


 

CLOSEUP PHOTO (2) OF CRACKED CYLINDER HEAD.

 

(See March Alerts for similar report—Ed.)

Part Total Time:  980.9 hours

 

AIR NOTES

INTERNET SERVICE DIFFICULTY REPORTING (iSDR) WEB SITE

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


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

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

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

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

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

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

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

The SDRS and iSDR web site point of contact is:

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

 


IF YOU WANT TO CONTACT US

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

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

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

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

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

 

AVIATION SERVICE DIFFICULTY REPORTS

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

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

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

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


Federal Aviation Administration

Service Difficulty Report Data

 

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

Control Number

Aircraft Make

Engine Make

Component Make

Part Name

Part Condition

Difficulty Date

Aircraft Model

Engine Model

Component Model

Part Number

Part Location

2010FA0000297

 

 

 

BEARING

FAILED

4/7/2010

 

 

RR12670F

RB56637

BOOSTER PUMP

DURING OVERHAUL OF THE CENTRIFUGAL FUEL BOOSTER PUMP 2 NEW ARMATURE SHAFT BEARINGS (PN: RB56637) WERE INSTALLED. ABOUT AN HOUR INTO THE BRUSH RUN-IN SEQUENCE, AN UNUSUAL NOISE WAS HEARD. THE NOISE WAS TRACED TO THE 2 NEWLY REPLACED BRGS. THE BRGS WERE SUBSEQUENTLY REMOVED FROM THE PUMP AND FOUND TO HAVE SOME ROUGHNESS.

COEA2010042107901

AEROSP

 

 

INTERCOSTAL

CORRODED

4/21/2010

ATR42320

 

 

S53371252200

FUSELAGE

HEAVY CK COE: LEVEL 2 CORROSION: LT STR 12A INTERCOSTAL BETWEEN FR 18 & 19 NEAR FORWARD CARGO DOOR IS CORRODED. INTERCOSTAL WAS REMOVED AND REPLACED PER ATR SRM.

2010FA0000298

AGUSTA

 

 

BLADE

CRACKED

3/19/2010

A109A

 

 

109010301115

MAIN ROTOR

(JBZR) DURING PILOT PRE-FLIGHT INSP, FOUND APPROX (1) 2.5 INCH LONG DELAMINATION AND A (2ND) .7500 INCH LONG DELAMINATION OF THE END PLIES OF ONE MAIN ROTOR BLADE, ALONG THE BLADE TIP END.

2010F00074

AIRBUS

RROYCE

 

OIL FILTER

DEBONDED

3/25/2010

A330300

RB211TRENT77

 

QA07168

ENGINE

ENGINE OIL PRESSURE FILTER RESIN DE-BONDING: DURING THE ROUTINE INSP PROCESS (IAW AMM 79-22-43, PG BLOCK 701) OF ENGINE OIL PRESSURE FILTERS, PN QA07168, DE-BONDING OF THE RESIN SECURING THE FILTER END-CAPS TO THE FILTER MEDIA WERE FOUND. TESTING OF THE UNITS SHOWED THAT THEY FAILED THE MFG TEST CRITERIA. THE DE-BONDING IS LIMITED TO FILTERS WITH SN BEGINNING RT3-. A NEW UNUSED FILTER, SN RT3-4146 HAS BEEN INSPECTED AND DE-BONDING OF EQUAL MAGNITUDE TO THAT OF USED FILTERS WAS RECORDED.

2010FA0000341

AIRTRC

PWA   

 

ISOLATOR

SPLIT  

4/14/2010

AT301

R1340*

 

22378

ENGINE MOUNT

ENGINE ISOLATOR MOUNTS PN 22387 WERE REPLACED WHEN ACFT RESTORED. FIRST ANNUAL AFTER INSTALLATION WITH APPROX 60 HRS TIS MOUNTS SHOWED EXCESSIVE CRACKING AND DETERIORATION REQUIRING REPLACEMENT. LOWER MOUNTS SHOWED THE MOST AMOUNT OF WEAR WITH THE AREA AROUND THE METAL ENGINE MOUNT CRACKED 2/3 THE WAY AROUND, AND PIECES MISSING. WAS TOLD BY ACFT OWNER, HE HAD HEARD THE MOUNT COMPOSITION HAD RECENTLY BEEN CHANGED. NO RECOMMENDATIONS AT THIS TIME OTHER THAN TO CLOSELY MONITOR.

2010FA0000284

AMD   

 

 

NONE

NONE

3/15/2010

FALCON900

 

 

 

NONE  

(JGVR) THESE CONTROL COLUMNS WERE REMOVED FOR ACCESS FOR AN EPIC INSTALLATION. UPON REINSTALLATION, IT WAS NOTICED THAT IF THE AILERON PUSH-PULL TUBE BOLT IS INSTALLED IAW ILLUSTRATION IN THE MM AND THE IPC. THE THREADS FROM THE BOLT WILL CONTACT THE CONTROL COLUMN CABLE. TECHS STATE THAT THEY HAVE SEEN THIS CONDITION ON ANOTHER OCCASION. PUSH-PULL TUBE ROD WAS ROTATED 180 DEGREES AND CHECKED FOR CLEARANCEES AT BOTH ROD ENDS. NO CLEARANCE ISSUES AT THIS TIME. MM AND PARTS CATALOG SHOULD BE UPDATED TO REFLECT PROPER CONTROL ROD FIXED NUT PLATE POSITION.

2010FA0000386

AMTR

LYC   

 

CARBURETOR

DEFECTIVE

4/16/2010

RV7A

O360A1A

 

AVXIO41641

ENGINE

PARTIAL LOSS OF POWER ON DEPARTURE AT 1,000` AGL. AFTER RETURNING TO LAND, ENGINE ROUGHNESS INCREASED. DURING TAXI IN, MAX ATTAINABLE RPM WAS 900. MECHANIC TROUBLESHOT AND DETERMINED THE PROBLEM TO BE FUEL STARVATION. FUEL SUPLY TO THE CARBURETOR WAS NORMAL AND ALL ENG CONTROLS FUNCTIONED NORMAL, PROMPTING THE DISASSEMBLY OF THE CARBURETOR. INTERMAL INSP REVEALED AN ANSWER. THE BOSS IN THE BOTTOM OF THE CARBURETOR WHICH RECEIVES THE MIXTURE SHAFT HAD ROTATED COUNTER-CLOCKWISE IN THE HSG. THIS PRODUCED THE SAME EFFECT AS PULLING THE MIXTURE CONTROL KNOB. LUCKILY, WAS CLOSE TO AN AIRPORT AND ABLE TO MAKE AN EMERGENCY RETURN.

2010FA0000391

AMTR

 

 

HOSE

FAILED

4/19/2010

TURBINLEGEND

 

 

 

HYD SYSTEM

ON APPROACH THE PILOT SELECTED GEAR DOWN AND DID NOT DOWN AND LOCKED LIGHT ON NOSE GEAR, GEAR WAS RECYCLED AND NOSE LANDING GEAR DID NOT INDICATE SAFE. EMERGENCY EXTENSION SYSTEM ACTIVATED AND STILL NO SAFE INDICATION. AIRCRAFT LANDED WITH GEAR PARTIALLY EXTENDED. POST LANDING INSPECTION REVEALED THAT ELECTRIC HYDRAULIC PUMP WAS NOT FUNCTIONING. HIGH PRESSURE HYDRAULIC HOSE EXITING PUMP FAILED DUE TO UNKNOWN REASON (HOSE WAS NOT IDENTIFIED BY PART NUMBER AND CURE DATE NOT ON THAT SECTION OF HOES) AND HYDRAULIC SYSTEM DEPLETED OF FLUID

2010FA0000277

BEECH

PWA   

 

OIL FILTER

SPLIT  

3/31/2010

200BEECH

PT6A42

 

302925701

ENGINE

DURING A 200 HR OIL FILTER INSP, THE ENGINE OIL FILTER INTERNAL FINGER SCREEN "CONE" WAS FOUND SPLIT AT THE WELDED OR SOLDERED JOINT.

2010F00078

BEECH

PWA   

 

OIL FILTER

SPLIT  

3/31/2010

200BEECH

PT6A60A

 

302925701

ENGINE

DURING A 200 HOUR OIL FILTER INSP THE ENGINE OIL FILTER INTERNAL FINGER SCREEN "CONE" WAS FOUND SPLIT AT THE WELDED OR SOLDIERED JOINT.

2010FA0000296

BEECH

LYC   

 

LINE

SPLIT  

4/7/2010

95   

AEIO360*

 

 

ENGINE OIL

DURING FLIGHT, SHUTDOWN THE RT ENGINE DUE TO OIL LOSS. AN INITIAL ASSESSMENT OF THE CAUSE WAS DUE TO THE ONE OF THE OIL LINE FROM THE OIL COOLER APPEARED TO SPLIT WHERE IT WAS ROUTED TO CLOSE TO AN EXHAUST MANIFOLD.

2010FA0000418

BEECH

CONT

CONT

EXHAUST VALVE

BROKEN

4/28/2010

A36   

IO550B

IO550B14B

646286

NR 2 CYLINDER

AIRCRAFT EXPERIENCED POWER LOSS, VIBRATION, AND LOW NR 2 EGT. ON INSPECTION THE NR 2 CYLINDER EXHAUST VALVE WAS FOUND TO BE MISSING ABOUT HALF OF IT'S FACE

2010FA0000281

BEECH

LYC   

 

FUEL NOZZLE

FOD   

12/15/2009

A36   

TIO540J2BD

 

GLT20628540GI

FUEL SYSTEM

(HOQR) ENGINE WOULD NOT MAKE RATED POWER AND WAS ROUGH RUNNING ONCE ACFT WAS OF THE GROUND. TROUBLESHOT ISSUE AND FOUND IT TO BE FOREIGH OBJECTS ON THE AIR SIDE OF THE FUEL INJECTOR NOZZLES. THE FOREIGH OBJECTS APPEARED TO BE O-RING MATERIAL INTRODUCED THRU THE INSTALLATION OF THE COLLARS OVER THE FUEL INJECTOR NOZZLES. A RE-DESIGNED COLLAR AND NEW FUEL INJECTOR NOZZLES WERE SENT. REPLACEMENT OF THE FUEL INJECTOR NOZZLES CORRECTED THE ISSUE.

2010FA0000280

BEECH

LYC   

 

WASTEGATE VALVE

LEAKING

12/15/2009

A36   

TIO540J2BD

 

LW12778X

TURBOCHARGER

OIL LEAKING FROM WASTEGATE ACTUATOR SHAFT. R & R WASTEGATE WITH A SECOND O/H UNIT. SECOND WASTEGATE ALSO LEAKED OUT THE ACTUATOR SHAFT. CHECKED INSTALLATION AND FOUND IT TO BE INSTALLED IAW STC NR SA 762NW INSTALLATION INSTRUCTION 68-1, DATED MAY 1, 1979, AND DWG 68-10021. REASEARCHED ORIGINAL INSTALL OF THIS ENGINE AND MFG WIDE CYLINDER FLANGE MM AND THERE IS NO REF TO ROUTING THE WASTEGATE VENT LINE BACK TO THE CRANKCASE. IT WAS SUGGESTED TO RELOCATE VENT TUBE FROM CRANKCASE AND ROUT IT TO BE VENTED OVERBOARD. ONCE THIS WAS DONE THE OIL LEAK FROM THE ACTUATOR WENT AWAY. UPON CONTACTING STC HOLDER WITH THIS INFO, THEY ARE NOT WILLING TO APPROVE ANY CHANGE TO THE DESIGN.

2010F00086

BEECH

 

BEECH

FASTENER

MISSING

4/6/2010

B300

 

 

 

FRAME

DURING A PHASE 3 AND 4 INSP MISSING RIVETS WERE DISCOVERED AT STA 100.5 ON THE LOWER FUSELAGE FRAME 128-555148-605 UNDER THE COPILOTS FLOORBOARDS JUST AFT OF THE RUDDER PEDALS. THE 4 MISSING RIVETS WERE SUPPOSE TO ATTACH THE FRAME TO AN OTBD CLIP. THERE WAS NO INDICATION THAT THE RIVETS WERE EVER INSTALLED AND MORE THAN LIKELY WERE MISSED DURING PRODUCTION OF THE ACFT.

2010FA0000383

BEECH

 

 

GASKET

OUT OF POSITION

4/3/2010

C23   

 

 

CP0711

INTAKE

GASKET IS OUT OF PLACE AND IS BEING INGESTED INTO INTAKE.

2010FA0000384

BEECH

 

 

GASKET

OUT OF POSITION

4/3/2010

C23   

 

 

CP1150

INTAKE

GASKET IS OUT OF PLACE AND IS BEING NGESTED INTO INTAKE.

2010FA0000339

BEECH

CONT

 

CIRCUIT BREAKER

FAILED

4/14/2010

F33A

IO520*

 

35380132103

EXTERIOR LIGHTS

(VJ3S) NO POWER THROUGHT THE C/B SWITCH. INTERNAL FIALURE.

2010FA0000290

BEECH

CONT

 

CIRCUIT BREAKER

FAILED

4/5/2010

F33A

IO520BB

 

35380132103

TAXI LIGHT

(VJ3R) PILOT REPORTED TAXI LIGHT INOP. ON TROUBLESHOOTING, TECH FOUND CIRCUIT BREAKER/SWITCH TO BE AT FAULT. AD 2008-13-17 HAD BEEN COMPLETED 1319 FLIGHT HOURS PRIOR AND ESTIMATED CYCLES 5276. NOTICED NEW CIRCUIT BREAKER. NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME.

2010FA0000291

BEECH

CONT

 

CIRCUIT BREAKER

FAILED

4/5/2010

F33A

IO520BB

 

35380132103

TAXI LIGHT

(VJ3R) PILOT REPORTED TAXI LIGHT INOP. ON TROUBLESHOOTING, TECH FOUND CIRCUIT BREAKER/SWITCH TO BE AT FAULT. AD 2008-13-17 HAD BEEN COMPLETED 1072 FLIGHT HOURS PRIOR AND ESTIMATED CYCLES 4288. NOTICED NEW CIRCUIT BREAKER. NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME.

2010FA0000292

BEECH

CONT

 

CIRCUIT BREAKER

FAILED

4/5/2010

F33A

IO520BB

 

35380132103

TAXI LIGHT

(VJ3R) PILOT REPORTED TAXI LIGHT INOP. ON TROUBLESHOOTING, TECH FOUND CIRCUIT BREAKER/ SWITCH TO BE AT FAULT. AD 2008-13-17 HAD BEEN COMPLETED 1271 FLIGHT HOURS PRIOR AND ESTIMATED CYCLES 5084. NOTICED NEW CIRCUIT BREAKER. NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME.

2010FA0000293

BEECH

CONT

 

CIRCUIT BREAKER

FAILED

4/5/2010

F33A

IO520BB

 

35380132103

TAXI LIGHT

(VJ3R) PILOT REPORTED TAXI LIGHT INOP. ON TROUBLESHOOTING TECH FOUND CIRCUIT BREAKER/SWITCH TO BE AT FAULT. AD 2008-13-17 HAD BEEN COMPLETED 859 FLIGHT HOURS PRIOR AND ESTIMATED CYCLES 3436. NOTICED NEW CIRCUIT BREAKER. NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME.

2010FA0000288

BEECH

CONT

 

PUMP

LOW PRESSURE

4/4/2010

F33A

IO520BB

 

AA3216CW

 

(VJ3R)ON PHASE RUN UP MECHANIC NOTICED THE GYRO WARNING LIGHT ON. UP ON TROUBLESHOOTING THE MECHANIC DETERMINED THE VANES ON THE AIR PUMP WERE WORN AND WAS NOT PRODUCING ENOUGH PRESSURE. INSTALLED NEW PUMP, SYS WORKED NORMAL. NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME.

2010FA0000294

BEECH

CONT

 

CIRCUIT BREAKER

FAILED

4/5/2010

F33A

IO520BB

 

35380132103

CABIN

(VJ3S) PILOT REPORTED LANDING LIGHT INOP. ON TROUBLESHOOTING, TECH FOUND CIRCUIT BREAKER/ SWITCH TO BE AT FAULT. AD 2008-13-17 HAD BEEN COMPLETED 1500 FLIGHT HOURS PRIOR AND ESTIMATED CYCLES 6000. NOTICED NEW CIRCUIT BREAKER. NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME.

2010FA0000340

BEECH

CONT

 

CIRCUIT BREAKER

FAILED

4/14/2010

F33A

IO520BB

 

58380132103

LANDING LIGHT

(VJ3S) PILOT REPORTED LANDING LIGHT INOP. ON TROUBLESHOOTING TECH FOUND CIRCUIT BREAKER/ SWITCH TO BE AT FAULT AD 2008-13-17 HAD BEEN COMPLETED 1248 FLIGHT HOURS PRIOR AND ESTIMATED CYCLES 4992. NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME.

2010FA0000295

BEECH

 

 

ROD END

CRACKED

4/2/2010

F35   

 

 

HM5S  

NLG  

NOSE GEAR RETRACT ASSY ROD END FAILED. IT APPEARED THAT THE ROD END HAD BEEN CRACKED AND THE CRACK WAS NOT DETECTED DURING LAST ANNUAL INSP. THE ROD END FAILED AND THE NOSE GEAR FOLDED UP ON LANDING CAUSING DAMAGE TO THE NOSE OF THE ACFT AND PROPELLER. THE ROD END IS IN A DIFFICULT POSITION TO INSPECT AND THE CRACK MAY BE HARD TO DETERMINE.

FOTR20006NR4888

BOEING

 

 

NOSE COWL

GOUGED

1/28/2010

7272A1

 

 

65196854141

ZONE 400

NR 3 ENGINE NOSE COWL AT 4 O`CLOCK POSITION T/E GOUGED. REPAIRED ON FASI WO 20006, N/R 04888. REPAIRED NR 3 ENGINE NOSE COWL T/E AT 4 O’CLOCK POSITION IAW B727 SRM 54-10-3 FIG 3, REV 102. MATERIAL USED: ANGLE; 2024-T3, 0.063, DIM: 10.0 BY 2.0, FILLER; 2024-T3, 0.050, DIM: 1.50 BY 0.750, SHIM; 2024-T3, 0.050, DIM: 1.0 BY 1.125. CUT OUT DIM: 1.50 BY 0.750.

FOTR20006NR1971

BOEING

 

 

SHEAR TIE

CRACKED

2/5/2010

7272A1

 

 

6515937

ZONE 200

STA 600 STR 16L SHEAR TIE CRACKED. REPAIRED ON FASI W/O NR 20006, NR 01971, REPLACED CRACKED SHEAR TIE AND DOUBLER AT BS 680, STR 16L IAW B727 SRM 53-20-2 FIG 3 AND 53-10-4 FIG 11, REV 102. MATERIAL USED: 7075-O, HEAT TREATED TO T6 CONDITION. DIM.; DOUBLER; 6 BY 5 BY 0.050, SHEAR TIE; 6 BY 21 BY 0.050.

FOTR20006NR5222

BOEING

PWA   

BOEING

SPAR

DAMAGED

1/29/2010

7272A1

JT8D17R

 

 

ZONE 300

C/W AD2008-17-14 SB 727-55-0089 ELEVATOR REAR SPAR AT THE TAB HINGE LOC. IAW PARA (A) REPLACEMENT OF THE ELEVATOR REAR SPAR AND SUPPORT FITTING IAW PART 2 OF S/B 727-55-0089 REV 1 (RT). REPAIRED ON FASI WO 20006. N/R 05222- R & R ELEVATOR REAR SPAR AND SUPPORT FITTINGS AT RT SIDE WITH KIT PN: 65C37663-2 IAW S/B 727-55-0089 REV 1, DATED 3/2/2000. ACCOMPLISHED WEIGHT AND BALANCE, NEW MOMENT 120.9 IN. LBS WITHIN LIMITS.

FOTR20006NR4709

BOEING

PWA   

 

STIFFENER

CORRODED

1/27/2010

7272A1

JT8D17R

 

6915768

ZONE 100

(FOTR) CORROSION AT 227.8 BULKHEAD, BL 0 SKIN INTERIOR, JUST AFT OF EQUIPMENT BAY ACCESS DOOR. REPAIRED ON FASI WO 20006. N/R 04709- R & R DAMAGED STIFFENER AT BL 0 STA 227.8 IAW SRM 51-30-2, 53-10-1 FIG. 1, REV 102 AND DWG 69-15768. MATERIAL USED: 7075-T6, 0.063", DIM.; 9.0" X 7.9".

2010FA0000345

BOEING

GE   

 

STIFFENER

CRACKED

4/15/2010

747281F

CF650E2

 

 

NR 2 PYLON

PYLON NR 2 INBD NR 3 STIFFENER CRACK 0.67 INCH BETWEEN NAC STA 248 AND NAC STA 259 ON THE RT SIDE.

2010FA0000346

BOEING

GE   

 

HINGE FITTING

CRACKED

4/15/2010

747281F

CF650E2

 

 

HORIZONTAL STAB

HORIZ STABILIZER LT 2 PLACES 0.9 INCH AND 0.8 INCH & RT 2 PLACES 1.1 INCH AND 0.85 INCH, HINGE FITTING CRACKED.

2010FA0000343

BOEING

GE   

 

DOUBLER

CRACKED

4/15/2010

747281F

CF650E2

 

 

ZONE 800

MAIN ENTRY DOOR NR 1 UPPER OUTER SKIN DOUBLER CRACK, 0.35 INCH AT UPPER HINGE DOOR.

2010FA0000344

BOEING

GE   

 

SKIN

CORRODED

4/15/2010

747281F

CF650E2

 

 

ZONE 100

FWD CARGO LOWER FUSELAGE SKIN AT STA 1000 WAS CORRODED LEVEL 2.

2010FA0000342

BOEING

GE   

 

STIFFENER

CRACKED

4/15/2010

747281F

CF650E2

 

 

NR 1 PYLON

PYLON NR 1, INBD NR 3, STIFFENER CRACK.

2010FA0000359

BOEING

 

 

SKIN

WORN

8/8/2008

7472B5F

 

 

65B904483

PYLON

(KADY) WEAR DAMAGE WAS FOUND ON THE CAP SKIN OF THE NR 1 PYLON AT NAC STA 210.00-221.90 WL 187.63-190.60.

2010FA0000360

BOEING

 

 

SKIN

WORN

8/8/2008

7472B5F

 

 

65B904483

PYLON

(KADY) WEAR DAMAGE WAS FOUND ON THE CAP SKIN OF THE NR 4 PYLON AT NAC STA 210.00-221.90 NAC WL 187.63-190.68.

2010FA0000331

BOEING

 

 

SEAT TRACK

CORRODED

7/12/2008

7472B5F

 

 

 

FUSELAGE

(KADY) CORROSION AT SEAT TRACK BS 1500, RBL 98.58. MAJOR REPAIR ACCOMPLISHED BY BLEND OUT OF CORROSION AND FABRICATE AND INSTALL A REPAIR STRAP.

2010FA0000333

BOEING

 

 

COWLING

DELAMINATED

7/17/2008

7472B5F

 

 

 

NR 2 ENGINE

(KADY) DELAMINATION ON THE NR 2 ENG NOSE COWL. MINOR REPAIR ACCOMPLISHED BY FABRICATE REPAIR DOUBLER, STRAP AND CURE AFTER BOND.

2010FA0000355

BOEING

 

 

SKIN

CORRODED

7/1/2008

7472B5F

 

 

 

PYLON

(KADY) CORROSION AT NR 1 PYLON OTBD CAP SKIN. MINOR REPAIR ACCOMPLISHED BY BLEND OUT THE CORROSION AND APPLY FINISH TREATMENT.

2010FA0000356

BOEING

 

 

SEAT TRACK

WORN

7/9/2008

7472B5F

 

 

 

CABIN

(KADY) ENLARGE THE MAIN DECK SEAT TRACK PIN HOLE AT SEC 42. MAJOR REPAIR ACCOMPLISHED BY OVERSIZE REAM AND INSTALL FREEZE PLUG BUSH.

2010FA0000353

BOEING

 

 

SKIN

WORN

6/9/2008

7472B5F

 

 

65B007263

COWLING

(KADY) WORN AT OUTER SKIN AND STIFFENER OF NR 4 LT SIDE COWL. MONOR REPAIR ACCOMPLISHED BY TRIM OUT THE DAMAGED SKIN AND STIFFENER AND INSTALL REPAIR DOUBLER.

2010FA0000352

BOEING

 

 

SKIN

PUNCTURED

6/9/2008

7472B5F

 

 

65B9155715

COWLING

(KADY) PUNCTURE OF NR 4 ENGINE LT SIDE FAN COWL INNER SKIN. MINOR REPAIR ACCOMPLISHED BY TRIM OUT THE DAMAGED SKIN AND INSTALL FILLER AND REPAIR DOUBLER.

2010FA0000354

BOEING

 

 

FLOORBEAM

CRACKED

6/24/2008

7472B5F

 

 

34065B10927529

FUSELAGE

(KADY) CRACK AT FLOORBEAM WEB AT UPPER DECK BS 340, 400, AND 500. MAJOR REPAIR ACCOMPLISHED BY TRIM OUT THE CRACKED FLOORBEAM AND INSTALL REPAIR FILLER AND REPAIR DOUBLER.

2010FA0000350

BOEING

 

 

FAIRING

CRACKED

5/23/2008

7472B5F

 

 

65B9007113

SLOT SEAL

(KADY) NR 1, 3 AND 4 ENG SLOT SEAL FAIRING FASTENER HOLES WORN. MINOR REPAIR ACCOMPLISHED BY OVERSIZE, THE AFFECTED HOLES AND INSTALL NEW GROMMET ASSY.

2010FA0000351

BOEING

 

 

SKIN

WORN

6/10/2008

7472B5F

 

 

65B007263

FUSELAGE

(KADY) WORN AT OUTER SKIN AND FLANGE OF FRAME. MINOR REPAIR ACCOMPLISHED BY TRIM OF DAMAGED SKIN AND FRAME AND INSTALL FILER AND REPAIR ANGLE AND REPAIR DOUBLER.

2010FA0000357

BOEING

 

 

FLOORBEAM

DAMAGED

8/5/2008

7472B5F

 

 

 

FUSELAGE

(KADY) AN ELONGATED FASTENER HOLE WAS FOUND ON THE UPPER DECK FLOORBEAM UPPER CHORD AT STA 380, LBL 22/12.

2010FA0000358

BOEING

 

 

FRAME

CRACKED

8/5/2008

7472B5F

 

 

 

FUSELAGE

(KADY) A CRACK WAS FOUND ON THE FRAME AT STA 1680, S13R-S14R.

2010FA0000332

BOEING

 

 

SEAT TRACK

WORN

7/14/2008

7472B5F

 

 

 

CABIN

(KADY) ENLARGE THE MAIN DECK SEAT TRACK PIN HOLE AT SEC 44 AND 46. MAJOR REPAIR ACCOMPLISHED BY OVERSIZE REAM AND INSTALL FREEZE PLUG BUSH.

2010F00082

BOEING

 

 

FRAME

CRACKED

1/14/2010

7472B5F

 

 

65B0250284

BS 2598 BULKHEAD

(KADY) CRACK AT FLANGE OF INNER CHORD OF BS 2598 BULKHEAD. MAJOR REPAIR ACCOMPLISHED BY TRIM OUT THE CRACKED CHORD AND INSTALL REPAIR PART INCLUDING SPLICE ANGLE.

2010F00083

BOEING

 

 

SKIN

CORRODED

7/1/2008

7472B5F

 

 

 

NR 4 PYLON

(KADY) CORROSION AT NR 4 PYLON OTBD CAP SKIN. MINOR REPAIR ACCOMPLISHED BY BLEND OUT THE CORROSION AND APPLY FINISH TREATMENT.

2010F00079

BOEING

 

 

SKIN

CRACKED

1/13/2010

7472B5F

 

 

65B007264

NR 3 NACELLE

(KADY) CRACK WAS FOUND ON THE SKIN OF THE NR 3 ENGINE RT SIDE COWL AT NAC STA 225.95.

2010F00084

BOEING

 

 

SKIN

CRACKED

6/30/2008

7472B5F

 

 

65B9045211

NR 3 PYLON

(KADY) CRACK WAS FOUND NR 3 PYLON INBD SKIN.

2010F00085

BOEING

 

 

SKIN

DAMAGED

7/4/2008

7472B5F

 

 

65B904529

NACELLE

(KADY) AN ENLARGED HOLE WAS FUND ON THE OTBD SKIN AT NAC STA 286.50.

2010FA0000365

BOEING

 

 

SKIN

DAMAGED

2/23/2010

747300

 

 

65B12736129

LT WING

(KADY) REPLACE TIME LIMITED REPAIR WITH PERMANENT REPAIR - LT WING L/E SKIN.

2010FA0000366

BOEING

 

 

DOOR

DELAMINATED

2/23/2010

747300

 

 

65B9003228

RT STRUT

(KADY) DISBOND (24.0" X 3.5") WAS FOUND BETWEEN OUTER SKIN (65B90036-2) AND ALUMINUM HONEYCOMB CORE (65B90036-18) OF THE NR 1 RT STRUT FAIRING DOOR (65B90032-28).

2010FA0000369

BOEING

 

 

DOOR

DELAMINATED

2/20/2010

747300

 

 

65B9003229

LT STRUT

DISBOND (21.0" X 5.0") WAS FOUND BETWEEN OUTER SKIN (65B90036-2) AND ALUMINUM HONEYCOMB CORE (65B90036-18) AND CRACK (2.0", 1.3" LONG) ON OUTER SKIN (65B90036-2) OF THE NR 1 LT STRUT FAIRING DOOR (65B90032-29).

2010FA0000371

BOEING

 

 

FITTING

DAMAGED

4/15/2008

747300

 

 

65B903358

NACELLE

(KADY) FRETTING DAMAGE.

2010FA0000361

BOEING

 

 

FRAME

CRACKED

2/17/2010

747300

 

 

65B9031024

NACELLE

(KADY) CRACK AT AFT FLANGE OF UPPER FRAME OF NR 1 ENGINE. MAJOR REPAIR ACCOMPLISHED BY TRIM OUT OF DAMAGED FRAME AND INSTALL REPAIR PARTS.

2010FA0000374

BOEING

 

 

SKIN

WORN

4/1/2008

747300

 

 

 

PYLON

(KADY) WORN DAMAGE WAS FOUND ON THE CAP SKIN OF THE NR 1 PYLON. THE DAMAGED CAP SKIN IS REPAIRED IAW SRM.

2010FA0000376

BOEING

 

 

SKIN

DEBONDED

4/17/2008

747300

 

 

65B00726459

NACELLE

(KADY) DISBONDED INNER DOUBLER WAS FOUND ON THE NR 1 LT SIDE COWL SKIN AT NAC STA 192.05-204.55, NAC WL 100-110.

2010FA0000362

BOEING

 

 

LONGERON

WORN

2/20/2010

747300

 

 

65B00726256

NACELLE

(KADY) WORN AND BROKEN OF UPPER LONGERON AT NR 1 ENGINE RT SIDE COWL. MINOR REPAIR ACCOMPLISHED BY TRIM OUT THE DAMAGED UPPER LONGERON AND INSTALL REPAIR PARTS.

2010FA0000363

BOEING

 

 

LONGERON

WORN

2/20/2010

747300

 

 

65B00726256

NACELLE

(KADY) WORN AND BROKEN OF UPPER LONGERON AT NR 2 ENGINE RT SIDE COWL. MINOR REPAIR ACCOMPLISHED BY TRIM OUT THE DAMAGED UPPER LONGERON AND INSTALL REPAIR PARTS.

2010FA0000326

BOEING

 

 

LONGERON

WORN

2/16/2010

747300

 

 

65B00726256

NR 4 COWL

(KADY) WORN AND BROKEN OF UPPER LONGERON AT NR 4 ENGINE SIDE COWL. MONOR REPAIR ACCOMPLISHED BY TRIM OUT THE DAMAGED UPPER LONGERON AND INSTALL REPAIR PARTS.

2010FA0000327

BOEING

 

 

SKIN

DAMAGED

2/16/2010

747300

 

 

65B007264

NACELLE

(KADY) SHARP NICK AND GOUGES AT NR 4 LT SIDE COWL SKIN NAC STA 165.0. MINOR REPAIR ACCOMPLISHED BY TRIM OUT THE DAMAGED SKIN AND INSTALL REPAIR PARTS.

2010FA0000328

BOEING

 

 

CREASE BEAM

CRACKED

2/11/2010

747300

 

 

65B04913807808

FUSELAGE

(KADY) CRACK AT CREASE BEAM AT BS 1260 STG R 5 BOTH SIDES. MINOR REPAIR ACCOMPLISHED BY REPLACING OF CRACKED CREASE BEAM WEBS.

2010FA0000330

BOEING

 

 

BULKHEAD

CRACKED

2/10/2010

747300

 

 

65B903107880

NACELLE

(KADY) CRACKED 2 PLACES AT NR 1 ENGINE REAR MOUNT BULKHEAD WEB. MAJOR ALTERATION ACCOMPLISHED BY REPLACING OF AFFECTED FRAME WEBS.

2010FA0000364

BOEING

 

 

FLOORBEAM

CRACKED

2/16/2010

747300

 

 

65B1092745

FUSELAGE

(KADY) CRACK WAS FOUND ON THE WEB OF THE UPPER DECK FLOORBEAM AT STA 340 RT SIDE.

2010FA0000372

BOEING

 

 

FLOORBEAM

CRACKED

2/16/2010

747300

 

 

65B1092745

FUSELAGE

(KADY) CRACK WAS FOUND ON THE WEB OF THE UPPER DECK FLOORBEAM AT STA 340 RT SIDE.

2010FA0000373

BOEING

 

 

SKIN

DAMAGED

2/23/2010

747300

 

 

65B12736129

LT WING

(KADY) REPLACED TIME LIMITED REPAIR WITH PERMANENT REPAIR - LT WING L/E SKIN.

2010FA0000329

BOEING

 

 

CREASE BEAM

CRACKED

2/11/2010

747300

 

 

65B04913809

FUSELAGE

(KADY) CRACK AT CREASE BEAM AT BS 1240, STG 7L. MINOR REPAIR ACCOMPLISHED BY REPLACING OF CRACKED CREASE BEAM WEB.

2010FA0000377

BOEING

 

 

LONGERON

CRACKED

4/17/2008

747300

 

 

65B00726459

NACELLE

(KADY) CRACK WAS FOUND ON THE UPPER LONGERON AND SKIN OF THE NR ENG LT SIDE COWL.

2010FA0000378

BOEING

 

 

SKIN

CRACKED

4/18/2008

747300

 

 

65B9005518

NACELLE

(KADY) CRACK WAS FOUND ON THE NR 2 ENG RT SIDE COWL UPPER SKIN AT NAC STA 226.95-236.85.

2010FA0000379

BOEING

 

 

FRAME

CHAFED

4/4/2008

747300

 

 

 

FUSELAGE

(KADY) FRAME DAMAGE CAUSED BY CHAFING WITH SCREW AT BS 1540 BETWEEN STGR 19 AND 22 RT SIDE. MAJOR REPAIR ACCOMPLISHED BY CUT AND REMOVE FRAME AND INSTALL REPAIR PARTS INCLUDING ORIGINAL SEGMENT AND SPLICE PLATE.

2010FA0000380

BOEING

 

 

INTERCOSTAL

CRACKED

3/28/2008

747300

 

 

 

FUSELAGE

(KADY) FASTENER HOLE CRACK AT INTERCOSTAL WEB OF BS 1265 RT SIDE AND REPLACEMENT OF EXISTING REPAIR FOR LT SIDE TO REPLACE TIME LIMITED REPAIR INSTALLED LAST VISIT. MAJOR REPAIR ACCOMPLISHED BY CUT OUT OF END PORTION OF INTERCOSTAL WEB AND INSTALL REPAIR PARTS INCLUDING FILLERS AND REPAIR DOUBLERS.

2010FA0000381

BOEING

 

 

DOOR FRAME

CRACKED

4/15/2008

747300

 

 

65B0431111

FUSELAGE

FRAME CRACK NR 2 LT SIDE AND 4 BOTH SIDES MAIN ENTRY DOOR. MAJOR REPAIR ACCOMPLISHED BY CUT OUT CRACKED FRAME AND INSTALL REPAIR FILLER AND REPAIR DOUBLERS.

2010FA0000382

BOEING

 

 

STRINGER SPLICE

CRACKED

5/9/2008

747300

 

 

65B189924

FUSELAGE

(KADY) CRACK AT STRINGER SPLICE AT BS 520, STGR 10 RT SIDE. MAJOR REPAIR ACCOMPLISHED BY FABRICATION AND REPLACING OF THE AFFECTED SPLICE FITTING.

2010FA0000375

BOEING

 

 

SKIN

DAMAGED

4/15/2008

747300

 

 

65B9005518

NACELLE

(KADY) A BENT DAMAGE WAS FOUND ON THE NR 1 RT SIDE COWL SKIN AT NAS STA 155.61, NAC WL100.

2010FA0000403

CESSNA

 

 

HUB   

CRACKED

3/23/2010

152   

 

 

 

PROPELLER

(IT6R) PROPELLER SENT FOR AD 2010-04-05. PROPELLER TT 5379.2. PROPELLER HAS A CRACK DOWN THE L/E BOLT HOLE AND CLEAR AROUND THE HUB FACE DOWN THE SIDE OF THE HUB VISUALLY ABOUT 1.5 INCHES. CRACK CAN BE SEEN VISUALLY ABOUT .5" DOWN THE BOLT HOLE.

2010FA0000389

CESSNA

LYC   

 

GEAR

CRACKED

4/16/2010

172M

O360A4M

4373

M3827

MAGNETO

DISASSEMBLED BOTH MAGS TO COMPLY WITH SB3-08A. PRIOR TO REASSEMBLY MECHANIC NOTED THAT THE MAG ROTOR GEARS (PN M3827) ON BOTH MAGS HAD NUMEROUS CRACKS IN ONE OF THE GEAR TEETH. ORDERED 2 NEW GEARS AND FOUND NUMEROUS CRACKS IN ONE OF THE NEW GEARS AS WELL. ALL 3 GEARS HAD CRACKS IN THE SAME GEAR TOOTH. THE GEARS ARE MARKED WITH A LINE FOR LT AND RT ROTATION. THERE ARE 3 GEAR TEETH BETWEEN THE LT INDEX TOOTH AND THE RT INDEX TOOTH. ALL OF THE CRACKS IN ALL 3 GEARS WERE IN THE TOOTH ADJACENT TO THE LT INDEX TOOTH. THE CRACKS ARE FROM THE TOP LAND OF THE TOOTH INTO THE BOTTOM LAND AND EXTEND A SHORT DISTANCE INTO THE GEAR BODY. LT MAG: MFG 4373 SN 08052105 125.5 HOURS SINCE NEW; RT MAG: MFG 4370, SN 08060556, 125.5 HOURS SINCE NEW; NEW GEAR: AFT PN M3827, PO: T36925, LOT: 30-15310 0.0 HOURS SINCE NEW. BOTH NEW GEARS WERE PACKAGED SEPERATELY AND BOTH PACKAGES HAD THE SAME INFORMATION ON THE TAGS.

2010FA0000276

CESSNA

CONT

SLICK

CONTACT

BROKEN

2/22/2010

180D

O470*

 

M3081

LT MAGNETO

DURING ROUTINE ENGINE RUNUP, ENGINE DIED WHEN SWITCHED TO LT MAGNETO. REMOVED LT MAGNETO. OPENED TO INVESTIGATE, AND FOUND CONTACT ASSY BROKEN IN 2 PIECES. NO OTHER. DAMAGE FOUND. INSTALLED NEW CONTACT ASSY PN M3081. REINSTALLED MAGNETO. FUNCTIONAL, TEST GOOD. THERE WAS NO APPARENT REASON FOR THE COMPONENT FAILURE. TTSN 3.9.

2010FA0000271

CESSNA

 

 

RUDDER PEDAL

LOOSE

3/2/2010

182Q

 

 

07606781

COCKPIT

DURING AN ANNUAL INSP THE PILOT`S RT RUDDER PEDAL WAS FOUND LOOSE. UPON REMOVAL, THE BRAKE ATTACH HOLE AND THE PIVOT HOLES WERE FOUND WORN.

2010FA0000336

CESSNA

CONT

 

BAFFLE

BROKEN

4/12/2010

210N

IO520L

 

1250251

ENGINE

(M2ZR) FOLLOWING TAKEOFF, PILOT DETECTED AN UNUSUAL ENGINE SOUND ACCOMPANIED BY LOSS OF ENGINE POWER. PILOT RETURNED TO AIRPORT, LANDING DOWNWIND ON A TAXI WAY . INSP OF ENGINE REVEALED RT MUFFLER PN 1250251-16 BAFFLE/FLAME CONE ASSY. HAD COME LOOSE AND WAS OBSTRUCTING THE EXHAUST OUTLET. FURTHER INSP REVEALED LT MUFFLER ASSY. BAFFLE/FLAME CONE WAS ALSO LOOSE. REPLACED LT AND RT MUFFLER ASSY.

2010FA0000275

CESSNA

CONT

 

CLAMP

CRACKED

1/11/2010

340A

TSIO520NB

 

NH1000089770

WASTEGATE

DURING AN ANNUAL INSPECTION, THE CLAMP BETWEEN THE EXHAUST PIPE AND WASTEGATE ELBOW ON THE RT ENGINE WAS FOUND WITH A 2 INCH CRACK ALONG THE CIRCUMFERENCE.

2010FA0000387

CESSNA

CONT

 

BRACKET

BROKEN

4/1/2010

404   

GTSIO520F

 

581514612

ELEVATOR

(H12R) PREFLIGHT CONTROL CHECKED GOOD, THE ELEVATOR WAS HITTING THE CONTROL STOPS, ON TAKEOFF THE ACFT HAD PARTIAL ELEVATOR CONTROL, ON LANDING THE ACFT HAD PARTIAL ELEVATOR CONTROL, BEFORE FURTHER FLIGHTS THE CONTROLS WERE CHECKED, THE ELEVATOR BELLCRANK BRACKET WAS FOUND BROKEN OFF OF ITS ATTACHMENT TO THE SPAR. THE RIVETS WERE WORN THRU AND THE HOLES WERE ELONGATED. THE 15,000+ HOURS ON THE PART AND THE LACK OF MX AND PROPER INSPECTIONS ARE THE REASONS FOR THIS PART FAILURE.

2010FA0000274

CESSNA

CONT

 

CLAMP

CRACKED

3/9/2010

421B

GTSIO520*

 

NH100089750

TURBO TAILPIPE

DURING AN ANNUAL INSP, THE CLAMP BETWEEN THE TURBO AND EXHAUST OVERBOARD ON THE LT ENGINE WAS FOUND WITH A 4.5 IN CRACK ALONG THE CIRCUMFERENCE.

2010FA0000404

CESSNA

 

 

SEAT FRAME

BROKEN

3/24/2010

550   

 

 

551900947

CABIN

(GVRR) UPPER SEAT BASE ASSY CRACKED AT CHAIR BACK ATTACH POINTS. STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE. CHAIR WAS REPAIRED IAW STC 01042WI.

2010FA0000287

CESSNA

 

 

SEAT FRAME

BROKEN

3/10/2010

550   

 

 

551900922

UNKNOWN

(GVRR) UPPER SEAT BASE ASSY CRACKED AT CHAIR BACK ATTACH POINTS. STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE. ALSO PREVIOUS INAPPROPRIATE REPAIR. CHAIR WAS REPAIRED IAW STC 01042WI.

WTXR173J01

CESSNA

PWA   

 

CONNECTOR

MISINSTALLED

3/29/2010

560CESSNA

PW535A

 

 

FIRE LOOP

AT THE LT ENGINE FIRE LOOP, IT WAS DISCOVERED THAT BECAUSE THE THREADED CONNECTORS ARE OF THE SAME THREAD TYPE BETWEEN THE WIRING FOR THE FIRE LOOP AND THE FIRE LOOP ITSELF, IT IS VERY EASY FOR THE WIRES AND LOOPS TO BE CONNECTED INCORRECTLY WHICH WOULD PREVENT AN INDICATION OF FIRE IN THE COCKPIT IF ONE EXISTED. DURING NORMAL OPERATION, THE SYS APPEARS TO FUNCTION NORMALLY. THE ONLY WAY TO DETERMINE IF WIRED CORRECTLY/INCORRECTLY IS BY VISUAL INSP.

2010FA0000334

CESSNA

 

CESSNA

STIFFENER

CORRODED

4/9/2010

680CE

 

 

693101222

AFT SPAR

DURING REPLACEMENT OF RUDDER HINGE BRACKETS ON VERTICAL STABILIZERS REAR SPAR, EXFOLIATION CORROSION WAS FOUND ON THE LOWER BRACKET (P/N: 6931050-10) OF THE UPPER RUDDER HINGE POINT, LOWER BRACKET (P/N: 6931050-12) & UPPER BRACKET (P/N: 6931050-11) OF THE MIDDLE RUDDER HINGE POINT. ALSO NOTED EXFOLIATION CORROSION ON VERTICAL STAB AFT SPAR STIFFENER (P/N: 6931012-22) AT APPROXIMATE WL 190.763, REQUIRING REPLACEMENT OF STIFFENER.

2010FA0000283

CESSNA

ALLSN

 

PUMP

OVERHEATED

3/15/2010

750   

AE3007C

 

LR553852

LT FUEL BOOST

(JZ2R) FUEL PUMP WAS FOUND TO HAVE OVER HEATED TO THE POINT THAT THE SOLDIER HOLDING IT TOGETHER WAS MELTED. HEAT CAUSED THE PHENOLIC COVER TO BECOME MELTED AS WELL.

2010FA0000367

CESSNA

 

 

SWITCH

INOPERATIVE

4/16/2010

S550

 

 

991207612

COCKPIT

OVERSPEED WARNING INOPERATIVE. TESTED ON GROUND AND FOUND OVERSPEED WARNING SWITCH, P/N 9912076-12, S/N 173 TO BE OUT OF CALIBRATION. REMOVED AND REPLACED SWITCH WITH OVERHAULED UNIT, S/N 259. TESTED AND UNIT FAILED. R & R SWITCH WITH INSPECTED UNIT, S/N 09J108. TESTED AND UNIT FAILED. REMOVED AND REPLACED SWITCH WITH OVERHAULED UNIT, S/N 152. TESTED AND UNIT FAILED. REMOVED AND REPLACED SWITCH WITH OVERHAULED UNIT, S/N 191.

2010FA0000385

CIRRUS

CONT

 

PLACARD

WRONG PART

4/1/2010

SR20

IO360ES

 

22042002

COCKPIT

INCORRECT MANEUVERING SPEED (VO) PLACARD WAS FOUND TO BE INSTALLED ON NEW ACFT. THE INSTALLED PLACARD, LOCATED ON THE FAR LT SIDE OF THE INSTRUMENT PANEL (NEXT TO THE PFD), INDICATED "MANEUVERING SPEED: VO 133 KIAS". THE CORRECT PLACARD SHOULD INDICATE "MANEUVERING SPEED: VO 130 KIAS". AFTER COMMUNICATING WITH MFG TECH SUPPORT, IT WAS DETERMINED THAT A MANEUVERING SPEED PLACARD FOR THIS MODEL (PN 22042-001) WAS INSTALLED BY MISTAKE AT THE FACTORY. CORRECT PLACARD FOR THIS ACFT, SN 2016, IS PN 22042-002. THE TECH REP RESPONDED IMMEDIATELY AND DISPATCHED THE CORRECT PLACARD THE SAME DAY THE PROBLEM WAS REPORTED. MFG TECH EXPRESSED ASSURANCE THAT THE ISSUE WOULD BE BROUGHT TO ATTENTION OF THEIR QA DEPT.

2010FA0000408

CIRRUS

CONT

 

TORQUE TUBE

LOOSE

4/23/2010

SR22

IO550N

 

10146005

ELEVATOR

THE (2) BLIND RIVETS ATTACHING THE FLANGE TO THE TORQUE TUBE WERE FOUND LOOSE AND "WORKING" ON THE ELEVATOR. NOT THAT AD 01-25-03 WAS PREVIOUSLY COMPLIED WITH, AND THE DIMPLED (AD) RIVET WAS INSTALLED. THIS COMPONENT MAY REQUIRE CONTINUED INSP AT SOME HOURLY INTERVAL.

V0XR201004160002

DHAV

 

 

SEAT TRACK

CORRODED

4/16/2010

DHC8106

 

 

14530659011

ZONE 100

LT LOWER SEAT TRACK AT FR 17-24 IS CORRODED BEYOND LIMITS. R & R LT SEAT TRACK. W/C 2182.

V0XR201004160002A

DHAV

 

 

GUSSET

CORRODED

4/16/2010

DHC8106

 

 

14522226003

ZONE 100

CTR GUSSET FR 59-61 IS CORRODED BEYOND LIMITS. R & R CTR GUSSET. W/C 1154. (V0XR)

V0XR201004160001

DHAV

 

 

SEAT TRACK

CORRODED

4/16/2010

DHC8106

 

 

85320490133SP

ZONE 100

LT SEAT TRACK FR 182-484 IS CORRODED BEYOND LIMITS. R &R LT SEAT TRACK.

V0XR201004260001

DHAV

PWA   

 

SEAT TRACK

CORRODED

4/26/2010

DHC8106

PW120

 

85320490135SP

ZONE 100

(V0XR) RT SEAT TRACK RAIL FR 182.0 TO 424.12 CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 1087.

V0XR201004260002

DHAV

PWA   

 

SEAT TRACK

CORRODED

4/26/2010

DHC8106

PW120

 

 

ZONE 100

(V0XR) LT SEAT TRACK DRIP RAIL CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 2225.

V0XR201004260003

DHAV

PWA   

 

SEAT TRACK

CORRODED

4/26/2010

DHC8106

PW120

 

14532605017

ZONE 100

(V0XR) RT UPPER SEAT TRACK FR 46-52 CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 1098.

2010FA0000347

DIAMON

CONT

 

STARTER

MISMANUFACTURED

3/9/2010

DA20C1

IO240B

 

C12ST2S

ENGINE

STARTER FAILED DURING ATTEMPTED ENGINE START. UPON REMOVAL, GALLING WAS EVIDENT ON STARTER NOSE BOWL FROM STARTER PINION GEAR. DAMAGE WAS ALSO FOUND ON THE AFT SIDE OF THE ENGINE CASE, JUST FWD OF THE STARTER PINION GEAR. THE STARTER PINION GEAR HAS EIGHT TEETH, WHILE THE MAINTENANCE MANUAL DESCRIBES A NINE-TOOTH PINION GEAR.

2010FA0000310

DOUG

 

 

FINGER DOUBLER

CORRODED

3/26/2010

DC871F

 

 

 

FLOOR WEB

(SPUY) DURING ROUTINE C-CHECK INSP, FLIGHT COMPARTMENT - HORIZ PRESS PANEL (SUB FLOOR) FINGER DOUBLER CORRODED AT STA 58.000 AND LBL 19.

2010FA0000305

DOUG

 

 

SKIN

DAMAGED

3/26/2010

DC871F

 

 

 

LT WING TE FLAP

( SPUY) DURING ROUTINE C-CHECK INSPECTION, LT WING INBD FLAP - AFT UPPER SURFACE SKIN PANEL SHOWS SCRATCHES AND (05EA) DENTS (STA XW 1.000 - 91.000).

2010FA0000304

DOUG

 

 

SKIN

DENTED

3/26/2010

DC871F

 

 

 

RT WING TE FLAP

( SPUY) DURING ROUTINE C-CHECK INSPECTION, RT WING INBD FLAP - FWD UPPER SURFACE SKIN PANEL SHOWS DENTS ( STA XW 104.000-122.000)

2010FA0000301

DOUG

 

 

HOOK

CRACKED

3/26/2010

DC871F

 

 

 

DOOR HOLD OPEN

( SPUY) DURING ROUTINE C-CHECK INSPECTION, FUSELAGE NOSE SECTION SKIN - FWD PASSENGER DOOR HOLD OPEN HOOK CRACKED .5" AT STA FS 15,000, L-16.

2010FA0000309

DOUG

 

 

ANGLE

CRACKED

3/26/2010

DC871F

 

 

 

BS 1690

(SPUY) DURING ROUTINE C-CHECK INSPECTION, AFT FUSELAGE INTERNAL SECTION- RING ANGLE CRACKED AT STA FS 1690.000 BETWEEN 30L AND L36.

2010FA0000311

DOUG

 

 

STRUCTURE

CRACKED

3/26/2010

DC871F

 

 

 

LT WING

(SPUY) DURING ROUTINE C-CHECK INSPECTION, LT OTBD WING L/E INNER SECTION. LOWER PLATING CRACKED AT STA XFS 597.500.

2010FA0000300

DOUG

 

 

DOUBLER

WORN

3/26/2010

DC871F

 

 

 

FUSELAGE

(SPUY) DURING ROUTINE C-CHECK INSP, FUSELAGE NOSE SECTION, INTERNAL DOUBLER WORN AND BROKEN AT STA FS-156.00 (THRU NR 2 ACCESS DOOR. GROUND PNEU CONNECTION).

2010FA0000303

DOUG

 

 

SKIN

DENTED

3/26/2010

DC871F

 

 

 

RT WING TE FLAP

( SPUY) DURING ROUTINE C-CHECK INSPECTION, RT WING OTBD FLAP - AFT LOWER SURFACE SKIN PANEL SHOWS INTERM REPAIR AND DENT ( STA XF375.00-415.00).

2010FA0000316

DOUG

 

 

UNKNOWN

UNKNOWN

3/26/2010

DC873

 

 

 

SCHEDULED MAINT

(SPUY) DURING ROUTINE C-CHECK INSPECTION, R & R EXISTING REPAIR LOCATED FS 1180.000- 1200.000, L36 WITH A REPAIR IAW APPROVED DATA (SRM) LIST ANY AND ALL REINSPECTIONS ON THE NON-ROUTINE.

2010FA0000324

DOUG

 

 

FRAME

WORN

3/26/2010

DC873

 

 

 

THRUST REVERSER

(SPUY) DURING ROUTINE C-CHECK INSPECTION, NR 2 ENGINE. T/R FIXED STRUCTURE FRAME WORN, STA YN 203.000 AT 5 O`CLOCK POSITION RT.

2010FA0000312

DOUG

 

 

SKIN

CORRODED

3/26/2010

DC873

 

 

 

VERTICAL STAB

(SPUY) DURING ROUTINE C-CHECK INSPECTION, VERT STAB - CORROSION BETWEEN SKIN AND BEADED DOUBLER (STA ZR 153.000 - 281.963).

2010FA0000325

DOUG

 

 

FRAME

WORN

3/26/2010

DC873

 

 

 

THRUST REVERSER

(SPUY) DURING ROUTINE C-CHECK INSPECTION, NR 3 ENG LT T/R FIXED STRUCTURE FRAME WORN, STA YN 203.000 AT 7 O`CLOCK POS.

EE4Y1004072

DOUG

 

 

FRAME

DAMAGED

4/14/2010

DC915F

 

 

 

FUSELAGE

DURING THE UPPER FUSELAGE, CARGO CABIN AT STA 699, BETWEEN LONG 5R AND 10R COOPESA FOUND FRAME WITH DOUBLE HOLES AND HOLES AT THE FRAME RADIUS.

EE4Y1004073

DOUG

 

 

FRAME

DAMAGED

4/14/2010

DC915F

 

 

 

FUSELAGE

DURING THE UPPER FUSELAGE, CARGO CABIN AT STA 718, BETWEEN LONG 5R AND 6R COOPESA FOUND FRAME I/B FLANGE WITH DOUBLE HOLE.

EE4Y1004074

DOUG

 

 

FRAME

DAMAGED

4/14/2010

DC915F

 

 

 

FUSELAGE

DURING THE UPPER FUSELAGE, CARGO CABIN AT STA 465, BETWEEN LONG 12L AND 14L COOPESA FOUND FRAME WITH DOUBLE HOLE.

EE4Y1004075

DOUG

 

 

FRAME

DAMAGED

4/14/2010

DC915F

 

 

 

FUSELAGE

DURING THE UPPER FUSELAGE, CARGO CABIN AT STA 237, BETWEEN LONG 3L AND 10L COOPESA FOUND FRAME WITH DOUBLE HOLE.

EE4Y1004076

DOUG

 

 

FRAME

DAMAGED

4/14/2010

DC915F

 

 

 

FUSELAGE

DURING THE UPPER FUSELAGE, CARGO CABIN AT STA 294, BETWEEN LONG 3R AND 16R COOPESA FOUND FRAME WITH DOUBLE HOLES.

EE4Y1004077

DOUG

 

 

FRAME

DAMAGED

4/14/2010

DC915F

 

 

 

FUSELAGE

DURING THE UPPER FUSELAGE, CARGO CABIN AT STA 351, BETWEEN LONG 3R AND 14R COOPESA FOUND FRAME WITH DOUBLE HOLES IN SEVERAL PLACES.

V0XR201003390001

EMB   

 

 

SEAT TRACK

CORRODED

3/29/2010

EMB145EP

 

 

14530659007

ZONE 100

LT LOWER SEAT TRACK BETWEEN FR 47-52 CTR FUSELAGE II IS CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 2158.

V0XR201003220003

EMB   

 

 

GUSSET

CORRODED

3/22/2010

EMB145EP

 

 

14530633006

ZONE 100

CTR GUSSET FRM 2-35 IS CORRODED BEYOND LIMITS. R & R CTR GUSSET. W/C 1079.

V0XR201003220005

EMB   

 

 

ANGLE

CORRODED

3/22/2010

EMB145EP

 

 

14524131011

ZONE 100

ANGLE(S) UNDER PASSENGER DOOR SILL IS CORRODED BEYOND LIMITS. R & R ANGLE. W/C 1062.

V0XR1003230001A

EMB   

 

 

BEAM

CORRODED

3/23/2010

EMB145EP

 

 

14521713005

ZONE 100

CTR BEAM Y0.0 FROM FR 17-24 IS CORRODED BEYOND LIMITS. R & R CTR BEAM. W/C 1066.

V0XR201003230001

EMB   

 

 

SEAT TRACK

CORRODED

3/23/2010

EMB145EP

 

 

14532606009

ZONE 100

UPPER LT SEAT TRACK BETWEEN FR 53-59 CTR FUSELAGE IV IS CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 2153.

V0XR201003240008

EMB   

 

 

GUSSET

CORRODED

3/24/2010

EMB145EP

 

 

14530634011

ZONE 100

CTR GUSSET AT FRM 46-52 IS CORRODED BEYOND LIMITS. R & R GUSSET. W/C 1133.

V0XR201004270002

EMB   

 

 

GUSSET

CORRODED

4/27/2010

EMB145EP

 

 

1452226003

FUSELAGE

(V0XR) CORRECTION TO NR3 MAJOR EQUIPMENT IDENTITY: CTR GUSSET AT FR 59-61 Y.0.0 IS CORRODED BEYOND LIMITS. R & R CTR GUSSET. W/C 1088.

V0XR201004270003

EMB   

 

 

SILL

CORRODED

4/27/2010

EMB145EP

 

 

14525422003

ZONE 100

(V0XR) RT SILL AT FR 61-65 IS CORRODED BEYOND LIMITS. R & R RT SILL. W/C 1089.

V0XR201004270004

EMB   

 

 

PARTITION

CORRODED

4/27/2010

EMB145EP

 

 

14525991004

ZONE 100

(V0XR) RT LOWER PARTITION AT FR 61 IS CORRODED BEYOND LIMITS. R & R RT PARTITION. W/C 2102.

V0XR201004270001

EMB   

 

 

PROFILE

CORRODED

4/27/2010

EMB145EP

 

 

14524199005

ZONE 100

(V0XR) CORRECTION TO NR5 SPECIFIC PART OR STRUCTURE CAUSING DIFFICULTY: PROFILE AT FR 16 LY-479.0 -LY 780.0 IS CORRODED BEYOND LIMITS. R & R PROFILE. W/C 1076.

V0XR201004270005

EMB   

 

 

PROFILE

CORRODED

4/27/2010

EMB145EP

 

 

14525994003

ZONE 100

(V0XR) LT PROFILE AT FR 61 IS CORRODED BEYOND LIMITS. R & R LT PROFILE. W/C 2103.

V0XR201004270007

EMB   

 

 

SEAT TRACK

CORRODED

4/27/2010

EMB145EP

 

 

14532606003

ZONE 100

(V0XR) LT UPPER SEAT TRACK AT FR 30-36 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 1091.

V0XR201004270008

EMB   

 

 

SEAT TRACK

CORRODED

4/27/2010

EMB145EP

 

 

14532606001

ZONE 100

(V0XR) LT UPPER SEAT TRACK AT FR 23-30 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 1092.

V0XR201004270009

EMB   

 

 

GUSSET

CORRODED

4/27/2010

EMB145EP

 

 

14526437001

ZONE 100

(V0XR) RT GUSSET AT RY- 479.0 FR 59-61 IS CORRODED BEYOND LIMITS. R & R GUSSET. W/C 1087.

V0XR201004270006

EMB   

 

 

STRUCTURE

CORRODED

4/27/2010

EMB145EP

 

 

14521699003

ZONE 100

(V0XR) LT DIGITAL AT LY-479.0 FR 18-23 IS CORRODED BEYOND LIMITS. R & R LT DIGITAL. W/C 1061.

V0XR201004260005

EMB   

ALLSN

 

PROFILE

CORRODED

4/26/2010

EMB145EP

AE3007A

 

14524196001

ZONE 100

(V0XR) PROFILE AT FR 22 LY 479.0 - LY 780.0 IS CORRODED BEYOND LIMITS. R & R PROFILE. W/C 1062.

V0XR201004260006

EMB   

ALLSN

 

SEAT TRACK

CORRODED

4/26/2010

EMB145EP

AE3007A

 

14532606015

ZONE 100

LT UPPER SEAT TRACK AT FR 36-46 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 1093.

V0XR201004260004

EMB   

ALLSN

 

SEAT TRACK

CORRODED

4/26/2010

EMB145EP

AE3007A

 

14532605009

ZONE 100

(V0XR) RT UPPER SEAT TRACK FR 52-57 CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 1099.

V0XR201004260007

EMB   

ALLSN

 

SEAT TRACK

CORRODED

4/26/2010

EMB145EP

AE3007A

 

14532605003

ZONE 100

(V0XR) RT UPPER SEAT TRACK AT FR 30-36 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 1096.

V0XR201003300001

EMB   

ALLSN

 

SEAT TRACK

CORRODED

3/30/2010

EMB145EP

AE3007A

 

14530658007

ZONE 100

RT LOWER SEAT TRACK BETWEEN FR 47-52 CTR FUSELAGE III IS CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 2155.

V0XR201003260009

EMB   

ALLSN

 

FLOOR SUPPORT

CORRODED

3/26/2010

EMB145EP

AE3007A

 

14521721009

ZONE 100

LT OTBD FWD DIGITAL FR 14-17 IS CORRODED BEYOND LIMITS. R & R DIGITAL. W/C 2102

V0XR201003390002

EMB   

ALLSN

 

SEAT TRACK

CORRODED

3/29/2010

EMB145EP

AE3007A

 

14530658007

ZONE 100

RT LOWER SEAT TRACK BETWEEN FR 47-52 CTR FUSELAGE II IS CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 2155.

V0XR201003390003

EMB   

ALLSN

 

SEAT TRACK

CORRODED

3/29/2010

EMB145EP

AE3007A

 

14530658005

ZONE 100

RT LOWER SEAT TRACK BETWEEN FR 36-47 CTR FUSELAGE III IS CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 2159.

V0XR201004160003

EMB   

 

 

PROFILE

CORRODED

4/16/2010

EMB145LR

 

 

14525140023

ZONE 100

PROFILE ON LT SIDE BETWEEN LY 479.0 AND LY 780.0 AT FR 17-18 IS CORRODED BEY0ND LIMITS. R & R PROFILE. W/C 1204.

V0XR201004160004

EMB   

 

 

SEAT TRACK

CORRODED

4/16/2010

EMB145LR

 

 

14530659011

ZONE 100

LT LOWER SEAT TRACK AT FR 17-24 IS CORRODED BEYOND LIMITS. R & R LT SEAT TRACK. W/C 2182.

V0XR201004160005

EMB   

 

 

SEAT TRACK

CORRODED

4/16/2010

EMB145LR

 

 

14532606011

ZONE 100

LT UPPER SEAT TRACK AT FR 17-24 IS CORRODED BEYOND LIMITS. R & R LT UPPER SEAT TRACK. W/C 2183.

V0XR201004090001

EMB   

 

 

CHANNEL

CORRODED

4/9/2010

EMB145LR

 

 

14521713005

ZONE 100

RT HAT CHANNEL BEAM AT RY 479.0 FR 16-24 IS CORRODED BEYOND LIMITS. R & R CHANNEL BEAM. W/C 1132.

V0XR201004130001

EMB   

 

 

PROFILE

CORRODED

4/13/2010

EMB145LR

 

 

14524199401

ZONE 100

PROFILE AT FR 17 LY-479.0 TO LY-780.0 IS CORRODED BEYOND LIMITS. R & R PROFILE. W/C 1143.

V0XR201004130002

EMB   

 

 

SILL

CORRODED

4/13/2010

EMB145LR

 

 

14520609001

ZONE 100

LT SILL AT FR 23-29 IS CORRODED BEYOND LIMITS. R & R SILL. W/C 1199.

V0XR201004130003

EMB   

 

 

GUSSET

CORRODED

4/13/2010

EMB145LR

 

 

14530633006

ZONE 100

CTR GUSSET AT FR 29-35 IS CORRODED BEYOND LIMITS. R & R CTR GUSSET. W/C 1169.

V0XR201004130004

EMB   

 

 

SILL

CORRODED

4/13/2010

EMB145LR

 

 

14529495005

ZONE 100

RT SILL AT FR 53-59 IS CORRODED BEYOND LIMITS. R & R RT SILL. W/C 1200.

V0XR201004130005

EMB   

 

 

SILL

CORRODED

4/13/2010

EMB145LR

 

 

14520609005

ZONE 100

RT SILL AT FR 23-29 IS CORRODED BEYOND LIMITS. R & R RT SILL. W/C 1198.

V0XR201004070005

EMB   

 

 

SEAT TRACK

CORRODED

4/7/2010

EMB145LR

 

 

14530659007

ZONE 100

LT LOWER SEAT TRACK AT FR 46-52 IS CORRODED BEYOND LIMITS. R & R LT LOWER SEAT TRACK. W/C 2186.

V0XR201004070006

EMB   

 

 

SEAT TRACK

CORRODED

4/7/2010

EMB145LR

 

 

14532606017

ZONE 100

LH UPPER SEAT TRACK AT FR 46-52 IS CORRODED BEYOND LIMITS. R &R LT UPPER SEAT TRACK. W/C 2187.

V0XR201004080002

EMB   

 

 

SILL

CORRODED

4/8/2010

EMB145LR

 

 

14525800012

ZONE 100

RT SILL FR 348-52 IS CORRODED BEYOND LIMITS. R & R RT SILL. W/C 1182.

V0XR201004090002

EMB   

 

 

FLOORBEAM

CORRODED

4/9/2010

EMB145LR

 

 

14522466009

ZONE 100

FLOOR SUPPORT ANGLE AT LY 479.0 TO RY 780.0 FR 18 IS CORRODED BEYOND LIMITS. R & R SUPPORT ANGLE. W/C 1136.

V0XR201004150003

EMB   

 

 

PROFILE

CORRODED

4/15/2010

EMB145LR

 

 

14521718007

ZONE 100

AFT FLOOR SUPPORT AT LY 479.0 FR 19-20 IS CORRODED BEYOND LIMITS. R & R FLOOR SUPPORT. W/C 1142.

V0XR201004150006

EMB   

 

 

ANGLE

CORRODED

4/15/2010

EMB145LR

 

 

14529063007

ZONE 100

ANGLE AT RY 780.0 FR 23 IS CORRODED BEYOND LIMITS. R & R ANGLE. W/C 1163.

V0XR201004150007

EMB   

 

 

SILL

CORRODED

4/15/2010

EMB145LR

 

 

14520609007

ZONE 100

RT SILL FR 29-35 IS CORRODED BEYOND LIMITS. R & R RT SILL. W/C 1168.

V0XR201004150009

EMB   

 

 

GUSSET

CORRODED

4/15/2010

EMB145LR

 

 

14530633001

ZONE 100

GUSSET OMEGA BEAM LY 479.0 FR 23-29 IS CORRODED BEYOND LIMITS. R & R GUSSET. W/C 1167

V0XR201004140001

EMB   

 

 

SILL

CORRODED

4/14/2010

EMB145LR

 

 

14529495003

ZONE 100

LT SILL FR 59-60.5 IS CORRODED BEYOND LIMITS. R & R LT SILL. W/C 1159.

V0XR201004150008

EMB   

 

 

GUSSET

CORRODED

4/15/2010

EMB145LR

 

 

14530634003

ZONE 100

CTR GUSSET FR 35-39 IS CORRODED BEYOND LIMITS. R & R CTR GUSSET. W/C 1176.

V0XR201004140003

EMB   

 

 

SEAT TRACK

CORRODED

4/14/2010

EMB145LR

 

 

14530637006

ZONE 100

RT UPPER SEAT TRACK SUPPORT FR 48-52 IS CORRODED BEYOND LIMITS. R & R RT SEAT TRACK. W/C 2215.

V0XR201004140002

EMB   

 

 

SILL

CORRODED

4/14/2010

EMB145LR

 

 

14525422001

ZONE 100

LT SILL FR 61-65.5 IS CORRODED BEYOND LIMITS. R & R LT SILL. W/C 1193.

V0XR201004150005

EMB   

 

 

ANGLE

CORRODED

4/15/2010

EMB145LR

 

 

14529150009

ZONE 100

SCALLOPED ANGLE AT Y0.0 - RY 780.0 FR 23 IS CORRODED BEYOND LIMITS. R & R ANGLE. W/C 1162.

V0XR201004080003

EMB   

 

 

SEAT TRACK

CORRODED

4/8/2010

EMB145LR

 

 

14532605017

ZONE 100

RT UPPER SEAT TRACK FR 46-53 IS CORRODED BEYOND LIMITS. R & R RT UPPER SEAT TRACK. W/C 2184.

V0XR201004080001

EMB   

 

 

SILL

CORRODED

4/8/2010

EMB145LR

 

 

14525800010

ZONE 100

RT SILL FR 35-41 IS CORRODED BEYOND LIMITS. R & R RT SILL. W/C 1175.

V0XR201004080004

EMB   

 

 

SEAT TRACK

CORRODED

4/8/2010

EMB145LR

 

 

14532606015

ZONE 100

LT UPPER SEAT TRACK FR 36-47 IS CORRODED BEYOND LIMITS. R & R LT UPPER SEAT TRACK. W/C 2188.

2010FA0000299

LEAR

GARRTT

 

MUFFLER

CRACKED

4/8/2010

45LEAR

TFE73160

 

12945096001

ZONE 200

COCKPIT ECS MUFFLER ASSY DEVELOPED CRACKS ON EACH END OF THE MUFFLER IN THE WELDED SEAMS AND ALONG THE SIDE OF THE MUFFLER IN THE BEND RADIUS. THE MUFFLER IS FABRICATED FROM ALUMINUM WITH DUCTS WELDED TO EACH END AND IS WRAPPED WITH INSULATION AND FIBERGLASS TAPE. THE MUFFLER IS INSTALLED FWD OF THE AFT BAGGAGE COMPARTMENT ON THE RT SIDE AND IS ACCESSED BY REMOVING THE BAGGAGE COMPARTMENT FWD PANEL. THIS AREA IS ACCESSED AT 300 HOUR INTERVALS TO REPLACE THE MAIN HYD FILTERS. CRACKS WERE DISCOVERED AT THIS TIME DUE TO LOOSE INSULATION IN THE AREA AROUND THE MUFFLER.

2010FA0000337

MRCHTI

LYC   

 

CYLINDER

CRACKED

4/12/2010

F260C

O540E4A5

 

 

ENGINE

PILOT EXPERIENCED ROUGH ENGINE OPERATION. INSP REVEALED THAT NR 2 CYLINDER WAS CRACKED AROUND CIRCUMFERENCE OF HEAD AREA. WHEN TECH TOUCHED CYLINDER DURING THE INSP PROCESS, THE CYLINDER HEAD COMPLETELY SEPARATED FROM ASSY.

5APR577Y33

PILATS

PWA   

 

BRAKE DISC

BROKEN

3/23/2010

PC1247

PT6A67B

 

244759C

MLG BRAKE ASSY

DURING A LINE CHECK THE RT BRAKE WAS DISCOVERED TO HAVE A BROKEN BRAKE DISC. R & R BRAKE ASSY IAW MFG SRM.

2010FA0000269

PIPER

 

 

SPINNER

DESTROYED

3/25/2010

PA24180

 

 

TCB1644300

ZONE 400

AFTER TAKE OFF, AT ABOUT 500 AGL, MAJOR VIBRATION, THEN MINOR VIBRATION UNTILL LANDING, ABOUT 3 MINUTES. MINOR DAMAGE TO PAINT AND ENGINE BAFFLING, PROPELLER REMOVED AND SENT OUT FOR 100 HOUR CHECK . NO APPARENT DAMAGE TO PROPELLER OR ENGINE.

2010FA0000338

PIPER

LYC   

 

CARBURETOR

DETACHED

4/13/2010

PA28161

O320D3G

 

105217

ENGINE

(OG5S) UPON LEVELING OFF FOR CRUISE FLIGHT CREW DISCOVERED THROTTLE COULD NOT BE REDUCED BELOW 2400 RPM. FLIGHT WAS ABORTED AND POWER OFF LANDING WAS PERFORMED. UPON INSP BY MX THE DISCHARGE TUBE FOR THE ACCELORATOR PUMP HAD COME LOOSE AND LODGED IN THE BUTTERFLY VALVE IN THE CARBURATOR. CARB WAS REPLACED AND ACFT RETURNED TO SERVICE.

2010FA0000282

PIPER

 

PIPER

DRAIN VALVE

LOOSE

2/2/2010

PA28R201

 

 

492312

GASCOLATOR BOWL

ACFT EXPERIENCED LOSS OF FUEL FLOW CAUSING ENGINE FUEL STARVATION. AFTER INSP, IT WAS FOUND THAT THE GASCOLATOR BOWL DRAIN VALVE WAS MISSING. PROBABLE CAUSE: POSSIBLE LACK OF CHEMICAL LOCKING AGENT ON VALVE THREADS CAUSING VALVE TO LOOSEN DUE TO USAGE. RECOMMEND INSP OF DRAIN VALVE FOR SECURITY IAW SB NR 1037. NOTE: THIS ACFT SN IS NOT AFFECTED BY SB 1037, BUT COMPLIANCE COULD HAVE POSSIBLY PREVENTED THE MALFUNCTION.

2010FA0000272

PIPER

 

 

BOLT

SHEARED

3/17/2010

PA421000

 

 

AN514400159

RT MLG ACTUATOR

BOLT PN 400-159 WAS FOUND SHEARED. SB 885 SPECIFIES BOLT REPLACEMENT AT 500 HR INTERVALS. FAILED BOTH TTSN WAS 414.1 HRS. REPLACEMENT BOLT PN 400-159, RIB PN 50377-011, BRACKET PN 73524-003, ACTUATORS AND MISC. HARDWARE.

2010FA0000279

PIPER

LYC   

 

MUFFLER

CRACKED

3/3/2010

PA44180

LO360A1H6

 

86299007

RT ENGINE

UPON PREFLIGHT INSP, THE RT ENG AFT MUFFLER WAS FOUND TO BE MISSING THE TAIL/EXIT PIPE SECTION. THE MUFFLER HAD BEEN ON THE ENG FOR ONLY 350 HRS TIS. UPON INSP, THE MUFFLER WAS NOTICED TO HAVE SOME CAN AREA CHAFING MARKS ON IT. ANALYSIS WAS DONE ON THIS MUFFLER PLUS A COUPLE OTHERS THAT WERE REMOVED FOR REPAIR, THE ANALYSIS SHOWED THAT THE CHAFED AREA ON THE MUFFLER CAN HAD WORN INTO THE METAL SURFACE. THIS HAD CAUSED SOME METAL FATIGUE LEADING TO VERY SMALL CRACKS ON ALL THE MUFFLERS THAT WERE ANALYZED. THE PROBLEM STEMS FROM THE FWD AND AFT MUFFLERS CHAFING ON EACH OTHER BETWEEN EACH UNIT AND WEARING/FATIGUING THE METAL. THE PROBLEM IS THAT THE MUFFLERS ON HAVE ABOUT .2500 INCH CLEARANCE BETWEEN THE 2 UNITS ON AVERAGE WHEN THEY ARE COLD BUT PROBABLY EXPAND ENOUGH WHEN HOT TO CAUSE CONTACT IN FLIGHT. MUFFLERS NEED TO BE NARROWED OR THE RISER DESIGN CHANGED TO ALLOW MORE CLEARANCE BETWEEN THE UNITS. ALSO, A 4 CYLINDER INTO 1 SINGLE MUFFLER DESIGN WOULD WORK EVEN BETTER.

2010FA0000270

PIPER

LYC   

SLICK

ROTOR SHAFT

SHEARED

3/16/2010

PA44180

O360*

 

M3513

MAGNETO

ROTOR SHAFT SHEARED AT SPLIT FOR POINT CAM.

2010FA0000410

PIPER

LYC   

 

RIB   

CRACKED

4/15/2010

PA44180

O360*

 

38210000

WING  

( BF8R) (W/O NR: 01000553) THE DISCREPANCY WAS FOUND DURING (1) OF OUR PROGRESSIVE INSPECTIONS. IN THE LT AND RT WING GEAR WELL AREA, THE WING RIB BEHIND EACH MAIN GEAR STRUT AT THE OPEN ACCESS HOLE IN THE RIB THERE ARE 4 CRACKS PROPAGATING FROM THE HOLE OUTWARD IN VARYING LENGTHS UP 1.25 INCHES. NO APPARENT DAMAGE WAS FOUND ON THE ACFT TO SUGGEST ANY KIND OF OVERSTRESS OF THE WINGS OR AIRFRAME. THIS ACFT IS USED FOR FLIGHT TRAINING AND DOES SEE MORE THAN NORMAL TAKEOFFS/LANDINGS, SUSPECT CRACKS POSSIBLY CAUSED BY MULTIPLE HARD LANDINGS OVER THE YEARS. SUGGEST MFG MIGHT LOOK INTO SOME KIND OF STRENGTHENING PLATE FOR THE RIB IF THIS IS HAPPENING WITH OTHER ACFT.

E81RJW302511

RAYTHN

 

 

DETECTOR

MALFUNCTIONED

3/22/2010

390   

 

 

0871KK2

HORIZONTAL STAB

INVESTIGATED PILOT REPORT OF HORIZ STABILIZER L/E ANTI-ICE SYS FAIL INDICATION. AFTER EXTENSIVE TROUBLESHOOTING, FOUND RT ICE DETECTOR WOULD SHOW A FAIL INDICATION WHEN PROBE WAS LIGHTLY COVERED BY A RAG. IF TESTED IAW STEP 3 OF MM 30-11-00-501 OPS TEST WITH A LIGHT FINGER PRESSURE ON THE PROBE, WOULD NOT INDICATE A FAILURE. REPLACED THE RT ICE DETECTOR AND SYS TESTED NORMAL. RECOMMEND MFG INVESTIGATE A MORE ACCURATE METHOD OF TESTING ICE DETECTOR OPERATIONS.

E81RJW302513

RAYTHN

 

 

RELAY

FAILED

3/22/2010

390   

 

 

M8353610028L

IGNITION SYSTEM

INVESTIGATED REPORT OF LT ENGINE IGNITION SYS STAYING ACTIVATED AFTER ENGINE START SEQUENCE COMPLETED. VERIFIED COMPLAINT, FOUND LT ENGINE IGNITION STANDBY POWER RELAY 80K7 FAILED. REPLACED RELAY WITH NEW RELAY, IGNITION SYS OPERATIONS NORMAL. HAVE NOTED THIS RELAY AND IGNITION POWER RELAYS 80K4, 80K6, AND RT IGNITION STANDBY POWER RELAY 80K8 TO FAIL OFTEN, FREQUENTLY WITH LOW TIME IN SERVICE, IN 390 SERIES ACFT. FAILURES ARE OFTEN CAUSING FAILED START ATTEMPTS OR OTHER IGNITION SYS FAULTS.

E81RJW302543

RAYTHN

 

 

SHUTOFF VALVE

FAILED

3/30/2010

390   

 

 

5188001

RIGHT ENGINE

(E81R) INVESTIGATED PILOT REPORT OF RT ENG ANTI-ICE VALVE FAIL ANNUNCIATOR ILLUMINATED. FOUND NACELLE ANTI-ICE SHUTOFF VALVE ASSY, INOPERATIVE. INSTALLED VALVE WAS INSTALLED NEW 6 WEEKS PREVIOUS. REPLACED SHUTOFF VALVE WITH NEW VALVE, FUNCTIONAL TESTS OK. 4TH RT ENGINE ANTI-ICE SHUTOFF VALVE THAT HAS FAILED ON THIS ACFT IN LAST 12 MONTHS AND 184 HRS. THE AIRFRAME MFR IS AWARE OF FLEET-WIDE ISSUE WITH THIS VALVE FAILURE PROBLEM.

E81RPT600772

RAYTHN

 

 

LIMIT SWITCH

INTERMITTENT

4/1/2010

G58RAYTHEON

 

 

BZ3AT

TE FLAPS

( E81R) INVESTIGATED REPORT OF FLAPS NOT EXTENDING FROM APPROACH POSITION TO FULL DOWN POSITION. FOUND ONE SET OF CONTACTS INSIDE OF S76 14 DEGREE LIMIT SWITCH TO BE INTERMITTENTLY OPEN. REPLACED S76 14 DEGREE LIMIT SWITCH AND ADJUSTED FLAP 14 DEGREE AND 16 DEGREE LIMIT SWITCHES RIGGING AS REQUIRED. FLAP SYS OPS NORMAL.

2010FA0000289

RAYTHN

GARRTT

 

LINK PIN

CORRODED

3/22/2010

HAWKER800XP

TFE731*

 

25UN619

NLG STEERING

DURING THE REPLACEMENT OF THE NLG STEERING PIN (PN 25UN605) IAW MANDATORY SB 32-3962, REV 2, THE STEERING LINK PIN, PN 25UN619, WAS FOUND CORRODED.

EVGR20100405

ROBSIN

LYC   

 

OIL FILTER

CHAFED

4/2/2010

R44RAVENII

IO540AE1A5

 

CH48109

ENGINE

(EVGR) AS THE MECHANIC WAS PREPARING TO REMOVE THE OIL FILTER FOR AN ANNUAL INSP, HE NOTICED THE RUST LIKE DUST ON THE OIL FILTER TOP SIDE. AS HE LOOKED CLOSER HE THOUGHT, "THIS IS AN INCORRECT OIL FILTER FOR THIS INSTALLATION." AFTER HE GOT THE FILTER OUT HE WAS ABLE TO CONFIRM THE OIL FILTER WAS A CHAMPION CH48109 "LONG" FILTER AND ONLY THE CH48108 "SHORT" FILTER IS AN APPROVED FILTER. THE FILTER BODY HAD BEEN CHAFING ON THE HORIZONTAL FIREWALL AND CREATED THE RUST LIKE DUST. A FLAT SPOT WAS ON THE FILTER AND A SMALL DIVOT IN THE FIREWALL. NOTE: OIL AND FILTER WERE CHANGED 54.2 HOURS PREVIOUSLY BY ANOTHER FACILITY.

2010FA0000286

SWRNGN

 

 

SELECTOR VALVE

MISMANUFACTURED

2/13/2010

STCSA26

 

 

2781014021A

MLG  

(17UR) RECEIVED 2 EMERGENCY GEAR SELECTOR VALVES, NEW PART FROM M7, PN 27-81014-021A. IT IS THE SECOND ONE RECEIVED THAT IS ASSEMBLED INCORRECTLY AND DOES NOT PORT PROPERLY FOR EMERGENCY GEAR SELECTION. WHEN THE SELECTOR ARM IS IN THE NORMAL POSITION, THE VALVE IS CLOSED AND VICE VERSA FOR THE EMERGENCY POSITION. ITEMS ARE BEING RETURNED TO THE MFG FOR DISPOSITION.

2010FA0000349

UNIVAR

 

 

CLEVIS

SHEARED

4/15/2010

415C

 

 

4008  

BRAKE PEDAL

ON LANDING, LOST BRAKING ACTION. INVESTIGATION FOUND THE BRAKE PISTON CLEVIS ROD BETWEEN THE BRAKE PEDAL ARM AND THE BRAKE MASTERCYLINDER HAD SHEARED BELOW THE LOCK NUT.