Številka PTZ | Referenčna PTZ | Datum efektive | Rok izvršitve | Proizvajalec | Vsebina PTZ | Referenčni SB |
001-08 PTZ | CF-2008-01 | 24.01.2008 | Within 4500 hours air time after the effective date of this directive, modify the fuel tank climb vent loop pipes; See AD for details | Bombardier Inc. Model CL-600-2C10 aircraft, serial numbers 10003 through 10169 and CL-600-2D24 aircraft, serial numbers 15001 through 15025 | Fuel System Safety - Fuel Tank Climb Vent Loop Fuel Leak onto Anti-Ice Duct | Bombardier Service Bulletin (SB) 670BA-28-011, Revision B, dated 4 July 2007 |
002-08 PTZ | CF-2008-02 | 24.01.2008 | Within 4500 hours air time after the effective date of this directive; See AD for details | Bombardier Inc. Model CL-600-2C10 aircraft, serial numbers 10003 through 10169 and CL-600-2D24 aircraft, serial numbers 15001 through 15025 | Fuel System Safety -Insufficient Electrical Bonding Between Fuel Tubes and Insufficient Lightning Current Capability of Fuel Tube Couplings | Bombardier SB 670BA-28-014, Revision A, dated 7 May 2007 |
003-08 PTZ | FAA 2007-26-12 | 18.01.2008 | Within 10 hours time-in-service (TIS), unless accomplished previously; Before further flight, replace any unairworthy blade with an airworthy | Robinson Helicopter Company
Model R22, R22 Alpha, R22 Beta, R22 Mariner helicopters, serial numbers 0002 through 4100; R44 helicopters, serial numbers 0001 through 1670; and R44 II helicopters, serial numbers 10001 through 11570, certificated in any category | Detect main rotor blade skin debond and prevent blade failure and subsequent loss of control of the helicopter | Robinson R22 Service Letter SL-56 and
R44 Service Letter SL-32 and ADDITIONAL INFORMATION REGARDING MAIN ROTOR BLADE SKIN DEBONDING |
004-08 PTZ | UK G-2008-0001-E
Emergency AD | 12.01.2008 | Before further flight; See AD compliance for details | LINDSTRAND HOT AIR BALLOONS LTD (LHAB)
ALL LINDSTRAND HOT AIR BALLOONS with Burner hoses manufactured by Flexquip | FUEL HOSES - REPLACEMENT OF DEFECTIVE HOSES | LHAB Service Bulletin No 11. |
005-08 PTZ | EASA Emergency AD 2007-0306-E | 18.12.2007 | See AD compliance for details | Agusta S.p.A.
A109E, A109K2 and A109C Helicopters | Rotor - Main Rotor Blade Tip Cap p/n 709-0103-29-109 – Inspection | Agusta - Alert Service Bulletins 109EP-85, 109K-48 and 109-25 |
006-08 PTZ | UK G-2008-0002 Emergency AD | 16.01.2008 | Before further flight; See AD compliance for details | CAMERON BALLOONS LIMITED (CBL)
All Cameron Balloons with gas cylinders supplied by CBL balloons which have a CB-0824-0001 Rego Type Cylinder Liquid Valve fitted which is date stamped between 12/05 and 08/06 | Defective inlet self seal valves | Cameron Balloons Service Bulletin 16 and Service Bulletin 17 |
007-08 PTZ | EASA 2007 - 0067R1 | 27.03.2007 | See AD compliance for details | AIRBUS SAS
A319 and A320 series aircraft | Wings – Centre and Outer Wing Box at level of Rib 1 Junction – Inspection | See AD Ref. Publications for list |
008-08 PTZ | CF-2007-34 | 10.01.2008 | See AD compliance for details | Bombardier Inc. Model CL-600-2B19 aircraft, serial numbers 7003 through 7067, and 7069 through 7929 | Fuel System Safety - Insufficient Electrical Bonding for Lightning Protection Inside Fuel Tanks | Bombardier Service Bulletin (SB) 601R-28-055, Revision D |
009-08 PTZ | CF-2007-35 | 10.01.2008 | See AD compliance for details | Bombardier Inc. Model CL-600-2B19 aircraft, all serial numbers | Fuel System Safety - Introduction of Critical Design Configuration Control Limitations | See AD for details |
010-08 PTZ | CF-2007-36 | 11.01.2008 | Within 10,000 hours air time after the effective date of this AD; See AD compliance for details | Bombardier Inc. Model CL-600-2B19 aircraft, serial numbers 7003 through 7067, 7069 through 7982 | Fuel System Safety - Chafing of Fuel Quantity Gauging System Wiring | Bombardier Service Bulletin (SB) 601R-28-059, Rev E |
011-08 PTZ | CF-2007-24R1 Supersedes Airworthiness Directive (AD) CF-2007-24 | 10.01.2008 | See AD compliance for details | Pratt & Whitney Canada
PW206 and PW207 Compressor Turbine (CT) Disk | PW 200 Compressor Turbine Disk Inspection and Retaining Nut Replacement | Alert Service bulletin PW200-72-A28280 R4 |
012-08 PTZ | EASA 2008-0016 | 05.02.2008 | Within the next 110 Flight Hours (FH) or 6 months or during the next
scheduled maintenance, whichever occurs first after the effective date of this AD; See AD | Thielert Aircraft Engines
TAE125-01 engines, all serial numbers
These engines are known to be installed on, but not limited to, Cessna 172 and
(Reims-built) F172 series (EASA STC Nr. EASA.A.S.01527); Piper PA-28 series (EASA STC Nr. EASA.A.S.01632), APEX (Robin) DR 400 series (EASA STC Nr. EASA.A.S.01380); and Diamond DA40 and DA42 | Engine Oil System – Piston Cooling Nozzles – Inspection | Thielert Service Bulletin TM TAE125-0017 |
013-08 PTZ | EASA 2008-0018 | 07.02.2008 | See AD compliance for details | TURBOMECA
ARRIUS 2B1, ARRIUS 2B1A, ARRIUS 2B2, ARRIUS 2K1 and ARRIUS 2K2 engines, all serial numbers These engines are known to be installed on, but not limited to, Eurocopter Deutschland EC135 and Agusta A109 twin-engine helicopters | Engine Fuel & Control – Electronic Engine Control (EEC) Unit – Identification / Modification | TURBOMECA Service Bulletin N° 319 73 2835, Update No.1 |
014-08 PTZ | FAA 2008-02-06 | 26.02.2008 | See AD compliance for details | GARMIN International
GSM 85 servo gearbox units
These units are installed in, but notlimited to:
Cessna Aircraft Company 182T, T182T, 206H, and T206H
Hawker Beechcraft Corporation G36 and G58
Diamond Aircraft Industries GmbH DA40 and DA40F
Columbia Aircraft Manufacturing 350 and 400 Mooney Airplane Company, Inc. M20M and M20R | Detect and correct defective GARMIN GSM 85 servo gearbox units, which could result in jamming of the servo gearbox | GARMIN International, Inc. Service Bulletin No. 0713, Revision A, B, C, D
Cessna Aircraft Company Single Engine Service Bulletin SB07-22-01 |
015-08 PTZ | FAA 2008-02-18 | 28.02.2008 | Within the next 25 hours
time-in-service after February 28, 2008; See AD compliance for details | Cessna Aircraft Company:
Cessna 172 Models
Cessna 182 Models
equipped with:
BRS-172 Parachute System installed via STC No.
SA01679CH, or BRS-182 Parachute System installed via STC No. SA01999CH | Prevent premature separation of the collar. This condition could result in the parachute failing to successfully deploy. | For Cessna 172 series airplanes follow
BRS SB 07-01
For Cessna 182 series airplanes, follow BRS SB 07-02 |
016-08 PTZ | UK G-2008-0003 | 18.01.2008 | See AD compliance for details | Dowty Propellers Propeller Electronic Controller Part No. 699018002 | PROPELLER ELECTRONIC CONTROLLER - UNIT REMOVAL | Dowty Propellers Alert Service Bulletin D8400-61-A77 |
017-08 PTZ | CF-2008-07 | 15.02.2008 | Within 60 days after the effective date of this directive; See AD compliance for details | Bombardier Inc. Model CL-600-2C10, CL-600-2D15 and CL-600-2D24 aircraft, all serial numbers | Fuel System Safety - Introduction of Critical Design Configuration Control Limitations | See AD for details |
018-08 PTZ | EASA 2008-0022 | 12.02.2008 | Within 30 days after the effective date of this AD; See AD compliance for details | Saab AB, Saab Aerosystems (formerly Saab Aircraft AB)
Model SF340A and 340B [including variant 340B (WT)] aircraft, all serial numbers | Ice & Rain Protection – Flight in Icing Conditions / Airplane Flight Manual – Amendment | SAAB SF340A Airplane Flight Manuals Doc.No:
AFM 340A 000,
AFM 340A 001,
AFM 340A 003
SAAB 340B Airplane Flight Manuals Doc.No:
AFM 340B 000,
AFM 340B 001,
AFM 340B 003, AFM 340B 010 |
019-08 PTZ | FAA 2008-03-02 | 06.03.2008 | Within the next 100 hours
time-in-service (TIS) after
March 6, 2008 or within the
next 12 months after March 6, 2008, whichever occurs first; See AD compliance for details | Cessna Aircraft Company
172R 172S | Detect and correct chafing of the fuel return line assembly, which could result in fuel leaking under the cabin floor and fuel vapors entering the cabin. This condition could lead to fire under the floor or in the cabin area | Cessna
Service Bulletin
SB07-28-01, dated June 18, 2007 |
020-08 PTZ | FAA 2008-03-09 | 10.03.2008 | See AD compliance for details | CFM International, S.A.
CFM56-7B18, -7B20, -7B22, -7B24, -7B26, -
7B27, -7B22/B1, -7B24/B1, -7B26/B1, -7B27/B1, -7B22/B2, -7B26/B2, -7B27/B3 turbofan engines
with turbine rear frame (TRF), part numbers 340-166-205-0, 340-166-206-0, 340-166-207-0, 340-166-208-0, 340-166-209-0, and 340-166-210-0, installed. These engines are installed on, but not limited to, Boeing 737 series airplanes | Prevent failure
of the TRF from low-cycle fatigue cracks. Failure of the TRF could result in engine separation from the airplane, which could lead to loss of control of the airplane | CFM International Service Bulletin CFM56-7B S/B 72-0579, Rev 1 |
021-08 PTZ | FAA 2008-03-10 | 11.03.2008 | Within the next 90
days after March 11,
2008 (the effective date of this AD); See AD compliance for details | Cessna Aircraft Company Models 525, 525A and 525B | Detect and correct any damage from corrosion on the airplane structure. Corrosion of the airplane structure could cause structural degradation and lead to structural failure of the airplane with consequent loss of control. | See Table 2 for list of SB´s |
022-08 PTZ | FAA 2008-03-12 | 11.03.2008 | See AD compliance for details | McDonnell Douglas
Model DC-8-11, DC-8-12, DC-8-21, DC-8-31,
DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 Airplanes; Model DC-8F-54 and DC-8F-55
Airplanes; Model DC-8-50, -60, -60F, -70, and -70F Series Airplanes; Model DC-9-10, -20, -30, -
40, and -50 Series Airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) Airplanes; and Model MD-88 Airplanes | Prevent
failure of the rudder pedal bracket assembly, which could result in the loss of rudder and braking control at either the captain's or first officer's position | See Table 2 |
023-08 PTZ | FAA 2008-03-16 | 11.03.2008 | See AD compliance for details | Cirrus Design Corporation
Model SR20 airplanes, serial numbers (SN) 1005 through 1861, and Model SR22 airplanes, SN 0002 through 2333, SN 2335 through 2419, and SN 2421 through 2437, that are certificated in any category | Prevent the possibility of jamming of the rudder-aileron interconnect system, which may result in loss of rudder and aileron flight controls | Cirrus Service
Bulletin No. SB 2X-27-14
R3, Revised: October 10, 2007 |
024-08 PTZ | FAA 2008-02-19 | 06.03.2008 | See AD compliance for details | Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine
Engine Co.)
TFE731-2C, -3B, -3BR, -3C, -
3CR, -3D, -3DR, -4R, -5AR, -5BR, -5R, -20R, -20AR, -20BR, -40, -40AR, -40R, and -60 series turbofan engines with certain high pressure (HP) turbine rotor discs part numbers and serial numbers
These engines are installed on, but not limited to the airplanes listed in AD applicability | Prevent uncontained failure of the HP turbine rotor assembly, which could result in damage to the airplane | Honeywell Alert SB No. TFE731-A72-5185, dated July 5, 2006,
and SB No. TFE731-72-3720, dated July 5, 2006 |
025-08 PTZ | FAA 2008-03-20 | 17.03.2008 | Within 60 months after the effective date of this AD, modify the door-mounted escape system
of the forward right side door slide compartment, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-25-1567, dated March 21, 2007; See AD for details | Boeing Model 737-300, -400, and -500 series airplanes | Prevent the escape slide from being unusable during an emergency evacuation and consequent injury to passengers or crewmembers | Boeing Special Attention Service Bulletin 737-25-1567, dated March 21, 2007 |
026-08 PTZ | CF-2008-08 | 07.02.2008 | See AD for details | Pratt & Whitney Canada (P&WC) - PW305A and PW305B engines certain serial numbers | Engine Fan Blade Fracture | Alert Service Bulletin (ASB) No. A24588
Special Instructions (SI) No.37-2007. ASB No. A24588R2 Service Bulletin (SB) No. 24595 |
027-08 PTZ | CF-2008-09 | 18.02.2008 | See AD for details | Bombardier Inc. Model: CL-600-2B19 – Serial numbers 7305 through 7990 and 8000 and subsequent | Air-Driven Generator – Internal Wiring | Bombardier Aerospace Service Bulletin 601R-24-113, original issue, dated 22 April 2004, or Revision A, dated 11 August 2005 |
028-08 PTZ | CF-2008-10 | 19.02.2008 | See AD for details | Bombardier Inc. Models: CL-600-2C10 – Serial numbers 10004 and subsequent. CL-600-2D15 and CL-600-2D24 – Serial numbers 15002 and subsequent | Air-Driven Generator – Internal Wiring | Bombardier Aerospace Service Bulletin 670BA-24-015, dated 17 May 2004, or Revision A, dated 18 December 2006 |
029-08 PTZ | CF-2008-12 | 25.02.2008 | Within 30 days of the effective date of this AD; See AD for details | Bombardier Inc.
CL-600-1A11 (CL-600)
CL-600-2A12 (CL-601)
CL-600-2B16 (CL-601-3A/3R) CL-600-2B16 (CL-604) | Stick Pusher Capstan Shaft Failure | See AD |
030-08 PTZ | EASA Emergency AD 2008-0027-E | 13.02.2008 | Total Engine Time below 20h: before achieving 30 hours total engine time or at the next engine inspection,
whichever occurs first
Total Engine Time above 20h:
within the next 10 flight hours or at the next engine inspection, whichever
occurs first; See AD for details | Thielert Aircraft Engines
TAE125-02-99 (CENTURION 2.0) engines
These engines are known to be installed on, but not limited to, Cessna 172 and (Reims-built) F172 series Piper PA-28 series, APEX (Robin) DR 400 series and Diamond DA40 and DA42 aircraft | Engine Fuel Injection System – High-Pressure Fuel Line Bracket – Installation | Thielert Aircraft Engines Service Bulletin TM TAE 125-1005 P1, Revision 1 dated 11 February 2008 |
031-08 PTZ | CF-2007-25R1
Supersedes Airworthiness Directive CF-2007-25 (132-07 PTZ) | 29.10.2007 | See AD Corrective Actions for details | Pratt & Whitney Canada (P&WC)
PW305A and PW305B Engine High Pressure Compressor (HPC) Drum Rotor Cracks | PW305A and PW305B Engine High Pressure Compressor (HPC) Drum Rotor Cracks | SB PW300-72-24462;
SB PW300-72-24376;
SIL PW300-093
and PW305-MM-05-20-00 requirements |
032-08 PTZ | EASA Emergency AD 2008-0028-E | 15.02.2008 | Within the next 25 Flight Hours (FH) or within 30 days after the effective date of
this AD, whichever occurs first.
Repeat thereafter,inspections at intervals
not to exceed 100 FH.
See AD compliance for details | Costruzioni Aeronautiche TECNAM S.r.l.
Model P92-JS; from serial number (s/n) 013 up to s/n 068 inclusive | Stabilizers – Vertical Fin Spar - Inspection | Costruzioni Aeronautiche TECNAM S.r.l. SB 006-CS |
033-08 PTZ | EASA 2008-0033 | 04.03.2008 | At the next scheduled 1600 Flight Hours (FH) aircraft check after the
effective date of this AD, or after any blade accumulates 15 000 FH time in service, whichever occurs later, and thereafter at intervals not to exceed 1600 FH, inspect the blade outer sleeves for cracks; See AD compliance for details | Dowty Propellers (part of GE Aviation Systems)
R354, R375, R389 and R390 propellers These propellers are known to be installed on Saab SF340A and 340B aircraft | Propellers – Blade Outer Sleeve - Inspection | Dowty Propellers Alert Service Bulletin No. SF340-61-A106 |
034-08 PTZ | EASA 2008-0034 | 05.03.2008 | Before 31 May 2009; See AD compliance for details | AIRBUS (formerly AIRBUS INDUSTRIE) A318, A319, A320 and A321 aircraft | Hydraulic Power – Auxiliary Hydraulic Power – Ram Air Turbine (RAT) Gerotor Pump - Replacement | AIRBUS Service Bulletin A320-29-1122 original issue |
035-08 PTZ | CF-2008-14 | 10.03.2008 | See AD compliance for details | Bombardier Inc. Models CL-600-2C10 – Serial numbers 10004 and subsequent. CL-600-2D15 and CL-600-2D24 – Serial numbers 15002 and subsequent | Air Driven Generator Power Centre - Contactors | Bombardier Aerospace Service Bulletin 670BA-24-021 |
036-08 PTZ | EASA 2008-0032 | 06.03.2008 | See AD compliance for details | AIRBUS A318, A319, A320 and A321 aircraft | Indicating Systems- Electronic Instrument System (EIS) –
Display Management Computer (DMC) Software EIS2 Standard S7 / Installation | AIRBUS Service Bulletin A320-31A1220
AIRBUS Service Bulletin A320-31-1263 AIRBUS Service Bulletin A320-31-1276 |
037-08 PTZ | ENAC Emergency AD 2008-62 | 20.20.2008 | Before the next flight of the helicopter with the rescue hoist installed
or before the installation on the helicopter of the rescue hoists
and/or for the hooks stored as spare parts, after the effective date
of this AD inspect the hook of the rescue hoist in accordance with
the instructions of the Agusta Alert BT 412-124. However the inspection of spare parts must be done not later then 31.March.2008 | Agusta S.p.A. AB412 (series) and AB412EP | Rescue hoist P/N BL-10300-60 and P/N 412-8800-01-315 – inspection of hook P/N S6150-61090-1 and P/N 412-8800-05-101 | Alert BT Agusta 412-124 |
038-08 PTZ | EASA 2008-0016 R1 This AD revises and replaces AD 2008-0016 (012-08 PTZ) | 05.02.2008 | Within the next 110 Flight Hours (FH) or 6 months or during the next
scheduled maintenance, whichever occurs first after the effective date of this AD; Thereafter, at intervals not to exceed 100 FH (+/- 10 FH); See AD compliance for details | Thielert Aircraft Engines TAE125-01 engines | Engine Oil System – Piston Cooling Nozzles – Inspection | Thielert Service Bulletin TM TAE125-0017 dated 14 December 2007 |
039-08 PTZ | FAA 2008-05-01 | 03.04.2008 | Within 2,200 flight
hours after the effective date of this AD, but not to exceed 24 months after the effective date of this AD; See AD compliance for details | General Electric Company (GE) CF34-8C1/-8C5/-8C5B1/-8E5/-8E5A1 turbofan engines
GE CF34-10E series turbofan engines
This engines are installed on, but not limited to, Bombardier Inc. Model CL-600-2C10 (CRJ-700 & -701), and CL-600-2D24/-2D15 (CRJ-900) airplanes; Embraer ERJ 170- 100/ -200 series airplanes and Embraer ERJ 190-100/- 200 series airplanes | Prevent the engine from failing to shutdown during an overspeed which may lead to uncontained engine failure | See Table 1- Incorporation by Reference |
040-08 PTZ | FAA 2008-05-09 | 08.04.2008 | Within the next 50 hours time-inservice
after April 8, 2008 or within
the next 6 months after April 8, 2008 whichever occurs first | Cessna Aircraft Company Certain S/N of Models: 172R, 172S, 182T, T182T, 206H, T206H | Prevent failure of the seat base/back attach brackets, which could result in the seats collapsing backwards during flight with consequent loss of control | Cessna Aircraft Company Service
Bulletin SB07-25-04, dated April 23, 2007 |
041-08 PTZ | FAA 2008-05-02 | 08.04.2008 | See AD compliance for details | Empresa Brasileira de Aeronautica S.A. (EMBRAER)
Model EMB-135BJ, -135ER, -135KE, -135KL, -135LR, - 145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes; certificated in any category | Prevent failure of multiple hinge fittings, which could result in severe vibration, and to prevent failure
of the rudder control rods, which could result in jamming of the rudder II; and possible structural failure and reduced controllability of the airplane | See Table 1 and Table 2 |
042-08 PTZ | FAA 2008-04-21 | 03.04.2008 | Before the accumulation of 20,000 total flight hours, or within 7,000 flight cycles after the effective date of this AD, whichever occurs later; See AD compliance for details | Boeing Model 737-300, -400, and -500 series airplanes, certificated in any category; as identified in Boeing Service Bulletin 737-57-1210, Revision 2, dated June 13, 2007 | Prevent failure of the main deck floor beams at certain body stations due to fatigue cracking, which could result in rapid decompression of the airplane | Boeing Service Bulletin 737-57-1210, Revision 2, dated June 13, 2007 |
043-08 PTZ | FAA 2008-05-06 | 08.04.2008 | See AD compliance for details | Boeing Model 737-100, -200, -300, -400, and -500 series airplanes, certificated in any category; as identified in Boeing Service Bulletin 737-57-1296, dated June 13, 2007 | Detect and correct fatigue cracking
of the upper and lower chords and web of the longitudinal floor beams, which could result in rapid loss of cabin pressure | Boeing Service Bulletin 737-57-1296, dated June 13, 2007 |
044-08 PTZ | EASA 2008-0038 | 12.03.2008 | See AD compliance for details | Moravan Aviation s.r.o. (formerly Moravan n.p, Moravan a.s, MORAVAN - AEROPLANES a.s)
Z 143L aircraft variant, all serial numbers, certificated in any category | Carburettor Heating System - Vortex Inserts in the Heat Exchanger - Inspection / Replacement | Moravan Aviation Mandatory Service Bulletin Z143L/31a original issue; Revision No. 9 to Airplane Maintenance Manual, Doc. No. 005.022.1 (English Version) |
045-08 PTZ | EASA 2008- 0044 | 12.03.2008 | See AD compliance for details | EUROCOPTER (formerly EUROCOPTER-FRANCE, AEROSPATIALE) AS 350 and AS 355 helicopters | Equipment / Furnishings - Rear Bench Seat and Sliding Doors - Limitation / Removal / Modification | EUROCOPTER AS 350 Service Bulletin No. 25.00.70 original issue; EUROCOPTER AS 355 Service Bulletin No. 25.00.66 original issue |
046-08 PTZ | EASA 2008-0046 | 13.03.2008 | Before further flight after the effective date of this AD, modify the AFM; See AD compliance for details | Moravan Aviation s.r.o (formerly Moravan n.p, Moravan a.s, Moravan –Aeroplanes a.s) Z 43 and Z 143L aeroplanes, all serial numbers | Airworthiness Limitations - Permissible Aerobatic manoeuvres in Utility category - Modification | MORAVAN Aviation Mandatory Service Bulletins Z43/46a initial issue and Z143L/29a initial issue |
047-08 PTZ | EASA 2008- 0048 | 13.03.2008 | Before 30 September 2009; See AD compliance for details | Before 30 September 2009; See AD compliance for details | Landing Gear – Braking and Steering Control Unit (BSCU) – Modification / Replacement | AIRBUS Service Bulletin A320-32-1336 original issue |
048-08 PTZ | EASA 2008-0039 | 21.03.2008 | See AD compliance for details | Centre Est Aéronautique, Avions Pierre ROBIN, Constructions Aéronautiques
de Bourgogne (CAB), APEX INDUSTRIES APEX AIRCRAFT DR400 | DC generation - Voltage regulator and IFR & Night-VFR operations - Modification / Restrictions | APEX AIRCRAFT SB No.070306 Revision 1 |
049-08 PTZ | EASA 2008- 0051 | 19.03.2008 | No later than 31 December 2009; See AD compliance for details | AIRBUS (formerly AIRBUS INDUSTRIE) A318, A319, A320 and A321 aircraft | Fuel / Electrical Power - Prevention of Fuel Tank Explosion Risks - Electrical Cables - Modification | AIRBUS Service Bulletin A320-24-1062 Revision 6 |
050-08 PTZ | EASA 2008-0054 | 19.03.2008 | Within the next 6 months after the effective date of this AD, and thereafter at intervals not to exceed 2 years; See AD compliance for details | Saab AB, Saab Aerosystems SAAB SF340A and 340B aircraft | Landing Gear – Emergency Extension Valve – Functional Check | SAAB SB 340-32-136 dated 9 January 2008; and SAAB 340 Maintenance Review Board (MRB) Report, Section F, Revision 6 |
051-08 PTZ | EASA 2008-0056-E
This AD is superseded by EASA Emergency AD 2008-0056R1-E
(PTZ 054-08) | 10.03.2008 | Before next flight; See AD compliance for details | Thielert Aircraft Engines
TAE125-02-99 engines
These engines are known to be installed on, but not limited to, Cessna 172 and (Reims-built) F172 series (EASA STC Nr. EASA.A.S.01527); Piper PA-28 series (EASA STC Nr. EASA.A.S.01632), APEX (Robin) DR 400 series (EASA STC Nr. EASA.A.S.01380); and Diamond DA40 and DA42 aircraft | Engine Fuel Injection System – High-Pressure Fuel Line Bracket –Installation | Thielert Aircraft Engines Service Bulletin TM TAE 125-1005 P1, Revision 2 dated 06 March 2008 |
052-08 PTZ | CF-2008-15 TRANSPORT CANADA EMERGENCY AD | 10.03.2008 | See AD Corrective Actions for details | All Bombardier Inc. Model CL-600-2B19 “Regional Jet” aircraft | Enhancement to Takeoff Operational Safety Margins | Aircraft Flight Manual (AFM) Temporary Revision (TR) RJ/155-2, dated 07 March 2008 |
053-08 PTZ | CF-2008-16 TRANSPORT CANADA EMERGENCY AD | 12.03.2008 | See AD Corrective Actions for details | All Bombardier Inc. CL-600-1A11, CL-600-2A12 and CL-600-2B16 aircraft | Enhancement to Takeoff Operational Safety Margins | See AD Corrective Actions for details |
054-08 PTZ | EASA Emergency AD 2008-0056R1-E
This AD supersedes EASA AD 2008-0027-E (051-08 PTZ) | 10.03.2008 | Before next flight; See AD compliance for details | Thielert Aircraft Engines
TAE125-02-99 engines
These engines are known to be installed on, but not limited to, Cessna 172 and (Reims-built) F172 series,
Piper PA-28 series, APEX (Robin) DR 400 series, and Diamond DA40 and DA42 | Engine Fuel Injection System – High-Pressure Fuel Line Bracket – Installation | Thielert Aircraft Engines Service Bulletin TM TAE 125-1005 P1, Rev. 1
and Thielert Aircraft Engines Service Bulletin TM TAE 125-1005 P1, Rev. 2 |
055-08 PTZ | Swedish Civil Aviation Authority AD 1-201 | 01.03.2008 | To be performed within three months from the effective date of this AD | FOLA Airsafe life vests type A-190 or A-290 | Inspection of the zipper on the life vest valise | FOLA Airsafe Service Bulletin 9-387 rev. A or later revision |
056-08 PTZ | EASA 2006-0316 R1
This AD revises and replaces EASA Emergency AD 2006-0316-E (PTZ 103-06) | 17.10.2006 | See AD compliance for details | BRP-Rotax GmbH & Co. KG; Bombardier-Rotax GmbH & Co. KG; Bombardier-
Rotax GmbH Rotax 912 and 914 series engines | Engine – Magnetic Plug – Inspections | BRP-Rotax Alert Service Bulletin ASB-912-051 and ASB-914-034 and BRP-Rotax Service Bulletin SB-912-051 and SB-914-034 |
057-08 PTZ | FAA Emergency AD 2008-06-51
EASA Notification for FAA 2008-06-51 | 12.03.2008 | Before further flight, unless the actions have already been done; See AD compliance for details | Lycoming Engines IO, (L)IO, TIO, (L)TIO, AEIO, AIO, IGO, IVO, and HIO series reciprocating engines, Teledyne Continental Motors (TCM) TSIO-360-RB reciprocating engines, and Superior Air Parts, Inc. IO-360 series reciprocating engines with certain Precision Airmotive LLC RSA-5 and RSA-10 series fuel injection servos | Substantial loss of engine power and subsequent loss of control of the airplane | Precision Airmotive LLC Mandatory Service Bulletin (MSB) No. PRS- 107, Revision 1, dated March 6, 2008 |
058-08 PTZ | CF-2008-08R1
This AD Supersedes CF-2008-08 | 07.02.2008 | See AD for details | Pratt & Whitney Canada (P&WC) - PW305A and PW305B engines | Engine Fan Blade Fracture | Alert Service Bulletin (ASB) No. A24588
Special Instructions (SI) No.37-2007. ASB No. A24588R2 Service Bulletin (SB) No. 24595 |
059-08 PTZ | FAA 2008-06-24 | 23.04.2008 | Within 60 months after the effective date of this AD; See AD compliance for details | Boeing Model 737-300, -400, and -500 series airplanes | Prevent the in-line
flow indicators of the passenger oxygen masks from fracturing and separating, which could inhibit
oxygen flow to the masks and consequently result in exposure of the passengers and cabin attendants to hypoxia following a depressurization event | Boeing Special Attention Service Bulletin 737-35-1099, dated April 9, 2007;
B/E Aerospace Service Bulletin 174080-35-01, dated February 6, 2006; and Revision 1, dated May 1, 2006 |
060-08 PTZ | FAA 2008-06-27 | 28.04.2008 | See AD compliance for details | Goodrich (Formerly BFGoodrich) Goodrich evacuation systems approved under Technical Standard Orders (TSOs) TSO-C69, TSO-C69a, and TSO-C69b, installed on certain Boeing airplanes, McDonnell Douglas airplanes and Airbus airplanes certificated in any category, as listed in Table 1-3 of this AD | Prevent failure of an evacuation system, which could impede an emergency evacuation and increase the chance of injury to passengers and flightcrew during the evacuation | Goodrich Service
Bulletin 25-343, Revision 3, dated January 12, 2007
Goodrich Service Bulletin 25-344, Revision 2, dated October 11, 2006 |
061-08 PTZ | FAA 2008-06-29 | 08.04.2008 | See AD compliance for details | Boeing Model 737-300, -400, and -500 series airplanes, certificated in any category | Detect and correct loose or missing parts from the main slat track downstop assemblies, which could puncture the slat can and result in a fuel leak and consequent fire | Boeing Alert Service Bulletin 737-57A1301, dated February 5, 2008 |
062-08 PTZ | FAA 2008-06-28 | 10.04.2008 | See AD compliance for details | Avidyne Corporation (Avidyne)
Primary Flight Displays (PFDs) certain Part
Numbers (P/Ns) that are installed on, but not limited to the following airplanes:
Adam Aircraft, Cessna Aircraft; Cirrus Design Corporation; Diamond Aircraft Industries; Hawker Beechcraft Corporation; Hawker Beechcraft Corporation; Piper Aircraft. See AD for models. | Prevent certain conditions from existing when PFDs
display incorrect attitude, altitude, and airspeed information. This could result in airspeed/altitude
mismanagement or spatial disorientation of the pilot with consequent loss of airplane control, inadequate traffic separation, or controlled flight into terrain. | See AD |
063-08 PTZ | EASA 2008-0064 This AD supersedes EASA AD 2007-0313 | 18.04.2008 | See AD compliance for details | EUROCOPTER DEUTSCHLAND GmbH
EC135 and EC635 series helicopters, all models, all serial numbers, if equipped
with Control rod Part Number (P/N) L672M2005207, Ball pivot P/N 92-201-00 and/or Ball pivot P/N 92-207-00 | Rotor Flight Controls – Tail Rotor Control Rod and Ball Pivot – Inspection / Replacement | EUROCOPTER EC 135 Alert Service Bulletin No. EC135-67A-017 Revision 2 dated 17 March 2008 |
064-08 PTZ | EASA 2008-0069 | 25.04.2008 | See AD compliance for details | Saab AB, Saab Aerosystems SAAB SF340A Serial No’s 004 thru 159 and SAAB 340B Serial No’s 160 thru 459 | Power Plant – Forward Engine Cowl Door – Inspection / Reporting | SAAB Service Bulletin SB-340-71-060, dated 08 Feb. 2008 |
065-08 PTZ | FAA 2008-0628R1 | 10.04.2008 | See AD compliance for details | Avidyne Corporation (Avidyne) Primary Flight Displays (PFDs) certain P/N that are installed on, but not limited to the following airplanes: Adam Aircraft, Cessna Aircraft, Cirrus Design Corporation, Diamond Aircraft, Hawker Beechcraft, Piper Aircraft | Prevent certain conditions from
existing when PFDs display incorrect attitude, altitude, and airspeed information. This could result in
airspeed/altitude mismanagement or spatial disorientation of the pilot with consequent loss of airplane control, inadequate traffic separation, or controlled flight into terrain | Avidyne Service Alert No. SA-08-001, dated February 12, 2008 |
066-08 PTZ | FAA 2008-08-14 | 29.04.2008 | Before further
flight, unless the actions have already been done; see AD compliance for details
Repetitive Inspections- At every engine oil change or within every 50 hours of engine run time, whichever occurs First. | Precision Airmotive LLC
This AD applies to the reciprocating engines (Lycoming Engines, Teledyne Continental Motors, Superior Air Parts) with an installed Precision Airmotive LLC, RSA-5 or RSA-10 series fuel injection servo, having a servo plug gasket, part number (P/N) 365533, installed under the fuel injection servo plug, P/N 383493 | Prevent a lean running engine, which could result in a substantial loss of engine power and subsequent loss of control of the airplane | Precision Airmotive LLC Mandatory Service Bulletin No. PRS-107, Revision 1 |
067-08 PTZ | FAA 2008-08-10 | 19.05.2008 | See AD compliance for details | Boeing 737-100, -200, -200C, -300, -400, and -500 series airplanes, certificated in any category | Detect and correct that cracking, which could result in disconnection of the MLG actuator
from the rear spar and support beam, consequent damage to the hydraulic system, and possible loss of the ''A'' and ''B'' hydraulic systems and damage or jamming of the flight control cables | Boeing Alert Service Bulletin 737-57A1266, Revision 1, dated January 3, 2007 |
068-08 PTZ | EASA 2008-0070 | 29.04.2008 | See AD compliance for details | PILATUS AIRCRAFT Ltd. PC-6 | Landing Gear - Locking plate attachment screw - Replacement | PILATUS PC-6 Service Bulletin No. 32-001 |
069-08 PTZ | EASA 2008-0064 R1 | 18.04.2008 | See AD compliance for details | EUROCOPTER DEUTSCHLAND GmbH
EC135 and EC635 helicopters
if equipped with Control rod Part Number (P/N) L672M2005207, Ball pivot P/N 92-201-00 and/or Ball pivot P/N 92-207-00 | Rotor Flight Controls – Tail Rotor Control Rod and Ball Pivot – Inspection / Replacement | EUROCOPTER EC135 Alert Service Bulletin No. EC135-67A-017 Revision 2 dated 17 March 2008 |
070-08 PTZ | FAA 2008-08-17 | 06.05.2008 | Within 10 hours
time-in-service or at the next regular inspection interval, whichever occurs first, unless the actions have already been done | Kelly Aerospace Power Systems turbochargers referenced in paragraphs (c)(1) through (c)(15)(vi) of this AD installed on Lycoming Engines, Teledyne Continental Motors. See AD Applicability for details | Prevent hazardous amounts of carbon monoxide
from entering the cabin, an increase in under-cowl temperatures hampering engine and accessory
function, and loss of tailpipe retention, which could lead to an in-flight fire and loss of control of the airplane | See table 1 |
071-08 PTZ | EASA 2008-0077 | 13.05.2008 | No later than 30 Sept. 2009; See AD compliance for details | TURBOMECA ARRIEL 2B turboshaft engines
ARRIEL 2B, 2B1 and 2B1A turboshaft engines, all serial numbers.
These engines are known to be installed on, but not limited to: Eurocopter AS 350 B3 and EC 130 B4 helicopters. | Engine Fuel & Control – Hydro Mechanical Unit (HMU) – Low Fuel Pressure Switch – Inspection/Replacement | Turboméca Mandatory Service Bulletin 292 73 2826 |
072-08 PTZ | EASA 2008-0078 | 08.05.2008 | See AD compliance for details | Société de Motorisations Aéronautiques (SMA) Cessna Model 182M, 182N, 182P, 182Q, 182R, and (Reims-manufactured) F182P and F182Q aircraft, all serial numbers, if modified in accordance with STC EASA.A.S.00774 (SMA SR305-230 engine installation) | Engine Air – Air Inlet Manifold Hose Clamps – Inspection | SMA SB N° SB-C182-75-002 Revision 2 |
073-08 PTZ | EASA 2008-0082 | 09.05.2008 | See AD compliance for details | EUROCOPTER DEUTSCHLAND GmbH EC135 and EC635 series helicopters, all models, all serial numbers | Main Rotor Drive – Main Gearbox (MGB) Oil Sampling & Analysis Program – Introduction | Eurocopter EC 135 Alert Service Bulletin No. EC135-63A-012 Revision 02 |
074-08 PTZ | FAA 2008-10-02 | 12.05.2008 | See AD compliance for details | Cessna Aircraft Company See Table 1 and Table 2 for list of types and S/N | Prevent erroneous indications from the altimeter, airspeed, and vertical speed indicators, which could cause the pilot to react to incorrect flight information and possibly result in loss of control | none |
075-08 PTZ | FAA 2008-10-03 | 21.05.2008 | See AD compliance for details | Bell Helicopter Textron
204B, 205A, 205A-1, 212, 412, 412CF, and 412EP 205B, 210 | To detect any damage in a T/R blade, prevent cracking of a T/R blade leading to failure from static overload, and subsequent loss of control of the helicopter | none |
076-08 PTZ | FAA 2008-09-13 | 06.06.2008 | See AD compliance for details | Boeing Model 737-300, -400, and -500 series airplanes, certificated in any category | To maintain the continued structural integrity of the entire fleet of Model 737-300, -400, and -500 series airplanes | Boeing Document D6-82669, ''Supplemental Structural Inspection Document Models 737-300/400/500 Airplanes,'' Original Release, dated May 2007 |
077-08 PTZ | FAA 2008-09-15 | 06.06.2008 | See AD compliance for details | Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, certificated in any category | Detect and correct cracking in the vinyl interlayer or damage to the
structural inner glass panes of the flight deck No. 2, No. 4, and No. 5 windows, which could result in
loss of a window and rapid loss of cabin pressure. Loss of cabin pressure could cause crew communication difficulties or crew incapacitation | Boeing Alert Service Bulletin 737-56A1023, dated May 24, 2007 |
078-08 PTZ | EASA 2008-0083 | 19.05.2008 | Within 12 calendar months after the effective date of this AD; See AD compliance for details | PILATUS AIRCRAFT Ltd. All PC-6 series aircraft models, from Manufacturer Serial Number (MSN) 101 through MSN 949 inclusive and all PC-6 series aircraft models, manufactured by Fairchild, from MSN 2001 through MSN 2092 inclusive | Fuselage - Self-locking Stop Nuts - Replacement | PILATUS PC-6 Service Bulletin No. 53-002 Rev. 2 |
079-08 PTZ | CF-2008-18 | 28.05.2008 | See AD Corrective Action for details | Bombardier Inc. Models
CL-600-1A11
CL-600-2A12
CL-600-2B16 CL-600-2B16 | Wing Anti-Ice Piccolo Ducts | See AD for list |
080-08 PTZ | CF-2008-19 | 28.05.2008 | Within 450 hours air time after the effective date of this AD; See AD Corrective Action for details | Bombardier Inc. Models:
CL-600-2C10
CL-600-2D15 CL-600-2D24 | Water Ingress into the Cockpit | Bombardier
Aerospace Alert Service Bulletin, A670BA-56-002, Revision “A”, dated 26 Feb 2008 |
081-08 PTZ | FAA 2008-10-09 | 12.06.2008 | See AD for details | Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes | Potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane | Boeing 737-100/200/200C/300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), D6-38278-CMR, Revision March 2008 |
082-08 PTZ | CF-2007-13R1 Supersedes AD CF-2007-13 | 28.05.2008 | See AD Corrective Action for details | Bell Helicopter Textron Canada (BHTC) Model 206B series helicopters | Power Turbine RPM Steady State Operation Avoidance | Alert Service Bulletin
(ASB) 206-07-115 Rev B
or 206L-07-146 Rev A |
083-08 PTZ | EASA 2008-0086 | 27.05.2008 | Within the next 200 flight hours after the effective date of this AD; See AD for details | Diamond Aircraft Industries GmbH
DA 42 and DA 42 M aircraft, all S/N, if aileron bellcranks P/N DA4-2717-50-00 are installed | Flight Controls – Aileron Bellcrank and Rod Ends – Replacement | Diamond Aircraft Industries GmbH MSB-42-043
or MSB-42-043/1 |
084-08 PTZ | EASA 2008-0082R1
This AD revises and replaces EASA AD 2008-0082 | 09.05.2008 | See AD compliance for details | Eurocopter Deutschland GmbH
EC135 and EC635 series helicopters, all models, all serial numbers | Main Rotor Drive – Main Gearbox (MGB) Oil Sampling & Analysis Program – Introduction | Eurocopter EC 135 Alert Service Bulletin No. EC135-63A-012 Rev. 02 |
085-08 PTZ | FAA 2008-11-04 | 25.06.2008 | See AD compliance for details | Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, certificated in any category | Reports of cracks found in the skin, bearstrap, and/or frame outer chord in the hinge cutout areas of the forward entry and forward galley service doorways. We
are issuing this AD to detect and correct such cracking, which could result in rapid decompression of the airplane | Boeing Alert Service Bulletin 737-53A1200, dated April 13, 2006 |
086-08 PTZ | EASA Emergency AD 2008-0100-E
This AD is superseded by EASA Emergency AD 2008-0106-E
(090-08 PTZ) | 27.05.2008 | See AD Required action(s)
and Compliance Time(s) | Thielert Aircraft Engines GmbH
TAE125-02-99 (commercial designation Centurion 2.0) engines, all serial numbers, except those with clutch Part Number (P/N) 05-7211-K006001 installed | Engine – Clutch Assembly – Inspection / Replacement | Thielert Aircraft Engines GmbH SB TM TAE 125-1006 P1 |
087-08 PTZ | LBA D-2008-178 | 31.05.2008 | Within the next 50 fh after publication of this AD, but not later than June 30, 2008.
The inspection must be repeated together with the periodical inspection or with the 12-month inspection (whatever comes first) | EUROCOPTER Deutschland
EC135 all models EC635 all models | Impair of the controls’ freedom of movement by incorrect fixed bearings in the main rotor and tail rotor flight controls due to a production discrepancy | EUROCOPTER Alert Service Bulletin EC135-67A-019 dated April 28, 2008 |
088-08 PTZ | CF-1996-24R1 Cancels Airworthiness Directive (AD) CF-96-24 | 13.06.2008 | See AD Corrective Action for details | Pratt & Whitney Canada (P&WC) PT6A Series engines | Compressor Bleed-off Valve Cover Assembly Inspection/Replacement | none |
089-08 PTZ | FAA 2008-11-15 | 03.06.2008 | See AD compliance for details | McDonnell Douglas airplanes Model 717-200; Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, and DC-9-15F; DC-9-21; DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, DC-9-34F, and DC-9-32F (C-9A, C-9B); DC-9-41; DC-9-51; DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87); MD-88; MD-90-30 airplanes; certificated in any category | Potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane | Boeing Twinjet Special Compliance Items Report, MDC-92K9145, Revision G |
090-08 PTZ | EASA Emergency AD 2008-0106-E
This AD supersedes AD 2008-0100-E (086-08 PTZ )dated 23 May 2008 | 03.06.2008 | See AD required action(s)
and Compliance Time(s) section for details | Thielert Aircraft Engines GmbH
All TAE125-02-99 (commercial designation Centurion 2.0) engines having the clutch assembly P/N 05-7211-K000304 installed.
These engines are known to be installed on, but not limited to, Cessna 172 and (Reims-built) F172 series, Piper PA-28 series, APEX (Robin) DR 400 series and Diamond DA40 and DA42 aircraft | Engine - Clutch Assembly - Replacement | Thielert Aircraft Engines GmbH SB TM TAE 125-1006 P1 Rev. 1 |
091-08 PTZ | FAA 2008-11-18 | 07.07.2008 | See AD compliance for details | Cirrus Design Corporation Model SR20 airplanes, serial numbers 1005 through 1815 | Detect and correct leaks in the exhaust system, which could result in exhaust gases leaking into the cabin heating system. This condition could lead to carbon monoxide in the cabin and incapacitation of the pilot. | Cirrus Service Bulletin SB 2X-78-07 R1, Rev 1 | |
092-08 PTZ | FAA 2008-12-03 | 09.07.2008 | See AD compliance for details | This AD applies to airplanes, certificated in any category and equipped with auxiliary fuel tanks installed in accordance with specified Supplemental Type Certificates (STCs), as identified in Table 1 of this AD (Boeing, British Aerospace, McDonnell Douglas). | Prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane | See AD | |
093-08 PTZ | EASA Emergency AD 2008-0116-E | 19.06.2008 | See AD Required action(s)
and Compliance Time(s) for details | Eurocopter Deutschland GmbH
EC135 and EC635 helicopters | Main Rotor Drive – Main Gearbox (MGB) Oil Sampling & Analysis Program – Amendment | Eurocopter EC135 Alert Service Bulletin No. EC135-63A-012 Revision 03 | |
094-08 PTZ | HB-2008-242 EMERGENCY | 04.07.2008 | Before the next flight after the effective date of this AD; see AD
COMPLIANCE/ ACTION for details | Pilatus – PC-6 | FLAP OPERATING MECHANISM – LEAF SPRINGS – Inspection, Replacement | PILATUS PC-6 Service Bulletin No. 27-002
PILATUS PC-6 Service Bulletin No. 27-003 | |
095-08 PTZ | D-2008-222
This AD is supersedes by AD D-2008-222R1
The AD D-2008-222 has been cancelled | 23.06.2008 | See AD compliance for details | Rolls-Royce Deutschland, Dahlewitz, Germany
BR700-710 | BR700-710 - Re-use of Potentially Damaged Engine Material | RRD Worldwide Communication WW/20209/1/30
May 08, which is also covered by EASA Safety Information Bulletin SIB 2008-49 | |
096-08 PTZ | EASA 2007-0241R2 | 07.09.2007 | See AD compliance for details | Pilatus Aircraft Ltd.
PC-6 series aircraft | Wing – Wing Strut Fitting – Inspection / Replacement | Pilatus Aircraft Ltd. PC-6 SB No. 57-005 dated 30 August 2007, Rev. 1
dated 19 Nov. 2007 and Rev 2 dated 19 May 2008 | |
097-08 PTZ | EASA 2008-0113 | 24.06.2008 | See AD compliance for details | Eurocopter Deutschland GmbH
EC135 and EC635 series helicopters and
MBB-BK 117 C-2 helicopters | Rotors Flight Control – Cyclic-Stick Locking Device – Modification | Eurocopter Deutschland GmbH ASB MBB BK117C-2-67A-008 and
ASB EC135-67A-015, both dated 14 April 2008 | |
098-08 PTZ | CF-2008-20 | 30.06.2008 | See AD Corrective
Action for details | Bombardier Inc. Model CL-600-2B19 aircraft | Fuel System Safety - Insufficient Electrical Bonding at the Refuel/Defuel Shutoff
Valves | Bombardier SB 601R-28-053, Revision C, dated
14 March 2006 | |
099-08 PTZ | CF-2008-21 | 30.06.2008 | See AD Corrective
Action for details | Bombardier Inc. CL-600-2B19 Aircraft | Cracking of Main Landing Gear Trunnion Fitting Web | Temporary
Revision (TR) 2B-2136 of the Canadair Regional Jet Maintenance Requirement Manual
(MRM), Appendix B, “Airworthiness Limitations” | |
100-08 PTZ | EASA 2008- 0121 | 11.07.2008 | See AD compliance for details | EUROCOPTER
AS 350 helicopters | Stabilizers – Upper and Lower Fin Attachment Fitting -
Modification | EUROCOPTER AS 350 ALERT SERVICE BULLETIN No. 55.00.16 Rev 0 dated 28 February 2008 | |
101-08 PTZ | EASA 2008-0127R1 | 22.07.2008 | See AD compliance for details | Saab AB, Saab Aerosystems
SF340A and 340B aircraft | Fuel System – Refuel/Defuel Panel Illuminated Placard – Inspection /
Replacement | SAAB Service Bulletin SB-340-28-027 | |
102-08 PTZ | EASA 2008-0128 | 23.07.2008 | See AD compliance for details | Thielert Aircraft Engines GmbH
TAE 125-01, all serial numbers | Time Limits / Maintenance Checks – Airworthiness Limitations –
Implementation | Thielert Aircraft Engines GmbH Operation & Maintenance Manual TAE 125-01 OM-02-01, Chapter 5 at Issue 3 Rev 5 | |
103-08 PTZ | D-2008-232 | 11.07.2008 | See AD compliance for details | Grob Aerospace, Germany
Grob G103 Twin Astir | Bolt cracking in the airbrake control system as a result of exceeding bolt torque and / or irregular adjustment of the airbrake system | GROB Service Bulletin NO. MSB 315-76/1 | |
104-08 PTZ | FAA 2008-12-01 | 16.06.2008 | See AD compliance for details | Cessna Aircraft Company
Model 525 airplanes, serial numbers 525-0600 through 525-0662 | Detect and correct missing firewall sealant between the aft firewall assembly and seal assembly, which could result in failure of the fire extinguishing system to prevent the spread of fire through the firewall gap | Cessna
Aircraft Company
Citation Service
Letter SL525-71-05 | |
105-08 PTZ | FAA 2008-13-28 | 17.07.2008 | See AD compliance for details | Hartzell Propeller Inc.
left-hand rotating ( )HC-( )(2,3)Y(K,R)-2 two- and
three-bladed, aluminum hub, ''compact'' series propellers;
These propellers
are installed on Lycoming Engines LIO-360 series and LO-360 series reciprocating engines, installed
on Piper Aircraft, Inc. Seneca PA-34-200 and Seminole PA-44-180, and Hawker Beechcraft Corporation Model 76 Duchess, airplanes | Prevent failure of the propeller hub, which could result
in blade separation and loss of control of the airplane | Hartzell Propeller Inc. Alert Service Bulletin (ASB) No. HC-ASB-61-297, Rev 1 | |
106-08 PTZ |
