[Federal Register Volume 75, Number 79 (Monday, April 26, 2010)]
[Proposed Rules]
[Pages 21528-21530]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-9572]
[[Page 21528]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0433; Directorate Identifier 2009-NM-117-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
certain Model MD-90-30 airplanes. This proposed AD would require
inspecting for corrosion of the retract cylinder support fitting for
the main landing gear (MLG) and the mating bore for the support fitting
in the MLG trunnion fitting and performing corrective actions if
necessary, and replacing cadmium-plated retract cylinder support
bushings and bearings. This proposed AD results from reports of the
retract cylinder support fitting for the MLG failing during gear
extension and subsequently damaging the hydraulic system. We are
proposing this AD to prevent corrosion and damage that could compromise
the integrity of the retract cylinder support fitting for the MLG,
which could adversely affect the airplane's safe landing.
DATES: We must receive comments on this proposed AD by June 10, 2010.
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,
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 (telephone 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,
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.
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-2010-0433;
Directorate Identifier 2009-NM-117-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 reports of failure of the retract cylinder support
fitting for the main landing gear (MLG) during gear extension, damaging
the hydraulic system on McDonnell Douglas Corporation MD-80 series
airplanes. This condition, if not corrected, could result in corrosion
and damage that could compromise the integrity of the retract cylinder
support fitting for the MLG, which could subsequently damage the
hydraulic system and adversely affect the airplane's ability to make a
safe landing.
The retract cylinder support fittings for the MLG on McDonnell
Douglas Model MD-80 series airplanes have the same design as those
installed on Model MD-90-30 airplanes. Therefore, Model MD-90-30
airplanes may be subject to the identified unsafe condition.
Relevant Service Information
We have reviewed Boeing Service Bulletin MD90-57-016, Revision 2,
dated April 28, 2006. The service bulletin describes procedures for
doing a general visual inspection of the cylinder bore in the MLG
support for corrosion, and performing corrective actions if necessary.
Corrective actions include the following:
For airplanes on which a cadmium-plated fitting is
installed with or without corrosion present: Replacing the cadmium-
plated retract cylinder support fitting for the MLG with an electroless
nickel-plated fitting, and replacing the cadmium-plated retract
cylinder support bushings and bearings for the MLG with bushings and
bearings having no cadmium plating in the bore.
For airplanes on which an electroless nickel-plated
fitting is installed with no corrosion present: Installing the retained
electroless nickel-plated retract cylinder support fitting for the MLG,
and replacing the cadmium-plated retract cylinder support bushings and
bearings for the MLG with bushings and bearings having no cadmium
plating in the bore.
For airplanes on which the electroless nickel plated
fitting is installed with corrosion present: Replacing the electroless
nickel-plated retract cylinder support fitting for the MLG, and
replacing the cadmium-plated retract cylinder support bushings and
bearings for the MLG with bushings and bearings having no cadmium
plating in the bore.
For airplanes on which an electroless nickel-plated fitting is
installed in accordance with a previous issue of the service bulletin,
no further work is required if the following actions have been
accomplished.
An inspection for corrosion and damage of the cylinder
bore in the MLG support has been performed.
The cadmium-plated retract cylinder support fitting for
the MLG has been replaced with an electroless nickel-plated fitting.
An electroless nickel-plated retract cylinder support
fitting for the MLG is already installed and has no corrosion.
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The cadmium-plated retract cylinder support bushings and
bearings for the MLG have been replaced with bushings and bearings with
no cadmium plating in the bore.
For airplanes on which the cadmium-plated fitting is installed, and
on which the cadmium-plated retract cylinder support fitting for the
MLG was reinstalled and on which a previous issue of the service
bulletin was performed, the service bulletin specifies:
Removing the cadmium-plated retract cylinder support
fitting for the MLG and replacing with an electroless nickel-plated
fitting.
Verifying that the cadmium-plated retract cylinder support
bushings and bearings for the MLG have been replaced with bushings and
bearings with no cadmium plating in the bore.
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 these same type
designs. This proposed AD would require accomplishing the actions
specified in the service information described previously.
Costs of Compliance
We estimate that this proposed AD would affect 16 airplanes of U.S.
registry. The following table provides the estimated costs for U.S.
operators to comply with this proposed AD.
Table--Estimated Costs
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Number of U.S.-
Action Work hours Average labor Parts Cost per registered Fleet cost
rate per hour product airplanes
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Inspection.............................................. 1 $85 $0 $85 16 $1,360
Replacement............................................. 8 85 24,580 25,260 16 404,160
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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), 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:
McDonnell Douglas Corporation: Docket No. FAA-2010-0433; Directorate
Identifier 2009-NM-117-AD.
Comments Due Date
(a) We must receive comments by June 10, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to McDonnell Douglas Corporation Model MD-
90-30 airplanes, certificated in any category, as identified in
Boeing Service Bulletin MD90-57-016, Revision 2, dated April 28,
2006.
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Unsafe Condition
(e) This AD results from reports of the retract cylinder support
fitting for the main landing gear (MLG) failing during gear
extension, and subsequently damaging the hydraulic system. The
Federal Aviation Administration is issuing this AD to prevent
corrosion and damage that could compromise the integrity of the
retract cylinder support fitting for the MLG, which could adversely
affect the airplane's safe landing.
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 and Corrective Actions
(g) Before the accumulation of 30,000 total flight hours, or
within 15,000 flight hours after the effective date of this AD,
whichever occurs later, do a general visual inspection of the
retract cylinder support fitting for the MLG and the mating bore in
the MLG trunion fitting for corrosion, install bushings and bearings
without cadmium plating in the bore, and do all applicable
corrective actions, in accordance with Configuration 1 of the
Accomplishment Instructions of Boeing Service Bulletin MD90-57-016,
Revision 2, dated April 28, 2006. Do all applicable corrective
actions before further flight.
Note 1: For the purposes of this AD, a general visual inspection
is: ``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
ensure visual access to all surfaces in the inspection area. This
level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or
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droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''
(h) Doing a general visual inspection, installing bushings and
bearings, and doing all applicable corrective actions is also
acceptable for compliance with the requirements of paragraph (g) of
this AD if done before the effective date of this AD in accordance
with the Accomplishment Instructions of Boeing Service Bulletin
MD90-57-016, Revision 1, dated October 26, 2005.
(i) Doing a general visual inspection, installing bushings and
bearings, and doing all applicable corrective actions is also
acceptable for compliance with the requirements of paragraph (g) of
this AD if done before the effective date of this AD in accordance
with the Accomplishment Instructions of Boeing Service Bulletin
MD90-57-016, dated September 18, 2002, provided that before the
accumulation of 30,000 total flight hours, or within 15,000 flight
hours after the effective date of this AD, whichever occurs later,
electroless nickel fittings are installed, and bushings and bearings
without cadmium plating in the bore are installed in accordance with
the Accomplishment Instructions of any of the service bulletins
listed in Table 1 of this AD.
Table 1--Acceptable Service Information
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Document Revision Date
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Boeing Service Bulletin MD90-57-016........... 0 September 18, 2002.
Boeing Service Bulletin MD90-57-016........... 1 October 26, 2005.
Boeing Service Bulletin MD90-57-016........... 2 April 28, 2006.
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Alternative Methods of Compliance (AMOCs)
(j)(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. Send
information to ATTN: 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.
(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 Boeing
Commercial Airplanes Organization Designation Authorization (ODA)
who 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.
Issued in Renton, Washington, on April 16, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-9572 Filed 4-23-10; 8:45 am]
BILLING CODE 4910-13-P