N516AU

Part: ENGINE — FAILED (NR 1) · airframe 68,391 hrs · 44,353 cycles

NR 1 ENGINE SURGED PLUS TO MINUS 3 PERCENT N1 DURING CLIMB TO ALTITUDE. EGT, N2, FF SURGED AS WELL. AUTOTHROTTLES WERE IN USE. THRUST LEVER DID NOT FOLLOW ENGINE SURGE ALSO NR 1 THRUST LEVER 1 KNOB WIDTH PAST NR 2 DURING CLIMB. OK IN CRUISE AND DESCENT. REMOVED AND REPLACED THE #1 ENGINE ASSEMBLY PER J/C 03L50671001.

Part: SKIN PANEL — CRACKED (NR 2 PYLON) · airframe 67,871 hrs · 43,899 cycles

C5 CHECK - CRACK ON NR 2 ENGINE PYLON UPPER FORWARD SKIN PANEL 5827R AT NAC STA196.840. REPAIRED NR 2 ENGINE PYLON UPPER FORWARD SKIN PANEL 5827R AT NAC STA196.840 IAW TYPICAL REPAIR TR 737-5430-10-0054.

Part: FLAP — DELAMINATED (LT WING) · airframe 67,676 hrs · 43,724 cycles

C5 CHECK - DELAMINATION ON LEFT OUTBOARD FOREFLAP AT INBOARD AFT CORNER. REPLACED LEFT OUTBOARD FOREFLAP IAW B737 AMM 27-51-37.

Part: KEELBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 67,871 hrs · 43,899 cycles

C5 CHECK - LEVEL 2 EXFOLIATION CORROSION ON KEEL BEAM AT BS 727+12 INCHES, S27R. REPAIRED KEEL BEAM AT BS 727+12 INCHES, S27R IAW EA 103352.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 67,869 hrs · 43,898 cycles

SKIN PANEL VISIT - FOUND 1 ELONGATED FUSELAGE SKIN FASTENER HOLE AT BS 727B S25R. REPAIRED FUSELAGE SKIN FASTENER HOLE AT BS 727B S25R IAW EA 200762.

Part: CHARGER — INOPERATIVE (CABIN) · airframe 67,869 hrs · 43,898 cycles

MAINTENANCE REPORTED THE RIGHT OVERWING EXIT SIGN, LEFT CEILING EXIT SIGN AND BULLNOSE EMERGENCY LIGHTS AT ROW 5L AND 9L WERE INOPERATIVE. MAINTENANCE TROUBLESHOT AND FOUND CHARGER ASSEMBLY BAD. REMOVED AND REPLACED CHARGER ASSEMBLY PER AMM 33-51-51, TASK 962-016. OPERATIONAL CHECK GOOD.

Part: SKIN — CRACKED (FUSELAGE) · airframe 67,869 hrs · 43,898 cycles

SKIN PANEL - CRACK IN FUSELAGE SKIN 1.8 INCHES FORWARD OF FR727D, S23R. REPLACED FUSELAGE SKIN AT BS 727D, S23R IAW US AIRWAYS EA 103291.

Part: SKIN — CRACKED (FUSELAGE) · airframe 67,869 hrs · 43,898 cycles

SKIN PANEL - .25 INCH CRACK INDICATION BOTTOM RIVET ROW SECOND LAYER SKIN LAP JOINT AT BS 817, S4R. REPAIRED FUSELAGE SKIN AT BS 817, S4R IAW B737 SRM 53-00-01, REPAIR 31.

Part: SKIN — CRACKED (FUSELAGE) · airframe 67,869 hrs · 43,898 cycles

SKIN PANEL - CRACK IN FUSELAGE SKIN 10 INCHES AFT OF BS 727C, S4L. REPAIRED FUSELAGE SKIN AT BS 727 + 10", S4L IAW B737 SRM 53-00-01.

Part: SKIN — CRACKED (FUSELAGE) · airframe 67,869 hrs · 43,898 cycles

SKIN PANEL - CRACK IN FUSELAGE SKIN 8 INCHES AFT OF BS 727C, S4R. REPAIRED IAW B737 SRM 53-00-01 REPAIR 31.

Part: FRAME — CRACKED (BS 616 S17R) · airframe 67,869 hrs · 43,898 cycles

CRACK IN FUSELAGE FRAME AT BS 616, S17R. REPAIRED FRAME IAW TR737-5362-10-0023.

Part: FRAME — CRACKED (BS 616 S17L) · airframe 67,869 hrs · 43,898 cycles

CRACK IN FUSELAGE FRAME AT BS 616, S17L. REPAIRED FRAME IAW TR737-5362-10-0023.

Part: LIGHT — UNSECURE (CABIN)

CLT - CREW REPORTED THE FLOOR EMERGENCY LIGHT AT SEAT ROW SIX IS NOT SECURED. MAINTENANCE RESECURED EMERGENCY LIGHT AT SEAT ROW SIX. OPS CHECK GOOD.

Part: SKIN PANEL — CRACKED (FUSELAGE) · airframe 67,035 hrs · 43,172 cycles

CLT - RON - 3 CRACKS IN FUSELAGE SKIN BETWEEN BS 500A TO 500C, S10R. REPAIRED FUSELAGE SKIN BETWEEN BS 500A TO 500C, S10R IAW EA 102894 & B737 SRM 53-00-01 REPAIR 31.

Part: LIGHT — INOPERATIVE (CABIN)

CLT - MAINTENANCE REPORTED THE FLOOR EMERGENCY LIGHT BROKEN/INOPERATIVE AT SEAT 7C. MAINTENANCE REMOVED AND REPLACED THE LIGHT ASSEMBLY AT SEAT 7C PER MM 33-50-01. OPERATIONAL CHECK GOOD.

Part: WIRE — ARCED (SLIDING WINDOW)

CLT - FLIGHT CREW REPORTED THE WIRE RUNNING TO THE CAPTAIN'S L2 SLIDING WINDOW ARCED AT CLAMP. MAINTENANCE REPAIRED WIRING AT L2 SLIDING WINDOW PER SWPM 20-10-13. WINDOW HEAT CHECKS NORMAL.

Part: SKIN — CRACKED (FUSELAGE) · airframe 66,317 hrs · 42,644 cycles

CLT - MAJOR REPAIR - RON - 1.7 INCH LONG CRACK ON FUSELAGE SKIN AT STA 747, STR 19R. REPAIRED FUSELAGE SKIN AT STA 747, STR 19R IAW B737 SRM 53-00-01, REPAIR 31.

Part: SKIN — CRACKED (FUSELAGE) · airframe 66,317 hrs · 42,644 cycles

CLT - MAJOR REPAIR - RON - 1 INCH CRACK ON FUSELAGE SKIN AT STA 727D+18 INCHES, STR 23R. REPAIRED FUSELAGE SKIN AT STA 727D+18 INCHES, STR 23R IAW ENGINEERING AUTHORIZATION 102368 AND B737 SRM 51-00-01, REPAIR 31.

Part: FITTING — CRACKED (FUSELAGE) · airframe 66,138 hrs · 42,490 cycles

PIT - GEAR CHANGE - MAJOR REPAIR - JOB CARD 03T10553005 - CRACK IN CLIP BETWEEN BS 294 TO BS 303, S10L. REPLACED CLIP BETWEEN BS 294 TO BS 303, S10L IAW B737 SRM 53-10-04 & BOEING DRAWING 50-7946.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 65,791 hrs · 42,189 cycles

PIT - FORWARD CARGO EA - MAJOR REPAIR - FORWARD CARGO DOOR CUTOUT, FORWARD FRAME CRACKED AT LOWER DOOR STOP AT S24R. REPAIRED FORWARD CARGO DOOR CUTOUT, FORWARD FRAME AT LOWER DOOR STOP AT S24R IAW EA 115799 & B737 SRM 53-30-07.

Part: LIGHT — DETACHED (CABIN) · airframe 64,206 hrs · 41,005 cycles

FLT 1176 - IAH TO CLT - EEL - FLOOR LEVEL EMERGENCY LIGHTING AT 8C BROKEN. RE-ATTACHED FLOOR LEVEL LIGHTING EMERGENCY TO SEAT 8C.

Part: LIGHT — DAMAGED (CABIN) · airframe 64,163 hrs · 41,024 cycles

FLT 1495 - BDL TO CLT - EEL - SEAT 8C EMERGENCY LIGHTING LIGHT WAS KNOCKED OFF AND WIRE BROKE. REPLACED LIGHT AND OPS CHECK GOOD.

Part: SKIN — CRACKED (FUSELAGE) · airframe 63,880 hrs · 40,825 cycles

CLT - C3 - MAJOR REPAIR - CRACK IN RADIUS OF FUSELAGE SKIN CUTOUT OF R-2 DOOR UPPER HINGE BS 947.5, BELOW S11R. REPAIRED FUSELAGE SKIN CUTOUT OF R-2 DOOR UPPER HINGE IAW B737 SRM 53-60-01 REPAIR 5.

Part: RETAINER — MISSING (FWD ENTRY DOOR)

CLT - MAINTENANCE REPORTED THE FORWARD ENTRY DOOR WAS HARD TO OPEN. MAINTENANCE FOUND THE GUIDE ARM LINK RADIUS PIN RETAINER OFF. REPLACED ENTIRE PIN, WASHER AND RING. DOOR OPERATION CHECKS GOOD. REF: MM 52-11-00-434, FIGURE 401.

Part: CARRIAGE — CORRODED (TE FLAP) · airframe 63,571 hrs · 40,616 cycles

PHL - RON - MAJOR REPAIR - CORROSION FOUND ON FORWARD END OF LEFT WING OUTBOARD FLAP SPINDLE ON FRONT OF TIE AT WBL 355 AND BROKEN BOLT HEAD ON TOP OF SAME CARRIAGE ASSEMBLY INBOARD SIDE. REPLACED LEFT OUTBOARD FLAP CARRIAGE IAW B737 AMM 27-51-34-825-001.

Part: SKIN — CRACKED (FUSELAGE) · airframe 63,463 hrs · 40,540 cycles

CLT - RON - MAJOR REPAIR - CRACK ON FUSELAGE SKIN ALONG LAP JOINT AT BS 520, S10R. REPAIRED FUSELAGE SKIN ALONG LAP JOINT AT BS 520, S10R IAW US AIRWAYS EA 101256.

Part: OUTFLOW VALVE — FAULTY (CABIN PRESSURE)

DURING CRUISE AT FL360, EN ROUTE FROM CLT TO DFW, THE CABIN ALTITUDE INDICATED A SLOW CLIMB (200 FPM) UP TO 10,000 FEET. THE CABIN ALTITUDE WARNING HORN SOUNDED. CREW DESCENDED AIRCRAFT TO FL300 WITH PACKS IN HIGH. CABIN DESCENDED TO 8,000 FEET AND STABILIZED. FLIGHT LANDED AT DFW WITHOUT FURTHER INCIDENT. MAINTENANCE REMOVED AND REPLACED THE FORWARD OUTFLOW VALVE PER MM 21-43-11-004-001. PERFORMED OPERATIONAL TEST PER MM 21-43-11-705-001. TEST OK. PERFORMED PRESSURE LEAK TEST PER MM 05-51-91-702-01. TEST OK.

Part: WIRE — DISCONNECTED (SMOKE DETECTOR)

EWR - PILOT REPORTED THE FORWARD LAVATORY SMOKE DETECTOR WAS NOT WORKING. MAINTENANCE RECONNECTED WIRES TO BATTERY TERMINAL. OPERATIONAL CHECK GOOD PER MM 26-14-00-5.

Part: SKIN — CRACKED (FUSELAGE) · airframe 62,728 hrs · 40,076 cycles

CLT - RON - MAJOR REPAIR - CRACK IN AFT FUSELAGE SKIN BETWEEN BS 727D TO BS 727E, S20R. REPAIRED AFT FUSELAGE SKIN BETWEEN BS 727D TO BS 727E, S20R IAW B737 SRM 53-00-01 REPAIR 31.

Part: BATTERY PACK — DISCHARGED (CABIN)

MX REPORTED THE EMERGENCY LIGHT OVER THE AFT RT SERVICE DOOR WAS INOPERATIVE. MX REMOVED AND REPLACED THE BATTERY PACK. OPS CHECK GOOD. (K)

Part: SKIN — CRACKED (ZONE 100) · airframe 62,250 hrs · 39,755 cycles

PIT - PILOT WALK AROUND - MAJOR REPAIR- CRACK IN FUSELAGE SKIN AT BS 727D - BS 727E, S24L. REPAIRED FUSELAGE SKIN AT BS 727D - BS 727E, S24L IAW SRM 53-00-01 REPAIR 31.

Part: PIN — CORRODED (RT MLG TRUNNION) · airframe 61,425 hrs · 39,174 cycles

RT MLG TRUNNION PIN THREADS AND NUT BADLY CORRODED. REPLACED RT MLG TRUNNION PIN IAW MM 32-11-11. (K)

Part: SKIN — CRACKED (ELEVATOR) · airframe 61,425 hrs · 39,174 cycles

CLT Q6 MAJOR REPAIR NR 03C71227004/001 AND NR 5030650. CRACK ON LOWER SURFACE OF RT ELEVATOR AT ELEVATOR STATION 24.90. REPLACED RT ELEVATOR IAW US AIRWAYS JOB CARD NR 03C71227004 AND 03C71127003.

Part: FRAME — CRACKED (ZONE 100) · airframe 61,425 hrs · 39,174 cycles

FRAME CRACKED AT BS 500B BETWEEN S20R AND S21R. REPAIRED FRAME AT BS 500B BETWEEN S20R AND S21R IAW EA NR 100623. (K)

Part: SLIDE — LOW PRESSURE (PAX DOOR) · airframe 61,425 hrs · 39,174 cycles

CTO Q6 EES LOG NR 4390815 FORWARD MAIN ENTRY DOOR SLIDE HAS LOW PRESSURE. REPLACED FORWARD MAIN ENTRY DOOR SLIDE IAW JOB CARD 03C10552008.

Part: SKIN PANEL — CRACKED (FUSELAGE) · airframe 61,425 hrs · 39,174 cycles

CLT Q6 MAJOR REPAIR NR 03-0553-8-0364/008 AND NR 5030674. CRACK IN FUSELAGE SKIN AT BS520, WL 198.5. REPAIRED FUSELAGE SKIN AT BS520, WL198.5 IAW US AIRWAYS EA NR 100609.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 61,425 hrs · 39,174 cycles

CLT Q6 MAJOR REPAIR NR 03C21952009/013 2 CRACKS ON FORWARD CARGO DOOR INNER SKIN. REPAIRED FORWARD CARGO DOOR INNER SKIN IAW US AIRWAYS EA NR 100614.

Part: BULKHEAD — CRACKED (BS 178) · airframe 61,425 hrs · 39,174 cycles

CRACK IN BS 178 BULKHEAD WEB AT RBL 17, WL 234. REPAIRED BS 178 BULKHEAD WEB AT RBL 17, WL 234, IAW SRM 51-10-08 & SRM 51-70-13.

Part: SKIN — DELAMINATED (L/E SLAT) · airframe 61,425 hrs · 39,174 cycles

CLT Q6 MAJOR REPAIR NR 03C40257009/001 AREA OF DELAMINATION ON RT WING NR 6 SLAT TRAILING EDGE WEDGE LOWER SURFACE. REPLACED RT WING NR 6 SLAT IAW US AIRWAYS TASK CARD 03C40227004.

Part: TAB — DELAMINATED (AILERON) · airframe 61,425 hrs · 39,174 cycles

CLT - Q6 - MAJOR REPAIR - NR 03C30627004/001 - LEFT AILERON TAB OUTBOARD AFT CORNER DELAMINATED. REPAIRED LEFT AILERON TAB OUTBOARD AFT CORNER IAW B737 SRM 57-60-01 AND 51-70-16.

Part: TAB — CRACKED (RT ELEVATOR) · airframe 61,425 hrs · 39,174 cycles

CLT - Q6 - MAJOR REPAIR - NR 03C71227005/002 & JOB CARD 03C71227004 - SKIN CRACKED AND DISBONDED ON RT ELEVATOR TAB FORWARD INBOARD LOWER SURFACE AT ELEVATOR STA. 124.047. REPLACED RT ELEVATOR TAB IAW JOB CARD 03C71227004.

Part: SKIN — DELAMINATED (NR 2 SPOILER) · airframe 61,425 hrs · 39,174 cycles

CLT - Q6 - MAJOR REPAIR - NR 03C10753005/004 - NR 2 SPOILER DELAMINATED ON SKIN UPPER SURFACE. REPLACED NR 2 SPOILER IAW B737 AMM 27-61-11.

Part: SKIN — DELAMINATED (ZONE 600) · airframe 61,425 hrs · 39,174 cycles

CLT - Q6 - MAJOR REPAIR - NR 03C40257009/003 - DELAMINATION ON NR 5 SLAT LOWER SURFACE OUT BOARD TRAILING EDGE. REPLACED NR 5 SLAT.

Part: FRAME — CRACKED (ZONE 100) · airframe 61,425 hrs · 39,174 cycles

CLT-Q6 - MAJOR REPAIR - CRACK IN AFT FUSELAGE FRAME AT FORWARD CARGO DOOR CUTOUT AT LOWER DOOR STOP BS 492.4, S24R. REPLACED FUSELAGE FRAME AT FORWARD CARGO DOOR CUTOUT AT LOWER DOOR STOP BS 492.4, S24R IAW B737 SRM 51-40-02. (S)

Part: STRAP — CRACKED (ZONE 200) · airframe 61,425 hrs · 39,174 cycles

CLT - Q6 - MAJOR REPAIR - NR # 03C10753005/012 - FLOOR STRAP CRACKED BETWEEN BS328 TO BS344, LBL45. REPLACED FLOOR STRAP BETWEEN BS328 TO BS344, LBL45 IAW B737 SRM 51-20-01.

Part: SUPPORT — CRACKED (ZONE 200) · airframe 61,425 hrs · 39,174 cycles

CLT - Q6 - MAJOR REPAIR - NR 03C10753005/005 - STABILIZER SUPPORT CRACKED BETWEEN BS312 & 328, BLO. REPLACED STABILIZER SUPPORT BETWEEN BS312 & 328, BLO IAW B737 SRM 53-10-51.

Part: SUPPORT ANGLE — CRACKED (ZONE 200) · airframe 61,425 hrs · 39,174 cycles

CLT - Q6 - MAJOR REPAIR - NR 03C10753005/008 - SUPPORT ANGLE CRACKED AT BS 312 TO BS 328, RBL32. REPLACED SUPPORT ANGLE AT BS 312 TO BS 328, RBL32 IAW B737 SRM 51-10-02.

Part: STRAP — CRACKED (ZONE 200) · airframe 61,425 hrs · 39,174 cycles

CLT-Q6- MAJOR REPAIR - CRACK ON WEB SUPPORT STRAP AT BS 639, S16R. REPAIRED WEB SUPPORT STRAP AT BS 639, S16R IAW B737 SRM 51-40-02 AND BOEING DRAWING 65-46920. (S)

Part: STIFFENER — CRACKED (ZONE 200) · airframe 61,425 hrs · 39,174 cycles

CLT - Q6 - MAJOR REPAIR - NR 03C10753005/025 - FLOOR BEAM WEB VERTICAL STIFFENER CRACKED AT BS328, BLO. REPLACED FLOORBEAM WEB VERTICAL STIFFENER AT BS 328, BL 0 IAW B737 SRM 51-10-02.

Part: STIFFENER — CRACKED (FLOORBEAM) · airframe 61,425 hrs · 39,174 cycles

CLT-Q6 -MAJOR REPAIR- CRACK ON FLOORBEAM WEB VERTICAL STIFFENER AT BS 328, BL 0. REPLACED FLOORBEAM WEB VERTICAL STIFFENER AT BS 328, BL 0 IAW B737 SRM 51-10-02. (S)

Part: SKIN — CRACKED (ZONE 300) · airframe 61,425 hrs · 39,174 cycles

CLT-Q6 -MAJOR REPAIR - CRACK ON LT HORIZONTAL STABILIZER LOWER SKIN AT STAB STA 138.7 AND 147.9. REPAIRED LT HORIZONTAL STABILIZER LOWER SKIN AT STAB STA 138.7 AND 147.9 IAW US AIRWAYS EA 100592. (S)

Part: SKIN — CRACKED (ZONE 100) · airframe 61,425 hrs · 39,174 cycles

CLT-Q6 -MAJOR REPAIR - CRACK IN FUSELAGE SKIN AT BS 727D, S23R. REPAIRED FUSELAGE SKIN AT BS 727D, S23R IAW US AIRWAYS EA 100595. (S)

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 61,425 hrs · 39,174 cycles

CLT -Q6- MAJOR REPAIR - LEVEL 2 EXFOLIATION CORROSION ON SEAT TRACK AT BS 328 TO BS 344, RBL 24. REPAIRED SEAT TRACK AT BS 328 TO BS 344, RBL 24 IAW B737 SRM 53-00-52. (S)

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 61,425 hrs · 39,174 cycles

CLT Q6 MAJOR REPAIR NR 03C10853057/006 LEVEL 2 CORROSION ON FLOOR BEAM T CAP AT BS986, BLO. REPAIRED T CAP UPPER FLANGE IAW B737 TYPICAL REPAIR NR 53-60-01 REV A.

Part: INTERCOSTAL — CORRODED (ZONE 100) · corrosion level 2 · airframe 61,425 hrs · 39,174 cycles

CLT Q6 MAJOR REPAIR NR 03C10753005/011 LEVEL 2 CORROSION ON INTERCOSTAL AT BS 332, RBL 11. REPLACED INTERCOSTAL AT BS332, RBL 11 IAW B737 SRM, 51-10-2.

Part: INTERCOSTAL — CORRODED (ZONE 200) · corrosion level 2 · airframe 61,425 hrs · 39,174 cycles

CLT-Q6 -MAJOR REPAIR- LEVEL 2 GALVANIC CORROSION ON INTERCOSTAL AT BS 314, WL 208, RBL 10. REPLACED INTERCOSTAL AT BS 314, WL 208, RBL 10 IAW BOEING DRAWING 6545834 AND B737 SRM 53-00-04. (S)

Part: INTERCOSTAL — CORRODED (BS 314) · corrosion level 2 · airframe 61,425 hrs · 39,174 cycles

CLT -Q6- MAJOR REPAIR - LEVEL 2 GALVANIC CORROSION ON INTERCOSTAL AT BS 314, WL 208, RBL 10. REPLACED INTERCOSTAL AT BS 314, WL 208, RBL 10 IAW BOEING DRAWING 65-45834. (S)

Part: FLOORBEAM — CORRODED (ZONE 200) · corrosion level 2 · airframe 61,425 hrs · 39,174 cycles

CLT-Q6 -MAJOR REPAIR- LEVEL 2 INTERGRANULAR CORROSION ON FLOORBEAM AT BS 328, BL 0 TO RBL 44. REPAIRED FLOORBEAM AT BS 328, BL 0 TO RBL 44. REPAIRED IAW B737 SRM 53-10-51. (S)

Part: INTERCOSTAL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 61,425 hrs · 39,174 cycles

CLT Q6 MAJOR REPAIR NR 03C10753005/017 LEVEL 2 CORROSION ON INTERCOSTAL AT BS330, RBL10. REPLACED INTERCOSTAL AT BS330. RBL10 IAW B737 SRM 51-10-2.

Part: PAN — CORRODED (ZONE 100) · corrosion level 2 · airframe 61,425 hrs · 39,174 cycles

CLT-Q6 -MAJOR REPAIR- LEVEL 2 EXFOLIATION CORROSION ON RT LAV PAN AT BS 1016, RBL 25 TO RBL 26. REPAIRED RT LAV PAN AT BS 1016, RBL 25 TO RBL 26 IAW B737 SRM 51-70-13. (S)

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 61,425 hrs · 39,174 cycles

CLT Q6 MAJOR REPAIR NR 03C10853057/002 LEVEL 2 EXFOLIATION CORROSION ON STUB STRINGER AT BS 1008, S27R. REPLACED STUB STRINGER AT BS 1008, S27R IAW B737 SRM 51-10-02 & SRM 51-40.

Part: FRAME — CRACKED (ZONE 200) · airframe 61,425 hrs · 39,174 cycles

CLT-Q6 - MAJOR REPAIR - CRACK ON FRAME AT BS 360 BETWEEN S8L & S9L. REPAIRED FRAME AT BS 360 BETWEEN S8L & S9L IAW US AIRWAYS TYPICAL REPAIR 53-10-20E. (S)

Part: FRAME — CRACKED (FUSELAGE) · airframe 61,425 hrs · 39,174 cycles

CLT-Q6 -MAJOR REPAIR- FRAME CRACKED AT BS 887 BETWEEN S8L AND S9L. REPAIRED FRAME AT BS 887 BETWEEN S8L AND S9L IAW US AIRWAYS TYPICAL REPAIR 53-10-20E. (S)

Part: FRAME — CRACKED (ZONE 200) · airframe 61,425 hrs · 39,174 cycles

CLT-Q6 - MAJOR REPAIR - CRACK ON FRAME AT BS 847 BETWEEN S8L & S9L. REPAIRED FRAME AT BS 847 BETWEEN S8L & S9L IAW US AIRWAYS TYPICAL REPAIR 53-10-20E. (S)

Part: TAB — DEBONDED (LT AILERON) · airframe 61,425 hrs · 39,174 cycles

CLT-Q6- MAJOR REPAIR - LT AILERON TAB OUTBOARD CORNER DELAMINATED. REPAIRED LT AILERON TAB OUTBOARD CORNER IAW B737 SRM57-60-01. (S)

Part: SKIN — CRACKED (FUSELAGE) · airframe 60,218 hrs · 38,277 cycles

CLT - MAJOR REPAIR - DAILY CHECK - CRACKED FUSELAGE SKIN, BS 762, S 19R. REPAIRED FUSELAGE SKIN, BS 762, S19R IAW B737 SRM 53-00-01 REPAIR 31.

Part: WEB — CRACKED (CARGO DOOR) · airframe 60,198 hrs · 38,260 cycles

CLT - MAJOR REPAIR - RON - AFT CARGO DOOR HAS CRACKED WEB INSIDE THE DOOR UNDER THE LINER. REPAIRED THE AFT CARGO DOOR WEB IAW USAIRWAYS EA 110557.

Part: CHARGER — INOPERATIVE (CABIN)

BDL - MAINTENANCE REPORTED THE EMERGENCY LIGHTS AT THE LEFT AFT OVER DOOR SIGN AND THE RIGHT AFT ESCAPE SLIDE INOPERATIVE. MAINTENANCE REMOVED AND REPLACED THE M1137 CHARGER ASSEMBLY. OPERATIONAL CHECK GOOD.

Part: STRINGER CLIP — CRACKED (ZONE 200) · airframe 59,443 hrs · 37,662 cycles

CLT - MAJOR REPAIR - FPBH INSPECTION, CRACKED CLIP ANGLE, BS 360, S16L. REPLACED CLIP ANGLE, BS 360 S16L IAW BOEING DRAWING 65-17685.

Part: FITTING — CRACKED (FUSELAGE) · airframe 59,435 hrs · 37,656 cycles

CLT - MAJOR REPAIR - FPBH INSPECTION, CRACKED CLIP BS 360, S15L. REPLACED CLIP, BS 360, S15L IAW BOEING DRAWING 65-17685.

Part: STRINGER CLIP — CRACKED (ZONE 200) · airframe 59,443 hrs · 37,662 cycles

CLT - MAJOR REPAIR - FPBH INSPECTION, CRACKED TIE CLIP ANGLE, BS 360, S16L. REPLACED TIE CLIP ANGLE, BS 360 S16L IAW BOEING DRAWING 65-17685.

Part: ANGLE — CRACKED (ZONE 100) · airframe 59,435 hrs · 37,656 cycles

CLT - MAJOR REPAIR - FPBH INSPECTION, CRACKED ANGLE, BS 360, S14L - S15L. REPLACED ANGLE, BS 360, S14L - S15L IAW B737 SRM 51-10-02.

Part: INTERCOSTAL — CRACKED (ZONE 200) · airframe 59,435 hrs · 37,656 cycles

CLT - MAJOR REPAIR - FPBH INSPECTION - INTERCOSTAL WEB ANGLE .25 CRACKED AT BS 294, S16L. REPLACED INTERCOSTAL WEB ANGLE BS 294, S16L IAW SRM 51-10-02.

Part: TIE CLIP — CRACKED (FUSELAGE) · airframe 59,435 hrs · 37,656 cycles

CLT - MAJOR REPAIR - FPBH INSPECTION, CRACKED TIE CLIP, BS 294.5, S11L. REPLACED TIE CLIP, BS 294.5, S11L IAW B737-300 SRM 51-10-02.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 59,435 hrs · 37,656 cycles

CLT - MAJOR REPAIR - FPBH INSPECTION, CRACKED BULKHEAD WEB, BS 178, LBL 5, WL 184. REPAIRED BULKHEAD WEB, BS 178, LBL 5, WL 184 IAW USAIRWAYS EA 98903.

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 59,435 hrs · 37,656 cycles

CLT - MAJOR REPAIR - FPBH INSPECTION, CRACKED STRINGER ATTACH ANGLE, BS 300, S13L. REPLACED STRINGER ATTACH ANGLE BS 300, S13L IAW B737-300 SRM 51-10-02.

Part: BATTERY PACK — DISCHARGED (EMERGENCY LIGHT)

PIT - MAINTENANCE REPORTED THE UPPER EMERGENCY LIGHTS AT ROWS 12 THRU 20 INOPERATIVE. MAINTENANCE REMOVED AND REPLACED THE BATTERY PACK FOR AFFECTED LIGHTS. OPERATIONAL CHECK GOOD.

Part: SWITCH — FAILED (EMERGENCY LIGHTS)

ORF - PILOT REPORTED THE EMERGENCY EXIT LIGHTS NOT ARMED LIGHT WILL NOT PRESS-TO-TEST. MAINTENANCE REMOVED AND REPLACED THE EMERGENCY EXIT LIGHT SWITCH ASSEMBLY. OPERATIONAL CHECK GOOD.

Part: BATTERY PACK — DISCHARGED (EMERGENCY LIGHT)

PIT - THE EMERGENCY LIGHTS WERE OUT IN THE FIRST CLASS SECTION AND FORWARD GALLEY. MAINTENANCE REPLACED THE BATTERY CELL ASSEMBLY IN THE FORWARD GALLEY. OPERATIONALLY CHECKS OK.

Part: REFLECTOR — CORRODED (EMERGENCY LIGHT)

FORWARD ENTRY DOOR EXTERIOR EMERGENCY EVACUATION LIGHT INOPERATIVE. R & R REFLECTOR ASSEMBLY DUE TO CORROSION. ALSO, R & R LAMP. OPS CHECK GOOD.

Part: BATTERY PACK — DISCHARGED (EMERGENCY LIGHT)

PIT - MAINTENANCE REPORTED THE EMERGENCY EXIT LIGHTS AT THE LEFT OVERWING EXIT INOPERATIVE. MAINTENANCE REMOVED AND REPLACED THE BATTERY PACK. OPERATIONAL CHECK GOOD.

Part: SKIN — CRACKED (FUSELAGE)

CLT - FOUND EXT FUSELAGE SKIN CRACKED .5 INCH, FORWARD SERVICE DOOR LOWER HINGE CUTOUT. INSTALLED DOUBLER IAW TR 52-10-13. (M)

Part: PMC — FAULTY (NR 2 ENGINE)

IAD - FLT1187 - ON CLIMB-OUT FROM IAD, EN ROUTE TO CLT, THE NR 2 ENGINE SURGED AS N1 ROLLED BACK 10 PERCENT AND BEGAN TO FLUCTUATE 4-5 PERCENT THEREAFTER. AIRCRAFT BEGAN TO YAW AND ROLL. AT 11,000 FEET, CREW DISENGAGED AUTOPILOT BUT PROBLEM CONTINUED. FLIGHT RETURNED TO FIELD AT IAD AND LANDED WITHOUT FURTHER INCIDENT. NO EMERGENCY WAS DECLARED. MAINTENANCE INSPECTED ENGINE INLET AND EXHAUST AREA. NO FAULTS FOUND. GROUND RUN OF NR 1 AND NR 2 ENGINE CHECKS NORMAL. RELEASED AIRCRAFT ON MEL 73-7. BOTH PMC'S ARE OFF. MAINTENANCE ACCOMPLISHED TROUBLESHOOTING AND REPLACED THE NR 2 PMC PER MM 73-21-04. OPERATIONAL CHECK GOOD. REMOVED AND CLEARED MEL 73-7.

Part: TIE CLIP — CRACKED (FUSELAGE)

PIT - Q5 - STRINGER TIE CLIP, .7500 INCH CRACK, BS 500B, STR 13,LT. FABRICATED IAW MFG DWG 69-45156 AND INSTALLED IAW SRM 51-40-02.

Part: SUPPORT ANGLE — CRACKED (FUSELAGE)

PIT - Q5 - SUPPORT ANGLE, .1250 INCH CRACK, STA 260 C/L. REPAIRED WITH NEW PART IAW MFG DWG 65-45833. REPAIRED WITH NEW PART IAW MFG DWG 65-45833.

Part: SKIN — CHAFED (RUDDER)

PIT - Q5 - SKIN SURFACE, 1.5 INCH LONG, TAPERING DEPTH, DEEP CHAFE WEAR, RUDDER LOWER RT L/E CORNER. INSTALLED REPAIR PLYS IAW SRM AND EA.

Part: SKIN — DAMAGED (RUDDER)

PIT - Q5 - SKIN SURFACE, SEVERAL AREAS OF 2 INCH SQUARE, SINGLE LAYER COMPOSITE DAMAGE, RUDDER LT SIDE BETWEEN STA 96 AND 121. INSTALLED REPAIR PLYS IAW SRM AND EA.

Part: SPOILER — DELAMINATED (WING)

PIT - Q5 - SPOILER, 4 BY 6 INCH AREA, DELAMINATION. REMOVED AND REPLACED SPOILER IAW MM 27-62-91.

Part: SKIN — CHAFED (RUDDER)

PIT - Q5 - SKIN SURFACE, 1 INCH CHAFE WEAR, RUDDER RT SIDE L/E AT STA 170. INSTALLED REPAIR PLYS IAW SRM AND EA.

Part: SKIN — DAMAGED (RUDDER)

PIT - Q5 - SKIN SURFACE, 3 INCH LONG, SINGLE LAYER COMPOSITE DAMAGE, RUDDER LT SIDE AT STA 178 AND 13 INCHES FROM FWD SPAR. INSTALLED REPAIR PLYS IAW SRM AND EA.

Part: FRAME — SEPARATED (RUDDER)

PIT - Q5 - CONDUCTIVITY FRAME, 15 INCHES X 12 INCHES, SEPARATION, RUDDER TOP LT SURFACE, UPPER LT CONDUCTIVITY FRAME SEPARATING FROM RUDDER. INSTALLED NEW CONDUCTIVITY FRAME IAW MM AND BAC 5010 AND DWG 65C25841.

Part: SKIN — GOUGED (RUDDER)

PIT - Q5 - SKIN SURFACE, 5 INCH LONG GOUGE, RUDDER LT SIDE STA 186, NEAR T/E. INSTALLED REPAIR PLYS IAW SRM.

Part: SKIN — CHAFED (RUDDER)

PIT - Q5 - SKIN SURFACE, 1 INCH CHAFE WEAR, RUDDER RT SIDE L/E AT STA 170. INSTALLED REPAIR PLYS IAW SRM AND EA.

Part: FAILSAFE — CRACKED (FUSELAGE)

PIT - Q5 - FAIL SAFE CHORD, .75 INCH CRACK, STA 380 AT STR 15R. REMOVED DAMAGE AND INSTALLED DOUBLER IAW SRM 51-70-11, FIG 1.

Part: SKIN — CORRODED (LT WING)

PIT - Q6 - WING SKIN CUTOUT, .5 INCH X .75 INCH AT (4) LOCATIONS, CORROSION; NO LEVEL OR TASK; LT WING 7403L PANEL FUEL BOOST PUMP ACCESS AREA. REMOVED CORROSION AND REPAIRED IAW DRAFT EA 79514.

Part: SKIN — DAMAGED (RUDDER)

PIT - Q5 - TOP COMPOSITE LAYER, SEVERAL AREAS 2 INCH SQUARE, SINGLE LAYER COMPOSITE DAMAGE, RUDDER LT SIDE BETWEEN STA 96 AND 121. APPLIED WET LAY UP REPAIR IAW SRM AND EA.

Part: STRINGER CLIP — CRACKED (FUSELAGE)

STRINGER CLIP, .2500 INCH CRACK, BS 663.75, STRINGER 10 LT. DEFECTIVE PART REPLACED WITH IDENT PN.

Part: SKIN — DAMAGED (RUDDER)

PIT - Q5 - TOP COMPOSITE LAYER, 1 INCH X .2500 INCH AREA, SINGLE LAYER COMPOSITE DAMAGE, RUDDER LT SIDE STA 0 L/E. APPLIED WET LAY UP REPAIR IAW SRM AND EA.

Part: SKIN — DAMAGED (RUDDER)

PIT - Q5 - TOP COMPOSITE LAYER, 3 INCHES LONG, SINGLE LAYER COMPOSITE DAMAGE, RUDDER LT SIDE AT STA 178, 13 INCHES FROM FWD SPAR. APPLIED WET LAY UP REPAIR IAW SRM AND EA.

Part: STIFFENER — CRACKED (WING)

PIT- Q6 - VERTICAL STIFFENER, 1.2500 INCH CRACK, AT RBBL 6.15, STA 663.75. REPLACED VERTICAL STIFFENER IAW EA 79313 AND EO 5704V245 (RAFT).

Part: SKIN — CORRODED (RT WING)

PIT - Q6 - WING SKIN CUT OUT, 1.2500 INCH X .2500 INCH AT 4 LOCATIONS, CORROSION; NO LEVEL OR TASK, RT WING BOOST PUMP CUT OUT. REMOVED CORROSION AND INSTALLED REPAIR IAW SRM.

Part: ATTACH ANGLE — CRACKED (THRUST BEAM)

PIT - Q5 - ANGLE, 6 INCH LONG CRACK, HORIZ STAB CTR SECTION THRUST BEAM ATTACH ANGLE LT SIDE. REMOVED AND REPLACED ANGLE, REPLACED IAW TYP REP SRM 51-00-30. REMOVED AND REPLACED IAW TYP REP SRM 51-00-30.

Part: STRAP — CORRODED (DOOR FRAME)

PIT - Q5 - STRAP, .2500 INCH BY .2500 INCH IN 66 AREAS, CORROSION; LEVEL 1; TASK NR-C53-107-02, AFT CARGO DOOR FRAME SECTION S25R, STA 807-848. REPLACED PART IAW SRM 53-00-07.

Part: ANGLE — CRACKED (HORIZONTAL STAB)

HORIZ STAB CENTER SECTION THRUST BEAM ATTACH ANGLE RT SIDE. REMOVED AND REPLACED ANGLE IAW TYP REP REMOVED AND REPLACED SRM 51-00-30.

Part: SUPPORT FITTING — CRACKED (LT MLG AFT SPAR)

PIT - Q5 - L/G SUPPORT FITTING, .2500 INCH CRACK, LT MLG SUPPORT FITTING AT REAR SPAR. REMOVED AND REPLACED WITH NEW FITTING IAW EO 5702V054.

Part: SKIN — DELAMINATED (NR 2 SLAT)

PIT - Q5 - NR 2 SLAT SKIN, 3 INCH BY 4 INCH AREA, DELAMINATION, OB END T/E. REMOVED DAMAGE SKIN AND CORE, INSTALLED NEW CORE, TOP DOUBLER IAW SRM 51-70-10.

Part: SKIN — CRACKED (NR 4 SLAT)

PIT - Q5 - NR 4 SLAT SKIN, 6 FASTENER HOLES, .1250 INCH TO .2500 INCH CRACK. FASTENER HOLES, LOWER SKIN AREA BELOW ACTUATOR ATTACH POINT. CUT OUT DAMAGE, INSTALLED FILLER AND DOUBLER IAW SRM 57-43-01, FIG 206.

Part: SKIN — DELAMINATED (RT TE FLAP)

PIT - Q5 - SKIN TO CORE, 7 INCHES BY 2.5 INCH AREA DELAMINATED, IB RT AFT FLAP TOP SURFACE 34.5 INCHES- 42 INCHES FROM OB END. REMOVED UPPER SKIN AND CORE, INSTALLED NEW CORE AND TOP DOUBLER IAW SRM 51-70-10.

Part: SKIN — CRACKED (FUSELAGE)

PIT - Q5 - SKIN, 1.5 INCH CRACK, FWD SERVICE DOOR CUTOUT AFT LOWER CORNER. INSTALLED REPAIR DOUBLER IAW SRM 53-10-01.

Part: SKIN — DELAMINATED (NR 4 SLAT)

SKIN AND CORE, 4 INCH BY 4 INCH AREA, IB T/E NR 4 SLAT. REMOVED DELAMINATED SKIN AND CORE, INSTALLED DOUBLER, NEW CORE IAW 51-70-10.

Part: CREASE BEAM — CORRODED (FUSELAGE)

PIT - Q5 - CREASE BEAM WEB, .75 INCH (6 AREAS), CORROSION; NO LEVEL OR TASK, BETWEEN STA 420 AND STA 440, RT SIDES. CREASE BEAM WEB MFG IAW DWG 65-96956 AND BACD2003.

Part: SUPPORT ANGLE — CRACKED (FUSELAGE)

PIT - Q5 - SUPPORT ANGLE, 1 INCH LONG, CRACKED. SUPPORT DOWNLOCK VIEWER LT FWD CORNER, STA 259.5. REPLACED PART IAW DWG 65-45833.

Part: FLOORBEAM — MISMANUFACTURED (FUSELAGE)

PIT-Q5- FLOORBEAM, INCORRECT MATERIAL FROM MFG. FLOORBEAM UPPER CHORD REMOVED AND REPLACED IAW EA 68822A, FLOOR STA 328.

Part: SKIN — GOUGED (FUSELAGE)

PIT - Q5 - SKIN, .025 INCH DEEP AND AT 10 INCHES LONG, GOUGED, STA 887-867, STR 1. CUT OUT DAMAGE INSTALLED SHIMS, FILLERS, STRAPS, DOUBLER AND TRIPLER IAW EA 79291.

Part: FRAME — CORRODED (FUSELAGE)

PIT - Q5 - ANTENNA MOUNT FRAME, 3 INCHES L BY 1 INCH W, CORROSION; LEVEL 1; TASK NR C53-107-01, VHF ANTENNA NR 2 MOUNT. REPAIRED IAW SM 51-10-2 AND 51-40-00.

Part: FLOOR PANEL — CORRODED (CABIN)

PIT - Q5 - FLOOR PANEL, 1 INCH BY 5 INCH AREA CORROSION, LEVEL 1; TASK NR C53-107-02, PANEL NR 99, STA 1016. REPLACED FLOOR PANEL NR 99 IAW SRM 51-70-12.

Part: CHANNEL — CRACKED (FUSELAGE)

PIT - Q5 - CHANNEL, .5 INCH CRACK, STA 540 LBBL 0, RBBL U CHANNEL. REPLACED CHANNEL IAW SRM 53-00-03.

Part: PAN — TORN (FUSELAGE)

PIT, Q5, FLOOR PAN, .5 INCH TEAR, LBL 18 INCH AT STA 986.5. INSTALLED FILLER/DOUBLER IAW SRM 51-70-13, FIG 1.

Part: SUPPORT ANGLE — CORRODED (FUSELAGE)

PIT - Q5 - SUPPORT ANGLE, 1.2500 INCH BY .5 INCH AREA, CORROSION; LEVEL 1; TASK NR C53-208-01, FLOOR SUPPORT, STA 859. BURNISHED, TREATED AND PRIMED IAW TYP REP 53-10-06B.

Part: DOOR FRAME — CRACKED (FUSELAGE)

PIT - Q5 - FRAME, .5 INCH CRACK. FWD SERVICE DOOR SURROUND FRAME AT 294.5 AND S17R. FABRICATED DOUBLER IAW SRM 51-70-11.

Part: STIFFENER — CRACKED (LBB6.15 TO663.45)

PIT- Q5 - VERTICAL STIFFENER, .7500 INCH CRACK, VERTICAL STIFFENER OF LBBL 6.15 TO 663.45. REPLACED VERTICAL STIFFENER OF LBBL 6.15 TO 663.45. REPLACED VERT STIFFENER IAW EA 79313/ EO5704V245 (DRAFT).

Part: FRAME — CRACKED (FUSELAGE)

PIT- Q5 - FRAME, 2 INCH CRACK, STA 440 S9L. INSTALLED DOUBLERS IAW TYP REP 53-10-20A.

Part: STRINGER CLIP — CRACKED (FUSELAGE)

PIT- Q5- STRINGER TIE CLIP, .2500 INCH CRACK, BS 344, STR8, RT. FABRICATED IAW MFG DWG 66-244553 AND INSTALLED IAW SRM 51-40-01.

Part: STRINGER CLIP — CRACKED (FUSELAGE)

PIT- Q5- STRINGER TIE CLIP, 1.25 INCH CRACK, BS 360, STR 4, RT. DEFECTIVE PART REPLACED WITH IDENT PART NR IAW SRM 51-10-02.

Part: ANGLE — CRACKED (FUSELAGE)

PIT - Q5 - ANGLE, .5 INCH CRACK, STA 380 AT STR 15R. FABRICATED REPAIR ANGLE IAW SRM 51-70-11.

Part: TIE CLIP — CRACKED (FUSELAGE)

PIT - Q5 - STRINGER TIE CLIP, .7500 INCH CRACK, BS 663 STRINGER 2 RT. FABRICATED NEW CLIP IAW DWG 69-45156 IAW SRM 51-40-02.

Part: SKIN — DELAMINATED (NR 2 SLAT)

PIT - Q5 - NR 2 SLAT, 2 SQ INCH AREA, DELAMINATION, IB T/E. REMOVED DAMAGED SKIN AND CORE, INSTALLED NEW CORE, TOP DOUBLER IAW SRM 51-70-10.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT)

PIT - MAINTENANCE REPORTED THE EMERGENCY LIGHT BATTERY PACK, IN FORWARD GALLEY OVERHEAD, HAS LOW CHARGE. MAINTENANCE REMOVED AND REPLACED THE BATTERY PACK. OPS CHECK GOOD. (M)

Part: FRAME — CORRODED (BULKHEAD)

PIT - FOUND LOWER LEG OF CHORD CORRODED .5 INCH BY 1 INCH AREA, AFT SIDE OF PRESSURE BULKHEAD FROM STRINGER 27L TO 26L. CLEANED CORROSION, TREATED AND PRIMED PER SRM 51-10-02 AND 51-20-01. (M)

Part: SKIN — CRACKED (FUSLEAGE)

FOUND SKIN CRACKED 3.5 INCH, FS 882 AND S25R. INSTALLED DOUBLER AND TRIPLER PER SRM 53-00-00 FIG 229. (M)

Part: SKIN — CRACKED (FUSELAGE)

CLT - FOUND SKIN CRACKED .4375 INCH STATION 380 STRINGER 00 BOTTOM FUSELAGE CENTER LINE. INSTALLED DOUBLER PER TR 53-30-07. (M)

Part: SKIN — CRACKED (FUSELAGE)

CLT - FOUND SKIN CRACKED .5 INCH, BOTTOM OF FORWARD FUSELAGE AND R/B COOLING DUCT. DAMAGED REMOVED, DOUBLER INSTALLED PER TYPICAL REPAIR 53-30-07. (M)

Part: ANGLE — CRACKED (FUSELAGE)

CLT - FOUND SUPPORT ANGLE CRACKED 3 INCHES, STATION 540, STRINGER 22L RAM AIR INLET SUPPORT ANGLE. INSTALLED DOUBLER PER TR 53-50-03. (M)

Part: SKIN — CRACKED (NR 1 PYLON)

CLT - FOUND SKIN AND DOUBLER CRACKED 1 INCH, NR 1 PYLON AT ACCESS PANEL 5728L. INSTALLED DOUBLER PER TR 54-30-07. (M)

Part: SKIN — CRACKED (NR 3 SLAT)

CLT - FOUND NR 3 SLAT SKIN CRACKED .25 INCH, LOWER SKIN AFT FASTENER ROW 4 INCHES L/B ACTUATOR. INSTALLED DOUBLER PER SRM 57-43-01 FIG 206. (M)

Part: DOOR FRAME — CRACKED (FUSELAGE)

CLT - FOUND FRAME CRACKED 1 INCH, LEFT AFT DOOR FRAME UPPER HINGE FITTING. REPLACED FITTING PER SRM 51-10-02. (M)

Part: STRINGER — CRACKED (FUSELAGE)

CLT - Q-4, STRINGER CRACKED, 2 INCHES, LEFT SIDE STR 5A, AFT STA 1138 FRAME. REPAIRED ANGLES AND DOUBLER PER SRM 53-00-01. (X)

Part: BULKHEAD — CRACKED (FUSELAGE)

CLT - Q-4, BULKHEAD CRACKED, .25 INCH, BS 178, WL 206.5, RBL 1.0. INSTALLED DOUBLER PER EA 68148 AND SRM 53-10-08 FIG 203. (X)

Part: BULKHEAD — CRACKED (FUSELAGE)

CLT - Q-4, BULKHEAD CRACKED, .25 INCH, BS 178, WL 199, LBL 5.5. REMOVED AND INSTALLED DOUBLER PER EA 68148 AND SRM 53-10-08, FIG 203. (X)

Part: BULKHEAD — CRACKED (FUSELAGE)

CLT - Q-4, WEB CRACKED, .25 INCH, STA 178, RBL 1, WL 206. INSTALLED DOUBLER PER EA 68148 AND SRM 53-10-08 FIG 203. (X)

Part: BULKHEAD — CRACKED (FUSELAGE)

CLT - Q-4, BULKHEAD CRACKED, .50 INCH, BS 178, WL 188, RBL 1.0. INSTALLED DOUBLER PER EA 68148 AND SRM 53-10-08 FIG 203. (X)

Part: BULKHEAD — CRACKED (FUSELAGE)

CLT - Q-4, SKIN CRACKED, 1 INCH, RBL 5, WL 188, STA 178. REMOVED CRACK, INSTALLED DOUBLER PER EA 68148 AND SRM 53-10-08, FIG 203. (X)

Part: BULKHEAD — CRACKED (FUSELAGE)

CLT - Q-4, SKIN CRACKED, STA 178, RBL 7, WL 210.5. INSTALLED DOUBLER PER EA 68148 AND SRM 53-10-08 FIG 203. (X)

Part: BULKHEAD — CRACKED (FUSELAGE)

CLT - Q-4, BULKHEAD CRACKED, 1 INCH, BS 178, WL 202, LBL 5.5. INSTALLED DOUBLER PER EA 68148 AND SRM 53-10-08 FIG 203. (X)

Part: BULKHEAD — CRACKED (FUSELAGE)

CLT - Q-4, BULKHEAD CRACKED, .50 INCH, BS 178, WL 202, RBL 5.5. INSTALLED DOUBLER PER EA 68148 AND SRM 53-10-08. (X)

Part: BULKHEAD — CRACKED (FUSELAGE)

CLT - Q-4, SKIN CRACKED, 1 INCH, BS 178, WL 195, LBL 5.7. REMOVED AND INSTALLED DOUBLER PER EA 68148 AND SRM 53-10-08, FIG 203. (X)

Part: BULKHEAD — CRACKED (FUSELAGE)

CLT - Q-4, SKIN CRACKED, 1 INCH, BS 178, WL 195, RBL 5.7. REMOVED AND INSTALLED DOUBLER PER EA 68148 AND SRM 53-10-08 FIG 203. (X)

Part: STIFFENER — CRACKED (BULKHEAD)

CLT - Q-4, VERTICAL STIFFENER CRACKED .5 INCH AFT SIDE BULKHEAD 178, WL 184, LBL 5.7 ON INBOARD SIDE. INSTALLED REPAIR ANGLE AND STRAP PER SRM 53-10-08 FIG 205. (X)

Part: SKIN — CRACKED (NACELLE)

CLT - Q-4, SKIN CRACKED .50 INCH AT RIGHT AFT CORNER ACCESS PANEL AT NAC STA 225. INSTALLED FILLER AND DOUBLER PER TR 54-30-07. (X)

Part: SEAT TRACK — CORRODED (FUSELAGE)

CLT - Q-4, SEAT TRACK CORRODED, 24 INCHES, CORROSION LEVEL 1 C53-107-02, CENTER BETWEEN STA 328 AND STA 344. REPLACED SEAT TRACK PER SRM 53-00-92. (X)

Part: FLOORBEAM — CORRODED (FUSELAGE)

CLT - Q-4, FLOORBEAM CORRODED, 120 INCHES, CORROSION LEVEL 1. STA 967 T-CAP AREA OF FLOORBEAM. INSTALLED NEW T-CAP AND DOUBLER PER TR 53-60-01. (X)

Part: FLOORBEAM — CORRODED (FUSELAGE)

CLT - Q-4, FLOORBEAM CORRODED, 2 INCH BY 1 INCH, STA 312, LBL 50 TO RBL 50. CORROSION LEVEL 1 C53-107-02. REPAIRED PER SRM 53-10-51. (X)

Part: FLOORBEAM — CORRODED (FUSELAGE)

CLT - Q-4, FLOORBEAM CORRODED, 120 INCHES, CORROSION LEVEL 1, STA 986.5 T-CAP AREA. INSTALLED NEW T-CAP AND DOUBLER PER TR 53-60-01. (X)

Part: FLOORBEAM — CORRODED (FUSELAGE)

CLT - Q-4, FLOORBEAM CORRODED, .50 INCH X 2 INCH, CORROSION LEVEL 1 C53-107-02, STA 294.5, BL ZERO TO RBL 52. SPLICED T-CAP PER SRM 53-10-51. (X)

Part: FLOORBEAM — CORRODED (FUSELAGE)

CLT - Q-4, T-CAP/FLOORBEAM CORRODED, 2 INCHES BY 100 INCHES, CORROSION LEVEL 1, STA 328. REPLACED T-CAP PER SRM 53-10-52, FIG 205. (X)

Part: FLOORBEAM — CORRODED (FUSELAGE)

CLT - Q-4, FLOORBEAM CORRODED, 2 INCHES BY 2 INCHES, CORROSION LEVEL 1 AT FLOORBEAM STA 967, BL 31. INSTALLED NEW T-CAP AND DOUBLER PER TR 53-60-01. (X)

Part: FRAME — CRACKED (FUSELAGE)

CLT - Q-4, FRAME HAD .25 INCH CRACK AT BS 907 BETWEEN S8L - S9L. FABRICATED REPAIR DOUBLER PER TR 53-10-14. (X)

Part: STRINGER CLIP — CRACKED (FUSELAGE)

CLT - FOUND TIE BRACE CRACKED .250 INCH, STATION 294.5 STRINGER 17R. REPLACED TIE CLIP PER SRM 51-10-2. (M)

Part: FRAME — CRACKED (FUSELAGE)

CLT - Q-4, FRAME HAD .25 INCH CRACK AT STA 887 S8R - S 9R. FABRICATED DOUBLER AND INSTALLED PER TR 53-10-14. (X)

Part: WEB — CORRODED (FUSELAGE)

CLT - FOUND WEB CORRODED 5 INCHES BY 1.5 INCHES, STRINGER 17L BETWEEN STATION 847-867. CORROSION LEVEL 1, TASK NR C53-107-01. REPLACED WEB PER SRM 51-10-02. (M)

Part: BEAM — CORRODED (FUSELAGE)

CLT - FOUND CREASE BEAM WEB CORRODED 1 INCH BY 2 INCHES IN 6 PLACES, BETWEEN STATION 847-867 STRINGER 17L. CORROSION LEVEL 1, TASK NR C53-107-01. DEFECTIVE PART REPLACED WITH IDENTICAL PART NR PER SRM 51-10-2. (M)

Part: CREASE BEAM — CRACKED (FUSELAGE)

CLT - Q-4, CREASE BEAM HAD 3 INCH CRACK AT FORWARD END OF S17R STA 617. FABRICATED REPAIR ANGLES PER SRM 53-60-13. (X)

Part: TIE CLIP — CRACKED (FUSELAGE)

CLT - Q-4, TIE CLIP HAD .25 INCH CRACK AT S4L STA 907. REPLACED WITH ORIGINAL PART NUMBER PER SRM 51-10-02. (X)

Part: TIE CLIP — CRACKED (FUSELAGE)

CLT - Q-4, TIE CLIP HAD .1250 INCH CRACK AT STA 500A STR 2L. REPLACED TIE CLIP PER SRM 51-10-2. (X)

Part: FRAME — CRACKED (FUSELAGE)

CLT - Q-4, FRAME HAD .1250 INCH CRACK AT STA 480 STR 9R. FABRICATED DOUBLER, HEAT TREATED AND INSTALLED PER TR 53-10-14. (X)

Part: FRAME — CRACKED (FUSELAGE)

CLT - Q-4, FRAME CRACKED .25 INCH AT BS 727D BETWEEN S9R - S8R. FABRICATED REPAIR DOUBLER, HEAT TREATED AND INSTALLED WET PER TR 53-10-14. (X)

Part: TIE CLIP — CRACKED (FUSELAGE)

CLT - Q-4, TIE CLIP CRACKED AT STA 597 S10L. DEFECTIVE PART REPLACED WITH IDENTICAL PART NUMBER PER SRM 51-10-02 - SRM 51-40-02. (X)

Part: FRAME — CRACKED (FUSELAGE)

CLT - Q-4, FRAME HAD .25 INCH CRACK AT STA 400 BETWEEN S9L AND S8L. DOUBLER INSTALLED PER TR NR 53-10-14. (X)

Part: CREASE BEAM — CORRODED (FUSELAGE)

CLT - Q-4, CREASE BEAM 20 SQUARE INCHES OF CORROSION. CORROSION LEVEL 1, TASK NR C53-107-01. S17R CREASE BEAM STA 616 - STA 639. REMOVED OLD CREASE BEAM WEB AND REPLACED WITH NEW PART PER SRM 53-60-13. (X)

Part: ANGLE — CORRODED (FUSELAGE)

CLT - FOUND SURFACE CORROSION ON Z-ANGLE, 41 INCHES LONG, STATION 950 TO 994 RBL 55. CORROSION LEVEL 1, TASK NR C53-107-01. DEFECTIVE PART REPLACED WITH IDENTICAL PART NR PER SRM 51-20-01 AND 51-10-02. (M)

Part: ANGLE — CORRODED (FUSELAGE)

CLT - FOUND SURFACE CORROSION ON Z-ANGLE, 45 INCHES LONG, STATION 955-994 RBL 54. CORROSION LEVEL 1, TASK NR C53-107-01. DEFECTIVE PART REPLACED WITH IDENTICAL PART NR PER SRM 51-10-02 AND 51-20-01. (M)

Part: SKIN — CRACKED (STABILIZER)

CLT - Q-4, SKIN HAD 1 INCH CRACK AT LOWER SKIN STABILIZER, STA 134, FORWARD OF REAR SPAR. INSTALLED DOUBLER PER 55-10-07. (X)

Part: STIFFENER — CRACKED (FUSELAGE)

CLT - Q-4, STRINGER, STIFFENER/WEB CRACKED, .1250 INCH, AT STA 294.5 - 277, STR 14R. FABRICATED NEW WEB PER SRM 53-30-01 AND SRM 51-70-13. (X)

Part: DOOR FRAME — CRACKED (FUSELAGE)

CLT - DURING Q-4 INSPECTION, FOUND DOOR FRAME CRACKED .375 INCH AT UPPER STOP PAD SUPPORT R-1 DOOR INBOARD FRAME. REPLACED WITH NEW STUB FRAME PER SRM 51-40-02 AND DWG 65 45807. (X)

Part: FRAME — CRACKED (FUSELAGE)

CLT - DURING Q-4 INSPECTION, FOUND DOOR FRAME CRACKED .500 INCH AT INBOARD UPPER FORWARD CORNER R-1. FABRICATED SPLICE AND INSTALLED PER SRM 51-40-02. (X)

Part: ANGLE — CORRODED (FUSELAGE)

CLT - FOUND CORROSION AT T-ANGLE AND WEB, 2 INCHES BY 4 FEET, AFT STATION 1088 ABOUT WL 294. REMOVED CORROSION PER RM 51-10-02. (M)

Part: Z-ANGLE — CORROSION (BS 277-360)

CLT - FOUND Z-ANGLE CORRODED, STATION 277 TO 360, LBL 58. INSTALLED NEW Z-ANGLE PER SRM 51-10-02. CORROSION LEVEL 1. (M)

Part: BULKHEAD — CRACKED (FUSELAGE)

BULKHEAD CRACKED. FABRICATED NEW WEB PER SRM 51-10-02

Part: ANGLE — CORRODED (FUSELAGE)

CLT - FOUND SUPPORT ANGLE CORRODED 2 INCHES BY 4 INCHES, STATION 312 TO STATION 344, LBL 60. INSTALLED NEW ANGLE PER RM 51-10-2. (M)

Part: TIE CLIP — CRACKED (FUSELAGE)

TIE CLIP CRACK. REPLACED TIE CLIP PER SRM 51-10-2

Part: ANGLE — CORRODED (FUSELAGE)

CLT - FOUND ANGLE CORRODED 2 INCHES BY 6 INCHES, BETWEEN BS 747 AND 767 TRANSITION ANGLE. FABRICATED NEW ANGLE AND INSTALLED PER SRM 51-10-02. (M)

Part: FLOORBEAM — CORRODED (FUSELAGE)

CLT - FOUND 2 INCH BY 1 INCH AREA OF CORROSON, STATION 244, LBL 32 TO RBL 54. CORROSION LEVEL 1. INSTALLED NEW T-CAP PER SRM 53-10-51 FIG 205. (M)

Part: ANGLE — CORRODED (FUSELAGE)

CLT - FOUND Z-ANGLE CORRODED 1 INCH BY 20 INCHES, STATION 270 TO 360, RBL 58. INSTALLED NEW Z-ANGLE PER SRM 51-10-2. (M)

Part: WEB — CORRODED (FUSELAGE)

CLT - FOUND WEB CORRODED 20 INCHES, STRINGER 17L CREASE BEAM STATION 616 TO 639. CORROSION LEVEL 1. REMOVED AND REPLACED WEB PER SRM 51-10-02. (M)

Part: WEB — CRACKED (FUSELAGE)

WEB CRACKED. FABRICATED NEW WEB PER SRM 51-10-02

Part: TIE CLIP — CRACKED (FUSELAGE)

CLT - FOUND TIE CLIP CRACKED .250 INCH, STRINGER 10LT STATION 663.75. REPLACED TIE CLIP PER SRM 51-40-02. (M)

Part: TIE CLIP — CRACKED (FUSELAGE)

TIE CLIP CRACK. FABRICATED NEW TIE CLIP PER SRM 51-10-02

Part: TIE CLIP — CRACKED (FUSELAGE)

CLT - FOUND TIE CLIP CRACKED .25 INCH, BS 663.75, STRINGER 10R. INSTALLED NEW TIE CLIP PER SRM 51-10-02. (M)

Part: CONTROLLER — FAILED (RUDDER)

CLT - FLT 1750 - EN ROUTE FROM PVD TO CLT, AIRCRAFT EXPERIENCED AN UNCOMMANDED ROLL IN CRUISE AT FL350, MACH .75. WITH B AUTOPILOT AND AUTOTHROTTLE ON AND UNAV AND LNAV ENGATED, THE YAW DAMPER DISENGAGED AND THE AIRCRAFT ROLLED 15-20 DEGREES LEFT. THE AUTOPILOT KICKED OFF AND THE CREW STABILIZED THE AIRCRAFT. CREW ATTEMPTED TO TURN THE YAW DAMPER BACK ON WITH AUTOPILOT OFF, BUT AIRCRAT ROLLED LEFT AGAIN. CREW THEN ATTEMPTED TO TURN ON BOTH A/B AUTOPILOT WITH YAW DAMPER OFF AND AIRCRAFT ROLLED AGAIN TO THE LEFT. CREW DID NOT DETECT ANY RUDDER MOVEMENT IN RUDDER PEDALS. CREW REQUESTED A LOWER ALTITUDE AND PROCEEDED ONTO CLT WITHOUT INCIDENT. NO EMERGENCY WAS DECLARED. MAINTENANCE FOUND THE RUDDER POWER CO

Part: BATTERY PACK — DISCHARGED (FORWARD CABIN)

PHL - MAINTENANCE FOUND THE FORWARD THIRD OF CABIN FLOOR PROXIMITY EVACUATION LIGHTS INOPERATIVE. MAINTENANCE REMOVED AND REPLACED THE BATTERY PACK AT SEAT ROW 1. OPS CHECK GOOD. (M)

Part: ANTI-ICE VALVE — FAILED (NR 1 ENGINE)

PIT - FLT 620 - EN ROUTE FROM LAS TO PHL, DURING CRUISE, THE NR 1 ENGINE COWL ANTI-ICE LIGHT ILLUMINATED WHEN SELECTED ON. CREW REDUCED POWER AND LIGHT EXTINGUISHED. FLIGHT DIVERTED TO PIT AND LANDED WITHOUT FURTHER INCIDENT. (M)

Part: AIR DATA COMP — FAILED (E/E COMP)

TPA - FLT 1425 - DURING CLIMB, THE FIRST OFFICERS AIRSPEED INDICATION FAILED AND THE FIRST OFFICERS ALTIMETER READING WAS VERY LOW. FLIGHT RETURNED TO FIELD AT TPA. NO EMERGENCY WAS DECLARED AND THE FLIGHT LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED THE NR 2 AIR DATA COMPUTER PE MM 34-12-11. FUNCTIONAL CHECK GOOD. (M)

Part: ACTUATOR — FAILED (RT MLG)

IAD - FL 2116 - ON APPROACH TO DCA AT 3,200 FEET, AN UNSAFE RIGHT GEAR INDICATION WAS NOTED. CREW RECYCLED GEAR AND DID A TOWER FLYBY. TOWER REPORTED GEAR LOOKED DOWN AND LOCKED. CREW EXECUTED MISSED APPROACH AND HELD WHILE RUNNING CHECKLIST AND TRYING MANUAL DEPLOYMENT. STILL RECEIVED UNSAFE LIGHT. CAPTAIN DECIDED TO DIVERT TO IAD. NO EMERGENCY WAS DECLARED AND THE FLIGHT LANDED SAFELY WITH NO FURTHER INCIDENT. MAINTENANCE REPLACED THE RIGHT MAIN LANDING GEAR ACTUATOR. ADJUSTMENT AND TEST PER MAINTENANCE MANUAL CHECKS GOOD. (M)

Part: INDICATION — MALFUNCTIONED (LANDING GEAR)

CLT - FLT 57 - UPON LOWERING LANDING GEAR INTO CLT, CREW RECEIVED RED RIGHT MAIN GEAR LIGHT. GREEN RIGHT MAIN GEAR LIGHT WAS OFF. CREW RECYCLED GEAR AND ALL GEAR INDICATIONS WERE NORMAL. FLIGHT LANDED WITH NO FURTHER INCIDENT. MAINTENANCE CHECKED GEAR WARNING AND POSITION SYSTEM PER MM 32-09-20. COMPLIED WITH GEAR LUBE. OPS CHECK GOOD. (M)