Document ID: chunk:federal_register_of_legislation:F2007L02358:body:0:p2
Version: federal_register_of_legislation:F2007L02358
Segment Type: other
Provision Reference: 
Character Range: 6082–14981

1, dated 20 November 2003
   747-400 and 747-400F                                                                                                                                                                                                                                                                              747-31A2342, Revision 1, dated 20 November 2003

   747-400 and 747-400F

   Note 2:  Each ASB identified in Table 4 refers to Rockwell Collins SB
   IDS-7000-31-46, IDS-7000-31-47 or IDS-7000-31-48; all dated 22 April 2003; as applicable; as an additional source of service information for installing the IDS-503 software.
   Installing IDS-505 or IDS-506 software during production of the aeroplane is acceptable for compliance with Requirement 1.  Additionally, installing IDS-506 software as a retrofit in accordance with the applicable SB identified in Table 5, is acceptable for compliance with Requirement 1.
   Table 5
   747 Series Aeroplanes                                                                                                                                                                                                                                                                             Boeing SB

   747-400, 747-400D and 747-400F                                                                                                                                                                                                                                                                    747-31-2376, dated 5 September 2006
   747-400 and 747-400F                                                                                                                                                                                                                                                                              747-31-2377, dated 5 September 2006
   747-400 and 747-400F                                                                                                                                                                                                                                                                              747-31-2378, dated 5 September 2006
   Note 3:  Each SB identified in Table 5 refers to Rockwell Collins SB IDS-7000-31-52, IDS-7000-31-53 or IDS-7000-31-54; all dated 30 August 2006; as applicable; as an additional source of service information for installing the IDS-506 software.

      2. For aeroplanes on which FR-HiTEMP fuel pumps have been installed in accordance with Boeing SB 747-28-2258, dated 19 December 2003, or Revision 1, dated 11 August 2005 or during production - Remove the ground wire of the wire integration unit that corresponds to the connector and pin locations in Table 6, in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA.  Chapter 20-41-03 of the Boeing 747-400 Aircraft Maintenance Manual is one approved method.
   Table 6
            Connector                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              Pin

   L-EIU DM7353CA                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              G13
   C-EIU DM7352CA                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              G13
   R-EIU DM7351CA                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              G13
      3. Except as specified in Requirement 4, revise the Limitations section of the Aircraft Flight Manual (AFM) to include the information at Annex A to this Directive.
      4. For aeroplanes on which FR-HiTEMP fuel pumps have been installed in accordance with SB 747-28-2258, original issue or Revision 1, or during production - Revise the Limitations section of the AFM to include the information at Annex A to this Directive.
   Amendment of the AFM may be accomplished by inserting a copy of Annex A to this Directive into the AFM.
      5. Remove the AFM amendments specified in the Airworthiness Directives identified in Table 7.
      Table 7
      Directive                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   Requirement     Equivalent FAA AD

        AD/B747/270                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1               2001-12-21 Amdt 39-12277
       AD/B747/188 Amdt 3                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      4               2001-21-07 Amdt 39-12478
       AD/B747/280                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2               2002-19-52 Amdt 39-12900
       AD/B747/283                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             Not Applicable  2002-24-52 Amdt 39-12993
   Later revisions of the above SBs, approved by the United States Federal Aviation Administration (FAA) as an Alternate Method of Compliance (AMOC) to FAA AD 2007-13-14, are considered acceptable for compliance with the equivalent Requirements of this Directive.
   Note 4:  FAA AD 2007-13-04 Amdt 39-15108 refers.

Compliance:  For Requirement 1 - Within six months after the effective date of this Directive.