N703S
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
AFT CABIN OVERHEAD EMERGENCY EXIT LIGHT INOPERATIVE.
OVERWING EMERGENCY EXITS LIGHTS INOPERATIVE.
L1 AND R1 DOOR EMERGENCY ESCAPE SLIDE LIGHTS FAIL TO ILLUMINATE.
L-1 AND R-1 DOOR EMERGENCY ESCAPE SLIDE LIGHTS FAIL TO ILLUMINATE
CABIN AISLE EMERGENCY LIGHT FAILS TO ILLUMINATE.
MID CABIN EMERGENCY CEILING LIGHT INOPERATIVE.
MID CABIN EMERGENCY EXIT CEILING LIGHT INOP.
PORTABLE EMERGENCY EXIT LIGHT AT R2 DOOR, FORWARD SERVICE DOOR, FAILS TO ILLUMINATE. REPLACED EMERGENCY EXIT LIGHT ASSY.
FORWARD R2 SERVICE DOOR PORTABLE EMERGENCY EXIT LIGHT INOPERATIVE.
MID CABIN OVERHEAD EMERGENCY EXIT LIGHT FAILS TO ILLUMINATE.
CORRODED SHEAR TIE AT BS 727A, STRINGER 23L, AFT CARGO BAY AREA
CENTER, PASSENGER CABIN, OVERHEAD EMERGENCY EXIT LIGHT INOPERATIVE.
CENTER PASSENGER CABIN OVERHEAD EMERGENCY EXIT LIGHT INOPERATIVE. REPLACED EXIT LIGHT BATTERY PACK IAW AMM 33-51-81.
MID CABIN FIXED EMERGENCY EXIT SIGN FAILS TO ILLUMINATE. REPLACED EXIT SIGN POWER SUPPLY IAW AMM 33-51-101. FUNCTIONALLY TESTED IAW AMM 33-51-11
MID CABIN FIXED EMERGENCY EXIT SIGN FAILS TO ILLUMINATE. REPLACED EXIT SIGN BATTERY IAW AMM 33-51-8. FUNCTIONALLY TESTED IAW AMM 33-51-11.
MID CABIN EMERGENCY LIGHT FAILED TO ILLUMINATE DURING TEST. REPLACED THE BATTERY PACK IAW AMM 33-51-11. TESTED SATISFACTORY.
FWD CABIN EMERGENCY EXIT LIGHT FAILED TO TEST. REPLACED THE POWER SUPPLY IAW AMM 33-51-01. TESTED SATISFACTORY.
MID CABIN EMERGENCY EXIT LIGHT FAILS TO ILLUMINATE ON TEST. REPLACED BATTERY PACK IAW AMM 33-51-81. TESTED SATISFACTORY.
MID CABIN OVERHEAD EMERGENCY LIGHT FAILS TO ILLUMINATE. REPLACED MID CABIN EMERGENCY LIGHT POWER SUPPLY IAW AMM 33-51-01. TESTED SATISFACTORY.
FRAME WEB CRACK AT BS 639, LBL 50,UNDER FLOOR. REPAIRED OVERWING STUB BEAM WEB IAW EO R22529.1-053-015-032
CORROSION IN THREE PLACES UNDER SREW HOLES AT BS BS 328, RBL 45 TO 60. REPAIRED FLOORBEAM UPPER TEE IAW EO R22529-1-053-010-032, REV NC.
SIDE CHORD CRACKED AR WL 193, BS 178. REPAIRED IAW SB 737-53A1137 AND EO R22529 1-053-013-032.
STRINGER 16R AT BS 500-520 HAS 2 CRACKS. REPAIRED IAW SB 737-53-1145 AND EO R22529-1-053-011-03.
STRINGER 16L, HAS TWO CRACKS BS 500-520. REPAIRED IAW SB 737-53-1145, REV 0 AND EO R22529 1-053-007-032.
CRACKED ANGLE AT BS 639, LBL 46, FRAME TO LONGITUDINAL BEAM ATTACHMENT UNDER FLOOR. ANGLE REPLACED IAW SRM 51-10-01, PARA 7, 51-10-02 AND DWG 65C25211, REV B.
CORROSION ON AFT PRESSURE BULKHEAD STIFFENER AT GROUND WIRE ATTACH POINT AT STRINGER 12L AT WL220. REMOVED STRINGER, REPAIRED IAW EO R22529-1-053-O32, REV A.
STRINGER 15L INTERCOSTAL ANGLE CRACKED AT BS 348. REPAIRED IAW EO R22529-1-053-009-032.
FUSELAGE BS 578, RBL 72, WL 207 FLOORBEAM WEB SUPPORT ANGLE CRACKED AT RIVET HOLE. FLOORBEAM WEB AND SUPPORT ANGLE CRACKS REPAIRED IAW EO R22529 1-053-014-032.
CORROSION ON UPPER AFT FLANGE OF FLOORBEAM BS 947 , RBL 48. REPAIRED IAW INSTRUCTIONS GIVEN IN EO R22529 1-053-008-032.
AFT CABIN EMERGEMCY ESCAPE FLOOR PATH LIGHTING FAILS TO ILLUMINATE. REPLACED EMERGENCY ESCAPE FLOOR PATH LIGHTING AFT EGRESS BATTERY IAW CMM 33-21-27. FUNCTIONALLY TEASTED IAW AMM 33-51-11. ALL FUNCTIONS SATISFACTORY.
FWD CABIN EMERGENCY ESCAPE PATH LIGHTING FAILS TO ILLUMINATE. REPLACED EGRESS BATTERY PACK IAW CMM 33-21-27. FUNCTIONALLY TESTED SATIFACTORY IAW AMM 33-51-81.
FWD CABIN EMERGEMCY ESCAPE PATH LIGHTING FAILS TO ILLUMINATE. REPLACED EGRESS BATTTERY CHARGER ASSEMBLY IAW CMM 33-21-27. FUNCTIONALLY TESTED EMERGENCY LIGHTS IAW AMM 33-51-11. ALL FUNCTIONS SATISFACTORY.
AFT CABIN EMERGENCY ESCAPE FLOOR PATH LIGHTING FAILS TO ILLUMINATE. REPLACED EMERGENCY ESCAPE FLOOR PATH LIGHTING AFT BATTERY CHARGER ASSY IAW CMM 33-21-27. FUNCTIONALLY TESTED EMERGENCY LIGHTS IAW AMM 33-51-11. ALL FUNCTIONS SATISFACTORY.
DURING SCHEDULED MAINTNANCE, A SKIN CRACK WAS FOUND AT BS 727A, S15R. REPAIRED IAW SRM 53-30-3, FIG 48, REV 106 AND EO R22529.1-053-004-032, REV A.
FOUND FUSELAGE SKIN CRACKED AT BS 727A, S25L. REPAIRED IAW EO R22529, 1-053-005-032, REV D AND SR 3-24I97151079.
RIGHT WING LOWER SURFACE SKIN, WBL 221; GOUGE. ACCOMPLISHED REWORK/BLEND OUT OF THE GOUGE PER REPAIR PLAN DESCRIBED ON SPA TASK CARD R3R57001. BSF FINDS REPAIR PLAN STRUCTURALLY ACCEPTABLE. BOEING DER ISSUED 8100-9.
TUS-CYLW INTO C8 MAINTENANCE CHECK. ON APPROACH AND LANDING INTO CYLW, ELEVATOR CONTROLS STIFF. FOUND ELEVATOR INPUT TORQUE TUBE BEARINGS FROZEN/STIFF TO MOVE. REMOVED TORQUE TUBE ASSY, REPLACED AFFECTED BEARINGS, AND REINSTALLED ASSEMBLY AND RIGGED PER CMM 27-37-07 AND AMM 27-31-71.
DURING TAXI IN, LOST ALL HYDRAULIC SYS "A" PRESSURE,( PIREP). SERVICED A SYS HYD IAW AMM 12-12-00, FOUND NR 4 KRUEGER L/E FLAP ACTUATOR LEAKING AT REAR OF ACTUATOR BODY CASTING. REPLACED ACTUATOR IAW AMM 27-81-31. RII INSP ACCOMPLISHED. SERVICED AIRPLANE HYD SYS IAW AMM 12-12-00.
FWD CTR CABIN EMERGENCY EXIT LIGHT FAILS TO ILLUMINATE. REPLACED FWD CTR AISLE EXIT LIGHT POWER SUPPLY IAW AMM 33-51-01, OPS CHECKED SATISFACTORY IAW AMM 33-51-11.
LT OTBD MIDFLAP THRUST BEARING BORES (2 EA) CORRODED. REPLACED MIDFLAP WITH O/H UNIT IAW AMM.
RT WING MIDFLAP HAS CORRODED THRUST BEARING BORES, 2 EA REPLACED MIDFLAP WITH SERVICEABLE UNIT IAW AMM.
AFT OVERHEAD EMERGENCY EXIT LIGHT INOPERATIVE. REPLACED EMERGENCY EXIT LIGHT ASSEMBLY PER AMM 33-51-01. OPERATIONAL CHECK SATISFACTORY.
AFT EXIT AND FLOOR PROXIMITY EMERGENCY LIGHTING DOES NOT ILLUMINATE WHEN TURNED ON. REPLACED CHARGER AND BATTERY PACK IAW AMM 33-51-81,SYSTEM OPS TEST NORMAL IAW AMM 33-51-11.
AFT EXIT AND FLOOR PROXIMITY EMERGENCY LIGHTING DOES NOT ILLUMINATE WHEN TURNED ON. REPLACED CHARGER AND BATTERY PACK IAW AMM 33-51-81,SYSTEM OPS TEST NORMAL IAW AMM 33-51-11.
AFT EXIT AND FLOOR PROXIMITY EMERGENCY LIGHTING DOES NOT ILLUMINATE WHEN TURNED ON. REPLACED CHARGER AND BATTERY PACK IAW AMM 33-51-81,SYSTEM OPS TEST NORMAL IAW AMM 33-51-11.
AFT SECTION OF FLOORTRACK ESCAPE PATH LIGHTING INOP. REPLACED BATTERY POWER SUPPLY AND FUNCTIONAL CHECK SATISFACTORY IAW CMM 33-21-27.
FORWARD SECTION OF FLOORTRACK ESCAPE PATH LIGHTING INOP. REPLACED POWER SUPPLY AND FUNCTIONALLY TESTED SATISFACTORY IAW CMM.
CENTER OVERHEAD EMERGENCY EXIT LIGHT STAYS ON ONLY BRIEFLY. REPLACED CENTER OVERHEAD EMERGENCY EXIT LIGHT BATTERY CHARGER IAW MM 33-51-81. GROUND CHECK NORMAL IAW MM 33-51-11.
CRACK ON BS1156 OUTER CHORD RT SIDE WL270. REPAIRED CRACK IAW SB 737-53-1086.
AFT LOWER CARGO DOOR HAS CRACKS ON THE FWD AND AFT CORNER FRAMES & THE LOWER BEAM FWD END. REPAIRED CRACKS ON AFT CARGO DOOR FWD AND AFT CORNERS AND LWR BEAM FORWARD END IAW BOEING SERVICE BULLETIN 737-52A-1079.
CRACK IN FUSELAGE SKIN AT FWD LWR L-2 DOOR CUTOUT, BS 947.5 STR 14 LT. REPAIRED CRACK IAW SRM 53-30-3.
CRACK IN FUSELAGE SKIN AT FWD LWR L-2 DOOR CUTOUT, BS 947.5 STR 14 LT. REPAIRED CRACK IAW BOEING SRM 53-30-3.
PREFLIGHT CHECK, AFT OVERHEAD AISLE EMERGENCY EXIT SIGN DOES NOT LIGHT. REPLACED BATTERY POWER SUPPLY IAW 33-51-81. OPERATIONAL CHECK NORMAL.
AFT CEILING EMERGENCY EXIT SIGN DOESN'T ILLUMINATE WHEN SWITCHED ON. REPLACED BATTERY PACK PER MM 33-51-81, OPS CHECK NORMAL.
ON PREFLIGHT CHECK FOUND EMERGENCY EXIT LIGHT AT CABIN DOOR 2L DIM. REPLACED EMERGENCY EXIT LIGHT/BATTERY PACK ASSEMBLY PER MM 33-51-101, OPERATIONAL CHECK NORMAL.
POST SHOP REPAIR OF ENGINE S/N P700543 , OPERATIONAL TEST FLIGHT UNSATISFACTORY. ENGINE EXHIBITS CONTINUOUS COMPRESSOR STALLS AT TOP OF CLIMB, 37FL. ACCOMPLISHED UNSCHEDULED RETURN TO FIELD. ENGINE TO BE REMOVED FROM AIRPLANE AND PLACED IN SHOP FOR DISCREPANCY CAUSE AND REPAIR.
NR 1 ENGINE S/N COMPRESSOR STALLS AT TOP OF CLIMB FL 37.
Corrosion on frame at BS1006, Stringer 25L. Beltframe at Sta 1006 repaired I.A.W. Boeing SRM 53-10-4, Fig 1-4.
Intercostal at Fuselage Station 178 R/H side, WL 195, RBL 24 is cracked.
CORROSION ON FLOORBEAM TOP FLANGE AT STA. 1016, LBL 6 TO RBL 5. BEYOND SRM LIMITS. REPAIRED FLOOR BEAM TOP FLANGE PER SRM 53-10-9, FIG 1 PGAS 1-9
Corrosion on frame at BS1006, Stringer 20R. Repaired frame at Sta 1006 per Boeing SRM 53-10-4, Fig 1, Sheets 1 of 4.
Initial compliance of A.D. 2000-05-29, Service Bulletin 737-53A1173 revealed a crack in the intercostal on the L/H side behind Sta 178 pressure bulkhead at WL 195 LBL 24. Intercostal repaired per SRM 53-10-1, Figure 10.
CORROSION ON UNDERSIDE OF FLOOR SKIN AT SINK FITTINGS FS 1000 LBL 45. REPAIRED FLOOR PER SRM 51-402 FIGURE 1.
CORROSION ON FLOORBOARD SUPPORT AT LAV DOOR, BS 990 TO BS 1016, LBL 6 TO LBL 19. REPLACED FLOORBOARD SUPPORTS PER SRM 51-10-1 AND 51-30-1, P/N 65-46812-185 AND 65-46812-187.
CRACKS NOTED IN SIDE FRAME AT BS 178, WL 195 TO WL 207 BL36L. VISUAL CRACKS VERIFIED BY HFEC INSPECTION. REPLACED SIDE CHORD PER BOEING SERVCICE BULLETIN 737-53A1173.
CORROSION ON FLOORBOARD SUPPORT AT BS 986 TO BS1006, BL 0. REPLACED FLOORBOARD SUPPORT PER SRM 53-40-4, FIG 1 PGS 1-7.
L-2 DOOR EMERGENCY BATTERY PACK FALLS OFF. REPLACED EMERGENCY DOOR BATTERY PACK PER AMM 33-51-0, OPS CHECK GOOD PER AMM 31-51-101.
L-1 DOOR EMERGENCY LIGHT PACK DIM. REPLACED LIGHT PACK PER AMM 33-51-101, OPS CHECK GOOD
R-2 DOOR EMERGENCY ESCAPE SLIDE DID NOT DEPLOY FOR CREW TRAINING EXCERCISE. MAINTENANCE DETERMINED THAT SLIDE INFLATION CYLINDER SAFETY PIN WAS ENGAGED. SAFETY PIN WAS REMOVED AND STOWED. SLIDE WAS DEPLOYED.
PREFLIGHT MAINTENANCE NOTED APPEARANCE OF CRACK IN FUSELAGE SKIN BETWEEN BS 727A AND BS 727B ABOVE THE FLOOR LINE. NDT INSPECTION (EDDY CURRENT) VERIFIED DISCREPANCY TO BE 1 INCH CRACK IN FUSELAGE SKIN ABOVE STRINGER S-16L, FORWARD OF BS 727B. AIRCRAFT FERRIED TO REPAIR STATION. ACCOMPLISHED BOEING SERVICE BULLETIN 737-53-1065, PERMANENT SKIN REPAIR PER FIGURE 54.
DURING PREFLIGHT, NOTED DELAMINATION ON LEFT WING UPPER SURFACE TRAILING EDGE FIXED PANEL. PANEL LOCATED BETWEEN AILERON AND #1 FLIGHT SPOILER PANEL
FORWARD EMERGENCE ESCAPE SLIDE LIGHTS INTERMITTENT. REPLACED FWD EMERGENCY SLIDE LIGHTS BATTERY POWER SUPPLY PER MM 33-51-71. OPS CHECK GOOD.
FWD CEILING EMERGENCY EXIT LIGHT INTERMITTENT. REPLACED EXIT LIGHT HOUSING ASSEMBLY PER BMM 33-51-11. OPS CHECK GOOD
PREFLIGHT CHECK FOUND CENTER AISLE CEILING EMERGENCY EXIT LIGHT INTERMITTANT. REPLACED BATTERY CHARGER IAW BMM 33-51-71, OPS CHECK GOOD.
ON CLIMB-OUT FROM RNO, AFT CARGO DOOR WARNING LIGHT ILLUMINATED. RETURNED TO RNO. INVESTIGATION REVEALED AFT CARGO DOOR TO BE CLOSED AND SECURED. PLACE ITEM ON MEL 52-3, DEPARTED RNO TO BOI. AFTER ARRIVAL IN BOI, ADJUSTED AFT CARGO DOOR WARNING SWITCH. CLEARED MEL, PLACARDS REMOVED.
ACCOMPISHMENT OF PREFLIGHT CHECK FOUND OVERWING EMERGENCY EXIT LIGHT INTERMITTANT. REPLACED BATTERY PAC IAW BOEING MM 33-51-81 OPS CHECK GOOD
DURING ACCOMPLISHMENT OF PRE-FLIGHT CHECK FOUND EMERGENCY EXIT LIGHT AT L-2 DOOR INOPERATIVE. REMOVED AND REPLACED EMERGENCY EXIT LIGHT IAW B737 MM 33-51-101. OPERATIONAL CHECK GOOD.
DURING PREFLIGHT INSPECTION FOUND L-2 DOOR EMERGENCY EXIT LIGHT INOP.REMOVED AND REPLACED EMERGENCY EXIT LIGHT ASSEMBLY
HORIZONTAL STABILIZER CENTER SECTION REAR SPAR LOWER CLEVIS LUG AFT EAR, AFT FACE, HAS A PREVIOUS BLEND IN THE SPOTFACE AREA. REPAIRED PER ECRA N703S-55-B737-008-EAC. (X)
DURING PREFLIGHT INSPECTION, FOUND L-2 DOOR MOUNTED EVACUATION SLIDE CYLINDER PRESSURE LOW. REMOVED AND REPLACED EVACUATION SLIDE ASSEMBLY.
CORROSION ON THE HORIZONTAL STABILIZER CENTER SECTION REAR SPAR FITTING RIGHT HAND SIDE LOWER AFT LUG. REPAIRED PER ECRA N703S-55-B737-004-EAC. (X)
HORIZONTAL STABILIZER CENTER SECTION FRONT SPAR, LOWER CLEVIS LUG,LEFT HAND SIDE, FORWARD FACE HAS EXISTING TOOLING MARK. REPAIRED PER ECRA N703S-55-B737-007-EAC.
HORIZONTAL STABILIZER REAR SPAR FITTING, UPPERMOST LUG, LEFT HAND SIDE INNER BORE SPOTFACE HAS A CHIPPED CORNER. REPAIRED PER ECRA N703S-55-B737-006-EAC. (X)
HORIZONTAL STABILIZER CENTER SECTION REAR SPAR FITTING RIGHT HAND SIDE INNER BORE HAS CORROSION. REPAIRED PER ECRA N703S-55-B737-005-EAC. (X)
EXISTING GOUGES ON THE AFT SURFACE OF THE LEFT HAND VERTICAL STABILIZER FRONT SPAR FITTING LUG. REPAIRED PER S/B 737-55-1028, ECRA N703S-55-B737-003-EAC. (X)
CORROSION VERTICAL REAR SPAR FITTING, LEFT SIDE OUTBOARD LUG AFT FACE OF FITTING. (X)
CRACK IN AFT CARGO DOOR SILL WEB, BS 822, STR 25R. (X)
DURING ACCOMPLISHMENT OF SB 737-55-1055 FOUND UNEVEN PREVIOUSLY BLENDED AREA AT LEFT SIDE HORIZONTAL STABILIZER CENTER SECTION REAR SPAR FITTING LOWER CLEVIS AFT LUG, AFT FACE. REPAIRED BY SPOT FACING/MACHINING SURFACE TO OBTAIN A FLAT SURFACE. APPROVAL FOR REPAIR PROVIDED BY FAA FORM 8110-3 DATED DECEMBER 18, 2000. WORK ACCOMPLISHED ON ECRA N703S -55-B737-008-EAC.
DURING ACCOMPLISHMENT OF SB 737-55-1055, RT SIDE OF HORIZONTAL STABILIZER CENTER SECTION LOWER AFT CLEVIS LUG, FWD EAR BUSHING HOLE WAS FOUND TO HAVE CORROSION AND WAS ABOVE ALLOWABLE DIMENSIONS PER DRAWING 65C22125. REPAIRED BY REMOVING CORROSION AND INCREASING BUSHING BORE DIAMETER TO 1.503 MAX. APPROVAL OF REPAIR PLAN PROVIDED BY FAA FORM 8110-3 DATED DECEMBER 18, 2000. WORK ACCOMPLISHED PER ECRA N703S-55-737-005-EAC.
DURING ACCOMPLISHMENT OF SB 737-55-1055, CORROSION WAS FOUND AT THE LOWER AFT LUG BUSHING HOLE COMMON TO THE HORIZONTAL STABILIZER CENTER SECTION REAR SPAR FITTING RIGHT HAND SIDE. REPAIRED BY INCREASING THE DIAMETER OF THE BUSHING HOLE TO 1.540 DIAMETER. REPAIR APPROVAL IS LISTED ON FAA FORM 8110-3 DATED DECEMBER 18, 2000.
DURING ACCOMLISHMENT OF SB 737-55-1055 FOUND TOOLING MARK ON THE LT HORIZONTAL STAB CENTER SECTION FRONT SPAR LOWER CLEVIS FORWARD LUG, FORWARD FACE. BLENDED AND SPOT FACED EXISTING DAMAGE. APPROVAL OF REPAIR PROVIDED BY FAA FORM 8110-3 DATED DECEMBER 13, 2000. WORK ACCOMPLISHED ON ECRA N703S-55-B737-007-EAC.
DURING SPECIAL MAINTENANCE VISIT, THE AFT CARGO DOORWAY SILL WEB AT STA 822.00 WAS FOUND CRACKED.THE REPAIR PROVIDED FOR TRIMMING OUT THE DAMAGED AREA IN THE SILL WEB AND INSTALLING A FILLER AND REINFORCING DOUBLER PER FIG. 1 OF ECRA N703S-53-B737-001-EAC. FAA FORM 8110-3 DATED DECEMBER 14, 2000 PROVIDES STRUCTURAL SUBSTANTIATION FOR THIS REPAIR.
DURING THE ACCOMPLISHMENT OF SERVICE BULLETIN 737-55-1028, CORROSION WAS FOUND ON THE AFT SURFACE OF THE OUTBOARD LUG COMMON TO THE VERTICAL STABILIZER REAR SPAR FITTING. CORROSION WAS REMOVED PER ECRA N703S-55-737-002-EAC AND THE REWORK WAS FINISHED PER SB 737-55-1028. STRUCTURAL SUBSTANTIATION FOR THIS REPAIR WAS PROVIDED ON FAA FORM 8110-3 DATED DECEMBER 8, 2000. IN ADDITION, THIS IS AN AMOC TO PARAGRAPH A OF AD 90-06-02
DURING ACCOMPLISHMENT OF CPCP TASK C57-306-04 PART 1 OF 2, CORROSIOIN WAS FOUND ON THE LET WING OUTBOARD FLAP, INBOARD FLAP CARRIAGE SPINDLE. REMOVED AND REPLACED FLAP CARRIAGE SPINDLE PER BOEING MM 27-51-81 AND RIGGED SYSTEM PER BOEING MM 27-51-12 A/T
DURING ACCOMPLISHMENT OF CPCP TASK C57-306-04 1OF2 CORROSION WAS FOUND ON THE LEFT WING OUTBOARD MIDFLAP, OUTBOARD CARRAIGE SPINDLE. REMOVED AND REPLACED OUTBOARD FLAP CARRAIGE IAW BOEING MM 27-51-81. RIGGED FLAP SYSTEM PER BOEING MM 27-51-12 A/T
DURING ACCOMPLISHMENT OF CPCP TASK C57-306-04 PART 2 OF 2, CORROSION WAS FOUND ON THE RT OUTBOARD MIDFLAP, OUTBOARD CARRIAGE SPINDLE. REMOVED AND REPLACED CARRIAGE PER BOEING MM 27-51-81. RIGGED FLAP SYSTEM PER BOEING MM 27-51-12 A/T
DURING ACCOMLISHMENT OF CPCP TASK C57-306-04 PART 2 OF 2, CORROSION WAS FOUND ON THE RIGHT OUTBOARD MIDFLAP, INBOARD CARRIAGE SPINDLE. REMOVED AND REPLACED SPINDLE PER BOEING MM 27-51-81 AND RIGGED SYSTEM PER BOEING MM A/T 27-51-12
DURING ACCOMPLISHMENT OF CPCP TASK C57-306-04 PART 1 OF 2, CORROSION WAS FOUND ON THE LT WING OUTBOARD FLAP, INBOARD FLAP CARRIAGE SPINDLE. REMOVED AND REPLACED FLAP CARRIAGE SPINDLE PER BOEING MM 27-51-81 AND RIGGED SYSTEM PER BOEING MM 27-51-12 A/T
DURING ACCOMLISHMENT OF CPCP TASK C57-306-04 PART 2 OF 2, CORROSION WAS FOUND ON THE RIGHT OUTBOARD MIDFLAP, INBOARD CARRIAGE SPINDLE. REMOVED AND REPLACED SPINDLE PER BOEING MM 27-51-81 AND RIGGED SYSTEM PER BOEING MM A/T 27-51-12
DURING ACCOMPLISHMENT OF SB 737-55-1055 DAMAGE WAS FOUND TO THE LEFT HAND HORIZONTAL STABILIZER REAR SPAR UPPER TERMINAL FITTING. BLENDED DAMAGED AREA, FLAP PEENED, AND FINISHED REWORK PER SB 737-55-1055. APPROVAL PROVIDED BY FAA FORM 8110-3 DATED DECEMBER 8,2000. WORK ACCOMPLISHED PER ECRA N703S-55-737-006-EAC.
DURING SCHEDULED CHECK, THE COCKPIT CEILING EMERGENCY EXIT LIGHT WAS FOUND DIM DURING TEST. THE LIGHT ASSEMBLY WAS REPLACED. SUBSEQUENT SYSTEM CHECK WAS SATISFACTORY PER MM 33-51-101.
DURING SCHEDULED CHECK, THE FORWARD AISLE OVERHEAD INTERNAL EMERGENCY EXIT LIGHT WAS FOUND INOPERATIVE. THE ASSOCIATED SYSTEM BATTERY CHARGER WAS REPLACED. SUBSEQUENT SYSTEM TEST WAS SATISFACTORILY ACCOMPLISHED PER MM 33-51-11.
DURING SCHEDULED CHECK, THE RT OVERWING EXTERIOR EMERGENCY EXIT LIGHT WAS FOUND INOPERATIVE. THE ASSOCIATED SYSTEM BATTERY CHARGER WAS REPLACED. SUBSEQUENT SYSTEM TEST WAS SATISFACTORY PER MM 33-51-31.
DURING C4 CHECK, CRACKED SUPPORT BRACE FOR THE FORWARD LOWER CARGO PIT FLOOR, BS 520 AT S-20R, WAS DISCOVERED. THE SUPPORT BRACE WAS REPLACED PER B-737 SRM 51-10-1, PARAGRAPH 4 AND INSTALLED PER SRM 51-30-2.
DURING C4 CHECK, CARGO TIE DOWN TRACK, BS 540 AT S-26L, HAD CORROSION AT NUMEROUS ANCHOR NUT HOLES. THE AFFECTED AREAS WERE REPAIRED PER B-737 SRM 51-40-4, FIGURE 1.
DURING C4 CHECK, MAIN FLOOR SUPPORT BRACE AT BS 520, LBL 20, WAS FOUND CRACKED. REPAIRS WERE ACCOMPLISHED PER B-737 SRM 51-10-1, PARAGRAPH 4 AND SRM 51-30-2.
DURING C4 CHECK, LOWER FORWARD CARGO PIT FLOOR RAIL AT BS 520, S-28L, WAS FOUND TO HAVE CORROSION AT ANCHOR NUT HOLE. THE DAMAGED AREA WAS REPAIRED PER B-737 SRM 51-40-4, FIGURE 1.
DURING C4 CHECK, FRAMING FOUND CRACKED AT BS 1138, BELOW RT HORIZONTAL STABILIZER AT S-12R. REPAIRS ACCOMPLISHED PER B-737 SRM 53-30-3, SRM 51-10-1, PARAGRAPH 4, DRAWINGS 65C35132 AND 65C25276.
DURING ACCOMPLISHMENT OF AD 85-01-06, A CRACK WAS DISCOVERED IN THE BS 360 FRAME AT S-21L. THE DAMAGE WAS REPAIRED PER BOEING SERVICE BULLETIN 737-53A1064.
DURING C4 CHECK, THE LONGITUDINAL FLOORBEAM WEB WAS FOUND CRACKED, BS 677, LBL 25, 2 BELOW FLOOR LEVEL AT THE LT AILERON QUADRANT CUT-OUT. THE DAMAGE WAS REPAIRED PER BOEING SERVICE BULLETIN 737-57-1139, FIGUR E 5.
DURING C4 CHECK, FLOORBEAM ANGLE AT BS 596.5 WAS FOUND CRACKED WHERE IT ATTACHES TO THE RT OUTBOARD SKIN, APPROXIMATELY 4 FT BELOW FLOOR LEVEL. THE DAMAGED FRAME SECTION WAS REPLACED PER B-737 SRM 51-10-1 SRM 51-30-2.
DURING C4 CHECK, CRACKED SUPPORT BRACE FOR THE FORWARD LOWER CARGO PIT FLOOR, BS 420 BETWEEN S-25L AND S-26L, WAS DISCOVERED. THE SUPPORT BRACE WAS REPLACED PER B-737 SRM 51-10-1, PARAGRAPH 4 AND INSTALLED PER SRM 51-30-2.
DURING C4 CHECK, CORRODED STRINGER SPLICE WAS DISCOVERED AT BS 907, S-27R. THE SPLICE WAS REPLACED PER B-737 SRM 51-10-1, PARAGRAPH 4 AND SRM 51-30-3.
DURING C4 CHECK, LOWER FORWARD CARGO PIT TIE DOWN TRACK AT BS 540, LBL 28, WAS FOUND WITH CORROSION EXCEEDING LIMITS AT ANCHOR NUT HOLES. THE TIE DOWN TRACK WAS COMPLETELY REPLACED PER B-737 SRM 51-10-1, PARAGRAPH 4 AND SRM 51-30-2.
DURING C4 CHECK, CRACKED INTERCOSTAL, BS 480 BETWEENS-27L AND S-28L, WAS DISCOVERED. REPAIR WAS ACCOMPLISHED PER B-737 SRM 51-10-1, PARAGRAPH 4 AND INSTALLED PER SRM 51-30-2.
DURING C4 CHECK, THE LONGITUDINAL FLOORBEAM WEB WAS FOUND CRACKED, BS 677, RBL 25, 2 BELOW FLOOR LEVEL AT THE RT AILERON QUADRANT CUT-OUT. THE DAMAGE WAS REPAIRED PER BOEING SERVICE BULLETIN 737-57-1139, FIGURE 5.
DURING C4 CHECK, FRAMING FOUND CRACKED AT BS 1138, BELOW LT HORIZONTAL STABILIZER AT S-12L. REPAIRS ACCOMPLISHED PER B-737 SRM 53-30-3, SRM 51-10-1, PARAGRAPH 4, DRAWINGS 65C35132 AND 65C25276.
DURING C4 CHECK, CARGO PIT FLOOR SUPPORT, BS 500 AT S-28R, HAD CORROSION AT ANCHOR NUT HOLE. THE DAMAGED AREA WAS REPAIRED PER B-737 SRM 53-10-5, FIGURE 6.
DURING SCHEDULED CHECK, THE FORWARD AISLE EMERGENCY EXIT LIGHTS WERE FOUND INOPERATIVE. THE ASSOCIATED SYSTEM BATTERY CHARGER WAS REPLACED. SUBSEQUENT SYSTEM TEST WAS SATISFACTORY PER BMM 33-51-81.
RDD - NR 1 ENGINE LOST ALL A SYSTEM HYDRAULIC FLUID DURING ENGINE START. INVESTIGATION REVEALED THAT THE NR 1 ENGINE DRIVEN HYDRAULIC PUMP PRESSURE LINE WAS DAMAGED, CAUSING THE FLUID LOSS. THE HYDRAULIC PRESSURE LINE WAS REPLACED AND LEAK CHECKED PER MM 29-11-0. CASE DRAIN FILTER INSPECTED PER MM 29-11-41. HYDRAULIC SYSTEM SERVICED PER MM 12-12-0.
DURING ROUTINE CHECK, THE INTERIOR EMERGENCY EXIT LIGHT ABOVE THE LT OVERWING ESCAPE HATCH WAS FOUND INOPERATIVE. THE ASSOCIATED SYSTEM BATTERY CHARGER WAS REPLACED. SUBSEQUENT SYSTEM TEST WAS SATISFACTORY PER MM 33-51-81.
DURING SCHEDULED CHECK, THE AFT SECTION OF EMERGENCY FLOOR PATH LIGHTING DID NOT ILLUMINATE. THE ASSOCIATED SYSTEM BATTERY CHARGER WAS REMOVED AND REPLACED. SUBSEQUENT SYSTEM TEST WAS SATISFACTORY PER BMM 33-51-11.
DURING SCHEDULED CHECK, THE AFT SECTION OF EMERGENCY FLOOR PATH LIGHTING DID NOT ILLUMINATE. THE ASSOCIATED SYSTEM BATTERY CHARGER WAS REMOVED AND REPLACED. SUBSEQUENT SYSTEM TEST WAS SATISFACTORY PER BMM 33-51-11.
DURING SCHEDULED CHECK, THE EXTERIOR EMERGENCY EXIT LIGHT AFT OF THE RT BODY FAIRING WAS FOUND INOPERATIVE. THE BULB WAS REPLACED, SUBSEQUENT SYSTEM TEST WAS SATISFACTORY.
DURING PREFLIGHT CHECK, THE LOWER EMERGENCY ESCAPE PATH LIGHTS AT BOTH OVERWING EXIT LOCATIONS WERE FOUND INOPERATIVE. BOTH BATTERY CHARGERS, FORWARD AND AFT, ASSOCIATED WITH THESE LIGHTS WERE REPLACED. SUBSEQUENT SYSTEM TEST WAS SATISFACTORY PER BMM 33-51-11.
DURING ACCOMPLISHMENT OF MANDATORY SERVICE BULLETIN 737-53-1085 INSPECTION, AD 93-08-04, ELEVEN STRINGER TO FRAME TIE CLIPS WERE FOUND CRACKED AT THE FOLLOWING LOCATIONS: BS 616 AT S3L, BS 685 AT S2L AND S4R, BS 706 AT S2R, BS 727 AT S4L, BS 727B AT S5L, S6L AND S7R, BS 747 AT S7L, BS 767 AT S6L AND 787 AT S6R. ALL WERE REPLACED PER SRM 51-30-2.
DURING ACCOMPLISHMENT OF CPCP TASK C53-107-02, FLOORBEAM STIFFENER AT BS 957, RBL 17 TO RBL 45, WAS FOUND TO HAVE CORROSION BEYOND SRM LIMITS. THE DAMAGED PIECE WAS REPLACED AND INSTALLED PER SRM 51-10-1 AND 51-20-1.
DURING ACCOMPLISHMENT OF CPCP TASK C53-208-01, AFT CARGO PIT FLOOR BEAM, BS 736A TO 758, LBL 14 WAS FOUND CORRODED BEYOND SRM LIMITS AT FLOORING ATTACHMENT HOLES. DAMAGE AREAS WERE REPAIRED PER SRM 53-10-5.
DURING ACCOMPLISHMENT OF CPCP TASK C53-107-01, FRAME SECTION AT BS 887, RBL 65 WHERE IT PASSES THROUGH FLOOR STRUCTURE, WAS FOUND TO HAVE CORROSION BEYOND SRM LIMITS. DAMAGE WAS REPAIRED PER SRM 51-40-3.
DURING ACCOMPLISHMENT OF CPCP TASK C53-208-01, STRINGER END FITTING AT BS 1016, S21R, WAS FOUND CORRODED BEYOND SRM LIMITS. THE DAMAGED PART WAS REPLACED PER SRM 51-30-2.
DURING ACCOMPLISHMENT OF CPCP TASK C53-107-01, CABIN FLOORBEAM AT BS 328, RBL 38, WAS FOUND CORRODED BEYOND SRM LIMITS. DAMAGE WAS REPAIRED PER SRM 53-10-9, FIG 5.
DURING ACCOMPLISHMENT OF CPCP TASK C53-208-01, BS 747 FRAME WAS FOUND WITH CORROSION BEYOND SRM LIMITS BETWEEN S27R AND S28R. DAMAGE WAS REPAIRED PER SRM 53-10-4, FIG. 7.
DURING ACCOMPLISHMENT OF CPCP TASK C53-107-02, STRINGERS 24L AND 25L WERE FOUND CORRODED BEYOND SRM LIMITS AT VARIOUS LOCATIONS FROM BS 259.5 TO BS 390. STRINGER SECTIONS WERE REPLACED WITH NEW PARTS PER SRM 51-10-1.
DURING ACCOMPLISHMENT OF CPCP TASK C53-107-02, FLOORBEAM SECTION AT BS 947.5 FROM RBL 22 TO LBL 22, WAS FOUND CORRODED BEYOND SRM LIMITS. DAMAGE REPAIRED PER SRM 53-10-9, FIG 2.
DURING ACCOMPLISHMENT OF CPCP TASK C53-107-02, CABIN FLOOR TRACK AT BS 335, RBL 22, WAS FOUND CORRODED BEYOND SRM LIMITS. DAMAGED PART WAS REPLACED PER SRM 53-10-5, FIG 2.
DURING ACCOMPLISHMENT OF CPCP TASK C53-107-02, CABIN FLOORBEAM AT BS 277, LBL 10 TO LBL 29, WAS FOUND CORRODED BEYOND SRM LIMITS. DAMAGE WAS REPAIRED PER SRM 53-10-9, FIG 6.
DURING ACCOMPLISHMENT OF CPCP TASK C53-208-01, SHEAR TIE AT BS 727B FRAME BETWEEN S27R AND S28R WAS FOUND CORRODED BEYOND SRM LIMITS. THE DAMAGED PIECE WAS REPLACED, REPAIR ACCOMPLISHED PER SRM 53-10-4, FIG. 8.
DURING ACCOMPLISHMENT OF CPCP TASK C53-107-02, FLOORBEAM AT BS 967, RBL 3, WAS FOUND CORRODED BEYOND SRM LIMITS. THE PART WAS REPLACED PER SRM 51-20-1, 51-10-1 AND 51-30-6.
DURING ACCOMPLISHMENT OF CPCP TASK C53-208-01, ANTENNA MOUNT BETWEEN BS 767 AND 787 WAS FOUND CORRODED BEYOND SRM LIMITS. THE ANTENNA DOUBLER WAS REPLACED WITH A NEW PART PER SRM 51-30-2, FIG 1.
DURING ACCOMPLISHMENT OF CPCP TASK C53-107-02, CABIN FLOORBEAM AT BS 294.5 AT FORWARD GALLEY TRACK WAS FOUND TO HAVE CORROSION BEYOND SRM LIMITS. DAMAGE WAS REPAIRED PER SRM 53-10-9, FIG. 5 AND SRM 53-10-5, FIG 2.
DURING ACCOMPLISHMENT OF CPCP TASK C53-107-02, FLOORBEAM BRACE ANGLE AT BETWEEN BS 1006 AND BS 1016, LBL 3, WAS FOUND CORRODED BEYOND SRM LIMITS. NEW PART INSTALLED PER SRM 51-20-1, 51-10-1 AND 51-30-2.
DURING ACCOMPLISHMENT OF CPCP C53-208-01, THE AFT RIGHT HAND CARGO TIE DOWN FITTING AT BS 540 WAS FOUND CORRODED BEYOND SRM LIMITS. THE PART WAS REPLACED PER SRM 53-10-5, 51-10-5 AND 53-10-2.
DURING ACCOMPLISHMENT OF CPCP TASK C53-208-01, S27L WAS FOUND CORRODED BEYOND SRM LIMITS AT BS 904. THE STRINGER SECTIONS WERE REPLACED BETWEEN BS 881 AND BS 933 PER SRM 51-10-2, 51-30-0 AND 53-10-3 FIG 1.
DURING ACCOMPLISHMENT OF CPCP TASK C53-107-02, FLOORBEAM ANGLE AT BS 1016, P/N- 65-46812-185, WAS FOUND CORRODED BEYOND SRM LIMITS. THE PART WAS REPLACED PER SRM 51-30-0.
DURING ACCOMPLISHMENT OF CPCP TASK C53-107-01, THE INNER CHORD THAT RUNS FORE AND AFT OF THE L2 DOOR ENTRY WAY WAS FOUND TO HAVE CORROSION BEYOND SRM LIMITS AT THE POINT OF THE FORWARD DOOR FRAME. DAMAGED AREA WAS REPAIRED PER SRM 51-40-3.
DURING ACCOMPLISHMENT OF CPCP TASK C53-107-02, CABIN FLOORBEAM AT BS 312, LBL 10 TO RBL 9, WAS FOUND CORRODED BEYOND SRM LIMITS. DAMAGE WAS REPAIRED PER SRM 53-10-9, FIG 6.
DURING ACCOMPLISHMENT OF CPCP TASK C53-107-02, FLOORBEAM AT BS 986.5, LBL 38.75, WAS FOUND TO HAVE CORROSION BEYOND SRM LIMITS AT THE FORWARD CHORD AND UPPER CAP. DAMAGE WAS REPAIRED PER SRM 53-10-9, FIG 2.
DURING ACCOMPLISHMENT OF CPCP TASK C53-107-02, FLOORBEAM AT BS 1006, LBL 4 TO LBL 14, WAS FOUND CORRODED BEYOND SRM LIMITS. DAMAGE WAS REPAIRED PER SRM 53-10-9, FIG 2.
R1 DOOR EMERGENCY ESCAPE SLIDE FAILED TO PROPERLY INFLATE DURING CREW TRAINING EXERCISE. THE EVACUATION SLIDE ASSEMBLY WAS ROUTED TO THE OVERHAUL VENDOR FOR EVALUATION. THE OVERHAUL VENDOR REPLACED THE REGULATOR VALVE ASSEMBLY, (P/N 3001-BN) AND INFLATION HOSE ASSEMBLY, (P/N 1271-1080K) TO CORRECT THE SLOW INFLATION AND LOW PRESSURE SITUATION.
DURING COMPLIANCE WITH AD 84-20-03, CORROSION WAS FOUND ON THE AFT PRESSURE BULKHEAD WEB, CHORDS, ANGLES AND FITTINGS AT BS 1016. REPAIR WAS ACCOMPLISHED IN ACCORDANCE WITH AN ALTERNATE METHOD THAT WAS APPROVED BY BOEING ENGINEERING. FAA FORM 8110-3 AND ACCOMPANYING DATA ON FILE.
DURING SCHEDULED CHECK, THE FORWARD SECTION EMERGENCY EXIT LIGHTS FAILED TO ILLUMINATE. THE ASSOCIATED SYSTEM POWER SUPPLY WAS REMOVED AND REPLACED. SUBSEQUENT SYSTEM CHECK WAS SATISFACTORY PER BMM 33-51-11.
DURING SCHEDULED CHECK, THE RT OVERWING EXTERNAL EMERGENCY EXIT LIGHT FAILED TO ILLUMINATE. THE ASSOCIATED SYSTEM BATTERY PACK WAS REMOVED AND REPLACED. SUBSEQUENT SYSTEM CHECK WAS SATISFACTORY PER BMM 33-51-11.
EN ROUTE BETWEEN DLH AND JAX, THE NR 1 ENGINE WAS SHUT DOWN DUE TO AN OVERHEAT WARNING. BOTH ENGINE FIRE EXTINGUISHER CYLINDERS WERE DISCHARGED. AIRCRAFT DIVERTED TO SAV AND LANDED WITHOUT INCIDENT. UPON INSPECTION, THE NR 1 ENGINE LOWER OVERHEAT SENSING ELEMENT WAS FOUND TO BE IN CONTACT WITH THE LOOP PROTECTIVE ENCLOSURE CAUSING A SHORT CIRCUIT IN THE SYSTEM. THE CONDITION WAS RECTIFIED, BOTH ENGINE EXTINGUISHERS WERE REPLACED. ALL SYSTEM TESTS PER BMM 26-11-0 AND 26-11-11 WERE ACCOMPLISHED SATISFACTORILY. THE AIRPLANE RETURNED TO SERVICE.
DURING SCHEDULED CHECK, THE FORWARD SECTIONS OF THE FLOOR TRACK EMERGENCY EXIT LIGHT SYSTEM ILLUMINATED WHEN THE CONTROL SWITCH WAS PLACED IN THE ARMED POSITION. THE ASSOCIATED SYSTEM BATTERY CHARGER WAS REPLACED. SUBSEQUENT SYSTEM TESTS WERE SATISFACTORY PER BMM 33-51-11.
DURING SCHEDULED CHECK, THE EXTERNAL EMERGENCY EXIT LIGHT AFT OF THE R2 DOOR WAS FOUND INOPERATIVE. THE LAMP WAS REPLACED. SUBSEQUENT SYSTEM CHECK WAS SATISFACTORY PER BMM 33-51-11.
DURING SCHEUDLED CHECK, THE CENTER CABIN OVERHEAD INTERNAL EMERGENCY EXIT LIGHT WAS FOUND INOPERATIVE. THE ASSOCIATED SYSTEM BATTERY PACK WAS REPLACED. SUBSEQUENT SYSTEM CHECK WAS SATISFACTORY PER B-737 MM 33-51-1.
DURING SCHEDULED CHECK, THE EXTERIOR EMERGENCY EXIT LIGHT AFT OF THE R-1 DOOR WAS FOUND INOPERATIVE. THE LIGHT BULB WAS REPLACED. SUBSEQUENT SYSTEM CHECK WAS SATISFACTORY PER B-737 MM 33-51-1. (X)
A/C RETURNED TO SLC AFTER T/O ON A REPOSITIONING FLIGHT TO BOI WHEN THE NR 1 AND NR 2 'A' SYS HYD PUMP LOW PRESS WARNING LIGHTS ILLUMINATED FOLLOWED BY THE HYDRAULIC QTY LOW LVL LIGHT. THE A/C LANDED W/O INCIDENT BUT HAD TO BE TOWED FROM THE RUNWAY DUE TO LOSS OF STEERING CAPABILITY. TROUBLESHOOTING REVEALED THAT A HOLE HAD WORN INTO THE .5 INCH HYD PRESS LINE RUNNING FROM THE FWD END OF THE NR 2 ENG PYLON AFT AND OVER THE ENG TO THE ENG DRIVEN HYDRAULIC PUMP RESULTING IN FLUID LOSS. THE UNSERVICEABLE HYDRAULIC LINE WAS REMOVED AND REPLACED. ALL 'A' SYS PRESS AND CASE DRAIN FILTERS CHECKED FOR CONTAM. THE HYD SYS WAS RESERVICED, ALL LK AND OPS CHECK ACCOMP. A/C WAS RETURNED TO SERV. (M)
DURING SCHEDULED CHECK, THE AFT SECTION OF EMERGENCY FLOOR TRACK LIGHTING WAS FOUND INOPERATIVE. THE ASSOCIATED SYSTEM BATTERY PACK WAS REPLACED. SUBSEQUENT SYSTEM CHECK WAS SATISFACTORY PER BMM 33-51-11. (M)
DURING SCHEDULED CHECK, THE AFT FLOOR TRACK EMERGENCY EXIT LIGHTS WERE FOUND INOPERATIVE. THE ASSOCIATED SYSTEM BATTERY PACK WAS REPLACED. SUBSEQUENT SYSTEM CHECK WAS SATISFACTORY PER BMM 33-51-11. (M)
DURING SCHEDULED CHECK, FOUND LEFT LOWER AFT AND UPPER AFT EXTERIOR EMERGENCY EXIT LIGHTS INOPERATIVE. LAMPS WERE REPLACED AT EACH LOCATION. SUBSEQUENT OPERATIONAL CHECK WAS SATISFACTORY PER BMM 33-51-11. (M)
UPON LANDING AT TPA, THE NR 1 ENGINE OVERHEAT LIGHT CAME ON INTERMITTENTLY. THE NR 1 ENGINE OVERHEAT/FIRE DETECTION LOOPS WERE VISUALLY INSPECTED, SUSPECTED AREAS REPOSITIONED, CONNECTIONS CLEANED. SUBSEQUENT SYSTEM TESTS WERE SATISFACTORY PER BOEING MAINTENANCE MANUAL 26-11-0.
UPON LANDING AT TPA, THE NR 1 ENGINE OVERHEAT LIGHT CAME ON INTERMITTENTLY. THE FIRE DETECTION ACCESSORY UNIT WAS REPLACED, SUBSEQUENT SYSTEM TEST WAS SATISFACTORY PER BOEING MM 26-11-0.
DURING SCHEDULED CHECK, THE FORWARD AREA LIGHT/EMERGENCY EXIT LIGHT WAS FOUND INOPERATIVE. WIRING LEADING TO THE BATTERY PACK POWER SUPPLY WAS FOUND TO BE BROKEN. THE WIRING WAS REPAIRED, SUBSEQUENT SYSTEM OPS CHECK WAS SATISFACTORY PER B-737 MM 33-51-11. (M)
DURING SCHEDULED CHECK, THE FORWARD AREA LIGHT/EMERGENCY EXIT LIGHT WAS FOUND INOPERATIVE. THE ASSOCIATED BATTERY PACK WAS REMOVED, CHARGED, AND REINSTALLED. SUBSEQUENT OPS CHECK WAS SATISFACTORY PER B-737, MM 33-51-11.
DURING SCHEDULED CHECK, THE FORWARD AREA LIGHT/EMERGENCY EXIT LIGHT WAS FOUND INOPERATIVE. THE ASSOCIATED BATTERY PACK WAS REMOVED, CHARGED, AND REINSTALLED. SUBSEQUENT OPS CHECK WAS SATISFACTORY PER B-737, MM 33-51-11.
DURING SCHEDULED CHECK, THE FORWARD 'AREA LIGHT/LIGHTED EXIT' INTERIOR EMERGENCY EXIT LIGHT WAS FOUND INOPERATIVE. THE ASSOCIATED BATTERY PACK WAS REPLACED. SUBSEQUENT OPS CHECKS WERE SATISFACTORY PER THE BOEING MM 33-51-11.
DURING SCHEDULED CHECK, THE FORWARD BULLNOSE INTERIOR EMERGENCY EXIT LIGHT WAS FOUND INOPERATIVE. THE ASSOCIATED SYSTEM BATTERY PACK WAS REPLACED. SUBSEQUENT SYSTEM TEST WAS SATISFACTORY.
DURING COMPLIANCE WITH AD 90-25-01, CPCP TASK C53-701-02, CORROSION FOUND AT THE LEFT HORIZONTAL STABILIZER AFT, UPPER CENTER SECTION LUG AROUND THE BUSHINGS. THE BUSHINGS WERE REPLACED PER BOEING SB 737-55-1033 AND 737-55-1055.
DURING COMPLIANCE WITH AD 90-25-01, CPCP TASK C53-107-01, FLOOR BEAM SECTION RUNNING VERTICALLY FROM BS 986 TO 1006 WAS FOUND CORRODED BEYOND LIMITS. THE DAMAGED AREA WAS REPAIRED PER B-737 SRM 51-20-1 AND 51-30-2. (W)
DURING COMPLIANCE WITH AD 90-25-01, CPCP TASK C53-701-02, THE RT HORIZONTAL STABILIZER AFT, LOWER BOLT WAS EXTREMELY DIFFICULT TO LOOSEN/REMOVE. ONCE REMOVED, THE BOLT AND BUSHINGS WERE FOUND GALLED. EVIDENCE OF CORROSION AROUND BUSHING TO FITTING LUG MATING SURFACES. THE BUSHINGS WERE REPLACED PER BOEING SB 737-55-1033 AND 737-55-1055. THE BOLT WAS REPLACED WITH A NEW UNIT. (W)
DURING COMPLIANCE WITH AD 90-25-01 CPCP TAKS C53-107-01, FLOOR BEAM RUNNING HORIZONTALLY AT BS 986 WAS FOUND CORRODED BEYOND LIMITS. THE DAMAGED FLOOR BEAM SECTION WAS REPAIRED PER B-737 SRM 53-10-9. (W)
DURING COMPLIANCE WITH AD 90-25-01, CPCP TASK C53-701-02, THE LEFT HORIZONTAL STABILIZER AFT, LOWER BOLT WAS EXTREMELY DIFFICULT TO LOOSEN/REMOVE. ONCE REMOVED, THE BOLT AND BUSHINGS WERE FOUND GALLED. EVIDENCE OF CORROSION AROUND BUSHING TO FITTING LUG MATING SURFACES. THE BUSHINGS WERE REPLACED PER BOEING SB 737-55-1033 AND 737-55-1055. THE BOLT WAS REPLACED WITH A NEW UNIT. (W)