!

"#$%$%&	%"'&()**+,'&'$",$))*,-+%"."'	/$'$*'$/0%'$1

'*#*	%.*%'	'#%'$2*$#"/*$&)*%.$-

3% !'$- 
 2 

 

4$ %" 5'$%$$# **( 5$61 7!5 
8 *%  '*9*%"'$&& '('%%'$&/ *(, %" ():

**+ ,'&'$    	*( %" !#%'$    61 !+&%( '('%%'$& $- '$&*% %"'& $9 ():

**+ ,'&'$

#*- %"'& ()**+ ,'&'$ 0 $- %" *1,$% '$	*(%'$ '$ %" ))*)*'% #16($& 	 %" 5:

;< =4!4;0! 403> % %" 	*$% 	  / !5 


	  	

,'&& %" 61 !+&%(& '('%%'$& 7!8 & 	119&

 (,& *	*$#& % !*,'# 2611%'$& '$ %" ))1'#'1'%+ #16($/

 ,'&& 5-&6(& '$ %" ))1'#'1'%+ #16($/

 ,'&& 0; $- -1%& 0; -6 % %" *1& 	 '*9*%"'$&& 3'*#%', . 9"'#"

%?& )*#-$#

"'& ()**+ ,'&'$ *)1#&       9& '&&6- )*,'6&1+ % *,'& %" !

0; $- 0;

()**+ ,'&'$    9& *)1#- +       9& '&&6- )*,'6&1+ %

-- %" %&?& ! $- !
 $- % *,'& %" ! 0;

()**+ ,'&'$    9& *)1#- +       9& '&&6- )*,'6&1+ %

-- %" %&?& ! $- ! %"*6 !
 $- % *,'& %" 4$%*-6#%'$

()**+ ,'&'$    9& *)1#- +   @   @ 9& '&&6- )*,'6&1+ %

-- %" %&? !

()**+ ,'&'$   @ 9& *)1#- +   
   
 9& '&&6- )*,'6&1+ %

-- %" %&? !

()**+ ,'&'$   
 9& *)1#- +   
   
 9& '&&6- )*,'6&1+ %

'$%*-6# %" 61 !+&%( '('%%'$& '$% %"'& ($61 & ($-%- + %" !)#'1 -*1 ,'%'$ 61:

%'$ 7!8 

 $- % -- %" %&? !



A& %" .*'%'#1 3&'$ .$	'6*%'$& .$%*1 '('%%'$& & ',$ '$ %"'& ()**+ ,'&'$
	 



		 
   	  

	







		

	
 	  

 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:

A !<!5 4544;0! 7!8

Task Number Applicability Task Description Interval

A B C D

A. Task Number: Task reference number.

B. Applicability: “All” is for all aircraft. A Mod or Modsum 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.
	 

		 
   	  

		  

	
 	  

FUEL SYSTEM LIMITATIONS (FSL)

Task Number Applicability Task Description 

FSL−01 All Detailed Inspection of the Flap Shroud Lightning Strips. 6,000 flight hFSL−02 Standard Fuel Tank

Configuration

with

Modsum

8Q101512

or 8Q101514

Detailed Inspection of the Fuel Tank Bonding Jumpers. 18,000 flight h

Long Range Fuel

Tank Configuration

with

Modsum

8Q902090

or

8Q902091

or

8Q902177
	 

		 
   	  

		  

	
 	  

FUEL SYSTEM LIMITATIONS (FSL)

Task Number Applicability Task Description 

FSL−02

(Cont’d)

APU Fuel Tank

Bonding Jumpers

with

Modsum

8Q902140

or

8Q902144

Detailed Inspection of the Fuel Tank Bonding Jumpers. 18,000 flight h

FSL−03 All Functional Check of the Flap Shroud Lightning Strips

Electrical Bonding.

18,000 flight h

FSL−04 All Detailed Inspection of the Fuel Tank Water Drain Valve

Domed Nut.

18,000 flight h

FSL−05 All Functional Check of the Fuel Tank Water Drain Valve

Electrical Bonding.

18,000 flight h

FSL−06 All Detailed Inspection of the Fuel Tank Scavenge and

Vent Line Wiggins Fittings.

18,000 flight h

FSL−07 All Functional Check of the Dielectric Properties of the Aluminum Loaded Primer and Enamel on the Wing Skin. 18,000 flight hFSL−08 All Functional Check of the Magnetic Dipstick Electrical

Bonding.

18,000 flight h
	 

		 
   	  

		  

	
 	  

FUEL SYSTEM LIMITATIONS (FSL)

Task Number Applicability Task Description 

FSL−09 All Functional Check of the Auxiliary Fuel Boost Pump

Electrical Bonding.

18,000 flight h

FSL−10 All Detailed Inspection of the Fuel Tank Ladder Plate to

Access Panel Interface and the Ladder Plate Seals.

18,000 flight h

FSL−11 All Detailed Inspection of the Fuel Quantity Gauging Wiring Harness Metal Overall Shield. 6,000 flight h

FSL−12 All Functional Check of the Fuel Quantity Gauging Wiring

Harness Metal Overall Shield Electrical Bonding.

18,000 flight h

FSL−13 All Functional Check of the Fuel Quantity Gauging Wiring

Harness Aluminum Support Conduit Electrical Isolation.

18,000 flight h

FSL−14 Standard Fuel Tank

Configuration

with

Modsum

8Q101527

Detailed Inspection of the Fuel Tank Fuel QuantityGauging Wiring Harness Outside of the Aluminum Support Conduit.

18,000 flight h

Long Range Fuel

Tank Configuration

with

Modsum

8Q902123
	 

		 
   	  

		  

	
 	  

FUEL SYSTEM LIMITATIONS (FSL)

Task Number Applicability Task Description 

FSL−15 Standard Fuel Tank

Configuration

Pre Modsum

8Q101527

Discard the Fuel Tank Fuel Quantity Gauging Wire Harness (without Kynar sleeving) 18,000 flight h

Long Range Fuel

Tank Configuration

Pre Modsum

8Q902123

FSL−16 Standard Fuel Tank

Configuration

with

Modsum

8Q101527

Discard the Fuel Tank Fuel Quantity Gauging Wire Harness (with Kynar sleeving) 72,000 fligh

Long Range Fuel

Tank Configuration

with

Modsum

8Q902123
	 

		 
   	  

		  

	
 	  

  !!!"# $%

Task Number Applicability Task Description 

FSL−17 Standard Fuel Tank

Configuration

with

Modsums

8Q101512

and

8Q101865

or 8Q101514

Functional Check of the Fuel Tank Components andthe Plumbing Lines Electrical Bonding.

18,000 flight h

Long Range Fuel

Tank Configuration

with

Modsum

8Q902090

or

8Q902091

and

8Q101865

or 8Q902177

APU Installation

with

Modsum

8Q902140

or 8Q902144
	 

		 
   	  

		  

	
 	  

  !!!"# $%

Task Number Applicability Task Description 

FSL−18 with

Modsums

8Q101514

or

8Q902090

Functional Check of the Pressure Relief Valve Electrical Bonding. 18,000 flight h

NOTE1: For aircraft retrofited by modsum, if the FSL task has not already been performed, then this task is to be p

flight hours or 36 months whichever occurs first as tracked from the release date of this Temporary Retime of an Airworthiness Directive (AD) will take precedence over this phase−in time.