N428FE

Part: STRUCTURE — DAMAGED (NR 6 SPOILER) · airframe 40,903 hrs · 27,646 cycles

LT WING NR 6 SPOILER HAS HOLE APPROX .25W X .56L X .25D. LOCATED 12.125" FROM OTBD EDGE AND 21" FROM T/E OF SPOILER REPAIRED ONE HOLE MEASURING .25W X .56L X .25D ON NR 6 SPOILER USING RESIN & CARBON FIBER IAW SRM 57-76-11, PAR 12C. COMPLIED WITH EA 6-5750-160173, PT 1.

Part: STRUCTURE — CRACKED (CENTER WING) · airframe 40,052 hrs · 27,074 cycles

ONE CRACK INDICATION EXCEEDS 25 PERCENT FSH WAS FOUND AT NR 63 FASTENER HOLE OF RT CENTER WING, REF NTM PART 6 51-10-01 PROCEDURE A RECORD SHEET FIG 611 AND NTM PART 6-57-10-12. CRACK REAMED TO THE NEXT NOMINAL DIAMETER 0.561" IAW EO 6-5710-7-3322 PART 1. NDI COMPLETED, NO CRACK INDICATION FOUND IAW EO 6-5710-7-3322 PART 1. INSTALLED NEW FASTENERS IAW EO 6-5710-7-3322 PART 1. THE REPAIR EVALUATED PER G.M.M. 6-2-100 AND CLASSIFIED AS MAJOR.

Part: TEE FITTING — CRACKED (CENTER WING) · airframe 40,052 hrs · 27,074 cycles

ONE CRACK INDICATION EXCEEDS 25 PERCENT FSH, WAS FOUND AT NR 63 FASTENER HOLE OF LT CENTER WING REF PART 6, NTM 51-10-01 PROCEDURE A, RECORD SHEET FIG 610 AND NTM PART 6 57-10-12. REPAIR EVALUATED IAW GMM 6-2-100 AND CLASSIFIED AS MAJOR.

Part: STRUCTURE — CRACKED (CENTER WING) · airframe 40,052 hrs · 27,074 cycles

ONE CRACK INDICATION EXCEEDS 25 PERCENT FSH WAS FOUND AT NR 30 FASTENER HOLE OF RT CENTER WING, REF NTM PART6 51-10-01, PROCEDURE A, RECORD SHEET FIG 612 AND NTM PART6 57-10-12. CRACK REAMED TO THE NEXT NOMINAL DIAMETER SIZE 0.561" IAW EO 6-5710-7-3322 PART 1. NDI WAS COMPLETED. NO CRACK INDICATION WAS FOUND IAW EO 6-5710-7-3322 PART 1. INSTALLED NEW FASTENERS IAW EO 6-5710-7-3322 PART 1. THE REPAIR EVALUATED PER G.M.M. 6-2-100 AND CLASSIFIED AS MAJOR. .

Part: STRUT — CORRODED (TAIL CONE) · airframe 40,052 hrs · 27,074 cycles

FUSELAGE TAIL SECTION FR 86, 2EA CROSS STRUTS CORRODED AT STR15 LT AND RT.

Part: CROSSBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 40,052 hrs · 27,074 cycles

FUSELAGE TAIL SECTION FR84, 1EA CROSS STRUT GOT CORROSION AT STR14 LT 1. REMOVED THE CROSS STRUT IAW SRM 51-40-20 AND 51-40-21. INSTALLED NEW CROSS STRUT WITH FASTEN REF SRM 51-40-21. THE REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100.

Part: STRUCTURE — CRACKED (NR 2 NACELLE) · airframe 40,052 hrs · 27,074 cycles

NR 2 ENGINE INBD CORE COWL OUTER SURFACE FOUND 1EA CRACKED POSITION ABOUT 7 O'CLOCK. REPAIRED PER E.O. 6-5440-149014. REPAIR, PER G.M.M. 6-2-100, CLASSIFIED AS MINOR.

Part: SKIN — DENTED (RT WING TE FLAP) · airframe 40,052 hrs · 27,074 cycles

RT WING OTBD FLAP LOWER SURFACE FOUND LIGHTLY DENTS POSITION NEAR T/E AREA. THE DIMENSION OF THE DAMAGED AREA 4.6"L X 2.5 W X 0.063" MAX DEPTH. THE AREA IS OVER THE LIMITS IAW SRM57-53-12 (TOOL:TS 482). CUT THE DAMAGED AREA AND REPAIRED BY THE DOUBLER AND FASTENERS REFER TO SRM 57-53-12. THE REPAIR EVALUATED IAW GMM 6-2-100 AND CLASSIFIED AS MINOR. THE DIMENSION OF THE DAMAGED AREA 4.6"L X 2.5"W X 0.063" MAX DEPTH. THE AREA IS OVER THE LIMITS I.AW SRM 57-53-12 (TOOL: TS482). CUT THE DAMAGED AREA AND REPAIRED BY THE DOUBLER AND FASTENERS REFER TO SRM 57-53-12. THE REPAIR EVALUATED GMM 6-2-100 AND CLASSIFIED AS MINOR.

Part: SKIN — CHAFED (THRUST REVERSER) · airframe 40,052 hrs · 27,074 cycles

NR 2 ENGINE OTBD THRUST REVERSER UPPER SIDE T/E AREA FOUND SKIN CHAFED. ACCOMPLISHED THE EA 6-7830-149011. REPAIR EVALUATED IAW GMM 6-2-100 AND CLASSIFIED AS MINOR.

Part: SKIN — CORRODED (LT WING) · airframe 40,052 hrs · 27,074 cycles

LT WING OUTER OVERWING REFUEL ADAPTOR REMOVED, FOUND CORROSION AT TOP SKIN SHROUND (FROM 5 TO 11 O'CLOCK POSITION ). ACCOMPLISHED EA 6-5720-149013. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100. CLEANED UP IAW AMM 28-11-00.

Part: SKIN — CHAFED (LT WING) · airframe 40,052 hrs · 27,074 cycles

LT WING OUTER OVERWING REFUEL ADAPTOR REMOVED. FOUND CORROSION AT TOP SKIN SHROUND (FROM 5 TO 11 O'CLOCK POSITION ). ACCOMPLISHED EA 6-5730-149017. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: FITTING — CRACKED (FUSELAGE) · airframe 40,052 hrs · 27,074 cycles

1EA CRACK (.2500", .1250") WAS FOUND AT NLG DOOR ACTUATOR UPPER ATTACHMENT RT FITTING. REMOVED NLG DOOR ACTUATOR R/H UPPER FITTING. MATCHED DRILL HOLES FROM OLD FITTING TO NEW FITTING IAW EO 6-5340-7-5001 A5. IAW EO 6-5340-7-5001 A5 PT2, REPLACEMENT OF NLG DOOR ACTUATOR RT UPPER FITTING ACCOMPLISHED EO 6-5340-7-5001 A5 PT2, AND CHECKED CONDITION NORMAL. IAW EO 6-5340-7-5001 A5 PT5, REPLACEMENT OF RT NLG ACTUATOR ATTACHMENT BOLT WITH LOCKING PLATE. ACCOMLISHED EO 6-5340-7-5001 A5 PT5. CONDITION CHECKED NORMAL. REPAIR CLASSIFIED AS MINOR PER G.M.M. 6-2-100.

Part: RIB — CRACKED (LT WING) · airframe 40,052 hrs · 27,074 cycles

LT WING NR 6 SPOILER INBD HINGE SUPPORT RIB GOT CRACKED AT LWR CORNER . REPAIRED IAW SRM 57-51-11 FIT.203. CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: SWITCH — FAULTED (LE FLAPS) · airframe 39,483 hrs · 26,683 cycles

KRUGER FLAP WOULD NOT RETRACT AFTER TAKEOFF OR EXTEND FOR LANDING. FOUND EXTEND SWITCH FAULTING IAW TSM 27-80-12. R & R SWITCH IAW AMM 27-89-11-04-0. OPS CKD GOOD.

Part: ENGINE — LEAKING (NR 1) · airframe 39,447 hrs · 26,652 cycles

DURING CLIMB OUT NOTICED OIL QTY NR 1 ENGINE WAS AT 4 QTS. REDUCED POWER TO 60 PERCENT N1, QTY CONTINUED TO DROP TO 0 QTS OVER NEXT 10 MINUTES. PRESSURE GOOD FOR ANOTHER 5-10 MINUTES THEN IT BEGAN TO DROP. FINALLY SHUT ENGINE DOWN A FL220. ENGINE CONTINUED TO WINDMILL, DID NOT SEIZE. REMOVED AND REPLACED NR 1 ENGINE PER WORK CARD.

Part: CONTROLLER — FAILED (CABIN PRESSURE) · airframe 39,325 hrs · 26,553 cycles

ACFT WRITTEN UP PREVIOUSLY ON 21-31-02A ACFT PRESSURIZED ON GROUND, FOLLOWED MEL PROCEDURES, HOWEVER, AFTER TAKEOFF. COULD NOT GET MANUAL PRESS AMBER ARROW TO EXTINGUISH. RETURNED TO DEPARTURE. R&R NR 1 CABIN PRESSURE CONTROLLER 105HM AS PER A310-200 M/M 21-31-11-04. PERFORMED CABIN PRESSURE CONTROL AND MONITORING ADJUSTED AND TESTED AS PER M/M 21-31-00-5 STEP C.2. (G).OPS CHECKED GOOD.OK FOR SERVICE

Part: PRESSURE SWITCH — MALFUNCTIONED (FUEL SYSTEM) · airframe 38,399 hrs · 25,833 cycles

FUEL CLOG LT NR 2 ENG CAME ON AFTER T/O STAYED ON FOR A WHILE/WENT OUT AFTER 4 MINUTES. REMOVED AND REPLACED FUEL PRESSURE DIFFERENTIAL PRESSURE SWITCH IAW MM 73-34-11-4-04. OPS AND LK CK GOOD.

Part: SPAR — CRACKED (ZONE 100) · airframe 38,333 hrs · 25,791 cycles

CENTER WING FRONT SPAR; UPPER LEFT FISH PLATE HAS A CRACK INDICATION AT THE FWD, UPPER INBD HOLE COMMON TO THE SPAR. REMOVED FITTING REF A310-200 SRM 51-40-21, PG 7. ACCOMPLISHED BHEC ON HOLES REF NTM 57-10-25 PART 6. REMOVED AND INSTALLED 4 FASTENERS ON THE SIDE OF THE FUSELAGE; 2 LEFT SIDE AND 2 RIGHT SIDE FOR ACCESS REF A310-200 SRM 51-40-21; PG 7. REAMED HOLE, FABRICATED AND INSTALLED REPAIR BUSHINGS AND 1 FASTENER REF EA 6-5710-127901

Part: SPAR — CRACKED (WING BOX) · airframe 38,333 hrs · 25,791 cycles

CENTER WING FRONT SPAR UPPER RIGHT FISH PLATE HAS A CRACK INDICATION AT THE FWD, UPPER INBD HOLE COMMON TO THE SPAR. REMOVED AND RE-INSTALLED FITTING REF A310-200 SRM 51-40-21, PG 7. ACCOMPLISHED BHEC ON HOLES REF NTM 57-10-25 PART 6. REMOVED AND INSTALLED 4 FASTENERS; 2 LEFT SIDE AND 2 RIGHT SIDE OF THE FUSELAGE; REF A310-200 SRM 51-40-21; PG 7. REAMED HOLE, FABRICATED AND INSTALLED REPAIR BUSHINGS AND 1 FASTENER REF EA 6-5710-127901 "WINGS, AD 98-26-01 - EO 6-5710-7-3324 LT AND RT WING RIB 1 INSPECTION AT FRAME 40 INCHES.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 38,333 hrs · 25,791 cycles

MAIN CABIN FLOOR PANEL 231 HH IS DAMAGED. FABBED NEW PANEL PER FEDEX DWG SRZ 25-005, REV "G".

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 38,333 hrs · 25,791 cycles

MAIN CABIN FLOOR PANEL 211 GG IS DAMAGED. FABBED REPLACEMENT PANEL PER FEDEX DWG SRZ 25-005, REV "G".

Part: SHEAR TIE — WORN (ZONE 200) · airframe 38,333 hrs · 25,791 cycles

FRAME 44, LEFT FOOT FITTING NEEDS TO BE REPLACED DUE TO THE FASTENER HOLES BEING WORN OUT OF LIMITS. REMOVED & REPLACED THE FRAME FOOT FITTING IAW A310-200 SRM 51-40-21.

Part: FRAME — CRACKED (ZONE 100) · airframe 38,333 hrs · 25,791 cycles

FRAME 44, RIGHT LOWER SECTION NEEDS TO BE REPLACED DUE TO THE FASTENER HOLES BEING OUT OF LIMITS. REMOVED FRAME IAW SRM 51-40-21; PGS 6 AND 7. LOCATED AND DRILLED FRAME IAW SRM 51-72-10. INSTALLED IAW SRM 51-40-21 PGS 6 AND 7. APPLIED CIC IAW SRM 51-23-20.

Part: STIFFENER — CRACKED (ZONE 600) · airframe 38,333 hrs · 25,791 cycles

RIGHT WING FLAP FAIRING 633 CB FWD CENTER STIFFENER ANGLE IS CRACKED. REMOVED STIFFENER IAW A310-200 SRM 51-40-21; PG 22. INSTALLED A NEW STIFFENER IAW A310-200 SRM 51-40-21; PG 9; PARAGRAPH B. THE STIFFENER WAS FABRICATED ON N/R N01416 23416.

Part: FRAME — CRACKED (ZONE 100) · airframe 38,333 hrs · 25,791 cycles

FRAME 44, LEFT LOWER SECTION NEEDS TO BE REPLACED DUE TO FASTENERS HOLES BEING OUT OF LIMITS REMOVED FRAME IAW SRM 51-40-21; PGS 6 AND 7. LOCATED AND DRILLED FRAME IAW SRM 51-72-10. INSTALLED IAW SRM 51-40-21 PGS 6 AND 7. APPLIED CIC IAW SRM 51-23-20.

Part: WEB — CRACKED (FLAP FAIRING) · airframe 38,333 hrs · 25,791 cycles

LEFT WING FLAP FAIRING 533 CB HAS A CRACKED WEB. REMOVED AND REPLACED WEB IAW A310-200 SRM 51-40-21; PG 7. THE WEBS WERE FABRICATED ON N/R N01426/23426 AND N/R N01427/23427.

Part: WEB — CRACKED (ZONE 100) · airframe 38,333 hrs · 25,791 cycles

FWD PIT; 3 INCH AFT OF FRAME 37 AT STRINGER 44LTHE VERTICAL BILGE CLOSE OUT PANEL WEB IS CRACKED ON THE AFT SIDE OF THE DUCT. REMOVED WEB FROM FRAME 37 AT STRINGER 44L IAW SRM 51-40-21. DISPLACED AIR DUCT RUNNING THROUGH THE WEB IAW SRM 51-40-21. FORMED NEW WEB REF DWG 14A21277653; ISSUE "C". LOCATED AND DRILLED HOLES ON THE NEW WEB IAW SRM 51-40-44. ALODINED IAW SRM 51-21-10. PRIMED AND TOPCOATED IAW SRM 51-23-10. INSTALLED WEB IAW SRM 51-40-21.

Part: STRINGER CLIP — CRACKED (ZONE 200) · airframe 38,333 hrs · 25,791 cycles

MAIN CABIN UPPER CLIP IS CRACKED AT FRAME 43, STRINGER 26R. REMOVED AND REPLACED CLIP IAW A310-200 SRM 51-40-21, PARA 5 AND 6.

Part: PAN — CRACKED (ZONE 100) · airframe 38,333 hrs · 25,791 cycles

AFT PIT FWD LEFT SIDE PDU MOUNT PLATE HAS CRACKS AT FRAME 54.2. REMOVED PDU IAW AMM 25-52-26-4. REMOVED PDU TRAY IAW SRM 51-40- 21; PARAGRAPH 6. REMOVED FRAME IAW A310-200 SRM 51-40-21; PARAGRAPH 5. INSTALLED NEW PAN ASSY P/N A2577260600600 INTO FRAME IAW SRM 51-40-21; PARAGRAPH 6. INSTALLED FRAME IAW SRM 51-40-21; PARAGRAPH 5. INSTALLED PDU IAW AMM 25-52-26-4. PERFORMED OPS CHECK IAW AMM 25-52-26-4.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 38,333 hrs · 25,791 cycles

MAIN CABIN FLOOR PANEL UPPER SURFACE IS CRACKED AT FRAME 49, RBL 34 INCHES. FABRICATED NEW PANEL 242 ZJ USING THE OLD FLOOR PANEL AS A TEMPLATE. POTTED EDGES, INSTALLED INSERTS, APPLIED NON SKID AND PART MARKED IAW DWG SRZ 25-005, REV "G".

Part: PAN — CRACKED (ZONE 100) · airframe 38,333 hrs · 25,791 cycles

AFT PIT POWERED ROLLER AT FRAME 54.2 RT TRAY IS CRACKED. REMOVED PDU IAW AMM 25-52-26-4. REMOVED PDU TRAY IAW SRM 51-40-21; PARAGRAPH 6. REMOVED FRAME IAW SRM 51-40-21; PARAGRAPH 5. INSTALLED PDU TRAY IAW SRM 51-40-21; PARAGRAPH 6. INSTALLED FRAME IAW SRM 51-40-21; PARAGRAPH 5. INSTALLED PDU IAW AMM 25-52-26-4. PERFORMED OPS CHECK IAW AMM 25-52-26-4.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 38,333 hrs · 25,791 cycles

MAIN CABIN FLOOR PANEL UPPER SURFACE IS CRACKED AT FRAME 50; RBL 37 INCH FABRICATED NEW PANEL 242 ZJ USING THE OLD FLOOR PANEL AS A TEMPLATE. POTTED EDGES, INSTALLED INSERTS, APPLIED NON SKID AND PART MARKED IAW DWG SRZ 25- 005; REV "G".

Part: HINGE — CRACKED (E/E DOOR) · airframe 38,333 hrs · 25,791 cycles

AVIONICS COMPARTMENT DOOR 121 BL RIGHT HINGE ARM IS CRACKED IN THE RADIUS. REMOVED DOOR IAW AMM 52-41-14. REPAIRED DOOR IAW IAW SRM 52-41-14. RE-INSTALLED DOOR & ADJUSTED IAW AMM 52-41-14. OPS CHECKED DOOR AND WARNING SYS IAW AMM 52-41-14. OPS CHECKED GOOD.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 38,333 hrs · 25,791 cycles

FLOOR PANEL 241 RT NEEDS FABBED. FABRICATED NEW PANEL 241 RJ USING THE OLD FLOOR PANEL AS A TEMPLATE; POTTED EDGES; INSTALLED INSERTS; APPLIED NON SKID AND PART MARKED IAW DWG SRZ 25-005; REV "G".

Part: SHIM — MISALIGNED (ZONE 100) · airframe 38,333 hrs · 25,791 cycles

MARKER ANTENNA REQUIRES A SHIM BETWEEN THE FWD END OF THE ANTENNA AND FUSELAGE DUE TO A REPAIR DOUBLER INSTALLED AT THE AFT SECTION. FABRICATED AND INSTALLED SHIM IAW FEDEX EA 6-3435-123700 "NAVIGATION MARKER ANTENNA INSTALLATION BETWEEN FRAME 37 AND FRAME 38".

Part: FRAME — CRACKED (E/E DOOR) · corrosion level 2 · airframe 38,333 hrs · 25,791 cycles

E/E BAY DOOR 121 BL, THE BRAKE FORMED SECTION A52110744202 IS CRACKED. REMOVED FORMED SECTION IAW SRM 51-40-21, PARA 6. MATERIAL ID, FABBED DRILLED AND LOCATED IAW DWG A52110744202 AND SRM 51-44-40. ALODINED IAW SRM 51-21-10. PRIMED AND PAINTED IAW SRM 51-23-10. INSTALLED IAW SRM 51-40-21, PARA 6. PART MARKED IAW GMM 7-0-1000.

Part: ANGLE — CRACKED (ZONE 100) · airframe 38,333 hrs · 25,791 cycles

AVIONICS COMP DOOR 121 BL, AFT UPPER FLOOR SUPPORT ANGLE IS CRACKED. REMOVED PLATE IAW SRM 51-40-21. DRILLED AND LOCATED NEW PLATE IAW SRM 51-40-44 AND DWG NR A521110744. INSTALLED NEW PLATE P/N A52110744 IAW SRM 51-40-21.

Part: STRUCTURE — GOUGED (HORIZONTAL STAB) · airframe 38,333 hrs · 25,791 cycles

RIGHT HORIZONTAL STAB TIP NR 342 AB EROSION STRIP IS GOUGED. APPLIED WIRE MESH TO THE EXTERIOR SURFACE OF THE RIGHT STAB TIP PANEL NR 342 AB IAW SRM 55-14-11 AND EA 6-5510-123691. INSTALLED EROSION SHIELD IAW DWG 36-A551-76100.

Part: FLOOR PANEL — BROKEN (ZONE 200) · airframe 38,333 hrs · 25,791 cycles

MAIN CABIN FLOOR PANEL 241 NK IS BROKEN. FABRICATED NEW PANEL NR 541 NK USING THE OLD PANEL AS A TEMPLATE; POTTED EDGES. INSTALLED INSERTS, APPLIED NON-SKID TAPE AND PART MARKED PANEL IAW DWG SRZ25-005; REV "G".

Part: SKIN — CORRODED (ZONE 200) · corrosion level 2 · airframe 38,333 hrs · 25,791 cycles

LEFT UPPER FUSELAGE AT FR 84 FROM STR 6 TO STRI 7; CHECK FOR CORROSION UNDER PAINT; THERE IS TRASH AND DEBRIS IN THE PAINT. REMOVED FASTENERS TO FOM IAW A310-200 SRM 51-40-21; PG 7. REMOVED CORROSION IAW SRM 51-24-10 AND WAS FOUND TO BE OUT OF LIMITS PER SRM 53-19-12. ACCOMPLISHED HFEC INSP OF REWORKED AREA PER NTM 51-10-01 AND FOUND 1 HOLE CRACKED. OVERSIZED HOLE TO 0.250 IAW SRM 51-40-21, PG 7. ACCOMPLISHED HFEC INSP OF THE HOLE PER NTM 51-10-08 AND NO CRACKS FOUND. PERFORMED FLAP PEEN PER EA 6-5330-123699 IAW SRM 51-29-02. I=0.15 WEAR. ALODINED IAW SRM 51-21-10. PRIMED AND PAINTED IAW SRM 51-75-10. INSTALLED FASTENERS IAW SRM 51-40-21; PG 7.

Part: FRAME — CRACKED (FUELAGE) · airframe 38,333 hrs · 25,791 cycles

2 CRACK INDICATIONS WERE FOUND IN HOLE NR 7 AT FRAME 54 ON THE AFT FASTENER ROW BETWEEN STRINGER 36L AND STRINGER 37L PER NTM 53-15-90; PT6; PAGE 602. COMPLIED WITH E.A. 6-5310-127907.

Part: SKIN — DENTED (PAX DOOR) · airframe 38,333 hrs · 25,791 cycles

LEFT AFT PASSENGER/CREW DOOR EXTERNAL SKIN LOWER EDGE IS DENTED. REMOVED L-2 DOOR IAW AMM 52-13-11-4. REMOVED SEAL RETAINER IAW SRM 52-10-00. CHECKED DAMAGE, OUT OF LIMITS. REMOVED DAMAGE AREA OF THE SKIN IAW SRM 52-10-00, PG 217; FIG 204. INSTALLED DOUBLER IAW SRM 51-40-20. PRIMED AND PAINTED DOUBLER IAW SRM 51-21-10 AND SRM 51-23-10. INSTALLED L-2 DOOR IAW AMM 52-13-12-4; PG 3; PARA D. CHECKED BONDING WIRES IAW AMM 20-28-11-0.

Part: FITTING — INOPERATIVE (ZONE 700) · airframe 38,333 hrs · 25,791 cycles

RIGHT MLG FWD TRUNNION WILL NOT TAKE GREASE. COMPLIED WITH E.A. 6-3210-123696.

Part: LINE — LOOSE (NR 1 PYLON) · airframe 38,333 hrs · 25,791 cycles

NR1 PYLON LINES ARE LOOSE AT THE WING T/E. COMPLIED WITH E.A. 6-5730-123698. LEAK CHECKS GOOD IAW AMM 29-11-33-4. HYDRAULIC FIRE VALVES OPS CHECK GOOD IAW AMM 29-10-00-5.

Part: LINE — LOOSE (HYD SYSTEM) · airframe 38,333 hrs · 25,791 cycles

RT WING T/E AFT OF THE PYLON ; THE HYD LINES HAVE LOOSE MOUNT NUTS WHERE THE LINES PASS THROUGH THE WING T/E AREA. COMPLIED WITH EA 6-5730-123698. LEAK CHECKS GOOD IAW AMM 29-11-33-4. HYDRAULIC FIRE VALVES OPS CHECK GOOD IAW AMM 29-10-00-5.

Part: RIB — CRACKED (ZONE 600) · airframe 38,333 hrs · 25,791 cycles

COMPLY WITH EA 6-5710-123695. REWORKED HOLE TO 5.000". FABRICATED BUSHINGS "E" AND "F"; CAD PLATED BUSHINGS AND INSTALLED BUSHINGS "E" AND "F" IAW EA 6-5710-123695 "WINGS - AD2007-02-09 - WINGS GEAR RIB 5 FWD LUG BORE REWORK (RHS)".

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 38,333 hrs · 25,791 cycles

MAIN CABIN FLOOR PANEL IS PUNCTURED 8 INCHES FROM FRAME 52, RBL 64 INCHES. REPAIRED THE PUNCTURED AREA IAW SRM 53-10-20, PG 202, PARA 9-C.

Part: FLOOR PANEL — DAMAGED (FWD CARGO BAY) · airframe 38,333 hrs · 25,791 cycles

FWD CARGO PIT FLOOR PANEL NR 132QF IS DAMAGED. THIS SDR WAS GENERATED TO CORRECT THE P/N IN SECTION 5 OF SDR TRACKING NR 08-5248. FABBED NEW PANEL USING THE OLD PANEL AS A TEMPLATE. MATERIAL ID; LOCATED HOLES USING THE THE OLD PANEL; COUNTERBORED HOLES; POTTED AND SANDED EDGE; INSTALLED INSERTS; APPLIED ANTI-SKID AND PART MARKED IAW DWG SRZ 25-005; REV "G".

Part: FLOOR PANEL — DAMAGED (ZONE 100) · airframe 38,333 hrs · 25,791 cycles

FWD CARGO PIT FLOOR PANEL NR 132 ZF IS DAMAGED. FABRICATED NEW PANEL USING THE OLD PANEL AS A TEMPLATE. MATERIAL ID; LOCATED HOLES USING THE OLD PANEL; COUNTERBORED HOLES; POTTED AND SANDED EDGE; INSTALLED INSERTS; APPLIED ANTI-SKID AND PART MARKED IAW DWG SRZ 25-005; REV "G".

Part: SHEAR TIE — CORRODED (BS 2029) · corrosion level 2 · airframe 38,333 hrs · 25,791 cycles

FWD PIT BILGE FRAME NR 37 BETWEEN STRINGER 51L AND STRINGER 52L SHEAR TIE HAS CORROSION ON THE AFT SURFACE. REMOVED SHEAR TIE FROM FRAME 37 IAW SRM 51-40-21. REMOVED CORROSION IAW SRM 51-73-10. ORIGINAL MATERIAL 0.055 IAW SRM 53-14-13. REMAINING MATERIAL 0.042 IAW DWG 6-17-09. FOUND TO BE OUT OF LIMITS IAW SRM 53-73-10. LOCATED AND DRILLED NEW SHEAR TIE IAW SRM 51-40-40. ALODINED IAW SRM 51-21-00. PRIMED IAW SRM 51-24-00. INSTALLED IAW SRM 51-40-21.

Part: SKIN — CORRODED (ZONE 100) · airframe 38,333 hrs · 25,791 cycles

MAIN CABIN, CENTER FUEL TANK UPPER SKIN AT FRAME 44, RBL 77 - 96 HAS CORROSION RUNNING FROM BELOW THE TRACK WEB OTBD UNDER THE FRAME ATTACH FITTING TO UNDER THE OTBD ATTACH FITTING. REMOVED AND RE-INSTALLED 2 ANGLES IAW SRM 51-40-21, PG 7. REMOVED CORROSION AND FOUND TO BE WITHIN LIMITS IAW SRM 57-10-12, FIG 101. ALODINED AND PRIMED AREA IAW SRM 51-21-10; PG 2.

Part: PANEL — DENTED (CARGO BAY) · airframe 38,333 hrs · 25,791 cycles

FWD CARGO PIT; BETWEEN FRAMES 23 & 24 AT STRINGER 44L; THE TRANS PANEL HAS A DENT ON THE TOP & BARE METAL ON THE LOWER SURFACE. REPAIRED DENT IAW SRM 51-73-10; PG 202. ALODINED BARE METAL IAW SRM 51-21-10. PRIMED & APPLIED TOPCOAT IAW SRM 51-23-10.

Part: BEARING — CORRODED (ZONE 400) · corrosion level 2 · airframe 38,333 hrs · 25,791 cycles

NR 1 PYLON THRUST SIDE LOAD FITTING BEARING IS EMITTING RUST ON THE TOP AND BOTTOM SIDES. CLEANED AREA IAW AMM 51-78-00-7. REMOVED AND REPLACED NR 1 PYLON SPIGOT P/N IAW DWG 22A57150065.

Part: FLOOR PANEL — DENTED (ZONE 100) · airframe 38,333 hrs · 25,791 cycles

FWD CARGO PIT FLOOR PANEL 132 ZF IS DAMAGED. FABBED NEW PANEL USING THE OLD PANEL AS A TEMPLATE. MATERIAL ID; LOCATED HOLES USING THE THE OLD PANEL; COUNTERBORED HOLES; POTTED & SANDED EDGE; INSTALLED INSERTS; APPLIED ANTI-SKID & PART MARKED IAW DWG SRZ 25-005; REV "G".

Part: FLOOR PANEL — DENTED (ZONE 100) · airframe 38,333 hrs · 25,791 cycles

BULK CARGO PIT FLOOR PANEL 162 HF HAS SEVERAL DENTS. FABBED NEW PANEL USING THE OLD PANEL AS A TEMPLATE. MATERIAL ID; LOCATED HOLES USING THE THE OLD PANEL; COUNTERBORED HOLES; POTTED & SANDED EDGE; INSTALLED INSERTS; APPLIED ANTI-SKID & PART MARKED IAW DWG SRZ 25-005; REV "G".

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 38,333 hrs · 25,791 cycles

L/H TAIL COMPARTMENT FLOORBOARD IS DELAMINATED AT THE AFT CORNER ACCESS THRU 312 AR. FABBED A NEW FLOOR PANEL USING THE OLD PANEL AS A TEMPLATE. MATERIAL ID; LOCATED HOLES; COUNTERBORED HOLES; POTTED & SANDED EDGE; INSTALLED INSERTS; APPLIED ANTI-SKID & PART MARKED IAW DWG SRZ25-005: REV "G". INSTALLED FLOOR PANEL IAW SRM 51-40-21.

Part: FLOOR PANEL — DAMAGED (ZONE 100) · airframe 38,333 hrs · 25,791 cycles

FWD CARGO PIT FLOOR PANEL NR 132 QF IS DAMAGED. FABBED NEW PANEL USING THE OLD PANEL AS A TEMPLATE. MATERIAL ID; LOCATED HOLES USING THE THE OLD PANEL; COUNTERBORED HOLES; POTTED & SANDED EDGE; INSTALLED INSERTS; APPLIED ANTI-SKID & PART MARKED IAW DWG SRZ 25-005; REV "G".

Part: FLOOR PANEL — DAMAGED (ZONE 100) · airframe 38,333 hrs · 25,791 cycles

FWD CARGO PIT FLOOR PANEL 131 ZF IS DAMAGED. FABBED NEW PANEL USING THE OLD PANEL AS A TEMPLATE. MATERIAL ID; LOCATED HOLES USING THE THE OLS PANEL; COUNTERBORED HOLES; POTTED & SANDED EDGE; INSTALLED INSERTS; APPLIED ANTI-SKID & PART MARKED IAW DWG SRZ 25-005; REV "G".

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 38,333 hrs · 25,791 cycles

MAIN CABIN FLOOR PANEL 242 RJ IS DAMAGED. FABBED NEW PANEL USING THE OLD PANEL AS A TEMPLATE. MATERIAL ID; LOCATED HOLES USING THE THE OLD PANEL; COUNTERBORED HOLES; POTTED & SANDED EDGE; INSTALLED INSERTS; APPLIED ANTI-SKID & PART MARKED IAW DWG SRZ 25-005; REV "G".

Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 38,333 hrs · 25,791 cycles

CABIN SEAT TRACK BETWEEN RBL 28 & RBL 38 IS GOUGED AT FR 37. REMOVED DAMAGE AND CHECKED LIMITS REF SRM 53-10-16. ALODINED REF SRM 51-21-10. PRINED & PAINTED REF SRM 51-23-10.

Part: FITTING — CORRODED (ZONE 400) · corrosion level 2 · airframe 38,333 hrs · 25,791 cycles

NR 2 PYLON TO WING ATTACHMENT FITTING LUG INNER RACE BEARING AT RIB 18 RUSTED. R & R AFT ATTACH FITTING IAW AMM 54-51-75-4-02 TW - T8312G.

Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 38,333 hrs · 25,791 cycles

CABIN SEAT TRACK GOUGED BETWEEN FR 18 & FR 19 AT RBL 63. REMOVED DAMAGE AND CHECKED LIMITS REF SRM 53-10-16. ALODINED REF SRM 51-21-10. PRIMED & PAINTED REF SRM 51-23-10.

Part: SEAT TRACK — GOUGED (FUSELAGE) · airframe 38,333 hrs · 25,791 cycles

SEAT TRACK AT BL " 0 " APPROX 5" FWD OF FR 53, GOUGED. REMOVED AND REPLACED SEAT TRACK AS REQUIRED IAW SRM 51-40-21; PARA 5 AND 6.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 38,333 hrs · 25,791 cycles

SEAT TRACK AT RBL 35 AND FR47/48 HAS CORROSION ON OTBD FLANGE AT FASTENER HOLE, LOWER SURFACE. BLENDED CORROSION ON SEAT TRACK. ORIGINAL THICKNESS 0.078. THICKNESS REMAINING 0.054. MATERIAL LOSS 0.024. FOUND TO BE OUT OF LIMITS IAW SRM 53-10-16; FIG 101. REPLACED TRACK WITH NEW. DRILLED AND LOCATED TRACK IAW SRM 51-40-21; PG 24; PARA 7: SRM 53-10-16; FIG 201; PG 206, PO NR 644456.7, SRM 51-40-21, PG 7, PARA 6 AND DWG A538112.8.

Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 38,333 hrs · 25,791 cycles

CABIN SEAT TRACK AT RBL 38 HAS GOUGES BETWEEN FR 38.1 & FR 38.2. BLENDED & REMOVED GOUGES ON THE SEAT TRACK AT FRAMES 38.1 & 38.2; RBL 38 REF SRM 51-73-10. ALODINED REF SRM 51-21-10. PRIMED & PAINTED REF SRM 51-23-10.

Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 38,333 hrs · 25,791 cycles

CABIN SEAT TRACK AT RBL 38 GOUGED IN AREAS BETWEEN FR 36 AND FR 37. BLENDED & REMOVED GOUGE ON THE SEAT TRACK FRAMES 36 & 37; RBL 38 REF 51-73-10. ALODINED REF SRM 51-21-10. PRIMED & PAINTED REF SRM 51-23-10.

Part: FITTING — CORRODED (S36L) · airframe 38,333 hrs · 25,791 cycles

AFT PIT FWD BULKHEAD AT S36L, END FITTING CORRODED. REMOVED CORROSION; FOUND TO BE OUT OF LIMITS IAW SRM 53-15-14; FIG 7; SHEET 2. REMOVED FITTING IAW SRM 51-40-21. RECEIVED NEW FITTING, LOCATED & DRILLED NEW FITTING IAW DWG A53811093. INSTALLED FITTING IAW SRM 51-40-21.

Part: FITTING — CORRODED (S40L) · airframe 38,333 hrs · 25,791 cycles

AFT PIT FWD BULKHEAD AT S40L, CORROSION ON END FITTING. REMOVED CORROSION; FOUND TO BE OUT OF LIMITS IAW SRM 53-15-14; FIG 7; SHEET 2. REMOVED FITTING IAW SRM 51-40-21. RECEIVED NEW FITTING, LOCATED & DRILLED NEW FITTING IAW DWG A53811093. INSTALLED FITTING IAW SRM 51-40-21.

Part: FLOORBEAM — DELAMINATED (ZONE 200) · airframe 38,333 hrs · 25,791 cycles

FLOORBOARD 252WG IS DELAMINATED ON THE LWR SURFACE FROM FRAME 62 TO FRAME 65 R/H. REPAIRED FLOOR PANEL 252 WG BY FABRICATING A NEW FLOOR PANEL FROM STOCK MATERIAL USING THE OLD PANEL AS A TEMPLATE IAW FEDEX DWG SRZ20-005; REV " G ".

Part: FLOORBEAM — DAMAGED (ZONE 200) · airframe 38,333 hrs · 25,791 cycles

FLOORBOARD 251FG BROKE AT CORNER FROM FRAME 69 TO FRAME 71 LT SIDE. REPAIRED FLOORBOARD BY FABRICATING A NEW FLOORBOARD FROM STOCK MATERIAL USING THE OLD PANEL AS A TEMPLATE IAW DWG SRZ20-005; REV " G ".

Part: BULKHEAD — CORRODED (ZONE 100) · airframe 38,333 hrs · 25,791 cycles

AFT PIT FWD BULKHEAD AT STGR 38L END FITTING CORRODED. REPLACED THE FITTING AT THE AFT PIT FWD BULKHEAD LT SIDE IF STRINGER 38L IAW SRM 51-40-21.

Part: BULKHEAD — CORRODED (S37L) · airframe 38,333 hrs · 25,791 cycles

AFT PIT FWD BULKHEAD AT S37L, END FITTING CORRODED. REMOVED CORROSION; FOUND TO BE OUT OF LIMITS IAW SRM 53-15-14; FIG 7; SHEET 2. REMOVED FITTING IAW SRM 51-40-21. RECEIVED NEW FITTING, LOCATED & DRILLED IAW DWG A53811093. INSTALLED FITTING IAW SRM 51-40-21.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 38,333 hrs · 25,791 cycles

FLOORBOARD 252YG IS CRACKED. FR 62 - 65 RT. REPAIRED FLOORBOARD BY FABRICATING A NEW FLOORBOARD FROM STOCK MATERIAL USING THE OLD PANEL AS A TEMPLATE IAW DWG SRZ20-005; REV " G ".

Part: FITTING — CORRODED (ZONE 100) · airframe 38,333 hrs · 25,791 cycles

AFT PIT FWD BULKHEAD AT S35L END FITTING CORRODED. REMOVED CORROSION; FOUND TO BE OUT OF LIMITS IAW SRM 53-15-14; FIG 7; SHEET 2. REMOVED FITTING IAW SRM 51-40-21. RECEIVED NEW FITTING, LOCATED & DRILLED NEW FITTING IAW DWG A53811093. INSTALLED FITTING IAW SRM 51-40-21.

Part: FITTING — CORRODED (S33L) · airframe 38,333 hrs · 25,791 cycles

AFT PIT FWD BULKHEAD AT S33L, END FITTING CORRODED. REMOVED CORROSION; FOUND TO BE OUT OF LIMITS IAW SRM 53-15-14; FIG 7; SHEET 2. REMOVED FITTING IAW SRM 51-40-21. LOCATED & DRILLED NEW FITTING IAW DWG A53811093. INSTALLED FITTING IAW SRM 51-40-21.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 38,333 hrs · 25,791 cycles

FLOOR PANEL BROKEN ON THE END ( 232HG ). REPAIRED FLOOR PANEL 232 HG BY FABRICATING A NEW FLOOR PANEL FROM STOCK MATERIAL USING THE OLD PANEL AS A TEMPLATE IAW DWG SRZ20-005; REV " G ".

Part: FITTING — CORRODED (S43L) · airframe 38,333 hrs · 25,791 cycles

AFT PIT FWD BULKHEAD AT S43L, CORROSION ON END FITTING. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS IAW SRM 53-15-14; FIG 7; SHEET 2. REMOVED FITTING IAW SRM 51-40-21. RECEIVED NEW FITTING, LOCATED & DRILLED NEW FITTING IAW DWG A53811093. INSTALLED FITTING IAW SRM 51-40-21.

Part: SKIN — CORRODED (ZONE 100) · airframe 38,333 hrs · 25,791 cycles

FWD PIT BILGE 6 INCH FWD OF FR 38, BL 0 INTERNAL SKIN HAS CORROSION. REMOVED DAMAGED AREA IAW SRM 53-10-12; FIG 225. FABRICATED THE DOUBLER IAW SRM 53-10-12; FIG 225. ALODINED DOUBLER IAW SRM 51-21-10. PRIMED DOUBLER IAW SRM 51-23-10. INSTALLED DOUBLER IAW A310-200 SRM 53-10-12; FIG 225. TOPCOATED DOUBLER IAW SRM 51-23-10.

Part: FLOOR PANEL — DENTED (ZONE 200) · airframe 38,333 hrs · 25,791 cycles

CABIN FLOOR PANEL 252GF DENTED IN 2 PLACES. REPAIRED FLOOR PANEL 252 GF BY FABRICATING A NEW FLOOR PANEL FROM STOCK MATERIAL USING THE OLD PANEL AS A TEMPLATE IAW DWG SRZ20-005; REV " G ".

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 38,333 hrs · 25,791 cycles

FLOOR PANEL BETWEEN FR 45 - 46 & BETWEEN RBL 71 - 91 IS BROKEN ON THE EDGE. 242SK REPAIRED FLOOR PANEL BY FABRICATING A NEW FLOOR PANEL FROM STOCK MATERIAL USING THE OLD PANEL AS A TEMPLATE IAW DWG SRZ20-005; REV " G ".

Part: FITTING — CORRODED (S34L) · airframe 38,333 hrs · 25,791 cycles

AFT PIT FWD BULKHEAD AT S34L, END FITTING CORRODED. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS IAW SRM 53-15-14 FIG 7 SHEET 2. REMOVED FITTING IAW SRM 51-40-21. RECEIVED NEW FITTING LOCATED & DRILLED NEW FITTING IAW DWG A53811093. INSTALLED FITTING IAW SRM 51-40-21.

Part: FLOOR PANEL — DELAMINATED (ZONE 200) · airframe 38,333 hrs · 25,791 cycles

FLOORBOARD 252BG DELAMED LWR. SURFACE FR 65 - 69 R/H. REPAIRED FLOOR PANEL 252 BG BY FABRICATING A NEW FLOOR PANEL FROM STOCK MATERIAL USING THE OLD PANEL AS A TEMPLATE IAW FEDEX DWG SRZ20-005; REV " G ".

Part: FITTING — CORRODED (S39L) · airframe 38,333 hrs · 25,791 cycles

AFT PIT FWD BULKHEAD AT S39L CORROSION ON END FITTING. REMOVED CORROSION; FOUND TO BE OUT OF LIMITS IAW SRM 53-15-14; FIG 7; SHEET 2. REMOVED FITTING IAW SRM 51-40-21. RECEIVED NEW FITTING, LOCATED & DRILLED NEW FITTING IAW DWG A53811093. INSTALLED FITTING IAW SRM 51-40-21.

Part: SHEAR TIE — CORRODED (ZONE 200) · corrosion level 2 · airframe 38,333 hrs · 25,791 cycles

FWD PIT BILGE FR 36 BETWEEN STGR 51L AND 52L SHEAR TIE HAS CORROSION FWD AND AFT SURFACES. REMOVED SHEAR TIE FROM FRAME 36 BETWEEN STRINGER 51L & 52L IAW SRM 51-40-21. REMOVED CORROSION FROM SHEAR TIE IAW SRM 51-73-10. ORIGINAL MATERIAL 0.055 IAW SRM 53-14-13. MATERIAL LOSS 0.043. FOUND TO BE OUT OF LIMITS IAW SRM 51-73-10. LOCATED & DRILLED NEW SHEAR TIE IAW SRM 51-40-44. ALODINED IAW SRM 51-21-10. PRIMED IAW SRM 51-23-10. INSTALLED SHEAR TIE IAW SRM 51-40-21.

Part: FRAME — CHAFED (THRUST REVERSER) · airframe 38,333 hrs · 25,791 cycles

NR 1 OTBD T/R AFT FRAME INNER SURFACE HAS CHAFED AREAS FROM CONTACT WITH CORE COWLS. REMOVED AFT CLOSE OUT FRAME IAW SRM 51-40-21, PARA 5 AND 6. FABRICATED AND PART MARKED NEW CLOSE OUT FRAME IAW EA 6-7830-123697. ALODINED 7 PRIMED FRAME IAW SRM 51-21-10 AND 51-75-10. INSTALLED FRAME IAW SRM 51-40-21, PG 7 AND PG 90; AND CMM 78-32-02; FIG 702.

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 38,333 hrs · 25,791 cycles

MAIN CABIN FLOOR PANEL NR 242 KJ IS DAMAGED. FABBED A NEW FLOOR PANEL USING THE OLD PANEL AS A TEMPLATE. LOCATED, COUNTERBORED HOLES, POTTED & SANDED EDGE; INSTALLED INSERTS. APPLIED ANTI-SKID & PART MARKED IAW DWG SRZ25-005: REV "G".

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 38,333 hrs · 25,791 cycles

MAIN CABIN FLOOR PANEL NR 242 GF IS DAMAGED. FABRICATED A NEW FLOOR PANEL USING THE OLD PANEL AS A TEMPLATE. LOCATED & COUNTERBORED HOLES; POTTED & SANDED EDGE; INSTALLED INSERTS; APPLIED ANTI-SKID & PART MARKED IAW DWG SRZ25-005: REV "G".

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 38,333 hrs · 25,791 cycles

MAIN CABIN FLOOR PANEL NR 242 QJ IS DAMAGED. FABBED A NEW FLOOR PANEL USING THE OLD PANEL AS A TEMPLATE. LOCATED HOLES, COUNTERBORED, POTTED & SANDED EDGE. INSTALLED INSERTS, APPLIED ANTI-SKID & PART MARKED IAW DWG SRZ25-005: REV "G".

Part: VAPOR BARRIER — WORN (ZONE 100) · airframe 38,333 hrs · 25,791 cycles

A/C BAY HORZONTAL VAPOR BARRIER NR 7 IS WORN THROUGH. FABRICATED DOUBLER IAW SRM 51-71-31; PG 201. ALODINED & PRIMED IAW SRM 51-21-10; PG 3 & SRM 51-23-10; PG 24. INSTALLED DOUBLERS IAW SRM 51-40- 21; PG 3 & SRM 51-71-31; PG 201. ROUTED OUT DAMAGE IAW SRM 51-71-30; PG 201.

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 38,333 hrs · 25,791 cycles

MAIN CABIN FLOOR PANEL NR 242 BF IS DAMAGED. FABBED A NEW FLOOR PANEL USING THE OLD PANEL AS A TEMPLATE. LOCATED HOLES, COUNTERBORED HOLES, POTTED & SANDED EDGE, INSTALLED INSERTS; APPLIED ANTI-SKID & PART MARKED IAW DWG SRZ25-005: REV "G".

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 38,333 hrs · 25,791 cycles

THE MAIN CABIN SEAT TRACK IS CORRODED BETWEEN FRAME 46 AND FRAME 47/48 RBL 37. SEAT TRACK REPLACED ON NON-ROUTINE CARD N01243.

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 38,333 hrs · 25,791 cycles

MAIN CABIN FLOOR PANEL NR 241 LK IS DAMAGED. FABBED A NEW FLOOR PANEL USING THE OLD PANEL AS A TEMPLATE. LOCATED, COUNTERBORED HOLES; POTTED & SANDED EDGE; INSTALLED INSERTS; APPLIED ANTI-SKID & PART MARKED IAW DWG SRZ25-005: REV "G".

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 38,333 hrs · 25,791 cycles

MAIN CABIN FLOOR PANEL NR 251 WG IS DAMAGED. FABBED A NEW FLOOR PANEL USING THE OLD PANEL AS A TEMPLATE. LOCATED & COUNTERBORED HOLES; POTTED & SANDED EDGE; INSTALLED INSERTS; APPLIED ANTI-SKID & PART MARKED IAW DWG SRZ25-005: REV "G".

Part: SEAL — TORN (CENTER TANK) · airframe 38,333 hrs · 25,791 cycles

VERTICAL VAPOR SEAL IS TORN AT THE CENTER WING BOX AT FRAME 40/41 AT LBL 58. REPAIRED VAPOR SEAL SEAM IAW AMM 28-13-12-8; PG 1; FIG 802 AND PARA 2-B.

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 38,333 hrs · 25,791 cycles

MAIN CABIN FLOOR PANEL NR 242 MF IS DAMAGED. FABRICATED A NEW FLOOR PANEL USING THE OLD PANEL AS A TEMPLATE. LOCATED & COUNTERBORED HOLES; POTTED & SANDED EDGE; INSTALLED INSERTS; APPLIED ANTI-SKID & PART MARKED IAW DWG SRZ25-005: REV "G".

Part: STRUCTURE — CORRODED (WING BOX) · airframe 38,333 hrs · 25,791 cycles

CENTER WING BOX LOWER SURFACE HAS LIGHT CORROSION BETWEEN FRAMES 40/41- 43, ADJACENT TO RIB 1 LEFT. CLEANED AREA IAW AMM 12-21-11-0; PG 3. CORROSION FOUND TO BE A PAINT CHIPPED OFF. NO MATERIAL LOSS. ALODINED AND PRIMED BARE AREA IAW SRM 51-21-10. PAINTED AREA IAW SRM 51-23-10; PG 7 AND 8.

Part: VAPOR BARRIER — CRACKED (FUSELAGE) · airframe 38,333 hrs · 25,791 cycles

ACFT HORIZONTAL VAPOR BARRIER NR 1 AFT IS CRACKED. RECEIVED NEW A2811028300500 SHEET METAL ASSY (PO 643383.1) TO BE INSTALLED ON WIC 41X5087ALI.

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 38,333 hrs · 25,791 cycles

MAIN CABIN FLOOR PANEL NR 242 LK IS DAMAGED. FABBED A NEW FLOOR PANEL USING THE OLD PANEL AS A TEMPLATE. LOCATED HOLES; COUNTERBORED HOLES; POTTED & SANDED EDGE; INSTALLED INSERTS; APPLIED ANTI-SKID & PART MARKED IAW FEDEX DWG SRZ25-005: REV "G".

Part: SEAT TRACK — WORN (FUSELAGE) · airframe 38,333 hrs · 25,791 cycles

THE MAIN CABIN SEAT TRACK IS WORN BEWTEEN FRAME 50 AND FRAME 51 RBL 18. REMOVED & REPLACED SEAT TRACK SECTION DUE TO BEING OUT OF LIMITS IAW SRM 53-10-6. INSTALLED NEW SEAT TRACK RAIL P/N A5381192220251; PO 644457.1 IAW SRM 51-72-10; PG 1.

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 38,333 hrs · 25,791 cycles

MAIN CABIN FLOOR PANEL NR 262 AH IS DAMAGED. FABBED A NEW FLOOR PANEL USING THE OLD PANEL AS A TEMPLATE. LOCATED & COUNTERBORED HOLES; POTTED & SANDED EDGE; INSTALLED INSERTS; APPLIED ANTI-SKID & PART MARKED IAW FEDEX DWG SRZ25-005: REV "G".

Part: SEAT TRACK — WORN (FUSELAGE) · airframe 38,333 hrs · 25,791 cycles

THE MAIN CABIN SEAT TRACK IS WORN BETWEEN FRAME 54.2 AND FRAME 54.3 RBL 77. FOUND TO BE OUT OF LIMITS IAW SRM 53-10-16. REMOVED & REPLACED THE SEAT TRACK IAW SRM 53-10-16; FIG 208 & SRM 51-40-21.

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 38,333 hrs · 25,791 cycles

MAIN CABIN FLOOR PANEL NR 242 BF IS DAMAGED. FABBED A NEW FLOOR PANEL USING THE OLD PANEL AS A TEMPLATE. LOCATED & COUNTERBORED HOLES; POTTED & SANDED EDGE; INSTALLED INSERTS; APPLIED ANTI-SKID & PART MARKED IAW DWG SRZ25-005: REV "G".

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 38,333 hrs · 25,791 cycles

MAIN CABIN FLOOR PANEL NR 242 SF IS DAMAGED. FABBED A NEW FLOOR PANEL USING THE OLD PANEL AS A TEMPLATE. LOCATED, COUNTERBORED HOLES; POTTED & SANDED EDGE; INSTALLED INSERTS; APPLIED ANTI-SKID & PART MARKED IAW FEDEX DWG SRZ25-005: REV "G".

Part: ATTACH FITTING — CRACKED (RT NACELLE) · airframe 38,333 hrs · 25,791 cycles

RIGHT WING AFT OTBD PYLON FAIRING SUPPORT ATTACH FITTING ON THE WING, RIB 9, STRINGERS 8 - 9, IS CRACKED. REMOVED AND REPLACED FITTING IAW DWG 3 A57250004, ISSUE "E" AND SRM 51-40-21, PARA 7 AND PART 5.

Part: WEB — CRACKED (HORIZONTAL STAB) · airframe 38,333 hrs · 25,791 cycles

RIGHT HORIZONTAL STAB L/E 341 CB WEB IS CRACKED, APPROX 5' FROM OTBD END. STOP DRILLED CRACK IAW SRM 51-73-10. ACCOMPLISHED HFEC IAW NTM 51-10-08 AND NO FURTHER DAMAGE WAS FOUND. FABRICATED REPAIR IAW SRM 51-71-40. ALODINED IAW SRM 51-21-10 PRIMED IAW SRM 51-23-10. INSTALLED REPAIR IAW SRM 51-40-21.

Part: WIRE HARNESS — UNKNOWN (MLG) · airframe 35,409 hrs · 23,956 cycles

NR 1 GEAR SYSTEM WOULD NOT RETRACT GEAR AFTER T/O. NR 2 BROUGHT GEAR UP BUT LOST NUMEROUS SYSTEMS AFTERWARDS, SUCH AS A/C PRESSURIZATION, A/C PITOT/HEAT SYSTEM, TRANSPONDER, ETC. REPEAT TROUBLE SHOT PER TSM 32-61-00 SENSORS 55GB FOUND TO BE BAD. NIS IN MEM ORDER SAME. INSP HARNESS TO SENS OR FOUND PLUG AT JUNCTION BOX TO BE LOOSE. REMOVED AND REPLACED HARNESS AS A PRECAUTIONARY ON SYSTEM NR 1. ALSO, AS A PRECAUTIONARY REPLACED RELAY 20GB. OPERATED GEAR, GEAR OPERATED NORMALLY IN BOTH SYSTEMS, A310 MM 32-21-44-4.

Part: DAMPER — MALFUNCTIONED (MLG) · airframe 35,403 hrs · 23,950 cycles

LDG GEAR HANDLE WON'T GO PAST NEUTRAL ON RETRACT IN SYS2. WORKED SYS1. ACN RELEASED MEL: 32-61-04 CAT: C XP: 30SEP05 "LDG GEAR POS DET SYS2 INOP." PERFORMED BITE TEST ON PROX . ALL TESTS OK. MEMORY RECALL ,FC 04 ON THE PROX UNIT. SHAKE TEST OF ALL 4 LDG GEAR HARNESSES OM PROX DET UNIT. BOGIE SENSORS, C/P 929VC,1930VC, 25VC,1926VC TO BOGIE SENSORS NO SHORTS/OPENS NOTED. INSP BOGIE SENSOR/TARGET NO DEFECTS. CLEANED AND INSP BOTH C/P AT MID-POINT OF EA GEAR, ALL PINS CLEAN/SECURE, NO EROSION/DAMAGE. R/R RMLG BOGIE PITCH DAMPER FOR LOW FLUID/N2 SERVICE. REMOVED AND REPLACED 8GA/12GA PROX SENSORS, RMLG/BOGIE DET SYS. GEAR RETRACT CK GOOD SYS 1/2.

Part: INDICATOR — MALFUNCTIONED (FUEL QTY) · airframe 34,543 hrs · 23,355 cycles

REACHING CRUISE FL330 THE RIGHT OUTER TANK QUANTITY BEGAN DECREASING BY 4 TO 5 HUNDRED INCREMENTS FROM 6300 LBS TO 2500 LBS ON THE ECAM AND ON THE OVERHEAD. REFERENCE QRH AND HAD SYMPTOMS OF A FUEL LEAK. RETURNED TO RENO, TURNED OFF THE RIGHT OUTER FUEL PUMPS AND LEAKS STOPPED, TANK STOPPED DECREASING. ON RETURNING THE RIGHT OUTER QUANTITY CAME BACK TO NORMAL 6300 LBS. PRECAUTIONARY- MEL 28-42-01-01: ALL (IDENTIFY LEFT OR RIGHT). OUTER TANK INDICATIONS INOP. EITHER FUEL TO KNOWN QTY OR, AFTER REFUELING VERIFY TANK QTY WITH MAG MEASURING STICKS AND RECORD IN AML/EAML.

Part: ATTACH BRACKET — CORRODED (VERTICAL STAB) · corrosion level 2 · airframe 34,178 hrs · 23,091 cycles

RIGHT SIDE OF VERTICAL STAB FROM RIB 22 TO 26 OF REAR SPAR HAS SEVERAL AREAS OF CORROSION ON FLANGES (PANEL ATTACH BRACKET). REMOVED CORROSION AT RT SIDE OF VERTICAL STAB REAR SPAR AREA, 3 AREAS NEEDED REWORK. FABRICATED & INSTALLED REPAIRS IAW EA 6-5530-77658A.

Part: RIB — CORRODED (HORIZ STAB) · corrosion level 2 · airframe 34,178 hrs · 23,091 cycles

RIGHT HORIZONTAL STAB END RIB UPPER AND LOWER FORMER PROFILE CORRODED. REMOVED CORROSION FROM RIGHT HORIZONTAL STAB, END RIB UPPER & LOWER FORMER PROFILES IAW A310-200 SRM 51-74-10. FABRICATED REPAIR STRAP & INSTALLED IAW EA 6-5510-77671.

Part: ATTACH ANGLE — CORRODED (VERTICAL STAB) · corrosion level 2 · airframe 34,178 hrs · 23,091 cycles

RT SIDE OF VERTICAL STAB T/E, AT RIB 26 TOP FLANGE (PANEL ATTACHMENT ANGLE BRACKET) HAS CORROSION ON INNER SIDE OF FLANGE. REPAIRED IAW EA 6-5530-77670A RT SIDE OF VERTICAL STAB T/E AT RIB 26 TOP FLANGE.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 34,178 hrs · 23,091 cycles

AVI BAY FROM FR 7 TO 10 STR 48L TO 48R E&E GROUND ACCESS DOOR CUTOUT SKIN SURFACE, FRAME ATTACHING SUPPORT ANGLES, PLATES, FITTINGS & FASTENERS HAVE CORROSION OVER ENTIRE CUTOUT AREA. REMOVED CORROSION AT AVI BAY FR 7 TO 10 STR 48L TO 48R, DOOR CUTOUT SKIN SURFACE, FRAME, SUPPORT ANGLES, PLATES, FITTINGS. ALL AREAS WITHIN LIMITS, FRAME SECTION NR 7 OUT OF LIMITS. REMOVED CORRODED SECTION OF FRAME NR 7 & ATTACHING PARTS. REINSTALLED NEW SECTION OF FRAME NR 7, RE-INSTALLED ATTACHING PARTS PER A310 SRM 51-40-21, 51-22-00, 51-74-10, 51-72-10.

Part: STRUCTURE — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 34,178 hrs · 23,091 cycles

LEFT HORIZONTAL STABILIZER FIXED LEADING EDGE, ZONE 330 (FWD SPAR) UPPER LIP UPPER SECTION APPROX STA 158 RIB 5, 4 EA AREAS 1.0 INCH L ,(.200 INCH W AREA 2 & 3 AS MARKED), (.100 INCH W AREA 1 & 4 AS MARKED). UNABLE TO DETERMINE DEPTH WITHOUT BLENDOUT, CORROSION AT THIS TIME MEETS LEVEL 1 CORROSION, WITHOUT MATERIAL AND SURFACE PROTECTION REMOVAL. CHORD FLANGE, BLENDED CORROSION IAW SRM 51-74-10 & FOUND UPPER T-CHORD OUT OF LIMITS. CUT & REMOVED DAMAGED SECTION OF UPPER TEE CHORD IAW A310 SRM 55-11-21, PARA 6(E) 2 FIG 205 & 210. APPLIED ALODINE AND PRIMER & TOP COAT TO ALL REPAIR SURFACES IAW A310 SRM 51-21-00 & 51-23-00. INSTALLED REPAIR IAW A310 SRM 55-11-21 FIG 205 & 210.

Part: RIB — CORRODED (VERTICAL STAB) · corrosion level 2 · airframe 34,178 hrs · 23,091 cycles

VERTICAL STABILIZER TRAILING EDGE ON RIGHT SIDE EDGE FOR ACCESS PANEL ATTACHMENT STRUCTURE, PROPAGATION OF CORROSION NOTED FROM RIB 12-17, AS MARKED. REMOVED CORROSION IAW A310-200 SRM 51-74-10. REPAIRED IAW FEDEX EA 6-5530-77658 AND SRM A310-200 51-74-10 AND 55-30-00.

Part: CROSSBEAM — CORRODED (FUSELAGE) · corrosion level 2

MAIN CABIN FLOOR SUPPORT CROSSBEAM AT FR14A FROM Y953 TO Y1456 IS CORRODED. REMOVED AND INSTALLED FLOOR SUPPORT IAW A310-200 SRM 51-40-21.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2

MAIN CABIN FLOOR SUPPORT FROM FR14 TO 15A JUST I/B OF Y1456 IS CORRODED. REMOVED FAB AND INSTALLED FLOOR SUPPORT IAW A310-200 SRM 51-40-21.

Part: PROXIMITY SENSOR — MALFUNCTIONED (MLG) · airframe 34,089 hrs · 22,999 cycles

ON TAKEOFF FROM IAD GEAR WOULD NOT RETRACT, BOTH SYSTEMS TRIED. FOLLOWED ECAMS. RETURNED TO IAD. REMOVED AND REPLACED PROX BOX PER MM 32-31-71, OP'S GOOD. PREMATURE REMOVAL/INSTALLATION OFF MFG 8-371-01A. SERVICED LT LANDING GEAR BOGIE BEAM DAMPER PER MM 12-12-32-0.

Part: DAMPER — MALFUNCTIONED (MLG) · airframe 34,088 hrs · 22,998 cycles

AFTER T/O LANDING GEAR WOULD NOT RETRACT- TRIED BOTH SYSTEMS, FOLLOWED ECAM (270 SPEED WAS NOT EXCEEDED), FOLLOWED QRM, RETURNED. REMOVED LT GEAR PITCH DAMPER PER MM 32-11-15-4-01. INSTALLED NEW DAMPER THROUGH STEP 4 (B) (4).

Part: HYDRAULIC SYSTEM — LOW (GREEN SYS)

DURING CLIMB ECAM IND GREEN HYD RESERVOIR LO LEVEL.

Part: TRANSPONDER — MALFUNCTIONED (E&E BAY) · airframe 31,394 hrs · 21,255 cycles

AFT DEP LOST TRANSPONDER (1 & 2), NR 2 PITCH TRIM, NR 1 ATS, CAPT/STBY BY PROBE HEAT AND NR 2 PRESSURE CONTROLLER. ALSO ACARS DID NOT RECORD OFF OR ON TIMES CAPT SRS INOP. EVERYTHING APPEAR TO RESET UPON LANDING.

Part: DAMPER — FAILED (RT MLG PITCH) · airframe 31,322 hrs · 21,213 cycles

LANDING GEAR FAILED TO RETRACT WITH POSITION DETECTOR ON BOTH NR 1 AND 2 POS. REMOVED AND REPLACED RT MLG PITCH DAMPER PER MM REF 32-11-15. PERF GEAR SWING IN BOTH POS PER MM REF 7-11. OPS CK GOOD.