[Federal Register Volume 78, Number 159 (Friday, August 16, 2013)]
[Rules and Regulations]
[Pages 49903-49906]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-18090]
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Rules and Regulations
Federal Register
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Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Rules
and Regulations
[[Page 49903]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0637; Directorate Identifier 2012-NM-006-AD;
Amendment 39-17532; AD 2013-15-16]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for certain
The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER
series airplanes. 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. This AD requires
repetitive inspections for cracking of the inboard MLG door hinge
fittings; and replacement or modification of cracked fittings. This AD
also provides an option to remove the affected MLG door. 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, and the MLG door assembly could impact the flight
control surfaces and result in reduced controllability of the airplane.
DATES: This AD is effective September 20, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of September 20,
2013.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 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, WA. 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: Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6440; fax:
425-917-6590; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
The NPRM published in the Federal Register on June 18, 2012 (77 FR
36222). The NPRM proposed to require repetitive inspections for
cracking of the inboard MLG door hinge fittings; and modification of
cracked fittings, which would terminate the repetitive inspections.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(77 FR 36222, June 18, 2012) and the FAA's response to each comment.
Request To Extend Compliance Time
American Airlines requested that we revise the NPRM (77 FR 36222,
June 18, 2012) to extend the compliance time for the initial
inspections from 10,000 total flight cycles to before 18,000 total
flight cycles. American Airlines stated that the FAA has not provided
sufficient evidence to warrant issuance of regulatory action with such
a reduced compliance time. American Airlines calculated that the event
described in the service information represents only 0.085 percent of
the airplanes under U.S. registry, and that the event described
occurred at 24,000 total flight cycles.
We disagree with the request to extend the compliance time. In
developing an appropriate compliance time for this action, we
considered the safety implications, parts availability, and normal
maintenance schedules for the timely accomplishment of the inspections
and modifications. There is additional data related to the MLG door
hinge failures that is not included in the manufacturer's service
bulletin. Up to 10 percent of hinges inspected to date have been found
with cracking. The cracking occurred between 11,000 and 24,000 total
flight cycles, and has been found on both hinges of the inboard MLG
door. In consideration of these items, we have determined that a
compliance time of before 10,000 total flight cycles will ensure an
acceptable level of safety and allow the inspections and modifications
to be done during scheduled maintenance intervals for most affected
operators. We have not changed the AD in this regard.
Request To Allow New Hinges Having Part Numbers (P/Ns) 113A8341-1 and
113A8341-2
American Airlines requested that we revise paragraph (g) of the
NPRM (77 FR 36222, June 18, 2012) to allow installation of new hinges
having P/Ns 113A8341-1 and 113A8341-2 as replacements for cracked
hinges found during the inspections. American Airlines stated that
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-
52A1167, dated December 1, 2011 (referred to in the NPRM as the
appropriate source of service information), implies that an operator
may install a new set of hinges having P/Ns 113A8341-1 and 113A8341-2
and restart the inspection threshold and
[[Page 49904]]
interval; however, the Accomplishment Instructions recommend
installation of new hinges having P/Ns 113A8341-9 and 113A8341-10 if
cracking is found. American Airlines stated that installation of a new
set of hinges having P/Ns 113A8341-1 and 113A8341-2 should be
acceptable as long as the on-going repetitive inspections are
accomplished as defined in paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 737-52A1167, dated December 1, 2011.
We agree to allow replacement of cracked hinges with new hinges
having P/Ns 113A8341-1 and 113A8341-2, as long as inspections of the
replacement hinges are accomplished at the time specified in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-52A1167,
dated December 1, 2011. We have added new paragraph (h)(2) to this AD
to clarify that installing new MLG door hinge fittings having P/N
113A8341-1 and 113A8341-2, is acceptable for compliance with the
modification specified in paragraphs (g)(1)(ii) and (g)(2)(i) of this
AD. Paragraph (h)(2) also specifies that installation of the MLG door
hinge fittings having P/N 113A8341-1 and 113A8341-2, must be done using
a method approved in accordance with the procedures specified in
paragraph (j) of this AD. We have revised subsequent paragraph
identifiers accordingly. This difference has been coordinated with
Boeing.
Request for Clarification of Follow-On Actions
Boeing requested that we reword paragraph (g) of the NPRM (77 FR
36222, June 18, 2012) to clarify the follow-on actions required after
the inspections. Boeing stated that the requirement to continue
repetitive inspections needs to be clarified since it only pertains if
the hinges were found to be uncracked.
We agree that clarification is needed. The repetitive inspections
are not required if the modification has been accomplished with hinges
having P/Ns 113A8341-9 and 113A8341-10. However, the repetitive
inspections are required if hinges having P/N 113A8341-1 and 113A8341-2
are installed. We have added this clarification in paragraphs (g)(1)
and (g)(2) of this AD.
Request To Require Modification of Only Doors Having Cracked Hinges
Southwest Airlines (Southwest) requested that replacement of the
hinges be required only on the door where cracks were found, rather
than replacing both doors if cracking is found only on one door.
Southwest stated it wants the option to not modify a door on which the
hinges are not cracked, even though there is hinge cracking on the door
on the other side of the airplane. Southwest added that, for a door
that has no cracked hinges, the repetitive inspections would remain
effective, and modification would not be required prior to further
flight.
We agree that only doors with cracked hinges need to be modified,
and that the repetitive inspections specified in the AD remain in
effect for the door that has not been modified. We have revised
paragraph (g)(2)(i) of this AD to clarify that modification is only
required on affected doors.
Request for the Option To Remove Inboard MLG Door in Accordance With
the Configuration Deviation List (CDL)
Southwest requested that we allow the option of removing the
inboard MLG door from the airplane as specified in the CDL. Southwest
noted that the CDL allows for continued operation without the inboard
MLG door.
We agree with adding an option to the AD to remove the affected
inboard MLG door. However, the removal must be done in accordance with
a method approved by the FAA because applicable flight effects and
restrictions must be accounted for. In addition, if a door with new
hinge fittings is reinstalled, the inspection required by paragraph (h)
of this AD must be done. We have added paragraph (g)(2)(ii) of this AD
accordingly. We have also added note 1 to paragraph (g)(2)(ii) of this
AD to this AD to refer to the CDL as guidance.
Supplemental Type Certificate (STC) Winglet Comment
Aviation Partners Boeing stated that the installation of winglets
per STC ST00830SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/408E012E008616A7862578880060456C?OpenDocument&Highlight=st00830se) does
not affect the accomplishment of the manufacturer's service
instructions.
We have added paragraph (c)(1) to this AD to state that
installation of STC ST00830SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/408E012E008616A7862578880060456C?OpenDocument&Highlight=st00830se) does
not affect the ability to accomplish the actions required by this AD.
Therefore, for airplanes on which STC ST00830SE is installed, a
``change in product'' alternative method of compliance (AMOC) approval
request is not necessary to comply with the requirements of 14 CFR
39.17. For all other AMOC requests, the operator must request approval
of an AMOC in accordance with the procedures specified in paragraph (j)
of this AD.
New Optional Installation Paragraph
We have added new paragraph (h)(1) to this AD to clarify that
installing new MLG door hinge fittings having P/N 113A8341-9 and
113A8341-10, terminates the inspection requirements of this AD for only
the door on which new fittings are installed.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (77 FR 36222, June 18, 2012) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (77 FR 36222, June 18, 2012).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 1,175 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Inspection...................... 3 work-hours x $85 per $0 $255 per inspection $299,625 per
hour = $255 per cycle. inspection cycle.
inspection cycle.
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[[Page 49905]]
We estimate the following costs to do any necessary modification
that would be required based on the results of the inspection. We have
no way of determining the number of airplanes that might need this
modification:
On-Condition Costs
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Action Labor cost Parts cost Cost per product
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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 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
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
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 adding the following new airworthiness
directive (AD):
2013-15-16 The Boeing Company: Amendment 39-17532; Docket No. FAA-
2012-0637; Directorate Identifier 2012-NM-006-AD.
(a) Effective Date
This AD is effective September 20, 2013.
(b) Affected ADs
None.
(c) Applicability
(1) 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.
(2) Installation of Supplemental Type Certificate (STC)
ST00830SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/408E012E008616A7862578880060456C?OpenDocument&Highlight=st00830se)
does not affect the ability to accomplish the actions required by
this AD. Therefore, for airplanes on which STC ST00830SE is
installed, a ``change in product'' alternative method of compliance
(AMOC) approval request is not necessary to comply with the
requirements of 14 CFR 39.17.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 52, Doors.
(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, and 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 (i) of this AD, at the
applicable time specified in paragraph 1.E., ``Compliance,'' 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.
(1) If no cracking is found, at the times specified in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-52A1167,
dated December 1, 2011, do the actions specified in either paragraph
(g)(1)(i) or (g)(1)(ii) of this AD, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1167, dated December 1, 2011.
(i) Repeat either a detailed or a surface HFEC inspection for
cracking of the left- and right-side inboard MLG door hinge
fittings.
(ii) Modify the hinge fittings on the inboard MLG doors by
installing P/N 113A8341-9 and 113A8341-10, in accordance with Part 3
of the Accomplishment Instructions of Boeing Alert Service Bulletin
737-52A1167, dated December 1, 2011. Doing the modification
specified in this paragraph terminates the inspection requirements
for only the door on which new fittings are installed.
(2) If any cracking is found, before further flight, do the
actions specified in either paragraph (g)(2)(i) or (g)(2)(ii) of
this AD.
(i) Modify the hinge fittings on all affected inboard MLG doors
by installing P/N 113A8341-9 and 113A8341-10, in accordance with
Part 3 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 737-52A1167, dated December 1, 2011. Doing the modification
specified in this paragraph terminates the inspection requirements
for only the door on which new fittings are installed.
(ii) Remove the affected MLG door, using a method approved in
accordance with the procedures specified in paragraph (j) of this
AD. For airplanes on which this door is reinstalled, before further
flight, accomplish the actions specified in either paragraph
[[Page 49906]]
(h)(1) or (h)(2) of this AD on the reinstalled door.
Note 1 to paragraph (g)(2)(ii) of this AD: Guidance for removing
the door can be found in Section 32-10 of Appendix CDL,
Configuration Deviation List, Model 737-100/200/300/400/500/600/700/
800/900/900 ER Series, to the Boeing 737-700 Airplane Flight Manual
Document D631A001.
(h) Optional Installation
(1) Installing new MLG door hinge fittings having P/N 113A8341-9
and 113A8341-10, terminates the inspection requirements of this AD
for only the doors on which new fittings are installed.
(2) Installing new MLG door hinge fittings having P/N 113A8341-1
and 113A8341-2, is acceptable for compliance with the modification
specified in paragraphs (g)(1)(ii) and (g)(2)(i) of this AD,
provided the inspections (both the initial and the repetitive
inspections) required by paragraph (g) of this AD are done within
the applicable times specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 737-52A1167, dated December 1, 2011.
Installation of the MLG door hinge fittings having P/N 113A8341-1
and 113A8341-2, as applicable, must be done using a method approved
in accordance with the procedures specified in paragraph (j) of this
AD. Accomplishing the requirements of this paragraph does not
terminate the inspection requirements of paragraph (g) of this AD.
(i) Exception to the Service Information
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.
(j) 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: [email protected].
(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.
(k) Related Information
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, WA 98057-3356;
phone: 425-917-6440; fax: 425-917-6590; email: [email protected].
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 737-52A1167, dated December 1,
2011.
(ii) Reserved.
(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
(4) You may view this service information at FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on July 21, 2013.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-18090 Filed 8-15-13; 8:45 am]
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