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B767 LINE MAINTENANCE FORMS MANUAL

1. 10 24 03 PAGE 2 OF 2 B767 DAILY EICAS NON NORMAL FAULT MESSAGE RETRIEVAL FORM AIRCRAFT STATION LOG PAGE NUMBER DATE mm dd yyyy m my ACCOMPLISHED DUE TO TIME _ NO STATUS OR MAINT MESSAGES 1 EICAS MESSAGE EICAS MESSAGE BITE INFO CODE S CLEARED LEVEL Record EXACT Message As Displayed AFTER RESET Circle A B C S or M Circle YES or SYSTEM BITE INFO CODE S 2 EICAS MESSAGE EICAS MESSAGE BITE INFO CODE S CLEARED LEVEL Record EXACT Message As Displayed AFTER RESET Circle A B C S or M Circle YES or NO SYSTEM BITE INFO CODE S 3 EICAS MESSAGE EICAS MESSAGE BITE INFO CODE S CLEARED LEVEL Record EXACT Message As Displayed AFTER RESET Circle B 5 or Circle YES SYSTEM BITE INFO CODE S EICAS MESSAGE EICAS MESSAGE BITE INFO CODE S CLEARED LEVEL Record EXACT Message As Displayed AFTER RESET Circle A B C S or M Circle YES or NO SYSTEM BITE INFO CODE S ADDITIONAL INFORMATION COMPLETED BY NAME PRINT EMPLOYEE FAX COMPLETED PAGE 2 ONLY TO ABX MAINT CONTROL 937 383 1919 ae BX AIR CARD NO B767 90 PAGE 1 of 6 B767 ETOPS PREDEPARTURE CHECK DATE 11 29 19 NOTE This check B767 90 is accomplished prior to each scheduled ETOPS departure in addition to the B767 1A B card which is
2. AIRCRAFT NO DATE Mechanic s Job Description Initials AUXILIARY POWER UNIT APU 59 59 Perform a general visual inspection of the APU compartment internal 60 60 Service APU oil to maximum limits with turbo oil 2380 Record OIL ADDED QUARTS in aircraft log book If no oil was added enter zero 0 CARD NO 767 9 BX AIR PAGE 1 of 6 B767 LIGHTNING STRIKE CHECKLIST DATE 10 06 06 Aircraft No Station Log Page No Work Order No Date 1 Complete the Lightning Strike Checklist in the following situations A If the flight crew reports a lightning strike B If reports indicate that the aircraft may have experienced heavy static discharge while passing through an electrical storm region Evidence of lightning strike discovered by Maintenance personnel 2 Check the listed items areas for damage before aircraft is released for service NOTE Items that do not apply may be signed off as not applicable N A ITEM ACCOMP NO DESCRIPTION BY 1 Examine the Zone 1 Figure 1 surface areas for signs of a lightning strike A Examine the internal and external surfaces of the nose radome Look at the honeycomb sandwich structure for burns punctures and pin holes 1 Examine the internal external radome Look for pin holes punctures and paint that has chipped per M M 05 51 19 2 2 Examine the radome bon
3. PAGE 30 of 55 B767 SERVICE CHECK DESCRIPTION EF I DATE 12 06 10 NO 2 ENGINE AND PYLON CF6 80A SERIES 1 Check to see if there is contamination on the scavenge filter element in the filter in the filter bowl or in the oil drained from the filter cavity NOTE Contamination is defined as bright metal deposits which can be defined as chunks or pieces caused breakage in contrast to non metallic flakes slivers caused by normal wear moderate number of scattered small metallic flakes bronze or silver colored metal or flakes of generator insulation are normal products of wear during operation Even a considerable number of non metallic items such as black epoxy chips sleeving and other forms of generator insulation does not always indicate damage to the IDG 2 Check to see if the O rings or the filter is damaged This would allow contaminated oil to bypass the filter and enter the external oil cooling circuit d If no contamination is found and no condition is observed that would allow oil to bypass the filter do the following NOTE When the filter DPI has activated for the fourth time replace the IDG Ref AMM 24 11 01 1 Verify there are no IDG related EICAS or BPCU BITE messages If the EICAS or BITE messages are present take necessary corrective action If message was caused by the IDG replace the IDG Ref AMM 24 11 01 2 Reset the filter DPI e If contamination is foun
4. Interior Light L313 L1 Door Ovhd Light Interior Light L9201 L1 Door Exit Sign Interior Light L950 Cockpit Door Exit Sign Interior Light SF and BDSF Aircraft L388 L1 Door L H Grd Illum Exterior Light L312 L1 Threshold Exit Sign Interior Light L313 L1 Door Ovhd Light Interior Light L393 R1 Door R H Grd Illum Exterior Light L287 Threshold Exit Sign Interior Light L288 Door Ovhd Light Interior Light L950 Cockpit Door Exit Sign Interior Light BCSF Aircraft L1343 L1 Door L H Grd Illum Exterior Light L312 L1 Door Threshold Exit Sign Interior Light L313 L1 Door Ovhd Light Interior Light L1342 Entryway Ovhd Light Interior Light L1270 Cockpit Ovhd Light LH Interior Light L1271 Cockpit Ovhd Light RH Interior Light NOTE minute maximum to prevent depleting emergency battery pack voltage 3 Turn emergency light switch to OFF Verify the interior and exterior emergency lights extinguish and overhead panel UNARMED light is ON 6 Perform a general visual inspection of flight compartment including windows for general condition cleanliness and sec
5. ae BX AIR CARD NO B767 2B PAGE 2 of 12 REV NO 82 B767 SERVICE CHECK SIGN OFF RECORD DATE 12 06 10 AIRCRAFT NO STATION LOG PAGE NO WORK ORDER NO DATE Mechanic s Job Description Initials ABBREVIATED SERVICE CHECK NOTE Unserviceable emergency equipment must be replaced before flight 1 1 If the aircraft has sat statically the main engines have not been operated and less than 72 hours have elapsed since the last full Service Check perform the 72 hour reduced service check and N A the remainder of Service Check If the aircraft has moved the main engines have been operated or 72 hours have elapsed since the last full Service Check N A this step and accomplish remainder of Service Check In either case document accomplishment of Abbreviated Service Check or Full Service Check with a log book entry ae BX AIR CARD NO B767 2B PAGE 3 of 12 REV NO 82 B767 SERVICE CHECK SIGN OFF RECORD DATE 12 06 10 AIRCRAFT NO STATION LOG PAGE NO WORK ORDER NO DATE Mechanic s Job Description Initials FLIGHT COMPARTMENT NOTE Unserviceable emergency equipment must be replaced before flight Perform an EICAS maintenance message read out and record in Aircraft Logbook Operationally check the Takeoff Configuration Warning Alert N315AA Only Check LT CTR and RT hydraulic f
6. BX AIR B767 LINE MAINTENANCE FORMS MANUAL ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 82 DATED 12 06 10 B767 2A B767 2B Service Check Description and Signoff Record revised to incorporate QAR maintenance requirements add requirements of AD 2010 23 03 and delete references to 312AA per MPRR 38615 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 81 DATED 11 29 10 B767 90 Pages 4 6 added Figures 1 2 and 3 regarding engine oil servicing per MPRR 38632 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 80 DATED 11 17 10 B767 14 Page 4 Item 1 A 4 deleted for JT9 engines or 54 10 00 for CF6 engines per MPRR 38613 Page 4 Item 1 A 4 a deleted for CF6 engines or FIM 71A 05 00 for JT9 engines per MPRR 38613 Deleted Item 4 Disposition of Remains per MPRR 38613 Page 4 revised Records Mail Code to 2061 MPRR 38613 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 79 DATED 11 04 10 B767 90 Page 1 Note added or the B767 2A B Service Check when scheduled MPRR 38604 Page 2 Job Description Engines revised Item 4 and Item 5 to incorporate PW4000 requirements per MPRR 38604 Page 2 Job Description Engi
7. REV NO 78 B767 DAILY CHECK DESCRIPTION DATE 1028 10 AIRCRAFT GENERAL 7 Check brakes for wear evidence of leakage and damage A Prepare for the inspection 1 Ensure the downlocks are installed on the nose and main landing gear AMM 32 00 20 2 Ensure that chocks are installed on the wheels 3 Release the parking brake B Procedure CAUTION BE VERY CAREFUL WHEN YOU DO A CHECK OF THE BRAKES TO NOT SPILL HYDRAULIC BRAKE FLUID ON THE BRAKE LININGS IF YOU SPILL BRAKE FLUID ON THE BRAKE LININGS THE BRAKES WILL NOT OPERATE CORRECTLY 1 Pressurize the right hydraulic system and reservoir AMM 29 11 00 201 2 Fully apply and release the left and right Captain s or First Officer s brake pedals five times 3 With the brake pedals not applied do a check of the brakes for fluid leaks at these locations a Brake pistons b Brake housing plugs c Inlet and drain ports d Bleed ports e All hydraulic line connections 4 If the total leakage per brake at the above locations is greater than one 1 drop per minute with the brake pedals not applied repair the leaks or replace the brake prior to dispatch 5 Slowly apply the brake pedals to the stops 6 While the brake pedals are applied do a check for leaks at the same places on the brake that you did in Step 3 7 If the total leakage per brake at the above locations is greater than five 5 drops per minute while the brakes
8. R Right computer COMPUTER BRT BAT AUTO O BAL VENT L R a Qe Displays secondary eng parameters on the lower CRT Depress a second time to clear the lower CRT of any display Displays flight control SPI brake temp hydraulic qty APU RPM amp EGT and crew O2 pressure along with minimum equipment list related status messages This page wil be displayed on the lower CRT only increases or decreases display EICAS MESSAGES FIGURE 2 Selects EICAS computer upper and lower displays provide source but right automatically if left fails THRUST REF Sy Bal knob varies the intensity of the color display in relation to the format white background BRT brightness for entire Manual set knob for derated N1 reference cursor L both R knob selects cursor to be moved Center knob causes reference temp to increase or decrease thus causing N1 cursor to move around N1 indicator R MAX INO ores RESET PULL Erases overspeed or overtemp value displayed beneath digital readout on respective EICAS eng indicator Cannot erase any data from a MTC TP003702 lt N gt en 7 z lt O 42 of 55 PAGE 82 12 06 10 REV NO DATE DESCRIPTION B767 SERVICE CHECK e9w passaidap SI YOWMS pue si wayed ueu
9. Check oxygen masks 6 each for PC2SF BCSF and BDSF 4 each for SF for presence condition and security 1 Make sure the oxygen masks are not damaged and are clean protected and stored properly NOTE Ensure oxygen mask and smoke goggles are manufactured by EROS Do not intermix manufactures G Check smoke goggles 6 each for PC2SF BCSF and BDSF 4 each for SF for presence condition and security 1 Make sure the goggles are not damaged and are clean protected and stored properly H Check Fire Ax for presence and security Check condition security and inspection due date of Protective Breathing Equipment Assembly Ensure red Visual Service Indicator VSI is NOT protruding beyond face of mounting box and tamper seal s are intact Record hydrostatic due dates on form B767 2B NOTE Not all PBE s have a blue pink humidity indicator but if installed near handle of pouch blue color indicates serviceable PBE pink color indicates need for replacement within 36 hours of discovery Notify Maintenance Control if humidity indicator is pink but PBE is not replaced 1 Check the new style PBE with humidity indicators as follows a If red VSI protrudes beyond face of mounting box or green tamper seal s are broken place hand in box and feel pouch DO NOT remove pouch from box If pouch is soft and spongy replace PBE assembly within 36 hours Notify Maintenance Control and generate a Deferred Item to have
10. MPRR 36166 Page 6 Item 6 E added and PC2SF per MPRR 36166 Page 6 Item 6 F added and PC2SF per MPRR 36166 Page 6 Item 6 1 added and PC2SF per MPRR 36166 Page 11 revised section title from Supernumerary Compartment SF Mod Only to Supernumerary Compartment SF Crew Service Area PC2SF per MPRR 36166 Page 11 Item 12 added crew service and added PC2SF MPRR 36166 Page 11 Item 14 added service per MPRR 36166 Page 11 Item 14 D revised Life vest 4 ea to Life vest 4 ea SF 1 ea PC2SF per MPRR 36166 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL Page 11 Item 14 E 1 deleted located above supernumerary seats MPRR 36166 Page 11 Item 14 G added if installed MPRR 36166 Page 12 Item 23 added and PC2SF MPRR 36166 Page 13 Item 26 added PC Only per MPRR 36166 Page 13 Item 26 A 2 added other per MPRR 36166 Page 13 deleted Item 26 A 3 Installed on aft face of aft lavatory wall on SF aircraft MPRR 36166 Page 14 Item 30 added PC2SF MPRR 36166 Page 53 revised Figure 13 Sheet 1 of 2 Cockpit Equipment PC and PC2SF Configured Aircraft per MPRR 36166 B767 2B Page 3 revised title from Supernumerary Compartment SF Mod Only to Supernumerary Compartment SF Crew Ser
11. PW 4000 SERIES FAILURE TO DEACTIVATE THRUST REVERSER ISOLATION VALVE FOR GROUND MAINTENANCE COULD RESULT IN INADVERTENT THRUST REVERSER OPERATION WITH POSSIBLE INJURY TO PERSONNEL AND DAMAGE TO EQUIPMENT WARNING Check to see if the IDG is disconnected Correct the DISCONNECT TRIP message if necessary Ref AMM 24 20 00 Service IDG as follows Ref Fig 9 1 If IDG is being serviced due to oil loss during system maintenance drain IDG case M M 12 13 03 IDG Oil Drain Procedure and then continue servicing at step D 3 2 If IDG is being serviced for any other reason continue servicing at step D 3 3 Remove dust cover from overflow drain coupling on IDG 4 Put a container below the IDG to catch the which will flow from the IDG 5 Place end of oil drain hose into a container to catch oil WHEN CONNECTING HOSE TO OVERFLOW DRAIN COUPLING USE RAG AROUND FITTING TO PREVENT SPLASH DUE TO PRESSURE BUILDUP IN IDG CASE HOT OIL CAN CAUSE INJURY TO PERSONNEL CHECK THAT IDG OIL DRAIN HOSE IS NOT SUBMERGED IN OIL IN CONTAINER IS NOT BENT OR KINKED SO AS TO INHIBIT DRAINAGE AND IS LOWER THAN IDG AT ALL POINTS FREE DRAINAGE DEPENDS ON AIR GETTING BACK TO IDG CASE THROUGH DRAIN HOSE FAILURE TO OBTAIN PROPER DRAINAGE CAN RESULT IN AN OVER FILLED CONDITION AND CAUSE DAMAGE TO IDG USE THE CORRECT ADAPTER TO RELEASE THE PRESSURE FROM THE IDG AN INCORRECT ADAPTER WILL NOT RELEASE THE PRESSURE IN THE IDG THIS CAN CA
12. the IDG do the following a Mark the next sequential number on the DPI RESET placard located on the IDG housing b Record in the A C Logbook the DPI reset number marked in step E 1 a c Do check for the following conditions AMM 24 11 02 1 Check to see if there is contamination on the scavenge filter element in the filter in the filter bowl or in the oil drained from the filter cavity NOTE Contamination is defined as bright metal deposits which can be defined as chunks or pieces caused by breakage in contrast to non metallic flakes or slivers caused by normal wear A moderate number of scattered small metallic flakes bronze or silver colored metal or flakes of generator insulation are normal products of wear during operation Even a considerable number of non metallic items such as black epoxy chips sleeving and other forms of generator insulation does not always indicate damage to the IDG 2 Check to see if the O rings or the filter is damaged This would allow contaminated oil to bypass the filter and enter the external oil cooling circuit d If no contamination is found and no condition is observed that would allow oil to bypass the filter do the following NOTE When the filter DPI has activated for the fourth time replace the IDG Ref AMM 24 11 01 1 Verify there are no IDG related EICAS or BPCU BITE messages If the EICAS or BITE messages are present take necessary corrective action If message was cause
13. 3 If an external light shows damage from a lightning strike examine the internal wires of the light fixture Also look at those wires that go from the light to the circuit breaker 4 Ensure the navigation lamps rotary lights and the landing lights operate 5 Do the following examinations of the flight controls If the rudder shows signs of a lightning strike examine the surface hinges bearings and bondings for signs of damage B Ifthe elevators show signs of a lightning strike examine the surface hinges bearings and bondings for signs of damage C Ifthe ailerons show signs of a lightning strike examine the surface hinges bearings and bondings for signs of damage 6 Do an operational test of the rudder if there are signs of lightning strike damage Ref 27 21 00 a CARD NO B767 9 BX AIP 3 PAGE 3 of 6 B767 LIGHTNING STRIKE CHECKLIST DATE 10 06 06 ITEM ACCOMP NO DESCRIPTION BY 7 Do an operational test of the elevator if there are signs of lightning strike damage Ref 27 31 00 8 Do an operational test of the ailerons if there are signs of lightning strike damage Ref 27 11 00 9 If the wingtips show signs of a lightning strike examine the wingtips carefully Also look carefully at the fuel vent outlet for signs of damage 10 Examine the static dischargers A Visually examine all dischargers to ensure they are there and installed correctly on the moun
14. Check No 2 engine IDG oil level and filter pop out indicators CAUTION DO NOT SERVICE IDG IF IDG IS DISCONNECTED REFER TO FIM 24 20 00 FAULT ISOLATION AND CORRECT DISCONNECT TRIP BITE MESSAGE CAUTION DO NOT REMOVE OIL DRAIN HOSE FROM OVERFLOW DRAIN COUPLING UNTIL DRAINAGE SUBSIDES TO A SLOW DRIPPING CONDITION FAILURE TO DRAIN THE IDG PROPERLY WILL RESULT IN AN OVERFILLED CONDITION AND CAUSE DAMAGE TO THE IDG ae BX AIR CARD NO B767 2B PAGE 10 of 12 B767 SERVICE CHECK SIGN OFF RECORD REV NO 82 DATE 12 06 10 AIRCRAFT NO DATE Mechanic s Initials Job Description NO 1 ENGINE AND PYLON PW4000 SERIES 53 53 54 54 WARNING Perform a general visual inspection walk around check of the No 1 engine Check engine cowling engine inlet fan rotor spinner fan rotor blades pylons open blow out doors open latches visible turbine blades and exhaust area for obvious damage and fluid leaks Service oil at No 1 engine with 2380 engine oil Check the No 1 and No 2 engine oil levels using EICAS and service with Turbo Oil 2380 if required An EICAS indication of Left 24 3 Right 21 3 is full and oil servicing is not required If next flight segment is ETOPS oil tank level must be visually checked Record OIL ADDED QUARTS in aircraft log book If no oil was added enter zero 0 WAIT A M
15. to Record OIL ADDED QUARTS in aircraft log book per MPRR 31923 Page 8 Item 56 deleted Oil added in quarts Eng 1 IDG MPRR 31923 Page 9 Item 58 revised Oil added quarts Eng 2 _ to Record OIL ADDED QUARTS in aircraft log book per MPRR 31923 Page 9 Item 59 deleted Oil added in quarts Eng 2 IDG MPRR 31923 Page 10 Item 61 revised Oil added in quarts Eng 1 to Record OIL ADDED QUARTS in aircraft log book per MPRR 31923 Page 10 Item 62 deleted Oil added in quarts Eng 1 __ per MPRR 31923 Page 11 Item 64 revised Oil added in quarts Eng 2 _ to Record OIL ADDED QUARTS in aircraft log book per MPRR 31923 Page 11 Igem 65 deleted Oil added in quarts Eng 32 per MPRR 31923 Page 12 Item 67 revised Oil added in quarts APU to Record OIL ADDED QUARTS in aircraft log book per MPRR 31923 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 69 DATED 09 23 09 B767 2A Page 9 deleted Item 9 C 1 d Airport Analysis Book no longer carried onboard per MPRR 36475 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 68 DATED 09 15 09 B767 1A Page 7 Item 10 deleted first Note If an excessive amount of oil is used per MPRR 36469 Page 7 added new Item 10 D regar
16. EMERG iRcuLT TEMP SPEED DATA og DOOR RLY SENSOR SOL SENSOR SENSOR SENSOR SENSOR SWITCH CONTROL VALVE EGT 1 tef f IGV TGN DIV SOL CONTROL STARTER CIRCUIT SENSOR SENSOR Eeu VALVE SWCGEN MANUAL CURRENT SHUTDOWN LRU STATUS FAULTY RAKE T C RAKE UNIT UNIT LOW FAULTY LRU CONTROL STARTER CIRCUIT P ECU FAN FILTER SENSOR VALVE SWITCH SPARE SPARE WALT DISPLAY Q RECORD SELECTED ERASE H MEMORY REASON P E L ERASE T Li APU CONTROL UNIT FRONT PANEL APU CONTROL UNIT Or FRONT PANEL AIRPLANES WITH gt 18 APU CONTROL UNIT AIRPLANES WITH 2 19 THRU 999 APU CONTROL UNIT TP006238 APU BITE PROCEDURES FIGURE 11 ae BX AIR CARD NO B767 2A PAGE 51 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 approx 18 0 TAPE 5 0 typ B767 COCKPIT DOOR VIEW LOOKING FORWARD NOTES Aluminum tape is applied to the cockpit doors to give the flight crew location fo apply security tags 1 Warm surface be taped amp tape to above 50 F 2 Clean area where tape is to be applied with a general purpose cleaner Wipe dry 3 Apply aluminum tape at locations shown 4 Cut amp smooth down tape loc
17. EXTINGUISHER VIEW LOOKING OUTBOARD VIEW LOOKING OUTBOARD TP006480 FLIGHT DECK EMERGENCY EQUIPMENT SF CONFIGURED AIRCRAFT FIGURE 13 SHEET 2 OF 3 ae BX AIR CARD NO B767 2A PAGE 54 of 55 B767 SERVICE CHECK DESCRIPTION 82 DATE 12 06 10 CINTERIOR LAVATORY WALL CEXTERIOR LAVATORY WALL OBSERVERS OXYGEN MASK REGULA TOR ACCESSORY PANEL FIRST OFFICERS OXYGEN MASK REGULA TOR RIGHT SIDEWALL CAPTAINS Ta MASK REGULA TOR LEFT SIDEWALL CO AT EACH CREW STATION SUPERNUMERARY OXYGEN MASK 3 PLACES OVERHEAD CONSOLE SUPERNUMERARY LIFE VESTS 3 PLACES UNDER SEAT SAFETY HARNESSES 2 BELOW EACH SEAT INSIDE LIFE RAFTS LIFE RAFT STOWAGE COMPARTMENT 007093 EMERGENCY EQUIPMENT BCSF AND BDSF CONFIGURED AIRCRAFT FIGURE 13 SHEET 3 OF 3 ae BX AIR CARD NO B767 2A PAGE 55 of 55 B767 SERVICE CHECK DESCRIPTION REV NO 82 DATE 12 06 10 OUTER CYLINDER CREF INNER CYLINDER RETRACTABLE TAIL SKID MAINTENANCE LOCK BOLTS WASHERS 2 LOCATIONS LOW PRESSURE POP UP INDICATOR SHOCK STRUT ACTUATOR CEXTENDED POSITION PUSHED IN POSITION NORMAL EXTENDED POSITION CSERVICING REQUIRED LOW PRESSURE POP UP INDICATOR TP007106 TAIL SKID STRUT ACTUATOR PRESSURIZATION FIGURE 14 ae BX AIR CARD N
18. Engine Oil Tank Filler Cap Sight Glass Scupper Drain Relief Valve CF6 80A SERIES ENGINES TP003705 ENGINE OIL SERVICING FIGURE 5 ae BX AIR CARD NO B767 2A PAGE 45 of 55 REV NO 8 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 DISCONNECT RESET RING INTEGRATED DRIVE GENERATOR VALVE OIL RETURN FROM EXTERNAL OIL CIRCUIT OIL SUPPLY TO S NY EXTERNAL OIL fi CIRCUIT OVERFLOW DRAIN COUPLING PRESSURE FILL O RINGS COUPLING INTEGRATED DRIVE GENERATOR TP003706 CF6 80A SERIES ENGINES IDG OIL SERVICING FIGURE 6 ae BX AIR CARD NO B767 2A PAGE 46 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 ENGINE OIL ACCESS DOOR OIL TANK SIGHT GAGE ENGINE OIL SCUPPER l 1 1 ENGINE OIL TG TANK ENGINES PRE PW SB 79 65 P ENGINES POST PW SB 79 65 EEA PW4000 ENGINE OIL SERVICING FIGURE 7 ae BX AIR CARD NO B767 2A PAGE 47 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 SCUPPER N DRAIN FILLER SCUPPER LEVEL BRAIN 1 LINE FULL FILL LEVEL MAXIMUM FILL LEVEL ON ENGINES TP007103 PW4000 ENGINE OIL SERVICING FIGURE 8 CARD NO B767 2A BX AIR 48 of 55 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 QIL RETURN FRO
19. J Check the positive pressure relief valves for FLAG indication that valves have opened K Check RAM air inlet exhaust doors for obstructions L Check fuselage exterior skin doors and door seals as viewed from the ground for condition and obvious damage M Check tail skid indicator for evidence of tail strike and low pressure pop out indicator is not extended Ref Figure 14 300 only N Raise flaps and slats and remove hydraulic system pressure 39 Check operation and illumination of exterior lights DO NOT LOOK AT STROBE LIGHTS AND ANTI COLLISION LIGHTS FOR A LONG TIME THESE LIGHTS CAN CAUSE INJURIES TO YOUR EYES A Check the following exterior lights and replace all bulbs not illuminated 1 Fwd and aft position navigation lights 2 Strobe lights 3 Anti collision lights upper lower and wing body 4 Wing position lights 5 Wing flood lights 6 Landing and taxi lights 7 Runway turnoff lights 8 NLG and MLG wheel well lights and gear inspection lights ae BX AIR CARD NO B767 2A PAGE 20 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 AIRCRAFT GENERAL 40 Check all tires and wheels for wear cuts obvious damage or broken tie bolts NOTE wheels removed for low pressure should be returned to ABX Air Wheel and Tire Shop ILN Please note the following information on the parts tag Tire removed due to LOW PRESSURE and actual tire
20. filler caps have been opened two separate ETOPS mechanics must service engine oil Also see GMM 04 44 Par 5 for alternate flight crew procedure Check here if alternate flight crew procedure is used 12 13 01 Job Description APU Mechanic s AMM Initials Check APU oil level for full via sight gage Add oil as necessary to service to full 12 13 04 Ensure EICAS APU OIL QTY message is not displayed Record oil added quarts in aircraft log book If no oil was added enter zero 0 ae BX AIR CARD NO B767 90 PAGE 3 of 6 B767 ETOPS PREDEPARTURE CHECK DATE 11 29 10 Job Description Mechanic s LOGBOOK Initials 1 Complete Airworthiness Release entry for ETOPS PDSC Inspection XXXX 2 Ensure ETOPS Reporting Form binder and ETOPS APU Reporting Form XXXX onboard the aircraft 3 Contact Maintenance Control to confirm Aircraft ETOPS Significant Systems XXXX status Ref GMM 04 44 Par 6 and overall maintenance history Ensure ETOPS Status placard reflects any current downgraded conditions or need for verification flight as determined by Maintenance Control ETOPS PRE DEPARTURE SERVICE CHECK COMPLETE signoff blocks of the check have been accomplished action taken where necessary and initialed properly Fax all signoff sheets to Maintenance Control ILN Ensure ETOPS PDSC Inspection has been ent
21. make a logbook entry with expiration date place on Deferred Item and notify Maintenance Control Life raft 2 ea if installed D Life vest 4 ea SF 1 ea PC and PC2SF and demonstration life vest 1 ea E Emergency descent device for presence condition and security 1 There is 1 ea inertia reel assembly 2 Check 6 ea inertia reel harnesses for presence condition and security Portable oxygen bottle 1 ea SF and PC2SF G Verify MEC safety barrier 1 ea is located on the upper galley shelf SF and PC2SF ae BX AIR CARD NO B767 2A PAGE 16 of 55 B767 SERVICE CHECK DESCRIPTION REV NO 82 DATE 12 06 10 UPPER CARGO COMPARTMENT 20 Check sidewall lining ceiling panels and lights for condition and security 21 Clean and vacuum compartment 22 Check cabin floor and seat tracks for cleanliness and condition clean as required A Ensure floor is clean and free of debris B Ensure seat tracks are clean and free of debris Check anti slip tape for condition 23 Check internal markings for condition legibility 24 Compartment lighting A On the forward attendant s panel P21 push the MN DK CARGO light switch and the CABIN ENTRY light switch to the on position B Make sure all the cargo compartment lights come on 25 Perform a general visual inspection of the cargo net for security SF and PC2SF only 26 Weight and Balance Comput
22. 1 Check for presence and condition 2 Check compass card is filled out properly and is legible 12 Inspect aluminum tape on cargo compartment side of the cockpit door for condition and security N A to BCSF and BDSF NOTE X Aluminum tape is used as a surface to place the red cockpit security tag A If necessary clean surface of tape with a mild cleaner Ref Figure 12 Security Tag Locator Cockpit Door Ref AMM 11 35 02 13 Test engine APU cargo squibs on squib test control panel A Push the indicator lights on the SQUIB TEST panel P61 to do a test of the bulbs B Push the TEST 1 switch on the SQUIB TEST panel Ensure all of the indicator lights the panel come on green NOTE L amp R Emergency Escape Lights have been deactivated D Release the TEST 1 switch 1 Ensure the indicator lights go off ae BX AIR CARD NO B767 2A PAGE 13 of 55 B767 SERVICE CHECK DESCRIPTION REV NO 82 DATE 12 06 10 14 FLIGHT COMPARTMENT E Push the TEST 2 switch on the SQUIB TEST panel APU Fire Bottles 1 Airplanes with single APU Fire Bottle a Ensure all of the indicator lights on the panel but not the APU light come on green 2 Airplanes with dual APU Fire Bottles a Ensure all of the indicator lights on the panel come on green G Release the TEST 2 switch H Ensure the indicator lights go off Test the FUEL CONFIG Light and the LOW FUEL Message NOTE Re
23. 14 Item 26 B 6 a revised from Program version is 4 164 2007 405 or later to Program version is 4 222 2007 1011 or later per MPRR 34102 Page 14 added new Item 26 B 9 After 10 minutes of operation check battery condition for increase in of charge renumbered subsequent item per MPRR 33883 Page 14 added new Item 26 B 9 Note Batteries that will not charge above 50 should be replaced per MPRR 33883 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL Page 18 Item 44 added except 84227 XX configuration per MPRR 33084 Page 18 Item 44 added Note For easy identification 84227 XX configurations have ball mats installed per MPRR 33084 Page 23 deleted Item 54 Check center hydraulic system ADP Air Driven Pump oil level and delta pop up indicator and sub items moved to B767 3A as new Item 72 renumbered subsequent items per MPRR 33695 B767 2B Page 2 Item 7 revised applicable for Saturday maintenance visits only to applicable for Saturday or Sunday once per week maintenance visits only per MPRR 31834 Page 2 Item 8 revised applicable for Saturday maintenance visits only to applicable for Saturday or Sunday once per week maintenance visits only per MPRR 31834 Page 6 Item 44 added except 84227 XX configuration per MPRR 33084 Page 7 deleted Item 54 Check center hydr
24. A C Logbook Ref Figures 1 2 and 3 NOTE Ensure all prerequisites are met in step A NOTE Figures 1 2 and 3 contain additional information to aid the mechanic in troubleshooting NOTE If EICAS maintenance level messages are not recorded as soon as the aircraft is released to maintenance it is possible to set EICAS maintenance level messages in the course of other maintenance performed on the aircraft The technician should determine if messages are generated by other maintenance and not record them in the log book Recording maintenance generated messages could cause unnecessary follow up work If the validity of the message cannot be determined enter the information in the log book and not if the message cleared after EICAS erase procedure NOTE Required by CMR 31 41 00 2A at 100 HR intervals accomplished at each Service Check Accomplish a read out of EICAS maintenance messages PREREQUISITES Standby Power Selector AUTO Battery Switch LATCHED External APU Power All Three IRUS ALIGNED WITH PRESENT POSITION SAM Modules in MEC CLEAR FAULT BALLS Yaw Damper Modules in MEC CLEAR FAULT BALLS Parking Brake eei SET 1 On the EICAS maintenance panel P 61 press the ECS MSG Select switch Maintenance messages will be displayed in white lettering on th
25. B767 LINE MAINTENANCE FORMS MANUAL REVISION 60 DATED 08 29 08 B767 1A Page 1 added new Item 1 C Note M 1A entry required for all O2 bottle servicing M 1A entry to include O2 bottle pressure before and after servicing per MPRR 35134 Page 2 revised Item 4 regarding portable oxygen bottles per MPRR 33876 B767 1B Page 2 added new Item 1 C Note M 1A entry required for all O2 bottle servicing M 1A entry to include O2 bottle pressure before and after servicing per MPRR 35134 Page 3 Item 4 deleted 2 ea per MPRR 33876 B767 2A Page 1 added new Item Note M 1A entry required for all O2 bottle servicing M 1A entry to include O2 bottle pressure before and after servicing per MPRR 35134 Page 4 Item 5 C revised to read Check spare bulb supply and presence of the thrust reverser isolation valve deactivation pins 2 ea P N B78001 3 replenish as necessary per MPRR 34311 Page 5 added new Item 6 A Note M 1A entry required for all O2 bottle servicing M 1A entry to include O2 bottle pressure before and after servicing per MPRR 35134 Page 10 deleted Item 12 TCAS Self Test and sub items renumbered subsequent items per MPRR 34267 Page 13 revised Item 26 regarding portable oxygen bottles per MPRR 33876 Page 14 added Item 32 A Note 714AX only has four 4 volumes per MPRR 34271 Page 55 revised Figure 13 Sheet 1 of 2 Cockpit Equipment PC Con
26. S3 Max Normal Switch setting from D to B 4 Change the S5 Max Cold Switch setting from to B 5 Change the S8 Duct Press Switch setting from E to B 6 Ensure that all ECS Switches are set to the revised Airborne Express settings AIRBORNE EXPRESS SETTINGS UE S2 MES us xad Pd Norm Down Cold TR Press T Reinstall the ECS switch cover 8 Make Log Book entry that Form B767 50 was completed to change the ECU ECS Switch settings from the Factory settings to the revised Airborne Express settings 767 50 Page 2 of 2 DATE 02 11 04 NOTE REMOVE ACCESS PANEL COVER 5 CAPTIVE SCREWS TO SET SWITCHES 1 8 A 9 D E B C p C p m 53 5 57 51 PART OF RS s o aS p E 7 yt B 82 54 56 58 TP003875 Test Set and ECU Controls Af B767 51 Page 1 of 2 BX AIR DATE 05 06 03 B767 APU ECU FUNCTION ADJUSTMENT SWITCHES SETTINGS ECU REMOVED FROM THE AIRCRAFT This form provides instructions to change the ECS Switch settings on the B767 APU ECU from the revised Airborne Express settings to the original factory settings This form is to be accom plished when an ECU is removed from the aircraft REMOVED ECU 1 Record ECU S N Record ECU P N 2 Remove ECS switch cover 5 captive screws so that the function adjust switches 51 7 8 through S8 can be accessed Reference Honeywell CMM 49 61 26 Figure 103 Sheet 2 Change the 53 Max Normal
27. Service Check perform this step and N A the remainder of Service Check If the aircraft has moved the main engines have been operated or 72 hours have elapsed since the last full Service Check accomplish remainder of Service Check In either case document accomplishment of Abbreviated Service Check or Service Check with a log book entry NOTE External APU power must be applied with the hydraulic and fuel systems pressurized DO NOT operate the main engines for this step Operating the main engines prior to or during the reduced check will require a full Service Check to be accomplished Detailed instructions stated in the Service A Check Description must be referenced for the following items Place Maintenance In Work placard in front of radar display Review the aircraft log book and Deferred Items A B C Apply external APU power to the aircraft and pressurize the hydraulic and fuel systems D Check battery voltage E Check general condition of cockpit and cabin areas Check oxygen bottles for required pressure NOTE M IA entry required for all O2 bottle servicing M 1A entry to include O2 bottle pressure before and after servicing Check the cockpit fire extinguishers for required pressure Ensure weight and balance computers are operable G H 1 Check the hydraulic brake pressure J From the ground check for fluid leakage and general condition of the entire aircraft K Check MLG strut height and tire press
28. THE IDG PROPERLY WILL RESULT IN AN OVERFILLED CONDITION AND CAUSE DAMAGE TO THE IDG ae BX AIR CARD NO B767 2B PAGE 9 of 12 B767 SERVICE CHECK SIGN OFF RECORD REV NO 82 DATE 12 06 10 AIRCRAFT DATE Mechanic s Job Description Initials NO 2 ENGINE AND PYLON CF6 80A SERIES 50 50 Perform general visual inspection walk around check of the No 2 engine Check engine cowling engine inlet fan rotor spinner fan rotor blades pylons open blow out doors open latches visible turbine blades and exhaust area for obvious damage and fluid leaks 51 51 Check the No 2 engine oil level using EICAS and service with Turbo 2380 oil if required Ref Fig 5 An EICAS indication of 20 or more is full and oil servicing is not required Record OIL ADDED QUARTS in aircraft log book If no oil was added enter zero 0 WARNING ON GE CF6 80A ENGINES SERVICING SHOULD BE ACCOMPLISHED WITHIN 30 MINUTES OF ENGINE SHUTDOWN WAIT MINIMUM OF 5 MINUTES AFTER ENGINE SHUTDOWN BEFORE REMOVING FILLER CAP NOTE If oil servicing does not occur within 30 minutes of shutdown operate the engines until the RPM is stable Ref AMM 71 00 00 20 NOTE Engine oil consumption is acceptable if consumption is not more than 0 55 U S quarts per hour Ref MM 71 00 00 If excessive amount of oil is added notify Maintenance Control 52 52
29. accomplished daily or the B767 2A B Service Check when scheduled AIRCRAFT STATION LOG PAGE DATE Job Description Mechanic s FUSELAGE EMPENNAGE AMM Initials 1 Visually inspect the crew oxygen discharge indicator disc for presence 35 10 00 1 2 Visually inspect the positive pressure relief valves for flag indication that valves 21 32 00 have opened 3 Visually inspect the static ports TAT and pitot static probes and angle of attack 34 10 00 3 vanes for obvious damage 4 Visually inspect the ram air inlet exhaust doors and cabin pressure outflow valve 21 00 00 4 to ensure there are no obstructions 5 Visually inspect from ground level for missing or damaged navigation 34 00 00 5 communication antennas 6 Visually inspect the fuselage in areas of drain masts and drains for fluid leakage 53 00 00 6 7 Visually inspect lower cargo compartment liners and door seals for obvious 25 52 00 7 damage 52 09 02 8 Visually inspect the visible portions of the vertical fin and rudder and horizontal 55 00 00 8 stabilizer and elevators from ground level for obvious damage evidence of fluid leakage and missing or damaged dischargers 9 Visually inspect the nose and main landing gear tires and wheels for obvious 32 45 00 9 damage Job Description Mechanic s WINGS AMM Initials 1 Visually inspect the lower wing surfaces and wing tips from ground l
30. aft wear pins is 0 031 1 32 inch or less from housing sub assembly brakes parked and hydraulic system pressurized d Remove the pressure from the right hydraulic system if it is not necessary AMM 29 11 00 e Release parking brake Check NLG and MLG shock struts for evidence of leakage and general condition Ref MM 12 15 01 for any corrective action Wipe the exposed chrome surface of the shock strut piston with a clean cloth dampened with ROYCO SSFP fluid MIL H 5606 or MIL H 6083 oils are acceptable alternatives to remove any accumulated grit or grime Remove debris with a downward motion to prevent inserting the debris into the shock strut Drain left and right wing center aux main and surge fuel tank sumps after aircraft has been on ground 1 hour or more A After aircraft has remained in static position for a minimum of one 1 hour drain all fuel tank sumps If more than one 1 hour ground time is available allow fuel to settle as long as schedule permits prior to sumping NOTE Use appropriate sump bottle with drain probe attached NOTE Drain a minimum of two 2 quarts from each sump 46 NOTE Check sump bottle after each draining for water and sediment A clear sump sample can be all water or all fuel To distinguish add a small quantity of water to bottle and observe reaction If sample is all water no change will be observed If sample is all fuel the added water will settle to the
31. anti slip tape 23 23 Check internal markings for condition legibility 24 24 Compartment lighting 25 25 Perform a general visual inspection of the cargo net for security SF and PC2SF only 26 26 Weight and Balance Computer 27 27 Check that all access doors panels are closed secured 28 28 Operate forward L1 R1 door and latching mechanism Ensure smooth operation without restriction 29 29 Check that all volumes of the B767 Wiring Diagram Manual are present and in serviceable condition in manual storage bin Check manual storage bin for general condition PC PC2SF and SF ae BX AIR CARD NO B767 2B PAGE 6 of 12 B767 SERVICE CHECK SIGN OFF RECORD REV NO 82 DATE 12 06 10 AIRCRAFT DATE Mechanic s Job Description Initials LOWER CARGO COMPARTMENT 30 30 Check cargo door for operation door stops and seals for security and evidence of damage 31 31 Check cargo compartments for general condition and evidence of damage NOTE tears holes or damage penetrations through cargo compartment ceiling sidewall shrouds contour panels and door liners must be repaired prior to further flight except as authorized in specific aircraft Minimum Equipment List MEL 32 32 Check condition and cleanliness of interior lining thresholds door barriers restraining equipment nets st
32. back of this form If flap position is unknown examine trailing edge flaps and leading edge flaps and slats in fully extended position For allowable bird hail damage and repair refer to the Structural Repair Manual Make a Log Book M 1A entry of any damage found and corrective action taken ae CARD NO B767 14 BX AIR PAGE 2 of 4 B767 BIRD HAIL STRIKE INSPECTION DATE 11 17 10 ITEM ACCOMP NO DESCRIPTION BY 1 Bird Hail Strike Conditional Inspection A Bird Hail Strike Conditional Inspection Procedure WARNING DO THE DEACTIVATION PROCEDURE FOR THE FLAP SLAT ACTUATION SYSTEMS INJURY TO A PERSON OR DAMAGE TO EQUIPMENT CAN OCCUR IF THE FLAPS SLATS MOVE FLAP SLAT ACTUATION SYSTEMS MUST NOT BE OPERATED DURING THIS INSPECTION FAILURE TO OBEY CAN CAUSE INJURY TO PERSONS 1 Do the deactivation procedure for the leading edge slat system Ref 27 81 00 2 Do the deactivation procedure for the trailing edge flap system Ref 27 51 00 3 Do the examinations that follow NOTE For hail damage to control surfaces contact ABX Planning ILN to issue appropriate Planning Engineering Authorization s NOTE When you examine the honeycomb panels look at the two sides for cracks delaminations soft spots and core damage a Examine the internal and external areas of the radome Look for honeycomb damage and for soft spots b Examin
33. bottom of the bottle and form a visible interface with the fuel Check external power interrupt spare fuses on P34 panel 2 ea ae BX AIR CARD NO B767 2A PAGE 23 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 NO 1 ENGINE AND PYLON CF6 80A SERIES 47 Perform a general visual inspection walk around check of the No 1 engine Check engine cowling engine inlet fan rotor spinner fan rotor blades pylons open blow out doors open latches visible turbine blades and exhaust area for obvious damage and fluid leaks A Check engines for fluid leaks and obvious damage B Check inlet cowl lip assembly and inner outer panels for security condition and damage C Check inlet cone fan blades and annulus fillers for security condition and damage D Check fan duct and cold stream duct thrust reverser blocker doors and acoustic panels for security condition and damage E Check core engine exhaust area including turbine blades for condition and damage F Check engine pylons for fluid leaks and obvious damage 48 Check the No 1 engine oil level using EICAS and service with Turbo 2380 oil if required Ref Figure 5 An EICAS indication of 20 or more is full and oil servicing is not required NOTE Itis not required to service the engine oil if Service Check is being performed on a CF6 80A equipped aircraft that has sat statically and not operated either or bo
34. corrective action taken hi Ko ea Z x lt Q 6of6 PAGE 10 06 06 DATE B767 LIGHTNING STRIKE CHECKLIST STABILIZER AND FIN CAP INSTALLATION EXAMPLE TRAILING EDGE SURFACE INSTALLATION EXAMPLE 2 ZONE 3 ZONE 1 HIGH PROBABILITY PROBABLE LOW PROBABILITY pg AS External Lighting Strike Areas TP006240 Figure CARD NO B767 14 BX AIR PAGE lof4 B767 BIRD HAIL STRIKE INSPECTION DATE 11 17 10 AIRCRAFT NO STATION LOG PAGE NO WORK ORDER NO DATE TOTAL SIGN OFF PAGES 4 The examinations that follow are for a bird strike and a hail strike condition Follow the procedures as indicated below Bird Strike 1 Examine the external surfaces of the airplane structure in the general area of the bird strike All engine intakes and surrounding area must be inspected following a bird strike If external surfaces are damaged the internal structure must be inspected Also inspect the hydraulic pneumatic and other systems in the area of the bird strike for damage Items that do not apply may be signed off as not applicable N A B Hail Strike 1 Complete Items 1 through 3 and N A Step 4 Aircraft configuration should be the same as when bird hail strike occurred i e position of flaps slats etc This information should be obtained from the flight crew and annotated on the
35. edge flap mechanism and track fairing links Look for distortion cracks misalignment or other signs of distress h Examine the control surfaces Look for binding too much play misalignment distortion or displacement of skins Also look for fasteners that have pulled out or are missing i Examine the strut panels doors and structure for buckling cracks and fasteners that have pulled out or are not there 0 Examine wing tip fairings and navigation lights for distortion cracks or other signs of damage pt CARD NO B767 14 BX AIR PAGE 4of4 B767 BIRD HAIL STRIKE INSPECTION DATE 11 17 10 ITEM ACCOMP NO DESCRIPTION BY 1 Bird Hail Strike Conditional Inspection Cont Cont k Examine the external fuselage structure upper and lower 1 If signs of hail damage to the external fuselage structure are found refer to SRM 51 10 04 for the analysis and continued service of airplanes with on ground hail damage 2 Examine any remaining windows for cracks displacement crazing or other signs of damage 3 Examine all antennas for distortion cracks or other signs of damage 1 Examine entry service doors for displacement distortion paint that has flaked dents cracks and fasteners that have pulled out or are not there or other signs of distress m Examine the nose landing gear doors and linkage Look for distortion cracks and othe
36. equipment Component or Exceedance of Event record switch list related component J system certain limits or on pilot display or system failure failure which does values in panel or rec not affect safety of powerplant or Switch on MTC flight aircraft systems panel p 61 SOURCE OF MESSAGE Repair or replace faulty component or dispatch A C per minimum equipment list procedures and requirements Determine if message is real time or latched in non volatile memory Correct any existing problems and checkout system per MTC manual procedures Determine if system is still malfunctioning and take appropriate action to restore system to normal Check out system per MTC manual procedures All auto events are latched in non volatile Utilize system snap shot in conjunction with logbook entry to determine faulty component Repair system and check out per MTC manual procedures CORRECTIVE ACTION Determine if message is real or latched in non volatile memory Real time messages are cleared by repair or replacement of faulty component or system or by clearing memory of respective bite box Messages latched in the EICAS non volatile memory may be cleared by pressing erase Switch EICAS self detected faults may only be cleared by performing EICAS self test with parking brak
37. pressure gauge reading when removed A Replace tire when any portion of an interior tread groove is worn away completely around the visible portion of the circumference OR NOTE Interior grooves are those exclusive of the grooves in or adjacent to the shoulder areas B When the fabric reinforcing ply is exposed NOTE Excessive wear past the fabric reinforcing plies could make the tire non re treadable When tire is worn to limits and requires replacement but circumstances do not permit replacement may be deferred provided the following conditions are met 1 No more than 5 additional landings are made 2 No peeling or chunking of the tire exists and no carcass plies are exposed 3 Item is forwarded to a Deferred Item with an entry in the Aircraft Log Book to monitor landings and tire for maximum wear limits stated in Items A and B above 4 Advise Maintenance Control of requirement to replace deferred tire within 5 landings D Examine the tires for the presence of contaminants 1 Keep the tires clean of contaminants such as oils fuels hydraulic fluids aircraft cleaning agents and greases Cover the tire if these or other potentially harmful chemicals may spill or drip on the tire 2 Wipe off the tire with a soapy solution if the tire becomes contaminated 3 The tire should be removed from service as soon as practical if the surface of the tire appears soft spongy or there are
38. tire for maximum wear limits stated in Items A and B above ae BX AIR CARD NO B767 1A PAGE 4 of 14 B767 DAILY CHECK DESCRIPTION REV NO 78 DATE 10 28 10 AIRCRAFT GENERAL 4 Advise Maintenance Control of requirement to replace deferred tire within 5 landings Examine the tires for the presence of contaminants 1 Keep the tires clean of contaminants such as oils fuels hydraulic fluids aircraft cleaning agents and greases Cover the tire if these or other potentially harmful chemicals may spill or drip on the tire 2 Wipe off the tire with a soapy solution if the tire becomes contaminated 3 The tire should be removed from service as soon as practical if the surface of the tire appears soft spongy or there are bulges present 6 Check tires for proper pressure using approved ABX tool WARNING SERVICE TIRES USING APPROVED ABX TOOL DO NOT USE AN UNREGULATED HIGH PRESSURE NITROGEN SOURCE TO SERVICE TIRES USE OF AN UNREGULATED HIGH PRESSURE NITROGEN SOURCE COULD LEAD TO EXPLOSIVE TIRE FAILURE AND POSSIBLE INJURY NOTE Never deflate a warm or hot tire to obtain desired pressure NOTE Required by AD 87 08 09 Service with dry nitrogen only If nitrogen is not available for re inflation refer to MM 12 15 03 A When tire pressure is below minimum re inflate to desired pressure using approved ABX tool within the following guidelines 1 When a tire is re infla
39. unit replaced a If pouch is firm to touch replace green tamper seal s only using new padlock style seals Model 1001 or notify Maintenance control and generate a Deferred Item to replace tampered seal s or assembly at next station where parts are available b If humidity indicator located below barrier pouch handles has changed in color from blue to pink unit must be replaced within 36 hours Notify Maintenance Control and generate a Deferred Item to have unit replaced J Check life vests 6 each for PC2SF BCSF and BDSF 4 each for SF for presence condition and security ae BX AIR CARD NO B767 2A PAGE 9 of 55 8 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 FLIGHT COMPARTMENT NOTE Replace Life Vests that are due inspection within the next 30 days or generate a Deferred Item so Life Vests can be replaced before due date K ELT BCSF L Check all crew and observer lap seatbelts for ease of length adjustment M Check air sickness bags 5 ea located in First Officer s seat back pocket 8 Perform readout of the Maintenance Control Display Panel MCDP applicable for Saturday or Sunday once per week maintenance visits only A Energize the MCDP and do the self test 1 Close these circuit breakers on the overhead panel P11 a 11C29 LANDING GEAR POSITION AIR GND SYS 2 ALTN b 11C30 LANDING GEAR POSITION AIR GND SYS 1 c 11U9 MAINT CONT DSP
40. upper corners per MPRR 38732 Page 1 Item 1 B revised to read Remove completed Engine Trend Monitoring Reports from the binder at the operations hub Aircraft that do not transit an operations hub forward to Aircraft Records ILN per MPRR 38732 Page 2 Item 3 A 2 deleted at ILN per MPRR 38732 B767 1B Page 1 PC Package Carrier revised RH upper corner to upper corners per MPRR 38732 Page 1 PC2SF revised RH upper corner to external upper corners per MPRR 38732 B767 2A Page 1 PC Package Carrier revised RH upper corner to upper corners per MPRR 38732 Page 1 PC2SF revised RH upper corner to external upper corners per MPRR 38732 Page 1 revised title of section from FLIGHT COMPARTMENT to ABBREVIATED SERVICE CHECK per MPRR 38732 NOTE Item 1 and sub items are now ABBREVIATED SERVICE CHECK Items 2 through 12 are now FLIGHT COMPARTMENT Page 1 Item 1 revised per MPRR 38732 Page 1 Item 1 B revised Deferred Item placards to Deferred Items per mPRR 38732 Page 4 added new Item 3 Operationally Check the Takeoff Configuration Warning Alert N315AA Only renumbered subsequent items per MPRR 38732 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL Page 6 added new Item 6 B Remove completed Engine Trend Monitoring Reports from the binder at the operations hub Airc
41. voltage dip at starter engagement 3 Record APU BAT amperage indication during start 4 Record APU start time from battery voltage dip until RUN light illuminates 5 Record idle EGT with bleed valve closed and generator off 6 Generator on and bleed valve open Record EGT and pneumatic pressure 7 Operate both packs until stabilized record EGT 8 Both packs off and dry motor either engine and record APU GT at max motor pneumatic pressure at max motor and aircraft engine N2 RPM at max motor 9 Terminate MES and monitor pneumatic pressure dip and recovery to normal pressure 10 Shut down APU and check ECU for any faults including mini flags 11 Check that the following manuals forms and certificates are onboard the aircraft and in serviceable condition A Ensure ETOPS Reporting Form Binder is onboard ETOPS aircraft only B Ensure ETOPS APU Reporting Form Binder is onboard ETOPS aircraft only Replenish forms and manuals as applicable 1 Items provided Flight Operations a Two 2 Flight Crew Normal Checklists b Two 2 Quick Reference Handbooks Non Normal Procedures c Passenger Briefing Card 2 Items provided by ABX Document Distribution a One 1 spare Aircraft Log Book b One 1 spare Engine Performance Report c Radio License d B767 Fueling Manual e Emergency Response Guidebook Hazardous Materials f Fault Reporting Manual FRM ae BX AIR CARD
42. 028 10 NOTE Daily Check is accomplished in accordance with the Description on this Form B767 1A documented on Sign Off Form B767 1B Configuration Designations Identifiable Features PC2SF B767 200 Package Carrier Converted to an IAI Special Freighter Main Deck Cargo Door Door Locked external view ports are functional A protective impact doubler is installed on the external upper corners of the L1 Door cutout The supernumerary seat is in the cockpit SF B767 200 IAI Special Freighter Main Deck Cargo Door Door Locked external view ports are functional The supernumerary seat is between the cockpit and smoke barrier BCSF B767 200 Boeing Converted Special Freighter Main Deck Cargo Door Door Locked external view ports cannot be used and are covered with Do Not Remove decals Lavatory is in the cockpit BDSF B767 300 Special Freighter Main Deck Cargo Door Door Locked external view ports are functional Airplane has a tail skid Lavatory is in the cockpit FLIGHT COMPARTMENT NOTE Utilize GSE as much as possible to decrease APU operation Communicate with flight crew on arrival for any requirements or servicing Request APU be shut down if GSE equipment is connected and supplying power to the aircraft Enter all discrepancies and corrective actions in Aircraft Log Book M 1A Record all non airworthy and non safety items that are found during the check on t
43. 11 Record OIL ADDED QUARTS in aircraft log book If no oil was added enter zero 0 58 Service engine IDG oil level and check filter pop out indicator IDGs use turbo 2380 oil CAUTION DO NOT SERVICE IDG IF IDG IS DISCONNECTED A DISCONNECTED IDG MUST BE REMOVED FROM THE AIRCRAFT WITHIN 50 FLIGHT HOURS NOTE Itis not required to service the IDG if Service Check is being performed on a PW 4000 equipped aircraft that has sat statically and not operated either or both engines for the previous 72 hours since last Service Check A Deactivate thrust reverser isolation valve for ground maintenance ae BX AIR CARD NO B767 2A PAGE 37 of 55 B767 SERVICE CHECK DESCRIPTION REV NO 82 DATE 12 06 10 WARNING NO 2 ENGINE AND PYLON PW 4000 SERIES FAILURE TO DEACTIVATE THRUST REVERSER ISOLATION VALVE FOR GROUND MAINTENANCE COULD RESULT IN INADVERTENT THRUST REVERSER OPERATION WITH POSSIBLE INJURY TO PERSONNEL AND DAMAGE TO EQUIPMENT WARNING Check to see if the IDG is disconnected Correct the DISCONNECT TRIP message if necessary Ref AMM 24 20 00 Service IDG as follows Ref Fig 9 1 If IDG is being serviced due to oil loss during system maintenance drain IDG case M M 12 13 03 IDG Oil Drain Procedure and then continue servicing at step D 3 2 If IDG is being serviced for any other reason continue servicing at step D 3 3 Remove dust cover from overflow drain
44. 12 06 10 2 3 4 FLIGHT COMPARTMENT Messages which are latched in the memory of the various BITE boxes on the aircraft are also displayed on the ECS MSG page Messages may only be erased by clearing the faults from the individual system BITE box For example EEC MONITOR message on the ECS MSG page may only be cleared by depressing the RESET switch on the EEC MONITOR and clearing the stored data Some maintenance messages are generated when individual component malfunctions are sensed These messages are erased when normal system operation is restored The EICAS BITE message may be erased by first depressing the TEST switch on the EICAS maintenance panel P 61 and releasing it This initiates the EICAS Self Test which terminates after 5 seconds After the test is complete and a TEST OK is annunciated depress the ERASE switch and release it The message PRESS ERASE TO CLEAR MEMORY will appear on the EICAS screen Depress the ERASE switch a second time and release it The message MEMORY CLEARED will appear on the EICAS screen Depress the TEST switch on the EICAS Maintenance Panel and release it The test pattern will extinguish and the normal engine display will return NOTE Figures 1 2 and 3 contain additional information to aid mechanic in troubleshooting Record all EICAS maintenance messages in the aircraft logbook Indicate the appropriate action taken per paragraph A 2 amp 3 NOT
45. 2 of 55 B767 SERVICE CHECK DESCRIPTION 82 DATE 12 06 10 AIRCRAFT GENERAL 9 If it is suspected that a brake has been exposed to significant levels of contamination the brake should be removed inspected and cleaned in accordance with the brake supplier component maintenance manual Signs of contamination include a wet or oily appearance buildup of charred residue or heavy smoking after landing 10 Release the brakes and ensure that the pressure plate returns to the proper brake released position Do a check for missing brake wear indicator pins Diagram 661181 CAUTION DO NOT LEAVE BRAKES SET FOR MORE THAN FIVE MINUTES WHEN HOT DO NOT SET BRAKES UNDER EXTREME CONDITIONS 1 Set parking brake NOTE Each brake has two brake wear indicator pins a If the two wear pins are missing you must replace the brake prior to the next flight b If one wear pin is missing the brake can stay in service if the remaining wear pin operation is satisfactory NOTE Required by AD 91 18 10 Aircraft cannot be dispatched if fwd or aft brake wear indicator pin is below FLUSH with brakes parked and hydraulic system pressurized Brake wear pin limits are more restrictive than the AD Limits on the brake wear indicator pins are 1 32 with brakes parked not flush Ref Figure 4 43 44 45 Measure fwd and aft brake wear indicator pins Replace brake if end of fwd or
46. 5 minutes and a maximum of 2 hours after initial engine shut down 2 If the engine has been shut down for more than 2 hours motor engine for 2 minutes AMM 71 00 00 201 before checking the oil level 3 Check the oil level indication using the EICAS Full is Left 24 3 Right 21 3 4 If engine EICAS indicates Left 21 Right 19 or less engine oil must be added 5 If next flight segment is ETOPS oil tank level must be visually checked Engine Oil Servicing 1 Supply electrical power Ref 24 22 00 WARNING DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE OPERATION OF THE THRUST REVERSER ACCIDENTAL OPERATION OF THE THRUST REVERSER CAN CAUSE INJURY TO YOU OR DAMAGE TO EQUIPMENT 2 Do the Thrust Reverser for Ground Maintenance Ref 78 31 00 201 3 Open the access door to the oil tank of the left side of the core cowl panel 4 Do the steps that follow to open the oil tank cap WARNING BEFORE YOU OPEN THE OIL TANK CAP PERMIT A MINIMUM OF FIVE MINUTES AFTER ENGINE SHUTDOWN TO LET THE PRESSURE IN THE OIL TANK BLEED OFF A FAST FLOW OF HOT OIL CAN OCCUR AND CAUSE INJURY TO YOU CAUTION DO NOT USE THE OIL TANK SIGHT GAGE TO DO A CHECK OF THE OIL LEVEL YOU MUST LOOK INSIDE THE OIL TANK TO CORRECTLY MEASURE THE OIL a Lift the handle to the position vertical to the top of the oil tank cap b Turn the handle counter clockwise to the OPEN position c Remove the oil tank cap from the fi
47. 58 DATED 01 22 08 B767 1A Page 1 Item 1 G revised all aircraft to CETOPS aircraft only per MPRR 33856 B767 1B Page 2 Item 1 G revised all aircraft to CETOPS aircraft only per MPRR 33856 B767 2A Page 3 Item 4 A 6 a 1 added A T Disc per MPRR 33683 Page 6 Item 7 revised applicable for Saturday maintenance visits only to applicable for Saturday or Sunday once per week maintenance visits only per MPRR 31834 Page 7 Item 8 revised applicable for Saturday maintenance visits only to applicable for Saturday or Sunday once per week maintenance visits only MPRR 31834 Page 9 Item B revised all aircraft to ETOPS aircraft only per MPRR 33856 Page 14 Item 26 B added If the Maintenance Check fails use 767 AMM 25 57 33 5 Config 40 Check Out Procedure to run Weight and Balance program If successful the error in Maintenance Check may be ignored per MPRR 34102 Page 14 added new Item 26 B 4 Check battery condition and note of charge per MPRR 33883 Page 14 added new Item 26 B 6 Note If the printer is inoperative it is acceptable to use the VIEW button in the Maintenance Check program instead of the PRINT button to verify the program version and other error messages Normal printer operation must then be verified with a test loadplan printout or deferred per B767 MEL 25 63 5 per MPRR 33704 Page
48. 67 LINE MAINTENANCE FORMS MANUAL REVISION 67 DATED 08 12 09 B767 90 Page 3 Job Description Logbook Item 1 deleted ETOPS PDSC required and MPRR 36459 Page 3 Item ETOPS Pre Departure Service Check Complete revised Forward all signoff sheets to Fax all signoff sheets per MPRR 36459 Page 3 Item ETOPS Pre Departure Service Check Complete added Ensure ETOPS PDSC Inspection has been entered in the Airworthiness Release block at the bottom of the log page per MPRR 36459 Page 3 Item ETOPS Pre Departure Service Check Complete added Attach this form to the white copy of the log page per MPRR 36459 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 66 DATED 07 13 09 B767 1A Page 2 Item 2 A added per MPRR 36166 Page 2 Item 4 A deleted and hydrostatic test inspection due dates MPRR 36166 Page 2 deleted Item 4 A Note If there are less than ninety 90 days until the expiration date per MPRR 36166 Page 2 Item 4 A 2 added other per MPRR 36166 Page 3 Item 5 F added PC only MPRR 36166 B767 1B Page 3 Item 2 added per MPRR 36166 B767 2A Page 4 Item 4 B 2 revised PC Aircraft to PC and PC2SF Aircraft per MPRR 36166 Page 5 Item 6 B added PC2SF per MPRR 36166 Page 5 Item 6 C 2 added PC2SF
49. A mild soap may be used if necessary to remove spills or splatters Dry with a soft cloth Care should be taken in cleaning the touch control panel CAUTION DO NOT USE ANY TYPE OF ABRASIVE CLEANER SCOURING PADS ARE ALSO UNACCEPTABLE AS THEY MAY SCRATCH THE PRECOATED METAL AND PLASTIC THE ONLY ACCEPTABLE CLEANSER IS A CLOTH MOISTENED IN WATER AND A MILD SOAP 18 Portable oxygen bottle 1 ea located near L1 door SF and PC2SF A Check condition security and hydrostatic test inspection due dates FULL 1850 50 PSI MIN 1400 PSI NOTE If there are any bottles with less than ninety 90 days until the expiration date replace the bottle If there is not an adequate supply of bottles in stock and time remains on the bottle in question make a log book entry with expiration date place on Deferred Item and notify Maintenance Control 19 Check emergency equipment in supernumerary crew service area Ref Figure 13 Sheet 2 of 2 A ELT SF and PC2SF if equipped B Halon fire extinguisher 1 ea for presence and security SF PC2SF and BDSF 1 Pressure gauge indication should be within green band 2 Check and ensure seal is not broken 3 Check hydrostatic test inspection due dates Record hydrostatic due dates on form B767 2B NOTE If there are less than ninety 90 days until the expiration date replace the bottle If there is not an adequate supply of bottles in stock and time remains on the bottle in question
50. AFT GENERAL 38 Perform general visual inspection walk around check of the aircraft fuselage wings and empennage sections viewed from ground level BEFORE MOVING FLAP SLAT HANDLE MAKE CERTAIN THAT AREAS AROUND FLAPS AND SLATS ARE CLEAR OF PERSONNEL AND EQUIPMENT A Accomplish a general visual inspection walk around check with the flaps set at 20 or more spoilers up slats extended and L C and R hydraulic systems pressurized Check external surfaces of Land R wings including leading edges slats flaps spoilers ailerons wing tips and trailing edges for damage corrosion fluid leaks general condition and security B Check wheel well for condition and fluid leaks Check the crew oxygen discharge indicator disc for presence D Check AOA TAT pitot static ports antennas and radome for condition E Check the fuselage in areas of drain masts and drains for fluid leakage F Check vertical and horizontal stabilizer assemblies leading edges skin tips elevator rudder tabs and fairings for general condition and security as viewed from ground level G Check LT and RT wing to fuselage fillets upper and lower external surfaces for damage corrosion fuel leaks general condition and security H Ensure that all access doors are secured I Check fueling station door is secured BEFORE MOVING FLAP SLAT HANDLE MAKE CERTAIN THAT AREAS AROUND FLAPS AND SLATS ARE CLEAR OF PERSONNEL AND EQUIPMENT
51. AIN COUPLING IS FULLY ATTACHED FAILURE TO OBTAIN NEEDED DRAINAGE CAN RESULT IN OVERFILLING AND CAUSE DAMAGE TO THE IDG 10 Discontinue pumping oil into IDG when a minimum of one 1 quart 0 9463 liter has overflowed into container NOTE The one quart of oil overflow is in addition to any oil that may have drained when the hose was connected to the overflow drain coupling CAUTION 11 Disconnect the oil in hose from coupling on IDG 12 Install dust cover on pressure fill coupling on IDG DO NOT REMOVE OIL DRAIN HOSE FROM OVERFLOW DRAIN COUPLING UNTIL DRAINAGE SUBSIDES TO A SLOW DRIPPING CONDITION FAILURE TO DRAIN THE IDG PROPERLY WILL RESULT IN AN OVERFILLED CONDITION AND CAUSE DAMAGE TO THE IDG 13 When oil flow from oil drain hose slows to drops remove oil drain hose 14 Install dust cover on overflow drain coupling on IDG E Check scavenge filter Differential Pressure Indicator DPI NOTE 24 11 01 allows the DPI to be reset three times before IDG replacement If DPI RESET placard is not installed on the IDG contact Maintenance Control to place reset on Deferred Item 1 When an extended DPI is found the IDG do the following a Mark the next sequential number on the DPI RESET placard located on the IDG housing b Record in the A C Logbook the DPI reset number marked in step E 1 a c Do check for the following conditions ae BX AIR CAR
52. AIR CARD NO B767 2A PAGE 5 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 120610 FLIGHT COMPARTMENT 7 If any of the above conditions cannot be verified troubleshoot and repair the Takeoff Warning System and do the Takeoff Configuration Warning Alert check again AMM 31 51 00 101 4 Check LT CTR and hydraulic fluid quantities using EICAS status display If servicing is required refer to MM 12 12 01 A Release parking brakes and pressurize systems for approximately one 1 minute B With pumps OFF quantity should read between 0 88 and 1 11 for left and right systems and between 0 93 and 1 07 for the center system NOTE refill message appears EICAS when HYD QTY reading is 0 75 or below If O FULL overfull appears refer to MM 12 12 01 for servicing 5 Check operation and illumination of all flight compartment lights NOTE Ensure each indicator has two functional lamps If not re lamp as necessary A Press MASTER DIM and TEST SWITCH to illuminate all flight compartment lights 1 Supply electrical power AMM 24 22 00 201 2 Ensure the equipment cooling system is operating AMM 21 58 00 501 3 Ensure the flight data recorder system is operating AMM 31 31 00 501 NOTE bright day put a cover on the windshield to make it easier to do this test 4 At the overhead panel P5 ensure the light override switch is in th
53. ATE 10 28 10 IT 2 j Oil Tube Engine Oil Tank Filler Cap Engine Oi Tank Sight Glass Scupper Drain Relief Valve CF6 80A SERIES ENGINES TP003699 ENGINE OIL SERVICING FIGURE 2 X CARD NO 767 1 AIR 13 of 14 REV NO 78 B767 DAILY CHECK DESCRIPTION DATE 10 28 10 ENGINE QIL ACCESS DOOR OIL TANK SIGHT GAGE n ENGINE OIL TANK CAP SCUPPER s N DRAIN T ENGINE OIL IU TANK 1 ENGINES PRE PW SB 79 65 2 ENGINES POST PW SB 79 65 TP007100 PW 4000 ENGINE OIL SERVICING FIGURE 3 ae BX AIR CARD NO 767 1 PAGE 14 of 14 REV NO 78 B767 DAILY CHECK DESCRIPTION DATE 10 28 10 SCUPPER SCUPPER LEVEL DRAIN LINE FULL FILL LEVEL MAXIMUM FILL LEVEL ON ENGINES TP007101 PW 4000 ENGINE OIL SERVICING FIGURE 4 a BX AIR CARD NO B767 1B PAGE 1 of 4 REV NO 78 B767 DAILY CHECK SIGN OFF RECORD DATE 10 28 10 AIRCRAFT NO STATION LOG PAGE NO WORK ORDER NO DATE TOTAL SIGN OFF PAGES 4 GENERAL DESCRIPTION AND OPERATION NOTE Sign Off Section of the Daily Check Form B767 1B is a signature record and contains general information only The Description Section on Form B767 1A MUST be used to accomplish the Daily Check Configuration Designations Identifiable Features PC2SF B767 200
54. COUPLING UNTIL DRAINAGE SUBSIDES SLOW DRIPPING CONDITION FAILURE TO DRAIN THE IDG PROPERLY WILL RESULT IN AN OVERFILLED CONDITION AND CAUSE DAMAGE TO THE IDG 13 When oil flow from oil drain hose slows to drop wait two minutes then remove oil drain hose 14 Install dust cover on overflow drain coupling on IDG E Check scavenge filter Differential Pressure Indicator DPI Ref Figure 10 NOTE 24 11 01 allows the DPI to be reset three times before IDG replacement If DPI RESET placard is not installed on the IDG contact Maintenance Control to place reset on Deferred Item 1 When an extended DPI is found the IDG do the following a Mark the next sequential number on the DPI RESET placard located on the IDG housing b Record in the A C Logbook the DPI reset number marked in step E 1 a c Do check for the following conditions AMM 24 11 02 1 Check to see if there is contamination on the scavenge filter element in the filter in the filter bowl or in the oil drained from the filter cavity NOTE Contamination is defined as bright metal deposits which can be defined as chunks or pieces caused by breakage in contrast to non metallic flakes or slivers caused by normal wear A moderate number of scattered small metallic flakes bronze or silver colored metal or flakes of generator insulation are normal products of wear during operation Even a considerable nu
55. D HIGH PRESSURE NITROGEN SOURCE TO SERVICE TIRES USE OF AN UNREGULATED HIGH PRESSURE NITROGEN 42 SOURCE COULD LEAD TO EXPLOSIVE TIRE FAILURE AND POSSIBLE INJURY Check brakes for wear evidence of leakage and damage A Replace brake if end of fwd or aft wear indicator pins are 0 031 1 32 inch or less with brakes parked and hydraulic system pressurized Ref Fig 4 NOTE Required by AD 91 18 10 Under no circumstances may an aircraft be dispatched with end of fwd or aft wear indicator pins below FLUSH with brakes parked Ref Figure 4 BRAKE WEAR PIN LIMITS ARE MORE RESTRICTIVE THAN THE AD LIMITS ON THE BRAKE WEAR INDICATOR PINS ARE 1 32 WITH THE BRAKES PARKED NOT FLUSH REF FIGURE 4 43 44 45 43 44 45 Check NLG amp shock struts for general condition With a clean cloth apply a film of ROYCO SSF fluid to the exposed chrome surface of the shock strut pistons to remove any accumulated dirt or debris Drain left and right wing center aux main and surge fuel tank sumps after aircraft has been left on ground 1 hour or more 46 46 Check external power interrupt spare fuses on P34 panel 2 ea ae BX AIR CARD NO B767 2B PAGE 8 of 12 B767 SERVICE CHECK SIGN OFF RECORD REV NO 82 DATE 12 06 10 AIRCRAFT DATE Mechanic s Job Description Initials NO 1 ENGINE A
56. D NO B767 2A PAGE 26 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 NO 1 ENGINE AND PYLON CF6 80A SERIES 1 Check to see if there is contamination on the scavenge filter element in the filter in the filter bowl or in the oil drained from the filter cavity NOTE Contamination is defined as bright metal deposits which can be defined as chunks or pieces caused by breakage in contrast to non metallic flakes or slivers caused by normal wear A moderate number of scattered small metallic flakes bronze or silver colored metal or flakes of generator insulation are normal products of wear during operation Even a considerable number of non metallic items such as black epoxy chips sleeving and other forms of generator insulation does not always indicate damage to the IDG 2 Check to see if the O rings or the filter is damaged This would allow contaminated oil to bypass the filter and enter the external oil cooling circuit d If no contamination is found and no condition is observed that would allow oil to bypass the filter do the following NOTE When the filter DPI has activated for the fourth time replace the IDG Ref AMM 24 11 01 1 Verify there are no IDG related EICAS or BPCU BITE messages If the EICAS or BITE messages are present take necessary corrective action If message was caused by the IDG replace the IDG Ref AMM 24 11 01 2 Reset the filter DPI e If con
57. E If there are no EICAS maintenance messages record in logbook that no messages were found Operationally Check the Takeoff Configuration Warning Alert N315AA Only NOTE Required by CMR 31 51 00 5C Interval should not exceed 72 elapsed clock hours A Procedure 1 Make sure the Parking Brake is set AMM 32 44 00 101 2 Make sure the P10 control stand Parking Brake Light is 3 Push the EICAS Test Switch on the P61 EICAS maintenance panel 4 Verify the following a The red CONFIG light on the instrument panel is on b The WARNING lights on the glareshield come on c The siren Aural Warning is on d The red EICAS message PARKING BRAKE shows on the upper EICAS display NOTE These EICAS messages may or may not appear depending on airplane configuration and should be ignored 1 SPOILERS 2 FLAPS 3 STABILIZER 4 MAIN CARGO DOOR NOTE The red PARKING BRAKE message will show if you push the TEST switch again in less than 6 seconds After 6 seconds only the yellow PARKING BRAKE message will show 5 Push and release the EICAS Self Test button to return the EICAS to normal operation NOTE EICAS warning messages may not come on if you wait more than approximately 10 seconds before you push the EICAS Test Switch The MAIN CARGO DOOR will extinguish immediately if it appears 6 Do the EICAS maintenance message erase procedure as necessary AMM 31 41 00 201 ae BX
58. E ENGINE COULD RESULT IN ENGINE DAMAGE c Add oil in whole quart quantities only When the oil level reaches the bottom of the continue to pour in any remaining oil until the quart can is empty Do not add any more oil d Write down the quantity of oil added 7 If you do see oil the oil is above the bottom of the V a Do not add engine oil 8 Install the oil tank cap as follows a Do a visual inspection of the oil tank cap packing to ensure it is free of cuts and shows no evidence of deterioration b Lubricate the packing of the oil tank cap with engine oil c Turn the handle on the oil tank cap to the OPEN position with the smooth side of the handle away fro the recess d Align the lugs of the oil tank cap with the slots in the filler neck e Install the oil tank cap into the filler neck f Lock the oil tank cap g Apply pressure down on the oil tank cap h Turn the handle to the CLOSE position approximately 45 degrees 1 Pull up on the handle to make sure that the installation of the oil tank cap is correct 0 Put the handle in the recess to lock the oil tank cap k Apply pressure to the outer rim of the oil tank cap at the opposite points to make sure that the installation is correct Make sure that the oil tank cap does not move 9 Close the access door to the oil tank on the left core cowl panel 10 Make sure the EICAS oil indication is Left 24 3 Right 21 3
59. E TO PRESSURE BUILDUP IN IDG CASE HOT OIL CAN CAUSE INJURY TO PERSONNEL ae BX AIR CARD NO B767 2A PAGE 29 of 55 B767 SERVICE CHECK DESCRIPTION REV NO 82 DATE 12 06 10 CAUTION NO 2 ENGINE AND PYLON CF6 80A SERIES CHECK THAT IDG OIL DRAIN HOSE IS NOT SUBMERGED IN OIL IN CONTAINER IS NOT BENT OR KINKED SO AS TO INHIBIT DRAINAGE AND ISLOWER THANIDG AT ALL POINTS FREE DRAINAGE DEPENDS ON AIR GETTING BACK TO IDG CASE THROUGH DRAIN HOSE FAILURE TO OBTAIN PROPER DRAINAGE CAN RESULT IN FILLED CONDITION AND CAUSE DAMAGE IDG USE THE CORRECT ADAPTER TO RELEASE THE PRESSURE FROM THE IDG AN INCORRECT ADAPTER WILL NOT RELEASE THE PRESSURE IN THE THIS CAN CAUSE ANINCORRECT OIL LEVEL IN THE IDG 6 Connect oil drain hose to overflow drain coupling on IDG Allow any oil draining through oil drain hose to flow into container Keep hose below the level of the IDG NOTE It is normal for some oil to drain when the hose is connected to the coupling CAUTION 7 Remove dust cover from pressure fill coupling 8 Connect service cart oil in hose to pressure fill coupling on IDG SOON AFTER STARTING TO PUMP OIL INTO IDG OIL MAY FLOW FROM THE OIL DRAIN HOSE THIS DOES NOT INDICATE A FULL IDG CONTINUE SERVICING UNTIL A MINIMUM OF ONE QUART ONE LITER OF OIL HAS OVERFLOWED INTO THE CONTAINER THIS IS REQUIRED TO ASSURE THE IDG OVERFLOW DRAIN COUPLING
60. G TO PREVENT SPLASH DUE TO PRESSURE BUILDUP IN IDG CASE HOT OIL CAN CAUSE INJURY TO PERSONNEL ae BX AIR CARD NO B767 2A PAGE 25 of 55 B767 SERVICE CHECK DESCRIPTION REV NO 82 DATE 12 06 10 CAUTION NO 1 ENGINE AND PYLON CF6 80A SERTES CHECK THAT IDG OIL DRAIN HOSE IS NOT SUBMERGED IN OIL IN CONTAINER IS NOT BENT OR KINKED SO AS TO INHIBIT DRAINAGE AND IS LOWER THAN IDG AT ALL POINTS FREE DRAINAGE DEPENDS ON AIR GETTING BACK TO IDG CASE THROUGH DRAIN HOSE FAILURE TO OBTAIN PROPER DRAINAGE CAN RESULT IN AN OVER FILLED CONDITION AND CAUSE DAMAGE TO IDG USE THE CORRECT ADAPTER TO RELEASE THE PRESSURE FROM THE IDG AN INCORRECT ADAPTER WILL NOT RELEASE THE PRESSURE IN THE IDG THIS CAN CAUSE AN INCORRECT OIL LEVEL IN THE IDG 6 Connect oil drain hose to overflow drain coupling on IDG Allow any oil draining through oil drain hose to flow into container Keep hose below the level of the IDG NOTE It is normal for some oil to drain when the hose is connected to the coupling CAUTION 7 Remove dust cover from pressure fill coupling 8 Connect service cart oil in hose to pressure fill coupling on IDG SOON AFTER STARTING TO PUMP OIL INTO IDG OIL MAY FLOW FROM THE OIL DRAIN HOSE THIS DOES NOT INDICATE A FULL IDG CONTINUE SERVICING UNTIL A MINIMUM OF ONE QUART ONE LITER OF OIL HAS OVERFLOWED INTO THE CONTAINER THIS IS REQUIRED TO ASSURE THE IDG OVERFLOW DR
61. INIMUM OF 5 MINUTES AFTER ENGINE SHUTDOWN BEFORE REMOVING FILLER CAP NOTE NOTE NOTE Servicing should be accomplished between 15 minutes and 2 hours of engine shutdown If engine has been shut down for more than 2 hours dry motor engine for 2 minutes before checking the oil level PW 4000 Engines Engine oil consumption is acceptable if consumption is not more than 0 5 U S quarts per hour Ref MM 71 00 00 If excessive amount of oil is added notify Maintenance Control 55 55 CAUTION Check No 1 engine IDG oil levels and filter pop out indicators DO NOT SERVICE IDG IF IDG IS DISCONNECTED A DISCONNECTED IDG MUST BE REMOVED FROM THE AIRCRAFT WITHIN 50 FLIGHT HOURS CAUTION DO NOT REMOVE OIL DRAIN HOSE FROM OVERFLOW DRAIN COUPLING UNTIL DRAINAGE SUBSIDES TO A SLOW DRIPPING CONDITION FAILURE TO DRAIN THE IDG PROPERLY WILL RESULT IN AN OVERFILLED CONDITION AND CAUSE DAMAGE TO THE IDG ae BX AIR CARD NO B767 2B PAGE 11 of 12 B767 SERVICE CHECK SIGN OFF RECORD REV NO 82 DATE 12 06 10 AIRCRAFT NO DATE Mechanic s Job Description Initials NO 2 ENGINE AND PYLON PW4000 SERIES 56 56 Perform a general visual inspection walk around check of the No 2 engine Check engine cowling engine inlet fan rotor spinner fan rotor blades pylons open blow out doors open latches visible turbine blades and exhaust area
62. ION REV NO 82 DATE 12 06 10 LAVATORY 15 Perform general visual inspection of lavatory A Check for toilet condition cleanliness and security 1 Replenish tissue as required B Contact Maintenance Control if leaking conditions and or contamination of surrounding areas are noted C Lavatory Portable Oxygen Bottle 1 Check condition security and hydrostatic test inspection due dates FULL 1850 50 PSI MIN 1400 PSI NOTE If there are any bottles with less than ninety 90 days until the expiration date replace the bottle If there is not an adequate supply of bottles in stock and time remains on the bottle in question make a log book entry with expiration date place on Deferred Item and notify Maintenance Control D Check that ea ash tray is installed in receptacle on exterior lavatory compartment wall next to lavatory door AD 74 08 09 R2 ae BX AIR CARD NO B767 2A PAGE 15 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 SUPERNUMERARY COMPARTMENT SF CREW SERVICE AREA PC2SF BCSF and BDSF 16 Visually check supernumerary crew service area ceiling and reading lights for cleanliness condition and security of installation 17 Clean oven if installed WARNING USE A DAMP CLOTH ONLY TO CLEAN OVEN EXCESSIVE WATER MAY CAUSE SHORT CIRCUIT A Daily 1 Using a damp cloth wipe all areas of the oven including exterior interior and door
63. IS FULLY ATTACHED FAILURE TO OBTAIN NEEDED DRAINAGE CAN RESULT IN OVERFILLING AND CAUSE DAMAGE TO THE IDG 10 Discontinue pumping oil into IDG when a minimum of one 1 quart 0 9463 liter has overflowed into container NOTE The one quart of oil overflow is in addition to any oil that may have drained when the hose was connected to the overflow drain coupling CAUTION 11 Disconnect the oil in hose from coupling on IDG 12 Install dust cover on pressure fill coupling on IDG DO NOT REMOVE OIL DRAIN HOSE FROM OVERFLOW DRAIN COUPLING UNTIL DRAINAGE SUBSIDES TO A SLOW DRIPPING CONDITION FAILURE TO DRAIN THE IDG PROPERLY WILL RESULT IN AN OVERFILLED CONDITION AND CAUSE DAMAGE TO THE IDG 13 When oil flow from oil drain hose slows to drops remove oil drain hose 14 Install dust cover on overflow drain coupling on IDG E Check scavenge filter Differential Pressure Indicator DPI NOTE 24 11 01 allows the DPI to be reset three times before IDG replacement If DPI RESET placard is not installed on the IDG contact Maintenance Control to place reset on Deferred Item 1 When an extended DPI is found the IDG do the following a Mark the next sequential number on the DPI RESET placard located on the IDG housing b Record in the A C Logbook the DPI reset number marked in step E 1 a c Do check for the following conditions ae BX AIR CARD NO B767 2A
64. L d 11U15 AIR GND SYS 1 e 11U24 LANDING GEAR POSITION AIR GND SYS 2 2 Supply electrical power AMM 24 22 00 201 3 Put the MCDP ON OFF switch to the ON position a Ensure the FAIL light and the GRD TEST light come on for 5 seconds and then go off b Ensure the FLT FAULT light comes on and stays on 4 To do a check for flight faults go to the Flight Faults procedure To do the ground tests go to the Ground Test procedure B Show the Last Flight Faults and record on form B767 30 MCDP Flight Fault Recording Report located in the B767 Blank Forms Manual NOTE Last Flight Faults shows the faults kept by the MCDP during the last time the MCDP was automatically turned on by touchdown If the Flight Faults Mode is engaged on the ground it causes the MCDP to show LAST FLT FAULT Push the YES ADV button to show a fault that was found during the last flight Each time the YES ADV switch is pushed a different fault will show until all of the faults have been shown The display will then show ALL LAST FLT FAULTS DSPLY 1 Push the NO SKIP switch to go out of Last Flight Faults NOTE If no faults are found the message that shows after the YES ADV switch is pushed will be NO LAST FLT FAULT C Show the Previous Flight Faults and record on form B767 30 MCDP Flight Fault Recording Report located in the B767 Blank Forms Manual NOTE When you go into Previous Flight Faults the message PREV FLT FAULT shows The MCDP will show faul
65. M EXTERNAL OIL CIRCUIT IDG BOTTOM VIEW SEE 5 OIL SUPPLY TO EXTERNAL OIL DIFFERENTEAL CIRCUIT PRESSURE INDICATOR OIL IN LINE INTEGRATED DRIVE GENERATOR OIL OUT LINE SCAVENGE FILTER PRESSURE FILL COUPLING EN OVERFLOW DRAI 5 AIN A COUPLING e 3 Gy COUPLING COVERS FILL DRAIN LOW OIL LEVEL INDICATOR PANEL SEE CASE DRAIN PLUG 0IL IDG BOTTOM VIEW TP007104 PW4000 INTEGRATED DRIVE GENERATOR IDG OIL SERVICING FIGURE 9 ae BX AIR CARD NO B767 2A PAGE 49 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 gt S lt INTEGRATED DRIVE OVERFLOW DRAIN 3 FILTER 4 O RING ELEMENT BOTTOM VIEW RED BUTTON NORMAL RESET EXTENDED PRESSURE DIFFERENTIAL INDICATOR Scavenge Filter Installation ete PW4000 IDG SERVICING FIGURE 10 CARD NO 767 2 BX AIR PAGE 500455 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 S o Q NG SPARE ECU ACCEL NORMAL CONTROL UNDER START NO STOP 616 FAILUR SPEED ABORTED IGHTOFF SPARE REASO DISPLAY SPARE OPERATING FLOW OVERTEMP Loss PRESSURE FILTER 57 POOR CIRCUIT spare FIRE OVER FAILED FILTER EMERG P TEIT FUEL SPARE sensor sot 2 SPD LOF T C RAKE RAKE SWITCH CONTROL 16 N SYSTE
66. MM 04 44 guidelines when performing maintenance on ETOPS aircraft per MPRR 35521 Page 2 deleted Item 1 F Ensure ETOPS Reporting Form Binder is onboard ETOPS aircraft only per MPRR 35521 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL Page 2 deleted Item 1 G Ensure ETOPS APU Reporting Form Binder is onboard ETOPS aircraft only per MPRR 35521 Page 4 Item 5 deleted 5 per MPRR 35521 Page 5 Item 10 revised to read Check the No 1 and No 2 engine oil levels and service with Turbo 2380 oil if required Ref Figure 2 per MPRR 35521 Page 6 Item 12 deleted ETOPS per MPRR 35521 Page 7 deleted Item 13 regarding Auxiliary Power Unit per MPRR 35521 B767 2A Page 16 Item 36 added sills deleted ETOPS per MPRR 35521 Page 16 Item 37 deleted 5 per MPRR 35521 Page 16 Item 38 deleted ETOPS per MPRR 35521 Page 16 Item 39 deleted ETOPS per MPRR 35521 Page 18 Item 44 D added TAT per MPRR 35521 Page 18 44 L deleted ETOPS per MPRR 35521 Page 22 Item 55 revised to read Check the No 1 engine oil level and service with Turbo 2380 oil if required Ref Figure 5 per MPRR 35521 Page 22 Item 55 third Note revised to read When servicing the oil tank observe for odor of fuel at engine oil tank fill port If you find fuel in the oil syste
67. ND PYLON CF6 80A SERIES 47 47 Perform a general visual inspection walk around check of the No I engine Check engine cowling engine inlet fan rotor spinner fan rotor blades pylons open blow out doors open latches visible turbine blades and exhaust area for obvious damage and fluid leaks 48 48 Check the No 1 engine oil level using EICAS and service with Turbo 2380 oil if required Ref Fig 5 An EICAS indication of 20 or more is full and oil servicing is not required Record OIL ADDED QUARTS in aircraft log book If no oil was added enter zero 0 WARNING ON GE CF6 80A ENGINES SERVICING SHOULD BE ACCOMPLISHED WITHIN 30 MINUTES OF ENGINE SHUTDOWN WAIT A MINIMUM OF 5 MINUTES AFTER ENGINE SHUTDOWN BEFORE REMOVING FILLER CAP NOTE If oil servicing does not occur within 30 minutes of shutdown operate the engines until the RPM is stable Ref AMM 71 00 00 20 NOTE Engine oil consumption is acceptable if consumption is not more than 0 55 U S quarts per hour Ref MM 71 00 00 If excessive amount of oil is added notify Maintenance Control 49 49 Check No 1 engine IDG oil level and filter pop out indicators CAUTION DO NOT SERVICE IDG IF IDG IS DISCONNECTED REFER TO FIM 24 20 00 FAULT ISOLATION AND CORRECT DISCONNECT TRIP BITE MESSAGE CAUTION DO NOT REMOVE OIL DRAIN HOSE FROM OVERFLOW DRAIN COUPLING UNTIL DRAINAGE SUBSIDES TO A SLOW DRIPPING CONDITION FAILURE TO DRAIN
68. NO B767 2A PAGE 12 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 FLIGHT COMPARTMENT g Minimum Equipment List Configuration Deviation List MEL CDL and Non Essential Furnishings NEF NOTE N315AA has a 315 Only MEL CDL h MEL Maintenance Practices i WDM Supplement BCSF 3 Items Provided by ABX Maintenance a Aircraft Airworthiness Certificate b Aircraft Registration Certificate c Flight crew circuit breaker collars orange Five 5 each in the aircraft log book d 10 ea M 3 and 5 ea M 3R Deferred Item Placards e Maintenance In Use placard 4 Items Provided by Charter Operations a ICAO Doc 9481 Emergency Response Guidance for Aircraft Incidents Involving Dangerous Goods 219 315 740 744 745 747 only 5 Binder P N Reference a Flight Log A07588 1 b Engine Performance A07590 1 APU Reporting A08775 1 d ETOPS Event A08775 501 D Check the tail number and registration number to ensure the Aircraft Registration and Airworthiness Certificate reflect the same E Check contents of the Flight Crew Deferral Packet stowed in the pocket behind the Pilot seat 1 Replace as necessary any missing items CONTENTS QUANTITY Tie wraps yellow resealable cut to 4 length 10 ea Labels yellow 3 4 diameter P N MR1212 12 3 sheets Bag Ziplock approximately 5 x 8 1 ea Check standby magnetic compass card
69. O B767 2B PAGE 1 of 12 B767 SERVICE CHECK SIGN OFF RECORD REV NO 82 DATE 12 06 10 AIRCRAFT NO STATION LOG PAGE NO WORK ORDER NO DATE TOTAL SIGN OFF PAGES 12 GENERAL DESCRIPTION AND OPERATION NOTE Sign Off Section of the Service Check Form B767 2B is a signature record and contains general information only The Description Section on Form B767 2A MUST be used to accomplish the Service Check Configuration Designations Identifiable Features PC2SF B767 200 Package Carrier Converted to an IAI Special Freighter Main Deck Cargo Door Door Locked external view ports are functional A protective impact doubler is installed on the external upper corners of the L1 Door cutout The supernumerary seat is in the cockpit SF B767 200 IAI Special Freighter Main Deck Cargo Door Door Locked external view ports are functional The supernumerary seat is between the cockpit and smoke barrier BCSF B767 200 Boeing Converted Special Freighter Main Deck Cargo Door Door Locked external view ports cannot be used and are covered with Do Not Remove decals Lavatory is in the cockpit BDSF B767 300 IAI Special Freighter Main Deck Cargo Door Door Locked external view ports are functional Airplane has a tail skid Lavatory is in the cockpit Remove the yellow Maintenance in Work placard from F O s seat back pocket and place in fr
70. OTE CF6 80A Engines Oil consumption is acceptable if consumption is not more than 0 55 U S quarts per hour ref MM 71 00 00 If excessive amount of oil is added notify Maintenance Control a BX AIR CARD NO B767 1B PAGE 4 of 4 B767 DAILY CHECK SIGN OFF RECORD REV NO 78 DATE 10 28 10 AIRCRAFT NO DATE Mechanic s Job Description Initials ENGINES amp PYLONS PW 4000 ENGINES ONLY 10 10 Perform a general visual inspection walk around check of the No 1 and No 2 engines fluid leaks 11 11 Check the No 1 and No 2 engine oil levels using EICAS and service with Turbo Oil 2380 if required An EICAS indication of Left 24 3 Right 21 3 is full and oil servicing is not required 0 Check engine cowling engine inlet fan rotor spinner fan rotor blades pylons open blow out doors open latches visible turbine blades and exhaust area for obvious damage and If next flight segment is ETOPS oil tank level must be visually checked Record OIL ADDED QUARTS in aircraft log book If no oil was added enter zero minutes before checking the oil level oil is added notify Maintenance Control NOTE Servicing should be accomplished between 15 minutes and 2 hours of engine shutdown NOTE If engine has been shut down for more than 2 hours dry motor engine for 2 NOTE PW 4000 Engines Engine oil consump
71. Package Carrier Converted to an IAI Special Freighter Main Deck Cargo Door Door Locked external view ports are functional A protective impact doubler is installed on the external upper corners of the L1 Door cutout The supernumerary seat is in the cockpit SF B767 200 IAI Special Freighter Main Deck Cargo Door Door Locked external view ports are functional The supernumerary seat is between the cockpit and smoke barrier BCSF B767 200 Boeing Converted Special Freighter Main Deck Cargo Door Door Locked external view ports cannot be used and are covered with Do Not Remove decals Lavatory is in the cockpit BDSF B767 300 IAI Special Freighter Main Deck Cargo Door Door Locked external view ports are functional Airplane has a tail skid Lavatory is in the cockpit e Utilize GSE as much as possible to decrease APU operation Communicate with flight crew on arrival for any servicing or special requirements Check aircraft Logbook for pilot reports Enter all discrepancies and corrective actions in Aircraft Logbook M 1A Record all non airworthy and non safety items that are found during the check on the Non Routine Work Sheet M 17 If any errors are identified with a Line Maintenance Check submit a Maintenance Programs Revision Request MPRR per GMM Chapter 1 Section 01 03 and forward to maintenance Programs Any material referenced in the text or tables of the Line Maintenance Chec
72. RSER CAN CAUSE INJURY TO YOU OR DAMAGE TO EQUIPMENT 2 Do the Thrust Reverser for Ground Maintenance Ref 78 31 00 201 3 Open the access door to the oil tank of the left side of the core cowl panel 4 Do the steps that follow to open the oil tank cap WARNING BEFORE YOU OPEN THE OIL TANK CAP PERMIT A MINIMUM OF FIVE MINUTES AFTER ENGINE SHUTDOWN TO LET THE PRESSURE IN THE OIL TANK BLEED OFF A FAST FLOW OF HOT OIL CAN OCCUR AND CAUSE INJURY TO YOU CAUTION DO NOT USE THE OIL TANK SIGHT GAGE TO DO A CHECK OF THE OIL LEVEL YOU MUST LOOK INSIDE THE OIL TANK TO CORRECTLY MEASURE THE OIL a Lift the handle to the position vertical to the top of the oil tank cap b Turn the handle counter clockwise to the OPEN position c Remove the oil tank cap from the filler neck ae BX AIR CARD NO B767 2A PAGE 36 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 NO 2 ENGINE AND PYLON PW 4000 SERIES 5 Look inside the oil tank at the oil Ref Figure 8 NOTE Ifyou see black oil in the oil system refer to AMM 72 00 00 601 Black oil can be an indication of a serious problem or it can be a condition that requires no maintenance action 6 If you do not see oil the oil is below the bottom of V a With a clean screwdriver push open the valve of the filler neck b With a strong light look at the oil CAUTION DO NOT OVERFILL THE ENGINE OIL TOO MUCH OIL IN TH
73. S REQUIRED TO ASSURE THE IDG OVERFLOW DRAIN COUPLING IS FULLY ATTACHED FAILURE TO OBTAIN NEEDED DRAINAGE CAN RESULT IN OVERFILLING AND CAUSE DAMAGE TO THE IDG 10 Discontinue pumping oil into IDG when a minimum of one 1 quart 0 9463 liter has overflowed into container The one quart of oil overflow is in addition to any oil that may have drained when the hose was connected to the overflow drain coupling 11 Disconnect the oil in hose from coupling on IDG ae BX AIR CARD NO B767 2A PAGE 38 of 55 B767 SERVICE CHECK DESCRIPTION REV NO 82 DATE 12 06 10 CAUTION NO 2 ENGINE AND PYLON PW 4000 SERIES 12 Install dust cover on pressure fill coupling on IDG DO NOT REMOVE OIL DRAIN HOSE FROM OVERFLOW DRAIN COUPLING UNTIL DRAINAGE SUBSIDES SLOW DRIPPING CONDITION FAILURE TO DRAIN THE IDG PROPERLY WILL RESULT IN AN OVERFILLED CONDITION AND CAUSE DAMAGE TO THE IDG 13 When oil flow from oil drain hose slows to drop wait two minutes then remove oil drain hose 14 Install dust cover on overflow drain coupling on IDG E Check scavenge filter Differential Pressure Indicator DPI Ref Figure 10 NOTE 24 11 01 allows the DPI to be reset three times before IDG replacement If DPI RESET placard is not installed on the IDG contact Maintenance Control to place reset on Deferred Item 1 When an extended DPI is found
74. SION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 71 DATED 01 19 10 B767 2A Page 9 Added the following Flight Compartment items per MPRR 31933 Item 9 C 4 Items provided by Charter Operations Item 9 C 4 a ICAO Doc 9481 Emergency Response Guidance for Aircraft Incidents Involving Dangerous Goods 312 740 744 745 747 only ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 70 DATED 10 27 09 B767 1A Page 8 added new Item 10 H Record OIL ADDED QUARTS in aircraft log book MPRR 31923 Page 10 deleted Item 12 B 1 e 1 Record quantities added in the Aircraft Log Page renumbered subsequent item per MPRR 31923 Page 10 deleted Item 12 B 1 h Write in the Aircraft Log Page the amount of oil added to the oil tank renumbered subsequent item per MPRR 31923 Page 10 added new Item 12 B 1 1 Record OIL ADDED QUARTS in aircraft log book per MPRR 31923 B767 1B Page 5 Item 10 revised Oil added in quarts Eng 1 ___ Eng 2 to Record OIL ADDED QUARTS in aircraft log book per MPRR 31923 Page 6 Item 12 revised Oil added in quarts Eng 1 ___ Eng 2 to Record OIL ADDED QUARTS in aircraft log book per MPRR 31923 767 2 Page 13 revised Items 25 B 6 a and regarding Weight and Balance Computer MPRR 31960 Page 14
75. Switch setting from B to D Change the S5 Max Cold Switch setting from B to E Change the S8 Duct Press Switch setting from B to E Ensure that all ECS Switches are set to the factory settings FACTORY SETTINGS S2 S3 4 5 6 7 8 MES Max Cool Max EGT ADP Duct Norm Down Cold Deg F eqq Eee qe e Reinstall the ECS switch cover Route this form with the PIL to Aircraft Records ILN NOTE Repair Services if the ECU switches were not set to the factory settings contact Line Maintenance to adjust the switches 767 51 Page 2 of 2 DATE 05 06 03 NOTE REMOVE ACCESS PANEL COVER 5 CAPTIVE SCREWS TO SET SWITCHES 1 8 A 9 D E B C p C p m 53 5 57 51 PART OF RS s o aS p E 7 yt B 82 54 56 58 TP003875 Test Set and ECU Controls 10 24 03 1 2 d B767 60 AIR B767 DAILY EICAS NON NORMAL FAULT MESSAGE RETRIEVAL FORM 1 EICAS Form B767 60 Description and Use General 1 The purpose
76. TION DATE 1206 10 AIRCRAFT GENERAL 4 Replace both tires on the same axle if the aircraft is taxied with tire deflated more than 35 PSI below limits or wheel bearing failure Removal of the adjacent tire is not required if the tire deflates while aircraft is parked or under tow 5 Adjacent tire replacement may be deferred if circumstances do not permit provided the following conditions are met NOTE Tires with excessive heat will be too hot to comfortably leave your hand in the shoulder area a No more than 5 additional landings are made b Tire is visually inspected for signs of damage excessive heat bulges leakage or other unusual conditions prior to each flight c Tire pressure is checked and properly serviced NOTE wheels removed for low pressure should be returned to ABX Air Wheel and Tire Shop ILN Please note the following information on the parts tag Tire removed due to LOW PRESSURE and actual tire pressure gauge reading when removed d Item is forwarded as a Deferred Item with an entry in the Aircraft Log Book to monitor landings and tire condition per items a and b above e Advise Maintenance Control of requirement to replace deferred tire within 5 landings 42 Check brakes for wear evidence of leakage and damage A Prepare for the inspection 1 Ensure the downlocks are installed on the nose and main landing gear AMM 32 00 20 2 Ensure that chocks a
77. USE AN INCORRECT OIL LEVEL IN THE IDG 6 Connect oil drain hose to overflow drain coupling on IDG Allow any oil draining through oil drain hose to flow into container Keep hose below the level of the IDG NOTE It is normal for some oil to drain when the hose is connected to the coupling CAUTION NOTE 7 Remove dust cover from pressure fill coupling 8 Connect service cart oil in hose to pressure fill coupling on IDG SOON AFTER STARTING TO PUMP OIL INTO IDG OIL MAY FLOW FROM THE OIL DRAIN HOSE THIS DOES NOT INDICATE A FULL IDG CONTINUE SERVICING UNTIL A MINIMUM OF ONE QUART ONE LITER OF OIL HAS OVERFLOWED INTO THE CONTAINER THIS IS REQUIRED TO ASSURE THE IDG OVERFLOW DRAIN COUPLING IS FULLY ATTACHED FAILURE TO OBTAIN NEEDED DRAINAGE CAN RESULT IN OVERFILLING AND CAUSE DAMAGE TO THE IDG 10 Discontinue pumping oil into IDG when a minimum of one 1 quart 0 9463 liter has overflowed into container The one quart of oil overflow is in addition to any oil that may have drained when the hose was connected to the overflow drain coupling 11 Disconnect the oil in hose from coupling on IDG ae BX AIR CARD NO B767 2A PAGE 34 of 55 B767 SERVICE CHECK DESCRIPTION 82 DATE 12 06 10 CAUTION NO 1 ENGINE AND PYLON PW 4000 SERIES 12 Install dust cover on pressure fill coupling on IDG DO NOT REMOVE OIL DRAIN HOSE FROM OVERFLOW DRAIN
78. added enter zero 0 per MPRR 36882 B767 1B Page 5 Item 10 added If no oil was added enter zero 0 MPRR 36882 Page 6 Item 12 added If no oil was added enter zero 0 MPRR 36882 B767 2A Page 11 added new Item 13 Clean microwave oven SF and PC2SF only renumbered subsequent items per MPRR 31956 Page 24 Item 56 H added If no oil was added enter zero 0 MPRR 36882 Page 28 Item 59 H added If no oil was added enter zero 0 MPRR 36882 Page 33 Item 62 B 1 i added Tf no oil was added enter zero 0 per MPRR 36882 Page 38 Item 65 B 1 i added Tf no oil was added enter zero 0 MPRR 36882 Page 41 Item 68 C added If no oil was added enter zero 0 MPRR 36882 B767 2B Page 3 added new Item 13 Clean microwave oven SF and PC2SF Only renumbered subsequent items per MPRR 31956 Page 8 Item 56 added If no oil was added enter zero 0 MPRR 36882 Page 9 Item 59 added If no oil was added enter zero 0 MPRR 36882 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL Page 10 Item 62 added If no oil was added enter zero 0 per MPRR 36882 Page 11 Item 65 added Tf no oil was added enter zero 0 MPRR 36882 Page 12 Item 68 added If no oil was added enter zero 0 per MPRR 36882 ae BX AIR REVI
79. anchions and doors 33 33 Check that all blow out panels are in place 34 34 Check operation of cargo compartment lights Replace bulbs as necessary 35 35 Check drain holes are unobstructed 36 36 Remove all foreign matter from cargo compartment door jambs 37 37 Check fwd and aft cargo compartments cargo loading system for general condition and cleanliness ae BX AIR CARD NO B767 2B PAGE 7 of 12 B767 SERVICE CHECK SIGN OFF RECORD REV NO 82 DATE 12 06 10 AIRCRAFT DATE Mechanic s Job Description Initials AIRCRAFT GENERAL 38 38 Perform a general visual inspection walk around check of the aircraft fuselage wings and empennage sections viewed from ground level 39 39 Check operation and illumination of exterior lights 40 40 Check all tires and wheels for wear cuts obvious damage or broken tie bolts 41 41 Check tires for proper pressure using approved ABX tool NOTE Required by AD 87 08 09 Service with dry nitrogen only If dry nitrogen is not available for reinflation refer to MM 12 15 03 200 COLD WARM HOT NOSE TIRES 145 150 PSI 151 160 PSI MAIN TIRES 185 190 PSI 191 200 PSI 201 205 PSI MIN 300 COLD WARM HOT NOSE TIRES 175 180 PSI 181 9065 MAIN TIRES 195 200 PSI 201 210 PSI 211 215 PSI MIN 42 WARNING SERVICE TIRES USING APPROVED ABX TOOL DO NOT USE AN UNREGULATE
80. anel CAUTION Check oil level as indicated by the hollow ball in the sight glass within 30 minutes of shutdown LUBRICATING OILS CONTAIN ADDITIVES WHICH ARE READILY ABSORBED THROUGH THE SKIN AND ARE CONSIDERED TOXIC AVOID PROLONGED OR CONTINUOUS CONTACT OF LUBRICATING OIL WITH SKIN IF INADVERTENTLY SERVICED WITH DISSIMILAR FLUIDS SUCH AS MIL L 6081 FLUSHING OIL OR HYDRAULIC FLUID DO NOT OPERATE ENGINE UNTIL A COMPREHENSIVE EVALUATION OF EFFECTS ON OIL SYSTEM AND ENGINE IS PERFORMED AND CORRECTIVE ACTION IS COMPLETED NOTE NOTE A sight glass with a hollow float ball is installed below the fill port scupper The oil tank is fully serviced when the ball is at the top of the glass Use oil from freshly opened cans in order to assure that uncontaminated oil is used WAIT A MINIMUM OF 5 MINUTES AFTER ENGINE IS SHUT DOWN BEFORE REMOVING FILLER CAP TO ALLOW TANK PRESSURE TO BLEED OFF HOT OIL GUSHING FROM TANK COULD CAUSE SEVERE BURNS IF FILLER NECK FLOAT VALVE IS DISPLACED BEFORE PRESSURE DISSIPATES If the oil level is below the top of the sight glass remove engine oil tank filler cap Add oil in whole quart quantities only When the floating ball reaches the top of the sight glass continue to pour in any remaining oil until the quart can is empty Do not add any more oil NOTE Make sure you add oil slowly and carefully If you add oil into the filler cap too quickly the oil may flow out the fill port The
81. are being applied repair the leakage or replace the brake prior to dispatch 8 Brakes with leaks below these limits must be rechecked prior to each flight and should be repaired or replaced at the next opportunity that manpower and material allow 9 If it is suspected that a brake has been exposed to significant levels of contamination the brake should be removed inspected and cleaned in accordance with the brake supplier component maintenance manual Signs of contamination include a wet or oily appearance buildup of charred residue or heavy smoking after landing 10 Release the brakes and ensure that the pressure plate returns to the proper brake released position C Do check for missing brake wear indicator pins CAUTION DO NOT LEAVE BRAKES SET FOR MORE THAN FIVE MINUTES WHEN HOT DO NOT SET BRAKES UNDER EXTREME CONDITIONS 1 Set parking brake NOTE Each brake has two brake wear indicator pins a If the two wear pins are missing you must replace the brake prior to the next flight b If one wear pin is missing the brake can stay in service if the remaining wear pin operation is satisfactory ae BX AIR CARD NO B767 1A PAGE 6 of 14 REV NO 78 B767 DAILY CHECK DESCRIPTION DATE 10 28 10 AIRCRAFT GENERAL NOTE Required by AD 91 18 10 Aircraft cannot be dispatched if fwd or aft brake wear indicator pin is below FLUSH with brakes parked and hydraulic syste
82. ated over openings TP002954 SECURITY TAG LOCATOR COCKPIT DOOR FIGURE 12 ae BX AIR CARD NO B767 2A PAGE 52 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 OXYGEN MASK 6 SMOKE GOGGLES 6 HALON FIRE EXTINGUISHER LICENSE HOLDERS CRASH AXE ESCAPE ROPES DESCENT DEVICE 2 INERTIAL REEL DESCENT DEVICE LIFE VEST 6 EMERGENCY MEDICAL KIT 10 PROTECTIVE BREATHING EQUIPMENT PBE 14 LIFE RAFT 2 IF INSTALLED 12 PORTABLE 02 BOTTLE 13 ESCAPE HARNESS 2 1 2 3 4 5 6 7 8 9 14 PORTABLE 02 BOTTLE STANDARD AIRWORTHINESS CERTIFICATE 15 INERTIA REEL DESCENT DEVICE CERTIFICATE OF REGISTRATION 16 HALON FIRE EXTINGUISHER FCC REGISTRATION TP603713 COCKPIT EQUIPMENT PC2SF CONFIGURED AIRCRAFT FIGURE 13 SHEET 1 OF 3 CARD NO B767 2A BX AIR PAGE 53of55 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 EMERGENCY UFE VEST LOCATOR BARRIER PLACES TRANSMITTER SMOKE GOGGLES EMERGENCY ESCAPE ROPE OVERHEAD FIRE EXTINGUISHER LIFE RAFT 2 LIFE VEST 3 PLACES DESCENT DEVICES AUTOMATIC FIRE SMOKE GOGGLES EXTINGUISHER OXYGEN BOTTLE OXYGEN BOTTLE FIRE FULL FACE MASK EXTINGUISHER LIFE VEST 1 SPARE 1 DEMO PERSONAL BREATHING EQUIPMENT EMERGENCY LOCATOR TRANSMITTER LIFE VEST FIRST AID KIT FIRE
83. aulic system ADP Air Driven Pump oil level and delta pop up indicator moved to B767 3A as new Item 72 renumbered subsequent items per MPRR 33695 B767 3A Revised per MPRRs 33695 33121 33692 31280 33652 33700 33697 33862 33712 and 31848 B767 3B Revised per MPRR 33084 Also revised to correspond with changes per MPRRs 33695 33700 33697 33862 and 33712 p CHAPTER 00 SECTION Index AIR EE B767 LINE MAINTENANCE FORMS MANUAL Fo DATE 12 06 10 PAGE CARD FORM RANGE IN NUMBER DESCRIPTION PAGES DIGITAL DATE FILE 767 1 B767 Daily Check Description 1 14 37 50 10 28 10 B767 1B B767 Daily Check Sign Off Record 1 4 51 54 10 28 10 B767 2A B767 Service Check Description 1 55 55 109 12 06 10 B767 2B B767 Service Check Sign Off Record 1 12 110 121 12 06 10 B767 9 B767 Lightning Strike Checklist 1 6 122 127 10 06 06 B767 14 B767 Bird Hail Strike Inspection 1 4 128 131 11 17 10 B767 50 B767 APU ECU Function Adjustment 1 2 132 133 02 11 04 Switches Settings ECU Installed B767 51 B767 APU ECU Function Adjustment 1 2 134 135 05 06 03 Switches Settings ECU Removed B767 60 B767 Daily EICAS Non Normal Fault 1 2 136 137 10 24 03 Message Retrieval Form B767 90 B767 ETOPS Predeparture Check 1 6 138 143 11 29 10 a BX AIR CARD B767 1A PAGE 1 of 14 REV NO 78 B767 DAILY CHECK DESCRIPTION DATE 1
84. ayauuejed pue jeorosjo euin jea S RIdsIg SJILUN 9594 pasdeja pepeeoxe YDIYM spaads pue sduay skedsig Xoq JOIN vonounfuoo uj pasn 159 pue jeued ejdsip 01409 21 s ejdsta pue 10 gyep sKejdsig JLN pue sjojouieJed 953 one s ejdsip opne uj awy JLN V UYA 2 wojs s Joguoo SUN jeas 54610510 TP003703 EICAS MESSAGES FIGURE 3 ae BX AIR CARD NO B767 2A PAGE 43 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 BRAKE WEAR LIMITS ARE MORE RESTRICTIVE THAN THE AD LIMITS ON PRESSURE PLATE THE BRAKE WEAR INDICATOR PINS ARE 1 32 WITH BRAKES PARKED NOT FLUSH WEAR INDICATOR PIN PISTON HOUSING 003704 NOTE Replace brake if either end of fwd or aft wear indicator pins is 0 031 1 32 inch or less from housing sub assembly with brakes parked and hydraulic system pressurized BRAKE WEAR LIMITS FIGURE 4 ae BX AIR CARD NO B767 2A PAGE 44 of 55 B767 SERVICE CHECK DESCRIPTION REV NO 82 DATE 12 06 10 IH Ot J Tube
85. bulges present Visually inspect wheels for broken damaged or missing tie bolts Replace any wheel with broken or missing tie bolts 41 Check tires for proper pressure using approved ABX tool SERVICE TIRES USING APPROVED ABX TOOL DO NOT USE AN UNREGULATED HIGH PRESSURE NITROGEN SOURCE TO SERVICE TIRES USE OF AN UNREGULATED HIGH PRESSURE NITROGEN SOURCE COULD LEAD TO EXPLOSIVE TIRE FAILURE AND POSSIBLE INJURY CAUTION DO NOT LEAVE TIRE UNATTENDED DURING SERVICING OVER INFLATION AND EXPLOSION COULD OCCUR NOTE Never deflate a warm or hot tire to obtain desired pressure NOTE Required by AD 87 08 09 Service with dry nitrogen only If dry nitrogen is not available for re inflation refer to MM 12 15 03 A When tire pressure is below minimum re inflate to desired pressure using approved ABX tool within the following guidelines 1 When a tire is re inflated more than 10 PSI an Aircraft Log Book entry is required 2 If pressure is 10 20 PSI below the lower limit of the applicable inflation range service tire to the upper limit of the inflation range and make an entry into the Aircraft Log Book If log book indicates a previous history of under inflation for 3 or more days tire must be replaced 3 If pressure is more than 20 PSI below limits the tire must be replaced prior to further flight ae BX AIR CARD NO B767 2A PAGE 21 of 55 REV NO 82 B767 SERVICE CHECK DESCRIP
86. chanic s Initials Job Description AIRCRAFT GENERAL Check brakes for wear evidence of leakage and damage A Replace brake if end of fwd or aft wear indicator pins are 0 031 1 32 inch or less with brakes parked and hydraulic system pressurized Ref Fig 1 NOTE Required by AD 91 18 10 Under no circumstances may an aircraft be dispatched with end of fwd or aft wear indicator pins below FLUSH with brakes parked BRAKE WEAR PIN LIMITS ARE MORE RESTRICTIVE THAN THE AD LIMITS ON THE BRAKE WEAR INDICATOR PINS ARE 1 32 WITH THE BRAKES PARKED NOT FLUSH REF FIGURE 1 Mechanic s Initials Job Description ENGINES amp PYLONS 80 ENGINES ONLY Perform a general visual inspection walk around check of the No 1 and No 2 engines Check engine cowling engine inlet fan rotor spinner fan rotor blades pylons open blowout doors open latches visible turbine blades and exhaust area for obvious damage and fluid leaks Check the No 1 and No 2 engine oil levels using EICAS and service with Turbo 2380 oil if required Ref Figure 2 An BICAS indication of 20 or more is full and oil servicing is not required Record OIL ADDED QUARTS in aircraft log book If no oil was added enter zero 0 WARNING ON GE CF6 80A ENGINES SERVICING SHOULD BE ACCOMPLISHED WITHIN 30 MINUTES OF ENGINE SHUTDOWN WAIT A MINIMUM OF 5 MINUTES AFTER ENGINE SHUTDOWN BEFORE REMOVING FILLER CAP N
87. check filter pop out indicator IDGs use turbo 2380 oil CAUTION DO NOT SERVICE IDG IF IDG IS DISCONNECTED A DISCONNECTED IDG MUST BE REMOVED FROM THE AIRCRAFT WITHIN 50 FLIGHT HOURS NOTE Itis not required to service the IDG if Service Check is being performed on a CF6 80A equipped aircraft that has sat statically and not operated either or both engines for the previous 72 hours since last Service Check NOTE Access through panels 417CL and 427CL on No 2 engine core panels A Deactivate thrust reverser isolation valve for ground maintenance FAILURE TO DEACTIVATE THRUST REVERSER ISOLATION VALVE FOR GROUND MAINTENANCE COULD RESULT IN INADVERTENT THRUST REVERSER OPERATION WITH POSSIBLE INJURY TO PERSONNEL AND DAMAGE TO EQUIPMENT B Check to see if the IDG is disconnected Correct the DISCONNECT TRIP message if necessary Ref AMM 24 20 00 D Service IDG as follows Ref Fig 6 1 If IDG is being serviced due to oil loss during system maintenance drain IDG case M M 12 13 03 IDG Oil Drain Procedure and then continue servicing at step D 3 2 If IDG is being serviced for any other reason continue servicing at step D 3 3 Remove dust cover from overflow drain coupling on IDG 4 Put a container below the IDG to catch the oil which will flow from the IDG 5 Place end of oil drain hose into a container to catch oil WHEN CONNECTING HOSE TO OVERFLOW DRAIN COUPLING USE RAG AROUND FITTING TO PREVENT SPLASH DU
88. coupling on IDG 4 Put a container below the IDG to catch the which will flow from the IDG 5 Place end of oil drain hose into a container to catch oil WHEN CONNECTING HOSE TO OVERFLOW DRAIN COUPLING USE RAG AROUND FITTING TO PREVENT SPLASH DUE TO PRESSURE BUILDUP IN IDG CASE HOT OIL CAN CAUSE INJURY TO PERSONNEL CHECK THAT IDG OIL DRAIN HOSE IS NOT SUBMERGED IN OIL IN CONTAINER IS NOT BENT OR KINKED SO AS TO INHIBIT DRAINAGE AND IS LOWER THAN IDG AT ALL POINTS FREE DRAINAGE DEPENDS ON AIR GETTING BACK TO IDG CASE THROUGH DRAIN HOSE FAILURE TO OBTAIN PROPER DRAINAGE CAN RESULT IN AN OVER FILLED CONDITION AND CAUSE DAMAGE TO IDG USE THE CORRECT ADAPTER TO RELEASE THE PRESSURE FROM THE IDG AN INCORRECT ADAPTER WILL NOT RELEASE THE PRESSURE IN THE IDG THIS CAN CAUSE AN INCORRECT OIL LEVEL IN THE IDG 6 Connect oil drain hose to overflow drain coupling on IDG Allow any oil draining through oil drain hose to flow into container Keep hose below the level of the IDG NOTE It is normal for some oil to drain when the hose is connected to the coupling CAUTION NOTE 7 Remove dust cover from pressure fill coupling 8 Connect service cart oil in hose to pressure fill coupling on IDG SOON AFTER STARTING TO PUMP OIL INTO IDG OIL MAY FLOW FROM THE OIL DRAIN HOSE THIS DOES NOT INDICATE A FULL IDG CONTINUE SERVICING UNTIL A MINIMUM OF ONE QUART ONE LITER OF OIL HAS OVERFLOWED INTO THE CONTAINER THIS I
89. d refer to AMM 24 11 02 for corrective action Activate thrust reverser isolation valve Ref AMM 78 31 00 ae BX AIR CARD NO B767 2A PAGE 31 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 NO 1 ENGINE AND PYLON PW 4000 SERIES 53 Perform a general visual inspection walk around check of the No 1 engine Check engine cowling engine inlet fan rotor spinner fan rotor blades pylons open blow out doors open latches visible turbine blades and exhaust area for obvious damage and fluid leaks A Check engines for fluid leaks and obvious damage B Check inlet cowl lip assembly and inner outer panels for security condition and damage Check inlet cone fan blades and fan case rub strips for security condition and damage D Check fan duct and cold stream duct thrust reverser blocker doors and acoustic panels for security condition and damage E Check core engine exhaust area including turbine blades for condition and damage Check engine pylons for fluid leaks and obvious damage 54 Service oil at No 1 engine with 2380 engine oil Ref Figure 7 NOTE Itis not required to service the engine oil if Service Check is being performed on a PW 4000 equipped aircraft that has sat statically and not operated either or both engines for the previous 72 hours since last Service Check A Engine Oil Check 1 To check the engine oil wait a minimum of 1
90. d by the IDG replace the IDG Ref AMM 24 11 01 2 Reset the filter DPI e If contamination is found refer to AMM 24 11 02 for corrective action Activate thrust reverser isolation valve Ref AMM 78 31 00 ae BX AIR CARD NO 767 2 PAGE 39 of 55 B767 SERVICE CHECK DESCRIPTION REV NO 82 DATE 12 06 10 AUXILIARY POWER UNIT 59 Perform a general visual inspection of the internal section of the APU compartment A Open APU access doors B Do a general visual inspection of the APU compartment and check for condition security and fluid leaks 60 Service auxiliary power unit APU oil to maximum limits with turbo 2380 oil A Service APU oil quantity to maximum limit with turbo 2380 oil WARNING DO NOT REMOVE THE OIL FILL CAP IF THE APU IS WARM AND THE OIL LEVEL IS AT OR ABOVE THE FULL MARK THE HOT OIL CAN CAUSE INJURY ALLOW THE APU TEMPERATURE TO DECREASE AS MUCH AS POSSIBLE BEFORE YOU FILL THE OIL 2 Slowly add oil until the oil flows into the scupper drain 3 Install fill cap ensure cap is secure B Close APU access doors C Record OIL ADDED QUARTS in aircraft log book If no oil was added enter zero 0 ae BX AIR CARD NO B767 2A PAGE 40 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 EICAS MAINTENANCE amp STATUS MESSAGES MSG TYPE STATUS MAINTENANCE AUTO EVENT MANUAL EVENT Minimum
91. d servicing per MPRR 35521 Page 28 Item 60 deleted 5 per MPRR 35521 Page 32 Item 63 deleted ETOPS per MPRR 35521 Page 34 Item 64 deleted ETOPS per MPRR 35521 Page 37 Item 66 deleted ETOPS per MPRR 35521 Page 39 Item 67 deleted ETOPS per MPRR 35521 Page 42 Item 69 deleted ETOPS per MPRR 35521 B767 2B Page 1 General Description and Operation added Item This check includes ETOPS tasks which require Technicians to adhere to GMM 04 44 guidelines when performing maintenance on ETOPS aircraft per MPRR 35521 Page 6 Items 36 37 38 and 39 deleted ETOPS per MPRR 35521 Page 7 Item 44 deleted ETOPS per MPRR 35521 Page 8 Item 55 revised to read Check the No 1 engine oil level and service with Turbo 2380 oil if required Ref Fig 5 per MPRR 35521 Page 8 Item 56 deleted ETOPS per MPRR 35521 Page 9 Item 59 revised to read Check the No 2 engine oil level and service with Turbo 2380 oil if required Ref Fig 5 per MPRR 35521 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL Page 9 Item 60 deleted 5 per MPRR 35521 Page 10 Items 63 and 64 deleted ETOPS MPRR 35521 Page 11 Items 66 and 67 deleted ETOPS per MPRR 35521 Page 12 Item 69 deleted 5 MPRR 35521 ae BX AIR REVISION HIGHLIGHTS
92. deleted Item 32 Note N714AX only has four 4 volumes per MPRR 31923 Page 23 added new Item 55 H Record OIL ADDED QUARTS in aircraft log book per MPRR 31923 Page 27 added new Item 58 H Record OIL ADDED QUARTS in aircraft log book per MPRR 31923 Page 31 deleted Item 61 B 1 e 1 Record quantities added in the Aircraft Log Page renumbered subsequent item per MPRR 31923 Page 32 deleted Item 61 B 1 h Write in the Aircraft Log Page the amount of oil added to the oil tank renumbered subsequent item per MPRR 31923 Page 32 added new Item 61 B 1 1 Record OIL ADDED QUARTS in aircraft log book per MPRR 31923 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL Page 36 deleted Item 64 B 1 e 1 Record quantities added in the Aircraft Log Page renumbered subsequent item per MPRR 31923 Page 37 deleted Item 64 B 1 h Write in the Aircraft Log Page the amount of oil added to the oil tank renumbered subsequent item per MPRR 31923 Page 37 added new Item 64 B 1 1 Record OIL ADDED QUARTS in aircraft log book per MPRR 31923 Page 40 Item 67 A deleted Enter the amount added in quarts in the aircraft log book per MPRR 31923 Page 40 added new Item 67 C Record OIL ADDED QUARTS in aircraft log book per MPRR 31923 B767 2B Page 8 Item 55 revised Oil added quarts Eng 1 __
93. ding excessive oil use and sub items renumbered subsequent items per MPRR 36469 Page 10 Item 12 B 1 e 2 deleted Maximum One Time Oil Addition Limits For Oil Quantity per MPRR 36469 Page 10 Item 12 B 1 e 2a revised Fax a note to Manager Powerplant Engineering to Contact Maintenance Control per MPRR 36469 Page 10 Item 12 B 1 e 2a revised Engine Number to Engine Position per MPRR 36469 B767 2A Page 23 added new Item 55 D regarding excessive oil use and sub items renumbered subsequent items per MPRR 36469 Page 27 added new Item 58 D regarding excessive oil use and sub items renumbered subsequent items per MPRR 36469 Page 31 Item 61 B 1 e 2 deleted Maximum One Time Oil Addition Limits For Oil Quantity per MPRR 36469 Page 31 Item 61 B 1 e 2a revised Fax a note to Manager Powerplant Engineering to Contact Maintenance Control per MPRR 36469 Page 31 Item 61 B 1 e 2a revised Engine Number to Engine Position per MPRR 36469 Page 36 Item 64 B 1 e 2 deleted Maximum One Time Oil Addition Limits For Oil Quantity per MPRR 36469 Page 36 Item 64 B 1 e 2a revised Fax a note to Manager Powerplant Engineering to Contact Maintenance Control MPRR 36469 Page 36 Item 64 B 1 e 2a revised Engine Number to Engine Position per MPRR 36469 ae BX AIR REVISION HIGHLIGHTS B7
94. ding straps Ensure they are attached correctly to the airframe 3 Look at the condition of the lightning diverter strips Repair or replace them if they are damaged 4 If the radome is damaged examine the antenna and the waveguide for damage B Examine the metallic structure for holes or pits Look for burned or unusual colored skin or rivets Examine the external surfaces of the composite honeycomb sandwich components Look for discolored paint burned punctured or delaminated skin plies apt CARD NO B767 9 BX AIR PAGE 2of B767 LIGHTNING STRIKE CHECKLIST DATE 10 06 06 ITEM ACCOMP NO DESCRIPTION BY 1 CAUTION MAKE SURE TO SEAL OR REPAIR ALL DAMAGE FAILURE Cont TO SEAL OR REPAIR DAMAGE CAN CAUSE MORE INTERNAL DAMAGE BECAUSE MOISTURE CAN GET IN D Repair or seal the damaged areas 2 Examine the Zone 2 Figure 1 surface areas for signs of a lightning strike Make sure you look in the areas where one surface ends and the other surface starts A Examine the metallic structure for holes or pits Look for burned or discolored skin or rivets B Examine external surfaces of composite honeycomb sandwich components Look for discolored paint burned punctured or delaminated skin plies CAUTION MAKE SURE TO SEAL OR REPAIR ALL DAMAGE FAILURE TO SEAL OR REPAIR DAMAGE CAN CAUSE MORE INTERNAL DAMAGE BECAUSE MOISTURE CAN GET IN C Repair or seal the damaged areas
95. e wings and empennage sections as viewed from ground level A Perform a general visual inspection walk around check of the aircraft to ensure that all access doors are secured Check fuselage empennage L and R wings wing tips and flight control surfaces for fluid leaks and damage Correct any discrepancy found and clean stained areas Perform a general visual inspection from ground level for missing or damaged navigational communication antennas and static ports static probes and angle of attack vanes for obvious damage Check wheel well areas for general condition and evidence of fluid leaks D Visually inspect wheels for broken damaged or missing tie bolts Replace any wheel with broken or missing tie bolts E Check NLG and MLG struts for evidence of leakage Ref MM 12 15 01 for any corrective action 1 Wipe the exposed chrome surface of the shock strut piston with a clean cloth dampened with ROYCO SSP fluid MIL H 5606 or MIL H 6083 oils are acceptable alternates to remove any accumulated grit or grime Remove debris with a downward motion to prevent inserting the debris into the shock strut F Inspect Main Deck Cargo Door within six 6 inches of cutout for dents nicks and general condition G Check the crew oxygen discharge indicator disc for presence H Check the fuselage in areas of drain masts and drains for fluid leakage I Check RAM air inlet exhaust doors for obstructions J Check fueling s
96. e OFF mode 5 At the P5 panel set the switch for the indicator lights to the bright mode 6 Put the adjacent test switch to the ON mode a Ensure all of the annunciators lights and switches connected to the master dim and test system come on brightly 1 Ensure the Alt Alert A P A P Disc and A T Disc annunciator lights are on 7 Set the switch for the indicator lights to the dim mode a Ensure the annunciators lights and switches connected to the master dim and test system become dim 8 When the test is done put the test switch in the OFF mode 9 Set the switch for the indicator lights to the usual mode 10 Put the aircraft back to its usual condition CAUTION DO NOT KEEP THE EMERGENCY LIGHTS ON FOR MORE THAN 1 MINUTE EXTENDED OPERATION WILL REDUCE THE CHARGE ON THE BATTERIES AND MAY RESULT IN DAMAGE B Check flight compartment emergency lights 1 Select emergency lights switch to ARMED Verify UNARM light is extinguished and the emergency lights did not illuminate validates 28 VDC Pin 2 power system i e ground service buss 2 Turn emergency light switch to ON Verify all emergency lights illuminate and UNARM light is ON ae BX AIR CARD NO B767 2A PAGE 6 of 55 B767 SERVICE CHECK DESCRIPTION REV NO 8 DATE 12 06 10 FLIGHT COMPARTMENT PC2SF Aircraft L388 L1 Door L H Grd Illum Exterior Light L312 L1 Threshold Exit Sign
97. e printer box cabinet to the OFF position 27 Check that all access doors panels are closed secured 28 Operate forward entry service door s and latching mechanism Ensure smooth operation without restriction L1 PC2SF BCSF and BDSF only L1 and R1 SF only 29 Wiring Diagram Manuals PC2SF and SF A Check that all volumes of the B767 Wiring Diagram Manual are present and in serviceable condition BX AIR CARD NO B767 2A PAGE 17 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 UPPER CARGO COMPARTMENT B Check manual storage bin for general condition ae BX AIR CARD NO B767 2A PAGE 18 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 LOWER CARGO COMPARTMENT 30 Check cargo doors for operation door stops door sills and seals for security and evidence of damage A Ensure all cargo compartment door stops are not broken or missing B Ensure all cargo door handles are faired when cargo door is closed Check cargo door operation and cargo door proximity targets for damage 31 Check cargo compartments for general condition and evidence of damage A Repair liners using AKRO Fireguard Repair Kit AF888 or by replacing the entire fiberglass panel NOTE AAlltears holes or damage penetrations through cargo compartment ceiling sidewall shrouds contour panels and door liners must be repaired prior to furthe
98. e right side of the lower EICAS screen If the message 1 or page 2 appears at the bottom of the message list pressing the ECS MSG switch will cause additional messages to be displayed 2 Record each of the messages as a separate item in the aircraft logbook Consult the EICAS Message Table Ref MM 31 41 00 for general conditions which generate each message Note which messages may have been generated as part of an Auto Event ECS HYD ELEC or APU since these messages may have a Snap Shot of the respective system parameters recorded 3 Operationally check each item or perform a BITE check as applicable and correct any discrepancies as necessary NOTE Any time the Inertial Reference Units are shut down the L FLT CONT ELEC and R FLT CONT ELEC maintenance messages will be generated and latched in Non Volatile Memory These messages DO NOT indicate a malfunction unless they cannot be erased by the method outlined below When all discrepancies are cleared the maintenance messages must be erased by the following methods 1 Messages recorded in Non Volatile Memory NVM are recalled by pressing the ECS MSG switch to display all messages then pressing the AUTO switch to isolate the NVM messages These messages may then be erased by pressing the ERASE switch for 5 seconds ae BX AIR CARD NO B767 2A PAGE 4 of 55 B767 SERVICE CHECK DESCRIPTION 82 DATE
99. e set then pressing erase switch twice while test pattern is displayed Determine if message is real time or latched in non volatile memory Real time messages are cleared by repair or replacement of faulty component or system or by clearing memory of respective bite box MTC messages latched in EICAS memory may also cause status messages to be displayed To erase these select ECS MSG page press auto read switch then press erase Switch All manual events are snap shots of the respective EICAS MTC page displays To erase select each of the pages press the manual read switch then press the erase switch message select ECS MSG page press the auto read switch then press the erase Switch To clear the system snap shot select the respective system display press the auto read swilch then press the erase switch ERASE PROCEDURE TP003701 EICAS MESSAGES FIGURE 1 ae BX AIR CARD NO B767 2A PAGE 41 of 55 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 Takes manual snap shot of eng and system parameters on EICAS MTC pages Will record over any manual event data already latched in memory Only the most recent manual event may be recalled DISPLAY ENGINE STATUS which will power both L Left computer Auto Left computer computer will come on
100. e the forward body nose section eyebrow area above the windows and radome Look for cracks distortion delamination misalignment and displacement of the skins Also look for fasteners that have pulled out or are not there c Examine the pilots windows for delamination spalling or cracks Also examine the adjacent structure for distortion cracks and fasteners that have pulled out or are not there CARD NO X AIR PAGE B767 14 3 of 4 B767 BIRD HAIL STRIKE INSPECTION DATE 11 17 10 ITEM NO DESCRIPTION ACCOMP BY 1 Cont Bird Hail Strike Conditional Inspection Cont d Examine all wing horizontal surfaces nacelle strut and the horizontal and vertical stabilizer leading edge fairing Look for displacement distortion fastener hole elongation or tearout and paint that has flaked Also look for skin cracks and fasteners that have pulled out or are not there Examine the wing leading and trailing edge structure panels and doors Look for displacement distortion paint that has flaked cracks and fasteners that have pulled out or are not there Also examine the two sides of the honeycomb panels for cracks delamination soft spots and core damage f Examine the leading edge slat mechanism and track fairing links Look for distortion cracks misalignment or other signs of distress g Examine the trailing
101. el assembly located above 3rd and 4th observer seats PC and PC2SF only E Check First Aid Kit 1 Check condition and security if seal is broken inventory first aid kit contents and replace any missing or damaged items a Contents Each first aid kit must contain the following ae BX AIR CARD NO B767 2A PAGE 8 of 55 B767 SERVICE CHECK DESCRIPTION 82 DATE 12 06 10 FLIGHT COMPARTMENT CONTENTS QUANTITY Adhesive bandage compress 1 1 16 Put PUIG S WADS e 005 20 Ammonia 10 Bandage compresses 41 8 Triangular bandage compresses 40 inch 5 Arm splint non inflammable eese enne 1 Leg splint non inflammable 1 Roller bandage 4 1 2 2 6 00000000000 4 Adhesive tape I inch standard roll sse 2 950 RM 1 Protective latex gloves or equivalent non permeable gloves pair 1 2 Sealing of First Aid Kits a After contents of the first aid kit have been inventoried and replenished complete an Emergency Sticker M 38 Ref GMM Chapter 1 Section 07 07 and seal the first aid kit b Enter N A in the Inspection Due Date due to no time requirements for this unit
102. er A Run the Maintenance Check program as follows and check for sufficient amount of paper If the Maintenance Check fails use 767 AMM 25 57 33 5 Config 40 Check Out Procedure to run Weight and Balance program If successful the error in Maintenance Check may be ignored 1 On the printer box cabinet toggle the ON OFF switch to ON 2 Select the W amp B 1 or W amp B 2 position as applicable 3 Press the red ON button on the WBC 4 Check battery condition and note of charge 5 Click on the Maintenance Check icon 6 Follow the on screen instructions to print and verify the following NOTE If the printer is inoperative it is acceptable to use the VIEW button in the Maintenance Check program instead of the PRINT button to verify the program version and other error messages Normal printer operation must then be verified with a test loadplan printout or deferred per B767 MEL 25 63 5 a Verify that weight and balance program is current version 4 709 or later b Check for spare paper P N LD RAKNSB for printer c No other error messages will be shown 7 Close the Maintenance Check program using the small x in the upper right corner 8 Check the print for correct values and readability 9 After 10 minutes of operation check battery condition for increase in of charge NOTE Batteries that will not charge above 50 should be replaced 10 Turn off the WBC and toggle the ON OFF switch on th
103. er panels for security condition and damage Check inlet cone fan blades and fan case rub strips for security condition and damage D Check fan duct and cold stream duct thrust reverser blocker doors and acoustic panels for security condition and damage E Check core engine exhaust area including turbine blades for condition and damage Check engine pylons for fluid leaks and obvious damage 57 Service oil at No 2 engine with 2380 engine oil Ref Figure 9 NOTE Itis not required to service the engine oil if Service Check is being performed on a PW 4000 equipped aircraft that has sat statically and not operated either or both engines for the previous 72 hours since last Service Check A Engine Oil Check 1 To check the engine oil wait a minimum of 15 minutes and a maximum of 2 hours after initial engine shut down 2 If the engine has been shut down for more than 2 hours motor engine for 2 minutes AMM 71 00 00 201 before checking the oil level 3 Check the oil level indication using the EICAS Full is Left 24 3 Right 21 3 4 If engine EICAS indicates Left 21 Right 19 or less engine oil must be added 5 If next flight segment is ETOPS oil tank level must be visually checked B Engine Oil Servicing 1 Supply electrical power Ref 24 22 00 WARNING DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE OPERATION OF THE THRUST REVERSER ACCIDENTAL OPERATION OF THE THRUST REVE
104. ered in the Airworthiness Release block at the bottom of the log page Check Completed ETOPS Authorized A amp P Technician Signature Employee Number Attach this form to the white copy of the log page ae BX AIR CARD NO B767 90 PAGE 4 of 6 B767 ETOPS PREDEPARTURE CHECK DATE 11 29 10 ET J 4 d Oil Tube Engine Oil l Tank Filler Cap Engine Oi Tank Sight Glass Scupper Drain Relief Valve CF6 80A SERIES ENGINES TP003699 ENGINE OIL SERVICING FIGURE 1 4 CARD NO B767 90 AIR 5 of 6 B767 ETOPS PREDEPARTURE CHECK DATE 11 29 10 ENGINE GIL ACCESS DOOR 011 TANK SIGHT GAGE ENGINE OIL R TANK SCUPPER DRAIN IER ENGINE OIL TANK 1 ENGINES PRE PW SB 79 65 2 ENGINES POST PW SB 79 65 007100 PW 4000 ENGINE OIL SERVICING FIGURE 2 ae BX AIR CARD NO B767 90 PAGE 6 of 6 B767 ETOPS PREDEPARTURE CHECK DATE 11 29 10 SCUPPER SCUPPER LEVEL BRAIN a LINE FULL FILL LEVEL MAXIMUM FILL LEVEL ON ENGINES 007101 PW 4000 ENGINE OIL SERVICING FIGURE 3
105. es for the previous 72 hours since last Service Check NOTE Lubricating oil for the engine is replenished through the engine oil tank filler port Servicing should be accomplished within 30 minutes of engine shutdown for consistent results If after 30 minutes operate the engines until the rpm is stable Ref AMM 71 00 00 20 NOTE When servicing the oil tank observe for odor of fuel at engine oil tank fill port If you find fuel in the oil system you must do the troubleshooting procedure FIM 71 05 00 101 Fig 129 and flush the oil system AMM 79 11 00 301 A Open the engine oil servicing door on right fan cowl panel WARNING WAIT A MINIMUM OF 5 MINUTES AFTER ENGINE IS SHUT DOWN BEFORE REMOVING FILLER CAP TO ALLOW TANK PRESSURE TO BLEED OFF HOT OIL GUSHING FROM TANK COULD CAUSE SEVERE BURNS IF FILLER NECK FLOAT VALVE IS DISPLACED BEFORE PRESSURE DISSIPATES Check oil level as indicated by the hollow float ball in the sight glass LUBRICATING OILS CONTAIN ADDITIVES WHICH ARE READILY ABSORBED THROUGH THE SKIN AND ARE CONSIDERED TOXIC AVOID PROLONGED OR CONTINUOUS CONTACT OF LUBRICATING OIL WITH SKIN CAUTION IF INADVERTENTLY SERVICED WITH DISSIMILAR FLUIDS SUCH AS MIL L 6081 FLUSHING OIL OR HYDRAULIC FLUID DO NOT OPERATE ENGINE UNTIL A COMPREHENSIVE EVALUATION OF EFFECTS ON OIL SYSTEM AND ENGINE IS PERFORMED AND CORRECTIVE ACTION IS COMPLETED NOTE sight glass with a hollow float ball is installed be
106. es in stock and time remains on the bottle in question make a logbook entry with expiration date place on Deferred Item and notify Maintenance Control Check 2 ea Crew Oxygen Bottle Pressure 1300 PSI MINIMUM NOTE M 1A entry required for all O2 bottle servicing M 1A entry to include O2 bottle pressure before and after servicing NOTE Crew oxygen bottles are located in the Main Equipment Center 1 Compare Crew Oxygen cylinder pressure gauges with flight deck indication should agree within 50 PSD 2 Check hydrostatic test inspection due dates Check portable oxygen bottle BCSF and BDSF 1 Check condition security and hydrostatic test inspection due dates Full 1850 50 PSI MIN 1400 PSI NOTE _ If there are less than ninety 90 days until the expiration date replace the bottle If there is not an adequate supply of bottles in stock and time remains on the bottle in question make a logbook entry with expiration date place on Deferred Item and notify Maintenance Control C Check portable Halon fire extinguisher s for presence and security 2 each for BCSF and BDSF and 1 each for SF and PC2SF 1 Pressure gauge indication should be within green band 2 Check and ensure seal is not broken 3 Check hydrostatic test inspection due dates D Check emergency descent device and escape ropes for presence condition and security 1 There is 1 escape rope at each no 2 window 2 There is ea inertia re
107. evel for 57 50 00 1 obvious damage and fuel leakage and missing or damaged dischargers 2 Visually inspect the visible portions of the left and right wing flight control 27 00 00 2 surfaces from ground level for obvious damage 3 Visually inspect that the fueling station door is secured 28 21 00 3 ae BX AIR CARD NO B767 90 PAGE 2 of 6 B767 ETOPS PREDEPARTURE CHECK DATE 11 29 10 Job Description ENGINES AMM Mechanic s Initials ENGINE 1 ENGINE 2 Visually inspect the engine cowling for obvious damage open blow out doors open latches and signs of fluid leakage 71 00 00 1 1 Visually inspect the inlet cowl fan rotor spinner and fan rotor blades for obvious damage 72 00 00 Visually inspect the turbine exhaust sleeve plug and visible turbine blades 72 00 00 Check engine oil level for full Ref B767 1A Daily Check for detailed procedures CF6 80A Ball at the top of sight gage is full PW4000 Requires two separate ETOPS mechanics or alternate flight crew procedure per GMM 04 44 Par 5 Oil level must be at or above the V in the filler neck 12 13 01 Check EICAS oil level indication CF6 80A 20 or greater is full PW4000 Left 24 3 is full Right 21 3 is full 12 13 01 Document any oil added on M 1A If no oil was added enter zero 0 If both engines require oil to be added and or both
108. figured Aircraft MPRR 33876 B767 2B Page 2 deleted Item 12 TCAS Self Test and sub items renumbered subsequent items MPRR 34267 Page 4 Item 26 deleted 2 ea installed in galley and near weight and balance computer PC only per MPRR 33876 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL B767 3A B767 3A A Check Description deleted from B767 Line Maintenance Forms Manual A Checks are now in PMI Job Cards per MPRR 34281 B767 3B B767 3B A Check Signoff Record deleted from B767 Line Maintenance Forms Manual A Checks are now in PMI Job Cards per MPRR 34281 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 59 DATED 02 26 08 B767 1A Page 2 Item 2 added Reference AMM 25 20 01 6 for net damage cuts tears stitching limits per MPRR 34372 B767 2A Page 13 Item 23 A added Reference AMM 25 20 01 6 for net damage cuts tears stitching limits MPRR 34372 Page 23 added new Item 54 Check external power interrupt spare fuses on P34 panel 2 ea renumbered subsequent items per MPRR 34260 B767 2B Page 7 added new Item 54 Check external power interrupt spare fuses on P34 panel 2 renumbered subsequent items per MPRR 34260 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION
109. for obvious damage and fluid leaks 57 57 Service oil at No 2 engine with 2380 engine oil Check the No 1 and No 2 engine oil levels using EICAS and service with Turbo Oil 2380 if required An EICAS indication of Left 24 3 Right 21 3 is full and oil servicing is not required If next flight segment is ETOPS oil tank level must be visually checked Record OIL ADDED QUARTS in aircraft log book If no oil was added enter zero 0 NOTE Servicing should be accomplished between 15 minutes and 2 hours of engine shutdown NOTE If engine has been shut down for more than 2 hours dry motor engine for 2 minutes before checking the oil level NOTE PW 4000 Engines Engine oil consumption is acceptable if consumption is not more than 0 5 U S quarts per hour Ref MM 71 00 00 If excessive amount of oil is added notify Maintenance Control 58 58 Check No 2 engine IDG oil levels and filter pop out indicators CAUTION DO NOT SERVICE IDG IF IDG IS DISCONNECTED A DISCONNECTED IDG MUST BE REMOVED FROM THE AIRCRAFT WITHIN 50 FLIGHT HOURS CAUTION DO NOT REMOVE OIL DRAIN HOSE FROM OVERFLOW DRAIN COUPLING UNTIL DRAINAGE SUBSIDES TO A SLOW DRIPPING CONDITION FAILURE TO DRAIN THE IDG PROPERLY WILL RESULT IN AN OVERFILLED CONDITION AND CAUSE DAMAGE TO THE IDG ae BX AIR CARD NO B767 2B PAGE 12 of 12 REV NO 82 B767 SERVICE CHECK SIGN OFF RECORD DATE 12 06 10
110. ge now This Figure Intentionally Left Blank per MPRR 35591 B767 2B Page 8 No 1 Engine and Pylon CF6 80A Series deleted Item 57 Check No 1 Engine Master Chip Detector s MCD for metal and Notes renumbered subsequent items per MPRR 35591 Page 9 No 2 Engine and Pylon CF6 80A Series deleted Item 60 Check No 2 engine Master Chip Detector s MCD for metal and Notes renumbered subsequent items per MPRR 35591 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 63 DATED 04 21 09 B767 90 ETOPS Predeparture Check revised per MPRR 35587 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 62 DATED 03 31 09 B767 90 Moved Mechanic s Initials column from left side of form to right side of form per MPRR 35578 Page 2 Job Description Engines revised Item 4 and added new Items 5 and 6 per MPRR 35578 Page 2 Job Description APU revised Item 1 per MPRR 35578 Page 2 Job Description Logbook added new Item 3 per MPRR 35578 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 61 DATED 03 09 09 B767 1A Page 1 deleted Item 1 F Ensure ETOPS Reporting Form Binder is onboard ETOPS aircraft only per MPRR 35521 Page 1 deleted Item 1 G Ensure ETOPS APU Reporting Form Binder is onboard ETOPS aircraft o
111. gure 4 NOTE If you see black oil in the oil system refer to AMM 72 00 00 601 Black oil can be an indication of a serious problem or it can be a condition that requires no maintenance action 6 If you do not see oil the oil is below the bottom of the V a With a clean screwdriver push open the valve of the filler neck b With a strong light look at the oil c Add oil in whole quart quantities only When the oil level reaches the bottom of the continue to pour in any remaining oil until the quart can is empty Do not add any more oil a BX AIR CARD NO B767 1A PAGE 10 of 14 B767 DAILY CHECK DESCRIPTION NO 78 DATE 10 28 10 7 8 9 10 11 12 ENGINES AND PYLONS PW4000 SERIES If an excessive amount of oil is used 0 5 U S quarts per hour or more contact Maintenance Control Ref MM 71 00 00 indicating a Aircraft Number b Engine Position c Qty per flight hour used d Qty oil added If you do see oil the oil is above the bottom of the V a Do not add engine oil Install the oil tank cap as follows a Do a visual inspection of the oil tank cap packing to ensure it is free of cuts and shows no evidence of deterioration b Lubricate the packing of the oil tank cap with engine oil c Turn the handle on the oil tank cap to the OPEN position with the smooth side of the handle awa
112. he Non Routine Work Sheet M 17 1 Check flight compartment items A Check Aircraft Logbook for pilot reports Remove completed Engine Trend Monitoring Reports from the binder at the operations hub Aircraft that do not transit an operations hub forward to Aircraft Records ILN Check 2 ea crew oxygen bottle pressures 1000 psi MINIMUM NOTE M IA entry required for all O2 bottle servicing M 1A entry to include O2 bottle pressure before and after servicing D Inspect Logbook binder for serviceable condition E Inspect document holder sleeves for condition and security If found unserviceable or in poor condition contact Maintenance for deferral I A W GMM Chapter 1 Section 07 04 a BX AIR CARD NO B767 1A PAGE 2 of 14 REV NO 78 B767 DAILY CHECK DESCRIPTION DATE 1028 10 LAVATORY 2 Check Lavatory A Check for toilet condition 1 Replenish tissue as required 2 If toilet requires servicing service per MM 38 30 01 If unable to service contact Maintenance Control to have servicing performed and place toilet on Deferred Item List UPPER CARGO COMPARTMENT 3 Check the cargo compartment for general condition ae BX AIR CARD NO B767 1A PAGE 3 of 14 B767 DAILY CHECK DESCRIPTION REV NO 78 DATE 10 28 10 AIRCRAFT GENERAL 4 Perform general visual inspection walk around check of the aircraft fuselag
113. heck this box if there were no Non Normal EICAS messages complete and fax form 4 Circle EICAS message level Level A Warning Level B Caution Level C Advisory S Status M Maintenance 5 Record EXACT EICAS message as displayed 6 Record system BITE information related to EICAS message as applicable Provide additional follow up information and or details as required A Example Left PTC Low Limit Valve Fault Light On B Example FQPU Channel 1 Fault Codes A4 B4 61 and 91 C Example Zone Temperature Controller Aft Zone Trim Valve Fault Light On 7 Circle YES or NO to indicate if system BITE info code s cleared after reset 8 Provide any additional information that may be beneficial to assist with system troubleshooting 9 Print name and employee number when form is completed and fax to ABX Maintenance Control AIRCRAFT STATION LOG PAGE NUMBER DATE mm ad yyyy GO 7 AX 0 vor ACCOMPLISHED DUE TO TIM 3 NO STATUS OR MAINT MESSAGES EICAS MESSAGE EICAS MESSAGE BITE INFO CODE S CLEARED LEVEL G Record EXACT Message As Displayed AFTER RESET Circle B 5 or Circle YES or o No l SYSTEM BITE INFO CODE S 6 O COMPLETED PRINT FAX COMPLETED PAGE 2 TO MAINT CONTROL 937 383 1919 7 767 60
114. hts will come on one at a time for 4 seconds from the left to the right and from the top to the bottom of the control unit 4 If FAULTY LRU lights came on correct the failure FIM 49 11 00 Fig 103 B APU Control Unit BITE Test 1 Put the RECORD SELECT switch to the LAST RUN 1 position a Put the FAULT switch to the LRU UNIT position and release ae BX AIR CARD NO B767 2A PAGE 11 of 55 B767 SERVICE CHECK DESCRIPTION REV NO 82 DATE 12 06 10 FLIGHT COMPARTMENT NOTE This does a check for the FAULTY LRUs that could have caused the last auto shutdown failure on the APU 1 Make a record of the FAULTY LRU lights that come on NOTE If there are FAULTY LRUs the lights will come on at the same time for 4 6 seconds b Put the FAULT switch to the REASON DISPLAY position NOTE The APU shutdowns are put in the memory of the control unit You can see the reason for the last shutdown when the RECORD FAULT SELECT switch is in the LAST RUN position 1 Make a record of the REASON DISPLAY APU NOT OPERATING lights that come on c Correct the failures for the REASON DISPLAY APU NOT OPERATING and the FAULTY LRU lights that you recorded FIM 49 11 00 Fig 103 d Push the ERASE MEMORY switch to erase the failures from the memory of the APU control unit APU Start Operational Check 1 Record APU battery voltage prior to start 2 Start APU and record battery
115. internal self sealing valve limits the flow of oil to 1 quart 1 liter every 40 seconds at 70 F 21 C If an excessive amount of oil is used 0 55 U S quarts per hour or more contact Maintenance Control Ref MM 71 00 00 indicating 1 Aircraft Number 2 Engine Position 3 Qty per flight hour used 4 Qty oil added BX AIR CARD NO B767 1A PAGE 8 of 14 B767 DAILY CHECK DESCRIPTION REV NO 78 DATE 10 28 10 m Q m m ENGINES AND PYLONS CF6 80A SERIES Install filler cap and check for looseness and positive locking Verify the ball is at the top of the sight glass Close the engine oil servicing door on the right fan cowl panel Record OIL ADDED QUARTS in aircraft log book If no oil was added enter zero 0 a BX AIR CARD NO B767 1A PAGE 9 of 14 REV NO 78 B767 DAILY CHECK DESCRIPTION DATE 10 28 10 ENGINES AND PYLONS PW4000 SERIES 10 Perform a general visual inspection walk around check of the No 1 and No 2 engines Check engine cowling engine inlet fan rotor spinner fan rotor blades fan cowls pylons open blow out doors open latches visible turbine blades and exhaust area for obvious damage and fluid leaks 11 Service at No 1 and No 2 engines with 2380 engine oil Ref Figure 3 A Engine Check 1 To check the engine oil wait a minimum of 15 minutes and a maximum of 2 hours after in
116. ions and operation tests comes from flight crew information and the aircraft conditions during and after the incident NOTE Itis not necessary to examine the coaxial cables and the connectors if the radio system had no problems during and after the incident and operational checks were done and no problems were found Accomplish Operational Check of the following systems per the reference provided 1 Communications System Ref 23 12 00 501 2 Navigation General Ref 34 00 00 201 3 ILS Navigation System Ref 34 31 00 501 4 Marker Beacon System Ref 34 32 00 501 5 Radio Altimeter System Ref 34 33 00 501 6 Weather Radar System Ref 34 43 00 501 7 System Ref 34 51 00 501 8 ATC System Ref 34 53 00 501 9 DME System Ref 34 55 00 501 10 Automatic Direction Finder ADF System Ref 34 57 00 501 11 Nose Radome Ref 53 12 01 201 ae CARD NO B767 9 X AIR PAGE 5 of 6 B767 LIGHTNING STRIKE CHECKLIST DATE 10 06 06 o DESCRIPTION 12 C Inspection of the Radio and Navigation Systems Cont 1 Examine the antennas of the following systems for damage a VHF b VOR e ILS f ADF g Radio Altimeter h Marker Systems D Accomplish operational check of the Radio and Navigation Systems 18 Make Log Book M 1A entry of any damage found and
117. itial engine shut down 2 If the engine has been shut down for more than 2 hours motor engine for 2 minutes AMM 71 00 00 201 before checking the oil level 3 Check the oil level indication using the EICAS Full is Left 24 3 Right 21 3 4 If engine EICAS indicates Left 21 Right 19 or less engine oil must be added 5 If next flight segment is ETOPS oil tank level must be visually checked Engine Oil Servicing 1 Supply electrical power Ref 24 22 00 DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE OPERATION OF THE THRUST REVERSER ACCIDENTAL OPERATION OF THE THRUST REVERSER CAN CAUSE INJURY TO YOU OR DAMAGE TO EQUIPMENT 2 Do the Thrust Reverser for Ground Maintenance Ref 78 31 00 201 3 Open the access door to the oil tank of the left side of the core cowl panel 4 Do the steps that follow to open the oil tank cap WARNING BEFORE YOU OPEN THE OIL TANK CAP PERMIT A MINIMUM OF FIVE MINUTES AFTER ENGINE SHUTDOWN TO LET THE PRESSURE IN THE OIL TANK BLEED OFF A FAST FLOW OF HOT OIL CAN OCCUR AND CAUSE INJURY TO YOU CAUTION DO NOT USE THE OIL TANK SIGHT GAGE TO DO A CHECK OF THE OIL LEVEL YOU MUST LOOK INSIDE THE OIL TANK TO CORRECTLY MEASURE THE OIL a Lift the handle to the position vertical to the top of the oil tank cap b Turn the handle counter clockwise to the OPEN position c Remove the oil tank cap from the filler neck 5 Look inside the oil tank at the oil Ref Fi
118. k entry to document accomplishment of Abbreviated Service Check or Service Check with a log book entry per MPRR 38732 Page 3 added new Item 3 Operationally check the Takeoff Configuration Warning Alert N315AA Only renumbered subsequent items per MPRR 38732 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 74 DATED 06 11 10 B767 1A B767 1B B767 2A B767 2B Daily and Service Check forms revised to incorporate the BCSF configuration and delete JT9D requirements per MPRR 38726 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 73 DATED 04 14 10 B767 90 Page 2 Job Description Engines Item 6 added If no oil was added enter zero 0 per MPRR 36880 Page 2 Job Description APU Item 1 added Record oil added quarts in aircraft log book If no oil was added enter zero 0 per MPRR 36880 Page 3 Job Description Logbook Item 1 revised to read Complete Airworthiness Release entry for ETOPS PDSC Inspection per MPRR 36880 Page 3 Check Completed section added space for Employee Number per MPRR 36880 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 72 DATED 03 12 10 B767 1A Page 8 Item 10 H added If no oil was added enter zero 0 per MPRR 36882 Page 10 Item 12 B 1 i added Tf no oil was
119. ks may be substituted in accordance with the Consumable Material Equivalents List located in Chapter 20 B767 Maintenance Manual This bullet item does not apply to AD related tasks e This check includes ETOPS tasks which require Technicians to adhere to GMM 04 44 guidelines when performing maintenance on ETOPS aircraft CERTIFICATION OF AIRWORTHINESS All signoff pages of the check have been received action taken where necessary and initialed properly Aircraft Log book properly noted GMM Chapter 1 Section 04 03 Forward all sign off sheets and attach M 17 forms to Aircraft Records ILN Daily Check Completed A amp P Technician signature a BX AIR CARD NO B767 1B PAGE 2 of 4 REV NO 78 B767 DAILY CHECK SIGN OFF RECORD DATE 10 28 10 AIRCRAFT NO DATE Mechanic s Job Description Initials FLIGHT COMPARTMENT 111 Check flight compartment items A Check Aircraft Logbook for pilot reports Remove Engine Trend Monitoring Reports from binder sheets at ILN or from aircraft that are not returning to ILN and forward to Aircraft Records ILN Check 2 ea crew oxygen bottle pressures 1000 psi MINIMUM NOTE M IA entry required for all O2 bottle servicing M 1A entry to include O2 bottle pressure before and after servicing D Inspect Logbook binder for serviceable condition E Inspect document holder sleeves for co
120. l and check filter pop out indicator IDGs use turbo 2380 oil CAUTION DO NOT SERVICE IDG IF IDG IS DISCONNECTED A DISCONNECTED IDG MUST BE REMOVED FROM THE AIRCRAFT WITHIN 50 FLIGHT HOURS NOTE Access through panels 417CL and 427CL No 1 amp No 2 engine core panels NOTE Itis not required to service the IDG if Service Check is being performed on CF6 80A equipped aircraft that has sat statically and not operated either or both engines for the previous 72 hours since last Service Check A Deactivate thrust reverser isolation valve for ground maintenance FAILURE TO DEACTIVATE THRUST REVERSER ISOLATION VALVE FOR GROUND MAINTENANCE COULD RESULT IN INADVERTENT THRUST REVERSER OPERATION WITH POSSIBLE INJURY TO PERSONNEL AND DAMAGE TO EQUIPMENT B Check to see if the IDG is disconnected Correct the DISCONNECT TRIP message if necessary Ref AMM 24 20 00 D Service IDG as follows Ref Fig 6 1 If IDG is being serviced due to oil loss during system maintenance drain IDG case M M 12 13 03 IDG Oil Drain Procedure and then continue servicing at step D 3 2 If IDG is being serviced for any other reason continue servicing at step D 3 3 Remove dust cover from overflow drain coupling on IDG 4 Put a container below the IDG to catch the oil which will flow from the IDG 5 Place end of oil drain hose into a container to catch oil WHEN CONNECTING HOSE TO OVERFLOW DRAIN COUPLING USE RAG AROUND FITTIN
121. led below the fill port scupper The oil tank is fully serviced when the ball is at the top of the glass NOTE Use oil from freshly opened cans in order to assure that uncontaminated oil is used If the oil level is below the top of the sight glass remove engine oil tank filler cap Add oil in whole quart quantities only When the floating ball reaches the top of the sight glass continue to pour in any remaining oil until the quart can is empty Do not add any more oil ae BX AIR CARD NO B767 2A PAGE 24 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 1206 10 NO 1 ENGINE AND PYLON CF6 80A SERIES NOTE Make sure you add oil slowly and carefully If you add oil into the filler cap too quickly the oil may flow out the fill port The internal self sealing valve limits the flow of oil to 1 quart 1 liter every 40 seconds at 70 F 21 C D If an excessive amount of oil is used 0 55 U S quarts per hour or more contact Maintenance Control Ref MM 71 00 00 indicating 1 Aircraft Number 2 Engine Position 3 Qty per flight hour used 4 Qty oil added Install filler cap and check for looseness and positive locking Verify the ball is at the top of the sight glass Close the engine oil servicing door on the right fan cowl panel Record OIL ADDED QUARTS in aircraft log book If no oil was added enter zero 0 Zam m 49 Service engine IDG oil leve
122. ller neck 5 Look inside the oil tank at the oil Ref Figure 8 ae BX AIR CARD NO B767 2A PAGE 32 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 NO 1 ENGINE AND PYLON PW 4000 SERTES NOTE _ If you see black oil in the oil system refer to AMM 72 00 00 601 Black oil can be an indication of a serious problem or it can be a condition that requires no maintenance action 6 If you do not see oil the oil is below the bottom of the V a With a clean screwdriver push open the valve of the filler neck b With a strong light look at the oil CAUTION DO NOT OVERFILL THE ENGINE OIL TOO MUCH OIL IN THE ENGINE COULD RESULT IN ENGINE DAMAGE c Add oil in whole quart quantities only When the oil level reaches the bottom of the V continue to pour in any remaining oil until the quart can is empty Do not add any more oil d Write down the quantity of oil added 7 If you do see oil the oil is above the bottom of the V a Do not add engine oil 8 Install the oil tank cap as follows a Do a visual inspection of the oil tank cap packing to ensure it is free of cuts and shows no evidence of deterioration b Lubricate the packing of the oil tank cap with engine oil c Turn the handle on the oil tank cap to the OPEN position with the smooth side of the handle away fro the recess d Align the lugs of the oil tank cap with the slots i
123. low the fill port scupper The oil tank is fully serviced when the ball is at the top of the glass NOTE Use oil from freshly opened cans in order to assure that uncontaminated oil is used If the oil level is below the top of the sight glass remove engine oil tank filler cap Add oil in whole quart quantities only When the floating ball reaches the top of the sight glass continue to pour in any remaining oil until the quart can is empty Do not add any more oil ae BX AIR CARD NO B767 2A PAGE 28 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 1206 10 NO 2 ENGINE AND PYLON CF6 80A SERIES NOTE Make sure you add oil slowly and carefully If you add oil into the filler cap too quickly the oil may flow out the fill port The internal self sealing valve limits the flow of oil to 1 quart 1 liter every 40 seconds at 70 F 21 C D If an excessive amount of oil is used 0 55 U S quarts per hour or more contact Maintenance Control Ref MM 71 00 00 indicating 1 Aircraft Number 2 Engine Position 3 Qty per flight hour used 4 Qty oil added Install filler cap and check for looseness and positive locking Verify the ball is at the top of the sight glass Close the engine oil servicing door on the right fan cowl panel Record OIL ADDED QUARTS in aircraft log book If no oil was added enter zero 0 Zam m 52 Service engine IDG oil level and
124. luid quantities using EICAS status display Check operation and illumination of all flight compartment lights A Urn NRS NOTE Ensure each indicator has 2 functional lamps Re lamp as necessary CAUTION DO NOT KEEP THE EMERGENCY LIGHTS ON FOR MORE THAN 1 MINUTE EXTENDED OPERATION WILL REDUCE THE CHARGE ON THE BATTERIES AND MAY RESULT IN DAMAGE 6 6 Perform a general visual inspection of flight compartment including windows for general condition cleanliness and security 7 7 Check flight compartment items for presence condition and safeties if required Ref Figure 13 88 Perform readout of the Maintenance Control Display Panel MCDP applicable for Saturday or Sunday once per week maintenance visits only 9 9 Replace the Compact Flash CF data card in the QAR at the P 61 panel Applicable to 219 315 744 and 747 at BRU CVG JFK LGG and MIA Saturday or Sunday once per week maintenance visits only 10 10 Perform APU Health Check applicable for Saturday or Sunday once per week maintenance visits only 11 11 Check that listed manuals forms and certificates are onboard the aircraft and in serviceable condition 12 12 Inspect aluminum tape on cargo compartment side of the cockpit door for condition and security Ref Figure 12 Ref AMM 11 35 02 N A to BCSF and BDSF 13 13 Test engine APU cargo squibs on squib test c
125. m you must do the troubleshooting procedure FIM 71 05 00 101 Fig 129 and flush the oil system AMM 79 11 00 301 per MPRR 35521 Page 22 deleted Item 55 B Remove engine oil tank filler cap renumbered subsequent items per MPRR 35521 Page 22 Item 55 B Note revised to read sight glass with a hollow float ball is installed below the fill port scupper The oil tank is fully serviced when the ball is at the top of the glass per MPRR 35521 Page 22 Item 55 C revised to read Tf the oil level is below the top of the sight glass remove engine oil tank filler cap Add oil in whole quart quantities only When the floating ball reaches the top of the sight glass continue to pour in any remaining oil until the quart can is empty Do not add any more oil per MPRR ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL 35521 Page 23 Item 55 C Note revised to read Make sure you add oil slowly and carefully If you add oil into the filler cap too quickly the oil may flow out the fill port The internal self sealing valve limits the flow of oil to 1 quart 1 liter every 40 seconds at 70 F 21 per MPRR 35521 Page 23 added new Item 55 E Verify the ball is at the top of the sight glass renumbered subsequent item per MPRR 35521 Page 23 Item 56 deleted 5 per MPRR 35521 Page 27 revised Item 59 and sub items regarding No 2 engine oil level an
126. m pressurized Brake wear pin limits are more restrictive than the AD Limits on the brake wear indicator pins are 1 32 with brakes parked not flush Ref Figure 1 c Measure fwd and aft brake wear indicator pins Replace brake if end of fwd or aft wear pins is 0 031 1 32 inch or less from housing sub assembly brakes parked and hydraulic system pressurized d Remove the pressure from the right hydraulic system if it is not necessary AMM 29 11 00 e Release parking brake ae BX AIR CARD NO 767 1 PAGE 7 of 14 B767 DAILY CHECK DESCRIPTION REV NO 78 DATE 10 28 10 ENGINES AND PYLONS CF6 80A SERIES 8 Perform a general visual inspection walk around check of the No 1 and No 2 engines Check engine cowling engine inlet fan rotor spinner fan rotor blades pylons open blow out doors open latches visible turbine blades and exhaust area for obvious damage and fluid leaks 9 Check the No 1 and No 2 engine oil level using EICAS and service with Turbo 2380 oil if required Ref Figure 2 An EICAS indication of 20 or more is full and oil servicing is not required NOTE When servicing the oil tank observe for odor of fuel at engine oil tank fill port If you find fuel in the oil system you must do the troubleshooting procedure FIM 71 05 00 101 Fig 129 and flush the oil system AMM 79 11 00 301 A Open the engine oil servicing door on right fan cowl p
127. mber of non metallic items such as black epoxy chips sleeving and other forms of generator insulation does not always indicate damage to the IDG 2 Check to see if the O rings or the filter is damaged This would allow contaminated oil to bypass the filter and enter the external oil cooling circuit d If no contamination is found and no condition is observed that would allow oil to bypass the filter do the following NOTE When the filter DPI has activated for the fourth time replace the IDG Ref AMM 24 11 01 1 Verify there are no IDG related EICAS or BPCU BITE messages If the EICAS or BITE messages are present take necessary corrective action If message was caused by the IDG replace the IDG Ref AMM 24 11 01 2 Reset the filter DPI e If contamination is found refer to AMM 24 11 02 for corrective action Activate thrust reverser isolation valve Ref AMM 78 31 00 ae BX AIR CARD NO B767 2A PAGE 35 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 NO 2 ENGINE AND PYLON PW 4000 SERTES 56 Perform a general visual inspection walk around check of the No 2 engine Check engine cowling engine inlet fan rotor spinner fan rotor blades pylons open blow out doors open latches visible turbine blades and exhaust area for obvious damage and fluid leaks A Check engines for fluid leaks and obvious damage B Check inlet cowl lip assembly and inner out
128. n the filler neck e Install the oil tank cap into the filler neck f Lock the oil tank cap g Apply pressure down on the oil tank cap h Turn the handle to the CLOSE position approximately 45 degrees 1 Pull up on the handle to make sure that the installation of the oil tank cap is correct G Put the handle in the recess to lock the oil tank cap k Apply pressure to the outer rim of the oil tank cap at the opposite points to make sure that the installation is correct Make sure that the oil tank cap does not move 9 Close the access door to the oil tank on the left core cowl panel 10 Make sure the EICAS oil indication is Left 24 3 Right 21 3 11 Record OIL ADDED QUARTS in aircraft log book If no oil was added enter zero 0 55 Service engine IDG oil level and check filter pop out indicator IDGs use turbo 2380 oil CAUTION DO NOT SERVICE IDG IF IDG IS DISCONNECTED DISCONNECTED IDG MUST BE REMOVED FROM THE AIRCRAFT WITHIN 50 FLIGHT HOURS NOTE Itis not required to service the IDG if Service Check is being performed on a PW 4000 equipped aircraft that has sat statically and not operated either or both engines for the previous 72 hours since last Service Check A Deactivate thrust reverser isolation valve for ground maintenance ae BX AIR CARD NO B767 2A PAGE 33 of 55 B767 SERVICE CHECK DESCRIPTION REV NO 82 DATE 12 06 10 WARNING NO 1 ENGINE AND PYLON
129. ndition and security If found unserviceable or in poor condition contact Maintenance for deferral I A W GMM Chapter 1 Section 07 04 Mechanic s Job Description Initials LAVATORY 2 2 Check lavatory Mechanic s Job Description Initials UPPER CARGO COMPARTMENT 3 3 Check the cargo compartment for general condition Mechanic s Job Description Initials AIRCRAFT GENERAL 4 4 Perform a general visual inspection walk around check of the aircraft fuselage wings and empennage sections as viewed from ground level 5 5 Check tires and wheels for wear cuts and obvious damage 6 6 Check tires for proper pressure using approved ABX tool SERVICE TIRES USING APPROVED ABX TOOL DO NOT USE AN UNREGULATED HIGH PRESSURE NITROGEN SOURCE TO SERVICE TIRES USE OF AN UNREGULATED HIGH PRESSURE NITROGEN SOURCE COULD LEAD TO EXPLOSIVE TIRE FAILURE AND POSSIBLE INJURY NOTE Required by AD 87 08 09 Service with dry nitrogen only If dry nitrogen is not available for reinflation refer to MM 12 15 03 200 COLD WARM HOT NOSE TIRES 145 150 PSI 151 160 PSI MAIN TIRES 185 190 PSI 191 200 PSI 201 205 PSI MIN 300 COLD WARM HOT NOSE TIRES 175 180 PSI 181 190PST MAIN TIRES 195 200 PSI 201 210 PSI 211 215 PSI MIN ae BX AIR CARD NO B767 1B PAGE 3 of 4 B767 DAILY CHECK SIGN OFF RECORD REV NO 78 DATE 10 28 10 AIRCRAFT NO DATE Me
130. nes Item 6 revised If both engines require oil to be added and both filler caps have been opened to If both engines require oil to be added and or both filler caps have been opened per MPRR 38604 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 78 DATED 10 28 10 B767 1A Daily Check Description B767 1B Daily Check Signoff Record B767 2A Service Check Description B767 2B Service Check Signoff Record Cards revised to delete the PC configuration and add the B767 300 BDSF with PW4000 engine configuration per MPRR 38606 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 77 DATED 10 07 10 B767 5 Card B767 JT9D PT7 Probe Cleaning deleted from manual per MPRR 38560 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 76 DATED 07 15 10 B767 2A Page 7 added new Item 7 B Check portable oxygen bottle BCSF sub item 7 B 1 and Note per MPRR 38671 B767 2B Page 3 Item 7 deleted Sheet 1 and Sheet 2 MPRR 38671 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 75 DATED 06 17 10 B767 1A Page 1 PC Package Carrier revised RH upper corner to upper corners per MPRR 38732 Page 1 25 revised RH upper corner to external
131. nly per MPRR 35521 Page 3 Item 5 M added door sills deleted ETOPS per MPRR 35521 Page 3 Item 5 N deleted ETOPS per MPRR 35521 Page 7 Item 10 revised from Service oil at No 1 and No 2 engines to maximum limits with turbo 2380 oil Ref Figure 2 ETOPS to Check the No 1 and No 2 engine oil levels and service with Turbo 2380 oil if required Ref Figure 2 per MPRR 35521 Page 7 Item 10 C deleted Fill the tank with oil until the oil overflows at the filler neck added Add oil in whole quart quantities only When the floating ball reaches the top of the sight glass continue to pour in any remaining oil until the quart can is empty Do not add any more oil per MPRR 35521 Page 7 Item 10 C Note revised to read Make sure you add oil slowly and carefully If you add oil into the filler cap too quickly the oil may flow out the fill port The internal self sealing valve limits the flow of oil to 1 quart 1 liter every 40 seconds at 70 F 21 per MPRR 35521 Page 7 added new Item 10 E Verify the ball is at the top of the sight glass renumbered subsequent item per MPRR 35521 Page 8 Item 12 deleted ETOPS per MPRR 35521 Page 10 deleted Item 13 and sub items regarding Auxiliary Power Unit per MPRR 35521 B767 1B Page 1 General Description and Operation added new Item This check includes ETOPS tasks which require Technicians to adhere to G
132. of the EICAS form is to record and collect B767 EICAS non normal fault messages along with related system BITE information and or codes Collection and analysis of the EICAS fault messages along with system BITE information and or codes will provide valuable aircraft system troubleshooting information and allow full utilization of the information provided by the EICAS system 2 The best time to retrieve the EICAS information on an impending problem is when the aircraft blocks into a gate No maintenance has been performed on the aircraft to change status and the flight crew is available to provide in flight observations 3 The EICAS form is to be used as soon as maintenance personnel can enter the flight deck upon completion of a flight The EICAS messages should be reviewed and recorded on the EICAS form The form can be left with the logbook for reference when working other items on the aircraft Also other shifts will have this information at their disposal to assist with troubleshooting Any information found as a result of investigating the EICAS message s will be added to the form before it is faxed to Maintenance Control 4 Maintenance Control will analyze the EICAS messages and codes and make follow up recommendations as required B EICAS Form Entries and Procedures 1 Enter basic form information aircraft station log page date 2 Check this box if form was not completed due to available maintenance time complete and fax form 3 C
133. ont of throttle levers Remove placard and re stow after check is complete Utilize GSE as much as possible to decrease APU operation Communicate with flight crew on arrival for any servicing or special requirements Check aircraft Log Book for pilot reports Complete B767 Daily EICAS Non Normal Fault Message Retrieval Form B767 60 Enter all discrepancies and corrective actions in Aircraft Log Book M 1A Record all non airworthy and non safety items that are found during the check on the Non Routine Work Sheet 17 If any errors are identified with a Line Maintenance Check submit a Maintenance Programs Revision Request MPRR per GMM Chap 1 Section 01 03 and forward to Maintenance Programs Any material referenced in the text or tables of the Line Maintenance Checks may be substituted in accordance with the Consumable Material Equivalents List located in Chapter 20 B767 Maintenance Manual This bullet item does not apply to AD related tasks This check includes ETOPS tasks which require Technicians to adhere to GMM 04 44 guidelines when performing maintenance on ETOPS aircraft CERTIFICATION OF AIRWORTHINESS All signoff pages of the check have been received action taken where necessary and initialed properly Aircraft Log book properly noted GMM Chapter 1 Section 04 03 Forward all sign off sheets and attach M 17 forms to Aircraft Records ILN Service Check Completed A amp P Technician signature
134. ontrol panel 14 14 Test the FUEL CONFIG Light and the LOW FUEL Message Required by AD 2010 23 03 Mechanic s Job Description Initials LAVATORY 15 15 Perform general visual inspection of lavatory ae BX AIR CARD NO B767 2B PAGE 4 of 12 B767 SERVICE CHECK SIGN OFF RECORD REV NO 82 DATE 12 06 10 AIRCRAFT DATE Mechanic s Job Description Initials SUPERNUMERARY COMPARTMENT SF CREW SERVICE AREA PC2SF AND BCSF 16 16 Visually check supernumerary crew service area ceiling and reading lights for cleanliness 17 18 19 condition and security of installation SF and PC2SF Only 17 Clean oven if installed 18 Check portable oxygen bottles SF and PC2SF Only 19 Check emergency equipment in supernumerary crew service area Ref Figure 13 ae BX AIR CARD NO B767 2B PAGE 5 of 12 B767 SERVICE CHECK SIGN OFF RECORD REV NO 82 DATE 12 06 10 AIRCRAFT DATE Mechanic s Job Description Initials UPPER CARGO COMPARTMENT NOTE Unserviceable emergency equipment must be replaced before flight or placed on deferral if allowable Ref MEL 20 20 Check sidewall lining ceiling panels and lights 21 21 Clean and vacuum compartment 22 22 Check condition of floor seat tracks and
135. quired by AD 2010 23 03 at 100 hr intervals accomplished at Service Check A Supply electrical power Refer to 767 AMM 24 22 00 as an accepted procedure B Ensure the following six EICAS circuit breakers are closed CIRCUIT BREAKER NAME PANEL LOCATION CAOT EIC AS L CMPTR uas iens PUE on J2 LOT u ne EC AS R CMPTR sangene us 29 BJ EEE EICAS DISPLAY SELECT PULS Bass 132 o snb tates EICAS DISPLAY SWITCHING 11 5 J31 or EICAS LOWER DISPLAY msn J30 BICAS UPPER PU au eis J3 C Do the test 1 Push the CAUTION Cancel button on the P1 3 Captain Instrument Panel Right to reset EICAS caution and advisory messages 2 Put the FUEL QTY test switch in the FUEL QTY position and release located on the M10398 P61 Panel 3 Make sure the FUEL CONFIG light comes on P5 Pilot s Overhead Panel 4 Make sure the LOW FUEL message shows Upper EICAS Display NOTE Ifthe test fails contact Maintenance Control Corrective action requires FAA approval before further flight NOTE Ifthe test fails troubleshoot for wire faults bent connector pins or damaged equipment Refer to Fault Isolation Manual 767 FIM 28 41 00 as an accepted procedure and to Wire Diagram Manual 767 WDM 28 41 13 for related wires ae BX AIR CARD NO B767 2A PAGE 14 of 55 B767 SERVICE CHECK DESCRIPT
136. r flight except as authorized in specific aircraft Minimum Equipment List MEL B Check that 2 ea fire extinguisher nozzles are unobstructed by tape or liner panels along the upper corner on the left side wall of the forward and aft compartments AD 08 13 04 NA N315AA 32 Check condition and cleanliness of interior lining thresholds door barriers restraining equipment nets stanchions and doors Pay particular attention to holes in lining and sharp edges which could cause personal injury or damage to baggage A Repair liners using AKRO Fireguard Repair Kit AF888 or by replacing the entire fiberglass panel Repair formed cargo liner panels and detail features using Kit AF400 The repair kits are located at each ABX B767 outbase station NOTE Use oldest kits first AF400 or AF888 as determined by expiration date at top of kit label 33 Check that all blow out panels are in place 34 Check operation of cargo compartment lights Replace bulbs as necessary 35 Check that drain holes are unobstructed NOTE Drains are openings in the structure located in the lower fwd and aft corners of the door jambs 36 Remove all foreign matter from cargo compartment door jambs 37 Check fwd and aft cargo compartments cargo loading system for general condition and cleanliness ae BX AIR CARD NO B767 2A PAGE 19 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 AIRCR
137. r signs of distress n Examine the main landing gear doors and linkage Look for distortion cracks and other signs of distress 4 Examine the nose and the engine for foreign object damage Reference SRM 54 10 00 for allowable damage limits a If engine bird ingestion suspected perform Engine Foreign Object Damage Inspection in accordance with B767 FIM 71 05 00 2 Do the reactivation procedure for the leading edge slat system AMM 27 81 00 201 3 Do the reactivation procedure for the trailing edge flap system AMM 27 51 00 201 RETURN COMPLETED FORM TO RECORDS BUILDING 2061 R wtf B767 50 Page 1 of 2 BX AIP DATE 02 11 04 B767 APU ECU FUNCTION ADJUSTMENT SWITCHES SETTINGS ECU TO BE INSTALLED ON THE AIRCRAFT This form provides instructions to change the ECS Switch settings on the B767 APU ECU from the original factory settings to the revised Airborne Express settings This form is to be accom plished when ECU is installed on an aircraft INSTALLED ECU NOTE If time does not permit the switch setting adjustment defer this Form B767 50 for tracking IAW ABX GMM Section 07 04 for tracking to be completed at the next con venient maintenance opportunity 1 Record ECU S N Record ECU P N 2 Remove the ECS switch cover 5 captive screws so that the function adjust switches S1 through S8 can be accessed Reference Honeywell CMM 49 61 26 Figure 103 Sheet 2 3 Change the
138. raft that do not transit an operations hub forward to Aircraft Records ILN renumbered subsequent items MPRR 38732 Page 14 added new Item 17 D Check that 1 ea ash tray is installed in receptacle on exterior lavatory compartment wall next to lavatory door AD 74 08 09 R2 SF and PC2SF per MPRR 38732 Page 17 added new Item 30 A Check that 1 ea ash tray is installed in receptacle on exterior lavatory compartment wall next to lavatory door AD 74 08 09 R2 renumbered subsequent item per MPRR 38732 Page 17 Item 34 revised Volumes 1 2 3 4 and 5 to all volumes per MPRR 38732 Page 19 added new Item 39 B Check that 2 ea fire extinguisher nozzles are unobstructed by tape or liner panels along the upper corner on the left side wall of the forward and aft compartments AD 08 13 04 NA N315AA per MPRR 38732 B767 2B Page 1 Total Sign Off Pages revised from 10 to 11 Page 1 PC Package Carrier revised upper corner to upper corners per MPRR 38732 Page 1 PC2SF revised RH upper corner to external upper corners per MPRR 38732 Page 2 revised title of section from FLIGHT COMPARTMENT to ABBREVIATED SERVICE CHECK per MPRR 38732 NOTE Item 1 and sub items are now ABBREVIATED SERVICE CHECK Items 2 through 12 are now FLIGHT COMPARTMENT Page 2 Item 1 revised document accomplishment of Service Check with log boo
139. rd to station stock after upload is completed E CVG JFK and MIA 1 COMAT or overnight ship removed Compact Flash card to ABX Engineering ILN 2061 R 10 Comply with APU Health Check and record on APU Health Check form B767 40 located in the B767 Blank Forms Manual applicable for Saturday or Sunday once per week maintenance visits only A APU Control Unit Self Test 1 Supply electrical power AMM 24 22 00 201 a Ensure the following circuit breaker on the overhead circuit breaker panel P11 is closed 1 11B35 APU ALTN CONT b Ensure the APU control switch on the P5 overhead panel is OFF and attach a DO NOT OPERATE tag c Ensure the APU RPM is less than 7 d Put the TEST switch on the APU control unit in the LAMP position and release the switch 1 Ensure all of the lights come on column by column 2 If all of the lights do not come on replace the APU control unit WARNING DO NOT DO THE ECU BITE TEST AND MAINTENANCE ON THE IGNITION SYSTEM AT THE SAME TIME THE IGNITER LEAD ENERGIZES DURING THE SELF TEST AND CAN CAUSE AN INJURY e Put the TEST switch to the SELF position and release the switch NOTE This will do a test of the software in the APU control unit and of the APU hardware 1 The WAIT light will come on during the test 2 The TEST OK light will come on if the self test does not find defective units 3 Make a record of the FAULTY LRU lights that come on NOTE The FAULTY LRU lig
140. re installed on the wheels 3 Release the parking brake B Procedure CAUTION BE VERY CAREFUL WHEN YOU DO A CHECK OF THE BRAKES TO NOT SPILL HYDRAULIC BRAKE FLUID ON THE BRAKE LININGS IF YOU SPILL BRAKE FLUID ON THE BRAKE LININGS THE BRAKES WILL NOT OPERATE CORRECTLY 1 Pressurize the right hydraulic system and reservoir AMM 29 11 00 201 2 Fully apply and release the left and right Captain s or First Officer s brake pedals five times 3 With the brake pedals not applied do a check of the brakes for fluid leaks at these locations a Brake pistons b Brake housing plugs c Inlet and drain ports d Bleed ports e All hydraulic line connections 4 If the total leakage per brake at the above locations is greater than one 1 drop per minute with the brake pedals not applied repair the leaks or replace the brake prior to dispatch 5 Slowly apply the brake pedals to the stops 6 While the brake pedals are applied do a check for leaks at the same places on the brake that you did in Step 3 7 If the total leakage per brake at the above locations is greater than five 5 drops per minute while the brakes are being applied repair the leakage or replace the brake prior to dispatch 8 Brakes with leaks below these limits must be rechecked prior to each flight and should be repaired or replaced at the next opportunity that manpower and material allow ae BX AIR CARD NO 767 2 PAGE 2
141. tamination is found refer to AMM 24 11 02 for corrective action Activate thrust reverser isolation valve Ref AMM 78 31 00 ae BX AIR CARD NO B767 2A PAGE 27 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 12 06 10 NO 2 ENGINE AND PYLON CF6 80A SERIES 50 Perform general visual inspection walk around check of the No 2 engine Check engine cowling engine inlet fan rotor spinner fan rotor blades pylons open blow out doors open latches visible turbine blades and exhaust area for obvious damage and fluid leaks A Check engines for fluid leaks and obvious damage B Check inlet assembly and inner outer panels for security condition and damage C Check inlet cone fan blades and annulus fillers for security condition and damage D Check fan duct and cold stream duct thrust reverser blocker doors and acoustic panels for security condition and damage E Check core engine exhaust area including turbine blades for condition and damage F Check engine pylons for fluid leaks and obvious damage 51 Check the No 2 engine oil level using EICAS and service with Turbo 2380 oil if required Ref Figure 5 An EICAS indication of 20 or more is full and oil servicing is not required NOTE Itis not required to service the engine oil if Service Check is being performed on CF6 80A equipped aircraft that has sat statically and not operated either or both engin
142. tation door is secured K Check the positive pressure relief valves for FLAG indication that valves have opened L Check fuselage exterior skin doors door sills and door seals as viewed from the ground for condition and obvious damage M Check tail skid indicator for evidence of tail strike 300 only N Visually check lower cargo compartment linings to verify integrity of compartment sealings 5 Check tires and wheels for wear cuts and obvious damage NOTE wheels removed for low pressure should be returned to ABX ILN Please note the following information on the parts tag Tire removed due to LOW PRESSURE and actual tire pressure gauge reading when removed NOTE Interior grooves are those exclusive of the grooves in or adjacent to the shoulder areas A Replace tire when any portion of an interior tread groove is worn away completely around the visible portion of the circumference OR when the fabric reinforcing ply is exposed NOTE Excessive wear past the fabric reinforcing plies could make the tire non re treadable When tire is worn to limits and requires replacement but circumstances do not permit replacement may be deferred provided the following conditions are met 1 No more than 5 additional landings are made 2 No peeling or chunking of the tire exists and no carcass plies are exposed 3 Item is forwarded as a Deferred Item with an entry in the Aircraft Log Book to monitor landings and
143. ted more than 10 PSI an Aircraft Log Book entry is required 2 If pressure is 10 20 PSI below the lower limit of the applicable inflation range service tire to the upper limit of the inflation range and make an entry into the Aircraft Log Book If log book indicates previous history of under inflation for 3 or more days tire must be replaced 3 If pressure is more than 20 PSI below limits the tire must be replaced prior to further flight 4 Replace both tires on the same axle if the aircraft is taxied with tire deflated more than 35 PSI below limits or wheel bearing failure Removal of the adjacent tire is not required if the tire deflates while aircraft is parked or under tow 5 Adjacent tire replacement may be deferred if circumstances do not permit provided the following conditions are met NOTE Tires with excessive heat will be too hot to comfortably leave your hand in the shoulder area a No more than 5 additional landings are made b Tire is visually inspected for signs of damage excessive heat bulges leakage or other unusual conditions prior to each flight c Tire pressure is checked and properly serviced d Item is forwarded as a Deferred Item with an entry in the Aircraft Log Book to monitor landings and tire condition per items a and b above e Advise Maintenance Control of requirement to replace deferred tire within 5 landings ae BX AIR CARD NO B767 1A PAGE 5 of 14
144. th engines for the previous 72 hours since last Service Check NOTE Lubricating oil for the engine is replenished through the engine oil tank filler port Servicing should be accomplished within 30 minutes of engine shutdown for consistent results If after 30 minutes operate the engines until the rpm is stable Ref AMM 71 00 00 20 NOTE When servicing the oil tank observe for odor of fuel at engine oil tank fill port If you find fuel in the oil system you must do the troubleshooting procedure FIM 71 05 00 101 Fig 129 and flush the oil system AMM 79 11 00 301 A Open the engine oil servicing door on right fan cowl panel WARNING WAIT A MINIMUM OF 5 MINUTES AFTER ENGINE IS SHUT DOWN BEFORE REMOVING FILLER CAP TO ALLOW TANK PRESSURE TO BLEED OFF HOT OIL GUSHING FROM TANK COULD CAUSE SEVERE BURNS IF FILLER NECK FLOAT VALVE IS DISPLACED BEFORE PRESSURE DISSIPATES B Check oil level as indicated by the hollow float ball in the sight glass LUBRICATING OILS CONTAIN ADDITIVES WHICH ARE READILY ABSORBED THROUGH THE SKIN AND ARE CONSIDERED TOXIC AVOID PROLONGED OR CONTINUOUS CONTACT OF LUBRICATING OIL WITH SKIN CAUTION IF INADVERTENTLY SERVICED WITH DISSIMILAR FLUIDS SUCH AS MIL L 6081 FLUSHING OIL OR HYDRAULIC FLUID DO NOT OPERATE ENGINE UNTIL A COMPREHENSIVE EVALUATION OF EFFECTS ON OIL SYSTEM AND ENGINE IS PERFORMED AND CORRECTIVE ACTION IS COMPLETED NOTE A sight glass with a hollow float ball is instal
145. ting retainer Also ensure they are not broken B Examine the dischargers for damage as shown by a burned and roughened coating Also look for pitted metal discharger retainers C Examine the dischargers for broken bent or blunted tungsten pins Bent pins must be made straight D Look for erosion of the discharger coating or peeling of the tip cup The leading edge erosion of the discharger must not extend back more than 1 3 of the width of the discharger E Do aresistance test if a damaged static discharger is found Ref 23 61 01 11 Aircraft Internal Examination A If a lightning strike has caused a system malfunction do a full examination of the defective system Use the applicable maintenance manual section for that system Do a check of the standby compass system only if the flight crew found a very large compass deviation AMM 34 23 00 201 Ensure that the fuel quantity system is accurate If it is not do a check of the applicable tank units and compensator AMM 28 41 00 501 ae CARD NO B767 9 BX AIP PAGE 4 of 6 B767 LIGHTNING STRIKE CHECKLIST DATE 10 06 06 ITEM ACCOMP NO DESCRIPTION BY 12 Inspection and Operational Check of Radio and Navigation Systems General 1 The radio and navigation systems must have a full examination after the aircraft was hit by lightning The examination is also necessary after heavy static discharger The level of the inspect
146. tion is acceptable if consumption is not more than 0 5 U S quarts per hour Ref MM 71 00 00 If excessive amount of ae BX AIR CARD NO B767 2A PAGE 1 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 1206 10 NOTE Service Check is accomplished in accordance with the Description on this Form 767 2 and documented on Sign Off Form B767 2B Configuration Designations Identifiable Features PC2SF B767 200 Package Carrier Converted to an IAI Special Freighter Main Deck Cargo Door Door Locked external view ports are functional A protective impact doubler is installed on the external upper corners of the L1 Door cutout The supernumerary seat is in the cockpit SF B767 200 IAI Special Freighter Main Deck Cargo Door Door Locked external view ports are functional The supernumerary seat is between the cockpit and smoke barrier BCSF B767 200 Boeing Converted Special Freighter Main Deck Cargo Door Door Locked external view ports cannot be used and are covered with Do Not Remove decals Lavatory is in the cockpit BDSF 767 300 Special Freighter Main Deck Cargo Door Door Locked external view ports are functional Airplane has a tail skid Lavatory is in the cockpit ABBREVIATED SERVICE CHECK 1 If the aircraft has sat statically the main engines have not been operated and less than 72 hours have elapsed since the last full
147. ts from the flight before the last flight the same way as the Last Flight Fault messages were shown The same messages for all previous faults shown and no previous faults are shown as applicable The Previous Flight Faults gives historical flight data Faults from up to 99 flights are kept in the MCDP unless more than 10 flight have had faults Faults for a specified flight are kept together and given a number 02 two flights before 05 5 flights before etc Flight numbers are left off if the flight had no faults 1 To show Subsequent Previous Flight Faults push the YES ADV switch a BX AIR CARD NO B767 2A PAGE 10 of 55 REV NO 82 B767 SERVICE CHECK DESCRIPTION DATE 1206 10 FLIGHT COMPARTMENT 9 Replace the Compact Flash CF data card in the QAR at the P 61 panel Applicable to 219 315 744 and 747 at BRU CVG JFK LGG and MIA Saturday or Sunday once per week maintenance visits only A Obtain 1 each P N SDCFX3 002G A21 Compact Flash card from station stock B Locate microQAR reader installed in the Flight Recorder System Test Plug on the P 61 panel Remove Compact Flash card from microQAR recorder and install card obtained from station stock D BRU and LGG stations with upload capability 1 Upload data from removed Compact Flash card using Polaris Transfer program and card reader installed on station computer Ref Polaris Transfer Program User Manual 2 Return Compact Flash ca
148. ure ae BX AIR CARD NO B767 2A PAGE 2 of 55 B767 SERVICE CHECK DESCRIPTION REV NO 82 DATE 12 06 10 ABBREVIATED SERVICE CHECK L Check main hydraulic system reservoir quantity M Check NLG strut height and tire pressure N Check each engine fire extinguishing discharge light is not illuminated O Sump fuel tanks checking for water and sediments Ensure all access doors panels and cowlings are closed and secured Q Check that the aircraft log book has been properly cleared signed and that the inspection has been entered Check that non routine items generated are corrected R Remove external APU power from the aircraft S Check APU oil quantity if APU has been operated since the last service check T Stow Maintenance In Work placard in F O s seat back pocket NOTE Utilize GSE as much as possible to decrease APU operation Communicate with flight crew arrival for any servicing or special requirements Check aircraft Log Book for pilot reports Enter all discrepancies and corrective actions in Aircraft Log Book M 1A Record all non airworthy and non safety items that are found during the check on the Non Routine Work Sheet M 17 ae BX AIR CARD NO B767 2A PAGE 3 of 55 B767 SERVICE CHECK DESCRIPTION REV NO 82 DATE 12 06 10 FLIGHT COMPARTMENT Perform an EICAS maintenance message read out and record in
149. urity A Check Aircraft Logbook for pilot reports B Remove completed Engine Trend Monitoring Reports from the binder at the operations hub Aircraft that do not transit an operations hub forward to Aircraft Records ILN Visually check cockpit windows for cracks crazing and delamination Ref 56 11 00 for limitations D Check spare bulb supply and presence of the thrust reverser isolation valve deactivation pins 2 ea P N B78001 3 replenish as necessary E Check for presence and condition of headsets 3 ea Clean cockpit windows G Clean flight compartment 1 Trash 2 Glareshield 3 Ashtrays and cup holders 4 Floor tracks 5 Instrument panels H Saturday AM Service Check 1 Ensure all trash and debris is removed 2 Vacuum the entire cockpit ae BX AIR CARD NO B767 2A PAGE 7 of 55 B767 SERVICE CHECK DESCRIPTION REV NO 82 DATE 12 06 10 FLIGHT COMPARTMENT 3 Clean all cockpit windows sun visors and glareshield 4 Clean dust vacuum all cockpit instruments and pedestal areas Check flight compartment items for presence condition and safeties if required NOTE Unserviceable emergency equipment must be replaced before flight Replace any equipment found with a broken seal NOTE If there are any bottles with less than ninety 90 days until the expiration date replace the bottle If there is not an adequate supply of bottl
150. vice Area PC2SF per MPRR 36166 Page 3 Item 12 added crew service and added PC2SF per MPRR 36166 Page 3 Item 14 added service MPRR 36166 Page 4 Item 23 added and PC2SF per MPRR 36166 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 65 DATED 06 24 09 B767 2A Page 11 Item 14 D added and demonstration life vest 1 ea per MPRR 36216 Page 13 revised Item 25 B 6 a regarding Weight and Balance Computer program version number per MPRR 36102 Page 54 revised illustration Flight Deck Emergency Equipment SF Configured Aircraft Figure 13 Sheet 2 of 2 per MPRR 36216 ae BX AIR REVISION HIGHLIGHTS B767 LINE MAINTENANCE FORMS MANUAL REVISION 64 DATED 04 21 09 B767 2A Page 25 No 1 Engine and Pylon CF6 80A Series deleted Item 57 Check engine master chip detector for metal Ref Figures 7 and 8 renumbered subsequent items per MPRR 35591 Page 29 No 2 Engine and Pylon CF6 80A Series deleted Item 60 Check engine master chip detector for metal Ref Figures 7 and 8 renumbered subsequent items per MPRR 35591 Page 47 deleted Figure 7 CF6 80A Series Engines Magnetic Chip Detector Locations page now This Figure Intentionally Left Blank per MPRR 35591 Page 48 deleted Figure 8 CF6 80A Series Engines MCD Data Retrieval pa
151. w sayndwos SVOI3 peuoje sese 14 seu peal saye eBed SSW S23 ALA peuoje saseg peKejdsip si SAQoedsel USYM 5104 deus yenuew pue ojne 25213 YIJME 291 JO jaued 013400 ejdsip lt pioa BuisseJd Arowew ui PAYNE Si deus 1 HO Jamoj UO po ejdsip Auauno 9114 34 JO pauoje Sey MOLA JO no peseiq s xoq Ul soDessau PUB s Bess tu pos poKejdsip st 9SW S93 USYM O LIA payoje siE29 189 Jamoj uo pakeldsip Aqueuno OLIN 20 sjue e OPNE SEIH YS SY31 94 uo po ejdsip Apuauno 1 OLN 94 JO jous deus 1 e 5 102 dua Jo peads uleyeo U9UA je S RJdSIP peoJ U 039 Ye eyep N Jusuno YIM Suge 1 2 1 4 pue Bua euim jea sKejdsig Nowe u PSYDJE YOIUM sapos ynejep uy Aejdsip us ned 1591 39 si pue pub uo SI OY USYM 159 19 SYOI3 ue sejeniu 919A ulead USYM 1u9S91d siajowesed je sKejdsip oye Ul ej
152. y fro the recess d Align the lugs of the oil tank cap with the slots in the filler neck e Install the oil tank cap into the filler neck f Lock the oil tank cap g Apply pressure down on the oil tank cap h Turn the handle to the CLOSE position approximately 45 degrees i Pull up on the handle to make sure that the installation of the oil tank cap is correct 0 Put the handle in the recess to lock the oil tank cap k Apply pressure to the outer rim of the oil tank cap at the opposite points to make sure that the installation is correct Make sure that the oil tank cap does not move Close the access door to the oil tank on the left core cowl panel Make sure the EICAS oil indication is Left 24 3 Right 21 3 Record OIL ADDED QUARTS in aircraft log book If no oil was added enter zero 0 ae BX AIR CARD NO B767 1A PAGE 11 of 14 REV NO 78 B767 DAILY CHECK DESCRIPTION DATE 10 28 10 BRAKE WEAR LIMITS ARE MORE RESTRICTIVE THAN THE AD LIMITS ON PRESSURE PLATE THE BRAKE WEAR INDICATOR PINS ARE 1 32 WITH BRAKES PARKED NOT FLUSH WEAR INDICATOR PIN PISTON HOUSING 003698 NOTE Replace brake if end of fwd or aft wear indicator pins are 0 031 1 32 inch or less with brakes parked and hydraulic system pressurized BRAKE INDICATOR PIN LIMIT FIGURE 1 ae BX AIR CARD NO B767 1A PAGE 12 of 14 REV NO 78 B767 DAILY CHECK DESCRIPTION D

B767 LINE MAINTENANCE FORMS MANUAL

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