N733PA
Registered owner: AMAZON.COM SERVICES LLC, WA (owner ≠ operator)
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
POST-FLIGHT INSPECTION FOUND PORTION OF SKIN MATERIAL TORN ON VERTICAL STABILIZER DURING FLIGHT.
ON CLIMBOUT, RIGHT WING TO BODY OVERHEAT LIGHT ILLUMINATED. REDUCED POWER ON RIGHT ENGINE LIGHT EXTINGUISHED. RETURNED TO AIRPORT FOR UNEVENTFUL LANDING. REPLACED BLEED AIR CLAMP ON RIGHT BLEED AIR DUCT ON RIGHT ENGINE. SUBSEQUENT LEAK CHECK OF DUCT WAS SATISFACTORY.
STRAP DAMAGED.
DAMAGE /DRILL START ON FRAME.
CORROSION FOUND ON LOWER SPAR CHORD.
DAMAGED FRAME AT BS 867 S26R.
FRAME CRACKED AT AIR CONDITIONING BRACKET.
CRACKED FRAME AT AIR CONDITIONING SUPPORT BRACKET.
STRINGER CLIP AT BS 663 S10L CRACKED.
STRINGER CLIP CRACKED AT BS 360 S5L.
LEVEL 1 CORROSION FOUND ON STRINGER.
CRACKED STRINGER CLIP AT BS 500A S19R.
STRINGER CLIP CRACKED AT BS 908 S4R.
STRINGER CLIP CRACKED AT BS 767 S22L.
STRINGER CLIP CRACKED AT BS 907 S21R.
CRACKED STRINGER CLIP AT BS 706 S13R.
STRINGER CLIP AT BS 663 S9R IS CRACKED.
LEVEL 1 CORROSION FOUND ON L1 DOOR INNER SILL. SECOND BLEND ON THIS PART'S HISTORY.
LEVEL 1 CORROSION FOUND ON FORWARD SERVICE DOOR SILL CHORD. SECOND BLEND IN THIS PART'S HISTORY.
DURING INSPECTION, CRACKS WERE FOUND IN THE BEAR STRAP RE-INFORCEMENT OF THE L1 DOOR, BS 304 S10-13L.
STRINGER CLIP CRACKED AT BS 400 S18R.
DAMAGED SHEAR TIE FRAME.
EXPERIENCED SMOKE IN THE COCKPIT AT THE GATE PRIOR TO DEPARTURE. THE FLIGHT CREW QUICKLY POWERED DOWN THE AIRCRAFT; NO PASSENGERS WERE ON BOARD. MAINTENANCE FOUND THE GROUND SERVICE CONTACTOR TO BE THE PROBLEM AND ONE PHASE OF THE THREE PHASE GROUND POWER CIRCUIT BREAKER OVERHEATED AND DID NOT OPEN. GROUND POWER CONTACTOR AND KLIXON CIRCUIT BREAKER P/N BACC18AE25 REPLACED.
REPAIRED FUSELAGE SKIN BLEND OUT 0.4 INCHES BELOW STRINGER S-20L, STA: BS 896 IN ACCORDANCE WITH BOEING 737-200 STRUCTURAL REPAIR MANUAL (SRM), REV 101, DATED MARCH 10, 2010, SECTION 53-30-3, FIGURE 48. REFERENCE NON-ROUTINE TASK CARD 799, DATED MARCH 25, 2010.
REPAIRED FUSELAGE SKIN BLEND OUT BELOW STRINGER S-25R, STA BS 885.25 IN ACCORDANCE WITH BOEING 737-200 STRUCTURAL REPAIR MANUAL, REV 101, DATED MAR 10, 2010, SECTION 53-30-3, PAGES 254, 257 TO 263 AND 286 AND 51-30-1, PAGE 3. REFERENCE NON-ROUTINE TASK CARD 661, 662, AND 660, DATED MARCH 18, 2010.
REPAIRED SHEAR TIE BETWEEN STRINGERS 20L AND S-21L, STA: BS 907 IN ACCORDANCE WITH BOEING 737-200 STRUCTURAL REPAIR MANUAL (SRM), REV 101, DATED MARCH 10, 2010, SECTION 53-10-4, FIGURE 8. REFERENCE NON-ROUTINE TASK CARD 813, DATED APRIL 01, 2010.
REPAIRED FUSELAGE SKIN SCRIBE LINES LEFT WING TO BODY FAIRING AT STRINGERS S-16L TO 3 INCHES BELOW S-17L, STA: BS 500B - 516 IN ACCORDANCE WITH MESSAGE KFC-ATR-10-0001-01C, DATED MARCH 30, 2010, KFC-ATR-10-0001-05B, DATED MARCH 31, 2010, KFC-ATR-10-0001-06B, DATED APRIL 02, 2010, KFC-10-0001-07C, DATED APRIL 15, 2010, BOEING REPAIR SKETCH KEL-ATR-10-0001-01C, SHTS 1 AND 2, AND BOEING ENGINEERING APPROVED FORM 8100-9, NO. 201003310069-0002D1, DATED APRIL 20, 2010. REFERENCE NON-ROUTINE TASK CARD 763, DATED MARCH 19, 2010.
REPAIRED FUSELAGE SKIN BLEND OUT AT STRINGER S-20L, STA: BS 974 IN ACCORDANCE WITH BOEING 737-200 STRUCTURAL REPAIR MANUAL, REV 101, DATED MARCH 10, 2010, SECTION 53-30-3, FIGURE 48, DETAIL XV. REFERENCE NON-ROUTINE TASK CARD 743, 742 AND 744, DATED MARCH 18, 2010.
REPAIRED FUSELAGE SKIN BLEND OUT 1.6 INCHES ABOVE STRINGER S-23L, STA: BS 926.5 IN ACCORDANCE WITH BOEING 737-200 STRUCTURAL REPAIR MANUAL, REV 101, DATED MARCH 10, 2010, SECTION 53-30-3, FIGURE 48, PAGES 256 TO 260 AND 264, DETAIL VII, PAGES 261 AND 281 AND 51-70, FIGURE 1, PAGE 4, 51-30-2, PAGE 3C AND 51-30-3, PAGE 7. REFERENCE NON-ROUTINE TASK CARD 737 AND 514, DATED MARCH 18, 2010.
REPAIRED FUSELAGE SKIN BLEND OUT ABOVE STRINGER S-26R, STA: BS 838.5 IN ACCORDANCE WITH MESSAGE KFC-ATR-10-0001-01C, DATED MARCH 31, 2010, KFC-ATR-10-0001-05B, DATED APRIL 05, 2010, KFC-ATR-10-0001-06C, DATED APRIL 19, 2010, BOEING REPAIR DRAWING 65-45775, SHT 18, AND BOEING ENGINEERING APPROVED FORM 8100-9, NO 201004010066-0002D1, DATED APRIL 21, 2010. REFERENCE NON-ROUTINE TASK CARD 702, DATED MARCH 18, 2010.
REPAIRED FUSELAGE NICK 3 INCHES ABOVE STRINGER S-20R, STA: BS 914 IN ACCORDANCE WITH BOEING 737-200 STRUCTURAL REPAIR MANUAL (SRM), REV 101, DATED MARCH 10, 2010, SECTION 53-30-3, FIGURE 48. REFERENCE NON-ROUTINE TASK CARD 617, DATED MARCH 18, 2010.
REPAIRED STRINGER INTERCOSTAL AT STRINGER S-4L, STA: BS 305 BY REPLACEMENT WITH NEW PART 50-8261-62 IN ACCORDANCE WITH BOEING 737-200 STRUCTURAL REPAIR MANUAL (SRM), REV 101, DATED MARCH 10, 2010, SECTION 53-30-3 AND BOEING DRAWING 50-8261, REV H. REFERENCE NON-ROUTINE TASK CARD 428, DATED MARCH 15, 2010.
REPAIRED FUSELAGE SKIN BLEND OUT 1.75 INCHES ABOVE STRINGER S-23R, STA: BS 904.8 IN ACCORDANCE WITH BOEING 737-200 STRUCTURAL REPAIR MANUAL, REV 101, DATED MARCH 10, 2010, SECTION 53-30-3, FIGURE 48. REFERENCE NON-ROUTINE TASK CARD 380, 374, 375, AND 383, DATED MARCH 12, 2010.
REPAIRED FUSELAGE SKIN BLEND OUT THREE INCHES BELOW STRINGER S-25R, STA: BS 775 IN ACCORDANCE WITH BOEING 737-200 STRUCTURAL REPAIR MANUAL, REV 101, DATED MARCH 10, 2010, SECTION 53-30-3, FIGURE 48, DETAIL XII. REFERENCE NON-ROUTINE TASK CARD 334, 316 AND 663, DATED MARCH 12, 2010.
REPLACED NLG UPPER ATTACH BEARING IN ACCORDANCE WITH FAA DER APPROVED FORM 8110-3 NO. 091-1236-10-848, DATED APRIL 01, 2010, ASI ENGINEERING REPORT 5310848-ER, REV IR, DATED MARCH 25, 2010 AND ASI DRAWING 5310848-1, SHTS 1 THRU 3, REV IR, DATED MARCH 25, 2010. REFERENCE NON-ROUTINE TASK CARD 261, DATED MARCH 11, 2010.
REPAIRED FUSELAGE SKIN BLEND OUT AT STRINGER S-23L, STA: BS 897 IN ACCORDANCE WITH BOEING 737-200 STRUCTURAL REPAIR MANUAL, REV 101, DATED MAR 10, 2010, SECTION 53-30-1, FIGURE 1 AND 53-30-3, FIGURE 48. REFERENCE NON-ROUTINE TASK CARD 206, DATED MAR 08, 2010.
REPAIRED LEFT AND RIGHT GRAVEL EQUIPPED NOSE LANDING GEAR FILLET FAIRINGS AND DOOR FAIRINGS IN ACCORDANCE WITH FAA DER APPROVED FORM 8110-3, REV IR, DATED JANUARY 22, 2010 AND ENGINEERING STRESS REPORT SCS-3220-001, REV IR, DATED OCTOBER 05, 2009 AND SCS-3220-002SR, REV IR, DATED JANUARY 21, 2010. REFERENCE ROUTINE TASK CARD 43, DATED MARCH 01, 2010.
NLG WOULD NOT RETRACT AFTER TAKE-OFF. SELECTED GEAR DOWN AND RETURNED TO DEPARTURE AIRPORT. FOUND NOSE GEAR GRAVEL DEFLECTOR ACTUATOR FUNCTIONING IMPROPERLY.
DURING MINI EVACUATION DEMONSTRATION TRAINING SLIDE DEPLOYED BUT DID NOT INFLATE. WAITING ON TEAR DOWN REPORT FOR FINAL DISPOSITION.
DURING MINI EVACUATION DEMONSTRATION TRAINING SLIDE DEPLOYED BUT DID NOT INFLATE. WAITING ON TEAR DOWN REPORT FOR FINAL DISPOSITION. 11/20/08 FINAL DISPOSITION. TEARDOWN REPORT INDICATED NO FINDINGS.
CRACK IN INTERCOSTAL ATTACH CLIP STA BS 294.5 STR 11L. REPLACED INTERCOSTAL ATTACH CLIP STA BS 294.5 STR 11L IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-2, FIGURE 1, 51-20-1, FIGURE 7, 51-30-2, 7.D.(6), AND 51-30-2, FIGURE 7, 3, 11 AND 12. REFERENCE NON-ROUTINE CARD 648, DATED 03/05/08.
CORROSION FOUND ON FLOORBEAM STA BS 1016 BL 5 THRU BL 38 LEFT HAND. CORROSION ON FLOORBEAM STA BS 1016 BL 5 THRU BL 28 LEFT REMOVED AND FOUND TO BE BEYOND LIMITS IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-10-01, FIGURE 1. FLOORBEAM REPAIRED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-40-04, FIGURE 1. REFERENCE NON-ROUTINE CARD 19, DATED 03/04/08.
CLIP CRACKED AT STA BS 1006 STR 21L. REPLACED CLIP AT STA BS 1006 STR 21L IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-01 AND 51-30-02. REFERENCE NON-ROUTINE CARD 578, DATED 03/04/08.
STRINGER TO FRAME CLIP REQUIRES BLENDING AT STA BS 907 STR 25L (REAR CARGO PIT). INSTALLED NEW CLIP AT STA BS 907 STR 25L IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-03. REFERENCE NON-ROUTINE CARD 586, DATED 03/04/08.
LEFT HAND ENGINE TAILPIPE CRACKED AT BRACKET MOUNT (3 O'CLOCK POSITION). REPAIRED LEFT HAND ENGINE TAILPIPE BRACKET MOUNT (3 O'CLOCK POSITION) IN ACCORDANCE WITH FAA DER APPROVED FORM 8110-3, 073-1236-08-477 AND ASI SOLUTIONS DRAWING 7830477-1, REV IR, DATED MARCH 18, 2008. REFERENCE NON-ROUTINE CARD 826, DATED 03/11/08.
LOWER LONGITUDINAL FLOORBEAM CHORD CRACKED AT LBL 24.5 STA BS 663. REPLACED LOWER LONGITUDINAL FLOORBEAM CHORD AT LBL 24.5 STA BS 663 IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-01 AND BOEING DRAWING 65-45410. REFERENCE NON-ROUTINE CARD 843, DATED 03/18/08.
CORROSION ON AFT GALLEY FLOORBEAM AT STA BS 980 RBL 4. BLENDED AND FOUND CORROSION ON AFT GALLEY FLOORBEAM AT STA BS 980 RBL 4 TO BE BEYOND LIMITS. REPAIRED AFT GALLEY FLOORBEAM AT STA BS 980 RBL 4 IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-40-4. REFERENCE NON-ROUTINE CARD 488, DATED 03/04/08.
REPAIR CRACKED SPREADER BARS ON PASSENGER SEATS. REPAIRED CRACKED SPREADER BARS ON PASSENGER SEATS IN ACCORDANCE WITH CPAI EO C007-2525-B737-01 AND FAA DER APPROVED 8110-3, 080-1226-08-471 AND ASI DRAWING 2520471-1, REV IR, DATED MARCH 19, 2008. REFERENCE KELOWNA FLIGHTCRAFT NON-ROUTINE CARD 160, DATED 02/28/08.
CRACK IN FUSELAGE SKIN AT STA BS 760 STR 19L, (NDT CONFIRMED CRACK). REPAIRED FUSELAGE SKIN AT STA BS 760 STR 19L IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-30-03, FIGURE 48, FASTENERS INSTALLED IN ACCORDANCE WITH SRM 51-30-02. REFERENCE NON-ROUTINE CARD 542, DATED 03/04/08.
LIGHTNING STRIKE AT STA BS 933 STR 25.5R. REPAIRED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-30-03, FIGURE 23 (PERMANENT REPAIR), SECTION 1, PARAGRAPH 3., (NDT08-0509). REFERENCE NON-ROUTINE CARD 602, DATED 03/04/08.
LOWER LONGITUDINAL FLOORBEAM CHORD CRACKED AT RBL 24.5 STA BS 663. REPLACED LOWER LONGITUDINAL FLOORBEAM CHORD AT RBL 24.5 STA BS 663 IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-01 AND BOEING DRAWING 65-45410. REFERENCE NON-ROUTINE CARD 844, DATED 03/18/08.
CORROSION ON UPPER CAP OF FLOORBEAM AT STA BS 294.5 BETWEEN LBL 12 AND RBL 50. CORROSION ON UPPER CAP OF FLOORBEAM AT STA BS 294.5 BETWEEN LBL 12 AND RBL 50 BLENDED BEYOND LIMITS IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-10-1. REPAIRED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-10-9. REFERENCE NON-ROUTINE CARD 494, DATED 03/04/08.
LOWER CHORDS OF KEEL BEAM IN MAIN LANDING GEAR HAS CORROSION AT LOWER FLANGE IN SEVERAL AREAS UPPER & LOWER SURFACES FROM STA BS 663-727 RBL 6.5 & LBL 6.5. REPAIRED LOWER CHORD OF KEEL BEAM IN MLG WHEEL WELL AT LOWER FLANGE IN ACCORDANCE WITH BOEING MESSAGE 1-789220434-4, DATED MARCH 28, 2008. FASTENERS INSTALLED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-2. REFERENCE NON-ROUTINE CARD 570, DATED 03/04/08.
CORROSION ON FLOOR I-BEAM AT STA BS 344 LBL 18 THRU RBL 39. REPAIRED FLOOR I-BEAM AT STA BS 344 LBL 18 THRU RBL 39 IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-10-9, FIGURE 5. REFERENCE NON-ROUTINE CARD 858, DATED 03/25/08.
CRACKED APU TORQUE BOX WEB AT STA BS 1115 RBL 2. HFEC CARRIED OUT IN ACCORDANCE WITH BOEING 737 NDT MANUAL 51-00-00, FIGURE 23, PART 6 ON A CUT-OUT ON THE APU TORQUE BOX, STA BS 1115. NO DEFECTS EVIDENT (NDT08-0461). APU TORQUE BOX WEB AT STA BS 1115 RBL 2 REPAIRED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-40-01, FIGURE 1 AND INSTALLED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-02, FIGURE 3 AND 11. REFERENCE NON-ROUTINE CARD 859, DATED 03/25/08.
CRACK ON BODY FRAME INNER CHORD STA BS 616 LEFT HAND AT STUB BEAM LOWER CHORD. REPAIRED BODY FRAME INNER CHORD STA BS 616 LT AT STUB BEAM LOWER CHORD IN ACCORDANCE WITH BOEING SB 737-53A-1254. REFERENCE KELOWNA FLIGHTCRAFT NON-ROUTINE CARD 672, DATED 03/05/08.
LEFT HAND MAIN LANDING GEAR WHEEL WELL FAIRING SUPPORT GOUGED AT AFT OUTBOARD SIDE. REPAIRED LT MLG WHEEL WELL SUPPORT AT AFT OUTBOARD SIDE IN ACCORDANCE WITH FAA DER APPROVED FORM 8110-3, 073-1236-08-476 AND ASI SOLUTIONS DRAWING 5350476-1, REV IR, DATED MARCH 13, 2008. REFERENCE NON-ROUTINE CARD 27, DATED 02/27/08.
STRINGER TIE CLIP DAMAGED AT STA BS 500A, STR 25R. REPLACED STRINGER TIE CLIP AT STA BS 500A STR 25R IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-1, PAGE 9, SECTION 7 AND 51-30-03. REFERENCE NON-ROUTINE CARD 590, DATED 03/04/08.
LOOSE BUSHING ON STABILIZER SCREW JACK LOWER RIGHT HAND MOUNTING STRUCTURE (P/N 6-37464-1). REPLACED BUSHING ON STABILIZER SCREW JACK LOWER RT MOUNTING STRUCTURE IN ACCORDANCE WITH FAA DER APPROVED FORM 8110-3, 078-1236-08-473 AND ASI SOLUTIONS DRAWING 5340473-1, REV IR, DATED MARCH 14, 2008. REFERENCE NON-ROUTINE CARD 740, DATED 03/06/08.
CORROSION BETWEEN STA BS 1118 AND STA BS 1138 IN THE RIGHT HAND TORQUE BOX, BY THE APU INLET DUCT. CORROSION BETWEEN STA BS 1118 AND STA BS 1138 IN THE RIGHT HAND TORQUE BOX, BY THE APU INLET DUCT REMOVED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-06. ORIGINAL MATERIAL 0.063, AMOUNT OF REMOVED MATERIAL 0.025, OUT OF LIMITS IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-01, PAGE 45, DETAIL V. FORMED SECTION REPAIR CARRIED OUT IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-40-03.
CRACK IN INTERCOSTAL ATTACH CLIP AT STA BS 360 STR 11L. REPLACED INTERCOSTAL ATTACH CLIP AT STA BS 360 STR 11L IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-2, FIGURE 1, 51-20-1, FIGURE 7, 51-30-2, 7.D.(6), AND 51-30-2, FIGURE 7,3,11 AND 12. REFERENCE KELOWNA FLIGHTCRAFT NON-ROUTINE CARD 647, DATED 03/05/08.
LOWER CHORD OF KEEL BEAM IN MLG HAS CORROSION ON VERTICAL AND HORIZONTAL FLANGES IN SEVERAL AREAS FROM STA BS 663-727 LBL 615. REPAIRED LOWER CHORD OF KEEL BEAM ON LT SIDE BETWEEN STA BS 663 THRU 727 IN ACCORDANCE WITH FAA DER APPROVED FORM 8110-3, 095-1236-08-483 AND ASI SOLUTIONS DRAWING 5310483-1, REV IR, DATED APRIL 4, 2008. CORROSION BLENDED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-06 AND FAIRED AT A 10:1 RATIO IN ACCORDANCE WITH SRM 51-10-06. ALL PARTS TREATED AND PROTECTED IN ACCORDANCE WITH SRM 51-10-2. ALL FASTENERS INSTALLED IN ACCORDANCE WITH SRM 51-30-2. REFERENCE NON-ROUTINE CARD 876, DATED 03/31/08.
TRAILING EDGE FLAPS ASYMMETRY LOCKOUT BETWEEN ZERO AND ONE DEGREE. THERE IS A SPLIT IN T/E FLAP INDICATION, LT T/E FLAPS INDICATE ONE DEGREE AND RT T/E FLAPS INDICATE ZERO. FLIGHT CREW EXPERIENCED AN UNEVENTFUL LANDING AND NO UNCOMMANDED ROLL. MAINTENANCE DISCOVERED RT T/E FLAP POSITION TRANSMITTER WIRE HARNESS HAD CHAFED WIRES. REPLACED WIRE HARNESS FROM RT TRANSMITTER TO DISCONNECT STATION 720R CONNECTOR D4876P.
UPON DEPARTURE DURING HEAVY SNOW CONDITIONS WITH GRAVEL SKI EQUIPPED AIRCRAFT THE NOSE GEAR UNLOCK LIGHT REMAINED ON AFTER LANDING GEAR RETRACTION. LANDING GEAR EXTENDED AND AIRCRAFT RETURNED TO DEPARTURE AIRPORT WITH NORMAL LANDING. UPON INSPECTION FOUND GRAVEL DEFLECTOR TO BE CONTAMINATED WITH SNOW AND ICE. REMOVED SNOW AND ICE, JACKED AIRCRAFT AND SWUNG GEAR WITH NO DEFECTS NOTED. VERY HEAVY SNOW CONDITIONS ALLOWED FOR SNOW BUILD UP ON DEFLECTOR DURING TAXI OUT. DEFLECTOR WAS DEICED PRIOR TO TAXI.
ON POST FLIGHT INSPECTION FOUND THREE INCH SKIN GOUGE AT FUSELAGE BS 895 BETWEEN STRS 22R AND 23R. REPAIRED WITH SKIN DOUBLER PER BOEING 737 SRM 53-30-3 AND 51-20-1.
DURING MAINTENANCE INSPECTION FOUND CRACK IN NR 2 LOWER THRUST REVERSER DOOR P/N 65MK78413-2 ALONG IB BUMPER. REMOVED BUMPER, STOP DRILLED CRACK, FABRICATE/INSTALL DOUBLER AND TRIPLER. FABRICATE AND INSTALL NEW CAP TO COMPENSATE FOR DOUBLER AND TRIPLER. ALL WORK ACCOMPLISHED IAW 8110-3 APPROVED DRAWING NR 7830233-1, REV ORIGINAL, DATED 03-20-2006 AND MATERIAL SUBSTITUTION REPORT NR 7830233-ER, REV ORIGINAL, DATED 03-20-2006.
DURING HEAVY MAINTENANCE INSPECTION FOUND CRACKS IN UPPER FLANGE RADIUS OF LONGERON/WEB P/N 65-20726-23 AT STA 455 AND 470, STR 26R. REMOVED WEB BETWEEN STA 440 - 493, FABRICATED REPLACEMENT WEB WITH 7075-T6 .063, IN LIEU OF ORIGINAL .056, AND INSTALLED IAW SRM AND MFG DRAWING NO 65-20726 AS SPECIFIED IN 8110-3 APPROVED DRAWING 5330-236-ERA, REV ORIGINAL, DATED 03-23-2006 AND MATERIAL SUBSTITUTION REPORT NO 5330236-ER, REV. ORIGINAL, DATED 03-23-2006.
DURING HEAVY MAINTENANCE VISIT FOUND DENT ON UPPER SURFACE OF LT IB MIDFLAP. REPAIRED FLAP BY INSTALLING INTERNAL DOUBLER AND FLUSH PART IN IAW SRM 57-50-4, FIG. 4 PG. 8 AND 9.
AFT EMERGENCY EXIT LIGHT UNDER AFT F/A SEAT INOP. REMOVED AND REPLACED EMERGENCY EXIT LIGHT ASSEMBLY IAW B737MM 33-51-191.
RT FLOOR LEVEL EMERGENCY EXIT DOOR LIGHT INOP. REMOVED AND REPLACED RT EMERGENCY EXIT POWER SUPPLY P/N 5822-12, CABLE LEAD AND 1 EL LAMP STRIP. OPS CHECKED GOOD PER AMM 33-51-191.
EXTERIOR EMERGENCY LIGHT BY L2 DOOR INOP. CLEANED CORROSION FROM EMERGENCY ESCAPE SLIDE LIGHTS, REINSTALLED LAMP ASSEMBLY AND TESTED GOOD IAW B737 MM33-51-61.
EMERGENCY EGRESS AFT FLOOR LIGHTING VERY DIM, THEN WENT INOP ON OPS CHECK. REMOVED AND REPLACED EMERGENCY EGRESS AFT BATTERY PACK IAW B737MM 33-51-93, OPS CHECK GOOD.
EMERGENCY ESCAPE FLOOR LIGHTING INOP FROM ROWS 15 TO 18. REPLACED BATTERY PACK, ESCAPE LIGHTING OPS CHECK GOOD IAW CPA AMM SUPPLEMENT 33-51-191.
FWD SECTION EMERGENCY FLOOR LIGHTS INOPERATIVE ROWS 1 - 3. REPLACED BROKEN FLOOR LIGHT STRIP IAW MM 33-51-191. OPS CHECK NORMAL.
FLOOR PROXIMITY EMERGENCY ESCAPE PATH LIGHTING INOP BETWEEN ROWS 9 TO 15. TROUBLESHOT, REMOVED AND REPLACED FLOOR PROXIMITY ESCAPE PATH LIGHTING CABLE LEAD ASSEMBLY IAW B737 MM 33-51-191, OPS CHECK GOOD.
EMERGENCY ESCAPE FLOOR LIGHTING FROM ROWS 16 TO 19 INOP AND L2 DOOR INTERIOR EMERGENCY EXIT LIGHTS INOP. CLEANED CONNECTOR ON EMERGENCY ESCAPE FLOOR LIGHT STRIP AT ROW 18 AND REMOVED AND REPLACED R2 DOOR EMERGENCY EXIT LIGHTS BATTERY PACK IAW B737MM 33-51-191, OPS CHECK GOOD.
AFT GALLEY DOOR EMERGENCY LIGHT INOP. REMOVED AND REPLACED BATTERY PACK IAW B737 NN 3351-71, OPS CHECKED GOOD.
"AT FL 280 & 6PSID A LOUD HIGH PITCHED NOISE AND VIBRATION AT L1 DOOR. RETURNED TO ANC AND AS A/C DEPRESSURIZED THE NOISE LESSENED BUT DID NOT GO AWAY" "INSPECTED FWD ENTRY DOOR IAW B737MM 52-11-0. ADJUSTED DOOR STOP PINS AND UPPER GATE DOOR IAW B737 MM 52-11-0, OPERATIONAL CHECK GOOD". DURING GROUND PRESSURIZATION CHECK ORIGINAL PROBLEM WAS DUPLICATED. FURTHER INSPECTION FOUND TEAR IN RUBBER SEAL OF THE HINGE FLAP ASSY LOCATED UNDER THE UPPER HINGE COVER. FURTHER GROUND PRESSURE CHECK CONFIRMED THIS TO BE THE PROBLEM. REPLACED HINGE FLAP ASSY.
R1 EMERGENCY EXIT SIGN INOPERATIVE. REMOVED AND REPLACED R-1 EMERGENCY EXIT SIGN BATTERY PACK. OPS CK GOOD IAW MM 33-51-00.
DURING POST D-CHECK FERRY FLIGHT, RETURNED TO DEPARTURE DUE TO AUTO PILOT CAPTURE LOC VERY SLUGGISH AND OVERSHOOTS DURING CORRECTION. WILL NOT CAPTURE GLIDE SLOPE. ALSO, RADIO ALTIMETER DH LIGHT COMES ON WHEN DH IS SET ABOVE 2500 FT AGL STARTS INDICATING WHEN PASSING 600 FT, INDICATOR FLICKERS WILDLY UPON READING DH. DURING CLIMB BETWEEN 4000 AND 5000 RAD ALT FLAGG APPEARED BRIEFLY.
DURING D CHECK INSPECTION RT HORIZONTAL STAB CENTER SECTION, AFT CENTER LUG FORWARD BUSHING FITTING WORN. REMOVED DAMAGE, INSTALLED REPAIR BUSHING IAW EA 5510-01191 AND AAR EA 10351.
DURING D CHECK INSPECTION DENT IN SKIN STA 1147.5, 8.5 INCHES ABOVE S5. A=2 INCHES Y=.056 A/Y=35.7, BUT DUE TO PROXIMITY OF CUTOUT FOR HORIZONTAL FITTING IT IS BEYOND LIMITS IAW SRM 53-30-1, FIG 1 NOTE K AND DETAIL 111. COMPLIED WITH HFEC. NO DEFECTS NOTED, COMPLIED WITH IAW ASA EA 5330-01757 AND AAR EA 10285.
DURING D CHECK INSPECTION COMPLIED WITH EA 10324 AND ASA EA 5720-01237 (LT WING MLG SUPPORT BEAM FITTING INSPECTION AND REPLACEMENT, SB 737-57-1216 REV. 2) REMOVED AND REPLACED LT WING SUPPORT BEAM FITTING IAW ASA EA 5720-01237 AND AAR EA 10324.
DURING D CHECK INSPECTION RT WING REAR SPAR TO MLG SUPPORT BEAM FITTING CRACKED AT IB UPPER CORNER. REMOVED DAMAGED MLG SUPPORT BEAM FITTING AND INSTALLED A NEW MLG SUPPORT BEAM FITTING IAW ASA EA 5720-01238 AND EA 10325.
DURING D CHECK INSPECTION TWO CRACKS FOUND ON KEELBEAM LOWER SKIN BETWEEN STA 660 AND 724 1 EA, 1.G INCH AND 1 EA. 1.25 INCH. REMOVED DAMAGE WEB, INSTALLED NEW WEB IAW B737 SRM 51-30-2.
DURING D CHECK RT WING UPPER SPAR AND SPAR WEB HAS ELONGATED HOLES. REAMED HOLES, TRIMMED UPPER FOOTPRINT IAW ASA EA 5720-01241 AND AAR EA 10336.
DURING D CHECK INSPECTION STA 651 FLOORBEAM, BL O REPAIR ANGLE HAS A FASTNER GIVING SHORTED ON P/N 65C34537-11 ANGLE. TRIMMED P/N 65C34537-11 ANGLE, FLAP PEENED, TREATED, PRIMED AND INSTALLED IAW ASA EA 5310-02318 AND AAR EA 10312.
DURING D CHECK INSPECTION C/W 061 LOG 4755634 REPLACE SKIN PANEL BS 173 - 259 STR 19R - 24R. REMOVED AND REPLACED SKIN PANEL IAW B737 SRM 51-30-2. SKIN REPLACE TO ELIMINATE PREVIOUS DENT REPAIRS.
DURING D CHECK INSPECTION C/W LOG 4755645 REPLACE SKIN PANEL BS 178-259 STR 24R - BLO. REMOVED AND REPLACED SKIN PANEL IAW B737 SRM 51-30-2. PANEL REPLACED TO ELIMINATE PREVIOUS REPAIRS DUE TO DENTS.
DURING D CHECK INSPECTION C/W 063 LOG 4755636 REPLACE SKIN PANEL BS 360 - 540 STR 19R - 25R. REMOVED AND REPLACED SKIN PANEL IAW B737 SRM 51-30-2. SIN REPLACED TO ELIMINATE PREVIOUS REPAIRS FOR DENTS.
DURING D CHECK INSPECTION C/W 064 LOG 4755637 REPLACE SKIN PANEL BS 727 - 968 STR 14R - 20R. REMOVED AND REPLACED SKIN PANEL IAW B737 SRM 51-30-2. PANEL REPLACED TO ELIMINATE PREVIOUS REPAIRS FOR DENTS.
DURING D CHECK INSPECTION C/W 065 LOG 4755638 REPLACE SKIN PANEL BS 727 - 908 STR 20R - 25R. REMOVED AND REPLACED SKIN PANEL IAW B737 SRM 51-30-2. PANEL REPLACED TO ELIMINATE PREVIOUS REPAIRS DUE TO DENTS.
DURING D CHECK INSPECTION C/W 066 LOG 4755639 REPLACED SKIN PANEL MFG 908 STR 20L TO 25L. REMOVED AND REPLACED SKIN IAW MFG SRM 51-30-2. PANEL REPLACED TO ELIMINATE PREVIOUS REPAIRS DUE TO DENTS.
DURING D CHECK INSPECTION C/W 067 LOG 4755640 REPLACE SKIN PANEL BS 908 - 1016 STR 20R - 25R. REMOVED AND REPLACED SKIN PANEL IAW B737 SRM 51-30-2. PANEL REPLACED TO ELIMINATE PREVIOUS REPAIRS DUE TO DENTS.
DURING D CHECK INSPECTION C/W 062 LOG 4753635 REPLACE SKIN PANEL BS 360 - 540 STR 14R - 19R. REMOVED AND REPLACED SKIN PANEL IAW B737 SRM 51-30-2. REPLACED TO ELIMINATE PREVIOUS REPAIRS DUE TO DENTS.
DURING D CHECK INSPECTION LT MLG SUPPORT BEAM HAS CORROSION IN OB ATTACH HOLE IN BETWEEN BUSHINGS. REMOVED BUSHINGS AND CORROSION. INSPECTED AND INSTALLED REPLACEMENT BUSHINGS IAW MFG EA 5750-01939 AND EA 10537. MINOR REPAIR.
DURING D CHECK INSPECTION BEAR STRAP HAS A HOLE BROKE FROM EDGE (NO E/D) STA 767, STR 18R. TRIMMED DAMAGE, FABRICATED AND INSTALLED REPAIR FILLER IAW MFG EA. 5330-01764 AND MFG EA 10311.
DURING D CHECK INSPECTION FOUND DENT AT STA 338 TO 344 JUST BELOW FWD AIRSTAIR DOOR CUTOUT BEYOND LIMITS IAW SRM 53-30-1 FIG 1 DETAIL 3. REF. SAD LOG 0176053 BEYOND LIMITS DUE TO CHANGES TO SRM INCLUDING PROXIMITY TO CUTOUTS AND SEAMS. REMOVED DAMAGED DOUBLER, FABRICATED AND INSTALLED REPLACEMENT REPAIR DOUBLER IAW ASA EA 5310-02327 AND AAR 10300.
DURING D CHECK INSPECTION C/W 069 LOG 4755642 REPLACE SKIN PANEL BS 908 - 1016 STR 20L TO 25L. REMOVED SKIN PANEL, RECEIVED AND INSTALLED NEW SKIN PANEL IAW MFG SRM 51-30-2.
DURING D CHECK INSPECTION FOUND LT HORIZONTAL STABILIZER LOWER SINGLE LEG ATTACH RIB FORWARD OF AFT SPAR, CRACKED. REMOVED RIB, FABRICATED AND INSTALLED REPLACEMENT RIB IAW B737 SRM 51-20-1, 51-30-5. STAB STA 67.54 - 69.
DURING D CHECK INSPECTION C/W 068 LOG 4755641, REPLACE SKIN PANEL BS 908 - 1016, STR 14L - 20L. REMOVED SKIN, INSTALLED NEW SKIN PANEL IAW SRM 51-30-2. REPLACED AT CUSTOMER REQUEST DUE TO DENT.
DURING D CHECK INSPECTION FOUND LOSS OF E.D. AT HOLE ON STA 251 FRAME AND W/W LT HAND EDGE STRAP. REMOVED DAMAGED AREA, FABRICATED AND INSTALLED REPAIR FILLER IAW EA 5330-01765 AND E.A. 10340.
DURING D CHECK INSPECTION DENT AT STA 479, 12 INCHES BELOW CARGO DOOR. EDGE OF DENT LESS THAN 3 INCHES FROM CLOSEST FASTNERS IN LAP IAW SRM 53-30-1, FIG. 1 DETAIL 3, DENT IS BEYOND LIMITS. REF. SAD LOG NR 4600061. AREA IS NOW BEYOND LIMITS DUE TO CHANGES IN SRM WHICH INCLUDE PROXIMITY TO CUTOUT, LAP SEAMS AND BUTT SPLICES. REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR DOUBLERS IAW ASA EA 5330-01766 AND AAR EA. 10304.
DURING D CHECK INSPECTION, BEAR STRAP HAS A HOLE BROKEN FROM EDGE (NO E/D) AT STA 767 AND STR 18R. REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR FILLER IAW ASA EA 5330-01764 AND AAR EA 10311.
DURING D CHECK INSPECTION EEC DOOR EXTERIOR SKIN HAS LIGHT CORROSION AND BARE METAL. REMOVED DAMAGED SKIN, FABRICATED AND INSTALLED REPLACEMENT SKIN IAW SRM 51-30-2 AND MFG DRAWING NR 65-45830.
DURING D CHECK INSPECTION FOUND STR 24R BENT BETWEEN STA 420 AND 440. REMOVED DAMMAGED SECTION OF STR 24R, FABRICATED AND INSTALLED REPAIR ANGLE IAW B737 SRM 53-10-3.
DURING D CHECK INSPECTION FOUND SKIN DOUBLER AT STA 1006 BETWEEN STR 11R AND 12R DOES NOT MEET SRM REQUIREMENTS. REMOVED SKIN DOUBLER, FABRICATED AND INSTALLED REPLACEMENT SKIN IAW B737 SRM 51-20-1.
DURING D CHECK INSPECTION FOUND DENT STA 400 BETWEEN STR 19L & 20L LESS THEN 3 INCHES FROM LAP RIVET AREA IS BEYOND LIMITS IAW SRM 53-30-1 FIG 1 DETAIL 3. REF SAD LOG 4465763 BEYOND LIMITS DUE TO CHANGE IN SRM WHICH INCLUDED PROXIMITY TO SEAM AND CUTOUT. REMOVED DAMAGE FABRICATED AND INSTALLED REPAIR FILLERS, DOUBLER AND TRIPLER IAW SRM 53-30-3.
DURING D CHECK INSPECTION FOUND HORIZONTAL WEB ABOVE APU BENT AT STA 1138. REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR DOUBLER IAW SRM 51-40-2.
DURING D CHECK INSPECTION FOUND GOUGES ON FORWARD SIDE OF FRAME STA 1104 BETWEEN 2ND AND 3RD STR UP FROM APU COMPARTMENT RT WEB. REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR DOUBLER IAW SRM 51-40-3.
DURING D CHECK INSPECTION FOUND STR 19R STA 360 - 440 HAS DAMAGE FROM EXISTING REPAIR (GOUGED). REMOVED DAMAGE STRINGER SECTION, FABRICATED AND INSTALLED REPLACEMENT STRINGER IAW SRM 51-30-5.
DURING D CHECK INSPECTION FOUND STINGER CLIP STA 495 STR 22R HAS A DAMAGED HOLE. REMOVED DAMAGED CLIP, FABRICATED AND INSTALLED REPLACEMENT CLIP IAW B737 SRM 51-31-5.
DURING D CHECK INSPECTION REQUESTED REMOVAL OF EXTERNAL DOUBLER FROM SKIN STA 970 TO 1016 LT STR 10L TO 14L. RE-EVALUTED SKIN FOR DAMAGE. REMOVED AND REPLACED SKIN IAW B737 SRM 51-30-2 STA 970 TO 1016 STR 10L TO 14L.
DURING D CHECK INSPECTION FOUND LT HORZ. STAB T/E I/B ATTACH FITTING HAS SMALL GOUGES. BLENDED AREA, REMOVED DAMAGE, FLAP PEENED, TREATED AND PRIMED IAW ASA EA 5510-01186 AND AAR EA 10289.
DURING D CHECK INSPECTION FOUND STR 20R BETWEEN STA 360 AND 400 HAS HOLES THAT ARE LARGER THAN SRM LIMITS. REMOVED DAMAGED STRINGER, FABRICATED AND INSTALLED REPLACEMENT STRINGER IAW B737 SRM 51-30-2.
DURING D CHECK INSPECTION FOUND E AND E COMPARTMENT LOWER LOBE INTERIOR HAS CORROSION IN STR 28L BETWEEN STA 316 AND 328. REMOVED DAMAGED STRINGER CHANNEL, ORDERED AND INSTALLED NEW STRINGER SECTION IAW MFG SRM 51-30-12. CPCP LEVEL 1 FINDING.
DURING D CHECK INSPECTION FOUND CRACKED SHEAR TIE AT STA 360 BETWEEN STR 14 & 15 RT. REMOVED DAMAGE, FABRICATED AND INSTALLED REPLACEMENT SHEAR TIE IAW B737 SRM 53-10-4.
DURING D CHECK INSPECTION FOUND AFT CARGO PIT STRINGER 21R HAC ELONGATED HOLE STA 927. REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR FILLER CHANNEL SRM 53-10-3.
DURING D CHECK INSPECTION FOUND ELONGATED HOLE IN SHEAR TIE AT STA 400 BETWEEN STR 14R AND 15R AT UPPER HOLE. REMOVED DAMAGE, FABRICATED AND INSTALLED REPLACEMENT SHEAR TIE AND REPAIR DOUBLER IAW SRM 53-10-4.
DURING D CHECK INSPECTION FOUND STRINGER TO FRAME CLIP CRACKED AT STA 495-500, STR 24R. REMOVED DAMAGED STRINGER CLIP, FABRICATED AND INSTALLED REPLACEMENT STRINGER CLIP IAW B737 SRM 51-20-1, 51-30-2.
DURING D CHECK INSPECTION FOUND AFT PIT STA 807 LOWER FORWARD CARGO CUTOUT HAS NON-CPCP CORROSION. REMOVED DAMAGE FABRICATED AND INSTALLED REPAIR DOUBLER IAW 53-10-1, 51-40-3 AND 51-30-2.
DURING D CHECK INSPECTION FOUND SHEAR TIE AT STA 380 BETWEEN STR 19R AND 20R HAS HOLES THAT ARE LARGER THEN SRM LIMITS. REMOVED DAMAGED SHEAR TIE, FABRICATED REPLACEMENT SHEAR TIE IAW SRM 53-10-4.
DURING D CHECK INSPECTION FOUND AT STA 747 SHEAR TIE CRACKED AT FASTNER HOLE BETWEEN STR 20L AND 21L. REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR SHEAR TIE IAW SRM 53-10-4.
DURING D CHECK INSPECTION FOUND AFT CARGO PIT STRINGER 20L HAS SEVERAL ELONGATED FASTNER HOLES AND MULTIPLE CRACK INDICATIONS AROUND HOLES STA 747 TO 887. REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR STRINGER AND SPLICES IAW SRM 53-10-3.
DURING D CHECK INSPECTION FOUND NON-CPCP CORROSION ON LOWER T-CHORD IN APU CAVITY RT BULKHEAD AT STA 1120-1130. REMOVED DAMAGED T-CHORD, ORDERED AND INSTALLED NEW T-CHORD IAW SRM 51-30-2.
DURING D CHECK INSPECTION FOUND CRACKED STRINGER CLIP AT STA 639, STR 4L. REMOVED DAMAGED CLIP, ORDERED AND INSTALLED NEW CLIP IAW B737 SRM 51-30-2
DURING D CHECK INSPECTION FOUND SHEAR TIE AT STA 380 BETWEEN STR 20R AND 21R HAS HOLES THAT ARE LARGER THEN SRM LIMITS. REMOVED DAMAGED SHEAR TIE, FABRICATED AND INSTALLED REPLACEMENT SHEAR TIE IAW B737 SRM 51-40-3.
DURING D CHECK INSPECTION FOUND CRACKED STRINGER CLIP AT STA 616, STA 4L. REMOVED DAMAGED CLIP, ORDERED AND INSTALLED NEW STRINGER CLIP IAW B737 SRM 51-30-2
DURING D CHECK INSPECTION FOUND CRACKED STRINGER CLIP AT STA 639, STR 4R. REMOVED DAMAGED CLIP, ORDERED AND INSTALLED NEW STRINGER CLIP IAW B737 SRM 51-30-2.
DURING D CHECK INSPECTION FOUND ELONGATED HOLE IN SHEAR TIE AT STA 500 BETWEEN STR 16R AND 17R, FORWARD UPPER HOLE. REMOVED DAMAGED SHEAR TIE. FABRICATED AND INSTALLED REPLACEMENT SHEAR TIE IAW B737 SRM 53-10-4.
DURING PREFLIGHT INSPECTION FORWARD SECTION OF FLOOR TRACK EMERGENCY LIGHTING AND EXIT SIGN AT L1 DOOR INOPERATIVE. CHANGED EMERGENCY BATTERY OVER L1 DOOR. SUSPECT MOISTURE IN THE LIGHT STRIP WAS A CONTRIBUTING, IF NO THE ROOT CAUSE OF THE PROBLEM.
DURING CRUISE FLIGHT AT 330 A BURNING ODOR WAS NOTED IN THE COCKPIT ONLY. ALL SYSTEMS CONTINUED TO FUNCTION NORMAL. PRECAUTIONARY LANDING AT FAI WAS MADE. UPON LANDING MAINTENANCE WAS UNABLE TO FIND THE SOURCE OF THE SMELL AND ALL OPERATIONS NORMAL. IT WAS DECIDED TO FERRY AIRCRAFT TO ANC FOR FURTHER INVESTIGATION. DURING FLIGHT TO ANC ODOR WAS NOTICE MOMENTARILY AND DISSIPATED. NO OTHER PROBLEMS NOTED. ANC MAINTENANCE WAS UNABLE TO CONFIRM SOURCE OF ODOR. PRECAUTIONARY REPLACEMENT OF NORMAL ELECTRICAL EQUIPMENT BLOWER AND ITS CIRCUIT BREAKER WAS ACCOMPLISHED. ON SUBSEQUENT FLIGHT NO PROBLEMS REPORTED.
DURING RON INSPECTION FOUND FUSELAGE CRACK APROXIMATELY 2 INCHES LONG AND TWO INCHES ABOVE FWD WING TO BODY FAIRING APROXIMATE STA 520, BETWEEN STRS 15 L AND 16L. INSTALLED REPAIR DOUBLER IAW B 737 SRM 53-30-3, FIG 48, DETAIL 10.
DURING CLIMB THE NR 2 MACH/AIRSPEED INDICATOR FAILED WITH FLAG PRESENT. RETURNED TO DEPARTURE AIRPORT. DURING APPROACH, JUST PRIOR TO TOUCH DOWN FLAG WENT AWAY AND INDICATOR BEGAN WORKING PROPERLY. REPLACED AIRSPEED/MACH INDICATOR. GROUND FUNCTION CHECKED OK.
DURING TEST OF FLOOR EGRESS LIGHTING SECTION BETWEEN ROWS 11 & 16 FOUND TO BE INOPERATIVE. REPLACED LEAD-IN CABLE. OPS CHECKED NORMAL.
DURING C CHECK INSPECTION FOUND NR 2 ENGINE OB TR ACTUATOR FAIRING PUNCTURED ABOVE THE LOWER AFT MOUNTING HOLE. REMOVED DAMAGE AREA, FABRICATED REPAIR PART AND INSTALLED PER SRM 54-30-1 AND 51-40-2. MINOR REPAIR
During C check inspection found # 2 engine OB cowl # 3 rib chaffed 13" from lower edge. Removed damage, fabricated parts and installed fabricated parts per SRM 54-10-2, 51-40-4, 51-10-2 and 51-30-2. Minor repair,
DURING C CHECK INSPECTION FOUND NR 1 ENGINE OB NACELLE FWD IB BREATHER CUT OUT IS CRACKED. REMOVED AND REPALCED BREATHER CUT OUT WITH NEW PART PER SRM 51-30-5, 51-10-2, 51-30-3 AND MM 51-21-17.
DURING C CHECK INSPECTION FOUND LOWER APU SHROUD CRACKED 3.5 INCHES AFT OF PREVIOUS REPAIRED AREA. REMOVED DAMAGED AREA, FABRICATED REPAIR DOUBLER & FILLER AND INSTALLED ON SHROUD PER EA 4910-01089 & 4910-01077. MONOR REPAIR
DURING C CHECK INSPECTION FOUND NR 1 ENGINE IB NACELLE NR 2 LATCH CUTOUT DAMAGED. REMOVED DAMAGE, FABRICATED REPAIR PARTS AND INSTALLED PER SRM 54-30-1, 51-40-2 & 51-10-2. MINOR REPAIR
DURING C CHECK INSPECTION FOUND NR 1 ENGINE IB FIXED FAIRING AFT UPPER LONGERON ANGLE BROKE. REMOVED DAMAGE, FABRICATED REPAIR PARTS AND INSTALLED PER SRM 54-10-1, 51-30-2 & 51-20-1. MINOR REPAIR.
DURING C CHECK INSPECTION FOUND NR 2 ENGINE IB NACELLE SKIN CRACKED BETWEEN NR 3 & 4 RIBS, 27 INCHES FROM LOWER EDGE. CUT OUT DAMAGE 1.3 X 1.5 INCHES, FABRICATED REPAIR DOUBLER, ALODINED & PRIMED PART AND INSTALLED REPAIR DOUBLER PER SRM 51-40-2, 51-10-3 & 54-30-1.
DURING C CHECK INSPECTION FOUND NR 2 ENGINE OB NACELLE NR 10 RIB CHAFED 8 INCHES FROM LOWER EDGE. CUT OUT DAMAGE 1 X 3 INCHES, FABRICATED REPAIR DOUBLER, ALODINED, PRIMED PART AND INSTALLED REPAIR DOUBLER PER SRM 51-40-3 AND 54-30-1. MINOR REPAIR.
DURING C CHECK INSPECTION FOUND NR 1 ENGINE SLIPPER FAIRING INBOARD AFT CORNER SKIN TORN. REMOVED DAMAGE AREA 1.1 X 0.8 INCH, FABRICATED REPAIR PARTS AND INSTALLED PER SRM 51-30-2, 51-10-2, 51-10-1, 51-40-2 AND 54-30-1. MINOR REPAIR.
DURING C CHECK INSPECTION FOUND LOWER AFT NR 2 PYLON WEB TORN AT AFT T/R HYDRAULIC LINE HOLE. REPAIRED WEB PER SRM 51-40-2. MINOR REPAIR
DURING C CHECK INSPECTION FOUND NUMBER ONE ENGINE O/B FIXED FAIRING AFT UPPER GUSSET GOUGED. REPAIRED #1 ENGINE O/B FIXED FAIRING AFT UPPER GUSSET PER SRM 54-10-1, 51-20-1 AND 51-30-2. MINOR REPAIR
DURING C CHECK INSPECTION FOUND MECHANICL DAMAGE ON FLOOR TO SIDEWALL SUPPERT AT BS 480 IN FWD CARGO BAY. REMOVED DAMAGED PART, DRILLED NEW PART, INSTALLED HARDWARE & INSTALLED PART PER SRM 51-30-2. MINOR REPAIR.
DURING C CHECK INSPECTION FOUND CORROSION ON UPPER FLANGE OF INTERCOSTAL AT STA 967, RBL20, CARGO FLOOR LEVEL. REMOVED INTERCOSTAL AND REPLACED WITH NEW PER SRM 53-10, 53-30-2, 51-10-2 AND 57-20-1. MINOR REPAIR. NOT A CPCP GENERATED FINDING.
DURING C CHECK INSPECTION FOUND NR 2 ENGINE I/B FIXED FAIRING MOST AFT I/B CHANNEL STIFFENER CRACKED. REPAIRED NR 2 ENGINE I/B FIXED FAIRING AFT I/B CHANNEL PER SRM 51-20-1 & 51-30-2. MINOR REPAIR.
DURING C CHECK INSPECTION FOUND NR 2 ENGINE IB NACELLE SKIN DENTED. REPAIRED NR 2 ENGINE IB NACELLE SKIN BY FABRICATING REPAIR PARTS FOR SKIN AND INSTALLING ON NACELLE AFTER REMOVING DAMAGE PER SRM 54-10-3. MINOR REPAIR.
DURING C CHECK INSPECTION FOUND NR 2 ENGINE O/B TAILPIPE COWLING DENTED 30 INCHES FROM FWD END AND 22 INCHES FROM BOTTOM. REMOVED & REPAIRED DENTED SECTION PER SRM 51-40-02 PG. 1-3 FIG. 1. MINOR REPAIR.
DURING C CHECK INSPECTION FOUND NR 1 TAIL PIPE FAIRING LOPWER CORNER DAMAGED. REPAIRED PER SRM 54-10-1. MONOR REPAIR.
DURING C CHECK INSPECTION FOUND NR 1 ENGINE TAIL PIPE FAIRING DAMAGED CORNER (LOWER) REPAIRED PER SRM 51-40-3. MINOR REPAIR.
DURING C CHECK INSPECTION FOUND CORROSION AT E & E BAY, RT SIDE OF DOOR CUTOUT ABOVE LATCH PLATE. REMOVED AND REPLACED WEB PER SRM 51-30-2, 53-10-1. MINOR REPAIR. FINDING NOT A CPCP ITEM.
DURING C CHECK INSPECTION FOUND FWD CARGO DOOR CUT OUT AFT FRAME CRACKED AT NR 5 STOP FITTING. RECEIVED, DRILLED AND INSTALLED FWD CARGO DOOR AFT FRAME REPAIR PARTS PER 51-40-03, FIG. 1, PARA. 1,2 & 3. MAJOR REPAIR
ON AN AIRCRAFT EQUIPED WITH A NOSE GEAR GRAVEL DEFLECTOR SKI THE NOSE GEAR FAILED TO GIVE A UP AND LOCKED INDICATION 9 RED NOSE GEAR LIGHT WOULD NOT GO OUT) UPON RETRACTION AFTER TAKE-OFF. RETURNED TO DEPARTURE AIRPORT WITHOUT INCIDENT. NOTE: THERE WAS HEAVY SNOW CONDITIONS AND THE SKI AREA WAS DE-ICED PRIOR TO TAXI. ACCOMPLISHED NOSE GEAR RETRACTION TEST AFTER REMOVING ICE FROM SKI. PS CHECKED GOOD PER WORK CARDS. NO PROBLEMS ON SUBSEQUENT FLIGHT.
ROW 16 RT AISLE EMERGENCY LIGHT INOP. REPLACED BATTERY PACK M1137. CKECKED GOOD. REF. 33-51-151.
"ANTI-ICE ENG 2 & WING VALVE CIRCUT BREAKER POPS WHEN ANTI-ICE IS TURNED ON". AIRCRAFT RETURNED TO DEPARTURE AIRPORT DUE TO WEATHER CONDITIONS AT DESTINATION AIRPORT. "T/S TO #2 ENGINE COWL VALVE. REPLACED SAME. REF MM 75-11-11. OPS & LEAK CHECK GOOD".
L2 EMERGENCY EXIT SIGN LIGHT DIM. REPLACED BOTH AFT EXIT SIGNS AND BATTERY PACK AT L2 DOOR. OPS CHECKED NORMAL.
AFT LT BULLNOSE EMERGENCY LIGHTS INOPERATIVE. REPLACED AFT OVERHEAD EMERGENCY LIGHTS BATTERY PACK. ALL OPS NORMAL. REF. 33-51-151
OVERHEAD BIN EMERGENCY LIGHTS ROW 9 (RT) AND LAST 3 LIGHTS ON LT SIDE OUT. RELAMPED AND ALL OPS NORMAL
DURING C CHECK INSPECTION FOUND FORWARD CARGO DOOR FORWARD LOWER FRAME CRACKED AT NR 4 FWD STOP FITTING.(COUNTING FROM TOP TO BOTTOM) REMOVED AND REPLACED FRAME PER ASA EM 5230-01097.
DURING C CHECK INSPECTION FOUND FORWARD CARGO DOOR NR 1 TRANSVERSE BEAM FROM BOTTOM O/B TEE CHORD CRACKED ON VERTICAL FLANGE AT AFT STOP PIN FITTING BETWEEN FASTNESRS. REPAIRED TEE CHORD PER ASA EM 5230-01097 STEP 6 C OF SECTION 2.
DURING C CHECK INSPECTION FOUND FRAME SHEAR TIE BS 380 BETWEEN STR 20 RT & STR 21 RT TO HAVE ELONGATED HOLES. REMOVED DAMAGE SECTION OF FRAME SHEAR TIE, FABRICATED NEW SECTION & INSTALLED I.A.W. SRM 53-10-4 FIG. 8.
DURING C CHECK INSPECTION FOUND CORROSION ON FLOORBEAM STA 344 LBL 2 TO RBL 10 WL 208. REPAIRED PER SRM 53-10-9 FIG. 6.
DURING C CHECK INSPECTION FOUND AT BS 967 RBL 29 W.L. 208 FASTNER HOLE IN FLOOR BEAM ELONGATED. CUT OUT FWD. FLANGE OF BS 967 UPPER FLOORBEAM CHORD AT RBL 29 AND RBL 43 IN A 1.2 X 3 INCH AREA. FABRICATED REPAIR ANGLES AND FILLERS AND INSTALLED REPAIR PER SRM 53-10-09 FIG. 7.
DURING C CHECK INSPECTION FOUND AFT CARGO DOOR NR 1 TRANSVERSE BEAM FROM BOTTOM O/B T-CHORD VERTICAL FLANGE CRACKED AT FWD STOP-PIN FITTING BETWEEN FIRST & SECOND FASTNER. REMOVED AFT CARGO DOOR TRANSVERSE BEM & INSTALLED REPLACEMENT BEAM.
DURING C CHECK INSPECTION FOUND DENT IN FUSELAGE SKIN AT B.S. 404 1 INCH ABOVE STRINGER 19R. TRIMMED OUT DAMAGE, INSTALLED REPAIR PER ER 02-0215 ASA EA 5330-01572
DURING C CHECK INSPECTION FOUND DENT IN FUSELAGE SKIN AT B.S. 898, 2 INCHES ABOVE STRINGER 24R. DENT FOUND TO BE OUT OF LIMITS. REMOVED DAMAGE IN A 4X8 INCH AREA. FABRICATED DOUBLER AND FILLER AND INSTALLED PER SRM 53-30-03 FIG. 6.
DURING C CHECK INSPECTION FOUND DENT IN FUSELAGE SKIN AT B.S. 910, 2 INCHES BELOW STRINGER 22R. REPAIRED DENT IN FUSELAGE SKIN AT B.S. 910 2" BELOW STRINGER I.A.W. SRM 53-30-03 PAGE 97.
DURING C CHECK INSPECTION FOUND FUSELAGE SKIN HAS SEVERAL DENTS FROM B.S. 847 TO 872 BETWEEN STR. 19R AND 20R. REMOVED DAMAGE 11 INCHES X 7 INCHES AT STA. 864 TO 874. FABRICATED REPAIR DOUBLE & FILLER, ALODINED & PRIMED AND INSTALLED PARTS PER SRM 53-30-2 FG 6 PG 11-12A AND SRM 51-10-02.
ON GRAVEL DEFLECTOR EQUIPED AIRCRAFT "NOSE GEAR RED LIGHT STAYED ON AFTER GEAR RETRACTION (GEAR SOUNDED LIKE IT DID NOT RETRACT COMPLETELY) RECYCLED GEAR SAME PROBLEM. RETURNED TO ANC LANDING WT. WAS 109.7. INSP. FOUND SLUSH IN GEAR AREA (NOSE) AND STRUT WAS A LITTLE LOW. CLEANED GEAR OF SLUSH AND RESET NOSE STRUT PRESS. LUBED NOSE GEAR CYCLED NOSE SEVERAL TIMES OPS CK GOOD.
ON GRAVEL DEFLECTOR EQUIPED AIRCRAFT "NOSE LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF - RETURNED TO AIRPORT".
ON GRAVEL DEFLECTOR EQUIPED AIRCRAFT "ON DEPARTURE FROM ANCHORAGE NOSE WHEEL WOULD NOT RETRACT CYCLED GEAR ONCE, NOSE WHEEL WOULD NOT RETRACT, RETURNED TO AIRPORT FOR OVERWEIGHT LANDING WAS SMOOTH AND NORMAL". AIRCRAFT PLACED ON JACKS AND GEAR TESTED NORMAL. AS PRECAUTION REPLACED NLG MODULAR PACKAGE, AND LUBED GEAR. GEAR AGAIN TESTED NORMAL.
ON GRAVEL DEFLECTOR EQUIPED AIRCRAFT NOSE GEAR WOULD NOT LOCK UP AFTER T/O. CYCLED GEAR WITH SAME RESULTS. NOSE GREEN LIGHT GOES OUT, BUT RED LIGHT STAYS ON WITH AIR NOISE HEARD. GEAR LOCKED DOWN OK. REMOVED AND REPLACED NOSE GEAR GRAVEL DEFLECTOR ACTUATOR PER MM 32-23-22. LUBED NOSE GEAR PER TASK CARD 18212000. OPS CK PER TASK 18132003. EMERGENCY EXTENSION CK GOOD. FOUND STRUT FLAT SERVICED PER A/C PLACARD.
L1 EXIT LIGHT AT BOTTOM RIGHT CORNER IS VERY DIM. REPLACED BATTERY PACK AND LIGHT/LENS, ALSO REPAIRED BROKEN WIRE AT CONNECTOR. PERFORMED OPS CHECK WITH NO AMBIENT LIGHT, BRIGHTNESS EQUAL TO OTHER EXIT SIGNS.
DURING CABIN PREFLIGHT FOUND EMERGENCY TRACK LIGHTS IN FORWARD CABIN INOP. FOUND WATER PUDDLE IN TRACK LIGHT CHANNEL. DRIED AREA. EMERGENCY EXIT LIGHTS OPS CHECKED NORMAL.