# Service difficulty reports: Boeing 727-200

A list on [Boeing 727-200](https://openairdocs.org/model/boeing-727-200.md).

Newest first. General aviation reporting is voluntary.

Page 1 of 57 · 2,835 reports

- [SDR FXGA202307122336](https://openairdocs.org/sdr/FXGA202307122336.md): Unknown · unknown · Jul 12, 2023 · N794AJ · Boeing 727200 · Fuselage Structure (General)
  > DAMAGE TO FLOOR STRUCTURE F/S 1148 BL RIGHT 45 WL 208. REPAIR OF DAMAGE FLOOR STRUCTURE AT F/S1148 BL RIGHT 45 WL 208. FABRICATE REPLACEMENT PARTS AND INSTALL PER SRM.
- [SDR 2022F00286](https://openairdocs.org/sdr/2022F00286.md): None · defective · Jun 28, 2022 · N209TR · Boeing 727200 · Hydraulic Quantity Indicator
  > ON 6/28/2022 AT 0610Z, N209TR DEPARTED KTOL FOR KCHA. WHILE CLIMBING THROUGH FL220, "A" SYSTEM HYD LOW LEVEL LIGHT ILLUMINATED AND REMAINED ON. ALSO, THE "A" SYSTEM QTY INDICATOR DROPPED TO 2.2 GALLONS AND STOPPED AT THAT VALUE. CREW PERFORMED MEMORY ITEMS FOR
- [SDR K11A2021092200076](https://openairdocs.org/sdr/K11A2021092200076.md): Seat Track · corroded · Jul 11, 2021 · N724CK · Boeing 727200 · Fuselage Main, Structure
  > SEAT TRACK CORROSION STA 492 TO 500 RBL 50
- [SDR VGCA2019112619003](https://openairdocs.org/sdr/VGCA2019112619003.md): Floorbeam · corroded · Nov 19, 2019 · N281FL · Boeing 727200 · Fuselage Main, Floor Beam
  > FLOOR BEAM CORRODED AT STATION 920 AT LEFT BODY LINE 28
- [SDR 7IWB2019F00137](https://openairdocs.org/sdr/7IWB2019F00137.md): Bleed Air Sys · leaking · Mar 4, 2019 · N209TR · Boeing 727200 · Pneumatic Distribution System
  > ON 3/2/2019, DEPARTED, APROX 3 MINUTES AFTER TO, THE CREW GOT A NR 1 ENGINE FIRE INDICATION IN THE COCKPIT. THE CREW REDUCED THE POWER SETTING TO IDLE AND THE FIRE INDICATION WENT AWAY. THEY RETURNED TO KMFE SAFELY. AFTER TROUBLESHOOTING BY IJW MECHANICS, IT W
- [SDR 2017FA0000038](https://openairdocs.org/sdr/2017FA0000038.md): Access Panel · stuck · Feb 1, 2017 · N724YS · Boeing 727200 · Doors
  > DURING ROUTINE GEAR SWING AND MANUAL GEAR DEPLOYMENT, THE MAINTENANCE ENGINEER HAD DIFFICULTY IN ACCESSING GEAR DEPLOYMENT PANELS. SCREW DRIVERS AND PRY BARS WERE REQUIRED TO LIFT THE CARPET AND UNDERLAY, DUE TO THE COVERS BEING BONDED TO THE FLOOR. THE AIRCR
- [SDR FOTR20160719002](https://openairdocs.org/sdr/FOTR20160719002.md): Web · cracked · Jul 19, 2016 · N209TR · Boeing 727200 · Ailerons
  > RIGHT WING T/E INBD AILERON OTBD SIDE WEB IS CRACKED.
- [SDR VGCA20160509001](https://openairdocs.org/sdr/VGCA20160509001.md): Battery · discharged · May 9, 2016 · N281FL · Boeing 727200 · Emergency Lighting
  > DURING PREFLIGHT, COCKPIT EMERGENCY LIGHT BATTERY DEAD.
- [SDR I5PA2016022642501](https://openairdocs.org/sdr/I5PA2016022642501.md): Unknown · malfunctioned · Feb 26, 2016 · N86425 · Boeing 727200 · Landing Gear Retraction/Extension System
  > SHORTLY AFTER TAKEOFF THE CREW CALLED IN THE COMPANY RADIO THAT THEY WERE NOT GETTING A GREEN LIGHT FOR THE NOSE GEAR & THAT THE RED UNSAFE LIGHT STAYED ILLUMINATED. THEY CYCLED THE GEARS & STILL DID NOT GET THE RED NOSE GEAR LIGHT TO EXTINGUISH & THE GREEN L
- [SDR PCSA2015011202](https://openairdocs.org/sdr/PCSA2015011202.md): Warning Light · illuminated · Jan 8, 2015 · N395AJ · Boeing 727200 · Landing Gear Position and Warning
  > LEFT GEAR UNSAFE LIGHT.
- [SDR PCSA2015011201](https://openairdocs.org/sdr/PCSA2015011201.md): Warning Light · illuminated · Jan 8, 2015 · N395AJ · Boeing 727200 · Landing Gear Position and Warning
  > LEFT MAIN GEAR UNSAFE LIGHT ILLUMINATED.
- [SDR FY4Y20141006003](https://openairdocs.org/sdr/FY4Y20141006003.md): Skin · corroded · Oct 1, 2014 · N705AA · Boeing 727200 · Fuselage Main, Plate/Skin
  > DURING CPCP INSPECTION THE INSPECTOR PERFORMED VISUAL INSPECTION & FOUND LEVEL 2 CORROSION ON FUSELAGE SKIN OF BS 950B STRINGER 28L. THE CORROSION THROUGH THE SKIN WAS OVER LIMIT IAW SRM 53-30-01 FIG 1. THE ITEM HAS BEEN REPORTED FOR REQUESTING THE REPAIR AP
- [SDR FY4Y20141006002](https://openairdocs.org/sdr/FY4Y20141006002.md): Skin · corroded · Oct 1, 2014 · N705AA · Boeing 727200 · Fuselage Main, Plate/Skin
  > DURING INSPECTION THE INSPECTOR PERFORMED VISUAL INSPECTION & FOUND LEVEL 2 CORROSION ON FUSELAGE SKIN OF BS 950D STRINGER 26L. THE CORROSION THROUGH THE SKIN WAS OVER LIMIT IAW SRM 53-30-01 FIG 1. THE ITEM HAS BEEN REPORTED FOR REQUESTING THE REPAIR APPROVA
- [SDR FY4Y20141006001](https://openairdocs.org/sdr/FY4Y20141006001.md): Skin · corroded · Oct 1, 2014 · N705AA · Boeing 727200 · Fuselage Main, Plate/Skin
  > DURING CPCP INSPECTION THE INSPECTOR FOUND LEVEL 2 CORROSION ON FUSELAGE SKIN BETWEEN BS 720E & 720F STRINGER 26L. THE CORROSION THROUGH THE SKIN WAS OVER LIMIT IAW SRM 53-30-01 FIG 1. THE ITEM HAS BEEN REPORTED FOR REQUESTING THE REPAIR APPROVAL DATA.
- [SDR FY4Y20141003007](https://openairdocs.org/sdr/FY4Y20141003007.md): Skin · corroded · Sep 30, 2014 · N705AA · Boeing 727200 · Fuselage Main, Plate/Skin
  > DURING INSPECTION THE INSPECTOR PERFORMED VISUAL INSPECTION & FOUND LEVEL 2 CORROSION ON FUSELAGE SKIN OF BS 950E+4 STRINGER 28L. THE CORROSION THROUGH THE SKIN WAS OVER LIMIT IAW SRM 53-30-01 FIG 1. THE ITEM HAS BEEN REPORTED FOR REQUESTING THE REPAIR APPRO
- [SDR FY4Y20141003006](https://openairdocs.org/sdr/FY4Y20141003006.md): Skin · corroded · Sep 30, 2014 · N705AA · Boeing 727200 · Fuselage Main, Plate/Skin
  > DURING CPCP INSPECTION THE INSPECTOR FOUND LEVEL 2 CORROSION ON FUSELAGE SKIN BETWEEN BS 720B & 720C STRINGER 28L & 28R. THE CORROSION THROUGH THE SKIN WAS OVER LIMIT IAW SRM 53-30-01 FIG 1. THE ITEM HAS BEEN REPORTED FOR REQUESTING THE REPAIR APPROVAL DATA
- [SDR FY4Y20141003005](https://openairdocs.org/sdr/FY4Y20141003005.md): Skin · corroded · Sep 30, 2014 · N705AA · Boeing 727200 · Wing, Plate/Skin
  > DURING PERFORMED C CHECK CORROSION WAS FOUND ON THE LT WING UPPER SKIN FROM WS 611.5 TO WS 613.5. DIMENSIONS OF CORROSION AREA 3 INCHES X 1.25 INCHES. AFTER THE CORROSION BLEND OUT THE MIN REMAINING THICKNESS OF 0.085 INCH, ORIGINAL THICKNESS IS 0.184 INCH,
- [SDR FY4Y20141003004](https://openairdocs.org/sdr/FY4Y20141003004.md): Plate · corroded · Sep 30, 2014 · N705AA · Boeing 727200 · Wing Miscellaneous Structure
  > DURING PERFORMED C CHECK CORROSION WAS FOUND ON THE LT WING FRONT SPAR LOWER CHORD PLATE FROM WS 520 TO WS 526. DIMENSIONS OF CORROSION AREA 6 INCHES X 1.5 INCHES. AFTER THE CORROSION BLEND OUT THE MIN REMAINING THICKNESS OF 0.141 INCH, ORIGINAL THICKNESS IS
- [SDR FY4Y20141003003](https://openairdocs.org/sdr/FY4Y20141003003.md): Plate · corroded · Sep 30, 2014 · N705AA · Boeing 727200 · Wing Miscellaneous Structure
  > DURING PERFORMED C CHECK CORROSION WAS FOUND ON THE LT WING FRONT SPAR LOWER CHORD PLATE FROM WS 701 TO WS 696. DIMENSIONS OF CORROSION AREA 5 INCHES X 1.5 INCHES. AFTER THE CORROSION BLEND OUT THE MIN REMAINING THICKNESS OF 0.126 INCH, ORIGINAL THICKNESS IS
- [SDR FY4Y20141003002](https://openairdocs.org/sdr/FY4Y20141003002.md): Plate · corroded · Sep 30, 2014 · N705AA · Boeing 727200 · Wing Miscellaneous Structure
  > DURING PERFORMED C CHECK CORROSION WAS FOUND ON THE LT WING FRONT SPAR LOWER CHORD PLATE FROM WS 726 TO WS 734. DIMENSIONS OF CORROSION AREA 8 INCHES X 2 INCHES. AFTER THE CORROSION BLEND OUT, THE MIN REMAINING THICKNESS OF 0.031 INCH, ORIGINAL THICKNESS IS
- [SDR FY4Y20141003001](https://openairdocs.org/sdr/FY4Y20141003001.md): Plate · corroded · Sep 30, 2014 · N705AA · Boeing 727200 · Wing Miscellaneous Structure
  > DURING PERFORMED C CHECK CORROSION WAS FOUND ON THE LT WING FRONT SPAR LOWER CHORD PLATE FROM WS 738.5 TO WS 742. DIMENSIONS OF CORROSION AREA IS 3.5 INCHES X 1.5 INCHES. AFTER THE CORROSION BLEND OUT THE MIN REMAINING THICKNESS OF 0.104 INCH, ORIGINAL THICK
- [SDR I5PA201406010002](https://openairdocs.org/sdr/I5PA201406010002.md): Engine · leaking · Jun 25, 2014 · N705AA · Boeing 727200 · Engine (Turbine/Turboprop)
  > NUMBER 3 ENG SHUT DOWN IN FLIGHT DUE TO POSSIBLE COMPRESSOR STALL, FOLLOWED BY OIL LOSS. THE INLET & EXHAUST LOOKED OK, BUT EVIDENCE OF OIL LOSS FROM THE EXHAUST. NR 3 ENG HAS BEEN R & R. INSTALLED IAW AMM. PERFORMED OPERATIONS CHECK & HIGH POWER ASSURANCE
- [SDR I5PA201406010001](https://openairdocs.org/sdr/I5PA201406010001.md): Engine · leaking · Jun 25, 2014 · N705AA · Boeing 727200 · Turbine Engine Oil System
  > NR 3 ENGINE SHUTDOWN IN FLIGHT DUE TO POSSIBLE COMPRESSOR STALL FOLLOWED BY OIL LOSS. THE INLET & EXHAUST LOOKED OK, BUT EVIDENCE OF OIL LOSS FROM THE EXHAUST. NR 3 ENGINE HAS BEEN REMOVED & REPLACED. INSTALLED IAW AMM. PERFORMED OPS CHECK & HIGH POWER A
- [SDR FY4Y20121122197](https://openairdocs.org/sdr/FY4Y20121122197.md): Web · corroded · Nov 19, 2012 · N705AA · Boeing 727200 · Wing Main, Frame Structure
  > DURING PERFORMED 7C CHECK, CORROSION WAS FOUND ON CENTER FUEL TANK AFT VERTICAL WEB AT STATION BS 865, LBL 38, 39,WL 165-168 (DIMENSIONS OF CORROSION AREA:2.3750" × 1.5"). AFTER BLEND OUT CORROSION, THE PENETRATION DEPTH WAS OVER LIMIT IAW SRM 57-10-01, PAGE
- [SDR FY4Y20121116197](https://openairdocs.org/sdr/FY4Y20121116197.md): Skin · corroded · Nov 13, 2012 · N705AA · Boeing 727200 · Fuselage Main, Plate/Skin
  > DURING PERFORMED 7C CHECK, CORROSION WAS FOUND ON FUSELAGE LOWER LOBE SKIN PANEL AT STATION BS 1010, WL 148 BETWEEN S-28R AND S-29R. (DIMENSIONS OF CORROSION AREA:5 3/8" × 2"). AFTER BLEND OUT CORROSION, THE PENETRATION DEPTH (0.019") WAS OVER LIMIT IAW SRM
- [SDR FY4Y201211130001](https://openairdocs.org/sdr/FY4Y201211130001.md): Structure · corroded · Nov 13, 2012 · N705AA · Boeing 727200 · Fuel Storage
  > DURING PERFORMED 7C CHECK, CORROSION WAS FOUND ON CENTER FUEL TANK AFT LOWER EDGE AT STATION BS 865, LBL 54, WL 169 TO LBL 58 WL 171 ( DIMENSIONS OF CORROSION AREA:3.7500" × 1.7500"). AFTER BLEND OUT CORROSION, THE PENETRATION DEPTH (0.280") WAS OVER LIMIT IA
- [SDR FY4Y2012F00244](https://openairdocs.org/sdr/FY4Y2012F00244.md): Structure · corroded · Nov 13, 2012 · N705AA · Boeing 727200 · Fuel Storage
  > PERFORMED 7C CHECK, CORROSION WAS FOUND ON CENTER FUEL TANK AFT LOWER EDGE AT BS 865, LBL 54, WL 169 TO LBL 58, WL 171 (DIMENSIONS OF CORROSION AREA: 3.7500" × 1.7500"). AFTER BLEND OUT CORROSION, THE PENETRATION DEPTH (0.280") WAS OVER LIMIT IAW SRM 53-00-00
- [SDR FDEA201206212293](https://openairdocs.org/sdr/FDEA201206212293.md): Skin · gouged · Jun 21, 2012 · N482FE · Boeing 727200 · Fuselage Main, Plate/Skin
  > SKIN GOUGED AND DENTED STA 1087 STR 24R. CUT OUT DAMAGED AREA IAW SRM 51-10-1 AND 53-30-3 FIG 3 FABRICATED REPAIR DOUBLER AND FILLER IAW SRM 53-30-3 FIG 3 AND 53-30-2 FIG 2 INSTALLED REPAIR DOUBLER AND FILLER IAW SRM 51-30-02
- [SDR CA111025007](https://openairdocs.org/sdr/CA111025007.md): Detector · failed · Oct 20, 2011 · Boeing 727200 · Overheat Detection
  > (CAN) ON CLIMB OUT, CREW EXPERIENCED A "STRUT OVERHEAT" WARNING ON THE NR 3 SIDE. CREW THROTTLED THE ENGINE TO IDLE AND THE WARNING EXTINGUISHED. ACFT RETURNED TO BASE WHERE MX REPLACED A FAULTY FIRE SENSE LOOP.
- [SDR CA111025006](https://openairdocs.org/sdr/CA111025006.md): Engine · failed · Oct 17, 2011 · Boeing 727200 · Engine (Turbine/Turboprop)
  > (CAN) ON CLIMB OUT, CREW EXPERIENCED A "BANG" AND VIBRATION FROM THE NR 3 ENGINE. CREW SECURED THE ENGINE AND RETURNED TO BASE. MX DISCOVERED THE NR 3 ENGINE HAD EXPERIENCED A CATASTROPHIC INTERNAL FAILURE. THE ENGINE WAS REPLACED AND ACFT RETURNED TO SERVICE
- [SDR C8GA2011000007](https://openairdocs.org/sdr/C8GA2011000007.md): Shaft · sheared · Jun 22, 2011 · N713AA · Boeing 727200 · Hydraulic Pump (Electric/Engine), Main
  > DURING CRUISE OPERATION AT FL 300, THE NR 1 ENGINE HYD SYS "A" LOW PSI LIGHT ILLUMINATED. ACFT DIVERTED WHERE IT LANDED WITHOUT INCIDENT. POST FLIGHT INSP WAS PERFORMED, NOTING THAT THE NR1 ENGINE "A" SYSTEM HYD SYSTEM PUMP WAS AT FAULT. PERFORMED OPS CHECK
- [SDR FDEA201106102374](https://openairdocs.org/sdr/FDEA201106102374.md): Skin · dented · Jun 10, 2011 · N495FE · Boeing 727200 · Fuselage Main, Plate/Skin
  > AFT AIRSTAIRS LT TORQUE BOX EXTERIOR SKIN AT STA 1308, LIGHTING CUT-OUT, SKIN HAS DENT AND CRACK ALONG EDGE. CUTOUT DAMAGED AREA & FABRICATED REPAIR DOUBLER IAW SRM 51-40-2 FIG 1 & 53-10-2 FIG 6, TREATED & PRIMED PARTS IAW SRM 51-10-2, INSTALLED REPAIR DOUBLE
- [SDR FY4Y20110317](https://openairdocs.org/sdr/FY4Y20110317.md): Strap · corroded · Mar 16, 2011 · N705AA · Boeing 727200 · Trailing Edge Flaps
  > HE CORROSION WAS FOUND AT TENSION STRAP OF LT OTBD MID FLAP AT WBL 452 DURING 6C CHECK. THE ORIGINAL THICKNESS OF THE STRAP IS 0.225". AFTER BLEND OUT, THE DIMENSION OF THE CORROSION AREA IS 2.5" (LENGTH) X 2" (WIDTH) AND REMAINDER THICKNESS IS 0.172", IAW
- [SDR FY4Y197M20110315B](https://openairdocs.org/sdr/FY4Y197M20110315B.md): Beam · corroded · Mar 11, 2011 · N705AA · Boeing 727200 · Horizontal Stabilizer Structure
  > LT HORIZONTAL STAB TRAILING LOWER BEAM LOWER SURFACE STA96 TO 97 HAD EXFOLIATION CORROSION. ORIGINAL THICKNESS IS 0.120". AFTER CORROSION REMOVED, THE REMAINED THICKNESS WAS 0.078" AREA WAS 2.25" X 1.5". IT'S BEYOND LIMIT IAW SRM 55-10-1, PAGE 1, NOTE B. CORR
- [SDR FY4Y197M20110315A](https://openairdocs.org/sdr/FY4Y197M20110315A.md): Spar · corroded · Mar 11, 2011 · N705AA · Boeing 727200 · Fuselage Main, Frame
  > HEAVY CORROSION ON RT WING INBD MIDFLAP REAR SPAR LOWER CHORD AT WBL142, ORIGINAL THICKNESS 0.121". AFTER CORROSION REMOVED, THE REMAINED THICKNESS WAS 0.051", AREA WAS 3" X 1". IT'S BEYOND LIMITED IAW SRM 57-50-1, PAGE 8. REPAIR METHOD REF SRM 57-50-2, PAG
- [SDR FY4Y197M20110315](https://openairdocs.org/sdr/FY4Y197M20110315.md): Skin · corroded · Mar 11, 2011 · N705AA · Boeing 727200 · Trailing Edge Flaps
  > HEAVY CORROSION ON RT WING INBD MIDFLAP UPPER EXTERNAL SURFACE, AT WBL128, FWD OF FLAP T/E ABOUT 22.5". ORIGINAL THICKNESS IS 0.054" AFTER CORROSION REMOVE, REMAIN THICKNESS IS 0" IAW SRM 57-50-1, PAGE 8, AREA ABOUT 1" X 1.3750". REPAIR METHOD SRM 57-50-4, F
- [SDR FOTR2019813123](https://openairdocs.org/sdr/FOTR2019813123.md): Hinge · cracked · Dec 1, 2010 · N713AA · Boeing 727200 · Fuselage, Door Hinge
  > MCD UPPER AFT MOST SEGMENT FUSELAGE SIDE AFT LOBE IS CRACKED. REMOVED MAIN CARGO DOOR AFT SEGMENT HINGE IAW FREIGHTER MM, FIG 5201B, REV F. FABRICATED NEW SECTION FROM MS20001-16-7200 PO 9002399, DIM 18" X 3.75" IAW FREIGHTER MM FIG 5201B REV F. LOCATED AND
- [SDR FOTR2019813715](https://openairdocs.org/sdr/FOTR2019813715.md): Frame · misinstalled · Nov 21, 2010 · N713AA · Boeing 727200 · Fuselage Main, Frame
  > BS 890 FRAME HAS FASTENER WITH NO ED IN WINDOW AREA, LT SIDE. CUTOUT DAMAGED AREA DIM.75" X.5' ON STA 890 FRAME IAW SRM 53-10-4 FIG 1. FABRICATED 2 EA DOUBLERS FROM 7075-0.071 DIM. 11" X 3" PO 20198132 IAW SRM 53-10-4 FIG 1. HEAT TREATED PARTS TO 7075T6
- [SDR FOTR201728764](https://openairdocs.org/sdr/FOTR201728764.md): Seat Track · damaged · Oct 25, 2010 · N17773 · Boeing 727200 · Fuselage, Seat/Cargo Attach Fittings
  > SEAT TRACK STA. 720-740 LBL24 DAMAGED. REPAIRED ON NR 8764 FASI W/O 20172
- [SDR C8GA20100012](https://openairdocs.org/sdr/C8GA20100012.md): Valve · stuck · Jul 23, 2010 · N713AA · Boeing 727200 · Cabin Cooling System
  > DURING CLIMB OPERATION WITH THE LT PACK DEFERRED THE RT PACK WOULD NOT PRESSURIZE ACFT. THE ACFT RETURNED TO TOL WHERE IT LANDED WITHOUT INCIDENT. POST FLIGHT INSP WAS PERFORMED AND NOTED THAT THE RT PACK VALVE WOULD ONLY OPEN SLIGHTLY WHEN THE PACK IS TURNED
- [SDR FDEA201007132504](https://openairdocs.org/sdr/FDEA201007132504.md): Stringer · corroded · Jul 13, 2010 · N265FE · Boeing 727200 · Fuselage Main, Longeron/Stringer
  > CORROSION ON STRINGER 27L FROM BS 950A TO 1130. REMOVED SECTION OF STRINGER 27L FROM BS 950D PLUS 10 INCHES TO BS 1005, 85 INCHES LONG IAW SRM, REV 103, 53-10-3 FIG 1. FABRICATED STRINGER SECTIONS USING BAC 1498-147, 7075-T6, 19 INCHES LONG, 20 1/2 INCHES L
- [SDR FDEA201001140152](https://openairdocs.org/sdr/FDEA201001140152.md): Rib · cracked · Jan 14, 2010 · N481FE · Boeing 727200 · Leading Edge Devices
  > NR 2 SLAT HAS 2 CRACKED RIBS AT FWD MOUNT OF ACTUATOR. REMOVED CRACKED RIBS (2 EA) AT NR 2 SLAT & INSTALLED NEW RIBS INBD/OTBD IAW SRM 51-30-2, SRM 51-30-5, SRM 57-50-2 FIG 2, REV 102.
- [SDR I5PA20090802](https://openairdocs.org/sdr/I5PA20090802.md): Spar · corroded · Aug 6, 2009 · N705AA · Boeing 727200 · Wing Spar
  > DURING 5C CHECK AND INSPECTION, CORROSION WAS FOUND ON LT WING REAR SPAR LWR SKIN AT WS706 DIMENSION AREA 1.3 INCH X 1.7 INCH. AFTER CORROSION BLENDOUT FOUND MAX BLDOUT DEPT IS BEYOND LIMITATIONS. NO REINFORCEMENT REQUIRED, REMOVE ALL FASTENERS BLEND SMOO
- [SDR FDEA200906172139](https://openairdocs.org/sdr/FDEA200906172139.md): Skin · cracked · Jun 17, 2009 · N284FE · Boeing 727200 · Wing, Plate/Skin
  > LT OTBD FORE FLAP WBL 442, CRACK ON CUTOUT FWD OF ATTACH FITTING. TRIMMED OUT CRACKED AREA, DIM 0.100 INCH LENGTH IAW SRM 51-10-1. FOUND WITHIN LIMITS IAW SRM 57-50-1. FIG 3 TREATED AND PRIMED IAW SRM 51-10-2.
- [SDR FDEA200906172134](https://openairdocs.org/sdr/FDEA200906172134.md): Shear Tie · damaged · Jun 17, 2009 · N284FE · Boeing 727200 · Fuselage Internal Mounting Structure
  > FWD PIT- EXTRA HOLE IN SHEAR TIE AT BS 660, BETWEEN STRINGERS 28L AND 27L. REMOVED FASTENERS FOR ACCESS IAW SRM 51-30-2. REMOVED DAMAGED SECTION OF SHEAR TIE IAW SRM 53-10-4 FIG 15. FABRICATED NEW SHEAR TIE IAW SRM 53-10-4 FIG 15. FABRICATED RADIUS FILLER I
- [SDR FDEA200906152115](https://openairdocs.org/sdr/FDEA200906152115.md): Frame · cracked · Jun 15, 2009 · N284FE · Boeing 727200 · Fuselage Main, Frame
  > FWD CARGO AREA, STA 540, STR 21-22L, LWR STUB FRAME EXTENSION, CRACK ON RADIUS. REPAIRED FORWARD CARGO COMPARTMENT LOWER STUB FRAME EXTENSION IAW EA 7-5310-126829.
- [SDR FDEA200906022004](https://openairdocs.org/sdr/FDEA200906022004.md): Shear Tie · corroded · Jun 2, 2009 · N245FE · Boeing 727200 · Fuselage Internal Mounting Structure
  > SHEAR TIE CORRODED STA 950E BETWEEN STR 28L AND 29L. REMOVED SHEAR TIE REPAIR, FABRICATED NEW SHEAR TIE, FABRICATED NEW VERTICAL STIFFENER, HEAT TREATED PARTS TO T6 CONDITION AND INSTALLED IAW SRM 51-30- 2, 53-10-2, 51-10-1, AND 53-10-4.
- [SDR CA090601004](https://openairdocs.org/sdr/CA090601004.md): Duct · ruptured · May 30, 2009 · Boeing 727200 · Compressor Bleed Valve
  > (CAN) ACFT RETURNED TO YOW AFTER APPROX 30 MINUTES INTO FLIGHT DUE TO FIRE ALARM ON NR 2 ENGINE. ALARM WOULD NOT GO OFF AFTER NORMAL PROCEDURE SO ENGINE SHUTDOWN AND FIRE BOTTLE DISCHARGED. MX FOUND A 4 INCH HOLE IN THE 13TH STAGE BLEED AIR DUCT TO THE NOSE AN
- [SDR FDEA200905141663](https://openairdocs.org/sdr/FDEA200905141663.md): Bypass Valve · failed · May 14, 2009 · N258FE · Boeing 727200 · Trailing Edge Flap Control System
  > ON DEPARTURE, FLAP RETRACTION NOT NORMAL, SPLIT FLAPS, OUTBOARD FLAPS IN AGREEMENT W/HANDLE AT FLAPS 5 DEG INBOARD FLAPS STAYED AT 15 DEG. RAN QRH, SOME SLATS EXTENDED. ATTEMPTED FLAP MASTER & RAISE INBD FLAPS, ALT FLAP MOTOR INBD C/B POPPED. RTB. INBD FLA
- [SDR FDEA200905121629](https://openairdocs.org/sdr/FDEA200905121629.md): Vertical Beam · damaged · May 12, 2009 · N245FE · Boeing 727200 · Fuselage Main, Bulkhead
  > VERTICAL BEAM HAS FASTENERS WITH 0 SPACING BS 1183 LBL 17.8. REPAIRED BS 1183 BULKHEAD VERTICAL BEAM AT LBL 17.8 IAW EA NR 7-5310-127962. "BS 1183 BULKHEAD WITH INSUFFICIENT FASTENER SPACING AT LBL 20 BELOW WL190".

Next page: https://openairdocs.org/model/boeing-727-200/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 aircraft_model_key = '727200'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/model/boeing-727-200/reports

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