N213FE

Part: SKIN — DAMAGED (ZONE 100) · airframe 27,800 hrs · 18,625 cycles

SKIN HAS 2 EA DOUBLE DRILLED HOLES AT BS 970 BETWEEN STRINGERS 24L AND 25L. CUT OUT DAMAGED SKIN IAW SRM 53-30-3, FIG 1. FABRICATED FILLER AND REPAIR DOUBLER IAW SRM 53-30-3, FIG 1. TREATED AND PRIMED REPAIR PARTS IAW SRM 51-10-2. INSTALLED REPAIR FILLER AND DOUBLER IAW SRM 51-30-2 AND 53-30-3, FIG 1.

Part: WEB — CRACKED (ZONE 500) · airframe 27,800 hrs · 18,625 cycles

LT WING FIXED L/E INTERIOR, INBD MOUNT ANGLE FOR NR 1 SLAT ACTUATOR IS CRACKED. REMOVED CRACKED WEB IAW SRM 51-30-2. FABRICATED NEW WEB AND HEAT TREATED WEB TO 7076-T6 IAW EA 75740-152461. TREATED, PRIMED AND INSTALLED NEW WEB AT LT WING INBD MOUNT FOR NR 1 SLAT ACTUATOR IAW SRM 51-10-2 AND EA 7-5740-152461.

Part: SKIN — GOUGED (BS 720D S19L) · airframe 27,800 hrs · 18,625 cycles

LEFT FUSELAGE SKIN GOUGED AT BS 720D PLUS 15" STRINGER 19L. CUT OUT DAMAGE, FABRICATED DOUBLER AND STRUCTURAL FILLER AND INSTALLED REPAIR IAW SRM 53-30-3 FIG 14.

Part: SKIN — CORRODED (BS 990-1030) · corrosion level 2 · airframe 27,800 hrs · 18,625 cycles

CORROSION ON SKIN JUST OTBD OF STRINGER 28L FROM 990 TO 1030. CUTOUT AREA OUT OF LIMITS ON FUSELAGE SKIN DIMENSION 2.5 INCHES BY 1.8750 ", FABRICATED REPAIR DOUBLER FROM 2024T3 .080, DIM 11.3750" BY 9.3750 " IAW SRM 53-30-2, FIG 2 AND 53-30-3, FIG 1. INSTALLED REPAIR DOUBLER IAW SRM 51-30-2 AND 53-30-3, FIG 1.

Part: SKIN — PUNCTURED (RT ELEVATOR) · airframe 27,800 hrs · 18,625 cycles

RIGHT ELEVATOR LOWER SKIN IS PUNCTURED. CUT OUT DAMAGE, FABRICATED REPAIR DOUBLER AND INSTALLED IAW SRM 55-20-3 FIG. 1. THIS REPAIR IS A CATEGORY B REPAIR.

Part: SHEAR TIE — CORRODED (ZONE 100) · corrosion level 2 · airframe 27,800 hrs · 18,625 cycles

CORROSION ON SHEAR TIE AT BS 1148 BETWEEN STRINGER 30 AND 29R. CUT OUT DAMAGED SHEAR TIE IAW SRM 51-10-1 AND 53-10-4, FIG 15, FABRICATED NEW SHEAR TIE IAW SRM 53-10-4 FIG 15. INSTALLED SHEAR TIE IAW SRM 53-10-4, FIG 15.

Part: SHEAR TIE — MISINSTALLED (BS 970 S24-25L) · airframe 27,800 hrs · 18,625 cycles

IMPROPER FASTENERS IN SHEAR TIE AT BS 970 BETWEEN S24-25L. REMOVED SHEAR TIE AND FAIRING SUPPORT FITTING IAW SRM 51-30-2. FABRICATED NEW SHEAR TIE IAW SRM 53-10-2 FIGURE 5 AND 51-30-05. LOCATED AND DRILLED NEW SHEAR TIE AND NEW FAIRING SUPPORT FITTING IAW SRM 51-30-5. TREATED, PRIMED, AND INSTALLED NEW SHEAR TIE AND FAIRING SUPPORT FITTING IAW SRM 51-10-2 AND 51-30-2.

Part: SKIN — DAMAGED (NR 1 NACELLE) · airframe 27,800 hrs · 18,625 cycles

NR 1 ENGINE NOSE COWL T/E SKIN DAMAGED 8 O'CLOCK POSITION. CUT OUT DAMAGED SKIN NOSE COWL NR 1 ENGINE IAW SRM 54-30-3 FIG 3A. FABRICATED AND INSTALLED DOUBLER AND FILLER IAW SRM 54-30-3 FIG 3A.

Part: SPAR — CHAFED (VERTICAL STAB) · airframe 27,800 hrs · 18,625 cycles

VERTICAL STAB RT MID SPAR CHORD IS CHAFED AT AFT END. REMOVED DAMAGED AREA IAW SRM 55-30-6 FIG 3. FABRICATED AND INSTALLED REPAIR ANGLE AND FILLERS IAW SRM 55-30-6 FIG 3.

Part: SEAT TRACK — CORRODED (BS 373) · corrosion level 2 · airframe 27,800 hrs · 18,625 cycles

SEAT TRACK INBD BS 373, LBL 60 HAS CORROSION. REMOVED CORROSION FROM SEAT TRACKIAW SRM 51-10-6. FOUND SEAT TRACK ASSY OUT OF LIMITS IAW B727 SRM 53-10-1 FIGURE 3. REMOVED SEAT TRACK IAW SRM 51-30-2. FABRICATED NEW SEAT TRACK IAW SRM 51-30-5 AND 53-10-2 FIGURE 7. TREATED, PRIMED AND INSTALLED NEW SEAT TRACK IAW SRM 51-10-2 AND 51-30-2.

Part: SEAT TRACK — CORRODED (BS 515-520) · airframe 27,800 hrs · 18,625 cycles

CABIN SEAT TRACK UPPER OTBD FLANGE BS 515 TO 520, RBL 24 HAS CORROSION.

Part: FRAME — CORRODED (BS 950E S28-29R) · corrosion level 2 · airframe 27,800 hrs · 18,625 cycles

CORROSION ON STUB FRAME WEB AT BS 950E, PLUS 5 BOTH FWD AND AFT OF FRAME BETWEEN STRINGERS 29R AND 28R. REMOVED STUB FRAME BS 950E PLUS 5 IAW SRM 51-30-2 FABRICATED, LOCATED AND DRILLED NEW STUB FRAME IAW DRAWING 65-56129 AND SRM 51-30-5. INSTALLED NEW STUB FRAME IAW DRAWING 65-56129 AND SRM 51-30-2.

Part: FLOORBEAM — CORRODED (BS 344) · corrosion level 2 · airframe 27,800 hrs · 18,625 cycles

FLOORBEAM BS 344, LBL 24- RBL24 CORRODED. REMOVED CORROSION AND FOUND OUT OF LIMITS IAW B727 SRM 51-10-6 AND 53-10-1 FIG.5. REMOVED UPPER TEE SECTIONS AND SPLICE REPAIR PARTS IAW SRM 51-30-2. FABRICATED NEW TEE SECTIONS IAW SRM 53-10-8 FIG. 9. TEATED, PRIMED AND INSTALLED NEW TEE SECTIONS AND SPLICE REPAIR PARTS IAW SRM 53-10-8 FIG. 9 AND 51-30-2.

Part: SEAT TRACK — CORRODED (BS 480-560) · corrosion level 2 · airframe 27,800 hrs · 18,625 cycles

CABIN SEAT TRACK BS480 TO 560, LBL60 INBD FLANGE HAS CORROSION SEVERAL PLACES. REMOVED SEAT TRACK SECTION STA 480 - 655 IAW SRM 51-30-2, FABRICATED, LOCATED AND DRILLED NEW SEAT TRACK SECTION IAW SRM 53-10-2 FIG 7 AND 51-30-5. INSTALLED SEAT TRACK IAW SRM 53-10-2 FIG 7 AND 51-30-2.

Part: KEELBEAM — CRACKED (ZONE 100) · airframe 27,800 hrs · 18,625 cycles

RT KEELBEAM CHORD IS CRACKED AT 2ND FASTENER, BS 870, RBL 6, BELOW AND TO THE RT OF THE DUCTING. HFEC INSPECTED AREA AND VERIFIED CRACK, TRIMMED OUT CRACKED AREA AND FABRICATED REPAIR DOUBLER IAW EA 7-5310-152459. HEAT TREATED DOUBLER TO 177 KSI AND CAD PLATED DOUBLER IAW SOPM 20-42-01. PRIMED AND INSTALLED REPAIR IAW SRM 51-10-2 AND EA 7-5310-152459.

Part: FRAME — CORRODED (BS 950E) · airframe 27,800 hrs · 18,625 cycles

CORROSION ON STUB FRAME WEB AT BS 950E PLUSE 5 INCHES, BOTH FWD AND AFT OF FRAME BETWEEN STRINGER 29R AND 28R.

Part: FLOORBEAM — CORRODED (BS 344) · corrosion level 2 · airframe 27,800 hrs · 18,625 cycles

CABIN FLOORBEAM BS 344 UPPER AFT. FLANGE LBL 24 TO 44 HAS CORROSION. UPPER TEE REPAIR ACCOMPLISHED ON NR NOO585.

Part: FLOORBEAM — CORRODED (BS 880) · corrosion level 2 · airframe 27,800 hrs · 18,625 cycles

FLOORBEAM WEB CORRODED BS 880, LBL 45 TO LBL 62. REMOVED CORROSION IAW SRM 51-10-6. NDT INSPECTED AFFECTED AREA IAW EA 7-5310-152465. TREATED AND PRIMED AFFECTED AREA IAW SRM 51-10-2, AND EA 7-5310-152465.

Part: STRINGER — CORRODED (BS 335-360 S4L) · corrosion level 2 · airframe 27,800 hrs · 18,625 cycles

STRINGER 4L HAS AREAS OF CORROSION BS 335 TO 360. REMOVED CORROSION IAW SRM 51-10-6. FOUND OUT OF LIMITS IAW SRM 53-10-1. CUT OUT DAMAGED SECTION IAW EA 3 7-5310-152464. FABRICATED NEW STRINGER SECTION AND SPLICE IAW EA 7-5310-152464. TREATED AND PRIMED NEW SECTION AND SPLICE IAW SRM 51-10-2 AND INSTALLED IAW EA 7-5310-152464.

Part: SPAR — CRACKED (RT WING TE FLAP) · airframe 27,800 hrs · 18,625 cycles

RT WING, INBD FLAP, MID FLAP, MOST INBD NR1 HINGE AREA HAS REAR SPAR CRACKED AT CUT-OUT. REPAIRED SPAR.

Part: SPAR — CRACKED (RT WING TE FLAP) · airframe 27,800 hrs · 18,625 cycles

RT WING, INBD FLAP, MOST INBD NR 2 HINGE AREA HAS REAR SPAR CHORD CRACKED AT CUT-OUT. CUT OUT DAMAGED SECTION OF SPAR IAW SRM 51-40-4 FIG 3. FABRICATED NEW SPAR SECTION AND SPLICE IAW SRM 51-40-4 FIG 3 AND 57-50-2 FIGURE 5. TREATED, PRIMED AND INSTALLED NEW SPAR SECTION AND SPLICE ANGLE IAW SRM 51-30-2, 51-40-4 FIGURE 3, AND EA 7-5750-152462.

Part: LIGHT — INOPERATIVE (COCKPIT) · airframe 27,699 hrs · 18,520 cycles

WHILE COCKING ACFT, FOUND COCKPIT EMERGENCY EXIT LIGHT INOP IN ARMED/ON POSITION. REPLACED LIGHT REF MM 33-50-101-2-0. GROUND OPS CK NORMAL AT THIS TIME. ACFT OK FOR SERVICE. PREMATURE REMOVAL/INSTALLATION.

Part: ACTUATOR — FAILED (NR 2 SLAT) · airframe 27,617 hrs · 18,460 cycles

NR 2 SLAT FAILED TO RETRACT. RAN QRH AND NO HELP IAW QRH, FLAPS SET TO 5 DEG AND THEN RAN CONFIGURED ON SCHEDULE FOR RTB MEM. DISCONNECTED THE CONNECTOR PLUG ON THE NR 2 LT SLAT ACTUATOR AND LIGHT WENT OUT. REMOVED NR 2 SLAT ACTUATOR AND CHECKED ADJUSTMENT OF THE SWITCH (ADJ SWITCH TYPE ACTUATOR). COULD NOT ADJUST THE SWITCH TO AMM SPECS. REPLACED ACTUATOR ASSY WITH NON ADJUSTABLE SWITCH TYPE REF AMM 727-200-27-81-032-4. OPS AND LEAK CK WAS GOOD. L/E LIGHTS NOW ARE WORKING CORRECTLY.

Part: ACTUATOR — FAILED (NR 2 SLAT) · airframe 27,612 hrs · 18,454 cycles

DURING FLAP RETRACTION, NR 2 SLAT REMAINED IN TRANSIT IAW QRH, EXTENDED FLAPS TO 2 DEGREES. HAD NORMAL INDICATIONS. RETRACTED FLAPS AGAIN AND NR 2 SLAT DID NOT RETRACT. ACFT APPEARED TO FLY NORMAL. NO UNDUE CROSS CORRECTION. INSTALLED NEW NR 2 ACTUATOR PER MM 27-81-032-4. RAN SLATS UP AND DOWN SEVERAL TIMES AND NO LEAKS NOTED. INSTALLED ALL REMOVED PANELS. OK FOR SERVICE.

Part: ACTUATOR — FAILED (NR 2 SLATS) · airframe 27,612 hrs · 18,454 cycles

DURING FLAP RETRACTION, NR 2 SLAT REMAINED IN TRANSIT IAW QRH, EXTENDED FLAPS TO 2 DEGREES. HAD NORMAL INDICATIONS. RETRACTED FLAPS AGAIN AND NR 2 SLAT DID NOT RETRACT. ACFT APPEARED TO FLY NORMAL. NO UNDUE CROSS CORRECTION. INSTALLED NEW NR 2 ACCUATOR IAW MM 27-81-032-4. RAN SLATS UP AND DOWN SEVERAL TIMES AND NO LEAKS NOTED.

Part: SLIDE — MISALIGNED (DOOR) · airframe 27,148 hrs · 18,103 cycles

DOOR SLIDE PRESSURE GAUGE UNREADABLE. REMOVED AND REPOSITIONED SLIDE IN DOOR COVER REF AMM 25-60-015-2-0.

Part: ENGINE — FAILED (NR 3) · airframe 26,134 hrs · 17,293 cycles

NR 3 ENG FIRE WARNING INDICATION. SHUT DOWN ENG IAW QRH. INDICATION PERSISTED. BLEW BOTH FIRE BOTTLES. INDICATION PERSISTED INTERMITTENTLY THROUGHOUT LANDING AND TAXI-IN. NR 3 ENG WINDMILLED FOR 6 MINS. UNABLE TO DETERMINE IF OIL PRESS WAS GREATER THAN 10 PSI. PER MM 72-00-00, PAGE 531, ITEM I-1D, ENG MUST BE DISASSEMBLED FOR A OIL SYSTEM COMPONENTS EXAMINATION. ENG CHANGE REQUIRED. OPEN

Part: ANGLE — CRACKED (RT WING) · airframe 25,937 hrs · 17,142 cycles

CRACKED LOWER ANGLE FALSE SPAR AT SPOILER NR 8 RT WING. REMOVED SPAR DOUBLER & INBD WEB SECTION IAW SRM 51-30-2. FABBED NEW DOUBLER IAW SRM 51-30-2 & DWG NR SR 27-57-038 REV C. FABBED NEW INBD WEB SECTION IAW DWG NR SR 27-57-038 REV C & SRM 51-30-2. FABBED 2 ANGLES IAW DWG NR SR 27-57-038 REV C & 51-30-5. HEAT TREATED NEW DOUBLER & HEAT TREATED NEW ANGLES IAW NDTM PT 6 51-00-00 FIG 20 & ER 2-37153-801 REV A. CUT LOWER SECTION IAW DWG NR SR27-57-038 REV C. FABBED INBD LOWER SECTION IAW DWG NR SR 27-57-038 REV C & SRM 51-30-5. FABBED NEW STRAP IAW DWG NR SR 27-57-038 REC C & SRM 51-30-5. TREATED PRIMED REPAIR PART IAW SRM 51-10-2 & INSTALLED REPAIR PART IAW DWG NR SR27-57-038 REV C.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 25,937 hrs · 17,142 cycles

SKIN AT STA 1290 STR 20R HAS TOOLING MARKS, FASTENERS WITH IMPROPER ED AND THE SKIN IS BULGING. REMOVED PREVIOUS REPAIR IAW B727 SRM 51-30-02. CUT-OUT DAMAGE PER B727 SRM 51-10-01, FABRICATED REPAIR DOUBLER IAW B727 SRM 53-30-3 & 53-30-2 FIG 3. FABRICATED TRIPLER IAW B727 SRM 53-30-3 & 53-30-2 FIG 3. TREATED AND PRIMED DOUBLERS IAW B727 SRM 51-10-2. INSTALLED REPAIR DOUBLERS IAW B727 SRM 51-30-2 & 53-30-03 FIG 5.

Part: WIRE HARNESS — BURNED (ZONE 100) · airframe 25,410 hrs · 16,682 cycles

WHILE WORKING WRI 31-30/9464, TECH FOUND A SHORTED WIRE HARNESS IN AVIONICS COMPT. THE 3 PHASE WIRE HARNESS FROM THE EXTERNAL POWER RELAY HAS MADE CONTACT WITH GND BUS STRIP T268 (LOCATED DIRECTLY ABOVE APU GCU). INITIAL VISUAL INSPECTION SHOWS SEVERAL GND STUDS ARE BURNED/DAMAGED, ONE OR MORE WIRES FROM EPR ARE DAMAGED AND A SECOND HARNESS LOCATED IN THE SAME AREA APPEARS TO BE DAMAGED. INSTALLED T00268 PER WDM 91-21-41 PG 37, EXT POWER FEEDER CABLES PER WDM 91-21-11 PG 1, UP LIST 91-21-11 PG1 AND AS PER MM 20-20-00, BOEING SWPM CHAPT 20. REF EA 7-2440-119592 USE OF ORIGINAL TERMINAL STRIP IN REVERSE POSITION.

Part: WINDSHIELD — CRACKED (COCKPIT) · airframe 25,266 hrs · 16,577 cycles

AT APPROX 27000' ON CLIMB-OUT, CAPT'S L-1 WINDOW CRACKED/SHATTERED AND BEGAN ARCING. COMPLIED WITH RED TABS PROCEDURES. RETURNED TO MEMPHIS. REMOVED CAPT'S NR 1 WINDOW AND COMPLIED WITH PREPARATION FOR INSTALL IAW B727-200 AMM 56-11-011-4. COMPLETED INSTALLATION OF WINDSHIELD AND APPLIED AERODYNAMIC SEALANT REF 727-200 AMM 56-11-011-4. REINSTALLED GLARESHIELD PER 7272-200 AMM 25-10-062-4.

Part: UNKNOWN — GROUND DAMAGE (FUSELAGE) · airframe 23,735 hrs · 15,432 cycles

AIRCRAFT DAMAGED ON PUSHBACK, ON BELLY. REPAIRED AND INSPECTED.

Part: REPAIR — UNDAMAGED (FORE FLAP) · airframe 23,703 hrs · 15,401 cycles

FOUND REPAIR RT INBD FORE FLAP. LEADING EDGE REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION, AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA, PREVIOUSLY INSTALLED REPAIR AT RT INBD FORE FLAP WAS DETERMINED TO BE IAW SRM 57-50-4 FIG 1. BASED ON AN EXTERNAL VISUAL EVALUATION WITH REPAIR INSTALLED.

Part: REPAIR — UNDAMAGED (KRUGER FLAP) · airframe 23,703 hrs · 15,401 cycles

FOUND REPAIR TOP SIDE NR 3 L/E KRUGER FLAP LT WING. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. PREVIOUSLY INSTALLED REPAIR AT NR 3 L/E KRUGER FLAP, TOP SIDE ON LT WING WAS DETERMINED TO BE IAW SRM 57-50-3 FIG 3. BASED ON AN EXTERNAL VISUAL EVALUATION WITH REPAIR INSTALLED.

Part: REPAIR — DAMAGED (FORE FLAP) · airframe 23,703 hrs · 15,401 cycles

FOUND REPAIR LT I/B FORE FLAP, L/E REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. PREVIOUSLY INSTALLED REPAIR AT LT I/B, FORE FLAP WAS DETERMINED TO BE IAW SRM 57-50-4 FIG 1. BASED ON AN EXTERNAL VISUAL EVALUATION WITH REPAIR INSTALLED. REPAIR CLASSIFIED AS MAJOR. BASED ON GMM 6-2-100 CRITERIA.

Part: REPAIR — UNDAMAGED (FUSELAGE) · airframe 23,703 hrs · 15,401 cycles

FOUND REPAIR STA 500-520 LT BOTTOM FUSELAGE SKIN, BELOW MAIN CARGO DOOR. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. PREVIOUSLY INSTALLED REPAIR AT FS 500-FS520 S24L-S25L WAS DETERMINED TO BE IAW SRM 53-30-3 FIG 3. BASED ON AN EXTERNAL VISUAL EVALUATION WITH REPAIR INSTALLED. REPAIR IS CLASSIFIED AS MAJOR BASED ON GMM 6-2-100 CRITERIA.

Part: REPAIR — UNDAMAGED (KRUGER FLAP) · airframe 23,703 hrs · 15,401 cycles

FOUND REPAIR AT NR 4 L/E KRUGER FLAP, RT WING TOP SIDE. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. PREVIOUSLY INSTALLED REPAIR AT NR 4 L/E KRUGER FLAP, RT WING TOP SIDE WAS DETERMINED TO BE IAW SRM 57-50-3 FIG 3. BASED ON AN EXTERNAL VISUAL EVALUATION WITH REPAIR INSTALLED. REPAIR IS CLASSIFIED AS A MAJOR REPAIR BASED ON GMM 6-2-100 CRITERIA.

Part: STRINGER — UNDAMAGED (BS 1030) · airframe 23,703 hrs · 15,401 cycles

FOUND REPAIR AT STA 1030, RT SIDE OF FUSELAGE AT CUSP. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. PREVIOUSLY INSTALLED REPAIR AT FS STA 1030 RT S 17R WAS DETERMINED TO BE IAW SRM 53-30-3 BASED ON AN EXTERNAL VISUAL EVALUATION WITH REPAIR INSTALLED.

Part: SKIN — UNDAMAGED (BS 1135) · airframe 23,703 hrs · 15,401 cycles

FOUND REPAIR AFT CARGO COMPARTMENT STA 1135 RBL 8, REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. PREVIOUSLY INSTALLED REPAIR AT STA 1135 RBL 8 WAS DETERMINED TO BE IAW SRM 53-10-5 FIG 4 SHT 1 SHT 5 BASED ON AN EXTERNAL VISUAL EVALUATION WITH REPAIR INSTALLED.

Part: SKIN — UNDAMAGED (BS 1080) · airframe 23,703 hrs · 15,401 cycles

FOUND REPAIR AFT CARGO COMPARTMENT STA 1080, LBL3. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. PREVIOUSLY INSTALLED REPAIR AT STA 1080 LBL 3 WAS DETERMINED TO BE IAW SRM 53-10-5 FIG 4 BASED ON AN EXTERNAL VISUAL EVALUATION WITH REPAIR INSTALLED.

Part: REPAIR — UNDAMAGED (BS 1010) · airframe 23,703 hrs · 15,401 cycles

FOUND REPAIR AFT CARGO COMPARTMENT STA 1010 RBL 8, REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. PREVIOUSLY INSTALLED REPAIR AT STA 1010, RBL 8 WAS DETERMINED TO BE IAW SRM 51-40-4-FIG 1, BASED ON EXTERNAL VISUAL EVALUATION WITH REPAIR INSTALLED.

Part: SKIN — UNDAMAGED (BS 1105) · airframe 23,703 hrs · 15,401 cycles

FOUND REPAIR AFT, CARGO COMPARTMENT STA 1105, RBL 5. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. PREVIOUSLY INSTALLED REPAIR AT STA 1105, RBL 5 WAS DETERMINED TO BE IAW SRM 53-10-5 FIG 4 BASED ON AN EXTERNAL VISUAL EVALUATION WITH REPAIR INSTALLED.

Part: SKIN — UNDAMAGED (BS 560-620) · airframe 23,703 hrs · 15,401 cycles

FOUND REPAIR FORWARD CARGO COMPARTMENT, STA. 560- STA 620 RBL 20. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. PREVIOUSLY INSTALLED REPAIR AT STA 560 STA 620 RBL 20 WAS DETERMINED TO BE IAW SRM 51-40-4 FIG 1 SHT 8 ZEE SECTION, BASED ON EXTERNAL VISUAL EVALUATION WITH REPAIR INSTALLED.

Part: SKIN — DENTED (BS 1050) · airframe 23,703 hrs · 15,401 cycles

EXTERNAL FUSELAGE SKIN DENTED BS 1050 S-17R. CHECKED LIMITS MEASURED DENT .900 WIDE .750 LONG AND .055 DEEP A/Y =13.6 OUT OF LIMITS IAW SRM 53-10-1 FIG 1 SHEET 3 DETAIL II. NDT PERFORMED NO CRACK NOTED, FABRICATED DOUBLER AND CUT OUT DAMAGE. INSTALLED DOUBLER IAW SRM 53-30-2, PAINTED IAW SRM 51-20-151-7, CLASSIFIED AS MAJOR REPAIR.

Part: FLOORBEAM — CORRODED (BS 1090-1110) · airframe 23,703 hrs · 15,401 cycles

LATERAL / LONGITUDINAL FLOORBEAM HAS SEVERAL CORRODED NUT PLATES AND SURFACE UNDER NUT PLATES ,FROM STA. 1090 TO 1110 BL 0 TO RBL 15., REMOVED CORROSION ON LWR. CHORD .090 BEFORE REWORK .040AFTER REWORK OUT OF LIMITS. IAW SRM 53-10-1. REMOVED CORRODED NUT PLATES AND CORROSION ON LWR SURFACE OF BL 0 CHORD .090 BEFORE REWORK.050 AFTER REWORK OUT OF LIMITS IAW SRM 53-10-.REMOVED FLOORBEAM IAW SRM 51-30-2 STA 1080-1166. REMOVED SPLICE IAW SRM 51-30-2 REMOVED ANGLE& STIFFENER STA. 1070 IAW SRM 51-30-2. REMOVED CEILING SUPPORT IAW SRM 51-30- 2.REMOVED SPLICE PLATE STA.1160 IAM SRM 51-30-2. LOCATED & DRILLED NEW LWR. CHORD 51-10-5.INSTALLED ANGLE, STIFFENER LWR. CHORD & SPLICES IAW SRM 51-30- 2

Part: FLAP TRACK — CORRODED (NR 3 FLAP) · airframe 23,703 hrs · 15,401 cycles

NR 3 FLAP TRACK AFT MOUNT PAD HAS HEAVY CORROSION. REPLACED FLAP TRACK WITH SERVICEABLE FLAP TRACK IAW MM 27-51-031-4.

Part: FLAP TRACK — CORRODED (NR 6) · airframe 23,703 hrs · 15,401 cycles

NR 6 FLAP TRACK HAS CORROSION ON AFT MOUNT PAD. REPLACED FLAP TRACK WITH SERVICEABLE FLAP TRACK IAW MM 27-51-031-4.

Part: FLAP TRACK — CORRODED (NR 6) · airframe 23,703 hrs · 15,401 cycles

NR 6 FLAP TRACK HAS CORROSION ON AFT MOUNT PAD. REPLACED FLAP TRACK WITH SERVICEABLE FLAP TRACK IAW MM 27-51-031-4.

Part: FLOORBEAM — CORRODED (BS 344) · airframe 23,703 hrs · 15,401 cycles

MDCC - FLOORBEAM BS 344 LBL-14-40 HAS SURFACE CORROSION. REMOVED CORROSION IAW SRM 51-10-6, BEFORE REMOVED MATERIAL 0.110 AFTER 0.104 WITHIN LIMITS IAW SRM 51-10-1. TREATED AND PRIMED IAW SRM 51-10-2.

Part: FLOORBEAM — CORRODED (BS 560) · airframe 23,703 hrs · 15,401 cycles

MDCC - FLOORBEAM BS 560 LBL21 HAS CORROSION. REMOVED CORROSION IAW SRM 53-10-1MAT LOSS OF .001 ORIGINAL THICKNESS OF 0.230 FOUND TO BE WITHIN LIMITS IAW SRM 51-10-6 TREATED AND PRIMED IAW SRM 51-10-2.

Part: FLOORBEAM — CORRODED (BS 312) · airframe 23,703 hrs · 15,401 cycles

MDCC - FLOORBEAM CORRODED BS 312 LBL-42. REMOVED CORROSION IAW SRM 53-10- 1 MATERIAL LOSS OF 0.007 ORIGINAL THICKNESS 0.080 , FOUND TO BE WITHIN LIMITS PER SRM 53-10-1 FIG 5. TREATED AND PRIMED AREA IAW SRM 51-10-2.

Part: FLOORBEAM — CORRODED (BS 1166) · airframe 23,703 hrs · 15,401 cycles

FLOORBEAM HAS SEVERAL CORRODED FASTENERS NUT PLATES AND SURFACE UNDER NUT PLATES. BS 1166 FROM RBL 27 TO OB END. REMOVED CORRODED NUT PLATES IAW SRM 51-31-2 REMOVED CORROSION IAW SRM51-10-6,CHECKED LIMITS . ORIGINAL MATERIAL: .125 AFTER REWORK: .118 WITH IN LIMITS IAW SRM 53-10--1 PG 1. TREATED AND PRIMED IAW SRM 51-10-2, INSTALLED NUT PLATES IAW SRM 51-30-2.

Part: ACTUATOR — LEAKING (KRUEGER FLAP) · airframe 23,419 hrs · 15,205 cycles

LOSS SYSTEM-A HYDRALICS IN FLIGHT. COMPLETED QRH/RED TAB PROCEDURES. SYSTEM-A FLUID SHUTOFF SWITCHED CLOSED AT 1032, LANDED AT 1048. *S/D* REMOVED AND REPLACED A-HYD SYS PRESS FILTERS PER M/M 29-11-062-3, NO CONTAMINATION FOUND. REMOVED AND REPLACED A-HYD SYS CASE DRAIN FILTERS PER M/M 29-11-041-2, NO CONTAMINATION FOUND. REMOVED AND REPLACED NR 4 KRUEGER FLAP ACT PER M/M 27-81-022-4. SERVICED HYD SYS-A PER M/M 12-12-000-2.

Part: SENSOR — MALFUNCTIONED (AOA) · airframe 23,389 hrs · 15,186 cycles

ON DEPARTURE AT APPROX 1000 FT AGL CALLED FOR QUIET EPP, FLAPS 5 DEGREES, STICK SHAKER INITIATED AT FLAPS 15 DEGREES, SPEED 160 KIAS, APPEARED TO ACTIVATE 15 KTS ABOVE MMS DURING CLIMBOUT. VIBRATED ONCE AT 8 - 10 KTS ABOVE BUG SPEED AT FLAPS 30 DEGREES, GEAR DOWN THEN WORKED WELL AT BUG 5 - 10 KTS. REMOVED & REPLACED AOA SENSOR IAW MM 34-18-051. OP'S CHECK GOOD IAW MM 34-18-001.

Part: STICK SHAKER — ACTIVATED (STALL WARNING) · airframe 23,388 hrs · 15,184 cycles

DURING TAKEOFF, AIRSPEED BUGS SET CORRECTLY GOT STICK SHAKER AT MMS 15 ADVANCED TO FIREWALL POWER APPROX 16 SEC. CLEANED UP, ACCELERATED STICK STOPPED AT 0 MMS 30 (230 KTS) STICK SHAKER RETURNED AND REMAINED ON THROUGH OUT APPROACH.

Part: WARNING LIGHT — ILLUMINATED (COCKPIT)

ON CLIMB NR 1 ENG STRUT OVERHEAT LIGHT ILLUM. REMOVED AND REPLACED HIGH PRESSURE SUPPLY LINE PER MAINT PRACTICE.

Part: LINE — LEAKING (THRUST REVERSER)

NR 1 ENG STRUT O/H IL FOR 5 SEC. RAN RED TABS WING A/I SWITCH WAS CK. SYS TEST GOOD. REMOVED AND REPLACED LEAKING FLEX LINE PER SMP AND OPS CK NORM PER MM 26-14-000-5.

Part: LINE — FAILED (NR 1 ENGINE)

00-360 REPEAT WRITE-UP, AFT TO BOTH ENGINE AND WING A/I OFF THE NR 1 ENGINE STRUT OVERHEAT LIGHT CAME ON. SUSPECT AIR LEAK IN STUB WING. ** S/D ** R&R BUSTED BRAIDED LINE. LEAK CK GOOD USING APU AIR MM STANDARD PRACTICES. OK FOR SERVICE.

Part: CONTROL UNIT — FAULTY (NR 1 ENGINE)

00-358 AFT T/O, NR 1 ENGINE STRUT OVERHEAT LIGHT CAME ON. RED TAB ACCOMPLISHED. R&R CONTROL UNIT PER IAW MM 26-14-0. NO FAULTS NOTED.

Part: CONTROL UNIT — MALFUNCTIONED (E&E COMPT)

99-194 - FIRE WARN BELL AND CAPT AND 1ST OFF FIRE WARNING LIGHTS CAME ON. CHANGED THE ENGINE FIRE DETECTION PANEL PER MM 26-11-001-0. OPS CK GOOD.

Part: FIRE WARNING — ACTIVATED (COCKPIT)

99-178 - AT FLT LEVEL 280, W/THRUST AT CR PWR RECEIVED MULTIPLE INTERMITTENT MASTER FIRE WARN LIGHT AND FIRE BELL. ENG OIL TEMP INCREASED TO 138 DEG, ALL OTHER ENG INSTRUMENT NORM. RETARD NR 3 THROTTLE TO IDLE. START DUCT REALIGNED AND SECURED PER MM 36-00-001-2. ENG RUNS C/O AT FULL PWR PER JET RUN HDBK 6-15. ALL LIMITS OBSERVED. AC OK FOR SERVICE.

Part: TURBINE — FAILED (NR 2 ENGINE)

NR 2 ENGINE WAS SHUTDOWN VIBRATION ENDED WITH ENGINE SHUTDOWN. ENGINE TURBINE BLADES BROKEN AND CRACKED. *S/D* REMOVED AND REPLACED NR 2 ENGINE PER WORK CARD 70T0002, OPER AND LEAK CK GOOD.

Part: RETRACT MECH — MALFUNCTION (NLG DOOR)

ON TAKEOFF WHEN LANDING GEAR WAS RETRACTED NOSE GEAR DOOR A REMAINED ON. NOISE IN NOSE GEAR AREA CONFIRMED DOORS WERE NOT CLOSED. GEAR WAS RECYCLED AND ALL FURTHER OPERATIONS WERE NORMAL. ADJUSTED BOTH NOSE GEAR DOOR SWITCHES AS PER MAINTENANCE MANUAL 32-62-11 PAR 3-B PAGE 402 AND 403, OPERATIONAL CHECK GOOD.

Part: LOCK ACTUATOR — DAMAGED (NLG)

NOSE GEAR FAILED TO RETRACT WHEN GEAR HANDLE WAS PLACED UP. FOLLOWED RED TAB PROCEDURES AND RETURNED TO BASE. FOUND NOSE GEAR LOCK ACTUATOR DAMAGED. REMOVED AND REPLACED NOSE GEAR LOCK ACTUATOR PER MAINTENANCE MANUAL 32-33-11. OPERATIONAL CHECK OK. OK FOR SERVICE.

Part: CONTROL VALVE — INOPERATIVE (TE FLAPS)

INBOARD TRAILING EDGE FLAPS FAILED TO EXTEND, INBOARD ALTERNATE FLAP CIRCUIT BREAKER POPPED WHEN ALTERNATE FLAP SWITCH ACTUATED. REPLACED INBOARD FLAP CONTROL VALVE PER 727-200 MAINTENANCE MANUAL CHAPTER 27-51-51. SERVICED HYDRAULIC SYSTEM, RIGGED SYSTEM PER MAINTENANCE MANUAL.

Part: SKIN — CRACKED (BS 1223)

CRACK IN CORNER OF SKIN BS 1223 LBL 16 WL 148. REPAIRED CRACK IN CORNER OF SKIN AT BS 1223 LBL 16 WL 148 PER FEDEX EA 7-5330-26829.

Part: SKIN — DENT (BS 512)

THE FUSELAGE SKIN IS DENTED AT BS 512 BETWEEN STR 26 TO 27L. REMOVED DENT AND REPAIRED WITH DOUBLER AT BS 512 BETWEEN STR 26 TO 27L IAW FEDEX SRM 53-30-3.

Part: SKIN — CRACKED (BS 1223)

CRACK IN CORNER OF SKIN, BS 1223, LBL 16, WL 148. REPAIRED CRACK IN CORNER OF SKIN, BS 1223, LBL 16, WL 148, PER FEDEX EA 7-5330-26829.

Part: SKIN — CRACKED (RT ELEVATOR)

DUE TO SEVERAL DISCREPANCIES CONSISTING OF CRACKS AND WORN FASTENER HOLES, RT ELEVATOR REQUIRED REPLACEMENT. REMOVED AND REPLACED RT ELEVATOR PER FEDEX MM 27-30-0, 27-30-01, 27-30-21, 27-30-05, 27-30-11. FUNCTIONAL TEST PER FEDEX MM 27-30-01 CHECKS GOOD.

Part: SKIN — GOUGED (BS 527)

THERE IS A GOUGE IN FUSELAGE SKIN EXTERIOR AT BS 527, WL 192 BETWEEN STR 18 - 19L.

Part: FIRE LOOP — MALFUNCTIONED (NR 1 ENGINE)

INTERMITTENT FIRE WARNING NR 1 ENG FOLLOWED BY CONTINUOUS INTERMITTENT WARNING ON SAME. COMPLIED WITH PROCEDURE AND SHUTDOWN NR 1 ENG WARNING, PERSISTED. FIRED NR 1 AND NR 2 BOTTLE INTO NR 1 ENG PER PROCEDURE. WARNING PERSISTED INTERMITTENTLY TILL TOUCHDOWN AND TAXI TO PARKING. REMOVED AND REPLACED NR 1 ENG FIRE DETECT ELEMENT AS PRECAUTION. ALSO, CK'D INLET AND EXT-RAN NR 1 PNU DUCTS. ALL OK AND PYLON AREA. REMOVED AND REPLACED 2 EA BOTTLE ASSY PER MM 26-21-1, DUE TO DISCHARGE. FOUND NR 1 ENG A-LOOP INOP. SUSPECT MOISTURE IN FIRE DETECT BOX. DEFERRED PER 26-6(A) CNT NR 1219105 EXP 12-29-95.