BOEING 777.pdf

DGCANO SUBJECT REFERENCE COMPLIANCE APPLICABILI

TY

DGCA/BOEING 777/01 TO PREVENT FAILURE OF THE LOCKWIRES ON THE BEARING RETAINER NUT OF THE PIVOT FITTINGS OF THE HORIZONTAL STABILIZER

FAA AD 96-14-06 AS IN AD & ASB

AS IN AD & ASB

DGCA/BOEING 777/02 TO DETECT AND CORRECT CORROSION, WHICH COULD REDUCE SYSTEM PROTECTION AGAINST LIGHTNING STRIKES OR HIGH INTENSITY REDIATED FIELD (HIRF) EVENTS.


AS IN AD & ASB

DGCA/BOEING 777/03 TO DETECT AND CORRECT LOOSE BUSHING RETAINER NUT OF THE PIVOT FINS IF THE HORIZONTAL STABILIZER HINGE ASSEMBLY.

FAA AD 97-17-02 AS IN AD & SB

AS IN AD & SB

DGCA/BOEING 777/04 TO PREVENT FAILURE OF THE LOCK PIN MECHANISM TO LOCK THE MLG IN DOWN POSITION

FAA AD 98-02-06 R1 AS IN AD & ASB

AS IN AD & ASB

DGCA/BOEING 777/05 TO DETECT AND CORRECT FATIGUE CRACKING OF THE FLAPERON SUPPORT STRUCTURE


AS IN AD & ASB

DGCA/BOEING 777/06 TO PREVENT CORROSION AND POSSIBLE CRACKING OF ALUMINIUM RIBS AND BRACKETS OF THE TRAILING EDGE EMPENNAGE


AS IN AD & ASB

DGCA/BOEING 777/07 TO DETECT AND CORRECT WEAR OF THE SAFETY SPRING WEAR PLATE DOUBLERS ON THE APU FIREWALL


AS IN AD & SB

DGCA/BOEING 777/08 TO PREVENT FATIGUE CRACKING OF THE UPPER WING SKIN FAA AD 2000-08-15 AS IN AD & ASB

AS IN AD & ASB

DGCA/BOEING 777/09 TO PREVENT FATIGUE CRACKING OF THE AFT WHEEL WELL BULKHEAD FAA AD 2000-11-11 AS IN AD & ASB

AS IN AD & ASB

DGCA/BOEING 777/10 TO PROHIBIT THE DISPATCH OF AN AIRPLANE WITH AN ENGINE MOUNTED BACKUP GENERATOR HAVING A SHEARED SHAFT

FAA AD 2000-13-04 AS IN AD AS IN AD

DGCA/BOEING 777/11 TO PREVENT FAILURE OF THE SUPPLEMENTAL OXYGEN SYSTEM TO THE PASSENGERS AND FLIGHT ATTENDANTS


AS IN AD & SB

DGCA/BOEING 777/12(R1) TO PREVENT POTENTIAL IGNITION OF THE MOISTURE BARRIER COVER OF THE DRIP SHIELD

FAA AD 2005-17-09 ( FAA AD 2000-26-04 IS SUPERSEEDED)

AS IN AD & SB

AS IN AD & SB

DGCA/BOEING 777/13 TO FIND AND FIX INCORRECT INSTALLATION OF THE RELEASE PIN IN THE GENERATOR FIRING MECHANISM


AS IN AD & 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 &


TY

WEARPLATE, WHICH COULD RESULT IN LOSS OF THE MLG DURING THE TAKEOFF ROLL

ASB ASB

DGCA/BOEING 777/15 TO PREVENT STRESS CORROSION CRACKING AND CONSEQUENT FRACTURE OF THE AFT TRUNNION OF THE OUTER CYLINDER OF THE MLG.


AS IN AD & ASB

DGCA/BOEING 777/16 TO PREVENT FRACTURE OF THE INBOARD SUPPORT STRUCTURE, OF THE INBOARD FLAPERON


AS IN AD & ASB

DGCA/BOEING 777/17 TO FIND AND FIX CRACKING OF THE WEB OF THE HORIZONTAL AND SLOPING PRESSURE DECKS


AS IN AD & ASB

DGCA/BOEING 777/18 TO DETECT AND CORRECT CRACKING OR MISSING PIECES OF THE COVE SKIN ON THE OUTBOARD LEADING EDGE SLATS


AS IN AD & ASB

DGCA/BOEING 777/19 TO PREVENT CHAFING OF THE FQIS WIRING ON SURROUNDING STRUCTURES AND SYSTEMS


AS IN AD & SB

DGCA/BOEING 777/20 TO PREVENT AN UNCOMMANDED STABILIZER TRIM DUE TO SIMULTANEOUS FAILURE OF TWO STATIC SEALS ON ONE STABILIZER TRIM CONTROL MODULES (STCM)


AS IN AD & SB

DGCA/BOEING 777/21 TO PREVENT CRACKING OF THE LEADING EDGE OUTBOARD SLATS FAA AD 2003-19-02 AS IN AD & ASB

AS IN AD & ASB

DGCA/BOEING 777/22 TO PREVENT LEAKAGE OF HYDRAULIC FLUID INTI THE STRUT AFT DRY BAY

FAA AD2003-25-02 AS IN AD & ASB

AS IN AD & ASB

DGCA/BOEING 777/23 TO DETECT AND CORRECT CRACKS OR DAMAGE TO THE WEB OF THE AFT PRESSURE BULKHEAD


AS IN AD & ASB

DGCA/BOEING 777/24 TO PREVENT THE POSSIBILITY OF THE AIRPLANE DEPARTING THE RUNWAY DURING CATEGORY IIIB AUTOLAND OPERATIONS


AS IN AD & ASB

DGCA/BOEING 777/25 TO PREVENT WATER FROM BEING TRAPPED INSIDE THE JOYSTICK COVERS


AS IN AD & SB

DGCA/BOEING 777/26 TO PREVENT DAMAGE TO THE STABILIZER CUTOUT CIRCUIT WIRES IN THE BUNDLES DUE TO CONTACT BETWEEN THE BUNDLES AND THE STABILIZER COMMAND CIRCUIT, COULD RESULT IN HYDRAULIC TUBES.


AS IN AD & SB


TY

DGCA/BOEING 777/27 TO PREVENT LEAKAGE OF FIRE EXTINGUISHING AGENT THROUGHT THE FILTER/REGULATOR OF THE CARGO FIRE EXTINGUISHING SYSTEM


AS IN AD & SB

DGCA/BOEING 777/28 TO PREVENT A POSSIBLE SOURCE OF IGNITION IN A FLAMMABLE LEAKAGE ZONE.


AS IN AD & SB

DGCA/BOEING 777/29 TO DETECT AND CORRECT CRACKS OR DEFECTS THAT COULD RESULT IN A FRACTURE OF THE CYLINDER OF THE MLG


AS IN AD & SB

DGCA/BOEING 777/30 TO PREVENT A GALLEY, PURSER WORK STATION, OR CLOSET FROM DETACHING FROM THE TIE DOWN FITTING STUDS DURING AN EMERGENCY LANDING


AS IN AD & SB

DGCA/BOEING 777/31(R1) TO PREVENT THE DISPLAY OF ERRONEOUS HEADING INFORMATION TO THE PILOT

FAA AD 2005-18-51(FAA AD 2005-10-03 IS SUPERSEEDED)

AS IN AD & ASB

AS IN AD & SB

DGCA/BOEING 777/32 TO PREVENT FATIGUE CRACKS IN THE LOWER T- CHORD AT THE BOLT HOLES COMMON TO THE PADDLE FITTINGS.


AS IN AD & SB

DGCA/BOEING 777/33 TO PREVENT THE FUEL PUMPS IN THE CENTER FUEL TANK FROM RUNNING DRY AND BECOMING A POTENTIAL IGNITION SOURCE.


AS IN AD & SB

DGCA/BOEING 777/34 TO PREVENT THE OVERHEATING OF THE FREQUENCY CONVERTER'S UNDERSIZWD OUTPUT WIRING


AS IN AD & SB

DGCA/BOEING 777/35 TO PREVENT A LATENT OPEN CIRCUIT THAT COULD LEAVE THE FUEL SPAR SHUTOFF VALVE IN A PARTIALLY OPEN POSITION


AS IN AD & SB

DGCA/BOEING 777/36 TO PREVENT FAILURE OF THE VERTICAL TIE RODS SUPPORTING CERTAIN ELECTRICAL RACKS AND THE CENTER STOWAGE BINS.


AS IN AD & SB

DGCA/BOEING 777/37 TO PREVENT WIRE CHAFING, WHICH COULD RESULT IN THE LOSS OF FLIGHT CONTROL, COMMUNICATION, NAVIGATION, AND THE ENGINE FIRE CONTROL SYSTEMS


AS IN AD & SB

DGCA/BOEING 777/38 TO PREVENT OVERHEATING OF THE LIGHT CONNECTORS FAA AD 2005-13-34 AS IN AD & SB

AS IN AD & SB

DGCA/BOEING 777/39 TO PREVENT A FIRE IN THE CARGO COMPARTMENT FAA AD 2005-14-04 AS IN AD & SB

AS IN AD & SB


TY

DGCA/BOEING 777/40 TO PREVENT AN UNCONTROLLABLE FIRE IN THE LEADING EDGE OF THE WING


AS IN AD & SB

DGCA/BOEING 777/41 TO PREVENT WIRE BUNDLES OF THE FUEL SYSTEM CHAFING AGAINST THE REAR SPAR STIFFNERS OUTSIDE THE FUEL TANK


AS IN AD & SB

DGCA/BOEING 777/42 TO PREVENT LOSS OF THE CAPABILITY OF THE CABIN FLOOR AND SEAT TRACK STRUCTURE TO SUPPORT THE AIRPLANE INERTIA LOADS UNDER EMERGENCY LANDING CONDITIONS


AS IN AD & SB

DGCA/BOEING 777/43 TO PREVENT DAMAGE AND EVENTUAL FRACTURE OF THE YOKE ASSEMBLY, PIN ASSEMBLY, AND ATTACHEMENT BOLTS THAT CONNECT THE INBOARD AND OUTBOARD POWER CONTROL UNIT (PCU) TO A FLAPERON


AS IN AD & SB

DGCA/BOEING 777/44 TO PREVENT ENERGY FROM A LIGHTNING STRIKE ON THE BUSHING FOR THE SUMP DRAIN VALVE FROM ARCING TO THE INSIDE OF THE CENTER FUEL TANK WALL.


AS IN AD & SB

DGCA/BOEING 777/45 TO PREVENT FAILURE OF FLIGHT DECK ELECTRONIC EQUIPMENT FAA AD 2005-05-20 AS IN AD & SB

AS IN AD & SB

DGCA/BOEING 777/46 TO PREVENT FAILURE OF THE EMERGENCY POWER ASSIST SYSTEM (EPAS)


AS IN AD & SB

DGCA/BOEING 777/47 TO PREVENT FIRE PROPAGATION OR SMOKE IN THE CABIN AREA DUE TO ELECTRICAL ARCING OR SPARKING AND IGNITION OF THE SPIRAL WIRE WRAPPING


AS IN AD & SB

DGCA/BOEING 777/48 TO PREVENT ARCING OR SPARKING DURING A LIGHTNING STRIKE AT THE INTERFACE BETWEEN THE BULKHEAD FITTINGS OF THE FUEL FEED TUBE AND THE FRONT SPAR INSIDE THE FUEL TANK


AS IN AD & SB

DGCA/BOEING 777/49 TO PREVENT FAILURE OF THE SAFETY FITTINGS FOR THE CARGO FIRE EXTINGUISHING BOTTLES DUE TO CORROSION


AS IN AD & SB

DGCA/BOEING 777/50R1 TO DETECT AND CORRECT DEGRADATION OF THE AFT FAIRING LOWER WEB

FAA AD 2016-23-02 SUPERSEDED FAA AD 2006-19-12

AS IN AD & SB

AS IN AD & SB


TY

DGCA/BOEING 777/51 TO PREVENT DUAL ENGINE THRUST ROLLBACK DURING THE TAKEOFF PHASE OF FLIGHT

FAA AD 2006-20-51R1 AS IN AD & SB

AS IN AD & SB

DGCA/BOEING 777/52 TO PREVENT AN INCREASED PRESSURE DROP ACROSS THE HUMIDIFIER


AS IN AD & SB

DGCA/BOEING 777/53 TO PREVENT FAILURE OF A THRUST REVERSER (TR) AND ADJACENT COMPONENTS


AS IN AD & SB

DGCA/BOEING 777/54 TO DETECT AND CORRECT CORROSION, AND PREVENT SUBSEQUENT FATIGUE CRACKS, ON THE FUSELAGE SKIN UNDER THE FORWARD AND AFT WING TO BODY FAIRINGS


AS IN AD & SB

DGCA/BOEING 777/55R1 TO DETECT CRACKED OUTER V-BLADE FITTINGS AT THE HINGE BEAM END OF ROLLS-ROYCE ENGINE THRUST REVERSERS, ON AIRPLANES ON WHICH THE OPTIONAL TERMINATING ACTION WAS DONE

FAA AD 2014-15-21 SUPERSEDURE FAA AD 2006-26-06

AS IN AD & SB

AS IN AD & SB

DGCA/BOEING 777/56 TO PREVENT DISCONNECTION OF DRIVE ARM FROM ITS DRIVE GIMBAL


AS IN AD & SB

DGCA/BOEING-777/ 57(R1) TO PREVENT AIR SUPPLY AND CABIN PRESSURE CONTROLLER FAILURE FAA AD 2007-07-05(R1) AS IN AD & SB

AS IN AD & SB

DGCA/BOEING-777/ 58 TO DETECT AND CORRECT CORROSION OR CRACKING OF THE TORQUE TUBE AND CLOSE OUT RIB FITTINGS THAT SUPPORT THE INBOARD END OF THE INBOARD TRAILING EDGE FLAP


AS IN AD & SB

DGCA/BOEING-777/ 59R1 TO DETECT AND CORRECT EXCESSIVE WEAR IN THE LOAD LOOP COMPONENTS OF THE CONTROL SURFACES, WHICH COULD LEAD TO EXCESSIVE FREEPLAY OF THE CONTROL SURFACES, FLUTTER, AND CONSEQUENT LOSS OF CONTROL OF THE AIRPLANE

FAA AD 2015-12-03 amendment FAA AD 2007-13-05

AS IN AD & SB

AS IN AD & SB

DGCA/BOEING-777/ 60 TO PREVENT AN UNDETECTED FAILURE OF THE PRIMARY LOAD PATH FOR THE BALLSCREW IN THE DRIVE MECHANISM OF THE HORIZONTAL STABLIZER AND SUBSEQUENT WEAR AND FAILURE OF THE SECONDARY LOAD PATH

FAA AD 2009-14-06 AS IN AD &SB AS IN AD & SB

DGCA/BOEING-777/ 61 TO PREVENT WEAR AND CORROSION AT THE FLAP SUPPORT JOINTS FAA AD 2007-23-11 AS IN AD & SB

AS IN AD & SB


TY

DGCA/BOEING-777/ 62R1 TO DETECT AND CORRECT A CRACKED ACTUATOR FITTING OR INCORRECTLY INSTALLED BOLTS TO THE ACTUATOR FITTING ,WHICH COULD LEAD TO THE ELEVATOR BECOMING DETACHED AND UNRESTRAINED


AS IN AD & SB

DGCA/BOEING-777/ 63 SSAD ------------------------------ AS IN AD & SB

AS IN AD & SB

DGCA/BOEING-777/ 64R1 TO PREVENT POTENTIAL IGNITION SOURCES INSIDE FUEL TANKS,WHICH,IN COMBINATION WITH FLAMMABLE FUEL VAPOURS,COULD RESULT IN A FUEL TANK EXPLOSION & CONSEQUENT LOSS OF THE AIRPLANE


AS IN AD & SB

DGCA/BOEING-777/ 65 TO PREVENT THE INLINE FLOW INDICATORS OF THE PASSENGER OXYGEN MASKS FROM FRACTUARING AND SEPRATING


AS IN AD & SB

DGCA/BOEING-777/ 66 TO PREVENT ETOPS OPERATION WITH INSUFFICIENT CARGO FIRE SUPPRESSION CAPABILITY


AS IN AD & SB

DGCA/BOEING-777/ 67 TO DETECT AND CORRECT WRINKLES AND CRACKS IN CERTAIN EXTERNAL PANELS OF SECTION 48


AS IN AD & SB

DGCA/BOEING-777/ 68 TO PREVENT ICE FROM ACCUMULATING IN THE MAIN TANK FUEL FEED SYSTEM WHICH WHEN RELEASED COULD RESULT IN A RESTRICTION IN THE ENGINE FUEL SYSTEM

FAA AD 2009 - 05 -11 AS IN AD & SB

AS IN AD & SB

DGCA/BOEING-777/ 69 TO PREVENT AN UNANNUNCIATED LOSS OF CABIN PRESSURE.IF AN UNDETECTED LOSS OF PRESSURE EVENT WERE TO CAUSE AN UNSAFE PRESSURE IN THE CABIN,THE FLIGHT CREW COULD BECOME INCAPACITATED

FAA AD 2009 - 02 - 05 AS IN AD & SB

AS IN AD & SB

DGCA/BOEING-777/ 70R1 TO DETECT & CORRECT SCRIBE LINES,WHICH CAN DEVELOP INTO FATIGUE CRACKS IN THE SKIN.UNDETECTED FATIGUE CRACKS CAN GROW & CAUSE SUDDEN DECOMPRESSION OF THE AIRPLANE

FAA AD 2013 - 07 - 11 AS IN AD & SB

AS IN AD & SB

DGCA/BOEING-777/ 71 TO PREVENT A STANDBY STATIC INVERTER FROM OVERHEATINGWHICH COULDRESULT IN SMOKE IN THE FLIGHT DECK & CABIN & LOSS OF THE ELECTRICAL STANDBY POWER SYSTEM

FAA AD 2009 -26-03 AS IN AD & SB

AS IN AD & SB

DGCA/BOEING-777/ 72 TO PREVENT INADVERTENT ENGAGEMENT OF THE AUTOPILOT FAA AD 2010-06-09 AS IN AD & AS IN AD &


TY

DURING TAKE OFF ROLL,WHICH COULD RESULT IN REJECTED TAKE OFF AT ROTATION SPEED & PREVENT A LOWER THAN OPTIMAL CLIMB GRADIENT DURING TAKE OFF

SB SB

DGCA/BOEING-777/ 73 TO PREVENT LOSS OF LOWER WING SKIN LOAD PATH,WHICH COULD CAUSE CATASTROPHIC STRUCTURAL FAILURE OF THE WING


AS IN AD & SB

DGCA/BOEING-777/ 74 TO PREVENT SMOKE & FIRE IN THE COCKPIT WHICH COULD LEAD TO LOSS OF VISIBILITY AND INJURIES TO OR INCAPACITATION OF THE FLIGHTCREW


AS IN AD & SB

DGCA/BOEING-777/ 75 TO DETECT & CORRECT DAMAGE TO THE OUTBOARD SLAT MAIN TRACK SLAT CANS,WHICH CAN ALLOW FUEL LEAKAGE INTO THE FIXED WING LEADING EDGE


AS IN AD & SB

DGCA/BOEING-777/ 76 TO PREVENT FAILURE OF DEFECTIVE FLIGHT DECK DOOR WHICH COULD JEOPARADIZE FLIGHT SAFETY


AS IN AD & SB

DGCA/BOEING-777/ 77 TO PREVENT DAMAGE & POSSIBLE PUNCTURE OF THE OIL SCAVENGE TUBE & CONSEQUENT OIL LOSS,WHICH COULD RESULT IN AN IN FLIGHT SHUTDOWN OF THE ENGINE


AS IN AD & SB

DGCA/BOEING-777/ 78 TO DETECT & CORRECT IMPROPERLY APPLIED SEALANT ,WHICH COULD RESULT IN THE DISBONDING AND DISPLACING OF SEALANT AND CONSEQUENT FUEL LEAKS.


AS IN AD & SB

DGCA/BOEING-777/ 79R2 JOINT AIRCRAFT SYSTEM COMPONENT (JASC) /AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 57: WINGS


AS IN AD & SB

AS IN AD & SB

DGCA/BOEING-777/ 80 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 78: EXHAUST FAA AD 2010-26-01 AS IN AD & SB

AS IN AD & SB

DGCA/BOEING-777/ 81 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 55: STABILIZERS


AS IN AD & SB

DGCA/BOEING-777/ 82 JOINT AIRCRAFT SYSTEM COMPONENT (JASC )/ AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 28: FUEL


AS IN AD & SB

DGCA/BOEING-777/ 83R1 ATA 54, NACELLES/PYLONS, TO DETECT AND CORRECT HYDRAULIC FAA AD 2015-01-01 AS IN AD & AS IN AD &


TY

FLUID CONTAMINATION, WHICH CAN CAUSE CRACKING OF TITANIUM PARTS IN THE SYSTEM DISCONNECT ASSEMBLY; AND ALSO TO DETECT 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

amendment FAA AD 2011-09-11

SB SB

DGCA/BOEING-777/ 84 JOINT AIRCRAFT SYSTEM COMPONENT (JASC )/ AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 29: HYDRAULIC POWER:AND 24:ELECTRICAL POWER


AS IN AD & SB

DGCA/BOEING-777/ 85 TO ENSURE THAT FATIGUE CRACKING OF VARIOUS PRINCIPAL STRUCTURAL ELEMENTS (PSEs) IS DETECTED AND CORRECTED,SUCH FATIGUE CRACKING COULD ADVERSELY AFFECT THE STRUCTURAL INTEGRITY OF THESE AIRPLANES


AS IN AD & SB

DGCA/BOEING-777/ 86R1 TO DETECT AND CORRECT CORROSION ON BONDING JUMPERS INSTALLED ON THE FLIGHT CONTROL SURFACES, WHICH, IN THE EVENT OF A LIGHTNING STRIKE, COULD DAMAGE THE ACTUATOR 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

FAA AD 2014-11-03 AMENDMENT FAA AD 2012-08-13

AS IN AD & SB

AS IN AD & SB

DGCA/BOEING-777/ 87 TO DETECT AND CORRECT CRACKING IN THE WCS SPANWISE BEAMS,WHICH COULD RESULT IN REDUCED STRUCTURAL INTEGRITY OF THE WINGS


AS IN AD & SB

DGCA/BOEING-777/ 88 TO PREVENT AN INCORRECT EMERGENCY LANDING MLG BREAK-AWAY SEQUENCE,WHICH COULD RESULT IN PUNCTURING OF THE WING BOX AND CONSEQUENT FUEL LEAKS AND AN AIRPLANE FIRE


DGCA/BOEING-777/ 89 TO PREVENT A FRACTURED HORIZONTAL STABILIZER PIVOT PIN ,WHICH MAY CAUSE EXCESSIVE HORIZONTAL STABILIZER FREEPLAY AND STRUCTURAL DAMAGE SIGNIFICANT ENOUGH TO RESULT IN LOSS


AS IN AD & SB


TY

OF THE AIRPLANE

DGCA/BOEING-777/ 90 TO DETECT AND CORRECT FRACTURED AND MISSING LATCH PIN RETENTION BOLTS ,WHICH COULD RESULT IN POTENTIAL SEPERATION OF THE CARGO DOOR FROM THE AIRPLANE AND CATASTROPHIC DECOMPRESSION OF THE AIRPLANE


AS IN AD & SB

DGCA/BOEING-777/ 91R2 TO PREVENT STRUCTURAL DAMAGE TO THE SIDE AND DRAG BRACE LOCK ASSEMBLIES,WHICH COULD RESULT IN LANDING GEAR COLLAPSE DURING TOUCH DOWN ,ROLLOUT OR TAXI

FAA AD 2014-05-09 SUPERSEDURE FAA AD 2012-12-08

AS IN AD & SB

AS IN AD & SB

DGCA/BOEING-777/ 92 TO PREVENT THE FORWARD LOWERED CEILING PANELS AND SUPPORT STRUCTURE FROM BECOMING DISLODGED DURING A 9.0 G FORWARD LOAD AND CONSEQUENT INJURY TO PERSONNEL OR INTERFERENCE WITH AN EMERGENCY EVACUATION


AS IN AD & SB

DGCA/BOEING-777/ 93 TO PREVENT ELECTRICAL CURRENT FROM PASSING THROUGH THE LOW PRESSURE OXYGEN HOSE INTERNAL ANTI COLLAPSE SPRING WHICH CAN CAUSE THE LOW PRESSURE OXYGEN HOSE TO MELT OR BURN AND A CONSEQUENT OXYGEN FED FIRE IN THE FLIGHT COMPARTMENT


AS IN AD & SB

DGCA/BOEING-777/ 94 TO DETECT & CORRECT SUCH FATIGUE CRACKING,WHICH COULD GROW LARGE AND CAUSE SUDDEN DECOMPRESSION AND THE INABILITY TO SUSTAIN LIMIT FLIGHT & PRESSURE LOADS


AS IN AD & SB

DGCA/BOEING-777/ 95 TO ELIMINATE THRUST REVERSER THERMAL DAMAGE CAUSED BY EXCESSIVE HEAT DOWNSTREAM OF THE 8TH STAGE IP8 EXHAUST PORTS,WHICH COULD RESULT IN THRUST REVERSER STRUCTURAL FAILURE


AS IN AD & SB

DGCA/BOEING-777/ 96 TO DETECT & CORRECT CRACKING IN THE MLG CENTER AXLE AND SHOCK STRUT INNER CYLINDER LUGS (PIVOT JOINT ) WHICH COULD RESULT IN FRACTURE OF THE MLG PIVOT JOINT COMPONENTS AND CONSEQUEBT COLLAPSE OF THE MLG


AS IN AD & SB

DGCA/BOEING-777/ 97 TO PREVENT EXCESSIVE FREEPLAY IN THE RUDDER CONTROL SURFACE ,WHICH COULD CAUSE RUDDER VIBRATION,AND RESULT IN


AS IN AD & SB


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 CHAFING AND POTENTIAL ARCING AND CONSEQUENT FIRE IN SECTION 48 ( A FLAMMABLE FLUID LEAKAGE ZONE ) OR HEAT DAMAGE TO THE AUXILIARY POWER UNIT (APU) POWER FEEDER CABLE.


AS IN AD & SB

DGCA/BOEING-777/ 99 TO PREVENT ELECTRICAL CURRENT FROM FLOWING THROUGH A MOTOR OPERATED VALVE (MOV) ACTUATOR INTO A FUEL TANK,WHICH COULD CREATE A POTENTIAL IGNITION SOURCE INSIDE THE FUEL TANK.


AS IN AD & SB

DGCA/BOEING-777/ 100 TO PREVENT CONTACTOR FAILURES,WHICH COULD RESULT IN UNCONTAINED HOT DEBRIS FLOW DUE TO ELMS CONTACTOR BREAKDOWN,CONSEQUENT SMOKE & HEAT DAMAGE TO AIRPLANE


AS IN AD & SB

DGCA/BOEING-777/ 101 TO DETECT & CORRECT CORROSION IN THE PACKBOARD RELEASE MECHANISM WHICH COULD INTERFERE WITH ESCAPE SLIDE /RAFT DEPLOYMENT,PROHIBIT DOORS FRM OPENING IN THE ARMED MODE AND CAUSE CONSEQUENT DELAY AND INJURY DURING EVACUATION OF PASSENGERS


AS IN AD & SB

DGCA/BOEING-777/ 102 TO PREVENT THE OXYGEN SYSTEM FLEX LINE FROM SEPERATING RESULTING IN IMPROPER FLOW OF OXYGEN THROUGH THE PASSENGER MASKS AND INJURY TO PASSENGERS


AS IN AD & SB

DGCA/BOEING-777/ 103R1 TO DETECT AND CORRECT HYDRAULIC FLUID CONTAMINATION OF THE STRUT FORWARD DRY TO DETECT AND CORRECT HYDRAULIC FLUID CONTAMINATION OF THE STRUT FORWARD DRY BAY, WHICH 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

2014-20-10 AMENDMENT FAA AD 2013-11-14

AS IN AD & SB

AS IN AD & SB


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 THAT COULD RESULT IN LOSS OF CONTROLLABILITY OF THE AIRPLANE OR LANDING SHORT OF THE RUNWAY DURING LANDING


AS IN AD & SB

DGCA/BOEING-777 / 105 TO DETECT AND CORRECT CRACKING AND CORROSION IN THE FUSELAGE SKIN, WHICH COULD LEAD TO RAPID DECOMPRESSION AND LOSS OF STRUCTURAL INTEGRITY OF THE AIRPLANE


AS IN AD & SB

DGCA/BOEING-777 / 106 TO PREVENT ELECTRICAL CURRENT FROM PASSING THROUGH AN INTERNAL, ANTI-COLLAPSE SPRING OF THE LOW-PRESSURE OXYGEN HOSE WHICH CAN CAUSE THE LOW - PRESSURE OXYGEN HOSE TO MELT OR BURN AND LEAD TO AN OXYGEN - FED FIRE NEAR THE FLIGHT DECK


AS IN AD & SB

DGCA/BOEING-777 / 107 TO DETECT AND CORRECT FAILURE OF THE ENGINE FUEL SUCTION FEED OF THE FUEL SYSTEM, WHICH, IN THE EVENT OF TOTAL LOSS OF THE FUEL BOOST PUMPS, COULD RESULT IN DUAL ENGINE FLAMEOUT, INABILITY TO RESTART THE ENGINES, AND CONSEQUENT FORCED LANDING OF THE AIRPLANE


AS IN AD & SB

DGCA/BOEING-777 / 108R1 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 28, FUEL FAA AD 2019-16-13 AFFECTS FAA AD 2014-11-01

AS IN AD & SB

AS IN AD & SB

DGCA/BOEING-777 / 109 TO ENSURE THAT THE FLIGHTCREW IS ABLE TO TURN OFF ELECTRICAL POWER TO THE IFE SYSTEMS AND OTHER NON-ESSENTIAL ELECTRICAL SYSTEMS THROUGH ONE OR TWO SWITCHES IN THE FLIGHT DECK IN THE EVENT OF SMOKE OR FLAMES


AS IN AD & SB

DGCA/BOEING-777 / 110 TO PREVENT LOSS OF FLIGHT-CRITICAL INFORMATION DISPLAYED TO THE FLIGHTCREW DURING A CRITICAL PHASE OF FLIGHT, SUCH AS AN APPROACH OR TAKEOFF, WHICH COULD RESULT IN LOSS OF AIRPLANE CONTROL AT AN ALTITUDE INSUFFICIENT FOR RECOVERY, OR CONTROLLED FLIGHT


AS IN AD & SB


TY

INTO TERRAIN

DGCA/BOEING-777 / 111 TO PREVENT A DUAL PRS FAILURE THAT COULD CAUSE AN AUTOMATIC DISENGAGEMENT OF THE AUTOPILOT AND AUTOLAND, 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.


AS IN AD & SB

DGCA/BOEING-777 / 112 TO PREVENT BROKEN OR MIGRATED SPRING PINS OF THE GIRT BAR FLOOR FITTINGS, WHICH COULD RESULT IN IMPROPER DEPLOYMENT 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


AS IN AD & SB

DGCA/BOEING-777 / 113 TO PREVENT EXTENDED DRY RUNNING OF THE JETTISON FUEL PUMPS, WHICH CAN BE A POTENTIAL IGNITION SOURCE INSIDE THE MAIN FUEL TANKS, AND CONSEQUENT FUEL TANK FIRE OR EXPLOSION IN THE EVENT THAT THE JETTISON PUMP OVERHEATS OR HAS AN ELECTRICAL FAULT


AS IN AD & SB

DGCA/BOEING-777 / 114 TO DETECT AND CORRECT ROTARY ACTUATORS MADE WITH A MATERIAL HAVING POOR ACTUATOR GEAR WEAR CHARACTERISTICS, 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


AS IN AD & SB

DGCA/BOEING-777 / 115 TO DETECT AND CORRECT MISSING SEALANT FROM THE WING SKIN PANEL GAPS ABOVE THE UNDERWING FITTINGS, WHICH COULD 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


AS IN AD & SB

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 &


TY

FORWARD STRUT DRAIN LINES, WHICH COULD CAUSE FLAMMABLE 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.

SB SB

DGCA/BOEING-777 / 117 SUBJECT OF AD IS AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 78,ENGINE EXHAUST, WE ARE ISSUING THIS AD TO PREVENT 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


AS IN AD & SB

DGCA/BOEING 777/118 TO DETECT AND CORRECT FATIGUE CRACKING IN THE AFT WEBS OF THE RADIAL LAP SPLICES OF THE AFT PRESSURE BULKHEAD


AS IN AD & SB

DGCA/BOEING777/119 TO DETECT AND CORRECT FATIGUE CRACKING OF THE SKIN LAP SPLICES, AND CONSEQUENT RISK OF SUDDEN DECOMPRESSION AND THE INABILITY TO SUSTAIN LIMIT FLIGHT AND PRESSURE LOADS


DGCA/BOEING777/120 TO PREVENT FIRE AND SMOKE AT THE ENGINE AFT PYLON AREA IN THE EVENT OF A FUEL LEAK


AS IN AD & SB

DGCA/BOEING777/121 TO DETECT AND CORRECT FATIGUE CRACKING OF THE OUTER FLANGES OF THE LEFT AND RIGHT SIDE FORWARD OUTER CHORDS OF THE STA 2370 PIVOT BULKHEAD


AS IN AD & SB

DGCA/BOEING 777/122 TO DETECT AND CORRECT CRACKS AND HEAT DAMAGE TO THE STRUT AFT FAIRING LOWER SPAR WEB STRUCTURE

FAA AD 2016 – 10-02 AS IN AD & SB

AS IN AD & SB

DGCA/BOEING 777/123R1 TO PREVENT FUEL EXHAUSTION AND SUBSEQUENT POWER LOSS OF ALL ENGINES DUE TO LOSS OF CAPABILITY TO SCAVENGE FUEL IN THE CENTER FUEL TANK.

FAA AD 2018-14-08 SUPERSEDED FAA AD 2016 –11-03

AS IN AD & SB

AS IN AD & SB

DGCA/BOEING 777/124 TO DETECT AND CORRECT A DEGRADED T/R INNER WALL PANEL. A DEGRADED T/R INNER WALL PANEL

FAA AD 2016 – 11-16 AS IN AD & SB

AS IN AD & 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 &


TY

TURNNION PIN SB SB

DGCA/BOEING 777/126 ATA 35 OXYGEN,TO PREVENT ELECTRICAL CURRENT CURRENT FROM PASSING THROUGH THE LOW PRESSURE OXYGEN FLEX HOUSE IN THE GASEOUS PASSENGER OXYGEN SYSTEM.


AS IN AD & SB

DGCA/BOEING 777/127 TO PREVENT LOSS OF CONTROL OF BOTH THE LEFT AND RIGHT ENGINE FUEL SPAR VALVES DURING A SINGLE EVENT


AS IN AD & SB

DGCA/BOEING 777/128 TO PREVENT A BREACH IN THE ENGINE FIREWALL DUE TO A FAILED UPPER BIFURCATION FORWARD FIRE SEAL. A BREACH COULD DELAY OR PREVENT THE FIRE DETECTION AND SUPPRESSION SYSTEM FROM FUNCTIONING PROPERLY


AS IN AD & SB

DGCA/BOEING 777/129 TO PREVENT UNCOMMANDED CHANGES TO THE MCP SELECTED ALTITUDE; SUCH UNCOMMANDED CHANGES COULD RESULT IN INCORRECT SPATIAL SEPARATION BETWEEN AIRPLANES, MIDAIR COLLISION, OR CONTROLLED FLIGHT INTO TERRAIN.


AS IN AD & SB

DGCA/BOEING 777/130 TO DETECT AND CORRECT AN UNCONNECTED GALLEY TRIPOD MOUNT ASSEMBLY TO THE TIE RODS IN THE OVERHEAD SUPPORT STRUCTURE, 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.


AS IN AD & SB

DGCA/BOEING 777/131R1 TO DETECT AND CORRECT CRACKS IN THE UNDERWING LONGERONS, WHICH COULD RESULT IN FUEL LEAKAGE INTO THE FORWARD CARGO AREA AND CONSEQUENT INCREASED RISK OF A FIRE OR, IN A MORE SEVERE CASE, COULD ADVERSELY AFFECT THE STRUCTURAL INTEGRITY OF THE AIRPLANE.


AS IN AD & SB

AS IN AD & SB

DGCA/BOEING 777/132 TO DETECT AND CORRECT UNTREATED VACUUM WASTE SYSTEM SPILLS OR LEAKS, WHICH COULD CAUSE CORROSION OF THE AIRPLANE STRUCTURE, WHICH COULD LEAD TO FATIGUE CRACKS, AND COULD ULTIMATELY RESULT IN RAPID DECOMPRESSION AND LOSS OF STRUCTURAL INTEGRITY


AS IN AD & SB


TY

DGCA/BOEING 777/133 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 25, EQUIPMENT/FURNISHINGS- WATER CAN ENTER THE STEAM OVEN 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


AS IN AD & SB

DGCA/BOEING 777/134 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 25, EQUIPMENT/FURNISHINGS- TO ADDRESS BMS 8-39 FLEXIBLE 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.


AS IN AD & SB

DGCA/BOEING 777/135 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 78, ENGINE EXHAUST- TO ADDRESS DAMAGED WIRES, WHICH COULD RESULT IN IN-FLIGHT SHUTDOWN OF THE ENGINE, OR THE INABILITY TO PROPERLY CONTROL THRUST, AND CONSEQUENT REDUCED CONTROLLABILITY OF THE AIRPLANE.


AS IN AD & SB

DGCA/BOEING 777/136 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 28, FUEL- TO ADDRESS LATENT FAILURE OF THE FUEL SHUTOFF SPAR VALVE TO THE 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.


AS IN AD & SB

DGCA/BOEING 777/137 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 25, EQUIPMENT/FURNISHINGS- TO ADDRESS NON-COMPLIANT FLIGHT 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


AS IN AD & SB

DGCA/BOEING 777/138 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 25, EQUIPMENT/FURNISHINGS.


AS IN AD & SB

BOEING 777.pdf

Documents

Transcript of BOEING 777.pdf