48018 Federal Register / Vol. 79, No. 158 / Friday, August 15, 2014 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0531; Directorate 

Identifier 2014–NM–142–AD; Amendment 

39–17940; AD 2014–16–16] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(Embraer) 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 all 

Embraer S.A. Model ERJ 190–100 STD, 

–100 LR, –100 ECJ, –100 IGW, –200 

STD, –200 LR, and –200 IGW airplanes. 

This AD requires, for certain airplanes, 

retorquing and replacing the pylon 

outboard and inboard lower link 

fittings. For all airplanes, this AD 

requires repetitive retorquing of the 

pylon outboard and inboard lower link 

fittings. This AD was prompted by a 

report of a loose lower link assembly on 

the left and right pylons. We are issuing 

this AD to prevent loss of a shear pin 

on the pylon outboard and inboard 

lower link fittings, which could result in 

failure of the fitting and consequent 

separation of the engine from the wing. 

DATES: This AD becomes effective 

September 2, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 2, 2014. 

We must receive comments on this 

AD by September 29, 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 Embraer S.A., 

Technical Publications Section (PC 

060), Av. Brigadeiro Faria Lima, 2170— 

Putim—12227–901 Sa ̃o Jose dos 

Campos—SP—Brazil; telephone +55 12 

3927–5852 or +55 12 3309–0732; fax 

+55 12 3927–7546; email 

distrib@embraer.com.br; Internet http:// 

www.flyembraer.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– 

0531; 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: 

Kathrine Rask, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2180; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The Ageˆncia Nacional de Aviac ̧a ̃o 

Civil (ANAC), which is the aviation 

authority for Brazil, has issued Brazilian 

Airworthiness Directive 2014–07–01, 

dated July 10, 2014 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

on all Embraer S.A. Model ERJ 190–100 

STD, –100 LR, –100 ECJ, –100 IGW, 

–200 STD, –200 LR, and –200 IGW 

airplanes. The MCAI states: 

It has been found that repetitive tightening 

torque check required by EAD 2014–06–02— 

EMBRAER S.A./39–1383 may not be 

sufficient to prevent the lower inboard and 

outboard link fitting attaching parts, of the 

left hand (LH) and right hand (RH) pylon, 

from getting loose which could lead to the 

failure of one of those fittings and the 

consequent separation of the engine from the 

wing. 

Required actions include retorquing and 

replacing the pylon outboard and 

inboard lower link fittings on certain 

airplanes, and repetitively retorquing 

the pylon outboard and inboard lower 

link fittings on all airplanes. You may 

examine the MCAI on the Internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2014– 

0531. 

Relevant Service Information 

Embraer has issued the following 

service information: 

• Embraer Alert Service Bulletin 190– 

54–A015, Revision 03, dated June 27, 

2014. 

• Embraer Alert Service Bulletin 

190LIN–54–A006, Revision 02, dated 

June 27, 2014. 

• Embraer Service Bulletin 190–54– 

0013, dated November 27, 2012. 

• Embraer Service Bulletin 190–54– 

0015, dated July 3, 2014. 

• Embraer Service Bulletin 190LIN– 

54–0004, dated December 20, 2012. 

• Embraer Service Bulletin 190LIN– 

54–0006, dated July 3, 2014. 

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 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 

develop on other products of the same 

type design. 

Difference Between This AD and the 

MCAI or Service Information 

The applicability of the MCAI does 

not include production airplanes. This 

FAA AD, however, applies to all 

airplanes of the affected models to 

ensure that the repetitive retorquing is 

done on the fleet (as specified in 

paragraph (i) of this AD) and to prohibit 

the installation of certain lock nuts on 

any airplane in the fleet (as specified in 

paragraph (j) of this AD). 

The airplanes affected by paragraph 

(g)(2) of this AD include one airplane 

(serial number 19000641) that is not 

included in the corresponding 

requirement of the ANAC AD. For the 

airplanes affected by this requirement, 

the ANAC AD refers to Embraer Alert 

Service Bulletin 190LIN–54–A006, 

Revision 02, dated June 27, 2014. This 

FAA AD, however, refers to the most 

recent service information—Embraer 

Service Bulletin 190LIN–54–0006, dated 

July 3, 2014, which includes this 


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additional airplane. This has been 

coordinated with ANAC. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. 

The MCAI or referenced service 

information in an FAA AD often directs 

the owner/operator to contact the 

manufacturer for corrective actions, 

such as a repair. Briefly, the Airworthy 

Product paragraph allowed owners/ 

operators to use corrective actions 

provided by the manufacturer if those 

actions were FAA-approved. In 

addition, the paragraph stated that any 

actions approved by the State of Design 

Authority (or its delegated agent) are 

considered to be FAA-approved. 

In an NPRM having Directorate 

Identifier 2012–NM–101–AD (78 FR 

78285, December 26, 2013), we 

proposed to prevent the use of repairs 

that were not specifically developed to 

correct the unsafe condition, by 

requiring that the repair approval 

provided by the State of Design 

Authority or its delegated agent 

specifically refer to the FAA AD. This 

change was 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 proposed to 

change the phrase ‘‘its delegated agent’’ 

to include a design approval holder 

(DAH) with State of Design Authority 

design organization approval (DOA), as 

applicable, to refer to a DAH authorized 

to approve required repairs for the 

proposed AD. 

One commenter to the NPRM having 

Directorate Identifier 2012–NM–101–AD 

(78 FR 78285, December 26, 2013) stated 

the following: ‘‘The proposed wording, 

being specific to repairs, eliminates the 

interpretation that Airbus messages are 

acceptable for approving minor 

deviations (corrective actions) needed 

during accomplishment of an AD 

mandated Airbus service bulletin.’’ 

This comment has made the FAA 

aware that some operators have 

misunderstood or misinterpreted the 

Airworthy Product paragraph to allow 

the owner/operator to use messages 

provided by the manufacturer as 

approval of deviations during the 

accomplishment of an AD-mandated 

action. The Airworthy Product 

paragraph does not approve messages or 

other information provided by the 

manufacturer for deviations to the 

requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed the 

paragraph and retitled it ‘‘Contacting the 

Manufacturer.’’ This paragraph now 

clarifies that for any requirement in this 

AD to obtain corrective actions from a 

manufacturer, the actions must be 

accomplished using a method approved 

by the FAA, ANAC, or ANAC’s 

authorized Designee. 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the ANAC Designee, the approval 

must include the Designee’s authorized 

signature. The Designee’s signature 

indicates that the data and information 

contained in the document are ANACapproved, which is also FAA-approved. 

Messages and other information 

provided by the manufacturer that do 

not contain the ANAC Designee’s 

authorized signature approval are not 

ANAC-approved, unless ANAC directly 

approves the manufacturer’s message or 

other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

Interim Action 

We consider this AD interim action. If 

final action is later identified, we might 

consider further rulemaking then. 

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 loss of a shear pin on the 

pylon outboard and inboard lower link 

fittings could result in failure of the 

fitting and consequent separation of the 

engine from the wing. 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 less 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–2014–0531; 

Directorate Identifier 2014–NM–142– 

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. 

Costs of Compliance 

We estimate that this AD affects 86 

airplanes of U.S. registry. We also 

estimate that it will take about 6 workhours per product to comply with the 

basic requirements of this AD. Required 

parts will cost about $0. 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 $43,860, 

or $510 per product. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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 


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48020 Federal Register / Vol. 79, No. 158 / Friday, August 15, 2014 / Rules and Regulations 

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): 

2014–16–16 Embraer S.A.: Amendment 39– 

17940. Docket No. FAA–2014–0531; 

Directorate Identifier 2014–NM–142–AD. 

(a) Effective Date 

This AD becomes effective September 2, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Embraer S.A. Model 

ERJ 190–100 STD, –100 LR, –100 ECJ, –100 

IGW, –200 STD, –200 LR, and –200 IGW 

airplanes, certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 54, Nacelles/Pylons. 

(e) Reason 

This AD was prompted by a report of a 

loose lower link assembly on the left and 

right pylons. We are issuing this AD to 

prevent loss of a shear pin on the pylon 

outboard and inboard lower link fittings, 

which could result in failure of the fitting 

and consequent separation of the engine from 

the wing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Initial Retorque 

Retorque the left and right pylon outboard 

and inboard lower link fittings, as specified 

in paragraph (g)(1) or (g)(2) of this AD, as 

applicable. 

(1) For airplanes identified as Groups 1 and 

2 in Embraer Service Bulletin 190–54–0015, 

dated July 3, 2014: Retorque at the applicable 

time specified in paragraph (g)(1)(i) or 

(g)(1)(ii) of this AD, in accordance with the 

Accomplishment Instructions of Embraer 

Alert Service Bulletin 190–54–A015, 

Revision 03, dated June 27, 2014. 

(i) For Group 1 airplanes: Retorque at the 

applicable time specified in paragraph 

(g)(1)(i)(A) or (g)(1)(i)(B) of this AD. 

(A) If, as of the effective date of this AD, 

the airplane has accumulated fewer than 600 

total flight cycles and less than 750 total 

flight hours since accomplishment of the 

actions specified in Embraer Service Bulletin 

190–54–0013: Retorque within 50 flight 

hours after the effective date of this AD. 

(B) If, as of the effective date of this AD, 

the airplane has accumulated 600 or more 

total flight cycles or 750 or more total flight 

hours after accomplishment of Embraer 

Service Bulletin 190–54–0013: Retorque 

within 10 flight hours after the effective date 

of this AD. 

(ii) For Group 2 airplanes: Retorque at the 

applicable time specified in paragraph 

(g)(1)(ii)(A) or (g)(1)(ii)(B) of this AD. 

(A) If, as of the effective date of this AD, 

the airplane has accumulated fewer than 600 

total flight cycles and less than 750 total 

flight hours: Retorque within 50 flight hours 

after the effective date of this AD. 

(B) If, as of the effective date of this AD, 

the airplane has accumulated 600 or more 

total flight cycles or 750 or more total flight 

hours: Retorque within 10 flight hours after 

the effective date of this AD. 

(2) For airplanes identified as Groups 1 and 

2 in Embraer Service Bulletin 190LIN–54– 

0006, dated July 3, 2014: Retorque at the 

applicable time specified in paragraph 

(g)(2)(i) or (g)(2)(ii) of this AD, in accordance 

with the Accomplishment Instructions of 

Embraer Alert Service Bulletin 190LIN–54– 

A006, Revision 02, dated June 27, 2014. 

(i) For Group 1 airplanes: Retorque at the 

applicable time specified in paragraph 

(g)(2)(i)(A) or (g)(2)(i)(B) of this AD. 

(A) If, as of the effective date of this AD, 

the airplane has accumulated fewer than 200 

total flight cycles and less than 750 total 

flight hours since accomplishment of the 

actions specified in Embraer Service Bulletin 

190LIN–54–0004: Retorque within 50 flight 

hours after the effective date of this AD. 

(B) If, as of the effective date of this AD, 

the airplane has accumulated 200 or more 

total flight cycles or 750 or more total flight 

hours since accomplishment of the actions 

specified in Embraer Service Bulletin 

190LIN–54–0004: Retorque within 10 flight 

hours after the effective date of this AD. 

(ii) For Group 2 airplanes: Retorque at the 

applicable time specified in (g)(2)(ii)(A) or 

(g)(2)(ii)(B) of this AD. 

(A) If, as of the effective date of this AD, 

the airplane has accumulated fewer than 200 

total flight cycles and less than 750 total 

flight hours: Retorque within 50 flight hours 

after the effective date of this AD. 

(B) If, as of the effective date of this AD, 

the airplane has accumulated 200 or more 

total flight cycles or 750 or more total flight 

hours: Retorque within 10 flight hours after 

the effective date of this AD. 

(h) Replacement 

Replace the left and right pylon outboard 

and inboard lower link fittings as specified 

in paragraph (h)(1) or (h)(2), as applicable. 

(1) For airplanes identified as Groups 1 and 

2 in Embraer Service Bulletin 190–54–0015, 

dated July 3, 2014: Within 150 flight cycles 

or 200 flight hours, whichever occurs first 

after the effective date of this AD, replace the 

pylon outboard and inboard lower link 

fittings, in accordance with Parts I and II of 

the Accomplishment Instructions of Embraer 

Service Bulletin 190–54–0015, dated July 3, 

2014. 

(2) For airplanes identified as Groups 1 and 

2 in Embraer Service Bulletin 190LIN–54– 

0006, dated July 3, 2014: Within 60 flight 

cycles or 200 flight hours, whichever occurs 

first after the effective date of this AD, 

replace the pylon outboard and inboard 

lower link fittings, in accordance with Parts 

I and II of the Accomplishment Instructions 

of Embraer Service Bulletin 190LIN–54– 

0006, dated July 3, 2014. 

(i) Repetitive Retorquing 

Retorque the left and right pylon outboard 

and inboard lower link fittings, as specified 

in paragraph (i)(1) or (i)(2) of this AD, as 

applicable. 

(1) For Model ERJ 190–100 STD, &100 LR, 

–100 IGW, –200 STD, –200 LR, and –200 

IGW airplanes: Retorque as specified in 

paragraph (i)(1)(i) or (i)(1)(ii) of this AD, as 

applicable, in accordance with Parts III and 

IV of the Accomplishment Instructions of 

Embraer Service Bulletin 190–54–0015, dated 

July 3, 2014. 

(i) For airplanes identified as Groups 1 and 

2 in Embraer Service Bulletin 190–54–0015, 


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Federal Register / Vol. 79, No. 158 / Friday, August 15, 2014 / Rules and Regulations 48021 

dated July 3, 2014: Retorque within 6,000 

flight cycles or 7,500 flight hours, whichever 

occurs first after replacement of the pylon 

outboard and inboard lower link fittings 

required by paragraph (h) of this AD, and 

thereafter at intervals not to exceed 6,000 

flight cycles or 7,500 flight hours, whichever 

occurs first. 

(ii) For airplanes identified as Group 3 in 

Embraer Service Bulletin 190–54–0015, dated 

July 3, 2014, and Model ERJ 190–100 STD, 

–100 LR, –100 IGW, –200 STD, –200 LR, and 

–200 IGW airplanes having serial numbers 

19000586 and subsequent: Retorque within 

6,000 flight cycles or 7,500 flight hours, 

whichever occurs first after the effective date 

of this AD, and thereafter at intervals not to 

exceed 6,000 flight cycles or 7,500 flight 

hours, whichever occurs first. 

(2) For Model ERJ 190–100 ECJ airplanes: 

Retorque as specified in paragraph (i)(2)(i) or 

(i)(2)(ii) of this AD, as applicable, in 

accordance with Parts III and IV of the 

Accomplishment Instructions of Embraer 

Service Bulletin 190LIN–54–0006, dated July 

3, 2014. 

(i) For airplanes identified as Groups 1 and 

2 in Embraer Service Bulletin 190LIN–54– 

0006, dated July 3, 2014: Retorque within 

2,000 flight cycles or 7,500 flight hours, 

whichever occurs first after replacement of 

the pylon outboard and inboard lower link 

fittings required by paragraph (h) of this AD, 

and thereafter at intervals not to exceed 2,000 

flight cycles or 7,500 flight hours, whichever 

occurs first. 

(ii) For airplanes identified as Group 3 in 

Embraer Service Bulletin 190LIN–54–0006, 

dated July 3, 2014, and Model ECJ airplanes 

having serial numbers 19000572 and 

subsequent: Retorque within 2,000 flight 

cycles or 7,500 flight hours, whichever 

occurs first after the effective date of this AD, 

and thereafter at intervals not to exceed 2,000 

flight cycles or 7,500 flight hours, whichever 

occurs first. 

(j) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install, at the inboard or 

outboard lower link fitting on any airplane, 

a lock assembly identified in Embraer Service 

Bulletin 190–54–0013, dated November 27, 

2012; or Embraer Service Bulletin 190LIN– 

54–0004, dated December 20, 2012. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using the service 

information specified in paragraphs (k)(1) 

through (k)(5) of this AD, as applicable. This 

service information is not incorporated by 

reference in this AD. 

(1) Embraer Alert Service Bulletin 190–54– 

A015, dated June 23, 2014. 

(2) Embraer Alert Service Bulletin 190–54– 

A015, Revision 01, dated June 26, 2014. 

(3) Embraer Alert Service Bulletin 190–54– 

A015, Revision 02, dated June 27, 2014. 

(4) Embraer Alert Service Bulletin 190LIN– 

54–A006, dated June 23, 2014. 

(5) Embraer Alert Service Bulletin 190LIN– 

54–A006, Revision 01, dated June 26, 2014. 

(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, 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: 

Kathrine Rask, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; telephone 425– 

227–2180; fax 425–227–1149. Information 

may be emailed to 9-ANM-116-AMOCREQUESTS@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 

ANAC; or ANAC’s authorized Designee. If 

approved by the ANAC Designee, the 

approval must include the Designee’s 

authorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Brazilian 

Airworthiness Directive 2014–07–01, dated 

July 10, 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–2014–0531. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (n)(3) and (n)(4) of this AD. 

(n) 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) Embraer Alert Service Bulletin 190–54– 

A015, Revision 03, dated June 27, 2014. 

(ii) Embraer Alert Service Bulletin 190LIN– 

54–A006, Revision 02, dated June 27, 2014. 

(iii) Embraer Service Bulletin 190–54– 

0013, dated November 27, 2012. 

(iv) Embraer Service Bulletin 190–54–0015, 

dated July 3, 2014. 

(v) Embraer Service Bulletin 190LIN–54– 

0004, dated December 20, 2012. 

(vi) Embraer Service Bulletin 190LIN–54– 

0006, dated July 3, 2014. 

(3) For service information identified in 

this AD, contact Embraer S.A., Technical 

Publications Section (PC 060), Av. Brigadeiro 

Faria Lima, 2170—Putim—12227–901 Sa ̃o 

Jose dos Campos—SP—Brasil; telephone +55 

12 3927–5852 or +55 12 3309–0732; fax +55 

12 3927–7546; email distrib@embraer.com.br; 

Internet http://www.flyembraer.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. 

Issued in Renton, Washington, on August 

6, 2014. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–19263 Filed 8–14–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0121; Directorate 

Identifier 2013–NM–151–AD; Amendment 

39–17928; AD 2014–16–04] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2008–14– 

17 for certain Airbus Model A330–200 

and A340–300 series airplanes. AD 

2008–14–17 required a high frequency 

eddy current (HFEC) inspection, 

corrective actions if necessary, and 

modifications. This new AD requires the 

same actions as those required by AD 

2008–14–17, but with a reduced 

compliance time. This AD was 

prompted by a determination from a 

fatigue and damage tolerance evaluation 

that the compliance time needs to be 

revised. We are issuing this AD to detect 

and correct damage of the upper shell 

structure at the skin and frame interface, 

which could result in reduced structural 

integrity of the airframe. 

DATES: This AD becomes effective 

September 19, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 19, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 


emcdonald on DSK67QTVN1PROD with RULES