N17356

Part: A/C PACK — FAILED (LEFT) · airframe 4,540 hrs · 1,533 cycles

LEFT PACK TRIPPED OFF UNCONTROLLABLE TEMP EVEN AFTER RESET REQUESTING MEL 2151AM. FMCS BITE AGREES WITH POSITION WITH PACK. NO LOW AIR SUPPLY MESSAGE. BITE TEST OF CPC 1 . NO PRESENT FAULTS. BITE TEST OF CPC 2. NO FAULTS. APPROVED IAW MEL 2151AM ECS AGREES WITH PACK POSITION. PLACARD APPLIED. PERFORMED AIR CONDITION SYS TEST FOR LT PACK IAW WITH AMM 21-00-00. TEST PASSED. UPON TURNING ON LT PACK. COULD SMELL A SENSE OF A BURNING. LT PACK IS HIGHER THAN RT PACK BY 30 DEGREES. WHILE RUNNING LT PACK OBSERVED NO DRAW OF AIR FROM RAM AIR INLET & NO EXHAUST OF AIR FROM EXIT LOUVERS. SUSPECT LT PACK ACM IS SEIZED. R & R OF LT PACK AIR CYCLE MACHINE. OPS CHECKED GOOD.

Part: SLIDE — UNPACKED (ZONE 800) · airframe 4,128 hrs · 1,388 cycles

SLIDE AT POS 2L HAS A LOT OF MATERIAL COMING FROM UNDERNEATH THE SLIDE COVER INSTALLED SAFTEY PIN ON SLIDE. REPACKED Z FOLD ON L-2 SLIDE. REMOVED SAFETY PIN AND STOWED IN POUCH IN SLIDE.REF MM25-66-01-400-804. CHECK SLIDE EXPIRATION DATE AND SHIPPING / SAFETY PIN REMOVAL AND OBSERVE PROPER TORQUE OF SLIDE ATTACH FASTENERS WHERE APPLICABLE. INSPECT GIRT BAR ALIGNMENT, SLIDE TO AIRFRAME ATTACHMENTS SECURITY, PER GMM 09-25-05

Part: FILTER — DIRTY (ZONE 100) · airframe 3,532 hrs · 1,202 cycles

UNKNOWN BURNING ODOR COMING FROM AIR VENT OVER FORWARD FA JUMPSEAT. CHECKED CEILING AREA ABOVE ENTRY. NO ODORS PRESENT & NO ANOMALIES FOUND. OPS SAFETY VIDEO & CHANGED LIGHTING SCHEMES WHILE RUNNING PACKS & WITH RECIRC FANS ALONE. ALL OVENS & AFT CHILLER OPERATING. COULD NOT DUPLICATE ODOR. GAINED ACCESS TO MIX BAY. NO ODORS NOTED. DISCONNECTED & RECONNECTED RECIRC FANS. START, STOP & OPS SMOOTH. FILTERS HAVE DUST BUILD UP. NO ODORS NOTED IN AVIONICS BAY. VERIFIED ALL C/B'S CLOSED ON P91 & P92 PANELS. CHKD E11 & E6 RACK UNITS IN AFT CARGO BAY. NO ODORS NOTED. REPLACED BOTH LT & RT RECIRC FILTERS IAW AMM 21-25-01/401. NO FAILED UNITS OR SUSPECT ITEMS SHOWING ON CURRENT OR EXISTING FAULTS. ACCOMPLISHED 10 MIN IDLE RUN BOTH ENGS WITH ALL BLEEDS & BOTH PACKS RUNNING IAW FIM 21-00 TASK 830, STEP Q. NO SUSPECT ODORS GENERATED THROUGHOUT CABIN.

Part: CABLE ASSY — FRAYED (EVAC SLIDE) · airframe 58,415 hrs · 31,353 cycles

L-2 DOOR EMERGENCY ESCAPE SLIDE LATCH CABLE HAS BROKEN STRANDS. REPLACED L-2 DOOR EMERGENCY ESCAPE SLIDE LATCH CABLE PER MM 25-61-35.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 57,678 hrs · 30,967 cycles

WEB CRACKED BODY STATION 294.3 LT INTERCOSTAL 12. REMOVED AND REPLACED CRACKED WED PER ECRA 5311-01424 REV A.

Part: KEELBEAM — CORRODED (FUSELAGE) · airframe 57,678 hrs · 30,967 cycles

RIGHT KEEL BEAM HAS CORROSION ON OUTBOARD FLANGE AT STATION 500D PLUS 3 - 6. REPAIRED KEEL BEAM RIGHT SIDE PER SRM 53-60-12 PAGE 206 FIGURE 201.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 57,678 hrs · 30,967 cycles

WEB CRACKED BODY STATION 294.3 LT INTERCOSTAL 16. REMOVED AND REPLACED CRACKED WEB PER ECRA 5311-01424 REV A.

Part: ATTACH FITTING — CRACKED (FUSELAGE) · airframe 57,678 hrs · 30,967 cycles

ATTACH CLIP STATION 294.5 LT STR 10 CRACKED. INSTALLED REPAIR/MODIFICATION PER ECRA 5311-01423.

Part: WEB — CRACKED (CARGO DOOR) · airframe 57,678 hrs · 30,967 cycles

C2 DOOR WEB CRACKED ON UPPER FORWARD SIDE UNDER PULLEY BRACKET OF COUNTER BALANCE. INSTALLED NEW FRAME PER 51-40-02.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 57,678 hrs · 30,967 cycles

C-2 DOOR EXTERIOR SKIN CRACKED AT HANDLE CUTOUT AFT UPPER CORNER. CUT OUT DAMAGE, FABRICATED AND INSTALLED REPAIR DOUBLER AND FILLER PER SRM 52-00-01 FIG 201.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 57,678 hrs · 30,967 cycles

FUSELAGE SKIN CREASED AFT OF PREVIOUS REPAIR, STATION 847 AT S-4L. REPAIRED PER SRM 53-00-01 FIG 201, PAGE 23.

Part: FRAME — CORRODED (FUSELAGE) · airframe 57,678 hrs · 30,967 cycles

B737-53-4-0033 NWW LT TUNNEL LEVELING COMPOUND AT BOTTOM AREA BETWEEN FRAMES 259.5 AND 277 IS BUBBLED UP AND LOOSE CTN 53-310-202 SEQ 309 03-5310-1-2613. REMOVED AND REPLACED LT NWW CHORD REF SRM 51-40-02 AND BOEING DWG 65-45819.

Part: SKIN — CRACKED (L1 DOOR) · airframe 57,678 hrs · 30,967 cycles

L-1 DOOR SKIN IS CRACKED AT 4TH STOP FROM TOP, AFT SIDE OF DOOR. TRIMMED OUT CRACK AND INSTALLED REPAIR DOUBLER PER ECRA 5210-02035.

Part: SKIN — CRACKED (L1 DOOR) · airframe 57,678 hrs · 30,967 cycles

L-1 DOOR SKIN IS CRACKED AT 5TH STOP FROM TOP. TRIMMED OUT CRACK AND INSTALLED REPAIR DOUBLER PER ECRA 5210-02035.

Part: SKIN — GOUGED (HORIZ STAB) · airframe 57,678 hrs · 30,967 cycles

02/21/2008, LEFT HORIZONTAL STABILIZER STATION 108 16 INCHES AFT OF LEADING EDGE PANEL APPROXIMATELY 8.5" X 2.5" X .300 DEPTH. COMPLETED INTERIM REPAIR OF LEFT HORIZONTAL STABILIZER PER SRM 55-10-01 REPAIR 4, ISSUED DIP TO INSPECT FASTENERS EVERY 3,000 FLT HRS AND INSTALL SOLID FASTENERS WITHIN 15,000 FLT CYC'S AFTER BLIND FASTENERS INSTALLED. 09/26/2008, REMOVED DAMAGE AND INSTALLED PERMANENT REPAIR PER SRM 55-10-01, REPAIR 7.

Part: SKIN — CRACKED (FUSELAGE) · airframe 57,678 hrs · 30,967 cycles

R1 DOOR FUSELAGE SKIN AFT OF LOWER CUTOUT CRACKED. CUT OUT DAMAGED AREA AND INSTALLED REPAIR PLATES AND FILLERS PER SRM 53-10-01 REPAIR 2. RESTORATION OF AIRCRAFT FINISH WILL BE ACCOMPLISHED ON L/P 9698525 SEQ N00667.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 57,678 hrs · 30,967 cycles

STATION 986.5 FLOORBEAM SURFACE CORROSION AT LBL 29 AND LBL 32. INSTALLED REPAIR STRAP PER SRM 53-00-51 FIGURE 201.

Part: SKIN — CRACKED (FUSELAGE) · airframe 56,738 hrs · 30,551 cycles

CRACK AT AFT END OF E&E COOLING EXHAUST PORT AT CENTER OF FUSELAGE. INSTALLED REPAIR PER EC/RA 5330-03806, STEPS 1-19. PLACED ON DIP FOR PERMANENT REPAIR TO BE ACCOMPLISHED WITHIN 12 MONTHS.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 56,071 hrs · 30,264 cycles

FOUND CORROSION ON FLOORBEAM AT BS 328 AND LBL 30.0 AS SEEN FROM E&E COMPARTMENT CEILING. INSTALLED REPAIR AND REPAIR PARTS PER SRM 53-10-51.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 56,071 hrs · 30,264 cycles

FOUND CORROSION ON CABIN LATERAL FLOORBEAM UPPER CAP AT BS 344 AND LBL 6.0 AS VIEWED FROM E&E CEILING. INSTALLED REPAIR PER SRM 53-10-51.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 55,137 hrs · 29,840 cycles

FWD CARGO DOOR INNER SKIN LIGHTNING HOLE CRACKED, AFT SIDE CENTER ROW. REPAIRED SKIN IAW ECRA 5232-01094.

Part: SKIN — CORRODED (BS 460-480) · airframe 52,630 hrs · 28,674 cycles

INSPECTION FOUND SURFACE CORROSION ON SKIN UNDER NR 1 DME ANTENNA AT STA 460-480, S29L. A REPAIR DOUBLER WAS INSTALLED IAW ECRA 5331-01285.

Part: FRAME — CORRODED (BS 227 S28LR) · airframe 52,630 hrs · 28,674 cycles

INSPECTION FOUND FRAME CORRODED AT STA 227, S28L TO S28R, LBL 4 TO RBL 4. THE FRAME WAS REPAIRED IAW ECRA 5311-01286.

Part: SKIN — CRACKED (NR 5 SLAT) · airframe 52,630 hrs · 28,674 cycles

INSPECTION FOUND A .25 INCH CRACK AT FASTENERS (11 EACH) IN RIGHT WING NR 5 SLAT LOWER SKIN. THE SLAT SKIN WAS REPAIRED IAW SRM 57-43-01.

Part: SKIN — CRACKED (NR 6 SLAT) · airframe 52,630 hrs · 28,674 cycles

INSPECTION FOUND A 5 INCH CRACK AT FASTENER IN RIGHT WING NR 6 SLAT LOWER SKIN. THE CRACKED AREA WAS REMOVED AND A DOUBLER REPAIR WAS INSTALLED IAW SRM 57-43-01.

Part: SKIN — CRACKED (NR 3 SPOILER) · airframe 52,630 hrs · 28,674 cycles

INSPECTION FOUND A 0.125 INCH CRACK IN NR 3 SPOILER UPPER SKIN. A DOUBLER REPAIR WAS INSTALLED IAW SRM 57-70-01.

Part: CHARGER — INOPERATIVE (SEAT 21 ABC) · airframe 49,277 hrs · 27,074 cycles

INSPECTION FOUND SEAT 21 ABC EMERGENCY LIGHT INOPERATIVE. THE BATTERY CHARGER ASSEMBLY WAS REMOVED AND REPLACED IAW MM 33-51-81.

Part: SKIN — CRACKED (PAX DOOR) · airframe 46,741 hrs · 25,818 cycles

INSPECTION FOUND A .5 INCH CRACK IN THE MID INNER SKIN PANEL OF THE FORWARD ENTRY DOOR. THE SKIN WAS REPAIRED IAW ECRA 5211-01072.

Part: SKIN — CRACKED (NR 3 SLAT) · airframe 46,741 hrs · 25,818 cycles

INSPECTION FOUND A 1 INCH CRACK IN NR 3 SLAT LOWER EXTERNAL SKIN AT WS 270. A REPAIR WAS INSTALLED IAW SRM 57-43-01.

Part: SKIN — LOOSE (FUSELAGE) · airframe 46,741 hrs · 25,818 cycles

INSPECTION FOUND SMOKING AND LOOSE RIVETS IN FUSELAGE SKIN AT STA 1006-1016, S2L TO S3L. REMOVED AND REPLACED DOUBLER IAW SRM 53-00-01, FIGURE 229, PAGE 332.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 46,741 hrs · 25,818 cycles

INSPECTION FOUND FLOORBEAM CORRODED AT STA 312, RBL 21. THE CORRODED SECTION OF FLOORBEAM WAS REMOVED AND A NEW SECTION WAS INSTALLED IAW SRM 53-10-51, FIGURE 205.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 46,741 hrs · 25,818 cycles

INSPECTION FOUND A 1 INCH CRACK IN LEFT O/B SEAT TRACK AT STA 727B. THE CRACKED AREA WAS CUT OUT AND A REPAIR STRAP WAS INSTALLED IAW ECRA 5321-01200.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 46,741 hrs · 25,818 cycles

INSPECTION FOUND CABIN FLOORBEAM CORRODED AT UPPER FLANGE STA 986.5 FROM BL 0 TO RBL 36. THE CORRODED SECTION OF FLOORBEAM WAS REMOVED AND A NEW SECTION WAS INSTALLED IAW ECRA 5310-03851.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 46,741 hrs · 25,818 cycles

INSPECTION FOUND ZEE ANGLE CORRODED AT R-2 DOOR, STA 967-986.5, RBL 45. THE ZEE ANGLE WAS REMOVED AND REPLACED IAW SRM 51-10-02 AND 51-40-02.

Part: FLOORBEAM — CRACKED (FUSLEAGE) · airframe 46,741 hrs · 25,818 cycles

INSPECTION FOUND A CRACK IN THE LONGITUDINAL FLOORBEAM UPPER CHORD AT ITS ATTACHMENT TO THE TRANSVERSE FLOORBEAM AT STA 727B, LBL 45.50. THE CRACK WAS LOCATED ON THE OB SIDE OF THE LONGITUDINAL FLOORBEAM AT THE FIRST HI-LOK FASTENER HOLE FORWARD OF STA 727B. THE CRACK RAN FROM THE AFT EDGE OF THE LONGITUDINAL FLOORBEAM TO THE HI-LOK FASTENER HOLE. THE FLOORBEAM WAS REPAIRED IAW ECRA 5321-01200.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 46,741 hrs · 25,818 cycles

INSPECTION FOUND A 1 INCH CRACK IN STRINGER 16L AT STA 500C. A NEW STRINGER SECTION WAS SPLICED IN IAW SRM 53-00-03.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 43,953 hrs · 24,296 cycles

INSPECTION FOUND A .5 INCH CRACK AND UPPER SHIM DAMAGE IN FLOOR PANEL SUPPORT AT STA 540, LBL 10. THE FLOOR SUPPORT WAS REMOVED AND REPLACED IAW SRM 51-10-02.

Part: SKIN — DENTED (CARGO DOOR) · airframe 43,953 hrs · 24,296 cycles

INSPECTION FOUND AFT BAGGAGE BIN DOOR SKIN DENTED AT CENTER AREA 38 INCHES FROM BOTTOM AND FORWARD 22 INCHES FROM AFT WITH A DEPTH OF 0.128 INCH, 3.5 INCH WIDTH, AND 6 INCHES IN LENGTH. THE DENTED AREA WAS REMOVED AND A REPAIR DOUBLER WAS INSTALLED IAW SRM 52-00-01.

Part: SOCKET — INOPERATIVE (CABIN) · airframe 41,427 hrs · 22,949 cycles

EMERGENCY ESCAPE PATH AISLE LIGHT INOP AT SEAT 23 LEFT. REPLACED LIGHT SOCKET ASSEMBLY PER MM 33-51-81.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND A .25 INCH CRACK IN FLOORBEAM AT STA 520, RBL 45.5. THE FLOORBEAM WAS REPAIRED IAW ECRA 5310-04105 AND EA 04-5310-0669.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND FLOORBEAM UPPER FLANGE CORRODED AT STA 294.5, BL 0. THE FLOORBEAM UPPER FLANGE WAS REPAIRED IAW ECRA 5310-04110 AND EA 04-5310-0697.

Part: SKIN — CRACKED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND A 1 INCH CRACK IN FUSELAGE EXTERNAL SKIN AT R-1 DOOR LOWER HINGE CUTOUT. THE SKIN WAS REPAIRED IAW ECRA 5330-03036 AND EA 04-5311-0688.

Part: DOOR FRAME — DENTED (CARGO BAY) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND FORWARD CARGO DOOR JAMB DENTED AT STA 492, FLOOR LINE. THE DENTED AREA WAS REMOVED AND A REPAIR WAS INSTALLED IAW SRM 51-70-13.

Part: SKIN — GOUGED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND A VERTICAL GOUGE IN FUSELAGE EXTERNAL SKIN FROM WINDOW EDGE TO LAP SEAM AT STA 877, STRINGER 14L. THE SKIN WAS REPAIRED IAW ECRA 5330-03037.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND A CRACK APPROXIMATELY .25 INCH LONG AT HOLE IN STRINGER 21L BETWEEN STA 460 - 480. THE HOLE WAS REAMED TO 0.312 INCH. AN ANGLE REPAIR WAS INSTALLED IAW SRM 53-00-03.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND FLOORBEAM CORRODED AROUND FASTENER HOLES ON TOP SURFACE AT STA 947, RBL 12 TO LBL 25. THE CORROSION WAS REMOVED AND A REPAIR WAS INSTALLED IAW ECRA 5310-03851.

Part: SKIN — DENTED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND FUSELAGE SKIN DENTED AT STA 344 AND TWO INCHES BELOW S19R. THE DENTED AREA WAS REMOVED AND A REPAIR WAS INSTALLED IAW ECRA 5330-03035 AND EA 04-5310-0679.

Part: WEB — CRACKED (CARGO BAY) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND A 1 INCH CRACK BETWEEN RIVETS ON FORWARD EDGE OF WEB ON AFT CARGO DOOR CUTOUT AFT SIDE, BS 847 BETWEEN S24R AND S25R. THE CRACKED AREA OF WEB WAS REMOVED AND A REPAIR WEB WAS INSTALLED IAW SRM 53-60-15, 51-20-01, AND 51-40-02.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND INTERCOSTAL CRACKED BETWEEN STA 500D AND 520, RBL 45, WL 208.1. THE INTERCOSTAL WAS REMOVED AND A NEW INTERCOSTAL WAS INSTALLED IAW SRM 51-40-2.

Part: DOOR FRAME — DENTED (CARGO BAY) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND FORWARD CARGO DOOR JAMB DENTED AT STA 440 AT FLOOR LINE. THE DENTED AREA WAS REMOVED AND A REPAIR WAS INSTALLED IAW DRAWING 69-15224 AND SRM 51-70-13.

Part: SKIN — DELAMINATED (RT WING) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND RT WING L/E DELAMINATED AT WBL 254.0. THE LEADING EDGE WAS REPAIRED IAW SRM 57-41-01, FIGURE 2, 51-70-16, PARAGRAPH 3A, ECRA 5720-01838, AND EA 04-5741-0672.

Part: FRAME — CRACKED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND A 1 INCH CRACK IN R-1 DOOR FORWARD STUB FRAME JUST ABOVE THE INNER FLANGE OF THE LOWER SILL AT STA 294.5. THE INNER FLANGE OF THE FWD FRAME WAS REPAIRED IAW EA 5310-03895 AND SRM 51-20-01.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND FLOORBEAM CORRODED AROUND FASTENER HOLES ON TOP SURFACE AT STA 967, LBL 20 - LBL 45. THE CORRODED SECTION OF FLOORBEAM WAS CUT OUT AND A REPAIR WAS INSTALLED IAW ECRA 5310-04101 AND EA 04-5310-0678.

Part: STRAP — CORRODED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND FLOORBOARD SUPPORT STRAP CORRODED AT STA 1006 - 1016, LBL 2. THE STRAP WAS REMOVED AND A NEW STRAP WAS INSTALLED IAW DRAWING 65C32677 AND SRM 51-10-2.

Part: SKIN — DAMAGED (CARGO DOOR) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND INNER SKIN TORN ON INSIDE OF FWD CARGO DOOR AT LIGHTENING HOLE. THE TORN AREA WAS REMOVED AND A DOUBLER WAS INSTALLED IAW SRM 51-70-13, 52-30-01, AND 51-40-02.

Part: WEB — CORRODED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND CREASE BEAM SHEAR WEB CORRODED AT STA 797, LT SIDE. A NEW WEB WAS INSTALLED IAW SRM 51-40-2.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND FLOOR SUPPORT ATTACH ANGLE CORRODED AROUND FASTENER AT STA 259, RBL 2.0. THE CORROSION WAS REMOVED IAW SRM 51-10-2 AND A REPAIR WAS INSTALLED IAW SRM 51-70-11.

Part: WEB — CRACKED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND A 1.25 INCH CRACK IN WEB AT FRAME OF AFT PIT CUTOUT AREA, FORWARD SIDE, BS 787, S25R. THE WEB WAS REMOVED AND A NEW WEB WAS INSTALLED IAW SRM 53-60-15, FIGURE 1, 51-20-01, AND 51-40-01.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 967 - 986, LBL 16. THE FLOOR SUPPORT WAS REMOVED AND REPLACED IAW SRM 51-40-2.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND FLOOR SUPPORT CUSP ANGLE CORRODED AT STA 927 - 1000, LBL 50. THE FLOOR SUPPORT CUSP ANGLE WAS REMOVED AND REPLACED IAW SRM 51-40-2.

Part: ANGLE — CORRODED (L1 DOOR SILL) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND L-1 LOWER DOOR SILL INNER ANGLE SUPPORT CORRODED FROM STA 315 - 340. THE ANGLE SUPPORT WAS REMOVED AND A NEW ANGLE SUPPORT WAS INSTALLED IAW SRM 51-40-02.

Part: SEAT TRACK — CORRODED (CABIN) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND SEAT TRACK CORRODED AT STA 900 - 927, RBL 45. THE CORRODED SECTION OF SEAT TRACK WAS REMOVED AND A REPAIR SECTION OF SEAT TRACK WAS INSTALLED IAW SRM 51-10-02 AND 53-00-52.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND AFT CABIN FLOORBEAM T-CAP CORRODED FROM LEFT TO RIGHT SIDE AT STA 986.5. THE FLOORBEAM T-CAP WAS REMOVED AND REPLACED IAW SRM 51-70-13 AND ECRA 5310-03851.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND FLOOR SUPPORT CORRODED IN AFT CARGO COMPARTMENT AT STA 727E-807 ABOVE STRINGER 26R. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED USING TWO SPLICES IAW SRM 53-60-53.

Part: SKIN — DENTED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND FOUR DENTS WITHIN A FOUR INCH AREA IN FUSELAGE EXTERNAL SKIN AT STA 460, STRINGER 7R. REPAIRED SKIN IAW SRM 53-00-01, FIGURE 201.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND FLOORBEAM CAP UPPER AND LOWER FLANGE CORRODED AT STA 312, RBL 12. THE UPPER CAP WAS REMOVED AND A REPAIR WAS INSTALLED IAW SRM 53-10-51, FIGURE 205.

Part: SEAT TRACK — CORRODED (CABIN) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND SEAT TRACK CORRODED AT STA 900 - 947, LBL 45, LBL 25, AND RBL 25. THE CORRODED SECTIONS OF SEAT TRACK WERE REMOVED AND REPAIR SECTIONS WERE INSTALLED IAW SRM 51-40-02.

Part: SKIN — CRACKED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND A 0.3 INCH CRACK IN FUSELAGE SKIN AT R-2 DOOR LOWER HINGE CUTOUT, STA 951, S15R-16R. THE SKIN WAS REPAIRED IAW SRM 53-60-01, FIGURE 7, SHEET 207.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 947-967, LBL 12. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-40-2.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND L-1 DOOR LOWER SILL OUTER ANGLE CORRODED AT STA 315-340. THE ANGLE WAS REMOVED AND A NEW ANGLE WAS INSTALLED IAW SRM 51-40-02.

Part: STRAP — CORRODED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND FLOORBOARD SUPPORT STRAP CORRODED AT STA 1006-1016, RBL 2. THE STRAP WAS REMOVED AND A NEW STRAP WAS INSTALLED IAW SRM 51-10-2 AND DRAWING 65C32677.

Part: WEB — CORRODED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND LT AND RT FLOOR WEBS CORRODED AROUND FASTENERS AT STA 1006-1016, BL 0 TO LEFT SIDE AND BL 0 TO RIGHT SIDE. THE CORRODED SECTIONS OF WEB WERE ROUTED OUT AND REPAIR DOUBLERS WERE INSTALLED IAW SRM 51-70-13, FIGURE 1.

Part: SKIN — DENTED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND FUSELAGE SKIN DENTED AND CREASED AT STA 350, STRINGER 22R. A REPAIR WAS INSTALLED IAW SRM 51-20-01 AND 53-00-01, FIGURE 202, SHEET 3.

Part: SKIN — DENTED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND TWO DENTS IN FUSELAGE EXTERNAL SKIN AT STA 727A, STRINGER 8L. THE DENTED AREA WAS REPAIRED IAW SRM 53-00-01, FIGURE 213.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 328, RBL 26.75. THE FLOOR SUPPORT WAS REMOVED AND A NEW SUPPORT WAS INSTALLED IAW SRM 51-40-02.

Part: CREASE BEAM — CORRODED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND CORROSION ON CREASE BEAM AT R-1 DOOR, STA 315, RBL 50.5. THE CREASE BEAM WAS REMOVED AND REPLACED IAW SRM 51-40-02.

Part: BRACKET — CRACKED (FWD CARGO BAY) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND A 2 INCH CRACK IN FWD CARGO COMPARTMENT BRACKET FOR VHF NR 2 ON AFT SIDE OF FRAME AT STA 500 BETWEEN STRINGERS 28L AND 28R. THE BRACKET WAS REMOVED AND REPLACED IAW SRM 51-10-02 AND 51-40-02.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND EXTERNAL FUSELAGE SKIN CREASED WITH A GOUGE AT STA 285 JUST BELOW STRINGER 4L. A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-00-01, FIGURE 202, 51-20-01, AND 51-40-00.

Part: SEAT TRACK — CORRODED (CABIN) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND SEAT TRACK CORRODED AT STA 927-967, RBL 13. THE TRACK WAS REMOVED AND A NEW TRACK WAS INSTALLED IAW SRM 51-10-2 AND 53-00-52.

Part: SKIN — CRACKED (LT SLAT) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND LT WING NR 3 SLAT COVER SKIN CRACKED AROUND FASTENER HOLE AT WBL 254.0. THE CRACKED SKIN WAS CUT OUT. DOUBLER AND FILLER WERE INSTALLED IAW SRM 57-43-01, PAGE 216.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND TWO FLOOR SUPPORTS CORRODED AT STA 967-986, RBL 16. THE FLOOR SUPPORTS WERE REMOVED AND NEW FLOOR SUPPORTS WERE INSTALLED IAW SRM 51-40-2.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 950, LBL 25 - LBL 40. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-40-2.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 38,368 hrs · 21,411 cycles

INSPECTION FOUND A .5 INCH CRACK AT LIGHTENING HOLE IN FORWARD CARGO DOOR INNER SKIN ABOVE INTERIOR HANDLE. THE CRACK WAS STOP DRILLED AND A REPAIR WAS INSTALLED IAW SRM 52-30-01 AND 51-70-13.

Part: FUSE — BLOWN (BATTERY PACK) · airframe 36,912 hrs · 20,638 cycles

INSPECTION FOUND EMERGENCY LIGHTS AT ROWS 22 - 25 AND AT RT AND LT AFT ESCAPE SLIDES INOPERATIVE. MAINTENANCE FOUND BAD FUSES AT CENTER BATTERY PACK AND BAD BULBS AT EXIT DOOR IDENTITY SIGNS. THE FUSE AND BULBS WERE REPLACED AND OPERATION OF THE LIGHTS CHECKED GOOD.

Part: LP TURBINE — FAILED (NR 2 ENGINE) · airframe 36,446 hrs · 20,397 cycles

THE NR 2 ENGINE QUIT RUNNING SHORTLY AFTER TAKEOFF FROM IAH. THE AIRCRAFT WAS RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. INITIAL EXAMINATION OF THE NR 2 ENGINE REVEALED THAT THE LPT HAD FAILED AND THE FAILURE WAS CONTAINED. THE NR 2 ENGINE WAS REMOVED AND REPLACED. *S/D* INVESTIGATION CONCLUDED THAT THE PRIMARY CAUSE OF ENGINE FAILURE WAS DUE TO FAILURE OF HPT FORWARD ROTATING AIR SEAL.

Part: STRINGER — DENTED (BS 827-892)

INSPECTION FOUND STRINGER 5L DENTED AT STA 827 AND BETWEEN STA 842 AND 892. STRINGER REPAIRS WERE INSTALLED IAW SRM 53-00-03, FIGURE 201 AND 203.

Part: SEAL — CRACKED (NR 1 ENGINE)

SHORTLY AFTER TAKEOFF FROM PBI, THE NR 1 ENGINE EXPERIENCED AN UNCONTAINED FAILURE AT APPROXIMATELY 1,000 FEET. THE AIRCRAFT WAS RETURNED TO PBI WHERE IT LANDED SAFELY. INITIAL FINDINGS REVEALED DAMAGE TO THE LT SIDE OF THE FUSELAGE AND VERTICAL STABILIZER. THE AIRCRAFT WAS TAKEN OUT OF SERVICE. THE NR 1 ENGINE WILL BE REMOVED AND REPLACED. INVESTIGATION REVEALED THAT THE PRIMARY CAUSE OF FAILURE WAS DUE TO A CRACKED BOLT HOLE FOR THE HPT ROTATING AIR SEAL. SERVICE BULLETIN 72-9-22 IS BEING ISSUED FOR AN EDDY CURRENT INSPECTION OF THE BOLT HOLE.

Part: STRUT — CRACKED (RT MLG)

RIGHT MAIN LANDING GEAR LEAKING FLUID. FOUND 1 CRACK IN MLG CYLINDER. REPLACED MAIN LANDING GEAR.

Part: PANEL — CORRODED (BS 867)

INSPECTION FOUND TRANSITION PANEL CORRODED FROM AFT CARGO DOOR TO STA 867. A NEW TRANSITION PANEL WAS INSTALLED IAW SRM 51-40-02.

Part: INTERCOSTAL — CRACKED (BS 927-947.5)

INSPECTION FOUND 1 INCH CRACKS IN FLOOR INTERCOSTAL AROUND NUTPLATE HOLES AT BL 0 BETWEEN STA 927 AND 947.5. A NEW INTERCOSTAL WAS FABRICATED AND INSTALLED IAW SRM 53-60-51 AND 51-10-2.

Part: TRANS RAIL — CORRODED (BS 867-727E)

INSPECTION FOUND RIGHT TRANSITION RAIL IN AFT CARGO AREA CORRODED FROM STA 867 TO 727E. THE TRANSITION RAIL WAS REPLACED IAW SRM 53-60-53.

Part: TRANS RAIL — CORRODED (BS 707)

INSPECTION FOUND RIGHT TRANSITION RAIL CORRODED WITH A 1 INCH CRACK FROM STA 707 TO FORWARD OF AFT CARGO DOOR CUTOUT. THE TRANSITION RAIL WAS REPLACED IAW SRM 53-60-53.

Part: CROSS RAIL — CORRODED (BS 767/867)

INSPECTION FOUND AFT CARGO FLOOR CROSS RAIL CORRODED AT STA 767 AND 867. THE PARTS WERE REMOVED AND REPLACED IAW SRM 51-10-02.

Part: ANGLE — CORRODED (BS 312-328)

INSPECTION FOUND CABIN FLOOR SUPPORT T-ANGLES CORRODED BETWEEN STA 312 AND 328, 12 INCHES RIGHT OF CENTERLINE AND BETWEEN STA 312 AND 328, 12 INCHES LEFT OF CENTERLINE. PARTS WERE FABRICATED AND INSTALLED IAW SRM 51-40-02 AND 51-10-02.

Part: FLOOR WEB — CORRODED (BS 638)

INSPECTION FOUND CABIN LEFT SIDE FLOOR WEB CORRODED AT STA 638. THE FLOOR WEB WAS REPAIRED IAW SRM 51-10-2.

Part: FLOORBEAM — CORRODED (BS 986.5)

INSPECTION FOUND FLOORBEAM TEE CORRODED AT STA 986.5. THE ENTIRE LENGTH OF UPPER CHORD WAS REMOVED AND A TEE EXTRUSION REPAIR WAS INSTALLED IAW ECRA 5310-03235.

Part: ANGLE — CORRODED (BS 312-344)

INSPECTION FOUND FLOOR SUPPORT ANGLE UNDER L-1 DOOR SCUFF PLATE CORRODED BETWEEN STA 312 AND 344. THE ANGLE WAS REMOVED AND REPLACED IAW SRM 51-10-02.

Part: ANGLE — CORRODED (BS 299.5)

INSPECTION FOUND FLOOR SUPPORT T-ANGLE CORRODED AT STA 299.5, 18 INCHES RIGHT OF CENTERLINE. THE FLOOR SUPPORT WAS REPLACED IAW ECRA 5310-03399.

Part: ANGLE — CORRODED (BS 328-344)

INSPECTION FOUND FLOOR SUPPORT T-ANGLE CORRODED AROUND NUTPLATE HOLES BETWEEN STA 328 AND 344, 12 INCHES LEFT OF CENTERLINE. A PART WAS FABRICATED AND INSTALLED IAW SRM 51-40-02.

Part: ANGLE — CORRODED (BS 294.5-344)

INSPECTION FOUND FLOOR SUPPORT Z-ANGLE CORRODED UNDER R-1 DOOR SCUFF PLATE BETWEEN STA 294.5 AND 344. THE ANGLE WAS REMOVED AND A NEW Z-ANGLE WAS INSTALLED IAW SRM 51-10-02.

Part: ANGLE — CORRODED (BS 294.5-312)

INSPECTION FOUND FLOOR SUPPORT T-ANGLE CORRODED AT STA 294.5 AND 312, 12 INCHES RIGHT OF CENTERLINE. THE FLOOR SUPPORT WAS REPLACED IAW ECRA 5310-03399.

Part: FLOORBEAM — CORRODED (BS 312-344)

INSPECTION FOUND MAIN CABIN FLOORBEAM CORRODED AT STA 312, 328 AND 344. THE SECTIONS WERE REPAIRED IAW SRM 53-10-51.

Part: FLOORBEAM — CORRODED (BS 294.5)

INSPECTION FOUND FLOORBEAM CORRODED AROUND NUTPLATE HOLES AT STA 294.5. THE FLOORBEAM TOP T-SECTION WAS REMOVED AND REPLACED IAW SRM 53-10-51.

Part: SUPPORT — CORRODED (BS 787-807)

INSPECTION FOUND CENTER FLOOR RIGHT SUPPORT RAIL CORRODED AT STA 787 TO 807. THE RAIL WAS REPLACED IAW SRM 53-60-53.

Part: SKIN — CRACKED (NR 2 LE SLAT)

INSPECTION FOUND A 7 INCH CRACK IN NR 2 SLAT LOWER SKIN NEAR ACTUATOR. THE SLAT SKIN WAS REPAIRED IAW ECRA 5750-01159.

Part: SKIN — CRACKED (LE FLAP)

INSPECTION FOUND A 8.5 INCH CRACK IN LOWER SLAT SKIN NEAR ACTUATOR. THE AREA WAS REPAIRED IAW ECRA 5750-01159.

Part: PWR CONTL UNIT — INOPERATIVE (RUDDER)

THE AIRCRAFT EXPERIENCED AN UNCOMMANDED ROLL AFTER TAKEOFF. RIGHT RUDDER INPUT WAS USED TO COUNTER ACT THE MOVEMENT. THE YAW DAMPER SWITCH WAS CONFIRMED ON. THE FLIGHT WAS CONTINUED TO BOS WHERE IT LANDED WITHOUT FURTHER EVENT. MAINTENANCE REMOVED AND REPLACED THE YAW DAMP COUPLER. THE MAIN RUDDER PCU WAS REPLACED AS A PRECAUTIONARY MEASURE. AN ECRA FOR UNCOMMANDED ROLL INSPECTION WAS ISSUED AND COMPLIED WITH AND NO DEFECTS WERE FOUND. IN ADDITION, THE RUDDER TRIM SWITCH WAS REPLACED PER ECRA 2726-01001 AND THE NR 3 SPOILER ACTUATOR WAS REPLACED DUE TO LEAKAGE. THE SDR WILL REMAIN OPEN FOR PART INFORMATION PENDING INVESTIGATION. *S/D* VENDOR TEARDOWN FOUND NO FAULTS WITH THE YAW DAMP COUPLER. TEARDOW

Part: CIRCUIT BREAKER — POPPED (AIR/GROUND SENSE)

EWR - FLT 0220 - THE GEAR INDICATOR WOULD NOT GO GREEN WHEN GEAR WAS EXTENDED ON APPROACH TO EWR. THE GEAR WAS VISUALLY CONFIRMED DOWN. IN ADDITION, THE STALL WARNING ACTIVATED AND THE GEAR WARNING HORN SOUNDED WITH FLAPS AT 15 ON FINAL. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE AIR/GROUND SENSE CIRCUIT BREAKER POPPED. THE CIRCUIT BREAKER WAS RESET. A BITE TEST OF THE LANDING GEAR LOGIC SHELF WAS PERFORMED IAW MM 32-09-10. THE LANDING GEAR WAS PINNED AND THE GEAR HANDLE WAS CYCLED SEVERAL TIMES. NO DEFECTS WERE NOTED. (X)