[Federal Register: April 5, 2006 (Volume 71, Number 65)]
[Proposed Rules]
[Page 17033-17035]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr05ap06-24]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24271; Directorate Identifier 2006-NM-006-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 727 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 727 airplanes. This proposed AD would require
repetitive measurements of the freeplay of the left and right outboard
aileron balance tabs and of the upper and lower rudder tabs, and
related investigative/corrective actions if necessary. This proposed AD
also would require repetitive lubrication of the hinge bearings and rod
end bearings of the aileron balance tabs. This proposed AD results from
reports of freeplay-induced vibration of the outboard aileron balance
tab and rudder tab. We are proposing this AD to prevent excessive
vibration of the airframe during flight, which could result in
divergent flutter and loss of control of the airplane.
DATES: We must receive comments on this proposed AD by May 22, 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.
[[Page 17034]]
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: Dennis Stremick, Aerospace Engineer,
Airframe Branch, ANM-120S, Seattle Aircraft Certification Office, FAA,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6450; 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-
24271; Directorate Identifier 2006-NM-006-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://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://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 several reports of freeplay-induced vibration of
the outboard aileron balance tab and a couple of reports of freeplay-
induced vibration of the rudder tab on Boeing Model 727 airplanes.
Excessive corrosion and wear of components and/or interfaces allows
excessive freeplay movement of the control surfaces and can cause
excessive vibration of the airframe during flight. The point of
transition from vibration to divergent flutter is unknown. When
divergent flutter occurs, the amplitude of each cycle or oscillation is
larger than the last one and the surface can reach its structural
limits. This condition, if not corrected, could result in loss of
control of the airplane.
Relevant Service Information
We have reviewed Boeing Special Attention Service Bulletin 727-27-
0234, dated November 10, 2005. The service bulletin describes
procedures for repetitive measurements of the freeplay of the left and
right outboard aileron balance tabs and of the upper and lower rudder
tabs. If the freeplay exceeds certain specified limits, the service
bulletin describes procedures for doing applicable related
investigative and corrective actions. These related investigative and
corrective actions include doing a general visual inspection for wear
of the affected bearings, bolts, and bushings; and repairing or
replacing the affected part. The corrective actions also include
repeating the freeplay measurement and any related investigative and
corrective actions until the maximum freeplay is within acceptable
limits. For the repetitive measurements of the freeplay, the service
bulletin specifies an initial compliance time of 18 months and
repetitive intervals of 8,000 flight hours or 24 months, whichever
occurs first. The service bulletin also describes procedures for
repetitive lubrication of the hinge bearings and rod end bearings of
the aileron balance tabs. For the repetitive lubrications, the service
bulletin specifies an initial compliance time of 9 months and
repetitive intervals of 3,200 flight hours and 6,000 flight hours,
depending on if grease was used. Accomplishing the actions specified in
the service bulletin is intended to adequately address the unsafe
condition.
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.
Costs of Compliance
There are about 944 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.
Estimated Costs
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Number of U.S.-
Action Work hours Average labor Cost per registered Fleet cost
rate per hour airplane airplanes
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Freeplay measurement......... 8 $80 $640, per 539 $344,960, per
lubrication measurement
cycle. cycle.
Lubrication.................. 4 80 $320, per 539 $172,480, per
measurement lubrication
cycle. cycle.
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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
[[Page 17035]]
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-2006-24271; Directorate Identifier 2006-NM-
006-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by May 22,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 727, 727C, 727-100, 727-
100C, 727-200, and 727-200F series airplanes, certificated in any
category; as identified in Boeing Special Attention Service Bulletin
727-27-0234, dated November 10, 2005.
Unsafe Condition
(d) This AD results from reports of freeplay-induced vibration
of the outboard aileron balance tab and rudder tab. We are issuing
this AD to prevent excessive vibration of the airframe during
flight, which could result in divergent flutter and loss of control
of the airplane.
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.
Compliance Times
(f) Except as provided by paragraph (h) of this AD, at the
applicable times specified in paragraph 1.E., ``Compliance,'' of
Boeing Special Attention Service Bulletin 727-27-0234, dated
November 10, 2005, do the actions specified in paragraph (g) of this
AD. Where the service bulletin specifies a compliance time ``from
the initial release of this service bulletin,'' this AD requires
compliance within the applicable compliance time after the effective
date of this AD.
Freeplay Measurement, Related Investigative and Corrective Actions, and
Lubrication
(g) At the applicable times specified in paragraph (f) of this
AD, do the actions specified in paragraphs (g)(1) and (g)(2) of this
AD in accordance with the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 727-27-0234, dated November 10,
2005.
(1) Measure the freeplay of the left and right outboard aileron
balance tabs and of the upper and lower rudder tabs, and do
applicable related investigative and corrective actions if
necessary.
(2) Lubricate the hinge bearings and rod end bearings of the
aileron balance tabs.
Concurrent Repetitive Cycles
(h) If a freeplay measurement required by paragraph (g)(1) of
this AD and a lubrication cycle required by paragraph (g)(2) of this
AD are due at the same time or will be done during the same
maintenance visit, the freeplay measurement and applicable related
investigative and corrective actions must be done before the
lubrication.
Alternative Methods of Compliance (AMOCs)
(i)(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.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who has been authorized
by the Manager, Seattle ACO, to make those findings. For a repair
method to be approved, the repair must meet the certification basis
of the airplane, and the approval must specifically refer to this
AD.
Issued in Renton, Washington, on March 29, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-4924 Filed 4-4-06; 8:45 am]
BILLING CODE 4910-13-P