N87070
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
29 reports on file, 1995-02-01 – 2000-11-24.
Part: BEAM — CORRODED (FUSELAGE) · airframe 84,635 hrs · 17,230 cycles
INSPECTION FOUND GALLEY G3 L/H AND R/H O/B SUPPORT BEAMS CORRODED AT STA Y = 450-535, X = 24L AND AT X = 23R. THE SUPPORT BEAMS WERE REMOVED AND NEW SUPPORT BEAMS WERE INSTALLED IAW ECRA 5100-01844 AND SRM 53-11-01.
Part: SUPPORT BRACKET — CORRODED (FUSELAGE) · airframe 84,635 hrs · 17,230 cycles
INSPECTION FOUND LONGITUDINAL J SECTION FLOOR SUPPORT BEAM CORRODED AT STA Y = 1900-2007, X = 24R. THE SUPPORT BEAM WAS REMOVED AND A NEW SUPPORT BEAM WAS INSTALLED IAW ECRA 5100-01844 AND SRM 53-16-01.
Part: ANGLE — CORRODED (FUSELAGE) · airframe 84,635 hrs · 17,230 cycles
INSPECTION FOUND T-ANGLE ON REAR PRESSURE BULKHEAD CORRODED AT ATTACHMENT POINTS TO FORE AND AFT BEAMS AT STA Y = 2007, X = 24L, 58L, 24R, AND 58R. THE T-ANGLE WAS REMOVED AND A NEW SECTION WAS INSTALLED IAW SRM 53-40-00, FIGURE 16.
Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 84,635 hrs · 17,230 cycles
INSPECTION FOUND TRANSVERSE J SECTION AFT OF LAVS E AND F CORRODED AT STA Y = 1884, X = 27L-33L. THE J SECTION WAS REMOVED AND A NEW SECTION WAS INSTALLED IAW ECRA 5100-01844 AND SRM 53-16-01.
Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 84,635 hrs · 17,230 cycles
INSPECTION FOUND GALLEY G3 FORWARD J-SECTIONS CORRODED AT STA Y = 450, X = 2L-19L, AND AT X = 2R-19R. THE J-SECTIONS WERE REMOVED AND NEW SECTIONS WERE INSTALLED IAW ECRA 5100-01844 AND SRM 53-11-01.
Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 84,635 hrs · 17,230 cycles
INSPECTION FOUND FORWARD GALLEY/LAV AREA FLOORBEAM SECTIONS CORRODED AT Y = 375-475, X = 30R, 46R-48R, AND 50R-60R. THE FLOORBEAM SECTIONS WERE REMOVED AND NEW SECTIONS WERE INSTALLED IAW SRM 53-11-01.
Part: BEAM — CORRODED (FUSELAGE) · airframe 84,635 hrs · 17,230 cycles
INSPECTION FOUND LAV E O/B SUPPORT BEAM CORRODED AT STA Y = 1821-1884, X = 36L. THE SUPPORT BEAM WAS REMOVED AND A NEW SUPPORT BEAM WAS INSTALLED IAW ECRA 5100-01844 AND SRM 53-16-01.
Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 84,635 hrs · 17,230 cycles
INSPECTION FOUND TRANSVERSE J-SECTIONS AFT OF LAVS E AND F CORRODED AT STA Y = 1884, X = 60R-90R, X = 60L-90L, AND X = 27R-33R. THE J-SECTIONS WERE REMOVED AND NEW SECTIONS WERE INSTALLED IAW ECRA 5100-01844 AND SRM 53-16-01.
Part: SUPPORT BRACKET — CORRODED (FUSLAGE) · airframe 84,635 hrs · 17,230 cycles
INSPECTION FOUND LONGITUDINAL J-SECTION FLOOR SUPPORT BEAM CORRODED AT STA Y = 1900-2007, X = 24L. THE SUPPORT BEAM WAS REMOVED AND A NEW SECTION WAS INSTALLED IAW ECRA 5100-01844 AND SRM 53-16-01.
Part: BEAM — CORRODED (FUSELAGE) · airframe 84,635 hrs · 17,230 cycles
INSPECTION FOUND LAV E AND F I/B SUPPORT BEAMS CORRODED AT Y = 1844-1857, X = 5R AND AT X = 5L. THE SUPPORT BEAMS WERE REMOVED AND NEW SUPPORT BEAMS WERE INSTALLED IAW ECRA 5100-01844 AND SRM 53-16-01.
Part: STRUCTURE — CORRODED (FUSLEAGE) · airframe 84,635 hrs · 17,230 cycles
INSPECTION FOUND GALLEY G3 FORWARD J-SECTION CORRODED AT STA Y = 450, X = 25R-50R. THE J-SECTION WAS REMOVED AND A NEW SECTION WAS INSTALLED IAW ECRA 5100-01844 AND SRM 53-11-01.
Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 84,635 hrs · 17,230 cycles
INSPECTION FOUND TRANSVERSE J-SECTION AFT OF LAVS E AND F CORRODED AT STA Y = 1884, X = 38L-58L, AND AT X = 39R-58R. THE J-SECTIONS WERE REMOVED AND NEW SECTIONS WERE INSTALLED IAW ECRA 5100-01844 AND SRM 53-16-01.
Part: SUPPORT BRACKET — CORRODED (FUSELAGE) · airframe 84,635 hrs · 17,230 cycles
INSPECTION FOUND GALLEY G6 SUPPORT BEAMS CORRODED AT POSITION JUST FORWARD OF REAR PRESSURE BULKHEAD AND AT EACH ATTACHMENT POINT, STA 1884-2007, X = 24L AND AT STA 1900-2007, X = 58L. THE SUPPORT BEAMS WERE REMOVED AND NEW SUPPORT BEAMS WERE INSTALLED IAW ECRA 5100-01844 AND SRM 53-16-01.
Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 84,635 hrs · 17,230 cycles
INSPECTION FOUND O/B LEFT AND RIGHT SEAT TRACKS CORRODED AT ATTACHMENT TO REAR PRESSURE BULKHEAD T-PIECE AT STA 1986-2007, X= 72L AND X= 72R. THE CORRODED SECTIONS OF SEAT TRACK WERE REMOVED AND NEW SECTIONS WERE INSTALLED IAW SRM 53-70-00, FIGURE 2.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 84,635 hrs · 17,230 cycles
INSPECTION FOUND FLOOR PANEL 293HF CENTER U-CHANNEL SUPPORT CORRODED AT STA Y = 1900-2007, X = 0. THE CORRODED SECTION WAS REMOVED AND A NEW SECTION WAS INSTALLED IAW SRM 53-16-01 AND ECRA 5100-01844.
Part: SUPPORT BRACKET — CORRODED (FUSELAGE) · airframe 84,635 hrs · 17,230 cycles
INSPECTION FOUND LAV F O/B SUPPORT BEAM CORRODED AT STA Y = 1821-1884, X = 36R. THE SUPPORT BEAM WAS REMOVED AND A NEW SUPPORT BEAM WAS INSTALLED IAW ECRA 5100-01844 AND SRM 53-16-01.
Part: SUPPORT BRACKET — CORRODED (FUSELAGE) · airframe 84,635 hrs · 17,230 cycles
INSPECTION FOUND GALLEY G7 SUPPORT BEAMS CORRODED AT STA 1900-2007, X= 57R, AND AT STA 1884-2007, X= 25R. THE SUPPORT BEAMS WERE REMOVED AND NEW SUPPORT BEAMS WERE INSTALLED IAW ECRA 5100-01844 AND SRM 53-16-01.
Earlier reports · 1995–1999 · 12 reports
1999
Part: BEAM — CORRODED (BS 475)
INSPECTION FOUND FORWARD AVIONICS BAY CROSS BEAM CORRODED AT STA Y475, LT SIDE. REPAIRED IAW ECRA 5312-01015 AND FLS DRAWING 90-53-1057.
1998
Part: SKIN — CRACKED (L4 DOOR)
INSPECTION FOUND A SMALL CRACK WITH SOME PULLED RIVETS IN TOP EDGE OF DOOR L-4 SKIN. REPAIRED IAW ECRA 5210-01332.
Part: BRACKET — FAILED (LT MLG WW)
THE LT MLG RED LIGHT REMAINED ILLUMINATED ON BOTH PANELS WITH GEAR UP AFTER TAKEOFF FROM EWR. A VISUAL CHECK THROUGH VIEWPORT INDICATED DOOR PARTIALLY OPEN. THE AIRCRAFT WAS RETURNED TO EWR WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE TORQUE LINK BRAKE HOSE SUPPORT BRACKET IN LT MLG WHEEL WELL FAILED. THE SUPPORT BRACKET WAS REPLACED. IN ADDITION, THE NR 6 BRAKE HOSE AND LT MLG UPPER TORQUE LINK HOSE GUIDE ASSEMBLY WERE REPLACED DUE TO RESULTANT DAMAGE. A GEAR SWING WAS PERFORMED IAW MM 07-11-00, PAGE 201 AND OPERATION CHECKED GOOD.
Part: HYD LINE — RUPTURED (LT ENGINE)
THE AIRCRAFT LOST NR 1 HYDRAULIC SYSTEM QUANTITY WHILE EN ROUTE. FLIGHT MANUAL PROCEDURES WERE COMPLIED WITH AND THE AIRCRAFT LANDED AT EWR WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 1 ENGINE LEFT PUMP SUCTION LINE RUPTURED. THE LINE WAS REMOVED AND REPLACED. LEAK AND OPERATIONAL CHECKS WERE GOOD.
1997
Part: SUPPORT — CORRODED (BS 420)
INSPECTION FOUND CORROSION ON FLOOR SUPPORT PANEL IN MID DECK FORWARD LAV/GALLEY AT STA 420. THE PANEL WAS REMOVED AND A NEW PANEL WAS FABRICATED AND INSTALLED IAW SRM 51-33-01, FIGURE 1.
Part: FLOOR SUPPORT — CORRODED (STA 1841-1887)
INSPECTION FOUND MID DECK AFT LAV/GALLEY FLOOR SUPPORT CORRODED AT STA 1841 TO 1887. THE FLOOR SUPPORT WAS REMOVED AND A NEW SUPPORT WAS FABRICATED AND INSTALLED IAW SRM 53-16-01, FIGURE 10E AND 51-33-01, FIGURE 1.
1996
Part: SKIN — CRACKED (WS 602)
A-1 CRACK WAS FOUND IN THE RT WING LOWER LEADING EDGE SKIN AT XOS 602. A DOUBLER REPAIR WAS INSTALLED IAW ECRA 5730-01421, REV A.
Part: SKIN — CRACKED (WS 602)
RIGHT HAND WING LEADING EDGE LOWER SKIN AT STATION XOS602 HAS A ONE INCH CRACK. INSTALLED DOUBLER PER EC/RA 5730-01421 REV A.
Part: TRIM MOTOR — LEAKING (HOR STAB)
THE HYDRAULIC SYSTEM NR 3 ELEVATOR OFF CAUTION LIGHT ILLUMINATED AND THE NR 3 HYDRAULIC QUANTITY BEGAN TO DECREASE WHILE EN ROUTE FROM FRA TO EWR. SHORTLY AFTERWARDS, THE NR 3 LEFT HYDRAULIC PUMP PRESSURE LOW LIGHT ILLUMINATED. ALL APPROPRIATE CHECKLISTS WERE ACCOMPLISHED AND THE AIRCRAFT WAS DIVERTED TO LGW WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 3 HORIZONTAL STABILIZER TRIM MOTOR LEAKING. THE STABILIZER TRIM MOTOR WAS REMOVED AND REPLACED. THE NR 3 HYDRAULIC SYSTEM WAS SERVICED. LEAK AND OPERATIONAL CHECKS WERE GOOD.
Part: AIR DUCT — FAILED (NR 3 ENGINE)
IAH - FLT 0010 - TAKEOFF WAS REJECTED AT 100 KNOTS AFTER THE NR 3 ENGINE EXPERIENCED LOSS OF POWER. THE NR 3 ENGINE WAS REMOVED AND REPLACED. THE SDR WILL REMAIN OPEN FOR PART INFORMATION PENDING INVESTIGATION. SUPPLEMENT: PRELIMINARY INVESTIGATION REVEALED UNCONTAINED FAILURE IN LPT ROTOR AREA. SHOP INSPECTION FOUND THE FAN MID-SHAFT SHEARED OFF. SUBMITTER STATED THE SUSPECTED CAUSE OF FAILURE WAS THE HPC ROTOR AIR DUCT FAILED AND RUBBED ON FAN MID-SHAFT. (X)
1995
Part: LINKAGE — BINDING (NR 2 ENGINE)
EWR - FLT 0063 - TAKEOFF WAS ABORTED AT 110 KNOTS WHEN THE NR 2 ENGINE THROTTLE WOULD NOT MOVE PAST THE 25 DEGREE ANGLE POSITION. MAINTENANCE FOUND THE NR 2 ENGINE THROTTLE BINDING. THE POWER LEVER LINKAGE WAS MISALIGNED AT THE QUADRANT CONNECTION AND AN ADDITIONAL LINKAGE WAS FOUND OBSTRUCTED BY DEBRIS. THE DEBRIS WAS REMOVED. THE NR 2 ENGINE WAS RUN TO 90 PERCENT N1 WITH NO BINDING NOTED. IN ADDITION, THE NR 2 ENGINE THROTTLE TELEFLEX CABLE WAS REMOVED AND REPLACED AS A PRECAUTIONARY MEASURE. AN ADJUSTMENT AND TEST WAS PERFORMED IAW MM 76-11-01, PAGE 201 AND OPERATION OF THE NR 2 ENGINE THROTTLE CHECKED GOOD WITH NO DEFECTS NOTED. (X)
Part: OIL TUBE — LEAKING (NR 2 ENGINE)
EWR - FLT 0004 - THE NR 2 ENGINE LOST OIL QUANTITY WHILE IN-FLIGHT. THE ENGINE WAS SHUT DOWN AND THE AIRCRAFT WAS DIVERTED TO EWR WHERE IT LANDED WITHOUT INCIDENT. THE AIRCRAFT WAS TAKEN OUT OF SERVICE AND AN ENGINE CHANGE IS PLANNED. THE SDR WILL REMAIN OPEN FOR FURTHER DETAILS AND PART INFORMATION PENDING INVESTIGATION. SUPPLEMENT - INVESTIGATION REVEALED THE OIL SUPPLY TUBE HAD RUBBED AGAINST INSULATION BLANKET RESULTING IN TWO SMALL PIN HOLES. (X)