N330DL

Part: ATTACH FITTING — CORRODED (HORIZ STAB) · airframe 48,607 hrs · 38,678 cycles

DURING ACCOMPLISHMENT OF 03-069697-03 NUMEROUS ATTACHMENT LUGS REQUIRED MACHINING BEYOND THE LIMITS PROVIDED, IN ORDER TO REMOVE ALL CORROSION DAMAGE FOUND. LUGS WERE REWORKED PER INSTRUCTIONS CONTAINED IN ERA 385802-14AD.

Part: SKIN PANEL — CRACKED (FUSELAGE) · airframe 48,607 hrs · 38,678 cycles

DURING ACCOMPLISHMENT OF 03-058543-03, ME-01 EXISTING REPAIRS AND NEW CRACK DAMAGE WERE NOTED ON THE KEEL BEAM LOWER SKIN PANEL. THE SUBJECT SKIN PANEL WAS REPLACED PER INSTRUCTIONS CONTAINED IN ERA 385772-14.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 48,607 hrs · 38,678 cycles

DURING MODIFICATION OF THE BL 24 FLOORBEAMS PER EO 03-056673-03AD ADDITIONAL WORK WAS REQUIRED DUE TO ADDITIONAL DAMAGE INCURRED. ERA 385831-14AD IMPLEMENTS THE LBL 24 BEAM MOD, PROVIDES NEW REPAIRS FOR THE BEAM WEBS AND ADDRESSES INCURRED DAMAGE.

Part: FITTING — CORRODED (VERTICAL STAB) · airframe 48,607 hrs · 38,678 cycles

CORROSION DAMAGE WAS FOUND ON THE VERTICAL STAB NR 2 FIN LUG AND THE NR 11 BODY CLEVIS LUG. CORROSION WAS REMOVED AND REWORKED PER ERA 385810-14.

Part: SKIN — DENTED (FUSELAGE) · airframe 48,607 hrs · 38,678 cycles

A DENT WAS NOTED IN THE FUSELAGE SKIN AT BS 380, BETWEEN S17L AND S18-L. THE DENT WAS CUT OUT AND REPAIRED PER ERA 385827-14.

Part: SKIN — GOUGED (FUSELAGE) · airframe 48,607 hrs · 38,678 cycles

THE FUSELAGE SKIN WAS FOUND DENTED AND GOUGED NEAR FS 178 AND STRINGER 24R. THE DAMAGED SECTION OF SKIN WAS CUT OUT AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 087582-14, REV A.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 48,607 hrs · 38,678 cycles

THE FUSELAGE SKIN WAS FOUND DAMAGED AROUND 2 NUT PLATE HOLES USED FOR ATTACHMENT OF A WING TO FUSELAGE FAIRING PANEL AT FS 760 BETWEEN STRINGERS 19R & 20R. THE DAMAGED HOLES WERE REMOVED WITH 1.5 X 1 INCH LOCAL CUTOUTS. THE CUTOUTS WERE REPAIRED WITH A SINGLE ALUMINUM DOUBLER/TRIPLER REPAIR PER ER/A 087539-14, REV A.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 48,607 hrs · 38,678 cycles

THE FS 520 FLOORBEAM WAS FOUND WITH 1 INCH TO 2 INCH CRACKS NEAR THE UPPER CAP FLANGE AT RBL & LBL 24 & 45. THE CRACKS WERE TYPICAL OF BAC S/B 737-53-1120. THE UPPER CAP WAS TRIMMED OFF TO REMOVE ALL CRACKS. A NEW CAP WAS FABRICATED FROM ALUMINUM EXTRUSION AND INSTALLED PER ER/A 087489-14, REV A.

Part: STOP FITTING — DAMAGED (CARGO DOOR) · airframe 48,607 hrs · 38,678 cycles

DURING ACCOMPLISHMENT OF EO 3-059252-3AD, OPN 0301, (S/B 737-52A1100), A 65-46861-0) FITTING WAS FOUND. EO INSTRUCTIONS REQUIRE ENGINEERING EVALUATION. EVALUATION FOUND THAT FITTING REQUIRED REPLACEMENT PER S/B 737-52-1065. FITTING REPLACED PER S/B 737-52-1065 PER DELTA ERA 423638-14AD.

Part: FRAME — CRACKED (CARGO DOOR) · airframe 48,607 hrs · 38,678 cycles

THE LOWER FORWARD FRAME OF THE C1 DOOR HAD A TIME-LIMITED REPAIR PREVIOUSLY INSTALLED AND NEEDED PERMANENT REPAIR INSTRUCTIONS. PERMANENT REPAIR ISSUED VIA ERA 377407-14AD, REV A.

Part: KEELBEAM — CRACKED (FUSELAGE) · airframe 47,967 hrs · 38,409 cycles

THE LT STRINGER 18A SHEAR BEAM AT FS 727 WAS FOUND WITH A 1 INCH CRACK EMANATING FROM THE EDGE OF THE WEB. THE CRACK IS TYPICAL OF THOSE SHOWN IN BAC S/B 737-53-1066, HOWEVER THE S/B IS NOT EFFECTIVE FOR THIS AIRCRAFT. THE CRACK WAS STOP DRILLED AND REPAIRED PER ER/A 381542-14, REV A.

Part: KEELBEAM — CRACKED (FUSELAGE) · airframe 46,494 hrs · 37,773 cycles

THE RT STRINGER 18A SHEAR BEAM WAS FOUND WITH A WEB CRACK AT FS 727. THE CRACK IS TYPICAL OF THOSE FOUND IN BAC S/B 737-53-1066, HOWEVER THE S/B IS NOT EFFECTIVE FOR THIS AIRCRAFT. THE CRACK WAS STOP DRILLED AND REPAIRED WITH A STEEL REPAIR CHANNEL PER ER/A 380238-14, REV A.

Part: RELAY — FAILED (BOOST PUMP) · airframe 45,854 hrs · 37,495 cycles

DURING CLIMB RIGHT CENTER LOW PRESSURE LIGHT ILLUMINATED. CB POPPED RETURNED TO EWR. - REPLACED CONTROL RELAY FOR RT CENTER FUEL BOOST PUMP

Part: LIGHT — INOPERATIVE (ROW 10) · airframe 44,615 hrs · 36,958 cycles

ON LAYOVER, EMERGENCY LIGHT INOP AT ROW 10 DEF. REPLACED LIGHT ASSY, CKS GOOD.

Part: SEAT — CRACKED (ROW 3) · airframe 43,264 hrs · 36,348 cycles

SEAT ROW 3 DEF LOOSE ON MOUNTS LIKE A ROCKING CHAIR. FOUND SEAT FRAME CRACKED. REPLACED SEAT ASSEMBLY.

Part: FRAME — CRACKED (BS 332)

THE AFT DOOR JAMB FRAME OF THE R1 DOOR OPENING WAS FOUND WITH A 3 INCH LONG CRACK UNDER UPPER DOOR STOP FITTING. THE CRACKED FRAME WAS REPAIRED PER THE REQUIREMENTS OF B737 SRM 53-10-4, FIG 1 AND DOCUMENTED PER ER/A 366934-14AD.

Part: ACTUATOR — FAILED (STAB TRIM)

RUNAWAY STAB TRIM ON SHORT FINAL. GO-AROUND MADE. REPLACED STAB TRIM ACTUATOR.

Part: SKIN — GOUGED (BS 489)

SEVERAL GOUGES AND NICKS WERE FOUND IN THE EDGE OF THE SKIN O THE AFT SIDE OF THE C1 DOOR CUTOUT AT APPROX FS 489, BETWEEN S21R AND S23R. REPAIRED PER ERA 331462-14.

Part: INTERCOSTAL — CRACKED (BS 337)

DURING INSPECTION PER SI 3-55852-12, THE R1 DOOR AFT FRAME INTERCOSTALS BETWEEN FS 332 AND 344 WERE FOUND CRACKED AT 3 LOCATIONS S8A, 10A, AND 11A. REPAIRED PER ERA 331432-14AD.

Part: BLKHD WEB — CRACKED (BS 178)

THE BS 178 BULKHEAD WEB WAS FOUND CRACKED BENEATH THE VERTICAL STIFFENERS AT LBL 5.7 AND RBL 5.7. DAMAGE REMOVAL RESULTED IN A 1.45 INCH LEFT AND RIGHT BY 1.2 INCH UP AND DOWN CUTOUT ON THE LT SIDE AND A 1.5 INCH LEFT AND RIGHT BY 5.1 INCH UP AND DOWN CUTOUT ON THE RT SIDE. DAMAGE WAS FOUND ON LAYOVER IN ATL. ACCOMPLISHED REPAIRS PER SRM 53-10-11, REF DL ERA 303315-14.

Part: COWL — DENTED (ENGINE)

DURING SHOP VISIT, ENGINE NOSE COWL ASSEMBLY WAS RESTORED PER CMM 65-85378. OUTER SKIN DENTED AT 5:30 POSITION. REPAIRED PER SRM 51-40-2.