AD 2017-13-09

[Federal Register Volume 82, Number 124 (Thursday, June 29, 2017)]
[Rules and Regulations]
[Pages 29376-29379]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2017-13411]



[[Page 29376]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-7529; Directorate Identifier 2014-NM-207-AD; 
Amendment 39-18939; AD 2017-13-09]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc., Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2014-16-02, 
which applied to certain Bombardier, Inc., Model CL-600-1A11 (CL-600) 
airplanes. AD 2014-16-02 required revising the airplane flight manual 
to prohibit thrust reverser operation, doing repetitive detailed 
inspections of both engine thrust reversers for cracks, and modifying 
the thrust reversers if necessary. The modification is also an interim 
(optional) terminating action for the repetitive inspections. This new 
AD adds a new terminating modification of the thrust reversers, which 
includes new inspections and repair, if necessary. This AD was prompted 
by a determination that it is necessary to add a requirement to repair 
or modify the thrust reversers, which would terminate the requirements 
of AD 2014-16-02. We are issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective August 3, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 3, 
2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of August 
12, 2014 (79 FR 46968, August 12, 2014).

ADDRESSES: For service information identified in this final rule, 
contact Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, 
Qu[eacute]bec H4S 1Y9, Canada; Widebody Customer Response Center North 
America; toll-free telephone number 1-866-538-1247 or direct-dial 
telephone number 1-514-855-2999; fax 514-855-7401; email 
<a href="/cdn-cgi/l/email-protection#91f0f2bfe8e4fdd1f0f4e3febff3fefcf3f0e3f5f8f4e3bff2fefc"><span class="__cf_email__" data-cfemail="bddcde93c4c8d1fddcd8cfd293dfd2d0dfdccfd9d4d8cf93ded2d0">[email&#160;protected]</span></a>; Internet <a href="http://www.bombardier.com">http://www.bombardier.com</a>. You may 
view this referenced service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the 
availability of this material at the FAA, call 425-227-1221. 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-2015-7529.

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-2015-
7529; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, 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: Cesar Gomez, Aerospace Engineer, 
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft 
Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, 
NY 11590; telephone 516-228-7318; fax 516-794-5531.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 to supersede AD 2014-16-02, Amendment 39-17926 (79 
FR 46968, August 12, 2014) (``AD 2014-16-02''). AD 2014-16-02 applied 
to certain Bombardier, Inc. Model CL-600-1A11 (CL-600) airplanes. The 
SNPRM published in the Federal Register on December 13, 2016 (81 FR 
89881) (``the SNPRM''). We preceded the SNPRM with a notice of proposed 
rulemaking (NPRM) that published in the Federal Register on December 
24, 2015 (80 FR 80293) (``the NPRM''). The NPRM was prompted by a 
determination that it is necessary to add a requirement to repair or 
modify the thrust reversers, which would terminate the requirements of 
AD 2014-16-02 after modification or repair. The NPRM proposed to 
continue to require the actions specified in AD 2014-16-02 until 
modification or repair of the thrust reversers. The SNPRM proposed to 
reduce the compliance time for modification of the thrust reversers, 
and add new modification procedures. We are issuing this AD to detect 
and correct cracks of the translating sleeve at the thrust reverser 
actuator attachment points, which could result in deployment or 
dislodgement of an engine thrust reverser in flight and subsequent 
reduced control of the airplane.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2014-19R1, dated March 11, 2016 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Bombardier, Inc. Model CL-600-
1A11 (CL-600) airplanes. The MCAI states:

    There have been two reported incidents of partial deployment of 
an engine thrust reverser in-flight, caused by a failure of the 
translating sleeve at the thrust reverser actuator attachment 
points. Inspection of the same area on some other thrust reversers 
revealed cracks emanating from the holes under the nut plates.
    In both incidents, the affected aeroplane landed safely without 
any noticeable controllability issues, however structural failure of 
thrust reverser actuator attachment points resulting in thrust 
reverser deployment or dislodgment in flight is a safety hazard 
warranting an immediate mitigating action.
    To help in mitigating any immediate safety hazard, Bombardier 
Inc. has revised the Aircraft Flight Manual (AFM) through Temporary 
Revisions (TR) 600/29, 600/30, 600-1/24 and 600-1/26, to prohibit 
the thrust reverser operation on affected aeroplanes. Additionally, 
as an interim corrective action, Bombardier Inc. has issued alert 
service bulletin (ASB) A600-0769 requiring an inspection and/or a 
mechanical lock out of the thrust reverser to prevent it from moving 
out of forward thrust mode.
    Original [TCCA] Emergency AD CF-2014-19 [which corresponds to 
FAA AD 2014-16-02] was issued 20 June 2014 to mandate the 
incorporation of above mentioned revised AFM procedures and 
compliance with ASB A600-0769. This [TCCA] AD is now being revised 
to include the terminating action [modification of the thrust 
reversers] in accordance with Part C of the ASB A600-0769 Rev 02 
dated 22 February 2016.

    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-2015-
7529.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the SNPRM or on the determination 
of the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed, except for 
minor editorial

[[Page 29377]]

changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
SNPRM for correcting the unsafe condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the SNPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed Bombardier Alert Service Bulletin A600-0769, Revision 
02, dated February 22, 2016. The service information describes 
procedures for a new permanent modification of the thrust reversers on 
both engines, which includes inspections for cracks and elongated 
holes.
    We also reviewed the following TRs, which introduce procedures to 
prohibit thrust reverser operation. These documents are distinct since 
they apply to different airplane configurations.
    <bullet> Canadair TR 600/29-2, dated January 18, 2016, to the 
Canadair CL-600-1A11 AFM.
    <bullet> Canadair TR 600-1/24-2, dated January 18, 2016, to the 
Canadair CL-600-1A11 AFM (Winglets).
    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

    We estimate that this AD affects 18 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
AFM revision; inspection [retained      29 work-hours x $85 per              N/A          $2,465         $44,370
 actions from AD 2014[dash]16[dash]02].  hour = $2,465.
New modification......................  100 work-hours x $85 per            $509           9,009         162,162
                                         hour = $8,500.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary modifications 
that will be required based on the results of the inspection. We have 
no way of determining the number of aircraft that might need this 
modification:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Modification...............................  36 work-hours x $85 per hour =                 $509          $3,569
                                              $3,060.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions for the inspections that 
are part of the new modification 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.
    We are 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

    We 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. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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) 
2014-16-02, Amendment 39-17926 (79 FR 46968, August 12, 2014), and 
adding the following new AD:

2017-13-09 Bombardier, Inc.: Amendment 39-18939; Docket No. FAA-
2015-7529; Directorate Identifier 2014-NM-207-AD.

(a) Effective Date

    This AD is effective August 3, 2017.

(b) Affected ADs

    This AD replaces AD 2014-16-02, Amendment 39-17926 (79 FR 46968, 
August 12, 2014) (``AD 2014-16-02'').

(c) Applicability

    This AD applies to Bombardier, Inc., Model CL-600-1A11 (CL-600) 
airplanes, certificated in any category, serial numbers 1004 through 
1085 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 78, Engine 
Exhaust.

[[Page 29378]]

(e) Reason

    This AD was prompted by reports of partial deployment of an 
engine thrust reverser in flight caused by a failure of the 
translating sleeve at the thrust reverser attachment points. We are 
issuing this AD to detect and correct cracks of the translating 
sleeve at the thrust reverser actuator attachment points, which 
could result in deployment or dislodgement of an engine thrust 
reverser in flight and subsequent reduced control of the airplane.

(f) Compliance

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

(g) Retained Airplane Flight Manual (AFM) Revision With Revised Service 
Information

    This paragraph restates the requirements of paragraph (g) of AD 
2014-16-02, with revised service information. Within 1 calendar day 
after August 12, 2014 (the effective date of AD 2014-16-02): Revise 
the applicable sections of the AFM to include the information 
specified in the temporary revisions (TRs) identified in paragraphs 
(g)(1) and (g)(2) of this AD, as applicable. These TRs introduce 
procedures to prohibit thrust reverser operation. Operate the 
airplane according to the limitations and procedures in the TRs 
identified in paragraphs (g)(1) and (g)(2) of this AD, as 
applicable. The revision required by paragraph (g) of this AD may be 
done by inserting copies of the applicable TRs identified in 
paragraphs (g)(1) and (g)(2) of this AD into the AFM. When these TRs 
have been included in the general revisions of the AFM, the general 
revisions may be inserted in the AFM, provided the relevant 
information in the general revision is identical to that in the 
applicable TRs, and the TRs may be removed.
    (1) Canadair TR 600/29, dated June 20, 2014, to the Canadair CL-
600-1A11 AFM; or Canadair TR 600/29-2, dated January 18, 2016, to 
the Canadair CL-600-1A11 AFM. As of the effective date of this AD, 
use only Canadair TR 600/29-2, dated January 18, 2016, to the 
Canadair CL-600-1A11 AFM.
    (2) Canadair TR 600-1/24, dated June 20, 2014, to the Canadair 
CL-600-1A11 AFM (Winglets), including Erratum, Publication No. PSP 
600-1AFM (US), TR No. 600-1/24, June 20, 2014; or Canadair TR 600-1/
24-2, dated January 18, 2016, to the Canadair CL-600-1A11 AFM 
(Winglets). As of the effective date of this AD, use only Canadair 
TR 600-1/24-2, dated January 18, 2016, to the Canadair CL-600-1A11 
AFM (Winglets).

(h) Retained Repetitive Inspections and Modifications, With Revised 
Service Information

    This paragraph restates the requirements of paragraph (h) of AD 
2014-16-02, with revised service information. Within 25 flight 
cycles or 90 days, whichever occurs first, after August 12, 2014 
(the effective date of AD 2014-16-02), do detailed inspections 
(including a borescope inspection) of both engine thrust reversers 
for cracks, in accordance with the Accomplishment Instructions of 
Bombardier Alert Service Bulletin A600-0769, Revision 01, dated June 
26, 2014; or Bombardier Alert Service Bulletin A600-0769, Revision 
02, dated February 22, 2016. As of the effective date of this AD, 
use only Bombardier Alert Service Bulletin A600-0769, Revision 02, 
dated February 22, 2016.
    (1) If no cracking is found during any inspection required by 
paragraph (h) of this AD, repeat the inspection required by 
paragraph (h) of this AD thereafter at intervals not to exceed 100 
flight cycles until the repair or modification specified in 
paragraph (i) or (k) of this AD is done.
    (2) If any cracking is found during any inspection required by 
paragraph (h) of this AD, before further flight, modify the thrust 
reversers on both engines, in accordance with Part B of the 
Accomplishment Instructions of Bombardier Alert Service Bulletin 
A600-0769, Revision 01, dated June 26, 2014; or Bombardier Alert 
Service Bulletin A600-0769, Revision 02, dated February 22, 2016. As 
of the effective date of this AD, use only Bombardier Alert Service 
Bulletin A600-0769, Revision 02, dated February 22, 2016.

(i) Retained Optional Terminating Modification, With Revised Service 
Information

    This paragraph restates the optional terminating action 
specified in paragraph (i) of AD 2014-16-02, with revised service 
information. Modifying the thrust reversers on both engines, in 
accordance with Part B of the Accomplishment Instructions of 
Bombardier Alert Service Bulletin A600-0769, Revision 01, dated June 
26, 2014; or Bombardier Alert Service Bulletin A600-0769, Revision 
02, dated February 22, 2016; terminates the inspections required by 
paragraph (h) of this AD. As of the effective date of this AD, use 
only Bombardier Alert Service Bulletin A600-0769, Revision 02, dated 
February 22, 2016.

(j) Retained Credit for Previous Actions, With No Changes

    This paragraph restates the credit provided in paragraph (j) of 
AD 2014-16-02, with no changes. This paragraph provides credit for 
actions required by paragraphs (h) and (i) of this AD, if those 
actions were performed before August 12, 2014 (the effective date of 
AD 2014-16-02), using Bombardier Alert Service Bulletin A600-0769, 
dated June 19, 2014.

(k) New Requirement of This AD: Permanent Modification and Inspections

    Within 24 months after the accomplishing the modification 
specified in paragraph (h)(2) of this AD, or within 48 months after 
accomplishing the initial inspection required by paragraph (h) of 
this AD, whichever occurs later: Modify the thrust reversers on both 
engines, including doing the inspections specified in paragraphs 
(k)(1) through (k)(6) of this AD, in accordance with Part C of the 
Accomplishment Instructions of Bombardier Alert Service Bulletin 
A600-0769, Revision 02, dated February 22, 2016, except as required 
by paragraphs (m)(1) and (m)(2) of this AD. Modification of all 
thrust reversers terminates the requirements of paragraphs (g), (h), 
and (i) of this AD.
    (1) Do general visual inspections of the flipper doors for 
cracks.
    (2) Do a general visual inspection of the thrust reverser skin, 
frames, joints, splices, and fasteners for cracks.
    (3) Do a general visual inspection of the thrust reverser for 
cracks.
    (4) Do liquid penetrant or eddy current inspections, as 
applicable, of the frames for cracks.
    (5) Do a detailed visual inspection of the frames for cracks and 
elongated holes, and do a liquid penetrant inspection of the frames 
for cracks.
    (6) Do a liquid penetrant or an eddy current inspection of the 
translating sleeve skin for cracks.

(l) New Requirement of This AD: Repair

    If, during any inspection required by paragraph (k) of this AD, 
any cracking or elongated hole is found, before further flight, 
repair using a method approved by the Manager, New York Aircraft 
Certification Office (ACO), ANE-170, FAA; or Transport Canada Civil 
Aviation (TCCA); or Bombardier, Inc.'s TCCA Design Approval 
Organization (DAO).

(m) New Exceptions to Service Information

    (1) If it is not possible to follow all instructions specified 
in Bombardier Alert Service Bulletin A600-0769, Revision 02, dated 
February 22, 2016, during accomplishment of the actions required by 
paragraph (k) of this AD, before further flight, repair using a 
method approved by the Manager, New York ACO, ANE-170, FAA; or TCCA; 
or Bombardier, Inc.'s TCCA DAO.
    (2) Where Bombardier Alert Service Bulletin A600-0769, Revision 
02, dated February 22, 2016, specifies to contact Bombardier if shim 
thickness is over the applicable thicknesses identified in 
Bombardier Alert Service Bulletin A600-0769, Revision 02, dated 
February 22, 2016, before further flight, repair using a method 
approved by the Manager, New York ACO, ANE-170, FAA; or TCCA; or 
Bombardier, Inc.'s TCCA DAO.

(n) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York ACO, ANE-170, 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 ACO, send it 
to ATTN: Program Manager, Continuing Operational Safety, FAA, New 
York ACO, 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 local flight standards 
district office/certificate holding district office.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, 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, ANE-170,

[[Page 29379]]

FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO. If approved by the 
DAO, the approval must include the DAO-authorized signature.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian AD CF-2014-19R1, dated March 11, 2016, 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-2015-7529.
    (2) For more information about this AD, contact Cesar Gomez, 
Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE-171, 
FAA, New York Aircraft Certification Office (ACO), 1600 Stewart 
Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7318; fax 
516-794-5531.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (p)(5) and (p)(6) of this AD.

(p) 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 
August 3, 2017.
    (i) Bombardier Alert Service Bulletin A600-0769, Revision 02, 
dated February 22, 2016.
    (ii) Canadair Temporary Revision 600/29-2, dated January 18, 
2016, to the Canadair CL-600-1A11 Airplane Flight Manual.
    (iii) Canadair Temporary Revision 600-1/24-2, dated January 18, 
2016, to the Canadair CL-600-1A11 Airplane Flight Manual (Winglets).
    (4) The following service information was approved for IBR on 
August 12, 2014 (79 FR 46968, August 12, 2014).
    (i) Bombardier Alert Service Bulletin A600-0769, Revision 01, 
dated June 26, 2014.
    (ii) Canadair TR 600/29, dated June 20, 2014, to the Canadair 
CL-600-1A11 Airplane Flight Manual.
    (iii) Canadair TR 600-1/24, dated June 20, 2014, to the Canadair 
CL-600-1A11 AFM (Winglets), including Erratum, Publication No. PSP 
600-1AFM (US), TR No. 600-1/24, June 20, 2014.
    (5) For service information identified in this AD, contact 
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, 
Qu[eacute]bec H4S 1Y9, Canada; Widebody Customer Response Center 
North America; toll-free telephone number 1-866-538-1247 or direct-
dial telephone number 1-514-855-2999; fax 514-855-7401; email 
<a href="/cdn-cgi/l/email-protection#dfbebcf1a6aab39fbebaadb0f1bdb0b2bdbeadbbb6baadf1bcb0b2"><span class="__cf_email__" data-cfemail="9dfcfeb3e4e8f1ddfcf8eff2b3fff2f0fffceff9f4f8efb3fef2f0">[email&#160;protected]</span></a>; Internet <a href="http://www.bombardier.com">http://www.bombardier.com</a>.
    (6) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (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, call 202-741-6030, 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 Renton, Washington, on June 16, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-13411 Filed 6-28-17; 8:45 am]
 BILLING CODE 4910-13-P