N579PE

Part: SPOILER — OUT OF RIG (WINGS)

FLT 705 - DFW-FWA - DURING CRUISE, THE FLIGHT CREW NOTICED THE AIRCRAFT SHUDDER AT .78 MACH. THE SHUDDER STOPPED WHEN THE AIRCRAFT SLOWED TO KIAS. THE CREW ELECTED TO DIVERT TO MEM. AN UNEVENTFUL LANDING WAS MADE. THE NR 1, NR 5, NR 6, NR 10 AND NR 11 SPOILERS WERE RIGGED PER THE B727 AIRCRAFT MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE. (M)

Part: FRAME — CRACKED (FUSELAGE)

DURING INSPECTION, IT WAS DISCOVERED THAT A FUSELAGE FRAME WAS CRACKED AT STATION 640. ACCOMPLISHED FRAME REPAIR IAW B727 SRM 51-40-3. (M)

Part: FRAME — CRACKED (FUSELAGE)

DURING INSPECTION, IT WAS DISCOVERED THAT A FUSELAGE FRAME WAS CRACKED AT STATION 580. ACCOMPLISHED FRAME REPAIR IAW B727 SRM 51-40-3. (M)

Part: WARNING LIGHT — ILLUMINATED (NR 2 ENGINE)

FLT 1844 - FWA-ORF - DURING TAKEOFF, THE NR 2 ENGINE FIRE WARNING LIGHT ILLUMINATED AND BELL SOUNDED. THE CREW DECLARED A EMERGENCY LANDING BACK AT FWA. THE CREW RAN EMERGENCY CHECKLIST AND DISCHARGED FIRE BOTTLE. DURING SHUT DOWN NR 2 ENGINE, THROTTLE DIFFICULT TO RETARD AND START LEVER BINDING TO CUTOFF. THE AIRCRAFT LANDED SAFELY. (M)

Part: LIGHT — INOPERATIVE (CABIN)

DURING ROUTINE MAINTENANCE, FOUND EMERGENCY EXIT LIGHT OVER L-1 DOOR INOPERATIVE. REMOVED AND REPLACED EMERGENCY EXIT LIGHT. OPS CHECK GOOD. AIRCRAFT RETURNED TO SERVICE. (X)

Part: SEAT TRACK — DAMAGED (BS 344-480)

DURING PHASE IN INSPECTION, DAMAGE WAS FOUND ALONG SEAT TRACK FROM STATION 344 TO 480, RIGHT BODY LINE 24.75. REPLACED SEAT TRACK FROM STATION 344 TO STATION 480, RBL 24.75. MATERIAL USED, PART NR CAB1520-792. ACCOMPLISHED IAW SUPPLEMENTAL TYPE CERTIFICATE (STC) SA1798SO. SEE NON-ROUTINE 5527 FOR DETAILS. (M)

Part: SEAT TRACK — DAMAGED (BS 1080-1135)

DURING PHASE-IN INSPECTION, DAMAGE WAS FOUND ALONG CABIN SEAT TRACK FROM BS 1080 TO 1135, RIGHT BODY LINE 45. REPLACED SECTION OF CABIN SEAT TRACK FROM BS 1080 TO BS 1135, RBL 45 IAW SRM 53-10-5 FIG 7. MATERIAL USED, PART NR BAC1520-792, 55 INCHES LONG. SEE NON-ROUTINE 5623 FOR DETAILS. (M)

Part: GUSSET — DAMAGED (BS 825)

DURING PHASE-IN INSPECTION, DAMAGE WAS FOUND ON GUSSET AT STATION 825 LEFT INNER FLANGE, LEFT BODY LINE. REPLACED GUSSET AT STATION 825 LEFT INNER FLANGE JUST ABOVE CENTER SECTION UPPER SKIN, LBL 70. MATERIAL USED, 7075-T6, .090 INCH, 5 INCH BY 3 INCH. REPAIR ACCOMPLISHED IAW SERVICE BULLETIN 727-53-0197. SEE NON-ROUTINE 3497 FOR DETAILS. (M)

Part: FLOORBEAM — DAMAGED (BS 400)

DURING PHASE-IN INSPECTION, DAMAGE WAS FOUND ALONG CABIN FLOORBEAM SUPPORT BS 400, RIGHT BODY LINE 55. INSTALLED REPAIR AT CABIN FLOORBEAM SUPPORT BS 400, RBL 55. MATERIAL USED, PART NR BAC1505-100617 AND BAC1490-2831, T-ANGLE 15 INCH LONG, SUPPORT ANGLES, 14 INCH AND 15 INCH LONG. REPAIR ACCOMPLISHED IAW SRM 53-10-8 FIG 1. SEE NON-ROUTINE 5622 FOR DETAILS. (M)

Part: SEAT TRACK — DAMAGED (BS 344-480)

DURING PHASE-IN INSPECTION, DAMAGE WAS FOUND ALONG SEAT TRACK FROM STATION 344 TO 480 RIGHT BODY LINE 45.5. REPLACED SEAT TRACK FROM STATION 344 TO STATION 480, RBL 45.5. MATERIAL USED, PART NR CAB1520-792. ACCOMPLISHED IAW SUPPLEMENTAL TYPE CERTIFICATE (STC) SA1798SO. SEE NON-ROUTIEN 5528 FOR DETAILS. (M)

Part: SEAT TRACK — DAMAGED (BS 950-1135)

DURING PHASE-IN INSPECTION, DAMAGE WAS FOUND ALONG CABIN SEAT TRACK FROM BS 950 TO 1135 RIGHT BODY LINE 25. REPLACED SECTION OF CABIN SEAT TRACK FROM BS 950 TO 1135, RBL 25. MATERIAL USED, PART NR CAB1520-792, 185 INCH LONG. REPAIR ACCOMPLISHED IAW SRM 53-10-5 FIG 7. SEE NON-ROUTINE 5624, 5630, 5634, 5637, 5642 AND 5665 FOR DETAILS. (M)

Part: SEAT TRACK — DAMAGED (BS 344-480)

DURING PHASE-IN INSPECTION, DAMAGE WAS FOUND ALONG SEAT TRACK FROM STATION 344 TO 480 LEFT BODY LINE 45.5. REPLACED SEAT TRACK FROM STATION 344 TO STATION 480, LBL 45.5. MATERIAL USED, PART NR BAC1520-792. ACCOMPLISHED IAW SUPPLEMENTAL TYPE CERTIFICATE (STC) SA1798SO. SEE NON-ROUTINE 5526 FOR DETAILS. (M)

Part: FLOORBEAM — DAMAGED (BS 344)

DURING PHASE-IN INSPECTION, DAMAGE WAS FOUND ALONG FLOORBEAM UPPER T-CAP AT STATION 344 LEFT BODY LINE 62.5 TO RT BODY LINE 62.5. REPLACED FLOORBEAM UPPER T-CAP AT STATION 344, LBL 62.5. MATERIAL USED, PART NR BAC1505-29222. REPAIR ACCOMPLISHED IAW SRM 53-10-8 FIG 1. SEE NON-ROUTINE 5599 FOR DETAILS. (M)

Part: FLOORBEAM — CORRODED (BS 327)

INSPECTION FOUND FORWARD LAV FLOORBEAM CORRODED AT STA 327, RBL 44-60. THE FLOORBEAM WAS REPAIRED IAW ECRA 5310-03889.

Part: BULB — FAILED (COCKPIT)

DURING POST FLIGHT, MAINTENANCE DISCOVERED THE EMERGENCY EXIT LIGHT OVER THE COCKPIT DOOR WAS INOPERATIVE. MAINTENANCE RE-LAMPED THE LIGHT ASSEMBLY AND PERFORMED AN SATISFACTORY OPS CHECK IAW BOEING 727 MM 33-50-4. THE AIRCRAFT WAS THEN RELEASED BACK TO SERVICE. (M)

Part: SKIN — DELAMINATED (NR 8 SPOILER)

INSPECTION FOUND THE RT WING NR 8 SPOILER DELAMINATED. THE SPOILER WAS REMOVED AND REPLACED IAW MM 27-62-1, PAGE 401-404.

Part: TAB — BENT (LT AILERON)

INSPECTION FOUND LT OUTBOARD AILERON TAB INBOARD END BENT. THE AILERON TAB WAS REMOVED AND REPLACED IAW MM 27-10-41, PAGE 401-403.

Part: SKIN — DELAMINATED (LT AILERON)

INSPECTION FOUND THE LT OUTBOARD AILERON TRAILING EDGE DELAMINATED SIX INCHES FROM OUTBOARD END. THE PANEL WAS REMOVED, REPAIRED, AND REINSTALLED IAW SRM 51-30-2.

Part: SKIN — BENT (RT TE FOREFLAP)

INSPECTION FOUND RT INBOARD FOREFLAP BENT AT O/B TRAILING EDGE. THE FOREFLAP WAS REMOVED AND REPLACED IAW MM 27-51-1.

Part: SKIN — DELAMINATED (LT TE FLAP)

INSPECTION FOUND LT WING OUTBOARD AFT FLAP UPPER SURFACE DELAMINATED 9 TO 15 INCHES FROM OUTBOARD EDGE. THE LT OUTBOARD AFT FLAP ASSEMBLY WAS REMOVED AND REPLACED IAW MM 27-51-12, PAGE 401.

Part: STRINGER — CORRODED (BS 1000)

INSPECTION FOUND STRINGER 29R CORRODED AT STA 1000. THE CORRODED AREA WAS CUT OUT AND REPAIR PARTS WERE INSTALLED IAW SRM 51-40-3, 51-10-2, AND SB 727-53-0179.

Part: RIB — CRACKED (NR 3 LE SLAT)

INSPECTION FOUND A 1.25 INCH CRACK AT AFT LOWER END OF NR 3 SLAT LEADING EDGE RIB AND A 1.25 INCH CRACK WAS FOUND AT FORWARD LOWER END OUTBOARD OF ACTUATOR ROD MOUNT. THE CRACKS WERE STOP DRILLED IAW SRM 51-30-2, A DOUBLER WAS INSTALLED IAW SRM 57-50-3, PAGE 26 AND 51-30-2, PAGE 14.

Part: BEAM — CRACKED (LT WING)

INSPECTION FOUND A .375 INCH CRACK IN LT WING J-BEAM ABOVE NR 7 SPOILER ACTUATOR. A REPAIR WAS INSTALLED IAW ECRA 5750-02914.

Part: SKIN — DELAMINATED (RT ELEVATOR TAB)

INSPECTION FOUND RT ELEVATOR CONTROL TAB TRAILING EDGE DELAMINATED. THE RT ELEVATOR CONTROL TAB WAS REMOVED AND REPLACED IAW MM 27-30-11.

Part: ANGLE — CORRODED (R-2 DOORWAY)

INSPECTION FOUND FLOOR SUPPORT ANGLE JUST INSIDE R-2 DOOR THRESHOLD AREA CORRODED AROUND SCREW HOLES. THE FLOOR SUPPORT ANGLE WAS REMOVED AND REPLACED IAW SRM 51-30-2, PAGE 4.

Part: INTERCOSTAL — CORRODED (BS 1050)

INSPECTION FOUND INTERCOSTAL CORRODED AT BS 1050, STRINGER 28R. THE INTERCOSTAL WAS REMOVED AND REPLACED IAW SRM 51-10-1, 51-30-2, AND 51-10-6.

Part: SKIN — TORN (BS 1050)

INSPECTION FOUND A TEAR IN RT LOWER FUSELAGE SKIN AT STA 1050, STRINGER 28R. THE TORN AREA WAS CUT OUT AND A DOUBLER WAS INSTALLED IAW SRM 53-30-3 AND 51-10-1.

Part: DUCT — BROKEN (NR 3 ENGINE)

NUMBER 3 ENGINE FIRE WARNING LIGHT BELL ON AFTER TAKEOFF. RETARDED THROTTLE, LIGHT WENT OUT. FOUND NOSE COWL ANTI-ICE DUCT BROKEN. REPLACED DUCT ASSEMBLY.

Part: BATTERY — DISCHARGED (CABIN)

LEFT OVER WING EMERGENCY EXTERIOR LIGHTS ARE INOP. CLEANED AND RECHARGED BATTERY PACK PER MM 33-50-00.

Part: BATTERY — DISCHARGED (CABIN)

MAIN CABIN OVERHEAD AT STATION 520 LEFT SIDE ESCAPE PATH BATTERY PACK DEAD. REPLACED BATTERY PACK PER MM 33-00-00.

Part: STRINGER — CRACKED (WS 304)

2 CRACK ON UPPER WING STRINGER AT W/S 304 IN NR 1 FUEL TANK. CUT OUT DAMAGED AREA AND INSTALLED A 'J' STIFFENER AS PER SRM 57-10-4 FIG 6.

Part: STRINGER — GOUGED (BS 1213)

INSPECTION FOUND STRINGER GOUGED AT LT FUSELAGE STA 1213 ABOVE PANEL NR 3901. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-10-3, FIGURE 2.

Part: STRINGER — CORRODED (BS 480)

INSPECTION FOUND STRINGER SPLICE AND STRINGER 28L CORRODED IN FORWARD CARGO COMPARTMENT AT STA 480. THE CORRODED AREA WAS REMOVED, A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-10-3.

Part: FRAME — CRACKED (BS 783.5)

INSPECTION FOUND A 2 INCH CRACK AT LOWER INBOARD FASTENER HOLE OF FRAME AT STA 783.5, RT SIDE. THE CRACK WAS STOP DRILLED, REPAIR PARTS WERE FORMED, HEAT TREATED, AND INSTALLED IAW BOEING DRAWING NR 65C36280.

Part: FRAME — CORRODED (CARGO DOOR)

INSPECTION FOUND FORWARD SIDE OF AFT BAGGAGE BIN DOOR CORRODED AT UPPER STOP. THE CORRODED AREA WAS CUT OUT. A DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-40-3.

Part: ANGLE — CRACKED (BS 1175)

LEFT AFT LAV FLOOR PANEL TO DITCH PAN ATTACH ANGLE AT LBL 50 HAS 3 FOOT LONG CRACK AT STA 1175. FABRICATED AND INSTALLED NEW ANGLE IN ACCORDANCE WITH SRM 51-30-2.

Part: FLOORBEAM — CORRODED (BS 1070)

INSPECTION FOUND UPPER SURFACE OF FLOORBEAM CORRODED AT STA 1070, RBL 40. THE CORRODED AREA WAS CUT OUT. FILLER AND DOUBLER WERE FABRICATED AND INSTALLED IAW SRM 53-10-8.

Part: FLOORBEAM — CORRODED (BS 303-344)

INSPECTION FOUND TOP OF FLOORBEAM CORRODED FROM BS 303-344, LBL 30 TO RBL 30. THE CORROSION WAS REMOVED. A T-CAP WAS FABRICATED AND INSTALLED IAW SRM 53-10-8.

Part: WEB — CORRODED (BS 780)

INSPECTION FOUND DELTA BEAM CENTER BOTTOM WEB CORRODED AT BS 780. THE CORRODED SECTION OF WEB WAS CUT OUT. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-40-2, FIGURE 1.

Part: RIB — CRACKED (RT TE MIDFLAP)

INSPECTION FOUND A .5 INCH CRACK IN INBOARD END RIB OF RT OUTBOARD MID FLAP LOWER END AT FAIRING LOWER BOLT. THE CRACK WAS STOP DRILLED. A REPAIR DOUBLER AND ANGLE WERE FABRICATED AND INSTALLED IAW SRM 51-40-2.

Part: FLOORBEAM — CORRODED (BS 380)

INSPECTION FOUNDTOP OF FLOORBEAM CORRODED AT STA 380, RBL 24 TO RBL 45.5. THE FLOORBEAM UPPER CHORD WAS REMOVED AND A REPLACEMENT WAS FABRICATED AND INSTALLED IAW SRM 53-10-8.

Part: SHEAR TIE — DENTED (BS 380)

FUSELAGE HAS DENT IN SHEAR TIE AT STA 380 STR 18L. CUT OUT, FABRICATED REPAIR DOUBLER AND FILLER AND INSTALLED IN ACCORDANCE WITH SRM 53-30-3 FIG 3.

Part: SKIN — DEBONDED (LT AILERON)

INSPECTION FOUND LT OUTBOARD AILERON OUTBOARD MOST TRAILING EDGE SPLIT/DEBONDED. THE AILERON TRAILING EDGE WEDGE WAS REMOVED. REPLACEMENT SKIN PANELS WERE FABRICATED AND INSTALLED IAW SRM 51-40-6 AND 51-30-2. THE AILERON WEDGE WAS REINSTALLED.

Part: FLAP — DELAMINATED (RT TE FLAP)

RIGHT INBOARD AFT FLAP IS DELAMINATED 32 THROUGH 54 FROM INBOARD END. REMOVED, REPAIRED AND REINSTALLED IN ACCORDANCE WITH MM 57-53-2.

Part: BRACKET — CRACKED (LT LE FLAP)

LEFT WING MOUNT BRACKETS CRACKED AT ALL FOUR CORNER AREAS WHERE NUMBER 2 LEADING EDGE FLAP ACTUATOR MOUNTS, INSIDE LEADING EDGE. LENGTH .75. FABRICATED AND INSTALLED NEW MOUNT BRACKET PER MM 27-91-1.

Part: TAB — DEBONDED (LT AILERON)

INSPECTION FOUND LEFT OUTBOARD AILERON TAB INBOARD END DEBONDED AND END FILLER MISSING. THE AILERON TAB WAS REMOVED AND REPLACED IAW MM 27-10-0.

Part: SKIN — CRACKED (LT WING LE)

INSPECTION FOUND A .3125 INCH CRACK IN LT WING LEADING EDGE SKIN CUTOUT ABOVE NR 3 SLAT INBOARD TRACK. THE CRACKED SECTION OF SKIN WAS CUT OUT, FILLER AND DOUBLER WERE FABRICATED AND INSTALLED IAW SRM 57-30-4.

Part: BRACKET — CRACKED (LT LE FLAP)

LEFT WING NUMBER 1 L/E FLAP ACTUATOR MOUNT BRACKET CRACKED BELOW INBOARD UPPER CORNER AREA INSIDE LEADING EDGE, LENGTH .75 FABRICATED AND INSTALLED NEW BRACKET IN ACCORDANCE WITH MM 27-81-1.

Part: SKIN — DENTED (BS 188)

INSPECTION FOUND FUSELAGE SKIN DENTED AT STA 188. THE DENTED AREA OF SKIN WAS CUT OUT, A DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-30-3.

Part: SKIN — DISBONDED (LT TE FOREFLAP)

INSPECTION FOUND LEFT WING TRAILING EDGE INBOARD FOREFLAP DISBONDED AT INBOARD EDGE OF LOWER SURFACE. A HOT BOND REPAIR WAS ACCOMPLISHED IAW ENGINEERING WORK ORDER 97-0630.

Part: CLAMP — BROKEN (A-SYS FILTER)

ON APPROACH, GEAR EXTENDED NORMAL THEN FLAPS SELECTED TO 30, A-SYTEM QUANTITY REDUCED TO 0. SYSTEM PUMPS WERE TURNED OFF. FOUND A-SYSTEM RETURN FILTER MOUNT CLAMP BROKEN. REPLACED RETURN FILTER ASSEMBLY PER MM 29-11-102 AND REPLACED ENGINE A-PUMP, EDP CASE DRAIN FILTER, PRESSURE FILTER AND FLUSHED A-SYSTEM PER MM 29-11-33, MM 29-11-41, MM 29-11-41 AND 29-11-0.

Part: SKIN — CORRODED (BS 1150)

INSPECTION FOUND SKIN CORRODED AT DRAIN LINE IN AFT CARGO COMPARTMENT, STA 1150, STRINGER 30. THE AREA WAS REPAIRED IAW SRM 51-10-1.

Part: SKIN — DENTED (RT ELEVATOR)

INSPECTION FOUND INBOARD UPPER SKIN TRAILING EDGE OF RIGHT ELEVATOR DENTED. A REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 55-20-3, FIGURE 5.

Part: RIB — CORRODED (BS 1130)

INSPECTION FOUND RIB CORRODED AT STA 1130, STRINGER 29R. THE CORRODED SECTION OF RIB WAS REMOVED. NEW SPLICE REPAIR PARTS WERE FABRICATED AND INSTALLED IAW SRM 53-10-4.

Part: STIFFENER — CRACKED (BS 328)

INSPECTION FOUND A 1.5 INCH CRACK IN FLOORBEAM LOWER CHORD STIFFENER AT STA 328, LBL 24. THE STIFFENER WAS REMOVED, A NEW STIFFENER WAS FABRICATED AND INSTALLED IAW SRM 51-10-1.

Part: STIFFENER — CRACKED (BS 328)

INSPECTION 'A', 2 INCH CRACK IN FLOORBEAM LOWER CHORD STIFFENER AT STA 328, RBL 48. THE CRACKED AREA WAS CUT OUT, A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-40-2.

Part: STIFFENER — CRACKED (BS 344)

INSPECTION FOUND A 1.5 INCH CRACK IN FLOORBEAM LOWER CHORD STIFFENER AT STA 344, BL 0. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-40-3.

Part: SPLICE — CORRODED (CARGO DR CUTOUT)

INSPECTION FOUND STRINGER 27R SPLICES AT AFT CARGO DOOR CUTOUT LOWER CENTER SECTION CORRODED. A REPAIR WAS INSTALLED IAW ECRA 5310-02509.

Part: DOOR FRAME — CRACKED (AFT ENTRY DR)

INSPECTION FOUND A HOLE AND CRACKS IN AFT ENTRY DOOR FRAME ON LT SIDE, 31 INCHES UP FROM FLOOR. THE DAMAGED AREA WAS CUT OUT, AN ANGLE REPAIR WAS INSTALLED IAW SRM 51-40-3.

Part: FRAME — CORRODED (BS 970)

INSPECTION FOUND STRINGER 29R AND FRAME CORRODED AT STA 970. THE CORROSION WAS REMOVED FROM STRINGER AND FRAME IAW SRM 51-10-6. THE AREA WAS REPAIRED IAW SRM 53-10-4.

Part: STRINGER — CRACKED (BS 940)

INSPECTION FOUND A 1.125 INCH CRACK IN STRINGER 18A OUTBOARD FLANGE AT LT SIDE AFT OF BS 940 FRAME. THE CRACK WAS STOP DRILLED, REPAIR PARTS WERE FABRICATED AND INSTALLED IAW ECRA 5310-03340, SRM 51-10-00 AND BOEING DRAWING 65C27166.

Part: ANGLE — CRACKED (FS 333)

INSPECTION FOUND A 1.5 INCH CRACK AT AFT END OF UPPER RIB CAP INSIDE OF RT WING LEADING EDGE, FS 333. THE CRACKED ANGLE WAS REMOVED AND A REPLACEMENT ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-20-2.

Part: ANGLE — CRACKED (WS 333)

INSPECTION FOUND A 1 INCH CRACK IN ANGLE OF LT WING LEADING EDGE CAVITY AT STA 333. THE ANGLE WAS REMOVED, A REPLACEMENT ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-20-2.

Part: SKIN — CRACKED (NR 5 LE SLAT)

INSPECTION FOUND A .50 INCH CRACK IN LOWER SKIN OF NR 5 SLAT. THE CRACK WAS LOCATED AT CORNER OF SKIN BELOW INBOARD TRACK. THE CRACK WAS STOP DRILLED. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 57-50-3.

Part: ACTUATOR — INOPERATIVE (NR 8 LE SLAT)

EWR - FLT 1900 - THE NR 8 LEADING EDGE SLAT WOULD NOT RETRACT AFTER TAKEOFF FROM EWR. THE FLAPS WERE CYCLED WITH NO EFFECT. THE AIRCRAFT WAS RETURNED TO EWR WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 8 LEADING EDGE SLAT ACTUATOR AT FAULT. THE NR 8 LEADING EDGE SLAT ACTUATOR WAS REMOVED AND REPLACED. THE LEADING EDGE SLATS WERE CYCLED SEVERAL TIMES PER MM 27-81-32, PAGE 406, AND OPERATION CHECKED GOOD. (X)

Part: TEST MODULE — INOPERATIVE (FLIGHT COMPT)

IAH - FLT 0423 - SEVERAL WARNING LIGHTS ILLUMINATED DURING TAKEOFF FROM IAH. THE TERRAIN WARNING, AUTOPILOT DISENGAGE, WINDSHEAR, ALL THREE ENGINE OIL LIGHTS, HYDRAULIC LIGHT, AILERON, RUDDER, AND ELEVATOR LIGHTS, AND MASTER WARNING LIGHT ALL ILLUMINATED. THE AIRCRAFT WAS RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. THE M833 AND M981 MASTER DIM AND TEST MODULES WERE REMOVED AND REPLACED. IN ADDITION, THE MASTER DIM AND TEST SWITCH WERE REPLACED. AN OPERATIONAL CHECK OF ALL WARNING LIGHTS WAS NORMAL (X)

Part: FITTING — CORRODED (LT TE FLAP)

THE LEFT INBOARD FLAP TRACK FORWARD SUPPORT FITTING WAS FOUND CORRODED IN THE INBOARD RADIUS FOR THE TRUNNION PIN. THE SUPPORT FITTING WAS REMOVED AND REPLACED IAW MM 27-51-31. (M)

Part: FLOORBEAM — CORRODED (BS 1130)

STATION 31J - THE AFT PIT WAS FOUND CORRODED ON THE BOTTOM OF THE CABIN FLOORBEAM AT BS 1130, LBL 60 TO RBL 60. THE CORROSION WAS REMOVED AND THE AREA WAS TREATED AND PRIMED. A STRAP WAS FABRICATED AND INSTALLED IAW ECRA 5710-01675, REV IR AND AERO CORP ENGINEERING 95-180, REV IR. (M)

Part: SPAR CAP — CORRODED (LT HORIZ STAB)

STA 31J - INSPECTION FOUND THE LEFT HORIZONTAL STABILIZER UPPER OUTBOARD SPAR CAP HAD INTERGRANULAR CORROSION. A REPAIR ANGLE WAS FABRICATED AND INSTALLED IAW SRM 55-10-5, DETAIL 1. (M)

Part: T-ANGLE — CORRODED (BS 500)

STATION 31J - INSPECTION FOUND CORROSION ON T-ANGLE AT BS 500, STRINGER 26R. A NEW T-ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-40-3. (M)

Part: SKIN — CRACKED (FUSELAGE)

STATION 31J - INSPECTION FOUND A 1 INCH CRACK IN THE LEFT FORWARD FUSELAGE SKIN AT THE FORWARD END OF THE L-1 DOOR LOWER HINGE CUTOUT. A DOUBLER AND FILLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-30-3. (M)