Airworthiness Directives; Bombardier, Inc., Airplanes, 53563-53567 [2018-23031]
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53563
Rules and Regulations
Federal Register
Vol. 83, No. 206
Wednesday, October 24, 2018
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0160; Product
Identifier 2017–NM–139–AD; Amendment
39–19476; AD 2018–22–03]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2016–24–
03, which applied to certain
Bombardier, Inc., Model DHC–8–400
series airplanes. AD 2016–24–03
required 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. This AD retains the
requirements of AD 2016–24–03 and
requires modifying the airplane by
installing a sealing disk to a certain
location and replacing certain barrel
nuts. This AD was prompted by reports
of cracked and corroded barrel nuts
found at the mid-spar location of the
horizontal-stabilizer-to-verticalstabilizer attachment joint, and the
issuance of new service information that
includes a terminal modification. We
are issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective November
28, 2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 28, 2018.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of January 12, 2017 (81 FR
88623, December 8, 2016).
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SUMMARY:
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For service information
identified in this final rule, 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. It is also available on the internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2018–0160.
ADDRESSES:
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 Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
the regulatory evaluation, any
comments received, and other
information. The address for Docket
Operations (phone: 800–647–5527) is
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Aziz
Ahmed, Aerospace Engineer, Airframe
and Propulsion Section, FAA, New York
ACO Branch, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590;
telephone 516–228–7329; fax 516–794–
5531; email 9-avs-nyaco-cos@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2016–24–03,
Amendment 39–18720 (81 FR 88623,
December 8, 2016) (‘‘AD 2016–24–03’’).
AD 2016–24–03 applied to certain
Bombardier, Inc., Model DHC–8–400
series airplanes. The NPRM published
in the Federal Register on March 9,
2018 (83 FR 10408). The NPRM was
prompted by reports of cracked and
corroded barrel nuts found at the midspar location of the horizontalstabilizer-to-vertical-stabilizer
attachment joint, and the issuance of
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new service information that includes a
terminal modification. The NPRM
proposed to continue to require
repetitive detailed inspections of each
barrel nut and cradle, a check of the bolt
torque of the PLI washers, and
corrective action if necessary. The
NPRM also proposed to require
modifying the airplane by installing a
sealing disk to a certain location and
replacing certain barrel nuts. We are
issuing this AD to address 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.
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian AD
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.
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.
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Comments
We gave the public the opportunity to
participate in developing this final rule.
The following presents the comment
received on the NPRM and the FAA’s
response.
Request To Refer to New Repair
Drawing (RD)
Horizon Air requested that we revise
paragraph (h)(1)(i) of the proposed AD
to refer to Bombardier RD 8/4–55–1143,
Issue 2, dated May 25, 2015 (we referred
to Bombardier RD 8/4–55–1143, Issue 1,
dated May 21, 2015, as the appropriate
source of service information for the
repair specified in paragraph (h)(1)(i) of
the proposed AD). Horizon Air noted
that Bombardier RD 8/4–55–1143, Issue
2, dated May 25, 2015, adds nominal
bore diameters to sheets 1–4.
We agree with the commenter’s
request. Bombardier RD 8/4–55–1143,
Issue 2, dated May 25, 2015, clarifies the
bore hole diameters for repair but does
not otherwise change the substantive
requirements of this AD. No additional
work is necessary for airplanes on
which Bombardier RD 8/4–55–1143,
Issue 1, dated May 21, 2015, has already
been done. We have revised paragraph
(h)(1)(i) of this AD to include
Bombardier RD 8/4–55–1143, Issue 2,
dated May 25, 2015, as the appropriate
service information for repairing
corrosion and damage of the bore of the
fitting.
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting this
final rule with the change described
previously and minor editorial changes.
We have determined that these minor
changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this final rule.
Related Service Information Under 1
CFR Part 51
Bombardier has issued the following
service information.
• Bombardier Alert Service Bulletin
A84–55–04, Revision C, dated May 3,
2016. This service information describes
procedures for a detailed inspection and
repair for cracks and corrosion of the
barrel nuts and cradles; a bolt preload
check of the PLI washers and applicable
corrective actions; a detailed inspection
and repair for corrosion and damage of
the bore of the fitting; and replacement
of the barrel nuts.
• Bombardier Service Bulletin 84–55–
06, dated January 31, 2017. This 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.
This service information describes
procedures for an inspection for part
number and damage of the barrel nuts
at the horizontal-stabilizer-to-verticalstabilizer attachment joints, and
replacement of discrepant parts.
• Bombardier Repair Drawing (RD) 8/
4–55–1143, Issue 2, dated May 25, 2015.
This service information describes
procedures for repairing corrosion and
damage of the fitting bore.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 54
airplanes of U.S. registry. We estimate
the following costs to comply with this
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 action) .............
Replacement of DSC228 series barrel nuts
(new action).
8 work-hours × $85 per hour = $680 .............
$0
$680
$36,720
4 work-hours × $85 per hour = $340 .............
2 work-hours × $85 per hour = $170 .............
781
2,236
1,121
2,406
60,534
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 other on-condition
actions specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
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2 work-hours × $85 per hour = $170 ...........................
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
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$8,881
Cost per
product
$9,051
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.
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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 and associated appliances to
the Director of the System Oversight
Division.
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under 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.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
[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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■
2018–22–03 Bombardier, Inc.: Amendment
39–19476; Docket No. FAA–2018–0160;
Product Identifier 2017–NM–139–AD.
(a) Effective Date
This AD is effective November 28, 2018.
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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
Regulatory Findings
§ 39.13
(b) Affected ADs
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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 address 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.
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53565
(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; or Bombardier RD 8/4–
55–1143, Issue 2, dated May 25, 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; or
Bombardier RD 8/4–55–1143, Issue 2, dated
May 25, 2015; accomplish corrective actions
in accordance with the procedures specified
in paragraph (q)(2) of this AD. As of the
effective date of this AD, use Bombardier RD
8/4–55–1143, Issue 2, dated May 25, 2015,
for the repair required by this paragraph.
(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,
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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
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.
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(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-verticalstabilizer attachment joint on the modified
airplane.
(o) Terminating Actions for Paragraphs (h),
(i), and (j) of This AD
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
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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) Canadian
AD 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 Propulsion Section, FAA, New
York ACO Branch, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone
516–228–7329; fax 516–794–5531; email 9avs-nyaco-cos@faa.gov.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (s)(5) and (s)(6) of this AD.
(s) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(3) The following service information was
approved for IBR on November 28, 2018.
(i) Bombardier Repair Drawing (RD) 8/4–
55–1143, Issue 2, dated May 25, 2015.
(ii) Bombardier Service Bulletin 84–55–06,
dated January 31, 2017.
(iii) Bombardier Service Bulletin 84–55–08,
Revision A, dated August 2, 2017.
(4) The following service information was
approved for IBR on January 12, 2017 (81 FR
88623, December 8, 2016).
(i) Bombardier Alert Service Bulletin A84–
55–04, Revision C, dated May 3, 2016.
(ii) Reserved.
(5) 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.
E:\FR\FM\24OCR1.SGM
24OCR1
Federal Register / Vol. 83, No. 206 / Wednesday, October 24, 2018 / Rules and Regulations
(6) 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.
(7) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on
October 12, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–23031 Filed 10–23–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
SUPPLEMENTARY INFORMATION:
[Docket No. FAA–2018–0189; Product
Identifier 2017–CE–022–AD; Amendment
39–19460; AD 2018–21–02]
Discussion
RIN 2120–AA64
Airworthiness Directives; Viking Air
Limited Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Viking
Air Limited Model DHC–3 airplanes.
This AD results from mandatory
continuing airworthiness information
(MCAI) issued by an aviation authority
of another country to identify and
correct an unsafe condition on an
aviation product. The MCAI describes
the unsafe condition as pitting corrosion
on the shank of the wing strut attach
bolts. We are issuing this AD to require
actions to address the unsafe condition
on these products.
DATES: This AD is effective November
28, 2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of November 28, 2018.
ADDRESSES: You may examine the AD
docket on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0189; or in person at Docket Operations,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE,
Washington, DC 20590.
amozie on DSK3GDR082PROD with RULES
SUMMARY:
VerDate Sep<11>2014
16:10 Oct 23, 2018
Jkt 247001
For service information identified in
this AD, contact Viking Air Limited
Technical Support, 1959 De Havilland
Way, Sidney, British Columbia, Canada,
V8L 5V5; telephone: (North America)
(800) 663–8444; fax: (250) 656–0673;
email: technical.support@vikingair.com;
internet: https://www.vikingair.com/
support/service-bulletins. You may view
this referenced service information at
the FAA, Policy and Innovation
Division, 901 Locust, Kansas City,
Missouri 64106. For information on the
availability of this material at the FAA,
call (816) 329–4148. It is also available
on the internet at https://
www.regulations.gov by searching for
Docket No. FAA–2018–0189.
FOR FURTHER INFORMATION CONTACT: Aziz
Ahmed, Aerospace Engineer, FAA, New
York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, New York
11590; telephone: (516) 287–7329; fax:
(516) 794–5531; email: aziz.ahmed@
faa.gov.
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to Viking Air Limited Model
DHC–3 airplanes. The NPRM was
published in the Federal Register on
March 13, 2018 (83 FR 10809). The
NPRM proposed to correct an unsafe
condition for the specified products and
was based on MCAI originated by an
aviation authority of another country.
The MCAI states:
Pitting corrosion has been found on the
shank of the following part number wing
strut attach bolts: C3W114–3, C3W129–3 and
C3W128–3. These bolts are manufactured
using a standard AN12 bolt. Metallurgical
evaluation concluded that pitting corrosion
was present on the affected AN12 bolts prior
to forming of the bolt head and threads. The
pitting and un-plated voids could cause a
surface condition that may have a
detrimental effect on fatigue and corrosion
resistance, leading to bolt failure and
consequent failure of the wing.
Viking has not been able to confirm the
affected batch numbers or specific
manufacture date range. New wing strut bolts
manufactured after 21 March 2016 are
inspected for pitting during manufacturing
and issued new P/Ns C3W114–5, C3W129–
5 and C3W128–5 under MOD 3/1010.
The MCAI can be found in the AD
docket on the internet at: https://
www.regulations.gov/document
?D=FAA-2018-0189-0002.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
53567
received on the proposal and the FAA’s
response to each comment.
Request To Issue SAIB Instead of an AD
Christopher Campbell requested that
we withdraw the AD and issue a special
airworthiness information bulletin
(SAIB) instead. The commenter stated
this AD is unnecessary and redundant
since the manufacturer has already
addressed this issue with a mandatory
service bulletin and all affected bolts
should now be removed. The
commenter stated the affected bolts are
3/4-inch diameter bolts and only the
surface cadmium plating is
compromised, not the strength of the
bolt. The commenter also disagreed
with the manufacturer that the
compromised cadmium plating would
cause accelerated corrosion because the
bolts are treated with anti-corrosion
grease on installation. The commenter
further stated an AD is unnecessary
because the defect would be obvious to
any installing mechanic. Lastly, the
commenter stated that the proposed AD
does little to further enhance safety but
adds unwelcome recordkeeping and
cost for owners.
We do not agree. We concur with
Transport Canada’s finding of an unsafe
condition, as explained in Transport
Canada AD No. CF–2017–11, dated
March 23, 2017. An SAIB would not be
an appropriate solution. An SAIB
contains information and recommended
actions that are voluntary and not
regulatory. Moreover, an SAIB is issued
only for airworthiness concerns that do
not rise to the level of an unsafe
condition. Similarly, while an operator
may incorporate the procedures
described in a manufacturer’s service
bulletin into its maintenance program,
not all operators are required to do so.
For the corrective actions in a service
bulletin to become mandatory and to
correct the unsafe condition, the FAA
must issue an AD. Based on the
manufacturer’s metallurgical evaluation,
the pitting corrosion was present on the
affected AN 12 bolts prior to forming of
the bolt head and thread. Corrosion
pitting was found on airplanes when
doing the inspections per Transport
Canada’s AD CF–2017–11. Specifically,
the pitting was discovered on the bolt
shanks of both wing strut fitting to wing
spar lug bolts. Relying on an assumption
that the corrosion will be obvious at the
time of bolts installation, as suggested
by the commenter, is not a reliable
method to correct an unsafe condition.
We have not changed this AD based on
this comment.
E:\FR\FM\24OCR1.SGM
24OCR1
]]>Agencies
[Federal Register Volume 83, Number 206 (Wednesday, October 24, 2018)]
[Rules and Regulations]
[Pages 53563-53567]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-23031]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
========================================================================
Federal Register / Vol. 83, No. 206 / Wednesday, October 24, 2018 /
Rules and Regulations
[[Page 53563]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0160; Product Identifier 2017-NM-139-AD; Amendment
39-19476; AD 2018-22-03]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc., Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2016-24-03,
which applied to certain Bombardier, Inc., Model DHC-8-400 series
airplanes. AD 2016-24-03 required 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. This AD
retains the requirements of AD 2016-24-03 and requires modifying the
airplane by installing a sealing disk to a certain location and
replacing certain barrel nuts. 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 address the unsafe condition on
these products.
DATES: This AD is effective November 28, 2018.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 28,
2018.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of January
12, 2017 (81 FR 88623, December 8, 2016).
ADDRESSES: For service information identified in this final rule,
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. It is also available on the
internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2018-0160.
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 Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this final rule, the regulatory evaluation, any comments received, and
other information. The address for Docket Operations (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer,
Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7329; fax 516-
794-5531; email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2016-24-03, Amendment 39-18720 (81 FR 88623,
December 8, 2016) (``AD 2016-24-03''). AD 2016-24-03 applied to certain
Bombardier, Inc., Model DHC-8-400 series airplanes. The NPRM published
in the Federal Register on March 9, 2018 (83 FR 10408). The NPRM 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. The NPRM proposed to continue to
require repetitive detailed inspections of each barrel nut and cradle,
a check of the bolt torque of the PLI washers, and corrective action if
necessary. The NPRM also proposed to require modifying the airplane by
installing a sealing disk to a certain location and replacing certain
barrel nuts. We are issuing this AD to address 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.
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian AD 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.
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.
[[Page 53564]]
Comments
We gave the public the opportunity to participate in developing
this final rule. The following presents the comment received on the
NPRM and the FAA's response.
Request To Refer to New Repair Drawing (RD)
Horizon Air requested that we revise paragraph (h)(1)(i) of the
proposed AD to refer to Bombardier RD 8/4-55-1143, Issue 2, dated May
25, 2015 (we referred to Bombardier RD 8/4-55-1143, Issue 1, dated May
21, 2015, as the appropriate source of service information for the
repair specified in paragraph (h)(1)(i) of the proposed AD). Horizon
Air noted that Bombardier RD 8/4-55-1143, Issue 2, dated May 25, 2015,
adds nominal bore diameters to sheets 1-4.
We agree with the commenter's request. Bombardier RD 8/4-55-1143,
Issue 2, dated May 25, 2015, clarifies the bore hole diameters for
repair but does not otherwise change the substantive requirements of
this AD. No additional work is necessary for airplanes on which
Bombardier RD 8/4-55-1143, Issue 1, dated May 21, 2015, has already
been done. We have revised paragraph (h)(1)(i) of this AD to include
Bombardier RD 8/4-55-1143, Issue 2, dated May 25, 2015, as the
appropriate service information for repairing corrosion and damage of
the bore of the fitting.
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting
this final rule with the change described previously and minor
editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this final
rule.
Related Service Information Under 1 CFR Part 51
Bombardier has issued the following service information.
Bombardier Alert Service Bulletin A84-55-04, Revision C,
dated May 3, 2016. This service information describes procedures for a
detailed inspection and repair for cracks and corrosion of the barrel
nuts and cradles; a bolt preload check of the PLI washers and
applicable corrective actions; a detailed inspection and repair for
corrosion and damage of the bore of the fitting; and replacement of the
barrel nuts.
Bombardier Service Bulletin 84-55-06, dated January 31,
2017. This 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. This service information describes procedures for an
inspection for part number and damage of the barrel nuts at the
horizontal-stabilizer-to-vertical-stabilizer attachment joints, and
replacement of discrepant parts.
Bombardier Repair Drawing (RD) 8/4-55-1143, Issue 2, dated
May 25, 2015. This service information describes procedures for
repairing corrosion and damage of the fitting bore.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 54 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspections (retained actions from AD 8 work-hours x $85 per $0 $680 $36,720
2016-24-03). hour = $680.
Sealing disk installation (new action) 4 work-hours x $85 per 781 1,121 60,534
hour = $340.
Replacement of DSC228 series barrel 2 work-hours x $85 per 2,236 2,406 129,924
nuts (new action). hour = $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 2016-24- 2 work-hours x $85 per hour = $8,881 $9,051
03). $170.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the other on-condition actions specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``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.
[[Page 53565]]
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 and associated
appliances to the Director of the System Oversight Division.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under 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.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2016-24-03, Amendment 39-18720 (81 FR 88623, December 8, 2016), and
adding the following new AD:
2018-22-03 Bombardier, Inc.: Amendment 39-19476; Docket No. FAA-
2018-0160; Product Identifier 2017-NM-139-AD.
(a) Effective Date
This AD is effective November 28, 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 address 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; or Bombardier
RD 8/4-55-1143, Issue 2, dated May 25, 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; or Bombardier RD 8/4-55-1143,
Issue 2, dated May 25, 2015; accomplish corrective actions in
accordance with the procedures specified in paragraph (q)(2) of this
AD. As of the effective date of this AD, use Bombardier RD 8/4-55-
1143, Issue 2, dated May 25, 2015, for the repair required by this
paragraph.
(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,
[[Page 53566]]
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 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 for Paragraphs (h), (i), and (j) of This AD
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) Canadian AD 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 Propulsion Section, FAA, New York
ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
telephone 516-228-7329; fax 516-794-5531; email [email protected].
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (s)(5) and (s)(6) of this AD.
(s) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(3) The following service information was approved for IBR on
November 28, 2018.
(i) Bombardier Repair Drawing (RD) 8/4-55-1143, Issue 2, dated
May 25, 2015.
(ii) Bombardier Service Bulletin 84-55-06, dated January 31,
2017.
(iii) Bombardier Service Bulletin 84-55-08, Revision A, dated
August 2, 2017.
(4) The following service information was approved for IBR on
January 12, 2017 (81 FR 88623, December 8, 2016).
(i) Bombardier Alert Service Bulletin A84-55-04, Revision C,
dated May 3, 2016.
(ii) Reserved.
(5) 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.
[[Page 53567]]
(6) 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.
(7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on October 12, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-23031 Filed 10-23-18; 8:45 am]
BILLING CODE 4910-13-P
