N518DA

Part: POWER SUPPLY — DISCHARGED (CABIN) · airframe 67,654 hrs · 51,130 cycles

FOUND FWD CLOSET, ROW 1-4, ROW 10-11 EMERGENCY ESCAPE PATH LIGHTING INOP. REPLACED POWER SUPPLY AND BATTERY PACK CKS GOOD

Part: POWER SUPPLY — DISCHARGED (CABIN) · airframe 67,565 hrs · 51,073 cycles

FIRST CLASS EMERGENCY PATH LIGHTS INOP. REPLACED FIRST CLASS EMERGENCY LIGHT POWER SUPPLY/CHARGER.

Part: SKIN — CRACKED (FUSELAGE) · airframe 65,946 hrs · 49,997 cycles

INSPECTION OF THE STRINGER 4L SKIN LAP SPLICE YIELDED CRACK INDICATIONS. INTERNAL MFEC INSPECTION CONFIRMED A CRACK IN THE LOWER FASTENER ROW OF THE LOWER SKIN PANEL AT FS 383 & 384. THE CRACKED AREA WAS ROUTED OUT AND A REPAIR DOUBLER AND STRUCTURAL FILLER INSTALLED PER B727 SRM 53-30-3, FIG. 5 AND ER/A 380513-14AD.

Part: COMPRESSOR — STALLED (NR 2 ENGINE) · airframe 64,904 hrs · 49,292 cycles

COMPRESSOR STALL ON T/O ROLL NR 2 ENG. ABORT AT 30 KTS RETURN TO GATE. INSP INLET AND EXAUST. RAN ENG PER PFHB. ALL CK NORMAL, 13 KNT CROSS WIND GUSTING TO 19 KNTS.

Part: CHARGER — INOPERATIVE (AFT CABIN) · airframe 64,372 hrs · 48,907 cycles

BATTERY CHARGER INOP DAL (P/N 334701744) (S/N 7744).

Part: MEGAPHONE — INTERMITTENT (CABIN) · airframe 64,221 hrs · 48,799 cycles

CABIN MEGAPHONE INTERMITTANT OPS. REPLACED SAME.

Part: ATTACH ANGLE — CRACKED (LT WING) · airframe 64,193 hrs · 48,778 cycles

A .75 INCH CRACK AT I/B UPPER CORNER OF NR 5 LEADING EDGE FLAP ACTUATOR ATTACH ANGLE. REPAIRED SAME.

Part: SKIN — CORRODED (FUSELAGE) · airframe 64,193 hrs · 48,778 cycles

THE FUSELAGE SKIN WAS FOUND WITH SEVERAL AREAS OF CORROSION BETWEEN FS 1010 & 1070 AND BETWEEN STRINGERS 26L & 26R. THE SKIN WAS CUT NEAR FS 1070 FROM THE SKIN SPLICE AT STRINGER 26L TO THE SKIN SPLICE AT STRINGER 26R. THE SECTION OF SKIN FROM THE CUT TO THE BUTT SPLICE AT FS 1010 WAS REMOVED. A NEW SECTION OF SKIN WAS INSTALLED WITH AN EXTERNAL ALUMINUM SPLICE AT THE NEW CUT PER ER/A 378121-14, REV A.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 64,193 hrs · 48,778 cycles

CORROSION AT STR 26L O/B VERT LEG STA 950D - 950E. REMOVED AND REPLACED STRINGER FROM STA 950 - 1010.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 64,193 hrs · 48,778 cycles

CORROSION AT O/B VERT LEG OF STR 26L STA 1010 - 1030. REMOVED AND REPLACED STR SECTION FROM STA 1010 TO STA 1183.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 64,193 hrs · 48,778 cycles

FOUND DURING MV4 CORROSION VISIT NRC 375 CORROSION INSIDE STR 30 STA 1110 - 1130. REPLACED STR 30 FROM STA 1010 TO 1183.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 64,193 hrs · 48,778 cycles

FOUND DURING MV4 VISIT CORROSION INSIDE STR 27L STA 950B TO 950C. DRILLED UP NEW STR 27L STA 950 TO STA 1010.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 64,193 hrs · 48,778 cycles

FOUND DURING MV4 CORROSION VISIT NRC 335 CORROSION INSIDE STR 27L FROM STA 1010 TO 1030. REPLACED STR 27L FROM STA 1010 TO STA 1130.

Part: FRAME — CRACKED (FUSELAGE) · airframe 64,193 hrs · 48,778 cycles

THE FS 950F FRAME WAS FOUND WITH A 3 INCH LONG CRACK AT STRINGER 26L. THE CRACK IS TYPICAL OF BAC S/B 727-53A0195. THE FRAME WAS REPAIRED WITH A B727 SRM REPAIR AS REQUIRED OF THE S/B AND DOCUMENTED PER ER/A 378052-14AD.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 64,193 hrs · 48,778 cycles

CORROSION INSIDE STR 29L STA 1110 - 1130. REMOVED AND REPLACED STR 29L FROM STA 1010 TO 1183 PER SRM 53-10-1.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 64,193 hrs · 48,778 cycles

FOUND DURING MV4 VISIT CORROSION INSIDE STR 30 STA 970 - 990. REMOVED AND REPLACED STR 30 FROM 950 TO 1010 PER SRM 53-10-1.

Part: THRESHOLD — CORRODED (FUSELAGE) · airframe 64,193 hrs · 48,778 cycles

THE OUTER CHORD OF THE C2 DOOR CUTOUT LOWER SILL WAS FOUND WITH CORROSION ON THE O/B FLANGE BETWEEN FS 950E AND FS 990. THE CORROSION WAS BLENDED AWAY, ROTO PEENED, AND TREATED FOR CORROSION PREVENTION. AN EXTERNAL REPAIR STRAP WAS INSTALLED TO REPAIR THE DAMAGE PER ER/A 377932-14, REV A.

Part: RIB — CRACKED (CENTER WING) · airframe 64,193 hrs · 48,778 cycles

THE RBL 70.5 WING RIB WAS FOUND WITH A CRACK AT FS 760.96. THE CRACK IS TYPICAL OF BAC S/B 727-57-0112 AND PROGRESSED BETWEEN TWO FASTENER HOLES. THE HOLES WERE OVERSIZED TO ENSURE CRACK CONTAINMENT AND A REPAIR ANGLE INSTALLED PER S/B 727-57-0112 AND ER/A 377889-14AD, REV C.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 64,193 hrs · 48,778 cycles

CORROSION INSIDE STR 23L STA 950D TO 950E. REPLACED STR 23L FROM STA 950 TO 1010 DUE TO OUT OF LIMIT CORROSION ON ENTIRE LENGTH OF STR 23L (REF NR''S 99, 206, 208, 211, 212, 220, 223, 226, 230).

Part: STRINGER — CORRODED (FUSELAGE) · airframe 64,193 hrs · 48,778 cycles

CORROSION INSIDE STR 24L STA 950D TO 950E AROUND RIVETS. REPLACED STR 23L FROM STA 950 TO 1010 DUE TO OUT OF LIMIT CORROSION ON ENTIRE LENGTH OF STRINGER. (REF NR''S 209, 210, 213, 219, 222, 225, 229).

Part: STRINGER — CORRODED (FUSELAGE) · airframe 64,193 hrs · 48,778 cycles

CORROSION INSIDE STR 25L STA 950D TO 950E AROUND RIVETS. REPLACED STR 25L FROM STA 950 TO 1010 DUE TO OUT OF LIMIT CORROSION ON ENTIRE LENGTH OF STRINGER. (REF NR''S 207, 214, 218, 221, 224).

Part: ATTACH ANGLE — CRACKED (LE FLAP) · airframe 64,193 hrs · 48,778 cycles

FOUND DURING MV4 VISIT, .75 INCH CRACK AT I/B UPPER CORNER NR 5 L/E FLAP ACT ATTACH ANGLE. REMOVED L/E SUPPORT ROD AND INSTALLED DOUBLER PER MM 57-20-21 FIG 807. INSTALLED L/E SUPPORT ROD.

Part: RIB — CRACKED (NR 5 SLAT) · airframe 64,193 hrs · 48,778 cycles

A 2 INCH CRACK IN NR 5 SLAT L/E RIB LWR AFT CORNER I/B OF ACT ROD END. REPAIRED PER 727 M/M 57-54-0 PG 805.

Part: FLAP TRACK — CORRODED (TE FLAP) · airframe 63,254 hrs · 48,144 cycles

DURING OVERHAUL OF THE I/B FLAP TRACK ASSY, TYPICAL CORROSION WAS FOUND AT THE MLG AND SPOILER BEAM ATTACH PAD AREAS; AND TYPICAL WEAR WAS FOUND AT THE FWD ATTACH LUGS AND THE MLG DOOR HINGE FITTING ATTACH HOLES. PART REPAIRED PER ER/A 387423-14AD AND BF GOODRICH ENGINEERING REPAIR NR 23-0649.

Part: LIGHT — CONTAMINATED (RT WING)

DURING GROUND TRANSFER OF FUEL, THE NR 1 VALVE INDICATOR LIGHT SPARKED AND CAUGHT ON FIRE. DE-POWERED SWITCH AND FIRE EXTINGUISHED. MAINTENANCE FOUND LIGHT ASSY FULL OF FUEL. CHECKED FOR FUEL LEAKS, NONE FOUND. REPLACED LIGHT ASSY, OPN NOW NORMAL.

Part: BATTERIES — DISCHARGED (CABIN)

ON L/O, FOUND MID CABIN OVERHEAD EMERGENCY LIGHT INOP. REPLACED BATTERIES, OPERATION NOW NML.

Part: WEB — CRACKED (BS 1266)

FOUND ON C2 LETTER CK, .0625 INCH CRACK IN LT TORQUE BOX WEB LT SIDE STA 1266. REPAIRED PER MM 53-11-0.

Part: SKIN — CRACKED (BS 360-481)

LFEC INSPECTION OF THE STRINGER 4R SKIN LAP SPLICE BETWEEN FS 360 AND 481 INDICATED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN PANEL. HFEC INTERNAL INSPECTION CONFIRMED 4 CRACKS IN TWO CONSECUTIVE FRAME BAYS. THE ENTIRE SKIN LAP SPLICE WAS CUTOUT ALONG THE PANEL LENGTH. THE LAP WAS REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER INSTALLED PER ER/A 366743-14, REV A.

Part: SKIN — CRACKED (BS 481-680)

LFEC INSPECTION OF THE STRINGER 4R SKIN LAP SPLICE BETWEEN FS 481 AND 680 INDICATED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN PANEL. HFEC INTERNAL INSPECTION CONFIRMED 7 CRACK LOCATIONS ALONG THE PANEL. THE ENTIRE LAP SPLICE WAS CUTOUT ALONG THE PANEL LENGTH. THE LAP WAS REPLACED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 366740-14, REV A.

Part: BATTERY PACK — DISCHARGED (1L DOOR)

BATTERY DEAD ON EMERGENCY FLASHLIGHT AT 1L DOOR. REPLACED BATTERY AND BULB.

Part: LIGHT — INOP (CABIN)

MID CEILING EMER LIGHT WOULD NOT ELIMINATE WHEN CHECKING EMERGENCY LIGHTS. REPLACED LIGHT ASSY.

Part: SKIN — CRACKED (BS 681-740)

LFEC INSPECTION REVEALED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN AT THE STRINGER 4R LAP SPLICE BETWEEN FS 681 AND 740. INTERNAL HFEC INSPECTION CONFIRMED 12 CRACKS ALONG THE LENGTH OF THE PANEL. THE LAP SPLICE WAS CUT OUT ALONG THE ENTIRE PANEL LENGTH AND REPAIRED WITH AN EXTERNAL ALUMINUM REPAIR DOUBLER PER ER/A 366741-14, REV A.

Part: SKIN — CRACKED (BS 1100)

LFEC INSPECTION OF THE STRINGER 4R SKIN LAP SPLICE INDICATED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN PANEL. INTERNAL HFEC INSPECTION CONFIRMED 4 CRACK INDICATIONS AT APPROX FS 1100 WITH NO OTHER CRACK INDICATIONS FOR THE ENTIRE PANEL LENGTH. THE CRACKED AREA OF SKIN WAS TRIMMED OUT AND REPAIRED PER THE B727 SRM 53-30-3, FIG 5. THE REPAIR WAS DOCUMENTED PER ER/A 366742-14.

Part: TEE — CORRODED (BS 865)

AT HMV, FOUND RT DOOR ATTACH TEE CORRODED. SECTION REMOVED FOR MTC ACCESS AT APPROX FUSELAGE STA 865. CUT OUT SECTION OF DOOR ATTACH TEE. FABRICATED REPAIR PARTS PER MM 53-30-1 AND SRM 51-40-3. INSTALLED REPAIR PER M/M 53-30-1.

Part: SKIN — DENTED (RT AILERON)

UPPER SKIN HAS A SMALL DENT AT AFT INBD CORNER. REPAIRED PER SRM 57-50-5 FIG 3.

Part: SKIN — DAMAGED (LT AILERON)

IMPROPER SPLICE REPAIR ON LOWER SKIN. REPAIRED PER M/M 57-51-0.

Part: WEB — CRACKED (BS 1213)

WEB CRACKED .5 INCH ON LT VENTRAL STAIR TORQUE BOX AT STA 1213. REMOVED FASTENER, DYE CHECKED AREA, STOP DRILLED ENDS OF CRACK, FABRICATED REPAIR DOUBLER PER M/M 53-11-0 NR 19. INSTALLED REPAIR AS PER MM 53-11-0 NR 19.

Part: DOUDLER — CRACKED (LT TE MID FLAP)

REPAIR DOUBLER CRACKED ON LOWER AFT CHORD ANGLE 37 FROM I/B END OF FLAP. DAMAGE REPAIRED PER M/M 57-52-0 PAGE 807, ON SHOP ORDER 331063.

Part: FLAP — DAMAGED (LT TE FLAP)

AFT LWR CHORD IS CRACKED AT I/B AFT FLAP TRACK CUT OUT, TWO PLACES. ALSO, AFT LOWER CHORD ANGLE IS CRACKED 57 FROM I/B END. BOTH REPAIRS PER M/M 57-52-0 FIG 807.

Part: FLOORBEAM — WORN (BS 344)

CABIN FLOORBEAM UPPER CAP IS WORN THIN AT FLOOR PNL SCREW HOLE FS 344 RBL 12 TO LBL 45. BLENDED AREAS FOR FURTHER EVALUATION. FOUND BEAM OUT OF LIMITS PER 53-10-1 FIG 4. REMOVED T-CAP FROM RBL 60 TO LBL 60. STARTED DRILLING NEW T-CAP PER SRM 53-10-8. INSTALLED NEW T-CAP AND SPLICE RBL 60 LBL 60 PER SRM 53-10-9 PG 56.

Part: FRAME — CRACKED (BS 1233)

FRAME CRACKED NR 2 INLET S-DUCT HOUSING FRAME CRACKED ON LT SIDE FS 1233 AT INTERSECTION WITH HORSE COLLAR. REMOVED DAMAGE AND FABRICATED DOUBLERS PER SRM 51-400-3, INSTALLED DOUBLERS PER SRM 51-40-3.

Part: WEB — CRACKED (VERT STAB)

WEB - CRACKED VETICAL STAB INTERIOR FS 1303 WEB CRACKED AT STRINGER CUTOUT, RH SIDE FABRICATED REPAIR DOUBLER AND DRILLED PE R SRM 53-10-4 FIG 17BEGAN INSTALLING DOUBLER PER SRM 53-10-4 FIG 17.STOP DRILLEDCRACK AND DYE CHECKED PER SRM 53-10-4. COMPLETED INSTALLING DOUBLER PER SRM 53-10-4 FIG 17

Part: SKIN — CRACKED (VERT STAB)

VERTICAL STAB SKIN CRACKED. CUT OUT CRACK PER SRM 55-30-3 AND VERIFIED CRACK REMOVAL. FABRICATED REPAIR AND INSTALLED DOUBLER/REPAIR.

Part: BULKHEAD BEAM — CRACKED (BS 1183)

A CRACK WAS FOUND IN THE VERTICAL STIFFENER AT LBL 36.83 ON THE FWD SIDE OF THE BS 1183 BULKHEAD. THE CRACK IS APPROX 1 LONG AND IS LOCATED AT APPROX WL237 IN THE INBD RADIUS OF THE AFT CHORD. REPAIRED PER ERA 330932-14.

Part: SKIN — CRACKED (VERT STAB)

VERTICAL STAB SKIN CRACKED. DRILLED REPAIR DOUBLER PER SRM 55-30-3, CUTOUT DAMAGE PER SRM 55-30-3. VERIFIED CRACK REMOVAL AND INSTALLED REPAIR DOUBLER PER SRM 55-30-3.

Part: WEB — CRACKED (VERT STAB)

WEB - CRACKED VERT STAB INTERIOR FS1303 WEB CRACKED A T LOWER LH CORNER FABRICATED REPAIR DOUBLER AND DRILLED PE R SRM 53-10-4 FIG 17DYE CHECKED AND STOP DRILLED CRACK PER SRM 53-10-4. OK TO INSTALL REPAIR. INSTALLED REPAIR PER SRM 53-10-4 FIG 17

Part: RIB — CRACKED (NR 6 LE SLAT)

NR 6 SLAT HAS A CRACKED RIB ON INSIDE RADIUS, MARKED. DYE PENETRANT INSPECTED CRACK PER PS 900-6-3 NR 1, STOP DRILLED CRACK AND FABRICATED DOUBLER PER MM 57-40-0 FIG 814. OK TO INSTALL DOUBLER. INSTALLED DOUBLER ON NR 6 SLAT JUST O/B OF ANTI-ICE DUCT.

Part: FRAME — CRACKED (NR 2 LE SLAT)

NR 2 SLAT RACK FRAME CRACKED SECOND FROM RT END. REMOVED DAMAGE, FABRICATED DOUBLER PER MM 57-54-0 PG 818. INSTALLED DOUBLER PER MM 57-54-0 PG 818.

Part: SKIN — CRACKED (BS 1090)

SKIN IS CRACKED AT RIVET ON THE LT SIDE OF S1 STA 1090. INSP OF SKIN 2 EA CRACKS LT AND RT FIRST FAST, EACH SIDE OF S1 STA 1090. FABRICATED REPAIR DOUBLER AS PER SRM 53-30-3 PAGE 15B. OK TO INSTALL. INSTALLED DOUBLER PER SRM 53-30-3, TREAT PAINT PER SRM 53-30-3 PAGE 15B.

Part: SKIN — LOOSE (RT AILERON)

RIGHT O/B AILERON LOOSE C-MAX RIVETS ON OUTER SKIN SEVERAL PLACES, MARKED W/ RED CRAYON AND NUMBERS. FABRICATED DOUBLER PER SRM 57-50-5 FIG 3, INSTALLED SKIN SPLICE PER SRM 57-50-5 FIG 3. OK TO INSTALL SKIN SPLICE. REMOVED AND INSTALLED ON RC 654.

Part: LIGHT — INOPERATIVE (CABIN)

EMERGENCY LIGHT ABOVE L-1 DOOR INOP. REPLACED LIGHT ASSY AND BATTERIES, CKS GOOD.

Part: WEB — CRACKED (BS 1230)

.5 INCH CRACK IN TORQUE BOX LIGHTENING HOLE RT SIDE APPROX STA 1230. REPAIRED PER M/M 53-11-0 PG 828.

Part: SKIN — GOUGED (CARGO DOOR)

DURING INSPECTION OF C-3 CARGO DOOR, A SMALL GOUGE WAS FOUND IN THE EXTERIOR SKIN. THE DAMAGE WAS REPAIRED PER SRM 52-00-3.

Part: BLKHD CHANNEL — WORN (BS 720)

AT MID VISIT 2, FOUND VERT SUPPORT CHANNEL WORN AT TOP STA 720D ABOVE STR 26 LT. REMOVED DAMAGED SECTION PER SRM 53-10-9 FIG 9. DRILLED NEW DOUBLER AND INSTALLED PER SRM 53-10-9 FIG 9.

Part: PANEL — WORN (NR 4 TE FLAP)

HMV, LEADING EDGE O/B END WORN, NR 4 TRAILING EDGE FLAP. REPLACED WORN SEAL ON TRAILING EDGE PANEL, CUT OUT DAMAGE AND REPAIRED PER M/M 57-52-0 FIG 803.

Part: SKIN — CRACKED (NR 5 LE FLAP)

DURING SHOP INSPECTION, A CRACK WAS FOUND IN THE EXTERIOR SKIN 37.5 INCHES FROM THE OUTBOARD END AT THE FENCE ATTACH POINT. THE DAMAGE WAS REPAIRED PER THE B-727 M/M 57-54-0, PG 817 FOR NR 5 L/E SLAT.

Part: RIB — CRACKED (NR 5 LE FLAP)

DURING SHOP INSPECTION, RIB NR 17 WAS FOUND TO BE CRACKED. THE RIB WAS REPAIRED PER B-727 M/M 57-54-0 FOR NR 5 L/E SLAT.

Part: ANGLE — CRACKED (NR 5 LE FLAP)

DURING SHOP INSPECTION, THE LOWER ATTACH ANGLE WAS FOUND TO BE CRACKED AT THE ACTUATOR RIB. THE CRACK WAS REPAIRED PER THE B-727 M/M 57-54-0 FOR NR 5 L/E SLAT.

Part: SKIN — GOUGED (NR 1 LE SLAT)

DURING SHOP INSPECTION, NR 1 L/E SLAT WAS FOUND WITH LOWER SKIN GOUGED AT ACTUATOR ATTACH RIBS. REPAIRED PER SRM 57-50-3.

Part: FAIRING — CRACKED (NR 3 LE SLAT)

THE O/B TRACK FAIRING WAS CRACKED. REPAIRED AS PER MM 57-54-0 FOR NR 3 L/E SLAT.

Part: RIB — CRACKED (NR 3 LE FLAP)

DURING A SHOP INSPECTION, A CRACK WAS FOUND ON THE NR 3 RIB AT THE I/B TRACK ATTACH. A REPAIR WAS INSTALLED PER THE M/M 57-54-0 PG 807, FOR NR 3 L/E SLAT.

Part: COVE PANEL — CRACKED (NR 3 LE FLAP)

DURING A SHOP INSPECTION, A CRACK WAS FOUND ON A COVE PANEL LOCATED AT THE I/B UP STOP ATTACH POINT. A REPAIR WAS INSTALLED PER THE M/M 57-54-0, FOR NR 3 L/E SLAT.

Part: ANGLE — CRACKED (NR 2 LE SLAT)

DURING F-1 LETTER CHECK, FOUND NR 2 L/E SLAT COVE SKIN ATTACH ANGLE CRACKED. REPAIRED PER MM 57-54-0 PAR 5A.

Part: ANGLE — CRACKED (NR 7 SLAT)

DURING F-1 LETTER CHECK, FOUND NR 7 L/E SLAT COVE SKIN ANGLE CRACKED BELOW TAI DUCT. REPAIRED PER MM 57-54-0 PAR 5A.

Part: RIBS — CRACKED (LE FLAPS)

DURING INITIAL SHOP INSPECTION, FOUND RIBS NR 16 AND 17 CRACKED AT UPPER FORWARD CORNER. REPAIRED CRACKED AS PER MM 57-54-0.

Part: ANGLE — CRACKED (NR 1 LE SLAT)

DURING SHOP INSPECTION, NR 1 L/E SLAT LOWER COVE SKIN SUPPORT ANGLE WAS FOUND CRACKED. REPAIRED PER MM 57-54-0 FIG 812.

Part: CONNECTOR — LOOSE (LT 1 WINDSHIELD)

DURING CRUISE, WIRING CONNECTION AT TOP LEFT CORNER OF L-1 WINDSHIELD BEGAN TO SPARK AND BURN. SHUT OFF POWER ARCING STOPPED. FOUND TERMINAL CONNECTION VERY LOOSE. REPLACED TERMINAL DUE TO ARCING DAMAGE. OPERATION NORMAL.

Part: FITTING — PITTED (NLG)

DURING SCHEDULED TRIPLE LANDING GEAR CHANGE FOUND LT AND RT NOSE GEAR TRUNNION CAPS AND BEARINGS WORN AND PITTED. REPAIRED PER M/M 53-40-0.

Part: COWL — CRACKED (NR 1 ENGINE)

DURING SHOP INSPECTION, NR 1 ENGINE NOSE COWL WAS FOUND WITH LEADING EDGE LIP CRACKED. REPAIRED PER SRM 54-30-3.

Part: RIB — CRACKED (NR 3 LE FLAP)

NR 3 RIB CRACKED AT I/B TRACK ATTACH POINT. REPAIRED PER M/M 57-54-0 PG 807. FOUND DURING NR 3 L/E SLAT AT SHOP INSPECTION.

Part: ANGLE — CRACKED (NR 3 LE FLAP)

COVE ANGLE CRACKED AT I/B UP STOP ATTACH POINT. REPAIRED PER M/M 57-54-0, FOR NR 3 L/E SLAT AT SHOP INSPECTION.

Part: NOSE COWL — WORN (NR 1 ENGINE)

DURING SHOP INSPECTION, NR 1 ENGINE NOSE COWL WAS FOUND WITH THE AFT LIP WORN TO A KNIFE EDGE AT THE 6:30 TO 7:30 POSITION. REPAIRED PER SRM 54-10-3.