Page 1 of 25 A/C Registration: Performed date: Performed by: Time UTC: Stamp: ETOPS 48HRS CHECK as per Operator Maintenance Program Ref. JAF/MP/B767 Latest Revision. 1. Zones: CHECK ON-BOARD DOCS FOR OPEN ENTRIES AND REQUIRED CORRECTIVE ACTION(S), RECORD SERVICINGS PERFORMED, ENANCE FINDINGS AND/OR ACTIONS AND CHECK OUTSTANDING DEFERRED ITEMS. 1. Review AIRCRAFT TECHNICAL LOG and CABIN TECHNICAL LOG for reported discrepancies 2. Check ACCEPTABLE DEFERRED DEFECT SHEET and CABIN DEFERRED DEFECT SHEET 3. Check if there is one spare AIRCRAFT TECHNICAL LOG and on spare CABIN TECHNICAL LOG on board 2. VCK AMM 12-15-08-603-001 Zones: 211, 212 CREW OXYGEN DISPATCH PRESSURE (1) Check minimum dispatch pressure for crew oxygen cylinder (4 crew members) a) If the pressure is below the minimum pressure necessary to dispatch, do the crew oxygen servicing procedure (cylinder replacement method per AMM 12-15-08-603-001) CAUTION: To prevent the airplane dispatch with a partially open valve make sure the shut off valve is closed (clockwise) one quarter turn after fully opening the shut off valve. NOTE: By making sure the shut off valve is turned closed (clockwise) one quarter turn will prevent damage to the shut off valve.
3. OPC MP 26-015-00-01 AMM 26-10-00-716-019 Zones: 212 OPERATIONALLY CHECK AFOLTS (AUTOMATIC FIRE/OVERHEAT LOGIC TEST SYSTEM) WITH ENG/APU/CARGO TEST SWITCH (1) Push and hold the ENG/APU/CARGO switch, on the aft pilots control stand, P8. Make sure these indications occur: a) The fire bell is heard. b) The red master WARNING lights on the glareshield panel, P7, come on. c) The discrete FIRE warning light, on the captains instrument panel, P1-3, comes on. d) The LEFT, RIGHT, and APU fire switch handle lights (P8) come on. e) The FWD and AFT CARGO FIRE switchlights (P8) come on. f) The L and R fuel control switchlights, on the quadrant stand, P10, come on. g) The yellow L and R ENG OVHT lights (P8) come on. h) These EICAS messages show on the top display: 1) L and R ENGINE FIRE 2) L and R ENG OVHT 3) APU FIRE 4) FWD and AFT CARGO FIRE (2) Release the test switch and make sure the above indications stop. Page 2 of 25 4. OPC MP 24-010-02-01 AMM 24-33-00-206-244 Zones: 212 OPERATIONALLY CHECK THE STANDBY POWER SYSTEM (1) Make sure the BAT switch on the standby power control panel (P5) is in the ON position. (2) Make sure the STANDBY PWR switch on the standby power control panel (P5) is in the AUTO position. (3) Turn the STBY POWER switch on the P5 panel to the BAT position. (4) Make sure the yellow DISCH light on the standby power control panel (P5) comes on. (5) Make sure the yellow STBY BUS OFF light next to the STBY POWER switch on the standby power control panel (P5) is off. (6) Turn the STBY POWER switch on the standby power control panel (P5) to the AUTO position. (7) Make sure the yellow DISCH light on the standby power control panel (P5) goes off. (8) Make sure the yellow STBY BUS OFF light next to the STBY POWER switch on the standby power control panel (P5) is off. 5. OPC MP 26-021-02-01 AMM 26-21-04-736-001 Zones: 212 TEST ENG, APU CARGO AND EMER ESCAPE SQUIBS ON TEST CONTROL PANEL Do a test of the Squib Test Panel (1) Push the indicator lights on the SQUIB-TEST panel (P61) to do a test of the bulbs. (2) Push the TEST 1 switch on the SQUIB TEST panel. (3) Make sure all of the indicator lights on the panel come on (green). (4) Release the TEST 1 switch and make sure the indicator lights go off. (5) Push the TEST 2 switch on the SQUIB TEST panel. (6) Make sure all of the indicator lights on the panel, but not the APU light, come on (green). (7) Release the TEST 2 switch. (8) Make sure the indicator lights go off.
6. OPC Zones: 200 OPERATIONALLY CHECK THE INTERIOR EMERGENCY LIGHT ETOPS 48 HRS CHECK Page 3 of 25 Do the steps which follow for each attendant's test switch: (1) At the attendant's panel, set the test switch for the emergency lights to the on position. (2) Make sure the emergency lights in the passenger compartment come on, and then go off automatically after approximately one minute. Note: AIRPLANES WITH AN ELECTROLUMINESCENT FLOOR PROXIMITY LIGHTING SYSTEM; The floor proximity lighting system will stay off in this test. 7. OPC MP 31-007-00-01 AMM 31-41-00-912-001 Zones: 212 PERFORM A READOUT OF ALL EICAS ENANCE MESSAGES BY PRESSING THE ECS/MSG DISPLAY SWITCH (1) Make sure that the EICAS circuit breakers are closed. (2) Do the steps that follow to show all the EICAS maintenance messages: a) Push the ECS/MSG switch on the EICAS panel on the right side panel, P61, to show the ECS MSG page and the first page of maintenance messages. b) If PAGE 1 shows, push the ECS MSG switch again. c) Continue to push the ECS MSG switch as necessary to see all the additional pages. d) After all of the pages of messages show, the ECS MSG page will show without the message list. Push the ECS MSG switch again to go back to the secondary engine page. (3) Do the steps that follow to show all the EICAS EPCS messages: a) Push the EPCS switch to show the EPCS page and the first page of EPCS messages. b) If PAGE 1 shows, push the EPCS switch again. c) Continue to push the EPCS switch as necessary to see all the additional pages. d) After all of the pages of messages show, the EPCS page will show without the message list. Push the EPCS switch again to go back to the secondary engine page. Note: Additional data on the EPCS is included in AMM 77-35-00. 8. OPC AMM 34-45-00 Zones: 211, 212 PERFORM A TCAS SYSTEM SELF TEST (1) Put the TCAS/ATC control panel mode switch at the test position to start a self-test. (2) If there is a failure during the BITE test; A failure LED indicator will come on the front panel of the TCAS computer. The EFIS displays show an indication of the system status.
9. FNC Zones: FUNCTIONAL TEST OF FLIGHT DECK DOOR SECURITY LOCK ETOPS 48 HRS CHECK Page 4 of 25 (1) With the Flight deck door open, set Flight Deck Access System (FDAS) switch, on the door chime module to NORM, ensure keypad red LED is on. (2) Key in 123ENT, on the keypad, and ensure that a continuous tone is heard, red keypad LED goes out and amber LED illuminates. (3) Ensure AUTO-UNLK light on the P5 panel is on. (4) Select DENY on the P5 panel and release, ensure AUTO-UNLK light goes off, and that the amber LED on the keypad goes off, and the red LED comes on. (5) Enter flight deck, close the door, ensure it cannot be pushed open, ensure that no further tones are heard for one minute. (6) Select UNLCKED ensure a click is heard from the door solenoid, release the door switch. (7) Rotate door handle and open the door, key in 123ENT and ensure that the following sequence occurs: a continuous tone is heard for 30 seconds with flashing AUTO-UNLK light. After tone, ensure door solenoid energizes for 5 seconds and green keypad LED is on. After 5 seconds green LED goes out and solenoid relaxes. (8) Set Chime module FDAS switch to off, ensure lock fail light (P5) comes on. 10. GVI MP 25-006-00-01 Zones: 200 INSPECT TOILET COMPARTMENTS Inspect toilet compartments: Items Inspection Requirements All Waste Receptacles Check no damage or distortion & correctly stowed. All waste receptacle enclosure access doors & disposal doors & all selfclosing entry flaps. Check for proper operation, correct spring and sealing, correct fitment & latching, for containment of possible fire. Check for wear & condition. Check sealing strips for security & condition. Check all debris removed & receptacle is clean. Ashtrays inside & outside compartment. Check ashtrays are fitted & secured. Placards NO SMOKING NO CIGARETTE DISPOSAL Check placards are fitted to each side of each lavatory door. Check placards for clarity & security. Toilet floor covering. Check for security, condition & no spillage. Fire extinguisher bottle. Check Eutectic solder intact, security of attachment. Check fire extinguisher temp indicator intact.
Page 5 of 25 11. GVI JC/EO/4296-1 Zones: 200 CHECK FOLLOWING EMERGENCY EQUIPMENT FOR PRESENCE AND PROPER CONDITION IAW SAFETY EQUIPMENT CHECKLIST ON BOARD Note: Safety Equipment Checklists are located in the stowage units below cabin attendant seats. (1) Check all portable oxygen bottles and masks for presence, security, condition and pressure. (2) Check all portable fire extinguisher bottles for presence, security, condition and pressure. (3) Check all smoke hoods for presence, security, condition, integrity of tamper seal and status of serviceability indicator (vacuum seal) in window. Note: If tamper seal is missing, inspect for serviceability and re-apply seal PN E28297-00. (4) Check Forward, Center and Aft First Aid Kits for presence, security, condition, due date and seal. (Replace First Aid Kit when: Due date is expired, Seal number does not match Placard, Placard or Seal is missing or Red Seal is installed) (5) Check Medical Kit for presence, security, condition, due date and seal. (Replace Medical Kit when: Due date is expired, Seal number does not match Placard, Placard or Seal is missing, Red Seal is installed or Padlock is missing) (6) Check megaphones for presence, security and condition. (7) Check dangerous goods kit for presence, condition and seal (Replace dangerous goods kit when tamper seal is missing/broken) (8) Check AED Kit (PN JAF-FR3 only) a. Check condition of the green ready light through the inspection window (bracket should not be opened) b. Replace the unit i.a.w. JC/EO/4296-1 if: i. The green light is not flashing ii. Or the AED is making a chirping noise 12. GVI EASA STC 10014411 TEO/767/1462 CMM 25-23-55 Zones: 200 INSPECTION OF SEATS, COVERS, ATTACHMENTS AND BASIC FUNCTIONS (1) Visually examine the general condition of the seats and seat covers (2) Check the seat track fittings for secure attachment to the floor tracks (3) Check the condition of life vest pouches and bottom cushions (4) Ensure that recline controls operate correctly (5) Check in-arm foodtray tables for damage, correct operation, and trash accumulation (6) Check back-mounted foodtray tables for damage and correct operation (7) Check IFE and electrical components for proper operation (8) Check foodtray latches for damage and correct operation.
13. VCK Zones: 211, 212 COCKPIT SWITCHES LOCKWIRE INSPECTION ETOPS 48 HRS CHECK Page 6 of 25 (1) Check if the following switch guards in the cockpit are lockwired with lockwire PN MS20995CY20. a) Both IDG disconnect switches. b) PASS OXYGEN switch. (2) If not verify Technical logbook for any related pilot entry. If no entry is found, apply a lockwire in accordance with SWPM 20-60-07. No other switch should be lockwired, remove if necessary. 14. Zones: 100, 200, 300, 400, 500, 600, 700 EXTERIOR INSPECTION Items at each location may be checked in any sequence. Use the detailed inspection route to check that: The surfaces and structures are clear, not damaged, no missing parts and there are no fluid leaks The tires are not too worn, not damaged, and there is no tread separation The gear struts are not fully compressed The engine inlets and tailpipes are clear, the access panels are secured, the exterior is not damaged, and the reversers are stowed The doors and access panels that are not in use are latched The probes, vents, and static ports are clear and not damaged The skin area adjacent to the pitot probes and static ports is not wrinkled The antennas are not damaged The light lenses are clean and not damaged 15. VCK MP 52-414-00-01 AMM 52-05-03-212-807 Zones: 100, 200 LEFT FORWARD FUSELAGE (1) Visually inspect (from ground level) for missing or damaged navigation/communication antennas. (2) Visually inspect for obvious damage: Static ports Total Air Temperature probe Angle of Attack sensor (3) Visually inspect the fuselage in areas of drain masts and drains for fluid leakage (4) Check doors and access panels (not in use) are closed and secured (5) General visual inspection of the FWD and MID entry door.
16. VCK Zones: 100, 200 NOSE ETOPS 48 HRS CHECK Page 7 of 25 (1) Visually inspect (from ground level) for missing or damaged navigation/communication antennas. (2) Check radome and radome diverter strips (3) Check forward access door is closed and secured (4) Check E/E access door is closed and secured 17. GVI MP 32-029-00-02 AMM 32-45-04-216-001-003 MP 32-029-02-01 AMM 12-15-03-613-006 MP 32-030-00-01 AMM 32-45-03-216-001 Zones: 710 NOSE WHEEL WELL (1) Visually inspect the nose landing gear tires and wheels for obvious damage (Figure 1) (2) Check and record NLDG Tires pressure on the ETOPS 48 HRS recap sheet CAUTION: TIRE PRESSURE MUST BE CHECKED WITH CALIBRATED GAGE AND CORRECTED WHENEVER POSSIBLE WHEN TIRES ARE COLD. SERVICE WITH NITROGEN ONLY (AD 87-08-09) NOSE ACTION REQUEST 187 TO 192 PSI N.O.R. (Normal Operating Range) 178 TO 186 PSI Inflate to max of N.O.R. 168 TO 178 PSI Inflate to max of N.O.R. Do check again after 24 hours, if the pressure falls, replace wheel and create defect report. 149 TO 168 PSI Replace the wheel and adjacent wheel. (3) Check Nose Gear strut and doors (4) Check Nose wheel steering assembly (5) Check exterior lights Taxi lights Left and Right Nose Gear Landing Lights (6) Nose gear steering lockout pin As needed (7) Gear pin..as needed (8) Nose wheel spin brake (snubbers)..in place (9) Wheel well light switches As needed 18. VCK MP 25-035-01-01 AMM 25-52-00-206-001 MP 52-414-00-01 AMM 52-05-03-212-807 Zones: 100, 200 RIGHT FORWARD FUSELAGE (1) Visually inspect (from ground level) for missing or damaged navigation/communication antennas. (2) Visually inspect for obvious damage: Static ports Pitot static probes Angle of Attack sensor
(3) Visually inspect the crew discharge indicator disc for presence ETOPS 48 HRS CHECK (4) Visually inspect the fuselage in areas of drain masts and drains for fluid leakage (5) Visually check the FWD cargo compartment linings to verify integrity of compartment sealing (6) Visually inspect the condition of the FWD cargo door seal and seal depressor (7) Check doors and access panels (not in use) are closed and secured (8) General visual inspection of the FWD and MID galley service door. (9) Check negative pressure relief doors are closed. 19. VCK Zones: 100, 600 RIGHT WING ROOT, PACK AND LOWER FUSELAGE Page 8 of 25 (1) Check Probes, sensors, ports, vents, for obvious damage and drains for fluid leakage (as applicable) (2) Check exterior lights Lower body anti-collision light Wing illumination lights Wing landing light Runway Turnoff light (3) Visually inspect the RH pack ram air inlet and exhaust door for no obstructions (4) Check that the pack access doors are closed and secured (5) Check the leading edge slats (6) Check that the fuel tank measuring sticks are flush and secured 20. GVI MP 79-309-01-02 AMM 12-13-01-613-001-002 MP 24-001-02-02 AMM 12-13-03-213-046 Zones: 420 RIGHT ENGINE (1) Check the Engine Oil Tank for presence of Fuel WARNING: Before you open the Engine Oil Tank filler cap, permit a minimum of five minutes after the engine shutdown to let the pressure in the oil tank bleed off. Make sure that you do not smell fuel fumes when you open the oil filler cap. (2) Service engine oil tank to top level (through sight level glass 26 Quarts) and indicate amount added in the ATL. NOTE: Fill the engine oil tank in less than 30 minutes after the engine shutdown to get correct oil quantity indication. (3) Calculate oil consumption per AMM TASK 71-00-00-862-020-H03 Paragraph I and take corrective actions as required. (4) Check IDG Scavenge Filter Pressure Differential Indicator. Make sure the red button does not extend from the DPI leakages. (5) Visually inspect the engine cowlings for obvious damage, open blow out doors, open latches and sings of fluid leakages. (6) Visually inspect the inlet cowl, fan rotor spinner, engine inlet probes and the fan rotor blades for obvious damage. (7) Visually inspect the turbine exhaust sleeve, the exhaust tail plug, exhaust case strut and the visible turbine blades for obvious damage and evidence of metal/oil accumulation. (8) Check that the thrust reverser is in the stowed position. (9) Check that engine and pylon access panels are closed and secured.
21. VCK Zones: 600 RIGHT WING AND LEADING EDGE ETOPS 48 HRS CHECK Page 9 of 25 (1) Visually inspect the lower wing surfaces from ground level for obvious damage and fuel leakage (2) Check that access panels are closed and secured (3) Check the leading edge slats (4) Check the fuel tank vent (5) Check that the fuel tank measuring sticks are flush and secured 22. GVI MP 27-052-01-01 AMM 27-05-03-202-805 Zones: 600 RIGHT WING TIP AND TRAILING EDGE (1) Visually inspect the wing tip from ground level for obvious damage and fuel leakage (2) Check visible portion of right wing flight control surfaces, from ground level, for obvious damage. (3) Check exterior lights: Upper body anti-collision light Forward and rear position light Right wing anti-collision light (4) Check the static discharge wicks (5) Check fuel jettison nozzle 23. GVI MP 32-024-00-05 AMM 32-41-08-216-001-003 MP 32-029-00-02 AMM 32-45-04-216-001-003 MP 32-029-02-01 AMM 12-15-03-613-006 MP 32-030-00-01 AMM 32-45-03-216-001 Zones: 740 RIGHT MAIN GEAR AND WHEEL WELL (1) Visually inspect the RH main landing gear tires and wheels for obvious damage. (Figure 1) (2) Check and record RH MLDG Tires pressure on the ETOPS 48 HRS recap sheet CAUTION: TIRE PRESSURE MUST BE CHECKED WITH CALIBRATED GAGE AND CORRECTED WHENEVER POSSIBLE WHEN TIRES ARE COLD. SERVICE WITH NITROGEN ONLY (AD 87-08-09) MAIN GEAR ACTION REQUEST 200 TO 205 PSI N.O.R. (Normal Operating Range) 190 TO 199 PSI Inflate to max of N.O.R. 180 TO 190PSI Inflate to max of N.O.R. Do check again after 24 hours, if the pressure falls, replace wheel and create defect report. 160 TO 180 PSI Replace the wheel and adjacent wheel. (3) Verify that wheel chocks are in place as needed. (4) Check each brake wear indicator (Figure 2 and 3) If the parking brake is set, the brake wear indicator pins must extend out of the guides. (5) Check gear strut, actuators, and doors.
(6) Check that the LDG Hydraulic lines are secured. (7) Gear pins.as needed (8) Check RH MLDG Wheel Well with Wheel well doors closed. ETOPS 48 HRS CHECK 24. VCK MP 25-035-01-01 AMM 25-52-00-206-001 MP 52-414-00-01 AMM 52-05-03-212-807 Zones: 100, 200 RIGHT AFT FUSELAGE Page 10 of 25 (1) Check the Ram Air Turbine door (2) Check that doors and access panels (not in use) are closed and secured (3) Check probes, sensors, ports, vents, for obvious damage and drains for fluid leakages (as applicable) (4) Visually check the AFT cargo compartment linings to verify integrity of compartment sealing (5) Visually inspect the condition of the AFT cargo door seal and seal depressor (6) Check that the negative pressure relief doors are closed (7) General visual inspection of the AFT galley service door. (8) Visually inspect (from ground level) for missing or damaged navigation/communication antennas 25. SVC MP 49-021-00-01 AMM 12-13-04-613-001 Zones: 211, 212, 315, 316 CHECK APU OIL AND SERVICE TO FULL LEVEL AS REQUIRED Fill the APU Oil: (1) Make sure the APU control switch is in the OFF position and attach a DO-NOT-OPERATE tag. (2) Open the left access door, 315AL and RH access door, 316AR. (3) If the oil level is below the FULL MARK, fill the APU oil. Use a calibrated beaker. Indicate amount added on the ETOPS 48 HRS recap sheet. (4) Calculate oil consumption per AMM 49-11-00-802-001 and take corrective actions as required. (5) Close the left access door, 315AL and RH access door, 316AR. (6) Remove the DO-NOT-OPERATE tag in the cockpit.
26. VCK MP 32-040-00-01 AMM 12-15-05-203-022 Zones: 300 TAIL Page 11 of 25 (1) Visually inspect from ground level for obvious damage: a) Vertical fin and rudder b) Horizontal stabilizer and elevator (2) Verify that the tail skid is not damaged (3) Visually check the tail skid shock strut pop-up indicator (4) Check the static discharge wicks (5) Check the APU exhaust outlet. 27. VCK MP 25-035-01-01 AMM 25-52-00-206-001 MP 52-414-00-01 AMM 52-05-03-212-807 Zones: 100, 200 LEFT AFT FUSELAGE (1) Visually inspect the cabin pressure outflow valve to ensure there are no obstructions (2) Visually check the bulk cargo compartment linings to verify integrity of compartment sealing. (3) Visually inspect the condition of the bulk cargo door seal and seal depressor. (4) Check that doors and access panels (not in use) are closed and secured (5) Check probes, sensors, ports, vents, for obvious damage and drains for fluid leakages (as applicable) (6) General visual inspection of the AFT entry door. (7) Visually inspect (from ground level) for missing or damaged navigation/communication antennas. 28. GVI MP 32-024-00-02 AMM 32-41-08-216-001-003 MP 32-029-00-02 AMM 32-45-04-216-001-003 MP 32-029-02-01 AMM 12-15-03-613-006 MP 32-030-00-01 AMM 32-45-03-216-001 Zones: 730 LEFT MAIN GEAR AND WHEEL WELL (1) Visually inspect the LH main landing gear tires and wheels for obvious damage. (Figure 1) (2) Check and record LH MLDG Tires pressure on the ETOPS 48 HRS recap sheet CAUTION: TIRE PRESSURE MUST BE CHECKED WITH CALIBRATED GAGE AND CORRECTED WHENEVER POSSIBLE WHEN TIRES ARE COLD. SERVICE WITH NITROGEN ONLY (AD 87-08-09) MAIN GEAR ACTION REQUEST 200 TO 205 PSI N.O.R. (Normal Operating Range) 190 TO 199 PSI Inflate to max of N.O.R. 180 TO 190PSI Inflate to max of N.O.R. Do check again after 24 hours, if the pressure falls, replace wheel and create defect report. 160 TO 180 PSI Replace the wheel and adjacent wheel. (3) Verify that wheel chocks are in place as needed. (4) Check each brake wear indicator (Figure 2 and 3) If the parking brake is set, the brake wear indicator pins must extend out of the guides.
(5) Check gear strut, actuators, and doors. (6) Check that the LDG Hydraulic lines are secured. (7) Gear pins.as needed (8) Check LH MLDG Wheel Well with Wheel well doors closed. ETOPS 48 HRS CHECK Page 12 of 25 29. GVI MP 27-052-01-01 AMM 27-05-03-202-805 Zones: 500 LEFT WING TIP AND TRAILING EDGE (1) Visually inspect the wing tip from ground level for obvious damage and fuel leakage (2) Check visible portion of left wing flight control surfaces, from ground level, for obvious damage. (3) Check exterior lights: Forward and rear position light Left wing anti-collision light (4) Check the static discharge wicks (5) Check fuel jettison nozzle 30. VCK Zones: 500 LEFT WING AND LEADING EDGE (1) Visually inspect the lower wing surfaces from ground level for obvious damage and fuel leakage (2) Check that access panels are closed and secured (3) Check that the fuelling station door is secured. (4) Check the leading edge slats (5) Check the fuel tank vent (6) Check that the fuel tank measuring sticks are flush and secured 31. GVI MP 24-001-02-01 AMM 12-13-01-613-001-002 MP 79-309-01-01 Zones: 410 LEFT ENGINE (1) Check the Engine Oil Tank for presence of Fuel WARNING: Before you open the Engine Oil Tank filler cap, permit a minimum of five minutes after the engine shutdown to let the pressure in the oil tank bleed off. Make sure that you do not smell fuel fumes when you open the oil filler cap. (2) Service engine oil tank to top level (through sight level glass 26 Quarts) and indicate amount added in the ATL. NOTE: Fill the engine oil tank in less than 30 minutes after the engine shutdown to get correct oil quantity indication. (3) Calculate oil consumption per AMM TASK 71-00-00-862-020-H03 Paragraph I and take corrective actions as required. (4) Check IDG Scavenge Filter Pressure Differential Indicator. Make sure the red button does not extend from the DPI leakages. (5) Visually inspect the engine cowlings for obvious damage, open blow out doors, open latches and sings of fluid leakages. (6) Visually inspect the inlet cowl, fan rotor spinner, engine inlet probes and the fan rotor blades for obvious damage. (7) Visually inspect the turbine exhaust sleeve, the exhaust tail plug, exhaust case strut and the visible turbine blades for obvious damage and evidence of metal/oil accumulation. (8) Check that the thrust reverser is in the stowed position. (9) Check that engine and pylon access panels are closed and secured.
32. VCK Zones: 100, 500 LEFT WING ROOT, PACK AND LOWER FUSELAGE ETOPS 48 HRS CHECK Page 13 of 25 (1) Check probes, sensors, ports, vents, for obvious damage and drains for fluid leakages (as applicable) (2) Check exterior lights: Wing illumination light Wing landing light Runway Turnoff light (3) Visually inspect the LH pack ram air inlet and exhaust door for no obstructions. (4) Check that the pack access doors are closed and secured (5) Check that the negative pressure relief door is closed (6) Check the leading edge slats (7) Check that the fuel tank measuring sticks are flush and secured (8) Visually inspect the positive pressure relief valves for (flag) indication that valves have opened. 33. SVC AMM 12-14-01-683-008-001 Zones: DRAIN THE POTABLE WATER SYSTEM WHEN AMBIENT TEMPERATURE FORECAST IS BELOW FREEZING CONDITION DURING NIGHT LAYOVER. WARNING: IF THE POTABLE WATER SYSTEM IS NOT DRAINED OR IN NORMAL SERVICE A MINIMUM OF ONE TIME EACH THREE DAYS, THE GROWTH OF BACTERIA CAN OCCUR. IF BACTERIA GROWTH CONTINUES, AND YOU DRINK THE WATER, ILLNESS CAN OCCUR. (1) Make sure the shutoff valves for the lavatories and galleys are open. (2) Open the doors for the potable water service panel and for the potable water drain panel. (3) Connect a drain line to each water drain connection. (4) Move the handles for the WATER SYSTEM DRAIN VALVES to OPEN (one on each panel). (5) Move the handle for the WATER TANK FILL VALVE to the OPEN POSITION. This will open the WATER TANK FILL VALVE. (6) When all the water has drained from the potable water system move the handle for the WATER TANK FILL VALVE to the CLOSED position. (7) Move the two handles for the WATER SYSTEM DRAIN VALVES to CLOSED. (8) Disconnect the drain lines from the water drain connections. (9) Close the doors for the potable water service panel and the forward potable water drain panel (10) Open these circuit breakers and attach DO-NOT-CLOSE tags: Number Name Panel 11U28 POT WATER PRESS P11 33H6 WATER SYS AIR CPRSR P33 34P10 WATER QTY/PRESS P34 36D6 or 36D7 or 36E7 WTR HTR LAV SYS 1 P36 37H7 or 37E7 WTR HTR LAV SYS 2 P37 (11) Make an maintenance entry in technical log: Potable water to be replenished prior to a/c departure
Task Related Documents Item 34. GVI STG M40-10 14.B.3 Rev P or later Zones: 200 GENERAL VISUAL INSPECTION AND SERVICING OF THE PHOTOLUMINSCENT ESCAPE PATH MARKING SYSTEM Page 14 of 25
35. OPC 28-AWL-ENG AD: 2015-21-09 Zones: 200 ENGINE FUEL SHUTOFF VALVE (FUEL SPAR VALVE) POSITION INDICATION OPERATIONAL CHECK. Page 15 of 25 Concern: The fuel spar valve actuator design can result in airplanes operating with a failed fuel spar valve actuator that is not reported. A latently failed fuel spar valve actuator could prevent fuel shutoff to an engine. In the event of certain engine fires, the potential exists for an engine fire to be uncontrollable. NOTE: In case aircraft is dispatched per MEL 28-40-02 perform option 2 Option 1: Operational check without engine operation. 1. Supply electrical power to the airplane using standard practices. 2. Make sure all fuel pump switches on the Overhead Panel are in the OFF position. 3. If the auxiliary power unit (APU) is running, open and collar the L FWD FUEL BOOST PUMP (C00372) circuit breaker on the Main Power Distribution Panel. 4. Make sure LEFT and RIGHT ENG FIRE switches on the Aft Aisle Stand are in the NORMAL (IN) position. 5. Make sure L and R ENG START Selector Switches on the Overhead Panel, are in the OFF position. 6. Do an operational check of the left engine fuel spar valve actuator. a. Move L FUEL CONTROL switch on the quadrant control stand to the RUN position and wait approximately 10 seconds. NOTE: It is normal under this test condition for the ENG VALVE disagreement light on the quadrant control stand to stay illuminated. b. Move L FUEL CONTROL switch on the quadrant control stand to the CUTOFF position. c. Verify the left SPAR VALVE disagreement light on the quadrant control stand illuminates and then goes off. d. If the test fails (light fails to illuminate), before further flight, repair faults as required (refer to Boeing AMM 28-22-11). 7. Do an operational check of the right engine fuel spar valve actuator. a. Move R FUEL CONTROL switch on the quadrant control stand to the RUN position and wait approximately 10 seconds once the FUEL CONTROL switch is in the RUN position. NOTE: It is normal under this test condition for the ENG VALVE disagreement light on the quadrant control stand to stay illuminated. b. Move R FUEL CONTROL switch on the quadrant control stand to the CUTOFF position. c. Verify the right SPAR VALVE disagreement light on the quadrant control stand illuminates and then goes off. d. If the test fails (light fails to illuminate), before further flight, repair faults as required (refer to Boeing AMM 28-22-11). 8. If the L FWD FUEL BOOST PUMP circuit breaker was collared in step 3, remove collar and close.
Page 16 of 25 Option2: Perform an inspection of the fuel spar valve actuator position. NOTE: This inspection may be most useful whenever the SPAR VALVE light does not function properly. 1. Make sure the L FUEL CONTROL switch on the quadrant control stand is in the CUTOFF position. NOTE: It is not necessary to cycle the FUEL CONTROL switch to do this inspection. 2. Inspect the left engine fuel spar valve actuator located in the left rear spar. NOTE: The Fuel Spar Valve actuators are located behind main gear doors on the rear spar. a. Verify the manual override handle on the engine fuel spar valve actuator is in the CLOSED position. b. Repair or replace any fuel spar valve actuator that is not in the CLOSED position (refer to Boeing AMM 28-22-11). 3. Make sure the R FUEL CONTROL switch on the quadrant control stand is in the CUTOFF position. NOTE: It is not necessary to cycle the FUEL CONTROL switch to do this inspection. 4. Inspect the right engine fuel spar valve actuator located in the right rear spar. NOTE: The Fuel Spar Valve actuators are located behind main gear doors on the rear spar. a. Verify the manual override handle on the engine fuel spar valve actuator is in the CLOSED position. b. Repair or replace any fuel spar valve actuator that is not in the CLOSED position (refer to Boeing AMM 28-22-11).
Page 17 of 25 Figure 1 Damage/Wear Conditions (Sheet 1 of 7)
Page 18 of 25 Figure 1 Damage/Wear Conditions (Sheet 2 of 7)
Page 19 of 25 Figure 1 Damage/Wear Conditions (Sheet 3 of 7)
Page 20 of 25 Figure 1 Damage/Wear Conditions (Sheet 4 of 7)
Page 21 of 25 Figure 1 Damage/Wear Conditions (Sheet 5 of 7)
Page 22 of 25 Figure 1 Damage/Wear Conditions (Sheet 6 of 7)
Page 23 of 25 Figure 1 Damage/Wear Conditions (Sheet 7 of 7 )
Page 24 of 25 Figure 2 Brake Wear Check and Brake inspection
Page 25 of 25 Figure 3 Brake inspection