N988DN

Part: LIGHT — BROKEN (SEAT 21B) · airframe 35,633 hrs · 28,638 cycles

EMERGENCY LIGHT STRIP BROKEN AT SEAT 21B. REINSTALLED THE LIGHT STRIP. CHECKED OK.

Part: UNKNOWN — MALFUNCTIONED (TE FLAP) · airframe 35,611 hrs · 28,617 cycles

THE FLIGHT CREW DECLARED AN EMERGENCY ON APPROACH INTO CAE AFTER THE FLAPS STOPPED EXTENDING BEYOND 18 DEGREES. MAINTENANCE FUNCTIONALLY CHECKED THE FLAP CONTROL SYSTEM, THE FLAP POSITION TRANSMITTERS, THE FLAP RATE TEST, AND THE ADJUSTMENT OF THE FLAP BUS CABLE SYSTEM. ALL CHECKS WERE GOOD AND WITHIN LIMITS PER THE AMM 27-50. NO ASYMMETRY EXISTS. THE FLAP POSITION TRANSMITTER WAS REPLACED PER AMM 27-54 AS A PRECAUTION. THE FLAP SYSTEM AND FCC NR 1 & NR 2 WERE ALL RETURNED TO SERVICEABLE OPERATION.

Part: POWER SUPPLY — INOPERATIVE (CABIN) · airframe 35,597 hrs · 28,604 cycles

THE OVERWING EMERGENCY LIGHT DOES NOT TURN ON. TROUBLE SHOT PER 33-50-00 810-801. DURING CHECK POWER SUPPLY B5-119 REPLACEMENT BECAME REQUIRED. POWER SUPPLY WAS REPLACED PER AMM 33-51-03 AND TEST WAS PERFORMED PER AMM 33-51-00. OPERATIONAL TEST IS OK.

Part: SKIN — CRACKED (SERVICE DOOR) · airframe 35,733 hrs · 28,705 cycles

CRACK WAS FOUND OF 0.250" ON R1 FWD SERVICE DOOR, BOTTOM AREA, OUTER SKIN. PERMANENT REPAIR. CRACK ON R1 FWD SERVICE DOOR BOTTOM AREA WAS REPAIRED PER SRM 51-70-01-2R. HFEC INSPECTION WAS ACCOMPLISHED ON R1 FWD SERVICE DOOR BOTTOM AREA, OUTER SKIN AFTER TRIM OUT AND NO CRACKS WERE FOUND PER NDT SPM 06-10-01.001.

Part: ACCESS PANEL — DAMAGED (LT WING) · airframe 35,597 hrs · 28,604 cycles

ELONGATED HOLES ON FUEL ACCESS PANEL 520DT ON THE LT WING. THE ACCESS PANEL WAS REPAIRED IAW SRM 57-10-01-2R-2, PAR 5, CONDITION II.

Part: LENS — DAMAGED (EMERGENCY LIGHT) · airframe 35,305 hrs · 28,402 cycles

EMERGENCY EXIT COVER DIFFUSER LENS DAMAGED. MAINTENANCE REPLACED LIGHT ASSY IAW DRAWING BR9051. OPS CHECKED GOOD.

Part: BATTERY — DISCHARGED (CABIN) · airframe 33,237 hrs · 26,950 cycles

FWD EMERGENCY LIGHT FOUND INOP DURING SERVICE CHECK. REPLACED EMERGENCY LIGHT BATTERY IAW AMM 33-51. OPS CHECK GOOD AT THIS TIME. A/C OK FOR SVC.

Part: SKIN — DENTED (BS 332-351) · airframe 30,566 hrs · 24,934 cycles

AA WORK CARD 2330-01340-01A. DURING STEP 3 OF TASK CARD, 7 EA DENT DOTS FOUND AT ANTENNA INSTALLATION AREA. CUT OUT AREAS ON FUSELAGE SKIN BETWEEN BS 332 AND BS 351, BETWEEN LONGERONS 29LT AND 29RT. CUTOUT DIMENSIONS: 8.25" X 4.875" AND 1.875" X 1.125". FABRICATED DOUBLER DIMENSIONS: .071" X 18.5" X 16.60", FILLER DIMENSIONS .063" X 8.25" X 4.875", AND INSTALLED REPAIR PARTS IAW ER/A 542811-14, REV 0, REV 1, AND ER/A 542811-14, REV A.

Part: SEAT TRACK — CORRODED (BS 218-589) · corrosion level 2 · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN SEAT TRACK CORRODED BETWEEN BS 218-589, RBL 54. CORROSION DAMAGE ON MAIN CABIN SEAT TRACK, RBL 54, STA 218-589. FOUND OUT OF LIMITS, ORIGINAL THICKNESS .100", MATERIAL LOSS .042", MATERIAL REMAINING .058" IAW SRM 53-20-52. REPLACED SEAT TRACK IAW SRM 51-41-01 AND DWG 5930547, REV CZ.

Part: FLOORBEAM — CORRODED (BS 195) · corrosion level 2 · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR SUPPORT, BS 195, LBL 22-LBL 44 CORRODED. CORROSION DAMAGE ON MAIN CABIN FLOOR SUPPORT BS 195, LBL 22-LBL 44 FOUND TO BE OUT OF LIMITS, ORIGINAL THICKNESS .070", MATERIAL LOSS .029", MATERIAL REMAINING .041" DIM 3" X 1" IAW SRM 53-00-00, 53-10-51, AND DWG S2929169, REV B. REPLACED FLOOR SUPPORT IAW SRM 51-41-02 AND DWG 9936534, REV BW.

Part: SEAT TRACK — CORRODED (BS 237) · corrosion level 2 · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN SEAT TRACK CORRODED UNDER TIEDOWN BS 237, RBL 44. CORROSION DAMAGE ON MAIN CABIN SEAT TRACK BS 237, RBL 44 FOUND OUT OF LIMITS, ORIGINAL THICKNESS .100", MAT. LOSS 100 PERCENT, DIM. 8" IAW 53-20-52 ALLOWABLE DAMAGE 1 AND DWG S00484, REV B. REPLACED SEAT TRACK SECTION BS 200-240, EBL 44 IAW SRM 51-41-05 AND 51-41-01.

Part: FLOOR PANEL — DAMAGED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL, NR 222YF HAS 2 EA DAMAGED COVERS AND 2 EA DAMAGED STIFFENERS, LT AND RT SIDES. REPLACED MAIN CABIN FLOOR PANEL 222YF STIFFENERS, 2 EA AND COVERS 2 EA IAW SRM 51-41-08 AND DWG 9936639, REV P.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL NR 222ADF IS DELAMINATED AND 1 EA COVER DAMAGED. MAIN CABIN FLOOR PANEL NR 222ADF FOUND TO BE 40 PERCENT DELAMINATED AND OUT OF LIMITS IAW SRM 53-20-50 ALLOWABLE DAMAGE 1. FABRICATED NEW FLOOR PANEL AND INSTALLED NEW COVER ON NEW PANEL IAW SRM 53-20-50, REPAIR 3 AND DWG 9936639, REV P.

Part: CUSP WEB — CORRODED (BS 908-946) · corrosion level 2 · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN CORRODED ON CUSP WEB CORRODED BETWEEN BS 908 TO 946 RT SIDE. CORROSION DAMAGE FOUND TO BE OUT OF LIMITS IN TWO LOCATIONS, BS 908-927 AND BS 927-946. CUT OUT DAMAGED AREAS AND INSTALLED REPAIR TO ENCOMPASS BOTH AREAS IAW SRM 53-00-55, REPAIR 4.

Part: ANGLE — DAMAGED (BS 676) · airframe 30,566 hrs · 24,934 cycles

UPPER ANGLE FOUND TO BE DAMAGED INSIDE OF CENTER TANK, FWD OF ACCESS PANEL 141AL CUTOUT BS 676, LBL 22. REPLACED UPPER ANGLE IAW SRM 51-41-05 AND DWG 9919346, REV. W.

Part: FLOOR SUPPORT — BROKEN (BS 150) · airframe 30,566 hrs · 24,934 cycles

FLIGHT COMPARTMENT FLOOR SUPPORT ANGLE IS BROKEN AT APPROXIMATELY BS 150, RBL 52. REPLACED FLIGHT COMPARTMENT FLOOR SUPPORT ANGLE APPROXIMATELY RBL 52, STA 150 IAW SRM 51-41-02 AND DWG 9936533, REV CM.

Part: FLOOR SUPPORT — CRACKED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL 222AFF LOWER HAT CHANNEL CRACKED. REPLACED FLOOR PANEL 222AFF LOWER HAT CHANNEL IN MAIN CABIN IAW SRM 51-20-05, DWG 9952521, REV BB, AND PROCESS STANDARD 1.07-100, REV NEW.

Part: SEAT TRACK — CORRODED (BS 200-265) · corrosion level 3 · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN SEAT TRACK BETWEEN BS 200-265, RBL 24 CORRODED. FOUND TO BE OUT OF LIMITS DUE TO 100 PERCENT MATERIAL LOSS IAW SRM 53-20-52, ALLOWABLE DAMAGE 1 AND DWG S00483, REV A. REPLACED SEAT TRACK SECTION IAW SRM 51-41-01.

Part: FORMER — CRACKED (BS 969) · airframe 30,566 hrs · 24,934 cycles

LEFT KEELBEAM BARREL BS 696-OTBD END OF FORMER CRACKED. DISPLACED BARREL WEB LT KEELBEAM AT BS 696 IAW SRM 51-41-02 AND SRM 51-41-05 TO FOM. REMOVED FORMER IAW SRM 51-41-02 AND SRM 51-41-05. LOCATED, DRILLED, DEBURRED NEW FORMER IAW SRM 51-40-08 AND DWG 9923453, REV A. ALODINED AND PRIMED HOLES IAW SRM 51-10-04. INSTALLED FORMER AT BS 969 LT KEELBEAM AREA IAW SRM 51-41-02 AND SRM 51-41-05 AND DWG 9923453, REV A AND REINSTALLED DISPLACED WEB IAW SRM 51-41-02 AND 51-41-05.

Part: WEB — CRACKED (BS 696) · airframe 30,566 hrs · 24,934 cycles

RT SIDE KEELBEAM BARREL BS 696 OTBD END OF FORMER CRACKED. DISPLACED BARREL WEB FOR FOM , R & R RT SIDE KEELBEAM BARREL FORMER, BS 696 IAW SRM 51-41-02, 51-40-05 AND DWG 9923453, REV A , AB, C REINSTALLED IAW SRM 51-41-02 AND 51-41-05.

Part: FLOOR PANEL — PUNCTURED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL NR 222ZF HAS A PUNCTURE APPROXIMATELY BS 730, RBL 46. CUTOUT DAMAGED AREA ON MAIN CABIN FLOOR PANEL NR 222ZF, DIM 1.8" X 1.2", FABRICATED REPAIR PARTS, AND INSTALLED REPAIR PARTS, DOUBLER DIM. 4" X 5" IAW SRM 53-20-50, REPAIR 2.

Part: FORMER — CRACKED (BS 679) · airframe 30,566 hrs · 24,934 cycles

RIGHT SIDE KEEL BEAM BARREL BS 679, OTBD END OF FORMER CRACKED. REPLACED RT KEEL BEAM BARREL BS 679 FORMER IAW SRM 51-41-02 AND DWG 9923453, REV A AND REV C. ACCOMPLISHED A REPAIR TO FORMER TO ACCOMMODATE FLANGE SHORTNESS ISSUE IAW ER/A'S 536322-14, REV 0 AND REV 1, AND ER/A 536322-14, REV ORIGINAL CRACK DIM. 1.750" ASSOCIATED ER/A 14-536322 ADDED FOR AC 9588.

Part: FORMER — CRACKED (BS 679) · airframe 30,566 hrs · 24,934 cycles

LEFT KEEL BEAM BARREL BS 679 OTBD END OF FORMER CRACKED. REPLACED FORMER AS LT KEEL BEAM BARREL BS 679 IAW SRM 51-41-02 AND DWG 9923453, REV C AND REV A. ACCOMPLISHED A REPAIR TO FORMER TO ACCOMMODATE FLANGE SHORTNESS ISSUE IAW ER/A 536323-14, REV 0 AND REV 1, AND DELTA ER/A 536323-14, REV ORIGINAL. NO FURTHER MAINTENANCE REQUIRED DIM OF CRACK 1.5" ASSOCIATED ER/A 14-536323 ADDED FOR AC 9588.

Part: SUPPORT ANGLE — CORRODED (BS 813) · corrosion level 2 · airframe 30,566 hrs · 24,934 cycles

WING TO BS 813, LONGERON 30 CLIP SUPPORT CORRODED. CORROSION DAMAGE ON WING TO BODY CLIP BS 813, BL 0 FOUND TO BE OUT OF LIMITS, ORIG THICKNESS .156", MATERIAL LOSS .056", MAT REMAINING .100", DIM. 1" X 2" IAW SRM 53-00-00 AND DWG S2914624, REV A. REPLACED CLIP IAW DWG 5971098, REV E AND SRM 51-41-05.

Part: SUPPORT FRAME — CORRODED (BS 851) · corrosion level 2 · airframe 30,566 hrs · 24,934 cycles

RT WING TO BODY FAIRING SUPPORT FRAME BS 851 HAS CORROSION UNDER NUT CLIPS. CORROSION DAMAGE ON RT WING TO BODY FAIRING SUPPORT FRAME BS 851 FOUND OUT OF LIMITS, ORIG THICKNESS .050", MATERIAL LOSS .036", MATERIAL REMAINING .014" DIM 12" X 1" IAW SRM 53-00-00 AND 53-20-71. REPLACED FRAME IAW SRM 51-41-02.

Part: SEAT TRACK — DAMAGED (BS 899-1022) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN SEAT TRACK HAS SCRATCHES AND GOUGES BETWEEN BS 899- BS 1022, RBL 24. SEAT TRACK SECTION BS 899-1022, RBL 24 FOUND TO BE OUT OF LIMITS DUE TO SCALLOP DAMAGE, ORIGINAL THICKNESS .460", MATERAL LOSS .060", MATERIAL REMAINING .400" IAW SRM 53-20-53 AND DWG S00483, REV A. REPLACED SEAT TRACK SECTION IAW SRM 51-41-01.

Part: CAP — CRACKED (LT ELEVATOR) · airframe 30,566 hrs · 24,934 cycles

LEFT ELEVATOR OTBD END, T/E END CAP CRACKED. REPLACED LT ELEVATOR OTBD END T/E END CAP IAW SRM 51-41-02 AND DWG 5910412, REV DS CRACK DIM .750".

Part: FLOOR PANEL — CRACKED (COCKPIT) · airframe 30,566 hrs · 24,934 cycles

COCKPIT FLOOR PANEL 211AKF CRACKED. CUT OUT DAMAGED AREA OF COCKPIT FLOOR PANEL 211AKF DIM 2.5" X 1.5" AND INSTALLED A REPAIR IAW SRM 53-10-50 AND 53-10-50, REPAIR 1. DOUBLER DIM. 3.6" X 2.0" CRACK DIM. 1.0".

Part: SKIN — DELAMINATED (RUDDER) · airframe 30,566 hrs · 24,934 cycles

RUDDER UPPER AFT END DELAMINATED. REPAIRED RUDDER UPPER AFT END DIM 4" X 4" IAW SRM 55-00-01, REPAIR 2.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL 221AF IS DELAMINATED. MAIN CABIN FLOOR PANEL 221AF FOUND TO BE 40 PERCENT DELAMINATED AND OUT OF LIMITS IAW SRM 53-20-50 ALLOWABLE DAMAGE 1. FABRICATED NEW FLOOR PANEL DIM 36" X 11" IAW SRM 53-20-50, REPAIR 3 AND DWG 9936544, REV G.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL 222ACF IS DELAMINATED. MAIN CABIN FLOOR PANEL 222ACF FOUND TO BE 50 PERCENT DELAMINATED AND OUT OF LIMITS IAW SRM 53-20-50 ALLOWABLE DAMAGE 1. FABRICATED NEW FLOOR PANEL DIM 21" X 41" IAW SRM 53-20-50, REPAIR 3 AND DWG 9936640, REV D.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL NR 211ARF IS DELAMINATED. MAIN CABIN FLOOR PANEL NR 211ARF FOUND TO BE 50 PERCENT DELAMINATED AND OUT OF LIMITS IAW SRM 53-20-50 ALLOWABLE DAMAGE 1. FABRICATED NEW FLOOR PANEL DIM. 15" X 9" IAW SRM 53-20-50, REPAIR 3 AND DWG 9936537, REV AG.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL 222AAF IS DELAMINATED. MAIN CABIN FLOOR PANEL 222AAF FOUND TO BE 50 PERCENT DELAMINATED AND OUT OF LIMITS IAW SRM 53-20-50 ALLOWABLE DAMAGE 1. FABRICATED NEW FLOOR PANEL DIM. 21" X 22" IAW SRM 53-20-50, REPAIR 3 AND DWG NR 9936640, REV D.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL 22GF IS DELAMINATED. MAIN CABIN FLOOR PANEL 222GF FOUND TO BE 50 PERCENT DELAMINATED AND OUT OF LIMITS IAW SRM 53-20-50 ALLOWABLE DAMAGE 1. FABRICATED NEW FLOOR PANEL DIM. 21" X 19" IAW SRM 53-20-50 REPAIR 3 AND DWG 9936688, REV H.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL 221EF IS DELAMINATED. MAIN CABIN FLOOR PANEL FOUND TO BE 50 PERCENT DELAMINATED AND OUT OF LIMITS IAW SRM 53-20-50 ALLOWABLE DAMAGE 1. FABRICATED NEW FLOOR PANEL DIM. 40" X 9" IAW SRM 53-20-50, REPAIR 3 AND DWG 9936549, REV K.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL 211AQF IS DELAMINATED. MAIN CABIN FLOOR PANEL 211AQF FOUND TO BE 30 PERCENT DELAMINATED AND OUT OF LIMITS IAW SRM 53-20-50 ALLOWABLE DAMAGE 1. FABRICATED NEW FLOOR PANEL DIM. 11" X 9" IAW SRM 53-20-50. REPAIR 3 AND DWG 9936537, REV AG.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL NR 222FF IS DELAMINATED. MAIN CABIN FLOOR PANEL 222FF FOUND TO BE 60 PERCENT DELAMINATED AND OUT OF LIMITS IAW SRM 53-20-50 ALLOWABLE DAMAGE 1. FABRICATED NEW FLOOR PANEL DIM 21" X 38" IAW SRM 53-20-50, REPAIR 3 AND DWG NR 9936583 REV E.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL NR 222ABF IS DELAMINATED. MAIN CABIN FLOOR PANEL FOUND TO BE 40 PERCENT DELAMINATED AND OUT OF LIMITS IAW SRM 53-20-50 ALLOWABLE DAMAGE 1. FABRICATED NEW FLOOR PANEL DIM. 21" X 22" IAW SRM 53-20-50, REPAIR 3 AND DWG 9936640, REV D.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL 222DF IS DELAMINATED. MAIN CABIN FLOOR PANEL FOUND TO BE 30 PERCENT DELAMINATED AND OUT OF LIMITS IAW SRM 53-20-50 ALLOWABLE DAMAGE 1. FABRICATED NEW FLOOR PANEL DIM 21" X 19" IAW SRM 53-20-50, REPAIR 3 AND DWG 9936688, REV H.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL 222AEF IS DELAMINATED. MAIN CABIN FLOOR PANEL 222AEF FOUND TO BE 40 PERCENT DELAMINATED AND OUT OF LIMITS IAW SRM 53-20-50 ALLOWABLE DAMAGE 1. FABRICATED NEW FLOOR PANEL DIM. 21" X 41" IAW SRM 53-20-50, REPAIR 3 AND DWG 9936640, REV. D.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL 211ANF IS DELAMINATED. MAIN CABIN FLOOR PANEL FOUND TO BE 60 PERCENT DELAMINATED AND OUT OF LIMITS IAW SRM 53-20-50 ALLOWABLE DAMAGE 1. FABRICATED NEW FLOOR PANEL DIM. 22" X 28" IAW SRM 53-20-50, REPAIR 3 AND DWG 9936651, REV U.

Part: FLOOR SUPPORT — CORRODED (BS 149-200) · corrosion level 3 · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN BETWEEN BS 149-200, LBL 8 FLOOR SUPPORT CORRODED. REMOVED CORROSION FROM MAIN CABIN FLOOR SUPPORT BS 149-200, LBL 8, WITH 100 PERCENT MATERIAL LOSS ORIGINAL MATERIAL .125". R & R WITH NEW FLOOR SUPPORT IAW SRM 51-41-05, 51-41-02, AND DWG 9936534, REV BW.

Part: FLOOR SUPPORT — CORRODED · corrosion level 3 · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR SUPPORT CORRODED, BS 145, RBL 44. CORROSION DAMAGE ON FLOOR SUPPORT IN THE MAIN CABIN BS 145, RBL 44 FOUND TO BE OUT OF LIMITS DUE TO 100 PERCENT MATERIAL LOSS, ORIGINAL THICKNESS .070". DIM.1" X 3" IAW SRM 53-00-00 AND DWG S2929169, REV. B. REPLACED FLOOR SUPPORT IAW DWG 9936533, REV CM.

Part: SEAT TRACK — CORRODED (BS 589-899) · corrosion level 2 · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN SEAT TRACK CORRODED BETWEEN BS 589-899, RBL 54. THE SEAT TRACK WAS FOUND OUT LIMITS DUE TO SCALLOP DAMAGE. REPLACED THE SEAT TRACK IAW SRM 51-41-01 AND AMM 53-22-01.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL 211 ATF IS DELAMINATED. MAIN CABIN FLOOR PANEL 211ATF FOUND TO BE 50 PERCENT DELAMINATED AND TO BE OUT OF LIMITS IAW SRM 53-20-50 ALLOWABLE DAMAGE 1. FABRICATED NEW FLOOR PANEL DIM 15" X 11" IAW SRM 53-20-50, REPAIR 3 AND DWG 9936539, REV. AB.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL 221CF IS DELAMINATED. MAIN CABIN FLOOR PANEL 221CF FOUND TO BE 50 PERCENT DELAMINATED AND OUT OF LIMITS IAW SRM 53-20-50 ALLOWABLE DAMAGE 1. FABRICATED NEW FLOOR PANEL DIM. 40" X 12" IAW SRM 53-20-50, REPAIR 3 AND DWG 9936546, REV C.

Part: FLOOR PANEL — DAMAGED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL 221KF IS DELAMINATED. MAIN CABIN FLOOR PANEL 221KF FOUND TO BE 50 PERCENT DELAMINATED AND OUT OF LIMITS IAW SRM 53-20-50 ALLOWABLE DAMAGE 1. FABRICATED NEW FLOOR PANEL DIM. 56" X 36" IAW SRM 53-20-50, REPAIR 3 AND DG 9936552, REV K.

Part: CUSP WEB — CRACKED (BS 218) · airframe 30,566 hrs · 24,934 cycles

RT CUSP WEB HAS 2 EA CRACKS AT BS 218, RBL 45 AND BS 229, RBL 46 IN WORK REPAIRING AREA. CUT OUT DAMAGED AREAS ON RT CUSP WEB BETWEEN BS 218 TO 229 RBL 45-46 DIM. 12" X 1.5" IAW SRM 53-00-55, REPAIR 4. FABRICATED REPAIR PARTS: DOUBLER DIM .032" X 18" X 4", FILLER DIM. .020" X1.5" X 3", AND RING DOUBLER DIM. .100" X 5"X 2.5" AND INSTALLED REPAIR PARTS IAW SRM 53-00-55 REPAIR 4 DIM OF CRACKS: BS 218, DIM .750" AND BS 229 DIM .500". NO FURTHER MAINTENANCE REQUIRED.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL NR 221JF IS DELAMINATED. MAIN CABIN FLOOR PANEL 221JF FOUND TO BE 30PERCENT DELAMINATED AND OUT OF LIMITS IAW SRM 53-20-50 ALLOWABLE DAMAGE 1. FABRICATED NEW FLOOR PANEL IAW SRM 53-20-50, REPAIR 3 AND DWG 9936551, REV AN.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL NR 221DF IS DELAMINATED. MAIN CABIN FLOOR PANEL NR 221DF FOUND TO BE 40 PERCENT DELAMINATED AND OUT OF LIMITS IAW SRM 53-20-50 ALLOWABLE DAMAGE 1. FABRICATED NEW FLOOR PANEL DIM 36" X 20" IAW SRM 53-20-50, REPAIR 3 AND DWG NR 9936547, REV W.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL NR 221BF IS DELAMINATED. MAIN CABIN FLOOR PANEL NR 221BF FOUND TO BE 30 PERCENT DELAMINATED AND OUT OF LIMITS IAW SRM 53-20-50 ALLOWABLE DAMAGE 1. FABRICATED NEW FLOOR PANEL DIM. 40" X 36" IAW SRM 53-20-50, REPAIR 3 AND DWG 9936545, REV M.

Part: FLOOR PANEL — DAMAGED (COCKPIT) · airframe 30,566 hrs · 24,934 cycles

FLIGHT COMPARTMENT FLOOR PANEL 211ALF IS DAMAGED. FLIGHTS COMPARTMENT FLOOR PANEL 211ALF FOUND TO BE 40 PERCENT DELAMINATED AND OUT OF LIMITS IAW SRM 53-20-50 ALLOWABLE DAMAGE 1. FABRICATED NEW FLOOR PANEL DIM. 40" X 29" IAW SRM 53-20-50, REPAIR 3 AND DWG 9936537, REV AG.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN FLOOR PANEL NR 211 ASF IS DELAMINATED. MAIN CABIN FLOOR PANEL NR 211ASF FOUND TO BE 30 PERCENT DELAMINATED AND OUT OF LIMITS IAW SRM 53-20-50 ALLOWABLE DAMAGE 1. FABRICATED NEW FLOOR PANEL DIM 15" X 11" IAW SRM 53-20-50, REPAIR 3 AND DWG 9936539, REV AB.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 32,222 hrs · 26,222 cycles

MAIN CABIN STA 237 BL0 FLOOR SUPPORT CORRODED. REMOVED CORROSION ON MAIN CABIN STA 237 BL0 FLOOR SUPPORT FOUND WITH 100% MATERIAL LOSS, ORIGINAL THICKNESS .070". REPLACED FLOOR SUPPORT PER SRM 51-41-02, 51-41-05 AND DWG 5940663 REV N.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 32,222 hrs · 26,222 cycles

MAIN CABIN STA 168 RBL 54 FLOOR SUPPORT CORRODED. CORROSION DAMAGE ON MAIN CABIN FLOOR SUPPORT (GIRT BAR SUB FLOOR FITTING) STA 168 RBL 54 FOUND OUT OF LIMITS DUE TO 100% MAT LOSS, ORIG THICKNESS .105" IAW SRM 53-00-00 AND DRAWING 3936190 REV BW. REPLACED SUPPORT IAW DRAWING 9936534 REV BW AND 51-41-01.

Part: MEMBRANE — PUNCTURED (BS 168) · airframe 30,566 hrs · 24,934 cycles

MAIN CABIN BS 168, LBL 51 MEMBRANE HAS A PUNCTURE HOLE. MAIN CABIN BS 168, LBL 51 MEMBRANE, CUT OUT DAMAGE AREA DIM: .650" X .450", FABRICATED REPAIR DOUBLER, ALODINED + PRIMED, TOP COATED, AND INSTALLED REPAIR, ALL IAW SRM 51-70-10, SRM 53-10-51, SRM 51-40-08, SRM 51-10-04, AMM 51-10-00. ADDED MATERIAL DATA. WEB MEMBRANE IS .020", DOUBLER THICKNESS IS .032.

Part: STIFFENER — CRACKED · airframe 30,566 hrs · 24,934 cycles

AFT BULKHEAD DOOR JAMB STIFFENER CRACKED, NDT VERIFIED, LT SIDE APPROXIMATELY 18" ABOVE FLOOR LINE. REMOVED AFT BULKHEAD LT SIDE DOOR JAMB STIFFENER, FITTING IAW SRM 51-41-05, SRM 51-41-02. LOCATED DRILLED AND DEBURRED STIFFENER, FITTING IAW SRM 51-40-08 + DWG 5917579, REV EE & DZ . TOPCOATED NEW PART FITTING IAW AMM 51-10-00 AND INSTALLED STIFFENER, FITTING IAW SRM 51-41-05 AND SRM 51-41-02 AND DWG 5917579, REV EE + DZ.

Part: CUSP WEB — CRACKED (BS 655) · airframe 30,566 hrs · 24,934 cycles

CUSP WEB AT BS 655 LT SIDE HAS A CRACK. PART ON RACK. CUT OUT DAMAGED SECTION SECTION CRACK AT CUSP WEB AT BS 655 LT, DIM 1.75" X 1", FABRICATED NEW DOUBLER DIM 5.5" X 7" FROM 7075-T6 .032", AND FABRICATED NEW FILLER DIM. 1.75" X1" FROM 7075-T6 .020" AND INSTALLED REPAIR PARTS IAW SRM 53-00-55, REPAIR 4.

Part: CUSP WEB — CRACKED (BS 696-702) · airframe 30,566 hrs · 24,934 cycles

LT CUSP WEB HAS CRACKS BETWEEN BS 696 TO 702. PART ON RACK. CUT OUT DAMAGED AREA AT LT CUSP WEB BS. 696 TO 702 DIM 31", FABRICATED NEW CUSP WEB FROM 7075-T6 .020" DIM 31" X15", AND REPAIR SPLICE 7075-T6 .032" SIM. 15" X 3.75", AND INSTALLED REPAIR PARTS IAW SRM 53-00-55, REPAIR 4.

Part: DOOR FRAME — CRACKED (BS 200) · airframe 30,566 hrs · 24,934 cycles

L1 DOOR SURROUND, AFT SIDE WEB CRACKED AT FASTENER BS 200L-STR 15. L-1 DOOR AFT SIDE WEB CRACK, CUT OUT CRACKED AREA DIM 2" X 1", FABRICATED REPAIR DOUBLER RT FILLER DOUBLER DIM 3" X 4", FILLER 2" X 1" AND INSTALLED REPAIR ALL IAW SRM 53-10-15, REPAIR 1.

Part: SUPPORT FITTING — CRACKED (BS 737) · airframe 30,566 hrs · 24,934 cycles

SEAT TRACK SUPPORT FITTING FOUND CRACKED AT BS 737, LBL 43, BELOW WL 200, STREAMER ATTACHED. REPLACED CENTER WING SEAT TRACK SUPPORT FITTING AT BS 737, LBL 43 IAW SRM 51-41-05 AND DWG 5940863, REV R, 9923417, REV B.

Part: CUSP WEB — CRACKED (BS 655-674) · airframe 30,566 hrs · 24,934 cycles

RT CUSP WEB CRACKED 2 EA PLACES BETWEEN BS 655 AND 674. PART ON RACK. CUT OUT DAMAGED CUSP WEB SECTION FROM BS 655 TO 691, RT SIDE DIM 36" X 15" IAW SRM 53-00-55, REPAIR 4. FABRICATED NEW CUSP WEB, SECTION DIMENSIONS 36" X 15" AND A SPLICE DOUBLER DIMENSION 3.30" X 15" AND INSTALLED REPAIR PARTS IAW SRM 53-00-55, REPAIR 4 AND 53-20-51. ASSOCIATED AA 5310-01436 ADDED FOR AC 9588.