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
Federal Register / Vol. 80, No. 166 / Thursday, August 27, 2015 / Proposed Rules 51969 

• 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 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3148; 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 Operations 

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: 

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: 

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–2015–3148; Directorate Identifier 

2014–NM–254–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 based on those comments. 

We will post all comments we 

receive, without change, to http://

www.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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0278, dated December 

19, 2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for certain Airbus 

Model A320–212, -214, -232, and -233 

airplanes. The MCAI states: 

An operator reported finding a crack 

during an inspection in accordance with the 

instructions of Airbus Alert Operators 

Transmission (AOT) A53N007–14. What was 

found, a 170 mm through-thickness crack in 

the pocket radius between frame 36 and 37 

above stringer 6 on left hand (LH) side lap 

joint, was not the aim of the AOT inspection. 

Prior to this finding, the operator reported 

noise in the affected area during several 

weeks. 

This condition, if not detected and 

corrected, could lead to in-flight 

decompression of the aeroplane, possibly 

resulting in injury to occupants. 

To address this unsafe condition, Airbus 

published AOT A53N009–14 to provide 

inspection and repair instructions to detect 

and prevent crack propagation. 

EASA decided to agree on a sampling 

inspection to determine whether additional 

aeroplanes need to be inspected. 

For the reasons described above, this 

[EASA] AD requires, for the selected 

aeroplanes, repetitive Low Frequency Eddy 

Current (LFEC) or High Frequency Eddy 

Current (HFEC) inspections of the pocket 

radii [for cracks] located between fuselage 

frames 35 and 40, above stringer 6 on both 

LH and right hand (RH) sides and, depending 

on findings, accomplishment of repair 

instructions. 

This [EASA] AD is considered an interim 

action and further [EASA] AD action may 

follow. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3148. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Airbus Alert Operators 

Transmission A53N009–14, dated 

December 17, 2014. The service 

information describes procedures for 

repetitive inspections of the pocket radii 

located between fuselage frames 35 and 

40, above stringer 6 on both the left- and 

right-hand sides, and repair 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 NPRM. 

FAA’s Determination and Requirements 

of This 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 the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an 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 

affects 1 airplane of U.S. registry. 

We also estimate that it would take 

about 3 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $255, or $255 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 


rmajette on DSK2VPTVN1PROD with PROPOSALS
51970 Federal Register / Vol. 80, No. 166 / Thursday, August 27, 2015 / Proposed Rules 

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 

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): 

Airbus: Docket No. FAA–2015–3148; 

Directorate Identifier 2014–NM–254–AD. 

(a) Comments Due Date 

We must receive comments by October 13, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A320– 

212 airplanes having manufacturer serial 

number (MSN) 1011; Airbus Model A320– 

214 airplanes having MSNs 1009, 1026 and 

1030; Airbus Model A320–232 airplanes 

having MSN 0977; and Airbus Model A320– 

233 airplanes having MSNs 1007 and 1013, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report of a 

crack found during an inspection of the 

pocket radius of the fuselage frame. We are 

issuing 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. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

(1) Within 750 flight cycles or 4 months, 

whichever occurs first after the effective date 

of this AD: Do a low frequency eddy current 

(LFEC) inspection or a high frequency eddy 

current (HFEC) inspection for cracking of the 

pocket radii located between fuselage frames 

35 and 40, above stringer 6 on both the leftand right-hand sides, in accordance with the 

instructions of Airbus Alert Operators 

Transmission (AOT) A53N009–14, dated 

December 17, 2014. Repeat the inspection, 

thereafter, at intervals not to exceed the times 

specified in paragraphs (g)(1)(i) and (g)(1)(ii) 

of this AD. 

(i) For the LFEC inspection performed on 

the outside: Repeat the inspection at intervals 

not to exceed 1,000 flight cycles. 

(ii) For the HFEC inspection performed on 

the inside: Repeat the inspection at intervals 

not to exceed 2,000 flight cycles. 

(h) Corrective Action 

If, during any inspection required by 

paragraph (g) of this AD, any crack is found, 

before further flight, accomplish the repair in 

accordance with the instructions of Airbus 

AOT A53N009–14, dated December 17, 2014; 

except if the crack is beyond the structural 

repair manual limits as specified in Airbus 

AOT A53N009–14, dated December 17, 2014, 

before further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the European Aviation 

Safety Agency (EASA); or Airbus’s EASA 

Design Organization Approval (DOA). 

(i) Terminating Action 

Repair of an airplane as required by 

paragraph (h) of this AD terminates the 

repetitive inspections required by paragraph 

(g) of this AD for the repaired area only. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0278, dated 

December 19, 2014, for related information. 

This MCAI may be found in the AD docket 

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

by searching for and locating Docket No. 

FAA–2015–3148. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

You may view this service information at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on August 

19, 2015. 

Kevin Hull, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–21098 Filed 8–26–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2015–3322; Airspace 

Docket No. 15–ANM–16] 

Proposed Establishment of Class E 

Airspace; Vancouver, WA 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

establish Class E surface area airspace at 

Pearson Field, Vancouver, WA, to 

accommodate existing Standard 

Instrument Approach Procedures 

(SIAPs) at the airport. The FAA is taking 

this action to enhance the safety and 


rmajette on DSK2VPTVN1PROD with PROPOSALS