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

391

bald eagle watching over three eggs

FEBRUARY

2011

 


CONTENTS

AIRPLANES

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

CESSNA...................................................................................................................................... 9

DIAMOND................................................................................................................................ 15

EMBRAER................................................................................................................................. 17

PIPER......................................................................................................................................... 21

HELICOPTERS

SIKORSKY............................................................................................................................... 21

ACCESSORIES

SLICK MAGNETO................................................................................................................... 23

AIR NOTES

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

IF YOU WANT TO CONTACT US......................................................................................... 29

AVIATION SERVICE DIFFICULTY REPORTS...................................................................... 29

 


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

AVIATION MAINTENANCE ALERTS

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

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

 

AIRPLANES

Beechcraft:  E18S; Broken Elevator Cable; ATA 2730

(An aviation inspector from the Milwaukee Flight Standards Office provides this defect report.  Contact information is found below the last photograph.)

Inspector Anderson states, “This report concerns an operational check flight after an Annual inspection.  After takeoff, the pilot heard a “snap” and the aircraft pitched up.  The pilot realized he had lost down elevator.  Control of the aircraft was regained by the use of power reduction, help from the passenger in the right hand seat, and elevator trim.  The aircraft returned for a successful high speed wheel landing.

"The cable appears to be galvanized steel and was completely covered with Paralketone.  The break was at the pulley above the tail wheel, at bulkhead number 14.  The pulley was free to rotate, however, it did show signs of wear—possibly from over tensioning of the cable.  After removal of the cable from the aircraft, further inspection revealed broken strands in the area of its attachment to the elevator control bull wheel (reference the attached figure).  Note the total time on the elevator cable (P/N 414-187097-1) is unknown."


 

A) DRAWING OF CABLE ROUTING.


 

B) PHOTO OF WORN PULLEYS.


 

C) CABLE FRAYS; SHOWN UNDER BENDING LOAD.


 

D) CABLE WEAR; SHOWN UNDER TWISTING LOAD.

 

E) BROKEN CABLE; TWO ENDS SHOWN.


 

F) CLOSEUP OF BROKEN CABLE; ONE END SHOWN.

 

G) PHOTO OF AIRCRAFT TAIL SECTION.

 


(For further information contact Aviation Safety Inspector Timothy H. Anderson, Milwaukee Flight Standards District Office, 4915 South Howell Avenue, Milwaukee, Wisconsin, 53545; phone 414-486-2920.  Also reference SDRS control number 2011FA0000154.)

Part (aircraft) Total Time:  17,918.8 hours

 

Beechcraft:  M35; Cracked Flap (Leading Edge); ATA 5753

"(I) performed an inspection," says this repair station submitter, "according to Hawker Beechcraft Safety Communiqué number 313/FAA SAIB CE-11-21.  The R/H flap leading edge was found cracked (approx. 1.50 inches) in the vicinity of the 'flap actuator bracket'.  The nose rib was also cracked.  This flap (P/N: 35165050606) was removed for repairs."

 

A) PHOTO OF CRACK ON L.E. FLAP.

(Note—the SDRS database reflects four such defects.)

Part Total Time:  3,700.0 hours

 


Beechcraft:  58; Cracked Spar Web; ATA 5711

"A Beechcraft Barron 58...was in for a routine maintenance inspection at the operator's home facility," says this technician.  "During the Annual Inspection a crack in the right forward spar web bend radius (forward side) was noticed during a visual inspection of the area.  A dye penetrant inspection was performed and the crack was verified.  The inspection was performed following the Hawker Beechcraft Corporation Barron 55 and 58 Maintenance Manual: P/N 55-590000-13G, Rev. G2, dated October 1, 2010; Section 53-00-00, page 202; B(1) 'Wing Forward Spar Carry-through Structure Inspection—Without Repair Kit'.  The aircraft was then flown to our facility for verification of the crack and the installation of Hawker Beechcraft Corp. Kit P/N 58-4008-9 (which is applicable to this aircraft serial number TH-1990).  It should be noted AD90-08-14 'Wing Spar Structure'—and Beechcraft MSB2269 Rev. 1 'Fuselage: Wing Forward Spar Carry-Through Structure Inspection and/or Reinforcement' are not applicable to this aircraft by serial number.  The crack was found in the area referenced in both the AD and MSB, but 'stop' applicability for this aircraft model 58 was at serial number TH-1475.  The Hawker Beechcraft Corp. Kit P/N 58-4008-9 was installed on both the right and left forward spar, forward web structure in accordance with Beech Aircraft Corporation Kit Information—Reinforcement Installation Instructions, Drawing number 58-4009 and Kit Information Drawing number 58-4008, Revision C."

 

A) CRACKED WEB IN FLANGE RADIUS.

(Trick photography!  Not only is the crack quite apparent, but the overall photo provides a nice example of an inside/outside optical illusion—Ed.)

Part Total Time:  2,242.0 hours

 


Cessna:  177RG; Power Cable Short; ATA 2497

A technician writes, "(I) found an improperly sized (too long) interior trim replacement screw installed in the pilot side lower door sill opening, shorting into the Main Power Cable (P/N W-PA4).  The pilot (had) complained of intermittent panel lighting/flickering, and recent regulator replacement (twice) and alternator/charging issues."

 

A) TRIM SCREW LOCATIONS.


 

B) CLOSEUP OF TRIM SCREW LOCATIONS AND DAMAGE.


 

C) CLOSEUP OF TRIM SCREWS.

(Thank-you for the photo effort.  Please excuse my artistic butchering of your last picture—trying to save space—Ed.)

Part Total Time: 5,190.0 hours

 

Cessna:  208; Cracked Horizontal Stabilizer Spar; ATA 5511

(The FAA's Small Airplane Directorate provides this safety admonition. Contact information is found at the discussion's end.  Readers might also view the original SDR report: Control Number 2011FA0000145.)

"During a phase 10 inspection of a Cessna 208 (on floats), maintenance personnel discovered multiple cracks in the center section spar of the horizontal stabilizer (P/N 26300038).  Several ribs were also found wrinkled and distorted, and a straight-edge confirmed deformation of the stabilizer's top surface. 

Removal of this stabilizer revealed extensive damage to the center spar web, rendering it unairworthy.  Subsequent investigation determined the damage was caused by cleaning personnel using this critical flight surface as a work platform during cleaning of the tail area. 

Inspection of this operator's remaining fleet of aircraft found no other problems.  The stabilizer was repaired and reinstalled.  No Step placards were fixed on all subject aircraft in the effected areas.  The total cost of this repair exceeded $17,000.00—not including down-time of the aircraft.


Operators should be vigilant for those ground operations that can cause aircraft damage—cleaning activity is but one example.  Proper training and adequate support equipment (proper stands) are critical elements for elimination of this kind of safety hazard and economic waste."

A) PHOTO OF HORIZONTAL STABILIZER.


B) CLOSEUP OF HORIZONTAL STABILIZER WITH STRAIGHT-EDGE ON TOP.


C) CLOSEUP OF HORIZONTAL STABILIZER CRACKED SPAR WEB; PHOTO 1.

D) CLOSEUP OF HORIZONTAL STABILIZER CRACKED SPAR WEB, PHOTO 2.


 

E) CLOSEUP OF HORIZONTAL STABILIZER CRACKED SPAR WEB; PHOTO 3.

(For further information contact Aerospace Engineer Barry Ballenger, 901 Locust St., Kansas City, MO. 64106; phone 816-329-4152.)

Part Total Time:  2,609.0 hours

 

Diamond:  DA42; Broken Pedal Pivot Tubes; ATA 2720

A flight school submission states, "During preflight, the flight crew noticed the rudder pedals were no longer symmetrical, compared to each other.  A maintenance technician inspected the co-pilot's L/H pedal (P/N DA4-2723-35-00) and noticed the vertical web connecting the pedal to the brake master cylinder rod had torn at the welded intersection of the tube.  The tear/crack in the horizontal pedal pivot tube indicates a torsion failure of that tube."


 

A) CLOSEUP OF CRACKED PEDAL TUBE.


 

B) DRAWING OF PEDAL TUBE ASSEMBLY.

 

Part Total Time:  1,648.0 hours

 

Embraer:  145; Sheared Landing Gear Axle; ATA 3213

"This event occurred late in the evening," says a quality manager, "during disassembly of the landing gear at overhaul.  While accomplishing the un-torque check IAW SP145-32-0097, the nut fell off the subject axle as torque was applied to the upper attach axle (P/N 23092029001).  The axle had sheared at the point where the threads entered the nut.  The operator was informed of the defect by phone and e-mail, (and provided this defective) axle."


 

A) CLOSEUP OF AXLE; PHOTO 1.


B) CLOSEUP OF AXLE; PHOTO 2.


 

C) CLOSEUP OF AXLE NUT.

 

(Note the first photo has been slightly widened by this editor to fit the available space.)

Part Total Time:  25,128.0 hours

 


Piper:  PA23-250; Corroded Elevator Trim Arm; ATA 2731

A repair station technician states, "The elevator trim arm assembly (P/N 15618-05) is corroded to the point of having a 3/16 inch hole through both sides of the aft end of the tube."

 

A) CLOSEUP OF ROD-END.

 

Part Total Time:  9,032.0 hours

 

HELICOPTERS

Sikorsky:  S92A; Cracked Planetary Gear; ATA 6320

"A large crack was discovered (propagating) through the web section of this planetary gear," says a chief inspector.  "(It was found...) while conducting an MPI (magnetic particle inspection) as a normal part of the repair process.  Sikorsky and HSI have been notified; they will be conducting a full metallurgical investigation."  (Gear P/N: 9235115171101.)


 

A) CRACKED GEAR; PHOTO 1.


 

B) CRACKED GEAR; PHOTO 2.

Part Total Time:  (unknown)

 

ACCESSORIES

 

Slick Magneto:  6351; Burned Distributor Block; ATA 7414

A general aviation submitter states, "(I) removed the left magneto (from a Cessna 182T) for a 500-hour inspection and found the distributor block assembly burned through—pieces were floating around inside the (unit).  A large amount of dust coated the surfaces, and burning was evident on the coil and rotor housing.  The carbon brush and cam were extremely worn.  During pre-inspection run-up the magneto drop was no more than 75-80 RPM at 1800 RPM—mixture full rich.

"According to the engine log the magnetos were removed and replaced at tachometer time of 1,007.7 hours for a 500 hour inspection."  (The SDRS database reflects at least ten of these particular magnetos.)


 

A) CLOSEUP OF MAGNETO DRIVE GEAR.


 

B) CLOSEUP OF MAGNETO DRIVE GEAR; INTERNAL VIEW.


 

C) CLOSEUP OF BURNED DISTRIBUTOR PARTS; PHOTO 1.


 

D) CLOSEUP OF BURNED DISTRIBUTOR PARTS; PHOTO 2.

 

Part Total Time:  477.0 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 following address.

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

2010FA0001260

 

 

WINSLOW

FIRING HEAD

MISINSTALLED

12/21/2010

 

 

 

3RA11441

LIFE RAFT

LIFE RAFT WAS IMPROPERLY PACKED BY MFG AND WOULD NOT HAVE BEEN USABLE IN AN EMERGENCY. BOTTLE WAS INSTALLED ACROSS THE CENTER OF THE CONTAINER PLACING THE FIRING HEAD AT A 90 DEGREE ANGLE TO THE SIDE OF THE CASE AND THE FIRING LINE WAS ROUTED THROUGH THE FOLDED LIFE RAFT AND OUT THE OPPOSITE SIDE OF THE CASE.

2010FA0001261

 

 

WINSLOW

FIRING HEAD

MISINSTALLED

12/21/2010

 

 

 

3RA11441

LIFE RAFT

LIFE RAFT WAS IMPROPERLY PACKED BY MFG AND WOULD NOT HAVE BEEN USABLE IN AN EMERGENCY. BOTTLE WAS INSTALLED ACROSS THE CENTER OF THE CONTAINER PLACING THE FIRING HEAD AT A 90 DEGREE ANGLE TO THE SIDE OF THE CASE AND THE FIRING LINE WAS ROUTED THROUGH THE FOLDED LIFE RAFT AND OUT THE OPPOSITE SIDE OF THE CASE.

2010FA0001262

 

 

WINSLOW

FIRING HEAD

MISINSTALLED

12/22/2010

 

 

 

3RA11441

LIFE RAFT

LIFE RAFT WAS IMPROPERLY PACKED BY MFG AND WOULD NOT HAVE BEEN USABLE IN AN EMERGENCY. BOTTLE WAS INSTALLED ACROSS THE CENTER OF THE CONTAINER PLACING THE FIRING HEAD AT A 90 DEGREE ANGLE TO THE SIDE OF THE CASE AND THE FIRING LINE WAS ROUTED THROUGH THE FOLDED LIFE RAFT AND OUT THE OPPOSITE SIDE OF THE CASE.

CA101102007

 

CONT

 

GEAR SHAFT

CRACKED

11/1/2010

 

TSIO550C

 

655711

SCAVENGE PUMP

(CAN) MAGNETIC PARTICLE INSPECTION SHOWED A CRACK BEGINNING CLOSE TO THE END OF THE SCAVENGE PUMP GEAR SPLINE, PROGRESSING AROUND THE END OF THE SPLINE ABOUT 1/8".

2010FA0001263

 

LYC  

 

CRANKSHAFT

CORRODED

12/27/2010

 

O320B2B

 

 

ENGINE

CRANKSHAFT ID FOR CORROSION. DURING THE REMOVAL OF CRANKSHAFT EXPANSION PLUG STD 1211, CRANKSHAFT INTERNAL URETHABOND 104 WAS FOUND BUBBLED. REMOVED URETHABOND 104 AND FOUND CORROSION PITS THOUGHOUT THE TOP 3.5 INCH SURFACE. ENGINE IS FACTORY O/H, AD98-02-08 COMPLIED WITH DURING THAT TIME. "PID" WAS STAMPED ON CRANKSHAFT FLANGE. ACCORDING TO AD "CRANKSHAFTS CONTAINING "PID" STAMPED ON THE OUTSIDE DIAMETER OF THE PROPELLER FLANGE ARE EXEMPT FROM THE INSP REQUIREMENTS OF THIS AD. THERE SHOULD BE A (1) TIME INSP OF ALL CRANKSHAFTS STAMPED WITH "PID" TO DETERMINE ID CONDITION.

2011F00001

AEROSP

PWA  

 

POWER SUPPLY

INOPERATIVE

12/29/2010

ATR72212A

PW127

 

3013000

EMERGENCY LIGHTS

FWD EMERGENCY LIGHTS FAIL TEST. POWER SUPPLY INOPERATIVE.

EE4Y100510

AIRBUS

IAE  

 

FLOORBEAM

CORRODED

12/1/2010

A319132

V2524A5

 

D5347219320000

ZONE 200

PAX CABIN, UPPER REAR FUSELAGE, AFT SERVICE AREA AT STA 2884 -Y76.5 FLOOR SUPPORT STRUCTURE BEAM CORRODED (BEAM PN: D5347219320000) THE CORROSION REQUIRES A MAJOR REPAIR.

EE4Y100511

AIRBUS

IAE  

 

FLOOR SUPPORT

CORRODED

12/2/2010

A319132

V2524A5

 

D5347219220000

ZONE 200

(EE4Y) PAX CABIN, UPPER REAR FUSELAGE, AFT SERVICE AREA FROM STA 2799 TO STA 2884, +76.5 FLOOR SUPPORT STRUCTURE BEAM CORRODED (BEAM PN: D5347219220000) NOTE: THE CORROSION REQUIRES A MAJOR REPAIR.

EE4Y100528

AIRBUS

IAE  

 

BUMPER BLOCK

WORN

12/7/2010

A319132

V2524A5

 

 

THRUST REVERSER

(EE4Y) ENGINE NR 2, OTBD/RT THRUST REVERSE C-DUCT, PAN-DOWN ENGINE BUMPER WITH WEAR. NOTE: THE BUMPER WEAR REQUIRES A MAJOR REPAIR.

EE4Y100551

AIRBUS

IAE  

 

SEAT TRACK

CORRODED

12/14/2010

A319132

V2524A5

 

D5347213320200

ZONE 200

(EE4Y) PAX CABIN, UPPER REAR FUSELAGE, AFT SERVICE AREA FROM STA 2785 TO STA 2794 +Y765 SEAT TRACK CORRODED. (SEAT TRACK PN: D5347213320200) NOTE: THE CORROSION REQUIRES A MAJOR REPAIR.

EE4Y100561

AIRBUS

IAE  

 

BUMPER BLOCK

WORN

12/14/2010

A319132

V2524A5

 

 

THRUST REVERSER

(EE4Y) ENGINE NR2, OTBD/RT THRUST REVERSE C-DUCT, PAN-DOWN ENGINE AFT BUMPER WITH WEAR. NOTE: THE BUMPER WEAR REQUIRES A MAJOR REPAIR.

2010FA0001208

AIRBUS

 

 

FITTING

CORRODED

12/1/2010

A320232

 

 

D5347039420400

CARGO BAY  

CORROSION ON AFT CARGO COMPARTMENT FITTING (FLOOR STRUCTURE). FITTING IS LISTED AS PRIMARY STRUCTURE. NO CORROSION REMOVAL LIMITS AVAILABLE. R & R FITTING IAW SRM 51-42-11.

2010FA0001209

AIRBUS

 

 

PLATE

CRACKED

12/1/2010

A320232

 

 

D5337068220000

MLG WW

CRACK AT FASTENER HOLE ON CONNECTION PLATE FOR RT MLG DOOR ACTUATOR MOUNT FITTING. R & R CONNECTION PLATE IAW SRM 51-72-11.

2010FA0001253

AMTR

LYC  

 

ROCKER BOSS

BROKEN

12/14/2010

RV9A

IO360A1A

 

 

NR 2 CYLINDER

FAILURE OF NR 2 CYLINDER ROCKER ARM BOSSES RESULTING IN ROUGH RUNNING ENGINE, DAMAGE TO ROCKER ARM COVER, AND LOSS OF OIL.

2010FA0001271

AMTR

AMTR

 

EXHAUST VALVE

FAILED

10/16/2010

SKYSCOOTER

JABIRU2200A

 

4596074

NR 2 CYL

REDUCED POWER FROM 2900 RPM TO 2600 RPM, ALL ENGINE INSTRUMENTS IN NORMAL RANGE. EXPERIENCED SEVERE ENGINE VIBRATIONS LASTING ABOUT 10 SECONDS RESULTING IN CATASTROPHIC ENGINE FAILURE. DAMAGE CONTAINED WITHIN ENGINE CASE WITH NO LOSS OF OIL OR FUEL. CYLINDER HEAD FROM NR 2 CYLINDER WAS REMOVED TO INSPECT DAMAGE. HEAD OF NR2 EXHAUST VALVE WAS BROKEN OFF CLEANLY HORIZONTAL TO THE VALVE STEM. THE PISTON WAS DESTROYED. WRIST PIN REMAINS ATTACHED TO CONNECTING ROD. CONNECTING ROD TWISTED AND REMAINS ATTACHED TO CRANKSHAFT. SEVERE DAMAGE TO CYLINDER HEAD & CYLINDER. SUSPECT VALVE FAILED DUE TO LEAN OPERATION, CAUSING HIGH EGT ON EXHAUST VALVE. (NO EGT INDICATING SYS)

2010FA0001189

BALWKS

 

 

HOSE

LEAKING

8/9/2010

FIREFLY824

 

 

49SBSET

FUEL HOSE

HOT AIR BALLOON WAS DELIVERED FOR AN ANNUAL INSP, INCLUDING SCHEDULED REPLACEMENT OF ALL PROPANE FUEL HOSES. (7) REPLACEMENT FUEL HOSES SUPPLIED, WERE DELIVERED WITH THE LP GAS POL TYPE FITTING ATTACHED TO THE HOSE COUPLINGS. THE HOSES WERE PRESSURE TESTED FOR LEAKS AND INSTALLED INTO THE HOT AIR BALLOON GONDOLA BY REPAIR STATION, ACCORDING THE THE MFG TECHNICAL DATA, THE ENTIRE FUEL SYS WAS AGAIN PRESSURE TESTED FOR LEAKS AND RETURNED TO SERVICE. 3 LEAKS DEVELOPED ON 3 DIFFERENT HOSES WITHIN 3 MONTHS OF INSTALLATION, ALL AROUND THE THREADED CONNECTIONS NEAR THE POL FITTINGS. SYS WAS REMOVED FROM SERVICE AND THE CONNECTION WERE EXAMINED BY INSPECTOR. ALL CONNECTION SHOWED EVIDENCE OF PIPE DOPE ON THE EXPOSED THREADS AND ALL FITTINGS WERE FOUND TO BE TORQUED TIGHTLY TOGETHER. THERE WAS NO EVIDENCE OF CRACKING OR DAMAGE TO THE FITTINGS. THE CONNECTIONS WERE DISASSEMBLED, CLEANED, PIPE DOPE WAS RE-APPLIED AND THEN REASSEMBLED. NO SUBSEQUENT LEAKS WERE FOUND AND THE ACFT WAS RETURNED TO SERVICE. IT APPEARS AN INSUFFICIENT AMOUNT OF PIPE DOPE WAS USED ON THE FITTING THREADS DURING INITIAL ASSY. LEAKS MAY HAVE BEEN INITIATED IN PART BY THE ONSET OF COLD WEATHER. RECOMMEND THAT MFG INSURE THAT SUFFICIENT PIPE DOPE IS APPLIED TO COUPLING THREADS TO PREVENT LEAKAGE IN ALL TEMPERATURE RANGES.

2011F00000

BEECH

PWA  

 

STARTER GEN

DESTROYED

12/21/2010

100BEECH

PW305

 

23091002

ZONE 400

DURING CRUISE FLIGHT, EXPERIENCED VIBRATION, BELIEVED TO BE FROM ENGINE AREA. VIBRATION INCREASED, BUT DID NOT SHOW ON EVM INDICATOR, FOLLOWED BY GEN 1 FAIL INDICATION, WITH BUS TIE CLOSED IN FLIGHT. ACFT MADE UNSCHEDULED LANDING. MX FOUND NR1 STARTER GEN FAILED, COOLING FAN ON GEN SHATTERED, SHAFT SHEARED, MANY BROKEN PIECES OF UNIT IN ENGINE COWLING.

2011F00002

BEECH

 

 

DRAG BRACE

CRACKED

12/28/2010

18S  

 

 

404188446

MLG 

PILOT, REPORTED A NORMAL LANDING. TAPPED ON BRAKES, RT MLG COLLAPSED. ACFT REMOVED FROM ACTIVE RUNWAY. SECURED & INSPECTED RT MLG. INSPECTION REVEALED FAILURE DUE TO BROKEN DRAG BRACE. DRAG BRACE BROKE APPROX 3 " FROM BOTTOM HINGE WHERE IT ATTACHES TO RT STRUT. IT APPEARS DRAG BRACE DEVELOPED AN INTERNAL CRACK WHICH CAUSED STRUCTURE OF DRAG BRACE TO WEAKEN CAUSING GEAR TO COLLAPSE. BOTTOM HINGE GREASE FITTING LOOSE. HINGE BUSHING FROZEN IN-PLACE & SHOWED SIGNS OF CORROSION ON INSIDE WALLS OF BUSHING. BUSHING BOLT WORN DUE TO SPINNING IN BUSHING. TOP HINGE BUSHING HAD MINOR SCORING CORROSION INSIDE WALLS OF BUSHING. DRAG BRACE TUBE SHOWS SIGNS OF CORROSION INSIDE WALLS OF TUBE.

CA100723004

BEECH

PWA  

 

LINE

CRACKED

7/22/2010

1900C

PT6A65B

 

3033260

ENGINE

ON TAKEOFF, ENGINE WAS UNABLE TO ACHIEVE FULL POWER AND ACFT RETURNED TO BASE. A NORMAL LANDING WAS CARRIED OUT. UPON INSP, THE P3 LINE FROM THE COMPRESSOR CASE TO THE FCU WAS FOUND CRACKED, PREVENTING FULL P3 AIR FROM REACHING THE FCU. LINE WAS REPLACED, NO FURTHER ISSSUES.

E81RJT22919

BEECH

PWC  

 

WIRE

BROKEN

12/28/2010

400A

JT15D5D

 

 

BLEED AIR SYS

(E81R) DURING DESCENT "A/C FAIL" ANNUNUNCIATOR LIGHT ILLUMINATED AND EMERGENCY PRESSURIZATION SYS ACTIVATED. DURING TROUBLESHOOTING FOUND WIRE E067-P0108B-22 WIRE BROKEN AT BLEED AIR OVERPRESSURE SWITCH CONNECTOR P0108. REPAIRED WIRING AT CONNECTOR AND REPLACED DIRTY WATER SEPARATOR ASSY. COALESCER. ENVIRONMENTAL SYS OPS OK ON GROUND RUN-UP.

2010FA0001268

BEECH

CONT

 

RIB  

CRACKED

12/23/2010

58  

IO520*

 

 

RT WING TE FLAP

(CFOR) WHILE COMPLYING WITH MFG SAFETY COMMUNIQUE NR313 TITLED "FLAP ACTUATOR ATTACHMENT BRACKET AND NOSE RIB ASSEMBLY", DISCOVERED A CRACK ON RIB (PN35-165050-84) ORIGINATING FROM THE LIGHTENING HOLE. AFTER REMOVING THE RT FLAP FROM THE WING AND REMOVING THE ACTUATOR ATTACH BRACKET FROM THE FLAP, ANOTHER CRACK WAS FOUND IN THE SKIN (PN 95-160000-82 UNDER THE BRACKET.

2010FA0001265

BEECH

CONT

NIAGARA  

SUPPORT

BROKEN

12/29/2010

58  

IO550C

 

 

OIL COOLER

DURING AN A ANNUAL INSP IT WAS NOTICED THAT THE LT ENGINE OIL COOLER FWD FACE EXTERNAL DIAGONAL SUPPORT BAR HAD BROKEN OFF HALF WAY FROM THE CTR TO THE BOTTOM INBD CORNER. UNIT REMOVED FOR REPAIR.

CA100723003

BEECH

PWA  

 

DOWNLOCK SWITCH

FAILED

7/16/2010

C90A

PT6A21

 

903610373

MLG 

(CAN) PILOTS WERE PERFORMING TOUCH AND GO APPROACHES WHEN ON THE 6TH TAKE-OFF, THE LANDING GEAR FAILED TO RETRACT UPON SELECTING GEAR HANDLE UP. PILOTS ALERTED THE TOWER AND THE BELLS SOUNDED AT APPROX 14:45 LOCAL. THE ACFT RETURNED AND LANDED WITHOUT FURTHER INCIDENT. TOWER NOTIFIED THAT THE ACFT WAS SECURED AT 14:58 HRS LOCAL. MX JACKED THE ACFT AND PERFORMED SEVERAL LANDING GEAR CYCLES AND NOTED THAT WHEN GEAR WAS SELECTED DOWN, THE HYD PUMP CONTINUED TO RUN UNTIL THE CIRCUIT BREAKER POPPED. MX ISOLATED THE FAULT TO THE LT MLG DOWNLOCK SWITCH. THE SWITCH WAS REPLACED, AND SEVERAL GEAR SWINGS CARRIED OUT WITHOUT FURTHER INCIDENT AND THE ACFT WAS RETURNED TO SERVICE.

QMLRMD7084

BELL  

 

 

POST

DENTED

8/3/2010

407  

 

 

407030310107

BS 81

DENT BEYOND LIMITS ON LT SIDE OF CENTER POST ASSY P/N: 407-030-310-107 AT STATION 81.00 MIDDLE STRINGER.

FOTR2021700661

BOEING

 

 

FRAME

CRACKED

1/11/2011

727223

 

 

 

ZONE 200

(FOTR) REMOVED DAMAGED AREA FROM FRAME AT STR 17L DIMENSION 2.2500" X 1.5" IAW SRM 51-10-1, AND 51-30-2. FABRICATED REPAIR IAW SRM 51-40-3 FROM 7075-0 DIMENSION 9.1" X 4.1" PO 20198132. HEAT TREATED TO 7075T6 IAW FASI REPORT 2-37153-801A. FABRICATED CLIP FROM 7075-T6 PO 9009729, DIMENSION 4" X 3.5". TREATED AND PRIMED REPAIR PARTS IAW SRM 51-10-2. INSTALLED REPAIR PARTS IAW SRM 51-40-3, 51-30-2.

FOTR202170064

BOEING

 

 

FRAME

DENTED

1/11/2011

727223

 

 

 

ZONE 200

(FOTR) LT FUSELAGE CABIN INTERIOR HAS FRAME DENTED AT BS 720, STR 16L. CUTOUT DAMAGED AREA ON FRAME DIMENSION 9" X .9" AT BS 720, STR 16L IAW SRM 51-10-1. FABRICATED FRAME REPAIR FROM 7075-T6 .063" PO 90010361, DIMENSION 5.5" X 17.3" IAW SRM 51-40-3, FIG 1. TREATED AND PRIMED IAW SRM 51-10-2, INSTALLED REPAIR IAW SRM 51-40-3, FIG 1 AND 51-30-2.

FOTR2021700725

BOEING

 

 

SEAT TRACK

CORRODED

1/11/2011

727223

 

 

 

ZONE 200

(FOTR) MAIN CABIN CARGO DECK, AT BS 560-580 LBL 45 INBD SIDE OF SEAT TRACK FLANGE HAS CORROSION. REMOVED CORROSION ON CABIN SEAT TRACK LBL 45, BS 560-580 IAW SRM 51-10-1, FOUND OUT OF LIMITS. REMOVED SEAT TRACK FROM BS 480-689 IAW SRM 51-30-2. FABRICATED SEAT TRACK FROM BAC1520-792, 7178-T6511, PO 9006746 IAW SRM 53-10-3. TREATED AND PRIMED IAW SRM 51-10-2. INSTALLED SEAT TRACK IAW SRM 53-10-3 AND 51-30-2.

FOTR2021700821

BOEING

 

 

FRAME

DENTED

1/11/2011

727223

 

 

 

ZONE 200

(FOTR) CABIN FRAME AT BS 560 BETWEEN STR 15R-16R DENTED. CUTOUT DAMAGED AREA ON BS 560 BETWEEN STR 15R-16R, DIMENSION 1.1" X 1.1" IAW SRM 51-40-3, FIG 1. FABRICATED REPAIR ANGLE FROM 7075-T6 .071' PO 9009519, DIMENSION 6.5" X 3.5" AND REPAIR FILLER FROM 7075-T6 .063" DIMENSION 1.1" X 1.1" IAW SRM 53-10-2, FIG 3 AND 51-40-3, FIG 1. TREATED AND PRIMED PARTS IAW SRM 51-10-2. INSTALLED FRAME REPAIR IAW SRM 51-40-3, FIG 1.

FOTR/20217/00826

BOEING

 

 

FRAME

DAMAGED

1/11/2011

727223

 

 

 

ZONE 200

(FOTR) CABIN FRAME AT BS 680 BETWEEN STR 16L-17L HAS DOUBLE DRILLED HOLES. CUTOUT DAMAGED AREA DIMENSION 1.4" X .6" ON BS 680 BETWEEN STRINGER 16L-17L IAW SRM 51-40-3 FIGURE 1. FABRICATED REPAIR ANGLE FROM 7075-T6 .050" PO 9009353 DIMENSION 7" X 3.6" IAW SRM 51-40-3, FIG 1 AND 53-10-2 FIG 3. INSTALLED REPAIR IAW SRM 51-40-3, FIG 1 AND 51-30-2.

FOTR/20217/00827

BOEING

 

 

FRAME

DAMAGED

1/11/2011

727223

 

 

 

ZONE 200

(FOTR) MAIN CABIN FRAME AT BS 700 BETWEEN STR 16L-17L HAS DOUBLE DRILLED HOLES. CUTOUT DAMAGED AREA AT BS 700 DIMENSION 1" X .8" IAW SRM 51-10-1. FABRICATED DOUBLER FROM 7075-T6 .063 PO 90010361, DIMENSION 6.8750" X 3.5" IAW SRM 51-40-3, FIG 1. INSTALLED REPAIR PART IAW SRM 51-10-1, 51-40-3 FIG 1 AND 51-30-5.

FOTR2021700828

BOEING

 

 

FRAME

DAMAGED

1/11/2011

727223

 

 

 

ZONE 200

(FOTR) MAIN CABIN FRAME AT BS 720A BETWEEN STR 16L-17L HAS DOUBLE DRILLED HOLE. CUTOUT DAMAGED AREA, DIMENSION 1" X .75" IAW SRM 51-10-1. FABRICATED DOUBLER FROM 7075-T6 PO 90010361, .063" DIMENSION 5.8750" X 3.8750" IAW SRM 51-40-3, FIG 1. INSTALLED REPAIR PART IAW SRM 51-40-3, FIG 1 AND 51-30-5.

FOTR/20217/00378

BOEING

 

 

FRAME

DENTED

1/11/2011

727223

 

 

 

ZONE 200

(FOTR) CABIN FRAME AT BS 380 DENTED BETWEEN STR 5R-6R, REMOVED DAMAGE AREA OF BS 380 FRAME AT STR 5R-6R, DIMENSION 15" X 4" IAW SRM 53-10-4, FIG 1. FABBRICATED REPAIR FRAME AND 2 EACH SPLICES FROM 7075-0 .050 PO 90010501 AND HEAT TREATED TO T-6 IAW SRM 53-10-04, FIG 1 AND FASI REPORT NR2-37153-801A, TREATED AND PRIMED IAW SRM 51-10-2, INSTALLED REPAIR IAW SRM 53-10-4, FIG 1 AND SRM 51-30-2.

FOTR/20217/00381

BOEING

 

 

FRAME

DENTED

1/11/2011

727223

 

 

 

ZONE 200

(FOTR) CABIN FRAME DENTED AT BS 400 BETWEEN STRINGER 5R-6R. REMOVED DAMAGED AREA OF BS 400 FRAME AT STR 5R-6R DIMENSION 2.25" X 4" IAW SRM 53-10-4 FIG 1, FABRICATED REPAIR FILLER AND 2 EACH SPLICES FROM 7075-0, .050, PO 90010501 AND HEAT TREATED TO T-6 IAW SRM 53-10-4, FIG 1 AND FASI REPORT 2-37153-801A, TREATED AND PRIMED IAW SRM 51-10-2, INSTALLED REPAIR IAW SRM 53-10-4, FIG 1 AND SRM 51-30-2.

FOTR/20217/00507

BOEING

 

 

INTERCOSTAL

DENTED

1/11/2011

727223

 

 

655610136

ZONE 100

(FOTR) C1 DOOR CUTOUT INTERCOSTAL IS DENTED AT UPPER FLANGE BS 627 BETWEEN STR 24R-25R. REMOVED DAMAGED INTERCOSTAL IAW SRM 51-30-2. LOCATED AND DRILLED NEW INTERCOSTAL PN 65-56101-36, PO 2021752. AND INSTALLED AT BS 627 BETWEEN STR 24R-25R IAW SRM 51-30-2,51-30-5 AND 51-30-6.

FOTR2021700626

BOEING

 

 

STRINGER

CORRODED

1/11/2011

727223

 

 

 

ZONE 100

(FOTR) STR 27L BETWEEN BS 720F-740 IS CORRODED. CUT DAMAGED STR DIMENSION 12" LONG IAW SRM 53-10-3, FIG 1. FABRICATED REPAIR STR FROM BAC1498-147 7075T62 PO 2014059 DIMENSION 11.4375" LONG AND FABRICATED REPAIR STR SPLICE FROM BAC1498-131 7075-T6 PO90010803 DIMENSION 10.8750" LONG IAW SRM 53-10-3, FIG 1 AND 53-10-2 FIG 9. TREATED AND PRIMED IAW SRM 51-10-2. STR REPAIR INSTALLED ON STR 27L BETWEEN BS 720F AND 740 IAW SRM 53-10-3, FIG 1.

FOTR2021700631

BOEING

 

 

SKIN

DENTED

1/11/2011

727223

 

 

 

ZONE 100

(FOTR) AFT LOWER FUSELAGE EXTERIOR SKIN LT SIDE AT STATION 1148-1160 AND BETWEEN STR 25L-26L, SKIN IS DENTED. CUT DAMAGED AREA OUT OF UPPER LAP SKIN DIMENSION 4.5" X 5.5". FABRICATED REPAIR FILLER FROM 2024-T3 .063 PO 90010580 DIMENSION 12" X 14". FABRICATED REPAIR DOUBLER FROM 2024-T3, .071, PO 90010841 DIMENSION 15" X 12". TREATED AND PRIMED IAW SRM 51-10-2. REPAIR DOUBLER AND FILLER INSTALLED AT BS 1160 IAW SRM 53-30-3 FIG 14 AND SRM 51-30-2.

FOTR2021700651

BOEING

 

 

WEB  

CRACKED

1/11/2011

727223

 

 

 

ZONE 200

(FOTR) CABIN INNER WEB DENTED AT BS 640, STR 6L. (AFT MAIN CARGO DOOR). C/W HFEC ON WEB IAW NDTM 51-00-00 FIGURE 23, PART 6. CRACK FOUND. REMOVED TRIM PANEL FROM BS 520-600, REMOVED AFT UPPER INNER SKIN FROM BS 600-560. FABRICATED NEW INNER SKIN FROM 2024-T3 .080 PO 90010831, DIMENSION 51.75" X 43" IAW DWG AE5072, REV D. TREATED AND PRIMED PARTS IAW SRM 51-10-2, INSTALLED UPPER AFT INNER SKIN AND TRIM PANEL IAW SRM 51-30-2, 51-30-5 AND 51-30-6.

FOTR2021700653

BOEING

 

 

SHEAR TIE

CRACKED

1/11/2011

727223

 

 

 

ZONE 200

(FOTR) FUSELAGE CABIN INTERIOR, HAS CRACK INDICATION ON SHEARTIE, STR 8R BS 1130. REMOVED FASTENERS AT FUSELAGE FRAME IN MAIN CABIN BS 1130 STR 8R IAW SRM 51-30-2. C/W HFEC INSP IAW NDTM 51-00-00, FIG 23, PART 6. NO CRACKS NOTED. CUT SHEARTIE DIMENSION 6.2' X .2" IAW SRM 53-10-4, FIG 11. FABRICATED SHEARTIE REPAIR FROM 7075-0 .080 PO 900327, DIMENSION 3.5" X 6.2" IAW SRM 53-10-4, FIG 11. HEATED TREATED PART FROM 7075-0 TO 7075-T6 IAW REPORT 2-37153-801A. PARTS LOCATED AND DRILLED AT BS 1130 STRI 8R IAW SRM 51-30-5 AND 51-30-6. PARTS TREATED AND PRIMED IAW SRM 51-10-2. SHEARTIE AND SHEARTIE SUPPORT ANGLE INSTALLED IAW SRM 51-30-2 AND 53-10-4, FIG 11.

FOTR2021700656

BOEING

 

 

INTERCOSTAL

CRACKED

1/11/2011

727223

 

 

 

ZONE 200

(FOTR)FUSELAGE CABIN INTERIOR, INTERCOSTAL IS CRACKED AT STR 16L BETWEEN BS 348-360. REMOVED FASTENERS FOR ACCESS IAW SRM 51-30-2. FABRICATED NEW DOUBLER REPAIR FROM 2024-T3 .063 PO 90010689, DIMENSION 5" X 3" IAW SRM 51-40-2. TREATED AND PRIMED IAW SRM 51-10-2. INSTALLED NEW DOUBLER REPAIR IAW SRM 51-30-2 AND 51-40-2.

FOTR2021700658

BOEING

 

 

STRINGER

GOUGED

1/11/2011

727223

 

 

 

ZONE 200

(FOTR) FUSELAGE CABIN INTERIOR HAS GOUGE AT FRAME BS 360 STR 6L. CUTOUT DAMAGED AREA AT STR 6L BS 360, DIMENSION 9.8750" FABRICATED STR FILLER FROM BAC 1498-143-7075T6 DIMENSION 9.8750". FABRICATED STRAP PLATES NR1 (1 EA) FROM 2024T3 .250" DIMENSION .8" X 12.2500". FABRICATED STRAP PLATE NR2 (2 EA) FROM 7075T6 .125" DIMENSION 1" X 8.2500". FABRICATED STRAP PLATE NR 3 (2 EA) FROM 2024T3 .090' DIMENSION 1" X 12.3750". INSTALLED REPAIR STR PARTS IAW SRM 51-30-2, 51-10-1, 53-10-1, AND 53-10-3 FIG 3.

FOTR2021700682

BOEING

 

 

SEAT TRACK

CORRODED

1/11/2011

727223

 

 

 

ZONE 200

(FOTR) LT FUSELAGE CABIN INTERIOR, HAS SURFACE CORROSION ON SEAT TRACK FLANGE BETWEEN BS 720A-720D, LBL 24. REMOVED CORROSION AND FOUND TO BE OUT OF LIMITS IAW SRM 53-10-1, FABRICATED NEW SEAT TRACK FROM BAC1520-792 7178-T6511 PO 90010776 DIMENSION 17'1.7500" LONG IAW SRM 53-10-5, FIG 1. TREATED AND PRIMED IAW SRM 51-10-2. INSTALLED SEAT TRACK IAW SRM 51-30-2 AND 430-10-5, FIG 1.

FOTR2019813815

BOEING

PWA  

 

STRUCTURE

CRACKED

12/3/2010

727223

JT8D15

 

651751738

TORQUE BOX

RT SIDE OF AFT AIRSTAR TORQUE BOX UPPER CORD IS CRACKED AT AIRSTAIR ACTUATOR FITTING. REMOVED UPPER CHORD FROM RT SIDE AFT AIRSTAIR TORQUE BOX STA BS 1263 IAW 51-30-2. INSTALLED NEW ANGLE, PN 65-17517-38. PO NR 20198118 IAW SRM 51-30-2 & SB 53-0129, REV 5.

SROM2010017

BOEING

CFMINT

 

COMPRESSOR BLADE

NICKED

12/16/2010

7377BD

CFM567B22

 

 

NR 2 ENGINE

NR 2 ENG BIRD STRIKE AND INGESTION AT THE 9 O’CLOCK POSITION. BLOOD AND FEATHERS FOUND ON BLADES IN BYPASS PATH AND BOOSTER INLET. CONDITIONAL INSP COMPLIED WITH IAW AMM 05-51-18 AND 71-00-00. NO DEFECTS NOTED. ENGINE BORESCOPE INSP OF HIGH PRESSURE COMPRESSOR BLADES COMPLIED WITH. BLADES CHECKED GOOD WITH MINOR DEFECTS NOTED, ALL WITHIN LIMITS IAW MM 72-00-00.

AALA20100816SJU01

BOEING

 

 

SLAT

DAMAGED

8/16/2010

757223

 

 

 

LT WING

SJU INFLIGHT JFK-BGI - CREW REPORTED HOLE IN LEFT TRAILING EDGE SLAT. EMERGENCY DECLARED FLIGHT DIVERTED SJU LANDED WITHOUT INCIDENT. AIRCRAFT REMOVED FROM SERVICE. REPLACED LEFT WING NUMBER 5 INBOARD SLAT. SYSTEM GROUND CHECK NORMAL OPERATION.

AALA20101111TUL02

BOEING

 

 

ANGLE

CORRODED

11/11/2010

757223

 

 

18511

FUSELAGE

CREASE ANGLE CORRODED STATION 1031. REPLACED ANGLE.

2011FA0000003

BOEING

 

 

CHARGER

FAILED

1/3/2011

767383

 

 

20121

EMERGENCY LIGHT

RT WING SLIDE EMERGENCY LIGHT L391 INOP. R & R POWER SUPPLY BATTERY CHARGER.

2010FA0001259

CESSNA

CONT

 

CARBURETOR

CONTAMINATED

11/16/2010

172  

O300A

 

MA3 

ENGINE

ENGINE LOST POWER CAUSING ACFT TO MAKE AN EMERGENCY LANDING IN A SOFT FIELD RESULTING IN THE ACFT FLIPPING OVER AND CAUSING SUBSTANTIAL DAMAGE. UPON INVESTIGATION THE FAA FOUND MICROBIOLOGICAL GROWTH IN THE CARBURETOR'S FUEL BOWL AT THE DRAIN PLUG AREA CAUSING FUEL BLOCKAGE AT THE FUEL CHANNEL AND SUBSEQUENT LOSS OF POWER. THIS COULD BE AVOIDED BY REMOVING THE CARBURETOR DRAIN PLUG AT SPECIFIED INTERVALS AND DRAINING THE MOISTURE THAT MAY ACCUMULATE IN THAT AREA. RECOMMENDED INTERVAL: EVERY 100 HOURS OR AT EACH ANNUAL INSP.

2011FA0000004

CESSNA

ROTAX

 

LINK

CRACKED

12/31/2010

172E

ROTAX912ULS

 

05430358

NLG STEERING

THE NOSE GEAR UPPER STRUT TORQUE LINK HAD 2 CRACKS (1CRACK ON EACH SIDE) OF THE LOWER SIDE NEAR TO THE UPPER ATTACH POINT. IN TRYING TO FIND THE OWNER AN AIRWORTHY SERVICEABLE 1, CONTACTED 7 MAJOR SALVAGE DEALERS IN THE USA. THESE DEALERS FOUND THE SAME TYPE CRACKS IN THEIR LINKS. SUPPLIED THE DEALERS WITH A DIGITAL PHOTO OF THE DAMAGED PART. FINALLY FOUND AN UNCRACKED LINK FROM A DEALER, BUT HE FOUND 4 OF HIS WERE ALSO CRACKED. IF THE LINK WERE TO FAIL THERE WILL BE LOSS OF NOSE WHEEL STEERING AND IF THE LINK WERE TO FAIL AFTER TAKEOFF THERE IS THE POSSIBILITY OF THE NOSE WHEEL TURNING 90 DEGREES OR MORE, WHICH COULD RESULT IN COMPLETE LOSS OF THE ACFT, PILOT AND OCCUPANTS.

BIGR12/15/10

CESSNA

LYC  

 

CONTROL CABLE

FRAYED

12/15/2010

172N

O320*

 

051015262

ZONE 500

DURING ANNUAL INSP THE LT AND RT AILERON CABLES (P/N MC0510105-262)WERE FOUND TO HAVE HALF OF THE WIRE STRANDS BROKEN AT A IDLER PULLEY INBD OF THE AILERON BELLCRANKS. BOTH CABLES WERE REPLACED AND ACFT WAS RERIGGED NO OTHER DEFECTS WERE NOTED.

2011FA0000000

CESSNA

LYC  

 

CONDENSER

SHORTED

1/3/2011

172P

O360A4M

 

M3984

LT MAGNETO

ENGINE WILL ROTATE WITH STARTER BUT WILL NOT START. ACFT ENGINE REPLACED WITH ENGINE IAW STC SA-703-GL, ENGINE O/H WITH NEW MAGNETO'S AND HAS NOW ACCUMULATED 32.7 HS. FOUND THE LT MAGNETO CONDENSOR FAILED. THIS ENGINE MODIFIED BY STC TO START ON LT MAGNETO ONLY, WITH THE LT MAGNETO CONDENSOR FAILURE THE LT MAGNETO WAS INOPERATIVE. REPLACED THE LT MAGNETO CONDENSOR PN M-3984, REASSEMBLED MAGNETO AND REINSTALLED. SUBSIQUENT OPS SATISFACTORY.

2010FA0001255

CESSNA

CONT

CONT

CYLINDER HEAD

BROKEN

12/22/2010

182P

O470S

 

646680

NR 6 CYLINDER

IN CRUISE FLIGHT, ENGINE STARTED TO LOSE POWER AND BACKFIRE. PILOT MADE AN EMERGENCY LANDING IN FIELD WITH NO DAMAGE TO ACFT. VISUAL INSP OF THE ENGINE WAS ACCOMPLISHED. THE NR 6 CYLINDER WAS FOUND TO HAVE FAILURE OF EXHAUST ROCKER ARM BOSS RESULTING IN THE ROCKER ARM WRIST PIN TO BECOME DETACHED WITH PART OF THE ROCKER ARM BOSS ADHERED TO THE PIN AND UNABLE TO FUNCTION. THIS RESULTED IN THE EXHAUST PUSH ROD TUBE TO BECOME INEFFECTIVE CAUSING THE EXHAUST VALVE TO REMAIN CLOSED ALL OF THE TIME.

JRUR20101216715HP

CESSNA

 

 

DOUBLER

CRACKED

5/5/2010

182S

 

 

075360024

FIREWALL

(JRUR) A 1.25 INCH LONG CRACK WAS DISCOVERED IN THE FIREWALL FWD DOUBLER (PN 0753600-24). THE CRACK WAS LOCATED ON THE LOWER LT QUADRANT OF THE FWD FIREWALL DOUBLER. THE CRACKED LOCATION CAN BE FOUND BY LOCATING THE "BRACKET-PARKING BRAKE CONTROL" AFT OF THE FIREWALL ( REV 19, CHAPTER 32-32-02, FIGURE 01, ITEM NR38, PN 0713070-20) . TRANSLATE THIS LOCATION TO THE FWD SIDE OF THE FIREWALL. THE CRACK WAS CENTERED AROUND THE TOP RIVET ATTACHING THE (BRACKET-PARKING BRAKE CONTROL) TO THE FIREWALL AND FIREWALL DOUBLER. WHEN THE PARKING BRAKE HANDLE IS PULLED, THIS AREA OF THE FIREWALL & FIREWALL DOUBLER FLEX A LITTLE. IT IS VERY PROBABLE THAT THIS FLEXING ACTION HAS CAUSED THIS CRACK IN THE FIREWALL DOUBLER. 2 SMALL DENTS CAN BE SEEN IN THE FIREWALL FROM THE "BRACKET-PARKING BRAKE CONTROL".

JRUR2010122019HP

CESSNA

LYC  

 

DOUBLER

CRACKED

12/20/2010

182T

IO540AB1A5

 

075360024

FIREWALL

(JRUR) A 1.5 INCH LONG CRACK WAS DISCOVERED IN THE FIREWALL FWD DOUBLER (PN 0753600-24). THE CRACK WAS LOCATED ON THE LOWER LT QUADRANT OF THE FWD FIREWALL DOUBLER. THE CRACKED LOCATION CAN BE FOUND BY LOCATING THE "BRACKET-PARKING BRAKE CONTROL" AFT OF THE FIREWALL (SEE IPC REV 19, CHAPTER 32-32-02, FIGURE 01, ITEM NR38, PN 0713070-20) . TRANSLATE THIS LOCATION TO THE FWD SIDE OF THE FIREWALL. THE CRACK WAS CENTERED AROUND THE TOP RIVET ATTACHING THE "BRACKET-PARKING BRAKE CONTROL" TO THE FIREWALL AND FIREWALL DOUBLER. WHEN THE PARKING BRAKE HANDLE IS PULLED, THIS AREA OF THE FIREWALL & FIREWALL DOUBLER FLEX A LITTLE. IT IS VERY PROBABLE THAT THIS FLEXING ACTION HAS CAUSED THIS CRACK IN THE FIREWALL DOUBLER. 2 SMALL DENTS CAN BE SEEN IN THE FIREWALL FROM THE "BRACKET-PARKING BRAKE CONTROL".

2010FA0001269

CESSNA

 

 

SHAFT

FAILED

12/20/2010

208  

 

 

26012672

A/C PACK

NOTICING HIGH FAILURE RATE BETWEEN SHAFT (PN 2601267-2) AND GEAR (PN 3100450-01) LESS THAN 1,000 HRS. WHEN REPLACING GEAR WITH MFG O/H GEAR, NEW SHAFT DOES NOT FIT INTO GEAR. TRIED OTHER ACFT MFG NEW AIR CONDITIONER DRIVE SHAFTS AND THEY INSTALLED WITH NO PROBLEM. THIS IS THE 3RD MFG SHAFT/GEAR REPLACEMENT THIS YEAR, ENCOUNTERED SAME PROBLEM WITH EACH INSTALL. THE PROBLEM WAS CORRECTED BY INSTALLNG SEVERAL DIFFERENT SHAFTS, (PN 2601267-2), UNTIL THE CORRECT FIT COULD BE ACHIEVED.

2010FA0001252

CESSNA

CONT

 

ENGINE

FAILED

9/17/2010

340A

TSIO520NB

 

 

NR 2 

ENGINE SN 51773 WAS O/H UNDER WO 41675 ON 7/02/2010 AND INSTALLED IN POS 2. ACFT WAS OPERATED NORMALLY WITHOUT ANY INCIDENTS. ON 9/17/2010 THE ACFT RECEIVED A THOROUGH PREFLIGHT INSP ALONG WITH ENGINES RUN UP WITH NO DISCREPANCIES NOTED. 20 MINUTES AFTER TAKEOFF, THE ACFT HAD A CATASTROPHIC ENGINE FAILURE OF THE NR 2 ENGINE (SN 519773). NO OIL RESIDUE WAS NOTED ON THE ENGINE NARCELLE. ENGINE WAS REMOVED AND SENT FOR INSP. THE CREW THAT OPERATED THE ACFT INFORMED OF 2 QT OIL CONSUPTION ON THE NR 2 ENGINE.

2010FA0001270

CESSNA

PWA  

 

SEAT BACK

BROKEN

12/16/2010

551  

JT15D4

 

551900922

SEAT ASSY

UPPER SEAT BASE ASSY CRACKED AT CHAIR BACK ATTACH POINTS. STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE. PREVIOUS INAPPROPRIATE REPAIR. CHAIR WAS REPAIRED IAW STC STO1043WI, PN 42-0312K, AND DWG D-10394, REV A.

FCPR201000238

CESSNA

GARRTT

 

SPLICE PLATE

CORRODED

12/20/2010

650  

TFE731*

 

622112419

WS 32.0

9 CORRODED AREAS WERE FOUND ON THE LOWER SPLICE PLATE (PN 6221124-19) AT WS 32.00 COMMON TO THE LT SKID BOND ASSY (PN 6221264-47). 2 ELONGATED FASTENER HOLES AND 1 OVERSIZED FASTENER HOLE WERE ALSO FOUND ON THE LT LOWER SPLICE PLATE (PN 6221124-19) AT WS 32.00 COMMON TO THE SKID RAIL BOND ASSY. (PN 6221264-47).

2010FA0001213

CESSNA

CONT

 

ROD BOLT

LOOSE

12/2/2010

T210N

TSIO520R

 

 

CONNECTING ROD

PILOT EXPERIENCED ENGINE SUDDEN STOPPAGE IN FLIGHT AND MADE UNSCHEDULED LANDING. ANALYSIS OF THE CATASTROPHIC ENGINE FAILURE INDICATED FAILURE OCCURED WHEN THE NR5 CONNECTING ROD SEPARATED. THE CAUSE OF FAILURE OF THE CONNECTING ROD WAS A LOOSE ROD BOLT IN THE NR5 CONNECTING ROD. TIME SINCE MAJOR O/H - 4.5 HOURS.

2010FA0001272

CESSNA

CONT

 

SKIN

CRACKED

12/23/2010

T337H

IO550N

 

142256626

LT WING

(EH4R) A CRACK APPROX 1.5 INCHES IN LENGTH, RUNNING FORE AND AFT IN THE LT WING UPPER L/E SKIN AT WS 61.00 WAS DISCOVERED DURING ROUTINE MX INSP. INSP OF INSIDE L/E STRUCTURE FROM WS 49.12 TO WS 79.60 WAS PERFORMED. THE FOLLOWING DISCREPANCIES WERE FOUND: THE .032 2024 T3 "J" TYPE STRINGER, PN 1422578-11 (FIG 5, ITEM 39, STRINGER-UPPER, IPC 607-12) THAT EXTENDS FROM WS 66.0. A DETAILED BORE SCOPE INSP OF THE FRONT SPAR FROM WS 49.12 TO WS 79.60 AND AN EDDY-CURRENT INSP OF THE L/E SKIN FROM WS 55.50 TO WS 66.0 REVEALED NO OTHER DEFECTS. SAME INSP WAS PERFORMED ON RT WING. THE .032 2024 T3 "J" TYPE STRINGER, PN 1422578-1 (FIG 5, ITEM 21, STRINGER-UPPER IPC 607-12) THAT EXTENDS FROM WS 23.0 TO WS 66.0 HAS AN APPROX .2500 INCH CRACK AT THE END TERMINATING AT WS 66.0. THE .032 2024 T3 "J" TYPE STRINGER, PN 1422578-11 (FIG 5, ITEM 39, STRINGER-UPPER, IPC 607-12 THAT EXTENDS FROM WS 66.0 TO WS 121.60 HAS AN APPROX .2500 INCH CRACK AT THE END TERMINATING AT WS 66.0. THE DETAILED BORE SCOPE INSP OF THE FRONT SPAR FROM WS 49.12 TO WS 79.60 AND AN EDDY-CURRENT INSP OF THE L/E SKIN FROM WS 55.50 TO WS 66.0 REVEALED NO OTHER FAULTS. T

2010FA0001273

CESSNA

CONT

 

SKIN

CRACKED

12/23/2010

T337H

IO550N

 

14225503

WS61.00

A CRACK APPROX 2 INCHES IN LENGTH, RUNNING FORE AND AFT IN THE LT WING UPPER L/E SKIN AT WS 61.00 DISCOVERED DURING INSP. INSP OF THE INSIDE L/E STRUCTURE FROM WS 49.12 TO WS 79.60 WAS PERFORMED.

2010FA0001222

CESSNA

CONT

 

MAGNETO

FAILED

11/4/2010

TU206G

TSIO520M

 

103493504

LEFT 

THIS O/H MAGNETO WAS INSTALLED ON THE ACFT IAW MM AND STANDARD PRACTICES, TIMED TO ENG IAW MM. THE ENGINE WAS RUNUP IAW POH AND THE MAG CHECK WAS SATISFACTORY. THE ENGINE WAS SHUTDOWN AND COWLING INSTALLED. AT THE NEXT ENGINE STARE, THE LT MAGNETO FAILED TO FUNCTION, WAS REMOVED AND FOUND TO HAVE A BINDING PROBLEM WITH RESPECT TO ROTATION. ALSO, THE IMPULSE COUPLING WAS LOCKED UP AND WOULD NOT FUNCTION. THE MAG DRIVE COUPLING AND RETAINER WERE DAMAGED, CAUSING A SHIFT IN THE TIMING. EXAMINATION SHOWED A BINDING IN THE ROTATING PARTS OF THE MAGNETO AND A GRINDING SOUND. THE PART WILL BE RETURNED TO THE SUPPLIER FOR WARRANTY.

2010FA0001240

CESSNA

CONT

 

WIRE HARNESS

FAULTY

12/8/2010

U206A

IO520A

 

M1767

IGNITION

ENGINE MISFIRING AT ALL POWER SETTINGS. DIAGNOSED FAULT TO BE THE IGNITION HARNESS LEADS. UTILIZING AN EASTERN TECHNOLOGY IGNITION HARNESS TESTER. IT WAS DETERMINED ALL THE BOTTOM LEADS WERE EITHER INTERMITTENT OR NONFUNCTIONAL FOR BOTH MAGNETOS. INSTALLING A NEW HARNESS COMPLETELY ELIMINATED THE MISFIRE CONDITION.

2010FA0001258

CIRRUS

CONT

SLICK

DISTRIBUTOR BLK

MELTED

12/20/2010

SR20

IO360*

 

 

MAGNETO

DURING A 500 HOUR INSP, COMPLIANCE OF M/N 6314 MAGNETOS, LT MAGNETO SHOWED SIGNS OF EXTREAM HIGH HEAT INTERNALLY. SB SB3-08A ADDRESSES PROBLEM CAUSED BY "SOFT" CARBON BRUSHES PACKAGED FROM SEPT 1, 2004 THROUGH AUGUST 14, 2008. TT OF MAGNETO WAS DOCUMENTED AS 1672.8. MAGNETO CASE SCREW HAD FACTORY APPLIED TORQUE SEAL IN PLACE. BREAKER POINT ASSY HAD PLASTIC MATERIAL MELTED AROUND IT. FURTHER DISASSEMBLY REVEALED SOURCE OF MELTED PLASTIC AS MATERIAL FROM THE DISTRIBUTER BLOCK & GEAR ASSY. CARBON BRUSH WAS SEVERLY WORN AS DESCRIBED AND ILLUSTRATED IN SB3-08A, PAGE 2.

2011FA0000001

CNDAIR

GE  

 

SELECTOR VALVE

FAILED

12/31/2010

CL6002B16

CF34*

 

601R751461

NLG 

UPON LIFTOFF, FLIGHT CREW SELECTED GEAR UP. THE NLG WOULD NOT RETRACT AND THE NOSE GEAR DOORS WOULD NOT OPEN WITH THE "RETRACT COMMAND". THE MAIN GEAR DID RETRACT. FLIGHT CREW DECLARED AN EMERGENCY WITH ATC AND RETURNED TO DEPARTURE AIRPORT WITH ALL LANDING GEAR INDICATING DOWN AND LOCKED. AFTER LANDING, MX WAS UNABLE TO OPEN NLG DOOR WITH ELECTRICAL SELECTION VIA GROUND SERVICING SWITCH. DOOR SELECTOR VALVE WAS CHECKED FOR ELECTRICAL CONTINUITY AND AN "OPEN" WAS DISCOVERED IN THE VALVE'S WINDINGS. REPLACED VALVE AND RETURNED ACFT TO SERVICE.

V0XR413Y113010002

CNDAIR

 

 

SUPPORT FITTING

CORRODED

11/30/2010

CL6002C10

 

 

 

ZONE 200

(V0XR) SUPPORT FITTING STA 288, LBL 36 CORRODED. R & R IAW SRM 53-21-43. W/C 1055

V0XR413Y113010001

CNDAIR

GE  

 

SUPPORT FITTING

CORRODED

11/30/2010

CL6002C10

CF348C5B1

 

 

ZONE 100

(V0XR) SUPPORT FITTING STA 288, LBL 18 CORRODED. R & R FITTING IAW SRM 53-21-43. W/C 1056

V0XR413Y122210011

CNDAIR

GE  

 

ANGLE

CORRODED

12/22/2010

CL6002C10

CF348C5B1

 

 

THRESHOLD

KICKPLATE ANGLE, PASSENGER DOOR LWR THRESHOLD CORRODED. R & R KICKPLATE ANGLE DOOR LWR THRESHOLD IAW SRM 51-42-06, W/C 1068.

V0XR413Y122210012

CNDAIR

GE  

 

TRAY

CORRODED

12/22/2010

CL6002C10

CF348C5B1

 

 

L-BAND ANTENNA

AVIONICS BAY STA 195, STR 27 FWD LWR L-BAND ANTENNA TRAY CORRODED. R & R CORROSION AND OPS CK TCAS ANTENNA. IAW ARM 34-43-07. OPS CHECK OK. W/C 1072

V0XR413Y122210013

CNDAIR

GE  

 

SILL

CORRODED

12/22/2010

CL6002C10

CF348C5B1

 

 

ZONE 100

AFT CARGO DOOR THRESHOLD LOWER SILL CORRODED. R & R LOWER SILL AFT CARGO DOOR IAW SRM 53-61-23/ SRM 51-42-06/ SRM 51-42-13, W/C 2084.

V0XR413Y122210014

CNDAIR

GE  

 

SEAT TRACK

CORRODED

12/22/2010

CL6002C10

CF348C5B1

 

 

BS 797

MAIN PAX CABIN, RT SIDE WALL SEAT RAIL, FUS STA: 797.00 HAS LIGHT CORROSION. GROUND CORROSION, CLEANED, AND EVALUATED SEAT RAIL IAW SRM 53-41-49. DETERMINED OUT OF TOLERANCE. R & R STA 785, 15-797, W/C 2120

V0XR413Y122210006

CNDAIR

GE  

 

THRESHOLD

CORRODED

12/22/2010

CL6002C10

CF348C5B1

 

 

ZONE 100

(V0XR) FITTING, PASSENGER DOOR THRESHOLD CORRODED. R & R FITTING CLOSING IAW SRM 51-42-06. W/C 1048

V0XR413Y122210001

CNDAIR

GE  

 

THRESHOLD

CORRODED

12/22/2010

CL6002C10

CF348C5B1

 

 

ZONE 200

(V0XR) PASSENGER DOOR THRESHOLD MID CAP CORRODED. R & R MID CAP ANGLE IAW SRM 51-41-02. W/C 1039

V0XR413Y122210007

CNDAIR

GE  

 

FITTING

CORRODED

12/22/2010

CL6002C10

CF348C5B1

 

 

ZONE 100

(V0XR) FITTING STA 310 LBL 18 CORRODED. R & R FITTING IAW SRM 51-42-21. W/C 1049

V0XR413Y122210002

CNDAIR

GE  

 

CROSSBEAM

CORRODED

12/22/2010

CL6002C10

CF348C5B1

 

 

BS 280

(V0XR) STA 280 CROSSBEAM CORRODED BEYOND LIMITS. R & R CROSSBEAM FS 280.00 IAW REO 670-53-11-047 W/C 1040

V0XR413Y122210003

CNDAIR

GE  

 

BULKHEAD

CORRODED

12/22/2010

CL6002C10

CF348C5B1

 

 

BS 280

(V0XR) STA 280 BULKHEAD LOWER LT AND RT PANELS CORRODED. R & R LWR BULKHEAD LT AND RT PANELS IAW SRM 53-11-10 (STA 280). W/C 1045

V0XR413Y122210004

CNDAIR

GE  

 

SILL

CORRODED

12/22/2010

CL6002C10

CF348C5B1

 

 

BS 280-310

(V0XR) FLOOR SILL STRUCTURE FS 280-310 LT CORRODED. R & R LT FLOOR SILL FS 280-310 IAW SRM 51-42-06. W/C 1046

V0XR413Y122210005

CNDAIR

GE  

 

ANGLE

CORRODED

12/22/2010

CL6002C10

CF348C5B1

 

 

ZONE 100

(V0XR) SERVICE DOOR SURROUND STRUCTURE LWR THRESHOLD MOUNTING ANGLE CORRODED. R & R MOUNTING ANGLE IAW SRM 51-42-06/SRM 53-21-23/SRM 51-40-11. W/C 1047

V0XR413Y122210008

CNDAIR

GE  

 

FLOORBEAM

CORRODED

12/22/2010

CL6002C10

CF348C5B1

 

 

ZONE 100

(V0XR) FLOOR SUPPORT, STA 280 BL 0 CORRODED.

V0XR413Y122210009

CNDAIR

GE  

 

FLOORBEAM

CRACKED

12/22/2010

CL6002C10

CF348C5B1

 

 

BS 280

(V0XR) T-FITTING, STA 280, RVL 11.16 CRACKED. R & R TEE FITTING, STA 280, RBL 11.16 IAW SRM 51-42-21. W/C 1051

2010FA0001250

DHAV

PWA  

 

ATTACH BRACKET

CORRODED

11/9/2010

DHC2*

R985*

 

BSFS159160

HORIZONTAL STAB

BOTH LT AND RT FWD HORIZ STABILIZER ATTACH BRACKETS WERE INSTALLED AS PART OF THE AOG AIR SUPPORT WING ANGLE MOD (STC SA01258NY) DURING ANNUAL INSP FOUND HORIZ STABILIZER FWD ATTACH TO BE LOOSE. PART IS ATTACHED TO THE FWD SPAR OF THE HORIZ STABILIZER WITH 2 BOLTS. THE AREA OF CONCERN IS THE CTR ATTACH POINT, WHERE THE FUSELAGE ATTACH POINTS CONNECT TOTHE BRACKETS. THE PART IS MADE OF ALUMINUM AND HAS 2 STEEL BUSHINGS PRESSED INTO THE FITTING. THESE BUSHINGS ARE BELOW ALUMINUM SURFACE SO THE ATTACH POINT ON THE FUSELAGE WEARS INTO THE ALUMINUM BRACKET. DUE TO THIS BEING INSTALLED ON A SEA-PLANE, CORROSION SETS IN CAUSING THE STABILIZER TO HAVE EXCESSIVE PLAY ON THE FWD EDGE. CORRECTION PUT IN FLANGED STEEL BUSHING SO THE FUSELAGE ATTACH POINTS WOULD CONTACT THE STEEL BUSHING INSTEAD OF THE ALUMINUM BRACKET.

CA100729002

DIAMON

ROTAX

 

TUBE

CUT  

7/24/2010

DA20A1

ROTAX912F3

 

 

TIRE 

FOLLOWING A NORMAL LANDING, THE ACFT SUFFERED A FLAT TIRE ON TAXI BACK TO THE RAMP. UPON DISASSEMBLY OF THE WHEEL, IT WAS DISCOVERED THAT THE INNER TUBE WAS CUT BY A LOOSE CORD ON THE INSIDE OF THE TIRE. THIS IS THE 3RD SIMILAR INCIDENT WITHIN 6 MONTHS AT THIS FACILITY, ALL WITH THE SAME TIRE PN. UPON INVESTIGATION THE OTHER TIRES ALSO HAD A LOOSE CORD ON THE INSIDE OF THE TIRE WITH A CORRESPONDING SLICE IN THE INNER TUBE.

GSPA893DS

DIAMON

 

 

GPS  

FAILED

12/16/2010

DA40

 

 

0110108000

COCKPIT

(GSPR) OWNER REPORTED GPS "BLANKED OUT" AND WAS INOPERATIVE.

NX4R20101118001

DIAMON

 

 

TANK

CRACKED

11/18/2010

DA42

 

 

D6028141100

ZONE 400

(N3XR) DURING AN ANNUAL INSP, THE TECH NOTICED A WET FUEL STAIN UNDER THE LT AUX FUEL TANK. WHEN THE TANK WAS REMOVED, THE TANK WAS FOUND TO BE CRACKED AROUND SEVERAL OF THE AFT SPOT WELD LOCATION ON THE LOWER AFT SURFACE OF THE TANK.

NX4R20101004001

DIAMON

LYC  

 

TANK

CRACKED

10/4/2010

DA42

IO360M1A

 

D6028141100

ZONE 400

DURING AN ANNUAL INSP, THE TECH NOTICED A WET FUEL STAIN UNDER THE LT AUX FUEL TANK. WHEN THE TANK WAS REMOVED, THE TANK WAS FOUND TO BE CRACKED AROUND SEVERAL OF THE AFT SPOT WELD LOCATION ON THE LOWER AFT SURFACE OF THE TANK.

NX4R00006

DIAMON

THIELT

 

FUEL CELL

CRACKED

11/24/2010

DA42

TAE1250299

 

D6028141200

RT AUX

DURING AN ANNUAL INSP, THE TECH NOTICED A WET FUEL STAIN UNDER THE RT AUX FUEL TANK. WHEN THE TANK WAS REMOVED, THE TANK WAS FOUND TO BE CRACKED AROUND SEVERAL OF THE AFT SPOT WELD LOCATION ON THE LOWER AFT SURFACE OF THE TANK.

EE4Y100539

DOUG

 

 

LONGERON

CORRODED

12/15/2010

DC982

 

 

59364311

BS 1200 L28L

(EE4Y) LOWER FUSELAGE, AFT CARGO COMPARTMENT AT Y STA 1200 LONG 28 LT WITH CORROSION.

EE4Y100540

DOUG

 

 

LONGERON

CORRODED

12/15/2010

DC982

 

 

59360271

ZONE 100

(EE4Y) LOWER FUSELAGE, AFT CARGO COMPARTMENT AT Y STA 1200, LONG 29 LT WITH CORROSION.

EE4Y100542

DOUG

 

 

LONGERON

CORRODED

12/15/2010

DC982

 

 

59360281

ZONE 100

(EE4Y) LOWER FUSELAGE, AFT CARGO COMPARTMENT AT Y STA 1200, LONG 30 WITH CORROSION.

EE4Y100541

DOUG

 

 

LONGERON

CORRODED

12/15/2010

DC982

 

 

 

ZONE 100

(EE4Y) LOWER FUSELAGE, MID CARGO COMPARTMENT FROM Y STA 590 TO 780 LONG 30 CORRODED.

EE4Y100547

DOUG

 

 

SKIN

CORRODED

12/10/2010

DC982

 

 

 

BS 712-731

(EE4Y) LOWER FUSELAGE, MID CARGO COMPARTMENT FROM STA 712 TO STA 731 BETWEEN LONGERON 29LT & 29RT PLATING (SKIN) WITH CORROSION. NOTE: THE CORROSION (BLENDOUT) REQUIRES A MAJOR REPAIR.

EE4Y100538

DOUG

 

 

FRAME

CORRODED

12/10/2010

DC982

 

 

3936492501

ZONE 100

(EE4Y) LOWER FUSELAGE AFT CARGO COMPARTMENT Y:STA 1155 BETWEEN LONGERON 29R AND LONGERON 30, FORMER RIB WITH CORROSION.

EE4Y100536

DOUG

 

 

FLOORBEAM

CORRODED

12/10/2010

DC982

 

 

5936597511

ZONE 100

(EE4Y) LOWER FUSELAGE FWD CARGO COMPARTMENT STA Y 465 +X16 AND -X13 FLOOR SUPPORT TEE CORRODED.

EE4Y100537

DOUG

 

 

FLOORBEAM

CORRODED

12/10/2010

DC982

 

 

5936597513

ZONE 100

LOWER FUSELAGE FWD CARGO COMPARTMENT STA Y 370 BETWEEN -X8 AND +X15 FLOOR SUPPORT TEE CORRODED.

EE4Y20110004

DOUG

 

 

SUPPORT FITTING

CORRODED

1/10/2011

DC982

 

 

5956034561

ZONE 100

(EE4Y) LOWER FUSELAGE AFT CARGO COMPARMENT Y STA 1287 BETWEEN LONGERONS 27 AND 28RT AND BETWEEN LONGERONS 27 AND 28LT SUPPORT FITTING CORRODED.

EE4Y1012015

DOUG

 

 

SKIN

DENTED

12/30/2010

DC983

 

 

 

ZONE 100

(EE4Y) LOWER EXTERNAL FUSELAGE AT STA 1288 BETWEEN LONGERONS 25L AND 26L SKIN WITH DENT. PERMANENT REPAIR WAS PERFORMED ON THE FUSELAGE SKIN IAW SG09530002 VIEW H1, SHEETS 1 AND 10.

EE4Y1012004

DOUG

 

 

SUPPORT FITTING

CORRODED

12/27/2010

DC983

 

 

39361901

ZONE 200

(EE4Y) DURING STRUCTURAL INSP, REPORTED AT UPPER FUSELAGE PAX CABIN FWD RT DOOR CUTOUT SLIDE SUPPORT FITTING WITH CORROSION

EE4Y1012002

DOUG

 

 

FLOOR SUPPORT

CORRODED

12/24/2010

DC983

 

 

3957317501

ZONE 100

(EE4Y) LOWER FUSELAGE, AFT CARGO COMPARTMENT, ST YSTA 1152, BETWEEN LONG 30 AND 28R, FLOOR SUPPORT CORRODED.

EE4Y1012003

DOUG

 

 

FRAME

CRACKED

12/27/2010

DC983

 

 

 

ZONE 200

(EE4Y) REAR FUSELAGE, FRAME CANTED STA 1463 -X8.5 OTBD CHORD (CAP) WITH CRACK. NOTE: THE CAP CRACK REQUIRES A MAJOR REPAIR.

EE4Y1012009

DOUG

 

 

SKIN

DENTED

12/30/2010

DC983

 

 

 

FUSELAGE

(EE4Y) DURING STRUCTURAL INSP, REPORTED AT UPPER EXTERNAL FUSELAGE BETWEEN STA 55 AND STA 62 AT +Z15 RT SIDE SKIN WITH DENT.

EE4Y1012010

DOUG

 

 

SKIN

DENTED

12/30/2010

DC983

 

 

 

FUSELAGE

(EE4Y) DURING STRUCTURAL INSP, REPORTED AT LOWER EXTERNAL FUSELAGE AT STA 38-Z 2.5 RT SIDE SKIN WITH DENT.

EE4Y1012005

DOUG

 

 

SKIN

DAMAGED

12/27/2010

DC983

 

 

 

ZONE 200

DURING STRUCTURAL INSP, REPORTED AT UPPER EXTERNAL FUSELAGE AT STA 214 BETWEEN LONGERONS 17L AND 18L SKIN WITH BLEND OUT.

EE4Y1012006

DOUG

 

 

SKIN

CORRODED

12/27/2010

DC983

 

 

2024T3CLADSHEET

ZONE 100

(EE4Y) EXTERNAL FUSELAGE SKIN AT AFT TOILET SERVICE PANEL CUTOUT YSTA 1311, BETWEEN LONG 21L AND 22L, SKIN CORRODED.

EE4Y1012007

DOUG

 

 

SKIN

DELAMINATED

12/28/2010

DC983

 

 

 

DOOR 

LT WING T/E BUTTE DOOR DELAMINATED.

EE4Y1012008

DOUG

 

 

SKIN

CORRODED

12/27/2010

DC983

 

 

 

RT WING

(EE4Y) RT WING, FRONT SPAR AREA STA XFS 129 , L/E LOWER PLATING WITH CORROSION. NOTE: THE CORROSION REQUIRES A MAJOR REPAIR.

EE4Y1101027

DOUG

 

 

SEAT TRACK

CORRODED

1/4/2011

MD83

 

 

 

FUSELAGE

UPPER FUSELAGE PAX CABIN AT STA 218, -X55 SEAT TRACK WITH CORROSION. DAMAGED SEAT TRACK WAS REPAIRED IN ACCORDANCE WITH MD-80 SRM 53-05 FIGURE 4F VIEW E.

V0XR201012230031

EMB  

 

 

SEAT TRACK

CORRODED

12/23/2010

EMB145LR

 

 

14532605003

ZONE 100

(V0XR) RT SEAT TRACK D-2 BETWEEN 30-35 IS CORRODED BEYOND LIMITS. R & R RT SEAT TRACK. W/C 2132

V0XR201012230032

EMB  

 

 

SEAT TRACK

CORRODED

12/23/2010

EMB145LR

 

 

14532606015

ZONE 100

(V0XR) LT SEAT TRACK A-4 BETWEEN 35-47 IS CORRODED BEYOND LIMITS. R & R LT SEAT TRACK. W/C 2122

V0XR20101221001

EMB  

 

 

GUSSET

CORRODED

12/21/2010

EMB145LR

 

 

14522460015

ZONE 100

(V0XR) GUSSET AT FR 17-18, Y0.0, LY-479.0 IS CORRODED OUT OF LIMITS. REMOVED AND REPLACED GUSSET IAW EMB145 SRM 51-10-02, 51-10-03, AND 51-40-02. W/C 1074

V0XR20101221002

EMB  

 

 

FLOOR SUPPORT

CORRODED

12/21/2010

EMB145LR

 

 

14521713605

ZONE 100

(V0XR) RT HAT BEAM AT RY 479.0, FR 19-25 IS CORRODED OUT OF LIMITS. R & R RT OMEGA BEAM FROM FR 19-25 IAW SRM 51-40-00 AND 51-20-03. W/C 1079.

V0XR20101221003

EMB  

 

 

SILL

CORRODED

12/21/2010

EMB145LR

 

 

14521725001

ZONE 100

(V0XR) LT SILL AT FR 18-23 IS CORRODED OUT OF LIMITS. R & R LT SILL FROM FR 18-23 IAW SRM 51-40-02. W/C 1081

V0XR20101221004

EMB  

 

 

SUPPORT BRACKET

CORRODED

12/21/2010

EMB145LR

 

 

14524131009

ZONE 100

(V0XR) PAX DOOR THRESHOLD SUPPORT BRACKETS CORRODED OUT OF LIMITS. R & R ANGLES IAW SRM 51-20-03. W/C 1084

V0XR20101221005

EMB  

 

 

SILL

CORRODED

12/21/2010

EMB145LR

 

 

14520609001

ZONE 100

(V0XR) LT SILL AT FR 23-29 IS CORRODED OUT OF LIMITS. R & R SILL AT FR 23-29 IAW SRM 51-40-02. W/C 1106

V0XR20101221006

EMB  

 

 

SILL

CORRODED

12/21/2010

EMB145LR

 

 

14520609005

ZONE 100

(V0XR) RT SILL AR FR 23-29 IS CORRODED OUT OF LIMITS. R & R RT SILL AT FR 23-29 IAW SRM 51-10-02, 51-20-03, 51-40-02, CMP 51-21-04. W/C 1114

V0XR20101221007

EMB  

 

 

SILL

CORRODED

12/21/2010

EMB145LR

 

 

14529495001

ZONE 100

(V0XR) LT SILL AT FR 53-59 IS CORRODED OUT OF LIMITS. R & R SILL IAW SRM 53-24-10, 51-10-02, 51-20-03, 51-40-02, CMP 51-21-04. W/C 2081

V0XR201012230001

EMB  

 

 

PROFILE

CORRODED

12/23/2010

EMB145LR

 

 

14525994003

ZONE 100

(V0XR) LT PROFILE AT FR 61 IS CORRODED OUT OF LIMITS. R & R LT PROFILE. W/C 1063

V0XR201012230002

EMB  

 

 

GUSSET

CORRODED

12/23/2010

EMB145LR

 

 

14522460013

ZONE 100

(V0XR) CTR GUSSET AT YO.O FR 20-23 IS CORRODED OUT OF LIMITS. R & R CTR GUSSET. W/C 1073

V0XR201012230003

EMB  

 

 

FLOOR SUPPORT

CORRODED

12/23/2010

EMB145LR

 

 

14522459003

ZONE 100

(V0XR) FLOOR SUPPORT AT YO.O FR 19-20 IS CORRODED OUT OF LIMITS. R & R FLOOR SUPPORT. W/C 1077

V0XR201012230004

EMB  

 

 

PROFILE

CORRODED

12/23/2010

EMB145LR

 

 

14521718007

ZONE 100

(V0XR) PROFILE AT FR 20 IS CORRODED OUT OF LIMITS. R & R PROFILE. W/C 1078

V0XR20101221009

EMB  

 

 

SILL

CORRODED

12/21/2010

EMB145LR

 

 

14529495003

ZONE 100

(V0XR) LT SILL AT FR 59-60 IS CORRODED OUT OF LIMITS. R & R LT SILL AT FR 59-60 IAW SRM 51-40-02, 51-10-02, 51-20-02, AND CPM 51-21-05. W/C 2085

V0XR201012230006

EMB  

 

 

DOUBLER

CORRODED

12/23/2010

EMB145LR

 

 

14522461011

ZONE 100

(V0XR) DOUBLER AT RY 479.0 FR 20-22 IS CORRODED OUT OF LIMITS. R & R DOUBLER. W/C 1082

V0XR201012270019

EMB  

 

 

FLOOR PANEL

CORRODED

12/27/2010

EMB145LR

 

 

14533959401

COCKPIT

(V0XR) COCKPIT FLOOR PANEL 221GF IS DAMAGED BEYOND LIMITS. R & R FLOOR PANEL. W/C 2157

V0XR201012270020

EMB  

 

 

SEAL

WORN

12/27/2010

EMB145LR

 

 

14525921901

HORIZONTAL STAB

(V0XR) LT HORIZONTAL INBD L/E SEAL PANEL 333DL IS WORN BEYOND LIMITS. R & R SEAL. W/C 3063

V0XR201012270021

EMB  

 

 

ATTACH ANGLE

CRACKED

12/27/2010

EMB145LR

 

 

14567291001

LT WING

(V0XR) LT FWD BOTTOM WING-FAIRING ATTACHMENT ANGLE IS CRACKED. R & R ANGLE. W/C 5068

V0XR201101110013

EMB  

 

 

GUSSET

CORRODED

1/11/2011

EMB145LR

 

 

14522460015

ZONE 100

(V0XR) HORSHOE DIGITAL FR 17-18 FROM LY 479.0 TO Y0.0 IS CORRODED OUT OF LIMITS. R & R DIGITAL.

V0XR201101110014

EMB  

 

 

DOUBLER

CORRODED

1/11/2011

EMB145LR

 

 

14522461015

ZONE 100

(V0XR) RT BEAM DOUBLER AT FR 18 IS CORRODED BEYOND LIMITS. R & R DOUBLER.

V0XR201101110016

EMB  

 

 

SILL

CORRODED

1/11/2011

EMB145LR

 

 

14525800010

ZONE 100

(V0XR) RT SILL FR 36-41 IS CORRODED BEYOND LIMITS. R & R SILL.

V0XR201101110017

EMB  

 

 

SILL

CORRODED

1/11/2011

EMB145LR

 

 

14525800016

ZONE 100

(V0XR) RT SILL FR 48-52 IS CORRODED BEYOND LIMITS. R & R SILL.

V0XR201101110018

EMB  

 

 

SILL

CORRODED

1/11/2011

EMB145LR

 

 

14525800013

ZONE 100

(V0XR) LT SILL FR 41-48 IS CORRODED BEYOND LIMITS. R & R SILL.

V0XR201101110024

EMB  

 

 

BRACKET

BROKEN

1/11/2011

EMB145LR

 

 

14526324001

ZONE 800

(V0XR) UPLOCK BRACKET FOR CARGO DOOR BROKEN. R & R BRACKET.

V0XR201101110015

EMB  

 

 

ANGLE

CORRODED

1/11/2011

EMB145LR

 

 

14522466009

ZONE 100

(V0XR) SCALLOPED ANGLE AT FR 18 RY 780.0 TO LY 479.0 IS CORRODED BEYOND LIMITS. R & R DOUBLER.

V0XR201101120001

EMB  

 

 

GUSSET

CORRODED

1/12/2011

EMB145LR

 

 

14526437001

ZONE 100

GUSSET AT FR 59-62 RY 479.0 IS CORRODED BEYOND LIMITS. R & R GUSSET.

V0XR201101120003

EMB  

 

 

PROFILE

CORRODED

1/12/2011

EMB145LR

 

 

14525140023

ZONE 100

PROFILE AT FR 17 - 18 FROM LY780.0 IS CORRODED BEYOND LIMITS. R & R PROFILE.

V0XR201101120004

EMB  

 

 

SILL

CORRODED

1/12/2011

EMB145LR

 

 

14590070005

ZONE 100

AFT SILL AT FR 22-23 FROM RY780.0 IS CORRODED BEYOND LIMITS. R & R SILL.

V0XR201101120005

EMB  

 

 

SUPPORT ANGLE

CORRODED

1/12/2011

EMB145LR

 

 

1452459003

ZONE 100

SUPPORT ANGLE AT FR 19 - 20 FROM Y0.0 IS CORRODED BEYOND LIMITS. R & R ANGLE.

V0XR201101120006

EMB  

 

 

SUPPORT ANGLE

CORRODED

1/12/2011

EMB145LR

 

 

14590082003

ZONE 100

SUPPORT ANGLE AT FR 20 FROM Y0.0 IS CORRODED BEYOND LIMITS. R & R ANGLE. W/C 1098

V0XR201101120007

EMB  

 

 

DOUBLER

CORRODED

1/12/2011

EMB145LR

 

 

14522461011

ZONE 100

DOUBLERS AT FR 20 - 22 FROM RY479.0 IS CORRODED BEYOND LIMITS. R & R DOUBLERS.

V0XR201101120008

EMB  

 

 

FLOOR SUPPORT

CORRODED

1/12/2011

EMB145LR

 

 

14521700007

ZONE 100

LEFT FWD OMEGA BEAM AT FR 14-23 IS CORRODED BEYOND LIMITS. R & R BEAM.

V0XR201101120009

EMB  

 

 

GUSSET

CORRODED

1/12/2011

EMB145LR

 

 

14521699003

ZONE 100

LEFT GUSSET AT FR 20 - 24 IS CORRODED BEYOND LIMITS. R & R GUSSET.

V0XR2011011200010

EMB  

 

 

STRIP

CORRODED

1/12/2011

EMB145LR

 

 

14572167004

ZONE 100

RIGHT UPPER WING TO BODY FAIRING STRIP BETWEEN STA 16143.5 - 17445.0 IS CRACKED. R & R GUSSET.

V0XR2011011200011

EMB  

 

 

SILL

CORRODED

1/12/2011

EMB145LR

 

 

14525382001

ZONE 100

RIGHT SILL FR 65 - 68 IS CORRODED BEYOND LIMITS. R & R SILL.

V0XR2011011200012

EMB  

 

 

BRACKET

CORRODED

1/12/2011

EMB145LR

 

 

14572110002

ZONE 100

WING TO BODY FAIRING BRACKET BETWEEN FR 48-49 IS CRACKED. R & R STRIP.

V0XR2011011200013

EMB  

 

 

SEAT TRACK

CORRODED

1/12/2011

EMB145LR

 

 

14530659001

ZONE 100

(V0XR) SEAT TRACK POS B AT FR 24-30 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK.

V0XR2011011200014

EMB  

 

 

SEAT TRACK

CORRODED

1/12/2011

EMB145LR

 

 

14530659009

ZONE 100

(V0XR) SEAT TRACK POS B AT FR 52-60 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK.

V0XR2011011200015

EMB  

 

 

SEAT TRACK

CORRODED

1/12/2011

EMB145LR

 

 

14532605015

ZONE 100

(V0XR) SEAT TRACK POS D AT FR 36-47 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK.

V0XR2011011200016

EMB  

 

 

SEAT TRACK

CORRODED

1/12/2011

EMB145LR

 

 

14532605001

ZONE 100

SEAT TRACK POS D AT FR 24-30 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK.

V0XR2011011200017

EMB  

 

 

SEAT TRACK

CORRODED

1/12/2011

EMB145LR

 

 

14532605017

ZONE 100

SEAT TRACK POS D AT FR 47-52 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK.

V0XR2011011200018

EMB  

 

 

CHANNEL

CORRODED

1/12/2011

EMB145LR

 

 

14523171003

ZONE 100

RT HAT BEAM AT FR 58-62 IS CORRODED BEYOND LIMITS. R & R BEAM HAT.

V0XR2011011200019

EMB  

 

 

PARTITION

CORRODED

1/12/2011

EMB145LR

 

 

14523171003

ZONE 100

LT LOWER PARTITIAN AT FR 61 IS CORRODED BEYOND LIMITS. R & R PARTITIAN.

V0XR201101120002

EMB  

 

 

SILL

CORRODED

1/12/2011

EMB145LR

 

 

14525422003

ZONE 100

RIGHT SILL AT FR 61-65 IS CORRODED BEYOND LIMITS. R & R SILL.

V0XR201101130004

EMB  

 

 

SEAT TRACK

CRACKED

1/13/2011

EMB145LR

 

 

14530659011

ZONE 100

SEAT TRACK POS B FR 18-24 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 2139.

V0XR201101050001

EMB  

 

 

GUSSET

CORRODED

1/5/2011

EMB145LR

 

 

14530633001

ZONE 100

(V0XR) LT GUSSET FROM FRAMES 23-29 ARE CORRODED BEYOND LIMITS. R & R GUSSET.

V0XR201101050002

EMB  

 

 

GUSSET

CORRODED

1/5/2011

EMB145LR

 

 

14520609001

ZONE 100

(V0XR) LT SILL FROM FRAMES 23-29 ARE CORRODED BEYOND LIMITS. R & R GUSSET.

V0XR201101050003

EMB  

 

 

SILL

CORRODED

1/5/2011

EMB145LR

 

 

14520609005

ZONE 100

(V0XR) RT SILL FROM FRAMES 24-29 ARE CORRODED BEYOND LIMITS. R & R SILL.

V0XR201101070005

EMB  

 

 

GUSSET

CORRODED

1/7/2011

EMB145LR

 

 

14522226003

ZONE 100

(V0XR) GUSSET AT Y0 FRAME 59-62 IS CORRODED BEYOND LIMITS. R & R GUSSET.

V0XR201101070006

EMB  

 

 

SILL

CORRODED

1/7/2011

EMB145LR

 

 

14520609007

ZONE 100

(V0XR) RT SILL FRAME 29-35 IS CORRODED BEYOND LIMITS. R & R RT SILL.

V0XR201101070007

EMB  

 

 

SILL

CORRODED

1/7/2011

EMB145LR

 

 

14525422001

ZONE 100

(V0XR) LT SILL FRAME 61-65 IS CORRODED BEYOND LIMITS. R & R LT SILL.

V0XR201101070008

EMB  

 

 

GUSSET

CORRODED

1/7/2011

EMB145LR

 

 

14522226003

ZONE 100

(V0XR) GUSSET AT LY479.0 FRAME 59-61 IS CORRODED BEYOND LIMITS. R & R GUSSET.

V0XR201101070009

EMB  

 

 

SILL

CORRODED

1/7/2011

EMB145LR

 

 

14521725001

ZONE 100

(V0XR) SILL AT LY780.0 FRAME 19-24 IS CORRODED BEYOND LIMITS. R & R SILL.

V0XR201101070001

EMB  

 

 

SUPPORT ANGLE

CRACKED

1/7/2011

EMB145LR

 

 

14567291002

WNG-BDY FAIRING

(V0XR) LOWER RT WING TO BODY FAIRING SUPPORT ANGLE IS CRACKED. R & R RT ANGLE.

V0XR201101070002

EMB  

 

 

SUPPORT ANGLE

CRACKED

1/7/2011

EMB145LR

 

 

14567291001

WNG-BDY FAIRING

(V0XR) LOWER LT WING TO BODY FAIRING SUPPORT ANGLE IS CRACKED. R & R LT ANGLE.

V0XR201101070003

EMB  

 

 

ANGLE

CRACKED

1/7/2011

EMB145LR

 

 

14524131009

ZONE 100

(V0XR) SHAPE U ANGLE ON PASSENGER DOOR ENTRY CORRODED BEYOND LIMITS. R & R ANGLE.

V0XR201101070004

EMB  

 

 

ANGLE

CRACKED

1/7/2011

EMB145LR

 

 

14524131011

ZONE 100

(V0XR) SHAPE U ANGLE ON PASSENGER DOOR ENTRY CORRODED BEYOND LIMITS. R & R ANGLE.

V0XR201012280002

EMB  

 

 

SILL

CORRODED

12/29/2010

EMB145LR

 

 

14525800010

ZONE 100

(V0XR) RIGHT FLOOR SILL AT FRAME 36-41 IS CORRODED BEYOND LIMITS. R & R SILL. W/C 1091

V0XR201012280003

EMB  

 

 

FLOOR SUPPORT

CORRODED

12/29/2010

EMB145LR

 

 

2024T3050

ZONE 100

(V0XR) LT OMEGA BEAM AT FRAME 48 IS CORRODED BEYOND LIMITS. R & R DAMAGED AREA ON OMEGA BEAM. W/C 1110

V0XR201101110001

EMB  

 

 

ATTACH ANGLE

CRACKED

1/11/2011

EMB145LR

 

 

14566044603

LT WING ATTACH

(V0XR) LT LOWER FWD WING ATTACHMENT ANGLE CRACKED. R & R ATTACHMENT ANGLE.

V0XR201101110002

EMB  

 

 

GUSSET

CORRODED

1/11/2011

EMB145LR

 

 

14530634003

ZONE 100

(V0XR) GUSSET ON CENTER BEAM AT FR 36-41 IS CORRODED BEYOND LIMITS. R & R GUSSET.

V0XR201101110003

EMB  

 

 

GUSSET

CORRODED

1/11/2011

EMB145LR

 

 

14530634007

ZONE 100

GUSSET ON CTR BEAM AT FR 41-46 IS CORRODED BEYOND LIMITS. R & R GUSSET.

V0XR201101110004

EMB  

 

 

GUSSET

CORRODED

1/11/2011

EMB145LR

 

 

14530633006

ZONE 100

(V0XR) GUSSET ON CTR BEAM AT FR 29-35 IS CORRODED BEYOND LIMITS. R & R GUSSET.

V0XR201101110005

EMB  

 

 

SILL

CORRODED

1/11/2011

EMB145LR

 

 

14525800014

ZONE 100

(V0XR) RT SILL AT FR 41-48 IS CORRODED OUT OF LIMITS. R & R RT SILL.

V0XR201101110006

EMB  

 

 

GUSSET

CORRODED

1/11/2011

EMB145LR

 

 

14530633003

ZONE 100

(V0XR) CTR GUSSET AT FR 23-29 IS CORRODED OUT OF LIMITS. R & R GUSSET.

V0XR201101110007

EMB  

 

 

STRUCTURE

CORRODED

1/11/2011

EMB145LR

 

 

14521721009

ZONE 100

(V0XR) FWD DIGITAL AT FR 14-16 AT RY 780.0 TO RY780.0 IS CORRODED OUT OF LIMITS. R & R DIGITAL.

V0XR201101110008

EMB  

 

 

FLOOR SUPPORT

CORRODED

1/11/2011

EMB145LR

 

 

14530628001

ZONE 100

(V0XR) CTR OMEGA BEAM AT FR 17-25 AT Y0.0 IS CORRODED OUT OF LIMITS. R & R OMEGA BEAM.

V0XR201101110009

EMB  

 

 

GUSSET

CORRODED

1/11/2011

EMB145LR

 

 

14522460013

ZONE 100

(V0XR) CTR GUSSET FR 20-23 AT Y0.0 IS CORRODED OUT OF LIMITS. R & R GUSSET.

V0XR201101110010

EMB  

 

 

ANGLE

CORRODED

1/11/2011

EMB145LR

 

 

14529150009

ZONE 100

(V0XR) SCALLOPED ANGLE FR 23 AT Y0.0 TO RY 780.0 IS CORRODED OUT OF LIMITS. R & R ANGLE.

V0XR201101110011

EMB  

 

 

FLOOR SUPPORT

CORRODED

1/11/2011

EMB145LR

 

 

14521719003

ZONE 100

(V0XR) OMEGA CTR BEAM FR 14-18 IS CORRODED OUT OF LIMITS. R & R OMEGA CTR BEAM.

V0XR201101110012

EMB  

 

 

CHANNEL

CORRODED

1/11/2011

EMB145LR

 

 

14524151005

ZONE 100

(V0XR) CTR HAT CHANNEL BEAM SUPPORT FR 14 Y0.0 IS CORRODED OUT OF LIMITS. R & R SUPPORT.

V0XR201101110019

EMB  

 

 

SILL

CORRODED

1/11/2011

EMB145LR

 

 

14521725401

ZONE 100

(V0XR) FWD SILL FR 19-20 AT RY 780.0 IS CORRODED BEYOND LIMITS. R & R SILL.

V0XR201101110020

EMB  

 

 

SEAT TRACK

CORRODED

1/11/2011

EMB145LR

 

 

14532606015

ZONE 100

(V0XR) SEAT TRACK POSITION A FR 36-47 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK.

V0XR201101110021

EMB  

 

 

SEAT TRACK

CORRODED

1/11/2011

EMB145LR

 

 

14532606003

ZONE 100

(V0XR) SEAT TRACK POSITION A FR 30-36 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK.

V0XR201101110022

EMB  

 

 

SEAT TRACK

CORRODED

1/11/2011

EMB145LR

 

 

14530659003

ZONE 100

(V0XR) SEAT TRACK POSITION B FR 30-36 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK.

V0XR201101110023

EMB  

 

 

GUSSET

CORRODED

1/11/2011

EMB145LR

 

 

14573504406

ZONE 100

(V0XR) RT WINGTIP TO WING L/E GUSSET IS CRACKED. R & R GUSSET.

V0XR201012280004

EMB  

RROYCE

 

FLOOR SUPPORT

DAMAGED

12/28/2010

EMB145LR

AE3007A1

 

14520600003

ZONE 100

(V0XR) FLOOR SUPPORT BEAM DAMAGED BEYOND LIMITS. R & R BEAM. W/C 1112

V0XR201012280005

EMB  

RROYCE

 

GUSSET

DAMAGED

12/28/2010

EMB145LR

AE3007A12

 

14530633006

ZONE 100

(V0XR) CTR GUSSET AT FRAME 29-35 IS CORRODED BEYOND LIMITS. R & R CTR GUSSET. W/C 1144

V0XR201012280006

EMB  

RROYCE

 

GUSSET

DAMAGED

12/28/2010

EMB145LR

AE3007A12

 

14530633005

ZONE 100

(V0XR) LT GUSSET AT FRAME 29-35 IS CORRODED BEYOND LIMITS. R & R GUSSET. W/C 1145

V0XR201012280007

EMB  

RROYCE

 

SILL

DAMAGED

12/28/2010

EMB145LR

AE3007A12

 

14520609007

ZONE 100

(V0XR) RT SILL AT FRAME 29-35 IS CORRODED BEYOND LIMITS. R & R SILL. W/C 1146

V0XR201012280008

EMB  

RROYCE

 

PARTITION

DAMAGED

12/28/2010

EMB145LR

AE3007A12

 

14525991603

ZONE 100

(V0XR) LT PARTITIAN AT FRAME 61 IS CORRODED BEYOND LIMITS. R & R LT PARTITIAN. W/C 2089

V0XR201012280009

EMB  

RROYCE

 

SEAT TRACK

DAMAGED

12/28/2010

EMB145LR

AE3007A12

 

14532606011

ZONE 100

(V0XR) LEFT SEAT TRACK A-1 AROUND FASTENER IS CORRODED BEYOND LIMITS. R & R LT SEAT TRACK. W/C 2119

V0XR201012280010

EMB  

RROYCE

 

PROFILE

DAMAGED

12/28/2010

EMB145LR

AE3007A12

 

14525994003

ZONE 100

(V0XR) LT OTBD PROFILE AT FRAME 61 IS CORRODED BEYOND LIMITS. R & R PROFILE. W/C 2172

V0XR201012280011

EMB  

RROYCE

 

ATTACH FITTING

DAMAGED

12/28/2010

EMB145LR

AE3007A12

 

14572115402

RT WING

(V0XR) RT INBD L/E WING-FAIRING ATTACHMENT STRIP CRACKED. R & R STRIP. W/C 6017

V0XR201012280012

EMB  

RROYCE

 

ATTACH FITTING

DAMAGED

12/28/2010

EMB145LR

AE3007A12

 

14572167004

RT WING

(V0XR) RT TOP WING-FAIRING ATTACHMENT STRIP CRACKED. R & R STRIP. W/C 6018

V0XR201012280013

EMB  

RROYCE

 

ATTACH FITTING

DAMAGED

12/28/2010

EMB145LR

AE3007A12

 

14572167002

ZONE 100

(V0XR) RT TOP WING-FAIRING ATTACHMENT STRIP CRACKED. R & R STRIP. W/C 6020

V0XR201012300001

EMB  

RROYCE

 

SEAT TRACK

CORRODED

12/30/2010

EMB145LR

AE3007A12

 

14532606017

ZONE 100

(V0XR) LEFT SEAT TRACK A-5 HAS CORROSION AROUND FASTENER HOLES. R & R SEAT TRACK. W/C 2123

V0XR201012300002

EMB  

RROYCE

 

SEAT TRACK

CORRODED

12/30/2010

EMB145LR

AE3007A12

 

14530659003

ZONE 100

(V0XR) CENTER SEAT TRACK B-5 HAS CORROSION AROUND FASTENER HOLES. R & R SEAT TRACK. W/C 2126

V0XR201012300003

EMB  

RROYCE

 

SEAT TRACK

CORRODED

12/30/2010

EMB145LR

AE3007A12

 

14530658003

ZONE 100

(V0XR) RIGHT CENTER SEAT TRACK C-2 BETWEEN FRAME 30-35 HAS CORROSION AROUND FASTENER HOLES. R & R SEAT TRACK. W/C 2128

V0XR201012300004

EMB  

RROYCE

 

SEAT TRACK

CORRODED

12/30/2010

EMB145LR

AE3007A12

 

14530658007

ZONE 100

(V0XR) RIGHT CENTER SEAT TRACK C-4 BETWEEN FRAME 47-52 HAS CORROSION AROUND FASTENER HOLES. R & R SEAT TRACK. W/C 2129

V0XR201012300005

EMB  

RROYCE

 

SEAT TRACK

CORRODED

12/30/2010

EMB145LR

AE3007A12

 

14530658009

ZONE 100

(V0XR) RT CTR SEAT TRACK C-5 BETWEEN FRAME 52-60 HAS CORROSION AROUND FASTENER HOLES. R & R SEAT TRACK. W/C 2130

V0XR201012300006

EMB  

RROYCE

 

SUPPORT

BROKEN

12/30/2010

EMB145LR

AE3007A12

 

14534802003

ZONE 100

(V0XR) CABLE GUIDE SUPPORTS BROKEN. R & R CABLE GUIDE SUPPORTS. W/C 2200

V0XR201012300007

EMB  

RROYCE

 

SUPPORT

BROKEN

12/30/2010

EMB145LR

AE3007A12

 

14534802001

ZONE 100

(V0XR) SUPPORTS BROKEN AT FRAME 34. R & R SUPPORTS. W/C 1154

V0XR201012300008

EMB  

RROYCE

 

SEAT TRACK

CORRODED

12/30/2010

EMB145LR

AE3007A12

 

14530659011

ZONE 100

(V0XR) LT CTR SEAT TRACK B-1 HAD CORROSION AROUND FASTENER HOLES. R & R LT SEAT TRACK. W/C 2124

V0XR2010123000.10

EMB  

RROYCE

 

SEAT TRACK

CORRODED

12/30/2010

EMB145LR

AE3007A12

 

14530659003

ZONE 100

(V0XR) LT CTR SEAT TRACK B-3 HAD CORROSION AROUND FASTENER HOLES BETWEEN FRAME 30-35. R & R LT SEAT TRACK. W/C 2126

V0XR201012300011

EMB  

RROYCE

 

FLOOR PANEL

DELAMINATED

12/30/2010

EMB145LR

AE3007A12

 

14521843401

ZONE 100

(V0XR) CARGO FLOOR PANEL 272AF IS DELAMINATED. R & R CARGO PANEL. W/C 2197

V0XR201012300012

EMB  

RROYCE

 

ATTACH ANGLE

DELAMINATED

12/30/2010

EMB145LR

AE3007A12

 

14566044603

LT WING

(V0XR) LT FWD BOTTOM WING-FAIRING ATTACHMENT ANGLE IS CRACKED. R & R ANGLE. W/C 5069

V0XR201012230007

EMB  

RROYCE

 

SILL

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14521725015

ZONE 100

(V0XR) RT SILL AFT OF SERVICE DOOR FR 22-23 IS CORRODED OUT OF LIMITS. R & R RT SILL. W/C 1075

V0XR201012230008

EMB  

RROYCE

 

SILL

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14522178605

ZONE 100

(V0XR) SILL AT SERVICE DOOR IS CORRODED OUT OF LIMITS. R & R SILL. W/C 1085

V0XR201012230009

EMB  

RROYCE

 

ANGLE

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14522466009

ZONE 100

(V0XR) SCALLOPED ANGLE AT FR 18 IS CORRODED OUT OF LIMITS. R & R ANGLE. W/C 1086

V0XR20101223010

EMB  

RROYCE

 

ANGLE

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14521699003

ZONE 100

(V0XR) GUSSET AT LY-479.0 AT FR 18-23 IS CORRODED OUT OF LIMITS. R & R GUSSET. W/C 1087

V0XR20101223011

EMB  

RROYCE

 

PROFILE

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14525140023

ZONE 100

(V0XR) PROFILE AT FR 17-18 OTBD OF LY 479.0 IS CORRODED OUT OF LIMITS. R & R PROFILE. W/C 1088

V0XR20101223012

EMB  

RROYCE

 

PROFILE

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14525800014

ZONE 100

(V0XR) SILL AT FR 41-48R IS CORRODED OUT OF LIMITS. R & R SILL. W/C 1092

V0XR20101223013

EMB  

RROYCE

 

SILL

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14521725613

ZONE 100

(V0XR) RT SILL FWD OF SERVICE DOOR AT FR 19-20 IS CORRODED OUT OF LIMITS. R & R SILL. W/C 1076

V0XR20101223014

EMB  

RROYCE

 

GUSSET

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14530634005

ZONE 100

(V0XR) FLOOR GUSSET AT FR 39-46L IS CORRODED OUT OF LIMITS. R & R GUSSET. W/C 1095

V0XR20101223015

EMB  

RROYCE

 

GUSSET

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14530634011

ZONE 100

(V0XR) FLOOR GUSSET AT FR 46-52 IS CORRODED OUT OF LIMITS. R & R GUSSET. W/C 1098

V0XR20101223022

EMB  

RROYCE

 

PROFILE

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14525523003

ZONE 100

(V0XR) LT PROFILE ANGLE BEAM AT FR 66-67 IS CRACKED UNDER BAGGAGE COMPARTMENT. R & R BEAM. W/C 1136

V0XR20101223023

EMB  

RROYCE

 

PROFILE

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14530634003

ZONE 100

(V0XR) GUSSET AT FR 36-39 IS CORRODED BEYOND LIMITS. R & R GUSSET. W/C 2073

V0XR20101223024

EMB  

RROYCE

 

SILL

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14529495005

ZONE 100

(V0XR) RT SILL AT FR 53-59 IS CORRODED BEYOND LIMITS. R & R GUSSET. W/C 2080

V0XR20101223025

EMB  

RROYCE

 

GUSSET

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14522226003

ZONE 100

(V0XR) CTR GUSSET AT FR 59-61 IS CORRODED BEYOND LIMITS. R & R GUSSET. W/C 2087

V0XR20101223026

EMB  

RROYCE

 

GUSSET

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14522226003

ZONE 100

(V0XR) LT GUSSET AT FR 59-61 IS CORRODED BEYOND LIMITS. R & R GUSSET. W/C 2088

V0XR20101223027

EMB  

RROYCE

 

GUSSET

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14520609003

ZONE 100

(V0XR) LT SILL AT FR 29-35 IS CORRODED BEYOND LIMITS. R & R GUSSET. W/C 2112

V0XR20101223028

EMB  

RROYCE

 

GUSSET

DAMAGED

12/23/2010

EMB145LR

AE3007A12

 

14541338402

ZONE 100

(V0XR) CO-PILOTS LOWER AFT SIDEWALL PANEL IS DAMAGED. R & R SIDEWALL. W/C 2117

V0XR20101223029

EMB  

RROYCE

 

SEAT TRACK

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14532606003

ZONE 100

(V0XR) LEFT SEAT TRACK A-3 IS CORRODED BEYOND LIMITS. R & R LT SEAT TRACK. W/C 2121

V0XR20101223030

EMB  

RROYCE

 

SEAT TRACK

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14532605015

ZONE 100

(V0XR) RIGHT SEAT TRACK D-3 IS CORRODED BEYOND LIMITS. R & R RT SEAT TRACK. W/C 2133

V0XR201012230033

EMB  

RROYCE

 

BUSHING

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14527191009

RUDDER

(V0XR) BUSHINGS AT FWD RUDDER AT PCU-2 CORRODED BEYOND LIMITS. R & R LT SEAT TRACK. W/C 3059

V0XR201012270007

EMB  

RROYCE

 

BEAM

CORRODED

12/27/2010

EMB145LR

AE3007A12

 

14540484403

ZONE 100

(V0XR) RT BEAM AT FRAME 58-61 IS CORRODED BEYOND LIMITS. R & R BEAM. W/C 2079

V0XR201012270008

EMB  

RROYCE

 

GUSSET

CORRODED

12/27/2010

EMB145LR

AE3007A12

 

14530635003

ZONE 100

(V0XR) CTR GUSSET AT FRAME 53-59 IS CORRODED BEYOND LIMITS. R & R GUSSET. W/C 2082

V0XR201012270009

EMB  

RROYCE

 

GUSSET

CORRODED

12/27/2010

EMB145LR

AE3007A12

 

14530635001

ZONE 100

(V0XR) LT GUSSET AT FRAME 53-59 IS CORRODED BEYOND LIMITS. R & R GUSSET. W/C 2083

V0XR201012270010

EMB  

RROYCE

 

GUSSET

CORRODED

12/27/2010

EMB145LR

AE3007A12

 

14526437001

ZONE 100

(V0XR) RT GUSSET AT FRAME 53-59 IS CORRODED BEYOND LIMITS. R & R BEAM, GUSSET WAS PRE-INSTALLED ON BEAM. W/C 2086

V0XR201012270011

EMB  

RROYCE

 

SILL

CORRODED

12/27/2010

EMB145LR

AE3007A12

 

14525422003

ZONE 100

(V0XR) RT SILL AT FRAME 60-65 IS CORRODED BEYOND LIMITS. R & R SILL. W/C 2107

V0XR201012270012

EMB  

RROYCE

 

SEAT TRACK

CORRODED

12/27/2010

EMB145LR

AE3007A12

 

14532606001

ZONE 100

(V0XR) LT SEAT TRACK A-2 AT FRAME 24-30 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 2120

V0XR201012270013

EMB  

RROYCE

 

SEAT TRACK

CORRODED

12/27/2010

EMB145LR

AE3007A12

 

14532606015

ZONE 100

(V0XR) LT SEAT TRACK A-4 AT FRAME 35-47 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 2122

V0XR20101223016

EMB  

RROYCE

 

GUSSET

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14530634009

ZONE 100

(V0XR) LT FLOOR GUSSET AT FR 46-52R IS CORRODED OUT OF LIMITS. R & R GUSSET. W/C 1099

V0XR20101223017

EMB  

RROYCE

 

GUSSET

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14530633001

ZONE 100

(V0XR) LT FLOOR GUSSET AT FR 23-29 IS CORRODED OUT OF LIMITS. R & R GUSSET. W/C 1105

V0XR20101223018

EMB  

RROYCE

 

FLOOR SUPPORT

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14530633001

ZONE 100

(V0XR) LT OMEGA BEAM AT FR 45 IS CORRODED OUT OF LIMITS. R & R BEAM. W/C 1111

V0XR20101223020

EMB  

RROYCE

 

ANGLE

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14525523001

ZONE 100

(V0XR) LT PROFILE ANGLE BEAM AT FR 66-67 IS CRACKED UNDER BAGGAGE COMPARTMENT. R & R BEAM. W/C 1136

V0XR201012270001

EMB  

RROYCE

 

SILL

CORRODED

12/27/2010

EMB145LR

AE3007A12

 

14525800011

ZONE 100

(V0XR) SILL AT FRAME 48-52 IS CORRODED BEYOND LIMITS. R & R SILL. W/C 1097

V0XR201012230005

EMB  

RROYCE

 

CHANNEL

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14521713605

ZONE 100

(V0XR) CTR HAT BEAM AT YO.O FR 19-20 IS CORRODED OUT OF LIMITS. R & R CTR HAT BEAM. W/C 1080

V0XR201012270018

EMB  

RROYCE

 

SEAT TRACK

CORRODED

12/27/2010

EMB145LR

AE3007A12

 

14532605009

ZONE 100

(V0XR) RT SEAT TRACK D-5 AT FRAME 52-60 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 2135

V0XR201012270004

EMB  

RROYCE

 

GUSSET

CORRODED

12/27/2010

EMB145LR

AE3007A12

 

14530633006

ZONE 100

(V0XR) GUSSET AT FRAME 24-29 Y0.0 IS CORRODED BEYOND LIMITS. R & R GUSSET. W/C 1113

V0XR201012270014

EMB  

RROYCE

 

SEAT TRACK

CORRODED

12/27/2010

EMB145LR

AE3007A12

 

14532605001

ZONE 100

(V0XR) RT SEAT TRACK D-1 AT FRAME 24-30 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 2131

V0XR201012270015

EMB  

RROYCE

 

SEAT TRACK

CORRODED

12/27/2010

EMB145LR

AE3007A12

 

14532605003

ZONE 100

(V0XR) RT SEAT TRACK D-2 AT FRAME 30-35 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 2132

V0XR201012270016

EMB  

RROYCE

 

SEAT TRACK

CORRODED

12/27/2010

EMB145LR

AE3007A12

 

14532605015

ZONE 100

(V0XR) RT SEAT TRACK D-3 AT FRAME 35-47 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 2133

V0XR201012270017

EMB  

RROYCE

 

SEAT TRACK

CORRODED

12/27/2010

EMB145LR

AE3007A12

 

14532605017

ZONE 100

(V0XR) RT SEAT TRACK D-4 AT FRAME 47-52 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 2134

V0XR201012270005

EMB  

RROYCE

 

PROFILE

DAMAGED

12/27/2010

EMB145LR

AE3007A12

 

14525522005

ZONE 100

(V0XR) RT OTBD PROFILE AT FRAME 65 HAS NUMEROUS HOLES DRILLED AROUND NUTPLATE. R & R PROFILE W/C 1129

V0XR201012270006

EMB  

RROYCE

 

PARTITION

CORRODED

12/27/2010

EMB145LR

AE3007A12

 

14525991004

ZONE 100

(V0XR) RT PARTITIAN AT FRAME 61 IS CORRODED BEYOND LIMITS. R & R PARTITIAN. W/C 2078

V0XR20101223019

EMB  

RROYCE

 

ANGLE

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14525681011

ZONE 100

(V0XR) LT PROFILE ANGLE BEAM AT FR 66-67 IS CRACKED UNDER BAGGAGE COMPARTMENT. R & R BEAM. W/C 1136

V0XR20101223021

EMB  

RROYCE

 

ANGLE

CORRODED

12/23/2010

EMB145LR

AE3007A12

 

14525681007

ZONE 100

(V0XR) LT PROFILE ANGLE BEAM AT FR 66-67 IS CRACKED UNDER BAGGAGE COMPARTMENT. R & R BEAM. W/C 1136

V0XR201012300009A

EMB  

RROYCE

 

SEAT TRACK

CORRODED

12/30/2010

EMB145LR

AE3007A12

 

14530658003

ZONE 100

(V0XR) RT CTR SEAT TRACK C-2 HAD CORROSION AROUND FASTENER HOLES BETWEEN FRAME 30-35. R & R RT SEAT TRACK. W/C 2128

V0XR201012300009

EMB  

RROYCE

 

TRACK

WORN

12/30/2010

EMB145LR

AE3007A12

 

14566279401

TE FLAP

LEFT WING OTBD FLAP CENTER TORQUE BOX TRACK WORN. R & R TRACK ASSY. W/C 5072

V0XR201012270002

EMB  

RROYCE

 

GUSSET

CORRODED

12/27/2010

EMB145LR

AE3007A12

 

14530634001

ZONE 100

LEFT FLOOR GUSSET AT FRAME 36-3948-52 IS CORRODED BEYOND LIMITS. R & R GUSSET. W/C 1089

V0XR201012270003

EMB  

RROYCE

 

GUSSET

CORRODED

12/27/2010

EMB145LR

AE3007A12

 

14530634001

ZONE 100

LEFT GUSSET AT FRAME 36-39 IS CORRODED BEYOND LIMITS. R & R GUSSET. W/C 1089

V0XR201012280001

EMB  

RROYCE

 

SILL

CORRODED

12/28/2010

EMB145LR

AE3007A12

 

14525800016

ZONE 100

SILL AT FRAME 48-52 IS CORRODED BEYOND LIMITS. R & R SILL. W/C 1093

V0XR201012280002A

EMB  

RROYCE

 

GUSSET

CORRODED

12/28/2010

EMB145LR

AE3007A12

 

14530634007

ZONE 100

(V0XR) CTR GUSSET AT FRAME 39-46 IS CORRODED BEYOND LIMITS. R & R CTR GUSSET. W/C 1094

V0XR201012280003A

EMB  

RROYCE

 

SILL

CORRODED

12/28/2010

EMB145LR

AE3007A12

 

14525800013

ZONE 100

(V0XR) SILL AT FRAME 42-48L IS CORRODED BEYOND LIMITS. R & R SILL. W/C 1096

2010FA0001210

HUGHES

ALLSN

 

GOVERNOR

MALFUNCTIONED

7/20/2010

369E

250C20

 

252466715

TURBINE

THE PILOT IN COMMAND (PIC) REPORTED THAT WHILE INCREASING POWER IN A LEVEL FLIGHT ATTITUDE, THAT THE NR (MAIN ROTOR SPEED, RPM) AND THE N2 (ENGINE POWER TURBINE SPEED, RPM) INCREASED ABOVE 110 PERCENT N2. AN INITIAL ATTEMPT TO LOWER THE NR/N2 RPM WITH THE N2 BEEP/ TRIM SWITCH WAS UNRESPONSIVE. THE PIC IMMEDIATELY ROLLED THE THROTTLE BACK SLIGHTLY AND THE NR/N2 RESPONDED ACCORDINGLY. DURING THE OVERSPEED, THE PIC EXPERIENCE A SUDDEN RT YAW MOVEMENT OF THE HELICOPTER. THE PIC DID NOT NOTE WHAT THE ENGINE TOT (TURBINE OUTLET TEMPERATURE) READING WAS AND THERE WAS NO EXCEEDANCE RECORDED ON THE TOT INSTRUMENT. THE ENGINE TORQUE GAUGE REGISTERED AN EXCEEDANCE OF 99.6 PSI. THE POWER TURBINE GOVERNOR, PN: 23065123, SN: 24606, WAS REMOVED. NO SUBSEQUENT PROBLEMS WERE NOTED WHILE PERFORMING FUNCTIONAL FLIGHT TESTING WITH THE REPLACED GOVERNOR IAW MM 72-00-00, FIGURE 17. THE ENGINE WAS REMOVED AND SENT TO A MX CTR FOR COMPLETE INSPECTION.

2010FA0001245

PIAGIO

 

 

INDICATOR

FAILED

12/12/2010

P180

 

 

 

LT AIRSPEED

AIRSPEED INDICATOR ON LT SIDE FAILED IN DECENT, RETURNED TO NORMAL OPERATION AT LOWER ALTITUDE.

2011FA0000002

PIAGIO

PWA  

 

UNKNOWN

UNKNOWN

1/1/2011

P180

PT6A66

 

 

PROPELLER

UNCOMMANDED AUTOFEATHER ON APPROACH.

2010FA0001249

PIPER

LYC  

 

SPRING

BROKEN

12/16/2010

PA24250

O540*

 

SL14995

PUSHROD SHROUD

TRACING AN ENGINE OIL LEAK, IT WAS DISCOVERED THAT THE PUSHROD SHROUD TUBE RETAINING SPRINGS (SL14995)HAD FAILED ON ALL 6 CYLINDERS. THE PART FAILED BY BREAKING INTO 2 OR MORE FRAGMENTS; THIS ALLOWED THE SHROUD TO UNSEAT FROM THE HEAD AND LEAK OIL. ALL 6 SPRINGS WERE REPLACED.

2010FA0001266

PIPER

LYC  

 

CONTROL CABLE

BROKEN

12/29/2010

PA32300

IO540K1G5

 

 

STABILATOR

LOWER FWD STABILATOR CONTROL CABLE, THREADED ROD END BROKE AT THE SAFETY WIRE WRAP WHERE IT THREADS INTO THE TURNBUCKLE THE ONLY THING HOLDING CABLE TOGETHER WAS A SINGLE STRAND OF .041 SAFETY WIRE.

CA100723002

PIPER

LYC  

 

SPINNER

CRACKED

7/14/2010

PA44180

LO360E1A6

 

 

PROPELLER

WHEN SPINNER REMOVED CRACKS FOUND MIGRATING FROM SPINNER BULKHEAD MOUNTING HOLES TO PROPELLER. CRACKS FOUND ON 6 OF THE BOLT HOLE ATTACH POINTS. CRACKS FOUND ON THE SPINNER FILLET PLATES. A NEW PART WAS PURCHASE AND INSTALLED.

2010FA0001267

PIPER

LYC  

 

CLAMP

CRACKED

12/29/2010

PA46350P

TIO540AE2A

 

LW120936

TURBOCHARGER

UPON VISUAL INSPECTION OF THE EXHAUST SYS, DURING THE ANNUAL INSP, IT WAS FOUND THE THE UPPER V-BAND CLAMP LOCATED ON THE TURBOCHARGER WASTEGATE HAD CRACKED AND WAS SEPARATING. UPON REMOVAL OF THE CLAMP IT WAS FOUND THAT THE GASKET (PN 75845) HAD BLOWN OUT AND WAS BLOWING HOT EXHAUST ONTO THE REAR PORTION OF THE V-BAND CLAMP CAUSING IT TO CRACK AND SEPARATE.

2010FA0001254

ROBSIN

LYC  

 

BRACKET

BROKEN

12/13/2010

R44RAVENII

IO540AE1A5

RSA10AD1

D73211

FUEL CONTROL

PILOT REPORTED THAT AFTER ENGINE START AND DURING GROUND OPERATION WAS UNABLE TO REACH 100 PERCENT. ENGINE RPM DURING ACCELERATION FROM IDLE TO FULL THROTTLE. A NORMAL ENGINE SHUTDOWN WAS PERFORMED. PILOT NOTED MIXTURE CONTROL KNOB COULD NOT BE RETURNED TO FULL RICH. MX DISCOVERED THE BRACKET THAT SECURES THE MIXTURE CABLE AT THE FUEL CONTROL, BROKEN. THIS CAUSED THE CABLE TO BE UNSUPPORTED FROM THE FIREWALL TO THE MIXTURE CONTROL LEVER OF THE FUEL CONTROL, THUS PREVENTING PROPER OPERATION OF THE CABLE INNER WIRE. THE CABLE INNER WIRE REMAINED CONNECTED TO THE MIXTURE CONTROL LEVER AND ALTHOUGH THE PILOT HAD MOVED THE MIXTURE KNOB TO FULL RICH AT START-UP, THE CONTROL LEVER WAS NOT BEING MOVED TO THE FULL RICH POSITION. THIS PREVENTED THE ENGINE FROM BEING ABLE TO REACH 100 PERCENT RPM. IT APPEARS THAT THE NORMAL ACTUATION OF THE MIXTURE CONTROL CABLE FLEXES THE BRACKET AND WILL CAUSE IT TO FATIGUE AND EVENTUALLY FAIL. THE CONCERN IS THAT IF THE BRACKET WERE TO FAIL DURING FLIGHT THAT THE WEIGHT OF THE CABLE WOULD OVERCOME THE FUEL CONTROL MIXTURE LEVER SPRING THAT WOULD NORMALLY MOVE A BROKEN CABLE INNER WIRE TO THE FULL RICH POSITION. THE LEVER WOULD BE PULLED FROM FULL RICH TO SOME DEGREE AND EFFECT THE ENGINE OPERATION AND RPM AND THEREFORE EFFECT ROTOR RPM.

AC2R20101214001

SKRSKY

ALLSN

 

GEARBOX

MAKING METAL

12/14/2010

S76A

250C30S

 

7635109500044

MAIN ROTOR

(AC2R) APPROX 2 MILES FROM LANDING, THE MAIN GEARBOX CHIP LIGHT ILLUMINATED. PERFORMED THE MAIN GEARBOX CAUTION LIGHT ILLUMINATED EMERGENCY PROCEDURE AND LANDED. MX FOUND 1 FLAKE ON PLUG, PERFORMED A SERVICEABILITY CHECK AND RETURNED ACFT TO SERVICE. RECHECK OF CHIP PLUGS IN 3 TO 8 HOURS.

QMLRMD9951

SNIAS

TMECA

 

SUPPORT FRAME

MISLOCATED

12/29/2010

AS350B3

ARRIEL2B1

 

 

BS 115

(QMLR) 2 EA, 190 DIA BRACKET INSTALLATION HOLES WERE MISLOCATED ON THE OEM SUPPORT FRAME DURING INSTALLATION OF A SUPPORT BRACKET.

2010FA0001264

SNIAS

TMECA

 

OIL CAP

DETACHED

12/28/2010

AS350B3

ARRIEL2B1

 

 

ENGINE

THE ENGINE OIL RESERVOIR CAP CAME OFF IN FLIGHT RESULTING IN SIGNIFICANT OIL LOSS. HELICOPTER RETURNED TO BASE WITH NO PROBLEMS ENCOUNTERED. THE ISSUE IS MANUFACTURER`S "UNIQUE" RETAINING MECHANISM FOR CAP. RETAINING MECHANISM IS EASILY DISLODGED AND YET STILL APPEARS TO BE LOCKING CAP IN PLACE. UNLESS YOU ARE SPECIFICALLY LOOKING AT THE RETAINING MECHANISM DURING A PREFLIGHT AND YOU KNOW WHAT IT IS SUPPOSE TO LOOK LIKE WHEN IT IS IN THE LOCKED POSITION IT CAN BE EASILY OVERLOOKED. RECOMMEND THAT MFG DEVISE SOME TYPE OF SAFETY DEVICE FOR THEIR RETAINING MECHANISM. ALSO THIS SHOULD BE ADDED TO THEIR BEFORE FIRST FLIGHT (BFF) CHECKLIST.