Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 26113 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–6539; Directorate 

Identifier 2015–NM–036–AD; Amendment 

39–18504; AD 2016–09–06] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A318–111 and –112 

airplanes; Model A319–111, –112, –113, 

–114, and –115 airplanes; Model A320– 

211, –212, and –214 airplanes; and 

Model A321–111, –112, –211, –212, and 

–213 airplanes. This AD was prompted 

by the results of an evaluation by the 

design approval holder (DAH). During a 

residual fatigue test, the forward engine 

mount failed prior to reaching the 

threshold/interval for the detailed 

inspections of the forward engine 

mounts specified in the airworthiness 

limitations. This AD requires repetitive 

detailed inspections of the right and left 

forward engine mounts, and corrective 

action if necessary. These inspections 

are required by AD 2015–05–02. This 

AD reduces the compliance times for 

those inspections. We are issuing this 

AD to detect and correct fatigue 

cracking in the forward engine mounts. 

Such cracking could result in reduced 

structural integrity of the airplane and 

could lead to in-flight loss of an engine, 

possibly resulting in reduced 

controllability of the airplane. 

DATES: This AD is effective June 6, 2016. 

ADDRESSES: For service information 

identified in this final rule, 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. 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– 

6539; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket 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 by adding an AD that would 

apply to all Airbus Model A318–111 

and –112 airplanes; Model A319–111, 

–112, –113, –114, and –115 airplanes; 

Model A320–211, –212, and –214 

airplanes; and Model A321–111, –112, 

–211, –212, and –213 airplanes. The 

NPRM published in the Federal 

Register on November 30, 2015 (80 FR 

74723) (‘‘the NPRM’’). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2015–0038, dated March 4, 

2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for all Airbus 

Model A318–111 and –112 airplanes; 

Model A319–111, –112, –113, –114, and 

–115 airplanes; Model A320–211, –212, 

and –214 airplanes; and Model A321– 

111, –112, –211, –212, and –213 

airplanes. The MCAI states: 

During a A320 Extended Service Goal 

(ESG) residual fatigue test, in which new 

loads were used, taking into account the 

results of the 2006 fleet survey, the CFM56– 

5A/5B forward engine mount experienced a 

failure before reaching the threshold/interval 

for the detailed inspection of that forward 

engine mount, as identified in Airbus A318/ 

A319/A320/A321 Airworthiness Limitations 

Section (ALS) Part 2 (hereafter referred to in 

this [EASA] AD as ‘the ALS’) task 712111– 

01. In case of total loss of the primary load 

path, the current maintenance requirements 

do not ensure the design integrity of the 

remaining structure. 

This condition, if not corrected, could lead 

to in-flight loss of an engine, possibly 

resulting in reduced control of the aeroplane 

and injury to persons on the ground. 

For the reasons described above, this 

[EASA] AD requires implementation of a 

reduced threshold and interval for the 

detailed inspections (DET) of the forward 

engine mount on both right hand (RH) and 

left hand (LH) sides, as specified in the ALS, 

task 712111–01. 

Once further investigations and test are 

completed, the threshold and interval of the 

ALS task 712111–01 will likely be modified 

accordingly. 

Required actions include repair of 

discrepancies (cracks) found during the 

inspection. 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– 

6539. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM and the FAA’s 

response. 

Request To Clarify That This Final Rule 

Was Not Prompted by Widespread 

Fatigue Damage (WFD) 

Airbus requested that all references to 

WFD be removed from the NPRM. 

Airbus stated that the root cause of the 

unsafe condition was not associated 

with WFD. The unsafe condition was 

revealed during a residual fatigue test of 

the CFM56–5A/5B forward engine 

mount. The forward engine mount 

failed prior to reaching the threshold/

interval for the detailed inspections 

specified in the Airbus A318/A319/

A320/A321 Airworthiness Limitations 

Section Part 2—Damage-Tolerant 

Airworthiness Limitation Items. 

Based on the information provided by 

the commenter we agree to remove all 

references to WFD from the preamble 

and regulatory text and include an 

explanation that this final rule was 

prompted by the results of an evaluation 

by the DAH. 

Conclusion 

We reviewed the relevant data, 

considered the comment 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 minor 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. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

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26114 Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 

Costs of Compliance 

We estimate that this AD affects 940 

airplanes of U.S. registry. 

We also estimate that it will take 

about 1 work-hour per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $79,900, or $85 per 

product. 

We have received no definitive data 

that will enable us to provide cost 

estimates for the on-condition parts cost 

specified in this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

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): 

2016–09–06 Airbus: Amendment 39–18504. 

Docket No. FAA–2015–6539; Directorate 

Identifier 2015–NM–036–AD. 

(a) Effective Date 

This AD is effective June 6, 2016. 

(b) Affected AD 

This AD affects AD 2015–05–02, 

Amendment 39–18112 (80 FR 15152, March 

23, 2015) (‘‘AD 2015–05–02’’). 

(c) Applicability 

This AD applies to all Airbus airplanes, 

certificated in any category, identified in 

paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of 

this AD. 

(1) Model A318–111 and –112 airplanes. 

(2) Model A319–111, –112, –113, –114, and 

–115 airplanes. 

(3) Model A320–211, –212, and –214 

airplanes. 

(4) Model A321–111, –112, –211, –212, and 

–213 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Periodic Inspections. 

(e) Reason 

This AD was prompted by the results of an 

evaluation by the design approval holder. 

During a residual fatigue test the forward 

engine mount failed prior to reaching the 

threshold/interval for the detailed 

inspections of the forward engine mounts 

specified in the airworthiness limitations. We 

are issuing this AD to detect and correct 

fatigue cracking in the forward engine 

mounts. Such cracking could result in 

reduced structural integrity of the airplane 

and could lead to in-flight loss of an engine, 

possibly resulting in reduced controllability 

of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

At the latest of the times specified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD: 

Do a detailed inspection of the left and right 

forward engine mounts for discrepancies 

(cracking), using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA. Repeat 

the inspection thereafter at intervals not to 

exceed 800 flight cycles. 

Note 1 to paragraphs (g) and (h) of this 

AD: Guidance for the inspection and engine 

mount replacement can be found in Task 

712111–210–040 of the Airbus A318/A319/

A320/A321 Maintenance Manual. 

(1) Within 800 flight cycles since the first 

flight of the airplane. 

(2) Within 800 flight cycles since the most 

recent detailed inspection specified in Airbus 

Airworthiness Limitation Tasks 712111–01– 

1, 712111–01–2, 712111–01–3, or 712111– 

01–4, ‘‘Detailed Inspection of Forward 

Engine Mount Installation,’’ as applicable. 

(3) Within 800 flight cycles after the 

effective date of this AD. 

(h) Corrective Action 

If any discrepancy (cracking) is found 

during any inspection required by paragraph 

(g) of this AD: Before further flight, replace 

the affected forward engine mount with a 

serviceable part, 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). 

(i) No Terminating Action 

Replacement of a forward engine mount 

does not constitute terminating action for the 

repetitive inspections required by paragraph 

(g) of this AD. 

(j) Termination of Certain Tasks Required by 

AD 2015–05–02 

Accomplishment of the inspections 

required by paragraph (g) of this AD 

terminates the initial and repetitive 

inspections specified in paragraph (n)(2) of 

AD 2015–05–02, for Airbus Airworthiness 

Limitation Tasks 712111–01–1, 712111–01– 

2, 712111–01–3, and 712111–01–4, ‘‘Detailed 

Inspection of Forward Engine Mount 

Installation.’’ 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

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– 

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Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 26115 

AMOC–REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(l) 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. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0038, dated 

March 4, 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– 

2015–6539. 

(2) For 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. 

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. 

(n) Material Incorporated by Reference 

None. 

Issued in Renton, Washington, on April 20, 

2016. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–10117 Filed 4–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2458; Directorate 

Identifier 2014–NM–122–AD; Amendment 

39–18468; AD 2016–07–23] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A318, A319, A320, and 

A321 series airplanes. This AD was 

prompted by reports of in-flight loss of 

fixed and hinged main landing gear 

(MLG) fairings, and reports of postmodification MLG fixed fairing 

assemblies that have wear and 

corrosion. This AD requires, for certain 

airplanes, repetitive replacements of the 

fixed fairing upper and lower 

attachment studs of both left-hand (LH) 

and the right-hand (RH) MLG; and 

repetitive inspections for corrosion, 

wear, fatigue cracking, and loose studs 

of each forward stud assembly of the 

fixed fairing door upper and lower 

forward attachment of both LH and RH 

MLG; and replacement if necessary. 

This AD also provides an optional 

terminating modification for the 

repetitive replacements of the fixed 

fairing upper and lower attachment 

studs. We are issuing this AD to prevent 

in-flight detachment of an MLG fixed 

fairing and consequent damage to the 

airplane. 

DATES: This AD becomes effective June 

6, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 6, 2016. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

2458; or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC. 

For service information identified in 

this final rule, 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. 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– 

2458. 

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 by adding an AD that would 

apply to all Airbus Model A318, A319, 

A320, and A321 series airplanes. The 

NPRM published in the Federal 

Register on July 8, 2015 (80 FR 38992) 

(‘‘the NPRM’’). The NPRM was 

prompted by reports of in-flight loss of 

fixed and hinged MLG fairings, and 

reports of post-modification MLG fixed 

fairing assemblies that have wear and 

corrosion. The NPRM proposed to 

require, for certain airplanes, repetitive 

replacements of the fixed fairing upper 

and lower attachment studs of both the 

LH and RH MLG; and repetitive 

inspections for corrosion, wear, fatigue 

cracking, and loose studs of each 

forward stud assembly of the fixed 

fairing door upper and lower forward 

attachment of both LH and RH MLG; 

and replacement if necessary. The 

NPRM also proposed an optional 

terminating modification for the 

repetitive replacements of the fixed 

fairing upper and lower attachment 

studs. We are issuing this AD to prevent 

in-flight detachment of an MLG fixed 

fairing and consequent damage to the 

airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2015–0001R1, dated January 

15, 2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for all Airbus 

Model A318, A319, A320, and A321 

series airplanes. The MCAI states: 

Several occurrences of in-flight loss of 

main landing gear (MLG) fixed and hinged 

fairings were reported. The majority of 

reported events occurred following 

scheduled maintenance activities. One result 

of the investigation was that a discrepancy 

between the drawing and the maintenance 

manuals was discovered. The maintenance 

documents were corrected to prevent misrigging of the MLG fixed and hinged fairings, 

which could induce fatigue cracking. 

Airbus issued Service Bulletin (SB) A320– 

52–1083, providing instructions for a onetime inspection of the MLG fixed fairing 

composite insert and the surrounding area, 

replacement of the adjustment studs at the 

lower forward position and adjustment to the 

new clearance tolerances. That SB was 

replaced by Airbus SB A320–52–1100 (mod 

27716) introducing a re-designed location 

stud, rod end and location plate at the 

forward upper and lower leg fixed-fairing 

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