Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules 3533 

25–1141, dated August 19, 2013; as 

applicable. 

(1) If, during the measurement required by 

paragraph (i) of this AD, it is determined that 

there is a gap equal to or greater than 6 mm 

(0.236 inch): Before further flight, re-install 

the LH and RH Type III Emergency Exit 

Doors, in accordance with the 

Accomplishment Instructions of ATR Service 

Bulletin ATR42–25–0180, dated August 19, 

2013; or ATR72–25–1141, dated August 19, 

2013; as applicable. 

(2) If, during the measurement required by 

paragraph (i) of this AD, it is determined that 

there is a gap less than 6 mm (0.236 inch): 

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 ATR—GIE Avions 

de Transport Re ́gional’s EASA Design 

Organization Approval (DOA). 

(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, 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: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; 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 

EASA; or ATR—GIE Avions de Transport 

Re ́gional’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0280, dated 

November 26, 2013, 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–2015–0077. 

(2) For service information identified in 

this AD, contact ATR—GIE Avions de 

Transport Re ́gional, 1, Alle ́e Pierre Nadot, 

31712 Blagnac Cedex, France; telephone +33 

(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; 

email continued.airworthiness@atr.fr; 

Internet http://www.aerochain.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 January 

15, 2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–00956 Filed 1–22–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–1047; Directorate 

Identifier 2014–NM–157–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 A318, A319, A320, and 

A321 series airplanes. This proposed 

AD was prompted by a report that, 

during the assembly process, several 

gaps between the two parts of the girt 

bar fittings for the aft passenger doors 

were found to exceed tolerances. This 

proposed AD would require an 

inspection of the gap between the two 

parts of the girt bar fittings on left-hand 

(LH) and right-hand (RH) aft passenger 

doors, and corrective actions if 

necessary. We are proposing this AD to 

detect and correct incorrect gaps 

between the girt bar fittings. Detachment 

of a girt bar could lead to the separation 

of the slide or slide-raft from the 

fuselage, making the emergency exit 

inoperative, which could impede an 

emergency evacuation. 

DATES: We must receive comments on 

this proposed AD by March 9, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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 

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–2014– 

1047; 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–2014–1047; Directorate Identifier 

2014–NM–157–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 


emcdonald on DSK67QTVN1PROD with PROPOSALS
3534 Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules 

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 2014–0178, dated July 25, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for certain Airbus 

Model A318, A319, A320, and A321 

series airplanes. The MCAI states: 

During final assembly line process, several 

AFT passenger door lower fitting gaps were 

found excessive and out of tolerance between 

two parts of the girt bar fittings. The gap 

contributes to the correct locking of the girt 

bar during the door lifting movement, 

ensuring the retention of the girt bar when 

the loads applied on the girt by the slide are 

directed from the outside to the inside. If the 

gap is too large, there is a risk that the girt 

bar, when subjected to these loads, will 

detach from one of the girt bar fittings. 

This condition, if not detected and 

corrected, could lead to the separation of the 

slide/slide-raft from the fuselage, making the 

emergency exit inoperative and, 

consequently, significantly reducing the 

safety margin for the occupants during an 

evacuation. 

For the reason described above, this 

[EASA] AD requires a detailed inspection 

(DET) to check the gap between the two parts 

of the girt bar fittings, on AFT passenger 

doors, left-hand (LH) and right-hand (RH) 

sides, and, depending on findings, 

accomplishment of the applicable corrective 

actions [such as modifiying or replacing the 

automatic latch]. 

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–2014– 

1047. 

Related Service Information 

Airbus has issued Service Bulletin 

A320–53–1289, dated May 28, 2014. 

The service information describes 

procedures for a detailed inspection of 

the gap in the girt bar fittings of the aft 

passenger doors, LH and RH sides, and 

corrective actions. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

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 these same 

type designs. 

Explanation of ‘‘RC’’ Procedures and 

Tests in Service Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directives Implementation Aviation 

Rulemaking Committee (AD ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which procedures and tests 

in the service information are required 

for compliance with an AD. 

Differentiating these procedures and 

tests from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The actions specified in the 

service information identified 

previously include procedures and tests 

that are identified as RC (required for 

compliance) because these procedures 

have a direct effect on detecting, 

preventing, resolving, or eliminating an 

identified unsafe condition. 

As specified in a NOTE under the 

Accomplishment Instructions of the 

specified service information, 

procedures and tests identified as RC 

must be done to comply with the 

proposed AD. However, procedures and 

tests that are not identified as RC are 

recommended. Those procedures and 

tests that are not identified as RC may 

be deviated from using accepted 

methods in accordance with the 

operator’s maintenance or inspection 

program without obtaining approval of 

an alternative method of compliance 

(AMOC), provided the procedures and 

tests identified as RC can be done and 

the airplane can be put back in a 

serviceable condition. Any substitutions 

or changes to procedures or tests 

identified as RC will require approval of 

an AMOC. 

Costs of Compliance 

We estimate that this proposed AD 

affects 838 airplanes 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 $213,690, or $255 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 4 work-hours and require parts 

costing $435, for a cost of $775 per 

product. We have no way of 

determining the number of aircraft that 

might 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 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: 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules 3535 

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–2014–1047; 

Directorate Identifier 2014–NM–157–AD. 

(a) Comments Due Date 

We must receive comments by March 9, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus airplanes 

identified in paragraphs (c)(1) through (c)(4) 

of this AD, certificated in any category, 

except those on which Airbus Modification 

154966 has been embodied during 

production. 

(1) Model A318–111, –112, –121, and –122 

airplanes. 

(2) Model A319–111, –112, –113, –114, 

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

(3) Model A320–211, –212, –214, –231, 

–232, and –233 airplanes. 

(4) 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 a report that, 

during the assembly process, several gaps 

between the two parts of the girt bar fittings 

for the aft passenger doors were found to 

exceed tolerances. We are issuing this AD to 

detect and correct incorrect gaps between the 

girt bar fittings. Detachment of a girt bar 

could lead to the separation of the slide or 

slide-raft from the fuselage, making the 

emergency exit inoperative, which could 

impede an emergency evacuation. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Corrective Action 

Except as provided by paragraph (h) of this 

AD, within 36 months after the effective date 

of this AD, do a detailed inspection of the 

gap in the girt bar fittings of the aft passenger 

doors, LH and RH sides, and do all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–53–1289, 

dated May 28, 2014. Do all applicable 

corrective actions before further flight. 

(h) Exception 

For any airplane that has been modified to 

a configuration where one or both LH and RH 

aft passenger doors are permanently 

inoperative or deactivated: If any aft 

passenger door is reactivated, after 

reactivation but before further flight, do the 

detailed inspection of the reactivated aft 

passenger door(s) and all applicable 

corrective actions, as required by paragraph 

(g) of this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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) Required for Compliance (RC): If the 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures and tests that 

are not identified as RC are recommended. 

Those procedures and tests that are not 

identified as RC may be deviated from using 

accepted methods in accordance with the 

operator’s maintenance or inspection 

program without obtaining approval of an 

AMOC, provided the procedures and tests 

identified as RC can be done and the airplane 

can be put back in a serviceable condition. 

Any substitutions or changes to procedures 

or tests identified as RC require approval of 

an AMOC. 

(3) 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 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. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2014–0178, dated 

July 25, 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– 

2014–1047. 

(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 January 

14, 2015. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–00943 Filed 1–22–15; 8:45 am] 

BILLING CODE 4910–13–P 

CONSUMER PRODUCT SAFETY 

COMMISSION 

16 CFR Part 1422 

[Docket No. CPSC–2009–0087] 

Recreational Off-Highway Vehicles 

(ROVs); Notice of Extension of 

Comment Period 

AGENCY: U.S. Consumer Product Safety 

Commission. 

ACTION: Extension of comment period. 

SUMMARY: The Consumer Product Safety 

Commission (Commission or CPSC) 

published a notice of proposed 

rulemaking (NPR) in the Federal 

Register on November 19, 2014, 

concerning recreational off-highway 

vehicles (ROVs). The NPR invited the 

public to submit written comments by 

February 2, 2015. In response to two 

requests for an extension, the 

Commission is extending the comment 

period. 

DATES: Submit comments by April 8, 

2015. 

ADDRESSES: You may submit comments, 

identified by Docket No. CPSC–2009– 

0087, by any of the following methods: 

Electronic Submissions 

Submit electronic comments in the 

following way: 

Federal eRulemaking Portal: http://

www.regulations.gov. Follow the 

instructions for submitting comments. 

The Commission does not accept 

comments submitted by electronic mail 

(email), except through: http://

www.regulations.gov. The Commission 

encourages you to submit electronic 

comments by using the Federal 

eRulemaking Portal, as described above. 

Written Submissions 

Submit written submissions in the 

following way: 

Mail/Hand delivery/Courier, 

preferably in five copies, to: Office of the 


emcdonald on DSK67QTVN1PROD with PROPOSALS