DGCANO SUBJECT REFERENCE COMPLIANCE APPLICABILIT Y (APU) OR ENGINE FIRE DETECTION SYSTEM TO DETECT A FIRE IN TIMELY MANNER

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1 DGCA/B ,-700,-800/1 DGCA/B ,-700,-800/2 DGCA/B737 -NG/ 3 DGCA/B ,-700,-800/4 DGCA/B ,-700,-800/5(R1) DGCA/B ,-700,-800/6 DGCA/B ,-700,-800/7 DGCA/B ,-700,-800/8 DGCA/B ,-700,-800/9 DGCA/B ,-700,-800/10 DGCA/B ,-700,-800/11 DGCA/B ,-700,-800/12 TO PREVENT FAILURE OF THE AUXILIAR POWER UNIT (APU) OR ENGINE FIRE DETECTION SSTEM TO DETECT A FIRE IN TIMEL MANNER TO PREVENT MAJOR FUEL LEAKAGEDUE TO EXCESSIVE WEAR OF THE QUICK DISCONNECT COUPLING TO PREVENT EXPOSURE OF THE LOWER SURFACE OF THE STRUT TO EXTREME HIGH TEMP,CREATION OF A SOURCE OF IGNITION & INCREASED RISK OF UNCONTROLLABLE FIRE & POSSIBLE FUEL TANK EXPLOSION REPETITIVE INSPECTION AND FUNCTIONAL TEST OF TRAILING EDGE FLAP LIMIT SWITCH TO PREVENT FAILURE OF SECONDAR SERVO VALVE SLIDE IN THE RUDDER PCU DUE TO CRACKING OF THE SLIDE AND CONSEQUENT RUDDER HARD OVER AND REDUCE CONTROLLABILIT OF THE AEROPLANE TO PREVENT OVERHEATING, MELTING, AND SUBSEQUENT FAILURE OF THE POWER FEEDER TERMINALS TO DETECT AND CORRECT IMPROPER GROUNDING OF THE SQUIB CIRCUIT TO PREVENT LOSS OF CONTROLLABILIT OF THE AIRPLANE DUE TO EXCESSIVE FREEPLA IN ELEVATOR TAB TO DETECT AN INCORRECTL INSTALLED UPPER DECOMPRESSION PANEL TO PREVENT WATER ACCUMULATION IN THE LOWER CORNERS OF THE FLIGHT DECK EMERGENC EXITS CANCELLED IN VIEW OF DGCA/B ,-700,-800/5, VIDE LETTER NO 9-749/04 AI(2) DATED TO PRENEVT ELECTRICAL ARCING DUE TO CHAFING BETWEEN CERTAIN HDRAULIC HOSES & ADJACENT WIRE FAA AD FAA AD FAA AD FAA AD ,FAA AD FAA AD FAA AD FAA AD & FAA AD FAA AD FAA AD FAA AD

2 BUNDLES DGCA/B ,-700,-800/13 TO PREVENT FAILURE OF THE KEEL BEAM STRUCTURE FAA AD & DGCA/B ,-700,-800/14 DGCA/B ,-700,-800/15 DGCA/B ,-700,-800/16 TO PREVENT LOSS OF CONTROL OF THE AIRPLANE DURING TAKEOFF & LANDING TO PREVENT LOSS OF COMMUNICATION BETWEEN THE FLIGHT CREW & atc TO PREVENT FAILURE OF THE SUPPLEMENTAL OXGEN SSTEM TO DELIVER OXGEN TO THE PAX & FLIGHT ATTENDANTS IN THE EVENT OF DECOMPRESSION DGCA/B ,-700,-800/17(R1) TO ENSURE THAT THE FLIGHT CREW IS ADVISED OF THE PROCEDURESNECESSAR TO ADDRESS A CONDITION INVOLVING A JAMMED OR RESTRICTED RUDDER DGCA/B ,-700,-800/18 DGCA/B ,-700,-800/19 DGCA/B ,-700,-800/20 DGCA/B ,-700,-800/21 TO PREVENT EXCESSIVE INFLIGHT VIBRATIONS OF THE ELEVATOR TAB TO DETECT & CORRECT CRACKING OF THE ELEVATOR HINGE PLATES TO PREVENT JAMMING, RESTRICTING OR BINDING OF THE ELEVATOR CONTROL SURFACES TO PREVENT EXCESSIVE FREEPLA IN THE TAB CONTROL MECHANISM FAA AD FAA AD FAA AD FAA AD ,FAA AD's & R1 FAA AD , & FAA AD FAA AD FAA AD DGCA/B ,-700,-800/22 TO PREVENT IGNITION OF FUEL VAPOUR - CENTER TANK. FAA AD DGCA/B ,-700,-800/23 CHEMICAL OXGEN GENERATOR FAA AD DGCA/B ,-700,-800/24 TO PREVENT SEVERE DAMAGE TO THE HORIZONTAL STABILIZER FAA AD & FAA

3 DGCA/B ,-700,-800/25 DGCA/B ,-700,-800/26 DGCA/B ,-700,-800/27 DGCA/B ,-700,-800/28 DGCA/B ,-700,-800/29 DGCA/B ,-700,-800/30 DGCA/B ,-700,-800/31 DGCA/B ,-700,-800/32 DGCA/B ,700,800/33 DGCA/B737,600,700,800/34 DGCA/B ,700,800/35 DGCA/B ,700,800/36 DGCA/B ,700,800/37 TO PREVENT FATIGUE CRACKING ALONG THE BULKHEAD TO FUSELAGE ATTACHMENTS INSPECTION/ REPLACEMENT OF MOTOR OPERATED HDRAULIC SHUT OFF VALVES TO PREVENT FAILURE OF AN ESCAPE SLIDE TO DEPLO OR INFLATE CORRECTL TO PREVENT INABILIT TO SHUT OFF THE FLOW OF FUEL TO AN ENGINE AFTER UNCONTAINED ENGINE FAILURE TO FIND & FIX DAMAGE OF THE AFT PRESSURE BULKHEAD AT BOD STATION 1016 INSPECTION OF WIRE BUNDLES IN THE MWW TO DETECT CHAFFING OR DAMAGE PREVENTION OF UNRESTRAINED MOVEMENT OF PAX SEATS DURING HIGH FWD DECCELERATION OF AEROPLANE TO PREVENT LOSS OF FREE MOVEMENT OF THE RUDDER PEDALS. TO PREVENT JAMMING OF THE ELEVATOR FLIGHT CONTROLS TO PREVENT THE ACCUMULATION OF FLUID OR RESIDUE IN THE ELEVATOR BALANCE BAS TO PREVENT ICE FROM BLOCKING THE PILOT TUBE THAT PROVIDES AIRSPEED DATA TO PREVENT REDUCED RUDDER PEDAL FEEL AND CENTERING FORCE TO PREVENT FUEL VAPORS FROM COMING IN TO CONTACT WITH ANIGNITION SOURCE IN THE CENTER EMERGENC AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD EMERGENC FAA ADs &

4 DGCA/B737-NG / 38 (R1) WING FUEL TANK ) TO PREVENT CORROSION AND SUBSEQUENT MOISTURE INGRESS INTO THE ELECTRICAL CONNECTORS FAA AD ( FAA AD IS REPLACED) DGCA/B ,700,800/39 TO PREVENT OPERATION WITH FAILED FCMs FAA AD R1 DGCA/B ,700,800/40(R1) DGCA/B /41 DGCA/B ,-700,-800/42 DGCA/B737- NG/43R1 DGCA/B737-NG / 44 DGCA/B ,700,800/45R1 DGCA/B ,700,800/46 DGCA / B737-NG / 47 TO PREVENT AN UNCOMMANDED RUDDER HARDOVER EVENT TO PREVENT FLUID CONTAMINATION INSIDE THE FUELLING FLOAT SWITCH TO PREVENT SEVERE VIBRATION OF THE ELEVATOR AND ELEVATOR TAB ASSEMBL TO PREVENT INCREASED STRUCTURAL LOADS ON THE AFT ENGINE MOUNT,WHICH COULD RESULT IN FAILURE OF THE AFT ENGINE MOUNT TO PREVENT INADVERTENT RELEASE OF THE DECOMPRESSION LATCH AND CONSEQUENT OPENING OF THE DECOMPRESSION PANEL IN THE FLIGHT DECK DOOR.. TO PREVENT FAILURE OF THE FLIGHT CREW TO RECOGNIZE AND REACT TO A VALID CABIN ALTITUDE WARNING HORN WHICH COULD RESULT IN INCAPACITATION OF THE FLIGHT CREW DUE TO HPOXIA TO PREVENT A REDUCTION IN FLIGHT CREW VISIBILIT DUE TO STALLED WIPER MOTORS TO PREVENT FIRE EXTINGUISHING SSTEM AND FUEL SSTEM HOSE FAILURE DUE TO IMPROPERL HEAT TREATED ALUMINIUM B-NUTS FAA AD ,FAA AD R1 FAA AD FAA AD FAA AD FAA AD SUPERCEDES FAA AD FAA AD FAA AD FAA AD

5 DGCA / B737-NG / 48 DGCA / B737-NG / 49 DGCA / B737-NG / 50R2 DGCA / B737-NG / 51 DGCA / B737-NG / 52 TO PREVENT A SHORT CIRCUIT IN A VDU CONNECTOR AND CONSEQUENT ARCING TO PREVENT ARCING AND SUBSEQUENT LOSS OF ELECTRICAL POWER TO THE MAIN FUEL TANK AFT BOOST PUMPS TO PREVENT PREMATURE FAILURE OF THE ATTACH PINS, WHICH COULD CAUSE REDUCED STRUCTURAL INTEGRIT OF THE HORIZONTAL STABILIZER TO FUSELAGE ATTACHMENT, RESULTING IN LOSS OF CONTROL OF THE AIRPLANE. TO PREVENT A MALFUCTION OF THE AURAL WARNING FOR THE LANDING GEAR TO PREVENT OVERHEATING OF THE ELECTRICAL CONNECTOR OF THE SCU DGCA / B737-NG / 53 CANCELLED CANCELLED VIDE LETTER 9-749/04 AI (2) DATED DGCA / B737-NG / 54 (R1) DGCA / B737-NG / 55 DGCA / B737-NG / 56 DGCA / B737-NG / 57 DGCA / B737-NG / 58 REPLACING THE BRACKET FOR WIRE BUNDLES OF THE FUEL QUANTIT INDICATING SSTEM. TO PREVENT HIGH ELECTRICAL RESISTANCE IN THE SQUIB FIRING CIRCUIT, WHICH COULD RESULT IN INSUFFICIENT ELECTRICAL CURRENT TO FIRE THE FIRE EXTINGUISHER BOTTLE SQUIB AND DISCHARGE THE FIRE EXTINGUISHING AGENT FAA AD ALERT SB 737- AS IN ALERT 28A1148 & FAA AD SB FAA AD SUPERSEDURE FAA AD FAA AD FAA AD FAA AD FAA AD & ASB737-26A1118 TO PREVENT FLAMMABLE FLUID IN THE UPPER OR REAR FAA AD PLON AREAS FROM LEAKING PAST UNSEALED AREAS AND 27 ONTO A HOT ENGINE NOZZLE. TO DETECT AND CORRECT PREMATURE FATIGUE CRACKING AT CERTAIN LAP SPLICE LOCATIONS. TO DETECT AND CORRECT FATIGUE CRACKS IN THE WEBS OF THE AFT PRESSURE BULKHEAD. FAA AD FAA AD AS IN SB & AS IN ASB AS IN ALERT SB AS IN SB & AS IN ASB

6 DGCA / B737-NG / 59R1 DGCA / B737-NG / 60 DGCA / B737-NG / 61 DGCA / B737-NG / 62 TO DETECT & CORRECT AN UNSAFE CONDITION ASSOCIATED WITH ERRONEOUS OUTPUT FROM A RADIO ALTIMETER CHANNEL,WHICH COULD RESULT IN PREMATURE AUTO THROTTLE LANDING FLARE RETARD AND THE LOSS OF AUTOMATIC SPEED CONTROL & CONSEQUENT LOSS OF CONTROL OF THE AIRPLANE TO PREVENT FLAMMABLE FLUID (SUCH AS FUEL OR HDRAULIC FLUID) FROM LEAKING ONTO A HOT ENGINE EXHAUST NOZZLE OR INTO THE ENGINE CORE FIRE ZONE TO PREVENT FUEL OR VAPORS FROM LEAKING INTO THE CARGO OR PASSENGER COMPARTMENTS. TO PREVENT THE FMC FROM DISPLAING THE INCORRECT ACTUAL NAVIGATIONAL PERFORMANCE VALUE TO THE FLIGHT CREW FAA AD FAA AD FAA AD FAA AD DGCA / B737-NG / 63 TO DETECT AND CORRECT FATIGUE CRACKS FAA AD DGCA / B737-NG / 64 DGCA / B737-NG / 65 DGCA / B737-NG / 66(R1) TO PREVENT CHAFED WIRE BUNDLES NEAR THE CENTER FUEL TANK TO DETECT AND CORRECT CHAFING OF THE WIRE BEHIND THE P15 REFUEL PANEL T0 PREVENT INADEQUATE FASTENER CLAMP-UP, WHICH COULD RESULT IN CRACKING OF THE FASTENER HOLES. FAA AD FAA AD FAA AD R1 DGCA / B737-NG / 67(R1) TO PREVENT CRACKING OF THE EXISTING SPLICE FITTING FAA AD SUPERCEDES FAA AD DGCA / B737-NG / 68 TO PREVENT LOSS OF ELEVATOR CONTROL AND CONSEQUENT REDUCED CONTROLLABILIT OF THE AIRPLANE FAA AD DGCA / B737-NG/ 69 TO PREVENT DRAIN BLOKAGE B DEBRIS FAA AD

7 DGCA / B737-NG/ 70 DGCA / B737-NG/ 71 DGCA / B737-NG/ 72 DGCA / B737-NG/ 73R1 DGCA / B737-NG/ 74 DGCA / B737-NG/ 75 DGCA / B737-NG/ 76 DGCA / B737-NG/ 77 DGCA / B737-NG/ 78 DGCA / B737-NG/ 79 TO PREVENT WIRE BUNDLES FROM CONTACTING THE OVERHEAD DRIPSHIELD PANEL AND MODULES IN THE P5 OVERHEAD PANEL TO PREVENT FIRE PROPAGATION OR SMOKE IN THE CABIN AREA DUE TO ELECTRICAL ARCING OR SPARKING AND IGNITION OF THE SPIRAL WIRE WRAPPING TO PREVENT EXPOSED WIRES THAT COULD PROVIDE AN IGNITION SOURCE IN A FLAMMABLE LEAKAGE ZONE TO PREVENT FAILURE OF THE FLIGHT CREW TO RECOGNIZE AND REACT TO A VALID CABIN ALTITUDE WARNING HORN WHICH COULD RESULT IN INCAPACITATION OF THE FLIGHT CREW DUE TO HPOXIA TO PREVENT A SINGLE FAULT FAILURE IN FLIGHT FROM SIMULATING A TEST CONDITION AND SHOWING TEST PATTERNS INSTEAD OF THE SELECTED RADIO FREQUENCIES ON THE COMMUNICATION PANELS TO DETECT AND CORRECT CRACKING OF THE INTERCOSTALS LOCATED ABOVE THE CUTOUT FOR THE FORWARD AIRSTAIR DOOR TO PREVENT EXCESSIVE VIBRATION OF THE AIRFRAME DURING FLIGHT TO PREVENT FAILURE OF ONE OF THE TWO INPUT CONTROL ROD OF THE MAIN RUDDER POWER CONTROL UNIT TO PREVENT ARCING OR SPARKING IN THE FUEL TANK IN THE EVENT OF A LIGHTINING STRIKE INSPECTION OF SPOILERS AFTER EVER LANDING AND REJECTED TAKEOFF MANEUVERS 04 FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD SUPERSEDES FAA AD

8 DGCA/B737-NG/ 80 DGCA/B737-NG/ 81R1 DGCA/B737-NG/ 82 DGCA/ B 737-NG/83 TO PREVENT FAILURE OF ACTIVATION MECHANISM OF CHEMICAL OXGEN GENERATOR 52 SUPERCEDES FAA EAD FAA AD TO PREVENT LOOSE OR MISSING PARTS FROM THE MAIN FAA SLAT TRACK DOWNSTOP ASSEMBLIES FROM FALLING INTO SUPERCEDES FAA THE SLAT CAN AND CAUSING A PUNCTURE,WHICH COULD EAD RESULT IN A FUEL LEAK AND CONSEQUENT FIRE TO PREVENT CORROSION DAMAGE DUE TO MISSING OR INSUFFICIENT FILLET SEALANT TO DETECT AND CORRECT OIL CAN CONDITIONS,BULGES OR PREVIOUS REPAIRS IN THE AFT PRESSURE BULKHEAD FAA AD FAA AD DGCA/ B 737-NG/84 SS AD DGCA/ B 737-NG/85R1 DGCA/ B 737-NG/86 DGCA/ B 737-NG/87 DGCA/ B 737-NG/88R1 TO PREVENT ELECTRICAL ENERG FROM LIGHTNING,HOT SHORTS OR FAULT CURRENT ENTERING THE FUEL TANK THROUGH THE ACTUATOR SHAFT TO ENSURE THAT CORRECT AMOUNT OF SEALANT WAS APPLIED AROUND THE VERTICAL FIN LUGS,SKIN AND SKIN EDGES TO PREVENT A FIRE NEAR A COMPOSITE DRAIN MAST AND POSSIBLE DISRUPTION OF THE ELECTRICAL POWER SSTEM CAUSED B A LIGHTNING STRIKE ON A COMPOSITE DRAIN MAST TO PREVENT FAILURE OF THE DRAIN TUBE ASSEMBLIES AND CLAMPS ON THE AFT FAIRINGS OF THE ENGINE STRUTS.SUCH FAILURES COULD ALLOW LEAKED FLAMMABLE FLUIDS IN THE DRAIN SSTEMS TO FAA AD SUPERSEDED FAA AD FAA AD FAA AD FAA AD

9 DGCA/ B 737-NG/89 DGCA/ B 737-NG/90 R2 DGCA/ B 737-NG/91 DGCA/ B 737-NG/92 DGCA/ B 737-NG/93R1 DGCA/ B 737-NG/94R1 DGCA/ B 737-NG/95 DGCA/ B 737-NG/96 DGCA/ B 737-NG/97R1 DISCHARGE ONTO THE HEAT SHIELDS OF THE AFT FAIRINGS OF THE ENGINE STRUTS. TO DETECT AND CORRECT CRACKING IN THE VINL INTERLAER OR DAMAGE TO THE STRUCTURAL INNER GLASS PANES OF THE FLIGHT DECK NO.2, NO.4 AND NO.5 TO PREVENT THE POTENTIAL FOR IGNITION SOURCES INSIDE FUEL TANKS CAUSED B LATENT FAILURES, ALTERATIONS, REPAIRS, OR MAINTENANCE ACTIONS TO PREVENT THE SIMULTANEOUS MALFUNCTION OF ALL SIX FUEL BOOST PUMPS TO MAINTAIN THE CONTINUED STRUCTURAL INTEGRIT OF THE ENTIRE FLEET OF ODEL , -400 AND 500 SERIES AIRPLANES TO DETECT AND CORRECT FATIGUE RELATED CRACKS, WHICH COULD RESULT IN THE CRACK TIPS CONTINUING TO TURN AND GROW TO THE POINT WHERE THE SKIN BA FLAPS OPEN CAUSING DECOMPRESSION OF THE AIRPLAIN TO PREVENT THE CENTER TANK FUEL DENSITOMETER FROM OVERHEATIN AND BECOMING A POTENTIAL IGNITION SOURCE INSIDE THE CENTER FUEL TANK TO PREVENT FRACTURE OF THE ELEVATOR TAB PUSHROD ENDS TO PREVENT FAILURE OF THE WINDSHIELD WIPERS IN WET WEATHER WHICH COULD RESULT IN DECREASED VISIBILIT FOR THE FLIGHT CREW TO PREVENT FAILURE OF THE FLIGHT CREW TO RECOGNIZE AND REACT TO A VALID CABIN ALTITUDE WARNING HORN WHICH COULD RESULT IN FAA AD FAA AD SUPERSEDED FAA AD R1 FAA AD FAA AD FAA AD SUPERSEDED FAA AD FAA AD SUPERSEDED FAA AD FAA AD FAA AD FAA AD

10 DGCA/ B 737-NG/98R1 DGCA/ B 737-NG/99 INCAPACITATION OF THE FLIGHT CREW DUE TO HPOXIA TO PREVENT FAILURE OF AN ESCAPE SLIDE TO DEPLO, WHICH COULD RESULT IN THE SLIDE BEING UNUSABLE DURING AN EMERGENC EVACUATION AND INCREASED LIKELHOOD OF INJUR TO PASSENGERS OR CREWMEMBERS DUE TO THE DIFFICULT IN EVACUATING THE AIRPLANE TO PREVENT EXTENDED DR RUNNING OF THE FUEL PUMPSWHICH COULD LEAD TO LOCALIZED OVERHEATING OF PARTS INSIDE THE FUEL PUMP FAA AD FAA AD DGCA/ B 737-NG/100 TO PREVENT FRAME CRACKING FAA AD DGCA/ B 737-NG/101 DGCA/ B 737-NG/102 DGCA/ B 737-NG/103R1 DGCA/ B 737-NG/104 DGCA/ B 737-NG/1 TO ENSURE THAT THE FLIGHTCREW IS ABLE TO TURN OFF ELECTRICAL POWER TO IFE SSTEMS & OTHER NON ESSENTIAL ELECTRICAL SSTEMS TO PREVENT REDUCED RUDDER PEDAL FORCES WHICH COULD RESULT IN INCREASED POTENTIAL FOR PILOT INDUCED OSCILLATIONS FAA AD FAA AD TO PREVENT STRESS CORROSION CRACKING OF THE FAA AD FORWARD TRUNNION PINS,WHICH COULD RESULT IN 11 SUPERSEDES FRACTURE OF THE PINS & CONSEQUENT COLLAPSE OF THE FAA AD MLG TO PREVENT CRACKING OF THE FORWARD TRUNNION PIN,WHICH COULD RESULT IN FRACTURE OF THE PIN & CONSEQUENT COLLAPSE OF THE MLG TO PREVENT A STANDB STATIC INVERTER FROM OVERHEATINGWHICH COULDRESULT IN SMOKE IN THE FLIGHT DECK & CABIN & LOSS OF THE ELECTRICAL STANDB POWER SSTEM FAA AD FAA AD DGCA/ B 737-NG/106 TO PREVENT CRACKS FROM PROPOGATING FROM DRILL FAA AD

11 DGCA/ B 737-NG/1 DGCA/ B 737-NG/108R3 DGCA/ B 737-NG/109 DGCA/ B 737-NG/110 DGCA/ B 737-NG/111R1 DGCA/ B 737-NG/112 DGCA/ B 737-NG/113 STARTS IN THE FREE FLANGE,VERTICAL WEB, AND RADIUS BETWEEN THE FREE FLANGE & VERTICAL WEB OF THE LOWER STRINGER S OF THE WING CENTER SECTION TO PREVENT THE FAILURE OF THE VALVE IN THE CLOSED POSITION,OPEN POSITION,OR PARTIALL OPEN POSITION,WHICH COULD RESULT IN ENGINE FUEL FLOW PROBLEMS & POSSIBLE UNCONTROLLED FUEL LEAK OR FIRE TOPREVENT DISCREPANCIES IN THE AFT ATTACH LUGS OF THE ELEVATOR TAB CONTROL MECHANISM,WHICH COULD RESULT IN ELEVATOR AND TAB VIBRATION TO PREVENT FAILURE OF DEFECTIVE FLIGHT DECK DOOR WHICH COULD JEOPARADIZE FLIGHT SAFET TO PREVENT INADVERTENT ELECTRICAL CURRENT,WHICH CAN CAUSE THE LOW PRESSURE FLEX HOSES OF THE CREW OXGEN SSTEM TO MELT OR BURN,RESULTING IN OXGEN SSTEM LEAKAGE TO PREVENT PUMP HOUSING BURN THROUGH DUE TO ELECTRICAL ARCING WHICH COULD CREATE A POTENTIAL IGNITION SOURCE INSIDE A FUEL TANK 08 FAA AD FAA AD SUPERSEDES FAA AD FAA AD FAA AD FAA AD TO PREVENT THE POTENTIAL OF IGNITION SOURCES FAA AD INSIDE FUEL TANKS WHICH IN COMBINATION WITH 03 FLAMMABLE FUEL VAPOURS,COULD RESULT IN FUEL TANK EXPLOSIONS & CONSEQUENT LOSS OF THE AIRPLANE TO PREVENT ARCING AT CERTAIN FUEL TANK FASTENERS FAA AD IN THE EVENT OF A LIGHTNING STRIKE OR FAULT CURRENT 11 EVENT,WHICH,IN COMBINATION WITH FLAMMABLE FUEL VAPOURS,COULD RESULT IN A FUEL TANK EXPLOSION & CONSEQUENT LOSS OF THE AIRPLANE DGCA/ B 737-NG/114 TO DETECT & CORRECT SUCH CRACKING,WHICH COULD FAA AD

12 DGCA/ B 737-NG/115 DGCA/ B 737-NG/116 RESULT IN THE LOSS OF THE LOWER WING SKIN LOAD PATH & CONSEQUENT STRUCTURAL FAILURE OF THE WING AIR TRANSPORT ASSOCIATION OF AMERICA CODE 57:WINGS AIR TRANSPORT ASSOCIATION OF AMERICA CODE 53:FUSELAGE 01 FAA AD FAA AD DGCA/ B 737-NG/117 ATA 27 - FLIGHT CONTROLS FAA AD DGCA/ B 737-NG/118R1 AIR TRANSPORT ASSOCIATION OF AMERICA CODE 28:FUEL FAA AD SUPERSEDED FAA AD DGCA/ B 737-NG/119 DGCA/ B 737-NG/120 DGCA/ B 737-NG/121 DGCA/ B 737-NG/122 DGCA/ B 737-NG/123 AIR TRANSPORT ASSOCIATION OF AMERICA CODE 71:POWERPLANT TO PREVENT FAILURE OF THE FIRE SEAL,WHICH COULD ALLOW A FIRE IN THE FAN COMPARTMENT TO SPREAD BEOND THE FIREWALL & REACH THE FLAMMABLE FLUID LEAKAGE ZONES,RESULTING IN AN UNCONTROLLED FIRE. TO PREVENT AN UNDETECTED FAILURE OF THE PRIMAR LOAD PATH, WHICH COULD LEAD TO LOSS OF CONTROL OF THE HORIZONTAL STABILIZER & CONSEQUENT LOSS OF CONTROL OF THE AIRPLANE TO PREVENT A FIRE IN THE FAN COMPARTMENT (A FIRE ZONE) FROM MIGRATING THROUGH THE SEAL TO A FLAMMABLE FLUID IN THE THRUST REVERSER ACTUATOR COMPARTMENT (A FLAMMABLE FLUID LEAKAGE ZONE) WHICH COULD RESULT IN AN UNCONTROLLED FIRE. TO DETECT & CORRECT SUCH HEAT DAMAGE,WHICH COULD RESULT IN SEPERATION OF ADJACENT FAA AD FAA AD FAA AD FAA AD FAA AD

13 DGCA/ B 737-NG/124 DGCA/ B 737-NG/125R2 DGCA/ B 737-NG/126 DGCA/ B 737-NG/127 DGCA/ B 737-NG/128 COMPONENTS AND CONSEQUENT STRUCTURAL DAMAGE TO THE AIRPLANE,DAMAGE TO OTHER AIRPLANES,AND INJUR TO PEOPLE ON GROUND TO PREVENT FAILURE OF THE SEAT ATTACHMENT STRUCTURE AND POSSIBLE INJUR TO PASSENGERS DURING AN EMERGENC LANDING ATA-21, AIR CONDITIONING,TO PREVENT THE LOSS OF CABIN ALTITUDE WARNING, WHICH COULD DELA FLIGHTCREW RECOGNITION OF A LACK OF CABIN PRESSURIZATION, AND COULD RESULT IN INCAPACITATION OF THE FLIGHTCREW DUE TO HPOXIA (A LACK OF OXGEN IN THE BOD), AND CONSEQUENT LOSS OF CONTROL OF THE AIRPLANEINCAPACITATION OF THE FLIGHT CREW DUE TO HPOXIA (LACK OF OXGEN IN THE BOD) AND CONSEQUENT LOSS OF CONTROL OF THE AIRPLANE TO PREVENT ICE FROM FORMING ON AIR DATA SSTEM SENSORS AND CONSEQUENT LOSS OF OR MISLEADING AIRSPEED INDICATION ON ALL AIRSPEED INDICATING SSTEMS,WHICH COULD LEAD TO LOSS OF CONTROL OF THE AIRPLANE ATA 25: EQUIPMENT / FURNISHINGS. TO PREVENT DETACHMENT OF COS BOXES AT FORWARD LOAD LEVELS LESS THAN 9G DURING AN EMERGENC LANDING,WHICH WOULD CAUSE INJUR TO PASSENGERS & CREW AND COULD IMPEDE SUBSEQUENT RAPID EVACUATION. TO PREVENT ELECRICAL ARCING AND A POTENTIAL IGNITION SOURCE EITHIN THE ESC BA,WHICH IN COMBINATION WITH FLAMMABLE VAPOURS,COULD RESULT IN A CENTER WING FUEL TANK EXPLOSION AND CONSEQUENT LOSS OF THE AIRPLANE FAA AD FAA AD FAA AD FAA AD FAA AD

14 DGCA/ B 737-NG/129 DGCA/ B 737-NG/130 DGCA/ B 737-NG/131 DGCA/ B 737-NG/132 DGCA/ B 737-NG/133 DGCA/ B 737-NG/134 DGCA/ B 737-NG/135 DGCA/ B 737-NG/136 TO PREVENT AN IGNITION SOURCE,WHICH COULD RESULT IN AN OXGEN LED FIRE OR AN INLET VALVE JAM IN A CREW OXGEN MASK STOWAGE BOX UNIT TO DETECT & CORRECT FATIGUE CRACKING OF THE SKIN PANEL AT THE SPECIFIED CHEM -MILL STEP LOCATIONS,WHICH COULD RESULT IN RAPID DECOMPRESSION OF THE AIRPLANE. TO DETECT & CORRECT FATIGUE CRACKING OF THE SKIN PANEL AT THE SPECIFIED CHEM -MILL LOCATIONS, WHICH COULD RESULT IN RAPID DECOMPRESSION OF THE AIRPLANE TO PREVENT FLAMMABLE FLUIDS FROM ACCUMULATING IN THE WING LEADING EDGE AND DRAINING INBOARD AND ONTO THE ENGINE EXHAUST NOZZLE WHICH COULD RESULT IN A FIRE TO DETECT & CORRECT FATIGUE CRACKING OF THE SKIN PANEL AT THE SPECIFIED CHEM-MILL STEP LOCATIONS WHICH COULD RESULT IN RAPID DECOMPRESSION OF THE AIRPLANE TO DETECT & CORRECT FATIGUE CRACKING OF THE SKIN PANEL AT THE SPECIFIED CHEM-MILL STEP LOCATIONS WHICH COULD RESULT IN RAPID DECOMPRESSION OF THE AIRPLANE TO DETECT & CORRECT DAMAGE TO THE FIRE SEALS WHICH COULD ALLOW AIRFLOW INTO THE ENGINE FIRE ZONE AND COULD ULTIMATEL DEGRADE THE ABILIT TO EXTINGUISH AN ENGINE FIRE TO DETECT & CORRECT FATIGUE CRACKING IN THE INBOARD MLG DOOR HINGE FITTINGS,WHICH COULD RESULT IN LOSS OF THE MLG DOOR ASSEMBL FROM THE FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD FAA AD

15 DGCA/ B 737-NG/137R1 DGCA/ B 737-NG/138R1 DGCA/ B 737-NG/139 DGCA/ B 737-NG/140 DGCA/ B 737-NG/141 DGCA/ B 737-NG/142R1 AIRPLANE,AND THE MLG DOOR ASSEMBL COULD IMPACT THE FLIGHT CONTROL SURFACES AND RESULT IN REDUCED CONTROLLABILIT OF THE AIRPLANE TO DETECT & CORRECT LOSS OF THE ENGINE FUEL SUCTION FEED CAPABILIT OF THE FUEL SSTEM,WHICH IN THE EVENT OF TOTAL LOSS OF THE FUEL BOOST PUMPS COULD RESULT IN DUAL ENGINE FLAMEOUT TO DETECT & CORRECT FATIGUE CRACKING IN THE SKIN,WHICH CAN RESULT IN RAPID DECOMPRESSION OF THE CABIN FAA AD SUPERSEDED FAA AD FAA AD SUPERSEDED FAA AD TO DETECT & CORRECT POSSIBLE DAMAGE CAUSED B FAA AD INSUFFICIENT SEPERATION BETWEEN THE WIRE BUNDLES 03 AND HDRAULIC TUBING TO PREVENT ELECTRICAL ARCING IN A FLAMMABLE FLUID LEAKAGE ZONE WHICH COULD LEAD TO A WHEEL WELL FIRE TO DETECT & CORRECT FATIGUE CRACKING OF VARIOUS FAA AD PRINCIPAL STRUCTURAL ELEMENTS (PSEs) WHICH COULD 23 ADVERSEL AFFECT THE STRUCTURAL INTEGRIT OF THESE AIRPLANES TO DETECT & CORRECT MISSING OR SEVERED BOLT FAA AD HEADS,WHICH IF NOT CORRECTED,COULD RESULT IN THE 04 INABILIT OF THE SEAT TRACK TO CARR PASSENGER LOADS,WHICH COULD CAUSE THE SEATS TO DETACH FROM THE SEAT TRACK,RESULTING IN POSSIBLE INJUR TO PASSENGERS DURING AN EMERGENC ATA 53,FUSELAGE,TO PREVENT SEAT DETACHMENT IN AN EMERGENC LANDING,WHICH COULD CAUSE INJUR TO OCCUPANTS OF THE PASSENGER COMPARTMENT AND AFFECT EMERGENC EGRESSEMERGENC EGRESS FAA AD FAA AD

16 DGCA/ B 737-NG/143 R1 DGCA/ B 737-NG/144 DGCA/ B 737-NG/145 DGCA/ B 737-NG/146 DGCA/ B 737-NG/147 DGCA/ B 737-NG/148 to prevent arcing, smoke and fire in the flight deck, which FAA AD could lead to injuries to or incapacitation of the flightcrew. 16 TO DETECT AND CORRECT CRACKS IN THE IN-FLIGHT FAA AD ENTERTAINMENT SSTEM RADOME ASSEMBL, WHICH 19 COULD RESULT IN THE RADOME (OR PIECES) SEPARATING FROM THE AIRPLANE AND STRIKING THE TAIL, AND CONSEQUENTL REDUCING THE CONTROLLABILIT OF THE AIRPLANE TO PREVENT, IN CASE OF A DIRECT LIGHTNING STRIKE TO THE TAIL STROBE LIGHT, DAMAGE TO THE OPERATION OF OTHER CRITICAL AIRPLANE SSTEMS DUE TO ELECTROMAGNETIC COUPLING AND LARGE TRANSIENT VOLTAGES, AND DAMAGE TO THE CONTROL MECHANISMS OR SURFACES DUE TO A FIRE, WHICH COULD RESULT IN LOSS OF CONTROL OF THE AIRPLANE TO PREVENT ELECTRICAL ARCING AND A POTENTIAL IGNITION SOURCE, WHICH, IN COMBINATION WITH FLAMMABLE FUEL VAPORS, COULD RESULT IN A FUEL TANK EXPLOSION, AND CONSEQUENT LOSS OF THE AIRPLANE. TO PREVENT LOSS OF STRUCTURAL INTEGRIT OF THE HORIZONTAL STABILIZER ATTACHMENT AND LOSS OF CONTROL OF THE AIRPLANE. TO PREVENT A SINGLE, UNDETECTED, ERRONEOUS RADIO ALTIMETER OUTPUT FROM CAUSING PREMATURE AUTOTHROTTLE LANDING FLARE RETARD AND SUBSEQUENT LOSS OF AUTOMATIC SPEED CONTROL, WHICH COULD RESULT IN LOSS OF CONTROL OF THE AIRPLANE FAA AD FAA AD FAA AD FAA AD DGCA/ B 737-NG/149 TO PREVENT LOSS OF FLIGHT-CRITICAL INFORMATION FAA AD

17 DGCA/ B 737-NG/150 DGCA/ B 737-NG/151R1 DGCA/ B 737-NG/152 DGCA/B737-NG/153 DISPLAED 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 RECOVER, OR CONTROLLED FLIGHT INTO TERRAIN ATA 53, FUSELAGE TO DETECT AND CORRECT CRACKING IN A BULKHEAD LOWER FRAME WEB AND INNER CHORD, WHICH COULD RESULT IN A SEVERED FRAMED AND INDUCED SKIN CRACKS, AND COULD LEAD TO RAPID DECOMPRESSION OF THE FUSELAGE 06 FAA AD SUBJECT OF AD IS AIR TRANSPORT ASSOCIATION (ATA) OF FAA AD AMERICA CODE 2823, FUEL SELECTOR/SHUTOFF VALVE, 13 SUPERSEDED WE ARE ISSUING THIS AD TO TO DETECT AND CORRECT FAA AD LATENT FAILURES OF THE FUEL SHUTOFF VALVE TO THE ENGINE, WHICH COULD RESULT IN THE INABILIT TO SHUT OFF FUEL TO THE ENGINE AND, IN CASE OF CERTAIN ENGINE FIRES, AN UNCONTROLLABLE FIRE THAT COULD LEAD TO WING FAILURE. ATA 21& 20, Air Distribution System,to detect and correct latent failures of the equipment cooling system and low pressure environmental control system ATA 28, Fuel,to prevent electrical energy from lightning, hot shorts, or fault current from entering the fuel tank through the fuel valve actuator shaft FAA AD FAA AD DGCA/B737-NG/154R1 AIR TRANSPORT ASSOCIATION CODE 55: STABLIZERS FAA AD SUPERSEDED FAA AD DGCA/B737-NG/155 AIR TRANSPORT ASSOCIATION CODE 32: LANDING GEAR FAA AD

18 DGCA/B737-NG/156 AIR TRANSPORT ASSOCIATION CODE 53: FUSELAGE FAA AD DGCA/B737-NG/157 AIR TRANSPORT ASSOCIATION CODE 53: FUSELAGE FAA AD DGCA/B737-NG/158 AIR TRANSPORT ASSOCIATION CODE 29: HDRAULIC POWER 01 FAA AD DGCA/B737-NG/159 AIR TRANSPORT ASSOCIATION CODE 53: FUSELAGE FAA AD DGCA/B737-NG/160 ATA 32, LANDING GEAR- TO PREVENT STRESS CORROSION CRACKING OF THE EXTERNAL SURFACES OF THE MLG FAA AD DGCA/B737-NG/161 ATA-53, Fuselage, to detect and correct cracks of the web lap splices in the aft pressure bulkhead FAA AD DGCA/B737-NG/162 ATA-21- AIR CONDITIONING- TO PREVENT TEMPERATURES FAA AD IN EXCESS OF 100 DEGREES FAHRENHEIT IN THE FLIGHT DECK OR THE PASSENGER CABIN DURING CRUISE DGCA/B737-NG/163 ATA 25, EQUIPMENT AND FURNISHINGS- TO DETECT AND FAA AD CORRECT A PROTRUDING SCREW IN THE COVER 13 ASSEMBL OF THE HEEL REST OF A RUDDER PEDAL

19 DGCA/B737-NG/164 ATA 57, WINGS- TO DETECT AND CORRECT MISSING KRUEGER FLAP BULLNOSE HARDWARE FAA AD DGCA/B737-NG/165 TO PREVENT TAKEOFF WITH A STABILIZER POSITION SET FAA AD OUTSIDE ACCEPTABLE LIMITS FOR A MIS-TRIMMED 16 TAKEOFF CONDITION. SETTINGS OUTSIDE OF THE APPROPRIATE PITCH TRIM LIMITS COULD RESULT IN LOSS OF CONTROLLABILIT OF THE AIRPLANE DURING TAKEOFF