[Federal Register Volume 75, Number 230 (Wednesday, December 1, 2010)]
[Proposed Rules]
[Pages 74668-74670]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-30138]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1156; Directorate Identifier 2010-NM-128-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 777-200, -
200LR, -300, and -300ER 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 Model 777-200, -200LR, -300, and -300ER series airplanes. This
proposed AD would require repetitive detailed inspections for
disbonding and tearing and measurements for wear of the internal
diameter (ID) of the Karon-lined bushings of the bulkhead support
jackscrew fitting and of the jackscrew fitting of the horizontal
stabilizer; repetitive installations of the horizontal stabilizer trim
actuator (HSTA); and if necessary, replacement of the bushings with new
bushings and all applicable related investigative and corrective
actions. This proposed AD results from a report indicating that a
Karon-lined bushing with the liner broken into five pieces was found
during a scheduled inspection of the HSTA components; the broken liner
had worn and disbonded from the bushing. We are proposing this AD to
detect and correct discrepancies of the HSTA attachment locations,
which could result in reduced structural integrity of the horizontal
stabilizer and consequent loss of controllability of the airplane.
DATES: We must receive comments on this proposed AD by January 18,
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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, 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; 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 (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Duong Tran, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6452; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-1156;
Directorate Identifier 2010-NM-128-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.
[[Page 74669]]
Discussion
We received a report indicating that a Karon-lined bushing with the
liner broken into five pieces was found during a scheduled inspection
of the horizontal stabilizer trim actuator (HSTA) components; the
broken liner had worn and disbonded from the bushing. The broken liner
was found on a 777-200 airplane that had accumulated 35,145 total
flight hours and 5,335 total flight cycles. Analysis by the
manufacturer revealed that the broken liner was one of 149 bushings on
which an early manufacturing process was used; that process has since
been improved. Further investigation and analysis by the manufacturer
shows that Karon-lined bushings in the HSTA and HSTA attachment
locations on the airplane structure using both the early and the
improved process are susceptible to wear in service. The analysis also
shows that the wear may cause excessive joint clearance which could
lead to fatigue cracking of the pins. This condition, if not corrected,
could result in reduced structural integrity of the horizontal
stabilizer and consequent loss of controllability of the airplane.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 777-55A0017, dated
May 20, 2010, which describes procedures for:
Repetitive detailed inspections for disbonding and tearing
and measurements for wear of the internal diameter (ID) of the Karon-
lined bushings of the bulkhead support jackscrew fitting; and
replacement of the bushings with new bushings if necessary: The
replacement includes related investigative and corrective actions, if
necessary. The related investigative actions include a surface high-
frequency eddy current inspection for cracking of the inner surface of
the hole, and measurement of the ID, of the intermediate sleeve. The
corrective action for cracking of the intermediate sleeve or
measurements outside the ID specified in the service bulletin is
replacement of the intermediate sleeve, including related investigative
and corrective actions if necessary. The related investigative actions
include a surface high-frequency eddy current inspection for cracking
of the inner surface of the hole, and measurement of the ID of the hole
of the bulkhead support jackscrew fitting. The corrective action for
cracking of the bulkhead support jackscrew fitting or measurements
outside the ID specified in the service bulletin is contacting Boeing.
Repetitive detailed inspections for disbonding and tearing
and measurements for wear of the internal diameter (ID) of the Karon-
lined bushings of the jackscrew fitting of the horizontal stabilizer;
and replacement of the bushings with new bushings if necessary.
Repetitively installing either a known serviceable or
overhauled HSTA.
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
This proposed AD would require accomplishing the actions specified in
the service information described previously, except as discussed under
``Difference Between the Proposed AD and Service Information.''
Difference Between the Proposed AD and Service Information
The service bulletin specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing those conditions in one of the following ways:
Using a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by an Authorized Representative
for the Boeing Commercial Airplanes Organization Designation
Authorization whom we have authorized to make those findings.
Costs of Compliance
We estimate that this proposed AD would affect 145 airplanes of
U.S. registry. We also estimate that it would take about 7 work-hours
per product to comply with the detailed inspection, measurement, and
installation in this proposed AD. The average labor rate is $85 per
work-hour. Based on these figures, we estimate the cost of this
proposed AD to the U.S. operators to be $86,275, or $595 per product.
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), 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.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
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 AD:
The Boeing Company: Docket No. FAA-2010-1156; Directorate Identifier
2010-NM-128-AD.
[[Page 74670]]
Comments Due Date
(a) We must receive comments by January 18, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to The Boeing Company Model 777-200, -200LR,
-300, and -300ER series airplanes, certificated in any category, as
identified in Boeing Alert Service Bulletin 777-55A0017, dated May
20, 2010.
Subject
(d) Air Transport Association (ATA) of America Code 55:
Stabilizers.
Unsafe Condition
(e) This AD results from a report indicating that a Karon-lined
bushing with the liner broken into five pieces was found during a
scheduled inspection of the horizontal stabilizer trim actuator
(HSTA) components; the broken liner had worn and disbonded from the
bushing. The Federal Aviation Administration is issuing this AD to
detect and correct discrepancies of the HSTA attachment locations,
which could result in reduced structural integrity of the horizontal
stabilizer and consequent loss of controllability of the airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Inspection/Related Investigative and Corrective Actions
(g) Before the accumulation of 32,000 total flight cycles, or
within 24 months after the effective date of this AD, whichever
occurs later: Do a detailed inspection for disbonding and tearing,
and a measurement for wear of the internal diameter (ID) of the
Karon-lined bushings of the bulkhead support jackscrew fitting and
of the jackscrew fitting of the horizontal stabilizer; replace
bushings with new bushings, as applicable; do all applicable related
investigative and corrective actions; and install either a known
serviceable or overhauled HSTA. Do the actions in accordance with
the Accomplishment Instructions of Boeing Alert Service Bulletin
777-55A0017, dated May 20, 2010, except as provided by paragraph (h)
of this AD. Do all applicable related investigative and corrective
actions before further flight. Repeat the actions required by this
paragraph thereafter at intervals not to exceed 16,000 flight
cycles.
Exceptions to Corrective Actions
(h) If, during any inspection or measurement required by this
AD, any damage is found, or the inner diameter is greater than the
allowable hole diameter, and Part 1, Step 3.B.2.a.(1)(a)1)a) of the
Accomplishment Instructions of Boeing Alert Service Bulletin 777-
55A0017, dated May 20, 2010, specifies to contact Boeing for
appropriate action: Before further flight, do the repair using a
method approved in accordance with the procedures specified in
paragraph (i) of this AD.
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
using the procedures found in 14 CFR 39.19. Send information to
ATTN: Duong Tran, Aerospace Engineer, Airframe Branch, ANM-120S,
FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6452; fax (425) 917-6590. Or information
may be e-mailed to: [email protected].
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
(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 the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that 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 November 15, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-30138 Filed 11-30-10; 8:45 am]
BILLING CODE 4910-13-P