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ADVISORY CIRCULAR

43-16A

 

 

AVIATION MAINTENANCE ALERTS

 

 

flag of the United States of America

 

ALERT

NUMBER

360

bald eagle watching over three eggs

JULY

2008

 


CONTENTS

AIRPLANES

BOMBARDIER............................................................................................................................ 1

DIAMOND.................................................................................................................................. 3

HELICOPTERS

ROBINSON............................................................................................................................... 11

SIKORSKY............................................................................................................................... 11

POWERPLANTS

CONTINENTAL....................................................................................................................... 11

LYCOMING.............................................................................................................................. 14

THIELERT................................................................................................................................. 14

AIR NOTES

INTERNET SERVICE DIFFICULTY REPORTING (iSDR) WEB SITE................................... 17

IF YOU WANT TO CONTACT US......................................................................................... 18

AVIATION SERVICE DIFFICULTY REPORTS...................................................................... 18

 


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

BOMBARDIER

Bombardier: CL600; "Stick-Pusher" Capstan Failure; ATA 2730

(Most all airmen understand foreign aviation directives are not binding on U.S.-registered aircraft, but those who fly pay close attention nonetheless. Several such admonitions are found in this month’s publication. The following Airworthiness Directive from Transport Canada is published as received; as always, thank-you for the “heads-up.”)


 

AIRWORTHINESS DIRECTIVE


 

AIRWORTHINESS DIRECTIVE.

Part Total Time: (n/a).

 

DIAMOND

Diamond: DA40; Cracked Rear Door Hinge; ATA 5210

(The following submission combines two short M or D reports describing separate defects on the same model but different N-numbered aircraft, and on different dates. The next two Alert entries also contain combined discrepancy reports, providing a total of six reports—all referencing the same defect.)

A mechanic writes the same description for two different reports. “The rear hinge (can be seen) developing cracks in the (laminate) fibers under normal operating conditions. A probable cause: the rear hold-open cylinder is causing stress on the hinge point.” (Rear door P/N: D41-5221-00-00. Scary pictures can be found further down—keep reading.)

Part Total Times: 984.0 and 991.0 hours (respectively).

 

Diamond: DA40; Door Separation from Aircraft; ATA 5210

(The following combines two short M or D reports describing separate incidents on the same airplane, but on different dates. Closely related to this description, the next Alerts’ entry also provides enhanced information...and pictures!)


An FAA inspector notes for an operator, “While taxiing into take-off position on the runway, the aft passenger door departed the airframe.” Approximately 7 months later of this airplane he again writes, “On take-off climb out, the aft passenger door departed the airframe.” (Door P/N: DA4-5221-00-00-2. Airframe is pulled by a Lycoming IO-360-M1A.)

Part Total Times: 225.3 and 536.0 hours, (respectively).

 

Diamond: DA40; Door Separation from Aircraft; ATA 5210

(Two related discrepancy reports are combined here—again concerning a single airplane—but on different dates. The abbreviated descriptions are followed by relevant discussion and photographs as provided by submitting Aviation Safety Inspectors Michael Brown and Arthur Steffes from the Scottsdale Flight Standards District Office. Contact information is found at the discussion’s end, and appreciation for their effort provided up front: thank-you, gentlemen—Ed.)

The first incident report states, “On take-off roll (at rotation speed), the aft passenger door departed the airframe.” (Door P/N: DA4-5221-00-00-2; part total time: 615.0 hours.) The second report says, “Cracks were found in the aft door hinge.” (P/N: DA4-5221-00-00-2; part total time: 628.0 hours.)

Inspector Steffes expands the two discrepancies in supplemental correspondence stating, “In June of 2008 a Diamond DA40 aircraft operated by a flight school had the rear passenger door depart the aircraft, narrowly missing the tail plane and rudder. The door was later recovered. The aft hinge was broken off and the forward hinge damaged. Investigation revealed the hinge had cracked (then broke), due in part to the materials used in part fabrication and the high pressure placed upon it by the door opening strut (gas spring: Diamond P/N DA4-9052-00-11; vendor P/N G8-19-200-1-389-GZ10-400N). The door and hinge are one assembly made of a composite type material. The hinge is approximately ¾ inch wide. The strut is attached near the rear hinge. It exerts approximately 90 pounds of force near the hinge attach point. Even though the door employs a safety latch handle, when the aft hinge fails the door flexes enough to slide past the stop.

“An inspection of another aircraft in this (operator’s) fleet found it too had recently had doors separate in flight under similar circumstances. This same aircraft showed signs of cracking at the rear hinge on the replacement door. This (door separation defect) is the third such occurrence this operator has experienced.”

(The following photographs have been slightly compressed in the vertical dimension to conserve space—Ed.)


 

AFT VIEW OF DAMAGED DOOR.

 

SIDE VIEW OF DAMAGED DOOR.


 

TOP VIEW OF CRACKED HINGE (1).

 

TOP VIEW OF CRACKED HINGE (2).


 

BOTTOM VIEW OF CRACKED HINGE.

 

BOTTOM VIEW OF CRACKED HINGE WITH ADJACENT STRUT.


 

BOTTOM VIEW OF CRACKED HINGE WITH ADJACENT STRUT (DOOR REMOVED).

 

CLOSE-UP OF BOTTOM HINGE ON FUSELAGE.


 

CLOSE-UP OF BOTTOM HINGE ON DOOR.

 

IMPACT DAMAGE TO THE TRAILING EDGE OF THE DOOR.

 

(For further information contact Aviation Safety Inspector Arthur Steffes; Scottsdale Flight Standards District Office, 17777 N. Perimeter Dr., Suite 101, Scottsdale, AZ, 85255; phone 405-419-0330 ext. 254.)

Part Total Times: 615.0 and 628.0 hours (respectively).

 


Diamond: DA42; Cracked Clutch Springs; ATA 8510

(The following is a Service Information letter issued by Diamond Aircraft on this defect topic. The referenced European Emergency AD is located further down, under “engines”: see Thielert.)

SERVICE INFORMATION LETTER.

Part Total Time: (n/a).

 


HELICOPTERS

ROBINSON

Robinson: R22; Broken T/R Pedal Bearing Block Support; ATA 6720

A submitting technician states, “(This aircraft was conducting) a training flight—the instructor and student were practicing autorotation. On the third autorotation (with the aircraft settling to ground) the student was “inputting right pedal” to compensate for torque loss when a loud “snap” was heard. It came from the pilot side tail rotor pedal area. The (control) pedals became bound in place. After “shut-down” inspection (found) the bearing block support (P/N A359-2) for the pilot’s side pedals had broken....” (This helicopter is powered by a Lycoming O-320B2C.)

Part Total Time: 13,078.0 hours.

 

SIKORSKY

Sikorsky: S-76C+; Repetitive Landing Gear Lamp Failures; ATA 3340

An operator for this type helicopter describes an expensive, on-going light-bulb saga (P/N SB-4580) with a healthy suspicion that “...the manufactured parts are not meeting design specifications. The (source) manufacturer is of unknown origin (generic), and (neither the box nor the bulbs reveal manufacturing information). There is less than 7 flight hours average per (nose/main gear) lamp, from their installation to replacement. (We) have replaced at least 5 lamps (in our) two aircraft in less than 30 flight hours each. No circuit breakers are popping, and trouble shooting reveals no discrepancies on either aircraft. (Search light assembly P/N: 76550-02005104; Landing light assembly P/N: D-6490-3. An attached receipt indicates a box of 10 bulbs sells for $276.00.)

Part Total Time: 7.0 hours (average).

 

POWERPLANTS

CONTINENTAL

Continental: GTSIO-520-H; Missing Alternator Drive Parts; ATA 8520

An unidentified repair station submitter states, “This (Cessna 421B) engine was removed in August due to a cracked engine case. It was sent to Ram Aircraft for repair. The engine was returned in September and reinstalled back on the aircraft. During a November night flight the pilot experienced an alternator failure (which) he reported the next day. Upon inspection of the alternator it was found in pieces, with the mount housing still attached to the engine. The inside of the alternator installation hole was inspected, revealing the attach bolts on the alternator face gear had no tab lock plates installed (P/N 641909; item number 20). (Conclusion:) the attach bolts came loose and damaged the engine and alternator. Ram Aircraft was notified of the problem. It is (my) recommendation to inspect for missing parts in the alternator attach hole before engine installation. This engine had 65.6 hours since the previous installation.”


 

PARTS DRAWING OF THE ENGINE'S CRACKSHAFT ASSEMBLY.


 

PARTS DRAWING OF THE ENGINE'S CRANKSHAFT ASSEMBLY.

Part Total time: (unknown).

 


LYCOMING

Lycoming: TIGO-541-E1A; Incorrect Exhaust Gaskets; ATA 7810

(This engine report relates to a Piper PA31P and an ensuing accident. It’s not often submitters will include such details of their “thinking processes” as can be found here, lending high instructive value otherwise missing from a collection of facts. “Thank-you” for the extra effort—Ed.)

An aircraft mechanic states, “I found melted wiring at the number 6 cylinder—and behind it. The P-lead for the R/H magneto was melted, and when tested found to be shorted out. This (incapacitated) the right magneto. The number 6 bottom plug wire was hanging loose and the nut attaching the lead to the plug was melted off. Several other plug wires were burnt as well. The cause of this damage was a blown-out exhaust gasket on the number 6 cylinder. When this gasket failed, hot exhaust was allowed (to escape), burning up the plug wires and the R/H magneto P-lead.” “The number 6 bottom plug wire was from the L/H magneto. The bottom number 4 wire’s protective coating was also burnt off. So, now (at best) we have one magneto working and only firing on 5 cylinders—plus a large exhaust leak which will lower manifold pressure.

“I performed a high tension lead test on the R/H side of the right engine; number 6 tested bad—the rest were okay. No continuity test was done at this time. (Next...) the original R/H propeller was removed and a test propeller installed. The engine was started...but idled very rough. It would not take throttle or make any power above idle. The R/H magneto was disconnected and the engine started again: it idled much better and would take throttle, although it ran poorly.

“The lower plugs were removed to facilitate the exhaust removal—they showed signs of a rich mixture or incomplete burn. When I disassembled the R/H exhaust stack on the right engine (cylinders 2, 4, and 6) the following was found:

  (a)  “On the number 2 cylinder all exhaust nuts were loose—each about 2 turns. The exhaust gaskets were intact, but they appeared to be a copper gasket (P/N 76048). The parts book (specifies) a steel gasket (P/N 78056).

  (b)  “The number 4 cylinder’s inboard forward nut, inboard aft nut, and outboard forward nut were all found loose. The outboard aft nut was tight. The exhaust gaskets were intact and appeared to be the copper type (P/N 76048).

  (c)  “The number 6 cylinder exhaust stack had a gap between the stack and the cylinder where the exhaust gasket was blown out. There were three small pieces of gasket left that appeared to be the remains of a copper gasket (P/N76048).”

“The end result (of this defect) was an off-field landing after the right engine failed. The aircraft landed up-right with the gear up, flaps up, cowl flap closed, magneto switches on, fuel pumps on, fuel selectors on inboard tanks, and the R/H engine feathered. The L/H propeller (sustained) three bent blades, the R/H just one. (There was) significant damage to the R/H wing, both lower cowls, and the aircraft’s belly. The pilot did not receive any serious injury.”

Part Total Time: (unknown).

 

THIELERT

Thielert: TAE 125-02-99; Cracked Clutch Springs; ATA 8510

(The following Airworthiness Directive was issued by the European Aviation Safety Agency, EASA. It is published as received—having particular relevance to this issue’s Diamond DA42 Aircraft reports.)


 

AIRWORTHINESS DIRECTIVE.


 

AIRWORTHINESS DIRECTIVE.

Part Total Time: (n/a).

 


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:

Pennie Thompson
Service Difficulty Reporting System, Program Manager
Aviation Data Systems Branch, AFS-620
P.O. Box 25082
Oklahoma City, OK 73125
Telephone: (405) 954-1150
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

CA080319005

 

 

 

DRIVE SYSTEM

SEIZED

3/19/2008

 

 

 

EBB131A

STARTER

STARTER RECEIVED DUE TO DRIVE ASSEMBLY FAILURE. ENGINE COULD NOT BE STARTED BECAUSE DRIVE WOULD NOT ENGAGE. WHEN INSPECTED THE DRIVE COULD NOT BE TURNED OUT OR SPUN BY HAND TO EXTEND THE GEAR SECTION OF THE DRIVE. STARTER WAS RETURNED TO KELLY AEROSPACE FOR WARRANTY REPLACEMENT. (TC NR 20080319005)

CA080304004

 

 

 

ENCODER

DAMAGED

3/3/2008

 

 

 

5035PP41

ALTIMETER

WHEN RECEIVED FOUND WITH TIN BETWEEN CASE AND PIN ON CONNECTION RECEPTACLE.

CA080407002

 

 

 

WIRE HARNESS

MISINSTALLED

3/31/2008

 

 

 

472011

NLG WOW

AN OPERATOR FOUND THAT DURING INSTALLATION OF MOD SUM 4-125401, FINDING THE NEW HARNESSES PN.47201-1 THREE OUT OF SIX HARNESSES PULLED FROM STOCK WERE MISS WIRED. ON CONNECTOR 3261-P32 PINS A-B AND D-E WERE WIRED REVERSED. HARNESSES APPROPRIATELY REPAIRED IAW MANUFACTURER PROVIDED DATA AND RETURNED TO STOCK. TO ADDRESS THIS ISSUE, SERVICE LETTER DH8-SL-32-014A ADVISING OF POSSIBLE MANUFACTURING FAULTS WAS RAISED.

CA080411002

 

 

WOODWARD

PILOT VALVE

DAMAGED

4/9/2008

 

 

 

210332

GOVERNOR

THE GOVERNOR WAS MANUFACTURED BY ONTIC, ONTIC HAS THE MANUFACTURING RIGHTS TO THE FORMER WOODWARD GOVERNOR COMPANY PISTON ENGINE GOVERNORS. THE GOVERNOR WAS RECEIVED FROM THE AIRCRAFT MANUFACTURE, DIAMOND AIRCRAFT INDUSTRIES, FOR REPAIR IN APRIL 2008. ACCORDING TO A CUSTOMER CLAIM/RETURN AUTHORIZATION FORM RECEIVED FROM DIAMOND, THE GOVERNOR WAS REMOVED FROM AIRCRAFT SERIAL NR 40.438 ON OR ABOUT SEPTEMBER 21, 2005, WITH AIRCRAFT TTSN OF 96.9 HOURS. WITH ORIGINAL COMPLIANT OF ENGINE OVERREVED DURING FLIGHT, COULD NOT CONTROL PROPELLER. THE NAME PLATE ON THE GOVERNOR GIVES A ASSY DATE OF 08/04 DURING INSPECTION OF THE GOVERNOR IN OUR SHOP, AFTER REMOVAL OF THE TOP COVER, IT WAS FOUND THAT THE HEAD END HAD SEPARATED FROM THE TUBULAR PORTION OF THE PILOT VALVE ASSEMBLY. IT WAS ALSO NOTED THAT THE BEARING RETAINER PART NR 180231 HAD BEEN DAMAGED AND 10 OF THE 11, 0.125 INCH BALL BEARINGS HAD BEEN RELEASED FROM THE CAGE, FOUR WERE FOUND INSIDE OF THE GOVERNOR HOUSING, AND FIVE WERE FOUND INSIDE OF THE SHIPPING COVER FOR THE GOVERNOR, ONE HAS NOT BEEN FOUND. ATTACHED IS A COPY OF WOODWARD SERVICE BULLETIN 33571C ORIGINALLY ISSUED IN JULY 1979 THAT ADDRESSES THIS ISSUE, WE HAVE NEVER SEEN THESE PILOT VALVES COME APART BEFORE. IT APPEARS THAT THE SET SCREW RETAINS THE HEAD END TO THE TUBULAR PORTION HAS BACKED OUT OF ITS LOCATION, THERE IS NO VISUAL EVIDENCE OF THE REQUIRED EPOXY ON THE SET SCREW. WHEN THE HEAD END SEPARATED FROM THE TUBULAR PORTION OF THE PILOT VALVE ALL PITCH CHANGE CONTROL OF THE PROPELLER IS LOST.

CA080304006

 

 

 

STARTER

FAILED

3/4/2008

 

 

 

 

ENGINE

AFTER INSTALLATION TEST FOR FUNCTIONAL START, THE ENGINE LIGHT STAY ON IN THE COCKPIT. FOUND BY OUR TECHNICIAN THAT THE RECEPTACLE PLUG ON THE STARTER PIN B GROUNDED ALL THE TIME. (TC NR 20080304006)

CA080414009

 

 

 

DISPLAY

INOPERATIVE

4/14/2008

 

 

 

7003652631

COCKPIT

FAIL AT INSTALLATION, AND CAME BACK OUT WITH THE SAME PROBLEM THAT WE SENT FOR REPAIR. DISPLAY BLANK OUT AFTER POWER UP O 5800145883,DATE REPAIR MARCH 14 2008.

CA080328005

 

 

 

DISTRIBUTOR GEAR

WORN

3/28/2008

 

 

 

10357586

MAGNETO

MAG WAS RECEIVED TIME EXPIRED FOR OVERHAUL. WHEN DISASSEMBLED THE WASHER THAT RETAINS THE NYLON GEAR ON THE SHAFT WAS FOUND LOOSE AND HAD ALMOST WORN TO THE POINT THAT IT COULD HAVE COME OFF THE END OF THE SHAFT AND RUBBED AGAINST THE COIL TAB OR CARBON BRUSH. THIS CONDITION HAS BEEN NOTICED IN MANY OTHER MAGS AND IN CONVERSATION WITH TCM WE HAVE BEEN TOLD TO PUT THE GEAR IN A PRESS AND FLARE THE END OF THE SHAFT OVER MORE TO RETAIN THE WASHER IF IT IS FOUND LOOSE. THE WASHER IN THIS CASE WAS WORN AND THIS PROCEDURE COULD NOT BE ACCOMPLISHED. THE DATE CODE (BATCH CODE) ON THE GEAR WAS `94`. THE GEAR WAS REPLACED DURING THE OVERHAUL AND THE MAG WAS RETURNED TO SERVICE. (TC NR 20080328005)

CA080328006

 

 

 

DISTRIBUTOR GEAR

WORN

3/28/2008

 

 

 

10357586

MAGNETO

MAG WAS RECEIVED TIME EXPIRED FOR OVERHAUL. WHEN DISASSEMBLED THE WASHER THAT RETAINS THE NYLON GEAR ON THE SHAFT WAS FOUND LOOSE AND HAD ALMOST WORN TO THE POINT THAT IT COULD HAVE COME OFF THE END OF THE SHAFT AND RUBBED AGAINST THE COIL TAB OR CARBON BRUSH. THIS CONDITION HAS BEEN NOTICED ON MANY OTHER MAGS AND IN CONVERSATION WITH TCM WE HAVE BEEN TOLD TO PUT THE GEAR IN A PRESS AND FLARE THE END OF THE SHAFT OVER MORE TO RETAIN THE WASHER IF IT IS FOUND LOOSE. THE WASHER IN THIS CASE WAS WORN AND THIS PROCEDURE COULD NOT BE ACCOMPLISHED. THE DATE CODE (BATCH CODE) ON THE GEAR WAS `94`. THE GEAR WAS REPLACED DURING THE OVERHAUL AND THE MAG WAS RETURNED TO SERVICE. (TC NR 20080328006)

CA080319003

 

GARRTT

 

NOZZLE

DAMAGED

3/11/2008

 

TPE33111U

 

31038294

FUEL 

THE A/C CAME INTO THE HANGER FOR A ROUTINE FUEL NOZZLE AND BOROSCOPE INSPECTION. DURING THE BOROSCOPE INSPECTION OUR NIGHT MAINTENANCE FOUND SOME DISCREPANCIES IN THE ENGINE. FURTHER INSPECTION FROM THE TURBINE SHOP IT WAS NOTED THAT THE NOZZLE SEGMENTS THAT MAKE UP THE NR 1 STATOR ASSEMBLY HAD SOME DAMAGE TO THEM. THE NOZZLE SEGMENTS WERE OVERHAULED FROM SOUTHWEST TURBINE. THE ENGINE WAS REPLACED AND FORWARDED TO THE ENGINE SHOP FOR FURTHER REPAIR. (TC NR 20080319003)

CA080414005

 

PWA  

 

DUCT

DAMAGED

4/11/2008

 

PT6A27

 

3012060

 

METAL SWARF FOUND INSIDE COOLING PASSAGES OF DUCT ASSY.

CA080221007

 

PWA  

 

ENGINE

MALFUNCTIONED

2/8/2008

 

PT6A68

 

PT6A68

 

(CAN) DURING A TRAINING MISSION, THE PILOT REPORTED HIGH ITT, VIBRATION AND FLAME FROM THE ENGINE EXHAUST AND ELECTED TO SHUTDOWN THE ENGINE. LANDED WITHOUT INCIDENT. ENGINE WILL BE REMOVED AND RETURNED FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080221007)

CA080415006

 

TMECA

 

BLADE

DAMAGED

4/11/2008

 

ARRIEL1B

 

 

TURBINE WHEEL

1ST STAGE TURBINE WHEEL BLADE LEADING EDGE DAMAGE IN ZONE 2 ON A TOTAL OF 8 BLADES. THE DAMAGE WAS CAUSED BY THE SEMI-CONDUCTOR OF THE IGNITER, P/N 9550175400, THAT DISLODGED ITSELF FROM THE HOUSING. THIS WAS FOUND DURING A SCHEDULED 100/150 HR ENGINE INSPECTION. THE AFFECTED MO3 HAS BEEN SEND TO MANUFACTURER FOR FUTURE INVESTIGATION. SUBSEQUENTLY ALL OTHER ENGINE IGNITER WHERE INSPECTED AND REMOVED FROM SERVICE DO TO LOOSENESS OF THE SEMI-CONDUCTOR. PICTURES WERE TAKEN AND SEND TO MANUFACTURER.

CA080402005

AEROSP

PWA  

 

TANK

LEAKING

3/14/2008

ATR42*

PW120

 

 

ENGINE OIL

DURING DESCENT, OIL MIST WAS NOTED IN THE CABIN FOLLOWED BY A LOW OIL PRESSURE WARNING INDICATION. THE ENGINE WAS SHUT DOWN BY THE CREW. TROUBLESHOOTING REVEALED LOW OIL LEVEL IN THE TANK, AND SIGNS OF EXTERNAL OIL LEAKAGE. THE ENGINE IS TO BE REMOVED FOR INVESTIGATION. P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20080402005)

CA080402010

AEROSP

PWA  

 

EEC  

MALFUNCTIONED

3/16/2008

ATR72

PW124B

 

 

ENGINE

DURING TAKEOFF ROLL, THE ENGINE TORQUE INDICATED 75 PERCENT. THE TAKEOFF WAS ABORTED AND AIRCRAFT TAXIED BACK TO THE RAMP. THE EEC WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. THE REMOVED UNIT WILL BE RETURNED FOR INVESTIGATION AND UPDATES PROVIDED TO TC. (TC NR 20080402010)

CA080402014

AEROSP

PWA  

 

ENGINE

POWER LOSS

3/21/2008

ATR72

PW127

 

 

 

DURING CLIMB, ENGINE POWER WAS LOST ACCOMPANIED BY A LOUD NOISE. THE ENGINE WAS SECURED AND THE AIRCRAFT RETURNED TO BASE. INITIAL INVESTIGATION REVEALED SEVERE ENGINE DAMAGE INCLUDING FRACTURE OF THE 2ND STAGE POWER TURBINE BLADES. P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20080402014)

CA080402019

AEROSP

PWA  

 

ENGINE

DAMAGED

4/1/2008

ATR72

PW127

 

 

 

THE CREW HEARD A LOUD NOISE ACCOMPANIED BY AN AIRCRAFT YAW. UPON POWER REDUCTION, THE ENGINE SHUT DOWN BY ITSELF. INITIAL INVESTIGATION REVEALS SEVERE INTERNAL ENGINE DAMAGE. THE ENGINE WILL BE INVESTIGATED AND UPDATES WILL BE PROVIDED. (TC NR 20080402019)

CA080221011

AEROSP

PWA  

 

GOVERNOR

LEAKING

2/17/2008

ATR72

PW127

 

 

PROPELLER

(CAN) DURING CRUISE, THE LOW OIL PRESSURE WARNING WAS ACTIVATED. THE CREW ELECTED TO SHUTDOWN THE ENGINE AND DIVERT THE AIRCRAFT TO AN ALTERNATE LANDING SITE. INITIAL INVESTIGATION REVEALED SIGNIFICANT EXTERNAL OIL LEAKAGE FROM THE PROPELLER OVERSPEED GOVERNOR AREA. THE COMPONENT WAS REPLACED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080221011)

CA080402017

AEROSP

PWA  

 

ENGINE

MAKING METAL

3/27/2008

ATR72201

PW124B

 

 

 

THE OIL PRESSURE INDICATION REDUCED TO ZERO FOLLOWED BY A LOUD NOISE, OIL MIST AND ODOR IN THE CABIN. THE ENGINE THEN FLAMED OUT. INITIAL INSPECTION REVEALED A CONTAMINATED CHIP DETECTOR AND THE PROPELLER DIFFICULT TO TURN. THE ENGINE IS TO BE REMOVED FOR INSPECTION AND UPDATES WILL BE PROVIDED.

DT1R200800001

AGUSTA

 

 

LEVER

DAMAGED

5/8/2008

A109S

 

 

1090020477

YAW TRIM SYSTEM

OPENED THE ACCESS PANEL UNDER THE CO-PILOT'S SEAT, FOUND THE YAW TRIM LEVER (PN 109-0020-47-7 NSN) DETACHED FROM THE YAW TRIM MOTOR SHAFT. NO DAMAGE NOTED TO THE MOTOR SHAFT. THE LEVER WAS INTACT BUT DAMAGED AT THE POINT WHERE IT CONTACTS THE SHAFT, BUT HAD THE CORRECT HARDWARE AND COTTER PIN INSTALLED. THE APPLICABLE PUSH-ROD END (ATTACHED TO THE LEVER) WAS ALSO LOOSE. INSPECTED AND RETORQUED THE ROD-END. REPLACED AND TORQUED THE LEVER, REINSTALLED TO THE YAW TRIM MOTOR SHAFT, AND COMPLETED OPERATIONAL CHECK WITH NO DEFECTS NOTED.

CA080409003

AIRBUS

GE  

 

OUTFLOW VALVE

MALFUNCTIONED

4/7/2008

A310300

CF680C2*

 

 

CABIN PRESSURE

AFTER 30 MIN IN CRUISE, CAB PRESSURE REG NR 2 FAULT, FOLLOWED BY CAB PRESSURE REG NR 1 FAULT. UNABLE TO CONTROL IN MANUAL. EMERGENCY DESCENT AND QAR PROCEDURES FOLLOWED. PAX MASK SYSTEM ACTIVATED IN AUTO. FLIGHT RETURNED TO STATION AT FL 10,000 FT. ACFT WAS REMOVED FROM SERVICE FOR INVESTIGATION.

CA080304005

AIRBUS

GE  

 

LINE

SPLIT  

2/27/2008

A310304

CF680C

 

A3248021101100

HYD SYSTEM

WHILE AIRCRAFT WAS UNDER MAINTENANCE IN THE HANGAR, THE HYDRAULIC RETURN LINE FOR YELLOW SYSTEM ALTERNATE BRAKE FAILED WITH A SPLIT IN THE TUBING APPROX 1.5 INCHES IN LENGTH. AT THE TIME OF THE FAILURE THERE WAS NO HYDRAULIC PRESSURE OR OPERATION OF THE SYSTEM. THE LINE WAS REPLACED AND SYSTEM TESTED SERVICEABLE. LINE WAS SENT TO AIRBUS FOR ANALYSIS. (TC NR 20080304005)

CA080305001

AIRBUS

GE  

 

PRESSURE SWITCH

MALFUNCTIONED

3/3/2008

A310304

CF680C

 

 

ENGINE OIL

DURING CLIMB AT 18000 FEET, NR 1 ENGINE OIL FILTER CLOGGED LIGHT CAME ON. AS PER QRH, NR 1 ENGINE WAS SHUT DOWN. AIRCRAFT RETURNED TO STATION WITH NO FURTHER PROBLEM. THE OIL FILTER WAS REPLACED. NO SIGNIFICANT CONTAMINATION WAS NOTICED. THE OIL SYSTEM WAS DRAINED AND SERVICED AS PER MM. THE OIL DIFFERENTIAL PRESSURE SWITCH WAS REPLACED. A TEST FLIGHT WAS PERFORMED AND THE ENGINE OIL INDICATION SYSTEM WAS NORMAL. AIRCRAFT WAS RETURN TO SERVICE.

CA080409001

AIRBUS

GE  

 

WIRE

BURNED

3/25/2008

A310304

CF680C2*

 

40900011

COFFEEMAKER

IN CRUISE AFT GALLEY RT COFFEEMAKER BURNED. ALL C/B’S WERE PULLED. HALON FIRE EXTINGUISHER WAS USED AS A PRECAUTIONARY MEASURE. C/B ON COFFEE MAKER FOUND POPPED. FOUND WIRES TO PRESSURE SWITCH BURNED AND DISCONNECTED. NO OTHER WIRING DAMAGE ON THE COFFEE MAKER. COFFEE MAKER REPLACED AND ROUTED TO SHOP FOR REPAIR.

CA080403007

AIRBUS

CFMINT

 

BEARING

OVERHEATED

3/19/2008

A319112

CFM565B6

 

 

RECIRC FAN

NEAR TOP OF CLIMB, COCKPIT ODOR OF ACRID BURNING SMELL NOTICED. NO ECAM OR VISUAL CUES. DURING CRUISE CHECK NOTICED FAN IN AMBER DISPLAYED ON COND PAGE. RECYCLED CAB FAN AND SMELL REOCCURRED IMMEDIATELY. RETURNED TO AIRPORT. THE SHOP REPORT INDICATED THAT THE REAR BEARING SEIZED, THE FRONT BEARING WAS DRY, THE FAN OVERHEATED BUT THE STATOR WAS ELECTRICALLY NORMAL. THE FAN WAS DIRTY AND SMELLED OVERHEATING.

CA080314008

AIRBUS

GE  

 

ENGINE

FAILED

3/13/2008

A319114

CFM565A

 

 

 

DURING CLIMB A LOUD BANG AND VIBRATION WAS FELT, FOLLOWED BY ENG 2 FAIL ON ECAM AT 8300 FT AND CLIMBING. LANDED SAFELY WITH NO ISSUE WITH LANDING. AFTER LANDING DEBRIS WAS FOUND IN ENGINE EXHAUST AND AFT CENTER BODY WAS DAMAGED. INVESTIGATION INTO CAUSE OF ENGINE FAILURE IS ON GOING AND SDR WILL UPDATED ACCORDINGLY. ENGINE HAS BEEN CHANGED. (TC NR 20080314008)

CA080228001

AIRBUS

GE  

 

UPLOCK

FAILED

1/19/2008

A319114

CFM565A

 

C247300016

NLG 

AFTER TAKEOFF, THE CREW COULD NOT RETRACT THE NOSE GEAR. THE GEAR WAS RECYCLED WITH NO SUCCESS. THE CREW RETURNED TO LAND AT DEPARTURE AIRPORT. THE NLG UPLOCK ASSEMBLY WAS REPLACED AND A LANDING GEAR SWING CARRIED OUT. DESCRIPTION/ROOT CAUSE, THE UNIT WAS SENT FOR REPAIR WITH THE REQUEST FOR A TEARDOWN REPORT. THE UNIT WAS PRE-TESTED AND FAILED THE LOCKING TEST. THE LOCK MECHANISM INSIDE THE UNIT FAILED TO LOCK THE HOOK. THE REPAIR FACILITY CONCLUDED THAT THE DRIED GREASE CAUSED THE LOCKING MECHANISM TO HANG UP AND PREVENTED THE HOOK FROM LOCKING THE NOSE LANDING GEAR. THE WEAR TO THE UNIT WAS NORMAL AND NO OTHER MECHANICAL DIFFICULTIES WERE OBSERVED. AT TIME OF THIS REPORT THE REPAIR ORGANIZATION WAS AWAITING INSTRUCTIONS TO PROCEED WITH REPAIR AND OR OVERHAUL. (TC NR 20080228001)

CA080222007

AIRBUS

CFMINT

 

BOLT

CORRODED

2/15/2008

A321211

CFM565B3P

 

201660001010

MLG 

(CAN) CORRODED FAIL SAFE BOLTS THAT SECURE MAIN LANDING GEAR SIDE STAY ATTACH PINS TO UPPER AND LOWER CARDAN PINS. BOLTS ARE ITEMS 290 AND 296 IN A321 IPC 32-11-18-02E. ITEM 290 IS AN AN6-56A AND ITEM 295 IS AN AN6-62. THE LOWER BOLT ITEM 295 IS HEAVILY CORRODED. (TC NR 20080222007)

PJ6G20080147

AIRTRC

PWC  

 

GAS GENERATOR

ERODED

4/14/2008

AT802

PT6A67AG

 

310718501

ENGINE

'C' FLANGE EROSION AT SCAVENGE TUBE OIL COUPLING WITH ASSOCIATED PARTIALLY SEVERED 'T' BOLT.

CA080414006

AIRTRC

PWA  

 

STATIC LINE

DETERIORATED

4/7/2008

AT802A

PT6A67A

 

08071

AUTO PILOT SYS

DURING RE-ACTIVATION OF THE AIRCRAFT, THE MAINTENANCE CREW NOTICED THAT THE STATIC LINE FOR THE AUTO PILOT ALTITUDE HOLD P/N 0807-1 WAS DETERIORATED AND CRACKED. THE LINE WAS REPLACED WITH A SERVICEABLE PART. ALL OTHER AIRCRAFT IN THE FLEET WILL BE INSPECTED FOR SERVICEABILITY.

2008FA0000324

BBAVIA

 

 

DISPLAY

DEFECTIVE

5/7/2008

7DC  

 

 

011097203

INSTRUMENT PANEL

PRIMARY FLIGHT DISPLAY PANEL HAS A MALFUNCTION IN THE COARSE/BAROMETRIC PRESSURE ADJUSTMENT KNOB. THE DESIGN INCORPORATES A DUAL FUNCTION TYPE CONTROL KNOB. THE CENTER KNOB ADJUSTS THE DESIRED NAVIGATIONAL COARSE DISPLAYED ON THE HSI NAV DISPLAY. THE OUTER KNOB ADJUSTS THE PRIMARY ALTIMETER BAROMETRIC PRESSURE SETTING. AT TIMES DURING FLIGHT ADJUSTMENT OF THE INNER COARSE KNOB RESULTS IN AN INADVERTENT CHANGE IN THE BAROMETRIC PRESSURE. THIS MALFUNCTION CAN BE QUITE DANGEROUS, ESPECIALLY WHEN SHOOTING AN INSTRUMENT APPROACH, PILOT CHANGES COARSE HEADING DURING AN APPROACH AND MAY, WITHOUT KNOWING, CHANGE THE BAROMETRIC PRESSURE THUS CAUSING THE ALTITUDE DISPLAY TO BE INACCURATE.

2008FA0000323

BBAVIA

LYC  

 

SLEEVE

CRIMPED

5/4/2008

7GCBC

O320A2D

 

183M 

RUDDER CABLE

RIGHT RUDDER CABLE SEPARATED AT RUDDER BELLCRANK DURING RECOVERY OF INTENTIONAL LEFT SPIN. CABLE APPARENTLY PULLED OUT OF NICOPRESS SLEEVE. AIRPLANE WAS LANDED AT KCHA, WITHOUT INCIDENT, AFTER DECLARING AN EMERGENCY.

CA080402018

BEECH

PWA  

 

GOVERNOR

MISRIGGED

3/17/2008

1900C

PT6A67B

 

 

PROPELLOR

TAKEOFF WAS ABORTED WHEN THE ENGINE WOULD NOT PRODUCE FULL POWER. INVESTIGATION REVEALED IMPROPER RIGGING OF THE PROP GOVERNOR.

2008FA0000326

BEECH

 

 

SPAR CAP

CRACKED

4/25/2008

E90  

 

 

00011001316

WING 

THE CRACK EMANATES FROM THE 5TH RIVET OUTBOARD OF THE LOWER FORWARD WING BOLT FITTING, 4TH RIVET FROM END OF SPAR CAP, IN THE FRONT ROW OF RIVETS, AND EXTENDS TO THE LEADING EDGE OF CAP. THE A/C PASSED 2-400 HOUR WING SIRM INSPECTIONS. 181 HRS INTO NEXT INTERVAL WAS WHEN CRACK WAS DETECTED DURING ROUTINE MAINTENANCE. BEECH HAS REDUCED INTERVAL FOR EDDY CURRENT INSP OF SPAR CAP TO 200 HRS DUE TO RECURRENCE OF THIS PROBLEM REF 8110-4 FOR N692M FOR SIMILAR DETAILS. A/C IS ON USFS CONTRACT.

CA080303005

BELL  

ALLSN

 

FUEL CONTROL

LEAKING

3/2/2008

206B

250C20

 

23034702

ENGINE

AFTER INSTALLING THE FCU, IT WAS NOTED THAT FUEL WAS LEAKING FROM LOWER THROTTLE ARM HOUSING. FCU WAS REMOVED. (TC NR 20080303005)

CA080221004

BELL  

PWA  

 

GEARBOX

MISMANUFACTURED

2/9/2008

212  

PT6T3B

 

PT6T3B

MAIN ROTOR

(CAN) MAINT WAS TROUBLESHOOTING OIL PRESSURE PROBLEMS. THE POWER SECTION ALWAYS APPEARED THAT IT HAD LOTS OF OIL. VISUAL INDICATION. THE OIL PRESSURE FLUCTUATIONS OCCURRED FEB. 5TH. IN THE TROUBLESHOOTING PROCESS A LITTLE OIL WAS BEING DRAINED AND YET THE VISUAL INDICATION THERE WAS LOTS OF OIL. ON FEB. 9TH THE PWR SECTION WAS REMOVED DUE TO LOSS OF OIL PRESSURE. A TECH REP WAS BROUGHT TO THE BASE AND IT WAS NOTICED THAT THE LOWER HOLE INTO THE GEARBOX OF THE OIL LEVEL INDICATOR WAS NOT DRILLED INTO THE CASE. SINCE THE OIL COULD NOT DRAIN OUT OF THE VISUAL INDICATOR THE OIL LEVEL APPEARED FULL. (TC NR 20080221004)

CA080411006

BELL  

ALLSN

 

TURBINE

DAMAGED

4/9/2008

407  

250C47B

 

23063354

ENGINE

ON THE THIRD MAIN ROTOR STROBING FLIGHT OF THE MORNING AND WHILE ACCELERATING FROM 100KTS TO 120KTS, A LOW HOWLING NOISE WAS HEARD WHICH INTENSIFIED RAPIDLY AND WAS FOLLOWED IMMEDIATELY BY AN ENGINE CHIP LIGHT. A FORCED LANDING WAS MADE TO A FIELD. AN EXTERNAL INSP INCH BY 4 INCH PIECE OF SHEET METAL WAS FOUND BROKEN AWAY FROM THE AFT RIGHT SIDE OF THE EXHAUST STACK. AFTER REMOVAL OF THE OUTER COMBUSTION CASE MAJOR VISIBLE DAMAGE WAS FOUND TO THE 1ST AND 2ND STAGE TURBINE BLADE TIPS. TURBINE SECTION IS BEING SENT TO STANDARD AERO LTD FOR INSPECTION WITH ROLLS ROYCE PARTICIPATION. 1ST AND 2ND TURBINE WHEEL CYCLES ARE 2004, 3RD AND 4TH STAGE CYCLES ARE 4977. ENGINE DATA COULD NOT BE DOWNLOADED FROM THE ECU, INDICATING MAJOR INTERNAL DAMAGE. SEVERE VIBRATION IS SUSPECTED TO HAVE CAUSED THE EXHAUST STACK DAMAGE.

CA080409006

BELL  

PWA  

 

BLADES

FAILED

3/30/2008

412  

PT6T3

 

 

COMPRESSOR TURB

ON APPROACH, THE CREW NOTED ENGINE TEMP AT APPROX 900 DEGREES FOLLOWED BY SOME NOISES. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT LANDED. INITIAL INVESTIGATION REVEALED LOSS OF COMPRESSOR TURBINE BLADE MATERIAL AND SHROUD SEGMENT MATERIAL, THE ENGINE WAS SENT FOR REPAIR.

CA080407007

BELL  

LYC  

BELL  

GEAR SET

SHEARED

4/5/2008

47G4

VO540B1B3

4762060025

R476204971

COOLING FAN

APPROX 100 HRS AGO TRANSMISSION WAS O/H AND NEW PMA GEAR SET WAS INSTALLED S/N GR586A FROM HELICOPTER TECH DURING FLIGHT PILOT HEARD AND FELT NOISE AND MADE A PRECAUTIONARY LANDING AND FOUND COOLING FAN DRIVE PULLEY AND APPROX 1.25 INCHES OF THE DRIVE SHAFT WAS MISSING. WE ARE SENDING IN REMAINING SHAFT SEGMENT WHERE IT SHEARED FOR METALLURGICAL ANALYSIS.

CA080411004

BOEING

PWA  

 

LINE

LEAKING

4/8/2008

727223

JT8D15

 

6517840330

HYD SYSTEM

AFTER TAKEOFF WHEN GEAR SELECTED UP, HYDRAULIC SYSTEM "A" LOW LEVEL LIGHT ILLUMINATED AND HYDRAULIC QUANTITY DROPPED TO 2.0 GAL. FLIGHT CREW DECLARED AN EMERGENCY AND RETURNED FOR APPROACH. PER FLIGHT CREW CHECKLIST GEAR WAS MANUALLY LOWERED HOWEVER FLIGHT CREW WAS UNABLE TO MANUALLY LOWER THE LT GEAR. TWO ATTEMPTS WERE MADE AND THEN THE FLIGHT CREW SELECTED ON ONE "A" SYSTEM HYDRAULIC PUMP TO GET THE LT GEAR DOWN AND LOCKED. THE PUMP WAS THEN TURNED OFF AGAIN. THE AIRCRAFT LANDED SUCCESSFULLY WITH NO ADDITIONAL FAULTS. MAINTENANCE PERSONNEL FOUND A PIN HOLE LEAK ON THE A SYSTEM HYDRAULIC RETURN LINE RETURNING FROM THE A SYSTEM HEAT EXCHANGER. A PERMANENT REPAIR WAS CARRIED OUT BY THE INSTALLATION OF A PERMASWAGE FITTING OVER THE DAMAGED AREA. A LEAK CHECK WAS PERFORMED AND THE REPAIR CHECKED SERVICEABLE. THE AIRCRAFT WAS THE JACKED AND A GEAR SWING AND MANUAL GEAR EXTENSION WAS CARRIED OUT. THE FREE FALL EXTENSION CHECK WAS PERFORMED AND THE GEAR CRANKING FORCE REQUIRED TO RELEASE THE LANDING GEAR WAS WITHIN THE LIMITS PUBLISHED IN THE MANUFACTURERS MAINTENANCE MANUAL. NO ADDITIONAL FAULTS WERE FOUND. THE AIRCRAFT WAS RELEASED FOR SERVICE.

CA080219004

BOEING

PWA  

 

SKID

DEFECTIVE

2/18/2008

727227

JT8D9A

 

65715611

TAIL SKID

(CAN) UPON GEAR RETRACTION, TAIL SKID LIGHT REMAINED ILLUMINATED. A/C RETURNED TO STATION WHERE SKID TIP WAS REPLACED, SWITCH CONTACT CONFIRMED AND A/C RETURNED TO SERVICE. (TC NR 20080219004)

CA080401010

BOEING

 

 

ARM  

CRACKED

4/1/2008

737490

 

 

65C330325

MLG ACTUATOR

WHILE PERFORMING CUSTOMER T/C (AD 99-10-12) INSPECTION OF MLG ACTUATOR BEAM ARM, UT INSPECTION FINDS THAT RT MLG ACTUATOR BEAM ARM IS CRACKED CYCLES/TSN ARE AIRFRAME. NO EVIDENCE THAT THIS PART HAS BEEN REPLACED SINCE A/C MANUFACTURE. (TC NR 20080401010)

CA080304003

BOEING

CFMINT

 

DIODE

OPEN

2/29/2008

737522

CFM563C1

 

IN3311B

 

EN ROUTE, AFTER SHUTTING OFF CENTER TANK BOOST PUMPS, LEFT CENTER, LEFT AFT AND RIGHT FORWARD LOW PRESSURE LIGHTS DID NOT ILLUMINATE. WINDOW HEAT LIGHTS FOR THE LEFT SIDE WINDOW AND RIGHT FORWARD WINDOW WERE NOT ILLUMINATED. INITIALLY NO MASTER CAUTION, THEN ANTI-ICE MASTER CAUTION. THERE WAS NO LE DEVICES INDICATION. ON DOWNWIND FOR LANDING, THE PRESSURIZATION WENT FROM AUTO TO STANDBY AND DUMPED PRESSURE. UPON LOWERING GEAR, NO GREEN LIGHTS. THE CREW OVERSHOT AND USED THE GEAR VIEWERS AND A FLY BY TO DETERMINE THE GEAR STATUS. AFTER SPEAKING WITH DISPATCH, THE LIGHTS WERE CYCLED THROUGH BRIGHT/DIM/TEST AND THE GEAR INDICATION RETURNED. THE AIRCRAFT WAS LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE WAS DISPATCHED TO THE SITE AND EXAMINED THE AIRCRAFT. THE DIMMING SYSTEM WAS FOUND TO WORK ONLY IN THE BRIGHT POSITION FOR THE ABOVE MENTIONED SYSTEMS. MEL 33-23 WAS APPLIED AND THE AIRCRAFT WAS FLOWN TO A MAINTENANCE BASE FOR REPAIR. ON EXAMINATION, THE DIODE THAT SUPPLIES DIMMING POWER FOR THE ABOVE SYSTEMS WAS FOUND UNSERVICEABLE AND REPLACED. THE MASTER DIM CIRCUIT CARD FOR THE RELATED DIM CIRCUIT WAS REPLACED AS WELL. THE ANTI-ICE MASTER CAUTION AND THE PRESSURIZATION SWITCH TO STANDBY WERE ANOMALOUS EVENTS AND COULD NOT BE DUPLICATED. SYSTEMS CHECKED SERVICEABLE. (TC NR 20080304003)

CA080408003

BOEING

RROYCE

 

CABIN PRESSURE

MALFUNCTIONED

4/4/2008

75728A

RB211535E437

 

 

 

AIRCRAFT C-GTDX DEPARTING FROM YYZ ON APRIL 4TH 2008, AROUND 7000 FT AN EICAS MSG AUTO PRESSURIZATION SYS 1 AND 2, AIRCRAFT RETURNED BACK TO YYZ AND REQUESTED FIRE TRUCKS ON ARRIVAL DUE TO OVERWEIGHT LANDING. TROUBLESHOOTING CARRIED OUT, BOTH PRESSURIZATION CONTROL UNITS AND STBY ALTIMETER REPLACED AS PRECAUTIONARY MEASURE. FLIGHT TEST CARRIED OUT SUCCESSFULLY. INVESTIGATION IS ON GOING.

CA080225007

BOEING

RROYCE

 

MONITOR

MALFUNCTIONED

2/21/2008

75728A

RB211535E437

 

6009580001

CABIN

(CAN) CREW REPORTED A BURNING SMELL IN THE CABIN JUST BEFORE LANDING. IN-FLIGHT ENTERTAINMENT WAS SELECTED OFF AND SMELL DISSIPATED. MAINTENANCE DETERMINED THAT THE SMELL WAS COMING FROM THE NR 7 MONITOR. (TC NR 20080225007)

CA080407004

BOMBDR

HNYWL

 

LEVER

LOOSE

4/4/2008

BD1001A10

AS90711A

 

1760A000004

MLG 

AFTER TAKEOFF, IT WAS REPORTED THAT THE CREW WERE UNABLE TO RETRACT THE FLAPS FROM THE 10 DEGREE POSITION TO THE 0 DEGREE POSITION. PRELIMINARY REPORT STATES THAT A LOOSE SCREW WAS FOUND INSIDE THE FLAP LEVER GUARD. THE FORWARD RIGHT SCREW LOCATED INSIDE THE GUARD WAS FOUND TO BE PROTRUDING SUFFICIENTLY TO PREVENT THE LEVER FROM MOVING FROM THE 10 DEGREE POSITION TO THE 0 DEGREE POSITION. ALL THREE REMAINING SCREWS WERE FOUND TO BE SECURE. A VISUAL AND TACTILE INSPECTION CAN BE PERFORMED TO ENSURE THAT ALL 4 SCREWS LOCATED INSIDE THE FLAP LEVER GUARD ARE SLIGHTLY COUNTERSUNK AND DO NOT SHOW ANY SIGNS OF LOOSENESS (REFER TO FIGURE1). PLEASE REPORT ANY ANOMALIES FOUND DURING THIS INSPECTION.

CA080404004

BOMBDR

PWC  

 

PUMP

FAILED

4/2/2008

DHC8400

PW150A

 

6617303

HYDRAULIC SYS

DURING CRUISE FL 120, NR 2 ENG HYD PRES CAUTION LIGHT ILLUMINATED. HYD NR 2 PRESS - 0 PSI - AFTER PERFORMING ABNORMAL CHECKLIST WITH PTU ON, PRESS 3000 PSI. UNEVENTFUL LANDING. MAINTENANCE CREW REPLACED THE NR 2 ENGINE DRIVEN HYDRAULIC PUMP.

CA080313004

BRAERO

RROYCE

 

ENGINE

MALFUNCTIONED

3/11/2008

HS7482A

DART5342

 

 

NR 2 

DURING APPROACH IN ICING CONDITIONS AND HEAVY PRECIPITATION, WHEN THE PILOT THROTTLED BACK, ENGINE NR 2 FLAMED OUT AND AUTO FEATHERED. THE PILOT DID NOT ATTEMPT TO RE-LIGHT AND LANDED WITH ONE ENGINE OPERATING. MAINTENANCE CHECKED THE OIL SCREEN, FUEL SCREEN AND FUEL TANK SUMPS. NO CONTAMINATION WAS FOUND. MAINTENANCE CONDUCTED HIGH AND LOW POWER ENGINE RUNS AS WELL AS AUTO-FEATHER CHECKS AND FOUND NO PROBLEM WITH THE ENGINE. ROLLS-ROYCE NOTICE TO OPERATES NO. 1142 IS DIRECTED TO THE FLIGHT CREWS TO "SWITCH ON THE ENGINE IGNITION SWITCHES WHEN MODERATE OR SEVERE ICING IS ENCOUNTERED". THE PILOT DID NOT HAVE THE ENGINE IGNITION SWITCHES SELECTED TO "ON" DURING THIS EVENT. THE PILOTS HAVE BEEN REMINDED OF THIS "NOTICE TO OPERATORS" TO ENSURE THIS PROCEDURE IS FOLLOWED. A CONFIDENCE FLIGHT WITH CREW ONLY WILL BE ACCOMPLISHED PRIOR TO THE AIRCRAFT RETURNING TO REVENUE FLIGHTS. (TC# 20080313004)

CA080318002

CESSNA

LYC  

 

STUD

BROKEN

2/26/2008

152  

O235L2C

 

 

CYLINDER

DURING WALK AROUND, PILOT NOTICED ENGINE OIL COVERING LT SIDE OF FUSELAGE AND EMPENNAGE. MAINTENANCE INSPECTED ENGINE AND FOUND ON NR 2 CYLINDER, ONE BROKEN THROUGH STUD. OIL WAS RUNNING DOWN THROUGH STUD AND EXITING CYLINDER BASE WHERE ATTACH NUT USED TO BE. OIL LEAK WAS NOT DISCOVERED DURING OR AFTER PREVIOUS NIGHT FLIGHT. (TC NR 20080318002)

CA080320010

CESSNA

LYC  

 

SWITCH

BROKEN

3/7/2008

172M

O320E2D

 

S16612

TE FLAPS

INTERNAL RETURN SPRING OF SWITCH BROKEN. TOGGLE NOT RETURNING TO NEUTRAL POSITION. SWITCH REPLACED WITH NEW. (TC NR 20080320010)

CA080404009

CESSNA

LYC  

 

CABLE

OUT OF ADJUST

4/4/2008

172N

O320H2AD

 

 

PILOT SEAT

FLIGHT CREW DISCREPANCY, PILOTS SEAT DOES NOT SLIDE BACK INTERMITTENTLY. SEAT REMOVED AND VISUALLY INSPECTED. REEL ASSEMBLY CABLE ADJUSTED AND SEAT FUNCTION TESTED WITH NO DEFECTS FOUND. SEVERAL AIRCRAFT IN OUR FLEET OF CESSNA 100 SERIES AIRCRAFT HAVE EXPERIENCED SIMILAR DISCREPANCIES, AND THE PASSENGER SEATED WAS UNABLE TO EXIT THE CABIN.

CA080320004

CESSNA

LYC  

 

GASKET

LOOSE

3/14/2008

172R

IO360L2A

 

365533

SERVO PLUG

SERVO PLUGS FOUND LOOSE UPON INSPECTION. SERVO PLUG SEALS REPLACED WITH NEW AS PER THE CONVERSATION WITH PRECISION AIRMOTIVE REPRESENTATIVE. ENGINE REMANUFACTURE DATE OF JULY 14, 2004 DOES NOT FALL WITHIN THE DATES SPECIFIED THAT ARE AFFECTED BY THE AIRWORTHINESS DIRECTIVE. HOWEVER, THE SERVO PLUGS WERE LOOSE. (TC NR 20080320004)

CA080320005

CESSNA

LYC  

PRECISIONWND

GASKET

LOOSE

3/14/2008

172S

IO360L2A

 

365533

FCU 

AD2008-06-51 FUEL INJECTION SERVO PLUGS, SERVO PLUGS FOUND LOOSE UPON INSPECTION. SERVO PLUG SEALS REPLACED WITH NEW AS PER THE CONVERSATION WITH PRECISION AIRMOTIVE REPRESENTATIVE.ENGINE REMANUFACTURE DATE OF SEPT. 8, 2005 DOES NOT FALL WITHIN THE DATES SPECIFIED THAT ARE AFFECTED BY THE AIRWORTHINESS DIRECTIVE. HOWEVER, THE SERVO PLUGS WERE LOOSE. RIGHT MAGNETO P-LEAD WIRE BROKEN. (TC NR 20080320005)

CA080320006

CESSNA

LYC  

PRECISIONWND

GASKET

LOOSE

3/14/2008

172S

IO360L2A

 

365533

FCU 

SERVO PLUGS FOUND LOOSE UPON INSPECTION. SERVO PLUG SEALS REPLACED WITH NEW AS PER THE CONVERSATION WITH PRECISION AIRMOTIVE REPRESENTATIVE. ENGINE REMANUFACTURE DATE OF AUG 18, 2005 AND THE FUEL SERVO WAS REPAIRED JULY 28, 2006 AND BOTH DO NOT FALL WITHIN THE DATES SPECIFIED THAT ARE AFFECTED BY THE AIRWORTHINESS DIRECTIVE. HOWEVER, THE SERVO PLUGS WERE LOOSE. (TC NR 20080320006)

2008FA0000320

CESSNA

LYC  

 

BEARING

FAILED

4/25/2008

177RG

IO360A1B6

 

S34691

ACTUATOR

WHERE THE ROD END BEARING ATTACHES TO THE LATERAL BOLT, FWD. THIS BEARING (S34691 FAILED AT THE BEARING END. THIS BEARING IS UNDER EXTREEM TENSION LOAD AND WAS ORIGINAL. AGE WAS A FACTOR IN FAILING. REPLACING THIS BEARING AT 1000 HR INTERVALS IS NECESSARY. DATE OF THE ACTUATOR WAS 10/77. (K)

CA080320007

CESSNA

LYC  

PRECISIONWND

GASKET

LOOSE

3/14/2008

182T

IO540AB1A5

 

365533

FCU 

AD2008-06-51 FUEL INJECTION SERVO PLUGS, SERVO PLUGS FOUND LOOSE UPON INSPECTION. SERVO PLUG SEALS REPLACED WITH NEW AS PER THE CONVERSATION WITH PRECISION AIRMOTIVE REPRESENTATIVE. ENGINE REMANUFACTURE DATE OF SEPT 8, 2004 DOES NOT FALL WITHIN THE DATES SPECIFIED THAT ARE AFFECTED BY THE AIRWORTHINESS DIRECTIVE. HOWEVER, THE SERVO PLUGS WERE LOOSE. (TC NR 20080320007)

CA080320013

CESSNA

PWA  

 

TUBE

FAILED

3/19/2008

208  

PT6A114A

 

891250

TIRE 

ON TAXI PILOT FELT AIRCRAFT PULLING TO ONE SIDE AND DISCOVERED FLAT TIRE. TIRE WAS CHANGED AND FLOWN BACK TO BASE. TIRE ASSY WAS DISASSEMBLED AND TUBE WAS FOUND BLOWN WITH ABOUT A FOUR INCH SPLIT IN IT. THE TUBE WAS ALSO FUSED TO THE INSIDE OF THE TIRE IN THE AREA OF THE BALANCE PATCH. THIS WAS THE ORIGINAL TIRE INSTALLED AT CESSNA FACTORY WHEN AIRCRAFT WAS DELIVERED. I AM REPORTING THIS DUE TO AN ABNORMAL NUMBER OF TUBES THAT WE HAVE HAD LET GO IN THE LAST MONTH. TALKING TO OTHER OPERATORS HAS INDICATED THAT OTHERS ARE HAVING THE SAME PROBLEM. I HAVE BEEN TOLD BY A TIRE COMPANY THAT THE BUTYL RUBBER TUBES ARE NOT WORKING WELL IN OUR COLDER CLIMATE. (TC NR 20080320013)

CA080314011

CESSNA

PWA  

 

BRUSHES

FAILED

3/6/2008

208B

PT6A114A

 

200SGL119Q2

STARTER

SLOW SPOOLING OVER ENGINE, ENGINE STARTER BRUSHES WORN OUT (TC NR 20080314011)

CA080305014

CESSNA

PWA  

 

ENGINE

STOPPED

12/20/2007

208B

PT6A114A

 

 

 

DURING FLIGHT AT 12000 FEET ENGINE POWER WAS LOST. THE AIRCRAFT WAS FORCED TO DITCH 25 MILES OFF COAST. CREW WAS RESCUED. INVESTIGATION REVEALED THAT THE ENGINE WAS MAKING NO POWER AT TIME OF IMPACT. THE FUEL PUMP DRIVE SHAFT REVEALED WORN AND FRACTURED DRIVE SPLINES. INVESTIGATION IS ONGOING, UPDATES WILL BE PROVIDED.

CA080328003

CESSNA

CONT

 

BRACKET

CRACKED

3/19/2008

210J

IO520J

 

12326231

HORIZONTAL STAB

DURING THE ANNUAL INSPECTION REINFORCEMENT BRACKET (P/N 12 32623-1) WAS FOUND TO HAVE A CRACK RUNNING FROM THE BOTTOM BOLT HOLE TO THE EDGE OF THE BRACKET. THE BRACKET IS ATTACHED TO THE REAR SPAR OF THE LT HORIZ STABILIZER. AFFECTED PART REPLACED. (TC NR 20080328003)

CA080328004

CESSNA

CONT

 

DOUBLER

CRACKED

3/19/2008

210J

IO520J

 

12120031

BULKHEAD

DURING THE ANNUAL INSPECTION A CRACK WAS DETECTED RUNNING FROM THE ANCHOR NUT RIVET HOLE TO THE EDGE OF THE DOUBLER PLATE, THIS BRACKET IS ATTACHED TO THE REAR FRAME AT STN 209, P/N 12120402-3. AFFECTED PART REPLACED. (TC NR 20080328004)

CA080328007

CESSNA

CONT

 

ARM  

BROKEN

3/27/2008

401B

TSIO520EB

 

150450018

MLG DOOR

DURING PILOT WALKAROUND THE RT MAIN GEAR DOOR WAS HANGING SLIGHTLY DOWN FROM RETRACTED POSITION. MAINTENANCE TO REPLACE PART. (TC NR 20080328007)

CA080410009

CESSNA

CONT

 

CYLINDER HEAD

CRACKED

3/12/2008

414  

TSIO520N

 

AEC631397SN2B22

ENGINE

PILOT FLYING IN CRUISE FLIGHT, WHEN HE HEARD A POP AND EXPERIENCED LOSS OF ENGINE POWER. FEATHERED PROPELLER AND LANDED AT NEAREST AIRPORT. ENGINE CYLINDER REPLACED.

CA080411007

CESSNA

PWA  

 

TUBE

LEAKING

4/7/2008

425  

PT6A112

 

0923150

NLG WHEEL

NOSE TIRE FOUND LOW ON POST FLIGHT INSPECTION BY 10 PSI. NOSE WHEEL ASSY REMOVED FOR TEAR DOWN AND INVESTIGATION. SPARE BUILT-UP WHEEL ASSY INSTALLED. TEAR DOWN SHOWED INNER TUBE HAD PIN HOLE IN OUTER CIRCUMFERENCE AT ONE END OF A FOLD MARK. NO OTHER FAULTS FOUND WITH TIRE OR TUBE.

CA080402002

CESSNA

PWA  

 

BLEED VALVE

MALFUNCTIONED

3/5/2008

560XL

PW545A

 

 

COMPRESSOR

THE CREW EXPERIENCED ENGINE VIBRATIONS, FOLLOWED BY AN EEC MANUAL LIGHT. ENGINE POWER INCREASED AS EXPECTED, BUT THE CREW WAS UNABLE TO FURTHER MODULATE POWER BY MOVING THE THRUST LEVER. THE ENGINE WAS SHUT DOWN AS A RESULT AND THE FLIGHT CONTINUED TO PLANNED DESTINATION. THE COMPRESSOR BLEED VALVE ASSEMBLY WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE COMPONENT WILL BE INVESTIGATED AND RESULTS FORWARDED FOR REVIEW. (TC NR 20080402002)

2008FA0000319

CESSNA

LYC  

 

UNKNOWN

UNKNOWN

12/25/2007

R182

O540J3C5

 

 

 

INFLIGHT FAILURE OF PART OR PARTS UNKNOWN WITH NO SYMPTOMS FROM WITHIN COCKPIT, IE: OIL PRESSURE, OIL TEMPERATURE, AND CYLINDER HEAD TEMPERATURES WERE ALL INDICATING WITHIN NORMAL RANGES. OUTWARD MANIFESTATIONS WERE EXCESSIVE BLOW-BY OIL ON BELLY OF THE AIRPLANE. OTHER MANIFESTATIONS WERE: AN INTERRUPTION IN THE SMOOTH MOVEMENT OF THE PROP (WHEN ROTATING BY HAND) AT THE SAME LOCATION IN THE ROTATION ON EVERY OTHER COMPLETE ENGINE ROTATION, IE: RELATED TO THE CAMSHAFT (720 DEGREES OF ROTATION). A CRACK IN THE LT SIDE OF THE ENGINE CASE OVER THE BASE OF THE NR 5 CYLINDER WHERE THE ENGINE CASE FARES INTO THE INTAKE VALVE PUSHROD TUBE. A CRACK IN THE RT SIDE OF THE ENGINE CASE OVER THE BASE OF THE NR 6 CYLINDER WHERE THE ENGINE CASE FARES INTO THE INTAKE VALVE PUSHROD TUBE. METAL DEBRIS WAS FOUND IN THE SUMP FILTER SCREEN AND IN THE SUMP. THE LARGEST PIECE OF DEBRIS MEASURED APPROXIMATELY A .2500 INCH CUBE. (K)

CA080409008

CNDAIR

 

 

PISTON

CRACKED

4/9/2008

CL2151A10

 

 

33130131

ACTUATOR

ANOTHER OPERATOR INFORMED OUR QUALITY ASSURANCE DEPARTMENT OF THEIR FINDING CRACKS IN THE ACTUATOR THREADED PORTION IN 5 OUT OF 7 ACTUATORS. INSPECTED ALL 14 OF OUR FLEET ACTUATORS AND FOUND 4 TO BE CRACKED ALSO.

CA080403008

CNDAIR

PWA  

 

SHAFT

SHEARED

4/1/2008

CL2151A10

CA3  

 

100243

ENGINE OIL

(CAN) JUST BEFORE TURNING BASE LEG FOR LANDING THE RT BMEP GAUGE FELL TO ZERO. NO OIL WAS OBSERVED LEAKING FROM ENGINE ALTHOUGH THE OIL QUANTITY WAS SLOWLY FALLING. LANDING WAS CARRIED OUT NORMALLY. ON ROLL OUT QUANTITY WAS READING 8 GALLONS, SO THE RT ENGINE WAS SHUT DOWN. MAINTENANCE DISCOVERED THAT THE SCAVENGE PUMP HAD INGESTED A PIECE OF A CASTLE NUT WHICH HAD BROKEN OFF ONE OF THE NUTS P/N 542 FROM ONE OF THE REDUCTION PINION GEAR SHAFTS. THIS HAD CAUSED THE FAILURE OF THE GEAR/SHAFT P/N 100243 IN THE ACCESSORY DRIVE CASE.

CA080408002

CNDAIR

GE  

 

CONTROL UNIT

FAILED

3/29/2008

CL600*

CF348C5

 

70745

TE FLAP MOTOR

PRIOR TO DEPARTURE FLIGHT CREW COMPLETED A STAB TRIM RESET. SHORTLY AFTER FLAP RETRACTION ON TAKEOFF, FLIGHT CREW RECEIVED AN AP TRIM IS ND ASSOCIATED WITH AN AP PITCH TRIM ‘CAUTION MESSAGE. SUBSEQUENTLY CREW RECEIVED A ELEVATOR SPLIT’ CAUTION MESSAGE. CREW FOLLOWED QRH, CIRCLED TO BURN OFF FUEL AND LANDED BACK AT DEPARTURE AIRPORT WITHOUT INCIDENT. MAINTENANCE CHECKED ELEVATOR TRIM POSITION FULL NOSE DOWN, NEUTRAL AND FULL NOSE UP OK. AUTO PILOT ELEVATOR SERVO OPERATION CHECKED OK. ELEVATOR SPLIT MESSAGE TROUBLESHOT PER FIM TASK OK. PROBLEM ISOLATED AS MDC DISPLAYED AN INTERNAL FAULT OF THE MOTOR CONTROL UNIT CHANNEL 2 INTERNAL HOLD ON RELAY. MOTOR CONTROL UNIT REPLACED. OPERATIONAL TESTS OF THE SSCU, STABILIZER TRIM, AND AUTOPILOT SYSTEMS CARRIED OUT SERVICEABLE.

CA080410005

CNDAIR

GE  

 

BPSU

UNSERVICEABLE

4/8/2008

CL6002B19

CF343A1

 

855D1009

RT FLAP SYS

ON DESCENT, CREW SELECTED AND RECEIVED FLAPS 8 DEGREES, WHEN THEY ATTEMPTED TO PROCEED TO FLAPS 20 CREW RECEIVED A FLAP FAIL MESSAGE. FLIGHT LANDED WITHOUT INCIDENT. FECU MESSAGE POINTED TO THE RT BPSU AS THE FAULT. THE RT BPSU WAS REPLACED, FLAP SYSTEM RIGGED AND FUNCTION CHECKED SERVICEABLE. THE A/C RETURNED TO SERVICE WITH NO FURTHER FAULTS.

CA080403002

CNDAIR

GE  

 

BPSU

MALFUNCTIONED

3/31/2008

CL6002B19

CF343A1

 

855D1009

 

THE POST MAINTENANCE TEST FLIGHT WAS UNSUCCESSFUL. THE CREW RECEIVED A FLAP FAIL CAUTION MESSAGE ON APPROACH WHEN THE FLAPS WERE SELECTED FROM 0 TO 8 DEGREES. THE FLAP ELECTRONIC CONTROL UNIT (FECU) CODES WERE RETRIEVED. THE RT BRAKE AND POSITION SENSOR UNIT (BPSU) WAS REPLACED AND RIGGED, THE LT BPSU WAS RE-RIGGED AND THE FECU WAS REPLACED FOR TROUBLESHOOTING. THE AIRCRAFT WAS RELEASED AND COMPLETED A SUCCESSFUL TEST FLIGHT. RT BPSU, P/N 855D100-9, S/N 372, TSN 24045:44, CSN 13150, TSR 20:02, CSR 12. FECU, P/N 601R93050-7, S/N 331, TSN 14405:58, CSN 10815, TSR 7938:28, CSR 6408. (TC NR 20080403002)

CA080402007

CNDAIR

GE  

 

WARNING LIGHT

ILLUMINATED

4/2/2008

CL6002B19

CF343B1

 

 

 

AT THE TOP OF DESCENT WHEN PULLING BACK POWER, THE CREW GOT THE "LOW OIL PRES WARNING" ON THE LT ENG, SHORTLY FOLLOWED BY THE LOW OIL PRES INDICATION. ALL OTHER PARAMETERS NORMAL. CREW THEN ACTIONED EMERGENCY PROCEDURES AND SHUT DOWN LT ENG AND LANDED. (TC NR 20080402007)

CA080320002

CNDAIR

GE  

 

CONNECTOR

DAMAGED

3/18/2008

CL6002B19

CF343B1

 

MS27473T20B4

FLUTTER DAMPER

TASK NR 27-34-05-710-801 WAS BEING PERFORMED ON THE ELEVATOR FLUTTER DAMPERS. IT FAILED THIS TASK FOR LOW FLUID LEVEL TRANSMITTER SWITCHES. THIS TASK WAS CALLED UP DURING THE AIRCRAFT`S PLANNED HEAVY INSPECTION. T HERE WERE NO REPORTED FAILURES WHILE THE AIRCRAFT WAS IN-SERVICE PRIOR TO THIS HEAVY MAINTENANCE VISIT. DURING THE COURSE OF TROUBLE SHOOTING, THE AME FOUND THE CONNECTORS P300 AND J300 CORRODED TO THE EXTENT THAT THE PINS M AND N BROKE OFF WHEN THEY WERE DISCONNECTED. SEVERAL OTHER PINS WERE ALSO FOUND DISCOLORED. CONNECTOR P/N MS27497T20B41S, BACKSHELL P/N HEX41-AB90-21A9-1, CONNECTOR P/N MS27473T20B41P AND BACKSHELL P/N HEX41-AB00-21A9-1 WERE REPLACED AND SYSTEM FUNCTION CHECKED "SERVICEABLE". AIRCRAFT RETURNED TO SERVICE. (TC NR 20080320002)

CA080409004

CNDAIR

GE  

 

CONTROLLER

OVERTEMP

3/30/2008

CL6002B19

CF343B1

 

601R3303313

WINDSHIELD TEMP

ON DESCENT THROUGH 21000 FEET INTO ARRIVAL AIRPORT, CAPTAIN’S LT WINDSCREEN SHATTERED. CREW DONNED OXYGEN MASKS AS A PRECAUTION. CREW DECLARED AN EMERGENCY WITH ATC AND MADE ANNOUNCEMENT TO THE PASSENGERS. FLIGHT LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE WINDSHIELD ASSEMBLY P/N 601R33033-13, S/N 01057H1890, TIMES AND CYCLES SAME AS THE TEMPERATURE CONTROLLER. MAINTENANCE ALSO REPLACED THE LT WINDSHIELD TEMPERATURE CONTROLLER SUSPECTING THAT IT HAS CAUSED AN OVERHEAT CONDITION.

CA080407003

CNDAIR

GE  

 

ACTUATOR

UNSERVICEABLE

4/6/2008

CL6002B19

CF343B1

 

852D1001921

FLAP 

ON APPROACH AT 4000 FT SELECTING FLAPS FROM 0 - 8 DEG, FLAP FAIL MSG APPEARED IMMEDIATELY WITH NO MOVEMENT OF FLAPS. AIRSPEED 215 AT THE TIME. A/C WAS AT -57 DEG FOR 1 HR IN CRUISE, GND -4. FECU INTERGRADED AND FOLLOWING FAULT CODES DISPLAYED AS FECU WAS LOOKED AT: (1) JAM (2) LEFT BPSU (3) 1 5 1B. TRIED TO GO FURTHER AFTER THE STEP OF `GO` IN THE FIM AND IT WOULD GIVE THE FAULT CODE 1 5 1B CB 1-F4 AND CB 2-F4 AND SYSTEM RESET WITH NO FURTHER FAULTS. FERRY FLIGHT PAPERWORK COMPLETED. A/C FERRIED. TROUBLESHOOTING GOING ON, ACTION PLAN TO INSPECT AND LUBE ALL DRIVES AND CHANGE ALL FLAP ACTUATORS WITH NEWLY OVERHAULED UNITS SENT. INFORMATION WILL BE UPDATED WHEN AVAILABLE.

CA080229001

CNDAIR

GE  

 

WINDOW

CRACKED

2/18/2008

CL6002B19

CF343B1

 

NP1393222

COCKPIT

FLT NR 6671 - FIRST OFFICER SIDE WINDOW CRACKED ON DESCENT INTO PSP. WINDOW REPLACED (TC NR 20080229001)

CA080229002

CNDAIR

GE  

 

ACTUATOR

CRACKED

2/21/2008

CL6002D24

CF348C1

 

4129T17G04

LT ENGINE

"925 PWM, LT ENG FAILURE ON SHORT FINAL. ON SHORT FINAL (APPROX 1500 FT) CAPT REPORTED LT ENGINE FAILURE. N1 WENT TO 32 PERCENT AND EICAS DISPLAYED LT FADEC AND LT BLEED CAUTION ME PERCENT. CAPT SAW NO OTHER ENGINE RELATED ANOMALIES, IE NO PROBLEMS WITH FUEL FLOW, ITT, OIL PRESSURE OR WARNINGS. CVR AND FDR CIRCUIT BREAKERS HAVE BEEN PULLED. AIRCRAFT VERIFIED NOT IMPOUNDED BY THE NTSB. CONTRACT MX INTERROGATE MDC. MDC REVEALED LH PS3 SENSE LINE, L FMU FAILED AND VG CMD\POSN DISAGREE. MX INSPECT INLET FOR POSSIBLE INGESTION, NO FINDINGS. EXHAUST AREA LOOKED GOOD AS WELL. OPENED COWLING AND INSPECTED VG ACTUATORS AND AREA. MX THOROUGHLY INSPECTING AREA. WE HAVE SENT MM/IPC REFERENCES OF AREAS TO INSPECT. MX FOUND THE SHAFT ACTUATOR THAT OPERATES ALL THE GV LINKAGES BROKEN. P/N IS 4129T17G04. GOING AOG. ACTUATING SYSTEM LINKAGE ASSY P/N 4128T48G09 FROM PHX ETA 1528 HFPU" (TC NR 20080229002).

CA080402008

DHAV

PWA  

 

BRUSHES

WORN

3/14/2008

DHC2MK3

PT6A34

 

 

STARTER/GEN

STARTER WOULD NOT OPERATE TO START ENGINE. (TC NR 20080402008)

CA080403009

DHAV

PWA  

 

MAIN BEARING

BROKEN

1/16/2008

DHC2MKI

R985AN14B

 

128495

MASTER ROD

DURING INSPECTION METAL PIECES FOUND IN ENGINE SUMP. INVESTIGATION DETERMINED THEM TO BE PART OF FLANGE OF MASTER ROD BEARING. ENGINE REMOVED FOR OVERHAUL.

CA080404001

DHAV

PWA  

 

SPAR

CORRODED

3/3/2008

DHC2MKI

R985AN14B

 

C2TP63ND

FUSELAGE

WHEN REPLACING FRONT CENTER SPAR DUE CRACK. REAR CENTER SPAR DISCOVERED CORRODED BEHIND CENTER MOUNT BRACKET. SPAR REPLACED. THIS CORROSION WAS NOT VISABLE UNTIL ACCESS TO INSIDE OF TAILPLANE WAS GAINED (TC NR 20080404001)

CA080328002

DHAV

PWA  

 

CYLINDER HEAD

SEPARATED

3/9/2008

DHC2MKI

R985AN14B

 

399353

NR 2 

HEAD SEPERATED FROM NR 2 CYLINDER AFTER 4.9 HRS AIRTIME. CYLINDER HEAD SEPARATION OCCURRED DURING CRUISE FLIGHT. UNEVENTFUL LANDING CARRIED OUT. REPLACEMENT CYLINDER HEAD INSTALLED AND AIRCRAFT COMPLETED ITS MISSION. (TC NR 20080328002)

CA080414001

DHAV

PWA  

 

SPAR

CRACKED

4/7/2008

DHC2MKI

R985AN14B

 

 

WING 

CRACKS FOUND WHILE COMPLYING WITH SB2/47. CRACKS JUST VISIBLE WITH FLUORESCENT PENETRANT INSPECTION. WHEN SPAR REMOVED CRACKS WERE VISIBLE TO NAKED EYE ON THE INTERIOR OF SPAR AND ON GUSSET BETWEEN SPAR AND GUSSET.

CA080404005

DHAV

GARRTT

 

SHUTOFF VALVE

UNSERVICEABLE

3/31/2008

DHC3

TPE33110R

 

39423091

FUEL SYSTEM

ENGINE WOULD NOT SHUT DOWN USING NORMAL SHUT DOWN PROCEDURES. EMERGENCY SHUTOFF PROCEDURES USED. TROUBLESHOOTING FOUND FUEL SHUTOFF VALVE U/S (SOLENOID STICKING). REPLACED FUEL SHUTOFF VALVE. ENGINE RUN-UP AND SHUT DOWN NORMAL. AIRCRAFT RETURNED TO SERVICE.

CA080407005

DHAV

PWA  

 

ENGINE

STOPPED

4/3/2008

DHC6100

PT6A20

 

PT6A20

 

AFTER A NORMAL TAKEOFF, THE CREW WENT THROUGH POWER 1, FLAPS UP AND POWER 2 AND AFTER SETTING POWER 2 PRIOR TO CLIMB CHECKS, THE CREW HEARD A LOUD POP AND SCRAPPING NOISE FROM THE NUMBER ONE ENGINE. THE FLIGHT CREW OBSERVED THAT THE NUMBER ONE PROPELLER WAS STOPPED AND ALL ENGINE GAUGES WERE AT ZERO. EMERGENCY CHECKLIST WAS FOLLOWED AND THE AIRCRAFT LANDED SAFELY WITH ONE ENGINE RUNNING. ENGINE TO BE REMOVED FOR EVALUATION BY REPAIR FACILITY.

CA080407010

DHAV

PWA  

 

CABLE

BROKEN

4/2/2008

DHC6200

PT6A20

 

 

STEERING

STEERING CABLE BROKE ON TAXI WHILE THE AIRCRAFT WAS PREPARING FOR TAKEOFF.

CA080401004

DHAV

PWA  

 

ENGINE

POWER LOSS

3/26/2008

DHC6200

PT6A20

 

 

LEFT 

ON TAKEOFF, THE LEFT ENGINE LAGGED BEHIND NOT PRODUCING MAX. POWER, TROUBLE SHOOTING FOUND THE TEMPERATURE COMPENSATOR UNIT LEAKING P3 AIR. THE PART WAS REPLACED AND THE PROBLEM WAS FIXED. (TC NR 20080401004)

CA080214007

DHAV

PWA  

 

HYDRAULIC LINE

CRACKED

1/21/2008

DHC8102

PW120

 

82970009325

HYDRAULIC SYS

(CAN) WHILE ENROUTE THE "IB ROLL SPL HYD" AND NR 1 "HYD ISO VLV" CAUTION LIGHTS ILLUMINATED. CHECKED THE HYD QUANTITY AND NOTICED NR 1 QUANTITY AT 1.0 AND DECREASING. COMPLETED THE QRH CHECKLIST AND THEN BRIEFED THE F/A AND PASSENGERS. MADE A VISUAL APPROACH AND LANDING WITHOUT ANY FURTHER EVENTS. MAINT INVESTIGATION DETERMINED THE LEAK TO BE FROM THE NR 1 HYD SYS PRESSURE MANIFOLD ENGINE DRIVEN PUMP INLET PRESSURE TUBE FLARE AND FITTING. THE FLARE WAS FOUND TO BE CRACKED AND THE FITTING HAD EVIDENCE OF PITTING CORROSION. THE TUBE AND FITTING WERE BOTH REPLACED IAW THE AIRCRAFT MM AND SUBSEQUENTLY TESTED SERVICEABLE. (TC NR 20080214007)

CA080414008

DHAV

PWA  

BFGOODRICH

BRAKE DISC

WARPED

3/28/2008

DHC8102

PW120A

 

 

MLG BRAKE ASSY

RAMP CREW NOTICED THAT RT INBOARD (NR 3) MAIN WHEEL WAS FLAT WHILE AIRCRAFT WAS PARKED AT GATE. MAINTENANCE DISCOVERED THE NR 3 BRAKE UNIT WITH A WARPED/OVERHEATED BRAKE DISKS WHICH CAUSED THE FUSE PLUGS ON THE NR 3 MAIN WHEEL TO BLOW. MAINTENANCE REPLACED THE NR 3 BRAKE UNIT AND THE NR 3 AND 4 MAIN WHEEL ASSEMBLIES. TAXI AND FUNCTION CHECKS OF THE BRAKING SYSTEM WERE COMPLETED WITH NO FURTHER FAULTS FOUND. WHEEL SHOP CONFIRMED BRAKE UNIT DID OVERHEAT AND THAT IT WAS NOT A FAULT WITH THE UNIT.

CA080402001

DHAV

PWA  

 

HEATER

SMOKE

3/31/2008

DHC8311

PW123

 

 

WINDSHIELD

(CAN) DURING CLIMB, THE CREW OBSERVED SMOKE IN THE COCKPIT AND QUICKLY NOTICED THAT THE SMOKE WAS COMING FROM THE LT WINDSHIELD ELECTRICAL TERMINALS. THE WINDSHIELD HEATING SYSTEM WAS TURNED OFF AND THE SMOKE STOPPED. DECISION WAS MADE TO TURN BACK AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. LINE MAINTENANCE DISCOVERED THAT THE LT WINDSHIELD L1 TERMINAL WIRE NR 3041-48B12C WAS BURNT. THE RT WINDSHIELD TERMINALS WERE INSPECTED AND THE L2 TERMINAL WIRE NR 3041-40A12NA WAS FOUND WITH BURNT MARKS. BOTH WIRES WERE REPLACED AND THE SYSTEM TESTED SERVICEABLE. THE AIRCRAFT WAS RELEASED AND A VERIFICATION FLIGHT WAS CONDUCTED. (TC NR 20080402001)

CA080408004

DHAV

PWA  

 

UPLOCK ROLLER

SEIZED

3/30/2008

DHC8311

PW123

 

101655

RH MLG

RT MLG FAILED TO EXTEND ON LANDING GEAR SELECTION, CREW PERFORMED GO-AROUND AND USED ALTERNATE GEAR EXTENSION. ALL LANDING GEAR EXTENDED AND NORMAL LANDING CARRIED OUT. MAINTENANCE INSPECTION FOUND RT MLG UPLOCK ROLLER SEIZED, ROLLER REPLACED, GEAR SWINGS COMPLETED AND AIRCRAFT RETURNED TO SERVICE. TIMES PROVIDED ARE SHOCK STRUT TIMES, ROLLER IS NOT SERIALIZED AND NOT TRACKED FOR ACTUAL TIMES.

CA080314007

EMB  

ALLSN

 

ENGINE

LEAKING

3/12/2008

EMB135ER

AE3007A

 

 

 

OIL IMPENDING BYPASS INDICATION ILLUMINATED ALONG WITH OIL TEMPERATURE RISING TO 141 DEGREES. THE PILOT COMMANDED THE SHUT DOWN OF THE ENGINE DUE TO OIL TEMPERATURE AND QUANTITY INDICATING THREE QUARTS. AIRCRAFT RETURNED TO CMH WITHOUT INCIDENT. MAGNETIC INDICATING PLUGS WERE FOUND CLEAN. A SMALL PUDDLE OF OIL IN FAN SECTION AND A LOT OF OIL IN THE EXHAUST WAS REPORTED. THE OIL FILTER WAS FILLED WITH CARBON DEBRIS. ENGINE HAS ACCUMULATED 0.8 HOURS SINCE LAST REPAIR AND THIS WAS THE 1ST FLIGHT SINCE REPAIRS. ENGINE UNDER INVESTIGATION, FURTHER REPORT WILL BE SUBMITTED AFTER ENGINE TEARDOWN. (TC NR 20080314007)

CA080314009

EMB  

ALLSN

 

BEARING

FAILED

3/10/2008

EMB145LR

AE3007A

 

 

NR 4 

ENGINE REMOVED FOR ITT EXCEEDANCE, AUTO IFSD, SMOKE IN COCKPIT/CABIN, OIL DEBRIS ON ALL CHIP DETECTORS. TEARDOWN OF ENGINE REVEAL NR 4 BEARING FAILURE AND ALSO NR 3 BEARING FAILURE. EXCESSIVE DAMAGE IN COMPRESSOR AREA DUE TO BOTH SUPPORTING BEARING FAILURE. FAILED COMPONENTS WILL BE SENT TO THE OEM FOR INVESTIGATION. (TC NR 20080314009)

CA080402011

EMB  

PWA  

 

ENGINE

POWER LOSS

3/4/2008

EMB312

PT6*

 

 

 

DURING TRAINING MANEUVERS, THE PILOT REPORTED A LOSS OF ENGINE POWER. PILOT ATTEMPTED TO RECOVER WITHOUT SUCCESS, AND EJECTED SAFELY. AIRCRAFT CRASHED IN AN EMPTY FIELD. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.

CA080222010

EMB  

GE  

 

FLOORBEAM

CORRODED

2/21/2008

ERJ170200SU

CF348E5A1

 

 

FUSELAGE

(CAN) CORROSION FOUND ON FLOORBEAM LOCATED AT Y = 272.0 AND Z = -490.0 JUNCTION WITH FRAMES 16, 17, 18 AND ON FLOORBEAM LOCATED AT Y = -272.0 AND Z = -490.0 AND ON FRAME NR 14 AT Y = -337.0 AND Z = -490.0 ALSO (3) SILL PLATES CORRODED BEYOND LIMITS. CORROSION WAS ALSO FOUND ON FRAME 87, 88, 89 AND 90 UNDER THE AFT RT GALLEY ATTACHMENT POINT AT FLOOR STRUCTURE. REFERENCE: PICTURE, AFT FUSELAGE, FORWARD FUSELAGE DUE TO NO ALLOWABLE REWORK LIMITS AVAILABLE IN THE SRM (STRUCTURAL REPAIR MANUAL) , ALL AFFECTED PARTS WHERE REPLACED OR REPAIRED AS MFG INSTRUCTION. THE ROOT CAUSE SEEMS TO BE THE LACK OF FLOOR PROTECTION UNDER THE FWD AND AFT GALLEYS. (TC NR 20080222010)

CA080303002

EMB  

GE  

 

CONTROL CABLE

DAMAGED

2/28/2008

ERJ170200SU

CF348E5A1

 

17005825401

AILERONS

DURING CONTROL CABLES INSPECTION ON LT AND RT WINGS, FOUND AILERON CABLES (LT P/N 170-05825-401) WORN AND WITH WIRES BROKEN AT FAIRLEADS, LOCATED AT LT WINGS INB OF THE RIB 17. THE WORN AREAS AND BROKEN STRANDS ARE LOCATED UNDER NYLON GROMMETS (P/N PE49068-501) MOUNTED ON THE FAIRLEAD. EMBRAER HAVE BEEN ADVISED (TC NR 20080303002)

CA080401005

EMB  

GE  

 

PIN  

MISINSTALLED

4/1/2008

ERJ170200SU

CF348E5A1

 

 

NLG 

DURING INSPECTION, FOUND NUT ON LOWER DRAG BRACE ATTACHEMENT HINGE PIN NOT SAFETIED WITH CUTTER PIN AND PRC ADRIFT SEE ATTACHEMENT. NO EVIDENCE OF WORK PREVIOUS ACCOMPLISHED ON THE NOSE GEAR.

CA080401008

EMB  

GE  

 

STRUT

LEAKING

3/13/2008

ERJ190100IGW

CF3410E5A1

 

2821A000003

LT MLG

DURING THE SERVICING OF THE LEFT MAIN GEAR IT AT BEEN NOTICE THAT THE AIR KEPT COMING OUT FROM THE OIL VENT VALVE. AS PER EMBRAER, TO FIX THE PROBLEM THE MAIN GEAR AS TO BE CHANGE AIR CANADA FLEET AS BEEN ADVISED AND SEEMS TO BE A KNOWN CONDITION (TC NR 20080401008).

CA080404006

EMB  

GE  

 

GENERATOR

FAULTED

3/31/2008

ERJ190100IGW

CF3410E5A1

 

1701320

APU 

ON FIN 309 WHILE T/S A LONG HISTORY FAULT OF APU GEN FAULT. ARCING WAS FOUND AT THE LUG T3 ATTACH POINT WITH THE APU GENERATOR. APU GENERATOR WAS REPLACED.

CA080222008

EMB  

GE  

 

CONTROL CABLE

WORN

2/22/2008

ERJ190100IGW

CF3410E5A1

 

19004209401

AILERON

(CAN) DURING CONTROL CABLES INSPECTION ON LT AND RT WINGS, FOUND AILERON CABLES (LT P/N 190-04212-401, P/N 190-04209-401, RT P/N 190 -05551-401, P/N 190-04209-401) WORN AND WITH SEVERAL WIRES BROKEN AT FAIRLEAD, LOCATED AT LT AND RT WINGS RIB 4A WS -3025.80 MIL. SPAR 2 IN MLG WHEEL WELL. THE WORN AREAS AND BROKEN STRANDS ARE LOCATED UNDER NYLON GROMMETS (P/N PE49068-501) MOUNTED ON THE FAIRLEAD. MFG WILL COME UP WITH AN SB END OF MARCH (TC NR 20080222008)

CA080319004

EMB  

GE  

 

SUPPORT

CRACKED

3/7/2008

ERJ190100IGW

CF3410E5A1

 

19093649001

MLG WW

ON AIRCRAFT A CRACK WAS FOUND TO MLG WELL BULKHEAD SUPPORT. THE CRACK STARTS AROUND ONE OF THE ATTACHMENT HOLES AND GOES UP TO THE MIDDLE OF DISTANCE BETWEEN THE TWO ATTACHMENT HOLES. THE BULKHEAD IS ALSO FLEXING AND CONTACTING THE LOWER SECTOR OF THE AILERON CONTROL QUADRANT. PROBLEM ALSO FOUND ON THE FOLLOWING A/C FIN NUMBER: 307, 309, 311, 313, 315, 317, 318, 319, 320, 322, 323, 324, 326, 332 (TC NR 20080319004)

CA080404007

GULSTM

RROYCE

 

APU  

LEAKING

3/29/2008

GIV  

TAYMK6118

 

GTCP36150G

 

APU AUTO SHUT DOWN WITH LOW OIL PRESSURE FAULT. OIL QTY RE-ADJUSTED AND APU STILL SHUT DOWN FOR LOW OIL PRESSURE. REPLACED OIL PRESSURE SWITCH AND APU STILL SHUT DOWN INTERMITTENTLY. AFTER TROUBLE SHOOTING WITH DIRECT OIL PRESSURE GAUGE FOUND OIL PRESSURE DELIVERY WITH INTERMITTENT LOW OIL PRESSURE READING. SUSPECTING OIL PUMP OR PRESSURE REGULATOR. LOANER APU INSTALLATION IN PROGRESS, MORE INFO WILL BE GIVEN WHEN REPORT OF REPAIR SHOP WILL BE GIVEN.

2008FA0000333

ISRAEL  

 

 

INDICATOR

INOPERATIVE

4/25/2008

1124

 

 

 

OXYGEN MASK

PASSENGER OXYGEN MASK FLOW INDICATOR INOPERATIVE. THIS UNIT CAME FROM LOT LC 0521 K OR LOT LC 0526K

CA080319008

PAC  

PWA  

 

ENGINE

POWER LOSS

3/6/2008

CRESCO

PT6A34AG

 

 

 

DURING TAKEOFF ROLL, A NOISE WAS HEARD ACCOMPANIED BY LOSS OF ENGINE POWER. THE TAKEOFF WAS ABORTED. INITIAL INSPECTION REVEALED FRAGMENTS SIMILAR TO COMPRESSOR BLADE MATERIAL DISTRIBUTED THROUGHOUT THE INLET. TEARS IN THE INLET SCREEN WERE NOTED. THE ENGINE HAS BEEN REMOVED AND WILL BE INVESTIGATE ROOT CAUSE ONCE ESTABLISHED.

2008FA0000330

PILATS

PWA  

BFGOODRICH

BRAKE DISC

BROKEN

5/2/2008

PC12

PT6A67B

 

244755

 

WHILE REMOVING RIGHT MAIN WHEEL ASSEMBLY DISCOVERED THE OUTBOARD BRAKE DISC OF THE RIGHT BRAKE BROKEN INTO TWO PIECES. REPLACED RIGHT BRAKE ASSEMBLY.

2008FA0000331

PILATS

PWA  

BFGOODRICH

BRAKE DISC

BROKEN

5/6/2008

PC12

PT6A67B

 

244755

 

FLIGHT CREW REPORTS RIGHT BRAKE GRABBING. REMOVED RIGHT MAIN TIRE ASSEMBLY AND DISCOVERED THE OUTBOARD BRAKE DISC WAS BROKEN INTO TWO PIECES. REPLACED THE RIGHT BRAKE ASSEMBLY.

CA080225006

PILATS

PWA  

HARTZL

HUB  

LEAKING

2/21/2008

PC1245

PT6A67B

HCE4A3D

 

PROPELLER

(CAN) PROPELLER REMOVED DUE TO EXCESSIVE GREASE LEAK FROM BLADE CLAMPS. (TC NR 20080225006)

2008FA0000332

PILATS

PWA  

BFGOODRICH

BRAKE DISC

BROKEN

5/6/2008

PC1245

PT6A67B

 

244755

BRAKE ASSY

FLIGHT CREW REPORTS LEFT BRAKE GRABBING. REMOVED LEFT MAIN TIRE ASSEMBLY TO INVESTIGATE DISCREPANCY AND DISCOVERED THE OUTBOARD BRAKE DISC BROKEN INTO THREE PIECES. REPLACED THE LEFT BRAKE ASSEMBLY.

CA080408001

PILATS

PWA  

 

ATTACH FITTING

CRACKED

4/8/2008

PC1245

PT6A67B

 

4030082SRS

PAX SEAT

DURING 100 HOUR INSPECTION PASSENGER SEAT RECLINE HYDRAULIC MOUNT ATTACHMENT FOUND CRACKED. SEAT MANUFACTURER IS ERDA. NOT FOUND IN ASSEMBLY MANUFACTURER LIST. REPAIR INFORMATION REQUESTED THROUGH AIRCRAFT MANUFACTURER, PILATUS.

2008FA0000322

PIPER

 

 

SOLENOID

SHORTED

5/5/2008

PA28161

 

 

701122223

STARTER

WHEN MASTER SWITCH TURNED ON PROP BEGAN TO ROTATE UNCOMMANDED. TROUBLESHOT TO STUCK STARTER SOLENOID. SOLENOID REPLACED, OPS CHECK GOOD.

2008FA0000318

PIPER

LYC  

 

CRANKSHAFT

CRACKED

4/22/2008

PA28181

O360A4M

 

13B27134

ENGINE

AC WAS FLYING AT 5000 FT, WHEN ENGINE STARTED TO LOSE POWER AND FAILED. AC LANDED SAFELY IN A FIELD. ENGINE WAS FOUND TO BE LOCKED UP. ENGINE WAS DISASSEMBLED AND COMPONENTS INSPECTED. CRANKSHAFT WAS FOUND TO HAVE CRACK, CAUSING ENGINE TO LOCK UP. PROBABLE CAUSE: UNDERTERMINED AT THIS TIME. (K)

CA080303003

PIPER

LYC  

 

BEARING

FAILED

2/29/2008

PA31350

TIO540J2BD

 

 

ALTERNATOR

IN CRUISE, THE PILOT NOTICED THE RT ALTERNATOR WARNING LIGHT CAME ON. CHECKED THE BREAKER BUT IT HAD NOT BLOWN. PULLED BREAKER AND LANDED UNEVENTFULLY. MAINTENANCE INSPECTED THE RT ALTERNATOR AND DISCOVERED THAT THE ALTERNATOR BEARING HAD SEIZED AND BROKEN THE BELT. (TC NR 20080303003)

CA080402006

PIPER

LYC  

 

TAPPET

CRACKED

3/28/2008

PA31350

TIO540J2BD

 

72877

NR 1 CYLINDER

WHEN REPLACING NR 1 CYLINDER THE HYDRAULIC TAPPET BODY WAS FOUND CRACKED IN TWO PLACES. (TC NR 20080402006)

2008FA0000317

RAYTHN

 

PARKERHANFIN

BOLT

SHEARED

5/6/2008

G36  

 

 

10320400AN53

ZONE 700

THE PILOT REPORTED A "POP" AS HE WAS GROUND HANDLING THE AIRCRAFT ON THE RAMP (IN A STRAIGHT DIRECTION USING AN AIRTUG). FURTHER INVESTIGATION REVEALED 1 NUT/BOLT COMBINATION HAD SHEARED ON THE INBOARD WHEEL HALF OF THE RIGHT MAIN LANDING GEAR ASSEMBLY. THE BOLT HAD SUBSEQUENTLY BACK OUT APPROXIMATELY 1/4 INCH. THIS AIRCRAFT HAS BEEN THROUGH 1 ANNUAL INSPECTION AND HAS NEVER HAD THE WHEEL HALVES DISASSEMBLED. UPON DISCOVERY OF THE SHEARED BOLT, THE LEFT AND RIGHT WHEELS WERE DISASSEMBLED, CLEANED, INSPECTED AND REASSEMBLED WITH NEW BOLTS AND NUTS. DURING DISASSEMBLY OF THE WHEEL HALF RETAINING BOLTS IT WAS NOTED THAT VERY LITTLE FORCE WAS REQUIRED TO BREAK THE NUTS LOOSE. THE NOSE WHEEL WAS THEN CHECKED FOR PROPER TORQUE AND DETERMINED, WITH THE USE OF A DIAL INDICATOR TORQUE WRENCH, THAT THE INSTALLED TORQUE WAS APPROXIMATELY 40 IN/LBS. THE TORQUE SPECIFICATION FOR THE NOSE WHEEL IS 90 IN/LBS AND THE MAIN WHEELS ARE 150 INCH/LBS.

CA080414003

ROBSIN

LYC  

 

GEAR

WORN

4/10/2008

R44RAVENII

IO540AE1A5

 

 

STARTER GEN

UPON POST FLIGHT INSPECTION, STARTER TEETH FOUND WORN, REMOVED AND INSTALLED NEW STARTER.

CA080414004

ROBSIN

LYC  

 

CLUTCH ACTUATOR

MALFUNCTIONED

4/10/2008

R44RAVENII

IO540AE1A5

 

 

MAIN ROTOR

UPON INSPECTION, CARRIED OUT METHOD 2 AND THE ACTUATOR KEPT RUNNING .

CA080314021

SNIAS

TMECA

 

ENGINE

MAKING METAL

2/9/2008

AS350B3

ARRIEL2B

 

 

 

ON THE FIRST GROUND RUN OF THE DAY DURING GROUND WARM UP, A NOISE WAS EMITTED FROM THE ENGINE AND IMMEDIATLEY AFTER NOISE WAS HEARD THE ENGINE CHIP LIGHT ILLUMINATED. PILOT SHUT ENGINE DOWN. METAL PARTICLES WERE FOUND ON MOS CHIP PLUG AND SOME ON THE ELECTRIC CHIP PLUG. ENGINE WAS REMOVED AND SENT TO TURBOMECA MONTREAL FOR INSPECTION AND REPAIR. WE WERE LUCKY THIS DID NOT HAPPEN IN THE AIR AS WE WOULD BE LOOKING AT A TOTAL ENGINE FAILURE. (TC NR 20080314021)

CA080406001

SNIAS

TMECA

 

LINE

BROKEN

3/31/2008

AS350BA

ARRIEL1B

 

0301037950

FUEL CONTROL

TUBE WAS DISCOVERED CRACKED AND SEPARATED FROM FLARE AT P2 TAP END DURING ROUTINE INSPECTION. ORIGINALLY, BLACK DEPOSITS WERE NOTICED AT B-NUT AND WHEN DISASSEMBLED, FOUND COMPLETE FAILURE OF TUBE FROM FLARE END. CLOSE TOLERANCE FIT OF TUBE PROBABLY PROHIBITED ANOMALY FROM BEING NOTICED EARLIER.

CA080403005

SWRNGN

GARRTT

 

WINDSHIELD

CRACKED

3/31/2008

SA226T

TPE33110U

 

2621126905

COCKPIT

IN LEVEL CRUISE AT FLIGHT LEVEL 220 APPROXIMATELY 25 MINUTES AFTER DEPARTURE, THE LEFT HEATED WINDSHIELD SUDDENLY SHATTERED. ATC WAS ADVISED AND DESCENT REQUESTED FOLLOWED BY REQUEST FOR RETURN TO CYWG. AFTER ESTABLISHING THE RETURN COURSE AND LEVELING AT 9000 FEET, THE PASSENGERS WERE BRIEFED AND THE AIRCRAFT PROCEEDED BACK AT REDUCED CRUISE SPEED AND COMPLETED A NORMAL LANDING. UPON WINDOW REMOVAL NO DISCREPANCIES WERE NOTED WITH THE PREVIOUS INSTALLATION, ALL ATTACHING HARDWARE WAS CORRECT.

CA080320003

SWRNGN

GARRTT

 

FRAME

CRACKED

3/12/2008

SA226TC

TPE33110UA

 

2724050083

CARGO DOOR

DURING AN AGING AIRCRAFT INSPECTION A CRACK WAS DETECTED VISUALLY EXTENDING FROM THE LOWER AFT LATCH (POSITION 8). WHEN THE DOOR WAS REMOVED FOR REPAIR FURTHER CRACKS WERE DISCOVERED TO THE ATTACHING STRUCTURE FOR BOTH LOWER LATCHES (POSITIONS 7 AND 8). THIS FAILURE IS BELIEVED TO BE THE RESULT OF FATIGUE, AND IF REMAINED UNDETECTED COULD EVENTUALLY RESULT IN FAILURE OF THE CARGO DOOR. IT SHOULD ALSO BE NOTED THAT AD 98-06-25 REQUIRES AN INSPECTION OF THE LATCHING SYSTEM. (TC NR 20080320003)

CA080404002

SWRNGN

GARRTT

 

SHAFT

FAILED

3/26/2008

SA226TC

TPE33110UA

 

 

HYD PUMP

DURING A ROUTINE INSPECTION OF THE HYDRAULIC PUMP, THE RETAINING BOLT WHICH HOLDS THE SPLINE DRIVE INTO THE HYDRAULIC PUMP HAD SHEARED.

CA080415005

SWRNGN

GARRTT

 

WINDSHIELD

CRACKED

4/12/2008

SA226TC

TPE33110UA

 

2719442004

COCKPIT

DURING THE RETURN LEG TO MAIN BASE THE AIRCRAFT EXPERIENCED A RT HEATED WINDSHIELD CRACK IN A SPIDER WEB FASHION. THE AIRCRAFT DESCENDED THE CABIN DIFF WAS LOWERED AND AIRSPEED REDUCED. UPON WINDOW REMOVAL NO DISCREPANCIES WERE NOTED WITH THE PREVIOUS INSTALLATION, ALL ATTACHING HARDWARE WAS CORRECT.

CA080319007

SWRNGN

GARRTT

 

SWITCH

INTERMITTENT

3/6/2008

SA227AC

TPE331*

 

EN516

LT MLG

ON APPROACH, THE CREW NOTICED THAT THE LT GEAR HAD NO "GREEN" SAFE LIGHT. FLY BY WAS CARRIED OUT CONFIRMED GEAR DOWN. AIRCRAFT LANDED WITHOUT INCIDENT. SWITCH WAS FOUND STICKY. SWITCH REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20080319007)

CA080228011

SWRNGN

GARRTT

 

BELLCRANK

MISSING

2/27/2008

SA227AC

TPE3311

 

2752003042

NLG 

DURING MAINTENANCE GEAR RETRACTION A "CLICKING" NOISE WAS HEARD FROM THE NOSE GEAR WHEELWELL. THE ROLLER BEARING ON THE RT NOSE GEAR BELLCRANK WAS BROKEN AND ONLY THE INNER RACE REMAINED ON THE BOLT. THE BELLCRANK WAS REPLACED, GEARSWINGS CARRIED OUT AND AIRCRAFT RETURNED TO SERVICE (TC NR 20080228011)

CA080228012

SWRNGN

GARRTT

FRCHLD

PIN  

DAMAGED

2/20/2008

SA227AC

TPE3311

 

MS171536

RH TORQUE KNEE

PIVOT PIN FOR RT MAIN GEAR TORQUE KNEE WAS PROTRUDING FROM THE TORQUE KNEE. SPRING PIN REMOVED AND INSPECTED. NO DAMAGE FOUND. NEW SPRING PIN INSTALLED. NO FURTHER PROBLEMS SINCE REPLACEMENT OF SPRING PIN (TC NR 20080228012)

CA080403003

SWRNGN

GARRTT

 

TUBE

CRACKED

3/31/2008

SA227AC

TPE33111U

 

8945682

ENGINE

DURING TAKEOFF, THE CREW NOTED THE LT ENGINE WAS A LITTLE LOW ON POWER. DECIDED TO RETURN TO THE AIRPORT AS THE FUEL FLOW INDICATION FOR THAT ENGINE WAS ERRATIC. THE LANDING WAS UNEVENTFUL. ONCE ON THE GROUND THE AIRCRAFT WAS INSPECTED BY MAINTENANCE AND THEY DETERMINED THE LINE FROM THE FUEL FLOW TRANSMITTER TO THE FUEL FLOW DIVIDER HAD SPLIT AT A BEND RADIUS IN THE TUBE CAUSING A SOMEWHAT LARGE FUEL LEAK. THE LEAK WAS ENOUGH TO AFFECT ENGINE PERFORMANCE. THE LINE WAS FOUND TO BE INSTALLED CORRECTLY WITH NO EXISTING DAMAGE TO THE LINE OR AREA OF THE SPLIT. THE AGE OF THE LINE COULD NOT BE ACCURATELY DETERMINED BUT IT WAS IN VERY GOOD CONDITION AND THE PART NUMBER WAS CORRECT FOR THE ENGINE INSTALLATION. THE LINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER ENGINE PERFORMANCE PROBLEMS.

CA080415004

ZLIN

LYC  

 

CONTROL CABLE

FRAYED

4/8/2008

Z242L

AEIO360A1B6

 

Z4243130000

TE FLAPS

FLAP CENTER CABLE WAS FOUND FRAYED DURING REGULARLY SCHEDULED MAINTENANCE.

 

END OF REPORTS