[Federal Register Volume 76, Number 100 (Tuesday, May 24, 2011)]
[Proposed Rules]
[Pages 30043-30045]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-12728]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0475; Directorate Identifier 2010-NM-199-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 757 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 the
products listed above. For certain airplanes, this proposed AD would
require the installation of new relays adjacent to two of the spoiler
control modules that would prevent the deployment of certain spoiler
pairs when landing flaps are selected. For certain other airplanes,
this proposed AD would require torquing the bracket assembly
installation nuts and ground stud nuts, and doing bond resistance tests
between the bracket assemblies and the terminal lugs on the ground
studs. This proposed AD is prompted by numerous reports of unintended
lateral oscillations during the final approach, just before landing. We
are proposing this AD to reduce the chance of unintended lateral
oscillations near touchdown, which could result in loss of lateral
control of the airplane, and consequent airplane damage or injury to
flight crew and passengers.
DATES: We must receive comments on this proposed AD by July 8, 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; phone: 206-
544-5000, extension 1; fax: 206-766-5680; e-mail: [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: Marie Hogestad, Aerospace Engineer,
Flight Controls, ANM-130S, Seattle Aircraft Certification Office (ACO),
FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; phone: 425-
917-6418; fax: 425-917-6590; e-mail: [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-2011-0475;
Directorate Identifier 2010-NM-199-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 have received numerous reports of Boeing 757 events where the
flight crews experienced unintended lateral oscillations during the
final approach, just before landing. One event resulted in a nose gear
collapse after a hard landing and another event resulted in a tail
strike during a landing that was aborted because of the oscillations.
The oscillations are characterized by large
[[Page 30044]]
wheel inputs at high rates that are out of phase with the airplane
response and typically occur under certain gusty and turbulent wind
conditions during landing. Unintended lateral oscillations near
touchdown could result in loss of lateral control of the airplane, and
consequent airplane damage or injury to flight crew and passengers.
Related Rulemaking
On October 31, 2006, we issued AD 2006-23-15, Amendment 39-14827
(71 FR 66657, November 16, 2006). That AD applies to the Boeing Model
757 airplanes affected by this NPRM. That AD requires installing a
control wheel damper assembly at the first officer's drum bracket
assembly and aileron quadrant beneath the flight deck floor in section
41, doing a functional test and adjustment of the new installation, and
doing related investigative/corrective actions if necessary. For
certain airplanes, that AD also requires doing an additional adjustment
test of the re-located control wheel position sensor, and an
operational test of the flight data recorder and the digital flight
data acquisition unit. AD 2006-23-15 also requires installing vortex
generators on the leading edge of the outboard main flap on certain
airplanes. The addition of a wheel damper prevents large abrupt pilot
lateral control wheel inputs and the addition of vortex generators
creates vortices over the flap surface to help mitigate a sudden and
premature airflow separation when spoilers are deployed in response to
large control wheel movements. We issued that AD as interim action to
reduce unintended roll oscillations near touchdown, which could result
in loss of lateral control of the airplane, and consequent airplane
damage or injury to the flight crew and passengers.
The preamble to AD 2006-23-15 specifies that we consider the
requirements ``interim action'' and that the manufacturer is
investigating an additional modification that might further reduce or
eliminate the unsafe condition. AD 2006-23-15 explains that we might
consider further rulemaking if a modification is developed, approved,
and available. The manufacturer now has developed such a modification
that will further reduce the effects of the unsafe condition, and we
have determined that further rulemaking is indeed necessary; this
proposed AD follows from that determination. However, the requirements
of AD 2006-23-15 will continue in effect.
Relevant Service Information
We reviewed Boeing Alert Service Bulletin 757-27A0152, Revision 1,
dated June 30, 2010. This service information identifies two
configurations. Configuration 1 includes airplanes that have not
accomplished Boeing Alert Service Bulletin 757-27A0152, dated April 29,
2009; and Configuration 2 identifies airplanes on which Boeing Alert
Service Bulletin 757-27A0152, dated April 29, 2009, has been
accomplished, but need additional work. For Configuration 1 airplanes,
this service information describes procedures for changing the E3-1
electronics shelf by installing 3 new bracket assemblies and 3 new
relays, changing wire bundle W1265, and changing wire bundle W4471
between the E3-1 electronics shelf and the E5-1 electronics shelf.
Additionally, this service information specifies doing an operational
test of the spoiler/speedbrake control system. These changes will
reduce the lateral control capability by disabling spoiler pairs 1 and
12, and 5 and 8, from responding to control wheel commands when the
flaps are deployed in landing configuration (25 and 30 degrees). The
speedbrake operation will be unaffected in-air and during on-ground
operations. To maintain desired lateral controllability, spoiler pair 1
and 12 will be re-engaged if the right hydraulic system fails.
For Configuration 2 airplanes, this service information describes
procedures for torquing the bracket assembly installation nuts and
ground stud nuts, and doing bond resistance tests between the bracket
assemblies and the terminal lugs on the ground studs.
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 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 will affect 686 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Installation Group 1, Configuration 1 35 work-hours x $85 per $4,691 $7,666 $421,630
(55 airplanes). hour = $2,975.
Installation Group 2, Configuration 1 32 work-hours x $85 per 4,610 7,330 4,339,360
(592 airplanes). hour = $2,720.
Installation Group 3, Configuration 1 32 work-hours x $85 per 4,619 7,339 88,068
(12 airplanes). hour = $2,720.
Installation Group 4, Configuration 1 32 work-hours x $85 per 4,610 7,330 183,250
(25 airplanes). hour = $2,720.
Installation Group 5, Configuration 1 35 work-hours x $85 per 4,701 7,676 15,352
(2 airplanes). hour = $2,975.
Torque Bracket Assembly and Bond 12 work-hours x $85 per 0 1,020 699,720
Tests, Groups 1-5 Configuration 2. hour = $1,020.
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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
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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-2011-0475; Directorate Identifier
2010-NM-199-AD.
Comments Due Date
(a) We must receive comments by July 8, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to The Boeing Company Model 757-200, -200PF,
-200CB, and -300 series airplanes, certificated in any category, as
identified in Boeing Alert Service Bulletin 757-27A0152, Revision 1,
dated June 30, 2010.
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 27: Flight Control System.
Unsafe Condition
(e) This AD was prompted by numerous reports of unintended
lateral oscillations during the final approach, just before landing.
We are issuing this AD to reduce the chance of unintended lateral
oscillations near touchdown, which could result in loss of lateral
control of the airplane, and consequent airplane damage or injury to
flight crew and passengers.
Compliance
(f) Comply with this AD within the compliance times specified,
unless already done.
Installation
(g) Within 60 months after the effective date of this AD, do the
applicable actions specified in paragraphs (g)(1) and (g)(2) of this
AD.
(1) For Configuration 1 airplanes as defined in Boeing Alert
Service Bulletin 757-27A0152, Revision 1, dated June 30, 2010,
install three bracket assemblies, three new relays, and make changes
to the wire bundles, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 757-27A0152, Revision
1, dated June 30, 2010.
(2) For Configuration 2 airplanes as defined in Boeing Alert
Service Bulletin 757-27A0152, Revision 1, dated June 30, 2010,
torque the bracket assembly nuts and ground stud nuts, and do bond
resistance tests to verify bonding requirements are met, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 757-27A0152, Revision 1, dated June 30, 2010.
Alternative Methods of Compliance (AMOCs)
(h)(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 e-mailed 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
(i) For more information about this AD, contact Marie Hogestad,
Aerospace Engineer, Flight Controls, ANM-130S, Seattle Aircraft
Certification Office (ACO), FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; phone: 425-917-6418; fax: 425-917-6590; e-
mail: [email protected].
(j) 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; phone:
206-544-5000, extension 1; fax: 206-766-5680; e-mail:
[email protected]; Internet: https://www.myboeingfleet.com. You
may review copies of the referenced service information at the FAA,
Transport Airplane Directorate, the FAA, 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 May 16, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-12728 Filed 5-23-11; 8:45 am]
BILLING CODE 4910-13-P