[Federal Register Volume 87, Number 18 (Thursday, January 27, 2022)]
[Rules and Regulations]
[Pages 4145-4148]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-01569]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0514; Project Identifier MCAI-2020-01570-T; 
Amendment 39-21890; AD 2022-01-02]
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 adopting a new airworthiness directive (AD) for 
certain De Havilland Aircraft of Canada Limited Model DHC-8-400, -401, 
and -402 airplanes. This AD was prompted by a report that the epoxy 
primer on the internal bore of the nacelle and landing gear attachment 
pins was not applied, and corrosion on the internal bore of the wing 
rear spar attachment pins was found. This AD requires doing a detailed 
visual inspection of the nacelle to wing rear spar attachment pins, and 
the nacelle and landing gear attachment pins, for any corrosion, and 
doing all applicable corrective actions. The FAA is issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective March 3, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of March 3, 
2022.

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 service information 
at the FAA, Airworthiness Products Section, Operational Safety 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-2021-0514.

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-2021-
0514; 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, 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.

FOR FURTHER INFORMATION CONTACT: Deep Gaurav, Aerospace Engineer, 
Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart 
Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7300; fax 516-
794-5531; email [email protected].

SUPPLEMENTARY INFORMATION:

Background

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued TCCA AD CF-2020-51R1, dated February 
24, 2021 (also referred to as the Mandatory Continuing Airworthiness 
Information, or the MCAI), to correct an unsafe condition for certain 
De Havilland Aircraft of Canada Limited Model DHC-8-400, -401, and -402 
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-2021-0514.
    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to certain De Havilland 
Aircraft of Canada Limited Model DHC-8-400, -401, and -402 airplanes. 
The NPRM published in the Federal Register on June 29, 2021 (86 FR 
34163). The NPRM was prompted by a report that the epoxy

[[Page 4146]]

primer on the internal bore of the nacelle and landing gear attachment 
pins was not applied, and corrosion on the internal bore of the wing 
rear spar attachment pins was found. The NPRM proposed to require doing 
a detailed visual inspection of the nacelle to wing rear spar 
attachment pins, and the nacelle and landing gear attachment pins, for 
any corrosion, and doing all applicable corrective actions. The FAA is 
issuing this AD to address premature corrosion and subsequent failure 
of the nacelle to landing gear and nacelle to rear wing spar attachment 
pins, which if undetected, could lead to a single or dual collapse of 
the main landing gear. 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.

Request To Use the Latest Service Information

    Horizon Air requested that the latest service information be used 
in the proposed AD. Horizon Air stated that since the NPRM was issued, 
the applicable service information specified in figure 1 to paragraph 
(g) of the proposed AD has been revised to De Havilland Aircraft of 
Canada Limited Service Bulletin 84-54-31, Revision C, dated March 15, 
2021. Horizon Air also requested that paragraph (h)(3) of the proposed 
AD be revised to allow credit for De Havilland Aircraft of Canada 
Limited Service Bulletin 84-54-31, Revision B, dated February 21, 2020, 
if those actions were performed before the effective date of the 
proposed AD.
    The FAA agrees to use the latest service information in this AD. De 
Havilland Aircraft of Canada Limited Service Bulletin 84-54-31, 
Revision C, dated March 15, 2021, adds information to the 
``Effectivity'' section for production airplanes, i.e., specifying 
airplane line numbers that will have certain ModSums (for application 
of primer and corrosion preventive compound) installed before delivery. 
This information does not affect the applicability of this AD.
    De Havilland Aircraft of Canada Limited Service Bulletin 84-54-31, 
Revision C, dated March 15, 2021, also adds additional acceptable 
polyurethane enamel, and clarifies that production pins can be used to 
replace corroded pins. These changes do not affect operators who use 
previous revisions of the service information to show compliance with 
this AD. There are no substantive changes to the procedures between 
Revision C of the service information and Revision B, which was 
proposed as required in the NPRM. Further, the technical content of 
this AD and the service information remains unchanged. The FAA has 
revised the ``Related Service Information Under 1 CFR part 51'' 
paragraph, Figure 1 to paragraph (g) of this AD, and paragraphs (g)(2) 
and (i) of this AD accordingly. The FAA has also added paragraph (h)(4) 
of this AD to specify the requested credit.

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

    De Havilland Aircraft of Canada Limited has issued Service Bulletin 
84-54-28, Revision B, dated January 24, 2020; and Service Bulletin 84-
54-31, Revision C, dated March 15, 2021. This service information 
describes procedures for doing a detailed visual inspection of the 
nacelle to wing rear spar attachment pins, and the nacelle and landing 
gear attachment pins, for any corrosion; and doing all applicable 
corrective actions. Corrective actions include applying epoxy primer to 
the bore surface of the pins, a fluorescent magnetic particle 
inspection for any cracking, corrosion removal, reworking and part 
marking certain pins, and replacing any cracked or corroded pins with 
serviceable pins. These documents are distinct since they apply to 
different airplane configurations.
    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 will affect 41 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
            Labor cost                Parts cost          Cost per  product           Cost on U.S.  operators
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Up to 9 work-hours x $85 per hour               $0  Up to $765...................  Up to $31,365.
 = Up to $765.
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    The FAA has received no definitive data on which to base the cost 
estimates for the on-condition actions specified in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    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

    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

[[Page 4147]]

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 adding the following new airworthiness 
directive:

2022-01-02 De Havilland Aircraft of Canada Limited (Type Certificate 
Previously Held by Bombardier, Inc.): Amendment 39-21890; Docket No. 
FAA-2021-0514; Project Identifier MCAI-2020-01570-T.

(a) Effective Date

    This airworthiness directive (AD) is effective March 3, 2022.

(b) Affected ADs

    None.

(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 through 4550 inclusive, 4583 through 4585 
inclusive, 4587, 4588, and 4590.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report that the epoxy primer on the 
internal bore of the nacelle and landing gear attachment pins was 
not applied, and corrosion on the internal bore of the wing rear 
spar attachment pins was found. The FAA is issuing this AD to 
address premature corrosion and subsequent failure of the nacelle to 
landing gear and nacelle to rear wing spar attachment pins, which if 
undetected, could lead to a single or dual collapse of the main 
landing gear.

(f) Compliance

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

(g) Inspection and Corrective Actions

    (1) At the applicable compliance times specified in paragraphs 
(g)(1)(i) through (iii) of this AD: Do a detailed visual inspection 
of the nacelle to wing rear spar attachment pins, and the nacelle 
and landing gear attachment pins, for any cracking or corrosion, and 
do all applicable corrective actions, in accordance with Part A or 
Part B, as applicable, of Section 3., ``Accomplishment 
Instructions,'' of the applicable service information specified in 
figure 1 to paragraph (g) of this AD. Do all applicable corrective 
actions before further flight.
[GRAPHIC] [TIFF OMITTED] TR27JA22.005

    (i) For nacelle to wing rear spar attachment pins, or nacelle 
and landing gear attachment pins, as applicable, that have 
accumulated less than 26,000 flight cycles as of the effective date 
of this AD, and have been in service less than 12 years from their 
entry-into-service as of the effective date of this AD: Prior to the 
pins reaching 14 years from their entry-into-service, or prior to 
the airplane reaching 30,000 total flight cycles, whichever occurs 
first.
    (ii) For nacelle to wing rear spar attachment pins, or nacelle 
and landing gear attachment pins, as applicable, that have 
accumulated 26,000 flight cycles or more as of the effective date of 
this AD, or have been in service 12 years or more from their entry-
into-service as of the effective date of this AD: Within 4 years or 
8,000 flight hours after the effective date of this AD, whichever 
occurs first.
    (iii) For airplanes on which the actions specified in Bombardier 
Service Bulletin 84-54-27, dated August 11, 2017; or Bombardier 
Service Bulletin 84-54-28, dated August 11, 2017; as applicable, 
have been accomplished: Within 14 years or 30,000 flight cycles 
after the date of incorporation of Bombardier Service Bulletin 84-
54-27, dated August 11, 2017; or Bombardier Service Bulletin 84-54-
28, dated August 11, 2017; as applicable, whichever occurs first.
    (2) For serial numbers 4583, 4584, 4585, 4587, 4588 and 4590: At 
the applicable compliance times specified in paragraphs (g)(1)(i) 
through (iii) of this AD, re-part mark the yoke attachment pin, in 
accordance with Part B of the Accomplishment Instructions of De 
Havilland Aircraft of Canada Limited Service Bulletin 84-54-31, 
Revision C, dated March 15, 2021.

(h) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(g) of this AD, if those actions were performed before the effective 
date of this AD using the applicable service information specified 
in paragraphs (h)(1) through (4) of this AD.
    (1) Bombardier Service Bulletin 84-54-28, Revision A, dated 
April 10, 2019.
    (2) Bombardier Service Bulletin 84-54-31, dated May 1, 2019.
    (3) Bombardier Service Bulletin 84-54-31, Revision A, dated 
October 15, 2019.
    (4) De Havilland Aircraft of Canada Limited Service Bulletin 84-
54-31, Revision B, dated February 21, 2020.

(i) No Reporting Requirement

    Although De Havilland Aircraft of Canada Limited Service 
Bulletin 84-54-28, Revision B, dated January 24, 2020; and De 
Havilland

[[Page 4148]]

Aircraft of Canada Limited Service Bulletin 84-54-31, Revision C, 
dated March 15, 2021; specify to submit certain information to the 
manufacturer, this AD does not include that requirement.

(j) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (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 responsible Flight Standards 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. Before 
using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
responsible Flight Standards Office.
    (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 Aircraft of Canada Limited's TCCA Design Approval 
Organization (DAO). If approved by the DAO, the approval must 
include the DAO-authorized signature.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) TCCA AD CF-2020-51R1, dated February 24, 2021, 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-2021-0514.
    (2) For more information about this AD, contact Deep Gaurav, 
Aerospace Engineer, Airframe and Propulsion Section, FAA, New York 
ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
telephone 516-228-7300; 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 (l)(3) and (4) of this AD.

(l) 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.
    (i) De Havilland Aircraft of Canada Limited Service Bulletin 84-
54-28, Revision B, dated January 24, 2020.
    (ii) De Havilland Aircraft of Canada Limited Service Bulletin 
84-54-31, Revision C, dated March 15, 2021.
    (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.
    (4) You may view this service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 2200 
South 216th St., Des Moines, WA. For information on the availability 
of this material at the FAA, call 206-231-3195.
    (5) 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 on December 21, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2022-01569 Filed 1-26-22; 8:45 am]
BILLING CODE 4910-13-P