Airworthiness Directives; The Boeing Company Airplanes, 35641-35644 [2017-15486]
Download as PDF
Federal Register / Vol. 82, No. 146 / Tuesday, August 1, 2017 / Rules and Regulations
(l) Related Information
DEPARTMENT OF TRANSPORTATION
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Brazilian
Airworthiness Directive 2016–07–01, dated
July 18, 2016, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2017–0250.
(2) For more information about this AD,
contact Todd Thompson, Aerospace
Engineer, International Branch, ANM–116,
FAA, 1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1175; fax
425–227–1149.
(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 this AD specifies otherwise.
(i) Embraer Service Bulletin 145–27–0115,
Revision 03, dated October 5, 2015.
(ii) Embraer Service Bulletin 145–27–0126,
dated October 6, 2015.
(3) For service information identified in
this AD, contact Empresa Brasileira de
Aeronautica S.A. (Embraer), Technical
Publications Section (PC 060), Av. Brigadeiro
˜
Faria Lima, 2170—Putim—12227—901 Sao
Jose dos Campos—SP—Brasil; telephone +55
12 3927–5852 or +55 12 3309–0732; fax +55
12 3927–7546; email distrib@embraer.com.br;
Internet https://www.flyembraer.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/ibrlocations.html.
Issued in Renton, Washington, on July 19,
2017.
Victor Wicklund,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–15807 Filed 7–31–17; 8:45 am]
mstockstill on DSK30JT082PROD with RULES
BILLING CODE 4910–13–P
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9307; Directorate
Identifier 2016–NM–076–AD; Amendment
39–18970; AD 2017–15–10]
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 787–9
airplanes. This AD was prompted by a
determination that the shoulder bolt
used on the outboard clevis of the
forward support fitting of the ram air
turbine (RAT) might not be long enough
to allow for proper installation of the
RAT; therefore, the clevis of the joint
could be clamped together, resulting in
reduced fatigue life and possible
fracture of the clevis. This AD requires
inspecting for cracking of the clevis of
the forward support fitting of the RAT,
installing a longer shoulder bolt, and
replacing the forward support fitting if
any cracking is found. We are issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective September 5,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of September 5, 2017.
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;
telephone 562–797–1717; 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–2016–
9307.
SUMMARY:
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9307; or in person at the Docket
17:30 Jul 31, 2017
Jkt 241001
PO 00000
Frm 00019
Fmt 4700
Sfmt 4700
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:
Examining the AD Docket
VerDate Sep<11>2014
35641
Kelly McGuckin, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, FAA, Seattle Aircraft Certification
Office (ACO), 1601 Lind Avenue SW.,
Renton, WA 98057–3356; phone: 425–
917–6490; fax: 425–917–6590; email:
kelly.mcguckin@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 787–9 airplanes. The NPRM
published in the Federal Register on
November 28, 2016 (81 FR 85448) (‘‘the
NPRM’’). The NPRM was prompted by
a determination that the shoulder bolt
used on the outboard clevis of the
forward support fitting of the RAT
might not be long enough to allow for
proper installation of the RAT;
therefore, the clevis of the joint could be
clamped together, resulting in reduced
fatigue life and possible fracture of the
clevis. The NPRM proposed to require
inspecting for cracking of the clevis of
the forward support fitting of the RAT,
installing a longer shoulder bolt, and
replacing the forward support fitting
with a new fitting if any cracking is
found. We are issuing this AD to
prevent fracture of the clevis of the
forward support fitting of the RAT,
which could result in the RAT departing
the airplane during a dual nonrestartable engine loss, and consequent
loss of control of the airplane, or injury
to maintenance crews during periodic
RAT ground tests.
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.
Support for the NPRM
Boeing and Ahmed Ahmed Hamdy
concur with the content of the NPRM.
E:\FR\FM\01AUR1.SGM
01AUR1
35642
Federal Register / Vol. 82, No. 146 / Tuesday, August 1, 2017 / Rules and Regulations
Request To Clarify Certain
Requirements
United Airlines (UAL) asked that we
clarify the credit language used in
paragraph (h) of the proposed AD. UAL
stated that, as written, paragraph (h) of
the proposed AD specifies that previous
accomplishment of Boeing Message
TBC–CAL–15–0089–01B, dated
September 22, 2015 (identified in
paragraph (h)(3) of the proposed AD),
provides credit for the actions required
by paragraph (g) of the proposed AD.
UAL noted that if the intent is to give
credit for all the actions specified in
paragraph (g) of the proposed AD, it’s
incorrect because that Boeing message
only provides procedures to replace the
subject bolt; the high frequency eddy
current (HFEC) inspection and fitting
replacement are not included in those
procedures.
We agree that clarification of
paragraph (h) of this AD is necessary.
We have revised paragraph (h) of this
AD to provide credit for the shoulder
bolt replacement specified in paragraph
(g) of this AD, if it was performed before
the effective date of this AD using the
applicable service information specified
in paragraph (h) of this AD.
mstockstill on DSK30JT082PROD with RULES
Request To Replace the Bolt Before
Accomplishing the Inspection
UAL asked that we allow replacement
of the shoulder bolt before
accomplishing the HFEC inspection,
which will shorten the time for the
replacement. UAL stated that the
12,000-flight-hour or 24-month time
limit to accomplish all actions in
paragraph (g) of the proposed AD is
understandable; however, due to the
possibility of extended downtime if the
fitting replacement is required, the
HFEC inspection must be done during a
heavy maintenance check, which could
be a considerable amount of time after
the effective date of the AD. UAL added
that Boeing Alert Service Bulletin B787–
81205–SB290031–00, Issue 001, dated
March 25, 2016, does not separate the
bolt replacement from the inspection,
but the proposed AD should provide
that option.
We do not agree with the commenter’s
request. A fracture of the clevis of the
forward support fitting of the RAT will
not be addressed by replacing the
subject bolt without an HFEC inspection
of the fitting. When operators replace
the bolt, they must also inspect the
fitting. Replacing the bolt without
inspecting this fitting could result in
undetected cracking in the fitting,
which is the cause of the unsafe
condition in this AD. Repetitive removal
and replacement of the bolt may also
cause further stress on the forward
support fitting, which could contribute
to additional cracking of the fitting,
especially if the fitting is already
cracked. Paragraph (h) of this AD
provides credit to operators that have
replaced the subject bolt prior to the
effective date of this AD. However, as of
the effective date of this AD, when
complying with paragraph (g) of this
AD, all corrective actions must be done
before further flight. We acknowledge
that replacing the fitting due to potential
inspection findings will require
significant effort and downtime;
however, only two airplanes of U.S.
Registry are affected by the
requirements of this AD. With a limited
number of airplanes affected and a
relatively long compliance time
provided, operators should have
adequate time to schedule the
maintenance for accomplishing the
actions required by this AD. Therefore,
we have made no changes to this AD in
this regard.
Request To Change Unsafe Condition
One commenter, Julia Stotts, asked
that we change the unsafe condition
identified in the NPRM from ‘‘. . . to
prevent fracture of the clevis of the
forward support fitting of the RAT,
which could result in the RAT departing
the airplane during a dual nonrestartable engine loss, and consequent
loss of control of the airplane, or injury
to maintenance crews during periodic
RAT ground tests’’ to ‘‘. . . detect and
correct fatigue cracking in the forward
engine mounts, which could result in
reduced structural integrity of the
airplane and could lead to in-flight loss
of an engine, possibly resulting in
reduced controllability of the airplane.’’
The commenter suggested the change to
encompass both fracture of the clevis
and the possibility of the RAT departing
from the airplane, which could lead to
loss of an engine.
We do not agree with the commenter’s
request. The commenter provided no
justification for revising the unsafe
condition to include fatigue cracking in
the forward engine mounts and possible
loss of an engine. The unsafe condition
in this AD stems from a determination
that the shoulder bolt used on the
outboard clevis of the forward support
fitting of the RAT might not be long
enough to allow for proper installation
of the RAT; therefore, the clevis of the
joint could be clamped together,
resulting in reduced fatigue life and
possible fracture of the clevis causing
possible departure of the RAT from the
airplane. The suggested change is not
related to the identified unsafe
condition or the potential end level
effect resulting from that unsafe
condition. We have made no changes to
this AD in this regard.
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 B787–81205–SB290031–00,
Issue 001, dated March 25, 2016. The
service information describes
procedures for inspecting for cracking of
the clevis of the forward support fitting
of the RAT, installing a longer shoulder
bolt, and replacing the forward support
fitting with a new fitting if any cracking
is found. 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 2
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Inspection/shoulder bolt replacement .............
3 work-hours × $85 per hour = $255 .............
VerDate Sep<11>2014
17:30 Jul 31, 2017
Jkt 241001
PO 00000
Frm 00020
Fmt 4700
Sfmt 4700
Parts cost
E:\FR\FM\01AUR1.SGM
$152
01AUR1
Cost per
product
$407
Cost on U.S.
operators
$814
Federal Register / Vol. 82, No. 146 / Tuesday, August 1, 2017 / Rules and Regulations
We estimate the following costs to do
any necessary replacements of the
forward support fitting that would be
required based on the results of the
inspection. We have no way of
35643
determining the number of aircraft that
might need these replacements:
ON-CONDITION COSTS
Action
Labor cost
Forward support fitting replacement .............................
15 work-hours × $85 per hour = $1,275 ......................
According to the manufacturer, some
of the costs of this AD may be covered
under warranty, thereby reducing the
cost impact on affected individuals. We
do not control warranty coverage for
affected individuals. As a result, we
have included all costs in our cost
estimate.
mstockstill on DSK30JT082PROD 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.
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.
VerDate Sep<11>2014
17:30 Jul 31, 2017
Jkt 241001
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):
■
2017–15–10 The Boeing Company:
Amendment 39–18970; Docket No.
FAA–2016–9307; Directorate Identifier
2016–NM–076–AD.
(a) Effective Date
This AD is effective September 5, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 787–9 airplanes, certificated in any
category, as identified in Boeing Alert
Service Bulletin B787–81205–SB290031–00,
Issue 001, dated March 25, 2016.
(d) Subject
Air Transport Association (ATA) of
America Code 29; Hydraulic power.
(e) Unsafe Condition
This AD was prompted by a determination
that the shoulder bolt used on the outboard
clevis of the forward support fitting of the
ram air turbine (RAT) might not be long
enough to allow for proper installation of the
RAT; therefore, the clevis of the joint could
be clamped together, resulting in reduced
fatigue life and possible fracture of the clevis.
We are issuing this AD to prevent fracture of
the clevis of the forward support fitting of the
RAT, which could result in the RAT
departing the airplane during a dual nonrestartable engine loss, and consequent loss
of control of the airplane, or injury to
maintenance crews during periodic RAT
ground tests.
PO 00000
Frm 00021
Fmt 4700
Sfmt 4700
Parts cost
$28,309
Cost per
product
$29,584
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection, Replacement of Shoulder
Bolt, and Replacement of RAT Forward
Support Fitting if Necessary
Within 12,000 flight hours or 24 months
after the effective date of this AD, whichever
occurs first: Do a high frequency eddy
current inspection for cracking of the clevis
of the forward support fitting of the RAT, and
install a longer shoulder bolt, in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin B787–81205–
SB290031–00, Issue 001, dated March 25,
2016. If any cracking is found, before further
flight, replace the RAT forward support
fitting with a new fitting, in accordance with
the Accomplishment Instructions of Boeing
Alert Service Bulletin B787–81205–
SB290031–00, Issue 001, dated March 25,
2016.
(h) Credit for Previous Actions
This paragraph provides credit for the
shoulder bolt replacement specified in
paragraph (g) of this AD, if that action was
performed before the effective date of this AD
using the applicable service information
specified in paragraph (h)(1), (h)(2), (h)(3), or
(h)(4) of this AD.
(1) Boeing Message TBC–ANA–15–0272–
01B, dated September 22, 2015.
(2) Boeing Message TBC–ANZ–15–0016–
06B, dated October 14, 2015.
(3) Boeing Message TBC–CAL–15–0089–
01B, dated September 22, 2015.
(4) Boeing Message TBC–VAA–15–0089–
01B dated September 22, 2015.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (j)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-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,
E:\FR\FM\01AUR1.SGM
01AUR1
35644
Federal Register / Vol. 82, No. 146 / Tuesday, August 1, 2017 / Rules and Regulations
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, Seattle
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) For service information that contains
steps that are labeled as Required for
Compliance (RC), the provisions of
paragraphs (i)(4)(i) and (i)(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. 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.
mstockstill on DSK30JT082PROD with RULES
(j) Related Information
(1) For more information about this AD,
contact Kelly McGuckin, Aerospace
Engineer, Systems and Equipment Branch,
ANM–130S, FAA, Seattle ACO, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6490; fax: 425–917–6590;
email: kelly.mcguckin@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (k)(3) and (k)(4) of this AD.
(k) 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 B787–
81205–SB290031–00, Issue 001, dated March
25, 2016.
(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;
telephone 562–797–1717; 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/ibrlocations.html.
VerDate Sep<11>2014
17:30 Jul 31, 2017
Jkt 241001
Issued in Renton, Washington, on July 14,
2017.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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–
9055; 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: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–2125;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
We are adopting a new
airworthiness directive (AD) for certain
Airbus Model A300 B4–600R series
airplanes, Model A300 C4–605R Variant
F airplanes, and Model A300 F4–600R
series airplanes. This AD was prompted
by the results of a full stress analysis of
the lower area of a certain frame that
revealed that a crack could occur in this
area after a certain number of flight
cycles. This AD requires an inspection
of the lower area of a certain frame
radius for cracking, and corrective
action if necessary. We are issuing this
AD to address the unsafe condition on
these products.
DATES: This AD is effective September 5,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of September 5, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EAW, 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
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–2016–9055.
Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 by adding an AD
that would apply to certain Airbus
Model A300 B4–600R series airplanes,
Model A300 C4–605R Variant F
airplanes, and Model A300 F4–600R
series airplanes. The SNPRM published
in the Federal Register on March 2,
2017 (82 FR 12314) (‘‘the SNPRM’’). We
preceded the SNPRM with a notice of
proposed rulemaking (NPRM) that
published in the Federal Register on
September 8, 2016 (81 FR 62026) (‘‘the
NPRM’’). The NPRM proposed to
require an inspection of the lower area
of a certain frame radius for cracking,
and corrective action if necessary. The
NPRM was prompted by the results of
a full stress analysis of the lower area of
a certain frame that revealed a crack
could occur in the forward fitting lower
radius of a certain frame after a certain
number of flight cycles. The SNPRM
proposed to require extending the area
to be inspected for cracking and adding
an inspection for previously inspected
airplanes. We are issuing this AD to
detect and correct cracking in the
forward fitting lower radius of a certain
frame. Such cracking could reduce the
structural integrity of the fuselage.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2016–0179,
dated September 12, 2016 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
[FR Doc. 2017–15486 Filed 7–31–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9055; Directorate
Identifier 2016–NM–071–AD; Amendment
39–18977; AD 2017–15–17]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
AGENCY:
SUMMARY:
PO 00000
Frm 00022
Fmt 4700
Sfmt 4700
E:\FR\FM\01AUR1.SGM
01AUR1
Agencies
[Federal Register Volume 82, Number 146 (Tuesday, August 1, 2017)]
[Rules and Regulations]
[Pages 35641-35644]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-15486]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9307; Directorate Identifier 2016-NM-076-AD;
Amendment 39-18970; AD 2017-15-10]
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 787-9 airplanes. This AD was prompted by a
determination that the shoulder bolt used on the outboard clevis of the
forward support fitting of the ram air turbine (RAT) might not be long
enough to allow for proper installation of the RAT; therefore, the
clevis of the joint could be clamped together, resulting in reduced
fatigue life and possible fracture of the clevis. This AD requires
inspecting for cracking of the clevis of the forward support fitting of
the RAT, installing a longer shoulder bolt, and replacing the forward
support fitting if any cracking is found. We are issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective September 5, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of September 5,
2017.
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; telephone 562-797-1717; 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-2016-9307.
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-
9307; 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: Kelly McGuckin, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6490; fax: 425-917-6590; email:
kelly.mcguckin@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 787-9 airplanes. The NPRM published in the Federal Register on
November 28, 2016 (81 FR 85448) (``the NPRM''). The NPRM was prompted
by a determination that the shoulder bolt used on the outboard clevis
of the forward support fitting of the RAT might not be long enough to
allow for proper installation of the RAT; therefore, the clevis of the
joint could be clamped together, resulting in reduced fatigue life and
possible fracture of the clevis. The NPRM proposed to require
inspecting for cracking of the clevis of the forward support fitting of
the RAT, installing a longer shoulder bolt, and replacing the forward
support fitting with a new fitting if any cracking is found. We are
issuing this AD to prevent fracture of the clevis of the forward
support fitting of the RAT, which could result in the RAT departing the
airplane during a dual non-restartable engine loss, and consequent loss
of control of the airplane, or injury to maintenance crews during
periodic RAT ground tests.
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.
Support for the NPRM
Boeing and Ahmed Ahmed Hamdy concur with the content of the NPRM.
[[Page 35642]]
Request To Clarify Certain Requirements
United Airlines (UAL) asked that we clarify the credit language
used in paragraph (h) of the proposed AD. UAL stated that, as written,
paragraph (h) of the proposed AD specifies that previous accomplishment
of Boeing Message TBC-CAL-15-0089-01B, dated September 22, 2015
(identified in paragraph (h)(3) of the proposed AD), provides credit
for the actions required by paragraph (g) of the proposed AD. UAL noted
that if the intent is to give credit for all the actions specified in
paragraph (g) of the proposed AD, it's incorrect because that Boeing
message only provides procedures to replace the subject bolt; the high
frequency eddy current (HFEC) inspection and fitting replacement are
not included in those procedures.
We agree that clarification of paragraph (h) of this AD is
necessary. We have revised paragraph (h) of this AD to provide credit
for the shoulder bolt replacement specified in paragraph (g) of this
AD, if it was performed before the effective date of this AD using the
applicable service information specified in paragraph (h) of this AD.
Request To Replace the Bolt Before Accomplishing the Inspection
UAL asked that we allow replacement of the shoulder bolt before
accomplishing the HFEC inspection, which will shorten the time for the
replacement. UAL stated that the 12,000-flight-hour or 24-month time
limit to accomplish all actions in paragraph (g) of the proposed AD is
understandable; however, due to the possibility of extended downtime if
the fitting replacement is required, the HFEC inspection must be done
during a heavy maintenance check, which could be a considerable amount
of time after the effective date of the AD. UAL added that Boeing Alert
Service Bulletin B787-81205-SB290031-00, Issue 001, dated March 25,
2016, does not separate the bolt replacement from the inspection, but
the proposed AD should provide that option.
We do not agree with the commenter's request. A fracture of the
clevis of the forward support fitting of the RAT will not be addressed
by replacing the subject bolt without an HFEC inspection of the
fitting. When operators replace the bolt, they must also inspect the
fitting. Replacing the bolt without inspecting this fitting could
result in undetected cracking in the fitting, which is the cause of the
unsafe condition in this AD. Repetitive removal and replacement of the
bolt may also cause further stress on the forward support fitting,
which could contribute to additional cracking of the fitting,
especially if the fitting is already cracked. Paragraph (h) of this AD
provides credit to operators that have replaced the subject bolt prior
to the effective date of this AD. However, as of the effective date of
this AD, when complying with paragraph (g) of this AD, all corrective
actions must be done before further flight. We acknowledge that
replacing the fitting due to potential inspection findings will require
significant effort and downtime; however, only two airplanes of U.S.
Registry are affected by the requirements of this AD. With a limited
number of airplanes affected and a relatively long compliance time
provided, operators should have adequate time to schedule the
maintenance for accomplishing the actions required by this AD.
Therefore, we have made no changes to this AD in this regard.
Request To Change Unsafe Condition
One commenter, Julia Stotts, asked that we change the unsafe
condition identified in the NPRM from ``. . . to prevent fracture of
the clevis of the forward support fitting of the RAT, which could
result in the RAT departing the airplane during a dual non-restartable
engine loss, and consequent loss of control of the airplane, or injury
to maintenance crews during periodic RAT ground tests'' to ``. . .
detect and correct fatigue cracking in the forward engine mounts, which
could result in reduced structural integrity of the airplane and could
lead to in-flight loss of an engine, possibly resulting in reduced
controllability of the airplane.'' The commenter suggested the change
to encompass both fracture of the clevis and the possibility of the RAT
departing from the airplane, which could lead to loss of an engine.
We do not agree with the commenter's request. The commenter
provided no justification for revising the unsafe condition to include
fatigue cracking in the forward engine mounts and possible loss of an
engine. The unsafe condition in this AD stems from a determination that
the shoulder bolt used on the outboard clevis of the forward support
fitting of the RAT might not be long enough to allow for proper
installation of the RAT; therefore, the clevis of the joint could be
clamped together, resulting in reduced fatigue life and possible
fracture of the clevis causing possible departure of the RAT from the
airplane. The suggested change is not related to the identified unsafe
condition or the potential end level effect resulting from that unsafe
condition. We have made no changes to this AD in this regard.
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 B787-81205-SB290031-00,
Issue 001, dated March 25, 2016. The service information describes
procedures for inspecting for cracking of the clevis of the forward
support fitting of the RAT, installing a longer shoulder bolt, and
replacing the forward support fitting with a new fitting if any
cracking is found. 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 2 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspection/shoulder bolt 3 work-hours x $85 per hour $152 $407 $814
replacement. = $255.
----------------------------------------------------------------------------------------------------------------
[[Page 35643]]
We estimate the following costs to do any necessary replacements of
the forward support fitting 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 replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Forward support fitting replacement........ 15 work-hours x $85 per hour = $28,309 $29,584
$1,275.
----------------------------------------------------------------------------------------------------------------
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2017-15-10 The Boeing Company: Amendment 39-18970; Docket No. FAA-
2016-9307; Directorate Identifier 2016-NM-076-AD.
(a) Effective Date
This AD is effective September 5, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 787-9 airplanes,
certificated in any category, as identified in Boeing Alert Service
Bulletin B787-81205-SB290031-00, Issue 001, dated March 25, 2016.
(d) Subject
Air Transport Association (ATA) of America Code 29; Hydraulic
power.
(e) Unsafe Condition
This AD was prompted by a determination that the shoulder bolt
used on the outboard clevis of the forward support fitting of the
ram air turbine (RAT) might not be long enough to allow for proper
installation of the RAT; therefore, the clevis of the joint could be
clamped together, resulting in reduced fatigue life and possible
fracture of the clevis. We are issuing this AD to prevent fracture
of the clevis of the forward support fitting of the RAT, which could
result in the RAT departing the airplane during a dual non-
restartable engine loss, and consequent loss of control of the
airplane, or injury to maintenance crews during periodic RAT ground
tests.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection, Replacement of Shoulder Bolt, and Replacement of RAT
Forward Support Fitting if Necessary
Within 12,000 flight hours or 24 months after the effective date
of this AD, whichever occurs first: Do a high frequency eddy current
inspection for cracking of the clevis of the forward support fitting
of the RAT, and install a longer shoulder bolt, in accordance with
the Accomplishment Instructions of Boeing Alert Service Bulletin
B787-81205-SB290031-00, Issue 001, dated March 25, 2016. If any
cracking is found, before further flight, replace the RAT forward
support fitting with a new fitting, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin B787-
81205-SB290031-00, Issue 001, dated March 25, 2016.
(h) Credit for Previous Actions
This paragraph provides credit for the shoulder bolt replacement
specified in paragraph (g) of this AD, if that action was performed
before the effective date of this AD using the applicable service
information specified in paragraph (h)(1), (h)(2), (h)(3), or (h)(4)
of this AD.
(1) Boeing Message TBC-ANA-15-0272-01B, dated September 22,
2015.
(2) Boeing Message TBC-ANZ-15-0016-06B, dated October 14, 2015.
(3) Boeing Message TBC-CAL-15-0089-01B, dated September 22,
2015.
(4) Boeing Message TBC-VAA-15-0089-01B dated September 22, 2015.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in paragraph (j)(1) of this AD.
Information may be emailed to: 9-ANM-Seattle-ACO-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,
[[Page 35644]]
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, Seattle
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) For service information that contains steps that are labeled
as Required for Compliance (RC), the provisions of paragraphs
(i)(4)(i) and (i)(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. 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.
(j) Related Information
(1) For more information about this AD, contact Kelly McGuckin,
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA,
Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone:
425-917-6490; fax: 425-917-6590; email: kelly.mcguckin@faa.gov.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (k)(3) and (k)(4) of this AD.
(k) 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 B787-81205-SB290031-00, Issue
001, dated March 25, 2016.
(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;
telephone 562-797-1717; 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 July 14, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-15486 Filed 7-31-17; 8:45 am]
BILLING CODE 4910-13-P