```

[Federal Register Volume 81, Number 133 (Tuesday, July 12, 2016)]
[Rules and Regulations]
[Pages 44989-44993]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-16212]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3632; Directorate Identifier 2015-NM-023-AD; 
Amendment 39-18590; AD 2016-14-09]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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[[Page 44990]]

SUMMARY: We are superseding 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 required inspecting the aft engine mount retainers for 
surface finish, cracks, and failure, and replacement if necessary. This 
new AD requires repetitive inspections for damaged, cracked, broken, 
and missing aft engine mount retainers, and replacement if necessary. 
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.

DATES: This AD is effective August 16, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 16, 
2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of August 
27, 2014 (79 FR 42655, July 23, 2014).

ADDRESSES: 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.
    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.
    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-2015-
3632.

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 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: 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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2014-14-06, Amendment 39-17901 (79 FR 42655, 
July 23, 2014) (``AD 2014-14-06''). AD 2014-14-06 applied to 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. The NPRM published in 
the Federal Register on September 17, 2015 (80 FR 55798) (``the 
NPRM''). The NPRM 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. The NPRM proposed 
to continue to require inspecting the aft engine mount retainers for 
surface finish, cracks, and failure, and replacement if necessary. The 
NPRM also proposed to require repetitive inspections for damaged, 
cracked broken, and missing aft engine mount retainers, and replacement 
if necessary. 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.
    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 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] 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

[[Page 44991]]

Request To Use Alternative Inspection Method

    Delta Airlines (DAL) requested that we revise paragraph (m) of the 
NPRM to approve use of a boroscope with 10X magnification when 
performing the inspection of the center aft engine mount inner retainer 
as an option to removing the center retainer. DAL stated that this 
procedure was allowed by the FAA in Alternative Method of Compliance 
(AMOC) ANM-116-14-423, dated September 16, 2014, for AD 2014-14-06. DAL 
stated that this procedure provides an equivalent level of safety since 
the detectability of the subject condition using this alternate 
inspection method is the same as a detailed visual inspection using 10X 
magnification, mirror, and light.
    We disagree with DAL's request. AMOC ANM-116-14-423, dated 
September 16, 2014, provides an AMOC for replacing 10X magnification, 
mirror, and light with a boroscope with 10X magnification but that AMOC 
is not an option to removing the center retainer. However, under the 
provisions of paragraph (q)(1) of this AD, we will consider requests 
for approval of alternative procedures, if sufficient data are 
submitted to substantiate that the change would provide an acceptable 
level of safety. We have not changed this AD in this regard.
    We have clarified in paragraph (q)(1)(ii) of this AD that AMOCs 
approved previously for AD 2014-14-06, are approved as AMOCs for the 
corresponding provisions of paragraphs (g) and (i) of this AD.

Request To Use Later Revisions of Service Information

    DAL requested that we permit use of later approved revisions of the 
service information. DAL stated that Airbus has released Airbus Service 
Bulletin A320-71-1060, Revision 01, dated April 7, 2015.
    We partially agree with DAL's request. We do not agree to include 
an allowance for later approved revisions of the referenced service 
information. When referring to a specific service document in an AD, 
using the phrase, ``or later FAA-approved revisions,'' violates the 
Office of the Federal Register's regulations for approving materials 
that are incorporated by reference. See 1 CFR 51.1(f).
    However, affected operators may request approval to use a later 
revision of the referenced service document as an alternative method of 
compliance, under the provisions of paragraph (q)(1) of this AD. We 
have not changed this AD in this regard.
    We agree to reference to Airbus Service Bulletin A320-71-1060, 
Revision 01, dated April 7, 2015, in this final rule as the appropriate 
source of service information for accomplishing the actions required by 
paragraphs (l) and (m) of this AD (referred to as paragraphs (m) and 
(n) in the proposed AD).
    We have also redesignated paragraph (l) of the proposed AD to 
paragraph (p)(1) of this AD (the paragraph retains existing credit 
information) and added new paragraphs (p)(2) and (p)(3) of this AD to 
provide provisional credit for Airbus Service Bulletin A320-71-1060, 
dated October 9, 2014. For operators to obtain credit for Airbus 
Service Bulletin A320-71-1060, dated October 9, 2014, for the 
replacement, operators must use the torque value units applicable to 
nut item (14) specified in Airbus Service Bulletin A320-71-1060, 
Revision 01, dated April 7, 2015. Those torque value units were 
incorrectly stated in Airbus Service Bulletin A320-71-1060, dated 
October 9, 2014.

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 for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-71-1060, Revision 01, dated 
April 7, 2015. This service information describes procedures for 
inspecting 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 inspecting 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.

Costs of Compliance

    We estimate that this AD affects 922 airplanes of U.S. registry.
    The actions required by AD 2014-14-06, and retained in this 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 were 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 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 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 
airplanes 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

[[Page 44992]]

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

2016-14-09 Airbus: Amendment 39-18590. Docket No. FAA-2015-3632; 
Directorate Identifier 2015-NM-023-AD.

(a) Effective Date

    This AD is effective August 16, 2016.

(b) Affected ADs

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

(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, 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, 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, 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, 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, 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) New Requirement of This AD: Repetitive Inspections

    At the latest of the applicable times specified in paragraphs 
(l)(1), (l)(2), and (l)(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, Revision 01, dated April 7, 2015; or Goodrich 
Service Bulletin RA32071-160, dated September 18, 2014. Repeat the 
inspection of the aft engine mount 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.

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

    If, during any detailed inspection specified in paragraph (l) 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, Revision 01, dated April 7, 2015.

[[Page 44993]]

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

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

(o) New Requirement of This AD: Required Reporting

    Submit a report of positive findings of any inspection required 
by paragraph (l) of this AD to Airbus at the applicable time 
specified in paragraph (o)(1) or (o)(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.

(p) Credit for Previous Actions

    (1) This paragraph restates the provisions of paragraph (l) of 
AD 2014-14-06, 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. This service information is not incorporated by 
reference in this AD.
    (2) This paragraph provides credit for actions required by 
paragraph (l) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-71-
1060, dated October 9, 2014. Airbus Service Bulletin A320-71-1060, 
dated October 9, 2014, is not incorporated by reference in this AD.
    (3) This paragraph provides credit for actions required by 
paragraph (m) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-71-
1060, dated October 9, 2014, provided that it can be conclusively 
determined that the torque value units applicable to nut item (14) 
that are specified in Airbus Service Bulletin A320-71-1060, Revision 
01, dated April 7, 2015, have been used. Airbus Service Bulletin 
A320-71-1060, dated October 9, 2014, is not incorporated by 
reference in 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-ANM-116-AMOC-REQUESTS@faa.gov.
    (i) 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.
    (ii) AMOCs approved previously for AD 2014-14-06, are approved 
as AMOCs for the corresponding provisions of paragraphs (g), (i), 
(j), and (k) of 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) EASA 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) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (t)(5), (t)(6), and (t)(7) of this AD.

(t) 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 16, 2016.
    (i) Airbus Service Bulletin A320-71-1060, Revision 01, dated 
April 7, 2015.
    (ii) Goodrich Service Bulletin RA32071-160, dated September 18, 
2014.
    (4) The following service information was approved for IBR on 
August 27, 2014 (79 FR 42655, July 23, 2014).
    (i) Airbus Alert Operators Transmission A71N001-12, Rev. 2, 
dated February 27, 2013. The first page of this document contains 
the document number, revision, and date; no other page of this 
document contains this information.
    (ii) Goodrich Service Bulletin RA32071-146, Rev. 2, dated July 
26, 2012.
    (5) 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.
    (6) 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.
    (7) 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.
    (8) 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 July 1, 2016.
Phillip Forde,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-16212 Filed 7-11-16; 8:45 am]
 BILLING CODE 4910-13-P
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