FAA AD AS IN AD. AS IN AD.

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1 DGCA/B /1 DGCA/B /2 REPETIVE INSPECTION OF THE LATERAL FLIGHT CONTROL CABLES AND COMPONENTS IN THE WHEEL WELL TO DETECT & CORRECT FAILED CARRIAGE SPINDLES OR AFT LINKS OF THE INBOARD OR OUTWARD TRAILING EDGE FLAPS. FAA AD FAA AD DGCA/B /3 CORROSION PREVENTION & CONTROL. FAA AD R1 REVISES FAA AD & BOEING DOCUMENT DGCA/B /4 BRAKE WEAR LIMITS. FAA AD & BENDIX SB R2. DGCA/B /5 MID SPAR FUSE PIN INSPECTIONS. FAA AD AND BOEING SB R9 AND ASB A2150R1 DGCA/B /6 ENGINE SUPPORT STRUCTURE FAA AD AND BO SB R3 DT. NOV. 16 '1989. DGCA/B /7 DIAGONAL BRACE PIN INSPECTION. FAA AD AND BO. ASB A2153. DGCA/B /8 DGCA/B /9 DGCA/B /10 APU MODEL PW 901A- REMOVAL OF APU OIL STRAINER ELEMENT AND ìinspection GEARBOX CHIP DETECTORS AT REGULAR INTERVALS. INSTALLATION OF A SYSTEM TO PROVIDE FULL PITOT AND TOTAL AIR ìtemperature HEAT, AND REVISION OF AIRPLANE FLIGHT MANUAL. ULTRASONIC INSfPECTION OF INBOARD AND OUTBOARD MIDSPAR FITTING ìlugs OR SPRING AFT LUGS OF EACH STRUT AND ITS REPLACEMENT, IF ìnecessary. FAA AD AND PWC ASB A16159 R1 DT. MAY 12 '1993. FAA AD AND BOEING ASB A-2069 DT. JULY 15 '1993 FAA AD AND BOEING SB AND SB A AS IN A.D. & S.B. AS IN A.D. & S.B. AS IN A.D. & DOC. AS IN A.D. & DOC. AS IN A.D. & S.B. AS IN A.D. & S.B. AND SB. AND SB. AND SB. AND SB. AND SB. AND SB. AND ASB. AND ASB. AND SBs. AND ASB. AND ASB. AND SBs. DGCA/B /11 INSPECTIONS OF THE FIRE EXTINGUISHING FAA AD AND BOEING AND AND

2 DGCA/B /12 DISCHARGE TUBES AND SUPPORT ìclamps IN THE OUTBOARD ENGINES - REPAIR OR REPLACEMENT, IF ìnecessary. REVISION TO THE FAA APPROVED MAINTENANCE PROGRAM TO REQUIRE ìunrestricted OPENING OF THE PASSENGER SERVICE UNIT. DGCA/B /13 VHF RADIO COMMUNICATION SYSTEM - REPLACEMENT. DGCA/B /14 REVISION TO THE AIRPLANE FLIGHT MANUAL - TO IDENTIFY FUEL SYSTEM ìleaks. ASB A ASB. ASB. FAA AD AND BOEING TELEX M DT. JULY 20 '1993 AND TELEX. AND TELEX FAA AD R1.. FAA AD DGCA/B /15 ATA27- FLAP CONTROL UNIT INPUT WIRING. FAA AD AND BOEING ASB A-2346R1. DGCA/B /16 DGCA/B /17 DGCA/B /18 INSPECTION AND FUNCTIONAL TESTS OF THE THRUST REVERSER CONTROL ìand INDICATION SYSTEM AND THEIR CORRECTION. TO PREVENT DELAYED INFLATION OF EVACUATION RAMP/SLIDES. TO PREVENT POSSIBLE DEPLOYMENT OF A THRUST REVERSER IN FLIGHT. FAAAD AND BOE SB DT. NOV FAA AD SB 7A/ OR SB 7A/ REV2. FAA AD & ASB A128. AND ASB. AND ASB. AND SB. AND SB. & SB. & SB. & ASB. & ASB. DGCA/B /19 TO PREVENT LOSS OF AIR PRESSURE. FAA AD 95-O DGCA/B /20 DGCA/B /21 TO PREVENT EXPLOSIVE FAILURE OF THE WATER TANK TO ENSURE THAT THE FLIGHT CREW IS APPROPRIATELY AWARE OF THE ìconditions INVOLVING A SEVERELY CONTAMINATED AIRPLANE FUEL ìsystem. FAA AD FAA AD

3 DGCA/B /22 DGCA/B /23 TO PREVENT FAILURE OF THE DOOR EVACUATION SLIDE/RAFT TO DEPLOY ìproperly. TO PREVENT UNCOMMANDED ELEVATOR DEFLECTION WHICH COULD RESULT IN ìstructural DAMAGE AND REDUCED CONTROLLABILITY OF THE AIRPLANE. DGCA/B /24(R2) TO PREVENT RAPID DECOMPRESSION AND LOSS OF STRUCTURAL INTEGRITY OF THE AIRPLANE DUE TO DISBONDING AND SUBSEQUENT CRACKING OF THE SKIN PANELS. DGCA/B /25(R1) TO PREVENT INADVERTENT OPENING OR TEARING OF DECOMPRESSION PANEL DGCA/B /26 DGCA/B /27 DGCA/B /28 DGCA/B /29 FAA AD FAA AD & ASB A2348. FAA AD SUPERSEDES FAA AD FAA AD ,FAA AD & ASB A3064 & SUBSEQUENT REVISIONS TO THE SB. AS IN AS ASB & SUBSEQUENT REVISIONS TO THE SB. ASB & SUBSEQUENT REVISIONS TO THE AD. & ASB. & ASB.. ASB & SUBSEQUENT REVISIONS TO AD. TO PREVENT FAILURE OF THE ENGINE PYLON AND CONSEQUENT SEPARATION ìof THE ENGINE FROM THE WING DUE TO MIGRATION OF THE FUSE PINS ìinstalled AT THE MIDSPAR/SPRING BEAM FITTINGS OF THE PYLON. FAA AD R1.. TO PREVENT FUEL LEAKAGE AT THE FUEL BOOST AND OVERRIDE/JETTISON ìpumps WHICH COULD RESULT IN AFIRE AT THE LOCATION OF THE AFFECTED ìfuel PUMP. TO PREVENT LEAKAGE OF FUEL INTO THE FORWARD CARGO BAY TO DETECT & CORRECT CORROSION & CONSEQUENT FATIGUE CRACKING OF THE UPPER DECK FLOOR BEAM AT STATION 980. FAA AD FAA AD FAA AD DGCA/B /30 TO PREVENT UNCOMMANDED MOVEMENT OF FAA AD

4 DGCA/B /31 THE PILOTS SEAT DURING ACCELERATION & TAKEOFF OF THE AIRPLANE. TO PREVENT POTENTIAL WITH IN THE ELECTRICAL MOTOR ASEMBLY & THE SCAVENGE PUMP. FAA AD DGCA/B /32(R2) ATA 28 - FUEL FAA AD DGCA/B /33 DGCA/B /34 DGCA/B /35 DGCA/B /36 TO PREVENT ENGINE FLAME OUT AND CONSEQUENT SHUT DOWN DUE TO THE USE OF JP4 FUEL TO PREVENT APU FROM OVERHEAT AND HEAT DAMAGE. TO DETECT AND CORRECT FAULTY ILS RECEIVERS. TO DETECT & CORRECT FATIGUE CRACKING IN INTERNAL SKIN DOUBLER. FAA AD FAA AD FAA AD FAA AD DGCA/B /37 TO PREVENT LOSS OF RUDDER CONTROL. FAA AD DGCA/B /38 DGCA/B /39 DGCA/B /40 DGCA/B /41 DGCA/B /42 DGCA/B /43 TO PREVENT ACCELERATED FATIGUE CRACKING ON THE INNER CHECKS OF BS2598 BULKHEAD. HAZARDS OF DRY OPERATION OF OVERIDE /JETTISION PUMP OF CENTRE WING FUEL TANK. ONE TIME INSPECTION OF SEPARATION BETWEEN THE GALLEY POWER FEEDER & STATIC GROUND WIRING. TO PREVENT HIGH FUEL PRESSURE IN COMPONENT BETWEEN THE FUEL SHUT OFF SPAR. TO PREVENT UNCOMMANDED AUTOMATIC RETRACTION DURING TAKE OFF TO PREVENT PREVENT CONTACT BETWEEN THE ROTATING PADDLE WHEEL & STATIONARY END. FAA AD FAA AD & FAA AD FAA AD FAA AD FAA AD T

5 DGCA/B /44 DGCA/B /45 TO PREVENT FATIGUE CRACKING & LOOSE OR MISSING FASTENERS IN THE AFT TORQUE BULKHEADS OF THE OUTBOARD NACELLE STRUTS ONE TIME DETAILED VISUAL INSPECTION OF THE OUTBOARD SEQUENCE CARRIAGE ATTACHMENT FITTING DGCA/B /46(R1) TO DETECT AND CORRECT STRESS CORROSION OF THE STOP SUPPORT FITTINGS OF THE MAIN ENTRY DOORS DGCA/B /47 DGCA/B /48 DGCA/B /49 DGCA/B /50 DGCA/B /51 DGCA/B /52 DGCA/B /53 REPETITIVE DETAILED VISUAL INSPECTION AT BODY STATION 1241 REPETITIVE VISUAL INSPECTIONS FOR CRACKS & HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTIONS ON NO.2&3 ENGINE STRUTS FAA AD FAA AD FAA AD (FAA AD IS SUPERSEEDED) FAA AD FAA AD INSPECTION TO DETECT DISCREPANCIES OF THE CENTER FUEL TANK WIRING & COMPONENTS & ELECTRICAL BONDING TEST OF THE CENTER FUEL TANK COMPONENTS FAA AD R1 INSPECTIONS TO DETECT CRACKS IN THE EDGE FRAME WEB & DOUBLER OF THE NO.1 MAIN ENTRY DOOR CUT OUT TO PREVENT LOSS OF CONTROL OF THE CABIN PRESSURIZATION SYSTEM TO PREVENT AIRFRAME DAMAGE AS A RESULT OF BLUE ICE TO DETECT & CORRECT AN IMPROPERLY INSTALLED AILERON CABLE,WHICH COULD LEAD TO THE FAILURE OF THE AILERON CABLE & CONSEQUENT REDUCED LATERAL CONTROL CAPABILITY OF THE AIRPLANE FAA AD FAA AD FAA AD FAA AD

6 DGCA/B /54 DGCA/B /55 DGCA/B /56 TO PREVENT SEPARATION OF THE ENGINE FROM THE AIRPLANE IN THE EVENT OF A PRIMARY THRUST LINKAGE FAILURE TO DETECT & CORRECT DISBONDING OF THE DOUBLER ON THE UPPER RUDDER PEDAL COVER TO PREVENT CRACKING OF CORROSION OF THE FUSE PIN OF THE NACELLE STRUT DGCA/B /57 TO DETECT AND REPAIR CRACKING OF THE E-42 SATCOM RACK & ITS SUPPORTING STRUCTURE DGCA/B /58(R1) TO PREVENT CEILING PANELS FROM FALLING INTO THE PAX.AREA DGCA/B /59 DGCA/B /60 DGCA/B /61 DGCA/B /62 DGCA/B /63 DGCA/B /64 TO DETECT & CORRECT FAILURE OF THE MAWEA OR WEU POWER SUPPLIES TO PREVENT A REDUCTION IN MAXIMUM RUDDER & ELEVATOR SURFACE DEFLECTION TO PREVENT FAILURE OF THE THRUST REVERSER DEACTIVATION PINS TO PREVENT IMPROPER LATCHING OF LATCH PINS & THE MATING LATCH CAM ON THE CARGO DOOR TO DETECT & CORRECT CRACKING OF THE INNER CHORD & WEB OF THE BODY STATION 1265 EDGE FRAME BETWEEN STRINGERS 23 & 27 TO PREVENT CRACKS IN THE FIRE EXTINGUISHING DISCHARGE TUBES IN THE ENGINE STRUTS. DGCA/B /65(R4) TO DETECT AND CORRECT FATIGUE CRACKING OF THE BS 2598 BULKHEAD STRUCTURE, WHICH COULD ADVERSELY AFFECT THE STRUCTURAL INTEGRITY OF THE BULKHEAD AND THE FAA AD FAA AD FAA AD FAA AD & FAA AD FAA AD SUPERSEEDS FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD SUPERSEDURE FAA AD AMENDMENT FAA AD

7 DGCA/B /66 DGCA/B /67 DGCA/B /68 DGCA/B /69 DGCA/B /70 DGCA/B /71 DGCA/B /72 DGCA/B /73 DGCA/B /74 HORIZONTAL STABILIZER SUPPORT STRUCTURE, AND RESULT IN LOSS OF CONTROLLABILITY OF THE AIRPLANE. REPETITIVE INSPECTIONS OR CHECKS TO DETECT BROKEN H-11 STEEL BOLTS TO PREVENT CRACKING AND BUCKLING OF THE FRONT EDGE OF THE CREW REST HEAT EXCHANGER TO PREVENT A SLIDER DISENGAGING FROM THE AUXILIARY TRACK ASSEMBLY TO DETECT & CORRECT CRACKING IN THE AFT PRESSURE BULK HEAD TO PREVENT INADVERTENT DEPLOYMENT OF A THRUST REVERSER DURING FLIGHT TO PREVENT DAMAGE OF CERTAIN WIRE BUNDLES ROUTED TO THE FUEL TANK TRANSFER PUMPS IN THE HORIZONTAL STABILISER TO DETECT & CORRECT FATIGUE CRACKING OF CERTAIN AREAS OF THE FUSELAGE SKIN TO PREVENT HIGH VELOCITY SEPARATION OF A BRAKE SYSTEM ACCUMULATOR, PISTON OR END CAP TO DETECT & CORRECT FATIGUE CRACKING OF THE BULKHEAD WEB FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD DGCA/B /75 TO PREVENT LOSS OF MULTIPLE IRU'S INFLIGHT FAA AD DGCA/B /76 DGCA/B /77 TO PREVENT FATIGUE CRACKING OF THE FRAME WEB & DOUBLER OF THE FORWARD EDGE FRAME OF MAIN ENTRY DOOR No.1 TO DETECT & CORRECT FATIGUE CRACKING OF THE LONGERON SPLICE FITTINGS FAA AD FAA AD

8 DGCA/B /78 TO PREVENT REDUCED ACCELERATION & CLIMB PERFORMANCE FAA AD DGCA/B /79 TO PREVENT LOSS OF A FLAP TRANSMISSION FAA AD DGCA/B /80 TO FIND & FIX DISCREPANCIES OF THE INSTALLATION OF THE MID SPAR FUSE PINS OF THE INBOARD & OUTBOARD STRUT FAA AD DGCA/B /81 CHEMICAL OXYGEN GENERATORS FAA AD DGCA/B /82 DGCA/B /83 DGCA/B /84 TO DETECT AND CORRECT FATIGUE CRACKING OF NWW VERTICAL BEAMS AND FRAMES CANCELLED IN VIEW OF DGCA/B /65 (R1) VIDE LETTER NO 9-716/06 AI(2) DATED INPECTION OF WING LANDING GEAR OF TRUNION FOR CRACKS AND CORROSION FAA AD FAA AD DGCA/B /85(R3) TO DETECT & CORRECT SUCH CRACKS,WHICH COULD CAUSE DAMAGE TO THE ADJACENT BODY STRUCTURE & COULD RESULT IN DEPRESSURIZATION OF THE AIRPLANE IN FLIGHT FAA AD DGCA/B /86(R1) TO PREVENT CRACKING AND OTHER DAMAGE OF THE ACTUATOR ATTACH FITTING OF THE TRAILING EDGE FLAP DGCA/B /87 DGCA/B /88 DGCA/B /89 DGCA/B /90 TO REMOVE ELECTRICAL POWER FROM THE ENTIRE PASSENGER ENTERTAINMENT SYSTEM (PES) WHEN NECESSARY TO PREVENT REDUCED POWER TO THE HEATING SYSTEM OF THE PILOT STATIC PROBES. TO PREVENT LOOSE FASTENERS AND ASSOCIATED DAMAGE WHICH COULD RESULT IN SEPARETION OF REQUIRE TO PREVENT FAILURE OF THE CORE COWL LATCHES DURING AN ENGINE FIRE. FAA AD ( FAA AD IS SUPERSEEDED) FAA AD FAA AD FAA AD FAA AD

9 DGCA/B /91 TO DETECT AND CORRECT FATIGUE CRACKING OF THE SKIN DGCA/B /92(R1) TO PREVENT POTENTIAL IGNITION OF MOISTURE BARRIER COVER OF THE DRIP SHIELDS DGCA/B /93 DGCA/B /94 DGCA/B /95 DGCA/B /96 DGCA/B /97 DGCA/B /98 DGCA/B /99 DGCA/B /100 DGCA/B /101(R1) DGCA/B /102(R2) DGCA/B /103 TO PREVENT POTENTIAL IGNITION INSULATION IN THE (ECS) DUCTS PREVENTION OF UNRESPRAINED WOVEMENT OF PAX SEATS DURING HIGH FWAL DECCELERATION OF AEROPLANE TO PREVENT POTENTIAL FAILURE WITHIN THE ELECTRICAL MOTOR ASSEMBLY TO DETECT AND CORRECT FATIGUE CRACKING OF THE FULE ENGINE TO PREVENT LOSS OF RUDDER CONTROL DUE TO INPROPERLY LORQUED FASTERNESS TO PREVENT DAMAGE TO THE FLAP SYSTEM, ADJACENT SYSTEMS OR STRUCTURAL COMPONENTS TO PREVENT CHAFINING BETWEEN OXYGEN HOSE AND ELECTRICAKL WIRE BUNDLES TO PREVENT CHAFINING BURNING OF ELECTRICL WIRES TO PREVENT DETACHMENT OF THE SHOULDER RESTRAINT HARNESS TO DETECT AND CORRECT CRACKING IN THE OUTBOARD AND CENTER SECTION OF THE HORIZONTAL STABILIZER TO DETECT AND CORRECT CRACKED OR BROKEN ALLOY STEEL BOLTS ON BS1480 BULKHEAD FAA AD FAA AD ( FAA AD IS SUPERSEEDED) FAA AD FAA AD FAA AD FAA AD ASB IN AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD SUPERSEDED FAA AD (FAA AD'S AND ARE SUPERSEEDED) FAA AD

10 SPLICE DGCA/B /104R1 PROMPTED BY REPORTS OF CRACKS IN THE MAIN ENTRY DOOR NUMBER 1 UPPER MAIN SILL OUTER CHORD,ALONG THE BEND RADIUS OF THE CHORD ON SEVERAL AIRPLANES.TO DETECT & CORRECT SUCH CRACKS WHICH COULD RESULT IN LOSS OF STRUCTURAL INTEGRITY OF THE AIRPLANE DGCA/B /105 DGCA/B /106 T0 PREVENT FUEL VAPOURS FROM COMING INTO CONTACT WITH AN IGNITION SOURCE IN THE CENTER WING FUEL TANK TO FIND FIX CRACKING OF THE LOWER LOBE PANEL; OF THE FUSELAGE SKIN OF THE AFT CARGO BAY DGCA/B /107R1 TO DETECT AND CORRECT WEAR DAMAGE AND CRACKS OF THE FUSELAGE SKIN IN THE INTERFACE AREA OF THE VERTICAL STABILIZER SEAL AND FUSELAGE SKIN IN SECTIONS 46 & 48 WHICH COULD CAUSE IN -FLIGHT DEPRESSURIZATION OF THE AIRPLANE. DGCA/B /108 DGCA/B /109 DGCA/B /110 DGCA/B /111 TO PREVENT UNRESTRAINED DRIP SHIELDS FROM INTERFERING WITH RUDDER PEDAL MACHANISM TO FIND AND FIX POSSIBLE FATIGUE CRACKING OF THE FUSELAGE SKIN TO PREVENT ABNORMAL OPERATION OR RETRACTION OF A TRAILING` EDGE FLAP TO FIND AND FIX CRACKING OF THE SKIN, BEARSHAP AND SILL CHORD OF THE LOWER CARGODOR CUT OUT FAA AD EMERGENCY FAA ADs , & SUPERCEDED FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD

11 DGCA/B /112 DGCA/B /113 DGCA/B /114 DGCA/B /115 DGCA/B /116 DGCA/B /117 DGCA/B /118 DGCA/B /119 DGCA/B /120 DGCA/B /121 DGCA/B /122(R1) DGCA/B /123 DGCA/B /124 TO FIND AND FIX DISCREPANCIES OF THE RIVETS IN THE NOSE WHEEL WELL (NWW) PANELS CANCELLED IN VIEW OF DGCA/B /102 R1 VIDE LETTER NO 9-719/06 AI(2) DATED INSPECTION OF FLAP TRACK FORWARD END CLEVIS LUG TO PREVENT THE LOSS OF AN INBOARD TRAILING EDGE FOREFLAP DURING FLIGHT TO DETECT AND CORRECT FATIGUE CRACKING OF THE FRONT SPAR WEB OF THE WING TO PREVENT FAILURE OF THE STRUT AND SUBSEQUENT LOSS OF THE ENGINE TO PREVENT FAILURE OF THE STRUT AND SEPARATION OF AN ENGINE FROM THE AIRPLANE DUE TO FRACTURING OF THE FUSE PINS. INSPECTION OF UPPER AND LOWER SURFACE OF THE FORWARD LOWER SPAR INSPECTION OF INBOARD ENGINE STRUT TO DIAGONAL BRACE ATTTACH FITTING. CANCELLED IN VIEW OF DGCA/B /65 (R1) VIDE LETTER NO 9-716/06 AI(2) DATED TO PREVENT DETACHMENT OF THE SHOULDER RESTRAINT HARNESS OF THE ATTENDANT OR OBSERVER SEAT LOWER CARGO COMPARTMENT FIRE EXTINGUISHING SYSTEM - AFT CARGO DISCHARGE TUBE INSPECTION TO PREVENT AN UNCOMMANDED LEFT RUDDER HARDOVER IN THE EVENT OF CRACKING IN THE FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD & SB & SB BOEING SB A2270 AS IN SB AS IN SB FAA AD SUPERSEEDES FAA AD & SB & SB

12 DGCA/B /125 DGCA/B /126 DGCA/B /127 DGCA/B /128 DGCA/B /129 DGCA/B /130 DGCA/B /131 DGCA/B /132 YAW DAMPER ACTUATOR PORTION OF THE UPPER OR LOWER RUDDER PCMs TO PREVENT DEGRADATION / LOSS OF RUDDER FEEL AND CENTERING 17 FAA AD & SB & SB TO PREVENT LOSS OF A CARGO DOOR AND FAA AD & SB & SB CONSEQUENT RAPID DEPRESSURIZATION OF THE AIRPLANE. TO PREVENT LEAKAGE OF HYDRAULIC (FLAMMABLE) FLUID INTO AN ENGINE FIRE TO PREVENT FIRE EXTINGUISHING SYSTEM AND FUEL SYSTEM HOSE FAILURE DUE TO IMPROPERLY HEAT TREATED ALUMINIUM B- NUTS CANCELLEN IN VIEW OF DGCA/B /142 VIDE LETTER NO 9-716/03 DATED FAA AD & SB & SB FAA AD & SB & SB TO DETECT AND CORRECT FATIGUE CRACKS IN THE FUSELAGE SKIN AND FRAME SHEAR TIE ASSEMBLIES, WHICH COULD PROPAGATE AND RESULT IN POSSIBLE IN-FLIGHT DECOMPRESSION OF THE AIRPLANE FAA AD TO PREVENT POSSIBLE INTERFERENCE BETWEEN WIRE BUNDLE W4489 AND THE RECEPTACLE HOUSING OF THE CHILLER BOOST FAN, DRAIN TUBES AND ADJACENT STRUCTURE TO ENSURE THE CONTINUED STRUCTURAL INTEGRITY FAA AD FAA AD R1 REVISES FAA AD DGCA/B /133 TO PREVENT PASSENGER SERVICE UNIT ( PSU ) FAA AD & S B & SB PANELS FROM MOVING AND FALLING FROM PSU SUPPORT RAILS DGCA/B /134 TO PREVENT OVERHEATING OF THE HEATER FAA AD TAPE ON POTABLE WATER FILL AND DRAIN LINES SUPERSEDES FAA AD & SB & SB

13 DGCA/B /135 DGCA/B /136 DGCA/B /137 TO PREVENT A CHAFED HOLE IN THE FIRE EXTINGUISHING SYSTEM TUBE OF THE AFT CARGO COMPARTMENT TO ENSURE ADEQUATE ELECTRICAL BONDING BETWEEN THE PENETRATION FITTINGSOF THE HYDRAULIC HEAT EXCHANGER AND THE REAR SPARS OF THE FUEL TANKS TO PREVENT DAMAGE AND ARCING TO THE CONDUIT AND POWER FEEDER CABLES OF THE IDG 10 FAA AD FAA AD FAA AD DGCA/B /138 MODIFICATION OF AIR DATA COMPUTER (ADC) FAA AD DGCA/B /139 DGCA/B /140 DGCA/B /141(R1) DGCA/B /142 DGCA/B /143 DGCA/B /144 TO DETECT CORRECT FATIGUECRACKS IN THE SECTION 42 SKIN AT THE CUTOUT FOR THE GROUND EXHAUST VALVE OF THE ELECTRICAL EQUIPMENT INSPECTION OF THE FIRE EXTINGUISHER BOTTLES IN THE ENGINE AND THE APU, AND REPLACEMENT OF THE FIRE EXTINGUISHER BOTTLE. TO PREVENT FRACTURE OF THE OUTER CYLINDER OF THE WING LANDING GEAR TO DETECT AND CORRECT THE PROPAGATION OF FATIGUE CRACKS IN THE VICINITY OF OIL CANS ON THE WEB OF THE AFT PRESSURE BULKHEAD TO PREVENT MINERAL BUILD UP ON THE APU AND ENGINE FIRE SHUTOFF SWITCHES. TO PREVENT INADVERTENT COMMANDED SHUTDOWN OF THE ENGINE BLEED AIR DISTRIBUTION SYSTEM DUE TO AN ERRONEOUS FAA AD ASB A2340 FAA AD &ASB A2272 FAA AD ,FAA AD FAA AD CORRECTION 18TH MAY 2009 FAA AD &ASB747-26A2274 AS IN ASB & AS IN ASB & SB & ASB & ASB AS IN ASB & AS IN ASB & SB & ASB & ASB FAA AD

14 DGCA/B /145 DGCA/B /146(R3) DGCA/B /147 DGCA/B /148 DGCA/B /149 DGCA/B /150 DGCA/B /151 DGCA/B /152 ASCTU COMMAND TO PREVENT CRACKED/FRACTURED SIDE GUIDE SUPPORT FITTINGS IN THE LOWER LOBE CARGO COMPARTMENTS. TO PREVENT FATIGUE CRACKS IN THE TOP AND SIDE PANEL WEBS AND STIFFNESS OF THE NOSE WHEEL WELL (NWW). TO ENSURE THE STRUCTURAL INTEGRITY OF THE STRUT-TO-WING LOAD PATH AND PREVENT SEPERATION OF THE STRUT AND ENGINE FROM THE AIRPLANE FAA AD FAA AD (ORIGINAL AD , , ARE SUPERSEEDED) FAA AD TO PREVENT ARCING OR SPARKING AT THE INTERFACE BETWEEN THE BULKHEAD FITTINGS OF THE ENGINE FUEL FEED TUBE AND THE FRONT SPAR INSIDE THE FUEL TANK OF THE WINGS AND BETWEEN THE OVERWING FUEL FILL PORTS AND THE AIRPLANE STRUCTURE DURING A LIGHTNING STRIKE. FAA AD TO PREVENT DISCONNECTION OF AUTOLAND/ AUTOPILOT FUNCTIONS AND LOSS OF PRIMARY FLAPS CONTROL AND FLAPS INDICATION DISPLAY DUE TO DISENGAGEMENT OF ALL THREE FCU'S AT THE SAME TIME FAA AD TO PREVENT FATIGUE CRACKING OF THE FUSELAGE FRAME TO TENSION TIE JOINTS. TO FIND AND FIX FATIGUE CRACKING OF THE FUSELAGE FRAME TO ENSURE THAT THE GALLEY CART LIFT CAN BE SENT ONLY FROM THE DECK ON WHICH IT IS IN USE. FAA AD (BOEING SPL ATTENTION SB ) FAA AD (ASB A2505) & ASB & ASB FAA AD & ASB & ASB

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

16 DGCA/B /163 (DSB) OR UNDERWING MIDSPAR FITTING LOAD PATH TO DETECT AND CORRECT CORROSION, WHICH CAN PENETRATE THE THICKNESS OF THE SKIN AND CAUSE CRACKING AND RESULT IN RAPID DECOMPRESSION OF THE AIRPLANE DGCA/B /164R2 TO PREVENT TENSION TIES FROM BECOMING SEVERED OR DISCONNECTED FROM THE FRAMES,WHICH COULD LEAD TO REDUCED STRUCTURAL INTEGRITY AND SUDDEN DECOMPRESSION OF THE AIRPLANE IN FLIGHT DGCA/B /165R2 PROMPTED BY REPORTS OF CRACKS IN THE MAIN ENTRY DOOR NUMBER 1 UPPER MAIN SILL OUTER CHORD,ALONG THE BEND RADIUS OF THE CHORD ON SEVERAL AIRPLANES.TO DETECT & CORRECT SUCH CRACKS WHICH COULD RESULT IN LOSS OF STRUCTURAL INTEGRITY OF THE AIRPLANE DGCA/B /166R1 TO PREVENT FATIGUE CRACKING IN CERTAIN LAP JOINTS, WHICH COULD RESULT IN RAPID DEPRESSURIZATION OF THE AIRPLANE DGCA/B /167 TO DETECT AND CORRECT CRACKS IN THE SKIN, BEARSTRAP, AND SMALL STEEL DOUBLER ( IF INSTALLED) AT MAIN ENTRY DOORS NO 3. DGCA/B /168R1 TO DETECT AND CORRECT CRACKING OF THE TENSION TIES, SHEAR WEBS, AND FRAMES OF THE UPPER DECK WHICH COULD RESULT IN RAPID DECOMPRESSION & REDUCED STRUCTURAL INTEGRITY OF THE AIRPLANE DGCA/B /169 TO PREVENT FAILURE OF FLIGHT DECK ELECTRONIC EQUIPMENT FAA AD & SB & SB FAA AD AMENDMENT FAA AD & SB & SB FAA AD & SB & SB FAA AD & SB & SB FAA AD & SB & SB FAA AD SUPERSEDES FAA AD & SB & SB FAA AD & SB & SB

17 DGCA/B /170 (R1) DGCA/B /171 DGCA/B /172 DGCA/B /173 DGCA/B /174 DGCA/B /175 TO DETECT AND CORRECT FATIGUE CRACKING OF CERTAIN LOWER LOBE FUSELAGE FRAMES TO PREVENT AN UNDETECTED FAILURE OF THE PRIMARY LOAD PATH FOR THE BALLSCREW IN THE HORIZONTAL STABILIZER TO DETECT AND CORRECT CRACKING IN THE LONGERON EXTENSION FITTING TO ENSURE THAT THE MIDPIVOT BOLTS AND MIDPIVOT BOLT ACCESS DOORS ARE INSTALLED IN THE CORRECT POSITION FAA AD R1 & SB & SB FAA AD & SB & SB FAA AD & SB SUPERCEEDED FAA AD & SB FAA AD & SB & SB TO PREVENT FIRE PROPAGATION OR SMOKE IN THE CABIN AREA DUE TO ELECTRICAL ARCING OR SPARKING AND IGNITION OF THE SPIRAL WIRE WRAPPING FAA AD & SB & SB TO PREVENT FAILURE OF THE OXYGEN CYLINDER SUPPORT UNDER THE MOST CRITICAL FLIGHT LOAD CONDITIONS DGCA/B /176R1 TO DETECT AND CORRECT FATIGUE CRACKS THAT COULD EXTEND AND FULLY SEVER THE STATION 800 FRAME ASSEMBLY DGCA/B /177 DGCA/B /178 DGCA/B /179 TO PREVENT DETACHMENT OF THE CENTER OVERHEAD STOWAGE BINS DURING AN EXTREME FORWARD LOAD EVENT TO PREVENT AN INCREASED PRESSURE DROP ACROSS THE HUMIDIFIER TO DETECT AND CORRECT CRACKS IN THE OVERLAPPED SKIN PANELS IN THE FUSELAGE SKIN LAP JOINTS FAA AD R1 & SB & SB FAA AD SUPERSEDED FAA AD , FAA AD REPLACED BY & SB & SB FAA AD & SB & SB FAA AD & SB & SB FAA AD & SB & SB DGCA/B /180 TO DETECT AND CORRECT FATIGUE CRACKS AT FAA AD & SB & SB

18 DGCA/B /181 DGCA/B /182 DGCA/B /183 DGCA/B /184 DGCA/B /185 THE FASTENER ROWS OF THE FUSELAGE SKIN IN SECTION 41 TO DETECT AND CORRECT CRACKING OF BULKHEAD WEB AT MULTIPLE SITES ALONG THE RADIAL LAP SLICE TO DETECT AND CORRECT CRACKING OF THE CREASE BEAM AND ADJACENT STRUCTURE TO PREVENT LEAKAGE OF FUEL OR FUEL VAPORS INTO AREAS WHERE IGNITION SOURCE MAY BE PRESENT TO DETECT AND CORRECT CRACKING IN THE UPPER DECK FLOOR BEAM AT STATION 400 TO DETECT AND CORRECT CORROSION ON GIRT BAR SUPPORT FITTINGS, WHICH COULD RESULT IN SEPARATION OF THE ESCAPE SLIDES AT THE MAIN ENTRY DOORS DURING AN EMERGENCY. DGCA/B /186R1 TO PREVENT FATIGUE CRACKING OF THE TENSION TIES, WHICH COULD RESULT IN REDUCED STRUCTURAL INTEGRITY OF THE AIRPLANE AND RAPID DEPRESSURIZATION OF THE AIRPLANE DGCA/B /187R1 TO DETECT AND CORRECT CRACKING IN THE FAIL-SAFE INTERLAYER OF CERTAIN NO.2 AND NO.3 GLASS WINDOWS,WHICH COULD RESULT IN LOSS OF THE WINDOW AND CONSEQUENT RAPID LOSS OF CABIN PRESSURE DGCA/B /188 DGCA/B /189 TO DETECT AND CORRECT FATIGUE CRACKING OF THE FUSELAGE SKIN NEAR STRINGER 5 TO PREVENT ARCHING INSIDE THE FUEL TANKS IN THE EVENT OF LIGHTNING STRIKE OR HIGH- POWERED SHORT CIRCUIT FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD SUPERSEDUREFAA AD FAA AD FAA AD FAA AD

19 DGCA/B /190 DGCA/B / / / / / / / / /199 TO PREVENT INSUFFICIENT ELECTRICAL BONDING WHICH COULD RESULT IN A POTENTIAL OF IGNITION SOURCES INSIDE THE FUEL TANKS TO ENSURE THERE IS SUFFICIENT FIRE SUPPRESSANT TO CONTROL A CARGO FIRE TO DETECT AND CORRECT CRACKING IN THE STA 1241 BULKHEAD FITTINGS TO PREVENT THE IN LINE FLOW INDICATORS OF THE PASSENGER OXYGEN MASKS FROM FRACTURING AND SEPRATING TO PREVENT CRACKING AND BUCKLING OF THE FORWARD OR REAR HEAT EXCHANGER SHELL OF THE AIR DISTRIBUTION SYSTEM OF THE CREW REST AREA TO PREVENT DETACHMENT OF THE CENTER STOWAGE BINS OF THE ZONE E AT FORWARD LOAD LEVELS LESS THAN 9G DURING EMERGENCY LANDING TO DETECT AND CORRECT MIGRATED HINGE PINS AND DAMAGE FLIPPER DOORS FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD SSAD TO PREVENT FAILURE OF AN EVACUATION SYSTEM TO ENSURE THAT CERTAIN LIGHTED PUSHBUTTON SWITCHES IN THE FLIGHT COMPARTMENT DO NOT MALFUNCTION AND CAUSE THE FLIGHT CREW TO BE UNABLE TO CONTROL CRITICAL AIRPLANE SYSTEMS AND CONTINUE SAFE OPERATIONS FAA AD FAA AD

20 400/ / /202R1 400/ / / /206 TO DETECT AND CORRECT CRACKS AND BROKEN FASTNERS OF THE INBOARD AND OUTBOARD NACELLE STRUTS TO PREVENT A FRACTURED TRUNNION FORK ASSEMBLY WHICH COULD RESULT IN THE COLLAPSE OF A WING LANDING GEAR ON THE GROUND AND POSSIBLE DAMAGE TO HYD EQUIPMENT. TO PREVENT WATER FROM EXITING OVER THE EDGE OF THE EXISTING DRIP SHIELD AND CONTAMINATING ELECTRICAL COMPONENTS IN THE M826 CARDFILE, WHICH COULD RESULT IN AN ELECTRICAL SHORT AND POTENTIAL LOSS OF SEVERAL FUNCTIONS ESSENTIAL FOR SAFE FLIGHT TO PREVENT CRACKING IN THE FUESLAGE SKIN,WHICH COULD RESULT IN RAPID DECOMPRESSION & LOSS OF STRUCTURAL INTEGRITY OF THE AIRPLANE FAA AD FAA AD FAA AD SUPERSEDURE FAA AD FAA AD TO PREVENT THE POTENTIAL FOR IGNITION SOURCES INSIDE FUEL TANKS CAUSED BY LATENT FAILURES, ALTERATIONS, REPAIRS, OR MAINTENANCE ACTIONS FAA AD TO ENSURE FASTNERS IN THE SHEAR CLIP OF THE STUB FRAME TO AUXILIARY SILL JOINTS (LEFT AND RIGHT SIDES) ARE INSTALLED TO PREVENT INSUFFICIENT CLEARANCE BETWEEN THE WIRE BUNDLE AND HYDRAULIC TUBE THAT COULD LEAD TO CHAFING OF THE WIRE BUNDLE FAA AD FAA AD TO DETECT AND CORRECT BROKEN OR MISSIN FAA AD

21 400/207 FASTNERS IN THE HINGE SEGMENTS WITH A SINGLE FASTNER ROW WHICH COULD LEAD TO OPENING OF THE CARGO DOOR DURING FLIGHT 400/ / / / / /213R1 TO PREVENT LOSS OF IDUs DUE TO FAILURE OF ALL THREE ELECTRONIC FLIGHT INSTRUMENT SYSTEM/ENGINE INDICATING AND CREW ALERTING SYSTEM(EFIS/EICAS) INTERFACE UNITS (EIUs) FAA AD TO DETECT AND CORRECT FUESLAGE SKIN CRACKS AT FASTENER LOCATIONS ALONG THE SKIN TO STRINGER ATTACHMENTS TO PREVENT REDUCED STRUCTURAL INTEGRITY OF THE FUESLAGE. TO PREVENT LIGHTNING INDUCED ELECTRICAL ENERGY FROM ENTERING A RESERVE FUEL TANK THROUGH THE REFUEL VALVE,WHICH COULD RESULT IN A FUEL TANK EXPLOSION & CONSEQUENT LOSS OF AIRPLANE TO PREVENT A FIRE OR EXPLOSION IN THE FUEL TANK & CONSEQUENT LOSS OF THE AIRPLANE FAA AD FAA AD SUPERSEDES FAA AD & BOEING ASB A2312 LATEST REV. FAA AD FAA AD TO DETECT AND CORRECT FATIGUE CRACKING OF THE LOWER FORWARD CORNER REVEAL OF THE NUMBER 3 MAINENTRY DOORS (MEDS), WHICH COULD LEAD TO THE DOOR ESCAPE SLIDE DEPARTING THE AIRPLANE WHEN THE DOOR IS OPENED AND THE SLIDE IS DEPLOYED, AND CONSEQUENT INJURIES TO PASSENGERS AND CREW USING THE DOOR ESCAPE SLIDE DURING AN EMERGENCY EVACUATION FAA AD AMENDMENT FAA AD

22 400/ / / / / /219R1 400/ /221 HAZARDS POSED BY SKEWING & FAILED FLAPS FAA AD TO ENSURE THAT INSULATION BLANKETS CONSTRUCTED OF AN -26 ARE REMOVED FROM THE FUSELAGE.SUCH INSULATION BRACKETS COULD IGNITE & PROPOGATE A FIRE THAT IS THE RESULT OF ELECTRICAL ARCING OR SPARKING FAA AD TO PREVENT DAMAGE TO THE CONTROL SURFACE STRUCTURE DURING FLIGHT WHICH COULD RESULT IN LOSS OF CONTROL OF THE AIRPLANE TO DETECT & CORRECT CRACKS OR FRACTURES OF THE PRIMARY STRUCTURAL & FAIL SAFE LOAD PATHS OF THE INBOARD & OUTBOARD TRAILING EDGE FLAPS TO DETECT & CORRECT CRACKS IN THE UPPER LOBE DOUBLERS TO DETECT & CORRECT FATIGUE CRACKING IN CERTAIN UPPER CHORDS OF THE UPPER DECK FLOOR BEAM, WHICH COULD BECOME LARGE & CAUSE THE FLOOR BEAMS TO BECOME SEVERED & RESULT IN RAPID DECOMPRESSION OR REDUCED CONTROLLABILITY OF THE AIRPLANE FAA AD FAA AD FAA AD FAA AD TO DETECT & CORRECT FATIGUE CRACKING OF THE LONGERON,WHICH CAN PROPOGATE & CAUSE DAMAGE TO THE ADJACENT HORIZONTAL STABILIZER PIVOT BULKHEAD. FAA AD TO PREVENT AUTOMATIC RETRACTION OF THE LEADING EDGE FLAPS DURING TAKE OFF WHICH COULD RESULT IN REDUCED CLIMB PERFORMANCE & CONSEQUENT COLLISION FAA AD

23 400/ / / /225R1 400/ / /228 WITH TERRAIN & OBSTACLES OR FORCED LANDING OF THE AIRPLANE TO ENSURE THAT THE FLIGHTCREW IS ABLE TO TURN OFF ELECTRICAL POWER TO THE IFE SYSTEM AND OTHER NON ESSENTIAL PASSENGER CABIN SYSTEMS THROUGH UTILITY BUS SWITCHES IN THE FLIGHT COMPARTMENT IN THE EVENT OF SMOKE OR FUMES TO DETECT & CORRECT FRAME CRACKS,WHICH COULD RESULT IN CRACKING OF THE ADJACENT FUSELAGE SKIN & CONSEQUENT RAPID DECOMPRESSION OF THE AIRPLANE TO PREVENT A DECREASE OF THE AERODYNAMIC CONTROLLABILITY OF THE AIRPLANE WHICH COULD ADVERSELY AFFECT THE AIRPLANES CONTINUED SAFE FLIGHT & LANDING TO PREVENT INJURIES TO PERSONS & DAMAGE TO THE AIRPLANE AND EQUIPMENT TO DETECT & CORRECT MISSING FASTENERS AT THE STRINGER TO STRINGER CLIP JOINTS WHICH COULD RESULT IN SHEAR TIE & SKIN CRACKS & RAPID IN FLIGHT DECOMPRESSION OF THE AIRPLANE TO DETECT & CORRECT THE LOSS OF STRUCTURAL INTEGRITY OF THE FUSELAGE,WHICH COULD RESULT IN RAPID DEPRESSRIZATION OF THE AIRPLANE TO PREVENT A STANDBY STATIC INVERTER FROM OVERHEATING WHICH COULD RESULT IN SMOKE IN THE FLIGHT DECK & CABIN & LOSS OF THE ELECTRICAL STANDBY POWER SYSTEM FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD

24 400/ / / / / /234 TO PREVENT THE POTENTIAL FOR IGNITION SOURCES INSIDE FUEL TANKS CAUSED BY LATENT FAILURES, ALTERATIONS, REPAIRS, OR MAINTENANCE ACTIONS,WHICH,IN COMBINATION WITH FLAMMABLE FUEL VAPOURS,COULD RESULT IN A FUEL TANK EXPLOSION & CONSEQUENT LOSS OF THE AIRPLANE FAA AD R1 TO DETECT & CORRECT FATIGUE CRACKING AT MULTIPLE ADJACENT LOCATIONS IN THE SUBJECT AREAS,WHICH COULD CONNECT TO FORM LARGE CRACKS AND RESULT IN REDUCED STRUCTURAL INTEGRITY LEADING TO RAPID DECOMPRESSION AND CONSEQUENT LOSS OF CONTROL OF THE AIRPLANE TO DETECT & CORRECT SUCH CRACKING WHICH COULD GROW & RESULT IN A SEVERED INTERCOSTAL. TO PREVENT UNCOMMANDED OPERATION OF CERTAIN OVERRIDE/JETTISON PUMPS WHICH COULD CAUSE OVERHEAT,ELECTRICAL ARCS,OR FRICTIONAL SPARKS,AND COULD LEAD TO AN IGNITION SOURCE INSIDE A FUEL TANK TO DETECT & CORRECT CRACKS & FRACTURES OF THE NACELLE STRUT FRONT SPAR CHORD ASSEMBLY FAA AD FAA AD FAA AD FAA AD TO PREVENT DAMAGE TO THE FUEL PUMPS CAUSED BY ELECTRICAL ARCING THAT COULD INTRODUCE AN IGNITION SOURCE IN THE FUEL TANK WHICH IN COMBINATION WITH FLAMMABLE FUEL VAPOURS COULD RESULT IN A FUEL TANK EXPLOSION FAA AD

25 400/ / / / / / / / / / / /246 TO PREVENT FAILURE OF DEFECTIVE FLIGHT FAA AD DECK DOOR WHICH COULD JEOPARADIZE FLIGHT SAFETY TO PREVENT A POTENTIAL ELECTRICAL ARC FROM IGNITING THE BMS 8-39 POLYURETHANE FOAM INSULATION ON THE DUCT ASSEMBLIES OF THE ECS TO PREVENT INADVERTENT ELECTRICAL CURRENT,WHICH CAN CAUSE THE LOW PRESSURE FLEX HOSES OF THE CREW OXYGEN SYSTEM TO MELT OR BURN RESULTING IN OXYGEN SYSTEM LEAKAGE AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 52:DOORS AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 28:FUEL AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 53:FUSELAGE AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 28:FUEL AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 54:NACELLES/PYLONS AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 78:ENGINE EXHAUST FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD ATA 29 - HYDRAULIC POWER FAA AD ATA 25 - EQUIPMENT / FURNISHINGS FAA AD TO DETECT AND CORRECT SCRIBE LINES, WHICH CAN DEVELOP INTO FATIGUE CRACKS IN THE FAA AD

26 400/247R1 400/ / / /251 DGCA/B /252 SKIN AND CAUSE SUDDEN DECOMPRESSION OF THE AIRPLANE TO PREVENT FLAMMABLE FLUID FROM LEAKING ONTO THE ENGINE EXHAUST NOZZLE WHICH COULD RESULT IN A FIRE TO DETECT & CORRECT FRACTURED OR BROKEN LATCH PINS,WHICH COULD RESULT IN A FORWARD OR AFT LOWER LOBE CARGO DOOR OPENING AND DETACHING DURING FLIGHT AND CONSEQUENT RAPID DECOMPRESSION OF THE AIRPLANE TO PREVENT SMOKE & FIRE IN THE COCKPIT,WHICH COULD LEAD TO LOSS OF VISIBILITY,AND INJURIES TO OR INCAPACITATION OF THE FLIGHT CREW TO PREVENT WATER PENETRATION INTO THE MEC,WHICH COULD RESULT IN LOSS OF FLIGHT CRITICAL SYSTEMS TO PREVENT WATER FROM ENTERING THE MAIN EQUIPMENT CENTER,WHICH COULD RESULT IN AN ELCTRICAL SHORT AND POTENTIAL LOSS OF SEVERAL FUNCTIONS ESSENTIAL FOR SAFE FLIGHT FAA AD SUPERSEDED FAA AD FAA AD FAA AD FAA AD FAA AD TO DETECT AND CORRECT CORROSION AND SUBSEQUENT CRACKING IN THE OUTBOARD END FITTINGS,WHICH COULD RESULT IN SEPERATION OF THE FITTING AND DAMAGE TO ADJACENT FLIGHT CONTROL CABLES AND HYDRAULIC SYSTEMS AND COSEQUENT REDUCED CONTROLLABILITY OF THE AIRPLANE FAA AD DGCA/B /253R1 TO PREVENT COMPLETE FRACTURE OF THE FAA AD

27 CROWN FRAME ASSEMBLY AND CONSEQUENT DAMAGE TO THE SKIN AND IN FLIGHT DECOMPRESSION OF THE AIRPLANE SUPERSEDED FAA AD DGCA/B /254R2 TO PREVENT IDU MALFUNCTIONS & MODE CONTROL PANEL (MCP) MALFUNCTIONS,WHICH COULD AFFECT THE ABILITY OF THE FLIGHTCREW TO READ PRIMARY DISPLAYS FOR AIRPLANE ATTITUDE,ALTITUDE OR AIRSPEED AND CONSEQUENTLY REDUCE THE ABILITY OF THE FLIGHTCREW TO MAINTAIN CONTROL OF THE AIRPLANE FAA AD DGCA/B /255 DGCA/B /256 DGCA/B /257 TO PREVENT LOSS OF THE CARGO DOORS AND RAPID DEPRESSURIZATION OF THE AIRPLANE TO PREVENT AN IGNITION SOURCE,WHICH COULD RESULT IN AN OXYGEN LED FIRE OR AN INLET VALVE JAM IN A CREW OXYGEN MASK STOWAGE BOX UNIT TO DETECT & CORRECT LOSS OF THE ENGINE FUEL SUCTION FEED CAPABILITY OF THE FUEL SYSTEM,WHICH,IN THE EVENT OF TOTAL LOSS OF THE FUEL BOOST PUMPS,COULD RESULT IN MULTI ENGINE FLAMEOUT,INABILITY TO RESTART THE ENGINES DGCA/B /258R1 TO DETECT & CORRECT CRACKS IN THE LONGERON EXTENSION FITTINGS,WHICH CAN BECOME LARGE AND ADVERSELY AFFECTS THE STRUCTURAL INTEGRITY OF THE AIRPLANE DGCA/B /259 TO PREVENT A LATCH HOOK MOVING FROM CLOSED TO OPEN IN AN ESCAPE SLIDE/RAFT OR ESCAPE SLIDE, WHICH COULD RESULT IN THE ESCAPE SLIDE / RAFT OR ESCAPE SLIDE NOT FAA AD FAA AD FAA AD FAA AD amendment FAA AD FAA AD

28 DGCA/B /260 DGCA/B /261 DGCA/B /262 DGCA/B /263 DEPLOYING CORRECTLY IN AN EMERGENCY OR RELEASING /INFLATING INTO THE PASSENGER CABIN & CAUSING INJURY TO PASSENGERS & CREW TO PREVENT ERRONEOUS ACTIVATION OF THE CONTROL COLUMN SHAKER DURING TAKE OFF,WHICH COULD RESULT IN RUNWAY OVERRUN,FAILURE TO CLEAR TERRAIN OR OBSTACLES AFTER TAKE OFF,OR REDUCED CONTROLLABILITY OF THE AIRPLANE TO DETECT & CORRECT CRACKING OF THE SKIN AND BEAR STRAPS AT THE AFT UPPER CORNER OF THE MED 5 CUTOUT,WHICH COULD RESULT IN IN- FLIGHT DEPRESSURIZATION TO DETECT & CORRECT CRACKS IN THE SPLICE FITTING,SUPPORT FRAME,FLOOR SUPPORT,FORWARD & AFT INNER CHORDS,AND THE BULKHEAD UPPER & LOWER WEBS OF THE STA 2598 BULKHEAD,WHICH COULD ADVERSELY AFFECT THE STRUCTURAL INTEGRITY OF THE AIRPLANE FAA AD FAA AD FAA AD TO DETECT & CORRECT MISSING,OR INCORRECT FASTENERS,WHICH CAN LEAD TO CRACKING AND LOSS OF LOAD CARRYING CAPACITY,RESULTING IN A POSSIBLE DECOMPRESSION EVENT FAA AD DGCA/B /264R1 TO DETECT & CORRECT DEFECTIVE INBOARD ACTUATOR ATTACH FITTINGS WHICH,COMBINED WITH LOSS OF THE OUTBOARD ACTUATOR LOAD PATH,COULD RESULT IN UNCONTROLLED RETRACTION OF THE OUTBOARD FLAP,DAMAGE TO FLIGHT CONTROL SYSTEMS AND CONSEQUENT REDUCED FAA AD REPLACED BY FAA AD

29 DGCA/B /265 DGCA/B /266 DGCA/B /267 DGCA/B /268 DGCA/B /269 DGCA/B /270 DGCA/B /271 CONTROLLABILITY OF THE AIRPLANE TO DETECT & CORRECT FATIGUE CRACKS IN THE FUSELAGE SKIN THAT CAN PROPOGATE AND GROW,AND RESULT IN REDUCED STRUCTURAL INTEGRITY AND SUDDEN DECOMPRESSION OF THE AIRPLANE IN FLIGHT TO PREVENT WATER PENETRATION INTO THE MEC,WHICH COULD RESULT IN THE LOSS OF FLIGHT OF CRITICAL SYSTEMS TO PREVENT AN UNCOMMANDED IN-FLIGHT THRUST REVERSER DEPLOYMENT AND CONSEQUENT LOSS OF CONTROL OF THE AIRPLANE FAA AD FAA AD FAA AD TO PREVENT AN UNCOMMANDED THRUST REVERSER DEPLOYMENT DURING TAKEOFF OR IN FLIGHT RESULTING IN DECREASED AIRPLANE CONTROL AND PERFORMANCE, POSSIBLE RUNWAY EXCURSIONS, AND FAILURE TO CLIMB FAA AD TO DETECT AND CORRECT CHAFING OF THE APU POWER FEEDER CABLES WITHIN A FLAMMABLE FLUID LEAKAGE ZONE, WHICH, WITH ARCING, COULD RESULT IN FIRE AND STRUCTURAL DAMAGE TO DETECT AND CORRECT FATIGUE CRACKING OF THE UPPER DECK TENSION TIES. SEVERED OR DISCONNECTED TENSION TIES AT MULTIPLE LOCATIONS COULD RESULT IN RAPID DECOMPRESSION AND LOSS OF STRUCTURAL INTEGRITY OF THEAIRPLANE. TO PREVENT FOREIGN OBJECT PENETRATION OF THE FUEL TANK, WHICH COULD CAUSE A FUEL FAA AD FAA AD FAA AD

30 DGCA/B /272 DGCA/B /273 DGCA/B /274 DGCA/B /275 DGCA/B /276 LEAK NEAR AN IGNITION SOURCE (E.G., HOT BRAKES OR ENGINE EXHAUST NOZZLE), CONSEQUENTLY LEADING TO A FUEL-FED FIRE TO DETECT AND CORRECT SKIN CRACKING, WHICH CAN BECOME LARGE AND COULD ADVERSELY AFFECT THE STRUCTURAL INTEGRITY OF THE AIRPLANE TO PREVENT WATER PENETRATION INTO THE MEC, WHICH COULD RESULT IN AN ELECTRICAL SHORT AND POTENTIAL LOSS OF SEVERAL FUNCTIONS ESSENTIAL FOR SAFE FLIGHT TO PREVENT OVERHEATING OF THE AFT LOWER LOBE CARGO COMPARTMENT, WHERE, IF TEMPERATURE SENSITIVE CARGO IS PRESENT, THE RELEASE OF FLAMMABLE VAPORS COULD RESULT IN A FIRE OR EXPLOSION IF EXPOSED TO AN IGNITION SOURC TO PREVENT INTERMODAL CONTAINERS LOADED IN THE OFFSET METHOD FROM SHIFTING DURING FLIGHT GUST LOADS AND DAMAGING FUSELAGE FRAMES, WHICH COULD LEAD TO THE STRUCTURAL FAILURE OF THE AFT FUSELAGE IN FLIGHT, AND SUBSEQUENT IN-FLIGHT BREAKUP OF THE AIRPLANE. TO DETECT AND CORRECT HIDDEN CORROSION DUE TO COMPROMISED FILLET SEALS, WHICH CAN RESULT IN SKIN CRACKING AND CONSEQUENT LOSS OF CAPABILITY TO SUPPORT LIMIT LOADS FAA AD FAA AD FAA AD FAA AD FAA AD DGCA/B /277 TO DETECT AND CORRECT DEFECTIVE INBOARD FAA AD

31 DGCA/B /278 DGCA/B /279 DGCA/B /280 DGCA/B /281 DGCA/B /282 ACTUATOR ATTACH FITTINGS WHICH COMBINED WITH LOSS OF OUTBOARD ACTUATOR LOAD PATH TO DETECT AND CORRECT FATIGUE CRACKING IN CERTAIN LAP JOINTS, WHICH COULD RESULT IN RAPID DEPRESSURIZATION AND CONSEQUENT REDUED STRUCTURAL INTEGRITY OF THE AIRPLANE TO DETECT AND CORRECT CRACKING IN FUSELAGE TO DETECT AND CORRECT FUSELAGE SKIN DAMAGE OF THE DORSAL FAIRING AREA TO PREVENT FATIGUE CRACKING OF THE TENSION TIES, SHEAR WEBS AND FRAMES OF UPPER DECK TO DETECT FATIGUE CRACKING IN CERTAIN UPPER CHORDS OF THE UPPER DECK FLOOR BEAM DGCA/B /283 AIR TRANSPORT ASSOCIATION CHAPTER 53 FUSELAGE DGCA/B /284 AIR TRANSPORT ASSOCIATION CHAPTER 28, FUEL DGCA/B /285 DGCA/B /286 DGCA/B /287 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 53:FUSELAGE AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 54:NACELLES/PYLON FAA AD FAA AD FAA AD FAA-AD FAA-AD FAA AD FAA AD FAA AD FAA AD TO DETECT AND CORRECT CRACKING IN THE FAA AD FUSE PIN OF THE WING LANDING GEAR BEAM END FITTING. A BROKEN FUSE PIN WILL NOT SUPPORT THE WING LANDING GEAR BEAM, CAUSING DAMAGE TO THE SURROUNDING

32 DGCA/B /288 DGCA/B /289 DGCA/B /290 STRUCTURE, INCLUDING FLIGHT CONTROL CABLES AND HYDRAULIC SYSTEMS, WHICH COULD RESULT IN LOSS OF CONTROLLABILITY OF THE AIRPLANE. ATA-53, FUSELAGGE, TO DETECT AND CORRECT FAA AD CRACKS AND CORROSION ON THE CROWN SKIN INNER SURFACE. IF THE CRACKS OR CORROSION ARE NOT REPAIRED, THE CRACKS CAN RAPIDLY JOIN TOGETHER AND CAN CAUSE A SUDDEN DECOMPRESSION AND LOSS OF STRUCTURAL INTEGRITY OF THE AIRPLANE. ATA-57, WINGS, TO DETECT AND CORRECT FAA AD CRACKING IN THE FRONT SPAR WEB, WHICH COULD LEAD TO FUEL LEAKS AND A CONSEQUENT FIRE ATA 22, AUTO FLIGHT, TO PREVENT STABILIZER FAA AD MISTRIM, WHICH COULD RESULT IN A HIGH- SPEED REJECTED TAKEOFF AND RUNWAY OVERRUN, OR REDUCED CONTROLLABILITY OF THE AIRPLANE AFTER TAKEOFF DUE TO INSUFFICIENT PITCH CONTROL.