[Federal Register Volume 75, Number 246 (Thursday, December 23, 2010)]
[Proposed Rules]
[Pages 80742-80744]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-32207]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1202; Directorate Identifier 2010-NM-167-AD]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Corporation Model MD-
90-30 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 all
Model MD-90-30 airplanes. This proposed AD would require repetitive
inspections for cracking of the left and right upper center skin panels
of the horizontal stabilizer, and corrective action if necessary. This
proposed AD was prompted by a report of a crack found in the upper skin
panel at the aft inboard corner of a right horizontal stabilizer. We
are proposing this AD to detect and correct cracks in the horizontal
stabilizer upper center skin panel. Uncorrected cracks might ultimately
lead to the loss of overall structural integrity of the horizontal
stabilizer.
DATES: We must receive comments on this proposed AD by February 7,
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,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; telephone 206-544-5000, extension 2; fax 206-766-5683; 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: Roger Durbin, Aerospace Engineer, Los
Angeles ACO, Airframe Branch, ANM-120L, FAA Los Angeles Aircraft
Certification Office, 3960 Paramount Blvd, Lakewood, CA 90712-4137;
telephone: (562) 627-5233; fax: (562) 627-5210; 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-2010-1202;
Directorate Identifier 2010-NM-167-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 a report of a crack to a Model MD-80 airplane
upper center skin panel of the right horizontal stabilizer at the aft
inboard corner during an inspection for cracks in the upper and lower
aft skin panels of the horizontal stabilizer in accordance with AD
2007-10-04, Amendment 39-15045 (72 FR 25960, May 8, 2007). That
airplane had accumulated 47,146 total flight hours and 26,490 total
flight cycles when the crack was found. The cause of the cracking is
suspected to be fatigue. The Model MD-90-30 airplane horizontal
stabilizer is similar in design and loading to that of the Model MD-80
airplane horizontal stabilizer. Therefore, Model MD-90-30 airplanes may
also be subject to the identified unsafe condition.
A crack in the upper center skin panel may transfer the load to the
upper aft skin panel. This may result in the upper aft skin panel
cracking faster than the existing inspection intervals that are
required by AD 2009-13-08, Amendment 39-15947 (74 FR 30922, June 29,
2009). Uncorrected cracking could result in loss of the overall
structural integrity of the horizontal stabilizer.
Relevant Service Information
We reviewed Boeing Alert Service Bulletin MD90-55A015, dated July
16, 2010. This service bulletin describes procedures for repetitive
eddy current inspections, either (Option 1) two high frequency eddy
current (ETHF) scans and one low frequency eddy current (ETLF) scan, or
(Option 2) three ETHF scans, to detect cracking of the right and left
upper center skin panels of the horizontal stabilizer. Corrective
actions include replacing any cracked horizontal stabilizer upper
center skin panel with a serviceable panel or contacting Boeing for
possible temporary repair instructions.
The repetitive interval is 5,200 flight cycles or 2,500 flight
cycles depending on the eddy current inspection option selected.
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 design.
Proposed AD Requirements
This proposed AD would require accomplishing the actions specified
in the service information described previously, except as discussed
under ``Differences Between the Proposed AD and the Service
Information.''
Differences Between the Proposed AD and the Service Information
Boeing Alert Service Bulletin MD90-55A015, dated July 16, 2010,
provides an option to contact the manufacturer for instructions on how
to repair
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cracking, but this proposed AD would require replacing the cracked skin
panel.
Costs of Compliance
We estimate that this proposed AD will affect 19 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Inspection...................... 4 work-hours x $85 per $0 $340 per inspection $6,460 per
hour = $340 per cycle. inspection cycle
inspection cycle.
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We estimate the following costs to do any necessary repairs that would
be required based on the results of the proposed inspection. We have no
way of determining the number of aircraft that might need these
repairs.
On-Condition Costs
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Cost per
Action Labor cost Parts cost product
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Skin panel replacement....................... 648 work-hours x $85 per hour = $55,608 $110,688
$55,080.
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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
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):
McDonnell Douglas Corporation: Docket No. FAA-2010-1202; Directorate
Identifier 2010-NM-167-AD.
Comments Due Date
(a) We must receive comments by February 7, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all McDonnell Douglas Corporation Model
MD-90-30 airplanes, certificated in any category.
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 55: Stabilizers.
Unsafe Condition
(e) This AD was prompted by a report of a crack found in the
upper center skin panel at the aft inboard corner of a right
horizontal stabilizer. We are issuing this AD to detect and correct
cracks in the upper center skin panel of the horizontal stabilizer.
Uncorrected cracks might ultimately lead to the loss of overall
structural integrity of the horizontal stabilizer.
Compliance
(f) Comply with this AD within the compliance times specified,
unless already done.
Inspections
(g) Before the accumulation of 20,000 total flight cycles, or
within 3,778 flight cycles after the effective date of this AD,
whichever occurs later, do eddy current inspections to detect
cracking of the left and right upper center skin panels of the
horizontal stabilizer, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin MD90-55A015, dated
July 16, 2010.
(1) If no crack is found during any inspection required by
paragraph (g) of this AD, repeat the applicable inspections
thereafter at the applicable times specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin MD90-55A015, dated
July 16, 2010.
(2) If any crack is found during any inspection required by
paragraph (g) of this AD, before further flight, replace the skin
panel with a serviceable skin panel, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin MD90-
55A015, dated July 16, 2010. Within 20,000 flight cycles after the
replacement, do eddy current inspections as required by paragraph
(g) of this AD.
Alternative Methods of Compliance (AMOCs)
(h)(1) The Manager, Los Angeles 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. In accordance
with 14 CFR 39.19,
[[Page 80744]]
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.
(2) Before using any approved AMOC, notify your Principal
Maintenance Inspector or Principal Avionics Inspector, as
appropriate, or lacking a principal inspector, your local Flight
Standards 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 the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Los Angeles 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.
Related Information
(i) For more information about this AD, contact Roger Durbin,
Aerospace Engineer, Los Angeles ACO, Airframe Branch, ANM-120L, FAA
Los Angeles Aircraft Certification Office, 3960 Paramount Blvd,
Lakewood, CA 90712-4137; telephone: (562) 627-5233; fax: (562) 627-
5210; e-mail: [email protected].
(j) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; telephone 206-544-5000, extension 2; fax 206-766-5683; 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 December 16, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-32207 Filed 12-22-10; 8:45 am]
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