<table cellspacing="0" cellpadding="0" style="width:510.3pt; margin-top:0pt; margin-bottom:0pt; border-collapse:collapse"><tbody><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>Applicability:</span></p></td><td colspan="2" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>Boeing 747 series aeroplanes identified in the Boeing Alert Service Bulletins (ASB) listed in Table 1.</span></p></td></tr><tr style="height:12.75pt"><td rowspan="2" style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="2" style="width:414.55pt; border-bottom:0.75pt solid #000000; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="text-align:center"><span style="font-weight:bold">Table 1</span></p></td></tr><tr style="height:12.75pt"><td style="width:164.75pt; border:0.75pt solid #000000; padding-right:4.97pt; padding-left:4.97pt; vertical-align:top"><p style="margin-bottom:12pt; text-align:center"><span style="font-weight:bold">747 Series Aeroplanes</span></p><p style="margin-top:12pt"><span>747-400, 747-400D and 747-400F</span><br><span>747-400 and 747-400F</span><br><span>747-400 and 747-400F</span></p></td><td style="width:239.1pt; border:0.75pt solid #000000; padding-right:4.97pt; padding-left:4.97pt; vertical-align:top"><p style="margin-bottom:12pt; text-align:center"><span style="font-weight:bold">Boeing ASB</span></p><p style="margin-top:12pt"><span>747-31A2351, Revision 1, dated 17 March 2005</span><br><span>747-31A2350, Revision 1, dated 17 March 2005</span><br><span>747-31A2352, Revision 1, dated 17 March 2005</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>Requirement:</span></p></td><td colspan="2" style="width:414.55pt; border-top:0.75pt solid #000000; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="margin-left:21.3pt; text-indent:-21.3pt"><span>1.</span><span style="width:12.3pt; text-indent:0pt; display:inline-block"> </span><span>Install new IDS-504 software in the integrated display units and electronic flight instrument system/engine indication and crew alerting system interface units of the flight deck, in accordance with the Accomplishment Instructions of the applicable ASB identified in Table 2.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="2" style="width:414.55pt; border-bottom:0.75pt solid #000000; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="text-align:center"><span style="font-weight:bold">Table 2</span></p></td></tr><tr><td style="width:74.35pt; border-right:0.75pt solid #000000; padding-right:4.97pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td style="width:164.75pt; border:0.75pt solid #000000; padding-right:4.97pt; padding-left:4.97pt; vertical-align:top"><p style="margin-bottom:12pt; text-align:center"><span style="font-weight:bold">747 Series Aeroplanes</span></p><p style="margin-top:12pt"><span>747-400, 747-400D and 747-400F</span><br><span>747-400 and 747-400F</span><br><span>747-400 and 747-400F</span></p></td><td style="width:239.1pt; border:0.75pt solid #000000; padding-right:4.97pt; padding-left:4.97pt; vertical-align:top"><p style="margin-bottom:12pt; text-align:center"><span style="font-weight:bold">Boeing ASB</span></p><p style="margin-top:12pt"><span>747-31A2351, Revision 1, dated 17 March 2005</span><br><span>747-31A2350, Revision 1, dated 17 March 2005</span><br><span>747-31A2352, Revision 1, dated 17 March 2005</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p class="Note"><span></span></p></td><td colspan="2" style="width:414.55pt; border-top:0.75pt solid #000000; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p class="Note"><span>Note 1</span><span>:</span><span> </span><span>Each ASB identified in Table 2 refers to Rockwell Collins Service Bulletin (SB) IDS-7000-31-49, IDS-7000-31-50 or IDS-7000-31-51; all dated 28</span><span> </span><span>June</span><span> </span><span>2004; as applicable; as an additional source of service information for installing the new IDS software.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="2" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>Installing new IDS-504 software before the effective date of this Directive, in accordance with the applicable ASB identified in Table 3 or during production of the aeroplane, is acceptable for compliance with Requirement 1.</span></p></td></tr></tbody></table>
<table cellspacing="0" cellpadding="0" style="width:510.3pt; margin-top:0pt; margin-bottom:0pt; border-collapse:collapse"><tbody><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="4" style="width:414.55pt; border-bottom:0.75pt solid #000000; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="text-align:center"><span style="font-weight:bold">Table 3</span></p></td></tr><tr><td style="width:74.35pt; border-right:0.75pt solid #000000; padding-right:4.97pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td style="width:164.75pt; border:0.75pt solid #000000; padding-right:4.97pt; padding-left:4.97pt; vertical-align:top"><p style="margin-bottom:12pt; text-align:center"><span style="font-weight:bold">747 Series Aeroplanes</span></p><p style="margin-top:12pt"><span>747-400, 747-400D and 747-400F</span><br><span>747-400 and 747-400F</span><br><span>747-400 and 747-400F</span></p></td><td colspan="3" style="width:239.1pt; border:0.75pt solid #000000; padding-right:4.97pt; padding-left:4.97pt; vertical-align:top"><p style="margin-bottom:12pt; text-align:center"><span style="font-weight:bold">Boeing ASB</span></p><p style="margin-top:12pt"><span>747-31A2351, dated 3 September 2004</span><br><span>747-31A2350, dated 3 September 2004</span><br><span>747-31A2352, dated 3 September 2004</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="4" style="width:414.55pt; border-top:0.75pt solid #000000; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>For aeroplanes not equipped with a horizontal stabiliser tank (HST) - Installing</span><br><span>IDS-503 software before the effective date of this Directive, in accordance with the applicable ASB identified in Table 4, is acceptable for compliance with Requirement1.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="4" style="width:414.55pt; border-bottom:0.75pt solid #000000; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="text-align:center"><span style="font-weight:bold">Table 4</span></p></td></tr><tr><td style="width:74.35pt; border-right:0.75pt solid #000000; padding-right:4.97pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="2" style="width:186.05pt; border:0.75pt solid #000000; padding-right:4.97pt; padding-left:4.97pt; vertical-align:top"><p style="margin-bottom:12pt; text-align:center"><span style="font-weight:bold">747 Series Aeroplanes</span></p><p style="margin-top:12pt"><span>747-400, 747-400D and 747-400F</span><br><br><span>747-400 and 747-400F</span><br><br><span>747-400 and 747-400F</span><br><span></span></p></td><td colspan="2" style="width:217.8pt; border:0.75pt solid #000000; padding-right:4.97pt; padding-left:4.97pt; vertical-align:top"><p style="margin-bottom:12pt; text-align:center"><span style="font-weight:bold">Boeing ASB</span></p><p style="margin-top:12pt"><span>747-31A2340, Revision 1, dated 20</span><span> </span><span>November</span><span> </span><span>2003</span><br><span>747-31A2341, Revision 1, dated 20</span><span> </span><span>November</span><span> </span><span>2003</span><br><span>747-31A2342, Revision 1, dated 20</span><span> </span><span>November</span><span> </span><span>2003</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p class="Note"><span></span></p></td><td colspan="4" style="width:414.55pt; border-top:0.75pt solid #000000; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p class="Note"><span>Note 2: </span><span></span><span>Each ASB identified in Table 4 refers to Rockwell C</span><span>ollins SB</span><br><span>IDS-7000-31-46, IDS-</span><span>7000-31-47 </span><span>or IDS-7000-31-48; all dated 22 </span><span>April</span><span> </span><span>2003; as applicable; as an additional source of service information for installing the IDS-503 software.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="4" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>Installing IDS-505 or IDS-506 software during production of the aeroplane is acceptable for compliance with Requirement 1.</span><span> </span><span>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.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="4" style="width:414.55pt; border-bottom:0.75pt solid #000000; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="text-align:center"><span style="font-weight:bold">Table 5</span></p></td></tr><tr><td style="width:74.35pt; border-right:0.75pt solid #000000; padding-right:4.97pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="3" style="width:201.9pt; border:0.75pt solid #000000; padding-right:4.97pt; padding-left:4.97pt; vertical-align:top"><p style="margin-bottom:12pt; text-align:center"><span style="font-weight:bold">747 Series Aeroplanes</span></p><p style="margin-top:12pt"><span>747-400, 747-400D and 747-400F</span><br><span>747-400 and 747-400F</span><br><span>747-400 and 747-400F</span></p></td><td style="width:201.95pt; border:0.75pt solid #000000; padding-right:4.97pt; padding-left:4.97pt; vertical-align:top"><p style="margin-bottom:12pt; text-align:center"><span style="font-weight:bold">Boeing SB</span></p><p style="margin-top:12pt"><span>747-31-2376, dated 5 September 2006</span><br><span>747-31-2377, dated 5 September 2006</span><br><span>747-31-2378, dated 5 September 2006</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p class="Note"><span></span></p></td><td colspan="4" style="width:414.55pt; border-top:0.75pt solid #000000; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p class="Note"><span>Note 3:</span><span> </span><span>Each SB identified in Table 5 refers to Rockwell Collins SB IDS-7000-31-52, IDS-7000-31-53 </span><span>or IDS-7000-31-54; all dated 30 </span><span>August</span><span> </span><span>2006; as applicable; as an additional source of service information for installing the IDS-506 software.</span></p></td></tr><tr style="height:0pt"><td style="width:85.05pt"></td><td style="width:175.45pt"></td><td style="width:21.3pt"></td><td style="width:15.85pt"></td><td style="width:212.65pt"></td></tr></tbody></table>
<table cellspacing="0" cellpadding="0" style="width:510.3pt; margin-top:0pt; margin-bottom:0pt; border-collapse:collapse"><tbody><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="4" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="margin-left:21.3pt; text-indent:-21.3pt"><span>2.</span><span style="width:12.3pt; text-indent:0pt; display:inline-block"> </span><span>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.</span><span> </span><span>Chapter 20-41-03 of the Boeing 747-400 Aircraft Maintenance Manual is one approved method.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="4" style="width:414.55pt; border-bottom:0.75pt solid #000000; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="text-align:center"><span style="font-weight:bold">Table 6</span></p></td></tr><tr><td style="width:74.35pt; border-right:0.75pt solid #000000; padding-right:4.97pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="2" style="width:201.9pt; border:0.75pt solid #000000; padding-right:4.97pt; padding-left:4.97pt; vertical-align:top"><p style="margin-left:72pt; margin-bottom:12pt; text-indent:-72pt; text-align:center"><span style="font-weight:bold">Connector</span></p><p style="margin-top:12pt; text-align:center"><span>L-EIU DM7353CA</span><br><span>C</span><span>-EIU DM7352CA</span><br><span>R-EIU DM7351CA</span></p></td><td colspan="2" style="width:201.95pt; border:0.75pt solid #000000; padding-right:4.97pt; padding-left:4.97pt; vertical-align:top"><p style="margin-left:36pt; margin-bottom:12pt; text-indent:-36pt; text-align:center"><span style="font-weight:bold">Pin</span></p><p style="margin-top:12pt; margin-left:0.05pt; text-indent:-0.05pt; text-align:center"><span>G13</span><br><span>G13</span><br><span>G13</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="4" style="width:414.55pt; border-top:0.75pt solid #000000; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="margin-left:21.3pt; text-indent:-21.3pt"><span>3.</span><span style="width:12.3pt; text-indent:0pt; display:inline-block"> </span><span>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.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="4" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="margin-left:21.3pt; text-indent:-21.3pt"><span>4.</span><span style="width:12.3pt; text-indent:0pt; display:inline-block"> </span><span>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 </span><span>to include the information at Annex A to this Directive.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="4" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>Amendment of the AFM may be accomplished by inserting a copy of Annex A to this Directive into the AFM.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="4" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="margin-left:21.3pt; text-indent:-21.3pt"><span>5.</span><span style="width:12.3pt; text-indent:0pt; display:inline-block"> </span><span>Remove the AFM amendments specified in the Airworthiness Directives identified in Table 7.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="4" style="width:414.55pt; border-bottom:0.75pt solid #000000; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="margin-left:21.3pt; text-indent:-21.3pt; text-align:center"><span style="font-weight:bold">Table 7</span></p></td></tr><tr><td style="width:74.35pt; border-right:0.75pt solid #000000; padding-right:4.97pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td style="width:143.5pt; border:0.75pt solid #000000; padding-right:4.97pt; padding-left:4.97pt; vertical-align:top"><p style="margin-left:21.3pt; margin-bottom:12pt; text-indent:-21.3pt; text-align:center"><span style="font-weight:bold">Directive</span></p><p style="margin-top:12pt; margin-left:36pt; text-indent:-36pt"><span style="width:36pt; text-indent:0pt; display:inline-block"></span><span>AD/B747/270</span><br><span>AD/B747/188 Amdt 3</span><br><span>AD/B747/280</span><br><span>AD/B747/283</span></p></td><td colspan="2" style="width:102.7pt; border:0.75pt solid #000000; padding-right:4.97pt; padding-left:4.97pt; vertical-align:top"><p style="margin-left:21.3pt; margin-bottom:12pt; text-indent:-21.3pt; text-align:center"><span style="font-weight:bold">Requirement</span></p><p style="margin-top:12pt; text-align:center"><span>1</span><br><span>4</span><br><span>2</span><br><span>Not Applicable</span></p></td><td style="width:146.95pt; border:0.75pt solid #000000; padding-right:4.97pt; padding-left:4.97pt; vertical-align:top"><p style="margin-left:21.3pt; margin-bottom:12pt; text-indent:-21.3pt; text-align:center"><span style="font-weight:bold">Equivalent FAA AD</span></p><p style="margin-top:12pt"><span>2001-12-21 Amdt 39-12277</span><br><span>2001-21-07 Amdt 39-12478</span><br><span>2002-19-52 Amdt 39-12900</span><br><span>2002-24-52 Amdt 39-12993</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="4" style="width:414.55pt; border-top:0.75pt solid #000000; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>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.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="4" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p class="Note"><span>Note 4:</span><span> </span><span>FAA AD 2007-13-04 Amdt 39-15108 refers.</span></p></td></tr><tr style="height:0pt"><td style="width:85.05pt"></td><td style="width:154.2pt"></td><td style="width:58.4pt"></td><td style="width:55pt"></td><td style="width:157.65pt"></td></tr></tbody></table>
Compliance:
For Requirement 1 - Within six months after the effective date of this Directive.
For Requirement 2 - After installing the new IDS-504 software required by Requirement 1 and within six months after the effective date of this Directive.
For Requirement 3 - Concurrently with Requirement 1.
For Requirement 4 - Concurrently with the Requirement 2.
For Requirement 5 - Following compliance with Requirements 1 and 3.
This Airworthiness Directive becomes effective on 30 August 2007.
Background:
This Directive is issued following a fuel system reviews conducted by the manufacturer. The Directive is issued to reduce the potential for ignition sources inside fuel tanks, which, in combination with flammable fuel vapours, could result in fuel tank explosions and consequent loss of the aeroplane.
Image unavailable in extracted text
David Punshon
Delegate of the Civil Aviation Safety Authority
26 June 2007
Annex A
Certification Limitations
Center Wing Tank (CWT):
The CWT fuel quantity indication system must be operative to dispatch with CWT mission fuel.
If the FUEL LO CTR L or R message is displayed both CWT override/jettison pumps must be selected OFF.
If the FUEL PRESS CTR L or R message is displayed, the corresponding CWT override/jettison pump must be selected OFF.
Note: In a low fuel situation, both CWT override/jettison pumps may be selected ON and all CWT fuel may be used.
Horizontal Stabilizer Tank (HST):
The following additional limitations must be followed if the HST is fueled and used:
The HST fuel quantity indication system must be operative to dispatch with HST mission fuel.
If the FUEL PMP STB L or R message is displayed while on the ground both HST pumps must be selected OFF.
If the FUEL LO STAB L or R message is displayed in flight the corresponding HST pump must be selected OFF.
If the FUEL PRESS STAB L or R message is displayed the corresponding HST pump must be selected OFF.
The remaining fuel in the HST must be considered unusable, and the effects of that unusable fuel on balance (CG) must be considered.
Note: In a low fuel situation, both HST transfer pumps may be selected ON and all HST fuel may be used.
Warning
Do not cycle CWT and HST pump switches from ON to OFF to ON with any continuous low pressure indication present.
Do not reset a tripped fuel pump circuit breaker.
Defueling:
Prior to defueling any fuel tanks, perform a lamp test of the respective Fuel Pump Low Pressure indication lights. When defueling, the Fuel Pump Low Pressure indication lights must be monitored and the fuel pumps positioned to OFF at the first indication of fuel pump low pressure. When defueling with passengers on board, fuel pump switches must be selected OFF at or above approximately 7,000 pounds (3,200 kilograms) for the CWT, 3,000 pounds (1,400 kilograms) for main tanks, and 2,100 pounds (1,000 kilograms) for the HST.
The above requirements apply for defueling or transferring between tanks.
Division Boeing 747 Series Aeroplanes - AD/B747/358 - Integrated Display System and Fuel Tank Safety - Boeing 747 Series Aeroplanes | Zoe