[Federal Register Volume 78, Number 136 (Tuesday, July 16, 2013)]
[Rules and Regulations]
[Pages 42411-42415]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-15526]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0864; Directorate Identifier 2011-NM-023-AD;
Amendment 39-17496; AD 2013-13-08]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are superseding an existing airworthiness directive (AD)
for certain The Boeing Company Model 767 airplanes. That 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 actions if necessary. This new AD adds a general visual
inspection for the presence of a polytetrafluoroethylene
[[Page 42412]]
(TFE) sleeve at the clamp location on the rear spar, and installation
of a TFE sleeve if necessary. This new AD also adds airplanes to the
applicability. This AD was prompted by fuel system reviews conducted by
the manufacturer, and the identification of another possible ignition
source location. 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.
DATES: This AD is effective August 20, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of August 20,
2013.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of October
1, 2009 (76 FR 43621, August 27, 2009).
ADDRESSES: 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 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 http://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (phone: 800-647-5527) is Document Management Facility,
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
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: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2009-18-02, Amendment 39-15998 (74 FR 43621,
August 27, 2009). AD 2009-18-02 applied to the specified products. The
NPRM published in the Federal Register on September 6, 2012 (77 FR
54850). The NPRM proposed to continue to require 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.
The NPRM also proposed to require 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. The NPRM also proposed to add airplanes to the
applicability.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(77 FR 54850, September 6, 2012) and the FAA's response to each
comment.
United Airlines stated that it has no comment for the NPRM (77 FR
54850, September 6, 2012).
Request to Change Acronym
Boeing requested that we change the NPRM (77 FR 54850, September 6,
2012) to correct an acronym from ``TFE'' to ``PTFE.'' Boeing stated
that the proper acronym for polytetrafluoroethylene is ``PTFE.''
We disagree with changing the acronym in this AD. The service
information required by this AD refers to polytetrafluoroethylene as
``TFE'' throughout; therefore, to reduce the potential for confusion,
we have not changed the acronym ``TFE'' in this AD.
Request for Credit
Air New Zealand requested that we allow credit for prior
incorporation of Boeing Service Bulletin 767-57A0102, Revision 3, dated
December 2, 2010, for the requirements of paragraph (j) of the NPRM (77
FR 54850, September 6, 2012).
We agree with the request, but provide the following clarification.
Paragraph (j) of this AD specifies the compliance time for certain
airplanes to accomplish the actions of paragraph (h) of this AD. We
have changed the heading for paragraph (j) of this AD to focus on the
compliance time. Paragraph (h) of this AD specifies to do the actions
in accordance with Boeing Service Bulletins 767-57A0102, Revision 01,
dated November 27, 2007; or Revision 4, dated September 20, 2011. Since
paragraph (l)(2) of this AD gives credit for Boeing Service Bulletin
767-57A0102, Revision 3, dated December 2, 2010, for accomplishing the
actions in paragraph (h) of this AD, we have not changed the AD in this
regard.
STC Winglet Comment
Aviation Partners Boeing and Air New Zealand stated that the
installation of winglets per STC ST01920SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027F43B9A7486E86257B1D006591EE?OpenDocument&Highlight=st01920se) does
not affect the accomplishment of the manufacturer's service
instructions.
We have added paragraph (c)(2) to this AD to state that
installation of STC ST01920SE does not affect the ability to accomplish
the actions required by this AD. Therefore, for airplanes on which STC
ST01920SE is installed, a ``change in product'' alternative method of
compliance (AMOC) approval request is not necessary to comply with the
requirements of 14 CFR 39.17. For all other AMOC requests, the operator
must request approval for an AMOC in accordance with the procedures
specified in paragraph (m) of this AD.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the change described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (77 FR 54850, September 6, 2012) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (77 FR 54850, September 6, 2012).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 414 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
[[Page 42413]]
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[dash]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[dash]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 $21,250.
767[dash]57A0102 (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 $74,290.
767[dash]57A0102 (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[dash]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
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 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 hour = $510.
actions from AD 2009-18-02, Amendment
39-15998 (74 FR 43621, August 27,
2009)).
Installation of TFE sleeve--Boeing 1 work-hour x $85 per $0 $85.
Service Bulletin 767[dash]57A0102. hour = $85.
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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 AD will not have federalism
implications under Executive Order 13132. This AD will 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 this AD:
[[Page 42414]]
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under 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.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2009-18-02, Amendment 39-15998 (74 FR 43621, August 27, 2009), and
adding the following new AD:
2013-13-08 The Boeing Company: Amendment 39-17496; Docket No. FAA-
2012-0864; Directorate Identifier 2011-NM-023-AD.
(a) Effective Date
This airworthiness directive (AD) is effective August 20, 2013.
(b) Affected ADs
This AD supersedes AD 2009-18-02, Amendment 39-15998 (74 FR
43621, August 27, 2009).
(c) Applicability
(1) This AD applies to The Boeing Company Model 767-200, -300, -
300F, and -400ER series airplanes; certificated in any category; as
identified in Boeing Service Bulletin 767-57A0100, Revision 3, dated
July 28, 2011; and Boeing Service Bulletin 767-57A0102, Revision 4,
dated September 20, 2011.
(2) Installation of Supplemental Type Certificate (STC)
ST01920SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027F43B9A7486E86257B1D006591EE?OpenDocument&Highlight=st01920se)
does not affect the ability to accomplish the actions required by
this AD. Therefore, for airplanes on which STC ST01920SE is
installed, a ``change in product'' alternative method of compliance
(AMOC) approval request is not necessary to comply with the
requirements of 14 CFR 39.17.
(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 01, dated June 19, 2008:
Within 60 months after October 1, 2009 (the effective date of AD
2009-18-02), do the actions in paragraph (g)(1) or (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
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) Compliance Time for 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, which is not incorporated by reference in
this AD; Revision 1, dated June 19, 2008; or Revision 2, dated May
20, 2010, which is not incorporated by reference in this AD.
(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 1, dated November 27, 2007; Revision 2, dated January 7,
2010, which is not incorporated by
[[Page 42415]]
reference in this AD; or Revision 3, dated December 2, 2010, which
is not incorporated by reference in this AD.
(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: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) AMOCs approved previously in accordance with AD 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:
[email protected].
(2) Service information identified in this AD that is not
incorporated by reference may be obtained at the address specified
in paragraph (o)(5) of this AD. 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 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.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(3) The following service information was approved for IBR on
August 20, 2013.
(i) Boeing Service Bulletin 767-57A0100, Revision 3, dated July
28, 2011.
(ii) Boeing Service Bulletin 767-57A0102, Revision 4, dated
September 20, 2011.
(4) The following service information was approved for IBR on
October 1, 2009, (74 FR 43621, August 27, 2009).
(i) Boeing Service Bulletin 767-57A0100, Revision 01, dated June
19, 2008.
(ii) Boeing Service Bulletin 767-57A0102, Revision 01, dated
November 27, 2007.
(5) 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.
(6) You may view this service information at FAA, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
(7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on June 13, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-15526 Filed 7-15-13; 8:45 am]
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