N243FE

Part: SHUTOFF VALVE — FAILED (CABIN PRESSURE) · airframe 44,819 hrs · 34,942 cycles

DURING CLIMB-OUT CABIN ALTITUDE WAS NOTED AT 7,500' CLIMBING THRU FL220 WITH BOTH PACKS ON AND CARGO HEAT OUTFLOW VALVE CLOSED. SWAPPED BLEEDS WITH NO EFFECT. ATTEMPTED STANDBY MODE AS WELL AS MANUAL MODE WITH NO EFFECT. OUTFLOW VALVE WAS FULLY CLOSED IN DC MODE WITH NO EFFECT. TROUBLESHOOTING PRESS PROBLEM. ON BLOCK IN FOUND ALL DOORS SECURE AND PER CREW DE-BRIEF PACKS APPEARED TO BE OPERATING NORMALLY. FOUND RT PACK VALVE FAILED CLOSED. REMOVED AND REPLACED RT FWD PACK VALVE IAW MM 21-55-071-0. PRESS OPS CK GOOD PER MM 21-31-000-5.

Part: SKIN — MISREPAIRED · airframe 44,524 hrs · 34,731 cycles

REPAIR LOCATED JUST AFT OF STA 1070 BETWEEN STR 20L-21L AND BETWEEN STA 1050-1070, BETWEEN STR 20L-21L. FOUND NOT TO BE INSTALLED USING APPROVED DATA. FOUND TO BE WITHIN 3" OF REPAIR AT STA 1050-1070, STR 1050-1070, STR 21L-22L, NO FASTENERS ABOVE REPAIR AT SKIN LAP REF SRM 53-30-3 PG 20 FIG 5 AND PG 22 FIG 5 (SHEET 5). REPAIR BETWEEN STA 1050-1070 WRONG NUMBER OS FASTENERS AND WITHIN 3" OF REPAIR AT STA 1070 STR 20L-21L REF SRM 53-30-3 PG 8 FIG I. REMOVED EXISTING REPAIRS, FABRICATED NEW REPAIR DOUBLER AND INSTALLED REF SRM 53-30-3 FIG 24.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 44,524 hrs · 34,731 cycles

LT AFT SERVICE DOOR FWD FRAME IS CRACKED AT CUTOUT FOR GUIDE ARM, AT INBD LOWER CORNER. INSTALLED REPAIR DOUBLER REF EA NR I060464, FED EX EA NR 7-5210-105271. CLASSIFIED AS A MAJOR REPAIR.

Part: FLANGE — CORRODED (FUSELAGE) · airframe 44,524 hrs · 34,731 cycles

APU AIR INLET SOUND SUPPRESSOR AND MOUNTING FLANGE IN WHEEL WELL HAVE CORROSION ON MATING SURFACE. BLENDED FORWARD, AFT AND INTERCOSTAL HFEC FOR MATERIAL LOSS, FORWARD STIFFENER AND INTERCOSTAL BEYOND LIMITS, AFT STIFFENER, REPAIRED PER EA NR 7-5310-99309. REMOVED DAMAGED AREA FORWARD STIFFENER, FABRICATED REPAIR REF SRM 51-40-4 PG 3-13. INSTALLED WITH FAYING SEAL 870 B2. FABRICATED NEW INTERCOSTAL REF BOEING DWG 69-45883 AND INSTALLED CLASSIFIED AS MAJOR REPAIR.

Part: NUT PLATE — DAMAGED (FUSELAGE) · airframe 44,524 hrs · 34,731 cycles

NUT PLATE HOLE UNDER FLOORBOARD AT STA 1130 - 1183 LBL 15 IS DOUBLE DRILLED. REMOVED PNL NR 1148 FOR ACCESS. REMOVED DAMAGED AREA, FABRICATED REPAIR ANGLES FROM 7075-T6-.090. FABRICATED FILLER FROM 7075-T6-.125, TREATED PRIMED AND PAINTED REPAIR ANGLES AND FILLER REF SRM 51-10-02 PG 1-8. INSTALLED REPAIR ANGLES AND FILLER WITH FAYING SURFACE OF B 870-2 SEALANT. INSTALLED REF SRM 53-10-8, PG 44-48A, SHIMMED STIFFENER USING 2024-T3-.090. INSTALLED PNL NR 1148 AND FIRE TAPED CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 44,524 hrs · 34,731 cycles

REPAIR LOCATED AT STA 360 BETWEEN STR 15L-16L FOUND NOT TO BE INSTALLED USING APPROVED DATA. REF SNRM# N00920 AND SRM 53-30-3 FIG 2, REPAIR DOES NOT HAVE REQUIRED NUMBER OF FASTENER ROWS. REMOVED DOUBLER, EVALUATED REPAIR AND FOUND IT TO BE IAW WITH BACO DRAWING NR 69-61171. REINSTALLED REPAIR AND RESTORED FINISH REF SRM 51-30-02. CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — MISREPAIRED · airframe 44,524 hrs · 34,731 cycles

REPAIR LOCATED AT MED UPPER SKIN FOUND NOT TO BE INSTALLED USING APPROVED DATA. REF SNRM NR N00910 AND SRM 52-00-3 FIG 3/4 DAMAGE HAS NOT BEEN CUT OUT PER SRM. REMOVED EXISTING DOUBLER, FABRICATED AND INSTALLED NEW DOUBLER REF SRM 52-00-3 FIG 3 PRIMED AND PAINTED REF SRM 51-10-2.

Part: SKIN — MISREPAIRED · airframe 44,524 hrs · 34,731 cycles

EXTERNAL REPAIR LOCATED AT STA 710, STR 28R FOUND NOT TO BE INSTALLED USING APPROVED DATA. REF SNRM NR N00937 AND SRM 53-30-3 INCORRECT BLIND FASTENERS ARE INSTALLED ON REPAIR. REMOVED BLIND FASTENERS BS 710 STR 28R AND REINSTALLED SOLID FASTENERS REF SRM 51-30-02 PG 2. REMOVED INTERCOSTAL REPAIR SPLICE AND FRAME STRAP FOR ACCESS AND REINSTALLED REF SRM 51-30-02 PG 2. REMOVED FASTENERS STR 27R BS 710 FOR ACCESS AND REINSTALLED REF SRM 51-30-02 PG 2. REMOVED LEVELING COMPOUND FOR ACCESS AND REINSTALLED REF SRM 51-10-05 PG 1 APPLIED CIC REF SRM 51-10-02 PG 1 CLASSIFIED AS A MAJOR REPAIR, COMPLETED REF SRM 53-30-3 FIG 3.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 44,524 hrs · 34,731 cycles

EXT REPAIR LOCATED AT APPROX STA 39-410 BETWEEN STA 21R- 22R FOUND NOT TO BE INSTALLED USING APPROVED DATA, REF SNRM NR N00922 AND SRM 53-30-3 FIG 3 REPAIR HAS INSUFFICIENT FASTENER ROWS PAST INTERNAL STRUCTURE. REMOVED EXISTING SKIN REPAIR, INSTALLED NEW REPAIR REF AAR EA NR I060475 WHICH CONFORMS TO CURRENT SRM STANDARDS, REF FED EX EA NR 7-5330-105275. CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 44,524 hrs · 34,731 cycles

EXT REPAIR LOCATED BETWEEN STA 1148-1166 STR 30 AT BL 0. FOUND NOT TO BE INSTALLED USING APPROVED DATA, REF SNRM# N00949, REF SRM 53-30-3 FIG 3 ROWS OF FASTENERS. INSUFFICIENT AND SPACING INCORRECT REMOVED PREVIOUS REPAIR AND INTERCOSTALS FOR ACCESS. FABRICATED AND INSTALLED REPAIR DOUBLER AND INSTALLED (2) INTERCOSTALS REF B727 SRM 53-30-3 FIG 3 PG 12 AND SRM 51-30-02.

Part: ANGLE — CORRODED (ZONE 100) · airframe 44,524 hrs · 34,731 cycles

FORWARD CARGO PIT DOOR SECOND FROM AFT FRAME ANGLE CORRODED 6" FROM BOTTOM EDGE OF DOOR REMOVED AND REPLACED TEE ANGLE REF SRM 51-30-2 PG 2. CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — DAMAGED (FUSLEAGE) · airframe 44,524 hrs · 34,731 cycles

REPAIR LOCATED AFT OF STA 1070 BETWEEN STR 17L - 18L, FOUND NOT TO BE INSTALLED USING APPROVED DATA, SNRM# N00956 REF. SRM 53-30-3 FIG 3. THERE IS NO ALLOWANCE FOR TRIPLER INSTALLATION. INSTALLED REPAIR REF FED EX EA NR 7-5530-99315 AND AAR EA I060473 REV IR. CLASSIFIED AS A MAJOR REPAIR.

Part: FRAME — CRACKED (BS 277) · airframe 44,524 hrs · 34,731 cycles

FRAME AT ATTACH POINT STA 277 AT STR 21L IS CRACKED AT UPPER ATTACH HOLE TO SKIN. REMOVED DAMAGE AND REPAIRED FRAME REF SRM 53-10-4 FIG 11 PAGE 43. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 44,524 hrs · 34,731 cycles

UPPER AFT FUSELAGE BS 1130 EXTERIOR SKIN BETWEEN STRINGER 4L AND 5L HAS A 2" LONG GOUGE WITH ADJACENT SCRATCH. BLENDED DAMAGE OUT OF LIMITS REF SRM 53-30-1 FIG 1. REMOVED DAMAGE AREA. FABRICATED REPAIR DOUBLER ALODINED, AND PRIMED DOUBLER BEVELED EDGES OF DOUBLER COUNTERSUNK AND INSTALLED DOUBLER, ALODINED INTERIOR SURFACE OF DOUBLER AND PAINTED EXTERNAL SURFACE OF DOUBLER, REF SRM 53-30-3 FIG 1. REPAIR CLASSIFIED AS MAJOR. REPAIR IS CATAGORY A.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 44,524 hrs · 34,731 cycles

EXT REPAIR LOCATED AT STA 970-990, STR 18L FOUND NOT TO BE INSTALLED USING APPROVED DATA, REF SNRM# N00957 AND SRM 53-30-3 PG 13-14. FASTENER ROWS ARE INSUFFICIENT AT AFT LOWER CORNER. REMOVED EXISTING DOUBLER, FABRICATED NEW DOUBLER AND INSTALLED REF SRM 53-30-3 FIG 3. REPAIR IS CLASSIFIED AS MAJOR.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 44,524 hrs · 34,731 cycles

FLUSH REPAIR LOCATED AT STA 188, BL 0 FOUND NOT TO BE INSTALLED USING APPROVED DATA. REF SNRM NR N00917 REF SRM 53-30-3 FIG 2 DAMAGE CUTOUT NOT PARALLEL TO STRINGER CENTERLINE AND AMOUNT OF FASTENERS INCORRECT. REMOVED EXISTING REPAIR, REF SRM 51-30-02 ENLARGED CUTOUT REF SRM 53-30-3 FIG 1. FABRICATED REPAIR DOUBLER AND INSTALLED REF SRM 53-30-3. TREATED, PRIMED AND PAINTED, RESTORED CORROSION INHIBITER REF SRM 51-10-2 CLASSIFIED AS A MAJOR REPAIR, CATEGORY B.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 44,524 hrs · 34,731 cycles

EXT REPAIR LOCATED AT APPROX STA STA 470-490 BETWEEN STR 21R-22R FOUND NOT TO BE INSTALLED USING APPROVED DATA. REF SNRM # N00923 AND SRM 53-30-3 FIG 1 UPPER AND LOWER FASTENER ROWS DO NOT EXTEND BEYOND INTERNAL STRUCTURE. REMOVED DOUBLER, FABRICATED DOUBLER AND INSTALLED REF SRM 53-30-3 FIG 1, PG 5-8.

Part: STRINGER — DAMAGED (BS 265-285) · airframe 44,524 hrs · 34,731 cycles

STRINGER BETWEEN STA 265-285, STR 21L HAS SEVERAL NR 40 HOLES DRILLED IN STRINGER (FROM PREVIOUSLY INSTALLED REPAIR, REF N00918 & N01098). REMOVED STRINGER AND SPLICED IN NEW SECTION REF SRM 53-10-3 DETAIL 1, FIGURE 1, PAGE 4B. CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — MISREPAIRED · airframe 44,524 hrs · 34,731 cycles

REPAIR LOCATED ON RT WING NR 5 SLAT INBD TRACK FOUND NOT TO BE INSTALLED USING APPROVED DATA. REF SNRM NR N00930 AND CMM/SRM, THERE IS NO JUSTIFIED DOCUMENT FOR INSTALLATION OF STAINLESS DOUBLER IN THIS LOCATION ACCOMPLISHED REPAIR OF NR 5 SLAT SKIN EXTENSION REF FED EX DRAWING NR SR27-57-034 SHEET 1 OF 2. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — DENTED (BS 630) · airframe 44,524 hrs · 34,731 cycles

EXT FUSELAGE HAS DENT AT STA 630 STR 23R REMOVED DAMAGE AND REPAIRED USING A SINGLE DOUBLER REPAIR, REF SRM 53-30-3 FIGURE 13A PGS 74C THROUGH 74F. CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — MISREPAIRED · airframe 44,524 hrs · 34,731 cycles

EXT REPAIR LOCATED JUST AFT OF STA 700, STR 26L FOUND NOT TO BE INSTALLED USING APPROVED DATA. REF SNRM NR N00936 AND SRM 53-30-3 FIG 24, DOUBLER MISSING FASTENERS IN REPAIR AREA, RADIUS FILLER ALSO BENT. REMOVED DOUBLER, FABRICATED NEW DOUBLER AND FILLER. INSTALLED REPAIR WET W/ SEALANT REF SRM 53-30-3 FIG 5. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 44,524 hrs · 34,731 cycles

REPAIR LOCATED AT STA 265-285, BETWEEN STR 20L-21L FOUND NOT TO BE INSTALLED USING APPROVED DATA. REF SNRM NR N00918 AND SRM 53-30-3 FIG 3. INSUFFICIENT AMOUNT OF FASTENERS AT FRONT ROW (NEEDS 4 ROWS). REMOVED REPAIR AND REPLACED WITH A DOUBLER AND TRIPLER REPAIR REF EA I060484 AND FED EX EA NR 7-5330-99311 AND SRM 51-30-2. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 42,373 hrs · 32,981 cycles

WHILE PERFORMING MAIN CARGO DOOR OPS CHECK FOUND AFT DOOR FRAME BS 618, WL 228 TO BE CRACKED. REMOVED DAMAGE IN MCD AFT FRAME BS 618, WL 228. FABRICATED REPAIR PARTS AND INSTALLED REPAIR PARTS AND FASTENERS REMOVED FOR ACCESS. ALL WORK DONE IAW SRM 51-40-3 AND 51-30-2.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 42,373 hrs · 32,981 cycles

EXTERNAL FUSELAGE SKIN CHAFE DAMAGED UNDER FAIRING CONTACT AREA, BS 950D 15 - 990, STR 23L - 26L. SKIN CHAFE FOUND OUT OF LIMITS BS 973-989 IAW SRM 53-30-1. REPAIRED SKIN IAW SRM 53- 30-3 FIG 3. BLEND OUT FROM 950D 15 - 950E 12, AND 950E 18 TO 973 FOUND TO BE WITHIN LIMITS PER 727 SRM 53-30-1. BLEND OUT FROM BS 950E 12 TO 950E 18 FOUND TO BE OUT OF LIMITS AND TO BE REPAIRED ON N01061.

Part: SKIN — CHAFED (FUSELAGE) · airframe 42,373 hrs · 32,981 cycles

EXTERNAL FUSELAGE SKIN CHAFE DAMAGED UNDER FAIRING CONTACT AREA, BS 950D 15 - 990, STR 23L - 26L. SKIN CHAFE FOUND OUT OF LIMITS BS 973-989 IAW SRM 53-30-1. REPAIRED SKIN IAW SRM 53-30-3 FIG 3. BLEND OUT FROM 950D 15 - 950E 12, AND 950E 18 TO 973 FOUND TO BE WITHIN LIMITS PER 727 SRM 53-30-1. BLEND OUT FROM BS 950E 12 TO 950E 18 FOUND TO BE OUT OF LIMITS AND TO BE REPAIRED ON N01061.

Part: BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,373 hrs · 32,981 cycles

CORROSION STA 760 DELTA BEAM LWR ANGLE HAS CORROSION. REMOVED CORROSION. FOUND TO BE OUT OF LIMITS BS 760 DELTA BEAM LWR ANGLE. REMOVED AND INSTALLED NEW B S760 DELTA BEAM LWR ANGLE IAW SRM 51-30-2, 51-10-6 STEP 7, 51-10-1 FIG 1, 51-30-5.

Part: BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,373 hrs · 32,981 cycles

CORROSION STA 760 DELTA BEAM LWR ANGLE HAS CORROSION. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS BS 760 DELTA BEAM LWR ANGLE. REMOVED AND INSTALLED NEW BS 760 DELTA BEAM LWR ANGLE IAW SRM 51-30-2, 51-10-6 STEP 7, 51-10-1 FIG 1, 51-30-5.

Part: BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,373 hrs · 32,981 cycles

CORROSION STA 780 DELTA BEAM LWR ANGLE HAS CORROSION. REMOVED CORROSION. FOUND TO BE OUT OF LIMITS BS 780 DELTA BEAM LWR ANGLE. ACCESS LWR WEB. REMOVED, INSTALLED NEW BS 780 DELTA BEAM LWR ANGLE AND INSTALLED LWR WEB SUPPORT BEACON PANEL IAW SRM 51-30-2, 51-10-6 STEP 7, 51-10-1 FIG 1, 51-30-5.

Part: BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,373 hrs · 32,981 cycles

CORROSION STA 780 DELTA BEAM LWR ANGLE HAS CORROSION. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS BS 780 DELTA BEAM LWR ANGLE. ACCESS LWR WEB. REMOVED, INSTALLED NEW BS 780 DELTA BEAM LWR ANGLE AND INSTALLED LWR WEB SUPPORT BEACON PANEL IAW SRM 51-30-2, 51-10-6 STEP 7, 51-10-1 FIG 1, 51-30-5.

Part: SKIN — CHAFED (FUSELAGE) · airframe 42,373 hrs · 32,981 cycles

SKIN CHAFE DAMAGE FOUND AT BS 950E 12 TO 950E 19 BETWEEN STR 25L TO STR 26L. SKIN CHAFE FOUND TO BE OUT OF LIMITS FROM BS 950E 12 - 950E 19. REPAIRED DAMAGED SKIN FROM 950E 12 TO 950E 19 BETWEEN STR 25L TO 26L PER SRM 53-30-3 FIG 1.

Part: SKIN — CHAFED (FUSELAGE) · airframe 42,373 hrs · 32,981 cycles

SKIN CHAFE DAMAGE FOUND AT BS 950E 12 TO 950E 19 BETWEEN STR 25L TO STR 26L. SKIN CHAFE FOUND TO BE OUT OF LIMITS FROM BS 950E 12 - 950E 19. REPAIRED DAMAGED SKIN FROM 950E 12 TO 950E 19 BETWEEN STR 25L TO 26L PER SRM 53-30-3 FIG 1.

Part: SHEAR TIE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,373 hrs · 32,981 cycles

CORROSION (C53-111-01, 3) ON SHEAR TIE BS 950E LBL 18 WL 141. CORROSION OUT OF LIMITS. REPAIRED SHEAR TIE BS 950E, LBL 18, WL 141 PER SRM 53-10-4 FIG 15 AND EA 7-5310-55285.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,373 hrs · 32,981 cycles

MAIN CARGO COMPARTMENT CORROSION ON FLOORBEAM BS 344 WL 208 BL 0 TO LBL 45. REMOVED CORROSION ON FLOORBEAM STA 344, LBL 38, 2 X 8 X .020 FOUND OUT OF LIMITS IAW SRM 51-10-1. REMOVED AND FABRICATED NEW FLOOR BEAM BS 344, WL 208, RBL 6 TO LBL 65 (SKIN) BAC 1505-29222 7075-T6511 LOT 540294 IAW SRM 51-30-5. FABRICATED 4 EACH SPLICE ANGLES BAC 1410-2773, 7075-T6 LOT 540292 IAW SRM 53-10-8 FIG 9. ALODINED AND PRIMED PER SOPM 20-41-02. INSTALLED UPPER CHORD AND 4EA SPLICE ANGLES IAW SRM 53-10-8 FIG 9.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,373 hrs · 32,981 cycles

CORROSION (C53-111-01) AFT CARGO BAY, FLOORBEAM HAS CORROSION LWR FLANGE BS 1148, WL 200, LBL 20 TO LBL 29. *S/D* CORROSION ON AFT CARGO BAY FLOORBEAM LWR FLANGE BS 1148, WL 200, LBL 20 TO LBL 29 FOUND TO BE OUT OF LIMITS. INSTALLED REPAIR ANGLES AND FILLER ON LWR FLANGE BS 1148, WL 200, LBL 20 TO LBL 29 IAW SRM 53-10-8.

Part: TRUNNION — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,373 hrs · 32,981 cycles

CORROSION ON RIGHT TRUNNION UPPER TEE CHORD FWD UNDERSIDE, STA 295 WL 169 RBL 15. CORROSON ON NLG RT TRUNNION UPPER TEE CHORD STA 295, WL 169, RBL 15 FOUND TO BE OUT OF LIMITS. REPLACED CORRODED TEE CHORD AND INSTALLED NEW TEE CHORD PER 727 SRM 53-10-1, 51-30-2, 51-10-1.

Part: SENSING ELEMENT — FAULTY (NR 1 ENGINE) · airframe 40,803 hrs · 31,706 cycles

IN CRUISE NR 1 ENGINE OVERHEAT FLICKERED ON/OFF. REDUCED PWR AND COMPLETED ENG STRUT OVERHEAT CHECKLIST. LIGHT REMAINED OUT. THEN FLICKERED AND CAME ON. SHUTDOWN NR 1 ON TAXI IN. REMOVED AND REPLACED OVERHEAT SENSING ELEMENT, BOOT & CLAMP ON DUCT.

Part: UNKNOWN — ODOR (COCKPIT)

99-258 - BURNT RUBBER SMELL WAS NOTICED SHORTLY AFTER TAKEOFF. LEFT PACK ON ENG NR 1 WAS BLEED SOURCE. RAN LEFT PACK, WITH NR 1 ENG AS AIR SOURCE FOR ABOUT 20 MIN. NO BURNT RUBBER SMELL NOTICED.

Part: POWER UNIT — LEAKS (LOWER RUDDER)

98-245 AT FLT LVL 200, ON CLIMB-OUT 'A' SYS QUAN WAS 0.6 GAL GOOD PRESS. ON DESCENT QUANTITY DECREASE TOWARD 0 PRESS ERRATIC. MAN EXTEND GEAR AND FLAP A FLUID SHUTOFF SWITCH CLOSE AT 0835Z. FOUND LEAK LWR RUDDER PWR UNIT AT BASE RUDDER LOAD LIMIT VALVE MT PAD. REMOVED AND REPLACED PAD,VALVE PER MM 27-20-142 PG 401. SERV HYD SYS & OPER ALL SYS TO PURGE OUT AIR. OK FOR SERV.

Part: FITTING — CORRODED (VERT STAB)

NR 0467 008, WHILE WORKING CARD NR 7-5530-7-2310 F, FOUND CORROSION ON LT AND RT AFT CLOSURE RIB FITTING; CORROSION LOCATED AROUND BUSHING OUTSIDE DIAMETER. *S/D* REMOVED AND REPLACED LT AND RT AFT CLOSURE RIB FITTINGS IAW FED-EX EA NR 7-5510-32916.

Part: FLAP — DISBONDED (RT TE AFT FLAP)

NR 0470 007, RIGHT WING I/B AFT FLAP HAS SEVERAL DENTS ON THE MID SECTION OF UPPER SKIN. *S/D* REPAIRED RIGHT WING I/B AFT FLAP DENTS IAW FED-EX SRM 51-40-6.

Part: FLAP — DENTED (RT TE AFT FLAP)

NR 0469 006, REMOVED DAMAGE 5.5 BY 1.5 OF DAMAGE RIGHT WING I/B AFT FLAP UPPER SURFACE APPROXIMATELY 2.5 O/B OF I/B END.

Part: FLAP — DISBONDED (LT TE FOREFLAP)

LEFT INBOARD FOREFLAP IS DAMAGED AND DISBONDED AT INBOARD LOWER CORNER.

Part: REINFORCE CHORD — CORRODED (BS 1176)

NR 0086 003, CORROSION (C53-224-08) ON REINFORCEMENT CHORD AT BS 1176, LBL 48 AND 60, WL 208. *S/D* REMOVED CORROSION ON CHORD, FOUND TO BE OUT OF LIMITS PER FEX 727 SRM 53-10-1. REMOVED DAMAGED AREA, REPAIRED STA 1176 LT PER BOEING DRAWING NR 65C33557.

Part: FRAME — CRACKED (BS 640)

NR 0169 005, CRACK IN FRAME AT BS 640, RBL 13, WL 154. *S/D* REPAIRED CRACKED FRAME IAW FED-EX SRM 53-10-4.

Part: STRINGER — CORRODED (BS 1100-1120)

0238 002, CORROSION (C53-113-01, 2) ON STRINGER 30, BL 0 AT BS 1100 AND 1120. *S/D* REMOVED DAMAGED STRINGER AT BS 1080 TO 1140, STR 30 AND REPAIRED IAW FED-EX SRM 53-10-3.

Part: SHEAR TIE — CORRODED (BS 720)

NR 0163 004, CORROSION (C53-113-01) ON SHEAR TIE IN DISTRIBUTION BAY AT BS 720E BETWEEN STR 26 AND 25 RT. *S/D* REMOVED SHEAR TIE, FABRICATED NEW SHEAR TIE AND INSTALLED PER FED-EX SRM 53-10-4.

Part: SKIN — CORRODED (BS 1104-1124)

NR 0084 010, BULGES IN EXTERNAL SKIN AT BS 1104 AND 1124, STR 30. *S/D* REMOVED DAMAGED SKIN AT BS 1104 AND 1124, REPAIRED AS PER FED-EX SRM 53-30-03.

Part: CLOSING MECH — OUT OF ADJUST (PAX DOOR)

FORWARD ENTRY DOOR LIGHT ILLUMINATED IN-FLIGHT, DEPRESSURIZED AND DESCENT TO 5000 FEET MSL. A/C WAS DEPRESSURIZED FOR REMAINDER OF FLIGHT (15 MINUTES) AT 5000 FEET. REMOVED DOOR LINER AND ADJUSTED UPPER AND LOWER LATCH TORQUE TUBE CONTROL RODS. OPS CHECK NORMAL. REINSTALLED LINER. MM REF 52-11-01 PAGES 514 - 516 AND 52-11-61.

Part: DOOR — MISSING (HYD COMPT)

ACFT ARRIVED AT JFK WITH HYD SERVICE DOOR MISSING AND SLIGHT FAIRING DAMAGE. REPLACED MISSING HYD SERVICE DOOR AND MADE TEMPORARY REPAIR ON FAIRINGS.