Federal Register / Vol. 81, No. 133 / Tuesday, July 12, 2016 / Rules and Regulations 44989 

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 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2016–13–15 Dassault Aviation: 

Amendment 39–18580. Docket No. 

FAA–2016–3987; Directorate Identifier 

2015–NM–165–AD. 

(a) Effective Date 

This AD is effective August 16, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Dassault Aviation 

Model FALCON 7X airplanes, certificated in 

any category, manufacturer serial numbers 1 

through 221 inclusive, except serial numbers 

182 and 220. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report of 

improperly drilled bores, located on upper 

and lower stiffener joints to the web at a 

certain frame. We are issuing this AD to 

detect and correct an unsatisfactory bore that 

can adversely affect the structural integrity of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspect Bores 

Within 4,000 flight cycles or 98 months, 

whichever occurs first since date of issuance 

of the original airworthiness certificate or 

date of issuance of the original export 

certificate of airworthiness, do a detailed 

visual and rototest inspection of the bores, 

located on upper and lower stiffener joints to 

the web at pylon Frame 41, to determine if 

the bores are not satisfactory, in accordance 

with the Accomplishment Instructions of 

Dassault Service Bulletin 7X–346, dated 

April 24, 2015. 

(h) Repair 

If, during the inspection required by 

paragraph (g) of this AD, it is determined that 

any bore is not satisfactory: Before further 

flight, repair affected bores, in accordance 

with the Accomplishment Instructions of 

Dassault Service Bulletin 7X–346, dated 

April 24, 2015, except as required by 

paragraph (i) of this AD. 

(i) Exceptions 

Where the Dassault Service Bulletin 7X– 

346, dated April 24, 2015, specifies to contact 

Dassault Aviation: Before further flight, 

repair using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA); or 

Dassault Aviation’s EASA Design 

Organization Approval (DOA). 

(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: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; 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 

EASA; or Dassault Aviation’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2015–0204, dated October 8, 2015, for related 

information. This MCAI may be found on the 

Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2016–3987. 

(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. 

(i) Dassault Service Bulletin 7X–346, dated 

April 24, 2015. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Dassault Falcon Jet 

Corporation, Teterboro Airport, P.O. Box 

2000, South Hackensack, NJ 07606; 

telephone: 201–440–6700; Internet: http://

www.dassaultfalcon.com. 

(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. 

(5) 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/ibrlocations.html. 

Issued in Renton, Washington, on June 23, 

2016. 

Dorr M. Anderson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–15930 Filed 7–11–16; 8:45 am] 

BILLING CODE 4910–13–P 

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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44990 Federal Register / Vol. 81, No. 133 / Tuesday, July 12, 2016 / Rules and Regulations 

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. 

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Federal Register / Vol. 81, No. 133 / Tuesday, July 12, 2016 / Rules and Regulations 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 

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44992 Federal Register / Vol. 81, No. 133 / Tuesday, July 12, 2016 / Rules and Regulations 

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 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 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. 

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Federal Register / Vol. 81, No. 133 / Tuesday, July 12, 2016 / Rules and Regulations 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/ibrlocations.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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