[Federal Register Volume 77, Number 117 (Monday, June 18, 2012)]
[Proposed Rules]
[Pages 36222-36224]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-14806]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0637; Directorate Identifier 2012-NM-006-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company 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 The Boeing Company Model 737-600, -700, -700C, -800, -900, and
-900ER series airplanes. This proposed AD was prompted by a report of
an inboard main landing gear (MLG) door assembly departure due to
premature fatigue cracking in the inboard MLG door hinge fittings. This
proposed AD would require repetitive inspections for cracking of the
inboard MLG door hinge fittings; and modification of cracked fittings,
which would terminate the repetitive inspections. We are proposing this
AD to detect and correct fatigue cracking in the inboard MLG door hinge
fittings which could result in loss of the MLG door assembly from the
airplane; loss of the MLG door assembly could impact the flight control
surfaces and result in reduced controllability of the airplane.
DATES: We must receive comments on this proposed AD by August 2, 2012.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, 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,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; 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: Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917-
6440; fax: 425-917-6590; email: nancy.marsh@faa.gov.
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-2012-0637;
Directorate Identifier 2012-NM-006-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 received a report of an inboard MLG door assembly departure due
to premature fatigue cracking in the inboard MLG door hinge fittings.
Fatigue cracking in the inboard MLG door hinge fittings could result in
loss of the MLG door assembly from the airplane; such loss could impact
the flight control surfaces and result in reduced controllability of
the airplane.
[[Page 36223]]
Relevant Service Information
We reviewed Boeing Alert Service Bulletin 737-52A1167, dated
December 1, 2011. The service information describes procedures for
doing repetitive detailed or surface high frequency eddy current (HFEC)
inspections for cracking of the inboard MLG door hinge fittings; and
modification of fittings, which would eliminate the need for the
repetitive inspections. The modification consists of replacing the
hinge fitting assembly. The initial compliance time is before 10,000
total flight cycles, within 10,000 flight cycles since replacement, or
within 600 flight cycles after the effective date of this AD, whichever
occurs latest. The repetitive interval is 600 flight cycles or 5,500
flight cycles depending on inspection type.
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.
Costs of Compliance
We estimate that this proposed AD affects 1,175 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................ 3 work-hours x $85 $0 $255 per inspection $299,625 per
per hour = $255 per cycle. inspection cycle.
inspection cycle.
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We estimate the following costs to do any necessary replacements
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 replacements:
On-Condition Costs
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Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Optional Terminating Modification........... 9 work-hours x $85 per hour = $6,550 $7,315
$765.
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According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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):
The Boeing Company: Docket No. FAA-2012-0637; Directorate Identifier
2012-NM-006-AD.
(a) Comments Due Date
We must receive comments by August 2, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 737-600, -700, -
700C, -800, -900, and -900ER series airplanes; certificated in any
category; as identified in Boeing Alert Service Bulletin 737-
52A1167, dated December 1, 2011.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 52, Doors.
[[Page 36224]]
(e) Unsafe Condition
This AD was prompted by a report of an inboard main landing gear
(MLG) door assembly departure due to premature fatigue cracking in
the inboard MLG door hinge fittings. We are issuing this AD to
detect and correct fatigue cracking in the inboard MLG door hinge
fittings, which could result in loss of the MLG door assembly from
the airplane; loss of the MLG door assembly could impact the flight
control surfaces and result in reduced controllability of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Initial and Repetitive Inspections
Except as provided by paragraph (h) of this AD, at the
applicable time in paragraph 1.E. of Boeing Alert Service Bulletin
737-52A1167, dated December 1, 2011, do either a detailed or surface
high frequency eddy current (HFEC) inspection for cracking of the
left- and right-side inboard MLG door hinge fittings, in accordance
with the Accomplishment Instructions of Boeing Alert Service
Bulletin 737-52A1167, dated December 1, 2011. If any cracking is
found, before further flight, modify the inboard MLG door hinge
fittings on both left- and right-side inboard MLG doors, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-52A1167, dated December 1, 2011. Repeat either
inspection at the applicable time in paragraph 1.E. of Boeing Alert
Service Bulletin 737-52A1167, dated December 1, 2011. Doing the
modification terminates the inspection requirements of this AD.
(h) Exception
Where Boeing Alert Service Bulletin 737-52A1167, dated December
1, 2011, specifies a compliance time ``after the original issue date
of this service bulletin,'' this AD requires compliance within the
specified compliance time after the effective date of this AD.
(i) Alternative Methods of Compliance (AMOCs)
(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. 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. Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
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, 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.
(i) Related Information
(1) For more information about this AD, contact Nancy Marsh,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, Washington
98057-3356; phone: 425-917-6440; fax: 425-917-6590; email:
nancy.marsh@faa.gov.
(2) For service information identified in this 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; 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.
Issued in Renton, Washington, on June 8, 2012.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-14806 Filed 6-15-12; 8:45 am]
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