Airworthiness Directives; Bombardier, Inc., Airplanes, 10408-10411 [2018-04720]
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10408
Federal Register / Vol. 83, No. 47 / Friday, March 9, 2018 / Proposed Rules
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0160; Product
Identifier 2017–NM–139–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) 2016–24–
03, which applies to certain
Bombardier, Inc., Model DHC–8–400
series airplanes. AD 2016–24–03
requires repetitive detailed inspections
of barrel nuts and cradles, a check of the
bolt torque of the preload indicating
(PLI) washers, and corrective actions if
necessary. Since we issued AD 2016–
24–03, the manufacturer has developed
a modification that, when incorporated,
terminates the repetitive inspections.
This proposed AD would require
modifying the airplane by installing a
sealing disk to a certain location and
replacing certain barrel nuts. We are
proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on
this proposed AD by April 23, 2018.
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.,
Q-Series Technical Help Desk, 123
Garratt Boulevard, Toronto, Ontario
M3K 1Y5, Canada; telephone 416–375–
4000; fax 416–375–4539; email
thd.qseries@aero.bombardier.com;
internet https://www.bombardier.com.
You may view this referenced service
information at the FAA, Transport
Standards Branch, 2200 South 216th St.,
Des Moines, WA. For information on the
availability of this material at the FAA,
call 206–231–3195.
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SUMMARY:
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Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0160; 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, Aerospace 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:
stabilizer attachment joints and lead to
loss of control of the airplane.
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2018–0160; Product Identifier
2017–NM–139–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.
There has been one in-service report of a
cracked and corroded barrel nut, part number
(P/N) DSC228–12, found at the mid-spar
location of the horizontal stabilizer to vertical
stabilizer attachment joint. There have also
been two other reports of corroded barrel
nuts found at mid-spar locations.
Preliminary investigation determined that
the cracking is initiated by corrosion. Further
investigation confirmed that the corrosion
was caused by inadequate cadmium plating
on the barrel nuts. Failure of the barrel nuts
could compromise the structural integrity of
the joint and could lead to loss of control of
the aeroplane.
The original version of this [Canadian] AD
was issued to mandate the initial and
repetitive inspections of the barrel nuts [and
cradles for cracks and corrosion] at each of
the horizontal stabilizer to vertical stabilizer
attachment joints.
Revision 1 of this [Canadian] AD is issued
to terminate the repetitive inspection
requirement by requiring the incorporation of
a modification to install a sealing disc at the
middle spar location of the horizontal
stabilizer to vertical stabilizer attachment
joint, and the replacement of the DSC228
series barrel nuts with B0203073 series barrel
nuts that are more resistant to corrosion. The
applicability has been changed to account for
the introduction of the modifications in
production.
Discussion
We issued AD 2016–24–03,
Amendment 39–18720 (81 FR 88623,
December 8, 2016) (‘‘AD 2016–24–03’’),
for certain Bombardier, Inc., Model
DHC–8–400 series airplanes. AD 2016–
24–03 requires repetitive detailed
inspections of barrel nuts and cradles, a
check of the bolt torque of the PLI
washers, and corrective action if
necessary. AD 2016–24–03 resulted
from reports of cracked and corroded
barrel nuts found at the mid-spar
location of the horizontal-stabilizer-tovertical-stabilizer attachment joint. We
issued AD 2016–24–03 to detect and
correct cracked and corroded barrel
nuts, which could compromise the
structural integrity of the vertical-
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Actions Since AD 2016–24–03 Was
Issued
Since we issued AD 2016–24–03,
Bombardier, Inc. has issued new service
information that describes a
modification. We have determined that
accomplishment of this modification
will address the unsafe condition and
terminate the repetitive inspections
required by AD 2016–24–03. This
modification was applied to certain
airplanes in production.
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2015–13R1,
dated June 26, 2017 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Bombardier, Inc., Model
DHC–8–400 series airplanes. The MCAI
states:
Required actions include a bolt
preload check of the PLI washers and
applicable corrective actions (retorque
of the bolts and replacement of the
barrel nut), a detailed inspection of
cracked or broken barrel nuts for
damaged bores of the fittings,
replacement of discrepant barrel nuts
(those with signs of structural damaged,
corrosion, or cracking, or having a part
number other than B0203073 series),
adding an aluminum sealing disk to the
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mid-spar barrel nut bore, and repair of
damage and corrosion.
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–2018–
0160.
Explanation of Changes From AD 2016–
24–03
In paragraph (h)(2) of AD 2016–24–03,
we stated ‘‘. . . replace the barrel nut
accomplish corrective actions in
accordance with [methods approved by
the FAA, TCCA, or Bombardier’s TCCA
Design Approval Organization].’’ We
intended to match the language in the
MCAI and allow operators to either
replace the discrepant barrel nut in
accordance with the applicable service
information or to request an alternative
method of compliance (AMOC). In
addition, we left ‘‘paragraph (h)(2)’’ out
of the credit paragraph in AD 2016–24–
03. We have updated the retained
requirements in this proposed AD to
correct those errors.
Related Service Information Under 1
CFR Part 51
Bombardier, Inc. has issued the
following service information.
• Bombardier Service Bulletin 84–55–
06, dated January 31, 2017. The service
information describes procedures for
installing an aluminum sealing disk at
the mid-spar location of the vertical
stabilizer.
• Bombardier Service Bulletin 84–55–
08, Revision A, dated August 2, 2017.
The service information describes
procedures for an inspection for part
number and damage of the barrel nuts
at the horizontal-to-vertical-stabilizer
attachment joints, and replacement of
discrepant parts.
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.
Differences Between This Proposed AD
and the MCAI or Service Information
The applicability of Canadian AD CF–
2015–13R1, dated June 26, 2017, is
limited to Bombardier, Inc., Model
DHC–8–400, –401 and –402 airplanes,
serial numbers 4001 through 4547.
However, the applicability of this
proposed AD includes Bombardier, Inc.,
Model DHC–8–400, –401 and –402
airplanes, serial numbers 4001 and
subsequent. Because the affected barrel
nuts are rotable parts, we have
determined that discrepant parts could
later be installed on airplanes that were
initially delivered with B0203073 series
barrel nuts, thereby subjecting those
airplanes to the unsafe condition.
Costs of Compliance
We estimate that this proposed AD
affects 54 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
ESTIMATED COSTS
Cost per
product
Parts cost
Cost on U.S.
operators
Action
Labor cost
Inspections (retained actions from AD 2016–
24–03).
Sealing disk installation (new proposed action).
Replacement of DSC228 series barrel nuts
(new proposed action).
8 work-hours × $85 per hour = $680 .............
$0
$680
$36,720
4 work-hours × $85 per hour = $340 .............
781
1,121
60,534
2 work-hours × $85 per hour = $170 .............
2,236
2,406
129,924
We estimate the following costs to do
any necessary replacements 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
Action
Labor cost
Replacement (retained action from AD 2016–24–03)
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We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
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2 work-hours × $85 per hour = $170 ...........................
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
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$8,881
Cost per
product
$9,051
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
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delegated the authority to issue ADs
applicable to transport category
airplanes to the Director of the System
Oversight Division.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
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)
2016–24–03, Amendment 39–18720 (81
FR 88623, December 8, 2016), and
adding the following new AD:
■
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Bombardier, Inc.: Docket No. FAA–2018–
0160; Product Identifier 2017–NM–139–
AD.
(a) Comments Due Date
We must receive comments by April 23,
2018.
(b) Affected ADs
This AD replaces AD 2016–24–03,
Amendment 39–18720 (81 FR 88623,
December 8, 2016) (‘‘AD 2016–24–03’’).
(c) Applicability
This AD applies to Bombardier, Inc.,
Model DHC–8–400, –401 and –402 airplanes,
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certificated in any category, serial numbers
4001 and subsequent.
(d) Subject
Air Transport Association (ATA) of
America Code 55, Stabilizers.
(e) Reason
This AD was prompted by reports of
cracked and corroded barrel nuts found at the
mid-spar location of the horizontal-stabilizerto-vertical-stabilizer attachment joint, and the
issuance of new service information that
includes a terminal modification. We are
issuing this AD to detect and correct cracked
and corroded barrel nuts, which could
compromise the structural integrity of the
vertical-stabilizer attachment joints and lead
to loss of control of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Detailed Inspection of Barrel
Nuts for Cracks and Corrosion, With No
Changes
This paragraph restates the requirements of
paragraphs (g)(1) and (g)(2) of AD 2016–24–
03, with no changes.
(1) For airplanes that have accumulated
5,400 flight hours or more, or have been in
service 32 months or more since the date of
issuance of the original certificate of
airworthiness or the date of issuance of the
original export certificate of airworthiness, as
of January 12, 2017 (the effective date of AD
2016–24–03): Within 600 flight hours or 4
months, whichever occurs first after January
12, 2017, do a detailed visual inspection for
signs of cracks and corrosion of the barrel nut
and cradle, in accordance with paragraph
3.B., ‘‘Procedure,’’ of the Accomplishment
Instructions of Bombardier Alert Service
Bulletin A84–55–04, Revision C, dated May
3, 2016.
(2) For airplanes that have less than 5,400
flight hours, and have been in-service for less
than 32 months since the date of issuance of
the original certificate of airworthiness or the
date of issuance of the original export
certificate of airworthiness, as of January 12,
2017: Before the accumulation of 6,000 total
flight hours or 36 months since the date of
issuance of the original certificate of
airworthiness or the date of issuance of the
original export certificate of airworthiness,
whichever occurs first, do a detailed visual
inspection of the barrel nut for signs of cracks
and corrosion of the barrel nut and cradle, in
accordance with paragraph 3.B.,
‘‘Procedure,’’ of the Accomplishment
Instructions of Bombardier Alert Service
Bulletin A84–55–04, Revision C, dated May
3, 2016.
(h) Retained Corrective Actions, Detailed
Inspection, and Repetitive Inspections, With
New Service Information, Reference to
Terminating Action, and Reference to
Corrective Actions
This paragraph restates the requirements of
paragraph (h) of AD 2016–24–03, with new
service information and terminating action.
Depending on the findings of any inspection
required by paragraphs (g) and (j) of this AD,
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do the applicable actions in paragraphs
(h)(1), (h)(2), (h)(3), and (h)(4) of this AD.
Accomplishment of the actions required by
paragraphs (l) and (m) of this AD, as
applicable, terminates the requirements of
this paragraph.
(1) If any barrel nut or cradle is found
cracked or broken, before further flight,
replace the barrel nut and associated
hardware, in accordance with paragraph 3.B.,
‘‘Procedure,’’ of the Accomplishment
Instructions of Bombardier Service Bulletin
84–55–08, Revision A, dated August 2, 2017.
(i) Concurrently with the replacement of
any barrel nut, do a detailed inspection for
corrosion and damage of the bore of the
fitting, in accordance with paragraph 3.B.,
‘‘Procedure,’’ of the Accomplishment
Instructions of Bombardier Service Bulletin
84–55–08, Revision A, dated August 2, 2017,
and, before further flight, repair all corrosion
and damage, in accordance with Bombardier
Repair Drawing (RD) 8/4–55–1143, Issue 1,
dated May 21, 2015. If the bore of the fitting
cannot be repaired in accordance with
Bombardier RD 8/4–55–1143, Issue 1, dated
May 21, 2015, accomplish corrective actions
in accordance with the procedures specified
in paragraph (q)(2) of this AD.
(ii) Within 600 flight hours or 4 months,
whichever occurs first, after the replacement
of a cracked barrel nut, replace the remaining
barrel nuts and their associated hardware at
the horizontal-stabilizer-to-vertical-stabilizer
attachment joints, in accordance with
paragraph 3.B., ‘‘Procedure,’’ of the
Accomplishment Instructions of Bombardier
Service Bulletin 84–55–08, Revision A, dated
August 2, 2017.
(2) If any corrosion is found on any barrel
nut on the front or rear-spar joints, before
further flight, replace the barrel nut in
accordance with paragraph 3.B.,
‘‘Procedure,’’ of the Accomplishment
Instructions of Bombardier Service Bulletin
84–55–08, Revision A, dated August 2, 2017,
or accomplish corrective actions in
accordance with the procedures specified in
paragraph (q)(2) of this AD.
(3) If any corrosion above level 1, as
defined in Bombardier Alert Service Bulletin
A84–55–04, Revision C, dated May 3, 2016,
is found on a barrel nut at the mid-spar joint,
before further flight, replace the barrel nut
and accomplish corrective actions in
accordance with the procedures specified in
paragraph (q)(2) of this AD.
(4) If all corrosion found is at level 1 or
below, as defined in Bombardier Alert
Service Bulletin A84–55–04, Revision C,
dated May 3, 2016, on a barrel nut at the midspar joint, repeat the inspection specified in
paragraph (g) of this AD at intervals not to
exceed 600 flight hours or 4 months,
whichever occurs first, until completion of
the actions required by paragraph (k) of this
AD.
(i) Retained Preload Indicating (PLI) Washer
Check, With New Terminating Action
This paragraph restates the requirements of
paragraph (i) of AD 2016–24–03, with new
terminating action. For airplanes with PLI
washers installed at the front and rear-spar
joints, before further flight after
accomplishing any inspection required by
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paragraph (g) of this AD and all applicable
corrective actions required by paragraph (h)
of this AD, check the bolt preload, and do all
applicable corrective actions, in accordance
with paragraph 3.B., ‘‘Procedure,’’ of the
Accomplishment Instructions of Bombardier
Alert Service Bulletin A84–55–04, Revision
C, dated May 3, 2016. Do all applicable
corrective actions before further flight.
Accomplishment of the actions required by
paragraphs (l) and (m) of this AD, as
applicable, terminates the requirements of
this paragraph.
(j) Retained Repetitive Inspection Interval,
With New Terminating Action
This paragraph restates the requirements of
paragraph (j) of AD 2016–24–03, with new
terminating action. Repeat the inspection and
preload check required by paragraphs (g) and
(i) of this AD at intervals not to exceed 3,600
flight hours or 18 months, whichever occurs
first, except as provided by paragraph (k) of
this AD. Accomplishment of the actions
required by paragraphs (l) and (m) of this AD,
as applicable, terminates the requirements of
this paragraph.
(k) Retained Optional Barrel Nut
Replacement, With New Service Information
This paragraph restates the provisions of
paragraph (k) of AD 2016–24–03, with new
service information. Inspection and
replacement of all barrel nuts at the
horizontal-stabilizer-to-vertical-stabilizer
attachment joints, in accordance with
paragraph 3.B., ‘‘Procedure,’’ of the
Accomplishment Instructions of Bombardier
Service Bulletin 84–55–08, Revision A, dated
August 2, 2017, extends the next inspection
required by paragraph (j) of this AD to within
6,000 flight hours or 36 months, whichever
occurs first, after accomplishing the
replacement.
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(l) New Requirement of This AD: Sealing
Disk Installation
Within 8,000 flight hours or 48 months,
whichever occurs first, after the effective date
of this AD, install a sealing disk at the midspar location of the vertical stabilizer in
accordance with paragraph 3.B.,
‘‘Procedure,’’ of the Accomplishment
Instructions of Bombardier Service Bulletin
84–55–06, dated January 31, 2017.
Accomplishment of the actions required by
paragraphs (l) and (m) of this AD, as
applicable, terminates the requirements of
paragraphs (h), (i), and (j) of this AD.
(m) New Requirement of This AD:
Replacement of DSC228 Series Barrel Nuts
For Bombardier, Inc., Model DHC–8–400,
–401 and –402 airplanes, serial numbers
4001 through 4524 inclusive: Within 8,000
flight hours or 48 months, whichever occurs
first, after the effective date of this AD,
replace all DSC228 series barrel nuts at the
horizontal-stabilizer-to-vertical-stabilizer
attachment joints with B0203073 series barrel
nuts in accordance with paragraph 3.B.,
‘‘Procedure,’’ of the Accomplishment
Instructions of Bombardier Service Bulletin
84–55–08, Revision A, dated August 2, 2017.
Accomplishment of the actions required by
paragraphs (l) and (m) of this AD, as
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applicable, terminates the requirements of
paragraphs (h), (i), and (j) of this AD.
(n) Parts Installation Prohibition
After modification of an airplane as
required by paragraphs (l) and (m) of this AD,
no person may install a DSC228 series barrel
nut at the horizontal-stabilizer-to-verticalstabilizer attachment joint on the modified
airplane.
(o) Terminating Actions
Accomplishment of the actions required by
paragraphs (l) and (m) of this AD, as
applicable, terminates the requirements of
paragraphs (h), (i), and (j) of this AD.
(p) Credit for Previous Actions
(1) This paragraph provides credit for
actions required by paragraphs (g)(1), (g)(2),
(h)(1), (h)(1)(i), (h)(1)(ii), (h)(2), (h)(3), (h)(4),
(i), and (k) of this AD, if those actions were
performed before the effective date of this AD
using the service information identified in
paragraphs (p)(1)(i) through (p)(1)(iii) of this
AD.
(i) Bombardier Alert Service Bulletin A84–
55–04, dated May 21, 2015, which is not
incorporated by reference in this AD.
(ii) Bombardier Alert Service Bulletin A84–
55–04, Revision A, dated June 2, 2015, which
is not incorporated by reference in this AD.
(iii) Bombardier Alert Service Bulletin
A84–55–04, Revision B, dated July 30, 2015,
which is not incorporated by reference in this
AD.
(2) This paragraph provides credit for
actions required by paragraphs (h)(1),
(h)(1)(i), (h)(1)(ii), (h)(2), and (k) of this AD,
if those actions were performed before the
effective date of this AD using the service
information identified in paragraphs (p)(2)(i)
and (p)(2)(ii) of this AD.
(i) Bombardier Service Bulletin 84–55–08,
dated January 27, 2017, which is not
incorporated by reference in this AD.
(ii) Bombardier Alert Service Bulletin A84–
55–04, Revision C, dated May 3, 2016, which
was incorporated by reference in AD 2016–
24–03.
(q) Other FAA AD Provisions
(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.
(i) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(ii) AMOCs approved previously for AD
2016–24–03 are approved as AMOCs for the
corresponding provisions of this AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
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10411
actions from a manufacturer, the action must
be accomplished 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). If approved by
the DAO, the approval must include the
DAO-authorized signature.
(r) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) TCCA
Airworthiness Directive CF–2015–13R1,
dated June 26, 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–2018–0160.
(2) For more information about this AD,
contact Aziz Ahmed, Aerospace 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., Q-Series
Technical Help Desk, 123 Garratt Boulevard,
Toronto, Ontario M3K 1Y5, Canada;
telephone 416–375–4000; fax 416–375–4539;
email thd.qseries@aero.bombardier.com;
internet https://www.bombardier.com. You
may view this service information at the
FAA, Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
Issued in Renton, Washington, on March 2,
2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–04720 Filed 3–8–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0165; Product
Identifier 2017–NM–122–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all
Airbus Model A318–111 and –112
airplanes, Model A319–111, –112, –113,
–114, and –115 airplanes, Model A320–
211, –212, –214, and –216 airplanes,
and Model A321–111, –112, –211, –212,
and –213 airplanes. This proposed AD
was prompted by a report of a
production quality deficiency on the
SUMMARY:
E:\FR\FM\09MRP1.SGM
09MRP1
]]>Agencies
[Federal Register Volume 83, Number 47 (Friday, March 9, 2018)]
[Proposed Rules]
[Pages 10408-10411]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-04720]
[[Page 10408]]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0160; Product Identifier 2017-NM-139-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) 2016-24-
03, which applies to certain Bombardier, Inc., Model DHC-8-400 series
airplanes. AD 2016-24-03 requires repetitive detailed inspections of
barrel nuts and cradles, a check of the bolt torque of the preload
indicating (PLI) washers, and corrective actions if necessary. Since we
issued AD 2016-24-03, the manufacturer has developed a modification
that, when incorporated, terminates the repetitive inspections. This
proposed AD would require modifying the airplane by installing a
sealing disk to a certain location and replacing certain barrel nuts.
We are proposing this AD to address the unsafe condition on these
products.
DATES: We must receive comments on this proposed AD by April 23, 2018.
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., Q-Series Technical Help Desk, 123 Garratt Boulevard,
Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; fax 416-375-
4539; email [email protected]; internet https://www.bombardier.com. You may view this referenced service information at
the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines,
WA. For information on the availability of this material at the FAA,
call 206-231-3195.
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-2018-
0160; 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, Aerospace 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 proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2018-0160;
Product Identifier 2017-NM-139-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
We issued AD 2016-24-03, Amendment 39-18720 (81 FR 88623, December
8, 2016) (``AD 2016-24-03''), for certain Bombardier, Inc., Model DHC-
8-400 series airplanes. AD 2016-24-03 requires repetitive detailed
inspections of barrel nuts and cradles, a check of the bolt torque of
the PLI washers, and corrective action if necessary. AD 2016-24-03
resulted from reports of cracked and corroded barrel nuts found at the
mid-spar location of the horizontal-stabilizer-to-vertical-stabilizer
attachment joint. We issued AD 2016-24-03 to detect and correct cracked
and corroded barrel nuts, which could compromise the structural
integrity of the vertical-stabilizer attachment joints and lead to loss
of control of the airplane.
Actions Since AD 2016-24-03 Was Issued
Since we issued AD 2016-24-03, Bombardier, Inc. has issued new
service information that describes a modification. We have determined
that accomplishment of this modification will address the unsafe
condition and terminate the repetitive inspections required by AD 2016-
24-03. This modification was applied to certain airplanes in
production.
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Airworthiness Directive CF-
2015-13R1, dated June 26, 2017 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for certain Bombardier, Inc., Model DHC-8-400 series
airplanes. The MCAI states:
There has been one in-service report of a cracked and corroded
barrel nut, part number (P/N) DSC228-12, found at the mid-spar
location of the horizontal stabilizer to vertical stabilizer
attachment joint. There have also been two other reports of corroded
barrel nuts found at mid-spar locations.
Preliminary investigation determined that the cracking is
initiated by corrosion. Further investigation confirmed that the
corrosion was caused by inadequate cadmium plating on the barrel
nuts. Failure of the barrel nuts could compromise the structural
integrity of the joint and could lead to loss of control of the
aeroplane.
The original version of this [Canadian] AD was issued to mandate
the initial and repetitive inspections of the barrel nuts [and
cradles for cracks and corrosion] at each of the horizontal
stabilizer to vertical stabilizer attachment joints.
Revision 1 of this [Canadian] AD is issued to terminate the
repetitive inspection requirement by requiring the incorporation of
a modification to install a sealing disc at the middle spar location
of the horizontal stabilizer to vertical stabilizer attachment
joint, and the replacement of the DSC228 series barrel nuts with
B0203073 series barrel nuts that are more resistant to corrosion.
The applicability has been changed to account for the introduction
of the modifications in production.
Required actions include a bolt preload check of the PLI washers
and applicable corrective actions (retorque of the bolts and
replacement of the barrel nut), a detailed inspection of cracked or
broken barrel nuts for damaged bores of the fittings, replacement of
discrepant barrel nuts (those with signs of structural damaged,
corrosion, or cracking, or having a part number other than B0203073
series), adding an aluminum sealing disk to the
[[Page 10409]]
mid-spar barrel nut bore, and repair of damage and corrosion.
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-2018-
0160.
Explanation of Changes From AD 2016-24-03
In paragraph (h)(2) of AD 2016-24-03, we stated ``. . . replace the
barrel nut accomplish corrective actions in accordance with [methods
approved by the FAA, TCCA, or Bombardier's TCCA Design Approval
Organization].'' We intended to match the language in the MCAI and
allow operators to either replace the discrepant barrel nut in
accordance with the applicable service information or to request an
alternative method of compliance (AMOC). In addition, we left
``paragraph (h)(2)'' out of the credit paragraph in AD 2016-24-03. We
have updated the retained requirements in this proposed AD to correct
those errors.
Related Service Information Under 1 CFR Part 51
Bombardier, Inc. has issued the following service information.
Bombardier Service Bulletin 84-55-06, dated January 31,
2017. The service information describes procedures for installing an
aluminum sealing disk at the mid-spar location of the vertical
stabilizer.
Bombardier Service Bulletin 84-55-08, Revision A, dated
August 2, 2017. The service information describes procedures for an
inspection for part number and damage of the barrel nuts at the
horizontal-to-vertical-stabilizer attachment joints, and replacement of
discrepant parts.
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.
Differences Between This Proposed AD and the MCAI or Service
Information
The applicability of Canadian AD CF-2015-13R1, dated June 26, 2017,
is limited to Bombardier, Inc., Model DHC-8-400, -401 and -402
airplanes, serial numbers 4001 through 4547. However, the applicability
of this proposed AD includes Bombardier, Inc., Model DHC-8-400, -401
and -402 airplanes, serial numbers 4001 and subsequent. Because the
affected barrel nuts are rotable parts, we have determined that
discrepant parts could later be installed on airplanes that were
initially delivered with B0203073 series barrel nuts, thereby
subjecting those airplanes to the unsafe condition.
Costs of Compliance
We estimate that this proposed AD affects 54 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspections (retained actions from 8 work-hours x $85 per hour $0 $680 $36,720
AD 2016-24-03). = $680.
Sealing disk installation (new 4 work-hours x $85 per hour 781 1,121 60,534
proposed action). = $340.
Replacement of DSC228 series barrel 2 work-hours x $85 per hour 2,236 2,406 129,924
nuts (new proposed action). = $170.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
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
----------------------------------------------------------------------------------------------------------------
Replacement (retained action from AD 2016- 2 work-hours x $85 per hour = $170. $8,881 $9,051
24-03).
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This 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
[[Page 10410]]
delegated the authority to issue ADs applicable to transport category
airplanes to the Director of the System Oversight Division.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2016-24-03, Amendment 39-18720 (81 FR 88623, December 8, 2016), and
adding the following new AD:
Bombardier, Inc.: Docket No. FAA-2018-0160; Product Identifier 2017-
NM-139-AD.
(a) Comments Due Date
We must receive comments by April 23, 2018.
(b) Affected ADs
This AD replaces AD 2016-24-03, Amendment 39-18720 (81 FR 88623,
December 8, 2016) (``AD 2016-24-03'').
(c) Applicability
This AD applies to Bombardier, Inc., Model DHC-8-400, -401 and -
402 airplanes, certificated in any category, serial numbers 4001 and
subsequent.
(d) Subject
Air Transport Association (ATA) of America Code 55, Stabilizers.
(e) Reason
This AD was prompted by reports of cracked and corroded barrel
nuts found at the mid-spar location of the horizontal-stabilizer-to-
vertical-stabilizer attachment joint, and the issuance of new
service information that includes a terminal modification. We are
issuing this AD to detect and correct cracked and corroded barrel
nuts, which could compromise the structural integrity of the
vertical-stabilizer attachment joints and lead to loss of control of
the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Detailed Inspection of Barrel Nuts for Cracks and
Corrosion, With No Changes
This paragraph restates the requirements of paragraphs (g)(1)
and (g)(2) of AD 2016-24-03, with no changes.
(1) For airplanes that have accumulated 5,400 flight hours or
more, or have been in service 32 months or more since the date of
issuance of the original certificate of airworthiness or the date of
issuance of the original export certificate of airworthiness, as of
January 12, 2017 (the effective date of AD 2016-24-03): Within 600
flight hours or 4 months, whichever occurs first after January 12,
2017, do a detailed visual inspection for signs of cracks and
corrosion of the barrel nut and cradle, in accordance with paragraph
3.B., ``Procedure,'' of the Accomplishment Instructions of
Bombardier Alert Service Bulletin A84-55-04, Revision C, dated May
3, 2016.
(2) For airplanes that have less than 5,400 flight hours, and
have been in-service for less than 32 months since the date of
issuance of the original certificate of airworthiness or the date of
issuance of the original export certificate of airworthiness, as of
January 12, 2017: Before the accumulation of 6,000 total flight
hours or 36 months since the date of issuance of the original
certificate of airworthiness or the date of issuance of the original
export certificate of airworthiness, whichever occurs first, do a
detailed visual inspection of the barrel nut for signs of cracks and
corrosion of the barrel nut and cradle, in accordance with paragraph
3.B., ``Procedure,'' of the Accomplishment Instructions of
Bombardier Alert Service Bulletin A84-55-04, Revision C, dated May
3, 2016.
(h) Retained Corrective Actions, Detailed Inspection, and Repetitive
Inspections, With New Service Information, Reference to Terminating
Action, and Reference to Corrective Actions
This paragraph restates the requirements of paragraph (h) of AD
2016-24-03, with new service information and terminating action.
Depending on the findings of any inspection required by paragraphs
(g) and (j) of this AD, do the applicable actions in paragraphs
(h)(1), (h)(2), (h)(3), and (h)(4) of this AD. Accomplishment of the
actions required by paragraphs (l) and (m) of this AD, as
applicable, terminates the requirements of this paragraph.
(1) If any barrel nut or cradle is found cracked or broken,
before further flight, replace the barrel nut and associated
hardware, in accordance with paragraph 3.B., ``Procedure,'' of the
Accomplishment Instructions of Bombardier Service Bulletin 84-55-08,
Revision A, dated August 2, 2017.
(i) Concurrently with the replacement of any barrel nut, do a
detailed inspection for corrosion and damage of the bore of the
fitting, in accordance with paragraph 3.B., ``Procedure,'' of the
Accomplishment Instructions of Bombardier Service Bulletin 84-55-08,
Revision A, dated August 2, 2017, and, before further flight, repair
all corrosion and damage, in accordance with Bombardier Repair
Drawing (RD) 8/4-55-1143, Issue 1, dated May 21, 2015. If the bore
of the fitting cannot be repaired in accordance with Bombardier RD
8/4-55-1143, Issue 1, dated May 21, 2015, accomplish corrective
actions in accordance with the procedures specified in paragraph
(q)(2) of this AD.
(ii) Within 600 flight hours or 4 months, whichever occurs
first, after the replacement of a cracked barrel nut, replace the
remaining barrel nuts and their associated hardware at the
horizontal-stabilizer-to-vertical-stabilizer attachment joints, in
accordance with paragraph 3.B., ``Procedure,'' of the Accomplishment
Instructions of Bombardier Service Bulletin 84-55-08, Revision A,
dated August 2, 2017.
(2) If any corrosion is found on any barrel nut on the front or
rear-spar joints, before further flight, replace the barrel nut in
accordance with paragraph 3.B., ``Procedure,'' of the Accomplishment
Instructions of Bombardier Service Bulletin 84-55-08, Revision A,
dated August 2, 2017, or accomplish corrective actions in accordance
with the procedures specified in paragraph (q)(2) of this AD.
(3) If any corrosion above level 1, as defined in Bombardier
Alert Service Bulletin A84-55-04, Revision C, dated May 3, 2016, is
found on a barrel nut at the mid-spar joint, before further flight,
replace the barrel nut and accomplish corrective actions in
accordance with the procedures specified in paragraph (q)(2) of this
AD.
(4) If all corrosion found is at level 1 or below, as defined in
Bombardier Alert Service Bulletin A84-55-04, Revision C, dated May
3, 2016, on a barrel nut at the mid-spar joint, repeat the
inspection specified in paragraph (g) of this AD at intervals not to
exceed 600 flight hours or 4 months, whichever occurs first, until
completion of the actions required by paragraph (k) of this AD.
(i) Retained Preload Indicating (PLI) Washer Check, With New
Terminating Action
This paragraph restates the requirements of paragraph (i) of AD
2016-24-03, with new terminating action. For airplanes with PLI
washers installed at the front and rear-spar joints, before further
flight after accomplishing any inspection required by
[[Page 10411]]
paragraph (g) of this AD and all applicable corrective actions
required by paragraph (h) of this AD, check the bolt preload, and do
all applicable corrective actions, in accordance with paragraph
3.B., ``Procedure,'' of the Accomplishment Instructions of
Bombardier Alert Service Bulletin A84-55-04, Revision C, dated May
3, 2016. Do all applicable corrective actions before further flight.
Accomplishment of the actions required by paragraphs (l) and (m) of
this AD, as applicable, terminates the requirements of this
paragraph.
(j) Retained Repetitive Inspection Interval, With New Terminating
Action
This paragraph restates the requirements of paragraph (j) of AD
2016-24-03, with new terminating action. Repeat the inspection and
preload check required by paragraphs (g) and (i) of this AD at
intervals not to exceed 3,600 flight hours or 18 months, whichever
occurs first, except as provided by paragraph (k) of this AD.
Accomplishment of the actions required by paragraphs (l) and (m) of
this AD, as applicable, terminates the requirements of this
paragraph.
(k) Retained Optional Barrel Nut Replacement, With New Service
Information
This paragraph restates the provisions of paragraph (k) of AD
2016-24-03, with new service information. Inspection and replacement
of all barrel nuts at the horizontal-stabilizer-to-vertical-
stabilizer attachment joints, in accordance with paragraph 3.B.,
``Procedure,'' of the Accomplishment Instructions of Bombardier
Service Bulletin 84-55-08, Revision A, dated August 2, 2017, extends
the next inspection required by paragraph (j) of this AD to within
6,000 flight hours or 36 months, whichever occurs first, after
accomplishing the replacement.
(l) New Requirement of This AD: Sealing Disk Installation
Within 8,000 flight hours or 48 months, whichever occurs first,
after the effective date of this AD, install a sealing disk at the
mid-spar location of the vertical stabilizer in accordance with
paragraph 3.B., ``Procedure,'' of the Accomplishment Instructions of
Bombardier Service Bulletin 84-55-06, dated January 31, 2017.
Accomplishment of the actions required by paragraphs (l) and (m) of
this AD, as applicable, terminates the requirements of paragraphs
(h), (i), and (j) of this AD.
(m) New Requirement of This AD: Replacement of DSC228 Series Barrel
Nuts
For Bombardier, Inc., Model DHC-8-400, -401 and -402 airplanes,
serial numbers 4001 through 4524 inclusive: Within 8,000 flight
hours or 48 months, whichever occurs first, after the effective date
of this AD, replace all DSC228 series barrel nuts at the horizontal-
stabilizer-to-vertical-stabilizer attachment joints with B0203073
series barrel nuts in accordance with paragraph 3.B., ``Procedure,''
of the Accomplishment Instructions of Bombardier Service Bulletin
84-55-08, Revision A, dated August 2, 2017. Accomplishment of the
actions required by paragraphs (l) and (m) of this AD, as
applicable, terminates the requirements of paragraphs (h), (i), and
(j) of this AD.
(n) Parts Installation Prohibition
After modification of an airplane as required by paragraphs (l)
and (m) of this AD, no person may install a DSC228 series barrel nut
at the horizontal-stabilizer-to-vertical-stabilizer attachment joint
on the modified airplane.
(o) Terminating Actions
Accomplishment of the actions required by paragraphs (l) and (m)
of this AD, as applicable, terminates the requirements of paragraphs
(h), (i), and (j) of this AD.
(p) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraphs (g)(1), (g)(2), (h)(1), (h)(1)(i), (h)(1)(ii), (h)(2),
(h)(3), (h)(4), (i), and (k) of this AD, if those actions were
performed before the effective date of this AD using the service
information identified in paragraphs (p)(1)(i) through (p)(1)(iii)
of this AD.
(i) Bombardier Alert Service Bulletin A84-55-04, dated May 21,
2015, which is not incorporated by reference in this AD.
(ii) Bombardier Alert Service Bulletin A84-55-04, Revision A,
dated June 2, 2015, which is not incorporated by reference in this
AD.
(iii) Bombardier Alert Service Bulletin A84-55-04, Revision B,
dated July 30, 2015, which is not incorporated by reference in this
AD.
(2) This paragraph provides credit for actions required by
paragraphs (h)(1), (h)(1)(i), (h)(1)(ii), (h)(2), and (k) of this
AD, if those actions were performed before the effective date of
this AD using the service information identified in paragraphs
(p)(2)(i) and (p)(2)(ii) of this AD.
(i) Bombardier Service Bulletin 84-55-08, dated January 27,
2017, which is not incorporated by reference in this AD.
(ii) Bombardier Alert Service Bulletin A84-55-04, Revision C,
dated May 3, 2016, which was incorporated by reference in AD 2016-
24-03.
(q) Other FAA AD Provisions
(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.
(i) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(ii) AMOCs approved previously for AD 2016-24-03 are approved as
AMOCs for the corresponding provisions of this AD.
(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 Transport Canada Civil Aviation (TCCA); or
Bombardier, Inc.'s TCCA Design Approval Organization (DAO). If
approved by the DAO, the approval must include the DAO-authorized
signature.
(r) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) TCCA Airworthiness Directive CF-2015-13R1, dated June 26,
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-2018-0160.
(2) For more information about this AD, contact Aziz Ahmed,
Aerospace 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., Q-Series Technical Help Desk, 123 Garratt
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000;
fax 416-375-4539; email [email protected]; internet
https://www.bombardier.com. You may view this service information at
the FAA, Transport Standards Branch, 2200 South 216th St., Des
Moines, WA. For information on the availability of this material at
the FAA, call 206-231-3195.
Issued in Renton, Washington, on March 2, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-04720 Filed 3-8-18; 8:45 am]
BILLING CODE 4910-13-P
