Airworthiness Directives; Bombardier, Inc., Airplanes, 32664-32667 [2019-14391]
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Federal Register / Vol. 84, No. 131 / Tuesday, July 9, 2019 / Proposed Rules
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) AD 2019–
0049, dated March 11, 2019, 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–2019–0523.
(2) For more information about this AD,
contact Vladimir Ulyanov, Aerospace
Engineer, International Section, Transport
Standards Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; telephone and
fax 206–231–3229.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAW, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; internet https://www.airbus.com.
You may view this 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 Des Moines, Washington, on June
28, 2019.
Dionne Palermo,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–14399 Filed 7–8–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0493; Product
Identifier 2019–NM–043–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to
supersede Airworthiness Directive (AD)
2011–18–15, which applies to certain
Bombardier, Inc., Model DHC–8–400
series airplanes. AD 2011–18–15
requires initial and repetitive torque
checks of the bolt preload; detailed
inspection of the barrel nuts and cradle
for cracking, pitting, and corrosion if the
bolt preload is correct; and replacement
of hardware if necessary. Since the FAA
issued AD 2011–18–15, the agency has
determined that incorporation of a new
design change is necessary to address
the root cause of the failure of the barrel
nuts. This proposed AD would retain
the existing requirements and add new
inspections and replacement of certain
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SUMMARY:
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hardware, which would terminate the
repetitive torque checks and
inspections. This AD also removes
airplanes from the applicability. The
FAA is proposing this AD to address the
unsafe condition on these products.
The FAA must receive comments
on this proposed AD by August 23,
2019.
DATES:
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., QSeries Technical Help Desk, 123 Garratt
Boulevard, Toronto, Ontario M3K 1Y5,
Canada; phone: 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.
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–2019–
0493; 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 NPRM, the
regulatory evaluation, any comments
received, and other information. The
street address for Docket Operations is
listed above. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Andrea Jimenez, Aerospace Engineer,
Airframe and Propulsion Section, FAA,
New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY
11590; phone: 516–228–7330; fax: 516–
794–5531; email: 9-avs-nyaco-cos@
faa.gov.
SUPPLEMENTARY INFORMATION:
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Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under the ADDRESSES section. Include
‘‘Docket No. FAA–2019–0493; Product
Identifier 2019–NM–043–AD’’ at the
beginning of your comments. The FAA
specifically invites comments on the
overall regulatory, economic,
environmental, and energy aspects of
this proposed AD. The FAA will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
The FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
personal information you provide. The
FAA will also post a report
summarizing each substantive verbal
contact received about this proposed
AD.
Discussion
The FAA issued AD 2011–18–15,
Amendment 39–16797 (76 FR 54093,
August 31, 2011) (‘‘AD 2011–18–15’’),
for certain Bombardier, Inc., Model
DHC–8–400 series airplanes. AD 2011–
18–15 requires initial and repetitive
torque checks of the bolt preload;
detailed inspection of the barrel nuts
and cradle for cracking, pitting, and
corrosion if the bolt preload is correct;
and replacement of hardware if
necessary. AD 2011–18–15 resulted
from in-service reports of cracked barrel
nuts found at the front spar locations of
the wing-to-fuselage attachment joints,
and reports of a loose washer in the
barrel nut assembly. The FAA issued
AD 2011–18–15 to address cracked
barrel nuts and a loose washer in the
barrel nut assembly, which could result
in failure of the barrel nuts,
compromising the structural integrity of
the wing-to-fuselage attachments, and
possible separation of the wing from the
airplane during flight.
Actions Since AD 2011–18–15 Was
Issued
Since the FAA issued AD 2011–18–
15, the manufacturer has developed a
design change (replacement of the
existing wing front spar barrel nuts with
new barrel nuts that are more resistant
to hydrogen embrittlement, and
installation of new bolts and pre-load
indicating washers). The FAA has
determined that the design change will
address the root cause of the failure of
the barrel nuts.
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian AD
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CF–2011–24R1, dated January 21, 2019
(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:
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0493.
Related Service Information Under 1
CFR Part 51
There have been several in-service reports
of cracked barrel nuts found at the front spar
locations of the wing to fuselage attachment
joints. Additionally, three operators have
reported finding a loose washer in the barrel
nut assembly. Failure of the barrel nuts could
compromise the structural integrity of the
wing to fuselage attachments.
The investigation determined that these
cracks are due to hydrogen embrittlement.
The original version of this [Canadian] AD
mandated initial and repetitive detailed
inspections of the barrel nuts, part number
(P/N) DSC228–16.
Since the original version of this
[Canadian] AD, Bombardier Inc. has
developed a design change to address the
root cause of the failure of the barrel nuts.
This design change replaces the existing
wing front spar barrel nuts, P/N DSC228–16,
with new Inconel 718 barrel nuts, P/N
B0203072–16S, which are more resistant to
hydrogen embrittlement. The design change
also includes new bolts and new pre-load
indicating washers.
Revision 1 of this [Canadian] AD mandates
this design change as a terminating action to
the repetitive inspection requirements of Part
II of this [Canadian] AD. A torque verification
has also been introduced to address loose
washers in the barrel nut assembly.
You may examine the MCAI in the
AD docket on the internet at https://
Bombardier has issued the following
service information.
• Bombardier Alert Service Bulletin
A84–57–25, Revision A, dated July 16,
2018. This service information describes
procedures for initial and repetitive
torque checks of the bolt preload,
detailed inspection of the barrel nuts
and cradle for cracking, pitting, and
corrosion if the bolt preload is correct,
and replacement of hardware if
necessary.
• Bombardier Service Bulletin 84–57–
26, Revision C, dated July 16, 2018. This
service information describes
procedures for a visual inspection of the
saddle washer and retainer for any
damage (cracks) and corrosion, and
replacement of the existing wing front
spar barrel nuts, bolts, and pre-load
indicating washers.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
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bilateral agreement with the State of
Design Authority, the FAA has been
notified of the unsafe condition
described in the MCAI and service
information referenced above. The FAA
is proposing this AD because the agency
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design.
Proposed Requirements of This NPRM
This proposed AD would retain all of
the requirements of AD 2011–18–15.
This proposed AD would also require
accomplishing the actions specified in
the service information described
previously, which would terminate the
repetitive torque checks and inspections
and the corrective actions for incorrect
bolt preload.
Revised Applicability
The FAA also revised the
applicability of this AD from what was
specified in AD 2011–18–15 to remove
airplane serial numbers 4438 and
subsequent. The terminating actions
specified in this proposed AD are
accomplished on those airplanes during
production.
FAA’s Determination
Costs of Compliance
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
The FAA estimates that this proposed
AD affects 54 airplanes of U.S. registry.
The FAA estimates the following
costs to comply with this proposed AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Labor cost
Retained actions from AD 2011-18-15 ...........
New proposed actions ....................................
15 work-hours × $85 per hour = $1,275 ........
15 work-hours × $85 per hour = $1,275 ........
The FAA has received no definitive
data that would enable us to provide
cost estimates for the on-condition
repairs specified in this proposed AD.
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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.
The FAA is 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
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Parts cost
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 proposed AD is issued in
accordance with authority delegated by
the Executive Director, Aircraft
Certification Service, as authorized by
FAA Order 8000.51C. In accordance
with that order, issuance of ADs is
normally a function of the Compliance
and Airworthiness Division, but during
this transition period, the Executive
Director has delegated the authority to
issue ADs applicable to transport
category airplanes and associated
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$10,492
10,492
Cost per
product
$11,767
11,767
Cost on U.S.
operators
$635,418
635,418
appliances to the Director of the System
Oversight Division.
Regulatory Findings
The FAA 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. Will not affect intrastate aviation in
Alaska, and
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Federal Register / Vol. 84, No. 131 / Tuesday, July 9, 2019 / Proposed Rules
3. 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)
2011–18–15, Amendment 39–16797 (76
FR 54093, August 31, 2011), and adding
the following new AD:
■
Bombardier, Inc.: Docket No. FAA–2019–
0493; Product Identifier 2019–NM–043–AD.
(a) Comments Due Date
The FAA must receive comments by
August 23, 2019.
(b) Affected ADs
This AD replaces AD 2011–18–15,
Amendment 39–16797 (76 FR 54093, August
31, 2011) (‘‘AD 2011–18–15’’).
(c) Applicability
This AD applies to Bombardier, Inc.,
Model DHC–8–400, –401, and –402
airplanes, certificated in any category, serial
numbers 4001 through 4437 inclusive.
This paragraph restates the requirements of
paragraph (g) of AD 2011–18–15, with
revised service information. At the applicable
time specified in paragraph (g)(1) or (g)(2) of
this AD: Do a torque check to determine if
the bolt preload is correct, and if the preload
is correct, before further flight, do a detailed
inspection of each barrel nut and cradle for
cracking, pitting or corrosion, in accordance
with paragraph 3.B., part A, of the
Accomplishment Instructions of Bombardier
Alert Service Bulletin A84–57–25, dated July
20, 2011; or Bombardier Alert Service
Bulletin A84–57–25, Revision A, dated July
16, 2018. After the effective date of this AD,
only Bombardier Alert Service Bulletin A84–
57–25, Revision A, dated July 16, 2018, may
be used. Repeat the torque check and, as
applicable, the inspection thereafter at
intervals not to exceed 2,000 flight hours or
12 months, whichever occurs first.
(1) For airplanes that have accumulated
1,900 or more total flight hours as of
September 15, 2011 (the effective date of AD
2011–18–15), or for which it has been 12
months or more since the date of issuance of
the original Canadian airworthiness
certificate or the date of issuance of the
original Canadian export certificate of
airworthiness as of September 15, 2011:
Within 100 flight hours or 10 days after
September 15, 2011, whichever occurs first.
(2) For airplanes that have accumulated
less than 1,900 total flight hours as of
September 15, 2011 (the effective date of AD
2011–18–15), and for which it has been less
than 12 months since the date of issuance of
the original Canadian airworthiness
certificate or the date of issuance of the
original Canadian export certificate of
airworthiness as of September 15, 2011: Prior
to the accumulation of 2,000 total flight
hours or within 12 months since the date of
issuance of the original Canadian standard
airworthiness certificate or the date of
issuance of the original Canadian export
certificate of airworthiness, whichever occurs
first.
(i) Retained Corrective Actions for Barrel
Nut/Cradle Discrepancies, With Revised
Service Information
This paragraph restates the requirements of
paragraph (i) of AD 2011–18–15, with revised
service information. If any crack, pitting, or
corrosion of the barrel nut or cradle is found
during any inspection required by paragraph
(g) of this AD, before further flight, replace
all hardware at that location (except the
saddle washer and retainer) in accordance
with paragraph 3.B., part B, of the
Accomplishment Instructions of Bombardier
Alert Service Bulletin A84–57–25, dated July
20, 2011; or paragraph 3.B. of the
Accomplishment Instructions of Bombardier
Service Bulletin 84–57–26, Revision C, dated
July 16, 2018. After the effective date of this
AD, only Bombardier Service Bulletin 84–
57–26, Revision C, dated July 16, 2018, may
be used.
(j) New Requirement of This AD:
Replacement and Visual Inspection
Within 12,000 flight hours or 72 months
after the effective date of this AD, whichever
occurs first: Do a visual inspection of the
saddle washer and retainer for any damage
(cracks) or corrosion; and replace the wing
front spar barrel nuts, bolts, and pre-load
indicating washers; in accordance with
paragraph 3.B. of the Accomplishment
Instructions of Bombardier Service Bulletin
84–57–26, Revision C, dated July 16, 2018.
(k) New Corrective Actions for Damage
(Cracks) or Corrosion
If any damage (cracks) or corrosion is
found during any inspection required by
paragraph (j) of this AD: Before further flight,
accomplish corrective actions in accordance
with the procedures specified in paragraph
(p)(2) of this AD.
(l) New Provision of This AD: Terminating
Actions for Repetitive Torque Checks and
Detailed Inspections
Accomplishment of the applicable actions
required by paragraphs (j) and (k) of this AD,
at all four barrel nut locations, terminates the
repetitive torque checks and detailed
inspections of paragraph (g) of this AD.
Air Transport Association (ATA) of
America Code 57, Wings.
(h) Retained Corrective Actions for Incorrect
Bolt Preload, With Revised Service
Information
(m) Parts Installation Prohibition
As of the effective date of this AD, no
person may install, on any airplane, a barrel
nut having part number DSC228–16.
(e) Reason
This paragraph restates the requirements of
paragraph (h) of AD 2011–18–15, with
revised service information. If any bolt
preload is found to be incorrect (i.e., the ring
can be rotated during any torque check
required by paragraph (g) of this AD), before
further flight, replace all hardware at that
location (except the saddle washer and
retainer) in accordance with paragraph 3.B.,
part B, of the Accomplishment Instructions
of Bombardier Alert Service Bulletin A84–
57–25, dated July 20, 2011; or paragraph 3.B.
of the Accomplishment Instructions of
Bombardier Service Bulletin 84–57–26,
Revision C, dated July 16, 2018. After the
effective date of this AD, only Bombardier
Service Bulletin 84–57–26, Revision C, dated
July 16, 2018, may be used.
(n) Retained Special Flight Permit
Provisions, With No Changes
This paragraph restates the requirements of
paragraph (k) of AD 2011–18–15, with no
changes. Special flight permits, as described
in 14 CFR 21.197 and 21.199, may be issued
to operate the airplane to a location where
the requirements of this AD can be
accomplished, but concurrence by the
Manager, New York ACO Branch, FAA, is
required before issuance of the special flight
permit. Before using any approved special
flight permits, notify your principal
maintenance inspector (PMI) or principal
avionics inspector (PAI), as appropriate, or
lacking a principal inspector, your local
Flight Standards District Office (FSDO).
Operators must request a repair drawing from
(d) Subject
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(g) Retained Initial and Repetitive
Inspections, With Revised Service
Information
This AD was prompted by in-service
reports of cracked barrel nuts found at the
front spar locations of the wing-to-fuselage
attachment joints, and a loose washer in the
barrel nut assembly. The FAA is issuing this
AD to address cracked barrel nuts and a loose
washer in the barrel nut assembly, which
could result in failure of the barrel nuts,
compromising the structural integrity of the
wing-to-fuselage attachments, and possible
separation of the wing from the airplane
during flight.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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Bombardier, which provides
recommendations for a one-time special
flight permit. The repair drawing will be
applicable to the operator’s aircraft serial
number only. Special flight permits may be
permitted provided that the conditions
specified in paragraphs (n)(1), (n)(2), (n)(3),
(n)(4), and (n)(5) of this AD are met.
(1) Only one barrel nut out of four is
cracked, one cradle is cracked, or one washer
is loose; all other strut (wing front spar) bolt
locations must be free of damage.
(2) The airplane must operate with reduced
airspeed not to exceed 180 KIAS (knots
indicated air speed). No passengers and no
cargo are onboard.
(3) The airplane must not operate in known
or forecast turbulence, other than light
turbulence.
(4) The airplane descent rate on landing
flare-out is not to exceed 5 feet per second.
(5) Heavy braking or hard turning of the
airplane upon landing is to be avoided if
possible.
(o) Credit for Previous Actions
(1) This paragraph restates the provisions
of paragraph (j) of AD 2011–18–15, with
revised formatting and updated service
information. This paragraph provides credit
for torque checks, initial inspections, and
replacements required by paragraphs (g) and
(h) of this AD, if those actions were
performed before the effective date of this AD
using the service information specified in
paragraphs (o)(1)(i) through (o)(1)(v) of this
AD, which is not incorporated by reference
in this AD. The repetitive inspections
required by paragraph (g) of this AD must be
continued at the time specified.
(i) Bombardier Alert Service Bulletin A84–
57–19, dated February 1, 2008.
(ii) Bombardier Alert Service Bulletin A84–
57–19, Revision A, dated February 6, 2008.
(iii) Bombardier Alert Service Bulletin
A84–57–19, Revision B, dated March 6, 2008.
(iv) Bombardier Alert Service Bulletin
A84–57–19, Revision C, dated August 20,
2008.
(v) Bombardier Alert Service Bulletin A84–
57–19, Revision D, dated August 12, 2011.
(2) This paragraph provides credit for the
actions required by paragraphs (h), (i), (j),
and (k) of this AD, if those actions were
performed before the effective date of this AD
using the service information specified in
paragraphs (o)(2)(i) through (o)(2)(iii) of this
AD. This service information is not
incorporated by reference in this AD.
(i) Bombardier Service Bulletin 84–57–26,
dated March 21, 2013.
(ii) Bombardier Service Bulletin 84–57–26,
Revision A, dated July 18, 2014.
(iii) Bombardier Service Bulletin 84–57–26,
Revision B, dated February 26, 2015.
(3) This paragraph provides credit for the
actions required by paragraphs (h) and (i) of
this AD, if those actions were performed
before the effective date of this AD using the
service information specified in paragraphs
(o)(3)(i) and (o)(3)(ii) of this AD.
(i) Bombardier Alert Service Bulletin A84–
57–25, dated July 20, 2011, which was
incorporated by reference in AD 2011–18–15.
(ii) Bombardier Alert Service Bulletin A84–
57–25, Revision A, dated July 16, 2018,
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which is incorporated by reference in this
AD.
DEPARTMENT OF TRANSPORTATION
(p) Other FAA AD Provisions
Federal Aviation Administration
(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; phone: 516–
228–7300; fax: 516–794–5531. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(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.
(3) AMOCs approved previously for AD
2011–18–15 are approved as AMOCs for the
corresponding provisions of this AD.
(q) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
AD CF–2011–24R1, dated January 21, 2019,
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–2019–0493.
(2) For more information about this AD,
contact Andrea Jimenez, Aerospace Engineer,
Airframe and Propulsion Section, FAA, New
York ACO Branch, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; phone: 516–
228–7330; fax: 516–794–5531; email: 9-avsnyaco-cos@faa.gov.
(3) For service information identified in
this AD, contact Bombardier, Inc., Q-Series
Technical Help Desk, 123 Garratt Boulevard,
Toronto, Ontario M3K 1Y5, Canada; phone:
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 Des Moines, Washington, on June
28, 2019.
Dionne Palermo,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–14391 Filed 7–8–19; 8:45 am]
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14 CFR Part 39
[Docket No. FAA–2019–0252; Product
Identifier 2019–NM–048–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 727
airplanes, Model 757 airplanes, and
Model 767–200, –300, –300F, and
–400ER series airplanes. This proposed
AD was prompted by reports of
nuisance stick shaker activation while
the airplane accelerated to cruise speed
at the top of climb. This proposed AD
was also prompted by an investigation
of those reports that revealed that the
angle of attack (AOA) (also known as
angle of airflow) sensor vanes could not
prevent the build-up of ice, causing the
AOA sensor vanes to become
immobilized, which resulted in
nuisance stick shaker activation. This
proposed AD would require a general
visual inspection of the AOA sensors for
a part number, and replacement of
affected AOA sensors. We are proposing
this AD to address the unsafe condition
on these products.
DATES: We must receive comments on
this proposed AD by August 23, 2019.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster
Blvd., MC 110–SK57, Seal Beach, CA
90740–5600; telephone 562–797–1717;
internet https://
www.myboeingfleet.com. You may view
SUMMARY:
E:\FR\FM\09JYP1.SGM
09JYP1
]]>Agencies
[Federal Register Volume 84, Number 131 (Tuesday, July 9, 2019)]
[Proposed Rules]
[Pages 32664-32667]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-14391]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0493; Product Identifier 2019-NM-043-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc., Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2011-18-15, which applies to certain Bombardier, Inc., Model DHC-8-400
series airplanes. AD 2011-18-15 requires initial and repetitive torque
checks of the bolt preload; detailed inspection of the barrel nuts and
cradle for cracking, pitting, and corrosion if the bolt preload is
correct; and replacement of hardware if necessary. Since the FAA issued
AD 2011-18-15, the agency has determined that incorporation of a new
design change is necessary to address the root cause of the failure of
the barrel nuts. This proposed AD would retain the existing
requirements and add new inspections and replacement of certain
hardware, which would terminate the repetitive torque checks and
inspections. This AD also removes airplanes from the applicability. The
FAA is proposing this AD to address the unsafe condition on these
products.
DATES: The FAA must receive comments on this proposed AD by August 23,
2019.
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; phone: 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-2019-
0493; 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 NPRM, the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations is listed above.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer,
Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590; phone: 516-228-7330; fax: 516-
794-5531; email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2019-0493;
Product Identifier 2019-NM-043-AD'' at the beginning of your comments.
The FAA specifically invites comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. The
FAA will consider all comments received by the closing date and may
amend this proposed AD based on those comments.
The FAA will post all comments received, without change, to https://www.regulations.gov, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact received about this proposed AD.
Discussion
The FAA issued AD 2011-18-15, Amendment 39-16797 (76 FR 54093,
August 31, 2011) (``AD 2011-18-15''), for certain Bombardier, Inc.,
Model DHC-8-400 series airplanes. AD 2011-18-15 requires initial and
repetitive torque checks of the bolt preload; detailed inspection of
the barrel nuts and cradle for cracking, pitting, and corrosion if the
bolt preload is correct; and replacement of hardware if necessary. AD
2011-18-15 resulted from in-service reports of cracked barrel nuts
found at the front spar locations of the wing-to-fuselage attachment
joints, and reports of a loose washer in the barrel nut assembly. The
FAA issued AD 2011-18-15 to address cracked barrel nuts and a loose
washer in the barrel nut assembly, which could result in failure of the
barrel nuts, compromising the structural integrity of the wing-to-
fuselage attachments, and possible separation of the wing from the
airplane during flight.
Actions Since AD 2011-18-15 Was Issued
Since the FAA issued AD 2011-18-15, the manufacturer has developed
a design change (replacement of the existing wing front spar barrel
nuts with new barrel nuts that are more resistant to hydrogen
embrittlement, and installation of new bolts and pre-load indicating
washers). The FAA has determined that the design change will address
the root cause of the failure of the barrel nuts.
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian AD
[[Page 32665]]
CF-2011-24R1, dated January 21, 2019 (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 have been several in-service reports of cracked barrel
nuts found at the front spar locations of the wing to fuselage
attachment joints. Additionally, three operators have reported
finding a loose washer in the barrel nut assembly. Failure of the
barrel nuts could compromise the structural integrity of the wing to
fuselage attachments.
The investigation determined that these cracks are due to
hydrogen embrittlement.
The original version of this [Canadian] AD mandated initial and
repetitive detailed inspections of the barrel nuts, part number (P/
N) DSC228-16.
Since the original version of this [Canadian] AD, Bombardier
Inc. has developed a design change to address the root cause of the
failure of the barrel nuts. This design change replaces the existing
wing front spar barrel nuts, P/N DSC228-16, with new Inconel 718
barrel nuts, P/N B0203072-16S, which are more resistant to hydrogen
embrittlement. The design change also includes new bolts and new
pre-load indicating washers.
Revision 1 of this [Canadian] AD mandates this design change as
a terminating action to the repetitive inspection requirements of
Part II of this [Canadian] AD. A torque verification has also been
introduced to address loose washers in the barrel nut assembly.
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-2019-
0493.
Related Service Information Under 1 CFR Part 51
Bombardier has issued the following service information.
Bombardier Alert Service Bulletin A84-57-25, Revision A,
dated July 16, 2018. This service information describes procedures for
initial and repetitive torque checks of the bolt preload, detailed
inspection of the barrel nuts and cradle for cracking, pitting, and
corrosion if the bolt preload is correct, and replacement of hardware
if necessary.
Bombardier Service Bulletin 84-57-26, Revision C, dated
July 16, 2018. This service information describes procedures for a
visual inspection of the saddle washer and retainer for any damage
(cracks) and corrosion, and replacement of the existing wing front spar
barrel nuts, bolts, and pre-load indicating washers.
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
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, the FAA
has been notified of the unsafe condition described in the MCAI and
service information referenced above. The FAA is proposing this AD
because the agency evaluated all the relevant information and
determined the unsafe condition described previously is likely to exist
or develop on other products of the same type design.
Proposed Requirements of This NPRM
This proposed AD would retain all of the requirements of AD 2011-
18-15. This proposed AD would also require accomplishing the actions
specified in the service information described previously, which would
terminate the repetitive torque checks and inspections and the
corrective actions for incorrect bolt preload.
Revised Applicability
The FAA also revised the applicability of this AD from what was
specified in AD 2011-18-15 to remove airplane serial numbers 4438 and
subsequent. The terminating actions specified in this proposed AD are
accomplished on those airplanes during production.
Costs of Compliance
The FAA estimates that this proposed AD affects 54 airplanes of
U.S. registry.
The FAA estimates the following costs to comply with this proposed
AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 15 work-hours x $85 per $10,492 $11,767 $635,418
2011[dash]18[dash]15. hour = $1,275.
New proposed actions.................. 15 work-hours x $85 per 10,492 11,767 635,418
hour = $1,275.
----------------------------------------------------------------------------------------------------------------
The FAA has received no definitive data that would enable us to
provide cost estimates for the on-condition repairs 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.
The FAA is 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 proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes and associated appliances to the
Director of the System Oversight Division.
Regulatory Findings
The FAA 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. Will not affect intrastate aviation in Alaska, and
[[Page 32666]]
3. 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)
2011-18-15, Amendment 39-16797 (76 FR 54093, August 31, 2011), and
adding the following new AD:
Bombardier, Inc.: Docket No. FAA-2019-0493; Product Identifier
2019-NM-043-AD.
(a) Comments Due Date
The FAA must receive comments by August 23, 2019.
(b) Affected ADs
This AD replaces AD 2011-18-15, Amendment 39-16797 (76 FR 54093,
August 31, 2011) (``AD 2011-18-15'').
(c) Applicability
This AD applies to Bombardier, Inc., Model DHC-8-400, -401, and
-402 airplanes, certificated in any category, serial numbers 4001
through 4437 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by in-service reports of cracked barrel
nuts found at the front spar locations of the wing-to-fuselage
attachment joints, and a loose washer in the barrel nut assembly.
The FAA is issuing this AD to address cracked barrel nuts and a
loose washer in the barrel nut assembly, which could result in
failure of the barrel nuts, compromising the structural integrity of
the wing-to-fuselage attachments, and possible separation of the
wing from the airplane during flight.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Initial and Repetitive Inspections, With Revised Service
Information
This paragraph restates the requirements of paragraph (g) of AD
2011-18-15, with revised service information. At the applicable time
specified in paragraph (g)(1) or (g)(2) of this AD: Do a torque
check to determine if the bolt preload is correct, and if the
preload is correct, before further flight, do a detailed inspection
of each barrel nut and cradle for cracking, pitting or corrosion, in
accordance with paragraph 3.B., part A, of the Accomplishment
Instructions of Bombardier Alert Service Bulletin A84-57-25, dated
July 20, 2011; or Bombardier Alert Service Bulletin A84-57-25,
Revision A, dated July 16, 2018. After the effective date of this
AD, only Bombardier Alert Service Bulletin A84-57-25, Revision A,
dated July 16, 2018, may be used. Repeat the torque check and, as
applicable, the inspection thereafter at intervals not to exceed
2,000 flight hours or 12 months, whichever occurs first.
(1) For airplanes that have accumulated 1,900 or more total
flight hours as of September 15, 2011 (the effective date of AD
2011-18-15), or for which it has been 12 months or more since the
date of issuance of the original Canadian airworthiness certificate
or the date of issuance of the original Canadian export certificate
of airworthiness as of September 15, 2011: Within 100 flight hours
or 10 days after September 15, 2011, whichever occurs first.
(2) For airplanes that have accumulated less than 1,900 total
flight hours as of September 15, 2011 (the effective date of AD
2011-18-15), and for which it has been less than 12 months since the
date of issuance of the original Canadian airworthiness certificate
or the date of issuance of the original Canadian export certificate
of airworthiness as of September 15, 2011: Prior to the accumulation
of 2,000 total flight hours or within 12 months since the date of
issuance of the original Canadian standard airworthiness certificate
or the date of issuance of the original Canadian export certificate
of airworthiness, whichever occurs first.
(h) Retained Corrective Actions for Incorrect Bolt Preload, With
Revised Service Information
This paragraph restates the requirements of paragraph (h) of AD
2011-18-15, with revised service information. If any bolt preload is
found to be incorrect (i.e., the ring can be rotated during any
torque check required by paragraph (g) of this AD), before further
flight, replace all hardware at that location (except the saddle
washer and retainer) in accordance with paragraph 3.B., part B, of
the Accomplishment Instructions of Bombardier Alert Service Bulletin
A84-57-25, dated July 20, 2011; or paragraph 3.B. of the
Accomplishment Instructions of Bombardier Service Bulletin 84-57-26,
Revision C, dated July 16, 2018. After the effective date of this
AD, only Bombardier Service Bulletin 84-57-26, Revision C, dated
July 16, 2018, may be used.
(i) Retained Corrective Actions for Barrel Nut/Cradle Discrepancies,
With Revised Service Information
This paragraph restates the requirements of paragraph (i) of AD
2011-18-15, with revised service information. If any crack, pitting,
or corrosion of the barrel nut or cradle is found during any
inspection required by paragraph (g) of this AD, before further
flight, replace all hardware at that location (except the saddle
washer and retainer) in accordance with paragraph 3.B., part B, of
the Accomplishment Instructions of Bombardier Alert Service Bulletin
A84-57-25, dated July 20, 2011; or paragraph 3.B. of the
Accomplishment Instructions of Bombardier Service Bulletin 84-57-26,
Revision C, dated July 16, 2018. After the effective date of this
AD, only Bombardier Service Bulletin 84-57-26, Revision C, dated
July 16, 2018, may be used.
(j) New Requirement of This AD: Replacement and Visual Inspection
Within 12,000 flight hours or 72 months after the effective date
of this AD, whichever occurs first: Do a visual inspection of the
saddle washer and retainer for any damage (cracks) or corrosion; and
replace the wing front spar barrel nuts, bolts, and pre-load
indicating washers; in accordance with paragraph 3.B. of the
Accomplishment Instructions of Bombardier Service Bulletin 84-57-26,
Revision C, dated July 16, 2018.
(k) New Corrective Actions for Damage (Cracks) or Corrosion
If any damage (cracks) or corrosion is found during any
inspection required by paragraph (j) of this AD: Before further
flight, accomplish corrective actions in accordance with the
procedures specified in paragraph (p)(2) of this AD.
(l) New Provision of This AD: Terminating Actions for Repetitive Torque
Checks and Detailed Inspections
Accomplishment of the applicable actions required by paragraphs
(j) and (k) of this AD, at all four barrel nut locations, terminates
the repetitive torque checks and detailed inspections of paragraph
(g) of this AD.
(m) Parts Installation Prohibition
As of the effective date of this AD, no person may install, on
any airplane, a barrel nut having part number DSC228-16.
(n) Retained Special Flight Permit Provisions, With No Changes
This paragraph restates the requirements of paragraph (k) of AD
2011-18-15, with no changes. Special flight permits, as described in
14 CFR 21.197 and 21.199, may be issued to operate the airplane to a
location where the requirements of this AD can be accomplished, but
concurrence by the Manager, New York ACO Branch, FAA, is required
before issuance of the special flight permit. Before using any
approved special flight permits, notify your principal maintenance
inspector (PMI) or principal avionics inspector (PAI), as
appropriate, or lacking a principal inspector, your local Flight
Standards District Office (FSDO). Operators must request a repair
drawing from
[[Page 32667]]
Bombardier, which provides recommendations for a one-time special
flight permit. The repair drawing will be applicable to the
operator's aircraft serial number only. Special flight permits may
be permitted provided that the conditions specified in paragraphs
(n)(1), (n)(2), (n)(3), (n)(4), and (n)(5) of this AD are met.
(1) Only one barrel nut out of four is cracked, one cradle is
cracked, or one washer is loose; all other strut (wing front spar)
bolt locations must be free of damage.
(2) The airplane must operate with reduced airspeed not to
exceed 180 KIAS (knots indicated air speed). No passengers and no
cargo are onboard.
(3) The airplane must not operate in known or forecast
turbulence, other than light turbulence.
(4) The airplane descent rate on landing flare-out is not to
exceed 5 feet per second.
(5) Heavy braking or hard turning of the airplane upon landing
is to be avoided if possible.
(o) Credit for Previous Actions
(1) This paragraph restates the provisions of paragraph (j) of
AD 2011-18-15, with revised formatting and updated service
information. This paragraph provides credit for torque checks,
initial inspections, and replacements required by paragraphs (g) and
(h) of this AD, if those actions were performed before the effective
date of this AD using the service information specified in
paragraphs (o)(1)(i) through (o)(1)(v) of this AD, which is not
incorporated by reference in this AD. The repetitive inspections
required by paragraph (g) of this AD must be continued at the time
specified.
(i) Bombardier Alert Service Bulletin A84-57-19, dated February
1, 2008.
(ii) Bombardier Alert Service Bulletin A84-57-19, Revision A,
dated February 6, 2008.
(iii) Bombardier Alert Service Bulletin A84-57-19, Revision B,
dated March 6, 2008.
(iv) Bombardier Alert Service Bulletin A84-57-19, Revision C,
dated August 20, 2008.
(v) Bombardier Alert Service Bulletin A84-57-19, Revision D,
dated August 12, 2011.
(2) This paragraph provides credit for the actions required by
paragraphs (h), (i), (j), and (k) of this AD, if those actions were
performed before the effective date of this AD using the service
information specified in paragraphs (o)(2)(i) through (o)(2)(iii) of
this AD. This service information is not incorporated by reference
in this AD.
(i) Bombardier Service Bulletin 84-57-26, dated March 21, 2013.
(ii) Bombardier Service Bulletin 84-57-26, Revision A, dated
July 18, 2014.
(iii) Bombardier Service Bulletin 84-57-26, Revision B, dated
February 26, 2015.
(3) This paragraph provides credit for the actions required by
paragraphs (h) and (i) of this AD, if those actions were performed
before the effective date of this AD using the service information
specified in paragraphs (o)(3)(i) and (o)(3)(ii) of this AD.
(i) Bombardier Alert Service Bulletin A84-57-25, dated July 20,
2011, which was incorporated by reference in AD 2011-18-15.
(ii) Bombardier Alert Service Bulletin A84-57-25, Revision A,
dated July 16, 2018, which is incorporated by reference in this AD.
(p) 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; phone: 516-228-7300; fax: 516-794-5531. Before
using any approved AMOC, notify your appropriate principal
inspector, or lacking a principal inspector, the manager of the
local flight standards district office/certificate holding district
office.
(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.
(3) AMOCs approved previously for AD 2011-18-15 are approved as
AMOCs for the corresponding provisions of this AD.
(q) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian AD CF-2011-24R1, dated January 21, 2019, 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-2019-0493.
(2) For more information about this AD, contact Andrea Jimenez,
Aerospace Engineer, Airframe and Propulsion Section, FAA, New York
ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
phone: 516-228-7330; fax: 516-794-5531; email: [email protected].
(3) For service information identified in this AD, contact
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt
Boulevard, Toronto, Ontario M3K 1Y5, Canada; phone: 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 Des Moines, Washington, on June 28, 2019.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-14391 Filed 7-8-19; 8:45 am]
BILLING CODE 4910-13-P
