Federal Register / Vol. 80, No. 148 / Monday, August 3, 2015 / Rules and Regulations 45857 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0652; Directorate 

Identifier 2014–NM–076–AD; Amendment 

39–18223; AD 2015–15–13] 

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 certain 

Airbus Model A319 series airplanes; 

Model A320–211, –212, –214, –231, 

–232, and –233 airplanes; and Model 

A321 series airplanes. This AD was 

prompted by reports of cracks that could 

be initiated at the waste water service 

panel area and the potable water service 

panel area. This AD requires 

modification of the potable water 

service panel and waste water service 

panel, including doing applicable 

related investigative and corrective 

actions. We are issuing this AD to 

prevent any cracking at the waste water 

service panel area and the potable water 

service panel area, which could affect 

the structural integrity of the airplane. 

DATES: This AD becomes effective 

September 8, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 8, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0652 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. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2014–0652. 

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 certain Airbus Model A319 

series airplanes; Model A320–211, –212, 

–214, –231, –232, and –233 airplanes; 

and Model A321 series airplanes. The 

NPRM published in the Federal 

Register on October 1, 2014 (79 FR 

59160). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2014–0081, 

dated March 31, 2014 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Model A319 series 

airplanes; Model A320–211, –212, –214, 

–231, –232, and –233 airplanes; and 

Model A321 series airplanes. The MCAI 

states: 

During the full scale fatigue test on A320– 

200, it has been noticed that, due to fatigue, 

cracks could be initiated at the waste water 

service panel area and the potable water 

service panel area. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

Prompted by these findings, ALS 

[airworthiness limitations section] Part 2 

tasks have been introduced for the affected 

A320 family aeroplanes. Since those actions 

were taken, Airbus developed production 

mod 160055 and mod 160056 to embody 

reinforcements (cold working on certain rivet 

rows) of the potable water and waste water 

service panels, and published associated 

Airbus Service Bulletin (SB) A320–53–1272 

(retrofit mod 153074) and SB A320–53–1267 

(retrofit mod 153073) for in-service 

embodiment. 

Following complementary Design Office 

studies, it appears that the Sharklet 

installations on certain aeroplanes have a 

significant impact on the aeroplane structure 

(particularly, A319 and A320 post-mod 

160001, and A321 post-mod 160021), leading 

to different compliance times, depending on 

aeroplane configuration. 

For the reasons described above, this 

[EASA] AD requires reinforcement of the 

potable water and waste water service panels. 

Accomplishment of these modifications 

cancels the need for the related ALS Part 2 

Tasks. 

The modification includes doing 

applicable related investigative and 

corrective actions. Related investigative 

actions include measuring the diameter 

of a hole of a fastener and doing a 

rotating probe inspection. Corrective 

actions include repairs. You may 

examine the MCAI in the AD docket on 

the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0652- 

0003. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 59160, 

October 1, 2014) and the FAA’s 

response to each comment. 

Request To Include Latest Service 

Information 

United Airlines (UAL) and Airbus 

requested that we revise the NPRM (79 

FR 59160, October 1, 2014) to include 

the latest service information. UAL 

explained that Airbus Service Bulletin 

A320–53–1267, Revision 02, dated May 

19, 2014, has similar modification 

requirements to those specified in 

Airbus Service Bulletin A320–53–1267, 

Revision 01, dated October 2, 2013, but 

also has updates including two new 

airplane configurations, which update 

compliance times corresponding to the 

times listed in paragraph (g)(2) of the 

NPRM. Airbus stated that Airbus 

Service Bulletin A320–53–1267, 

Revision 02, dated May 19, 2014, 

updates the effectivity and compliance 

times in the service information. 

We agree to include Airbus Service 

Bulletin A320–53–1267, Revision 02, 

dated May 19, 2014, in this AD. Airbus 

Service Bulletin A320–53–1267, 

Revision 02, dated May 19, 2014, was 

issued to provide updated compliance 

times and effectivity. Airbus Service 

Bulletin A320–53–1267, Revision 02, 

dated May 19, 2014, does not add 

additional requirements for AD 

compliance times. 

Also, we have added Airbus Service 

Bulletin A320–53–1267, Revision 01, 

dated October 2, 2013, to paragraph 

(j)(2) of this AD to offer credit for the 

corresponding actions performed before 

the effective date of this AD. 

Request To Omit Paragraph (h) of the 

NPRM (79 FR 59160, October 1, 2014) 

UAL requested that we revise the 

NPRM (79 FR 59160, October 1, 2014) 

to omit paragraph (h) of the proposed 

AD. UAL explained that Task 534126– 

01–3, of the Airworthiness Limitation 

Section (ALS) Part 2, ‘‘Damage-Tolerant 

Airworthiness Limitation Items’’ of the 

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45858 Federal Register / Vol. 80, No. 148 / Monday, August 3, 2015 / Rules and Regulations 

Airbus A319/A320/A321 Airworthiness 

Limitation Items is addressed separately 

in other rulemaking, NPRM Docket No. 

FAA–2013–0692, Directorate Identifier 

2012–NM–024–AD (78 FR 49213, 

August 13, 2013), and that NPRM 

contains the instructions for the 

corrective actions in paragraph (o)(2) of 

that NPRM. UAL concluded that 

paragraph (h) of the NPRM (79 FR 

59160, October 1, 2014), which specifies 

corrective actions for Task 534126–01– 

3, might cause confusion. UAL also 

suggested that, as an alternative to 

omitting paragraph (h) of NPRM (79 FR 

59160, October 1, 2014), paragraph (h) 

of the NPRM could be revised so that 

the Task 534126–01–3 requirement 

refers to the other rulemaking, NPRM 

Docket No. FAA–2013–0692, Directorate 

Identifier 2012–NM–024–AD (78 FR 

49213, August 13, 2013), which has 

since been issued as AD 2014–23–15, 

Amendment 39–18031 (80 FR 3871, 

January 26, 2015). (AD 2014–23–15 has 

since been superseded by AD 2015–05– 

02, Amendment 39–18112 (80 FR 

15152, March 23, 2015)). 

We disagree to omit or revise 

paragraph (h) of this AD. Paragraph (h) 

of this AD is not a duplicated action. 

Paragraph (h) of this AD specifies that 

for Airbus A320 airplanes having premodification 160001, that have 

exceeded 46,400 flight cycles or 92,800 

flight hours, whichever occurred first 

since the airplane’s first flight, operators 

must repair cracks found during 

accomplishment of Task 534126–01–3, 

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. This 

specific condition and corrective action 

is not included in paragraph (p)(2) of 

AD 2015–05–02, Amendment 39–18112 

(80 FR 15152, March 23, 2015, which 

corresponds to paragraph (o)(2) of 

NPRM Docket No. FAA–2013–0692, 

Directorate Identifier 2012–NM–024–AD 

(78 FR 49213, August 13, 2013). AD 

2015–05–02, does not mandate 

corrective actions associated with Task 

534126–01–3, of the Airworthiness 

Limitation Section (ALS) Part 2, 

‘‘Damage-Tolerant Airworthiness 

Limitation Items’’ of the Airbus A319/

A320/A321 Airworthiness Limitation 

Items, but instead mandates 

incorporation of that task into operators’ 

maintenance or inspection programs. 

We have made no changes to this AD in 

this regard. 

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 NPRM (79 FR 

59160, October 1, 2014) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 59160, 

October 1, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Airbus Service 

Bulletin A320–53–1267, Revision 02, 

dated May 19, 2014; and Airbus Service 

Bulletin A320–53–1272, Revision 02, 

dated May 19, 2014. The service 

information describes procedures for a 

modification, which includes measuring 

the diameter of a hole of a fastener and 

doing a rotating probe inspection, and 

repairs if necessary. This service 

information is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section of this AD. 

Costs of Compliance 

We estimate that this AD affects 851 

airplanes of U.S. registry. 

We also estimate that it will take 

about 25 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts will cost 

about $420 per product. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $2,165,795, or 

$2,545 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-2014-0652; 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 adding 

the following new airworthiness 

directive (AD): 

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Federal Register / Vol. 80, No. 148 / Monday, August 3, 2015 / Rules and Regulations 45859 

2015–15–13 Airbus: Amendment 39–18223. 

Docket No. FAA–2014–0652; Directorate 

Identifier 2014–NM–076–AD. 

(a) Effective Date 

This AD becomes effective September 8, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1), (c)(2), and (c)(3) of this 

AD, certificated in any category, all 

manufacturer serial numbers, except those on 

which Airbus Modification 160055 or Airbus 

Modification 160056 has been embodied in 

production. 

(1) Airbus Model A319–111, –112, –113, 

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

(2) Airbus Model A320–211, –212, –214, 

–231, –232, and –233 airplanes. 

(3) Airbus Model A321–111, –112, –131, 

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

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by reports of cracks 

that could be initiated at the waste water 

service panel area and the potable water 

service panel area. We are issuing this AD to 

prevent any cracking at the waste water 

service panel area and the potable water 

service panel area, which could affect the 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification 

(1) Within the compliance time specified 

in paragraphs (g)(1)(i), (g)(1)(ii), (g)(1)(iii), 

(g)(1)(iv), and (g)(1)(v) of this AD, as 

applicable, modify the potable water service 

panel, including doing all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1272, Revision 02, dated May 19, 2014, 

except where Airbus Service Bulletin A320– 

53–1272, Revision 02, dated May 19, 2014, 

specifies to contact Airbus, repair before 

further flight 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). Do all applicable related 

investigative and corrective actions within 

the compliance time specified in paragraphs 

(g)(1)(i), (g)(1)(ii), (g)(1)(iii), (g)(1)(iv), and 

(g)(1)(v) of this AD. 

(i) For Model A319 airplanes premodification 160001: Within 48,500 flight 

cycles or 97,000 flight hours, whichever 

occurs first since the airplane’s first flight. 

(ii) For Model A319 airplanes postmodification 160001: Within 46,000 flight 

cycles or 92,000 flight hours, whichever 

occurs first since the airplane’s first flight. 

(iii) For Model A320 airplanes premodification 160001: Within 54,200 flight 

cycles or 108,400 flight hours, whichever 

occurs first since the airplane’s first flight. 

(iv) For Model A320 airplanes postmodification 160001: Within 36,000 flight 

cycles or 72,000 flight hours, whichever 

occurs first since the airplane’s first flight. 

(v) For Model A321 airplanes: Within 

60,000 flight cycles or 120,000 flight hours, 

whichever occurs first since the airplane’s 

first flight. 

(2) Within the compliance time specified 

in paragraphs (g)(2)(i), (g)(2)(ii), (g)(2)(iii), 

(g)(2)(iv), (g)(2)(v), and (g)(2)(vi) of this AD, 

as applicable, modify the waste water service 

panel, including doing all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1267, Revision 02, dated May 19, 2014, 

except where Airbus Service Bulletin A320– 

53–1267, Revision 02, dated May 19, 2014, 

specifies to contact Airbus, repair before 

further flight using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

EASA; or Airbus’s EASA DOA. Do all 

applicable related investigative and 

corrective actions within the compliance 

time specified in paragraphs (g)(2)(i), 

(g)(2)(ii), (g)(2)(iii), (g)(2)(iv), and (g)(2)(v) of 

this AD. 

(i) For Airbus A319 airplanes premodification 160001: Within 44,400 flight 

cycles or 88,800 flight hours, whichever 

occurs first since the airplane’s first flight. 

(ii) For Airbus A319 airplanes postmodification 160001: Within 43,600 flight 

cycles or 87,200 flight hours, whichever 

occurs first since the airplane’s first flight. 

(iii) For Airbus A320 airplanes premodification 160001, within the compliance 

times specified in paragraph (g)(2)(iii)(A) or 

(g)(2)(iii)(B) of this AD, whichever occurs 

later: 

(A) Within 46,400 flight cycles or 92,800 

flight hours, whichever occurs first since the 

airplane’s first flight. 

(B) Within 2,300 flight cycles or 4,600 

flight hours, whichever occurs first since last 

accomplishment of Task No. 534126–01–3, of 

the Airworthiness Limitation Section (ALS) 

Part 2, ‘‘Damage-Tolerant Airworthiness 

Limitation Items’’ of the Airbus A319/A320/ 

A321 Airworthiness Limitation Items, 

without exceeding 48,000 flight cycles or 

96,000 flight hours, whichever occurs first 

since the airplane’s first flight. 

(iv) For Airbus A320 airplanes postmodification 160001: Within 39,200 flight 

cycles or 78,400 flight hours, whichever 

occurs first since the airplane’s first flight. 

(v) For Airbus A321 airplanes premodification 160021: Within 51,600 flight 

cycles or 103,200 flight hours, whichever 

occurs first since the airplane’s first flight. 

(vi) For Airbus A321 airplanes postmodification 160021: Within 51,200 flight 

cycles or 102,400 flight hours, whichever 

occurs first since the airplane’s first flight. 

(h) Corrective Action 

For Airbus A320 airplanes having premodification 160001, that have exceeded 

46,400 flight cycles or 92,800 flight hours, 

whichever occurred first since the airplane’s 

first flight: If any crack is found during 

accomplishment of Task No. 534126–01–3, of 

the ALS Part 2, ‘‘Damage-Tolerant 

Airworthiness Limitation Items’’ of the 

Airbus A319/A320/A321 Airworthiness 

Limitation Items, before further flight, repair 

using a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the EASA; or 

Airbus’s EASA DOA. 

(i) Terminating Action for ALS Task 

(1) Modification of an airplane as required 

by paragraph (g)(1) of this AD, terminates the 

requirement for the task in the ALS Part 2, 

‘‘Damage-Tolerant Airworthiness Limitation 

Items’’ of the Airbus A318/A319/A320/A321 

Airworthiness Limitation Items for that 

airplane, as identified in paragraphs (i)(1)(i), 

(i)(1)(ii), (i)(1)(iii), (i)(1)(iv), (i)(1)(v), and 

(i)(1)(vi) of this AD, as applicable. 

(i) For Airbus A319 airplanes premodification 160001: Task No. 534125–01–2. 

(ii) For Airbus A319 airplanes postmodification 160001: Task No. 534125–01–5. 

(iii) For Airbus A320 airplanes premodification 160001: Task No. 534125–01–3. 

(iv) For Airbus A320 airplanes postmodification 160001: Task No. 534125–01–6. 

(v) For Airbus A321 airplanes premodification 160021: Task No. 534125–01–4. 

(vi) For Airbus A321 airplanes postmodification 160021: Task No. 534125–01–7. 

(2) Modification of an airplane as required 

by paragraphs (g)(2) and (g)(3) of this AD, 

terminates the requirement for the task in the 

ALS Part 2, ‘‘Damage-Tolerant Airworthiness 

Limitation Items’’ of the Airbus A318/A319/ 

A320/A321 Airworthiness Limitation Items 

for that airplane, as identified in paragraphs 

(i)(2)(i), (i)(2)(ii), (i)(2)(iii), (i)(2)(iv), (i)(2)(v), 

and (i)(2)(vi) of this AD, as applicable. 

(i) For Airbus A319 airplanes premodification 160001: Task No. 534126–01–2. 

(ii) For Airbus A319 airplanes postmodification 160001: Task No. 534126–01–5. 

(iii) For Airbus A320 airplanes premodification 160001: Task No. 534126–01–3. 

(iv) For Airbus A320 airplanes postmodification 160001: Task No. 534126–01–6. 

(v) For Airbus A321 airplanes premodification 160021: Task No. 534126–01–4. 

(vi) For Airbus A321 airplanes postmodification 160021: Task No. 534126–01–7. 

(j) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraph (g)(1) of this 

AD, if those actions were performed before 

the effective date of this AD using Airbus 

Service Bulletin A320–53–1272, dated 

January 10, 2013; or Airbus Service Bulletin 

A320–53–1272, Revision 01, dated August 6, 

2013; which are not incorporated by 

reference in this AD. 

(2) This paragraph provides credit for the 

actions required by paragraph (g)(2) of this 

AD, if those actions were performed before 

the effective date of this AD using Airbus 

Service Bulletin A320–53–1267, dated June 

24, 2013; or Airbus Service Bulletin A320– 

53–1267, Revision 01, dated October 2, 2013; 

which are not incorporated by reference in 

this AD. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

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45860 Federal Register / Vol. 80, No. 148 / Monday, August 3, 2015 / Rules and Regulations 

(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. 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) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0081, dated 

March 31, 2014, for related information. This 

MCAI may be found in the AD docket on the 

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

#!documentDetail;D=FAA-2014-0652-0003. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (m)(3) and (m)(4) of this AD. 

(m) 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 Service Bulletin A320–53–1267, 

Revision 02, dated May 19, 2014. 

(ii) Airbus Service Bulletin A320–53–1272, 

Revision 02, dated May 19, 2014. 

(3) 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. 

(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 July 22, 

2015. 

Victor Wicklund, 

Acting Manager,Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–18564 Filed 7–31–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No. 31028; Amdt. No. 3653] 

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 establishes, amends, 

suspends, or removes Standard 

Instrument Approach Procedures 

(SIAPs) and associated Takeoff 

Minimums and Obstacle Departure 

Procedures (ODPs) 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 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 August 3, 

2015. The compliance date for each 

SIAP, associated Takeoff Minimums, 

and ODP is specified in the amendatory 

provisions. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of August 3, 

2015. 

ADDRESSES: Availability of matters 

incorporated by reference in the 

amendment is as follows: 

For Examination 

1. U.S. Department of Transportation, 

Docket Ops-M30, 1200 New Jersey 

Avenue SE., West Bldg., Ground Floor, 

Washington, DC 20590–0001. 

2. The FAA Air Traffic Organization 

Service Area in which the affected 

airport is located; 

3. The office of Aeronautical 

Navigation Products, 6500 South 

MacArthur Blvd., Oklahoma City, OK 

73169 or, 

4. 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/code_of_federal_

regulations/ibr_locations.html. 

Availability 

All SIAPs and Takeoff Minimums and 

ODPs are available online free of charge. 

Visit the National Flight Data Center at 

nfdc.faa.gov to register. Additionally, 

individual SIAP and Takeoff Minimums 

and ODP copies may be obtained from 

the FAA Air Traffic Organization 

Service Area in which the affected 

airport is located. 

FOR FURTHER INFORMATION CONTACT: 

Richard A. Dunham III, Flight Procedure 

Standards Branch (AFS–420), Flight 

Technologies and Programs Divisions, 

Flight Standards Service, Federal 

Aviation Administration, Mike 

Monroney Aeronautical Center, 6500 

South MacArthur Blvd., Oklahoma City, 

OK 73169 (Mail Address: P.O. Box 

25082, Oklahoma City, OK 73125) 

Telephone: (405) 954–4164. 

SUPPLEMENTARY INFORMATION: This rule 

amends Title 14 of the Code of Federal 

Regulations, Part 97 (14 CFR part 97), by 

establishing, amending, suspending, or 

removes SIAPS, Takeoff Minimums 

and/or ODPS. The complete regulatory 

description of each SIAP and its 

associated Takeoff Minimums or ODP 

for an identified airport is listed on FAA 

form documents which are incorporated 

by reference in this amendment under 5 

U.S.C. 552(a), 1 CFR part 51, and 14 

CFR part § 97.20. The applicable FAA 

forms are FAA Forms 8260–3, 8260–4, 

8260–5, 8260–15A, and 8260–15B when 

required by an entry on 8260–15A. 

The large number of SIAPs, Takeoff 

Minimums and ODPs, their complex 

nature, and the need for a special format 

make publication in the Federal 

Register expensive and impractical. 

Further, airmen do not use the 

regulatory text of the SIAPs, Takeoff 

Minimums or ODPs, but instead refer to 

their graphic depiction on charts 

printed by publishers of aeronautical 

materials. Thus, the advantages of 

incorporation by reference are realized 

and publication of the complete 

description of each SIAP, Takeoff 

Minimums and ODP listed on FAA form 

documents is unnecessary. This 

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