15266 Federal Register / Vol. 79, No. 53 / Wednesday, March 19, 2014 / Proposed Rules 

May 26, 2009, for multi-engine airplanes; and 

in OIL OI331–18R4, dated May 26, 2009, for 

single-engine airplanes. Information on fuel 

control drive spline inspection can be found 

in Section 72–00–00 of the applicable 

TPE331 maintenance manuals. These 

Honeywell International Inc., OILs and the 

TPE331 maintenance manuals, which are not 

incorporated by reference in this AD, can be 

obtained from Honeywell International Inc., 

using the contact information in paragraph 

(i)(4) of this AD. 

(4) For service information identified in 

this AD, contact Honeywell International 

Inc., 111 S. 34th Street, Phoenix, AZ 85034– 

2802; Internet: https://

myaerospace.honeywell.com/wps/portal/!ut; 

phone: 800–601–3099. 

(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 

March 10, 2014. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–06029 Filed 3–18–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0143; Directorate 

Identifier 2012–NM–113–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 all 

Airbus Model A300 B4–603, B4–620, 

B4–622, B4–605R, B4–622R; F4–605R, 

F4–622R and C4–605R variant F 

airplanes. This proposed AD was 

prompted by reports of cracks in the 

frame base fittings connecting the frame 

lower positions to the center wing box. 

This proposed AD would require 

repetitive detailed inspections of the 

lower frame fittings, related 

investigative actions, and corrective 

actions if necessary. We are proposing 

this AD to detect and correct cracking 

on the lower frame fittings, which could 

reduce the structural integrity of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by May 5, 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 SAS, 

Airworthiness Office—EAW, 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– 

0143; 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; 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–2014–0143; Directorate Identifier 

2012–NM–113–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 

Community, has issued EASA 

Airworthiness Directive 2012–0103, 

dated June 11, 2012 (corrected June 19, 

2012) (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 maintenance checks, cracks were 

discovered by A300 and A300–600 operators 

in the frame [base] feet fittings, connecting 

the frame lower positions to the centre wing 

box. 

These occurrences were followed by a 

dedicated sampling inspection programme 

carried out by Airbus. During this sampling 

programme, 22 A300–600 aeroplanes were 

found with cracks on the lower fittings of 

frame 44 to frame 46 left hand (LH) and right 

hand (RH) side. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the fuselage of all aeroplanes operated up 

to the extended service goal (ESG). 

For the reasons described above, this 

[EASA] AD requires repetitive detailed visual 

inspections [for discrepancies (cracking)] of 

the lower frame fittings between frame 41 

and frame 46 and, depending on findings, 

accomplishment of a repair. 

This [EASA] AD has been republished to 

correct Note 2 in Appendix 1. 

Related investigative actions include 

doing a rotating probe inspection for 

cracking of the crack stop hole. 

Corrective actions include repairing or 

replacing cracking and cracked base 

fittings. 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– 

2014–0143. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A300–53–6111, Revision 05, 

including Appendix 01, dated January 

28, 2013. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 53 / Wednesday, March 19, 2014 / Proposed Rules 15267 

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. 

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, 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 required repairs 

for this proposed AD. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

Unlike the procedures described in 

Airbus Mandatory Service Bulletin 

A300–53–6111, Revision 05, including 

Appendix 01, dated January 28, 2013; 

this proposed AD would not permit 

further flight if discrepancies (cracking 

or cracked frames) are detected in the 

base fitting of the left-hand and righthand frames 41 to 46 of the fuselage. We 

have determined that, because of the 

safety implications and consequences 

associated with that cracking, any 

cracked frame must be repaired or 

modified before further flight. This 

difference has been coordinated with 

EASA. 

Airbus Mandatory Service Bulletin 

A300–53–6111, Revision 05, including 

Appendix 01, dated January 28, 2013, 

does not provide corrective action for 

cracking that measures 20 mm. This AD 

would require repairing the cracking 

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 with 

EASA’s design organization approval, as 

applicable. 

Costs of Compliance 

We estimate that this proposed AD 

affects 124 airplanes of U.S. registry. 

We also estimate that it would take 

about 4 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 $0 per product. 

Based on these figures, we estimate the 

cost of this proposed AD on U.S. 

operators to be $340, or $42,160 per 

product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 348 work-hours and require parts 

costing $61,810, for a cost of $91,390 

per product. We have no way of 

determining the number of aircraft that 

might need these actions. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to 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 control 

number for the collection of information 

required by this proposed AD is 2120– 

0056. The paperwork cost associated 

with this proposed AD has been 

detailed in the Costs of Compliance 

section of this document and includes 

time for reviewing instructions, as well 

as completing and reviewing the 

collection of information. Therefore, all 

reporting associated with this proposed 

AD is 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. 

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. 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
15268 Federal Register / Vol. 79, No. 53 / Wednesday, March 19, 2014 / Proposed Rules 

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. Amend § 39.13 by adding the 

following new airworthiness directive 

(AD): 

Airbus: Docket No. FAA–2014–0143; 

Directorate Identifier 2012–NM–113–AD. 

(a) Comments Due Date 

We must receive comments by May 5, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A300 B4– 

603, B4–620, B4–622, B4–605R, B4–622R; 

F4–605R, F4–622R and C4–605R variant F 

airplanes; certificated in any category; all 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by reports of cracks 

in the frame base fittings connecting the 

frame lower positions to the center wing box. 

We are issuing this AD to detect and correct 

cracking on the lower frame fittings, which 

could reduce the structural integrity of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Corrective Actions 

At the applicable time specified in 

paragraphs (g)(1) through (g)(4) of this AD, do 

a detailed inspection for discrepancies 

(cracking) of the base fitting of the left-hand 

and right-hand frames 41 to 46 of the 

fuselage, and do all applicable related 

investigative actions and corrective actions, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A300–53–6111, Revision 05, dated 

January 28, 2013, except as required by 

paragraph (k) of this AD. Do all applicable 

related investigative actions and corrective 

actions before further flight. Repeat the 

inspections at the applicable time specified 

in paragraphs (h)(1) through (h)(4) of this AD. 

(1) For any frame on which no affected 

repairs specified in paragraph (i) of this AD 

have been accomplished as of the effective 

date of this AD, and the airplane has 

operated with an average flight time (AFT) of 

more than 1.5 hours: At the later of the times 

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

of this AD. 

(i) Within 5,000 flight cycles (FC) or 10,800 

flight hours, whichever occurs first, since 

airplane first flight. 

(ii) Within 1,000 flight cycles after the 

effective date of this AD. 

(2) For any frame on which no affected 

repairs specified in paragraph (i) of this AD 

have been accomplished as of the effective 

date of this AD, and the airplane has 

operated with an AFT of equal to or less than 

1.5 hours: At the later of the times specified 

in paragraphs (h)(2)(i) and (h)(2)(ii) of this 

AD. 

(i) Within 5,400 flight cycles or 8,100 flight 

hours, whichever occurs first since airplane 

first flight. 

(ii) Within 1,000 flight cycles after the 

effective date of this AD. 

(3) For any frame on which any of the 

affected repairs specified in paragraph (i) of 

this AD have been accomplished as of the 

effective date of this AD, and the airplane has 

operated with an AFT of more than 1.5 

hours: At the later of the times specified in 

paragraphs (h)(3)(i) and (h)(3)(ii) of this AD. 

(i) Within 45,400 flight cycles or 98,000 

flight hours, whichever occurs first since 

frame repair embodiment. 

(ii) Within 1,000 flight cycles after the 

effective date of this AD. 

(4) For any frame on which any of the 

affected repairs specified in paragraph (i) of 

this AD have been accomplished as of the 

effective date of this AD, and the airplane 

operated with an AFT of equal to or less than 

1.5 hours: At the later of the times specified 

in paragraphs (h)(4)(i) and (h)(4)(ii) of this 

AD. 

(i) Within 49,000 flight cycles or 73,500 

flight hours, whichever occurs first since 

frame repair embodiment. 

(ii) Within 1,000 flight cycles after the 

effective date of this AD. 

(h) Repetitive Inspection Compliance Times 

(1) For any frame on which no affected 

repairs specified in paragraph (i) of this AD 

have been accomplished as of the effective 

date of this AD, and the airplane has 

operated with an AFT of more than 1.5 

hours: Inspect within 3,200 flight cycles or 

7,000 flight hours, whichever occurs first. 

(2) For any frame on which no affected 

repairs specified in paragraph (i) of this AD 

have been accomplished as of the effective 

date of this AD, and the airplane operated 

with an AFT of equal to or less than 1.5 

hours: Inspect within 3,500 flight cycles or 

5,300 flight hours, whichever occurs first 

since airplane first flight. 

(3) For any frame on which any of the 

affected repairs specified in paragraph (i) of 

this AD have been accomplished as of the 

effective date of this AD and the airplane 

operated with an AFT of more than 1.5 

hours: Inspect within 45,400 flight cycles or 

98,000 flight hours, whichever occurs first 

since frame repair embodiment. 

(4) For any frame on which any of the 

affected repairs specified in paragraph (i) of 

this AD have been accomplished as of the 

effective date of this AD, and the airplane 

operated with an AFT of equal to or less than 

1.5 hours: Inspect within 49,000 flight cycles 

or 73,500 flight hours, whichever occurs first, 

since frame repair embodiment. 

(i) Definition of Affected Repairs 

For the purposes of this AD, affected 

repairs are R53810322, R53810323, 

R53810329, R53810330, R53810331, 

R53810332, and any repair specified in 

Airbus Mandatory Service Bulletin A300–53– 

6111, Revision 05, including Appendix 01, 

dated January 28, 2013, as well as repairs 

accomplished in accordance with Airbus 

Mandatory Service Bulletin A300–53–6111, 

any revision. 

(j) Definition of Average Flight Time (AFT) 

For the purposes of this AD, the AFT is 

defined as a computation of the number of 

flight hours divided by the number of flight 

cycles accumulated since last inspection, or 

since airplane first flight, as applicable. 

(k) Exceptions to Service Information 

Specifications 

Where Airbus Mandatory Service Bulletin 

A300–53–6111, Revision 05, including 

Appendix 01, dated January 28, 2013, does 

not specify action for a repair that measures 

20 mm, if during any inspection required by 

paragraph (g) of this AD cracking is found 

that measures 20 mm, 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 with EASA’s design organization 

approval, as applicable). For a repair method 

to be approved, the repair approval must 

specifically refer to this AD. 

(l) Reporting of Inspection Results 

At the applicable time specified in 

paragraphs (l)(1) and (l)(2) of this AD: After 

accomplishment of any inspection specified 

in paragraph (g) of this AD, report 

discrepancies (cracking) to Airbus, in 

accordance with Appendix 01 of Airbus 

Mandatory Service Bulletin A300–53–6111, 

Revision 05, dated January 28, 2013. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(m) Clarification 

Accomplishment of corrective action(s) as 

required by paragraph (g) of this AD does not 

constitute terminating action for the 

repetitive inspections required by paragraph 

(h) of this AD. 

(n) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus 

Mandatory Service Bulletin A300–53–6111, 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 53 / Wednesday, March 19, 2014 / Proposed Rules 15269 

Revision 04, including Appendix 01, dated 

August 25, 2011, which is not incorporated 

by reference in this AD. 

(o) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, ANM–116, 

International Branch, 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–2125; 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). 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. 

(3) Reporting Requirements: A federal 

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. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2012–0103, dated 

June 11, 2012, (corrected June 19, 2012) 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– 

0143. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 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 March 7, 

2014. 

Michael J. Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–06009 Filed 3–18–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0776; Directorate 

Identifier 2009–NE–32–AD] 

RIN 2120–AA64 

Airworthiness Directives; Dowty 

Propellers Constant Speed Propellers 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to revise 

airworthiness directive (AD) 2010–17– 

11R1, which applies to all Dowty 

Propellers R408/6–123–F/17 model 

propellers. AD 2010–17–11R1 requires 

initial and repetitive application of 

sealant between the bus bar assembly 

and the backplate assembly of certain 

line-replaceable units (LRUs). That AD 

also provides an optional terminating 

action to the repetitive re-application of 

sealant. This proposed AD would 

increase the interval allowed between 

the required re-application of sealant, 

and would specify an additional 

acceptable sealant. We are proposing 

this AD to prevent an in-flight double 

generator failure, which could result in 

reduced control of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 19, 2014. 

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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact Dowty Propellers, 

Anson Business Park, Cheltenham Road 

East, Gloucester GL2 9QN, UK; phone: 

44 (0) 1452 716000; fax: 44 (0) 1452 

716001. 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. 

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–2009– 

0776; 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 

mandatory continuing airworthiness 

information, the regulatory evaluation, 

any comments received, and other 

information. The street address for the 

Docket Office (phone: 800–647–5527) is 

in the ADDRESSES section. Comments 

will be available in the AD docket 

shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Michael Schwetz, Aerospace Engineer, 

Boston Aircraft Certification Office, 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA 01803; phone: 781– 

238–7761; fax 781–238–7170; email: 

michael.schwetz@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–2009–0776; Directorate Identifier 

2009–NE–32–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://


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS