Airworthiness Directives; The Boeing Company Airplanes, 72511-72515 [2016-23078]
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Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Rules and Regulations
TABLE 1 TO PARAGRAPH (j)(4) OF THIS
AD—ASM REPLACEMENT—Continued
Affected airplane
configuration
Post-Airbus Service Bulletin
A320–47–1011 ..................
ASM part No.
2060017–102
(k) Retained Requirement: No Alternative
Actions, Intervals, and/or CDCCLs, With No
Changes
This paragraph restates the requirements of
paragraph (k) of AD 2012–20–07, with no
changes. Except as required by paragraph (l)
of this AD, after accomplishing the revisions
required by paragraph (j) of this AD, no
alternative actions (e.g., inspections),
intervals, and/or CDCCLs may be used other
than those specified in Airbus A318/A319/
A320/A321 ALS Part 5—Fuel Airworthiness
Limitations, dated February 28, 2006, as
defined in Airbus A318/A319/A320/A321
Fuel Airworthiness Limitations, Document
95A.1931/05, Issue 4, dated August 26, 2010,
unless the actions, intervals, and/or CDCCLs
are approved as an alternative method of
compliance (AMOC) in accordance with the
procedures specified in paragraph (n)(1) of
this AD.
(l) New Requirement of This AD: Revise the
Maintenance or Inspection Program
Within 60 days after the effective date of
this AD, revise the maintenance or inspection
program, as applicable, by incorporating the
fuel airworthiness limitations (e.g., life
limits, tasks, and CDCCLs, and associated
thresholds and intervals) described in Airbus
A318/A319/A320/A321 ALS Part 5, Fuel
Airworthiness Limitations, Revision 01,
dated July 9, 2014. The initial compliance
times for the tasks are at the times specified
in Airbus A318/A319/A320/A321 ALS Part
5, Fuel Airworthiness Limitations, Revision
01, dated July 9, 2014, or within 60 days after
the effective date of this AD, whichever
occurs later. Incorporating the requirements
of this paragraph terminates the requirements
of paragraphs (g) through (k) of this AD.
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(m) New Requirement of This AD: No
Alternative Actions, Intervals, or CDCCLs
After the maintenance or inspection
program has been revised as required by
paragraph (l) of this AD, no alternative
actions (e.g., inspections), intervals, or
CDCCLs may be used unless the actions,
intervals, or CDCCLs are approved as an
AMOC in accordance with the procedures
specified in paragraph (n)(1) of this AD.
(n) 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 International Branch, send it to ATTN:
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15:55 Oct 19, 2016
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Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov.
(i) 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. The AMOC
approval letter must specifically reference
this AD.
(ii) AMOCs approved previously for AD
2012–20–07 are approved as AMOCs for the
corresponding provisions of this AD.
(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
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the
DOA-authorized signature.
(o) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0260, dated
December 5, 2014, 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–2016–5589.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (p)(7) and (p)(8) of this AD.
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(6) The following service information was
approved for IBR on August 28, 2007 (72 FR
40222, July 24, 2007).
(i) Airbus A318/A319/A320/A321 Fuel
Airworthiness Limitations, Document
95A.1931/05, Issue 1, dated December 19,
2005.
(ii) Reserved.
(7) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
(8) 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.
(9) 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: https://www.archives.
gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on
September 28, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–24078 Filed 10–19–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
(p) Material Incorporated by Reference
14 CFR Part 39
(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 this AD specifies otherwise.
(3) The following service information was
approved for IBR on November 25, 2016.
(i) Airbus A318/A319/A320/A321
Airworthiness Limitations Section (ALS) Part
5, Fuel Airworthiness Limitations, Revision
01, dated July 9, 2014. The title page of this
document does not contain the revision date.
The remaining pages of this document do not
include the revision level.
(ii) Reserved.
(4) The following service information was
approved for IBR on November 21, 2012 (77
FR 63716, October 17, 2012).
(i) Airbus A318/A319/A320/A321 Fuel
Airworthiness Limitations, Document
95A.1931/05, Issue 4, dated August 26, 2010.
(ii) Reserved.
(5) The following service information was
approved for IBR on December 14, 2009 (74
FR 62219, November 27, 2009).
(i) Airbus A318/A319/A320/A321 Fuel
Airworthiness Limitations, Document
95A.1931/05, Issue 2, dated July 8, 2008.
(ii) Reserved.
[Docket No. FAA–2015–6538; Directorate
Identifier 2015–NM–031–AD; Amendment
39–18668; AD 2016–20–02]
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RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 737–300,
–400, and –500 series airplanes. This
AD was prompted by an evaluation by
the design approval holder (DAH)
indicating that the aft pressure bulkhead
is subject to widespread fatigue damage
(WFD). This AD requires repetitive
inspections of the aft pressure bulkhead
web for any cracking, incorrectly drilled
fastener holes, and elongated fastener
holes; and related investigative and
corrective actions, if necessary. We are
issuing this AD to detect and correct
fatigue cracking of the aft pressure
bulkhead web at the ‘‘Y’’-chord, which
could result in reduced structural
SUMMARY:
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Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Rules and Regulations
integrity of the airplane and rapid
decompression of the fuselage.
DATES: This AD is effective November
25, 2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 25, 2016.
ADDRESSES: For service information
identified in this final rule, 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 https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
6538.
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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–2015–
6538; 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
Docket 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:
Payman Soltani, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office,
3960 Paramount Boulevard, Lakewood,
CA 90712–4137; telephone: 562–627–
5313; fax: 562–627–5210; email:
payman.soltani@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model 737–100, –200, –200C, –300,
–400, and –500 series airplanes. The
NPRM published in the Federal
Register on November 30, 2015 (80 FR
74731) (‘‘the NPRM’’). The NPRM was
prompted by an evaluation by the DAH
indicating that the aft pressure bulkhead
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is subject to WFD. The NPRM proposed
to require repetitive inspections of the
aft pressure bulkhead web for any
cracking, incorrectly drilled fastener
holes, and elongated fastener holes, and
related investigative and corrective
actions, if necessary. We are issuing this
AD to detect and correct fatigue
cracking of the aft pressure bulkhead
web at the ‘‘Y’’-chord, which could
result in reduced structural integrity of
the airplane and rapid decompression of
the fuselage.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Effect of Winglets on Accomplishment
of the Proposed Actions
Aviation Partners Boeing stated that
the installation of winglets per
supplemental type certificate (STC)
ST01219SE does not affect the
accomplishment of the manufacturer’s
service instructions.
We agree with the commenter. We
have redesignated paragraph (c) of the
NPRM as paragraph (c)(1) in this final
rule and added a new paragraph (c)(2)
to state that STC ST01219SE does not
affect the mitigating action or
accomplishment of the actions required
by this final rule. Therefore, for
airplanes on which STC ST01219SE is
installed, ‘‘a change in product’’
alternative method of compliance
(AMOC) approval request is not
necessary to comply with the
requirements of 14 CFR 39.71.
Request To Clarify the Proposed
Requirements of the NPRM
Mr. Cas Lausberg stated that the
subject of the NPRM is addressed in AD
99–08–23, Amendment 39–11132 (64
FR 19879, April 23, 1999) (‘‘AD 99–08–
23’’), which was superseded by AD
2012–18–13 R1, Amendment 39–17429
(78 FR 27020, May 9, 2013) (‘‘AD 2012–
18–13 R1’’). The commenter questioned
the need for the new NPRM.
We agree to provide clarification. As
stated in the ‘‘Discussion’’ section of the
NPRM, this final rule is being issued as
part of the overall joint effort by Boeing
and the FAA to satisfy requirements of
the FAA’s WFD final rule (75 FR 69746,
November 15, 2010), which became
effective on January 14, 2011. The
inspections required by AD 99–08–23
and AD 2012–18–13 R1 do not address
WFD concerns. However, Boeing Alert
Service Bulletin 737–53A1214, Revision
5, dated January 30, 2015, addresses
WFD with new inspection requirements,
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which incorporate a compliance time
(threshold) corresponding to the WFD
inspection start point (ISP) and shorter
repetitive intervals where indicated.
These requirements are included in this
AD. We have not changed this AD in
this regard.
Request To Revise the Term ‘‘Global
Fatigue Damage’’
Boeing requested that the term ‘‘global
fatigue damage’’ be changed to
‘‘widespread fatigue damage’’ in the
NPRM. Boeing stated that this is the first
time it has seen the term ‘‘global’’ used
to describe WFD. Boeing commented
that it is better not to introduce a new
term.
We agree with the commenter.
Although the ‘‘Discussion’’ section of
the proposed rule is not carried over
into the final rule, we agree that the
term ‘‘global fatigue damage’’ should not
be introduced as a new term. We have
not changed this AD in this regard.
Request To Correct Reference to Group
1 LOV (Limit of Validity)
Boeing requested that we change the
wording in the ‘‘Differences Between
This Proposed AD and the Service
Information’’ paragraph of the NPRM,
which referred to WFD-based
inspections specified in certain tables of
Boeing Alert Service Bulletin 737–
53A1214, Revision 5, dated January 30,
2015. The NPRM stated that the WFDbased inspections would affect only
Group 2 airplanes because Group 1
airplanes will reach their LOV before
the compliance times specified ‘‘in
tables 9, 10, and 11’’ of Boeing Alert
Service Bulletin 737–53A1214, Revision
5, dated January 30, 2015.
Boeing stated that the inspections
listed in tables 9, 10, and 11 of Boeing
Alert Service Bulletin 737–53A1214,
Revision 5, dated January 30, 2015, also
include non-WFD inspections that are
required prior to the ISP threshold of
76,000 cycles. Boeing stated that,
therefore, it is not true to say that Group
1 airplanes will reach their limit of
validity before the compliance times
specified in tables 9, 10 and 11.
We partially agree with the
commenter. Although the ‘‘Differences
Between This Proposed AD and the
Service Information’’ paragraph of the
proposed rule is not carried over into
the final rule, we agree to provide
clarification.
Since AD 2012–18–13 R1 was issued,
Boeing issued Alert Service Bulletin
737–53A1214, Revision 5, dated January
30, 2015. Affected airplanes are now
divided into two groups: Group 1, line
numbers 1 through 2565 inclusive; and
Group 2, line numbers 2566 through
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3132 inclusive. Boeing’s evaluation
determined that inspections to address
WFD concerns are required for the aft
pressure bulkhead web at the ‘‘Y’’ chord
at an ISP of 76,000 total flight cycles.
Since Group 1 airplanes will reach their
LOV of 75,000 total flight cycles (34,000
total flight cycles for line numbers 1
through 291 inclusive), which is prior to
this ISP, no WFD inspections are
provided for those airplanes. For Group
2 airplanes, which have an LOV of
85,000 total flight cycles, new tables 9,
10, and 11 of Boeing Alert Service
Bulletin 737–53A1214, Revision 5,
dated January 30, 2015, include
inspections to address WFD. We have
not changed this AD in this regard.
Request To Clarify the Applicability
Boeing requested that we clarify the
applicability of the proposed AD.
Boeing stated that Model 737–100, –200,
and –200C airplanes should be removed
from the ‘‘Applicability’’ paragraph.
Boeing stated that the Group 2 airplanes
only include Model 737–300, –400, and
–500 airplanes.
We agree with the commenter’s
request for the reasons stated above. We
have revised the applicability in
paragraph (c) of this AD to remove
Model 737–100, –200, and –200C series
airplanes and revised the SUMMARY
section to specify certain Model 737–
300, –400, and –500 series airplanes.
Request To Clarify Airplanes Affected
by Terminating Action Provisions
Boeing requested that we change the
wording for the terminating action in
paragraph (j) of the proposed AD.
Boeing stated that the paragraph should
specify that the terminating action
applies only to Group 2 airplanes.
Boeing stated that specifying Group 2
airplanes clearly states the intent of the
terminating action.
We agree with the commenter’s
request for the reasons stated above. We
have expanded the structure of
paragraph (j) of this AD accordingly. In
addition, we have clarified that the
terminating action does not apply to
stringer S–5L to S–7L and stringer S–5R
to S–9R, as specified in AD 2012–18–13
R1 and Boeing Alert Service Bulletin
737–53A1214, Revision 5, dated January
30, 2015.
Request To Revise the Inspections for
Group 2 Airplanes
All Nippon Airways (ANA) requested
that we revise the inspection
requirements in the proposed AD for
Group 2 airplanes. ANA requested that
we either mandate the inspections in
tables 10 and 11 of Boeing Alert Service
Bulletin 737–53A1214, Revision 5,
dated January 30, 2015, for only Group
2 airplanes with 76,000 flight cycles and
more, or create a new NPRM to
supersede AD 2012–18–13 R1 to
mandate all inspection requirements
using Boeing Alert Service Bulletin
737–53A1214, Revision 5, dated January
30, 2015. ANA stated that if a new
proposed rule is created, it requests that
credit be given for any previously
approved AMOCs to AD 2012–18–13
R1, to reduce additional burden for
operators and the FAA.
We agree with the commenter’s
request for the reasons stated by the
commenter. The intent of this final rule
is to address the WFD concerns in
accordance with the FAA’s WFD final
rule (75 FR 69746, November 15, 2010).
We have revised paragraphs (g), (h), and
(l) of this AD accordingly.
Additional Changes to This AD
In paragraphs (g) and (h) of this AD,
we have clarified the compliance times
by explicitly stating the compliance
times instead of referring to the
compliance tables in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 5,
dated January 30, 2015.
The actions in paragraph (h) of the
proposed AD states to do detailed and
eddy current inspections of the aft
pressure bulkhead web from the forward
or aft side of the bulkhead for any
cracking, incorrectly drilled fastener
72513
hole, and elongated fastener hole. In this
AD, we have clarified the actions by
providing the operators the option of
doing detailed and LFEC inspections
from the aft side of the aft pressure
bulkhead, or doing a detailed and HFEC
inspections from the forward side of the
aft pressure bulkhead, for any cracking,
incorrectly drilled fastener hole, and
elongated fastener hole.
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 for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 737–53A1214, Revision 5,
dated January 30, 2015. The service
information describes procedures for,
among other actions, repetitive
inspections of the aft pressure bulkhead
web for any cracking, incorrectly drilled
fastener holes, and elongated fastener
holes; and related investigative and
corrective actions. 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.
Costs of Compliance
We estimate that this AD affects 122
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
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Inspections of the web
at the ‘‘Y’’-chord.
Labor cost
Parts cost
Up to 60 work-hours × $85 per hour = Up to
$5,100 per inspection cycle.
$0
We have received no definitive data
that will enable us to provide cost
estimates for the on-condition actions
specified in this 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:
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Cost per product
Up to $5,100 per inspection cycle.
Cost on U.S. operators
Up to $622,200 per inspection cycle.
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:
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Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Rules and Regulations
‘‘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
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):
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■
2016–20–02 The Boeing Company:
Amendment 39–18668; Docket No.
FAA–2015–6538; Directorate Identifier
2015–NM–031–AD.
(a) Effective Date
This AD is effective November 25, 2016.
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(b) Affected ADs
This AD affects AD 2012–18–13 R1,
Amendment 39–17429 (78 FR 27020, May 9,
2013) (‘‘AD 2012–18–13 R1’’).
(c) Applicability
(1) This AD applies to The Boeing
Company Model 737–300, –400, and –500
series airplanes, certificated in any category,
identified as Group 2 in Boeing Alert Service
Bulletin 737–53A1214, Revision 5, dated
January 30, 2015.
(2) Installation of Supplemental Type
Certificate (STC) ST01219SE (https://
rgl.faa.gov/Regulatory_and_Guidance_
Library/rgstc.nsf/0/EBD1CEC7B301293E8625
7CB30045557A?
OpenDocument&Highlight=st01219s) does
not affect the ability to accomplish the
actions required by this AD. Therefore, for
airplanes on which STC ST01219SE 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
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 aft pressure bulkhead is subject to
widespread fatigue damage. We are issuing
this AD to detect and correct fatigue cracking
of the aft pressure bulkhead web at the ‘‘Y’’chord, which could result in reduced
structural integrity of the airplane and rapid
decompression of the fuselage.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections of the Aft Pressure
Bulkhead Web at the ‘‘Y’’-Chord Upper
Bulkhead
Within 76,000 total flight cycles, or within
4,500 flight cycles since the most recent low
frequency eddy current (LFEC) inspection
accomplished in accordance with AD 2012–
18–13 R1, or within 9,500 flight cycles since
the most recent high frequency eddy current
(HFEC) inspection accomplished in
accordance with AD 2012–18–13 R1,
whichever occurs latest: Do detailed and
LFEC inspections from the aft side of the aft
pressure bulkhead web, or do detailed and
HFEC inspections from the forward side of
the aft pressure bulkhead web, for any
cracking, incorrectly drilled fastener hole,
and elongated fastener hole, and do all
applicable related investigative and
corrective actions, in accordance with Part I
of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1214,
Revision 5, dated January 30, 2015, except as
required by paragraph (i) of this AD. Do all
related investigative and corrective actions
before further flight. If any cracking,
incorrectly drilled fastener hole, or elongated
fastener hole is found, before further flight,
repair the aft pressure bulkhead web using a
method approved in accordance with the
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procedures specified in paragraph (l) of this
AD. Thereafter, repeat the inspections at the
applicable times specified in table 10 of
paragraph 1.E., ‘‘Compliance’’ of Boeing Alert
Service Bulletin 737–53A1214, Revision 5,
dated January 30, 2015.
(h) Repetitive Inspections of the Aft Pressure
Bulkhead Web at the ‘‘Y’’-Chord Below S–15
Within 76,000 total flight cycles, or within
4,500 flight cycles since the most recent
LFEC inspection accomplished in accordance
with AD 2012–18–13 R1, or within 9,500
flight cycles since the most recent HFEC
inspection accomplished in accordance with
AD 2012–18–13 R1, whichever occurs latest:
Do detailed and LFEC inspections from the
aft side of the aft pressure bulkhead, or do
detailed and HFEC inspections from the
forward side of the aft pressure bulkhead, for
any cracking, incorrectly drilled fastener
hole, and elongated fastener hole, and do all
applicable corrective actions, in accordance
with Part III of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1214, Revision 5, dated January 30,
2015, except as required by paragraph (i) of
this AD. Do all corrective actions before
further flight. If any cracking, incorrectly
drilled fastener hole, or elongated fastener
hole is found, before further flight, repair the
aft pressure bulkhead web using a method
approved in accordance with the procedures
specified in paragraph (l) of this AD.
Thereafter, repeat the inspections at the
applicable times specified in table 11 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1214,
Revision 5, dated January 30, 2015.
(i) Exception to the Service Information
Where Boeing Alert Service Bulletin 737–
53A1214, Revision 5, dated January 30, 2015,
specifies to contact Boeing for repair
instructions: Before further flight, repair
using a method approved in accordance with
the procedures specified in paragraph (l) of
this AD.
(j) Terminating Action for Other Rulemaking
(1) For Group 2 airplanes specified in
Boeing Alert Service Bulletin 737–53A1214,
Revision 5, dated January 30, 2015:
Accomplishing the actions required by
paragraph (g) of this AD terminates the
inspections required by paragraph (k) of AD
2012–18–13 R1, except for stringer S–5L to
S–7L and stringer S–5R to S–9R.
(2) For Group 2 airplanes specified in
Boeing Alert Service Bulletin 737–53A1214,
Revision 5, dated January 30, 2015:
Accomplishing the actions required by
paragraph (h) of this AD terminates the
inspections required by paragraph (l) of AD
2012–18–13 R1.
(k) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraphs (g) and (h) of
this AD, if the actions were performed before
the effective date of this AD using Boeing
Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011.
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Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Rules and Regulations
(l) 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 (m)(1) of this AD. Information may
be emailed to: 9-ANM-LAACO-AMOCRequests@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, 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) AMOCs approved previously for AD
2012–18–13 R1, Amendment 39–17429 (78
FR 27020, May 9, 2013), are approved as
AMOCs for the corresponding provisions of
this AD.
asabaliauskas on DSK3SPTVN1PROD with RULES
(m) Related Information
(1) For more information about this AD,
contact Payman Soltani, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles ACO, 3960 Paramount Boulevard,
Lakewood CA 90712–4137; telephone: 562–
627–5313; fax: 562–627–5210; email:
payman.soltani@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (n)(3) and (n)(4) of this AD.
(n) 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–
53A1214, Revision 5, dated January 30, 2015.
(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 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.
(5) You may view this service information
that is incorporated by reference at the
VerDate Sep<11>2014
15:55 Oct 19, 2016
Jkt 241001
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on
September 16, 2016.
Thomas Groves,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–23078 Filed 10–19–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–0465; Directorate
Identifier 2015–NM–096–AD; Amendment
39–18679; AD 2016–20–13]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Airbus Model A330–200 and –300 series
airplanes; and Model A340–200 and
–300 series airplanes. This AD was
prompted by a determination that the
compliance times for certain post-repair
inspections and certain allowable
damage limits (ADLs) must be reduced
in order to address fatigue. This AD
requires identifying any repairs and
ADLs used to assess or control any
structural damage on certain structural
areas, and corrective action if necessary.
We are issuing this AD to prevent
fatigue damage on primary structure and
structural repairs, which could result in
reduced structural integrity of the
airplane.
SUMMARY:
This AD is effective November
25, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 25, 2016.
ADDRESSES: For service information
identified in this final rule, contact
Airbus, Airworthiness Office—EIAS, 1
Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone: +33 5
61 93 36 96; fax: +33 5 61 93 44 51;
email: account.airworth-eas@
airbus.com; Internet: https://
www.airbus.com. You may view this
referenced service information at the
DATES:
PO 00000
Frm 00035
Fmt 4700
Sfmt 4700
72515
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 https://www.regulations.gov by
searching for and locating Docket No.
FAA–2016–0465.
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–2016–
0465; 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 street address for
the Docket Office (telephone: 800–647–
5527) is Docket 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:
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.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Airbus Model A330–
200 and –300 series airplanes; and
Model A340–200 and –300 series
airplanes. The NPRM published in the
Federal Register on February 18, 2016
(81 FR 8160) (‘‘the NPRM’’). The NPRM
was prompted by a determination that
the compliance times for certain postrepair inspections and certain ADLs
must be reduced in order to address
fatigue. The NPRM proposed to require
identifying any repairs and ADLs used
to assess or control any structural
damage on certain structural areas, and
corrective action if necessary. We are
issuing this AD to prevent fatigue
damage on primary structure and
structural repairs, which could result in
reduced structural integrity of the
airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2015–
0101R1, dated June 12, 2015 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
E:\FR\FM\20OCR1.SGM
20OCR1
]]>Agencies
[Federal Register Volume 81, Number 203 (Thursday, October 20, 2016)]
[Rules and Regulations]
[Pages 72511-72515]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-23078]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-6538; Directorate Identifier 2015-NM-031-AD;
Amendment 39-18668; AD 2016-20-02]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
The Boeing Company Model 737-300, -400, and -500 series airplanes. This
AD was prompted by an evaluation by the design approval holder (DAH)
indicating that the aft pressure bulkhead is subject to widespread
fatigue damage (WFD). This AD requires repetitive inspections of the
aft pressure bulkhead web for any cracking, incorrectly drilled
fastener holes, and elongated fastener holes; and related investigative
and corrective actions, if necessary. We are issuing this AD to detect
and correct fatigue cracking of the aft pressure bulkhead web at the
``Y''-chord, which could result in reduced structural
[[Page 72512]]
integrity of the airplane and rapid decompression of the fuselage.
DATES: This AD is effective November 25, 2016.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of November 25,
2016.
ADDRESSES: For service information identified in this final rule,
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 https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
6538.
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-2015-
6538; 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 Docket 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: Payman Soltani, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; telephone:
562-627-5313; fax: 562-627-5210; email: payman.soltani@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain The Boeing Company
Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The
NPRM published in the Federal Register on November 30, 2015 (80 FR
74731) (``the NPRM''). The NPRM was prompted by an evaluation by the
DAH indicating that the aft pressure bulkhead is subject to WFD. The
NPRM proposed to require repetitive inspections of the aft pressure
bulkhead web for any cracking, incorrectly drilled fastener holes, and
elongated fastener holes, and related investigative and corrective
actions, if necessary. We are issuing this AD to detect and correct
fatigue cracking of the aft pressure bulkhead web at the ``Y''-chord,
which could result in reduced structural integrity of the airplane and
rapid decompression of the fuselage.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Effect of Winglets on Accomplishment of the Proposed Actions
Aviation Partners Boeing stated that the installation of winglets
per supplemental type certificate (STC) ST01219SE does not affect the
accomplishment of the manufacturer's service instructions.
We agree with the commenter. We have redesignated paragraph (c) of
the NPRM as paragraph (c)(1) in this final rule and added a new
paragraph (c)(2) to state that STC ST01219SE does not affect the
mitigating action or accomplishment of the actions required by this
final rule. Therefore, for airplanes on which STC ST01219SE is
installed, ``a change in product'' alternative method of compliance
(AMOC) approval request is not necessary to comply with the
requirements of 14 CFR 39.71.
Request To Clarify the Proposed Requirements of the NPRM
Mr. Cas Lausberg stated that the subject of the NPRM is addressed
in AD 99-08-23, Amendment 39-11132 (64 FR 19879, April 23, 1999) (``AD
99-08-23''), which was superseded by AD 2012-18-13 R1, Amendment 39-
17429 (78 FR 27020, May 9, 2013) (``AD 2012-18-13 R1''). The commenter
questioned the need for the new NPRM.
We agree to provide clarification. As stated in the ``Discussion''
section of the NPRM, this final rule is being issued as part of the
overall joint effort by Boeing and the FAA to satisfy requirements of
the FAA's WFD final rule (75 FR 69746, November 15, 2010), which became
effective on January 14, 2011. The inspections required by AD 99-08-23
and AD 2012-18-13 R1 do not address WFD concerns. However, Boeing Alert
Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015,
addresses WFD with new inspection requirements, which incorporate a
compliance time (threshold) corresponding to the WFD inspection start
point (ISP) and shorter repetitive intervals where indicated. These
requirements are included in this AD. We have not changed this AD in
this regard.
Request To Revise the Term ``Global Fatigue Damage''
Boeing requested that the term ``global fatigue damage'' be changed
to ``widespread fatigue damage'' in the NPRM. Boeing stated that this
is the first time it has seen the term ``global'' used to describe WFD.
Boeing commented that it is better not to introduce a new term.
We agree with the commenter. Although the ``Discussion'' section of
the proposed rule is not carried over into the final rule, we agree
that the term ``global fatigue damage'' should not be introduced as a
new term. We have not changed this AD in this regard.
Request To Correct Reference to Group 1 LOV (Limit of Validity)
Boeing requested that we change the wording in the ``Differences
Between This Proposed AD and the Service Information'' paragraph of the
NPRM, which referred to WFD-based inspections specified in certain
tables of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated
January 30, 2015. The NPRM stated that the WFD-based inspections would
affect only Group 2 airplanes because Group 1 airplanes will reach
their LOV before the compliance times specified ``in tables 9, 10, and
11'' of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated
January 30, 2015.
Boeing stated that the inspections listed in tables 9, 10, and 11
of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January
30, 2015, also include non-WFD inspections that are required prior to
the ISP threshold of 76,000 cycles. Boeing stated that, therefore, it
is not true to say that Group 1 airplanes will reach their limit of
validity before the compliance times specified in tables 9, 10 and 11.
We partially agree with the commenter. Although the ``Differences
Between This Proposed AD and the Service Information'' paragraph of the
proposed rule is not carried over into the final rule, we agree to
provide clarification.
Since AD 2012-18-13 R1 was issued, Boeing issued Alert Service
Bulletin 737-53A1214, Revision 5, dated January 30, 2015. Affected
airplanes are now divided into two groups: Group 1, line numbers 1
through 2565 inclusive; and Group 2, line numbers 2566 through
[[Page 72513]]
3132 inclusive. Boeing's evaluation determined that inspections to
address WFD concerns are required for the aft pressure bulkhead web at
the ``Y'' chord at an ISP of 76,000 total flight cycles. Since Group 1
airplanes will reach their LOV of 75,000 total flight cycles (34,000
total flight cycles for line numbers 1 through 291 inclusive), which is
prior to this ISP, no WFD inspections are provided for those airplanes.
For Group 2 airplanes, which have an LOV of 85,000 total flight cycles,
new tables 9, 10, and 11 of Boeing Alert Service Bulletin 737-53A1214,
Revision 5, dated January 30, 2015, include inspections to address WFD.
We have not changed this AD in this regard.
Request To Clarify the Applicability
Boeing requested that we clarify the applicability of the proposed
AD. Boeing stated that Model 737-100, -200, and -200C airplanes should
be removed from the ``Applicability'' paragraph. Boeing stated that the
Group 2 airplanes only include Model 737-300, -400, and -500 airplanes.
We agree with the commenter's request for the reasons stated above.
We have revised the applicability in paragraph (c) of this AD to remove
Model 737-100, -200, and -200C series airplanes and revised the SUMMARY
section to specify certain Model 737-300, -400, and -500 series
airplanes.
Request To Clarify Airplanes Affected by Terminating Action Provisions
Boeing requested that we change the wording for the terminating
action in paragraph (j) of the proposed AD. Boeing stated that the
paragraph should specify that the terminating action applies only to
Group 2 airplanes. Boeing stated that specifying Group 2 airplanes
clearly states the intent of the terminating action.
We agree with the commenter's request for the reasons stated above.
We have expanded the structure of paragraph (j) of this AD accordingly.
In addition, we have clarified that the terminating action does not
apply to stringer S-5L to S-7L and stringer S-5R to S-9R, as specified
in AD 2012-18-13 R1 and Boeing Alert Service Bulletin 737-53A1214,
Revision 5, dated January 30, 2015.
Request To Revise the Inspections for Group 2 Airplanes
All Nippon Airways (ANA) requested that we revise the inspection
requirements in the proposed AD for Group 2 airplanes. ANA requested
that we either mandate the inspections in tables 10 and 11 of Boeing
Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015,
for only Group 2 airplanes with 76,000 flight cycles and more, or
create a new NPRM to supersede AD 2012-18-13 R1 to mandate all
inspection requirements using Boeing Alert Service Bulletin 737-
53A1214, Revision 5, dated January 30, 2015. ANA stated that if a new
proposed rule is created, it requests that credit be given for any
previously approved AMOCs to AD 2012-18-13 R1, to reduce additional
burden for operators and the FAA.
We agree with the commenter's request for the reasons stated by the
commenter. The intent of this final rule is to address the WFD concerns
in accordance with the FAA's WFD final rule (75 FR 69746, November 15,
2010). We have revised paragraphs (g), (h), and (l) of this AD
accordingly.
Additional Changes to This AD
In paragraphs (g) and (h) of this AD, we have clarified the
compliance times by explicitly stating the compliance times instead of
referring to the compliance tables in paragraph 1.E., ``Compliance,''
of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January
30, 2015.
The actions in paragraph (h) of the proposed AD states to do
detailed and eddy current inspections of the aft pressure bulkhead web
from the forward or aft side of the bulkhead for any cracking,
incorrectly drilled fastener hole, and elongated fastener hole. In this
AD, we have clarified the actions by providing the operators the option
of doing detailed and LFEC inspections from the aft side of the aft
pressure bulkhead, or doing a detailed and HFEC inspections from the
forward side of the aft pressure bulkhead, for any cracking,
incorrectly drilled fastener hole, and elongated fastener hole.
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 for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 737-53A1214, Revision 5,
dated January 30, 2015. The service information describes procedures
for, among other actions, repetitive inspections of the aft pressure
bulkhead web for any cracking, incorrectly drilled fastener holes, and
elongated fastener holes; and related investigative and corrective
actions. 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.
Costs of Compliance
We estimate that this AD affects 122 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
----------------------------------------------------------------------------------------------------------------
Inspections of the web at the Up to 60 work-hours x $0 Up to $5,100 per Up to $622,200
``Y''-chord. $85 per hour = Up to inspection cycle. per inspection
$5,100 per inspection cycle.
cycle.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that will enable us to provide
cost estimates for the on-condition actions specified in this 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:
[[Page 72514]]
``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):
2016-20-02 The Boeing Company: Amendment 39-18668; Docket No. FAA-
2015-6538; Directorate Identifier 2015-NM-031-AD.
(a) Effective Date
This AD is effective November 25, 2016.
(b) Affected ADs
This AD affects AD 2012-18-13 R1, Amendment 39-17429 (78 FR
27020, May 9, 2013) (``AD 2012-18-13 R1'').
(c) Applicability
(1) This AD applies to The Boeing Company Model 737-300, -400,
and -500 series airplanes, certificated in any category, identified
as Group 2 in Boeing Alert Service Bulletin 737-53A1214, Revision 5,
dated January 30, 2015.
(2) Installation of Supplemental Type Certificate (STC)
ST01219SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/EBD1CEC7B301293E86257CB30045557A?OpenDocument&Highlight=st01219s)
does not affect the ability to accomplish the actions required by
this AD. Therefore, for airplanes on which STC ST01219SE 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
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 aft pressure bulkhead is subject to
widespread fatigue damage. We are issuing this AD to detect and
correct fatigue cracking of the aft pressure bulkhead web at the
``Y''-chord, which could result in reduced structural integrity of
the airplane and rapid decompression of the fuselage.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections of the Aft Pressure Bulkhead Web at the
``Y''-Chord Upper Bulkhead
Within 76,000 total flight cycles, or within 4,500 flight cycles
since the most recent low frequency eddy current (LFEC) inspection
accomplished in accordance with AD 2012-18-13 R1, or within 9,500
flight cycles since the most recent high frequency eddy current
(HFEC) inspection accomplished in accordance with AD 2012-18-13 R1,
whichever occurs latest: Do detailed and LFEC inspections from the
aft side of the aft pressure bulkhead web, or do detailed and HFEC
inspections from the forward side of the aft pressure bulkhead web,
for any cracking, incorrectly drilled fastener hole, and elongated
fastener hole, and do all applicable related investigative and
corrective actions, in accordance with Part I of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1214, Revision
5, dated January 30, 2015, except as required by paragraph (i) of
this AD. Do all related investigative and corrective actions before
further flight. If any cracking, incorrectly drilled fastener hole,
or elongated fastener hole is found, before further flight, repair
the aft pressure bulkhead web using a method approved in accordance
with the procedures specified in paragraph (l) of this AD.
Thereafter, repeat the inspections at the applicable times specified
in table 10 of paragraph 1.E., ``Compliance'' of Boeing Alert
Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015.
(h) Repetitive Inspections of the Aft Pressure Bulkhead Web at the
``Y''-Chord Below S-15
Within 76,000 total flight cycles, or within 4,500 flight cycles
since the most recent LFEC inspection accomplished in accordance
with AD 2012-18-13 R1, or within 9,500 flight cycles since the most
recent HFEC inspection accomplished in accordance with AD 2012-18-13
R1, whichever occurs latest: Do detailed and LFEC inspections from
the aft side of the aft pressure bulkhead, or do detailed and HFEC
inspections from the forward side of the aft pressure bulkhead, for
any cracking, incorrectly drilled fastener hole, and elongated
fastener hole, and do all applicable corrective actions, in
accordance with Part III of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January
30, 2015, except as required by paragraph (i) of this AD. Do all
corrective actions before further flight. If any cracking,
incorrectly drilled fastener hole, or elongated fastener hole is
found, before further flight, repair the aft pressure bulkhead web
using a method approved in accordance with the procedures specified
in paragraph (l) of this AD. Thereafter, repeat the inspections at
the applicable times specified in table 11 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 5, dated January 30, 2015.
(i) Exception to the Service Information
Where Boeing Alert Service Bulletin 737-53A1214, Revision 5,
dated January 30, 2015, specifies to contact Boeing for repair
instructions: Before further flight, repair using a method approved
in accordance with the procedures specified in paragraph (l) of this
AD.
(j) Terminating Action for Other Rulemaking
(1) For Group 2 airplanes specified in Boeing Alert Service
Bulletin 737-53A1214, Revision 5, dated January 30, 2015:
Accomplishing the actions required by paragraph (g) of this AD
terminates the inspections required by paragraph (k) of AD 2012-18-
13 R1, except for stringer S-5L to S-7L and stringer S-5R to S-9R.
(2) For Group 2 airplanes specified in Boeing Alert Service
Bulletin 737-53A1214, Revision 5, dated January 30, 2015:
Accomplishing the actions required by paragraph (h) of this AD
terminates the inspections required by paragraph (l) of AD 2012-18-
13 R1.
(k) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraphs (g) and (h) of this AD, if the actions were performed
before the effective date of this AD using Boeing Alert Service
Bulletin 737-53A1214, Revision 4, dated December 16, 2011.
[[Page 72515]]
(l) 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 (m)(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, 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) AMOCs approved previously for AD 2012-18-13 R1, Amendment
39-17429 (78 FR 27020, May 9, 2013), are approved as AMOCs for the
corresponding provisions of this AD.
(m) Related Information
(1) For more information about this AD, contact Payman Soltani,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO,
3960 Paramount Boulevard, Lakewood CA 90712-4137; telephone: 562-
627-5313; fax: 562-627-5210; email: payman.soltani@faa.gov.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (n)(3) and (n)(4) of this AD.
(n) 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 737-53A1214, Revision 5, dated
January 30, 2015.
(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 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.
(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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on September 16, 2016.
Thomas Groves,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-23078 Filed 10-19-16; 8:45 am]
BILLING CODE 4910-13-P
