[Federal Register Volume 84, Number 234 (Thursday, December 5, 2019)]
[Rules and Regulations]
[Pages 66582-66586]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-26232]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0479; Product Identifier 2019-NM-020-AD; Amendment
39-19790; AD 2019-22-11]
RIN 2120-AA64
Airworthiness Directives; De Havilland Aircraft of Canada Limited
(Type Certificate Previously Held by Bombardier, Inc.) Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2009-09-
02, which applied to certain Bombardier, Inc., Model DHC-8-400 series
airplanes. AD 2009-09-02 required repetitive inspections for damage of
certain main landing gear (MLG) forward stabilizer brace assemblies,
repetitive inspections for cracking of both MLG forward stabilizer
braces, liquid penetrant inspections for cracking, and corrective
actions if necessary. This AD retains the existing actions and also
requires installation of an elbow restrictor. This AD was prompted by
reports of failures of the aft hinge of the MLG forward stabilizer
brace due to fatigue cracks. The FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective January 9, 2020.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 9,
2020.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of May 6,
2009 (74 FR 18121, April 21, 2009).
ADDRESSES: For service information identified in this final rule,
contact De Havilland Aircraft of Canada Limited, 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://dehavilland.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-2019-0479.
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-
0479; 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 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.
[[Page 66583]]
FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer,
Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600
Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7330;
fax 516-794-5531; email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian AD CF-2009-11R2, dated May
31, 2018 (also referred to as the Mandatory Continuing Airworthiness
Information, or ``the MCAI''), to correct an unsafe condition for
certain Bombardier, Inc., Model DHC-8-400 series airplanes. 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-
0479.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2009-09-02, Amendment 39-15888 (74 FR
18121, April 21, 2009) (``AD 2009-09-02''). AD 2009-09-02 applied to
certain Bombardier Model DHC-8-400 series airplanes. The NPRM published
in the Federal Register on July 12, 2019 (84 FR 33185). The NPRM was
prompted by reports of failures of the aft hinge of the MLG forward
stabilizer brace due to fatigue cracks. The NPRM proposed to continue
to require inspections for damage (including excessive wear, corrosion,
foreign object damage, and cracking) of certain MLG forward stabilizer
brace assemblies and applicable corrective actions; and repetitive
inspections for cracking of both MLG forward stabilizer braces,
applicable liquid penetrant inspections for cracking, and corrective
actions if necessary. The NPRM also proposed to require installation of
an elbow restrictor. The FAA is issuing this AD to address failure of
the stabilizer brace, which could result in the collapse of the MLG.
See the MCAI for additional background information.
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The following presents the comments
received on the NPRM and the FAA's response to each comment.
Support for the NPRM
Air Line Pilots Association, International (ALPA) stated its
support for the NPRM.
Request To Exclude Certain Service Information Procedures
Horizon Air requested that paragraphs (h) and (k) of the proposed
AD refer specifically to paragraph 3.B., ``Procedure,'' in the
Accomplishment Instructions of the referenced service information
rather than ``the Accomplishment Instructions.'' Horizon Air stated
that the ``Job-Set Up'' and ``Close Out'' procedures in the
Accomplishment Instructions of the applicable service information do
not directly correct the unsafe condition.
The FAA agrees with the commenter's request for the reason provided
above. The FAA has revised paragraphs (h) and (k) of this AD to require
accomplishment of paragraph 3.B., ``Procedure,'' of the Accomplishment
Instructions of the applicable service information.
Explanation of Additional Change Made to This Final Rule
The FAA has revised this final rule to identify the legal name of
the manufacturer, De Havilland Aircraft of Canada Limited, as published
in the most recent type certificate data sheet for the affected
airplane model.
Conclusion
The FAA reviewed the relevant data, considered the comments
received, and determined that air safety and the public interest
require adopting this final rule with the changes described previously
and minor editorial changes. The FAA has 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.
The FAA 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 Service Bulletin 84-32-69, Revision C, dated
January 20, 2011, which describes procedures for replacing the standard
elbow fitting with a new restrictor elbow fitting.
Bombardier Service Bulletin 84-32-76, Revision B, dated
August 1, 2018, which describes procedures for replacing the standard
elbow fitting with a new restrictor elbow fitting and introduction of a
new configuration stabilizer brace assembly.
Bombardier Repair Drawing 8/4-32-099, Issue 4, dated
September 4, 2018, which describes, among other actions, procedures for
inspections for cracking of the apex lug stop on the MLG forward
stabilizer brace assembly.
UTC Aerospace Systems Service Concession Request 026-09,
Revision H, dated August 29, 2018, which describes, among other
actions, procedures for inspections for excessive wear of the apex pins
on the MLG forward stabilizer brace assembly.
This AD also requires the following service information, which the
Director of the Federal Register approved for incorporation by
reference as of May 6, 2009 (75 FR 18121, April 21, 2009).
Bombardier Q400 All Operator Message 338, dated February
23, 2009.
Bombardier Repair Drawing 8/4-32-099, Issue 1, dated March
10, 2009.
Goodrich Service Concession Request 026-09, Revision B,
dated March 10, 2009.
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
The FAA estimates that this AD affects 54 airplanes of U.S.
registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2009-09-02... 8 work-hours x $85 per $0 $680 $36,720
hour = $680.
New actions........................... 19 work-hours x $85 per 10,867 12,482 674,028
hour = $1,615.
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[[Page 66584]]
The FAA has received no definitive data that would enable it to
provide cost estimates for the on-condition actions specified in this
AD.
According to the manufacturer, some or all of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected individuals. The FAA does not control warranty coverage for
affected individuals. As a result, the FAA has included all known costs
in the cost estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
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 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 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) Will not affect intrastate aviation in Alaska, and
(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.
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)
2009-09-02, Amendment 39-15888 (74 FR 18121, April 21, 2009), and
adding the following new AD:
2019-22-11 De Havilland Aircraft of Canada Limited (Type Certificate
Previously Held by Bombardier, Inc.): Amendment 39-19790; Docket No.
FAA-2019-0479; Product Identifier 2019-NM-020-AD.
(a) Effective Date
This AD is effective January 9, 2020.
(b) Affected ADs
This AD replaces AD 2009-09-02, Amendment 39-15888 (74 FR 18121,
April 21, 2009) (``AD 2009-09-02'').
(c) Applicability
This AD applies to De Havilland Aircraft of Canada Limited (Type
Certificate Previously Held by Bombardier, Inc.) Model DHC-8-400, -
401, and -402 airplanes, certificated in any category, serial
numbers 4001, 4003, and subsequent, equipped with main landing gear
(MLG) forward stabilizer brace part number (P/N) 46401-7.
(d) Subject
Air Transport Association (ATA) of America Code 32, Main landing
gear.
(e) Reason
This AD was prompted by reports of failures of the aft hinge of
the MLG forward stabilizer brace due to fatigue cracks. The FAA is
issuing this AD to address failure of the stabilizer brace, which
could result in the collapse of the MLG.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspection and Corrective Actions, With Revised Service
Information and Removed Reporting Requirement
This paragraph restates the requirements of paragraph (f) of AD
2009-09-02, with new service information and removed reporting
requirement. Unless already done, do the following actions:
(1) At the applicable time specified in one of paragraphs
(g)(1)(i) through (iv) of this AD: Perform non-destructive
inspections for damage of the MLG forward stabilizer brace
assemblies P/N 46401-7, in accordance with Bombardier Repair Drawing
8/4-32-099, Issue 1, dated March 10, 2009, and Goodrich Service
Concession Request 026-09, Revision B, dated March 10, 2009; or
Bombardier Repair Drawing 8/4-32-099, Issue 4, dated September 4,
2018, and UTC Aerospace Systems Service Concession Request 026-09,
Revision H, dated August 29, 2018. Repeat the inspection thereafter
at intervals not to exceed 2,000 flight cycles. As of the effective
date of this AD, use Bombardier Repair Drawing 8/4-32-099, Issue 4,
dated September 4, 2018, and UTC Aerospace Systems Service
Concession Request 026-09, Revision H, dated August 29, 2018, for
the actions required by this paragraph.
(i) For airplanes with MLG forward stabilizer braces that have
accumulated 12,000 or more total flight cycles as of May 6, 2009
(the effective date of AD 2009-09-02): Inspect within 50 flight
cycles after May 6, 2009.
(ii) For airplanes with MLG forward stabilizer braces that have
accumulated 9,000 or more total flight cycles but fewer than 12,000
total flight cycles as of May 6, 2009 (the effective date of AD
2009-09-02): Inspect before the accumulation of 12,050 total flight
cycles, or within 500 flight cycles after May 6, 2009, whichever
occurs earlier.
(iii) For airplanes with MLG forward stabilizer braces that have
accumulated 4,500 or more total flight cycles but fewer than 9,000
total flight cycles as of May 6, 2009 (the effective date of AD
2009-09-02): Inspect before the accumulation of 9,500 total flight
cycles, or within 1,500 flight cycles after May 6, 2009, whichever
occurs earlier.
(iv) For airplanes with MLG forward stabilizer braces that have
accumulated fewer than 4,500 total flight cycles as of May 6, 2009
(the effective date of AD 2009-09-02): Inspect before the
accumulation of 6,000 total flight cycles.
(2) If any damage is found during any inspection required by
paragraph (g)(1) of this AD, before further flight, do all
applicable corrective actions in accordance with Goodrich Service
Concession Request 026-09, Revision B, dated March 10, 2009; or UTC
Aerospace Systems Service Concession Request 026-09, Revision H,
dated August 29, 2018; except as provided by paragraphs (g)(3)
through (6) of this AD. As of the effective date of this AD, use UTC
Aerospace Systems Service Concession Request 026-09, Revision H,
dated August 29, 2018, for the actions required by this paragraph.
(3) For airplanes on which step 24. of Goodrich Service
Concession Request 026-09, Revision B, dated March 10, 2009, has
been done: Within 1,200 flight cycles after May 6, 2009 (the
effective date of AD 2009-
[[Page 66585]]
09-02), rework the MLG forward stabilizer brace, and except for
airplanes on which the rework has been done, within 600 flight
cycles after May 6, 2009, do a detailed visual inspection for damage
of the stabilizer brace apex lugs, in accordance with Goodrich
Service Concession Request 026-09, Revision B, dated March 10, 2009;
or UTC Aerospace Systems Service Concession Request 026-09, Revision
H, dated August 29, 2018. If any damage is found, repair before
further flight in accordance with Section C of Goodrich Service
Concession Request 026-09, Revision B, dated March 10, 2009; or
Section C of UTC Aerospace Systems Service Concession Request 026-
09, Revision H, dated August 29, 2018. As of the effective date of
this AD, use UTC Aerospace Systems Service Concession Request 026-
09, Revision H, dated August 29, 2018, for the actions required by
this paragraph.
(4) At the applicable time specified in one of paragraphs
(g)(4)(i) through (iii) of this AD, replace the forward stabilizer
brace assembly, in accordance with Goodrich Service Concession
Request 026-09, Revision B, dated March 10, 2009; or UTC Aerospace
Systems Service Concession Request 026-09, Revision H, dated August
29, 2018. As of the effective date of this AD, use UTC Aerospace
Systems Service Concession Request 026-09, Revision H, dated August
29, 2018, for the actions required by this paragraph.
(i) For airplanes on which cracking is found during any
inspection required by this AD, and the cracking exceeds the limit
specified in paragraph (g)(4)(i)(A) or (B) of this AD, as
applicable: Replace the assembly before further flight.
(A) For cracking found before the effective date of this AD: The
limit specified in Section C of Goodrich Service Concession Request
026-09, Revision B, dated March 10, 2009.
(B) For cracking found on or after the effective date of this
AD: The limit specified in Section C or Section D of UTC Aerospace
Systems Service Concession Request 026-09, Revision H, dated August
29, 2018.
(ii) For airplanes on which any cracking is found after the
rework specified in Section C of Goodrich Service Concession Request
026-09, Revision B, dated March 10, 2009; or specified in Section C
or Section D of UTC Aerospace Systems Service Concession Request
026-09, Revision H, dated August 29, 2018: Replace the assembly
before further flight.
(iii) For airplanes on which no cracking is found after the
rework specified in Section C of Goodrich Service Concession Request
026-09, Revision B, dated March 10, 2009; or specified in Section C
or Section D of UTC Aerospace Systems Service Concession Request
026-09, Revision H, dated August 29, 2018: Replace the assembly
within 2,700 flight cycles after doing the rework.
(5) If foreign object damage is found during any inspection
required by this AD, or if damage is found to a forward stabilizer
brace lug or stop bracket retention hole apex bushing, before
further flight, repair using a method approved by the Manager, New
York ACO Branch, FAA; or Transport Canada Civil Aviation (TCCA); or
Bombardier, Inc.'s TCCA Design Approval Organization (DAO); or De
Havilland Aircraft of Canada Limited's TCCA DAO. If approved by the
DAO, the approval must include the DAO-authorized signature.
(6) If any crack is found during the visual inspection under 10X
magnification, repair before further flight, in accordance with
Goodrich Service Concession Request 026-09, Revision B, dated March
10, 2009; or UTC Aerospace Systems Service Concession Request 026-
09, Revision H, dated August 29, 2018. As of the effective date of
this AD, use UTC Aerospace Systems Service Concession Request 026-
09, Revision H, dated August 29, 2018, for the actions required by
this paragraph.
(7) Before the accumulation of 6,000 total flight cycles on the
MLG forward stabilizer braces, or within 600 flight hours after May
6, 2009 (the effective date of AD 2009-09-02), whichever occurs
later: Do a detailed visual inspection for cracking of both MLG
forward stabilizer braces and do all applicable liquid penetrant
inspections for cracking, in accordance with Bombardier Q400 All
Operator Message 338, dated February 23, 2009. Repeat the inspection
thereafter at intervals not to exceed 600 flight hours. If any
cracking is found during any inspection required by this paragraph,
repair before further flight in accordance with Bombardier Repair
Drawing 8/4-32-099, Issue 1, dated March 10, 2009, and Goodrich
Service Concession Request 026-09, Revision B, dated March 10, 2009;
or Bombardier Repair Drawing 8/4-32-099, Issue 4, dated September 4,
2018, and UTC Aerospace Systems Service Concession Request 026-09,
Revision H, dated August 29, 2018. As of the effective date of this
AD, use Bombardier Repair Drawing 8/4-32-099, Issue 4, dated
September 4, 2018, and UTC Aerospace Systems Service Concession
Request 026-09, Revision H, dated August 29, 2018, to repair
cracking found during any inspection required by this paragraph.
(h) New Requirement of This AD: Installation of Elbow Restrictor
Within 2,000 flight hours or 12 months, whichever occurs first,
from the effective date of this AD: Install an elbow restrictor, P/N
46610-1, in accordance with paragraph 3.B., ``Procedure,'' of the
Accomplishment Instructions of Bombardier Service Bulletin 84-32-69,
Revision C, dated January 20, 2011.
(i) Terminating Actions
(1) Installation of an elbow restrictor as required by paragraph
(h) of this AD terminates the repetitive inspection requirements of
paragraphs (g)(1) and (7) of this AD.
(2) Installation of an elbow restrictor as required by paragraph
(h) of this AD terminates the replacement of the forward stabilizer
brace assembly requirement of paragraph (g)(4)(iii) of this AD.
(j) New Requirement of This AD: Revised Repetitive Inspections of the
MLG Forward Stabilizer Brace
(1) Within 2,000 flight cycles after the installation specified
in paragraph (h) of this AD, or within 12 months after the effective
date, whichever occurs later, do the non-destructive inspection, in
accordance with Bombardier Repair Drawing 8/4-32-099, Issue 4, dated
September 4, 2018, and UTC Aerospace Systems Service Concession
Request 026-09, Revision H, dated August 29, 2018. Thereafter,
repeat the non-destructive inspection at the times specified in
paragraph (j)(2) of this AD.
(2) Repeat the non-destructive inspection required in paragraph
(j)(1) of this AD at the applicable intervals specified in
paragraphs (j)(2)(i) through (iii) of this AD.
(i) For forward stabilizer braces, P/N 46401-7, that have not
had any required rework done, as specified in Goodrich or UTC
Aerospace Systems Service Concession Request 026-09, Section C or D,
and have had Bombardier Service Bulletin 84-32-69 or Bombardier
Service Bulletin 84-32-76 incorporated: Do the non-destructive
inspection at intervals not to exceed 6,000 flight cycles.
(ii) For forward stabilizer braces, P/N 46401-7, that have been
reworked in accordance with Goodrich or UTC Aerospace Systems
Service Concession Request 026-09, Section D, and have had
Bombardier Service Bulletin 84-32-69 or Bombardier Service Bulletin
84-32-76 incorporated: Do the non-destructive inspection at
intervals not to exceed 6,000 flight cycles.
(iii) For forward stabilizer braces, P/N 46401-7, that have been
reworked in accordance with Goodrich or UTC Aerospace Systems
Service Concession Request 026-09, Section C, and have had
Bombardier Service Bulletin 84-32-69 or Bombardier Service Bulletin
84-32-76 incorporated: Do the non-destructive inspection at
intervals not to exceed 3,000 flight cycles.
(k) Acceptable Method of Compliance for Paragraph (h) of This AD
Replacing the standard elbow fitting at the retract port of the
lock actuator with a new custom elbow fitting in accordance with
paragraph 3.B., ``Procedure,'' of the Accomplishment Instructions of
Bombardier Service Bulletin 84-32-76, Revision B, dated August 1,
2018, is an acceptable method of compliance for the installation
required by paragraph (h) of this AD.
(l) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraph (h) of this AD, if those actions were performed before the
effective date of this AD using the service information in one of
paragraphs (l)(1)(i) through (iii) of this AD.
(i) Bombardier Service Bulletin 84-32-69, dated June 30, 2009.
(ii) Bombardier Service Bulletin 84-32-69, Revision A, dated
August 19, 2009.
(iii) Bombardier Service Bulletin 84-32-69, Revision B, dated
September 17, 2009.
(2) This paragraph provides credit for actions specified in
paragraph (j) of this AD, if those actions were performed before the
effective date of this AD using the service information in one of
paragraphs (l)(2)(i) through (iii) of this AD.
(i) Bombardier Repair Drawing 8/4-32-099, Issue 1, dated March
10, 2009, and Goodrich Service Concession Request 026-09, Revision
B, dated March 10, 2009.
(ii) Bombardier Repair Drawing 8/4-32-099, Issue 2, dated April
20, 2009, and
[[Page 66586]]
Goodrich Service Concession Request 026-09, Revision C, dated April
17, 2009.
(iii) Bombardier Repair Drawing 8/4-32-099, Issue 3, dated
December 3, 2009, and Goodrich Service Concession Request 026-09,
Revision D, dated November 27, 2009.
(3) This paragraph provides credit for actions performed using
the method of compliance specified in paragraph (k) of this AD, if
those actions were performed before the effective date of this AD
using the service information in paragraph (l)(3)(i) or (ii) of this
AD.
(i) Bombardier Service Bulletin 84-32-76, dated May 20, 2010.
(ii) Bombardier Service Bulletin 84-32-76, Revision A, dated
June 19, 2014.
(m) 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. AMOCs approved previously in
accordance with AD 2009-09-02 are approved as AMOCs for the
corresponding requirements in paragraph (g) 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 TCCA; or Bombardier, Inc.'s TCCA DAO; or De
Havilland Aircraft of Canada Limited's TCCA DAO. If approved by the
DAO, the approval must include the DAO-authorized signature.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian AD CF-2009-11R2, dated May 31, 2018, 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-2019-0479.
(2) For more information about this AD, contact Andrea Jimenez,
Aerospace Engineer, Airframe and Mechanical Systems Section, FAA,
New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY
11590; telephone 516-228-7330; 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 (o)(5) and (6) of this AD.
(o) 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
January 9, 2020.
(i) Bombardier Repair Drawing 8/4-32-099, Issue 4, dated
September 4, 2018.
(ii) Bombardier Service Bulletin 84-32-69, Revision C, dated
January 20, 2011.
(iii) Bombardier Service Bulletin 84-32-76, Revision B, dated
August 1, 2018.
(iv) UTC Aerospace Systems Service Concession Request 026-09,
Revision H, dated August 29, 2018.
(4) The following service information was approved for IBR on
May 6, 2009 (75 FR 18121, April 21, 2009).
(i) Bombardier Q400 All Operator Message 338, dated February 23,
2009. The issue date is specified on only the first page of this
document.
(ii) Bombardier Repair Drawing 8/4-32-099, Issue 1, dated March
10, 2009. The issue date is specified on only the first page of this
document.
(iii) Goodrich Service Concession Request 026-09, Revision B,
dated March 10, 2009. Pages 1 through 8 of this document are
identified as Revision B, dated March 5, 2009; pages 9 through 22
are identified as Revision B, dated March 10, 2009.
(5) For service information identified in this AD, contact De
Havilland Aircraft of Canada Limited, 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://dehavilland.com.
(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, email [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on November 7, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-26232 Filed 12-4-19; 8:45 am]
BILLING CODE 4910-13-P