UNITED PARCEL SERVICE CO.

Operated by UNITED PARCEL SERVICE CO (per NTSB report)

Operated by UNITED PARCEL SERVICE CO (per NTSB report)

Encounter with windshear during landing which resulted in a tailstrike.

Operated by United Parcel Service Co (per NTSB report)

The pilot’s incorrect pitch attitude during a bounced landing which resulted in a tailstrike.

Operated by UNITED PARCEL SERVICE CO (per NTSB report)

Operated by UNITED PARCEL SERVICE CO (per NTSB report)

Operated by UNITED PARCEL SERVICE CO (per NTSB report)

Operated by UNITED PARCEL SERVICE CO (per NTSB report)

The flight crew’s incorrect pitch attitude during go-around.

Operated by UNITED PARCEL SERVICE CO (per NTSB report)

Operated by United Parcel Service (per NTSB report)

Operated by United Parcel Service (per NTSB report)

Operated by UNITED PARCEL SERVICE CO (per NTSB report)

the pilot flying's failure to maintain airspeed and correct pitch attitude. Contributing to the accident was the pilot's failure to maintain appropriate thrust after disconnecting the autothrottles. Also contributing was the first officer's failure to monitor the decaying airspeed and increasing pitch.

Operated by United Parcel Service (per NTSB report)

The controller's issuance of a landing clearance to an arriving aircraft while another aircraft was in position on the same runway. Contributing to the incident was the controller's non-compliance with traffic advisory procedures, and insufficient requirements for use of memory aids to track arrival and departure operations.

Operated by United Parcel Service (per NTSB report)

Operated by UNITED PARCEL SERVICE CO (per NTSB report)

the flight crew's continuation of an unstabilized approach and their failure to monitor the aircraft's altitude during the approach, which led to an inadvertent descent below the minimum approach altitude and subsequently into terrain. Contributing to the accident were (1) the flight crew's failure to properly configure and verify the flight management computer for the profile approach; (2) the captain's failure to communicate his intentions to the first officer once it became apparent the vertical profile was not captured; (3) the flight crew's expectation that they would break out of the clouds at 1,000 feet above ground level due to incomplete weather information; (4) the first officer's failure to make the required minimums callouts; (5) the captain's performance deficiencies likely due to factors including, but not limited to, fatigue, distraction, or confusion, consistent with performance deficiencies exhibited during training; and (6) the first officer's fatigue due to acute sleep loss resulting from her ineffective off-duty time management and circadian factors.

Operated by United Parcel Service Company (per NTSB report)

The captain's failure to control the airplane pitch-up induced by ground spoiler deployment during the go-around.

Operated by UNITED PARCEL SERVICE CO (per NTSB report)

Operated by United Parcel Service Co. (per NTSB report)

The captain's failure to maintain clearance from a parked airplane awaiting for a gate. A contributing factor was that taxi procedures were not issued by ground control to advise the captain that the ramp area where he was taxing was designated as a non-movement area and not under the tower's control. Another factor was that company notices to airmen (NOTAMS) were not issued to advise their pilots that tarmac markings in that particular ramp area were not accurate, and that the area was a non-movement area not under the control of the tower.

Operated by UNITED PARCEL SERVICE (per NTSB report)

Operated by UNITED PARCEL SERVICE (per NTSB report)

Operated by UNITED PARCEL SERVICE CO. (per NTSB report)

FAILURE OF THE AIRCRAFT OPERATOR MAINTENANCE PERSONNEL TO ADEQUATELY LUBRICATE AND SEAL THE MAIN LANDING GEAR BOGIE BEAM SWIVEL JOINT AS REQUIRED BY MANUFACTURER AND OPERATOR MAINTENANCE PROGRAM REQUIREMENTS. THIS ALLOWED MOISTURE TO ENTER THE SWIVEL JOINT AND CAUSE CORROSION DAMAGE WHICH CAUSED STRESS CORROSION CRACKING AND FAILURE OF THE SWIVEL JOINT LUGS. CONTRIBUTING TO THE INCIDENT WAS LACK OF CLEAR INSTRUCTIONS IN THE OPERATORS MAINTENANCE PROGRAM REGARDING LUBRICATION OF THE SWIVEL JOINT.

Operated by UNITED PARCEL SERVICE (per NTSB report)

INADEQUATE OBSTACLE CLEARANCE, WHICH RESULTED IN ON GROUND COLLISION WITH A BLAST FENCE. CONTRIBUTING WAS INADEQUATE INSTRUCTION FROM GROUND PERSONNEL.

Sanction: $10,000 · case closed 2015-02-13

Sanction: $5,000 · case closed 2015-02-13

Sanction: $20,000 · case closed 2014-12-23

Sanction: $9,500 · case closed 2014-07-23

Sanction: $5,000 · case closed 2018-09-18

Sanction: $15,000 · case closed 2014-04-30

Sanction: $10,000 · case closed 2014-03-03

Sanction: $24,750 · case closed 2013-09-17

Sanction not stated · case closed 2013-09-17

Sanction: $18,000 · case closed 2013-11-14

Sanction: $6,600 · case closed 2013-03-04

Sanction: 38750 · case closed 2012-02-15

Sanction: $63,000 · case closed 2012-06-20

Sanction: $8,000 · case closed 2013-06-10

Sanction: $116,970 · case closed 2012-08-06

Sanction: $15,000 · case closed 2011-10-20

Sanction: 40000 · case closed 2012-07-24

Sanction: $30,625 · case closed 2011-10-07

Sanction: $35,000 · case closed 2011-06-02

Sanction: $10,000 · case closed 2011-10-20

Sanction: $15,000 · case closed 2011-06-02

Sanction: $10,000 · case closed 2011-10-20

Sanction: $10,000 · case closed 2011-10-20

Sanction: $10,000 · case closed 2011-10-20

Sanction: $35,000 · case closed 2010-08-13

Sanction: 40000 · case closed 2012-07-24

Sanction: $128,135 · case closed 2011-10-07

Sanction: $4,000 · case closed 2010-03-05

Sanction: $29,350 · case closed 2010-03-05

Sanction: $7,700 · case closed 2011-07-14

Sanction: $5,000 · case closed 2011-07-14

Sanction: $13,250 · case closed 2011-07-14

Sanction: $10,000 · case closed 2011-07-14

Sanction: $1,500 · case closed 2010-04-30

Sanction: $48,000 · case closed 2011-06-09

Sanction: $25,000 · case closed 2009-10-26

Sanction: $4,000 · case closed 2009-06-19

Sanction: $4,500 · case closed 2009-06-19

Sanction: $7,500 · case closed 2009-02-10

Sanction: $25,000 · case closed 2009-08-13

Sanction: $1,000 · case closed 2009-02-10

Sanction: $5,000 · case closed 2008-11-24

Sanction: $10,000 · case closed 2009-05-22

Sanction: $20,000 · case closed 2008-06-30

Sanction: $10,000 · case closed 2009-11-16

Sanction: $5,000 · case closed 2009-01-08

Sanction: $21,000 · case closed 2009-01-12

Sanction: $53,000 · case closed 2007-11-15

Sanction: $7,000 · case closed 2006-01-17

Sanction: $11,250 · case closed 2006-01-17

Sanction: $18,000 · case closed 2006-01-26

Sanction: $11,000 · case closed 2005-01-12

Sanction: $8,000 · case closed 2005-03-11

Sanction: $44,400

Sanction: $50,000 · case closed 2001-10-30

Sanction: $5,500 · case closed 2001-07-23

Sanction: $6,500 · case closed 2001-07-23

Sanction: $5,000 · case closed 2001-11-01

Sanction: $1,100 · case closed 2005-03-14

Sanction: $2,200 · case closed 2005-03-14

Sanction: $6,600 · case closed 2005-03-17

Sanction: $15,000 · case closed 2000-11-08

Sanction: $2,200 · case closed 2005-03-17

Sanction: $11,000 · case closed 2001-11-05

Sanction: $22,000 · case closed 2001-11-05

Sanction: $8,000 · case closed 2001-11-05

Sanction: $4,500 · case closed 2000-09-05

Sanction: $4,500 · case closed 2001-11-05

Sanction: $5,500 · case closed 2001-03-08

Sanction: $5,500 · case closed 2000-08-31

Sanction: $5,500 · case closed 2001-03-08

Sanction: $3,000 · case closed 2000-12-04

Sanction: $3,000 · case closed 1999-08-13

Sanction: $27,500 · case closed 1999-07-19

Sanction: $2,000 · case closed 1999-06-29

Sanction: $8,000 · case closed 2002-10-21

Part: ACTUATOR — FAULTED (ZONE 700) · airframe 38,364 hrs · 22,843 cycles

ATB, GEAR DISAGREE EICAS AND GEAR LIGHT. RAN CHECKLIST RETURN TO CAE & CAUTION LIGHT TOO. REVERSED DMP 32-30-1. REPLACED PROX SWITCH 065 REF FIM 32-09 FAULT TREE 821. ADJUSTED PROX SWITCHES 065 AND 078 AS REQUIRED TO 5.5 MILIHENRI NEAR BOTH LOCKED AND UNLOCKED ARE IN THE NEAR POSITION. ALSO REF TECH ALERT ATTACHED TO THIS WORK PACKAGE FOR REPLACEMENT OF THE NLG LOCK ACTUATOR. OPS CHECKED SEVERAL TIMES ALL INDICATIONS WERE NORMAL. REQUIRES A FINAL OPS CHECK AND PLACARD REMOVAL. C/W FINAL OPS CHECKS OF NOSE LANDING GEAR EXTENSION AND RETRACTION IAW AMM 32-34-00

Part: LIFE VEST — MISSING (ZONE 200) · airframe 17,323 hrs · 2,568 cycles

FO'S LIFEVEST MISSING. INSTALLED LIFEVEST PER MM 25-62-05.

Part: CRASH AXE — CORRODED (ZONE 200) · airframe 27,578 hrs · 4,067 cycles

MAIN CARGO DECK CRASH AX IS CORRODED AND DAMAGED REMOVED AND REPLACED THE MAIN CARGO DECK CRASH AX IAW AMM 25-63-04-400-801.

Part: FLAP SYSTEM — WARNING MESSAGE · airframe 39,734 hrs · 26,696 cycles

EMD ON CLIMB OUT AT APPROX 3K' WE GOT A LE SLAT DISAGREE EICAS. MAINTAINED 230 KT OR LESS FOR ENTIRE FLIGHT. AFTER QRH PROCEDURE, MSG WENT OUT. PERFORMED BITE PROCEDURE IAW FIM 27-51 FAULT TREE 805 FLAP/SLAT ELECTRONIC UNIT (FSEU) BITE PROCEDURE. FOUND ALTERNATE FLAP SWITCH NOT IN NORMAL POSITION. PLACED ALTERNATE FLAP SWITCH IN NORMAL POSITION BITE PROCEDURE PASSED WITH NO FAULTS. FLAPS AND LE SLATS OPS CHECK GOOD IN ALTERNATE AND HYDRAULIC.

Part: CRASH AXE — DAMAGED (ZONE 200) · airframe 27,578 hrs · 4,067 cycles

MAIN CARGO DECK CRASH AX IS CORRODED AND DAMAGED. REMOVED AND REPLACED THE MAIN CARGO DECK CRASH AX IAW B747 AMM 25-63-04-400-801

Part: DISPLAY — FAILED (ZONE 200) · airframe 73,906 hrs · 25,353 cycles

EMERGENCY DECLARED, CAPT / FO LOST ALL PFD/MAP EICAS ALL LARGE DISPLAY SCREENS WERE LOST FROM FL200 TO PARK SPOT STBY INSTRUMENTS WORKED.

Part: STRUCTURE — CRACKED (ZONE 400) · airframe 26,579 hrs · 15,952 cycles

UPON FURTHER INSPECTION, CRACK DEFERRED ON TASK T3F18E0097P77 HAS GROWN TO 5.5IN? BEYOND SRM LIMITS. DEFERRED PER EO-98354.

Part: LENS — MISSING (ZONE 200) · airframe 28,975 hrs · 17,862 cycles

LENS MISSING FROM EMERGENCY LIGHT 150WL NEAR LAV.

Part: SEAL — LEAKING (ZONE 800) · airframe 29,737 hrs · 17,969 cycles

HOWLING SOUND COMING FROM MAIN CABIN DOOR DURING ENTIRE FLIGHT. CRUISE, CLIMB, DESCENT. R & R L1 DOOR SEAL IAW AMM 52-10-18 UP TO & INCL 2.D.(6). REQUIRES TEST AND LEAK CHECK. C/W REMAINING STEPS OF AMM 52-10-18, TEST GOOD. REF T3F18E009AJ1A FOR LEAK CHECK REQUIREMENT. LEAK CHECK GOOD WITH NO NOISES COMING FROM L1 DOOR AREA.

Part: LENS — MISSING (ZONE 200) · airframe 28,983 hrs · 17,868 cycles

LENS MISSING FROM EMERGENCY LIGHT 150WL NEAR LAV REPLACED EMERGENCY WALL LIGHT LENS ON LIGHT 150WL REF AMM 33-51-17. OPS CHECKED GOOD.

Part: COVER — CRACKED (ZONE 100) · airframe 29,160 hrs · 17,946 cycles

FR 13A, STR 51 LT NLG DOOR CUTOUT COVER PANEL HAS A .467" CRACK ON I/B EDGE.

Part: PUMP — LOW PRESSURE (ZONE 400) · airframe 29,296 hrs · 18,100 cycles

EMERGENCY DECLARED, GREEN ENG HYD PUMP 2 LOW PRESSURE FOLLOWED ECAM ,SELECTED OFF , RESULTED IN LOSS OF GREEN HYD FLUID RESULTED IN GREEN HYD FALURE.

Part: HINGE PIN — MIGRATED (HANDLE COVER) · airframe 31,778 hrs · 11,470 cycles

FLIGHT DECK. CREW ENTRY DOOR. DOOR HANDLE COVER PLATE, SPRING LOADED. HINGE PIN MIGRATED 1/4 OF WAY OUT. RE-ALIGNED HINGE PIN. OPS CK GOOD. OK TO CONTINUE. REF IPC 52-12-01-02 ITEM # 474 & 52-12-00/601.

Part: PUMP — LOW PRESSURE (HYD SYSTEM) · airframe 29,298 hrs · 18,102 cycles

EMERGENCY DECLARED. GREEN ENG HYD PUMP 2 LO PRESSURE FOLLOWED ECAM ,SELECTED OFF , RESULTED IN LOSS OF GREEN HYD FLUID RESULTED IN GREEN HYD FALURE. NUMBER 2 GREEN ENGINE DRIVEN HYDRAULIC PUMP REPLACEMENT COMPLETE IAW AMM 29-11-31. OPS CHECK, LEAK CHECKS GOOD. OK FOR SERVICE.

Part: BLEED AIR SYS — ODOR (APU) · airframe 29,292 hrs · 17,782 cycles

UPON TURNING ON APU BLEED AIR, NOTICED A STRONG FUEL ODOR COMING OUT OF THE VENTILATION AREAS IN COCKPIT AND SUPERNUMARY COMPARTMENT. T/S AND FOUND TORQUE MOTOR ON APU FUEL CONTROL LEAKING FUEL INTO THE APU INTAKE. R/R TORQUE MOTOR SEAL PER CMM 49-31-61. OPS AND LEAK CHECK GOOD. NO FUEL SMELL PRESENT. PLACARD REMOVED.

Part: LIFE VEST — EXPIRED (ZONE 200) · airframe 73,444 hrs · 25,012 cycles

FLT DECK RT SUPERNUMERARY SEAT CREW LIFE VEST EXPIRED. REMOVED AND REPLACED RT SUPERNUMERARY SEAT CREW LIFE VEST PER AMM 25-62-00.

Part: LIGHT — INOPERATIVE (ZONE 200) · airframe 65,237 hrs · 10,366 cycles

DOOR 1L, EMERGENCY EXIT SIGN LIGHT INOPERATIVE. C/W AMM33-51-05-962-031, REV. 137, OPC O.K.

Part: CRASH AXE — DAMAGED (ZONE 200) · airframe 29,150 hrs · 4,240 cycles

MAIN DECK CRASH AXE IS CORRODED AND DAMAGED. REPLACED CRASH AXE IAW AMM 25-63-04.

Part: LIGHT — INOPERATIVE (ZONE 200) · airframe 76,266 hrs · 26,278 cycles

EXIT LIGHT IS COMING OUT OF ITS SOCKET NEAR MAIN ENTERANCE DOOR CAREFULLY PUSHED THE LENS INTO ITS POSITION IAW AMM 33-51-01-402-030 4(B)(3)

Part: BULB — BURNED OUT (ZONE 200) · airframe 43,041 hrs · 24,508 cycles

FLIGHT DECK EXIT SIGN LIGHTS BURNED OUT. REPLACED THE BULBS IAW AMM 33-51-01, OPS CHECK GOOD.

Part: INDICATOR — INTERMITTENT (ZONE 800) · airframe 28,144 hrs · 17,220 cycles

FLASHING LIGHT FOR EMG SLIDE ARMED NOT WORKING . R & R SLIDE WARNING LIGHT IAW AMM 52-73-11. ASPSU BITE CHKD GOOD IAW AMM 52-73-00/0501. EMERGENCY WARNING LIGHT TEST GOOD IAW AMM 52-73-11/401.

Part: LAMP — INOPERATIVE (ZONE 200) · airframe 27,790 hrs · 17,307 cycles

EMERGENCY EXIT LIGHT HAS 2 EA LAMPS INOP. RELAMPED 2 EA EMER EXIT LIGHT LAMPS W/REF TO MM 33-51-13 PB 0401. OPS CK GOOD.

Part: FORMER — CRACKED (ZONE 600) · airframe 69,295 hrs · 23,159 cycles

CRACKED FORMER, RT WING FIXED L/E NOSE BEAM SUPPORT STRUCTURE AT STA OSS 499. REMOVE DAMAGE FORMER IAW SRM 51-40-02-0G, REV 95. INSTALL NEW FORMER IAW SRM 51-40-02-0G, REV 95 AND DWG 114T2161, SH 1, REV E, & EO SREO-50900-REQ001, REV 2.

Part: SPOILER SYS — FAULTED · airframe 24,880 hrs · 16,751 cycles

ON TOUCHDOWN SPOILERS DEPLOYED NORMALLY, BUT IMMEDIATELY RETRACTED. REQUIRED MANUAL RE-DEPLOYMENT & MANUAL BRAKES. STARTED REMOVAL OF SPEED BRAKE MECHANISM PER AMM 27-62-02 UP TO AND INCLUDING STEP H2.

Part: WINDOW — SCRATCHED (ZONE 200) · airframe 36,100 hrs · 22,127 cycles

FO€™S R2 WINDOW SCRATCHED HEAVILY AND IT IMPAIRS CREWS VIEW DURING GROUND OPS WITH BRIGHT LIGHT ON RAMP REPLACED WINDOW REF AMM 56-11-02.

Part: FAIRING — DEBONDED (ZONE) · airframe 69,295 hrs · 23,159 cycles

DEBONDED SKIN, RT AFT WING TO BODY FAIRING EXTERNAL, PANEL 198CR. IAW SRM 52-40-02-2R-4, REF SRM 51-70-17-0G-0, & SRM 51-70-14-0G-0, REV 95. REMOVED DEBONDED MATERIAL & CLEANED. BONDED THE REPAIR PLIES WITH RESIN CURED AT 200F FOR 220 MINUTES WITH MINIMUM VACUUM OF 22 IN/HG. BONDED THE FOIL WITH RESIN CURED AT 200F FOR 220 MINUTES WITH MINIMUM VACUUM OF 22 IN/HG IAW SRM 52-40-02-2R-4, REF SRM 51-70-17-0G-0, & SRM 51-70-14-0G-0, REV 95.

Part: FORMER — CRACKED (ZONE 500) · airframe 69,295 hrs · 23,159 cycles

CRACKED FORMER, LT WING OTBD FXD LE NOSE SKIN SUPPORT, OSS 499.60. INSTALLED A NEW FORMER IAW SRM 51-40-02-0G REV.95 AND DWG 114T2161 SH 1 REV. E AND EO SREO-50900-REQ001 REV2.

Part: FLOOR PANEL — CRACKED (ZONE 100) · airframe 69,295 hrs · 23,159 cycles

FOUND AFT CARGO FLOOR PANEL CRACKED. IAW SRM 53-00-50-2R-0 REV. 95, CUT OUT THE DAMAGE AND CLEANED. BONDED THE REPAIR PLIES WITH RESIN CURED AT 170F FOR 2 HOURS WITH A MINIMUM VACUUM OF 20 IN/HG IAW SRM 53-00-50-2R-0, REV 95.

Part: COWLING — DENTED (ZONE 400) · airframe 69,295 hrs · 23,159 cycles

DENTED NR 2 ENG NOSE COWL INLET AT 7 & 5 O'CLOCK POSITIONS. CUT OUT THE DAMAGE & CLEAN, MEASURE THE CUT OUT ( (1) DIA : 1", 15.5" FROM FWD EDGE AT 7 O'CLOCK , (2) DIA : 1" , 15.3" FROM FWD EDGE AT 5 O'CLOCK ON THE INNER BARREL OF NR 2 ENG INLET COWL. BONDED THE SPACER WITH FILM ADHESIVE CURED AT 250F FOR 2 HOURS AND FILL THE CUT OUT WITH ADHESIVE CURED AT 200F FOR 1 HOUR IAW SRM 54-15-01-2R-3, REV 95. CONFIRM THAT THE ENGINE NACELLE IS ACOUSTICALLY COMPLIANT IAW SRM 54-00-00-2R-0, REV 95.

Part: CAP — CRACKED (ZONE 500) · airframe 57,187 hrs · 20,803 cycles

CRACK CAP , L/H WING T/E OUTBD FLAP INBD END CAP. (REPAIR). I.A.W UPS SREO-70175-REQ001 REV. 1 PERFORM REPAIR AS BELOW. REMOVED THE CRACKED MATERIALS AND CLEANED. MEASURED DAMAGE AREA ( L : 1.1", W : 0.1", 6.5" FROM AFT EDGE , AT INBD EDGE ). BOND THE REPAIR PLIES WITH RESIN CURED CONDITION CHECK IS SATISFACTORY.

Part: BUSHING — MIGRATED (NR 7 SPOILER) · airframe 57,187 hrs · 20,803 cycles

NR 7 SPOILER ACTUATOR , ROD END BOLT BEARING MIGRATION. REPLACED. IAW CMM:57-70-11 REV.43 REPAIR:2-1 PAGE:601 STEP:3, COMPLETED NEW BUSHING REPLACEMENT OF THE NO.7 SPOILER ACTUATOR ROD END.

Part: BUSHING — MIGRATED (ZONE 500 SPOILER) · airframe 57,187 hrs · 20,803 cycles

MIGRATION - BUSHING , LT WING T/E OTBD SPOILER NR 1 UPPER. I.A.W AMM 27-61-02-024-001 REV.148 DISCONNECT LT WING NR 1 SPOILER PCA ROD END. IAW CMM 57-70-51, REV.38, REPAIR 2-1, PAGE 601, STEP 2, COMPLETED NEW BUSHING REPLACEMENT OF THE NR 1 SPOILER ACTUATOR ROD END.

Part: SHAFT — CORRODED (ZONE 500 FLAP) · airframe 69,295 hrs · 23,159 cycles

FOUND LT WING OTBD FLAP NR 2 SUPPORT CRANK ARM AND INPUT SHAFT CORROSION. IAW AMM 27-51-21-024-001, REV 148, REMOVED LT WING NR 2 FLAP ACTUATOR CRANK ARM & INPUT SHAFT. IAW AMM 27-51-21-424-032, REV 148. INSTALLED LT WING NR 2 FLAP ACTUATOR CRANK ARM & INPUT SHAFT WITH NEW PARTS.

Part: CONTROLLER — UNSERVICEABLE (OVRHEAT DETECTOR) · airframe 27,421 hrs · 16,226 cycles

AIR TURN BACK, ENG 1 BLEED LEAK RESULTING IN AIR TURN BACK FOUND LT WING MFA ILLUMINATED ON MX PANEL. INSPECTED WING PNEUMATIC JOINTS FROM PACK BAY OUT TO LT WING TIP. NO LEAKS NOTED IAW TSM 36-22-00/401. RAN NR 1 ENGINE, NO LEAK INDICATIONS. CHANGED NR 2 OVERHEAT DETECTION CONTROLLER (13HF) OPS CHKD GOOD.

Part: WEDGE — DAMAGED (ZONE 500 FLAP) · airframe 57,187 hrs · 20,803 cycles

RIGHT OUTBOARD FLAP, INBOARD T/E WEDGE UPPER AND LOWER SKIN DAMAGE. (REPAIR). I.A.W UPS SREO-70175-REQ001 REV. 1 PERFORM REPAIR AS BELOW. REMOVED THE CRACK MATERIALS AND CLEANED. MEASURE THE DAMAGE AREA ( L : 0.8", W : 0.05", 6" FROM AFT EDGE , AT INBD EDGE ). BOND THE REPAIR PLIES WITH RESIN CURED. CONDITION CHECK IS SATISFACTORY.

Part: FLOOR PANEL — CRACKED · airframe 69,295 hrs · 23,159 cycles

CRACKS ON THE FLOOR PANEL NO. 251XFF (P/N 146T5869-89) IN THE MAIN DECK CARGO COMPARTMENT. REMOVED THE FLOOR PANEL IAW AMM 53-01-06-000-801 REV. 148. IAW AMM 53-01-06-400-801 REV.148. INSTALLED THE FLOOR PANEL 251XFF.

Part: BRACKET — CHAFED (ZONE 400) · airframe 57,187 hrs · 20,803 cycles

CHAFED BRACKET, NR 1 ENG LT LOWER T/R COWL FWD CLOSURE DOOR T/E ATTACHED. REMOVED DAMAGE BRACKET IAW SRM 51-40-02-0G, REV 55. INSTALLED A NEW BRACKET IAW SRM 51-40-02-0G, REV.55, AND IPC 78-32-21 REV.96.

Part: ANGLE — CRACKED (ZONE 100) · airframe 69,295 hrs · 23,159 cycles

THE BULK CARGO OTBD ANGLE AT BS 1578, RBL 80 IS CRACKED. REMOVED DAMAGE ANGLE IAW SRM 51-40-02-0G REV.95. INSTALL NEW ANGLE IAW SRM 51-40-02-0G REV.95 AND DWG 146T5650 SH 5 REV.C.

Part: ANGLE — CRACKED (ZONE 100) · airframe 69,295 hrs · 23,159 cycles

THE BULK CARGO OUTBOARD ANGLE AT BS 1578 LBL 80 IS CRACKED. REMOVED DAMAGE ANGLE I.A.W SRM 51-40-02-0G REV.95. INSTALLED NEW ANGLE IAW SRM 51-40-02-0G, REV.95 AND DWG 146T5650, SH 5, REV C.

Part: ANGLE — CRACKED (ZONE 100) · airframe 69,295 hrs · 23,159 cycles

THE BULK CARGO INBOARD ANGLE AT BS 1578, LBL 80 IS CRACKED. REMOVED DAMAGE ANGLE IAW SRM 51-40-02-0G REV.95. INSTALL NEW ANGLE IAW SRM 51-40-02-0G, REV 95 AND DWG 146T5650, SH 5, REV C.

Part: ANGLE — CRACKED (ZONE 100) · airframe 69,295 hrs · 23,159 cycles

FOUND THE FIRE DETECTION LOOP FASTENER STRIP CRACKED AT BS 1562 LBL 76 IN BULK CARGO COMPARTMENT. REMOVED DAMAGE ANGLE I.A.W SRM 51-40-02-0G REV.95. INSTALL NEW ANGLE I.A.W SRM 51-40-02-0G REV.95 AND BOEING DWG NO: 218T4100 SH 3 REV: B AND BOEING DWG NO: 218T4004 SH 16 REV: D.

Part: RING — CRACKED (ZONE 400) · airframe 69,295 hrs · 23,159 cycles

FOUND NR 1L T/R AFT CASCADE SUPPORT RING CRACK.

Part: RING — CRACKED (THRUST REVERSER) · airframe 69,295 hrs · 23,159 cycles

FOUND NR 1R T/R AFT CASCADE SUPPORT RING CRACK. COMPLETED THRUST REVERSER AFT CASCADE SUPPORT RING (ACSR) REPLACEMENT I.A.W EO-87822-REQ01R-REPL REV4.

Part: SKIN — CRACKED (ZONE 200) · airframe 69,295 hrs · 23,159 cycles

MAJOR REPAIR, SKIN , DURING PERFORM T/C : EO-24301-JIC001 FOUND SKIN CRACK AT BS 1725.5 , S-7R.

Part: SKIN — DEBONDED (ZONE 500) · airframe 57,187 hrs · 20,803 cycles

DISBOND - SKIN , LT WING T/E OUTBD FLAP INBD LWR. (REPAIR). IAW SRM 57-53-01-2R-1 REFER TO SRM 51-70-07-0G-0 REV.55. PERFORM REPAIR AS BELOW STEP:1.1 REMOVED THE DISBOND MATERIALS AND CLEANED. MEASURE THE DAMAGE SIZE AND LOCATION (L:4.5", W:2", 1.3" FROM AFT EDGE, 0.5" FROM INBD EDGE). BOND THE REPAIR PLIES WITH FILM ADHESIVE CURED AT 260F FOR 130 MINUTES AND KEEP A MINIMUM VACUUM OF 22 IN/HG.CONDITION CHECK IS SATISFACTORY.

Part: WEDGE — DEBONDED (NR 4 SLAT) · airframe 69,295 hrs · 23,159 cycles

DEBONDED SKIN , LT WING NR 4 SLAT TE WEDGE INBD. RII COMPLETED FOR OK TO INSTALL CHECK

Part: ANTENNA — ERODED (ZONE 100) · airframe 69,295 hrs · 23,159 cycles

FOUND V.S.T HF ANTENNA (321E) EROSION. REMOVE THE EROSION MATERIALS AND CLEAN IAW SRM 55-30-01-2R-6 REFER TO SRM 51-70-07-0G-0 REV. 95. BOND THE REPAIR PLIES WITH FILM ADHESIVE CURED AT 260°F FOR 130 MINUTES WITH MINIMUM VACUUM OF 22 IN/HG.

Part: FORMER — CRACKED (ZONE 600) · airframe 57,187 hrs · 20,803 cycles

RIGHT WING OUTBOARD L/E NOSE FORMER CRACK , OSS 499 (NR 8 SLAT OUTBOARD SEAL DOOR UPPER AREA). REMOVED DAMAGE FORMER IAW SRM 51-40-02-0G, REV 55. INSTALLED A NEW FORMER IAW SRM 51-40-02-0G, REV 55 AND DWG 114T2161, SH 3, REV B, AND SREO-50900-REQ001, REV 2.

Part: BRACKET — CHAFED (ZONE 400) · airframe 57,187 hrs · 20,803 cycles

CHAFED BRACKET , NR 1 ENG RT T/R COWL LOWER FWD CLOSURE DOOR T/E ATTACHED. REMOVED DAMAGE BRACKET IAW SRM 51-40-02-0G, REV.55. INSTALLED A NEW BRACKET IAW SRM 51-40-02-0G, REV.55 AND IPC 78-32-22, REV 96.

Part: SPLICE PLATE — CORRODED (ZONE 300) · airframe 31,943 hrs · 20,896 cycles

UPON REMOVAL OF RT ELEVATOR TIP TRAILING EDGE WEDGE FOUND CORROSION ON UPPER SPLICE PLATE AND UPPER CONDUCTIVE FRAME. VERIFIED STEPS 4, 5 AND 6