N407DA

Part: BRACKET — CRACKED (LE FLAP ACTUATOR)

A 1.25 INCH CRACK NR 8 SLAT ACTUATOR I/B AFT ATTACH BRACKET. REPAIRED PER MM 57-20-21.

Part: LIGHT — INOPERATIVE (COCKPIT)

FLIGHT DECK EMERGENCY PORTABLE EXIT IDENTIFIER LIGHT WOULD NOT TEST. REPLACED BATTERY PACK, OP CKS GOOD.

Part: SKIN — CRACKED (BS 481-681)

LFEC INSPECTION OF THE STRINGER 26L SKIN LAP SPLICE BETWEEN FS 481 & 681 INDICATED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN. INTERNAL HFEC INSPECTION CONFIRMED 5 CRACKS ALONG THE JOINT. THE SKIN LAP WAS CUTOUT ALONG THE ENTIRE PANEL LENGTH AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 367640-14, REV A.

Part: CSD — REQUIRED SERVICE (NR 2 ENGINE)

CSD LOW PRESSURE LIGHT FLICKERED AND THEN STAYED ON, LOST MAIN AC NR 2. FOUND CSD LOW. SERVICED CSD, RAN ENG AND NO LEAKS NOTED.

Part: WEB — CRACKED (BS 1226)

TPA LTR CHK B-2, LT VERT TORQUE BOX WEB CRACKED .25 INCH AT UPPER LIGHTENING HOLE AT STA 1226. REPAIRED PER MM 53-11-0 PG 828, LT VERT TORQUE BOX WEB LWR LIGHTENING HOLE .375 INCH CRACK AT UPPER END AND A .625 INCH CRACK ON LWR END STA 1226. REPAIRED PER MM 53-11-0 PG 832.

Part: FRAME — CRACKED (PAX DOORWAY)

FOUND AT B-2 LETTER CHECK, LT AFT ENTRYWAY DOOR FRAME HAS .375 INCH VISIBLE CRACK. REPAIRED PER SRM 53-10-9.

Part: SKIN — CRACKED (BS 481-681)

LFEC INSPECTION OF THE STRINGER 4R SKIN LAP SPLICE BETWEEN FS 481 AND 681 INDICATED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN. INTERNAL HFEC INSPECTION CONFIRMED 8 CRACKS ALONG THE PANEL LENGTH. THE SKIN LAP WAS CUT OUT ALONG THE PANEL LENGTH AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 366907-14AD, REV A.

Part: SKIN — CRACKED (BS 510)

LFEC INSPECTION OF THE STRINGER 26L SKIN LAP SPLICE BETWEEN FS 360 AND 680 INDICATED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN. HFEC INTERNAL INSPECTION CONFIRMED 3 CRACKS BETWEEN FS 500 AND 520. THE CRACKS WERE ROUTED OUT OF THE SKIN LAP AND REPAIRED PER B727 SRM 53-30-3, FIGURE 5 AND DOCUMENTED PER ER/A 366894-14AD, REV A.

Part: SKIN — CRACKED (BS 720)

LFEC INSPECTION OF THE STRINGER 4R SKIN LAP SPLICE BETWEEN FS 680 TO 740 INDICATED A CRACK IN THE LOWER FASTENER ROW OF THE LOWER SKIN. INTERNAL HFEC INSPECTION CONFIRMED A SINGLE CRACK BETWEEN FS 720 AND 720A. THE CRACKED AREA WAS ROUTED OUT AND REPAIRED PER B727 SRM 53-30-3, FIG 5 AND DOCUMENTED PER ER/A 366917-14AD.

Part: SKIN — CRACKED (BS 360-380)

LFEC INSPECTION OF THE STRINGER 4R SKIN LAP SPLICE BETWEEN FS 360 AND 481 REVEALED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN. INTERNAL HFEC INSPECTION CONFIRMED 3 CRACKS BETWEEN FS 360 AND 380. THE CRACKS WERE ROUTED OUT AND REPAIRED PER B727 SRM 53-30-3, FIG 5 AND DOCUMENTED PER ER/A 366916-14AD.

Part: SKIN — CRACKED (BS 400-420)

LFEC INSPECTION OF THE STRINGER 4L SKIN LAP SPLICE BETWEEN FS 360 AND 480 INDICATED A CRACK IN LOWER FASTENER ROW OF THE LOWER SKIN. INTERNAL HFEC INSPECTION CONFIRMED 3 CRACKS BETWEEN FS 400 AND 420. THE CRACKS WERE CUT OUT AND REPAIRED PER B727 SRM 53-30-3, FIG 5. THE REPAIR WAS DOCUMENTED PER ER/A 366923-14AD.

Part: PUMP — FAILED (NR 2 ENGINE)

B-SYSTEM HYD WENT TO 0, FOLLOWED PROCEDURES. WHEN GEAR EXTENDED HYD PRESS WENT TO 1700 PSI. OPERATED BRAKE INTERCONNECT, USED PNEUMATIC BRAKES TO STOP. TOWED ACFT TO GATE FROM RUNWAY. FOUND NR 2 B-HYD PUMP LEAKING. REPLACED SAME AND FITTINGS, LEAK CKS OK. CHARGED XFER TUBE AND SERVICED PNEUMATIC BOTTLE.

Part: ACTUATOR — LEAKING (RT LE FLAP)

AIRCRAFT LOST 'A SYSTEM HYDRAULICS WHILE TAXING TO THE GATE AFTER LANDING IN CVG. MTC FOUND THAT THE NUMBER 7 LEADING EDGE SLAT ACTUATOR HAD FAILED. REPLACED ACTUATOR AND BOTH HYDRAULIC PUMPS.

Part: STRINGER — CRACKED (BS 950)

FUSE STR 29R WAS FOUND CRACKED AT FS 950E. REPAIRED PER ERA 332275-14.

Part: STRINGER — CRACKED (WS 304)

RT WING UPPER SURFACE S18 AT WS 304 WAS FOUND CRACKED, REQUIRING A 2.5 INCH CUTOUT. REPAIRED PER ERA 332341-14.

Part: FRAME — CRACKED (BS 760)

CRACK WAS FOUND IN THE VERT FLANGE OF THE WING TO FUSE UPPER ATTACH CHORD, LWR FRAME HOLE RBL 70.85, FS 760. REPAIRED PER ERA 332283-14AD.

Part: STRINGER — CRACKED (WS 171.5)

S18 TAB ON THE RT WING VENT BOX AT WS 171.5 WAS FOUND CRACKED. ADDITIONAL DAMAGE INCURRED WHILE INSTALLING THE SRM REPAIR. REPAIRED PER ERA 332288-14.

Part: SKIN — CRACKED (BS 295)

FUSELAGE SKIN WAS FOUND WITH A TIME LIMITED EXT REPAIR DOUBLER FOR A CRACK IN THE SKIN AT FS 294.5, BELOW S15R. THE TIME LIMITED REPAIR WAS REMOVED AND ADDITIONAL DAMAGE FOUND. REPAIRED PER ERA 332347-14.

Part: SPAR — DAMAGED (CTR WING)

DURING INSPECTION OF THE CTR WING REAR SPAR AND REPAIR MANY FASTENER LOCATIONS IN THE SPAR PANEL WERE OVERSIZED DUE TO TOOLING DAMAGE. REPAIRED PER ERA 332359-14AD.

Part: SKIN — CRACKED (BS 294)

FUSE SKIN HAD A TIME LIMITED REPAIR REMOVED AT FS294, S15R; AND ADDITIONAL DAMAGE WAS FOUND. REPAIRED PER ERA 332347-14.

Part: FRAME — CRACKED (BS 784)

A CRACK WAS FOUND IN THE FS 784 RT FRAME INBD FLANGE. THE CRACK PROPAGATES FROM THE FIRST FASTENER HOLE ABOVE THE FLOOR LINE. REPAIRED PER ERA 300891-14AD, REV A.

Part: TRACK — CORRODED (TE FLAP)

CORROSION FOUND AT FWD ATTACH LUG FACES AND BORE AND TO MLG BEAM ATTACH HOLES. BUSH LUG HOLES AND INSTALLED SPLICE PLATE REPAIR FOR MLG BEAM ATTACH HOLES.

Part: SKIN — CRACKED (RT TE MIDFLAP)

DURING SHOP INSPECTION, THE COVE SKIN WAS FOUND CRACKED 34 INCHES FROM I/B END OF FLAP. THE SKIN WAS REPAIRED PER MM 57-52-0, FIG 809 BY REMOVING THE DAMAGE AND INSTALLING A DOUBLER.

Part: ANGLE — CRACKED (RT TE MIDFLAP)

DURING SHOP INSPECTION, THE AFT CHORD ANGLE WAS FOUND CRACKED 18 INCHES FROM I/B END OF FLAP. THE ANGLE WAS REPAIRED PER MM 57-52-0 FIG 802 BY REPLACING A SECTION OF THE ANGLE AND INSTALLING A SPLICE DOUBLER.

Part: ANGLE — REPAIRED (RT TE MIDFLAP)

DURING SHOP INSPECTION, THE AFT CHORD ANGLE WAS FOUND CRACKED AT 2 PLACES APPROX 34 INCHES FROM I/B END OF FLAP. THE ANGLE WAS REPAIRED PER MM 57-52-00, FIG 802 BY REPLACING A SECTION OF THE ANGLE AND INSTALLING A SPLICE DOUBLER.

Part: RIB — CRACKED (LT TE FLAP)

INBOARD AFT CLOSE OUT RIB CRACKED AT LWR AFT CORNER. DAMAG REPAIRED PER MM 57-52-0 ON SHOP ORDER 582612.

Part: PIN — CORRODED (LEFT)

BORE CORRODED LEFT AFT BTL PIN IS CORRODED. CLEANED CORROSION PER SRM 53-40-1 FIG 4 DAMAGE WITHIN LIMITS OK TO TREAT. TREATED BORE PER PS 900-2-4-1 NO O2.

Part: SUPPORT — WORN (NR 2 COWL)

ITEM: NR 2 ENG FWD COWL SUPPORT RING IS WORN AT THE 9 O'CLOCK POS LOC ON FUSELAGE. REMOVED DAMAGED AREA. FABRICATED DOUBLER AND FILLER PER M/M 53-11-0 PG 801. OK TO INSTALL. INSTALLED REPAIR PER M/M 53-11-0 PG 801.

Part: ANGLE — CRACKED (LT TE MIDFLAP)

DURING SHOP VISIT THE AFT LOWER CHORD ANGLE WAS FOUND CRACKED 21 AND 34 FR OM IB END OF FLAP. THE ANGLE WAS REPAIRED BY SPLICING IN A NE W SECTION OF ANGLEPER MM 57-52-0, FIG. 802.

Part: BATTERY PACK — DISCHARGED (CABIN)

ON L/O, AFT OVERWING ESCAPE LIGHT INOP. REPLACED BATTERY PACK.

Part: CONTROL MECH — MALFUNCTIONED (TE FLAPS)

ON APPROACH OUTBD FLAPS WOULD NOT EXTEND. MADE MISSED APPROACH. FLAPS EXTENDED NORMAL ON SECOND ATTEMP. FLAP OPERATIONAL TEST NORMAL ON GROUND AND VISUALLY INSPECTED NO DEFECT FOUND.

Part: SEQUENCE VALVE — DAMAGED (LT MLG DOOR)

AFTER T/O DURING GEAR RETRACTION, SYS-A PRESSURE/QUANTITY WENT TO 0, A-SYSTEM PUMPS TURNED OFF 1 MIN LATER. CASTING DAMAGED ON LT GEAR DOOR SEQUENCE VALVE. REPLACED SAME.

Part: SKIN — CORRODED (BS 520-540)

CORROSION REMOVED AROUND RADIO ALTIMETER ANTENNA CUTOUT BTWN FS 520 TO 540, STR 28L AND 29R. INTERNAL REPAIR WILL BE INSTALLED. ADDITIONAL DAMAGE WAS FOUND AT LETTER CHECK ON 041297. CUT OUT 2 IN BY 2.625 IN AT FS 540, STR 28L. A SEPARATE REPAIR WAS INSTALLED.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

LEFT AFT OVERWING EMERGENCY LIGHT INOP. REPLACED POWER SUPPLY, OPS CHECKS GOOD.

Part: BRACKET — CRACKED (NR 1 LE SLAT ACT)

FOUND ON F1 LETTER CK, NR 1 SLAT ACTUATOR ATTACH BRACKETS CRACKED INBD AND OUTBD SIDES. REPAIRED PER MM 57-20-21.

Part: SWIVEL — LEAKING (LE SLAT ACTUATOR)

DURING CLIMB, A-HYD QTY WENT TO ZERO AND A PUMP LIGHT FLICKERED, RETURNED TO SHV. REPLACED CASE DRAIN FILTERS, NO METAL FOUND. FOUND THE NR 4 SLAT ACTUATOR SWIVEL LEAKING. REPLACED O-RING, REFILLED HYD SYS, RAN ENGINES AND B-PUMPS, OPERATED ALL FLT CONTROLS TO REMOVE AIR FROM HYD SYS AND SERVICED TO FULL, NO LEAKS NOTED.

Part: SKIN — CORROSION (BS 500-520)

CORROSION WAS REMOVED AT STR 28R BETWEEN BS 500 AND BS 520, RESULTING IN A 5.5 BY 2.25 CUT OUT. THERE IS AN EXISTING STRINGER SPLICE AT BS 490 AND A NEW SPLICE BEING INSTALLED AT BS 510 PER B727 SRM. THE SKIN IS MANUFACTURED FROM MACHINED CLAD 2024-T3 WITH A LOCAL THICKNESS OF .090. AN EXTERNAL REPAIR DOUBLER WAS INSTALLED PER DL ERA 303440-14.

Part: SKIN — CORROSION (BS 520-540)

CORROSION DAMAGE WAS REMOVED FROM AROUND THE HOLE CUTOUT FOR THE RADIO ALTIMETER ANTENNA BETWEEN STATION 520 AND STATION 540, BETWEEN STRINGER 28 LEFT AND STRINGER 29 RIGHT. THE SKIN IS MACHINED CLAD 2024-T3 SHEET WITH A LOCAL THICKNESS OF 0.090 THICK. AN INTERNAL REPAIR DOUBLER WILL BE INSTALLED. DURING THE LETTER CHECK ON 4/12/96, ADDITIONAL CORROSION WAS FOUND IN THE FUSELAGE SKIN AT STA 540 AND STR 28L. DAMAGE REMOVAL RESULTED IN A CUT OUT MEASURING 2 BY 2.625. DUE TO TIME CONSTRAINTS ON THE LETTER CHECK VISIT, A TIME LIMITED REPAIR WAS INSTALLED PER DL ERA 259289-14.

Part: BULKHEAD WEB — CRACKED (BS 1183)

THE BS 1183 BULKHEAD WEB WAS FOUND CRACKED AT RBL 26. THERE IS A 1 INCH CRACK AT WL 170. THE WEB IS A BONDED ASSEMBLY OF 2024-T3 CLAD WITH A LOCAL THICKNESS OF 0.050 INCH. THE CRACK LOCATION IS OUTSIDE OF THE INSPECITON AREA SPECIFIED BY BOEING SERVICE BULLETIN 727-53-171. THE VERTICAL STIFFENER AT RBL 26, THE TOPIC OF BOEING SERVICE BULLETIN 727-53-0182, IS NOT DAMAGED. THE CRACK WILL BE STOP DRILLED AND A REPAIR DOUBLER INSTALLED.

Part: ANGLE — CRACKED (FUSELAGE)

FOUND ON E-2 LETTER CHECK, LWR T-ANGLE CRACKED AT AFT HINGE FOR LWR FUS PANEL 3448R. REPAIRED PER M/M 53-30-1 PG 807.

Part: LIGHT — LOOSE (CABIN)

ON PRE-FLIGHT, FOUND SECTION OF TRACK LIGHTING LOOSE WITH EXPOSED WIRING. REPAIRED WIRING SECURED TRACK, OPERATION NORMAL.

Part: SENSOR — DIRTY (RT MLG)

ON GEAR RETRACTION, RED RT GEAR AND GREEN RT GEAR LIGHTS REMAINED ON. COMPLETED LDG GEAR RETRACTION MALFUNCTION CHECK LIST, BOTH LIGHTS REMAINED ON. ABOUT 40 SECONDS LATER, BOTH LIGHTS OUT. CHECKED AND CLEANED RIGHT MAIN LANDING GEAR DOWNLOCK, SENSOR OPERATION NORMAL.

Part: SKIN — CRACKED (FS 480)

A SKIN CRACK, 1.75 INCH BY 2 INCH WAS DISCOVERED BETWEEN STRINGER 27R AND 28R, FS 481. THE PREVIOUS REPAIR ON THIS SECTION MEASURED 5.5 INCH BY 13 INCH. THE REPAIRS WERE INCORPORATED INTO ONE REPAIR AFTER REMOVAL OF PREVIOUS REPAIR. THIS ER/A SUPERCEDES ER/A 233402-14. DURING INSTALLATION OF REPAIR FURTHER CORROSION WAS DISCOVERED AT PREVIOUS CUT OUT. FINAL CUT OUT DIMENSIONS ARE 9 INCHES BY 15 INCHES. REVISION WILL REMOVE CORROSION AND INSTALL A LARGER DOUBLER PER B727 SRM 53-30-3 FIG 3A.

Part: STRINGER — CRACKED (BS 480)

FORWARD LOWER FUSELAGE BS-480 STRINGER 28R SKIN BULGING AND CRACKED. REPAIRED PER DL ERA 302938-14.

Part: BATTERY PACK — DISCHARGED (RT OVERWING)

EMERGENCY LIGHT OUT LOWER RT OVERWING FAIRING. REPLACED EMERGENCY LIGHT BATTERY PACK. CKS NORMAL.

Part: COOLING VALVE — FAILED (AIR CONNECTOR)

DURING CLIMB AND LEVEL AT FL 240, WERE UNABLE TO MAINTAIN, CABIN SLOWEST RATE OF ASSENT WAS 700 FPM. DESCENDED AND RETURNED TO JFK. FOUND EQUIPMENT COOLING VALVE STUCK OPEN. REPLACED VALVE. RETURNED TO SERVICE.

Part: WEB — CRACKED (WL 216 L1 DOOR)

DURING SERVICE CHECK INSPECTION, THE REPLACEMENT WEB PREVIOUSLY INSTALLED AS PART OF THE FRAME REPAIR KIT WAS FOUND CRACKED AT WL 216. IN ACCORDANCE WITH BAC S/B 727-53-0153, R.6., THE EXISTING WEB WAS REPLACED.