AD Number |
Effective Date |
Manufacturer |
Description |
Recurring |
 |
|
|
|
|
2008-18-51 E |
08/21/2008 |
MD Helicopters, Inc |
To prevent loss of yaw control and subsequent loss of control of the helicopter |
N |
2008-17-51 E |
08/14/2008 |
McDonnell Douglas Hel. |
To prevent loss of yaw control and subsequent loss of control of the helicopter |
N |
2008-17-09 |
09/23/2008 |
Socata Groupe |
To prevent a rupture of the alternator and vapour cycle cooling system pulley drive assembly, contd. |
N |
2008-17-08 |
09/23/2008 |
DG Flugzeugbau GmbH |
To mandate the replacement of eight bolts, the four connecting the fork 5M203 to the 5M204 adapter and,contd. |
N |
2008-17-07 |
09/23/2008 |
APEX Aircraft |
To mandate the replacement of the tie rod bolts and spacers |
N |
2008-17-06 |
09/02/2008 |
Dehavilland Aircraft |
To prevent possible loss of both the No. 1 and No. 2 hydraulic systems, resulting in the potential loss,contd. |
N |
2008-17-05 |
09/23/2008 |
Embraer |
To prevent an ignition source inside the fuel tank that could ignite fuel vapor and cause a fuel tank,contd. |
N |
2008-17-04 |
09/23/2008 |
BAE Systems (Operations) |
To prevent internal fuel tank wiring chafing damage, if not corrected, could lead to ignition of fuel, contd. |
N |
2008-17-03 |
09/23/2008 |
Boeing Commercial |
To detect and correct such cracking, which could prevent the left forward entry door from scaling correcly,contd. |
Y |
2008-17-02 |
09/17/2008 |
Airbus Industrie |
To inspect and detect any crack at an early stage in the forward lug of the RH (right-hand) and LH,contd. |
Y |
2008-17-01 |
09/17/2008 |
AvCraft Aerospace GmbH |
To reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel,contd. |
N |
2008-16-20 |
09/17/2008 |
Diamond Aircraft |
To require the replacement of the aileron bellcrank with an improved part and the replacement of any bend,contd. |
N |
2008-16-19 |
09/17/2008 |
Pilatus Aircraft Ltd. |
To a replace self-locking stop nuts P/N 938.07.65.105 from the Tail Landing Gear Assembly, the Fuel,contd. |
N |
2008-16-18 |
09/15/2008 |
Rolls-Royce Limited |
To detect cracks that could cause the HP turbine disc to fail and result in uncontained failure of the engine |
N |
2008-16-17 |
09/02/2008 |
PZL Swidnik S.A. |
To prevent leakage in the pipe between the hydraulic block and the ground hydraulic unit panel |
N |
2008-16-16 |
09/15/2008 |
Bell Helicopter |
To inspect and correct the rigging of the tail rotor pitch change mechanism |
N |
2008-16-15 |
08/07/2008 |
Eclipse Aviation Corp. |
To reduce the likelihood of the throttle position signal exceeding its maximum range, which could cause loss,contd. |
N |
2008-16-14 |
09/17/2008 |
Boeing Commercial |
To prevent reduced structural integrity of the fuselage |
Y |
2008-16-13 |
09/09/2008 |
Boeing Commercial |
To prevent fracture of the elevator tab pushrod ends, which could result in excessive in-flight,contd. |
N |
2008-16-12 |
09/09/2008 |
Boeing Commercial |
To detect and correct wrinkles and cracks in certain external skin panels of Section 48, which could join,contd. |
Y |
2008-16-11 |
09/17/2008 |
McDonnell Douglas Corp. |
To detect and correct fatigue cracking of door jamb corners of the forward and aft service doors, which could,contd. |
Y |
2008-16-09 |
09/15/2008 |
Short Brothers Limited |
To prevent failure of the balance weight bracket of the elevator trim tab, which could cause loss of the,contd. |
Y |
2008-16-08 |
09/09/2008 |
Dassault Aviation |
To prevent a momentary loss of data on the EFIS screens, which could lead to the pilot's loss of,contd. |
N |
2008-16-07 |
09/09/2008 |
Bombardier, Inc. |
To replace elevator centering torsion spring on the horizontal stabilizer torque tube |
N |
2008-16-06 |
09/09/2008 |
BAE Systems (Operations) |
To identify and correct the insufficient or defective bonding in the fuel tank area, if not corrected, could,contd. |
N |
2008-16-05 C |
09/04/2008 |
Rolls-Royce Deutschland |
To prevent HPT disk failure, which can result in an uncontained engine failure and damage to the airplane |
N |
2008-16-04 |
09/15/2008 |
Bell Helicopter |
To inspect and correct the rigging of the tail rotor pitch change mechanism |
N |
2008-16-03 |
08/11/2008 |
Pilatus Aircraft Ltd. |
To inspect and replace broken leaf spring that could lead to an uncommanded flap retraction which could lead to,contd. |
Y |
2008-16-02 |
09/03/2008 |
Hawker Beechcraft |
To correct potentially inadequate stall warning with loss of stick pusher function |
Y |
2008-16-01 |
08/15/2008 |
General Electric Co. |
To prevent loss of thrust control and controllability of the airplane |
N |
2008-15-06 |
09/02/2008 |
Cessna Aircraft Company |
To detect & correct cracks in the engine mounting brackets, which could result in failure of the engine mounting bracket |
Y |
2008-15-05 |
08/05/2008 |
Boeing Commercial |
To detect and correct corrosion of the carriage spindle, which could result in fracture |
Y |
2008-15-04 |
09/03/2008 |
Bell Helicopter |
To prevent the misalignment of the tail rotor counterweight bellcrank |
N |
2008-15-03 |
09/03/2008 |
MD Helicopters, Inc. |
To prevent disbonding and subsequent separation of an abrasion strip from a T/R blade, which could,contd. |
Y |
2008-15-02 |
09/03/2008 |
Eurocopter Deutschland |
To correct the unsafe condition by further securing the injection tubes with improved clamps,contd. |
N |
2008-15-01 |
08/21/2008 |
Embraer |
To prevent pitch upsets if the pitch trim actuators jam or freeze, which could result in reduced controllability,contd. |
N |
2008-14-17 |
08/21/2008 |
Airbus Industrie |
To identify and correct the loss of integrity of the upper shell structure of the fuselage between FR84 and FR87 |
N |
2008-14-16 |
08/21/2008 |
328 Support Services GmbH |
To prevent further incidents of inadvertent opening and possible detachment of a passenger door,contd. |
N |
2008-14-15 |
08/20/2008 |
International Aero Engine |
To prevent heat damage to high-pressure turbine (HPT) and low-pressure turbine (LPT) critical life limited,contd. |
N |
2008-14-14 |
08/21/2008 |
Boeing Commercial |
To prevent insufficient clearance between the wire bundle and hydraulic tube that could lead to chafing,contd. |
N |
2008-14-13 |
08/14/2008 |
Cirrus Design Corp. |
To prevent in-flight failure of the cabin door, which could result in door separation from the airplane |
N |
2008-14-12 |
08/21/2008 |
Pacific Aerospace |
To require inspections of the vertical fin for cracking, corrosion, scratches, dents, creases, and/or,contd. |
Y |
2008-14-11 |
07/23/2008 |
Boeing Commercial |
To prevent ETOPS operation with insufficient cargo fire suppression capability, which could result in an,contd. |
N |
2008-14-10 |
07/22/2008 |
Lockheed Aircraft Corp |
To prevent failure of the upper engine mount bolts, which could result in reduced structural capability,contd. |
Y |
2008-14-09 |
08/14/2008 |
Airbus Industrie |
To render manditory an inspection subsequent to accomplishment of SB A200-53-0282 or,cont'd |
Y |
2008-14-08 |
08/14/2008 |
Boeing Commercial |
To detect and correct broken or missing fasteners in the hinge segments with a single fastener row, which,contd. |
Y |
2008-14-07 |
08/14/2008 |
Lycoming Engines |
To prevent failure of the fuel injector fuel lines that would allow fuel to spray into the engine compartment,contd. |
Y |
2008-14-06 |
08/14/2008 |
Bell Helicopter |
To identify and correct manufacturing flaws on the inside surface of the upper and/or lower skin at,contd. |
N |
2008-14-05 |
08/21/2008 |
Agusta |
To extend the same mandatory corrective actions to A119 model due to its design similarity with A109E |
Y |
2008-14-04 |
08/05/2008 |
Eurocopter France |
To prevent the power drawn by the starter generators from the engines from exceding the consumption capacity at,contd. |
N |
2008-14-03 |
08/14/2008 |
Bell Helicopter |
To identify and correct an improper installation of the tailboom attachment bolt in the upper left-hand,contd. |
N |
2008-14-02 |
08/14/2008 |
Agusta |
To detect cracks in the fuselage frame structure and to prevent structural failure in this area |
Y |
2008-14-01 |
08/14/2008 |
Bell Helicopter |
To prevent interruption of the fuel supply caused by failure of the switch, which could result in loss of,contd. |
N |
2008-13-32 |
08/12/2008 |
APEX Aircraft |
To mandate revision of the AFM which introduces the corrected values for arms of front and rear fuel tanks |
N |
2008-13-31 |
08/12/2008 |
Dassault Aviation |
To secure safe closure of engine cowlings and improve the existing locking devices |
N |
2008-13-30 |
08/12/2008 |
Gulfstream Aerospace LP |
To prevent failure of the attachment fasterners which could result in possible in-flight loss of a,contd. |
N |
2008-13-29 |
08/12/2008 |
McDonnell Douglas Corp. |
To detect and correct such cracking, which could sever the frame, increase the loading of adjacent,contd. |
Y |
2008-13-28 |
07/17/2008 |
Hartzell Propeller |
To prevent failure of the propeller hub, which could result in blade separation and loss of control of the,contd. |
Y |
2008-13-27 |
08/06/2008 |
Turbomeca Engine Corp. |
To prevent uncommanded shutdown of the engine, which could lead to an accident |
N |
2008-13-26 |
08/12/2008 |
Lockheed Aircraft Corp |
To prevent the loss of hydraulic pressure and steering control |
Y |
2008-13-25 |
08/12/2008 |
Boeing Commercial |
To prevent fatigue cracking in the web panel of the main wheel well pressure deck, which could result in,contd. |
N |
2008-13-24 |
08/12/2008 |
Aerospatiale |
To require the inspection [for proper hole diameter] of the aileron tab bellcrank retainer and, if necessary, the,contd. |
N |
2008-13-23 |
08/06/2008 |
328 Support Services GmbH |
To install a drain hole in the lower skin of the left and right-hand elevator horns, contd. |
N |
2008-13-22 |
08/06/2008 |
Boeing Commercial |
To prevent loss of the IDUs due to failure of all three electronic flight instrument system/engine,contd. |
N |
2008-13-21 |
08/06/2008 |
Boeing Commercial |
To prevent the in-line flow indicators of the passenger oxygen masks from fracturing and separating, which,contd. |
N |
2008-13-20 |
08/06/2008 |
Boeing Commercial |
To prevent failure of the attachment bolts and consequent separation of a thrust reverser from,contd. |
Y |
2008-13-19 |
08/06/2008 |
ATR |
To require repetitive verification of the Pitot probes' resistance and replacement of any,contd. |
Y |
2008-13-18 |
07/30/2008 |
Pilatus Aircraft Ltd. |
To prevent, on take-off or landing runs, possible hazards associated with loss of directional control |
N |
2008-13-17 |
08/06/2008 |
Hawker Beechcraft |
To prevent failure of the circuit breaker toggle switch, which could result in smoke in the cockpit and the,contd. |
N |
2008-13-16 |
07/10/2008 |
Pratt & Whitney Canada |
To inspect Low-Pressure (LP) compressor fan blades and replace any blade that is found to be under,contd. |
N |
2008-13-15 |
07/30/2008 |
Embraer |
To require the inclusion of new maintenance tasks in the Critical Design Configuration Control Limitations,contd. |
Y |
2008-13-14 |
07/30/2008 |
Embraer |
To require the inclusion of new maintenance tasks in the Critical Design Configuration Control Limitations,contd. |
Y |
2008-13-13 |
08/12/2008 |
Airbus Industrie |
To prevent the airplane from departing the runway during a CAT 2 or CAT 3 automatic landing or roll-out,contd. |
N |
2008-13-12 |
08/12/2008 |
Boeing Commercial |
To detect and correct fatigue cracking of the upper frame to side frame splice of the fuselage, which could,contd. |
Y |
2008-13-11 |
08/05/2008 |
Viking-Air Ltd. |
To perform the corrosion tasks (CTs) required by the corrosion prevention and control program |
Y |
2008-13-09 |
09/17/2008 |
Bombardier, Inc. |
To prevent potential ignition sources within the fuel system, which could result in a fuel tank explosion |
N |
2008-13-08 |
08/06/2008 |
Dehavilland Aircraft |
To prevent potential ignition sources inside the fuel system, which could result in a fuel tank explosion |
Y |
2008-13-07 |
07/30/2008 |
Dehavilland Aircraft |
To identify and correct the installation of the elevator overload bungees, reinstallation if,contd. |
N |
2008-13-06 |
07/30/2008 |
Cessna Aircraft Company |
To detect and correct damaged wiring of the auto-control wing de-ice system, fuel quantity indication,contd. |
N |
2008-13-01 |
08/01/2008 |
Fokker Aircraft B.V. |
To require a one-time inspection for improper welds |
N |
2008-11-10 |
08/05/2008 |
Viking-Air Ltd. |
To mandate modification and inspection of the wing front spar adapter fitting and replacement of cracked,contd. |
Y |
2008-02-04 C |
02/26/2008 |
Eclipse Aviation Corp. |
To prevent long-term reliance on special operating limitations when a design change exists that,contd. |
N |
