N913DE

Part: SWITCH — OUT OF POSITION (EMERGENCY LIGHTS) · airframe 63,777 hrs · 49,971 cycles

ON ENTRY TO COCKPIT FOLLOWING SHIP RON FOUND EMR LIGHTS SWITCH IN ARM POSITION AND EMERGENCY LIGHTS DEAD. NO FAULTS NOTED ALL EMR LIGHTS OPS CK NORMAL A/C OK FOR SVC. (LP5087898)

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 63,699 hrs · 49,907 cycles

FOUND 16-24 OVERHEAD EMER LIGHT OUT. R+R BATTERY FOR 16-24 OVERHEAD PANEL EMER LIGHTS. OPS CHECK GOOD. (LP5087857)

Part: DRAG BRACE — CORRODED (NLG) · airframe 63,024 hrs · 49,320 cycles

NLG DRAG BRACE ASSY WAS CORODED AT THE PIN HOLES. REPLACED THE NLG DRAG BRACE ASSY IAW AMM 32-21-03.

Part: BATTERY — DISCHARGED (CABIN) · airframe 62,731 hrs · 49,055 cycles

DOOR 2 LEFT OVER HEAD LIGHTS INOP. CHANGED BATTERIES PACK TWO 'D' CELL P/N AD4002P UNIT 107 DOOR 2 LEFT EMERGENCY OVERHEAD LIGHT OPS CHECK GOOD IAW AMM 33-50.

Part: DOOR — CRACKED (CARGO BAY) · airframe 61,598 hrs · 48,144 cycles

FOUND 1.5" CRACK ON FWD B/B DOOR LOWER FWD CORNER. FABRICATED AND INSTALLED NEW REPAIR DOUBLER PER ERA 486624-14MA REV 0.

Part: DOOR FRAME — DAMAGED (CARGO DOORWAY) · airframe 61,191 hrs · 47,823 cycles

MID CARGO DOOR FRAME ON AFT SIDE DAMAGED. REPAIRED THE DOOR FRAME IAW RI 563492-14, REV ORIG.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 60,965 hrs · 47,636 cycles

EMERGENCY LIGHTS IN CEILING BETWEEN ROWS 16-23 FOUND INOPERATIVE. REPLACED THE BATTERY PACK B5-102. CHECKED GOOD.

Part: LIGHT — BURNED OUT (COCKPIT) · airframe 60,220 hrs · 47,031 cycles

WHILE PARKED AT GATE DURING BOARDING, CAPTAIN AND FIRST OFFICER SMELLED A HOT ELECTRICAL OR MELTING PLASTIC BURNING ODOR IN THE COCKPIT. PASSENGERS WERE DEPLANED. MAINTENANCE PERFORMED AMDS WC 2120-2367 WITH NO TROUBLE FOUND. DURING TROUBLESHOOTING, MAINTENANCE FOUND THE FIRST OFFICER`S OVERHEAD FLOOD LIGHT BURNED OUT. REPLACED. A DUCT BURNOUT WAS PERFORMED. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: SKIN — CRACKED (LT WING) · airframe 60,134 hrs · 46,961 cycles

CRACKED LOWER SKIN ON THE LT WING REAR SPAR XCW 75. THE SKIN WAS REPAIRED IAW ETI-88-17-178, REV 7, AND ERA 558148-14AD, REV ORIG.

Part: BRACKET — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON PULLEY BRACKETS (2 E/A), ON FRAME STA Y=1463 CANT 12 HRS POSITION AT AFT ACCESSORY COMPARTMENT. REPAIRED PER ERA 558121-14.

Part: BLANKET — CORRODED (HEATER) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON THE RT HEATER BLANKET AROUND OF SECONDARY ACCESS COVER. THE HEATER BLANKET WAS REPLACED IAW AMM 30-80-02, PAGE BLOCK 401, PARAGRPH 2.

Part: DOUBLER — CORRODED (LAV PANEL) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON INTERNAL DOUBLER OF AFT LAVATORY SERVICE PANEL. A NEW DOUBLER WAS INSTALLED IAW ETI-88-17-155, REV 3, AND ER/A 558108-14, REV ORG.

Part: VANE — WORN (LT WING TE FLAP) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

WEAR ON THE LT OTBD VANE OTBD FLAP INBD SIDE. THE FLAP VANE WAS REPAIRED IAW ERA 558119-14, REV ORIG. AND ETI.-88-17-161, REV ORIG.

Part: SKIN — CORRODED (BS 1224-1229) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION OUT OF LIMITS ON BELLY DRAIN AREA FROM BS 1224 - 1229. . REPAIRED IAW SRM 53-05, FIG 150.

Part: SKIN — CRACKED (RT WING) · airframe 60,134 hrs · 46,961 cycles

CRACK INDICATION WAS FOUND AT OPEN HOLE, RT LOWER ACCESS DOOR CUTOUT AT XRS 202, FWD STRINGER 15. REPAIRED IAW ETI-88-17-157, REV 1, & ER/A 558111-14AD, REV ORIGINAL.

Part: SERVICE PANEL — CORRODED (LAVATORY) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION FOUND ON THE AFT LAVATORY SERVICE PANEL. THE SERVICE PANEL WAS REPLACED IAW DWG 5914792, REV AG, AND SRM 51-30-5.

Part: FRAME — CRACKED (BS 1485) · airframe 60,134 hrs · 46,961 cycles

CRACK ON FRAME BS 1485, 9 HR POSITION IN THE AFT ACCESSORY COMPARTMENT. REPAIRED THE FRAME IAW ER/A 558090-14, REV ORIGINAL.

Part: VANE — DAMAGED (LT WING TE FLAP) · airframe 60,134 hrs · 46,961 cycles

MATERIAL EXPOSED ON THE LT INBD VANE, INBD FLAP. REPAIRED IAW ERA 411033-14, REV A.

Part: RIB — CRACKED (RT WING) · airframe 60,134 hrs · 46,961 cycles

CRACK RIB WAS FOUND NEAR STA XRS=414 AT FRONT SPAR WING RT SIDE. RIB NEAR STA XRS=414 AT FRONT SPAR WING RT SIDE WAS REPAIRED PER SRM 57-06B FIG 12 SHEET 2. 51-30-2 AND 51-30-5.

Part: SKIN — DAMAGED (RUDDER) · airframe 60,134 hrs · 46,961 cycles

DAMAGED METALIZED SKIN ON RUDDER. THE DAMAGE WAS REPAIRED IAW ERA 092613-14MA, REV C.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 60,134 hrs · 46,961 cycles

CRACK ON CAP DOUBLER FRAME STA Y=1463 CANT, PROJECTION LONG 18 RT AT AFT ACCESSORY COMPARTMENT. CAP WAS REPLACED PER DWG 9953015 REV CB AND SRM 51-30-5.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON LT/RT FLOOR SUPPORT BTW STA Y=1309 AND Y=-1338 X=18/-18 AFT WET AREA. RT FLOOR SUPPORT REPLACED PER SRM 51-30-5. AND LT FLOOR SUPPORT WAS REPAIRED PER ETI-88-17-159 REV ORIGINAL AND ERA 558114-14 REV ORIGINAL.

Part: FRAME — CRACKED (FUSELAGE) · airframe 60,134 hrs · 46,961 cycles

CRACK ON FRAME STA Y=1418 BELOW LONG 2 LT AT AFT ACCESSORY COMPARTMENT. FRAME (SPLICE CAP) WAS REPLACED PER SRM 53-14-4, 51-30-2 AND 51-30-5.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON FRAME CLIP STA Y =1287 BTW LONG 28L TO 29L. FRAME CLIP WAS REPLACED PER SRM 51-30-2 AND DWG 9957739 ITEM 101 REV DD.

Part: INTERCOSTAL — CRACKED (L1 DOOR) · airframe 60,134 hrs · 46,961 cycles

CRACKED L1 DOOR AFT INTERCOSTAL BTW BEAM 4 AND 5. INTERCOSTAL WAS REPLACED PER SRM 51-30-2 AND DWG 9955763.

Part: FLOOR PANEL — CORRODED (BS 148-200) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON FLOOR PANEL IN FRONT OF FWD SERVICE DOOR BETWEEN BS 148 & 200. THE FLOOR PANEL WAS REPLACED IAW DWG 9957828, REV AB, AND 51-30-2.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON COUNTERSINK ON FUEL TANK ACCESS NR 1409C, 1454C, 1456C AND 1466C. ACCESS PANELS WERE REPLACED PER PAR 6 SRM 51-22-2A CONDITION 2.

Part: FLOOR PANEL — CRACKED (FUSELAGE) · airframe 60,134 hrs · 46,961 cycles

CRACKED FLOOR PANEL NR 120A. FLOOR PANEL NR 120A WAS REPAIRED PER SRM 53-01 FIG 4.

Part: CUSP WEB — CORRODED (BS 626-732) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON CUSP WEB UPPER & LOWER, RBL 54 - 60 BETWEEN BS 626 - 723 AND BS 730 - 732. THE CUSP WEB WAS REPLACED IAW SRM 53-14-3, AND 53-05 ,FIG 131, A-24.

Part: FITTING — CRACKED (SPOILERS) · airframe 60,134 hrs · 46,961 cycles

CRACK ON GROUND SPOILERS FITTING AT LT WING. GROUND SPOILERS FITTING AT THE LT WING WAS REPLACED IAW SRM 51-30-2, 51-30-5, AND DWG 5936824 REV CC.

Part: FLOOR PANEL — CRACKED (NOT REPORTED) · airframe 60,134 hrs · 46,961 cycles

CRACK ON FLOOR PANEL 200F. THE FLOOR PANEL WAS REPAIRED IAW SRM 53-05, FIG 131B, PAR 145.

Part: PAN — CRACKED (CARGO DOOR) · airframe 60,134 hrs · 46,961 cycles

CRACK ON PAN BS 427 BETWEEN BEAMS 1 AND 2 AT THE FWD CARGO DOOR. INNER AND OUTER PANS WERE REPAIRED IAW ER/A 558110-14, REV ORIGINAL, AND ETI-88-17-156, REV 3.

Part: DOUBLER — CORRODED (CARGO DOOR) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION BELOW PRODUCTION DOUBLERS ON THE AFT CARGO DOOR. SKIN CORNERS REPAIRED IAW ER/A 558112-14, REV ORIGINAL, AND ETI-88-17-158, REV 1.

Part: ANGLE — CORRODED (BS 1212) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORRODED ANGLE ON THE CARGO DOOR FRAME BS 1212, LONGERON 22R IN THE AFT CARGO BAY. THE ANGLE WAS REPLACED IAW DWG 4912817, ITEM 503, REV C.

Part: CUSP WEB — CORRODED (BS 518-579) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON CUSP WEB UPPER & LOWER SURFACE LBL 54 TO 60 BETWEEN BS 518 - 541, BS 553 - 556, AND BS 573 - 579 IN THE PAX CABIN. THE CUSP WEB WAS REPLACED IAW SRM 53-14-3, AND 53-05, FIG 131, A-24.

Part: CUSP WEB — CORRODED (BS 739-769) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON THE CUSP WEB UPPER & LOWER SURFACE RBL 54 - 60, BETWEEN BS 739 - 769, IN THE PAX CABIN. THE CUSP WEB WAS REPLACED IAW SRM 53-14-3, AND 53-05, FIG 131, A-24.

Part: SEAT TRACK — CORRODED (BS 840-986) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON THE SEAT TRACK RBL 54, BETWEEN BS 840 - 986. THE DAMAGE AREA WAS REPAIRED IAW SRM 53-05, FIG 4F.

Part: ACCESS PANEL — CORRODED (NOT REPORTED) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON COUNTERSINK ON FUEL TANK ACCESS PANEL 1361C. THE ACCESS PANEL WAS REPLACED IAW PAR 6, SRM 51-22-2A, CONDITION II.

Part: SKIN — WORN (L1 DOOR CUTOUT) · airframe 60,134 hrs · 46,961 cycles

WEAR AROUND CUT OUT OF L1 DOOR HOOK ON FUSELAGE SKIN. THE SKIN WAS REPAIRED IAW SRM 53-04, FIG 24, 51-10-3, PAR 14, & 21, 51-30-2, 51-30-5, AND 51-10-4.

Part: TAB — DENTED (RT ELEVATOR) · airframe 60,134 hrs · 46,961 cycles

DENTS ON THE RT GEARED TAB. THE TAB WAS REPAIRED IAW SRM 55-04, PAR 2.

Part: DOUBLER — WORN (BS 1485-1510) · airframe 60,134 hrs · 46,961 cycles

WEAR ON DOUBLER REPAIRS ON FUSELAGE SKIN BETWEEN BS 1485 - 1510, 5 O`CLOCK POSITION AT AFT ACCESSORY COMPARTMENT. DOUBLERS WERE REPLACED IAW SRM 53-01, FIG 2, SHEET 3, AND 51-30-2.

Part: DOUBLER — WORN (CARGO DOOR) · airframe 60,134 hrs · 46,961 cycles

WEAR ON THE LOWER AFT & FWD DOUBLER CORNERS ON THE MID CARGO DOOR. THE DOUBLERS WERE REPLACED IAW SRM 51-30-2, AND DWG 5910141, REV FE.

Part: SEAT TRACK — DAMAGED (BS 792-798) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

ELONGATED HOLES ON THE RT SEAT TRACK LBL 54 BETWEEN BS 792 - 798. THE DAMAGE AREA WAS REPAIRED IAW SRM 53-05, FIG 4F.

Part: DOUBLER — WORN (CARGO DOOR) · airframe 60,134 hrs · 46,961 cycles

WEAR ON THE LOWER AFT & FWR DOUBLER CORNERS AT THE AFT CARGO DOOR. THE LOWER AFT & FWR DOUBLER CORNERS WERE REPLACED IAW SRM 51-30-2, AND DWG 5910141, FIG FE.

Part: CUSP WEB — CORRODED (BS 503-604) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON CUSP WEB UPPER & LOWER RBL 54 TO 60 BETWEEN BS 503 & 604. THE CUSP WEB WAS REPLACED IAW SRM 53-14-3, AND 53-05 FIG 131 A-24.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON SETTLEMENT AREA ON THE FUEL TANK ACCESS PANEL 1379C. THE ACCESS PANEL WAS REPLACED IAW SRM 51-22-2A, PAR 6.

Part: CUSP WEB — CORRODED (BS 579-704) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION THE ON CUSP WEB UPPER & LOWER SURFACES LBL 54 - 60, BETWEEN BS 579 - 665 ,AND BS 681 - 704, IN THE PAX CABIN. THE CUSP WEB WAS REPLACED IAW SRM 53-14-3, AND 53-05, FIG 131, A-24.

Part: SEAT TRACK — DAMAGED (BS 323-330) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

ELONGATED HOLES ON THE RT SEAT TRACK LBL 54 BETWEEN BS 323 - 330. THE DAMAGED AREA WAS REPAIRED IAW SRM 53-05, FIG 4F.

Part: SEAT TRACK — CORRODED (BS 671-672) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION OUT OF LIMITS AT BS 671 - 672 ON SEAT TRACK PLUG LBL 54. THE PLUG WAS REPLACED IAW SRM 53-05, FIG 4A.

Part: DOUBLER — DEBONDED (CUSP WEB) · airframe 60,134 hrs · 46,961 cycles

DISBONDED PREVIOUS REPAIR DOUBLER AND IMPROPERLY DISTANCE OF FASTENER TO EDGE ON RH CUSP WEB BTW BS 427-434 RBL 54 TO 60 AT PAX CABIN. THE REPAIR DOUBLER WAS FABRICATED AND WAS INSTALLED IAW SRM 51-30-2, 51-05, FIG 131A, AND 51-30-5.

Part: CUSP WEB — CORRODED (BS 1222-1224) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON CUSP WEB, BS 1222 - 1224, LBL 54 - 60. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-6.

Part: SPACER — CORRODED (BS 696-693) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON PREVIOUS REAPAIR SPACER AND ON BEAM BETWEEN BS 636 - 693, LONGERON 28R. REPAIRED IAW SRM 53-05, FIG 123.

Part: DOUBLER — DEBONDED (BS 294) · airframe 60,134 hrs · 46,961 cycles

DISBONDED REPAIR DOUBLER BS 294, BETWEEN LONGERONS 17 & 18L. THE DOUBLER WAS REPLACED IAW SRM 53-04-3, FIG 2, & 51-30-2.

Part: CUSP WEB — CRACKED (BS 885) · airframe 60,134 hrs · 46,961 cycles

CRACKED RT CUSP WEB BS 885 BETWEEN LBL 54 AND 60. DOUBLER AND FILLER FABRICATED AND INSTALLED IAW SRM 53-05, FIG 131A-3.

Part: LONGERON — CORRODED (BS 1170) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON LONGERON 24L, BS 1170. THE LONGERON WAS REMOVED AND REPLACED IAW SRM 51-30-02, SRM 51-10-4, AND SRM 51-30-5.

Part: LONGERON — CRACKED (BS 1437) · airframe 60,134 hrs · 46,961 cycles

CRACK ON LONGERON 12L, BS 1437. THE LONGERON WAS REPAIRED IAW SRM 53-02, FIG 18.

Part: FLOOR SUPPORT — CORRODED (BS 160-200) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON FLOOR SUPPORT BETWEEN BS 160 - 200, RBL 44. FLOOR SUPPORT REPLACED IAW SRM 51-30-2, 51-30-5, AND 51-10-3, PAR 26.

Part: PAN — CRACKED (L1 DOOR) · airframe 60,134 hrs · 46,961 cycles

CRACKED L1 DOOR FWD & AFT PAN BETWEEN BEAM 1 AND TOP. THE PAN CORNERS WERE REPAIRED IAW SRM 52-05, FIG 18A.

Part: FITTING — CRACKED (BS 655) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CRACK ON FITTING BS 655 BETWEEN BEAM 1 AND LWR EDGE AT MID CARGO DOOR. FITTING REPLACED IAW SRM 51-30-5 AND 51-30-2. (LP0016410)

Part: BEAM — CRACKED (L1 DOOR) · airframe 60,134 hrs · 46,961 cycles

CRACKED L1 DOOR BEAM NR 7 AFT SECTION. THE DOOR BEAM WAS REPAIRED IAW SRM 52-05, FIG.109.

Part: FLOORBEAM — CORRODED (BS 200) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON FLOORBEAM BS 200, RBL 47 TO 58. THE FLOORBEAM WAS REPLACED IAW SRM 51-30-5 AND 51-10-4.

Part: CUSP WEB — CRACKED (BS 844) · airframe 60,134 hrs · 46,961 cycles

CRACK ON CUSP WEB BETWEEN BS 844, RBL 57. DAMAGE AREA WAS REPAIRED IAW SRM 53-05, FIG 131A-3.

Part: VANE — DELAMINATED (LT WING TE FLAP) · airframe 60,134 hrs · 46,961 cycles

DELAMINATION ON INBD VANE OF THE OTBD FLAP. THE VANE WAS REPLACED IAW SRM 57-03 D, PARAGRAPH 11 B.

Part: DOUBLER — CRACKED (BS 905) · airframe 60,134 hrs · 46,961 cycles

CRACK ON DOUBLER REPAIR BETWEEN BS 905, LBL 56 IN THE PAX CABIN LT SIDE. THE DOUBLER WAS REPLACED IAW SRM 53-05, FIG 131A-12.

Part: CHANNEL — CRACKED (EMERGENCY EXIT) · airframe 60,134 hrs · 46,961 cycles

CRACKED CHANNEL ON RT FWD EMERGENCY EXIT DOOR BELOW STOP FITTING NR 1. THE CHANNEL WAS REPLACED IAW SRM 51-30-2 AND 51-30-5.

Part: BEAM — CRACKED (R1 DOOR) · airframe 60,134 hrs · 46,961 cycles

CRACKED R1 DOOR NR 1 BEAM FWD SECTION. THE BEAM WAS REPLACED IAW SRM 51-30-1, 51-30-2, AND 51-30-5.

Part: FLOOR SUPPORT — CORRODED (BS 210) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON FLOOR SUPPORT BETWEEN BS 210, RBL 12, IN THE PAX CABIN. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-30-5, AND 51-10-4.

Part: SKIN — DENTED (RT WING TE FLAP) · airframe 60,134 hrs · 46,961 cycles

SEVERAL DENTS ON OTBD VANE AT RT INBD FLAP. DUE TO SEVERAL DENTS ON OUTBD VANE AT RT INBD FLAP. WILL BE REPLACED IAW SRM 57-04, PARAGRAPH. 5. C. (1).

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORRODED ACCESS PANEL 1303C ON LT WING. THE ACCESS PANEL WAS REPLACED IAW SRM 51-22-2A, PAR 6, CONDITION III.

Part: SKIN — CRACKED (RT WING) · airframe 60,134 hrs · 46,961 cycles

DURING NDT INSPECTION, A DISCREPANT AREA WAS FOUND ON THE LOWER SKIN BETWEEN XRS 163 - 168, REAR SPAR ON RT WING. REPAIRED IAW ER/A 556412-14AD, REV.ORIGINAL.

Part: FLOOR SUPPORT — CORRODED (BS 160-200) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON FLOOR SUPPORT BETWEEN BS 160 - 200 LBL 54. FLOOR SUPPORT STA Y=160-169 X=44 WAS REMOVED; DRILLED; ADJUSTED; TREATED AND PAINTED; AND INSTALLED PER DC9/MD80 SRM 51-30-2; 51-30-5; 51-10-4; 51-10-3 PAR 14 AND 21/FLOOR SUPPORT STA Y=186-195 X=44 CORROSION WAS REMOVED, TREATED AND PAINTED PER DC9/MD80 SRM 51-10-3 PAR 26, 21 AND 14; MEASURE WAS ACCOMPLISHED WITH NDT SPM 04-00-07 PAR 5 FIG 3 SHEET 1 AND 2 ORIGINAL THICKNESS .063" REMAINING THICKNESS .061" ON FLOOR SUPPORT (1 EA) THEREFORE ITS WITHIN LIMITS IAW SRM 53-01 FIG 1 (SHEET 3). CIC WAS APPLIED IAW SRM 51-10-3 PAR 38.

Part: SKIN — WORN (L1 DOOR) · airframe 60,134 hrs · 46,961 cycles

WEAR ON HOOK DOUBLER AT L1 DOOR EXTERNAL SKIN. DOUBLER WAS REPLACED PER DC-9/MD-80 ER/A 486216-14MA REV. A. (LP0012218)

Part: SKIN — CRACKED (WING) · airframe 60,134 hrs · 46,961 cycles

DURING NDT INSPECTION, A DISCREPANT AREA WAS FOUND ON LOWER SKIN BETWEEN XRS 163 - 168, REAR SPAR. REPAIRED IAW ER/A 556412-14AD, REV ORIGINAL.

Part: SPAR CAP — CRACKED (HORIZONTAL STAB) · airframe 60,134 hrs · 46,961 cycles

CRACK ON UPPER INBD HOLE ON THE HORIZONTAL STABILIZER RT REAR UPPER SPAR CAP. REPAIRED.

Part: DOUBLER — WORN (CARGO DOOR) · airframe 60,134 hrs · 46,961 cycles

WEAR ON LWR AFT/FWR DOUBLER CORNERS AT FWD CARGO DOOR. REPAIRED IAW ER/A 486624-14 MA, REV ORIGINAL.

Part: FLOOR SUPPORT — CORRODED (BS 160-200) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON FLOOR SUPPORT BETWEEN BS 160 - 200, LBL 44. A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-30-2, AND 51-30-5.

Part: SKIN — DAMAGED (BS 200-218) · airframe 60,134 hrs · 46,961 cycles

SUNKEN FASTENERS ON REPAIR DOUBLER ON THE SKIN AT BS 200 AND 218, LONGERON 26L. THE REPAIR WAS REPLACED IAW SRM 53-04-3, FIG 10.

Part: SUPPORT — CRACKED (LT ENGINE) · airframe 60,134 hrs · 46,961 cycles

CRACKED SYNCRONIZER ACTUATOR SUPPORTS AT LT ENGINE. SUPPORTS THREE EAS WERE REPLACED IAW DWG 5938303 REV E AND SRM 51-30-1.

Part: BUSHING — CORRODED (NOT REPORTED) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON BUSHINGS AFT AT RT HEATER BLANKET. DAMAGED BUSHINGS WERE REPLACED IAW SRM 51-30-10.

Part: FLOOR SUPPORT — CRACKED (BS 1287-1309) · airframe 60,134 hrs · 46,961 cycles

CRACKED FLOOR SUPPORT AT BL 0 BETWEEN BS 1287 AND 1309. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-30-2, AND 51-30-5.

Part: TAB — DAMAGED (LT ELEVATOR) · airframe 60,134 hrs · 46,961 cycles

PRESENCE OF WATER WAS FOUND ON LEFT ELEVATOR ANTI-FLOAT TAB HONEYCOMB STRUCTURE. LEFT ELEVEATOR ANTI FLOAT TAB WAS REMOVED PER MD 88 AMM 27-30-14, WAS REPLACED.

Part: CUSP WEB — WORN (BS 1000) · airframe 60,134 hrs · 46,961 cycles

WEAR ON CUSP WEB, BS 1000, RBL 56 IN THE PAX CABIN. DOUBLER WAS FABRICATED IAW SRM 53-05 FIG.131A-13. AREA WAS TREATED AND PAINTED IAW SRM 51-10-3, PAR 21, AND 14, THE DOUBLER WAS INSTALLED IAW SRM 53-05, FIG 131A-13.

Part: CUSP WEB — CORRODED (BS 470-474) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON CUSP WEB RBL 54 TO 60 BETWEEN BS 470 TO 474. DAMAGED AREA WAS REPAIRED IAW SRM 53-05, FIG 131A-14.

Part: SEAT TRACK — CORRODED (BS 203-205) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION OUT OF LIMITS ON THE SEAT TRACK RBL 22, BS 203 - 205. THE SEAT TRACK WAS REPLACED IAW SRM 53-05, FIG 4F, CONF. 7001.

Part: FLOOR SUPPORT — CORRODED (BS 200) · corrosion level 2 · airframe 60,134 hrs · 46,961 cycles

CORROSION ON THE FLOOR SUPPORT BS 200, LBL 56. THE FLOOR SUPPORT WAS REMOVED IAW SRM 51-30-2, AND 51-30-5. A NEW FLOOR SUPPORT WAS FABRICATED IAW SRM 51-10-2, AND DWG 9910078, REV JC. TREATED AND PAINTED IAW SRM 51-10-3, PAR 21, AND 14 AND INSTALLED IAW SRM 51-30-2, AND 51-30-5.

Part: TAB — DELAMINATED (LT ELEVATOR) · airframe 60,134 hrs · 46,961 cycles

DELAMINATED CONTROL TAB AT LT ELEVATOR. LT CONTROL TAB REPLACED IAW SRM 55-04 PAR 2.

Part: TAB — DENTED (RT ELEVATOR) · airframe 60,134 hrs · 46,961 cycles

DENTS ON RT CONTROL TAB, THE TAB WAS REPLACED IAW SRM 55-04 PAR 2.

Part: PAN — CRACKED (BS 1250) · airframe 60,134 hrs · 46,961 cycles

CRACKED LT WINDOW RING PAN UPPER AFT CORNER BS 1250. REPAIRED IAW SRM 53-05, FIG 122.

Part: PAN — CRACKED (BS 1041) · airframe 60,134 hrs · 46,961 cycles

CRACKED LWR /FWD CORNER RING PAN LH SIDE STA Y=1041. REPAIRED IAW SRM 53-05, FIG 122.

Part: PAN — CRACKED (BS 1136) · airframe 60,134 hrs · 46,961 cycles

CRACKED RT WINDOW RING PAN UPPER /AFT CORNER BS 1136. REPAIRED IAW SRM 53-05 FIG 122.

Part: PAN — CRACKED (BS 845) · airframe 60,134 hrs · 46,961 cycles

CRACKED ON LWR/AFT ,FWD/UPPER CORNER RING PAN LH SIDE BS 845. REPAIRED IAW SRM 53-05 FIG 122.

Part: PAN — CRACKED (BS 927) · airframe 60,134 hrs · 46,961 cycles

CRACKED FWD/UPPER CORNER RING PAN LT BS 927. REPAIRED IAW SRM 53-05 FIG 122.

Part: FRAME — CRACKED (FUSELAGE) · airframe 59,404 hrs · 46,417 cycles

TAIL CONE GUIDE PIN 12 O’CLOCK FRAME CRACKED. INSTALLED REPAIR AS PER ERA 497316-14MA SEC 1 REV ORIGINAL.

Part: FASTENER — SHEARED (TAIL CONE) · airframe 59,404 hrs · 46,417 cycles

TAIL CONE AT LT UPPER LATCH RECEPTACLE HAS SHEARED FASTENERS AT SUPPRT BRACKETS. REPLACED SHEAR FASTENERS PER SRM 51-30, OK FOR SERVICE.

Part: DOOR — CRACKED (LT MLG) · airframe 58,004 hrs · 45,397 cycles

LEFT LANDING GEAR DOOR FOUND CRACK AFT EDGE AT CURVE. R & R LT MLG DOOR ASSY IAW AMM 32-12, GEAR SWING CKS GOOD.

Part: PIN — PULLED (L1 DOOR SLIDE) · airframe 56,753 hrs · 44,513 cycles

MAINTENANCE FOUND THE L1 DOOR SLIDE PINS PULLED OUT. THE L1 DOOR SLIDE WAS REPLACED.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 56,202 hrs · 44,119 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE OVERHEAD EMERGENCY LIGHTING IN THE FIRST CLASS SECTION OF THE CABIN WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES. OPS CHECKED GOOD.

Part: RELEASE CABLE — FRAYED (TAILCONE) · airframe 55,534 hrs · 43,659 cycles

TAIL CONE RELEASE CABLE, DAMAGED AND FRAYED AFT OF BS 1485 AT 9 O`CLOCK POSITION. REPLACED THE RELEASE CABLE IAW AMM 53-53-02.

Part: CABLE — DAMAGED (NOT REPORTED) · airframe 55,534 hrs · 43,659 cycles

CABLE DAMAGED AND FRAYED. REPLACED THE CABLE IAW AMM 53-53-02.

Part: SKIN — DAMAGED (VERTICAL STAB) · airframe 55,534 hrs · 43,659 cycles

VERTICAL STABILIZER L/E SPLICE AT ZFS=52.267, HAVE WORN COUNTER SINKS. FASTENERS ARE PULLED TO DEEP INTO THE SKIN; MARKED, RII: N ENTR 575200 W APPROVAL LEVEL ACCOMPLISHED BY INSPECTED BY FINAL, C/A 01045-08, VERTICAL L/E TO BE INSTALLED ON AMDS WC 5530-01045-0602, TASKS, NO APPROVAL LEVEL TASK DESCRIPTION, REMOVED VERTICAL L/E PANEL WIP: OPENED DAMAGED .1875 HOLES TO .311, OPENED DAMAGED .2500 HOLES TO .359 IAW SRM 55-03. ACCOMPLISHED OPEN HOLE EDDY CURRENT INSPECTION IAW SRM 55-03, PG 134, SECTION 27.C, D, 1, NO CRACKS NOTED.

Part: DOOR SILL — CORRODED · corrosion level 2 · airframe 54,647 hrs · 43,062 cycles

AFTER OPENING OF AFT CARGO DOOR SILL, FOUND PREVIOUS REPAIR FILLER WITH CORROSION BETWEEN STA 1156 AND 1210. GAINED ACCESS AT PREVIOUS REPAIR STA 1156 AND 1210 IAW SRM 51-30-5. REMOVED PREVIOUS REPAIR FILLER, SPACER. FABRICATED NEW -9 SPACER AND REINSTALLED -9 SPACER, ALL ACCESS GAINED RESTORED IAW SRM 53-05, FIG 123A PERMANENT REPAIR ACCOMPLISHED.

Part: SKIN — DENTED (BS 1226) · airframe 54,669 hrs · 43,077 cycles

TWO DENTS IN BELLY AT BS 1226 IAW ERA 532852-14, REV ORIGINAL PERMANENT REPAIR ACCOMPLISHED.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 53,653 hrs · 42,369 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT SEVERAL OF THE OVERHEAD EMERGENCY LIGHTS WERE INOPERATIVE. REPLACED LAMP EACH LIGHT, BUT THE LIGHT ASSEMBLY AT THE RT FORWARD OVERWING EXIT REQUIRED REPLACEMENT. A SATISFACTORY FUNCTIONAL CHECK WAS PERFORMED FOLLOWING REPLACEMENT.

Part: PIN — MISSING (TAILCONE) · airframe 53,512 hrs · 42,277 cycles

DURING CHECK, MAINTENANCE FOUND THE TAILCONE TELEFLEX CABLE TEE PIN ATTACH BOLT NUT AND COTTER PIN MISSING. THE BOLT STARTED TO MIGRATE OUT OF POSITION. MAINTENANCE REPLACED THE HARDWARE.

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHT) · airframe 51,876 hrs · 41,168 cycles

EMERGENCY LIGHT AT SEAT 34DE INOPERATIVE. REPAIRED DAMAGED SEAT WIRE HARNESS, OPS CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 51,847 hrs · 41,148 cycles

EMERGENCY LIGHT INOPERATIVE AT ROW 29. BATTERY PACK REPLACED AND OPS NORMAL.

Part: INLET — CONTAMINATED (APU) · airframe 51,134 hrs · 40,681 cycles

DURING CLIMBOUT, FLIGHT CREW DETECTED A BURNING ODOR. NO SMOKE NOTED. ODOR DISSAPATED AFTER FIVE MINUTES. FOUND RESIDUAL HYD FLUID NEAR THE APU INLET WITH NO LEAKS FOUND. THE APU INLET WAS CLEANED AND THE DUCT BURNOUT WAS COMPLETED IAW WC 4950-2215. THE COALESCER BAGS WERE ALSO REPLACED. EXCESS PARKER LUBE NOTED ON THE WATER SEPARATOR PACKINGS. THE WATER SEPARATORS WERE ALSO CLEANED WITH NO FURTHER ODOR NOTED AFTER MX WAS PERFORMED. THE ACFT WAS RETURNED TO SERVICE.

Part: BRACKET — CRACKED (TAILCONE) · airframe 49,818 hrs · 39,745 cycles

DURING CHECK, TAILCONE UPPER LT BAYONET BRACKET WAS FOUND CRACKED. REMOVED, FABRICATED, HEAT TREATED, PRIMED AND INSTALLED BRACKET IAW DWG 9911957.

Part: SKIN — CRACKED (BS 1418) · airframe 49,758 hrs · 39,706 cycles

SKIN HAS A CRACKED FASTENER HOLE, BS 1418 L2R OTBD OF VERTICAL SKATE ANGLE. PERFORMED HFEC IAW NDT SPM 06-10-01. ALL FASTENERS INSTALLED REPAIR DOUBLER, C/W PRI 512397-14AD REV 0. AWAITING FINAL ER/A.

Part: SKIN — CRACKED (BS 1418) · airframe 49,772 hrs · 39,714 cycles

BS 1418, L2R SKIN CRACKED. REPAIRED IAW ERA 512397-14

Part: FRAME — CRACKED (BS 1418) · airframe 49,758 hrs · 39,706 cycles

CRACK AT BS 1418, LONGERON L2R WITHIN FRAME BACKUP ANGLE. REPAIR ANGLE PRIMED AND HOLES PICKED UP. OK TO INSTALL ANGLE C/W PRI 512493-14 REV 0.

Part: BRACKET — WORN (TAILCONE) · airframe 49,758 hrs · 39,706 cycles

DURING SERVICE CHECK, TAILCONE BUNGEE SPRING BRACKET IS WORN. R & R IAW MM.

Part: SKIN — CRACKED (RUDDER) · airframe 49,758 hrs · 39,706 cycles

DURING SERVICE CHECK, RUDDER SKIN UPPER MID HINGE CUTOUT FOUND CRACKED. REMOVED DAMAGED PLIES AND TAPERED BACK IAW SRM 51-70-01A, PG 189. DAMAGED CONTAINED. OK TO INSTALL REPAIR. PRIMED, PAINTED AND INSTALLED REPAIR IAW SRM 51-70-01A.

Part: BATTERY PACK — FAILED (EMERGENCY LIGHT) · airframe 49,758 hrs · 39,706 cycles

DURING SERVICE CHECK, FORWARD OVERWING EMERGENCY EXIT LIGHTS FAILED TEST. R & R BATTERIES IN PACK B5103 IAW MM. OPS CHECKED GOOD.

Part: LAMP — BURNED OUT (EMERGENCY LIGHT) · airframe 49,492 hrs · 39,514 cycles

DURING SERVICE CHECK, MX FOUND EMERGENCY EXIT SIGNS AT BOTH FWD OVERWING EXITS INOPERATIVE. RELAMPED BOTH FORWARD OVERWING EMEGENCY EXIT SIGNS. OPS CHECKS GOOD.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 48,758 hrs · 38,944 cycles

FORWARD FUSELAGE SKIN DAMAGED AT WATER DRAIN HOLE. REPAIRED IAW ERA 507489-14, REV O.

Part: LONGERON — DAMAGED (BS 256-275) · airframe 48,758 hrs · 38,944 cycles

LONGERON 29R DAMAGED BETWEEN BS 275-256. REMOVED DAMAGE, TREATED, PRIMED AND INSTALLED REPAIR IAW ERA 507489-14, REV O.

Part: SHEAR TIE — DAMAGED (BS 275) · airframe 48,758 hrs · 38,944 cycles

SHEAR TIE AND FRAME BENT AND BUCKLED, STA 275 L29R. REMOVED DAMAGED FORMER AND STRAIGHTENED SHEAR TIE. DAMAGED CONTAINED. TREATED, PRIMED AND INSTALLED REPAIR IAW SRM 53-03, FIG 3. ALL COMPLETED IAW ERA 507489-14, REV O.

Part: SOCKET — DAMAGED (EMERGENCY LIGHT) · airframe 47,758 hrs · 38,235 cycles

DURING SERVICE CHECK, MAINTENANCE FOUND EMERGENCY LIGHT OUT AT SEAT 18. REPLACED LAMP SOCKET. OPERATION CHECKED NORMAL.

Part: CAM — WORN (TAILCONE) · airframe 47,639 hrs · 38,148 cycles

DURING OPERATION 6908 FUNCTIONAL CHECK OF TAIL CONE RELEASE SYSTEM, MAINTENANCE FOUND TEE PIN 11 WORN WITH BUSHING AND BASE FOR RELEASE CAM WORN. REMOVED AND REPLACED TEE PIN 11 AND CAM ASSEMBLY PER AMM. RII COMPLETED FUNCTIONAL CHECK GOOD.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 47,237 hrs · 37,882 cycles

DUE PERMANENT REPAIR PER ERA 485618-14 REV B CODE 53-31-10 ACTL 2151. SKIN STA 218 L-30 TO 1-29R JACK PAD FITTING DAMAGE. COMPLY WITH PERMANENT REPAIR ERA 485618-14 REV C.. ACTL 215 SKIIN STA 218 L-30 TO L-29R JACK PAD FITTING DAMAGE.

Part: BATTERY PACK — DISCHARGED (VENTRAL STAIRWAY) · airframe 47,172 hrs · 37,834 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN THE VENTRAL STAIRWAY WERE INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: SKIN — CORRODED (FUSELAGE) · airframe 46,295 hrs · 37,253 cycles

DURING HMV CORROSION WAS FOUND ON FUSELAGE SKIN STA Y=1097-1117 BETWEEN LONGERON 27LT AND L=27RT. FUSELAGE SKIN WAS REPAIRED IAW MD80 SRM 53-04 FIG 53.

Part: PAN — CRACKED (CARGO DOOR) · airframe 46,295 hrs · 37,253 cycles

DURING HMV A CRACK WAS FOUND ON PAN OF MID CARGO COMPARTMENT DOOR AFT EDGE BEHIND SETTLEMENT AREA OF STOP NUMBER 4. C1 DOOR PAN WAS REPAIRED IAW MD80 SRM 52-05D FIG 50.

Part: SKIN — CORRODED (FUSELAGE) · airframe 46,295 hrs · 37,253 cycles

DURING HMV CORROSION WAS FOUND ON FUSELAGE SKIN STA Y=1079 AND LONGERON L=30 ALSO STA Y=1098 BTW L=28LT AND L=29LT. FUSELAGE SKIN WAS REPAIRED IAW MD80 SRM 53-04D FIG 53.

Part: PAN — CRACKED (CARGO DOOR) · airframe 46,295 hrs · 37,253 cycles

DURING HMV A CRACK WAS FOUND ON MID CARGO COMPARTMENT DOOR PAN OUTBOARD EDGE BELOW OF FWD DOOR STOP NR 4. MID C2 DOOR PAN WAS REPAIRED IAW MD80 SRM 52-05D FIG 50.

Part: SKIN — CORRODED (FUSELAGE) · airframe 46,295 hrs · 37,253 cycles

CORROSION ON FUSELAGE SKIN STA Y=742-788 BETWEEN LONGERONS 26LT AND 29LT. ON 17SEP MAINTENANCE REPAIRED FUSELAGE SKIN IAW MD-80 SRM 53-04D FIG 53.

Part: SKIN — SCRATCHED (FUSELAGE) · airframe 46,295 hrs · 37,253 cycles

DURING HMV SCRATCHES ON FUSELAGE SKIN STA Y=1098-1115 BETWEEN LONGERON 18LT AND 20LT, ALSO STA Y=946-1037 BETWEEN LONGERON 18LT AND 17LT. FUSELAGE SKIN WAS REPAIRED IAW MD80 SRM 53-04D FIG 53.

Part: BEAM — CORRODED (FUSELAGE) · airframe 46,295 hrs · 37,253 cycles

DURING HMV CORROSION WAS FOUND ON LOWER BEAM OF MID CARGO COMPARTMENT DOOR JAMB FROM STA Y=636 TO Y=693 BEAM. REPAIRED IAW MD80 SRM 53-05D FIG 123.

Part: SKIN — DENTED (ELEVATOR TAB) · airframe 46,295 hrs · 37,253 cycles

DURING HMV DENTS WERE FOUND ON LT/RT ELEVATOR GEAR TAB UPPER AND LOWER SKIN TAB. REPAIRED IAW MD80 SRM 55-04D PARA 3A.

Part: SKIN — CORRODED (FUSELAGE) · airframe 46,295 hrs · 37,253 cycles

CORROSION ON FUSELAGE SKIN STA Y=1079 L=30. DOUBLER REPAIR INSTALLED IAW DC9/MD80 SRM 53-040 FIG 53.

Part: FITTING — BENT (FUSELAGE) · airframe 46,295 hrs · 37,253 cycles

BENT ON FRAME CLIP STA 237 BETWEEN LONG 18LT-17LT. NEW FORMER WAS INSTALLED IAW DC9/MD80 SRM 51-30-5.

Part: DOUBLER — CORRODED (FUSELAGE) · airframe 46,295 hrs · 37,253 cycles

SDR DURING HMV CORROSION WAS FOUND ON PREVIOUS REPAIR DOUBLER ON LOWER BEAM IN AFT CARGO COMPARTMENT DOOR JAMB FROM STA Y=1186 TO 1198.

Part: BEAM — CORRODED (FUSELAGE) · airframe 46,295 hrs · 37,253 cycles

DURING HMV CORROSION WAS FOUND ON LOWER BEAM OF AFT CARGO COMPARTMENT DOOR JAMB FROM STA Y=1171 TO Y=1212.

Part: BEAM — DAMAGED (FUSELAGE) · airframe 46,295 hrs · 37,253 cycles

DURING HMV ELONGATED HOLES WERE FOUND AFTER REMOVING FITTING ON MID CARGO COMPARTMENT DOOR JAMB LOWER BEAM.

Part: TAB — DAMAGED (ELEVATOR) · airframe 46,295 hrs · 37,253 cycles

SUPP INFO NRC T0220281 LIGHTNING STRIKES ON LT ELEVATOR CONTROL TAB TRAILING EDGE WAS REPAIRED IAW SRM 55-04 PARA 3A.

Part: TAB — DENTED (ELEVATOR) · airframe 46,295 hrs · 37,253 cycles

SUPP INFO NRC T0220282 DENTS ON LT ELEVATOR CONTROL TAB EDGE WAS REPAIRED IAW SRM 55-04 PARA 3A.

Part: SKIN — DELAMINATED (AILERON) · airframe 46,295 hrs · 37,253 cycles

SDR DURING HMV DELAMINATION WAS FOUND ON LOWER SKIN OF LT AILERON STA XW=476 TO XW=486 AND AT UPPER SKIN OUTBD EDGE AT STA XW=486.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 46,295 hrs · 37,253 cycles

DURING HMV CORROSION WAS FOUND ON FORWARD SERVICE DOOR JAMB CUSP ANGLE STA Y=196-218 X=-42 TO X=-60.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 46,295 hrs · 37,253 cycles

DURING HMV CORROSION WAS FOUND ON RT CUSP WEB STA Y=1174-1193, 1193-1212, 1212-1231 AND 1231-1250 BTW X=-54 AND X=-60 AT PAX CABIN (TO 220410). MAINTENANCE REPLACED THE CUSP WEB IAW MD80 SRM 53-20-02D.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 46,295 hrs · 37,253 cycles

DURING HMV CORROSION WAS FOUND ON RT CUSP WEB STA Y= 1098-1117, 1117-1136, 1136-1155 AND 1155-1174 BTW X=-54 AND X=-60 AT PAX CABIN (TO 220409).

Part: SKIN — DENTED (FUSELAGE) · airframe 46,295 hrs · 37,253 cycles

DURING HMV DENTS AND SCRATCHES WERE FOUND ON FUSELAGE SKIN REPAIR DOUBLER STA Y=236 BETWEEN LONG 18LT AND 17LT (TO 220111).

Part: DOOR FRAME — DAMAGED (FUSELAGE) · airframe 46,295 hrs · 37,253 cycles

HIDDEN DAMAGE ELONGATED HOLES WERE FOUND AFTER REMOVED FITTINGS ON MID CARGO DOOR JAMB LOWER BEAM. DAMAGE REMOVED IAW DC9/MD80 SRM 53-05 FIG 123. REPAIR ACCOMPLISHED IAW DC9/MD80 SRM 51-30-2, 51-30-5 FIG 123.

Part: ANGLE — WORN (FUSELAGE) · airframe 46,295 hrs · 37,253 cycles

WEAR ON TEE ANGLE STA 1338 BTW LONG 25RT-27RT AT AFT CARGO COMPARTMENT. TEE WAS REMOVED AND NEW TEE INSTALLED IAW DC9/MD80 SRM 53-03 FIG 37.

Part: SKIN PANEL — DAMAGED (VERTICAL STAB) · airframe 46,295 hrs · 37,253 cycles

DRILLED COUNTERSINK ON VERTICAL STABILIZER REMOVABLE LEADING EDGE HOLES. REAMED AND INSTALLED BUSHINGS AND DOUBLER IAW AMR0955182.

Part: DOOR FRAME — CORRODED (FUSELAGE) · airframe 46,295 hrs · 37,253 cycles

CORROSION ON LOWER BEAM OF AFT CARGO COMPARTMENT DOOR JAMB FROM STA Y=1171 TO Y=1212. REPAIR ANGLE AND BUSHINGS INSTALLED IAW DC9/MD80 SRM 53-05 FIG 123 AND ERA 495239-14 REV ORIG.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 46,295 hrs · 37,253 cycles

CORROSION ON RT CUSP WEB STA Y=1098-1117,Y=1117-1136,Y=115 BTW X=-54 AND X=-60 AT PAX CABIN. CUSP WEB WAS REPLACED IAW DRD 53-20-02D.

Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 46,295 hrs · 37,253 cycles

DENT AND SCRATCH ON FUSELAGE SKIN REPAIR DOUBLER STA 236 BTW LONG 18LT AND 17LT. REPAIR DOUBLER WAS REPLACED IAW DC-9/MD80 SRM 53-04D FIG 12B SHEET 34.

Part: SKIN — CRACKED (FUSELAGE) · airframe 46,295 hrs · 37,253 cycles

CRACKS ON FUSELAGE SKIN STA Y=1436 BETWEEN LONGS 3LT-5LT. REPAIR INSTALLED IAW DC9/MD80 SRM 53-04D FIG 27.

Part: SKIN — DELAMINATED (LT AILERON) · airframe 46,295 hrs · 37,253 cycles

DELAMINATION ON LOWER SKIN OF LT AILERON STA XW=476 TO XW=486 AND AT UPPER SKIN OUTBD EDGE AT STA XW=486. UPPER SKIN WAS REPAIRED IAW DC9/MD80 SRM 51-10-1A PARA 14. UPPER SKIN WAS INSPECTED NO DELAM FOUND.

Part: WIRE — DISCONNECTED (EMERGENCY LIGHT) · airframe 45,971 hrs · 37,007 cycles

DURING SERVICE CHECK, MX FOUND ROW 22 EMERGENCY PATHWAY LIGHTS INOPERATIVE. MX RE-ATTACHED WIRES PER SWPM. OPS NOW CHECKS NORMAL.

Part: CONNECTOR — BROKEN (EMERGENCY LIGHT) · airframe 43,980 hrs · 35,688 cycles

DURING LINE CHECK, MX FOUND EMERGENCY PATH LIGHT AT 11D & 13D INOPERATIVE. MX REPAIRED BROKEN CONNECTORS. OPS OF LIGHTS NOW CHECKS OK.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 43,952 hrs · 35,667 cycles

JACK PAD AND STRUCTURE AROUND IT DAMAGED.

Part: WIRE — BROKEN (EMERGENCY LIGHT) · airframe 43,798 hrs · 35,572 cycles

MX FOUND THE EMERGENCY ESCAPE PATH LIGHT AT ROW 15 TO BE INOPERATIVE. MX FOUND A BROKEN WIRE ON THE OTBD SIDE OF THE SEAT. MX APPLIED A CRIMP SPLICE TO THE WIRE IAW SWPM 20-10-03. AN OPS CHECK WAS PERFORMED AND THE ACFT WAS RETURNED TO SERVICE.

Part: REGULATOR — FAULTY (RT ENGINE) · airframe 43,728 hrs · 35,520 cycles

FLIGHT CREW RETURNED TO ATL DUE TO RIGHT ENGINE "HIGH OIL PRESSURE" INDICATION. MAINTENANCE REPLACED THE RIGHT ENGINE OIL PRESSURE REGULATOR, PRESSURE TRANSMITTER, AND OIL ECK OF FILTER. ALSO CHECKED THE OIL PRESSURE SENSE LINE FOR OBSTRUCTIONS AND FOUND THAT IT WAS CLEAR. AN ENGINE RUN-UP TO TAKEOFF POWER SHOWS THAT THE OIL PRESSURE NOW INDICATES PROPERLY (2010-D0946) (DLM88102116).

Part: FRAME — UNKNOWN (FUSELAGE) · airframe 43,360 hrs · 35,284 cycles

FUSELAGE OVERWING FRAMES REPAIRED IAW EA 09-460094-12, ME03.

Part: SLIDE — MISINSTALLED (DOOR L1) · airframe 42,904 hrs · 34,931 cycles

ON LAYOVER, MX FOUND L1 DOOR SLIDE LANYARD WAS DIFFERENT THEN R1 DOOR. IT WAS DISCOVERED SLIDE LANYARD AT L1 DOOR WAS INSTALLED INCORRECTLY. THE LANYARD WAS REROUTED AND CORRECTED FOR PROPER OPERATION.

Part: MOUNT BRACKET — CRACKED (RADAR) · airframe 41,304 hrs · 33,912 cycles

WHILE REPLACING RADOME FOUND RADAR ANTENNA MOUNTING BRACKET BROKEN AT THE TWO TOP ATTACHING BOLTS. ANTENNA WAS HELD IN PLACE BY THE TWO LOWER BOLTS ALLOWING THE ANTENNA TO PULL AWAY FROM THE PRESSURE BULKHEAD. REPLACED WX RADAR ANTENNA ASSY PER AMM, TEST NORMAL.

Part: SKIN — CRACKED (HORIZONTAL STAB) · airframe 36,789 hrs · 29,168 cycles

FATIGUE CRACK FOUND IN RT HORIZONTAL STABILIZER UPPER INBOARD SKIN PANEL. SKIN PANEL REPLACED.

Part: BULB — FAULTY (NR 1 ENGINE) · airframe 35,773 hrs · 27,871 cycles

AT FL 210 OVER PVD HIGH OIL TEMP WAS INDICATED ON LT ENGINE AND ENGINE SHUTDOWN PROCEDURE WAS PERFORMED. INITIAL TEMP WAS 158 DEGREES C AND THEN SPIKED TO 199 DEGREES C AND REMAINED HIGH AFTER ENGINE SHUTDOWN. ALL OTHER ENGINE INDICATIONS WERE NORMAL. ENGINE WINDMILLED FOR 15 MINS APPROX THE REMAINDER OF FLIGHT WITH POSITIVE OIL PRESSURE. REPLACED FDR. PERF BITE ON FLAT SCREEN NO DISCREP NOTED. CLEANED AND INSP C/PLUG FOR NBR 1 ENG OIL TEMP BULB. REPLACED TEMP BULB. SHOOK DOWN WIRING. PERFORMED WINDMILL INSP. ENGINE RUNUP AND LEAK CHK NML AT ALL PWR SETTINGS

Part: APU — CONTAMINATED (APU BAY) · airframe 34,761 hrs · 26,553 cycles

AIR TURNBACK, LT AFT LAV SMOKE ALARM WITH FUMES. PERFORMED OPN 5088 AND FOUND APU INLET CONTAMINATED WITH GLYCOL. PERFORMED OPN 5090 - ALT DUCT BURNOUT. ALSO CLEANED A LOT OF GLYCOL FROM 48 SECTION. RAN PACKS, NO SMOKE PRESENT.

Part: LINE — LEAKING (HYD SYSTEM) · airframe 31,950 hrs · 24,549 cycles

LEFT HYD QTY DROPPED TO 3 WITH AMBER LIGHT ON. GOOD PRESS OF 3000 QTY, NOW MOVING BETWEEN 3 AND 16 QTS. AMBER LIGHT GOING ON AND OFF WITHOUT REGARD TO QTY SHOWING. FOUND LEAKING HYD RETURN LINE ON LEFT REV CONTROL VALVE. TIGHTENED LINE AND LEAK CK'ED GOOD. CLEANED APU INLET AREA, RAN APU AND PACKS. NO FOUL ODOR NOTED IN CABIN.

Part: OIL SYSTEM — LOW (APU) · airframe 30,942 hrs · 23,824 cycles

A/C 9013 DIVERTED TO LGA FROM ATL EN ROUTE TO ALB DUE TO APU FAULT LIGHT ILLUMINATED AFTER LEFT ENGINE CSD DISCONNECTED. SERVICED APU OIL TO FULL.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 30,304 hrs · 23,374 cycles

FOUND EMERGENCY LIGHTS FROM ROW 31 AFT INOP. REPLACED POWER SUPPLY. CHECKS GOOD.

Part: ENGINE — MALFUNCTIONED (NR 1) · airframe 28,956 hrs · 22,466 cycles

ON CLIMB, LT ENG OIL TEMP HI - ATB TO ATL - REPLACED ENGINE

Part: CHARGER — FAILED (EMERGENCY LIGHTS) · airframe 28,140 hrs · 21,913 cycles

DURING LAYOVER, FOUND AFT SECTION OF EMERGENCY LIGHTS FROM SEAT 31 AFT WERE INOPERATIVE. REPLACED FUSE IN EMERGENCY LIGHT BATTERY CHARGER, NOW OP NORMAL.

Part: ENGINE — DAMAGED (NR 2) · airframe 28,037 hrs · 21,842 cycles

ON T/O HEARD LOUD BANG AND NR 2 ENG EPR AT 1.5. WITH CLIMB POWER SELECTED RT ENG STAYED AT IDLE 3-5 MINS. THEN OIL QTY WENT TO 0 AND RT ENGINE WAS SHUT DOWN. A/C RETURNED TO ATL. FOUND RT ENG TURBINE DAMAGED. NO DAMAGE FOUND IN FAN OR COMPRESSOR AREA. ENG HAS 1726.7 HRS. REPLACED ENGINE.

Part: CONTROL VALVE — LEAKING (THRUST REVERSER) · airframe 23,870 hrs · 18,768 cycles

AFTER 2 HOURS IN CRUISE HYDRAULIC QTY WAS 4. TURNED OFF LT PUMP QTY INDICATED 7-16. USED LT PUMP FOR APPROACH. AFTER BALANCING HYD QTY DECREASE TO 2. FOUND LT T/R CONTROL VLV LEAKING AT B-NUT. TIGHTENED SAME.

Part: FILTER — DIRTY (NR 2 ENGINE)

RT ENGINE OIL STRAINER CLOGGED LIGHT ON IN FLT. ENGINE SHUT DOWN. REPLACED MAIN OIL FILTER DUE TO BEING CLOGGED WITH CARBON.

Part: CONTROLLER — INOPERATIVE (RT PACK)

AFTER TAKEOFF FROM MKE, NOTICED RIGHT PACK PRESSURE AT 55 PSI (LEFT PACK PRESSURE 25 PSI) AFT F/A COULD SMELL BURNING ODOR. THEN RIGHT PACK SHUTDOWN AND PRESSURE DROPPED TO 12 PSI. RAN ABNORMAL CHECKLIST AND LEFT THE RIGHT PACK OFF. RIGHT PACK OPERATED NORMALLY ON GROUND WITH APU AIR IN MANUAL MODE. CHECKED LT AND RT PACKS AND DUCTING ACMS OPERATING NORMAL. REPLACED RT PACK A/C CONTROLLER RT PACK OPERATES IN NORMAL MODES. NO SMELLS NOTED, PACK SYSTEM CKS NORMAL.

Part: BATTERY PACK — DISCHARGED (EMER EXIT)

OVERWING EMERGENCY LIGHTS INOP. REPLACED OVERWING BATTERY PACK, OPS CKD GOOD.

Part: BATTERY — DISCHARGED (CABIN)

ON L/O, FOUND AFT EXTERIOR EMERGENCY LIGHT INOP. REPLACED EMERGENCY LIGHTS BATTERY, OKS CKS GOOD.

Part: FILTER O-RING — FAILED (RT HYD MODULE)

ON APPROACH, GEAR WOULD NOT EXTEND UNTIL SECOND TRY WHEN RT HYD QTY WENT TO 0 AND FLUID LEAKING IN TAIL COMPARTMENT. FOUND RT HYD FILTER MODULE O-RING BAD. REPLACED SAME.

Part: WINDOW — SHORTED (FLT DECK)

CAPTAIN RECEIVED ELECTRIC SHOCK WHEN TOUCHING FRAME OF LEFT WINDSCREEN. REPLACED WINDOW AND CONTROLLER.

Part: SKIN — DENTED (FS 237)

THE FUSELAGE SKIN NEAR FS 237, BELOW THE CUSP AT S-18L WAS BADLY DENTED BETWEEN S-18L AND 20L. ACCOMPLISHED REPAIRS PER DL ERA 271814-14.

Part: GENERATOR — FAILED (APU)

ON CLIMBOUT, NR 2 ENG GENERATOR ON MCO. APU GENERATOR FAILED COULD NOT RESET. DIVERTED ATL. REPLACED APU GENERATOR CONTROL UNIT AND NR 2 ENGINE CSD. OPERATION NORMAL.

Part: DOOR FRAME — GOUGED (NR 1 CARGO DOOR)

C-1 CARGO DOOR AFT PAN GOUGED AND WORN THROUGH FIRST LAYER OF PAN. FOUND AT B-2 LTR CK. REPAIRED PER SRM 52-05 FIG 27.

Part: FIRE BOTTLES — FAILED (TAIL COMP)

DURING PNEUMATIC SYSTEM CHECKOUT, A LOUD NOISE WAS HEARD IN THE TAIL OF THE AIRCRAFT. ON INVESTIGATION, BOTH FIRE BOTTLES WERE FOUND RIPPED FROM THEIR MOUNTS AND DISCHARGED, CAUSING EXTENSIVE DAMAGE TO PNEUMATIC DUCTS, AFT PRESSURE DOME AND STRINGER 10 AT FS 1338. CAUSE OF DISCHARGE AND BOTTLE FAILURE IS UNDER INVESTIGATION.