DGCANO SUBJECT REFERENCE COMPLIANCE APPLICABILITY

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1 DGCA/BOEING 757/01 EVACUATION SLIDES FAA AD DGCA/BOEING 757/02 ESCAPE SLIDE RELEASE CABLE FAA AD R1 DGCA/BOEING 757/03 LEADING EDGE INSPECTION FAA AD DGCA/BOEING 757/04 TRAILING EDGE WEDGES INSPECTION FAA AD DGCA/BOEING 757/05 EMERGENCY POWER ASSIST CABLE FAA AD DGCA/BOEING 757/06 THRUST REVERSER SYSTEM FAA AD DGCA/BOEING 757/07 PASSENGER DOOR FAA AD DGCA/BOEING 757/08 WIRE TERMINAL ASSEMBLY FAA AD DGCA/BOEING 757/09 FIRE EXTINGUISHING AND SMOKE DETECTION SYSTEM FAA AD DGCA/BOEING 757/10 AUXILIARY POWER UNIT BATTERY GROUNDS FAA AD DGCA/BOEING 757/11 MIDSPAR FUSE PINS FAA AD DGCA/BOEING 757/12 ENGINE THRUST CONTROL CABLE SYSTEM FAA AD DGCA/BOEING 757/13 FORWARD TRUNNION SUPPORT FAA AD DGCA/BOEING 757/14 CARGO COMPARTMENTS FAA AD DGCA/BOEING 757/15 ENVIRONMENTAL CONTROL SYSTEM (ECS) FAA AD DGCA/BOEING 757/16 LOWER SPAR CHORD FAA AD DGCA/BOEING 757/17 MAIN LANDING GEAR TRUCK BEAM FAA AD DGCA/BOEING 757/18 PASSENGER OXYGEN SYSTEM FAA AD DGCA/BOEING 757/19 DGCA/BOEING 757/20 ELEVATOR POWER CONTROL ACTUATOR LOAD LOOP AND HINGE LINE RIGHT MAIN LANDING GEAR AND AUTO-SPEEDBRAKE CONTROL SYSTEM FAA AD FAA AD DGCA/BOEING 757/21 AIRPLANE FLIGHT MANUAL (AFM) FAA AD DGCA/BOEING 757/22 FORWARD AND AFT FRAMES FAA AD DGCA/BOEING 757/23 AIRPLANE FLIGHT MANUAL - FUEL LEVELS AND FUEL TANKS FAA AD DGCA/BOEING 757/24 OVERHEAD STOWAGE BIN(S) FAA AD DGCA/BOEING 757/25 TORQUE TUBE COUPLINGS FAA AD

2 DGCA/BOEING 757/26 NUMBER 3 LEFT AND RIGHT EMERGENCY EXIT DOORS FAA AD DGCA/BOEING 757/27R2 TO DETECT & CORRECT CRACKING OF THE FUSELAGE SKIN & BEAR STRAP AT THE FORWARD UPPER CORNER OF THE L1 ENTRY DOOR CUTOUT WHICH COULD RESULT IN REDUCED STRUCTURAL INTEGRITY OF THE L1 ENTRY DOOR FAA AD DGCA/BOEING 757/28 AIR DATA COMPUTER (ADC) SYSTEM FAA AD DGCA/BOEING 757/29 INTERCOSTALS THAT BACK UP THE DOOR STOPS AND HINGES AT DOOR 2 LEFT AND DOOR 2 RIGHT FAA AD DGCA/BOEING 757/30 HANGER ARM OF THE HYDRAULIC PUMP OF THE RAT FAA AD DGCA/BOEING 757/31 TO PREVENT SHIFTING OR UNRESTRAINED CARGO IN THE CARGO COMPARTMENT FAA AD DGCA/BOEING 757/32 WIRE BUNDLE CLAMP BRACKET FAA AD DGCA/BOEING 757/33 GUIDE ARM ASSEMBLY ON PASSENGER DOOR NUMBER 1 FAA AD DGCA/BOEING 757/34 TRAILING EDGE FLAP SYSTEM FAA AD DGCA/BOEING 757/35 HYDRAULIC LINES LOCATED IN THE NACELLE STRUTS FAA AD DGCA/BOEING 757/36 AIR CONDITIONING OVERHEAD DUCTS FAA AD DGCA/BOEING 757/37 SHIMS FAA AD R1 DGCA/BOEING 757/38 CABLE ASSEMBLY FOR THE LOWER ANTI-COLLISION LIGHT FAA AD DGCA/BOEING 757/39 MASTER DIM AND TEST SYSTEM CIRCUIT FAA AD DGCA/BOEING 757/40R1 ATA-57 WINGS; TO PREVENT DELAMINATION OF THE TRAILING EDGE SLAT WEDGES OF THE LEADING EDGE SLATS. THIS DELAMINATION COULD CAUSE LOSS OF PIECES OF THE TRAILING EDGE SLAT EDGE ASSEMBLIES DURING FLIGHT, REDUCTION OF MANEUVER AND STALL MARGINS, AND CONSEQUENT REDUCED CONTROLLABILITY OF THE AIRPLANE. FAA AD SUPERSEDED FAA AD DGCA/BOEING 757/41 AFT TORQUE BULKHEAD FAA AD DGCA/BOEING 757/42 FLIGHT DECK DOOR FAA AD

3 SUPERCEDES FAA AD DGCA/BOEING 757/43 CLOSET ASSEMBLY AND FORWARD PURSER WORK STATION FAA AD DGCA/BOEING 757/44 HORIZONTAL STABILIZER TRIM ACTUATOR (HSTA) FAA AD DGCA/BOEING 757/45 UPPER LINK FORWARD FUSE PINS FAA AD DGCA/BOEING 757/46 DRIP SHIELDS FAA AD DGCA/BOEING 757/47 PEGASUS FLIGHT MANAGEMENT COMPUTER (FMC) SYSTEM FAA AD DGCA/BOEING 757/48 LEFT AND RIGHT ENGINE-TO-WING AFT FAIRINGS FAA AD DGCA/BOEING 757/49 TRAILING EDGE FLAP TRANSMISSION ASSEMBLY FAA AD DGCA/BOEING 757/50 NACELLE STRUTS FAA AD DGCA/BOEING 757/51 AUXILIARY POWER UNIT (APU) BATTERY AND THE APU START TRANSFORMER RECTIFIER UNIT (TRU) FAA AD DGCA/BOEING 757/52 OVERHEAD DISTRIBUTION DUCTS FAA AD DGCA/BOEING 757/53 NACELLE STRUTS FAA AD DGCA/BOEING 757/54 POWER CONTROL UNITS (PCUS) FAA AD DGCA/BOEING 757/55 FLIGHT DECK FAA AD DGCA/BOEING 757/56 STRUT FITTING AND THE FORWARD ENGINE MOUNT ASSEMBLY FAA AD DGCA/BOEING 757/57R1 FATIGUE CRACKING OF PSES FAA AD SUPERSEDED FAA AD DGCA/BOEING 757/58 DGCA/BOEING 757/59 SPIRAL WIRE WRAPPING OF THE ELECTRICAL CABLES OF THE GALLEYS AND CLOSETS REWORKING THE SPAR BONDING PATH AND REAPPLYING SEALANT FAA AD FAA AD DGCA/BOEING 757/60 AUXILIARY FUEL SYSTEM FAA AD DGCA/BOEING 757/61R1 TO DETECT AND CORRECT PREMATURE FATIGUE CRACKING AT CERTAIN SKIN LAP SPLICE LOCATIONS OF THE FUSELAGE FAA AD SUPERSEDED FAA

4 DGCA/BOEING 757/62 DGCA/BOEING 757/63 DGCA/BOEING 757/64 TO PREVENT ESCAPE SLIDES FROM DISENGAGING FROM THE AIRPLANE DURING DEPLOYMENT OR IN USE TO PREVENT UNINTENDED ROLL OSCILLATIONS NEAR TOUCHDOWN TO PREVENT DETACHMENT OF THE SHOULDER RESTRAINT HARNESS DGCA/BOEING 757/65R1 TO PREVENT ARCING THAT COULD BE A POSSIBLE IGNITION SOURCE FOR LEAKED FLAMMABLE FLUIDS DGCA/BOEING 757/66 DGCA/BOEING 757/67 DGCA/BOEING 757/68 TO PREVENT FAILURE OF ACTIVATION MECHANISM OF CHEMICAL OXYGEN GENERATOR TO DETECT AND CORRECT CRACKS WHICH COULD GROW AND CAUSE RAPID DECOMPRESSION OF THE AIRPLANE TO ENSURE THERE IS SUFFICIENT FIRE SUPPRESSANT TO CONTROL A CARGO FIRE AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD DGCA/BOEING 757/69 SS AD DGCA/BOEING 757/70 DGCA/BOEING 757/71 DGCA/BOEING 757/72 TO ENSURE THAT CERTAIN LIGHTED PUSHBUTTON SWITCHES I THE FLIGHT COMPARTMENT DO NOT MALFUNCTION AND CAUSE THE FLIGHT CREW TO BE UNABLE TO CONTROL CRITICAL AIRPLANE SYSTEMS AND CONTINUE SAFE OPERATIONS TO DETECT AND CORRECT A WEAK BOND BETWEEN THE SKIN AND TEAR STRAP TO PREVENT ELECTRICAL ENERGY FROM LIGHTNING,HOT SHORTS OR FAULT CURRENT ENTERING THE FUEL TANK THROUGH THE ACTUATOR SHAFT DGCA/BOEING 757/73R1 TO DETECT AND CORRECT CRACKS, LOOSE AND BROKEN BOLTS AND SHIM MIGRATION IN THE JOINTS BETWEEN THE AFT TORQUE BULKHEAD AND THE STRUT-TO-DIAGONAL BRACE FITTINGS,WHICH COULD RESULT IN DAMAGE TO THE STRUT FAA AD FAA AD FAA AD FAA AD

5 DGCA/BOEING 757/74R1 TO PREVENT MALFUNCTION & THRUST LOSS ON BOTH ENGINES,WHICH COULD RESULT IN A FORCED OFF AIRPORT LANDING DGCA/BOEING 757/75 DGCA/BOEING 757/76 DGCA/BOEING 757/77 TO PREVENT FAILURE OF THE ANCHOR TAB OF THE BULKHEAD SEAL ASSEMBLY WHICH IN ICING CONDITIONS COULD RESULT IN INSUFFICIENT AIRFLOW TO THE WING TAI SYSTEM TO PREVENT THE IN LINE FLOW INDICATORS OF THE PASSENGER OXYGEN MASKS FROM FRACTURING & SEPARATING TO PREVENT CENTER TANK FUEL PUMP OPERATION WITH CONTINUOUS LOW PRESSURE DGCA/BOEING 757/78R1 TO PREVENT THE POTENTIAL FOR IGNITION SOURCES INSIDE FUEL TANKS CAUSED BY LATENT FAILURES, ALTERATIONS, REPAIRS, OR MAINTENANCE ACTIONS DGCA/BOEING 757/79R1 TO PREVENT FAILURE OF THE ATTACHMENT BOLTS AND CONSEQUENT SEPRATION OF A THRUST REVERSER FROM THE AIRPLANE DGCA/BOEING 757/80R1 TO PREVENT IMPROPERLY SEALED FASTENERS IN THE MAIN & CENTER FUEL TANKS FROM BECOMING AN IGNITION SOURCE DGCA/BOEING 757/81 TO PREVENT A FIRE NEAR A COMPOSITE DRAIN MAST & POSSIBLE DISRUPTION OF THE ELECTRICAL POWER SYSTEM DUE TO A LIGHTNING STRIKE ON A COMPOSITE DRAIN MAST DGCA/BOEING 757/82 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 DGCA/BOEING 757/83 DGCA/BOEING 757/84 TO PREVENT A SHORT CIRCUIT OF THE ELECTRICAL CONNECTOR FOR THE FUEL BOOST PUMP TO PREVENT THE CENTER FUEL TANK DESITOMETER FROM OVERHEATING & BECOMING A POTENTIAL IGNITION SOURCE INSIDE THE FUEL TANK WHICH IN COMBINATION WITH FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD

6 DGCA/BOEING 757/85 DGCA/BOEING 757/86 DGCA/BOEING 757/87 FLAMMABLE FUEL VAPOURS COULD RESULT IN A CENTER FUEL TANK EXPLOSION WITH FLAMMABLE FUEL VAPOURS TO PREVENT DAMAGE OF THE WIRING BUNDLE OF THE RIGHT RECIRCULATION FAN TO PREVENT A STANDBY STATIC INVERTER FROM OVERHEATING WHICH COULD RESULT IN SMOKE IN THE FLIGHT DECK & CABIN & LOSS OF THE TO PREVENT INADVERTENT ELECTRICAL CURRENT WHICH CAN CAUSE THE LOW PRESSURE FLEX HOSES USEDIN THE FLIGHTCREW AND SUPERNUMERARY OXYGEN SYSTEM TO MELT OR BURN DGCA/BOEING 757/88R1 TO PREVENT SMOKE & FIRE IN THE FLIGHT DECK WHICH CAN LEAD TO LOSS OF VISIBILITY AND INJURIES TO OR INCAPACITATION OF THE FLIGHTCREW DGCA/BOEING 757/89 DGCA/BOEING 757/90 DGCA/BOEING 757/91 TO PREVENT FAILURE OF DEFECTIVE FLIGHT DECK DOOR WHICH COULD JEOPARADIZE FLIGHT SAFETY AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 57:WINGS JOINT AIRCRAFT SYSTEM COMPONENT (JSAC) / AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 28: FUEL DGCA/BOEING 757/92R1 JOINT AIRCRAFT SYSTEM COMPONENT (JSAC) / AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 53: FUSELAGE DGCA/BOEING 757/93 DGCA/BOEING 757/94 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 32:LANDING GEAR TO PREVENT THE IN-FLIGHT LOSS OF THE OFF-WING ESCAPE SLIDE, WHICH COULD RESULT IN THE UNAVAILABILITY OF THE ESCAPE SLIDE DURING AN EMERGENCY EVACUATION FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD SUPERSEDED FAA AD FAA AD FAA AD DGCA/BOEING 757/95 TO DETECT AND CORRECT FRONT SPAR LOWER CHORD FAA AD

7 DGCA/BOEING 757/96 DGCA/BOEING 757/97 DGCA/BOEING 757/98 DGCA/BOEING 757/99 DGCA/BOEING 757/100 DGCA/BOEING 757/101 DGCA/BOEING 757/102 DGCA/BOEING 757/103 CRACKING AND CORROSION WHICH COULD GROW AND RESULT IN STRUCTURAL FAILURE OF THE SPAR 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 AND CONSEQUENT LOSS OF THE AIRPLANE TO PREVENT UNDETECTED FAILURE OF THE PRIMARY & SECONDARY LOAD PATHS FOR THE BALL SCREW IN THE HORIZONTAL STABILIZER,WHICH COULD LEAD TO LOSS OF CONTROL OF THE HORIZONTAL STABILIZER TO PREVENT POWER FROM BEING SUPPLIED TO PASSENGER SEATS WHEN THE ENTERTAINMENT CONTROL SWITCH IS IN OFF POSITION,WHICH COULD CAUSE AN ELECTRICAL SHOCK HAZARD RESULTING IN SERIOUS OR FATAL INJURY TO DETECT & CORRECT INCORRECTLY INSTALLED MAIN TRACK DOWNSTOP ASSEMBLIES,WHICH,WHEN THE SLAT IS RETRACTED,COULD CAUSE A PUCTURE IN THE SLAT TRACK HOUSING AND LEAD TO A FUEL LEAK AND POTENTIAL FIRE TO PREVENT SMOKE & FIRE IN THE FLIGHT DECK WHICH CAN LEAD TO LOSS OF VISIBILITY & INJURIES TO OR INCAPACITATION OF THE FLIGHTCREW TO DETECT & CORRECT DEFECTIVE SURFACES & INSUFFICIENT THICKNESS OF THE SECONDARY FUEL BARRIER WHICH COULD ALLOW LEAKS OR FUMES INTO THE PRESSURIZED CABIN TO PREVENT FATIGUE CRACKING IN PRIMARY STRUT STRUCTURE & CONSEQUENT REDUCED STRUCTURAL INTEGRITY OF THE STRUT FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD TO DETECT & CORRECT LOSS OF THE ENGINE FUEL SUCTION FEED FAA AD CAPABILITY OF THE FUEL SYSTEM,WHICH IN THE EVENT OF TOTAL

8 DGCA/BOEING 757/104 DGCA/BOEING 757/105 DGCA/BOEING 757/106 DGCA/BOEING 757/107 DGCA/BOEING 757/108 DGCA/BOEING 757/109 DGCA/BOEING 757/110 LOSS OF THE FUEL BOOST PUMPS COULD RESULT IN DUAL ENGINE FLAMEOUT,INABILITY TO RESTART THE ENGINES AND CONSEQUENT FORCED LANDING OF THE AIRPLANE TO PREVENT FOREIGN OBJECT PENETRATION OF THE FUEL TANK,WHICH COULD CAUSE A FUEL LEAK NEAR AN IGNITION SOURCE TO DETECT & CORRECT CRACKING OF THE FORWARD SUPPORT FITTING ASSEMBLY,WHICH COULD RESULT IN LOSS OF INBOARD FLAP CONTROL & SUBSEQUENT LOSS OF AIRPLANE CONTROL FAA AD FAA AD TO PREVENT DISCHARGE OF THE MAIN BATTERY,WHICH COULD FAA AD RESULT IN MULTIPLE SYSTEM DEGRADATION,REDUCED AIRPLANE CONTROLLABILITY,AND RUNWAY EXCURSION UPON LANDING TO PREVENT FRACTURE OF THE RUDDER PEDAL PUSHROD CONNECTING BOLTS DURING PEDAL USE, WHICH COULD RESULT IN LARGE INVOLUNTARY INPUTS TO THE RUDDER AND NOSE- WHEEL STEERING AND AN ASYMMETRIC APPLICATION OF BRAKING, IF PEDAL BRAKES ARE APPLIED, LEADING TO A RUNWAY EXCURSION TO PREVENT FATIGUE CRACKING IN PRIMARY STRUT STRUCTURE AND CONSEQUENT REDUCED STRUCTURAL INTEGRITY OF THE STRUT TO PREVENT THE FAILURE OF AIR INTAKE COWL COMPONENTS DUE TO CRACKING, WHICH COULD RESULT IN THE AIR INTAKE COWL SEPARATING FROM THE ENGINE AND STRIKING CRITICAL AIRPLANE CONTROL SURFACES THAT COULD RESULT IN A LOSS OF AIRPLANE CONTROL; SEVERE ENGINE DAMAGE, AND LOSS OF THRUST; OR LARGE PARTS STRIKING A PERSON OR PROPERTY ON THE GROUND TO PREVENT AN INOPERATIVE RAT, WHICH, FOLLOWING A DUAL ENGINE SHUTDOWN IN FLIGHT, WILL CAUSE LOSS OF ALL FAA AD FAA AD FAA AD FAA AD

9 DGCA/BOEING 757/111R1 DGCANO SUBJECT REFERENCE COMPLIANCE APPLICABILITY HYDRAULIC POWER TO THE PRIMARY FLIGHT CONTROLS, RESULTING IN SUBSEQUENT LOSS OF CONTROL OF THE AIRPLANE TO REDUCE THE CHANCE OF UNINTENDED LATERAL OSCILLATIONS NEAR TOUCHDOWN, WHICH COULD RESULT IN LOSS OF LATERAL CONTROL OF THE AIRPLANE, AND CONSEQUENT AIRPLANE DAMAGE OR INJURY TO FLIGHTCREW AND PASSENGERS FAA AD SUPERSEDED FAA AD DGCA/BOEING/757/112 (ATA) OF AMERICA CODE 28, TO DETECT AND CORRECT LATENT FAA AD FAILURES OF THE FUEL SHUTOFF VALVE TO THE ENGINE AND AUXILIARY POWER UNIT (APU), WHICH COULD RESULT IN THE INABILITY TO SHUT OFF FUEL TO THE ENGINE AND APU AND, IN CASE OF CERTAIN FIRES, AN UNCONTROLLABLE FIRE THAT COULD LEAD TO STRUCTURAL FAILURE. DGCA/BOEING/757/113 (ATA) OF AMERICA CODE 52, DOORS FAA AD DGCA/BOEING/757/114 ATA 52, Doors FAA AD DGCA/BOEING/757/115 ATA 11, PLACARD AND MARKINGS FAA AD DGCA/BOEING/757/116 ATA 53, FUSELAGE FAA AD DGCA/BOEING/757/117 ATA 28, FUEL FAA AD DGCA/BOEING/757/118 ATA 53, FUSELAGE FAA AD DGCA/BOEING/757/119 DGCA/BOEING/757/120 DGCA/BOEING/757/121 ATA 22, AUTO FLIGHT- TO PREVENT STABILIZER MISTRIM, WHICH COULD RESULT IN A HIGH-SPEED REJECTED TAKEOFF AND RUNWAY OVERRUN ATA 27, FLIGHT CONTROL- TO PREVENT AN UNCOMMAND EXTENSION OF MULTIPLE SPOILER PANELS ON ONE WING ATA 53, FUSELAGE- TO PREVENT FATIGUE CRACKING THAT COULD RESULT IN REDUCED STRUCTURAL INTEGRITY OF THE AIRPLANE FAA AD FAA AD FAA AD

10 DGCA/BOEING/757/122 THIS AD TO DETECT AND CORRECT CRACKING OF THE CAM FAA AD SUPPORT ASSEMBLIES OF THE MCD, WHICH COULD RESULT IN REDUCED STRUCTURAL INTEGRITY OF THE MCD AND CONSEQUENT RAPID DECOMPRESSION OF THE AIRPLANE. DGCA/BOEING-757/123 DGCA/BOEING-757/124 DGCA/BOEING-757/125 DGCA/BOEING-757/126 ATA-53 FUSELAGE; TO DETECT AND CORRECT SUCH CRACKS, FAA AD WHICH COULD RESULT IN THE CARGO DOOR OPENING DURING FLIGHT, AND RESULT IN RAPID DECOMPRESSION OF THE AIRPLANE AND THE INABILITY TO SUSTAIN LOADS REQUIRED FOR CONTINUED SAFE FLIGHT AND LOADING. ATA-52 DOORS; TO DETECT AND CORRECT DISCREPANCIES OF FAA AD THE MCD CAM LATCHES, LATCH PINS, AND LACH PIN CROSS BOLTS, WHICH, IF LEFT UNDETECTED, COULD REDUCE THE STRUCTURAL INTEGRITY OF THE MCD AND RESULT IN POTENTIAL LOSS OF THE MCD AND RAPID DECOMPRESSION OF THE AIRPLANE. ATA-53 FUSELAGE; TO DETECT AND CORRECT CRACKING OF THE FAA AD FUSELAGE FRAME AT STA 1681, WHICH COULD RESULT IN REDUCED STRUCTURAL INTEGRITY OF THE AIRPLANE. TO DETECT AND CORRECT SCRIBE LINE DAMAGE, FAILURE TO FAA AD DETECT AND COMPLETELY REMOVE SCRIBE LINES MAY LEAD TO FATIGUE CRACKING, RAPID DECOMPRESSION, AND INABILITY OF THE PRINCIPAL STRUCTURAL ELEMENT TO SUSTAIN LIMIT LOAD DGCA/BOEING-757/127 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 53, FAA AD FUSELAGE- TO PREVENT FATIGUE CRACKING AT THE ATTACHMENT POINTS OF THE SIDE PANEL-TO-FRAME ATTACHMENTS OF THE AFT CARGO COMPARTMENT, WHICH COULD RESULT IN REDUCED STRUCTURAL INTEGRITY OF THE BODY FRAMES, AND CONSEQUENT RAPID DECOMPRESSION OF

11 THE AIRPLANE

DGCANO SUBJECT REFERENCE COMPLIANCE APPLICABILITY DGCA/BOEING 767/01 EMERGENCY EVACUATION SLIDES FAA AD AS IN THE AD AS IN THE AD

DGCANO SUBJECT REFERENCE COMPLIANCE APPLICABILITY DGCA/BOEING 767/01 EMERGENCY EVACUATION SLIDES FAA AD AS IN THE AD AS IN THE AD DGCA/BOEING 767/01 EMERGENCY EVACUATION SLIDES FAA AD 86-06-06 DGCA/BOEING 767/02 PNEUMATIC SYSTEM CHECK VALVE INSPECTION FAA AD 90-12-02 DGCA/BOEING 767/03 FLAPS CARRIAGE SPINDLES FAA AD 90-17-19 DGCA/BOEING