DGCANO SUBJECT REFERENCE COMPLIANCE APPLICABILITY DGCA/R44/1 TO PREVENT FAILURE OF THE CYCLIC CONTROL SYSTEM FAA AD 94-26-10 'AS IN AD' 'AS IN AD' DGCA/R44/2 TO PREVENT M/R STALL OR MAST BUMPING FAA AD 95-04-13 'AS IN AD' 'AS IN AD' DGCA/R44/3 TO PREVENT IN FLIGHT M/R SEPARATION FAA AD 95-11-10 'AS IN AD' 'AS IN AD' DGCA/R44/4 TO PREVENT BINDING IN THE CYCLIC CONTROL SYSTEM FAA AD 95-09-07 'AS IN AD' 'AS IN AD' DGCA/R44/5 TO MINIMISE THE POSSIBILITY OF THE PILOT MIS ENGAGEMENT OF THE M/R RPM FAA AD 97-02-15 'AS IN AD' 'AS IN AD' DGCA/R44/6 TO PREVENT LOOSENING OF THE BOLTS SECURING THE GFEAR TO THE GEAR CARRIER FAA AD 96-18-22 'AS IN AD' 'AS IN AD' DGCA/R44/7 TO DETECT EXCESSIVE WEAR ON THE LATERAL CYCLIC TRIM SPRING SHAFT FAA AD 98-0412 'AS IN AD' 'AS IN AD' DGCA/R44/8 TO PREVENT FAILURE OF EITHER 45DEG. OR 90DEG. AL. ELBOWS FAA AD 98-05-10 'AS IN AD' 'AS IN AD' DGCA/R44/9 TO PREVENT FAILURE OF M/R BLADE FAA AD 98-22-16 'AS IN AD' 'AS IN AD' DGCA/R44/10 TO RPEVENT USE OF ASSEMBLY THAT MAY CRACK RESULTING FAILURE FAA AD 98-21-36 'AS IN AD' 'AS IN AD' DGCA/R44/11 TO ALERT PILOTS OF THE POTENTIAL FOR THE SPRAG CLUTCH FAILING TO OVERRUN FAA AD 99-0718 'AS IN AD' 'AS IN AD' DURING AUTOROTATION DGCA/R44/12 TO PREVENT FUEL LEAKS FROM THE AUXILIARY FUELTANK SUMP DRAIN FAA AD 99-13-11 'AS IN AD' 'AS IN AD' DGCA/R44/13 TO PREVENT FAILURE OF YOKE ASSEMBLY FAA AD 99-17-17 'AS IN AD' 'AS IN AD' DGCA/R44/14 FLIGHT MANUAL DGAC AD 2000- 'AS IN AD' 'AS IN AD' 075(A) DGCA/R44/15 TO PREVENT SPRAG CLUTCH FAILURE, LOSS OF MAIN ROTOR RPM DURING FAA AD 2000-08-04 'AS IN AD' 'AS IN AD' AUTOROTION DGCA/R44/16 TO PREVENT CONTACT BETWEEN THE WIRE HARNESS & THE FUEL LINE ASSEMBLY FAA AD 2000-07-03 'AS IN AD' 'AS IN AD' DGCA/R44/17 TO PREVENT A CRACK THROUGH A VERTICAL TO HORIZONTAL STABILIZER ATTACH FAA AD 2001-20-18 'AS IN AD' 'AS IN AD' CHANNE DGCA/R44/18 TO DETECT CORROSION OF A TAIL ROTOR PITCH CONTROL BEARING FAA AD 2003-04-05 'AS IN AD' 'AS IN AD' DGCA/R44/19 TO PREVENT FAILURE OF THE BOLT THAT SECURES PARTS OF THE MAIN ROTOR FAA AD 2003-24-51 'AS IN AD' 'AS IN AD' SWASHPLATE AND ATTACHES THE TAIL ROTOR BLADE DGCA/R44/20(R2) TO DETECT BLADE SKIN DEBOND AND PREVENT BLADE FAILURE AND SUBSEQUENT FAA AD 2011-12-10 'AS IN AD' 'AS IN AD' LOSS OF CONTROL OF THE HELICOPTER (CORRECTION) DGCA/R44/21 TO PREVENT THE TAIL ROTOR (T/R) CONTROL PEDAL BEARING BLOCK SUPPORT FROM FAA AD 2010-24-03 'AS IN AD' 'AS IN AD' DGCANO SUBJECT REFERENCE COMPLIANCE APPLICABILITY BREAKING,WHICH CAN BIND THE T/R CONTROL PEDALS,RESULTING IN A REDUCTION OF YAW CONTROL & SUBSEQUENT LOSS OF CONTROL OF HELICOPTER DGCA/R44/22 UNSAFE CONDITION AS BINDING OF THE NEEDLE WITHIN THE FLOAT INFLATION FAA AD 2013-05-15 'AS IN AD' 'AS IN AD' VALVE ASSEMBLY ,WHICH HAS RESULTED IN THE EMERGENCY FLOATS FAILING TO INFLATE DGCA/R44/23 THIS AD DEFINES THE UNSAFE CONDITION AS BLADE SKIN DEBONDING, WHICH FAA AD 2014-23-16 'AS IN AD' 'AS IN AD' COULD RESULT IN BLADE FAILURE AND SUBSEQUENT LOSS OF CONTROL OF THE HELICOPTER. DGCA/R44/24 THIS AD DEFINES THE UNSAFE CONDITION AS A FATIGUE CRACK ON AN MRB. THIS FAA AD 2016-26-04 'AS IN AD' 'AS IN AD' CONDITION COULD RESULT IN FAILURE OF AN MRB AND LOSS OF HELICOPTER CONTROL. DGCA/R44/25 JOINT AIRCRAFT SYSTEM COMPONENT (JASC)/AIR TRANSPORT ASSOCIATION (ATA) FAA AD 2019-12-18 'AS IN AD' 'AS IN AD' OF AMERICA CODE: 7160, ENGINE AIR INTAKE SYSTEM- TO PREVENT THE UNSAFE CONDITION ON THESE HELICOPTERS .