Številka PTZ | Referenčna PTZ | Datum efektive | Rok izvršitve | Proizvajalec | Vsebina PTZ | Referenčni SB |
001-06 PTZ | FAA-2005-25-08.pdf | 23.1.2006 | As indicated in AD | Shadin; ADC-2000 air data computers (may be installed in Cessna 172,206G,208,210L, Piper PA-28-181,31-350,32-300,34-200T) | Certain ADC-2000 units may display incorrect altitude info on the EFIS. Upgrade of Air Data Computer (see AD for p/n) is required. | Shadin Service Bulletin SB28-05-002,Rev C, dated June 29, 2005 |
002-06 PTZ | FAA-2005-26-10.pdf | 31.1.2006 | Superseeded by 052-06 PTZ (N-2006-12-07) | Lycoming engines; models 320,360,540 series with certain Engine Components Inc. (ECi) cylinder assemblies installed | Reported failures of the ECi cylinder assemblies. Removal & Replacement of certain cylinder assemblies from service. | ECi Service Bulletin No. 05-08, dated September 1, 2005 |
003-06 PTZ | F-2006-011R1.pdf | 14.1.2006 | REVISED | Airbus SAS; A318, A319, A320, A321 Aircraft | Engine pylon spar box ribs; identify and repair ribs, that might not have been heat-treated in production | Airbus All Operators Telex A320-54A1015, dated December 14, 2005 or any later approved revision |
004-06 PTZ | F-2006-007.pdf | 4.1.2006 | before the next flight | Cessna 182 and Reims F182, equipped with SMA SR305-230 engine | Engine operation in cold conditions | SMA service Bulletin SB-C182-71-002, dated November 24, 2005 |
005-06 PTZ | I-2006-001.htm | 10.1.2006 | | Agusta; A109A & A109AII helicopters | Inspection for cracks of tail rotor blades, P/N 109-0132-02-11/-15/-121 | Agusta Bolletino Tecnico 109-110 rev.A, dated December 12, 2005
109-110_3.pdf |
006-06 PTZ | FAA-2005-24-10.pdf | 17.1.2006 | As indicated in AD | Bellanca (Champion) Aircraft Corp., 7GCBC Citabria and others, see listing | Partial loss of Aileron control due to incorrectly swaged cable sleeve. | |
087-04R2 PTZ | A-2004-004R2.pdf | 12.1.2006 | Not later than August 31, 2006 | Rotax; 912 A/F/S,914 F series engines | Replacement of coolant/Reduction of Cylinder Head Temperature Limits. This AD replaces AD A-2004-004 R1 (087-04R1 PTZ) | |
007-06 PTZ | CF-2005-41.pdf | 15.2.2006 | When indicated, unless already accomplished | Bombardier Inc. Model CL-600-2B19 | Shear Pin Failure in Pitch Feel Simulator Input Lever This AD Superseedes and cancels AD CF-2003-26 | Bombardier Alert SB A601R-27-144, dated September 15 2005, or later approved |
008-06 PTZ | EASA-2005-0035.pdf | 30.12.2005 | See AD for details | Piper Aircraft Inc., (The New); PA-28 and PA-32 | Repetitive Inspections on MLG casted oleo housing for cracks. | The New Piper Aircraft, Inc. Service Bulletin 1131 |
093-05 R1 PTZ | EASA-2005-0023R2.pdf | 1.11.2005 | Revised | Lycoming Engines | Same as original issue, prolonged period before initial inspection in order to allow more time to obtain the required tooling | |
003-06 R1 PTZ | EU-2006-0136.pdf | 14.1.2006 | Superseeded by EU-2006-0136 | Airbus SAS; A318, A319, A320, A321 Aircraft | Engine pylon spar box ribs; identify and repair ribs, that might not have been heat-treated in production | Airbus All Operators Telex A320-54A1015, dated December 14, 2005 or any later approved revision |
009-06 PTZ | F-2006-040.pdf | 27.1.2006 | Upon receipt from January 27, 2006 | EUROCOPTER; EC 120 B helicopters | Certain s/n Spherical thrust bearings prohibition for flight (expecting correction) | EC 120B Eurocopter Alert Telex No 04A006 or later approved revision of the same |
010-06 PTZ | EASA-2005-021.pdf | 1.8.2005 | 1.may 2006 | Honeywell;Aicrafts, equipped with RCZ-83() and RCZ-85() Comm Units | Correction of the design deficiency- Incorporation of SB's on affected units. | Honeywell SB A21-3851-005, A24-3851-002 |
011-06 PTZ | FAA-2006-03-08.pdf | 10.3.2006 | within 100 hours time-in-service (TIS) or the next 12 calendar months, whichever occurs first | Aero Advantage; ADV200 series vacuum pumps | Vacuum pumps removal from service. May be installed in Champion 7GCBC, Cessna 172M,N,P,182G,TU206G,U206B, Commander 112TC, Piper PA-18-150, PA-25-235,PA-28-140,PA-28-161, PA-28-181,PA-28R-200,PA-28R-201T,PA-31-350,PA-32-300, SOCATA MS 893A,MS893E, RALLYE 150 ST, TB 9 and others | |
017-03R1 | CF-2003-05R1.pdf | 31.3.2006 | As indicated, unless already accomplished | Bombardier Inc. Model CL-600-2B19; s/n 7003 and subsequent | Amended aircraft applicability of the bulkhead inspection | ASB A601R-21-054, Revisions A,B,C or later; ASB A601R-21-053, Revision A or later |
012-06 PTZ | F-1997-144-038R1.pdf | 11.2.2006 | Effective date the original issue July 12,1997 | EUROCOPTER; SA 341/342 helicopters | updated referenced Alert Service Bulletin | EUROCOPTER SA 341/342 ASB No. 05.32 R1 |
013-06 PTZ | 2006-04-10.pdf | 24.3.2006 | Within 100 flight hours or latest by may 23,2006 | Cessna Aircraft Company; Model 500,550,S550,560,560XL and 750 airplanes | Installation of identification sleeves on the wires of Fire extinguishing Bottles | See AD text |
014-06 PTZ | 2006-04-12.pdf | 30.3.2006 | Within the compliance times specified in this AD unless the actions have already been done | General Electric Company (GE); CF34-3A1 and -3B1 series turbofan engines | Additional population of stage 5 and 6 LPT disks with possibility of Low-cycle-fatique (LCF) failure | GE Alert Service Bulletin (ASB) No. CF34-AL S/B 72-A0173, Revision 05 |
015-06 PTZ | 2006-05-04.pdf | 7.4.2006 | Within the compliance times specified unless the actions have already been done | General Electric Company (GE); CF34-1A,-3A,-3A1, -3A2,-3B and -3B1 series turbofan engines | Removal of Certain Fan Disks From Service This AD supersedes AD 2001-10-03 | GE ASB CF34-BJ 72-A0088, Revision 1 and GE ASB CF34-AL 72-A0103 |
093-05 R2 PTZ | EASA-2005-0023R2.pdf
This Ad is superseded by EASA 2005-0023 R3 (PTZ 043-07 PTZ) | 1.11.2005 | As indicated in AD | Lycoming Engines | Inspection of exhaust valves and guides in accordance with Lycoming SB 388C - Hi-Crome exhaust valves and guides exclusion | Lycoming Service Bulletin & Service Instruction
SB388C.pdf
SI1485A.pdf |
016-06 PTZ | N-2006-06-03.pdf | 20.4.2006 | Within the compliance times specified unless the actions have already been done | Cessna Aircraft Company; Model 500 and 501,550 and 551,S550,560 airplanes | Chafed Electrical wiring harness inside the fuel tank | See Table 2 for applicable service bulletin |
017-06 PTZ | N-2006-06-16.pdf | 27.4.2006 | Within 50 hours Time-In-Service (TIS) or 6 months after the effective date of this AD | Lycoming Engines; AEIO-360, IO-360, O-360, LIO-360, and LO-360 Series Reciprocating Engines | Retirement of certain S/N crankshafts | Lycoming engines MSB 566 supp.1
SB566S-1.pdf |
018-06 PTZ | EU-2006-044.pdf | 28.2.2006 | Immediately after the effective date of this AD | Thielert Aircraft Engines; TAE 125-01 | Revision of Chapter 5 of the MM; Added new exchange interval for the LP fuel pump | Thielert Service Bulletin
2005-152-Thielert-TM-TAE-125-0010.pdf |
019-06 PTZ | EU-2006-0065.pdf | 6.4.2006 | Within the next 1000 hours Time-in-Service (TiS) or within 2 years after the effective date of this AD | Robinson Helicopter Company; All Robinson R22 Helicopters | Installation of landing skid extensions and shoes | |
020-06R1 PTZ | EU-2006-0069-E-R1.pdf | 7.4.2006 | Within eight days of aircraft operation following the effective date of this AD | Airbus; A318, A319, A320 and A321 aircraft | The forward lugs of MLG rib 5 fittings inspection and repair | See AD for details |
021-06 PTZ | N-2006-07-06.pdf | 11.5.2006 | Within eight days of aircraft operation following the effective date of this AD | Cirrus Design Corporation; SR20 and SR22 | Inspection of the fuel line, installation of parts to protect the fuel line | Cirrus Design Corporation Service Bulletin
SB2X-28-04R1.pdf |
022-06 PTZ | CF-2006-04.pdf | 28.4.2006 | Within 60 days of the effective date of this AD | Bombardier Inc.; Model CL-600-2B19, all serial numbers | Backlash wear limits in aileron PCUs | See AD for details |
023-06 PTZ | EU-2006-0093.pdf | 5.5.2006 | Within 110 Flying hours or within 4 months- first limit reached | Eurocopter, EC 120 helicopters | Engine controls- Collective levers twist grip assembly- bonding between the drive tube and the control pinion | EUROCOPTER EC 120 Alert Service Bulletin No. 76A006 |
024-06 PTZ | CF-2006-07.pdf | 25.4.2006 | Within 90 days of the effective date of this directive | Bombardier Inc. Model CL-600-2B19 | AC service Bus Contractor wiring modification | Bombardier Alert SB A601R-24-121, dated April 18 2006, or later approved |
025-06 PTZ | EU-2006-0106-E.pdf | 2.5.2006 | Immediately from the effective date of this AD | Airbus; A318, A319, A320, A321 Aircraft | Fuel - Main Fuel Pump System / Fuel Pumps Airworthiness Limitation | AIRBUS AFM TR 4.03.00/28 |
026-06 PTZ | EU-2006-0092.pdf | 8.5.2006 | Within 50 hours Time-In-Service (TIS) from the effective date of this AD, see AD for details | Hartzell Propeller Inc.; Hartzel Propellers ( )HC-( )2Y( )-( ), installed on Lycoming ( )-360 series engines | Hub cracks in Hartzell two blade "compact" series aluminum hub propellers | SB227-R04.pdf
SB269-R00.pdf |
027-06 PTZ | EU-2006-0108.pdf | 15.5.2006 | See AD for details | Airbus; A318, A319, A320, A321 Aircraft | Temporary loss of all display units | A315/319/320/321 Flight Manual Temporary Revision 4.02.00/22, AIRBUS Service Bulletin A320-31A1220 or latter approved revisions |
028-06 PTZ | N-2006-10-21.pdf | 22.6.2006 | Within the compliance times specified in this AD unless the actions have already been done | Lycoming Engines; 360 and 540 series with Engine Components Incorporated (ECi) Reciprocating Engine Connecting Rods | To prevent fatigue failure of the connecting rod. | |
029-06 PTZ | EU-2006-0135.pdf | 5.6.2006 | Operational Limitation is mandatory from the effective date of this AD | Airbus; A318, A319, A320 and A321 Aircraft | Speed Limitation to 250 IAS with RAT (Ram Air Turbine) deployed - Valid During Flight Tests Only | AFM TR 2.05.00/67 or later approved revisions |
003-06 R2 PTZ | EU-2006-0136R2.pdf | 5.6.2006 | As indicated in AD | Airbus; A318, A319, A320 and A321 Aircraft | Nacelles/Pylons - Engine Pylon Spar Box Ribs | AOT A320-54A1015 Rev.2, dated May 18, 2006 or latter approved revisions |
030-06 PTZ | CF-2006-12.pdf | 5.7.2006 | No later than 3 months from the effective date | Bell Helicopter Textron Canada; Model 206A/B helicopters | Vertical stabilizer (fin) supports One time inspection and recurring torque check | Alert Service Bulletin (ASB) 206-06-107 or later approved Revisions |
031-06 PTZ | EU-2006-0153.pdf | 9.6.2006 | As indicated in AD | Airbus; A318, A319, A320 and A321 Aircraft | Auxiliary Power Unit (APU)- Starter Motor and Air Intake System- Inspection/Cleaning | AIRBUS Service Bulletin A320-49-1068 rev. 1 |
032-06 PTZ | EU-2006-0112.pdf | 26.5.2006 | As indicated, unless already accomplished | Airbus; A318, A319, A320 and A321 Aircraft | Main Landing Gear Door Actuator | AIRBUS Service Bulletin A320-32-1309, any later approved revision
and
FAA AD 2007-06-18 |
033-06 PTZ | EU-2006-0150-2.pdf | 12.6.2006 | June 30th, 2006 | GROB Luft- und Raumfahrt; Astir CS | Elevator Spherical Attachment Bolt Replacement | GROB Service Bulletin
MSB_306-38-1.pdf |
034-06 PTZ | EU-2006-0140-E.pdf | 25.5.2006 | As indicated in AD | CTT Systems AB; Bombardier CL-600-2B19 with STC LBA.21E2.TA0270 zonal dryer installed | Zonal Drying System Deactivation | Lufthansa Technik AG SIL LHT 06-001 |
035-06 PTZ | CF-2006-11.pdf | 19.6.2006 | As indicated, unless already accomplished | Bombardier Inc.; Model CL-600-2B19 | Inspection of Chemical Oxygen Generator for Improper Installation of Release Pin | Bombardier Service Bulletins, listed in AD |
036-06 PTZ | EU-2006-0162.pdf | 22.6.2006 | As indicated in AD | Airbus; A318, A319, A320 and A321 Aircraft | Safe life Airworthiness Limitation Items- ALS Part 1 (Supersedes 012-04 PTZ (F-2004-032)) | A318/A319/A320/A321 MPD section 9-1 revision 06, approved June 13, 2003 and A318/A319/A320/A321 ALS Part 1, approved February 28, 2006 |
037-06 PTZ | EU-2006-0165.pdf | 16.6.2006 | June 30th, 2006 | Airbus; A318, A319, A320 and A321 Aircraft | Airworthiness Limitation Items (ALI)- Structural Maintenance- Superseedes 006-04PTZ | Airbus AI/SE-M4/95A.0252/96 issue 6, 7 or later approved revisions |
038-06 PTZ | EU-2006-0166.pdf | 28.6.2006 | Within the next 1000 hours time-in-service (TIS) or within 2 years, whichever comes first | Robinson Helicopter Company, R44 Helicopters | Doors- Cotter pins installation | |
039-06 PTZ | EU-2006-0167.pdf | 28.6.2006 | Within the next 1000 hours time-in-service (TIS) or within 2 years, whichever comes first | Robinson Helicopter Company; Model R22 helicopter | Doors- Hinges Modification | |
040-06 PTZ | EU-2006-0171.pdf | 3.7.2006 | Within the next 1000 hours time-in-service (TIS) or within 2 years, whichever comes first | Schweizer Aircraft Corporation; Model 269A, 269A-1, 269B, 269C, 269C-1 and 269D helicopters | Fuel Vent Modification; to prevent release of fuel in the event of a roll-over | Schweizer Service Letter L-168 |
041-06 PTZ | EU-2006-0172.pdf | 3.7.2006 | Before further flight, after the effective date of this Directive | Enstrom Helicopter Corporation; F-28A and 280 series helicopters fitted with certain blade grips | Inspection and rework of the tail rotor blade assy | Service Directive Bulletin 0067 |
042-06 PTZ | EU-2006-0173.pdf | 3.7.2006 | Not later than May 31, 2007 | Bell Helicopter Textron Inc.; Bell 212 series helicopters with Sperry Helipilot automatic flight control system | Relocation of the Helipilot disconnect switch | |
043-06 PTZ | N-2006-13-10.pdf | 7.8.2006 | See Original AD for details | Raytheon Aircraft Company (Beech); C90A | Rudder trim tab-moisture drainage provisions- added serial numbers to FAA AD N-92-07-05 | SB55-2365, Revision 2 |
044-06 PTZ | N-2006-13-06.pdf | 26.7.2006 | Within the compliance times specified unless the actions have already been done | Rolls-Royce Corporation (formerly Allison); model 250 turboshaft and turboprop engines | Removal from service of certain P/N gas producer rotor assembly tie bolts | Various RRC Commercial Engine Bulletins |
045-06 PTZ | EU-2006-0174.pdf | 5.7.2006 | As indicated in AD | Airbus; A318, A319, A320 and A321 Aircraft | Supersedure of AD F-2005-191 (Si-099-05 PTZ), extended applicability and introduced a repetitive boroscopic inspection | See AD text |
046-06 PTZ | EU-2006-0176.pdf | 10.7.2006 | See AD for details | Airbus; A318, A319, A320 and A321 Aircraft | Supersedes AD F-2005-028 (Si-019-05 PTZ) and mandates new, revised SB;
see also FAA 2007-07-09 | AIRBUS Service Bulletin A320-28-1104 revision 03 |
047-06 PTZ | EU-2006-0184.pdf | 17.7.2006 | Within 36 months from the effective date of this AD | Airbus; A319, A320, A321 Aircraft | Semi automatic cargo loading-Modification of fixed YZ latches | AIRBUS Service Bulletin A320-25-1294 Revision 1 or later |
048-06 PTZ | EU-2006-0141.pdf | 9.6.2006 | As indicated in AD | Turbomeca; Arrius 2F engines | Supersedes AD F-2005-122 (Si-068-05 PTZ), introduces revised SB | Turbomeca Alert SB A319 79 4802, Update No 1 |
049-06 PTZ | N-2006-14-03.pdf | 9.8.2006 | Within the compliance times specified unless the actions have already been done | Honeywell International Inc. (formerly Garret); model TPE331 turboprop and TSE331 turboshaft engines | New flight cycle counting method for first, second, and third-stage turbine rotors used in aircraft that make multiple takeoffs and landings without an engine shutdown, and removing turbine rotors from service that have reached or exceeded their cycle life limits. | See AD text |
050-06 PTZ | CF-2006-17.pdf
This AD is superseded by CF-2006-17R1 (068-07 PTZ) | 17.7.2006 | Within four months or prior to accumulating 800 hours air time from the effective date of this AD, whichever reached first, unless already accomplished | Bombardier Inc. Model CL-600-2B19 | AC Contactor Failure - Ultem 2200 Terminal base plate Sealing | Bombardier SB 601R-24-122, dated 27 June 2006 or later approved revisions |
051-06 PTZ | EU-2006-0203.pdf | 19.7.2006 | See AD for details | Airbus; A318, A319, A320 and A321 Aircraft | Fuel Airworthiness Limitations; changes in maintenance/inspection tasks and operator internal documentation amendment | A320 Fuel Airworthiness Limitations, 95A.1931/05 Issue 1, or later approved revisions |
052-06 PTZ | N-2006-12-07.pdf | 11.7.2006 | Within the compliance times specified unless the actions have already been done | Lycoming engines; models 320,360,540 series with certain Engine Components Inc. (ECi) cylinder assemblies installed | Applicability errors were found in Si-002-06 PTZ (AD N-2005-26-10). | ECi Service Bulletin No. 05-08, Revision 2,dated February 28, 2006
05-8.pdf |
053-06 PTZ | EU-2006-0220.pdf | 31.7.2006 | Within the next 8 weeks from the effective date of this AD | Recaro Aircraft Seating GmbH;Passanger Seats Type 3410,3510,4400,4420 and 6510, delivered between 1.nov.2005 and 5.may 06 | Visual inspection of the seat shackle | Various Recaro Service Bulletins, listed in AD |
054-06 PTZ | N-2006-15-08.pdf | 24.8.2006 | At the next scheduled inspection of the fuel control drive, but within 1,000 hours-in-service | Honeywell International Inc., formerly Garrett; TPE331 Turboprop Engines With Affected Woodward FCU Assemblies | Initial and Repetitive Inspection of Affected Woodward FCU Assemblies | Honeywell Alert Service Bulletin (ASB) No. TPE331-A73-0271, -0262, -0254 |
055-06 PTZ | EU-2006-0221.pdf | 31.7.2006 | Unless already accomplished, listed actions must be performed within 3 months from effective date of AD | Saab AB, Saab Aerosystems; SAAB SF340A and 340B all serial numbers | Fuel System Airworthiness Limitations (comprising maintenance/inspection tasks and Critical Design Control Configuration Limitations (CDCCL) | SAAB Fuel Airworthiness Limitations Document No 340LKS 9033 or later |
056-06 PTZ | EU-2006-0223.pdf | 7.8.2006 | See AD for details | AIRBUS; A318, A319, A320 and A321; all certified models, all manufactured S/N | Flight controls – Trimmable Horizontal Stabilizer Actuator- Inspections | AIRBUS Service Bulletin (SB) A320-27-1164 Revision 2, 3, 4 |
057-06 PTZ | CF-2006-19.pdf | 25.8.2006 | Within 1500 hours air time after the effective date of this AD, Repeat the inspection not to exceed 1500 hours air time, Within 4000 hours air time replace the existing engine exhaust nozzle attachment hardware | Bombardier Inc. CL600-2B19 Regional Jet (CRJ), aircraft serial numbers 7003 through 7067, and 7069 through 7947. | Engine Exhaust Nozzle In-Flight Loss INSPECTION and REPLACEMENT of the hardware attaching the engine nozzle to the engine flange. | Bombardier service bulletin (SB) 601R-78-021 |
058-06 PTZ | EU-2006-0228-E.pdf | 28.7.2006 | EMERGENCY AD Upon receipt of this AD and before next flight | Agusta S.p.a. A109A, AII, C, K2, E, S, LUH | Tail Rotor - Tail Rotor Pitch Control Link Assy P/N 109-0130-05-117 INSPECTION | Agusta - Agusta Alert SB 109-122, 109K-47, 109EP-70, 109S-5, 109L-001, 119-15 |
059-06 PTZ | EU-2006-0222.pdf | 31.7.2006 | See AD for details | AIRBUS; A318, A319, A320 and A321 aircraft, all certified models, all S/N that are equipped with fuel pumps manufactured by Eaton Aerospace Limited (formerly FR-HITEMP limited) part number (PN) 568-1-27202-005 with a S/N from 6137 and above. | Fuel - Main Fuel Pump System/Fuel Pumps | SB A320-28-1152 and A320-28-1153 |
060-06 PTZ | N-2006-16-01.pdf | 15.8.2006 | within 60 days after the effective date of this AD, unless the actions have already been done | Hamilton Sundstrand Propellers, Model 14RF-19 with propeller system actuator yoke arms, P/N 810436-2, which might be installed in actuator assemblies P/N790199-6. These propellers are installed on, but not limited to, SAAB 340 airplanes. | To prevent actuator yoke arms breaking during flight, which could cause high propeller vibration and contribute to reduced controllability of the airplane. Replacement of all actuator yoke arms, P/N 810436-2, with improved actuator yoke arms, P/N 810436-3.Mark newly installed actuators. Do not install any actuator yoke arms, P/N 810436-2, into any propeller assembly. | Hamilton Sundstrand Service Bulletin 14RF-19-61-113, Revision 1 |
061-06 PTZ | N-2006-16-04.pdf | 7.9.2006 | See AD for details (For fuel nozzles with a P/N listed in Table 3 within 50 operating hours after the effective date; P/N listed in Table 4 within 150 operating hours after January 5, 2005). | Rolls-Royce Corporation (formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison) (RRC) 250-B and 250-C series turboshaft and turboprop engines; Engines Installed on, But Not Limited To- see table 2 (BELL 206) | Minimizing the risk of sudden loss of engine power and uncommanded shutdown of the engine due to fuel contamination and collapse of the screen in the FUEL NOZZLE. | Rolls-Royce Corporation Alert Commercial Engine Bulletins (CEBs); all at Revision 1, all dated August 30, 2004, listed in the Table 5 of this AD. |
062-06 PTZ | EU-2006-0234.pdf | 24.8.2006 | Within the next 50 hours TIS after the effective date of this AD,unless accomplished previously, verify the installation of the forward plugs and stops of the seat rails | Costruzioni Aeronautiche TECNAM; All models P92-J, P92-JS and P2002-JF aeroplanes, certified in any category | Equipment & Furnishings - Seat Rail Stops - Inspection; | Tecnam MANDATORY SB 001-CS dated 24th March 2006 or later approved revisions.
MSB_001-CS.pdf |
063-06 PTZ | N-2006-16-07.pdf | 9.8.2006 | Within 800 flight hours or four months after the effective date of this AD, whichever occurs first, unless the actions have already been done in accordance with Bombardier SB 601R-24-122,dated June 27, 2006. | Bombardier, Inc. (Formerly Canadair):Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, certificated in any category, S/N 7003 through 7990 inclusive and 8000 and subsequent. | Prevention of short circuit failures of certain AC contactors, which could result in arcing and consequent smoke or fire. | Instructions of Bombardier SB 601R-24-122, Rev A, dated July 13, 2006. |
064-06 PTZ | EU-2006-0235-E.pdf
This AD is superseded by EASA EAD 2007-0138-E (PTZ 057-07) | 10.8.2006 | Mandatory measures from the effective date of this AD. At each check after the last flight of the day without exceeding 10 flying hours between two successive checks, visually check for absence of cracks in the blade pressure face and blade suction face. | EUROCOPTER; AS 350 and AS 355 helicopters | EMERGENCY AD Tail Rotor - Tail Rotor Blade Skin - Check | EUROCOPTER AS 350 Alert Service Bulletin No. 05.00.40 Revision 1 and AS 355 Alert Service Bulletin No. 05.00.38 Revision 1 or later approved revisions. |
065-06 PTZ | EU-006-0261-E.pdf | 28.8.2006 | Before the next flight | EUROCOPTER (formerly EUROCOPTER-FRANCE, AEROSPATIALE,SUD-AVIATION) | Emergency AD Oxygen - Oxygen Cylinders – Removal/Emptying AS 350 B3 and SA 315 B helicopters, all serial numbers with certain Oxygen Cylinders PN´s | EUROCOPTER AS 350 Alert Service Bulletin No. 05.00.54,EUROCOPTER SA 315 Alert Service Bulletin No. 05.42, or any subsequent approved revision. |
066-06 PTZ | CF-2006-20.pdf | 29.8.2006 | Within seven days, from the effective date of this directive. | Bombardier Inc. Model CL-600-2B19, serial number 7003 thru 7990 and 8000 and subsequent | Horizontal Stabilizer Trim – Uncommanded Motion | |
067-06 PTZ | CF-2006-21.pdf | 29.8.2006 | Within seven days, from the effective date of this directive. | Bombardier Inc. Model CL-600-2B16 (CL-604), serial number 5301 and subsequent. | Horizontal Stabilizer Trim – Uncommanded Motion | |
068-06 PTZ | EU-2006-0236.pdf | 24.8.2006 | See AD for compliance details | AIRBUS (formerly AIRBUS INDUSTRIE); AIRBUS A319-100 series and A320-200 series, see AD for AC S/N | Fuel, Wings - Fuel system – Labels in Fuel Tank | See AD for details |
069-06 PTZ | EU-2006-0248.pdf | 1.9.2006 | The following measure is mandatory as from June 11, 2004, the effective date of DGAC AD No. F-2004-085 | EUROCOPTER, AS 350 Helicopters | Equipment and Furnishings – Emergency All-Up Operating Weight Limitation | EUROCOPTER AS 350 Alert Service Bulletin No. 01.00.55 R1 or later approved revisions. |
070-06 PTZ | EU-2006-0252.pdf | 1.9.2006 | 31.12.2006; See AD for details | EUROCOPTER; SA 330, AS 332, SA 341/342, AS 350, AS 355, SA 360, SA 365, AS 365,EC 155, SE 3160 and SA 316/319 helicopters | Equipment and Furnishings – Hoist Operator’s Belt Snap Hook | EUROCOPTER Alert Service Bulletins: See AD for details |
071-06 PTZ | EU-2006-0247.pdf | 1.9.2006 | See AD for compliance details | EUROCOPTER (formerly EUROCOPTER-FRANCE, AEROSPATIALE); AS 350 Helicopters | Rotor Flight Controls – Tail Servo-Control | EUROCOPTER AS 350 Alert Service Bulletin No. 67.00.30 or later approved revisions |
072-06 PTZ | EU-2006-0249.pdf | 1.9.2006 | See AD for compliance details | EUROCOPTER (formerly EUROCOPTER-FRANCE, AEROSPATIALE); AS 350 and AS 355 Helicopters | Doors – Sliding Door – Wear on Rollers and Rails | EUROCOPTER AS 350 ASB No. 05.00.41 Rev 2;EUROCOPTER AS 355 ASB No. 05.00.39 Rev 2, as applicable, or later approved revisions. |
073-06 PTZ | EU-2006-0262.pdf | 8.9.2006 | Within 9,000 Flight Cycles (FC) or 12,000 Flight Hours (FH), or 60 months,whichever occurs first after the effective date of this AD | AIRBUS (formerly AIRBUS INDUSTRIE); A320 aircraft | Stabilizers – Rudder Actuator Fittings – Replacement | AIRBUS Service Bulletin A320-55-1030 original issue or later approved revisions
and FAA AD 2007-06-17 |
074-06 PTZ | EU-2006-0263.pdf | 12.9.2006 | Within 8,000 flight cycles since the last MLG overhaul, or within 1,500 flight cycles or 6 months after the effective date of this directive, whichever occurs later | Saab AB, Saab Aerosystems (Saab Aircraft AB); SAAB SF340A and SAAB 340B | Landing Gear – MLG Shock Strut & Axle Adaptors – Inspection/Modification | SAAB SB 340-32-133; and APPH Ltd. SB AIR83022-32-32 or AIR83064-32-12, as applicable, or later approved revisions. |
075-06 PTZ | EU-2006-0251R1.pdf | 1.9.2006 | See AD for compliance details | EUROCOPTER (formerly EUROCOPTER FRANCE, AEROSPATIALE); AS 350 AND AS 355 Helicopters | Doors – Sliding Door Rear Roller Support Shaft and Rear Fitting | EUROCOPTER AS 350 Alert Service Bulletins No. 05.00.47 and No. 52.00.30; or EUROCOPTER AS 355 Alert Service Bulletins No. 05.00.45 and No. 52.00.23, as applicable, or later approved revisions |
076-06 PTZ | EU-2006-0264.pdf | 13.9.2006 | Within 18 months after the effective date of this directive | AVIOINTERIORS S.p.A.; Passengers Seats, various Part Numbers. | Equipment & Furnishings – Passenger Seats Rear Fitting Assembly Attachment – Replacement The affected seats are known to be installed on, but not limited to, the following aircraft: Airbus A319, A320 and A321 series; Boeing 737, 747 and 777 series;McDonnell Douglas DC-9, DC-10 and MD90 series. | Aviointeriors Service Bulletin 180/A84-01 Rev. 1 or later approved revisions. |
077-06 PTZ | EU-2006-0267.pdf | 14.9.2006 | Unless accomplished previously, within 100 hours time-in-service (TIS) after the effective date of this AD, and thereafter at intervals not to exceed 100 hours TIS | Reims Aviation, S.A.; F150, FA150, FRA150, F152 and FA152 series | Stabilizers – Horizontal and Vertical Stabilizer Attachment– Inspection/Replacement | Reims Aviation SB 24, Revision n°1 or later approved revisions; or Cessna Single Engine Service Information Letter SE79-49, Revision # 1,dated April 28, 1980 or later approved revisions. |
078-06 PTZ | EU-2006-0269.pdf | 14.9.2006 | Within the next 15 days after the effective date of this directive,unless previously accomplished; See AD for details | Honeywell International Inc., MST 67A Mode S transponder; known to be installed in various aircraft- See AD for details (SAAB SF340A and 340B) | Navigation Systems – Mode S Transponder - Modification | Honeywell Software Bulletin SWB MST 67A–SW2 |
079-06 PTZ | N-2006-16-14.pdf | 22.9.2006 | Within 6,000 flight hours or 24 months after the effective date of this AD, whichever is first. | AIRBUS; Model A318, A319, A320, and A321 airplanes, certificated in any category, except airplanes having manufacturer serial numbers (MSN) 2155 and subsequent | To ensure that, in the event of an engine fire, the valve actuator functions will properly block the fuel flow to the engine and prevent an uncontrollable fire. | Airbus SB A320-28-1122, Rev 01, including Appendix 01; FRHiTEMP Service Bulletin HTE190001-28-003, dated March 30, 2004. |
080-06 PTZ | N-2006-17-04.pdf | 1.9.2006 | Within the next 5 hours TIS after the effective date of this AD on airplanes that have not had a 100-hour or annual inspection of the engine installation fuel hoses for security and tightness of the end fittings | Cessna Aircraft Company; Models: 172R, 172S, 182T,T182T, 206H and T206H (see S/N´s) | Inspection of the two end fittings on each of the flexible fuel hoses located in the engine compartment for the correct torque values | Cessna Service Bulletin No. SB06-71-02, dated June 19, 2006 |
081-06 PTZ | N-2006-16-18.pdf | 25.9.2006 | Within 14 days and within 90 days after the effective date of this AD (see AD for compliance details) | Sandel Avionics Incorporated; (Sandel) Model ST3400 terrain awareness warning system/radio magnetic indicator (TAWS/RMI) units | Installation of warning placard on the TAWS/RMI and revising the Limitations section of the airplane flight manual (AFM) as result of in-flight bearing error. Units installed on various small and transport category airplanes see table 1 foe details (for example- Cessna 208, 208B, 421C; 501, 525, 550, 560, 650, S550) | Sandel ST3400 Service Bulletin SB3400-01,Rev B, dated Sept. 15, 2004 |
082-06 PTZ | N-2006-17-13.pdf | 27.9.2006 | You are responsible for having the actions required by this AD performed within 60 days after the effective date of this AD, unless the actions have already been done. | RECARO Aircraft Seats GmbH & Co; (RECARO) Model 3410 302, 303, 306, 307, 314, 316, 317, 791, 792, and 795 series seats. | Replacing the existing attachment bolts for the seat belts with longer attachment bolts. These seats are installed on, but not limited to, Boeing 737, 747, 777 and Airbus A319-100 series, A320-200 series, and A321-200 series airplanes. | RECARO service bulletin SB-No.: 3410-25MR477, Rev 3, dated May 17, 2004 |
083-06 PTZ | EU-2006-0273.pdf | 14.9.2006 | See AD for compliance details | EUROCOPTER (formerly EUROCOPTER-FRANCE, AEROSPATIALE); AS 350 and AS 355 Helicopters | Fuselage – RH Cabin Vibration Damper & Blade – Inspection /Replacement / Modification | EUROCOPTER AS 350 Alert Service Bulletin (ASB) No. 05.00.48 and 53.00.34; and EUROCOPTER AS 355 ASB No. 05.00.46 and No.53.00.22, as applicable, or later approved revisions. |
084-06 PTZ | EU-2006-0274.pdf | 15.9.2006 | Not later than at the next annual inspection after the effective date of this AD or within 12 months after the last inspection. Thereafter, at intervals not exceeding 12 months, repeat the inspection | Carling Technologies, Inc.; Rocker-type Switches,Part Number (P/N) TA 201TBW | Electrical Power – Switches – Inspection/Replacement This switches known to be installed in, but not limited to,aircraft manufactured by the Piper Aircraft Corporation, Cessna Aircraft Company and Grumman American Aviation Corporation, certificated under FAR Part 23. | This AD is superseded and canceled by EASA AD 2006-0375 |
085-06 PTZ | EU-2006-0279.pdf | 17.9.2006 | Prohibited use in flight of the PARACHUTE SHOP equipments with a manufacturing date after 1st Jan 2001. Equipment must be removed from service. | PARACHUTE SHOP; Parachute Harnesses and Reserve Canopies (see AD for Applicability) | Equipment/Furnishings – Parachute Equipment – Removal from Service. | None |
086-06 PTZ | EU-2006-0275.pdf | 22.9.2006 | Within the next scheduled 100-hours or annual inspection but no later than three (3) months after the effective date of this AD. | Agusta S.p.a.; AB206A and AB206B helicopters | Stabilizers - Vertical Fin Supports - Inspection | Agusta “Bollettino Tecnico” 206-240 issued on 5 July 2006 or later approved revisions. |
087-06 PTZ | N-2006-18-12.pdf | 13.10.2006 | Required as indicated in AD, unless accomplished previously. | Saab Aircraft AB; Model SAAB-Fairchild SF340A (SAAB/SF340A) airplanes and SAAB 340B airplanes, | To prevent false warning indications to the flightcrew from the hot detection system of the tail pipe harness of the engine nacelles due to discrepancies of the harness. | Saab SB 340-26-030, dated Oct 28, 2002; or Saab SB 340-26-018, Rev 02, and 340-26-029, both dated Oct 28, 2002 |
088-06 PTZ | N-2006-18-15.pdf | 25.9.2006 | Within 50 operating hours time-in-service (TIS) after the effective date of this AD,Within every 100 operating hours TIS after the last propeller hub ECI inspection, or at every annual inspection,perform repetitive ECIs. | Hartzell Propeller Inc.; ( )HC-( )2Y( )-( ) series propellers with non-suffix SN propeller hubs installed on Lycoming O-, IO-, LO-, and AEIO-360 series reciprocating engines.Could be installed on different aircraft (see AD). | Prevent failure of the propeller hub causing blade separation and subsequent loss of airplane control. Performing Propeller Hub Eddy Current Inspection (ECI). | Hartzell Propeller Inc. SB HC-SB-61-227
SB227-R05.pdf |
089-06 PTZ | EU-2006-0280.pdf | 26.9.2006 | See AD for compliance details | AIRBUS (formerly AIRBUS INDUSTRIE); A319, A320 and A321 aircraft | Electrical Power, Engine – Integrated Drive Generator connector on IAE V2500 engine – Operational Procedure | AIRBUS SB A320-71-1030 original issue, AIRBUS SB A320-71-1034 original issue or later approved revisions; AIRBUS AFM TR 4.02.00/20 |
090-06 PTZ | EU-2006-0281.pdf | 28.9.2006 | See AD for compliance details | EXTRA Flugzeugproduktions- und Vertriebs-GmbH; (former Extra Flugzeugbau GmbH); EA 300 aircraft | Fuselage –Upper Longeron at Horizontal Stabilizer - Inspection/Modification | EXTRA Service Bulletin No. 300-2-95, Issue F or later approved revisions.
2003-001R1-sb-300-2-95-issue-f.pdf
and FAA 2007-02-11 |
091-06 PTZ | EU-2006-0171-R1.pdf | 24.9.2006 | Within the next 1,000 hours time-in-service after 03 July 2006, but not later than 03 July 2008,whichever occurs first. | Schweizer Aircraft Corporation; Hughes Helicopters, Inc.; Schweizer (Hughes) 269 Series | Fuel – Fuel Vent System – Modification | Schweizer Service Letter L-169 dated 10 August 2000 |
092-06 PTZ | CF-2006-10-_R2.pdf | 10.10.2006 | As indicated in AD, unless already accomplished. | Bell Helicopter Textron Canada (BHTC), Model 206 A/B series helicopters | Fuel Distribution System | Alert Service Bulletin (ASB) 206-05-103, Revision A, dated 12 July 2006
ASB_206-05-103_Rev_A.pdf |
093-06 PTZ | N-2006-19-04.pdf | 17.10.2006 | See AD for compliance details | Honeywell International, Inc.: certain Communication (COM) units and Mode S transponder- See AD for details | To prevent the transponder of the COM unit from going into standby mode, which could increase the workload on the flightcrew and result in improper functioning of the traffic alert and collision avoidance system. Installed in- see AD for details: Bombardier, Cessna (Model 550 and 560 and 650), Dassault (Falcon), EMBRAER, Learjet, Lockheed, Raytheon, certificated in any category. | Different Honeywell Alert Service Bulletins- See Table 1 in AD |
094-06 PTZ | N-2006-19-10.pdf | 24.10.2006 | Within 50 hours time-in-service or within 180 days,whichever occurs first after the effective date of this AD | Cirrus Design Corporation; airplane models SR20 and SR22 | To prevent the crew seats from folding forward during emergency landing dynamic loads with consequent occupant injury. | Cirrus Design Corporation SB SB 2X-25-17 R1, Issued:December 15, 2005, Revised: January 20, 2006
SB2X-25-17R1.pdf |
095-06 PTZ | zacasna_odredba.pdf | 3.10.2006 | Takoj, velja do preklica | Vsi batni letalski motorji | Prepoved uporabe avtomobilskega bencina (čisti bencin ali mešanica z letalskim bencinom 100LL) za batne letalske motorje, razen v primerih, če je proizvajalec letalskega motorja drugače določil, kar se dokaže z originalnim priročnikom za uporabo letalskega motorja, ki je za tip in serijsko številko letalskega motorja potrjen s strani proizvajalca. | SI1070N.pdf |
096-06 PTZ | EU-2006-0286-E-Corr.2.pdf | 25.9.2006 | Required as indicated, unless accomplished previously in accordance with EAD 2006-0261-E, See AD for details | INTERTECHNIQUE, Zodiac Aircraft Systems; Oxygen Reserve Cylinders | Oxygen - Oxygen Reserve Cylinders – Removal/Emptying Which are known to be installed on,but not limited to Airbus A300, Dassault Aviation Mystère-Falcon 20, Mystère-Falcon 50, Falcon 200 and Falcon 900 aircraft; Pilatus aircraft; Eurocopter SA 315 B and AS 350 B3 helicopters;and Hindustan Aeronautics Limited helicopters. | INTERTECHNIQUE SB GLD/GLF-35-150; EUROCOPTER AS 350 Alert Service Bulletin No. 05.00.54; EUROCOPTER SA 315 Alert Service Bulletin No. 05.42, or any subsequent approved revision. |
097-06 PTZ | EU-2006-0295-E.pdf | 28.9.2006 | Inspection as per Diamond MSB 40-048/2 has to be carried before the next flight but not later than 30 November 2006. | Diamond Aircraft Industries Inc., Canada; DA 40 | Engine – Contamination of the Engine Fuel System -Inspection | Diamond Aircraft Industries Mandatory Service Bulletin, MSB 40-048/2 or later approved revisions. |
098-06 PTZ | EU-2006-0292.pdf | 9.10.2006 | Required as indicated in AD compliance details, unless already accomplished in accordance with CAA UK AD 007-12-83 Revision 1. | Enstrom Helicopter Corporation; All Enstrom F-28 and 280 series helicopters. | Tail Rotor – Pitch Link & Pitch Arm Plate – Inspection/Replacement | |
099-06 PTZ | EU-2006-0290.pdf | 9.10.2006 | After the effective date of this directive, replacement of the listed parts in the AD is required at or before the accumulation of the following times in service. | Enstrom Helicopter Corporation; All 480 and 480B Helicopters | Time Limits / Maintenance Checks – Life Limited Components – Replacement | Enstrom Service Information Letter (SIL) T-002
SIL_T-002R4.pdf |
100-06 PTZ | N-2006-20-09.pdf | 3.11.2006 | You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done | Lycoming Engines (formerly Textron Lycoming); (L)O-360, (L)IO-360, AEIO-360, O-540, IO-540, AEIO-540, (L)TIO-540, IO-580, and IO-720 series reciprocating engines listed in AD | To prevent failure of the crankshaft, which will result in total engine power loss, in-flight engine failure, and possible loss of the aircraft. | You must use the service information specified in Table 1 of this AD to perform the actions required by this AD.
SB569A.pdf
SI1009AS.pdf |
101-06 PTZ | CF-2006-20_R1.pdf | 16.10.2006 | Within 14 days and Within 12 months of the effective date of this directive, see AD for details | Bombardier Inc. Model CL-600-2B19, serial numbers 7003 thru 7990 and 8000 thru 8066. | Horizontal Stabilizer Trim – Uncommanded Motion | AFM Temporary Revision (TR) RJ/152-5 dated 03 Oct 2006; Bombardier In-Service ModSum No. IS601R27410051,Revision C, approved 29 September 2006; Bombardier Service Bulletin (SB) 601R-27-147 dated 28 September 2 |
102-06 PTZ | CF-2006-21_R1.pdf | 16.10.2006 | Within 14 days and Within 12 months of the effective date of this directive, see AD for details | Bombardier Inc. Model CL-600-2B16 (CL-604), serial numbers 5301 through 5665. | Horizontal Stabilizer Trim – Uncommanded Motion | AFM Temporary Revision (TR) 604/21-1 dated 03 October 2006; Bombardier Alert Service Bulletin (ASB) A604-27-029 dated 28 September 2006; Bombardier ASB A604-27-029 dated 28 September 2006 |
103-06 PTZ | EU-2006-0316-E.pdf | 17.10.2006 | EMERGENCY AD; Before the next engine start up from the effective date of this AD,Within 5 hours of operation after the effective date of this AD, see AD for details | BRP-Rotax GmbH & Co. KG; Bombardier-Rotax GmbH & Co. KG;Bombardier-Rotax GmbH; | Engine – Magnetic Plug – Inspections installed on, but not limited to: Sky Arrow, Aeromot, Aircraft Philipp, Aquila, Cessna 150 and A150, Diamond (formerly HOAC) H 36 Dimona, HK 36 series Super Dimona, DV 20 Katana and DA20-A1 Katana;Evektor-Aerotechnik, Grob, Issoire, Reimsn Aviation F150 and FA150 series, Scheibe, Stemme, Tecnam, W.D. Aircraft. | BRP-Rotax Alert Service Bulletin, ASB-912-051 and ASB-914-034 or later approved revisions.
ASB-912-051.pdf |
104-06 PTZ | EU-2006-0334 | 14.11.2006 | Not later then 30 months from effective date | Thales VHF Data Radio, Part Numbers:
EVR716-11-0300A
EVR716-11-0350A
EVR716-01-0100A
EVR716-01-0200A
EVR750-03-0100A
known to be installed on, but not limited to, the following aircraft:
- Dash 8-400;
- Airbus A318, A319, A320, A321, A330, A340 (all series);
- Boeing 717, 727, 737, 747, 757, 767, 777 (all series). | Communications - Thales Communications VHF Data Radio -
Modification | Thales Communications Service Bulletins:
EVR716-23-015 ;
EVR716-23-012 Initial Issue or Rev. 01;
EVR7-23-05 Initial Issue or Rev. 01
or later approved revisions. |
105-06 PTZ | FAA-2006-22-05 | 01.12.2006 | See AD for details | Applies to aircraft, certificated in any category, equipped with a Honeywell Primus II RNZ-850( )/-851( ) integrated navigation unit (INU); including, but not limited to, Jetstream Model 4101; Bombardier Model BD-700-1A10 series airplanes; Model Bombardier CL-215-6B11 (CL-415 variant) series airplanes; Cessna Model 560, 560XL, and 650 airplanes; Dassault Model Mystere-Falcon 50 series airplanes; AvCraft Dornier Model 328-100 and -300 series airplanes; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 airplanes and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes; Learjet Model 45 airplanes; Raytheon Model Hawker | Inspection to determine wheather certain modifications have been done | Honeywell Tehnical Newsletter A23-3850-001, Rev 1. |
106-06 PTZ | EU-2006-0323 | 13.11.2006 | At the next scheduled maintenance inspection, or at the next annual shop visit, whichever occurs first after the effective date of this directive | APEX AIRCRAFT; DR 400/180 and DR400/180R aircraft | Power Plant – Air Intake Box – Inspection/Modification | APEX AIRCRAFT SB 040706 dated June 19th 2006 or later approved revisions1 |
107-06 PTZ | FAA-2006-23-02 | 13.12.2006 | Within 100 hours time-in-service after December 13, 2006 or At the next annual inspection that occurs at least 30 days after December 13, 2006 | Raytheon Aircraft Company (Formerly Beech); C90A, B200, B200C, B300, B300C | To detect and correct improperly assembled or damaged flight controls | Raytheon Aircraft Company Mandatory Service Bulletin Number SB 27-3761, Issued: February 2006 |
108-06 PTZ | FAA-2006-23-04 | 28.11.2006 | Prior to further flight, unless already done, inspect engine fuel system for possible contamination of fuel | Diamond Aircraft Industries GmbH:
Model DA 40 airplanes equipped with Garmin G1000 supplemental type certificate (STC) SA01254WI | Some parts of the installed fuel system indicating system were contaminated with particles from the manufacturing process. | Diamond Aircraft Industries GmbH Mandatory Service Bulletin No. MSB-40-048/2, Revision 2, dated September 26, 2006 |
109-06 PTZ | EASA 2006 - 0345 | 28.11.2006 | During each pre-flight inspection and “100-hours” inspection | MT-Propeller Entwicklung GmbH;
All MT- fixed pitch propellers and MTV- variable pitch propellers MTV-1,
MTV-2, MTV-3, MTV-5, MTV-6, MTV-7, MTV-9, MTV-10, MTV-11, MTV-12,
MTV-14, MTV-15, MTV-17, MTV-18, MTV-20, MTV-21, MTV-22 and MTV-24
manufactured before 1995 and not overhauled since April 1994.
Installed on, but not limited to:
René Fournier RF4
Apex ATL
Apex DR400
Extra EA-300
EADS Socata Rallye Piper PA-46 | Propeller – Blade Leading Edge Protection – Inspection | MT-propeller Service Bulletin No. 8B dated March 8, 2006
or later approved revisions;
Operation and Installation Manual
E-112, E-118, E-124, E-148, E-309 |
110-06 PTZ | EASA EAD 2006-0347-E | 17.11.2006 | Before next flight after the effective date And Thereafter, at intervals not to exceed 55 flight hours | APEX AIRCRAFT; All DR 400 series aircraft, all models except the DR 400/500; see AD for details | Wings – Lower Surface Fabric Covering – Inspection | |
111-06 PTZ | CF-2006-23
This AD is superseded by CF-2006-23 R1 (see 042-07 PTZ) | 04.12.2006 | At the next scheduled main rotor hub disassembly, but no later than 25 January 2007 | Bell Helicopter Textron Canada; Model 206 A and Model 206 B certain S/N; see AD for details | Main Rotor Latch Bolts - Removal from Service | Alert Service Bulletin
(ASB) 206-06-109, or later revisions |
112-06 PTZ | EASA 2006 - 0153 R1 | 11.12.2006 | See AD compliance for details | AIRBUS, (formerly AIRBUS INDUSTRIE); AIRBUS A318, A319, A320 and A321 aircraft See AD for details | Auxiliary Power Unit (APU) - Starter Motor and Air Intake System – Inspection/Cleaning | AIRBUS Service Bulletin A320-49-1068/ A320-49-1070/ A320-49-1075 |
113-06 PTZ | FAA 2006-24-07 | 03.01.2007 | See AD compliance for details | Hartzell Propeller Inc. (formerly TRW Hartzell Propeller) and McCauley Propeller Systems (formerly Cessna Aircraft Co.) propellers (certain P/N and S/N- see AD) serviced by Oxford Aviation Limited, doing business as CSE Aviation (UK) | CSE Aviation failed to perform some specific inspections and repairs | |
114-06 PTZ | FAA 2006-24-08 | 19.12.2006 | See AD actions and compliance for details | Pratt & Whitney Canada (P&WC) PW535A turbofan engines that have fuel manifold, part number (P/N) 3025267-01, installed. These engines are installed on, but not limited to Cessna Airplane Co. model 560 Citation Ultra Encore airplanes. | Unsafe condition as fuel manifold leakage that could result in engine fire, in-flight shutdown or damage to the airframe. | Transport Canada Airworthiness Directive CF-2006-22, dated Oct 26, 2006, and P&WC Alert Service Bulletin PW500-72-A30314 dated Sep. 27, 2006 |
115-06 PTZ | FAA 2006-25-01 | 08.01.2007 | See AD compliance for details | International Aero Engines AG (IAE) V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5 turbofan engines | Prevention of the No. 3 bearing failure, which could result in an in-flight shutdown (IFSD) and smoke in the cockpit and cabin. | IAE SB No. V2500-ENG-72-0452;
IAE SB No. V2500-ENG-72-0459 IAE SB No. V2500-ENG-72-0460 |
116-06 PTZ | EASA 2006-0353
This AD is superseded by EASA 2007-0010 (see PTZ 007-07) | 18.12.2006 | See AD compliance for details | All Agusta Helicopters A109E where Tail Rotor blades
P/N 109-8132-01-111 are installed. | Tail Rotor - Tail Rotor Blades P/N 109-8132-01-111 – Inspection/Replacement | Agusta Bollettino Tecnico 109EP-30 Rev. C, Agusta A109E Maintenance Planning Manual Rev. 1 |
117-06 PTZ | EASA 2006-0318 R1 | 20.10.2006 | See AD compliance for details | EUROCOPTER DEUTSCHLAND GmbH EC 135 helicopter, all models, having certain components installed (see AD for details) | Rotorcraft Flight Control – T/R Control Linear Transducer (LVDT Collective) Bearing– Inspection/Replacement & Rod and Floor Modification | Eurocopter Deutschland EC 135 ASB No. EC135-67A-012 Revision 1
dated 18 October 2006 |
118-06 PTZ | EASA Emergency AD 2006-0371-E | 18.12.2006 | See AD compliance for details | Agusta helicopters AB206A and AB206B series having Main Rotor latch bolts P/N 206-010-169-1/-3 or P/N 206-011-122-3 installed | Main Rotor - Main Rotor latch bolts P/N 206-010-169-1/-3 and P/N 206-011-122-3 -Replacement | Transport Canada AD CF-2006-23 and Agusta Alert “Bollettino Tecnico” 206-241 original issue |
119-06 PTZ | FAA 2006-25-15 | 19.01.2007 | Within 90 days after the effective date of this AD, see AD compliance for details | Sicma Aero Seat: third occupant seat assemblies, 133 series, nstalled on, but not limited to, Airbus A319, A320, and A321 series airplanes. | Visual inspect the installation of the two headrest bushings and install Mecanindus pins to secure the bushings | DGAC 2000-042(AB), dated January 26, 2000 |
120-06 PTZ | EASA 2006-0375 | 29.12.2006 | Not later than at the next annual inspection after 15 September 2006
or within 12 months after the last
inspection as previously required by CAA UK Additional AD 001-09-96 or
EASA AD 2006-0274, whichever occurs later, visually inspect the affected
switches. Thereafter, at intervals not exceeding 12 months, repeat the inspection | Carling Technologies, Inc.
Rocker-type Switches,
The affected switches are known to be installed on, but not
limited to, aircraft manufactured by the Piper Aircraft Corporation, Cessna
Aircraft Company and Grumman American Aviation Corporation, certificated under FAR Part 23. | Electrical Power – Switches – Inspection/Replacement | This AD supersedes and cancels EASA AD 2006-0274 |
121-06 PTZ | FAA AD 2006-23-02 | 13.12.2006 | See AD compliance for details | This AD affects certain airplane models and S/N that are certificated in any category.
Raytheon Aircraft Company (Formerly Beech):
C90A, B200, B200C, B300, B300C See AD for S/N | Inspect the flight controls for improper assembly or damage, and if any improperly assembled or damaged flight controls are found, take corrective action | Raytheon Aircraft Company Mandatory Service Bulletin Number SB 27-3761, Issued: February 2006. |
