Airworthiness Directives
The following are Airworthiness Directives approved or modified in the last 60 days.
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| AD Number | Effective Date | Manufacturer | Description | Recurring |
| 2010-05-51 E | 02/24/2010 | Aerospatiale | To prevent failure of a main rotor hub, excessive vibrations, loss of a main rotor blade, and,contd. | Y |
| 2010-05-14 | 03/24/2010 | Bombardier Inc. | To prevent an early or late activation of the stick shaker or stick pusher, which can lead to loss of control,contd. | N |
| 2010-05-13 C | 04/13/2010 | Boeing Commercial | To prevent rapid decompression of the airplane due to fatigue cracks resulting from scribe lines on pressurized,contd. | N |
| 2010-05-12 | 04/13/2010 | Bombardier Inc. | To prevent a fuel tank explosion caused by a strike on a top wing fuel tank | Y |
| 2010-05-11 | 04/13/2010 | Boeing Commercial | To prevent the malfunction of one or more electrical and electronic units in the main equipment center, which,contd. | N |
| 2010-05-10 | 04/08/2010 | Beech Aircraft Corp. | To detect and correct the installation of an incorrect bus bar, which could result in failure of the pitot,contd. | N |
| 2010-05-09 | 04/07/2010 | Dowty Aerospace | To prevent blade counterweight release, which could result in injury or damage to the airplane | Y |
| 2010-05-07 | 03/12/2010 | Airbus Industrie | To require detailed inspection of the link assembly to identify a possible oversized bearing repair and,contd. | Y |
| 2010-05-06 | 03/12/2010 | Airbus Industrie | To mandate a repetitive inspection program in order to detect any crack by means of two Non-Destructive,contd. | Y |
| 2010-05-05 | 03/12/2010 | BAE Systems (Operations) | To detect and correct fatigue cracking of certain structural elements, which could result in reduced structural,contd. | N |
| 2010-05-04 | 04/01/2010 | McDonnell Douglas Corp. | To detect and correct such cracking, which could sever the frame, increase the loading of adjacent,contd. | Y |
| 2010-05-03 | 04/08/2010 | Boeing Commercial | To detect and correct fatigue cracking at multiple adjacent locations in the subject areas, which could,contd. | Y |
| 2010-05-02 | 04/01/2010 | Pilatus Aircraft Ltd. | To prevent an undesired bank angle, heading splits and/or incorrect heading, which would constitute an unsafe condition | N |
| 2010-05-01 | 03/12/2010 | ATR-GIE Avions de Transp | To identify and remove the L'Hotellier Halon 1211 (BCF) fire extinguishers and replace with serviceable units | N |
| 2010-04-16 | 03/08/2010 | SICLI | To identify and replace fire extinguishers Halon 1211 (BCF) with serviceable units | N |
| 2010-04-15 | 03/15/2010 | Scheibe-Flugzeugbau | To require an inspection of the affected tube rivets and, if necessary, their replacement | N |
| 2010-04-14 | 03/24/2010 | Augustair, Inc | To detect and correct cracks in the vertical stabilizer front spar, which could result in separation of the,contd. | N |
| 2010-04-13 | 03/30/2010 | Airbus Industrie | To require repetitive inspections of the affected seat springs and replacement of missing or broken parts | Y |
| 2010-04-12 | 04/08/2010 | Bombardier, Inc | To prevent structural failure of the airplane due to corrosion | Y |
| 2010-04-11 | 03/30/2010 | Extra Flugzeugproduktions | To mandate instructions for recurring inspections and modification in the area of the tail spring support,contd. | Y |
| 2010-04-10 | 03/10/2010 | Airbus Industrie | To require an inspection program to detect cracks and to replace the MFTF#6 based on findings | Y |
| 2010-04-09 C2 | 03/30/2010 | Airbus Industrie | To require the installation of plugs on the heat shield panels of the Left Hand (LH) and Right Hand (RH) air,contd. | N |
| 2010-04-08 | 03/30/2010 | Embraer | To prevent cracking and deformation of wing spar and rib flanges, which could result in loss of,contd. | N |
| 2010-04-07 | 03/23/2010 | Turbomeca Engine Corp. | To prevent loss of full automatic control of the engine during acceleration up to the One Engine,contd. | N |
| 2010-04-06 | 03/30/2010 | Thielert Aircraft Engines | To prevent engine in-flight shutdown, possibly resulting in reduced control of the aircraft | N |
| 2010-04-05 | 03/10/2010 | McCauley | To prevent propeller separation due to hub fatigue cracking, which can result in loss of control of the,contd. | Y |
| 2010-04-04 | 03/30/2010 | Bombardier, Inc. | To mandate replacement of the existing cages with new cages that have greater damage resistance | N |
| 2010-04-03 | 03/19/2010 | Airbus Industrie | To detect and correct cracks around the wing top skin panel fastener holes at Rib 2 (LH or RH) between stingers 2,contd. | Y |
| 2010-04-02 | 03/19/2010 | Airbus Industrie | To identify and correct the possible failure of the T/R latch and detachment of the T/R from the airplane,contd. | Y |
| 2010-04-01 | 03/19/2010 | Dassault Aviation | To prevent an oxygen leak, which would result in insufficient oxygen flow to passenger oxygen masks,contd. | N |
| 2010-03-09 | 03/11/2010 | Piaggio Aero Ind. | To identify and correct cracks on the upper flange (cap) of several "O" pressure bulkheads on the production line,contd. | N |
| 2010-03-08 | 02/19/2010 | Boeing Commercial | To prevent loss of the strut and engine due to corrosion damage and cracking of both fuse pins on the same strut | Y |
| 2010-03-07 | 03/11/2010 | Embraer | To prevent loss of the MLG trailing arm axle, disconnecting the trailing arm from the main strut,contd. | N |
| 2010-03-06 | 03/11/2010 | Turbomeca Engine Corp. | To prevent a forced autorotation landing or an accident | N |
| 2010-03-05 | 03/11/2010 | Boeing Commercial | To prevent cracking of the upper chords and straps (or angles) of the floor beams, which could lead to,contd. | N |
| 2010-03-04 | 03/11/2010 | Piaggio Aero Ind. | To inspect and detect damaged cables/sleeves, & replacement/ repair as necessary; in addition, this AD,contd. | N |
| 2010-03-03 | 02/19/2010 | Bell Helicopter | To detect an edge void, corrosion, or a crack on a M/R blade and subsequent loss of control of the helicopter | Y |
| 2010-03-02 | 02/11/2010 | Lifesaving Systems Corp. | To prevent the failure of a hook during rescue hoist operations, loss of the rescued passenger, and,contd. | N |
| 2010-03-01 | 02/12/2010 | Aerospatiale | To correct the condition that can lead the failure of the plug & fragments being caught inside the buckle,contd. | N |
| 2010-02-51 E | 01/14/2010 | Agusta | To prevent a crack in a main rotor scissor fitting assembly fixing bolt (fixing bolt), failure of a fixing,contd. | N |
| 2010-02-12 | 03/04/2010 | Fokker Aircraft B.V. | To require the replacement of existing airstair door actuators with improved actuators | N |
| 2010-02-11 | 03/04/2010 | BAE Systems (Operations) | To inspect and correct the degradation of the structural integrity of Frame 29 and the wing-to-fuselage,contd. | Y |
| 2010-02-10 | 03/04/2010 | Airbus Industrie | To require detailed inspections under the bogie stop pad of both MLG bogie beams and, in case,contd. | N |
| 2010-02-09 | 03/02/2010 | Airbus Industrie | To prevent excessive vibration of the elevators, which could result in reduced structural integrity and,contd. | Y |
| 2010-02-08 | 02/03/2010 | Turbomeca Engine Corp. | To prevent a helicopter engine in-flight shutdown resulting in an emergency auto-rotation landing or accident | N |
| 2010-02-07 | 02/12/2010 | Aerospatiale | To prevent failure of a blade and subsequent loss control of the helicopter | Y |
| 2010-02-06 | 02/24/2010 | SICMA | To prevent failure of the central spreaders that could result in injury to an occupant during,contd. | Y |
| 2010-02-04 | 02/18/2010 | Boeing Commercial | To prevent the failure of the valve in the closed position, open position, or partially open position, which,contd. | N |
| 2010-02-03 | 01/29/2010 | Airbus Industrie | To prevent a loss of structural integrity of the forward engine mounts that could lead to the loss,contd. | Y |
| 2010-02-02 | 01/28/2010 | Dassault Aviation | To mandate application of a new abnormal Airplane Flight Manual (AFM) procedure when radio-altimeter 1,contd. | N |
| 2010-02-01 | 02/18/2010 | Turbomeca Engine Corp. | To prevent the rupture of the reduction gear box intermediate pinion, which could result in an,contd. | N |
| 2010-01-12 | 02/18/2010 | Embraer | To modify the electrical wiring in the overhead panel of the cockpit, modifying the air data smart probe 3B,contd. | N |
| 2010-01-11 | 02/18/2010 | Fokker Aircraft B.V. | To inspect & correct blacklash remover of the elevator Booster Control Unit (BCU) | N |
| 2010-01-10 | 02/24/2010 | Boeing Commercial | To detect and correct cracks and fractures of the nacelle strut front spar chord assembly | Y |
| 2010-01-09 | 02/16/2010 | Boeing Commercial | To detect and correct fatigue cracking of the fuselage skin panels at the chem-milled steps, which could,contd. | Y |
| 2010-01-08 | 02/16/2010 | Boeing Commercial | To prevent cracks from propagating from drill starts in the free flange, vertical web, and radius between,contd. | N |
| 2010-01-07 | 01/27/2010 | Airbus Industrie | To require the revision of the ALS of the Instruction for Continued Airworthiness by incorporating new and,contd. | N |
| 2010-01-05 | 02/18/2010 | CFM International | To prevent failure of the LP turbine rear frame from low-cycle-fatigue cracks | Y |
| 2010-01-02 | 02/24/2010 | Boeing Commercial | To detect and correct fatigue cracking in the specified fuselage stringers, which, if left undetected,could,contd. | Y |
| 2010-01-01 | 02/16/2010 | Boeing Commercial | To prevent the loss of structural integrity of the fuselage, which could result in rapid,contd. | Y |
| 2009-26-13 | 02/24/2010 | Airbus Industrie | To require the modification of the movable flap track fairing No. 3, both Left Hand (LH) and Right Hand (RH) side,contd. | N |
| 2009-26-11 | 02/24/2010 | Thrush Aircraft, Inc. | To prevent wing front lower spar cap failure caused by undetected fatigue cracks | Y |
| 2009-23-51 | 02/19/2010 | Sikorsky Aircraft | To prevent loss of an MGB and subsequent loss of control of the helicopter | Y |
| 2009-21-10 R1 | 02/04/2010 | AVOX Systems | To prevent an oxygen cylinder from rupturing, which, depending on the location, could result in,contd. | N |
| 2009-21-10 R1 | 02/04/2010 | BE Aerospace | To prevent an oxygen cylinder from rupturing, which, depending on the location, could result in,contd. | N |
| 2009-19-51 | 02/08/2010 | Agusta | To prevent failure of a tailboom and subsequent loss of control of the helicopter | Y |
| 2009-06-05 R1 | 04/01/2010 | Bombardier, Inc | To prevent anti-ice system air leakage which could adversely affect the anti-ice capability without,contd. | N |
| 2008-10-10 R1 | 01/27/2010 | Boeing Commercial | To prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations,contd. | N |
