3868 Federal Register / Vol. 80, No. 16 / Monday, January 26, 2015 / Rules and Regulations 

Airworthiness Limitations Section ALS Part 

3—Certification Maintenance Requirements, 

Revision 04, dated August 27, 2013, except 

as provided by paragraph (k)(2) of this AD, 

accomplish all applicable maintenance tasks. 

Accomplishing these actions terminates the 

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

of this AD. 

(2) Where paragraph 3 of the ‘‘Record of 

Revisions’’ section of Airbus A330 

Airworthiness Limitations Section ALS Part 

3—Certification Maintenance Requirements, 

Revision 04, dated August 27, 2013, specifies 

accomplishing the actions ‘‘from 27 August 

2013,’’ this AD requires compliance within 

the specified compliance time after the 

effective date of this AD. 

(l) No Alternative Inspections or Intervals 

After accomplishing the action required by 

paragraph (k)(1) of this AD, no alternative 

inspections or inspection intervals may be 

used, other than those specified in Airbus 

A330 Airworthiness Limitations Section ALS 

Part 3—Certification Maintenance 

Requirements, Revision 04, dated August 27, 

2013, except as provided by paragraph (k)(2) 

of this AD, unless the inspections or intervals 

are approved as an AMOC in accordance 

with the procedures specified in paragraph 

(m) of this AD. 

(m) 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425)227–1138; 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: 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. 

(n) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0245, dated 

October 2, 2013, for related information. You 

may examine the MCAI in the AD docket on 

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

#!documentDetail;D=FAA-2014-0587-0002. 

(o) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on March 2, 2015. 

(i) Airbus A330 Airworthiness Limitations 

Section ALS Part 3—Certification 

Maintenance Requirements, Revision 04, 

dated August 27, 2013. 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) Reserved. 

(4) The following service information was 

approved for IBR on August 1, 2011 (76 FR 

37255, June 27, 2011). 

(i) Airbus A330 ALS Part 3—Certification 

Maintenance Requirements, Revision 03, 

dated July 29, 2010. 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) Reserved. 

(5) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330@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 19, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–30918 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–2014–0770; Directorate 

Identifier 2014–CE–024–AD; Amendment 

39–18064; AD 2015–01–03] 

RIN 2120–AA64 

Airworthiness Directives; PILATUS 

Aircraft Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Pilatus 

Aircraft Ltd. Model PC–7 airplanes. This 

AD results from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as possible cracking from 

stress corrosion on various parts of the 

airplane structure made of aluminum 

alloy AA2024–T351. We are issuing this 

AD to require actions to address the 

unsafe condition on these products. 

DATES: This AD is effective March 2, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of March 2, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0770; or in person at Document 

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 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.pilatusaircraft.com. You may review this 

referenced 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. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 16 / Monday, January 26, 2015 / Rules and Regulations 3869 

Missouri 64106; telephone: (816) 329– 

4059; fax: (816) 329–4090; email: 

doug.rudolph@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to add an AD that would apply 

to Pilatus Aircraft Ltd. Model PC–7 

airplanes. The NPRM was published in 

the Federal Register on October 7, 2014 

(79 FR 60389). The NPRM proposed to 

correct an unsafe condition for the 

specified products and was based on 

mandatory continuing airworthiness 

information (MCAI) originated by an 

aviation authority of another country. 

Since the NPRM was issued, the MCAI 

was revised based on revised service 

information. The NPRM we issued 

already referenced the revised service 

information. The revised MCAI states: 

This Airworthiness Directive (AD) is 

prompted due to the possibility of cracks in 

some critical parts. It is possible that stress 

corrosion cracks may occur on various parts 

of the aircraft structure initially made of 

aluminium alloy AA2024–T351 which is 

susceptible to Stress Corrosion Cracking 

(SCC). Later in production, the material 

specification was changed to aluminium 

alloy AA2124–T851 to decrease the risk of 

stress corrosion. The Part Number (P/N) of 

the affected structural parts are not always 

changed when the new material was 

introduced. 

Such a condition, if left uncorrected, could 

lead to failure of critical parts on the aircraft 

structure and will prejudice the structural 

integrity of the aircraft. 

To address this potential unsafe condition 

Pilatus Aircraft Ltd. issued PILATUS PC–7 

Service Bulletin (SB) No. 51–001 and FOCA 

Switzerland issued AD HB–2014–001 to 

require a one-time check to identify the 

material specification and inspect the 

affected areas of the airframe that are made 

of aluminium alloy AA2024–T351. Any 

structural parts of the aircraft structure found 

to be cracked must be reported to Pilatus 

prior to further flight. 

In the meantime Pilatus Aircraft Ltd. 

issued PILATUS PC–7 SB No. 51–001 

Revision 1 to correct paragraphs (§ ) 1.C.(3) 

and § 1.D. to update Part Number (P/N) 

references of the AA2024–T351 material and 

to add a clarification that an inspection can 

be carried out if an elevator center controlrod P/N 116.35.07.345 is installed. It also 

clarifies which center tank support bracket is 

covered by SB 51–001. 

For the reasons described above, this AD 

retains the requirements of FOCA 

Switzerland AD HB–2014–001, which is 

revised and clarifies that an inspection of the 

elevator center control-rod can be carried out 

if P/N 116.35.07.345 is installed and corrects 

some paragraphs and clarifies the 

information which center tank support 

bracket is affected. 

The MCAI also requires replacement of 

the elevator center control-rod, P/N 

116.35.07.271 or 116.35.07.345; and 

shackle, P/N 116.35.07.183. The MCAI 

can be found in the AD docket on the 

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

#!docketBrowser;rpp=25;

po=0;dct=PR%252BSR;D=FAA-2014- 

0770. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the proposal and the FAA’s 

response to the comment. 

Request Revision of Paragraph (f)(3) 

Tom Langen of Pilatus commented 

that the NPRM (79 FR 60389, October 7, 

2014) referred to MCAI AD HB–2014– 

001, dated July 25, 2014. Since issuance 

of the NPRM, the MCAI was revised to 

AD HB–2014–001R1, dated October 22, 

2014. The revised MCAI clarified P/N 

116.35.07.271 needed to be replaced 

where the other P/N 116.35.07.345 

should be inspected and not 

automatically replaced. Tom Langen 

requested we revise paragraph (f)(3) of 

the AD to read like the revised MCAI. 

We agree. We revised this AD as 

requested. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change 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 

60389, October 7, 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 60389, 

October 7, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of the AD. 

Relevant Service Information 

Pilatus Aircraft Ltd. has issued Pilatus 

PC–7 Service Bulletin No: 51–001, 

Revision No. 1, dated August 26, 2014. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. The service bulletin describes 

procedures for inspecting for stress 

corrosion and replacing various parts of 

the airplane structure made of 

aluminum alloy AA2024–T351. You can 

find this service information on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2014–0770. 

Costs of Compliance 

We estimate that this AD will affect 

10 products of U.S. registry. We also 

estimate that it would take about 30 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts would cost about $4,700 

per product. 

Based on these figures, we estimate 

the cost of the AD on U.S. operators to 

be $72,500, or $7,250 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 14 work-hours and require parts 

costing $10,000, for a cost of $11,190 

per product. We have no way of 

determining the number of products 

that may need these actions. 

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 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 


tkelley on DSK3SPTVN1PROD with RULES
3870 Federal Register / Vol. 80, No. 16 / Monday, January 26, 2015 / Rules and Regulations 

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 by searching for 

and locating Docket No. FAA–2014– 

0770; 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 the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone (800) 647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

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 AD: 

2015–01–03 Pilatus Aircraft Ltd: 

Amendment 39–18064; Docket No. 

FAA–2014–0770; Directorate Identifier 

2014–CE–024–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective March 2, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Pilatus Aircraft Ltd. 

Model PC–7 airplanes, manufacturer serial 

numbers (MSN) 101 through MSN 618, 

certificated in any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 51: Standard Practices/

Structures. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as possible 

cracking from stress corrosion on various 

parts of the airplane structure made of 

aluminum alloy AA2024–T351. We are 

issuing this AD to detect and correct stress 

corrosion cracks that may occur on various 

parts of the airplane structure initially made 

of aluminum alloy AA2024–T351, which is 

susceptible to stress corrosion cracking 

(SCC). Such a condition, if left uncorrected, 

could lead to failure of critical parts on the 

airplane structure and weaken the structural 

integrity of the airplane. 

(f) Actions and Compliance 

Unless already done, within the next 12 

months after March 2, 2015 (the effective 

date of this AD), perform a one-time 

conductivity test of items 6 through 9 and 11 

through 13 as listed in paragraph 1.A.(2) of 

Pilatus PC–7 Service Bulletin No: 51–001, 

Revision No. 1, dated August 26, 2014, to 

check the material of the parts—determine 

whether they are made of aluminum alloy 

AA2124–T851 or aluminum alloy AA2024– 

T351. Do not install any item unless it has 

been inspected following the applicable 

paragraph of Pilatus PC–7 Service Bulletin 

No: 51–001, Revision No. 1, dated August 26, 

2014. 

(1) For airplanes with any parts made of 

aluminum alloy AA2124–T851: Within 12 

months after March 2, 2015 (the effective 

date of this AD), make an entry in the 

airplane logbook as required by paragraph 

3.D.(3) of Pilatus PC–7 Service Bulletin No: 

51–001, Revision No. 1, dated August 26, 

2014. The only other actions of this AD that 

apply to airplanes with all parts made of 

aluminum alloy AA2124–T851 are the 

actions in paragraphs (f)(3), (f)(4), and (f)(5) 

of this AD. 

(2) For airplanes with any parts made of 

aluminum alloy AA2024–T351: Within 12 

months after March 2, 2015 (the effective 

date of this AD), do the actions in paragraphs 

(f)(2)(i) through (f)(2)(iii) as applicable, 

including all subparagraphs: 

(i) For items 7 through 9 and 11 through 

13 as listed in paragraph 1.A.(2) of Pilatus 

PC–7 Service Bulletin No: 51–001, Revision 

No. 1, dated August 26, 2014, within 12 

months after March 2, 2015 (the effective 

date of this AD), do a one-time inspection for 

cracks. If any cracks are found as a result of 

the inspection, before further flight, you must 

contact Pilatus Aircraft Ltd. to obtain FAAapproved repair instructions approved 

specifically for compliance with this AD and 

incorporate those instructions. Use the 

contact information found in paragraph (h) of 

this AD. 

(ii) For item 6 as listed in paragraph 1.A.(2) 

of Pilatus PC–7 Service Bulletin No: 51–001, 

Revision No. 1, dated August 26, 2014, 

within 12 months after March 2, 2015 (the 

effective date of this AD), replace with a part 

made of aluminum alloy AA2124–T851. 

(iii) For Items 1, 2, 4, 5, and 10 as listed 

in paragraph 1.A.(2) of Pilatus PC–7 Service 

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

August 26, 2014, within 12 months after 

March 2, 2015 (the effective date of this AD), 

do the following actions in paragraphs 

(f)(2)(iii)(A) and (f)(2)(iii)(B), as applicable. 

(A) For items 1, 2, 4, and 10 as listed in 

paragraph 1.A.(2) of Pilatus PC–7 Service 

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

August 26, 2014, do a one-time inspection for 

cracks. If any cracks are found, before further 

flight, you must contact Pilatus Aircraft Ltd. 

to obtain FAA-approved repair instructions 

approved specifically for compliance with 

this AD and incorporate those instructions. 

Use the contact information found in 

paragraph (i)(3) of this AD. 

(B) For item 5 as listed in paragraph 1.A.(2) 

of Pilatus PC–7 Service Bulletin No: 51–001, 

Revision No. 1, dated August 26, 2014, 

replace with a part made of aluminum alloy 

AA2124–T851. 

(3) For all airplanes: For item 3 as listed 

in paragraph 1.A.(2) of Pilatus PC–7 Service 

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

August 26, 2014, within 12 months after 

March 2, 2015 (the effective date of this AD), 

replace elevator center control-rods with 

P/N 116.35.07.271 (item 3 as listed in 

paragraph 1.A.(2) of Pilatus PC–7 Service 

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

August 26, 2014), because the inspection for 

cracks on this type of control-rods is difficult. 

If elevator center control-rods P/N 

116.35.07.345 (Item 3 as listed in paragraph 

1.A.(2) of Pilatus PC–7 Service Bulletin No: 

51–001, Revision No. 1, dated August 26, 

2014), are installed, these type of control rods 

will be inspected. 

(4) For all airplanes: As of 12 months after 

March 2, 2015 (the effective date of this AD), 

do not install the parts listed in items 1 and 

2, 4, and 7 through 13 of paragraph 1.A.(2) 

of Pilatus PC–7 Service Bulletin No: 51–001, 

Revision No. 1, dated August 26, 2014, that 

are made of aluminum alloy AA2024–T351 

unless they have been inspected and found 

free of cracks. 

(5) For all airplanes: As of 12 months after 

March 2, 2015 (the effective date of this AD), 

do not install the parts listed in items 3, 5, 

and 6 of paragraph 1.A.(2) of Pilatus PC–7 

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

dated August 26, 2014, that are made of 

aluminum alloy AA2024–T351. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4059; fax: (816) 329– 

4090; email: doug.rudolph@faa.gov. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, a federal 


tkelley on DSK3SPTVN1PROD with RULES
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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