AD/A320/104 - Flight Controls - Inspection and Modification of Spoiler Servocontrols

Airworthiness Directive - AD/A320/104 - Flight Controls - Inspection and Modification of Spoiler Servocontrols Airworthiness Directive - AD/A320/104 - Flight Controls - Inspection and Modification of Spoiler Servocontrols CASA Airworthiness Directive Jurisdiction:Commonwealth of Australia;CorporateName:Civil Aviation Safety Authority; Issue 11/1999,Aircraft above 5700 kg,Airbus Industrie A319, A320 and A321 Series Aeroplanes,Flight Controls - Inspection and Modification of Spoiler Servocontrols,104 DellaCa, Donna 2 0 2022-10-26T00:36:00Z 2022-10-26T00:36:00Z 1 227 1296 Office of Parliamentary Counsel 10 3 1520 16.0000 2006-09-22T00:00:00Z Toolkit http://www.activepdf.com 2022-10-26T00:00:00Z COMMONWEALTH OF AUSTRALIA   (Civil Aviation Regulations 1998) , PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES   Airbus Industrie A319, A320 and A321 Series Aeroplanes   AD/A320/104   Flight Controls - Inspection and Modification of Spoiler Servocontrols 11/99   Applicability:   All Airbus Industrie model A319 (MSN 0546 to 0972 (inc)), A320 (MSN 002 to 0842, 0846 to 0859, 0865, 0866, 0872 to 0960 (inc)) and A321 (MSN 0364 to 0974 (inc)) aircraft.   Requirement:   1. For A319 and A321 aircraft, inspect the servocontrol for serial number identification and apply, if necessary, the corrective actions in accordance with the instructions contained in AIRBUS INDUSTRIE Service Bulletin A320-27-1126.   2. For A320 aircraft, inspect the servocontrol for serial number identification and apply, if necessary, the corrective actions in accordance with the instructions contained in AIRBUS INDUSTRIE Service Bulletin A320-27-1127.   Note: DGAC AD 1999-362-139 (B) dated 8 September 1999 refers.   Compliance:   1. Before 30 November 1999.   2. Before 31 December 2001.   This Airworthiness Directive becomes effective on 4 November 1999.   Background:     Several cases of spoiler servo control piston rod bearing breakage were experienced leading in almost all cases to the associated hydraulic system loss and spoiler extension in flight to the zero hinge moment position. This condition could lead to a transient perturbation of the aircraft flight path and to a reduction in handling qualities.