MAINTENANCE REQUIREMENTS MANUALAIRWORTHINESS LIMITATION ITEMS**Jan 11/2011 ALI−112** **Page 1 of 9**TEMPORARY REVISION ALI−112Ref #: 84ALI_110_R 5−1 CDCCLDate..............................Signed.....................................The contents of this Temporary Revision have been approved by the Chief, Engineering, National Aircraft Certification Branch, Transport Canada31 Dec 2010**FILING INSTRUCTIONS:**This Temporary Revision revises PSM 1−84−7 Maintenance Requirements Manual, Airworthiness Limitation ItemsPart 2,Section 5−1, Critical Design Configuration Control Limitations. Put this Temporary Revision in front of 5−1, page1.This Temporary Revision replaces Temporary Revision ALI−104. RemoveTemporary Revision ALI−104and enter thedate removed on the RECORD OF TEMPORARY REVISIONS sheet at the front of Part 2, of this manual.Recordthis Temporary Revision number and the date inserted, on the RECORD OF TEMPORARY REVISIONS pageat the front of Part 2, of this manual.Keep this Temporary Revision until the normal revision service puts this information into the MaintenanceRequirements Manual or the TR is cancelled.**REASON FOR ISSUE:**This Temporary Revision revises Section 5−1, Critical Design Configuration Control Limitations (CDCCL), as follows:Updatesthe Effectivity information for the entry “Fuel vent lines Teflon protective sleeve inside the fuel tank” (adds thetext“or Post Modsum 4−110139” to the Applicability column).This Temporary Revision also adds a new CDCCL entryfor “Fuel tank lines Teflon protective sleeve inside the fuel tank and isolation of lines from aircraft”. The changes areshown with revision bars.Replaced TR ALI−104 was issued previously to update the Effectivity information for the entry “Fuel tank vent linebracket fillet sealant and dome sealed attachment hardware, Sta. YW 42.000” (in Applicability column, deleted text“or Post Modsum 4−113523”), also added an entry for wide cut fuel.**ACTION:**Ignore the existing Section 5−1 and substitute this Section 5−1 as shown on pages 2 to 9 of this TR:TEMPORARYREVISIONTEMPORARYREVISION	
MAINTENANCE REQUIREMENTS MANUALAIRWORTHINESS LIMITATION ITEMS**Jan 11/2011 ALI−112** **Page 2 of 9**CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONSCDCCL DescriptionDesign Feature to beMaintainedManual ReferenceApplicabilityFuel quantity gauging metaloverall shield between thefuselage disconnect andthe fuel tank penetration.To provide lightning protection, metal overall shield tobe free of damage and corrosion. Metal overall shieldto be electrically bonded tothe aircraft structure at bothextremities of the cable harness.PSM 1−84−2Maintenance Manual, Part 2Chapter 28Fuel System Limitation − DetailedInspection of the Metal OverallShield on the Fuel QuantityGauging SystemFuel System Limitation −Functional Check of the FuelQuantity Metal Overall Shield forElectrical BondingPSM 1−84−4Illustrated Parts Catalogue,Chapter 24, Section 00Harness, Electrical − WingPSM 1−84−2W Wiring Diagram Manual,Chapter 28, Section 40Fuel Indicating SystemAllTEMPORARYREVISIONTEMPORARYREVISION	
MAINTENANCE REQUIREMENTS MANUALAIRWORTHINESS LIMITATION ITEMS**Jan 11/2011 ALI−112** **Page 3 of 9**CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONSCDCCL DescriptionDesign Feature to beMaintainedManual ReferenceApplicabilityFuel tank plumbing lines,self bonding couplings,conductive fittings andmetal to metal interfaceelectrical bonding of fueltank components.To provide electrostatic andlightning protection, fueltank plumbing lines andcomponents must be electrically bonded with conductive fittings and metal tometal conductive finishes.PSM 1−84−2Maintenance Manual, Part 2Chapter 28, Section 12 Vents,Section 21 Engine Fuel Feed,Section 23 Fuel Transfer,Section 24 Refuel/Defuel,Section 40 IndicationFuel System Limitation − DetailedInspection of the Self BondingCouplings Inside the Fuel TankFuel System Limitation −Functional Check of the SelfBonding Couplings, ConductiveFittings and Fuel TankComponents for ElectricalBondingPSM 1−84−4Illustrated Parts Catalogue,Chapter 28, Section 11 FuelSystem, Section 12 Fuel Vents,Section 21 Engine Fuel Feed,Section 23 Fuel Transfer,Section 24 Refuel/Defuel,Section 40 IndicatingFor non−APU lines,couplings and fittings:Modsum 4−126330orModsum 4−126336TEMPORARYREVISIONTEMPORARYREVISION	
MAINTENANCE REQUIREMENTS MANUALAIRWORTHINESS LIMITATION ITEMS**Jan 11/2011 ALI−112** **Page 4 of 9**CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONSCDCCL DescriptionApplicabilityManual ReferenceDesign Feature to beMaintainedAPU fuel tank plumbinglines, self bonding couplings, conductive fittingsand metal to metal interfaceelectrical bonding of fueltank components.To provide electrostatic andlightning protection, fueltank plumbing lines andcomponents must be electrically bonded with conductive fittings and metal tometal conductive finishes.PSM 1−84−2Maintenance Manual, Part 2Section 22 APU Fuel FeedFuel System Limitation − DetailedInspection of the Self BondingCouplings Inside the Fuel TankFuel System Limitation −Functional Check of the SelfBonding Couplings, ConductiveFittings and Fuel TankComponents for ElectricalBondingPSM 1−84−4Illustrated Parts Catalogue,Section 22 APU Fuel SystemFor APU lines, couplingsand fittings:Modsum 4−901425orModsum 4−901423Sealant around fuel tankaccess panel anchor nuts(Sta. YW 42.000 to YW191.200).To provide lightning protection, sealant covering baseof anchor nuts and attachment rivets to be intact.PSM 1−84−2Maintenance Manual, Part 2Chapter 51, Section 23 SealantFuel System Limitation − DetailedInspection of the Sealant Aroundthe Anchor Nuts at Access Panels,Sta. YW 42.000 to YW 191.200PSM 1−84−3Structural Repair ManualChapter 57, Section 25 Main FuelTanksAllTEMPORARYREVISIONTEMPORARYREVISION	
MAINTENANCE REQUIREMENTS MANUALAIRWORTHINESS LIMITATION ITEMS**Jan 11/2011 ALI−112** **Page 5 of 9**CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONSCDCCL DescriptionApplicabilityManual ReferenceDesign Feature to beMaintainedFuel tank access panel towing skin mating surfacesand access panel gasket(Sta. YW 191.200 to YW425.019).To provide lightning protection, specified interfaces ofthe wing skin and fuel access cover to be finishedwith chemical conversioncoating for electrical bonding (no other finishes permitted), and an insulatinggasket installed on the access panel.PSM 1−84−3Structural Repair ManualChapter 57, Section 25 Main FuelTanksFuel System Limitation − DetailedInspection of the Access Panel toWing Skin Mating Surfaces andAccess Panel Gasket,Sta. YW 191.200 to YW 425.019AllFuel low level float switchwire harness inside the fueltank.To prevent fretting and tomaintain wire integrity, specified segments of the fuellow level float switch wireharness to be containedwithin the protective sleeveand wire harness supports.PSM 1−84−2 Maintenance Manual, Part 2,Chapter 28, Section 40 Switch,FloatFuel System Limitation − DetailedInspection of the Low LevelFloat Switch Harness Inside theFuel TankModsum 4−126370orModsum 4−126336TEMPORARYREVISIONTEMPORARYREVISION	
MAINTENANCE REQUIREMENTS MANUALAIRWORTHINESS LIMITATION ITEMS**Jan 11/2011 ALI−112** **Page 6 of 9**CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONSCDCCL DescriptionApplicabilityManual ReferenceDesign Feature to beMaintainedFuel tank water drain valvemetal to metal interface anddome nut.To provide lightning protection, specified interfaces ofthe drain valve and thewing skin to be finishedwith chemical conversioncoating for electrical bonding (no other finishes permitted), and the drain valveto be installed with an internal non−metallic dome nut.PSM 1−84−2 Maintenance Manual, Part 2,Chapter 28, Section 11 Fuel TanksFuel System Limitation − DetailedInspection of the Dome Nut on theFuel Tank Water Drain ValveFuel System Limitation −Functional Check of the Fuel TankWater Drain Valve For ElectricalBondingPSM 1−84−4Illustrated Parts Catalogue,Chapter 28, Section 11Fuel SystemAllFuel vent lines Teflonprotective sleeve inside thefuel tank.To maintain electrical isolation of the aircraft vent linefrom aircraft structure, thefuel vent line Teflon protective sleeves to be intact andfree of damage.PSM 1−84−2 Maintenance Manual, Part 2,Chapter 28, Section 12 VentsFuel System Limitation − DetailedInspection of the Teflon Sleeve onthe Fuel Tank Vent LinePSM 1−84−4Illustrated Parts Catalogue,Chapter 28, Section 12 Fuel VentsModsum 4−113299orModsum 4−121195orModsum 4−110139TEMPORARYREVISIONTEMPORARYREVISION	
MAINTENANCE REQUIREMENTS MANUALAIRWORTHINESS LIMITATION ITEMS**Jan 11/2011 ALI−112** **Page 7 of 9**CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONSCDCCL DescriptionApplicabilityManual ReferenceDesign Feature to beMaintainedFuel quantity wire harnessin the center fuselage andthe high level sensor wireharness in the center fuselage and along the rearspar.To prevent ignition source,both the fuel quantity wiringharness and the high levelsensor wire harness to becontained within protectivesleeving and segregatedfrom other aircraft wiring.PSM 1−84−2 Maintenance Manual, Part 2,Chapter 05EWIS − Detailed Inspection of theW12 and W13 Harnesses Underthe Cabin Floor, Between the Sidewall and the Fuel QuantityComputer, Sta. X371.15EWIS − Detailed Inspection of theW12 and W13 Harnesses on thePassenger Cabin Sidewall,Sta. X361.00EWIS − Detailed Inspection of theW12 and W13 Harnesses at theCabin Roof, Sta. X361.00PSM 1−84−2W Wiring Diagram Manual,Chapter 28, Section 40Fuel Indicating SystemModsum 4−126366orModsum 4−126333High level sensor wireharness inside the fueltank.To prevent fretting and tomaintain wire integrity, specified segments of the highlevel sensor wire harnessto be contained within protective sleeving and wireharness supports.PSM 1−84−2 Maintenance Manual, Part 2,Chapter 28, Section 24Sensor, High LevelFuel System Limitation − DetailedInspection of the High LevelSensor Harness Inside the FuelTankModsum 4−126370orModsum 4−126336TEMPORARYREVISIONTEMPORARYREVISION	
MAINTENANCE REQUIREMENTS MANUALAIRWORTHINESS LIMITATION ITEMS**Jan 11/2011 ALI−112** **Page 8 of 9**CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONSCDCCL DescriptionApplicabilityManual ReferenceDesign Feature to beMaintainedFuel quantity gauging wireharness inside the fueltank.To prevent fretting and tomaintain wire integrity, specified segments of the fuelquantity gauging wire harness to be contained withinprotective sleeving and wireharness supports.PSM 1−84−2 Maintenance Manual, Part 2,Chapter 28, Section 40IndicatingFuel System Limitation − DetailedInspection of the Fuel ProbeHarness Inside the Fuel TankModsum 4−126370orModsum 4−126336Fuel tank vent line bracketfillet sealant and domesealed attachment hardware, Sta. YW 42.000.To provide electrical bonding of vent line to supportbracket, sealant coveringbracket hardware to beintact.PSM 1−84−2 Maintenance Manual, Part 2,Chapter 28Fuel System Limitation − DetailedInspection of the Sealant on theVent Line Support Bracket andAttachment Hardware, Sta. YW42.000Modsum 4−126330orModsum 4−122242Wide cut fuel CGSB 3.22 orASTM−D1655 Jet B orMIL−DTL−5624 JP−4.Only post Modsum4−113538 (PWC SB 35189)aircraft may use wide cuttype fuel. Dispatch withwide cut type fuel is prohibited with an outside air temperature (OAT) or static airtemperature (SAT) warmerthan −20C.PSM 1−84−1AAirplane Flight Manual,Section 2.5.2 FuelModsum 4−113538(PWC SB 35189)TEMPORARYREVISIONTEMPORARYREVISION	
MAINTENANCE REQUIREMENTS MANUALAIRWORTHINESS LIMITATION ITEMS**Jan 11/2011 ALI−112** **Page 9 of 9**CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONSCDCCL DescriptionApplicabilityManual ReferenceDesign Feature to beMaintainedFuel vent lines Teflonprotective sleeve inside thefuel tank and isolation oflines from aircraft.To maintain electrical isolation of the aircraft fuel linesfrom aircraft structure, thefuel line Teflon protectivesleeves to be intact andfree of damage and ensureminimum fuel line separation from aircraft structureand other fuel lines.PSM 1−84−2 Maintenance Manual, Part 2,Chapter 28Fuel System Limitation −DetailedInspection of the Teflon Sleeve on theFuel Tank Lines and ClearancesBetween Fuel Lines and StructurePSM 1−84−4Illustrated Parts Catalogue,Chapter 28Modsum 4−113643TEMPORARYREVISIONTEMPORARYREVISION