```

[Federal Register Volume 80, Number 180 (Thursday, September 17, 2015)]
[Proposed Rules]
[Pages 55798-55801]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-23328]

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3632; Directorate Identifier 2015-NM-023-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2014-14-
06 for all Airbus Model A318-111 and -112 airplanes; Model A319-111, -
112, -113, -114, and -115 airplanes; Model A320-111, -211, -212, and -
214 airplanes; and Model A321-111, -112, -211, -212, and -213 
airplanes. AD 2014-14-06 currently requires inspecting the aft engine 
mount retainers for surface finish, cracks, and failure, and 
replacement if necessary. Since we issued AD 2014-14-06, inspection 
results have shown that the main cause of crack initiation remains the 
vibration dynamic effect that affects both retainers, either with 
``dull'' or ``bright'' surface finishes. This proposed AD would require 
repetitive inspections for damage, cracks, broken, and missing aft 
engine mount retainers, and replacement if necessary. We are proposing 
this AD to detect and correct failure of retainer brackets of the aft 
engine mount and consequent loss of the locking feature of the nuts of 
the inner and outer pins; loss of the pins will result in the aft mount 
engine link no longer being secured to the aft engine mount.

DATES: We must receive comments on this proposed AD by November 2, 
2015.

ADDRESSES: You may send comments 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 Airbus service information identified in this proposed AD, 
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet 
http://www.airbus.com.
    For Goodrich Aerostructures service information identified in this 
proposed AD, contact Goodrich Aerostructures, 850 Lagoon Drive, Chula 
Vista, CA 91910-2098; telephone 619-691-2719; email 
jan.lewis@goodrich.com; Internet http://www.goodrich.com/TechPubs.
    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-
3632; 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 
Operations 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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
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-2015-3632; 
Directorate Identifier 2015-NM-023-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

    On July 3, 2014, we issued AD 2014-14-06, Amendment 39-17901 (79 FR 
42655, July 23, 2014). AD 2014-14-06 requires actions intended to 
address an unsafe condition on all Model A318-111 and -112 airplanes; 
Model A319-111, -112, -113, -114, and -115 airplanes; Model A320-111, -
211, -212, and -214 airplanes; and Model A321-111, -112, -211, -212, 
and -213 airplanes.
    Since we issued AD 2014-14-06, Amendment 39-17901 (79 FR 42655, 
July 23, 2014), we have determined that additional inspections are 
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 2015-0021, dated February 13, 2015 (referred to after this as 
the Mandatory Continuing Airworthiness Information, or ``the MCAI''), 
to correct an unsafe condition. The MCAI states:

    During in-service inspections, several aft engine mount 
retainers, fitted on aeroplanes equipped with CFM56-5A/5B engines, 
have been found broken. The results of the initial investigations 
highlighted that two different types of surface finish had been 
applied (respectively bright and dull material finishes), and that 
dull finish affects the strength of the retainer with regard to 
fatigue properties of the part. The pins which attach the engine 
link to the aft mount are secured

[[Page 55799]]

by two nuts, which do not have a self-locking feature; this function 
is provided by the retainer brackets. In case of failure of the 
retainer bracket, the locking feature of the nuts of the inner and 
outer pins is lost; as a result, these nuts could subsequently 
become loose.
    In case of full loss of the nuts, there is the potential to also 
lose the pins, in which case the aft mount link will no longer be 
secured to the aft engine mount. The same locking feature is used 
for the three link assemblies of the aft mount.
    This condition, if not detected and corrected, could lead to in-
flight loss of an aft mount link, possibly resulting in damage to 
the aeroplane and injury to person on the ground.
    To address this potential unsafe condition, EASA issued AD 2013-
0050 (http://ad.easa.europa.eu/blob/easa_ad_2013_0050_superseded.pdf/AD_2013-0050_1 [which corresponds 
to FAA AD 2014-14-06, Amendment 39-17901 (79 FR 42655, July 23, 
2014)] to require detailed inspections (DET) of the aft engine mount 
retainers and the replacement of all retainers with dull finish with 
retainers having a bright finish.
    Since that [EASA] AD was issued, inspection results have shown 
that the main cause of crack initiation remains the vibration 
dynamic effect that affects both retainers, either with ``dull'' or 
``bright'' surface finishes. The non-conforming ``dull'' surface's 
pitting is an aggravating factor.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2013-0050, which is superseded, and requires 
repetitive DET of all aft engine mount retainers and, depending on 
findings [damaged, cracked, broken, or missing retainers], their 
replacement.
    This [EASA] AD is considered to be an interim action, pending 
development and availability of a final solution.

    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-
3632.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-71-1060, dated October 9, 
2014. This service information describes procedures for inspection of 
the aft engine mount retainers for surface finish (dull or bright), for 
damaged, cracked, broken, or missing retainers, and replacement.
    Goodrich Aerostructures has issued Service Bulletin RA32071-160, 
dated September 18, 2014. This service information describes procedures 
for inspection of the aft engine mount inner retainers for cracks or 
failure, and replacement.
    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 
NPRM.

FAA's Determination and Requirements of This Proposed AD

    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 these 
same type designs.

Explanation of ``RC'' Procedures and Tests in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which procedures and tests in the service information are 
required for compliance with an AD. Differentiating these procedures 
and tests from other tasks in the service information is expected to 
improve an owner's/operator's understanding of crucial AD requirements 
and help provide consistent judgment in AD compliance. The procedures 
and tests identified as Required for Compliance (RC) in any service 
information have a direct effect on detecting, preventing, resolving, 
or eliminating an identified unsafe condition.
    As specified in a NOTE under the Accomplishment Instructions of the 
specified Airbus service information, procedures and tests that are 
identified as RC in any service information must be done to comply with 
the proposed AD. However, procedures and 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 alternative method of compliance 
(AMOC), provided the procedures and tests identified as RC can be done 
and the airplane can be put back in a serviceable condition. Any 
substitutions or changes to procedures or tests identified as RC will 
require approval of an AMOC.

Costs of Compliance

    We estimate that this proposed AD affects 922 airplanes of U.S. 
registry.
    The actions required by AD 2014-14-06, Amendment 39-17901 (79 FR 
42655, July 23, 2014), and retained in this proposed AD take about 3 
work-hours per product, at an average labor rate of $85 per work-hour. 
Based on these figures, the estimated cost of the actions that are 
required by AD 2014-14-06 is $255 per inspection cycle per product (for 
two engines).
    We also estimate that it would take about 10 work-hours per product 
to comply with the basic requirements of this proposed AD, and 1 work-
hour per product to report inspection findings. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this proposed AD on U.S. operators to be $862,070, or $935 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 2 work-hours and require parts costing $10,000, for a cost 
of $10,170 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

[[Page 55800]]

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 removing Airworthiness Directive (AD) 
2014-14-06, Amendment 39-17901 (79 FR 42655, July 23, 2014), and adding 
the following new AD:

Airbus: Docket No. FAA-2015-3632; Directorate Identifier 2015-NM-
023-AD.

(a) Comments Due Date

    We must receive comments by November 2, 2015.

(b) Affected ADs

    This AD replaces AD 2014-14-06, Amendment 39-17901 (79 FR 42655, 
July 23, 2014).

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A318-111 and -112 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, and -115 airplanes.
    (3) Airbus Model A320-211, -212, and -214 airplanes.
    (4) Airbus Model A321-111, -112, -211, -212, and -213 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Powerplant.

(e) Reason

    This AD was prompted by inspection results that have shown that 
the main cause of crack initiation in the aft engine mount retainers 
is the vibration dynamic effect that affects both retainers, either 
with ``dull'' or ``bright'' surface finishes. We are issuing this AD 
to detect and correct failure of retainer brackets of the aft engine 
mount and consequent loss of the locking feature of the nuts of the 
inner and outer pins; loss of the pins will result in the aft mount 
engine link no longer being secured to the aft engine mount.

(f) Compliance

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

(g) Retained Inspection, With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2014-14-06, Amendment 39-17901 (79 FR 42655, July 23, 2014), with no 
changes. Within 3 months after August 27, 2014 (the effective date 
of AD 2014-14-06): Do a detailed inspection of the aft engine mount 
retainers for surface finish (dull or bright), and for cracks and 
failure, in accordance with Section 4.2.2, ``Inspection 
Requirements,'' of Airbus Alert Operators Transmission (AOT) 
A71N001-12, Rev. 2, dated February 27, 2013, except as specified in 
paragraph (h) of this AD.

(h) Retained Exception to Paragraph (g) of This AD, With No Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2014-14-06, Amendment 39-17901 (79 FR 42655, July 23, 2014), with no 
changes. The actions required by paragraph (g) of this AD are not 
required to be done on airplanes with manufacturer serial numbers 
4942 and higher, provided a review of maintenance records verifies 
that no aft engine mount retainers have been replaced since first 
flight of the airplane.

(i) Retained Repetitive Inspection and Retainer Replacement for Dull 
Finish Retainers, With No Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2014-14-06, Amendment 39-17901 (79 FR 42655, July 23, 2014), with no 
changes. If, during the detailed inspection required by paragraph 
(g) of this AD, any installed dull finish aft engine mount retainer 
is found without cracks and not failed: Do the actions specified in 
paragraphs (i)(1) and (i)(2) of this AD.
    (1) Within 25 flight cycles after doing the actions required by 
paragraph (g) of this AD: Repeat the detailed inspection specified 
in paragraph (g) of this AD.
    (2) Within 50 flight cycles after doing the first detailed 
inspection specified in paragraph (g) of this AD: Replace all dull 
finish retainers with new retainers, in accordance with Section 
4.2.3.1, ``Replacement Procedure,'' of Airbus AOT A71N001-12, Rev. 
2, dated February 27, 2013.

(j) Retained Replacement of Cracked or Failed Retainers, With No 
Changes

    This paragraph restates the requirements of paragraph (j) of AD 
2014-14-06, Amendment 39-17901 (79 FR 42655, July 23, 2014), with no 
changes. If, during any detailed inspection specified in paragraph 
(g) of this AD, any installed aft engine mount retainer is found 
cracked or failed: Before further flight, replace all affected aft 
engine mount retainers with new retainers, in accordance with 
Section 4.2.3, ``Replacement Procedure,'' of Airbus AOT A71N001-12, 
Rev. 2, dated February 27, 2013.

(k) Retained Parts Prohibition, With No Changes

    This paragraph restates the requirements of paragraph (k) of AD 
2014-14-06, Amendment 39-17901 (79 FR 42655, July 23, 2014), with no 
changes. As of August 27, 2014 (the effective date of AD 2014-14-
06), no person may install any aft engine mount retainer with a dull 
finish on any airplane. The instructions of Airbus AOT A71N001-12, 
Rev. 2, dated February 27, 2013; or the Accomplishment Instructions 
of Goodrich Service Bulletin RA32071-146, Rev. 2, dated July 26, 
2012; may be used to verify the correct finish of the part.

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

    This paragraph restates the provisions of paragraph (l) of AD 
2014-14-06, Amendment 39-17901 (79 FR 42655, July 23, 2014), with no 
changes. This paragraph provides credit for actions required by 
paragraphs (g), (i), and (j) of this AD, if those actions were 
performed before August 27, 2014 (the effective date of AD 2014-14-
06) using Airbus AOT A71N001-12, Rev. 1, dated August 9, 2012, which 
is not incorporated by reference in this AD.

(m) New Requirement of This AD: Repetitive Inspections

    At the latest of the applicable times specified in paragraphs 
(m)(1), (m)(2), and (m)(3) of this AD: Do a detailed inspection for 
damaged, cracked, broken, or missing aft engine mount retainers, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-71-1060, dated October 9, 2014; or Goodrich Service 
Bulletin RA32071-160, dated September 18, 2014. Repeat the 
inspection of the aft engine mount

[[Page 55801]]

retainers thereafter at intervals not to exceed 12 months.
    (1) Within 12 months since the date of issuance of the original 
airworthiness certificate or the date of issuance of the original 
export certificate of airworthiness.
    (2) Within 12 months after installation of new retainers.
    (3) Within 9 months after the effective date of this AD.

(n) New Requirement of This AD: Replacement of Retainers With Findings

    If, during any detailed inspection specified in paragraph (m) of 
this AD, any installed aft engine mount retainer is found damaged, 
cracked, broken, or missing: Before further flight, replace all 
affected aft engine mount retainers with new retainers, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-71-1060, dated October 9, 2014.

(o) New Requirement of This AD: No Terminating Action

    Replacement of retainers on an airplane, as required by 
paragraph (n) of this AD, does not constitute terminating action for 
the repetitive inspections required by paragraph (m) of this AD for 
that airplane.

(p) New Requirement of This AD: Required Reporting

    Submit a report of positive findings of any inspection required 
by paragraph (m) of this AD to Airbus at the applicable time 
specified in paragraph (p)(1) or (p)(2) of this AD. The report must 
include the inspection results, a description of any discrepancies 
found, the airplane serial number, and the number of landings and 
flight hours on the airplane.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

(q) 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: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. Information may be 
emailed to: 9-0ANM-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: 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, 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) 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.
    (4) Required for Compliance (RC): If any Airbus 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 a serviceable 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(r) Special Flight Permits

    Special flight permits, as described in Section 21.197 and 
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199), are not allowed.

(s) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency Airworthiness Directive 2015-
0021, dated February 13, 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-
2015-3632.
    (2) For Airbus service information identified in this AD, 
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
Internet http://www.airbus.com.
    (3) For Goodrich Aerostructures service information identified 
in this AD, contact Goodrich Aerostructures, 850 Lagoon Drive, Chula 
Vista, CA 91910-2098; telephone 619-691-2719; email 
jan.lewis@goodrich.com; Internet http://www.goodrich.com/TechPubs.
    (4) 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 September 9, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-23328 Filed 9-16-15; 8:45 am]
 BILLING CODE 4910-13-P
```