[Federal Register Volume 85, Number 49 (Thursday, March 12, 2020)]
[Proposed Rules]
[Pages 14423-14427]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-03271]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 85, No. 49 / Thursday, March 12, 2020 / 
Proposed Rules  

[[Page 14423]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0099; Product Identifier 2019-NM-169-AD]
RIN 2120-AA64


Airworthiness Directives; De Havilland Aircraft of Canada Limited 
(Type Certificate Previously Held by Bombardier, Inc.) Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2010-23-04, which applies to all De Havilland Aircraft of Canada 
Limited Model DHC-8-400 series airplanes. AD 2010-23-04 requires 
repetitive detailed inspections of the nacelle attachment fittings for 
cracks, a conductivity inspection of the nacelle attachment fittings, 
and replacement if necessary. Since AD 2010-23-04 was issued, the FAA 
has determined that it is necessary to do a replacement with new 
nacelle attachment fittings. This proposed AD would retain the 
requirements of AD 2010-23-04, remove a certain inspection requirement 
for certain airplanes, and add a new requirement to replace the rear 
spar fitting and nacelle attaching structure with a new nacelle 
attachment fitting. 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 April 27, 
2020.

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 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 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-2020-
0099; 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; telephone 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-2020-0099; 
Product Identifier 2019-NM-169-AD'' at the beginning of your comments. 
The FAA specifically invite 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 2010-23-04, Amendment 39-16493 (75 FR 68174, 
November 5, 2010) (``AD 2010-23-04''), for all De Havilland Aircraft of 
Canada Limited Model DHC-8-400 series airplanes. AD 2010-23-04 requires 
repetitive detailed inspections of the nacelle attachment fittings for 
cracks, a conductivity inspection of the nacelle attachment fittings, 
and replacement if necessary. AD 2010-23-04 resulted from reports of 
cracked nacelle attachment fittings, which a preliminary investigation 
determined to be caused by stress corrosion. The FAA issued AD 2010-23-
04 to address this condition, which, if not detected and corrected, 
could compromise the structural integrity of the nacelle attachment 
fitting and possibly result in collapse of the landing gear.

Actions Since AD 2010-23-04 Was Issued

    Since AD 2010-23-04 was issued, the FAA has determined that it is 
necessary to require a replacement with new nacelle attachment 
fittings, which would be terminating action for the inspections 
specified in AD 2010-23-04. Additionally, paragraph (i) of AD 2010-23-
04 requires repetitive detailed inspections for cracking on each of the 
four nacelle attachment fittings for airplanes having serial numbers 
4305 through 4313 inclusive, and 4316 and subsequent. The FAA has 
retained this inspection in paragraph (h) of this proposed AD, but 
serial numbers 4381 and subsequent were modified in production and 
cannot have the affected part installed, so those airplanes were 
removed from the retained actions in paragraph (h) of this proposed AD.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian AD CF-2010-30R2, dated July 
30, 2019 (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe

[[Page 14424]]

condition for all De Havilland Aircraft of Canada Limited 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-2020-0099.
    This proposed AD was prompted by a determination that it is 
necessary to install new nacelle attachment fitting in order to address 
the unsafe condition. The FAA is proposing this AD to address cracked 
nacelle attachment fittings, which a preliminary investigation 
determined to be caused by stress corrosion. This condition, if not 
detected and corrected, could compromise the structural integrity of 
the nacelle attachment fitting and possibly result in collapse of the 
landing gear. See the MCAI for additional background information.

Related Service Information Under 1 CFR Part 51

    Bombardier has issued Service Bulletin 84-54-14, Revision K, dated 
August 7, 2018. This service bulletin describes procedures for a 
conductivity inspection of the nacelle attachment fittings, repetitive 
detailed inspections of the nacelle attachment fittings for cracks, and 
replacement of the fitting.
    Bombardier has also issued Service Bulletin 84-54-16, Revision D, 
dated August 7, 2018. This service information describes procedures for 
replacing the rear spar nacelle attachment fitting and associated 
structure with a new nacelle attachment fitting, part number (P/N) 
8Z9305. The replacement includes applicable related investigative and 
corrective actions. The related investigative actions include an 
inspection of the internal bore and external surface of the main 
landing gear yoke pins, the drag strut pins, and the stabilizer brace 
pins for signs of corrosion and damage; an inspection of the inner bore 
and outer surface of the coat hangar pins for signs of corrosion and 
damage. The corrective actions include repair, rework, or replacement.
    Bombardier has also issued Modification Summary Package 
IS4Q5400012, Revision B, dated July 11, 2012. This service information 
describes procedures for applying a fay sealant gasket to the rear spar 
access fitting access panel.
    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 a 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 2010-
23-04. This proposed AD would also require accomplishing the actions 
specified in the service information described previously.

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 *
--------------------------------------------------------------------------------------------------------------------------------------------------------
               Action                      Labor cost                  Parts cost                  Cost per product            Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Retained actions from AD 2010-23-04  3 work-hours x $85 per  $0............................  $255........................  $13,770.
                                      hour = $255.
New proposed actions...............  320 work-hours x $85    Up to $104,739................  Up to $131,939..............  Up to $7,124,706.
                                      per hour = $27,200.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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.

Regulatory Findings

    The FAA has 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
    (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) 
2010-23-04, Amendment 39-16493 (75 FR 68174, November 5, 2010), and 
adding the following new AD:


[[Page 14425]]


De Havilland Aircraft of Canada Limited (Type Certificate Previously 
Held by Bombardier, Inc.): Docket No. FAA-2020-0099; Product 
Identifier 2019-NM-169-AD.

(a) Comments Due Date

    The FAA must receive comments by April 27, 2020.

(b) Affected ADs

    This AD replaces AD 2010-23-04, Amendment 39-16493 (75 FR 68174, 
November 5, 2010) (``AD 2010-23-04'').

(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 and subsequent.

(d) Subject

    Air Transport Association (ATA) of America Code 54, Nacelles/
pylons.

(e) Reason

    This AD was prompted by reports of cracked nacelle attachment 
fittings, which a preliminary investigation determined to be caused 
by stress corrosion. The FAA is issuing this AD to address this 
condition, which, if not detected and corrected, could compromise 
the structural integrity of the nacelle attachment fitting and 
possibly result in collapse of the landing gear.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Detailed and Conductivity Inspections and Replacement, 
With Revised Service Information and Revised Replacement Instructions

    This paragraph restates the requirements of paragraph (g) of AD 
2010-23-04, with revised service information and revised replacement 
instructions. For airplanes having serial numbers 4001 through 4304 
inclusive, 4314, and 4315: Within 100 flight hours after November 
22, 2010 (the effective date of AD 2010-23-04), do a detailed 
inspection for cracking, and a conductivity inspection on each of 
the 4 nacelle attachment fittings, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 84-54-14, 
Revision K, dated August 7, 2018. Repeat the detailed inspection at 
intervals not to exceed 300 flight hours, except as provided by 
paragraph (i) of this AD. Accomplishing the replacement specified in 
paragraph (g)(1)(ii) or (g)(2)(ii)(B) of this AD terminates the 
inspections required by this paragraph.
    (1) If any nacelle attachment fitting is found cracked, before 
further flight, do the action specified in paragraph (g)(1)(i) or 
(ii) of this AD. As of the effective date of this AD, only the 
action specified in paragraph (g)(1)(ii) of this AD may be done.
    (i) Replace the fitting with a new fitting in accordance with 
paragraph (2) of Part A of the Accomplishment Instructions of 
Bombardier Service Bulletin 84-54-14, Revision K, dated August 7, 
2018.
    (ii) Replace the rear spar nacelle attachment fitting and 
associated structure with a new nacelle attachment fitting, part 
number (P/N) 8Z9305, and do all applicable related investigative and 
corrective actions, in accordance with Part B of the Accomplishment 
Instructions of Bombardier Service Bulletin 84-54-16 Revision D, 
dated August 7, 2018. Do all applicable related investigative and 
corrective actions before further flight.
    (2) If the conductivity of any test points on any fitting is 
found to be greater than 45.0 percent International Annealed Copper 
Standard (IACS) or if the conductivity of any test points on any 
fitting is found to be less than 38.0 percent IACS, do the actions 
required by paragraphs (g)(2)(i) and (ii) of this AD.
    (i) Within 24 hours after accomplishing the conductivity 
inspection specified in paragraph (g) of this AD, do a detailed 
inspection of the nacelle attachment fitting for cracking, in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 84-54-14, Revision K, dated August 7, 2018, and 
repeat thereafter at intervals not to exceed 24 hours. If cracking 
is found, before further flight, replace the fitting with a new 
fitting in accordance with the requirements of paragraph (g)(2)(ii) 
of this AD. Replacement of the fitting terminates the daily detailed 
inspection requirements of this paragraph.
    (ii) Except as required by paragraph (g)(2)(i) of this AD: 
Within 300 flight hours after accomplishing the conductivity 
inspection specified in paragraph (g) of this AD, do the action 
specified in paragraph (g)(2)(ii)(A) or (B) of this AD. As of the 
effective date of this AD, only the action specified in paragraph 
(g)(2)(ii)(B) of this AD may be done.
    (A) Replace the fitting with a new fitting in accordance with 
paragraph (2) of Part A of the Accomplishment Instructions of 
Bombardier Service Bulletin 84-54-14, Revision K, dated August 7, 
2018.
    (B) Replace the rear spar nacelle attachment fitting and 
associated structure with a new nacelle attachment fitting, P/N 
8Z9305, and do all applicable related investigative and corrective 
actions, in accordance with Part B of the Accomplishment 
Instructions of Bombardier Service Bulletin 84-54-16 Revision D, 
dated August 7, 2018. Do all applicable related investigative and 
corrective actions before further flight.

(h) Retained Inspections and Replacement, With Revised Service 
Information, Revised Affected Airplanes, and Revised Replacement 
Instructions

    This paragraph restates the requirements of paragraph (i) of AD 
2010-23-04, with revised service information, revised affected 
airplanes, and revised replacement instructions. For airplanes 
having serial numbers 4305 through 4313 inclusive, and 4316 through 
4380 inclusive, and airplanes that have replaced nacelle attachment 
fitting(s) with P/N 854146663: Within 1,200 flight hours after 
November 22, 2010 (the effective date of AD 2010-23-04), do a 
detailed inspection for cracking on each of the 4 nacelle attachment 
fittings, in accordance with the Accomplishment Instructions of 
Bombardier Service Bulletin 84-54-14, Revision K, dated August 7, 
2018. If any nacelle attachment fitting is found cracked, before 
further flight, do the action specified in paragraph (h)(1) or (2) 
of this AD. As of the effective date of this AD, only the action 
specified in paragraph (h)(2) of this AD may be done. Thereafter, 
repeat the detailed inspection at intervals not to exceed 300 flight 
hours, except as provided by paragraph (i) of this AD. Accomplishing 
the replacement specified in paragraph (h)(2) of this AD terminates 
the inspections required by this paragraph.
    (1) Replace the fitting with a new fitting in accordance with 
paragraph (2) of Part A of the Accomplishment Instructions of 
Bombardier Service Bulletin 84-54-14, Revision K, dated August 7, 
2018.
    (2) Replace the rear spar nacelle attachment fitting and 
associated structure with a new nacelle attachment fitting, P/N 
8Z9305, and do all applicable related investigative and corrective 
actions, in accordance with Part B of the Accomplishment 
Instructions of Bombardier Service Bulletin 84-54-16 Revision D, 
dated August 7, 2018. Do all applicable related investigative and 
corrective actions before further flight.

(i) Retained Inspection Compliance Time, With Revised Service 
Information

    This paragraph restates the requirements of paragraph (j) of AD 
2010-23-04, with revised service information. For any fitting that 
is replaced in accordance with paragraph (3) of Part A of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-54-14, 
Revision J, dated September 17, 2010; or paragraph (2) of Part A of 
the Accomplishment Instructions of Bombardier Service Bulletin 84-
54-14, Revision K, dated August 7, 2018, as specified in paragraph 
(g) or (h) of this AD: Within 1,200 flight hours after replacing the 
fitting, do a detailed inspection of that replaced fitting as 
specified in paragraph (g) or (h) of this AD, and repeat the 
detailed inspection thereafter at intervals not to exceed 300 flight 
hours. Accomplishing the replacement specified in paragraph 
(g)(1)(ii), (g)(2)(ii)(B), or (h)(2) of this AD terminates the 
inspections required by this paragraph.

(j) Retained Credit for Previous Actions (Replacing the Fitting), With 
Revised Paragraph References

    This paragraph restates the credit provided in paragraph (k) of 
AD 2010-23-04, with revised paragraph references. Accomplishing the 
replacement of the nacelle fittings in accordance with any 
Bombardier service bulletin identified in figure 1 to paragraphs (j) 
and (k) of this AD before November 22, 2010 (the effective date of 
AD 2010-23-04) is also acceptable for compliance with the fitting 
replacements specified in paragraphs (g)(1)(i), (g)(2)(ii)(A), and 
(h)(1) of this AD.

[[Page 14426]]

[GRAPHIC] [TIFF OMITTED] TP12MR20.000

(k) Retained Credit for Previous Actions (Inspections), With No Changes

    This paragraph restates the credit provided in paragraph (l) of 
AD 2010-23-04, with no changes. Accomplishment of the inspections 
required by paragraphs (g) and (h) of this AD before November 22, 
2010 (the effective date of AD 2010-23-04) in accordance with any 
Bombardier service bulletin identified in figure 1 to paragraphs (j) 
and (k) of this AD is acceptable for compliance with the 
corresponding actions required by paragraphs (g) and (h) of this AD.

(l) New Requirements of This AD: Modification of the Rear Spar Fitting 
and Nacelle Attaching Structure

    For airplanes with nacelle attachment fitting P/N 85414663: 
Unless already done as specified in paragraph (g)(1)(ii), 
(g)(2)(ii)(B), or (h)(2) of this AD: Within 8,000 flight hours or 48 
months, whichever occurs first, from the effective date of this AD, 
replace the rear spar nacelle attachment fitting and associated 
structure with a new nacelle attachment fitting, P/N 8Z9305, and do 
all applicable related investigative and corrective actions, in 
accordance with Part B of the Accomplishment Instructions of 
Bombardier Service Bulletin 84-54-16, Revision D, dated August 7, 
2018. Do all applicable related investigative and corrective actions 
before further flight.

(m) New Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraphs (g) and (h) of this AD that are identified in Bombardier 
Service Bulletin 84-54-14, Revision K, dated August 7, 2018, if 
those actions were performed before the effective date of this AD 
using Bombardier Service Bulletin 84-54-14, Revision J, dated 
September 17, 2010, which was incorporated by reference in AD 2010-
23-04; except as provided by paragraph (p) of this AD.
    (2) This paragraph provides credit for accomplishing the 
replacement of the rear spar fitting and nacelle attaching structure 
required by paragraph (l) of this AD, if those actions were 
performed before the effective date of this AD using the service 
information specified in paragraphs (m)(2)(i) through (iii) of this 
AD.
    (i) Bombardier Service Bulletin 84-54-16, dated April 29, 2011.
    (ii) Bombardier Service Bulletin 84-54-16, Revision A, dated 
August 1, 2011.
    (iii) Bombardier Service Bulletin 84-54-16, Revision C, dated 
January 31, 2017.
    (3) This paragraph provides credit for accomplishing the 
replacement of the rear spar fitting and nacelle attaching structure 
required by paragraph (l) of this AD, if those actions were 
performed before the effective date of this AD using Bombardier 
Service Bulletin 84-54-16, Revision B, dated October 6, 2016, 
Although Bombardier Service Bulletin 84-54-16, Revision B, dated 
October 6, 2016, incorrectly stated that airworthiness limitations 
(AWLs) or damage tolerance inspections (DTIs) are not affected, they 
are affected. Refer to the applicable AWLs for Post/Pre-Modification 
Summary (ModSum) 4-113697 and Bombardier Service Bulletin 84-54-16 
in the existing maintenance requirements manual.
    (4) This paragraph provides credit for accomplishing the action 
identified in Bombardier Service Bulletin 84-54-14, Revision K, 
dated August 7, 2018, that are 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 
(m)(4)(i) through (iv) of this AD.
    (i) Bombardier Service Bulletin 84-54-15, dated August 20, 2010.
    (ii) Bombardier Service Bulletin 84-54-15, Revision A, dated 
October 25, 2010.
    (iii) Bombardier Service Bulletin 84-54-15, Revision B, dated 
February 2, 2017.
    (iv) Bombardier Service Bulletin 84-54-15, Revision C, dated 
August 7, 2018.

(n) Terminating Action for Certain Actions in Paragraphs (g), (h), and 
(i) of This AD

    Accomplishing the modification of the rear spar fitting and 
nacelle attaching structure required by paragraph (l) of this AD 
terminates the repetitive inspection required by paragraphs (g), 
(h), and (i) of this AD for that airplane.

(o) Parts Installation Limitations

    As of the effective date of this AD, no person may install a 
rear spar nacelle attachment fitting P/N 85414663 on any airplane.

(p) Credit for Alternative to Certain Credit Actions

    For airplanes on which Bombardier Service Bulletin 84 54 14, 
Revision J, dated September 17, 2010, was done before the effective 
date of this AD: As an alternative to applying sealant to each 
fitting and access panel as specified in paragraph C.(1) of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-54-14, 
Revision J, dated September 17, 2010, the use of the instructions of 
Bombardier Modification Summary Package IS4Q5400012, Revision B, 
dated July 11, 2012, to apply sealant is also

[[Page 14427]]

acceptable if accomplished before the effective date of this AD.

(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 2010-23-04, are approved 
as AMOCs for the corresponding provisions of this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain instructions from a manufacturer, the instructions must be 
accomplished using a method approved by the Manager, New York ACO 
Branch, FAA; or Transport Canada Civil Aviation (TCCA); or de 
Havilland'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 Airworthiness Directive CF-2010-30R2, dated July 30, 
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-2020-0099.
    (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; 
telephone 516-228-7330; fax 516-794-5531; email [email protected].
    (3) 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. 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 on February 12, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2020-03271 Filed 3-11-20; 8:45 am]
 BILLING CODE 4910-13-P