N705AA, cancelled Feb 3, 2021

Service difficulty reports · 52

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

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duckdb -csv -c "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"

Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.

SDR I5PA20200106104Engine · damagedAFTER 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 -Dec 21, 2019 · N705AA · Boeing 757200 · Engine (Turbine/Turboprop)SDR I5PA2019030800000Smoke Detector · activatedMAIN CARGO SMOKE DETECTOR GOES ON IN FLIGHT.Mar 8, 2019 · N705AA · Boeing 727223 · Smoke DetectionSDR I5PA2018110470501Smoke Detector · unserviceableMAIN CARGO FIRE LIGHT AND BELL CAME ON IN FLIGHT. REPLACED FAULTY SMOKE DETECTOR UNIT.Nov 4, 2018 · N705AA · Boeing 727223 · Smoke DetectionSDR I5PA2017121170501Indicator · inoperativeDISCREPANCY: 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 GOODDec 10, 2017 · N705AA · Boeing 727223 · Airspeed/Mach IndicatorSDR FY4Y20141006003Skin · corrodedDURING 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 APOct 1, 2014 · N705AA · Boeing 727200 · Fuselage Main, Plate/SkinSDR FY4Y20141006002Skin · corrodedDURING 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 APPROVAOct 1, 2014 · N705AA · Boeing 727200 · Fuselage Main, Plate/SkinSDR FY4Y20141006001Skin · corrodedDURING 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.Oct 1, 2014 · N705AA · Boeing 727200 · Fuselage Main, Plate/SkinSDR FY4Y20141003007Skin · corrodedDURING 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 APPROSep 30, 2014 · N705AA · Boeing 727200 · Fuselage Main, Plate/SkinSDR FY4Y20141003006Skin · corrodedDURING 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 DATASep 30, 2014 · N705AA · Boeing 727200 · Fuselage Main, Plate/SkinSDR FY4Y20141003005Skin · corrodedDURING 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, Sep 30, 2014 · N705AA · Boeing 727200 · Wing, Plate/SkinSDR FY4Y20141003004Plate · corrodedDURING 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 ISSep 30, 2014 · N705AA · Boeing 727200 · Wing Miscellaneous StructureSDR FY4Y20141003003Plate · corrodedDURING 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 ISSep 30, 2014 · N705AA · Boeing 727200 · Wing Miscellaneous StructureSDR FY4Y20141003002Plate · corrodedDURING 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 Sep 30, 2014 · N705AA · Boeing 727200 · Wing Miscellaneous StructureSDR FY4Y20141003001Plate · corrodedDURING 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 THICKSep 30, 2014 · N705AA · Boeing 727200 · Wing Miscellaneous StructureSDR I5PA201406010002Engine · leakingNUMBER 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 ASSURANCEJun 25, 2014 · N705AA · Boeing 727200 · Engine (Turbine/Turboprop)SDR I5PA201406010001Engine · leakingNR 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 AJun 25, 2014 · N705AA · Boeing 727200 · Turbine Engine Oil SystemSDR FY4Y20121122197Web · corrodedDURING 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, PAGENov 19, 2012 · N705AA · Boeing 727200 · Wing Main, Frame StructureSDR FY4Y20121116197Skin · corrodedDURING 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 Nov 13, 2012 · N705AA · Boeing 727200 · Fuselage Main, Plate/SkinSDR FY4Y201211130001Structure · corrodedDURING 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 IANov 13, 2012 · N705AA · Boeing 727200 · Fuel StorageSDR FY4Y2012F00244Structure · corrodedPERFORMED 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 53-00-00Nov 13, 2012 · N705AA · Boeing 727200 · Fuel StorageSDR FY4Y20110317Strap · corrodedHE 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 Mar 16, 2011 · N705AA · Boeing 727200 · Trailing Edge FlapsSDR FY4Y20110315Splice · corrodedTHE 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.Mar 14, 2011 · N705AA · Boeing 727223 · Trailing Edge FlapsSDR FY4Y197M20110315ESeat Track · corrodedDURING 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.Mar 11, 2011 · N705AA · Boeing 727223 · Fuselage, Seat/Cargo Attach FittingsSDR FY4Y201103151Spar · corrodedTHE 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 ISMar 11, 2011 · N705AA · Boeing 727223 · Trailing Edge FlapsSDR FY4Y197M20110315DBeam · corrodedRT 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. CORROSMar 11, 2011 · N705AA · Boeing 727223 · Horizontal Stabilizer StructureSDR FY4Y197M20110315CBeam · corrodedLT 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. CORMar 11, 2011 · N705AA · Boeing 727223 · Horizontal Stabilizer StructureSDR FY4Y197M20110315BBeam · corrodedLT 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. CORRMar 11, 2011 · N705AA · Boeing 727200 · Horizontal Stabilizer StructureSDR FY4Y197M20110315ASpar · corrodedHEAVY 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, PAGMar 11, 2011 · N705AA · Boeing 727200 · Fuselage Main, FrameSDR FY4Y197M20110315Skin · corrodedHEAVY 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, FMar 11, 2011 · N705AA · Boeing 727200 · Trailing Edge FlapsSDR FY4Y197M20110310Skin Panel · corrodedDURING 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.Mar 7, 2011 · N705AA · Boeing 727223 · Fuselage Main, Plate/SkinSDR I5PA20090805Structure · corrodedDURING 5C CHECK AND INSP, CORROSION WAS FOUND BETWEEN BS 950C AND 950E AND STR 28L AND 28R. REPAIRED IAW EI-727-090705.Aug 6, 2009 · N705AA · Boeing 727223 · Fuselage Main, StructureSDR I5PA20090804Skin · damagedDURING 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.Aug 6, 2009 · N705AA · Boeing 727223 · Wing, Plate/SkinSDR I5PA20090803Keelbeam · corrodedDURING 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 AAug 6, 2009 · N705AA · Boeing 727223 · Wing, Center BoxSDR I5PA20090802Spar · corrodedDURING 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 SMOOAug 6, 2009 · N705AA · Boeing 727200 · Wing SparSDR I5PA20090801Spar · corrodedDURING 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 Aug 6, 2009 · N705AA · Boeing 727223 · Wing SparSDR 2008FA0000746Pump · malfunctionedCRUISE 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, ENGINEOct 15, 2008 · N705AA · Boeing 727200 · Engine Fuel PumpSDR 2007FA0000946Stringer · crackedTHE 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 SOct 16, 2007 · N705AA · Boeing 727200 · Fuselage Main, Longeron/StringerSDR 20010411CW003Trunnion · damagedSEVERE DAMAGE TO THE AFT TRUNNION SPUD AREA.Mar 19, 2001 · N705AA · Boeing 727223 · Landing Gear Retraction/Extension SystemSDR AALA991403Light · defectiveDFW - DURING OVERNIGHT MAINTENANCE, AFT STAIR EMERGENCY LIGHTING INOPERATIVE. REPLACED EMERGENCY EXIT LIGHT ASSEMBLY. SYSTEM GROUND CHECKED NORMAL OPERATION. (M)Sep 18, 1999 · N705AA · Boeing 727223 · Emergency LightingSDR AALA990684Skin · corrodedTUL - 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)May 7, 1999 · N705AA · Boeing 727223 · Wing, Plate/SkinSDR AALA981090Light · inoperativeTPA - DURING OVERNIGHT MAINTENANCE, AFT STAIR EMERGENCY EXIT LIGHT INOPERATIVE. REPLACED AFT STAIR EMERGENCY EXIT LIGHT ASSEMBLY. SYSTEM GROUND CHECKED NORMAL OPERATION. (M)May 31, 1998 · N705AA · Boeing 727223 · Emergency LightingSDR AALA980864Floorbeam · corrodedTUL - 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)Apr 30, 1998 · N705AA · Boeing 727223 · Fuselage Main, Floor BeamSDR AALA960894Skin · crackedTUL - 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)Jun 8, 1996 · N705AA · Boeing 727223 · Fuselage Main, Plate/SkinSDR AALA960893Stringer · crackedTUL - 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)Jun 8, 1996 · N705AA · Boeing 727223 · Fuselage Main, Longeron/StringerSDR AALA960892Shear Tie · corrodedTUL - 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)Jun 8, 1996 · N705AA · Boeing 727223 · Fuselage Miscellaneous StructureSDR AALA960891Stringer · corrodedFOUND CORROSION IN STRINGER 27R AT STATION 701. REMOVED OUT OF LIMITS STRINGER AND REPAIRED PER SRM 53-10-3. (M)Jun 8, 1996 · N705AA · Boeing 727223 · Fuselage Main, Longeron/StringerSDR AALA960890Skin · corrodedTUL - 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)Jun 8, 1996 · N705AA · Boeing 727223 · Fuselage Main, Plate/SkinSDR AALA960889Skin · corrodedTUL - 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)Jun 8, 1996 · N705AA · Boeing 727223 · Fuselage Main, Plate/SkinSDR AALA960888Stringer · corrodedTUL - 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)Jun 8, 1996 · N705AA · Boeing 727223 · Fuselage Main, Longeron/StringerSDR AALA960887Eng Inlet · corrodedTUL - 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)Jun 8, 1996 · N705AA · Boeing 727223 · Nacelle/Pylon Structure
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