
[Federal Register Volume 81, Number 108 (Monday, June 6, 2016)]
[Proposed Rules]
[Pages 36211-36214]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-13049]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3631; Directorate Identifier 2015-NM-060-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

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SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) for certain Airbus Model A330-200 and -300 series airplanes; Model 
A330-200 Freighter series airplanes; and Model A340-200, -300, -500, 
and -600 series airplanes. The NPRM proposed to require modifying the 
cockpit door frame structure, installing bonding-leads to the upper 
cockpit door frame, and modifying the upper cockpit door plate cover. 
The NPRM was prompted by reports of chafed wiring at the upper left 
corner of the cockpit door. The affected wire bundle was not grounded 
on the cockpit door frame. This action revises the NPRM by also 
requiring, for certain airplanes, installing a noise-reduced cockpit 
door locking system (CDLS). We are proposing this supplemental NPRM 
(SNPRM) to prevent electrical shock injury to persons contacting the 
cockpit door. Since these actions impose an additional burden over 
those proposed in the NPRM, we are reopening the comment period to 
allow the public the chance to comment on these proposed changes.

DATES: We must receive comments on this SNPRM by July 21, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this SNPRM, 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3631; 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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (telephone: 800-647-5527) is in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

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: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-3631; 
Directorate Identifier 2015-NM-060-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Airbus Model A330-
200 and -300 series airplanes; Model A330-200 Freighter series 
airplanes; and Model A340-200, -300, -500, and -600 series airplanes. 
The NPRM published in the Federal Register on September 18, 2015 (80 FR 
56405) (``the NPRM''). The NPRM was prompted by reports of chafed 
wiring at the upper left corner of the cockpit door. The affected wire 
bundle was not grounded on the cockpit door frame. The NPRM proposed to 
require modifying the cockpit door frame structure, installing bonding-
leads to the upper cockpit door frame, and modifying the upper cockpit 
door plate cover.

Actions Since Previous NPRM Was Issued

    Since we issued the NPRM, new service information has been issued 
that specifies, for certain airplanes, prior or concurrent actions of 
installing a noise-reduced CDLS. We have determined this installation 
is necessary to address the identified unsafe condition.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0037, dated March 2, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A330-200 and -300 series airplanes; Model A330-200 Freighter series 
airplanes; and Model A340-200, -300, -500, and -600 series airplanes. 
The MCAI states:

    An operator has reported chafed wiring at the upper left corner 
of the cockpit door. The investigation concluded that the affected 
wire bundle, which supplies a voltage of 115V [volt] AC [alternating 
current], was not grounded on the cockpit door frame as part of the 
design of A330 and A340 aeroplanes.
    This condition, if not corrected, could result in injury 
[electrical shock], in case any person gets in contact with the door 
frame.
    Prompted by these findings, Airbus issued SB [service bulletin] 
A330-25-3534, SB A340-25-4349 and SB A340-25-5212 to

[[Page 36212]]

provide instructions to modify the electrical bonding of the cockpit 
door.
    For the reasons described above, this [EASA] AD requires 
modification of the cockpit door frame structure, installation of 
bonding-leads to the upper cockpit door frame and modification of 
the upper cockpit door plate cover.

Required actions for certain airplanes include installation of a noise-
reduced CDLS.
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3631.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.
     Service Bulletin A330-25-3213, Revision 01, dated April 
25, 2005. This service information describes procedures for 
modification of the upper cockpit door plate cover.
     Service Bulletin A330-25-3254, Revision 02, dated December 
13, 2004. This service information describes procedures for installing 
a noise-reduced CDLS.
     Service Bulletin A330-25-3534, Revision 02, dated May 18, 
2015. This service information describes procedures for modifying the 
cockpit door frame structure and installing bonding-leads to the upper 
cockpit door frame.
     Service Bulletin A340-25-4217, Revision 01, dated April 
25, 2005. This service information describes procedures for 
modification of the upper cockpit door plate cover.
     Service Bulletin A340-25-4349, Revision 02, dated 
September 4, 2015. This service information describes procedures for 
modifying the cockpit door frame structure and installing bonding-leads 
to the upper cockpit door frame.
     Service Bulletin A340-25-5046, Revision 02, dated February 
5, 2007. This service information describes procedures for modification 
of the upper cockpit door plate cover.
     Service Bulletin A340-25-5212, Revision 01, dated October 
27, 2014. This service information describes procedures for modifying 
the cockpit door frame structure and installing bonding-leads to the 
upper cockpit door frame.
    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.

Comments

    We gave the public the opportunity to participate in developing 
this proposed AD. We considered the comments received.

Requests To Refer to Revised Service Information

    An anonymous commenter and Delta Air Lines (DAL) requested that we 
reference revised service information. DAL requested that we refer to 
Airbus Service Bulletin A330-25-3534, Revision 02, dated May 18, 2015, 
for accomplishing the actions in paragraphs (g) and (h) of the proposed 
AD (in the NPRM). The anonymous commenter requested that we refer to 
Airbus Service Bulletin A340-25-4349, Revision 02, dated September 4, 
2015, in paragraphs (g)(2) and (h)(2) of the proposed AD (in the NPRM).
    We partially agree with the commenters' requests. We agree to refer 
to Airbus Service Bulletin A330-25-3534, Revision 02, dated May 18, 
2015; and Airbus Service Bulletin A340-25-4349, Revision 02, dated 
September 4, 2015; in paragraph (g) of this proposed AD. This service 
information contains updated accomplishment instructions. Airbus 
Service Bulletin A330-25-3534, Revision 02, dated May 18, 2015, also 
revises the specified concurrent requirements.
    However, in paragraph (h) of this proposed AD, we have determined 
that Airbus Service Bulletin A330-25-3534, Revision 02, dated May 18, 
2015; and Airbus Service Bulletin A340-25-4349, Revision 02, dated 
September 4, 2015; are not appropriate sources of service information 
for accomplishing the proposed concurrent actions. Instead, we refer to 
Airbus Service Bulletin A330-25-3213, Revision 01, dated April 25, 
2005; Airbus Service Bulletin A340-25-4217, Revision 01, dated April 
25, 2005; and Airbus Service Bulletin A340-25-5046, Revision 02, dated 
February 5, 2007; for accomplishing the concurrent action of modifying 
the upper cockpit door plate cover. We refer to Airbus Service Bulletin 
A330-25-3534, Revision 02, dated May 18, 2015; and Airbus Service 
Bulletin A340-25-4349, Revision 02, dated September 4, 2015; in 
paragraphs (h)(1) and (h)(2) of this AD, respectively, in order to 
identify the affected airplanes.
    We have added a new paragraph (j) to this proposed AD to provide 
credit for actions accomplished using Airbus Service Bulletin A330-25-
3534, Revision 01, dated October 23, 2014; Airbus Service Bulletin 
A330-25-3213, dated October 12, 2004; and Airbus Service Bulletin A340-
25-4217, dated October 12, 2004. We have reidentified the subsequent 
paragraphs accordingly.
    DAL also requested that we approve using later issued revisions of 
Airbus Service Bulletin A330-25-3534.
    We disagree with approving unspecified later revisions of the 
service information. When referring to a specific service bulletin in 
an AD, using the phrase, ``or later FAA-approved revisions,'' violates 
Office of the Federal Register regulations for approving materials that 
are incorporated by reference. Once we issue a final rule, affected 
operators may request approval to use a later revision of the 
referenced service bulletin as an alternative method of compliance 
(AMOC), under the provisions of paragraph (k)(1) of this proposed AD.

Requests To Extend Compliance Time

    DAL requested that we extend the compliance time from 24 months to 
30 months. DAL stated that a 24-month compliance time does not provide 
the necessary time to procure parts and develop internal paperwork to 
accomplish the modifications. DAL explained that mandating a 24-month 
compliance time will result in several airplanes being missed during 
scheduled maintenance, which will result in requiring costly special 
visits that adversely impact passenger operations. DAL also stated it 
had not experienced problems with the cockpit door bonding during a 
service history of over 12 years and noted there is higher awareness to 
electrical wiring interconnect system (EWIS) issues, making wire 
chafing problems less likely. DAL concluded that a moderate extension 
to the compliance time should provide a sufficient level of safety 
without burdening the airlines unnecessarily.
    We disagree with DAL's request. The compliance time has been 
determined by EASA and Airbus through the specific analysis to ensure 
continued operational safety of the affected airplanes. If an operator 
wishes to extend the compliance time, this can be done through a 
specific request for approval of an AMOC under the provisions of 
paragraph (k)(1) of this proposed AD. The operator must justify in the 
request that an extension of the compliance time will provide an 
adequate level of safety (such as by accomplishment of specific 
inspections or tasks).
    Airbus has specified a standard lead time of 90 calendar days from 
the date of a purchase order for component kits, which ensures 
sufficient time for planning the appropriate operator's action to 
modify the airplane and

[[Page 36213]]

comply with this proposed AD. We have not changed this proposed AD in 
this regard.

Requests To Allow Alternative Consumable Materials

    DAL requested that we allow the use of industry standard consumable 
materials already stocked by the airlines, instead of burdening the 
airlines with procuring the specific consumables specified in the 
service information. DAL stated that there are many industry standard 
materials that fulfill the roles of each of the specific materials 
called out in the service bulletins that are used daily by every 
airline. DAL also stated that the use of these industry standard 
consumable materials will in no way reduce the level of safety of the 
modifications.
    We disagree with DAL's request. DAL did not provide details on the 
specific consumable materials it proposes to use for the actions 
required by this proposed AD and did not provide any technical 
justification that the use of other consumable materials would provide 
an equivalent level of safety. In addition, for service information 
that contains ``Required for Compliance'' (RC) sections in the 
Accomplishment Instructions, the consumable materials in the RC 
sections must be used to comply with the AD requirements. Completion of 
all steps in accordance with the RC sections ensures that the actions 
required by this proposed AD address the identified unsafe condition. 
Operators may request approval for the use of other consumable 
materials through the AMOC process, under the provisions of paragraph 
(k)(1) of this proposed AD. We have not changed this proposed AD in 
this regard.

FAA's Determination and Requirements of This SNPRM

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type designs.
    Certain changes described above expand the scope of the NPRM. As a 
result, we have determined that it is necessary to reopen the comment 
period to provide additional opportunity for the public to comment on 
this SNPRM.

Costs of Compliance

    We estimate that this SNPRM affects 70 airplanes of U.S. registry.
    We estimate that it would take about 53 work-hours per product to 
comply with the new basic requirements of this SNPRM. The average labor 
rate is $85 per work-hour. Required parts would cost about $2,430 per 
product. Based on these figures, we estimate the cost of this SNPRM on 
U.S. operators to be $485,450, or $6,935 per product.
    According to the manufacturer, some of the costs of this SNPRM may 
be covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

    Airbus: Docket No. FAA-2015-3631; Directorate Identifier 2015-
NM-060-AD.

(a) Comments Due Date

    We must receive comments by July 21, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus airplanes, certificated in any 
category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of 
this AD, except airplanes on which Airbus Modification 203066, 
Modification 203074, or Modification 203372 has been embodied in 
production.
    (1) Model A330-201, -202, -203, -223, -223F, -243, -243F, -301, 
-302, -303, -321, -322, -323, -341, -342, and -343 airplanes; all 
manufacturer serial numbers (MSNs); if modified in-service as 
specified in Airbus Service Bulletin A330-25-3161, or in production 
with Airbus Modification 50014.
    (2) Model A340-211, -212, -213, -311, -312, and -313 airplanes; 
all MSNs, if modified in-service as specified in Airbus Service 
Bulletin A340-25-4181, or in production with Airbus Modification 
50014.
    (3) Model A340-541 airplanes and Model A340-642 airplanes; all 
MSNs.

(d) Subject

    Air Transport Association (ATA) of America Code 25, Equipment/
furnishings.

(e) Reason

    This AD was prompted by reports of chafed wiring at the upper 
left corner of the cockpit door. The affected wire bundle was not 
grounded on the cockpit door frame. We are issuing this AD to 
prevent electrical shock injury to persons contacting the cockpit 
door.

[[Page 36214]]

(f) Compliance

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

(g) Door Modification and Installation

    Within 24 months after the effective date of this AD, modify the 
cockpit door frame structure and install bonding-leads to the upper 
cockpit door frame, in accordance with the Accomplishment 
Instructions of the applicable service information identified in 
paragraphs (g)(1), (g)(2), and (g)(3) of this AD.
    (1) Airbus Service Bulletin A330-25-3534, Revision 02, dated May 
18, 2015.
    (2) Airbus Service Bulletin A340-25-4349, Revision 02, dated 
September 4, 2015.
    (3) Airbus Service Bulletin A340-25-5212, Revision 01, dated 
October 27, 2014.

(h) Cover Plate Modification of the Upper Flight Deck Door

    Except for airplanes on which Airbus Modification 52869 or 
Modification 53292 has been embodied in production: Prior to or 
concurrently with accomplishing the actions required by paragraph 
(g) of this AD, modify the upper cockpit door plate cover, in 
accordance with the Accomplishment Instructions of the applicable 
service information identified in paragraphs (h)(1), (h)(2), and 
(h)(3) of this AD.
    (1) For configuration 1 airplanes identified in Airbus Service 
Bulletin A330-25-3534, Revision 02, dated May 18, 2015: Airbus 
Service Bulletin A330-25-3213, Revision 01, dated April 25, 2005.
    (2) For airplanes identified in Airbus Service Bulletin A340-25-
4349, Revision 02, dated September 4, 2015: Airbus Service Bulletin 
A340-25-4217, Revision 01, dated April 25, 2005.
    (3) For airplanes identified in Airbus Service Bulletin A340-25-
5212, Revision 01, dated October 27, 2014: Airbus Service Bulletin 
A340-25-5046, Revision 02, dated February 5, 2007.

(i) Additional Concurrent Action for Certain Airplanes

    Prior to or concurrently with accomplishing the actions required 
by paragraph (g) of this AD: For configuration 1 airplanes 
identified in Airbus Service Bulletin A330-25-3534, Revision 02, 
dated May 18, 2015, install the noise-reduced cockpit door locking 
system (CDLS), in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A330-25-3254, Revision 02, dated December 
13, 2004.

(j) Credit for Previous Actions

    (1) 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 Airbus Service Bulletin A330-25-
3534, Revision 01, dated October 23, 2014; or Airbus Service 
Bulletin A340-25-4349, Revision 01, dated October 27, 2014, as 
applicable. These service bulletins are not incorporated by 
reference in this AD.
    (2) This paragraph provides credit for actions required by 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using the applicable service information 
specified in paragraphs (j)(2)(i) through (j)(2)(iv) of this AD. 
This service information is not incorporated by reference in this 
AD.
    (i) Airbus Service Bulletin A330-25-3213, dated October 12, 
2004.
    (ii) Airbus Service Bulletin A340-25-4217, dated October 12, 
2004.
    (iii) Airbus Service Bulletin A340-25-5046, dated October 12, 
2004.
    (iv) Airbus Service Bulletin A340-25-5046, Revision 01, dated 
May 11, 2005.
    (3) This paragraph provides credit for actions required by 
paragraph (i) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A330-25-
3254, dated October 25, 2004; or Airbus Service Bulletin A330-25-
3254, Revision 01, dated December 3, 2004. This service information 
is not incorporated by reference in this AD.

(k) 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 
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.
    (3) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0037, dated March 2, 2015, 
for related information. This MCAI may be found in the AD docket on 
the Internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2015-3631.
    (2) 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 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.


    Issued in Renton, Washington, on May 20, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-13049 Filed 6-3-16; 8:45 am]
 BILLING CODE 4910-13-P


