[Federal Register Volume 71, Number 26 (Wednesday, February 8, 2006)]
[Proposed Rules]
[Pages 6404-6408]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-1682]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23803; Directorate Identifier 2005-NM-238-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-400, 747-400D, and 
747-400F Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking.

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to all Boeing Model 747-400, -400D, and -
400F series airplanes. The existing AD currently requires revising the 
airplane flight manual (AFM) to require the flightcrew to maintain 
certain minimum fuel levels in the center fuel tanks, and to prohibit 
the use of the horizontal stabilizer fuel tank. This proposed AD would 
require installing new integrated display software in the integrated 
display units and electronic flight instrument system/engine indication 
and crew alerting system interface units (EIUs) of the flight deck. 
This proposed AD also would require revising the AFM to include 
procedures to prevent dry operation of the center wing and horizontal 
stabilizer fuel tanks; for maintaining minimum fuel levels; and for de-
fueling fuel tanks. For certain airplanes, the proposed AD also 
requires removing G13 pin ground wires of a certain wire integration 
unit of the EIUs at certain connector locations. This proposed AD 
results from fuel system reviews conducted by the manufacturer. We are 
proposing this AD to reduce the potential for ignition sources inside 
fuel tanks, which, in combination with flammable fuel vapors, could 
result in fuel tank explosions and consequent loss of the airplane.

DATES: We must receive comments on this proposed AD by March 27, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for service information identified in this 
proposed AD.

FOR FURTHER INFORMATION CONTACT: Sulmo Mariano, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone 
(425) 917-6501; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``Docket No. 
FAA-2006-23803; Directorate Identifier 2005-NM-238-AD'' at the 
beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of the 
proposed AD. We will consider all comments received by the closing date 
and may amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or may 
visit http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    The FAA has examined the underlying safety issues involved in fuel 
tank explosions on several large transport airplanes, including the 
adequacy of existing regulations, the service history of airplanes 
subject to those regulations, and existing maintenance practices for 
fuel tank systems. As a result of those findings, we issued a 
regulation titled ``Transport Airplane Fuel Tank System Design Review, 
Flammability Reduction and Maintenance and Inspection Requirements'' 
(67 FR 23086, May 7, 2001). In addition to new airworthiness standards 
for transport airplanes and new maintenance requirements, this rule 
included Special Federal Aviation Regulation No. 88 (``SFAR 88,'' 
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
    Among other actions, SFAR 88 requires certain type design (i.e., 
type certificate (TC) and supplemental type certificate (STC)) holders 
to substantiate that their fuel tank systems can prevent

[[Page 6405]]

ignition sources in the fuel tanks. This requirement applies to type 
design holders for large turbine-powered transport airplanes and for 
subsequent modifications to those airplanes. It requires them to 
perform design reviews and to develop design changes and maintenance 
procedures if their designs do not meet the new fuel tank safety 
standards. As explained in the preamble to the rule, we intended to 
adopt airworthiness directives to mandate any changes found necessary 
to address unsafe conditions identified as a result of these reviews.
    In evaluating these design reviews, we have established four 
criteria intended to define the unsafe conditions associated with fuel 
tank systems that require corrective actions. The percentage of 
operating time during which fuel tanks are exposed to flammable 
conditions is one of these criteria. The other three criteria address 
the failure types under evaluation: single failures, single failures in 
combination with another latent condition(s), and in-service failure 
experience. For all four criteria, the evaluations included 
consideration of previous actions taken that may mitigate the need for 
further action.
    We have determined that the actions identified in this AD are 
necessary to reduce the potential of ignition sources inside fuel 
tanks, which, in combination with flammable fuel vapors, could result 
in fuel tank explosions and consequent loss of the airplane.

Relevant Rulemaking

    On December 23, 2002, we issued AD 2002-24-52, amendment 39-12993 
(68 FR 14, January 2, 2003), for all Boeing Model 747-400, -400D, and -
400F series airplanes. That AD requires revising the airplane flight 
manual (AFM) to require the flightcrew to maintain certain minimum fuel 
levels in the center fuel tanks, and to prohibit the use of the 
horizontal stabilizer fuel tank. That AD resulted from reports 
indicating that two fuel pumps showed evidence of extreme localized 
overheating of parts in the priming and vapor pump section of the fuel 
pump. We issued that AD to require the flightcrew to maintain certain 
minimum fuel levels in the center fuel tanks, and to prohibit the use 
of the horizontal stabilizer fuel tank.

Other Relevant Rulemaking

    We also issued the following ADs:

                                            Other Relevant Rulemaking
----------------------------------------------------------------------------------------------------------------
                 AD--                         Requires--                 And--                    And--
----------------------------------------------------------------------------------------------------------------
2001-12-21, amendment 39-12277 (66 FR  Revising the AFM to      For certain airplanes,   For certain airplanes,
 33170, June 21, 2001).                 include procedures to    prohibits operation of   requires installing
                                        prevent dry operation    the horizontal           improved fuel pumps,
                                        of the center wing       stabilizer tank          which terminates the
                                        fuel tank override/      transfer pumps in        AFM revision.
                                        jettison pumps.          flight.
2001-21-07, amendment 39-12478 (66 FR  For certain airplanes,   For all airplanes,       Reworking of certain
 54652, October 30, 2001).              revising the AFM.        performing repetitive    components, which ends
                                                                 inspections for wear     the repetitive
                                                                 or damage of the inlet   inspection
                                                                 check valves and inlet   requirements.
                                                                 adapters of the
                                                                 override/jettison
                                                                 pumps, and doing
                                                                 corrective actions if
                                                                 necessary.
2002-19-52, amendment 39-12900 (67 FR  Removing currently       Prohibits installation   Permits the AFM
 61253, September 30, 2002).            required AFM             of any uninspected       revision and placard
                                        revisions, inserting     pumps.                   to be removed under
                                        new AFM revisions, and                            certain conditions.
                                        installing placards to
                                        alert the flightcrew
                                        to the operating
                                        restrictions.
----------------------------------------------------------------------------------------------------------------

Actions Since Existing ADs Were Issued

    The preambles to ADs 2002-24-52 and 2002-19-52 explain that we 
consider the requirements ``interim action'' and were considering 
further rulemaking. We now have determined that further rulemaking is 
indeed necessary, and this proposed AD follows from that determination.
    We have reviewed the following service bulletins:

                            Service Bulletins
------------------------------------------------------------------------
    Boeing Alert Service Bulletin--                For Model--
------------------------------------------------------------------------
747-31A2350, Revision 1, dated March     747-400 and 747-400F series
 17, 2005.                                airplanes.
747-31A2351, Revision 1, dated March     747-400, 747-400D, and 747-400F
 17, 2005.                                series airplanes.
747-31A2352, Revision 1, dated March     747-400 and 747-400F series
 17, 2005.                                airplanes.
------------------------------------------------------------------------

    The service bulletins describe procedures for installing new 
integrated display software in the integrated display units (IDUs) and 
electronic flight instrument system (EFIS)/engine indication and crew 
alerting system (EICAS) interface units (EIU) of the flight deck. The 
new software provides new IDS EICAS fuel system messages. These 
messages alert the flightcrew when to shut the fuel pumps off. 
Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.
    Each service bulletin described previously refers to Rockwell 
Collins Service Bulletins IDS-7000-31-49, IDS-7000-31-50, or IDS-7000-
31-51; all dated June 28, 2004; as applicable; as an additional source 
of service information for installing the new software.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to develop on other airplanes of the 
same type design. For this reason, we are proposing this AD, which 
would supersede AD 2002-24-52 to continue to require revising the AFM 
to require the flightcrew to maintain certain minimum fuel levels in

[[Page 6406]]

the center fuel tanks, and to prohibit the use of the horizontal 
stabilizer fuel tank. The proposed AD also would require:
     Accomplishing the actions specified in the Boeing service 
information described previously;
     Revising the Limitations section of the AFM to include 
procedures to prevent dry operation of the center wing and horizontal 
stabilizer fuel tanks; for maintaining minimum fuel levels; and for de-
fueling fuel tanks; and
     For certain airplanes: Removing G13 pin ground wires of 
the wire integration unit on the E2-6 electronic shelf of the left, 
center, and right electronics interface units at certain connector 
locations.
    After installing the new software and incorporating the new AFM 
revisions, the AFM revision required by AD 2002-24-52 and certain AFM 
revisions required by ADs 2001-12-21, 2001-21-07, and 2002-19-52 may be 
removed.

Change to Existing AD

    This proposed AD would retain all the requirements of AD 2002-24-
52. Since AD 2002-24-52 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                            Corresponding requirement in
       Requirement in AD 2002-24-52               this proposed AD
------------------------------------------------------------------------
paragraph (a).............................  paragraph (g).
paragraph (b).............................  paragraph (h).
------------------------------------------------------------------------

Costs of Compliance

    There are about 520 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                  Number of U.S.-
              Action                   Work hours       Average labor           Parts         Cost per airplane      registered          Fleet cost
                                                        rate per hour                                                airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
AFM revision (required by AD 2002-                 1                $65  None...............                $65                101  $6,565.
 24-52).
Installation of new IDS software                   3                 65  $100...............                295                101  $29,795.
 (new proposed action).
Removal of G-13 pin ground wires                   1                 65  None...............                 65                  0  $65 if an affected
 (new proposed action).                                                                                                              airplane is
                                                                                                                                     imported and placed
                                                                                                                                     on the U.S.
                                                                                                                                     Register in the
                                                                                                                                     future.
AFM revision (new proposed                         1                 65  None...............                 65                101  $6,565.
 action).
--------------------------------------------------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-12993 (68 FR 14, January 2, 2003) and adding the 
following new airworthiness directive (AD):

Boeing: Docket No. FAA-2006-23803; Directorate Identifier 2005-NM-
238-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by March 27, 
2006.

Affected ADs

    (b) This AD supersedes AD 2002-24-52. In addition, after 
accomplishing the requirements of paragraphs (h) and (k) of this AD, 
the airplane flight manual (AFM)

[[Page 6407]]

requirements specified in table 1 of this AD may be removed.

                         Table 1.--Affected ADs
------------------------------------------------------------------------
         AFM requirements of--                         Of--
------------------------------------------------------------------------
(1) Paragraph (a)......................  AD 2001-12-21, amendment 39-
                                          12277.
(2) Paragraph (a)......................  AD 2001-21-07, amendment 39-
                                          12478.
(3) Paragraph (c)......................  AD 2002-19-52, amendment 39-
                                          12900.
(4) Paragraphs (f) and (g).............  This AD.
------------------------------------------------------------------------

Applicability

    (c) This AD applies to airplanes identified in table 2 of this 
AD, certificated in any category.

                         Table 2.--Applicability
------------------------------------------------------------------------
                                         As identified in Boeing Service
             Boeing model--                         Bulletin--
------------------------------------------------------------------------
(1) 747-400, 747-400D, and 747-400F      747-31A2351, Revision 1, dated
 series airplanes.                        March 17, 2005.
(2) 747-400 and 747-400F series          747-31A2350, Revision 1, dated
 airplanes.                               March 17, 2005.
(3) 747-400 and 747-400F series          747-31A2352, Revision 1, dated
 airplanes.                               March 17, 2005.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from fuel system reviews conducted by the 
manufacturer. We are issuing this AD to reduce the potential for 
ignition sources inside fuel tanks, which, in combination with 
flammable fuel vapors, could result in fuel tank explosions and 
consequent loss of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of Requirements of AD 2002-24-52

Airplane Flight Manual (AFM) Revision

    (f) Within 4 days after receipt of emergency AD 2002-24-51, 
instead of complying with the requirements of paragraph (d) of AD 
2002-24-51, revise the Limitations section of the AFM to include the 
following (this may be accomplished by inserting a copy of this AD 
into the AFM):

CERTIFICATE LIMITATIONS

    Fueling and use of the horizontal stabilizer tank (if installed) 
is prohibited.
    The center wing tank (CWT) must contain a minimum of 17,000 
pounds (7,700 kilograms) prior to engine start, if the CWT override/
jettison pumps are to be selected ON during flight.
    The CWT fuel quantity indication system must be operative to 
dispatch with CWT mission fuel.
    Both CWT override/jettison pump switches must be selected OFF at 
or before CWT fuel quantity reaches 7,000 pounds (3,200 kilograms), 
if CWT fuel quantity is less than 50,000 pounds (22,700 kilograms) 
prior to engine start. The CWT override pumps may be selected ON 
during stabilized cruise conditions. Both CWT override/jettison pump 
switches must be selected OFF at or before the CWT fuel quantity 
reaches 3,000 pounds (1,400 kilograms).

    Note: With CWT override/jettison pumps selected OFF and CWT fuel 
quantity greater than 6,000 pounds (2,800 kilograms), the FUEL OVRD 
CTR L & R EICAS messages will be displayed. Do not accomplish the 
associated non-normal procedure.

    Both CWT override/jettison pump switches must be selected OFF at 
or before CWT fuel quantity reaches 3,000 pounds (1,400 kilograms), 
if CWT fuel quantity is greater than or equal to 50,000 pounds 
(22,700 kilograms) prior to engine start.
    Both CWT override/jettison pumps must be selected OFF when 
either CWT override/jettison fuel pump low pressure light 
illuminates.
    Warning: Do not reset a tripped fuel pump circuit breaker.
    Warning: Do not cycle CWT override/jettison pump switches from 
ON to OFF to ON with any continuous low pressure indication present.

    Note: The center wing tank may be emptied normally during an 
emergency fuel jettison.


    Note: In a low fuel situation, both CWT override/jettison pumps 
may be selected ON and all CWT fuel may be used.

    If a center wing tank pump fails with fuel in the center tank, 
accomplish the FUEL OVRD CTR L, R non-normal procedure.
    If the main tanks are not full, the zero fuel gross weight of 
the airplane plus the weight of CWT tank fuel may exceed the maximum 
zero fuel gross weight by up to 7,000 pounds (3,200 kilograms) for 
takeoff, climb, cruise, descent, and landing, provided that the 
effects of balance (CG) have been considered.
    When defueling any fuel tanks, 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. Defueling 
with passengers on board is prohibited.
    The limitations contained in this AD supersede any conflicting 
basic airplane flight manual limitations.''
    (g) If an operator has already complied with AD 2002-24-51, it 
can comply with paragraph (f) of this AD by deleting the phrase ``if 
a placard prohibiting its use is installed'' from the first 
paragraph of the AFM revision required by paragraph (d) of AD 2002-
24-51.

New Actions Required by This AD

Installation of New Integrated Display System (IDS) Software

    (h) Within 6 months after the effective date of this AD, install 
new IDS 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 service bulletin in 
table 3 of this AD.

                Table 3.--Revision 1 of Service Bulletins
------------------------------------------------------------------------
              For model--                   Boeing service bulletin--
------------------------------------------------------------------------
(1) 747-400, 747-400D, and 747-400F       747-31A2351, Revision 1, dated
 series airplanes.                        March 17, 2005.
(2) 747-400 and 747-400F series          747-31A2350, Revision 1, dated
 airplanes.                               March 17, 2005.

[[Page 6408]]

 
(3) 747-400 and 747-400F series          747-31A2352, Revision 1, dated
 airplanes.                               March 17, 2005.
------------------------------------------------------------------------


    Note 1: Each service bulletin identified in table 3 of this AD 
refers to Rockwell Collins Service Bulletins IDS-7000-31-49, IDS-
7000-31-50, or IDS-7000-31-51; all dated June 28, 2004; as 
applicable; as an additional source of service information for 
installing the new IDS software.

    (i) Installing new IDS software before the effective date of 
this AD in accordance with the applicable service bulletin in table 
4 of this AD, is acceptable for compliance with the requirements of 
paragraph (h) of this AD.

                  Table 4.--Original Service Bulletins
------------------------------------------------------------------------
              For model--                   Boeing service bulletin--
------------------------------------------------------------------------
(1) 747-400, 747-400D, and 747-400F      747-31A2351, dated September 3,
 series airplanes.                        2004.
(2) 747-400 and 747-400F series          747-31A2350, dated September 3,
 airplanes.                               2004.
(3) 747-400 and 747-400F series          747-31A2352, dated September 3,
 airplanes.                               2004.
------------------------------------------------------------------------

Removal of Pin Ground Wires

    (j) For airplanes on which FR-HiTEMP fuel pumps have been 
incorporated in accordance with Boeing Service Bulletin 747-28-2258, 
dated December 19, 2003; or Revision 1, dated August 11, 2005: 
Before further flight after installing the new IDS software required 
by paragraph (h) of this AD, remove the G13 pin ground wires of the 
wire integration unit on the E2-6 electronic shelf of the left, 
center, and right electronics interface units, that correspond to 
the connector locations in table 5 of this AD, 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 5.--Connector Location
------------------------------------------------------------------------
                 Connector                            Location
------------------------------------------------------------------------
DM7353CA..................................  Left EIU.
DM7352CA..................................  Center EIU.
DM7351CA..................................  Right EIU.
------------------------------------------------------------------------

AFM Revision

    (k) Concurrently with the requirements of paragraph (h) of this 
AD, revise the Limitations section of the AFM to include the 
following (this may be done by inserting a copy of this AD into the 
AFM):

Certification Limitations

    Center Wing Tank (CWT): The CWT fuel quantity indication system 
must be operative to dispatch with CWT mission fuel.
    The CWT must contain a minimum of 17,000 pounds (7,700 
kilograms) prior to engine start, if the CWT override/jettison pumps 
are to be selected ON during takeoff.
    If the FUEL LOW 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.
    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 LOW 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 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.
    Warning: 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.

Alternative Methods of Compliance (AMOCs)

    (l)(1) The Manager, Seattle ACO, FAA, has the authority to 
approve AMOCs for this AD, if requested in accordance with the 
procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

    Issued in Renton, Washington, on January 30, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-1682 Filed 2-7-06; 8:45 am]
BILLING CODE 4910-13-P