DHC-8-400 SERIES.pdf

DGCANO SUBJECT REFERENCE COMPLIANCE APPLICABILITY

DGCA/DHC-8 -400SERIES/01R1 AIR TRANSPORT ASSOCIATION OF AMERICA CODE 57: WINGS FAA AD 2019-20-09 FAA AD 2011-18-15

AS IN AD AS IN AD

DGCA/DHC-8-400 SERIES/02 AIR TRANSPORT ASSOCIATION OF AMERICA CODE 32:LANDING GEAR FAA AD 2011-17-17 AS IN AD AS IN AD


DGCA/DHC-8-400 SERIES/04 AIR TRANSPORT ASSOCIATION OF AMERICA CODE 27:FLIGHT CONTROLS FAA AD 2011-18-18 AS IN AD AS IN AD


DGCA/DHC-8-400 SERIES/06 TO PREVENT THE LOSS OF ICE PROTECTION SYSTEMS FOR THE ANGLE OF ATTACK VANES,PITOT PROBES,ENGINE INLETS,AND WINDSHIELDS,AND CONSEQUENT LOSS OF MISLEADING AIRSPEED INDICATION AND INCREASED WORKLOAD FOR THE FLIGHT CREW WHICH COULD LEAD TO LOSS OF CONTROL OF THE AIRPLANE

FAA AD 2012-02-12 AS IN AD AS IN AD

DGCA/DHC-8-400 SERIES/07 TO PREVENT LOSS OF BOTH RUDDER PCU ACTUATORS WHICH COULD RESULT IN FREE PLAY OF THE RUDDER CONTROL SURFACE AND LOSS OF CONTROLLABILITY OF THE AIRPLANE


DGCA/DHC-8-400 SERIES/08 AIR TRANSPORT ASSOCIATION OF AMERICA CODE 53: FUSELAGE FAA AD 2012-06-04 AS IN AD AS IN AD

DGCA/DHC-8-400 SERIES/09 AIR TRANSPORT ASSOCIATION OF AMERICA CODE 52: DOORS FAA AD 2012-06-05 AS IN AD AS IN AD


DGCA/DHC-8-400 SERIES/11 TO PREVENT CRACKING OF FUEL ACCESS PANELS,WHICH COULD RESULT IN ARCING & IGNITION OF FUEL VAPOUR IN THE OUTER WING FUEL TANK DURING A LIGHTNING STRIKE


DGCA/DHC-8-400 SERIES/12 TO PREVENT CHAFING OF THE HIGH PRESSURE FUEL LINES,WHICH COULD CAUSE FUEL LEAKAGE IN THE FIRE ZONE


DGCA/DHC-8-400 SERIES/13 TO PREVENT THE LOSS OF RUDDER CONTROL,REDUCED DIRECTIONAL CONTROL OF THE AIRPLANE ON THE GROUND,OR A JAMMED NOSE LANDING GEAR (NLG) DOOR THAT COULD PREVENT THE NLG FROM RETRACTING OR EXTENDING


DGCA/DHC-8-400 SERIES/14 TO PREVENT LOSS OF AUTOMATIC DE-ICING MODE AND CONSEQUENT INCREASED WORKLOAD FOR THE FLIGHTCREW,WHICH DEPENDING ON



ADDITIONAL FAILURES,COULD LEAD TO LOSS OF CONTROL OF THE AIRPLANE

DGCA/DHC-8-400 SERIES/15 TO DETECT AND CORRRECT CHAFING DAMAGE TO THE WIRE HARNESS ALONG THE WING LEADING EDGE,WHICH IF NOT CORRECTED,COULD LEAD TO LOSS THE AIRFRAME DE-ICING SYSTEM AND COULD BECOME A POSSIBLE IGNITION SOURCE CAUSING FIRE


DGCA/DHC-8-400 SERIES/16 TO DETECT & CORRECT FAILURE OF THE MAIN LANDING GEAR (MLG) TO EXTEND AND LOCK ,WHICH COULD ADVERSELY AFFECT THE SAFE LANDING OF THE AIRPLANE

FAA AD 2012 -20-09

AS IN AD AS IN AD

DGCA/DHC-8-400 SERIES/17 TO PREVENT ROTOR WINDINGS FROM COMING IN CONTACT WITH THE GENERATOR HOUSING WHICH COULD RESULT IN DEBRIS CONTAMINATING AND POTENTIALLY BLOCKING THE ENGINE OIL SCAVENGE SYSTEM,LEADING TO LOSS OF OIL PRESSURE AND IN FLIGHT SHUTDOWN OF THE ENGINE


DGCA/DHC-8-400 SERIES/18 TO PREVENT FAILURE OF THE SCREW CAPS AND /PR END CAPS OF THE HYDRAULIC AND PARKING BRAKE ACCUMULATORS WHICH COULD RESULT IN DAMAGE TO THE AIRPLANES PRIMARY STRUCTURES


DGCA/DHC-8-400 SERIES/19 TO DETECT & CORRECT DAMAGED ,CHAFED,OR LOOSE WIRING WITHIN AN ACCB,WHICH COULD AFFECT THE OPERATION OF THE WINDSHIELD HEATER,ICE DETECTOR.ANGLE OF ATTACK (AOA) VANE HEATER,PILOT PROBE HEATER , ENGINE INTAKE HEATER


DGCA/DHC-8-400 SERIES/20 TO PREVENT CHAFING BETWEEN THE NACELLE FIRE DETECTION WIRES AND THE MLG YOKE.CHAFING COULD LEAD TO CRACKING AND SUBSEQUENT FAILURE OF THE MLG YOKE


DGCA/DHC-8-400 SERIES/21 TO DETECT & CORRECT EXCESSIVE FREE PLAY OF THE SWAGED BEARINGS,WHICH COULD LEAD TO EXCESSIVE AIRFRAME VIBRATIONS AND DIFFICULTIES IN PITCH CONTROL ,AND CONSEQUENT LOSS OF CONTROLLABILITY OF THE AIRPLANE


DGCA/DHC-8-400 SERIES/22 TO PREVENT A CONTINUED ENGINE FIRE INDICATION IN THE COCKPIT AFTER THE ACTUAL FIRE HAS BEEN EXTINGUISHED



DGCA/DHC-8-400 SERIES/23 TO DETECT & CORRECT A WORN OR CRACKED CLEVIS HOLE,WHICH COULD CAUSE FAILURE OF THEBELLCRANK ON ONE SIDE ,WITH SUBSEQUENT ASYMMETRIC BRAKING & CONSEQUENT RUNWAY EXCURSION


DGCA/DHC-8-400 SERIES/24 TO DETECT & CORRECT ANY SIGN OF ROUGH MOVEMENT OR SEIZURE OF THE TRUNNION SHAFT & ITS BUSHING,WHICH COULD CAUSE A RUDDER CONTROL JAM OR A LARGE & RAPID ALTERNATING RUDDER INPUT LEADING TO A STRUCTURAL FAILURE OF THE VERTICAL FIN


DGCA/DHC-8-400 SERIES/25 TO PREVENT A MIGRATED PIN FROM JAMMING A TRANSLATING DOOR HANDLE, WHICH COULD PREVENT OPENING OF THE DOOR AND IMPEDE AN EMERGENCY EVACUATION


DGCA/DHC-8-400 SERIES/26 TO PREVENT INCORRECTLY INSTALLED SCRAPERS, WHICH COULD HINDER THE OPERATION OF THE MLG ALTERNATE EXTENSION SYSTEM (AES), AND RESULT IN FAILURE OF THE MLG AES ON ONE SIDE, AND CONSEQUENT UNSAFE ASYMMETRICAL LANDING CONFIGURATION


DGCA/DHC-8-400 SERIES/27R1 TO DETECT AND CORRECT UP-LOCK HOOKS WORN BEYOND THE WEAR LIMIT, WHICH COULD PREVENT THE SUCCESSFUL EXTENSION OF THE MLG USING THE PRIMARY LANDING GEAR EXTENSION SYSTEM, WHICH IN COMBINATION WITH AN ALTERNATE EXTENSION SYSTEM FAILURE COULD RESULT IN THE INABILITY TO EXTEND THE MLG

FAA AD 2018-17-09 SUPERSEDED FAA AD 2014-05-28

AS IN AD AS IN AD

DGCA/DHC-8-400 SERIES/28 TO PREVENT IMPROPER OPERATION OF THE CAM MECHANISM OR RUPTURE OF THE DOOR RELEASE CABLE, WHICH COULD RESULT IN LOSS OF CONTROL OF THE AIRPLANE DURING LANDING


DGCA/DHC-8-400 SERIES/29 TO PREVENT AN INOPERATIVE TMU, WHICH COULD RESULT IN THE LOSS OF THE AUTOMATIC DE-ICING MODE, AND LEAD TO AN INCREASED WORKLOAD FOR THE FLIGHT CREW AND LOSS OF CONTROL OF THE AIRPLANE


DGCA/DHC-8-400 SERIES/30 TO DETECT AND CORRECT IMPROPER BEARING INSTALLATION, WHICHCOULD RESULT IN ABNORMAL WEAR AND POTENTIAL INCREASED FREEPLAY IN THE RUDDER SYSTEM, AND RESULTANT



AIRFRAME VIBRATION, LEADING TO COMPROMISE OF THE FLUTTER MARGINS OF THE AIRPLANE

DGCA/DHC-8-400 SERIES/31 TO DETECT AND CORRECT CHAFING OF THE AC FEEDER CABLE. A CHAFED AND ARCING AC FEEDER CABLE COULD PUNCTURE THE ADJACENT HYDRAULIC LINE, WHICH, INCOMBINATION WITH THE USE OF THE ALTERNATE EXTENSION SYSTEM, COULD RESULT IN AN IN-FLIGHT FIRE


DGCA/DHC-8-400 SERIES/32 TO PREVENT BLOCKED ENGINE FUEL FLOW AND POSSIBLE ENGINE FLAMEOUT


DGCA/DHC-8-400 SERIES/33 TO PREVENT FAILURE OF THE PIVOT PIN RETENTION BOLT, WHICH COULD RESULT IN A LOSS OFDIRECTIONAL CONTROL OR A NOSE LANDING GEAR (NLG) TIRE DURING TAKE-OFF OR LANDING


DGCA/DHC-8-400 SERIES/34 ATA32, LANDING GEAR, TO DETECT AND CORRECT INSUFFICIENTLY GREASED STABILIZER BRACE LOCK LINKAGE OF THE MLG AND OVER-TORQUED LOCK LINKAGE ATTACHMENT BOLTS, WHICH COULD LEAD TO THE FAILURE TO EXTEND AND DOWN-LOCK THE MLG, AND COULD AFFECT THE SAFE LANDING OF THE AIRPLANE.


DGCA/DHC-8-400 SERIES/35 ATA 28 FUEL, TO PREVENT THE POTENTIAL OF IGNITION SOURCES INSIDE FUEL TANKS, WHICH, IN COMBINATION WITH FLAMMABLE FUEL VAPORS, COULD RESULT IN FUEL TANK EXPLOSIONS AND CONSEQUENT LOSS OF THE AIRPLANE


DGCA/DHC-8-400 SERIES/36 ATA 32, LANDING GEAR. TO DETECT AND CORRECT IMPROPER INSTALLATION OF THE CLEVIS, WHICH COULD CAUSE LOSS OF THE ALTERNATE RELEASE SYSTEM AND PREVENT THE MLG FROM EXTENDING AND RETRACTING, AND COULD CONSEQUENTLY AFFECT THE AIRPLANE'S CONTINUED SAFE FLIGHT AND LANDING.


DGCA/DHC-8-400 SERIES/37R1 IN THE EVENT OF A FAILURE OF THE PRIMARY MLG EXTENSION SYSTEM, PREVENT FAILURE OF THE ALTERNATE MLG EXTENSION SYSTEM TO FULLY EXTEND THE MLG INTO A DOWN-AND-LOCKED POSITION, WHICH COULD RESULT IN COLLAPSE OF BOTH LEFT-HAND AND RIGHT-HAND

FAA AD 2015-15-07 amendFAA AD 2015-10-01

AS IN AD AS IN AD


MLG SIDES DURING TOUCHDOWN

DGCA/DHC-8-400 SERIES/38 ATA-26, FIRE PROTECTION, TO PREVENT PERFORATION OF THE LOW-RATE DISCHARGE TUBES, WHICH COULD RESULT IN INSUFFICIENT FIRE EXTINGUISHING AGENT REACHING THE FORWARD BAGGAGE COMPARTMENT IN THE EVENT OF A FIRE, WHICH COULD RESULT IN DAMAGE TO THE AIRPLANE AND INJURY TO THE OCCUPANTS.


DGCA/DHC-8-400 SERIES/39 TO PREVENT LOOSE BOLTS FROM FALLING OUT. IF BOTH BOLTS BECOME LOOSE OR FALL OUT AFTER THE DOOR IS CLOSED AND LOCKED, THE DOOR CANNOT BE OPENED FROM INSIDE OR OUTSIDE, WHICH COULD IMPEDE EVACUATION IN THE EVENT OF AN EMERGENCY


DGCA/DHC-8-400 SERIES/40 TO PREVENT AN UNCOMMANDED NOSE WHEEL STEERING DURING TAKEOFF OR LANDING IN THE EVENT OF AN OPEN CIRCUIT IN THE STEERING SYSTEM, AND POSSIBLE CONSEQUENT RUNWAY EXCURSION.


DGCA/DHC-8-400 SERIES/41 TO PREVENT AN UNSECURED LEVER FROM MIGRATING FROM ITS STOWED POSITION, FOULING AGAINST THE MLG, AND SUBSEQUENTLY PUNCTURING THE NACELLE STRUCTURE, WHICH COULD ADVERSELY AFFECT THE SAFE LANDING OF THE AIRPLANE


DGCA/DHC-8-400 SERIES/42 TO PREVENT CHAFING OF THE FUEL LINES IN THE FUEL TANK, WHICH COULD RESULT IN POTENTIAL IGNITION SOURCES IN THE FUEL TANK IN THE EVENT OF A LIGHTNING STRIKE AND CONSEQUENT FIRE OR EXPLOSION.


DGCA/DHC-8-400 SERIES/43 TO PREVENT A LOW VOLTAGE CONDITION ON THE LEFT MAIN DC BUS WHICH , DURING CRITICAL PHASES OF FLIGHT , COULD RESULT IN THE LOSS OF FLIGHT MANAGEMENT , NAVIAGATION , AND TRANSPONDER SYSTEMS, AND COULD EFFECT CONTINUED SAFE FLIGHT.


DGCA/DHC-8-400 SERIES/44 TO PREVENT LEAKAGE OF THE PISTON HEAD SEAL AND PISTON ROD SEALS OF THE OUTBOURD SPOILER PCU , WHICH COULD RESULT IN INADVERTENT SPOILER DEPLOYMENT AND REDUCED CONTROLLABILITY OF THE AIRPLANE.


DGCA/DHC-8-400 SERIES/45 To DETECT AND CORRECT CRACKS IN THE FORWARD PASSENGER AIR FAA AD 2016-01-09 AS IN AD AS IN AD


STAIR DOOR STEP ASSEMBLY, WHICH COULD PROPAGATE AND RESULT IN THE STRUCTURAL FAILURE OF THE STEP

DGCA/DHC-8-400 SERIES/46R1 TO DETECT AND CORRECT FATIGUE CRACKING OF THE LEFT AND RIGHT MLG RETRACT ACTUATOR ROD ENDS, WHICH COULD LEAD TO LEFT OR RIGHT MLG COLLAPSE

FAA AD 2017-23-01 SUPERSEDED FAA AD 2016-13-14

AS IN AD AS IN AD

DGCA/DHC-8-400 SERIES/47 ATA 32, LANDING GEAR FAA AD 2016-16-15 AS IN AD AS IN AD

DGCA/DHC-8-400 SERIES/48 ATA 30, ICE AND RAIN PROTECTION FAA AD 2016-19-11 AS IN AD AS IN AD

DGCA/DHC-8-400 SERIES/49 ATA 61, PROPELLERS/PROPULSORS FAA AD 2016-22-03 AS IN AD AS IN AD

DGCA/DHC-8-400 SERIES/50R1 ATA 55, STABILIZERS FAA AD 2018-22-03 SUPERSEDED FAA AD 2016-24-03

AS IN AD AS IN AD

DGCA/DHC-8-400 SERIES/51 ATA 53,FUSELAGE FAA AD 2016-24-04 AS IN AD AS IN AD

DGCA/DHC-8-400 SERIES/52 ATA 32, LANDING GEAR- MAIN LANDING GEAR RETRACTION ACTUATOR ROD-END FAILURE, TO REPLACE THE MLG RETRACTION ACTUATOR ROD-END SUBASSEMBLIES MANUFACTURED WITH POTENTIALLY NON-CONFORMING THREADS WITH UNITS THAT FULLY CONFORM TO THE DESIGN REQUIREMENTS.

CF-2016-36R1 AS IN AD AS IN AD

DGCA/DHC-8-400 SERIES/53 ATA 32, NOSE LANDING GEAR – LOSS OF PIVOT PIN RETENTION BOLT- TO PREVENT THE POTENTIAL FAILURE OF THE PIVOT PIN RETENTION BOLT, BOMBARDIER AEROSPACE DEVELOPED A MODIFICATION WHICH INCLUDED A NEW RETENTION BOLT, A REVERSE ORIENTATION OF THE RETENTION BOLT AND A REWORK OF THE WEIGHT ON WHEEL (WOW) PROXIMITY SENSOR COVER TO PROVIDE CLEARANCE FOR THE RE-ORIENTED RETENTION BOLT.


DGCA/DHC-8-400 SERIES/54 ATA 27, FLIGHT CONTROL SYSTEM – CRACKING OF THE SPOILER POWER CONTROL UNIT- MANDATES THE REPLACEMENT OF THE AFFECTED SPOILER PCUS


DGCA/DHC-8-400 SERIES/55 ATA 61, PROPELLERS – IN-FLIGHT OPERATION OF PROPELLER IN BETA RANGE, TO INSTALL NEW ELECTRICAL CIRCUITS (BETA LOCKOUT



SYSTEM) THAT ARE DESIGNED TO PREVENT THE PROPELLERS FROM ENTERING THE BETA RANGE OF OPERATION DURING FLIGHT.

DGCA/DHC-8-400 SERIES/56 ATA 28, FUEL SYSTEM – CORROSION AND WEAR OF HYDRAFLOW COUPLINGS AND SLEEVES, FUEL TUBE END FERRULES, AND FUEL COMPONENT END FERRULES, TO INSPECT AND REPAIR OR REPLACEMENT, AS REQUIRED, OF AFFECTED FUEL COUPLINGS AND SLEEVES, FUEL TUBES, AND FUEL COMPONENTS, AS WELL AS THE COLLECTION OF WEAR DATA, TO MITIGATE THE RISK OF LIGHTNING STRIKE INDUCED FUEL TANK IGNITION.


DGCA/DHC-8-400 SERIES/57R2 ATA 28, FUEL SYSTEM – MOTIVE FLOW LINE FOULING AND MOTIVE FLOW LINE AND PRESSURE RELIEF LINE BROKEN P-CLAMPS, MANDATES DESIGN CHANGES THAT MITIGATE THE RISK OF LIGHTNING STRIKE INDUCED FUEL TANK IGNITION.


DGCA/DHC-8-400 SERIES/58 ATA 54, NACELLE – A-FRAME STRUCTURE – INSUFFICIENT FILLET RADIUS

AND FOULING WITH MAIN LANDING GEAR STABILIZER BRACE AND THE

ELECTRICAL WIRING HARNESSES INSPECTION AND REWORK OF THE

NACELLE A-FRAME STRUCTURE, AND THE REWORK OF THE FORWARD

MLG STABILIZER BRACE ASSEMBLY AND THE ELECTRICAL HARNESSES IN

THE NACELLE AREA ADJACENT TO THE AFRAME STRUCTURE.

CF 2014-45R3 AS IN AD AS IN AD

DGCA/DHC-8-400 SERIES/59 ATA 32, LANDING GEAR – DYNAMIC RESPONSE OF MAIN LANDING GEAR

SYSTEM TO EXTERNAL LOADS, TO CHANGES TO THE DOWNLOCK

SENSOR RIGGING AND AN INCREASE IN THE LOCK LINK OVER-CENTRE

STOP PIN HEIGHT AS MITIGATING ACTIONS. IT ALSO MANDATES THE

INSTALLATION OF PROXIMITY SENSOR ELECTRONIC UNIT (PSEU) 30145-

0601, WHICH INCORPORATES NEW SOFTWARE TO ENSURE HYDRAULIC

PRESSURE IS RETAINED IN THE MLG DOWNLOCK ACTUATOR WHENEVER

THE LANDING GEAR IS DOWN AND LOCKED.



DGCA/DHC-8-400 SERIES/60 ATA 32, LANDING GEAR- MAIN LANDING GEAR RETRACTION ACTUATOR

ROD-END FAILURE, TO REPLACE THE MLG RETRACTION ACTUATOR ROD-

END SUBASSEMBLIES MANUFACTURED WITH POTENTIALLY NON-

CONFORMING THREADS WITH UNITS THAT FULLY CONFORM TO THE

DESIGN REQUIREMENTS.


DGCA/DHC-8-400 SERIES/61 ATA 32, LANDING GEAR – MAIN LANDING GEAR UP-LOCK ASSEMBLY

LATCH WEAR - INTRODUCTION OF ONE-STAR CERTIFICATION

MAINTENANCE REQUIREMENT (CMR) TASK 323100-102, MANDATES

THE INCORPORATION OF CMR TASK NUMBER 323100-102.

CF-2017-15 AS IN AD AS IN AD

DGCA/DHC-8-400 SERIES/62 ATA 30, WINDOWS – WINDSHIELD CRACKING, TO CORRECT THE

LOOSENING OF WINDSHIELD HEATER TERMINAL LUGS.


DGCA/DHC-8-400 SERIES/63 ATA 74/76, ENGINE IGNITION - LOSS OF #2 ENGINE AUTO RELIGHT

FUNCTION, TO CLARIFY THE APPLICABILITY SECTION AND CORRECT A

TYPOGRAPHIC ERROR IN THE SB NUMBER REFERENCED IN THE

CORRECTIVE ACTION SECTION OF THE ORIGINAL AD.



DGCA/DHC-8-400 SERIES/64 ATA 55, STABILIZERS – CRACKED BARREL NUT AT THE HORIZONTAL

STABILIZER TO VERTICAL STABILIZER ATTACHMENT JOINT, TO

TERMINATE THE REPETITIVE INSPECTION REQUIREMENT BY REQUIRING

THE INCORPORATION OF A MODIFICATION TO INSTALL A SEALING DISC

AT THE MIDDLE SPAR LOCATION OF THE HORIZONTAL STABILIZER TO

VERTICAL STABILIZER ATTACHMENT JOINT, AND THE REPLACEMENT OF

THE DSC228 SERIES BARREL NUTS WITH B0203073 SERIES BARREL NUTS

THAT ARE MORE RESISTANT TO CORROSION.


DGCA/DHC-8-400 SERIES/65 ATA 30, WINDOWS – WINDSHIELD CRACKING, TO CORRECT THE

LOOSENING OF WINDSHIELD HEATER TERMINAL LUGS.


DGCA/DHC-8-400 SERIES/66 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 26, FIRE

PROTECTION, TO PREVENT FAILURE OF THE FCA AND SUBSEQUENT

DISCHARGE OF FIRE EXTINGUISHING BOTTLES AND FALSE FIRE

INDICATIONS, LEAVING THE FLIGHT CREW WITH REDUCED

FIREFIGHTING CAPABILITY IN THE EVENT OF A FIRE


DGCA/DHC8-400 SERIES/67 ATA 2520-PASSENGER COMPARTMENT EQUIPMENT; TO PREVENT SERIOUS INJURY TO THE OCCUPANT DURING FORWARD IMPACTS IN EMERGENCY LANDING CONDITIONS.


DGCA/DHC8-400 SERIES/68 FAILURE OF THE MAIN LANDING GEAR STABILIZER BRACES. CF AD 2009-11R1 AS IN AD AS IN AD

DGCA/DHC8-400 SERIES/69 FLIGHT CONTROLS – POWER LEVER MODULE – INTRODUCTION OF OPERATIONAL CHECK OF GROUND SPOILER SWITCHES.

CF AD 2017-35 AS IN AD AS IN AD

DGCA/DHC8-400 SERIES/70 LANDING GEAR-NOSE LANDING GEAR DRAG STRUT LOCK LINK WEAR; REQUIRES A REPITIVE INSPECTION AND CORRECTIVE ACTIONS BASED

TC AD CF-2018-01 AS IN AD AS IN AD


ON THE INSPECTION FINDINGS.

DGCA/DHC8-400 SERIES/71 TO DETECT AND CORRECT BEARING CORROSION AND PREVENT DOOR OPERATION INTERRUPTIONS THAT COULD INHIBIT SAFE EVACUATION OF THE AIRPLANE IN AN EMERGENCY


DGCA/DHC8-400 SERIES/72 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 30, ICE AND RAIN PROTECTION- TO DETECT AND CORRECT LOOSE WINDSHIELD HEATER TERMINAL LUGS. LOOSE TERMINAL LUGS COULD CREATE SPARKS THAT LEAD TO BURNING OF THE LUGS AND, DUE TO THE EXCESSIVE HEAT, CRACKING OF THE WINDSHIELDS. IF NOT CORRECTED, SUCH A CONDITION COULD CAUSE A LOSS OF CABIN PRESSURE RESULTING IN AN EMERGENCY DESCENT


DGCA/DHC8-400 SERIES/73 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 27, FLIGHT CONTROLS- TO ADDRESS FAULTY SWITCHES IN THE POWER LEVER MODULE, WHICH COULD RESULT IN UNCOMMANDED DEPLOYMENT OF THE GROUND SPOILERS AND A POSSIBLE RUNWAY EXCURSION.


DGCA/DHC8-400 SERIES/74 ATA 25 - FURNISHINGS – FORWARD LAVATORY DOOR HINGE FLEXING TC AD CF-2018-09 AS IN AD AS IN AD

DGCA/DHC8-400 SERIES/75 ATA 57 - WINGS – CRACKED SPOILER ACTUATOR BRACKET TC AD CF-2018-21R1

AS IN AD AS IN AD

DGCA/DHC8-400 SERIES/76 FLIGHT CONTROLS – ELEVATOR POWER CONTROL UNIT BRACKET CRACKING


DGCA/DHC8-400 SERIES/77 FUSELAGE – NON-CONFORMING KEEL TENSION FITTINGS AND STRINGER END FITTINGS


DGCA/DHC8-400 SERIES/78 FIRE DETECTION SYSTEM - CONTAMINATION OF THE SENSOR CONTACTS FOR ADVANCED PNEUMATIC DETECTORS (APD) SYSTEM


DGCA/DHC8-400 SERIES/79 ATA 52 - DOORS – TRANSLATING DOORS LOOSE BOLTS TC AD CF-2014-08R1

AS IN AD AS IN AD

DGCA/DHC8-400 SERIES/80 ATA 54 - CRACKING OF THE NACELLE ATTACHMENT FITTING(S)

TC AD CF-2010-30R2

AS IN AD AS IN AD

DGCA/DHC8-400 SERIES/81 AIR TRANSPORT ASSOCIATION (ATA) OF AMERICA CODE 32, LANDING FAA AD 2019-18-05 AS IN AD AS IN AD


GEAR

DGCA/DHC8-400 SERIES/82 ATA 55 – STABILIZERS – ELEVATOR POWER CONTROL UNIT (PCU) ARM FITTINGS INSUFFICIENT FILLET RADIUS.


DHC-8-400 SERIES.pdf

Documents

Transcript of DHC-8-400 SERIES.pdf