
[Federal Register Volume 75, Number 239 (Tuesday, December 14, 2010)]
[Proposed Rules]
[Pages 77790-77793]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-31371]



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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 Model 767 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 supersede an existing airworthiness 
directive (AD) that applies to all 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. This proposed AD would reduce 
the initial compliance time and repetitive inspection interval in the 
existing AD. This proposed AD results from 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 proposing 
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.

DATES: We must receive comments on this proposed AD by January 28, 
2011.

ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, 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; e-mail me.boecom@boeing.com; 
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 (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

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

SUPPLEMENTARY INFORMATION:

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

    On May 23, 2000, we issued AD 2000-11-06, amendment 39-11754 (65 FR 
34928, June 1, 2000), for all Model 767 airplanes. (A correction of the 
rule was published in the Federal Register on August 1, 2000 (65 FR 
46862).) That AD 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. 
That AD resulted from reports of chafing of Teflon sleeves that 
surround and protect electrical wires inside conduits installed in the 
fuel tanks. We issued that AD to ensure adequate protection to the fuel 
pump wire insulation. Such chafing of the wire insulation could 
eventually result in exposure of the electrical conductor, permit 
arcing from the wire to the conduit, and create a potential for a fuel 
tank fire or explosion.

Actions Since Existing AD Was Issued

    Since we issued AD 2000-11-06, we received fleet information from 
the manufacturer indicating that excessive chafing of the sleeving 
continues to occur much earlier than expected between scheduled 
inspections. Due to that fact, the manufacturer has revised the service 
information to reduce the initial and repetitive inspection intervals.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 767-28A0053, 
Revision 2, dated June 24, 2010. Boeing Service Bulletin 767-28A0053, 
Revision 1, dated August 5, 1999, was referred to as the appropriate 
source of service information for accomplishing the actions in the 
existing AD. Revision 2 of this service bulletin reduces the initial 
compliance time and repetitive inspection interval for the repetitive 
inspections required by the existing AD.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to develop on other products of the 
same type design. For this reason, we are proposing this AD, which 
would supersede AD 2000-11-06 and would retain the requirements of the 
existing AD at reduced compliance times.

Change to Existing AD

    This proposed AD would retain all requirements of AD 2000-11-06. 
Since that AD was issued, the AD format has been revised, and certain 
paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers

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have changed in this proposed AD, as listed in the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                           Corresponding requirement in
     Requirement in AD  2000-11-06               this proposed AD
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paragraph (a)..........................  paragraph (g).
paragraph (b)..........................  paragraph (h).
paragraph (c)..........................  paragraph (i).
paragraph (d)..........................  paragraph (j).
paragraph (e)..........................  paragraph (k).
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Costs of Compliance

    There are about 932 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 410 airplanes of 
U.S. registry. The new requirements of this proposed AD add no 
additional economic burden. The current costs for this proposed AD are 
repeated below for the convenience of affected operators.
    The actions that are required by AD 2000-11-06 and retained in this 
proposed AD take about 5 work-hours per airplane (for airplanes with 
jettison pumps) or 3 work-hours per airplane (for airplanes without 
jettison pumps), at an average labor rate of $85 per work-hour. 
Required parts cost about $336 per airplane. Based on these figures, 
the estimated cost of the currently required actions is either $761 or 
$591 per airplane, per inspection cycle.

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, 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

    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 FAA amends Sec.  39.13 by removing Amendment 39-11754 (65 FR 
34928, June 1, 2000) and adding the following new AD:

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

Comments Due Date

    (a) The FAA must receive comments on this AD action by January 
28, 2011.

Affected ADs

    (b) This AD supersedes AD 2000-11-06, Amendment 39-11754.

Applicability

    (c) This AD applies to all The Boeing Company Model 767-200, -
300, -300F, and -400ER series airplanes, certificated in any 
category.

Subject

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

Unsafe Condition

    (e) This AD results from 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. The Federal 
Aviation Administration is 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.

Compliance

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

Restatement of Requirements of AD 2000-11-06, Amendment 39-11754

Inspections

    (g) Perform a detailed visual inspection to detect 
discrepancies--including the presence of splices, 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; or Boeing 
Alert Service Bulletin 767-28A0053, Revision 2, dated June 24, 2010; 
as applicable. Repeat the inspection thereafter at intervals not to 
exceed 60,000 flight hours or 30,000 flight cycles, whichever occurs 
first. After the effective date of this AD, only Revision 2 of 
Boeing Alert Service Bulletin 767-28A0053 may be used.
    (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), whichever occurs later.
    (2) Within 18 months after July 6, 2000.

    Note 1: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc. may be used. Surface cleaning and 
elaborate access procedures may be required.''

Corrective Actions

    (h) 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 paragraph D. of 
the Accomplishment Instructions of Boeing Service Bulletin 767-
28A0053, Revision 1, dated August 5, 1999; or Boeing Alert Service 
Bulletin 767-28A0053, Revision 2, dated June 24, 2010; as 
applicable. After the effective date of this AD, only Revision 2 of 
Boeing Alert Service Bulletin 767-28A0053 may be used.
    (1) If no damage to the wiring is detected, prior to further 
flight, install new Teflon sleeves in accordance with Boeing Service

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Bulletin 767-28A0053, Revision 1, dated August 5, 1999; or Boeing 
Alert Service Bulletin 767-28A0053, Revision 2, dated June 24, 2010.
    (2) If any damage to the wiring is detected, prior to further 
flight, accomplish the requirements of paragraph (i) of this AD.
    (i) 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 paragraph D. 
of the Accomplishment Instructions of Boeing Service Bulletin 767-
28A0053, Revision 1, dated August 5, 1999; or Boeing Alert Service 
Bulletin 767-28A0053, Revision 2, dated June 24, 2010, as 
applicable. After the effective date of this AD, only Revision 2 of 
Boeing Alert Service Bulletin 767-28A0053 may be used.
    (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 Boeing Service Bulletin 767-28A0053, 
Revision 1, dated August 5, 1999; or Boeing Alert Service Bulletin 
767-28A0053, Revision 2, dated June 24, 2010.
    (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 Boeing Service Bulletin 767-
28A0053, Revision 1, dated August 5, 1999; or Boeing Alert Service 
Bulletin 767-28A0053, Revision 2, dated June 24, 2010.
    (i) If no sign of fuel is found, accomplish the actions 
specified by 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 Boeing Service Bulletin 767-28A0053, Revision 1, dated August 
5, 1999; or Boeing Alert Service Bulletin 767-28A0053, Revision 2, 
dated June 24, 2010.
    (B) Prior to further flight, install new Teflon sleeves, in 
accordance with Boeing Service Bulletin 767-28A0053, Revision 1, 
dated August 5, 1999; or Boeing Alert Service Bulletin 767-28A0053, 
Revision 2, dated June 24, 2010.
    (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 (h)(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 Boeing Service Bulletin 767-28A0053, Revision 1, dated August 
5, 1999; or Boeing Alert Service Bulletin 767-28A0053, Revision 2, 
dated June 24, 2010. 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.
    (D) Within 6,000 flight hours or 18 months after the initial 
fuel inspection specified by paragraph (h)(2) of this AD, whichever 
occurs first, replace the conduit with a new or serviceable conduit, 
in accordance with Boeing Service Bulletin 767-28A0053, Revision 1, 
dated August 5, 1999; or Boeing Alert Service Bulletin 767-28A0053, 
Revision 2, dated June 24, 2010. Such conduit replacement 
constitutes terminating action for the repetitive fuel inspections 
required by paragraph (i)(2)(i)(C) of this AD.
    (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 Boeing Service 
Bulletin 767-28A0053, Revision 1, dated August 5, 1999; or Boeing 
Alert Service Bulletin 767-28A0053, Revision 2, dated June 24, 2010. 
Thereafter, repeat the inspection specified in paragraph (a) of this 
AD at intervals not to exceed 60,000 flight hours or 30,000 flight 
cycles, whichever occurs first.

Pump Retest

    (j) 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 paragraph 
G., H., I., or J., as applicable, of the Accomplishment Instructions 
of Boeing Service Bulletin 767-28A0053, Revision 1, dated August 5, 
1999.

Reporting Requirement

    (k) Submit a report of positive inspection findings (findings of 
discrepancies only), along with any damaged wiring and sleeves, to 
the Seattle Manufacturing Inspection District Office (MIDO), 2500 
East Valley Road, Suite C-2, Renton, Washington 98057-3356; fax 
(425) 227-1159; at the applicable time specified in paragraph (k)(1) 
or (k)(2) of this AD. The report must include the airplane serial 
number; the number of total flight hours and flight cycles on the 
airplane; the location of the electrical cable on the airplane; and 
a statement indicating, if known, whether any wire has ever been 
removed and inspected during maintenance, along with the date (if 
known) of any such inspection. Information collection requirements 
contained in this regulation have been approved by the Office of 
Management and Budget (OMB) under the provisions of the Paperwork 
Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been 
assigned OMB Control Number 2120-0056.
    (1) For airplanes on which the initial inspection required by 
paragraph (g) of this AD is accomplished after July 6, 2000: Submit 
the report within 10 days after performing the initial inspection.
    (2) For airplanes on which the initial inspection required by 
paragraph (g) of this AD has been accomplished prior to July 6, 
2000: Submit the report for the initial inspection within 10 days 
after the effective date of this AD.

New Reduced Inspection Intervals

Repetitive Inspections

    (l) Do the inspection required by paragraph (g) of this AD at 
the time specified in paragraph (l)(1) or (l)(2) of this AD, as 
applicable, in accordance with Boeing Alert Service Bulletin 767-
28A0053, Revision 2, dated June 24, 2010. 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 of 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.

Paperwork Reduction Act Burden Statement

    (m) A federal agency may not conduct or sponsor, and a person is 
not required to respond to, nor shall a person be subject to a 
penalty for failure to comply with a collection of information 
subject to the requirements of the Paperwork Reduction Act unless 
that collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 5 minutes per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

Alternative Methods of Compliance (AMOCs)

    (n)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. Send information to 
Attn: Douglas Bryant, Aerospace Engineer, Propulsion Branch, ANM-
140S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; telephone (425) 917-6505; fax (425) 917-6590. 
Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.
    (3) AMOCs approved previously in accordance with AD 2000-11-06, 
Amendment 39-11754, are approved as

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alternative methods of compliance with the corresponding 
requirements of this AD. Compliance time extensions approved 
previously in accordance with AD 2000-11-06 are not approved as 
alternative methods of compliance for the compliance times required 
by paragraph (l) of this AD.


    Issued in Renton, Washington, on November 15, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-31371 Filed 12-13-10; 8:45 am]
BILLING CODE 4910-13-P


