N123DN

Part: BATTERY PACK — INOPERATIVE (CABIN) · airframe 70,240 hrs · 31,469 cycles

RIGHT/LEFT AFT, L1 AND R1 EMERGENCY EXIT THRESHOLD LIGHTS INOPERATIVE. REMOVED AND REPLACED BATTERY PACK PER MM 33-51-07. OPERATIONAL CHECKED GOOD.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 67,442 hrs · 30,716 cycles

THE FOLLOWING ITEMS WERE NOTED REGARDING THE EMERGENCY LIGHTING SYSTEM DURING THE INSPECTION AND TESTING OF THE C-CHECK ON AIRCRAFT N123DN: EMERGENCY LIGHT OUTSIDE R1 DOOR INOPERABLE AND 3 RT OVERWING. EMERGENCY EXIT SIGN INOPERABLE LEFT AND RIGHT SIDE O/H FWD OF MID GALLEY. AISLE O/H EMERGENCY LIGHT BY SEAT 28 AB. AISLE O/H EMERGENCY LIGHT INOPERABLE BY SEAT 31 AB. AISLE O/H EMERGENCY LIGHT INOPERABLE BY SEAT 34 AB. AISLE O/H EMERGENCY LIGHTS IN MID GALLEY INOPERABLE. AISLE O/H EMERGENCY LIGHT INOPERABLE BY SEAT 34 FG. AISLE O/H EMERGENCY LIGHT INOPERABLE BY SEAT 31 FG. AISLE O/H EMERGENCY LIGHT INOPERABLE BY SEAT 20 FG. AISLE O/H EMERGENCY LIGHT INOPERABLE BY SEAT 25 AB. AISLE O/H EMERGENCY LIGHT INOPERABLE BY SEAT 20 AB. AISLE O/H EMERGENCY LIGHT INOPERABLE SEAT ROW 34-46 LEFT AND RIGHT SIDE. EMERGENCY LIGHT ON SEAT 1 AB INOPERABLE. REMOVED AND REPLACED THE FOLLOWING BATTERY PACKS AND CHARGERS, M731, M732, M733, M9010 AND M738 PER APPLICABLE AMM’S. ADDITIONALLY REPLACED AFT F/A PANEL PUSH BUTTON SWITCH. ALL CHECKS COMPLETED AND OPS CHECKS GOOD.

Part: STRAP — CRACKED (FUSELAGE) · airframe 67,442 hrs · 30,716 cycles

DURING THE ACCOMPLISHMENT OF EO RN767-53-02 RELATED TO BOEING SB 767-53A0100 AND AD 2004-19-06-R1 .1875 INCH CRACK WAS FOUND ON THE RT REAR BULKHEAD SIDE FITTING FAIL-SAFE STRAP. ACCOMPLISHED REPAIR ON RT SIDE PER EO RN767-53-02 AND BOEING SB 767-53A0100.

Part: STRAP — CRACKED (FUSELAGE) · airframe 67,442 hrs · 30,716 cycles

DURING THE ACCOMPLISHMENT OF EO RN767-53-02 RELATED TO BOEING SB 767-53A0100 AND AD 2004-19-06 R1 A .0937 INCH CRACK WAS FOUND ON THE LT REAR BULKHEAD SIDE FITTING FAIL-SAFE STRAP. ACCOMPLISHED REPAIR ON LT SIDE PER EO RN767-53-02 AND BOEING SB 767-53A0100.

Part: UNKNOWN — MALFUNCTIONED (E&E DOOR) · airframe 66,833 hrs · 30,556 cycles

DURING CLIMB EICAS E/E LIGHT ILLUMINATED, CABIN CONTINUED SLIGHT CLIMB. PERFORMED AIR TURNBACK. PLACARD THE LOWER LOBE ELECTRONIC EQUIPMENT ACCESS DOOR ITEM DEFERRED PER MEL 52-71-1 ITEM IS A CATEGORY C. ADDITIONALLY PERFORMED CABIN PRESSURE CONTROL BITE CHECK, NO DEFECTS NOTED.

Part: STRUCTURE — CRACKED (FUSELAGE) · airframe 66,592 hrs · 30,500 cycles

PERFORMING FLEET CAMPAIGN DIRECTIVE (FCD) 53-205 FOUND CRACKING WITHIN STA 287 AT WL 159 WHICH EXTENDS APPROXIMATELY 0.375 INCHES ABOVE WL 159 AND APPROXIMATELY 0.750 INCHES BELOW WL 159. FERRY WAS AGREED TO UNDER THE LIMITATIONS: FLIGHT TO BE CONDUCTED USING MINIMAL FUEL LOAD NECESSARY TO ACCOMPLISH THE FLIGHT SAFELY AS DETERMINED BY THE PILOT IN COMMAND (PIC). CRACK ENDS ARE STOP DRILLED IN ACCORDANCE WITH (IAW) BOEING STRUCTURAL REPAIR MANUAL (SRM). REMOVED AND REPLACED THE CORD MFG P/N 141T2938-30 PER BOEING DRAWING 141T2929 SHEETS 1, 6 AND 7; 141T9920 SHEET 14 AND OTHER APPLICABLE DRAWINGS AS REQUIRED. INCLUDING BAC SR 1-1421280777 IN ACCORDANCE WITH S/B 767-53A0113.

Part: PROXIMITY SENSOR — FAULTY (DOOR) · airframe 66,409 hrs · 30,458 cycles

DURING PREFLIGHT INSPECTION THE PILOT’S OVERHEAD EMERGENCY ADVISORY LIGHT CAME ON. PLACARD THE PILOT’S OVERHEAD EMERGENCY ADVISORY LIGHT PER MEL 52-71-1 DMI REFERENCE 60510. REMOVED AND REPLACED SENSOR 192 PER AMM 52-71-01 PAGE 412-414. OPS CHECK GOOD, CLEARED DMI, REMOVED PLACARD.

Part: B-NUT — LOOSE (HYDRAULIC PUMP) · airframe 65,718 hrs · 30,289 cycles

LEFT HYDRAULIC SYSTEM PRESSURE, RUDDER RATIO, LEFT HYDRAULIC QUANTITY, YAW DAMPER, AND SPOILER EICAS MESSAGES. TIGHTENED B NUT THAT BACKED OFF ON NR 1 ENGINE HYDRAULIC PUMP. REMOVED AND REPLACED PRESSURE, CASE DRAIN AND RETURN FILTERS.

Part: FAN BLADE — OUT OF BALANCE (RT ENGINE) · airframe 64,065 hrs · 29,865 cycles

DURING CLIMB AND LEVEL OFF AT F/L 370 RIGHT ENGINE VIBRATION REACHED 3.9 UNITS. THE AIRCRAFT DIVERTED TO ATLANTA FOR MAINTENANCE TO DELTA AIRLINES MAINTENANCE CENTER. ACCOMPLISHED BORESCOPE INSPECTION, FAN BLADE LUBRICATION, RIGGED VSV & VBV SYSTEM AND BALANCED THE FAN BLADES. PERFORMED ENGINE RUN AND ALL SYSTEMS & PARAMETERS CHECKED NORMAL.

Part: RADIO — FAILED (RT HF SYSTEM)

ACFT DIVERTED DUE TO LOSS OF THE RT HF COMMUNICATION SYSTEM. THE LT HF IS ALREADY ON DEFERRAL PER MEL 23-11-1-2. TROUBLESHOOTING IN WORK (ISSUED MEL 23-11-1-2OH DMI NR62632). (S)

Part: WINDOW — CRACKED (COCKPIT) · airframe 62,302 hrs · 29,401 cycles

F/O WINDSHIELD CRACKED AND IS ARCHING. REPLACED R1 WINDOW WINDOW HEAT CONTROL UNIT PER AMM. BITE CHECKED CONTROL UNIT IT VERIFIED GOOD.

Part: FITTING — DAMAGED (NR 2 PYLON) · airframe 59,681 hrs · 28,432 cycles

THE NUMBER 2 PYLON UPPER SPAR FITTING WAS FOUND TO HAVE A PREVIOUSLY OVERSIZED HOLE, AT THE AFT OUTER PERIMETER FASTENER. A BOEING APPROVED REPAIR WAS INSTALLED AT THE SUBJECT LOCATION, PER ERA 456536-14.

Part: FITTING — CORRODED (BS 955) · airframe 59,681 hrs · 28,432 cycles

CORROSION WAS IDENTIFIED ON THE INBOARD FORWARD SURFACE OF THE REAR SPAR BULKHEAD TERMINAL FITTING. THE BOEING APPROVED REPAIR INVOLVED REMOVING BOLTS FOR ACCESS AND LIGHT BLENDING OF THE SURFACE TO REMOVE THE CORROSION PER ERA 456629-14.

Part: SPAR — DAMAGED (NR 2 PYLON) · airframe 59,681 hrs · 28,432 cycles

DURING ACCOMPLISHMENT OF EO 01-074906-03 THE NUMBER 2 PYLON SPLICE PLATE UPPER OUTBOARD HOLE WAS FOUND TO ALREADY BE OVERSIZED TO BEYOND MAX EO LIMIT. THE BOEING APPROVED REPAIR INVOLVED INSTALLATION OF AN OVERSIZED FASTENER PER ERA 456537-14.

Part: FLOORBEAM — CORRODED (BS 1502) · airframe 59,681 hrs · 28,432 cycles

CORROSION WAS FOUND AROUND THE NUT PLATES ON THE LOWER TEE OF THE 1502 FLOORBEAM. THE CORROSION WAS REMOVED AND REPAIR PARTS INSTALLED PER BOEING INSTRUCTIONS AS CONTAINED IN 456631-14.

Part: SPAR — CRACKED (NR 1 NACELLE) · airframe 59,681 hrs · 28,432 cycles

THE NUMBER 1 PYLON UPPER SPAR FITTING, RHS AT ATTACH FITTING HOLE SHOWED A CRACK INDICATION. THE SUBJECT HOLE WAS OVERSIZED, AND THE BOEING APPROVED REPAIR INVOLVED INSTALLATION OF A STRAIGHT SHANK FREEZE PLUG PER ERA 456634-14.

Part: SKIN — MISREPAIRED (FS 500 S36L) · airframe 59,681 hrs · 28,432 cycles

A PREVIOUS REPAIR FOUND ON THE FUSELAGE SKIN AT 500 AND S36L DOES NOT CONFORM TO SRM AND NO RECORDS WERE FOUND. REPAIR WAS REMOVED AND A BOEING APPROVED REPAIR WAS INSTALLED PER ERA 456627-14.

Part: BULKHEAD — DAMAGED (NR 1 PYLON) · airframe 59,681 hrs · 28,432 cycles

DURING ACCOMPLISHMENT OF THE SIP MOD ON THE AIRCRAFT, AN EXISTING FREEZE PLUG REPAIR WAS FOUND ON THE NR 1 PYLON LHS UPPER ATTACH HOLE FOR GSE FITTING. THE PLUG WAS COMMON TO THE BULKHEAD FLANGE AND SIDE LOAD FITTING. THE SIDE LOAD FITTING WAS REPLACED AS PART OF THE SIP MOD. A BOEING APPROVED BUSHING REPAIR WAS INSTALLED IN THE OVERSIZED HOLE OF THE BULKHEAD FLANGE PER ERA 456539-14.

Part: SKIN — CRACKED (BS 1197 S39L-39R) · airframe 59,681 hrs · 28,432 cycles

THE FUSELAGE SKIN WAS FOUND CRACKED AT THE NR 3 VHF ANTENNA, FS 1197+90, AT STR 39L 39R. REPAIR INVOLVED CUTTING OUT THE DAMAGE AND INSTALLATION OF BOEING APPROVED REPAIR PARTS PER ERA 455968-14.

Part: FRAME — CRACKED (FUSELAGE) · airframe 59,070 hrs · 28,224 cycles

FUSELAGE FRAME FS 883.5 RHS LOWER INNER CHORD CRACK. CRACK WAS LOCATED ON THE LOWER END OF THE .25 RADIUS TRANSITION BETWEEN CHORD FLANGES.

Part: FRAME — CRACKED (FS 903) · airframe 59,070 hrs · 28,224 cycles

CRACKS WERE FOUND ON THE INNER CHORD OF THE FS 903 FRAME, RT SIDE. DAMAGE WAS CUT OUT AND A REPAIR ANGLE WAS INSTALLED.

Part: FITTING — MISALIGNED (NR 1 PYLON) · airframe 59,070 hrs · 28,224 cycles

THE NR 1 PYLON INBOARD PITCH LOAD FITTING UPPER LINK BUSHING HAS MIGRATED 0.004 INCH. THE MIGRATED BUSHING WAS REPLACED. AD 2004-16-12, B767-57-0053.

Part: LINKAGE — MISINSTALLED (EVAC SLIDE) · airframe 59,070 hrs · 28,224 cycles

DURING INSPECTION OF THE LT OFF WING ESCAPE SLIDE PER JIC 6075 THE TECHNICIAN FOUND THAT THE INTEGRATOR LOCK HANDLE HAD TO BE FORCED INTO THE SAFETY POSITION. UPON FURTHER INVESTIGATION IT WAS DETERMINED THAT SLIDE DOOR OPENING ACTUATOR LINKAGE LEVER WAS INSTALLED UPSIDE DOWN CAUSING BINDING BETWEEN THE LEVER AND LINKAGE CLEVIS. LEFT AFT OFF, WING SLIDE DOOR OPENING ACTUATOR LINKAGE REINSTALLED AND ADJUSTED PER AMM 25-65-10-404-016.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 46,886 hrs · 22,522 cycles

SVC CHECK FOUND EMERGENCY OVERHEAD LIGHT AT ROW 17 LT SIDE INOP. REPLACED EMERGENCY LIGHT ASSY AT ROW 17 LT SIDE, CHECKS OK.

Part: BATTERY PACK — DISCHARGED (CABIN RT SIDE) · airframe 45,275 hrs · 21,709 cycles

RT EMERGENCY ESCAPE SQUIB WILL NOT TEST. REPLACED RT BATTERY PACK TEST OK.

Part: BATTERY — DISCHARGED (CABIN) · airframe 42,166 hrs · 20,239 cycles

EMERGENCY LIGHT BATTERY PACK AND POWER SUPPLY INOP. REPLACED BATTERY.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

DURING ROUTINE MAINTENANCE, THE LEFT AND RIGHT EMERGENCY EXIT THRESHOLD LIGHTS FOUND INOP. REPLACED POWER SUPPLY, OPS CK NORMAL.

Part: WEDGE — DELAMINATED (NR 1 LE SLAT TE)

WINGS NR 1 SLAT TRAILING EDGE WEDGE, REPAIR FOR DELAMINATION. THE NR 1 SLAT TRAILING EDGE WEDGE WAS FOUND WITH A 3 BY 4 AREA OF DELAMINATION ON THE UPPER SKIN. THE DAMAGE WAS REPAIRED PER B767 SRM 57-43-02 AND DOCUMENTED PER ER/A 364345-14AD.

Part: WEDGE — DELAMINATED (NR 8 LE SLAT TE)

WINGS NR 8 SLAT TRAILING EDGE WEDGE, REPAIR FOR DELAMINATION. THE NR 8 SLAT TRAILING EDGE WEDGE WAS FOUND WITH A 5 BY 9 AREA OF DELAMINATION ON THE UPPER SKIN. THE DELAMINATION WAS REPAIRED PER THE B767 SRM 57-43-02 AND DOCUMENTED PER ER/A 364347-14AD.

Part: SKIN — DELAMINATED (NR 11 LE SLAT)

WINGS LEADING EDGE SLAT NR 11, TRAILING EDGE WEDGE, SKIN DELAMINATION REPAIR. THE UPPER SKIN OF THE NR 11 SLAT TRAILING EDGE WEDGE WAS FOUND WITH A 3 BY 6 AREA OF DELAMINATION. THE DAMAGE WAS TRIMMED OUT AND REPAIRED PER B767 SRM 57-43-02 AND DOCUMENTED PER ER/A 364348-14AD.

Part: WEDGE — DELAMINATED (NR 2 LE SLAT TE)

WINGS NR 2 SLAT TRAILING EDGE WEDGE, REPAIR FOR DELAMINATION. THE NR 2 SLAT TRAILING EDGE WEDGE WAS FOUND WITH A 7 BY 4.5 AREA OF DELAMINATION ON THE UPPER SKIN. THE DAMAGE WAS REPAIRED PER B767 SRM 57-43-02 AND DOCUMENTED PER ER/A 364346-14AD.

Part: BATTERY PACK — DISCHARGED (CABIN)

RIGHT AND LEFT AFT SERVICE DOOR INTERIOR EMERGENCY EXIT LIGHT SIGNS INOP. REPLACED BATTERY PACK, CHECKS GOOD.

Part: SKIN — DELAMINATION (RT LE SLAT)

THE NR 10 LEADING EDGE SLAT TRAILING EDGE WEDGE WAS FOUND TO HAVE THE UPPER SKIN DELAMINATED AT THE INBD CORNER. THE DAMAGE CUTOUT MEASURES 8 FWD-AFT AND 6 INBD-OUTBD. DAMAGE REPAIRED PER ER/A 361270-14AD.

Part: TE WEDGE — DELAMINATED (LE FLAP)

THE NRS 10, 11, 12 LEADING EDGE SLATS' TRAILING EDGE WEDGES WERE FOUND TO HAVE AREAS OF DELAMINATION. THE AREAS MEASURE 4 INCHES BY 6 INCHES, 2 INCHES BY 3 INCHES, AND 10 INCHES BY 6 INCHES, RESPECTIVELY. REPAIRED IN ACCORDANCE WITH B767-300 SRM, 57-43-02, FIG 201.

Part: CHECK VALVE — CRACKED (LT MLG WW)

INFLIGHT GOT EICAS FOR LT SYS HYDRAULIC'S, FOLLOWED IMMEDIATELY BY LEFT HYDRAULIC SYS PRESSURE MESSAGE. STATUS PAGE SHOWS LT QTY AT 0.04. FOUND CHECK VALVE AT GROUND HYD SERV QUICK DISCONNECT LEAKING.

Part: SKIN — LIGHTNING STRIKE (FS 355)

FOUND DURING LETTER CHECK, LIGHTNING STRIKES ABOVE COCKPIT SECTION OF FUSELAGE. BURNISHED OUT DAMAGES, FOUND ONE LIGHTING STRIKE OUT OF LIMITS. REPLACED RIVETS STA 355 BETWEEN STR 3 AND 4R STA 400 STR 4R, STA 484 STR 3R. DYE CHECKED AREAS, TREATED AND PAINTED. OUT LIMIT REPAIR STA 460 STR 3 AND 4R REPAIRED PER SRM 53-00-01.

Part: SKIN — LIGHTNING STRIKE (FUSELAGE)

DURING LETTER CHECK, FOUND SEVERAL LIGHTNING STIKES TO FUSELAGE SKIN. RT SIDE REPAIRED PER SRM 53-00-01 ITEM 3.