[Federal Register Volume 76, Number 214 (Friday, November 4, 2011)]
[Proposed Rules]
[Pages 68366-68368]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-28568]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 76, No. 214 / Friday, November 4, 2011 /
Proposed Rules
[[Page 68366]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-1165; Directorate Identifier 2011-NM-002-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 777-200 and -
300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain The Boeing Company Model 777-200 and -300 series airplanes.
This proposed AD would require replacing certain single-tabbed bonding
brackets in the airplane empennage with two-tabbed bonding brackets.
This proposed AD would also require, for certain airplanes, installing
new bonding jumpers, and measuring the resistance of the modified
installation to verify resistance is within specified limits. This
proposed AD was prompted by reports of two failures of the single-
tabbed bracket on the rudder. We are proposing this AD to prevent
failure of the bonding jumper bracket, which could result in loss of
lightning protection ground path, which could lead to increased
lightning-induced currents and subsequent damage to composite
structures, hydraulic tubes, and actuator control electronics. In the
event of a lightning strike, loss of lightning ground protection could
result in the loss of control of the airplane.
DATES: We must receive comments on this proposed AD by December 19,
2011.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: 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, Washington 98124-2207; telephone
(206) 544-5000, extension 1; fax (206) 766-5680; email
[email protected]; Internet https://www.myboeingfleet.com. You may
review copies of the referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the availability of this material at the
FAA, call (425) 227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (phone: (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Georgios Roussos, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, Seattle Aircraft Certification
Office (ACO), FAA, 1601 Lind Avenue SW., Renton, Washington 98057-3356;
telephone (425) 917-6482; 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 proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2011-1165;
Directorate Identifier 2011-NM-002-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
We received reports of two failures of the single-tabbed bracket on
the rudder. The bracket was discolored and melted, the tab was
completely severed and burned, and the bonding jumpers were detached
from the bracket. We also received a report of a similar failure of the
ground clip that connects to the other end of the jumpers to the
vertical stabilizer. Boeing has determined that the root cause of these
failures was a combination of electromagnetic forces on the jumpers and
resistive heating of the bracket and ground clip during lightning
strikes. This condition, if not corrected, could result in loss of
lightning protection ground path, which could lead to increased
lightning-induced currents and could subsequently damage composite
structures, hydraulic tubes, and actuator control electronics. In the
event of a lightning strike, loss of lightning ground protection could
result in loss of control of the airplane.
Relevant Service Information
We reviewed Boeing Service Bulletin 777-55A0014, Revision 1, dated
April 1, 2010. This service bulletin describes procedures for replacing
certain single-tabbed bonding brackets in the airplane empennage with
two-tabbed bonding brackets.
Boeing Service Bulletin 777-55A0014, Revision 1, dated April 1,
2010, specifies prior or concurrent accomplishment of Boeing Service
Bulletin 777-55A0010, Revision 1, dated April 17, 2001, for installing
new bonding jumpers, and measuring the resistance of the modified
installation to verify resistance is within specified limits.
[[Page 68367]]
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 these same type
designs.
Proposed AD Requirements
This proposed AD would require accomplishing the actions specified
in the service information described previously.
Costs of Compliance
We estimate that this proposed AD affects 87 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
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Parts Cost per Cost on U.S.
Action Labor cost cost product operators
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Replacement................................ 21 work-hours x $85 per hour $1,235 $3,020 $262,740
= $1,785.
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Estimated Costs for Concurrent Actions
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Parts Cost per Cost on U.S.
Action Labor cost cost product operators
----------------------------------------------------------------------------------------------------------------
Replacement................................ 66 work-hours x $85 per hour $2,668 $8,278 $248,340
= $5,610.
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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 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 this 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:
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 adding the following new
airworthiness directive (AD):
The Boeing Company: Docket No. FAA-2011-1165; Directorate Identifier
2011-NM-002-AD.
Comments Due Date
(a) We must receive comments by December 19, 2011.
Affected ADs
(b) None.
Applicability
(c) The Boeing Company Model 777-200 and -300 series airplanes,
certificated in any category, as identified in Boeing Service
Bulletin 777-55A0014, Revision 1, dated April 1, 2010.
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 55: Stabilizers.
Unsafe Condition
(e) This AD was prompted by reports of two failures of the
single-tabbed bonding bracket on the rudder. We are issuing this AD
to prevent failure of the bonding jumper bracket, which could result
in loss of lightning protection ground path, which could lead to
increased lightning-induced currents and subsequent damage to
composite structures, hydraulic tubes, and actuator control
electronics. In the event of a lightning strike, loss of lightning
ground protection could result in loss of control of the airplane.
Compliance
(f) Comply with this AD within the compliance times specified,
unless already done.
Replacement
(g) Within 48 months after the effective date of this AD,
replace certain single-tabbed bonding brackets in the airplane
empennage with two-tabbed bonding brackets, in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 777-55A0014,
Revision 1, dated April 1, 2010.
Concurrent Requirements
(h) For airplanes identified in Boeing Service Bulletin 777-
55A0010, Revision 1, dated April 17, 2001: Prior to or concurrently
with accomplishing the requirements of paragraph (g) of this AD,
install new bonding jumpers, and do resistance measurements of the
modified installation to verify resistance is within the limits
specified in the Accomplishment Instructions of Boeing Service
Bulletin 777-55A0010, Revision 1, dated April 17, 2001. Do the
actions in accordance with the Accomplishment Instructions of Boeing
Service Bulletin 777-55A0010, Revision 1, dated April 17, 2001.
[[Page 68368]]
Credit for Actions Accomplished in Accordance With Previous Service
Information
(i) Replacing certain single-tabbed bonding brackets with two-
tabbed bonding brackets in accordance with Boeing Alert Service
Bulletin 777-55A0014, dated May 8, 2008, before the effective date
of this AD, is acceptable for compliance with the corresponding
modification required by paragraph (g) of this AD.
(j) Installing new bonding jumpers, and doing resistance
measurements of the modified installation that verify the resistance
is within the specified limits, in accordance with Boeing Alert
Service Bulletin 777-55A0010, dated October 26, 2000, before the
effective date of this AD, is acceptable for compliance with the
corresponding modification required by paragraph (h) of this AD.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, Seattle Aircraft Certification Office, 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.
Related Information
(l) For more information about this AD, contact Georgios
Roussos, Aerospace Engineer, Systems and Equipment Branch, ANM-130S,
Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue
SW., Renton, Washington 98057-3356; telephone (425) 917-6482; fax
(425) 917-6590; email: [email protected].
(m) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone
(206) 544-5000, extension 1; fax (206) 766-5680; email
[email protected]; Internet https://www.myboeingfleet.com. You
may review copies of the referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the availability of this material at
the FAA, call (425) 227-1221.
Issued in Renton, Washington, on October 20, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-28568 Filed 11-3-11; 8:45 am]
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