Airworthiness Directives; The Boeing Company Airplanes, 8325-8328 [2018-03600]
Download as PDF
<![CDATA[
Federal Register / Vol. 83, No. 39 / Tuesday, February 27, 2018 / Rules and Regulations
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):
■
2018–04–05 Airbus: Amendment 39–19200;
Docket No. FAA–2016–9519; Product
Identifier 2016–NM–099–AD.
(a) Effective Date
This AD is effective April 3, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A319–
112, A319–115, A320–214, A320–232, and
A321–211 airplanes, certificated in any
category, manufacturer’s serial numbers
1479, 3096, 3693, 3713, 3739, 3791, 3896,
3902, 3907, 3931, 3949, 3969, 4030, 4045,
4049, 4059, 4066, 4077, 4083, 4124, 4146,
4158, 4188, 4198, 4206, 4209, 4218, 4235,
4255, 4264, 4304, 4321, 4371, 4374, 4395,
4411, 4417, 4431, 4485, 4492, 4502, 4528,
4541, 4548, 4592, 4595, 4638, 4651, 4669,
4703, 4724, 4737, 4746, 4770, 4780, 4783,
4826, 4827, 4860, 4863, 4865, 4902, 4934,
4945, 4951, 4952, 4971, 4996, 5023, 5029,
5042, 5088, 5095, 5132, 5159, 5164, 5171,
5175, 5192, 5210, 5227, 5241, 5247, 5251,
5275, 5277, 5297, 5306, 5340, 5343, 5348,
5356, 5366, 5370, 5385, 5387, 5392, 5396,
5400, 5407, 5418, 5427, 5438, 5456, 5458,
5469, 5495, 5517, 5555, 5624, 5674, 5678,
5698, 5699, 5704, 5709, 5714, 5791, 5745,
5753, 5761, 5781, 5786, 5788, 5789, 5798,
5804, 5810, 5821, 5827, 5842, 5874, 5882,
5889, 5903, 5907, 5916, 5924, 5958, 5984,
5994, 6000, 6004, 6054, 6080, 6107, 6166,
6176, 6234, 6266, 6293, 6335, 6344, 6365,
6430, and 6444.
(d) Subject
Air Transport Association (ATA) of
America Code 25, Equipment/furnishings.
(e) Reason
This AD was prompted by in-service
experience and further analysis, which
showed that the galley 5 without kick-load
retainers was unable to withstand the
expected loading during several flight phases
or in case of emergency landing. We are
issuing this AD to prevent galley/trolley
detachment and collapse into an adjacent
cabin aisle or cabin zone, possibly spreading
loose galley equipment items, compartment
doors, or leaking fluids. These hazards could
block an evacuation route and result in injury
to crew or passengers.
daltland on DSKBBV9HB2PROD with RULES
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Install Kick-Load Retainers
Within 12 months after the effective date
of this AD, install kick-load retainers on the
galley 5 trolley compartments as specified in
paragraph (g)(1), (g)(2), or (g)(3) of this AD,
as applicable. For airplanes on which galley
5 is not installed, no action is required by
this paragraph.
VerDate Sep<11>2014
19:20 Feb 26, 2018
Jkt 244001
(1) For Airbus Model A319–115 airplanes,
manufacturer’s serial numbers 5678, 5698,
5704, 5745, 5753, 5761, 5781, 5786, 5788,
5789, 5798, 5810, 5827, and 5842, do the
installation in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–25–1B29, dated June
19, 2014.
(2) For Airbus Model A320–232 airplanes,
manufacturer’s serial numbers 5458, 5517,
5624, and 5804, do the installation in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
25–1B30, dated June 19, 2014.
(3) For airplanes not identified in
paragraph (g)(1) or (g)(2) of this AD, do the
installation using a method approved by the
Manager, International Section, Transport
Standards Branch, FAA; or the European
Aviation Safety Agency (EASA); or Airbus’s
EASA Design Organization Approval (DOA).
If approved by the DOA, the approval must
include the DOA-authorized signature
(h) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards 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 International Section, send it
to the attention of the person identified in
paragraph (i)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@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: 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 Section,
Transport Standards Branch, FAA; or EASA;
or Airbus’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
(i) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2016–0040, dated
March 2, 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–
2016–9519.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th Street, Des
Moines, WA 98198; telephone 206–231–
3223; fax 206–231–3398.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
8325
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.
(i) Airbus Service Bulletin A320–25–1B29,
dated June 19, 2014.
(ii) Airbus Service Bulletin A320–25–1B30,
dated June 19, 2014.
(3) 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.
(4) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th Street, Des Moines, WA.
For information on the availability of this
material at the FAA, call 206–231–3195.
(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/ibrlocations.html.
Issued in Des Moines, Washington, on
February 9, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–03495 Filed 2–26–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0766; Product
Identifier 2017–NM–046–AD; Amendment
39–19203; AD 2018–04–08]
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 all The
Boeing Company Model 737–100, –200,
–200C, –300, –400, and –500 series
airplanes. This AD was prompted by an
evaluation by the design approval
holder (DAH) indicating that the gore
web lap splices of the aft pressure
bulkhead are subject to widespread
fatigue damage (WFD). This AD requires
repetitive inspections of the gore webs,
gore web lap splices, and repair webs,
as applicable, of the aft pressure
bulkhead, and applicable on-condition
actions. We are issuing this AD to
address the unsafe condition on these
products.
SUMMARY:
E:\FR\FM\27FER1.SGM
27FER1
8326
Federal Register / Vol. 83, No. 39 / Tuesday, February 27, 2018 / Rules and Regulations
This AD is effective April 3,
2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 3, 2018.
ADDRESSES: For service information
identified in this final rule, 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 service information at the
FAA, Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2017–
0766.
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–
0766; 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 final rule, 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:
George Garrido, Aerospace Engineer,
Airframe Section, FAA, Los Angeles
ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5232; fax: 562–627–
5210; email: george.garrido@faa.gov.
SUPPLEMENTARY INFORMATION:
daltland on DSKBBV9HB2PROD with RULES
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all The Boeing Company Model
737–100, –200, –200C, –300, –400, and
–500 series airplanes. The NPRM
published in the Federal Register on
August 11, 2017 (82 FR 37546). The
NPRM was prompted by an evaluation
by the DAH indicating that the gore web
lap splices of the aft pressure bulkhead
are subject to WFD. The NPRM
proposed to require repetitive
inspections of the gore webs, gore web
lap splices, and repair webs, as
VerDate Sep<11>2014
18:04 Feb 26, 2018
Jkt 244001
applicable, of the aft pressure bulkhead,
and applicable on-condition actions.
We are issuing this AD to detect and
correct cracking in the gore webs, gore
web lap splices, and repair webs of the
aft pressure bulkhead, which could
result in possible rapid decompression
and loss of structural integrity.
Comments
We gave the public the opportunity to
participate in developing this final rule.
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
accomplishing the Supplemental Type
Certificate (STC) ST01219SE does not
affect the actions specified in the
NPRM.
We concur with the commenter. We
have redesignated paragraph (c) of the
proposed AD as paragraph (c)(1) of this
AD and added paragraph (c)(2) to this
AD to state that installation of STC
ST01219SE 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.
Request To Clarify ‘‘Related AD’’
Section
Boeing recommended that a statement
be added to the ‘‘Related AD’’ section of
the NPRM to provide clarification of the
effect of the proposed AD on the
requirements of paragraph (o) of AD
2012–18–13 R1, Amendment 39–17429
(78 FR 27020, May 9, 2013) (‘‘AD 2012–
18–13 R1’’). Boeing asserted that the
‘‘Related AD’’ section could be
misinterpreted to imply that the
inspections required by the proposed
AD are in addition to the requirements
of paragraph (o) of AD 2012–18–13 R1.
We agree with the commenter’s
rationale, but the ‘‘Related AD’’ section
is not included in this final rule.
Therefore, no change has been made.
Request To Address the Termination of
AD 2012–18–13 R1
Boeing requested a clarification that
actions required by the proposed AD
terminate the requirements of paragraph
(o) of AD 2012–18–13 R1. Boeing
asserted that the actions of Boeing Alert
Service Bulletin 737–53A1355, dated
March 10, 2017, supersede the actions
of Boeing Alert Service Bulletin 737–
53A1214, Revision 4, dated December
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
16, 2011, which are mandated by
paragraph (o) of AD 2012–18–13 R1.
All Nippon Airways (ANA) also
requested clarification regarding
termination of the requirements of
paragraph (o) of AD 2012–18–13 R1.
ANA stated that, because the
compliance time is changed to ‘‘after the
effective date of this AD’’ in the
proposed AD, the inspections and
corrective actions required by paragraph
(o) of AD 2012–18–13 R1 may be
terminated as long as the inspections for
Zone 1, as specified in Boeing Alert
Service Bulletin 737–53A1355, dated
March 10, 2017, have been done within
the changed compliance time.
We agree with the requests for
clarification. We have added the
requested terminating action
information as paragraph (i) of this AD
and redesignated subsequent
paragraphs.
Request To Clarify the Zone 2
Definition
Boeing requested a clarification of the
definition of Zone 2 in the ‘‘Related
Service Information under 1 CFR part
51’’ paragraph of the NPRM. Boeing
observed that the definition given could
be misleading because it does not
specify that Zone 2 contains only the
gore web lap splices outside the apex
area.
We agree and have added the phrase
‘‘outside the apex area’’ to the specified
paragraph of this final rule.
Clarification of Compliance Exception
We have revised the compliance
exception in paragraph (j)(1) of this AD
to clarify that where Boeing Alert
Service Bulletin 737–53A1355, dated
March 10, 2017, uses the phrase ‘‘the
original issue date of this service
bulletin,’’ this AD requires using ‘‘the
effective date of this AD.’’
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this
final rule 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 final rule.
E:\FR\FM\27FER1.SGM
27FER1
8327
Federal Register / Vol. 83, No. 39 / Tuesday, February 27, 2018 / Rules and Regulations
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 737–53A1355, dated March 10,
2017. The service information describes
procedures for repetitive inspections of
the gore web in Zone 1 (i.e., inspections
around fastener locations in the gore
web lap splices and around fastener
locations in the apex area outside the
gore web lap splices) and gore web lap
splices in Zone 2 (i.e., inspections
around fastener locations in the gore
web lap splices outside the apex area)
of the aft pressure bulkhead, and
applicable on-condition actions. The
service information also describes, for
airplanes with an existing single gore
web repair, procedures for repetitive
inspections of the gore web (i.e.,
inspections around fastener locations in
the gore web lap splices) and repair
webs (i.e., inspections around fastener
locations in the gore web lap splices and
around fastener locations in the apex
area outside the gore web lap splices);
and, for airplanes with an existing all
gore web repair, procedures for
repetitive inspections of the repair webs
(i.e., inspections around fastener
locations in the repair gore web lap
splices and around fastener locations in
the apex area outside the repair gore
web lap splices); and procedures for
applicable on-condition 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 281
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
ESTIMATED COSTS
Action
Labor cost
Inspection .........
46 work-hours × $85 per hour = $3,910 per inspection cycle.
We estimate the following costs to do
any necessary on-condition actions that
Parts cost
Cost per product
$0
$3,910 per inspection
cycle.
would be required based on the results
of the inspection. We have no way of
Cost on U.S. operators
$1,098,710 per inspection
cycle.
determining the number of aircraft that
might need these on-condition actions:
ON-CONDITION COSTS
Action
Labor cost
Inspection of previous single gore web repair .............
Inspection of previous all gore web repair ...................
8 work-hours × $85 per hour = $680 ...........................
10 work-hours × $85 per hour = $850 .........................
We have received no definitive data
that would enable us to provide cost
estimates for the repairs specified in this
AD.
daltland on DSKBBV9HB2PROD with RULES
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 AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
VerDate Sep<11>2014
18:04 Feb 26, 2018
Jkt 244001
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
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
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
Cost per
product
Parts cost
$0
0
$680
850
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):
■
2018–04–08 The Boeing Company:
Amendment 39–19203; Docket No.
FAA–2017–0766; Product Identifier
2017–NM–046–AD.
(a) Effective Date
This AD is effective April 3, 2018.
E:\FR\FM\27FER1.SGM
27FER1
8328
Federal Register / Vol. 83, No. 39 / Tuesday, February 27, 2018 / Rules and Regulations
(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 all The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes,
certificated in any category.
(2) Installation of Supplemental Type
Certificate (STC) ST01219SE (https://rgl.faa.
gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/EBD1CEC7B301293E86257CB30
045557A?OpenDocument&Highlight=
st01219se) 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 (DAH) indicating
that the gore web lap splices of the aft
pressure bulkhead are subject to widespread
fatigue damage (WFD). We are issuing this
AD to detect and correct cracking in the gore
webs, gore web lap splices, and repair webs
of the aft pressure bulkhead, which could
result in possible rapid decompression and
loss of structural integrity.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions for Group 1 Airplanes
For airplanes identified as Group 1 in
Boeing Alert Service Bulletin 737–53A1355,
dated March 10, 2017: Within 120 days after
the effective date of this AD, inspect the
airplane, using a method approved in
accordance with the procedures specified in
paragraph (k) of this AD.
daltland on DSKBBV9HB2PROD with RULES
(h) Actions Required for Compliance
Except as required by paragraph (j) of this
AD: For airplanes identified as Group 2 in
Boeing Alert Service Bulletin 737–53A1355,
dated March 10, 2017, at the applicable times
specified in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1355,
dated March 10, 2017, do all applicable
actions identified as required for compliance
(‘‘RC’’) in, and in accordance with, the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1355, dated March
10, 2017.
(i) Termination of Requirements of
Paragraph (o) of AD 2012–18–13 R1
Accomplishment of the initial inspection
for Zone 1, defined in Boeing Alert Service
Bulletin 737–53A1355, dated March 10,
2017, and required by paragraph (h) of this
AD terminates the requirements of paragraph
(o) of AD 2012–18–13 R1.
VerDate Sep<11>2014
18:04 Feb 26, 2018
Jkt 244001
(j) Exceptions to Service Information
Specifications
(1) For purposes of determining
compliance with the requirements of this AD:
Where Boeing Alert Service Bulletin 737–
53A1355, dated March 10, 2017, uses the
phrase ‘‘the original issue date of this service
bulletin,’’ this AD requires using ‘‘the
effective date of this AD.’’
(2) Although Boeing Alert Service Bulletin
737–53A1355, dated March 10, 2017,
specifies to contact Boeing for repair
instructions, and specifies that action as
‘‘RC’’ (Required for Compliance), this AD
requires repair before further flight using a
method approved in accordance with the
procedures specified in paragraph (k) of this
AD.
(k) 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 (l) of this
AD. Information may be emailed to: 9-ANMLAACO-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 paragraph (j)(2)
of this AD: For service information that
contains steps that are labeled as Required
for Compliance (RC), the provisions of
paragraphs (k)(4)(i) and (k)(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.
(l) Related Information
For more information about this AD,
contact George Garrido, Aerospace Engineer,
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
Airframe Section, FAA, Los Angeles ACO
Branch, 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627–
5232; fax: 562–627–5210; email:
george.garrido@faa.gov.
(m) 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–
53A1355, dated March 10, 2017.
(ii) Reserved.
(3) 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.
(4) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(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/ibrlocations.html.
Issued in Renton, Washington, on February
14, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–03600 Filed 2–26–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9435; Product
Identifier 2016–NM–108–AD; Amendment
39–18830; AD 2017–06–06]
RIN 2120–AA64
Airworthiness Directives; Fokker
Services B.V. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2012–22–
15, which applied to all Fokker Services
B.V. Model F28 Mark 0070 and Mark
0100 airplanes. AD 2012–22–15
required revising the maintenance
program to incorporate the limitations,
SUMMARY:
E:\FR\FM\27FER1.SGM
27FER1
]]>Agencies
[Federal Register Volume 83, Number 39 (Tuesday, February 27, 2018)]
[Rules and Regulations]
[Pages 8325-8328]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-03600]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0766; Product Identifier 2017-NM-046-AD; Amendment
39-19203; AD 2018-04-08]
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 all The
Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series
airplanes. This AD was prompted by an evaluation by the design approval
holder (DAH) indicating that the gore web lap splices of the aft
pressure bulkhead are subject to widespread fatigue damage (WFD). This
AD requires repetitive inspections of the gore webs, gore web lap
splices, and repair webs, as applicable, of the aft pressure bulkhead,
and applicable on-condition actions. We are issuing this AD to address
the unsafe condition on these products.
[[Page 8326]]
DATES: This AD is effective April 3, 2018.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of April 3,
2018.
ADDRESSES: For service information identified in this final rule,
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 service information at the
FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA.
For information on the availability of this material at the FAA, call
206-231-3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0766.
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-
0766; 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 final rule, 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: George Garrido, Aerospace Engineer,
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5232; fax: 562-627-
5210; email: [email protected].
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 all The Boeing Company
Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The
NPRM published in the Federal Register on August 11, 2017 (82 FR
37546). The NPRM was prompted by an evaluation by the DAH indicating
that the gore web lap splices of the aft pressure bulkhead are subject
to WFD. The NPRM proposed to require repetitive inspections of the gore
webs, gore web lap splices, and repair webs, as applicable, of the aft
pressure bulkhead, and applicable on-condition actions.
We are issuing this AD to detect and correct cracking in the gore
webs, gore web lap splices, and repair webs of the aft pressure
bulkhead, which could result in possible rapid decompression and loss
of structural integrity.
Comments
We gave the public the opportunity to participate in developing
this final rule. 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 accomplishing the Supplemental
Type Certificate (STC) ST01219SE does not affect the actions specified
in the NPRM.
We concur with the commenter. We have redesignated paragraph (c) of
the proposed AD as paragraph (c)(1) of this AD and added paragraph
(c)(2) to this AD to state that installation of STC ST01219SE 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.
Request To Clarify ``Related AD'' Section
Boeing recommended that a statement be added to the ``Related AD''
section of the NPRM to provide clarification of the effect of the
proposed AD on the requirements of paragraph (o) of AD 2012-18-13 R1,
Amendment 39-17429 (78 FR 27020, May 9, 2013) (``AD 2012-18-13 R1'').
Boeing asserted that the ``Related AD'' section could be misinterpreted
to imply that the inspections required by the proposed AD are in
addition to the requirements of paragraph (o) of AD 2012-18-13 R1.
We agree with the commenter's rationale, but the ``Related AD''
section is not included in this final rule. Therefore, no change has
been made.
Request To Address the Termination of AD 2012-18-13 R1
Boeing requested a clarification that actions required by the
proposed AD terminate the requirements of paragraph (o) of AD 2012-18-
13 R1. Boeing asserted that the actions of Boeing Alert Service
Bulletin 737-53A1355, dated March 10, 2017, supersede the actions of
Boeing Alert Service Bulletin 737-53A1214, Revision 4, dated December
16, 2011, which are mandated by paragraph (o) of AD 2012-18-13 R1.
All Nippon Airways (ANA) also requested clarification regarding
termination of the requirements of paragraph (o) of AD 2012-18-13 R1.
ANA stated that, because the compliance time is changed to ``after the
effective date of this AD'' in the proposed AD, the inspections and
corrective actions required by paragraph (o) of AD 2012-18-13 R1 may be
terminated as long as the inspections for Zone 1, as specified in
Boeing Alert Service Bulletin 737-53A1355, dated March 10, 2017, have
been done within the changed compliance time.
We agree with the requests for clarification. We have added the
requested terminating action information as paragraph (i) of this AD
and redesignated subsequent paragraphs.
Request To Clarify the Zone 2 Definition
Boeing requested a clarification of the definition of Zone 2 in the
``Related Service Information under 1 CFR part 51'' paragraph of the
NPRM. Boeing observed that the definition given could be misleading
because it does not specify that Zone 2 contains only the gore web lap
splices outside the apex area.
We agree and have added the phrase ``outside the apex area'' to the
specified paragraph of this final rule.
Clarification of Compliance Exception
We have revised the compliance exception in paragraph (j)(1) of
this AD to clarify that where Boeing Alert Service Bulletin 737-
53A1355, dated March 10, 2017, uses the phrase ``the original issue
date of this service bulletin,'' this AD requires using ``the effective
date of this AD.''
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this final rule 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 final
rule.
[[Page 8327]]
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 737-53A1355, dated March
10, 2017. The service information describes procedures for repetitive
inspections of the gore web in Zone 1 (i.e., inspections around
fastener locations in the gore web lap splices and around fastener
locations in the apex area outside the gore web lap splices) and gore
web lap splices in Zone 2 (i.e., inspections around fastener locations
in the gore web lap splices outside the apex area) of the aft pressure
bulkhead, and applicable on-condition actions. The service information
also describes, for airplanes with an existing single gore web repair,
procedures for repetitive inspections of the gore web (i.e.,
inspections around fastener locations in the gore web lap splices) and
repair webs (i.e., inspections around fastener locations in the gore
web lap splices and around fastener locations in the apex area outside
the gore web lap splices); and, for airplanes with an existing all gore
web repair, procedures for repetitive inspections of the repair webs
(i.e., inspections around fastener locations in the repair gore web lap
splices and around fastener locations in the apex area outside the
repair gore web lap splices); and procedures for applicable on-
condition 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 281 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
----------------------------------------------------------------------------------------------------------------
Inspection................. 46 work-hours x $85 $0 $3,910 per inspection $1,098,710 per
per hour = $3,910 cycle. inspection cycle.
per inspection cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary on-condition
actions that would be required based on the results of the inspection.
We have no way of determining the number of aircraft that might need
these on-condition actions:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Inspection of previous single gore web 8 work-hours x $85 per hour = $680. $0 $680
repair.
Inspection of previous all gore web repair. 10 work-hours x $85 per hour = $850 0 850
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the repairs 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: ``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 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
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):
2018-04-08 The Boeing Company: Amendment 39-19203; Docket No. FAA-
2017-0766; Product Identifier 2017-NM-046-AD.
(a) Effective Date
This AD is effective April 3, 2018.
[[Page 8328]]
(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 all The Boeing Company Model 737-100, -
200, -200C, -300, -400, and -500 series airplanes, certificated in
any category.
(2) Installation of Supplemental Type Certificate (STC)
ST01219SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/EBD1CEC7B301293E86257CB30045557A?OpenDocument&Highlight=st01219se)
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 (DAH) indicating that the gore web lap splices of the aft
pressure bulkhead are subject to widespread fatigue damage (WFD). We
are issuing this AD to detect and correct cracking in the gore webs,
gore web lap splices, and repair webs of the aft pressure bulkhead,
which could result in possible rapid decompression and loss of
structural integrity.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions for Group 1 Airplanes
For airplanes identified as Group 1 in Boeing Alert Service
Bulletin 737-53A1355, dated March 10, 2017: Within 120 days after
the effective date of this AD, inspect the airplane, using a method
approved in accordance with the procedures specified in paragraph
(k) of this AD.
(h) Actions Required for Compliance
Except as required by paragraph (j) of this AD: For airplanes
identified as Group 2 in Boeing Alert Service Bulletin 737-53A1355,
dated March 10, 2017, at the applicable times specified in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1355,
dated March 10, 2017, do all applicable actions identified as
required for compliance (``RC'') in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1355, dated March 10, 2017.
(i) Termination of Requirements of Paragraph (o) of AD 2012-18-13 R1
Accomplishment of the initial inspection for Zone 1, defined in
Boeing Alert Service Bulletin 737-53A1355, dated March 10, 2017, and
required by paragraph (h) of this AD terminates the requirements of
paragraph (o) of AD 2012-18-13 R1.
(j) Exceptions to Service Information Specifications
(1) For purposes of determining compliance with the requirements
of this AD: Where Boeing Alert Service Bulletin 737-53A1355, dated
March 10, 2017, uses the phrase ``the original issue date of this
service bulletin,'' this AD requires using ``the effective date of
this AD.''
(2) Although Boeing Alert Service Bulletin 737-53A1355, dated
March 10, 2017, specifies to contact Boeing for repair instructions,
and specifies that action as ``RC'' (Required for Compliance), this
AD requires repair before further flight using a method approved in
accordance with the procedures specified in paragraph (k) of this
AD.
(k) 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 (l) of this AD. Information may
be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, 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 paragraph (j)(2) of this AD: For
service information that contains steps that are labeled as Required
for Compliance (RC), the provisions of paragraphs (k)(4)(i) and
(k)(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.
(l) Related Information
For more information about this AD, contact George Garrido,
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5232; fax: 562-627-5210; email: [email protected].
(m) 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 737-53A1355, dated March 10,
2017.
(ii) Reserved.
(3) 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.
(4) You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
(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 February 14, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-03600 Filed 2-26-18; 8:45 am]
BILLING CODE 4910-13-P
