N297WA

Part: STRINGER — CRACKED (VERT STAB R/H) · airframe 61,819 hrs · 42,218 cycles

VERT. STAB R/H SIDE STRINGER CRACKED SIXTH FROM BOTTOM 3RD BAY DOWN REPAIR PER MM 55-30-000-8

Part: ANGLE — CRACKED (L/H WHEEL WELL) · airframe 61,819 hrs · 42,218 cycles

FOUND ON E-2 LETTER CK 1.25 INCH CRACK THRU ONE FASTENER HOLE TO FASTENER HOLE, AFT FLANGE OF VERTICAL ANGLE STA 870 TO KEEL BEEM. REPAIRED PER SRM 53-10-9D FIG 806D TIME LIMITED REPAIR

Part: MOUNT — CRACKED (NR 3 ENGINE) · airframe 61,720 hrs · 42,152 cycles

HFEC BOLT HOLE INSPECTION OF THE FWD ENGINE MOUNT ON THE NR 3 PYLON PER AD 97-05-08 INDICATED CRACKS IN HOLES -C- AND -D- OF BAC S/B 727-54A0010. THE HOLES WERE OVERSIZED WITH A .0312 INCH ADDITIONAL INSURANCE CUT TO REMOVE ALL CRACKS. LARGER DIAMETER FASTENERS WERE INSTALLED IN THE REWORKED HOLES PER ER/A 382517-14AD, REV A.

Part: SKIN — DAMAGED (ELEVATOR) · airframe 61,718 hrs · 42,151 cycles

DURING ACCOMPLISHMENT OF EO 4-57713-3AD ON SUBJECT ELEVATOR, FASTENERS HOLES THAT ATTACH THE UPPER SKIN PNLS TO THE REAR SPAR WERE FOUND OVERSIZED. REPAIR PER ER/A 410467-14AD.

Part: SKIN — GOUGED (FS 360, S-4L) · airframe 60,742 hrs · 41,524 cycles

FUSELAGE / SKIN / FS 360 / STRG. 4L : GOUGE REPAIR THE FUSELAGE SKIN WAS GOUGED OVER A 6" LENGTH AT FS 360, BELOW STRINGER 4L. THE SKIN WAS CUTOUT TO REMOVE THE GOUGEDAREA. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 381559-14, REV. A.

Part: BATTERY — DISCHARGED (RT / LT FUSELAGE) · airframe 59,704 hrs · 40,827 cycles

DURING LAYOVER CHECK FOUND RT CENTER OVERWING EMERGENCY LIGHT INOP. ALSO FOUND LT AFT OVERWING EMERGENCY LIGHT INOP. REPLACED BATTERIES AT BOTH LIGHTS OPS CHECKED GOOD.

Part: LIGHT — SMOKE (COCKPIT) · airframe 59,051 hrs · 40,386 cycles

CAPT REPORTED ENGINEERS O/H LIGHT BULB FLASHED AND CREATED SMALL AMOUNT OF SMOKE. CONTRACT MTC WAS CALLED TO A/C NO TROUBLE FOUND.

Part: SPAR — CRACKED (RT ELEVATOR) · airframe 58,822 hrs · 40,219 cycles

STABILIZERS / RT ELEVATOR / REAR SPAR : TAB HINGE CRACK REPAIR. THE REAR SPAR OF THE RT ELEVATOR WAS FOUND WITH TWO CRACKS EMANATING .25 INCH FROM THE SHEAR PLATE OF THE TAB HINGE BRACKET AT THE 2ND FROM OUTBD LOCATION. THE CRACKING IS TYPICAL OF AD 96-06-05 AND BAC S/B 727-55-0089. THE CRACKS WERE STOP DRILLED ON A TIME LIMITED BASIS PER THE REQUIREMENTS OF THE AD. THE DAMAGE AND TIME TRACKING REQUIREMENTS ARE DOCUMENTED PER ER/A 379578-14AD.

Part: LIGHT — INOPERATIVE (SEAT 4) · airframe 58,072 hrs · 39,699 cycles

SEAT MOUNTED EMERGENCY PROXIMITY LIGHTS ON SEAT 04B FOUND INOP ON L/O INSP. REPAIRED BROKEN WIRE AT SEAT OPERATION NORMAL.

Part: RIB — CRACKED (RT WING) · airframe 58,042 hrs · 39,676 cycles

THE UPPER RIB CHORD ON THE RT WING AT FS 760.95 AND RBL 70.85 WAS FOUND WITH A CRACK IN THE VERTICAL FLANGE OF THE CHORD. THE FLANGE WAS TRIMMED AWAY TO REMOVE THE CRACK AND REPAIRED WITH A REPAIR ANGLE MODIFICATION PER BAC S/B 727- 57-0112 AND ER/A 378263-14AD.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 58,035 hrs · 39,672 cycles

STRINGER 29 WAS FOUND CORRODED BETWEEN FS 950D AND 950F. REMOVED THE CORROSION BETWEEN FS 950D+10AND 950E+10. A NEW SECTION WAS FABRICATED AND SPLICED IN PLACE WITH STEEL REPAIR SPLICE CHANNELS PER ER/A 378232-14, REV A.

Part: SHEAR TIE — CORRODED (FUSELAGE) · airframe 58,035 hrs · 39,672 cycles

THE FRAME TO SKIN SHEAR CLIPS ON THE FS 970 FRAME WERE FOUND CORRODED ON THE SKIN FLANGES. THE CORROSION WAS REMOVED BY TRIMMING OFF THE FLANGES. THE SHEAR CLIPS WERE REPAIRED WITH ALUMINUM ANGLES. INSTALLED PER THE B727 SRM 53-10-4, FIG 11 AND ER/A 378259-14.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 58,035 hrs · 39,672 cycles

THE FS 1183 BULKHEAD WEB WAS FOUND WITH A 1 INCH CRACK AT RBL 25 AND WL 169. THE CRACK IS TYPICAL OF BAC S/B 727-53-0215. THE CRACK WAS CUT OUT OF THE WEB AND REPAIRED WITH AN ALUMINUM DOUBLER PER THE REQUIREMENTS OF THE S/B AND ER/A 378285-14.

Part: ANGLE — CRACKED (RT MLG WW) · airframe 58,035 hrs · 39,672 cycles

FOUND ON MV4 CK, .5 INCH CRACK RT MLG W/W I/B FWD VERTICAL SUPPORT ANGLE STA 870. REPLACED ANGLE PER B727 DRD 53-10-9D FIG 806B.

Part: STRINGER — CRACKED (VERTICAL STAB) · airframe 58,035 hrs · 39,672 cycles

A 1 INCH CRACK IN VERT STAB Z ANGLE STR S-8 LT SIDE IN TUNNEL, STA 157.2. REPAIRED PER 727 M/M 55-30-0 FIG 802.

Part: RIB — CRACKED (NR 5 SLAT) · airframe 58,035 hrs · 39,672 cycles

A .5 INCH CRACK ON NR 5 SLAT LT NOSE RIB UPPER LEG AT FWD SIDE OF AC ROD END. REPAIRED PER MM 57-54-0.

Part: ANGLE — CRACKED (RT WING SPAR) · airframe 58,035 hrs · 39,672 cycles

FOUND ON MV4 CK, 1 INCH CRACK IN NR 11 SPOILER ACTUATOR FITTING I/B ATTACH ANGLE AT LOWER BOLT. REPLACED ANGLE PER MM 57-42-0.

Part: BATTERY — DISCHARGED (CABIN) · airframe 57,958 hrs · 39,616 cycles

ON L/O, FOUND LT EMERGENCY OVERWING HATCH LIGHTS FLICKERING. REPLACED BATTERY AND BATTERY CHARGER. LIGHTS OP NORMAL.

Part: BATTERY — DISCHARGED (CABIN) · airframe 57,749 hrs · 39,469 cycles

BATTERIES IN EMERGENCY LIGHT ABOVE L1 DOOR WEAK. REPLACED BATTERIES, OPS NORMAL.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 57,431 hrs · 39,251 cycles

THE FS 1183 BULKHEAD WEB WAS FOUND WITH A CRACK AT THE LOWEST FASTENER HOLE COMMON TO THE RBL 8 VERTICAL BEAM. THE CRACK WAS REMOVED WITH A 1 X 1.5 CUTOUT IN THE WEB AND REPAIRED WITH A DOUBLER PER ER/A 377376-14AD.

Part: ENGINE — FAILED (NR 2) · airframe 57,192 hrs · 39,084 cycles

AT 37,000 FT, LOAD BANG AND DECREASE OF EPR ON NR 2 ENG AT.802 MACH OAT WAS 44 SAT, FUEL ON BOARD 26,000, FUEL TOTAL 147,000. THE EPR WAS REDUCED TO 1.3 AND A DESCENT TO LWR ALT. THROUGHOUT DESCENT NOTICED EPR VARIATIONS UP/DN. NO FURTHER MOVEMENT OF THROTTLE UNTIL LANDING. INSPECTED AND RAN IN ACCORDANCE WITH MM 72-00 PAGE 112G. FWD TO MCO AND PLAC AND INSTALLED PLACARD TO BLEED NR 2 ENG ABOVE 20,000. ENGINE SETUP FOR COMPRESSOR WASH.

Part: FIRE LOOP — INTERMITTENT (NR 2 ENGINE) · airframe 57,141 hrs · 39,053 cycles

AT 15,000 FT WITH B LOOP SELECTED FOR NR 3 ENGINE FIRE DETECTION SYS, NR 2 ENGINE FIRE LIGHT ILLUMINATED AND BELL. ABNORMAL POM C/W AND NR 2 ENG SHUTDOWN. FIRE LIGHT NEVER WENT OUT AND BELL INTERMITTENT. FOUND DETECTOR LOOP NR M447 BAD. REMOVED AND REPLACED LOOP, RAN ENG AT T/O AND PART POWER. LOOP AND ENG RUN, CHECK NORMAL. LOOP (S/N 3386) OFF, (P/N 264101400).

Part: LIGHT — INOPERATIVE (OVERWING) · airframe 57,087 hrs · 39,020 cycles

OVERHEAD EMERGENCY LIGHTS OVER THE FWD OVERWING ESCAPE DOORS INOP. REPLACED BATTERY PACK.

Part: BULKHEAD WEB — CRACKED (BS 1183)

THE FS 1183 BULKHEAD WEB WAS FOUND WITH A 1 INCH TYPICAL CRACK AT WL 178 AND LBL 8. THE CRACK IS TYPICAL OF BAC S/B 727-53-0175. THE CRACK WAS CUT OUT OF THE WEB AND REPAIRED WITH AN ALUMINUM DOUBLER PER THE S/B AND ER/A 368608-14AD. THE WEB WILL BE MODIFIED PER S/B REQUIREMENTS PRIOR TO 60K CYCLES.

Part: ANGLE — CRACKED (BS 1253)

TORQUE BOX Z ANGLE CRACKED LT SIDE STA 1253. REPAIRED PER SRM 51-40-3.

Part: FIRE LOOP — FAILED (NR 1 ENGINE)

NR 1 ENG B-FIRE LOOP ON MCO. A-LOOP FAULT LIGHT ILLUM, WOULD NOT TEST. CREW SHUT DOWN ENGINE IN FLT AND BLEW THE FIRE BOTTLE PER THE POM. REPLACED LOWER LOOP.

Part: CONNECTOR — DIRTY (NR 1 ENGINE)

INTERMITTENT FLASHING LIGHT SYS A FOR NR 1 ENG FIRE DETAT CRUISE, SMOOTH AIR. RAN PROCEDURE AND SHUT DOWN NR 1 ENG. REPLACED BLOWN FIRE EXT BOTTLE. FOUND OIL SOAKED CONNECTORS ON LOWER LOOP AND PYLON LOOP. CLEANED CONNECTORS, FIRE TEST NOW OPS NORMAL. INSPECTED ENG, NO EVIDENCE OF FIRE. RAN NR 1 ENG, NO TROUBLE FOUND.

Part: FIRE LOOP — MALFUNCTIONED (NR 1 ENGINE)

WHEN TESTING SYS, NR 1 DETECTOR SYS A NR 1 FIRE HANDLE LIGHT COMES ON AND STAYS ON AFTER TEST IS COMPLETE. IN FLIGHT SHUTDOWN FOR FIRE WARNING EARLY TODAY. B SYSTEM ALREADY ON MCO. REPLACED LWR A-B FIRE LOOP, DET UNIT AND CONTROL PANEL.

Part: ANGLE — CRACKED (NR 4 LE SLAT)

FOUND ON B2 LETTER CK, .5 INCH CRACK COVE SKIN ATTACH ANGLE I/B SIDE OF I/B UPSTOP NR 4 SLAT. REPAIRED PER MM 57-54-0.

Part: WEB — CRACKED (BS 1303)

FOUND DURING B-2 LETTER CHECK, VERT WEB ABOVE S- DUCT AT STA 1303 HAS A .5 INCH CRACK ON RT SIDE AT CUTOUT FOR STR. REPAIRED PER SRM 53-10-4 FIG 7.

Part: ANGLE — CRACKED (NR 3 TE MIDFLAP)

REPAIR DOULBER CRACKED ON LOWER CHORD ANGLE 33 FROM I/B END. REPAIRED PER M/M 57-52-0 FIG 802.

Part: SPAR — CRACKED (LT TE MIDFLAP)

AFT LOWER SPAR RAIL CRACKED TWO PLACES 33 AND 36 FROM I/B END. REPAIRED PER M/M 57-52-0 FIG 802.

Part: BRACKET — CRACKED (NR 5 SLAT ACT)

ANGLE CRACKED ON O/B SIDE OF NR 5 SLAT ACTUATOR BRACKET. REPAIRED PER M/M 57-54-0 PG 805.

Part: STRINGER — CRACKED (VERT STAB)

THE 3RD BAY DOWN INSIDE ACCESS 9504 STRINGER IS CRACKED ON LT SIDE. STOP DRILLED CRACK, DYE CKD TO VERIFY CRACK END, FAB REPAIR PARTS PER M/M 55-30-0 FIG 803. INSTALLED REPAIR.

Part: STRINGER — CRACKED (VERT STAB)

THE 3RD BAY DOWN INSIDE ACCESS 9504 ON LT SIDE STRINGER HAS .25 INCH CRACK EMANATING FROM BELOW BOLT HEAD. DYE CHECKED AREA PER PS 900-6-3. AREA VERIFIED AS CRACKED. STOP DRILLED ENDS OF CRACKS. DYE CKD TO VERIFY CRACK END. FAB REPAIR PARTS PER M/M 55-30-0 FIG 803. OK TO INSTALL REPAIR.

Part: BRACKET — CRACKED (NR 3 LE SLAT ACT)

NR 3 L/E SLAT ACTUATOR BRACKET CRACKED. REPAIRED PER M/M 57-54-0 FIG 804.

Part: ANGLE — WORN (NR 2 ENG COWL)

THE NR 2 ENGINE FWD COWL MATING SURFACE ANGLE (STA 1352) IS WORN AT 6 O'CLOCK POSITION. ROUTED OUT DAMAGE PER MM 53-11-0 PG 801. INSTALLED REPAIR ANGLE AND FILLES INSTALLED CLOSE OUT PANELS.

Part: STRINGER — CRACKED (TAIL)

DURING ROUTINE HMV, FOUND STRINGER CRACKED INSIDE ACCESS 9504ON RT SIDE 4TH BAY UP. REPAIRED PER M/M 55-30-0 ON NRC 668.

Part: STRINGER — CRACKED (FUSELAGE)

AT HMV, FOUND STRINGER CRACKED INSIDE ACCESS 9504 ON RT SIDE 4TH BAY UP. FAB NEW REPAIR PER MM 55-30-00, INSTALLED PER MM 55-30-00 FIG 803.

Part: SKIN — WORN (NR 1 TE MID FLAP)

LEADING EDGE SKIN WORN 60 FROM O/B END OF FLAP. REPAIRED PER M/M 57-52-0 FIG 803.

Part: STRINGER — CRACKED (VERT STAB)

STRINGER CRACKED INSIDE VERTICAL STAB RT SIDE 3RD BAY UP FROM LOWER WEB. REPAIRED PER M/M 55-30-0 FIG 803.

Part: ANGLE — CRACKED (RT WING)

AT HMV, FOUND BOTH O/B AND LWR I/B ANGLES CRACKED NR 6 LE FLAP ACT MNT POINT. REMOVED ACT, STOP DRILLED CRACKS, FABED DOUBLER, INSTALLED PER MM 57-20-21 FIG 807.

Part: SKIN — CRACKED (BS 1218)

AT HMV, FOUND SKIN AFT I/B CORNER OF OPENING FOR PNEU CONNECTION ACCESS PANEL STA 1218 RBL 10. STOP DRILLED CRACK DRILLED DOUBLER PER MM 53-30-0 FIG 872. INSTALLED PER MM 53-30-0 FIG 802.

Part: BRACKET — CRACKED (NR 1 LE FLAP)

ITEM AT HMV, FOUND BRACKET CRACKED, NR 1 L/E FLAP ACTUATOR ATTACH BRACKET CRACKED ON THE I/B SIDE AT BOTH UPPER AND LOWER ATTACK POINTS. REMOVED NR 1 L/E FLAP ACT. CKD PER PS 900-5-5 CRACKS CONFIRMED REMOVED BRACKET FAB NEW BRACKET PER MM 57-20-21 FIG 807 CONTINUED ON N/R 1046.

Part: HYDRAULIC PUMP — INOPERATIVE (NR 1 ENGINE)

NR 1 ENGINE HYDRAULIC PUMP CHANGED FOR A SYSTEM PRESSURE LOSS.

Part: ACTUATOR — FAILED (NR 3 LE SLAT)

LOST ALL HYD SYS A-PRESS AND FLUID 90 MILES FROM AIRPORT. USED ABNORMAL CHECKLIST. REPLACED RUPTURED NUMBER 3 SLAT ACTUATOR.

Part: BATTERIES — DISCHARGED (CABIN)

ON LAYOVER, FOUND FORWARD CROSS-AISLE CEILING LIGHT FOR EMERGENCY LIGHTS INOPERATIVE. REPLACED BATTERIES, LIGHTS CHECK GOOD.

Part: FRAME — CRACKED (R2 DOOR)

R2 DOOR FWD FRAME CRACKED AT UPPER HINGE CUTOUT. REPAIRED PER SRM 52-40-02 FIG 4.

Part: SKIN — CRACKED (BS 1095.9)

THE FUSELAGE SKIN WAS INITIALLY CRACKED AT STA 1095.9 OUTBOARD OF STR 1. THE DAMAGE WAS REPAIRED WITH A TIME LIMITED DOUBLER. WHEN THE PERMANENT REPAIR WAS BEING INSTALLED, TWO ADDITIONAL DAMAGE LOCATIONS WERE FOUND. A NEW PERMANENT REPAIR DOUBLER WAS INSTALLED IN ACCORDANCE WITH S/B 727-53A0204.

Part: HEAT EXCHANGERS — LEAKING (LEFT AND RIGHT)

AT 25,000 FT ENG'S AT IDLE, ENG ANTI-ICE ON, LOST CONTROL OF CABIN PRESSURIZATION. DURING EMERGENCY DECENT CABIN CLIMBED TO 12,000 FT. FOUND BOTH LEFT AND RIGHT HEAT EXCHANGERS LEAKING THROUGH CORE. REPLACED BOTH EXCHANGERS, LEAK AND PRESSURIZATION CHECKS GOOD.

Part: ANGLE — CRACKED (NR 2 LE SLAT)

NR 2 SLAT COVE SKIN ATTACH ANGLE AT TAI DUCT. PREVIOUS REPAIR DOUBLER CRACKED .25 INCH. FOUND DURING F-1 LTR CK TPAMM. REPAIRED PER 57-54-0.

Part: HYD HOSE — LEAKING (LT ELEVATOR)

ON GEAR RETRACTION, HAD LOSS OF A-SYSTEM HYD QTY AND PRESS. RETURNED SLC. FOUND LINE TO LEFT ELEVATOR ACTUATOR CRACKED. REPLACED LINE, OPERATION NORMAL.

Part: ANGLE — CRACKED (FS 910)

FOUND DURING E-2 LETTER CHECK, ANGLE AT STATION LEFT FS 910 MLG UPLOCK ATTACH FRAME WAS FOUND CRACKED. REPAIRED PER MM 53-11-0.

Part: FAIRING — CRACKED (NR 8 LE FLAP)

FOUND DURING E-2 LETTER CHECK, SEVERAL CRACKS AT NR 8 SLAT I/B TRACK FAIRING. REPAIRED PER MM 57-54-0.

Part: WEB — MIS MFG (FS 1223)

FOUND DURING E-2 LETTER CHECK, LIGHTNING HOLE TRIMMED OUT PAST STIFFENER LIP LT LWR TORQUE BOX, JUST AFT OF STA 1223. REPAIRED PER MM 53-11-0.