Airworthiness Directives; The Boeing Company Airplanes, 37366-37369 [2017-16355]
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37366
Federal Register / Vol. 82, No. 153 / Thursday, August 10, 2017 / Proposed Rules
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(q) Exception to Initial Inspection
Compliance Time
For the purposes of table 1 to paragraph
(h)(1) of this AD, table 2 to paragraph (l)(1)
of this AD, and table 3 to paragraph (l)(1) of
this AD: As soon as a cargo door is inspected
using any applicable service information
specified in this AD, the previous inspections
accomplished in accordance with any alert
operator transmission can be disregarded for
the determination of the compliance time for
the initial inspection required by this AD.
(r) Credit for Previous Actions
(1) This paragraph provides credit for the
initial inspection required by paragraph (h)
of this AD, if that inspection was performed
before the effective date of this AD using
Airbus Service Bulletin A330–52–3087,
dated August 29, 2013; Airbus Service
Bulletin A340–52–4095, dated August 29,
2013; or Airbus Service Bulletin A340–52–
5020, dated August 29, 2013; as applicable;
provided that the actions identified as
‘‘additional work’’ in the Accomplishment
Instructions of Airbus Service Bulletin A330–
52–3087, Revision 01, dated July 9, 2014;
Airbus Service Bulletin A340–52–4095,
Revision 01, dated July 28, 2014; or Airbus
Service Bulletin A340–52–5020, Revision 01,
dated July 9, 2014; as applicable; are
accomplished within 1,100 flight cycles after
that inspection; and provided the next
inspection of all frame fork areas, frame head
areas, and outer skin area of each affected
forward cargo door is accomplished within
1,100 flight cycles after that inspection, in
accordance with the Accomplishment
Instructions of A330–52–3087, R2; A330–52–
3095, R2; or A340–52–5020, R2, as
applicable.
(2) This paragraph provides credit for the
initial inspection required by paragraph (h)
of this AD, if that inspection was performed
before the effective date of this AD using
Airbus Service Bulletin A330–52–3087,
Revision 01, dated July 9, 2014; Airbus
Service Bulletin A340–52–4095, Revision 01,
dated July 28, 2014; or Airbus Service
Bulletin A340–52–5020, Revision 01, dated
July 9, 2014; as applicable; provided that the
next inspection of all frame fork areas, frame
head areas, and outer skin area of each
affected forward cargo door, is accomplished
within 1,100 flight cycles after that
inspection in accordance with the
Accomplishment Instructions of A330–52–
3087, R2; A330–52–3095, R2; or A340–52–
5020, R2, as applicable.
(3) This paragraph provides credit for the
initial inspection required by paragraph (l) of
this AD, if that inspection was performed
before the effective date of this AD using
Airbus Service Bulletin A330–52–3095,
dated August 29, 2013; Airbus Service
Bulletin A340–52–4101, dated August 29,
2013; or Airbus Service Bulletin A340–52–
5023, dated August 29, 2013; provided that
the actions identified as ‘‘additional work’’ in
the Accomplishment Instructions of Airbus
Service Bulletin A330–52–3095, Revision 01,
dated July 28, 2014; Airbus Service Bulletin
A340–52–4101, Revision 01, dated July 28,
2014; or Airbus Service Bulletin A340–52–
5023, Revision 01, dated July 28, 2014; as
applicable; are accomplished within 550
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flight cycles after that inspection, and
provided the next inspection of all frame fork
areas, frame head areas, and outer skin area
of each affected aft cargo door is
accomplished within 550 flight cycles after
that inspection in accordance with the
Accomplishment Instructions of A330–52–
3095, R2; A340–52–4101, R2; or A340–52–
5023, R2, as applicable.
(4) This paragraph provides credit for the
initial inspection required by paragraph (l) of
this AD, if that inspection was performed
before the effective date of this AD using
Airbus Service Bulletin A330–52–3095,
Revision 01, dated July 28, 2014; Airbus
Service Bulletin A340–52–4101, Revision 01,
dated July 28, 2014; or Airbus Service
Bulletin A340–52–5023, Revision 01, dated
July 28, 2014; as applicable; provided that
the next inspection of all frame fork areas,
frame head areas, and outer skin area of each
affected aft cargo door is accomplished
within 550 flight cycles after that inspection
in accordance with the Accomplishment
Instructions of A330–52–3095, R2; A340–52–
4101, R2; or A340–52–5023, R2, as
applicable.
(s) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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 International Branch,
send it to the attention of the person
identified in paragraph (t)(2) of this AD.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. 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.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Required for Compliance (RC): Except
as required by paragraph (p) of this AD: If
any service information contains procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
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 procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
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changes to procedures or tests identified as
RC require approval of an AMOC.
(t) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0188, dated September 21, 2016;
corrected September 22, 2016, for related
information. This MCAI may be found in the
AD docket on the Internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2017–0713.
(2) For more information about this AD,
contact, Vladimir Ulyanov, Aerospace
Engineer, International Branch, ANM–116,
Transport Airplane Directorate, FAA, 1601
Lind Avenue SW., Renton, WA 98057–3356;
telephone: 425–227–1138; fax: 425–227–
1149.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone: +33
5 61 93 36 96; fax: +33 5 61 93 45 80; email:
airworthiness.A330-A340@airbus.com;
Internet: https://www.airbus.com. You may
view this 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 19,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–16051 Filed 8–9–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0715; Product
Identifier 2017–NM–073–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 737–200,
–200C, –300, –400, and –500 series
airplanes. This AD was prompted by an
evaluation by the design approval
holder (DAH) indicating that the
fuselage crown skin panels are subject
to widespread fatigue damage (WFD).
This proposed AD would require
repetitive inspections, replacement, and
applicable on-condition actions for
certain fuselage crown skin panels. We
are proposing this AD to address the
unsafe condition on these products.
SUMMARY:
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Federal Register / Vol. 82, No. 153 / Thursday, August 10, 2017 / Proposed Rules
We must receive comments on
this proposed AD by September 25,
2017.
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
https://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 NPRM, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster
Blvd., MC 110–SK57, Seal Beach, CA
90740–5600; telephone 562–797–1717;
Internet https://
www.myboeingfleet.com. You may view
this referenced service information at
the FAA, Transport Standards Branch,
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 https://www.regulations.gov by
searching for and locating Docket No.
FAA–2017–0715.
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DATES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0715; 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 NPRM, 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:
Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Section, FAA, Los
Angeles Aircraft Certification Office
(ACO) Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5264; fax: 562–627–
5210; email: Jennifer.tsakoumakis@
faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
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this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2017–0715; Product Identifier 2017–
NM–073–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this NPRM. We will consider
all comments received by the closing
date and may amend this NPRM
because of those comments.
We will post all comments we
receive, without change, to https://
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
Fatigue damage can occur locally, in
small areas or structural design details,
or globally, in widespread areas.
Multiple-site damage is widespread
damage that occurs in a large structural
element such as a single rivet line of a
lap splice joining two large skin panels.
Widespread damage can also occur in
multiple elements such as adjacent
frames or stringers. Multiple-site
damage and multiple-element damage
cracks are typically too small initially to
be reliably detected with normal
inspection methods. Without
intervention, these cracks will grow,
and eventually compromise the
structural integrity of the airplane. This
condition is known as WFD. It is
associated with general degradation of
large areas of structure with similar
structural details and stress levels. As
an airplane ages, WFD will likely occur,
and will certainly occur if the airplane
is operated long enough without any
intervention.
The FAA’s WFD final rule (75 FR
69746, November 15, 2010) became
effective on January 14, 2011. The WFD
rule requires certain actions to prevent
structural failure due to WFD
throughout the operational life of
certain existing transport category
airplanes and all of these airplanes that
will be certificated in the future. For
existing and future airplanes subject to
the WFD rule, the rule requires that
DAHs establish a limit of validity (LOV)
of the engineering data that support the
structural maintenance program.
Operators affected by the WFD rule may
not fly an airplane beyond its LOV,
unless an extended LOV is approved.
The WFD rule (75 FR 69746,
November 15, 2010) does not require
identifying and developing maintenance
actions if the DAHs can show that such
actions are not necessary to prevent
WFD before the airplane reaches the
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LOV. Many LOVs, however, do depend
on accomplishment of future
maintenance actions. As stated in the
WFD rule, any maintenance actions
necessary to reach the LOV will be
mandated by airworthiness directives
through separate rulemaking actions.
In the context of WFD, this action is
necessary to enable DAHs to propose
LOVs that allow operators the longest
operational lives for their airplanes, and
still ensure that WFD will not occur.
This approach allows for an
implementation strategy that provides
flexibility to DAHs in determining the
timing of service information
development (with FAA approval),
while providing operators with certainty
regarding the LOV applicable to their
airplanes.
We have received a report indicating
that an operator of a Model 737–300
series airplane reported multiple cracks
of the chem-milled steps in adjacent
bays of the fuselage crown skin. These
cracks were discovered by visual
inspection 855 flight cycles after the
most recent detailed inspection. The
initial visual inspection revealed three
cracks varying in length from 1.8 inches
to 8.5 inches. Further inspection using
ultrasonic phased array revealed nine
additional subsurface cracks. The
airplane had 55,232 total flight cycles.
Multiple adjacent cracks in the fuselage
crown skin panels, if not detected and
corrected, could link up and lead to
decompression or loss of structural
integrity of the airplane.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 737–53A1358, dated April 27,
2017. The service information describes
procedures for repetitive inspections,
replacement, and applicable oncondition actions for certain fuselage
crown skin panels. 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.
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
accomplishment of the actions
identified as ‘‘RC’’ (required for
compliance) in the Accomplishment
Instructions of Boeing Alert Service
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Federal Register / Vol. 82, No. 153 / Thursday, August 10, 2017 / Proposed Rules
Bulletin 737–53A1358, dated April 27,
2017, described previously, except for
any differences identified as exceptions
in the regulatory text of this proposed
AD.
For information on the procedures
and compliance times, see this service
information at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0715.
Explanation of Compliance Time
The compliance time for the
replacement specified in this proposed
AD for addressing WFD was established
to ensure that discrepant structure is
replaced before WFD develops in
airplanes. Standard inspection
techniques cannot be relied on to detect
WFD before it becomes a hazard to
flight. We will not grant any extensions
of the compliance time to complete any
AD-mandated service bulletin related to
WFD without extensive new data that
would substantiate and clearly warrant
such an extension.
Costs of Compliance
We estimate that this proposed AD
affects 200 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Inspection ............
Up to 507 work-hours × $85 per
hour = $43,095 per inspection
cycle.
304 work-hours × $85 per hour =
$25,840 per skin panel.
Replacement .......
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
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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.
This proposed AD is issued in
accordance with authority delegated by
the Executive Director, Aircraft
Certification Service, as authorized by
FAA Order 8000.51C. In accordance
with that order, issuance of ADs is
normally a function of the Compliance
and Airworthiness Division, but during
this transition period, the Executive
Director has delegated the authority to
issue ADs applicable to transport
category airplanes to the Director of the
System Oversight Division.
Regulatory Findings
16:24 Aug 09, 2017
$0
95,000
Cost per product
Cost on U.S. operators
Up to $43,095 per inspection cycle
Up to $8,619,000 per inspection
cycle.
$120,840 per skin panel .................
Up to $24,168,000.
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
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The Boeing Company: Docket No. FAA–
2017–0715; Product Identifier 2017–
NM–073–AD.
(a) Comments Due Date
We must receive comments by September
25, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 737–200, –200C, –300, –400, and –500
series airplanes, certificated in any category,
as identified in Boeing Alert Service Bulletin
737–53A1358, dated April 27, 2017.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by
the design approval holder indicating that
the fuselage crown skin panels are subject to
widespread fatigue damage. We are issuing
this AD to detect and correct cracking in the
fuselage crown skin panels. Multiple
adjacent cracks in the fuselage crown skin
could link up and lead to decompression or
loss of structural integrity of the airplane.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
(f) Compliance
PART 39—AIRWORTHINESS
DIRECTIVES
(g) Required Actions
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
We determined that this proposed AD
would not have federalism implications
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Comply with this AD within the
compliance times specified, unless already
done.
Except as required by paragraph (h) of this
AD: At the applicable times specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1358, dated
April 27, 2017, do all applicable actions
identified as ‘‘RC’’ (required for compliance)
in, and in accordance with, the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1358, dated April
27, 2017.
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(h) Exceptions to Service Information
Specifications
(1) For purposes of determining
compliance with the requirements of this AD,
the phrase ‘‘the effective date of this AD’’
may be substituted for ‘‘the original issue
date of this service bulletin,’’ as specified in
Boeing Alert Service Bulletin 737–53A1358,
dated April 27, 2017.
(2) Where Boeing Alert Service Bulletin
737–53A1358, dated April 27, 2017, specifies
contacting Boeing, and specifies that action
as RC: This AD requires using a method
approved in accordance with the procedures
specified in paragraph (j) of this AD.
(3) Part 7 of Boeing Alert Service Bulletin
737–53A1358, dated April 27, 2017, specifies
post-modification airworthiness limitation
inspections in compliance with 14 CFR
25.571(a)(3) at the modified locations to
support compliance with 14 CFR
121.1109(c)(2) or 129.109(b)(2). Although
Part 7 is identified as RC, this AD does not
require accomplishment of Part 7. As
airworthiness limitations, these inspections
are required by maintenance and operational
rules. It is therefore unnecessary to mandate
them in this AD. Deviations from these
inspections require FAA approval, but do not
require approval of an alternative method of
compliance.
(i) Terminating Action for Repetitive
Inspections
(1) Replacement of a skin panel, in
accordance with Part 8 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1358, dated April
27, 2017, except as required by paragraph
(h)(2) of this AD, terminates the actions
specified in Parts 1, 4, and 6 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1358, dated April
27, 2017, as required by paragraph (g) of this
AD, for that replaced skin panel only. To be
acceptable as terminating action, the
replacement may not be done prior to the
applicable time specified in Table 4 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1358, dated
April 27, 2017.
(2) Completion of a structural repair
manual repair to repair cracking, in
accordance with Part 2 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1358, dated April
27, 2017, except as required by paragraph
(h)(2) of this AD, terminates the repetitive
inspections specified in Part 1 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1358, dated April
27, 2017, as required by paragraph (g) of this
AD, for that repair location only.
(3) Completion of a ‘‘Category C repair’’ to
repair cracking, in accordance with Part 3 of
the Accomplishment Instructions of Boeing
Alert Service Bulletin 737–53A1358, dated
April 27, 2017, except as required by
paragraph (h)(2) of this AD, terminates the
repetitive inspections specified in Part 1 of
the Accomplishment Instructions of Boeing
Alert Service Bulletin 737–53A1358, dated
April 27, 2017, as required by paragraph (g)
of this AD, for that repair location only.
(4) Completion of a ‘‘Change Category C
Repair to SB Repair,’’ in accordance with Part
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6 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1358,
dated April 27, 2017, except as required by
paragraph (h)(2) of this AD, terminates the
inspections specified in Part 4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1358, dated April
27, 2017, as required by paragraph (g) of this
AD, for that repair location only.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles ACO Branch,
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
certification office, send it to the attention of
the person identified in paragraph (k)(1) of
this AD. Information may be emailed to: 9ANM-LAACO-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,
modification, or alteration 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 Branch, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraphs (h)(2)
and (h)(3) of this AD: For service information
that contains steps that are labeled as RC, the
provisions of paragraphs (j)(4)(i) and (j)(4)(ii)
of this AD 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. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. 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.
(k) Related Information
(1) For more information about this AD,
contact Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Section, FAA, Los
Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5264; fax: 562–627–5210;
email: Jennifer.tsakoumakis@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
37369
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; Internet https://
www.myboeingfleet.com. You may view this
referenced service information at the FAA,
Transport Standards Branch, 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 26,
2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
[FR Doc. 2017–16355 Filed 8–9–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2016–9546; Airspace
Docket No. 16–AGL–32]
Proposed Establishment of Class E
Airspace; Onida, SD
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
This action proposes to
establish Class E airspace at Onida, SD.
Controlled airspace is necessary to
accommodate new special instrument
approach procedures developed at
Onida Municipal Airport, for the safety
and management of instrument flight
rules (IFR) operations at the airport.
DATES: Comments must be received on
or before September 25, 2017.
ADDRESSES: Send comments on this
proposal to the U.S. Department of
Transportation, Docket Operations,
West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590; telephone (202)
366–9826, or (800) 647–5527. You must
identify FAA Docket No. FAA–2016–
9546; Airspace Docket No. 16–AGL–32,
at the beginning of your comments. You
may also submit comments through the
Internet at https://www.regulations.gov.
You may review the public docket
containing the proposal, any comments
received, and any final disposition in
person in the Dockets Office between
9:00 a.m. and 5:00 p.m., Monday
through Friday, except Federal holidays.
FAA Order 7400.11A, Airspace
Designations and Reporting Points, and
subsequent amendments can be viewed
online at https://www.faa.gov/air_traffic/
publications/. For further information,
you can contact the Airspace Policy
Group, Federal Aviation
Administration, 800 Independence
SUMMARY:
E:\FR\FM\10AUP1.SGM
10AUP1
Agencies
[Federal Register Volume 82, Number 153 (Thursday, August 10, 2017)]
[Proposed Rules]
[Pages 37366-37369]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-16355]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0715; Product Identifier 2017-NM-073-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain The Boeing Company Model 737-200, -200C, -300, -400, and -500
series airplanes. This AD was prompted by an evaluation by the design
approval holder (DAH) indicating that the fuselage crown skin panels
are subject to widespread fatigue damage (WFD). This proposed AD would
require repetitive inspections, replacement, and applicable on-
condition actions for certain fuselage crown skin panels. We are
proposing this AD to address the unsafe condition on these products.
[[Page 37367]]
DATES: We must receive comments on this proposed AD by September 25,
2017.
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 https://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 NPRM, contact Boeing
Commercial Airplanes, Attention: Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600;
telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may
view this referenced service information at the FAA, Transport
Standards Branch, 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 https://www.regulations.gov by
searching for and locating Docket No. FAA-2017-0715.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0715; 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 NPRM, 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: Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Section, FAA, Los Angeles Aircraft Certification
Office (ACO) Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137;
phone: 562-627-5264; fax: 562-627-5210; email:
Jennifer.tsakoumakis@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-2017-0715;
Product Identifier 2017-NM-073-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this NPRM. We will consider all
comments received by the closing date and may amend this NPRM because
of those comments.
We will post all comments we receive, without change, to https://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
Fatigue damage can occur locally, in small areas or structural
design details, or globally, in widespread areas. Multiple-site damage
is widespread damage that occurs in a large structural element such as
a single rivet line of a lap splice joining two large skin panels.
Widespread damage can also occur in multiple elements such as adjacent
frames or stringers. Multiple-site damage and multiple-element damage
cracks are typically too small initially to be reliably detected with
normal inspection methods. Without intervention, these cracks will
grow, and eventually compromise the structural integrity of the
airplane. This condition is known as WFD. It is associated with general
degradation of large areas of structure with similar structural details
and stress levels. As an airplane ages, WFD will likely occur, and will
certainly occur if the airplane is operated long enough without any
intervention.
The FAA's WFD final rule (75 FR 69746, November 15, 2010) became
effective on January 14, 2011. The WFD rule requires certain actions to
prevent structural failure due to WFD throughout the operational life
of certain existing transport category airplanes and all of these
airplanes that will be certificated in the future. For existing and
future airplanes subject to the WFD rule, the rule requires that DAHs
establish a limit of validity (LOV) of the engineering data that
support the structural maintenance program. Operators affected by the
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV
is approved.
The WFD rule (75 FR 69746, November 15, 2010) does not require
identifying and developing maintenance actions if the DAHs can show
that such actions are not necessary to prevent WFD before the airplane
reaches the LOV. Many LOVs, however, do depend on accomplishment of
future maintenance actions. As stated in the WFD rule, any maintenance
actions necessary to reach the LOV will be mandated by airworthiness
directives through separate rulemaking actions.
In the context of WFD, this action is necessary to enable DAHs to
propose LOVs that allow operators the longest operational lives for
their airplanes, and still ensure that WFD will not occur. This
approach allows for an implementation strategy that provides
flexibility to DAHs in determining the timing of service information
development (with FAA approval), while providing operators with
certainty regarding the LOV applicable to their airplanes.
We have received a report indicating that an operator of a Model
737-300 series airplane reported multiple cracks of the chem-milled
steps in adjacent bays of the fuselage crown skin. These cracks were
discovered by visual inspection 855 flight cycles after the most recent
detailed inspection. The initial visual inspection revealed three
cracks varying in length from 1.8 inches to 8.5 inches. Further
inspection using ultrasonic phased array revealed nine additional
subsurface cracks. The airplane had 55,232 total flight cycles.
Multiple adjacent cracks in the fuselage crown skin panels, if not
detected and corrected, could link up and lead to decompression or loss
of structural integrity of the airplane.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 737-53A1358, dated April
27, 2017. The service information describes procedures for repetitive
inspections, replacement, and applicable on-condition actions for
certain fuselage crown skin panels. 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.
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 accomplishment of the actions
identified as ``RC'' (required for compliance) in the Accomplishment
Instructions of Boeing Alert Service
[[Page 37368]]
Bulletin 737-53A1358, dated April 27, 2017, described previously,
except for any differences identified as exceptions in the regulatory
text of this proposed AD.
For information on the procedures and compliance times, see this
service information at https://www.regulations.gov by searching for and
locating Docket No. FAA-2017-0715.
Explanation of Compliance Time
The compliance time for the replacement specified in this proposed
AD for addressing WFD was established to ensure that discrepant
structure is replaced before WFD develops in airplanes. Standard
inspection techniques cannot be relied on to detect WFD before it
becomes a hazard to flight. We will not grant any extensions of the
compliance time to complete any AD-mandated service bulletin related to
WFD without extensive new data that would substantiate and clearly
warrant such an extension.
Costs of Compliance
We estimate that this proposed AD affects 200 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Parts Cost on U.S.
Action Labor cost cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection........................ Up to 507 work-hours $0 Up to $43,095 per Up to $8,619,000 per
x $85 per hour = inspection cycle. inspection cycle.
$43,095 per
inspection cycle.
Replacement....................... 304 work-hours x $85 95,000 $120,840 per skin Up to $24,168,000.
per hour = $25,840 panel.
per skin panel.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
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.
This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes to the Director of the System Oversight
Division.
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-2017-0715; Product Identifier
2017-NM-073-AD.
(a) Comments Due Date
We must receive comments by September 25, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 737-200, -200C, -
300, -400, and -500 series airplanes, certificated in any category,
as identified in Boeing Alert Service Bulletin 737-53A1358, dated
April 27, 2017.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by the design approval
holder indicating that the fuselage crown skin panels are subject to
widespread fatigue damage. We are issuing this AD to detect and
correct cracking in the fuselage crown skin panels. Multiple
adjacent cracks in the fuselage crown skin could link up and lead to
decompression or loss of structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
Except as required by paragraph (h) of this AD: At the
applicable times specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 737-53A1358, dated April 27, 2017, do
all applicable actions identified as ``RC'' (required for
compliance) in, and in accordance with, the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1358, dated
April 27, 2017.
[[Page 37369]]
(h) Exceptions to Service Information Specifications
(1) For purposes of determining compliance with the requirements
of this AD, the phrase ``the effective date of this AD'' may be
substituted for ``the original issue date of this service
bulletin,'' as specified in Boeing Alert Service Bulletin 737-
53A1358, dated April 27, 2017.
(2) Where Boeing Alert Service Bulletin 737-53A1358, dated April
27, 2017, specifies contacting Boeing, and specifies that action as
RC: This AD requires using a method approved in accordance with the
procedures specified in paragraph (j) of this AD.
(3) Part 7 of Boeing Alert Service Bulletin 737-53A1358, dated
April 27, 2017, specifies post-modification airworthiness limitation
inspections in compliance with 14 CFR 25.571(a)(3) at the modified
locations to support compliance with 14 CFR 121.1109(c)(2) or
129.109(b)(2). Although Part 7 is identified as RC, this AD does not
require accomplishment of Part 7. As airworthiness limitations,
these inspections are required by maintenance and operational rules.
It is therefore unnecessary to mandate them in this AD. Deviations
from these inspections require FAA approval, but do not require
approval of an alternative method of compliance.
(i) Terminating Action for Repetitive Inspections
(1) Replacement of a skin panel, in accordance with Part 8 of
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1358, dated April 27, 2017, except as required by paragraph
(h)(2) of this AD, terminates the actions specified in Parts 1, 4,
and 6 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 737-53A1358, dated April 27, 2017, as required by paragraph
(g) of this AD, for that replaced skin panel only. To be acceptable
as terminating action, the replacement may not be done prior to the
applicable time specified in Table 4 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1358, dated
April 27, 2017.
(2) Completion of a structural repair manual repair to repair
cracking, in accordance with Part 2 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1358, dated
April 27, 2017, except as required by paragraph (h)(2) of this AD,
terminates the repetitive inspections specified in Part 1 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1358, dated April 27, 2017, as required by paragraph (g) of this
AD, for that repair location only.
(3) Completion of a ``Category C repair'' to repair cracking, in
accordance with Part 3 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-53A1358, dated April 27, 2017, except as
required by paragraph (h)(2) of this AD, terminates the repetitive
inspections specified in Part 1 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 737-53A1358, dated April 27, 2017,
as required by paragraph (g) of this AD, for that repair location
only.
(4) Completion of a ``Change Category C Repair to SB Repair,''
in accordance with Part 6 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1358, dated April 27, 2017,
except as required by paragraph (h)(2) of this AD, terminates the
inspections specified in Part 4 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 737-53A1358, dated April 27, 2017,
as required by paragraph (g) of this AD, for that repair location
only.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles ACO Branch, 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 certification office, send it to the attention of
the person identified in paragraph (k)(1) of this AD. Information
may be emailed to: 9-ANM-LAACO-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, modification, or alteration 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 Branch, to make those findings. To be
approved, the repair method, modification deviation, or alteration
deviation must meet the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraphs (h)(2) and (h)(3) of this
AD: For service information that contains steps that are labeled as
RC, the provisions of paragraphs (j)(4)(i) and (j)(4)(ii) of this AD
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. If a step or substep is labeled ``RC Exempt,'' then the
RC requirement is removed from that step or substep. 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.
(k) Related Information
(1) For more information about this AD, contact Jennifer
Tsakoumakis, Aerospace Engineer, Airframe Section, FAA, Los Angeles
ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137;
phone: 562-627-5264; fax: 562-627-5210; email:
Jennifer.tsakoumakis@faa.gov.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may view this referenced service
information at the FAA, Transport Standards Branch, 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 26, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-16355 Filed 8-9-17; 8:45 am]
BILLING CODE 4910-13-P