PTZ-AD 2004

Številka PTZReferenčna PTZDatum efektiveRok izvršitveProizvajalecVsebina PTZReferenčni SB
001-04 PTZENAC_2004-022.pdf26.1.2004As established in the referenced Bolletino Tecnico, as of the effective date of this AD unless already accomplished.AGUSTA-BELL, AB 205A1, AB 212 and AB 412Main hydraulic servo actuator rod end locker washer inspection and replacement of. 
002-04 PTZCAA-AD-T-005-2004.pdf12.2.2004Before next flightLetecke zavody (former LET a.s.), L 23 Super-BlanikNDT inspection of elevator rocker lever.MB_L23-48a.pdf
003-04 PTZLBA_D-2004-060_R1.pdf30.1.2004Immediately and up to the issuance of a new ADDIAMOND AIRCRAFT, H 36 DimonaDaily inspection of the propeller control rods 
004-04 PTZLBA_D-2004-084.pdf4.2.2004Until 30.04.2004SCHEMPP-HIRTH, Duo DiscusChech the bonding between the upper spar cup and the spar web.Technical Note
No 396-9 dated 30.01.2004
005-04 PTZDGAC_F-2004-022_Urgent_.pdf12.2.2004Before 05.03.2004AIRBUS, A319, A320, A321Identify the SN and PN of both MLG sliding tubes 
128-02 R2 PTZDGAC_2002-556(B)R2.pdf4.2.2004 AIRBUS, A319, A320, A321CANCELLATION NOTICE 
006-04 PTZDGAC_F-2004-018(B).pdf14.2.200430.04.2004AIRBUS, A319, A320, A321Limitation items 
007-04 PTZDGAC_F-2004-019(B).pdf14.2.2004Before 30.10.2005AIRBUS, A319, A320, A321APUSB A320-24-1106
008-04 PTZFAA_AD_2004-03-08.pdf15.3.2004Prior to accumulation of 3000 total flight hours or within 1200 flight hours or 1 year after effective date of this AD, whichever occurs first.LEARJET, 31, 31A, 35, 35A (C-21A), 36 and 36A airplanesInspection of the shear webs of the forward engine beams for crackingBombardier SB 31-51-2 or 35/36-51-3
009-04 PTZCF-2004-01.pdf20.2.2004Within 1000 ours air-time after the effective date of this ADBombardier, Regional Jet CL-600-2B19Engine Throttle Control Gearbox. Repeat the inspection at intervals not to exceed 1000 hours air-time.SB 601R-76-019 dated 21 August 2003.
010-04 PTZDGAC_UF-2004-026.pdf25.2.2004Within 10 flying hoursEUROCOPTER, EC 120Check: - the tightening torque load of the connecting part attachment bolts - the connecting part for cracksAlert telex No. 67A014
011-04 PTZFAA_AD_2003-24-07.pdf9.2.2004Within 150 hours TIS after 09.02.2004 install the inspection hole and conduct visual inspection before further flightThe New Piper Aircraft, Inc. Models PA-31, PA-31-300, PA-31-325, PA-31-350, PA-31P, PA-31T, PA-31T1, PA-31T2, PA-31T3 and PA-31P-350 AirplanesInstall aninspection hole and conduct a detailed visual inspection of the rudder torque tube and associated ribs for corrosion.SB 1105A
012-04 PTZEU-2006-0162.pdf10.2.2004Superseeded by 036-06 PTZ (EU-2006-0162)AIRBUS, A319, A320 and A321 aircraftLife limits/Monitored Parts - MPD Section 9-1 
008-03 R1 PTZDGAC_F-2003-002(A)_R1.pdf28.2.2004Within the compliance times specified in this AD.EUROCOPTER, AS 350 helicoptersRotor flight controls - Cyclic stickAS 350 ASB 67.00.24
127-02 R1 PTZDGAC_F-2002-555(B)_R1.pdf28.2.200428.02.2004AIRBUS, A319, A320 and A321 aircraftCertified Limitations - Life limited parts. CANCELLATION NOTICE . This AD is replaced by
DGAC_F-2004-032(B).pdf
 
013-04 PTZCF-2004-04.pdf23.2.2004Part A: within 14 days; Part B: according with the schedule in this ADBombardier, CL-600-2C10 and CL-600-2D24 (CRJ-700 and CRJ-900 Series)Fuel Ejector Leak Check 
113-03 R1 PTZDGAC_F-2003-465(A)_R1.pdf3.3.2004Within 50 flight hours for helicopters which have logged 500 FH or more and no later than at 550 FH for helicopters that have logged less than 500 FH.EUROCOPTER, EC 120 helicoptersTail rotor - Tail rotor drive shaft damper.Alert Telex No. 65A004 R1
101-03 R2 PTZDGAC_F-2003-368(A)_R2.pdf13.3.2004Within 300 FH or 12 months (whichever occurs first) following the aircraft delivery or the latest replacement done of the 3 gimbal joints of aileron and elevator controls or within 50 FH from the effective date of this AD inspect the gimbal joints.EADS SOCATA, TB9, TB10, TB200, TB20 and TB21Flight controls - Gimbal joint aileron and elevator control inspection.EADS_Socata_SB_10-130-27_JAN04.pdf
012-03 R2 PTZ 7.4.200401.05.2004Vsi zrakoploviUporaba radijskih postaj s 25 kHz kanalno razdelitvijo. 
014-04 PTZCF-2004-05.doc23.3.2004Before next flightBell, 206A, 206B, 206L SeriesTail Rotor Blade Trailing Edge Skin CracksASB 206-04-100 Rev. A in ASB 206L-04-127 Rev. A
013-04 R1 PTZCF-2004-04R1.pdf8.4.2004Part A: within 14 days; Part B: within 3 days of the effective date; Part C: within 14 days; Part D: according with the schedule in this ADBombardier, CL-600-2C10 and CL-600-2D24 (CRJ-700 and CRJ-900 Series)Fuel Ejector Leak Check 
015-04 PTZDGAC_F-2002-281-091_R1(A).pdf27.3.2004No later then within 100 hours FH or within 1 month (whichever is reached first); Before installing an HSI KI 525AEUROCOPTER, AS 350 helicoptersNavigation - Horizontal situation indicator KI 525A 
016-04 PTZDGAC_F-2002-282-009_R1(A).pdf27.4.2004No later then within 100 hours FH or within 1 month (whichever is reached first); Before installing an HSI KI 525AEUROCOPTER, EC 120 helicoptersNavigation - Horizontal situation indicator KI 525A 
017-04 PTZDGAC_F-2003-456(B)_R1.pdf3.3.2004No later than 31.12.2007CFM INTERNATIONAL, CFM56-5, CFM56-5B and CFM56-5C turbofan enginesStarting - Starter 
018-04 PTZDGAC_F-2004-038(B).pdf17.3.2004For A319 before 31.03.2004; For A320 and A321 before 31.03.2005AIRBUS A319, A320, A321Fuel system - Additional Center Tanks (ACT) manhole cover seal.SB A320-28-1105 R1
019-04 PTZFAA_AD_2004-06-52.pdf18.4.2004Within 10 hours FISROBINSON HELICOPTER COMPANY, R22, R22 Alfa, R22 Beta and R22 Mariner helicoptersReplacing the blades 
020-04 PTZFAA_AD_2004-05-24.pdf30.3.2004Within compliance times specified unless the action have already been done.Lycoming Engines, AEIO-540, IO-540, LTIO-540, O-540 and TIO-540 seriesCrankshaft gear retaining bolt. 
021-04 PTZLBA_D-2004-168.pdf23.3.200430.04.2004GROB, ASTIR CSInspection of the vertical attachment on horizontal sabilizer.MSB 306-38, dated 12.02.2004
LBA_2004-168-MSB306-38.pdf
022-04 PTZLBA_D-2004-195.pdf23.4.200428.05.2004DG Flugzeugbau, DG-800A and DG-800BPropeller inspectionTN 873/29, dated April 01, 2004
023-04 PTZDGAC_UF_2004-065(B).pdf11.5.2004Within 10 days and Before 06.06.2004AIRBUS, A318, A319, A320 and A321 aircraftVisual inspection at intervals not exceeding 10 days andidentify the serial number of both MLG sliding tubes. This AD replaces 
024-04 PTZFAA_AD_2004-09-05.pdf2.6.2004Wihout 50 landings or 90 days after the effective date of thid AD, whichever is first.Cessna Airplane Company, Model 500, 501, 550 and 551airplanesInspection of stator disks 
025-04 PTZFAA_AD_2004-08-17.pdf17.5.2004Within the next 10 hourt TIS and before further flight after this inspectionCessna Aircraft Company, Model 208 and 208B airplanesInspect any upper wing strut attach fittingSSP04-2, dated April 5, 2004
026-04 PTZFAA_AD_2004-07-25.pdf21.5.2004Before further flightHartzell Propeller Inc., Model HC-B5MP-3C/M10876Kreplace propeller blades. This AD SUpersedes AD 87-16-02 
027-04 PTZCF-2004-06.pdf2.4.200415.04.2004Pratt & Whitney Canada, PW206 and PW207 enginesEnsure the engine DCU is powered during data transfer, Confirmation of DCU properly collecting engine LCF data and confirmation of engine LCF count values and Revision of the Airworthiness limitation section.ASB A28252
028-04 PTZFAA_AD_2004-08-15.pdf7.6.2004Before further flight, as of June 7, 2004Goodrich Avionicd Systems Inc., TAWS8000 Terrain AwarenessInspect the TAWS8000 TAWS innstalation to determine if both the TAWS8000 and any other device are connected to the same baro set potentiometer.SM 134, ASB A117
029-04 PTZDGAC_F-2004-045(A).pdf31.3.2004Before the first flight of the dayEUROCOPTER, AS 350 helicoptersEngine controls - Twist grip solenoid 
030-04 PTZDGAC_F-2004-026(A).pdf19.2.2004Within 10 flight hoursEUROCOPTER, EC 120 helicoptersRotor flight controlsAlert telex 67A014
031-04 PTZDGAC_F-2004-046(A).pdf31.3.2004No later than within 2 monthsEUROCOPTER, AS 350, AS 355, AS 365 N, EC 155, AS 332, AS 332 L2, SA 330, SA 315, SA 341/342, SA 360, SA 365 C, SA 313/318 and SA 316/319 helicoptersEquipment for furnishings - Hoist hooks 
032-04 PTZDGAC_F-2004-044(B).pdf10.4.2004Within 600 hoursAIRBUS, A319, A320 and A321 aircraftsFuel system - Cable segregation. Tis AD replaces AD 2000-407-150.A320-92-1007
033-04 PTZDGAC_F-2004-055(A).pdf8.5.2004As soon as the outside air temperature is below minus 15ºC.EUROCOPTER, AS 350 helicoptersReplacement of hydraulic fluid in cold weather.ASB 05.00.45
035-04 PTZDGAC_F-2004-053(AB).pdf14.4.2004Before December 31, 2007THALES AVIONISC, System TCAS II/ACAS II equipmentTA/RA VSI-TCAS indicator THALES AVIONICS PN 457400-() 
092-02 R1 PTZDGAC_F-2002-371-010(A)_R1.pdf8.5.2004Within 10 flight hoursEUROCOPTER, EC 120 helicoptersCyclic pitch control stickASB 67A008
036-04 PTZENAC_2004-99.pdf30.3.2004As established in Bollettino Technico 109EP-43 dated 25.03.2004, as of the effective date of this AD unless already accomplished.Agusta, A 109EChech of bolts P/N NAS625-14 securing the transmission support fittings to the structure.BT 109EP-43
037-04 PTZENAC_2004-141.pdf29.4.2004As established in Bollettino Technico 206-237, as of the effective date of this AD unless already accomplished.Agusta-Ball, AB 206A/BInstalling Tail Rotor Blads with S/Ns as indicated in referenced BT.BT 206-237
038-04 PTZFAA_AD_2004-10-14.pdf25.6.2004Before further flight unless already done.Lycoming Engines, direct-drive reciprocating enginesInspect and if necessary repair, the crankshaft counter bored recess, the alignment dowel, the bolt hole threads, and the crankshaft gear for wear, galling, corrosion, and fretting.Lycoming MSB 475C, dated Januar 30, 2003
039-04 PTZFAA_AD_2004-10-15.pdf9.7.2004Within 30 days after 09.07.2004, unless already done.GARMIN International Inc, GTX 330 Mode S Transponder and GTX 330D Diversity Mode S Transponder.Install the software upgrade. 
087-03 R1 PTZDGAC_F-2003-325(A)_R1.pdf22.5.2004Within compliance times specified unless the action have already been done.EUROCOPTER, EC 120 helicoptersCrack detection inspection, remove and replace any coupling tube which has one or more cracks.ASB 05A003 R3, ASB 04A005, SB 71.003 and SB 71.005
040-04 PTZFAA_AD_2004-09-29.pdf15.6.2004within the compliance times specified by this AD, unless the actions have already been done.Honeywell International Inc. (formerly AlliedSignal Inc., Garrett Turbine Engine Company, and AiResearch Manufacturing Company of Arizona),Perform a fluorescent penetrant inspection (FPI) of first stage turbine disks, perform repetitive FPIs of first stage turbine disks and replacing a first stage turbine disk, that has a SN specified in this AD, with a disk that does not have a SN specified in this AD, is terminating action for the repetitive inspection requirements.ASB TPE331-A72-2102, dated March 28, 2002.
024-04 R1 PTZEASA_correction_of_FAA_AD_2004-09-05_Official_Copy.pdf2.6.2004Wihout 200 total landings or 50 landings after the effective date of thid AD, whichever is laterCessna Airplane Company, Model 500, 501, 550 and 551airplanesInspection of stator disks 
076-02 R1 PTZDGAC_F-2002-340(B)_R1.pdf
DGAC_2002-337(B)R1.pdf
  AIRBUS, A319, A320 and A321 aircraftThrust reverser and Junction Fuselage/wing 
075-02 R1 PTZDGAC_F-2002-370-043(A)_R1.pdf19.6.2004Within the compliance times specified in this AD.EUROCOPER, SA 341/342 helicoptersEquipement/furnishing-Electric hoist instalation-Pyrotechnic squib 
094-02 R1 PTZDGAC_F-2002-418(B)_R1.pdf19.6.2004 AIRBUS, A320 and A321 aircraftCancallation notice 
042-04 PTZDGAC_F-2004-070(A).pdf26.5.2004Effective dateEUROCOPTER, SA 341/342Limitations 
089-03 R1 PTZDGAC_F-2003-322(A)_R1.pdf5.6.2004Within 100 flying hours check and if necessary adjust the stops; Within 500 FH or within 1 year (whichever is reached first), seal the stop screwsEUROCOPTER, AS 350, AS 355, AS 365n, EC 130, SA 366, EC 155 and EC 120 helicoptersRotor flight controls 
059-03 R1 PTZDGAC_F-2003-260(A)_R1.pdf19.6.2004Before next flightEUROCOPTER, AS 350Electrical power 
043-04 PTZLBA_D-2004-347.pdf2.7.2004Prior to and after each flightDG Flugzeugbau, DG-800A and DG-500MPower plant 
044-04 PTZLBA_D-2004-348.pdf2.7.2004Every daily inspectionDG Flugzeugbau, DG-100, DG-200, DG-300, DG-400, DG-500, DG-500M, DG-600 and DG-600MLower mounting of the rudder 
045-04 PTZLBA_D-2004-350.pdf2.7.2004Every daily inspectionDG Flugzeugbau, DG-800A and DG-500MPower plant - primer valve 
046-04 PTZFAA_AD_2004-13-20.pdf3.8.2004Within 6 months after the effective date of this ADGARMIN AT, Appolo GX Series GPSModify and test the software 
013-04 R2 PTZCF-2004-04R2.pdf8.4.2004Part A: within 14 days; Part B: within 3 days of the effective date; Part C: within 14 days; Part D: according with the schedule in this ADBombardier, CL-600-2C10 and CL-600-2D24 (CRJ-700 and CRJ-900 Series)Fuel Ejector Leak Check  
047-04 PTZFAA_AD_2004-12-08.pdf23.7.2004Within the next 90 days after the effective date of this ADInternational Aero Engines AG (IAE), V2500-A1, V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5 and V2533-A5Revise the approved continous airworthiness maintenance program 
048-04 PTZCF-1998-14_R4.pdf25.6.2004When indicated, unless already accomplishedBombardier, CL-600-2B19Flap system failure 
049-04 PTZDGAC_F-2004-074(B).pdf5.6.2004From the effective date of this ADAIRBUS, A319, A320 and A321 aircraft  
050-04 PTZFAA_AD_95-26-05_R1.pdf6.7.200406.07.2004Robinson Helicopter Company, Model R44 helicoptersTis AD rescinds AD 95-26-05 
051-04 PTZFAA_AD_2003-13-15_R1.pdf10.8.2004Within 10 hours TIS and thereafter at intervals not exceed 50 hours TISSchweizer Aircraft Company, Model 269A, 269-A1, 269B, 269C and TH-55A helicoptersDye-penetrant inspectionSchweizer SB B-277, dated 25.01.2002
052-04 PTZDGAC_F-2004-073(B).pdf5.6.2004No later than 31.12.2005AIRBUS, A318, A319, A320 and A321 aircraftPrevention against explosion risksSB A320-92-1032
053-04 PTZDGAC_F-2004-072(B).pdf5.6.2004Before 30.06.2007AIRBUS, A318, A319, A320 and A321 aircraftPassenger door emergency escape slidesSB A320-35-1338
054-04 PTZDGAC_F-2004-065(B).pdf11.5.2004Within the compliance times specified in this AD.AIRBUS, A318, A319, A320 and A321 aircraftShock absorber sliding tube.  
005-04 R1 PTZDGAC_F-2004-022(B)_R1_.pdf26.5.2004 AIRBUS, A318, A319, A320 and A321 aircraftCANCALLATION NOTICE Replaced with PTZ 054-04
DGAC_F-2004-065(B).pdf
 
055-04 PTZDGAC_F-2004-089(A).pdf3.7.200431.12.2004EUROCOPTER, AS 350 helicoptersHydraulic cut off function. Embody the modifications to the electrical wiring.ASB 29.00.07
056-04 PTZDGAC_F-2004-085(A).pdf11.7.200411.07.2004EUROCOPTER, AS 350 helicoptersEmergency flotating gearSB 01.00.35
057-04 PTZDGAC_F-2004-096(B).pdf3.7.2004At the latest, each time before using the hoist operator's beltEUROCOPTER, SA 330, AS 332. AS 332 L2, SA 341/342, AS 350, AS 355, SA 360, SA 365 C, AS 365 N, EC 155, SA 316/319 helicoptersHoist operator's belt snap hook 
058-04 PTZDGAC_F-2004-088(A).pdf23.6.2004Either at next engine shop visit or as soon as there is an acces to the 2-nd stage nozzle quide vanes, whichever occours first.TURBOMECA, ARRIEL 1 turboshaft engines.2-nd stage nozzle guide vanes inspection (NGV2)SB 292 72 0231 Rev.4, dated 11.02.2004
059-04 PTZDGAC_F-2004-095(B).pdf3.7.2004Either at next engine shop visit or at next main fuel pump replacement or before 01.01.2007, whichever occours firstCFM INTERNATIONAL, CFM56-2C, CMF56-3 and CFM56-5 turbofan enginesReplacement of main fuel pumps equipped with solid bronze bearings with pumps equipped with bi-metal, aluminium/bronze bearing. 
060-04 PTZLBA_D-2004-352.pdf12.7.2004Prior to further flightHoffmann Propeller GmbH&Co. KG, HO-V343 propellersDetailed visual inspection of the propeller hub in a specified area. Exchange or repair of the propeller if any signs of cracks have been detected during the inspection.SB_Hoffman_61-10-03_E15.pdf
SI_Hoffman_61-10-05_E4.pdf
061-04 PTZCAA_G-2004-0013.pdf8.7.2004At the next Annual Check after the effective date of this ADSLINGSBY AVIATION LIMITED, T67A, T67B, T67C, T67M, T67M-MK II, T67M200, T67M260 and T67M260-T3A aircraftInspection of aluminium components for exfoliation.SB 127 Issue 3 or later
060-04 R1 PTZLBA_D-2004-352_R1.pdf19.7.2004Prior to further flightsHoffmann Propeller GmbH&Co. KG, HO-V343 propellersDetailed visual inspection of the propeller hub in a specified area. Exchange or repair of the propeller if any signs of cracks have been detected during the inspection.SB_Hoffman_61-10-03_E15-A.pdf
SI_Hoffman_61-10-05_E4-A.pdf
062-04 PTZFAA_AD_2004-14-20.pdf23.8.2004Within the compliance times specified in this AD.Cessna Aircraft Company, Model 525 AirplanesThe actions specified in this AD are intended to correct this single-point failure in the electric pitch trim system, which will result in a runaway pitch trim condition where the pilot could not disconnect using the control wheel autopilot/trim disconnect switch. Failure of the electric trim system would result in a large pitch mistrim and would cause excessive control forces that the pilot could not overcome. 
063-04 PTZCF-2004-18.pdf16.9.20048000 FC since new or 50 FC after effective date of this AD, whichever occurs laterBombardier, CL-600-2B19Superseded by 063-04R1 PTZ
CF-2004-18R1.pdf
ASB A601R-32-099, dated 15 September 2004, or later revision
060-04 R2 PTZLBA_D-2004-352R2.pdf23.7.2004Prior to further flightsHoffmann Propeller GmbH&Co. KG, HO-V343 propellersDetailed visual inspection of the propeller hub in a specified area. Exchange or repair of the propeller if any signs of cracks have been detected during the inspection.SB_Hoffman_61-10-03_E15-B.pdf
SI_Hoffman_61-10-05_E4-B.pdf
060-04 R3 PTZLBA_D-2004-352_R3.pdf18.8.2004Within the compliance times specified in this AD.Hoffmann Propeller GmbH&Co. KG, HO-V343 propellers1. Examination of the propeller blade shake. 2. Examination of the blade retention nut preload torque. 3. Eddy current inspection and visual inspection of the propeller hub in the internal blade retention area for cracks and damages. Alternative eddy current inspection procedures must provide the same level of safety and must be approved by the responsible local aviation authority. 4. Exchange or repair of the propeller if any blade shake or signs of cracks or damages of the propeller hub outside serviceable limits have been detected during the inspection.SI_Hoffman_61-10-05_E4-C.pdf
SB_Hoffman_61-10-03_E15-B.pdf
064-04 PTZENAC_2004-271.pdf5.7.2004As established in Bulletino Technico 109EP-45 dated 23.06.2004, as of the effective date of this AD unless already accomplished.Agusta, A 109ECheck of emergency release mechanism of cargo hook installation.BT 109EP-45 dated 23.06.2004
014-04 R1 PTZCF-2004-05R1.pdf23.3.2004Before next flightBell, 206A, 206B, 206L SeriesTail Rotor Blade Trailing Edge Skin Cracks ASB 206-04-100 Rev. B in ASB 206L-04-127 Rev. B
065-04 PTZFAA_AD_2004-19-09.pdf7.10.2004Within 10 hours time-in-servise (TIS) or 30 days, whichever occours first.Robinson Helicopter Company, Model R22 series helicoptersTo prevent a fatique crack, blade failure and subsequent loss of control of the helicopter 
066-04 PTZCF-2002-05R1.pdf30.7.2004When indicated unless olready accomplished.Bombardier, CL-600 "Challenger", CL-600-1A11, CL-600-2A12, CL-600-2B16Angle of Attack Transducer 
067-04 PTZCF-2004-13.pdf20.8.2004When indicated, unless already accomplishedBombardier, CL-600-2B19 "Regional Jet"Aileron Power Control Unit LinksASB A601R-27-130, dated 13 November 2003
068-04 PTZCF-2004-14.pdf24.8.2004When indicated, unless already accomplishedBombardier, CL-600-2C10 and CL-600-2D24 (CRJ-700 and CRJ-900 Series)Aft Pressure Bulkhead Structure and Hydraulic Lines 
069-04 PTZFAA_AD_2004-19-01.pdf1.11.2004Within the compliance times specified in this AD.Cessna Aircraft Company, 120, 140, 140A, 150, F150, 170, 172, F172, FR172, P172D, 175, 177, 180, 182, 185, A185E, 190, 195, 206, P206, U206, TP206, TU206, 207, T207, 210, T210, 336, 337 and T337 Series AirplanesTo prevent slippage of the pilot/co-pilot shoulder harness, which could result in failure of the shoulder harness to maintain proper belt length adjustment and tension. This failure could result in pilot/co-pilot injury.Cessna Single Engine Service Bulletin SEB86-8, Revision 1, and Cessna Multi-engine Service Bulletin MEB86-22, Revision 1, both dated July 28, 2003.
070-04 PTZFAA_AD_2004-15-03.pdf16.8.2004RevisedGeneral Electric Company, CF34-3A1 and -3B1 series turbofan enginesRevised- AD 2004-15-03R1 (070-04 R1 PTZ)GE Aircraft Engines ASB No. CF34-AL S/B 72-A0173, Revision 3, dated July 20, 2004
071-04 PTZFAA_AD_2004-17-02.pdf4.10.2004Within the compliance times specified in this AD.Raytheon Aircraft Company, 65, 90, 99, 100, 200, 300, and 1900 Series AirplanesThis AD is the result of numerous reports of loose bolts on the pedestal attachment of the throttle/prop cross shaft assembly. The actions specified in this AD are intended to detect and correct loose bolts not securing the pedestal cross shaft, which could result in limited effectiveness of the control levers. This failure could lead to an aborted takeoff.Mandatory Service Bulletin No. SB 73-3634, dated September, 2003.
070-04 R1 PTZFAA_AD_2004-15-03_R1.pdf
2006-04-12.pdf
31.8.2004SupersededGeneral Electric Company, CF34-3A1 and -3B1 series turbofan enginesSuperseded by AD 2006-04-12 (014-06 PTZ)GE ASB No. CF34-AL S/B 72-A0173, Revision 3, dated July 20, 2004
072-04 PTZFAA_AD_2004-15-18.pdf12.9.2004Within the compliance times specified in this AD.Cessna Aircraft Company, Models 172R, 172S, 182S, 182T, T182T,The actions specified in this AD are intended to prevent unintentionally engaging the KAP 140 autopilot computer system, which could cause the pilot to take inappropriate actions. This AD supersedes AD 2003-24-13.Cessna Single Engine SB98-22-01, dated May 18, 1998; Cessna Single Engine SB02-22-01, dated November 25, 2002; Honeywell Service Bulletin No: KC 140-M1, dated August 2002; and Honeywell Installation Bulletin No. 491, Rev. 3, dated April 2003.
073-04 PTZFAA_AD_2004-14-12.pdf10.8.2004Within the compliance times specified in this AD.The New Piper Aircraft, Inc., Models PA-28-161, PA-28-181, PA-28R-201, PA-32R-301 (HP), PA-32R-301T, PA-32-301FT, PA-32-301XTC, PA-34-220T, PA-44-180, PA-46-350P, and PA-46-500TP AirplanesTo detect and correct inadequate control wheel attachment design, which could result in loss of control of the ailerons and elevator. This failure could lead to loss of airplane.Service Bulletin No. 1139A, dated April 9, 2004
074-04 PTZDGAC_F-2004-104.pdf17.7.200424.09.2004AIRBUS SAS, A318, A319, A320 and A321 aircraftTemprorary loss of all display units 
074-04 R1 PTZDGAC_F-2004-104(B)_R1.pdf28.8.200424.09.2004AIRBUS SAS, A318, A319, A320 and A321 aircraftTemprorary loss of all display units 
075-04 2004DGAC_F-2004-120(B).pdf31.7.2004Before June 30 2007AIRBUS SAS, A319, A320 and A321 aircraftFuel system - Air Release Valve (ARV)AIRBUS Service Bulletin A320-28-1002, AIRBUS Service Bulletin A320-28-1123
076-04 PTZDGAC_F-2004-121(B).pdf31.7.2004Before December 31, 2005, unless olready accomplishedAIRBUS SAS, A319, A320 and A321 aircraftLights - Emergency escape path markingAIRBUS Service Bulletin A320-33-1041
077-04 PTZDGAC_F-2004-122(B).pdf31.7.2004Before July 31, 2005, unless already accomplished.AIRBUS SAS, A318, A319, A320 and A321 aircraftFlight controls - Spoiler actuatorsAIRBUS Service Bulletines A320-27-1158, A320-27-1159.
078-04 PTZDGAC_F-2004-123(B).pdf31.7.2004Before October 31, 2006.AIRBUS SAS, A319, A320 and A321 aircraftEnvironmental/Air Conditioning - Cargo compartment - Heating temperature sensorAIRBUS Service Bulletin A320-21-1141
088-03 R1 PTZDGAC_F-2003-373(B)_R1.pdf31.7.200431.07.2004AIRBUS SAS, A318, A319, A320, A321, A330 and A340 aircraftTemporary loss of all display units. Cancellation notice. Replaced by
DGAC_F-2004-104.pdf
 
079-04 PTZDGAC_F-2004-129(B).pdf14.8.2004Before August 05, 2005, unless already accomplished.AIRBUS SAS, A319, A320 and A321 aircraftFuel - Cable segregation around rack 90 VUAIRBUS Service Bulletin A320-92-1007 Revision 8
032-04 R1 PTZDGAC_F-2004-044(B)_R1.pdf14.8.200414.08.2004AIRBUS SAS, A319, A320 and A321 aircraftsFuel system - Cable segregation around rack 90 VU This Revision 1 cancels Airworthiness Directive (AD) F-2004-044, which is replaced by
DGAC_F-2004-129(B).pdf
 
058-04 R1 PTZDGAC_F-2004-088(A)_R1.pdf4.8.2004Unless already done and at the latest on December 31, 2006.TURBOMECA, ARRIEL 1 turboshaft engines.Engine - 2nd stage nozzle guide vanes inspection (NGV2)Service Bulletin No. 292 72 0231 Revision 5.
080-04 PTZDGAC_F-1997-083-096(B)_R1.pdf28.8.2004 AIRBUS SAS, A320 aircraftWing - Inspection of bottom skin panel between ribs 13 and 22. This Revision 1 cancels Airworthiness Directive (AD) 97-083-096, which is replaced by
DGAC_F-2004-146(B).pdf
 
082-04 PTZDGAC_F-2004-146(B).pdf28.8.2004Unless already accomplished, before accumulation of 20,000 FC or 34,200 FH, whichever occurs first; Repeat the inspection defined in paragraph 3.1. of this AD at intervals not exceeding 15,000 FC or 25,600 FH, whichever occurs first.AIRBUS SAS, A320 aircraftWing - Inspection of bottom skin panel between ribs 13 and 22.AIRBUS Service Bulletin A320-57-1055 Revision 2 and A320-57-1056 Revision 2.
083-04 PTZDGAC_F-2000-222-079(A)_R1.pdf25.9.2004At the latest within 10 flying hours, at each check after the last flight of the day.EUROCOPTER, AS 350 helicoptersTail rotor - Bearing spacer of the tail rotor head pitch change plateEUROCOPTER AS 350 Alert Service Bulletin No. 05.00.33 R1
084-04 PTZDGAC_F-2004-148(A).pdf11.9.2004Within the next 110 flight hours or in the next 12 months, whichever occurs first; Then in a recurring way, not to exceed 13 months.EADS SOCATA, TB 21 aeroplanesWindows-Windshield inspectionSB EADS SOCATA No 10-144-56 dated June 2004.
085-04 PTZDGAC_F-2004-150(B).pdf11.9.2004Within the compliance times specified in this AD.AIRBUS SAS, A320 aircraftAuxiliary hydraulic power - Airborne ground check module (AGCM)AIRBUS Service Bulletin A320-29-1111; All Operator Telex A320-29A1112 Revision 1 dated April 08, 2004.
086-04 PTZLTA_A-2004-001.pdf1.10.2004Inspect within 50 hours Time-in-Service (TIS) after the effective date ofRotax 912 A/F/S and 914 F Series enginesInspection for possible cracks in crankcase. This AD replaces ACG AD No.
107 R3 dated 01. February 2003
SB 912-029 R2 and 914-018 R2
087-04 PTZLTA_A-2004-004.pdf
SUPERSEEDED BY 087-04R2 PTZ
1.10.2004Superseeded by A-2004-004R2Rotax 912 A/F/S and 914 F Series enginesIntroduction of new coolant liquid type “EVANS NPG+”
A-2004-004R2.pdf
SB 912-043 and 914-029
088-04 PTZLTA_A-2004-005.pdf1.10.2004Inspect within 50 hours Time-in-Service (TIS) after the effective date of this AD.Rotax 914 F-Series enginesInspection of the Exhaust Muffler Part No. 979402 and Part No. 979404. Pod točko 5. se doda, da se izvaja na vsakih 50. ur. This AD replaces ACG AD No.
AUSTRO_117.pdf
SB 914-028
089-04 PTZCF-2004-22.pdf26.10.2004Within the compliance times specified in this AD.Bombardier, CL-600 "Challenger", CL-600-1A11, CL-600-2A12, CL-600-2B16Angle of Attack Vane. ASB A600-0729, ASB A601-0571, ASB A601-0571, ASB A604-27-026
050-01 R2 PTZCAA-AD-T-037_2001R2.pdfUpon receiptBefore further flightLETECKÉ ZÁVODY a.s., L 410 and L 420 aircraftValues of flight levels and Maximum Operating Limit Speed 
044-04 R1 PTZLBA_D-2004-348_R1.pdf16.9.2004Every daily inspectionDG Flugzeugbau, DG-100, DG-200, DG-300 and DG-400:all, DG-500/22 ELAN and DG-500M: all up to 5E23, DG-600 and DG-600M:allLower mounting of the rudder. This AD supersedes AD 044-04 PTZ
LBA_D-2004-348.pdf
 
090-04 PTZENAC_2004-351.pdf22.9.2004As established in the referenced Bollettino Technico, as of the effective date of this AD unless olready accomplished.Agusta-Bell; AB205A1, AB212 and AB412 helicoptersTail rotor blade Tip block and tip closure retention modification.BT 205A1-126 Rev.A, 212-193 Rev.A and 412-88 Rev.A all dated 17.08.2004
076-04 R1 PTZDGAC_F-2004-121(B)_R1.pdf23.10.2004Before December 31, 2005, unless already accomplishedAIRBUS SAS, A319, A320 and A321 aircraftLights - Emergency escape path marking - BRUCE FPEEPMSAIRBUS Service Bulletin A320-33-1041
091-04 PTZCAA_G-2004-0026.pdf2.11.2004Before further flightCameron Balloons Limited; Shadow/Shadow Stealth - Triple, Quadand Stratus Triple, Quad gimballed burnerassembliesInspect the burner support plate andmounting tubeCameron Balloons Ltd SB No 13 issue A or later EASA approved revision.
092-04 PTZCF-2004-20.pdf1.11.2004Within 24 months after the effective date of this directive, unless already accomplished.Bombardier Inc. Model CL-600-2B19 “Regional Jet” Series 100/440, serial numbers 7003 through 7067, 7069 through 7165, 7167 through 7169 and 7171 through 7188.Hydraulic Line ShieldsBulletin 601R-57-021, Revision C, dated 23 February 2004, or later revisions
093-04 PTZCAA_G-2004-0028.pdf26.11.2004Within 7 days of the effective date of this AD.CAMERON BALLOONS LIMITED; All solid floor baskets manufactured by Cameron Balloons Limited, Thunder Balloons Ltd, ColtBalloons Ltd, Thunder and Colt Ltd and Sky Balloons Ltd.Pre-Flight Check Of Basket Suspension Wires.Cameron Balloons Service Bulletin No 12 revision 0
094-04 PTZDGAC_F-2004-168(B).pdf20.10.2004At the next opportunity, but not later than three calendar days following the effective date of this AD.AIRBUS SAS; A318, A319, A320 and A321 aircraftLoss of integrated standby instrument system (ISIS). Superseeded by 094-04R1 PTZ
F-2004-168R1.pdf
 
095-04 PTZDGAC_F-2004-170(A).pdf6.11.2004Within the compliance times specified in this AD.EUROCOPTER; AS 350, AS 355, AS 332, SA 341/342 helicoptersEquipment and furnishings - Hoists hooksEUROCOPTER AS 350 Alert Telex No. 01.00.56, AS 355 Alert Telex No. 01.00.50, AS 332 Alert Telex No. 01.00.70 and SA 341/342 Alert Telex No. 01.33.
096-04 PTZDGAC_F-2004-172(B).pdf6.11.2004Before April 30, 2005.AIRBUS SAS; A318, A319, A320 and A321 aircraftFire protection - Cargo compartment water drain valves.AIRBUS Service Bulletin A320-52-1124
097-04 PTZDGAC_F-2004-173(B).pdf6.11.2004No later than December 31st, 2009.AIRBUS SAS; A320 aircraftFuel system - Prevention against explosion risks - Electrical cablesAIRBUS Service Bulletin A320-24-1062 R5.
098-04 PTZDGAC_F-2004-174(A).pdf20.11.2004No later than within one month.EUROCOPTER; AS 350 helicoptersHydraulic power - Hydraulic power loss. 
077-02 R1 PTZDGAC_F-2002-344-093(A)_R1.pdf20.11.2004Before the next flight after the effective date of the original issue of this AD, then at intervals not exceeding 100 flying hours.EUROCOPTER; AS 350 helicoptersDoors - Sliding door - Wear on rollers and rails. Check the diameter of the roller and the dimension of the front end opening of the middle rail.EUROCOPTER AS 350 Alert Service Bulletin No. 05.00.41, Revision 1
099-04 2004DGAC_F-2004-137(B).pdf20.11.2004Before March 31, 2009.AIRBUS SAS; A319, A320 and A321 aircraftLanding gear - Parking brake system. Modify the parking brake system.AIRBUS Service Bulletin A320-32-1201 Revision 1.
100-04 PTZFAA_AD_2004-23-17.pdf7.12.2004Within 10 hours TIS after December 1, 2004 (the effective date of this AD), unless already done.Mooney Airplane Company, Inc.: Model M20M airplanes, serial numbers 27-0001 through 27-0321.To prevent the Vclamp from detaching from the turbocharger and to prevent exposure of the firewall to hot exhaust gases, which could result in an in-flight fire.Mooney Airplane Company, Inc. Service Bulletin M20-283A, dated March 30, 2004.
101-04 PTZFAA_AD_2004-23-02.pdf23.12.2004Within the compliance times specified in this AD.Raytheon Aircraft Company 65, 90, 99, 100, 200, and 1900 SeriesThe actions specified in this AD are intended to detect and correct cracks in the nose landing gear (NLG) fork.Raytheon Aircraft Company Mandatory Service Bulletin SB 32-2102, Revision 7, Revised: July, 2003.
102-04 PTZFAA_AD_2004-23-16.pdf7.12.2004Within the compliance times specified in this AD.McCauley Propeller Systems Five-Blade Propeller AssembliesPerforming the eddy-current inspectionMcCauley ASB No. A247, dated April 30, 2004 and Alert Service Bulletin No. ASB247A, Revision A, dated August 18, 2004,
103-04 PTZLBA_D-2004-489.pdf11.11.2004Within 50 flight hours, but not later than 3 months.Extra Flugzeugbau; EA-300, EA-300/S, EA-300/L and EA-300/200To prevent fuel from entering the cockpit, gaps between the bottom fuselage cover (belly fairing) and the firewall need to be sealed with firewall sealant.Extra Service Bulletin No. 300-4-04, Issue A dated May 25, 2004.
087-04 R1 PTZSUPERSEEDED28.12.2004Superseeded by A-2004-004R2Bombardier; Rotax 912 A/F/S and 914 F Series enginesReplacement of coolant/Reduction of Cylinder Head Temperature Limits. Immediately after receipt. AD replaced by
LTA_A-2004-004.pdf
A-2004-004R2.pdf
SB_Rotax_912-043_914-029.pdf
088-04 R1 PTZLTA_A-2004-005_R1.pdf28.12.2004Initial inspection within 50 hours Time-in-Service (TIS) after receipt of this AD, andBombardier; Rotax 914 F-Series enginesInspection of the Exhaust Muffler Part No. 979402 and Part No. 979404 for possible existance of traces of smoke or cracks. AD A-2004-005 R1 replaces
LTA_A-2004-005.pdf
SB_Rotax_914-028.pdf
074-02 R1 PTZDGAC_F-2001-580-085(B)_R2.pdf18.12.2004In compliance with the instructions described in § 2.A. of Revision 1 of referenced EUROCOPTER AS350 Alert Service Bulletin (ASB) No. 05.00.37EUROCOPTER; AS 350 helicoptersRotor flight controls - Tail servocontrols - Eye end fitting lockingEUROCOPTER AS 350 Alert Service Bulletin No. 05.00.37 R1
053-00 R1 PTZDGAC_F-2000-521-160(B)_R1.pdf18.12.200418.12.2004AIRBUS SAS, A319, A320 and A321 aircraftMain landing gear door actuator fitting at the keel beam. This Revision 1 cancels Airworthiness Directive (AD) 2000-521-160, which is replaced by AD F-2004-189. 
104-04 PTZDGAC_F-2004-189(B).pdf18.12.2004Within the compliance times specified in this AD.AIRBUS SAS, A319, A320 and A321 aircraftKeel beam - Main landing gear door actuator fitting. AIRBUS Service Bulletin A320-53A1135 Revision 3, A320-53-1140 Revision 2, A320-53-1148, A320-53-1149, A320-53-1160, A320-53-1158
105-04 PTZCF-2004-23.pdf30.11.2004Within 5,500 flight hours of the effective date of this directive, unless already accomplished.Bombardier Inc. Model CL-600-2B19, serial numbers 7003 thru 7979.Camloc Fasteners on Center PedestalService Bulletin (SB) 601R-31-030, dated 22 June 2004, or SB 601R-31-030, Revision A, dated 06 October 2004.
106-04 PTZCF-2004-24.pdf15.12.2004As soon as practicable, but not later that 31 December 2004, unless already accomplished.Bell Helicopter Textron Canada (BHTC) Model 206LLow Fuel Level Detector 
107-04 PTZCF-2004-25.pdf10.12.2004As indicated, unless already accomplished.Bell Helicopter Textron Canada (BHTC); Bell 206A, 206B, 206LPart A: Identification of Affected Tail Rotor Blades. Part B: Check for Tail Rotor Doubler De-bonding. Part C: Replacement of the Blades.ASB 206-04-101 and 206L-04-131.
108-04 PTZFAA_AD_2004-25-04.pdf21.1.2005Within the next 12 months after 21.01.2005Mooney Aircraft Corporation; M20C, M20D, M20E, M20F, M20G, and M20J airplanes, all serial numbersThis AD requires you to inspect the drain valve to assure that it is inserted fully into the drain nipple and modify any drain valve found not to be inserted fully into the drain nipple. This AD also requires certain modifications and replacements on the affected fuel cells to reduce the chances of water/ice contamination.MSB No. ON–100, dated 01.02. 1998.