Številka PTZ | Referenčna PTZ | Datum efektive | Rok izvršitve | Proizvajalec | Vsebina PTZ | Referenčni SB |
001-04 PTZ | ENAC_2004-022.pdf | 26.1.2004 | As 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 412 | Main hydraulic servo actuator rod end locker washer inspection and replacement of. | |
002-04 PTZ | CAA-AD-T-005-2004.pdf | 12.2.2004 | Before next flight | Letecke zavody (former LET a.s.), L 23 Super-Blanik | NDT inspection of elevator rocker lever. | MB_L23-48a.pdf |
003-04 PTZ | LBA_D-2004-060_R1.pdf | 30.1.2004 | Immediately and up to the issuance of a new AD | DIAMOND AIRCRAFT, H 36 Dimona | Daily inspection of the propeller control rods | |
004-04 PTZ | LBA_D-2004-084.pdf | 4.2.2004 | Until 30.04.2004 | SCHEMPP-HIRTH, Duo Discus | Chech the bonding between the upper spar cup and the spar web. | Technical Note
No 396-9 dated 30.01.2004 |
005-04 PTZ | DGAC_F-2004-022_Urgent_.pdf | 12.2.2004 | Before 05.03.2004 | AIRBUS, A319, A320, A321 | Identify the SN and PN of both MLG sliding tubes | |
128-02 R2 PTZ | DGAC_2002-556(B)R2.pdf | 4.2.2004 | | AIRBUS, A319, A320, A321 | CANCELLATION NOTICE | |
006-04 PTZ | DGAC_F-2004-018(B).pdf | 14.2.2004 | 30.04.2004 | AIRBUS, A319, A320, A321 | Limitation items | |
007-04 PTZ | DGAC_F-2004-019(B).pdf | 14.2.2004 | Before 30.10.2005 | AIRBUS, A319, A320, A321 | APU | SB A320-24-1106 |
008-04 PTZ | FAA_AD_2004-03-08.pdf | 15.3.2004 | Prior 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 airplanes | Inspection of the shear webs of the forward engine beams for cracking | Bombardier SB 31-51-2 or 35/36-51-3 |
009-04 PTZ | CF-2004-01.pdf | 20.2.2004 | Within 1000 ours air-time after the effective date of this AD | Bombardier, Regional Jet CL-600-2B19 | Engine 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 PTZ | DGAC_UF-2004-026.pdf | 25.2.2004 | Within 10 flying hours | EUROCOPTER, EC 120 | Check: - the tightening torque load of the connecting part attachment bolts - the connecting part for cracks | Alert telex No. 67A014 |
011-04 PTZ | FAA_AD_2003-24-07.pdf | 9.2.2004 | Within 150 hours TIS after 09.02.2004 install the inspection hole and conduct visual inspection before further flight | The 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 Airplanes | Install aninspection hole and conduct a detailed visual inspection of the rudder torque tube and associated ribs for corrosion. | SB 1105A |
012-04 PTZ | EU-2006-0162.pdf | 10.2.2004 | Superseeded by 036-06 PTZ (EU-2006-0162) | AIRBUS, A319, A320 and A321 aircraft | Life limits/Monitored Parts - MPD Section 9-1 | |
008-03 R1 PTZ | DGAC_F-2003-002(A)_R1.pdf | 28.2.2004 | Within the compliance times specified in this AD. | EUROCOPTER, AS 350 helicopters | Rotor flight controls - Cyclic stick | AS 350 ASB 67.00.24 |
127-02 R1 PTZ | DGAC_F-2002-555(B)_R1.pdf | 28.2.2004 | 28.02.2004 | AIRBUS, A319, A320 and A321 aircraft | Certified Limitations - Life limited parts. CANCELLATION NOTICE . This AD is replaced by
DGAC_F-2004-032(B).pdf | |
013-04 PTZ | CF-2004-04.pdf | 23.2.2004 | Part A: within 14 days; Part B: according with the schedule in this AD | Bombardier, CL-600-2C10 and CL-600-2D24 (CRJ-700 and CRJ-900 Series) | Fuel Ejector Leak Check | |
113-03 R1 PTZ | DGAC_F-2003-465(A)_R1.pdf | 3.3.2004 | Within 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 helicopters | Tail rotor - Tail rotor drive shaft damper. | Alert Telex No. 65A004 R1 |
101-03 R2 PTZ | DGAC_F-2003-368(A)_R2.pdf | 13.3.2004 | Within 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 TB21 | Flight controls - Gimbal joint aileron and elevator control inspection. | EADS_Socata_SB_10-130-27_JAN04.pdf |
012-03 R2 PTZ | | 7.4.2004 | 01.05.2004 | Vsi zrakoplovi | Uporaba radijskih postaj s 25 kHz kanalno razdelitvijo. | |
014-04 PTZ | CF-2004-05.doc | 23.3.2004 | Before next flight | Bell, 206A, 206B, 206L Series | Tail Rotor Blade Trailing Edge Skin Cracks | ASB 206-04-100 Rev. A in ASB 206L-04-127 Rev. A |
013-04 R1 PTZ | CF-2004-04R1.pdf | 8.4.2004 | Part 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 AD | Bombardier, CL-600-2C10 and CL-600-2D24 (CRJ-700 and CRJ-900 Series) | Fuel Ejector Leak Check | |
015-04 PTZ | DGAC_F-2002-281-091_R1(A).pdf | 27.3.2004 | No later then within 100 hours FH or within 1 month (whichever is reached first); Before installing an HSI KI 525A | EUROCOPTER, AS 350 helicopters | Navigation - Horizontal situation indicator KI 525A | |
016-04 PTZ | DGAC_F-2002-282-009_R1(A).pdf | 27.4.2004 | No later then within 100 hours FH or within 1 month (whichever is reached first); Before installing an HSI KI 525A | EUROCOPTER, EC 120 helicopters | Navigation - Horizontal situation indicator KI 525A | |
017-04 PTZ | DGAC_F-2003-456(B)_R1.pdf | 3.3.2004 | No later than 31.12.2007 | CFM INTERNATIONAL, CFM56-5, CFM56-5B and CFM56-5C turbofan engines | Starting - Starter | |
018-04 PTZ | DGAC_F-2004-038(B).pdf | 17.3.2004 | For A319 before 31.03.2004; For A320 and A321 before 31.03.2005 | AIRBUS A319, A320, A321 | Fuel system - Additional Center Tanks (ACT) manhole cover seal. | SB A320-28-1105 R1 |
019-04 PTZ | FAA_AD_2004-06-52.pdf | 18.4.2004 | Within 10 hours FIS | ROBINSON HELICOPTER COMPANY, R22, R22 Alfa, R22 Beta and R22 Mariner helicopters | Replacing the blades | |
020-04 PTZ | FAA_AD_2004-05-24.pdf | 30.3.2004 | Within compliance times specified unless the action have already been done. | Lycoming Engines, AEIO-540, IO-540, LTIO-540, O-540 and TIO-540 series | Crankshaft gear retaining bolt. | |
021-04 PTZ | LBA_D-2004-168.pdf | 23.3.2004 | 30.04.2004 | GROB, ASTIR CS | Inspection of the vertical attachment on horizontal sabilizer. | MSB 306-38, dated 12.02.2004
LBA_2004-168-MSB306-38.pdf |
022-04 PTZ | LBA_D-2004-195.pdf | 23.4.2004 | 28.05.2004 | DG Flugzeugbau, DG-800A and DG-800B | Propeller inspection | TN 873/29, dated April 01, 2004 |
023-04 PTZ | DGAC_UF_2004-065(B).pdf | 11.5.2004 | Within 10 days and Before 06.06.2004 | AIRBUS, A318, A319, A320 and A321 aircraft | Visual inspection at intervals not exceeding 10 days andidentify the serial number of both MLG sliding tubes. This AD replaces | |
024-04 PTZ | FAA_AD_2004-09-05.pdf | 2.6.2004 | Wihout 50 landings or 90 days after the effective date of thid AD, whichever is first. | Cessna Airplane Company, Model 500, 501, 550 and 551airplanes | Inspection of stator disks | |
025-04 PTZ | FAA_AD_2004-08-17.pdf | 17.5.2004 | Within the next 10 hourt TIS and before further flight after this inspection | Cessna Aircraft Company, Model 208 and 208B airplanes | Inspect any upper wing strut attach fitting | SSP04-2, dated April 5, 2004 |
026-04 PTZ | FAA_AD_2004-07-25.pdf | 21.5.2004 | Before further flight | Hartzell Propeller Inc., Model HC-B5MP-3C/M10876K | replace propeller blades. This AD SUpersedes AD 87-16-02 | |
027-04 PTZ | CF-2004-06.pdf | 2.4.2004 | 15.04.2004 | Pratt & Whitney Canada, PW206 and PW207 engines | Ensure 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 PTZ | FAA_AD_2004-08-15.pdf | 7.6.2004 | Before further flight, as of June 7, 2004 | Goodrich Avionicd Systems Inc., TAWS8000 Terrain Awareness | Inspect 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 PTZ | DGAC_F-2004-045(A).pdf | 31.3.2004 | Before the first flight of the day | EUROCOPTER, AS 350 helicopters | Engine controls - Twist grip solenoid | |
030-04 PTZ | DGAC_F-2004-026(A).pdf | 19.2.2004 | Within 10 flight hours | EUROCOPTER, EC 120 helicopters | Rotor flight controls | Alert telex 67A014 |
031-04 PTZ | DGAC_F-2004-046(A).pdf | 31.3.2004 | No later than within 2 months | EUROCOPTER, 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 helicopters | Equipment for furnishings - Hoist hooks | |
032-04 PTZ | DGAC_F-2004-044(B).pdf | 10.4.2004 | Within 600 hours | AIRBUS, A319, A320 and A321 aircrafts | Fuel system - Cable segregation. Tis AD replaces AD 2000-407-150. | A320-92-1007 |
033-04 PTZ | DGAC_F-2004-055(A).pdf | 8.5.2004 | As soon as the outside air temperature is below minus 15ºC. | EUROCOPTER, AS 350 helicopters | Replacement of hydraulic fluid in cold weather. | ASB 05.00.45 |
035-04 PTZ | DGAC_F-2004-053(AB).pdf | 14.4.2004 | Before December 31, 2007 | THALES AVIONISC, System TCAS II/ACAS II equipment | TA/RA VSI-TCAS indicator THALES AVIONICS PN 457400-() | |
092-02 R1 PTZ | DGAC_F-2002-371-010(A)_R1.pdf | 8.5.2004 | Within 10 flight hours | EUROCOPTER, EC 120 helicopters | Cyclic pitch control stick | ASB 67A008 |
036-04 PTZ | ENAC_2004-99.pdf | 30.3.2004 | As established in Bollettino Technico 109EP-43 dated 25.03.2004, as of the effective date of this AD unless already accomplished. | Agusta, A 109E | Chech of bolts P/N NAS625-14 securing the transmission support fittings to the structure. | BT 109EP-43 |
037-04 PTZ | ENAC_2004-141.pdf | 29.4.2004 | As established in Bollettino Technico 206-237, as of the effective date of this AD unless already accomplished. | Agusta-Ball, AB 206A/B | Installing Tail Rotor Blads with S/Ns as indicated in referenced BT. | BT 206-237 |
038-04 PTZ | FAA_AD_2004-10-14.pdf | 25.6.2004 | Before further flight unless already done. | Lycoming Engines, direct-drive reciprocating engines | Inspect 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 PTZ | FAA_AD_2004-10-15.pdf | 9.7.2004 | Within 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 PTZ | DGAC_F-2003-325(A)_R1.pdf | 22.5.2004 | Within compliance times specified unless the action have already been done. | EUROCOPTER, EC 120 helicopters | Crack 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 PTZ | FAA_AD_2004-09-29.pdf | 15.6.2004 | within 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 PTZ | EASA_correction_of_FAA_AD_2004-09-05_Official_Copy.pdf | 2.6.2004 | Wihout 200 total landings or 50 landings after the effective date of thid AD, whichever is later | Cessna Airplane Company, Model 500, 501, 550 and 551airplanes | Inspection of stator disks | |
076-02 R1 PTZ | DGAC_F-2002-340(B)_R1.pdf
DGAC_2002-337(B)R1.pdf | | | AIRBUS, A319, A320 and A321 aircraft | Thrust reverser and Junction Fuselage/wing | |
075-02 R1 PTZ | DGAC_F-2002-370-043(A)_R1.pdf | 19.6.2004 | Within the compliance times specified in this AD. | EUROCOPER, SA 341/342 helicopters | Equipement/furnishing-Electric hoist instalation-Pyrotechnic squib | |
094-02 R1 PTZ | DGAC_F-2002-418(B)_R1.pdf | 19.6.2004 | | AIRBUS, A320 and A321 aircraft | Cancallation notice | |
042-04 PTZ | DGAC_F-2004-070(A).pdf | 26.5.2004 | Effective date | EUROCOPTER, SA 341/342 | Limitations | |
089-03 R1 PTZ | DGAC_F-2003-322(A)_R1.pdf | 5.6.2004 | Within 100 flying hours check and if necessary adjust the stops; Within 500 FH or within 1 year (whichever is reached first), seal the stop screws | EUROCOPTER, AS 350, AS 355, AS 365n, EC 130, SA 366, EC 155 and EC 120 helicopters | Rotor flight controls | |
059-03 R1 PTZ | DGAC_F-2003-260(A)_R1.pdf | 19.6.2004 | Before next flight | EUROCOPTER, AS 350 | Electrical power | |
043-04 PTZ | LBA_D-2004-347.pdf | 2.7.2004 | Prior to and after each flight | DG Flugzeugbau, DG-800A and DG-500M | Power plant | |
044-04 PTZ | LBA_D-2004-348.pdf | 2.7.2004 | Every daily inspection | DG Flugzeugbau, DG-100, DG-200, DG-300, DG-400, DG-500, DG-500M, DG-600 and DG-600M | Lower mounting of the rudder | |
045-04 PTZ | LBA_D-2004-350.pdf | 2.7.2004 | Every daily inspection | DG Flugzeugbau, DG-800A and DG-500M | Power plant - primer valve | |
046-04 PTZ | FAA_AD_2004-13-20.pdf | 3.8.2004 | Within 6 months after the effective date of this AD | GARMIN AT, Appolo GX Series GPS | Modify and test the software | |
013-04 R2 PTZ | CF-2004-04R2.pdf | 8.4.2004 | Part 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 AD | Bombardier, CL-600-2C10 and CL-600-2D24 (CRJ-700 and CRJ-900 Series) | Fuel Ejector Leak Check | |
047-04 PTZ | FAA_AD_2004-12-08.pdf | 23.7.2004 | Within the next 90 days after the effective date of this AD | International Aero Engines AG (IAE), V2500-A1, V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5 and V2533-A5 | Revise the approved continous airworthiness maintenance program | |
048-04 PTZ | CF-1998-14_R4.pdf | 25.6.2004 | When indicated, unless already accomplished | Bombardier, CL-600-2B19 | Flap system failure | |
049-04 PTZ | DGAC_F-2004-074(B).pdf | 5.6.2004 | From the effective date of this AD | AIRBUS, A319, A320 and A321 aircraft | | |
050-04 PTZ | FAA_AD_95-26-05_R1.pdf | 6.7.2004 | 06.07.2004 | Robinson Helicopter Company, Model R44 helicopters | Tis AD rescinds AD 95-26-05 | |
051-04 PTZ | FAA_AD_2003-13-15_R1.pdf | 10.8.2004 | Within 10 hours TIS and thereafter at intervals not exceed 50 hours TIS | Schweizer Aircraft Company, Model 269A, 269-A1, 269B, 269C and TH-55A helicopters | Dye-penetrant inspection | Schweizer SB B-277, dated 25.01.2002 |
052-04 PTZ | DGAC_F-2004-073(B).pdf | 5.6.2004 | No later than 31.12.2005 | AIRBUS, A318, A319, A320 and A321 aircraft | Prevention against explosion risks | SB A320-92-1032 |
053-04 PTZ | DGAC_F-2004-072(B).pdf | 5.6.2004 | Before 30.06.2007 | AIRBUS, A318, A319, A320 and A321 aircraft | Passenger door emergency escape slides | SB A320-35-1338 |
054-04 PTZ | DGAC_F-2004-065(B).pdf | 11.5.2004 | Within the compliance times specified in this AD. | AIRBUS, A318, A319, A320 and A321 aircraft | Shock absorber sliding tube. | |
005-04 R1 PTZ | DGAC_F-2004-022(B)_R1_.pdf | 26.5.2004 | | AIRBUS, A318, A319, A320 and A321 aircraft | CANCALLATION NOTICE Replaced with PTZ 054-04
DGAC_F-2004-065(B).pdf | |
055-04 PTZ | DGAC_F-2004-089(A).pdf | 3.7.2004 | 31.12.2004 | EUROCOPTER, AS 350 helicopters | Hydraulic cut off function. Embody the modifications to the electrical wiring. | ASB 29.00.07 |
056-04 PTZ | DGAC_F-2004-085(A).pdf | 11.7.2004 | 11.07.2004 | EUROCOPTER, AS 350 helicopters | Emergency flotating gear | SB 01.00.35 |
057-04 PTZ | DGAC_F-2004-096(B).pdf | 3.7.2004 | At the latest, each time before using the hoist operator's belt | EUROCOPTER, 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 helicopters | Hoist operator's belt snap hook | |
058-04 PTZ | DGAC_F-2004-088(A).pdf | 23.6.2004 | Either 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 PTZ | DGAC_F-2004-095(B).pdf | 3.7.2004 | Either at next engine shop visit or at next main fuel pump replacement or before 01.01.2007, whichever occours first | CFM INTERNATIONAL, CFM56-2C, CMF56-3 and CFM56-5 turbofan engines | Replacement of main fuel pumps equipped with solid bronze bearings with pumps equipped with bi-metal, aluminium/bronze bearing. | |
060-04 PTZ | LBA_D-2004-352.pdf | 12.7.2004 | Prior to further flight | Hoffmann Propeller GmbH&Co. KG, HO-V343 propellers | Detailed 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 PTZ | CAA_G-2004-0013.pdf | 8.7.2004 | At the next Annual Check after the effective date of this AD | SLINGSBY AVIATION LIMITED, T67A, T67B, T67C, T67M, T67M-MK II, T67M200, T67M260 and T67M260-T3A aircraft | Inspection of aluminium components for exfoliation. | SB 127 Issue 3 or later |
060-04 R1 PTZ | LBA_D-2004-352_R1.pdf | 19.7.2004 | Prior to further flights | Hoffmann Propeller GmbH&Co. KG, HO-V343 propellers | Detailed 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 PTZ | FAA_AD_2004-14-20.pdf | 23.8.2004 | Within the compliance times specified in this AD. | Cessna Aircraft Company, Model 525 Airplanes | The 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 PTZ | CF-2004-18.pdf | 16.9.2004 | 8000 FC since new or 50 FC after effective date of this AD, whichever occurs later | Bombardier, CL-600-2B19 | Superseded by 063-04R1 PTZ
CF-2004-18R1.pdf | ASB A601R-32-099, dated 15 September 2004, or later revision |
060-04 R2 PTZ | LBA_D-2004-352R2.pdf | 23.7.2004 | Prior to further flights | Hoffmann Propeller GmbH&Co. KG, HO-V343 propellers | Detailed 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 PTZ | LBA_D-2004-352_R3.pdf | 18.8.2004 | Within the compliance times specified in this AD. | Hoffmann Propeller GmbH&Co. KG, HO-V343 propellers | 1. 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 PTZ | ENAC_2004-271.pdf | 5.7.2004 | As established in Bulletino Technico 109EP-45 dated 23.06.2004, as of the effective date of this AD unless already accomplished. | Agusta, A 109E | Check of emergency release mechanism of cargo hook installation. | BT 109EP-45 dated 23.06.2004 |
014-04 R1 PTZ | CF-2004-05R1.pdf | 23.3.2004 | Before next flight | Bell, 206A, 206B, 206L Series | Tail Rotor Blade Trailing Edge Skin Cracks | ASB 206-04-100 Rev. B in ASB 206L-04-127 Rev. B |
065-04 PTZ | FAA_AD_2004-19-09.pdf | 7.10.2004 | Within 10 hours time-in-servise (TIS) or 30 days, whichever occours first. | Robinson Helicopter Company, Model R22 series helicopters | To prevent a fatique crack, blade failure and subsequent loss of control of the helicopter | |
066-04 PTZ | CF-2002-05R1.pdf | 30.7.2004 | When indicated unless olready accomplished. | Bombardier, CL-600 "Challenger", CL-600-1A11, CL-600-2A12, CL-600-2B16 | Angle of Attack Transducer | |
067-04 PTZ | CF-2004-13.pdf | 20.8.2004 | When indicated, unless already accomplished | Bombardier, CL-600-2B19 "Regional Jet" | Aileron Power Control Unit Links | ASB A601R-27-130, dated 13 November 2003 |
068-04 PTZ | CF-2004-14.pdf | 24.8.2004 | When indicated, unless already accomplished | Bombardier, CL-600-2C10 and CL-600-2D24 (CRJ-700 and CRJ-900 Series) | Aft Pressure Bulkhead Structure and Hydraulic Lines | |
069-04 PTZ | FAA_AD_2004-19-01.pdf | 1.11.2004 | Within 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 Airplanes | To 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 PTZ | FAA_AD_2004-15-03.pdf | 16.8.2004 | Revised | General Electric Company, CF34-3A1 and -3B1 series turbofan engines | Revised- 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 PTZ | FAA_AD_2004-17-02.pdf | 4.10.2004 | Within the compliance times specified in this AD. | Raytheon Aircraft Company, 65, 90, 99, 100, 200, 300, and 1900 Series Airplanes | This 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 PTZ | FAA_AD_2004-15-03_R1.pdf
2006-04-12.pdf | 31.8.2004 | Superseded | General Electric Company, CF34-3A1 and -3B1 series turbofan engines | Superseded 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 PTZ | FAA_AD_2004-15-18.pdf | 12.9.2004 | Within 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 PTZ | FAA_AD_2004-14-12.pdf | 10.8.2004 | Within 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 Airplanes | To 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 PTZ | DGAC_F-2004-104.pdf | 17.7.2004 | 24.09.2004 | AIRBUS SAS, A318, A319, A320 and A321 aircraft | Temprorary loss of all display units | |
074-04 R1 PTZ | DGAC_F-2004-104(B)_R1.pdf | 28.8.2004 | 24.09.2004 | AIRBUS SAS, A318, A319, A320 and A321 aircraft | Temprorary loss of all display units | |
075-04 2004 | DGAC_F-2004-120(B).pdf | 31.7.2004 | Before June 30 2007 | AIRBUS SAS, A319, A320 and A321 aircraft | Fuel system - Air Release Valve (ARV) | AIRBUS Service Bulletin A320-28-1002, AIRBUS Service Bulletin A320-28-1123 |
076-04 PTZ | DGAC_F-2004-121(B).pdf | 31.7.2004 | Before December 31, 2005, unless olready accomplished | AIRBUS SAS, A319, A320 and A321 aircraft | Lights - Emergency escape path marking | AIRBUS Service Bulletin A320-33-1041 |
077-04 PTZ | DGAC_F-2004-122(B).pdf | 31.7.2004 | Before July 31, 2005, unless already accomplished. | AIRBUS SAS, A318, A319, A320 and A321 aircraft | Flight controls - Spoiler actuators | AIRBUS Service Bulletines A320-27-1158, A320-27-1159. |
078-04 PTZ | DGAC_F-2004-123(B).pdf | 31.7.2004 | Before October 31, 2006. | AIRBUS SAS, A319, A320 and A321 aircraft | Environmental/Air Conditioning - Cargo compartment - Heating temperature sensor | AIRBUS Service Bulletin A320-21-1141 |
088-03 R1 PTZ | DGAC_F-2003-373(B)_R1.pdf | 31.7.2004 | 31.07.2004 | AIRBUS SAS, A318, A319, A320, A321, A330 and A340 aircraft | Temporary loss of all display units. Cancellation notice. Replaced by
DGAC_F-2004-104.pdf | |
079-04 PTZ | DGAC_F-2004-129(B).pdf | 14.8.2004 | Before August 05, 2005, unless already accomplished. | AIRBUS SAS, A319, A320 and A321 aircraft | Fuel - Cable segregation around rack 90 VU | AIRBUS Service Bulletin A320-92-1007 Revision 8 |
032-04 R1 PTZ | DGAC_F-2004-044(B)_R1.pdf | 14.8.2004 | 14.08.2004 | AIRBUS SAS, A319, A320 and A321 aircrafts | Fuel 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 PTZ | DGAC_F-2004-088(A)_R1.pdf | 4.8.2004 | Unless 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 PTZ | DGAC_F-1997-083-096(B)_R1.pdf | 28.8.2004 | | AIRBUS SAS, A320 aircraft | Wing - 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 PTZ | DGAC_F-2004-146(B).pdf | 28.8.2004 | Unless 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 aircraft | Wing - 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 PTZ | DGAC_F-2000-222-079(A)_R1.pdf | 25.9.2004 | At the latest within 10 flying hours, at each check after the last flight of the day. | EUROCOPTER, AS 350 helicopters | Tail rotor - Bearing spacer of the tail rotor head pitch change plate | EUROCOPTER AS 350 Alert Service Bulletin No. 05.00.33 R1 |
084-04 PTZ | DGAC_F-2004-148(A).pdf | 11.9.2004 | Within 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 aeroplanes | Windows-Windshield inspection | SB EADS SOCATA No 10-144-56 dated June 2004. |
085-04 PTZ | DGAC_F-2004-150(B).pdf | 11.9.2004 | Within the compliance times specified in this AD. | AIRBUS SAS, A320 aircraft | Auxiliary 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 PTZ | LTA_A-2004-001.pdf | 1.10.2004 | Inspect within 50 hours Time-in-Service (TIS) after the effective date of | Rotax 912 A/F/S and 914 F Series engines | Inspection 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 PTZ | LTA_A-2004-004.pdf
SUPERSEEDED BY 087-04R2 PTZ | 1.10.2004 | Superseeded by A-2004-004R2 | Rotax 912 A/F/S and 914 F Series engines | Introduction of new coolant liquid type “EVANS NPG+”
A-2004-004R2.pdf | SB 912-043 and 914-029 |
088-04 PTZ | LTA_A-2004-005.pdf | 1.10.2004 | Inspect within 50 hours Time-in-Service (TIS) after the effective date of this AD. | Rotax 914 F-Series engines | Inspection 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 PTZ | CF-2004-22.pdf | 26.10.2004 | Within the compliance times specified in this AD. | Bombardier, CL-600 "Challenger", CL-600-1A11, CL-600-2A12, CL-600-2B16 | Angle of Attack Vane. | ASB A600-0729, ASB A601-0571, ASB A601-0571, ASB A604-27-026 |
050-01 R2 PTZ | CAA-AD-T-037_2001R2.pdf | Upon receipt | Before further flight | LETECKÉ ZÁVODY a.s., L 410 and L 420 aircraft | Values of flight levels and Maximum Operating Limit Speed | |
044-04 R1 PTZ | LBA_D-2004-348_R1.pdf | 16.9.2004 | Every daily inspection | DG 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:all | Lower mounting of the rudder. This AD supersedes AD 044-04 PTZ
LBA_D-2004-348.pdf | |
090-04 PTZ | ENAC_2004-351.pdf | 22.9.2004 | As established in the referenced Bollettino Technico, as of the effective date of this AD unless olready accomplished. | Agusta-Bell; AB205A1, AB212 and AB412 helicopters | Tail 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 PTZ | DGAC_F-2004-121(B)_R1.pdf | 23.10.2004 | Before December 31, 2005, unless already accomplished | AIRBUS SAS, A319, A320 and A321 aircraft | Lights - Emergency escape path marking - BRUCE FPEEPMS | AIRBUS Service Bulletin A320-33-1041 |
091-04 PTZ | CAA_G-2004-0026.pdf | 2.11.2004 | Before further flight | Cameron Balloons Limited; Shadow/Shadow Stealth - Triple, Quadand Stratus Triple, Quad gimballed burnerassemblies | Inspect the burner support plate andmounting tube | Cameron Balloons Ltd SB No 13 issue A or later EASA approved revision. |
092-04 PTZ | CF-2004-20.pdf | 1.11.2004 | Within 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 Shields | Bulletin 601R-57-021, Revision C, dated 23 February 2004, or later revisions |
093-04 PTZ | CAA_G-2004-0028.pdf | 26.11.2004 | Within 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 PTZ | DGAC_F-2004-168(B).pdf | 20.10.2004 | At the next opportunity, but not later than three calendar days following the effective date of this AD. | AIRBUS SAS; A318, A319, A320 and A321 aircraft | Loss of integrated standby instrument system (ISIS). Superseeded by 094-04R1 PTZ
F-2004-168R1.pdf | |
095-04 PTZ | DGAC_F-2004-170(A).pdf | 6.11.2004 | Within the compliance times specified in this AD. | EUROCOPTER; AS 350, AS 355, AS 332, SA 341/342 helicopters | Equipment and furnishings - Hoists hooks | EUROCOPTER 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 PTZ | DGAC_F-2004-172(B).pdf | 6.11.2004 | Before April 30, 2005. | AIRBUS SAS; A318, A319, A320 and A321 aircraft | Fire protection - Cargo compartment water drain valves. | AIRBUS Service Bulletin A320-52-1124 |
097-04 PTZ | DGAC_F-2004-173(B).pdf | 6.11.2004 | No later than December 31st, 2009. | AIRBUS SAS; A320 aircraft | Fuel system - Prevention against explosion risks - Electrical cables | AIRBUS Service Bulletin A320-24-1062 R5. |
098-04 PTZ | DGAC_F-2004-174(A).pdf | 20.11.2004 | No later than within one month. | EUROCOPTER; AS 350 helicopters | Hydraulic power - Hydraulic power loss. | |
077-02 R1 PTZ | DGAC_F-2002-344-093(A)_R1.pdf | 20.11.2004 | Before 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 helicopters | Doors - 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 2004 | DGAC_F-2004-137(B).pdf | 20.11.2004 | Before March 31, 2009. | AIRBUS SAS; A319, A320 and A321 aircraft | Landing gear - Parking brake system. Modify the parking brake system. | AIRBUS Service Bulletin A320-32-1201 Revision 1. |
100-04 PTZ | FAA_AD_2004-23-17.pdf | 7.12.2004 | Within 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 PTZ | FAA_AD_2004-23-02.pdf | 23.12.2004 | Within the compliance times specified in this AD. | Raytheon Aircraft Company 65, 90, 99, 100, 200, and 1900 Series | The 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 PTZ | FAA_AD_2004-23-16.pdf | 7.12.2004 | Within the compliance times specified in this AD. | McCauley Propeller Systems Five-Blade Propeller Assemblies | Performing the eddy-current inspection | McCauley ASB No. A247, dated April 30, 2004 and Alert Service Bulletin No. ASB247A, Revision A, dated August 18, 2004, |
103-04 PTZ | LBA_D-2004-489.pdf | 11.11.2004 | Within 50 flight hours, but not later than 3 months. | Extra Flugzeugbau; EA-300, EA-300/S, EA-300/L and EA-300/200 | To 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 PTZ | SUPERSEEDED | 28.12.2004 | Superseeded by A-2004-004R2 | Bombardier; Rotax 912 A/F/S and 914 F Series engines | Replacement 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 PTZ | LTA_A-2004-005_R1.pdf | 28.12.2004 | Initial inspection within 50 hours Time-in-Service (TIS) after receipt of this AD, and | Bombardier; Rotax 914 F-Series engines | Inspection 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 PTZ | DGAC_F-2001-580-085(B)_R2.pdf | 18.12.2004 | In compliance with the instructions described in § 2.A. of Revision 1 of referenced EUROCOPTER AS350 Alert Service Bulletin (ASB) No. 05.00.37 | EUROCOPTER; AS 350 helicopters | Rotor flight controls - Tail servocontrols - Eye end fitting locking | EUROCOPTER AS 350 Alert Service Bulletin No. 05.00.37 R1 |
053-00 R1 PTZ | DGAC_F-2000-521-160(B)_R1.pdf | 18.12.2004 | 18.12.2004 | AIRBUS SAS, A319, A320 and A321 aircraft | Main 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 PTZ | DGAC_F-2004-189(B).pdf | 18.12.2004 | Within the compliance times specified in this AD. | AIRBUS SAS, A319, A320 and A321 aircraft | Keel 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 PTZ | CF-2004-23.pdf | 30.11.2004 |
