19846 Federal Register / Vol. 79, No. 69 / Thursday, April 10, 2014 / Proposed Rules 

Pratt & Whitney Canada Corporation: Docket 

No. FAA–2014–0159; Directorate 

Identifier 2014–NE–01–AD. 

(a) Comments Due Date 

We must receive comments by June 9, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Pratt & Whitney Canada 

Corporation (P&WC) model PW150A 

turboprop engines, serial number PCE– 

FA0916 and earlier. 

(d) Reason 

This AD was prompted by reports of 

damage to a high-pressure fuel line, which 

could result in a high-pressure fuel leak into 

the engine nacelle. We are issuing this AD to 

prevent high-pressure fuel leaks, which 

could cause engine fire and damage to the 

engine and the airplane. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) At the next shop visit, but before 36 

months from the effective date of this AD, 

reroute the igniter cables and install new 

support brackets in accordance with 

Accomplishment Instructions, paragraph 

3.B., of P&WC Service Bulletin (SB) No. 

PW150–72–35274, Revision 1, dated May 3, 

2012. 

(2) Reserved. 

(f) Definition 

For the purpose of this AD, a shop visit is 

when the engine is disassembled to the 

extent necessary to gain access to the igniter 

cables. 

(g) Credit for Previous Action 

If you performed the actions of paragraph 

(e) of this AD before the effective date of this 

AD using P&WC SB No. PW150–72–35274, 

Initial Issue, dated March 23, 2012, you met 

the requirements of this AD. 

(h) 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. 

(i) Related Information 

(1) For more information about this AD, 

contact Wego Wang, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7134; fax: 781–238–7199; 

email: wego.wang@faa.gov. 

(2) Refer to MCAI Transport Canada AD 

CF–2014–09, dated February 12, 2014, for 

more information. You may examine the 

MCAI in the AD docket on the Internet at 

http://www.regulations.gov by searching for 

and locating it in Docket No. FAA–2014– 

0159. 

(3) P&WC SB No. PW150–72–35274, 

Revision 1, dated May 3, 2012, pertains to the 

subject of this AD and can be obtained from 

P&WC using the contact information in 

paragraph (i)(4) of this AD. 

(4) For service information identified in 

this AD, contact Pratt & Whitney Canada 

Corp., 1000 Marie-Victorin, Longueuil, 

Quebec, Canada, J4G 1A1; phone: 800–268– 

8000; fax: 450–647–2888; Internet: 

www.pwc.ca. 

(5) 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 

April 3, 2014. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–08009 Filed 4–9–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0193; Directorate 

Identifier 2013–NM–234–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 of a crack 

found in the fuselage during a fatigue 

test campaign. This proposed AD would 

require repetitive rototest inspections 

for cracking; corrective actions if 

necessary; and modification of the 

torsion box, which would terminate the 

repetitive inspections. We are proposing 

this AD to prevent cracking in the side 

box beam flange of the fuselage, which 

could affect the structural integrity of 

the airplane. 

DATES: We must receive comments on 

this proposed AD by May 27, 2014. 

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 

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—EAS, 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– 

0193; 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–2014–0193; Directorate Identifier 

2013–NM–234–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 


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Federal Register / Vol. 79, No. 69 / Thursday, April 10, 2014 / Proposed Rules 19847 

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 

Community, has issued EASA 

Airworthiness Directive 2013–0261, 

dated October 28, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

During the full scale fatigue test campaign 

of the A320 family type design, a crack was 

reported in the fuselage side box beam flange 

at frame (FR) 43 level, both sides. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

For the reason describe above, this [EASA] 

AD requires repetitive inspections of the 

fuselage side box beam flange at FR43, and, 

depending on findings, corrective action(s) 

[repair]. This [EASA] AD also requires a 

modification, which constitutes terminating 

action for the repetitive inspections. 

The modification includes related 

investigative and corrective actions. The 

related investigative actions include a 

rotoprobe inspection of the holes for 

cracks, and a high frequency eddy 

current (HFEC) inspection for cracks. 

The corrective action includes repair. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating it in Docket No. FAA– 

2014–0193. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–53–1251, Revision 01, dated 

October 18, 2013, and Service Bulletin 

A320–53–1258, dated October 18, 2012. 

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 the same 

type design. 

Repair Approvals 

In many FAA transport ADs, when 

the service information specifies to 

contact the manufacturer for further 

instructions if certain discrepancies are 

found, we typically include in the AD 

a requirement to accomplish the action 

using a method approved by either the 

FAA or the State of Design Authority (or 

its delegated agent). 

We have recently been notified that 

certain laws in other countries do not 

allow such delegation of authority, but 

some countries do recognize design 

approval organizations. In addition, we 

have become aware that some U.S. 

operators have used repair instructions 

that were previously approved by a 

State of Design Authority or a Design 

Approval Holder (DAH) as a method of 

compliance with this provision in FAA 

ADs. Frequently, in these cases, the 

previously approved repair instructions 

come from the airplane structural repair 

manual or the DAH repair approval 

statements that were not specifically 

developed to address the unsafe 

condition corrected by the AD. Using 

repair instructions that were not 

specifically approved for a particular 

AD creates the potential for doing 

repairs that were not developed to 

address the unsafe condition identified 

by the MCAI AD, the FAA AD, or the 

applicable service information, which 

could result in the unsafe condition not 

being fully corrected. 

To prevent the use of repairs that 

were not specifically developed to 

correct the unsafe condition, certain 

requirements of this proposed AD 

would require that the repair approval 

specifically refer to the FAA AD. This 

change is intended to clarify the method 

of compliance and to provide operators 

with better visibility of repairs that are 

specifically developed and approved to 

correct the unsafe condition. In 

addition, we use the phrase ‘‘its 

delegated agent, or the DAH with State 

of Design Authority design organization 

approval, as applicable’’ in this 

proposed AD to refer to a DAH 

authorized to approve certain required 

repairs for this proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 851 airplanes of U.S. registry. 

We also estimate that it would take 

about 178 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $31,334 per 

product. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $39,540,864, or 

$46,464 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. 

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: 


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19848 Federal Register / Vol. 79, No. 69 / Thursday, April 10, 2014 / Proposed Rules 

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–2014–0193; 

Directorate Identifier 2013–NM–234–AD. 

(a) Comments Due Date 

We must receive comments by May 27, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A318– 

111, –112, –121, and –122 airplanes; Model 

A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes; Model A320–111, 

–211, –212, –214, –231, –232, and –233 

airplanes; and Model A321–111, –112, –131, 

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

certificated in any category; all manufacturer 

serial numbers on which Airbus modification 

21202 has been embodied in production, 

except those on which modification 152569 

has been embodied in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report of a 

crack found in the side box beam flange of 

the fuselage at the frame (FR) 43 level during 

a fatigue test campaign. We are issuing this 

AD to prevent cracking in the side box beam 

flange of the fuselage, which could affect the 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

At the time specified in paragraph (g)(1) or 

(g)(2) of this AD, whichever occurs later: Do 

a rototest inspection for cracking of the beam 

flange of the stiffener 15 side box on the leftand right-hand sides in the FR43 area, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1258, dated October 18, 2012. Repeat the 

inspection thereafter at intervals not to 

exceed 7,500 flight cycles or 15, 000 flight 

hours, whichever occurs first. 

(1) Before exceeding 24,000 flight cycles or 

48,000 flight hours, whichever occurs first 

since the airplane’s first flight. 

(2) Within 3,000 flight cycles or 6,000 

flight hours, whichever occurs first after the 

effective date of this AD. 

(h) Corrective Action 

If any crack is found during any inspection 

required by paragraph (g) of this AD: Before 

further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or European Aviation 

Safety Agency (EASA) (or its delegated agent, 

or the Design Approval Holder (DAH) with 

EASA design organization approval). For a 

repair method to be approved, the repair 

approval must specifically refer to this AD. 

(i) Modification 

Before exceeding 48,000 flight cycles or 

96,000 flight hours, whichever occurs first 

since the airplane’s first flight: Modify the 

fittings on the left- and right-hand sides of 

the torsion box, including doing all 

applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1251, Revision 01, 

dated October 18, 2013; except where Airbus 

Service Bulletin A320–53–1251, Revision 01, 

dated October 18, 2013, specifies to contact 

Airbus for repair, before further flight, repair 

using a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or European 

Aviation Safety Agency (EASA) (or its 

delegated agent, or the Design Approval 

Holder (DAH) with EASA design 

organization approval). For a repair method 

to be approved, the repair approval must 

specifically refer to this AD. 

(j) Terminating Action 

Modification of the airplane as required by 

paragraph (i) of this AD constitutes 

terminating action for the repetitive 

inspections required by paragraph (g) of this 

AD. 

(k) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (i) of this AD, if those 

actions were performed before the effective 

date of this AD using Airbus Service Bulletin 

A320–53–1251, November 16, 2012, which is 

not incorporated by reference in this AD. 

(l) 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) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or the DAH with a State 

of Design Authority’s design organization 

approval, as applicable). For a repair method 

to be approved, the repair approval must 

specifically refer to this AD. You are required 

to ensure the product is airworthy before it 

is returned to service. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0261, dated 

October 28, 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 it in Docket No. 

FAA–2014–0193. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 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 April 1, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–08071 Filed 4–9–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HEALTH AND 

HUMAN SERVICES 

42 CFR Part 85a 

[Docket No. CDC–2014–0001; NIOSH–271] 

RIN 0920–AA51 

Occupational Safety and Health 

Investigations of Places of 

Employment 

AGENCY: Centers for Disease Control and 

Prevention, HHS. 

ACTION: Notice of proposed rulemaking; 

withdrawal. 

SUMMARY: The National Institute for 

Occupational Safety and Health 

(NIOSH) in the Centers for Disease 

Control and Prevention (CDC) within 

the Department of Health and Human 

Services (HHS) is withdrawing a 

previously published notice of proposed 

rulemaking that solicited public 

comment on minor technical 

amendments to regulatory text. 

DATES: The notice of proposed 

rulemaking published at 79 FR 2809, 


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