Document ID: chunk:federal_register_of_legislation:F2006B03176:body:0:p2
Version: federal_register_of_legislation:F2006B03176
Segment Type: other
Provision Reference: 
Character Range: 3112–6271

60B92603-26
                                60-98976-4           60B89004-15
Model 747-400, -400D, and -     60-98976-4           60B89004-15
400F series                     60-72101-4           60B92603-26

5.        Fuel pump motor- impeller assembly having any part number may not be installed 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 747-28A2248 or Crane Hydro-Aire SB Crane Hydro-Aire Motor-Impeller-28-01, including Appendix A.

6.        Remove the Requirement 2 AFM revision and the Requirement 3 placards.

7.        Remove the Requirement 3.c. placard

           Note 1: Requirements 6 and 7 are optional termination actions for the fuel usage restrictions at Requirement 2 and 3.

           Note 2: FAA AD 2002-19-52 Amdt 39-12900 refers.

 Compliance: For Requirement 1 - Within 14 days after the effective date of this Directive.

           For Requirement 2 - Concurrent with Requirement 1.

           For Requirement 3 - Within 14 days after the effective date of this Directive. For Requirement 4 - As of the effective date of this Directive.
           For Requirement 5 - Within 14 days after the effective date of this Directive.

           For Requirement 6 - 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 747-28A2248 or Crane Hydro-Aire SB Crane Hydro-Aire Motor-Impeller-28-01, including Appendix A.

           For Requirement 7 - When both horizontal stabilizer tank pumps have been inspected using X-ray methods in accordance with Boeing ASB 747-28A2248 or Crane Hydro- Aire SB Crane Hydro-Aire Motor-Impeller-28-01, including Appendix A.

           For Requirement 6 and 7:

           Inspection of a pump by Crane Hydro-Aire before the effective date 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 747-28A2248 or Crane Hydro- Aire SB Crane Hydro-Aire Motor-Impeller-28-01, including Appendix A, before the effective date of this Directive is acceptable for removal of the AFM revision and placard.

           This Airworthiness Directive becomes effective on 3 October 2002.

           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.