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

352

bald eagle watching over three eggs

NOVEMBER

2007

 


CONTENTS

AIRPLANES

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

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

CESSNA...................................................................................................................................... 2

DIAMOND.................................................................................................................................. 4

GRUMMAN................................................................................................................................ 6

PIPER........................................................................................................................................... 6

POWERPLANTS

LYCOMING................................................................................................................................ 9

ACCESSORIES

SIGMA TEC.............................................................................................................................. 14

AIR NOTES

INTERNET SERVICE DIFFICULTY REPORTING (iSDR) WEB SITE................................... 15

IF YOU WANT TO CONTACT US......................................................................................... 16

AVIATION SERVICE DIFFICULTY REPORTS...................................................................... 16

 


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

AVIATION MAINTENANCE ALERTS

The Aviation Maintenance Alerts provide a common communication channel through which the aviation community can economically interchange service experience, cooperating in the improvement of aeronautical product durability, reliability, and safety. This publication is prepared from information submitted by those who operate and maintain civil aeronautical products. The contents include items that have been reported as significant, but have not been evaluated fully by the time the material went to press. As additional facts such as cause and corrective action are identified, the data will be published in subsequent issues of the Alerts. This procedure gives Alerts’ readers prompt notice of conditions reported via a Malfunction or Defect Report (M or D) or a Service Difficulty Report (SDR). Your comments and suggestions for improvement are always welcome. 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

Beech: 65-B80; Cracked Elevator Bell Crank Support Arm; ATA 2730

A mechanic for an air taxi operator states, “A crack was found on the R/H bell crank support arm assembly (P/N 50-524414) during a mandatory five year inspection (service bulletin 2231, revision 1).”

 

A "two view" hand drawing of the cracked bell crank.

 

(Thanks! Those are two nice hand drawings showing precisely where to inspect—Ed.)

Part Total Time: (unknown).

 


BOEING

Boeing: 737; Cracked Hydraulic Steering Valve Body; ATA 3250

The submitting technician provides sparse descriptions stating, “The body (of this unit) is cracked in the check-valve port, probably caused by overpressure and cyclic stress. (I) recommend redesigning this (component’s) body (housing).” (This steering valve’s manufacturer is listed as Sargent P/N 4129RA9.)

A mechanical drawing showing the relative position of a crack in the hydraulic steering valve unit.

Part Total Time: (unknown).

 

CESSNA

Cessna: 500; Corroded Hydraulic Brake Lines; ATA 3240

A repair station submission observes a corrosion trail that leads to overt brake failure. The writer says, “(We were...) investigating a soft-brake condition when Skydrol was noted leaking from around the belly beacon—its lens was full of fluid. (We) removed the interior and the center aisle floor panels. Hydraulic fluid was noted dripping from the rigid brake line to the right brake (P/N 90E5517010-64 at fuselage station FS248.1). The Cessna installed Keith Air Conditioning cold air duct is Ty-wrapped to the brake fluid lines. The belly beacon is directly below the corrosion and the Skydrol leakage. This aircraft is not equipped with belly drains. Condensation lies in the belly of the aircraft and the beacon creates heat—(in turn generating) humidity, causing corrosion on component parts in the under-floor area.

“Cessna probably should engineer a drainage system of some other method of eliminating the humidity from the under-floor area.”


An aircraft "outline" view showing the relative position of fluid collection.


Black and white photo of brake line corrosion.

 

A close-up of previous photo showing brake line corrosion.

Part Total Time: 8,348.8 hours.

 

DIAMOND

Diamond: DA42; Bent Nose Gear Torque Link Bolts; ATA 3222

A technician for a flight training school submitted a worn and bent nose landing gear torque link attach bolt (P/N LN9037-M5 x 22). He says, “...The nose landing gear torque links were removed to facilitate other maintenance. The four bolts used to secure the torque links were found to be bent and joggled; presumably, from sheer loads.”

(There are no additional records of this defect in the SDRs data base. Given this relatively new, light twin is used in a training environment, one might reasonably be concerned these bolts are of insufficient strength and/or size for their loads. Similar aircraft should be inspected for bolt deformation—and the torque links for corresponding damage. A cohort inspector at a different training school relates his company has also purchased multiple, new models of this aircraft. He is well positioned to observe new manifestations of this specific defect and promises to keep the Alerts posted as their student-flown aircraft are...'broken in.’—Ed.)


A mechanical drawing of the nose gear assembly.


(The attached digital photo was taken by this editor of the single bolt physically accompanying the defect report.)

A color close-up of the bent bolt.

Part Total Time: 616.0 hours.

 

GRUMMAN

Grumman: G164A; Failed Main Gear Leg (Spring Style); ATA 3213

A technician describes the following aircraft incident. “The R/H main gear leg (spring gear style; P/N A1530-34) failed at the upper end, just outboard of the clamp bar. This is an area of major flex of the gear leg, and it is (also) the thickest part. In twenty-five years of working on this type of aircraft, I have never seen a failure of the main gear leg(s). This set of gear was installed on the aircraft in April of 2002—it was magna-fluxed, sandblasted, and painted prior to installation. The gear legs were a used set at that time and the total time on the pair is unknown. The time since magna-flux and installation is 1,687.1 hours. This is not a common failure and I do not believe there is a need for an Airworthiness Directive or other such action.”

Part Total Time: (unknown).

 

PIPER

Piper: PA28-161; Corroded Main Gear Attach Bolt; ATA 3211

A mechanic states, “While washing the aircraft, the scrub brush knocked off the nut...for one of the AN4-11A bolts securing the right main landing gear assembly (P/N 35644-05) to the right wing. The bolt was corroded all the way across its cross section.

(I) suggest: 1) periodically check torque on these bolts to ensure the bolt is not corroded through like this one (see pictures); and 2) replace these bolts periodically to preclude corrosion failure.”


Pictures showing bolt location at bottom of wing, different view of the first picture, and picture of corroded bolt head inadvertently knocked off the airplane's lower wing surface.

Part Total Time: 8,236.1 hours.

 

Piper: PA32RT; Engine Mount Corrosion; ATA 7120

(The following discrepancy and attendant safety discussion is provided by FAA Aerospace Engineer Barry Ballenger from the office of Continued Operational Safety Branch. Contact information is found at the article’s end.)

“The following defect description is an example of what can result when an inadequate inspection is performed during an annual or 100-hour inspection. The aircraft (pictured below) is a 1978 Piper PA-32RT-300T Lance with a total time around 3,600 hours. It was brought to a maintenance facility for an oil change and an engine discrepancy: ‘Failure to develop take-off RPM.’ A recent annual inspection had been accomplished.

“While accessing the engine compartment to perform maintenance, corrosion damage to the engine mount was noted. Further investigation revealed extensive corrosion damage to both the engine mount and the galvanized metal firewall. The damage was hidden by the upholstery covering on the baggage side of the fire wall and the insulation blanket on the engine side. Additionally, this portion of the firewall is difficult to inspect due to the turbocharger installation.


“The corrosion damage was due to leaking turbocharger and exhaust system components. This aircraft’s engine installation is very compact with little isolation distance between the turbo/exhaust systems and the firewall/engine mount structure. Close proximity allows the heat generated by the turbo and exhaust systems to impact the firewall. At significant expense and downtime, this aircraft was repaired by replacing several engine mount tubes, the firewall, and associated engine compartment ducting.

“This maintenance facility recommends insulation blankets and upholstery (that may cover damaged firewalls) should be removed during annual or 100-hour inspections. All turbo and exhaust systems should be closely inspected for signs of leakage and heat damage.”

 

Picture of the damaged engine mount/firewall structure.


Another view of the damaged engine mount/firewall structure.

(For further information contact Aerospace Engineer Mr. Barry Ballenger, 901 Locust, Room 301, Kansas City, MO., 64106-2641; 816-329-4152; barry.ballenger@faa.gov.)

Part Total Time: 3,600.0 hours.

 

Piper: PA46; Cracked Fuel Pressure Tube; ATA 7310

A repair station Airframe and Powerplant mechanic says, “The pilot described a loss of power over Ensenada (CA). He continued the flight to Gillespie (TX). The engine quit upon landing—the fire department responded, but no action was required except for absorbent to collect the fuel dripping from the belly. (The cause was found to be) a cracked fuel tube at the fuel control unit (Pratt & Whitney P/N 3033981). The reason for the crack is unknown. Fuel streamed the full length of the fuselage....” (The crack was found on the end B-nut taper at the fuel control.)

Part Total Time: (unknown).

 

POWERPLANTS

LYCOMING

Lycoming: TIO-540-S1AD; Cracked Turbo-Oil Line Adapter; ATA 8120

An Airframe and Powerplant mechanic provides the following description and pictures for this turbo-charger’s oil-inlet adapter: P/N LW-14465. “This part is bolted to the turbocharger assembly between the hot and cold sections. The high pressure oil line connects to this part via a fitting in the top of the part.


“After an annual inspection, the engine was run-up and systems checked. An oil seep was noted in the turbocharger area. The high pressure oil line and fitting (P/N LW 14465) was removed and cleaned: the crack was noted. This part was replaced with a new (unit).

“After researching the aircraft records, it was noted the exhaust system—including the turbocharger waste gate and control rod end—had not been overhauled with the engine core as required by Lycoming. The turbocharger itself was replaced with a new unit at the time of overhaul. It is unknown if P/N LW-144654 was replaced at that time.

“This part is critical to safety of flight (in my opinion) for the following reason. Another aircraft I’m familiar with, a Cessna 421, had this fitting come apart in flight. It caused an oil-fed, in-flight fire. Examination (after an emergency landing) revealed the high pressure oil line was still connected to the fitting and the threads in the fitting and the adapter were (also) still intact—not stripped. A crack was discovered in that part as well. It is assumed this crack swelled when heated to operating temperatures and the parts separated.

“This part is manufactured from (apparently)...cast aluminum. Maybe a stronger material should be considered.” (Part time since overhaul listed as 522.38 hours.)


Parts catalog drawing of turbocharger assembly.


Lycoming parts list.


(This next picture deserves special note. Russell is holding his camera with one hand, the part in the other...while trying to focus through a desk mounted magnifying glass! The crack is just discernable. What fails in execution was nonetheless a noble effort. A surreptitious photo of him taking this shot would probably have made money....)

Photo 1 of cracked part.

(Eventually...we arrive at a visible crack—sans the magnifying glass.)


Photo 2 of cracked part.

(Thanks for the effort, Russell. Any fire is too much fire. I’ll target this item for engineering consideration, as possible--Ed.)

Part Total Time: (unknown).

 

ACCESSORIES

SIGMA TEC

Sigma Tec: Vacuum Pumps; 1U478; Sheared Drive Shafts; ATA 3710

An FAA Principal Maintenance Inspector submits five defect reports for failed vacuum pumps occurring on an aviation training school’s aircraft—the Grob 120A. He states, “The flight school is the only operator of the German build Grob...in the United States. These reports indicate to me an unacceptable level of early failures (average 84.2 hours time since new) of the dry air pump, part number 1U478-003. They are mounted to Lycoming AEIO-540D4D5 powerplants. Sheared shafts appear to be the most common cause of the pump failures, but what needs to be determined is why the shafts are breaking. This pump provides vacuum to flight instrument gyros (for their operation)....”


(A search of the SDRS data base under the JASC code 3710 generates approximately 258 returns for reported vacuum pump failures since 1993. Sixty of these—or 23 percent are confirmed sheared shafts. Further investigation into this matter is awaiting feedback from the submitter.)

Part Total Times: 84.2 hours (average of the reported 5 vacuum pumps).

 

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) data base 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/.

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


The SDRS and iSDR web site point of contact is:

Tom Marcotte
Service Difficulty Reporting System, Program Manager
Aviation Data Systems Branch, AFS-620
P.O. Box 25082
Oklahoma City, OK 73125
Telephone: (405) 954-6500
SDRS Program Manager e-mail address: 9‑AMC‑SDR‑ProgMgr@faa.gov

 

IF YOU WANT TO CONTACT US

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

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

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

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

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

 

AVIATION SERVICE DIFFICULTY REPORTS

The following are abbreviated reports processed for the previous month, which have been entered into the FAA Service Difficulty Reporting (SDR) System data base. 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

2007FA0000862

 

ALLSN

RROYCE

RETAINING RING

FRACTURED

8/15/2007

 

250C20B

 

672332390

COMPRESSOR

OPERATOR REPORTED ENGINE CHIP LIGHTS AND A PRECAUTIONARY LANDING WAS MADE. INSPECTION OF ENGINE CHIP DETECTORS REVEALED ONE SMALL PIECE OF THE FAILED RETAINING RING HAD CAUSED THE LIGHT. THE COMPRESSOR WAS REMOVED FROM THE ENGINE AND FURTHER INVESTIGATION REVEALED THE RETAINING RING HAD FRACTURED INTO 5 PIECES. 3 PIECES WERE CONTAINED IN THE RETAINING RING GROOVE OF THE IMPELLER, 1 PIECE WAS IN THE GEARBOX SUMP AREA AND THE 5TH PIECE WAS RECOVERED FROM THE CHIP DETECTOR. THE FAILED RETAINING RING SCORED THE SPUR ADAPTER GEAR ADJACENT TO THE RETAINING RING GROOVE IN THE IMPELLER. NO FURTHER DAMAGE WAS NOTED. A NEW SPUR ADAPTER GEAR AND RETAINING RING WERE INSTALLED AND THE COMPRESSOR RETURNED TO SERVICE. CAUSE OF THE SNAP RING FRACTURE IS UNKNOWN. (K)

2007FA0000881

 

ALLSN

ALLSN

PINION GEAR

FRACTURED

9/18/2007

 

250C47B

 

23066678

GEARBOX

RECEIVED THE ENGINE FOR REPAIR DUE TO VIBRATIONS, AND METAL IN OIL. UPON DISASSEMBLY OF THE GEARBOX FOUND THE ROLLER RETAINER OF THE NR 3 BEARING FRACTURED IN (4) PLACES. ALSO FOUND THAT THE NR 1 TURBINE WHEEL BLADE TIPS HAD BEEN RUBBING THE BLADE TRACK WHICH CAUSED THE VIBRATION. TECH SUSPECTS THE FRACTURED RETAINER MAY HAVE BEEN A RESULT OF THE VIBRATION. (K)

2007FA0000842

 

CONT

 

ROCKER SHAFT

LOOSE

9/7/2007

 

O200*

 

654375

CYLINDER

IAW OWNERS REQUEST, REMOVED ALL (4) ROCKER COVERS TO INSPECT THE ROCKER SHAFT AND SET SCREWS. AFTER REMOVING THE ROCKER COVERS. FOUND ALL(4) SET SCREWS LOOSE AND ALL (4) SHAFTS MOVED TOWARD THE INTAKE SIDE OF THE BOSSES. NONE HAVE CUT THE ROCKER COVERS YET, IN ANOTHER 20 HOURS OR SO THEY WOULD. NOTE: THE NEW ENGINE HAVE A FLAT CUT INTO THE ROCKER SHAFT, AND A SET SCREW IN THE CENTER BOSS, TO RETAIN THE SHAFT. ALSO, THE SHAFT IS SHARP ON THE END, UNLIKE THE OLD STYLE, AND HAVE A CUT MARK ACROSS THE END OF THE SHAFT FOR USE IN ALINING THE FLAT FOR THE SET SCREW. THE SET SCREW IS A MS51963-64, AND USES NO LOCKTITE, OR MECHANICAL TYPE LOCK. THE FLAT IN THE ROCKER SHAFT IS NOT DEEP ENOUGH TO PROVIDE ADEQUATE L

2007FA0000878

 

GARRTT

 

TRANSPONDER

FAILED

6/29/2007

 

TFE731*

 

TDR906221270001

TAILCONE

ON 6/27/2007 WHILE ENROUTE, THE PRIMARY TRANSPONDER FAILED WHILE THE AIRCRAFT WAS OPERATING IN AIRSPACE. THE CREW WAS ABLE TO SWITCH TO THE SECONDARY TRANSPONDER AND CONTINUE THEIR FLIGHT TO LOCK WITHOUT FURTHER INCIDENT. UPON ARRIVAL, THE PRIMARY TRANSPONDER WAS CONFIRMED FAILED AND WAS REPLACED WITH A SERVICEABLE TRANSPONDER. THE SYSTEM WAS TESTED IAW FAR PART 43, APPENDIX F AND APPENDIX E, SUB PARA C, AND ICA NR 30A05002, REVISION C. THE SYSTEM WAS FOUND TO BE OPERATING NORMALLY AND THE AIRCRAFT WAS RETURNED TO SERVICE. (K)

CA070905004

AEROSP

PWA  

 

TRANSMITTER

INOPERATIVE

8/28/2007

ATR42300

PW120

 

810710000

OIL PRESSURE

(CAN) WHILE INBOUND, THE CREW OBSERVED LOW OIL PRESSURE ON THE NR 1 ENGINE WITH A LOCAL ALERT LIGHT INDICATION THE CREW SHUT THE ENGINE DOWN AND LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE VERIFIED THAT THERE WAS NO OIL LOSS AND REPLACED THE NR 1 OIL PRESSURE TRANSMITTER. THE AIRCRAFT WAS GROUND RUN SATISFACTORILY AND RETURNED TO SERVICE. FULL P/N IS 8107-100-00-10 (TC NR 20070905004)

CA071003019

AEROSP

PWA  

 

FUEL CONTROL

FAULTY

8/13/2007

ATR72

PW127

 

32448716

ENGINE

(CAN) IN FLIGHT, ENGINE POWER REDUCED UNCOMMANDED AND THE ENGINE WAS SHUTDOWN. AN IN-FLIGHT RELIGHT ATTEMPT WAS UNSUCCESSFUL. SUBEQUENT INSPECTION REVEALED A FAULTY FUEL CONTROL UNIT. (TC NR 20071003019)

2007FA0000868

AGUSTA

ALLSN

 

BLADE

CRACKED

9/11/2007

A109

250C20B

 

10901030115

MAIN ROTOR

EXCESSIVE 1 PER REVOLUTION VIBRATION NOTICED IN MAIN ROTOR SYSTEM. THE AIRCRAFT WAS LANDED WITHOUT INCIDENT. INVESTIGATION REVEALED CORD WISE CRACKS IN UPPER AND LOWER SKINS AT STATION 1979 EXTENDING FROM THE TRAILING EDGE TO THE AFT SIDE OF THE SPAR. THE HONEYCOMB CORE OF THE BLADE IS ALSO SEPARATED AND DAYLIGHT CAN BE SEEN THROUGH CRACKS IN THE BLADE. THE CRACKS IN BOTH SKINS THEN EXTEND SPAN-WISE ALONG THE SPAR FROM STA 1925 TO STA 2075. THESE CRACKS ARE EXACTLY AS DESCRIBED IN TECH BULLETIN 109-50, PART 1 REQUIRES DAILY VISUAL INSPECTIONS OF BLADES WITH GREATER THAN 500 HOURS OF OPERATION BETWEEN STATIONS 1550 AND 3100. BT 109-50, PART II REQUIRES INSPECTION OF THIS AREA WITH A 3X MAGNIFYING GLASS EVERY 25 FLIGHT HOURS. NO DISCREPANCIES WERE NOTED DURING THESE INSPECTIONS PRIOR TO THE REPORT OF UNUSUAL VIBRATION. (K)

CA071003016

AIRTRC

PWA  

 

BLADES

FRACTURED

6/30/2007

AT502A

PT6A65B

 

FRACTURE

COMPRESSOR

(CAN) ON TAKEOFF, THE ENGINE EXPERIENCED A POWER LOSS ACCOMPANIED BY FLAMES EXITING THE EXHAUST. THE AIRCRAFT WAS DAMAGED, RESULTING IN A FORCED LANDING. SUBSEQUENT INSPECTION REVEALED FRACTURED COMPRESSOR BLADES. MFG WILL MONITOR THE INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071003016)

2007FA0000891

AMCNLG

CONT

 

SETSCREW

MISMANUFACTURED

9/14/2007

AL3  

O200*

 

O200D

ROCKER ARM BOSS

CHECKING ROCKER ARM SHAFT SET SCREWS AND TO ASSURE INTAKE AND EXHAUST ROCKER ARMS NOT SWITCHED IAW INFORMATION TO OWNERS FORM INTERNET OWNERS AIRCRAFT FORUM. CYLINDER NR 1, SN AC06HB070, SET SCREW AND ROCKER ARMS, OK. CYLINDER NR 2, SN AC06FA543, SET SCREW LOOSE ENOUGH TO ALLOW SHAFT TO MOVE, ROCKER ARMS, OK. CYLINDER NR 3, SN AC06HA911, SET SCREW OK, INTAKE AND EXHAUST ROCKER ARMS SWITCHED. CYLINDER NR 4, SN AC06HA935, SET SCREW AND ROCKER ARMS, OK. (K)

2007FA0000870

AMD  

GARRTT

 

BLADE

BROKEN

9/12/2007

FALCON50MYST

TFE73140

 

30606266

3RD STG ROTOR

BROKEN TURBINE BLADE. ENGINE SENT TO MFG FOR INVESTIGATION. (K)

2007FA0000863

AVIAT

LYC  

 

RUDDER PEDAL

FAILED

8/14/2007

A1B  

O360*

 

30730501

COCKPIT

RUDDER PEDAL OPERATION CAN LEAD TO NO BRAKE OPERATION AT FULL TRAVEL OF RUDDER. SENDING IN THIS FIELD APPROVAL REQUEST FOR A VERNIER MIXTURE CONTROL. BELIEVE THAT THE LT RUDDER PEDAL WHEN PRESSED FULLY ALLOWS YOU TO DEPRESS THE RT BRAKE OVER CENTER THUS GIVING YOU NO BRAKE AND DILEMMA WHEN APPLYING THE BRAKE. THE SAME THING HAPPENS IN REVERSE WHEN THE RT PEDAL IS DEPRESSED FULLY AND THEN THE LT BRAKE WILL GO OVER CENTER AND BECOME USELESS. THIS AC, AS AN EXAMPLE WAS GROUND LOOPED AT 68 HRS TT. IF THIS CONDITION CAN BE ACHIEVED EASILY ON THE GROUND THEN IT COULD HAPPEN ON LANDING, IN A CROSSWIND OR TURN. FURTHER MORE THE BRAKE PEDAL IN THE OVER CENTER CONDITION WILL BE POINTED FORWARD AND AT A 90 DEGREE ANGLE TO THE RUDDER PEDAL AND WILL RESTRICT THE TRAVEL OF THE RUDDER PEDAL PREVENTING IT FROM GOING FULL TRAVEL OF THE RUDDER IN THE DIRECTION OF WHICH (LT OR RT) BRAKE PEDAL HAS GONE OVER CENTER. IN A CROSSWIND CONDITION FULL CONTROL IS A NECESSITY.

2007FA0000858

BBAVIA

CONT

 

SPAR

DETERIORATED

4/27/2007

11CC

C85*

 

1369 

RT WNG

REPORT IAW AD 200-25-02R1 PARAGRAPH D (4) LOOSE, MISSING AND RUSTED NAILS IN RIBS ALLOWING RUSTY MOISTURE INTO SPAR, FRETTING ON TOP CAP GREATER THAN .0625 INCH ON LOOSE RIBS, CRACKS AT AILERON BELLCRANK BRACKET, CAUSED FROM OVER TORQUING OF BOLTS, PREVIOUS WING TIP DAMAGE, LOGS MISSING HISTORY, SPARS REPLACED. (K)

2007FA0000859

BBAVIA

CONT

 

SPAR

CRACKED

7/26/2007

7FC  

C90*

 

5146R

RT WING

AC WAS BEING MODIFIED TO INCLUDE THE INSTALLATION OF WING SPAR INSPECTION HOLE KIT IAW STC NR SA005278E. A PORTION OF THE WING LEADING EDGE SKIN WAS REMOVED AND THE WING SPAR WAS VISUALLY INSPECTED AS SPECIFIED IN THE INSTALLATION INSTRUCTIONS SUPPLIED WITH THE STC. DURING THIS VISUAL INSPECTION, A CRACK WAS OBSERVED ON THE TOP SURFACE OF THE RT WING FRONT SPAR. THE CRACK ORIGINATES AT THE IB AND OF THE AFT PLYWOOD REINFORCEMENT PLATE. REINFORCEMENT PLATE IS LOCATED ON THE AFT SIDE OF THE FRONT SPAR, UNDER THE LT STRUT ATTACHMENT FITTING. THE CRACK PROGRESSES OB ALONG THE TOP SURFACE OF THE SPAR AT A SLIGHT FORWARD ANGLE (CRACK ANGLE TOWARD THE FORWARD PLYWOOD REINFORCEMENT PLATE). THE SURFACE OF THE CRACK IS ALONG THE TOP OF THE SPAR, NOT THROUGH BOLT HOLES OR NAIL HOLES. THE AIRCRAFT MAINTENANCE RECORDS INDICATES THAT A WING SPAR INSPECTION HAD PREVIOUSLY BEEN COMPLETED IAW AD 2000-25-02. THE AC SHOWED NO EVIDENCE OF WING DAMAGE SUBSEQUENT TO SAID INSPECTION.

N843E12007

BEECH

PWA  

 

HED  

FAULTED

8/1/2007

1900D

PT6A6

 

9036102331

BATTERY  

CREW LEFT STATION. TWENTY MINUTES IN FLIGHT "BATT TIE OPEN" ANNUNCIATOR ILLUMINATED. CREW RETURNED TO STATION WITHOUT ISSUE. REMOVED AND REPLACED BATTERY HED. OPS CHECK GOOD.

CA071003024

BEECH

PWA  

 

OIL SYSTEM

FLUCTUATES

8/24/2007

1900D

PT6A67D

 

 

ENGINE

(CAN) ON APPROACH, ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE AND THE ENGINE WAS SHUTDOWN IN FLIGHT. MFG WILL MONITOR INVESTIGATION OF THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071003024)

CA071003026

BEECH

PWA  

 

COUPLING

FRACTURED

8/26/2007

200BEECH

PT642A

 

 

THROTTLE

(CAN) ON INITIATING DESCENT, THE ENGINE WAS FOUND NOT TO RESPOND TO THROTTLE INPUT. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A FRACTURED FUEL CONTROL (PLASTIC) DRIVE COUPLING. (TC NR 20071003026)

2007FA0000850

BEECH

PWA  

 

EXHAUST DUCT

CRACKED

9/27/2007

200BEECH

PT6A41

 

02R3022406

RT ENGINE

WHILE PERFORMING SCHEDULED MAINTENANCE, REMOVED RT EXHAUST STACKS TO FACILITATE INSPECTING THE EXHAUST DUCT. FOUND A 1 INCH CRACK IN THE SKI SLOPE. SB 3380 WAS COMPLIED WITH 711 HOURS EARLIER. POWER SECTION WAS PULLED AND SENT OFF FOR REPAIR.

2007FA0000826

BEECH

 

 

CONTROL CABLE

FRAYED

8/8/2007

300BEECH

 

 

NAS302261510

ELEVATOR TRIM

DURING SCHEDULED INSPECTION OF THE AC, THE MECHANIC FOUND THE LT ELEVATOR PITCH TRIM CONTROL CABLE CHAFING ON THE ELEVATOR CABLE PASS THROUGH HOLE LOCATED IN SKIN PN 101-620000-3. THE ELEVATOR CABLE PASS THROUGH HOLE REQUIRED TRIMMING TO ALLOW PROPER CLEARANCE. ADJUSTMENTS TO PASS THROUGH HOLE ACCOMPLISHED IAW IAW MFG. (K)

2007FA0000895

BEECH

 

 

UNKNOWN

UNKNOWN

10/1/2007

400A

 

 

 

 

AC EXPERIENCED A FLAP ASYMMETRIC LIGHT IN FLIGHT. THE CREW DID NOT TRY TO PUT THE FLAPS DOWN AND DIVERTED FOR A NO FLAP LANDING. CRITICAL CARE MAINTENANCE DROVE DOWN TO REPAIR THE AIRCRAFT. MAINTENANCE COULD NOT DUPLICATE THE PROBLEM AFTER SEVERAL ATTEMPTS. MAINTENANCE INSPECTED AND CLEANED ALL CONNECTORS, INSPECTED HYDRAULIC SYSTEMS, AND FLAP RIGGING AND CABLES. MAINTENANCE C/W ALL OPERATIONAL CHECK IAW THE MM. THE PROBLEM WAS NEVER DUPLICATED.

2007FA0000909

BEECH

PWA  

 

DOOR

CRACKED

9/11/2007

400A

JT15D5

 

45A3161521

NLG 

FOUND DURING INSPECTION. NOSE GEAR FOLLOW UP DOOR PN 45A31615-21 ON BRACKETS, PN 45A31613-9 AND 45A31613-7 AT ATTACHING RIVET HAS CRACKS GOING FORWARD TO AFT THROUGH THE FIRST RIVET ALONG THE RIVET ROW. RELATIVE WIND PUSHING AFT ON THE DOOR WHILE GEAR IS EXTENDED FOR TAKEOFF AND LANDING AND VIBRATION. USING THICKER MATERIAL DURING MFG AND OR ADDING A DOUBLER. (K)

2007FA0000910

BEECH

PWA  

 

DOOR

CRACKED

9/20/2007

400A

JT15D5

 

45A3161521

NLG 

FOUND DURING INSPECTION. NOSE GEAR FOLLOW UP DOOR, P/N 45A31615-21 ON BRACKETS PN 45A31613-9, 45A31613-7 AND 45A31616-3 AT ATTACHING RIVET HAS CRACKS GOING FORWARD TO AFT THOUGH THE FIRST RIVET ALONG THE RIVET ROW. RELATIVE WIND PUSHING AFT ON THE DOOR WHILE GEAR IS EXTENDED FOR TAKEOFF AND LANDING AND VIBRATION. USING THICKER MATERIAL DURING MFG AND OR ADDING A DOUBLER. (K)

2007FA0000939

BEECH

PWA  

 

LAMP

INOPERATIVE

10/21/2007

400A

JT15D5

 

 

MLG INDICATOR

PILOT HAD NO GREEN DOWN AND LOCKED INDICATION FOR THE RT GEAR WHEN LANDING. PILOT CONFIRMED WITH THE TOWER THE GEAR WAS DOWN, ALSO THE PILOT CONFIRMED THAT THE LIGHT WOULD NOT ILLUMINATE WHEN TESTED. AFTER LANDING MAINTENANCE CHECKED OUT AIRCRAFT AND REPLACED LAMP IN GEAR INDICATION. SYSTEM OPERATIONAL CHECK GOOD.

CA071003022

BEECH

PWA  

 

TURBINE BLADES

DAMAGED

8/19/2007

400A

JT15D5

 

 

ENGINE

(CAN) THE ENGINE FLAMED OUT IN FLIGHT AND AN ATTEMPTED RELIGHT WAS UNSUCCESSFUL. SUBSEQUENT INSPECTION REVEALED DAMAGED POWER TURBINE BLADES. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071003022)

2007FA0000830

BEECH

PWA  

 

COVER

CORRODED

9/12/2007

400A

JT15D5

 

 

SPOILER MIXER

WHILE PERFORMING A SCHEDULED A-D INSPECTION FOUND SPOILER MIXER ASSEMBLY BOX COVER NOT SEALED. REMOVED COVER AND FOUND CORROSION ON ACTUATOR AND MIXER ASSEMBLY. RECOMMEND THAT THE SPOILER MIXER AREA BE INSPECTED THOROUGHLY THE BOX COVER REMOVED. INSTALLED THE BOX COVER WITH THE APPROPRIATE SEALANT. (K)

2007FA0000831

BEECH

PWA  

 

AIR DUCT

CRACKED

9/12/2007

400A

JT15D5

 

45A63517073

BLEED AIR

WHILE PERFORMING A SCHEDULED A-D INSPECTION FOUND THE LEFT AFT FUSELAGE BLEED AIR LINE BELLOWS BLOWN APART PN 45A63517-073 AND THE RT AFT FUSELAGE BLEED AIR LINE BELLOWS BRAIDING FRAYING PN 45A63517-075. WHEN THE LT BLEED AIR LINE BLEW APART IT CRACKED A FUSELAGE BULKHEAD AT UPPER FRAME STATION 329.92 AND BP 29.92L. WOULD RECOMMEND THAT DETAILED INSPECTIONS OF THESE BLEED AIR LINES BE PERFORMED AT SCHEDULED INTERVALS AND THE UPPER FRAME STATION IN THE AREA AROUND THE BLEED AIR LINES BE CAREFULLY INSPECTED FOR DAMAGE. IT IS SUSPECTED THAT BOTH THE BLEED AIR LINES FAILED DUE TO FATIGUE OR TIME IN SERVICE. (K)

2007FA0000832

BEECH

PWA  

 

WINDOW

CRACKED

9/12/2007

400A

JT15D5

 

45AS3101012

COPILOT

WHILE PERFORMING A SCHEDULED A-D INSPECTION FOUND COPILOT COCKPIT SIDE WINDOW CRACKED USING THE PRISM INSPECTION METHOD. THE D-INSPECTION REQUIRES THAT BOTH WINDSHIELDS BE INSPECTED BY REMOVING THE WINDSHIELD RETAINERS OR USING OPTICAL PRISM INSPECTION METHOD. THERE IS NO STATEMENT IN THE AC MM OR IN THE A-D INSPECTION CHECKLIST THAT REQURIES YOU TO INSPECT THE COCKPIT SIDE WINDOWS IN THE SAME MANNER AS THE WINDSHIELDS. ALL OF THE WINDOWS IN THE COCKPIT AREA ARE INSTALLED OR FASTENED IN THE SAME MANNER AS THE WINDSHIELDS. IT IS SUSPECTED THAT THE COPILOT SIDE WINDOW CRACKED FROM FATIGUE, OR TOTAL TIME INSTALLED. THE WINDOW WAS MFG MAY OF 1997. WOULD RECOMMEND THAT INSPECTION OF ALL COCKPIT WINDOWS WITH A

2007FA0000833

BEECH

PWA  

 

STRUCTURE

DAMAGED

9/12/2007

400A

JT15D5

 

 

HORIZONTAL STAB

WHILE PERFORMING A SCHEDULED A-D INSPECTION FOUND 6 SHEARED RIVETS AND 2 LOOSE RIVETS IN THE FORWARD RIVET LINE OF THE ATTACHMENT PIVOT FITTING PN 45A21183-11 ON THE BOTTOM OF THE HORIZONTAL STABILIZER. IT IS SUSPECTED THAT THE MISSING RIVETS FAILED FROM FATIGUE. RECOMMEND INSPECTING AREA THOROUGHLY AT EACH INSPECTION, CONTACTING MFG FOR REPAIR OPTIONS. THIS IS SECOND AC THAT THE SAME DISCREPANCY HAS BEEN FOUND. (K)

2007FA0000834

BEECH

PWA  

 

STRUCTURE

DAMAGED

9/12/2007

400A

JT15D5

 

 

HORIZONTAL STAB

WHILE PERFORMING A SCHEDULED A-D INSPECTION FOUND 8 SHEARED RIVETS IN THE FORWARD RIVET LINE OF THE ATTACHMENT PIVOT FITTING PN 45A21183-11 ON THE BOTTOM OF THE HORIZONTAL STABILIZER. IT IS SUSPECTED THAT THE MISSING RIVETS FAILED FROM FATIGUE. RECOMMEND INSPECTING AREA THOROUGHLY AT EACH INSPECTION. (K)

2007FA0000914

BEECH

PWA  

 

FITTING

LOOSE

10/3/2007

400A

JT15D5

 

 

HORIZONTAL STAB

WHILE PERFORMING AN A-D INSPECTION FOUND 8 LOOSE RIVETS IN THE FORWARD RIVET LINE OF THE ATTACHMENT PIVOT FITTING PN 45A21183-11 ON THE BOTTOM OF THE HORIZONTAL STABILIZER. IT IS SUSPECTED THAT THE LOOSE RIVETS WERE CAUSED BY FATIGUE AND AGE. RECOMMEND INSPECTING AREA THOROUGHLY AT EACH INSPECTION. RECOMMEND CONTACTING MFG FOR REPAIR OPTIONS. THIS IS THE 3RD AIRCRAFT IN A ROW THAT THESE SAME RIVETS HAVE BEEN LOOSE OR MISSING. (K)

2007FA0000867

BEECH

 

 

SCREW

UNSAFETIED

9/11/2007

58  

 

 

AN520C8R6

PROPELLER

HAVE SEEN THIS ATTACHMENT ARRANGEMENT ON MANY AC. FOUND NON SAFETIED SCREWS ATTACHING PROPELLER DEICE BRUSH ASSY TO MOUNTING. REMOVED NON SAFETIED SCREWS WITHOUT LOCKING DEVICES WITH MS35265-44 SCREW THAT CAN BE LOCKED WITH SAFETY WIRE. (K)

2007FA0000886

BEECH

LYC  

 

ENGINE

MAKING METAL

8/17/2007

A60  

TIO541E1C4

 

 

 

DURING ROUTINE OIL CHANGE, METAL SHAVINGS WERE FOUND IN OIL FILTER AND SCREEN. SHAVINGS WERE MAGNETIC. THESE ENGINES DO HAVE WEAR ISSUES ON CAM AND LIFTERS. AFTER REMOVING OIL PAN, FOUND CAM BAD AND LIFTER WEAR. OIL ANALYSIS DIDN`T PICK UP LARGER MICRON IN OIL. RECOMMEND INSPECTION OF CAM AND LIFTER BEFORE 1000 HOUR. REMOVED OIL PAN ON RT ENGINES AND FOUND BEAD WEAR AS WELL. NO METAL IN FILTER. (K)

2007FA0000853

BEECH

PWA  

 

FLANGE

CRACKED

9/20/2007

E90  

PT6A135

 

310103901

EXHAUST

(2) NEW ENGINES WERE INSTALLED IAW MFG MODIFICATIONS, WITH 938.0 HRS SINCE NEW. AIRCRAFT WAS IN FOR A PHASE INSPECTION AND FOUND 3 OUT OF L1 EXHAUST FLANGES ON THE ENGINE CRACKED. ACCORDING TO THE MFG PARTS MANUAL, EXHAUST STIFFENERS ARE NOT USED ON THIS SN AC AND ARE NOT USED WITH MFG INSTALLATION INSTRUCTIONS. (K)

CA070910007

BELL  

ALLSN

 

FUEL CONTROL

UNSERVICEABLE

9/10/2007

206B

250C20B

 

23070606

ENGINE

(CAN) OVERSPEED OCCURED DURING FLIGHT, FUEL CONTROL REPLACED WITH SERVICEABLE UNIT. WHEN REMOVED, IT WAS NOTED THAT THE FCU INPUT SHAFT BEARING WAS DAMAGED. FCU SENT OUT FOR INSP/REPAIR. (TC NR 20070910007)

2007FA0000855

BELL  

ALLSN

 

FADEC

FAILED

9/6/2007

407  

250C47B

 

23072790

 

AIRCRAFT WAS STARTED IN A NORMAL MANNER. JUST PRIOR TO LIFT OFF THE (FADEC FAIL), (AUTO RELIGHT) WARNING LIGHTS ILLUMINATED AND THE FADEC FAIL HORN SOUNDED. NO LIMITATIONS WERE RECORDED OR OBSERVED. THE FADEC CONTROL ASSY WAS RETURNED TO MFG FOR ANALYSIS. (K)

CA071003027

BELL  

PWA  

 

ENGINE

MAKING METAL

8/29/2007

412EP

PT6T3

 

 

 

(CAN) AN ENGINE CHIP DETECTOR WARNING ACTIVED AND THE POWER SECTION WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE ENGINE OIL SYSTEM. MFG WILL INVESTIGATE AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071003027)

2007FA0000946

BOEING

PWA  

 

STRINGER

CRACKED

10/16/2007

727200

JT8D217C

 

 

BS940-945

THE AIRCRAFT INPUT FOR 4C CHECK AND CPCP ON SEPT 3, 2007. DURING CPCP, THE INSPECTOR PERFORMED VISUAL INSPECTION AND FOUND 5 INCH CRACK BOTH ON LT AND RT FUSELAGE STRINGER S18A BETWEEN BS940 AND BS945 ON SEPT 21, 2007. A PROPOSAL WAS INITIALLY SUBMITTED ON SEPT 22. AFTER REPAIR TO THE STRINGERS, FORM 337 WILL BE SUBMITTED TO FAA FOR FINAL RESULT OF CORRECTIVE ACTIONS DETAIL. (K)

SROM200725

BOEING

PWA  

 

WIRE

BURNED

10/5/2007

737205

JT8D17A

 

 

START SWITCH

DURING CLIMB SPARKS AND SMOKE EMITTED FROM THE AREA OF THE NR 1 START SWITCH. LOW IGNITION CB POPPED AT WHICH TIME THE SPARKS AND SMOKE CEASED. FLIGHT CREW RETURNED TO THE DEPARTURE AIRPORT FOR AN UNEVENTFUL LANDING. REPLACED SWITCH DUE TO ARCING ON CASE AND REPAIRED WIRING. INSPECTED OTHER AIRCRAFT IN FLEET NO OTHER CHAFED WIRES FOUND IN VICINITY OF THE START SWITCHES.

CA070911003

BOEING

PWA  

 

VALVE

MALFUNCTIONED

9/7/2007

737217

JT8D17

 

32015

FUEL HEAT

(CAN) APPROXIMATELY 25 MINUTES AFTER DEPARTING, THE CREW OBSERVED THE NR 1 ENGINE OIL TEMPERATURE CLIMBING THROUGH THE YELLOW BAND. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. MAINTENANCE REPLACED THE NR 1 FUEL HEAT VALVE AND CONDUCTED THE APPROPRIATE OVERWEIGHT LANDING INSPECTION BEFORE THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070911003)

2007FA0000949

BOEING

GE  

 

WINDSCREEN

CRACKED

10/17/2007

7377H4

CFM567B24

 

58935578

COCKPIT

IN CRUISE, 41,000FT (8.5PSID), -60C, ARCING AND SMOLDERING OBSERVED FROM MID BOTTOM OF WINDOW PROPAGATING UP TO TOP FWD EDGE OF RT NR 2 SLIDING WINDOW. WINDOW HEAT, RT, SIDE SWITCH SELECTED OFF. WHILE QRH CONSULTED, AS WINDOW COOLED, CRACKING OBSERVED ON OUTER PANE ONLY THROUGHOUT THE WINDOW AREA. QRH STATES NO FURTHER ACTION REQUIRED DUE OUTER PANE NOT PRIMARY STRUCTURAL SUPPORT. FLIGHT CONTINUED AT 41,000 FT FOR NEXT 20 MINS TO TOP OF DESCENT. LANDING CARRIED OUT NORMALLY. WINDOW ASSY REPLACED..

2007FA0000950

BOEING

GE  

 

WINDSCREEN

CRACKED

10/17/2007

7377H4

CFM567B24

 

58935578

COCKPIT

IN CRUISE, 41,000FT (8.5PSID), -60C, ARCING AND SMOULDERING OBSERVED FROM MID BOTTOM OF WINDOW PROPAGATING UP TO TOP FWD EDGE OF RT NR 2 SLIDING WINDOW. WINDOW HEAT, RT, SIDE SWITCH SELECTED OFF. WHILE QRH CONSULTED, AS WINDOW COOLED, CRACKING OBSERVED ON OUTER PANE ONLY THROUGHOUT THE WINDOW AREA. QRH STATES NO FURTHER ACTION REQUIRED DUE OUTER PANE NOT PIMARY STRUCTURAL SUPPORT. FLIGHT CONTINUED AT 41,000 FT FOR NEXT 20 MINS TO TOP OF DESCENT. LANDING CARRIED OUT NORMALLY. WINDOW ASSY REPLACED.

2007FA0000837

BOEING

CFMINT

 

BLADE

DAMAGED

8/22/2007

737800*

CFM567B26US

 

 

HPC 

ENGINE SURGED ON WING AND WAS INDUCTED INTO SHOP FOR I/V. DURING STRIP IT WAS NOTED THAT 1 OFF HPC STAGE 3 BLADE HAD BEEN LIBERATED TOGETHER WITH A SECTION OF THE DOVETAIL FROM THE STG 3 DISK. SECONDARY DAMAGE WAS ALSO NOTED ON THE HPC ROTOR AND STATORS. INSPECTION OF THE FRONT STATOR CASES REVEALED THAT A VSV STAGE 3 LEVER ARM WAS MISSING AND APPEARED NOT TO HAVE INSTALLED. NB ESN 892123 INPUTTED AS 1ST SV SINCE NEW. (K)

CA070907001

BOMBDR

PWC  

 

WIRE HARNESS

DAMAGED

9/6/2007

DHC8400

PW150A

 

471515

NLG 

(CAN) AFTER TAKEOFF, GEAR WOULD NOT RETRACT RESULTING IN AN AIR TURNBACK. DURING GROUND INSPECTION FOUND NOSE GEAR HARNESS TO BE INTERMITTENT DURING TESTING. DETAILED INSPECTION OF HARNESS FOUND IN SHARP BEND OF CONDUIT BOTH WOW SENSOR HARNESS AND NOSE WHEEL CENTERING HARNESS CRACKED AND SHIELDING EXPOSED. NLG WOW 2/CENTERING HARNESS HARNESS REPLACED. (TC NR 20070907001)

CA071003025

BOMBDR

PWC  

 

WIRE HARNESS

UNKNOWN

8/25/2007

DHC8400

PW150A

 

 

ENGINE

(CAN) IN CRUISE, THE PROPELLER ELECTRONIC CONTROL (PEC) AND POWER PLANT WARNINGS ACTIVATED. THE ENGINE WAS SHUTDOWN IN FLIGHT. THE PEC, SENSOR AND RELATED HARNESS WERE SUBSEQUENTLY REPLACED. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071003025)

2007FA0000885

BRAERO

GARRTT

 

VANE

CORRODED

9/10/2007

BAE125800A

TFE731*

 

257WF101A

TE FLAP

LT IB FLAP VANE, UPPER SKIN CORRODED BEYOND LIMITS. POSSIBLE CAUSE: DISSIMILAR METAL CORROSION AS TRAILING EDGE IS MAGNESIUM AND SKIN IS ALUMINUM OR ENVIRONMENT IN WHICH THE VANE OPERATES. IT IS LOCATED BEHIND THE MLG. ASSURE THE SKIN IS PROPERLY TREATED IAW CORROSION PREVENTION PROCEDURES AND PAINTED WITH EPOXY PRIMER BEFORE INSTALLATION. (K)

CA070905005

BRAERO

RROYCE

 

LEVER

FAILED

8/30/2007

HS7482A

DART5342

 

30Z10322

PARK BRAKE

(CAN) AFTER ARRIVING AT AIRPORT, THE AIRCRAFT ROLLED FORWARD AFTER THE PARK BRAKE WAS APPLIED WITH ENGINES STILL RUNNING AND THEN CONTACTED GROUND EQUIPMENT. MAINTENANCE DETERMINED THAT THERE WAS A FAULT WITH THE PARK BRAKE SYSTEM AND THE HANDLE ASSEMBLY WAS REPLACED. THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070905005)

CA070910001

CESSNA

CONT

 

PROPELLER

CORRODED

9/7/2007

150H

O200A

 

1A101

 

(CAN) WHILE PERFORMING A 5 YEAR CORROSION INSPECTION ON SUBJECT PROPELLER IAW CAR 625 APPENDIX C, PARA.5, CORROSION WAS NOTED IN THE MOUNTING HOLE BORE. IN CONSULTATION WITH THE PROPELLER OVERHAUL AMO, IT WAS DECIDED TO SEND IT TO THEM FOR FURTHER EVALUATION. CURRENTLY AWAITING THEIR REPORT AS TO IT`S STATUS. (TC NR 20070910001)

ZB0R20070002

CESSNA

LYC  

 

CARBURETOR

LEAKING

10/15/2007

152  

O235*

 

105220

ENGINE

DURING PROGRESSIVE INSP, FOUND CARBURETOR BOWL LEAKING AT GASKET. BOLTS WOULD NOT TIGHTEN - STRIPED THREADS. REPLACED CARBURETOR TO CORRECT DISCREPANCY.

ZB0R20070005

CESSNA

LYC  

 

CYLINDER

LEAKING

10/1/2007

152  

O235*

 

 

NR 2 

DURING PROGRESSIVE INSP, FOUND NR 2 CYLINDER UPPER TOP THROUGH BOLT LEAKING SEVERELY. REMOVED ENGINE FOR REPAIR. REINSTALLED AFTER REPAIR BY SERVICE CENTER. (CASE WAS FOUND FRETTING AND BEARING WEAR WAS EVIDENT AT BOLT LOCATION).

2007FA0000874

CESSNA

CONT

 

ROD END

BROKEN

7/28/2007

172D

O300*

 

MC05430221

NLG STEERING

LT SIDE STEERING ROD WITH 215.92 HRS SINCE NEW HAD THE REAR BALL END THAT ATTACHES TO THE RT RUDDER BAR ASSY BREAK. THE BALL ROD END BROKE AND LEFT THE T/R STEERING ROD AS THE ONLY STEERING FOR THE NOSE GEAR. THE RODS ARE NOT SOLID RODS, THEY ARE DESIGNED TO PUSH AND NOT TO PULL THAT SLIP INSIDE WHEN PULLED ON. IT REQUIRES BOTH RODS TO STEER THE RT PEDAL AND LT ROD WILL TURN NOSE TO THE RT AND LT PEDAL AND RT ROD WILL TURN IT TO THE LT. ON LANDING ROLL OUT, THE PLANE STARTS TO DRIFT TO THE LT AND WITH THE LT RUDDER PEDAL TO NOSE GEAR DISCONNECTED. NOSE GEAR WOULD NOT RESPOND AND THE PLANE WAS SLOWING UP TO THE POINT OF LOSING ENOUGH AIR FLOW OVER THE RUDDER FOR IT TO CONTROL THE PLANE. THE PILOT STARTED TO DRIFT MORE AND MORE TO THE LT AND WITH NO RESPONSE TO THE RT RUDDER PEDALS THE PILOT APPLIED THE BRAKES. PLANE WAS GOING OFF THE LT SIDE OF THE RUNWAY AND BEFORE HE COULD STOP IT, THE NOSE GEAR COLLAPSED. AIRCRAFT HAD 3321.80 HOURS TT. REPLACEMENT PART ONLY HAD 216.92 HRS ON IT. THE BALL ROD END HAD BEEN CRACKED FOR A PERIOD OF TIME AND PART OF THE CRACK HAD RUST IN IT AND THEN THE LAST OF IT FAILED. THE METAL LOOKED LIKE IT HAD CRYSTALLIZED AND THE VERY LITTLE THAT WAS HOLDING, BROKE. AFTER EXTENSIVE INSP OF THE BROKEN PARTS, IT WAS FOUND THAT THE MFG ROD ENDS PN S1107-3 THAT HAD BROKEN, ALSO HAD THREAD CRACKS WITH RUST. THESE ROD ENDS THREAD INTO NOSE GEAR STEERING COLLAR, PN 07430114 THE BALL END ATTACHES TO THE NOSE GEAR STEERING RODS, PN 0543022-1 OR IN THIS CASE PN MC0543022-1. ROD END S1107-3 IS A HOLLOW THREADED SHAFT STYLE THAT THREADS INTO THE STEERING COLLAR AND HAS A JAM NUT TIGHTENED DOWN ON THE STEERING COLLAR. BOTH RT AND LT ROD END FAILED AT THE JAM NUT. THERE WAS NO ENTRY ON THE REPLACEMENT OF RT OR LT ROD END PN S1107-3. (K)

2007FA0000880

CESSNA

LYC  

 

ALTERNATOR

INOPERATIVE

9/17/2007

172M

O320*

 

DOFF10300JR

 

THIS ALTERNATOR WAS OVERHAULED, OPERATED LESS THAN 50 HOURS, FAILED. THE STUD THAT HOLDS THE DIODE PLATE IN THE ALTERNATOR WAS BROKEN, AND THE SECOND STUD WAS LOOSE. THIS HAS BEEN AN ONGOING PROBLEM WITH OVERHAULS. WE ARE A SMALL SHOP, YET WE HAVE HAD MANY FAILURE WITH THIS PRODUCT IN THE PAST 2 YEARS. APPROXIMATELY 70 PERCENT OF THE OVERHAULS WE HAVE INSTALLED HAVE GONE BACK FOR WARRANTY. PROBLEMS INCLUDE LOOSE DRIVE PULLEYS, LOOSE HARDWARE, SHORT CIRCUITS, DEAD FIELD WINDINGS, DEFECTIVE BRUSHES. MY SUPPLIERS STATE THAT THEY HAVE HAD MANY COMPLAINTS ABOUT THIS REPAIR.

CA070905006

CESSNA

LYC  

CESSNA

CHANNEL

CRACKED

8/10/2007

172M

O320E2D

 

051218712

BULKHEAD

(CAN) SEB 97-1 ADDRESSES THE POSSIBILITY OF CRACKING OF THE AFT DOORPOST CHANNELS AT THE LOWER END, IN THE SMALL CUTOUT RADIUS BETWEEN THE VERTICAL AND HORIZONTAL FLANGE BENDS. THE CRACK IS VERY DIFFICULT TO SEE. BOTH DOORPOSTS WILL CRACK, AND IT IS THE SUBMITTERS OPINION THAT THIS CRACKING IS CAUSED CHIEFLY BY TAXIING OVER ROUGHER GROUND SO THAT THE FUSELAGE BULKHEAD THAT INCORPORATES THE AFT DOORPOSTS FLEXES MORE THAN IN MOST OTHER OPERATIONS. THIS IS THE THIRD AC WE HAVE FOUND WITH THIS DEFECT WITHIN THE LAST 7 YEARS. (TC NR 20070905006)

2007FA0000888

CESSNA

LYC  

 

WHEEL

FAILED

8/30/2007

172M

O360A4M

 

C163003102

LT MLG

WHEEL IS A 3 PIECE CONSTRUCTION, OUTER RIM AND THE INNER SPACER. BROKE APART ON TAXIING OF AIRCRAFT. JACKED AIRCRAFT AND INSTALLED SERVICEABLE UNIT, THREADS STRIPPED OUT OF CENTER SECTION. (K)

2007FA0000823

CESSNA

LYC  

 

ROTOR

FAILED

8/24/2007

172N

O360A4M

 

M3548

SHAFT

PILOT DEPARTED ON A VFR, DAY FLIGHT. DURING THE CLIMB FROM DEPARTURE, THE PILOT NOTICED A SLIGHT ENGINE ROUGHNESS THAT LASTED ONLY A SECOND. THE ENGINE SMOOTHED OUT UNTIL THE AC WAS LEVELED OUT AT CRUISE ALTITUDE AND CRUISE POWER SETTINGS THE ENGINE BEGAN RUNNING ROUGH. THE PILOT PERFORMED A MAGNETO CHECK IN FLIGHT FINDING THE RT MAGNETO INOPERATIVE. THE PILOT SWITCHED TO LT MAGNETO AND RETURNED TO LAND AT DEPARTURE WITHOUT INCIDENT. UPON OPENING THE MAGNETO, THE ROTO GEAR PN M3827 AND THE GEAR IN THE DISTRIBUTOR BLOCK ASSY PN K3822 WERE NOT DAMAGED AND WERE FREE OF OBSTRUCTION AND MOVED WITHOUT BINDING. THE SHAFT BROKE JUST BELOW THE SLOT IN THE SHAFT THAT HOLDS THE CAM WHICH OPENS THE CONTACTS. THERE D

2007FA0000824

CESSNA

LYC  

 

FITTING

CRACKED

8/26/2007

172P

O320*

 

05430161

NLG 

AC WAS BEING TAXIED FROM THE RAMP TO THE TAXIWAY, AND DURING TAXI, THE PILOTS REPORTED THAT THE NOSE GEAR STEERING SEEMED TO BE MALFUNCTIONING. UPON INSPECTION, THE NOSE GEAR STRUT APPEARED TO BE PRESSED UP AGAINST THE REAR HALF OF THE LOWER COWLING. THE LOWER NOSE GEAR FITTING (PN 0543016-1) WAS INSPECTED AND FOUND TO BE CRACKED COMPLETELY OFF ON THE RT SIDE. THE LT SIDE OF THE NOSE GEAR FITTING WAS STILL INTACT. THE CAP PN 05430181 WHICH CLAPS THE NOSE GEAR STRUT TO THE LOWER NOSE GEAR FITTING WAS FOUND TO BE MISSING FROM THE AIRCRAFT. THE HARDWARE WHICH ATTACHED THE LT SIDE OF THE CAP TO THE LOWER NOSE GEAR FITTING WAS FOUND TO BE MISSING ALONG WITH THE CAP. (K)

2007FA0000841

CESSNA

LYC  

 

CYLINDER

FAILED

8/18/2007

172P

O320D2J

 

AEL65102

NR 4 

DURING CRUISE FLIGHT, THE PILOT REPORTED A LOUD BANG FOLLOWED BY EXCESSIVE VIBRATION, INCREASED POWER TO FULL TO MAINTAIN ALTITUDE AND MADE A WELL-EXECUTED,, PRECAUTIONARY LANDING. AFTER SHUTDOWN THERE WAS A LARGE OIL PUDDLE DEVELOPING UNDER THE AIRCRAFT. AIRPLANE COWL REMOVED AND NR 4 CYLINDER WAS FOUND TO HAVE THE TOP HALF SEPARATED FROM THE BOTTOM. THIS CYLINDER REPORTED TO BE IN SERVICE LESS THAN A YEAR. THE CYLINDER HAS THE CASTING NR AEL85099 WHICH IS NOT SUBJECT TO AD2006-12-07 OR SB NR 05-8. ENGINE HAS (3) OTHER CYLINDERS WITH THE SAME CASTING NUMBER INSTALLED. IT IS ESTIMATED THAT ENGINE LOST 2.5 QUARTS OF OIL DURING THE FEW MINUTES BETWEEN THE SEPARATION AND THE SHUTDOWN. MECHANIC SUGGEST FAA L

2007FA1015001

CESSNA

LYC  

 

STARTER GEN

MAKING METAL

10/15/2007

172P

O320D2J

 

MHB6016

ENGINE

STARTER BENDIX DRIVE HAS NOT BEEN FULLY RETRACTING AFTER ENGINE START AND HAS BEEN SCRAPING THE ENGINE STARTER RING GEAR, CAUSING WEAR ON STARTER RING GEAR AND BENDIX ENGAGEMENT GEAR. WHEN THE BENDIX DRIVE DOES NOT DISENGAGE FROM STARTER RING GEAR COMPLETELY, THE BENDIX DRIVE DISENTIGRATES ALSO DAMAGING THE ENGINE STARTER RING GEAR. THIS IS A REOCCURING PROBLEM. WITH SILVER BENDIX DRIVES, P/N EBB-75A.

2007FA0000929

CESSNA

LYC  

 

BULKHEAD

MISALIGNED

7/12/2007

172R

IO360L2A

 

051179616

ZONE 100

CONTROL CABLE, ( P/N 0510105-308), FOUND WORN TO REPLACEMENT LIMITS IAW CABLE WEAR INSPECTION GUIDELINES IN AC43.13-1A. THE CABLE CONSTANTLY RUBS THE S338-7 FAIRLEAD IN THE LANDING GEAR BULKHEAD HOLE. IT IS BELIEVED THAT A HOLE MISLOCATION CAUSES THE MISALIGNMENT WHICH ALLOWS THE CABLE RUB. MM DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR COMMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMITS.

2007FA0000898

CESSNA

LYC  

 

BULKHEAD

MISALIGNED

10/12/2007

172R

IO360L2A

 

051179616

ZONE 100

CONTROL CABLE, (P/N 0510105-339), FOUND WORN TO REPLACE LIMITS IAW AC43.13-1A, CABLE INSPECTION. CABLE WAS WORN DUE TO CONSTANT CONTACT WITH LANDING GEAR BULKHEAD FAIRLEAD P/N S338-7. IT IS BELIEVED THAT THE HOLE MISALIGNMENT CAUSED THIS CONSTANT CONTACT. CESSNA MAINTENANCE MANUAL DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR COMMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMITS.

2007FA0000907

CESSNA

LYC  

 

BULKHEAD

MISALIGNED

10/12/2007

172R

IO360L2A

 

051179616

ZONE 100

CONTROL CABLE, (P/N 0510105-308), FOUND WORN TO REPLACE LIMITS IAW AC43.13-1A, CABLE INSPECTION. CABLE WAS WORN DUE TO CONSTANT CONTACT WITH LANDING GEAR BULKHEAD FAIRLEAD P/N S338-7. IT IS BELIEVED THAT THE HOLE MISALIGNMENT CAUSED THIS CONSTANT CONTACT. MM DOES NOT CONTAIN ANY "CABLE WEAR" LIMITS OR COMMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMITS.

2007FA0000924

CESSNA

LYC  

 

BULKHEAD

MISLOCATED

6/16/2007

172R

IO360L2A

 

051179616

FUSELAGE

CONTROL CABLE, ( P/N 0510105-308), FOUND WORN TO REPLACEMENT LIMITS IAW CABLE WEAR INSPECTION GUIDELINES IN AC43.13-1A. THE CABLE CONSTANTLY RUBS THE S338-7 FAIRLEAD IN THE LANDING GEAR BULKHEAD HOLE. IT IS BELIEVED THAT A HOLE MISLOCATION CAUSES THE MISALIGNMENT WHICH ALLOWS THE CABLE RUB. MM DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR COMMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMITS.

2007FA0000846

CESSNA

LYC  

 

HORN

LOOSE

9/13/2007

172S

IO360A1A

 

05341221

ELEVATOR

ELEVATOR HORN BEARING LOOSE IN BORE OF HORN, PN 0534122-1, BEARING ITSELF IS NOT WORN OUT BUT THERE IS PLAY BETWEEN THE TWO PARTS.

2007FA0000926

CESSNA

LYC  

 

BULKHEAD

WORN

8/12/2007

172S

IO360L2A

 

051179616

ZONE 100

CONTROL CABLE, ( P/N 0510105-308), FOUND WORN TO REPLACEMENT LIMITS IAW CABLE WEAR INSPECTION GUIDELINES IN AC43.13-1A. THE CABLE CONSTANTLY RUBS THE S338-7 FAIRLEAD IN THE LANDING GEAR BULKHEAD HOLE. IT IS BELIEVED THAT A HOLE MISLOCATION CAUSES THE MISALIGNMENT WHICH ALLOWS THE CABLE RUB. MM DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR COMMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMITS.

2007FA0000897

CESSNA

LYC  

 

CONTROL CABLE

WORN

10/12/2007

172S

IO360L2A

 

 

ELEVATORS

CONTROL CABLE, (P/N 0510105-308), FOUND WORN TO REPLACE LIMITS PER AC43.13-1A, CABLE INSPECTION. CABLE WAS WORN DUE TO CONSTANT CONTACT WITH LANDING GEAR BULKHEAD FAIRLEAD P/N S338-7. IT IS BELIEVED THAT THE HOLE MISALIGNMENT CAUSED THIS CONSTANT CONTACT. MM DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR COMMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMITS.

2007FA0000906

CESSNA

LYC  

 

BULKHEAD

MISALIGNED

10/12/2007

172S

IO360L2A

 

051179616

ZONE 100

CONTROL CABLE, (P/N 0510105-308), FOUND WORN TO REPLACE LIMITS IAW AC43.13-1A, CABLE INSPECTION. CABLE WAS WORN DUE TO CONSTANT CONTACT WITH LANDING GEAR BULKHEAD FAIRLEAD P/N S338-7. IT IS BELIEVED THAT THE HOLE MISALIGNMENT CAUSED THIS CONSTANT CONTACT. MM DOES NOT CONTAIN ANY "CABLE WEAR" LIMITS OR COMMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMITS.

2007FA0000904

CESSNA

LYC  

 

BULKHEAD

MISALIGNED

10/12/2007

172S

IO360L2A

 

051179616

ZONE 100

CONTROL CABLE, (P/N 0510105-339), FOUND WORN TO REPLACE LIMITS IAW AC43.13-1A, CABLE INSPECTION. CABLE WAS WORN DUE TO CONSTANT CONTACT WITH LANDING GEAR BULKHEAD FAIRLEAD P/N S338-7. IT IS BELIEVED THAT THE HOLE MISALIGNMENT CAUSED THIS CONSTANT CONTACT. MM DOES NOT CONTAIN ANY "CABLE WEAR" LIMITS OR COMMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMITS.

2007FA0000931

CESSNA

LYC  

 

BULKHEAD

MISALIGNED

9/12/2007

172S

IO360L2A

 

051179616

ZONE 100

CONTROL CABLE, ( P/N 0510105-308), FOUND WORN TO REPLACEMENT LIMITS IAW CABLE WEAR INSPECTION GUIDELINES IN AC43.13-1A. THE CABLE CONSTANTLY RUBS THE S338-7 FAIRLEAD IN THE LANDING GEAR BULKHEAD HOLE. IT IS BELIEVED THAT A HOLE MISLOCATION CAUSES THE MISALIGNMENT WHICH ALLOWS THE CABLE RUB. MM DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR COMMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMITS.

RDA092407

CESSNA

CONT

 

TRANSMITTER

CRACKED

9/24/2007

175  

GO300*

 

05235571

FUEL QTY

WHILE CALIBRATING THE FUEL QUANTITY SYSTEM THE LT FUEL GAUGE WOULD SHOW AN INCREASE IN QUANTITY THEN START DECREASING. WHILE TROUBLESHOOTING THE LT TANK FUEL QUANTITY SENDER, FOUND 2 CRACKS APPROXIMATELY 1 INCH LONG IN THE BRASS FLOAT.

2007FA0000851

CESSNA

CONT

 

ROD END

BROKEN

10/1/2007

182A

O470*

 

S11073

MLG 

ROD END AT STEERING COLLAR SHEARED CAUSING LOSS OF DIRECTIONAL CONTROL.

2007FA0000840

CESSNA

CONT

 

CARBURETOR

FAILED

8/18/2007

182G

O470R

 

1048931

ENGINE

PILOT REPORTED THAT AFTER A NORMAL START, HE WAS UNABLE TO ADVANCE THE THROTTLE CONTROL TO CRUISE OR TAKEOFF POWER. A PARTIAL DISASSEMBLY OF THE CARBURETOR REVEALED THAT THE AIR METERING PIN/AIR METERING JET WAS BLOCKING THE THROTTLE SHAFT TRAVEL. THE CARBURETOR WAS SENT FOR REPAIR. (K)

2007FA0000937

CESSNA

LYC  

 

CONTROL CABLE

WORN

9/12/2007

182S

IO360L2A

 

 

ZONE 100

LT AND RT ELEVATOR CONTROL CABLES, ( P/N 0510105-189), FOUND WORN TO REPLACEMENT LIMITS IAW CABLE WEAR INSPECTION GUIDELINES IN AC43.13-1A. CABLE WAS WORN DUE TO CONSTANT CONTACT WITH THE MICARDA PLATES OVER THE FUEL LINES AT FUEL SELECTOR AREA JUST FORWARD OF THE FRONT SEATS. THE CABLE TENSIONS ARE CORRECT BUT THE CABLES ARE IN CONSTANT CONTACT WITH PLATES. MM DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR COMMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMITS.

2007FA0000900

CESSNA

LYC  

 

CONTROL CABLE

WORN

10/12/2007

182S

IO540AB1A5

 

 

ZONE 100

CONTROL CABLE, (P/N 0510105-189), FOUND WORN TO REPLACE LIMITS IAW AC43.13-1A, CABLE INSPECTION. CABLE WAS WORN DUE TO CONSTANT CONTACT WITH MICARDA GUARD PLATE OVER FUEL LINES AT FUEL SELECTOR AREA JUST FORWARD OF FRONT SEATS. THE CABLES ARE IN CONSTANT CONTACT WITH PLATES EVEN WITH CABLE TENSION CORRECT. MM DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR COMMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMITS.

2007FA0000884

CESSNA

PWA  

 

PLATE

CRACKED

7/17/2007

208  

PT6A6

 

07516800

 

FOUND TORQUE PLATE CRACKED DURING ROUTINE INSPECTION. (K)

2007FA0000856

CESSNA

PWA  

 

RECEIVER

SMOKE

9/11/2007

208B

PT6*

 

066011480102

GPS 

SHORTLY AFTER TAKEOFF FROM ISP THE PILOT NOTICED SMOKE IN THE COCKPIT. THE PILOT IMMEDIATELY RETURNED TO DEPARTURE AND LANDED. THE PILOT REPORTED THAT THE SMOKE APPEARED TO BE CAUSED BY AN ELECTRICAL PROBLEM. THE PILOT REPORTED THAT THE GPS NO LONGER OPERATED. ON 9/12/2007, MECHANIC INSPECTED THE AIRCRAFT, REMOVED THE GPS AND FOUND THAT IT SMELLED OF ELECTRICAL SMOKE, THE MECHANIC EXAMINED THE RADIO RACK, WIRING HARNESSES AND ENTIRE INSTRUMENT PANEL AREA AND FOUND NO PROBLEM. THE ENGINE COMPARTMENT AND ELECTRICAL EQUIPMENT BOX WERE INSPECTED WITH NO PROBLEMS FOUND. THE AIRCRAFT WAS GROUND RUN AND ALL ELECTRICAL EQUIPMENT WAS OPERATIONAL TESTED WITH THE GPS UNIT REMOVED AND ALL OPERATED NORMALLY. THE GPS WAS PLACED ON MEL AND THE AIRCRAFT WAS RELEASED FOR SERVICE. (K)

2007FA0000908

CESSNA

CONT

 

STOP

BROKEN

9/19/2007

310Q

IO470*

 

JE1 

MLG GEARBOX

PILOT HAD NO LT GEAR DOWN INDICATION. HE CYCLED GEAR WITH NO SUBSEQUENT GEAR DOWN INDICATION. HE ATTEMPTED MANUAL EXTENSION, CRANKED TO THE MECHANICAL STOP IN THE GEARBOX AND BROKE THE STOP. BELLCRANK CONTINUED PAST DOWN AND THEN WENT PARTIALLY (UP). GEAR COLLAPSED ON LANDING. (K)

2007FA0000922

CESSNA

CONT

 

MOTOR

NOISY

10/2/2007

340A

TSIO520*

 

MHJ4003S

STARTER

STARTER STARTED MAKING A LOUD SQUEALING NOISE WHEN OPERATING STARTER, AND SLOW ROTATION OF ENGINE. REMOVED AND RETURNED FOR WARRANTY. (K)

4757

CESSNA

CONT

CONT

CYLINDER

CRACKED

9/25/2007

414A

TSIO520NB

 

AEC631397

RT ENGINE

PILOT WAS INFORMED BY LINE PERSONNEL DURING TAXI TO TIE DOWN, THAT ENGINE WAS MAKING A LOUD (AIR PULSING) SOUND. PILOT COULD ONLY HEAR THE SOUND AFTER REMOVING NOISE CANCELLING HEAD SET. PILOT THEN SHUTDOWN ENGINE. INSPECTION REVEALED THE NR 4 CYLINDER TO BE CRACKED AT THE PARTING SURFACE. EXHAUST WAS ESCAPING FROM THE CRACK CAUSING THE (AIR PULSING) SOUND.

2007FA0000872

CESSNA

CONT

 

SKIN

CORRODED

7/19/2007

421C

GTSIO520*

 

 

WINGS

LT AND RT WING UPPER SKINS UNDER THE NACELLE FUEL BLADDER TANKS HAD CORROSION PRESENT TO THEM AND RELATED AREA AROUND THE BLADDER BAYS. WO NR 10688. (K)

2007FA0000944

CESSNA

CONT

 

STARTER

SHORTED

10/12/2007

421C

GTSIO520N

 

6462751

RT ENGINE

OVERHAULED STARTER FAILED AFTER 30 HOURS. (K)

CA070910004

CESSNA

PWA  

 

BUCKLE

DISCONNECTED

9/9/2007

550  

JT15D4

 

110195203

SEATBELT

(CAN) WHILE COMPLYING WITH COMPANY CAMPAIGN NOTICE 010-25-10-011 CREW SEAT BELT BUCKLE INSPECTION, (REFER TO FAA SAIB NM-06-29)INTERFERENCE BETWEEN THE COCKPIT SEATBELT BUCKLES AND THE CONTROL COLUMN WOULD UNLATCH THE SEATBELT BUCKLE WHEN THE YOKE WAS MOVED THROUGH FULL TRAVEL LT AND RT. THERE ARE NO CURRENTLY APPROVED SEAT BELT REPLACEMENTS AVAILABLE TO ELIMINATE THIS HAZARDOUS SITUATION. (TC NR 20070910004)

CA071003018

CESSNA

PWA  

 

ENGINE

SMOKE

8/13/2007

550  

JT15D4

 

 

 

(CAN) IN CRUISE SMOKE BECAME EVIDENT IN THE AIRCRAFT CABIN REQUIRING THE ENGINE AIR BLEED TO BE SELECTED OFF. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071003018)

2007FA0000866

CESSNA

PWC  

 

BUSS BAR

LOOSE

9/7/2007

680CE

PW306C

 

691835432

LT JBOX

THE AIRCRAFT WENT TO START ENGINES, 6 CAS MESSAGES APPEARED ON THE DISPLAY. TROUBLESHOT PROBLEM AND FOUND MOUNTING STUD FOR EMERGENCY BUSS BAR WAS LOOSE CAUSING ARCING AND WELDING OF THE STUD. THIS STUD WAS LOOSE FROM FACTORY. DO AN INSPECTION OF ALL STUDS TORQUE CHECK) (K)

2007FA0000923

CESSNA

ALLSN

 

CONNECTOR

MISINSTALLED

10/5/2007

750  

AE3007C

 

 

 

PRIMARY STAB TRIM FAILED CLIMBING THROUGH FL280 AT 300 KTS. NO CAS MESSAGE WAS PRESENT. CLACKER WAS STUCK ON. STAB WAS NOT MOVING WHEN CLACKER WAS GOING OFF. AUTO PILOT DISENGAGED ON ITS OWN DUE TO HEAVY NOSE CONFIG. AFTER TROUBLESHOOTING SHOULD THE ECM TO BE BAD. REMOVED AND REPLACED (ECM NR 421400216J1) WITH NEW PART 4214-0021-11 (LATEST DASH NR) COMPLETED PRIMARY CHANNEL A/B TRAVEL VERIFICATION CHECKS IAW 750 MM, TASK 27-40-00-721, NO FAULTS NOTED. FOUND THE PRIMARY AND SECONDARY CONNECTORS SWAPPED. WHICH HAD NO EFFECT IN THIS FAILURE. (K)

2007FA0000892

CESSNA

ALLSN

 

FLEX DRIVE

BROKEN

10/10/2007

750  

AE3007C

 

1434425

RT TE FLAPS

THE RT FLAP FLEX DRIVE HOUSING FAILED AT THE SWAGED END OF THE HOUSING AT THE IB END. ON SEPTEMBER 11, 2007 THIS AIRCRAFT HAD A SIMILAR EVENT WITH THE LT OB FLAP DRIVE WHICH ALLOWED THE FLEX DRIVE TO DISENGAGE FROM THE OB FLAP DRIVE CAUSING THE FLAPS TOP REMAIN AT 3 DEGREES POSITION AND PREVENTING FURTHER EXTENSION OR RETRACTION. WE OPERATE 2 AIRCRAFT AND THIS IS THE 4TH FAILURE OF THE FLEX DRIVE BETWEEN THE 2 AIRCRAFT.

2007FA0000925

CESSNA

CONT

 

LINK ROD

WORN

10/18/2007

A185F

IO520D

 

632558A1

THROTTLE

THROTTLE BUTTERFLY (P/N: 625601G) AND THROTTLE BODY (P/N: 639437)ARE WORN, ALLOWING BUTTERFLY SHAFT TO SLIDE SIDE TO SIDE CAUSING THE LINK ROD ASSEMBLY (P/N: 632558A1)TO WEAR CHAFING THE WAVE WASHER AND COTTER PIN. THE COTTER PIN AND WAVE WASHER AT THE THROTTLE BODY WERE MISSING AT THE TIME OF INSPECTION. IF THE LINK ROD FROM THE THROTTLE BODY ARM AND THE METERING BLOCK ARM DETACHES, PROPER FUEL METERING CEASES.

2007FA0000915

CESSNA

PWA  

 

HINGE BRACKET

CORRODED

10/1/2007

S550

JT15D4

 

 

LT ELEVATOR

LT OB HINGE BRACKET BROKE OFF DURING AILERON REMOVAL. APPEARS TO HAVE FAILED DUE TO CORROSION. (K)

CA071003028

CESSNA

PWA  

 

STRAINER

BLOCKED

8/23/2007

S550

JT15D4

 

 

NR 4 BEARING

(CAN) IN DESCENT, ENGINE OIL PRESSURE REDUCED AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED OIL COKING AND BLOCKAGE OF THE NR 4 BEARING SCAVENGE OIL STRAINER. (TC NR 20071003028)

2007FA0000887

CESSNA

ALLSN

 

TURBINE WHEEL

FAILED

8/3/2007

STC206C

250C30P

 

 

ENGINE

AFTER 13 HOURS OF OPERATION SINCE OVERHAUL, DURING A POWER CHECK, THE TURBINE ASSY FAILED CAUSING THE FORCED LANDING OF THE HELICOPTER. FORCED LANDING CAUSED SUBSTANTIAL DAMAGE TO THE AIRCRAFT. (K)

2007FA0000854

CESSNA

LYC  

 

EXHAUST STACK

LOOSE

8/9/2007

T206H

TIO540AJ1A

 

40B22318

ENGINE

DURING AN INSPECTION, FOUND THE EXHAUST STACK AT NR 2 CYLINDER, PULLED DOWN .0625 INCH APPROX. FURTHER INVESTIGATION FOUND THE NR1, NR3, NR5 AND NR 6 ENGINE CYLINDERS EXHAUST STACKS PULLED DOWN, BUT NOT AS MUCH. AFTER RECOMMENDATIONS FROM ENGINE MFG ALSO, THE SUPPLIER EXHAUST SYSTEM (WHICH IS ONE IN THE SAME). DURING THE ENGINE CYLINDER REMOVAL PROCESS FOUND LOWER FWD, .7500 INCH STUD NUT UNDER TORQUED. FURTHER INVESTIGATION REVEALED THE FORWARD 2 STUDS BOTH BELOW, MFG RECOMMENDED DRIVING TORQUE OF CYLINDER HOLDDOWN STUDS IN CASE. INSTALLED NEW OVERSIZE (.003) STUDS IAW ENG MFG RECOMMENDATIONS. INSTALLED NEW NR 2 ENGINE CYLINDER AND NEW EXHAUST CROSSOVER PIPE AS REQUIRED. TIGHTENING THE EXHAUST FLANGE NUTS DOES NOT STOP THE LEAK ON ALL OF THE STUDS, SOME OF THE STUDS THE NUT BOTTOMS OUT ON THE THREAD. THE PREVIOUSLY EFFECTED EXHAUST FLANGE AREAS AFTER TIGHTENED UP HAVE COME LOOSE AGAIN IN 50 HRS TIME IN SERVICE. (K)

2007FA0000879

CESSNA

CONT

 

SELECTOR VALVE

MISMANUFACTURED

9/9/2007

T207A

TSIO520M

 

12161001

FUEL SYSTEM

WHEN THE FUEL SELECTOR VALVE IS SELECTED TO THE RT TANK, FUEL IS BEING DELIVERED FROM THE LT TANK, VISE VERSA. THIS WAS DISCOVERED DURING A SHORT FLIGHT IN WHICH THE PILOT NOTICED THE RT TANK FUEL GAUGE WAS DROPPING WHEN THE LT TANK WAS SELECTED. THIS WAS LATER CONFIRMED DURING AN INSPECTION IN WHICH FUEL WAS DRAINED FROM BOTH TANKS. IN FACT THE SELECTOR VALVE IS PUT TOGETHER INTERNALLY BACKWARDS. (K)

CA070905012

CESSNA

CONT

 

CYLINDER HEAD

CRACKED

8/31/2007

U206E

IO520F

 

TSIN712ACA

ENGINE

(CAN) CRACKED FROM SPARK PLUG HOLE TO EXHAUST VALVE (TC NR 20070905012)

2007FA0000828

CESSNA

CONT

 

CYLINDER

CRACKED

9/6/2007

U206G

IO520F

 

SA52000A20P

NR 2 

CYLINDER HEAD HAS A CRACK. BEGINNING AT INTAKE PORT AND EXTENDING TO UPPER SPARK PLUG HOLE. (K)

2007FA0000845

CIRRUS

CONT

 

MAGNETO

ARCED

8/17/2007

SR20

IO360ES

 

6314 

ENGINE

DURING ANNUAL INSPECTIO, 500 HR MAG INSP COMPLIED WITH EARLY DUE TO NR OF HOURS PREVIOUSLY FLOWN. BOTH MAGNETOS SHOWED SAME INTERNAL ARCING, SO SEVERE, THAT BRUSH HOLDER PN K3823 WAS MELTED/ BURNED UP, CONTACTED SLICK TECH SUPPORT 904-739-4360, OUR MAG S/N`S WERE MATCHED TO PROBLEM MAGS WHICH SLICK WAS AWARE OF CARBON USED IN MFG OF BRUSHES TOO SOFT, CARBON DUST CAUSED ARCING. IT IS A WONDER THIS CUSTOMERS ENGINE CONTINUED TO RUN. (K)

2007FA0000882

CIRRUS

CONT

 

MUFFLER

CRACKED

8/31/2007

SR20

IO360ES

 

20559002

ENGINE

CHECK MUFFLER IAW MFG SB, SB2X-78-07, ISSUED JUNE, 2007. FOUND SPOT WELDS ON EXTERNAL BAFFLE CRACKED. REPLACED MUFFLER. THIS SB APPLIES ONLY TO SR20`S SN 1005 THRU 1797. (K)

2007FA0000861

CIRRUS

CONT

 

EXHAUST HEADER

CRACKED

8/20/2007

SR22

IO550N

 

15070001

NR 5 

NR 5 EXHAUST HEADER HAS CRACKED OFF AT FLANGE, JUNE 6/06 AT 440.6, NOV 18/06 AT 636.1 HOBBS, MAY 18/07 AT 746.7 HOBBS AND AGAIN AUG 20/07 HOBBS NOT AVAILABLE. AFTER INSPECTING HEADER IT WOULD SEEM THAT A HEAVER GAUGE PIPE WOULD RESOLVE THE PROBLEM. THE LAST HEADER WAS INSTALLED WITH BACK UP FLANGES WELDED TO PIPE AT FLANGE SECTION WITH NO EFFECT. (K)

2007FA0000849

CIRRUS

CONT

 

FAIRING

SEPARATED

9/26/2007

SR22

IO550N

 

18583002

RT WING ROOT

LOWER SECTION OF RT WING ROOT FAIRING SEPARATED FROM AIRCRAFT IN FLIGHT. FAIRING IS RETAINED WITH JUST A FEW SCREWS AND AN AREA OF THE LOWER PORTION OF FAIRING IS RETAINED WITH DOUBLE SIDED TAPE AND AN AREA OF DOUBLE SIDED TAPE CAME DEBONDED AND AIR GOT UNDER IT AND IT RIPED OFF.

CA070905007

CNDAIR

GE  

 

DCU  

INOPERATIVE

8/31/2007

CL6002B19

CF343A1

 

6229820009

NR 3 

(CAN) DURING CLIMB OUT, CREW REPORTED A (L ENG MISCOMP) MESSAGE FOLLOWED BY A HIGH ITT. THE CREW ELECTED TO SHUTDOWN THE ENGINE. AFTER SHUTDOWN THE ITT REMAINED AT 998 DEGREES CELSIUS. AT TIME OF THE INCIDENT, THE AIRCRAFT WAS OPERATING UNDER MEL31-41-01 DUE TO AN INOPERATIVE DCU NR 3. DURING TROUBLESHOOTING, IT WAS DISCOVERED THAT SEVERAL SNAGS OCCURRED FOLLOWING THE REPLACEMENT OF ONE DCU WITH A P/N 622-9820-009. ALL OTHERS DCU WERE P/N 622-9820-008. ACCORDING TO SL RJ-SL-31-011 BOTH P/N ARE INTERCHANGEABLE AND INTERMIXABLE. DCU NR 1 AND NR 3 WERE REPLACED AND THE AIRCRAFT WAS RELEASED INTO SERVICE. NO SIMILAR INCIDENT TO DATE HAS BEEN NOTED. (TC NR 20070905007)

CA070905003

CNDAIR

GE  

 

BPSU

INOPERATIVE

9/4/2007

CL6002B19

CF343B1

 

601R9310511

TE FLAPS

(CAN) WING FLAPS FAILED TO FULLY EXTEND FOR LANDING. AFTER SELECTING FLAPS 8 THE CREW RECEIVED A FLAP FAULT CAUTION MESSAGE AND THE FLAPS WOULD NOT MOVE ANY FURTHER. THE CREW LANDED WITH FLAPS AT 8 DEGREES UNEVENTFULLY. FECU SHOWS LT BPSU AT FAULT. BPSU REPLACED, RIGGED AND FUNCTIONAL TEST COMPLETED SUCCESFULLY. AIRCRAFT RETURNED TO SERVICE. (TC NR 20070905003)

CA070906009

CNDAIR

GE  

 

BLADES

DAMAGED

8/13/2007

CL6002B19

CF343B1

 

 

NR 2 ENGINE

(CAN) A/C DIVERTED DUE TO NR 2 ENG. VIBRATION AND LOUD NOISE. NR 2 ENGINE WAS SHUTDOWN IN FLIGHT. PILOT DECLARED AN EMERGENCY. CONTRACT MAINTENANCE FOUND THE EXHAUST TURBINE BLADES DAMAGED. PRELIMINARY INSPECTION THAT THE LAST STAGE TURBINE WITH TOTAL DAMAGE TO ALL BLADES. APPEARS THAT SOMETHING IN BETWEEN THE FIRST STAGE HPT AND LAST STAGE LPT CAME LOOSE AND DEPARTED THROUGH THE TURBINE. ENG WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. ENG IS IN ENG SHOP AND IS BEING PREPPED FOR SHIPPING. (TC NR 20070906009)

CA070906008

CNDAIR

 

 

WINDOW

CRACKED

9/3/2007

CL6002C10

 

 

NP1393225

COCKPIT

(CAN) CREW REPORTED THAT ON SHORT FINAL, CAPTAIN LT SIDE WINDOW CRACKED. REPLACED SIDE WINDOW IAW AMM (TC NR 20070906008)

2007FA0000877

COLUMB

CONT

 

ALTERNATOR

FAILED

8/7/2007

LC41550FG400

TSIO550A

 

LC41550FG

ENGINE

A FLIGHT TEST WAS BEING CONDUCTED ON 07/30/07 ON A REWORKED THERMAL SYSTEMS (KATS) EVADE SYSTEM, WHEN THE SYSTEM WENT UNSTABLE CAUSING THE ALTERNATOR TO GO OFF LINE. THE TECHNICIAN MONITORING THE SYSTEM ON A DIAGNOSTIC LAPTOP COMPUTER ANNOUNCED TO THE PILOT THAT THE SYSTEM WAS FAILED BUT THE PILOT DID NOT HAVE A "FAILED" ANNUNCIATION ON THE INSTRUMENT PANEL. KATS CONFIRMED THAT THERE WAS A PROBLEM WITH THE FAULT DETECTION SOFTWARE THAT WOULD ALLOW THIS UNDER VERY SPECIFIC CONDITIONS. KATS STATED THAT THEY DO NOT BELIEVE THIS TO BE A SERIOUS SITUATION SINCE THE SYSTEM IS CERTIFIED INADVERTENT ICING ONLY.

2007FA0000890

CUBCFT

CONT

 

SETSCREW

DAMAGED

9/11/2007

CC11100

O200A

 

MS5196364

CYL ROCKER BOSS

IN THE NEW STYLE CYLINDER ASSY PN 655482 FOR THE ENGINE, THE ROCKER ARM PIN PN 654375 IS RETAINED BY A SET SCREW PN MS51966364 IN THE CENTER ROCKER BOSS SUPPORT. FOUND IN THIS ENGINE (2) SET SCREWS LOOSE AND A THIRD FOUND RATTLING AROUND AND LODGED UNDER THE INTAKE ROCKER ARM BETWEEN THE CYLINDER HEAD. THE ROCKER SHAFTS ARE MOVING OFF CENTER AND ROTATING AND WITH A MACHINED SHARP CUT IN THE END OF THE ROCKER SHAFT TO INDICATE WERE SET SCREW IS TO LINE UP WITH THE ROCKER SHAFT, IT IS CUTTING THROUGH THE VALVE COVERS AND WILL LEAD TO LOSS OF ENGINE OIL AND OPERATION OF THE ENGINE AND POSSIBLE LOSS OF PERSONAL LIFE. (K)

2007FA0000889

CUBCFT

CONT

 

ROCKER

MISINSTALLED

9/11/2007

CC11100

O200A

 

 

NR 4 CYLINDER

FOUND THE ROCKER ARMS REVERSED, INTAKE EXHAUST ROCKERS IN CYLINDER NR 4 LEADING TO POSSIBLE EXHAUST GUIDE AND VALVE DAMAGE DO TO THE EXHAUST ROCKER ARM HAS AN OILING PORT FOR THE EXHAUST VALVE AND THE INTAKE ROCKER ARM DOES NOT HAVE THE OILING PORT. THE ROCKER ARMS WERE REMOVED AND INSTALLED CORRECTLY. DAMAGE TO VALVE AND GUIDE UNKNOWN AT THIS TIME, WILL HAVE TO CONTACT MFG. (K)

CA070905011

DHAV

PWA  

 

DUCT

CRACKED

9/3/2007

DHC8311

PW123

 

16673301

BLEED AIR SYS

(CAN) CABIN PACK REPORTED AS UNCONTROLLABLE AT LOW POWER SETTINGS. MAINTENANCE GROUND RUNS NOTED NON SUPPLY OF BLEED AIR AT FLIGHT IDLE SETTINGS, ALSO NOTED BLEED AIR LEAK FROM CEILING OF ACM COMPARTMENT. ACCESS GAINED TO INTERNAL OF DORSAL FIN AND FOUND BLEED AIR DUCT P/N 16673-301 CONNECTS TO FUSELAGE DUCT, CRACKED AND SPLIT OPEN APPROX HALF OF ITS DIAMETER. DUCT REPLACED, GROUND RUNS COMPLETED AND AIRCRAFT RETURNED TO SERVICE. PART IS CONSIDERED AS AN EXPENDABLE AND TIMES NOT TRACKED. AIRFRAME TIMES 36419HR/51123CY (TC NR 20070905011)

2007FA0000825

DIAMON

CONT

 

PUMP

FAILED

8/21/2007

DA20C1

IO240B

 

64936849A1

FUEL SYSTEM

THE MIXTURE CONTROL SHAFT ON THE ENGINE DRIVEN FUEL PUMP FROZE UP AT HALF TRAVEL BETWEEN FULL RICH AND IDLE CUT OFF. THIS CREATED A LEAN MIXTURE CONTROL WAS DISCONNECTED FROM THE FUEL PUMP, THEN THE FUEL PUMP CONTROL SHAFT HAD TO BE FREED UP. THE MIXTURE CABLE WAS COMPLETELY FREE WITH NO BINDING ONCE DISCONNECTED FRO THE FUEL PUMP. THE FUEL PUMP WAS REPLACED AND SENT BACK TO MFG. (K)

2007FA0000869

DIAMON

 

 

SKIN

CRACKED

8/1/2007

DA40

 

 

 

RUDDER

FOUND 3 INCH CRACK AFT OF RUDDER BALANCE WEIGHT IN COMPOSIT SKIN FWD OF UPPER ATTACH POINT. AIRCRAFT WAS BASED OUT OF A HEAT RELATED AREA. (K)

Y5CR200700001

DOUG

 

 

BEVEL GEAR

BROKEN

10/5/2007

MD500E

 

 

369D2512311

M/R GEARBOX

PART OF TOOTH ON INPUT BEVEL GEAR BROKEN OFF.

2007FA0000917

EMB  

PWA  

 

ROD  

BROKEN

8/20/2007

EMB110P1

PT6A34

 

3013460

FUEL CONTROL

DURING A 150 HR INSPECTION THE LOWER FUEL CONTROL ROD WAS FOUND BROKEN ON THREADED SHAFT WHERE IT SCREWS INTO COUPLING. IT LOOKS LIKE IT MAY HAVE BEEN BENT AND A MORE DETAILED INSPECTION OF THIS COMPONENT SHOULD OCCUR. (K)

CA070905010

EMB  

GE  

 

PIPE

CUT  

9/3/2007

ERJ170100SU

CF348E5A1

 

15E0803003

HYD SYSTEM

(CAN) DURING ROUTINE A CHECK INSPECTION A CUT APPROXIMATELY 1 CM LONG WAS NOTICED ON THE ENGINE HYDRAULIC PUMP SUPPLY PIPE. THIS CUT WAS APPROXIMATELY .050 DEEP AND WAS THE RESULT OF CHAFFING WHEN THE COWLS WERE CLOSED. (TC NR 20070905010)

CA071003029

FOKKER

PWA  

 

THERMOCOUPLE

UNSERVICEABLE

8/29/2007

F27MK50

PW125B

 

 

ENGINE

(CAN) THE ENGINE OVER-TEMPERATURE WARNING ACTIVATED IN FLIGHT AND THE ENGINE WAS SHUTDOWN. SUBSEQUENT INSPECTION REVEALED TWO UNSERVICEABLE T6 THERMOCOUPLES. (TC NR 20071003029)

2007FA0000860

GULSTM

RROYCE

 

CONNECTOR

CORRODED

8/15/2007

GULFSTREAMGV

BR700710A110

 

 

NLG STEERING

EXCESSIVE CORROSION AT CONNECTOR PINS CAUSING NWS FAIL MSG. SUGGEST PERIODIC INSPECTION AND CLEANING OR IMPROVED CONNECTOR SEALING FROM MOISTURE. (K)

2007FA0000829

HUGHES

 

 

CONTROL SYSTEM

ROUGH

8/31/2007

369D

 

 

369D21800501

T/R PITCH

DURING 100 HR INSPECTION, PLAY WAS NOTICED BETWEEN THE ROTATING AND NOT-ROTATING SWASH PLATES OF THE TAIL ROTOR PITCH CONTROL AFTER REMOVAL, IT WAS NOTED THAT THE BEARING WAS DRY AND ROUGH. RECORDS INDICATE IT WAS REGREASED IN DEC OF 2006. (K)

2007FA0000835

LEAR

 

LEAR

ADJUSTER

DAMAGED

8/2/2007

25D  

 

 

3321209

BRAKE VALVE

UPON VISUAL INSPECTION OF THE POWER BRAKE VALVE PN 60810741-804, SN 9711105, IT WAS FOUND THAT THE ADJUSTMENT SCREW HAD BEEN GROUND DOWN AND MODIFIED. AS WE BEGAN TO LOOK THROUGH SB 23/24/25-32-12 AND FOUND THAT THIS UNIT PN WAS NOT IN THIS SB. WE THEN FOUND THAT THIS UNIT WAS FOR A LEAR 60. WE THEN LOOKED INTO THE MFG PARTS BREAKDOWN AND FOUND THAT THE LEVER AS WELL AS THE MODIFIED ADJUSTMENT SCREW, THE STOP SCREW AND PIN DID NOT BELONG ON THIS PN OF POWER BRAKE VALVE. THISE PARTS ARE FOR A PN 2380002 OR PN 2381443 OR PN 3321200-3 POWER BRAKE VALVE. WE CONTACTED OUR CUSTOMER AND FOUND THAT THIS UNIT WAS REMOVED FROM LEAR 25D.

2007FA0000836

LEAR

GARRTT

 

STATIC SYSTEM

MISINSTALLED

8/6/2007

35A  

TFE731*

 

 

 

THIS RVSM AIRCRAFT HAD AN ALTIMETRY SYSTEM SPLIT. CONTACTED STC GROUP HOLDER FOR PROPER ROUTING OF STATIC SYSTEM PLUMBING. FOUND CO-PILOTS SYSTEM WAS NOT CROSS COUPLED WITH PILOTS SYSTEM. INSTALLED FABRICATED HOSES TO THE CO-PILOTS SYSTEM TO MEET STC NR ST 00563DE-D. PROBABLE CAUSE: CO-PILOTS STATIC SYS NOT CROSS-COUPLED AT STC INSTALLATION OR SYSTEM WAS MODIFIED/ ALTERED POST-STC WITHOUT APPROVED DATA. (K)

2007FA0000916

LEAR

GARRTT

 

STRUCTURE

DAMAGED

9/28/2007

35A  

TFE7312

 

 

THRUST REVERSER

DURING THE PILOT PREFLIGHT, THE PILOT HAD NOTICED THAT THERE WAS A TEAR IN THE SHEET METAL OF THE LT ENGINE THRUST REVERSER INNER SKIN. WE COULD NOT IDENTIFY WHAT HAS CAUSED THIS TEAR. THE UNIT WILL BE REPAIRED BY THE MFG AND WILL INFORM YOU WITH ANY INFO THEY GIVE TO US ABOUT THIS INCIDENT. (K)

2007FA0000827

LEAR

GARRTT

 

MANIFOLD

DAMAGED

8/14/2007

45LEAR

TFE731*

 

4536102150V431

LT ENGINE

LT PYLON OVERHEAT INDICATION OCCURRED IN FLIGHT. FOUND HIGH PRESSURE BLEED AIR MANIFOLD MATING FLANGE DEFORMED. REPLACED ASSY 4536102150V43-1 WITH NAV ASSY 45361020228-001. CAUSE MAY BE AGE OR REPEATED CLAMPING. ORIGINAL PART HAS BEEN SUPERSEDED BY THE MFG. (K)

CA071003023

LEAR

PWA  

 

FAN BLADE

FRACTURED

8/12/2007

60LEAR

PW305A

 

30B285501

COMPRESSOR

(CAN) IN CRUISE, THE ENGINE EMITTED A LOUD NOISE AND WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED TWO FRACTURED FAN BLADES. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071003023)

CA070904003

LKHEED

ALLSN

 

TRUNNION

CRACKED

8/29/2007

382G

501D22A

 

 

NLG 

(CAN) DURING THE A-CHECK INSPECTION, MAINTENANCE DETECTED A CRACKED RT NOSE LANDING GEAR TRUNNION FITTING. THE AIRCRAFT WAS RE- POSITIONED FOR PART REPLACEMENT. (TC NR 20070904003)

PAI52007S4724

PIAGIO

PWA  

 

DUCT

CRACKED

9/26/2007

P180

PT6*

 

80232118401

WING LE

DURING 3000 HOUR D-CHECK FOUND 3 OF 4 WING OB LEADING EDGE PANELS WITH CRACKED HEATING DUCTS.

CA070911007

PILATS

PWA  

PARKER

PAD  

WORN

9/7/2007

PC1245

PT6A67B

 

10903000

BRAKE ASSY

(CAN) PILOT REPORTED SPONGY FEELING WHEN RT BRAKE PEDAL ACTUATED. UPON FURTHER INSPECTION FOUND BRAKE WEAR PADS PREMATURELY WORN IN A CUPPING SHAPE BEYOND LIMITS. BRAKE ASSEMBLY REPLACED AND RETURNED TO STORES. (TC NR 20070911007)

2007FA0000875

PIPER

LYC  

 

BOLT

LOOSE

10/3/2007

PA28181

O360*

 

 

VERTICAL STAB

LOSE VERTICAL ATTACH BOLTS ON AFT BULKHEAD.

ZB0R20070004

PIPER

LYC  

 

CAM  

WORN

9/15/2007

PA28R200

IO360A1A

 

LW18840

ENGINE

ON CLIMB-OUT, PILOT NOTICED LOW POWER. RETURNED TO AIRPORT. MAINTENANCE INSPECTION REVEALED BELOW MINIMUM VALVE TRAVELS FOR ALL INTAKE VALVES. REMOVED NR 1 CYLINDER. FOUND CAM LOBES SEVERELY WORN AND TAPPETS CORRODED AND WORN IN A CONCAVE MANNER. ENGINE REPAIRED BY SERVICE CENTER. REINSTALLED ON ACFT. ALL SYSTEMS OPS CK NORMAL.

CA070909002

PIPER

LYC  

 

PUMP

FAULTY

9/4/2007

PA31

TIO540A2C

 

RG908054AM

ENGINE

(CAN) DURING START UP THE ENGINE WOULD NOT MAINTAIN FUEL PRESSURE AT 700 RPM. ENGINE WOULD NOT SUSTAIN POWER AT 2000 RPM AND PRESURE DROPS AND ENGINE QUITS. ENGINE DRIVEN FUEL PUMP WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. ENGINE WAS PREVIOUS OVERHAULED ALONG WITH FUEL PUMP. (TC NR 20070909002)

2007FA0000883

PIPER

LYC  

 

AXLE

BROKEN

8/7/2007

PA32300

IO540K1A5

 

7873804

LT MLG

ON TAXI TO TAKEOFF, AC TURNED AROUND AFTER BACK TAXI. PIVOTING ON LT M/G. SIDE LOAD BROKE AXLE AT END OF DRILLED OUT CENTER. EVIDENCE OF PREVIOUS CRACKING FROM INSIDE OB. (K)

2007FA0000873

PIPER

LYC  

 

MAGNETO

DAMAGED

8/27/2007

PA32R301T

TIO540AH1A

 

6361 

LT 

THIS AIRCRAFT HAD A SET OF MAGS INSTALLED AT APPROXIMATELY 400 HRS TT, AT 596 HRS TT, INSTALLED ANOTHER O/H MAG ON THE LT, DUE TO AN OVERHEAT SITUATION. IT APPEARS THAT THE COIL HAS BROKEN DOWN DUE TO EXCESS HEAT, DURING NORMAL OPERATION. NEW AC SHOULD HAVE AIR BLAST TUBES INSTALLED FOR EACH MAGNETO, AS WELL AS A COOLING KIT FOR THE VACUUM PUMP. THE MAGS, NOR THE VACUUM PUMP CAN OPERATE UNDER THESE CONDITIONS WITHOUT AN OUTSIDE AIR SUPPLY. SB 1157A AFFECTS AC FOR THE TACHOMETER SENSOR ALLOWING MOISTURE TO DAMAGE THE MAGNETO. (K)

ZB0R20070003

PIPER

LYC  

 

ACTUATOR

LEAKING

10/15/2007

PA34200

IO360A1A

 

9686002

NLG 

DURING GEAR MAINTENANCE, FOUND NLG ACTUATOR LEAKING. INSPECTION REVEALED WORN SEALS. REPLACED SEALS BUT STILL LEAKED. FURTHER INSPECTION WITH BORESCOPE IN BODY OF ACTUATOR REVEALED LONGITUDINAL SCORING ON INSIDE WALL OF ACTUATOR BODY. REPLACED ACTUATOR TO CORRECT DISCREPANCY.

2007FA0000942

PIPER

CONT

 

LANDING GEAR

COLLAPSED

9/21/2007

PA34220T

TSIO360KB

 

 

NOSE 

AIRCRAFT TAXIED TO RUNWAY AFTER LOADING CARGO. AFTER NORMAL RUNUP, THE PILOT TAXIED ONTO THE RUNWAY AND STOPPED. THE PILOT ADVANCED THROTTLES AND RELEASED BRAKES, AFTER RELEASING BRAKE, THE NOSE GEAR COLLAPSED. AIRCRAFT WAS RECOVERED AND TOWED OFF RUNWAY TO A SAFE TIE DOWN SPOT. NO CAUSE IS YET KNOWN AS TO WHY THE NOSE GEAR COLLAPSED. (K)

2007FA0000938

PIPER

LYC  

PIPER

BOLT

SHEARED

10/22/2007

PA44180

O360*

 

AN551

DRAG LINK

FORWARD DRAG LINK BOLT ON NOSE GEAR FAILED DURING TOUCH AND GO PRACTICE. A/C RETURNED TO DEPARTURE AND LANDED WITH THE NOSE GEAR STUCK IN THE NOSEWHEEL WELL.

2007FA0000948

PIPER

CONT

PIPER

CENTERING MECH

FAILED

10/24/2007

PA46310P

TSIO520*

 

 

NLG 

UPON TOUCHDOWN AIRCRAFT VEERED LT ABRUPTLY AND DEPARTED RUNWAY SURFACE. GEAR EXTENSION AND INDICATION WERE NORMAL. INVESTIGATION REVEALED THAT UPON TOUCHDOWN THE NOSE LANDING GEAR HAD FAILED TO CENTER CORRECTLY DURING EXTENSION.

MINR2007918A

PIPER

LYC  

 

EXHAUST PIPE

BULGED

9/18/2007

PA46350P

TIO540AE2

 

40B19974

ENGINE

THE EXHAUST CROSSOVER EXHAUST PIPE WAS FOUND SEVERELY BULGED IN THE AREA COVERED BY THE HEAT SHROUD. THE DAMAGE WAS TO THE POINT, ISSUES WERE FORMING THAT WOULD HAVE LED TO RUPTURE. IF AN EXHAUST LEAK OCCURS IN THIS AREA, THE HEAT WILL AFFECT THE MAGNETO, FUEL AND OIL LINES. IT IS HIGHLY RECOMMENDED BY MAINTENANCE PERSONNEL THAT THE HEAT SHROUD BE REMOVED AT EACH 100 HOUR INSPECTION FOR AIRCRAFT WITH MORE THAT 500 HOURS. NR 3 CYLINDER EXHAUST RISER PN 40B19827 WAS ALSO FOUND SEVERELY BULGED. THIS CAN BE SEEN WITH THE ENGINE COWLING REMOVED WITHOUT FURTHER DISASSEMBLY. THE LT EXHAUST TRANSITION PN 47C19848 WAS FOUND BULGED AND CRACKED. THIS CAN BE SEEN WITH A MIRROR AND FLASHLIGHT. IF ANY DAMAGE IS FOUND ON T

2007FA0000945

RAYTHN

WILINT

 

PUMP

DAMAGED

10/12/2007

390  

FJ442A

 

 

HYD SYSTEM

HYDRAULIC PUMP ASSY, PN 390-389022-0003, INSPECTED AND FOUND NOT DEFECTIVE. FOUND DEFECTIVE/ DAMAGED PART PN MS28778-6, PACKING. FLIGHT CREW COMPLETED ABNORMAL CHECKLIST. UPON INSPECTION FOUND THAT PACKING AT HYDRAULIC PUMP PRESSURE OUTLET FITTING HAD FAILED. THIS COMPONENT WAS WORKED ON IAW MFG SAFETY COMMUNIQUE , CONTROL NR JAS-SDR-001. (K)

2007FA0000893

RAYTHN

GARRTT

 

TURBINE WHEEL

FAILED

9/14/2007

HAWKER800XP

TFE7315BR

 

307516034

LP COMPRESSOR

CLIMBING THROUGH FL270, A LOUD BANG IN REAR OF ACFT. LT ENGINE COMPUTER LIGHT ILLUMINATED. PF BROUGHT LT ENGINE TO IDLE, PNF PULLED CHECKLIST. AFTER SURVEY OF ENGINE PARAMETERS, PF TURNED LT ENGINE COMPUTER BACK ON TO CONTROL PARAMETERS. ENGINE COMPUTER DID STAY ON & DID APPEAR TO CONTROLL ENGINE. POWER ADVANCED SLOWLY ON LT ENGINE. AT APPROXIMATELY 70 % N1 ANOTHER LOUD BANG IN REAR & LT ENGINE COMPUTER LIGHT ILLUMINATED AGAIN. ENGINE PARAMETERS MOVED TO RED LINE. PF SHUTDOWN LT ENGINE. PNF CONTACTED ATC, DECLARED AN EMERGENCY & REQUESTED & RECEIVED DIRECT CLOSEST AIRPORT. SINGLE ENGINE APPROACH CHECKLIST & PROGRAMMED FMS FOR AN APPROACH. ACFT CLEARED FOR VISUAL APPROACH. AFTER A NON-EVENTFUL LANDING. PAX DEPLANED & ACFT SURVEYED FOR DAMAGE, NONE FOUND. AFTER ENGINE REMOVED & TORN DOWN, DETERMINED A 2ND STAGE LOW PRESSURE COMPRESSOR ROTOR DISC POST SEPARATION. LP SECTION SEIZED.

2007FA0000852

RKWELL

 

 

COTTER PIN

MISSING

9/24/2007

OV10A

 

 

MS24665134

PROP SPINNER

SPINNER WAS LOST FROM RT ENGINE WHILE IN A RT TURN AT 7000 FT DAMAGING ONE PROPELLER BLADE. SPINNER NOT RECOVERED.

CA071004001

ROBSIN

LYC  

 

STARTER

INOPERATIVE

10/3/2007

R44RAVENII

IO540AE1A5

 

14924HTH

 

(CAN) ZERO TIMED STARTER INSTALLED ON AIRCRAFT. WOULD NOT TURN OVER DURING FUNCTIONAL CHECK. (TC NR 20071004001)

2007FA0000876

RYAN

CONT

 

TRANSMITTER

UNRELIABLE

9/19/2007

NAVION

IO520B

 

PT100GA

ENGINE OIL PRESS

AIRCRAFT LANDED WITH ZERO OIL PRESSURE INDICATION. AFTER TESTING WITH DIRECT READING GAUGE IT WAS DETERMINED THAT THE ACTUAL ENGINE OIL PRESSURE WAS WITHIN LIMITS SPECIFIED BY THE MFG. FURTHER TESTING REVEALED PRESSURE INDICATING SYSTEM WOULD OPERATE NORMALLY AFTER ENGINE TEMPERATURES HAD COOLED BUT WOULD PROVIDE FALSE INDICATIONS WITH ENGINE AT OPERATING TEMPERATURE. FEEL THIS IS A SERIOUS PROBLEM BECAUSE THIS SYSTEM IS STC APPROVED AS A PRIMARY INSTRUMENT AND ITS MALFUNCTION COULD CAUSE UNNECESSARY AND DANGEROUS OFF AIRPORT LANDINGS.

2007FA0000838

SCWZER

ALLSN

 

BEARING

FAILED

8/15/2007

269D

250C20

 

6898607

NR 1 

PILOT REPORTED CHIP LIGHT CAME ON DURING TRAINING FLIGHT. LANDED AS SOON AS POSSIBLE AND PROBE REMOVED AND CLEANED. GROUND RUN MADE IAW MM AND CHIP PULLED AND INSPECTED. MORE METAL FOUND SO ENGINE REMOVED FROM AC AND INSPECTED. FOUND NR 1 BEARING OF COMPRESSOR ASSY FAILING. NO EVIDENCE OF OVERHEATING OR OIL STARVATION. PILOT REPORTED NO LOSS OF OIL PRESSURE DURING FLIGHT. (K)

CA070905001

SKRSKY

ALLSN

 

BEARING

DISINTEGRATED

8/11/2007

S76A

250C30S

 

TBA 

NR 5 

(CAN) FLIGHT CREW ENCOUNTERED A NR 2 ENGINE CHIP WARNING LIGHT FOLLOWED BY COMPLETE ENGINE FAILURE WITHIN 1 MIN EMERGENCY LANDING EXECUTED. NR 2 ENGINE AND OIL COOLER REPLACED, A/C RETURNED TO SERVICE. SUBSEQUENT INVESTIGATION CARRIED OUT AT AMO REVEALED FAILURE OF THE NR 5 BEARING. THE BEARING FAILURE CAUSED POWER TURBINE ROTOR VIBRATION AND OSCILLATION RESULTING IN SUBSEQUENT DAMAGE AND DECOUPLING OF TURBINE TO COMPRESSOR (N1) COUPLING. THE GAS GENERATOR TURBINE ENTERED OVER-SPEED OF UNKNOWN VALUE. THE GP TURBINE OVER SPEED CAUSED NR 2 TURBINE BLADES TO PROGRESSIVELY SEPARATE FROM THE DISK. THE NR 5 BEARING HAD BEEN OVERHAUL INSPECTED BY THIS AMO APPROXIMATELY 757.9 HRS PRIOR TO FAILURE AND RE-INSTALLED AS (SERVICEABLE). THE BEARING HAS ACCUMULATED AT LEAST 3576 HRS. POSSIBLY AS MUCH AS 7040.4 HRS. (ON CONDITION PART). (TC NR 20070905001)

CA070906001

SNIAS

TMECA

 

SPAR

CRACKED

8/27/2007

AS350BA

ARRIEL1B

 

 

VERTICAL STAB

(CAN) CRACKS DISCOVERED ON BOTH SIDES OF STABILIZER THROUGH LOWER DOUBLER AT SPAR. FOUR RIVETS FOUND MISSING FROM FORWARD SPAR ATTACHMENT OF LOWER STABILIZER FRAME. (VISISBLE UPON REMOVAL ONLY) SUSPECT INCORRECT SHIMMING AT THIS TIME. (TC NR 20070906001)

CA071003017

UROCOP

PWA  

 

ENGINE

POWER LOSS

8/10/2007

EC135P1

PW206B

 

 

 

(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION IN FLIGHT. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071003017)

2007FA0000844

WACO  

JACOBS

 

CABLE

INOPERATIVE

8/13/2007

YMFF5C

R7557

 

700232

PITCH SERVO

THE PITCH SERVO BRIDLE CABLE WAS FOUND TO BE LOOSE AND NOT CONNECTED TO THE CAPSTAN. IT WAS WOUND BETWEEN THE BOTTOM END OF THE CAPSTAN AND THE CAPSTAN END PLATE WITH THE CLAMP TO THE ELEVATOR CABLE HAVING BEEN SLIDING ON THE ELEVATOR CABLE. THE ELEVATOR WAS FOUND TO BE FREE TO MOVE NORMALLY IT IS NOT KNOWN HOW THIS MALFUNCTION OCCURRED. IT IS POSSIBLE THAT THE BRIDLE CABLE CLAMP WAS NOT SUFFICIENTLY TIGHT ALLOWING THE BRIDLE CABLE TO BECOME SLACK AND COMING LOOSE IN THE CAPSTAN. (K)

 

END OF REPORTS