[Federal Register Volume 78, Number 46 (Friday, March 8, 2013)]
[Proposed Rules]
[Pages 14934-14939]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-05295]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 78, No. 46 / Friday, March 8, 2013 / Proposed 
Rules  

[[Page 14934]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1160; Directorate Identifier 2010-NM-148-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening 
of comment period.

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

SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) to supersede an existing AD for certain The Boeing Company Model 
767 airplanes. The existing AD currently requires repetitive 
inspections to detect discrepancies of the wiring and surrounding 
Teflon sleeves of the fuel tank boost pumps and override/jettison 
pumps; replacement of the sleeves with new sleeves, for certain 
airplanes; and repair or replacement of the wiring and sleeves with new 
parts, as necessary. The first SNPRM proposed to reduce the initial 
compliance time and repetitive inspection interval in the existing AD. 
The first SNPRM also proposed to mandate a terminating action for the 
repetitive inspections, to eliminate wire damage. In addition, the 
first SNPRM proposed to remove certain airplanes from the applicability 
of the existing AD. The first SNPRM was prompted by fleet information 
indicating that the repetitive inspection interval in the existing AD 
is too long, because excessive chafing of the sleeving continues to 
occur much earlier than expected between scheduled inspections. This 
action revises the first SNPRM by also proposing to require revising 
the maintenance program to incorporate changes to the airworthiness 
limitations section. We are proposing this second SNPRM to detect and 
correct chafing of the fuel pump wire insulation and consequent 
exposure of the electrical conductor, which could result in electrical 
arcing between the wires and conduit and consequent fire or explosion 
of the fuel tank. Since these actions impose an additional burden over 
that proposed in the first SNPRM, we are reopening the comment period 
to allow the public the chance to comment on these proposed changes.

DATES: We must receive comments on this proposed AD by April 22, 2013.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, P. 
O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, Washington. For information on the availability of 
this material at the FAA, call 425-227-1221.

Examining the AD Docket

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

FOR FURTHER INFORMATION CONTACT: Rebel Nichols, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 
425-917-6509; fax: 425-917-6590; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-1160; 
Directorate Identifier 2010-NM-148-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 to supersede airworthiness directive (AD) 2000-11-
06, Amendment 39-11754 (65 FR 34928, June 1, 2000; corrected August 1, 
2000 (65 FR 46862)). That first SNPRM would apply to certain Model 767-
200, -300, -300F, and -400ER series airplanes. The first SNPRM 
published in the Federal Register on July 2, 2012 (77 FR 39188). The 
first SNPRM proposed to continue to require repetitive inspections to 
detect discrepancies of the wiring and surrounding Teflon sleeves of 
the fuel tank boost pumps and override/jettison pumps; replacement of 
the sleeves with new sleeves, for certain airplanes; and repair or 
replacement of the wiring and sleeves with new parts, as necessary. The 
first SNPRM also proposed to reduce the initial compliance time and 
repetitive inspection interval in the existing AD, and remove certain 
airplanes from the applicability of the existing AD. In addition, the 
first SNPRM proposed to include a terminating action for the

[[Page 14935]]

repetitive inspections, to eliminate wire damage.

Actions Since First SNPRM Was Issued

    Since we issued the first SNPRM (77 FR 39188, July 2, 2012), we 
have reviewed the information specified in Airworthiness Limitation 
Instruction, Critical Design Configuration Control Limitations (CDCCL) 
Task 28-AWL-29, ``In-Tank AC Fuel Pump Wire Bundles with Protective 
Liner;'' and CDCCL Task 28-AWL-30, ``Fuel Boost Pump Wires in Conduit 
Installation--In Fuel Tank;'' of Section 9 of Boeing 767 Airworthiness 
Limitations (AWLs) and Certification Maintenance Requirements (CMRs), 
D622T001-9, Revision October 2012. We have determined it is necessary 
to revise the maintenance program to include these tasks in order to 
address the identified unsafe condition.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(77 FR 39188, July 2, 2012), and the FAA's response to each comment.

Request To Change Terminating Action Requirement

    Air Canada (ACN) asked that the terminating action mandated by the 
first SNPRM (77 FR 39188, July 2, 2012) be deemed optional. American 
Airlines (AAL) stated that after complying with the inspections in the 
first SNPRM, very little damage was found. AAL added that damage is 
confined to the outer sleeve beyond 44,400 flight hours, and the wiring 
damage does not occur until 17 years later when undisturbed. AAL 
concluded that, given its service experience, Boeing's service data and 
analysis and the proposed 15,000 flight-hour inspection interval, the 
terminating action should not be mandated. ACN provided no 
justification for its request.
    We do not agree with the commenters. Mandating the terminating 
action is based on our determination that, in this case, long term 
continued operational safety would be better ensured by a modification 
to remove the source of the problem, rather than by repetitive 
inspections. As a matter of policy, we have determined that long-term 
inspections might not provide the degree of safety necessary for the 
transport airplane fleet. This determination has led us to consider 
placing less emphasis on inspections and more emphasis on design 
improvements. The modification is consistent with these conditions. 
Therefore, we have not changed the second SNPRM in this regard.

Request To Justify Existing Repetitive Inspection Interval

    ACN stated that it would like the FAA to confirm that the new 
repetitive inspection interval proposed by Boeing is based on 
sufficient evidence and supported by proper risk analysis. ACN noted 
that the information should be specific to the Model 767 fleet and 
should justify such a drastic increase in the frequency of the 
repetitive inspection interval.
    We agree to provide justification. Operators have reported finding 
chafing of the fuel pump wire bundle before the accumulation of 30,000 
flight cycles or 60,000 flight hours. Wire bundle chafing could wear 
away the sleeving, jacket, and wire installation, in addition to 
exposing metal conductors and causing electrical arcing. Based on these 
reports, the design approval holder (DAH) recommended that the wiring 
inspection required by this proposed AD be done within 15,000 flight 
hours after doing the most recent inspection. The DAH also recommended 
not including flight cycles in the inspection interval. We analyzed 
their recommendations and agreed. The repetitive interval for the 
wiring inspection is within 15,000 flight hours after the most recent 
inspection until the terminating action has been done. We have not 
changed the second SNPRM in this regard.

Request To Correct Certain Paragraph Identifiers

    United Airlines (UAL), Japan Airlines (JAL), and UPS asked that the 
paragraph identifiers referenced within certain paragraphs in the first 
SNPRM (77 FR 39188, July 2, 2012) be corrected. UAL, JAL, and UPS 
stated that those paragraph identifiers are incorrect and suggested 
changes. The suggested changes to the first SNPRM are as follows:
     The reference within paragraph (i)(2)(i)(C) that 
identifies paragraph (h)(2)(i)(D) should identify paragraph 
(i)(2)(i)(D).
     The reference within paragraph (i)(2)(i)(D) that 
identifies paragraph (h)(2) should identify paragraph (i)(2).
     The reference within paragraph (k) that identifies 
paragraph (l)(1) or (l)(2) should identify paragraph (k)(1) or (k)(2).
    We agree with the commenters' requests for the reasons provided. We 
have changed those paragraphs identified above accordingly.

Request To Clarify Terminating Action

    JAL asked that paragraph (g) be added to paragraph (l) of the first 
SNPRM (77 FR 39188, July 2, 2012), so that accomplishing the 
terminating action specified in Boeing Alert Service Bulletin 767-
28A0104, Revision 1, dated March 2, 2012, applies to paragraphs (g) and 
(k) of the first SNPRM. JAL also asked that Boeing Alert Service 
Bulletin 767-28A0104, Revision 1, dated March 2, 2012, be added to 
paragraph (m) of the first SNPRM.
    We agree to clarify the terminating action. We have changed the 
last sentence of paragraph (l) of this second SNPRM to read: 
``Accomplishing the replacement specified in this paragraph ends the 
repetitive inspection requirements in paragraphs (g) and (k) of this 
AD.'' However, we have not changed paragraph (m) of this second SNPRM 
in this regard, because that paragraph gives credit for accomplishing 
the terminating action required by paragraph (l) of this second SNPRM, 
if the terminating action was done before the effective date of the AD 
using Boeing Alert Service Bulletin 767-28A0104, dated January 25, 
2011.

Request To Reference Certain AD Paragraph

    UAL stated that it reviewed Boeing Service Bulletin 767-28A0053, 
Revision 3, dated November 11, 2011, which contains a note that refers 
to paragraph (c)(2)(ii) of AD 2000-11-06, Amendment 39-11754 (65 FR 
34928, June 1, 2000; corrected August 1, 2000 (65 FR 46862)). UAL 
suggested that the first SNPRM (77 FR 39188, July 2, 2012), provide 
information regarding the applicable equivalent paragraph in the 
superseding AD.
    We acknowledge that Boeing Service Bulletin 767-28A0053, Revision 
3, dated November 11, 2011, refers to paragraph (c)(2)(ii) of AD 2000-
11-06, Amendment 39-11754 (65 FR 34928, June 1, 2000; corrected August 
1, 2000 (65 FR 46862)). Paragraph (c)(2)(ii) of AD 2000-11-06 
corresponds to paragraph (i)(2)(ii) of this second SNPRM. However, we 
do not agree with requiring a service information update, because the 
note which refers to paragraph (c)(2)(ii) of that service information 
will not adversely affect accomplishment of the required actions. We 
have not changed the second SNPRM in this regard.

Request To Clarify Certain Language in the ``Comments'' Section of the 
First SNPRM (77 FR 39188, July 2, 2012)

    Boeing asked that the language in the ``Comments'' section of the 
preamble of

[[Page 14936]]

the first SNPRM (77 FR 39188, July 2, 2012), which refers to Boeing 
Alert Service Bulletin 767-28A0104, Revision 1, dated March 2, 2012, 
including procedures for a wiring change, be clarified. Boeing stated 
that the language should emphasize that the procedures include the 
addition of a conduit liner and new wire bundle.
    We acknowledge and agree with the commenter's request for 
clarification; however, the content of that section of the preamble of 
the first SNPRM (77 FR 39188, July 2, 2012) does not reappear in this 
second SNPRM. However, we have added the words ``with a conduit liner'' 
to paragraph (l) of this second SNPRM for clarification.

Request To Clarify Service Information

    UAL requested that we reference new service information to address 
minor corrections for Boeing Alert Service Bulletin 767-28A0104, 
Revision 1, dated March 2, 2012. UAL noted that certain figure callouts 
should be revised.
    We do not agree. Boeing has not yet issued a revised service 
bulletin. Accomplishing Boeing Alert Service Bulletin 767-28A0104, 
Revision 1, dated March 2, 2012, addresses the identified unsafe 
condition. If a new service bulletin is issued later, operators may 
request an alternative method of compliance (AMOC) in accordance with 
the procedures specified in paragraph (p) of this AD. We have not 
changed the second SNPRM in this regard.

Request to Increase Work-Hours

    UAL asked that the work-hours specified in the ``Costs of 
Compliance'' section of the first SNPRM (77 FR 39188, July 2, 2012) be 
increased. UAL stated that the new proposed action in the first SNPRM 
specifies that it will take 33 work-hours per airplane; however, Boeing 
Alert Service Bulletin 767-28A0104, Revision 1, dated March 2, 2012, 
specifies 41.5 work-hours per airplane. UAL suggested increasing the 
work-hours to be consistent with the service information.
    We agree with the commenter. The cost data that was included in the 
first SNPRM (77 FR 39188, July 2, 2012) has been updated. We have 
changed the total number of work-hours for the ``new proposed action'' 
in the ``Costs of Compliance'' section of this second SNPRM 
accordingly.

FAA's Determination

    We are proposing this second supplemental NPRM because we evaluated 
all the relevant information and determined the unsafe condition 
described previously is likely to exist or develop in other products of 
the same type design. Certain changes described above expand the scope 
of the first SNPRM (77 FR 39188, July 2, 2012). As a result, we have 
determined that it is necessary to reopen the comment period to provide 
additional opportunity for the public to comment on this second SNPRM.

Proposed Requirements of the Second SNPRM

    This second SNPRM would require repetitive inspections to detect 
discrepancies of the wiring and surrounding Teflon sleeves of the fuel 
tank boost pumps and override/jettison pumps; replacement of the 
sleeves with new sleeves, for certain airplanes; and repair or 
replacement of the wiring and sleeves with new parts, as necessary; a 
terminating action for the repetitive inspections, to eliminate wire 
damage. This second SNPRM also would require revising the maintenance 
program to incorporate changes to the airworthiness limitations 
section.

Costs of Compliance

    We estimate that this proposed AD affects 414 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                  Labor cost           Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Actions for airplanes with       7 work-hours x $85  None...............  $595 per            Up to $246,330 per
 jettison pumps, required by AD   per hour = $595                          inspection cycle.   inspection cycle.
 2000-11-06, Amendment 39-11754   per inspection
 (65 FR 34928, June 1, 2000;      cycle.
 corrected August 1, 2000 (65
 FR 46862)).
Actions for airplanes without    5 work-hours x $85  None...............  $425 per            Up to $175,950 per
 jettison pumps, required by AD   per hour = $425                          inspection cycle.   inspection cycle.
 2000-11-06 Amendment 39-11754    per inspection
 (65 FR 34928, June 1, 2000;      cycle.
 corrected August 1, 2000 (65
 FR 46862)).
New proposed action: Replace     42 work[dash]hours  $6,061.............  $9,631............  $3,987,234.
 existing wire bundles with new   x $85 per hour =
 wire bundles.                    $3,570.
New proposed revision to         1 work-hour x $85   None...............  $85...............  $35,190.
 maintenance program.             per hour = $85.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the inspections. We have no 
way of determining the number of aircraft that might need these 
repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace wire bundle sleeves if damage found    1 work hour x $85 per hour =             $1,452          $1,537.
 during inspections.                            $85.
----------------------------------------------------------------------------------------------------------------

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,

[[Page 14937]]

Part A, Subpart III, Section 44701, ``General requirements.'' Under 
that section, Congress charges the FAA with promoting safe flight of 
civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2000-11-06, Amendment 39-11754 (65 FR 34928, June 1, 2000; corrected 
August 1, 2000 (65 FR 46862)), and adding the following new AD:

The Boeing Company: Docket No. FAA-2010-1160; Directorate Identifier 
2010-NM-148-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by April 22, 
2013.

(b) Affected ADs

    This AD supersedes AD 2000-11-06, Amendment 39-11754 (65 FR 
34928, June 1, 2000; corrected August 1, 2000 (65 FR 46862)).

(c) Applicability

    (1) This AD applies to The Boeing Company Model 767-200, -300, -
300F, and -400ER series airplanes, certificated in any category, as 
identified in Boeing Service Bulletin 767-28A0053, Revision 3, dated 
November 11, 2011.
    (2) This AD requires revisions to certain operator maintenance 
documents to include new actions (e.g., inspections) and/or Critical 
Design Configuration Control Limitations (CDCCLs). Compliance with 
these actions and/or CDCCLs is required by 14 CFR 91.403(c). For 
airplanes that have been previously modified, altered, or repaired 
in the areas addressed by this AD, the operator may not be able to 
accomplish the actions 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 actions that will ensure the 
continued operational safety of the airplane.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by fleet information indicating that the 
repetitive inspection interval in the existing AD is too long 
because excessive chafing of the sleeving continues to occur much 
earlier than expected between scheduled inspections. We are issuing 
this AD to detect and correct chafing of the fuel pump wire 
insulation and consequent exposure of the electrical conductor, 
which could result in electrical arcing between the wires and 
conduit and consequent fire or explosion of the fuel tank.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Retained Repetitive Inspections

    This paragraph restates the requirements of paragraph (a) of AD 
2000-11-06, Amendment 39-11754 (65 FR 34928, June 1, 2000; corrected 
August 1, 2000 (65 FR 46862)), with revised service information. 
Perform a detailed visual inspection to detect discrepancies--
including the presence of cuts, splits, holes, worn areas, and 
lacing ties installed on the outside of the sleeves (except at the 
sleeve ends)--of the Teflon sleeves surrounding the wiring of the 
fuel tank boost pumps and override/jettison pumps, at the earlier of 
the times specified in paragraphs (g)(1) and (g)(2) of this AD, in 
accordance with Boeing Service Bulletin 767-28A0053, Revision 1, 
dated August 5, 1999; Boeing Alert Service Bulletin 767-28A0053, 
Revision 2, dated June 24, 2010; or Boeing Service Bulletin 767-
28A0053, Revision 3, dated November 11, 2011. Repeat the inspection 
thereafter at intervals not to exceed 60,000 flight hours or 30,000 
flight cycles, whichever occurs first. As of the effective date of 
this AD, only Boeing Service Bulletin 767-28A0053, Revision 3, dated 
November 11, 2011, may be used to do the actions required by this 
paragraph.
    (1) Prior to the accumulation of 50,000 total flight hours, or 
within 90 days after July 6, 2000 (the effective date of AD 2000-11-
06, Amendment 39-11754 (65 FR 34928, June 1, 2000; corrected August 
1, 2000 (65 FR 46862)), whichever occurs later.
    (2) Within 18 months after July 6, 2000 (the effective date of 
AD 2000-11-06, Amendment 39-11754 (65 FR 34928, June 1, 2000; 
corrected August 1, 2000 (65 FR 46862)).

(h) Retained Corrective Actions

    This paragraph restates the requirements of paragraph (b) of AD 
2000-11-06, Amendment 39-11754 (65 FR 34928, June 1, 2000; corrected 
August 1, 2000 (65 FR 46862)), with revised service information. If 
any discrepancy is detected during any inspection required by 
paragraph (g) of this AD: Prior to further flight, remove the Teflon 
sleeves and perform a detailed visual inspection to detect damage of 
the wiring, in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin 767-28A0053, Revision 1, dated August 5, 
1999; Boeing Alert Service Bulletin 767-28A0053, Revision 2, dated 
June 24, 2010; or Boeing Service Bulletin 767-28A0053, Revision 3, 
dated November 11, 2011. As of the effective date of this AD, only 
Boeing Service Bulletin 767-28A0053, Revision 3, dated November 11, 
2011, may be used to do the actions required by this paragraph.
    (1) If no damage to the wiring is detected, prior to further 
flight, install new Teflon sleeves, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 767-28A0053, 
Revision 1, dated August 5, 1999; Boeing Alert Service Bulletin 767-
28A0053, Revision 2, dated June 24, 2010; or Boeing Service Bulletin 
767-28A0053, Revision 3, dated November 11, 2011. As of the 
effective date of this AD, only Boeing Service Bulletin 767-28A0053, 
Revision 3, dated November 11, 2011, may be used to do the actions 
required by this paragraph.
    (2) If any damage to the wiring is detected, prior to further 
flight, accomplish the requirements of paragraph (i) of this AD.

(i) Retained Corrective Actions

    This paragraph restates the requirements of paragraph (c) of AD 
2000-11-06, Amendment 39-11754 (65 FR 34928, June 1, 2000; corrected 
August 1, 2000 (65 FR 46862)), with revised service information. If 
any damage to the wiring is detected during any inspection required 
by paragraph (h) of this AD: Prior to further flight, perform a 
detailed visual inspection to determine if the wiring damage was 
caused by arcing, in accordance with the Accomplishment Instructions 
of Boeing Service Bulletin 767-

[[Page 14938]]

28A0053, Revision 1, dated August 5, 1999; Boeing Alert Service 
Bulletin 767-28A0053, Revision 2, dated June 24, 2010; or Boeing 
Service Bulletin 767-28A0053, Revision 3, dated November 11, 2011. 
As of the effective date of this AD, only Boeing Service Bulletin 
767-28A0053, Revision 3, dated November 11, 2011, may be used to do 
the actions required by this paragraph.
    (1) If the wire damage was not caused by arcing: Prior to 
further flight, repair any damaged wires or replace the wires with 
new or serviceable wires, as applicable, and install new Teflon 
sleeves, in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin 767-28A0053, Revision 1, dated August 5, 
1999; Boeing Alert Service Bulletin 767-28A0053, Revision 2, dated 
June 24, 2010; or Boeing Service Bulletin 767-28A0053, Revision 3, 
dated November 11, 2011. As of the effective date of this AD, only 
Boeing Service Bulletin 767-28A0053, Revision 3, dated November 11, 
2011, may be used to do the actions required by this paragraph.
    (2) If any damage caused by arcing is found: Prior to further 
flight, perform an inspection for signs of fuel inside the conduit 
or on the wires, in accordance with the Accomplishment Instructions 
of Boeing Service Bulletin 767-28A0053, Revision 1, dated August 5, 
1999; Boeing Alert Service Bulletin 767-28A0053, Revision 2, dated 
June 24, 2010; or Boeing Service Bulletin 767-28A0053, Revision 3, 
dated November 11, 2011. As of the effective date of this AD, only 
Boeing Service Bulletin 767-28A0053, Revision 3, dated November 11, 
2011, may be used to do the actions required by this paragraph.
    (i) If no sign of fuel is found, accomplish the actions 
specified in paragraphs (i)(2)(i)(A), (i)(2)(i)(B), (i)(2)(i)(C), 
and (i)(2)(i)(D) of this AD.
    (A) Prior to further flight, repair the wires or replace the 
wires with new or serviceable wires, as applicable, in accordance 
with the Accomplishment Instructions of Boeing Service Bulletin 767-
28A0053, Revision 1, dated August 5, 1999; Boeing Alert Service 
Bulletin 767-28A0053, Revision 2, dated June 24, 2010; or Boeing 
Service Bulletin 767-28A0053, Revision 3, dated November 11, 2011. 
As of the effective date of this AD, only Boeing Service Bulletin 
767-28A0053, Revision 3, dated November 11, 2011, may be used to do 
the actions required by this paragraph.
    (B) Prior to further flight, install new Teflon sleeves, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 767-28A0053, Revision 1, dated August 5, 1999; Boeing Alert 
Service Bulletin 767-28A0053, Revision 2, dated June 24, 2010; or 
Boeing Service Bulletin 767-28A0053, Revision 3, dated November 11, 
2011. As of the effective date of this AD, only Boeing Service 
Bulletin 767-28A0053, Revision 3, dated November 11, 2011, may be 
used to do the actions required by this paragraph.
    (C) Repeat the inspection for signs of fuel inside the conduit 
thereafter at intervals not to exceed 500 flight hours, until the 
requirements of paragraph (i)(2)(i)(D) of this AD have been 
accomplished. If any fuel is found inside the conduit during any 
inspection required by this paragraph, prior to further flight, 
replace the conduit with a new or serviceable conduit in accordance 
with the Accomplishment Instructions of Boeing Service Bulletin 767-
28A0053, Revision 1, dated August 5, 1999; Boeing Alert Service 
Bulletin 767-28A0053, Revision 2, dated June 24, 2010; or Boeing 
Service Bulletin 767-28A0053, Revision 3, dated November 11, 2011. 
Thereafter, repeat the inspection specified in paragraph (g) of this 
AD at intervals not to exceed 60,000 flight hours or 30,000 flight 
cycles, whichever occurs first. As of the effective date of this AD, 
only Boeing Service Bulletin 767-28A0053, Revision 3, dated November 
11, 2011, may be used to do the actions required by this paragraph.
    (D) Within 6,000 flight hours or 18 months after the initial 
fuel inspection specified by paragraph (i)(2) of this AD, whichever 
occurs first, replace the conduit with a new or serviceable conduit, 
in accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 767-28A0053, Revision 1, dated August 5, 1999; Boeing Alert 
Service Bulletin 767-28A0053, Revision 2, dated June 24, 2010; or 
Boeing Service Bulletin 767-28A0053, Revision 3, dated November 11, 
2011. Such conduit replacement constitutes terminating action for 
the repetitive fuel inspections required by paragraph (i)(2)(i)(C) 
of this AD. As of the effective date of this AD, only Boeing Service 
Bulletin 767-28A0053, Revision 3, dated November 11, 2011, may be 
used to do the actions required by this paragraph.
    (ii) If any fuel is found in the conduit or on any wire: Prior 
to further flight, replace the conduit with a new or serviceable 
conduit, replace damaged wires with new or serviceable wires, and 
install new Teflon sleeves; in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 767-28A0053, Revision 1, 
dated August 5, 1999; Boeing Alert Service Bulletin 767-28A0053, 
Revision 2, dated June 24, 2010; or Boeing Service Bulletin 767-
28A0053, Revision 3, dated November 11, 2011. Thereafter, repeat the 
inspection specified in paragraph (g) of this AD at intervals not to 
exceed 60,000 flight hours or 30,000 flight cycles, whichever occurs 
first. As of the effective date of this AD, only Boeing Service 
Bulletin 767-28A0053, Revision 3, dated November 11, 2011, may be 
used to do the actions required by this paragraph.

(j) Retained Pump Retest

    This paragraph restates the requirements of paragraph (d) of AD 
2000-11-06, Amendment 39-11754 (65 FR 34928, June 1, 2000; corrected 
August 1, 2000 (65 FR 46862)), with revised service information. For 
any wire bundle removed and reinstalled during any inspection 
required by this AD: Prior to further flight after such 
reinstallation, retest the fuel pump in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 767-28A0053, 
Revision 1, dated August 5, 1999; Boeing Alert Service Bulletin 767-
28A0053, Revision 2, dated June 24, 2010; or Boeing Service Bulletin 
767-28A0053, Revision 3, dated November 11, 2011. As of the 
effective date of this AD, only Boeing Service Bulletin 767-28A0053, 
Revision 3, dated November 11, 2011, may be used to do the actions 
required by this paragraph.

(k) New Repetitive Inspections With Reduced Inspection Intervals

    Do the inspection required by paragraph (g) of this AD at the 
time specified in paragraph (k)(1) or (k)(2) of this AD, as 
applicable, in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin 767-28A0053, Revision 3, dated November 11, 
2011. Repeat the inspection thereafter at intervals not to exceed 
15,000 flight hours. Accomplishing the first inspection in this 
paragraph ends the repetitive inspection requirements in paragraph 
(g) of this AD.
    (1) For airplanes on which the inspection required by paragraph 
(g) of this AD has been done as of the effective date of this AD: Do 
the inspection within 15,000 flight hours after the most recent 
inspection or within 6,000 flight hours after the effective date of 
this AD, whichever occurs later, but not to exceed 60,000 flight 
hours after the most recent inspection required by paragraph (g) of 
this AD.
    (2) For airplanes on which the inspection required by paragraph 
(g) of this AD has not been done as of the effective date of this 
AD: Do the inspection before the accumulation of 15,000 total flight 
hours or within 6,000 flight hours after the effective date of this 
AD, whichever occurs later.

(l) New Terminating Action

    Within 60 months after the effective date of this AD: Replace 
the fuel boost pump and override/jettison pump wire bundles inside 
the in-tank electrical conduit with a conduit liner and new wire 
bundles, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 767-28A0104, Revision 1, dated March 
2, 2012. Accomplishing the replacement specified in this paragraph 
ends the repetitive inspection requirements in paragraphs (g) and 
(k) of this AD.

(m) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (l) of this AD, if those actions were performed before the 
effective date of this AD using Boeing Alert Service Bulletin 767-
28A0104, dated January 25, 2011.

(n) New Maintenance Program Revision

    Within 180 days after the effective date of this AD: Revise the 
maintenance program to incorporate CDCCL Task 28-AWL-29, ``In-Tank 
AC Fuel Pump Wire Bundles With Protective Liner;'' and CDCCL Task 
28-AWL-30, ``Fuel Boost Pump Wires in Conduit Installation--In Fuel 
Tank;'' of Section 9, of Boeing 767 Airworthiness Limitations (AWLs) 
and Certification Maintenance Requirements (CMRs), of the Boeing 767 
Maintenance Planning Data (MPD) Document, D622T001-9, Revision 
October 2012.

[[Page 14939]]

(o) No Alternative Actions, Intervals, and/or CDCCLs

    After accomplishing the revision required by paragraph (n) of 
this AD, no alternative actions (e.g., inspections), intervals, and/
or CDCCLs may be used unless the actions, intervals, and/or CDCCLs 
are approved as an alternative method of compliance in accordance 
with the procedures specified in paragraph (p) of this AD.

(p) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in the Related Information 
section of this AD. Information may be emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) AMOCs approved previously in accordance with AD 2000-11-06, 
Amendment 39-11754 (65 FR 34928, June 1, 2000; corrected August 1, 
2000 (65 FR 46862)), are approved as AMOCs with the corresponding 
requirements of this AD. Compliance time extensions approved 
previously in accordance with AD 2000-11-06 are not approved as 
AMOCs for the compliance times required by paragraph (k) of this AD.

(q) Related Information

    (1) For more information about this AD, contact Rebel Nichols, 
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle 
Aircraft Certification Office, 1601 Lind Avenue SW., Renton, 
Washington 98057-3356; phone: 425-917-6509; fax: 425-917-6590; 
email: [email protected].
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 
206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced 
service information at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue SW., Renton, Washington. For information on the 
availability of this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, February 26, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-05295 Filed 3-7-13; 8:45 am]
BILLING CODE 4910-13-P