Document ID: FAA-2014-0584-0005
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2015-05-29T04:00Z

[Federal Register Volume 80, Number 103 (Friday, May 29, 2015)]
[Rules and Regulations]
[Pages 30608-30612]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-11393]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0584; Directorate Identifier 2014-NM-092-AD; 
Amendment 39-18158; AD 2015-10-03]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2014-09-05, 
for certain Airbus Model A330-200 and -300 series airplanes, and Model 
A340-200 and -300 series airplanes. AD 2014-09-05 required repetitive 
inspections of certain sidestay upper cardan pins of the main landing 
gear (MLG) and associated nuts and retainer assemblies, and pin 
replacement if necessary. This AD was prompted by a determination that 
a previously optional measurement is necessary to address the 
identified unsafe condition. This new AD continues to require a 
detailed inspection for visible chrome of each affected MLG sidestay 
upper cardan pin, associated nuts, and retainer assembly, and pin 
replacement if needed, and adds new requirements for measuring cardan 
pin clearance dimensions (gap check), doing corrective actions, and 
reporting all findings. We are issuing this AD to detect and correct 
migration of the sidestay upper cardan pin, which could result in 
disconnection of the sidestay upper arm from the airplane structure, 
and could result in a landing

[[Page 30609]]

gear collapse and consequent damage to the airplane and injury to 
occupants.

DATES: This AD becomes effective July 6, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 14, 2014 
(79 FR 23909, April 29, 2014).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0584; or in person at the 
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.
    For service information identified in this AD, contact Airbus SAS--
Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; 
email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. 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 http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0584.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2014-09-05, Amendment 39-17840 (79 FR 23909, 
April 29, 2014). AD 2014-09-05 applied to certain Airbus Model A330-200 
and -300 series airplanes, and Model A340-200 and -300 series 
airplanes. The NPRM published in the Federal Register on August 26, 
2014 (79 FR 50863).
    The European Aviation Safety Agency, which is the Technical Agent 
for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0066, corrected March 20, 2014 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on certain Airbus Model 
A330-200 and -300 series airplanes, and Model A340-200 and -300 series 
airplanes. The MCAI states:

    An A330 aeroplane equipped with Basic (main landing gear) MLG 
was rolling out after landing when it experienced a nose wheel 
steering fault (unrelated to the safety subject addressed by this 
[EASA] AD), which resulted in the crew stopping the aeroplane on the 
taxiway after vacating the runway.
    The subsequent investigation revealed that the right-hand MLG 
sidestay upper cardan pin had migrated out of position. The sidestay 
upper cardan nut and retainer were found in the landing gear bay 
detached from the upper cardan pin. The nut and the retainer were 
still bolted together.
    This condition, if not detected and corrected, could lead to a 
complete migration of the sidestay upper cardan pin and a 
disconnection of the sidestay upper arm from the aeroplane 
structure, possibly resulting in MLG collapse with consequent damage 
to the aeroplane and injury to occupants.
    To address this potential condition, Airbus published Alert 
Operators Transmission (AOT) A32L003-14, providing inspection 
instructions.
    For the reasons described above, this [EASA] AD requires 
accomplishment of repetitive [detailed inspections for visible 
chrome] of the MLG upper cardan pin, nut and retainer [and pin 
replacement if necessary]. This [EASA] AD also requires 
accomplishment of a gap check between wing rear spar fitting lugs 
and the bush flanges [and corrective actions if necessary. 
Corrective actions include repair or replacement of the cardan pin 
assembly].

You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0584-0003.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (79 
FR 50863, August 26, 2014) and the FAA's response to each comment.

Request To Match the Applicability of Terminating Action to Inspections

    U.S. Airways requested that we revise the affected airplanes of 
paragraph (h) of the NPRM (79 FR 50863, August 26, 2014) to match those 
of paragraph (g) of the NPRM. U.S. Airways stated that paragraph (g) of 
the NPRM limits the repetitive inspections to MLG that have exceeded 8 
years since first overhaul but not yet had a second overhaul; whereas 
paragraph (h) of the NPRM provides a new terminating action to the 
repetitive inspections, but does not limit the applicability to MLG 
that have exceeded 8 years since first overhaul but not yet had a 
second overhaul.
    We agree to revise the affected airplanes of paragraph (h) of this 
AD because the terminating action provisions of paragraph (h) of the 
NPRM (79 FR 50863, August 26, 2014) was intended to apply to the same 
subset of affected airplanes identified in paragraph (g)(1) of the 
NPRM. We have changed the language in paragraph (h) of this AD by 
limiting the affected airplanes to those identified in paragraph (g)(1) 
of this AD.

Request To Change Compliance Time of Sending Results of Gap Check

    U.S. Airways requested that we revise the compliance time for 
sending the results of the inspection and gap check to Airbus from 
``before further flight'' to ``within 30 days.'' U.S. Airways stated 
that paragraph (h)(2)(i) of the NPRM (79 FR 50863, August 26, 2014) 
states to send inspection findings to Airbus ``before further flight,'' 
if the gap check result measures between 0.6 mm and 1.5 mm, and 
paragraph (h)(2)(ii) states to repair within 30 days. U.S. Airways 
stated that mechanics who inspect the cardan pin typically do not send 
data directly to Airbus and that since the repair is not required for 
30 days after the inspection, communicating the inspection findings 
should not restrict aircraft flight.
    We agree to revise the compliance time because the proposed 
compliance time for sending the results of the inspection and gap check 
does not affect the compliance time for accomplishment of the repair. 
We have changed the compliance time in paragraph (h)(2)(i) of this AD 
from before further flight, to 30 days. This difference has been 
coordinated with EASA.

Request To Allow Replacement of Cardan Pin Assembly as Terminating 
Action

    U.S. Airways requested that we allow the replacement of the cardan 
pin assembly to be considered as a terminating action. Paragraph (h)(1) 
of the NPRM (79 FR 50863, August 26, 2014) would mandate the 
replacement of the cardan pin if the gap is found to be greater than 
1.5mm. However paragraph (h)(2) of the NPRM would require an approved 
repair for smaller gaps. US Airways suggested that the AD also allow 
the replacement of the cardan pin assembly before further flight as an 
alternative to the actions specified in paragraphs (h)(2)(i) and 
(h)(2)(ii) of the NPRM.
    We agree with the request to allow replacement of the cardan pin 
assembly as an alternative to small repairs because replacing the 
cardan pin assembly is terminating action regardless of the size of the 
gap. We have revised paragraph (h) of this AD to

[[Page 30610]]

provide for replacement of the cardan pin assembly as an option to 
doing a repair.

Related Service Information Under 1 CFR Part 51

    The manufacturer has issued Airbus AOT A32L003-14, dated March 10, 
2014. The service information describes procedures for inspecting 
sidestay upper cardan pins of the MLG and associated nuts and retainer 
assemblies. 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 of this 
AD.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 50863, August 26, 2014) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 50863, August 26, 2014).

Costs of Compliance

    We estimate that this AD affects 83 airplanes of U.S. registry.
    The actions required by AD 2014-09-05, Amendment 39-17840 (79 FR 
23909, April 29, 2014), and retained in this AD take about 1 work-hour 
per product, at an average labor rate of $85 per work-hour. Required 
parts cost $0 per product. Based on these figures, the estimated cost 
of the actions that were required by AD 2014-09-05 is $85 per product.
    We also estimate that it will take about 1 work-hour per product to 
comply with the new basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $7,055, or $85 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 4 work-hours and require parts costing $7,530, for a cost of 
$7,870 per product. We have no way of determining the number of 
aircraft that might need these actions.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-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.
    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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0584; 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 street address for the Docket Operations office (telephone 800-647-
5527) is in the ADDRESSES section.

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) 
2014-09-05, Amendment 39-17840 (79 FR 23909, April 29, 2014), and 
adding the following new AD:

2015-10-03 Airbus: Amendment 39-18158. Docket No. FAA-2014-0584; 
Directorate Identifier 2014-NM-092-AD.

(a) Effective Date

    This AD becomes effective July 6, 2015.

(b) Affected ADs

    This AD replaces AD 2014-09-05, Amendment 39-17840 (79 FR 23909, 
April 29, 2014).

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category.
    (1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes, all 
manufacturer serial numbers (MSNs), equipped with basic (201252 
series) main landing gear (MLG), or growth (201490 series) MLG.
    (2) Airbus Model A340-211, -212, -213, -311, -312, and -313 
airplanes, all MSNs, equipped with basic (201252 series) MLG or 
growth (201490 series) MLG.

[[Page 30611]]

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
Gear.

(e) Reason

    This AD was prompted by a report of a sidestay upper cardan pin 
of the MLG migrating out of position. We are issuing this AD to 
detect and correct migration of the sidestay upper cardan pin, which 
could result in disconnection of the sidestay upper arm from the 
airplane structure, and could result in a landing gear collapse and 
consequent damage to the airplane and injury to occupants.

(f) Compliance

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

(g) Retained Repetitive Detailed Inspections With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2014-09-05, Amendment 39-17840 (79 FR 23909, April 29, 2014), with 
no changes.
    (1) For airplanes identified in paragraphs (g)(1)(i) and 
(g)(1)(ii) of this AD on which the affected MLG has exceeded 8 years 
since first overhaul, as of May 14, 2014 (the effective date of AD 
2014-09-05, Amendment 39-17840 (79 FR 23909, April 29, 2014), except 
those MLG that have had a second overhaul: Within 30 days after May 
14, 2014, accomplish a detailed inspection for visible chrome of 
each affected MLG sidestay upper cardan pin, and associated nut and 
retainer assembly, in accordance with the instructions of Airbus 
Alert Operators Transmission (AOT) A32L003-14, dated March 10, 2014, 
including Appendices 1, 2, and 3 (the issue date is not specified on 
the appendices).
    (i) Airplanes equipped with any MLG sidestay upper cardan pin 
subassembly part number (P/N) 201267202 (on 201252 series MLG).
    (ii) Airplanes equipped with any MLG sidestay upper cardan pin 
subassembly P/N 201483202 (on 201490 series MLG).
    (2) If, during any inspection required by paragraph (g)(1) of 
this AD, no pin chrome is visible inboard of the wing rear spar 
fitting lug, repeat the detailed inspection for visible chrome 
specified in paragraph (g)(1) of this AD thereafter at intervals not 
to exceed 10 days.
    (3) If, during any inspection required by paragraphs (g)(1) or 
(g)(2) of this AD, a pin chrome is visible inboard of the wing rear 
spar fitting lug, before further flight, replace the affected cardan 
pin assembly, in accordance with the instructions of Airbus AOT 
A32L003-14, dated March 10, 2014, including Appendices 1, 2, and 3 
(the issue date is not specified on the appendices). Replacement of 
the affected cardan pin assembly terminates the repetitive 
inspections required by paragraph (g)(2) of this AD.
    Note 1 to paragraph (g) of this AD: MLG sidestay upper cardan 
pin subassembly P/N 201267202 (found in Airbus Illustrated Parts 
Catalogue (IPC) as item 32-11-18-01) includes the cardan pin P/N 
201267600. MLG sidestay upper cardan pin subassembly P/N 201483202 
(found in Airbus IPC as item 32-11-18-01) includes the cardan pin P/
N 201483600.

(h) New Terminating Action--Gap Check

    For airplanes identified in paragraphs (g)(1)(i) and (g)(1)(ii) 
of this AD on which the affected MLG has exceeded 8 years since 
first overhaul, as of May 14, 2014 (the effective date of AD 2014-
09-05, Amendment 39-17840 (79 FR 23909, April 29, 2014), except 
those MLG that have had a second overhaul: Within 4 months after the 
effective date of this AD: Measure the cardan pin clearance 
dimensions (gap check) and do the applicable corrective action 
specified in paragraph (h)(1) or (h)(2) of this AD. Measuring the 
gap check and doing the applicable corrective action specified in 
paragraph (h)(1) or (h)(2) of this AD, as applicable, terminates the 
inspections required by paragraphs (g)(1) and (g)(2) of this AD for 
that sidestay upper cardan pin, nut, and retainer only. The 
measurement must be done in accordance with Airbus AOT A32L003-14, 
dated March 10, 2014, including Appendices 1, 2, and 3 (the issue 
date is not specified on the appendices).
    (1) If the total clearance dimension (gap check result) is equal 
to or greater than 1.5 mm, before further flight, replace the cardan 
pin assembly, in accordance with Airbus AOT A32L003-14, dated March 
10, 2014, including Appendices 1, 2, and 3 (the issue date is not 
specified on the appendices).
    (2) If the total clearance dimension (gap check) is less than 
1.5 mm but greater than 0.6 mm, do the actions specified in 
paragraphs (h)(2)(i) or (h)(2)(ii) of this AD.
    (i) Do the actions specified in paragraphs (h)(2)(i)(A) and 
(h)(2)(i)(B) of this AD.
    (A) Within 30 days after accomplishing the gap check, send the 
information (Appendix 2 proforma, photographs, and the movement 
traceability sheet) specified in paragraph 4.2.3, ``Findings,'' of 
Airbus AOT A32L003-14, dated March 10, 2014, including Appendices 1, 
2, and 3 (the issue date is not specified on the appendices), to 
Airbus at the address specified in Appendix 2 (the issue date is not 
specified on this appendix) of Airbus AOT A32L003-14, dated March 
10, 2014.
    (B) Within 30 days after accomplishing the gap check, repair 
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or the European Aviation 
Safety Agency (EASA); or Airbus's EASA Design Organization Approval 
(DOA). If approved by the DOA, the approval must include the DOA-
authorized signature.
    (ii) Within 30 days after accomplishing the gap check, replace 
the cardan pin assembly, in accordance with Airbus AOT A32L003-14, 
dated March 10, 2014, including Appendices 1, 2, and 3 (the issue 
date is not specified on the appendices).

(i) New Reporting of Inspection Results

    For airplanes on which a gap check specified in paragraph (h) of 
this AD has been done: Except as required by paragraph (h)(2)(i) of 
this AD, at the applicable time specified in paragraphs (i)(1) and 
(i)(2) of this AD, report all findings (including no findings) to 
Airbus, in accordance with Airbus AOT A32L003-14, dated March 10, 
2014, including Appendices 1, 2, and 3, (the issue date is not 
specified on the appendices).
    (1) If the gap check was done on or after the effective date of 
this AD: Submit the report within 30 days after the gap check.
    (2) If the gap check was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

(j) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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. The 
AMOC approval letter must specifically reference this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; 
or Airbus's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(k) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA

[[Page 30612]]

Airworthiness Directive 2014-0066 (Corrected March 20, 2014), for 
related information. You may examine the MCAI in the AD docket on 
the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-
2014-0584.

(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.
    (3) The following service information was approved for IBR on 
May 14, 2014, (79 FR 23909, April 29, 2014).
    (i) Airbus Alert Operators Transmission A32L003-14, dated March 
10, 2014, including Appendices 1, 2, and 3 (the issue date is not 
specified on the appendices).
    (ii) Reserved.
    (4) For service information identified in this AD, contact 
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; 
Internet http://www.airbus.com.
    (5) 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.
    (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, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on April 30, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-11393 Filed 5-28-15; 8:45 am]
BILLING CODE 4910-13-P