ADs - Steel Aviation

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ADs FAA Airworthiness Directives Compliance Record Company: Category: Airframe Manufacturer: Cirrus Design Corp. Model: SR22 ssue Number ffective Date mendment# 006-21 -03 11/17/2006 ©ATP o detect and correct anti-ice fluid istribution lines with improperly installed ompression fittings,contd. o prevent in-flight failure of the cabin oor, which could' result in door separation rom the airplane o prevent the possibility of jamming of the dder-aileron interconnect system, which ay result in loss of,contd. o prevent moisture from accumulating long the wing shear web where it may reeze in certain conditions o correct pick-up collar support fasteners fthe CAPS, which could result in the o detect, correct, & prevent overheating amage to the brake caliper piston 0 -ring eals, which could,contd. Position: PIN: S/N: 2493 07/14/2016 I :38 PM Aircraft Registration No: N215JP ATP Revision: 07/07/2016 acility Cert No. I Type uthorized By Signed BAVIATION 3349690/A&P 1/8 Issue Number ffective Date mendment# 000-08- 51 E 412812000 ©ATP o prevent an in-flight engine shutdown due o a failed fuel servo diaphragm, and amage to the airplane o prevent excessive hydraulic lifter wear, hi ch can result in loss of engine power & oss of control of the airplane uperseded by 20 I 0- 11 -04 Superseded by 2009-24-52 o prevent loss of engine power due to racks in the cylinder head & possible ngine failure caused,contd. o prevent crankshaft connecting rod ·ournal fracture, which could result in total ngine power,contd. Superseded by 2000-23- 21 o prevent crankshaft failure due to rankshaft cheek cracks, which could result ·n total engine power loss,contd. Method of IA AVSTAR FUEL ERVONOT NSTALLED IA BY ENGINE ATE OF ANUFACTURE ND NO LIFTERS HANGED IA BY ENGINE ATE OF ANUFACTURE IA BY ENGINE ANUFACTURE ATE 07/14/2016 1:38 PM ext Due rs: rs: rs: rs: rs: rs : rs: Facility ert No. I Type uthorized By igned 318 Issue Number Effective Date Amendment# Description 99 -09- 17 L Superseded by 99- 19 - 01 K>412211999 Category: Propeller Manufacturer: Hartzell Propeller Model: PHC-J3YF- l ssue Number ffective Date mendment# 007-26-09 1/3012008 002-09-08 611312002 o prevent failure of the propeller blade rom fatigue cracks in the aluminum blade hank radius, which can,contd. o prevent blade failure that could result in eparation of a propeller blade and loss of ontrol of the airplane Superseded by 2007-26-09 o prevent propeller failure of the propellers Method of (:om plied Compliance ~rs: ""'· '-' · Position: PIN: SIN: FPS619B rs: NIA PROPELLER OT SERVICED BY SOUTHERN ALIFORNIA PROPELLER SERVICES etumed to service by BASCO, & possible rs: IA PROPELLER OT SERVICED BY 3- 16 - 14 110511994 ©ATP oss of airplane control Recurring] TO PREVENT POSSIBLE ROPELLER HUB FAILURE DUE TO RACKS THAT ORIGIN ATE IN THE REASE FITTING HOLES ON HE, CONTD. Recurring] Superseded by 94- 17-13 ASCO IABY PROPELLER SIN 07/14/2016 1:38 PM kecur Next Due N Hrs: "'· '-'· ext Due rs: rs : Facility Cert No. I Type Authorized By Signed I ATP Revision: 0710712016 acility ert No. I Type uthorized By igned B AVIATION 3496901A&P 4/8 Issue Number Effective Date Amendment# Description 89-22-05 L [Recurring] Superseded by 93 - 16 - 14 11/16/1989 77 - 12-06 R(2) Recurring] Superseded by 2002-09-08 12/21/1977 r?5-07 -05 Superseded by 77-12-06 ps10111977 r?4 -15-02 Superseded by 77- 12 -06 p110111914 r?3-I0-03 Superseded by 77-12-06 01/01/1973 70-02-01 Superseded by 73- 10 -03 01101/1970 70 - 16 -03 R Superseded by 77-12-06 01/01/1970 Category: GPS/NA V/COM Manufacturer: GARMIN Model: GNS 430 ssue Number ffective Date mendment# ©ATP Method of lcomplied Comoliance Hrs: t: !Hrs : t: !Hrs: t: Hrs: t: Hrs: t: !Hrs: t: Hrs: C: . .Position: P/N: SIN: ethod of Com liance 07/14/2016 1:38 PM Recur !Next Due y l-lrs: ~. IV· y l-lrs: ~ . IV· N Hrs: ,-, . ...... N Hrs: ,-,. '-'· N Hrs: ,-, . '-' · N Hrs: ,-,. '-'• N Hrs: ,-.. '-'• Facility Cert No. I Type !Authorized By !Signed II II I I I I I ATP Revision: 07/07/2016 acility ert No. / Type uthorized By igned 5/8 Issue Number Effective Date Amendment# Description Category: Magnetos Manufacturer: Teledyne Continental Model: SC-20 SERIES ssue Number ffective Date mendment# 8-09-07 R3 1/17/1983 ©ATP [Recurring] To prevent failure of the agneto impulse coupling assembly and ossible engine failure Recurring] Superseded by 2005-12-06 0 PREVENT MAGNETO FAILURE ND SUBSEQUENT ENGINE FAILURE 0 PREVENT INJURY OR DEATH TO ROUND PERSONNEL DUE TO A NON- ROUNDED MAGNETO 0 PREVENT FAILURE OF IMPULSE OUPLING DUE TO IMPROPERLY EAT TREATED (SOFT) FLYWEIGHTS SULTING IN ENGINE,CONTD. [Recurring] Superseded by 96-12-07 Method of Complied Compliance Position: PIN: 10 -50056- 101 SIN: D07BAl42 IA BY MAGNETO SIN 07/14/2016 1:38 PM Recur Next Due ext Due rs: rs: rs: rs: rs: Facility Cert No. I Type Authorized By Signed ATP Revision: 07/07/2016 acility Cert No. I Type uthorized By igned B AVIATION 349690/A&P 6/8 ssue Number ffective Date mendment# 3-07-04 1011111973 Category: Magnetos Manufacturer: Teledyne Continental Model: SC-20 SERIES ssue Number ffective Date mendment# ©ATP [Recurring] To prevent failure of the agneto impulse coupling assembly and ossible engine failure [Recurring] Superseded by 2005-12-06 0 PREVENT MAGNETO FAILURE D SUBSEQUENT ENGINE FAILURE 0 PREVENT INJURY OR DEATH TO ROUND PERSONNEL DUE TO A NON- ROUNDED MAGNETO 0 PREVENT FAILURE OF IMPULSE OUPLING DUE TO IMPROPERLY HEAT TREATED (SOFT) FLYWEIGHTS ESULTING IN ENGINE, CONTD. Method of Position: PIN: 10 -500556- 101 SIN: DOTCA 197 IA BY MAGNETO SIN NIA BY MAGNETO SIN IA BY MAGNETO SIN 07114/2016 1:38 PM ext Due rs: rs: ATP Revision: 07107 12016 acility ert No. I Type uthorized By igned B AVIATION 3496901A&P 7/8 ssue Number ffective Date mendment# 8-09-07 R3 1/1711983 3-07-04 10/1111973 -20,-200,-1200 SERIES MAGNETOS Category: Ignition Systems Manufacturer: ACS Products Company Model: IGNITION SWITCHES ssue Numher ffective Date mendment#