[Federal Register Volume 72, Number 131 (Tuesday, July 10, 2007)]
[Proposed Rules]
[Pages 37479-37484]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-13326]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28661; Directorate Identifier 2007-NM-013AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 737-600, -700, -700C, -
800, and -900 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Boeing Model 737-600, -700, -700C, -800, and -900 series 
airplanes. This proposed AD would require installation of an automatic 
shutoff system for the center tank fuel boost pumps, installation of a 
placard in the airplane flight deck if necessary, and concurrent 
modification of the P5-2 fuel control module assembly. This proposed AD 
would also require revisions to the Limitations and Normal Procedures 
sections of the airplane flight manual to advise the flightcrew of 
certain operating restrictions for airplanes equipped with an automated 
center tank fuel pump shutoff control. This proposed AD would also 
require a

[[Page 37480]]

revision to the Airworthiness Limitations (AWLs) section of the 
Instructions for Continued Airworthiness to incorporate AWL No. 28-AWL-
19 and No. 28-AWL-23. This proposed AD would also require installation 
of two secondary override fuel pump control relays to each existing 
primary override fuel pump control relay for the center fuel tank fuel 
boost pumps. This proposed AD results from fuel system reviews 
conducted by the manufacturer. We are proposing this AD to prevent 
center tank fuel pump operation with continuous low pressure, which 
could lead to friction sparks or overheating in the fuel pump inlet or 
could create a potential ignition source inside the center fuel tank; 
these conditions, in combination with flammable fuel vapors, could 
result in a center fuel tank explosion and consequent loss of the 
airplane.

DATES: We must receive comments on this proposed AD by August 24, 2007.

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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room W12-140 on the ground floor of the 
West Building, 1200 New Jersey Avenue SE., 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 the service information identified in this 
proposed AD.

FOR FURTHER INFORMATION CONTACT: Kathrine Rask, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Ave SW., Renton, Washington 98057-3356; telephone 
(425) 917-6505; 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 ``FAA-2007-
28661; Directorate Identifier 2007-NM-013-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 DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
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 Operations office between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The 
Docket Operations office (telephone (800) 647-5527) is located on the 
ground floor of the West 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'' 
(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 proposed 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.
    Boeing has found that certain failures will result in the center 
tank fuel pumps continuing to run after the tank has been depleted. 
Depending on the failure, pump low pressure may not be annunciated, or 
power may not be removed from the pump when the pump has been commanded 
``OFF.'' Operation of the center tank fuel pump with continuous low 
pressure could lead to friction sparks or overheating in the fuel boost 
pump inlet. This condition, if not corrected, could result in a fuel 
tank explosion and consequent loss of the airplane.

Other Relevant Rulemaking

    On April 18, 2001, we issued AD 2001-08-24, amendment 39-12201 (66 
FR 20733, April 25, 2001), applicable to all Boeing Model 737 
airplanes. That AD requires revising the airplane flight manual (AFM) 
to prohibit extended dry operation of the center tank fuel pumps (with 
no fuel passing through the pumps). Accomplishing the actions

[[Page 37481]]

specified in paragraphs (g), (h), (i), (j), and (k) of this proposed AD 
would terminate the AFM revision required by paragraph (a) of AD 2001-
08-24 for Model 737-600, -700, -700C, -800, and -900 series airplanes 
that have the automatic shutoff system installed.
    On September 24, 2002, we issued AD 2002-19-52, amendment 39-12900 
(67 FR 61253, September 30, 2002), applicable to all Boeing Model 737-
600, -700, -700C, -800, and -900 series airplanes, Model 747 airplanes, 
and Model 757 airplanes. That AD requires revising the AFM to advise 
the flightcrew of certain operating restrictions for maintaining 
minimum fuel levels, prohibits use of the horizontal stabilizer tank on 
certain airplanes, and prohibits the installation of certain fuel 
pumps. That AD requires concurrent removal of the currently required 
AFM revisions and insertion of new AFM revisions, requires installation 
of placards to alert the flightcrew to the operating restrictions, and 
prohibits installation of any un-inspected pumps. That AD permits the 
AFM revision and placard to be removed under certain conditions. 
Installation of a placard in accordance with paragraph (e) of AD 2002-
19-52, amendment 39-12900, is acceptable for compliance with paragraph 
(h) of this AD.
    On November 23, 2002, we issued emergency AD 2002-24-51, amendment 
39-12992, applicable to all Boeing Model 737-600, -700, -700C, -800, 
and -900 series airplanes, Model 747 airplanes, and Model 757 
airplanes. (We issued a Federal Register version of AD 2002-24-51 on 
December 23, 2002 (68 FR 10, January 2, 2003).) That AD requires 
revising the AFM to require the flightcrew to maintain certain minimum 
fuel levels in the center fuel tanks and, for certain airplanes, to 
prohibit the use of the horizontal stabilizer fuel tank and certain 
center auxiliary fuel tanks. Accomplishing the actions specified in 
paragraphs (g), (h), (i), (j), and (k) of this proposed AD would 
terminate the AFM revision specified in paragraph (b) of AD 2002-24-51 
for Model 737-600, -700, -700C, -800, and -900 series airplanes that 
have the automatic shutoff system installed.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 737-28A1206, dated 
January 11, 2006. This service bulletin describes procedures for 
installing an automatic shutoff system for the center tank fuel boost 
pumps. Installation of the automatic shutoff system includes the 
following actions:
     In the J4 junction box, changing wiring and connector 
termination positions and installing relays, transformers, markers, and 
wires to a certain wire bundle.
     In the J20 junction box, changing wiring and installing 
relays, markers, and wires to a certain wire bundle.
     At the P5 overhead panel in the flight compartment, 
replacing the P5-2 fuel control module with a reworked P5-2 fuel 
control module.
     In the flight compartment, installing the P61-8 fuel test 
panel and installing circuit breakers and markers in the P6-3 circuit 
breaker panel.
     Adding wiring to certain wire bundles in the P6 circuit 
breaker panel, between the flight and electronics compartment, in the 
J4 and J20 junction boxes, in the E2-1 and E4-2 electronics shelves in 
the electrical compartment, between the E2-1 electronics shelf and the 
P5-2 fuel control panel, between the E4-2 electronics shelf and the P5-
2 fuel control panel, between the E2-1 electronics shelf and the J20 
junction box, and between the E4-2 electronics shelf and the J4 
junction box.
    We have also reviewed Boeing Alert Service Bulletin 737-28A1248, 
dated December 21, 2006. This service bulletin describes procedures for 
installing two secondary override fuel pump control relays to each 
existing primary override fuel pump control relay for the center fuel 
tank fuel boost pumps. The installation includes installing a new 
overlay marker and Brady label, changing and adding certain wires, and 
connecting the new relays to the power distribution panel.
    We have also reviewed Revision December 2005 and Revision May 2006 
of Section 9 of the Boeing 737-600/700/700C/700IGW/800/900 Maintenance 
Planning Data (MPD) Document, D626A001-CMR (hereafter referred to as 
``the MPD''). Subsection F, ``AIRWORTHINESS LIMITATIONS--FUEL SYSTEM 
AWLs,'' of the MPD describes new airworthiness limitations (AWLs) for 
fuel tank systems. The AWLs include:
     AWL inspections, which are periodic inspections of certain 
features for latent failures that could contribute to an ignition 
source.
     Critical design configuration control limitations 
(CDCCLs), which are limitation requirements to preserve a critical 
ignition source prevention feature of the fuel tank system design that 
is necessary to prevent the occurrence of an unsafe condition. The 
purpose of a CDCCL is to provide instruction to retain the critical 
ignition source prevention feature during configuration change that may 
be caused by alterations, repairs, or maintenance actions. A CDCCL is 
not a periodic inspection.
    Subsection F of the MPD, Revision December 2005, adds new fuel 
system AWL No. 28-AWL-19, which is a repetitive inspection of the 
automatic shutoff system for the center tank fuel boost pumps to verify 
functional integrity. Subsection F of the MPD, Revision May 2006, adds 
new fuel system AWL No. 28-AWL-23, which is a repetitive inspection of 
the power failed on protection system for the center tank fuel boost 
pumps to verify functional integrity.
    Boeing Alert Service Bulletin 737-28A1206 recommends concurrent 
accomplishment of Boeing Component Service Bulletin 233A3202-28-03, 
dated January 12, 2006. Boeing Component Service Bulletin 233A3202-28-
03 describes procedures for replacing the left and right center boost 
pump switches of the P5-2 fuel control module assembly with new 
switches and changing the wiring of the P5-2 fuel control module 
assembly.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of this same type design. For this reason, we are proposing this AD, 
which would require the following actions:
     Installation of an automatic shutoff system for the center 
tank fuel boost pumps.
     Installation of a placard in the airplane flight deck, if 
necessary. (Placards are necessary only for ``mixed fleet operation,'' 
which means that some airplanes in an operator's fleet are equipped 
with automatic shutoff systems while other airplanes are not.)
     Concurrent modification of the P5-2 fuel control module 
assembly.
     Revisions to the Limitations and Normal Procedures 
sections of the AFM to advise the flightcrew of certain operating 
restrictions for airplanes equipped with an automated center tank fuel 
pump shutoff control.
     Revision to the AWLs section of the Instructions for 
Continued Airworthiness to incorporate AWL No. 28-AWL-19, which would 
require repetitive inspections of the automatic shutoff system for the 
center tank fuel boost pumps to verify functional integrity.

[[Page 37482]]

     Installation of two secondary override fuel pump control 
relays to each existing primary override fuel pump control relay for 
the center fuel tank fuel boost pumps.
     Revision to the AWLs section of the Instructions for 
Continued Airworthiness to incorporate AWL No. 28-AWL-23, which would 
require repetitive inspections of the power failed on protection system 
for the center tank fuel boost pumps to verify functional integrity.
    This proposed AD would also allow accomplishing the revision to the 
AWLs section of the Instructions for Continued Airworthiness in 
accordance with later revisions of the MPD as an acceptable method of 
compliance if they are approved by the Manager, Seattle Aircraft 
Certification Office (ACO), FAA.

Costs of Compliance

    There are about 2,109 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs, at 
an average labor rate of $80 per work hour, for U.S. operators to 
comply with this proposed AD. The estimated cost of parts for 
installing an automatic shutoff system depends on the configuration of 
an airplane.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Number of
                                                                                      U.S.-
            Action               Work hours        Parts        Cost per airplane   registered     Fleet cost
                                                                                    airplanes
----------------------------------------------------------------------------------------------------------------
Installation of the automatic            89  $23,072 to         $30,192 to                 616  $18,598,272 to
 shutoff system.                              $34,559.           $41,679.                        $25,674,264.
Placard installation, if                  1  $10..............  $90..............          616  $55,440.
 necessary.
Concurrent modification of                9  $3,815...........  $4,535...........          616  $2,793,560.
 fuel control module assembly.
AFM revision..................            1  None.............  $80..............          616  $49,280.
AWL revision to add 28-AWL-19.            1  None.............  $80..............          616  $49,280.
Installation of secondary pump           65  $2,964...........  $8,164...........          726  $5,927,064.
 control relays.
AWL revision to add 28-AWL-23.            1  None.............  $80..............          726  $58,080.
----------------------------------------------------------------------------------------------------------------

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 
adding the following new airworthiness directive (AD):

Boeing: Docket No. FAA-2007-28661; Directorate Identifier 2007-NM-
013-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by August 
24, 2007.

Affected ADs

    (b) Accomplishing certain paragraphs of this AD terminates 
certain requirements of AD 2001-08-24, amendment 39-12201, and 
terminates certain requirements of AD 2002-24-51, amendment 39-
12992.

Applicability

    (c) This AD applies to Boeing Model 737-600, -700, -700C, -800, 
and -900 series airplanes, certificated in any category; as 
identified in Boeing Alert Service Bulletin 737-28A1248, dated 
December 21, 2006.

    Note 1: This AD requires revisions to certain operator 
maintenance documents to include new inspections of the automatic 
shutoff system for the center tank fuel boost pumps. Compliance with 
these inspections is required by 14 CFR 43.16 and 91.403(c). For 
airplanes that have been previously modified, altered, or repaired 
in the areas addressed by these inspections, 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 according 
to paragraph (p) of this AD. The request should include a 
description of changes to the required inspections that will ensure 
acceptable maintenance of the automatic shutoff system.

Unsafe Condition

    (d) This AD results from fuel system reviews conducted by the 
manufacturer. We are issuing this AD to prevent center tank

[[Page 37483]]

fuel pump operation with continuous low pressure, which could lead 
to friction sparks or overheating in the fuel pump inlet or could 
create a potential ignition source inside the center fuel tank; 
these conditions, in combination with flammable fuel vapors, could 
result in a center fuel tank explosion 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.

Service Information References

    (f) The term ``Revision December 2005 of the MPD,'' as used in 
this AD, means the Boeing 737-600/700/700C/700IGW/800/900 
Maintenance Planning Data (MPD) Document, D626A001-CMR, Section 9, 
Revision December 2005. The term ``Revision May 2006 of the MPD,'' 
as used in this AD, means the Boeing 737-600/700/700C/700IGW/800/900 
MPD Document, D626A001-CMR, Section 9, Revision May 2006. The term 
``service bulletin,'' as used in this AD, means the Accomplishment 
Instructions of the following service bulletins, as applicable:
    (1) For installation of an automatic shutoff system required by 
paragraph (g) of this AD: Boeing Alert Service Bulletin 737-28A1206, 
dated January 11, 2006;
    (2) For modification of the fuel control module assembly 
required by paragraph (i) of this AD: Boeing Component Service 
Bulletin 233A3202-28-03, dated January 12, 2006; and
    (3) For installation of the secondary override pump control 
relays required by paragraph (l) of this AD: Boeing Alert Service 
Bulletin 737-28A1248, dated December 21, 2006.

Installation of Automatic Shutoff System for the Center Tank Fuel Boost 
Pumps

    (g) For the airplanes identified in paragraph 1.A.1. of Boeing 
Alert Service Bulletin 737-28A1206, dated January 11, 2006: Within 
36 months after the effective date of this AD, install an automatic 
shutoff system for the center tank fuel boost pumps, by 
accomplishing all of the actions specified in the applicable service 
bulletin. If a placard has been previously installed on the airplane 
in accordance with paragraph (h) of this AD, the placard may be 
removed from the flight deck of only that airplane after the 
automatic shutoff system has been installed. Installing automatic 
shutoff systems on all airplanes in an operator's fleet, in 
accordance with this paragraph, terminates the placard installation 
required by paragraph (h) of this AD, for all airplanes in an 
operator's fleet.

Placard Installation for Mixed Fleet Operation

    (h) For the airplanes identified in paragraph 1.A.1. of Boeing 
Alert Service Bulletin 737-28A1206, dated January 11, 2006: 
Concurrently with installing an automatic shutoff system on any 
airplane in an operator's fleet, as required by paragraph (g) of 
this AD, install a placard adjacent to the pilot's primary flight 
display on all airplanes in the operator's fleet not equipped with 
an automatic shutoff system for the center tank fuel boost pumps. 
The placard must read as follows (unless alternative placard wording 
is approved by an appropriate FAA Principal Operations Inspector):
    ``AD 2002-24-51 fuel usage restrictions required.''

Installation of a placard in accordance with paragraph (e) of AD 
2002-19-52, amendment 39-12900, is acceptable for compliance with 
the requirements of this paragraph. Installing an automatic shutoff 
system on an airplane, in accordance with paragraph (g) of this AD, 
terminates the placard installation required by this paragraph, for 
only that airplane. Installing automatic shutoff systems on all 
airplanes in an operator's fleet, in accordance with paragraph (g) 
of this AD, terminates the placard installation required by this 
paragraph, for all airplanes in an operator's fleet. If automatic 
shutoff systems are installed concurrently on all airplanes in an 
operator's fleet in accordance with paragraph (g) of this AD, or if 
operation according to the fuel usage restrictions of AD 2002-24-51 
is maintained until automatic shutoff systems are installed on all 
airplanes in an operator's fleet, the placard installation specified 
in this paragraph is not required.

Concurrent Modification of P5-2 Fuel Control Module Assembly

    (i) For the airplanes identified in paragraph 1.A.1. of Boeing 
Alert Service Bulletin 737-28A1206, dated January 11, 2006, equipped 
with any fuel control module assembly identified in paragraph 1.A.1. 
of Boeing Component Service Bulletin 233A3202-28-03, dated January 
12, 2006: Before or concurrently with accomplishing the actions 
required by paragraph (g) of this AD, replace the left and right 
center boost pump switches of the P5-2 fuel control module assembly 
with new switches and change the wiring of the P5-2 fuel control 
module assembly, by accomplishing all the applicable actions 
specified in the applicable service bulletin.

Airplane Flight Manual (AFM) Revision

    (j) For the airplanes identified in paragraph 1.A.1. of Boeing 
Alert Service Bulletin 737-28A1206, dated January 11, 2006: 
Concurrently with accomplishing the actions required by paragraph 
(g) of this AD, do the actions specified in paragraphs (j)(1) and 
(j)(2) of this AD.
    (1) Revise Section 1 of the Limitations section of the Boeing 
737-600/-700/-700C/-800/-900 AFM to include the following statement. 
This may be done by inserting a copy of this AD in the AFM.
    ``Intentional dry running of a center tank fuel pump (low 
pressure light illuminated) is prohibited.''

    Note 2: When a statement identical to that in paragraph (j)(1) 
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.

    (2) Revise Section 3 of the Normal Procedures section of the 
Boeing 737-600/-700/-700C/-800/-900 AFM to include the following 
statements. This may be done by inserting a copy of this AD in the 
AFM.

``Center Tank Fuel Pumps

    Alternative Method of Compliance (AMOC) to AD 2001-08-24 and AD 
2002-24-51 for Aircraft with the Automated Center Tank Fuel Pump 
Shutoff
    Center tank fuel pumps must not be ``ON'' unless personnel are 
available in the flight deck to monitor low pressure lights.
    For ground operation, center tank fuel pump switches must not be 
positioned ``ON'' unless the center tank fuel quantity exceeds 1000 
pounds (453 kilograms), except when defueling or transferring fuel. 
Upon positioning the center tank fuel pump switches ``ON'' verify 
momentary illumination of each center tank fuel pump low pressure 
light.
    For ground and flight operations, the corresponding center tank 
fuel pump switch must be positioned ``OFF'' when a center tank fuel 
pump low pressure light illuminates [1]. Both center tank fuel pump 
switches must be positioned ``OFF'' when the first center tank fuel 
pump low pressure light illuminates if the center tank is empty.
    [1] When established in a level flight attitude, both center 
tank pump switches should be positioned ``ON'' again if the center 
tank contains usable fuel.

Defueling and Fuel Transfer

    When transferring fuel or defueling center or main tanks, the 
fuel pump low pressure lights must be monitored and the fuel pumps 
positioned to ``OFF'' at the first indication of the fuel pump low 
pressure [1].
    Defueling the main tanks with passengers on board is prohibited 
if the main tank fuel pumps are powered [2].
    Defueling the main tanks with passengers on board is prohibited 
if the center tank fuel pumps are powered and the auto-shutoff 
system is inhibited [2].
    [1] Prior to transferring fuel or defueling, conduct a lamp test 
of the respective fuel pump low pressure lights.
    [2] Fuel may be transferred from tank to tank or the aircraft 
may be defueled with passengers on board, provided fuel quantity in 
the tank from which fuel is being taken is maintained at or above 
2000 pounds (900 kilograms).''

    Note 3: When statements identical to those in paragraph (j)(2) 
of this AD have 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.

Airworthiness Limitations (AWLs) Revision for AWL No. 28-AWL-19

    (k) For the airplanes identified in paragraph 1.A.1. of Boeing 
Alert Service Bulletin 737-28A1206, dated January 11, 2006: 
Concurrently with installing an automatic shutoff system in 
accordance with paragraph (g) of this AD, revise the AWLs section of 
the Instructions for Continued Airworthiness by incorporating AWL 
No. 28-AWL-19 of Subsection F of Revision December 2005 of the MPD 
into the MPD. Accomplishing the revision in accordance with a later 
revision of the MPD is an acceptable method of compliance if the 
revision is approved by the Manager, Seattle Aircraft Certification 
Office (ACO), FAA.

[[Page 37484]]

Installation of Secondary Override Pump Control Relays

    (l) For the airplanes identified in paragraph 1.A.1. of Boeing 
Alert Service Bulletin 737-28A1248, dated December 21, 2006: Within 
60 months after the effective date of this AD, install two secondary 
override fuel pump control relays to each existing primary override 
fuel pump control relay for the center fuel tank fuel boost pumps, 
in accordance with the applicable service bulletin.

AWLs Revision for AWL No. 28-AWL-23

    (m) For the airplanes identified in paragraph 1.A.1. of Boeing 
Alert Service Bulletin 737-28A1248, dated December 21, 2006: 
Concurrently with installing the secondary override pump control 
relays in accordance with paragraph (l) of this AD, revise the AWLs 
section of the Instructions for Continued Airworthiness by 
incorporating AWL No. 28-AWL-23 of Subsection F of Revision May 2006 
of the MPD into the MPD. Accomplishing the revision in accordance 
with a later revision of the MPD is an acceptable method of 
compliance if the revision is approved by the Manager, Seattle ACO.

Terminating Action for AD 2001-08-24

    (n) Accomplishing the actions required by paragraphs (g), (h), 
(i), (j), and (k) of this AD terminates the requirements of 
paragraph (a) of AD 2001-08-24 for Model 737-600, -700, -700C, -800, 
and -900 series airplanes that have the automatic shutoff system 
installed. After accomplishing the actions required by paragraphs 
(g), (h), (i), (j), and (k) of this AD, the AFM limitation required 
by paragraph (a) of AD 2001-08-24 may be removed from the AFM for 
those airplanes.

Terminating Action for AD 2002-24-51

    (o) Accomplishing the actions required by paragraphs (g), (h), 
(i), (j), and (k) of this AD terminates the requirements of 
paragraph (b) of AD 2002-24-51 for Model 737-600, -700, -700C, -800, 
and -900 series airplanes that have the automatic shutoff system 
installed. After accomplishing the actions required by paragraphs 
(g), (h), (i), (j), and (k) of this AD, the AFM limitations required 
by paragraph (b) of AD 2002-24-51 may be removed from the AFM for 
those airplanes.

Alternative Methods of Compliance (AMOCs)

    (p)(1) The Manager, Seattle ACO, has the authority to approve 
AMOCs for this AD, if requested in accordance with the procedures 
found in 14 CFR 39.19.
    (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 appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.

    Issued in Renton, Washington, on June 26, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-13326 Filed 7-9-07; 8:45 am]
BILLING CODE 4910-13-P