APPLICABILI DGCANO SUBJECT REFERENCE COMPLIANCE TY DGCA//01 TO PREVENT FAILURE OF THE LOCKWIRES ON THE BEARING RETAINER FAA AD 96-14-06 AS IN AD & AS IN AD & NUT OF THE PIVOT FITTINGS OF THE HORIZONTAL ASB ASB DGCA/BOEING 777/02 TO DETECT AND CORRECT CORROSION, WHICH COULD REDUCE FAA AD 97-10-02 AS IN AD & AS IN AD & SYSTEM PROTECTION AGAINST LIGHTNING STRIKES OR HIGH ASB ASB INTENSITY REDIATED FIELD (HIRF) EVENTS. DGCA/BOEING 777/03 TO DETECT AND CORRECT LOOSE BUSHING RETAINER NUT OF THE FAA AD 97-17-02 AS IN AD & AS IN AD & PIVOT FINS IF THE HORIZONTAL STABILIZER HINGE ASSEMBLY. SB SB DGCA/BOEING 777/04 TO PREVENT FAILURE OF THE LOCK PIN MECHANISM TO LOCK THE FAA AD 98-02-06 R1 AS IN AD & AS IN AD & MLG IN DOWN POSITION ASB ASB DGCA/BOEING 777/05 TO DETECT AND CORRECT FATIGUE CRACKING OF THE FLAPERON FAA AD 99-13-05 AS IN AD & AS IN AD & SUPPORT STRUCTURE ASB ASB DGCA/BOEING 777/06 TO PREVENT CORROSION AND POSSIBLE CRACKING OF ALUMINIUM FAA AD 99-14-05 AS IN AD & AS IN AD & RIBS AND BRACKETS OF THE ASB ASB DGCA/BOEING 777/07 TO DETECT AND CORRECT WEAR OF THE SAFETY SPRING WEAR PLATE FAA AD 99-17-02 AS IN AD & AS IN AD & DOUBLERS ON THE APU FIREWALL SB SB DGCA/BOEING 777/08 TO PREVENT FATIGUE CRACKING OF THE UPPER WING SKIN FAA AD 2000-08-15 AS IN AD & AS IN AD & ASB ASB DGCA/BOEING 777/09 TO PREVENT FATIGUE CRACKING OF THE AFT WHEEL WELL BULKHEAD FAA AD 2000-11-11 AS IN AD & AS IN AD & ASB ASB DGCA/BOEING 777/10 TO PROHIBIT THE DISPATCH OF AN AIRPLANE WITH AN ENGINE FAA AD 2000-13-04 AS IN AD AS IN AD MOUNTED BACKUP GENERATOR HAVING A SHEARED SHAFT DGCA/BOEING 777/11 TO PREVENT FAILURE OF THE SUPPLEMENTAL OXYGEN SYSTEM TO FAA AD 2000-15-16 AS IN AD & AS IN AD & THE PASSENGERS AND FLIGHT ATTENDANTS SB SB DGCA/BOEING 777/12(R1) TO PREVENT POTENTIAL IGNITION OF THE MOISTURE BARRIER COVER FAA AD 2005-17-09 ( AS IN AD & AS IN AD & OF THE DRIP SHIELD FAA AD 2000-26-04 IS SB SB SUPERSEEDED) DGCA/BOEING 777/13 TO FIND AND FIX INCORRECT INSTALLATION OF THE RELEASE PIN IN FAA AD 2001-10-14 AS IN AD & AS IN AD & THE GENERATOR FIRING MECHANISM SB SB DGCA/BOEING 777/14 TO PREVENT MIGRATION OR LOSS OF THE UPPER HOUSING FAA AD 2001-08-03 AS IN AD & AS IN AD & APPLICABILI DGCANO SUBJECT REFERENCE COMPLIANCE TY WEARPLATE, WHICH COULD RESULT IN LOSS OF THE MLG DURING ASB ASB THE TAKEOFF ROLL DGCA/BOEING 777/15 TO PREVENT STRESS CORROSION CRACKING AND CONSEQUENT FAA AD 2001-09-02 AS IN AD & AS IN AD & FRACTURE OF THE AFT TRUNNION OF THE OUTER CYLINDER OF THE ASB ASB MLG. DGCA/BOEING 777/16 TO PREVENT FRACTURE OF THE INBOARD SUPPORT STRUCTURE, OF FAA AD 2001-12-10 AS IN AD & AS IN AD & THE INBOARD FLAPERON ASB ASB DGCA/BOEING 777/17 TO FIND AND FIX CRACKING OF THE WEB OF THE HORIZONTAL AND FAA AD 2001-18-09 AS IN AD & AS IN AD & SLOPING PRESSURE DECKS ASB ASB DGCA/BOEING 777/18 TO DETECT AND CORRECT CRACKING OR MISSING PIECES OF THE FAA AD 2002-11-06 AS IN AD & AS IN AD & COVE SKIN ON THE OUTBOARD SLATS ASB ASB DGCA/BOEING 777/19 TO PREVENT CHAFING OF THE FQIS WIRING ON SURROUNDING FAA AD 2002-16-15 AS IN AD & AS IN AD & STRUCTURES AND SYSTEMS SB SB DGCA/BOEING 777/20 TO PREVENT AN UNCOMMANDED STABILIZER TRIM DUE TO FAA AD 2003-12-01 AS IN AD & AS IN AD & SIMULTANEOUS FAILURE OF TWO STATIC SEALS ON ONE STABILIZER SB SB TRIM CONTROL MODULES (STCM) DGCA/BOEING 777/21 TO PREVENT CRACKING OF THE LEADING EDGE OUTBOARD SLATS FAA AD 2003-19-02 AS IN AD & AS IN AD & ASB ASB DGCA/BOEING 777/22 TO PREVENT LEAKAGE OF INTI THE AFT DRY FAA AD2003-25-02 AS IN AD & AS IN AD & BAY ASB ASB DGCA/BOEING 777/23 TO DETECT AND CORRECT CRACKS OR DAMAGE TO THE WEB OF THE FAA AD 2004-03-05 AS IN AD & AS IN AD & ASB ASB DGCA/BOEING 777/24 TO PREVENT THE POSSIBILITY OF THE AIRPLANE DEPARTING THE FAA AD 2004-04-08 AS IN AD & AS IN AD & RUNWAY DURING CATEGORY IIIB AUTOLAND OPERATIONS ASB ASB DGCA/BOEING 777/25 TO PREVENT WATER FROM BEING TRAPPED INSIDE THE JOYSTICK FAA AD 2004-05-26 AS IN AD & AS IN AD & COVERS SB SB DGCA/BOEING 777/26 TO PREVENT DAMAGE TO THE STABILIZER CUTOUT CIRCUIT WIRES IN FAA AD 2004-12-15 AS IN AD & AS IN AD & THE BUNDLES DUE TO CONTACT BETWEEN THE BUNDLES AND THE SB SB STABILIZER COMMAND CIRCUIT, COULD RESULT IN HYDRAULIC TUBES. APPLICABILI DGCANO SUBJECT REFERENCE COMPLIANCE TY DGCA/BOEING 777/27 TO PREVENT LEAKAGE OF FIRE EXTINGUISHING AGENT THROUGHT FAA AD 2004-17-05 AS IN AD & AS IN AD & THE FILTER/REGULATOR OF THE CARGO FIRE EXTINGUISHING SYSTEM SB SB DGCA/BOEING 777/28 TO PREVENT A POSSIBLE SOURCE OF IGNITION IN A FLAMMABLE FAA AD 2004-18-09 AS IN AD & AS IN AD & LEAKAGE ZONE. SB SB DGCA/BOEING 777/29 TO DETECT AND CORRECT CRACKS OR DEFECTS THAT COULD RESULT FAA AD 2005-07-02 AS IN AD & AS IN AD & IN A FRACTURE OF THE CYLINDER OF THE MLG SB SB DGCA/BOEING 777/30 TO PREVENT A GALLEY, PURSER WORK STATION, OR CLOSET FROM FAA AD 2005-07-16 AS IN AD & AS IN AD & DETACHING FROM THE TIE DOWN FITTING STUDS DURING AN SB SB EMERGENCY LANDING DGCA/BOEING 777/31(R1) TO PREVENT THE DISPLAY OF ERRONEOUS HEADING INFORMATION FAA AD 2005-18-51(FAA AS IN AD & AS IN AD & TO THE PILOT AD 2005-10-03 IS ASB SB SUPERSEEDED) DGCA/BOEING 777/32 TO PREVENT FATIGUE CRACKS IN THE LOWER T- CHORD AT THE BOLT FAA AD 2005-10-17 AS IN AD & AS IN AD & HOLES COMMON TO THE PADDLE FITTINGS. SB SB DGCA/BOEING 777/33 TO PREVENT THE FUEL PUMPS IN THE CENTER FROM FAA AD 2005-10-20 AS IN AD & AS IN AD & RUNNING DRY AND BECOMING A POTENTIAL IGNITION SOURCE. SB SB DGCA/BOEING 777/34 TO PREVENT THE OVERHEATING OF THE FREQUENCY CONVERTER'S FAA AD 2005-12-10 AS IN AD & AS IN AD & UNDERSIZWD OUTPUT WIRING SB SB DGCA/BOEING 777/35 TO PREVENT A LATENT OPEN CIRCUIT THAT COULD LEAVE THE FUEL FAA AD 2005-13-20 AS IN AD & AS IN AD & SHUTOFF VALVE IN A PARTIALLY OPEN POSITION SB SB DGCA/BOEING 777/36 TO PREVENT FAILURE OF THE VERTICAL TIE RODS SUPPORTING FAA AD 2005-13-28 AS IN AD & AS IN AD & CERTAIN ELECTRICAL RACKS AND THE CENTER STOWAGE BINS. SB SB DGCA/BOEING 777/37 TO PREVENT WIRE CHAFING, WHICH COULD RESULT IN THE LOSS OF FAA AD 2005-13-29 AS IN AD & AS IN AD & FLIGHT CONTROL, COMMUNICATION, NAVIGATION, AND THE ENGINE SB SB FIRE CONTROL SYSTEMS DGCA/BOEING 777/38 TO PREVENT OVERHEATING OF THE LIGHT CONNECTORS FAA AD 2005-13-34 AS IN AD & AS IN AD & SB SB DGCA/BOEING 777/39 TO PREVENT A FIRE IN THE CARGO COMPARTMENT FAA AD 2005-14-04 AS IN AD & AS IN AD & SB SB APPLICABILI DGCANO SUBJECT REFERENCE COMPLIANCE TY DGCA/BOEING 777/40 TO PREVENT AN UNCONTROLLABLE FIRE IN THE LEADING EDGE OF FAA AD 2005-14-05 AS IN AD & AS IN AD & THE WING SB SB DGCA/BOEING 777/41 TO PREVENT WIRE BUNDLES OF THE FUEL SYSTEM CHAFING AGAINST FAA AD 2005-17-02 AS IN AD & AS IN AD & THE REAR SPAR STIFFNERS OUTSIDE THE FUEL TANK SB SB DGCA/BOEING 777/42 TO PREVENT LOSS OF THE CAPABILITY OF THE CABIN FLOOR AND SEAT FAA AD 2005-18-10 AS IN AD & AS IN AD & TRACK STRUCTURE TO SUPPORT THE AIRPLANE INERTIA LOADS SB SB UNDER EMERGENCY LANDING CONDITIONS DGCA/BOEING 777/43 TO PREVENT DAMAGE AND EVENTUAL FRACTURE OF THE FAA AD 2005-25-24 AS IN AD & AS IN AD & ASSEMBLY, PIN ASSEMBLY, AND ATTACHEMENT BOLTS THAT SB SB CONNECT THE INBOARD AND OUTBOARD POWER CONTROL UNIT (PCU) TO A FLAPERON DGCA/BOEING 777/44 TO PREVENT ENERGY FROM A LIGHTNING STRIKE ON THE BUSHING FAA AD 2006-05-08 AS IN AD & AS IN AD & FOR THE SUMP DRAIN VALVE FROM ARCING TO THE INSIDE OF THE SB SB CENTER FUEL TANK WALL. DGCA/BOEING 777/45 TO PREVENT FAILURE OF FLIGHT DECK ELECTRONIC EQUIPMENT FAA AD 2005-05-20 AS IN AD & AS IN AD & SB SB DGCA/BOEING 777/46 TO PREVENT FAILURE OF THE EMERGENCY POWER ASSIST SYSTEM FAA AD 2006-11-13 AS IN AD & AS IN AD & (EPAS) SB SB DGCA/BOEING 777/47 TO PREVENT FIRE PROPAGATION OR SMOKE IN THE CABIN AREA DUE FAA AD 2006-12-06 AS IN AD & AS IN AD & TO ELECTRICAL ARCING OR SPARKING AND IGNITION OF THE SPIRAL SB SB WIRE WRAPPING DGCA/BOEING 777/48 TO PREVENT ARCING OR SPARKING DURING A LIGHTNING STRIKE AT FAA AD 2006-12-26 AS IN AD & AS IN AD & THE INTERFACE BETWEEN THE BULKHEAD FITTINGS OF THE FUEL FEED SB SB TUBE AND THE FRONT SPAR INSIDE THE FUEL TANK DGCA/BOEING 777/49 TO PREVENT FAILURE OF THE SAFETY FITTINGS FOR THE CARGO FIRE FAA AD 2006-17-11 AS IN AD & AS IN AD & EXTINGUISHING BOTTLES DUE TO CORROSION SB SB DGCA/BOEING 777/50R1 TO DETECT AND CORRECT DEGRADATION OF THE AFT FAIRING LOWER FAA AD 2016-23-02 AS IN AD & AS IN AD & WEB SUPERSEDED FAA AD SB SB 2006-19-12 APPLICABILI DGCANO SUBJECT REFERENCE COMPLIANCE TY DGCA/BOEING 777/51 TO PREVENT DUAL ENGINE THRUST ROLLBACK DURING THE TAKEOFF FAA AD 2006-20-51R1 AS IN AD & AS IN AD & PHASE OF FLIGHT SB SB DGCA/BOEING 777/52 TO PREVENT AN INCREASED PRESSURE DROP ACROSS THE FAA AD 2006-21-05 AS IN AD & AS IN AD & HUMIDIFIER SB SB DGCA/BOEING 777/53 TO PREVENT FAILURE OF A THRUST REVERSER (TR) AND ADJACENT FAA AD 2006-21-09 AS IN AD & AS IN AD & COMPONENTS SB SB DGCA/BOEING 777/54 TO DETECT AND CORRECT CORROSION, AND PREVENT SUBSEQUENT FAA AD 2006-25-05 AS IN AD & AS IN AD & FATIGUE CRACKS, ON THE SKIN UNDER THE FORWARD AND SB SB AFT WING TO BODY FAIRINGS DGCA/BOEING 777/55R1 TO DETECT CRACKED OUTER V-BLADE FITTINGS AT THE HINGE BEAM FAA AD 2014-15-21 AS IN AD & AS IN AD & END OF ROLLS-ROYCE ENGINE THRUST REVERSERS, ON AIRPLANES ON SUPERSEDURE FAA AD SB SB WHICH THE OPTIONAL TERMINATING ACTION WAS DONE 2006-26-06 DGCA/BOEING 777/56 TO PREVENT DISCONNECTION OF DRIVE ARM FROM ITS DRIVE FAA AD 2007-02-23 AS IN AD & AS IN AD & GIMBAL SB SB DGCA/BOEING-777/ 57(R1) TO PREVENT AIR SUPPLY AND CABIN PRESSURE CONTROLLER FAILURE FAA AD 2007-07-05(R1) AS IN AD & AS IN AD & SB SB DGCA/BOEING-777/ 58 TO DETECT AND CORRECT CORROSION OR CRACKING OF THE TORQUE FAA AD 2007-09-04 AS IN AD & AS IN AD & TUBE AND CLOSE OUT FITTINGS THAT SUPPORT THE INBOARD SB SB END OF THE INBOARD TRAILING EDGE DGCA/BOEING-777/ 59R1 TO DETECT AND CORRECT EXCESSIVE WEAR IN THE LOAD LOOP FAA AD 2015-12-03 AS IN AD & AS IN AD & COMPONENTS OF THE CONTROL SURFACES, WHICH COULD LEAD TO amendment FAA AD SB SB EXCESSIVE FREEPLAY OF THE CONTROL SURFACES, FLUTTER, AND 2007-13-05 CONSEQUENT LOSS OF CONTROL OF THE AIRPLANE DGCA/BOEING-777/ 60 TO PREVENT AN UNDETECTED FAILURE OF THE PRIMARY LOAD PATH FAA AD 2009-14-06 AS IN AD &SB AS IN AD & FOR THE BALLSCREW IN THE DRIVE MECHANISM OF THE HORIZONTAL SB STABLIZER AND SUBSEQUENT WEAR AND FAILURE OF THE SECONDARY LOAD PATH DGCA/BOEING-777/ 61 TO PREVENT WEAR AND CORROSION AT THE FLAP SUPPORT JOINTS FAA AD 2007-23-11 AS IN AD & AS IN AD & SB SB APPLICABILI DGCANO SUBJECT REFERENCE COMPLIANCE TY DGCA/BOEING-777/ 62R1 TO DETECT AND CORRECT A CRACKED ACTUATOR FITTING OR FAA AD 2013-08-02 AS IN AD & AS IN AD & INCORRECTLY INSTALLED BOLTS TO THE ACTUATOR FITTING ,WHICH SB SB COULD LEAD TO THE BECOMING DETACHED AND UNRESTRAINED DGCA/BOEING-777/ 63 SSAD ------AS IN AD & AS IN AD & SB SB DGCA/BOEING-777/ 64R1 TO PREVENT POTENTIAL IGNITION SOURCES INSIDE FUEL FAA AD 2011-09-15 AS IN AD & AS IN AD & TANKS,WHICH,IN COMBINATION WITH FLAMMABLE FUEL SB SB VAPOURS,COULD RESULT IN A FUEL TANK EXPLOSION & CONSEQUENT LOSS OF THE AIRPLANE DGCA/BOEING-777/ 65 TO PREVENT THE INLINE FLOW INDICATORS OF THE PASSENGER FAA AD 2008-12-05 AS IN AD & AS IN AD & OXYGEN MASKS FROM FRACTUARING AND SEPRATING SB SB DGCA/BOEING-777/ 66 TO PREVENT ETOPS OPERATION WITH INSUFFICIENT CARGO FIRE FAA AD 2008-14-11 AS IN AD & AS IN AD & SUPPRESSION CAPABILITY SB SB DGCA/BOEING-777/ 67 TO DETECT AND CORRECT WRINKLES AND CRACKS IN CERTAIN FAA AD 2008-16-12 AS IN AD & AS IN AD & EXTERNAL PANELS OF SECTION 48 SB SB DGCA/BOEING-777/ 68 TO PREVENT ICE FROM ACCUMULATING IN THE MAIN TANK FUEL FAA AD 2009 - 05 -11 AS IN AD & AS IN AD & FEED SYSTEM WHICH WHEN RELEASED COULD RESULT IN A SB SB RESTRICTION IN THE ENGINE FUEL SYSTEM DGCA/BOEING-777/ 69 TO PREVENT AN UNANNUNCIATED LOSS OF CABIN PRESSURE.IF AN FAA AD 2009 - 02 - 05 AS IN AD & AS IN AD & UNDETECTED LOSS OF PRESSURE EVENT WERE TO CAUSE AN UNSAFE SB SB PRESSURE IN THE CABIN,THE FLIGHT CREW COULD BECOME INCAPACITATED DGCA/BOEING-777/ 70R1 TO DETECT & CORRECT SCRIBE LINES,WHICH CAN DEVELOP INTO FAA AD 2013 - 07 - 11 AS IN AD & AS IN AD & FATIGUE CRACKS IN THE SKIN.UNDETECTED FATIGUE CRACKS CAN SB SB GROW & CAUSE SUDDEN DECOMPRESSION OF THE AIRPLANE DGCA/BOEING-777/ 71 TO PREVENT A STANDBY STATIC INVERTER FROM FAA AD 2009 -26-03 AS IN AD & AS IN AD & OVERHEATINGWHICH COULDRESULT IN SMOKE IN THE FLIGHT DECK & SB SB CABIN & LOSS OF THE ELECTRICAL STANDBY POWER SYSTEM DGCA/BOEING-777/ 72 TO PREVENT INADVERTENT ENGAGEMENT OF THE FAA AD 2010-06-09 AS IN AD & AS IN AD & APPLICABILI DGCANO SUBJECT REFERENCE COMPLIANCE TY DURING TAKE OFF ROLL,WHICH COULD RESULT IN REJECTED TAKE OFF SB SB AT ROTATION SPEED & PREVENT A LOWER THAN OPTIMAL CLIMB GRADIENT DURING TAKE OFF DGCA/BOEING-777/ 73 TO PREVENT LOSS OF LOWER WING SKIN LOAD PATH,WHICH COULD FAA AD 2010-13-03 AS IN AD & AS IN AD & CAUSE CATASTROPHIC STRUCTURAL FAILURE OF THE WING SB SB DGCA/BOEING-777/ 74 TO PREVENT SMOKE & FIRE IN THE COCKPIT WHICH COULD LEAD TO FAA AD 2010-15-01 AS IN AD & AS IN AD & LOSS OF VISIBILITY AND INJURIES TO OR INCAPACITATION OF THE SB SB FLIGHTCREW DGCA/BOEING-777/ 75 TO DETECT & CORRECT DAMAGE TO THE OUTBOARD SLAT MAIN FAA AD 2010-14-13 AS IN AD & AS IN AD & TRACK SLAT CANS,WHICH CAN ALLOW FUEL LEAKAGE INTO THE FIXED SB SB WING LEADING EDGE DGCA/BOEING-777/ 76 TO PREVENT FAILURE OF DEFECTIVE FLIGHT DECK DOOR WHICH FAA AD 2008-01-01 AS IN AD & AS IN AD & COULD JEOPARADIZE FLIGHT SAFETY SB SB DGCA/BOEING-777/ 77 TO PREVENT DAMAGE & POSSIBLE PUNCTURE OF THE OIL SCAVENGE FAA AD 2010-16-12 AS IN AD & AS IN AD & TUBE & CONSEQUENT OIL LOSS,WHICH COULD RESULT IN AN IN SB SB FLIGHT SHUTDOWN OF THE ENGINE DGCA/BOEING-777/ 78 TO DETECT & CORRECT IMPROPERLY APPLIED SEALANT ,WHICH FAA AD 2010-23-15 AS IN AD & AS IN AD & COULD RESULT IN THE DISBONDING AND DISPLACING OF SEALANT SB SB AND CONSEQUENT FUEL LEAKS. DGCA/BOEING-777/ 79R2 JOINT SYSTEM COMPONENT (JASC) /AIR TRANSPORT FAA AD 2017-11-14 AS IN AD & AS IN AD & ASSOCIATION (ATA) OF AMERICA CODE 57: WINGS SUPERSEDED FAA AD SB SB 2011-26-03 DGCA/BOEING-777/ 80 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 78: EXHAUST FAA AD 2010-26-01 AS IN AD & AS IN AD & SB SB DGCA/BOEING-777/ 81 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 55: FAA AD 2011-05-12 AS IN AD & AS IN AD & STABILIZERS SB SB DGCA/BOEING-777/ 82 JOINT AIRCRAFT SYSTEM COMPONENT (JASC )/ AIR TRANSPORT FAA AD 2011-09-05 AS IN AD & AS IN AD & ASSOCIATION (ATA) OF AMERICA CODE 28: FUEL SB SB DGCA/BOEING-777/ 83R1 ATA 54, /PYLONS, TO DETECT AND CORRECT HYDRAULIC FAA AD 2015-01-01 AS IN AD & AS IN AD & APPLICABILI DGCANO SUBJECT REFERENCE COMPLIANCE TY FLUID CONTAMINATION, WHICH CAN CAUSE CRACKING OF TITANIUM amendment FAA AD SB SB PARTS IN THE SYSTEM DISCONNECT ASSEMBLY; AND ALSO TO DETECT 2011-09-11 AND CORRECT MISSING FASTENERS, WHICH RESULTS IN UNSEALED OPENINGS ON THE SYSTEM DISCONNECT ASSEMBLY. BOTH UNSAFE CONDITIONS CAN COMPROMISE THE ENGINE FIREWALL AND RESULT IN FIRE HAZARDS FOR BOTH THE ENGINE COMPARTMENT AND THE STRUT DGCA/BOEING-777/ 84 JOINT AIRCRAFT SYSTEM COMPONENT (JASC )/ AIR TRANSPORT FAA AD 2011-21-03 AS IN AD & AS IN AD & ASSOCIATION (ATA) OF AMERICA CODE 29: HYDRAULIC POWER:AND SB SB 24:ELECTRICAL POWER DGCA/BOEING-777/ 85 TO ENSURE THAT FATIGUE CRACKING OF VARIOUS PRINCIPAL FAA AD 2012-07-06 AS IN AD & AS IN AD & STRUCTURAL ELEMENTS (PSEs) IS DETECTED AND CORRECTED,SUCH SB SB FATIGUE CRACKING COULD ADVERSELY AFFECT THE STRUCTURAL INTEGRITY OF THESE AIRPLANES DGCA/BOEING-777/ 86R1 TO DETECT AND CORRECT CORROSION ON BONDING JUMPERS FAA AD 2014-11-03 AS IN AD & AS IN AD & INSTALLED ON THE , WHICH, IN THE AMENDMENT FAA AD SB SB EVENT OF A LIGHTNING STRIKE, COULD DAMAGE THE ACTUATOR 2012-08-13 CONTROL ELECTRONICS (ACES) AND RESULT IN THE LOSS OF THE ABILITY TO COMMAND INDIVIDUAL FLIGHT CONTROL SURFACES OR CAUSE UNCOMMANDED MOTION OF INDIVIDUAL FLIGHT CONTROL SURFACES DGCA/BOEING-777/ 87 TO DETECT AND CORRECT CRACKING IN THE WCS SPANWISE FAA AD 2012-08-09 AS IN AD & AS IN AD & BEAMS,WHICH COULD RESULT IN REDUCED STRUCTURAL INTEGRITY SB SB OF THE WINGS DGCA/BOEING-777/ 88 TO PREVENT AN INCORRECT EMERGENCY LANDING MLG BREAK- FAA AD 2012-11-03 AS IN AD &SB AS IN AD & AWAY SEQUENCE,WHICH COULD RESULT IN PUNCTURING OF THE SB WING BOX AND CONSEQUENT FUEL LEAKS AND AN AIRPLANE FIRE DGCA/BOEING-777/ 89 TO PREVENT A FRACTURED HORIZONTAL STABILIZER PIVOT PIN FAA AD 2012-10-10 AS IN AD & AS IN AD & ,WHICH MAY CAUSE EXCESSIVE HORIZONTAL STABILIZER FREEPLAY SB SB AND STRUCTURAL DAMAGE SIGNIFICANT ENOUGH TO RESULT IN LOSS APPLICABILI DGCANO SUBJECT REFERENCE COMPLIANCE TY OF THE AIRPLANE DGCA/BOEING-777/ 90 TO DETECT AND CORRECT FRACTURED AND MISSING LATCH PIN FAA AD 2012-09-14 AS IN AD & AS IN AD & RETENTION BOLTS ,WHICH COULD RESULT IN POTENTIAL SEPERATION SB SB OF THE CARGO DOOR FROM THE AIRPLANE AND CATASTROPHIC DECOMPRESSION OF THE AIRPLANE DGCA/BOEING-777/ 91R2 TO PREVENT STRUCTURAL DAMAGE TO THE SIDE AND DRAG BRACE FAA AD 2014-05-09 AS IN AD & AS IN AD & LOCK ASSEMBLIES,WHICH COULD RESULT IN SUPERSEDURE FAA AD SB SB COLLAPSE DURING TOUCH DOWN ,ROLLOUT OR TAXI 2012-12-08 DGCA/BOEING-777/ 92 TO PREVENT THE FORWARD LOWERED CEILING PANELS AND SUPPORT FAA AD 2012-12-19 AS IN AD & AS IN AD & STRUCTURE FROM BECOMING DISLODGED DURING A 9.0 G FORWARD SB SB LOAD AND CONSEQUENT INJURY TO PERSONNEL OR INTERFERENCE WITH AN EMERGENCY EVACUATION DGCA/BOEING-777/ 93 TO PREVENT ELECTRICAL CURRENT FROM PASSING THROUGH THE FAA AD 2012-13-05 AS IN AD & AS IN AD & LOW PRESSURE OXYGEN HOSE INTERNAL ANTI COLLAPSE SPRING SB SB WHICH CAN CAUSE THE LOW PRESSURE OXYGEN HOSE TO MELT OR BURN AND A CONSEQUENT OXYGEN FED FIRE IN THE FLIGHT COMPARTMENT DGCA/BOEING-777/ 94 TO DETECT & CORRECT SUCH FATIGUE CRACKING,WHICH COULD FAA AD 2012-14-03 AS IN AD & AS IN AD & GROW LARGE AND CAUSE SUDDEN DECOMPRESSION AND THE SB SB INABILITY TO SUSTAIN LIMIT FLIGHT & PRESSURE LOADS DGCA/BOEING-777/ 95 TO ELIMINATE THRUST REVERSER THERMAL DAMAGE CAUSED BY FAA AD 2012-16-04 AS IN AD & AS IN AD & EXCESSIVE HEAT DOWNSTREAM OF THE 8TH STAGE IP8 EXHAUST SB SB PORTS,WHICH COULD RESULT IN THRUST REVERSER STRUCTURAL FAILURE DGCA/BOEING-777/ 96 TO DETECT & CORRECT CRACKING IN THE MLG CENTER AXLE AND FAA AD 2012-19-10 AS IN AD & AS IN AD & SHOCK STRUT INNER CYLINDER LUGS (PIVOT JOINT ) WHICH COULD SB SB RESULT IN FRACTURE OF THE MLG PIVOT JOINT COMPONENTS AND CONSEQUEBT COLLAPSE OF THE MLG DGCA/BOEING-777/ 97 TO PREVENT EXCESSIVE FREEPLAY IN THE CONTROL SURFACE FAA AD 2012-21-10 AS IN AD & AS IN AD & ,WHICH COULD CAUSE RUDDER VIBRATION,AND RESULT IN SB SB APPLICABILI DGCANO SUBJECT REFERENCE COMPLIANCE TY STRUCTURAL DAMAGE SEVERE ENOUGH TO PREVENT CONTINUED SAFE FLIGHT AND LANDING DGCA/BOEING-777/ 98 TO PREVENT FAILURE OF THE CLAMP , WHICH COULD RESULT IN WIRE FAA AD 2012-23-06 AS IN AD & AS IN AD & CHAFING AND POTENTIAL ARCING AND CONSEQUENT FIRE IN SB SB SECTION 48 ( A FLAMMABLE FLUID LEAKAGE ZONE ) OR HEAT DAMAGE TO THE (APU) POWER FEEDER CABLE. DGCA/BOEING-777/ 99 TO PREVENT ELECTRICAL CURRENT FROM FLOWING THROUGH A FAA AD 2013-05-03 AS IN AD & AS IN AD & MOTOR OPERATED VALVE (MOV) ACTUATOR INTO A FUEL SB SB TANK,WHICH COULD CREATE A POTENTIAL IGNITION SOURCE INSIDE THE FUEL TANK. DGCA/BOEING-777/ 100 TO PREVENT CONTACTOR FAILURES,WHICH COULD RESULT IN FAA AD 2013-05-05 AS IN AD & AS IN AD & UNCONTAINED HOT DEBRIS FLOW DUE TO ELMS CONTACTOR SB SB BREAKDOWN,CONSEQUENT SMOKE & HEAT DAMAGE TO AIRPLANE DGCA/BOEING-777/ 101 TO DETECT & CORRECT CORROSION IN THE PACKBOARD RELEASE FAA AD 2013-05-10 AS IN AD & AS IN AD & MECHANISM WHICH COULD INTERFERE WITH ESCAPE SLIDE /RAFT SB SB DEPLOYMENT,PROHIBIT DOORS FRM OPENING IN THE ARMED MODE AND CAUSE CONSEQUENT DELAY AND INJURY DURING EVACUATION OF PASSENGERS DGCA/BOEING-777/ 102 TO PREVENT THE OXYGEN SYSTEM FLEX LINE FROM SEPERATING FAA AD 2013-08-09 AS IN AD & AS IN AD & RESULTING IN IMPROPER FLOW OF OXYGEN THROUGH THE SB SB PASSENGER MASKS AND INJURY TO PASSENGERS DGCA/BOEING-777/ 103R1 TO DETECT AND CORRECT HYDRAULIC FLUID CONTAMINATION OF 2014-20-10 AS IN AD & AS IN AD & THE STRUT FORWARD DRY TO DETECT AND CORRECT HYDRAULIC AMENDMENT FAA AD SB SB FLUID CONTAMINATION OF THE STRUT FORWARD DRY BAY, WHICH 2013-11-14 COULD RESULT IN HYDROGEN EMBRITTLEMENT OF THE TITANIUM FORWARD ENGINE MOUNT BULKHEAD FITTINGS, AND CONSEQUENT INABILITY OF THE FITTINGS TO CARRY ENGINE LOADS, RESULTING IN ENGINE SEPARATION. HYDROGEN EMBRITTLEMENT ALSO COULD CAUSE A THROUGH-CRACK FORMATION ACROSS THE FITTINGS APPLICABILI DGCANO SUBJECT REFERENCE COMPLIANCE TY THROUGH WHICH AN ENGINE FIRE COULD BREACH INTO THE STRUT, RESULTING IN AN UNCONTAINED STRUT FIRE DGCA/BOEING-777/ 104 TO PREVENT ADVERSE SYSTEM RESPONSES AND FLIGHT DECK EFFECTS FAA AD 2014-05-05 AS IN AD & AS IN AD & THAT COULD RESULT IN LOSS OF CONTROLLABILITY OF THE AIRPLANE SB SB OR LANDING SHORT OF THE RUNWAY DURING LANDING DGCA/BOEING-777 / 105 TO DETECT AND CORRECT CRACKING AND CORROSION IN THE FAA AD 2014-05-03 AS IN AD & AS IN AD & FUSELAGE SKIN, WHICH COULD LEAD TO RAPID DECOMPRESSION AND SB SB LOSS OF STRUCTURAL INTEGRITY OF THE AIRPLANE DGCA/BOEING-777 / 106 TO PREVENT ELECTRICAL CURRENT FROM PASSING THROUGH AN FAA AD 2014-09-06 AS IN AD & AS IN AD & INTERNAL, ANTI-COLLAPSE SPRING OF THE LOW-PRESSURE OXYGEN SB SB HOSE WHICH CAN CAUSE THE LOW - PRESSURE OXYGEN HOSE TO MELT OR BURN AND LEAD TO AN OXYGEN - FED FIRE NEAR THE FLIGHT DECK DGCA/BOEING-777 / 107 TO DETECT AND CORRECT FAILURE OF THE ENGINE FUEL SUCTION FAA AD 2014-09-09 AS IN AD & AS IN AD & FEED OF THE FUEL SYSTEM, WHICH, IN THE EVENT OF TOTAL LOSS OF SB SB THE FUEL BOOST PUMPS, COULD RESULT IN DUAL ENGINE FLAMEOUT, INABILITY TO RESTART THE ENGINES, AND CONSEQUENT FORCED LANDING OF THE AIRPLANE DGCA/BOEING-777 / 108R1 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 28, FUEL FAA AD 2019-16-13 AS IN AD & AS IN AD & AFFECTS FAA AD 2014- SB SB 11-01 DGCA/BOEING-777 / 109 TO ENSURE THAT THE FLIGHTCREW IS ABLE TO TURN OFF ELECTRICAL FAA AD 2014-16-11 AS IN AD & AS IN AD & POWER TO THE IFE SYSTEMS AND OTHER NON-ESSENTIAL ELECTRICAL SB SB SYSTEMS THROUGH ONE OR TWO SWITCHES IN THE FLIGHT DECK IN THE EVENT OF SMOKE OR FLAMES DGCA/BOEING-777 / 110 TO PREVENT LOSS OF FLIGHT-CRITICAL INFORMATION DISPLAYED TO FAA AD 2014-20-06 AS IN AD & AS IN AD & THE FLIGHTCREW DURING A CRITICAL PHASE OF FLIGHT, SUCH AS AN SB SB APPROACH OR TAKEOFF, WHICH COULD RESULT IN LOSS OF AIRPLANE CONTROL AT AN ALTITUDE INSUFFICIENT FOR RECOVERY, OR CONTROLLED FLIGHT APPLICABILI DGCANO SUBJECT REFERENCE COMPLIANCE TY INTO TERRAIN DGCA/BOEING-777 / 111 TO PREVENT A DUAL PRS FAILURE THAT COULD CAUSE AN FAA AD 2014-23-04 AS IN AD & AS IN AD & AUTOMATIC DISENGAGEMENT OF THE AUTOPILOT AND AUTOLAND, SB SB WHICH MAY PREVENT CONTINUED SAFE FLIGHT AND LANDING IF DISENGAGEMENT OCCURS AT LOW ALTITUDE AND THE FLIGHT CREW IS UNABLE TO SAFELY ASSUME CONTROL AND EXECUTE A GO- AROUND OR MANUAL LANDING. DGCA/BOEING-777 / 112 TO PREVENT BROKEN OR MIGRATED SPRING PINS OF THE GIRT BAR FAA AD 2014-25-05 AS IN AD & AS IN AD & FLOOR FITTINGS, WHICH COULD RESULT IN IMPROPER DEPLOYMENT SB SB OF THE ESCAPE SLIDE/RAFT AND CONSEQUENT DELAY AND INJURY DURING EVACUATION OF PASSENGERS AND CREW FROM THE CABIN IN THE EVENT OF AN EMERGENCY DGCA/BOEING-777 / 113 TO PREVENT EXTENDED DRY RUNNING OF THE JETTISON FUEL PUMPS, FAA AD 2015-07-07 AS IN AD & AS IN AD & WHICH CAN BE A POTENTIAL IGNITION SOURCE INSIDE THE MAIN SB SB FUEL TANKS, AND CONSEQUENT FUEL TANK FIRE OR EXPLOSION IN THE EVENT THAT THE JETTISON PUMP OVERHEATS OR HAS AN ELECTRICAL FAULT DGCA/BOEING-777 / 114 TO DETECT AND CORRECT ROTARY ACTUATORS MADE WITH A FAA AD 2015-12-11 AS IN AD & AS IN AD & MATERIAL HAVING POOR ACTUATOR GEAR WEAR CHARACTERISTICS, SB SB WHICH COULD RESULT IN FAILURE OF THE ROTARY ACTUATORS FOR THE FORWARD OR AFT LARGE LOWER LOBE CARGO DOORS AND SUBSEQUENT UNCOMMANDED DOOR CLOSURE, WHICH COULD POSSIBLY RESULT IN FATAL INJURY TO PEOPLE ON THE GROUND DGCA/BOEING-777 / 115 TO DETECT AND CORRECT MISSING SEALANT FROM THE WING SKIN FAA AD 2015-15-15 AS IN AD & AS IN AD & PANEL GAPS ABOVE THE UNDERWING FITTINGS, WHICH COULD SB SB RESULT IN CORROSION AND FATIGUE CRACKING IN THE WING SKIN PANEL, AND CONSEQUENT LOSS OF LIMIT LOAD CAPABILITY OF THE WING SKIN AND POTENTIAL SUBSEQUENT STRUCTURAL FAILURE OF THE WINGS DGCA/BOEING-777 / 116 ATA-54, NACELLES/PYLONS TO DETECT AND CORRECT BLOCKAGE OF FAA AD 2015-17-13 AS IN AD & AS IN AD & APPLICABILI DGCANO SUBJECT REFERENCE COMPLIANCE TY FORWARD STRUT DRAIN LINES, WHICH COULD CAUSE FLAMMABLE SB SB FLUIDS TO COLLECT IN THE FORWARD STRUT AREA AND POTENTIALLY CAUSE AN UNCONTROLLED FIRE OR CAUSE FAILURE OF ENGINE ATTACHMENT STRUCTURE AND CONSEQUENT AIRPLANE LOSS. DGCA/BOEING-777 / 117 SUBJECT OF AD IS AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA FAA AD 2015-19-16 AS IN AD & AS IN AD & CODE 78,ENGINE EXHAUST, WE ARE ISSUING THIS AD TO PREVENT SB SB SEPARATION OF THE AFT PLUG FROM THE FORWARD PLUG OF THE TURBINE EXHAUST PLUG ASSEMBLY WHICH COULD RESULT IN PARTS DEPARTING THE AIRPLANE AND HITTING THE EMPENNAGE OR HITTING A PERSON ON THE GROUND, AND DESTABILIZING THE AIRPLANE DURING A CRITICAL FLIGHT PHASE; PARTS REMAINING ON A RUNWAY COULD CAUSE DAMAGE TO ANOTHER AIRPLANE DGCA/BOEING 777/118 TO DETECT AND CORRECT FATIGUE CRACKING IN THE AFT WEBS OF FAA AD 2015-25-08 AS IN AD & AS IN AD & THE RADIAL LAP SPLICES OF THE AFT PRESSURE BULKHEAD SB SB DGCA/BOEING777/119 TO DETECT AND CORRECT FATIGUE CRACKING OF THE SKIN LAP FAA AD 2016-04-17 AS IN AD &SB AS IN AD & SPLICES, AND CONSEQUENT RISK OF SUDDEN DECOMPRESSION AND SB THE INABILITY TO SUSTAIN LIMIT FLIGHT AND PRESSURE LOADS DGCA/BOEING777/120 TO PREVENT FIRE AND SMOKE AT THE ENGINE AFT PYLON AREA IN FAA AD 2016-06-05 AS IN AD & AS IN AD & THE EVENT OF A FUEL LEAK SB SB DGCA/BOEING777/121 TO DETECT AND CORRECT FATIGUE CRACKING OF THE OUTER FAA AD 2016-09-01 AS IN AD & AS IN AD & FLANGES OF THE LEFT AND RIGHT SIDE FORWARD OUTER CHORDS OF SB SB THE STA 2370 PIVOT BULKHEAD DGCA/BOEING 777/122 TO DETECT AND CORRECT CRACKS AND HEAT DAMAGE TO THE STRUT FAA AD 2016 – 10-02 AS IN AD & AS IN AD & AFT FAIRING LOWER SPAR WEB STRUCTURE SB SB DGCA/BOEING 777/123R1 TO PREVENT FUEL EXHAUSTION AND SUBSEQUENT POWER LOSS OF FAA AD 2018-14-08 AS IN AD & AS IN AD & ALL ENGINES DUE TO LOSS OF CAPABILITY TO SCAVENGE FUEL IN THE SUPERSEDED FAA AD SB SB CENTER FUEL TANK. 2016 –11-03 DGCA/BOEING 777/124 TO DETECT AND CORRECT A DEGRADED T/R INNER WALL PANEL. A FAA AD 2016 – 11-16 AS IN AD & AS IN AD & DEGRADED T/R INNER WALL PANEL SB SB DGCA/BOEING 777/125 ATA 32 LANDING GEAR, TO PREVENT A FRACTURED MLG AFT FAA AD 2016-17-10 AS IN AD & AS IN AD & APPLICABILI DGCANO SUBJECT REFERENCE COMPLIANCE TY TURNNION PIN SB SB DGCA/BOEING 777/126 ATA 35 OXYGEN,TO PREVENT ELECTRICAL CURRENT CURRENT FROM FAA AD 2016-18-02 AS IN AD & AS IN AD & PASSING THROUGH THE LOW PRESSURE OXYGEN FLEX HOUSE IN THE SB SB GASEOUS PASSENGER OXYGEN SYSTEM. DGCA/BOEING 777/127 TO PREVENT LOSS OF CONTROL OF BOTH THE LEFT AND RIGHT FAA AD 2016-21-05 AS IN AD & AS IN AD & ENGINE FUEL SPAR VALVES DURING A SINGLE EVENT SB SB DGCA/BOEING 777/128 TO PREVENT A BREACH IN THE ENGINE FIREWALL DUE TO A FAILED FAA AD 2017-05-07 AS IN AD & AS IN AD & UPPER BIFURCATION FORWARD FIRE SEAL. A BREACH COULD DELAY SB SB OR PREVENT THE FIRE DETECTION AND SUPPRESSION SYSTEM FROM FUNCTIONING PROPERLY DGCA/BOEING 777/129 TO PREVENT UNCOMMANDED CHANGES TO THE MCP SELECTED FAA AD 2017-15-1 AS IN AD & AS IN AD & ALTITUDE; SUCH UNCOMMANDED CHANGES COULD RESULT IN SB SB INCORRECT SPATIAL SEPARATION BETWEEN AIRPLANES, MIDAIR COLLISION, OR CONTROLLED FLIGHT INTO TERRAIN. DGCA/BOEING 777/130 TO DETECT AND CORRECT AN UNCONNECTED GALLEY TRIPOD MOUNT FAA AD 2017-13-14 AS IN AD & AS IN AD & ASSEMBLY TO THE TIE RODS IN THE OVERHEAD SUPPORT STRUCTURE, SB SB WHICH CAN CAUSE A GALLEY TO COME LOOSE UNDER A HIGH DYNAMIC LOAD, CAUSING A RISK OF SERIOUS INJURY TO PASSENGERS AND THE BLOCKING OF EVACUATION ROUTES. DGCA/BOEING 777/131R1 TO DETECT AND CORRECT CRACKS IN THE UNDERWING , FAA AD 2019-11-02 AS IN AD & AS IN AD & WHICH COULD RESULT IN FUEL LEAKAGE INTO THE FORWARD CARGO SUPERSEDED FAA AD SB SB AREA AND CONSEQUENT INCREASED RISK OF A FIRE OR, IN A MORE 2017-16-10 SEVERE CASE, COULD ADVERSELY AFFECT THE STRUCTURAL INTEGRITY OF THE AIRPLANE. DGCA/BOEING 777/132 TO DETECT AND CORRECT UNTREATED VACUUM WASTE SYSTEM FAA AD 2018-02-20 AS IN AD & AS IN AD & SPILLS OR LEAKS, WHICH COULD CAUSE CORROSION OF THE AIRPLANE SB SB STRUCTURE, WHICH COULD LEAD TO FATIGUE CRACKS, AND COULD ULTIMATELY RESULT IN RAPID DECOMPRESSION AND LOSS OF STRUCTURAL INTEGRITY APPLICABILI DGCANO SUBJECT REFERENCE COMPLIANCE TY DGCA/BOEING 777/133 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 25, FAA AD 2018-12-04 AS IN AD & AS IN AD & EQUIPMENT/FURNISHINGS- WATER CAN ENTER THE STEAM OVEN SB SB CAVITY AND BECOME HEATED AND THEN RELEASED WHEN THE OVEN DOOR IS OPENED. THIS CONDITION, IF NOT ADDRESSED, COULD RESULT IN INJURY TO THE CABINCREW DGCA/BOEING 777/134 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 25, FAA AD 2018-14-02 AS IN AD & AS IN AD & EQUIPMENT/FURNISHINGS- TO ADDRESS BMS 8-39 FLEXIBLE SB SB URETHANE FOAM FOUND IN CERTAIN AREAS OF AN AIRPLANE, WHICH, IF EXPOSED TO AN IGNITION SOURCE, COULD CAUSE LOSS OF CONTROL OF THE AIRPLANE DURING A FIRE. DGCA/BOEING 777/135 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 78, ENGINE FAA AD 2018-25-11 AS IN AD & AS IN AD & EXHAUST- TO ADDRESS DAMAGED WIRES, WHICH COULD RESULT IN SB SB IN-FLIGHT SHUTDOWN OF THE ENGINE, OR THE INABILITY TO PROPERLY CONTROL THRUST, AND CONSEQUENT REDUCED CONTROLLABILITY OF THE AIRPLANE. DGCA/BOEING 777/136 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 28, FUEL- TO FAA AD 2018-26-05 AS IN AD & AS IN AD & ADDRESS LATENT FAILURE OF THE FUEL SHUTOFF SPAR VALVE TO THE SB SB ENGINE, WHICH COULD RESULT IN THE INABILITY TO TERMINATE FUEL FLOW TO THE ENGINE AND, IN THE CASE OF AN ENGINE FIRE, COULD LEAD TO WING FAILURE. DGCA/BOEING 777/137 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 25, FAA AD 2019-01-08 AS IN AD & AS IN AD & EQUIPMENT/FURNISHINGS- TO ADDRESS NON-COMPLIANT FLIGHT SB SB ATTENDANT SEATS, WHICH COULD FAIL IN A HIGH-G CRASH AND RESULT IN POTENTIAL INJURY TO FLIGHT ATTENDANTS AND CONSEQUENT INABILITY OF THE FLIGHT ATTENDANTS TO ASSIST WITH PASSENGER EVACUATION IN A TIMELY MANNER DGCA/BOEING 777/138 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 25, FAA AD 2019-16-05 AS IN AD & AS IN AD & EQUIPMENT/FURNISHINGS. SB SB