Federal Register / Vol. 80, No. 16 / Monday, January 26, 2015 / Rules and Regulations 3871 

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. 

(h) Related Information 

Refer to MCAI Federal Office of Civil 

Aviation (FOCA) AD HB–2014–001, dated 

July 25, 2014; and AD HB–2014–001R1, 

dated November 5, 2014 for related 

information. The MCAI can be found in the 

AD docket on the Internet at: http://

www.regulations.gov/

#!docketBrowser;rpp=25;po=0;dct=PR%25

2BSR;D=FAA-2014-0770. 

(i) 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 the AD specifies otherwise. 

(i) Pilatus Aircraft Ltd. Pilatus PC–7 

Service Bulletin No: 51–001, Revision No. 1, 

dated August 26, 2014. 

(ii) Reserved. 

(3) For Pilatus Aircraft Ltd. service 

information identified in this AD, contact 

Pilatus Aircraft Ltd., Customer Technical 

Support (MCC), P.O. Box 992, CH–6371 

Stans, Switzerland; phone: +41 (0)41 619 67 

74; fax: +41 (0)41 619 67 73; email: 

Techsupport@pilatus-aircraft.com; internet: 

http://www.pilatus-aircraft.com. 

(4) You may view this service information 

at the FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

(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 Kansas City, Missouri, on 

December 31, 2014. 

Robert Busto, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–00010 Filed 1–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0692; Directorate 

Identifier 2012–NM–024–AD; Amendment 

39–18031; AD 2014–23–15] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) AD 2011– 

14–06 for all Airbus Model A318, A319, 

A320, and A321 series airplanes. AD 

2011–14–06 required revising the 

maintenance program. This new AD 

requires revising the maintenance 

program to incorporate new, more 

restrictive limitations. This AD was 

prompted by the determination that 

more restrictive limitations are 

necessary. We are issuing this AD to 

prevent fatigue cracking, accidental 

damage, or corrosion in principal 

structural elements, and possible failure 

of certain life limited parts, which could 

result in reduced structural integrity of 

the airplane. 

DATES: This AD becomes effective 

March 2, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 2, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of August 22, 2011 (76 FR 

42024, July 18, 2011). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of November 7, 2007 (72 FR 

56262, October 3, 2007). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0692; 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 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.airwortheas@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. 

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 supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to supersede AD 

2011–14–06, Amendment 39–16741 (76 

FR 42024, July 18, 2011). AD 2011–14– 

06 applied to Airbus Model A318, A319, 

A320, and A321 series airplanes. The 

SNPRM published in the Federal 

Register on May 28, 2014 (79 FR 30492). 

We preceded the SNPRM with a notice 

of proposed rulemaking (NPRM) that 

published in the Federal Register on 

August 13, 2013 (78 FR 49213). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0147, 

dated July 16, 2013 (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: 

The airworthiness limitations for Airbus 

A320 family aeroplanes are currently 

included in Airbus A318/A319/A320/A321 

Airworthiness Limitations Section (ALS) 

document. The airworthiness limitations 

applicable to the Damage Tolerant 

Airworthiness Limitation Items (DT ALI) are 

currently given in Airbus ALS Part 2, which 

is approved by EASA. 

Previously, EASA issued AD 2010–0071R1 

[http://ad.easa.europa.eu/blob/easa_ad_

2010_0071_R1.pdf/AD_2010–0071R1_1] 

[associated with FAA AD 2011–14–06, 

Amendment 39–16741 (76 FR 42024, July 18, 

2011)], which required the implementation of 

the DT ALI maintenance instructions as 

specified in Airbus A318/A319/A320/A321 

ALI Document ref. AI/SE–M4/95A.0252/96 

issue 10 and Airbus A319 Corporate Jet ALI 

Document ref. AI/SE–M2/95A.1038/99. 

The new Airbus A318/A319/A320/A321 

ALS Part 2 Revision 02, which includes also 

Airbus A319 Corporate Jet, introduces more 

restrictive DT ALI maintenance instructions. 

Failure to comply with these instructions 

could result in an unsafe condition. 

Application of new DT ALI tasks 531129– 

02–2 and 531129–02–3 introduces initial and 


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repetitive inspections of the windshield 

central lower node continuity fittings, 

replacing the one time inspection for that 

subject, previously required by EASA AD 

2011–0231 [http://ad.easa.europa.eu/blob/

easa_ad_2011_0231.pdf] [associated with 

FAA AD 2013–13–03, Amendment 39–17491 

(78 FR 41280, July 10, 2013)]. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2010–0071R1 * * *, which are 

superseded, and requires compliance with all 

maintenance tasks as described in Airbus 

A318/A319/A320/A321 ALS part 2 at 

Revision 02. 

The unsafe condition is fatigue cracking, 

accidental damage, or corrosion in 

principal structural elements, and 

possible failure of certain life limited 

parts, which could result in reduced 

structural integrity of the airplane. You 

may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the SNPRM (79 FR 30492, 

May 28, 2014) and the FAA’s response 

to each comment. 

Request To Extend Compliance Time 

United Airlines (UAL), Delta Airlines 

(DAL), and Virgin America asked that 

we extend the compliance time for 

incorporation of Airbus A318/A319/

A320/A321 ALS Part 2—DamageTolerant Airworthiness Limitation Items 

(DT ALI), Revision 02, dated May 28, 

2013. UAL stated that it would like to 

manage the task incorporation on an 

individual basis. UAL proposed that we 

revise the compliance times specified in 

paragraph (n) of the SNPRM (79 FR 

30492, May 28, 2014) as follows: ‘‘After 

the effective date of this AD, incorporate 

each task into the program within the 

specific threshold/interval provided.’’ 

DAL and Virgin America stated that, to 

provide time to revise the maintenance 

program and perform any related tasks 

that might exceed the compliance 

thresholds specified in the ALI, the 

grace period specified in paragraph (n) 

of the SNPRM should be changed from 

4 to 12 months. 

DAL asked for more time to update 

the maintenance program to incorporate 

Airbus A318/A319/A320/A321 ALS 

Part 2—Damage-Tolerant Airworthiness 

Limitation Items (DT ALI), Revision 02, 

dated May 28, 2013. DAL and Virgin 

America requested 9 months, as 

opposed to 30 days, because 9 months 

was the allowed compliance time for 

incorporating airworthiness limitation 

items into the maintenance program 

required by AD 2011–14–06, 

Amendment 39–16741 (76 FR 42024, 

July 18, 2011). 

We acknowledge the commenters’ 

concerns; however, we do not agree to 

extend the compliance times for 

incorporation of the tasks into the 

maintenance program. We based the 

compliance times in this AD primarily 

on our assessment of the safety risk. 

Since some safety issues are more timesensitive than others, we consider the 

overall risk to the fleet, including the 

severity of the failure and the likelihood 

of the occurrence of the failure. In this 

case, the primary reason for requiring 

incorporation of Airbus A318/A319/

A320/A321 ALS Part 2—DamageTolerant Airworthiness Limitation Items 

(DT ALI), Revision 02, dated May 28, 

2013, is to cover extension of the design 

service goal and preliminary results 

from widespread fatigue damage. 

Therefore, we do not agree to extend 

the grace period or compliance times for 

incorporation of the tasks into the 

maintenance program. However, under 

the provisions of paragraph (p)(1) of this 

AD, we will consider requests for 

approval of extending the compliance 

time based on the current status of the 

maintenance and inspection programs 

relative to the ALI tasks if sufficient data 

are submitted to substantiate that it 

would provide an acceptable level of 

safety. We have not changed this AD in 

this regard. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. 

We have become aware that some 

operators have misunderstood or 

misinterpreted the Airworthy Product 

paragraph to allow the owner/operator 

to use messages provided by the 

manufacturer as approval of deviations 

during the accomplishment of an ADmandated action. The Airworthy 

Product paragraph does not approve 

messages or other information provided 

by the manufacturer for deviations to 

the requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed the 

paragraph and retitled it ‘‘Contacting the 

Manufacturer.’’ This paragraph now 

clarifies that for any requirement in this 

AD to obtain corrective actions from a 

manufacturer, the actions must be 

accomplished using a method approved 

by the FAA, the European Aviation 

Safety Agency (EASA), or Airbus’s 

EASA Design Organization Approval 

(DOA). 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DOA, the approval must include 

the DOA-authorized signature. The DOA 

signature indicates that the data and 

information contained in the document 

are EASA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DOA-authorized signature approval are 

not EASA-approved, unless EASA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

We also have decided not to include 

a generic reference to either the 

‘‘delegated agent’’ or ‘‘design approval 

holder (DAH) with State of Design 

Authority design organization 

approval,’’ but instead we have 

provided the specific delegation 

approval granted by the State of Design 

Authority for the DAH. 

Conclusion 

We reviewed the relevant data, 

considered 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 minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM (79 FR 


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Federal Register / Vol. 80, No. 16 / Monday, January 26, 2015 / Rules and Regulations 3873 

30492, May 28, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM (79 FR 30492, 

May 28, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 851 

airplanes of U.S. registry. 

The actions required by AD 2011–14– 

06, Amendment 39–16741 (76 FR 

42024, July 18, 2011), and retained in 

this AD take about 1 work-hour per 

product, at an average labor rate of $85 

per work-hour. Based on these figures, 

the estimated cost of the required 

actions is $85 per product. 

We also estimate that it will take 

about 1 work-hour per product to 

comply with the new 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 $72,335, 

or $85 per product. 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0692; 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 Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

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) 

2011–14–06, Amendment 39–16741 (76 

FR 42024, July 18, 2011), and adding the 

following new AD: 

2014–23–15 Airbus: Amendment 39–18031. 

Docket No. FAA–2013–0692; Directorate 

Identifier 2012–NM–024–AD. 

(a) Effective Date 

This AD becomes effective March 2, 2015. 

(b) Affected ADs 

This AD replaces AD 2011–14–06, 

Amendment 39–16741 (76 FR 42024, July 18, 

2011). 

(c) Applicability 

This AD applies to all Airbus Model A318– 

111, –112, –121, and –122 airplanes; Model 

A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes; Model A320–111, 

–211, –212, –214, –231, –232, and –233 

airplanes; and Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Periodic Inspections. 

(e) Reason 

This AD was prompted by a determination 

that more restrictive limitations are 

necessary. We are issuing this AD to prevent 

fatigue cracking, accidental damage, or 

corrosion in principal structural elements, 

and possible failure of certain life limited 

parts, which could result in reduced 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Revision of Airworthiness 

Limitations Section (ALS) To Incorporate 

Safe Life Airworthiness Limitation Items 

(ALIs) 

This paragraph restates the requirements of 

paragraph (g) of AD 2011–14–06, 

Amendment 39–16741 (76 FR 42024, July 18, 

2011). For Model A318–111 and –112 

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

–114, –115, –131, –132, and –133 airplanes; 

Model A320–111, –211, –212, –214, –231, 

–232, and –233 airplanes; and Model A321– 

111, –112, –131, –211, –212, –213, –231, and 

–232 airplanes: Within 3 months after 

November 7, 2007 (the effective date of AD 

2007–20–05, Amendment 39–15215 (72 FR 

56262, October 3, 2007)), revise the ALS of 

the Instructions for Continued Airworthiness 

to incorporate Sub-part 1–2, ‘‘Life Limits,’’ 

and Sub-part 1–3, ‘‘Demonstrated Fatigue 

Lives,’’ of Airbus A318/A319/A320/A321 

ALS Part 1—Safe Life Airworthiness 

Limitation Items, Revision 00, dated 

February 28, 2006. Accomplish the actions in 

Sub-part 1–2, ‘‘Life Limits,’’ and Sub-part 1– 

3, ‘‘Demonstrated Fatigue Lives,’’ of Airbus 

A318/A319/A320/A321 ALS Part 1—Safe 

Life Airworthiness Limitation Items, 

Revision 00, dated February 28, 2006, at the 

times specified in Sub-part 1–2, ‘‘Life 

Limits,’’ and Sub-part 1–3, ‘‘Demonstrated 

Fatigue Lives,’’ of Airbus A318/A319/A320/ 

A321 ALS Part 1—Safe Life Airworthiness 

Limitation Items, dated February 28, 2006, 

except as provided by paragraph (i) of this 

AD. Accomplishing the actions required by 

paragraph (j) of this AD terminates the 

requirements of this paragraph. 

(h) Retained Revision to ALS To Incorporate 

Damage Tolerant ALIs 

This paragraph restates certain provisions 

of paragraph (h) of AD 2011–14–06, 

Amendment 39–16741 (76 FR 42024, July 18, 

2011). For Model A318–111 and –112 

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

–114, –115, –131, –132, and –133 airplanes; 

Model A320–111, –211, –212, –214, –231, 

–232, and –233 airplanes; and Model A321– 

111, –112, –131, –211, –212, –213, –231, and 

–232 airplanes; except Model A319 airplanes 

on which Airbus Modifications 28238, 

28162, and 28342 have been incorporated in 

production: Within 14 days after November 


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7, 2007 (the effective date of AD 2007–20–05, 

Amendment 39–15215 (72 FR 56262, October 

3, 2007)), revise the ALS of the Instructions 

for Continued Airworthiness to incorporate 

Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 7, dated 

December 2005 (approved by the European 

Aviation Safety Agency (EASA) on February 

7, 2006); Issue 08, dated March 2006 

(approved by the EASA on January 4, 2007); 

or Issue 09, dated November 2006 (approved 

by the EASA on May 21, 2007). Accomplish 

the actions in Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 7, dated 

December 2005; Issue 08, dated March 2006; 

or Issue 09, dated November 2006; at the 

times specified in Airbus A318/A319/A320/ 

A321 Airworthiness Limitation Items, 

Document AI/SE–M4/95A.0252/96, Issue 7, 

dated December 2005; Issue 08, dated March 

2006; or Issue 09, dated November 2006; as 

applicable; except as provided by paragraph 

(i) of this AD. Accomplishing the actions 

required by paragraph (j) or (n) of this AD, 

as applicable, terminates the requirements of 

this paragraph. 

(i) Retained Grace Period for New or More 

Restrictive Actions 

This paragraph restates certain provisions 

of paragraph (i) of AD 2011–14–06, 

Amendment 39–16741 (76 FR 42024, July 18, 

2011). For Model A318–111 and –112 

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

–114, –115, –131, –132, and –133 airplanes; 

Model A320–111, –211, –212, –214, –231, 

–232, and –233 airplanes; and Model A321– 

111, –112, –131, –211, –212, –213, –231, and 

–232 airplanes: For any new or more 

restrictive life-limit introduced with Sub-part 

1–2, ‘‘Life Limits,’’ and Sub-part 1–3, 

‘‘Demonstrated Fatigue Lives,’’ of Airbus 

A318/A319/A320/A321 ALS Part 1—Safe 

Life Airworthiness Limitation Items, 

Revision 00, dated February 28, 2006, replace 

the part at the time specified in Sub-part 1– 

2, ‘‘Life Limits,’’ and Sub-part 1–3, 

‘‘Demonstrated Fatigue Lives,’’ of Airbus 

A318/A319/A320/A321 ALS Part 1—Safe 

Life Airworthiness Limitation Items, 

Revision 00, dated February 28, 2006, or 

within 6 months after November 7, 2007 (the 

effective date of AD 2007–20–05, 

Amendment 39–15215 (72 FR 56262, October 

3, 2007)), whichever is later. Accomplishing 

the actions required by paragraph (n) of this 

AD terminates the requirements of this 

paragraph. 

(j) Retained Revision of ALS To Incorporate 

Damage-Tolerant ALIs With Revised 

Compliance Times 

This paragraph restates the requirements of 

paragraph (j) of AD 2011–14–06, Amendment 

39–16741 (76 FR 42024, July 18, 2011), with 

revised compliance times. Within 9 months 

after August 22, 2011 (the effective date of 

AD 2011–14–06): Revise the maintenance 

program by incorporating all maintenance 

requirements and associated airworthiness 

limitations specified in the Airbus A318/

A319/A320/A321 Airworthiness Limitation 

Items, Document AI/SE–M4/95A.0252/96, 

Issue 10, dated October 2009; or Issue 11, 

dated September 2010. Comply with all 

applicable maintenance requirements and 

associated airworthiness limitations included 

in Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 10, dated 

October 2009; or Issue 11, dated September 

2010; except as provided by paragraph (k) of 

this AD. Accomplishing the actions required 

by this paragraph terminates the 

requirements of paragraph (h) of this AD. 

Accomplishing the actions required by 

paragraph (n) of this AD terminates the 

requirements of this paragraph. 

(k) Retained Special Compliance Times for 

Certain Tasks 

This paragraph restates the requirements of 

paragraph (k) of AD 2011–14–06, 

Amendment 39–16741 (76 FR 42024, July 18, 

2011), with changes to table 1 to paragraph 

(k) of this AD. For new and more restrictive 

tasks introduced with Airbus A318/A319/

A320/A321 Airworthiness Limitation Items, 

Document AI/SE–M4/95A.0252/96, Issue 10, 

dated October 2009; or Issue 11, dated 

September 2010; as specified in table 1 to 

paragraph (k) of this AD: The initial 

compliance time for doing the tasks is 

specified in table 1 to paragraph (k) of this 

AD. Accomplishing the actions required by 

paragraph (n) of this AD terminates the 

requirements of this paragraph. 

TABLE 1 TO PARAGRAPH (K) OF THIS AD—COMPLIANCE TIMES FOR TASKS

Task Applicability 

(as specified in the applicability column 

of the task) 

Compliance time, whichever occurs later 

545102–01–6 .......... Group 19–1A CFM, Group 19–1B 

CFM, and Model A320-200 airplanes 

with CFM Industrial (CFM)/International Aero Engine (IAE) engines.

The threshold as defined in Airbus 

A318/A319/A320/A321 Airworthiness 

Limitation Items, Document AI/

SE-M4/95A.0252/96, Issue 10, dated 

October 2009; or Issue 11, dated 

September 2010.

Within 2,000 flight cycles or 5,500 

flight hours, after August 22, 2011 

(the effective date of AD 2011–14– 

06, Amendment 39–16741 (76 FR 

42024, July 18, 2011)), whichever 

occurs first. 

545102–01–7 .......... Model A320–100 series airplanes ....... The threshold as defined in Airbus 

A318/A319/A320/A321 Airworthiness 

Limitation Items, Document AI/

SE-M4/95A.0252/96, Issue 10, dated 

October 2009; or Issue 11, dated 

September 2010.

Within 2,000 flight cycles or 2,000 

flight hours, after August 22, 2011 

(the effective date of AD 2011–14– 

06, Amendment 39–16741 (76 FR 

42024, July 18, 2011)), whichever 

occurs first. 

572050–01–1 or alternative task 

572050-02–1.

Group 19-1A and Group 19–1B airplanes.At the time of the next due accomplishment of any one of the tasks 

572004, 572020, or 572053 as currently described in the Airbus A318/

A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/

95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 

2006; or Issue 09, dated November 

2006.

Within 6 months after August 22, 2011 

(the effective date of AD 2011–14– 

06, Amendment 39–16741 (76 FR 

42024, July 18, 2011)). 

572050–01–4 or alternative task 

572050-02–4.

Model A320–200 series airplanes ....... At the time of the next due accomplishment of any one of the tasks 

572004, 572020, or 572053 as currently described in the Airbus A318/

A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/

95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 

2006; or Issue 09, dated November 

2006.

Within 6 months after August 22, 2011 

(the effective date of AD 2011–14– 

06, Amendment 39–16741 (76 FR 

42024, July 18, 2011)). 


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Federal Register / Vol. 80, No. 16 / Monday, January 26, 2015 / Rules and Regulations 3875 

TABLE 1 TO PARAGRAPH (K) OF THIS AD—COMPLIANCE TIMES FOR TASKS—Continued 

Task 

572050–01–5 or alternative task 

572050-02–5.

Group 21-1A airplanes ......................... At the time of the next due accomplishment of any one of the tasks 

572004, 572020, or 572053 as currently described in the Airbus A318/

A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/

95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 

2006; or Issue 09, dated November 

2006.

Within 6 months after August 22, 2011 

(the effective date of AD 2011–14– 

06, Amendment 39–16741 (76 FR 

42024, July 18, 2011)). 

572050–01–7 or alternative task 

572050-02–7.

Model A320–100 series airplanes ....... At the time of the next due accomplishment of any one of the tasks 

572004, 572020, or 572053 as currently described in the Airbus A318/

A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/

95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 

2006; or Issue 09, dated November 

2006.

Within 6 months after August 22, 2011 

(the effective date of AD 2011–14– 

06, Amendment 39–16741 (76 FR 

42024, July 18, 2011)). 

534132–01–1 .......... Model A320 PRE 30748 airplanes ...... The threshold/interval as defined in 

Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 

10, dated October 2009; or Issue 

11, dated September 2010.

Within 100 days after August 22, 2011 

(the effective date of AD 2011–14– 

06, Amendment 39–16741 (76 FR 

42024, July 18, 2011)), without exceeding the previous threshold/interval as defined in Airbus A318/A319/

A320/A321 Airworthiness Limitation 

Items, Document AI/SE-M4/

95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 

2006; or Issue 09, dated November 

2006. 

531118–01–1 .......... Model A318 (except (A318–121 and 

-122), Group 19–1A, Group 19–1B, 

and Model A320 and A321 series 

airplanes.

The threshold/interval as defined in 

Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 

10, dated October 2009; or Issue 

11, dated September 2010.

Within 100 days after August 22, 2011 

(the effective date of AD 2011–14– 

06, Amendment 39–16741 (76 FR 

42024, July 18, 2011)), without exceeding the previous threshold/interval as defined in Airbus A318/A319/

A320/A321 Airworthiness Limitation 

Items, Document AI/SE-M4/

95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 

2006; or Issue 09, dated November 

2006. 

531118–01–1 .......... Model A318–121 and -122 airplanes ... The threshold/interval as defined in 

Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 

10, dated October 2009; or Issue 

11, dated September 2010.

Within 100 days after August 22, 2011 

(the effective date of AD 2011–14– 

06, Amendment 39–16741 (76 FR 

42024, July 18, 2011)). 

Note 1 to table 1 to paragraph (k) of this 

AD: ALI Task 572050 refers to the outer wing 

dry bay and is comprised of extracts from 

three ALI Tasks 572004, 572020, and 572053. 

The threshold of ALI Task 572050 for the 

whole dry bay area is that of the lowest 

threshold of the source ALI tasks, i.e., that of 

ALI Task 572053. 

(l) Retained Limitation: No Alternative Life 

Limits, Inspections, or Inspection Intervals 

After Accomplishment of the Actions 

Specified in Paragraphs (g) and (h) of This 

AD 

This paragraph restates the requirements of 

paragraph (l) of AD 2011–14–06, Amendment 

39–16741 (76 FR 42024, July 18, 2011). After 

the actions specified in paragraphs (g) and (h) 

of this AD have been accomplished, no 

alternative life limits, inspections, or 

inspection intervals may be used, except as 

provided by paragraphs (i) and (m) of this 

AD, and except as required by paragraphs (j) 

and (n) of this AD. 

(m) Retained Limitation: No Alternative Life 

Limits, Inspections, or Inspection Intervals 

After Accomplishment of the Actions 

Specified in Paragraph (j) of This AD 

This paragraph restates the requirements of 

paragraph (m) of AD 2011–14–06, 

Amendment 39–16741 (76 FR 42024, July 18, 

2011). After the actions specified in 

paragraph (j) of this AD have been 

accomplished, no alternative life limits, 

inspections, or inspection intervals may be 

used, except as required by paragraph (n) of 

this AD. 

(n) New Maintenance or Inspection Program 

Revision 

Within 30 days after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to incorporate the 

ALIs specified in paragraphs (n)(1), (n)(2), 

and (n)(3) of this AD. The initial compliance 

time for accomplishing the actions is at the 

applicable time specified in the ALIs 

specified in paragraphs (n)(1), (n)(2), and 

(n)(3) of this AD; or within 4 months after the 

effective date of this AD; whichever occurs 


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3876 Federal Register / Vol. 80, No. 16 / Monday, January 26, 2015 / Rules and Regulations 

later. Accomplishing these actions terminates 

the requirements of paragraphs (g), (h), (i), (j), 

and (k) of this AD. 

(1) Airbus A318/A319/A320/A321 ALS 

Part 1—Safe Life Airworthiness Limitation 

Items, Revision 02, dated May 13, 2011. 

(2) Airbus A318/A319/A320/A321 ALS 

Part 2—Damage-Tolerant Airworthiness 

Limitation Items (DT ALI), Revision 02, dated 

May 28, 2013. 

(3) Airbus A318/A319/A320/A321 ALS 

Part 4—Ageing Systems Maintenance, dated 

January 8, 2008. 

(o) New Limitation: No Alternative Actions, 

Intervals, and/or Critical Design 

Configuration Control Limitations (CDCCLs) 

After accomplishing the revision required 

by paragraph (n) of this AD, no alternative 

actions (e.g., inspections), intervals, and/or 

CDCCLs may be used unless the actions, 

intervals, and/or CDCCLs are approved as an 

alternative method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (p)(1) of this AD. 

(p) 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 

2011–14–06, Amendment 39–16741 (76 FR 

42024, July 18, 2011), are approved as 

AMOCs for the corresponding actions 

specified in 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. 

(q) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directives 2012–0008, dated January 16, 

2012; and 2013–0147, dated July 16, 2013; for 

related information. You may examine the 

MCAI in the AD docket on the Internet at 

http://www.regulations.gov/#!document

Detail;D=FAA-2013-0692-0002. 

(r) 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) Airbus A318/A319/A320/A321 ALS Part 

1—Safe Life Airworthiness Limitation Items, 

Revision 02, dated May 13, 2011. The 

revision level of this document is identified 

on only the title page and in the Record of 

Revisions. The revision date is not identified 

on the title page of this document. 

(ii) Airbus A318/A319/A320/A321 ALS 

Part 2—Damage-Tolerant Airworthiness 

Limitation Items (DT ALI), Revision 02, dated 

May 28, 2013. The revision date of this 

document is not identified on the title page 

of this document. 

(iii) Airbus A318/A319/A320/A321 ALS 

Part 4—Ageing Systems Maintenance, dated 

January 8, 2008. The revision date of this 

document is not identified on the title page 

of this document. 

(3) The following service information was 

approved for IBR on August 22, 2011 (76 FR 

42024, July 18, 2011). 

(i) Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 10, dated 

October 2009. The revision level of this 

document is identified on only the title page 

and in the Record of Revisions. 

(ii) Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 11, dated 

September 2010. The revision level of this 

document is identified on only the title page 

and in the Record of Revisions. 

(4) The following service information was 

approved for IBR on November 7, 2007 (72 

FR 56262, October 3, 2007). 

(i) Airbus A318/A319/A320/A321 ALS Part 

1—Safe Life Airworthiness Limitation Items, 

Revision 00, dated February 28, 2006. 

(ii) Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 7, dated 

December 2005 (approved by the European 

Aviation Safety Agency (EASA) on February 

7, 2006). 

Note 2 to paragraph (r)(4)(ii) of this AD: 

This document contains the following errors: 

The Summary of Changes is comprised of 11 

pages, which are all identified as Page 2— 

LEP of Section LEP instead of Page 1—SOC 

[through] Page 11—SOC of Section SOC; the 

List of Effective Pages only refers to Page 1— 

SOC for the Summary of Changes. The List 

of Effective Pages is comprised of two pages, 

and both of those pages are identified as Page 

2—LEP. The first page of Section 2 is 

identified as Page 6 of Section 1 and is not 

referred to in the List of Effective Pages. 

(iii) Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 08, dated 

March 2006 (approved by the EASA on 

January 4, 2007). 

(iv) Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 09, dated 

November 2006 (approved by the EASA on 

May 21, 2007). 

(5) 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. 

(6) 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. 

(7) 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 

December 23, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–01257 Filed 1–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No. 30996; Amdt. No. 3624] 

Standard Instrument Approach 

Procedures, and Takeoff Minimums 

and Obstacle Departure Procedures; 

Miscellaneous Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This rule amends, suspends, 

or removes Standard Instrument 

Approach Procedures (SIAPs) and 

associated Takeoff Minimums and 

Obstacle Departure Procedures for 

operations at certain airports. These 

regulatory actions are needed because of 

the adoption of new or revised criteria, 

or because of changes occurring in the 

National Airspace System, such as the 

commissioning of new navigational 

facilities, adding new obstacles, or 

changing air traffic requirements. These 

changes are designed to provide for the 

safe and efficient use of the navigable 

airspace and to promote safe flight 

operations under instrument flight rules 

at the affected airports. 

DATES: This rule is effective January 26, 

2015. The compliance date for each 


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