[Federal Register Volume 75, Number 209 (Friday, October 29, 2010)]
[Rules and Regulations]
[Pages 66653-66655]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-26555]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0645; Directorate Identifier 2009-NM-200-AD;
Amendment 39-16483; AD 2010-22-04]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Corporation Model MD-
90-30 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are superseding an existing airworthiness directive (AD)
for the products listed above. That AD currently requires a detailed
inspection for certain defects of the upper fasteners of the aft mount
support fittings of the left and right engines, and corrective actions
if necessary. This new AD requires repetitive replacement of the upper
row of fasteners of the support fittings of the engine aft mount with
new fasteners; and repetitive general visual inspections for defects of
the lower row fasteners (Row B) of the support fittings of the left and
right engine aft mounts, and replacement of all clearance fit fasteners
in the lower row if necessary. This AD was prompted by reports of
loose, cracked, or missing fasteners in the aft mount support fitting
of the left and right engines. We are issuing this AD to prevent loose,
cracked, or missing fasteners in the engine aft mount support fittings,
which could lead to separation of the support fittings from the pylon,
and could result in separation of the engine from the airplane.
DATES: This AD is effective December 3, 2010.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of December 3,
2010.
ADDRESSES: 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, 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 AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (phone: 800-647-5527) is Document Management Facility,
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Roger Durbin, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
telephone (562) 627-5233; fax (562) 627-5210; e-mail:
[email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede airworthiness
[[Page 66654]]
directive (AD) 2008-18-10, amendment 39-15667 (73 FR 52203, September
9, 2008). That AD applies to the specified products. The NPRM was
published in the Federal Register on July 1, 2010 (75 FR 38056). That
NPRM proposed to require repetitive replacement of the upper row of
fasteners (Row A) of the support fittings of the left and right engine
aft mount with new fasteners. That NPRM also proposed to require
repetitive general visual inspections for defects of the lower row
fasteners (Row B) of the support fittings of the left and right engine
aft mounts (that includes a gap check under the head or nut, and a
torque check), as necessary for defects of the lower row of fasteners
(Row B) of the support fittings of the left and right engine aft
mounts, and replacing all clearance fit fasteners in the lower row (Row
B) with new fasteners if any defect is found. Defects include missing,
loose, and damaged fasteners.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting the AD as proposed.
Costs of Compliance
We estimate that this AD affects 13 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Replacement..................... 14 work-hour x $85 $152 per $1,342 per $17,446 per
per hour = $1,190. replacement. replacement cycle. replacement
cycle.
Inspections..................... 4 work-hours x $85 $0................ $340 per $4,420 per
per hour = $340. inspection cycle. inspection 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
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will 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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under 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.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2008-18-10, Amendment 39-15667 (73 FR 52203, September 9, 2008), and
adding the following new AD:
2010-22-04 McDonnell Douglas Corporation: Amendment 39-16483; Docket
No. FAA-2010-0645; Directorate Identifier 2009-NM-200-AD.
Effective Date
(a) This airworthiness directive (AD) is effective December 3,
2010.
Affected ADs
(b) This AD supersedes AD 2008-18-10, Amendment 39-15667.
Applicability
(c) This AD applies to McDonnell Douglas Corporation Model MD-
90-30 airplanes, certificated in any category, as identified in
Boeing Alert Service Bulletin MD90-54A003, Revision 2, dated
February 12, 2010.
Subject
(d) Air Transport Association (ATA) of America Code 54:
Nacelles/Pylons.
Unsafe Condition
(e) This AD results from reports of loose, cracked, or missing
fasteners in the aft mount support fitting of the left and right
engines. The Federal Aviation Administration is issuing this AD to
prevent loose, cracked, or missing fasteners in the engine aft
support mount fittings, which could lead to separation of the
support fittings from the pylon, and could result in separation of
the engine from 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.
Replacement and Inspection
(g) Except as required by paragraph (i) of this AD, at the
applicable time specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin MD90-54A003, Revision 2, dated
February 12, 2010: Replace the upper row of fasteners (Row A) of the
support fittings of the left and right engine aft mounts with new
fasteners, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin MD90-54A003, Revision 2, dated
February 12, 2010. Repeat the replacement thereafter at intervals
not to exceed 10,000 flight cycles.
(h) Concurrently with any replacement required by paragraph (g)
of this AD: Perform a general visual inspection for defects of the
lower row fasteners (Row B) of the support fittings of the left and
right engine aft
[[Page 66655]]
mounts, in accordance with the Accomplishment Instructions of Boeing
Alert Service Bulletin MD90-54A003, Revision 2, dated February 12,
2010. Defects include missing, loose, and damaged fasteners.
(1) If no defect is found during any general visual inspection
required by paragraph (h) of this AD, before further flight, insert
a 0.0015-inch feeler gauge between the washer and the structure, or
between the fastener head and structure, as applicable, to detect a
gap condition, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin MD90-54A003, Revision 2, dated
February 12, 2010. A gap condition is a defect identified in any
location where the feeler gauge can slip completely between a washer
or a fastener head and the structure.
(i) If no defect is found during any gap check required by
paragraph (h)(1) of this AD, before further flight, apply torque to
the fasteners of the lower row (Row B) to determine if there is a
defect, in accordance with the Accomplishment Instructions of Boeing
Alert Service Bulletin MD90-54A003, Revision 2, dated February 12,
2010. A defect is any fastener that turns with the application of
the specified torque. If any defect is found, before further flight,
replace all clearance fit fasteners in the lower row (Row B), in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin MD90-54A003, Revision 2, dated February 12, 2010.
(ii) If any defect is found during any gap check required by
paragraph (h)(1) of this AD, before further flight, replace all
clearance fit fasteners in the lower row (Row B), in accordance with
the Accomplishment Instructions of Boeing Alert Service Bulletin
MD90-54A003, Revision 2, dated February 12, 2010.
(2) If any defect is found during any general visual inspection
required by paragraph (h) of this AD, before further flight, replace
all clearance fit fasteners in the lower row (Row B), in accordance
with the Accomplishment Instructions of Boeing Alert Service
Bulletin MD90-54A003, Revision 2, dated February 12, 2010.
Exception to Service Bulletin Compliance Times
(i) Where Boeing Alert Service Bulletin MD90-54A003, Revision 2,
dated February 12, 2010, specifies a compliance time after the
original issue date on the service bulletin, this AD requires
compliance within the specified compliance time after the effective
date of this AD.
Credit for Actions Accomplished in Accordance With Previous Service
Information
(j) Replacements and inspections accomplished before the
effective date of this AD in accordance with Boeing Alert Service
Bulletin MD90-54A003, Revision 1, dated November 17, 2009, are
considered acceptable for compliance with the corresponding actions
required by this AD.
Alternative Methods of Compliance (AMOCs)
(k)(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, 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 14 CFR 25.571,
Amendment 45, and the approval must specifically refer to this AD.
Related Information
(l) For more information about this AD, contact Roger Durbin,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO,
3960 Paramount Boulevard, Lakewood, California 90712-4137; telephone
(562) 627-5233; fax (562) 627-5210; e-mail: [email protected].
Material Incorporated by Reference
(m) You must use Boeing Alert Service Bulletin MD90-54A003,
Revision 2, dated February 12, 2010, to do the actions required by
this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) 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.
(3) You may review copies of the service information at the FAA,
1601 Lind Avenue, SW., Renton, Washington. For information on the
availability of this material at the FAA, call 425-227-1221.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at an NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on October 13, 2010.
John Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-26555 Filed 10-28-10; 8:45 am]
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