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

392

bald eagle watching over three eggs

MARCH

2011

 


CONTENTS

AIRPLANES

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

CESSNA...................................................................................................................................... 4

GULFSTREAM............................................................................................................................ 6

PIPER........................................................................................................................................... 8

HELICOPTERS

EUROCOPTER.......................................................................................................................... 10

POWERPLANTS

ECI CYLINDER........................................................................................................................ 12

GENERAL ELECTRIC.............................................................................................................. 13

HONEYWELL........................................................................................................................... 16

LYCOMING.............................................................................................................................. 18

PRATT & WHITNEY................................................................................................................ 20

AIR NOTES

INTERNET SERVICE DIFFICULTY REPORTING (iSDR) WEB SITE................................... 24

IF YOU WANT TO CONTACT US......................................................................................... 26

AVIATION SERVICE DIFFICULTY REPORTS...................................................................... 26

 


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

Beech:  58; Burned Landing Light Circuit Breaker Switch; ATA 3340

"The pilot reported a burning smell in the cabin," says this submitter.  "An inspection revealed the taxi light circuit breaker switch to have an unusual feel.  Following replacement of the switch, the failed switch was disassembled and found to have burned internal components.  This switch (P/N 35-380132-105) is the improved model that was required by AD2008-13-07 which was modified to prevent the burning situation in the failure mode.  This was accomplished by installing two insulator pads at the actuator spring to prevent current from flowing through the spring when the wire braid fails.  Unfortunately, when these switches overheat, it is difficult to impossible to determine if the insulators had been installed improperly, or installed at all.  This is the second post AD switch in our fleet that has failed and overheated."  (Switch manufacturer's name: Tyco.  Aircraft total time: 8,059 hours.)

 


 

A) CLOSEUP VIEW OF OPENED SWITCH.


 

B) CLOSEUP VIEW OF OPENED SWITCH WITH LABELS.


 

C) CLOSEUP VIEW OF OPENED SWITCH SHOWING CURRENT PATH.

(See also two similar reports in the August Alerts of last year—Ed.)

Part Total Time:  (unknown)

 

Cessna:  172S; Loosened Seat Lock Attach Screws; ATA 2510

A writer says, "During a training flight the student pilot reported his seat would not lock into position.  The aircraft returned to base without incident.  Upon troubleshooting the problem a maintenance technician found the attachment screws of the left and right seat stop pins had backed out, allowing them to be detached and ineffective.  A check of the other aircraft in the fleet found six (additional) aircraft (having) loose attachment screws (P/N MS35207256).  All loose screws were removed, inspected, and reinstalled with Loctite 242 as per the manufacturer's suggestion."  (Component name, P/N, and manufacturer:  Seat Latch Assembly; SPL19251; Birk Aerosystem.)


 

A) BELOW SEAT VIEW OF LOCK (VIEW 1).


 

B) BELOW SEAT VIEW OF LOCK (VIEW 2).

 

Part Total Time:  1,797.0 hours

 

Gulfstream:  G200; Burned Lavatory Electrical Connector; ATA 3897

An electrical technician states, "While troubleshooting the flight phone (I) found the lavatory plug (number) 548 P2 showing signs of discoloration and overheat.  I capped and stowed the wires for plug 548 P2 IAW WDM 20-00-00.  I collared (blocked) the circuit breakers for the lavatory water heater, the ribbon heater, the water system control, and the toilet—and verified no power at plugs 548 P2 and J2." 


 

A) CLOSEUP VIEW OF BURNED ELECTRICAL CONNECTOR (VIEW 1).


B) CLOSEUP VIEW OF BURNED ELECTRICAL CONNECTOR (VIEW 2).

(No causal speculation was provided with this report.)

Part Total Time:  2,869.0 hours (aircraft)

 

Piper:  PA28-180; Failed Landing Gear Strut; 3213

A general aviation report states, "The right main landing gear lower strut fell off when the aircraft lifted off the runway at (the airport).  The student pilot flew to (his destination) and landed, resulting in damage to the upper landing gear strut (P/N:  6531904).   When the lower strut departed (from the) upper housing, it struck and damaged the flap skin. 

"The right main landing gear upper torque link mounting ears broke off the cylinder, allowing the lower gear leg to fall out of the upper cylinder and depart the aircraft.  This cast aluminum cylinder is original since 1972.  The inboard ear appears to have been partially broken for some time.  Once it broke all the way, the outboard ear could not support the twisting forces applied during normal turns, taxi, and torque during takeoff.  I feel this led to the outboard ear breaking off, and on takeoff, the gear left the aircraft.  This upper torque link attach point is covered with a fairing, preventing the pilot from seeing any defects during preflight."  (The SDRS database reflects this part number 22 times.)


A) CLOSEUP VIEW OF BROKEN STRUT; UPPER SECTION.


 

B) CLOSEUP VIEW OF BROKEN STRUT; LOWER SECTION.

 

Part Total Time:  (unknown)

 

HELICOPTERS

Eurocopter:  AS350B2; Cracked Vertical Fin Mount; ATA 5330

(The following submission is short on words, but long in photography.) 

"A crack (was found) in the vertical fin mount,"  says an unidentified  technician.  (Vertical fin P/N: 350A1100201101).


 

A) VIEW OF THE TAIL BOOM AND THE VERTICAL STABILIZER.


 

B) AN INTERNAL VIEW OF THE CRACKED STABILIZER MOUNT.

(Okay....  You got my attention.  I hope others are looking too—Ed.)

Part Total Time:  23,797.0 hours

 

POWERPLANTS

ECI Cylinder; AEC631397; Separated Cylinder Head; ATA 8530

(This report references a Cessna 414 aircraft.)

"While in flight at cruise power," says this technician, "a loss of manifold pressure and engine roughness was experienced.  The engine was shut down.  A normal landing was made at the intended destination.  Inspection revealed the number two cylinder head had separated.  No structural damage occurred."  (This ECI cylinder was fitted to a Continental TSIO-520NB engine.  There are 81 records for this cylinder number in the SDRS database.)

Part Total Time:  1,163.0 hours

 


General Electric:  CF680C2B2; Transfer Gearbox Contamination; ATA 7261

(This engine defect report references a Boeing 767 airplane.  Removing the last digit "2" from the engine number and adding the wildcard "%" to the search criteria yields 81 entries for this powerplant in the SDRS database.)

A Chief Quality Control inspector from our southern neighbor Columbia writes, "(The aircraft pilot report read...) 'The right engine oil quantity (indicated) zero and the engine oil pressure was low.  (An) engine shutdown was directed by checklist (and subsequently performed in flight)..  The oil pressure was always above 10 PSI.   (This) flight diverted to another (airfield).'

"Corrective action:  (We) performed B767 FIM (fault isolation manual) 71-05-00, figure 119, block 1-6 and 25.  We found the transfer gearbox (TGB) (oil scavenge) screen blocked by (unknown) material....  The screen contamination was removed and an Oil System Contamination Inspection accomplished."  (The maintenance action concludes with a satisfactory engine run-up with all operational parameters normal.  A separate attached note indicates the debris in the following photos as "foreign plastic material.")

 

A) CLOSEUP PHOTO (1) SHOWING REMOVAL OF PLASTIC MATERIAL FROM FILTER.


 

B) CLOSEUP PHOTO (2) SHOWING REMOVAL OF PLASTIC MATERIAL FROM FILTER.


 

C) CLOSEUP PHOTO (3) SHOWING REMOVAL OF PLASTIC MATERIAL FROM FILTER.


 

D) CLOSEUP PHOTO (4) SHOWING ALL MATERIAL REMOVED FROM FILTERS.

(Thank-you for your documentation effort.  The engine time might be a giant clue to the material's original purpose—Ed.)

Part Total Time:  2.37 hours (since overhaul)

 

Honeywell: TFE73122B; Turbine Blade Separation; ATA 7250

(This engine defect report references a Lear 35A aircraft.)

"At 400 feet (AGL) after takeoff," says this submitter, "the crew heard a loud bang from the left engine, (then) the engine RPM went to zero.  The crew circled (the aircraft) and made a safe landing.  The engine was removed and sent to (a repair) facility.  During engine teardown, five high pressure turbine rotor blades were found broken (directly) under the blade platform and separated from the disk.  The outer engine cases were not penetrated.  The cause of the blade failure is being investigated by the engine manufacturer and the (repair facility's) engineering staff."  (Turbine blade P/N:  30727122.)


 

A) SIDE VIEW OF TURBINE SECTION.


 

B) END VIEW OF TURBINE SECTION.

 

Part Total Time:  1,512.0 hours

 

Lycoming:  LTIO540-J2BD; Improper Rocker Cover Installation; ATA 8530

(This R/H engine pulls a Piper PA31-350 through the clouds.)

"The aircraft was written up by the PIC (pilot in command) for a large oil leak on the number two engine," says this mechanic.  "Inspection revealed the number three cylinder (P/N LW-12966) had a gasket (P/N 66732) installed incorrectly under the rocker shaft cover (P/N 72710).  The cover is secured with two screws (P/N 72709).

"This engine was received from Lycoming as a factory remanufactured unit and accumulated only 44.7 hours time in service until the leak was discovered.  The effected parts were installed by the manufacturer and not disturbed by company personnel until the defect was discovered."


 

A) CLOSEUP PHOTO OF THE ROCKER COVER AND IMPROPERLY ALIGNED GASKET.


 

B) A WIDE VIEW OF THE CYLINDER HEAD.

 

Part Total Time:  44.7 hours (since overhaul)

 

Pratt & Whitney:  PW305B; Failed Starter/Generator; ATA 2435

"The (Hawker 1000) aircraft experienced moderate vibration in cruise (flight)," writes this technician.  "The flight crew felt the vibration (originated) from the number two engine, followed shortly with a Generator number two fail indication.  The crew shut down the engine and diverted their flight to an (alternate) airport for a non-eventful, single engine landing.

"Maintenance removed the engine starter/generator and found it failed—with the internal cooling fan assembly contacting the generator shroud.  This unit had 305.1 hours since overhaul (TBO is 1000 hours)."  (This Starter/generator's manufacturer:  BF Goodrich; P/N: 23091002.  At least three of these units are described in the SDRS database.)


 

A) A WIDE VIEW OF THE STARTER/GENERATOR.


 

B) FAN-END VIEW SHOWING BLADE CONTACT WITH HOUSING.


 

C) PHOTO OF ARMATURE SHOWING FRICTION/DRAG MARKS.


 

D) PHOTO OF STATOR SHOWING FRICTION/DRAG MARKS.

(A dozen more photographs accompanied this report.  Thank-you for the time and effort spent in documentation—Ed.)

Part Total Time:  305.0 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

2011FA0000061

 

 

 

COVER

MISINSTALLED

1/14/2011

 

 

 

56118

FUEL BOWL

UNAUTHORIZED THREAD SEALANT WAS FOUND ON THE FUEL SIDE OF THE INLET FITTINGS. SB-10 ADDRESSES THIS ISSUE. THREAD SEALANT INSIDE THE CARBURETOR`S FUEL AND AIR PASSAGES CAN BREAK FREE AND CAUSE A CARBURETOR TO MALFUNCTION LEADING TO PARTIAL OR COMPLETE LOSS OF ENGINE POSER. SUBMITTER RECOMMENDS FOLLOWING THE INSTRUCTIONS CONTAINED IN THE APPROPRIATE CARBURETOR O/H MANUAL AND OTHER APPLICABLE SERVICE INFORMATION WHEN SERVICING CARBURETORS. THE CARBURETOR WAS IDENTIFIED WITH A RED "AVSTAR" DATA TAG.

2011FA0000062

 

 

 

SLEEVE

LOOSE

1/6/2011

 

 

 

86151

CARB MIXTURE

THE MIXTURE SLEEVE WAS FOUND LOOSE/ROTATED IN A CARBURETOR SUBMITTED FIR INSPECTION AND COMPLIANCE WITH SB-18 WHICH PERTAINS TO LOOSE MIXTURE CONTROL LSEEVES. ALTHOUGH THIS SLEEVE HAD NOT ROTATED FAR ENOUGH TO CAUSE FUEL STARVATION, HAD IT MOVED FURTHER, FUEL STARVATION COULD HAVE OCCURRED, RESULTING IN LOSS OF POWER. SUBMITTER REITERATES THE IMPORTANCE OF HAVING CARBURETORS AFFECTED BY SB18 INSPECTED AND REPAIRED PRIOR TO FURTHER FLIGHT.

EE4Y20110022

AIRBUS

 

 

BRACKET

CRACKED

1/14/2011

A319132

 

 

D53912660000

ZONE 100

(EE4Y) LOWER FUSELAGE LATERAL AVIONIC COMPARTMENT BRACKET CRACKED. PART REPLACED.

EE4Y20110027

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

1/15/2011

A319132

 

 

D534721721722050

ZONE 200

UPPER FUSELAGE PAX CABIN AFT ENTRANCE AREA FROM STA 2800 TO STA 2870 BETWEEN -Y 116 AND -Y 129 FLOOR SUPPORT WITH CORROSION. THE DAMAGED PART WAS REPLACED IAW SRM 51-72-11, PARAGRAPH 4 AND 6.

EE4Y20110029

AIRBUS

 

 

FLOOR SUPPORT

CORRODED

1/15/2011

A319132

 

 

D5347219320000

ZONE 200

UPPER FUSELAGE PAX CABIN AFT ENTRANCE AREA STA 2835, -Y 76.5 FLOOR SUPPORT WITH CORROSION. THE DAMAGED PART WAS REPLACED IAW SRM 51-72-11, PARA 4 AND 6.

EE4Y20110028

AIRBUS

 

 

SEAT TRACK

CORRODED

1/15/2011

A319132

 

 

D5347213320700

ZONE 200

UPPER FUSELAGE PAX CABIN AFT ENTRANCE AREA STA 2765, -Y 129 SEAT TRACK FLOOR SUPPORT WITH CORROSION. THE DAMAGED PART IS GOING TO BE REPLACED IAW SRM 51-72-11, PARAGRAPH 4 AND 6.

EE4Y20110036

AIRBUS

 

 

SKIN

CORRODED

1/20/2011

A319132

 

 

 

NR 1 NACELLE

NR 1 ENGINE PYLON AFT LOWER SECTION INBD AND OTBD SKIN WITH CORROSION. REPLACED NR1 ENGINE PYLON AFT FAIRING SECTION INBD AND OTBD SKIN PANEL FROM PYLON STA 819 TO PYLON STA 1005 IAW SRM 51-72-11, PARA 4 AND 6.

EE4Y20110037

AIRBUS

 

 

SKIN

CORRODED

1/20/2011

A319132

 

 

 

NR 2 NACELLE

NR 2 ENGINE PYLON AFT LOWER SECTION OTBD AND INBD SKIN WITH CORROSION. REPLACED NR2 ENGINE PYLON AFT FAIRING SECTION INBD AND OTBD SKIN PANEL FROM PYLON STA829 TO PYLON STA1005 IAW SRM 51-72-11, PARA 4 AND 6.

EE4Y20110023

AIRBUS

 

 

BRACKET

CRACKED

1/14/2011

A319132

 

 

D5391687200

ZONE 100

LOWER FUSELAGE LATERAL AVIONIC COMPARTMENT BRACKET CRACKED. PART REPLACED.

EE4Y20110020

AIRBUS

 

 

STRUCTURE

CORRODED

1/14/2011

A319132

 

 

D57259162000

ZONE 500

LEFT WING REAR SPAR AREA, MACHINING JACK ANCHORAGE WITH CORROSION AROUND THE BORE UPPER AND LOWER SURFACE AND AT THE BORE INNER SURFACE. REQUIRE A MAJOR REPAIR.

EE4Y20110021

AIRBUS

 

 

STRUCTURE

CORRODED

1/14/2011

A319132

 

 

D57259162001

ZONE 600

RT WING REAR SPAR AREA, MACHINING JACK ANCHORAGE WITH CORROSION AROUND THE BORE UPPER AND LOWER SURFACE AND AT THE BORE INNER SURFACE. REQUIRES MAJOR REPAIR.

EE4Y20110026

AIRBUS

 

 

STRAP

CORRODED

1/14/2011

A319132

 

 

 

ZONE 600

RIGHT WING AILERON T/E LOWER SURFACE STRAP WITH CORROSION AT RIVET HEAD AREA. THE FASTENERS REPLACED.

EE4Y20110025

AIRBUS

 

 

SKIN

CORRODED

1/14/2011

A319132

 

 

 

ZONE 100

LOWER FUSELAGE FWD CARGO COMPARTMENT FLOOR CAVITY BETWEEN FR24 AND FR34 STR, RIVETS WITH CORROSION. FASTENERS REPLACED.

EE4Y20110024

AIRBUS

 

 

SHEAR WEB

CORRODED

1/14/2011

A319132

 

 

D53471124200

ZONE 200

UPPER FUSELAGE PAX CABIN AFT ENTRANCE AREA FROM STA 2936 TO STA 2992, -Y125 LATERAL SHEAR WEB WITH CORROSION AND LOOSE RIVETS. REPLACED.

CA100728004

BEECH

PWA  

 

ENGINE

FAILED

7/16/2010

200BEECH

PT6A41

 

PT6A41

RIGHT

AS ACFT DEPARTED JUST AFTER ROTATION RT ENGINE FAILED AND HAD NEGATIVE AUTOFEATHER. ACFT UNABLE TO CLIMB AND ADVISED TOWER OF ENGINE FAILURE. CONTINUED TO FLY ACFT, PRECEDED TO TROUBLESHOOT SITUATION. RT ENGINE WAS NOT FEATHERED WHICH WAS PREVENTING ACFT FROM CLIMBING. IMMEDIATELY FEATHERED RT ENGINE WHICH INSTANTLY ALLOWED US TO CLIMB OUT OF THE SITUATION. COMPLETED EMERGENCY FAILURE CHECKLIST AND CLIMBED TO 2500 FT. BRIEFED SINGLE ENGINE LANDING CHECKLIST. COMPLETED VISUAL APPROACH & LANDED SAFELY. TAXIED TO RAMP UNDER ONE ENGINE.

UA2R1101

BEECH

 

 

FLEX HOSE

BROKEN

9/27/2010

C90  

 

 

9091009913

INTAKE ANTI ICE

(UA2R) DURING ROUTINE INSP, FOUND RT ENGINE INBD HOTLIP HOSE BROKEN. INSTALLED NEW HOSE.

UA2R1102

BEECH

 

 

FLEX HOSE

CRACKED

7/14/2010

C90  

 

 

9091010017

INTAKE ANTI-ICE

(UA2R) ANTI-ICE FLEX HOSES (PAIR) ON BOTH ENGINE INLETS CRACKED. R & R. PN IN BLOCK 5(C) BELOW IS LT. RT SN 90-910099-13, ALSO REPLACED.

UA2R1103

BEECH

 

 

FLEX HOSE

BROKEN

11/5/2010

C90  

 

 

9091009913

INTAKE ANTI ICE

(UA2R) RT ENGINE HAS BROKEN AIR DUCT INBD FLEX TUBE. R & R.

UA2R1104

BEECH

 

 

FLEX HOSE

BROKEN

7/13/2010

C90  

 

 

9091010017

INTAKE ANTI ICE

(UA2R) NR 2 ENGINE OTBD ANTI-DE-ICE PLUMBING DUCT BROKEN. R & R.

2011FA0000040

BOEING

 

 

PACKING

DETERIORATED

1/24/2011

767241

 

 

NAS1611029NAS161

HYD SYSTEM

(TAMY) PILOT REPORT: C HYD QTY DECREASED TO 26 AND SYSTEM PRESS AND QTY LIGHT ILLUM. EICAS MSG C HYD SYS PRESS AND C HYD QTY DISPLAYED. AIRCRAFT RETURN TO MIA. CORRECTIVE ACTION: DURING VISUAL INSPECTION FOUND RH LCCA FILTER CASE GASKET DAMAGED. REMOVED AND REPLACED LCCA FILTER COVER GASKET IAW B767 AMM 27-11-15 PAGE 401-405. NO LEAKS NOTED.

V56R20110204001

CESSNA

 

 

ENCODER

DEFECTIVE

1/25/2011

152  

 

 

A30 

ALTITUDE

ALTITUDE REPORTING SYS DISPLAYED ALTITUDES IN EXCESS OF 20,000 FT AT AN ACTUAL ACFT ALTITUDE OF 1,000 FEET ASL. THE PROBLEM WAS CAUSED BY AN INTERNAL FAILURE IN THE ALTITUDE ENCODER. THE PROBLEM WAS WAS SUBSEQUENTLY DUPLICATED ON THE GROUND. THE DEFECTIVE ENCODER WAS REPLACED WITH A NEW ALTITUDE ENCODER, USING AN ADAPTOR MOUNTING PLATE. THE ALTITUDE REPORTING SYS WAS TESTED IAW 14CFR43, APPENDIX E, AND FOUND TO MEET THE REQUIREMENTS OF 14CFR91.411.

2011FA0000036

CESSNA

 

 

SPAR

CRACKED

12/30/2010

172I

 

 

 

RT WING

(GY1R) UPON INSP OF THE RT INBD FLAP, THE FLAP TRACK HAD EXCESSIVE MOVEMENT WHICH REVEALED A CRACKED REAR SPAR AT THE LOWER FLAP TRACT ATTACH POINT AND A CRACKED INBD FLAP TRACK LOWER BRACKET SECTION. THE PROBABLE CAUSE WAS THAT THE FLAP WAS OUT OF RIG, CAUSING THE FLAP TO BE DRAWN UP TOO TIGHT INTO THE FLAP CHANNEL. RECOMMENDATIONS: PROPER FLAP RIGGING AND FLAP INSPECTIONS.

2011FA0000068

CESSNA

 

 

POWER CABLE

BURNED

2/5/2011

177RG

 

 

WPA4 

ZONE 100

FOUND TOO LONG/OVERSIZED INTERIOR TRIM REPLACEMENT SCREW INSTALLED IN PILOT SIDE LOWER DOOR SILL OPENING SHORTING INTO MAIN POWER CABLE W-PA4. PILOT COMPLAINT OF INTERMITTENT PANEL LIGHTING FLICKERING AND RECENT REGULATOR REPLACEMENT (2X) AND ALTERNATOR/CHARGING ISSUES.

2011FA0000064

CESSNA

CONT

 

GASKET

LEAKING

1/16/2011

207A

IO520*

 

653191

NR 4 CYLINDER

PILOT REPORTED SMOKE IN THE COCKPIT, COMING FROM THE DEFROST VENT. INSPECTED UNDER PANEL WIRING FOR EVIDENCE OF HOT WIRES. NONE FOUND. INSPECTED ENGINE COMPARTMENT FOR ANY INDICATIONS OF BURNING WIRING OR ANY OTHER PROBLEM. FOUND NR 4 VALVE COVER LEAKING ONTO HEAT MUFF. REPLACED VALVE COVER GASKET.

2011FA0000053

CESSNA

 

 

WHEEL HALF

FAILED

1/27/2011

210L

 

 

D302912

LT MLG

LT WHEEL ASSY CAME APART AT OUTER WHEEL HALF DURING TAXI OF ACFT.

V0XR413Y012511003

CNDAIR

 

 

BULKHEAD

CORRODED

1/25/2011

CL6002C10

 

 

 

BS 280

(V0XR) STA 280 LT LWR BULKHEAD PANEL CORRODED. REMOVED AND INSTALLED LT LWR BULKHEAD FS 280.0 IAW SRM 53-11-10. W/C 1037.

V0XR413Y012511004

CNDAIR

 

 

BULKHEAD

CORRODED

1/25/2011

CL6002C10

 

 

 

BS 280

STA 280 RT LOWER BULKHEAD PANEL CORRODED. REMOVED AND INSTALLED RT LWR BULKHEAD FS 280.0 IAW SRM 53-11-10. W/C 1038.

V0XR413Y012511005

CNDAIR

 

 

FLOORBEAM

CORRODED

1/25/2011

CL6002C10

 

 

 

BS 280

STA 280 FLOORBEAM CRACKED AND CORRODED. ACCOMPLISHED GENERIC REPAIR FOR CROSSBEAM 280.00 REPLACEMENT-SPLICE IAW REO 670-53-11-047. W/C 1039.

V0XR413Y012511006

CNDAIR

 

 

ANGLE

CORRODED

1/25/2011

CL6002C10

 

 

 

ZONE 100

PASS DOOR KICK PLATE ANGLE CORRODED. REMOVED KICKPLATE ANGLE, CLEANED UP SURROUNDING AREA AND ATTACHING PARTS, TRANSFERRED HOLES ONTO NEW ANGLE PN SH670-31875-3 IAW SRM 53-22-00. W/C 1040.

V0XR413Y012511008

CNDAIR

 

 

FITTING

CORRODED

1/25/2011

CL6002C10

 

 

 

ZONE 200

PASS DOOR THRESHOLD FWD CLOSING FITTING CORRODED. REMOVED FWD CLOSING FITTING, CLEANED UP SURROUNDING AREA AND ATTACHING PARTS, THANSFERRED HOLES TO NEW FITTING PN SH670-31840-1 IAW SRM 53-22-00. W/C 2080.

V0XR413Y012511009

CNDAIR

 

 

SILL

CORRODED

1/25/2011

CL6002C10

 

 

 

ZONE 200

AFT CARGO PIT, DOOR THRESHOLD LWR SILL CORRODED. AFT CARGO PIT LOWER SILL. R & R IAW SRM 53-61-23. HOLES DRILL IAW SRM 51-41-00, COUNTERSINKS IAW SRM 51-42-00, CORROSION REMOVAL IAW 51-21-11, METAL FINISH IAW SRM 51-21-16, PAINTINER IAW SRM 51-25-21, AND HARDWARE INSTALLATION IAW SRM 51-42-00. W/C 2081.

V0XR413Y010611008

CNDAIR

 

 

FITTING

CORRODED

1/6/2011

CL6002C10

 

 

 

BS 314 S18L

(V0XR) CLOSING FITTING STR 18L, FS 314 CORRODED. DRILLED UP NEW FITTING PN SH670-31840-3 AND INSTALLED NUTPLATES IAW SRM 53-20-00 AND RE-INSTALLED ON ACFT.

V0XR413Y010611009

CNDAIR

 

 

STRIKER

CORRODED

1/6/2011

CL6002C10

 

 

 

SERVICE DOOR

(V0XR) STRIKER SEAL SERVICE DOOR LWR THRESHOLD CORRODED BEYOND LIMITS. REINSTALLED SERVICE DOOR SCUFF PLATE IAW AMM TASK 53-21-23-400-801. INSTALLED SERVICE DOOR STRIKER IAW SRM 51-21-11, 51-41-00, 51-42-00, 51-21-16, AND 51-25-21.

V0XR413Y010611010

CNDAIR

 

 

MOUNT

CORRODED

1/6/2011

CL6002C10

 

 

 

BS 310

(V0XR) GALLEY MOUNT STA 310, APPROX LBL 18, CORRODED. TRANSFERRED HOLES TO NEW GALLEY MOUNT PN SH670-31754-1 IAW SRM 53-20-00 AND INSTALLED WET.

V0XR413Y010611011

CNDAIR

 

 

MOUNT

CORRODED

1/6/2011

CL6002C10

 

 

 

BS 312

(V0XR) GALLEY MOUNT STA 312, RBL 6. APPROX CORRODED. INSTALLED GALLEY MOUNT IAW SRM 53-20-00, PN SH 670-32149-3.

V0XR413Y010611012

CNDAIR

 

 

MOUNT

CORRODED

1/6/2011

CL6002C10

 

 

 

BS 290

(V0XR) GALLEY MOUNT STA 290, (APROX) LBL 18, CORRODED. R & R GALLEY MOUNT IAW SRM 51-42-21.

V0XR413Y010611013

CNDAIR

 

 

SILL

CORRODED

1/6/2011

CL6002C10

 

 

 

ZONE 200

(V0XR) AFT CARGO DOOR SILL CORRODED BEYOND LIMITS. REMOVED AND FIT, DRILL, PREP AND INSTALLED NEW AFT CARGO DOOR SILL IAW SRM CODEV, 51-41-00, 51-42-00 AND 51-23-00.

V0XR413Y010611014

CNDAIR

 

 

ANGLE

CORRODED

1/6/2011

CL6002C10

 

 

 

ZONE 200

(V0XR) SERVICE DOOR THRESHOLD MOUNTING ANGLE CORRODED. R & R LOWER SEAL ANGLE AND THRESHOLD MOUNTING ANGLE IAW SRM 51-42-06. REINSTALLED LWR DOOR CLOSURE FITTINGS IAW SRM 51-42-00 AND 51-23-00.

V0XR413Y010611015

CNDAIR

 

 

ANGLE

CORRODED

1/6/2011

CL6002C10

 

 

 

ZONE 200

(V0XR) SERVICE DOOR THRESHOLD LOWER SILL ANGLE CORRODED. R & R THE LOWER SILL ANGLE IAW SRM 51-42-06.

V0XR413Y010511001

CNDAIR

 

 

SILL

CORRODED

1/5/2011

CL6002C10

 

 

 

ZONE 100

(V0XR) SILL STRUCTURE RT FS280 TO FS319 CORRODED BEYOND LIMITS. R & R RT SILL FS280 TO FS319 IAW SRM 51-42-06. W/C 1050

V0XR413Y010511002

CNDAIR

 

 

FLOORBEAM

CORRODED

1/5/2011

CL6002C10

 

 

 

BS 280

(V0XR) 280 BLO FLOOR SUPPORT CORRODED BEYOND LIMITS. REMOVED AND REPLACED FLOOR SUPPORT ANGLE FS 280 IAW SRM 51-42-06. W/C 1042

V0XR413Y010511003

CNDAIR

 

 

FLOORBEAM

CORRODED

1/5/2011

CL6002C10

 

 

 

BS 280

(V0XR) STA 280 CROSSBEAM CORRODED BEYOND LIMITS. ACCOMPLISH GENERIC REPAIR FOR CROSSBEAM 280.00. REPLACEMENT SPLICE IAW REO 670-53-11-047.

V0XR413Y010510004

CNDAIR

 

 

BULKHEAD

CORRODED

1/5/2011

CL6002C10

 

 

 

BS 280

(V0XR) RT LOWER BULKHEAD FS 280 CORRODED OUT OF LIMITS. R & R RT LWR BULKHEAD, FS280 IAW SRM 53-11-10.

V0XR413Y010510005

CNDAIR

 

 

BULKHEAD

CORRODED

1/5/2011

CL6002C10

 

 

 

BS 280

(V0XR) LT LOWER BULKHEAD FS 280 CORRODED OUT OF LIMITS. R & R LT LWR BULKHEAD FS 280 IAW SRM 53-11-10.

V0XR413Y010510006

CNDAIR

 

 

THRESHOLD

CORRODED

1/5/2011

CL6002C10

 

 

 

ZONE 200

(V0XR) PAX DOOR THRESHOLD MIDCAP CORRODED. TRANSFERRED HOLES TO NEW PART NR SH670-31825-7 IAW SRM 53-20-00 AND INSTALLED.

V0XR413Y010510007

CNDAIR

 

 

ANGLE

CORRODED

1/5/2011

CL6002C10

 

 

 

ZONE 200

(V0XR) PAX DOOR KICK ANGLE CORRODED. TRANSFERRED HOLES AND INSTALLED NEW NUTPLATES TO ANGLE IAW SRM 53-20-00.

V0XR413Y011411001

CNDAIR

 

 

FLOORBEAM

CORRODED

1/14/2011

CL6002C10

 

 

 

ZONE 100

(V0XR) FLOOR SUPPORT, FS 280, RBL 9 TO LBL 9 CORRODED BEYOND LIMITS. REMOVED AND INSTALLED FLOOR ANGLE SUPPORT FS278, RBL9.00 TO LBL 9.00 IAW SRM 51-42-06.

V0XR413Y011411002

CNDAIR

 

 

SILL

CORRODED

1/14/2011

CL6002C10

 

 

 

ZONE 200

(V0XR) AFT BAGGAGE BAY DOOR LOWER SILL CORRODED. SILL R & R IAW SRM 53-61-23 AND STANDARD PRACTICES. REF THE FOLLOWING HOLES AND C-SINK, IAW 51-41-00, 51-42-00, HARDWARE INSTALLATION IAW 51-42-00, SEALING IAW 51-23-00, METAL FINISHING IAW 51-21-16, AND PAINTING IAW 51-25-21 (AFT BAGGAGE BAY DOOR, LOWER).

V0XR413Y011411003

CNDAIR

 

 

FLOORBEAM

CORRODED

1/14/2011

CL6002C10

 

 

 

ZONE 200

(V0XR) 280 BEAM IS CORRODED. ACCOMP GENERIC REPAIR FOR CROSSBEAM 280.00 REPLACEMENT-SPLICE IAW REO NR 670-53-11-047.

V0XR413Y011411004

CNDAIR

 

 

BULKHEAD

CORRODED

1/14/2011

CL6002C10

 

 

 

ZONE 200

(V0XR) LOWER AFT FACING OF THE BULKHEAD AT FS280.00 LT WEB CORRODED. REMOVED AND INSTALLED LWR BULHEAD WEB FS280.00 IAW SRM 53-11-00.

V0XR413Y011411005

CNDAIR

 

 

BULKHEAD

CORRODED

1/14/2011

CL6002C10

 

 

 

ZONE 200

(V0XR) LOWER AFT FACING OF THE BULKHEAD AFT AT FS 280.00, RT WEB CORRODED. REMOVED AND INSTALLED RT LWR WEB BULKHEAD FS280 IAW SRM 53-11-10.

V0XR413Y011411006

CNDAIR

 

 

SUPPORT ANGLE

CORRODED

1/14/2011

CL6002C10

 

 

 

ZONE 200

(V0XR) PAX DOOR MID CAP SUPPORT ANGLE CORRODED. R & R PAX DOOR MIDCAP IAW SRM 51-41-02, SRM 53-21-23, SRM 51-40-11.

V0XR413Y011411007

CNDAIR

 

 

MOUNT

CORRODED

1/14/2011

CL6002C10

 

 

 

ZONE 200

(V0XR) GALLEY MOUNT CORRODED AT RBL 6 FS 315. R & R GALLEY MOUNT IAW SRM 51-42-21. W/C 2105.

V0XR413Y011411008

CNDAIR

 

 

FITTING

CORRODED

1/14/2011

CL6002C10

 

 

 

ZONE 200

PAX DOOR CLOSING FITTING APPROX FS 325 CORRODED. R & R DOOR CLOSING FITTING PN SH670-31840-3. IAW SRM 53-21-23, SRM 51-40-11, SRM 51-41-02, SRM 51-42-06 (PAX DOOR FS 325) W/C 2106.

V0XR413Y011411009

CNDAIR

 

 

ANGLE

CORRODED

1/14/2011

CL6002C10

 

 

 

PAX DOOR

PASSENGER DOOR KICK ANGLE CORRODED. REMOVED, LOCATED, DRILLED AND INSTALLED NEW PASSENGER DOOR KICK ANGLE IAW SRM 53-21-23, SRM 51-42-06, SRM 51-40-11. W/C 2117.

V0XR413Y011411010

CNDAIR

 

 

BONDING JUMPER

CORRODED

1/14/2011

CL6002C10

 

 

 

ZONE 500

(V0XR) LT WING NR 5 FLAP HINGE BOX FWD BONDING JUMPER LOWER HARDWARE CORRODED. R & R FWD LWR BONDING JUMPER AND HARDWARE IAW AMM 51-80-00, TASK 51-80-00-910-810. W/C 5053.

V0XR413Y012511001

CNDAIR

 

 

FLOORBEAM

CORRODED

1/25/2011

CL6002C10

 

 

 

BS 280

FLOOR SUPPORT STA 280, LBL 9 TO RBL 9 CORRODED. REMOVED CORRODED FLOOR SUPPORT AT FS 280, LBL 9 TO RBL 9 AND REPLACED WITH SERVICEABLE SUPPORT. W/C 1035.

V0XR413Y012511002

CNDAIR

 

 

SILL

CORRODED

1/25/2011

CL6002C10

 

 

 

BS 280

RT SILL, STA 280 CORRODED (FWD INBD CORNER). REPAIRED RT SILL STA 280 IAW REO 670-53-21-139. W/C 1036.

VGQY2012120100132

DOUG

 

 

SPAR CAP

CORRODED

12/1/2010

DC1010

 

 

ALC700922

ZONE 300

RIGHT HORIZONTAL STABILIZER INTEGRAL LOWER CHORD AND STRINGER NR 1, STA XE 48.500 TO XE 67.333 FOUND WITH EXFOLIATION CORROSION. COMPLIED WITH ORBIS EA DC10-5510-1134.

VGQY2011011500002

DOUG

 

 

SUPPORT BRACKET

CORRODED

1/15/2011

DC1010

 

 

ANB71355

ZONE 500

UPPER LT WING-TO-FUSELAGE AREA FS 1119 - FOUND 1 EA SUPPORT BRACKET WITH CORROSION. REMOVED AND DISCARDED CORRODED ANB7135-5 ANGLE. FABRICATED NEW ANGLE PER DWG LONG BEACH DWG ANB7135 REV A. NEW ANGLE INSTALLED AS PER DC-10 SRM 51-31-01 REVISION 97 VOLUME II.

VGQY2011011500003

DOUG

 

 

SPAR CAP

CORRODED

1/15/2011

DC1010

 

 

ALC70821

ZONE 300

LEFT HORIZONTAL STAB FRONT SPAR UPPER ANGLE STRAP AT STA XE 57 FOUND WITH CORROSION IN SEVERAL LOCATION. COMPLIED WITH EA DC10-5510-1140.

VGQY2011011500004

DOUG

 

 

SPAR CAP

CORRODED

1/15/2011

DC1010

 

 

ALC70821

ZONE 300

LT HORZ STAB FRONT SPAR LOWER ANGLE STRAP AT STA XE 57 FOUND WITH CORROSION IN SEVERAL LOCATION. COMPLIED WITH EA DC10-5510-1140.

VGQY2011011500005

DOUG

 

 

BALANCE WEIGHT

CRACKED

1/15/2011

DC1010

 

 

NLC60353

ZONE 300

LT HORZ STAB O/B ELEVATOR BALANCE WEIGHT AFT EDGE FOUND WITH ONE (1) INCH CRACKED. TRIMMED OUT DAMAGED AREA ON LT HORIZONTAL STABILIZER FAIRING AS PER DC-10 SRM 55-00-01 FIGURE 3 VOLUME I REVISION 97. FABRICATED REPAIR DOUBLER AND FILLER AS PER SRM 55-00-01 FIGURE 3 VOLUME I REVISION 97 USING MATERIAL 7075T6-0.050". INSTALLED REPAIR DOUBLER AND FILLER AS PER SRM 55-00-01 FIGURE 3 VOLUME I REVISION 97.

VGQY2011011500006

DOUG

 

 

SPAR CAP

CORRODED

1/15/2011

DC1010

 

 

 

ZONE 300

LT WING INNER REAR SPAR APPROX STA XORS 197 FOUND EXTRUSION CORRODED. COMPLIED WITH EA DC10-5710-1132.

VGQY2011011500007

DOUG

 

 

SPAR

CORRODED

1/15/2011

DC1010

 

 

ARC03991

ZONE 300

LT WING INNER REAR SPAR APPROX STA XORS 264 FOUND EXTRUSION CORRODED. COMPLIED WITH EA DC10-5710-1131.

VGQY2011011500008

DOUG

 

 

RETAINER

CORRODED

1/15/2011

DC1010

 

 

AJC733129

ZONE 300

LEFT LOWER VERTICAL STABILIZER, BELOW AIR INTAKE DUCT FOUND WITH CORROSION AFT OF PANEL 361BL. REMOVED AND DISCARDED CORRODED AJC7331-29 RETAINER. FABRICATED NEW RETAINER PER DWG AJC7331 REQUIREMENTS USING MATERIAL 7075-0-0.125". NEW RETAINER INSTALLED AS PER DC-10 SRM 51-31-01 REVISION 97 VOLUME II.

VGQY2011011500009

DOUG

 

 

SPAR CAP

CORRODED

1/15/2011

DC1010

 

 

 

WING 

RT MAIN LANDING GEAR WHEEL WELL - FOUND CORROSION AT OUTER WING REAR SPAR CAP, UPPER SIDE-BOTTOM SURFACE - STA XORS 118.200. COMPLIED WITH EA DC10-5730-1133.

VGQY2011011500010

DOUG

 

 

SPAR CAP

CORRODED

1/15/2011

DC1010

 

 

ALC70832

ZONE 300

RT HORZ STAB FRONT SPAR INTERIOR LOWER SURFACE FOUND WITH CORROSION AT STA APPROX XE 44 - XE 67. COMPLIED WITH EN 1003-11.

VGQY2011011500011

DOUG

 

 

STRUCTURE

CRACKED

1/15/2011

DC1010

 

 

 

RT ELEVATOR

RT HORZ STAB I/B ELEVATOR LOWER O/B FWD EDGE FOUND CRACKED. TRIMMED OUT CRACKED AREA ON RT HORIZONTAL STABILIZER INBOARD ELEVATOR LOWER OUTBOARD FORWARD EDGE AS PER DC-10 SRM 55-10-00 FIGURE 7 VOLUME I REVISION 97. INSTALLED FABRICATED REPAIR DOUBLER AND FILLER AS PER DC-10 SRM 55-00-01 FIGURE 7 VOLUME I (UPPER AND LOWER SURFACE ELEVATOR SKIN REPAIR) REVISION 97.

VGQY2011011500012

DOUG

 

 

STRUCTURE

CORRODED

1/15/2011

DC1010

 

 

 

NR 1 NACELLE

EVIDENCE OF CORROSION ON BOTH STREAKES ON NR 1 ENGINE COWLING EVALUATE CORROSION. COMPLIED WITH EA DC10-7110-1169.

VGQY2011011700013

DOUG

 

 

SKIN

CORRODED

1/17/2011

DC1010

 

 

 

BS 1701 L46-47L

SURFACE CORROSION FOUND AT FRAME STA 1701 - LONGERONS L 46 & L 47. REMOVED CORROSION AT STA 1701 LONGERON 46L TO 47L PER SRM 51-21-01 VOLUME II REVISION 97 AND FOUND EXCEEDED SRM 53-00-01 VOLUME I, FIGURE 1A REVISION 97 LIMITS. TRIMMED-OFF CORROSION AREA PER SRM 53-20-00 VOLUME I FIGURE 6 REVISION 97. FABRICATED INNER EXTERNAL DOUBLER AND OUTER EXTERNAL DOUBLER PER SRM 53-20-00 FIGURE 6 VOLUME I REVISION 97. FABRICATED FINGER DOUBLER AS FIGURE 6 PER SRM 53-20-00 VOLUME I REVISION 97. INSTALLED INNER EXTERNAL DOUBLER, OUTER EXTERNAL DOUBLER, FINGER DOUBLER AND FILLERS AT STA 1921 AS PER SRM 51-31-01 VOLUME II REVISION 97.

VGQY2011011700014

DOUG

 

 

SKIN

CORRODED

1/17/2011

DC1010

 

 

 

BS 1921 L45-48L

SKIN CORROSION FOUND ON FRAME STA 1921 LT SIDE - BETWEEN LONGERON 45L-48L. REMOVED CORROSION PER SRM 51-21-01 VOLUME II REVISION 97 AND FOUND EXCEEDED SRM 53-00-01 VOLUME I, FIGURE 1A REVISION 97 LIMITS. TRIMMED-OFF CORROSION AREA PER SRM 53-20-00 VOLUME I FIGURE 6 REVISION 97. FABRICATED INNER EXTERNAL DOUBLER AND OUTER EXTERNAL DOUBLER PER SRM 53-20-00 FIGURE 6 VOLUME I REVISION 97. FABRICATED FINGER DOUBLER PER SRM 53-20-00 FIGURE 6 VOLUME I REVISION 97. INSTALLED INNER EXTERNAL DOUBLER, OUTER EXTERNAL DOUBLER, FINGER DOUBLER AND FILLERS AT STA 1921 PER SRM 51-31-01 VOLUME II REVISION 97.

2011FA0000063

ECLIPS

PWC  

 

TURBINE

COKED

1/3/2011

ECLIPSEEA500

PW610FA

 

 

LT ENGINE

ON 1/3/11, ACFT DEPARTED AIRPORT. ACFT DEVELOPED A PROBLEM WITH THE LT ENGINE TEMP RUNNING HIGH, FOLLOWED BY A "LT ENGINE EXCEEDANCE" CREW ALTERTING SYS MESSAGE. PILOT REDUCED POWER ON ENGINE HOPING TO REDUCE TEMP, TEMP CONTINUED TO CLIMB, PILOT DECIDED TO SHUTDOWN ENGINE AND NOTIFIED DESTINATION CTR. ACFT FLYING AT FL370 WHEN THE CALL WAS MADE. ACFT DIVERTED DUE TO LOSS OF LT ENGINE & LANDED WITHOUT INCIDENT. PILOT NOTIFIED ACFT MFG, WHO DIRECTED PILOT TO CONTACT ENG MFG REP AT ACFT MX, WHO TRAVELED FLL WHERE THE LT ENGINE WAS REPLACED. ACCORDING THE THE ENG MFG REP, THIS IS THE SECOND ENGINE REPLACED ON THIS ACFT IN LESS THAN 10 HRS. THERE IS AN AD ON THIS ACFT, AD2008-24-07M LIMITING THIS ACFT TO FL 370, ALTITUDES ABOVE THIS FL CAUSES ACFT ENG TO PRODUCE HARD CARBON BUILDUP (COKING) RAPIDLY. GRAPHIC DEPICITION OF CARBON BUILDUP IS AVAILABLE UPON REQUEST.

V0XR201101250001

EMB  

 

 

SILL

CORRODED

1/25/2011

EMB145LR

 

 

14525422001

ZONE 100

PROFILE AT FR 61-65 Y-349L CORRODED BEYOND LIMITS. R & R SILL. W/C 1069

V0XR201101180003

EMB  

 

 

SILL

CORRODED

1/18/2011

EMB145LR

 

 

14525523001

ZONE 100

CARGO ENTRY SILL AT FR 65-68 IS CORRODED BEYOND LIMITS. R & R SILL. W/C 1122

V0XR201101180001

EMB  

 

 

SHEAR TIE

CORRODED

1/18/2011

EMB145LR

 

 

14524175001

ZONE 100

SHEAR CLIP AT FR 65 IS CORRODED BEYOND LIMITS. R & R SHEAR CLIP. W/C 1124

V0XR201101180002

EMB  

 

 

SHEAR TIE

CORRODED

1/18/2011

EMB145LR

 

 

14525369003

ZONE 100

(V0XR) SHEAR CLIP AT FR 68 STGR 9L-18L IS CORRODED BEYOND LIMITS. R & R SHEAR CLIP. W/C 1125.

V0XR201102010003A

EMB  

 

 

DOUBLER

CORRODED

2/1/2011

EMB145LR

 

 

14522461011

ZONE 100

DOUBLERS AT FR 20-22 OF Y-479L IS CORRODED BEYOND LIMITS. R & R DOUBLERS.

V0XR201102010003B

EMB  

 

 

SILL

CORRODED

2/1/2011

EMB145LR

 

 

14525800009

ZONE 100

LEFT SILL AT FR 36-42 IS CORRODED BEYOND LIMITS. R & R SILL.

V0XR201102010003C

EMB  

 

 

GUSSET

CORRODED

2/1/2011

EMB145LR

 

 

14530634009

ZONE 100

LEFT GUSSET AT FR 46-52 IS CORRODED BEYOND LIMITS. R & R GUSSET.

V0XR201102040001

EMB  

 

 

STRUCTURE

CRACKED

2/4/2011

EMB145LR

 

 

 

RT MLG DOOR

RIGHT MLG LOWER DOOR CRACKED. R & R RT MLG DOOR.

V0XR201101250005

EMB  

 

 

SILL

CORRODED

1/25/2011

EMB145LR

 

 

14520609005

ZONE 100

RT PARTITIAN AT FR 61 IS CORRODED BEYOND LIMITS. R & R PARTITIAN. W/C 1092.

V0XR201102030005

EMB  

 

 

GUSSET

CORRODED

2/3/2011

EMB145LR

 

 

14530634011

ZONE 100

RT GUSSET AT FR 46-52 IS CORRODED BEYOND LIMITS. R & R GUSSET.

V0XR201102030006

EMB  

 

 

SILL

CORRODED

2/3/2011

EMB145LR

 

 

14525800016

ZONE 100

RT SILL AT FR 47-52 IS CORRODED BEYOND LIMITS. R & R SILL.

V0XR201102030007

EMB  

 

 

SILL

CORRODED

2/3/2011

EMB145LR

 

 

14525800014

ZONE 100

RIGHT SILL AT FR 41-47 IS CORRODED BEYOND LIMITS. R & R SILL.

V0XR201102030008

EMB  

 

 

SILL

CORRODED

2/3/2011

EMB145LR

 

 

14525800010

ZONE 100

RIGHT SILL AT FR 36-41 IS CORRODED BEYOND LIMITS. R & R SILL.

V0XR201102030009

EMB  

 

 

SILL

CORRODED

2/3/2011

EMB145LR

 

 

14525800015

ZONE 100

LEFT SILL AT FR 48-52 IS CORRODED BEYOND LIMITS. R & R SILL.

V0XR201102030010

EMB  

 

 

SILL

CORRODED

2/3/2011

EMB145LR

 

 

14525800013

ZONE 100

LEFT SILL AT FR 42-48 IS CORRODED BEYOND LIMITS. R & R SILL.

V0XR201102030011

EMB  

 

 

PANEL

CORRODED

2/3/2011

EMB145LR

 

 

14530375001

ZONE 100

PANEL AT END OF CTR BEAM AT STA 23 IS CORRODED BEYOND LIMITS. R & R PANEL.

V0XR201102030012

EMB  

 

 

CONTROL CABLE

CORRODED

2/3/2011

EMB145LR

 

 

14521026417

AILERONS

AILERON CONTROL CABLES ARE WORN BEYOND LIMITS. R & R CABLES.

V0XR201102030013

EMB  

 

 

CONTROL CABLE

CORRODED

2/3/2011

EMB145LR

 

 

14521026419

AILERONS

AILERON CONTROL CABLES ARE WORN BEYOND LIMITS. R & R CABLES.

V0XR201102030014

EMB  

 

 

CONTROL CABLE

CORRODED

2/3/2011

EMB145LR

 

 

14521026421

ZONE 100

AILERON CONTROL CABLES ARE WORN BEYOND LIMITS. R & R CABLES.

V0XR201102030015

EMB  

 

 

CONTROL CABLE

CORRODED

2/3/2011

EMB145LR

 

 

14521026423

AILERONS

AILERON CONTROL CABLES ARE WORN BEYOND LIMITS. R & R CABLES.

V0XR201102030017

EMB  

 

 

CONTROL CABLE

CORRODED

2/3/2011

EMB145LR

 

 

14571009405

ZONE 500

LEFT AILERON CONTROL CABLES ARE WORN BEYOND LIMITS. R & R CABLE.

V0XR201102030016

EMB  

 

 

CONTROL CABLE

CORRODED

2/3/2011

EMB145LR

 

 

14571009401

ZONE 500

LEFT AILERON CONTROL CABLES ARE WORN BEYOND LIMITS. R & R CABLE.

V0XR201101250003

EMB  

 

 

GUSSET

CORRODED

1/25/2011

EMB145LR

 

 

14530633001

ZONE 100

GUSSET AT FR 23-29 LY 479.0 IS CORRODED BEYOND LIMITS. R & R GUSSET. W/C 1086.

V0XR201101250002

EMB  

 

 

SILL

CORRODED

1/25/2011

EMB145LR

 

 

14520609003

ZONE 100

LEFT SILL AT FR 29-35 IS CORRODED BEYOND LIMITS. R & R SILL. W/C 1080

V0XR201101250004

EMB  

 

 

SILL

CORRODED

1/25/2011

EMB145LR

 

 

14520609005

ZONE 100

RT SILL AT FR 24-29 IS CORRODED BEYOND LIMITS. R & R SILL. W/C 1087.

V0XR201101250006

EMB  

 

 

PARTITION

CORRODED

1/25/2011

EMB145LR

 

 

14525991003

ZONE 100

LEFT PARTITION AT FR 61 IS CORRODED BEYOND LIMITS. R & R PARTITION. W/C 1093.

V0XR201101250007

EMB  

 

 

SILL

CORRODED

1/25/2011

EMB145LR

 

 

14529495003

ZONE 100

SILL AT FR 59-61 IS CORRODED BEYOND LIMITS. REMOVED AND REPLACED SILL. W/C 1096

V0XR201101260001

EMB  

 

 

PLATE

CORRODED

1/26/2011

EMB145LR

 

 

14521721009

ZONE 100

FWD DIGITAL PLATE AT FR 14-16 IS CORRODED BEYOND LIMITS. R & R PLATE. W/C 1070.

V0XR201101260002

EMB  

 

 

GUSSET

CORRODED

1/26/2011

EMB145LR

 

 

14522460015

ZONE 100

GUSSET AT FR 17-18 Y0.0-Y479.0 IS CORRODED BEYOND LIMITS. R & R GUSSET. W/C 1071.

V0XR201101250008

EMB  

 

 

PLATE

CORRODED

1/25/2011

EMB145LR

 

 

14520699003

ZONE 100

PLATE ON TOP OF Y479.0L BEAM IS CORRODED BEYOND LIMITS. R & R PLATE. W/C 1090.

V0XR201101250009

EMB  

 

 

BEAM

CORRODED

1/25/2011

EMB145LR

 

 

14521715016

ZONE 100

BEAM AT FR 14 FROM YO TO YR 479.0 IS DRILLED IN RADIUS FROM PREVIOUS DIGITAL REPAIR. R & R BEAM. W/C 1119.

V0XR201101260003

EMB  

 

 

FLOOR SUPPORT

CORRODED

1/26/2011

EMB145LR

 

 

14521713005

ZONE 100

OMEGA BEAM AT FR 19-24 Y479.0 R IS CORRODED BEYOND LIMITS. R & R BEAM. W/C 1078.

V0XR201101260004

EMB  

 

 

FLOOR SUPPORT

CORRODED

1/26/2011

EMB145LR

 

 

14521713005

ZONE 100

OMEGA BEAM AT FR 19-24 YO.O IS CORRODED BEYOND LIMITS. R & R BEAM. W/C 1079.

V0XR201101260005

EMB  

 

 

SILL

CORRODED

1/26/2011

EMB145LR

 

 

14521725001

ZONE 100

SILL AFT OF PAX DOOR AT FR 19-23L IS CORRODED BEYOND LIMITS. R & R SILL. W/C 1081.

V0XR201101260006

EMB  

 

 

SILL

CORRODED

1/26/2011

EMB145LR

 

 

14520609007

ZONE 100

RT SILL AT FR 29-35 IS CORRODED BEYOND LIMITS. R & R SILL. W/C 1082.

V0XR201101260007

EMB  

 

 

SILL

CORRODED

1/26/2011

EMB145LR

 

 

14520609001

ZONE 100

LEFT SILL AT FR 23-29 IS CORRODED BEYOND LIMITS. R & R SILL. W/C 1084.

V0XR201101260008

EMB  

 

 

GUSSET

CORRODED

1/26/2011

EMB145LR

 

 

14526437001

ZONE 100

GUSSET AT FR 69-51, Y-479.0 R IS CORRODED BEYOND LIMITS. R & R GUSSET. W/C 1089.

V0XR201101260009

EMB  

 

 

SILL

CORRODED

1/26/2011

EMB145LR

 

 

14529495001

ZONE 100

LEFT SILL AT FR 53-59 IS CORRODED BEYOND LIMITS. R & R GUSSET. W/C 1095.

V0XR20110126000

EMB  

 

 

SILL

CORRODED

1/26/2011

EMB145LR

 

 

14529495005

ZONE 100

RIGHT SILL AT FR 53-59 IS CORRODED BEYOND LIMITS. R & R SILL. W/C 1097.

V0XR201101260010

EMB  

 

 

SILL

CORRODED

1/26/2011

EMB145LR

 

 

14525422003

ZONE 100

RIGHT SILL AT FR 61-65 IS CORRODED BEYOND LIMITS. R & R SILL. W/C 1116.

V0XR201101270001

EMB  

 

 

SUPPORT

CORRODED

1/27/2011

EMB145LR

 

 

14522459003

ZONE 100

TAPERED SUPPORT AT FR 19-20 Y0.0 IS CORRODED BEYOND LIMITS. R & R SUPPORT. W/C 1077

V0XR201101270002

EMB  

 

 

ANGLE

CORRODED

1/27/2011

EMB145LR

 

 

14590082003

ZONE 100

ANGLE AT FR 20 Y0.0 IS CORRODED BEYOND LIMITS. R & R ANGLE. W/C 1085

V0XR201101270003

EMB  

 

 

GUSSET

CORRODED

1/27/2011

EMB145LR

 

 

14522460013

ZONE 100

GUSSET AT FR 20-23 Y0.0 IS CORRODED BEYOND LIMITS. R & R GUSSET. W/C 1088

V0XR201101270004

EMB  

 

 

ANGLE

CORRODED

1/27/2011

EMB145LR

 

 

2024T3032

ZONE 100

GUSSET SUPPORT ANGLES (2) AT FR 21 LT SIDE OF CTR OMEGA BEAM CORRODED BEYOND LIMITS. R & R ANGLES. W/C 1091

V0XR201101270005

EMB  

 

 

ANGLE

CORRODED

1/27/2011

EMB145LR

 

 

14529150007

ZONE 100

ANGLE AT FR 23 BETWEE RY 780.0 AND RY O IS CORRODED BEYOND LIMITS. R & R ANGLE. W/C 1117

V0XR201101270006

EMB  

 

 

ANGLE

CORRODED

1/27/2011

EMB145LR

 

 

14529150009

ZONE 100

ANGLE (SCALLOPED) AT FR 23 RY 780.0 AND RY O IS CORRODED BEYOND LIMITS. R & R ANGLE. W/C 1118

V0XR201101130002

EMB  

 

 

SILL

CORRODED

1/13/2011

EMB145LR

 

 

14525800009

ZONE 100

(V0XR) LT SILL AT FR 36-41 IS CORRODED BEYOND LIMITS. R & R SILL. W/C 1078.

V0XR201101130003

EMB  

 

 

SUPPORT

CRACKED

1/13/2011

EMB145LR

 

 

14540575009

CARGO DOOR

(V0XR) CARGO DOOR CABLE TORSION RODS BRACKET CRACKED. R & R SUPPORT. W/C 2072

V0XR201101130005

EMB  

 

 

SEAT TRACK

CORRODED

1/13/2011

EMB145LR

 

 

14532606001

ZONE 100

(V0XR) CORRECTION SEAT TRACK POS A FR 24-30 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK. W/C 2146

V0XR201101130006

EMB  

 

 

SILL

CRACKED

1/13/2011

EMB145LR

 

 

14525422007

ZONE 100

(V0XR) RT CARGO FLOOR SILL BETWEEN FR 68-71 IS CRACKED. R & R SILL. W/C 2194

V0XR201101130007

EMB  

 

 

PROFILE

CRACKED

1/13/2011

EMB145LR

 

 

14523775601

ZONE 100

(V0XR) FWD LOWER CORNER OF CARGO FLOOR IS DAMAGED. R & R PROFILE. W/C 8011

V0XR201101140001

EMB  

 

 

SUPPORT

BROKEN

1/14/2011

EMB145LR

 

 

14534802001

BS 6938

(V0XR) FLIGHT CABLE STANDOFF SUPPORT BROKEN AT STA 6938. R & R SUPPORT. W/C 1128

V0XR2011011200022

EMB  

 

 

SEAT TRACK

CORRODED

1/12/2011

EMB145LR

 

 

14530658003

ZONE 100

SEAT TRACK POS C AT FR 30-36 IS CORRODED BEYOND LIMITS. R & R SEAT TRACK.

V0XR201101130001

EMB  

 

 

SUPPORT

CRACKED

1/13/2011

EMB145LR

 

 

14572167003

ZONE 500

LT UPPER WING TO BODY FAIRING SUPPORT STRIP STA 16143.5-17445.0 IS CRACKED. R & R STRIP. W/C 1054.

2011FA0000027

HUGHES

LYC  

 

THRUST BEARING

MISMANUFACTURED

1/14/2011

269C

HIO360*

 

269A18135

MAIN ROTOR

(OG5S) DURING 800 HR, 12 AND 24 MONTH INSP, THE MAIN ROTOR DRIVE SHAFT WAS FOUND TO BE WORN JUST ABOVE THE MAIN ROTOR THRUST BEARING. UPON FUTHER INSP, THE WEAR WAS DETERMINED TO BE CAUSED BY THE M/R THRUST BEARING TUBE NOT BEING CHAMFERED IN THE CONTACT AREA. THIS WAS CONFIRMED BY COMPARISON WITH A NEW THRUST BEARING TUBE. MFG HAS BEEN CONTACTED AND MAIN ROTOR DRIVE SHAFT HAS BEEN SENT TO THEM FOR EVALUATION.

2011FA0000049

PIPER

LYC  

 

SHAFT

MISMANUFACTURED

1/18/2011

PA28181

O360A1D

 

65246000

STAB TRIM

LOOKING UNDER 10X YOU CAN SEE MACHINE MARKS ON THE THREADS OF THE SHAFT PREVENTING THE SHAFT FROM THREADING INTO THE TRIM BARREL. 4 IN STOCK ALL ARE FROM DATE 3/19/10 WITH A BATCH NR OF 6641D28J ALL WITH SAME DEFECT. USED A SHAFT WITH A DIFFERENT BATCH NR AND NO DEFECTS NOTED.