N915DE

Part: WIRE — BROKEN (EMERGENCY LIGHT) · airframe 64,957 hrs · 50,892 cycles

EMERGENCY AISLE LIGHTS ROW 24-27 INOP. REPAIRED BROKEN WIRE SPLICE PER BOEING SWPM CH 20 AND MD88 WDM 33-51. OPS CHECK NORMAL. OK FOR SERVICE. (LP6658774)

Part: STRUCTURE — DAMAGED (AFT CARGO DOOR) · airframe 64,834 hrs · 50,769 cycles

AFT CARGO DOOR BOTTOM TRIM DAMAGED. PERFORMED TIME LIMITED REPAIR PER ERA 499926-14MA REV A. PERMANENT REPAIR TO BE ACCOMPLISHED WITHIN 100 FLIGHT HOURS. OK FOR SERVICE. (LP6032568)

Part: CONNECTOR — SPARKS (WINDOW HEAT) · airframe 64,505 hrs · 50,464 cycles

DURING FLT, CENTER WINDSHIELD WINDOW HEAT CONNECTION SPARKED AND MADE LOUD POPPING SOUND. REMOVED AND REPLACED CENTER WINDSHIELD IAW MD88 AMM 56-10-01C. LEAK CK GOOD. WINDOW HEAT CKS GOOD PER MD88 AMM 30-41. WINDOW, COCKPIT OFF 09-5611-9-0013 S/N 31037 ON 09-5611-9-0013 S/N 30782 (LP6031362)

Part: HANDLE — MALFUNCTIONED (TRIM SYSTEM) · airframe 64,131 hrs · 50,133 cycles

IN FLIGHT EMERGENCY. ON DEPARTURE F/OS PRIMARY TRIM AND SUITCASE HANDLES INOP WHEN TRIMMING AFT. CAPT YOKE SWITCH WAS INTERMITTENT WHEN TRIMMING AFT WITH PRIMARY TRIM. ALT TRIM OPERATED NORMALLY FORWARD AND AFT. AFTER LANDING CAPT PRIMARY, F/O PRIMARY ON YOKE AND SUITCASE HANDLES LONGITUDINAL TRIM INOPERATIVE IN BOTH DIRECTIONS. CIRCUIT BREAKERS ALL IN. R & R PRIMARY AND ALT TRIM MOTORS IAW AMM 27-40. NO HELP. REPLACED THE STAB TRIM BRAKE UP RELAY R20-18 IAW WDM 27-41 . ALL OPS NORMAL.

Part: HOUSING — LEAKING (APU FUEL) · airframe 63,997 hrs · 50,015 cycles

STRONG SMELL OF GASOLINE IN COCKPIT AND CABIN WHEN APU STARTED AFTER LANDING. C/W REQUIREMENTS OF NO GO ODI PREVENTION 2172. FOUND LEAKING FUEL FILTER HOUSING. REPLACED PACKING ON FILTER HOUSING PER B717 AMM 49-30. LK CHECK GOOD. PERFORM FULL DUCT BURNOUT PER WC 7100-2619 CLEANED APU INLET. NO SMOKE OR FUMES PRESENT. A/C OK FOR SVC. (LP5799778)

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 63,777 hrs · 49,820 cycles

OVERWING EMER LIGHTS ABOVE DOOR AFT POS INOP. R/R BATTERIES IN EMER BATT PACK PER MD88 AMM 33-53. OPS CK GOOD.

Part: STRUCTURE — DAMAGED (SLAT) · airframe 63,749 hrs · 49,791 cycles

SLATS 1 AND 2 RT. DAMAGED. REPLACED #1 RT. SLAT PER MD88 AMDS WORK CARD 2700-4224-RH-01, REPLACED #2 RT. SLAT PER MD88 AMDS WORK CARD 2700-4224-RH-02. (LP5742017)

Part: CONTROL CABLE — DAMAGED (SLATS) · airframe 63,749 hrs · 49,791 cycles

SLAT DRIVE CABLE ASSY RUN NO. 225 SEGMENT A & B EXTEND DAMAGED. REPLACED AND RIGGED CABLE REF AMDS W/C'S 2000-9000-01 AND 2000-9000-02. (LP1044890)

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 63,529 hrs · 49,595 cycles

L & R AFT EMERGENCY UPPER EXIT LIGHTS INOP. REMOVED & REPLACED ASSOCIATED BATTERY PACK LTS PER AMM 33-53. OPS CHECK GOOD. (LP5516259)

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 62,916 hrs · 49,067 cycles

AFT OVERWING OVERHEAD EXIT LIGHTS INOP. REMOVED AND REPLACED AFT OVERWING EMERGENCY LIGHT BATTERIES PER MD88 AMM 33-53 CKS GOOD. (LP4808226)

Part: SLAT — CRACKED (RT WNG) · airframe 62,702 hrs · 48,882 cycles

RIGHT WING SLAT 0 "ZERO" HAS 2, 4 INCH GOUGES AND 1 INCH CRACK. REMOVED AND REPLACED RT WING SLAT ZERO PER WORK CARD 2700-4224-RH-0. (LP5351990)

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 62,613 hrs · 48,808 cycles

EMERGENCY LIGHTS FOR OVERWING W/N ILLUMINATE FOR ROW 25. REMOVED BATTERY PACK AND REPLACED BATTERIES, OP'S CK'S GOOD PER AMM 33-53.

Part: STRINGER — DAMAGED (BS 332-360) · airframe 62,551 hrs · 48,746 cycles

TOOLING DAMAGE DISCOVERED ON STR 17R LWR LEG FROM STA 332-360. CHECKED LIMITS REF MD-88 SRM 53-01-00 WITHIN LIMITS. ASSOCIATED ER/A 88-550809 ADDED FOR AC 9015. ERA IS MAJOR THUS MAKING THIS LOG REPORTABLE. (LP0758656)

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 62,312 hrs · 48,539 cycles

EMERGENCY LIGHTS AT THE L1, R1, & COCKPIT WERE INOPERATIVE. REPLACED THE BATTERY PACK. OPS OK IAW AMM 33-53.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 62,203 hrs · 48,444 cycles

OVERWING EMERGENCY EXIT LIGHT W/N TEST AT SEATS 25ABC AND 25ED. REMOVED AND REPLACED BATTERY PACKS IAW AMM 33-53.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 61,947 hrs · 48,243 cycles

FOUND AFT OVERWING EXIT LIGHTS INOP. R&R BATTERY PACK B5-105 PER AMM 33--53, CHK OK.

Part: NONE — NONE (NONE) · airframe 62,551 hrs · 48,746 cycles

ER/A 550809-14 REV B INCORPORATES SECTION II PERMANENT REPAIR II REQUIREMENTS. ASSOCIATED ER/A 55-080914 ADDED FOR AC 9015 COMPLIED WITH ERA 550809-14 REV D SEC II REPAIR II. OKAY TO CLOSE MONITOR. (LP0482568)

Part: EFIS — ODOR (COCKPIT) · airframe 61,165 hrs · 47,621 cycles

CAPTAIN FOUND THE FIRST OFFICER`S PFD AND ND INOPERATIVE, ADF FLICKERING AND RADIO ALTIMETER INOPERATIVE. CAPTAIN STARTED APU AND NOTED AN ELECTRICAL ODOR IN THE COCKPIT. FOUND THE COCKPIT WET. REMOVED WATER AND DRIED COCKPIT. ODOR WAS ORIGINATING FROM EFIS SYMBOL GENERATOR. REPLACED EFIS SYMBOL GENERATOR AND ADF CONTROL PANEL. ALL CHECKED NORMAL.

Part: COMPRESSOR — STALLED (ENGINE) · airframe 61,143 hrs · 47,605 cycles

LARGE BOOM SOUND , FOLLOWED WITH VIOLENT A/C SHAKE AND FLASH OUTSIDE OF AIRCRAFT. FLIGHT ATTENDANT SMELLED SMOKE IN AFT CABIN. PASSENGER SMELLED ELECTRICAL FIRE AT ROW 19. NO AIRCRAFT SYSTEM OF ENGINE MALFUNCTIONS. OPENED LEFT AND RIGHT ENGINE FOR BOROSCOPE. C/W GVI FOR INDICATION OF LIGHTENING STRIKE, NO DAMAGE FOUND. PERFORMED BSI OF #1 ESN 726 908 FOR SURGE CONDITION PER MD88 AMM 72-00-00. NO RESTRICTIVE DAMAGE. PERFORMED BSI OF #2 ESN 718 543 FOR SURGE CONDITION PER MD88 AMM 72-00-00. NO RESTRICTIVE DAMAGE. CLOSED UP LEFT ANDRIGHT ENGINES AFTER BOROSCOPE PER MD88 AMM 72-00"456525". C/W GVI OF LEFT AND RIGHT ENGINE INLET, EXHAUST AND MAGNETIC CHIP DETECTORS, NTF. PROPULSION ENGINEERING VERIFIED COMPRESSOR STALL WITH AN EPR DROP OF .5 AND N1 DROP OF 10% AND IMMEDIATE RECOVERY. PERFORMED POWER ASSURANCE AND ACCEL/DECEL CHECK . ENG WITHIN OPERATIONAL LIMITS PER MD88 AMM 71-00-00. COMPLIED WITH PNEU DIST CABIN SMOKE/ODOR TROUBLESHOOTING. AMDS CARD# 2120-2362. ALL NORMAL. OK FOR SERVICE. (LP7106072)

Part: SKIN — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION ON BARREL NUT HOLE NR 1 IN SKIN AT LT SIDE OF HORIZONTAL STABILIZER. REPAIRED IAW ETI-88-17- 238 REV.1 AND ER/A 562431-14 AD REV A.

Part: FRAME — CRACKED (BS 1485) · airframe 60,898 hrs · 47,411 cycles

CRACK ON FRAME BS 1485 , LONGERON 24R. REPAIRED IAW SRM 53-03, FIG 43.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 60,898 hrs · 47,411 cycles

CRACKED WATER TANK SUPPORT STA Y=522 X=-43 Z=-7 AT CENTER CARGO COMPARTMENT (RT TUNNEL) (C2). CRACKED WATER TANK SUPPORT STA Y=522 X =-43 Z=-7 AT CENTER CARGO COMPARTMENT WAS REPLACED PER ETI-88-18-002 REV 1 AND ERA:564881-14 REV ORIGINAL.

Part: BEAM — CRACKED (CARGO DOOR) · airframe 60,898 hrs · 47,411 cycles

DURING C1 DOOR PAN DISASSEMBLY, CRACK WAS FOUND ON BEAM NR 5 FWD EDGE IN REF NRC 00240. CRACKS UPPER FWD EDGE PAN AND BEAM NR 5 WERE REPAIRED PER ETI-88-17-248 REV 3 AND ER/A:564810-14 REVISION ORIGINAL.

Part: ACCESS PANEL — CORRODED (RT WING) · airframe 60,898 hrs · 47,411 cycles

CORROSION ON RH/LH FUEL ACCESS PLATES NBR 1409C AND 1303C AT RH AND LH WING. (AD). LEVEL CORROSION 2: ACCESS PLATES NBR 1303C AND 1409C BLEND OUT REPAIR IS NOT PERMITTED ON THE UPPER WING ACCESS DOOR (P/N 3912757) DUE TO THE REDUCED AREA OF THE CONDUCTIVE INTERFACE. FUEL ACCESS PLATE FUEL 1303C AND 1409C WERE REPLACED PER DC-9/MD-80 SRM 51-22-2A CONDITION III. (LP0375572)

Part: TIE DOWN — CORRODED (BS 1003-1155) · airframe 60,898 hrs · 47,411 cycles

INITIAL INSPECTION: CORROSION ON TIE TRACKS LH/RH FROM STA Y=1003 TO STA Y=1155 AT AFT CARGO COMPARTMENT. CORROSION LEVEL II. TIE TRACKS LH/RH FROM STA Y=1003 TO STA Y=1155 AT AFT CARGO COMPARTMENT WERE REPLACED PER DC-9/MD-80 SRM 51-30-2 AND SRM 51-30-1. (LP0373197)

Part: CARGO TRACK — CORRODED (BS 1155-1322) · airframe 60,898 hrs · 47,411 cycles

CORROSION ON CARGO TRACKS, BS 1155 TO 1322 IN THE AFT CARGO BAY. THE CARGO TRACKS WERE REPLACED.

Part: INTERCOSTAL — CORRODED (BS 1309-1322) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION OUT OF LIMITS ON INTERCOSTAL BETWEEN BS 1309 - 1322, LONGERON 28L IN THE AFT CARGO BAY. THE INTERCOSTAL WAS REPAIRED IAW SRM 53-01, FIG 2.

Part: LONGERON — CORRODED (BS 1338) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION OUT LIMITS ON LONGERON 28L, BS 1338. THE LONGERON WAS REPAIRED IAW SRM 53-02, FIG 18.

Part: ANGLE — CORRODED (BS 1309) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION ON VERTICAL ANGLE BS 1309, LONGERON 23L IN THE AFT CARGO BAY. THE VERTICAL ANGLE WAS REPLACED IAW SRM 51-30-2, 51-30-1, AND DWG 5936661, REV BC.

Part: WEB — CRACKED (BS 1212-1222) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION AND A CRACK WAS FOUND ON THE WEB BS 1212 TO 1222, LONGERON 27R. THE WEB WAS REPAIRED IAW SRM 53-01, FIG 2, SHEET 3.

Part: PAN — CRACKED (CARGO DOOR) · airframe 60,898 hrs · 47,411 cycles

CRACK ON PAN UNDER STOPS FITTINGS 2,4 FWD AND 4, AND 5 AFT ON FWD CARGO DOOR. THE PAN WAS REPAIRED IAW ETI-88-17-245, REV. 3 AND ERA 564546-14 REV. ORIGINAL. STOP NR 4 WAS REPAIRED IAW SRM 52-05, FIG 50, AND STOP NR 5 WAS REPAIRED IAW SRM 52-03 D FIG.10.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION OUT LIMITS ON FRAME CLIP STA Y=1231 BTW LONG 30 AND 29R AT AFT CARGO COMPARTMENT. LEVEL CORROSION 2. FRAME CLIP STA Y=1231 BTW LONG 30 AND 29R AT AFT CARGO COMPARTMENT WAS REPLACED PER SRM 51-10-4, 51-30-2 AND 51-30-5.

Part: SKIN — DENTED (FUSELAGE) · airframe 60,898 hrs · 47,411 cycles

RE-EVALUATE DENT STA 1290-1338 ACROSS L-22R. DAMAGE AREA WAS REPAIRED PER ETI 88-17-241 REV 4 AND ER/A 494621-14 REV "B" SECTION III.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION ON FLOOR SUPPORT STA Y= 788 BTW LONG 24L AND LONG 24R AT MID CARGO COMPARTMENT. (LEVEL CORROSION 2) FLOOR SUPPORT STA Y=788 WAS REPAIRED PER SRM 53-01 FIG 2.

Part: ANGLE — CRACKED (CARGO DOOR) · airframe 60,898 hrs · 47,411 cycles

DURING DISASSEMBLY PARTS OF CARGO DOOR (C1), CRACK WAS FOUND ON ANGLE T IN REF NRC 00240. ANGLE T WAS REPLACED PER SRM 51-30-2, 51-30-4 AND DWG 9957663 REV W.

Part: SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION ON MEMBRANE AFT FACE SUPPORT LOWER SECTION Y=1338 PROJECTION LONGERON LT 29 AT AFT CARGO COMPARTMENT. REF NRC S/N 00778. LEVEL CORROSION II. SUPPORT WAS REPLACED PER SRM 53-14-3.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION OUT OF LIMITS ON FLOOR SUPPORT BTW STA Y=1136-1212 LONG 29R AT AFT CARGO COMPARTMENT (C3). (LEVEL CORROSION 2) FLOOR SUPPORT WAS REPLACED PER 51-30-1 AND 51-30-2.

Part: STIFFENER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION ON STIFFENER Y=1338 PROJECTION LONG 29RH AT BASE OF THE AFT PRESSURE BULKHEAD. LEVEL CORROSION II. STIFFENER WAS REPLACED PER SRM 53-14-3 FIG 7.

Part: STRAP — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CARGO C3, CORROSION OUT OF LIMITS ON STRAP AT STA Y=1155 BTW LONG'S 25L TO 27L. (LEVEL CORROSION 2) STRAP WAS REPLACED PER SRM 51-30-5 AND DWG 9936073 REV W.

Part: NOT REPORTED — CRACKED (BS 1402) · airframe 60,898 hrs · 47,411 cycles

02 CRACKS LOCALIZATED AT STA Y= 1402 ON LONG 2RH AND 2LH AND ALSO ONE CRACK ON STA Y= 1418 BETWEEN LONG 1 AND 2RH .DAMAGE AREA WAS REPAIRED PER ETI-88-17-237 REV. 2 AND ERA 493007-14AD REV. E SEC. IV. (LP0362157)

Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 60,898 hrs · 47,411 cycles

A DISCREPANT AREA WAS FOUND (EXTERNAL REPAIR DOUBLER IN SKIN) LOCALIZED ON STA Y=1418 BTW LONG 2RH AND 3RH.DAMAGE AREA WAS REPAIRED PER ETI-88-17-237 REV 2 AND ERA 493007-14AD REV E SEC IV.

Part: ANGLE — CORRODED · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION ON THE LT INTERNAL ANGLE IN THE AFT ACCESSORY BAY WALKING BRIDGE. CORROSION WAS REMOVED IAW SRM 51-10-3, PAR 26. UT WAS ACCOMPLISHED IAW NDT SPM 04-00-07, PAR 5, FIG 3 SHEET 1, AND 2, FOUND TO BE OUT LIMITS IAW ER/A 511165-14MA, REV D. REPAIRED IAW SRM 53-01 FIG 2.

Part: DOOR FRAME — CRACKED (RT MLG) · airframe 60,898 hrs · 47,411 cycles

CRACKED WEB ON THE RT MLG AFT DOOR FRAME. REPAIRED IAW SRM 57-01, FIG 3, SHEET 2.

Part: CHANNEL — CRACKED (LT LG DOOR FRAME) · airframe 60,898 hrs · 47,411 cycles

CRACKED CHANNEL ON THE RT MLG FWD DOOR FRAME. THE CHANNEL WAS REPLACED IAW SRM 51-30-2 AND SRM 51-30-5.

Part: ANGLE — CRACKED (BS 1463) · airframe 60,898 hrs · 47,411 cycles

CRACK ON THE LT ANGLE THAT ATTACH FUSELAGE TO VERTICAL STABILIZER BS 1463. DAMAGED AREA WAS REPAIRED IAW DWG SR09530296, REV.A, HFC IAW SPM 06-10-01.001. NO CRACKS WERE FOUND AFTER TRIM OUT.

Part: CHANNEL — CRACKED (LT MLG DOOR FRAM) · airframe 60,898 hrs · 47,411 cycles

CRACK ON PREVIOUS REPAIR DOUBLER OF FWD DOOR FRAME AT THE LEFT MLG WW. THE CHANNEL WAS REPLACED IAW SRM 51-30-5, AND SRM 51-30-2.

Part: DOUBLER — WORN (CARGO DOOR) · airframe 60,898 hrs · 47,411 cycles

WORN FWD AND AFT LOWER EDGES ON EXTERNAL PRODUCTION DOUBLERS AT CENTER CARGO DOOR. NEW AFT EXTERNAL DOUBLERS WERE INSTALLED IAW SRM 51-30-2 AND NEW FWD LOWER DOUBLER WAS INSTALLED IAW SRM 51-30-2.

Part: LONGERON — CRACKED (BS 1437) · airframe 60,898 hrs · 47,411 cycles

CRACK ON LONGERON 5R, BS 1437. THE LONGERON WAS REPAIRED IAW SRM 53-02, PAR 1, AND INSTALLED IAW SRM 51-30-05.

Part: ACCESS PANEL — CORRODED (RT WING) · airframe 60,898 hrs · 47,411 cycles

CORROSION ON RT FUEL ACCESS PLATES NR 1436C, 1410C AND 2302C AT RT WING. DUE TO CORROSION LEVEL 2 FUEL ACCESS PLATE NR 1436C, 1410C AND 2302C WERE REPLACED AND VERIFIED PER IPC 57-30-00-31A AND SRM 51-22-2A AND THEY WILL BE INSTALLED WITH AMDS 2800-0390.

Part: SKIN — WORN (TE FLAP) · airframe 60,898 hrs · 47,411 cycles

WEAR PREVIOUS REPAIR ON UPPER SKIN, OUTBD FLAP VANE AT RT INTERNAL FLAP (AD). PREVIOUS REPAIR ON UPPER SKIN, OUTBD FLAP VANE AT RT INTERNAL FLAP WAS REPLACED PER SRM 57-03D PAR 11.

Part: CHANNEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

OUT OF LIMITS CORROSION ON CHANNEL OF AFT LAVATORY TRY NR 1309A PAX CABIN. LEVEL CORROSION 2 CHANNEL WAS REPLACED PER SRM 51-30-2.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION ON "Z" FLOOR SUPPORT BESIDE RT TIE TRACK BTW STA Y 427 TO 446 AT FWD CARGO COMPARTMENT. CORROSION LEVEL II. CORROSION ON "Z" FLOOR SUPPORT BESIDE RT TIE TRACK BTW STA Y 427 TO 446 AT FWD CARGO COMPARTMENT WAS REPLACED PER SRM 51-30-1, SRM 51-30-2 AND DWG 5936660 REV BZ.

Part: BEAM — CRACKED (L1 DOOR) · airframe 60,898 hrs · 47,411 cycles

CRACKED BEAM 6 (MID SECTION) AT FWD PASSENGER DOOR (L1). THE BEAM WAS REPAIRED IAW ERA 498178-14MA REV. ORIGINAL.

Part: CUSP WEB — CORRODED (BS 1154) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION ON RT CUSP WEB BS 1154. CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A.

Part: INTERCOSTAL — CRACKED (BS 937) · airframe 60,898 hrs · 47,411 cycles

CRACK ON THE RT INTERCOSTAL BS 937 AT THE KEEL BEAM AREA. THE INTERCOSTAL WAS REPLACED IAW SRM 51-30-01, 51-30-02, 51-30-05, AND DWG 9936368, REV AW.

Part: INTERCOSTAL — CRACKED (PAX DOOR) · airframe 60,898 hrs · 47,411 cycles

CRACKED INTERCOSTAL BS 185 BETWEEN BEAM 4-5 AT FWD PASSENGER DOOR (L1). THE INTERCOSTAL WAS REPLACED IAW SRM 51-30-2.

Part: PAN — CRACKED (CARGO DOOR) · airframe 60,898 hrs · 47,411 cycles

CRACKED AFT INNER PAN LOCATED BETWEEN BEAMS NR 1 AND 2 AT THE CENTER CARGO DOOR. THE PAN WAS REPAIRED IAW SRM 52-05, PAR 25, FIG 26A.

Part: LONGERON — CRACKED (BS 1437) · airframe 60,898 hrs · 47,411 cycles

CRACKED LONGERON 16R, BS 1437 IN THE AFT ACCESSORY BAY. THE LONGERON WAS REPLACED IAW SRM 53-14-04, FIG 4, 51-10-03, PAR 14, 21, 51-30-02, 51-30-05, AND 51-10-04.

Part: SUPPORT ANGLE — CRACKED (RT WING) · airframe 60,898 hrs · 47,411 cycles

CRACKED SUPPORT ANGLE OF FWD VORTILON AT RT WING. THE SUPPORT ANGLE WAS REPAIRED IAW SRM 57-01, FIG 3, SHEET 3.

Part: RUB STRIP — CORRODED (RT WING) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION AND DEBONDED RUB STRIBS AT FUEL ACCESS PANELS 1414C, 1410C, 1409C, AND 1436C, RT WING. CORROSION LEVEL II. REPLACED IAW SRM 51-22-2A.

Part: INTERCOSTAL — CRACKED (BS 988) · airframe 60,898 hrs · 47,411 cycles

CRACKED LT INTERCOSTAL BS 988 AT KEEL BEAM AREA. THE INTERCOSTAL WAS REPLACED IAW SRM 51-30-2, AND SRM 51-30-5.

Part: ANGLE — CRACKED (BS 196) · airframe 60,898 hrs · 47,411 cycles

CRACKED ANGLE BELOW BEAM 1 BS 196 AT THE FWD SERVICE DOOR. THE ANGLE WAS REPLACED IAW SRM 51-30-1, 51-30-5, AND DWG 9911579, REV L.

Part: SUPPORT ANGLE — CRACKED (LT WING) · airframe 60,898 hrs · 47,411 cycles

CRACKED SUPPORT ANGLE OF FWD VORTILON AT THE LT WING. THE SUPPORT ANGLE WAS REPAIRED IAW SRM 57-01, FIG 3, SHEET 3.

Part: FLOOR SKIN — CORRODED (BS 130-148) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION ON DIAPHRAGM BETWEEN BS 130 - 148, RBL 33 COCKPIT FLOOR. THE DIAPHRAGM WAS REPAIRED IAW SRM 51-70-4, FIG 2.

Part: BEAM — CRACKED (R1 DOOR) · airframe 60,898 hrs · 47,411 cycles

CRACKED BEAM 1 AFT EDGE AT FWD R1 DOOR. THE BEAM WAS REPLACED IAW SRM 51-30-2, AND 51-30-5.

Part: FLOOR SUPPORT — CRACKED (BS 769-788) · airframe 60,898 hrs · 47,411 cycles

CRACKED FLOOR SUPPORT BL 0 BTW BS 769 - 788.

Part: SKIN — CRACKED (RT WING) · airframe 60,898 hrs · 47,411 cycles

15 CRACKS ON BOLT HOLES AT XRS 189 TO 214 AND STRINGERS 12 TO 15 ON THE RT WING LOWER ACCESS DOOR CUTOUT. REPAIRED IAW ETI-88-17-240, REV 1, AND ERA 564488-14AD, REV ORIGINAL.

Part: FLOORBEAM — CRACKED (BS 1098) · airframe 60,898 hrs · 47,411 cycles

CRACKED FLOORBEAM AT BS 1098 BETWEEN BL 0 AND LBL 22. THE FLOORBEAM WAS REPLACED IAW SRM 53-14-3, AND 51-30-5.

Part: SKIN — CRACKED (LT WING) · airframe 60,898 hrs · 47,411 cycles

CRACKS ON BOLT HOLES AT XRS=189 TO 214 AND STRINGER 12 TO 15, LT WING LOWER ACCESS DOOR CUTOUT. THE CRACKS WERE REPAIRED IAW ETI-88-17-240, REV 1, AND ER/A 564488-14AD, REV ORIGINAL.

Part: RETAINER — CORRODED (R1 DOOR) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION FOUND ON SEAL RETAINER LOWER AREA AT THE R1 SERVICE DOOR. THE SEAL RETAINER WAS REPLACED IAW SRM 51-30-1, AND 52-42-0.

Part: DOOR FRAME — CRACKED (BS 207) · airframe 60,898 hrs · 47,411 cycles

CRACKED DOOR FRAME WEB BS 207, LONGERON 15L AT PAX CABIN. THE DOOR FRAME WEB WAS REPAIRED IAW SRM 53-05, PAR 153, FIG 142.

Part: CUSP WEB — CORRODED (BS 1231-1245) · airframe 60,898 hrs · 47,411 cycles

CORROSION OUT LIMITS ON THE CUSP WEB AT BS 1231 AND 1245, LH SIDE OF THE PAX CABIN. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-11.

Part: FRAME ANGLE — CRACKED (BS 1309) · airframe 60,898 hrs · 47,411 cycles

CRACKED FRAME ANGLE BS 1309, BETWEEN LONGERONS 13L AND 14L. FABRICATED AND INSTALLED THE SECTION OF THE FRAME AND REPAIR SPLICE SRM 53-03, FIG 3 CLASS A, DRAWING 9912243 REV JB, SRM 51-30-2, & 51-30-5.

Part: CUSP WEB — CORRODED (BS 630) · airframe 60,898 hrs · 47,411 cycles

CORROSION ON THE RT CUSP WEB BS 630 BETWEEN RBL 56 TO 60. REPAIRED IAW SRM 53-05, FIG 131A-1.

Part: FRAME ANGLE — CRACKED (BS 1309) · airframe 60,898 hrs · 47,411 cycles

CRACKED FRAME ANGLE ON BS 1309 BETWEEN LONGERONS 13R - 14R. A REPAIR WAS FABRICATED IAW SRM 53-03, FIG 3. AND DRAWING 9912243, REV JB, AND INSTALLED IAW SRM 51-03 FIG.3, AND 51-30-2 & 51-30-5.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 60,898 hrs · 47,411 cycles

CRACK ON CUSP WEB STA 1184 LT SIDE CABIN PAX. CABIN PAX WAS REPAIRED PER SRM 53-05 FIG 131A-13.

Part: FLOOR SUPPORT — CRACKED (BS 1322) · airframe 60,898 hrs · 47,411 cycles

DURING INSPECTION, CRACKED FLOOR SUPPORT BS 1322, RBL 17. THE FLOOR SUPPORT WAS REPAIRED IAW SRM 53-01, FIG. 2.

Part: CUSP WEB — CORRODED (BS 1123) · airframe 60,898 hrs · 47,411 cycles

CORROSION ON RT CUSP WEB BS 1123. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-14.

Part: FLOOR SUPPORT — CRACKED (BS 332-598) · airframe 60,898 hrs · 47,411 cycles

DURING INSPECTION, CRACKED FLOOR SUPPOR BS 332 - 598. THE FLOOR SUPPORT WAS REPLACED IAW SRM 53-14-3, AND 51-30-5.

Part: CUSP WEB — CORRODED (BS 1227-1229) · airframe 60,898 hrs · 47,411 cycles

OUT OF LIMITS CORROSION ON THE RT CUSP WEB FROM BS 1227 TO 1229. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-13.

Part: ANGLE — CORRODED (BS 1350) · airframe 60,898 hrs · 47,411 cycles

CORROSION ON ANGLE IN THE AFT VENTRAL DOOR FRAME LOWER BS 1350 BETWEEN RBL 17 TO LBL 17. THE DAMAGED AREA WAS REPAIRED IAW SRM 53-05, FIG 34.

Part: CUSP WEB — CORRODED (BS 1069-1071) · airframe 60,898 hrs · 47,411 cycles

CORROSION OUT OF LIMITS ON THE RT CUSP WEB BETWEEN BS 1069 AND 1071. DAMAGE AREA WAS REPAIRED IAW SRM 53-05, FIG 131A-14.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 60,898 hrs · 47,411 cycles

CRACK ON LONG 3L STA Y=1437 AT AFT ACCESSORY COMPT. CRACK ON LONG 3L STA Y=1437 AT AFT ACCESSORY COMPT. WAS REPAIRED PER SRM 53-02 PAR 12.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION OUT OF LIMITS ON RT CUSP WEB STA Y= 569. (LEVEL CORROSION 2) CORROSION OUT OF LIMITS ON RT CUSP WEB STA Y= 569 WAS REPAIRED PER SRM 53-05 FIG 131A.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 60,898 hrs · 47,411 cycles

CRACK ON RT CUSP WEB STA Y= 832 BTW X= -56 TO X=-60 IN REF NRTC 00683 AT PAX CABIN. DAMAGE ON RT CUSP WEB STA Y= 832 BTW X= -56 TO X=-60 WAS REPAIR PER SRM 53-05 FIG 131A-14.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 60,898 hrs · 47,411 cycles

SEVERAL CORROSION POINTS ON FLOOR SUPPORT FROM Y 162 TO 195 AND X54 AT FWD WET AREA. LEVEL CORROSION 2. FLOOR SUPPORT FROM Y 162 TO 195 AND X54 AT FWD WET AREA WAS REPLACED PER SRM 51-30-2 AND 51-30-5.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION OUT OF LIMITS ON LT CUSP WEB FROM STA Y= 160 TO STA Y=164, X 54 AT PAX CABIN. CORROSION LEVEL 2 CUSP WEB WAS REPAIRED PER SRM 51-70-4.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 60,898 hrs · 47,411 cycles

SEVERAL CORROSION POINTS ON FLOOR SUPPORT Y 200 AND X54 AT FWD WET AREA (W1). FLOOR SUPPORT Y 200 AND X54 AT FWD WET AREA WAS REPLACED PER SRM 51-10-2 & DWG 9910078-627.

Part: FITTING — CORRODED (FLOOR PANEL) · airframe 60,898 hrs · 47,411 cycles

CORROSION ON FITTINGS OF FLOOR PANEL P/N SAA9957828-11. FITTINGS WERE REPLACED PER SRM 51-10-4.

Part: RIB — CRACKED (RT WING) · airframe 60,898 hrs · 47,411 cycles

CRACK ON RIB FORMER STA XRS=332 AT FIXED LEADING EDGE INTERNAL STRUCTURE, RT WING. CRACK RIB FORMER ON STA XRS=332 AT FIXED LEADING EDGE INTERNAL STRUCTURE, RT WING WAS REPAIRED PER ER/A 530827-14MA REV: ORIGINAL.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION ON CUSP WEBS BTW STA 522 TO 674 LT SIDE LOWER AND UPPER SURFACE CABIN PAX. LEVEL CORROSION 2 CUSP WEBS STA Y= 522 TO 598 AND STA Y= 598 TO STA Y=664 WERE REPLACED PER SRM 53-05 FIG 131 A-24 AND SRM 51-30-2 AND 51-30-5.

Part: SKIN — DAMAGED (RUDDER) · airframe 60,898 hrs · 47,411 cycles

DAMAGED METALIZED ON RUDDER SKIN RT AND LT SIDE (EHV). REPAIRED PER ERA 092613-14 MA, REV C.

Part: CUSP WEB — CORRODED (BS 739-742) · airframe 60,898 hrs · 47,411 cycles

CORROSION OUT OF LIMITS ON THE RT CUSP WEB BETWEEN BS 739 TO 742. DAMAGE AREA WAS REPAIRED.

Part: FORMER — CRACKED (RT WING) · airframe 60,898 hrs · 47,411 cycles

CRACKED FORMER RWS 290 AT FIXED LEADING EDGE INTERNAL STRUCTURE. REPAIRED IAW SRM 57-06B, PARA 7, FIG 18.

Part: SEAT TRACK — CORRODED (BS 855-997) · airframe 60,898 hrs · 47,411 cycles

OUT OF LIMITS CORROSION ON THE SEAT TRACK LBL 22 FROM BS 855 TO 856, BS 965 TO 966 AND BS 996 TO 997. THE DAMAGE AREAS WERE REPAIRED IAW SRM 53-05.

Part: LONGERON — CRACKED (BS 1437) · airframe 60,898 hrs · 47,411 cycles

CRACKED LONGERON 3R, BS 1437. REPAIRED IAW SRM 53-02, PARA 12.

Part: SEAT TRACK — CORRODED (BS 858-859) · airframe 60,898 hrs · 47,411 cycles

CORROSION ON LT SEAT TRACK LBL 54, BS 858 TO 859. REPAIRED IAW SRM 53-05, FIG 4A.

Part: FLOOR PANEL — CRACKED (NOT REPORTED) · airframe 60,898 hrs · 47,411 cycles

CRACKED FLOOR PANEL 1003F. THE FLOOR PANEL WAS REPAIRED.

Part: RIB — CRACKED (LT WING) · airframe 60,898 hrs · 47,411 cycles

CRACKED RIB AND ANGLE WS 217 TO 346 AT FIXED LEADING EDGE INTERNAL STRUCTURE , LT WING. THE RIB WAS REPLACED IAW SRM 51-30-2 AND SRM 51-30-5.

Part: COVER — TORN (FEEDER CABLE) · airframe 60,898 hrs · 47,411 cycles

TORN COVER TAPE ON AUXILIARY HYD PUMP POWER FEEDER WIRING CONNECTOR AT RH W/W. COVER TAPE ON AUX HYD PUMP FEEDER WIRING CONNECTOR WAS REPLACED PER ER/A 467688-14MA AD (LP# 0344059)

Part: FLOOR SUPPORT — CORRODED (BS 255) · airframe 60,898 hrs · 47,411 cycles

CORROSION ON FLOOR SUPPORT BS 255 LBL 33. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-30-5.

Part: RIB — CRACKED (LT WING) · airframe 60,898 hrs · 47,411 cycles

CRACKED RIB WS 300 TO 319 AT FIXED LEADING EDGE INTERNAL STRUCTURE, LT WING. THE RIB WAS REPLACED IAW SRM 51-30-2, SRM 51-30-5, AND DWG 9937588, REV G.

Part: ANGLE — CRACKED (EMERGENCY EXIT) · airframe 60,898 hrs · 47,411 cycles

CRACK CLIP ON STOP FITTING #1 AT FWD/LH OVERWING EMERGENCY EXIT DOOR. CLIP WAS REPLACED PER DC-9/MD80 DWG:9957735 REV:G AND SRM 51-30-5 ,51-30-2 (LP# 0344320)

Part: SEAT TRACK — CORRODED (BS 451-453) · airframe 60,898 hrs · 47,411 cycles

CORROSION OUT OF LIMITS ON THE SEAT TRACK LBL 22 FROM BS 451 TO 453 IN THE PAX CABIN. THE DAMAGED AREA WAS REPAIRED.

Part: CUSP WEB — CORRODED (BS 855) · airframe 60,898 hrs · 47,411 cycles

CORROSION OUT OF LIMITS ON CUSP WEB LT SIDE ON BS 855. REPAIRED IAW SRM 53-05 FIG. 131A-14.

Part: CHANNEL — CRACKED (FLOOR PANEL) · airframe 60,898 hrs · 47,411 cycles

CRACKED CHANNEL ON FLOOR PANEL NBR 313E, 465E, 389G 693E, 313A,1003A AND 256A AT CABIN FLOOR STRUCTURE. FLOOR PANELS 313E, 465E, 389G 693E, 313A, 1003A & 256A WERE REPAIRED PER DC9/MD80 SRM 53-05 PAR 145. (LP0343025)

Part: SEAT TRACK — CORRODED (BS 764-765) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION OUT OF LIMITS ON LH SEAT TRACK X 22 FROM STA Y=764 TO STA Y=765 AT PAX CABIN. (LEVEL CORROSION 2) DAMAGE SECTION WAS REPLACED PER DC9/MD80 SRM 51-30-1 AND 51-30-5. (LP0342845)

Part: SEAT TRACK — CORRODED (BS 794-496) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION OUT OF LIMITS ON LH SEAT TRACK X 22 FROM STA Y=794 TO STA Y=796 AT PAX CABIN. (LEVEL CORROSION 2) DAMAGE SECTION WAS REPLACED PER DC9/MD80 SRM 51-30-1 AND 51-30-5.

Part: BEARING — CORRODED (RUDDER YOKE) · airframe 60,898 hrs · 47,411 cycles

RUSTED RUDDER YOKE BEARING (EHV). DUE TO CORROSION LEVEL 2, BEARING WAS VERIFIED AND REPLACED.

Part: CUSP WEB — CORRODED (BS 560) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

SEVERAL CORROSION POINTS ON RH CUSP WEB DOUBLER REPAIR Y 560. LEVEL CORROSION 2.RH CUSP WEB Y=560 WAS REPAIRED PER SRM 53-05 FIG 131A.

Part: SEAT TRACK — CORRODED (BS 629-630) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION ON RH SEAT TRACK X=-54 BTW STA Y=-629-630 AT PAX CABIN IN REF NRC 00317. (LEVEL CORROSION 2) DAMAGE AREA WAS REPAIRED PER DC9/MD80 SRM 53-05 FIG 4A. (LP0342127)

Part: RIB — CRACKED (RT WING) · airframe 60,898 hrs · 47,411 cycles

CRACK ON RIB STA XRS=326 AT FIXED LEADING EDGE INTERNAL STRUCTURE , RH WING. RIB ON STA XRS=326 AT FIXED LEADING EDGE INTERNAL STRUCTURE , RH WING WAS REPLACED PER DC-9/MD-80 SRM 51-30-05, SRM 51-30-02, AND DWG 9937589 REV D. (AD)(LP0341549)

Part: SEAT TRACK — CORRODED (BS 531-532) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION ON RH SEAT TRACK X =-54 BTW Y=531-532 AT PAX CABIN IN REF NRC 00317. (LEVEL CORROSION 2) DAMAGE AREA WAS REPAIRED PER DC9/MD80 SRM 53-05 FIG 4A. (LP0342112)

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

SEVERAL CORROSION POINTS ON FLOOR SUPPORT X50 FROM Y 166 TO 182 AT FWD WET AREA. LEVEL CORROSION NR 2. FLOOR SUPPORT WAS REPLACED ON X=50 FROM Y=166 TO X=182 PER SRM 51-30-02.

Part: FLOORBEAM — CORRODED (BS 197) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

SEVERAL CORROSION POINTS ON FLOOR SUPPORT Y 197 AND FROM X16 TO 40 AT FWD WET AREA. (LEVEL CORROSION 2) FLOOR SUPPORT Y 197 AND FROM X16 TO 40 AT FWD WET AREA WAS REPLACED PER DC9/MD80 SRM 51-30-02.

Part: SEAT TRACK — CORRODED (BS 307) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION ON RH SEAT TRACK X=-54 STA Y=307 IN REF NRC 00317. (LEVEL CORROSION 2) DAMAGE AREA WAS REPAIRED PER DC9/MD80 SRM 53-05 FIG 4A. (LP0342099)

Part: FLOORBEAM — CORRODED (BS 200) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

SEVERAL CORROSION POINTS ON FLOOR SUPPORT Y 200 FROM X-5 TO X5 AT FWD WET AREA. LEVEL CORROSION 2. FLOOR SUPPORT Y 200 FROM X-5 TO X5 AT FWD WET AREA (W1) WAS REPLACED PER DC9/MD80 SRM 51-30-2. (LP0340778)

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION OUT LIMITS ON CUSP WEB BTW STA Y=730 TO Y=731 LT SIDE AT CABIN PAX. (LEVEL CORROSION 2) CUSP WEB WAS REPAIRED PER SRM 53-05 FIG 131A-9.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

SEVERAL CORROSION POINTS ON FLOOR SUPPORT Y 180 AND FROM X-11 TO -42 AT FWD WET AREA. LEVEL CORROSION NR 2. NEW FLOOR SUPPORT WAS REPLACED ON STA Y 180 AND FROM X-11 TO -42 PER SRM 51-30-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

SEVERAL CORROSION POINTS ON FLOOR SUPPORT Y 200 FROM X-45 TO -54 AT FWD WET AREA. (LEVEL CORROSION 2) FLOOR SUPPORT Y 200 FROM X-45 TO -54 AT FWD WET AREA WAS REPLACED PER SRM 51-30-02.

Part: CUSP WEB — CORRODED (BS 1010-1012) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION OUT OF LIMITS ON CUSP WEB BTW STA Y=1010 TO 1012 LH SIDE AT PAX CABIN, IN REF TO NRC S/N 00632.(LEVEL CORROSION 2) CUSP WEB WAS REPAIRED PER DC9/MD80 SRM 53-05 FIG 131A.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

SEVERAL CORROSION POINTS ON FLOOR SUPPORT X -44 FROM Y 161 TO 198 AT FWD WET AREA. LEVEL CORROSION NR 2. FLOOR SUPPORT WAS REPLACED ON X-44 FROM Y 161 TO 198 PER SRM 51-30-02.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

OUT OF LIMITS CORROSION ON RT SEAT TRACK X=-44 FROM STA Y=200 TO 247 PAX CABIN. (LEVEL CORROSION 2) DAMAGE SECTION WAS REPLACED PER SRM 53-05 FIG 4.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 60,898 hrs · 47,411 cycles

CRACK ON LONG NR 4R STA Y=1437 AT AFT ACCESSORY COMPT. REPAIRED PER SRM 53-02 PAR 12.

Part: RIB — CRACKED (LT WING) · airframe 60,898 hrs · 47,411 cycles

CRACK ON RIB FORMER STA X05=408 AT FIXED LEADING EDGE INTERNAL STRUCTURE, LT WING. RIB FORMER STA X05=408 AT FIXED LEADING EDGE INTERNAL STRUCTURE , LT WING WAS REPAIRED PER SRM 57-06B FIG 23, SRM 51-30-2, SRM 51-30-5.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

SEVERAL CORROSION POINTS ON FLOOR SUPPORT Y 200 FROM X-11 TO -42 AT FWD WET AREA. LEVEL CORROSION NR 2. FLOOR SUPPORT WAS REPLACED ON STA Y 200 FROM X-11 TO -42 PER SRM 51-30-02.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION ON RT CUSP WEB STA Y= 479 BTW X=-56 TO X=-60 AT PAX CABIN. LEVEL CORROSION 2: CUSP WEB WAS REPAIRED PER SRM 53-05 FIG 131A-13.

Part: CUSP WEB — CORRODED (BS 405) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION ON RH CUSP WEB STA Y=405 BTW X=-54 TO X=-60 AT PAXCABIN. LEVEL CORROSION 2: CUSP WEB WAS REPAIRED PER DC9/MD80 SRM 53-05 FIG 131A-13. (LP0339984)

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

SEVERAL CORROSION POINTS ON FLOOR SUPPORT FROM Y 160 TO 200 AND X-53 AT FWD WET AREA. (LEVEL CORROSION 2) FLOOR SUPPORT FROM Y 160 TO Y 200 AND X-53 AT FWD WET AREA WAS REPLACED PER SRM 51-30-02.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,898 hrs · 47,411 cycles

CORROSION ON RT CUSP WEB STA Y= 441 BTW X=-56 TO X=-60 AT PAX CABIN. CUSP WEB WAS REPAIRED PER SRM 53-05 FIG 131A-1.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 60,898 hrs · 47,411 cycles

CRACKED RT CUSP WEB STA Y=218 X=-45. DAMAGE AREA WAS REPAIRED PER SRM 53-05 FIG 131A-19 HFEC INSPECTION WAS ACCOMPLISHED ON RT CUSP WEB STA Y=218 X=-45, NO CRACKS WERE FOUND AFTER TRIM OUT.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 60,898 hrs · 47,411 cycles

CORROSION ON PLUGS (2EA) AT LT SEAT TRACK X22 BTW STA Y= 545 AND STA Y= 550 AND BTW STA Y= 700 AND STA Y= 705AT PAX CABIN. PLUGS WERE REPLACED PER SRM 53-05 FIG 4A.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 60,898 hrs · 47,411 cycles

CORROSION ON PLUG AT RT SEAT TRACK X -22 BTW STA Y= 1161 AND STA Y= 1166 AT PAX CABIN. PLUG WAS REPLACED PER SRM 53-05 FIG 4A.

Part: BEAM — CRACKED (PAX DOOR) · airframe 60,898 hrs · 47,411 cycles

CRACKED BEAM 2 (AFT EDGE) AT FWD PASSENGER DOOR (L1). CRACKED BEAM 2 (AFT EDGE) WAS REPAIRED PER SRM 52-05 PAR 77 FIG 99.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 60,898 hrs · 47,411 cycles

CRACK ON CUSP WEB BTW STA 788 TO 807 LT SIDE CABIN PAX. DAMAGE AREA WAS REPAIRED PER SRM 53-05 FIG 131A-13.

Part: PAN — CRACKED (BS 927) · airframe 60,898 hrs · 47,411 cycles

INITIAL INSPECTION : CRACKED LH RING PAN STA Y= 927 AND 946 AT UPPER FWD CORNER PAX CABIN. DAMAGE AREA WAS REPAIRED PER DC9/MD80 SRM 53-05 FIG. 122. HFEC INSPECTION WAS ACCOMPLISHED ON LH RING PAN STA. Y= 927 AND Y=946 AT UPPER FWD CORNER, NO CRACKS WERE FOUND AFTER TRIM OUT. (LP0336335)

Part: PAN — CRACKED (BS 1041) · airframe 60,898 hrs · 47,411 cycles

INITIAL INSPECTION : CRACKED LH RING PAN STA Y= 1041 AND 1079 AT LOWER FWD CORNER PAXCABIN. DAMAGE AREA WAS REPAIRED PER DC9/MD80 SRM 53-05 FIG. 122. HFEC INSPECTION WAS ACCOMPLISHED ON LH RING PAN STA Y= 1041 AND Y=1079 AT LOWER FWD CORNER, NO CRACKS WERE FOUND AFTER TRIM OUT. (LP0336314)

Part: PAN — CRACKED (BS 1212) · airframe 60,898 hrs · 47,411 cycles

INITIAL INSPECTION: CRAKED LH AFT UPPER RING PAN STA Y=1212 AND 1250 AT PAX CABIN. DAMAGE AREA WAS REPAIRED PER DC9/MD80 SRM 53-05 FIG. 122. HFEC INSPECTION WAS ACCOMPLISHED ON LH AFT UPPER RING PAN STA Y=1212 AND 1250 AT PAX CABIN, CRACK OF 0.1875" WAS CONFIRMED AND DELIMITED PER DC-MD NDTSPM 06-10-01.001. HFEC INSPECTION WAS ACCOMPLISHED ON LH AFT UPPER RING PAN ON STA Y=1212 AND 1250 AT PAX CABIN. NO CRACKS WERE FOUND AFTER TRIM OUT. (LP0336327)

Part: LONGERON — CRACKED (FUSELAGE) · airframe 60,898 hrs · 47,411 cycles

CRACK ON LONG NR 6RH STA Y=1437 AT AFT ACCESSORY COMPT. LONG NR 6R STA Y=1437 AT AFT ACCESSORY COMPT WAS REPAIRED PER SRM 53-02 PAR 12.

Part: PAN — CRACKED (BS 905-1231) · airframe 60,898 hrs · 47,411 cycles

INITIAL INSPECTION : CRACKED RH RING PAN STA Y= 905 AND 1231 LOWER AFT CORNER PAX CABIN. AREA WAS REPAIRED PER DC9/MD80 SRM 53-05 FIG. 122. HFEC INSPECTION WAS ACCOMPLISHED ON 1231 LOWER AFT CORNER AND TWO CRACKS WERE FOUND OF 0.200" AND 0.120". HFEC INSPECTION WAS ACCOPMPLISHED ALONG THE TRIM LINES ON RH RING PAN STA Y= 905 AND STA Y = 1231. NO CRACKS INDICATIONS WERE FOUND. (LP0334884)

Part: PAN — CRACKED (BS 807) · airframe 60,898 hrs · 47,411 cycles

INITIAL INSPECTION : CRACKED RH RING PAN STA Y= 807, 886, 927 AND 946 AT UPPER FWD CORNER PAX CABIN. SUMMARY OF NRC 00301: DAMAGE AREA WAS REPAIRED PER DC9/MD80 SRM 53-05 FIG. 122 (ET)(HFEC) WAS ACCOMPLISHED ON RH RING PAN STA Y=807, 886, 927 AND 946 AT UPPER FWD CORNER PAX CABIN AND NO CRACK INDICATIONS WERE FOUND AFTER TRIMMED. (LP0334889)

Part: PAN — CRACKED (BS 1231) · airframe 60,898 hrs · 47,411 cycles

INITIAL INSPECTION : CRACKED RH RING PAN STA Y= 1231 AND 1250 AFT UPPER CORNER PAX CABIN. DAMAGE AREA WAS REPAIRED PER DC9/MD80 SRM 53-05 FIG. 122 (ET)(HFEC) WAS ACCOMPLISHED ON RH RING PAN STA Y =1231 AND 1250 AFT UPPER CORNER PAX CABIN AND NO CRACK INDICATIONS WERE FOUND AFTER TRIMMED. (LP0334967)

Part: PAN — CRACKED (BS 984-1041) · airframe 60,898 hrs · 47,411 cycles

INITIAL INSPECTION : CRACKED RH RING PAN STA Y= 984 AND 1041 AT LOWER FWD CORNER PAX CABIN. DAMAGE AREA WAS REPAIRED PER DC9/MD80 SRM 53-05 FIG. 122. (ET)(HFEC) WAS ACCOMPLISHED ON RH RING PAN STA Y=984 AND 1041 AT LOWER FWD CORNER PAX CABIN AND NO CRACK INDICATIONS WERE FOUND AFTER TRIMMED. (LP0334901)

Part: SKIN — DAMAGED (RT WING) · airframe 60,898 hrs · 47,411 cycles

DURING NDT INSPECTION A DISCREPANT AREA WAS FOUND (SEVEN DIFFERENT FASTENERS OF PSE) ON LOWER SKIN BTW XRS= 163 TO 168 REAR SPAR AT RH WING. OF SERIAL NUMBER NRC.00126 AREA ON LOWER SKIN BTW XRS=163 TO 168 REAR SPAR AT RH WING. WAS FOUND REPAIRED WITH ER/A 562419-14AD REV. ORIGINAL. (LP0331154)

Part: SKIN — DAMAGED (LT WING) · airframe 60,898 hrs · 47,411 cycles

DURING NDT INSPECTION A DISCREPANT AREA WAS FOUND (SEVEN DIFFERENT FASTENERS OF PSE) ON LOWER SKIN BTW XRS= 163 TO 168 REAR SPAR AT LH WING. OF SERIAL NUMBER NRC.00125 AREA ON LOWER SKIN BTW XRS=163 TO 168 REAR SPAR AT LH WING. WAS FOUND REPAIRED WITH ER/A 562419-14AD REV. ORIGINAL. (LP0331163)

Part: B-NUT — LEAKING (HYD SYSTEM) · airframe 59,017 hrs · 45,949 cycles

AFTER STARTING THE APU AND OPENING THE BLEED AIR SUPPLY SWITCH, THE CABIN FILLED WITH MIST AND HAZE. THE DUCT TEMPERATURE WAS HIGH. MAINTENANCE TROUBLESHOT IAW WORK CARD 2120-2367 AND FOUND A HYDRAULIC LEAK AT THE LEFT REVERSER CONTROL VALVE. A B-NUT WAS SECURED AND LEAK CHECKED GOOD. AN ALTERNATE DUCT BURNOUT WAS PERFORMED PER WORK CARD 4950-2215. THE COALESCER BAGS WERE REPLACED. (LP9692817)

Part: BATTERY PACK — DISLODGED (EMERGENCY LIGHTS) · airframe 58,981 hrs · 45,923 cycles

EMERGENCY EXIT CELING LIGHTS ROW 1-10 INOPERATIVE. FOUND BATTERIES IN POWER PACK B5-100 DISLODGED. SECURED. CHECKED OK.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 58,981 hrs · 45,923 cycles

FWD OVERWING EXIT LIGHTS INOPERATIVE. FOUND ONE BATTERY NOT HOLDING CHARGE. REPLACED THE BATTERY AND CHECKED NORMAL.

Part: WIRE — BROKEN (CABIN) · airframe 58,890 hrs · 45,850 cycles

DURING THE BOARDING PROCESS, A PASSENGER REPORTED A SMOKE SMELL IN THE AFT CABIN. THE AFT LAVATORY SMOKE DETECTOR SOUNDED INTERMITTENTLY. THE PASSENGERS WERE DEPLANED. THE NO GO ODI ATA 2172 SMOKE FUME TROUBLESHOOTING PROCEDURE WAS ACCOMPLISHED. MAINTENANCE TROUBLESHOT PER WORK CARD 2120-2367 PNEUMATIC DISTRIBUTION CABIN/SMOKE/ODOR WORK CARD. THE ATTENDANT CALL LIGHT IN THE AFT LEFT LAVATORY WAS FOUND INOPERATIVE WITH A BROKEN WIRE THAT WAS ARCING AT THE TERMINAL. THE WIRE WAS REPAIRED PER WSPM CHAPTER 20. THE CALL LIGHT CHECKS OK. WORK CARD 2120-2367 WAS COMPLETED AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: FRAME — CRACKED (FUSELAGE) · airframe 58,637 hrs · 45,652 cycles

TAIL INTERIOR, CANTED FRAME WEB HAS 4" LONG CRACK, CBS 1485, APPROXIMATELY 8 O`CLOCK POSITION. REPAIRED IAW PRI 550919-14, REV 0 AND ERA 550919-14, REV ORIGINAL.

Part: LONGERON — CORRODED (FUSELAGE) · corrosion level 2 · airframe 58,635 hrs · 45,651 cycles

AFT CARGO BILGE-L28R CORRODED AT STA 1287 FWD AND AFT SIDES. REPAIRED LONGERON IAW SRM 53-02, PAR 12, FIG 18.

Part: FRAME — CRACKED (FUSELAGE) · airframe 58,635 hrs · 45,651 cycles

TAIL INTERIOR, CBS FRAME WEB 1463-WEB AFT SIDE IS CRACKED AT RIVET APPROXIMATELY 10 O`CLOCK POSITION, 11" INBD OF L10L END FITTING. REPAIRED IAW SRM 53-03D, FIG 38B.

Part: SPACER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 58,635 hrs · 45,651 cycles

AFT CARGO BILGE, DOOR SILL FILLER PLATE HAS CORROSION BS 1155-1212. R & R SPACER IAW ER/A 499523-14MA.

Part: ANGLE — CRACKED (RT MLG DOOR) · airframe 58,635 hrs · 45,651 cycles

RT MLG DOOR- INBD EXTERNAL ANGLE CRACKED AT FWD END, AFT SIDE OF ACTUATOR FITTING. R & R MLG DOOR IAW AMM 32-12-01.

Part: SUPPORT FITTING — CRACKED (LT WING) · airframe 58,635 hrs · 45,651 cycles

LEFT WING GROUND SPOILER ACTUATOR SUPPORT FITTING CRACKED AT FWD INBD CORNER. INSTALLED THE SUPPORT DRIVE FITTING IAW DRAWING SR09570010 REV H.

Part: TAB — CRACKED (RT ELEVATOR) · airframe 58,635 hrs · 45,651 cycles

RIGHT ELEVATOR CONTROL TAB HAS CRACK ON LOWER L/E, SECOND FROM OTBD HINGE. REMOVED AND INSTALLED RT ELEVATOR CONTROL TAB AMDS 2730-4634.

Part: DOOR FRAME — CORRODED (CARGO BAY) · corrosion level 2 · airframe 58,635 hrs · 45,651 cycles

AFT CARGO BAY LOWER DOOR FRAME HAD EVIDENCE OF CORROSION IN FWD CORNER. BLEND CORROSION AND CHECKED LIMITS IAW SRM 53-01 P5-8 FIG. 1. CORROSION BEYOND LIMITS. REPLACED THE BRACKET IAW DWG 5936469.

Part: SKIN — BUCKLED (BS 1183) · airframe 57,716 hrs · 44,978 cycles

DURING SERVICE CHECK, FOUND BUCKLED SKIN AT BS 1183, ON STR 27 AND 28L. REPAIRED IAW ER/A 546578-14.

Part: SKIN — BUCKLED (BS 1183) · airframe 57,716 hrs · 44,978 cycles

BUCKLED SKIN AT BS 1183 ON STR 27 AND 28 LT. INSTALLED DOUBLER AND SHIMS IAW SRM 53-04-3, FIG 4, SH 3, REF ER/A 546578-14, REV ORIGINAL.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 58,948 hrs · 45,895 cycles

ER/A 546578-14 SECTION I WAS ACCOMPLISHED IN MSP 01MAY16 TO ADDRESS CORROSION DAMAGE TO LT AFT FUSELAGE SKIN AND STRINGERS AT FS 1200, S-27L TO S-29L.

Part: INLET — CRACKED (RAM AIR) · airframe 57,716 hrs · 44,978 cycles

DURING SERVICE CHECK, FOUND RT SIDE OF RAM AIR INLET CRACKED IN 2 PLACES. REMOVED CRACKED RAM AIR, Y-DUCT IAW AMM 21-20-17-201. INSTALLED SERVICEABLE Y DUCT IAW AMM 21-20-17 LEAK CHECK GOOD. OK FOR SERVICE.

Part: ACCESS PANEL — CRACKED (LT WING) · airframe 57,474 hrs · 44,789 cycles

APARENT FUEL LEAK OBSERVED AROUND LT WING FLAP HINGE FAIRING, 3RD FROM INBD. REMOVED LT WING NR 3 FAIRING, FOUND PANEL CRACKED AT XRS 267. R & R PANEL IAW AMM. REINSTALLED FAIRING, LEAK CHECK OK.

Part: CONNECTOR — DISCONNECTED (EMERGENCY LIGHTB) · airframe 57,025 hrs · 44,492 cycles

MAINTENANCE FOUND SEAT ROW 3C EMERGENCY EXIT LIGHTING INOPERATIVE. CONNECTOR AT SEAT 3C WAS FOUND DISCONNECTED AND RESECURED.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 56,896 hrs · 44,400 cycles

MAINTENANCE FOUND EMERGENCY EXIT LIGHTS INOPERATIVE STARTING AT ROW 31 INCLUDING L2 DOOR AND AFT STAIRWAY. POWER SUPPLY B5-105 WAS REPLACED AND THE LIGHTS CHECKED OK.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 55,935 hrs · 43,710 cycles

MAINTENANCE FOUND AFT OVERWING UPPER SIDEWALL EXIT LIGHTS INOPERATIVE. POWER SUPPLY BATTERIES WERE REPLACED IAW MM 33-50.

Part: SEAL — MISSING (OUTFLOW VALVE) · airframe 55,503 hrs · 43,411 cycles

FLIGHT DIVERTED DUE TO LOSS OF CABIN PRESSURIZATION. FLOW LIGHT ILLUMINATED ON OVERHEAD PANEL AND CREW INITIATED AN EMERGENCY DESCENT. PASSENGER OXYGEN MASKS DID DEPLOY. MAINTENANCE FOUND THE RT PACK DISCHARGE BOOT SEPARATED FROM THE DUCT AND THE LT PACK FUNCTIONED WEAKLY. ACFT WAS MAINTENANCE FERRIED WHERE MAINTENANCE REPLACED THE BOOT ON THE NR 2 ACM DISCHARGE DUCT. ALSO REPLACED THE USED O2 GENERATORS AND A MISSING SEAL ON THE OUTFLOW VALVE.

Part: RELEASE CABLE — WORN (TAILCONE) · airframe 55,599 hrs · 43,474 cycles

MAINTENANCE DISCOVERED THAT THE LT RELEASE LATCH CABLE FOR THE TAILCONE WAS WORN OUT OF ALLOWABLE LIMITS. THE CABLE WAS REPLACED AND THE SYSTEM WAS RIGGED TO SPECIFICATIONS. THE FUNCTIONAL CHECK WAS COMPLETED SATISFACTORILY.

Part: SLIDE — MISINSTALLED (TAILCONE) · airframe 55,473 hrs · 43,390 cycles

INSPECTION DISCOVERED THAT THE EMERGENCY ESCAPE SLIDE IN THE TAILCONE WAS NO LONGER IN AN ACCEPTABLE CONFIGURATION. MISRIGGED, IMPROPERLY INSTALLED STRAP FOR THE SLIDE COVER WOULD PREVENT PROPER DEPLOYMENT OF THE ESCAPE SYSTEM AND IS NOT IN COMPLIANCE WITH 14 CFR PART 121.703. THE TAILCONE SLIDE COVER LANYARD WAS REINSTALLED CORRECTLY AND THE RII WAS COMPLETED SATISFACTORILY.

Part: SPAR CAP — DAMAGED (HORIZONTAL STAB) · airframe 55,425 hrs · 43,356 cycles

HORIZONTAL STABILIZER RT REAR CAP SPLICE DAMAGED. SPAR CAP REPAIRED.

Part: SPAR CAP — CRACKED (HORIZONTAL STAB) · airframe 55,425 hrs · 43,356 cycles

UPPER REAR SPAR CAP AFT BARREL NUT HOLE HAS APPROXIMATELY 1.5" CRACK FROM AFT SIDE OF HOLE. REPAIRED IAW AMDS CARD 5510-01074-16.

Part: LAMP — INOPERATIVE · airframe 54,704 hrs · 42,864 cycles

DURING LINE CHECK, MAINTENANCE FOUND SEVERAL EMERGENCY LIGHTS ON THE CAT WALK TO BE INOPERATIVE. MAINTENANCE RELAMPED 9 LIGHTS AND THE OPS CHECK WAS GOOD.

Part: ANGLE — CORRODED (LOWER DOOR FRAME) · corrosion level 2 · airframe 53,402 hrs · 41,919 cycles

OTBD FACE OF ZEE ANGLE ON CENTER CARGO LOWER DOOR FRAME HAS CORROSION AROUND RIVNUTS FROM BS 640-687. BLENDED AND TRIMMED OUT CORRODED SECTIONS OF THE ANGLE. REPAIRED IAW SRM 53-05, FIG 123A, OPTION 2.

Part: SPACER — CORRODED (CARGO DOOR FRAME) · corrosion level 2 · airframe 53,389 hrs · 41,908 cycles

CORROSION WAS FOUND ON THE OTBD SURFACE OF SPACER FOR A REPAIR AT THE AFT CARGO LOWER DOOR FRAME FROM BS 1175-1200. R & R DAMAGED SPACER & NUTSTRIPS IAW SRM 51-30-5, PAR 8 & SRM 53-05, PAR 140C.

Part: SKIN — BENT (PAX DOOR) · airframe 60,898 hrs · 47,411 cycles

FWD PASSENGER DOOR SKIN, LOWER-FWD REPAIR BENT. ACCOMPLISHED PERMANENT REPAIR IAW MD-80/DC-9 SRM 52-05D FIG 37. PAR 39 PAGE 209-211. (LP1561971)

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 53,389 hrs · 41,908 cycles

DURING CHECK, MAINTENANCE FOUND THE 2 EMERGENCY LIGHTS IN THE CEILING ABOVE THE VENTRAL EGRESS RAMP WERE INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACK AT B5-27 AND THE LIGHT WERE OPERATIONAL.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHTS) · airframe 53,389 hrs · 41,908 cycles

DURING CHECK, MAINTENANCE FOUND SEVERAL LIGHTS INOPERATIVE ON THE VENTRAL EGRESS RAMP. MAINTENANCE REPLACED THE LAMPS THE AREA AND THE LIGHTS RETURNED TO AN OPERATIONAL STATE.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 52,798 hrs · 41,487 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTS AT SEATS 32CB AND 32ED IN THE CABIN WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES. OPS CHECKED GOOD.

Part: FITTING — OUT OF ADJUST (GIRT BAR) · airframe 52,778 hrs · 41,471 cycles

CREW FOUND THAT THE R1 DOOR GIRT BAR WOULD NOT STAY IN THE FITTINGS. MAINTENANCE ADJUSTED THE THRESHOLD THAT WAS IN THE WAY OF THE GIRT BAR.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 51,447 hrs · 40,566 cycles

EMERGENCY LIGHTS OVER CATWALK INOPERATIVE. REPLACED BATTERY PACK. OPS CHECKED OK.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 51,272 hrs · 40,437 cycles

DURING LINE CHECK, THE OVERHEAD EMERGENCY LIGHTS WERE FOUND TO BE INOPERATIVE AT ROWS 10-13. BATTERIES REPLACED AND OPS CHECKED GOOD IAW AMM 33-50.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 51,116 hrs · 40,308 cycles

DURING LINE CHECK, THE COCKPIT EMERGENCY EXIT LIGHTS WERE FOUND TO BE INOPERATIVE. MX REPLACED POWER SUPPLY B5-23 AND OPS CHECKED NORMAL.

Part: SKIN — DAMAGED (VERTICAL STAB) · airframe 49,629 hrs · 39,257 cycles

SKIN DAMAGED VERTICAL STAB, APPROX ZFS=52-62. ACCOMPLISHED REPAIR IAW ER/A 511535-14AD, REV O.

Part: SPAR — DAMAGED (VERTICAL STAB) · airframe 49,629 hrs · 39,257 cycles

LT VERTICAL STAB FRONT SPAR DAMAGED. ACCOMPLISHED SECTION 1 OF ERA 511541-14AD, REV O.

Part: CAM — FAILED (TAILCONE RELEASE) · airframe 49,601 hrs · 39,233 cycles

TAILCONE RELEASE MECHANISM CAM FAILED. R & R CAM ASSY IAW AMM.

Part: SKIN — DAMAGED (LT ELEVATOR) · airframe 49,608 hrs · 39,239 cycles

LEFT ELEVATOR OTBD T/E TIP, LIGHTNING STRIKE. REPAIRED IAW ERA 511552-14, REV O.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 48,808 hrs · 38,681 cycles

DURING SERVICE CHECK, MX FOUND CEILING EMERGENCY EXIT LIGHT INOPERATIVE AT ROW 1. R & R BATTERY PACK IN OVERHEAD BIN 3R. OPS CHECKED NORMAL.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 48,587 hrs · 38,521 cycles

DURING SERVICE CHECK, MAINTENANCE FOUND EMERGENCY EXIT SIGNS ABOVE OVERWING EXIT INOPERATIVE AFT. MAINTENANCE REMOVED AND REPLACED EMERGENCY POWER PACK BATTERIES PER AMM. OPS CHECKED GOOD. OK FOR SERVICE.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

SDR. CABIN FLOOR BEAM AT STA 1309 RBL 00 UPPER CAP AFT, FLANGE, LOWER SURFACE CORRODED UNDER NUT PLATE. FABRICATED ANGLE REPAIR PER SRM 53-05 FIG 20A PAGE 100( 2EA AT RBL 22 AND LBL20 ). FABRICATED REPAIR FILLER PER SRM MD80 53-05 FIG 20A (2EA). INSTALLED ALL PARTS AT MAIN CABIN STA 1309 RBL 22 AND LBL 20 PER SRM MD80 SRM 53-05 FIG 204. AT SAA/SAT DURING HMV ON N/R 185690 W/O 88406830001.

Part: FRAME — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT CARGO COMPARTMENT BILGE AREA FROM STR 29R AND 29L FRAME HAS EXFOLIATING CORROSION ON AFT SIDE AT STA 1309. FABRICATED REPAIR ANGLE PER SRM MD80 53-03 PG 4J, 53-04 PG 4C53-03 PG 4J. FABRICATED REPAIR PLATE PER SRM MD80 51-10-3 PG 14 AND 21. INSTALLED ALL REPAIR PARTS (4EA) ANGLES AND (1EA) REPAIR PLATE AFT CARGO COMPARTMENT STA 1309 BETWEEN S28R AND S28L IAW SRM MD80 53-03 FIG 2A. AT SAA/SATB DURING HMV ON N/R 200103.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT CARGO DOOR INTERIOR CABIN CUSP WEB EVIDENCE OF CORROSION AT STATION 1193- 1211 RT. COMPLIED WITH ERA 495295-14 REV ORIGINAL. AT SAA/SAT DURING HMV ON N/R 183751.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

MAIN CABIN RT FS 670 CUSP WEB HAS CORROSION. FABRICATED REPAIR DOUBLER AND SHIM (FILLER). ACCOMPLISHED ERA 495295-14 REV ORIGINAL. AT SAA/SAT DURING HMV ON N/R 189847.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT CARGO DOOR INTERIOR CABIN CUSP WEB EVIDENCE OF CORROSION AT STATION 1174-1183. FABRICATED REPAIR PARTS (1EA DOUBLER AND 1EA FILLER) WITH 7075-T6 .025 PER ERA 398191-14MA. INSTALLED REPAIR PARTS (1EA DOUBLER AND 1EA FILLER ) AT STA 1183 TO STA 1188 PER ERA 495295-14 REV ORIGINAL. AT SAA/SAT DURING HMV ON N/R 203174.

Part: INTERCOSTAL — DAMAGED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT CARGO COMPARTMENT RT SIDE BETWEEN STA 1231 AND 1250 AT STRINGER 29R INTERCOSTAL HAS ENORMOUS TOOLING MARKS. HEAT TREATED PARTS IAW TRAVELER 88379430001 AND 88379420001. RECEIVED PRI 494615-14 REV 0 AND REV 1. ACCOMPLISHED PRI 494615-14 REV 0 AND REV 1. AT SAA/SATB DURING HMV ON N/R 203129.

Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT LAV FLOOR LT SIDE STA 1338 FROM LBL 28 TO LBL 25 EVIDENCE OF CORROSION. LOCATED AND DRILLED NEW EXTRUSION AT AFT LAV FLOOR STA 1338 FROM RBL 57 TO LBL 57 IAW MD 80 SRM 51-10-4 PG 8. INSTALLED NEW ANGLE STA 1338 AFT LAV FLOOR PERMD 80V SRM 61-30-2 PG 3 AND 51-30-5 PG 1. AT SAA/SAT DURING HMV ON N/R 184780 W/O 88402180001.

Part: FRAME — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT CARGO COMPARTMENT AT STA 1117 IN BILGE AREA FRAME IS EXFOILATED. FABRICATED REPLACEMENT CORD P/N SAA3936445-1 ON FAB TRAVELER 88379510001. INSTALLED NEW CORD AT AFT CARGO COMP STA 1117 IAW MD80 SRM 51-30-2 FIG 1 ATB SAA/SAT DURING HMV ON N/R 2000048.

Part: SKIN — DENTED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

TWO DENTS ON FUSELAGE SKIN EXTERIOR SURFRACE AT STA 245 AND STA 250 BETWEEN LONGERON 17L AND 18L. FABRICATED REPAIR FILLER AND DOUBLER IAW SRM DC9/MD80 53-04-5 PG 5. INSTALLED ALL REAIR PARTS IAW SRMMDC9/MD80 53-04-5 FIG 5. AT SAA/SAT DURING HMV ON N/R 172382.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

CRACK ON SHEAR TIE AT FUSELAGE SKIN AND FRAME STA 1429 BETWEEN LONGERON 1 AND LONGERON 2L. FABRICATED SHEAR TIE IAW DWG 99563016. INSTALLED SHEAR TIE AT FUSELAGE SKIN AND FRAME STA 1429 BETWEEN LONGERON 1 AND 2L IAW MD 80 SRM 51-30-5 PG 12.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT CARGO COMPARTMENT STRINGER 29L BETWEEN STA 1322/1338 END OF STRINGER IS EXFIOLIATED. INSTALLED NEW CLIP FITTING AND NEW SECTION STRINGER STA 1315 TO 1338 PER MD80 SRM 53-30-5 PAR7 AND 51-30-2 PAR 1. MACHINED LONGER O/B SPLICE FITTING STR 29L STA 1315 REF SRM 53-05. INSTALLED MACHINED SPLICE AT FS 1315 LONG 29L IAW MD80 SRM 53-02 FIG 18 IN AFR BAY. AT SAA/SAT DURING HMV ON N/R 203015.

Part: STOP FITTING — CRACKED (CARGO DOOR) · airframe 46,070 hrs · 36,764 cycles

MID CARGO DOOR FWD UPPER STOP FITTING CRACKED. C/W AT SAA/SAT DURING HMV ON N/R 185714 W/O 88407060001.

Part: SUPPORT FITTING — GOUGED (LT MLG) · airframe 46,070 hrs · 36,764 cycles

LT O/B GEAR SUPPORT FITTING HAS GOUGE ON FACE. MACHINED COUNTERBORE TO REMOVE DAMAGE. LUG THICKNESS BEFORE MACHINING 1.220. AFTER MACHINING 1.190 MATERIAL REMOVED .030 OUT TO 2.130 DIA WITH .093 RADIUS PER DRG 5935812. RECEIVED NEW FABRICATED WASHER AS PER ERA 494628-14 REV 0. COMPLIED WITH PRI 494628-14 REV 0 AND ERA 494628-14AD REV A. AT SAA/SAT DURING HMV ON N/R 203207.

Part: SKIN — GOUGED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

2EA GOUGES ON FUSELAE SKIN EXTERIOR SURFACE BETWEEN STA 246 AND 252 AND LONGERON 12L AND 19L. C/W AT SAA/SAT DURING HMV ON N/R 172380 W/O 88392680001.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT ACCESSORY COMPARTMENT SHEAR TIE CLIP CRACKED STA 1380 BETWEEN LONGERON 13 AND 14R. FABRICATED REPLACEMENT SECTION OF FORMER AND 2EA ANGLE REPAIR SPLICES IAW MD80 SRM 53-03 FIG 3. INSTALLED REPLACEMENT SECTION OF FORMER AND 2EA REPAIR SPLICES IAW MD80 SRM 53-03 FIG 3. AT SAA/SAT DURING HMV ON N/R 203268.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

CORROSION FOUND ON STRINGER 27L END BELOW FITTING CHANNEL STA 1322 - 1338 AFTER FITTING REMOVED. C/W AT SAA/SAT DURING HMV ON N/R 185739 W/O 88407280001.

Part: SKIN — DENTED (CARGO DOOR) · airframe 46,070 hrs · 36,764 cycles

AFT CARGO DOOR EXTERNAL SKIN AT MID AFT EDGE HAVE 08EA DENTS ON THE SAME AREA. C/W AT SAA/SAT DURING HMV ON N/R 200147 W/O 88396600001.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT CARGO COMPARTMENT BETWEEN STA 1322 -1338 STRINGER 27L HAS CORROSION IN CHANNEL AND END OF STRINGER. C/W AT SAA/SATDURING HMV ON N/R 203017 W/O 88398760001.

Part: SKIN — DENTED (CARGO DOOR) · airframe 46,070 hrs · 36,764 cycles

AFT CARGO DOOR EXTERNAL SKIN FWD MID EDGE SEVERAL DENTS ON THE SAME AREA. C/W AT SAA/SAT DURING HMV ON N/R 200115 W/O 88396550001.

Part: PLATE — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

CRACK ON MAIN CABIN RT WINDOW PLATE STA 845. INSATLLED REPAIR PARTS PER DC9 / MD80 SRM 53-05 FIG 122.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

FWD CABIN FLOOR SUPPORT BEAM STA 200 TO 148 LBL 8 CORROSION. INSTALLED FLOOR SUPPORT BEAM IAW MD 80 51-30-1. PG11

Part: STRINGER — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT CARGO STA 1322/1338 STR 24L CORROSION. INSTALLED END FITTING PER MD80 SRM 53-02 FIG 16 AND SRM 51-30 -5 PG 1-3.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT CARGO COMPARTMENT STA 1155 AT STRINGER 29L FLOOR SUPPORT STRUCTURE NON FWD EDGE EXFOLIATED. REMOVED AND REPLACED FLOOR SUPPORT STRUCTURE IAW SRM 51-30-05 PAGE 12. C/W AT SAA/SAT DURING HMV ON N/R 185741 W/O 88407300001.

Part: FRAME — GOUGED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT ACCESSORY COMPARTMENT FRAME STRUCTURE IS GOUGED AT STA 1401 AND LONGERON 21R. C/W AT SAA/SAT DURING HMV ON N/R 230196 W/O 88405010001.

Part: MOUNT — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

CRACK LT CABIN WINDOW MOUNT PLATE 1235. INSTALLED ANGLE REPAIR AND SHIM PER DC 9 / MD80 SRM 51-30-02 PG 1 AND 51-30-5 PG 1.

Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT CARGO LT STA 1287 S25 HAS EXFOLIATING CORROSION. INSTALLED SPLICE IAW SRM MD80 53-02 FIG 16 PG 43 AND SRM MD80 51-30-5 PG 1-3.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT CARGO COMPARTMENT LT SIDE BETWEEN STA 1287 AND 1309 STR 24 HAS EXFOILATING CORROSION. C/W AT SAA/SAT DURING HMV ON N/R 200212 W/O 88397230001.

Part: MOUNT — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

CRACK ON MAIN CABIN RT FUSE WINDOW MOUNT PLATE STA 1060. INSTALLED REPAIR PARTS PER DC9 /MD80 SRM 53-05 FIG 122 REF STEP 1.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT CARGO COMPT STA 1322 /1338 STR 24L CORRODED AROUND FAST AND CHANNEL. INSTALLED END FITTING PER SRM MD80 53-02 FIG 16 AND 51-30 -5 PG 1-3.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT CARGO COMPARTMENT BETWEEN STA 1322 - 1338 STRINGER 30 HAS EXFOILIATING CORROSION IN CHANNEL. C/W AT SAA/SAT ON N/R 203019 W/O 88398780001.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT CARGO DOOR INTERIOR CABIN CUSP WEB EVIDENCE OF CORROSION STA 1155-1174 RBL 58. ALL WORK WILL BE ACCOMPLISHED ON N/R 189781 AT SAA/SAT DURING HMV AS PER N/R 203170 W/O 88398940001.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT CARGO COMPARTMENT BETWEEN STA 1287 - 1309 STR 30 HAS CORROSION AROUND FASTENERS AND ON STRINGERS. C/W AT SAA/SAT DURING HMV ON N/R 203019 W/O 88398780001. AS PER N/R 200218 W/O 88397290001.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

INTERIOR CABIN FLOOR STA 826 RBL 22 PREDRILLED HOLES OUT OF LIMITS. FABRICATED SEAT TRACK FROM S00483 BATCH 0002085358. INSTALLED NEW SECTION OF SEAT TRACK, PLATE AND SPLICE AT MAIN CABIN BETWEEN STA 797 TO STA 873 IAW MD 80 SRM 51-30-1 AND 05. C/W AT SAA/SAT DURING HMV ON N/R 203250.

Part: MOUNT — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

CRACK MAIN CABIN RT WINDOW MOUNT PLATE STA 1098. INSTALLED REPAIR PARTS PER DC9 / MD80 SRM 53-05 FIG 122 REF STEP 1.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

INTERIOR SEAT TRACK FROM STA 674 TO 845 LBL 24L GOUGED AND TRACK WEAR MARKS. FABRICATED SEAT TRACK SECTION IAW SRM MD 80 53-24-0 FIG 5. LOCATED AND DRILLED HOLES AT 1EA SEAT TRACK SECTION 2EA PLATES AND 2EA SPLICE REPAIR PER SRM MD 8051-10-4 PG 1. INSTALLED REPAIR PARTS AT INTERIOR CABIN FLOOR SEAT TRACK FROM STA 712 TO 731 LBL 24L PER SRM MD 80 53-05 PG 32 FIG 4F. AT SAA/SAT DURING HMV ONN/R 203209.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

MAIN CABIN LT FS 693 CUSP WEB HAS CORROSION ON UPPER AND LOWER SURFACE IN SEVERAL LOCATIONS. C/W AT SAA/SAT DURING HMV ON N/R 165179 W/O 88406090001.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

CRACK ON SHEAR TIE AT FUSELAGE SKIN AND FRAME AT STA 1429 BETWEEN LONGERON 1 AND LONGERON 2R. C/W AT SAA/SAT DURING HMV ON N/R 185707 W/O 88407000001.

Part: MOUNT BRACKET — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

CRACK ON MOUNTING BRACKET AT FWD SIDE OF FRAME STA 1429 AT 11 O'CLOCK POSITION APPROX. REMOVED AND REPLACED MOUNTING BRACKET. C/W AT SAA/SAT DURING HMV ON N/R 185709 W/O 88407020001.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT LAV FLOORBEAM STA 1322 LBL 28 LBL 20 EVIDENCE OF CORROSION, FABRICATED -9 AND -11 FILLER IAW SRM MD80 53-05 IFG 79A AND SRM 51-10-4.N FABRICATED LOCATED AND DRILLED FLOORBEAM REPAIR ANGLE STA 1322 LBL 36-53 IAW MD80 SRM 53-05 FIG 79A. INSTALLED FILLER REPAIR 9, 11 AND ANGLE REPAIR AT MAIN CABIN STA 1322 LBL PER SRM MD80 53-05 FIG 79A PG 473. AT SAA/SAT DURING HMV ON N/R 184781.

Part: SKIN — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

FUSELAGE SKIN RT SIDE ABOVE PYLON AT APPX STA 1380 SKIN IS CRACKED AT FASTENERS. C/W AT SAA/SAT DURING HMV ON N/R 203007 W/O 88398320001.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

CORROSION ON MAIN CABIN SEAT TRACK I/B AND O/B FLANGES STA 1136 TO STA 1174 LBL 45. FABRICATED LOCATED AND DRILLED NEW SEAT TRACK IAW MD 80 SRM 51-10-4 INSTALLED SEAT TRACK MAIN CABIN LEFT SIDE STA 1107 TO STA 1202 REPLACEMENT OF SECTION IAW MD 80 SRM 51-30-5. C/W AT SAA/SAT DURING HMV ON N/R 189866.

Part: MOUNT — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

CRACK ON MAIN CABIN RT FUSELAGE WINDOW MOUNT PLATE AFT UPPER CORNER STAN 1098. C/W AT SAA/SAT DURING HMV ON N/R 203065 W/O 88400930001.

Part: WEB — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

CORROSION ON SUBFLOOR WEB ON MAIN CABIN STA 1142 LBL 55 AND STA 1165 LBL 56 LBL FOUND UPON REMOVAL FLOOR SUPPORT FITTING AND Z-CHANNEL ON ROUTINE 203117. FABRICATED DOUBLER AND FILLER IAW MD 80 SRM 51-70-4 PG 17. INSTALLED DOUBLER AND FILLER IAW MD 80 SRM 51-30-5 PG 12.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

MAIN CABIN LT FS 693-712 CUSP WEB HAS CORROSION ON UPPER AND LOWER SURFACES. C/W AT SAA/SAT ON N/R 165181 W/O 88406080001.

Part: FLOORBOARD — DAMAGED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

FLOORBOARD PANEL HAS LOWER CHANNEL STTR BROKEN. FABRICATED REPLACEMENT SKIN USING SHT -7075-T6 .020 BATCH 0002035034 IAW SRM 53-24-0D. REPLACEMENT HAT CHANNEL AND REPLACEMENT SKIN PER SRM 51-10-3 INSTALLED HAT CHANNEL ON SKIN PER MD 80 SRM 51-30-02.AT SAA/SAT DURING HMV ON N/R 203042.

Part: WEB — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

MAIN CABIN FLOOR WEB LWR SURFACE AT STA 200 LT SIDE OF BL 0 CORROSION ON FLOOR WEB. REMOVED DAMAGE AND INSTALLED REPAIR DURING HMV.

Part: PLATE — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

CRACK 2EA ON MAIN CABIN LT FUSELAGE WINDOW MOUNT PLATE FWD LOWER CORNER STA 1022 AND AFT UPPER CORNER ST 1041. REPAIRED AT SAA/SAT DURING HMV ON N/R 230071 W/O 88400990001.

Part: BRACE — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

FWD CABIN FLOOR SUPPORT BRACE STA 200 TO STA 150 LBL 55 EVIDENCE OF CORROSION. CA467. C/W DURING HMV AT SAA/SAT ON N/R 165120 W/O 88405430001.

Part: BRACE — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

FWD CABIN FLOOR BRACE STA 150 TO 200 LBL 44 EVIDENCE OF CORROSION CA 466. REPAIR C/W AT SAA/SAT DURING HMV ON N/R 165119W/O 88405440001.

Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT CARGO COMPARTMENT AFT PRESSURE BULKHEAD FROM STRINGER 27R TO 27L HAS EXFOLIATING CORROSION AT THE BASE OF STA OF STA 1338 AFT SIDE. REPAIRED DURING HMV AT SAA/SAT ON N/R 203013 W/O 88398810001.

Part: CABLE — KINKED (TAILCONE) · airframe 46,070 hrs · 36,764 cycles

TAIL CONE EMERGENCY RELEASE SYSTEM AFT DOOR PULL CABLE KINKED AT AFT PRESSURE BULKHEAD. REPLACE AFT DOOR PULL CABLE DURING HMV.

Part: MOUNT — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

CRACK ON MAIN CABIN RT FUSELAGE WINDOW MOUNT PLATE, FWD LOWER CORNER STA 1117. REMOVED DAMAGE AND REPAIRED DURING HMV.

Part: SKIN — DENTED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

DENT ON FUSELAGE SKIN AT STA 217 BETWEEN LONGERON 16L AND LONGERON 17L. FABRICATED AND INSTALLED PERMANENT REPAIR DOUBLER FOR STA 217 BETWEEN LONG 16L & 17L ON N/R 172381 W/O88392690001. FABRICATED REPAIR FILLER AND DOUBLER IAW SRM MD80 53-04-5 FIG 5 AND 53-34-0FIG 1. AS PER N/R 183818 W/O 88400120001. AT SAA/SAT DURING HMV.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

FWD CABIN FLOOR SUPPORT FROM STA 200 TO STA 147 RBL 8 TO RBL 10 EVIDENCE OF CORROSION. REMOVED AND REPLACED FLOOR SUPPORT AT ST AEROSPACE SAN ANTONIO DURING HMV.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

INTERIOR CABIN FLOORBEAM STRUCTURE STA 256 LBL 22 EVIDENCE OF CORROSION. REMOVED DAMAGED FLOORBEAM SECTION AND INSTALLED REPAIR DURING HMV.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

FWD CABIN FLOOR SUPPORT BEAM FROM STA 200 TO STA 148 LBL 8 EVIDENCE OF CORROSION. REMOVED AND REPLACED FLOOR SUPPORT DURING HMV.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

MAIN CABIN LT FS 465 CUSP WEB HAS CORROSION. REMOVED DAMAGE AND INSTALLED REPAIR DURING HMV.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT LAV FLOOR SUPPORT STA 1309 LBL 16 TO RBL 16 EVIDENCE OF CORROSION. REMOVED AND REPLACED FLOOR SUPPORT DURING HMV.

Part: MOUNT — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

CRACK ON MAIN CABIN LT FUSELAGE WINDOW MOUNT PLATE AFT UPPER CORNER STA 1060. REMOVED DAMAGE AND REPAIRED DURING HMV.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

FUSELAGE STA 1474 CANTED FRAME LT EXHAUST LOUVER BOTTOM VERTICAL ANGLE CRACKED. REMOVED AND REPLACED ANGLE DURING HMV.

Part: MOUNT — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

CRACK ON MAIN CABIN RT FUSELAGE WINDOW MOUNT PLATE AFT UPPER CORNER STA 1022. REMOVED DAMAGE AND REPAIRED DURING HMV.

Part: MOUNT — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

CRACK ON MAIN CABIN LT FUSELAGE WINDOW MOUNT PLATE AFT UPPER CORNER STA 1022. REMOVED DAMAGE AND REPAIRED DURING HMV.

Part: MOUNT — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

CRACK ON MAIN CABIN RT FUSELAGE WINDOW MOUNT PLATE AFT UPPER CORNER STA 1117. REMOVED DAMAGE AND REPAIRED DURING HMV.

Part: MOUNT — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

CRACK ON MAIN CABIN LT FUSELAGE WINDOW MOUNT PLATE, FWD LOWER CORNER STA 984. REMOVED DAMAGE AND REPAIRED AT ST AEROSPACE SAN ANTONIO DURING HMV.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

FUSELAGE STA 1474 CANTED FRAME AREA AT RT EXHAUST LOUVER UPPER VERTICAL ANGLE CRACKED. REPLACED ANGLE ON CANTED FRAME DURING HMV.

Part: MOUNT — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

CRACK ON MAIN CABIN RT FUSELAGE WINDOW MOUNT PLATE AFT UPPER CORNER STA 1041. REMOVED DAMAGE AND REPAIRED DURING HMV.

Part: MOUNT — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

CRACK ON MAIN CABN LT FUSELAGE WINDOW MOUNT PLATE, AFT UPPER CORNER STA 1098. REMOVED DAMAGE AND REPAIRED DURING HMV.

Part: MOUNT — CRACKED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

CRACK ON MAIN CABIN RT FUSELAGE WINDOW MOUNT PLATE FWD LOWER CORNER STA 1155. REMOVED DAMAGE AND REPAIRED DURING HMV.

Part: BEAM — CRACKED (L1 DOOR) · airframe 46,070 hrs · 36,764 cycles

CRACK IN BEAM 1 IN RADIUS OF DOWN LEG ON L1 PASS DOOR AT APPROX STA 161.375 VIEWED THRU 2 LIGHTENING HOLE. REMOVED AND REPLACED BEAM ON L1 DOOR DURING HMV.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 46,070 hrs · 36,764 cycles

AFT CARGO COMP BILGE AREA RT SIDE AFT OF STA 1309 INTERCOSTAL WEB HAS EXFOLATING CORROSION ON I/B FWD END AT STR 28. REMOVED AND REPLACED INTERCOSTAL DURING HMV.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 46,029 hrs · 36,734 cycles

DURING LINE CHECK, MX FOUND FORWARD EMERGENCY LIGHTS LT AND RT SIDE EXIT DOORS INOPERATIVE. MX R & R POWER SUPPLY IAW MM. OPS CHECKS GOOD.

Part: SKIN — CRACKED (FUSELAGE) · airframe 45,798 hrs · 36,572 cycles

DORSAL FIN SKIN CRACKED LEFT SIDE STA1418 AND SKIN CRACKED UNDER INTERNAL SKATE ANGLE JUST AFT OF STA 1418 LEFT SIDE.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 45,593 hrs · 36,414 cycles

CORROSION ON SUBFLOOR WEB ON MAIN CABIN STA 1142 LBL 55 AND STA 1165 LBL 56 FOUND UPON REMOVAL FLOOR SUPPORT FITTING AND Z CHANNEL ON NON ROUTINE 230177. C/W AT SAA/SAT DURING HMV ON N/R 185685 W/O 88406810001.

Part: LIGHT — INOPERATIVE (SEAT 2C/2D) · airframe 42,925 hrs · 34,625 cycles

PASSENGER SEAT EMERGENCY LIGHTING AT 2C INOP. MX REPLACED EMERGENCY LIGHT ASSY AT SEAT 2C/D. OPS CHECK OF LIGHT, NOW CHECKS GOOD.

Part: LIGHT — INOPERATIVE (SEAT 26D) · airframe 42,565 hrs · 34,379 cycles

SEAT LEVEL EMERGENCY LIGHT OUT AT 26D. R & R EMERGENCY LIGHT ASSY AT 26D. OPS NORMAL IAW MM.

Part: ENGINE — ODOR (NR 1) · airframe 39,507 hrs · 32,298 cycles

IMMEDIATELY UPON ROTATION, ALL F/A STATION AND COCKPIT SMELLED A VERY ACRID, HEAVY ODOR. APU WAS OFF A/C FLIGHT RETURNED TO LAND THERE WAS NO SMOKE PRESENT. MTC IN PROGRESS. FOUND LT ENGINE AS SOURCE OF ODOR. REMOVED AND REPLACED NR 1 PER TRANSMITTAL. CHECKS GOOD OK FOR SERVICE. RUN UP CK ALL GOOD.

Part: ENGINE — MAKING METAL (NR 2) · airframe 36,658 hrs · 28,819 cycles

NR TWO ENG LOUD BAND ON TAKEOFF ROLL. METAL FOUND IN TAIL PIPE. FOUND SMALL METAL PARTICLES IN TAIL PIPE. REPLACED NR 2 ENG PER TRANSMITAL CARDS.

Part: GIMBAL RING — MISINSTALLED (HORIZONTAL STAB) · airframe 35,440 hrs · 27,262 cycles

DURING ACCOMPLISHMENT OF ROUTINE OPERATION THE HORIZ STAB JACKSCREW ACTUATOR GIMBLE RING WAS FOUND TO BE INSTALLED UPSIDE DOWN AND BACKWARDS. THIS CONFIGURATION RESULTED IN WEAR ON THE ATTACH FITTING LUGS. REPLACED JACKSCREW PER MM AND RIGGED SYSTEM PER MM.

Part: COFFEEMAKER — SMOKE (FWD GALLEY) · airframe 32,738 hrs · 24,935 cycles

SMOKE IN FWD CABIN AND COCKPIT. UPON INSPECTION, DETERMINED FWD GALLEY COFFEEMAKER TO BE SOURCE. REPLACED SAME.

Part: WIRE — BURNED (F/C ELECT OUTLET) · airframe 31,952 hrs · 24,376 cycles

F/C ELECT 110 OUTLET WIRING BURNED HOLES IN FUSELAGE. REPLACED OUTLET, EXECUTED FLEET CAMPAIGN.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 31,463 hrs · 24,037 cycles

DURING LAYOVER INSPECTION FOUND FIRST CLASS SECTION EMERGENCY PATH LIGHTING INOP. T/S AND REPLACED PWR SUPPLY FOR SECTION PER AMM, OPS CHECKS NORMAL.

Part: HANDLE — STUCK (COCKPIT) · airframe 31,364 hrs · 23,963 cycles

CABIN PRESSURE CONTROL WENT INOPERATIVE IN CRUISE. CREW REPORTED OUTFLOW VALVE HANDLE STUCK. REMOVED FALLEN AUTOPILOT SELECTOR KNOB FROM OUTFLOW VALVE CONTROL WHEEL.

Part: BULB — BURNED OUT (MLG INDICATOR) · airframe 28,138 hrs · 21,729 cycles

GO-AROUND INITIATED AFTER FAILURE OF RT MLG GREEN DN LIGHT FAILURE. POM PROCEDURE FOLLOWED. CHANGED BULBS, DN INDICATION NORMAL. BOTH BULBS WERE BAD. BULBS REPLACED. CHECKED PROX BOX. SENSORS OK.

Part: POWER SUPPLY — DISCHARGED (CABIN) · airframe 26,603 hrs · 20,588 cycles

EMERGENCY LIGHTS ROWS 31 AND AFT WOULD NOT TEST. REPLACED POWER SUPPLY, OP CHECK NORMAL.

Part: VALVE — LEAKING (NLG STRUT) · airframe 25,192 hrs · 19,563 cycles

NOSE GEAR IN TRANSIT LIGHT REMAINED ILLUMINATED AFTER GEAR HANDLE RAISED. T/S FOUND SCHRADER VALVE LEAKING. REPLACED SAME AND TESTED IAW M/M.

Part: CHARGER — FAILED (CABIN) · airframe 24,910 hrs · 19,364 cycles

ON L/O, FOUND SEAT ROW 1-12 EMERGENCY LIGHTS INOP. T/S PER MM REPLACED CHARGER AND BATTERY FOR SAME PER MM, SYS OPS CHECK OK.

Part: SWITCH — UNSERVICEABLE (COCKPIT) · airframe 24,237 hrs · 18,860 cycles

EMERGENCY POWER SW ON,A/C EMERGENCY BUSS OFF WARNING LIGHT ILLUMINATED//REPLACED EMERGENCY POWER SWITCH __DAL P/N 249201504

Part: BULB — FAILED (INSTRUMENT PANEL) · airframe 21,542 hrs · 16,858 cycles

LEFT MAIN LDG GEAR GREEN LIGHT INOP. RELAMPED LEFT MAIN LDG GEAR GREEN LIGHT.

Part: INLET — DIRTY (APU)

LIGHT SMOKE IN CABIN AFTER T/O. FOUND APU AIR INLET COACKED UP WITH OIL. CLEANED AND PERFORMED DUCT BURNOUT.