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 | Apex SB No. 101 revision 5 dated 22 May 2007 |
087-07 PTZ | EASA Emergency AD 2007-0192-E | 17.07.2007 | Unless already accomplished, within the next 20 flight hours after the
effective date of this EAD and not later than Sept 30, 2007 See AD compliance for details | Agusta S.p.a.
A109E, A109S, A109LUH | Power Plant - Lower Semichannel assemblies p/n 109-0641-
10-213 OR 109-0642-01-171 of the Forward Firewall – Inspection / Modification | Agusta - Alert Bollettino Tecnico (BT) 109EP-79, 109S-15 and 109L-007 |
088-07 PTZ | EASA Emergency AD 2007-0194-E | 01.08.2007 | Within the next 25 flight hours or 50 flights, or during the next scheduled
100 hours (or annual) inspection, whichever occurs first after the effective
date of this AD See AD compliance for details | GROB AEROSPACE GmbH
TWIN ASTIR and G103 Gliders, all variants; and G103C TWIN III SL Powered Sailplanes | Fuselage, Wing & Stabilisers Structure – Inspection/Repair | Grob Aerospace Service Bulletin No. MSB 315-74/1, MSB 869-25/1 |
089-07 PTZ | EASA Emergency AD 2007-0200-E | 01.08.2007 | See AD compliance for details | Moravan Aviation s.r.o
Zlin Z 42, Z 42M, Z 42MU, Z 142, Z 142C and Z 242L aircraft, all serial numbers without the wing reinforcement modification | Introduction of new Airworthiness- and Operating Limitations | MORAVAN Mandatory Service Bulletins:
Z42/55a for Z42, Z42M and Z42MU aircraft;
Z142/54a for Z142 aircraft;
Z142C/31a for Z142C aircraft; and Z242L/51a for Z242L aircraft |
090-07 PTZ | CF-2007-10 | 31.07.2007 | See AD compliance for details | Bombardier Inc. Model CL-600-2B19, serial number 7003 thru 7990 and 8000 and subsequent | Bombardier Aerospace CL-600- 2B19 Flaps Failure | Bombardier Service Bulletin (SB) 601R-27-150
and
FAA 2007-17-07 |
091-07 PTZ | FAA 2007-14-03 | 16.08.2007 | Within the next 25 hours time-in-service (TIS) after August 16, 2007 or within 60 days after August 16, 2007 whichever occurs first | Cirrus Design Corporation
Model SR20 airplanes, serial numbers (SN) 1005 through 1798, and Model SR22 airplanes, SN 0002 through 2437 | Correct pick-up collar support fasteners of the CAPS- Cirrus
Airplane Parachute System | Cirrus Alert Service Bulletin No. SB A2X-95-10 R2
or Cirrus Alert Service Bulletin No. SB A2X-95-10 R1 |
092-07 PTZ | FAA 2007-16-01 | 15.08.2007 | Before further flight; See AD compliance for details | Enstrom Helicopter Corp.
Model F-28, F-28A, F-28C, F-28C-2, F-28C-2R, F-28F, F-28F-R, 280, 280C, 280F, 280FX, TH-28, 480, and 480B helicopters | Prevent failure of a retention pin, separation of a main rotor blade from the helicopter, and subsequent loss of control of the helicopter | Enstrom Service Directive Bulletin No. T-029 and Enstrom Service Directive Bulletin 0102 |
093-07 PTZ | EASA 2007- 0210 | 20.08.2007 | Within the next 50 flight hours after the effective date of this AD; See AD compliance for details | Centre Est Aéronautique, Avions Pierre Robin, Constructions Aéronautiques de
Bourgogne, APEX Industries
All DR220 series and DR221series aircraft models;
All DR200 and all DR250 series aircraft models;
All DR253 series aircraft models;
All R3000 series aircraft models;
All ATL series aircraft models;
All R1180T and R1180TD aircraft;
All DR300 series aircraft models, DR315, DR340, DR360 and DR380;
All DR400 series aircraft models, except DR400/500, DR400/RP and DR400/200R | Fuel – Fuel Pump Electrical Grounding – Modification | APEX SB No 060903 |
094-07 PTZ | EASA 2007-0211 | 21.08.2007 | See AD compliance for details | EUROCOPTER
EC 120 B helicopters, all serial numbers that are fitted with tail rotor drive shafts Part Number (P/N) C651A3102051 and C651A3102052. | Tail Rotor Drive - Rear Drive Shaft Friction Ring - Inspection / Replacement | EUROCOPTER EC120 Alert Service Bulletin No. 05A006 |
095-07 PTZ | EASA 2007-0212 | 21.08.2007 | At the next scheduled “A” Type maintenance inspection or within the next 3 months after the effective date of this AD, whichever occurs first; See AD compliance for details | Aircraft Industries a.s.; Strojírny první pětiletky n.p.; LET n.p.; and LET a.s.
L13 and L13A BLANÍK sailplanes, all serial numbers | Flight Controls – Control Sticks and Bridge – Inspection/Replacement | Aircraft Industries a.s Mandatory Bulletin No. L13/105a
and Documentation Bulletins No.L13/009d, L13/010d and L13/011d |
096-07 PTZ | EASA 2007-0213 | 21.08.2007 | See AD compliance for details | AIRBUS A318, A319, A320 and A321 aircraft, all certified models, all serial numbers (MSN) except aircraft that have received AIRBUS modification 32025 in production or AIRBUS Service Bulletin (SB) A320-57-1118 in service | Wings – Outer Wing Main Landing Gear Support Rib 5 Fitting – Inspection / Modification | AIRBUS Service Bulletin (SB) A320-57-1118 at original issue; and SB A320-57- 1138 Revision 01 |
097-07 PTZ | EASA 2007-0214 | 21.08.2007 | Before 31March 2009; See AD compliance for details | AIRBUS models A318-111, A318-112, A319-111, A319-112, A319-113, A319-114, A319-115, A319-131, A319-132, A319-133, A320-111, A320-211, A320-212, A320-214, A320-215, A320-216, A320-231, A320-232, A320-233, A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-231 and A321-232 | Equipment/Furnishings – 103VU Box – Hinge Pin Stopper – Modification | AIRBUS Service Bulletin (SB) A320 25-1535 |
098-07 PTZ | FAA 2007-16-10 | 23.08.2007 | See AD compliance for details | Teledyne Continental Motors (TCM) models TSIO-520-BE, TSIO-550-A, TSIO-550-B,
TSIO-550-C, TSIO-550-E, and TSIO-550-G
These engines are installed on, but not limited to, Adam Aircraft A500,
Columbia Aircraft Manufacturing LC41-550FG, Mooney Airplane Company M20TN (Acclaim), and Piper Aircraft Incorporated PA-46-310P (Malibu) airplanes | Prevent the turbine rotor from separating from the shaft of
the turbocharger due to a machining defect in the turbocharger compressor | Teledyne Continental Aircraft Engine Mandatory Service Bulletin (MSB) MSB07-4 |
099-07 PTZ | EASA 2007-0217 | 23.08.2007 | See AD compliance for details | AIRBUS A318, A319, A320 and A321 aircraft, all certified models and all serial numbers equipped with at least one NORTHROP-GRUMMAN (previously LITTON) air data/inertial reference unit (ADIRU) | Navigation – NORTHROP-GRUMMAN (previously LITTON) ADIRU – Replacement | See AD reference publications |
100-07 PTZ | EASA 2007–0218 This AD supersedes EASA 2006-0222 (059-06 PTZ) | 07.09.2007 | See AD compliance for details | AIRBUS A318, A319, A320 and A321 aircraft, all certified models, all serial
numbers (MSN), except aircraft that have received AIRBUS modification 37508 in production or AIRBUS Service Bulletin (SB) A320-28-1159 in service | Fuel – Main Fuel Pump System / Fuel Pumps – Airworthiness Limitations / Inspection / Replacement | AIRBUS SB A320-28-1159
and AIRBUS AFM TR 4.03.00/28 issue 02 |
101-07 PTZ | EASA 2007-0221 | 27.08.2007 | See AD compliance for details | CFM International SA (CFM) CFM56-5B series engines (see AD Aplicability for models) These engines are known to be installed on, but not limited to, Airbus A318, A319, A320 and A321 series aircraft | Time Limits – Low Pressure Turbine Rear Frame – Life Reduction | CFM56-5B Engine Shop Manual chapter 05, revision 47 and CFM56-5B Service Bulletin S/B 72-0620 |
102-07 PTZ | EASA 2007- 0018R1 This AD revises EASA AD 2007-0018 | 29.01.2007 | See AD compliance for details | TURBOMECA, S.A.
ARRIEL 1 turboshaft engines
(see AD Aplicability for models)
These engines are known to be installed on, but not limited to:
Eurocopter AS 350 B, AS 350 BA, AS 350 B1 and AS 350 B2 helicopters; and Sikorsky S-76C helicopters | Engine - Gas Generator 2nd Stage Turbine - Inspection/Replacement | Turbomeca, S.A. Alert Service Bulletins:
A292 72 0807
A292 72 0809
A292 72 0810 and Turbomeca Service Bulletin 292 72 0347 |
103-07 PTZ | EASA 2007-0231 | 06.09.2007 | See AD compliance for details | Agusta S.p.a.
A109E and A119 helicopters | Hydraulic Power – Hydraulic Pipes P/N’s 109-0761-64-103 and 109- 0761-65-103 – Inspection / Replacement | Agusta Bollettino Tecnico 109EP-73 and 119-22 at original issue or later approved revisions |
104-07 PTZ | EASA 2007-0232 | 06.09.2007 | Within the next 50 flight hours after the effective date of this directive, but not later than 31 October 2007, whichever occurs first; See AD compliance for details | Thielert Aircraft Engines
TAE125-01 engines all serial numbers (s/n), up to and including s/n 02-01-1018
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 series aircraft. | Engine Oil System - Catchtank (Sump) Filter Adaptor - Installation | Thielert Service Bulletin TM TAE 125-0016, Initial Issue or Revision 1 or later approved revisions |
105-07 PTZ | CF-2005-10R3 This AD supersedes CF-2005-10R2 | 17.09.2007 | Within the next 100 hours air time, but no later than 30 November 2007, See AD compliance for details | Bell Helicopter Textron Canada Models 206A and 206B | Fuel Distribution System | Alert Service Bulletin (ASB) 206-05-103, Revision A, dated 12 July 2006 |
106-07 PTZ | CF-2007-02R1
This AD supersedes CF-2007-02 (PTZ 028-07) | 14.09.2007 | Within the next 16 hours flight time, but no later than 15 October 2007, unless already accomplished | Bell Helicopter Textron Canada (BHTC) Models 206 A and B series helicopters that have the certain Transmission Pylon Support Spindle Part Number installed- see AD for details | Transmission Pylon Support Spindle | none |
107-07 PTZ | CF-2007-13 | 17.09.2007 | See AD compliance for details | Bell Helicopter Textron Canada (BHTC) Model 206B series helicopters including those converted from model 206A, serial numbers up to 4366 and certain 206L helicopters-see AD | Power Turbine RPM Steady State Operation Avoidance | Alert Service Bulletin (ASB) 206-07-115 or 206L-07-146, as applicable, dated 21 May 2007, or later revisions |
108-07 PTZ | CF-2007-16 | 17.09.2007 | As soon as possible, but not later than 25 hours air time or 30 days from the effective date of this directive, See AD compliance for details | Bell Helicopter Textron Canada (BHTC) Model 206 series helicopters S/N up to 4618 and Model 206L series helicopters S/N up to 52340 | Disc Assemblies –Tail rotor driveshaft (Thomas Couplings) | 206 series: ASB-206-07-114 dated 28 March 2007 206L series: ASB-206L-07-145 dated 28 March 2007 |
109-07 PTZ | FAA 2007-07-07 R1
This AD revises FAA 2007-07-07 (PTZ 049-07)
| 12.09.2007 | 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- 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 | GE Alert Service Bulletin No.
CF34-AL S/B 72-A0231,
CF34-AL S/B 72-A0233 and CF34-BJ S/B 72-A0212 |
110-07 PTZ | EASA 2007-0183 R1
This AD is revised and replaced with EASA 2007-0183 R2 (PTZ 137-07) | 16.07.2007 | Within the next 100 Flight Hours, but not later than 31 October 2007, whichever occurs first after the effective date of this AD, See AD compliance for details | Diamond Aircraft Industries GmbH
DA 42 airplanes, serial numbers 42.004, 42.006, 42.009 through 42.156, 42.158
through 42.176, 42.178 through 42.190, 42.192 through 42.233, 42.235 through 42.246, 42.248 through 42.254, 42.256 through 42.261, 42.263 through 42.269; and 42.AC001 through 42.AC109 | Engine Controls – Engine Control Unit Back-up Batteries - Installation | Diamond Aircraft Industries (DAI) Mandatory Service Bulletin MSB-42-042;
DAI WI-MSB-42-042;
DAI Service Information SI 42-040;
DAI AFM TR-MÄM-42-240 and AMM-TR-MÄM-42-240; TAE Installation Manual IM-02-01 Issue 4, Rev 1 and TAE Installation Manual IM-02-02 Issue 1, Rev 3 |
111-07 PTZ | FAA 2007-11-02 | 02.10.2007 | See AD compliance for details | Enstrom Helicopter Company: Model F-28A, F-28C, and F-28F helicopters, excluding serial number (S/N) 816 and subsequent; Model 280, 280C, 280F, and 280FX helicopters, excluding S/N 2100 and subsequent; and Model TH-28, 480, and 480B helicopters, excluding S/N 5058 and subsequent, certificated in any category | Detect corrosion and prevent failure of a main rotor push-pull control rod (push-pull rod), and
subsequent loss of control of the helicopter | Enstrom
Helicopter Corporation Service Directive Bulletin No. 0096, No. T-019, Enstrom Helicopter Corporation Service Information Letter No. T-019, No. 0156 |
112-07 PTZ | EASA 2007- 0236 This AD supersedes EASA AD 2006-0251R2 | 14.09.2007 | See AD compliance for details | EUROCOPTER AS 350 and AS 355 helicopters | Doors – Sliding Door Rear Roller Support Shaft and Rear Fitting Inspection/Replacement | EUROCOPTER AS350 ASB No. 05.00.47 initial issue and ASB No. 52.00.30 rev 1 or EUROCOPTER AS355 ASB No. 05.00.45 initial issues and ASB No. 52.00.23 rev 1 |
113-07 PTZ | FAA 2007-17-18 | 02.10.2007 | See AD compliance for details | McDonnell Douglas Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15,
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, 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), and DC-9-87 (MD-87) airplanes, and Model MD-88 airplanes | Prevent an electrical short of the static port heater from sparking and igniting the insulation
blanket adjacent to the static port heater, which could result in smoke and/or fire in the cabin area | Boeing
Service Bulletin DC9-30-097, Revision 2, dated May 27, 2005 |
114-07 PTZ | EASA 2007-0248 | 21.09.2007 | Within 72 months after the effective date of this directive, see AD compliance for details | Saab AB, Saab Aerosystems (formerly Saab Aircraft AB) Model SF340A and 340B aircraft, all serial numbers | Fuel System - Fuel Tank Conduits Wiring Protection – Modification [Fuel Tank Safety] | SAAB Service Bulletin SB-340-28-026 original issue or later approved revisions |
115-07 PTZ | CF-2007-17 | 24.09.2007 | Within 5000 hours air time after the effective date of this directive, unless already accomplished | Bombardier Inc. Model CL-600-2B19 aircraft, serial numbers 7003 through 7067 and 7069 through 7924 | Fuel System Safety - Lack of Sealant on Collector Fuel Tank Bolts and Transfer Ejector Pumps | Bombardier Service Bulletin (SB) 601R-28-051 rev.A; SB 601R-28-060 rev. A |
116-07 PTZ | CF-2007-18 | 24.09.2007 | Within 5000 hours air time after the effective date of this directive, see AD compliance for details | Bombardier Inc. Model CL-600-2B19 aircraft, serial numbers 7003 through 7067 and 7069 through 7797 | Fuel System Safety -Insufficient Electrical Bonding Between Fuel Boost Pump Canister and the Pressure Pick-Up Line | Bombardier Service Bulletin (SB) 601R-28-057 |
117-07 PTZ | Emergency AD CF-2007-21 | Upon receipt | Before further flight unless already accomplished | Bell Helicopter Textron Canada (BHTC) all helicopter Models:
206 series, 222 series, 230, 407, 427 and 430 | Tail Rotor Blades | 206 series ASB 206-07-116 see AD |
118-07 PTZ | FAA 2007-19-53 | Upon receipt | Before further flight, replace any affected blade with an airworthy blade with a serial number not listed in the applicability section of this AD, see AD compliance for details | Bell Helicopter Textron, Inc. (BHTI) Model 204B,
205A, 205A-1, 205B, 210, 212, 412, 412EP, and 412CF helicopters, certificated in any category,
with certain part-numbered and serial-numbered tail rotor blades installed | Tail rotor blade tip weights slung from the blades during flight | See AD for list of Alert Service Bulletins |
119-07 PTZ | EASA 2007-0257 | 02.10.2007 | Within the next 16 hours flight time, but not later than 15 October 2007, whichever occurs first after the effective date of this directive, see AD compliance for details | Agusta S.p.A
AB 206 A and AB 206 B helicopters, all S/N, that have certain Transmission Pylon Support Spindle Part Number (P/N) 206-031-554 (Spindle) S/N installed, repaired by H-S Tools & Parts Inc. | Main Rotor Drive – Transmission Pylon Support Spindle – Identification/Replacement | None |
120-07 PTZ | EASA 2007 - 0256 | 03.10.2007 | within 30 days after the effective date of this AD; see AD compliance for details | Pacific Scientific Company
Restraint Systems: 2000029, 2000067, 2000115
These p/n’s are known to be installed on, but not limited to, EUROCOPTER a/c models AS 350, AS 355, EC120, EC 130, EC 155 | Equipment and Furnishing - Seat Restraint System Plastic Rotary Buckle Handle - Inspection/Replacement | SB Notice of release
Pacific Scientific SB 25-1111432
Recall Application Form |
121-07 PTZ | ENAC EAD 2007-324 | 04.09.2007 | See AD compliance for details | Agusta S.p.A. AB206A and AB206B series Helicopters, all serial numbers | Tail Rotor Driveshaft Disk Assemblies | Agusta Alert Mandatory SB 206-243 |
122-07 PTZ | EASA 2007 - 0064R1
This AD revises EASA 2007-0064 (036-07 PTZ) | 05.10.2007 | Unless already accomplished, before November 27 2008; See AD compliance for details | AIRBUS
A319, A320 and A321 aircraft | Wing - Dry Bay Skin – Inspection | AIRBUS SB A320-57-1121 |
123-07 PTZ | EASA 2007 - 0249 | 08.10.2007 | Unless accomplished previously, within the next 600 Flight Hours after the effective date of this AD; See AD compliance for details | AIRBUS
A318, A319, A320 and A321 aircraft | Fire Protection – Cargo Compartment Fire Extinguishing –
Inspection of Bottle Wiring Connection – Inspection and Continuity Check | AIRBUS Service Bulletin A320-26A1068 |
124-07 PTZ | EASA 2007- 0261 | 16.10.2007 | At the next scheduled maintenance inspection or
within the next 3 months after the effective date of this AD, whichever occurs first; see AD compliance for details | Aircraft Industries a.s, LET k.p., LET a.s. and LETECKÉ ZÁVODY a.s.
L 23 SUPER-BLANÍK sailplanes, all serial numbers | Flight Controls – Control sticks and bridge –
Inspection/Replacement | Aircraft Industries a.s Mandatory Bulletin No. L23/050a Rev. 2
Aircraft Industries a.s Documentation Bulletin No.L23/020d original issue |
125-07 PTZ | FAA 2007-21-05 | 15.11.2007 | See AD compliance for details | International Aero Engines (IAE) model V2500-A1, V2522-A5, V2524-
A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, V2533-A5, V2525-D5, and V2528-D5 (see AD for details); These engines are installed on, but not limited to, Airbus A319, A320, A321, and Boeing MD-90 airplanes | Prevent uncontained failure of the HPT stage 2 air seal | IAE Service Bulletin (SB) V2500-ENG-72-0500;
IAE SB V2500-
ENG-72-0501; IAE SB V2500-ENG-72-0502 |
126-07 PTZ | EASA Emergency AD 2007-0274-E | 23.10.2007 | See AD compliance for details | Schweizer Aircraft Corporation 269D helicopters | Fuselage – Aft Fuselage Assembly and Horizontal Stabiliser Attachment – Inspection / Repair / Modification | Schweizer SB DB-018.2 |
127-07 PTZ | CF-2007-23 | 01.11.2007 | Within 5000 hours air time after the effective date of this AD | Bombardier Inc. Model CL-600-2B19 aircraft, serial numbers 7003 through 7067, and 7069 through 7981 | Fuel System Safety -Insufficient Electrical Bonding Between Fuel Tubes and Insufficient Lightning Current Capability of Fuel Tube Couplings | Bombardier Service Bulletin (SB) 601R-28-054, Revision A, dated 7 August 2006, or later revisions |
128-07 PTZ | CF-2007-24 | 08.11.2007 | See AD compliance for details | Pratt & Whitney Canada
PW 200 Compressor Turbine | Disk Inspection and Retaining Nut Replacement | P&WC Alert Service bulletin PW200-72-A28280 |
129-07 PTZ | FAA 2007-22-02 | 30.11.2007 | Within 100 hours time-in-service, unless accomplished previously; See AD compliance for details | Bell Helicopter Textron, Inc. Model 205A, 205A-1, 205B, 212, 412, 412CF, and 412EP helicopters | To prevent loss of the forward tip weight retention block (tip block) or aft tip closure (tip closure), loss of the blade, and subsequent loss of control of the helicopter | Bell Helicopter Textron, Inc. Alert Service Bulletins 205-00-80, 205B-00-34, 212-00-111, 412-00-106, and 412CF-00-13 |
130-07 PTZ | EASA 2007 - 0276 | 09.11.2007 | See AD compliance for details | AIRBUS
A318, A319, A320 and A321 aircraft | Equipment / Furnishing – 80VU Rack Attachments – Inspection / Repair / Replacement | AIRBUS SB A320-25A1555,
AIRBUS SB A320-25-1557 |
131-07 PTZ | AGÊNCIA NACIONAL DE AVIAÇÃO CIVIL – BRAZIL
ANAC 2007-08-01 | 27.09.2007 | Before 31 Dec. 2008; Within the next 180 days after the effective date of this AD; See AD compliance for details | EMBRAER
EMB-135BJ aircraft model | The inclusion of new maintenance tasks in the Critical Design Configuration Control Limitations (CDCCL) and in the Fuel System Limitations (FSL), necessary to preclude ignition sources in the fuel system | none |
132-07 PTZ | CF-2007-25 | 29.10.2007 | See AD compliance for details | Pratt & Whitney Canada
PW305A and PW305B Engine | PW305A and PW305B Engine High Pressure Compressor (HPC) Drum Rotor Cracks | See AD Corrective Actions for details |
133-07 PTZ | AIRWORTHINESS DIRECTIVE CANCELLATION
EASA 2006- 0279-CN (PTZ 085-06) is withdrawn and considered superseded by DGAC
France AD F-2007-004R1
(PTZ 134-07) | 08.11.2007 | See AD for details | PARACHUTE SHOP
Parachute Harnesses and Reserve Canopies | Equipment/Furnishings – Parachute Equipment – Removal from Service | DGAC France AD F-2007-004R1 |
134-07 PTZ | DGAC France F-2007-004 R1 | Upon receipt from August 01, 2007 | See AD for details | PARACHUTE SHOP Parachute Reserve Canopies and Parachute Harnesses certain types manufactured between January 1, 2001 and March 6, 2007 | Equipment/Furnishings - Parachute - Reactivation of reserve canopies and harnesses | none |
135-07 PTZ | EASA 2007-0182 R1
This AD revises and replaces EASA 2007-0182 (PTZ 084-07) | 16 July 2007 | Not later than 30 November 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 |
136-07 PTZ | AIRWORTHINESS DIRECTIVE CANCELLATION EASA F-2005-169 | See AD for details | See AD for details | PARACHUTE SHOP VEGA 120 type reserve canopy | Equipment/Furnishings - Strengthening of assemblies | none |
137-07 PTZ | EASA 2007-0183 R2 This AD revises and replaces EASA AD 2007-0182 R1 (PTZ 110-07) | 16 July 2007 | Within the next 200 Flight Hours, but not later than 30 November 2007, whichever occurs first; See AD compliance for details | Diamond Aircraft Industries DA 42 certain S/N | Engine Controls – Engine Control Unit Back-up Batteries - Installation | See AD ref. publications for details |
138-07 PTZ | EASA 2007 - 0286 | 28.11.2007 | Unless already accomplished, no later than 27 May 2011; see AD compliance for details | AIRBUS aircraft A318, A319, A320, A321, all certified models, all S/N, fitted with classical standby instruments installed by AIRBUS modification 20011 or 21999 in production or by AIRBUS Service Bulletin (SB) A320-34-1280 in service | Lights – Instrument & Panel Integral Lighting – Emergency Lighting for Stand-By Instruments - Modification | SB A320-33-1057
SB A320-34-1261
SB A320-34-1280 SB A320-34-1372 |
139-07 PTZ | FAA 2007-23-13 | 30.11.2007 | Within 14 days after the effective date of this AD | Cessna Aircraft Company Cessna Model 560 airplanes, certificated in any category, S/N 560-0001 through -0538 inclusive | Prevent an inadvertent stall due to the inadequate stall warning margin
provided by an improperly adjusted stall warning system, which could result in loss of controllability of the airplane | See AD for reference publications |
140-07 PTZ | CF-2007-27 | 23.11.2007 | Within 7 days after the effective date of this directive; see AD compliance for details | Diamond Aircraft Industries Inc. model DA20-C1 aircraft powered by either Teledyne Continental Motors (TCM) IO-240-B13B or IO-240-B17B model engines | In-Flight Engine Shutdown | DA20-C1 AFM DOC No. DA202-C1 Revision 22 dated 2 November 2007 |
141-07 PTZ | EASA 2007- 0289 | 03.12.2007 | See AD for details | EUROCOPTER helicopters models AS 350 B, AS 350 B1, AS 350 D, AS 355 E, AS 355 F, AS 355 F1 and AS 355 F2, all pre MOD 071995 | Rotor flight controls - Collective lever recess -Modification | EUROCOPTER AS 350 Alert Service Bulletin No. 67.00.16 rev. 2 and AS 355 Alert Service Bulletin No. 67.00.12 rev. 2 |
142-07 PTZ | FAA 2007-23-16 | 19.12.2007 | Within the next 30 days after December 19,
2007; Within the next 10 hours time-in-service after December 19, 2007; whichever occurs first; see AD compliance for details | Cessna Aircraft Company
Model 525B, serial numbers 0001 through 0013 airplanes, that are certificated in any category | Correct an incorrect wiring installation and to provide short-circuit protection for all wiring
from the aircraft power distribution system. This condition could result in burned wiring and loss of various aircraft electrical systems | Cessna Citation Service Bulletin SB525B-24-02, Revision 1, dated October 4, 2007 |
143-07 PTZ | CF-2007-29 | 10.12.2007 | See AD Corrective Actions for details | Bombardier Inc. Model CL-600-2B19 aircraft, all serial numbers | Fuel System Safety - Introduction of Maintenance Tasks | See AD Corrective Actions for details |
144-07 PTZ | EASA Emergency AD 2007-0295-E | 04.12.2007 | Within the next 5 flight hours but not later than 31 December 2007, whichever
occurs first after the effective date of this AD; see AD compliance for details | Agusta S.p.a.
A109E, A109S, A109LUH and A119 helicopters, all serial numbers | Fuselage – Pilot & Co-pilot Door Housing Slots – Inspection / Modification | Agusta Alert Bollettino Tecnico (BT) 109EP-83 for A109E, BT 109S-18 for A109S, BT 109L-010 for A109LUH and BT 119-25 for A119 |
145-07 PTZ | FAA 2007-24-05 | 02.01.2008 | See AD compliance for details | Rolls-Royce Corporation (RRC) (formerly Allison Engine Company,
Inc.) AE 3007A and AE 3007C series turbofan engines. These engines are installed on, but not limited to, Cessna Aircraft Company 750 series, and Empresa Brasileira de Aeronautica S. A. (EMBRAER) EMB-135 and EMB-145 series airplanes | Prevent an in-flight engine shutdown due to loss of engine oil from the starter shaft seal and possible loss of the airplane | See Table 1 for SB list |
146-07 PTZ | CF-2007-28 | 10.12.2007 | 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 Maintenance Tasks | See AD for details |
147-07 PTZ | EASA Emergency AD 2007-0301-E | 14.12.2007 | Within the next 5 flight hours or 5 days, whichever occurs first after the effective date of this AD; See AD compliance for details | Eurocopter Deutschland GmbH
EC135 and EC635 series helicopters, all models, serial numbers 0005 through 0444, except those equipped with autopilot | Rotors Flight Control – Tail Rotor Control Rod and Ball Pivot – Inspection/Replacement | EUROCOPTER EC 135 Alert Service Bulletin No. EC135-67A-017 |
148-07 PTZ | EASA Emergency AD 2007-0295R1-E | 04.12.2007 | Within the next 5 flight hours but not later than 31 December 2007, whichever occurs first after the effective date of this AD; See AD compliance for details | Agusta S.p.a.
A109E, A109S, A109LUH and A119 helicopters, all serial numbers | Fuselage – Pilot & Co-pilot Door Housing Slots – Inspection / Modification | Agusta Alert BT (Alert Service Bulletins) 109EP-83, 109S-18, 109L-010 and 119- 25, all dated 29 November 2007 |
149-07 PTZ | FAA 2007-25-16 | 14.01.2008 | See AD compliance for details | McDonnell Douglas Model DC-9-81 (MD-81) and DC-9-82 (MD-82)
airplanes; certificated in any category; as identified in Boeing Alert Service Bulletin MD80-53A298, dated August 1, 2006 | Prevent cracking of the fuselage skin at
the upper corners of the forward passenger doorjamb, which could lead to loss of overall structural integrity of the airplane | Boeing Alert Service Bulletin MD80- 53A298; see AD for details |
150-07 PTZ | CF-2007-27R1 Supersedes AD CF-2007-27 | 31.12.2007 | See AD Corrective Actions for details | Diamond Aircraft Industries Inc. model DA20-C1 aircraft serialnumbers C0001 to C0473 powered by either Teledyne Continental Motors (TCM) IO-240-B13B or IO-240-B17B model engines | In-Flight Engine Shutdown | Mandatory Service Bulletin (MSB) DAC1-73-05 Revision 1
Aircraft Fight Manual DA202-C1 Rev. 23 |
151-07 PTZ | EASA 2007-0313 | 04.01.2008 | Within the next 5 Flight Hours (FH) or 5 days, whichever occurs first after 14. Dec. 2007; Thereafter, at intervals not to exceed 50 FH; See AD compliance for details | Eurocopter Deutschland GmbH
EC135 and EC635 series helicopters, all models, serial numbers 0005 through 0444, except those equipped with autopilot | Rotors Flight Control – Tail Rotor Control Rod and Ball Pivot – Inspection/Replacement | Eurocopter Deutschland (ECD) EC 135 ASB No. EC135-67A-017 Rev.1 |
152-07 PTZ | EASA 2007- 0311 | 04.01.2008 | Within the next 110 Flight Hours but no later than 3 months, after the effective date of this AD; See AD compliance for details | EUROCOPTER
EC 120 B helicopters up to serial number (s/n) 1523 inclusive and all EC130 B4 helicopters PRE Mod 073380, fitted with SICMA Type 159 energy-absorbing seats | Equipment/Furnishings – Energy absorbing seat and Metallisation braid – Modification | EUROCOPTER EC120 Alert Service Bulletin No. 25A023 original issue
EUROCOPTER EC130 Alert Service Bulletin No. 25A025 original issue |
153-07 PTZ | FAA 2007-26-09 | 30.01.2008 | See AD compliance for details | Hartzell Propeller Inc.
models ( )HC-( )( )Y( )-( )( )( ) compact series constant speed or feathering propellers with Hartzell manufactured ''Y'' shank aluminum blades;
These propellers are used on, but not limited to, the following airplanes:
Aermacchi S.pA. (formerly Siai-Marchetti), Aero, Commander, Aerostar,
Beech, Bellanca , Cessna
Embraer, Maule, Mooney Pilatus Britten Norman, or Britten, Piper, Pitts, Rockwell; see AD for list | Prevent failure of the propeller blade from fatigue cracks in the aluminum blade shank radius, which can result in damage to the airplane and loss of airplane control | See Table 1 – Incorporation by Reference |
154-07 PTZ | ANAC 2007-11-04R1
This AD cancels and supersedes the AD No. 2007-11-04 original issue – Amdt 39-1223, dated 21 Dec. 2007 | 21.12.2007 | Within the next 2500 flight hours or 24 months after the effective date of this AD, whichever occurs first; See AD compliance for details | Embraer EMB-145 and EMB-135 aircraft models of serial numbers (S/N) 145002 thru 145362, 145364 thru 145590, and 145592 thru 14500987 | Occurrence of smoke in the flight deck originated from Pitot 1/2 and
TAT 1/2 current sensor relays and yours respective sockets, caused by poor electrical contacts between those relays and their sockets | Embraer Service Bulletins Nos. 145-30-0052 original issue or 145LEG-30-0019 original issue |
155-07 PTZ | F-2007-025
This AD replaces the AD F-2004-015 which is cancelled by its Rev. 1 | Upon receipt from February 04, 2004 (effective date of AD F-2004-015) | See AD for details | Any reserve canopy manufactured by PARACHUTES DE FRANCE (PdF) between January 1st, 1987 and February 28, 1989 with serial numbers from 87 01 001 up to 89 02 xxx | Equipment/Furnishings - Temporary grounding of reserve canopies | Service Bulletin PARACHUTES DE FRANCE No. 2/2003 |
156-07 PTZ | F-2007-026
This AD replaces EASA AD 2006-0160-E which is cancelled by EASA | June 08, 2006 (effective date of AD EASA 2006-0160-E) | Before the next use, as from the effective date of this AD, unless already accomplished; See AD for details | PARACHUTES DE FRANCE
TECHNO 240 equipments TECHNO 240-B, P/N R 01-240-B - All serial numbers - Reserve Parachute | Equipment/Furnishings - Reserve parachute - Mandatory packing modifications slider and steering lines replacement | PARACHUTE DE FRANCE Service Bulletin BSV-06-001 |
