[Federal Register Volume 71, Number 20 (Tuesday, January 31, 2006)]
[Proposed Rules]
[Pages 5021-5023]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-1188]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23734; Directorate Identifier 2005-NM-174-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 757 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Boeing Model 757 airplanes. This proposed AD would require 
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, this proposed AD would require 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. This proposed AD also would 
require installing vortex generators (vortilons) on the leading edge of 
the outboard main flap on certain airplanes. This proposed AD results 
from several reports that flightcrews experienced unintended roll 
oscillations during final approach, just before landing. We are 
proposing this AD to prevent unintended roll oscillations near 
touchdown, which could result in loss of directional control of the 
airplane, and consequent airplane damage and/or injury to flightcrew 
and passengers.

DATES: We must receive comments on this proposed AD by March 17, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for the service information identified in this 
proposed AD.

FOR FURTHER INFORMATION CONTACT: John Neff, Aerospace Engineer, Flight 
Test Branch, ANM-160S, FAA, Seattle Aircraft Certification Office, 1601 
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-
6521; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``FAA-2006-
23734; Directorate Identifier 2005-NM-174-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://
http://dms.dot.gov">dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://
http://dms.dot.gov">dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    We have received eleven confirmed reports that flightcrews on 
Boeing Model 757 airplanes experienced unintended roll oscillations 
during final approach, just before landing. One event resulted in a 
nose gear collapse after a hard landing; another event resulted in a 
tail strike during a landing that was aborted because of the 
oscillations. Of the eleven events that have been confirmed, three 
occurred with Flight Test personnel aboard, during flight-testing 
activities.
    These roll oscillations occur when the pilot makes large, rapid 
movements of the control wheel, and the airplane does not respond as 
expected. Boeing has developed a damper for the control wheel that 
reduces the likelihood of these roll oscillations by providing 
resistive force to large, rapid control wheel movements that exceed a 
set value.
    We have also received flight test data indicating that one 
potential cause of these unintended roll oscillations occurs when 
airflow over the outboard trailing edge flap separates due to the 
movement of the spoilers resulting from large control wheel inputs. 
Abrupt control wheel inputs to counteract the resulting roll can lead 
to roll oscillations of increasing magnitude. Boeing has developed 
vortex generators (vortilons) that create vortices over the flap 
surface and help to mitigate a sudden and premature airflow separation 
when the flaps are set in landing configuration and the spoilers 
forward of the flaps are deployed.
    Unintended roll oscillations near touchdown, if not corrected, 
could result in loss of directional control of the airplane, and 
consequent airplane

[[Page 5022]]

damage and/or injury to flightcrew and passengers.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 757-27A0146, dated 
October 14, 2004 (for Model 757-200, -200PF, and -200CB series 
airplanes); and Boeing Alert Service Bulletin 757-27A0147, dated 
October 14, 2004 (for Model 757-300 series airplanes). These service 
bulletins describe procedures for 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. This installation 
involves adding a new damper, bracket, crank arm, and control rod. The 
new damper bracket is installed at four existing holes on the drum 
bracket assembly. The service bulletins also describe procedures for 
doing a functional test and adjustment of the new installation, 
including doing any necessary related investigative and corrective 
actions and repeating the test and adjustment until all discrepancies 
are corrected. These service bulletins also describe procedures for 
sending a report when the applicable service bulletin is complete for 
each airplane.
    We have also reviewed Boeing Alert Service Bulletin 757-57A0058, 
Revision 1, dated January 10, 2002 (for Model 757-200, -200PF and -
200CB series airplanes). This service bulletin describes procedures for 
installing vortex generators (vortilons) on the leading edge of the 
outboard main flap. The service bulletin specifies that the vortex 
generators should be installed on both the left and right flaps at the 
same time. Installation of vortex generators on only one flap of an 
airplane may adversely affect the airplane's flight characteristics.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of this same type design. For this reason, we are proposing this AD, 
which would require accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Differences Between the Proposed AD and the Service Bulletins.''

Differences Between the Proposed AD and the Service Bulletins

    Boeing Alert Service Bulletin 757-27A0146 and Boeing Alert Service 
Bulletin 757-27A0147 specify a compliance time of 36 months for 
installing a control wheel damper assembly. Boeing Alert Service 
Bulletin 757-57A0058, Revision 1, recommends installing the vortex 
generators at the next ``heavy maintenance check.'' This proposed AD 
would require doing all the actions within 24 months after the 
effective date of the proposed AD. In developing an appropriate 
compliance time for this proposed AD, we considered the manufacturer's 
recommendation, the degree of urgency associated with the subject 
unsafe condition, the probability of future occurrences, and the 
average utilization of the affected fleet. In light of all these 
factors we find that a 24-month compliance time represents an 
appropriate interval of time for affected airplanes to continue to 
operate without compromising safety.
    Although the Accomplishment Instructions of Boeing Alert Service 
Bulletin 757-27A0146 and Boeing Alert Service Bulletin 757-27A0147 
describe procedures for submitting a sheet recording accomplishment of 
the service bulletin, this proposed AD would not require that action.
    Although Boeing Alert Service Bulletin 757-27A0146 and Boeing Alert 
Service Bulletin 757-27A0147 specify that operators may contact the 
manufacturer if a just-installed (new) wheel damper does not function 
properly, this proposed AD would require operators to correct that 
condition according to a method approved by the FAA.
    These differences have been coordinated with Boeing.

Interim Action

    We consider this proposed AD interim action. The manufacturer is 
currently investigating an additional modification that may further 
reduce or eliminate the unsafe condition identified in this AD. Once 
this modification is developed, approved, and available, we may 
consider additional rulemaking.

Costs of Compliance

    There are about 1,036 airplanes of the affected design in the 
worldwide fleet and about 629 U.S.-registered airplanes. The following 
table provides the estimated costs for U.S. operators to comply with 
this proposed AD. Not all of the required actions must be done on all 
U.S.-registered airplanes.

                                                                                         Estimated Costs
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                                                                                                                                                   Number of
                                                               Average                                                                               U.S.-
               Action                       Work hours        labor rate                 Parts                         Cost per airplane           registered              Fleet cost
                                                               per hour                                                                            airplanes
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Install control wheel damper          9 to 11..............          $65  $7,650 to $10,550.................  $8,235 to $11,265.................          578  $4,759,830 to $6,511,170.
 assembly, and do functional test
 (Model 757-200, -200PF, and -200CB
 series airplanes).
Install control wheel damper          15...................           65  $10,550...........................  $11,525...........................           51  $587,775.
 assembly, and do functional test
 (Model 757-300 series airplanes).
Install vortex generators (Model 757- 10...................           65  $3,336............................  $3,986............................          527  $2,100,622.
 200, -200PF, and -200CB series
 airplanes).
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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.

[[Page 5023]]

    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); and
    3. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Boeing: Docket No. FAA-2006-23734; Directorate Identifier 2005-NM-
174-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by March 17, 
2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Model 757-200, -200PF, -200CB, and -300 
series airplanes, certificated in any category; as identified in the 
applicable service bulletin or bulletins in Table 1 of this AD.

                                       Table 1.--Boeing Service Bulletins
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    Boeing Alert Service Bulletin             Revision                   Date                     Model
----------------------------------------------------------------------------------------------------------------
757-27A0146..........................  Original..............  October 14, 2004........  757-200, -200PF, and -
                                                                                          200CB.
757-27A0147..........................  Original..............  October 14, 2004........  757-300 series
                                                                                          airplanes.
757-57A0058..........................  1.....................  January 10, 2002........  757-200, -200PF, and -
                                                                                          200CB.
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Unsafe Condition

    (d) This AD results from several reports that flightcrews 
experienced unintended roll oscillations during final approach, just 
before landing. We are issuing this AD to prevent unintended roll 
oscillations near touchdown, which could result in loss of 
directional control of the airplane, and consequent airplane damage 
and/or injury to flightcrew and passengers.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Installations

    (f) Within 24 months after the effective date of this AD, do the 
actions in paragraphs (f)(1) and (f)(2) of this AD, as applicable.
    (1) For all airplanes: Install a control wheel damper assembly 
at the first officer's drum bracket assembly and aileron quadrant 
beneath the flight deck floor in section 41; and do all applicable 
functional and operational tests and adjustments of the new 
installation, and all applicable related investigative/corrective 
actions before further flight after the installation. Do all actions 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 757-27A0146, dated October 14, 2004 (for Model 757-
200, -200PF, and -200CB series airplanes); and Boeing Alert Service 
Bulletin 757-27A0147, dated October 14, 2004 (for Model 757-300 
series airplanes).
    (2) For Model 757-200, -200PF, and -200CB series airplanes: 
Install vortex generators (vortilons) on the leading edge of the 
outboard main flap in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-57A0058, Revision 
1, dated January 10, 2002.

Parts Installation

    (g) As of the effective date of this AD, no person may install a 
damper bracket assembly part number (P/N) 251N1432-2, a bracket-
sensor P/N 251N1430-2, or a crank arm P/N 251N1431-2, on any 
airplane.

Actions Accomplished in Accordance With Previous Revision of Service 
Bulletin

    (h) Actions done before the effective date of this AD in 
accordance with Boeing Special Attention Service Bulletin 757-57-
0058, dated March 9, 2000, are acceptable for compliance with the 
actions in paragraph (f)(2) of this AD.

No Reporting Required

    (i) Although the Accomplishment Instructions of Boeing Alert 
Service Bulletin 757-27A0146 and Boeing Alert Service Bulletin 757-
27A0147 describe procedures for submitting a sheet recording 
accomplishment of the service bulletin, this AD does not require 
that action.

Alternative Methods of Compliance (AMOCs)

    (j)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

    Issued in Renton, Washington, on January 11, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-1188 Filed 1-30-06; 8:45 am]
BILLING CODE 4910-13-P