FAA Airworthiness Directive Compliance Record

Transcription

1 Effective Categy Cessna Aircraft Company Airframe /17/ /11/ /5/ /4/ /26/ /17/1979 FAA Airwthiness Directive Compliance Recd 1751 W. Kearney Ave. Lincon, NE Rept Produced By: Silverhawk Aviation TO DETECT CRACKS AND BOLT LOOSENESS WHICH COULD LEAD TO INFLIGHT SEPARATION OF THE FIN AND THE RUDDER TO PREVENT MALFUNCTION OF THE P/N C OR P/N FUEL SELECTOR VALVE TO PRECLUDE INCREASED FLIGHT CONTROL FORCES CAUSED BY AN AUTOPILOT ACTUATOR THAT HAS FAILED TO DISENGAGE, CONTD. TO DETECT BINDING OF FUEL QUANTITY TRANSMITTER FLOAT ARMS AND ASSURE PROPER OPERATION OF THE FUEL, CONTD. TO PROVIDE INSTRUCTIONS FOR RECOGNITION OF FUEL SYSTEM VAPOR BLOCKAGE AND OPERATING PROCEDURES TO RESTORE, CONTD. TO PREVENT A POSSIBLE FUEL LEAK CAUSED BY THE INSTALLATION OF SYMBOLIC DISPLAYS, INC. FUEL, CONTD. P210N by model number by model number by s/n by s/n by s/n, STC not installed Printed 5/13/2013 4:48:43PM Page 1 of 11 P Auth. By

2 Effective Categy Cessna Aircraft Company Airframe /13/ /2/ /27/ R2 11/15/ /15/ /6/1985 FAA Airwthiness Directive Compliance Recd 1751 W. Kearney Ave. Lincon, NE Rept Produced By: Silverhawk Aviation TO PRECLUDE THE POSSIBILITY OF ELECTRICAL OR ELECTRONIC COMPONENT DAMAGE OR AN IN-FLIGHT FIRE, CONTD. TO PREVENT LOSS OF ROLL AXIS FLIGHT CONTROL TO FURTHER REDUCE THE POSSIBILITY OF ENGINE DETONATION AND IMPROVE THE AIRPLANE CLIMB PERFORMANCE TO ENSURE THE INTEGRITY OF THE ENGINE EXHAUST SYSTEM TO PREVENT LOSS OF VACUUM- DRIVEN-ATTITUDE INSTRUMENTS RESULTING FROM FAILURE OF THE SINGLE AIRBORNE, CONTD. TO ELIMINATE THE POSSIBILITY OF LOSS OF THE FUEL SELECTOR ROLL PIN INSTALLATION P210N by s/n by autopilot system model installed by s/n, modified by STC, subject exhaust system not installed by s/n by s/n Printed 5/13/2013 4:48:43PM Page 2 of 11 P Auth. By

3 Effective Categy Cessna Aircraft Company Airframe R1 8/9/ /4/ /7/ /24/ /26/ /4/1991 FAA Airwthiness Directive Compliance Recd 1751 W. Kearney Ave. Lincon, NE Rept Produced By: Silverhawk Aviation TO PREVENT ENGINE POWER INTERRUPTION DUE TO LOSS OF ATTACHMENT OF THE ENGINE CONTROLS P210N TO PREVENT POSSIBLE SEPARATION OF THE TURBOCHARGER OIL RESERVOIR OUTLET FITTING AND SUBSEQUENT RAPID LOSS, CONTD. TO ELIMINATE THE POSSIBILITY 5/21/1987 OF ENGINE POWER REDUCTION DUE TO CONTAMINATED FUEL TO PREVENT POWER LOSS OR FIRE DUE TO FAILURE OF CERTAIN AEROQUIP 601 HOSE ASSEMBLIES TO PRECLUDE MAGNETO MOISTURE CONTAMINATION, WHICH COULD RESULT IN DUAL MAGNETO FAILURE, ENGINE, CONTD. TO PREVENT FUEL LEAKAGE CAUSED BY DAMAGED FUEL LINES, WHICH COULD RESULT IN AN IN-FLIGHT FIRE, modified by STC, turbo not installed PCW by s/n, not equipped, mags not installeed by s/n Printed 5/13/2013 4:48:43PM Page 3 of 11 P Auth. By

4 Effective FAA Airwthiness Directive Compliance Recd 1751 W. Kearney Ave. Lincon, NE Rept Produced By: Silverhawk Aviation Categy Cessna Aircraft Company Airframe TO PREVENT LOSS OF ENGINE 7/22/1994 POWER CAUSED BY INADVERTENT FUEL LOSS OR INADEQUATE FUEL SERVICING /31/ /3/ R1 9/22/ /5/ /13/2002 P210N 12/1/2007 TO PREVENT LOSS OF ENGINE OIL CAUSED BY LOOSE OR SEPARATED OIL FILTER ADAPTERS, WHICH COULD RESULT IN ENGINE,CONTD. TO PREVENT FUEL, OIL, OR 12/1/2007 HYDRAULIC SYSTEMS FAILURE CAUSED BY A COLLAPSED HOSE TO MINIMIZE THE POTENTIAL HAZARDS ASSOCIATED WITH OPERATING THE AIRPLANE IN SEVERE ICING CONDITIONS,CONTD. To prevent feign material from entering the fuel system and engine, which could result in loss of engine power,contd. To detect and replace structurally deficient hizontal stabilizer attachment brackets 12/1/ /1/2007 6/29/2012 PCW BY CHECKING FUEL QUANTITY CALIBRATION BY TCM ENGINE NOT INSTALLED PCW, DETERMINED BY HOSE TYPE INSTALLED PCW BY INSERTING COPY OF AD TEST IN APPROPRIATE SECTION OF POH DUE TO ENGINE CONVERSION VERIFIED BY LOG BOOK REVIEW, NO HORIZONTAL STAB BRACKET PARTS REPLACED REPLACED DURING THIS TIME PERIOD Printed 5/13/2013 4:48:43PM Page 4 of 11 P Auth. By

5 FAA Airwthiness Directive Compliance Recd 1751 W. Kearney Ave. Lincon, NE Rept Produced By: Silverhawk Aviation Content Revision: 5/10/2013 Effective Categy Cessna Aircraft Company Airframe C To prevent erroneous indications 1/5/2009 from the altimeter, airspeed, and vertical speed,contd /17/ /5/2012 P210N 7/12/ To prevent seat slippage the seat 7/12/2012 roller housing from departing the seat rail, which may consequently cause,contd. To prevent structural failure of the 7/12/2012 wing with consequent loss of control VERIFIED BY LOG BOOK REVIEW, NO ALTERNATE STATIC SOURCE VALVE REPLACED DURING THIS TIME PERIOD C/W BY VISUAL INSPECTION SECTION G, VISUAL AND DIMENSIONAL INSPECTION OF SEAT RAILS, HOOKS, PINS, AND ROLLERS C/W BY VISUAL INSPECTION REF. PARA (g)(3) P Auth. By /2013 Printed 5/13/2013 4:48:43PM Page 5 of 11

6 Effective Rolls-Royce Cpation /8/ /18/ /23/ R1 6/3/ R1 C 2/28/ /1/1989 FAA Airwthiness Directive Compliance Recd 1751 W. Kearney Ave. Lincon, NE Rept Produced By: Silverhawk Aviation Categy Engine TO ENSURE ADEQUATE LIFE LIMIT MARGIN FOR P/N'S AND SECOND STAGE TURBINE WHEELS TO PREVENT ENGINE POWER LOSS RESULTING FROM BLEED VALVE DIAPHRAGM FAILURE TO PRECLUDE POSSIBLE ENGINE FAILURE RESULTING FROM POWER TURBINE COUPLING NUT FAILURE TO PRECLUDE POSSIBLE ENGINE POWER LOSS RESULTING FROM THIRD STAGE TURBINE WHEEL BLADE SEPARATION, CONTD. ENGINE POWER LOSS RESULTING FROM PARTIAL BLADE AND/OR SHROUD SEPARATION OF SLOTTED THIRD STAGE TURBINE WHEELS TO PREVENT POSSIBLE ENGINE OVER-TEMPERATURE, LOSS OF THROTTLE RESPONSE, OR UNSCHEDULED POWER INCREASE 250-B17F/2 BY MFG DATE BY MFG DATE BY MFG DATE BY MFG DATE BY MFG DATE BY MFG DATE Printed 5/13/2013 4:48:43PM Page 6 of 11 CAE Auth. By

7 FAA Airwthiness Directive Compliance Recd 1751 W. Kearney Ave. Lincon, NE Rept Produced By: Silverhawk Aviation Content Revision: 5/10/2013 Effective Rolls-Royce Cpation /26/ /7/ C 12/19/ /26/ /7/2006 Categy Engine TO PREVENT BEARING FAILURE DUE TO BEARING SEPARATOR INSTABILITY, WHICH CAN RESULT IN SUBSEQUENT TURBINE,CONTD. TO PREVENT MAIN FUEL CONTROL (MFC) BELLOWS ASSEMBLY LEAKAGE, WHICH CAN RESULT IN AN UNCOMMANDED MINIMUM,CONTD. To prevent uncontained release of power turbine blades & disk fragments caused by engine overspeed, resulting,contd. To prevent tie bolt failure that could cause loss of engine power, resulting in a first stage turbine,contd. To minimize the risk of sudden loss of engine power and uncommanded shutdown of the engine due to fuel,contd. 250-B17F/2 BY MFG DATE BY MFG DATE BY MFG DATE BY MFG DATE BY MFG DATE CAE Auth. By Printed 5/13/2013 4:48:43PM Page 7 of 11

8 Effective Hartzell Propeller /11/ R 8/22/ C 10/16/ /4/2009 FAA Airwthiness Directive Compliance Recd 1751 W. Kearney Ave. Lincon, NE Rept Produced By: Silverhawk Aviation Categy Propeller TO PREVENT PROPELLER BLADE FAILURES DETECTION OF BLADE CRACKS AND POSSIBLE BLADE FAILURES To prevent propeller hub, blade, blade clamp failure, which can result in loss of aircraft control To prevent separation of the propeller blade counterweight slug, which could lead to injury and damage to,contd. HC-B3TF-7 EXA /12/ by blade s/n by blade design number by hub s/n C/W BY REFERENCING PARA (3) SUB (3) BOTLS ARE NOT FROM EFFECTED LOT # Auth. By Printed 5/13/2013 4:48:43PM Page 8 of 11

9 Effective Bob Fields Aerocess R1 5/1/2000 FAA Airwthiness Directive Compliance Recd 1751 W. Kearney Ave. Lincon, NE Rept Produced By: Silverhawk Aviation Categy Appliance To prevent smoke & a possible fire in the cockpit caused by overheating of the electric do seal inflation,contd. Inflatable Do Seals 7/12/ VERIFIED PROPER DOOR MOTOR INSTALLED PER SB BFA-001, INSTALLED REQUIRED PLACARDS P/N 3904 AND 3902 Auth. By Printed 5/13/2013 4:48:43PM Page 9 of 11

10 FAA Airwthiness Directive Compliance Recd 1751 W. Kearney Ave. Lincon, NE Rept Produced By: Silverhawk Aviation Content Revision: 5/10/2013 Effective Garmin International /9/ /23/2005 Categy Appliance Superseded by To prevent interrogating aircraft from possibly receiving inaccurate replies, due to suppression,contd. GTX 330 7/12/ BY M/N INSTALLED Auth. By Printed 5/13/2013 4:48:43PM Page 10 of 11

11 FAA Airwthiness Directive Compliance Recd 1751 W. Kearney Ave. Lincon, NE Rept Produced By: Silverhawk Aviation Content Revision: 5/10/2013 Effective Shadin /23/2006 Categy Appliance To prevent ADC-2000 units, P/Ns A-1-S-8, A-2-S-8, and A-3-S-8,contd. ADC /12/ BY SHADIN UNIT NOT INSTALLED Auth. By Printed 5/13/2013 4:48:43PM Page 11 of 11