Tatonduk Outfitters, Ltd.

Operated by TATONDUK OUTFITTERS LTD DBA (per NTSB report)

A partial loss of engine power for reasons that could not be determined based on available evidence.

Operated by Tatonduk Outfitters Limited (per NTSB report)

The pilot's failure to maintain an adequate glidepath during the approach, which resulted in the airplane impacting rocks and dirt at the runway threshold, a separation of the right main landing gear, and a loss of directional control.

Operated by TATONDUK OUTFITTERS LIMITED DBA (per NTSB report)

The fatigue failure of the lower wing skin due to aging mechanisms. Contributing to the failure were lower wing skin inspection procedures insufficient to identify the crack.

Operated by TATONDUK OUTFITTERS LTD (per NTSB report)

A load shift during takeoff, which resulted in substantial damage to the aft bulkhead and associated structures.

Operated by TATONDUK OUTFITTERS LTD (per NTSB report)

The pilot's continued flight into adverse weather conditions, and an inadvertent stall. Factors associated with the accident are fog, obscuration, and icing conditions.

Operated by TATONDUK OUTFITTERS LTD (per NTSB report)

THE DAMAGE SUSTAINED WHEN STRIKING A ROCK DURING THE PREVIOUS TAKEOFF ROLL WHICH RESULTED IN THE MAIN LANDING GEAR'S COLLAPSE DURING LANDING.

Sanction: $7,500 · case closed 2020-10-21

Sanction: $8,250 · case closed 2020-02-21

Sanction: $4,500 · case closed 2017-02-22

Sanction: $11,000 · case closed 2014-10-02

Sanction: $7,500 · case closed 2013-04-12

Sanction: $10,000 · case closed 2008-05-20

Sanction: $6,800 · case closed 2008-08-20

Part: DRIVE CABLE — DEFORMED (ZONE 500) · airframe 985 hrs · 1,062 cycles

FLAP FAIL CASS MESSAGE INDICATED WHEN FLAP DEPLOYED FROM FULL UP. UPON INVESTIGATION FOUND THE LT FLAP HAD A SLIGHT TWIST. THE OTBD ACTUATOR HAD NOT ENGAGED TO DRIVE THE FLAP AND THE INBD ACTUATOR DROVE THE INBOARD SIDE DOWN ABOUT 3 DEGREES BEFORE THE SYSTEM DETECTED AN ASYMMETRY AND STOPPED THE MOVEMENT. AFTER THE FLAP WAS UNLOADED/UNTWISTED DURING MX INVESTIGATION THE FLAP APPEARS TO HAVE A SLIGHT DOWN TURN ON THE INBD TRAILING EDGE. THE CURRENT SUSPECTED CAUSE IS THE FLEXIBLE DRIVE SHAFT BETWEEN THE ACTUATORS MIGRATED INBD AND BECAME DISENGAGED WITH THE OTBD ACTUATOR.

Part: DOUBLER — CORRODED (ZONE 600) · airframe 40,283 hrs

R/H SPAR NEEDS REPAIR DOUBLER AT STA 167 REPLACED DUE TO CORROSION AT MAX LIMIT.

Part: FLANGE — CRACKED (ZONE 600) · airframe 40,283 hrs

CRACK INDICATION NR 3 TANK 182C FLANGE, REPAIRED PER EO 2609

Part: SKIN — CORRODED (ZONE 100) · airframe 40,283 hrs

CORROSION WAS NOTED ON FUSELAGE PLATING @ L/H OVERWING EMERGENCY EXIT DOOR FRAME, LOWER AFT CORNER. REPAIRED PER EO 2608

Part: STRUCTURE — DAMAGED (ZONE 100) · airframe 19,280 hrs · 12,427 cycles

AIRCRAFT HAD A STATIONARY TAIL STRIKE DAMAGING THE LOWER TAIL CONE AREA AND TAIL TIE DOWN FITTING. AIRCRAFT WAS PARKED ON A SLOPE AND WHEN THE PILOTS EXITED THE AIRCRAFT THE PLANE TILTED BACK AND THE TAIL STRUCK THE GROUND. CAUSED DAMAGE TO LOWER AFT TAIL CONE BULKHEAD, TAIL TIE DOWN FITTING, AND AFT CENTER LOWER TAIL CONE STRINGER.

Part: DUCT CLAMP — LEAKING (NR 2 ENGINE) · airframe 46,777 hrs · 26,321 cycles

TAIL COMPARTMENT TEMP HIGH ILLUMINATED, FOUND #2 ENGINE BLEED AIR LEAK IN TAIL SECTION, REPLACED CLAMP IAW MD-80 AMM 20-10-11. GROUND RUN-UP OPERATIONAL CHECK GOOD.

Part: OVERHEAT SENSOR — ACTIVATED (ZONE 100) · airframe 46,777 hrs · 26,322 cycles

TAIL COMPARTMENT TEMP HIGH ILLUMINATED, REPLACED R/H TAIL COMPARTMENT TEMP SENSOR IAW MD-80 AMM 36-20-02. OPERATIONAL CHECK GOOD

Part: DUCT — CRACKED (ZONE 100) · airframe 46,778 hrs · 26,323 cycles

TAIL COMPARTMENT TEMP HIGH LIGHT ILLUMINATED DURING CLIMB. FOUND RT BLEED AIR SOURCE DUCT WELD BROKEN. REMOVED AND REPLACED 13THSTAGE BLEED AIR SOURCE DUCTING BETWEEN ENGINE AND AUGMENTER VALVE IAW AMM 20-10-11. LEAK CHECK GOOD IAW AMM 71-00-00 CONFIG 4 STEP 4

Part: ENGINE — DAMAGED · airframe 187 hrs · 173 cycles

INERTIAL SEPARATOR ACTUATOR TOP ATTACHMENT ROD END LOOSENED AND BECAME EXCESSIVELY LOOSE ON BOTH LEFT AND RIGHT ENGINES. THE NUT RETAINER BRACKET OF THE RIGHT ENGINE'S I/S ACT. ROD END BROKE AT THE BOLT HOLE WHERE THE ROD END PASSES THROUGH, AND THE BRACKET WAS FOUND ON TOP OF THE ENGINE INLET SCREEN. THE SMALLER PIECE THAT BROKE OFF IS SUSPECTED TO HAVE MADE IT PAST THE INLET SCREEN AND GONE THROUGH THE ENGINE. A BORESCOPE INSPECTION THAT WAS DONE SUPPORT THIS THEORY AS THE FIRST STAGE COMPRESSOR SHOWS SIGNIFICANT FOD INGESTION DAMAGE TO THE LEADING EDGES OF THE COMPRESSOR BLADES.

Part: ROD END — DAMAGED · airframe 187 hrs · 173 cycles

INERTIAL SEPARATOR ACTUATOR TOP ATTACHMENT ROD END LOOSENED AND BECAME EXCESSIVELY LOOSE ON BOTH LEFT AND RIGHT ENGINES. THE NUT RETAINER BRACKET OF THE RIGHT ENGINE'S I/S ACT. ROD END BROKE AT THE BOLT HOLE AND THE BRACKET WAS FOUND ON TOP OF THE ENGINE INLET SCREEN. THE SMALLER PIECE THAT BROKE OFF IS SUSPECTED TO HAVE MADE IT PAST THE SCREEN AND GONE THROUGH THE ENGINE. BORESCOPE IMAGES SUPPORT THIS THEORY AS THE FIRST STAGE COMPRESSOR SHOWS SIGNIFICANT FOD INGESTION DAMAGE.

Part: ROD END — BROKEN · airframe 173 hrs · 135 cycles

FLIGHT CREW WROTE UP "INERTIAL SEP R" CAS WARNING MESSAGE WAS DISPLAYED. UPON INVESTIGATION OF THE RIGHT ENGINE INERTIAL SEPARATOR, IT WAS FOUND THAT THE UPPER ATTACHMENT ROD END FOR THE INERTIAL SEPARATOR ACTUATOR HAD BROKEN OFF AT THE SHANK OF THE ROD END CAUSING THE ACTUATOR TO FLOAT AROUND AND NOT PROPERLY ACTUATE THE ICE VANE DOORS.

Part: ROD END — BROKEN · airframe 173 hrs · 135 cycles

FLIGHT CREW WROTE UP "INERTIAL SEP R" CAS WARNING MESSAGE WAS DISPLAYED. UPON INVESTIGATION OF THE RIGHT ENGINE INERTIAL SEPARATOR, IT WAS FOUND THAT THE UPPER ATTACHMENT ROD END FOR THE INERTIAL SEPARATOR ACTUATOR HAD BROKEN OFF AT THE SHANK OF THE ROD END CAUSING THE ACTUATOR TO FLOAT AROUND AND NOT PROPERLY ACTUATE THE ICE VANE DOORS.

Part: LONGERON — CORRODED (ZONE 100) · corrosion level 3 · airframe 75,363 hrs · 55,749 cycles

CORROSION ON FUSELAGE LONGERON #30 AT STATION 1011. REMOVE CORROSION AND PERFORM REPAIR PER -STS EA 81-2024-037.

Part: HOSE — LEAKING (HYD SYSTEM) · airframe 62,955 hrs · 48,258 cycles

ON DESCENT "A" SYSTEM HYDRAULIC QUANTITY FLUID STARTED DECREASING. FOUND LEAK FROM HOSE FITTING ON #2 SPOILER ACTUATOR. REPLACED ORING ON FITTING

Part: UNLOCK CYLINDER — LEAKING (NLG) · airframe 46,075 hrs · 25,545 cycles

NOSE LANDING GEAR FAILED TO EXTEND WITH NORMAL MEANS, CYCLED GEAR AND NOSE GEAR EXTENDED NORMALLY. LANDED WITH NO FURTHER INCEDENT

Part: HINGE — WORN (NLG DOOR) · airframe 47,584 hrs · 25,104 cycles

BIG VIBRATION FELT AFTER TAKEOFF IN AIRCRAFT AND YOKE. NOSE GEAR FORWARD DOORS CLOSING LINKAGE FOUND TO BE WORN

Part: MOUNT — CRACKED (ZONE 400) · airframe 23 hrs · 22 cycles

LEFT AND RIGHT ENGINE INERTIAL SEPARATOR MOUNTING STRUCTURE, NS 41 TO NS 50 CRACKED.

Part: UNKNOWN — UNKNOWN (UNKNOWN)

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.

Part: UNKNOWN — UNKNOWN (UNKNOWN)

OUTER WING TIP, SLAT AND LEADING EDGE DAMAGED. REPAIR OF DAMAGE TO AIRCRAFT WING TIP CAUSED BY CONTACT WITH FENCE GATE. INSPECTION OF FRONT WING SPAR IN AFFECTED AREA, INSTALLATION OF SERVICABLE WING LEADING EDGE, WINGTIP AND SLAT.

Part: NONE — NONE

CORRODED ZEE CHANNEL REPLACEMENT, COCKPIT F.O./CENTER WINDSHIELD. REQUESTING AUTHORIZATION TO REPLACE ZEE CHANNEL AT LOWER INTERSECTION OF F.O'S AND CENTER WINDOWS. REMOVE AND REPLACE CORRODED ZEE ANGLE IAW DC-9/MD-80 SRM STANDARD PRACTICES. NEW ANGLE IS SAME TYPE AND SIZE AS REMOVED. HI-LOKS WILL BE SUBSTITUTED FOR MS20426AD RIVETS PER THE SRM.

Part: NONE — NONE

MAIN CARGO DOOR AFT SEAL DEPRESSOR PERMANENT REPAIR REFERENCE AEI TICKET 21004 R00 (002) STEP 1.2. TO REPAIR DAMAGE TO MAIN CARGO DOOR AFT SEAL DEPRESSOR. CUTOUT EXISTING SEAL DEPRESSOR DAMAGES SECTION AT AEO PROPOSED CUTOUT LINES AS PER ATTACHED (967 MCD #3) FOR AOG TICKET 21004 R00 (002) AND FABRICATE A NEW SEAL DEPRESSOR SECTION AS PER ATTACHED (AEI DWG AE5621_IR) TITLED SEAL DEPRESSOR FOR AOG TICKET 21004 R00 (002)) AND INSTALL A PERMANENT REPAIR.

Part: NONE — NONE

CRACKED TANG ON FRONT SPAR UPPER CAP. TO REPAIR A CRACKED TANG ON THE FORWARD EDGE OF THE FRONT SPAR UPPER CAP. USE THIS EO IN CONJUNCTION WITH STS EA 81-2022-151.

Part: BATTERY — DISCHARGED (SMOKE DETECTOR) · airframe 62,774 hrs · 48,170 cycles

CREW RECEIVED A LOWER AFT CARGO FIRE WARNING AT FL360 ON ARRIVAL INTO EFD. CREW IMMEDIATELY INITIATED THE EMERGENCY PROCEDURE AND BEGAN AN EMERGENCY DECENT AND DIVERTED TO CWF, WHICH WAS JUST SOUTH OF POSITION. THE FIRE CREW SWEPT AIRCRAFT UPON LANDING AND NO EVIDENCE OF FIRE WAS FOUND. LOWER CARGO DETECTION SYSTEM WAS TESTED AND FOUND THAT ONE DETECTOR HAD LOW BATTERY WHICH WAS REPLACED. SUBSEQUINT TESTING OF SYSTEM FOUND NO ADDITIONAL FAULTS AND SYSTEM TESTS PASSED.

Part: NONE — NONE

FUSELAGE SKIN GOUGED AT F/STA 463, STR 21L. TO REPAIR A DEEP GOUGE ON FUSELAGE SKIN. PERFORM SKIN REPAIR PER AEI EO 20455.

Part: NONE — NONE

MAIN CARGO DOOR LATCHES REPAIR. DURING TORQUE TUBE ISSUES ON ABOVE AIRCRAFT, ALL LATCHES RESULTED WITH GOUGES CAUSED BY THE LOCK PINS. IN ORDER TO CONTINUE WITH LATCHES EVALUATION, IT WILL BE REQUIRED TO BLEND OUT THE LATCHES AND PROVIDE THE THICKNESS OF REMAINING MATERIAL. REQUIRED TO BLEND OUT THE LATCHES AND STATIC ANALYSIS OF AE5003 LEVERS #4 AND #7 WERE FOUND TO BE OF NEGATIVE MARGIN AND WILL NEED TO BE REPLACED. SEE APPENDIX A FOR STATIC ANALYSIS NOTES.

Part: NONE — NONE

DENT ON FUESELAGE SKIN AT F/STA 393, STR 15L. TO REPAIR DENT DAMAGE ON THE FUSELAGE SKIN AT F/STA 393, STR 15L. PERFORM FUSELAGE SKIN REPAIR PER STS EA 81-2022-122. RE-INSPECTION INSTRUCTIONS TO BE PROVIDED WITH DTA NO LATER THAN 12 MONTHS FROM REPAIR COMPLETION. THE SIGNED WORKING COPY OF PRELIMINARY EO 2224 CAN BE ATTACHED TO THIS EO AT FINAL SIGN OFF.

Part: NONE — NONE

FUSELAGE STRINGER REPAIR AT F/STA -38, STRINGER 14R. TO REPAIR A CRACKED STRINGER BEHIND #4 FIRE BOTTLE, STRINGER 14R, F/STA -38. PERFORM STRINGER REPAIR PER DC-6A&B OVERHAUL MANUAL FIGURE 12-2.

Part: STRINGER — CRACKED (ZONE 100)

FUSELAGE STRINGER REPAIR AT F/STA -38, STRINGER 14R. TO REPAIR A CRACKER STRINGER BEHIND #4 FIRE BOTTLE. STRINGER 14R, F/STA -38. PERFORM STRINGER REPAIR PER DC-6A&B OVERHAUL MANUAL FIGURE 12-2.

Part: RETAINER — DAMAGED (DOOR SEAL)

SEAL RETAINER INSTALLATION - DEVIATION. DAMAGED SEAL RETAINER PN: AE5660-11 MUST BE REPLACED WITH ALTERNATE PN: AE5738-16. DURING A VISUAL INSPECTION AROUND THE DOOR, IT WAS FOUND A CRACKED SEAL RETAINER PN: AE5660-11 (SEE FIGURE 1). THUS, A SECTION OF EXISTING SEAL RETAINER IS GOING TO BE TRIMMED OUT AND WILL BE SUBSTITUTED WITH A SECTION OF SEAL RETAINER PN: AE5738-16, PER THE INSTRUCTIONS OF THIS ENGINEERING ORDER.

Part: LONGERON SPLICE — CORRODED (ZONE 100)

CORRODED LONGERON AND SPLICES FROM F/STA 1211 TO 1259. TO REMOVE AND REPLACE A CORRODED LONGERON SECTION (29L) AND ITS TWO CORRODED SPLICES AT F/STA 1211 AND 1259. REMOVED CORRODED SPLICES AND STRINGER SECTION, REPLACE WITH NEW. PERFORM ALL WORK FROM DC-9/MD-80 SRM 53-02 PAGES 43 FIGURE 16.

Part: NONE — NONE

L/H HORIZONTAL STAB FAIRING CRACKED. REPAIR OF CRACK IN L/H HOIZONTAL STAB TO VERT STAB FAIRING. REPAIR HORIZONTAL STAB FAIRINGS PER ENGINEERING DRAWING NR-0014.

Part: NONE — NONE

R/H HORIZONTAL STAB FAIRING CRACKED. REPAIR OF CRACK IN R/H HORIZONTAL STAB TO VERT STAB FAIRING. REPAIR HORIZONTAL STAB FAIRINGS PER ENGINEERING DRAWING NR-0014.

Part: NONE — NONE

CORRODED ZEE CHANNELS AROUND COCKPIT WINDSHIELD. TO REPLACE CORRODED ZEE CHANNELS AT THE BOTTOM CORNERS OF THE CENTER WINDSHIELD. REMOVE CORRODED ZEE ANGLES, AND INSTALL NEW ONES FOLLOWING STANDARD PRACTICES PER DC-9/MD-80 SRM. INSTALL NEW PARTS WITH SAME TYPE AND SIZES AS REMOVED, RIVETS AND HI-LOKS, AND USE SUBSTITUTE FASTENERS IF REQUIRED.

Part: NONE — NONE

FUSELAGE SKIN DAMAGED AT CANT STA 1497. TO REPAIR A DENT IN THE FUSELAGE SKIN AT CANT STATION 1497. FUSELAGE SKIN @ CANT/STA 1497 R/H DAMAGED. SEE ATTACHED REPORT NO. NR-0155SA REV IR FOR ACCOMPLISHMENT INSTRUCTION AND 8110-3 APPROVAL.

Part: DUCT — CRACKED (ZONE 400) · airframe 62,562 hrs · 48,035 cycles

ON CLIMB APPROXIMATELY 1500' #3 ENGINE HAD FIRE WARNING. ACCOMPLISHED CHECKLIST. LIGHT EXTINGUISHED DID NOT FIRE BOTTLE. RETURNED TO KFLL. ON VISUAL INSPECTION OF ENGINE IT WAS FOUND THAT THE BLEED AIR DUCT HAD RUPTURED/CRACKED.

Part: NONE — NONE · airframe 43,868 hrs · 23,210 cycles

LEFT PAC SUPPLY PRESSURE DROPPED TO ZERO FOLLOWED BY LOSS OF PRESSURIZATION WHILE IN CRUISE TO ANC. FOUND LOOSE CLAMP AND DUCTING FROM ACM OUTPUT.

Part: SKIN — CRACKED (HORIZONTAL STAB)

CRACKED R/H HORIZONTAL STABILIZER LEADING EDGE AT STATION 109. TO REPAIR A CRACK LEADING EDGE SKIN ON THE R/H HORIZONTAL STABILIZER AT STATION 109. STOP DRILL CRACK AND REPAIR LEADING EDGE PER DC-6 A&B OVERHAUL MANUAL FIGURED 15-31 SHEET 2 OF 2.

Part: SKIN — CORRODED (AFT CARGO DOOR)

AFT CARGO DOOR SKIN REPAIR. TO REPAIR A CORRODED SKIN SEAM AT THE AFT EDGE OF THE MAIN CARGO DOOR AT F/STA 798. PERFORM REPAIRS AT AFT EDGE OF MAIN CARGO DOOR PER DC-6 A&B OVERHAUL MANUAL FIGURE 12-22.

Part: SKIN — CORRODED (FWD CARGO DOOR)

FWD CARGO DOOR CORRODED STRUCTURE. TO REPAIR A CORRODED SKIN ON THE MAIN CABIN FORWARD CARGO DOOR AROUND THE DOOR LATCH ASSEMBLY (F/STA 122 APPROXIMATELY). PERFORM REPAIR PER STS EA 80-2021-124.

Part: SKIN — CORRODED (BS 82 S1-2R)

UPPER FUSELAGE SKIN CORROSION @ F/STA 157. TO REPAIR CORRODED FUSELAGE SKIN AROUND THE GPS ANTENNA AT F/STA 82 BETWEEN STRINGER 1R & 2R. PERFORM REPAIR PER DC-6 A&B OHM FIGURE 12-22.

Part: PUMP — FAULTED (FUEL BOOST) · airframe 59,085 hrs · 31,263 cycles

CENTER FUEL PRESSURE LOW LIGHT ILLUMINATED/CENTER TANK FAILS TO FEED IN FLIGHT. RAN QRH PROCEDURE.(FOUND AFT CENTER FUEL TANK BOOST PUMP CIRCUIT BREAKER OPEN)

Part: LINER — DELAMINATED (NR 1 ENGINE) · airframe 43,677 hrs · 23,017 cycles

ON DEPARTURE #1 ENGINE COMMPRESSOR STALLS, REDUCED POWER AND RETURNED TO KLRD, UPON VISUAL INSPECTION TURBINE LINER WAS DELAMINATED FROM ENGINE TURBINE CASE.

Part: FRAME — DAMAGED (BS 180 S24R)

OUT OF LIMIT GAUGE ON S/STA 180 FRAME AT STRINGER 24R. TO REPAIR A FUSELAGE FRAME WITH OUT OF LIMIT GAUGE. CUT OUT DAMAGE AND INSTALL REPAIR PARTS PER DC-9/MD-80 SRM 53-03 FIGURE 4. MAINTENANCE REQUIREMENTS: NORMAL MAINTENANCE, SEE PAGE 4 FOR DEATAILS.

Part: SKIN — CRACKED (BS 699-704)

6-8 INCH CRACK @ STA 699-704 APPX. RBL 24. REPAIR OF SKIN DAMAGE CAUSED BY CARGO LOADING/UNLOADING. REPAIR DAMAGE TO FUSELAGE SKIN @ STA 699-704 RBL 24 PER STS ENGINEERING AUTHORIZATION 81-2021-039.

Part: GENERATOR — INOPERATIVE (LEFT) · airframe 56,696 hrs · 30,089 cycles

LEFT GENERATOR OFF LIGHT ILLUMINATED IN FLIGHT. WHEN L GEN WAS RESET PER THE QRH THE AC CROSSTIE LOCKOUT LIGHT AND DC BUS OFF LIGHTS ALSO ILLUMINATED

Part: SKIN — CORRODED (RT WING)

CORROSION IN RIGHT HAND LOWER WING SKIN AT STATION 422, STRINGER 16. CORROSION IN RIGHT HAND LOWER WING SKIN AT STATION 422, STRINGER 16. CORROSION OF RH LOWER WING SKIN AT STA 422, STRINGER 16 WITH SMALL CRACK AROUND A FASTERNER REQUIRING A !" BY 0.5" TRIM OUT TO REMOVE DAMAGE.

Part: FIRE DETECTOR — FALSE ACTIVATION (CARGO BAY) · airframe 56,499 hrs · 29,833 cycles

CARGO FIRE MASTER WARNING ILLUMINATED WITH LOWER AFT COMPARTMENT FIRE INDICATION. NO FIRE DETECTED AFTER LANDING.

Part: STIFFENER — CRACKED (LT WING)

L/H WING FRONT SPAR VERTICAL STIFFENER CRACKED AT W/STA 255L. TO REPLACE A CRACKED VERTICAL STIFFENER ON THE LEFT WING FRONT SPAR WEB AT W/STA 254. REPLACE VERTICAL STIFFENER PER EA 20-2021-008. OBTAIN DTA WITHIN 12 MONTHS.

Part: SKIN — CORRODED (LT ELEVATOR TE)

CORROSION ON L/H ELEVATOR OUTBOARD TRAILING EDGE. TO REPAIR CORRODED ELEVATOR SKIN AT THE TRAILING EDGE IN THE STATIC WICKS AREA. PERFORM REPAIR OF ELEVATOR TRAILING EDGE PER STS ENGINEERING AUTHORIZATION 80-2021-016 AND 80-2021-015. OBTAIN DTA WITHIN 12 MONTHS.

Part: WEB — DAMAGED (LT AILERON) · airframe 62,415 hrs · 47,951 cycles

DAMAGE WEB AT L/H AILERON TAB HINGE ASSEMBLY. TO PREFORM SPLICE ON A DAMAGED WEB SUPPORTING THE L/H OUTBOARD AILERON TRIM ROD HINGE ASSEMBLY.REMOVE AILERON TRIM ROD HINGE ASSEMBLY. REPAIRE DAMAGE WEB PER B727 SRM 51-40-02 TYPICAL WEB REPAIR. INSTALL AILERON TRIM HINGE ASSEMBLY.