[Federal Register Volume 72, Number 127 (Tuesday, July 3, 2007)]
[Proposed Rules]
[Pages 36391-36397]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-12817]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28388; Directorate Identifier 2006-NM-163-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767-200, -300, -300F, and 
-400ER 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 767-200, -300, -300F, and -400ER series 
airplanes. This proposed AD would require revising the FAA-approved 
maintenance program to incorporate 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-
28388; Directorate Identifier 2006-NM-163-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

[[Page 36392]]

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'' 
(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 action. 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 Subsection D, ``AIRWORTHINESS LIMITATIONS--
SYSTEMS,'' of Boeing 767 Maintenance Planning Data (MPD) Document, 
D622T001-9, Section 9, Revision March 2006 (hereafter referred to as 
``Revision March 2006 of the MPD''). Subsection D of Revision March 
2006 of the MPD describes new airworthiness limitations (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 to 
incorporate the information in Subsection 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

[[Page 36393]]

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 D 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 changes with its governing regulatory agency.

Exceptional Short-Term Extensions

    Subsection D 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 D 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 824 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 U.S.-
            Action               Work hours          Parts           Cost per       registered      Fleet cost
                                                                     airplane        airplanes
----------------------------------------------------------------------------------------------------------------
Maintenance program revision.               8  None.............            $640             332        $212,480
Inspections..................               8  None.............             640             332         212,480
----------------------------------------------------------------------------------------------------------------


[[Page 36394]]

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-2007-28388; Directorate Identifier 2006-NM-
163-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 767-200, -300, -300F, and -
400ER series airplanes, certificated in any category; with an 
original standard airworthiness certificate or original export 
certificate of airworthiness issued before April 22, 2006.

    Note 1: Airplanes with an original standard airworthiness 
certificate or original export certificate of airworthiness issued 
on or after April 22, 2006, must already be 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 767 
Maintenance Planning Data (MPD) Document, D622T001-9, 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 767 Maintenance Planning Data (MPD) Document, 
D622T001-9, Section 9, Revision March 2006.

Maintenance Program Revision

    (g) Before December 16, 2008, revise the FAA-approved 
maintenance program by incorporating the information in Subsection 
D, ``AIRWORTHINESS LIMITATIONS--SYSTEMS,'' of Revision March 2006 of 
the MPD; 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.

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--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.''


[[Page 36395]]



                                          Table 1.--Initial Inspections
----------------------------------------------------------------------------------------------------------------
                                                                    Compliance time (whichever occurs later)
              AWL No.                       Description        -------------------------------------------------
                                                                         Threshold              Grace period
----------------------------------------------------------------------------------------------------------------
28-AWL-01.........................  A detailed inspection of    Before the accumulation of  Within 72 months
                                     external wires over the     36,000 total flight         after the effective
                                     center fuel tank for        cycles, or within 144       date of this AD.
                                     damaged clamps, wire        months since the date of
                                     chafing, and wire bundles   issuance of the original
                                     in contact with the         standard airworthiness
                                     surface of the center       certificate or the date
                                     fuel tank.                  of issuance of the
                                                                 original export
                                                                 certificate of
                                                                 airworthiness, whichever
                                                                 occurs first.
  8-AWL-05........................  A special detailed          Before the accumulation of  Within 60 months
                                     inspection of the           25,000 total flight         after the effective
                                     bulkhead fitting bond for   cycles, or within 72        date of this AD.
                                     the hydraulic line tank     months since the date of
                                     penetration.                issuance of the original
                                                                 standard airworthiness
                                                                 certificate or the date
                                                                 of issuance of the
                                                                 original export
                                                                 certificate of
                                                                 airworthiness, whichever
                                                                 occurs first.
  8-AWL-18........................  A special detailed          Before the accumulation of  Within 24 months
                                     inspection of the           36,000 total flight         after the effective
                                     lightning shield to         cycles, or within 144       date of this AD.
                                     ground termination on the   months since the date of
                                     out-of-tank fuel quantity   issuance of the original
                                     indicating system to        standard airworthiness
                                     verify functional           certificate or the date
                                     integrity.                  of issuance of the
                                                                 original export
                                                                 certificate of
                                                                 airworthiness, whichever
                                                                 occurs first.
  8-AWL-26........................  A special detailed          Before the accumulation of  Within 24 months
                                     inspection of the           36,000 total flight         after the effective
                                     lightning shield to         cycles, or within 144       date of this AD.
                                     ground termination on the   months since the date of
                                     out-of-tank surge tank      issuance of the original
                                     fuel level sensor to        standard airworthiness
                                     verify functional           certificate or the date
                                     integrity.                  of issuance of the
                                                                 original export
                                                                 certificate of
                                                                 airworthiness, whichever
                                                                 occurs first.
----------------------------------------------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, Seattle ACO, FAA, has the authority to 
approve AMOCs for this AD, if requested in accordance with the 
procedures found in 14 CFR 39.19.
    (2) 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 767-200, -300, -300F, and -400ER
                                                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      28-11-00-206-258.
                                                                           Over the Center
                                                                           Tank Inspection.
28-AWL-02......................  CDCCL..............  SWPM 20-10-11.....  Wiring Assembly     ..................
                                                                           and Installation
                                                                           Configuration.
28-AWL-03......................  CDCCL..............  AMM 28-22-07/401..  Install the Fuel    Varies with
                                                                           Lines and           configuration.
                                                                           Fittings.
28-AWL-04......................  CDCCL..............  AMM 29-11-27/401..  Install the Heat    29-11-27-424-015.
                                                                           Exchanger.
28-AWL-05......................  ALI................  AMM 29-11-27/601..  Bonding Resistance  29-11-27-026-001.
                                                                           Check of the Heat
                                                                           Exchanger Lines.
28-AWL-06......................  CDCCL..............  CMM 28-22-01,                           ..................
                                                       Revision 12; CMM
                                                       28-22-12,
                                                       Revision 16; CMM
                                                       28-22-21,
                                                       Revision 7; or
                                                       subsequent
                                                       revisions.
28-AWL-07......................  CDCCL..............  AMM 28-22-03/401..  Install the         28-22-03-404-027.
                                                                           Housing of the
                                                                           Fuel Boost Pump.
                                                      AMM 28-22-05/401..  Install the         Varies with
                                                                           Housing of the      configuration.
                                                                           Override (or
                                                                           Override/
                                                                           jettison) Pump.
28-AWL-08......................  CDCCL.                                                       ..................
28-AWL-09......................  CDCCL..............  SWPM 20-10-11.....  Wiring Assembly     ..................
                                                                           and Installation
                                                                           Configuration.
28-AWL-10......................  CDCCL..............  AMM 28-21-02/401..  Install the         28-21-02-404-021.
                                                                           Fueling Shutoff
                                                                           Valve.
                                                      AMM 28-21-12/401..  Install the         28-21-12-404-021.
                                                                           Control Unit of
                                                                           the Fueling
                                                                           Shutoff Valve.
28-AWL-11......................  CDCCL..............  CMM 28-41-68,                           ..................
                                                       Revision 4 or
                                                       subsequent
                                                       revisions.

[[Page 36396]]

 
28-AWL-12......................  CDCCL..............  CMM 28-40-56,                           ..................
                                                       Revision 4; CMM
                                                       28-40-59,
                                                       Revision 4; CMM
                                                       28-40-62,
                                                       Revision 3; CMM
                                                       28-41-68,
                                                       Revision 4; CMM
                                                       28-41-01,
                                                       Revision 5; CMM
                                                       28-41-07,
                                                       Revision 4; CMM
                                                       28-41-09,
                                                       Revision 6; CMM
                                                       28-41-30,
                                                       Revision 1; CMM
                                                       28-41-33,
                                                       Revision 2; CMM
                                                       28-41-34,
                                                       Revision 1; CMM
                                                       28-41-35,
                                                       Revision 1; CMM
                                                       28-41-36,
                                                       Revision 7; CMM
                                                       28-41-39,
                                                       Revision 7; CMM
                                                       28-41-41,
                                                       Revision 5; CMM
                                                       28-41-42,
                                                       Revision 0; or
                                                       subsequent
                                                       revisions.
28-AWL-13......................  CDCCL..............  SWPM 20-14-12.....  Repair of Fuel      ..................
                                                                           Quantity
                                                                           Indicator System
                                                                           (FQIS) Wire
                                                                           Harness.
                                                      AMM 28-41-09/401..  Install the Tank    Varies with
                                                                           Wiring Harness.     configuration.
28-AWL-14......................  CDCCL..............  AMM 28-11-01/401..  Install the Main    28-11-01-404-005.
                                                                           Tank Access Door.
                                                      AMM 28-11-02/401..  Install the         28-11-02-404-013.
                                                                           Auxiliary Tank
                                                                           Access Door.
                                                      AMM 28-11-03/401..  Install the Surge   28-11-03-404-011.
                                                                           Tank Access Door.
28-AWL-15......................  CDCCL..............  CMM 28-21-01,                           ..................
                                                       Revision 1 or
                                                       subsequent
                                                       revisions.
28-AWL-16......................  CDCCL..............  SWPM 20-14-12.....  Repair of Fuel      ..................
                                                                           Quantity
                                                                           Indicator System
                                                                           (FQIS) Wire
                                                                           Harness.
                                                      AMM 28-21-11/401..  Surge Tank Sensor   28-21-11-424-032.
                                                                           Harness
                                                                           Installation.
28-AWL-17......................  CDCCL..............  FIM 28-22-00/101.                       ..................
28-AWL-18......................  ALI................  AMM 20-55-54/601..  FQIS Wiring and     20-55-54-206-002.
                                                                           Bonding
                                                                           Inspection/Check.
28-AWL-19......................  CDCCL..............  SWPM 20-10-15.....  Assembly of Shield  ..................
                                                                           Ground Wires.
28-AWL-20......................  ALI................  AMM 28-22-00/501..  Override Pump Auto  28-22-00-725-529.
                                                                           Shutoff
                                                                           Functional Test.
28-AWL-21......................                                                               ..................
28-AWL-22......................  CDCCL..............  AMM 28-41-24/401..  Densitometer Hot    28-41-24-404-017.
                                                                           Short Protector
                                                                           Installation.
28-AWL-23......................  CDCCL..............  AMM 28-22-01/401..  Install the         28-22-01-404-030.
                                                                           Adapter Shaft of
                                                                           the Engine Fuel
                                                                           Shutoff Valve.
                                                      AMM 28-22-02/401..  Install the         28-22-02-404-023.
                                                                           Adapter Shaft of
                                                                           the Engine
                                                                           Crossfeed Valve.
                                                      AMM 28-22-11/401..  Install the         28-22-11-404-008.
                                                                           Actuator of the
                                                                           Engine Fuel
                                                                           Shutoff Valve.
                                                      AMM 28-22-12/401..  Install the         28-22-12-404-010.
                                                                           Actuator of the
                                                                           Engine Fuel
                                                                           Crossfeed Valve.
                                                      AMM 28-26-01/401..  Install the         28-26-01-404-059.
                                                                           Adapter Shaft of
                                                                           the Defueling
                                                                           Valve.
                                                      AMM 28-26-02/401..  Install the         28-26-11-404-020.
                                                                           Defueling Valve
                                                                           Actuator.
28-AWL-24......................  CDCCL..............  CMM 28-20-21.                           ..................
28-AWL-25......................  CDCCL..............  SWPM 20-10-15.....  Assembly of Shield  ..................
                                                                           Ground Wires.
28-AWL-26......................  ALI................  AMM 20-55-54/601..
----------------------------------------------------------------------------------------------------------------



[[Page 36397]]

    Issued in Renton, Washington, on June 22, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-12817 Filed 7-2-07; 8:45 am]
BILLING CODE 4910-13-P