# Service difficulty reports: N278FE, cancelled Aug 27, 2013

A list on [N278FE, cancelled Aug 27, 2013](https://openairdocs.org/deregistered/N278FE-2013-08-27.md).

Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. Newest first.

Page 1 of 2 · 71 reports

- [SDR FDEA201111114877](https://openairdocs.org/sdr/FDEA201111114877.md): Unknown · malfunctioned · Nov 11, 2011 · N278FE · Boeing 727233 · Attitude Gyro and Indicating System
  > AFTER BLOCK-OUT, COMPASS FLAG CAME INTO VIEW ON CAPTAIN'S HSI. COMPLIED WITH QRH PROCEDURES, RESOLVED COMPASS FLAG NO LONGER IN VIEW. AFTER TAKEOFF COMPASS FLAG REAPPEARED. RETURNED. REPLACED FLIGHT INSTRUMENT ACCESSORY UNIT PER MM 34-62-061-4, CHECKED
- [SDR FDEA201006192073](https://openairdocs.org/sdr/FDEA201006192073.md): Battery Pack · inoperative · Jun 19, 2010 · N278FE · Boeing 727233 · Emergency Lighting
  > EMERGENCY EXIT LIGHT ON BOTH DOORS INOP. REPLACED EMERGENCY EXIT LIGHT BATTERIES. OPS CHECK GOOD FOR SERVICE AT THIS TIME. FINAL CLOSED.
- [SDR FDEA201004141182](https://openairdocs.org/sdr/FDEA201004141182.md): Manifold · failed · Apr 14, 2010 · N278FE · Boeing 727233 · Fuel Heater
  > AFTER T/O NR 1 ENG FIRE LIGHT ON NR 1 FIRE DETECT LOOP. PWR REDUCED ON NR 1 ENG IAW QRH. NR 1 FIRE LIGHT WENT OUT. FIRE DETECT LIGHT REMAINED ON. FIRE DETECT LIGHT OUT WHEN FIRE HANDLE PULLED. NO OTHER ABNORMAL INDICATIONS NOTED. R & R FUEL HEAT MANIFOLD.
- [SDR FDEA201004141180](https://openairdocs.org/sdr/FDEA201004141180.md): Fire Loop · false activation · Apr 14, 2010 · N278FE · Boeing 727233 · Fire Detection
  > AFTER T/O NR 1 ENG FIRE LIGHT ON NR 1 FIRE DETECT LOOP. POWER REDUCED ON NR 1 ENG IAW QRH. NR 1 FIRE LIGHT WENT OUT. FIRE DETECT LIGHT REMAINED ON. FIRE DETECT LIGHT OUT WHEN FIRE HANDLE PULLED. NO OTHER ABNORMAL INDICATIONS NOTED. TRACKING NR 10-1182.
- [SDR FDEA201001290287](https://openairdocs.org/sdr/FDEA201001290287.md): Engine · malfunctioned · Jan 29, 2010 · N278FE · Boeing 727233 · Engine Oil Pressure
  > THRUSH LEVER BROUGHT BACK TO IDLE FOR DESCENT. NR 2 LOW OIL PRESSURE OR FILTER BYPASS LIGHT CAME ON, WENT OUT, CAME BACK ON. AT THAT TIME OIL QTY SLOWLY REDUCED TO 1 GALLON WITH OIL PRESSURE IN YELLOW BAND. FOLLOWED QRH WITH ENG SHUTDOWN. ENG WINDMILLED FOR
- [SDR FDEA200911053853](https://openairdocs.org/sdr/FDEA200911053853.md): Relay · false activation · Nov 5, 2009 · N278FE · Boeing 727233 · Door Warning System
  > AFTER DEPARTING EWR AND CLIMBING THROUGH 16000 FT MAIN CARGO DOOR "B" LIGHT ILLUMINATED. COMPLIED WITH QRH AND RETURNED TO DEPARTURE. RELEASED FOR SERVICE IAW MEL: 52-15-01. REMOVED AND REPLACED CARGO DOOR WARNING SYS "B". RELAY R9107. OPS CHECKS NORMAL I
- [SDR FDEA200906232245](https://openairdocs.org/sdr/FDEA200906232245.md): Skin · damaged · Jun 23, 2009 · N278FE · Boeing 727233 · Fuselage Main, Plate/Skin
  > 5 EA OEM HOLES AT RIVET HOLES BETWEEN BS 610 - 600 STR 3L. CUT-OUT DAMAGED AREA (INNER SKIN) DIM: 3.2500" X 1" AND 2.7500" X 1", FAB NEW FILLER FOM 2024T3.040, PO NR 9008328, DIM: 3.2500" X 1" AND 2.7500" X 1", HFEC AREA WITH NO DEFECT NOTED, TREATED, PRIME
- [SDR FDEA200906222202](https://openairdocs.org/sdr/FDEA200906222202.md): Sill · damaged · Jun 22, 2009 · N278FE · Boeing 727233 · Fuselage Miscellaneous Structure
  > DRILLED HOLE HAS SHORT "ED" CENTER LONGERON FITTING. DRILLED HOLE FOUND TO BE PART OF P TO F CONVERSION MOD AND FOUND TO BE STRUCTURALLY ACCEPTABLE IAW EA 7-5310-126827 STEP 13.
- [SDR FDEA200906202190](https://openairdocs.org/sdr/FDEA200906202190.md): Hinge · worn · Jun 20, 2009 · N278FE · Boeing 727233 · Cargo/Baggage Doors
  > MCD AFT END SECTION OF HINGE HAS PLAY. REMOVED, FABRICATED, AND INSTALLED MCD AFT END SECTION OF HINGE P.O. 79014501, PN NR 5212791, DIM: 42" - UPPER, AND 20" - LOWER. IAW P - F SRM ER 01-049 AND SRM 51- 30-2, 51-30-5, 51-30-8. MCD LEAK AND OPS CHECKED GOOD
- [SDR FDEA200906202189](https://openairdocs.org/sdr/FDEA200906202189.md): Hinge · worn · Jun 20, 2009 · N278FE · Boeing 727233 · Cargo/Baggage Doors
  > MCD FWD END SECTION OF HINGE HAS PLAY REMOVED, FABRICATED AND INSTALLED MCD FWD END SECTION OF HINGE P.O. NR 79014501, PN 5212791, DIM: 45" UPPER, AND 20" LOWER IAW FX P TO F SRM ER-01-049 AND SRM 51-30-2, 51-30-5, 51-30-8. MX LEAK AND OPS CHECKED GOOD IA
- [SDR FDEA200906132064](https://openairdocs.org/sdr/FDEA200906132064.md): Skin · damaged · Jun 13, 2009 · N278FE · Boeing 727233 · Fuselage Main, Plate/Skin
  > 5 EA. OEM HOLES ALONG RIVET LINE BETWEEN BS 610-600 STR 3L. CUT-OUT DAMAGED AREA. FABRICATED NEW FILLERS HFEC INSPECTED AREA WITH NO DEFECTS NOTED, TREATED, PRIMED AND INSTALLED NEW FAB PARTS, ALL IAW EA 7-5310-126827, SRM 51-10-2, AND NDTM 51-00-00 FIG 23 P
- [SDR FDEA200906122049](https://openairdocs.org/sdr/FDEA200906122049.md): Sill · damaged · Jun 12, 2009 · N278FE · Boeing 727233 · Fuselage Miscellaneous Structure
  > 1 EA OEM HOLE AT MCK CUT-OUT BS 620 STR 4L. ACCOMPLISHED REPAIR IAW EA 7-5310-126827 BY TRIMING OUT OPEN HOLE IN SKIN BS 620, STR 4L, PERFORMED HFEC INSP OF TRIMMED EDGE TO ENSURE NO CRACKS AND NO FINDINGS NOTED. TRIMMED ADDITIONAL.040 INSURANCE CUT AND FAB
- [SDR FDEA200906122054](https://openairdocs.org/sdr/FDEA200906122054.md): Sill · damaged · Jun 12, 2009 · N278FE · Boeing 727233 · Fuselage Miscellaneous Structure
  > 1 EA OEM HOLE AT RIVET HOLE BS 520 S3L. CUT-OUT DAMAGED AREA, FABRICATED NEW FILLER REPAIR, HFEC INSPECTED AREA IAW NDTM 51-00-00 FIG 23 PT6. TREATED PRIMED & INSTALLED FILLER REPAIR ALL IAW SRM 51-10-2 & EA 7-5310-126827.
- [SDR FDEA200906122053](https://openairdocs.org/sdr/FDEA200906122053.md): Sill · damaged · Jun 12, 2009 · N278FE · Boeing 727233 · Fuselage Miscellaneous Structure
  > 7 EA. OEM HOLES ALONG RIVET LINE BETWEEN BS 500-490 S3L. CUT-OUT DAMAGED AREA. FABRICATED NEW FILLER REPAIR, TREATED AND PRIMED, HFEC INSPECTED AREA IAW NDTM 51-00-00 FIG 23 PT6 WITH NO DEFECT NOTED. INSTALLED REPAIR FILLERS IAW EA 7-5310-126827 DATED: 06-09
- [SDR FDEA200906122051](https://openairdocs.org/sdr/FDEA200906122051.md): Sill · damaged · Jun 12, 2009 · N278FE · Boeing 727233 · Fuselage Miscellaneous Structure
  > 1 EA OEM HOLE NEXT TO RIVET HOLE MCD FUSELAGE SKIN BS 560 BETWEEN S2-3L. CUT-OUT DAMAGED, FABRICATED NEW FILLER REPAIR, TREATED AND PRIMED, HFEC INSPECTED AREA IAW NDTM 51-00-00 FIG 23 PT 6 WITH NO DEFECTS NOTED & INSTALLED FILLER REPAIR ALL IAW EA 7-5310-12
- [SDR FDEA200906122052](https://openairdocs.org/sdr/FDEA200906122052.md): Sill · damaged · Jun 12, 2009 · N278FE · Boeing 727233 · Fuselage Miscellaneous Structure
  > NUMEROUS OEM HOLES ALONG MCK CUT-OUT BS 480 S3-4L. TRIMMED OUT DAMAGED AREA, FABRICATED NEW FILLER, TREATED AND PRIMED IAW SRM 51-10-2. HFEC INSPECTED AREA IAW NDTM 51-00-00 FIG 23 PT6 WITH NO DEFECTS NOTED. INSTALLED FILLER REPAIR IAW EA 7-5310-126827 AND S
- [SDR FDEA200906041927](https://openairdocs.org/sdr/FDEA200906041927.md): Web · cracked · Jun 4, 2009 · N278FE · Boeing 727233 · Fuselage Miscellaneous Structure
  > FORWARD CARGO AREA STA 560 STR 19L PRELOAD SPRING DRUM WEB HAS CRACK. REMOVED AND INSTALLED C1 DOOR MECHANISM SPRING CARTRIDGE ASSY. REMOVED WEB AND FABRICATED NEW WEB, HEAT TREATED TO T6 CONDITION, TREATED, PRIMED & INSTALLED NEW FABRICATED WEB IAW SRM 51-30
- [SDR FDEA200905291854](https://openairdocs.org/sdr/FDEA200905291854.md): Sill · cracked · May 29, 2009 · N278FE · Boeing 727233 · Fuselage Miscellaneous Structure
  > MAIN CARGO MCK-UPPER SILL, BS 500 STR 3L - 4L CRACK COMING FROM RIVET FASTENER HOLE. REMOVED LOCATED AND INSTALLED LONGERON PN 53FX1467-101 P.O. NR 29052265. SPLICES PN 53FX1467114 PO NR 29057261 TREATED AND PRIMED NEW DRILLED PARTS AND BARE METAL ALL IAW SR
- [SDR FDEA200905291853](https://openairdocs.org/sdr/FDEA200905291853.md): Sill · cracked · May 29, 2009 · N278FE · Boeing 727233 · Fuselage Miscellaneous Structure
  > MAIN CARGO AREA MCK-UPPER SILL STA 600 STR 3L TO 4L, CRACKS ORIGINATING FROM TWO RIVET FASTENERS. REMOVED, LOCATED, TREATED, PRIMED AND INSTALLED MID AND AFT LONGERON SECTION OF MCD UPPER SILL IAW SRM 51-30-2, 51-10-2 AND EA 7-5310-126827 ACCOMPLISHED INSP OF
- [SDR FDEA200905291852](https://openairdocs.org/sdr/FDEA200905291852.md): Sill · cracked · May 29, 2009 · N278FE · Boeing 727233 · Fuselage Miscellaneous Structure
  > MAIN CARGO, MCD-UPPER SILL, BS 490 STR 3L-4L, CRACK COMING FROM FASTENER HOLE. REMOVED AND REINSTALLED MCD HINGE IAW ACCESS, HFEC. INSPECTED AREA IAW NDTM 51-00-00 FIG 23 PT6 AND SRM 51-30-2. REMOVED AND REPLACED MCD UPPER SILL IAW SRM 51-30-2, 51-10-2 AND
- [SDR FDEA200905281841](https://openairdocs.org/sdr/FDEA200905281841.md): Skin · cracked · May 28, 2009 · N278FE · Boeing 727233 · Trailing Edge Flaps
  > RT FORE FLAP OTBD WBL 442 CRACK ON SKIN ABOVE CARRIAGE ATTACH FITTING. REMOVED RT OTBD FORE FLAP TO FOM REPAIR IAW MM 27-51-011-4. STOPPED DRILLED CRACK IAW SRM 51-10-1. HFEC INSPECTED STOP DRILL AREA IAW NDTM 51-00-00 FIG 3 PT6 NO DEFECTS NOTED. FABRICA
- [SDR FDEA200905271806](https://openairdocs.org/sdr/FDEA200905271806.md): Seat Track · cracked · May 27, 2009 · N278FE · Boeing 727233 · Fuselage, Seat/Cargo Attach Fittings
  > CABIN SEAT TRACK HAS CRACK INDICATION AT BS 760 LBL 48 ACCESSED AREA OF INDICATION ON SEAT TRACK IAW SRM 51-30-2. HFEC INSPECTED AREA IAW NDTM PT6. 51-00-00 FIGURE 23. NO DEFECTS NOTED. REINSTALLED 2 EA BOLTS IAW SRM 51-30-2.
- [SDR FDEA200905271805](https://openairdocs.org/sdr/FDEA200905271805.md): Seat Track · cracked · May 27, 2009 · N278FE · Boeing 727233 · Fuselage, Seat/Cargo Attach Fittings
  > CABIN SEAT TRACK HAS CRACK INDICATION AT BS 760 RBL 48 ACCESSED AREA OF CRACK INDICATION IAW SRM 51-30-2. HFEC INSPECTED AREA IAW NDTM PT6. 51-00-00 FIG 23. NO DEFECTS NOTED. REINSTALLED 2EA BOLTS IAW SRM 51-30-2.
- [SDR FDEA200905231844](https://openairdocs.org/sdr/FDEA200905231844.md): Attach Angle · corroded · May 23, 2009 · N278FE · Boeing 727233 · Wing, Attach Fittings
  > LT WING LE NR 2 SLAT ACTUATOR ATTACH ANGLES MOUNT HOLES CORRODED AND PITTED. REMOVED LT WING FUEL ACCESS PNL 7215 IAW MM 28-11-021-4. REMOVED IB AND OB ATTACH ANGLES IAW EA 7-5750-120824 AND SRM 51-30-2. LOCATED, DRILLED, AND DEBURRED HOLES ON INBD AND OTBD
- [SDR FDEA200905231861](https://openairdocs.org/sdr/FDEA200905231861.md): Angle · cracked · May 23, 2009 · N278FE · Boeing 727233 · Leading Edge Devices
  > NR 4 SLAT AFT LOWER ANGLE IS CRACKED AT INBD UPSTOP PAD. REMOVED SLAT COVE PANELS IAW SRM 51-30-2. REMOVED DAMAGED AREA IAW SRM 51-40-4 FIGURE 1. FABRICATED NEW ANGLE IAW SRM 57-50-2 FIG.2 AND 51-30-5, AND 51-30-8. TREATED AND PRIMED ANGLE IAW SRM 51-10-2. INS
- [SDR FDEA200905231862](https://openairdocs.org/sdr/FDEA200905231862.md): Angle · cracked · May 23, 2009 · N278FE · Boeing 727233 · Leading Edge Devices
  > NR 8 SLAT AFT LOWER ANGLE IS CRACKED AT INBD AND OUTBD UPSTOP PADS. REMOVED COVE PANELS AT NR 8 SLAT IAW SRM 51-30-2. REMOVED DAMAGED ANGLE IAW SRM 51-30-2 FABRICATED NEW ANGLE IAW SRM 57-50-2 FIG 2, 51-30-5 AND 51-30-8, TREATED AND PRIMED ANGLE IAW SRM 51-
- [SDR FDEA200905221773](https://openairdocs.org/sdr/FDEA200905221773.md): Skin · gouged · May 22, 2009 · N278FE · Boeing 727233 · Cargo/Baggage Doors
  > LOWER CARGO C3 DOOR OUTER SKIN NUMEROUS DENTS & GOUGES ALL OVER SKIN. REMOVED OUTER SKIN AT C3 DOOR IAW SRM 51-30-2 AND FABRICATED NEW C3 DOOR SKIN IAW EA-7-5230-127967. TREATED AND PRIMED C3 DOOR SKIN IAW SRM 51-10-2 AND INSTALLED C3 DOOR SKIN IAW SRM 51-
- [SDR FDEA200905221772](https://openairdocs.org/sdr/FDEA200905221772.md): Frame · dented · May 22, 2009 · N278FE · Boeing 727233 · Fuselage Main, Frame
  > AFT CARGO COMPARTMENT FRAME IS DENTED IN UPPER FLANGE AT BS 950C ABOVE STR 26R. REWORKED DENTED AREA TO ORIGINAL CONTOUR. ABOVE STR 26R IAW DWG SR 27-53-139. NDT INSPECTED AREA WITH NO DEFECTED NOTED. FRAME THICKNESS FOUND TO BE.071 IAW SRM 53-10-2 FIG 5.
- [SDR FDEA200905221771](https://openairdocs.org/sdr/FDEA200905221771.md): Frame · dented · May 22, 2009 · N278FE · Boeing 727233 · Fuselage Main, Frame
  > AFT CARGO COMPARTMENT FRAME IS DENTED IN UPPER FLANGE RADIUS AT BS 990 ABOVE STR. 26L. REWORKED DENTED AREA TO ORIGINAL CONTOUR AT BS 990 STR 26L IAW DWG SR 27-53-139. NDT INSPECTED AREA WITH NO DEFECT NOTED IAW NDTM 51-00-00 FIG 23 PART 6. FRAME THICKNESS F
- [SDR FDEA200905211764](https://openairdocs.org/sdr/FDEA200905211764.md): Skin · corroded · May 21, 2009 · N278FE · Boeing 727233 · Fuselage Main, Plate/Skin
  > CORROSION AFT BOLT HEAD FITTING EXTERIOR FUSELAGE, BS 740, STR 26R - 28R. REMOVED BULKHEAD FITTING AT BS 740 STR 26R-28R EXTERIOR FUSELAGE IAW SRM 51-30-2. FABRICATED NEW FITTING IAW DWG NR 69-64841. HEAT TREATED NEW PART TO T6 IAW FAS ENG REPORT NR 2-37153
- [SDR FDEA200905211763](https://openairdocs.org/sdr/FDEA200905211763.md): Stringer · corroded · May 21, 2009 · N278FE · Boeing 727233 · Fuselage Main, Structure
  > SNAKE PIT FWD CARGO, CORROSION AT STR 27 R, STA 740. REMOVED SNAKE PIT FLOOR PANEL TO FOM IAW SRM 51-30-2. CUT OUT SECTION OF STRINGER FOR REPAIR IAW SRM 51-10-1 AND 53-10-3 FIGURE 1. CUT OUT 26.7500 INCH. FABRICATED NEW STRINGER SECTION AND FABRICATED STRIN
- [SDR FDEA200905211762](https://openairdocs.org/sdr/FDEA200905211762.md): Spar · cracked · May 21, 2009 · N278FE · Boeing 727233 · Wing Spar
  > CRACK ANGLE FALSE SPAR LT WING STA 244 AT NR 7 SPOILER ACTUATOR BRACKET. REMOVED DOUBLER AND WEB SECTION. CUT OUT DAMAGED ANGLE SECTION IAW DWG NR SR27-57-038 REV C. INSTALLED ALL PARTS IAW DRW NR SR27-57-038 REV. C.
- [SDR 07FDEA04538](https://openairdocs.org/sdr/07FDEA04538.md): Duct · blown · Oct 9, 2007 · N278FE · Boeing 727233 · Air Distribution System
  > HEARD LOUD BANG WHILE CLIMBING PAST 32,000 FEET. BANG APPEARED TO BE BELOW AND FORWARD OF THE INSTRUMENT PANEL. DID NOT NOTICE ANY ENGINE OR PRESSURIZATION FLUCTUATIONS. FOUND GASPER AIR DUCT BLOWN. COMPLETED TEMP REPAIR WITH CARGO PIT TAPE PER EA 7-2120-1
- [SDR 07FDEA00626](https://openairdocs.org/sdr/07FDEA00626.md): Bulkhead · cracked · Jan 25, 2007 · N278FE · Boeing 727233 · Fuselage Main, Bulkhead
  > COMPLY WITH FEDEX EA 7-5330-102012, FUSELAGE - BS 11 83 BULKHEAD WEB CRACK REPAIR AT WL 225, BL61. COMPLIED WITH EA 7-5330-102012, RII:575461.
- [SDR 07FDEA00124](https://openairdocs.org/sdr/07FDEA00124.md): Skin · bulged · Jan 16, 2007 · N278FE · Boeing 727233 · Fuselage Main, Plate/Skin
  > RT EXT FUSELAGE STA 288 BELOW STR 21 HAS A SKIN BULGE. REMOVED DAMAGE AND REPAIRED IAW SRM 53-30-2 FIG 3.
- [SDR 07FDEA00089](https://openairdocs.org/sdr/07FDEA00089.md): Floorbeam · corroded · Jan 14, 2007 · N278FE · Boeing 727233 · Fuselage Main, Floor Beam
  > COMPLIED WITH EA 7-5310-102014 FUSELAGE-BASIC-BS 870 FLOORBEAM UPPER CAP CORROSION, RBL 51-57.
- [SDR 07FDEA00081](https://openairdocs.org/sdr/07FDEA00081.md): Skin · cracked · Jan 12, 2007 · N278FE · Boeing 727233 · Fuselage Main, Plate/Skin
  > EXT FUSELAGE LOWER HALF BETWEEN STA 680-700 AND BETWEEN 28L - 30. SKIN SURFACE CRACKED AND HOLE NOTED DURING PRESSURIZATION CHECK. REPAIRED AREA AT STA 680 STR 28L IAW SRM 53-30-3 FIG 3A.
- [SDR 06FDEA03457](https://openairdocs.org/sdr/06FDEA03457.md): Module · cracked · Sep 27, 2006 · N278FE · Boeing 727233 · Hydraulic System, Main
  > SHORTLY AFTER LEVELOFF AT FL310, SYS A HYDRAULIC PUMP LIGHTS FLICKERED AND QUANTITY RAPIDLY DROPPED TO (ZERO). COMPLIED W/QRH AND LANDED IN MEM. FOUND HYD PRESS. LINE FROM NR 1 ENG TO "A" SYS MODULE CRACKED. INSTALLED NEW HYDRAULIC LINE AT "A" SYSTEM MOD
- [SDR 06FDEA2924](https://openairdocs.org/sdr/06FDEA2924.md): Compressor · stalled · Aug 10, 2006 · N278FE · Boeing 727200 · Turbine Engine Compressor Section
  > AS WE APPLIED T/O POWER (STD POWERS) HEARD A LOUD BANG (COMPRESSOR STALL) AND REJECTED T/O BEFORE T/O POWER WAS SET. MAX SPEED 20KTS WIND 12KT X-WIND. SAT CONFIRMED NR 2 ENGINE COMPRESSOR STALL. C/W AMM 71-00-000-6 3.B. CENTER ENG COMPRESSOR STALL INSPE
- [SDR 04FDEA03387](https://openairdocs.org/sdr/04FDEA03387.md): Actuator · leaking · Dec 7, 2004 · N278FE · Boeing 727233 · Landing Gear Actuator
  > TOTAL LOSS OF SYS A QUANTITY WITH LANDING GEAR DOWN AND FLAPS AT 30 DEGREE QTY WENT TO 1.0 GALLONS FOR TEN SECONDS THEN WENT IMMEDIATELY TO 0 GALLONS SYS A PRESSURE WENT TO ZERO WITH LOW PRESSURE LIGHTS IMMEDIATELY FOLLOWING QUANTITY LOSS. TROUBLESHOT LEAK T
- [SDR 04FDEA02847](https://openairdocs.org/sdr/04FDEA02847.md): Indicator · failed · Sep 29, 2004 · N278FE · Boeing 727233 · Hydraulic Indicating System
  > HYDRAULIC SYSTEM A QUANTITY INDICATOR WENT TO 0.2 GALLONS ON FLAP RETRACTION. QRH PROCEDURES RECOVERED QTY TO 1.2 GALLONS. ENT BY: 014562 RPT BY: 241937 FACT 29SEP04 11:20, MEM R REMOVED AND REPLACED INDICATOR IAW 727-200 M /M 31-00-011-4. OPS CHECK GOOD.
- [SDR 04FDEA00204](https://openairdocs.org/sdr/04FDEA00204.md): Seal · out of position · Jan 22, 2004 · N278FE · Boeing 727200 · Landing Gear Doors
  > NOSE GEAR DOOR WARNING LIGHT ILLUMINATED WITH GEAR DOWN. AFTER GO-AROUND DOOR LIGHT EXTINGUISHED. VISUALLY INSPECTED BOTH NOSE GEAR DOOR SWITCHES, NO DEFECTS NOTED. FOUND BOTH DOORS WERE DIFFICULT TO OPEN AND CLOSE. WHEN DOORS WERE LATCHED HAD TO BE PUSHED
- [SDR 03FDEA01098](https://openairdocs.org/sdr/03FDEA01098.md): Control Box · malfunctioned · Jul 15, 2003 · N278FE · Boeing 727200 · Detection System
  > GOT LOWER BODY OVERHEAT LIGHT ON CLIMBOUT UPON DESCENT, LIGHT EXTINGUISHED WITH THROTTLE REDUCTION. T/S IAW 26-14-000-1, FOUND AFT STAIR LT LOOP RUBBING AGAINST STREAMER OF A/C. REPOSITIONED SAME, RERACKED FIRE AND OVERHEAT CONTROL BOX. RAN ENGINES AT GA
- [SDR 02FDEA00191](https://openairdocs.org/sdr/02FDEA00191.md): Bulkhead · cracked · Mar 10, 2002 · N278FE · Boeing 727233 · Fuselage Main, Bulkhead
  > LEFT W/L BULKHEAD WEB IS CRACKED AT BS 870, LBL 61, WL 162. REMOVED AND REPLACED BULKHEAD WEB PER EA 7-5350-62780.
- [SDR 02FDEA00184](https://openairdocs.org/sdr/02FDEA00184.md): Frame · dented · Mar 6, 2002 · N278FE · Boeing 727233 · Fuselage Main, Frame
  > DENT IN FRAME AT BS 560 BETWEEN STR 24L AND 25L. REMOVED AND REPLACED FRAME PER SRM 51-10-2, 51-20-151.
- [SDR 02FDEA00146](https://openairdocs.org/sdr/02FDEA00146.md): Skin · dented · Feb 27, 2002 · N278FE · Boeing 727233 · Fuselage Main, Plate/Skin
  > SKIN DENTED AT BS 1279 TO 1282, BETWEEN STR 20R & 21R. REMOVED AND REPLACED SKIN WITH DOUBLER PER SRM 53-30-3.
- [SDR 02FDEA00149](https://openairdocs.org/sdr/02FDEA00149.md): Stringer · cracked · Feb 25, 2002 · N278FE · Boeing 727233 · Fuselage Main, Longeron/Stringer
  > STR 25L CRACKED AT BS 560. REMOVED AND REPLACED STR PER SRM 53-10-3.
- [SDR 02FDEA00142](https://openairdocs.org/sdr/02FDEA00142.md): Skin · corroded · Feb 23, 2002 · N278FE · Boeing 727233 · Fuselage Main, Plate/Skin
  > CORROSION ON SKIN AND STRINGER AT BS 950D TO 950E, STR 28L. REMOVED AND REPLACED SKIN PER SRM 53-30-3.
- [SDR 02FDEA00148](https://openairdocs.org/sdr/02FDEA00148.md): Frame · dented · Feb 23, 2002 · N278FE · Boeing 727233 · Fuselage Main, Frame
  > FRAME DENTED AT BS 420 BETWEEN STR 8L TO 9L. REMOVED AND REPLACED FRAME PER SRM 53-10-4 FIG 1.
- [SDR 02FDEA00212](https://openairdocs.org/sdr/02FDEA00212.md): Spar · worn · Feb 19, 2002 · N278FE · Boeing 727233 · Vertical Stabilizer, Spar/Rib
  > VERT FIN MID SPAR AT FIN STA 230-231 WORN OUT OF LIMITS AT STR 7. REMOVED AND REPLACED MIDSPAR PER EA 7-5510-62791.

Next page: https://openairdocs.org/deregistered/N278FE-2013-08-27/reports.md?page=2

## The whole list in SQL

Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS:

```sql
SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy
FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet'
WHERE n_number = 'N278FE' AND deregistration_id = 'N278FE-2013-08-27'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/deregistered/N278FE-2013-08-27/reports

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