Federal Register / Vol. 79, No. 82 / Tuesday, April 29, 2014 / Rules and Regulations 23909 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0255; Directorate 

Identifier 2014–NM–056–AD; Amendment 

39–17840; AD 2014–09–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A330–200 and –300 series 

airplanes, and Model A340–200 and 

–300 series airplanes. This AD requires 

repetitive inspections of certain sidestay 

upper cardan pins of the main landing 

gear (MLG), and associated nuts and 

retainer assemblies, and pin 

replacement if necessary. This AD also 

provides for an optional measurement of 

the cardan pin clearance dimensions 

(gap check) and corrective actions if 

necessary, which would terminate the 

repetitive inspections. This AD was 

prompted by a report of a sidestay upper 

cardan pin of the MLG migrating out of 

position. We are issuing this AD to 

detect and correct migration of the 

sidestay upper cardan pin, which could 

result in disconnection of the sidestay 

upper arm from the airplane structure, 

and could result in a landing gear 

collapse and consequent damage to the 

airplane and injury to occupants. 

DATES: This AD becomes effective May 

14, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 14, 2014. 

We must receive comments on this 

AD by June 13, 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: 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 AD, contact Airbus SAS— 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330–A340@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– 

0255; or in person at the Docket 

Operations office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1138; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

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 2014–0066, 

(correction) dated March 20, 2014 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for certain Airbus Model 

A330–200 and –300 series airplanes, 

and Model A340–200 and –300 series 

airplanes. The MCAI states: 

An A330 aeroplane equipped with Basic 

(main landing gear) MLG was rolling out after 

landing when it experienced a nose wheel 

steering fault (unrelated to the safety subject 

addressed by this [EASA] AD), which 

resulted in the crew stopping the aeroplane 

on the taxiway after vacating the runway. 

The subsequent investigation revealed that 

the right-hand MLG sidestay upper cardan 

pin had migrated out of position. The 

sidestay upper cardan nut and retainer were 

found in the landing gear bay detached from 

the upper cardan pin. The nut and the 

retainer were still bolted together. 

This condition, if not detected and 

corrected, could lead to a complete migration 

of the sidestay upper cardan pin and a 

disconnection of the sidestay upper arm from 

the aeroplane structure, possibly resulting in 

MLG collapse with consequent damage to the 

aeroplane and injury to occupants. 

To address this potential condition, Airbus 

published Alert Operators Transmission 

(AOT) A32L003–14, providing inspection 

instructions. 

For the reasons described above, this 

[EASA] AD requires accomplishment of 

repetitive [detailed inspections for visible 

chrome] of the MLG upper cardan pin, nut 

and retainer [and pin replacement if 

necessary. This [EASA] AD also requires 

accomplishment of a gap check between 

wing rear spar fitting lugs and the bush 

flanges [and corrective actions if necessary. 

Corrective actions include repair or 

replacement of the cardan pin assembly]. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2014–0255. 

Relevant Service Information 

Airbus has issued Airbus Alert 

Operators Transmission (AOT) 

A32L003–14, dated March 10, 2014, 

including Appendices 1, 2, and 3 (the 

issue date is not specified on the 

appendices). The actions described in 

this service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

Differences Between This AD and the 

MCAI 

Mandatory Continuing Airworthiness 

Information (MCAI) European Aviation 

Safety Agency Airworthiness Directive 

2014–0066, (correction) dated March 20, 

2014, specifies that accomplishment of 

the gap check and corrective actions 

constitute terminating action for the AD. 

We consider the replacement of the 

cardan pin assembly as specified in 

paragraph (g)(3) to be terminating action 

for the repetitive inspections required 

by this AD. 

FAA’s Determination and Requirements 

of This 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 issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 


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23910 Federal Register / Vol. 79, No. 82 / Tuesday, April 29, 2014 / Rules and Regulations 

develop on other products of these same 

type designs. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because migration of the sidestay 

upper cardan pin and disconnection of 

the sidestay upper arm from the 

airplane structure, could result in a 

landing gear collapse and consequent 

damage to the airplane and injury to 

occupants. Therefore, we determined 

that notice and opportunity for public 

comment before issuing this AD are 

impracticable and that good cause exists 

for making this amendment effective in 

fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2014–0255; 

Directorate Identifier 2014–NM–056– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 AD. 

Interim Action 

This AD is considered to be interim 

action. We are currently considering 

requiring a measurement of the cardan 

pin clearance dimensions (gap check) to 

determine that no gap exists between 

wing rear spar fitting lugs and the 

associated bush flanges of the left-hand 

and right-hand main landing gear 

(MLG), and applicable corrective 

actions, which will constitute 

terminating action for the repetitive 

inspections required by this AD action. 

However, the planned compliance time 

for the measurement would allow 

enough time to provide notice and 

opportunity for prior public comment 

on the merits of the measurement and 

applicable corrective actions. 

Costs of Compliance 

We estimate that this AD affects 83 

airplanes of U.S. registry. 

We also estimate that it will take 

about 1 work-hour per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $7,055, or $85 per 

product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 4 work-hours and require parts 

costing $7,530, for a cost of $7,870 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 AD is 2120–0056. The 

paperwork cost associated with this 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. 

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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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 that this AD: 

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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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): 

2014–09–05 Airbus: Amendment 39–17840. 

Docket No. FAA–2014–0255; Directorate 

Identifier 2014–NM–056–AD. 

(a) Effective Date 

This AD becomes effective May 14, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category. 

(1) Airbus Model A330–201, A330–202, 

A330–203, A330–223, A330–243, A330–301, 

A330–302, A330–303, A330–321, A330–322, 

A330–323, A330–341, A330–342, and A330– 

343 airplanes, all manufacturer serial 

numbers (MSNs), equipped with basic 

(201252 series) main landing gear (MLG), or 

growth (201490 series) MLG. 

(2) Airbus Model A340–211, A340–212, 

A340–213, A340–311, A340–312, and A340– 


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Federal Register / Vol. 79, No. 82 / Tuesday, April 29, 2014 / Rules and Regulations 23911 

313 airplanes, all MSNs, equipped with basic 

(201252 series) MLG or growth (201490 

series) MLG. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by a report of a 

sidestay upper cardan pin of the MLG 

migrating out of position. We are issuing this 

AD to detect and correct migration of the 

sidestay upper cardan pin, which could 

result in disconnection of the sidestay upper 

arm from the airplane structure, and which 

could result in a landing gear collapse and 

consequent damage to the airplane and injury 

to occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Detailed Inspections 

(1) For airplanes identified in paragraphs 

(g)(1)(i) and (g)(1)(ii) of this AD on which the 

affected MLG has exceeded 8 years since first 

overhaul, as of the effective date of this AD, 

except those MLG that have had a second 

overhaul: Within 30 days after the effective 

date of this AD, accomplish a detailed 

inspection for visible chrome of each affected 

MLG sidestay upper cardan pin, and 

associated nut and retainer assembly, in 

accordance with the instructions of Airbus 

Alert Operators Transmission (AOT) 

A32L003–14, dated March 10, 2014, 

including Appendices 1, 2, and 3 (the issue 

date is not specified on the appendices). 

(i) Airplanes equipped with any MLG 

sidestay upper cardan pin subassembly part 

number (P/N) 201267202 (on 201252 series 

MLG). 

(ii) Airplanes equipped with any MLG 

sidestay upper cardan pin subassembly P/N 

201483202 (on 201490 series MLG). 

(2) If, during any inspection required by 

paragraph (g)(1) of this AD, no pin chrome 

is visible inboard of the wing rear spar fitting 

lug, repeat the detailed inspection for visible 

chrome specified in paragraph (g)(1) of this 

AD, thereafter at intervals not to exceed 10 

days. 

(3) If, during any inspection required by 

paragraphs (g)(1) or (g)(2) of this AD, pin 

chrome is visible inboard of the wing rear 

spar fitting lug, before further flight, replace 

the affected cardan pin assembly, in 

accordance with the instructions of Airbus 

AOT A32L003–14, dated March 10, 2014, 

including Appendices 1, 2, and 3 (the issue 

date is not specified on the appendices). 

Replacement of the affected cardan pin 

assembly terminates the need for repetitive 

inspections required by paragraph (g)(2) of 

this AD. 

Note 1 to paragraph (g) of this AD: MLG 

sidestay upper cardan pin subassembly P/N 

201267202 (found in Airbus Illustrated Parts 

Catalogue (IPC) as item 32–11–18–01) 

includes the cardan pin P/N 201267600. 

MLG sidestay upper cardan pin subassembly 

P/N 201483202 (found in Airbus IPC as item 

32–11–18–01) includes the cardan pin P/N 

201483600. 

(h) Optional Terminating Action—Gap 

Check 

Measuring the cardan pin clearance 

dimensions (gap check) and doing the 

applicable corrective action specified in 

paragraph (h)(1) or (h)(2) of this AD 

terminates the repetitive inspections required 

by paragraphs (g)(1) and (g)(2) of this AD for 

that sidestay upper cardan pin, nut, and 

retainer only. The measurement must be 

done in accordance with the instructions of 

Airbus AOT A32L003–14, dated March 10, 

2014, including Appendices 1, 2, and 3 (the 

issue date is not specified on the 

appendices). 

(1) If the total clearance dimension (gap 

check result) is equal to or greater than 1.5 

mm, replace the cardan pin assembly, in 

accordance with Airbus AOT A32L003–14, 

dated March 10, 2014, including Appendices 

1, 2, and 3 (the issue date is not specified on 

the appendices). 

(2) If the total clearance dimension (gap 

check) is less than 1.5 mm but greater than 

0.6 mm, do the actions specified in 

paragraphs (h)(2)(i) and (h)(2)(ii) of this AD. 

(i) Send the information (Appendix 2 

proforma, photographs, and the movement 

traceability sheet) specified in paragraph 

4.2.3, ‘‘Findings’’ of Airbus AOT A32L003– 

14, dated March 10, 2014, including 

Appendices 1, 2, and 3, to Airbus at the 

address specified in Appendix 2 of Airbus 

AOT A32L003–14, dated March 10, 2014. 

(ii) 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). 

(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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; 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). 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. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2014–0066, (correction) dated 

March 20, 2014, for related information. You 

may examine the MCAI on the Internet at 

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

and locating Docket No. FAA–2014–0255. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Alert Operators Transmission 

(AOT) A32L003–14, dated March 10, 2014, 

including Appendices 1, 2, and 3 (the issue 

date is not specified on the appendices). 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(4) 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 


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23912 Federal Register / Vol. 79, No. 82 / Tuesday, April 29, 2014 / Rules and Regulations 

Issued in Renton, Washington, on April 16, 

2014. 

Michael J. Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–09412 Filed 4–28–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0164; Directorate 

Identifier 2013–NE–10–AD; Amendment 

39–17834; AD 2014–08–10] 

RIN 2120–AA64 

Airworthiness Directives; Austro 

Engine GmbH Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2013–14– 

08 for all Austro Engine GmbH model 

E4 engines. AD 2013–14–08 required 

removing from service certain part 

number (P/N) waste gate controllers. 

This AD requires removing certain 

additional P/N waste gate controllers 

from service. This AD was prompted by 

several reports of power loss events due 

to fracture of the waste gate controller 

lever. We are issuing this AD to prevent 

failure of the waste gate controller lever, 

which could lead to damage to one or 

more engines, loss of thrust control, and 

damage to the airplane. 

DATES: This AD is effective June 3, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Austro 

Engine GmbH, Rudolf-Diesel-Strasse 11, 

A–2700 Weiner Neustadt, Austria; 

phone: +43 2622 23000; fax: +43 2622 

23000–2711; Internet: 

www.austroengine.at. 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–2013– 

0164; 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 AD, the mandatory 

continuing airworthiness information 

(MCAI), the regulatory evaluation, any 

comments received, and other 

information. The address for the Docket 

Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION 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. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2013–14–08, 

Amendment 39–17513 (78 FR 42677, 

July 17, 2013), (‘‘AD 2013–14–08’’). AD 

2013–14–08 applied to the specified 

products. The NPRM published in the 

Federal Register on January 10, 2014 

(79 FR 1774). The NPRM proposed to 

continue to require removal from 

service of certain P/N waste gate 

controllers. The NPRM also proposed 

that, based on additional in-service 

failures, additional P/N waste gate 

controllers no longer be eligible for 

installation. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 1774, January 10, 2014). 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 128 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 0.5 hours per engine to 

comply with this AD. The average labor 

rate is $85 per hour. Required parts cost 

about $231 per engine. Based on these 

figures, we estimate the total cost of this 

AD to U.S. operators to be $35,008. 

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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will 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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends part 39 of the Federal 

Aviation Regulations (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 airworthiness directive (AD) 

2013–14–08, Amendment 39–17513 (78 

FR 42677, July 17, 2013) and adding the 

following new AD: 

2014–08–10 Austro Engine GmbH Engines: 

Amendment 39–17834; Docket No. 


sroberts on DSK5SPTVN1PROD with RULES