Airworthiness Directives; Bombardier, Inc., Airplanes, 38626-38629 [2017-16777]
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Federal Register / Vol. 82, No. 156 / Tuesday, August 15, 2017 / Proposed Rules
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(k) Related Information
(1) For more information about this AD,
contact Alan Pohl, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch,
1601 Lind Avenue SW., Renton, WA 98057–
3356; phone: 425–917–6450; fax: 425–917–
6590; email: alan.pohl@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; Internet https://
www.myboeingfleet.com. You may view this
referenced service information at the FAA,
Transport Standards Branch, 1601 Lind
Avenue SW., Renton, WA. For information
on the availability of this material at the
FAA, call 425–227–1221.
Issued in Renton, Washington, on August
2, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
[FR Doc. 2017–16780 Filed 8–14–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0775; Product
Identifier 2017–NM–048–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2016–25–
18, for certain Bombardier, Inc., Model
BD–700–1A10 and BD–700–1A11
airplanes. AD 2016–25–18 requires an
inspection for discrepancies of the
attachment points of the links between
the engine rear mount assemblies, and
corrective actions if necessary. Since we
issued AD 2016–25–18, we have
determined that replacement of certain
nuts and bolts in the engine rear mount
assemblies is necessary. This proposed
AD would require an inspection of
certain attachment points, corrective
action if necessary, and replacement of
certain bolts and nuts in the engine rear
mount assemblies. This proposed AD
also adds airplanes to the applicability.
mstockstill on DSK30JT082PROD with PROPOSALS
SUMMARY:
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We are proposing this AD to address the
unsafe condition on these products.
DATES: We must receive comments on
this proposed AD by September 29,
2017.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Bombardier, Inc.,
ˆ
400 Cote-Vertu Road West, Dorval,
´
Quebec H4S 1Y9, Canada; telephone
514–855–5000; fax 514–855–7401; email
thd.crj@aero.bombardier.com; Internet
https://www.bombardier.com. You may
view this referenced service information
at the FAA, Transport Standards
Branch, 1601 Lind Avenue SW., Renton,
WA. For information on the availability
of this material at the FAA, call 425–
227–1221.
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–
0775; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Aziz
Ahmed, Airframe Engineer, Airframe
and Mechanical Systems Section, FAA,
New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY
11590; telephone: 516–228–7329; fax:
516–794–5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
PO 00000
Frm 00014
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2017–0775; Product Identifier 2017–
NM–048–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On December 2, 2016, we issued AD
2016–25–18, Amendment 39–18744 (81
FR 90961, December 16, 2016) (‘‘AD
2016–25–18’’), for certain Bombardier,
Inc., Model BD–700–1A10 and BD–700–
1A11 airplanes. AD 2016–25–18 was
prompted by a report indicating that
during maintenance, an engine mount
pin was found backed out of the rear
mount link, and the associated retaining
bolt was also found fractured. AD 2016–
25–18 requires an inspection for
discrepancies of the attachment points
of the links between the engine rear
mount assemblies, and corrective
actions if necessary. We issued AD
2016–25–18 to detect and correct broken
engine attachment hardware, which
could result in separation of an engine
from the airplane.
Since we issued AD 2016–25–18, we
have determined that replacement of
certain nuts and bolts in the engine rear
mount assemblies is necessary.
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian AD
CF–2016–23R1, dated February 20, 2017
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ’’the MCAI’’), to correct an unsafe
condition for certain Bombardier, Inc.,
Model BD–700–1A10 and BD–700–
1A11 airplanes. The MCAI states:
Bombardier reported that during
maintenance of a BD–700 aeroplane, the
engine mount pin, part number (P/N)
BRR15838, was found backed out of the rear
mount link. The retaining bolt, P/N AS54020,
which passes through the engine mount pin
was also found fractured at the groove which
holds the locking spring. An investigation
revealed the most probable root cause of
failure to be a single axial tension static
overload, with no evidence of fatigue
contributing to the failure.
The above condition if not detected, may
result in the loss of engine attachment to the
airframe.
As an interim corrective action,
Bombardier issued Service Bulletins (SBs)
700–71–002, 700–71–6002, 700–71–5002,
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Federal Register / Vol. 82, No. 156 / Tuesday, August 15, 2017 / Proposed Rules
and 700–1A11–71–002 to inspect the
attachment points of the links between the
engine rear mount assemblies, and install
replacement hardware if required.
The original version of this [Canadian] AD
was issued to mandate incorporation of the
above Bombardier SBs to inspect and
maintain integrity of the affected engine rear
mount assembly.
Revision 1 of this [Canadian] AD is issued
to mandate incorporation of the Bombardier
SBs 700–71–003, 700–71–6003, 700–71–
5003, and 700–1A11–71–003 to replace the
existing bolts and self-locking nuts with new
bolts and nuts, as a final corrective action.
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The MCAI also adds airplanes having
serial numbers 9764, 9766, and 9771
through 9785 inclusive to the
applicability. Those airplanes are also
affected by the identified unsafe
condition. You may examine the MCAI
in the AD docket on the Internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2017–
0775.
Related Service Information Under 1
CFR Part 51
Bombardier has issued the following
service information.
• Bombardier Service Bulletin 700–
71–002, Revision 01, dated June 30,
2016.
• Bombardier Service Bulletin 700–
71–5002, Revision 01, dated June 30,
2016.
• Bombardier Service Bulletin 700–
71–6002, Revision 01, dated June 30,
2016.
• Bombardier Service Bulletin 700–
1A11–71–002, Revision 01, dated June
30, 2016.
This service information describes
procedures for an inspection for
discrepancies of the attachment points
of the links between the engine rear
mount assemblies and corrective
actions. These documents are distinct
since they apply to different airplane
models and serial numbers.
Bombardier has also issued the
following service information. The
service information describes
procedures for nut and bolt
replacement. These documents are
distinct since they apply to different
airplane models and serial numbers.
• Bombardier Service Bulletin 700–
71–003, dated December 5, 2016.
• Bombardier Service Bulletin 700–
71–5003, dated December 5, 2016.
• Bombardier Service Bulletin 700–
71–6003, dated December 5, 2016.
• Bombardier Service Bulletin 700–
1A11–71–003, dated December 5, 2016.
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.
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FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Costs of Compliance
We estimate that this proposed AD
affects 97 airplanes of U.S. registry.
The actions required by AD 2016–25–
18, and retained in this proposed AD
take about 1 work-hour per product, at
an average labor rate of $85 per workhour. Based on these figures, the
estimated cost of the actions that are
required by AD 2016–25–18 is $85 per
product.
The retained on-condition costs in
this proposed AD take about 2 workhours per product, at an average labor
rate of $85 per work-hour. Required
parts cost about $730 per product. Based
on these figures, the estimated cost of
the on-condition actions that are
required by AD 2016–25–18 is $900 per
product.
We have received no definitive data
that would enable us to provide cost
estimates for other retained oncondition actions specified in AD 2016–
25–18.
We also estimate that it would take
about 4 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Required
parts would cost up to $14,940 per
product. Based on these figures, we
estimate the cost of this proposed AD on
U.S. operators to be up to $1,482,160, or
up to $15,280 per product.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
According to the manufacturer, some
of the costs of this proposed AD may be
covered under warranty, thereby
reducing the cost impact on affected
individuals. We do not control warranty
coverage for affected individuals. As a
result, we have included all available
costs in our cost estimate.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
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38627
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
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
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Federal Register / Vol. 82, No. 156 / Tuesday, August 15, 2017 / Proposed Rules
the FAA proposes to amend 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
removing Airworthiness Directive (AD)
2016–25–18, Amendment 39–18744 (81
FR 90961, December 16, 2016), and
adding the following new AD:
■
Bombardier, Inc.: Docket No. FAA–2017–
0775; Product Identifier 2017–NM–048–
AD.
(a) Comments Due Date
We must receive comments by September
29, 2017.
(b) Affected ADs
This AD replaces AD 2016–25–18,
Amendment 39–18744 (81 FR 90961,
December 16, 2016) (‘‘AD 2016–25–18’’).
(c) Applicability
This AD applies to Bombardier, Inc.,
Model BD–700–1A10 and BD–700–1A11
airplanes, certificated in any category, serial
numbers (S/Ns) 9002 through 9785 inclusive,
and 9998.
(d) Subject
Air Transport Association (ATA) of
America Code 72, Engine.
(e) Reason
This AD was prompted by a report
indicating that during maintenance, an
engine mount pin was found backed out of
the rear mount link, and the associated
retaining bolt was also found fractured at the
groove that holds the locking spring. We are
issuing this AD to detect and correct broken
engine attachment hardware, which could
result in separation of an engine from the
airplane.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Inspection, With No Changes
This paragraph restates the requirements of
paragraph (g) of AD 2016–25–18, with no
changes. For airplanes having S/Ns 9002
through 9763 inclusive, 9765, 9767 through
9770 inclusive, and 9998: Within 500 flight
hours or 4 months, whichever occurs first
after January 3, 2017 (the effective date of AD
2016–25–18), do an inspection for
discrepancies of the engine rear mount
assemblies (including missing or broken
bolts, missing nuts, incorrect torque values,
and an incorrect gap between the bushing
and washer); in accordance with Part A of the
Accomplishment Instructions of the
applicable service information specified in
paragraphs (g)(1) through (g)(4) of this AD.
Accomplishing the actions required by
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paragraphs (j) and (k) of this AD terminates
the requirements of this paragraph.
(1) Bombardier Service Bulletin 700–71–
002, Revision 01, dated June 30, 2016 (for
Bombardier Model BD–700–1A10 airplanes).
(2) Bombardier Service Bulletin 700–71–
6002, Revision 01, dated June 30, 2016 (for
Bombardier Model BD–700–1A10 airplanes).
(3) Bombardier Service Bulletin 700–71–
5002, Revision 01, dated June 30, 2016 (for
Bombardier Model BD–700–1A11 airplanes).
(4) Bombardier Service Bulletin 700–
1A11–71–002, Revision 01, dated June 30,
2016 (for Bombardier Model BD–700–1A11
airplanes).
(h) Retained Corrective Action for Paragraph
(g) of This AD, With No Changes
This paragraph restates the requirements of
paragraph (h) of AD 2016–25–18, with no
changes. If any discrepancy is detected
during the inspection required by paragraph
(g) of this AD, before further flight, replace
missing parts and correct noncompliant gaps
and bolt torque, as specified in the
Accomplishment Instructions of the
applicable service information specified in
paragraphs (g)(1) through (g)(4) of this AD,
except as required by paragraph (i) of this
AD. Accomplishing the actions required by
paragraphs (j) and (k) of this AD terminates
the requirements of this paragraph.
(i) Retained Exception to Service
Information Specifications, With No
Changes
This paragraph restates the requirements of
paragraph (i) of AD 2016–25–18, with no
changes. Where the applicable Bombardier
service bulletin specified in paragraphs (g)(1)
through (g)(4) of this AD provides no
instructions for corrective actions, or
specifies to contact Bombardier for
appropriate action, accomplish corrective
actions in accordance with the procedures
specified in paragraph (o)(2) of this AD.
(j) New Requirement of This AD: Gap
Measurement
Within 1,000 flight hours or 12 months,
whichever occurs first after the effective date
of this AD: Measure the gaps between the
applicable shouldered bushing fitted on the
mount beam and the washer; and between
the applicable engine ring lug and the head
of the mount pin to determine if the gaps are
within acceptable limits; in accordance with
Part A of the Accomplishment Instructions of
the applicable service information specified
in paragraphs (j)(1) through (j)(4) of this AD.
Accomplishing the actions required by
paragraphs (j) and (k) of this AD terminates
the requirements of paragraphs (g) and (h) of
this AD.
(1) Bombardier Service Bulletin 700–71–
003, dated December 5, 2016 (for Bombardier
Model BD–700–1A10 airplanes).
(2) Bombardier Service Bulletin 700–71–
6003, dated December 5, 2016 (for
Bombardier Model BD–700–1A10 airplanes).
(3) Bombardier Service Bulletin 700–71–
5003, dated December 5, 2016 (for
Bombardier Model BD–700–1A11 airplanes).
(4) Bombardier Service Bulletin 700–
1A11–71–003, dated December 5, 2016 (for
Bombardier Model BD–700–1A11 airplanes).
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(k) New Requirement of This AD: Nut and
Bolt Replacement, and Gap Measurement
Within 1,000 flight hours or 12 months,
whichever occurs first after the effective date
of this AD: Replace the nuts having part
number (P/N) AS54365 and the bolts having
P/N AS54020 and AS54002 in the engine rear
mount assembly with new nuts and new
bolts; and do the gap measurement to
determine if the gap is within acceptable
limits; in accordance with Part B of the
Accomplishment Instructions the applicable
service information specified in paragraphs
(j)(1) through (j)(4) of this AD.
(l) New Requirement of This AD: Corrective
Action
If any gap is detected, during any
measurement required by paragraph (j) or (k)
of this AD, that is not within the applicable
limits specified in the service information
specified in paragraphs (j)(1) through (j)(4) of
this AD, before further flight repair using a
method approved by the Manager, New York
ACO Branch, FAA; or Transport Canada Civil
Aviation (TCCA); or Bombardier, Inc.’s TCCA
Design Approval Organization (DAO).
(m) No Reporting Required
Although the service information
identified in paragraphs (j)(1) through (j)(4) of
this AD specifies to submit certain
information to the manufacturer, this AD
does not include that requirement.
(n) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraphs (g) and (h) of this AD,
if those actions were performed before
January 3, 2017 (the effective date of AD
2016–25–18), in accordance with the
Accomplishment Instructions of the
applicable service information specified in
paragraphs (n)(1) through (n)(4) of this AD.
(1) Bombardier Service Bulletin 700–71–
002, dated May 31, 2016.
(2) Bombardier Service Bulletin 700–71–
6002, dated May 31, 2016.
(3) Bombardier Service Bulletin 700–71–
5002, dated May 31, 2016.
(4) Bombardier Service Bulletin 700–
1A11–71–002, dated May 31, 2016.
(o) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York 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 ATTN: Program Manager,
Continuing Operational Safety, FAA, New
York ACO Branch, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone:
516–228–7300; fax: 516–794–5531. 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.
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Federal Register / Vol. 82, No. 156 / Tuesday, August 15, 2017 / Proposed Rules
(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, New York ACO Branch,
FAA; or TCCA; or Bombardier, Inc.’s TCCA
DAO. If approved by the DAO, the approval
must include the DAO-authorized signature.
(p) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive 2016–23R1, dated
February 20, 2017, 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–2017–0775.
(2) For more information about this AD,
contact Aziz Ahmed, Airframe Engineer,
Airframe and Mechanical Systems Section,
FAA, New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590;
telephone: 516–228–7329; fax: 516–794–
5531.
(3) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; email thd.crj@
aero.bombardier.com; Internet https://
www.bombardier.com. You may view this
service information at the FAA, Transport
Standards Branch, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA, call
425–227–1221.
Issued in Renton, Washington, on August
2, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
[FR Doc. 2017–16777 Filed 8–14–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0771; Product
Identifier 2016–NM–212–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
mstockstill on DSK30JT082PROD with PROPOSALS
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2015–09–
07, which applies to all The Boeing
Company Model 787 airplanes. AD
2015–09–07 requires a repetitive
maintenance task for electrical power
deactivation. Since we issued AD 2015–
09–07, Boeing has developed new
software for the generator control unit
SUMMARY:
VerDate Sep<11>2014
16:14 Aug 14, 2017
Jkt 241001
(GCU) that addresses the software
counter overflow anomaly that
prompted the issuance of AD 2015–09–
07. This proposed AD would require
installing the new GCU software. This
proposed AD would also remove certain
airplanes from the applicability. We are
proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on
this proposed AD by September 29,
2017.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster
Blvd., MC 110–SK57, Seal Beach, CA
90740–5600; telephone 562–797–1717;
Internet https://
www.myboeingfleet.com. You may view
this referenced service information at
the FAA, Transport Standards Branch,
1601 Lind Avenue SW., Renton, WA.
For information on the availability of
this material at the FAA, call 425–227–
1221. It is also available on the Internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2017–0771.
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–
0771; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Stephen Oshiro, Aerospace Engineer,
Systems and Equipment Section, FAA,
Seattle ACO Branch, 1601 Lind Avenue
PO 00000
Frm 00017
Fmt 4702
Sfmt 4702
38629
SW., Renton, WA 98057–3356; phone:
425–917–6480; fax: 425–917–6590;
email: Stephen.Oshiro@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2017–0771; Product Identifier 2016–
NM–212–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On April 23, 2015, we issued AD
2015–09–07, Amendment 39–18153 (80
FR 24789, May 1, 2015) (‘‘AD 2015–09–
07’’), for all The Boeing Company Model
787 airplanes. AD 2015–09–07 requires
a repetitive maintenance task for
electrical power deactivation on Model
787 airplanes. AD 2015–09–07 resulted
from the determination that a Model 787
airplane that has been powered
continuously for 248 days can lose all
alternating current (AC) electrical power
due to the GCUs simultaneously going
into failsafe mode. This condition is
caused by a software counter internal to
the GCUs that will overflow after 248
days of continuous power. We issued
AD 2015–09–07 to prevent loss of all AC
electrical power, which could result in
loss of control of the airplane.
Actions Since AD 2015–09–07 Was
Issued
The preamble to AD 2015–09–07
specifies that we consider the
requirements ‘‘interim action’’ and that
the manufacturer is developing a
modification to address the unsafe
condition. That AD explains that we
might consider further rulemaking if a
modification is developed, approved,
and available. Since we issued AD
2015–09–07, Boeing has developed new
software for the Model 787 GCU that
addresses the software counter overflow
anomaly that prompted the issuance of
AD 2015–09–07. Installation of the new
software eliminates the need for
performing the repetitive maintenance
E:\FR\FM\15AUP1.SGM
15AUP1
]]>Agencies
[Federal Register Volume 82, Number 156 (Tuesday, August 15, 2017)]
[Proposed Rules]
[Pages 38626-38629]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-16777]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0775; Product Identifier 2017-NM-048-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc., Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2016-25-
18, for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11
airplanes. AD 2016-25-18 requires an inspection for discrepancies of
the attachment points of the links between the engine rear mount
assemblies, and corrective actions if necessary. Since we issued AD
2016-25-18, we have determined that replacement of certain nuts and
bolts in the engine rear mount assemblies is necessary. This proposed
AD would require an inspection of certain attachment points, corrective
action if necessary, and replacement of certain bolts and nuts in the
engine rear mount assemblies. This proposed AD also adds airplanes to
the applicability. We are proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on this proposed AD by September 29,
2017.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec
H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-7401; email
thd.crj@aero.bombardier.com; Internet https://www.bombardier.com. You
may view this referenced service information at the FAA, Transport
Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on
the availability of this material at the FAA, call 425-227-1221.
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-
0775; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Airframe Engineer,
Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600
Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 516-228-7329;
fax: 516-794-5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2017-0775;
Product Identifier 2017-NM-048-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this proposed AD. We will consider
all comments received by the closing date and may amend this proposed
AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On December 2, 2016, we issued AD 2016-25-18, Amendment 39-18744
(81 FR 90961, December 16, 2016) (``AD 2016-25-18''), for certain
Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. AD 2016-
25-18 was prompted by a report indicating that during maintenance, an
engine mount pin was found backed out of the rear mount link, and the
associated retaining bolt was also found fractured. AD 2016-25-18
requires an inspection for discrepancies of the attachment points of
the links between the engine rear mount assemblies, and corrective
actions if necessary. We issued AD 2016-25-18 to detect and correct
broken engine attachment hardware, which could result in separation of
an engine from the airplane.
Since we issued AD 2016-25-18, we have determined that replacement
of certain nuts and bolts in the engine rear mount assemblies is
necessary.
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian AD CF-2016-23R1, dated
February 20, 2017 (referred to after this as the Mandatory Continuing
Airworthiness Information, or ''the MCAI''), to correct an unsafe
condition for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-
1A11 airplanes. The MCAI states:
Bombardier reported that during maintenance of a BD-700
aeroplane, the engine mount pin, part number (P/N) BRR15838, was
found backed out of the rear mount link. The retaining bolt, P/N
AS54020, which passes through the engine mount pin was also found
fractured at the groove which holds the locking spring. An
investigation revealed the most probable root cause of failure to be
a single axial tension static overload, with no evidence of fatigue
contributing to the failure.
The above condition if not detected, may result in the loss of
engine attachment to the airframe.
As an interim corrective action, Bombardier issued Service
Bulletins (SBs) 700-71-002, 700-71-6002, 700-71-5002,
[[Page 38627]]
and 700-1A11-71-002 to inspect the attachment points of the links
between the engine rear mount assemblies, and install replacement
hardware if required.
The original version of this [Canadian] AD was issued to mandate
incorporation of the above Bombardier SBs to inspect and maintain
integrity of the affected engine rear mount assembly.
Revision 1 of this [Canadian] AD is issued to mandate
incorporation of the Bombardier SBs 700-71-003, 700-71-6003, 700-71-
5003, and 700-1A11-71-003 to replace the existing bolts and self-
locking nuts with new bolts and nuts, as a final corrective action.
The MCAI also adds airplanes having serial numbers 9764, 9766, and 9771
through 9785 inclusive to the applicability. Those airplanes are also
affected by the identified unsafe condition. You may examine the MCAI
in the AD docket on the Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2017-0775.
Related Service Information Under 1 CFR Part 51
Bombardier has issued the following service information.
Bombardier Service Bulletin 700-71-002, Revision 01, dated
June 30, 2016.
Bombardier Service Bulletin 700-71-5002, Revision 01,
dated June 30, 2016.
Bombardier Service Bulletin 700-71-6002, Revision 01,
dated June 30, 2016.
Bombardier Service Bulletin 700-1A11-71-002, Revision 01,
dated June 30, 2016.
This service information describes procedures for an inspection for
discrepancies of the attachment points of the links between the engine
rear mount assemblies and corrective actions. These documents are
distinct since they apply to different airplane models and serial
numbers.
Bombardier has also issued the following service information. The
service information describes procedures for nut and bolt replacement.
These documents are distinct since they apply to different airplane
models and serial numbers.
Bombardier Service Bulletin 700-71-003, dated December 5,
2016.
Bombardier Service Bulletin 700-71-5003, dated December 5,
2016.
Bombardier Service Bulletin 700-71-6003, dated December 5,
2016.
Bombardier Service Bulletin 700-1A11-71-003, dated
December 5, 2016.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Costs of Compliance
We estimate that this proposed AD affects 97 airplanes of U.S.
registry.
The actions required by AD 2016-25-18, and retained in this
proposed AD take about 1 work-hour per product, at an average labor
rate of $85 per work-hour. Based on these figures, the estimated cost
of the actions that are required by AD 2016-25-18 is $85 per product.
The retained on-condition costs in this proposed AD take about 2
work-hours per product, at an average labor rate of $85 per work-hour.
Required parts cost about $730 per product. Based on these figures, the
estimated cost of the on-condition actions that are required by AD
2016-25-18 is $900 per product.
We have received no definitive data that would enable us to provide
cost estimates for other retained on-condition actions specified in AD
2016-25-18.
We also estimate that it would take about 4 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost up to
$14,940 per product. Based on these figures, we estimate the cost of
this proposed AD on U.S. operators to be up to $1,482,160, or up to
$15,280 per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all available 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.
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
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator,
[[Page 38628]]
the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2016-25-18, Amendment 39-18744 (81 FR 90961, December 16, 2016), and
adding the following new AD:
Bombardier, Inc.: Docket No. FAA-2017-0775; Product Identifier 2017-
NM-048-AD.
(a) Comments Due Date
We must receive comments by September 29, 2017.
(b) Affected ADs
This AD replaces AD 2016-25-18, Amendment 39-18744 (81 FR 90961,
December 16, 2016) (``AD 2016-25-18'').
(c) Applicability
This AD applies to Bombardier, Inc., Model BD-700-1A10 and BD-
700-1A11 airplanes, certificated in any category, serial numbers (S/
Ns) 9002 through 9785 inclusive, and 9998.
(d) Subject
Air Transport Association (ATA) of America Code 72, Engine.
(e) Reason
This AD was prompted by a report indicating that during
maintenance, an engine mount pin was found backed out of the rear
mount link, and the associated retaining bolt was also found
fractured at the groove that holds the locking spring. We are
issuing this AD to detect and correct broken engine attachment
hardware, which could result in separation of an engine from the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspection, With No Changes
This paragraph restates the requirements of paragraph (g) of AD
2016-25-18, with no changes. For airplanes having S/Ns 9002 through
9763 inclusive, 9765, 9767 through 9770 inclusive, and 9998: Within
500 flight hours or 4 months, whichever occurs first after January
3, 2017 (the effective date of AD 2016-25-18), do an inspection for
discrepancies of the engine rear mount assemblies (including missing
or broken bolts, missing nuts, incorrect torque values, and an
incorrect gap between the bushing and washer); in accordance with
Part A of the Accomplishment Instructions of the applicable service
information specified in paragraphs (g)(1) through (g)(4) of this
AD. Accomplishing the actions required by paragraphs (j) and (k) of
this AD terminates the requirements of this paragraph.
(1) Bombardier Service Bulletin 700-71-002, Revision 01, dated
June 30, 2016 (for Bombardier Model BD-700-1A10 airplanes).
(2) Bombardier Service Bulletin 700-71-6002, Revision 01, dated
June 30, 2016 (for Bombardier Model BD-700-1A10 airplanes).
(3) Bombardier Service Bulletin 700-71-5002, Revision 01, dated
June 30, 2016 (for Bombardier Model BD-700-1A11 airplanes).
(4) Bombardier Service Bulletin 700-1A11-71-002, Revision 01,
dated June 30, 2016 (for Bombardier Model BD-700-1A11 airplanes).
(h) Retained Corrective Action for Paragraph (g) of This AD, With No
Changes
This paragraph restates the requirements of paragraph (h) of AD
2016-25-18, with no changes. If any discrepancy is detected during
the inspection required by paragraph (g) of this AD, before further
flight, replace missing parts and correct noncompliant gaps and bolt
torque, as specified in the Accomplishment Instructions of the
applicable service information specified in paragraphs (g)(1)
through (g)(4) of this AD, except as required by paragraph (i) of
this AD. Accomplishing the actions required by paragraphs (j) and
(k) of this AD terminates the requirements of this paragraph.
(i) Retained Exception to Service Information Specifications, With No
Changes
This paragraph restates the requirements of paragraph (i) of AD
2016-25-18, with no changes. Where the applicable Bombardier service
bulletin specified in paragraphs (g)(1) through (g)(4) of this AD
provides no instructions for corrective actions, or specifies to
contact Bombardier for appropriate action, accomplish corrective
actions in accordance with the procedures specified in paragraph
(o)(2) of this AD.
(j) New Requirement of This AD: Gap Measurement
Within 1,000 flight hours or 12 months, whichever occurs first
after the effective date of this AD: Measure the gaps between the
applicable shouldered bushing fitted on the mount beam and the
washer; and between the applicable engine ring lug and the head of
the mount pin to determine if the gaps are within acceptable limits;
in accordance with Part A of the Accomplishment Instructions of the
applicable service information specified in paragraphs (j)(1)
through (j)(4) of this AD. Accomplishing the actions required by
paragraphs (j) and (k) of this AD terminates the requirements of
paragraphs (g) and (h) of this AD.
(1) Bombardier Service Bulletin 700-71-003, dated December 5,
2016 (for Bombardier Model BD-700-1A10 airplanes).
(2) Bombardier Service Bulletin 700-71-6003, dated December 5,
2016 (for Bombardier Model BD-700-1A10 airplanes).
(3) Bombardier Service Bulletin 700-71-5003, dated December 5,
2016 (for Bombardier Model BD-700-1A11 airplanes).
(4) Bombardier Service Bulletin 700-1A11-71-003, dated December
5, 2016 (for Bombardier Model BD-700-1A11 airplanes).
(k) New Requirement of This AD: Nut and Bolt Replacement, and Gap
Measurement
Within 1,000 flight hours or 12 months, whichever occurs first
after the effective date of this AD: Replace the nuts having part
number (P/N) AS54365 and the bolts having P/N AS54020 and AS54002 in
the engine rear mount assembly with new nuts and new bolts; and do
the gap measurement to determine if the gap is within acceptable
limits; in accordance with Part B of the Accomplishment Instructions
the applicable service information specified in paragraphs (j)(1)
through (j)(4) of this AD.
(l) New Requirement of This AD: Corrective Action
If any gap is detected, during any measurement required by
paragraph (j) or (k) of this AD, that is not within the applicable
limits specified in the service information specified in paragraphs
(j)(1) through (j)(4) of this AD, before further flight repair using
a method approved by the Manager, New York ACO Branch, FAA; or
Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.'s TCCA
Design Approval Organization (DAO).
(m) No Reporting Required
Although the service information identified in paragraphs (j)(1)
through (j)(4) of this AD specifies to submit certain information to
the manufacturer, this AD does not include that requirement.
(n) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (g) and (h) of this AD, if those actions were performed
before January 3, 2017 (the effective date of AD 2016-25-18), in
accordance with the Accomplishment Instructions of the applicable
service information specified in paragraphs (n)(1) through (n)(4) of
this AD.
(1) Bombardier Service Bulletin 700-71-002, dated May 31, 2016.
(2) Bombardier Service Bulletin 700-71-6002, dated May 31, 2016.
(3) Bombardier Service Bulletin 700-71-5002, dated May 31, 2016.
(4) Bombardier Service Bulletin 700-1A11-71-002, dated May 31,
2016.
(o) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York 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 ATTN: Program Manager, Continuing Operational
Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone: 516-228-7300; fax: 516-794-5531.
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.
[[Page 38629]]
(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, New York ACO
Branch, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO. If approved by
the DAO, the approval must include the DAO-authorized signature.
(p) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian Airworthiness Directive 2016-23R1, dated February
20, 2017, 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-2017-0775.
(2) For more information about this AD, contact Aziz Ahmed,
Airframe Engineer, Airframe and Mechanical Systems Section, FAA, New
York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
telephone: 516-228-7329; fax: 516-794-5531.
(3) For service information identified in this AD, contact
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval,
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; email thd.crj@aero.bombardier.com; Internet https://www.bombardier.com. You may view this service information at the
FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA,
call 425-227-1221.
Issued in Renton, Washington, on August 2, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-16777 Filed 8-14-17; 8:45 am]
BILLING CODE 4910-13-P
