[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
----------------------------------------------------------------------------------------------------------------
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

[[Page 30045]]

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