
[Federal Register Volume 75, Number 127 (Friday, July 2, 2010)]
[Rules and Regulations]
[Pages 38397-38404]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-15935]



[[Page 38397]]

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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; 
Amendment 39-16353; AD 2010-14-08]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Model 747-400, 747-400D, and 747-400F series airplanes. For all 
airplanes, this AD requires 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 tank 
override/jettison fuel pumps; and, for certain airplanes, installing 
new relays and wiring for the horizontal stabilizer override/jettison 
fuel pumps. This AD also requires a revision to the maintenance program 
to incorporate Airworthiness Limitation No. 28-AWL-24 and No. 28-AWL-
26. For certain airplanes, this AD also requires installing an 
automatic shutoff system for the horizontal stabilizer tank fuel pumps 
and installing new integrated display system software. 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.

DATES: This AD is effective August 6, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of August 6, 
2010.

ADDRESSES: 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 me.boecom@boeing.com; 
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 AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Document Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Douglas Bryant, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 917-6505; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an airworthiness directive (AD) that would apply to 
certain Model 747-400, 747-400D, and 747-400F series airplanes. That 
NPRM was published in the Federal Register on June 2, 2009 (74 FR 
26317). That NPRM proposed to 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 tank 
override/jettison fuel pumps; and, for certain airplanes, installing 
new relays and wiring for the horizontal stabilizer override/jettison 
fuel pumps. That NPRM also proposed to require a revision to the 
maintenance program to incorporate Airworthiness Limitation No. 28-AWL-
24 and No. 28-AWL-26. For certain airplanes that NPRM proposed to 
require installing an automatic shutoff system for the horizontal 
stabilizer tank fuel pumps and installing new integrated display system 
software.

Explanation of Revised Service Information

    Boeing has published Boeing Service Bulletins 747-28A2280 and 747-
28A2281, both Revision 1, both dated November 25, 2009. In the NPRM, we 
referred to the original issues of Boeing Alert Service Bulletin 747-
28A2280, dated August 7, 2008; and Boeing Alert Service Bulletin 747-
28A2281, dated December 13, 2007. We referred to the original versions 
of these service bulletins as the appropriate sources of service 
information for accomplishing certain proposed actions. The procedures 
in Revision 1 of these service bulletins are essentially the same as 
those in the original issue of these service bulletins. Revision 1 
clarifies certain work instructions and specifies that no further work 
is necessary for airplanes on which the actions in the original issue 
were performed. Boeing Service Bulletin 747-28A2281, Revision 1, dated 
November 25, 2009, also removes airplanes having variable numbers RT966 
and RT967 from the effectivity. These airplanes are not equipped with 
horizontal stabilizer tanks and therefore are not affected by the 
identified unsafe condition.
    Boeing has also published Boeing Service Bulletin 747-28A2262, 
Revision 2, dated August 13, 2009. In the NPRM, we referred to Boeing 
Service Bulletin 747-28A2262, Revision 1, dated May 8, 2008, for 
accomplishing the installation of a new automatic shutoff system for 
the horizontal stabilizer tank (HST) fuel pumps, before or at the same 
time as the actions in Boeing Service Bulletin 747-28A2281. The 
procedures in Boeing Service Bulletin 747-28A2262, Revision 2, dated 
August 13, 2009, are essentially the same as those in Boeing Service 
Bulletin 747-28A2262, Revision 1, dated May 8, 2008. Revision 2 
clarifies certain work instructions and specifies that no further work 
is necessary for airplanes on which the actions in Revision 1 were 
performed.
    Therefore, we have changed this AD to refer to these revised 
service bulletins as the appropriate sources of service information for 
the applicable actions. We have also added a new paragraph (i) to this 
AD that specifies that actions done before the effective date of this 
AD in accordance with the previous issues of these service bulletins 
are acceptable for compliance with the corresponding requirements of 
this AD.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received.

Request to Clarify Certain Language

    Boeing asks that the term ``Integrated Display System (IDS)'' be 
changed to ``IDS software'' in all applicable sections of the NPRM. 
Boeing states that this change clarifies that the actions in the NPRM 
are for a software change to the IDS and not a change to the IDS 
hardware.
    We agree with the Boeing comment for the reason given. We have 
added the word ``software'' after all references to the IDS in this AD.

[[Page 38398]]

Request To Remove Certain Airplanes

    Boeing asks that Model 747-400D and -400F airplanes be removed from 
paragraph (l) of the NPRM. Boeing states that Model 747-400D and -400F 
airplanes are not affected by the horizontal stabilizer tank (HST) 
changes because those airplanes do not have a HST.
    We agree with the Boeing comment for the reason provided. We have 
removed Model 747-400D and -400F airplanes from paragraph (m) of this 
AD (paragraph (m) was referred to as paragraph (l) in the NPRM).

Request To Remove Airplane Flight Manual (AFM) Limitation

    Boeing asks that we remove the reference to the following AFM 
limitations: ``The 17,000-lb center wing tank (CWT) minimum fuel amount 
to select the CWT override/jettison pumps ON during takeoff'' and 
``There is no change to the maximum zero fuel gross weight found in the 
airplane flight manual.'' Boeing states that the NPRM should be 
consistent with the AFM certificate limitations contained in AD 2007-
13-04, Amendment 39-15108 (72 FR 33859, June 20, 2007). Boeing adds 
that in discussions regarding AFM limitations in this AD it was agreed 
that AFM limitations were not required for an obvious pilot action 
driven by engine indicating and crew alerting system (EICAS) messages.
    We agree with the Boeing comment for the reasons provided and 
because the certification limitation for CWT minimum fuel is covered by 
EICAS messages, which makes it redundant. We have removed the subject 
limitations and changed the FAA letter concerning these limitations 
referred to in Note 3 of this AD.

Request To Remove Airworthiness Limitation (AWL) 28-AWL-26

    Boeing asks that we remove the requirement to revise the 
maintenance program by incorporating AWL No. 28-AWL-26 of Section 9, 
``Airworthiness Limitations (AWLs) and Certification Maintenance 
Requirements (CMRs)'' of the Boeing 747-400 Maintenance Planning Data 
Document D621U400-9. Boeing states that, with the introduction of IDS-
506 software, it has implemented a status level EICAS message for the 
relays that control the Uncommanded-ON state of the main 2 and main 3 
tank fuel override/jettison pumps. Boeing adds that these messages are 
now consistent with the center tank Uncommanded-ON messages. Boeing 
notes that the EICAS message will detect a relay that remains latched 
when in the un-powered condition. Boeing concludes that for this 
reason, the need to perform the operational test found in Section 28-
31-00 of the Boeing 747-400 airplane maintenance manual (AMM), and 
called out in AWL No. 28-AWL-26, is not necessary.
    We disagree with the Boeing comment. The AWL is part of the 
airplane type design, and a design change has not been proposed to 
change the AWL. However, under the provisions of paragraph (p)(1) of 
the AD, we will consider removing the requirement if sufficient data 
are submitted to substantiate that a project has been completed showing 
that removing the requirement would provide an acceptable level of 
safety. We have made no change to the AD in this regard.

Request To Clarify the Requirements for Airplanes With a Deactivated 
HST

    Japan Airlines (JAL) asks that we clarify the NPRM requirements for 
airplanes with a deactivated HST. JAL states that it decided to 
deactivate the HST system in accordance with Boeing Service Bulletins 
747-28-2310, dated December 18, 2008; and 747-28-2314, dated December 
9, 2008. JAL adds that the service bulletins specify removing 
components, including the pumps on horizontal stabilizer fuel tank 
(HSFT), and reworking the system wiring. JAL notes that after the 
service bulletins have been incorporated, paragraphs (g)(2), (h)(2), 
and (l) of the NPRM will not apply. JAL asks that an additional 
description be included in the AD which clarifies that the requirements 
in those paragraphs are only for airplanes with an active HSFT. JAL 
suggests clarifying the applicability as follows: ``For Model 747-400 
series airplanes with the active horizontal stabilizer tank.'' In lieu 
of that sentence, JAL suggests a note that specifies the following: 
``The airplanes with the horizontal stabilizer tank deactivated in 
accordance with Boeing Service Bulletin are not applicable.'' JAL 
concludes that this additional description will save on superfluous 
paperwork.
    We partially agree with the JAL comments. We agree that the 
applicability should be clarified for airplanes with a deactivated HST 
because those airplanes have adequately addressed the unsafe condition. 
However, we do not agree with using the language JAL provided because 
it leaves ``active'' open to interpretation. Deactivation of a HST 
according to the applicable Boeing service bulletin referred to in 
Table 3 of this AD is the only acceptable method of compliance. We have 
added new paragraphs (n) and (o) to this AD (and reidentified 
subsequent paragraphs) to provide optional terminating action if the 
HST is deactivated and to reinstate the requirements if the HST is 
later reactivated.

Request for Analytical Justification of the Compliance Time

    Lufthansa German Airlines (Lufthansa) asks that we provide 
justification (including statistical and probabilistic background) for 
the compliance time in the NPRM. Lufthansa reiterates the NPRM 
requirements and notes that it assumes that the failure probability is 
part of the determination of the proposed compliance time of 60 months 
for the installations and wiring changes.
    We acknowledge the commenter's request and provide the following 
explanation. As stated in the preamble of the NPRM, ``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 ignition source can come from several sources seen in 
service that were not originally anticipated in the airplane design. 
Examples of those are friction in the pump which could lead to very 
high internal surface temperatures caused by mechanical failures or 
ingestion of debris into the pump, and electrical faults leading to 
internal arcs or pump case burn-through. Since there are several pumps 
in multiple fuel tanks, depending on the configuration of the airplane, 
there are several possible single failures on a given airplane. This is 
a single failure which cannot be reliably predicted with statistical 
and probabilistic methods.
    Currently, we are reliant on crew procedures to shut off the pumps 
early to mitigate the single failure risk. We are aware of accounts of 
pilots failing to turn pumps off due to the relatively short time 
between the points when the tank reaches the desired shutoff level and 
the pump runs dry. Given the multiple sources of a single failure that 
can cause ignition, and acknowledging the limited effectiveness of the 
current mitigating actions, we consider that this is an issue that 
requires action to return to the failsafe intent of the design.
    When we determine that a safety issue warrants AD action, we 
ascertain how quickly that issue can be eliminated based on the actions 
proposed by the manufacturer and other related factors.

[[Page 38399]]

This determination includes the safety issue, the time necessary to 
perform the work on an airplane, the number of affected operators, and 
parts availability. For major modification involving large fleets, and 
requiring specialized facilities, we consider the overall industry 
ability to perform the modification on all affected airplanes in a 
timely manner. Based on these considerations, we determine a compliance 
time that minimizes risk, as well as the impact on commercial airlines. 
We try to align compliance times with the majority of operators' 
maintenance schedules, but that is dependent on the severity of the 
unsafe condition. In light of this analysis, we have determined that a 
60-month compliance time is appropriate for this AD. We have made no 
change to the AD in this regard.

Requests To Extend Compliance Time

    Lufthansa also states that the 60-month compliance time is not in 
line with its heavy maintenance overlay schedule, which is based on the 
latest approved maintenance review board document, and asks for an 
extension to 72 months. Air Transport Association (ATA), on behalf of 
its member United Airlines (United), asks that the compliance time be 
extended to 72 months in order to allow accomplishment of the proposed 
modifications during heavy maintenance visits. KLM Royal Dutch Airlines 
(KLM) asks that the compliance time be extended to 8 years, which 
enables KLM to schedule the modification during a D-check without 
additional downtime requirements. JAL also asks that the compliance 
time be extended to 8 years because accomplishing the modification is 
extensive work which can only be done during an M check for heavy 
maintenance. Cargolux also asks that the compliance time be extended to 
8 years to coincide with its D-check heavy maintenance interval.
    We do not agree with the commenters' requests. In developing an 
appropriate compliance time for the modification, we considered the 
safety implications and the practical aspect of accomplishing the 
modification within a period of time that corresponds to the normal 
scheduled maintenance for most affected operators. In consideration of 
these items, and as noted under the Request for Analytical 
Justification of the Compliance Time, we have determined that a 60-
month compliance time will ensure an acceptable level of safety and 
allow the modification to be done during scheduled maintenance 
intervals for most affected operators. However, under the provisions of 
paragraph (p)(1) of the AD, we will consider requests to adjust the 
compliance time if sufficient data are submitted to substantiate that 
the new compliance time would provide an acceptable level of safety. We 
have made no change to the AD in this regard.
    Cargolux adds that if the compliance time is extended to 8 years, 
in the interim, it proposes to have the override jettison pump push 
buttons replaced with switches having a configuration ``D'' master 
module within 6 months after the effective date of the forthcoming AD. 
Cargolux states that this will prevent the ``cap pop-up'' or 
``jamming'' condition of the switch.
    We disagree with the Cargolux proposal to replace push buttons as 
mitigating action to allow for extending the compliance time to 8 
years, because its replacement is insufficient to mitigate the unsafe 
condition caused by possible single failures. We are aware of the 
problems with the push buttons and we are considering a separate 
rulemaking action. The faulty pressure switches are not related to this 
unsafe condition because they are not part of the pump power control 
circuit. We have made no change to the AD in this regard.

Request To Increase Work Hours and Include Parts Cost in the Costs of 
Compliance

    ATA, on behalf of United, states that the estimate for labor and 
parts in the NPRM is understated. United notes that Boeing Alert 
Service Bulletin 747-28A2281, dated December 13, 2007, estimates that 
it would take 101 to 107 work hours per product to install relays and 
wiring for the HST. United adds that this service bulletin also 
includes the kits of parts necessary for the modification, and 
indicates that the pricing for the kits can be obtained from Boeing 
spares. United also states that the work hours are underestimated for 
Boeing Alert Service Bulletin 747-28A2280, dated August 7, 2008; and 
Boeing Service Bulletin 747-28A2262, Revision 1, dated May 8, 2008.
    We infer that the commenter is asking to increase the work hours 
and include the cost of certain parts. We do not agree that the work 
hours are underestimated. The cost information in an AD describes only 
the direct costs of the specific actions required by this AD. Based on 
the best data available, the manufacturer provided the number of work 
hours necessary to do the required actions. This number represents the 
time necessary to perform only the actions actually required by this 
AD. We agree that the parts cost, which was inadvertently omitted from 
the Costs of Compliance table in the service bulletin, should be 
included because all three of these service bulletins have been 
revised. We have changed the Estimated Costs table to reduce certain 
work hours and increase the parts cost in the first row of the table to 
match Boeing Service Bulletins 747-28A2280 and 747-28A2281, both 
Revision 1, both dated November 25, 2009; and Boeing Service Bulletin 
747-28A2262, Revision 2, dated August 13, 2009. We have also included 
the parts cost in the third row of the table, and changed the costs per 
product and fleet costs in the table accordingly.

Explanation of Change to Applicability

    We have changed the applicability in this AD to identify model 
designations as published in the most recent type certificate data 
sheet for the affected models.

Explanation of Additional Change to ``Certificate Limitations'' Section

    We have removed the fourth note under ``Certificate Limitations'' 
in this AD for consistency with prior FAA approvals. The note specified 
the following: ``The CWT and the HST may be emptied normally during an 
emergency.''

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously. We also determined that 
these changes will not increase the economic burden on any operator or 
increase the scope of the AD.

Explanation of Additional Change to Costs of Compliance

    Since issuance of the NPRM, we have increased the labor rate used 
in the Costs of Compliance from $80 per work hour to $85 per work hour. 
The Costs of Compliance information, below, reflects this increase in 
the specified hourly labor rate.

Costs of Compliance

    We estimate that this AD would affect 102 airplanes of U.S. 
registry. The following table provides the estimated costs for U.S. 
operators to comply with this AD. The average labor rate is $85 per 
work hour.

[[Page 38400]]



                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                           Number of U.S.-
              Action                     Work hours               Parts             Cost per product          registered              Fleet cost
                                                                                                              airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Installing relays/changing wiring   369 to 389.........  $75,007 to $75,894....  $106,372 to $108,959..  102................  $10,849,944 to
 for center and main fuel tanks.                                                                                               $11,113,818.
Installing new IDS software and     2 to 3.............  $0....................  Up to $255............  Up to 102..........  Up to $26,010.
 revising the AFM when done (prior/
 concurrent action).
Installing relays and wiring for    73 to 79...........  $5,778 to $6,486......  $11,983 to $13,201....  74.................  $886,742 to $976,874.
 horizontal stabilizer tank (HST).
Installing a new automatic shutoff  44.................  $4,112................  $7,852................  74.................  $581,048.
 for the HST.
Revising the maintenance program..  1..................  $0....................  $85...................  102................  $8,670.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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

    This AD will not have federalism implications under Executive Order 
13132. This AD will 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under 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.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2010-14-08 The Boeing Company: Amendment 39-16353. Docket No. FAA-
2009-0454; Directorate Identifier 2008-NM-156-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective August 6, 
2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to The Boeing Company Model 747-400, 747-
400D, and 747-400F series airplanes, certificated in any category; 
as identified in Boeing Service Bulletins 747-28A2280, Revision 1, 
dated November 25, 2009, and 747-28A2281, Revision 1, dated November 
25, 2009.

    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 (p)(1) 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, 747-400D, and 747-400F 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 
Service Bulletin 747-28A2280, Revision 1, dated November 25, 2009. 
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 Service 
Bulletin 747-28A2281, Revision 1, dated November 25, 2009.

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, 747-400D, and 747-400F series airplanes 
identified in paragraphs (h)(1)(i), (h)(1)(ii), and (h)(1)(iii) of 
this AD: Install new integrated display system (IDS) software in 
accordance with the

[[Page 38401]]

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, 747-400D, and 747-400F 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 747-400F 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 747-400F 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 2, dated August 13, 2009.

Credit for Actions Done According to Previous Issues of Service 
Bulletins

    (i) Actions done before the effective date of this AD in 
accordance with the applicable service information contained in 
Table 1 of this AD are acceptable for compliance with the 
corresponding actions required by paragraphs (g) and (h) of this AD.

                                       Table 1--Credit Service Information
----------------------------------------------------------------------------------------------------------------
                  Document                             Revision                            Date
----------------------------------------------------------------------------------------------------------------
Boeing Alert Service Bulletin                Original...................  August 7, 2008.
 747[dash]28A2280.
Boeing Alert Service Bulletin                Original...................  December 13, 2007.
 747[dash]28A2281.
Boeing Service Bulletin 747-28A2262........  Original...................  March 15, 2007.
Boeing Service Bulletin 747-28A2262........  1..........................  May 8, 2008.
----------------------------------------------------------------------------------------------------------------

Maintenance Program Revision

    (j) 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),'' of the Boeing 747-
400 Maintenance Planning Data (MPD) 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

    (k) After accomplishing the action specified in paragraph (j) 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 (p)(1) of this 
AD.

Acceptable Action for Certain ADs

    (l) For Model 747-400, -400D, and -400F series airplanes: 
Installing new IDS software 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.

  Table 2--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.
----------------------------------------------------------------------------------------------------------------

    (m) For Model 747-400 series airplanes with a horizontal 
stabilizer fuel tank and with horizontal stabilizer tank fuel pump 
auto-shutoff installed: Installing new IDS software 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 3 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 3 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.
    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 (HST) is fueled and used:
    The 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 CWT, 3,000 pounds (1,400 kilograms) 
for main tanks, and 2,100 pounds (1,000 kilograms) for the HST. 
(These requirements apply for defueling or transferring between 
tanks.)

[[Page 38402]]

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

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

    Note 2: When a statement identical to that in paragraph (m) 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 (m) of this AD 
are also included as an enclosure to FAA Letter 140S-09-191, dated 
June 23, 2009.


 Table 3--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.
----------------------------------------------------------------------------------------------------------------

Optional Terminating Action for Paragraphs (g)(2), (h)(2), and (m) of 
this AD: Deactivation of the HST

    (n) Deactivation of the HST, in accordance with the applicable 
Boeing service information in Table 4 of this AD, terminates the 
requirements of paragraphs (g)(2), (h)(2), and (m) of this AD, 
except as provided by paragraph (o) of this AD. Deactivation of the 
HST before the effective date of this AD in accordance with the 
applicable service information in Table 5 of this AD also terminates 
the requirements of paragraphs (g)(2), (h)(2), and (m) of this AD, 
except as provided by paragraph (o) of this AD.

                Table 4--Deactivation Service Information
------------------------------------------------------------------------
  Boeing Service Information      Revision               Date
------------------------------------------------------------------------
Service Bulletin 747-28-2247.  Original.....  November 26, 2002.
Service Bulletin 747-28-2265.  Original.....  February 22, 2006.
Service Bulletin 747-28-2272.  Original.....  February 21, 2006.
Service Bulletin 747-28-2274.  1............  May 21, 2008.
Service Bulletin 747-28-2275.  4............  February 2, 2009.
Service Bulletin 747-28-2279.  2............  October 16, 2007.
Service Bulletin 747-28-2285.  3............  August 30, 2007.
Service Bulletin 747-28-2293.  2............  March 4, 2008.
Service Bulletin 747-28-2295.  2............  January 19, 2009.
Service Bulletin 747-28-2296.  Original.....  July 13, 2007.
Service Bulletin 747-28-2300.  1............  June 2, 2008.
Service Bulletin 747-28-2310.  Original.....  December 18, 2008.
Service Bulletin 747-28-2314.  Original.....  December 9, 2008.
------------------------------------------------------------------------


            Table 5--Deactivation Credit Service Information
------------------------------------------------------------------------
  Boeing Service Information      Revision               Date
------------------------------------------------------------------------
Service Bulletin 747-28-2274.  Original.....  March 13, 2006.
Service Bulletin 747-28-2275.  Original.....  June 12, 2006.
Service Bulletin 747-28-2275.  1............  March 16, 2007.
Service Bulletin 747-28-2275.  2............  July 2, 2007.
Service Bulletin 747-28-2275.  3............  March 11, 2008.
Service Bulletin 747-28-2279.  Original.....  June 12, 2006.
Service Bulletin 747-28-2279.  1............  May 25, 2007.
Service Bulletin 747-28-2285.  Original.....  January 23, 2007.
Service Bulletin 747-28-2285.  1............  May 9, 2007.
Service Bulletin 747-28-2285.  2............  August 3, 2007.
Service Bulletin 747-28-2293.  Original.....  May 9, 2007.
Service Bulletin 747-28-2293.  1............  August 29, 2007.
Service Bulletin 747-28-2295.  Original.....  November 17, 2006.
Service Bulletin 747-28-2295.  1............  March 20, 2008.
Service Bulletin 747-28-2300.  Original.....  January 16, 2008.
------------------------------------------------------------------------


[[Page 38403]]

Reactivation of the HST

    (o) For any airplane on which the HST is reactivated, the HST 
must be reactivated in accordance with a method approved by the 
Manager, Seattle Aircraft Certification Office (ACO), FAA. For any 
airplane on which the HST is reactivated, the requirements of 
paragraphs (g)(2), (h)(2), and (m) of this AD must be done before 
further flight following the reactivation, or within 60 months after 
the effective date of this AD, whichever occurs later. For a 
reactivation method to be approved, the reactivation method must 
meet the certification basis of the airplane, and the approval must 
specifically reference this AD.

Alternative Methods of Compliance (AMOCs)

    (p)(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: Douglas Bryant, Aerospace Engineer, Propulsion Branch, ANM-
140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, 
SW., Renton, Washington 98057-3356; telephone (425) 917-6505; fax 
(425) 917-6590. Or, e-mail information to 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) To request a different method of compliance or a different 
compliance 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.

Material Incorporated by Reference

    (q) You must use the service information contained in Table 6 of 
this AD, as applicable, to do the actions required by this AD, 
unless the AD specifies otherwise.

          Table 6--Required Material Incorporated by Reference
------------------------------------------------------------------------
  Boeing Service Information      Revision               Date
------------------------------------------------------------------------
Service Bulletin 747-28A2280.  1............  November 25, 2009.
Service Bulletin 747-28A2281.  1............  November 25, 2009.
Section 9, ``Airworthiness     April 2008...  April 2008.
 Limitations (AWLs) and
 Certification Maintenance
 Requirements (CMRs),'' of
 the 747-400 Maintenance
 Planning Data (MPD) Document
 D621U400-9.
Service Bulletin 747-28A2262.  2............  August 13, 2009.
Service Bulletin 747-31-2376.  Original.....  September 5, 2006.
Service Bulletin 747-31-2377.  Original.....  September 5, 2006.
Service Bulletin 747-31-2378.  Original.....  September 5, 2006.
------------------------------------------------------------------------

    If you accomplish the optional actions specified in this AD, you 
must use the service information specified in Table 7 of this AD, as 
applicable, to perform those actions unless the AD specifies 
otherwise.

          Table 7--Optional Material Incorporated by Reference
------------------------------------------------------------------------
  Boeing Service Information      Revision               Date
------------------------------------------------------------------------
Service Bulletin 747-28-2247.  Original.....  November 26, 2002.
Service Bulletin 747-28-2265.  Original.....  February 22, 2006.
Service Bulletin 747-28-2272.  Original.....  February 21, 2006.
Service Bulletin 747-28-2274.  1............  May 21, 2008.
Service Bulletin 747-28-2275.  4............  February 2, 2009.
Service Bulletin 747-28-2279.  2............  October 16, 2007.
Service Bulletin 747-28-2285.  3............  August 30, 2007.
Service Bulletin 747-28-2293.  2............  March 4, 2008.
Service Bulletin 747-28-2295.  2............  January 19, 2009.
Service Bulletin 747-28-2296.  Original.....  July 13, 2007.
Service Bulletin 747-28-2300.  1............  June 2, 2008.
Service Bulletin 747-28-2310.  Original.....  December 18, 2008.
Service Bulletin 747-28-2314.  Original.....  December 9, 2008.
------------------------------------------------------------------------


[[Page 38404]]

    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) 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 
me.boecom@boeing.com; Internet https://www.myboeingfleet.com.
    (3) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on June 17, 2010.
Robert D. Breneman,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-15935 Filed 7-1-10; 8:45 am]
BILLING CODE 4910-13-P


