N374FE
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
46 reports on file, 1998-10-02 – 2008-03-05.
Part: REDUCER — LEAKING (HYD SYSTEM) · airframe 84,856 hrs · 34,447 cycles
HYD 3 ELEV OFF AND HYD 3 QTY LOW ALERT ANNUNCIATED. HYDRAULIC QUANTITY STABILIZED AT 3.9 GALLON. TIGHTENED "B" NUT UNION (REDUCER) ON RT MAIN LANDING GEAR SWIVEL GLAND, SERVICED HYDRAULICS'S AND LEAK CHECKED CHECKED GOOD IAW MD10-10 AMM 20-50-01-2 AND MD10-10 AMM 29-00-00-2, MD10-10 AMM 12-00-00.
Part: INTERCOSTAL — CORRODED (ZONE 100) · corrosion level 2 · airframe 84,853 hrs · 34,443 cycles
LOWER AFT CARGO COMPARTMENT CORROSION ON INTERCOSTAL BETWEEN STRINGERS 44 AND 45 LT AT FS 1781. FABRICATED NEW INTERCOSTAL PER DAC DAW AFA 3870 REV F AND INSTALLED PER DC/MD10 SRM 51-33-01 VOL II.
Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 84,853 hrs · 34,443 cycles
CENTER WHEEL WELL LOWER SKIN HAS CORROSION FROM FS 1501 TO 1521 BETWEEN STR 50L TO51R. REMOVED, FABRICATED AND INSTALLED REPAIR PER E8-5330-113024" FUSELAGE-SKIN AT STA 1519 AND L-52-REPAIR.
Part: SKIN — CORRODED (RT WING) · corrosion level 2 · airframe 84,853 hrs · 34,443 cycles
RIGHT WING UPPER TRAILING EDGE PANEL HAS CORROSION ON THE UPPER SURFACE, APPROXIMATELY XORS 345. REMOVED CORROSION; OUT OF LIMITS IAW 10 SRM 51-21-01, VOL II & 57-31-01 FIG A, VOL III & 57-00-01 FIG A, VOL I. REMOVED PANEL IAW SRM 51-33-01, VOL II, 51-35-01, VOL II & 51-31-01, VOL III. REPAIRED PANEL BY REBUILDING PER DWG ARC 0263 REV AA & TPS 1001 REV E, IAW EA 8-5720-113029. INSTALLED PANEL IAW SRM 51-31-01, VOL II. MINOR REPAIR.
Part: WEB — CRACKED (BS 1781) · airframe 84,853 hrs · 34,443 cycles
CENTER CARGO COMP AT STA 1781 BELOW THE FLOOR AREA FROM L 52 - L 44 L WEB P/N AFA0154-5 1S CRACKED. FABRICATED NEW WEB PER REF. DAC DWG AFA 0154 REV. AT. INSTALLED IAW MD/DC 10 SRM 51-33-01 VOL. II. PART MARKED PER GMM7-0-1000. MINOR REPAIR.
Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 84,853 hrs · 34,443 cycles
CENTER WHEEL WELL LOWER INTERIOR SKIN HAS CORROSION BETWEEN STR 47 R AND STR 48 R FROM FS 1501 TO FS 1520. REMOVED, FABRICATED AND INSTALLED REPAIR PER E8-5330-113023 "FUSELAGE-SKIN AT STA 1507 AND 1519 AND L-48 RT-REPAIR.
Part: SHEAR TIE — DAMAGED (ZONE 100) · airframe 84,853 hrs · 34,443 cycles
FWD PIT AT STA 808 BETWEEN STR 42L AND STR 43L SHEARTIE HAS TOOL MARKS. FABBED NEW SHEARTIE IN REF TO FEDEX GMM 7-0-1001 AND DAC DWG RAM1470. REMOVED AND INSTALLED SHEARTIE AT STA 808 L42L - L43L IN REF TO DC/MD10-10 SRM 51-33-01 VOL II PG1.
Part: SKIN — FAILED (TE FLAP) · airframe 84,853 hrs · 34,443 cycles
LT I/B FLAP LOWER EXTERNAL SURFACE HAS ERRODED DENT FILLER. REMOVED FILLER,FABRICATED AND INSTALLED NEW REPAIR IAW MD/DC10 SRM 57-10-00 FIG 85 VOLI , 51-21-01 VOLII.
Part: SKIN — MISREPAIRED (TE FLAP) · airframe 84,853 hrs · 34,443 cycles
FOUND REPAIR DOUBLER R/W O/B FLAP LOWER SKIN STA XOF 458. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. EVALUATED REPAIR AND FOUND NOT TO BE WITHIN THE LIMITS OF DC/MD10 SRM 57-10-00 FIG9 VOL I. REWORKED REPAIR IAW DC/MD10 SRM 57-10-00 FIG 9 VOL I. MAJOR REPAIR.
Part: SKIN — CORRODED (CENTER TANK) · airframe 84,853 hrs · 34,443 cycles
LWW, CTR TANK UPPER SKIN CORRODED STA 1381, LBL 76. REMOVED AND REINSTALLED FASTENERS IAW 51-31-01 VOL II. REMOVED CORROSION, FOUND TO BE WITHIN LIMITS IAW SRM 57-00-01 FIG 1A VOL I AND SRM 57-33-01 FIG 1 VOL III. ALODINED AND PRIMED IAW SRM 51-21-01 VOL II
Part: SKIN — CORRODED (CENTER TANK) · airframe 84,853 hrs · 34,443 cycles
LWW, UPPER CTR TANK SKIN CORRODED, STA 1381, LBL 49. REMOVED AND REINSTALLED FASTENERS IAW SRM 51-31-01, VOL II. REMOVED CORROSION, FOUND TO BE WITHIN LIMITS IAW SRM 57-00-01 FIG 1A VOL I, AND SRM 53-33-01 FIG 1 VOL III. ALODINED AND PRIMED IAW SRM 51-21-01 VOL II
Part: ANGLE — CORRODED (FUSELAGE) · airframe 84,853 hrs · 34,443 cycles
LWW, SLANT BULKHEAD PANEL LWR ATTACH ANGLE CORRODED AT SEVERAL AREAS BET LT AND RT CORNERS, FWD AND AFT FACES, STA 1381. REMOVED CORROSION FOUND TO BE OUT OF LIMITS IAW MD/DC 10SRM 53-00-01 FIG 1A VOL I. MACHINED NEW SETION DWG APB7080 REV. D. INSTALLED PER SRM 53-40-00 FIG. 1 VOL I.
Part: DOOR FRAME — CRACKED (BS 692 S27L) · airframe 84,853 hrs · 34,443 cycles
NR 4 MCD LOWER JAMB SUPPORT FITTING HOLES A, B, C AND D HAS CRACK INDICATIONS FOUND WITH BHEC (SEE ATTACHED DRAWING). INSTALLED REPAIR BUSHINGS IN REFERENCE WITH DC/MD10-10 SRM VOLUME I, 53-50-00 PAGE 81 FIG 17 AT HOLE LOCATIONS A, B, C AND D TO CARGO DOOR JAMB BEAM ONLY. LOWER FITTING WAS REPLACED ON NON-ROUTINE N00950. MAJOR REPAIR
Part: SHEAR TIE — DAMAGED (ZONE 100) · airframe 84,853 hrs · 34,443 cycles
FWD PIT AT STA.808 BETWEEN STRINGER 34R AND 35R SHEAR TIE DAMAGED ON RADIUS. REMOVED, FABRICATED AND INSTALLED SHEAR TIE PER DC/MD10-10 SRM 53-13-01 VOL III FIG 8A AND 53-30-00 VOL I FIG10 AND 53-30-00 VOL I PAGE 34 FIG 9.
Part: DOOR FRAME — CRACKED (BS 738 S27L) · airframe 84,853 hrs · 34,443 cycles
NR 6 MCD LOWER JAMB SUPPORT FITTING HOLES A, C AND D HAS CRACK INDICATIONS FOUND WITH BHEC (SEE ATTACHED DRAWING). INSTALLED REPAIR BUSHINGS IN REFERENCE WITH DC/MD10-10 SRM VOLUME I, 53-50-00, PAGE 81 FIG 17 AT HOLE LOCATIONS A, C, AND D TO CARGO DOOR JAMB BEAM ONLY. LOWER FITTING WAS REPLACED ON NON-ROUTINE N00951. MAJOR REPAIR.
Part: FRAME — CORRODED (ZONE 100) · airframe 84,853 hrs · 34,443 cycles
FWD PIT AT STA 919 BETWEEN STR 51R AND 51L LOWER FLANGE, FRAME HAS CORROSION. REPAIRED LOWER FLANGE AT STA 919, LONG 51R & 51L IAW DC/MD10-10 SRM 53-30-00, VOL I FIGURE 5
Part: DOOR FRAME — CRACKED (BS 633 S27L) · airframe 84,853 hrs · 34,443 cycles
NR 1 MCD LOWER JAMB SUPPORT FITTING HOLE "C" HAS CRACK INDICATIONS, FOUND WITH BHEC (SEE ATTACHED DRAWING). INSTALLED REPAIR BUSHING IN REFERENCE WITH DC/MD10-10 SRM VOLUME I 53-50-00 PAGE 81 FIG 17 AT HOLE LOCATION C, TO CARGO DOOR JAMB BEAM ONLY. LOWER FITTING REPLACED ON NON-ROUTINE NR N00948.
Part: FLOORBEAM — CORRODED (ZONE 100) · airframe 84,853 hrs · 34,443 cycles
FWD PIT AT STA 879 RBL 57 FLOORBEAM HAS CORROSION. FOUND TO BE OUT OF LIMITS AND REPAIRED BY SPLICING IN NEW SECTION OF FLOORBEAM IAW SRM 53-00-01 VOL I FIG 7. THIS REPAIR IS CLASSIFIED AS MAJOR. ROLLER TRAY AT STA 765-879 RBL 56 REMOVED FOR ACCESS AND REINSTALLED IAW SRM 51-31-01 VOL II PG1.
Part: DOOR FRAME — CRACKED (BS 738 S27L) · airframe 84,853 hrs · 34,443 cycles
NR 6 MCD LOWER JAMB SUPPORT FITTING HOLES A, C AND D HAS CRACK INDICATIONS FOUND WITH BHEC (SEE ATTACHED DRAWING). INSTALLED REPAIR BUSHINGS IN REFERENCE WITH DC/MD10-10 SRM VOLUME I, 53-50-00, PAGE 81 FIG 17 AT HOLE LOCATIONS A, C, AND D TO CARGO DOOR JAMB BEAM ONLY. LOWER FITTING WAS REPLACED ON NON-ROUTINE N00951. MAJOR REPAIR.
Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 84,853 hrs · 34,443 cycles
NR 3 MCD LOWER JAMB SUPPORT FITTING HOLES A, B, C AND D HAS CRACK INDICATIONS FOUND WITH BHE (SEE ATTACHED DRAWING). INSTALLED REPAIR BUSHINGS IN REFERENCE WITH DC/MD10-10 SRM VOLUME I, 53-50-00 PAGE 81 FIGURE 17 AT HOLE LOCATIONS A, B, C AND D TO CARGO DOOR JAMB BEAM ONLY. LOWER FITTING WAS REPLACED ON NON-ROUTINE NR N00949.
Part: SHEAR TIE — CORRODED (ZONE 100) · corrosion level 2 · airframe 84,853 hrs · 34,443 cycles
LOWER FORWARD CARGO, STA 1099 BETWEEN L33L AND L35L, SHEAR TIE HAS CORROSION ON LOWER FLANGE, PART ADA0003-19 REMOVED CORROSION IAW DC/MD10-10 SRM, VOLUME II, 51-21-01 PAGE 28. ORIGINAL THICKNESS IS .071 IAW DAC DWG ADA0003, REV M, PARTS LIST, ITEM -19. MATERIAL REMOVED IS .030", MATERIAL REMAINING IS .041" PER TIMCO TOOL ( 8225B). FOUND TO BE OUT OF LIMITS IAW DC/MD10-10 SRM, VOLUME I, 53-00-01, FIGURE 1B. FABRICATED NEW -19 IAW DAC DWG ADA0003, REV M. HEAT TREAT LOAD NUMBER FOR NEW -19 IS( HT011508-1). MATERIAL ID FOR NEW -19 IS 7075-O, .071", PO NR 591979.2. INSTALLATION OF NEW -19 ACCOMPLISHED ON FEDEX NON-ROUTINE NR N00454.
Part: FRAME — CORRODED (ZONE 100) · airframe 84,853 hrs · 34,443 cycles
FOUND CORROSION ON FRAME LOWER SURFACE, FS 1099 BETWEEN L34L AND L35L. REMOVED CORROSION IAW SRM VOL II 51-21-01 PG 28A. FOUND TO BE OUT OF LIMITS IAW SRM VOL I 53-00-01 FIG 5 SHT 1. REMOVED AND REINSTALLED STRAP AND ANGLE IAW SRM VOLII 51-33-01. REMOVED AND REPLACED SHEAR TIE IAW SRM, VOL II 51-33-01. MAJOR REPAIR.
Part: SHEAR TIE — CORRODED (ZONE 100) · corrosion level 2 · airframe 84,853 hrs · 34,443 cycles
CAC, CORROSION, SHEAR TIE, FS 1099 BETWEEN L51 R AND L50R REMOVED CORROSION IN REFERENCE WITH DC/MD10-10 SRM, VOLUME II, 51-21-01, PAGE 28A. ORIGINAL THICKNESS IA .071 INCH IAW DC/MD10-10 SRM, VOL III 53-13-01, FIGURE 8A, SHEET 1, ITEM 33. MATERIAL REMOVED IS .011. MATERIAL REMAINING IS .060" PER TIMCO TOOL T8225C. FOUND TO BE WITHIN LIMITS IAW DC/MD10-10 SRM, VOLUME I, 53-00-01, FIGURE 1B. CUT OUT SHEAR CLIP AND REINSTALLED WITH SPLICE REPAIR IAW DC/MD10-10 SRM, VOLUME I, 53-30-00, FIGURE 10. MATERIAL ID FOR SPLICE IS 7075-T6, .071 INCH, PO NR 596629.4 IAW DC/MD10-10, SRM, VOLUME I , 53-30-00, FIGURE 10.
Part: SHEAR TIE — CORRODED (ZONE 100) · airframe 84,853 hrs · 34,443 cycles
LOWER FORWARD CARGO, STA 1099 BETWEEN L33L AND L35, SHEAR TIE HAS CORROSION ON LOWER FLANGE. REMOVED CORROSION IAW SRM VOLUME II, 51-21-01 PAGE 28. FOUND TO BE OUT OF LIMITS IAW SRM, VOLUME I, 53-00-01, FIGURE 1B. FABRICATED NEW -19 IAW DAC DGW ADA0003, REV M, INSTALLATION OF REPAIR ACCOMPLISHED ON NON-ROUTINE N00454.
Part: SHEAR TIE — DAMAGED (ZONE 100) · airframe 84,853 hrs · 34,443 cycles
FWD PIT AT STA 808 BETWEEN LONG 34R AND LONG 35R SHEAR TIE DAMAGED ON RADIUS. REMOVED, FABRICATED, AND INSTALLED SHER TIE PER SRM 53-13-01, VOL III FIG 8A AND SRM 53-30-00 VOL I FIG 10 AND SRM 53-30-00 VOL I PAGE 34 FIG 9 MAJOR REPAIR.
Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 84,853 hrs · 34,443 cycles
NR 5 MCD LOWER JAMB SUPPORT FITTING HOLES A AND D HAS CRACK INDICATIONS FOUND WITH BHEC. INSTALLED REPAIR BUSHINGS IAW SRM 53-50-00 VOL I PG 81 FIG 17 AT NR 5 FITTING LOCATION
Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 84,853 hrs · 34,443 cycles
NR 2 MCD LOWER JAMB SUPPORT FITTING HOLES A, B AND C HAS CRACK INDICATIONS, FOUND WITH BHEC. INSTALLED REPAIR BUSHINGS AT LOCATION NR 2 FITTING HOLES A, B AND C IAW SRM 53-50-00 VOL I PG 81 FIG 17.
Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 84,853 hrs · 34,443 cycles
MCD STA 1239 RBL 48 SEAT TRACK GOUGED AND WORN EVALUATED SEAT TRACK; SEVERAL BROKEN SCALLOPS, OUT OF LIMITS IAW DC/MD10-10 SRM 53-70-00 VOL I PG 21. REMOVED AND REINSTALLED 4 FLOOR PANELS AT STA 1199-1321 AND 1199-1259 RBL 27-76 IAW MD/DC 10-10 M/M 53-21-01-2. REMOVED DAMAGED SECTION OF TRACK AND INSTALLED NEW SECTION, IAW DC/MD10-10 SRM 53-70-00 VOL I PG 3/4 AT STA 1229 - 1249 RBL 48, MAT'L ID SECTION, HAT SPLICE AND PLATE ALODINED AND PRIMED IAW DC/MD10-10 SRM 51-21-01 PG 21 AND 24 VOL II. FABED SECTION IAW DC/MD10-10 SRM 53-70-00 VOL I PG 3 AND 4.
Part: FITTING — CRACKED (ZONE 200) · airframe 84,853 hrs · 34,443 cycles
UPPER MAIN CARGO DOOR, LOWER JAMB SUPPORT FITTING NR 6 IS CRACKED IN HOLE "A" BEYOND SRM LIMITS. REPLACED SUPPORT FITTING NUMBER 6 MAIN CARGO DOOR SPOOL LOCATION IN REF TO SRM 51-33-01 VOL II P/N AFA7132-1.
Part: FITTING — CRACKED (ZONE 200) · airframe 84,853 hrs · 34,443 cycles
UPPER MAIN CARGO DOOR, LOWER JAMB SUPPORT FITTING NR 7 IS CRACKED IN HOLES "A, B, D" BEYOND SRM LIMITS. REPLACED SUPPORT FITTING NR 7 MAIN CARGO DOOR SPOOL LOCATION IAW SRM 51-33-01 VOL II.
Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 84,853 hrs · 34,443 cycles
UPPER MAIN CARGO DOOR, LOWER JAMB SUPPORT FITTING NR 3 IS CRACKED IN HOLE "B" BEYOND SRM LIMITS. REPLACED SUPPORT FITTING NUMBER 3 MAIN CARGO DOOR SPOOL LOCATION IAW SRM 51-33-01 VOL II.
Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 84,853 hrs · 34,443 cycles
UPPER MAIN CARGO DOOR, LOWER JAMB SUPPORT FITTING NR 4 IS CRACKED IN HOLES "A, C, D" BEYOND SRM LIMITS. REPLACED SUPPORT FITTING NR 4 MAIN CARGO DOOR SPOOL LOCATION IAW SRM 51-33-01 VOL II.
Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 84,853 hrs · 34,443 cycles
UPPER MAIN CARGO DOOR, LOWER JAMB SUPPORT FITTING NR 1 IS CRACKED IN HOLE "C" BEYOND SRM LIMITS. REPLACED SUPPORT FITTING NR 1 MAIN CARGO DOOR SPOOL LOCATION IAW SRM 51-33-01 VOL II.
Part: SKIN — CRACKED (HORIZONTAL STAB) · airframe 84,853 hrs · 34,443 cycles
LT HORIZONTAL STAB UPPER REAR SKIN PANEL CRACKED, INITIATING FROM AFT EDGE OF SKIN AND PROCEDING FWD 21/4" (APPROXIMATELY). VERIFIED BY HFEC INSPECTION MARKED END OF CRACK. COMPLIED WITH AE 8-5510-116939. MAJOR REPAIR.
Part: SKIN — CRACKED (HORIZONTAL STAB) · airframe 84,853 hrs · 34,443 cycles
1 5/8" CRACK LOCATED ON THE RT HORIZONTAL STABILIZER AT THE INBOARD AFT CORNER OF THE OUTER SECTION UPPER AFT SKIN PANEL. END OF CRACK MARKED AND VERIFIED WITH HFEC INSPECTION. REPAIRED SKIN PLANK IAW EA 8-5510-116939, MAJOR REPAIR.
Earlier reports · 1998–2006 · 11 reports
2006
Part: PRESSURE SWITCH — FAILED (RT WING) · airframe 82,384 hrs · 33,292 cycles
NR 3 MANF FAIL INFLIGHT WHEN WING ANTI ICE SELECTED. FL340. COMPLIED WITH QRH. PERFORMED DECAY CHECK ON THE NR 3 MANIFOLD IAW MM 36-00-01-5, SYSTEM PASSED. CHECKED MANIFOLD FAIL DETECT UNIT IN CAC. FOUND RT WING PRESSURE SWITCH FAULTED. REMOVED AND REPLACED MANIFOLD FAIL DETECTION PRESSURE SWITCH IAW MM 36-23-03-4. OPS CHECKS NORMAL.
2005
Part: VALVE — MALFUNCTIONED (ANTI ICE SYSTEM) · airframe 79,150 hrs · 31,880 cycles
ENG 3 A-ICE DISAGREEMENT, LEVEL ONE ALERT ILLUMINATED STEADY WITH SWITCH IN EITHER POSITION. ENG NR 3 ANTI-ICE VALVE - INOP, FOUND OLD VALVE WAS BINDING SEVERLY AND DISAGREE LIGHT SWITCH WAS INOP ON VALVE. REMOVED AND REPLACED NR 3 NOSE COWL ANTI-ICE VALVE.
2004
Part: SKIN — DAMAGED (ZONE 100) · airframe 79,099 hrs · 31,851 cycles
NOT APPROVED FUSELAGE SKIN REPAIR AT LT AND RT LONG 44-47, STA 1526. SUBJECT REPAIRS WERE INSPECTED FOR COMPLIANCE WITH 14CFR 121.368, THE REPAIRS WERE EVALUATED TO BE ACCEPTABLE AS PERMANENT, PROVIDED REPAIRS ARE MODIFIED BY FEDEX EA 8-5310-84848.
Part: RAIL — CORRODED (ZONE 100) · airframe 79,099 hrs · 31,851 cycles
BULK CARGO DOOR JAMB RAIL P/N AFA3249-1 CORRODED APPROX AT STA 1755-1764. FILLER, CAP AND REPAIR ANGLE INSTALLED AFTER CORROSION REMOVAL IAW FEDEX EA 8-5310- 79980.
Part: PROXIMITY SWITCH — FAULTY (MLG) · airframe 78,426 hrs · 31,533 cycles
WHEN WE LOWERED THE GEAR FOR LANDING WE FELT THE GEAR COME DOWN BUT RED LIGHTS STAYED ON. WE MOVED THE HANDLE A FEW TIMES BUT NO HELP. RECYCLED GEAR AND THE RED LIGHTS STAYED ON. JIGGLED THE HANDLE AND THE LIGHTS FINALLY TURNED GREEN ALL AT THE SAME TIME. INDICATIONS SAME AT THE S/O PANEL . FACT IAW TAFI, 32-30-00-BB REMOVED AND REPLACED PROXIMITY SWITCH CONTROL UNIT IAW MM 32-61-00-2. OPS CHECKS GOOD.
2003
Part: SWITCH — INOPERATIVE (A/C DOOR) · airframe 77,821 hrs · 31,244 cycles
AIR CONDITIONING DOORS LIGHT ON S/O PANEL BEGAN FLICKERING INFLIGHT. FUEL WAS DUMPED AND LANDING ACCOMPLISHED AT SLC IAW RED TABS. ACN RELEASED FOR SERVICE IAW MEL/CDL: 52-04-04 CATEGORY: C EXPIRATION: 11OCT03, FACT 03OCT03 07:58 EWR R . REMOVED AND REPLACED ALL 3 DOOR SWITCHS IAW DC-10-10 MM 52-70-07-2. OPS CHECK GOOD.
2000
Part: WEB — CRACKED (RT MLG WW)
DURING MAINTENANCE, THREE 10 INCH CRACKS WERE FOUND ON RIGHT/CENTER WHEELWELL (Y=1386, Z=52) COMMON TO KEEL WEB, WEB DOUBLER, AND UPER WEB SPLICE, P/N'S, AEA0161-3, AEA0161-153, AND AEA0501 RESPECTIVELY. DATA WAS SENT TO BOEING/DOUGLAS 5-14-99 AND RESENT 7-9-99, WITH NO RESPONSE. (X)
1999
Part: WEB — CRACKED (KEEL BEAM)
DUR A/C P-F CONV AT AERONAVALI, 3 10' CRACKS WERE FOUND AT Y=1386 COMMON TO KEEL WEB, WEB DOUBLER & AEA0501 KEEL WEB UPPER SPLICE. REPAIRED KEEL WEB AND WEB DOUBLER PER IAW FEDEX EA NR 8-5314-44061.
1998
Part: SKIN — CRACKED (LT FLAP)
DUR A/C P-F CONV FOUND DAMAGE AT XIFH=288.14 ON THE UPPER SURFACE OF LT I/B FLAP SKIN. REMOVED AND REPLACED O/B UPPER SKIN SECTION DAMAGE ARC2369. SRM 57-10-00 FIG 4 IAW FEDEX IAW EA NR 8-5752-44069.
Part: BOLT — CORRODED (FUSELAGE)
DUR A/C P-F CONV CORROSION WAS FOUND IN ALL FOUR HOLE BORES COMMON TO ABA7003-2 & ABA7172 FITTINGS. THREE BOLTS FAILED IN TENSION. REMOVED AND REPLACED BOLTS FROM BORES IAW FEDEX EA NR 8-5311-41885.
Part: SKIN — CORRODED (FS 1099 - 1541)
DUR A/C P-F CONV ON EXT LWR FUSELAGE FROM BS 1099 TO BS 1541 CORROSION. REMOVED AND REPLACED FUSELAGE BELLY SKIN FROM Y=1119 TO Y-1308, BETWEEN L48L-L48R. REPAIRED THEN INSTALLED AN EXT SKIN SPLICE SIMILAR TO SRM 5320, FIG 17 AT Y-1308 TO RESTORE STRENGTH IAW FEDEX EA NR 8-5334-41825.