[Federal Register Volume 72, Number 127 (Tuesday, July 3, 2007)]
[Proposed Rules]
[Pages 36385-36391]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-12816]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28386; Directorate Identifier 2006-NM-162-AD]
RIN 2120-AA64


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

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Boeing Model 747-400, -400D, and -400F series airplanes. 
This proposed AD would require revising the FAA-approved maintenance 
program by incorporating new airworthiness limitations (AWLs) for fuel 
tank systems to satisfy Special Federal Aviation Regulation No. 88 
requirements. This proposed AD would also require the initial 
inspection of certain repetitive AWL inspections to phase in those 
inspections, and repair if necessary. This proposed AD results from a 
design review of the fuel tank systems. We are proposing this AD to 
prevent the potential for ignition sources inside fuel tanks caused by 
latent failures, alterations, repairs, or maintenance actions, which, 
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 August 17, 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-
28386; Directorate Identifier 2006-NM-162-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

[[Page 36386]]

Airplane Fuel Tank System Design Review, Flammability Reduction and 
Maintenance and Inspection Requirements'' (67 FR 23086, May 7, 2001). 
In addition to new airworthiness standards for transport airplanes and 
new maintenance requirements, this rule included Special Federal 
Aviation Regulation No. 88 (``SFAR 88,'' Amendment 21-78, and 
subsequent Amendments 21-82 and 21-83).
    Among other actions, SFAR 88 requires certain type design (i.e., 
type certificate (TC) and supplemental type certificate (STC)) holders 
to substantiate that their fuel tank systems can prevent ignition 
sources in the fuel tanks. This requirement applies to type design 
holders for large turbine-powered transport airplanes and for 
subsequent modifications to those airplanes. It requires them to 
perform design reviews and to develop design changes and maintenance 
procedures if their designs do not meet the new fuel tank safety 
standards. As explained in the preamble to the rule, we intended to 
adopt airworthiness directives to mandate any changes found necessary 
to address unsafe conditions identified as a result of these reviews.
    In evaluating these design reviews, we have established four 
criteria intended to define the unsafe conditions associated with fuel 
tank systems that require corrective actions. The percentage of 
operating time during which fuel tanks are exposed to flammable 
conditions is one of these criteria. The other three criteria address 
the failure types under evaluation: single failures, single failures in 
combination with another latent condition(s), and in-service failure 
experience. For all four criteria, the evaluations included 
consideration of previous actions taken that may mitigate the need for 
further action.
    We have determined that the actions identified in this proposed AD 
are necessary to reduce the potential of ignition sources inside fuel 
tanks, which, in combination with flammable fuel vapors, could result 
in a fuel tank explosion and consequent loss of the airplane.

Relevant Service Information

    We have reviewed the following subsections of Boeing 747-400 
Maintenance Planning Data (MPD) Document, D621U400-9, Section 9, 
Revision 23, dated March 2006 (hereafter referred to as ``Revision 
March 2006 of the MPD''):
     Subsection B, ``AIRWORTHINESS LIMITATIONS (AWLs)--
SYSTEMS''
     Subsection C, ``PAGE FORMAT: AIRWORTHINESS LIMITATIONS''
     Subsection D, ``AIRWORTHINESS LIMITATIONS--FUEL SYSTEMS''
    Those subsections of Revision March 2006 of the MPD describe new 
AWLs for fuel tank systems. The new AWLs include:
     AWL inspections, which are periodic inspections of certain 
features for latent failures that could contribute to an ignition 
source; and
     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.
    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 revising the FAA-approved maintenance program by 
incorporating the information in Subsections B, C, and D of Revision 
March 2006 of the MPD. This proposed AD would also require the initial 
inspection of certain repetitive AWL inspections to phase in those 
inspections, and repair if necessary.

Explanation of Compliance Time

    In most ADs, we adopt a compliance time allowing a specified amount 
of time after the AD's effective date. In this case, however, the FAA 
has already issued regulations that require operators to revise their 
maintenance/inspection programs to address fuel tank safety issues. The 
compliance date for these regulations is December 16, 2008. To provide 
for efficient and coordinated implementation of these regulations and 
this proposed AD, we are using this same compliance date in this 
proposed AD, instead of the 18-month compliance time recommended by 
Boeing.

Rework Required When Implementing AWLs Into an Existing Fleet

    The maintenance program revision for the fuel tank systems 
specified in paragraph (g) of this proposed AD, which involves 
incorporating the information specified in Revision March 2006 of the 
MPD, would affect how operators maintain their airplanes. After doing 
that maintenance program revision, operators would need to do any 
maintenance on the fuel tank system as specified in the CDCCLs. 
Maintenance done before the maintenance program revision specified in 
paragraph (g) would not need to be redone in order to comply with 
paragraph (g). For example, the AWL that requires fuel pumps to be 
repaired and overhauled per an FAA-approved component maintenance 
manual (CMM) applies to fuel pumps repaired after the maintenance 
programs are revised; spare or on-wing fuel pumps do not need to be 
reworked. For AWLs that require repetitive inspections, the initial 
inspection interval (threshold) starts from the date the maintenance 
program revision specified in paragraph (g) is done, except as provided 
by paragraph (h) of this proposed AD. This proposed AD would require 
only the maintenance program revision specified in paragraph (g), and 
initial inspections specified in paragraph (h). No other fleet-wide 
inspections need to be done.

Changes to Fuel Tank System AWLs

    Paragraph (g) of this proposed AD would require revising the FAA-
approved maintenance program by incorporating certain information 
specified in Revision March 2006 of the MPD. Paragraph (g) allows 
accomplishing the maintenance program revision 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. Paragraph (h) allows accomplishing the initial inspections and 
repair in accordance with later revisions of the MPD as an acceptable 
method of compliance if they are approved by the Manager, Seattle ACO. 
In addition, Subsection B of Revision March 2006 of the MPD specifies 
that any deviations from the published AWL instructions, including AWL 
intervals, in that MPD must be approved by the Manager, Seattle ACO. 
Therefore, after the maintenance program revision, any further revision 
to an AWL or AWL interval should be done as an AWL change, not as an 
alternative method of compliance (AMOC). For U.S.-registered airplanes, 
operators must make requests through an appropriate FAA Principal 
Maintenance Inspector (PMI) or Principal Avionics Inspector (PAI) for 
approval by the Manager, Seattle ACO. A non-U.S. operator should 
coordinate

[[Page 36387]]

changes with its governing regulatory agency.

Exceptional Short-Term Extensions

    Subsection B of Revision March 2006 of the MPD has provisions for 
an exceptional short-term extension of 30 days. An exceptional short-
term extension is an increase in an AWL interval that may be needed to 
cover an uncontrollable or unexpected situation. For U.S.-registered 
airplanes, the FAA PMI or PAI must concur with any exceptional short-
term extension before it is used, unless the operator has identified 
another appropriate procedure with the local regulatory authority. The 
FAA PMI or PAI may grant the exceptional short-term extensions 
described in Subsection B without consultation with the Manager, 
Seattle ACO. A non-U.S. operator should coordinate changes with its 
governing regulatory agency. As explained in Revision March 2006 of the 
MPD, exceptional short-term extensions must not be used for fleet AWL 
extensions. An exceptional short-term extension should not be confused 
with an operator's short-term escalation authorization approved in 
accordance with the Operations Specifications or the operator's 
reliability program.

Ensuring Compliance With Fuel Tank System AWLs

    Boeing has revised applicable maintenance manuals and task cards to 
address AWLs and to include notes about CDCCLs. Operators that do not 
use Boeing's revision service should revise their maintenance manuals 
and task cards to highlight actions tied to CDCCLs to ensure that 
maintenance personnel are complying with the CDCCLs. Appendix 1 of this 
proposed AD contains a list of Air Transport Association (ATA) sections 
for the revised maintenance manuals. Operators might wish to use the 
appendix as an aid to implement the AWLs.

Recording Compliance With Fuel Tank System AWLs

    The applicable operating rules of the Federal Aviation Regulations 
(14 CFR parts 91, 121, 125, and 129) require operators to maintain 
records with the identification of the current inspection status of an 
airplane. Some of the AWLs contained in Subsection D of Revision March 
2006 of the MPD are inspections for which the applicable sections of 
the operating rules apply. Other AWLs are CDCCLs, which are tied to 
conditional maintenance actions. An entry into an operator's existing 
maintenance record system for corrective action is sufficient for 
recording compliance with CDCCLs, as long as the applicable maintenance 
manual and task cards identify actions that are CDCCLs.

Changes to CMMs Cited in Fuel Tank System AWLs

    Some of the AWLs in Subsection D of Revision March 2006 of the MPD 
refer to specific revision levels of the CMMs as additional sources of 
service information for doing the AWLs. Boeing is referring to the CMMs 
by revision level in the applicable AWL for certain components rather 
than including information directly in the MPD because of the volume of 
that information. As a result, the Manager, Seattle ACO, must approve 
the CMMs. Any later revision of those CMMs will be handled like a 
change to the AWL itself. Any use of parts (including the use of parts 
manufacturer approval (PMA) approved parts), methods, techniques, and 
practices not contained in the CMMs need to be approved by the Manager, 
Seattle ACO, or governing regulatory authority. For example, certain 
pump repair/overhaul manuals must be approved by the Manager, Seattle 
ACO.

Changes to AMMs Referenced in Fuel Tank System AWLs

    In other AWLs in Subsection D of Revision March 2006 of the MPD, 
the AWLs contain all the necessary data. The applicable section of the 
maintenance manual is usually included in the AWLs. Boeing intended 
this information to assist operators in maintaining the maintenance 
manuals. A maintenance manual change to these tasks may be made without 
approval by the Manager, Seattle ACO, through an appropriate FAA PMI or 
PAI, by the governing regulatory authority, or by using the operator's 
standard process for revising maintenance manuals. An acceptable change 
would have to maintain the information specified in the AWL such as the 
pass/fail criteria or special test equipment.

Costs of Compliance

    There are about 596 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs, at 
an average labor rate of $80 per hour, for U.S. operators to comply 
with this proposed AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                         Number of
                                              Work                            Cost per     U.S.-
                  Action                     hours            Parts           airplane   registered   Fleet cost
                                                                                         airplanes
----------------------------------------------------------------------------------------------------------------
Maintenance program revision..............        8  None..................       $640           57      $36,480
Inspections...............................        8  None..................        640           57       36,480
----------------------------------------------------------------------------------------------------------------

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;

[[Page 36388]]

    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-2007-28386; Directorate Identifier 2006-NM-
162-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by August 
17, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 747-400, -400D, and -400F 
series airplanes, certificated in any category; with an original 
standard airworthiness certificate or original export certificate of 
airworthiness issued before April 12, 2006.

    Note 1: Airplanes with an original standard airworthiness 
certificate or original export certificate of airworthiness issued 
on or after April 12, 2006, must be already in compliance with the 
airworthiness limitations specified in this AD because those 
limitations were applicable as part of the airworthiness 
certification of those airplanes.


    Note 2: This AD requires revisions to certain operator 
maintenance documents to include new inspections and maintenance 
actions. Compliance with these limitations 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 
limitations, the operator may not be able to accomplish the actions 
described in the revisions. In this situation, to comply with 14 CFR 
43.16 and 91.403(c), the operator must request approval for revision 
to the airworthiness limitations (AWLs) in the Boeing 747-400 
Maintenance Planning Data (MPD) Document, D621U400-9, according to 
paragraph (g) or (i) of this AD, as applicable.

Unsafe Condition

    (d) This AD results from a design review of the fuel tank 
systems. We are issuing this AD to prevent the potential for 
ignition sources inside fuel tanks caused by latent failures, 
alterations, repairs, or maintenance actions, which, in combination 
with flammable fuel vapors, could result in a 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 Reference

    (f) The term ``Revision March 2006 of the MPD'' as used in this 
AD, means Boeing 747-400 Maintenance Planning Data (MPD) Document, 
D621U400-9, Section 9, Revision 23, dated March 2006.

Maintenance Program Revision

    (g) Before December 16, 2008, revise the FAA-approved 
maintenance program by incorporating the information in the 
subsections specified in paragraphs (g)(1), (g)(2), and (g)(3) of 
this AD; except that the initial inspections specified in Table 1 of 
this AD must be done at the compliance times specified in Table 1. 
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.
    (1) Subsection B, ``AIRWORTHINESS LIMITATIONS (AWLs)--SYSTEMS,'' 
of Revision March 2006 of the MPD.
    (2) Subsection C, ``PAGE FORMAT: AIRWORTHINESS LIMITATIONS,'' of 
Revision March 2006 of the MPD.
    (3) Subsection D, ``AIRWORTHINESS LIMITATIONS--FUEL SYSTEMS,'' 
of Revision March 2006 of the MPD.

Initial Inspections and Repair if Necessary

    (h) Do the inspections specified in Table 1 of this AD and 
repair any discrepancy, in accordance with Subsection D, 
``AIRWORTHINESS LIMITATIONS--FUEL SYSTEMS,'' of Revision March 2006 
of the MPD. The repair must be done before further flight. 
Accomplishing the actions required by this paragraph 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.


    Note 3: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''



    Note 4: For the purposes of this AD, a special detailed 
inspection is: ``An intensive examination of a specific item, 
installation, or assembly to detect damage, failure, or 
irregularity. The examination is likely to make extensive use of 
specialized inspection techniques and/or equipment. Intricate 
cleaning and substantial access or disassembly procedure may be 
required.''


                                          Table 1.--Initial Inspections
----------------------------------------------------------------------------------------------------------------
                                                                  Compliance time (whichever occurs later)
             AWL No.                    Description       ------------------------------------------------------
                                                                       Threshold                 Grace period
----------------------------------------------------------------------------------------------------------------
28-AWL-01.......................  A detailed inspection    Before the accumulation of 36,000  Within 72 months
                                   of external wires over   total flight cycles, or within     after the
                                   the center fuel tank     144 months since the date of       effective date of
                                   for damaged or loose     issuance of the original           this AD.
                                   clamps, wire chafing,    standard airworthiness
                                   and wire bundles in      certificate or the date of
                                   contact with the         issuance of the original export
                                   surface of the center    certificate of airworthiness,
                                   fuel tank.               whichever occurs first.
28-AWL-03.......................  A special detailed       Before the accumulation of 36,000  Within 24 months
                                   inspection of the        total flight cycles, or within     after the
                                   lightning shield to      144 months since the date of       effective date of
                                   ground termination on    issuance of the original           this AD.
                                   the out-of-tank fuel     standard airworthiness
                                   quantity indicating      certificate or the date of
                                   system to verify         issuance of the original export
                                   functional integrity.    certificate of airworthiness,
                                                            whichever occurs first.

[[Page 36389]]

 
28-AWL-10.......................  A special detailed       Before the accumulation of 36,000  Within 60 months
                                   inspection of the        total flight cycles, or within     after the
                                   fault current bond of    144 months since the date of       effective date of
                                   the fueling shutoff      issuance of the original           this AD.
                                   valve actuator of the    standard airworthiness
                                   center wing tank to      certificate or the date of
                                   verify electrical bond.  issuance of the original export
                                                            certificate of airworthiness,
                                                            whichever occurs first.
----------------------------------------------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (i)(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.

 Appendix 1.--Implementing Fuel Tank System Airworthiness Limitations on Model 747-400, -400D, and -400F Series
                                                    Airplanes
----------------------------------------------------------------------------------------------------------------
                                                      ATA section or CMM
            AWL No.                   ALI/CDCCL            document           Task title           Task No.
----------------------------------------------------------------------------------------------------------------
28-AWL-01......................  ALI................  AMM 28-11-00/601..  External Wires      28-11-00-210-801.
                                                                           Over the Center
                                                                           Fuel Tank--
                                                                           Inspection.
28-AWL-02......................  CDCCL..............  SWPM 20-10-11.....  Wiring Assembly
                                                                           and Installation
                                                                           Configuration.
28-AWL-03......................  ALI................  AMM 05-55-54/601..  FQIS Wiring and     05-55-54-200-801.
                                                                           Bonding--Inspecti
                                                                           on.
28-AWL-04......................  CDCCL..............  SWPM 20-10-15.....  Assembly of Shield
                                                                           Ground Wires.
28-AWL-05......................  CDCCL..............  AMM 29-11-22/401..  Heat Exchanger      29-11-22-404-014.
                                                                           Installation.
28-AWL-06......................  CDCCL..............  CMM 28-22-07,
                                                       Revision 1; CMM
                                                       28-31-03,
                                                       Revision 3; CMM
                                                       28-26-12,
                                                       Revision 0; CMM
                                                       28-26-14,
                                                       Revision 0; CMM
                                                       28-20-02,
                                                       Revision 9; or
                                                       subsequent
                                                       revisions.
28-AWL-07......................  CDCCL.
28-AWL-08......................  CDCCL..............  SWPM 20-10-11.....  Wiring Assembly
                                                                           and Installation
                                                                           Configuration..
28-AWL-09......................  CDCCL..............  AMM 28-21-02/401..  Refuel Valve        28-21-02-401-011.
                                                                           Control Unit--
                                                                           Installation.
                                                      AMM 28-21-13/401..  Refuel Valve        28-21-13-404-087.
                                                                           Control Unit--
                                                                           Installation.
28-AWL-10......................  ALI................  AMM 28-21-13/601..  Center Wing Tank    28-21-13-765-801.
                                                                           Refuel Valve--
                                                                           Fault Current
                                                                           Bond Inspection.
28-AWL-11......................  CDCCL..............  CMM 28-41-62,
                                                       Revision 4 or
                                                       subsequent
                                                       revisions.
28-AWL-12......................  CDCCL..............  CMM 28-21-02,
                                                       Revision 2 or
                                                       subsequent
                                                       revisions.
28-AWL-13......................  CDCCL..............  CMM 28-41-63,
                                                       Revision 4 or
                                                       subsequent
                                                       revisions.
28-AWL-14......................  CDCCL..............  CMM 28-40-55,
                                                       Revision 6; CMM
                                                       28-40-56,
                                                       Revision 4; CMM
                                                       28-40-59,
                                                       Revision 5; or
                                                       subsequent
                                                       revisions.
28-AWL-15......................  CDCCL..............  SWPM 20-14-12.....  Repair of Fuel
                                                                           Quantity
                                                                           Indicator System
                                                                           (FQIS) Wire
                                                                           Harness.
                                                      AMM 28-41-09/401..  FQIS Wire Bundle    28-41-09-404-019.
                                                                           in the Main or
                                                                           Reserve Tank--
                                                                           Installation.
                                                                          FQIS Wire Bundle    28-41-09-404-157.
                                                                           in the Center
                                                                           Wing Tank
                                                                           Installation.
                                                                          FQIS Wire Bundle    28-41-09-404-176.
                                                                           in the Horizontal
                                                                           Stabilizer Tank
                                                                           Installation.

[[Page 36390]]

 
28-AWL-16......................  CDCCL..............  AMM 28-11-02/401..  Reserve and Main    28-11-02-404-011.
                                                                           Tank Access Door
                                                                           Installation.
                                                      AMM 28-11-03/401..  Access Door for     28-11-03-404-007.
                                                                           the Wing Surge
                                                                           Tank Installation.
28-AWL-17......................  ALI................  AMM 28-31-14/501..  Fault Current       28-31-14-715-001.
                                                                           Detector
                                                                           Operational Test.
                                                      AMM 28-17-14/501..  Fault Current       28-17-14-715-001.
                                                                           Detector--Operati
                                                                           onal Test.
28-AWL-18......................  CDCCL..............  CMM 28-31-22,
                                                       Revision 4 or
                                                       subsequent
                                                       revisions.
28-AWL-19......................  CDCCL..............  FIM 28-22-00/201..  CMCS Message LEFT   28-21 Task 806.
                                                                           HORIZONTAL
                                                                           STABILIZER PUMP
                                                                           SYSTEM FAIL--
                                                                           Fault Isolation.
                                                                          CMCS Message RIGHT  28-21 Task 807.
                                                                           HORIZONTAL
                                                                           STABILIZER PUMP
                                                                           SYSTEM FAIL--
                                                                           Fault Isolation.
                                                                          CMCS Message MAIN   28-22 Task 860.
                                                                           TANK 1 FWD BOOST
                                                                           PUMP SYSTEM FAIL--
                                                                           Fault Isolation.
                                                                          CMCS Message MAIN   28-22 Task 861.
                                                                           TANK 1 AFT BOOST
                                                                           PUMP SYSTEM FAIL--
                                                                           Fault Isolation.
                                                                          CMCS Message MAIN   28-22 Task 862.
                                                                           TANK 2 FWD BOOST
                                                                           PUMP SYSTEM FAIL--
                                                                           Fault Isolation.
                                                                          CMCS Message MAIN   28-22 Task 863.
                                                                           TANK 2 AFT BOOST
                                                                           PUMP SYSTEM FAIL--
                                                                           Fault Isolation.
                                                                          CMCS Message MAIN   28-22 Task 864.
                                                                           TANK 3 FWD BOOST
                                                                           PUMP SYSTEM FAIL--
                                                                           Fault Isolation.
                                                                          CMCS Message MAIN   28-22 Task 865.
                                                                           TANK 3 AFT BOOST
                                                                           PUMP SYSTEM FAIL--
                                                                           Fault Isolation.
                                                                          CMCS Message MAIN   28-22 Task 866.
                                                                           TANK 4 FWD BOOST
                                                                           PUMP SYSTEM FAIL--
                                                                           Fault Isolation.
                                                                          CMCS Message MAIN   28-22 Task 867.
                                                                           TANK 4 AFT BOOST
                                                                           PUMP SYSTEM FAIL--
                                                                           Fault Isolation.
                                                                          CMCS Message LEFT   28-31 Task 826.
                                                                           CENTER TANK
                                                                           OVERRIDE/JETTISON
                                                                           PUMP SYSTEM FAIL--
                                                                           Fault Isolation.
                                                                          CMCS Message RIGHT  28-31 Task 827.
                                                                           CENTER TANK
                                                                           OVERRIDE/JETTISON
                                                                           PUMP SYSTEM FAIL--
                                                                           Fault Isolation.
                                                                          CMCS Message MAIN   28-31 Task 828.
                                                                           TK 2 AFT OVERRIDE/
                                                                           JETTISON PUMP
                                                                           SYSTEM FAIL--
                                                                           Fault Isolation.
                                                                          CMCS Message MAIN   28-31 Task 829.
                                                                           TK 2 FWD OVERRIDE/
                                                                           JETTISON PUMP
                                                                           SYSTEM FAIL--
                                                                           Fault Isolation.
                                                                          CMCS Message MAIN   28-31 Task 830.
                                                                           TK 3 AFT OVERRIDE/
                                                                           JETTISON PUMP
                                                                           SYSTEM FAIL--
                                                                           Fault Isolation.

[[Page 36391]]

 
                                                                          CMCS Message MAIN   28-31 Task 831.
                                                                           TK 3 FWD OVERRIDE/
                                                                           JETTISON PUMP
                                                                           SYSTEM FAIL--
                                                                           Fault Isolation.
28-AWL-20......................  CDCCL..............  AMM 28-22-07/401..  Front Spar          28-22-07-400-805-0
                                                                           Bulkhead Fitting--  01.
                                                                           Installation.
                                                                                              28-22-07-400-806-0
                                                                                               02.
                                                                                              28-22-07-400-807-0
                                                                                               03.
                                                                                              28-22-07-400-808-0
                                                                                               04.
28-AWL-21......................  ALI................  AMM 28-22-00/501.
                                                      AMM 28-17-00/501.
28-AWL-22......................  CDCCL..............  AMM 28-22-03/401..  Main Tank Boost     28-22-03-404-019-0
                                                                           Pump Motor/         01.
                                                                           Impeller Unit
                                                                           Installation.
                                                                                              28-22-03-404-026-0
                                                                                               02.
28-AWL-23......................  CDCCL..............  AMM 28-41-24/401.
47-AWL-01......................  CDCCL..............  AMM 47-21-06/401..  Flame Arrestor      47-21-06-400-801.
                                                                           Installation.
47-AWL-02......................  CDCCL.
47-AWL-03......................  ALI................  AMM 47-00-01/501..  Functional Test of  47-00-01-720-801.
                                                                           the Nitrogen
                                                                           Generation System.
47-AWL-04......................  ALI................  AMM 47-43-02/501..  Thermal Switch      47-43-02-700-801.
                                                                           Functional Test.
                                                                          Thermal Switch      47-43-02-700-802.
                                                                           Operational Test.
47-AWL-05......................  ALI................  AMM 47.
47-AWL-06......................  ALI................  AMM 47.
----------------------------------------------------------------------------------------------------------------


    Issued in Renton, Washington, on June 22, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-12816 Filed 7-2-07; 8:45 am]
BILLING CODE 4910-13-P