AD Number |
Effective Date |
Manufacturer |
Description |
Recurring |
 |
|
|
|
|
2009-14-08 |
08/05/2009 |
General Electric Co. |
To prevent HPCR stages 11-14 spool/shaft fatigue cracks caused by exceeding the life limit, which could,contd. |
N |
2009-14-02 |
08/03/2009 |
Boeing Commercial |
To detect and correct wear damage and cracks of the fuselage skin in the interface area of the vertical,contd. |
Y |
2009-14-01 |
08/03/2009 |
Turbomeca Engine Corp. |
To prevent an uncommanded in-flight shutdown of the engine, which could result in a forced autorotation,contd. |
Y |
2009-13-10 |
06/26/2009 |
British Aerospace |
To identify and replace unserviceable MLG radius rods |
N |
2009-13-09 |
07/14/2009 |
Microturbo Saphir |
To prevent rapid deterioration and physical breakdown of the exhaust thermal insulation, leading to loss of,contd. |
Y |
2009-13-08 |
08/03/2009 |
McDonnell Douglas Corp. |
To detect and correct cracks in the fail-safe structure that may not be able to sustain limit load,contd. |
N |
2009-13-07 |
07/24/2009 |
Airbus Industrie |
To perform a general visual inspection to detect any wrong orientation of the lugs of the fire extinguisher,contd. |
N |
2009-13-06 |
07/24/2009 |
Piper Aircraft Corp. |
To detect and correct damaged, worn, corroded, or non-conforming nose baggage door components, which,contd. |
Y |
2009-13-05 |
07/09/2009 |
Socata Groupe |
To mandate revision of the POH instructing users of the oxygen mask in proper use of the mask |
N |
2009-13-04 |
07/24/2009 |
Dornier-Werke G.M.B.H. |
To prevent loss of the pin that could cause loss of the flight idle stop and lead to inadvertent activation,contd. |
Y |
2009-13-03 |
07/06/2009 |
Boeing Commercial |
To prevent automatic retraction of the leading edge flaps during takeoff, which could result in reduced,contd. |
N |
2009-13-02 |
08/03/2009 |
Fokker Aircraft B.V. |
To prevent inadvertent operation in the prohibited stabilized engine speed range on the ground, which,contd. |
N |
2009-13-01 |
07/01/2009 |
Sikorsky Aircraft |
To prevent failure of a main (MGB) filter bowl assembly mounting titanium stud (titanium stud), which,contd. |
N |
2009-12-51 |
07/15/2009 |
Turbomeca Engine Corp. |
To prevent uncommanded in-flight engine shutdown, possible engine fire, and an emergency autorotation,contd. |
Y |
2009-12-16 |
07/17/2009 |
Dornier-Werke G.M.B.H. |
To require a visual inspection of the inner structure on rudder and elevator for signs of corrosion, de-bonded,contd. |
N |
2009-12-15 |
07/01/2009 |
Grob-Werke Gmbh & Co. |
To mandate inspection of all cable looms in the front of the instrument panel cover, repair as necessary and,contd. |
Y |
2009-12-14 |
07/17/2009 |
Aeromot-Industria |
To correct the unacceptable engine fire risk associated with the use of EVANS NPG+ fluid |
N |
2009-12-13 |
06/26/2009 |
Dehavilland Aircraft |
To mandate an identification check for elevator PCU serial numbers, a daily check for correct operation of,contd. |
Y |
2009-12-12 |
06/29/2009 |
ATR |
To verify the installation of the correct protection sleeves and correct routing of wire bundle in trim control,contd. |
N |
2009-12-11 |
06/29/2009 |
Airbus Industrie |
To require High Frequency Eddy Current (HFEC) inspections and detailed visual inspections on the NLG Actuator,contd. |
N |
2009-12-10 |
07/24/2009 |
BAE Systems (Operations) |
To prevent reduced structural integrity of the airplane |
Y |
2009-12-09 |
07/16/2009 |
ATR |
To mandate a one-time inspection and a routing modification of the electrical wires in the bulkhead area |
N |
2009-12-08 |
07/16/2009 |
Boeing Commercial |
To detect and correct fatigue cracking of the longeron, which can propagate and cause damage to the adjacent,contd. |
N |
2009-12-07 |
07/17/2009 |
Agusta |
To detect and correct cracks in the cargo hook lever P/N 232-028-00 |
Y |
2009-12-06 |
07/16/2009 |
Boeing Commercial |
To ensure that the flightcrew is able to turn off electrical power to IFE systems and other non-essential,contd. |
N |
2009-12-05 |
07/16/2009 |
Boeing Commercial |
To prevent loss of all attitude indications from both the standby indicator and EFIS displays, which could,contd. |
N |
2009-12-04 |
07/16/2009 |
Construcciones |
To detect and correct radial cracking around the top lid of the dynamic port of pitot tubes |
Y |
2009-12-03 |
07/16/2009 |
Boeing Commercial |
To prevent damage of the wiring bundle of the right recirculation fan |
N |
2009-12-02 |
07/24/2009 |
Airbus Industrie |
To prevent misrigging of the ejection jack of the RAT and to ensure removal of any RAT yoke fitting made from,contd. |
N |
2009-12-01 |
06/29/2009 |
Bell Helicopter |
To prevent a main rotor blade spar crack as a result of an incorrectly installed main rotor blade box beam,contd. |
N |
2009-11-13 |
06/17/2009 |
Learjet Corp. |
To detect and correct chafed hydraulic tubes in the left-hand engine & consequent hydraulic tube failure,contd. |
Y |
2009-11-11 |
07/07/2009 |
McDonnell Douglas Corp. |
To prevent possible damage to the fuel level float or pressure switch wires |
N |
2009-11-10 |
06/12/2009 |
MBB-Bolkow |
To detect and correct loose attachment screws in the lower hub-shaft bearing support |
N |
2009-11-09 |
06/12/2009 |
Airbus Industrie |
To require the deactivation of the electrical powered SOGERMA pilot seats 2510112 series and co-pilot seats 2510113,contd. |
N |
2009-11-08 |
06/12/2009 |
Airbus Industrie |
To require a repetitive special detailed inspection [high frequency eddy current to detect cracking] on,contd. |
Y |
2009-11-07 |
06/12/2009 |
BAE Systems (Operations) |
To revise the maintenance program to incorporate Critical Design Configuration Control Limitations to,cont'd |
N |
2009-11-06 |
07/02/2009 |
M7 Aerospace LP |
To detect and correct chafing of electrical wires and components, hydraulic tube assemblies, and bleed,contd. |
Y |
2009-11-05 |
06/01/2009 |
Air Tractor, Inc. |
To detect and correct cracks in the engine mount, which could result in failure of the engine mount |
Y |
2009-11-04 |
06/26/2009 |
Rolls-Royce Corporation |
To prevent separation of the propeller from the airplane, which could result in injury, and damage to the airplane |
N |
2009-11-03 |
06/04/2009 |
Lockheed Aircraft Corp |
To prevent cracking of the barrel nuts in the upper wing joint, engine truss, and rear beam pylon support,contd. |
N |
2009-11-02 |
06/23/2009 |
CFM International |
To prevent cracking of the HPC 4-9 spool, which could result in possible uncontained failure of the spool,contd. |
N |
2009-11-01 |
06/12/2009 |
MBB-Bolkow |
To detect the blades fitted with lead balance weights that could move and cause severe vibrations leading to,contd. |
N |
2009-10-14 |
06/04/2009 |
Hartzell Propeller |
To prevent separation of the propeller blade counterweight slug, which could lead to injury and damage to,contd. |
N |
2009-10-13 |
06/24/2009 |
Saab AB, Saab Aerosystems |
To inspect and correct cracks, deformation, or wear damage of the frame and closing angle on the forward engine cowl door |
N |
2009-10-12 |
06/04/2009 |
Boeing Commercial |
To prevent actuation delays in the inflation systems of the escape slides/rafts, which could result in delayed,contd. |
N |
2009-10-11 |
06/04/2009 |
Airbus Industrie |
To detect fluid ingress and/or inner skin disbond damage on rudders which could result in reduced structural,contd. |
N |
2009-10-10 |
05/29/2009 |
Bombardier, Inc. |
To mandate an interim repetitive check of the OFV manual mode motor and altitude limitation functions,contd. |
Y |
2009-10-09 |
06/17/2009 |
Cessna Aircraft Company |
To prevent the rudder from traveling past the normal travel limit |
N |
2009-10-08 |
06/17/2009 |
Pratt & Whitney |
To remove nonconforming HPT 2nd stage hubs, which could result in an uncontained release of turbine,contd. |
N |
2009-10-07 |
05/28/2009 |
Airbus Industrie |
To require an inspection program to detect cracks and to replace the MFTF#6 based on findings |
Y |
2009-10-06 |
06/17/2009 |
Boeing Commercial |
To detect and correct cracks in upper deck floor beam upper chords, which could become large and cause the,contd. |
Y |
2009-10-05 |
05/28/2009 |
Bombardier, Inc. |
To replace the Inboard Flap Actuators that are non-conforming |
N |
2009-10-04 |
06/17/2009 |
Diamond Aircraft |
To require repetitive inspections of the NLG leg and, in case cracks are found, replacement of the NLG,contd. |
Y |
2009-10-03 |
05/26/2009 |
328 Support Services GmbH |
To prevent structural failure of the dual load path attachment arrangement of the affected trim & spring,contd. |
N |
2009-10-02 |
06/11/2009 |
BAE Systems (Operations) |
To prevent failure of certain structurally significant items, including the main landing gear and the,contd. |
N |
2009-10-01 C2 |
06/09/2009 |
Pratt & Whitney |
To prevent uncontained failure of the 2nd stage High-Pressure Turbine (HPT) air seal assembly, leading to,contd. |
N |
2009-09-08 |
06/11/2009 |
Boeing Commercial |
To detect and correct cracks in the upper lobe doublers |
Y |
2009-09-07 |
06/11/2009 |
Boeing Commercial |
To detect and correct broken retract actuator beams of the MLG, which could result in damage to the beam arm,contd. |
Y |
2009-09-06 |
06/11/2009 |
Boeing Commercial |
To detect and correct fatigue cracking of the backup intercostals and upper sill web of the forward,contd. |
Y |
2009-08-51 |
05/27/2009 |
Rolls-Royce Corporation |
To prevent uncontained failure of the HPT stage 2 wheel and damage to the airplane |
N |
2009-06-22 C2 |
04/28/2009 |
Airbus Industrie |
To require the installation of improved cockpit door latch/striker assemblies |
N |
2009-04-18 C |
06/25/2009 |
Pratt & Whitney |
To prevent failure of the 2nd stage HPT rotor disk, which could result in uncontained engine failure, damage,contd. |
Y |
2009-04-06 C |
04/02/2009 |
Boeing Commercial |
To detect and correct the propagation of fatigue cracks in the vicinity of oil cans on the web of the aft,contd. |
Y |
