N918DE

Part: FUSE — FAILED (EMERGENCY LIGHTS) · airframe 66,619 hrs · 49,119 cycles

EMER LIGHTS ROW 31-36 INOP. RPLCD FUSE ON BATTERY PACK. ALL EMER LIGHTS NOW CK GOOD. REF MD88 AMM 33-50. (LP6658807)

Part: BATTERY PACK — DISCHARGED (CSABIN) · airframe 65,918 hrs · 48,428 cycles

DURING THE SERVICE CHECK, MAINTENANCE FOUND THE FORWARD FIRST CLASS OVERHEAD AND FLIGHT DECK EMERGENCY LIGHTS WERE INOPERATIVE. THE BATTERY PACK WAS FOUND TO BE BAD. MAINTENANCE REPLACED THE BATTERY PACK IN THE FORWARD CEILING PANEL IN THE GALLEY. OPERATIONAL CHECK WAS GOOD IAW AMM 33-53. (LP #5597012)

Part: CHARGER — INOPERATIVE (CABIN) · airframe 65,854 hrs · 48,376 cycles

EMERGENCY LIGHTS AFT OF L2 DOOR INOP.FOUND AFT BATTERY CHARGER INOP. REPLACED BATTERY CHARGER PER AMM 33-53 CKS GOOD. (LP4619564)

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 65,716 hrs · 48,247 cycles

EMERGENCY LIGHTS AFT OF ROW 31 INOP. REPLACED BATTERY PACKS BATTERIES FOR B5-28 AND B5-107. CKS GOOD REF MD88 AMM 33-53.

Part: FUEL CELL — CHAFED (CENTER) · airframe 65,430 hrs · 47,996 cycles

WORKING JOB INSP 88 AD CENTER TANK LOWER SKIN NDT-ET AND FOUND HYD LINE CHAFING TANK SKIN. BLENDED CHAFING. DAMAGE WITHIN LIMITS OF MD88 SRM 57-01 FIG 1 (SH3). APPLIED ALODINE TOP COAT PER SRM 57-01 AND SRM 51-10-3. AC OK FOR SVC. (LP5655176)

Part: SKIN — DAMAGED (FUSELAGE) · airframe 65,221 hrs · 47,809 cycles

DAMAGE AFT OF NR 2 ENG PYLON AT UPPER LEFT CORNER OF EMEGENCY EXIT STENCIL. ACCOMPLISHED ERA 576838-14 REV ORIG. STOP DRILLED CRACKS. REMOVED DAMAGE, FABRICATED DOUBLER, AND BEGAN INSTALLATION PER SRM 53-04-3 FIG 2 SHT 3. CLASS 2 REPAIR. COMPLETED INSTALLATION PER SRM 53-04-3 FIG.2 SHEET 3 CLASS 2. WILL REQUIRE INITIAL INSPECTION 20,000 CYCLES AND REPETITIVE INSPECTIONS 15,000 CYCLES. REF SRM 53-04-3 PG 108 TABLE 2. CW ERA 576838-14 REV ORIG SECTION II PERM REPAIR. (LP5730816)

Part: PIN — DISCONNECTED (L1 DOOR) · airframe 64,470 hrs · 47,196 cycles

FOUND L1 DOOR SLIDE PACK PINS DISCONNECTED. REPLACED L1 DOOR SLIDE PACK. (LP5299814)

Part: WARNING SYSTEM — FALSE ACTIVATION (COCKPIT) · airframe 64,113 hrs · 46,895 cycles

T/O CONFIG WARNING ABOVE 80KTS-SLATS-AURAL WARNING WITH SLAT DISAGREE. INITIATED RTO AROUND 90-100KTS. MAX BRAKE TEMP 250. C/W NO GO ODI PREVENTION SECTION ATA 2700 TAKE-OFF WARNING SYSTEM DISCREPANCIES. T/O WARNING CKS GOOD. ALSO VISUALLY INSPECTED SLAT POSITION SENSORS C/D ON EACH WING AND PERFORMED PSEU TEST FOR SAME SENSOR PER AMM 27-80. ALSO PERFORMED SENSOR SLAT ADVISORY ADJ/TEST. NO DISCREPANCIES FOUND AT THIS TIME. OK FOR SERVICE. (LP4933707)

Part: HEATER BLANKET — CORRODED (LT WING) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION ON LT WING HEADER BLANKET CUTOUT ACCESS PANEL NR 1307C AND 1303C. CORROSION LEVEL 2. DUE TO EXCESSIVE CORROSION ON LT WING HEATER BLANKET CUTOUT ACCESS PANEL NR 1307C AND 1303C. HEATER BLANKET WAS REPLACED PER AMM 30-80-02 PAGEBLOCK 401, EA:09-070683-03 AD REV L AND ER/A 356260-14AD REV ORIGINAL.

Part: HEATER BLANKET — CORRODED (RT WING) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION ON RT WING HEATER BLANKET CUTOUT ACCESS PANEL NR 1409C AND 1410C. CORROSION LEVEL 2. DUE TO EXCESSIVE CORROSION ON RT WING HEATER BLANKET CUTOUT ACCESS PANEL NR 1409C AND 1410C. HEATER BLANKET WAS REPLACED PER AMM 30-80-02 PAGEBLOCK 401, EA 09-070683-03 AD REV L, AND ER/A 356260-14AD REV ORIGINAL.

Part: ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION ON ANGLE BTW STA Y=1437-1418 AND BTW LONG 23-24L AT AFT ACCESSORY COMPT. CORROSION LEVEL 2. DUE TO THE EXCESSIVE CORROSION ON ANGLE BTW STA Y=1437-1418 AND BTW LONG 23-24L AT AFT ACCESSORY COMPT AREA WAS REPAIRED WITH ETI-88-18-044 REV 1 AND ER/A 568279-14 REV ORIGINAL.

Part: FRAME — CRACKED (FUSELAGE) · airframe 63,047 hrs · 46,024 cycles

CRACKS (2EA) ON CANTED STA Y=1510 AT 2'HRS AND 4'HRS CLOCK POS AT AFT ACCESSORY COMPT. ON CANTED STA Y=1510 CRACK AT 2'HRS WAS REPAIRED PER ETI-88-18-043 REV.2 AND ER/A 568215-14 REV. ORIGINAL AND CRACK AT 4'HRS CLOCK POS WAS REPAIRED PER ER/A 497316-14MA REV ORIGINAL.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 63,047 hrs · 46,024 cycles

CRACK ON LONG 14R AND FR STA Y=1380 AT AFT ACCESSORY COMPT. LONG 14R AND FR STA Y=1380 AT AFT ACCESSORY COMPT WAS REPAIRED PER ETI-88-18-038 REV 2 AND ER/A 568168-14 REV ORIGINAL.

Part: SKIN — DAMAGED (BS 1338) · airframe 63,047 hrs · 46,024 cycles

THE SKIN WAS FOUND DAMAGED BETWEEN LONGERONS 4 TO 7L, BS 1338. REPAIRED IAW ER/A 496010-14, REV A, SECTION II.

Part: VANE — DELAMINATED (RT WING TE FLAP) · airframe 63,047 hrs · 46,024 cycles

DELAMINATION ON THE CENTER RT VANE ASSY, LOWER SKIN ON THE RT WING TE FLAP. THE VANE ASSY WAS REPAIRED IAW SRM 57-03D, PAR. 11.

Part: SKIN — DENTED (AFT CARGO DOOR) · airframe 63,047 hrs · 46,024 cycles

SEVERALS DENTS FROM BS 1156 TO 1211 ON THE AFT CARGO DOOR SKIN. THE SKIN WAS REPLACED IAW SRM 51-30-2, AND DWG 5910141, REV FD.

Part: SKIN — CRACKED (BS 1150-1155) · airframe 63,047 hrs · 46,024 cycles

FOUND CRACKED INNER FUSELAGE SKIN BS 1150 - 1155, LONGERONS 29 AND 30R. THE SKIN WAS REPAIRED IAW ETI-88-18-026, REV 3, AND ER/A 568097-14, REV ORIGINAL.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION POINTS ON THE FUEL ACCESS PANEL 1460C. THE ACCESS PANEL WAS REPLACED IAW SRM 51-22-2A, PAR 6, CONDITION II.

Part: ACCESS PANEL — CORRODED (NOT REPORTED) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION FOUND ON FUEL ACCESS PANEL 1436C. THE ACCESS PANEL WAS REPLACED IAW SRM 51-22-2A.

Part: ACCESS PANEL — CORRODED (NOT REPORTED) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION FOUND ON THE FUEL ACCESS PANEL 1464C. THE ACCESS PANEL WAS REPLACED IAW SRM 51-22-2A, PAR 6

Part: ACCESS PANEL — CORRODED (NOT REPORTED) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION AT THE COUNTERSINK OF FUEL ACCESS PANEL 1462C. THE ACCESS PANEL WAS REPLACED IAW SRM 51-22-2A.

Part: BEAM — CRACKED (CARGO DOOR) · airframe 63,047 hrs · 46,024 cycles

CRACKED NR 5 BEAM BS 1156 IN THE AFT CARGO DOOR. THE BEAM WAS REPAIRED IAW ETI-88-18-017, REV 1, AND ERA 567908-14, REV ORIGINAL.

Part: ACCESS PANEL — CORRODED (NOT REPORTED) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION ON THE FUEL ACCESS PANEL 1470C. THE ACCESS PANEL WAS REPLACED.

Part: SKIN — DAMAGED (LT WING) · airframe 63,047 hrs · 46,024 cycles

DURING NDT INSPECTION A DISCREPANT AREA WAS FOUND ON THE LOWER SKIN REAR SPAR BETWEEN XRS 163 TO 168 WING. REPAIRED IAW ER/A 567436-14AD, REV ORIGINAL.

Part: SPAR — DAMAGED (RT WING) · airframe 63,047 hrs · 46,024 cycles

DURING NDT INSPECTION, A DISCREPANT AREA WAS FOUND ON THE LOWER SKIN REAR SPAR BETWEEN XRS 163 TO 168, RT WING. REPAIRED IAW ER/A 567436-14AD, REV ORIGINAL.

Part: ACCESS PANEL — CORRODED (NOT REPORTED) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION ON THE FUEL ACCESS PANEL 1355C. THE ACCESS PANEL WAS REPLACED.

Part: LONGERON — CRACKED (BS 1380) · airframe 63,047 hrs · 46,024 cycles

CRACKED LONGERON 13R, BS 1380. THE LONGERON WAS REPLACED IAW SRM 51-30-2, AND 51-30-5.

Part: SKIN — WORN (CARGO DOOR) · airframe 63,047 hrs · 46,024 cycles

WEAR ON THE CARGO DOOR SKIN BOTH CORNERS BS 1160 AND 1205 LOWER AREA. DOUBLERS OF BOTH LOWER CORNERS OF THE AFT CARGO DOOR WERE REPLACED IAW SRM 51-30-2, AND DWG 5910141, REV FE.

Part: PAN — CRACKED (CARGO DOOR) · airframe 63,047 hrs · 46,024 cycles

FOUND A CRACKED PAN BS 1211 BETWEEN THE NR 1 AND 2 BEAMS, AFT CARGO DOOR. THE PAN WAS REPAIRED IAW ER/A 567929-14, REV ORIGINAL, AND ETI-88-18-030, REV 2.

Part: BEAM — CRACKED (BS 693) · airframe 63,047 hrs · 46,024 cycles

CRACKED NR 5 BEAM BS 693 AT THE CENTER CARGO DOOR. THE BEAM WAS REPAIRED IAW ER/A 567906-14, REV ORIGINAL, AND ETI-88-18-016, REV 1.

Part: FITTING — CRACKED (BS 1156) · airframe 63,047 hrs · 46,024 cycles

CRACKED FITTING BS 1156 ON THE NR 5 BEAM AT THE AFT CARGO DOOR. THE FITTING WAS REPLACED PER DWG 3934011, REV ORIGINAL, SRM 51-30-4, AND 51-30-5. (LP0518355)

Part: ANGLE — CRACKED (CARGO DOOR) · airframe 63,047 hrs · 46,024 cycles

CRACKS AT HOLES IN THE FWD EDGE OF THE ANGLE TEE BEAM NR 5 AT THE AFT CARGO DOOR. THE ANGLE WAS REPLACED IAW SRM 51-30-2, AND DWG 9957663, REV W.

Part: FITTING — CRACKED (BS 1175) · airframe 63,047 hrs · 46,024 cycles

CRACKED FITTING BS 1175, BETWEEN BEAM 1 AND THE BOTTOM PAN OF THE AFT CARGO DOOR. THE FITTING WAS REPLACED IAW SRM 51-30-1, 51-30-2, 51-30-5, AND DWG 3926046, REV B.

Part: DOOR FRAME — CRACKED (BS 997) · airframe 63,047 hrs · 46,024 cycles

A CRACK WAS FOUND ON THE AFT MLG DOOR FRAME CHANNEL, BS 997, RBL 60 - LBL 60. THE AFT MLG DOOR FRAME CHANNEL WAS REPLACED IAW SRM 51-30-2, AND 51-30-5.

Part: FRAME — CRACKED (BS 1474) · airframe 63,047 hrs · 46,024 cycles

A CRACK WAS FOUND ON THE FRAME BS 1474, 3 HOURS POSITION IN THE AFT ACCESORIES COMPARTMENT. REPAIRED IAW ER/A 567676-14, REV ORIGINAL, & ETI-88-18-024 R1.

Part: STOP FITTING — CRACKED (CARGO DOOR) · airframe 63,047 hrs · 46,024 cycles

CRACKED FWD STOP FITTING ON THE MID CARGO DOOR. THE STOP FITTING WAS REPLACED IAW SRM 51-30-1, 51-30-2, AND 51-30-5.

Part: FLOOR SUPPORT — CRACKED (BS 1287-1307) · airframe 63,047 hrs · 46,024 cycles

CRACKED FLOOR SUPPORT BL 0, BS 1287 - 1307. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-30-2, AND 51-30-5.

Part: TEE FITTING — CRACKED (CARGO DOOR) · airframe 63,047 hrs · 46,024 cycles

CRACK FOUND ON THE INTERNAL TEE FITTING OF BEAM NR 5, AFT SIDE OF THE MID CARGO DOOR. THE TEE FITTING WAS REPLACED IAW SRM 51-30-2, 51-30-5, AND DWG 3934011, REV ORIGINAL.

Part: CUSP WEB — CORRODED (BS 965-984) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION FOUND ON THE LEFT CABIN FLOOR CUSP WEB, UPPER & LOWER SURFACES, LBL 44 TO 60, BS 965 - 984. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-13.

Part: CUSP WEB — CORRODED (BS 1086-1091) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION FOUND ON THE LT CUSP WEB, BS 1086 - 1091, LBL 54 TO 60 FOUND OUT OF LIMITS. THE CUSP WEB WAS REPAIRED IAW SRM 53-05.

Part: CUSP WEB — CORRODED (BS 522-598) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION ON THE LEFT CABIN FLOOR CUSP WEB UPPER & LOWER SURFACES FROM LBL 44 TO 60, BS 522 - 598. THE CUSP WEB WAS REPLACED IAW SRM 53-05, FIG131A, 51-30-1, AND 51-30-2.

Part: FLOOR PANEL — DAMAGED (NOT REPORTED) · airframe 63,047 hrs · 46,024 cycles

ELONGATED HOLE ON FLOOR PANEL 927A. A DOUBLER REPAIR WAS INSTALLED IAW SRM 53-05, FIG 131B.

Part: CUSP WEB — CORRODED (BS 1022-1041) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION ON THE LT CUSP WEB BETWEEN BS 1022 - 1041, LBL 54 TO 60 FOUND OUT OF LIMITS. THE CUSP WEB SECTION WAS REPAIRED IAW SRM 53-05, FIG 131A-14, AND SRM 51-30-2.

Part: TAB — CRACKED (LT ELEVATOR) · airframe 63,047 hrs · 46,024 cycles

DURING INSPECTION A CRACK AND LOST OF MATERIAL ON THE LT ELEVATOR GEARED TAB LE SKIN AROUND HINGE FITTING. THE TAB WAS REPLACED IAW AMM 27-30-04.

Part: LONGERON — CRACKED (BS 1434) · airframe 63,047 hrs · 46,024 cycles

LONGERON 11R CRACKED AT BS 1434. THE LONGERON WAS REPAIRED IAW SRM 53-02, FIG 18, SHEET 1.

Part: CUSP WEB — CORRODED (BS 845-857) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION FOUND OUT OF LIMITS ON THE CUSP WEB BETWEEN RBL 44 - 60, BS 845 - 857. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-2.

Part: CUSP WEB — CORRODED (BS 892-903) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION FOUND OUT OF LIMITS ON THE CUSP WEB, BETWEEN RBL 44 & 60, BS 892 TO 903. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-2.

Part: CUSP WEB — CORRODED (BS 1046-1049) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

AWR : IN REF NRC 00535: OUT OF LIMITS : CORROSION OUT OF LIMITS ON THE RT CABIN CUSP WEB, RBL 54 TO 60, BS 1046 - 1049. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-14, AND 51-30-2.

Part: TAB — DAMAGED (LT ELEVATOR) · airframe 63,047 hrs · 46,024 cycles

PRESENCE OF WATER WAS FOUND ON THE LT ELEVATOR ANTI-FLOAT TAB HONEYCOMB STRUCTURE AREA. THE LT ELEVATOR ANTI-FLOAT TAB WAS REPLACED IAW AMM 27-30-14.

Part: CUSP WEB — CORRODED (BS 1011-1013) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CUSP WEB BETWEEN RBL 44 TO 60, BS 1011 TO 1013 CORRODED OUT OF LIMITS. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-13, AND 51-30-2.

Part: CUSP WEB — CORRODED (BS 1240-1245) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION ON LEFT CABIN FLOOR CUSP WEB UPPER & LOWER SURFACES FROM LBL 54 TO 60, BETWEEN BS 1240 TO 1245. FOUND OUT OF LIMITS. AREA WAS REPAIRED IAW SRM 53-05, REPAIR CONFIGURATION 7011, FIG. 131A-6.

Part: CUSP WEB — CORRODED (BS 786-788) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION OUT OF LIMITS ON THE RT CUSP WEB, BETWEEN RBL 44 TO 60, BS 786 - 788. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-9, SHEET 1, AND SRM 51-30-2.

Part: CUSP WEB — CORRODED (BS 741-747) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION OUT OF LIMITS ON THE RT CUSP WEB BETWEEN RBL 44 TO 60, BS 741 - 747. REPAIRED IAW SRM 53-05, FIG 131A-14.

Part: CUSP WEB — CORRODED (BS 1237-1239) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION FOUND ON THE RT CABIN FLOOR CUSP WEB, RBL 54 TO 60, BS 1237 - 1239. FOUND TO BE OUT OF LIMITS. THE SECTION OF THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-13, AND 51-30-5,51-30-2.

Part: CUSP WEB — CORRODED (BS 1098-1117) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION FOUND ON THE RT CABIN FLOOR CUSP WEB RBL 54 TO 60, BS 1098 - 1117. FOUND TO BE OUT OF LIMITS. THE SECTION OF CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-6, 51-30-5, AND 51-30-2.

Part: CUSP WEB — CORRODED (BS 750-757) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

LEFT CUSP WEB BETWEEN BS 750 TO 757 AND LBL 44 -60, FOUND TO BE OUT OF LIMITS. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-9.

Part: INTERCOSTAL — CRACKED (PAX DOOR) · airframe 63,047 hrs · 46,024 cycles

CRACKED INTERCOSTAL BETWEEN RIBS 4 & 5, BS 185 AT FWD ENTRY DOOR. THE INTERCOSTAL WAS REPLACED IAW SRM 51-30-2, 51-30-5, AND DWG 9955763, REV K.

Part: CUSP WEB — CORRODED (BS 886-905) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION ON THE LEFT CABIN FLOOR CUSP WEB UPPER AND LOWER SURFACES, LBL 44 TO 60 BETWEEN BS 886 TO 905. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-2.

Part: SKIN — WORN (CARGO DOOR) · airframe 63,047 hrs · 46,024 cycles

INITIAL INSPECTION, WORN FWD AND AFT LOWER EXTERNAL DOUBERS ON OUTER SKIN AT FWD CARGO DOOR COMPARMENT. DOUBLERS WERE REPLACED PER ERA 486624-14MA REV ORIGINAL.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

OUT OF LIMITS CORROSION ON RT CABIN FLOOR CUSP WEB X= - 54 TO X=- 60 AND STA Y= 1162-1163. CUSP WEB X= - 54 TO X=- 60 AND STA Y= 1162-1163 WAS REPAIRED PER SRM 53-05 FIG 131A-5.

Part: CUSP WEB — DAMAGED (FUSELAGE) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

AREA OUT OF LIMITS ON LT CUSP WEB BETWEEN STA Y=826-845 AND X=44/X=60. AREA OUT OF LIMITS ON LT CUSP WEB BETWEEN STA Y=826-845 AND X=44/X=60. IN REF NRC 00556. WAS REPAIRED PER SRM 53-05 FIG 131A-13.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 63,047 hrs · 46,024 cycles

CRACKED FLOOR PANEL NBR: 200C. A NEW FLOOR PANEL WAS FABRICATED, AND REPLACED IAW AMM 53-20-01-201.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

CORROSION ON LEFT CABIN FLOOR CUSP WEB UPPER/LOWER SURFACE FROM X=44 TO X=60 BTW STA Y=332 TO Y=351. CORROSION ON LEFT CABIN FLOOR CUSP WEB UPPER/LOWER SURFACE FROM X=44 TO X=60 BTW STA Y=332 TO Y=351 (IN REFERENCE TO NRC 00549) WAS REPAIRED PER SRM 53-05 PAR 144, FIG 131A.

Part: BEAM — CRACKED (FUSELAGE) · airframe 63,047 hrs · 46,024 cycles

INITIAL INSPECTION. CRACK BEAM NR 5 BTW STA 370 TO STA 389 AT FWD CARGO DOOR COMPARTMENT. BEAM NR 5 WAS REPLACED PER SRM 51-30-2, 51-30-5 AND DWG 9957663 REV W.

Part: TAB — CRACKED (RT ELEVATOR) · airframe 63,047 hrs · 46,024 cycles

CRACKED UPPER LEADING EDGE SKIN AT RT GEARED TAB NEAR TO FIRST HINGE. REPLACED WITH SERVICEABLE RT ELEVATOR GEARED TAB.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 63,047 hrs · 46,024 cycles

CRACKS ON FLOOR PANELS NBRS 160D, 160F, 200B, 148B, 120E, 643C , AND 886B AT PAX CAB. FLOOR PANELS NBRS 160D, 160F, 200B, 148B, 120E, 643C , AND 886B WERE FABRICATE REPLACED AND IDENTIFIED PER MD88 A.M.M 53-20-01-201 AND WERE INSTALLED PER ROUTINE TASK CARD 001-0071:2500-0539. (LP0506411)

Part: CUSP WEB — CORRODED (MAIN CABIN) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

AWR : IN REF NRC 00535: OUT OF LIMITS : CORROSION ON RH CABIN FLOOR CUSP WEB X= - 54 TO X=- 60 AND STA Y= 1082-1094. CORROSION ON RH CABIN FLOOR CUSP WEB X= - 54 TO X=- 60 AND STA Y= 1082-1094 ( CPAX ) WAS REPAIRED PER DC9/MD80 SRM 53-05 FIG. 131 A-14. (LP0506182)

Part: ACCESS PANEL — WORN (WING) · airframe 63,047 hrs · 46,024 cycles

WEAR ON FUEL ACCESS PLATE NR 1367C. DUE TO EXCESSIVE DAMAGE FUEL ACCESS PLATE NR 1367C WAS REPLACED PER SRM 51-22-2A PAR 6.

Part: DIAPHRAGM — PUNCTURED (FUSELAGE) · airframe 63,047 hrs · 46,024 cycles

INITIAL INSPECTION: PUNCTURES ON DIAPHRAGM STA Y=200 X=-12 AT PAX CABIN. PUNCTURES ON DIAPHRAGM STA Y=200 X=-12 AT PAX CABIN (W1) WERE REPAIRED PER SRM 51-70-04.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

AWR AREA OUT OF LIMITS AT CUSP WEB BETWEEN X=-44 TO X=-54 ON STA Y= 559. IN REF NRC 00525. LEVEL CORROSION 2)CUPS WEB WAS REPAIRED PER SRM 53-05 FIG 131A-17 AND SRM 51-30-2.

Part: SKIN — CRACKED (RT PYLON) · airframe 63,047 hrs · 46,024 cycles

CRACK ON UPPER SKIN APPROX STA Y=1421 AT RT PYLON TRAILING EDGE. TRAILING EDGE WAS REPAIRED PER DC9-MD80 SRM 53-01 FIG 2 SHEET 3 EXAMPLE C.

Part: BEAM — CRACKED (ENTRY DOOR) · airframe 63,047 hrs · 46,024 cycles

CRACKED RIB 1 AFTER STOP DRILL ON AFTER EDGE AT FWD ENTRY DOOR. BEAM WAS REPAIRED PER SRM 52-05 PAR 76 FIG 97.

Part: ACCESS PANEL — CORRODED (WING) · airframe 63,047 hrs · 46,024 cycles

CORROSION AT FUEL ACCESS PLATES 1409C AND 1303C. 1409C AND 1303C BLEND OUT REPAIR IS NOT PERMITTED AND WERE REPLACED PER DC-9/MD-80 SRM 51-22-2A CONDITION III. (LP0503717)

Part: PAN — CRACKED (CARGO DOOR) · airframe 63,047 hrs · 46,024 cycles

CRACK ON FWD OUTER PAN BELOW STOP FITTING NR 4 AT FWD CARGO DOOR. REPAIRED IAW SRM-52-05, FIG 50.

Part: PAN — CRACKED (CARGO DOOR) · airframe 63,047 hrs · 46,024 cycles

CRACKED FWD OUTER PAN BELOW STOP FITTING NR 3 ON THE FWD CARGO DOOR. REPAIRED IAW SRM 52-05, FIG 50.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

OUT OF LIMITS CORROSION ON FLOOR SUPPORT STA Y=160 TO 195 X=54 LT SIDE PAX CABIN. LEVEL CORROSION 2 FLOOR SUPPORT X=54 BTW STA Y=160 TO 195 WAS REPLACED PER SRM 51-30-2 AND 51-10-04.

Part: DIAPHRAGM — PUNCTURED (FUSELAGE) · airframe 63,047 hrs · 46,024 cycles

PUNCTURES ON DIAPHRAGM BTW STA Y=200 TO Y= 160 AND X= -54 AT CABIN PAX. DIAPHRAGM BTW STA Y=200 TO Y=160 AND X= - 54 WAS REPAIRED PER SRM 53-01 FIG 4 SHEET 4.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 63,047 hrs · 46,024 cycles

OUT OF LIMITS CORROSION ON RT CABIN FLOOR SUPPORT BTW STA Y= 160-200 X= -8 PAX CABIN. LEVEL CORROSION 2. FLOOR SUPPORT STA Y=200 TO Y=160, X=-8 WAS REPLACED PER SRM 51-30-1 AND 51-30-5.

Part: PAN — CRACKED (FUSELAGE) · airframe 63,047 hrs · 46,024 cycles

INITIAL INSPECTION: CRACK LOWER AFT CORNER ON WINDOW RING PAN RT STA Y= 1250. LOWER AFT CORNER ON WINDOW RING PAN RT STA Y= 1250 WAS REPAIRED PER SRM 53-05 FIG 122 AND ER/A 493648-14 MA REV A.

Part: PAN — CRACKED (FUSELAGE) · airframe 63,047 hrs · 46,024 cycles

INITIAL INSPECTION: CRACK LOWER AFT CORNER ON WINDOW RING PAN RT STA Y= 1193. LOWER AFT CORNER ON WINDOW RING PAN RT STA Y= 1193 WAS REPAIRED PER SRM 53-05 FIG 122 AND ER/A 493648-14 MA REV A.

Part: PAN — CRACKED (FUSELAGE) · airframe 63,047 hrs · 46,024 cycles

INITIAL INSPECTION: CRACK UPPER AFT CORNER ON WINDOW RING PAN RT STA Y= 1079. UPPER AFT CORNER ON WINDOW RING PAN RT STA Y= 1079 WAS REPAIRED PER SRM 53-05 FIG 122 AND ER/A 493648-14 MA REV A.

Part: PAN — CRACKED (FUSELAGE) · airframe 63,047 hrs · 46,024 cycles

INITIAL INSPECTION: CRACK LOWER AFT CORNER ON WINDOW RING PAN RT STA Y=788. LOWER AFT CORNER ON WINDOW RING PAN RT STA Y= 788 WAS REPAIRED PER SRM 53-05 FIG 122 AND ER/A 493648-14 MA REV A.

Part: PAN — CRACKED (FUSELAGE) · airframe 63,047 hrs · 46,024 cycles

INITIAL INSPECTION: CRACK LOWER FWD CORNER ON WINDOW RING PAN LT STA Y= 1079. LOWER FWD CORNER ON WINDOW RING PAN LT STA Y= 1079 WAS REPAIRED PER SRM 53-05 FIG 122 AND ER/A 493648-14 MA REV A.

Part: PAN — CRACKED (FUSELAGE) · airframe 63,047 hrs · 46,024 cycles

INITIAL INSPECTION: CRACK UPPER AFT CORNER ON WINDOW RING PAN RT STA Y= 1041. UPPER AFT CORNER ON WINDOW RING PAN RT STA Y= 1041 WAS REPAIRED PER SRM 53-05 FIG 122 AND ER/A 493648-14 MA REV A.

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHT) · airframe 62,357 hrs · 45,512 cycles

CABIN EMERGENCY LIGHT AT SEAT 27D INOPERATIVE. REPLACED THE SEAT WIRE HARNESS AND LIGHT ASSY IAW AMM 33-53. OPS NORMAL.

Part: WIRE — PINCHED (EMERGENCY LIGHTS) · airframe 61,645 hrs · 44,926 cycles

DURING A SERVICE CHECK, FOUND THE L1, R1, SEAT ROWS 1 THRU 12, AND FWD GALLEY EMERGENCY LIGHTS INOPERATIVE. TROUBLESHOT AND FOUND A PINCHED WIRE AT ROW 12 CAUSING BATTERY PACK TO BLOW F1 FUSE. REPOSITIONED AND SECURED THE WIRE. R & R THE BATTERY PACK AND TRAY IN FWD AND AFT CABIN. OPS CHECKED NORMAL IAW WDM 33-51-14. ACFT OK FOR SERVICC.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 61,083 hrs · 44,476 cycles

EMERGENCY LIGHTS BETWEEN ROWS 25 AND 32 WONT COME ON. TROUBLESHOT IAW WDM 33-51-12 AND WDM 33-51-11. FOUND B5-106 AND B5-104 BAD. R & R IAW AMM 33-52.

Part: CONTROL CABLE — OUT OF ADJUST (AILERON) · airframe 60,968 hrs · 44,384 cycles

AILERONS AND ELEVATOR STIFF-DIFFICULT TO MOVE IN FLIGHT. FOUND AILERON CABLES 7&8 TENSION OUT OF LIMITS (TOO LOW) ADJUSTED CABLES IN REF TO AILERON CABLES 7&8 TENSION ADJUSTMENTS & SAFETIES PER AMM 27-10. LUBED LATERAL CONTROL MIXER IN REF TO AIM 12-21. FOUND ELEVATOR BRIDLE CABLE CLAMP ASSY COTTER PIN SNAGGED ON HORIZONTAL STAB TRIM CABLE SEPARATED, RESECURED SAME. ELEVATOR & AILERONS NOW OPERATE SMOOTHLY WITHIN FORCE LIMITS PER AIM 27-10 AND 27-30.

Part: CAM — WORN (TAILCONE RELEASE) · airframe 60,754 hrs · 44,211 cycles

TAILCONE CAM RELEASE MECHANISM HAS END PLAY. REMOVED AND REPLACED TAHE CAM IAW AMM 53-53-02.

Part: TAB — DELAMINATED (LT ELEVATOR) · airframe 60,754 hrs · 44,211 cycles

LEFT ELEVATOR ANTI-FLOAT TAB HAS TWO SPOTS OF DELAMINATION ON THE UPPER SURFACE. REMOVED AND REPLACED THE TAB IAW AMDS 2730-4382.

Part: SKIN — CRACKED (VERTICAL STAB) · airframe 60,754 hrs · 44,211 cycles

VERTICAL STAB AIR SCOOP LEFT LIP HAS A TWO INCH LONG CRACK, REPAIRED IAW ERA 382101-14MA, REV F.

Part: FRAME — CRACKED (BS 1510) · airframe 60,754 hrs · 44,211 cycles

BS 1510 TAILCONE FRAME IS CRACKED IN 3 PLACES. REMOVED AND REPLACED THE FRAME IAW SRM 51-01, PG 1.

Part: FRAME — CRACKED (BS 1510) · airframe 60,754 hrs · 44,211 cycles

BS 1510 TAILCONE FRAME IS CRACKED IN 2 PLACES. REMOVED AND REPLACED THE FRAME IAW SRM 51-01, PG 1.

Part: SKIN — CRACKED (FUSELAGE) · airframe 60,754 hrs · 44,211 cycles

A/C SKIN HAS 7/8" LONG CRACK AT BS 1436, BETWEEN L 4&5 LT. ENDS OF CRACK HAVE BEEN MARKED WITH HFEC. COMPLIED WITH PRI 554857-14 REV 0. REPAIR REF ERA 554857-14 REV ORIG. FINAL ERA RECEIVED.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 60,688 hrs · 44,166 cycles

AFT CABIN EMERGENCY LIGHT IS INOPERATIVE. R & R THE BATTERY PACK AMM 33-53. ALL CHECKS GOOD.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 60,451 hrs · 44,004 cycles

LEFT WING AFT OVERWING HATCH EMERGENCY LIGHT INOPERATIVE. REPLACED THE LAMP IAW AMM 33-51.

Part: TURBINE — DAMAGED (RT ENGINE) · airframe 60,044 hrs · 43,707 cycles

RETURNED TO OKC DUE TO A RIGHT ENGINE FAILURE. THE CREW REPORTED THAT AT FL200 THE ENGINE FAILED WITH AN ASSOCIATED EGT RISE. THE QRH WAS FOLLOWED AND THE ENGINE WAS SHUT DOWN. MAINTENANCE FOUND TURBINE DAMAGE AND METAL IN THE TAILPIPE. THE ENGINE WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 59,958 hrs · 43,643 cycles

FWD GALLEY EMERGENCY LIGHTS INOPERATIVE. REMOVED AND REPLACED THE BATTERY PACK IAW AMM 33-53. OPS CHECKED GOOD.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 59,782 hrs · 43,528 cycles

EMERGENCY LIGHTS, 2 AT TOP OF COCKPIT OVERHEAD ADJACENT TO LOOP LIGHTS ARE INOPERATIVE. R & R BATTERY PACK IAW AMM 33-53. CHECKS GOOD AT THIS TIME.

Part: SKIN — DAMAGED (L1 DOOR) · airframe 57,207 hrs · 41,653 cycles

CRACK FOUND ON EXTERNAL SKIN OF FWD L1 DOOR ON AFT LOWER CORNER. AREA REPAIRED IAW SRM 52-05D, FIG 55.

Part: SKIN — DAMAGED (BS 314-411) · airframe 57,207 hrs · 41,653 cycles

ACFT HAS A LIGHTNING STRIKE ON EXTERNAL FUSELAGE SKIN LONGERON 5L BS 314 - 411. THE SKIN WAS REPAIRED IAW SRM 53-04-2, PAR 3, FIG 2, SHEET 17.

Part: SLIDE — OUT OF POSITION (L1 DOOR) · airframe 57,207 hrs · 41,653 cycles

MAINTENANCE FOUND L1 DOOR SLIDE OUT OF PLACE. THE SLIDE PACK WAS REPLACED.

Part: SKIN — DAMAGED (BS 617-636) · airframe 57,207 hrs · 41,653 cycles

A LIGHTNING STRIKE ON LOWER FWD CORNER OF RT WINDOW BELT BS 617-636. WINDOW BELT WAS REPAIRED IAW ER/A 537820-14 REV ORIGINAL.

Part: ANGLE — CRACKED (VERTICAL STAB) · airframe 57,207 hrs · 41,653 cycles

CRACKED RT INNER ANGLE ON VERTICAL STABILIZER L/E BETWEEN BS 1401 - 1438. THE ANGLE WAS REPLACED IAW SRM 51-30-2, 51-30-5, AND DWG 5912188-RE BD.

Part: SKIN — DAMAGED (BS 1132-1136) · airframe 57,207 hrs · 41,653 cycles

LIGHTNING STRIKE ON EXTERNAL FUSELAGE SKIN BETWEEN LONGERON 1 - 2L, BS 1132-1136. THE SKIN WAS REPAIRED IAW SRM AND 53-04-2. PAR 3C (2) A.1 AND SRM 53-04-1, PAR.6C, COND.1.

Part: DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 57,207 hrs · 41,653 cycles

ACFT HAS CORROSION ON DOUBLER REPAIR AT LOWER DOOR JAMB C1. REPAIR DOUBLER AT LOWER DOOR JAMB C1 WAS REPLACED IAW SRM 51-30-2 AND DWG 5910142, REV DJ.

Part: DOOR FRAME — CORRODED (BS 636-693) · corrosion level 2 · airframe 57,207 hrs · 41,653 cycles

ACFT HAS CORROSION ON LOWER CARGO DOOR FRAME FROM BS 636 - 693 C2. PREVIOUS DOUBLER SPACER WAS REPLACED IAW SRM 53-05, FIG 123.

Part: SKIN — DAMAGED (BS 120) · airframe 57,207 hrs · 41,653 cycles

HAS A NICK ON FUSELAGE SKIN, BS 120 BETWEEN LONGERONS 28LT TO 28RT. AREA OUT OF LIMITS WAS REPAIRED IAW SRM 53-04-2, FIG 2, SHEET 13.

Part: CLAMP — LOOSE (WATER SEPARATOR) · airframe 57,058 hrs · 41,534 cycles

CREW SMELLED AN ELECTRICAL ODOR DURING CLIMBOUT. DISSAPATED AT CRUISE. ODOR CAME BACK DURING DESCENT. FOLLOWED MM 05-50-01 & NO GO ODI PREVIOUS SITE & AMDS CARD 2120-2367. NO SOURCE OF ODOR IDENTIFIED. PERFORMED FULL DUCT BURNOUT IAW MM 21-20-02. NO DEFECTS NOTED AT THIS TIME. TIGHTENED LOOSE CLAMPS ON WATER SEPARATOR DUCT & RT CROSSOVER DUCT. CONTACTED MCC, BLAKE. COALESCER BAGS CHANGED ON "A"-CK , VERY DIRTY. SYS OK FOR SERVICE.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 56,690 hrs · 41,289 cycles

OVERHEAD EMERGENCY EXIT ROW LIGHTS INOPERATIVE, ROWS 28-32. RII: N ENTR 906363 W R & R EMERGENCY LIGHT BATTERIES IAW AMM 33-53-00. OPS CHECK NORMAL. OK FOR SERVICE.

Part: COMPRESSOR — STALLED (NR 1 ENGINE) · airframe 56,552 hrs · 41,191 cycles

THE NR 1 ENGINE EXPERIENCED A COMPRESSOR STALL AFTER TAKEOFF. THE NR 1 ENGINE WAS SHUTDOWN AND AN AIR TURNBACK WAS ACCOMPLISHED. MAINTENANCE REPLACED THE NR 1 ENGINE AND THE ACFT HAS RETURNED TO SERVICE.

Part: FRAME — CRACKED (BS 1485) · airframe 54,384 hrs · 39,624 cycles

CANTED FRAME BS 1485 HAS A 3 INCH LONG CRACK IN WEB. COMPLIED WITH ER/A 527673-14, REV O.

Part: RELEASE CABLE — WORN (TAILCONE) · airframe 54,372 hrs · 39,614 cycles

MAINTENANCE DISCOVERED THAT THE TAILCONE EMERGENCY RELEASE CABLE WAS TORN AT CAM LOOP. THE CABLE WAS REPLACED AND THE SYSTEM WAS RIGGED TO SPECIFICATIONS.

Part: RELEASE MECH — WORN (TAILCONE) · airframe 54,372 hrs · 39,614 cycles

MAINTENANCE DISCOVERED THAT THE TAILCONE RELEASE MECHANISM CAM BASE WAS WORN OUT OF ALLOWABLE LIMITS. THE CAM BASE WAS REPLACED AND THE SYSTEM WAS RIGGED TO SPECIFICATIONS. THE RII WAS SATISFACTORY.

Part: LONGERON — CORRODED (BS 206) · corrosion level 3 · airframe 54,357 hrs · 39,602 cycles

LONGERON 21R CORRODED FULL THRU AT BS 206 . REPAIRED IAW SRM 53-02-FIG 18.

Part: FASTENER — LOOSE (TAILCONE) · airframe 54,372 hrs · 39,614 cycles

MAINTENANCE DISCOVERED THAT THE FASTENERS FOR THE SPADE RECEPTACLE FOR THE TAILCONE WERE WORN OUT OF ALLOWABLE LIMITS. THE RIVETS WERE REPLACED AND THE SYSTEM WAS RIGGED TO SPECIFICATIONS. THE FUNCTIONAL CHECK WAS COMPLETED SATISFACTORILY.

Part: SKIN — CORRODED (BS 206) · corrosion level 2 · airframe 54,357 hrs · 39,602 cycles

EXTERIOR SKIN PILLOWED WITH STRESSED BS 206, L21R. SKIN REPAIRED IAW SRM 53-04-3, FIG 2.

Part: DOOR FRAME — CRACKED (LT OVERWING) · airframe 54,363 hrs · 39,608 cycles

CRACKED OVERWING FRAME, BS 886 LT. FRAME REPLACED IAW EM 5310-01414, SEC.0301.

Part: BUSHING — WORN (TAILCONE) · airframe 54,372 hrs · 39,614 cycles

MAINTENANCE DISCOVERED THAT THE TEE PIN AND THE TEE PIN BUSHING WERE WORN BEYOND ALLOWABLE LIMITS AND REPLACED.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 53,972 hrs · 39,313 cycles

DURING LINE CHECK, MAINTENANCE FOUND THE CABIN CEILING EMERGENCY LIGHTS IN 1ST CLASS WERE INOPERATIVE. MAINTENANCE R & R THE BATTERIES INSIDE THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPERATIONAL STATE.

Part: WATER HEATER — FAILED (LAVATORY) · airframe 53,809 hrs · 39,187 cycles

FLIGHT WAS DIVERTED DUE TO FUMES COMING FROM FIRST CLASS LAVATORY. MAINTENANCE FOUND THE FIRST CLASS LAVATORY WATER HEATER INTERNAL WIRING CHARRED AND CONNECTOR P1-385 DISCOLORED. REPLACED BOTH THE CONNECTOR AND THE WATER HEATER.

Part: SKIN — DAMAGED (BS 484-541) · airframe 52,669 hrs · 38,394 cycles

DURING LINE CHECK, CREASES WERE FOUND ON THE LEFT SIDE OF THE FUSELAGE SKIN FROM BS 484-541. REPAIRED IAW SRM 53-04 FIG 12C.

Part: SKIN — DAMAGED (BS 484-541) · airframe 52,669 hrs · 38,394 cycles

DURING LINE CHECK, TWO CREASES WERE NOTED ON THE LEFT SIDE OF THE FUSELAGE SKIN. REPAIRED.

Part: CONNECTOR — DAMAGED (EMERGENCY LIGHTS) · airframe 52,478 hrs · 38,259 cycles

SEAT 10D EMERGENCY LIGHT INOPERATIVE. REPAIRED DAMAGED CONNECTOR IAW SWPM 20 AND CHECKED OK.

Part: SKIN — DAMAGED (BS 110-229) · airframe 51,687 hrs · 37,695 cycles

DURING INSPECTION, FOUND LIGHTNING STRIKES ON FUSELAGE BS 110-229 BETWEEN LONGERONS 28-30L. FOUND THREE LIGHTNING STRIKES AT BS 160, 180 AND 200 AT LONGERON 29L OUT OF LIMITS. REPAIRED IAW SRM 53-04-02, PG 11.

Part: LANYARD — FRAYED (GIRT BAR) · airframe 50,782 hrs · 37,013 cycles

DURING SERVICE CHECK, MX FOUND FORWARD SERVICE DOOR GIRT BAR LANYARD FRAYED. R & R LANYARD CABLE IAW AMM.

Part: RECEPTACLE — WORN (TAILCONE) · airframe 50,827 hrs · 37,042 cycles

DURING SERVICE CHECK, TAILCONE LT UPPER RECEPTACLE WORN. R & R LT UPPER RECEPTACLE IAW AMM.

Part: CABLE — FRAYED (TAILCONE) · airframe 50,827 hrs · 37,042 cycles

DURING SERVICE CHECK, KEVLAR CABLE INT TAILCONE FRAYED AT CAM ATTACH POINT. R & R KEVLAR CABLE IAW AMM. KEVLAR CABLE TO TAILCONE RELEASE MECHANISM CAM WILL BE ACCOMPLISHED ON AMDS 5350-01077-0101.

Part: RECEPTACLE — WORN (TAILCONE) · airframe 50,827 hrs · 37,042 cycles

TAILCONE LT UPPER RECEPTICLE WORN LT UPPER SPADE. R & R LEFT UPPER RECEPTICLE IAW AMM.

Part: LANYARD — BROKEN (L1 DOOR SLIDE) · airframe 50,330 hrs · 36,683 cycles

DURING SERVICE CHECK, MX FOUND L1 DOOR SLIDE LANYARD BROKEN. R & R LANYARD. OPS CHECKED OK.

Part: BULB — INOPERATIVE (EMERGENCY LIGHT) · airframe 49,971 hrs · 36,428 cycles

DURING SERVICE CHECK, MAINTENANCE FOUND L2 DOOR EMERGENCY EXIT SIGN LOWER TWO BULBS INOPERATIVE. REPLACED BULBS. OPS CHECKED GOOD.

Part: DOOR FRAME — DAMAGED (FUSELAGE) · airframe 48,539 hrs · 35,435 cycles

DURING HMV ELONGATED HOLES WERE FOUND ON LOWER VENTRAL DOOR JAMB STA Y=1350 X=18 AND Z=10. DOOR JAMB WAS REPAIRED IAW ERA 499474-14 REV ORIG.

Part: DOOR FRAME — CORRODED (FUSELAGE) · airframe 48,539 hrs · 35,435 cycles

DURING HMV CORROSION WAS FOUND ON LOWER VENTRAL DOOR JAMB STA Y=1350 X=18 TO X=-18. DOOR JAMB WAS REPAIRED IAW ERA 499474-14 REV ORIG.

Part: CONDUIT — WORN (TAILCONE) · airframe 48,539 hrs · 35,435 cycles

THE CONDUIT FOR THE TAIL CONE RELEASE MECHANISM CABLE WAS FOUND WORN AT STA 1510 & 5:00 POSITION. THIS WEAR WAS BEYOND ALLOWABLE LIMITS SO THE CONDUIT WAS REPLACED. FOUND DURING HMV.

Part: FASTENER — CORRODED (TAILCONE) · airframe 48,539 hrs · 35,435 cycles

EXCESSIVE CORROSION WAS FOUND ON THE TAIL CONE RELEASE MECHANISM PULLEY PINS, BOLTS, AND NUTS AT STA 1510 CANT. THIS CORROSION WAS BEYOND ALLOWABLE LIMITS SO THE AFFECTED HARDWARE WAS REPLACED.

Part: CLAMP — WORN (TAILCONE) · airframe 48,539 hrs · 35,435 cycles

A CLAMP FOR THE TAIL CONE RELEASE MECHANISM CABLE WAS FOUND WORN AT STA 1510 CANT. THIS WEAR WAS BEYOND ALLOWABLE LIMITS SO THE CLAMP WAS REPLACED. FOUND DURING HMV.

Part: CUSP WEB — CRACKED (CABIN) · airframe 48,539 hrs · 35,435 cycles

DURING HMV A CRACK WAS FOUND ON CUSP WEB ANGLE STA Y=200 AND X=-54 AT CABIN FLOOR STRUCTURE. CUSP WEB ANGLE WAS REPAIRED IAW ERA 498198-14 REV ORIG.

Part: FRAME — CORRODED (FUSELAGE) · airframe 48,539 hrs · 35,435 cycles

DURING HMV CORROSION AND WEAR WAS FOUND ON FRAME STA Y=1380 BTW LONGERON 25L TO 25R. FRAME WAS REPAIRED IAW ERA 499466-14 REV ORIG.

Part: SKIN — CRACKED (FUSELAGE) · airframe 48,539 hrs · 35,435 cycles

THREE CRACKS WERE FOUND ON FUSELAGE SKIN AT THE UPPER FORWARD DOORJAMB CORNER AND BTW LONGERONS 20 AND 21 OF THE FWD CARGO COMPT.

Part: TAB — DELAMINATED (RT ELEVATOR) · airframe 48,539 hrs · 35,435 cycles

DELAMINATION ON RT ELEVATOR ANTI-FLOAT TAB UPPER/LOWER SKIN. RT ELEVATOR ANTI-FLOAT TAB UPPER/LOWER SKIN WAS REPAIRED IAW MD88 SRM 55-04 PARA 3A.

Part: SKIN — DAMAGED (RUDDER) · airframe 48,539 hrs · 35,435 cycles

DURING HMV DAMAGED METALIZE COAT WAS FOUND ON RT AND LT FACE OF RUDDER REF MD88 SRM 51-70-1A PARA 23 FOR REPAIR. JAN 23,2011 RUDDER RT AND LT FACE WAS REPAIRED IAW MD88 SRM 51-70-1A PARA 23.

Part: TAB — DAMAGED (LT ELEVATOR) · airframe 48,539 hrs · 35,435 cycles

DURING HMV LIGHTNING STRIKE WERE FOUND ON LT ELEVATOR CONTROL TAB TRAILING EDGE. TAB TRAILING EDGE WAS REPAIRED IAW MD88 SRM 55-04 PAR 3A.

Part: TAB — DAMAGED (LT ELEVATOR) · airframe 48,539 hrs · 35,435 cycles

LIGHTNING STRIKE ON LT ELEVATOR GEARED TAB TRAILING EDGE. REPAIRED PER SRM 55-04.

Part: SKIN — CORRODED (FUSELAGE) · airframe 48,539 hrs · 35,435 cycles

CORROSION ON FUSE SKIN FROM STA Y=731 TO 826 BTW LONGS 18L AND 30L. REWORKED AREA OF FUSE SKIN FOUND WITHIN LIMITS IAW DC9/MD80 SRM 53-04D FIG 53 PARA 26 AND 53-04D FIG 38.

Part: SKIN — CORRODED (FUSELAGE) · airframe 48,539 hrs · 35,435 cycles

CORROSION ON FUSELAGE SKIN STA Y=927 TO 1041 ON LONG 18L.

Part: SKIN — CORRODED (FUSELAGE) · airframe 48,539 hrs · 35,435 cycles

HIDDEN DAMAGE; CORROSION ON SKIN WHERE RUB STRIPS SETTLES FROM LONG= 18 RT TO LONG 26 RT STA 965-1032, STA 1124 TO 1134. FUSELAGE SKIN WAS BLENDED AND FOUND WITHIN LIMITS REF MD88 SRM 53-04D FIG 53.

Part: SKIN — CORRODED (FUSELAGE) · airframe 48,539 hrs · 35,435 cycles

HIDDEN DAMAGE; CORROSION ON SKIN WHERE RUBSTRIPS SETTLES FROM LONG=17 TO LONGERON 26 RT, STA Y=728 TO STA Y=760.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 48,539 hrs · 35,435 cycles

OP NR 0103; CRACK ON LONGERON 24LT AT SAT Y=160 AND STA Y=200.EA 09-069225-12AD REV D ME01. NEW SECTION OF LONGERON WAS INSTALLED IAW DC9/MD80 SRM 51-30-2 AND 51-30-05.

Part: DOOR FRAME — CORRODED (FUSELAGE) · airframe 48,539 hrs · 35,435 cycles

CORROSION ON MID CARGO COMPARTMENT DOORJAMB LWR BEAM BTW STA Y=636 TO 693. REPAIR PARTS WERE FABRICATED AND INSTALLED IAW DC9/MD80 SRM 53-05 FIG 123 SHEET 1.

Part: SPACER — CORRODED (FUSELAGE) · airframe 48,539 hrs · 35,435 cycles

CORROSION ON AFT CARGO COMPARTMENT DOORJAMB LWR BEAM PREVIOUS REPAIR SPACER BTE STA 1174 TO 1199 SPACER WAS REMOVED. NEW SPACER WAS FABBED IAW DC9/MD80 SRM 53-05 FIG 123 ITEM 9. NEW SPACER WAS INSTALLED IAW DC9/MD80 SRM 53-05 FIG 123 AND 51-30-5.

Part: FRAME — SCRATCHED (FUSELAGE) · airframe 48,539 hrs · 35,435 cycles

SCRATCH ON FWD LOWER CORNER OF RT WINDOW BELT FRAME BTW STA Y=693 AND Y=712. HFEC PERFROME IAW NDT SPM 06-10-01.001 NO CRACKS FOUND. REWORK STATED AS 'G' WILL CONTINUE SERVICE IN AS-IS COND BUT WITH RESTRICTIONS STATED ON ERA 498184-14 REV-ORIG.

Part: WINDOW FRAME — SCRATCHED (BS 1193-1212) · airframe 48,539 hrs · 35,435 cycles

SCRATCHES ON AFT LOWER CORNER OF RT WINDOW BELT FRAME BTW STA Y=1193 TO Y=1212 ALSO ON STA Y=1212 TO 1231. SCRATCHES REWORK IAW DC9/MD80 SRM 53-05 FIG 111. REWORK AS STATED AS H1 WILL CONTINUE SERVICE IN AS-IS COND, BUT WITH RESTRICTIONS STATED ON ERA 498184-14 REV ORIG.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 47,845 hrs · 34,941 cycles

DURING PSV IN MSP ON 03SEP2011 LIGHTNING STRIKE DAMAGE WAS DISCOVERED AT FUSELAGE STA 1155 BETWEEN L7L AND L8L. REPAIRED PER ER/A 495978-14. REQUIRES VISUAL REINSPECT AT INTERVALS NOT TO EXCEED 3000 LANDINGS AND PERMANENT REPAIR PRIOR TO EXCEEDING 8000 LANDINGS.

Part: SKIN — CRACKED (FUSELAGE) · airframe 47,845 hrs · 34,941 cycles

AT MSP PSV VISIT FOUND CRACK TO THE FUSELAGE SKIN AT STA 1418 S-2R. CRACK EMANATING FROM UPPER MOST FASTENER HOLD COMMON TO SHEAR TIE. REPAIRED PER ERA 495952-14 AND WORKED ON NRC 11.

Part: SKIN — CRACKED (FUSELAGE) · airframe 47,845 hrs · 34,941 cycles

AT MSP PSV VISIT FOUND CRACK TO FUSELAGE SKIN AT STA 1418 S-2L. CRACK IS EMANATING FROM THE UPPER MOST FASTENER HOLE COMMON TO SHEAR TIE. REPAIRED PER ERA 495951-14 AND WORKED ON NRC 12.

Part: PRESSURE PANEL — CRACKED (FUSELAGE) · airframe 47,845 hrs · 34,941 cycles

DURING PSV IN MSP, MAINTENANCE NOTED 2.4 INCH LONG CRACK COMMON TO THE CANTED PRESSURE PANEL JAMB PAN LOCATED AT STA 69. THE CRACK IS LOCATED IN THE LOWER RADIUS OF THE VERTICAL LEG OF THE PAN. PERMANENT REPAIR INSTALLED PER ER/A 494540-14.

Part: WIRE HARNESS — DEFECTIVE (CABIN) · airframe 47,832 hrs · 34,930 cycles

DURING LINE CHECK MAINTENANCE FOUND EMERGENCY LIGHT AT SEAT 20D INOPERATIVE. MAINTENANCE REPLACED LIGHT HARNESS AT SEAT 20D. OPERATION OF LIGHT NOW CHECKS OK.

Part: SKIN — CORRODED (FUSELAGE) · airframe 47,568 hrs · 34,740 cycles

FUSELAGE SURROUND DOUBLER AND SKIN AFT LAV SERVICE DOOR CUTOUT FS 1315, L-22L. CORROSION REPAIRED IAW ERA 494539-14.

Part: BATTERY — DISCHARGED (CABIN) · airframe 46,327 hrs · 33,877 cycles

DURING LINE CK, MX FOUND AFT RT AND LT OVERWING EXIT SIGN LIGHTS INOPERATIVE. MX R & R BATTERIES ON B5-105 AND OPS CHECKED THE SYS. OK FOR SERVICE.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 46,176 hrs · 33,787 cycles

FUSELAGE SKIN LT WINDOW BELT PANEL FS 1060-1098. REPAIRED IA W ERA 486640-14.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 46,176 hrs · 33,787 cycles

FUSELAGE SKIN LT WINDOW BELT PANELS FS 1231-1250. REPAIRED IAW ERA 488977-14.

Part: LIGHT — INOPERATIVE (SEAT 11D) · airframe 43,670 hrs · 32,104 cycles

PASSENGER SEAT 11D EMERGENCY LIGHTING FLOOR LIGHTS INOP/DAMAGED. REPLACED LIGHT ASSY. OPS CK GOOD.

Part: SKIN — DENTED (BS 1231 L27R) · airframe 37,686 hrs · 28,194 cycles

FUSELAGE SKIN/DOUBLER WERE DENTED AT TWO LOCATIONS AT APPROXIMATELY STA 1231, L-27R AFT OF THE CARGO DOOR CUTOUT. THE DAMAGE IN THE SKIN AND DOUBLER WAS CUT OUT AND REPAIR DOUBLERS WERE INSTALLED.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 37,686 hrs · 28,194 cycles

FUSELAGE SKIN C-3 CARGO DOOR OPENING LOWER EDGE. REPAIRED IAW ERA 464004-14.

Part: STRUCTURE — WORN (FWD CARGO DOOR) · airframe 35,816 hrs · 27,003 cycles

MAJOR REPAIR TO MD88 CARGO DOOR AFT EDGE IAW SRM 52-05D, FIG 50 REF NRC 18168 AND SON W33364. DOOR REMOVED FROM 9018, STOCKED AS SPARE, REPLACED DOOR ASSY.

Part: SMOKE DETECTOR — CONTAMINATED (LAVATORY) · airframe 35,298 hrs · 26,650 cycles

F/A`S REPORTED SMELLING SMOKE IN AFT LAV. AFT LAV SMOKE DETECTOR WENT OFF, F/A DISCONNECTED LAV SMOKE DETECTOR, RETURNED TO FLL. REPLACED AFT RT LAV SMOKE DETECTOR. FOUND SMOKE DETECTOR SITTING IN POOL OF SOAP FROM DISPENSER, LAV FIRE EXTINGUISHER DID NOT DISCHARGE. FOUND NO EVIDENCE OF FIRE OR SMOKE IN LAV. COMPLETED OPN 5088 AND OPN 5089 TROUBLESHOOTING ODORS/SMOKE AND PNEUMATIC DUCT BURNOUT.

Part: STRIP — OUT OF ALIGNMENT (OVERWING DOOR) · airframe 33,585 hrs · 25,488 cycles

UNABLE TO OPEN OVERWING EXITS WITHOUT EXCESSIVE FORCE. REALIGNED CABIN LINER TRIM STRIPS.

Part: ENGINE — OVERSPEED (NR 2) · airframe 33,065 hrs · 25,137 cycles

SUSPECT RIGHT COMPRESSOR STALL. EPR PEGGED ABOVE 2, N1 ABOUT 108 PERCENT SHUTDOWN IN FLIGHT. FOLLOWED SEVERE DAMAGE CHECKLIST THERE WAS SOME SMELL OF SMOKE WHICH CLEARED WHEN THE ENGINE WAS SECURED. EDP SHOWED N1 109 PERCENT FOR 30 SEC. PERFORMED BORO NO DEFECTS FOUND. DURING T/S FOUND THROTTLE CONTROL ROD BOLT MISSING CAUSING ENGINE OVERSPEED/STALLS. REPLACED ENGINE ALSO PERFORMED DUCT BURNOUT FOR SMOKE IN CABIN.

Part: DUCT — CONTAMINATED (APU) · airframe 30,691 hrs · 23,386 cycles

SMOKE ALARM AND ODOR IN RIGHT AFT LAV AFTER T/O RETURNED TO ATL. PERFORMED DUCT BURNOUT.

Part: APU — LEAKING (APU BAY) · airframe 30,680 hrs · 23,378 cycles

ATB, SMOKE IN THE CABIN AFTER T/O AFT LAV SMOKE DETECTORS WENT OFF. NO SMOKE NOTED IN LAVS OR AFT CABIN. REPLACED APU AND PERFORMED DUCT BURNOUT.

Part: ADC — MALFUNCTIONED (E/E BAY) · airframe 28,381 hrs · 21,771 cycles

CAPTS A/S INDICATOR WOULD NOT INCREASE PAST 60 KTS ON T/O ROLL. ABORTED T/O AT 90 KTS ON F/O`S INDICATOR. REPLACED NR 1 CADC PER MM CHAPT 34. PERFORMED FUNCTIONAL TEST. OPERATION NORMAL.

Part: OVEN — ODOR (AFT GALLEY) · airframe 27,651 hrs · 21,263 cycles

F/A REPORTS BAD ODOR, LIKE BURNING OIL IN AFT LEFT CABIN AS A/C WAS CLIMBING THRU FL 280 TO FL 300. ODOR LASTED APPROX 2 TO 3 MINS AND DISSIPATED. ODOR DID NOT RETURN. REPLACED DIRTY OVEN.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 25,757 hrs · 19,928 cycles

TWO CEILING EMERGENCY LIGHTS INOP FWD OF AFT CABIN DOOR. REPLACED B5-27 BATTERY PACK POWER SUPPLY AND BATTERIES. LIGHTS NOW OP NML

Part: SMOKE — DETECTED (COCKPIT) · airframe 21,763 hrs · 16,963 cycles

ON TAKEOFF NOTICED THE SMELL IN THE COCKPIT AND THE AFT LAV SMOKE ALARM WENT OFF. PREPARED FOR FERRY FLIGHT TO ATL.

Part: UNKNOWN — ODOR (COCKPIT) · airframe 21,760 hrs · 16,960 cycles

SMELLED FUMES / ODOR IN COCKPIT FROM 120 KNOTS ON TAKEOFF ROLL UNTIL 10,000 FT. ODOR VERY ACIDIC. NO SMOKE VISABLE BUT STUNG OUR EYES. CROSSFEEDS WERE CLOSED, ALL ANTI-ICE AND APU WERE OFF. TEMP CONTROLS WERE BOTH AT 12 O'CLOCK AND FLEX 50 EPR SETTING WAS 1.86. REPLACED RECIRC FAN FILTER. PERFORMED OPN 5088 DUCT BURNOUT. COULD NOT IDENTIFY CAUSE. REF LOG D286229004 FOR APU MCO. REPLACED WATER SEPARATOR BAGS. LEAK CHECKED NORMAL. ALSO CHECKED ALL WIRING IN COCKPIT OVERHEAD AND C/B PANELS. ALL NORMAL. OK FOR SERVICE.

Part: HOSE — CHAFED (RT HYD SYS) · airframe 21,487 hrs · 16,756 cycles

DURING FLT RT HYD QTY WENT TO ZERO WIH LOSS OF PRESSURE. MTC FOUND HYD HOSE WITH HOLE IN IT FROM CHAFING. REPLACED RT SYSTEM HYDRAULIC FILTER SUPPLY LINE - REPLACED FILTER AND ENGINE DRIVEN PUMP

Part: BULB — BURNED OUT (LT FUSELAGE) · airframe 20,985 hrs · 16,382 cycles

DURING SERVICE CHECK, FOUND LEFT AFT EXTERIOR EMERGENCY EXIT LIGHT INOP. RELAMPED SAME, OP CHECKS NORMAL.

Part: SKIN — DENTED (FUSELAGE) · airframe 18,495 hrs · 14,520 cycles

THE FUSELAGE SKIN WAS FOUND TO HAVE A DENT AT THE CUSP LINE JUST AFT OF THE L1 DOOR. THE DENT WAS REMOVED WITH A 6 X 3 CUTOUT AND AN EXTERNAL REPAIR DOUBLER PER ERA 334171-14. THE DAMAGE WAS FOUND AT HMV.

Part: CHARGER — INOPERATIVE (CABIN)

FWD SECTION EMERGENCY LIGHTS INOP. REPLACED CHARGER.

Part: LIGHT — FAILED (ROW 38)

F/A NOTICED ELECTRICAL SMELL IN AFT OF CABIN NEAR LAVS. FOUND OVERHEAD FLUORSCENT LIGHT SHORTED OUT AT ROW 38 ABC. REMOVED WIRES FROM SOCKET AND CAPPED OFF.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

FIRST CLASS EMERGENCY FLOOR TRACK LIGHTS WILL NOT ILLUMINATE. REPLACED POWER SUPPLY.

Part: RADOME — COLLAPSED (FWD FUSELAGE)

A/C EXPERIENCED LOUD POP AND THEN LOUD RUSH OF AIR NEAR COCKPIT EXTERIOR. PRESSURIZATION OK. RTB ATL WHERE TWR NOTIFIED THE CREW THE RADOME HAD COLLAPSED. REMOVED AND REPLACED RADOME. INSPECTED BOTH ENGS FOR FOD AND AIRFRAME FOR DAMAGE, NONE NOTED. TESTED WX RADAR ALL CKS OK. ALL MTC COMPLETED PER M/M.

Part: LIGHT — BROKEN (CABIN)

WORKING MCO, RED EMER TRACK LIGHT, ONE INOP. REPLACED LIGHT ASSY.

Part: ANGLE — CRACKED (RT MLG WW)

FOUND DURING B-1 LETTER CHECK - RT WHEELWELL AFT O/B STRIKER ANGLE CRACKED - REPAIRED PER SRM 53-05, FIG 81A.

Part: SKIN — DAMAGED (RT ELEV TAB)

FOUND HAIL DAMAGE, RT ELEV MIDDLE TAB HAS HAIL DAMAGE. MADE BONDED REPAIRS PER MD 88 SRM 55-04 WEIGHT 5.48 LBS 5-1-95.

Part: SKIN — DAMAGED (LT ELEV TAB)

FOUND AFTER HAIL STORM, LT ELEV MIDDLE TRIM TAB HAS HAIL DAMAGE S/N 891LRH MADE BONDED REPAIR PER MD 88 SRM 55-04, BAL WEIGHT 5.38 LBS 5-1-95.