Številka PTZ | Referenčna PTZ | Datum efektive | Rok izvršitve | Proizvajalec | Vsebina PTZ | Referenčni SB |
001-07 PTZ | FAA 2006-26-01 | 03.01.2007 | See AD compliance for details | This AD applies to CFM International CFM56-2 series, -3 series, -5 series, and -7B series engines with certain fuel filters- see AD;
These engines are installed on, but not limited to, Airbus A320 and A340 series airplanes, Boeing DC8-71 series, -72 series, and -73 series airplanes, and Boeing 737 series airplanes |
To prevent the loss of engine thrust that could result in loss of control during takeoff or landing;
This AD requires replacing certain fuel filters- see AD | None |
002-07 PTZ | FAA 2007-01-06 | 13.02.2007 | See AD compliance for details | Bell Helicopter Textron Canada; Model 206A, B, L, L-1, L-3, and L-4 helicopters, with a tail rotor blade (blade) with the certain (see AD) part number (P/N) and serial number (S/N) installed, certificated in any category | To prevent blade failure and subsequent loss of control of the helicopter | Bell Helicopter Textron Alert Service Bulletin No. 206-04-100 for Model 206A and B and No. 206L-04-127 for Model 206L series, both Rev. C, both dated March 5, 2005 |
003-07 PTZ | FAA 2007-01-07 | 16.02.2007 | See AD compliance for details | Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, certificated in any category; S/N 7003 through 7067 inclusive, and 7069 through 8999 inclusive; equipped with main landing gear (MLG) main fittings, having P/N 601R85001-3 or -4 (Messier-Dowty P/N 17064-101, -102, -103, or -104) | To detect and correct fatigue cracking of the main fitting of the MLG and consequent failure of the main fitting, which could result in the collapse of the MLG | Canadian airworthiness directive CF-2004-18R1, dated September 21, 2005 |
004-07 PTZ | EASA 2006-0092R1
AD CANCELATTION NOTICE | 16.01.2007 | N/A | Hartzell two blade, aluminum hub, "compact" ( )HC-( )2Y( )-( ) series propellers manufactured before Dec 1991 that do not have an "A" or "B" suffix letter at the end of the hub and propeller S/N and are installed on Lycoming ( )-360 series engines
This Notice cancels EASA AD 2006-0092 dated 03 May 2006, including the ‘correction’ dated 07 Sept. 2006. The actions required by the FAA AD 2006-18-15 are almost identical to the ones required by EASA AD 2006- 0092. They are adequate to correct the unsafe condition and therefore that FAA AD is considered ‘accepted’ . | Propellers – Propeller Hub – Inspection | Hartzell Propeller Inc. Service Bulletin HC-SB-61-269, dated April 18,
2005 |
005-07 PTZ | FAA 2007-02-17 | 02.03.2007 | Within 90 days after the effective date of this AD, unless already done See AD compliance for details | Turbomeca Arriel -1A, -1A1, -1A2, -1B, -1B2, -1C, -1C1, -1C2, -1D, -
1D, -1D1, -1K1, -1E, -1E2, -1S, and -1S1 series turboshaft engines. These engines are installed on, but not limited to, Augusta A 109 series, Eurocopter AS 350, AS 365, SA 365, EC 155, and BK 117 series, and Sikorsky S-76A and S-76C series helicopters | Identify and correct an unsafe condition on an aviation product | EASA AD 2006-0068 |
006-07 PTZ | FAA 2007-02-16 | 01.03.2007 | See AD compliance for details | Saab Model SAAB-Fairchild SF340A (SAAB/SF340A) airplanes having
S/N 004 through 159 inclusive, and Model SAAB 340B airplanes having S/N 160 through 367 inclusive; certificated in any category; on which Saab Modification 2533 has not been implemented | To prevent failure of the starter generator, which could cause a low voltage situation in flight and result in increased pilot workload and reduced redundancy of the electrical powered systems | Saab Service Bulletin 340-24-035;
Saab Service
Bulletin 340-24-026 and Swedish airworthiness directive 1-197 |
007-07 PTZ | EASA 2007-0010 This AD supersedes EASA AD 2006-0353, which superseded ENAC(Italy) PA 2002-597 | 18.12.2006 (effective date of EASA 2006-0353 | 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 |
008-07 PTZ | EASA 2007-0025 | 01.10.2004 Effective date of AD A-2004-01 | From the last inspection date, as requested by AD A-2004-01, repeat
thereafter not to exceed 110 hours, TIS, See AD compliance for details | Rotax 912 A, F, S series; Rotax 914 F series and any other Rotax type 912 and 914 series engine whose crankcase assembly has been replaced by a crankcase having a S/N up to S/N 27811 inclusive.
These engines are known to be installed on, but not limited to, the following aircraft types:
3-i Sky Arrow, Aeromot, Aircraft Philipp (formerly Alpla-Werke; Nitsche), Diamond, Evektor- Aerotechnik, Grob, Issoire, Reims Aviation, Scheibe, Stemme, Tecnam, W.D. Aircraft | Engine – Crankcase – Inspections | BRP-Rotax Mandatory Service Bulletins, SB-912-029 R3 and SB-914-018 R3 or later approved revisions |
009-07 PTZ | EASA 2007-0027 | 19.02.2007 | See AD compliance for details | Vulcanair (formerly Partenavia) P68 series aircraft, all models, all serial numbers | Structures – Wings & Stabilizers Structural Fatigue Limits – Implementation | Vulcanair SB No.120 original issue or Rev. 1 dated 07 June 2006 or later approved rev. |
010-07 PTZ | FAA 2007-03-19 | 15.03.2007 | See AD compliance for details | Bombardier, Inc. (Formerly Canadair) Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, S/N 7003 and subsequent; certificated in any category; equipped with main landing gear (MLG) main fittings, certain part numbers (P/N), see AD for details | Detection and correction of premature cracking of the main fittings of the main landing gears (MLGs) | CF-2003-09R1, dated September 21, 2005 (PTZ 037-03);
Bombardier Alert Service Bulletin A601R-32-088; Bombardier Service Bulletin 601R-32-093 |
011-07 PTZ | FAA 2007-03-15 | 19.03.2007 | See AD compliance for details | CFM International CFM56-5 and -5B series turbofan engines- see AD for details; These engines are installed on, but not limited to Airbus Industrie A318, A319, A320, and A321 airplanes | Prevention of unexpected deterioration of critical rotating engine parts due to higher than desired engine operating exhaust gas temperature EGT | CFM56 Service Bulletin
No:
CFM56-5B S/B 77-0008
CFM56-5 S/B 77-0020
and DGAC AD F-2003-001 R2 (see 050-05 PTZ) |
012-07 PTZ | EASA EMERGENCY AD 2007-0036-E
This AD is superseded by EASA 2007-0036R1 | 16.02.2007 | See AD compliance for details | AIRBUS A318, A319, A320 and A321 aircraft | Power Plant – Forward Engine Mount Bolts – Inspection / Replacement / Retorque | AIRBUS All Operator Telex (AOT) A320-71A1042 Rev 01; Goodrich All Operator Letter (AOL) CFM56-074 Rev 1 |
013-07 PTZ | FAA 2004-23-02 Correction | 23.12.2004 | See AD compliance for details | Raytheon Aircraft Company
aircraft different models- see AD list; including C90, and C90A | Detection and correction of cracks in the NLG fork, which could result in reduced structural integrity and inability of the NLG fork to carry design limit and ultimate loads | Raytheon Aircraft Company Mandatory Service Bulletin SB 32-2102, Revision 7, Revised: July, 2003 |
014-07 PTZ | FAA 2007-04-15 | 23.03.2007 | Perform within 600 flight hours after the effective date of this AD, unless the actions have already been done- see AD | This AD applies to Sicma Aero Seat, passenger seat assemblies certain P/N- see AD These seat assemblies are installed on, but not limited to, Airbus A300, A310, A318, A319, A320, A321, A330, and A340 series airplanes | Prevent detachment of passenger seat assemblies, especially during emergency conditions, leading to occupant injury | Sicma Aero Seat Service Bulletin No. 90-25-005, Issue 2, dated March 31, 1999, and Annex 1, Issue 1, dated March 31, 1999 and Direction Generale de L'Aviation Civile, AD 1994-085(AB) R2, dated July 13, 1999 |
015-07 PTZ | FAA Emergency AD 2007-04-51
This AD is superseded by
FAA 2007-05-16 (PTZ 033-07 PTZ) | Takoj | Within 20 engine flight hours after
receipt of this emergency AD See AD for details | All owners and operators
of General Electric Aircraft Engines (GE) CF34-3A1/-3B/-3B1 turbofan engines installed on Bombardier, Inc. CL-600-2B16 (CL-601-3R Variant), CL-600-2B16 (CL-604 Variant), and CL-600- 2B19 (Regional Jet Series 100 and 440) model airplanes | An uncontained fan disk failure during flight operation | GE Alert Service Bulletin (ASB) No. CF34-BJ S/B 72- A0213, dated February 15, 2007, and GE ASB No. CF34-AL S/B 72-A0232, dated February 15, 2007 |
016-07 PTZ | FAA 2007-04-18 | 23.03.2007 | See AD compliance for details | Learjet models identified in the applicable Bombardier service bulletin listed in Table 1 of AD | Prevent inadvertent operation, which could result in inadvertent fuel transfer by the left or right wing fuel system and subsequent over-limit fuel imbalance between the left and right wing fuel loads | See Table 3 and 4 in AD for details |
017-07 PTZ | EASA 2007-0038 | 07.03.2007 | Within the next 50 flight hours, after the effective date of this AD;
Repeat thereafter, at intervals not to exceed 100 flight hours; See AD compliance for details | A109E Agusta Helicopters up to serial number (s/n) 11158 inclusive and from s/n 11501 to 11510 inclusive | Hydraulic Power - Hydraulic Pipes P/N 109-0761-64-103 and 109-0761-65-103 – Inspection / Replacement | Agusta Bollettino Tecnico 109EP-73 original issue or later approved revisions |
018-07 PTZ | EASA 2007-0041 | 07.03.2007 | Within the next 50 operating hours and however within and not later
than March 31, 2007; repeat every 300 flight hours or yearly,
whichever occurs first See AD compliance for details | Agusta helicopters A109A, A109AII, A109C series, all models | Exhaust – Exhaust Duct Grooved Clamps – Inspection/Replacement | Agusta Bollettino Tecnico 109-123 dated 16 November 2006
or later approved revisions |
019-07 PTZ | EASA 2007-0043 | 07.03.2007 | Within the next 50 hours time in service (TIS) and however within and not later than April 30, 2007;
repeated every 100 flight hours or yearly,
whichever occurs first See AD compliance for details | Agusta helicopters AB206A and AB206B series, all models | Exhaust – Exhaust Duct Grooved Clamps – Inspection/Replacement | Agusta Bollettino Tecnico 206-242 dated 18 December 2006 or later approved revisions |
020-07 PTZ | EASA 2007-0044 | 08.03.2007 | See AD compliance for details | TURBOMECA Arriel 2B, 2B1 and 2B1A turbo-shaft engines. These engines are known
to be installed on, but not limited to, the following helicopters: Eurocopter AS 350 B3 and EC 130 B4 helicopters | Engine Fuel and Control - Hydromechanical Metering Unit (HMU) - Visual Inspection of the Drive-Link Splines | Turbomeca, S.A. Mandatory Service Bulletin No. 292 73 2812 - Update No.4 |
021-07 PTZ | EASA 2007-0045 | 08.03.2007 | See AD compliance for details | TURBOMECA ARRIEL 1A,1A1,1A2,1B, 1C, 1C1, 1C2, 1D, 1D1, 1E2, 1K, 1K1, 1S, 1S1
turboshaft engines originally assembled by TURBOMECA and having previously been used by an operator who is not under the control of a civil Authority (Military, Paramilitary…). These engines are known to be installed on, but not limited to, the following helicopters: Eurocopter AS350B/BA/B1/B2, AS365 N/N1/N2/C/C1/C2/C3 and BK117 C1/C2 (EC 145), Agusta A109 K/K2, Sikorsky S76 A+/A++/C helicopters | Return to Service for Civil Use from an Operator Not Controlled by a Civil Authority | Turbomeca, S.A. Service Bulletin No. A292 72 0806 – Original Issue, or later approved revisions |
022-07 PTZ | EASA 2007-0034 | 08.03.2007 | See AD compliance for details | EADS SOCATA (formerly SOCATA) TB 9, TB 10 and TB 200 aircraft, all serial numbers | Time Limits - Airworthiness Limitations – New Life Limit for Engine and Nose Landing Gear Mounts | EADS SOCATA TB 9 MM Chapter 4 Revision 18;
EADS SOCATA TB 10 MM Chapter 4 Revision 18; EADS SOCATA TB 200 MM Chapter 4 Revision 18 |
023-07 PTZ | EASA 2007-0047 | 09.03.2007 | At the next scheduled Inspection, but no later than 15 April 2007; See AD compliance for details | Diamond Aircraft Industries GmbH; DA 42 airplanes with certain serial numbers- see AD for details | Fuel System – Auxiliary Fuel Tank Venting- Inspection / Modification | Diamond Aircraft Industries Mandatory Service Bulletin MSB 42-032/1
or later approved revisions and DA 42 Maintenance Manual AMM-TR-OÄM-42-056f Temporary Revision |
024-07 PTZ | FAA 2007-04-19 | 12.03.2007 | See AD compliance for details | This AD applies to Superior Air Parts, Inc. (SAP), cast cylinder assemblies, certain P/N installed in Teledyne Continental Motors (TCM) 470, 520, and 550 series
reciprocating engines.
This AD also applies to SAP, cast cylinder assemblies
certain P/N installed in Lycoming Engines (LE) 320, 360, and 540 series reciprocating engines
and Avco Lycoming 540 series reciprocating engines. See AD for details. | To prevent cylinder separation that can lead to engine failure, a possible engine compartment fire, and damage to the airplane | Superior Air Parts, Inc. Mandatory Service Bulletin B06-01, Rev. E, dated January 24, 2007 |
025-07 PTZ | EASA 2007-0036R1
This AD supersedes EASA EAD 2007-0036-E | 16 Februar 2007 (effective date of Emergency AD 2007-0036-E) | See AD compliance for details | AIRBUS Models A318-111 and -112; A319-111, -112, -113, -114 and -115;
A320-111, -211, -212, -214, -215 and -216; and A321-111, -112, -211, -212 and
-213 aircraft, all serial numbers, which have CFM International CFM56-5A or CFM56-5B series engines installed | Power Plant – Forward Engine Mount Bolts – Inspection / Replacement / Retorque | AIRBUS All Operator Telex (AOT) A320-71A1042 Revision 01; and Goodrich All Operator Letter (AOL) CFM56-074 Revision 1; or later approved revisions of these documents |
026-07 PTZ | FAA 2007-04-24 | 03.04.2007 | See AD compliance for details | This AD applies to Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440)
airplanes, certificated in any category; serial numbers (S/Ns) 7003 through 7067 inclusive and S/Ns 7069 through 7947 inclusive | To detect and correct missing or fractured attachment bolts, which could lead to the loss of an engine exhaust nozzle during flight and consequent structural damage to the airplane and hazard to people or property on the ground | Canadian airworthiness directive CF-2006-19, dated July 28, 2006;
Bombardier Service Bulletin 601R-78-021, dated June 2, 2006;
Bombardier Service Bulletin CF34-NAC-78-024, Revision 4, dated November 10, 2005 |
027-07 PTZ | EASA 2007-0057 | 14.03.2007 | Before April 30th 2008, implement modification Tf12 as per paragraph 2 of the Turbomeca Mandatory Service Bulletin no. 319 72 4012 | TURBOMECA ARRIUS 2F turboshaft engine (installed on EC120B helicopter) | Engine - Gas Generator Front Bearing- Modification | TURBOMECA Mandatory Service Bulletin N° 319 72 4012 update N°1 or any approved subsequent issue |
028-07 PTZ | CF-2007-02
This AD is superseded by CF-2007-02R1 (PTZ 106-07) | Upon receipt | Within the next 16 hours flight time, but no later than 1 May 2007, unless already accomplished | Bell Helicopter Textron Canada (BHTC) Model 206 A and B series helicopters with Transmission Pylon Support Spindle Part Number (P/N) 206-031-554 (Spindle) serial numbers installed- certain S/N
See AD for details | Transmission Pylon Support Spindle | none |
029-07 PTZ | FAA 2007-05-11
This AD supersedes
AD 98-13-24 and AD 2006-22-06 | 20.03.2007 | See AD compliance for details | This AD applies to Bombardier Model CL-600-2B16 (CL-604) airplanes, S/N 5301 through 5665 inclusive; and Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, S/N 7003 through 7990 inclusive and 8000 through 8066 inclusive; certificated in any category | Trim problems including uncommanded trim, trim in the opposite direction to that selected, loss of trim position indication and, in one case, potential loss of trim disconnect capability | Bombardier Service Bulletin S.B. 601R-27-053, Rev B, Feb 21, 1997.
Bombardier Alert Service Bulletin A604-27-029, Sept 28, 2006 ; or Bombardier Service Bulletin 601R-27-147, Sept 28, 2006
and
CF-2006-20R1, CF-2006-21R1 |
030-07 PTZ | CF-2007-01 | 05.03.2007 | Within the next 50 hours air time after the effective date of this directive, See AD compliance for details | Bell Helicopter Textron Canada (BHTC), Models 206A, 206B, 206L, 206L-1, 206L-3 and 206L-4 | Upper Left Hand Tailboom Attachment | For 206A/B see ASB 206-06-110
For 206L, L-1, L-3, L-4
see ASB 206L-06-140 |
031-07 PTZ | EASA EMERGENCY AD 2007-0060-E | 09.03.2007 | At the next maintenance event, or within the next 25 hours of engine
operation, but not later than 01 July 2007, whichever occurs first after the effective date of this directive; See AD compliance for details | BRP-Rotax GmbH & Co. KG; Bombardier-Rotax GmbH & Co. KG;
Bombardier-Rotax GmbH;
Rotax 912 A series
Rotax 912 F series Rotax 912 S series | Engine Fuel and Control - Fuel Pump - Replacement | BRP Rotax Alert Service Bulletin ASB-912-053, dated 20 February 2007, or later approved revision |
032-07 PTZ | FAA 2007-05-10 | 11.04.2007 | See AD compliance for details | Cessna Aircraft Company 172R, 172S, 182S, 182T, T182T, 206H, T206H; certain S/N- see AD applicability for details | To prevent the crew seat back cylinder lock assembly from bending, cracking, or failing | Cessna Single
Engine Service Bulletin
SB04-25-01, Rev 4,
Cessna Single
Engine Service Bulletin SB04-25-02, Rev 1 or Rev 2 |
033-07 PTZ | FAA 2007-05-16 This AD supersedes emergency AD 2007-04-51 (015-07 PTZ) | 12.03.2007 | Within 20 engine
flight hours after the effective date of this AD, unless the actions have already been done;
See AD compliance for details | This AD applies to General Electric Aircraft Engines (GE) CF34-3A1/-3B/-3B1 turbofan
engines that have fan disks with S/Ns listed in Table 1 of this AD
These engines are installed on, but not limited to, Bombardier, Inc. CL-600-2B16 (CL-601-3R Variant), CL-600-2B16 (CL-604 Variant), and CL-600-2B19 (Regional Jet Series 100 and 440) model airplanes | To prevent an uncontained fan disk failure and airplane damage | GE Alert Service Bulletin (ASB) No. CF34-AL S/B 72-A0232
GE ASB No. CF34-BJ S/B 72-A0213
And FAA AD 2006-05-04 (see 015-06 PTZ) |
034-07 PTZ | FAA 2007-05-13 | 12.04.2007 | Within 36 months after the effective date of this AD, See AD compliance for details | Airbus Model A319, A320, and A321 airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category see AD applicability for details | To prevent failure of the attachment points of the YZ-latches, which could result in unrestrained cargo causing damage to the fire protection system, hydraulic system, electrical wiring, or other equipment located in the forward and aft cargo compartments | Airbus Service
Bulletin A320-25-1294, Revision 02, dated September 5, 2006
and EASA 2006-0184 |
035-07 PTZ | FAA 2007-05-15 This AD supersedes AD 2005-20-04 (086-05 PTZ) | 16.04.2007 | See AD compliance for details | This AD applies to Teledyne Continental Motors (TCM) GTSIO-520 series reciprocating engines. These engines are installed on, but not limited to, Twin Commander (formerly Aero Commander) model 685, Cessna model 404, 411 series, and 421 series, British Aerospace, Aircraft Group, Scottish Division model B.206 series 2 and Aeronautica Macchi model AM-3 airplanes | To prevent failure of the starter adapter assembly and or crankshaft gear, resulting in failure of the engine and possible forced landing | TCM MSB No. MSB94-4G, dated October 31, 2005 |
036-07 PTZ | EASA 2007-0064
This AD is revised by EASA 2007 - 0064R1 (122-07 PTZ) | 27.03.2007 | Unless already accomplished, within the next 20 months after the effective date of this AD, see AD compliance for details | AIRBUS A319, A320 and A321 aircraft, all certified models, all serial
numbers on which zonal tasks ZL-540-02 and ZL-640-02 have already
been performed before the effective date of the AD, and for which it
cannot be confirmed that access panels 540CZ, 540DZ, 640CZ and 640DZ were removed for inspection | Wing - Dry Bay Skin - Inspection | AIRBUS Service Bulletin A320-57-1121 |
037-07 PTZ | EASA 2007-0065 | 28.03.2007 | See AD compliance for details | AIRBUS A318, A319, A320 and A321 aircraft, all models, all serial numbers; see AD applicability for details | Landing gear – Normal extension and retraction – Inspection of the selector valves 40GA and 41GA | AIRBUS Service Bulletin A320-32-1290 original issue or any later approved revisions |
038-07 PTZ | FAA 2007-06-15 | 23.04.2007 | See AD compliance for details | Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS350C, AS350D, and AS350D1; see AD applicability for details | Prevent in-flight failure of the drive belt or drive shaft, loss of hydraulic power to the flight control system, and subsequent loss of control of helicopter | Eurocopter Service Bulletin No. 63.00.08, dated May 27, 2002, and No. 29.00.04, Revision 1, date Jan 27, 2004 |
039-07 PTZ | FAA 2007-06-02
This AD supersedes AD 2006-07-09 | 19.04.2007 | See AD compliance for details | Airbus Model A318, A319, A320, and A321 airplanes, certificated in any category | Detect and correct
failure of the THSA's primary load path, which could result in latent (undetected) loading and
eventual failure of the trimmable horizontal
stabilizer actuator-
THSA's secondary load path and consequent uncontrolled movement of the horizontal stabilizer and loss of control of the airplane | EASA 2006-0223
(056-06 PTZ) |
040-07 PTZ | FAA 2007-06-05 | 30.03.2007 | See AD compliance for details | This AD applies to Airbus Model A318-111 and -112; A319-111, -112, -113, -114, and -115;
A320-111, -211, -212, and -214; and A321-111, -112, -211, -212, and -213 airplanes; certificated in any category; all serial numbers, which have CFM International CFM56-5A or CFM56-5B series engines installed | Application of the incorrect torque to the forward engine mount bolts during maintenance could result in failure of the forward engine mount and possible separation of the engine from the airplane and damage to the wing or loss of control of the airplane. This AD requires actions that are intended to address the unsafe condition | EASA 2007-
0036R1 (025-07 PTZ); Airbus All Operators Telex A320-71A1042, Rev 01, dated
Feb 12, 2007; and Goodrich All Operators Letter CFM56-074, Rev 1, dated Feb 1, 2007, for related information. |
041-07 PTZ | EASA 2007-0071 | 30.03.2007 | See AD compliance for details | APEX AIRCRAFT DR 400 series aircraft, all models except the DR 400/500, certain S/N- see for details | Wings - Main spar and fabric covering - Reinforcement / Modification / Inspection | APEX AIRCRAFT Technical Instr. No 1001047 issue H;
APEX AIRCRAFT Technical Instr. No.1000851 issue D and No.1001846 issue F |
042-07 PTZ | CF-2006-23 R1
This AD supersedes CF-2006-23 (111-06 PTZ) issued on 6 Nov 2006 | 19.04.2007 | At the next scheduled main rotor hub disassembly, but no later than 18 May 2007, see AD for details | Bell Helicopter Textron Canada (BHTC). Models 206 A and 206 B helicopters, up to S/N 3216 (inclusive), having main rotor latch bolts, part numbers 206-010-169-001/-003 and 206-011-122-003 | Main Rotor Latch Bolts - Removal from Service | Alert Service Bulletin ASB 206-06-109 dated 25 July 2006, or later revisions |
043-07 PTZ | EASA 2005-0023R3
This AD supersedes
EASA 2005-0023R2 (PTZ 093-05 R2) | 01.11.2005 | See AD compliance for details | All Lycoming Piston Engines (Formerly Textron Lycoming) | Engine - Exhaust Valve and Guide – Inspection | Lycoming SB No. 388C dated 22 Nov 2004;
Lycoming SI 1485A dated July 2, 2003; or later approved revisions |
044-07 PTZ | EASA 2006-0286R1 | 25.09.2006 | See AD compliance for details | INTERTECHNIQUE,
Zodiac Aircraft Systems
Oxygen Reserve Cylinders
Oxygen Reserve Cylinders having Part Number (P/N) GLF(XXX)-(X), GLD(XXX)-(X), PC2300 and SLF300, which are known to be installed on, but
not limited to Airbus A300 series aircraft; Dassault Aviation (AMD-BA), 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 lim.helicopters | Oxygen - Oxygen Reserve Cylinders – Removal/Emptying | INTERTECHNIQUE Service Bulletin GLD/GLF-35-150 ; and
EUROCOPTER AS 350 Alert Service Bulletin No. 05.00.54, EUROCOPTER SA 315 Alert Service Bulletin No. 05.42 |
045-07 PTZ | CF-2007-03 | 12.04.2007 | Within the next 100 hours air time but no later than 9 May 2007, See AD compliance for details | Bell Helicopter Textron Canada (BHTC), Models: 206L series and 407 | Horizontal Stabilizer (Horizontal stabilizers P/N 206-023-119-167 and 407-023-801-109) - Manufacturing Flaws | for 206L series see
ASB 206L-06 141
for 407 see ASB 407-06-72 |
046-07 PTZ | FAA 2007-04-19R1 | 07.05.2007 | See AD compliance for details | This AD applies to Superior Air Parts, Inc. (SAP), cylinder assemblies, manufactured
between April 2005 and November 2005, certain part numbers (P/Ns) (See AD for details), installed in Teledyne
Continental Motors (TCM) 470, 520, and 550 series reciprocating engines. These P/N cylinder assemblies may be installed in the TCM engine models listed in the Table 1 of this AD.
Also can be installed in Lycoming Engines (LE) 320, 360, and 540 series reciprocating engines and Avco Lycoming (AL)540 series reciprocating engines. These P/N cylinder assemblies may be installed in the LE and AL engine models listed in the Table 3. This engines can be installed in diferent aircraft models- see AD for details | To prevent cylinder separation that can lead to engine failure, a possible engine compartment fire, and damage to the airplane | Superior Air Parts, Inc. Mandatory Service Bulletin B06-01, Rev. E, dated January 24, 2007 |
047-07 PTZ | EASA 2007-0089 | 18.04.2007 | Within the next 16 hours flight time, but not later than 01 May 2007, whichever occurs first after the effective date of this AD | AB 206 A and AB 206 B helicopters, all serial numbers, that have the certain Transmission Pylon Support Spindle Part Number (P/N) 206- 031-554 (Spindle) serial numbers installed- see AD | Main Rotor Drive – Transmission Pylon Support Spindle – Identification/Replacement | See CF-2007-02 |
048-07 PTZ | FAA 2007-08-01 | 14.05.2007 | At the next engine or hot section module shop visit, but before accumulating an additional 6,000 cycles-in-service after the effective date of the AD, unless already done, also see AD compliance for details | General Electric Company (GE) CT7-5A2/-5A3/-7A/-7A1/-9B/-9B1/-9B2/-9C/-9C3/-9D/-9D2 turboprop engines with stage 2 turbine aft cooling plates, part number (P/N) 6064T07P01, 6064T07P02, 6064T07P05, or 6068T36P01 installed. These engines are installed on, but not limited to, Construcciones Aeronauticas, SA CN-235 series and SAAB Aircraft AB SF340 series airplanes | Prevent separation of the stage 2 turbine aft cooling plate, resulting in uncontained engine failure and damage to the airplane | General Electric Alert Service Bulletin No. CT7-TP S/B 72-A0464, Revision 04, dated December 12, 2005 |
049-07 PTZ | FAA 2007-07-07
This Ad is revised by FAA 2007-07-07 (PTZ 109-07) | 23.04.2007 | See AD compliance for details | This AD applies to General Electric Company (GE) CF34-1A, -3A, -3A1, -3A2, -3B, and -3B1 turbofan engines, with certain fan disks part numbers (P/Ns) installed. See AD. These engines are installed on, but not limited to, Bombardier Canadair airplane models CL-600-2A12, -2B16, and -2B19 | Prevent an uncontained fan disk failure and airplane damage | CF34-AL S/B 72-A0231
CF34-AL S/B 72-A0233
CF34-BJ S/B 72-A0212 Emergency AD FAA 2007-04-51 and FAA 2007-05-16 also pertain to the subject of this AD |
050-07 PTZ | EASA Emergency AD 2007-0100-E | 16.04.2007 | Within 7 days after the effective date of this AD,
see AD compliance for details | DG-Flugzeugbau GmbH
Manufacturer(s):
Elan Tovarna
Elan Flight Ltd
Elan Line d.o.o.
AMS-Flight d.o.o.
Glaser-Dirks Flugzeugbau GmbH
Applicable for:
DG Flugzeugbau GmbH
DG-300 , DG-300 ELAN
DG-300 CLUB ELAN
DG-300 ELAN ACRO DG-300 CLUB ELAN ACRO | Flight Envelope – Operating Limitations – Modification | DG Flugzeugbau Technical Note No. 359/24
DG-300 and DG-300 ELAN AFM:FM300TN359-24
DG-300 CLUB ELAN AFM:FM300CTN359-24
DG-300 ELAN ACRO AFM:FM300ATN359-24
DG-300 CLUB ELAN ACRO AFM:FM300CATN359-24
List of ADs and SBs applicable for DG-300 series (april 2007) |
051-07 PTZ | FAA 2007-08-03 | 02.05.2007 | See AD compliance for details | Cessna Aircraft Company:
172R, 172S, 182T, T182T, 206H, T206H. Affected S/N are listed in Table 1 of AD | Detect and correct potential loss of fuel flow, which may result in partial or complete loss of engine power and/or uncontrolled engine compartment fire due to fuel leakage forward of the firewall | Cessna Service Bulletin No. SB07-71-01, Revision 1, dated March 16, 2007 |
052-07 PTZ | EASA 2007-0101
This AD supesedes DGAC F-1991-143 R1 | 27.04.2007 | On the next scheduled 100 hour inspection or annual inspection, whichever occurs first, Repeat thereafter inspections at intervals not exceeding 110 flight hours | SOCATA, EADS SOCATA
TB 9, TB 10, TB 20 and TB 21 aircraft, all serial numbers equipped with aluminium alloy made cabin access door hooks | Doors – Cabin Access Door Hooks – Inspection / Replacement | EADS SOCATA Service Bulletin No 10-058 Amdt 2. |
053-07 PTZ | FAA 2007-09-01 | 25.04.2007 | See AD compliance for details | Cessna Aircraft Company
Models 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, and 182R airplanes See AD applicability for details | Detect and correct interference between the ground power electrical cable, the
fuel strainer cable, and the fuel line between the auxiliary electric fuel pump and the engine-driven fuel pump. This condition could lead to a fire in the engine compartment | Air Plains Services
Corporation Mandatory
Service Bulletin APS-07-01-01, date March 5, 2007 |
054-07 PTZ | EASA Emergency AD 2007-0060R1-E | 24.04.2007 | At the next maintenance event, or within the next 25 hours of engine
operation, but not later than 01 July 2007, whichever occurs first after the effective date of this AD, see AD compliance for details | All versions of the engine type Rotax 912 A, 912 F and 912 S all serial
numbers if Fuel pump part no. 892230, 892232, 892540 (standard
version) or part no. 892235, 892236, 892545 (version including flexible
fuel line), are installed.
These engines are known to be installed on, but not limited to, the
following aircraft types:
Skyfox CA-25, CA-25N; Diamond (formerly HOAC) HK-36R Super
Dimona, DV 20 Katana; Aeromot AMT-200 Super Ximango; Diamond DA20-A1 Katana; Evektor-Aerotechnik EV-97 Eurostar; Issoire APM-20 Lionceau; EIS (Fournier) RF-9; Scheibe SF 36R, SF 25C; Technoflug TFK-2 Carat; WD D4 BK Fascination; III Sky Arrow 650 TC, 650 TCN and 650 TCNS; ABS RF-9 motor glider (Fournier design) | Engine Fuel and Control - Fuel Pump - Replacement | BRP Rotax Service Bulletin SB-912-053, dated 13 April 2007, or later approved revision |
055-07 PTZ | EASA Emergency AD 2007- 0110-E | 25.04.2007 | Before further flight after the effective date of this AD, see AD compliance for details | MORAVAN AVIATION s.r.o. (formerly MORAVAN n.p, MORAVAN a.s,
MORAVAN AEROPLANES a.s)
MORAVAN Z 42, Z 42M, Z 42MU, Z 142 and Z 142C aircraft, all S/N and MORAVAN Z 242L aircraft S/N 0490, 0541 and from S/N 0651 to 0659 inclusive | Airworthiness Limitations- Permissible Aerobatic manoeuvres in Utility category - Modification | MORAVAN mandatory Service Bulletins Z 42/54a; Z 142/53a; Z 142C/30a;
and Z 242L/49a, all at original issue or later approved revision.
FAA 2007-11-19 |
056-07 PTZ | EASA Emergency AD 2007-0135-E | 16.05.2007 | Within the next 25 flight hours or 50 flight cycles, or during the next annual inspection, but not later than 31 December 2007, whichever occurs first after the effective date of AD | Grob Aerospace GmbH [and any predecessor company]
G102 "CLUB ASTIR III"
G102 "CLUB ASTIR IIIb"
G102 STANDARD ASTIR III
Affected S/N are listed in AD applicability section. | Flight Controls – Flight Control System Welded Components – Inspection / Replacement | Grob Aerospace Service Bulletin No. MSB 306-35 dated 27 April 2007 |
057-07 PTZ | EASA Emergency AD 2007-0138-E
This AD supersedes
EASA AD 2006-0235-E (064-06 PTZ) | 18.05.2007 | See AD compliance for details | EUROCOPTER – (formerly EUROCOPTER-FRANCE, AEROSPATIALE)
EUROCOPTER helicopters models:
- AS 350 B, BA, BB, B1, B2, B3 and D - AS 355 E, F, F1, F2 and N | Tail Rotor - Tail rotor blades skin- Inspection / Repair | EUROCOPTER AS 350 Alert Service Bulletin No. 05.00.40 Revision 2
EUROCOPTER AS 355 Alert Service Bulletin No. 05.00.38 Revision 2 |
058-07 PTZ | EASA Emergency AD 2007- 0139-E | 18.05.2007 | See AD compliance for details | EUROCOPTER (Formerly EUROCOPTER-FRANCE – AEROSPATIALE)
EUROCOPTER AS350 B, BA, BB, B1, B2, B3 and D
and
EUROCOPTER AS355 E, F, F1, F2 and N helicopters See AD applicability for details. | Fuselage - Center cross-member under the cabin floor -Inspection / Modification | EUROCOPTER AS 350 ASB No. 53.00.37 initial issue. EUROCOPTER AS 355 ASB No. 53.00.23 initial issue |
059-07 PTZ | FAA 2007-10-15 | 21.06.2007 | Unless already done, within the next 90 days after the effective date of this AD, see AD compliance for details | Cessna Aircraft Company
Models 208 and 208B, all serial numbers, that are certificated in any category | To assure that the pilot has enough information and the necessary equipment to prevent loss of control of the airplane while in-flight during icing conditions | None |
060-07 PTZ | EASA Emergency AD 2007- 0141-E | 23.05.2007 | Before further flight, verify the Part Number (P/N) and Serial Number (S/N) of the main rotor and tail rotor servo-controls, see AD compliance for details | EUROCOPTER – (formerly EUROCOPTER-FRANCE, AEROSPATIALE)
EUROCOPTER helicopters models:
- AS 350 B, BA, BB, B1, B2, B3 and D
- AS 355 E, F, F1, F2 and N See AD applicability for details | Rotor Flight Controls - Main & Tail Rotors Servo-Controls - Inspection / Replacement | EUROCOPTER AS 350 Alert Service Bulletin No. 01.00.58 Rev.1 EUROCOPTER AS 355 Alert Service Bulletin No. 01.00.53 Rev. 1 or any subsequent approved revision |
061-07 PTZ | FAA 2007-11-06 | 26.07.2007 | As soon as
practicable after the effective date of this AD but no later than July 31, 2007, unless the actions have already been done, see AD compliance for details | Turbomeca Arrius 2F turboshaft engines with fuel control units (FCUs) not incorporating modification Tf 55. These engines are installed on, but not limited to, Eurocopter EC120B helicopters | Prevent an uncommanded engine in-flight shutdown on a single-engine helicopter, resulting in a forced autorotation landing or an accident | EASA AD 2006-0237
and
Turbomeca Mandatory Service Bulletin No. 319 73 4055, Update No. 1, dated March 17,
2006 |
062-07 PTZ | FAA 2006-24-08 correction | 19.12.2006 | see AD compliance for details | Applies to Pratt & Whitney Canada (P&WC) PW535A turbofan engines that have
fuel manifold, part number (P/N) 3052627-01, installed. These engines are installed on, but not limited to Cessna Airplane Co. model 560 Citation Ultra Encore airplanes | PW535A fuel manifold leakage that could result in engine fire, in-flight shutdown or damage to the airframe | Transport Canada AD CF-2006-22,
and P&WC Alert Service Bulletin PW500-72-A30314 |
063-07 PTZ | FAA 2007-11-01 | 27.06.2007 | Within 100 hours time-in-service, unless accomplished previously; see AD compliance for details | Robinson Helicopter Company Model R44 helicopters, through serial number (S/N) 1576, and Model R44 II helicopters, through S/N 11107, with a seat belt buckle assembly (buckle assembly) part number C628-4, revision M or prior, installed, certificated in any category | Prevent cracking in the buckle assembly stainless support strap and failure of a seat belt | Robinson Helicopter Company Service Bulletin SB-56, dated March 29, 2006 |
064-07 PTZ | FAA 2007-11-11 | 29.06.2007 | See AD compliance for details | AIRBUS
Model A318, A319, A320, and A321 airplanes, certificated in any category | Detect and
correct cracking in an MLG sliding tube, which could result in failure of the sliding tube, loss of one axle, and consequent reduced controllability of the airplane | Airbus All Operators Telex (AOT) A320-32A1273, Rev.01;
Airbus
Service Bulletin A320-32A1273, Rev. 02;
Messier-Dowty Service Bulletin 201-32-43;
Messier-Dowty Service Bulletin 200-32-286, Re.1,
and F-2005-115 |
065-07 PTZ | EASA 2007- 0155 | 12.06.2007 | Corrective actions have to be performed on aircrafts with affected engines installed until December 31, 2007; See AD compliance for details | BRP-Rotax GmbH & Co. KG; Bombardier-Rotax GmbH & Co. KG;
Bombardier-Rotax GmbH;
Rotax 912 A series
Rotax 912 F series
Rotax 912 S series
Rotax 914 F series These engines are known to be installed on different aircraft types- see AD appicability for details | Engine Fuel and Control – Coolant Specification - Modification | BRP Rotax Service Bulletin SB-912-043 R2
and
SB-914-029 R2 |
066-07 PTZ | EASA 2007-0156
This AD supersedes and cancels EASA AD 2005-0021 | 14.06.2007 | See AD compliance for details | Honeywell International, Inc.
See AD Applicability for Communication Units and Mode S Transponder Units and P/N
The referenced equipment is known to be installed on, but not limited to the
following aeroplanes:
BAE Systems Jetstream 4100 series;
Bombardier BD-700-1A10 and BD-700-1A11;
Cessna Model 525, 550, 560 and 650 series;
Dassault Model Falcon 900EX and Falcon 2000EX series;
EMBRAER Model EMB-135 and -145 series;
Learjet Model 45;
Lockheed Model 382G series; Raytheon Model Hawker 800, Hawker 800XP, and Hawker 1000 series | Communication – Comm Units & Transponders – Modification / Replacement | Honeywell Technical Newsletter A23-1146-004;
Honeywell Alert Service Bulletin (ASB) A21-3851-002;
Honeywell ASB A24-3851-005;
Honeywell ASB 7510700-23-A0047 Rev.1;
Honeywell ASB 7510700-23-A0048;
Honeywell ASB 7517400-23-A0017;
Honeywell ASB 7517400-23-A6015 Rev.1; Honeywell ASB 7517400-23-A6016 |
067-07 PTZ | FAA 2007-11-17 | 06.06.2007 | See AD compliance for details | Cessna Aircraft Company: Cessna Model 500, 501, 550, 551, S550, 560, 560XL, and 750 airplanes | Ensure that the fire extinguishing bottles are activated in the event of an engine or auxiliary power
unit (APU) fire, and that flammable fluids are not supplied during a fire, which could result in an unextinguished fire in the nacelle or APU | SB500-26-02
SB500-26-02
SB550-26-05
SB560-26-01
SB560XL-26-02 1
SB750-26-05 SBS550-26-02 |
068-07 PTZ | CF-2006-17R1
This AD supersedes CF-2006-17 (050-06 PTZ) | 20.06.2007 | Within twelve (12) months from the effective date of this directive, unless already accomplished | Bombardier Inc. Model CL-600-2B19, serial number 7003 thru 7990 and 8000 thru 8070 | Short-circuit failures of Tyco Hartman AC contactors – 1K4XD and K4XA - located in the avionics bay | Bombardier service bulletin (SB) 601R-24-123, Revision B, dated 16 February 2007 |
069-07 PTZ | FAA 2007-08-07 | 18.05.2007 | Upon accumulating 1,500 hours time-in-service (TIS) or within the next 50 hours TIS after May 18, 2007 (the effective date of this AD), whichever occurs later, See AD compliance for details | Piper Aircraft Models PA-25, PA-25-235, and PA-25-260, all serial numbers up to LA-260-06008, certificated in any category | REAR AND FORWARD SUPPORTS OF BOTH HORIZONTAL STABILIZER MODIFICATION
Severe corrosion and cracks in both supports. The probable cause for those failures is the accumulation of steam or application products vapors | MCAI Dirección Nacional de Aeronavegabilidad AD No. RA 2006-06-01, Rev. 1 LAVIA S.A., Amendment No. 39/03-041, dated November 17, 2006; and Latinoamericana de Aviación S.A. Service Bulletin No. 25/53/03, dated May 10, 2006 |
070-07 PTZ | EASA Emergency AD 2007 – 0160-E | 11.06.2007 | Before the next cargo hook operations and however within and not
later than August 31, 2007; successively before each single operation of the cargo hook; See AD compliance for details | Agusta S.p.a.
Agusta helicopters A109E, A109LUH, A109S, A119 equipped with the single or double Cargo Hook installations with the certain P/N | Equipment & Furnishings - Cargo Hook P/N 528-010-01 / Lever P/N 232-028-00 - Inspection | Agusta - Alert Service Bulletins 109EP-78; 109L-006; 109S-12; 119-21 original issue or later approved revisions. |
071-07 PTZ | EASA 2007-0163 This AD Supersedes DGAC AD (CN) 2002-514 R1 | 25.06.2007 | See AD compliance for details | AIRBUS A318, A319, A320 and A321 aircraft, all certified models, all serial numbers | Flight Controls – Elevator Backlash – Inspection | AIRBUS AMM task 27.34.00.200.001 issued on February 1997; AIRBUS SB A320-27-1132 Revision 01; and SB A320-27-1114 Revision 05 |
072-07 PTZ | EASA 2007-0161 | 25.06.2007 | See AD compliance for details | AIRBUS A318, A319, A320 and A321 aircraft, all certified models, all serial
numbers up to MSN 2850 inclusive, except MSN’s 0115, 0184, 0782, 1151, 1190, 2650, 2675, 2706, 2801 and 2837 | Fuselage - Centre Fuselage - Main Landing Gear Door Keel Beam Hinge and Actuator Fitting - Inspection | AIRBUS Service Bulletin A320-53-1195
and AIRBUS Service Bulletin A320-53-1196 |
073-07 PTZ | EASA 2007-0065R1 | 28.03.2007 | See AD compliance for details | AIRBUS A318, A319, A320 and A321 aircraft, all models, all serial numbers | Landing gear – Normal extension and retraction – Inspection of the selector valves 40GA and 41GA | AIRBUS Service Bulletin A320-32-1290 |
074-07 PTZ | EASA 2006-0153R2 | 26.06.2007 | See AD compliance for details | A318, A319, A320 and A321 aircraft | Auxiliary Power Unit (APU) - Starter Motor and Air Intake System Inspection/Cleaning | AIRBUS Service Bulletin A320-49-1068; A320-49-1070; A320-49-1075; A320-49-1077 |
075-07 PTZ | FAA 2007-12-06 | 16.06.2007 | See AD compliance for details | Hawker Beechcraft Corporation-Type Certificate formerly held by Raytheon Aircraft Corp. and
Beech C90A; B200; B200C; B300; B300C | Detect and correct improperly assembled or damaged flight controls | Raytheon Aircraft Company Mandatory Service Bulletin Number SB 27-3761 or Mandatory Service Bulletin Number SB 27-3761 |
49-2002 R1 PTZ
| 49-2002 R1 PTZ | 14.06.2007 | veljavnost takoj | Velja za jadralna letala tipa B4-PC 11 za vse tri modele: B4-PC 11, B4-PC 11A ter B4-PC 11AF, proizvajalca PILATUS Flugzeugwerke AG, 6370 Stans, Schweiz, ki so vpisani v Register letal Republike Slovenije | Preklic omejitev in zahtev PTZ 49-2002 z dne 09. 05. 2002 (prepoved kakršnegakoli akrobatskega letenja ter zmanjšanje maksimalna dovoljene hitrosti letenja (VNE) na 200 km/h) | Referenčni dokument: Poročilo in ugotovitve komisije za preiskovanje vzrokov letalskih nesreč |
076-07 PTZ | EASA 2007-0165 | 28.06.2007 | At the next periodical inspection, but not later than 31 December 2007; See AD compliance for details | EUROCOPTER DEUTSCHLAND GmbH EC135 and EC635 helicopters | Electrical Power – DC Power Supply Lines – Modification | Eurocopter EC135 ASB No. EC135-24A-013 at Rev. 01 |
077-07 PTZ | EASA 2007-0156 | 14.06.2007 | See AD compliance for details | Honeywell International, Inc.
Comm Units and Mode S Transponders
RCZ-833J part numbers (P/Ns) 7510700-763 and -863; RCZ-833K P/Ns
7510700-765 and -875; RCZ-851J P/N 7510700-813; RCZ-851K P/N
7510700-815; and RCZ-854J P/Ns 7510700-725 and -825
Communication Units;
and XS-856A P/Ns 7517400-865 and -885; XS-856B P/Ns 7517400-866 and -886; and XS-857A P/Ns 7517400-876 and -896 Mode S TransponderUnits | Communication – Comm Units & Transponders – Modification / Replacement | Honeywell Technical Newsletter A23-1146-004; ASB A24-3851-002 [7510700-23-A6046]; Honeywell ASB A21-3851-005 [7510700-23-A0047];
Honeywell ASB 7510700-23-A0047 Rev.1;Honeywell ASB 7510700-23-A0048;
Honeywell ASB 7517400-23-A0017; Honeywell ASB 7517400-23-A6015 Rev.1;Honeywell ASB 7517400-23-A6016 |
078-07 PTZ | EASA 2007-0168 | 29.06.2007 | Within 72 months from the effective date of this AD; see AD compliance for details | Saab AB, Saab Aerosystems
(Saab Aircraft AB)
SAAB SF340A and SAAB 340B | Fuel Tank Safety Wing – Fuel Access Door – Improved Sealing | SAAB Service Bulletin SB-340-57-031 |
079-07 PTZ | EASA 2007-0169 | 29.06.2007 | Within 72 months from the effective date of this AD; see AD compliance for details | Saab AB, Saab Aerosystems
(Saab Aircraft AB)
SAAB SF340A and SAAB 340B | Fuel Tank Safety
Fuel - Indicating - Wire separation of Fuel Quantity Indication System (FQIS) Signal Conditioner 28 VDC supply - Fuselage | SAAB Service Bulletin SB-340-28-025 |
080-07 PTZ | EASA 2007-0170 | 29.06.2007 | Within 72 months from the effective date of this AD; see AD compliance for details | Saab AB, Saab Aerosystems
(Saab Aircraft AB)
SAAB SF340A and SAAB 340B | Fuel Tank Safety
Fuel - Indicating - Wire separation of Fuel Quantity Indication System (FQIS) Wiring - Wing | SAAB Service Bulletin SB-340-28-024 |
081-07 PTZ | EASA 2007 - 0178 | 06.07.2007 | Within 600 flight hours or 750 flight cycles or 100 days after the effective date of this AD, whichever occurs first; see AD compliance for details | AIRBUS A318, A319, A320 and A321 all certified models, all manufactured serial numbers (MSN) up to MSN 2860 | Flight controls – Trimmable Horizontal Stabilizer Actuator - Inspection | AIRBUS Service Bulletin A320-27A1179 |
082-07 PTZ | EASA Emergency AD 2007-0176-E | 26.06.2007 | Before next flight after the effective date of this directive and thereafter at intervals not to exceed 12 months; see AD compliance for details | DG Flugzeugbau GmbH; Glaser-Dirks Flugzeugbau GmbH; ELAN Flight Ltd
(Slovenia); ELAN Line d.o.o. (Slovenia); AMS-Flight d.o.o. (Slovenia)
Sailplanes:
DG-500/20 ELAN, all serial numbers;
DG-500/22 ELAN, all serial numbers;
DG-500 ELAN ORION, all serial numbers; and
DG-500 ELAN TRAINER, all serial numbers.
Powered Sailplanes:
DG-500M, all serial numbers; and DG-500MB, all serial numbers | Flight Controls – Bellcrank Bearing Attachment Bolt – Inspection / Re-Torque / Replacement [Life Limitation] | DG Flugzeugbau GmbH Technical Note (TN) 348/19 and 843/26 (same
document), dated 19 June 2007, including the related working instructions number 1 and number 2 |
083-07 PTZ | EASA 2006 – 0251 R2 This AD revises AD 2006-0251R1 | 01.09.2006 | see AD compliance for details | EUROCOPTER (formerly EUROCOPTER FRANCE, AEROSPATIALE)
Helicopters:
- AS 355 E, F, F1, F2, N
- AS 350 B, BA, BB, B1, B2, B3 and D, fitted with sliding door(s) before embodiment of MOD 073298 and/orMOD 073308 | Doors – Sliding Door Rear Roller Support Shaft and Rear Fitting | EUROCOPTER AS 350 Alert Service Bulletins No. 05.00.47 and 52.00.30; and AS 355 ASB No. 05.00.45 and 52.00.23 |
084-07 PTZ | EASA 2007-0182
This AD is revised and replaced by
EASA 2007-0182 R1 (PTZ 035-07)
| 16.07.2007 | Not later than 31 October 2007, see AD compliance for details | Thielert Aircraft Engines TAE125-01 and TAE125-02-99 engines, all serial numbers, installed in Diamond Aircraft Industries DA42 aircraft | Power Plant – Engine Installation – Inspection | TAE Installation Manual IM-02-01 Issue 4, Revision 1, Chapter 13
and TAE Installation Manual IM-02-02 Issue 1, Revision 3, Chapter 13 |
085-07 PTZ | EASA 2007-0183
This AD is revised and replaced by EASA 2007-0183 R1(PTZ 110-07) | 16.07.2007 | Within the next 100 Flight Hours, whichever occurs first after the effective date of this AD, but not later than 31 October 2007, see AD compliance for details | Diamond Aircraft Industries GmbH
DA 42 airplanes, serial numbers 42.004 through 42.269; and 42.AC001 through 42.AC109 (Canadian production line) | Engine Controls – Engine Control Unit Back-up Batteries - Installation | Diamond Aircraft Industries (DAI) MSB-42-042;
DAI WI-MSB-42-042;
DAI SI 42-040;
DAI AFM TR-MÄM-42-240 and
AMM-TR-MÄM-42-240;
TAE Installation Manual IM-02-01 Issue 4, Revision 1, Chapter 13 and TAE Installation Manual IM-02-02 Issue 1, Revision 3, Chapter 13 |
086-07 PTZ | EASA 2007-0171 | 01.08.2007 | See AD compliance for details | APEX AIRCRAFT
All HR100/200, HR100/200B, DR300 and DR400 equipped with “Avions Robin” nose landing gear | Nose Landing Gear – Support plate of oleo outer cylinder – Inspection/Repair |
