N612AW

Part: PANEL — CHAFED (STABILIZER)

CHAFE DAMAGE TO LEFT STABILIZER PANEL 275CL. MAINTENANCE BLENDED AND POLISHED DAMAGE AREA IAW BAE FAX BARA/AVR/3037/03-DC. (M)

Part: TAB — DENTED (ELEVATOR)

DENTS TO RT ELEVATOR AND TABS X 34 RECEIVED CONCESSION.

Part: STRUCTURE — DENTED (TE FLAP)

RIGHT FLAP INBOARD AND OUTBOARD TABS DENTED, RECEIVED CONCESSION.

Part: TAB — DENTED (LT ELEVATOR)

DENTS TO LEFT ELEVATOR AND TABS X 8 RECEIVED CONCESSION.

Part: TAB — DENTED (AILERON)

DENTS RIGHT AILERON INBOARD AND OUTBOARD TABS X 32 RECEIVED CONCESSION.

Part: TAB — DENTED (LT LE FLAP)

DENT LEFT FLAP INBOARD TAB X RECEIVED CONCESSION.

Part: DOOR — DENTED (MLG)

DENTS LEFT MAIN LANDING GEAR DOOR X 18 RECEIVED CONCESSION.

Part: SKIN — DENTED (FUSELAGE)

DENTS RIGHT FUSELAGE X 4 RECEIVED CONCESSION.

Part: TAB — DENTED (AILERON)

DENTS LEFT AILERON TABS X 9 RECEIVED CONCESSION.

Part: DOOR — DENTED (RT MLG)

DENTS RT MAIN LANDING GEAR X 26 RECEIVED CONCESSION.

Part: CONTROL BOX — FAILED (NR 1 ENGINE) · airframe 26,540 hrs · 35,779 cycles

NR 1 ENGINE FAILED IN FLIGHT, NO LEAKS NOTED OR DAMAGE NOTED. MAINTENANCE REMOVED AND REPLACED THE HIGH AND LOW PRESSURE FUEL FILTERS, FUEL CONTROL AND PRIMARY OVERSPEED CONTROL BOX.

Part: O-RING — FAILED (HYD SYSTEM) · airframe 26,218 hrs · 35,404 cycles

LOST ALL GREEN HYDRAULIC QUANTITY ON GEAR EXTENSION. MAINTENANCE REMOVED AND REPLACED O-RING ON PTU PLUG.

Part: A/C PACK — FAILED (AC BAY) · airframe 25,436 hrs · 34,477 cycles

AT 20,000 FEET NR 1 PACK VALVE LIGHT CAME ON, FLIGHT CREW TRIED TO RESET COULD NOT. THE RECIRCULATION VALVE WENT FREST COULD NOT RESET. NR 2 PACK VALVE LIGHT CAME ON, LOST PRESSURE. RESTORED CABIN PRESSURE AT 10,000 FEET PACK WORKED. MAINTENANCE PRESSURIZED A/C TO MAX DIFF, ON APU AIR AND ENGINE AIR LEAK CHECKED AT PACKS AT MAX DIFF GOOD, NO LEAKS NOTED. BOTH PACKS OPERATE NORMAL ON GROUND CHECKS, TEST FLIGHT SATISFACTORY.

airframe 24,866 hrs · 33,844 cycles

STRONG OIL SMELL IN CABIN WHEN APU AIR INTRODUCED INTO SYSTEM OK ON ENGINE AIR. MAINTENANCE PERFORMED CONTAMINATED DUCT CLEANING PROCEDURE. APU VACUUM TEST GOOD.

Part: ENGINE — FAILED (NR 1)

FLT 5510 - ORD-ATW - NR 1 ENGINE FAILED ON TAKEOFF OUT OF ORD. REMOVED AND REPLACED NR 1 ENGINE. (M)

Part: SKIN — WORN (NR 2 ENG COWL)

NR 2 ENGINE LEFT AFT AFT COWL DOOR INNER SKIN WORN THROUGH. PATCHED ABOVE DAMAGE PER PSI USING TA2 AND CHERRYMAXNUETS.

Part: DOOR — LACK OF LUBE (COCKPIT)

COCKPIT DOOR DIFFICULT TO OPEN FROM CABIN SIDE. LUBED AND RESHIMMED DOOR, OPS CHECK OK. (M)

Part: CONTROL CABLE — CORRODED (LT AILERON)

LEFT MAIN AILERON CONTROL CABLES ARE CORRODED AT PULLEY BETWEEN FUSELAGE FRAME NR 24 AND 25. REMOVED AND REPLACED LEFT MAIN AILERON CENTER CONTROL CABLES, TENSIONED AND SAFETIED. (M)

Part: LAYNARD — WORN (OXYGEN MASK)

OXYGEN MASK AT 20 RT REBREATHER FEL HAS HOLES AND PIN STRING FRAYED, 11 LT. REBREATHER FELT HAS HOLES. REPLACED FELTS RT 20, 11 LT. REPLACED LANYARD 20 RT. CHECKS OK. (M)

Part: VALVE — FAILED (ROW 2 DEF)

CABIN OXYGEN MASKS AT RIGHT SIDE ROW 2 DEF VALVE PISTON FAIL TEST. REMOVED AND REPLACED VALVE AT SEAT 2 DEF, OPS CHECK GOOD. (M)

Part: STRING — MISINSTALLED (OXYGEN DOOR)

OXYGEN CABIN DROP DOORS FOR MASKS AT POS RIGHT 7 DEF, RT 8 DEF, RT 12 DEF AND LT 5 ABC STRING HINGES ARE NOT LONG ENOUGH FOR DOOR TO SWING OPEN FULLY. ADJUSTED AND CHANGED STRINGS AT RT SIDE 7 DEF, 8 DEF, 12 DEF AND LT 5 ABC. ALL DOORS SWING FREE. OK FOR SERVICE. (M)

Part: DOOR — CRACKED (NR 4 ENGINE COWL)

NR 4 ENGINE INBOARD FAN DOOR, FORWARD INNER TITANIUM FIRESHIELD CRACKED AT CORNERS. REPAIRED CRACK BY PATCHING IAW BAE/AIR WISC SRM STD PRACTICES AND FOUND SERVICEABLE. (M)

Part: STRIP — CRACKED (NR 4 ENGINE COWL)

NR 4 ENGINE FORWARD OUTBOARD COWL DOORIS CRACKED AT INNER DOOR MIDDLE CAPPING. STRIP NEAR DRAIN LINE CLAMP. REPAIRED CAPPING STRIP PER BAE SRM 51-71-11 AND 12. (M)

Part: DOOR — CRACKED (NR 4 ENGINE COWL)

NR 4 ENGINE INBOARD FAN DOOR, 3RD DOOR RIB, CRACKED AT LOWER CORNER AREA NEAR VENT TUBE. REPAIRED CRACK BY PATCHING IAW BAE AIR/WISC SRM STD PRACTICES AND FOUND SERVICABLE. (M)

Part: ANGLE — MISSING (CARGO BAY)

ATW - FORWARD CARGO BAY: CENTER FORWARD CARGO FLOOR SUPPORT ANGLE AT FRAME 19D, SECTION MISSING. REPLACED FORWARD CARGO BAY CENTER FLOOR SUPPORT ANGLE AT FRAME 19D.

Part: RIB — CRACKED (RUDDER)

ATW - NR 1 (BOTTOM) RIB ON RUDDER IS CRACKED WITH A SMALL PIECE BROKEN OUT. REPLACED RIB PER REPAIR INSTRUCTIONS HC554H9005.

Part: STIFFENER — CRACKED (RT WING)

RIGHT WING TE SHROUD LOWER SKIN STIFFENER CRACKED INBOARD OF RIB 10. REMOVED AND REPLACED LOWER SKIN STIFFENER PER SRM. (M)

Part: SKIN — DAMAGED (FUSELAGE)

ATW - RIGHT MLG DOOR FORWARD LOWER CORNER DAMAGE DUE REPAIR IN 2,000 FLIGHTS PER AVRO FAX JM/0642-97. SEE SRM FOR SKIN REPAIR CRITERIA CURRENT TCA 25066 DUE REPAIR BY 27566 TCA. SEE FAX JM/RJ0317-98 FOR 500 FLIGHT EXTENSION TO 27566 TCA. REPAIRED FORWARD LOWER CORNER AND BOTTOM SKIN DAMAGE PER BAE SRM 53-81-11 FIG 204 AND BAE FAX REF JM/RJ0450-98.

Part: STIFFENER — CRACKED (LT WING)

LT WING TE SHROUD TOP SKIN STIFFENER CRACKED AT FORWARD END, INBOARD OF RIB NR 10. REPLACED LEFT TE WING SHROUD TOP SKIN STIFFENER INBOARD OF NR 10 RIB AT THIS TIME. (M)

Part: STIFFENER — CRACKED (LT WING)

LEFT WING TE SHROUD LOWER SKIN STIFFENERS, TWO HAVE TAG ANGLE CRACKED AT AFT END, BETWEEN RIBS 8/9. REPLACED TWO ANGLES ON TE SHROUD LOWER SKIN STIFFENERS BETWEEN RIBS 8/9 AT THIS TIME.

Part: STIFFENER — CRACKED (LT WING)

LEFT WING TE SHROUD TOP SKIN STIFFENER CRACKED AT FORWARD END INBOARD OF RIB NR 6. REPLACED TOP SKIN STIFFENER BETWEEN RIBS 5 AND 6 JUST INBOARD OF RIB 6 AT THIS TIME. (M)

Part: ANGLE — CRACKED (RT WING)

RIGHT WING TE TOP SKIN STIFFENER AFT TAG ANGLE CRACKED AT LOWER FLANGE BETWEEN RIBS 5 AND 6 OF SHROUD. REMOVED AND REPLACED AFT TAG ANGLE BETWEEN RIBS 5/6 FOR THE TOP SKIN STIFFENER. (M)

Part: STIFFENER — CRACKED (LT WING)

LT WING TE SHROUD TOP SKIN STIFFENER CRACKED AT FORWARD END, OUTBOARD OF RIB NR 8. REPLACED LEFT WING TE SHROUD TOP SKIN STIFFENER OUTBOARD OF RIB NR 8.

Part: STIFFENER — CRACKED (LT WING)

LT WING TE SHROUD TOP SKIN STIFFENER CRACK AT FORWARD END (BETWEEN RIBS 7/8). REPLACED LEFT WING TE SHROUD TOP SKIN STIFFENER BETWEEN RIB 7/8 AT THIS TIME.

Part: STIFFENER — CRACKED (RT WING)

RIGHT WING TOP SKIN TE STIFFENER CRACKED AT FORWARD END, INBOARD OF RIB 9, SHROUD AREA. REMOVED AND REPLACED STIFFENER PER SRM. (M)

Part: SKIN — DENTED (FUSELAGE)

ATW - REF W/C DATED 10-19-96, LT AFT FUSELAGE HAS DENT LOCATED 24 INCHES AFT OF LT PRESSURE BULKHEAD AND 6 INCHES BELOW 'N' NUMBERS. DENT IS 5 INCHES LONG BY MIN/D MAX - 1 INCHES/.078 INCH. REPAIRED DENT IAW BAE FAX DJR/RJO437-98.

Part: STIFFENER — CRACKED (RT WING)

RIGHT WING TE TOP SKIN STIFFENER CRACKED AT FORWARD END BETWEEN RIBS 7/8 OF SHROUD. REMOVED AND REPLACED STIFFENER PER SRM. (M)

Part: INTERCOSTAL — CORRODED (FRAME 18)

GUSSET PLATE AND FORWARD REST FLOOR SUPPORT INTERCOSTAL, LEFT OF CENTER, AT FRAME 18 IS CORRODED. INSTALLED NEW GUSSET PLATE.

Part: BRACKET — CRACKED (LT WING)

LEFT WING TE, HYDRAULIC LINE CLAMP BRACKET CRACKED AT FALSE SPAR RIB NR 5. REPLACED HYDRAULIC LINE CLAMP BLOCK BRACKET AT RIB 5 AT THIS TIME. (M)

Part: CAGE — DENTED (CARGO DOOR)

ATW - FORWARD CARGO DOOR AFT LOWER SEAL CAGE IS DENTED AND CRACKED. REPLACED FORWARD CARGO DOOR AFT LOWER SEAL CAGE.

Part: SILL — CORRODED (PAX DOORWAY)

FORWARD VESTIBULE, PAX AND SERVICE DOOR, SILL PLATE HAV SOME CORROSION AROUND SCREW HOLES AND OTHER SMALL AREAS. MINOR SURFACE CORROSION REMOVED FROM SILL PLATES, ALODINED AND PRIMED. (M)

Part: FITTING — LEAKING (COCKPIT OXY SYS)

COCKPIT OXYGEN SYSTEM HAS A LEAK. FAILED LEAK CHECK. REMOVED AND REPLACED 'T' FITTING BETWEEN SUPPLY GAUGE AND PRESSURE REDUCING VALVE UNDER RIGHT SIDE PANEL. COMPLIED WITH LEAK CHECK. ALL IAW MM. (M)

Part: CONTROL CABLE — CORRODED (RT AILERON)

THE CENTER FUSELAGE INTERCONNECT CABLES ARE CORRODED AT RIGHT WING ROOT. REMOVED AND REPLACED BOTH CENTER FUSELAGE INTERCONNECT CABLES AND ADJUSTED IAW MM 27-11-00. W/CS GENERATED FOR FUNCTIONAL TEST OF AILERON CONTROLS AND DISCONNECT. (M)

Part: MANIFOLD — LEAKING (NR 1 ENGINE)

NR 1 ENGINE FUEL LEAK AT BOTH MANIFOLDS AT START. REPLACED LEFT AND RIGHT FUEL MANIFOLDS, REF WORK CARD NR 29.

Part: MANIFOLD — LEAKING (NR 1 ENGINE)

NR 1 ENGINE FUEL LEAK AT BOTH MANIFOLDS AT START. REPLACED LEFT AND RIGHT FUEL MANIFOLDS, REF WORK CARD NR 29.

Part: INTERCOSTAL — CORRODED (FUSELAGE)

ATW - AFT VESTIBULE FLOOR SUPPORT STRUCTURE, FIRST INTERCOSTAL INBOARD OF AIRSTAIR RAILS, LT SIDE HAS A RIVET WITH CORROSION AROUND IT. DRILLED OUT RIVET, REMOVED MINOR SURFACE CORROSION, USED PROTECTIVE TREATMENT ON BARE SURFACE, PRINTED AND COVERED SURFACE WITH PRC. INSTALLED NEW RIVET.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

RIGHT REAR EMERGENCY EXIT LIGHT INOPERABLE. REMOVED AND REPAIRED EMERGENCY POWER SUPPLY.

Part: SLIDE — DEPLOYED (CABIN)

WITH A/C IN HANGAR FOR RON MX, REAR RT DOOR OPENED AND SLIDE WAS NOT DSIARMED AND WAS DEPLOYED DUE TO BEING UNSAFE. REMOVED AND REPLACED SLIDE. (M)

Part: LOCK MECHANISM — INOPERATIVE (COCKPIT DOOR)

FOUND COCKPIT DOOR LOCK MECHANISM INOP. REPAIRED LOCK MECHANISM. OPS CHECKED OK. (M)

Part: SUPPORT — CHAFED (FUSELAGE)

FAIRING SUPPORT FOR PANEL 281BT LOWER ATTACH POINT HAS THE REINFORCING PLATE CHAFED. THE CHAF IS 1 INCH LONG AND .018 INCH DEEP (LEFT SIDE OF FUSELAGE AT FRAME NR 25 BETWEEN STRINGERS 10 AND 12). FABRICATED PLATE USING DRAWING HC536B0065. INSTALLED FASTENERS USING DRAWING HC536H1215. ASSEMBLED WET, DEBURRED, AND PAINTED PER SRM CHAP 51.

Part: STRINGER — CRACKED (FUSELAGE)

STRINGERS OVER MAIN LANDING GEAR BAY CRACKED AT FRAME 29, STRINGER 7, 15, 19 FRAME 32 STRINGER (BEAM). REPAIRED IAW BAE REPAIR DRAWING HC536H9211 AND AIR FAX REF NR DS/W/TS/26605/97.

Part: STRINGER — CRACKED (FUSELAGE)

STRINGER (LONGERON) IN FLOOR FRAME 28-29 LEFT OF CENTER LINE, CRACKED AT GUSSET PLATE (UNDER FLOORBOARD 231KF). REPAIRED IAW AVRO FAX REF NR DJR/RJ0021-97 AND AIR FAX REF NR DS/W/TS/26605/97.

Part: SUPPORT — CHAFED (FUSELAGE)

FAIRING SUPPORT FOR PANEL 282BS LOWER ATTACH POINT HAS THE REINFORCING PLATE CHAFED. THE CHAF IS 1 INCH LONG AND .022 INCH DEEP, RIGHT SIDE OF FUSELAGE AT FRAME BETWEEN STRINGERS 10 AND 12. FABRICATED PLATE USING DRAWING HC536B0065. INSTALLED FASTENER USING DRAWING HC536H1215. ASSEMBLED WET, DEBURRED AND PAINTED PER SRM CHAP 51.

Part: BRACKET — WORN (RIGHT AILERON)

RIGHT AILERON INTERCONNECT CABLE CHAFING CABLE GUARD AND PULLEY BRACKET OF AILERON TRIM SYSTEM, ABOVE NR 4 FLAP TRACK. BRACKET AND CABLE ARE WORN. REPLACED ABOVE RIGHT AILERON INTERCONNECT PULLEY BRACKET W/C'S FOR WORN GUARD, DISTANCE TUBE AND RIGGING CHECKS.

Part: SILL — CORRODED (SERVICE DOOR)

RIGHT AFT SERVICE DOOR ENTRY SILL PLATE HAS A COUPLE OF SPOTS OF CORROSION IN THE RADIUS OF THE INNER FLANGE. REPLACED SILL PLATE AT AFT SERVICE DOOR.

Part: RIB — CHAFED (VERTICAL STAB)

VERTICAL STABILIZER LEADING EDGE STRUCTURE BEHIND ACCESS NR 325AL AND AR HAS TWO HOT AIR LINES PASSING THROUGH A DIAPHRAMS LIGHTNING HOLE AND CHAFING ON BOTH LEFT AND RIGHT SIDES. RIGHT SIDE HAS FLANGE OF HOLE WORN AWAY. REPAIRED VERTICAL STABILIZER LEADING EDGE RIG 1 ASSEMBLY IAW JM/RJ0038-97.

Part: BUSHING — MISDRILLED (RT WING)

UPON REMOVAL OF MANHOLE COVER, RIB 2 RIGHT WING SEVERAL BOLTS WOULD NOT REMOVE UPON DRILLING BOLTS OUT, DRILL OUT OF AILIGNMENT ON 3 BOLTS CAUSED ELONGATION 3 HOLES RIB 2. DRILLED HOLES A, B, AND C TO ACCOMMODATE BUSHINGS, MANUFACTURED BUSHINGS FROM 7075-T61. INSTALLED BUSHINGS PER FAXES AVOR JM/RJ00 45-97 AND DJR/RJ0055-97 ON RIB 2 RIGH WING.

Part: JO-BOLT — LOOSE (CTR WING TANK)

COMPLIED WITH A PERMANENT REPAIR TO LOOSE JO-BOLT FASTENERS INSIDE THE WING TANK CENTER SECTION AT RIB 0 AND RIB 2. AT THIS TIME THE LOOSE FASTENERS WERE MARKED WITH DYE. COMPLIED WITH JO-BOLT, REMOVED AND REPLACED AT WING CENTER SECTION RIB 0 PLUS 2 LEFT RIGHT PER INST.

Part: FLAP TRACK — WORN (NR 3 TE FLAP)

LEFT NR 3 FLAP TRACK TAB ROD TO CROSSHEAD PIVOT PIN INDICATES CRACKED SSI 57-55-123, SLEEVE ALSO WORN. INSTALLED NR 3 LEFT FLAP TRACK TO CROSSHEAD PIVOT BOLT ASSEMBLY WITH NEW BOLT AND SLEEVE.

Part: MEMBRANE — CRACKED (AFT FUSELAGE)

AFT FUSELAGE 'AIRBRAKE BAY UPPER MEMBRANE IS CRACKED AT RIGHT LOWER CORNER 36.5 INCH INBOARD OF RIGHT LOWER CORNER. REPAIRED AIRBRAKE BAY UPPER MEMBRANE AT RIGHT SIDE IAW AVRO DRAWING JM/RJO491-96.

Part: BOLT — CRACKED (FUSELAGE)

LEFT FRAME 29, AT STRINGER 12, BOTTOM BOLT AT WING ATTACH LUG NUT APPEARS TO BE SPINNING. REMOVED BOLT, FOUND HEAD CRACKED AT BOLT SHANK, BOLT CRACKED AT HEAD. REMOVED AND REPLACED BOLT PER SRM.

Part: INTERCOSTAL — CRACKED (CABIN)

AFT VEST FLOOR STRUCTURE BETWEEN FRAMES 41-43, CENTER INTERCOSTAL CRACKED UNDER GUSSET PLATE. INSTALLED REPAIR IAW SRM 51-71-11 PAGE 7 AND INSTALLED GUSSET PLATE.

Part: AIRSTAIR — CORRODED (CABIN)

FORWARD AIRSTAIR 1 STEP CORRODED (TOP). REPLACED STEP.

Part: SILL PLATE — CORRODED (PAX DOOR)

FORWARD SILL PLATE ON AFT PASSENGER DOOR CORRODED. REMOVED AND REPLACED FORWARD SILL PLATE AT AFT PASS DOOR.

Part: MANIFOLD — FAILED (NR 2 ENGINE)

INSPECTED FUEL MANIFOLD FOR EVIDENCE OF SOOT AND DISCOLORATION IND. FUEL FIRE, PERFORMED ET INSPECTION OF 5TH SCALLOP FROM TOP FOR CRACKS IAW TEXTRON SPEC PROCEDURE. PERFORMED DV INSPECTION OF RT FUEL MANIFOLD, S/N 863. FOUND A SMALL VISUAL IND IN THE 5TH SCALLOP . W/C GENERATED FOR REMOVAL OF THE RT FUEL MANIFOLD.

Part: SLIDE — DAMAGED (CABIN)

DEPLOYED THE LEFT FORWARD ESCAPE SLIDE S/N 0548, PER MM 25-60-11 PAGE 501 APRA 1A, 1C, AND ZW CHECK LIST 25-60-36-06. THEN REMOVED THE SLIDE FOR A DETAILED VISUAL INSPECTION, FORWARDED THE CHECK LIST WITH THE SLIDE TO THE SHOP. UPDATE TASK P/N 625601102, S/N 612-1. DEPLOYED SLIDE, VISUALLY INSPECTED AND UNCOVERED A SMALL HOLE IN SLIDE AFTER DEPLOYMENT. SLIDE DEPLOYED NORMALLY AND INFLATED WELL ABOVE PRESSURE MINIMUMS. INSTALLED SLIDE.

Part: EEL CONNECTOR — DIRTY (CABIN)

DEN - FLT 364 - LEFT AND CENTER EXIT SIGNS IN FORWARD VESTIBULE INOPERATIVE.

Part: FRICTION BRAKE — OUT OF ADJUST (RUDDER)

IN EITHER DIRECTION THE RUDDER WOULD NOT RETURN TO CENTER, THE CAPTAINS AND FLIGHT OFFICERS RUDDER PEDALS INPUTS HAVE SAME EFFECT. ADJUSTED RUDDER CABLE COMPENSATOR FRICTION BRAKE. (M)

Part: INTERCOSTAL — BENT (CARGO BAY)

INTERCOSTAL RIB BETWEEN FRAME 20 AND FRAME 21, RT LOWER SIDE, FORWARD CARGO BAY, BENT. REPLACED INTERCOSTAL RIB PER FAX DJH/RJ0504-95 DATED 4-5-95.

Part: STIFFENER — CORRODED (FUSELAGE)

FOUND CORROSION ON FRAME 29 STIFFENERS AT RT STATION 25.94 AND LEFT STATIONS 25.94, 31.13 AND 36.62. COMPLIED WITH EO E95/005/653 ORIG ISSUE ON FRAME 29 STIFFENERS AT RT STATION 25.94 AND LEFT STATIONS 25.94, 31.13 AND 36.62 TO REMOVED CORROSION.

Part: CLEAT — CRACKED (LT WING)

LEFT WING TRAILING EDGE STRUCTURE BETWEEN RIBS 7 AND 8 HAS A CRACKED CLEAT ATTACHING STIFFENER TO THE REAR FALSE SPAR. REMOVED AND REPLACED CLEAT BETWEEN LEFT WING TRAILING EDGE BETWEEN RIBS 7 AND 8 IAW BAE 146-300 SRM.

Part: FALSE SPAR — CRACKED (LT WING)

LEFT WING TRAILING EDGE FALSE SPAR HAS A 2.50 INCH CRACK AT THE INBOARD LIFT SPOILER CENTER HINGE POINT. STOP DRILLED CRACK. C/W PLATE REPAIR OVER LEFT WING TRAILING EDGE OF FALSE SPAR JUST INBOARD OF LIFT SPOILER CENTER HINGE POINT IAW REPAIR DRG HC572H9036 AND BAE 146-300 SRM.

Part: RAILS — CORRODED (AIR STAIR)

INNER AIR STAIR RAIL (AFT STAIRS) AFT END, CORRODED. REPLACED INNER AIR STAIR RAIL (TRACK ONLY) ON AFT STAIRS.

Part: SILL — CORRODED (SERVICE DOOR)

AFT SERVICE DOOR SILL PLATE HAS SOME CORROSION. REPLACED AFT RT SILL PLATE.

Part: TREAD PLATE — CORRODED (AIRSTAIR)

FORWARD AIRSTAIRS, 4TH TREAD PLATE FROM BOTTOM, CORRODED. REMOVED AND REPLACED 4TH FROM BOTTOM TREAD PLATE. ALSO, REMOVED AND REPLACED AFT TREAD PLATE SUPPORT BRACKET DUE TO BEING CORRODED.

Part: ROD END — CRACKED (AILERON)

LEFT INNER AILERON TRIM TAB ROD, SUSPECT CRACKED FERRULE, NEEDS CLEANING, STRIPPING AS NECESSARY. REMOVED AND REPLACED ROD END.

Part: CABLES — CORRODED (AILERONS)

AILERON INTERCONNECT CABLES HAVE SIGNS OF CORROSION AT BOTH WING ROOT PULLEYS ON LT AND RT SIDES. ALSO, ALL 4 PULLEYS HAVE RUST DEPOSITS. REMOVED AND REPAIRED BOTH CENTER SECTIONS OF AILERON INTERCONNECT CABLE CIRCUITS PER MM. REMOVED ALL 4 PULLEYS AND CLEANED RUST DEPOSITS. REINSTALLED PULLEYS AND TENSIONED CABLES PER MM. FUNCTION TEST OF DISCONNECT SYSTEM OK. REF: WC 5005.

Part: FIREWALL — CRACKED (APU)

FOUND APU BAY FORWARD WALL CRACK ABOVE EXHAUST PIPE LOOKING FROM ECS BAY. REMOVED AND REPLACED APU FIREWALL. ALL WORK ACCOMPLISHED IAW BAE DRAWING P/N HC260H9000 AND PARTS SUPPLIED IN MOD KIT P/N HCM36179A-A01. EXISTING TITANIUM DISHING RE-USED IN LIEU OF MISDRILLED SUPPLIED INNER SKIN. BOLT HOLES IN SKIN DYE CHECKED FOR CRACKS.