N963DN

Part: PIN — UNSECURE (L1 DOOR SLIDE) · airframe 55,221 hrs · 32,068 cycles

FOUND L1 ENTRY DOOR SLIDE PACK HAD BOTH PINS FELL OUT OF SLIDE EYELETS. REMOVED AND REPLACED SLIDE PACK PER WC 2561-4641. SYS CKS OK. ACFT OK FOR SERVICE.

Part: UNKNOWN — ODOR (CABIN) · airframe 54,600 hrs · 31,670 cycles

STRONG SMELL OF FUEL IN THE CABIN AFTER LANDING.THE SMELL IS STRONGER IN THE AFT CABIN, BUT IS STILL PRESENT UP TO THE FLAT DECK. INSPECTED A/C, APU, ENGINES, FUEL DRAINS. NO LEAKS FOUND. INOP APU. PERFORMED PNEU DUCT BURN OUT W/ENGINES PER AMM. 21-53-00 PG 201. NO FUEL NOTED AFTER BURN. REPLACED COALESCER BAGS. (LP#5821592)

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 54,600 hrs · 31,670 cycles

FOUND 2" CRACK AT STRINGER 1307 JUST LEFT OF CENTER LINE. FOUND CRACK TO BE IN FLOOR PANEL TO FORMER ATTACH ANGLE SUBSTRUCTURE. FABRICATED & INSTALLED REPAIR ANGLE PER SRM 51-70-01 FIGURE 1 PAGE 2 AND 4. SECURED PANEL 181MF PER AMM 25-50. (LP# 5821591)

Part: CHARGER — INOPERATIVE (EMERGENCY LIGHTS) · airframe 54,351 hrs · 31,499 cycles

DURING SVC, FOUND EMERGENCY LIGHT AT LEFT AFT OVERWING EXIT DOOR OUT. R/R BATTERY CHARGER PER MD90 AMM 33-51, OPS CHECK GOOD.

Part: TAIL CONE — LACK OF LUBE · airframe 52,938 hrs · 30,530 cycles

DURING OPS CHECK OF TAIL CONE DROP, AFT ENTRY DOOR DID NOT RELEASE TAIL CONE. LUBED TAIL CONE PER MD-90 AM 53-52. OPS WILL BE DONE ON AMDS 5352-7116. ALL RII COMPLIED WITH ON AMDS 5352-7116 QC2097. LUBED DOOR RELEASE CABLE PER PSM 900-8 #5. (LP# 5009704)

Part: SKIN — DEBONDED (VERTICAL STAB) · airframe 52,938 hrs · 30,530 cycles

FOUND VERTICAL STABILIZER PANEL 370TL LEADING EDGE DISBONDING. REMOVED PANEL 370TL AND ROUTED TO COMPOSITE SHOP. REMOVED DELAMINATED MESH AND DAMAGED PAINT IN PERPETRATION FOR REPAIR, MD90 SRM 55-41-01. REPAIRED COPPER LIGHTNING PROTECTION IAW MD90 SRM 55-41-01 PRIMED AND PAINTED. INSTALLED PANEL 370TL, JOB COMPLETE , OK FOR SERVICE. (LP# 0831154)

Part: CABLE — BINDING (VENTRAL STAIR) · airframe 51,919 hrs · 29,912 cycles

AFT VENTRAL STAIRS INOPERATIVE WILL NOT OPEN. DURING CHECKS, FOUND THE CONTROL CABLE ASSY FROM THE HANDLE BINDING IN THE OPEN DIRECTION. R & R BRACKET ASSEMBLY. REPLACED AFT VENTRAL STAIRS TELEFLEX CABLE.

Part: BRACKET — CRACKED (THRUST REVERSER) · airframe 51,255 hrs · 29,524 cycles

DURING INSPECTION, FOUND A CRACKED BRACKET ON FWD BULKHEAD AT THE RT UPPER ENGINE THRUST REVERSER. THE BRACKET WAS REPLACED.

Part: RIB — CRACKED (LT WING) · airframe 51,255 hrs · 29,524 cycles

CRACK ON RIB OF FIXED LEADING EDGE INTERIOR SURFACE SATA XOS 530 APROX LT WING. RIB WAS REPLACED PER SRM VOL II 51-30-02 AND 51-30-05, DWG 9919331-39 REV N.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

CORROSION ON INTERCOSTAL STA Y= 163 PROTECTION LONG 28L AT INNER FUSELAGE STRUCTURE E&E COMPARTMENT AREA. REPLACED PER SRM VOL II 51-30-02 AND 51-30-05, DWG 9911549 REV D.

Part: WEB — CRACKED (FUSELAGE) · airframe 51,255 hrs · 29,524 cycles

CRACK ON WEB AT STA CANT Y=1542 AND 1HRS POSITION VENT BOX LOUVERS AREA AT AFT ACCESSORY COMPARTMENT. WEB WAS REMOVED PER VOL II SRM 51-30-02 DAMAGE WAS REMOVED PER SRM 53-00-01 PAR 8 FIG 6. REPAIR PARTS WERE FABRICATED PER SRM VOL I 53-00-01 PAR 8 FIG 6. REPAIR PARTS WERE INSTALLED PER SRM VOL11 51-30-02 WEB WAS INSTALLED PER VOL II SRM 51-30-05 LENGTH OF CRACKS WERE 0.250" AND 0.125".

Part: BEAM — CRACKED (NLG WW) · airframe 51,255 hrs · 29,524 cycles

CRACK RT/LT WHEEL WELL DOOR JAMB INTERNAL SKIN STA Y= 47 AT NLG. BEAM WAS REPAIRED PER SRM VOL I 53-90-01 PAR 8. (LENGHT CRACK WAS 0.500"), FOR BEAM RT WAS ISSUED A NRC SERIAL NUMBER 00982 TO SEPARATE TYPE REPAIR, REPAIRED UNDER LOG 0463002.

Part: SKIN — CRACKED (NLG WW) · airframe 51,255 hrs · 29,524 cycles

CRACK RT WHEEL WELL DOOR JAMB INTERNAL SKIN STA Y=47 AT NLG. REPAIRED PER REV ETI-90-18-013 REV 4 AND ER/A 566722-14 REV ORIGINAL.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 51,255 hrs · 29,524 cycles

CRACK ON INBD/OUTBD WEB SUPPORTS (2EAS) STA CANT 1542 AND 1HRS POSITION VENT BOX LOUVERS AREA AT AFT ACCESSORY COMPARTMENT. ANGLES WERE REPLACE PER VOL II SRM 51-30-05 AND DWG 9923630-5 REV L AND 9911839-158 REV DP.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 51,255 hrs · 29,524 cycles

CRACK ON AFT ACCESORY COMPARTMENT VENT BOX LOUVER UPPER ANGLE STA CANT 1520 AND 1HRS POSITION. ANGLE WAS REPLACE PER VOL II SRM 51-30-05 AND 51-30-02.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

CORROSION ON FRAME OF STA Y 1362 BTW LONGS 29R-26L AT AFT CARGO COMPARTMENT. CORROSION LEVEL 2 WAS REPAIRED PER SRM VOL I 53-10-02 FIG 2.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 51,255 hrs · 29,524 cycles

CRACK ON WEB ANGLE STA CANT 1542 AT 11 HRS POSITION AFT ACCESORY COMPARTMENT VENT BOX LOUVERS AREA. ANGLE WAS REPLACE PER VOL II SRM 51-30-05, SRM 51-30-01 AND 51-30-02.

Part: SKIN — CRACKED (FUSELAGE) · airframe 51,255 hrs · 29,524 cycles

CRACK ON SKIN CUTOUT ON LT AFT NLG DOOR AFT HINGE AT EXTERNAL FUSELAGE. SKIN CUTOUT ON LT AFT NLG DOOR AFT HINGE AT EXTERNAL WAS REPAIRED PER SRM VOL I 53-30-01 PAR 14, AND VOL II 51-30-02 AND 51-30-05.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 51,255 hrs · 29,524 cycles

CRACKED LONG 20 LT STA Y= 1050 AT LT MLG WHEEL WELL AREA. LONG 20 LT STA Y= 1050 WAS REPAIRED (CRACK 1") PER SRM VOL I 53-10-01 FIG 9.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

CORROSION ON SEVERAL CLIPS FROM STA Y 1212-1269 LONG 19R AT AFT CARGO COMPARTMENT DOOR JAMB. CLIPS WERE REPLACED PER SRM VOL II 51-10-05.

Part: LONGERON — CORRODED (FUSELAGE) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

CORROSION LEVEL 2. CORROSION ON LONG 30 STA Y=218 AT INNER STRUCTURE E/E COMPARTMENT. LONGERON 30 BTW STA Y=160-229 WAS REPLACED PER SRM VOL II 51-30-02 AND 51-30-05.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

CORROSION ON CLIP SUPPORT OF STA Y=1212 AT AFT CARGO COMPARTMENT. CLIP WAS REPLACED PER SRM VOL II 51-30-05 DWG 5936660 REV BZ.

Part: FITTING — CORRODED (FUSELAGE) · airframe 51,255 hrs · 29,524 cycles

CRACKED FITTING SUPPORT STA Y=932, X=0 AT WING CENTER SECTION KEEL BEAM AREA. FITTING WAS REPLACED PER SRM VOL II 51-30-05.

Part: DOUBLER — CRACKED (MLG DOOR) · airframe 51,255 hrs · 29,524 cycles

CRACKED REPAIR DOUBLER ON LOWER AFT CORNER INBD SECTION AT LH MLG INBD DOOR. THE REPAIR DOUBLER WAS REPLACED IAW SRM 52-80-02, FIG 8, SRM 51-30-01, AND 51-30-02.

Part: ANGLE — CRACKED (BS 1046) · airframe 51,255 hrs · 29,524 cycles

DURING INSPECTION. FOUND A CRACKED ANGLE BS 1046, X=5 AT THE LT MLG WHEEL WELL KEEL BEAM AREA. REPAIRED IAW SRM 53-00-01, FIG 4, VOL I.

Part: ANGLE — CRACKED (BS 1364) · airframe 51,255 hrs · 29,524 cycles

DURING INSPECTION. A CRACKED ANGLE BS 1364, LONGERON 16R. REPLACED THE ANGLE IAW SRM 51-30-05.

Part: LONGERON — CRACKED (BS 1364) · airframe 51,255 hrs · 29,524 cycles

DURING INSPECTION. A CRACKED LONGERON 16L, BS 1364. THE AREA WAS REPAIRED IAW SRM 53-10-01, FIG 7.

Part: PAN — CRACKED (L1 DOOR) · airframe 51,255 hrs · 29,524 cycles

DURING INSPECTION, FOUND A CRACK ON THE UPPER AFT PAN BETWEEN BS 195 & 200 AT THE L1 DOOR. THE PAN WAS REPAIRED IAW ETI-90-18-007, REV. 3 AND ERA 566290-14, REV ORIGINAL.

Part: STRUCTURE — DAMAGED (L2 DOOR) · airframe 51,255 hrs · 29,524 cycles

DURING INSPECTION, FOUND AN ELONGATED SCREW HOLE ON THE AFT UPPER CORNER OF THE L2 DOOR. REPAIRED IAW ETI-90-18-005, REV 1 AND ERA 566537-14, REV ORIGINAL.

Part: DOOR FRAME — CRACKED (RT MLG) · airframe 51,255 hrs · 29,524 cycles

DURING INSPECTION, A CRACK WAS FOUND BEYOND A STOP DRILL ON THE AFT MLG DOOR FRAME AT THE RT MLG WW . REPAIRED IAW SRM VOL II 51-30-02 AND 51-30-05.

Part: WEB — CORRODED (BS 884) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

DURING INSPECTION, CORROSION WAS FOUND ON THE WEB AT BS 884, BETWEEN LONGERONS 28L - 28R. THE WEB WAS REPAIRED IAW ER/A 566426-14, REV ORIG, AND ETI -90-18-003, REV 2.

Part: ANGLE — CRACKED (MLG DOOR FRAME) · airframe 51,255 hrs · 29,524 cycles

DURING INSPECTION, FOUND A CRACKED ANGLE ON THE LT MLG DOOR FWD FRAME. THE ANGLE WAS REPLACED IAW SRM 51-30-02, AND 51-30-05.

Part: ANGLE — CRACKED · airframe 51,255 hrs · 29,524 cycles

CRACKED ANGLE IN FWD OUTBD CHANNEL ON FWD RT. THE ANGLE WAS REPLACED IAW SRM 51-30-02, AND 51-30-05.

Part: ANGLE — CRACKED (NLG WW) · airframe 51,255 hrs · 29,524 cycles

CRACKED ANGLE, BS 110, IN THE NLG W/W. THE ANGLE WAS REPLACED IAW SRM 51-30-08.

Part: DOUBLER — CORRODED (BS 1395) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

DURING INSPECTION, FOUND CORROSION ON THE INNER PRODUCTION DOUBLER, BS 1395 BETWEEN LONGERONS 29R - 29L IN THE AFT CARGO BAY. THE DOUBLER WAS REPLACED IAW SRM 51-30-02, AND 51-30-05.

Part: BRACKET — CRACKED (LT MLG WW) · airframe 51,255 hrs · 29,524 cycles

INITIAL INSPECTION. CRACKED HYD LINE BRACKET ON LT MLG WHEEL WELL FWD DOOR JAMB. BRACKET WAS REPLACED (CRACK 2") PER VOL II SRM 51-30-02.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 51,255 hrs · 29,524 cycles

CRACKS ON FLOOR PANELS NBRS 221GF, 211FG, 221PF, 211AJF 221NF, 223EF, 221QF, 222CG, 222TF AND FLOOR PANEL P/N 9981474-41 AT PAX CAB (CPAX ). FLOOR PANELS NBRS 221GF, 211FG, 221PF, 211AJF 221NF, 223EF, 221QF, 222CG, 222TF AND FLOOR PANEL P/N 9981474-41 WERE REPLACED FABRICATE AND IDENTIFIED PER MD-90 VOL I S.R.M. 53-20-03. (LP0450437)

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 51,255 hrs · 29,524 cycles

DELAMINATION ON FLOOR PANELS NBRS 221LF, 221BF, AND 221JF AT PAX CAB. FLOOR PANELS NBRS 221LF, 221BF, AND 221JF WERE REPLACED, FABRICATE AND IDENTIFIED PER MD-90 VOL 1 S.R.M. 53-20-03. (LP0450402)

Part: FLOOR PANEL — CORRODED (CABIN) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

CORROSION ON FLOOR PANEL 160G FROM STA Y 160-200 AND STA X -54 TO -60 AT PAX CABIN. LEVEL CORROSION 2 FLOOR PANEL 160G FROM STA Y 160-200 AND STA X -54 TO -60 WAS REPLACED PER DWG 9957828 REV AB.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 51,255 hrs · 29,524 cycles

DELAMINATION ON FLOOR PANELS NBRS 222AF, 222HG, 222LG, 222AKG, 222MF, 222RF, AND 222VF AT PAX CAB. FLOOR PANELS NBRS 222AF, 222HG, 222LG, 222AKG, 222MF, 222RF, AND 222VF WERE REPLACED FABRICATE AND IDENTIFIED PER MD-90 VOL I S.R.M. 53-20-03. (LP0450439)

Part: STIFFENER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

CORROSION ON STIFFENER OF STA Y 1395 AND LONG 30 WAS FOUND DURING REMOVAL OF INNER PRODUCTION DOUBLER OF STA Y 1395 BTW LONGS 29R-29L. STIFFENER WAS REPLACED PER VOL II SRM 51-30-05.

Part: CHANNEL — CRACKED (LT MLG WW) · airframe 51,255 hrs · 29,524 cycles

CRACK FWD INBD JAMB OF LT MLG DOOR WHEEL WELL. CHANNEL WAS REPLACED (CRACK 1") PER SRM VOL II 51-30-02 AND 51-30-05.

Part: ANGLE — CRACKED (BS 962) · airframe 51,255 hrs · 29,524 cycles

CRACKED ANGLES BETWEEN BS 962, LBL 44, RBL 44, Z=-7 LT & RT SIDE AT WING BOX AREA. THE ANGLES WERE REPLACED IAW SRM 51-30-05, AND DWG 9923417-17, REV B.

Part: SPLICE — CRACKED (LT WING) · airframe 51,255 hrs · 29,524 cycles

CRACKED SPLICE AND CLIP ANGLE ON LT WING INTERNAL FIXED LEADING EDGE STA XFS 194. SPLICE AND CLIP WERE REPLACED PER SRM VOL II 51-30-02 AND 51-30-05 AND DWG9937517 REV J.

Part: PANEL SUPPORT — CRACKED (FUSELAGE) · airframe 51,255 hrs · 29,524 cycles

CRACKED PANEL SUPPORTS (2EAS) STA Y=1473 X=-10 AND X=10 AT AFT ACCESSORY COMPARTMENT. PANEL SUPPORTS (BRACKETS 2EAS) STA Y=1473 X=-10 AND X=10 WERE REPLACED PER DWG 5937954 REV R.

Part: WEB — CORRODED (BS 131-141) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

CORROSION ON WEB BETWEEN BS 131 TO 141, RBL 30 TO 52. REPAIRED IAW. SRM 51-10-01, FIG 10.

Part: SKIN — CRACKED (THRUST REVERSER) · airframe 51,255 hrs · 29,524 cycles

CRACKED AND LOOSE FASTENERS ON AFT BIFURCATION TRACK FAIRING SKIN OUTBOARD SIDE AT RT LOWER ENGINE THRUST REVERSER C-DUCT. DAMAGE WAS REPAIRED IAW SRM 54-30-13, VOL IV.

Part: ANGLE — CRACKED (BS 883) · airframe 51,255 hrs · 29,524 cycles

CRACKED ANGLES BETWEEN BS 883, LBL 43, RBL 43, Z=-6. THE ANGLES WERE REPAIRED IAW ER/A 498192-14MA, REV A.

Part: SKIN — CRACKED (LT FAIRING) · airframe 51,255 hrs · 29,524 cycles

CRACK AFT BIFURCATION TRACK FAIRING SKIN INBOARD SIDE AT LT UPPER ENGINE THRUST REVERSER C-DUCT. CRACK WAS STOPPED DRILL PER SRM 54-30-13 PAR (5) VOL IV (ET) HFEC INSPECTION WAS ACCOMPLISHED ON AFT BIFURCATION TRACK FAIRING SKIN INBOARD SIDE AT LT UPPER ENGINE THRUST REVERSER C-DUCT. NO CRACKS WERE FOUND AFTER STOP DRILL, PER NDT SPM 06-10-01.001. DOUBLER OF REPAIR WAS FABRICATED PER SRM 54-30-13 (7) VOL IV AND INSTALLED PER SRM 54-30-13 PAR (9) VOL IV.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

CORROSION LEVEL 2. (IN REF NRC 00328) CORROSION ON RT CUSP WEB BTW STA Y=731 TO 741, X=-54 TO -60 AT PAX CABIN FLOOR STRUCTURE. CORROSION II IN REF NRC 00966 AREA WAS REPAIRED PER SRM 53-20-02 VOLUME I FIGURE 17.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 51,255 hrs · 29,524 cycles

CRACK ON STIFFENER OVER FRAME WEB STA CANT 1531 AND 11HRS POSITION AT AFT ACCESSORY COMPARTMENT. DAMAGE OVER FRAME WEB STA CANT 1531 AND 11HRS POSITION WAS REMOVED PER SRM 51-30-05 VOL II. NEW STIFFENER WAS DRILLING AND ADJUSTED PER SRM 51-10-05 VOL II. NEW STIFFENER WAS TREATED AND PAINTED PER SRM 51-10-03 PAR 14 AND 21 VOL II. NEW STIFFENER WAS INSTALLED PER SRM 51-30-05 VOL II LONG CRACK IS .300".

Part: RIB — CRACKED (LT HORIZ STAB) · airframe 51,255 hrs · 29,524 cycles

CRACK ON RIB STA LES=95.96 INTERNAL STRUCTURE AT LT HORIZONTAL STABILIZER. PERMANENT REPAIR WAS ACCOMPLISHED ON RIB STA LES=95.96 INTERNAL STRUCTURE AT LT HORIZONTAL STABILIZER PER ETI -37-18-359 REV 2. AND ER/A 566298-14 REV ORG.

Part: ANGLE — CRACKED (CARGO DOOR) · airframe 51,255 hrs · 29,524 cycles

CRACK ON UPPER ANGLES BTW INTERNAL PAN AND BEAM 5 ON STA Y=712 ALSO ON STA Y=730 AT MID CARGO DOOR. ANGLE AND WEB ON BEAM 5 STA Y=712 AND STA Y=730 AT MID CARGO DOOR WERE REPLACED PER SRM VOL II 51-30-02 AND 51-30-05.

Part: SKIN — DAMAGED (RUDDER) · airframe 51,255 hrs · 29,524 cycles

DAMAGE T, DURING WEIGHT AND BALANCE CHECK ON RUDDER, SKIN CUT OUT OF HINGES WERE DAMAGED. RUDDER OF THE VERTICAL STABILIZER WAS REPAIRED PER SRM VOL I 55-41-01 PARA 22, WEIGHT AND BALANCE CHECK WAS PERFORMED PER SRM VOL II 55-40-01.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

INITIAL INSPECTION. CORROSION ON FLOOR STRUCTURE SUPPORT BTW STA 160 TO STA 200, X=56, X=53 (2EA), X=44, X=24, AND X=14. LT SIDE. SUPPORTS WERE REPLACED PER SRM VOL II 51-30-02 AND 51-30-05.

Part: TEE FITTING — CRACKED (LT MLG WW) · airframe 51,255 hrs · 29,524 cycles

INITIAL INSPECTION. CRACKED AFT "T" JAMB ON LT MLG WHEEL WELL DOOR JAMB OUTBD SIDE. "T" WAS REPLACED (CRACK 2") PER VOL II SRM 51-30-02 AND 51-30-05.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

INITIAL INSPECTION. CORROSION ON FLOOR STRUCTURE SUPPORT BTW STA160 TO STA 200, X=-53 TO X=-44 RT SIDE. SUPPORTS WERE REPLACED PER SRM VOL II 51-30-02.

Part: TRIPLER — CORRODED (BS 1395 BULKHEAD) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

CORROSION ON REPAIR TRIPLER OF AFT P-DOME OF STA Y-1395 BTW LONGS 29LH-27RH AT AFT CARGO COMPARTMENT. FINGER DOUBLER, FILLER AND TRIPLER WERE REMPLACED PER MD90 VOL I SRM 53-10-03 FIG 1. (LP0441512)

Part: FRAME — CORRODED (BS 1395) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

CORROSION FOUND ON THE FRAME WEB AFT FACE AT BS 1395 BETWEEN LONGERONS 27R & 27L. THE FRAME WAS REPAIRED IAW SRM 51-11-01, FIG 1, VOL 1.

Part: PAN — CRACKED (CABIN) · airframe 51,255 hrs · 29,524 cycles

CRACK ON RINGPAN OF WINDOW UPPER CORNER AFT STA 1078 LT SIDE. (CRACK LONG 0.0405") AREA WAS REPAIRED PER VOL I SRM 56-20-02 FIG 3.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 51,255 hrs · 29,524 cycles

INITIAL INSPECTION : CRACKED CHANNEL ON FLOOR PANEL 222VG, 222QG, 222KG, 222FG, 221XF, 221TF, 222AG, 222AWG, 222ANG, 222YF, 223JF, 222ADF IN PAX CABIN. FLOOR GENERATION PANEL 222VG, 222QG, 222KG, 222FG, 221XF, 221TF, 222AG, 222AWG, 222ANG, 222YF, 223JF, 222ADF WERE REPAIR PER MD90 SRM VOL.I 53-20-03 PAR.8 FIG. 13 : (ET) HFEC INSPECTION WAS ACCOMPLISHED ON FLOOR PANEL 222VG, 222QG, 222KG, 222FG, 221XF, 221TF, 222AG, 222AWG, 222ANG, 222YF, 223JF, 222ADF IN PAX CABIN NO CRACKS WERE FOUND AFTER STOP DRILL (14 EAS) PER. DC-MD NDT SPM 06-10-01.001. (LP0439981)

Part: PAN — CRACKED (CABIN) · airframe 51,255 hrs · 29,524 cycles

CRACK ON RING PAN FWD UPPER CORNER STA Y= 1002 AND FWD LWR STA Y= 1136 RT. (CRACK LONG 0.400") AREA WAS REPAIRED PER VOL I SRM 56-20-02 FIG 3.

Part: PAN — CRACKED (CABIN) · airframe 51,255 hrs · 29,524 cycles

CRACK ON RINGPAN OF WINDOW UPPER CORNER AFT STA 1135 AND LOWER CORNER FWD STA 1154 LT SIDE. (CRACK LONG 0.380") AREA WAS REPAIRED PER VOL I SRM 56-20-02 FIG 3.

Part: PAN — CRACKED (CABIN) · airframe 51,255 hrs · 29,524 cycles

CRACK ON RINGPAN UPPER CORNER AFT STA 1154 AND LOWER CORNER FWD STA 1137 LT SIDE. AREA WAS REPAIRED PER VOL I SRM 56-20-02 FIG 3.

Part: PAN — CRACKED (CABIN) · airframe 51,255 hrs · 29,524 cycles

CRACK ON RINGPAN OF WINDOW UPPER CORNER AFT STA 1097 AND LOWER CORNER FWD STA 1079 LT SIDE. AREA WAS REPAIRED PER VOL I SRM 56-20-02 FIG 3.

Part: PAN — CRACKED (CABIN) · airframe 51,255 hrs · 29,524 cycles

CRACKED RINGPANS (2EA) ON LT/RT WINDOW UPPER AFT CORNER OF STA 1003. (CRACK LONG 0.400") AREA WAS REPAIRED PER VOL I SRM 56-20-02 FIG 3.

Part: PAN — CRACKED (CABIN) · airframe 51,255 hrs · 29,524 cycles

CRACK ON RING PAN AFT UPPER CORNER STA Y=1155 RT. (CRACK LONG 0.0380") AREA WAS REPAIRED PER VOL I SRM 56-20-02 FIG 3.

Part: PAN — CRACKED (CABIN) · airframe 51,255 hrs · 29,524 cycles

CRACK ON RINGPAN LOWER CORNER FWD STA 1156 RT SIDE. (CRACK LONG 0.385") AREA WAS REPAIRED PER VOL I SRM 56-20-02 FIG 3.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

CORROSION ON FLOOR STRUCTURE SUPPORT AT STA 200, BTW X=7 TO X=-7LT/RT, X=8 TO X=14 LT AND STA 196, X=14 TO X =44 LT SIDE. CORROSION 2 IN REF NRC 00643 SUPPORTS WERE REPLACED 3 E/A PER SRM 51-30-02 AND 51-30-05.

Part: PAN — CRACKED (CABIN) · airframe 51,255 hrs · 29,524 cycles

CRACK ON RINGPAN OF WINDOW UPPER CORNER AFT STA 1116 LT SIDE. (CRACK LONG 0.380") AREA WAS REPAIRED PER VOL I SRM 56-20-02 FIG 3.

Part: PAN — CRACKED (CABIN) · airframe 51,255 hrs · 29,524 cycles

CRACK ON RING PAN FWD UPPER CORNER STA Y= 522 AND AFT LWR STA Y=943 RT. (CRACK LONG 0.380") AREA WAS REPAIRED PER VOL I SRM 56-20-02 FIG 3.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 51,255 hrs · 29,524 cycles

CRACK ON LONG 12 LT STA Y=1486 AT AFT ACCESSORY COMPARTMENT. LONG 12 LT STA Y=1486 AT AFT ACCESSORY COMPARTMENT WAS REPAIRED PER VOL I SRM 53-10-01 FIG 7.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 51,255 hrs · 29,524 cycles

CRACK FLOOR STRUCTURE INTERCOSTAL BTW STA 1344 TO STA 1364, X=-0 CTR. NEW INTERCOSTAL BTW STA 1344 TO STA 1364, X=-0 WAS REPLACED PER VOL II SRM 51-30-02.

Part: SPLICE — CRACKED (LT MLG DOOR) · airframe 51,255 hrs · 29,524 cycles

LATE FINDING CRACK ON AFT LOWER INTERNAL SPLICE AT LT MLG DOOR. (CRACK LENGTH=4") AFT LOWER INTERNAL SPLICE AT LT MLG DOOR WAS REPAIRED PER CMM 32-17-05 REPAIR 2.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

CORROSION OUT OF LIMITS ON FLOOR SUPPORT STA 200, X-7 TO X-44 AT CPAX W1(RT SIDE). LEVEL CORROSION 2 FLOOR SUPPORT WAS REPLACED PER SRM VOL II 51-30-02 AND 51-30-05.

Part: WEB — CRACKED (FUSELAGE) · airframe 51,255 hrs · 29,524 cycles

CRACKED WEB STA Y=218, X= -26 AT E&E COMPARTMENT CEILING AREA. DIMENSIONS CRACKS, 1.125", .750" WEB WAS REPAIRED PER VOL I SRM 53-00-01 FIG 6 AND VOL II SRM 51-30-02.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

CORROSION ON SEAT TRACK X=-22, BTW STA 200 TO STA 237 RT SIDE. LEVEL CORROSION 2 SEAT TRACK WAS REPLACED X=-22 STA Y=200 TO Y=266 PER SRM 51-30-01 AND 51-30-05 VOLUME II.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

INITIAL INSPECTION. CORROSION ON SEAT TRACK X=-44, BTW STA 200 TO STA 256 RT SIDE. SEAT TRACK WAS REPLACED PER SRM 51-30-01 AND 51-10-05 VOLUME II.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

CORROSION ON FUEL TANK ACCESS PLATES NR 520AT, 520JB, 520DT ON LT WING. (CORROSION LEVEL 2) FUEL ACCESS PLATES NR 520DT, 520JB AND 520AT WAS REPLACED PER SRM VOL I 57-00-04 PAR 4 CONDITION II.

Part: WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

INITIAL INSPECTION. CORROSION ON WEB STA Y=195, X=-55 AT E/E. (CORROSION LEVEL 2 ) MEMBRANE WAS REPAIRED PER VOL I SRM 51-11-01.

Part: BEAM — CRACKED (L1 DOOR) · airframe 51,255 hrs · 29,524 cycles

INITIAL INSPECTION: CRACK ON BEAM 1 BTW STA Y195/200 AT FWD ENTRY DOOR L1. BEAM NR 1 BTW STA Y: 195-200 WAS REPAIRED PER SRM VOL I 52-10-02 PARAGRAPH 6, FIG 5.

Part: SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

CORROSION ON FLOOR STRUCTURE SUPPORT BTW STA160 TO STA 200, X=7 TO X=-7 LT/RT SIDE. FLOOR SUPPORT WERE REPLACED PER SRM 51-30-01 VOL II.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

OUT OF LIMITS CORROSION ON LT SEAT TRACK X=44 BTW STA Y 1277-1279 AT PASSENGER CABIN. AREA WAS REPAIRED PER VOL I SRM 53-40-01 FIG 2.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

OUT OF LIMITS CORROSION ON SEAT TRACK BTW STA Y=1260-1263 AND X=22 AT PASSENGER CABIN. CORROSION 2 AREA WAS REPAIRED PER VOL I SRM 53-40-01 FIG 2.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

OUT OF LIMITS CORROSION ON LT SEAT TRACK X=44 BTW STA Y 1262-1264 AT PASSENGER CABIN. AREA WAS REPAIRED PER VOL I SRM 53-40-01 FIG 2.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 51,255 hrs · 29,524 cycles

INITIAL INSPECTION, CRACK LT CUSP MEMBRANE ON STA Y=883 AT PASSENGER CABIN. REPAIRED PER VOL I SRM 53-20-02 FIG 6.

Part: CUSP WEB — PUNCTURED (FUSELAGE) · airframe 51,255 hrs · 29,524 cycles

INITIAL INSPECTION, PUNCTURE ON LT CUSP MEMBRANE STA Y=928 AT PASSENGER CABIN. DOUBLER WAS REMOVED ON STA Y=928 LT PER VOL II S-R-M 51-30-02 AND 51-30-01. PREVIOUS REPAIR DOUBLER WAS FABRICATED PER VOL II SRM 53-10-03, NEW DOUBLER WAS INSTALLED PER VOL II SRM 51-30-05.

Part: SHIM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 51,255 hrs · 29,524 cycles

INITIAL INSPECTION: CORROSION ON SHIMS BELOW LOWER FITTING STA Y=1231 AT AFT CARGO DOOR. SHIMS BELOW LOWER FITTING STA Y=1231 AT AFT CARGO DOOR WERE REPLACED PER SRM 51-30-02, 51-30-05, 51-30-01 VOL II.

Part: SKIN — CRACKED (VERTICAL STAB) · airframe 51,255 hrs · 29,524 cycles

CRACK ON RAM AIR SCOPE AT VERTICAL STABILIZER LEADING EDGE. CRACKS ON RAM AIR SCOPE AT VERTICAL STABILIZER LEADING EDGE, WERE REPAIRED (WELDED) PER ER/A 382101-14MA REV H.

Part: WEB — CRACKED (FUSELAGE) · airframe 51,255 hrs · 29,524 cycles

INITIAL INSPECTION. CRACKED WEB STA Y=133, X=7 AT COCKPIT FLOOR STRUCTURE. CRACK .750" AREA WAS REPAIRED PER SRM 53-00-01 PAR 8 FIG 6 VOL I.

Part: CUSP WEB — PUNCTURED (BS 1136-1140) · airframe 51,255 hrs · 29,524 cycles

PUNCTURE ON THE RT CUSP WEB BETWEEN BS 1136 AND 1140, RBL 54 AND 60. REPAIRED IAW SRM 53-00-01, PARAGRAPH 5C, (2), (B), FIG 2.

Part: WEB — CRACKED (BS 1231) · airframe 51,255 hrs · 29,524 cycles

CRACKED WEB, BS 1231. THE WEB WAS REPLACED IAW DWG 9957994, REV N, SRM 51-30-02, AND 51-30-05, VOL II.

Part: ANGLE — CRACKED (BS 1231) · airframe 51,255 hrs · 29,524 cycles

A CRACK ON THE ANGLE BETWEEN BEAM 5 AND INTERNAL PAN, BS 1231 AT AFT CARGO DOOR. THE ANGLE WAS REPLACED IAW SRM 51-30-02, 52-30-05, AND DRAWING 9957884, REV N.

Part: ACCESS PANEL — CORRODED (WINGS) · airframe 51,255 hrs · 29,524 cycles

CORROSION ON FUEL TANK ACCESS PLATES NBR 520CT AND 620CT ON LH/RH WINGS. FUEL ACCES PLATES 520CT AND 620CT WERE REPLACED DUE TO BLEND OUT REPAIR IS NOT PERMITED PER MD-90 SRM VOL I 57-00-04 PAR 4 CONDITION III . (LP0428283)

Part: HYDRAULIC LINE — LEAKING (HYDRAULIC SYS) · airframe 51,251 hrs · 29,522 cycles

RIGHT HYDRAULIC QUANTITY LOW, RAN QRH SHOWED NORMAL QUANTITY AFTER CONFIGURING, GOT DOWN TO 5 QUARTS ON LANDING. MAINTENANCE FOUND MAJOR LEAK IN RIGHT ENGINE PYLON, SMALL LEAK ON PTU RIGHT SYSTEM FEED LINE, RETORQUED SAME. FOUND STEADY LEAK DURING DRY MOTOR RIGHT ENGINE ABOVE PNEUMATIC DUCTS FROM MAJOR FEED LINE. REPLACED DAMAGED LINE. LEAK AND OPERATION CHECKS GOOD.

Part: BRAKE — CONTAMINATED (MLG) · airframe 51,058 hrs · 29,407 cycles

POST FLIGHT INSPECTION FOUND HYDRAULIC FLUID AROUND NR 1 TIRE. SMOKE VISIBLE IN BRAKE AREA. BRAKE TEMPERATURE ONLY 200 DEGREES. HYDRAULIC FLUID SMOKING. REMOVED AND REPLACED THE NR 1 BRAKE IAW MM. OPERATION AND LEAKS CHECK GOOD.

Part: ELECTRONIC UNIT — ODOR (LT ENGINE) · airframe 50,951 hrs · 29,348 cycles

DESCENDING THROUGH 600FT ON APPROACH LEFT GEN OFF AND LEFT AC PWR FAULT. MESSAGES ILLUMINATED ON OAP AFTER ABOUT 1 MINUTE WE LOST ALL AC PWR. SWITCHED EMERGENCY POWER SWITCH TO "ON" BUT GOT NO POWER RESTORED UNTIL THE APU CAME ONLINE. PER ASAP, EMERGENCY DECLARED. PERFORMED ENGINE RUN TWICE. NO FAULTS. WHILE INSPECTING LEFT GENERATOR CEU MAINTENANCE NOTICED SLIGHT ELECTRICAL SMELL. REPLACED LEFT GENERATOR CEU AND COTA PRECAUTIONARY, PER MM. REMOVED AND REPLACED #1 CABIN PRESSURE CONTROLLER PER MM. SERVICED NR 1 AND NR 2 VSCF'S. OKAY FOR SERVICE.

Part: ANGLE — CRACKED (BS 1486) · airframe 50,766 hrs · 29,232 cycles

DOUBLER ANGLE CRACKED AT BS 1486 BETWEEN LONGERONS 2 AND 3R. REMOVED, FABRICATED AND INSTALLED A REPAIR IAW DWG 9953016.

Part: SHEAR TIE — CRACKED (BS 1475) · airframe 50,766 hrs · 29,232 cycles

CRACKED SHEAR TIE AT BS 1475 FRAME AND LONGERON 2R. REMOVED, FABRICATED AND INSTALLED A REPAIR IAW SRM 53-10-02 AND PRI/ERA 502037-14.

Part: ANGLE — CRACKED (BS 1486) · airframe 50,766 hrs · 29,232 cycles

DOUBLER ANGLE CRACKED AT BS 1486 LONGERONS 1 AND 2R. REMOVED, FABRICATED AND INSTALLED A REPAIR IAW DWG 9953016.

Part: SHEAR TIE — CRACKED (BS 1475) · airframe 50,766 hrs · 29,232 cycles

SHEAR TIE AT BS 1475 CRACKED BETWEEN LONGERONS 1 AND 2R. REMOVED, FABRICATED AND INSTALLED A REPAIR IAW SRM 53-10-02, AND PRI/ERA 502037-14.

Part: FRAME — CRACKED (BS 1486) · airframe 50,766 hrs · 29,232 cycles

FRAME BS 1486 BETWEEN LONGERONS 1 AND 2L CRACKED. REMOVED, FABRICATED AND INSTALLED A REPAIR IAW DWG 9953016.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 49,580 hrs · 28,552 cycles

TAIL EMERGENCY LIGHT INOPERATIVE. REPLACED BATTERY AND BATTERY PACK IAW MM. OPERATION CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 49,230 hrs · 28,374 cycles

BOTH OVER WING EMERGENCY LIGHTS WILL NOT ILLUMINATE. REPLACED BATTERY PACK PER MM. OPERATION CHECKS GOOD. (LP# 9957216)

Part: CHANNEL — GOUGED · airframe 46,231 hrs · 26,679 cycles

FORWARD TURTLE DOME AFT TOP INNER CHANNEL GOUGED. REPAIRED IAW ERA 545243-14, REV O.

Part: FRAME — WORN (BS 1437) · airframe 46,231 hrs · 26,679 cycles

FRAME WEB WORN, BS 1437, NEAR L5L. REPAIRED IAW ERA 544923-14, REV A.

Part: ATTACH FITTING — CORRODED (HORIZONTAL STAB) · airframe 46,231 hrs · 26,679 cycles

HORIZONTAL STABILIZER AFT ATTACH POINT ON EMPENNAGE, LT LUG HAS FRETTING ON INBD VERTICAL FACE. REPAIRED IAW SRM 55-30-05, PARA 7.

Part: ATTACH FITTING — CORRODED (HORIOZNTAL STAB) · airframe 46,231 hrs · 26,679 cycles

HORIZONTAL STABILIZER ATTACH POINT ON EMPENNAGE, RT LUG HAS FRETTING ON INBD VERTICAL FACE. REPAIRED IAW SRM 55-30-05, PARA 7.

Part: ATTACH FITTING — CORRODED (HORIZONTAL STAB) · airframe 46,231 hrs · 26,679 cycles

HORIZONTAL STABILIZER AFT ATTACH POINT ON EMPENNAGE LT LUG HAS CORROSION ON IN BORE. REPAIRED IAW SRM 55-30-05, PARA 7.

Part: FRAME — CRACKED (BS 924) · airframe 46,231 hrs · 26,679 cycles

OVERWING FRAME AT BS 924 LT IS CRACKED IN THE UPPER RADIUS OF TAB. REPLACED FRAME IAW AMDS 5310-01375-07-LT.

Part: ATTACH FITTING — CORRODED (HORIZONTAL STAB) · airframe 46,231 hrs · 26,679 cycles

HORIZONTAL STABILIZER ATTACH POINT ON EMPENNAGE, RT LUG HAS FRETTING ON OUTOBARD VERTICAL FACE. REPAIRED IAW SRM 55-30-05, PARA 7.

Part: ATTACH FITTING — CORRODED (HORIZONTAL STAB) · airframe 46,231 hrs · 26,679 cycles

HORIZONTAL STABILIZER AFT ATTACH POINT ON EMPENNAGE, LT OTBD LUG HAS FRETTING ON OTBD VERTICAL FACE. REPAIRED IAW SRM 55-30-05, PARA 7.

Part: SPAR CAP — CORRODED (HORIZONTAL STAB) · airframe 46,231 hrs · 26,679 cycles

RIGHT HORIZONTAL STABILIZER UPPER REAR SPAR CAP HAS CORROSION INSIDE BORE OF AFT BARREL NUT HOLE. INSTALLED SPLICE REPAIR OF UPPER REAR SPAR CAP PER DRAWING SR 9055003, AND ER/A 548620-14AD.

Part: CONNECTOR — UNSECURE (EMERGENCY LIGHTS) · airframe 45,652 hrs · 26,342 cycles

EGRESS LIGHT AND LT AND RT EXIT SIGN L1 AND R1 INOPERATIVE. FOUND P1-791 CONNECTOR PLUG AT BATTERY PACK SECURED.

Part: BULB — INOPERATIVE (EMERGENCY LIGHT) · airframe 43,673 hrs · 25,163 cycles

TWO TAILCONE CEILING EMERGENCY LIGHTS ARE INOPERATIVE. R & R BOTH 313 BULBS WITH 316 BULBS. OPS CHECK GOOD. LP 6996627.

Part: A/C PACK — ODOR (LEFT) · airframe 43,543 hrs · 25,082 cycles

RECEIVED A BURNING ODOR AND HAZE WHEN LEFT PACK MOVED FROM FULL HOT TO COLD IN AUTO OR MANUAL. R & R TIMER RELAY, FAN, GROUND BLOWER AND R2-4. OPS CHECKED GOOD.

Part: BOTTLE — LOW PRESSURE (DOOR SLIDE) · airframe 41,597 hrs · 23,824 cycles

LEFT AFT DOOR SLIDE PRESSURE LOW. R & R LT AFT SERVICE DOOR SLIDE PACK IAW JIC 2561-4642.

Part: B-NUT — LEAKING (HYD SYSTEM) · airframe 38,318 hrs · 21,891 cycles

STRONG EXHAUST TYPE ODOR REPORTED BY F/A. TURNED OFF RT PACK, ODOR DISSIPATED. MX REMOVED AFT STAIRWELL PANELS AND FOUND LOOSE B-NUT AND HYD FLUID LEAKING FROM BLEED VALVE FORWARD OF HYD CONTROL VALVE, LT SIDE OF STAIRWELL. TIGHTENED B-NUT AND LEAK CHECKED. CHECKED GOOD. FOUND HYDRAULIC FLUID CONTAMINATION IN APU INLET. PERFORMED APU DUCT BURNOUT. OPS CHECKED NORMAL. STAIRWELL PANELS REINSTALLED.

Part: FRAME — CORRODED (BS 1328) · airframe 36,380 hrs · 20,789 cycles

DURING HMV, FOUND FRAME 1328 CORRODED FWD AND AFT. CUTOUT DAMAGED SECTION OF FRAME FABRICATED AND INSTALLED SPLICE PER SRM 53-10-02 FIG 2.

Part: DOOR FRAME — CORRODED (BS 1193-1288) · airframe 36,380 hrs · 20,789 cycles

DURING HMV, FOUND AFT CARGO BAY LOWER INBD DOOR JAMB HEADER BEAM STA 1193-1288 IS CORRODED. REMOVED CORRODED IBD JAMB HEADER AND REPLACED WITH NEW JAMB HEADER P/N 5936037-505 IAW MD90 SRM VOL2 51-30-05 FIG 13.

Part: SUPPORT — CHAFED · airframe 40,083 hrs · 20,495 cycles

FOUND AFT ACCESSORY COMPARTMENT, RT SIDE VENTRAL STAIR SIDEWALL PANEL FRAME CHAFED AGAINST RT A/C PACK DIVERTER BOX. REPAIRED RT VENTRAL STAIR SIDEWALL FRAME IAW SRM 51-70-01 FIG 1, VOL 1.

Part: FRAME — CORRODED (BS 1307) · airframe 36,380 hrs · 20,789 cycles

DURING HMV, FOUND FRAME 1307 CORRODED FROM 28L TO 28R. CUTOUT DAMAGED SECTION OF FRAME. FABRICATED AND INSTALLED SPLICE PER SRM 53-10-02 FIG 2.

Part: BULKHEAD — CRACKED (BS 1520.22) · airframe 36,380 hrs · 20,789 cycles

FOUND CRACK FWD FACE Y1520.22 ZRS - 16.00 RBL 20 REAR SPAR BULKHEAD. REMOVED LOUVER, REMOVED STIFFENERS AND WEB. FABRICATED NEW WEB, INSTALLED NEW WEB AND PREEXISTING STIFFENERS AND LOUVER BOX PER SRM 51-30-05, 51-30-02 AND 53-10-04 VOL II.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 36,380 hrs · 20,789 cycles

DURING HMV, FOUND LT FUSELAGE STA 47.875 SKIN IS CREASED ON FRAME. REMOVED DAMAGED AREA, FABRICATED DOUBLER, INSTALLED DOUBLER IAW SRM VOL I 53-31-01, 53-31-03 FIG 8.

Part: DOOR FRAME — CORRODED (BS 693-750 L28R) · airframe 36,380 hrs · 20,789 cycles

DURING HMV, FOUND MID CARGO BAY STA 693-750 L28R LOWER DOOR JAMB BEAM IS CORRODED. REMOVED AND REPLACED JAMB BEAM IAW SRM 51-30-05 AND DWG 5930481.

Part: SUPPORT — CRACKED · airframe 40,083 hrs · 20,495 cycles

FOUND AFT ACCESSORY COMPARTMENT LEFT A/C PACK DIVERTER BOX CHAFED AT VENTRAL STAIRS SIDEWALL PANEL FRAME, CRACKED. REPAIRED LT VENTRAL STAIRS SIDEWALL PANEL FRAME IAW SRM 51-70-01 FIG 1 VOL1.

Part: FRAME — CORRODED (BS 1437 L27L/R) · airframe 36,380 hrs · 20,789 cycles

FOUND CORROSION ON STA 1437 BETWEEN L27L TO L27R. REMOVED AND REPLACED LOWER FRAME CHORD AT STA 1437, BETWEEN L27R IAW MD90 SRM 51-10-05 FIG 5 VOL II, 51-30-02 AND 51-30-05 VOL II.

Part: SKIN — CORRODED (BS 160 L28R) · airframe 36,380 hrs · 20,789 cycles

FOUND LOWER FUSELAGE SKIN BULGING AT FS 160 LONGERON 28R. CUTOUT DAMAGED INNER DOUBLER. FABRICATED AND INSTALLED REPAIR DOUBLER IAW ERA 500901-14 REV ORIG.

Part: DOOR FRAME — CORRODED (BS 160 RBL 11) · airframe 36,380 hrs · 20,789 cycles

FOUND E/E BAY CUTOUT AFT DOOR FRAME HAS AREA OF CORROSION AT FS 160 RBL 11. CUTOUT AND REPLACED DAMAGED SECTION OF FRAME BS 160 RBL 11 IWA ERA 500898-14 REV ORIG.

Part: TEE FITTING — UNKNOWN (FS 1395) · airframe 36,380 hrs · 20,789 cycles

FUSELAGE BULKHEAD FS 1395 AFT PRESSURE BULKHEAD TEE CAP, REPAIRED IAW ERA 500900-14 LOG PAGES, C022673, C022674, C022675.

Part: NONE — NONE (NONE) · airframe 36,380 hrs · 20,789 cycles

FUSELAGE, SKIN, DOUBLER REPAIR INSPECTION, STA 1475 L3LH-L3RH, REPAIRED IAW ERA 502037-14.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 36,380 hrs · 20,789 cycles

DURING HMV/MOD AT FLIGHTSTAR FOUND FWD ENTRY STA 229 RBL-22 SEAT TRACK IS CORRODED. REMOVED CORRODED SECTION OF SEAT TRACK AT STA 229 RBL 22. INSTALLED NEW SEAT TRACK SECTION IAW SRM 53-40-01 FIG 6.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 36,380 hrs · 20,789 cycles

DURING HMV/MOD FOUND FWD ENTRY STA 229 RBL 44 SEAT TRACK IS CORRODED. REMOVED SECTION OF SET TRACK FROM STA 196-240. LOCATED AND DRILLED NEW SECTION OF SEAT TRACK AND INSTALLED IAW SRM 53-40-01 FIG 6.

Part: DOOR FRAME — CORRODED (CARGO BAY) · airframe 36,380 hrs · 20,789 cycles

DURING HMV/MOD FOUND FWD PIT DOOR JAMB BEAM STA 370-427 IS CORRODED. CUTOUT DAMAGE SECTION OF LWR JAMB. LOCATED AND DRILLED NEW JAMB SECTION, REPAIR SPLICES AND INSTALLED IAW SRM 53-60-02 FIG 11.

Part: FRAME — UNKNOWN (BS 883 - 962) · airframe 36,380 hrs · 20,789 cycles

BS 883-BS962 OVERWING FRAMES REPAIRED IAW AA 5310-01375.

Part: SPAR — CRACKED (WING) · airframe 36,380 hrs · 20,789 cycles

WING REAR SPAR CRACKING REPAIRED IAW AA 5710-01119.

Part: FASTENER — UNKNOWN (PYLON) · airframe 36,380 hrs · 20,789 cycles

PYLON AFT SPRT FITTING UPPER FASTENERS REPLACED IAW AA 5440-01069.

Part: SPAR CAP — UNKNOWN (VERTICAL STAB) · airframe 36,380 hrs · 20,789 cycles

VERTICAL STABILIZER, L/E FRONT SPAR CAP REPAIRED IAW AA 5530-01044.

Part: STOP FITTING — UNKNOWN (CARGO DOOR) · airframe 36,380 hrs · 20,789 cycles

CARGO DOOR STOP PAD FITTINGS REPAIRED IAW AA 5230-01136.

Part: JACKSCREW — UNKNOWN (HORIZONTAL STAB) · airframe 36,380 hrs · 20,789 cycles

HORIZONTAL STABILIZER, JACKSCREW ASSY REPAIRED IAW AA 2740-01071.

Part: LUG — UNKNOWN (H STAB HINGE RIB) · airframe 36,380 hrs · 20,789 cycles

HORIZONTAL STABILIZER HINGE RIB PIVOT BEARING LUG REPAIRED IAW AA 5510-01083.

Part: SUPPORT FITTING — UNKNOWN (MLG) · airframe 36,380 hrs · 20,789 cycles

MLG ACTUATOR SUPPORT FITTING REPAIRED IAW AA 5740-01140.

Part: SKIN — UNKNOWN (HORIZONTAL STAB) · airframe 36,380 hrs · 20,789 cycles

HORIZONTAL STABILIZER UPPER CENTER SKIN PANEL REPAIRED IAW AA 5510-01085.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 31,909 hrs · 17,873 cycles

LT ENGINE UPPER ROW FASTENER REPLACEMENT IAW EA 02-476701-12.

Part: SUPPORT FITTING — UNKNOWN (MLG) · airframe 31,909 hrs · 17,873 cycles

LEFT MLG, INSP/REPLACED RETRACT ACTUATOR SUPPORT FITTINGS. REPAIRED IAW EA 02-093855-03.

Part: DOOR FRAME — CORRODED (CARGO BAY) · airframe 31,905 hrs · 17,871 cycles

FUSELAGE, AFT CARGO DOORWAY LOWER JAMB BEAM, L-28R CORROSION REPAIRED IAW ERA 398119-14.