MAINTENANCE REQUIREMENTS MANUAL

AIRWORTHINESS LIMITATION ITEMS

Ja

Pa

TEMPORARY REVISION ALI−112

Ref #: 84ALI_110_R 5−1 CDCCL

Date.............................. Signed.....................

The contents of this Temporary Revision have been approved by the Chief, Engineering, National Aircraft Certification B

31 Dec 2010

FILING INSTRUCTIONS: This Temporary Revision revises PSM 1−84−7 Maintenance Requirements Manual, A

Part 2, Section 5−1, Critical Design Configuration Control Limitations. Put this Temporary 

1.This Temporary Revision replaces Temporary Revision ALI−104. Remove Temporary R

date removed on the RECORD OF TEMPORARY REVISIONS sheet at the front of PRecord this Temporary Revision number and the date inserted, on the RECORD OF TE

at the front of Part 2, of this manual.Keep this Temporary Revision until the normal revision service puts this informRequirements Manual or the TR is cancelled.

REASON FOR ISSUE: This Temporary Revision revises Section 5−1, Critical Design Configuration Control Lim

Updates the Effectivity information for the entry “Fuel vent lines Teflon protective sleeve 

text “or Post Modsum 4−110139” to the Applicability column). This Temporary Revision 

for “Fuel tank lines Teflon protective sleeve inside the fuel tank and isolation of lines froshown with revision bars.Replaced TR ALI−104 was issued previously to update the Effectivity information for bracket fillet sealant and dome sealed attachment hardware, Sta. YW 42.000” (in App“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 

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MAINTENANCE REQUIREMENTS MANUAL

AIRWORTHINESS LIMITATION ITEMS

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Pa

CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL Description Design Feature to be 

Maintained

Manual Reference 

Fuel 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 1−84−2 Maintenance Manual, Part 2

Chapter 28Fuel System Limitation − Detailed Inspection of the Metal Overall Shield on the Fuel Quantity Gauging SystemFuel System Limitation − Functional Check of the Fuel Quantity Metal Overall Shield for Electrical Bonding

PSM 1−84−4 Illustrated Parts Catalogue,

Chapter 24, Section 00Harness, Electrical − Wing

PSM 1−84−2W Wiring Diagram Manual,

Chapter 28, Section 40Fuel Indicating System

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MAINTENANCE REQUIREMENTS MANUAL

AIRWORTHINESS LIMITATION ITEMS

Ja

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CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL Description Design Feature to be 

Maintained

Manual Reference 

Fuel tank plumbing lines,self bonding couplings,conductive fittings and 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 1−84−2 Maintenance Manual, Part 2

Chapter 28, Section 12 Vents,Section 21 Engine Fuel Feed, Section 23 Fuel Transfer, Section 24 Refuel/Defuel, Section 40 IndicationFuel System Limitation − Detailed Inspection of the Self Bonding Couplings Inside the Fuel TankFuel System Limitation − Functional Check of the Self Bonding Couplings, Conductive Fittings and Fuel Tank Components for Electrical Bonding

PSM 1−84−4 Illustrated 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 Indicating

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MAINTENANCE REQUIREMENTS MANUAL

AIRWORTHINESS LIMITATION ITEMS

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CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL Description Design Feature to be Manual Reference 

Maintained

APU 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 1−84−2 Maintenance Manual, Part 2

Section 22 APU Fuel FeedFuel System Limitation − Detailed Inspection of the Self Bonding Couplings Inside the Fuel TankFuel System Limitation − Functional Check of the Self Bonding Couplings, Conductive Fittings and Fuel Tank Components for Electrical Bonding

PSM 1−84−4 Illustrated Parts Catalogue,

Section 22 APU Fuel System

Sealant 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 1−84−2 Maintenance Manual, Part 2

Chapter 51, Section 23 SealantFuel System Limitation − Detailed Inspection of the Sealant Around the Anchor Nuts at Access Panels,Sta. YW 42.000 to YW 191.200

PSM 1−84−3 Structural Repair Manual

Chapter 57, Section 25 Main Fuel Tanks

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MAINTENANCE REQUIREMENTS MANUAL

AIRWORTHINESS LIMITATION ITEMS

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CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL Description Design Feature to be Manual Reference 

Maintained

Fuel 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 1−84−3 Structural Repair Manual

Chapter 57, Section 25 Main Fuel TanksFuel System Limitation − Detailed Inspection of the Access Panel to Wing Skin Mating Surfaces and Access Panel Gasket, Sta. YW 191.200 to YW 425.019

Fuel 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 − Detailed Inspection of the Low Level Float Switch Harness Inside the Fuel Tank

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MAINTENANCE REQUIREMENTS MANUAL

AIRWORTHINESS LIMITATION ITEMS

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CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL Description Design Feature to be Manual Reference 

Maintained

Fuel 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 − Detailed Inspection of the Dome Nut on the Fuel Tank Water Drain ValveFuel System Limitation − Functional Check of the Fuel Tank Water Drain Valve For Electrical Bonding

PSM 1−84−4 Illustrated Parts Catalogue,

Chapter 28, Section 11 Fuel System

Fuel vent lines Teflon protective 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 − Detailed Inspection of the Teflon Sleeve on the Fuel Tank Vent Line

PSM 1−84−4 Illustrated Parts Catalogue,

Chapter 28, Section 12 Fuel Vents

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MAINTENANCE REQUIREMENTS MANUAL

AIRWORTHINESS LIMITATION ITEMS

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CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL Description Design Feature to be Manual Reference 

Maintained

Fuel 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 the W12 and W13 Harnesses Under the Cabin Floor, Between the Sidewall and the Fuel Quantity Computer, Sta. X371.15EWIS − Detailed Inspection of the W12 and W13 Harnesses on the Passenger Cabin Sidewall, Sta. X361.00EWIS − Detailed Inspection of the W12 and W13 Harnesses at the Cabin Roof, Sta. X361.00

PSM 1−84−2W Wiring Diagram Manual,

Chapter 28, Section 40Fuel Indicating System

High 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 24 Sensor, High LevelFuel System Limitation − Detailed Inspection of the High Level Sensor Harness Inside the Fuel Tank

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MAINTENANCE REQUIREMENTS MANUAL

AIRWORTHINESS LIMITATION ITEMS

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Pa

CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL Description Design Feature to be Manual Reference 

Maintained

Fuel 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 40 IndicatingFuel System Limitation − Detailed Inspection of the Fuel Probe Harness Inside the Fuel Tank

Fuel 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 be intact.

PSM 1−84−2 Maintenance Manual, Part 2, 

Chapter 28Fuel System Limitation − Detailed Inspection of the Sealant on the Vent Line Support Bracket and Attachment Hardware, Sta. YW 42.000

Wide 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 1−84−1A Airplane Flight Manual, 

Section 2.5.2 Fuel

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MAINTENANCE REQUIREMENTS MANUAL

AIRWORTHINESS LIMITATION ITEMS

Ja

Pa

CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL Description Design Feature to be Manual Reference 

Maintained

Fuel vent lines Teflon protective 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 − Detailed 

Inspection of the Teflon Sleeve on the Fuel Tank Lines and Clearances Between Fuel Lines and Structure

PSM 1−84−4 Illustrated Parts Catalogue,

Chapter 28

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