51966 Federal Register / Vol. 80, No. 166 / Thursday, August 27, 2015 / Proposed Rules 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 proposed regulation: 

(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 to the extent that it justifies 

making a regulatory distinction, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

General Electric Company: Docket No. FAA– 

2015–2984; Directorate Identifier 2015– 

NE–21–AD. 

(a) Comments Due Date 

We must receive comments by October 26, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all General Electric 

Company (GE) GEnx–1B54, –1B58, –1B64, 

–1B67, and –1B70 turbofan engines with 

high-pressure turbine (HPT) rotor stage 1 

blade, part number 2305M26P06, installed. 

(d) Unsafe Condition 

This AD was prompted by reports of two 

in-flight shutdowns caused by HPT rotor 

stage 1 blade failure. We are issuing this AD 

to prevent failure of the HPT rotor stage 1 

blades, which could lead to failure of one or 

more engines, loss of thrust control, and 

damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) After the effective date of this AD, 

perform an initial borescope inspection (BSI) 

of the convex surface of the HPT rotor stage 

1 blades for axial cracks from the platform to 

30% span, within 1,000 blade cycles since 

new or 25 cycles in service, whichever comes 

later, and disposition as follows: 

(i) If any axial crack with a length greater 

than or equal to 0.3 inch is found, or if any 

axial crack of any length turning in a radial 

direction is found, or if more than one axial 

crack of any length is found, remove the 

cracked blade before further flight. 

(ii) If an axial crack is found with a length 

greater than or equal to 0.2 inch and less than 

0.3 inch, remove the cracked blade within 10 

blade cycles in service. 

(iii) If an axial crack is found with a length 

greater than or equal to 0.1 inch and less than 

0.2 inch, inspect the cracked blade within 50 

blade cycles since last inspection (CSLI). 

(iv) If an axial crack is found with a length 

less than 0.1 inch, inspect the cracked blade 

within 100 blade CSLI. 

(v) If no cracks were found, perform a BSI 

of the blades within 125 blade CSLI. 

(2) Thereafter, perform a repetitive BSI of 

the convex surface of the HPT rotor stage 1 

blades for axial cracks from the platform to 

30% span within 125 blade CSLI and 

disposition as specified in (e)(1)(i) through 

(e)(1)(v), or remove the blades from service. 

(f) Definition 

For the purpose of this AD, a ‘‘blade cycle’’ 

is defined as the number of engine cycles that 

a set of rotor blades has accrued, regardless 

of the engine(s) in which they have operated. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs to this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. You may email your 

request to: ANE-AD-AMOC@faa.gov. 

(h) Related Information 

(1) For more information about this AD, 

contact Christopher McGuire, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7120; fax: 781–238– 

7199; email: chris.mcguire@faa.gov. 

(2) GE GEnx-1B Service Bulletin No. 72– 

0267 R00, dated April 10, 2015 can be 

obtained from GE using the contact 

information in paragraph (h)(3) of this 

proposed AD. 

(3) For service information identified in 

this proposed AD, contact General Electric 

Company, GE Aviation, Room 285, 1 

Neumann Way, Cincinnati, OH 45215; 

phone: 513–552–3272; email: 

aviation.fleetsupport@ge.com. 

(4) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

August 21, 2015. 

Colleen M. D’Alessandro, 

Directorate Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–21120 Filed 8–26–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3620; Directorate 

Identifier 2015–CE–029–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pacific 

Aerospace Limited Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Pacific Aerospace Limited Model 750XL 

airplanes that would supersede AD 

2014–20–13. This proposed AD results 

from 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 fatigue cracks on the fin 

forward pickup plates, which could 

cause it to fail. We are issuing this 

proposed AD to require actions to 

address the unsafe condition on these 

products. 

DATES: We must receive comments on 

this proposed AD by October 13, 2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 


rmajette on DSK2VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 166 / Thursday, August 27, 2015 / Proposed Rules 51967 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this proposed AD, contact Pacific 

Aerospace Limited, Airport Road, 

Hamilton, Private Bag 3027, Hamilton 

3240, New Zealand, phone: +64 7 843 

6144; fax: +64 7 843 6134; email: 

pacific@aerospace.co.nz; Internet: 

www.aerospace.co.nz. You may review 

copies of the 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3620; 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 proposed AD, 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. 

FOR FURTHER INFORMATION CONTACT: Karl 

Schletzbaum, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4123; fax: (816) 

329–4090; email: karl.schletzbaum@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–3620; Directorate Identifier 

2015–CE–029–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

regulations.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On September 26, 2014, we issued AD 

2014–20–13, Amendment 39–17986 (79 

FR 60329, October 7, 2014). That AD 

required actions intended to address an 

unsafe condition on all Pacific 

Aerospace Limited Model 750XL 

airplanes and was based on mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country. 

Since we issued AD 2014–20–13, 

Amendment 39–17986 (79 FR 60329, 

October 7, 2014), Pacific Aerospace 

Limited has revised the related service 

information and developed a 

terminating action for the repetitive 

inspections. 

The Civil Aviation Authority (CAA), 

which is the aviation authority for New 

Zealand, has issued AD DCA/750XL/

18A, dated August 4, 2015 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

DCA/750XL/18A revised to add note 2 and 

introduce minor editorial changes. This AD 

supersedes DCA/750XL/18 and DCA/750XL/ 

16A to introduce the requirements in Pacific 

Aerospace Limited Mandatory Service 

Bulletin (MSB) PACSB/XL/068 issue 5, dated 

29 June 2015. The revised MSB introduces a 

life limit for fin forward pickup P/N 11– 

10281–1 and reduces the torque setting for 

the fin forward pickup bolt to alleviate some 

of the loads applied to the pickup. The MSB 

also introduces a replacement fin forward 

pickup P/N 11–03375–1 which is not life 

limited. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–3620. 

Related Service Information Under 1 

CFR part 51 

Pacific Aerospace Limited has issued 

Mandatory Service Bulletin PACSB/XL/ 

068, Issue 5, dated June 29, 2015. This 

service bulletin reduces the torque 

setting for the fin forward pickup bolt 

and introduces a new, improved 

replacement fin forward pickup plate, 

part number P/N 11–0375–1, to replace 

P/N 11–10281–1. 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 NPRM. 

FAA’s Determination and Requirements 

of the Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 18 products of U.S. registry. 

We also estimate that it would take 

about 22 work-hours per product to 

comply with all the requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Required parts 

would cost about $1,692 per product. 

Based on these figures, we estimate 

the cost of the proposed AD on U.S. 

operators to be $64,116, or $3,562 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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 proposed regulation: 

(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 


rmajette on DSK2VPTVN1PROD with PROPOSALS
51968 Federal Register / Vol. 80, No. 166 / Thursday, August 27, 2015 / Proposed Rules 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 Amendment 39–17986 (79 FR 

60329, October 7, 2014), and adding the 

following new AD: 

Pacific Aerospace Limited: Docket No. FAA– 

2015–3620; Directorate Identifier 2015– 

CE–029–AD. 

(a) Comments Due Date 

We must receive comments by October 13, 

2015. 

(b) Affected ADs 

This AD supersedes AD 2014–20–13, 

Amendment 39–17986 (79 FR 60329, October 

7, 2014). 

(c) Applicability 

This AD applies to Pacific Aerospace 

Limited Model 750XL airplanes, all serial 

numbers through XL–193, XL–195, and XL– 

197, certificated in any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 53: Fuselage. 

(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 fatigue 

cracks on the fin forward pickup plates. We 

are issuing this AD to detect and correct 

cracked fin forward pickup plates to prevent 

failure of the fin forward pickup plates, 

which could result in reduced control. 

(f) Actions and Compliance 

Unless already done, do the actions in 

paragraphs (f)(1) through (f)(4) of this AD: 

(1) Within the next 150 hours time-inservice (TIS) after the effective date of this 

AD, reduce the fin forward pickup bolt 

torque following the procedures in section 

1.D., paragraphs A. 1) and A. 2) of the 

PLANNING INFORMATION in Pacific 

Aerospace Limited Mandatory Service 

Bulletin PACSB/XL/068, Issue 5, dated June 

29, 2015. 

(2) At or before reaching 2,000 hours total 

time-in-service (TTIS) or within the next 150 

hours TIS after the effective date of this AD, 

whichever occurs later, and repetitively 

thereafter at intervals not to exceed 600 hours 

TIS or 12 months, whichever occurs first, do 

a detailed visual inspection and liquid 

penetrant inspection of the fin forward 

pickup plates for any evidence of cracking. 

Do the inspections following the procedures 

in sections 2.A. and 2.B. of the 

ACCOMPLISHMENT INSTRUCTIONS in 

Pacific Aerospace Limited Mandatory Service 

Bulletin PACSB/XL/068, Issue 5, dated June 

29, 2015. 

(3) If cracks are found during any 

inspection required in paragraph (f)(2) of this 

AD, before further flight, replace the fin 

forward pickup plates with new fin forward 

pickup plates, part number (P/N) 11–03375– 

1. Do the replacement following the 

procedures in section 2.C. of the 

ACCOMPLISHMENT INSTRUCTIONS in 

Pacific Aerospace Limited Mandatory Service 

Bulletin PACSB/XL/068, Issue 5, dated June 

29, 2015. This replacement terminates the 

repetitive inspections required in paragraph 

(f)(2) of this AD. 

(4) If no cracks are found during any 

inspection required in paragraph (f)(2) of this 

AD, at or before reaching 6,000 hours TTIS 

or within the next 600 hours TIS after the 

effective date of this AD, whichever occurs 

later, replace the fin forward pickup plates, 

P/N 11–10281–1, with P/N 11–03375–1. Do 

the replacement following the procedures in 

section 2.D. of the ACCOMPLISHMENT 

INSTRUCTIONS in Pacific Aerospace 

Limited Mandatory Service Bulletin PACSB/ 

XL/068, Issue 5, dated June 29, 2015. This 

replacement terminates the repetitive 

inspections required in paragraph (f)(2) of 

this AD . 

(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: Karl Schletzbaum, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4146; fax: (816) 

329–4090; email: karl.schletzbaum@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. 

(h) Related Information 

Refer to MCAI Civil Aviation Authority 

(CAA) AD DCA/750XL/18A, dated August 4, 

2015, for related information. You may 

examine the MCAI on the Internet at http:// 

www.regulations.gov by searching for and 

locating Docket No. FAA–2015–3620. For 

service information related to this AD, 

contact Pacific Aerospace Limited, Airport 

Road, Hamilton, Private Bag 3027, Hamilton 

3240, New Zealand, phone: +64 7 843 6144; 

fax: +64 7 843 6134; email: pacific@

aerospace.co.nz; Internet: 

www.aerospace.co.nz. You may review 

copies of the 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. 

Issued in Kansas City, Missouri, on August 

14, 2015. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2015–21097 Filed 8–26–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3148; Directorate 

Identifier 2014–NM–254–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A320–212, –214, –232, 

and –233 airplanes. This proposed AD 

was prompted by a report of a crack 

found during an inspection of the 

pocket radius of the fuselage frame. This 

proposed AD would require repetitive 

low frequency eddy current inspections 

or repetitive high frequency eddy 

current inspections of this area, and 

repair if necessary. The repair 

terminates the repetitive inspections. 

We are proposing this AD to detect and 

correct any cracking of the pocket 

radius, which could lead to in-flight 

decompression of the airplane and 

possible injury to the passengers. 

DATES: We must receive comments on 

this proposed AD by October 13, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 


rmajette on DSK2VPTVN1PROD with PROPOSALS