Airworthiness Directives; The Boeing Company Airplanes, 54850-54854 [2012-21931]
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Federal Register / Vol. 77, No. 173 / Thursday, September 6, 2012 / Proposed Rules
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
The Boeing Company: Docket No. FAA–
2012–0863; Directorate Identifier 2012–
NM–108–AD.
(a) Comments Due Date
We must receive comments by October 22,
2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
airplanes, certificated in any category, as
identified in paragraphs (c)(1) and (c)(2) of
this AD.
(1) Model 737–300, –400, and –500 series
airplanes, as identified in Boeing Special
Attention Service Bulletin 737–33–1149,
dated April 13, 2012.
(2) Model 737–600, –700, –700C, –800,
–900, and –900ER series airplanes, as
identified in Boeing Special Attention
Service Bulletin 737–33–1146, dated
November 2, 2011.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 33, Lights.
(e) Unsafe Condition
This AD was prompted by a review of the
tail strobe light installation, which revealed
the tail strobe light is not electrically bonded
to primary structure of the airplane. We are
issuing this AD, in case of a direct lightning
strike to the tail strobe light, to prevent
damage to the operation of other critical
airplane systems due to electromagnetic
coupling and large transient voltages, and
damage to the control mechanisms or
surfaces due to a fire, which could result in
loss of control of the airplane.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Installation
Within 72 months after the effective date
of this AD, install a new tail strobe light
housing, install a new disconnect bracket,
and change the wire bundles, in accordance
with the Accomplishment Instructions of
Boeing Special Attention Service Bulletin
737–33–1146, dated November 2, 2011 (for
Model 737–600, –700, –700C, –800, –900,
and –900ER series airplanes), except as
provided by paragraph (i) of this AD; or
Boeing Special Attention Service Bulletin
737–33–1149, dated April 13, 2012 (for
Model 737–300, –400, and –500 series
airplanes).
(h) Concurrent Installation
For airplanes identified in Boeing Special
Attention Service Bulletin 737–33–1149,
dated April 13, 2012: Prior to or concurrently
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with the actions required by paragraph (g) of
this AD, install wingtips and tail strobe
lights, in accordance with the
Accomplishment Instructions of the
applicable service bulletin specified in
paragraph (h)(1), (h)(2), or (h)(3) of this AD:
(1) For Group 6 airplanes identified in
Boeing Special Attention Service Bulletin
737–33–1149, dated April 13, 2012: Use
Boeing Service Bulletin 737–33–1076, dated
September 22, 1988.
(2) For Group 7 airplanes identified in
Boeing Special Attention Service Bulletin
737–33–1149, dated April 13, 2012: Use
Boeing Service Bulletin 737–33–1078, dated
November 3, 1988.
(3) For Group 5 airplanes identified in
Boeing Special Attention Service Bulletin
737–33–1149, dated April 13, 2012: Use
Boeing Service Bulletin 737–33–1111, dated
August 29, 1996.
(i) Exception to Service Bulletin
Specifications
This paragraph clarifies the airplane
groups and configurations identified in
Boeing Special Attention Service Bulletin
737–33–1146, dated November 2, 2011.
Group 1, Config 1, comprises line number (L/
N) 1–1198 inclusive. Group 1, Config 2,
comprises L/N 1199–3060 inclusive.
(j) 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: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(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) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(k) Related Information
(1) For more information about this AD,
contact Marie Hogestad, Aerospace Engineer,
Systems and Equipment Branch, FAA, ANM–
130S, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, Washington
98057–3356; phone: (425) 917–6418; fax:
(425) 917–6590; email:
marie.hogestad@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
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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 98057–3356. For information on
the availability of this material at the FAA,
call 425–227–1221.
Issued in Renton, Washington, on August
24, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2012–21928 Filed 9–5–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0864; Directorate
Identifier 2011–NM–023–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede an
existing airworthiness directive (AD)
that applies to certain The Boeing
Company Model 767 airplanes. The
existing AD currently requires sealing
certain fasteners and stiffeners in the
fuel tank, changing certain wire bundle
clamp configurations on the fuel tank
walls, inspecting certain fasteners in the
fuel tanks and determining the method
of attachment of the vortex generators,
and performing corrective action if
necessary. We issued that AD to prevent
possible ignition sources in the
auxiliary (center) fuel tank, main fuel
tanks, and surge tanks caused by a
wiring short or lightning strike, which
could result in fuel tank explosions and
consequent loss of the airplane. Since
we issued that AD, another possible
ignition source location was identified.
This proposed AD would add a general
visual inspection for the presence of a
polytetrafluoroethylene (TFE) sleeve at
the clamp location on the rear spar, and
installation of a TFE sleeve if necessary.
This proposed AD would also add
airplanes to the applicability. We are
proposing this AD to correct the unsafe
condition on these products.
DATES: We must receive comments on
this proposed AD by October 22, 2012.
ADDRESSES: You may send comments by
any of the following methods:
SUMMARY:
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Federal Register / Vol. 77, No. 173 / Thursday, September 6, 2012 / Proposed Rules
• 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: 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, WA 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, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
TKELLEY on DSK3SPTVN1PROD with PROPOSALS
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
(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, WA
98057–3356; phone: 425–917–6509; fax:
425–917–6590; email:
rebel.nichols@faa.gov.
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–2012–0864; Directorate Identifier
2011–NM–023–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.
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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 August 7, 2009, we issued AD
2009–18–02, Amendment 39–15998 (74
FR 43621, August 27, 2009), for certain
Model 767–200, –300, –300F, and
–400ER series airplanes. That AD
requires sealing certain fasteners and
stiffeners in the fuel tank, changing
certain wire bundle clamp
configurations on the fuel tank walls,
inspecting certain fasteners in the fuel
tanks and determining the method of
attachment of the vortex generators, and
corrective action if necessary. That AD
resulted from fuel system reviews
conducted by the manufacturer. We
issued that AD to prevent possible
ignition sources in the auxiliary (center)
fuel tank, main fuel tanks, and surge
tanks caused by a wiring short or
lightning strike, which could result in
fuel tank explosions and consequent
loss of the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2009–18–02,
Amendment 39–15998 (74 FR 43621,
August 27, 2009), another possible
ignition source location was identified
that could also result in fuel tank
explosions and consequent loss of the
airplane.
Relevant Service Information
AD 2009–18–02, Amendment 39–
15998 (74 FR 43621, August 27, 2009),
refers to Boeing Service Bulletin 767–
57A0102, Revision 01, dated November
27, 2007, as the appropriate source of
service information for installing the
wire bundle sleeve and clamp and
applying fastener sealant. Boeing has
since revised this service bulletin. We
have reviewed Boeing Service Bulletin
767–57A0102, Revision 4, dated
September 20, 2011, which includes the
following changes (introduced in Boeing
Service Bulletin 767–57A0102, Revision
3, dated December 2, 2010): the addition
of work package 13, which includes a
general visual inspection of the clamp
location on the rear spar to determine
whether a polytetrafluoroethylene (TFE)
sleeve is installed between the clamp
and the plastic convoluted tubing, and
the installation of a TFE sleeve between
the clamp and the plastic convoluted
tubing, if necessary. Boeing Service
Bulletin 767–57A0102, Revision 4,
dated September 20, 2011, also adds
airplanes to the effectivity.
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54851
AD 2009–18–02, Amendment 39–
15998 (74 FR 43621, August 27, 2009),
refers to Boeing Service Bulletin 767–
57A0100, Revision 01, dated June 19,
2008, as the appropriate source of
service information for sealing certain
bracket fasteners and rear spar
stiffeners, and inspecting the vortex
generator attachment. Boeing has since
revised this service bulletin. We have
reviewed Boeing Service Bulletin 767–
57A0100, Revision 3, dated July 28,
2011, which adds clarifications, but no
new actions.
FAA’s Determination
We are proposing this AD 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.
Proposed AD Requirements
This proposed AD would retain all
requirements of AD 2009–18–02,
Amendment 39–15998 (74 FR 43621,
August 27, 2009). This proposed AD
would revise the applicability to
include additional airplanes. This
proposed AD would also add a general
visual inspection for the presence of a
TFE sleeve at the clamp location on the
rear spar, and installation of a TFE
sleeve if necessary.
Change to Existing AD
This proposed AD would retain all
requirements of AD 2009–18–02,
Amendment 39–15998 (74 FR 43621,
August 27, 2009). Since AD 2009–18–02
was issued, the AD format has been
revised, and certain paragraphs have
been rearranged. As a result, the
corresponding paragraph identifiers
have changed in this proposed AD, as
listed in the following table:
REVISED PARAGRAPH IDENTIFIERS
Requirement/information in AD 2009–18–
02, Amendment 39–
15998 (74 FR 43621,
August 27, 2009)
paragraph (f) .............
paragraph (g) ............
Note 1 .......................
Corresponding
requirement in this
proposed AD
paragraph (g).
paragraph (h).
paragraph (i).
Other Changes
We have revised certain headings
throughout this AD.
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:
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Federal Register / Vol. 77, No. 173 / Thursday, September 6, 2012 / Proposed Rules
ESTIMATED COSTS
Cost per product
Number of
U.S.-registered
airplanes
$0
$510
367
$187,170
114 work-hours × $85
per hour = $9,690.
0
9,690
37
358,530
1 work-hour × $85 per
hour = $85.
0
85
9
765
250 work-hours × $85
per hour = $21,250.
1,632
22,882
376
8,603,632
874 work-hours × $85
per hour = $74,290.
1,304
75,594
37
2,796,978
338
2,548
1
2,548
0
85
414
35,190
Action
Labor cost
Group 1—Seal ends of fasteners—Boeing Service Bulletin 767–57A0100 (retained actions
from AD 2009–18–02, Amendment 39–15998
(74 FR 43621, August 27, 2009)).
Group 2—Seal ends of fasteners—Boeing Service Bulletin 767–57A0100 (retained actions
from AD 2009–18–02, Amendment 39–15998
(74 FR 43621, August 27, 2009)).
Group 3—Inspection—Boeing Service Bulletin
767–57A0100 (retained actions from AD
2009–18–02, Amendment 39–15998 (74 FR
43621, August 27, 2009)).
Group 1—Change wire bundle clamp configurations, Boeing Service Bulletin 767–57A0102
(retained actions from AD 2009–18–02,
Amendment 39–15998 (74 FR 43621, August
27, 2009)).
Group 2—Change wire bundle clamp configurations, Boeing Service Bulletin 767–57A0102
(retained actions from AD 2009–18–02,
Amendment 39–15998 (74 FR 43621, August
27, 2009)).
Group 3—Change wire bundle clamp configuration and seal fasteners, Boeing Service Bulletin 767–57A0102 (retained actions from AD
2009–18–02, Amendment 39–15998 (74 FR
43621, August 27, 2009)).
All airplanes—Inspection (new proposed action)
6 work-hours × $85 per
hour = $510.
We estimate the following costs to do
any necessary repair that would be
Parts cost
26 work-hours × $85
per hour = $2,210.
1 work-hour × $85 per
hour = $85.
required based on the results of the
proposed inspection. We have no way of
Cost on U.S.
operators
determining the number of aircraft that
might need this repair:
ON-CONDITION COSTS
Cost per
product
Labor cost
Seal ends of fasteners—Boeing Service Bulletin 767–57A0100 (retained
actions from AD 2009-18–02, Amendment 39–15998 (74 FR 43621,
August 27, 2009)).
Installation of TFE sleeve—Boeing Service Bulletin 767–57A0102 ...........
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Action
6 work-hours × $85 per hour = $510
$0
1 work-hour × $85 per hour = $85 ...
0
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
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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
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Parts cost
Up to $510.
$85.
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:
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Federal Register / Vol. 77, No. 173 / Thursday, September 6, 2012 / Proposed Rules
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 airworthiness directive (AD)
2009–18–02, Amendment 39–15998 (74
FR 43621, August 27, 2009), and adding
the following new AD:
The Boeing Company: Docket No. FAA–
2012–0864; Directorate Identifier 2011–
NM–023–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by October 22, 2012.
(b) Affected ADs
This AD supersedes AD 2009–18–02,
Amendment 39–15998 (74 FR 43621, August
27, 2009).
(c) Applicability
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–
57A0100, Revision 3, dated July 28, 2011;
and Boeing Service Bulletin 767–57A0102,
Revision 4, dated September 20, 2011.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 57: Wings.
(e) Unsafe Condition
This AD was prompted by fuel system
reviews conducted by the manufacturer. We
are issuing this AD to prevent possible
ignition sources in the auxiliary (center) fuel
tank, main fuel tanks, and surge tanks caused
by a wiring short or lightning strike, which
could result in fuel tank explosions and
consequent loss of the airplane.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Fastener Sealant Application
This paragraph restates the requirements of
paragraph (f) of AD 2009–18–02, Amendment
39–15998 (74 FR 43621, August 27, 2009),
with revised service information. For
airplanes identified in Boeing Service
Bulletin 767–57A0100, Revision 1, dated
June 19, 2008: Within 60 months after
October 1, 2009 (the effective date of AD
2009–18–02), do the actions in paragraphs
(g)(1) and (g)(2) of this AD, as applicable, in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 767–
57A0100, Revision 01, dated June 19, 2008;
or Boeing Service Bulletin 767–57A0100,
Revision 3, dated July 28, 2011. As of the
effective date of this AD, only Boeing Service
Bulletin 767–57A0100, Revision 3, dated July
28, 2011, may be used to accomplish the
requirements of this paragraph.
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(1) For Groups 1 and 2 airplanes: Seal the
ends of the fasteners on the brackets that
hold the vortex generators, and seal the ends
of the fasteners on certain stiffeners on the
rear spar, as applicable.
(2) For Group 3 airplanes: Do a detailed
inspection to determine the method of
attachment of the vortex generators and,
before further flight, do all applicable
specified corrective actions.
(h) Retained Wire Bundle Sleeve and Clamp
Installation and Fastener Sealant
Application for Currently Affected Airplanes
This paragraph restates the requirements of
paragraph (g) of AD 2009–18–02,
Amendment 39–15998 (74 FR 43621, August
27, 2009), with revised service information.
For airplanes identified in Boeing Service
Bulletin 767–57A0102, Revision 01, dated
November 27, 2007: Within 60 months after
October 1, 2009 (the effective date of AD
2009–18–02), do the actions specified in
paragraphs (h)(1), (h)(2), and (h)(3) of this
AD, as applicable, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 767–57A0102, Revision 01,
dated November 27, 2007; or Boeing Service
Bulletin 767–57A0102, Revision 4, dated
September 20, 2011. As of the effective date
of this AD, only Boeing Service Bulletin 767–
57A0102, Revision 4, dated September 20,
2011, may be used to accomplish the actions
required by this paragraph.
(1) Change the wire bundle clamp
configurations at specified locations on the
fuel tank walls.
(2) Seal the fasteners and certain stiffeners
at specified locations in the fuel tank.
(3) Do a detailed inspection of the sealant
of the fasteners in the auxiliary tank center
bay and rib 28 of the left and right main fuel
tanks. Seal any unsealed fasteners before
further flight.
(i) Definition
This paragraph restates the information
specified in Note 1 of AD 2009–18–02,
Amendment 39–15998 (74 FR 43621, August
27, 2009). For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
(j) New Wire Bundle Sleeve and Clamp
Installation and Fastener Sealant
Application for Newly Added Airplanes
For airplanes identified in Boeing Service
Bulletin 767–57A0102, Revision 4, dated
September 20, 2011, but not identified in
paragraph (h) of this AD: Do the actions
required by paragraph (h) of this AD within
60 months after the effective date of this AD.
(k) New Inspection and Sleeve Installation
For airplanes identified as Groups 1 and 2
in Boeing Service Bulletin 767–57A0102,
Revision 4, dated September 20, 2011:
Within 60 months after the effective date of
this AD, do a general visual inspection of the
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54853
clamp location on the rear spar to determine
whether a polytetrafluoroethylene (TFE)
sleeve is installed between the clamp and the
plastic convoluted tube, in accordance with
Work Package 13 of the Accomplishment
Instructions of Boeing Service Bulletin 767–
57A0102, Revision 4, dated September 20,
2011.
(1) If a TFE sleeve is not installed between
the clamp and the plastic convoluted tubing,
before further flight, install a TFE sleeve, in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 767–
57A0102, Revision 4, dated September 20,
2011.
(2) If a TFE sleeve is installed between the
clamp and the plastic convoluted tubing, no
more work is required by this paragraph.
(l) Credit for Previous Actions
(1) This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using Boeing Service
Bulletin 767–57A0100, dated August 21,
2006; Revision 1, dated June 19, 2008; or
Revision 2, dated May 20, 2010.
(2) This paragraph provides credit for the
actions required by paragraph (h) of this AD,
if those actions were performed before the
effective date of this AD using Boeing Service
Bulletin 767–57A0102, Revision 01, dated
November 27, 2007; Revision 2, dated
January 7, 2010; or Revision 3, dated
December 2, 2010.
(m) 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: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(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 2009–18–02,
Amendment 39–15998 (74 FR 43621, August
27, 2009), are approved as AMOCs for the
corresponding provisions of this AD.
(n) 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, WA 98057–3356;
phone: 425–917–6509; fax: 425–917–6590;
email: rebel.nichols@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com. You
E:\FR\FM\06SEP1.SGM
06SEP1
54854
Federal Register / Vol. 77, No. 173 / Thursday, September 6, 2012 / Proposed Rules
may review copies of the referenced service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of
this material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on August
24, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2012–21931 Filed 9–5–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0862; Directorate
Identifier 2011–NM–198–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede an
existing airworthiness directive (AD)
that applies to certain The Boeing
Company Model 747–400 and 747–400F
series airplanes. The existing AD
currently requires installing drains and
drain tubes to eliminate water
accumulation in the dripshield above
the M826 cardfile in the main
equipment center. Since we issued that
AD, we received reports of continued
water damage to diode fire card
285U0072–1 in the M826 automatic fire
overheat logic test system cardfile
following a false FWD CARGO FIRE
message, with no change in frequency,
which resulted in an air turn back. This
proposed AD would instead require
installing drain tubes, relocating wire
bundle routing, installing a new drip
shield and drip shield deflectors, and
replacing insulation blankets. For
certain airplanes, this proposed AD
would also concurrently require sealing
the drain slot, installing spuds, and
installing drain tubes. We are proposing
this AD to prevent water from exiting
over the edge of the existing drip shield
and contaminating electrical
components in the M826 cardfile, which
could result in an electrical short and
potential loss of several functions
essential for safe flight.
DATES: We must receive comments on
this proposed AD by October 22, 2012.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
TKELLEY on DSK3SPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Mar<15>2010
16:15 Sep 05, 2012
Jkt 226001
11.43 and 11.45, 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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
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 98057–3356.
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
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Francis Smith, Aerospace Engineer,
Cabin Safety & Environmental Control
Systems, ANM–150S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, Washington
98057–3356; phone: 425–917–6457; fax:
425–917–6590; email: francis.smith@
faa.gov.
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–2012–0862; Directorate Identifier
2011–NM–198–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
PO 00000
Frm 00016
Fmt 4702
Sfmt 4702
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 April 7, 2008, we issued AD 2008–
08–25, Amendment 39–15479 (73 FR
21240, April 21, 2008), for certain
Boeing Model 747–400F and –400 series
airplanes. That AD requires installing
drains and drain tubes to eliminate
water accumulation in the dripshield
above the M826 cardfile in the main
equipment center. That AD resulted
from a report that water from the
dripshield entered the card file and
damaged a circuit card, causing the AFT
CARGO FIRE MSG message to be
illuminated, and resulting in an air turn
back. We issued that AD to prevent
water from entering the card file and
damaging a circuit card. Failure of one
or more of the 15 fuel system circuit
cards in the card file could cause loss
of fuel management, which could cause
unavailability of fuel. Failure of one or
more of the 35 fire detection circuit
cards could cause a false message of a
fire, or no message of a fire when there
is a fire.
Actions Since Existing AD Was Issued
Since we issued AD 2008–08–25,
Amendment 39–15479 (73 FR 21240,
April 21, 2008), we received reports of
continued water damage to diode fire
card 285U0072–1 in the M826
automatic fire overheat logic test system
cardfile following a false FWD CARGO
FIRE message, with no change in
frequency, which resulted in an air turn
back. These events occurred on
airplanes on which the actions required
by AD 2008–08–25 had already been
accomplished.
Relevant Service Information
We reviewed Boeing Alert Service
Bulletin 747–25A3580, Revision 1,
dated July 14, 2011 (for Model 747–
400F series airplanes); and Boeing Alert
Service Bulletin 747–25A3581, Revision
1, dated June 30, 2011 (for Model 747–
400 series airplanes). The service
information describes procedures for
installing drain tubes, relocating wire
bundle routing, installing a new drip
shield and drip shield deflectors, and
replacing insulation blankets.
E:\FR\FM\06SEP1.SGM
06SEP1
]]>Agencies
[Federal Register Volume 77, Number 173 (Thursday, September 6, 2012)]
[Proposed Rules]
[Pages 54850-54854]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-21931]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0864; Directorate Identifier 2011-NM-023-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to certain The Boeing Company Model 767 airplanes.
The existing AD currently requires sealing certain fasteners and
stiffeners in the fuel tank, changing certain wire bundle clamp
configurations on the fuel tank walls, inspecting certain fasteners in
the fuel tanks and determining the method of attachment of the vortex
generators, and performing corrective action if necessary. We issued
that AD to prevent possible ignition sources in the auxiliary (center)
fuel tank, main fuel tanks, and surge tanks caused by a wiring short or
lightning strike, which could result in fuel tank explosions and
consequent loss of the airplane. Since we issued that AD, another
possible ignition source location was identified. This proposed AD
would add a general visual inspection for the presence of a
polytetrafluoroethylene (TFE) sleeve at the clamp location on the rear
spar, and installation of a TFE sleeve if necessary. This proposed AD
would also add airplanes to the applicability. We are proposing this AD
to correct the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by October 22,
2012.
ADDRESSES: You may send comments by any of the following methods:
[[Page 54851]]
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: 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, WA 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, WA. 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 (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, WA 98057-3356; phone: 425-917-
6509; fax: 425-917-6590; email: rebel.nichols@faa.gov.
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-2012-0864;
Directorate Identifier 2011-NM-023-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 August 7, 2009, we issued AD 2009-18-02, Amendment 39-15998 (74
FR 43621, August 27, 2009), for certain Model 767-200, -300, -300F, and
-400ER series airplanes. That AD requires sealing certain fasteners and
stiffeners in the fuel tank, changing certain wire bundle clamp
configurations on the fuel tank walls, inspecting certain fasteners in
the fuel tanks and determining the method of attachment of the vortex
generators, and corrective action if necessary. That AD resulted from
fuel system reviews conducted by the manufacturer. We issued that AD to
prevent possible ignition sources in the auxiliary (center) fuel tank,
main fuel tanks, and surge tanks caused by a wiring short or lightning
strike, which could result in fuel tank explosions and consequent loss
of the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2009-18-02, Amendment 39-15998 (74 FR 43621,
August 27, 2009), another possible ignition source location was
identified that could also result in fuel tank explosions and
consequent loss of the airplane.
Relevant Service Information
AD 2009-18-02, Amendment 39-15998 (74 FR 43621, August 27, 2009),
refers to Boeing Service Bulletin 767-57A0102, Revision 01, dated
November 27, 2007, as the appropriate source of service information for
installing the wire bundle sleeve and clamp and applying fastener
sealant. Boeing has since revised this service bulletin. We have
reviewed Boeing Service Bulletin 767-57A0102, Revision 4, dated
September 20, 2011, which includes the following changes (introduced in
Boeing Service Bulletin 767-57A0102, Revision 3, dated December 2,
2010): the addition of work package 13, which includes a general visual
inspection of the clamp location on the rear spar to determine whether
a polytetrafluoroethylene (TFE) sleeve is installed between the clamp
and the plastic convoluted tubing, and the installation of a TFE sleeve
between the clamp and the plastic convoluted tubing, if necessary.
Boeing Service Bulletin 767-57A0102, Revision 4, dated September 20,
2011, also adds airplanes to the effectivity.
AD 2009-18-02, Amendment 39-15998 (74 FR 43621, August 27, 2009),
refers to Boeing Service Bulletin 767-57A0100, Revision 01, dated June
19, 2008, as the appropriate source of service information for sealing
certain bracket fasteners and rear spar stiffeners, and inspecting the
vortex generator attachment. Boeing has since revised this service
bulletin. We have reviewed Boeing Service Bulletin 767-57A0100,
Revision 3, dated July 28, 2011, which adds clarifications, but no new
actions.
FAA's Determination
We are proposing this AD 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.
Proposed AD Requirements
This proposed AD would retain all requirements of AD 2009-18-02,
Amendment 39-15998 (74 FR 43621, August 27, 2009). This proposed AD
would revise the applicability to include additional airplanes. This
proposed AD would also add a general visual inspection for the presence
of a TFE sleeve at the clamp location on the rear spar, and
installation of a TFE sleeve if necessary.
Change to Existing AD
This proposed AD would retain all requirements of AD 2009-18-02,
Amendment 39-15998 (74 FR 43621, August 27, 2009). Since AD 2009-18-02
was issued, the AD format has been revised, and certain paragraphs have
been rearranged. As a result, the corresponding paragraph identifiers
have changed in this proposed AD, as listed in the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Requirement/information in AD 2009-18-02,
Amendment 39-15998 (74 FR 43621, August Corresponding requirement in
27, 2009) this proposed AD
------------------------------------------------------------------------
paragraph (f)............................. paragraph (g).
paragraph (g)............................. paragraph (h).
Note 1.................................... paragraph (i).
------------------------------------------------------------------------
Other Changes
We have revised certain headings throughout this AD.
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:
[[Page 54852]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Labor cost Parts cost Cost per registered Cost on U.S.
product airplanes operators
----------------------------------------------------------------------------------------------------------------
Group 1--Seal ends of 6 work-hours x $0 $510 367 $187,170
fasteners--Boeing Service $85 per hour =
Bulletin 767-57A0100 $510.
(retained actions from AD
2009-18-02, Amendment 39-
15998 (74 FR 43621, August
27, 2009)).
Group 2--Seal ends of 114 work-hours x 0 9,690 37 358,530
fasteners--Boeing Service $85 per hour =
Bulletin 767-57A0100 $9,690.
(retained actions from AD
2009-18-02, Amendment 39-
15998 (74 FR 43621, August
27, 2009)).
Group 3--Inspection--Boeing 1 work-hour x 0 85 9 765
Service Bulletin 767-57A0100 $85 per hour =
(retained actions from AD $85.
2009-18-02, Amendment 39-
15998 (74 FR 43621, August
27, 2009)).
Group 1--Change wire bundle 250 work-hours x 1,632 22,882 376 8,603,632
clamp configurations, Boeing $85 per hour =
Service Bulletin 767-57A0102 $21,250.
(retained actions from AD
2009-18-02, Amendment 39-
15998 (74 FR 43621, August
27, 2009)).
Group 2--Change wire bundle 874 work-hours x 1,304 75,594 37 2,796,978
clamp configurations, Boeing $85 per hour =
Service Bulletin 767-57A0102 $74,290.
(retained actions from AD
2009-18-02, Amendment 39-
15998 (74 FR 43621, August
27, 2009)).
Group 3--Change wire bundle 26 work-hours x 338 2,548 1 2,548
clamp configuration and seal $85 per hour =
fasteners, Boeing Service $2,210.
Bulletin 767-57A0102
(retained actions from AD
2009-18-02, Amendment 39-
15998 (74 FR 43621, August
27, 2009)).
All airplanes--Inspection (new 1 work-hour x 0 85 414 35,190
proposed action). $85 per hour =
$85.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repair that
would be required based on the results of the proposed inspection. We
have no way of determining the number of aircraft that might need this
repair:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Seal ends of fasteners--Boeing Service 6 work-hours x $85 per $0 Up to $510.
Bulletin 767-57A0100 (retained actions hour = $510.
from AD 2009[dash]18-02, Amendment 39-
15998 (74 FR 43621, August 27, 2009)).
Installation of TFE sleeve--Boeing 1 work-hour x $85 per hour 0 $85.
Service Bulletin 767-57A0102. = $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, 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),
(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:
[[Page 54853]]
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 airworthiness directive
(AD) 2009-18-02, Amendment 39-15998 (74 FR 43621, August 27, 2009), and
adding the following new AD:
The Boeing Company: Docket No. FAA-2012-0864; Directorate Identifier
2011-NM-023-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by October 22,
2012.
(b) Affected ADs
This AD supersedes AD 2009-18-02, Amendment 39-15998 (74 FR
43621, August 27, 2009).
(c) Applicability
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 767-57A0100, Revision 3, dated
July 28, 2011; and Boeing Service Bulletin 767-57A0102, Revision 4,
dated September 20, 2011.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 57: Wings.
(e) Unsafe Condition
This AD was prompted by fuel system reviews conducted by the
manufacturer. We are issuing this AD to prevent possible ignition
sources in the auxiliary (center) fuel tank, main fuel tanks, and
surge tanks caused by a wiring short or lightning strike, which
could result in fuel tank explosions and consequent loss of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Fastener Sealant Application
This paragraph restates the requirements of paragraph (f) of AD
2009-18-02, Amendment 39-15998 (74 FR 43621, August 27, 2009), with
revised service information. For airplanes identified in Boeing
Service Bulletin 767-57A0100, Revision 1, dated June 19, 2008:
Within 60 months after October 1, 2009 (the effective date of AD
2009-18-02), do the actions in paragraphs (g)(1) and (g)(2) of this
AD, as applicable, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 767-57A0100, Revision 01,
dated June 19, 2008; or Boeing Service Bulletin 767-57A0100,
Revision 3, dated July 28, 2011. As of the effective date of this
AD, only Boeing Service Bulletin 767-57A0100, Revision 3, dated July
28, 2011, may be used to accomplish the requirements of this
paragraph.
(1) For Groups 1 and 2 airplanes: Seal the ends of the fasteners
on the brackets that hold the vortex generators, and seal the ends
of the fasteners on certain stiffeners on the rear spar, as
applicable.
(2) For Group 3 airplanes: Do a detailed inspection to determine
the method of attachment of the vortex generators and, before
further flight, do all applicable specified corrective actions.
(h) Retained Wire Bundle Sleeve and Clamp Installation and Fastener
Sealant Application for Currently Affected Airplanes
This paragraph restates the requirements of paragraph (g) of AD
2009-18-02, Amendment 39-15998 (74 FR 43621, August 27, 2009), with
revised service information. For airplanes identified in Boeing
Service Bulletin 767-57A0102, Revision 01, dated November 27, 2007:
Within 60 months after October 1, 2009 (the effective date of AD
2009-18-02), do the actions specified in paragraphs (h)(1), (h)(2),
and (h)(3) of this AD, as applicable, in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 767-57A0102,
Revision 01, dated November 27, 2007; or Boeing Service Bulletin
767-57A0102, Revision 4, dated September 20, 2011. As of the
effective date of this AD, only Boeing Service Bulletin 767-57A0102,
Revision 4, dated September 20, 2011, may be used to accomplish the
actions required by this paragraph.
(1) Change the wire bundle clamp configurations at specified
locations on the fuel tank walls.
(2) Seal the fasteners and certain stiffeners at specified
locations in the fuel tank.
(3) Do a detailed inspection of the sealant of the fasteners in
the auxiliary tank center bay and rib 28 of the left and right main
fuel tanks. Seal any unsealed fasteners before further flight.
(i) Definition
This paragraph restates the information specified in Note 1 of
AD 2009-18-02, Amendment 39-15998 (74 FR 43621, August 27, 2009).
For the purposes of this AD, a detailed inspection is: ``An
intensive examination of a specific item, installation, or assembly
to detect damage, failure, or irregularity. Available lighting is
normally supplemented with a direct source of good lighting at an
intensity deemed appropriate. Inspection aids such as mirror,
magnifying lenses, etc., may be necessary. Surface cleaning and
elaborate procedures may be required.''
(j) New Wire Bundle Sleeve and Clamp Installation and Fastener Sealant
Application for Newly Added Airplanes
For airplanes identified in Boeing Service Bulletin 767-57A0102,
Revision 4, dated September 20, 2011, but not identified in
paragraph (h) of this AD: Do the actions required by paragraph (h)
of this AD within 60 months after the effective date of this AD.
(k) New Inspection and Sleeve Installation
For airplanes identified as Groups 1 and 2 in Boeing Service
Bulletin 767-57A0102, Revision 4, dated September 20, 2011: Within
60 months after the effective date of this AD, do a general visual
inspection of the clamp location on the rear spar to determine
whether a polytetrafluoroethylene (TFE) sleeve is installed between
the clamp and the plastic convoluted tube, in accordance with Work
Package 13 of the Accomplishment Instructions of Boeing Service
Bulletin 767-57A0102, Revision 4, dated September 20, 2011.
(1) If a TFE sleeve is not installed between the clamp and the
plastic convoluted tubing, before further flight, install a TFE
sleeve, in accordance with the Accomplishment Instructions of Boeing
Service Bulletin 767-57A0102, Revision 4, dated September 20, 2011.
(2) If a TFE sleeve is installed between the clamp and the
plastic convoluted tubing, no more work is required by this
paragraph.
(l) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Boeing Service Bulletin 767-57A0100,
dated August 21, 2006; Revision 1, dated June 19, 2008; or Revision
2, dated May 20, 2010.
(2) This paragraph provides credit for the actions required by
paragraph (h) of this AD, if those actions were performed before the
effective date of this AD using Boeing Service Bulletin 767-57A0102,
Revision 01, dated November 27, 2007; Revision 2, dated January 7,
2010; or Revision 3, dated December 2, 2010.
(m) 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: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(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 2009-18-02,
Amendment 39-15998 (74 FR 43621, August 27, 2009), are approved as
AMOCs for the corresponding provisions of this AD.
(n) 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, WA
98057-3356; phone: 425-917-6509; fax: 425-917-6590; email:
rebel.nichols@faa.gov.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You
[[Page 54854]]
may review copies of the referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA,
call 425-227-1221.
Issued in Renton, Washington, on August 24, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-21931 Filed 9-5-12; 8:45 am]
BILLING CODE 4910-13-P
