[Federal Register Volume 77, Number 173 (Thursday, September 6, 2012)]
[Proposed Rules]
[Pages 54850-54854]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-21931]
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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]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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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 http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, 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 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: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-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 http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On 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
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paragraph (f)............................. paragraph (g).
paragraph (g)............................. paragraph (h).
Note 1.................................... paragraph (i).
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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
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Number of U.S.-
Action Labor cost Parts cost Cost per registered Cost on U.S.
product airplanes operators
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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.
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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
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Action Labor cost Parts cost Cost per product
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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.
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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 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: [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) 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]
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