Document ID: chunk:federal_register_of_legislation:F2011L01845:body:0:p2
Version: federal_register_of_legislation:F2011L01845
Segment Type: other
Provision Reference: 
Character Range: 4637–7743

on any aeroplane in any pump position as a replacement part, unless the assembly has been inspected since the most recent assembly of the end cap motor-impeller housing (whether during manufacture, after maintenance or inspection, or after overhaul) using X-ray methods to ensure that the wire bundle is properly routed in the pump in accordance with Boeing ASB
                     737-28A1197 or Crane Hydro-Aire SB Crane Hydro-Aire
                     Motor-Impeller-28-01, including Appendix A.
                   3. Remove the Requirement 1.b. AFM revision and the Requirement 1.c. placard.
                Note 1:  Requirement 3 is optional terminating actions for the fuel usage restrictions at Requirements 1.b and c.
                Note 2:  FAA AD 2002-19-52 Amdt 39-12900 refers.
Compliance:     For Requirement 1 - Within 14 days after the effective date of this Amendment.

                Despite the new AD/B737/198 Amdt 2, an exclusion or alternate method of compliance that was in force before the coming into effect of AD/B737/198 Amdt 2 continues to be in force.
                For Requirement 2 - As of the effective date of this Amendment.
                For Requirement 3 - When all fuel pumps for the centre wing tank, horizontal stabilizer tank, centre auxiliary tanks, together with auxiliary fuel tanks 1 and 4 on an aeroplane have been inspected using X-ray methods in accordance with Boeing ASB 737-28A1197 or Crane Hydro-Aire SB Crane Hydro-Aire Motor-Impeller-28-01, including Appendix A.
                Inspection of a pump by Crane Hydro-Aire before the effective date of the original issue of this Directive is considered equivalent to an inspection performed in accordance with Crane Hydro-Aire SB Crane Hydro-Aire Motor-Impeller-28-01, including Appendix A.

                Inspection of a pump in accordance with Boeing ASB 737-28A1197 or Crane Hydro-Aire SB Crane Hydro-Aire Motor-Impeller-28-01, including Appendix A, before the effective date of the original issue of this Directive is acceptable for removal of the AFM revision and placard.

                Date remains unchanged to that detailed in Amendment 1 of this Directive.
                This Amendment becomes effective on 30 September 2011.
Background:     The United States Federal Aviation Administration (FAA) has received reports indicating that fuel pumps on Boeing Model 737, 747 and 757 series aeroplanes have failed as a result of chafing of the stator lead wire bundle.  This occurred when the stationary wire bundle came into contact with the rotor in the pump motor.  The pumps failed when the pump power was short-circuited to the rotor and the circuit protection device tripped.
                Examination of failed pumps showed that arcing had occurred in the pump bearings both inside and outside of the explosion-proof cavity of the pump.  Such arcing could result in an ignition source in the fuel tank.  The fuel pump failures have been attributed to the manufacturing assembly process during which the stator lead wire bundle was improperly installed and positioned in the end