# Service difficulty reports: N705AA, cancelled Feb 3, 2021

A list on [N705AA, cancelled Feb 3, 2021](https://openairdocs.org/deregistered/N705AA-2021-02-03.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 · 52 reports

- [SDR I5PA20200106104](https://openairdocs.org/sdr/I5PA20200106104.md): Engine · damaged · Dec 21, 2019 · N705AA · Boeing 757200 · Engine (Turbine/Turboprop)
  > AFTER DEPARTURE OUT OF ROR, ON CLIMB OUT CREW EXPERIENCED A LOUD BANG FROM ENGINE #3, CREW KEPT ENGINE AT IDLE AND RETURNED AND LANDED SAFELY IN ROR. MAINTENANCE CREW PERFORMED INSPECTION OF #3 ENGINE, FOUND DAMAGE IN HOT SECTION. - ITEM STILL OPEN -
- [SDR I5PA2019030800000](https://openairdocs.org/sdr/I5PA2019030800000.md): Smoke Detector · activated · Mar 8, 2019 · N705AA · Boeing 727223 · Smoke Detection
  > MAIN CARGO SMOKE DETECTOR GOES ON IN FLIGHT.
- [SDR I5PA2018110470501](https://openairdocs.org/sdr/I5PA2018110470501.md): Smoke Detector · unserviceable · Nov 4, 2018 · N705AA · Boeing 727223 · Smoke Detection
  > MAIN CARGO FIRE LIGHT AND BELL CAME ON IN FLIGHT. REPLACED FAULTY SMOKE DETECTOR UNIT.
- [SDR I5PA2017121170501](https://openairdocs.org/sdr/I5PA2017121170501.md): Indicator · inoperative · Dec 10, 2017 · N705AA · Boeing 727223 · Airspeed/Mach Indicator
  > DISCREPANCY: F/O AIRSPEED INDICATOR INOP. CORRECTIVE ACTION: FOUND FOREIGN OBJECT IN AUXILIARY AND F/O PITOT PROBE. FLUSHED PER AMM 34-11-00. OPS CHECK GOOD
- [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 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 FY4Y20110315](https://openairdocs.org/sdr/FY4Y20110315.md): Splice · corroded · Mar 14, 2011 · N705AA · Boeing 727223 · Trailing Edge Flaps
  > THE EXFOLIATION CORROSION IS FOUND AT LT I/B MID FLAP CHORD SPLICE AT WBL 193 DURING 6C CHECK. THE ORIGINAL THICKNESS OF THE CHORD SPLICE IS 0.072”. AFTER BLENT OUT, THE DIMENSION OF THE CORROSION AREA IS 3" (LENGTH) X 1 (WIDTH) AND REMAINDER THICKNESS IS 0.
- [SDR FY4Y197M20110315E](https://openairdocs.org/sdr/FY4Y197M20110315E.md): Seat Track · corroded · Mar 11, 2011 · N705AA · Boeing 727223 · Fuselage, Seat/Cargo Attach Fittings
  > DURING PERFORMED CPCP CARD NR C53-224-01 PART 1 OF 3 FOR MAIN DECK CARGO COM'P FLOOR STRUCTURE, THE SEAT TRACK AT STA BS 640+3 AND BS 640+10 LBL. 0 WAS FOUND LEVEL 2 CORROSION. REPAIR METHOD IAW SRM 53-10-5 FOR FURTHER PROCESSING.
- [SDR FY4Y201103151](https://openairdocs.org/sdr/FY4Y201103151.md): Spar · corroded · Mar 11, 2011 · N705AA · Boeing 727223 · Trailing Edge Flaps
  > THE EXFOLIATION CORROSION IS FOUND AT LT INBD MID FLAP AFT SPAR LOWER CHORD AT WBL 82, DURING 6C CHECK. THE ORIGINAL THICKNESS OF THE CHORD IS 0.125". AFTER BLENT OUT, THE DIMENSION OF THE CORROSION AREA IS 3" (LENGTH) X 1" (WIDTH) AND REMAINDER THICKNESS IS
- [SDR FY4Y197M20110315D](https://openairdocs.org/sdr/FY4Y197M20110315D.md): Beam · corroded · Mar 11, 2011 · N705AA · Boeing 727223 · Horizontal Stabilizer Structure
  > RT HORIZONTAL STAB TRAILING LOWER BEAM SURFACE STA 220 TO 222 HAD EXFOLIATION CORROSION. ORIGINAL THICKNESS IS 0.105". AFTER CORROSION REMOVED, THE REMAINED THICKNESS WAS 0.065", AREA WAS 2.75" X 1". IT'S BEYOND LIMITED IAW SRM 55-10-1, PAGE 1, NOTE B. CORROS
- [SDR FY4Y197M20110315C](https://openairdocs.org/sdr/FY4Y197M20110315C.md): Beam · corroded · Mar 11, 2011 · N705AA · Boeing 727223 · Horizontal Stabilizer Structure
  > LT HORIZONTAL STAB TRAILING LOWER BEAM UPPER SURFACE STA 66 TO 70 HAD EXFOLIATION CORROSION. ORIGINAL THICKNESS WAS 0.091". AFTER CORROSION REMOVED, THE REMAINED THICKNESS WAS 0.025", AREA WAS 4" X 1". IT'S BEYOND LIMITED IAW SRM 55-10-1, PAGE 1, NOTE B. COR
- [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 FY4Y197M20110310](https://openairdocs.org/sdr/FY4Y197M20110310.md): Skin Panel · corroded · Mar 7, 2011 · N705AA · Boeing 727223 · Fuselage Main, Plate/Skin
  > DURING PERFORMED 6C-CHECK FOUND FUSELAGE EXTERIOR SKIN CORRODED (LEVEL 2) AT BS 1066 BETWEEN S-27L AND S-28L, IAW SRM 53-30-1, PAGE 2A PENETRATED DEPTH OUT OF LIMIT.
- [SDR I5PA20090805](https://openairdocs.org/sdr/I5PA20090805.md): Structure · corroded · Aug 6, 2009 · N705AA · Boeing 727223 · Fuselage Main, Structure
  > DURING 5C CHECK AND INSP, CORROSION WAS FOUND BETWEEN BS 950C AND 950E AND STR 28L AND 28R. REPAIRED IAW EI-727-090705.
- [SDR I5PA20090804](https://openairdocs.org/sdr/I5PA20090804.md): Skin · damaged · Aug 6, 2009 · N705AA · Boeing 727223 · Wing, Plate/Skin
  > DURING 5C CHECK AND INSP, CORROSION WAS FOUND ON THE SKIN INTERNAL SURFACE WHICH WAS UNDER THE PREVIOUS SKIN REPAIR DOUBLER FROM BS 1009 TO BS 1045 AND BETWEEN S-27L AND S-28R. REPAIRED IAW EI-727-090704.
- [SDR I5PA20090803](https://openairdocs.org/sdr/I5PA20090803.md): Keelbeam · corroded · Aug 6, 2009 · N705AA · Boeing 727223 · Wing, Center Box
  > DURING 5C CHECK AND INSP, CORROSION WAS FOUND ON RT KEEL BEAM INBD FLANGE AFT OF BS740. AFTER BLENDOUT AND MEASURED ORIGINAL THICKNESS BLEND OUT EXCEED LIMITS. REPAIRED CORROSION IAW EI-727-090703 AREA WAS BLEND OUT AND TREATED WITH ALODINE AND DOUBLE PRIME A
- [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 I5PA20090801](https://openairdocs.org/sdr/I5PA20090801.md): Spar · corroded · Aug 6, 2009 · N705AA · Boeing 727223 · Wing Spar
  > DURING 5C-CHECK AND INPS CORROSION WAS FOUND ON RT AND LT WING FRONT SPAR CHORD PLATE LWR SURFACE. AFTER BLEND OUT THE MAX LOSS OF MATERIAL THICKNESS WAS BEYOND THE ALLOWABLE LIMIT IAW SRM. FABRICATED AN INTERNAL REPAIR STRAP IAW EI-727-090701 HFEC ACCESSED
- [SDR 2008FA0000746](https://openairdocs.org/sdr/2008FA0000746.md): Pump · malfunctioned · Oct 15, 2008 · N705AA · Boeing 727200 · Engine Fuel Pump
  > CRUISE NR 1 ENG STARTED TO SPOOL DOWN OTHER PARAMETERS ARE NORMAL, PERFORMED IN-FLIGHT START CHECKLIST SEVERAL TIMES INCLUDING RESETTING SWITCHES, NO LIGHT OFF. ACFT DIVERTED AND THE CREW PERFORMED ENG INSPECTION AND START ON NR 1 ENG HIGH IGNITION SYS, ENGINE
- [SDR 2007FA0000946](https://openairdocs.org/sdr/2007FA0000946.md): Stringer · cracked · Oct 16, 2007 · N705AA · Boeing 727200 · Fuselage Main, Longeron/Stringer
  > THE AIRCRAFT INPUT FOR 4C CHECK AND CPCP ON SEPT 3, 2007. DURING CPCP, THE INSPECTOR PERFORMED VISUAL INSPECTION AND FOUND 5 INCH CRACK BOTH ON LT AND RT FUSELAGE STRINGER S18A BETWEEN BS940 AND BS945 ON SEPT 21, 2007. A PROPOSAL WAS INITIALLY SUBMITTED ON S
- [SDR 20010411CW003](https://openairdocs.org/sdr/20010411CW003.md): Trunnion · damaged · Mar 19, 2001 · N705AA · Boeing 727223 · Landing Gear Retraction/Extension System
  > SEVERE DAMAGE TO THE AFT TRUNNION SPUD AREA.
- [SDR AALA991403](https://openairdocs.org/sdr/AALA991403.md): Light · defective · Sep 18, 1999 · N705AA · Boeing 727223 · Emergency Lighting
  > DFW - DURING OVERNIGHT MAINTENANCE, AFT STAIR EMERGENCY LIGHTING INOPERATIVE. REPLACED EMERGENCY EXIT LIGHT ASSEMBLY. SYSTEM GROUND CHECKED NORMAL OPERATION. (M)
- [SDR AALA990684](https://openairdocs.org/sdr/AALA990684.md): Skin · corroded · May 7, 1999 · N705AA · Boeing 727223 · Wing, Plate/Skin
  > TUL - FOUND CORROSION ON LOWER CENTER TANK OUTER SKIN STATION 833 RBL 20-24. REMOVED CORROSION AND REPAIRED AREA PER ESO 11697, DATED 5-7-99 PAGES 1/2. (M)
- [SDR AALA981090](https://openairdocs.org/sdr/AALA981090.md): Light · inoperative · May 31, 1998 · N705AA · Boeing 727223 · Emergency Lighting
  > TPA - DURING OVERNIGHT MAINTENANCE, AFT STAIR EMERGENCY EXIT LIGHT INOPERATIVE. REPLACED AFT STAIR EMERGENCY EXIT LIGHT ASSEMBLY. SYSTEM GROUND CHECKED NORMAL OPERATION. (M)
- [SDR AALA980864](https://openairdocs.org/sdr/AALA980864.md): Floorbeam · corroded · Apr 30, 1998 · N705AA · Boeing 727223 · Fuselage Main, Floor Beam
  > TUL - RT AFT LAV FLOOR OUTBOARD OF FORWARD OUTBOARD TANK CABLE ATTACH LUG IS CORRODED, FORWARD OF INBOARD TANK CABLE ATTACH IS CORRODED. REMOVED CORRODED HAT CHANNEL AND INSTALLED SERVICEABLE HAT CHANNEL. (M)
- [SDR AALA960894](https://openairdocs.org/sdr/AALA960894.md): Skin · cracked · Jun 8, 1996 · N705AA · Boeing 727223 · Fuselage Main, Plate/Skin
  > TUL - FOUND CRACK IN FUSELAGE SKIN ON CROWN AT STATION 1096, RIGHT SIDE OF STRINGER NR 1 AT FASTENER FOR NR 2 ENG INLET FORWARD ATTACH. INSTALLED DOUBLER PER SB 727-53A0204 SRM 53-30-3 FIG 3 PAGE 12-14. (M)
- [SDR AALA960893](https://openairdocs.org/sdr/AALA960893.md): Stringer · cracked · Jun 8, 1996 · N705AA · Boeing 727223 · Fuselage Main, Longeron/Stringer
  > TUL - FOUND STRINGER END CRACKED STRINGER 15R AT THE LIGHT BOX FORWARD SIDE STATION 720B PLUS 4. REMOVED CRACK STRINGER AND SPLICED NEW STRINGER AS PER SRM 53-10-3 FIG 1. (M)
- [SDR AALA960892](https://openairdocs.org/sdr/AALA960892.md): Shear Tie · corroded · Jun 8, 1996 · N705AA · Boeing 727223 · Fuselage Miscellaneous Structure
  > TUL - FOUND CORROSION ON SHEAR TIE NEAR DOME NUTS, STATION 700 STRINGER 28L TO 28R. REMOVED SHEAR TIE AND INSTALLED NEW ONE PER SRM 57-10-3 PG 4. (M)
- [SDR AALA960891](https://openairdocs.org/sdr/AALA960891.md): Stringer · corroded · Jun 8, 1996 · N705AA · Boeing 727223 · Fuselage Main, Longeron/Stringer
  > FOUND CORROSION IN STRINGER 27R AT STATION 701. REMOVED OUT OF LIMITS STRINGER AND REPAIRED PER SRM 53-10-3. (M)
- [SDR AALA960890](https://openairdocs.org/sdr/AALA960890.md): Skin · corroded · Jun 8, 1996 · N705AA · Boeing 727223 · Fuselage Main, Plate/Skin
  > TUL - FOUND CORROSION ON BELLY SKIN AND CIRCUMFERENTIAL STRAP, STATION 680 TO 684, INBOARD OF STRINGER 27R. INSTALLED DOUBLER AND FILLER ALODINED, PRIMED, PER SRM 53-30-3. (M)
- [SDR AALA960889](https://openairdocs.org/sdr/AALA960889.md): Skin · corroded · Jun 8, 1996 · N705AA · Boeing 727223 · Fuselage Main, Plate/Skin
  > TUL - FOUND STRINGER 28 LEFT HAS CORROSION AND SKIN CORRODED STATION 580 TO 595. REMOVED AND REPLACED SECTION OF STRINGER AND SKIN AT STRINGER 28 LEFT STATION 580 TO 660 SRM 53-30-3 PAGE 12 - PG 14A. (M)
- [SDR AALA960888](https://openairdocs.org/sdr/AALA960888.md): Stringer · corroded · Jun 8, 1996 · N705AA · Boeing 727223 · Fuselage Main, Longeron/Stringer
  > TUL - FOUND STRINGER 27 LEFT HAS CORROSION STATION 514 TO STATION 525. CUT OUT CORROSION AND REPLACED STRINGER 27L FROM STATION 513 TO STATION 525, PER SRM 53-10-3 PG 3-4B. (M)
- [SDR AALA960887](https://openairdocs.org/sdr/AALA960887.md): Eng Inlet · corroded · Jun 8, 1996 · N705AA · Boeing 727223 · Nacelle/Pylon Structure
  > TUL - NR 2 ENGINE INLET CORRODED AT 11:00 POSITION. REMOVED CORRODED AREA AND MADE FLUSH REPAIR PER SRM 54-30-3 PAGE 2A AND 2B. (M)

Next page: https://openairdocs.org/deregistered/N705AA-2021-02-03/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 = 'N705AA' AND deregistration_id = 'N705AA-2021-02-03'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/deregistered/N705AA-2021-02-03/reports

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