AD 2019-20-09

[Federal Register Volume 84, Number 205 (Wednesday, October 23, 2019)]
[Rules and Regulations]
[Pages 56680-56684]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2019-23076]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0493; Product Identifier 2019-NM-043-AD; Amendment 
39-19762; AD 2019-20-09]
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.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2011-18-
15, which applied to certain De Havilland Aircraft of Canada Limited 
Model DHC-8-400 series airplanes. AD 2011-18-15 required 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 certain hardware if 
necessary. This AD continues to require those actions. This AD also 
requires new inspections and replacement of certain hardware, which 
would terminate the repetitive torque checks and inspections; and 
removes airplanes from the applicability. 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 the 
unsafe condition on these products.

DATES: This AD is effective November 27, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 27, 
2019.

[[Page 56681]]


ADDRESSES: For service information identified in this final rule, 
contact De Havilland Aircraft of Canada Ltd., Q-Series Technical Help 
Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; phone: 
416-375-4000; fax: 416-375-4539; email: <a href="/cdn-cgi/l/email-protection#8cf8e4e8cce8e9e4edfae5e0e0ede2e8a2efe3e1"><span class="__cf_email__" data-cfemail="0d7965694d6968656c7b6461616c6369236e6260">[email&#160;protected]</span></a>; internet: 
<a href="https://dehavilland.com">https://dehavilland.com</a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating 
Docket No. FAA-2019-0493.

Examining the AD Docket

    You may examine the AD docket on the internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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 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.

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: <a href="/cdn-cgi/l/email-protection#9ea7b3ffe8edb3f0e7fffdf1b3fdf1eddef8ffffb0f9f1e8"><span class="__cf_email__" data-cfemail="c7feeaa6b1b4eaa9bea6a4a8eaa4a8b487a1a6a6e9a0a8b1">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Discussion

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian AD 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 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and 
locating Docket No. FAA-2019-0493.
    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2011-18-15, Amendment 39-16797 (76 FR 
54093, August 31, 2011) (``AD 2011-18-15''). AD 2011-18-15 applied to 
certain De Havilland Aircraft of Canada Limited Model DHC-8-400 series 
airplanes. The NPRM published in the Federal Register on July 9, 2019 
(84 FR 32664). The NPRM 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 
NPRM proposed to continue to require 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. The NPRM also 
proposed to require new inspections and replacement of certain 
hardware, which would terminate the repetitive torque checks and 
inspections; and remove airplanes from the applicability. We are 
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. See the MCAI for additional background information.

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule. The FAA received no comments on the NPRM or 
on the determination of the cost to the public.

Explanation of Changes Made to This Final Rule

    The FAA has revised this final rule to identify the legal name of 
the manufacturer as published in the most recent type certificate data 
sheet (TCDS) for the affected airplane models.
    The FAA has revised paragraph (n) of this AD to refer to De 
Havilland Aircraft of Canada Limited (the current TCDS holder) as the 
appropriate contact for the referenced repair drawing.

Conclusion

    The FAA reviewed the relevant data and determined that air safety 
and the public interest require adopting this final rule as proposed, 
with the changes described previously and minor editorial changes. The 
FAA has determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
    <bullet> 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.
    <bullet> 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.
    <bullet> 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 preload 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.

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 2011-18-15...  15 work-hours x $85 per          $10,492         $11,767        $635,418
                                         hour = $1,275.
New actions...........................  15 work-hours x $85 per           10,492          11,767         635,418
                                         hour = $1,275.
----------------------------------------------------------------------------------------------------------------


[[Page 56682]]

    The FAA has received no definitive data that would enable us to 
provide cost estimates for the on-condition repairs 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.
    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) 
2011-18-15, Amendment 39-16797 (76 FR 54093, August 31, 2011), and 
adding the following new AD:

2019-20-09 De Havilland Aircraft of Canada Limited (Type Certificate 
Previously Held by Bombardier, Inc.): Amendment 39-19762; Docket No. 
FAA-2019-0493; Product Identifier 2019-NM-043-AD.

(a) Effective Date

    This AD is effective November 27, 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 De Havilland Aircraft of Canada Limited 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 Checks and 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 (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 Service Bulletin A84-57-25, Revision A, 
dated July 16, 2018. After the effective date of this AD, only 
Bombardier 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

[[Page 56683]]

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 preload 
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 Revised Compliance 
Language

    This paragraph restates the requirements of paragraph (k) of AD 
2011-18-15, with revised compliance language. 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 Bombardier, Inc., or De Havilland 
Aircraft of Canada Limited, which provides recommendations for a 
one-time special flight permit. After the effective date of this AD, 
only De Havilland Aircraft of Canada Limited may provide the repair 
drawing. 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) through 
(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 (v) of this AD, which is not 
incorporated by reference in this AD. The repetitive torque checks, 
and as applicable, the 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) through (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 (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 (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 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 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.
    (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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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: <a href="/cdn-cgi/l/email-protection#6a53470b1c194704130b0905470905192a0c0b0b440d051c"><span class="__cf_email__" data-cfemail="794054180f0a541700181a16541a160a391f1818571e160f">[email&#160;protected]</span></a>.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (r)(4) and (5) of this AD.

(r) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
November 27, 2019.
    (i) Bombardier Service Bulletin A84-57-25, Revision A, dated 
July 16, 2018.
    (ii) Bombardier Service Bulletin 84-57-26, Revision C, dated 
July 16, 2018.
    (4) For service information identified in this AD, contact De 
Havilland Aircraft of Canada Ltd., Q-Series Technical Help Desk, 123 
Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; phone: 416-375-
4000; fax:

[[Page 56684]]

416-375-4539; email: <a href="/cdn-cgi/l/email-protection#add9c5c9edc9c8c5ccdbc4c1c1ccc3c983cec2c0"><span class="__cf_email__" data-cfemail="3c4854587c5859545d4a5550505d5258125f5351">[email&#160;protected]</span></a>; internet: <a href="https://dehavilland.com">https://dehavilland.com</a>.
    (5) 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.
    (6) 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 <a href="/cdn-cgi/l/email-protection#dcbab9b8aeb9bbf2b0b9bbbdb09cb2bdaebdf2bbb3aa"><span class="__cf_email__" data-cfemail="a0c6c5c4d2c5c78eccc5c7c1cce0cec1d2c18ec7cfd6">[email&#160;protected]</span></a>, or go to: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Des Moines, Washington, on October 7, 2019.
Michael Kaszycki,
Acting Manager, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-23076 Filed 10-22-19; 8:45 am]
 BILLING CODE 4910-13-P