[Federal Register Volume 74, Number 104 (Tuesday, June 2, 2009)]
[Proposed Rules]
[Pages 26317-26322]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-12742]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0454; Directorate Identifier 2008-NM-156-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Boeing Model 747-400, 747-400D, and 747-400F series airplanes. 
For all airplanes, this proposed AD would require installing new pump 
control and time delay relays, doing related investigative and 
corrective actions if necessary, and changing the wiring for the center 
and main fuel tanks override/jettison fuel pumps; and, for certain 
airplanes, installing new relays and wiring for the horizontal 
stabilizer override/jettison fuel pumps. This proposed AD would also 
require a revision to the maintenance program to incorporate 
Airworthiness Limitation No. 28-AWL-24 and No. 28-AWL-26. For certain 
airplanes, this proposed AD would also require installing an automatic 
shutoff system for the horizontal stabilizer tank fuel pumps and 
installing a new integrated display system. This proposed AD results 
from fuel system reviews conducted by the manufacturer. We are 
proposing this AD to prevent uncommanded operation of certain override/
jettison pumps which could cause overheat, electrical arcs, or 
frictional sparks, and could lead to an ignition source inside a fuel 
tank. This condition, in combination with flammable fuel vapors, could 
result in a fuel tank explosion and consequent loss of the airplane.

DATES: We must receive comments on this proposed AD by July 17, 2009.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Boeing 
Commercial Airplanes, Attention: Data & Services Management, P.O. Box 
3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-544-5000, 
extension 1, fax 206-766-5680; e-mail [email protected]; Internet 
https://www.myboeingfleet.com.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Jon Regimbal, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 917-6506; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0454; 
Directorate Identifier 2008-NM-156-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

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

[[Page 26318]]

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'' (66 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 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 a 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.
    Safety assessments conducted by Boeing indicate that there is a 
risk of an ignition source in the main and center fuel tanks for Model 
747-400, 747-400D, and 747-400F series airplanes, and in the horizontal 
stabilizer fuel tanks of Model 747-400 series airplanes, if the 
override/jettison pump continues to run for an extended time after the 
fuel level goes below the pump inlet. The pump is normally commanded 
off if the fuel level goes below the pump inlet, but if a single 
failure in the pump control circuitry occurs, a pump can continue to 
run after it is commanded off. Uncommanded operation of certain 
override/jettison pumps could cause overheat, electrical arcs, or 
frictional sparks, and could lead to an ignition source inside a fuel 
tank. This condition, in combination with flammable fuel vapors, could 
result in a fuel tank explosion and consequent loss of the airplane.

Other Related Rulemaking

    Installing a new integrated display system (IDS) in accordance with 
Boeing Service Bulletin 747-31-2376, 747-31-2377, or 747-31-2378, all 
dated September 5, 2006, as applicable, would provide an acceptable 
substitute for complying with certain paragraphs of the ADs listed 
below.
     Paragraph E. of AD 90-09-06, amendment 39-6581 (55 FR 
15217, April 23, 1990). That AD applies to all Model 747 series 
airplanes and requires, among other actions, installing a system to 
provide visual warning signals to alert flightcrew members and ground 
crew personnel of certain incorrect indications.
     Paragraph (b) of AD 91-13-10 R1, amendment 39-8158 (57 FR 
2446, January 22, 1992). That AD applies to certain Boeing Model 747 
and 767 series airplanes and requires, among other actions, replacing 
the engine indicating and crew alerting system (EICAS) computers.
     Paragraph (d)(1) of AD 96-07-09, amendment 39-9558 (61 FR 
14608, April 3, 1996). That AD applies to all Boeing Model 747-400, 
757, and 767 series airplanes and requires, among other actions, 
installing an upgraded EICAS computer that provides ``advisory'' 
messages to the flightcrew to indicate an impending engine fuel filter 
bypass condition for each engine.
     Paragraph (a)(3)(iii) of AD 2000-02-22, amendment 39-11540 
(65 FR 5222, February 3, 2000). That AD applies to certain Boeing Model 
747-400 series airplanes and requires, among other actions, modifying 
the IDS software.
     Paragraph (a)(2)(ii) of AD 2000-12-21, amendment 39-11799 
(65 FR 39079, June 23, 2000). [A correction of that AD was published in 
the Federal Register on July 18, 2000 (65 FR 44432).] That AD requires, 
among other actions, modifying the IDS software.
     Paragraph (d)(2)(iv) of AD 2003-16-16, amendment 39-13269 
(68 FR 51439, August 27, 2003). That AD applies to certain Boeing Model 
747-400 series airplanes and requires, among other actions, installing 
new IDS software in six integrated display units and three electronic 
flight information (EFI)/EICAS interface units.
     Paragraph (d)(1) of AD 2004-10-05, amendment 39-13635 (69 
FR 28052, May 18, 2004). That AD applies to certain Boeing Model 747-
400, 747-400D, 747-400F, 757-200, 757-200PF, 757-200CB, 767-200, 767-
300, and 767-300F series airplanes. That AD requires, among other 
actions for Model 747-400, -400D, and -400F series airplanes, replacing 
the three EFIS/EICAS interface units (EIU), installing new software in 
the integrated display units (IDUs) and EIUs, replacing certain central 
maintenance computers (CMCs), and installing new software in the CMCs.
    For airplanes with a horizontal stabilizer fuel tank and with 
horizontal stabilizer tank fuel pump auto-shutoff installed, installing 
a new IDS in accordance with Boeing Service Bulletin 747-31-2376, 747-
31-2377, or 747-31-2378, all dated September 5, 2006, as applicable, 
would provide an acceptable method for complying with certain 
paragraphs of the ADs listed below, provided the certificate 
limitations enclosed with FAA Letter 140S-06-343, dated November 17, 
2006, are incorporated into the limitations section of the applicable 
airplane flight manual (AFM) revision specified in the applicable AD.
     Paragraph (a) of AD 2001-12-21, amendment 12777 (66 FR 
33170, June 21, 2001). That AD applies to all Boeing Model 747 series 
airplanes and requires, among other actions, revising the Limitations 
Section of the AFM to include procedures to prevent dry operation of 
the center wing fuel tank override/jettison pumps and, for certain 
airplanes, to prohibit operation of the horizontal stabilizer tank 
transfer pumps in-flight.
     Paragraph (a) of AD 2001-21-07, amendment 39-12478 (66 FR 
54652, October 30, 2001). That AD applies to certain Boeing Model 747 
series airplanes and requires, among other actions, revising the AFM to 
specify the amount of fuel necessary for operating the override/
jettison fuel pumps, and to specify not resetting the circuit breakers 
for the override/jettison fuel pumps if they are tripped.
     Paragraph (c)(2) of AD 2002-19-52, amendment 39-12900 (67 
FR 61253, September 30, 2002). That AD applies to all Boeing Model 737-
600, -700, -700C, -800, and -900 series airplanes; Model 747 series 
airplanes; and Model 757 series airplanes. That AD requires, among 
other actions, revising the AFM

[[Page 26319]]

to advise the flightcrew of certain operating restrictions for 
maintaining minimum fuel levels.
     Paragraph (a) of AD 2002-24-52, amendment 39-12993 (68 FR 
14, January 2, 2003). That AD applies to all Boeing Model 747-400, -
400D, and -400 F series airplanes and requires, among other actions, 
revising the AFM to require the flightcrew to maintain certain minimum 
fuel levels in the center wing fuel tank, and to prohibit the use of 
the horizontal stabilizer fuel tank.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 747-28A2280, dated 
August 7, 2008. This service bulletin describes procedures for 
installing new pump control and time delay relays, doing related 
investigative and corrective actions if necessary, and changing the 
wiring for the center and main fuel tanks override/jettison fuel pumps. 
The related investigative and corrective actions include doing a 
general visual inspection for corrosion of the ground stud assembly 
during the installation of the P914 relay panel and cleaning or 
replacing the ground stud assembly if necessary. Boeing Alert Service 
Bulletin 747-28A2280 specifies that the installation of a new 
integrated display system (IDS), as described in the following service 
bulletins, must be done before or at the same time as the actions in 
the alert service bulletin:
     Boeing Service Bulletin 747-31-2376, dated September 5, 
2006, for Model 747-400, and -400F series airplanes that have General 
Electric engines, except for airplanes having variable numbers (V/Ns) 
RL429, RL430, RL473, RL511, and RL521, which received new software in 
production.
     Boeing Service Bulletin 747-31-2377, dated September 5, 
2006, for Model 747-400, and -400F series airplanes that have Pratt & 
Whitney engines, except for airplanes having V/Ns RL456, RL492, and 
RL502, which received new software in production.
     Boeing Service Bulletin 747-31-2378, dated September 5, 
2006, for Model 747-400, -400D, and -400F series airplanes that have 
Rolls Royce engines.
    We have also reviewed Boeing Alert Service Bulletin 747-28A2281, 
dated December 13, 2007, for Model 747-400 series airplanes. This 
service bulletin describes procedures for installing new relays and 
wiring in the horizontal stabilizer override/jettison fuel pumps. 
Boeing Alert Service Bulletin 747-28A2281 specifies that the 
installation of a new automatic shutoff system for the horizontal 
stabilizer tank (HST) fuel pumps, as described in the following service 
bulletin, must be done before or at the same time as the actions in the 
alert service bulletin: Boeing Service Bulletin 747-28A2262, Revision 
1, dated May 8, 2008, for Model 747-400 series airplanes, except for 
airplanes having V/Ns RM403, RM441, RM442, RM443, and RM445.
    We have also reviewed Section 9, ``Airworthiness Limitations (AWLs) 
and Certification Maintenance Requirements (CMRs),'' Boeing 747-400 
Maintenance Planning (MPD) Data Document D621U400-9, Revision April 
2008 (hereafter referred to as ``Document D621U400-9''). Sub-section D 
of Document D621U400-9 describes AWLs for fuel tank systems. Sub-
section D of Document D621U400-9 includes the following fuel system 
AWLs:
     AWL No. 28-AWL-24, which is a repetitive functional test 
to verify continued functionality of the automatic shutoff system for 
the fuel boost pump of the HST. This AWL applies to Model 747-400 
airplanes, line numbers (L/Ns) 1343 and subsequent, and those that have 
been modified in accordance with Boeing Service Bulletin 747-28A2262.
     AWL No. 28-AWL-26, which is a repetitive operational test 
to verify the continued functionality of the uncommanded on system for 
the override/jettison pump of the main 2 and main 3 fuel tanks. This 
AWL applies to Model 747-400, -400D, and -400F airplanes, L/Ns 1380 and 
subsequent, and those that have been modified in accordance with Boeing 
Alert Service Bulletin 747-28A2280.

FAA's Determination and Requirements of This Proposed AD

    We are proposing this AD because we evaluated all relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design. 
This proposed AD would require, for all airplanes installing new pump 
control and time delay relays, doing related investigative and 
corrective actions if necessary, and changing the wiring for the center 
and main fuel tanks override/jettison fuel pumps; and, for certain 
airplanes, installing new relays and wiring for the horizontal 
stabilizer override/jettison fuel pumps. This proposed AD would also 
require a revision to the maintenance program to incorporate 
Airworthiness Limitation No. 28-AWL-24 and No. 28-AWL-26. For certain 
airplanes, this proposed AD would also require installing an automatic 
shutoff system for the horizontal stabilizer tank fuel pumps and 
installing a new integrated display system.

Costs of Compliance

    We estimate that this proposed AD would affect 102 airplanes of 
U.S. registry. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD. The average labor rate 
is $80 per work hour.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                               Number of U.S.-
               Action                      Work hours                 Parts            Cost per  product     registered airplanes        Fleet cost
--------------------------------------------------------------------------------------------------------------------------------------------------------
Installing relays/changing wiring    375 to 394............  $65,015 to $65,451....  $95,015 to $96,971...  102..................  $9,691,530 to
 for center and main fuel tanks.                                                                                                    $9,891,042.
Installing a new IDS and revising    2 to 3................  $0....................  Up to $240...........  Up to 102............  Up to $24,480.
 the AFM when done (prior/
 concurrent action).
Installing relays and wiring for     73 to 79..............  $0....................  $5,840 to $6,320.....  74...................  $432,160 to $467,680.
 horizontal stabilizer tank (HST).
Installing a new automatic shutoff   44....................  $4,112................  $7,632...............  74...................  $564,768.
 for the HST.
Revising the maintenance program...  1.....................  $0....................  $80..................  102..................  $8,160.
--------------------------------------------------------------------------------------------------------------------------------------------------------


[[Page 26320]]

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 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 this 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.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, 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 FAA amends Sec.  39.13 by adding the following new AD:

Boeing: Docket No. FAA-2009-0454; Directorate Identifier 2008-NM-
156-AD.

Comments Due Date

    (a) We must receive comments by July 17, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 747-400, 747-400D, and 747-
400F series airplanes, certificated in any category; as identified 
in Boeing Alert Service Bulletins 747-28A2280, dated August 7, 2008, 
and 747-28A2281, dated December 13, 2007.

    Note 1:  This AD requires revisions to certain operator 
maintenance documents to include a new inspection. Compliance with 
this inspection is required by 14 CFR 91.403(c). For airplanes that 
have been previously modified, altered, or repaired in the areas 
addressed by this inspection, the operator may not be able to 
accomplish the inspections described in the revisions. In this 
situation, to comply with 14 CFR 91.403(c), the operator must 
request approval for an alternative method of compliance (AMOC) 
according to paragraph (m) of this AD. The request should include a 
description of changes to the required inspection that will ensure 
the continued operational safety of the airplane.

Subject

    (d) Air Transport Association (ATA) of America Code 28: Fuel.

Unsafe Condition

    (e) This AD results from fuel system reviews conducted by the 
manufacturer. We are issuing this AD to prevent uncommanded 
operation of certain override/jettison pumps which could cause 
overheat, electrical arcs, or frictional sparks, and could lead to 
an ignition source inside a fuel tank. This condition, in 
combination with flammable fuel vapors, could result in a fuel tank 
explosion and consequent loss of the airplane.

Compliance

    (f) Comply with this AD within the compliance times specified, 
unless already done.

Installations and Wiring Changes

    (g) Within 60 months after the effective date of this AD, do the 
actions in paragraphs (g)(1) and (g)(2) of this AD, as applicable.
    (1) For Model 747-400, -400D, and -400F series airplanes: 
Install new pump control and time delay relays and do related 
investigative and all applicable corrective actions, and change the 
wiring for the center and main fuel tanks override/jettison fuel 
pumps, in accordance with the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-28A2280, dated August 7, 2008. Do all 
related investigative and applicable corrective actions before 
further flight.
    (2) For Model 747-400 series airplanes: Install new relays and 
wiring for the horizontal stabilizer override/jettison fuel pumps in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-28A2281, dated December 13, 2007.

Prior/Concurrent Requirements

    (h) Prior to or concurrently with the actions required by 
paragraph (g) of this AD, do the applicable actions in paragraphs 
(h)(1) and (h)(2) of this AD.
    (1) For Model 747-400, -400D, and -400F series airplanes 
identified in paragraphs (h)(1)(i), (h)(1)(ii), and (h)(1)(iii) of 
this AD: Install a new integrated display system (IDS) in accordance 
with the Accomplishment Instructions of the applicable service 
bulletin listed in paragraph (h)(1)(i), (h)(1)(ii), or (h)(1)(iii) 
of this AD.
    (i) For Model 747-400, -400D, and -400F series airplanes that 
have General Electric engines except airplanes having variable 
numbers (V/Ns) RL429, RL430, RL473, RL511, and RL521: Boeing Service 
Bulletin 747-31-2376, dated September 5, 2006.
    (ii) For Model 747-400 and -400F series airplanes that have 
Pratt & Whitney engines except airplanes having V/Ns RL456, RL492, 
and RL502: Boeing Service Bulletin 747-31-2377, dated September 5, 
2006.
    (iii) For Model 747-400 and -400F series airplanes that have 
Rolls Royce engines: Boeing Service Bulletin 747-31-2378, dated 
September 5, 2006.
    (2) For Model 747-400 series airplanes except V/Ns RM403, RM441 
through RM443 inclusive, and RM445: Install a new automatic shutoff 
system for the horizontal stabilizer tank (HST) fuel pumps in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 747-28A2262, Revision 1, dated May 8, 2008. Installations 
accomplished before the effective date of this AD in accordance with 
Boeing Service Bulletin 747-28A2262, dated March 15, 2007, are 
acceptable for compliance with the installation required by this 
paragraph.

Maintenance Program Revision

    (i) Concurrently with accomplishing the actions required by 
paragraph (g) of this AD, revise the maintenance program by 
incorporating Airworthiness Limitation (AWL) No. 28-AWL-24 and No. 
28-AWL-26 of Section 9, ``Airworthiness Limitations (AWLs) and 
Certification Maintenance Requirements (CMRs),'' Boeing 747-400 
Maintenance Planning (MPD) Data Document D621U400-9, Revision April 
2008. The inspection interval for AWL No. 28-AWL-24 and AWL No. 28-
AWL-26 starts on the date the modification is incorporated.

No Alternative Inspections or Inspection Intervals

    (j) After accomplishing the action specified in paragraph (i) of 
this AD, no alternative actions or intervals may be used unless the 
inspections or inspection intervals are approved as an AMOC in 
accordance with the procedures specified in paragraph (m) of this 
AD.

[[Page 26321]]

Acceptable Action for Certain ADs

    (k) For Model 747-400, -400D, and -400F series airplanes: 
Installing a new IDS in accordance with paragraph (h)(1) of this AD 
is an acceptable method of compliance for the action in the 
applicable AD paragraph listed in Table 1 of this AD.

  Table 1--Actions for Which Paragraph (h)(1) of This AD Is an Acceptable Method of Compliance (No Certificate
                                                  limitations)
----------------------------------------------------------------------------------------------------------------
            The action in--                                                Of--
----------------------------------------------------------------------------------------------------------------
(1) Paragraph E........................  AD 90-09-06, amendment 39-6581.
(2) Paragraph (b)......................  AD 91-13-10 R1, amendment 39-8158.
(3) Paragraph (d)(1)...................  AD 96-07-09, amendment 39-9558.
(4) Paragraph (a)(3)(iii)..............  AD 2000-02-22, amendment 39-11540.
(5) Paragraph (a)(2)(ii)...............  AD 2000-12-21, amendment 39-11799.
(6) Paragraph (d)(2)(iv)...............  AD 2003-16-16, amendment 39-13269.
(7) Paragraph (d)(1)...................  AD 2004-10-05, amendment 39-13635.
----------------------------------------------------------------------------------------------------------------

    (l) For Model 747-400, -400D, and -400F series airplanes with a 
horizontal stabilizer fuel tank and with horizontal stabilizer tank 
fuel pump auto-shutoff installed: Installing a new IDS in accordance 
with paragraph (h)(1) of this AD is an acceptable method of 
compliance for the action in the applicable AD paragraph listed in 
Table 2 of this AD, provided the certificate limitations included in 
the following statement are incorporated into the Limitations 
Section of the applicable airplane flight manual (AFM) in place of 
the certificate limitation required by the AFM revision specified in 
the applicable AD listed in Table 2 of this AD. This may be done by 
inserting a copy of this AD in the AFM.

``Certificate Limitations

Center Wing Tank

    The center wing tank (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 pump(s) 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

    The following additional limitations must be followed if the 
horizontal stabilizer tank is fueled and used:
    The horizontal stabilizer tank (HST) fuel quantity indication 
system must be operative to dispatch with HST mission fuel.
    If either the FUEL PMP STB L or R message is displayed while on 
the ground, both HST pumps must be selected OFF.
    If either the FUEL PRES STB L or R message is displayed, both 
HST pumps must be selected OFF.

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 center wing tank, 3,000 pounds 
(1,400 kilograms) for main tanks, and 2,100 pounds (1,000 kilograms) 
for the horizontal stabilizer tank. (These requirements apply for 
defueling or transferring between tanks.)

Warnings and Notes Applicable to All Fuel Operations

Warning

    Do not reset a tripped fuel pump circuit breaker.

Warning

    Do not cycle CWT and HST pump switches from ON to OFF to ON with 
any continuous low pressure indication present.

Note

    There is no change to the maximum zero fuel gross weight found 
in the airplane flight manual.

Note

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

Note

    In a low fuel situation, both HST transfer pumps may be selected 
ON and all HST fuel may be used.

Note

    The CWT and the HST may be emptied normally during an emergency.

Note

    The limitations contained in these certificate limitations 
supersede any conflicting basic airplane flight manual 
limitations.''

    Note 2: When a statement identical to that in paragraph (l) of 
this AD has been included in the general revisions of the AFM, the 
general revisions may be inserted into the AFM, and the copy of this 
AD may be removed from the AFM.


    Note 3: The certificate limitations in paragraph (l) of this AD 
are also included as an enclosure to FAA Letter 140S-06-343, dated 
November 17, 2006.


 Table 2--Actions for Which Paragraph (h)(1) of This AD Is an Acceptable Method of Compliance (With Certificate
                                                  Limitations)
----------------------------------------------------------------------------------------------------------------
            The action in--                                                Of--
----------------------------------------------------------------------------------------------------------------
(1) Paragraph (a)......................  AD 2001-12-21, amendment 39-12277.
(2) Paragraph (a)......................  AD 2001-21-07, amendment 39-12478.
(3) Paragraph (c)(2)...................  AD 2002-19-52, amendment 39-12900.
(4) Paragraph (a)......................  AD 2002-24-52, amendment 39-12993.
----------------------------------------------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (m)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. Send information to ATTN: Jon 
Regimbal, Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle 
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 917-6506; fax (425) 917-6590. 
Or, e-mail information to [email protected].
    (2) To request a different method of compliance or a different 
compliance

[[Page 26322]]

time for this AD, follow the procedures in 14 CFR 39.19. Before using 
any approved AMOC on any airplane to which the AMOC applies, notify 
your principal maintenance inspector (PMI) or principal avionics 
inspector (PAI), as appropriate, or lacking a principal inspector, your 
local Flight Standards District Office. The AMOC approval letter must 
specifically reference this AD.

    Issued in Renton, Washington, on May 11, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-12742 Filed 6-1-09; 8:45 am]
BILLING CODE 4910-13-P