Številka PTZ | Referenčna PTZ | Datum efektive | Rok izvršitve | Proizvajalec | Vsebina PTZ | Referenčni SB |
001-05 PTZ | ENAC_2004-522.pdf | 30.12.2004 | Within 30 days as of the effective date of this AD, unless already accomplished. | Vulcanair (former Partenavia); all P68 airplane variants | Carry out the operational checks/inspections/modifications. | MSB No.128, dated 12. October 2004 |
002-04 PTZ | F-2004-192_(A).pdf | 1.1.2005 | Before January 31, 2006. | TURBOMECA; ARRIEL 2 turboshaft engines | Check the torque measurements made by the production Digital Engine Control Unit (DECU) which is installed on the engine | Mandatory Service Bulletin A 292 73 2816 original issue or later approved revision. |
104-04 R1 PTZ | F-2004-189_(B)_R1.pdf | 15.1.2005 | Within the compliance times specified in this AD. | AIRBUS SAS; A319, A320 and A321 aircraft | Inspection of the uppermost fastener holes. | AIRBUS Service Bulletin A320-53A1135 Revision 3, A320-53-1140 Revision 2, A320-53-1148, A320-53-1149, A320-53-1160, A320-53-1158 |
003-05 PTZ | F-2005-010_(A).pdf | 5.1.2005 | No later than within the next 25 flying hours, then at intervals of no more than 100 flying hours. | EUROCOPTER; AS 350 helicopters | Check the spar of the upper and lower vertical fins for absence of cracks. | EUROCOPTER AS 350 Alert Telex No. 05.00.46 |
004-05 PTZ | F-2004-196_(A).pdf | 28.12.2004 | No later than within the next 50 flying hours from the effective date of this AD | EUROCOPTER; AS 350 helicopters | Check of the tail servo-control. | Alert Telex EUROCOPTER AS 350 No 67.00.30. |
005-05 PTZ | F-2005-013_(B).pdf | 29.1.2005 | 29.01.2005 | AIRBUS SAS; A320 aircraft | Insert in the Minimum Equipment List (MEL) of the aircraft, the Temporary Revision (TR) TR No 01-27/01H issue 01 of the Master Minimum Equipment List (MMEL) | AIRBUS Service Bulletin A320-27-1149, MMEL A318/A319/A320/A321 TR No 01-27/01H issue 01 approved by JAA on November 3, 2004. |
006-05 PTZ | FAA_AD_2004-26-02.pdf | 26.1.2005 | at the first piece-part exposure after 6,000 cycles-since-new (CSN), but no later than 20,000 CSN. | GE Aircraft Engines (GE); CF34-3A, CF34-3A2, CF34-1A, CF34-3A1, CF34-3B, and CF34-3B1 Series Turbofan Engines | HPC Spool Replacement After the effective date of this AD: (1) Do not install any HPC forward spool, P/N 6078T56P03; (2) Do not install any HPC forward spool, P/N 6078T56P04, with more than 0 CSN. | |
007-05 PTZ | CF-2005-03.pdf | 8.2.2005 | Within 14 days of the effective date of this directive. | Bombardier Inc.; Model CL-600-1A11 (600), CL-600-2A12 (601 Variant), CL-600-2B16 (601-3A Variant), CL-600-2B16 (601-3R Variant), CL-600-2B16 (604 Variant) | Amend all copies of the AFM by incorporating the applicable Temporary Revision (TR) and advise all flight crews on the changes introduced through the AFM TR. | |
008-05 PTZ | CF-2005-01.pdf | 2.2.2005 | Within 14 days after the effective date of this directive. | Bombardier Inc.; Model CL-600-2B19 Regional Jet Series 100 and 440 aircraft | Amend the AFM by inserting Temporary Revision (TR) RJ/149-1 dated 1 February 2005 and advise all flight crews on the changes introduced through the AFM TR. | |
009-05 PTZ | CF-2005-02.pdf | 2.2.2005 | Within 14 days after the effective date of this directive: | Bombardier Inc.; CL-600-2C10 Regional Jet Series 700 and 701, and CL-600-2D24 Regional Jet Series 900 aircraft. | Amend all copies of the AFM by incorporating the applicable Temporary Revision (TR) and dvise all flight crews on the changes introduced through the AFM TR. | |
010-05 PTZ | CF-2004-27.pdf | 28.5.2004 | At the next annual inspection, but not later than 31 January 2005, unless already accomplished. | Bell Helicopter Textron Canada (BHTC); Model 206B helicopters, Serial Number 3567 through 4577 and 5101 through 5284. | Inspect the inside door handle assembly. | BHTC ASB 206-04-102, dated 24 September 2004 |
011-05 PTZ | FOCA_AD_HB-2004-491.pdf | 30.12.2005 | Within the next 60 days after 30 December 2004. | PILATUS AIRCRAFT LTD; All Model B4-PC 11, B4-PC 11A and B4-PC 11AF gliders. | Inspect the control-column support P/N 112.35.11.072 for cracks. If during the inspection in paragraph 3.1.1. cracks are found; before further flight, replace the support P/N 112.35.11.072 with a new part. This AD superseded 027-03 R1 PTZ (FOCA AD HB-2003-199R1) | PILATUS B4-PC 11 Service Bulletin No. 1005 REV No. 2, dated 22 April 2004. |
012-05 PTZ | FAA_AD_98-20-38R1.pdf | 18.2.2005 | Within 30 days after November 4, 1998 | Raytheon Aircraft Company; Beech 200 Series Airplanes | Revise the FAA-approved Airplane Flight Manual (AFM) by incorporating the following into the Limitations Section of the AFM. This may be accomplished by inserting a copy of this AD in the AFM. | |
013-05 PTZ | FAA_AD_2005-01-18.pdf | 1.3.2005 | Within the compliance times specified in this AD. | Raytheon Aircraft Company; Beech 100, 200, and 300 Series Airplanes | Detect and correct any cracked fuselage stringers in the rear pressure bulkhead area, which could result in structural damage to the fuselage. | Raytheon Mandatory Service Bulletin SB 53-2472, Rev. 4, Issued: June, 1993, Revised: July, 2003. |
014-05 PTZ | EASA_V2500_PAD_2005_001.pdf | 17.1.2005 | Within 500 flight hours but no later than December 31, 2005 or at the next removal of the Fuel | International Aero Engines (IAE); V2500-A5 series engines | Inspect the area of the fuel filter cover of the Fuel Cooled Oil Cooler (FCOC). If fuel leakage is observed. This AD supersedes EASA member state AD number: France
DGAC_2003-355(B)_R2.pdf | Service Bulletin IAE 79-0085, Service Bulletin IAE 79-0086 |
015-05 PTZ | G-2005-0004.pdf | 30.1.2005 | Before further flight. | SLINGSBY AVIATION LTD; Model T67 all Series aeroplanes. | Thereafter, inspect the tailplane support brackets. Cracked tailplane support brackets must be replaced. Repetitive inspection of tailplane support brackets for aircraft where the brackets have previously been replaced. | SLINGSBY_No__179_R3.pdf |
090-02 R2 PTZ | CF-2002-35R2.pdf | 30.1.2005 | Within 60 days of the effective date of this directive, | Bombardier Inc.; Model CL-600-2B19 Airplane | Aileron Control Checks. Amend the Transport Canada approved maintenance schedule | |
016-05 PTZ | FAA_AD_2005-01-19.pdf | 23.2.2005 | Within 180 days after effective date of this AD | GARMIN International Inc.; GTX 33, GTX 33D, GTX 330, and GTX | Software Upgrade | Mandatory Software Service Bulletin No.: 0304, Rev B, dated June 12, 2003 or No.: 0409, dated July 19, 2004 |
017-05 PTZ | FAA_AD_2005-01-04.pdf | 22.2.2005 | Within the compliance times specified in this AD. | Raytheon Aircraft Company; 90, 99, 100, 200, and 300 Series | Documented compliance with AD 98–15–13 or follow PART II of the ACCOMPLISHMENT INSTRUCTIONS section in Raytheon Aircraft Mandatory Service Bulletin SB 2718, Revision 1, dated June 1997; or Revision 2, dated April 2000. | Mandatory Service Bulletin SB 2718, Revision 1, dated June 1997; or Revision 2, dated April 2000. |
018-05 PTZ | FAA_AD_2005-01-10.pdf | 22.2.2005 | Within the next 100 hours TIS after effective date of this AD), unless already done. | The New Piper Aircraft, Inc.; Models PA-23-235, PA-23-250, and PAE23-250 Airplanes | Replace any oil reservoir and installed oil reservoir hoses. | The New Piper Aircraft, Inc. Vendor Service Publication No. 166, dated August 20, 2004, and the procedures in Garrett Aviation Service Bulletin No. 1002143, Revision A, dated June 18, 2004. |
050-03 R1 PTZ | CF-2003-14R1.pdf | 26.2.2005 | Within the compliance times specified in this AD. | Bombardier Inc.; Model CL-600-2B19 Airplane | A. Inspection and Repair of Electrical Harnesses B. Modification of Routing and Support of Electrical Harnesses | Revision A of ASB A601R-27-101 or the original issue of ASB A601R-27-133 |
018-05 PTZ | FAA_AD_2005-05-53_Emergency.pdf | 5.3.2005 | Prior to further flight | Cessna Aircraft Company (Cessna); Models 172R, 172S, 182T, and T182T Airplanes | Follow Chapter 5 TIME LIMITS/ MAINTENANCE CHECKS of whichever of the following applies: • Model 172 Maintenance Manual using the List of Effective Pages, dated June 7, 2004. • Model 182/T182 Maintenance Manual using the List of Effective Pages, dated March 1, 2004. | |
019-05 PTZ | F-2005-028_(B).pdf | 26.2.2005 | Superseded by EU-2006-0176 (Si-046-06 PTZ) | AIRBUS SAS; A318, A319, A320 and A321 aircraft | Fuel system - Prevention against explosion risks - In tank bonding | Service Bulletin AIRBUS A320-28-1104. |
020-05 PTZ | F-2005-031_(B).pdf | 16.2.2005 | Before December 31st, 2009, | AIRBUS SAS; A320 aircraft | Fuel system - Fuel pumps - Prevention against explosion risks | AIRBUS Service Bulletin A320-28-1008 Revision 1 and A320-28-1054 |
021-05 PTZ | F-2005-032_(A).pdf | 16.2.2005 | Within the compliance times specified in this AD. | EUROCOPTER; AS 350 helicopters | Doors - Pin of the sliding door rear fitting | EUROCOPTER AS 350 Alert Telex No. 05.00.47 |
142-02 PTZ | F-2002-606_(A).pdf | 12.3.2005 | No later than within 110 flying hours or 3 months following the effective date of the original issue of this AD | EUROCOPTER; EC 120 helicopters | Rotor flight controls - Collective pitch lever | EUROCOPTER EC120 Alert Service Bulletin No. 67A009 |
022-05 PTZ | F-2005-035_(B).pdf | 12.3.2005 | Unless already accomplished, before 750 flight cycles, 600 flight hours or 100 days | AIRBUS SAS; A319, A320 and A321 aircraft | Outer wing - Inspection of the main landing gear support rib 5 | AIRBUS Alert Service Bulletin A320-57A1136 |
023-05 PTZ | F-2005-040_(B).pdf | 12.3.2005 | Not later than December 31, 2009, | AIRBUS SAS; A300, A310, A300-600, A319, A320, A321, A330, | Equipment/Furnishings - Non Textile Floor (NTF) replacement | AMM AIRBUS 25-28-12/42 PB 401 |
024-05 PTZ | FAA_AD_2005-05-15.pdf | 18.4.2005 | Within the compliance times specified unless the actions have already been done. | Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Co.) TFE731-2 and -2C series, and TFE731-3, -3A, -3AR, -3B, -3BR, and -3R series turbofan engines | Initial Inspection for TFE731-2 and -2C Series Engines. Repetitive Inspections for TFE731-2 and -2C Series Engines. Disk Replacement. | Honeywell Service Bulletin No. TFE731–72–3369RWK |
025-05 PTZ | F-2005-029_R1_(B).pdf | 26.3.2005 | Within one month following the effective date of this AD, except aircraft that have received AIRBUS modification 30650 or 30872 in production or AIRBUS (SB) A320-25-1248 in service. | AIRBUS SAS; A318, A319, A320 and A321 aircraft | NORTHROP-GRUMMAN (previously LITTON) ADIRU - Modification of shelf supports | AIRBUS Service Bulletin A320-25-1248 Revision 1 |
026-05 PTZ | F-2005-046_(B).pdf | 26.3.2005 | Within 2400 flight hours, or within 15 months from the effective date of this AD, whichever occurs first, | AIRBUS SAS; A319, A320 and A321 aircraft | Lavatories - DASELL lavatory walls corrosion | AIRBUS Service Bulletins A320-25-1365, A320-25-1289 and A320-25-1357 |
027-05 PTZ | F-2005-047_(A).pdf | 26.3.2005 | Compliance with this AD is required as indicated, unless already done. | TURBOMECA; ASTAZOU III turboshaft engines | Civil use | TURBOMECA Mandatory Service Bulletin A268 72 0 |
095-04 R1 PTZ | F-2004-170_R1_(A).pdf | 26.3.2005 | 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 SB No. 01.33. |
028-05 PTZ | F-2005-042_(A).pdf | 26.3.2005 | Within the compliance times specified in this AD. | EUROCOPTER; AS 350 | Rotor flight controls - Yaw control | EUROCOPTER AS 350 Alert Service Bulletin No. 67.00.26 R1 |
029-05 PTZ | F-2005-051_(B).pdf | 9.4.2005 | Unless already accomplished, within 20 months since first flight or within 600 flight hours from the. | AIRBUS SAS; A318, A319, A320 and A321 aircraft | Flight controls - Trimmable horizontal stabilizer actuator | AIRBUS Service Bulletin A320-27-1164 Revision 2. |
026-02 R1 PTZ | F-2002-125_(B).pdf | 26.2.2005 | | AIRBUS SAS; A319, A320 and A321 aircraft | CANCELLATION NOTICE | |
011-02 R1 PTZ | F-2002-075_R1_(B).pdf | 26.3.2005 | Within the compliance times specified in this AD. | AIRBUS SAS; A319, A320 and A321 aircraft | Main Landing Gear side-stay cuff lug | AIRBUS Service Bulletin A320-32A1224 and A320-32-1223 |
030-05 PTZ | F-2005-052_(B).pdf | 9.4.2005 | Unless already accomplished, within 600 flight hours from the effective date of this AD | AIRBUS SAS; A318, A319, A320 and A321 aircraft | 103VU panel - Hinge pin inspection | AIRBUS AOT 25A1440 dated February 15, 2005 |
060-04 R4 PTZ | LBA_D-2004-352R4.pdf | 10.4.2005 | 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. Ultrasonic inspection of the propeller hub. 4. Eddy current inspection of the propeller hub, if ultrasonic inspection shows any signs of damages. 5. 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. | SB_Hoffmann_E-015-B.pdf
SI_Hoffmann_61-10-05_SI_E_4D.pdf |
031-05 PTZ | CF-2005-04.pdf | 7.3.2005 | Within 30 days after the effective date of this directive | Bombardier Inc.; Model CL-600-2B19 Airplane, Serial Number 7003 and subsequent. | Horizontal Stabilizer Trim Actuator (HSTA) Secondary Load Path Indicator Inspection | Bombardier Alert Service Bulletin A601R-27-128 |
032-05 PTZ | CF-2005-05.pdf | 8.3.2005 | Within 30 days after the effective date of this directive | Bombardier Inc.; Model CL-600-2B19 Airplane, Serial Numbers 7003 and subsequent, that have not incorporated Modsum TC601R16421 or its subsequent revisions. | Revision of Structural Inspection Program | |
033-05 PTZ | FAA_AD_83-08-01R2.pdf | 11.5.2005 | Compliance with this AD is required as indicated, unless already done. | Hartzell Propeller Inc. (Formerly TRW Hartzell Propeller); HC-B3TN-2, HC-B3TN-3, HC-B3TN-5, HC-B4TN-3, HC-B4TN-5, HC-B4MN-5, HC-B5MP-3 | a) Install all new propellers and serviceable propellers, as follows, before further flight or b) Within the next 300 hours time-in-service after the effective date of this AD, do the following on all applicable turbopropellers presently installed with P/N A-2047 attaching bolts | |
030-05 R1 PTZ | F-2005-052_R1_(B).pdf | 9.4.2005 | Unless already accomplished, within 600 flight hours from the effective date of this AD at original issue | AIRBUS SAS; A318, A319, A320 and A321 aircraft | 103VU panel - Hinge pin inspection | AIRBUS AOT 25A1440 dated February 15, 2005 |
096-04 R1 PTZ | F-2004-172_R1_(B).pdf | 23.4.2005 | Before December 31, 2005 | AIRBUS SAS; A318, A319, A320 and A321 aircraft | Fire protection - Cargo compartment water drain valve | AIRBUS Service Bulletin A320-52-1124 |
034-05 PTZ | F-2005-058_(B).pdf | 23.4.2005 | Before December 31st, 2009 | AIRBUS SAS; A320 and A321 aircraft | Fuel system - Prevention against explosion risks - In tank bonding | AIRBUS Service Bulletin A320-28-1055 Revision 1 |
035-05 PTZ | F-2005-057_(B).pdf | 23.4.2005 | Within the compliance times specified in this AD. | AIRBUS SAS; A319, A320 and A321 aircraft | Passenger door - Slide raft telescopic girt bar | AIRBUS All Operator Telex A320-52A1111, A320-52-1112 Revision 05 |
036-05 PTZ | F-2005-056_(B).pdf
| 23.4.2005 | Before December 31st, 2009. | AIRBUS SAS; A320 aircraft | Fuel system - Prevention against explosion risks - In tank bonding | AIRBUS Service Bulletin A320-28-1067 Revision 2. |
037-05 PTZ | UF-2005-073_R1_(A).pdf
F-2005-073_(A)_R1.pdf | 29.4.2005 | Effective date of this AD | TURBOMECA; ARRIUS 2F turboshaft engines | Module 2 replacement | Alert Fax TURBOMECA No 057/05/DSO/TM dated April 26, 2005. |
038-05 PTZ | CF-2005-10.pdf | 2.5.2005 | Within the next 100 hours air time, but no later than 10 June 2005 fort Part 1 and At the first occasion when aircraft is defueled, but not later than 01 December 2005 for Part 2 | Bell Helicopter Textron Canada (BHTC); Model 206 A/B series helicopters: | Fuel Distribution System Superseeded by 038-05R1 PTZ
CF-2005-10R1.pdf | ASB 206-05-103, dated 11 February 2005 |
009-04 R1 PTZ | CF-2004-01R1.pdf | 20.2.2004 | Within 1000 hours air time, after the effective date of this directive. Repeat the inspection at intervals not to exceed 1000 hours air time. | Bombardier Inc.; Model CL-600-2B19, serial numbers 7003 through 7067, 7069 through | Engine Throttle Control Gearbox | Bombardier SB 601R-76-019 |
039-05 PTZ | FAA_AD_2005-10-12.pdf | 2.6.2005 | Required as indicated, unless accomplished previously. | Schweizer Aircraft Corporation; Model 269C, C-1, and D Helicopters | To prevent separation of the inner spring tube from the lateral trim control housing, the associated loss of trim control, increased local resistance to right cyclic stick movement, and subsequent emergency landing or loss of control of the helicopter. | Schweizer Service Bulletins B-283.1 and C1B-017.1, both dated March 4,2005 and DB-012, dated February 8, 2005, |
040-05 PTZ | UF-2005-087.pdf | 31.5.2005 | Within the compliance times specified in this AD. | EUROCOPTER; AS 350 and AS 355 helicopters | Untimely firing of squibs on GOODRICH electric hoists. | EUROCOPTER Alert Telex AS 350 n° 25.00.94 and AS 355 n° 25.00.84 |
041-05 PTZ | FAA_AD_2004-25-16_R1.pdf | 20.6.2005 | Within the compliance times specified in this AD. | Kelly Aerospace Power Systems (formerly owned by ElectroSystems, JanAero Devices, Janitrol, C&D Airmotive Products, FL Aerospace, and Midland-Ross Corporation) | Fuel regulator shutoff valve | Kelly Aerospace Power Systems Service Bulletin No. A–107A |
042-05 PTZ | F-2005-076_(A).pdf | 11.5.2005 | Within the compliance times specified in this AD. | EUROCOPTER; EC 120 helicopters | Tail rotor drive shaft - Rear drive shaft friction ring | EUROCOPTER EC 120 Alert Telex No. 05A006. |
043-05 PTZ | CF-2005-13.pdf | 6.6.2005 | Compliance is required as indicated unless already accomplished. | Bombardier Inc.; CL-600-2B19 | Cracking of Aft Pressure Bulkhead Web Superseded by 043-05 R1 PTZ
CF-2005-13R1.pdf | |
044-05 PTZ | FAA_AD_2005-12-06.pdf | 19.7.2005 | Within the compliance times specified in this AD. | Teledyne Continental Motors (Formerly Bendix) S-20, S-1200, D-2000, and D-3000 Series Magnetos | Initial Inspections of Impulse Coupling Assemblies. Repetitive Inspections of Impulse Coupling Assemblies. | TCM SB No. 639, dated March 1993, TCM Service Information Letter No. SIL648, dated October 18, 1994. |
045-05 PTZ | FAA_AD_2005-13-16.pdf | 8.8.2005 | Within the compliance times specified in this AD. | The New Piper Aircraft, Inc.: PA-34-200, PA-34-200T, and PA-34-220T airplanes, | The actions specified in this AD are intended to detect, correct, and prevent failure in certain components of the NLG, lack of cleanliness of the NLG due to inadequate maintenance, or lack of lubricant in the NLG or NLG components. This failure of the NLG could lead to loss of control of the airplane during take-off, landing, or taxiing operations. This AD supersedes AD 93-24-14. | Service Bulletin No. 1123A, dated November 30, 2004. |
046-05 PTZ | FAA_AD_2005-13-10.pdf | 9.8.2005 | Within the next 30 days after August 9, 2005 | Cessna Aircraft Company: 172R, 172S, 182T, T182T, 206H and T206H Airplanes | Replace any incorrect amp circuit breaker with the required 40-amp circuit breaker. | Cessna Service Bulletin No. SB05–24–01, January 31, 2005. |
047-05 PTZ | FAA_AD_2005-10-13.pdf | 22.6.2005 | At the next time the gas producer turbine rotor is disassembled for any reason, or within 1,750 hours time-since-lastoverhaul, inspection after the effective date of this AD, whichever occurs first, but no later than October 31, 2011, unless already done. | Rolls-Royce Corporation (Formerly Allison Engine Company) 250-B17B, -B17C, -B17D, -B17E, -C20, -C20B, -C20F, -C20J, -C20S, and -C20W Turboprop and Turboshaft Engines | Install a turbine energy absorbing ring | Rolls-Royce Corporation Alert Commercial Engine Bulletin No. CEB-A-1255, Revision 4, dated September 29, 2004 |
014-04 R1 PTZ | CF-2004-05R2.pdf | 30.6.2005 | Before next flight | Bell Helicopter Textron Canada: Models 206A, 206B, 206L Series | Revision 1 of this directive introduced terminating action requiring affected blades to be inspected for acceptable tail rotor blade skin thickness. | ASB 206-04-100 Rev. C in ASB 206L-04-127 Rev. C |
048-05 PTZ | FAA_AD_2005-11-05.pdf | 18.7.2005 | Within compliance times specified unless the action have already been done. | Precise Flight, Inc.: Models SVS I and SVS IA Standby Vacuum Systems | Incorporate the airplane flight manual supplement (AFMS) in the airplane flight manual with the appropriate revision, install placards described in the AFMS and upgrade the Model SVS I or SVS IA SVS to the Model VI SVS. | |
049-05 PTZ | FAA_AD_2005-13-07.pdf | 27.7.2005 | Within compliance times specified unless the action have already been done. | Honeywell International Inc. (Formerly AlliedSignal Inc. and Garrett Turbine Engine Co.) TFE731-2 and -3 Series Turbofan Engines | Replace discs | Honeywell International, Inc. Service Bulletin No. TFE731-72-3682, dated November 26, 2002 |
050-05 PTZ | F-2003-001_(B)_R2.pdf | 18.6.2005 | Within the compliance times specified in this AD. | CFM INTERNATIONAL; CFM56-5 and CFM56-5B engines | Engine indicating - EGT harnesses and couplings | CFM56-5 SB 77-0020 Revision 3 (or any subsequent approved issue), CFM56-5B SB 77-0008 Revision 3 (or any subsequent approved issue). |
051-05 PTZ | F-2005-086_(A).pdf | 18.6.2005 | Within the compliance times specified in this AD. | EUROCOPTER; EC 120 helicopters | Rotor flight controls - Collective torque tube assembly | EUROCOPTER EC 120 Alert Service Bulletin No. 67A014 |
052-05 PTZ | F-2005-088_(A).pdf | 8.6.2005 | within 25 engine operating hours and at the latest by July 31st, 2005. | TURBOMECA; ARRIUS 2F turboshaft engines | Fuel system and controls - Check of correct position of adjusted FCU fuel filter | Mandatory Alert Service Bulletin No A319 73 4823 (or any subsequent approved issue), ARRIUS 2F Maintenance Manual Ref X 319 L6 301 2. |
053-05 PTZ | CF-2005-18.pdf | 11.7.2005 | Compliance is required as indicated unless already accomplished. | Bombardier Inc.; CL-600-2B19 aircraft | Missing Restrictor on Refuel / Defuel Shut-Off Valves | Bombardier Alert Service Bulletin A601R-28-064, dated 21 April 2005, |
054-05 PTZ | LTA_2005-196.pdf | 14.6.2005 | Immediately after the effective date of this airworthiness directive. | DG-Flugzeugbau, DG-300, DG-300 ELAN, DG-300 ELAN ACRO, DG-300 CLUB ELAN, DG-300 CLUB ELAN ACRO | Increase of service life and revision of the appropriate maintenance manual. | DG-Flugzeugbau Technical Note No. 359/23 of 3 February 2005.
LTA_2005-196-TN-359-23.pdf |
055-05 PTZ | F-2005-101_(B).pdf | 2.7.2005 | From September 02, 2005, it is mandatory to strictly adhere to the requirements of the AIRBUS A318/A319/A320/A321 CMR document at issue 22. | AIRBUS SAS; A318, A319, A320 and A321 aircraft | Certified limitations - MPD Section 9-3 | AIRBUS A318/A319/A320/A321 CMR document reference AI/ST4/993.436/88 (Section 9-3 of the MPD), issue 22 approved on May 03, 2005 |
078-04 R1 PTZ | F-2004-123_(B)_R1.pdf | 2.7.2005 | Before May 31, 2007 | AIRBUS SAS; A319, A320 and A321 aircraft | Environmental/Air conditioning - Cargo compartment - Heating temperature sensor | AIRBUS Service Bulletin A320-21-1141 |
056-05 PTZ | F-2005-087_(A).pdf | 30.5.2005 | Within the compliance times specified in this AD. | EUROCOPTER; AS 350 and AS 355 helicopters | Equipment/Furnishings - Untimely firing of squibs on GOODRICH electric hoists | EUROCOPTER Alert Telex AS 350 n° 25.00.94 and AS 355 n° 25.00.84 |
057-05 PTZ | EASA_AD_05_0019_Robinson_R22.pdf | 5.7.2005 | Before 01 December 2005. | Robinson Helicopter Company; R22/ All models | Rotor Blades - Replacement | R22 Service Bulletin SB-94, dated 14.12.2004. |
058-05 PTZ | FAA_AD_2005-13-36.pdf | 9.8.2005 | Within 100 flight hours, or 90 days after the effective date of this AD, whichever occurs first | Learjet Inc.; Model 23, 24, 24A, 24B, 24B-A, 24C, 24D, 24D-A, 24E, 24F, 24F-A, 25, 25A, 25B, 25C, 25D, 25F, 28, 29, 31, 31A, 35, 35A (C-21A), and 36 Airplanes | Do a detailed inspection of the center ball of the aileron control cable or cables for a defective swage. | Bombardier alert service bulletins A23/24/25–27–17 December 23, 2002, A23/24/25–27–17 December 23, 2002, A31–27–25 December 23, 2002 and A35/36–27–42 December 23, 2002. |
059-05 PTZ | FAA_AD_2005-14-11.pdf | 17.8.2005 | Within 10 hours time-in-service after the effective date of this AD. | Hartzell Propeller, Inc., McCauley Propeller Systems, and Sensenich Propeller Manufacturing Company, Inc. Propellers | This AD requires maintenance actions amounting to an overhaul of the affected propellers. | Special Airworthiness Information Bulletin No. NE-01-19, dated March 20, 2001, |
060-05 PTZ | FAA_AD_2005-14-12.pdf | 29.7.2005 | Within the compliance times specified unless the actions have already been done. | Hartzell Propeller Inc.; Models HC-B3TN-2, HC-B3TN-3, HC-B3TN-5, HC-B3MN-3, HC-B4TN-3, HC-B4TN-5, HC-B4MN-5, HC-B4MP-3, HC-B4MP-5, and HCB5MP-3 Propellers | Visual Inspections and Torque Checks | AD 2004-21-01, Amendment 39-13822 (69 FR 60952) also pertains to the subject of this AD. |
061-05 PTZ | FAA_AD_2005-15-10.pdf | 26.8.2005 | Within the compliance times specified in this AD. | The New Piper Aircraft, Inc. Models PA-34-200T, PA-34-220T, PA-44-180, and PA-44-180T Airplanes | Visually inspect any installed aircraft heater fuel pump for leakage. | The New Piper Aircraft, Inc. Service Bulletin No. 1127, dated February 26, 2003 and No. 1127B, dated April 18, 2005; Kelly Aerospace Power Systems Service Information Letter Bulletin No. A-110A, dated March 6, 2003 and No. A-110B, dated December 20, 2004. |
062-05 PTZ | UF-2005-161_(A).pdf | 16.9.2005 | At the latest before the next hoisting operation, | EUROCOPTER; SA 341/342 HELICOPTERS | Equipment/Furnishings – Untimely firing of squibs on GOODRICH electric hoists. | EUROCOPTER SA 341/342 Alert Telex No. 25.12. |
063-05 PTZ | F-2005-108_(B).pdf | 16.7.2005 | Before December 31, 2010 or within 6500 Flight Hours from this AD effective date, whichever occurs first. | AIRBUS SAS; A318, A319, A320 and A321 aircraft | Fuel system - Magnetic fuel level indicator (MFLI) | AIRBUS Service Bulletin A320-28-1138 |
064-05 PTZ | F-2005-115_(B).pdf | 16.7.2005 | Within the compliance times specified in this AD. | AIRBUS SAS; A318, A319, A320 and A321 aircraft | Main landing gear (MLG) - Shock absorber sliding tube cracks | AIRBUS Service Bulletin A320-32A1273 Revision 2 |
054-04 R1 PTZ | F-2004-065_(B)_R1.pdf | 16.7.2005 | | AIRBUS, A318, A319, A320 and A321 aircraft | Main landing gear (MLG) - Shock absorber sliding tube. This Revision 1 cancels Airworthiness Directive (AD)
DGAC_F-2004-065(B).pdf | |
065-05 PTZ | CF-2005-26.pdf | 18.7.2005 | Within the compliance times specified in this AD. | Bombardier Inc.; CL-600-2B19 aircraft | Superseded by 065-05R1 PTZ
CF-2005-26R1.pdf | Bombardier Service Bulletin 601R-30-029, Revision A, dated 7 July 2005, |
066-05 PTZ | LTA_2005-248.pdf | 12.7.2005 | As of the effective date of this AD, | Personal Parachute OMEGA ( ) / QUICK ( ) | ----- THE USE OF ALL THE OMEGA ( ) / QUICK ( ) PERSONAL PARACHUTES IS PROHIBITED ----- | -- None – |
105-04 R1 PTZ | CF-2004-23R1.pdf | 18.8.2005 | Within 5500 flight hours of the effective date of this directive, unless already accomplished. | Bombardier Inc.; CL-600-2B19 aircraft | Camloc Fasteners On Center Pedestal. | Bombardier Aerospace Service Bulletin (SB) 601R-31-030, Revision D, dated 16 June 2005. |
067-05 PTZ | F-2005-121_(B).pdf | 30.7.2005 | Within the compliance times specified in this AD. | AIRBUS SAS; A319 and A320 aircraft | Fuel system - Labels in fuel tanks | AIRBUS Service Bulletin A320-28-1102 Revision 1, A320-57-1117 Revision 1 and A318/319/320/321 MMEL (Master Minimum Equipment List) No 01-28/01Z issue 01. |
068-05 PTZ | F-2005-122_(A).pdf | 30.7.2005 | Superseded by EU-2006-0141 (Si-048-06 PTZ) | TURBOMECA; ARRIUS 2F turboshaft engines | Oil - Replacement of check-valve piston o-ring | Mandatory Alert Service Bulletin No A319 79 4802 |
113-03 R2 PTZ | F-2003-465_(A)_R2.pdf | 30.7.2005 | Within the compliance times specified in this AD. | EUROCOPTER; EC 120 helicopters | Tail rotor drive - Tail rotor drive shaft damper | EUROCOPTER EC 120 B Alert Service Bulletin No. 65A004 |
066-05 R1 PTZ | LTA_2005-248_R1.pdf | 21.7.2005 | As indicated, unless already accomplished: | Personal Parachute OMEGA ( ) / QUICK ( ) | Personnel Parachute OMEGA ( ) / QUICK ( ) - OMEGA Container-System - Modification of Flap-No. 3, Visual Inspection of Bartecs, and Equipment Handbook Change. | Performance Variable Service Bulletin SB-O-200501, dated 18 July 2005. Performance Variable Equipment Handbook (German Version) EH-O-Q01, Revision 4, dated 01 July 2005.
LTA_2005-248_R1-SB-O-200501.pdf |
069-05 PTZ | F-2005-102_(A)_R1.pdf | 13.8.2005 | Within the compliance times specified in this AD. | EUROCOPTER; AS 350 and AS 355 helicopters | Fuselage - RH cabin vibration damper | EUROCOPTER AS 350 Alert Telex No. 05.00.48 R1 and EUROCOPTER AS 355 Alert Telex No. 05.00.46 R1 |
070-05 PTZ | F-2005-136_(A).pdf | 3.8.2005 | Within the compliance times specified in this AD. | EUROCOPTER; AS 350 and AS 355 helicopters | Doors - Sliding door rear roller support shaft and rear fitting. | EUROCOPTER AS 350 Alert Telex No. 05.00.47 R1 and EUROCOPTER AS 355 Alert Telex No. 05.00.45 R1 |
021-05 R1 PTZ | F-2005-032_(A)_R1.pdf | 3.8.2005 | | EUROCOPTER; AS 350 helicopters | Doors - Pin of the sliding door rear fitting. This Revision 1 cancels Airworthiness Directive (AD) F-2005-032, which is replaced by AD F-2005-136.
F-2005-032_(A).pdf | |
071-05 PTZ | FAA_AD_2005-16-04.pdf | 12.9.2005 | Required as indicated, unless accomplished previously. | Bell Helicopter Textron; Model 206A and 206B Helicopters | Detect a crack in the crosstube, which could lead to failure of the crosstube, collapse of the landing gear, and subsequent loss of control of the helicopter. | Aeronautical Accessories, Inc. Alert Service Bulletin No. AA-03121, dated October 25, 2004 |
072-05 PTZ | FAA_AD_2005-16-05.pdf | 26.8.2005 | Required as indicated, unless accomplished previously. | Robinson Helicopter Company; Model R-22 Series Helicopters | To prevent separation of a door window or door assembly from the helicopter, which could damage the tail rotor during flight and result in loss of control of the helicopter. | Tech-Tool Plastics, Inc. Service Bulletin No. TTP2005-01, Revision A, dated February 1, 2005 |
073-05 PTZ | FAA_AD_2005-16-09.pdf | 13.9.2005 | Within the compliance times specified, unless the actions have already been done. | Learjet; Model 23, 24, 25, 35, and 36 Airplanes | Perform an inspection to detect deterioration (such as cracks, cuts, breaks, splits, or warpage) of both flappers of the tip tank in each wing. | Learjet Service Bulletin SB 23/24/25-28-2, dated October 6, 1995 (for Model 23, 24, and 25 airplanes); or SB 35/36-28-10, dated October 6, 1995 (for Model 35 and 36 airplanes) |
074-05 PTZ | FAA_AD_2005-17-11.pdf | 7.10.2005 | Within the compliance times specified in this AD. | The Cessna Aircraft Company; Models 525, 525A, and 525B | Install identification sleeves on the wires for both engine fire extinguisher bottles. Reconnect the wires to both engine fire extinguisher bottles. Test the wires for correct installation | Cessna Citation Service Bulletins SB525-26-01, SB525A-26-02 and SB525B-26-01, all dated April 5, 2005 |
075-05 PTZ | F-2005-128_(B).pdf | 13.7.2005 | Unless already accomplished, within 500 flight hours from July 08, 2005 | AIRBUS SAS; A320 aircraft | Landing gear - Main Landing Gear (MLG) axle nut separation. Inspect the locking bolts, nuts, washers and cotter pins of each MLG wheel and apply corrective actions if necessary in accordance with AOT A320-32A1303. | AIRBUS AOT A320-32A1303 dated July 04, 2005 |
076-05 PTZ | F-2005-143_(A)_R1.pdf | 31.8.2005 | At the latest by February 28, 2006. | TURBOMECA; ARRIUS 2F turboshaft engines | Fuel control unit - Replacement | TURBOMECA Mandatory Alert Service Bulletin No. A319 73 4825, first issue dated August 2005 |
077-05 PTZ | FAA_AD_2005-17-19.pdf | 13.10.2005 | Within 50 hours TIS or within 180 days, whichever occurs first after October 13, 2005 | Cirrus Design Corporation; Models SR20 and SR22 Airplanes | This AD is the result of discovering that the crew seats, under emergency landing dynamic loads, may fold forward at less than 26 g required by the regulations, 14 Code of Federal Regulations (CFR) Section 23.562(b)(2). The actions specified in this AD are intended to prevent the crew seats from folding forward during emergency landing dynamic loads with consequent occupant injury. | Cirrus Design Corporation Alert Service Bulletin SB A2X-25-08, dated June 22, 2004 and SB 2X-25-06 R4, revised May 5, 2005. |
078-05 PTZ | FAA_AD_2005-18-12.pdf | 14.10.2005 | Within the compliance times specified unless the actions have already been done. | Hartzell Propeller Inc. Propellers | Perform visual and nondestructive inspections of propeller components for cracks, corrosion or pits, nicks, scratches, wear, blade minimum dimensions, and damage in the blade balance hole. | Hartzell Service Bulletin No. HC-SB-61-136, Revision I, dated April 25, 2003. |
079-05 PTZ | FAA_AD_2005-18-20.pdf | 14.10.2005 | Within 10 hours after the effective date of this AD | Goodrich De-icing and Specialty Systems; ''FASTprop'' Propeller Deicers | This AD results from reports of Goodrich ''FASTprop'' propeller de-icers becoming loose or debonded, and detaching from propeller blades during operation. We are issuing this AD to prevent Goodrich ''FASTprop'' propeller de-icers from detaching from the propeller blade, resulting in damage to the airplane, and possible injury to passengers and crewmembers. | Goodrich De-icing and Specialty Systems Alert Service Bulletin (ASB) No. 30-60-00-1, dated November 15, 2004 |
080-05 PTZ | FAA_AD_2005-19-11.pdf | 21.10.2005 | Within 50 hours time-in-service or 6 months after the effective date of this AD, whichever is earlier, unless the actions have already been done. | Lycoming Engines (Formerly TextronLycoming); AEIO-360, IO-360, O-360, LIO-360, LO-360, AEIO-540, IO-540, O-540, and TIO-540 Series Reciprocating Engines | Verify the crankshaft SN. After the effective date of this AD, do not install any crankshaft that has a SN listed in Table 4 of Lycoming MSB No. 566, dated July 11, 2005, into any engine. | Lycoming Mandatory Service Bulletin No. 566, dated July 11, 2005,
SB566.pdf
SB566S-1.pdf
customer_letter_nov_30.pdf |
081-05 PTZ | F-2005-117_(B).pdf | 29.6.2005 | Within 5 days from the effective date of this AD | AIRBUS SAS; A319, A320 and A321 aircraft | perform a detailed inspection of the forward engine mount primary load path components and apply all necessary corrective actions | AIRBUS AOT A320-71A1036 Revision 1 dated June 28, 2005 |
046-02 R3 PTZ | F-2001-499_R4_(B).pdf | 31.8.2005 | Within 10 days following June 26, 2002 [effective date of this AD at Revision 3] | AIRBUS SAS; A319, A320 | GOODRICH carbon brake - Reduction of performances. | AIRBUS Service Bulletin A320-32-1247 Revision 2 |
082-05 PTZ | F-2005-159_(A).pdf | 24.9.2005 | Replaced by EU-2006-0142 | TURBOMECA; ARRIUS 2B and 2K turboshaft engines | Oil - Replacement of check-valve piston o-ring | Mandatory Alert Service Bulletin No A319 79 2832 and No A319 79 2833 |
083-05 PTZ | F-2005-158_(A).pdf
F-2005-158.pdf | 1.10.2005 | Every 110 flying hours, comply with the maintenance operations specified in the referenced revisions, | EUROCOPTER; AS 350, EC 130 helicopters | Tail rotor drive - Tail rotor drive shaft | |
022-02 R1 PTZ | F-2002-027_R1_(A).pdf | 24.9.2005 | Before the next hoisting mission | EUROCOPTER; AS 350 helicopters | Equipment / Furnishings - BREEZE 450-lb electric hoist | EUROCOPTER AS 350 Alert Service Bulletin No. 25.00.73. |
084-05 PTZ | FAA_AD_2005-18-16.pdf | 13.10.2005 | Before exceeding the life limit of 6,000 cycles-since-new. | General Electric Company; CF34-3A1 Turbofan Engines | to prevent LCF cracking and failure of those components, which could result in uncontained engine failure and damage to the airplane. | GE Temporary Revision No. 05-0073, and Temporary Revision No. 05-0074, for CF34 Engine Manual, SEI-756. |
085-05 PTZ | FAA_AD_2005-19-20.pdf | 4.11.2005 | At the next 100-hour or annual inspection that occurs following 30 days after November 4, 2005 (the effective date of this AD), whichever occurs first. | The New Piper Aircraft, Inc.; Models PA-28-160, PA-28-161, PA-28-180, and PA-28-181 Airplanes | Replace the two AN894–6–4 bushing screw thread expanders on the two AN826–6 tees (one on the gascolator and the other one attached to a bushing (AN912–2J) attached to the inlet on the top of the top fuel pump) with NAS1564–6–4J reducers and AN818–6 nuts. | Bulletin No. SB 05-2, dated April 12, 2005. |
086-05 PTZ | FAA_AD_2005-20-04.pdf
This AD is superseded by FAA 2007-05-15 (035-07 PTZ)
EASA-2004-0006R1.pdf | 1.11.2005 | Within the compliance times specified in this AD. | Teledyne Continental Motors; GTSIO-520 Series Reciprocating Engines | Installation of TCM Service Kit, EQ6642R | Teledyne Continental Motors
MSB94-4G.pdf |
087-05 PTZ | CF-2005-35.pdf | 3.10.2005 | Prior to accumulating 5500 hours air time from the effective date of this directive or 36 months after the effective date of this directive, whichever is reached first, unless already accomplished. | Bombardier Inc. Model CL-600-2B19; s/n 7003 and subsequent | Junction Boxes - Leach TDH-Series Relays Malfunction | Bombardier Service Bulletin (SB) 601R-24-118, Revision A, dated 08 August 2005 |
036-05-R1 PTZ | F-2005-056-R1.pdf | 8.10.2005 | Cancellation Notice | Airbus SAS; A 320 Aircraft | This Revision 1 cancels 036-05 PTZ, and is replaced by 019-05 PTZ | already included in AIRBUS Service Bulletin A320-28-1104 |
022-03-R1 PTZ | F-2003-119-R1.pdf | 8.10.2005 | Cancellation Notice | Airbus SAS; A319,A320, A321 Aircraft | This Revision 1 cancels 022-03 PTZ, and is replaced by 089-05 PTZ | |
088-05 PTZ | F-2005-164.pdf | 8.10.2005 | No later than May 31, 2010 | Airbus SAS; A318, A319, A320, A321, A330, A340 Aircraft | Unwanted horizontal movements on EADS SOGERMA Services Pilot and co-pilot seats | EADS SOGERMA-SERVICES Service Bulletin TAAI1-25-617 dated February 01, 2005. |
089-05 PTZ | F-2005-165.pdf | 8.10.2005 | Measures are rendered mandatory from the effective date of this AD | Airbus SAS; A318, A319, A320, A321 Aircraft | Fuel leak procedure; Inserting Temporary Revision in the flight manual of the aircraft. The crew is required to strictly follow that procedure. | |
014-05-R1 PTZ | EASA-2005-0012R1.pdf | 1.5.2005 | See EASA AD; 1. Inspect the area within 500 Fl. hours after the effective date; and 2. Apply modifications no later than July 31, 2007 | International Aero Engines; V2500-A1,-A5 (Airbus A319, A320 & A321) | Retaining of Fuel filter cover on the FCOC. Loosen helicoil inserts possibility. Inspection and modification. | IAE SB 79-0085 or 79-0086 as applicable; All Operators Wire AOW 1048 |
090-05 PTZ | FAA-2005-20-25.pdf | 9.11.2005 | Within the next 200 hours time-in-service (TIS), the next 12 months, or at the next scheduled inspection, after November 9, whichever occurs first. | The Cessna Aircraft Company Models 401, 401A, 401B, 402, 402A, 402B, 402C, 404, 411, 411A, 414, 414A, 421, 421A, 421B, 421C, 425, and 441 Airplanes | Determining date code of certain avionics bus circuit breaker switch, also imposes a 1.000-hour safe limit for date code earlier than 0434. | Models 425 and 441 airplanes, procedures in Cessna Conquest SB CQB05–2, all other affected models Multi-engine SB MEB05-1, dated February 21, 2005, and the applicable maintenance manual. |
21-01R2 PTZ | CF-1999-32R3.pdf | 25.10.2002 | Replace MLG main fittings by June 30, 2007 | Bombardier Inc. Model CL-600-2B19; -3 and -4 MLG main fittings | Retrofiting of all aircrafts with the (-83/-84) main fittings to terminate the need to comply with Parts I, II, III, IV and V of this directive as well as with the requirements of 063-04R1 PTZ (AD CF-2004-18R1). | Bombardier SB 601R-32-093 Original issue, Rev A, B or later revisions |
037-03R1 PTZ | CF-2003-09R1.pdf | 6.6.2003 | Replace MLG main fittings by December 31, 2008 | Bombardier Inc. Model CL-600-2B19; P/N 601R85001-81/-82 MLG main fittings | Retrofiting of the aircraft with the redesigned (-83/-84) main fitting to terminate the need to comply with Parts I, II, III, IV and V of this directive. | Bombardier SB 601R-32-093 Original issue, Rev A, B or later revisions |
063-04R1 PTZ | CF-2004-18R1.pdf | 16.9.2004 | Replace MLG main fittings by June 30, 2007 | Bombardier Inc. Model CL-600-2B19; -3 and -4 MLG main fittings | Retrofiting of the aircraft with the redesigned (-83/-84) main fitting to terminate the need to comply with Parts I, II, III of this directive, as well as with the requirements of 21-01R2 PTZ (AD CF-1999-32R3). | Bombardier SB 601R-32-093 Original issue, Rev A, B or later revisions |
065-05R1 PTZ | CF-2005-26R1.pdf | 17.10.2005 | Within the compliance times specified in this AD. | Bombardier Inc.; certain Models CL-600-2B19 | Piccolo tubes; Revision 1 of this directive is issued to revise the aircraft serial number applicability. This revision does not introduce additional mandatory action. | Bombardier Service Bulletin 601R-30-029, Revision B, dated 29 August 2005, |
043-05R1 PTZ | CF-2005-13R1.pdf | 7.11.2005 | Compliance is required as indicated unless already accomplished. | Bombardier Inc.; CL-600-2B19 | Cracking of Aft Pressure Bulkhead Web; Revision 1 mandates new inspection threshold and updates A/c serial numbers | |
091-05 PTZ | EASA-2004-0009R1.pdf | 3.2.2005 | As indicated in AD | (former Allison Engine Company) Rolls Royce Corp; Model 250 Series Engines, installed in single/twin engined helicopters | The 'B'-nut torque values Superseded by 091-05R1 PTZ
EASA-2004-0009R2.pdf | |
092-05 PTZ | F-2005-161.pdf | 16.9.2005 | Before the next hoisting operation | EUROCOPTER;SA 341 G and SA 342 J helicopters, equipped with GOODRICH electric hoist 76370-XXX | Potential risk of untimely squib firing, which would cause the cable to be cut. | EUROCOPTER SA 341/342 Alert Telex n° 25.12 |
093-05 PTZ | EASA-2005-0023R2.pdf | 1.11.2005 | Revised | Lycoming Engines; see TCDS No. in EASA AD | Revised : 093-05 R2 PTZ (EASA AD No.: 2005-0023R2) | Lycoming Service Bulletin & Service Instruction
SB388C.pdf
SI1485A.pdf |
094-05 PTZ | I-2005-345.doc | 18.9.2005 | Within the next 50 flying hours, unless already accomplished | Costruzioni Aeronautiche TECNAM; certain s/n P- 92J, P 92-JS | Inspection of Rudder Pedals, SB P92-J/012Rev.1 | Costruzioni Aeronautiche TECNAM Service Bulletin
P92-J12-Rev1.pdf |
095-05 PTZ | F-2005-173.pdf | 5.11.2005 | Within 20 months following the effective date of this AD | AIRBUS SAS; A319 and A320 aircraft | Prevention against Explosion Risks, SB A320-28-1059 R6- Modification of wires to the pump control of the center tank | Service Bulletin AIRBUS A320-28-1059 Revision 6 or later approved revision |
096-05 PTZ | |
