[Federal Register Volume 80, Number 138 (Monday, July 20, 2015)]
[Proposed Rules]
[Pages 42756-42760]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-17688]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-2462; Directorate Identifier 2014-NM-224-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 737-100, -200, -200C, -300, -400, -500
series airplanes. This proposed AD was prompted by reports of cracked
antenna support channels, skin cracking underneath the number 2 very
high frequency (VHF) antenna, and cracking in the frames attached to
the internal support structure. This proposed AD would require
repetitive inspections to determine the condition of the skin and the
internal support structure, and follow-on actions including corrective
action as necessary. We are proposing this AD to detect and correct
skin cracking of the fuselage which could result in separation of the
number 2 VHF antenna from the airplane and rapid depressurization of
the cabin.
DATES: We must receive comments on this proposed AD by September 3,
2015.
[[Page 42757]]
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, WA 98124-2207; telephone 206-544-5000,
extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
You may view this 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. It
is also available on the Internet at http://www.regulations.gov by
searching for and locating Docket No. FAA-2015-2462.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
2462; 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: Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6447; fax: 425-917-6590; email: [email protected].
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-2015-2462;
Directorate Identifier 2014-NM-224-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 cracked antenna support channels, skin
cracking underneath the number 2 VHF antenna, and cracking in the
frames attached to the internal support structure. The cracking is
caused when the nose gear is let down, resulting in turbulent airflow
around the antenna. The turbulent airflow causes vibration in the
antenna, which results in the skin, as well as the internal support
structure and frames, to crack due to fatigue. This condition, if not
corrected, could result in separation of the antenna from the airplane
and rapid depressurization of the cabin.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Special Attention Service Bulletin 737-53-1159,
Revision 1, dated October 20, 2014. The service information describes
procedures for repetitive inspections to determine the condition of the
skin and the internal support structure, and follow-on actions
including corrective action as necessary. This service information is
reasonably available because the interested parties have access to it
through their normal course of business or by the means identified in
the ADDRESSES section of this NPRM.
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 identified previously, except as discussed
under ``Differences Between this Proposed AD and the Service
Information.''
Difference Between This Proposed AD and the Service Information
Tables 7, 8, and 9 in paragraph 1.E., ``Compliance,'' of Boeing
Special Attention Service Bulletin 737-53-1159, Revision 1, dated
October 20, 2014, specify post-modification and post-repair
inspections, which may be used in support of compliance with section
121.1109(c)(2) or 129.109(b)(2) of the Federal Aviation Regulations 14
CFR 121.1109(c)(2) or 129.109(b)(2)). However, this NPRM does not
propose to require those post-modification and post-repair inspections.
This difference has been coordinated with Boeing.
Boeing Special Attention Service Bulletin 737-53-1159, Revision 1,
dated October 20, 2014, specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing those conditions in one of the following ways:
In accordance with a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) whom we have
authorized to make those findings.
Explanation of ``RC (Required for Compliance)'' Steps in Service
Information
The FAA worked in conjunction with industry, under the
Airworthiness Directive Implementation Aviation Rulemaking Committee
(ARC), to enhance the AD system. One enhancement was a new process for
annotating which steps in the service information are required for
compliance with an AD. Differentiating these steps from other tasks in
the service information is expected to improve an owner's/operator's
understanding of crucial AD requirements and help provide consistent
judgment in AD compliance. The steps identified as RC (required for
compliance) in any service information identified previously have a
direct effect on detecting, preventing, resolving, or eliminating an
identified unsafe condition.
For service information that contains steps that are labeled as
Required for Compliance (RC), the following provisions apply: (1) The
steps labeled as RC, including substeps under an RC step and any
figures identified in an RC step, must be done to comply with the AD,
and an alternative method of compliance (AMOC) is required for any
deviations to RC steps, including substeps and identified figures; and
(2)
[[Page 42758]]
steps not labeled as RC may be deviated from using accepted methods in
accordance with the operator's maintenance or inspection program
without obtaining approval of an AMOC, provided the RC steps, including
substeps and identified figures, can still be done as specified, and
the airplane can be put back in an airworthy condition.
Costs of Compliance
We estimate that this proposed AD affects 609 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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Inspections........... 33 work-hours x $85 per $0 $2,805 per inspection $1,708,245 per
hour = $2,805 per cycle. inspection cycle.
inspection cycle.
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We estimate the following costs to do any necessary [repairs/
modifications] 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 repairs/modifications.
On-condition costs
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Action Labor cost Parts cost Cost per product
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Repair and Preventive Modification.. 63 work-hours x $85 per hour = $10,432 Up to $15,787.
$5,355.
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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
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):
The Boeing Company: Docket No. FAA-2015-2462; Directorate Identifier
2014 NM-224-AD.
(a) Comments Due Date
We must receive comments by September 3, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any
category, as identified in Boeing Special Attention Service Bulletin
737-53-1159, Revision 1, dated October 20, 2014.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of cracked antenna support
channels, skin cracking underneath the number 2 VHF antenna, and
cracking in the frames attached to the internal support structure.
We are issuing this AD to detect and correct skin cracking of the
fuselage that could result in separation of the antenna from the
airplane and rapid depressurization of the cabin.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection and Follow-on Actions: Group 1
For airplanes identified as Group 1 in Boeing Special Attention
Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014:
Within 120 days after the effective date of this AD, inspect for
cracking at the number 2 VHF antenna location, and do all applicable
follow-on actions, using a method approved in accordance with the
procedures specified in paragraph (m) of this AD.
[[Page 42759]]
(h) Inspection and Follow-on Actions: Groups 2 through 6,
Configurations 1 through 3
For airplanes identified as Groups 2 through 6, configurations 1
through 3 in Boeing Special Attention Service Bulletin 737-53-1159,
Revision 1, dated October 20, 2014: Within 1,250 flight cycles after
the effective date of this AD, do an external detailed inspection
for cracking of the fuselage skin, as applicable, and do all
corrective actions, in accordance with Part 1 of the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 737-53-
1159, Revision 1, dated October 20, 2014. Thereafter, at the
applicable time specified in paragraph 1.E., ``Compliance,'' of
Boeing Special Attention Service Bulletin 737-53-1159, Revision 1,
dated October 20, 2014, except as required by paragraph (l)(1) of
this AD: Do all applicable actions specified in paragraphs (h)(1)
through (h)(4) of this AD.
(1) Repeat the Part 1 inspection specified in paragraph (h) of
this AD until the accomplishment of paragraphs (k)(1) and (k)(2) of
this AD, as applicable.
(2) Inspect for cracking at the number 2 VHF antenna location
using internal and external detailed inspections, internal and
external high frequency eddy current (HFEC) inspections, and an HFEC
open-hole inspection, in accordance with Part 2 of the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 737-53-1159, Revision 1, dated October 20, 2014. Repeat the
inspections until the accomplishment of paragraphs (k)(1) and (k)(2)
of this AD, as applicable.
(3) Repair any crack found, in accordance with Part 3 of the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 737-53-1159, Revision 1, dated October 20, 2014, except as
required by paragraph (l)(2) of this AD.
(4) Do a preventive modification, in accordance with Part 4 of
the Accomplishment Instructions of Boeing Special Attention Service
Bulletin 737 53 1159, Revision 1, dated October 20, 2014, except as
specified in paragraph (l)(2) of this AD. The accomplishment of this
preventive modification terminates the inspections required by
paragraphs (g), (g)(1), and (h)(2) of this AD.
(i) Inspection and Follow-on Actions: Groups 3 through 6, Configuration
4
For airplanes identified as Groups 3 through 6, Configuration 4,
in Boeing Special Attention Service Bulletin 737-53-1159, Revision
1, dated October 20, 2014: At the applicable time specified in table
10 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention
Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014; Do
an external detailed inspection for cracking at the outer row of
fasteners common to the internal repair doubler, and do an internal
general visual inspection for cracking on the modified internal
support structure of the number 2 VHF antenna, skin, and surrounding
stringers, channel, and frames, in accordance with the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 737-53-1159, Revision 1, dated October 20, 2014.
(1) If any cracking is found, before further flight, repair
using a method approved in accordance with the procedures specified
in paragraph (m) of this AD.
(2) If no cracking is found, repeat the inspections at the time
specified in table 10 of paragraph 1.E., ``Compliance,'' of Boeing
SB 737-53-1159, Revision 1, dated October 20, 2014.
(j) Post Repair/Post Modification Inspections
For airplanes identified as Group 2, Configuration 1, and Groups
3 through 6, Configurations 1 through 3, in Boeing Special Attention
Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014:
The post-repair/post-modification inspections specified in tables 7
through 9 of paragraph 1.E., ``Compliance'' of Boeing Special
Attention Service Bulletin 737-53-1159, Revision 1, dated October
20, 2014, are not required by this AD.
Note 1 to paragraph (j) of this AD: The post-repair/post-
modification inspections specified in tables 7 through 9 of
paragraph 1.E., ``Compliance'' of Boeing Special Attention Service
Bulletin 737-53-1159, Revision 1, dated October 20, 2014, may be
used in support of compliance with section 121.1109(c)(2) or
129.109(b)(2) for the Federal Aviation Regulations (14 CFR
121.1109(c)(2) or 14 CFR 129.109(b)(2)).
(k) Terminating Action Provisions
The following describes terminating action for the airplane
groups and configurations, as identified in Boeing Special Attention
Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014.
(1) For airplanes in Group 2, Configuration 2; and Groups 3
through 6, Configuration 2: Accomplishment of the inspections
specified in paragraph (h)(2) of this AD terminates the repetitive
inspection requirements of paragraph (h)(1) of this AD.
(2) For airplanes in Group 2, Configuration 1, and Groups 3
through 6, Configuration 1, 2, and 3: Accomplishment of the repair
specified in paragraph (h)(3) of this AD terminates the repetitive
inspections specified in paragraph (h)(1) and (h)(2) of this AD.
(3) For airplanes in Group 2, Configuration 1; and Groups 3
through 6, Configurations 1 and 3: Accomplishment of the preventive
modification specified in paragraph (h)(4) of this AD terminates the
initial and repetitive inspections specified in paragraphs (h),
(h)(1), and (h)(2) of this AD.
(l) Exception to Service Bulletin Specifications
(1) Where Boeing Special Attention Service Bulletin 737-53-1159,
Revision 1, dated October 20, 2014 compliance is ``after the
Revision 1 date of this service bulletin,'' this AD requires
compliance within the specified compliance time after the effective
date of this AD. Do the inspection, in accordance with the
Accomplishment Instructions of the Boeing Special Attention Service
Bulletin 737-53-1159, Revision 1, dated October 20, 2014.
(2) Where Boeing Special Attention Service Bulletin 737-53-1159,
Revision 1, dated October 20, 2014, specifies to contact Boeing for
appropriate action, and specifies that action as ``RC'' (Required
for Compliance): Before further flight, repair the cracking using a
method approved in accordance with the procedures specified in
paragraph (m) of this AD.
(m) Alternative Methods of Compliance (AMOCs)
(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 paragraph (n)(2) of this AD.
(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 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 the approval must
specifically refer to this AD.
(4) For service information that contains steps that are labeled
as Required for Compliance (RC), the provisions of paragraphs
(m)(4)(i) and (m)(4)(ii) apply.
(i) The steps labeled as RC, including substeps under an RC step
and any figures identified in an RC step, must be done to comply
with the AD. An AMOC is required for any deviations to RC steps,
including substeps and identified figures.
(ii) Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection
program without obtaining approval of an AMOC, provided the RC
steps, including substeps and identified figures, can still be done
as specified, and the airplane can be put back in an airworthy
condition.
(n) Related Information
(1) For more information about this AD, contact Wayne Lockett,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6447; fax: 425-917-6590; email:
[email protected].
(2) For information on AMOCs, contact Nenita Odesa, Aerospace
Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft
Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA
90712-4137; phone: 562-627-5210; fax: 562-627-5234; email:
[email protected].
(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. You
[[Page 42760]]
may view this 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.
Issued in Renton, Washington, on July 10, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-17688 Filed 7-17-15; 8:45 am]
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