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# SERIES 200 

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# 31 August 2007

AWL 5 − Fuel System Limitations

FILING INSTRUCTIONS:

This Temporary Revision supercedes TR AWL 2−42. Remove the TR AWL 2−42 from the PART 2

Airworthiness Limitations, AWL 5 − Fuel System Limitations Section, and insert this new Temporary Revision.

REASON FOR ISSUE:

Revises the Part 2 Airworthiness Limitations, AWL 5 − Fuel System Limitations Section NOTE1

and NOTE2.

ACTION:

Use the Fuel System Limitations as given in this Temporary Revision.

RECORDING INSTRUCTIONS.

Record this T emporary Revision No. and the relevant information in the appropriate columns of the

TEMPORARY REVISIONS INDEX at the front of PART 2, PSM 1−82−7.

# PSM 1−82−7 Temporary Revision No. AWL 2−43 (Cont’d)



# SERIES 200 

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# FUEL SYSTEM LIMITATIONS

, 

# INTRODUCTION

This section lists the Fuel System Limitations (FSL) that are mandated by the Special Federal Aviation Regulation (SFAR) 88.

FSLs are limitation requirements that identify all the necessary maintenance and inspection instructions to maintain the design features required to preclude the existence or development of an ignition source within the fuel tank system throughout the operational life

of the aircraft.

, 

# RULES APPLICABLE TO FUEL SYSTEM LIMITATIONS

A. No person may operate an aircraft unless instructions for maintenance and inspection

of the fuel tank system are incorporated into the operator’s maintenance program.

B. Task intervals are provided in both flight hours and calendar intervals. Tasks are to be

performed at whichever interval occurs first.

, 

# PAGE FORMAT DESCRIPTION

The Fuel System Limitations (FSL) are presented in the following format:



# 	   ;<

Task Number Applicability Task Description Interval

A B C D

A. Task Number : Task reference number.

B. Applicability: “All” is for all aircraft. A Modsum and/or Service Bulletin may be

listed to identify the FSL as it applies to the aircraft configuration.

C. Task Description : Brief description of the task to be done.

D. Interval : Calculated limiting interval.PSM 1−82−7 Temporary Revision No. AWL 2−43 (Cont’d)SERIES 200FUEL SYSTEM LIMITATIONS (FSL)Task NumberApplicabilityTask DescriptionIntervalFSL−01AllDetailed Inspection of the Flap Shroud Lightning Strips.6,000 flight hours or 36 monthsNOTE1FSL−02Standard Fuel TankConfigurationwithService Bulletin8−57−44orModsum 8Q101514Detailed Inspection of the Fuel Tank Bonding Jumpers.18,000 flight hours or 108 monthsNOTE2Long Range FuelTank ConfigurationwithService Bulletin8−28−39orModsum 8Q902090APU Fuel TankBonding JumperswithService Bulletin8−28−44orModsum 8Q902140FSL−03AllFunctional Check of the Flap Shroud Lightning StripsElectrical Bonding.18,000 flight hours or 108 monthsNOTE2PSM 1−82−7 Temporary Revision No. AWL 2−43 (Cont’d)SERIES 200
FUEL SYSTEM LIMITATIONS (FSL)Task NumberApplicabilityTask DescriptionIntervalFSL−04AllDetailed Inspection of the Fuel Tank Water Drain ValveDomed Nut.18,000 flight hours or 108 monthsNOTE2FSL−05AllFunctional Check of the Fuel Tank Water Drain ValveElectrical Bonding.18,000 flight hours or 108 monthsNOTE2FSL−06Standard Fuel TankConfigurationDetailed Inspection of the Fuel Tank Scavenge andVent Line Wiggins Fittings.18,000 flight hours or 108 monthsNOTE2FSL−07AllFunctional Check of the Dielectric Properties of the Aluminum Loaded Primer and Enamel on the Wing Skin.18,000 flight hours or 108 monthsNOTE2FSL−08AllFunctional Check of the Magnetic Dipstick ElectricalBonding.18,000 flight hours or 108 monthsNOTE2FSL−09AllFunctional Check of the Auxiliary Fuel Boost PumpElectrical Bonding.18,000 flight hours or 108 monthsNOTE2FSL−10AllDetailed Inspection of the Fuel Tank Ladder Plate toAccess Panel Interface and the Ladder Plate Seals.18,000 flight hours or 108 monthsNOTE2FSL−11AllDetailed Inspection of the Fuel Quantity Gauging Wiring Harness Metal Overall Shield.6,000 flight hours or 36 monthsNOTE1FSL−12AllFunctional Check of the Fuel Quantity Gauging WiringHarness Metal Overall Shield Electrical Bonding.18,000 flight hours or 108 monthsNOTE2FSL−13AllFunctional Check of the Fuel Quantity Gauging WiringHarness Aluminum Support Conduit Electrical Isolation.18,000 flight hours or 108 monthsNOTE2PSM 1−82−7 Temporary Revision No. AWL 2−43 (Cont’d)SERIES 200FUEL SYSTEM LIMITATIONS (FSL)Task NumberApplicabilityTask DescriptionIntervalFSL−14Standard Fuel TankConfigurationwithService Bulletin8−28−37orModsum 8Q101527Detailed Inspection of the Fuel Tank Fuel QuantityGauging Wiring Harness Outside of the Aluminum Support Conduit.18,000 flight hours or 108 monthsNOTE2Long Range FuelTank ConfigurationwithService Bulletin8−28−40orModsum 8Q902123PSM 1−82−7 Temporary Revision No. AWL 2−43 (Cont’d)SERIES 200FUEL SYSTEM LIMITATIONS (FSL)Task NumberApplicabilityTask DescriptionIntervalFSL−15Standard Fuel TankConfigurationwithPre Service Bulletin8−28−37orPre Modsum8Q101527Discard the Fuel Tank Fuel Quantity Gauging Wire Harness (without Kynar sleeving)18,000 flight hours or 108 monthsNOTE2Long Range FuelTank ConfigurationwithPre Service Bulletin8−28−40orPre Modsum8Q902123PSM 1−82−7 Temporary Revision No. AWL 2−43 (Cont’d)SERIES 200FUEL SYSTEM LIMITATIONS (FSL)Task NumberApplicabilityTask DescriptionIntervalFSL−16Standard Fuel TankConfigurationwithService Bulletin8−28−37orModsum 8Q101527Discard the Fuel Tank Fuel Quantity Gauging Wire Harness (with Kynar sleeving)72,000 flight hours or 36 yearsLong Range FuelTank ConfigurationwithService Bulletin8−28−40orModsum 8Q902123PSM 1−82−7 Temporary Revision No. AWL 2−43 (Cont’d)SERIES 200!!!"#$%Task NumberApplicabilityTask DescriptionIntervalFSL−17Standard Fuel TankConfigurationwithService Bulletin8−57−44orModsum 8Q101514Functional Check of the Fuel Tank Components andthe Plumbing Lines Electrical Bonding.18,000 flight hours or 108 monthsNOTE2Long Range FuelTank ConfigurationwithService Bulletin8−28−39orModsum 8Q902090APU InstallationwithService Bulletin8−28−44orModsum 8Q902140PSM 1−82−7 Temporary Revision No. AWL 2−43 (Cont’d)SERIES 200&!!!"#$%Task NumberApplicabilityTask DescriptionIntervalFSL−18Service Bulletin8−57−44orModsum 8Q101514Functional Check of the Pressure Relief Valve Electrical Bonding.18,000 flight hours or 108 monthsNOTE2NOTE1: For aircraft that haveexceeded the task interval, this task to be incorporated within 2,000 flight hours or 12 months whicheveroccurs first as tracked from the release date of this Temporary Revision AWL 2−43. The phase−in time of an AirworthinessDirective (AD) will take precedence over this phase−in time.NOTE2: For aircraft that have exceeded 12,000 flight hours or 72 months, this task to be incorporated within 6,000 flight hoursor 36monthswhichever occurs first as tracked from the release date ofthis Temporary Revision AWL2−43. The phase−intime of anAirworthiness Directive (AD) will take precedence over this phase−in time.PSM 1−82−7 Temporary Revision No. AWL 2−43 (Cont’d)SERIES 200THIS PAGE INTENTIONALLY LEFT BLANK