[Federal Register Volume 69, Number 171 (Friday, September 3, 2004)]
[Proposed Rules]
[Pages 53853-53855]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-20123]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-18994; Directorate Identifier 2003-NM-210-AD]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model DC-9-14 and DC-
9-15 Airplanes; and Model DC-9-20, DC-9-30, DC-9-40, and DC-9-50 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain McDonnell Douglas Model DC-9-14 and DC-9-15 airplanes; and
Model DC-9-20, DC-9-30, DC-9-40, and DC-9-50 series airplanes. This
proposed AD would require repetitive high frequency eddy current
inspections to detect cracks in the vertical radius of the upper cap of
the center wing rear spar, and repair if necessary. This proposed AD is
prompted by reports of cracks in the upper cap of the center wing rear
spar that resulted from stress corrosion. We are proposing this AD to
detect and correct cracking of the left or right upper cap of the
center rear spar, which could cause a possible fuel leak and structural
failure of the upper cap, and result in
[[Page 53854]]
reduced structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by October 18,
2004.
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.
By 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.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood
Boulevard, Long Beach, California 90846, Attention: Data and Service
Management, Dept. C1-L5A (D800-0024).
You can examine the contents of this AD docket on the Internet at
http://dms.dot.gov, or at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., room PL-401, on
the plaza level of the Nassif Building, Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Technical Information: Wahib Mina, Aerospace Engineer, Airframe
Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office, 3960
Paramount Boulevard, Lakewood, California 90712-4137; telephone (562)
627-5324; fax (562) 627-5210.
Plain Language Information: Marcia Walters, [email protected].
SUPPLEMENTARY INFORMATION:
Docket Management System (DMS)
The FAA has implemented new procedures for maintaining AD dockets
electronically. As of May 17, 2004, new AD actions are posted on DMS
and assigned a docket number. We track each action and assign a
corresponding directorate identifier. The DMS AD docket number is in
the form ``Docket No. FAA-2004-99999.'' The Transport Airplane
Directorate identifier is in the form ``Directorate Identifier 2004-NM-
999-AD.'' Each DMS AD docket also lists the directorate identifier
(``Old Docket Number'') as a cross-reference for searching purposes.
Comments Invited
We invite you to submit any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2004-18994;
Directorate Identifier 2003-NM-210-AD'' in the subject line 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 submitted 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 can review DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit http://dms.dot.gov.
We are reviewing the writing style we currently use in regulatory
documents. We are interested in your comments on whether the style of
this document is clear, and your suggestions to improve the clarity of
our communications that affect you. You can get more information about
plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.
Examining the Docket
You can 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 DMS receives them.
Discussion
We have received several reports of cracking of the upper cap of
the center wing rear spar at station Xcw=58.500 on certain McDonnell
Douglas Model DC-9 airplanes. These airplanes had accumulated 20,100 to
76,183 total flight hours, and 25,150 to 88,029 total flight cycles.
Investigation revealed that the cracks resulted from stress corrosion.
This cracking of the left or right upper cap of the center wing rear
spar, if not detected and corrected in a timely manner, could cause a
possible fuel leak and structural failure of the upper cap, and result
in reduced structural integrity of the airplane.
Relevant Service Information
We have reviewed McDonnell Douglas Service Bulletin DC9-57-223,
dated July 21, 2003. The service bulletin describes procedures for
doing repetitive high frequency eddy current inspections of the left
and right upper caps of the center wing rear spar at station
Xcw=58.500, and contacting Boeing for repair instructions if any crack
is found during the inspections. Accomplishing the actions specified in
the service bulletin is intended to adequately address the identified
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. Therefore, we are proposing this AD, which
would require high frequency eddy current inspections, and corrective
actions if necessary, in accordance with the FAA. The proposed AD would
require you to use the service information described previously to
perform these actions, except as discussed under ``Difference Between
the Proposed AD and the Service Bulletin.''
Difference Between the Proposed AD and the Service Bulletin
Although the service bulletin specifies that operators may contact
the manufacturer for disposition of repair conditions, this proposed AD
would require operators to repair those conditions per a method
approved by the FAA.
Costs of Compliance
This proposed AD would affect about 396 airplanes of U.S. registry
and 963 airplanes worldwide. The proposed inspection would take about 3
work hours per airplane, per inspection cycle, at an average labor rate
of $65 per work hour. Based on these figures, the estimated cost of the
proposed AD for U.S. operators is $77,220, or $195 per airplane, per
inspection cycle.
[[Page 53855]]
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. 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 FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
McDonnell Douglas: Docket No. FAA-2004-18994; Directorate Identifier
2003-NM-210-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this AD action by October 18, 2004.
Affected ADs
(b) None.
Applicability
(c) This AD applies to certain McDonnell Douglas Model DC-9-14,
DC-9-15, DC-9-21, DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-
33F, DC-9-34, DC-9-34F, DC-9-32F (C-9A, C-9B), DC-9-41, and DC-9-51
airplanes, certificated in any category; as listed in McDonnell
Douglas Service Bulletin DC9-57-223, dated July 21, 2003.
Unsafe Condition
(d) This AD was prompted by reports of cracks in the upper cap
of the center wing rear spar that resulted from stress corrosion. We
are issuing this AD to detect and correct cracking of the left or
right upper cap of the center rear spar, which could cause a
possible fuel leak and structural failure of the upper cap, and
result in reduced structural integrity 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.
Inspection
(f) At the later of the times specified in paragraph (f)(1) or
(f)(2) of this AD: Do a high frequency eddy current inspection to
detect cracks in the vertical radius of the upper cap of the center
wing rear spar, in accordance with the Accomplishment Instructions
of McDonnell Douglas Service Bulletin DC9-57-223, dated July 21,
2003.
(1) Before the accumulation of 25,000 total flight cycles.
(2) Within 15,000 flight cycles or 5 years after the effective
date of this AD, whichever occurs first.
Corrective Action
(g)(1) If no crack is found, then repeat the inspection
thereafter at intervals not to exceed 15,000 flight cycles or 5
years, whichever occurs first.
(2) If any crack is found, before further flight, repair per a
method approved by the Manager, Los Angeles Aircraft Certification
Office (ACO), FAA. For a repair method to be approved by the
Manager, Los Angeles ACO, as required by this paragraph, the
Manager's approval letter must specifically refer to this AD.
Alternative Methods of Compliance (AMOCs)
(h) The Manager, Los Angeles ACO, FAA, has the authority to
approve AMOCs for this AD, if requested in accordance with the
procedures found in 14 CFR 39.19.
Issued in Renton, Washington, on August 20, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-20123 Filed 9-2-04; 8:45 am]
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