Airworthiness Directives; The Boeing Company Model 767 Series Airplanes, 77790-77793 [2010-31371]
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Federal Register / Vol. 75, No. 239 / Tuesday, December 14, 2010 / Proposed Rules
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
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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
https://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.
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SUMMARY:
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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 https://
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 https://
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
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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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Federal Register / Vol. 75, No. 239 / Tuesday, December 14, 2010 / Proposed Rules
have changed in this proposed AD, as
listed in the following table:
REVISED PARAGRAPH IDENTIFIERS
Requirement in AD
2000–11–06
paragraph
paragraph
paragraph
paragraph
paragraph
(a)
(b)
(c)
(d)
(e)
.....................
.....................
.....................
.....................
.....................
Corresponding
requirement in
this proposed
AD
paragraph
paragraph
paragraph
paragraph
paragraph
(g).
(h).
(i).
(j).
(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 workhour. 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
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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.
§ 39.13
[Amended]
2. The FAA amends § 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
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77791
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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Federal Register / Vol. 75, No. 239 / Tuesday, December 14, 2010 / Proposed Rules
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
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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,
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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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Federal Register / Vol. 75, No. 239 / Tuesday, December 14, 2010 / Proposed Rules
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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–1158; Directorate
Identifier 2010–NM–125–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 747 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to all Model
747 airplanes. The existing AD currently
requires repetitive inspections to detect
damage of the sleeving and wire
bundles of the boost pumps of the
numbers 1 and 4 main fuel tanks, and
of the auxiliary tank jettison pumps (if
installed); replacement of any damaged
sleeving with new sleeving; and repair
or replacement of any damaged wires
with new wires. For airplanes on which
any burned wires are found, the existing
AD also requires an inspection to detect
damage of the conduit, and replacement
of any damaged conduit with a
serviceable conduit. 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 abrasion of the
Teflon sleeving and wires in the
bundles of the fuel boost pumps for the
numbers 1 and 4 main fuel tanks and of
the auxiliary tank jettison pumps (if
installed), which could result in
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SUMMARY:
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electrical arcing between the wires and
aluminum 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
https://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 https://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: Jon
Regimbal, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton,
Washington 98057–3356; telephone
(425) 917–6506; 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
PO 00000
Frm 00011
Fmt 4702
Sfmt 4702
77793
to an address listed under the
section. Include ‘‘Docket No.
FAA–2010–1158; Directorate Identifier
2010–NM–125–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 https://
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.
ADDRESSES
Discussion
On December 9, 1997, we issued AD
97–26–07, Amendment 39–10250 (62
FR 65352, December 12, 1997), for all
Model 747 airplanes. That AD currently
requires repetitive inspections to detect
damage of the sleeving and wire
bundles of the boost pumps of the
numbers 1 and 4 main fuel tanks, and
of the auxiliary tank jettison pumps (if
installed); replacement of any damaged
sleeving with new sleeving; and repair
or replacement of any damaged wires
with new wires. For airplanes on which
any burned wires are found, that AD
also requires an inspection to detect
damage of the conduit, and replacement
of any damaged conduit with a
serviceable conduit. That AD resulted
from reports of chafing of the sleeving.
We issued that AD to detect and correct
abrasion of the Teflon sleeving and
wires in the bundles of the fuel boost
pumps for the numbers 1 and 4 main
fuel tanks and of the auxiliary tank
jettison pumps (if installed), which
could result in electrical arcing between
the wires and the aluminum conduit
and consequent fire or explosion of the
fuel tank.
Actions Since Existing AD Was Issued
Since we issued AD 97–26–07, 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
repetitive inspection intervals.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 747–28A2204, Revision
3, dated March 11, 2010. The service
information reduces the initial
compliance time and repetitive
inspection interval for detecting damage
E:\FR\FM\14DEP1.SGM
14DEP1
]]>Agencies
[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]
[[Page 77790]]
=======================================================================
-----------------------------------------------------------------------
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).
-----------------------------------------------------------------------
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 https://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 https://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 https://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
[[Page 77791]]
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
------------------------------------------------------------------------
paragraph (a).......................... paragraph (g).
paragraph (b).......................... paragraph (h).
paragraph (c).......................... paragraph (i).
paragraph (d).......................... paragraph (j).
paragraph (e).......................... paragraph (k).
------------------------------------------------------------------------
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
[[Page 77792]]
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
[[Page 77793]]
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
