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

403

bald eagle watching over three eggs

FEBRUARY

2012

 


CONTENTS

AIRPLANES

CESSNA...................................................................................................................................... 1

HAWKER.................................................................................................................................. 10

PIPER......................................................................................................................................... 11

HELICOPTERS

BELL.......................................................................................................................................... 13

POWERPLANTS

CONTINENTAL....................................................................................................................... 24

ECI CYLINDERS...................................................................................................................... 24

ROTAX...................................................................................................................................... 28

 

AIR NOTES

INTERNET SERVICE DIFFICULTY REPORTING (iSDR) WEB SITE................................... 29

IF YOU WANT TO CONTACT US......................................................................................... 30

AVIATION SERVICE DIFFICULTY REPORTS...................................................................... 30

 


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

Cessna:  208B; Cracked Elevator Pulley Support; ATA 5320

An air operator's submission states, "The left pulley support web below the floor at FS (fuselage station) 120.0 and LBL (butt line) 10.0 cracked—from the left elevator bell crank mount bolt access hole to the end of the web."  (Pulley Support P/N: 2613083-1.)


CATALOG DRAWING OF DEFECT LOCATION.


CLOSEUP PHOTO OF CRACKED WEB.


CLOSEUP PHOTO OF CRACKED WEB REPAIR.

Part Total Time:  12,853.3 hours

 


Cessna:  335; Corroded Wing Attach Fittings; ATA 5741

A technician for an air charter service says, "During a 100 hour inspection, the forward upper L/H wing attach point (was found to have) corrosion on the wing attach fitting (P/N 08113507).  After removing the upper wing-fuselage fairing, inspection revealed intergranular corrosion on the fitting, and severe rust on the mounting bolt heads.  The fitting was replaced due to the severity of the corrosion.  Probable cause (for this corrosion) is the fuselage-wing fairing not being sealed properly in the area above the fitting.  This allowed moisture to pool in the recessed area of the fitting, causing the rust and corrosion.  The fuselage-wing fairing is riveted to the fuselage, making (detailed) inspection of the upper forward mounts difficult."

PHOTO OF WING ROOT AREA AND FAIRING.


PHOTO OF WING TO FUSELAGE ATTACHMENT CORROSION.

(The SDRS data system reflects four of these P/N's.  Thanks for the..."ugly" photo—Ed.)

Part Total Time:  5,559.0 hours

 


Cessna:  560XL; Broken ECU Aspirator Tube; ATA 3600

An unidentified submitter provides this defect report.  "(I) discovered this  ECU aspirator high pressure tube...broken on preflight.  I also found the bias bleed air tube chafed.  This condition appears to be (caused) by poor tube routing, (creating) ongoing chafing over an unknown amount of time."  (No part numbers were provided with this report.  But a couple of nice photos leave little doubt as to which tube is in reference.  The photos are distorted vertically—Ed.)

INTERNAL TAIL VIEW OF CRACKED ECU TUBE.


INTERNAL TAIL VIEW OF CRACKED ECU TUBE.

INTERNAL TAIL VIEW OF CRACKED ECU TUBE.


INTERNAL TAIL VIEW OF CRACKED ECU TUBE.

INTERNAL TAIL VIEW OF CRACKED ECU TUBE.

Part Total Time:  1,378.0 hours

 


Hawker:  800XP; Corroded Fuselage Attachment Links; ATA 5741

A repair station technician says, "Severe corrosion was found in the L/H lower, wing-to-fuselage casting lug during a 12/8 year links/brackets/bolts inspection.

"Probable cause:  exposure to constant moisture from improper fuselage-to-wing fairing sealing practices (produced the corrosion), and/or constant exposure to TKS anti-icing fluid from improper plumbing practices that may have lead to system leaks (and then subsequent corrosion).

"Recommendation:  proper sealing methods (should be employed) when attaching wing-to-fuselage fairings.  And proper plumbing practices (should be used) when performing maintenance on wing anti-ice systems.  Note:  Use of a corrosion preventative compound...at this location may prevent this condition ...with scheduled applications."  (Wing-to-fuselage link/bearing P/N:  25-8WS3103-1.  The following photos are distorted vertically—Ed.)

PHOTO OF THE WING-TO-FUSELAGE ATTACHMENT LINK.


CLOEUP PHOTO OF THE LINK'S CORROSION.

Part Total Time:  4,420.0 hours

 

Piper:  PA44-180; Cracked Nacelle Angles; ATA 5413

"During a scheduled inspection, a crack was found in the nacelle angle," states this mechanic.  "Upon further investigation the crack was found to (run) between the two rivets that extend through the wing skin into the cap (P/N:  67097-002 or -003) which is attached to a web (P/N 67079-000 or 001).  (This web) is where the main gear aft attach point is mounted. 

"(I) suspect this failure is caused by fatigue."


PHOTO OF THE NACELLE ROOT.


PHOTO OF THE CRACKED SKIN.

Part Total Time:  6,210.0 hours

 

HELICOPTERS

Bell:  206L-3; Improper Pitch Link Hardware; ATA (n/a)

(The following safety admonition is provided by Aerospace Engineer Charles C. Harrison from the FAA's Rotorcraft Certification Office.  Contact information is found at the discussion's end—followed by another hardware Alerts article.)


SAFETY ADMONITION FROM FAA'S ROTORCRAFT CERTIFICATION OFFICE (ASW-170).


BELL OPERATIONS SAFETY NOTICE.

(Interested parties may contact Mr. Harrison at the Rotorcraft Certification Office, 2601 Meacham Blvd., Fort Worth, Texas; 76137; phone 817-222-5128; e-mail charles.c.harrison@faa.gov)

Part Total Time (n/a)

 


Bell, Robinson, Agusta Westland: (All) Hardware Failures; ATA (n/a)

(This second safety admonition also comes from Aerospace Engineer Charles C. Harrison from the FAA's Rotorcraft Certification Office.  Contact information is found at the article's end.  "Thank-you" to our Rotorcraft office for good counsel—Ed.)

 

SAFETY ADMONITION FROM ROTORCRAFT CERTIFICATION OFFICE (ASW-170).


BELL OPERATION SAFETY NOTICE.


BELL OPERATION SAFETY NOTICE.


BELL OPERATION SAFETY NOTICE.


BELL OPERATION SAFETY NOTICE.


BELL OPERATION SAFETY NOTICE.


BELL OPERATION SAFETY NOTICE.


BELL OPERATION SAFETY NOTICE.


(Interested parties may contact Mr. Harrison at the Rotorcraft Certification Office, 2601 Meacham Blvd., Fort Worth, Texas; 76137; phone 817-222-5128; e-mail charles.c.harrison@faa.gov)

Part Total Time (n/a)

 

POWERPLANTS

Continental:  TSIO-520C; Catastrophic Engine Failure; ATA 7100

"This aircraft engine had 35 hours since its overhaul," says this FAA inspector's ongoing report.  "The overhaul facility 'broke-in' the engine.  Post catastrophic failure inspection revealed extremely high temperatures:  crankshaft journals melted, stretched valves, and discoloration in the rods and cylinders.  The exact cause is undetermined.  A possible cause is improper lean-to-peak procedures."

Part Total Time:  35.0 hours

 

ECI Cylinders: TISN712BCA; Failed Valve Guides; ATA 8530

This general aviation report states, "Six new Engine Components, Inc. (ECI) cylinders were installed...at 2,812 hours total time.  The ECI cylinders experienced a failure of the valve guides on three of the six cylinders at 384 hours time in service.  All three failed valve guides broke off at the insert point (see photos), and one completely disintegrated—contaminating the engine with metal debris.  This (debris) caused chafing on at least two valve lifter assemblies, and damage to the camshaft.  The engine will require a complete tear down because of the metal contamination and damage.

"The only initial, abnormal indication noted from the broken exhaust valve guides was excessive engine oil blowing through the engine crankcase breather.  This was noted by a significant amount of oil on the belly of the aircraft.  The engine operated normally with no apparent power loss or abnormal indications of EGT, TIT, or oil pressure/temperature.  Eventually turbine operation became erratic, caused by momentary blockage within the turbine waste-gate controller.  This condition was intermittent.  Flaws were found by visual inspection after low compression was found on two of the effected cylinders...."

(The following photos suffer significant vertical distortion by this editor.  Nine of these cylinder P/N's are found in the SDRS database.  Individual part numbers were not provided with this report.)


CYLINDER HEAD NUMBER 1

DESTROYED VALVE GUIDE PIECES FOR NUMBER 1.


PHOTO OF CYLINDER HEAD NUMBER 3.

BROKEN VALVE GUIDE.


CYLINDER HEAD NUMBER 5.

DAMAGED VALVE LIFTERS (SAMPLE).

Part Total Time:  384.0 hours

 


Rotax:  912ULS; Cracked Fuel Hose; ATA 2820

(The following describes a powerplant on a Eurofox Light Sport Aircraft.)

"The engine surged like it was starved for fuel, and then quit," says this submitter.  "The engine was restarted in flight, but with the same result.  This aircraft was manufactured without fire sleeves on any of the fuel hoses in the engine compartment.  The Rotax 912 installation manual cautions to prevent vapor lock, all fuel lines on the suction side of the fuel pump have to be insulated from fire and heat.  These fuel hoses (P/N FUB386) were over four years old and were becoming stiff and cracked."

PHOTO OF CRACKED RUBBER FUEL HOSE.

Part Total Time:  778.0 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

2011FA0000744

 

 

 

CONVERTER

DEFECTIVE

10/18/2011

 

 

 

601509173

INTERNAL TO UNIT

DURING INSTALLATION OF REPAIRED CONVERTER RECEIVED FROM MFG, POWER WAS APPLIED, LT DIGITS WERE UNCONTROLLABLY BRIGHT (ALONG WITH ALL FUEL QUANTITY, EXCEPT TOTAL). ADDTIONALLY, THE RT LED'S WERE ALSO UNCONTROLLABLY BRIGHT.

2011FA0000732

 

PWA   

 

SUN GEAR

FAILED

10/14/2011

 

PT6A42

 

E3028456

RGB  

ENGINE REMOVED FOR METAL IN OIL CONDITION. UPON DISASSEMBLY FOUND 1ST STAGE SUN GEAR PN E3028456, SN SG35-055 AND 1ST STAGE PLANET GEAR SET PN E310152502, SN EE4072 WITH DAMAGED, BROKEN TEETH. THESE ARE PMA GEARS.

2011FA0000733

 

PWA   

 

PUSHROD

FAILED

9/26/2011

 

R1340AN1

 

11876

CYLINDER

AN EXHAUST PUSH ROD WAS FOUND TO HAVE FAILED. THE PUSH ROD BROKE ADJACENT TO TAPPET. IT WAS FOUND THAT SB 1722 HAD NOT BEEN COMPLIED WITH. THE SB RECOMMENDS SHOT PEENING OF ALUMINUM PUSH RODS FOR STRENGTH.

KY1R2011072510012

AEROSP

TMECA

 

CHIP DETECTOR

BROKEN

7/25/2010

AS365N2

ARRIEL1C

 

9520011655

NR 2 ENGINE

ON PREFLIGHT INSPECTION, PILOT FOUND M04 MAGNETIC DETECTOR TIP BROKEN FROM BASE. TIP OF THE DETECTOR WAS RETAINED BY THE MAGNETIC BASE, AND SUBSEQUENTLY REMOVED.

2011FA0000740

AYRES

PWA   

 

BEARING

FAILED

11/10/2011

S2RT34NORMAL

PT6*

 

3028004

ENGINE

NR 2 BEARING FAILED CAUSING LOSS OF OIL AND EMERGENCY LANDING.

2011FA0000780

BBAVIA

 

 

BOLT

BROKEN

11/28/2011

8KCAB

 

 

MS2000732

MLG LEG

BOLT BROKE ON ACFT ROLL OUT. SRM RECOMMENDS THE BOLT BE REPLACED EVERY 500 HRS, TIS.

V0DR20111114015

BEECH

 

 

BEARING

FAILED

11/14/2011

1900D

 

 

M4000AC3

VENT BLOWER

THE VENT BLOWER WAS REMOVED FOR MAINTENANCE. TECH REPORTED DURING DISASSEMBLY COM END BEARING HAD FAILED. INSPECTION OF THE BEARING REVEALED THE BEARING CAGE HAD LET GO.

V0DR20111114016

BEECH

 

 

BEARING

FAILED

11/14/2011

1900D

 

 

M4000AC3

VENT BLOWER

BLOWER WAS REPORTED TO CAUSE CURRENT LIMITER TO BLOW ON CUSTOMER'S ACFT. DURING DISASSEMBLY OF THE VENT BLOWER TECHNICIAN FOUND COMM END BEARING TO HAVE FAILED AND COME APART.

V0DR20111114017

BEECH

 

 

BEARING

FAILED

11/14/2011

1900D

 

 

M4000AC3

VENT BLOWER

TECH REPORTED THAT DURING DISSASEMBLY, FOUND THAT THE COMM END BEARING HAD FAILED.

RMIA2011112200056

BEECH

 

 

BULKHEAD

CRACKED

11/22/2011

1900D

 

 

11444002611

ZONE 100

LOWER PORTION OF FUSELAGE CANTED BULKHEAD AT FS 570 BUCKLED. THE LT SIDE OF THE BULKHEAD HAS SMALL CRACKS AROUND RIVET HOLES AT STRINGER 8L. EARLIER SN OF THIS MODEL ACFT HAD 0.032" BULKHEADS WITH A KIT TO UPSIZE THE SIDES OF THE BULKHEAD TO 0.050".

VIB8101420110001

BEECH

PWA   

 

ACCESS PANEL

CORRODED

10/10/2011

200BEECH

PT6A60A

 

10112007614

ZONE 600

REMOVED LT AND RT AUXILIARY FUEL TANK ACCESS COVERS FOR INSPECTION. FOUND CORROSION ON LT AND RT WING BONDED PANEL DISH FLANGES. RIGHT ACCESS COVER HAD SEVERE CORROSION AND WAS REPLACED WITH NEW. INSTALLED NEW GASKETS IAW RECOMMENDED SB 28-4059.

E81R2011010232281

BEECH

 

 

FLAP SYSTEM

MALFUNCTIONED

1/2/2012

400A

 

 

 

 

INVESTIGATED FLAP SYS ASSYMETRY WARNING ANNUNCIATOR LIGHT INDICATION. FOUND RT FLAP FOLLOW-UP SWITCH ACTUATING ARM .075 IN. LONGER THAN LT FOLLOW-UP SWITCH ACTUATING ARM. ADJUSTED RT FOLLOW-UP SWITCH ACTUATING ARM TO MATCH LT FOLLOW-UP SWITCH ACTUATING SWITCH ARM LENGTH. ADJUSTED LT AND RT FLAP POSITION TRANSMITTER VOLTAGES AND LT AND RT FLAP FOLLOW-UP SWITCH VOLTAGES AS REQUIRED TO BRING WITHIN MM 27-50-00 SERVICE LIMITS. VERIFIED FLAP SYS FOLLOW-UP SWITCH CLEARANCES AND FLAP SYS RIGGING WITHIN THE MM 27-50-00 SERVICE LIMITS. FLAP SYS FUNCTIONAL CHECKS SATISFACTORY, NO FAULTS INDICATED. PAST MX HISTORY ON FLAP SYS COMPONENTS UNKNOWN.

2011FA0000781

BEECH

 

GARMIN INTL

ANTENNA

INOPERATIVE

11/8/2011

C90   

 

 

0130023500

NR 2 GPS

TROUBLESHOT BOTH NR 1 & 2 GPS SYSTEMS DUE TO BEING INOPERATIVE. FOUND NR 2 ANTENNA RESISTANCE CHECKED OK, ANY TIME NR 2 GPS SYSTEM TURNED ON IT CAUSED A BLOCKAGE OF ALL GPS SIGNALS TO ACFT. WITH NR 2 GPS SYS TURNED OFF NR 1 GPS SYS OPERATED GOOD WITH NO PROBLEMS NOTED. INSTALLED NEW NR 2 ANTENNA AND BOTH SYS OPS TESTED OK WITH NO PROBLEMS NOTED.

2011FA0000731

BEECH

CONT

 

CIRCUIT BREAKER

FAILED

11/4/2011

F33A

IO520BB

 

35380132103

BEACON

PILOT REPORTED BEACON LIGHT INTERMITTENT. ON TROUBLESHOOTING, TECH FOUND CIRCUIT BREAKER/ SWITCH TO BE AT FAULT. BEACON SWITCH WAS PREVIOUSLY REPLACED 721.9 FLIGHT HOURS PRIOR. NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME.

2011FA0000737

BEECH

CONT

 

CIRCUIT BREAKER

FAILED

11/9/2011

F33A

IO520BB

 

35380132101

NAV LIGHTS

PILOT REPORTED NAV LIGHTS INOPERATIVE. MX FOUND CIRCUIT BREAKER TO BE AT FAULT. AD 2008-13-17 HAD BEEN COMPLETED 2489.0 FLIGHT HOURS PRIOR.

2011FA0000738

BEECH

CONT

 

CIRCUIT BREAKER

FAILED

11/9/2011

F33A

IO520BB

 

35380132103

TAXI LIGHT

PILOT REPORTED TAXI LIGHT INOPERATIVE. MX DISCOVERED TAXI LIGHT CIRCUIT BREAKER TO BE AT FAULT. AD 2008-13-17 HAD BEEN COMPLETED 1868.0 FLIGHT HOURS PRIOR AND THIS SWITCH HAS 834.2 FLIGHT HOURS SINCE BEING LAST REPLACED.

2011FA0000739

BEECH

CONT

 

CIRCUIT BREAKER

FAILED

11/10/2011

F33A

IO520BB

 

35380132101

ZONE 100

PILOT REPORTED NAV LIGHT ON WHEN CIRCUIT BREAKER/SWITCH IN THE OFF POSITION & OFF WHEN CIRCUIT BREAKER WAS IN THE ON POSITION. MX FOUND CIRCUIT BREAKER TO BE AT FAULT. AD 2008-13-17 HAD BEEN COMPLETED 2007.5 FLIGHT HOURS PRIOR.

2011FA0000745

BEECH

CONT

 

CIRCUIT BREAKER

UNSERVICEABLE

11/14/2011

F33A

IO520BB

 

35380132103

STROBE

PILOT REPORTED STROBE INOPERATIVE. ON TROUBLESHOOTING THE TECH FOUND THE CIRCUIT BREAKER AT FAULT. INSTALLED NEW CIRCUIT BREAKER/SWITCH. OPS CHECK OK. NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME.

2011FA0000743

BELL  

 

 

FITTING

FAILED

9/23/2011

206B3

 

 

 

T/R D/S BEARING

AFTER SUSPECTED TAIL ROTOR STRIKE IN SNOW, TAIL ROTOR DRIVE SYS WAS VISUALLY INSPECTED. TAIL TO FREEWHEELING UNIT, NO DAMAGE NOTED. ACFT GROUND RUN AND NO DISCREPANCIES NOTED. ON ATTEMPTING TO HOVER ACFT TO A MORE LEVEL SPOT ON GLACIER, NR 3 TAILROTOR DRIVESHAFT SEGMENT BONDED FITTING FAILED SLOWING TAIL ROTOR. BOND THAT SPECIFICALLY FAILED WAS FORWARD BOND NEAR TAIL ROTOR DRIVESHAFT BEARING FOR THAT SEGMENT. AIRCRAFT BEING REPAIRED IAW THE MM.

FOTR21180104091

BOEING

 

 

SKIN

MISREPAIRED

11/10/2011

727227

 

 

 

ZONE 100

FUSELAGE SKIN MISREPAIRED AT BS 332 S19R LAPJOINT. REPAIRED ON FASI WO 21180, NR104091.

FOTR2011111004092

BOEING

 

 

SKIN

MISREPAIRED

11/10/2011

727227

 

 

 

ZONE 100

FUSELAGE SKIN MISREPAIRED AT BS 412.5 S19R LAPJOINT. REPAIRED ON FASI WO 21180, NR104092.

FOTR201111104095

BOEING

 

 

SKIN

MISREPAIRED

11/10/2011

727227

 

 

 

ZONE 200

FUSELAGE SKIN MISREPAIRED AT BS 418 BETWEEN S15-18R. REPAIRED ON FASI WO 21180, NR 104095.

FOTR2011110804099

BOEING

 

 

SKIN

MISREPAIRED

11/8/2011

727227

 

 

 

ZONE 100

FUSELAGE SKIN AT BS 990, C-2 DOOR CUTOUT AFT EDGE MISREPAIRED. REPAIRED ON FASI WO 21180, NR 104099.

FOTR2011111004108

BOEING

 

 

SKIN

MISREPAIRED

11/10/2011

727227

 

 

 

ZONE 100

FUSELAGE SKIN AT BS 356 S23R MISREPAIRED. REPAIRED ON FASI WO 21180, NR 104108.

FOTR2011111004151

BOEING

 

 

SKIN

CORRODED

11/10/2011

727227

 

 

 

ZONE 100

BS 419 - 533 S19R LAP JOINT CORRODED. REPAIRED ON FASI WO 21180, NR 104151.

FOTR2011111004160

BOEING

 

 

SKIN

CORRODED

11/10/2011

727227

 

 

 

ZONE 100

SKIN BS 676 BETWEEN S21-22R CORRODED AROUND EDGES OF REPAIR. REPAIRED ON FASI WO 21180, NR 104160.

FOTR2011110804195

BOEING

 

 

SKIN

DENTED

11/8/2011

727227

 

 

 

ZONE 200

SKIN BS 690 ABOVE S4R DENTED. REPAIRED ON FASI WO 21180, NR 104195.

FOTR2011111204209

BOEING

 

 

SKIN

MISREPAIRED

11/12/2011

727227

 

 

 

ZONE 100

FUSELAGE SKIN AT BS 720D-740 BETWEEN S25-27 RT MISREPAIRED. REPAIRED ON FASI WO 21180, NR 104209.

FOTR2011111004230

BOEING

 

 

SKIN

MISREPAIRED

11/10/2011

727227

 

 

 

ZONE 100

SKIN AT BS 720C+16.5 - 720D+7.5 BETWEEN STR 27R-28R MISREPAIRED. REPAIRED ON FASI WO 21180, NR 104230.

FOTR2011102104205

BOEING

 

 

SKIN

DAMAGED

10/21/2011

727227

 

 

 

ZONE 100

UPON REMOVAL OF EXTERNAL DOUBLER AT BS 665 S21R FOUND DAMAGED. REPAIRED ON FASI WO 21180, NR 104205.

FOTR2011101714097

BOEING

 

 

SKIN

MISREPAIRED

10/17/2011

727227

 

 

 

ZONE 200

FUSELAGE SKIN, STA 254.5 BETWEEN S9-11L MISREPAIRED. REPAIRED ON FASI WO 21180, NR 104097.

FOTR2011100704143

BOEING

 

 

SKIN

MISREPAIRED

10/7/2011

727227

 

 

 

ZONE 100

FUSELAGE SKIN, BS 431 BETWEEN S21-23L MISREPAIRED. REPAIRED ON FASI WO 21180, NR 104143.

FOTR2011100704115

BOEING

 

 

SKIN

MISREPAIRED

10/7/2011

727227

 

 

 

ZONE 100

FUSELAGE SKIN STA 395.5 AT S22R MISREPAIRED. REPAIRED ON FASI WO 104115, NR 104115.

FOTR2011101704199

BOEING

 

 

INTERCOSTAL

CRACKED

10/17/2011

727227

 

 

 

ZONE 200

BS 375 S12R, UPPER INTERCOSTAL CRACKED. REPAIRED ON FASI WO 21180, NR 104199.

FOTR2011101704200

BOEING

 

 

INTERCOSTAL

CRACKED

10/17/2011

727227

 

 

 

ZONE 200

BS 375 S12R, LOWER INTERCOSTAL CRACKED. REPAIRED ON FASI WO 21180, NR 104200.

FOTR21180104148

BOEING

 

 

SKIN

BULGED

10/14/2011

727227

 

 

 

ZONE 100

S-19R, STA 694 SKIN HAS A BULGE (POSSIBLE CORROSION). REPAIRED ON FASI WO 21180, NR 104148.

FOTR2011100406432

BOEING

 

 

FRAME

CORRODED

10/4/2011

727232

 

 

 

ZONE 100

SURFACE CORROSION AT BS 727, FRAME LBL 5 TO RBL 5 , AFT SIDE, LWR AFT CARGO. REPAIRED ON FASI WO 21142, NR 06432.

ABXR2012F00007

BOEING

 

 

EXHAUST GATE

CORRODED

11/10/2011

737   

 

 

65C263116

ZONE 600

LOWER SKIN OF EXHAUST GATE CORRODED AT OTBD EDGE. REPAIRED IAW SRM 51-40-02 AND PROCESS STANDARDS MANUAL.

ABXR2012F00008

BOEING

 

 

EXHAUST GATE

CORRODED

11/10/2011

737   

 

 

65C263116

ZONE 600

LOWER SKIN OF EXHAUST GATE CORRODED AT OTBD EDGE. REPAIRED IAW SRM 51-40-02 AND AMES PROCESS STANDARDS MANUAL.

ZI3R201111150005

BOEING

CFMINT

 

VALVE

WRONG PART

11/15/2011

737*

CFM567B2US

 

6062120

FUEL NOZZLE

ELEVEN(11) CFM56-7B FUEL NOZZLES,PN 6840023E18,WERE RECEIVED FOR BENCH TEST AND REPAIR IAW CMM 73-11-42. NINE(9) OF THE ELEVEN(11) NOZZLES FAILED BENCH TEST AND WERE MOVED TO REPAIR. UPON REMOVAL OF THE FLOW DIVIDER VALVES, THE MACHINIST NOTICED THAT THE WRONG VALVE WAS INSTALLED IN 4 OF THE NOZZLES AS WELL AS THE WRONG O-RINGS FOR THOSE VALVES. THE CORRECT VALVE FOR FUEL NOZZLE 6840023E18 IS PN 6062120. THE CORRECT O-RING SEALS FOR VALVE PN 6062120 ARE PN'S 6062124-001 (WHITE), AND 6062125 (BROWN). THE INCORRECT VALVES FOUND INSTALLED IN THE SUBJECT NOZZLES ARE PN 6002135. THIS VALVE IS FOUND INSTALLED PRIMARILY ON FUEL NOZZLE 6840023M1 WITH A BLACK O-RING PN 6871674-965. IT APPEARS THAT THESE FOUR NOZZLES, SN PCY049E1, PCY068E1, PCY067E3, AND PCY067E6, WERE IMPROPERLY UPDATED FROM 6840023M1 TO 6840023E18 IAW SB 73-0132. EVIDENCE OF UPDATE AFTER OEM MFG INCLUDES LINED OUT MARKINGS, VISUALLY POOR QUALITY VALVE COVER WELDS, INCORRECT FLOW DIVIDER VALVE INSTALLED AND INCORRECT O-RING SEALS INSTALLED. THE SUBJECT FUEL NOZZLES HAD NOT BEEN PREVIOUSLY MAINTAINED AT THIS REPAIR STATION.

ZI3R201111150006

BOEING

CFMINT

 

VALVE

WRONG PART

11/15/2011

737*

CFM567B2US

 

6062120

FUEL NOZZLE

ELEVEN (11) CFM56-7B FUEL NOZZLES, PN 6840023E18, WERE RECEIVED FOR BENCH TEST AND REPAIR IAW CMM 73-11-42. NINE(9) OF THE ELEVEN(11) NOZZLES FAILED BENCH TEST AND WERE MOVED TO REPAIR. UPON REMOVAL OF THE FLOW DIVIDER VALVES, THE MACHINIST NOTICED THAT THE WRONG VALVE WAS INSTALLED IN 4 OF THE NOZZLES AS WELL AS THE WRONG O-RINGS FOR THOSE VALVES. THE CORRECT VALVE FOR FUEL NOZZLE 6840023E18 IS PN 6062120. THE CORRECT O-RING SEALS FOR VALVE PN 6062120 ARE PN'S 6062124-001 (WHITE), AND 6062125 (BROWN). THE INCORRECT VALVES FOUND INSTALLED IN THE SUBJECT NOZZLES ARE PN 6002135. THIS VALVE IS FOUND INSTALLED PRIMARILY ON FUEL NOZZLE 6840023M1 WITH A BLACK O-RING PN 6871674-965. IT APPEARS THAT THESE 4 NOZZLES, SNS PCY049E1, PCY068E1, PCY067E3, AND PCY067E6, WERE IMPROPERLY UPDATED FROM 6840023M1 TO 6840023E18 IAW SB 73-0132. EVIDENCE OF UPDATE AFTER OEM MFG INCLUDES LINED OUT MARKINGS, VISUALLY POOR QUALITY VALVE COVER WELDS, INCORRECT FLOW DIVIDER VALVE INSTALLED AND INCORRECT O-RING SEALS INSTALLED. THE SUBJECT FUEL NOZZLES HAD NOT BEEN PREVIOUSLY MAINTAINED AT THIS REPAIR STATION.

FOTR2011101406609

BOEING

 

 

FRAME

CORRODED

10/14/2011

737232

 

 

 

ZONE 100

TOP OF FRAME BS 727E, S25L CORRODED. REPAIRED ON FASI WO 21142, NR 06609.

FOTR2011103106811

BOEING

 

 

FRAME

CORRODED

10/31/2011

7373Q8

 

 

 

ZONE 100

AFT CARGO FRAME AT BS 807 BL 0, CORRODED. REPAIRED ON FASI WO21142, NR06811.

FOTR201110306608

BOEING

 

 

FRAME

GOUGED

10/3/2011

7373Q8

 

 

 

ZONE 100

TOP OF FRAME BS 747, S25L, GOUGED. REPAIRED ON FASI WO 21142, NR 06608.

FOTR2011103106450

BOEING

 

 

FRAME

CORRODED

10/31/2011

7373Q8

 

 

 

ZONE 100

AFT CARGO FRAME AT STA 787, S27R HAS CORROSION. REPAIRED ON FASI WO21142, NR 06450.

FOTR2011103106449

BOEING

 

 

FRAME

CORRODED

10/31/2011

7373Q8

 

 

 

ZONE 100

AFT CARGO FRAME AT STA 794, S28R HAS CORROSION. REPAIRED ON FASI WO21142, NR 06449.

FOTR2011101106444

BOEING

 

 

SHEAR TIE

CORRODED

10/11/2011

7373Q8

 

 

 

ZONE 100

CORROSION AT FRAME SHEAR TIE, BS 867, S28L TO 28R, AFT CARGO. REPAIRED ON FASI WO 21142, NR 06444.

FOTR2011101206434

BOEING

 

 

FRAME

CORRODED

10/12/2011

7373Q8

 

 

 

ZONE 100

CORROSION AT FRAME, BS 767 AFT SIDE, LWR RBL 2 AFT CARGO. REPAIRED ON FASI WO 21142, NR 0634. SUPPLEMENTAL.

FOTR2011110706431

BOEING

 

 

FRAME

CORRODED

11/7/2011

7373Q8

 

 

 

ZONE 200

LIGHT SURFACE CORROSION AT FRAME BS 727E, AFT SIDE LWR RBL 3. REPAIRED ON FASI WO 21142, NR 06431.

FOTR2011100406428

BOEING

 

 

FRAME

CORRODED

10/4/2011

7373Q8

 

 

 

ZONE 100

SURFACE CORROSION ON FRAME AT BS 727D AFT SIDE OF RBL 3 AFT CARGO. REPAIRED ON FASI WO 21142, NR 06428.

FOTR201110270639

BOEING

 

 

SKIN

CORRODED

10/27/2011

7373Q8

 

 

 

ZONE 100

CORROSION AT SKIN AND SKIN SPLICE, BS 907, S28L TO 27R, AFT CARGO. REPAIRED ON FASO WO 21142, NR 06439.

FOTR2011103106792

BOEING

 

 

DOOR FRAME

DAMAGED

10/31/2011

7373Q8

 

 

 

ZONE 100

AFT PIT INBD OF DOOR CUTOUT FRAME HAS 3 DRILL STARTS. REPAIRED ON FASI WO21142, NR06792.

FOTR2011101506876

BOEING

 

 

SKIN

DENTED

10/15/2011

7373Q8

 

 

 

HORIZONTAL STAB

RT HORIZONTAL STAB L/E DENTED AT STAB STA 75. REPAIRED ON FASI WO21142, NR 06876.

FOTR2011102606423

BOEING

 

 

SILL

DAMAGED

10/26/2011

7373Q8

 

 

 

ZONE 100

L2 DOOR LOWER SILL BS 986.5, S20L DAMAGED. REPAIRED ON FASI WO 21142, NR 06423.

FOTR2011103106818

BOEING

 

 

SKIN

DAMAGED

10/31/2011

7373Q8

 

 

 

ZONE 100

FUSELAGE BS 360 BUTT JOINT S25-27L DAMAGED. REPAIRED ON FASI WO 21142, NR 06818.

SROM2011012

BOEING

 

 

INTERCOSTAL

CRACKED

11/17/2011

7377BD

 

 

141A541012

FUSELAGE

FORWARD MAIN ENTRANCE DOOR WET AREA INTERCOSTAL AT BS 312 - BS 328, LBL 46 REPLACED WITH NEW P/N 141A5410-12 IN ACCORDANCE WITH BOEING STRUCTURAL REPAIR MANUAL (SRM) D634A201, REV 44, CHAPTER 51-40-02.

SROM2011013

BOEING

 

 

SKIN

CHAFED

11/17/2011

7377BD

 

 

 

FUSELAGE

FUSELAGE SKIN CHAFING WAS NOTED BELOW DORSAL FAIRING, BLENDED AND FOUND WITHIN LIMITS AT BS 847 IN ACCORDANCE WITH BOEING SR NO. 1-2034146972, MESSAGES XDV-ATR-11-0002-01C, DATED NOVEMBER 8, 2011, XDV-ATR-11-0002-05B, DATED NOVEMBER 10, 2011, AND XDV-ATR-11-0002-06C, DATED NOVEMBER 10, 2011 PER BOEING ODA-300064-NM APPROVED FORM 8100-9, DATED NOVEMBER 11, 2011. NOMINAL THICKNESS 0.640 INCH, REMAINING 0.036 INCH, MAX MATERIAL REMOVED 0.004 INCH.

TX9Y20111104001

BOEING

 

 

SPLICE PLATE

CRACKED

11/1/2011

747281F

 

 

65B035721

ZONE 300

A FASTENER HOLE WAS FOUND CRACKED AT HORIZONTAL STABILIZER CENTER SECTION LT SIDE LOWER SPLICE PLATE. REPLACED PER MN TEC-SOF-11-0082 AND SRM 51-30-05.

FOTR2011080901225

BOEING

 

 

FLOORBEAM

MISREPAIRED

8/9/2011

75721B

 

 

 

ZONE 200

FLOORBEAM BS 700, BL 0 MISREPAIRED. REPAIRED ON FASI WO 21119, NR 01225.

FOTR2011081201226

BOEING

 

 

FLOORBEAM

MISREPAIRED

8/12/2011

75721B

 

 

 

ZONE 200

FLOORBEAM, BS 1280, BL 0 MISREPAIRED. REPAIRED ON FASI WO 21119, NR 01226.

FOTR2011081601224

BOEING

 

 

FLOORBEAM

MISREPAIRED

8/16/2011

75721B

 

 

 

ZONE 200

FLOORBEAM BS 680 BL 0 MISREPAIRED. REPAIRED ON FASI WO 21119, NR 01224.

FOTR2011090606905

BOEING

 

 

SKIN

MISREPAIRED

9/6/2011

75721B

 

 

 

ZONE 100

FUSELAGE SKIN AT BS 660 STRINGER 26L MISREPAIRED. REPAIRED ON FASI WO 21118, NR 06905.

ABXR2011110700046

BOEING

 

 

STRINGER

CORRODED

11/7/2011

767231

 

 

 

HORIZONTAL STAB

DURING C-CHECK, FOUND HORIZONTAL STAB STRINGER S2 LWR, CORRODED ON AFT SIDE OF VERTICAL LEG BETWEEN RIB 1L-2L. REPAIRED IAW SRM AND REA B655-59478MR.

ABXR2011110700047

BOEING

 

 

STRINGER

CORRODED

11/7/2011

767231

 

 

181T41002

HORIZONTAL STAB

DURING C-CHECK, FOUND HORIZONTAL STAB STRINGER S5 LWR, CORRODED ON AFT SIDE OF VERT FLANGE BETWEEN RIB 1R-2R. REPAIRED IAW SRM AND REA B655-59479MR.

ABXR2011110700048

BOEING

 

 

BULKHEAD

CANNING

11/7/2011

767231

 

 

 

ZONE 200

DURING C-CHECK FOUND AFT PRESSURE BULKHEAD OIL CANNED. REPAIRED IAW WITH REA B653-59512MR.

ANZY20111120102

BOEING

 

 

STRINGER

CORRODED

11/30/2011

7673G5

 

 

 

ZONE 100

ON C CHECK, CORROSION OF STRINGER AT S34R HAD CAUSED MULTIPLE HOLES IN EXTRUSION TO THE POINT THAT NO STRUTURAL MATERIAL WAS LEFT. REPAIR UNDER WAY AT THIS TIME.

E81R2011122632222

BRAERO

GARRTT

 

PUMP

LOW PRESSURE

12/26/2011

BAE125800A

TFE731*

 

4202203

HYD SYSTEM

INVESTIGATED REPORTED "HYD 2 LO PRESS" ANNUNCIATOR LIGHT INDICATION. REPLACED FAILED NR 2 ENGINE HYD PUMP WITH AN O/H PUMP AND DRAINED HYD SYS RESERVOIR, REPLACED SYS SUCTION FILTER. HYDR SYS OPS NORMAL AFTER PUMP REPLACEMENT. HYD PUMP TSN/TSOH UNKNOWN, TRANSIENT ACFT. RECOMMEND O/H FACILITY INSPECT FAILED PUMP AT TEAR-DOWN FOR ANALYSIS.

2011FA0000741

CESSNA

LYC   

 

BUSHING

MIGRATED

11/11/2011

172R

IO360L2A

 

0541202

ZONE 700

BUSHING INSERT MIGRATED TO THE OUTSIDE OF THE BUSHING ASSEMBLY CAUSING PLAY IN THE MAIN LANDING GEAR. THIS HAS HAPPENED ON TWO 172'S THAT ARE OPERATED IN A FLIGHT SCHOOL ENVIRONMENT. BOTH 172'S HAVE SIMILAR TOTAL TIME. THE BUSHINGS ARE RETAINED FOR INSPECTION AS NECESSARY.

FK8R2011120100001

CESSNA

CONT

 

SUPPORT

CRACKED

12/1/2011

2105A

IO470S

 

07526151

SPINNER

CENTER SPINNER SUPPORT CRACKED.

Y2GR201111333574

CESSNA

CONT

 

GEAR

DAMAGED

11/3/2011

310N

IO470VO

 

653631

CRANKSHAFT

CRANKSHAFT GEAR WAS FOUND WITH FOUR TEETH MISSING FROM THE GEAR. THE CAMSHAFT GEAR THAT IT IS MESHED WITH STILL ROTATED AROUND THE GEAR AND MESHED WITH THE REMAINING TEETH. SB 08-12 DATED 9/9/08 SUPERSEDES THIS GEAR PN WITH A NEW HEAVIER GEAR PN 657175 AT THE NEXT ENGINE DISASSEMBLY. THIS ENGINE HAD BEEN DISASSEMBLED FOR A PROPELLER STRIKE INSPECTION.

2011FA0000782

CESSNA

CONT

 

CYLINDER

FAILED

11/8/2011

340A

TSIO520NB

 

AEC631397

NR 3  

NEW CYLINDERS WERE INSTALLED ON ACFT. 2 OF THE 12 CYLINDERS FAILED AT 25.3 TIME IN SERVICE, WITH WHAT LOOKED LIKE THE NICKEL COATING SEPARATING FROM THE CYLINDER WALLS. UPON REMOVAL OF THE CYLINDER (1 FROM EACH ENGINE), THE NICKEL COATING HAD SEPARATED AND THE PISTONS HAD EXTREME SIDE WALL DAMAGE. THE OIL FILTERS WERE REMOVED, CUT OPEN AND INSPECTED; ALUMINUM PARTICLES WERE FOUND IN THE FILTER ELEMENTS.

GNMA8840K112111

CESSNA

 

 

TRUNNION

CRACKED

11/21/2011

414A

 

 

51411036

RT MLG

CRACKS FOUND ON RIGHT MAIN GEAR UPPER BARREL & TRUNNION ASSEMBLY. CRACKS IN THE UPPER TORQUE LINK ATTACH POINTS WERE GREATER THAN ALLOWED PER MEB89-2 REV 1.

GNMA20111209

CESSNA

 

CESSNA

SKIN

WRINKLED

12/7/2011

414A

 

 

513300022

RUDDER

RUDDER WAS RUBBING ON HORIZONTAL UPPER AFT FAIRING ASSEMBLY AND CAUSED A 3" X 3" WRINKLE ON THE RT LOWER AFT SKIN.

EG6R2011101800769

CESSNA

 

 

TUBE

FAILED

10/18/2011

421B

 

 

0923150

NLG TIRE

NOSE TIRE BLEW UPON LANDING. UPON DISASSEMBLING TIRE AND WHEEL ASSY, FOUND APPROX 2 INCH HOLE IN TUBE. PROBABLE CAUSE UNKNOWN.

CWQR2011120632

CESSNA

 

 

TORQUE TUBE

CRACKED

12/6/2011

560CESSNA

 

 

55421029

RT MLG

DURING A SCHEDULED MX CHECK WE FOUND THIS RT LANDING GEAR TORQUE TUBE CRACKED AT THE MOUNT BOLT PIVOT PLATE WHERE IT IS WELDED TO THE TUBE. THIS WAS FOUND VISUALLY, WHILE PERFORMING A GEAR WELL INSPECTION. THE PART WAS R & R WITH NEW, THE ACFT HAS 1517 TOTAL CYCLES. WE HAVE SEEN THIS ISSUE SEVERAL TIMES BEFORE ON ACFT WITH SIMILAR TIMES AND CYCLES. THIS CONDITION WAS ALSO SUBMITTED TO SDR 598740.

DXTR20120113001

CESSNA

 

 

DOOR

STUCK

1/13/2012

560CESSNA

 

 

 

EMERGENCY EXIT

THE EMERGENCY EXIT DOOR WILL NOT RELEASE FROM AIRFRAME WHEN THE HANDLE IS TURNED AND PULLED. EXCESSIVE FORCE WAS REQUIRED TO OPEN.

DXTR20120113002

CESSNA

 

 

INLET

CRACKED

1/13/2012

560CESSNA

 

 

C46B1100022

RT ENGINE

RT ENGINE INLET IS CRACKED 2X (1 & 5 O'CLOCK POSITIONS) ON THE OUTER DUCT & FLANGE ATTACH POINTS.

17GR2011231100001

CESSNA

PWA   

 

OIL SYSTEM

OVERSERVICED

11/23/2011

560CESSNA

PW545A

 

 

RIGHT ENGINE

DURING A CLIMB THROUGH 8,500' MSL TO 10,000' ON SBN APPROACH CONTROL, NOTICED RT ENGINE LOW OIL PRESSURE (RED) ANNUNCIATOR ILLUMINATE. ALSO NOTICED RT ENGINE MANUAL MODE WHITE ANNUNCIATOR ILLUMINATED & OIL PRESSURE GAUGE ZERO FOR RT ENGINE. WITHIN A FEW SECONDS, NOTICED SMOKE IN COCKPIT. DECLARED AN EMERGENCY, PULLED RT POWER LEVER TO IDLE & PUT ON OXYGEN MASKS. WORKED CHECKLIST & SHUTDOWN RT ENGINE. FOLLOWED RADAR VECTORS FOR AN ILS. CONTINUED WITH SMOKE EVACUATION CHECKLIST & DEPRESSURIZED CABIN TO EVACUATED SMOKE. A NORMAL, SINGLE ENGINE, APPROACH & LANDING ACCOMPLISHED. AFTER LANDING, TAXIED TO FBO. SHUTDOWN NORMAL. ENGINE MFG SERVICES PERFORMED BORESCOPE INSPECTION THROUGH COMPRESSOR BLEED VALVE, NO DEFECTS NOTED. PERFORMED MOPLO TEST ON NR 4 BEARING CARBON SEAL. RECORDED VALUE OF 54 PSIA AT TO POWER OF MOPLO TEST FOUND TO BE WITHIN MM LIMITS. RAN ENGINE FOR 1 HR AT VARIOUS POWER SETTINGS, NO DEFECTS NOTED. ENGINE DETERMINED TO HAVE BEEN OVER SERVICED WITH OIL."

DXTR2012011102

CESSNA

 

 

TRIM TAB

WORN

1/11/2012

560XL

 

 

553320042

RUDDER

RUDDER TRIM TAB HAS EXCESSIVE PLAY.

DXTR2012011103

CESSNA

 

CESSNA

RIB   

CRACKED

1/11/2012

560XL

 

 

 

LT WING

LT FLAP WELL T/E RIB AT WS 64.0 IS CRACKED.

DXTR2012011104

CESSNA

 

CESSNA

RIB   

CRACKED

1/11/2012

560XL

 

 

 

RT WING

RT FLAP WELL T/E RIB AT WS 88.6 IS CRACKED.

DXTR2012011105

CESSNA

 

 

STIFFENER

CRACKED

1/11/2012

560XL

 

 

 

NLG WW

NOSE WHEEL STEERING CABLE STIFFNER FOR PULLEY BRACKET JUST FWD OF CENTER PEDESTAL UNDER FLOORBOARD 141BTC HAS APPROX 0.25 INCH CRACK AT TOP, AFT CORNER RADIUS, FROM EDGE HEADING FWD AND DOWN TOWARDS AFT PULLEY BRACKET.

DXTR2012011101

CESSNA

 

 

SKIN

DAMAGED

1/11/2012

560XL

 

 

 

ZONE 600

BOTTOM OF RIGHT INBD FLAP HAS SOFT SPOT FROM IMPACT DAMAGE.

DXTR2011122900001

CESSNA

 

 

CABLE

DAMAGED

12/29/2011

680CE

 

 

99147574

NLG STEERING

DURING NOSE WHEEL STEERING CHECK, THE TILLER WILL ONLY MOVE HALF WAY TO THE LEFT. IF YOU CONTINUE TO APPLY PRESSURE THERE IS A POP IN THE TILLER AND IT CONTINUES THE REMAINER OF TRAVEL TO THE LT.

2011FA0000805

CESSNA

CONT

 

CYLINDER

FRACTURED

11/15/2011

T210L

GTSIO520H

 

TISN712BCA

ZONE 400

6 NEW CYLINDERS WERE INSTALLED AUG 10, 2008 AT 2812 TOTAL TIME. THE CYLINDERS EXPERIENCED A FAILURE OF THE VALVE GUIDES ON 3 OF THE 6 AT 384 HOURS TIME IN SERVICE. ALL 3 FAILED VALVE GUIDES BROKE OFF AT THE INSERT POINT AND 1 COMPLETELY DISINTEGRATED, CONTAMINATING THE ENGINE WITH METAL DEBRIS. THIS IN TURN CAUSED CHAFING ON AT LEAST 2 VALVE LIFTER ASSEMBLIES AND DAMAGE TO THE CAMSHAFT. THE ENGINE WILL REQUIRE A COMPLETE TEAR DOWN DUE METAL CONTAMINATION AND DAMAGE. THE ONLY INITIAL ABNORMAL INDICATION NOTED DUE TO THE BROKEN EXHAUST VALVE GUIDES WAS EXCESSIVE ENGINE OIL BLOWING THROUGH THE ENGINE CRANKCASE BREATHER AS NOTED BY SIGNIFICANT AMOUNT OF OIL ON THE BELLY OF THE ACFT. THE ENGINE OPERATED NORMALLY WITH NO APPARENT POWER LOSS OR ABNORMAL INDICATIONS OF EGT, TIT, OR OIL PRESSURE/TEMPERATURE. EVENTUALLY THE TURBINE OPERATION WAS ERRATIC APPARENTLY CAUSED BY MOMENTARY BLOCKAGE WITHIN THE TURBINE WASTEGATE CONTROLLER. THIS CONDITION WAS INTERMITTENT. FLAWS WERE FOUND BY VISUAL INSP AFTER LOW COMPRESSION WAS FOUND ON 2 OF THE AFFECTED CYLINDERS. AFFECTED SN: 56357-17, 56229-30, 56358-11, 56375-03, 56291-22, 56258-15. CYCLES ARE ESTIMATED AT 1 PER HOUR AND ARE NOT TRACKED ON THIS ACFT.

2011FA0000768

CESSNA

CONT

 

ENGINE

FAILED

11/16/2011

TU206F

TSIO520C

 

TSIO520C

 

ACFT ENGINE HAD 35 HRS SINCE O/H. O/H FACILITY "BROKE IN" ENGINE. POST CATASTROPHIC FAILURE INSPECTION REVEALED EXTREMELY HIGH TEMPERATURES, IE: CRANKSHAFT JOURNALS MELTED, STRETCHED VALVES, DISCOLORATION IN RODS AND CYLINDERS. EXACT CAUSE UNDETERMINED. PROBABLE CAUSE IS IMPROPER LEAN-TO PEAK PROCEDURE.

2011FA0000725

CIRRUS

CONT

 

TUBE

FLAT

11/2/2011

SR22

IO550*

 

G156006

MLG  

APPROACH SPEED WAS APPROX 78 KTS WITH FULL FLAPS. PRIOR TO TOUCHDOWN, POWER WAS PULLED BACK TO IDLE AND THE PLANE TOUCH DOWNED PARALLEL WITH THE RUNWAY ON THE CENTERLINE. IMMEDIATELY DIRECTIONAL CONTROL WAS LOST WITH THE PLANE PULLED TO THE LT. RT BRAKE AND RUDDER INPUTS FAILED TO KEEP THE PLANE ON THE RUNWAY AND IT ROLLED OUT ONTO THE FIELD AROUND 800 FT HITTING A RUNWAY LIGHT AND MARKING SIGN AT THE TAXI WAY. IT CONTINUED PULLING TO THE LT. MARKINGS ON THE RUNWAY DISPLAYED 2 PARALLEL SKID MARKS FOR THE LT MAIN TIRE ABOUT 4" APART INDICATING POSSIBLY THE LT MAIN WAS FLAT BEFORE TOUCHDOWN. NO HEAVY SKID MARKS FROM EITHER TIRE WAS NOTED. NEITHER TIRE SHOWED SIGNS OF BEING LOCKED. AFTER DISASSEMBLING THE LT WHEEL AND TIRE. THE TUBE HAD A .1250" SLIT THAT FOLLOWED A MFG MOLD LINE. NO INDICATION AS TO WHAT COULD HAVE CAUSED THE PUNCTURE WAS FOUND.

JR2R2011110600565

CNDAIR

 

 

SILL

CORRODED

11/6/2011

CL6002D24

 

 

SH670319961

ZONE 100

SERVICE DOOR SILL FLOOR LANDING ANGLE CORRODED. R & R SERVICE DOOR SILL FLOOR LANDING ANGLE IAW SRM 51-42-06 & SRM 53-21-23 AS ON W/O 1007307 2700-0055 AND W/O 711009503.

JR2R2011110600566

CNDAIR

 

 

FLOOR PANEL

GOUGED

11/6/2011

CL6002D24

 

 

SH67035821

PRESSURE PANEL

PRESSURE FLOOR LWR FACE GOUGED/TOOL MARKS AT FS 693 RBL24 IN RT W/W. C/W PERMANENT REPAIR TO PRESSURE FLOOR LWR FACE AT FS 693 AT RBL 24 IN RT W/W IAW RO CRJ9-53-0868 AS ON WO 1007307-1700-0062 AND WO 711014235.

JR2R2011110600568

CNDAIR

 

 

SEAL

CORRODED

11/6/2011

CL6002D24

 

 

SH670314127

SERVICE DOOR

SERVICE DOOR SEAL LANDING CORRODED AT FASTNER HOLES. R & R SERVICE DOOR SEAL LANDING AND SERVICE DOOR PROTECTOR PLATE IAW SRM 51-42-06 AND 53-21-23 AS ON WO 1007307-8400-0024 AND WO 711009503.

JR2R2011110600569

CNDAIR

 

 

BULKHEAD WEB

CORRODED

11/6/2011

CL6002D24

 

 

 

BS 280

WHILE WORKING FS 280 BEAM FOUND CORRODED ON RT LOWER BULKHEAD WEB. R & R RT STA 280 LOWER BULKHEAD WEB IAW SRM 53-11-10 AS ON WO 1007307-1000-0175 AND WO 711009503.

JR2R2011110600570

CNDAIR

 

 

DIAPHRAGM

DAMAGED

11/6/2011

CL6002D24

 

 

CC670392052

ZONE 100

RT MLG WHEEL BIN SUPPORT WEB UPPER ATTACH FASTENER NUTPLATE BROKEN AND HOLE IS ENLOGATED. R & R DAMAGED BRACKET AND DIAPHRAGM IAW SRM 51-42-21 AS ON WO 1007307-1000-0038 AND WO 711009503.

JR2R2011110600571

CNDAIR

 

 

CROSSBEAM

DAMAGED

11/6/2011

CL6002D24

 

 

CC670341757

ZONE 100

LT 280 BEAM CRACKED. ACCOMPLISHED PERMENT REPAIR ON LT STA 280 CROSSBEAM IAW RO CRJ9-53-0843 AS ON WO 1007307-2700-0051 AND WO 711014235.

JR2R2011110600572

CNDAIR

 

 

CROSSBEAM

DAMAGED

11/6/2011

CL6002D24

 

 

CC670341757

ZONE 100

RT 280 BEAM CRACKED. ACCOMPLISHED PERMENANT REPAIR ON RT STA280 CROSSBEAM IAW RO CRJ9-53-0844 AS ON WO 1007307-1000-0093 AND WO 711014235.

JR2R2011110700574

CNDAIR

 

 

STRINGER

CORRODED

11/7/2011

CL6002D24

 

 

SH670316361

ZONE 100

STRINGER 21R HAS CORROSION BETWEEN FRAMES 280 AND 333 IN THE FWD E & E BAY. R & R STR 21R FROM FS 280 TO 333 IAW SRM 51-42-06 AND 51-42-21 AS ON WO 1007307-1000-0026 AND WO 711009503.

JR2R2011110700573

CNDAIR

 

 

STRINGER

CORRODED

11/7/2011

CL6002D24

 

 

SH670313831

ZONE 100

STRINGER 21R HAS CORROSION BETWEEN FRAMES 364 AND 379 IN THE FWD E & E BAY. R & R STR 21R BETWEEN FS 364 AND 379 IAW SRM 51-42-06 AND 51-42-21 AS ON WO 1007307-1000-0083 AND WO 711009503.

JR2R2011110700575

CNDAIR

 

 

MOUNT

CRACKED

11/7/2011

CL6002D24

 

 

601R3177457

ZONE 800

WHILE WORKING PAX DOOR MOD, FOUND CRACK ON AFT LOWER MOTOR SUPPORT. R & R AFT LOWER MOTOR SUPPORT IAW SRM 51-42-06 AS ON WO 1007307-8000-0034 AND WO 711009503.

JR2R2011114100553

CNDAIR

 

 

STRINGER

CORRODED

11/4/2011

CL6002D24

 

 

SH670313851

ZONE 100

FOUND CORRISION STR 21R FS477.40. REMOVED CORROSION WITH BLENDOUT AT STR 21R FS477.40 IAW RO CRJ9-53-0866 AS ON AAR WO 1007307-1000-0144 AMD WO 711014235.

JR2R2011114100554

CNDAIR

 

 

SKIN

CORRODED

11/4/2011

CL6002D24

 

 

SH6703115111

ZONE 100

FUSLAGE SKIN NEAR PAX DOOR AFT SIDE APROX LOCATION FS 349.00 HAS MULTIPLE SCRAPE MARKS/DAMAGE. REPAIRED FUSELAGE SKIN NEAR PAX DOOR AFT SIDE APPROX LOCATION FS 349.00 IAW RO CRJ9-53-0862 AS ON AAR WO 1007307-2000-0019 AND WO 711014235.

JR2R2011114100555

CNDAIR

 

 

SKIN

CORRODED

11/4/2011

CL6002D24

 

 

SH6703115111

ZONE 100

FUSLAGE SKIN NEAR PAX DOOR AFT SIDE APROX LOCATION FS 310.00 HAS LARGE AREA SCRAPE MARKS/DAMAGE. REPAIRED FUSELAGE SKIN NEAR PAX DOOR AFT SIDE APPROX LOCATION FS 310.00 IAW MESA RO CRJ9-53-0861 AS ON AAR WO 1007307-2200-0020 AND WO 711014235.

JR2R2011114100556

CNDAIR

 

 

STRIKER

CORRODED

11/4/2011

CL6002D24

 

 

SH670324715

ZONE 100

PAX DOOR FWD DOOR SEAL STRIKER ATTACHED TO FS 310.00 OTBD OF MID DOOR FITTING HAS DAMAGE. REPAIRED AND APPLIED TOP COAT TO PAX DOOR SEAL STRIKER IAW RO CRJ9-53-0841 AND WO 711014235.

JR2R2011114100558

CNDAIR

 

 

ATTACH BRACKET

CORRODED

11/4/2011

CL6002D24

 

 

SH670324717

ZONE 100

RIGHT LINE BRACKET BROKEN IN AFT EQUIPMENT BAY. R & R HYD BRACKET IN AFT EQUIPMENT BAY IAW SRM 51-42-21 AS ON WO 1007307-3000-0049 AND WO 711009503.

JR2R2011114100559

CNDAIR

 

 

ATTACH BRACKET

CORRODED

11/4/2011

CL6002D24

 

 

CN6220020207

ZONE 100

RIGHT ENGING UPPER HINGE LINE FAIRING CTR ATTACH BRACKET BROKEN. FRABRICATED AND INSTALLED HINGE LINE FAIRING BRACKET IAW SRM 51-24-21 AND 51-42-06 AS ON WO 1007307-4100-0028 AND WO 711009503.

JR2R2011114100560

CNDAIR

 

 

ATTACH BRACKET

CORRODED

11/4/2011

CL6002D24

 

 

CN6220020205

ZONE 100

RIGHT ENGINE LOWER HINGE LINE FAIRING CTR ATTACH BRACKET BROKEN. FRABRICATED AND INSTALLED HINGE LINE FAIRING BRACKET IAW SRM 51-24-21 AND 51-42-06 AS ON WO 1007307-4000-0019 AND MESA WO 711009503.

JR2R2011114100561

CNDAIR

 

 

MOUNT

CORRODED

11/4/2011

CL6002D24

 

 

BA670370154

ZONE 100

RIGHT ENGINE FRONT MOUNT YOKE NICKED AT LOWER ENG ATTACHMENT. REPAIRED LOWER LUG ON RT ENG FRONT MOUNT YOKE IAW RO CRJ9-71-0093 AS ON WO 1007307-4200-0062 AND WO 711014235.

JR2R2011114100562

CNDAIR

 

 

TRACK

CORRODED

11/4/2011

CL6002D24

 

 

CC670387985

ZONE 100

AFT CARGO DOOR AFT TRACK DAMAGED. R & R CARGO DOOR TRACKS IAW RO CRJ9-53-0858 AS ON WO 1007307-8300-0009 AND WO 711014235.

JR2R201111410557A

CNDAIR

 

 

STRIKER

CORRODED

11/4/2011

CL6002D24

 

 

SH670324717

ZONE 100

PAX DOOR AFT DOOR SEAL STRIKER ATTACHED TO FS 349.00 HAS MULTIPLE AREAS OF DAMAGE ALONG MID SECTION OF SEAL STRIKER. REPAIRED AND APPLIED TOP COAT TO PAX DOOR AFT SEAL STRIKER IAW RO CRJ9-53-0842 AS ON WO 1007307-2000-0025 AND WO 711014235.

JR2R2011114100557

CNDAIR

 

 

ATTACH BRACKET

CORRODED

11/4/2011

CL6002D24

 

 

SH670324717

ZONE 100

RIGHT LINE BRACKET BROKEN IN AFT EQUIPMENT BAY. R & R HYD BRACKET IN AFT EQUIPMENT BAY IAW SRM 51-42-21 AS ON WO 1007307-3000-0049 AND WO 711009503.

JR2R201111060567A

CNDAIR

 

 

PRESSURE PANEL

CORRODED

11/6/2011

CL6002D24

 

 

SH670319861

ZONE 100

PRESSURE PANEL LOWER FACE DAMAGED AT FS 693 RBL24 IN RT MLG WW. REPAIRED PRESSURE PANEL IAW RO CRJ9-53-0868.

JR2R2011110600567

CNDAIR

 

 

FLOOR SUPPORT

CORRODED

11/6/2011

CL6002D24

 

 

 

ZONE 100

SERVICE DOOR FLOOR LANDING CORRODED. R & R SERVICE DOOR FLOOR LANDING IAW SRM 51-42-06.

FOTR2118615249

DOUG

 

 

CUSP WEB

CORRODED

11/15/2011

DC982

 

 

 

ZONE 200

LEFT MAIN DECK CUSP WEB SHOWS CORROSION AT FWD AIR GRILL ATTACH ANGLE FS 598-617. REPAIRED ON FASI WO 21186, NR 15249.

BQVR2011110700010

GULSTM

 

 

ATTACH FITTING

CORRODED

11/7/2011

G1159A

 

 

 

WING  

DURING COMPLIANCE OF CMP CODES 576511 & 576516, WINGLET ATTACH HARDWARE INSPECTION (LT & RT), CORROSION FOUND IN THE WINGLET ATTACH BORES ONCE THE BUSHINGS WERE REMOVED.

ZKFR113188A

HAWBEE

 

 

FAN   

INOPERATIVE

11/15/2011

4000

 

 

4013851030001

A/C HEAT XCHANGR

DURING POSTFLIGHT, FOUND BOTH AFT BAY HEAT EXCHANGER FANS INOP. R & R BOTH HEAT EXCHANGERS FANS. OPS CHECKS GOOD. MX RECOMMENDS OTHER OPERATORS CHECK FOR OPS AS THERE IS NO COCKPIT INDICATION WHEN THESE FANS FAIL AND THEY ARE FOR HEAT PROTECTION FOR THE COMPOSITE REAR PRESSURE BULKHEAD STRUCTURE.

ZKFR201111153188B

HAWBEE

 

 

FAN   

INOPERATIVE

11/15/2011

4000

 

 

4013851030001

A/C HEAT XCHANGR

DURING POSTFLIGHT FOUND BOTH AFT BAY HEAT EXCHANGER FANS INOPERATIVE. R & R BOTH HEAT EXCHANGERS FANS. OPS CHECKED GOOD.

ZKFR201112223218A

HAWBEE

 

 

CHECK VALVE

FAULTY

12/22/2011

4000

 

 

4E42861

POTABLE WATER

POTABLE WATER IN LAV HAS LOW PRESSURE AND PUMP CONTINUOUSLY CYCLES. R & R DRAIN CHECK VALVE. OPS CHECKED GOOD. INSPECTED CHECK VALVE ON BENCH AND FOUND VALVE NOT COMPLETELY CLOSING AND REQUIRING EXCESSIVE PRESSURE TO CLOSE AT ALL.

2011FA0000735

LEAR

 

 

CONTROL VALVE

FAILED

11/9/2011

31A   

 

 

2415010

CABIN PRESSURE

PILOT REPORTED PRESSURIZATION SYSTEM REVERTED TO UNCOMMANDED EMERGENCY PRESSURIZATION MODE.

9JLA2011101300781

LEAR

 

 

SHUTOFF VALVE

FAILED

10/13/2011

45LEAR

 

 

6627602002005

SPOILER SYS

CREW REPORTED AFTER ENGINE START AND SPOILER CHECK RECEIVED A "SPOILER FAIL" CAS MESSAGE, MESSAGE WOULD NOT CLEAR. TROUBLESHOOTING FOUND THAT THE SPOILERON COMPUTER DEFECTIVE. THE COMPUTER WAS REPLACED WITH A REPAIRED COMPUTER, HALF WAY THROUGH THE CONFIGURATION AND CALIBRATION TESTING THE NEW COMPUTER THAT WAS INSTALLED WAS FOUND TO DEFECTIVE. TROUBLESHOOTING FOUND AN ISSUE WITH THE SPOILER HYDRAULIC SHUTOFF VALVE THAT WAS MAKING THE COMPUTER FAIL UNDER A LOAD. THE SHUTOFF VALVE WAS REPLACED WITH REPAIRED UNIT, FUNCTIONAL CHECKS WERE COMPLETED PER THE AMM 27-60-02.

2011FA0000746

MOONEY

CONT

 

ACTUATOR

NOISY

11/15/2011

M20R

IO550G

 

10200013

ZONE 100

DURING ROUTINE INSPECTION OF ACFT LANDING GEAR RETRACTION SYS, THE LANDING GEAR ACTUATOR WAS EXCESSIVELY NOISEY WHEN THE LANDING GEAR WAS RETRACTED AND EXTENDED.AFTER FURTHER EXAMINATION OF THE ACTUATOR IT WAS DISCOVERED THAT THE (INTERNAL) BOLTS THAT SECURE THE RETAINER PLATE FOR THE "NO BACK SPRING" WERE MISSING. A NEW ACTUATOR WAS INSTALLED AND THE PROBLEM WAS CORRECTED.

9JLA201110062011

PILATS

 

 

CONTROL UNIT

DEFECTIVE

9/26/2011

PC1247

 

 

9753731334

FUEL SYSTEM

CREW REPORTED AN INTERMITTENT "FUEL IMBALANCE" CAS MESSAGE. TROUBLESHOOTING INDICATED THAT THE FCMU WAS DEFECTIVE P/N 975.37.31.334. INSTALLED A REPAIRED UNIT PER THE PC12/47E AMM, FUNCTIONAL CHECKS SATISFACTORY. NOTE: THIS HAS BEEN THE 3RD FCMU REPLACED IN THIS AIRCRAFT IN 12 MONTHS, ALL 3 HAVE HAD SIMILAR DISCREPANCIES.

2011FA0000770

PIPER

LYC   

 

CRANKSHAFT

BROKEN

11/3/2011

PA32260

O540E4B5

 

O540E4B5

ENGINE

CRANKSHAFT BROKE IN FLIGHT. CONTINUED TO RUN BUT PILOT REPORTED KNOCKING NOISE IN ENGINE AND LANDED. ENGINE WAS REMOVED FROM AIRCRAFT AND SHIPPED TO SHOP FOR PARTIAL TEAR DOWN. FOUND METAL IN OIL SUMP AND A CRACK IN COUNTERBALANCE SECTION OF CRANKSHAFT.

2011FA0000779

SKRSKY

GARRTT

 

FUEL

INADEQUATE

6/26/2011

S55   

TPE33110UA

 

 

 

WHILE DEMONSTRATING EXTERNAL LOAD CAPABILITY DIRECTLY ABOVE A JUNGLE HELIPAD, THE ENGINE BEGAN TO LOOSE RPM AND THE ACFT LANDED BACK ON THE PAD. THE LANDING WAS CONTROLLED AND TOUCHDOWN WAS CUSHIONED SO AS TO AVOID ANY DAMAGE. POSTFLIGHT INSPECTION REVEALED NO DAMAGE OF ANY KIND OF AIRCRAFT. FOLLOWING EXTENSIVE EFFORTS TO IDENTIFY THE CAUSE, INCLUDING A COMPLETE ENGINE CHANGE, IT IS EVIDENT THAT THE LOCAL FUEL SUPPLY IS SUB-STANDARD. LABORATORY TESTING CONTINUES TO THIS DATE.

3S8R2011041600003

SNIAS

TMECA

 

ANGLE

CORRODED

4/16/2011

SA330J

TURMO4C

 

330A21904621

FUSELAGE

RIGHT INTERNAL UPPER ANGLE BETWEEN FRAME X3855 AND X5295 CORRODED BEYOND LIMITS. TO BE REPLACED WITH NEW.

KY1R201110291001

UROCOP

TMECA

 

STARTER GEN

FAILED

10/29/2010

AS365N3

ARRIEL2C

 

524031

NR 1  

OVERHAULED STARTER GENERATOR INSTALLED IN NR 1 POSITION. UPON GROUND RUN, FOLLOWING SUCCESSFUL GENERATOR VOLTAGE BALANCING PROCEDURE, IT WAS OBSERVED THAT GENERATOR NR 1 INDICATED 90 AMPS AND NR 2 GENERATOR INDICATED 5 AMPS AT 28.5 VDC. FURTHER, STARTER GENERATORS INDICATED 60 AMPS EA AT 28.5 VDC WHEN THE OPPOSITE STARTER GENERATOR WAS OFF LINE. STARTER GENERATOR NR 1 WAS R & R WITH OVERHAULED UNIT. OPS CHECKED SATISFACTORY.