49702 Federal Register / Vol. 77, No. 160 / Friday, August 17, 2012 / Rules and Regulations 

1Coughlin, Katie (2012). A Mathematical 

Analysis of Full Fuel Cycle Energy Use. Energy, 

Volume 37, Issue 1, January 2012, Pages 698–708. 

products to the end user. Each of these 

process steps consumes energy in the 

form of diesel or fuel oil, natural gas, or 

grid electricity. The data are used to 

estimate an intensity parameter for each 

fuel type, which is equal to the total 

amount of that fuel needed to produce 

one unit of the final product. The FFC 

energy and emissions factors are defined 

as a function of these parameters, using 

a formula that is described in detail in: 

‘‘A Mathematical Analysis of Full Fuel 

Cycle Energy Use’’; [http:// 

www.sciencedirect.com/science/article/ 

pii/S0360544211006803] 1 Energy, 

Volume 37, Issue 1, January 2012, Pages 

698–708; 

By using the FFC multipliers derived 

from NEMS, DOE would be able to 

ensure that the assumptions and inputs 

used in FFC analyses are consistent 

with the assumptions and inputs used 

to estimate primary energy savings and 

emissions impacts. In addition, this 

approach would make it easier for DOE 

to update the multipliers with each new 

edition of the AEO. The GREET model, 

in contrast, uses a representation of the 

energy production system to develop its 

own internal projections, which 

inevitably will differ some from those in 

the AEO. 

Based on this assessment, DOE is 

proposing to use this NEMS-based 

approach to estimating the FFC energy 

and emission impacts of alternative 

energy conservation standards levels in 

energy conservation standards 

rulemakings that reach the notice of 

proposed rulemaking (NOPR) stage after 

August 17, 2012. Rulemakings that do 

not reach the NOPR stage before August 

17, 2012 will continue to use the 

estimates of primary energy and 

emission impacts described in the 

notices of proposed rulemaking. DOE 

has not used the GREET model to 

estimate FFC energy and emission 

impacts in any past or current 

rulemakings but has started to use the 

NEMS-based approach to estimating 

these impacts in several energy 

conservation standards preliminary 

analyses. 

II. Public Participation 

DOE invites all interested parties to 

submit comments on this issue in 

writing at any time. In addition, 

interested parties will have an 

opportunity to review and comment on 

the specific methodologies employed by 

DOE to calculate FFC energy and 

emission impacts in NOPRs. See the 

ADDRESSES section of this notice for 

more information on how to submit a 

comment. 

III. Procedural Issues and Regulatory 

Review 

A. Review Under the National 

Environmental Policy Act 1969 

DOE has determined that this policy 

amendment falls into a class of actions 

that are categorically excluded from 

review under the National 

Environmental Policy Act of 1969 (42 

U.S.C. 4321 et seq.) and DOE’s 

implementing regulations at 10 CFR part 

1021. Specifically, this policy 

amendment describes methods for data 

analysis and how DOE plans to 

incorporate such data analysis into 

future energy conservation standards. 

For this reason, and because the policy 

amendment does not establish an energy 

conservation standard or take any action 

that might have an impact on the 

environment, it is covered by the 

Categorical Exclusion A9 under 10 CFR 

part 1021, subpart D. Accordingly, 

neither an environmental assessment 

nor an environmental impact statement 

is required. 

B. Review Under the Information 

Quality Bulletin for Peer Review 

In consultation with the Office of 

Science and Technology Policy (OSTP), 

OMB issued on December 16, 2004, its 

‘‘Final Information Quality Bulletin for 

Peer Review’’ (the Bulletin). 70 FR 2664 

(Jan. 14, 2005). The Bulletin establishes 

that certain scientific information shall 

be peer reviewed by qualified specialists 

before it is disseminated by the Federal 

government, including influential 

scientific information related to agency 

regulatory actions. The purpose of the 

Bulletin is to enhance the quality and 

credibility of the government’s scientific 

information. Under the Bulletin, NEMS 

is ‘‘influential scientific information,’’ 

which the Bulletin defines as ‘‘scientific 

information that the agency reasonably 

can determine will have or does have a 

clear and substantial impact on 

important public policies or private 

sector decisions.’’ 70 FR 2664, 2667 

(Jan. 14, 2005). The NEMS model, 

which is in the public domain, has been 

reviewed through its development and 

applications over the past 18 years. 

IV. Approval of the Office of the 

Assistant Secretary 

The Assistant Secretary of DOE’s 

Office of Energy Efficiency and 

Renewable Energy has approved 

publication of this final policy. 

Issued in Washington, DC, on August 9, 

2012. 

Kathleen B. Hogan, 

Deputy Assistant Secretary for Energy 

Efficiency, Energy Efficiency and Renewable 

Energy. 

[FR Doc. 2012–20122 Filed 8–16–12; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0423; Directorate 

Identifier 2011–NM–095–AD; Amendment 

39–17156; AD 2012–16–09] 

RIN 2120–AA64 

Airworthiness Directives; Embraer S.A. 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding two 

existing airworthiness directives (AD) 

for all Embraer S.A. Model ERJ 170 and 

ERJ 190 airplanes. Those ADs currently 

require revising the airplane flight 

manual (AFM) to introduce limitations 

for the use of auxiliary power unit 

(APU) bleed and to prohibit dispatch 

with a failed air management system 

(AMS) controller card. This new AD 

requires replacing the AMS controller 

processor module with one containing 

new software, and a new AFM revision. 

This AD was prompted by reports of the 

possible loss of automatic activation of 

the engine inlet ice protection system. 

We are issuing this AD to prevent the 

possibility of a right-hand (RH) engine 

compressor stall after the APU becomes 

the active bleed source for the left side, 

which may result in an engine failure; 

and to prevent the intermittent 

communication failure between the 

AMS controller cards and both 

secondary power distribution 

assemblies (SPDAs), which could lead 

to the loss of automatic activation of the 

engine inlet ice protection system when 

flying in icing conditions, which could 

result in ice accretion in the engine inlet 

and subsequent dual engine failure. 

DATES: This AD becomes effective 

September 21, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 21, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 160 / Friday, August 17, 2012 / Rules and Regulations 49703 

as of September 9, 2010 (75 FR 52238, 

August 25, 2010). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Cindy Ashforth, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

227–2768; fax: 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on May 1, 2012 (77 FR 25644), 

and proposed to supersede AD 2010– 

07–04, Amendment 39–16248 (75 FR 

14333, March 25, 2010); and AD 2010– 

18–01, Amendment 39–16414 (75 FR 

52238, August 25, 2010). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states: 

This [Ageˆncia Nacional de Aviac ̧a ̃o Civil 

(ANAC)] AD results from the possibility of 

loss of automatic activation of the engine 

inlet ice protection system when flying in ice 

condition. Even though the failure is 

announced by the caution messages ‘‘A–I Eng 

1 Fail’’ [and] ‘‘A–I Eng 2 Fail’’, if the engines 

inlet ice protection system is not manually 

activated, ice may accrete in the engine inlet 

and causes engine to shut down. 

Also there is the possibility of right hand 

(RH) engine compressor to stall after the 

Auxiliary Power Unit (APU) becomes the 

active bleed source for the left side, following 

left hand (LH) engine failure, under a 

condition where both engines are close to 

idle, the APU is running, and the APU bleed 

button is pushed in (automatic position). 

The required actions include replacing 

the AMS controller processor module 

with one containing new software and 

revising the Limitations section of the 

AFM. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. The 

Air Line Pilots Association, 

International (ALPA) stated that it fully 

supports the NPRM (77 FR 25644, May 

1, 2012). 

Explanation of Change Made to the AD 

We have revised this AD to identify 

the legal name of the manufacturer as 

published in the most recent type 

certificate data sheet for the affected 

airplane models. 

Conclusion 

We reviewed the available data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously— 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

25644, May 1, 2012) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 25644, 

May 1, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

about 253 products of U.S. registry. 

The actions that are required by AD 

2010–07–04, Amendment 39–16248 (75 

FR 14333, March 25, 2010); and AD 

2010–18–01, Amendment 39–16414 (75 

FR 52238, August 25, 2010); and that are 

retained in this AD take about 1 workhour per product, at an average labor 

rate of $85 per work-hour. Based on 

these figures, the estimated cost of the 

currently required actions is $85 per 

product. 

We estimate that it will take about 1 

work-hour per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Required parts will cost about $35 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$30,360, or $120 per product. 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; 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 the NPRM (77 FR 25644, May 

1, 2012), 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. 

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: 


tkelley on DSK3SPTVN1PROD with RULES
49704 Federal Register / Vol. 77, No. 160 / Friday, August 17, 2012 / Rules and Regulations 

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 

2010–07–04, Amendment 39–16248 (75 

FR 14333, March 25, 2010); and AD 

2010–18–01, Amendment 39–16414 (75 

FR 52238, August 25, 2010); and adding 

the following new AD: 

2012–16–09 Embraer S.A.: Amendment 39– 

17156. Docket No. FAA–2012–0423; 

Directorate Identifier 2011–NM–095–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective September 21, 2012. 

(b) Affected ADs 

This AD supersedes AD 2010–07–04, 

Amendment 39–16248 (75 FR 14333, March 

25, 2010); and AD 2010–18–01, Amendment 

39–16414 (75 FR 52238, August 25, 2010). 

(c) Applicability 

This AD applies to Embraer S.A. Model 

ERJ 170–100 LR, –100 STD, –100 SE., and 

–100 SU airplanes; Model ERJ 170–200 LR, 

–200 SU, and –200 STD airplanes; Model ERJ 

190–100 STD, –100 LR, –100 ECJ, and –100 

IGW airplanes; and Model ERJ 190–200 STD, 

–200 LR, and –200 IGW airplanes; 

certificated in any category; all serial 

numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 21: Air Conditioning. 

(e) Reason 

This AD was prompted by reports of the 

possible loss of automatic activation of the 

engine inlet ice protection system. We are 

issuing this AD to prevent the possibility of 

a right-hand (RH) engine compressor stall 

after the auxiliary power unit (APU) becomes 

the active bleed source for the left side, 

which may result in an engine failure; and 

to prevent the intermittent communication 

failure between the air management system 

(AMS) controller cards and both secondary 

power distribution assemblies (SPDAs), 

which could lead to the loss of automatic 

activation of the engine inlet ice protection 

system when flying in icing conditions, 

which could result in ice accretion in the 

engine inlet and subsequent dual engine 

failure. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Revision for Certain Airplanes 

This paragraph restates the requirements of 

paragraph (g) of AD 2010–07–04, 

Amendment 39–16248 (75 FR 14333, March 

25, 2010). For airplanes equipped with AMS 

controller cards having part number (P/N) 

1001050–1–YYY or 1001050–2–YYY 

containing software version Black Label 08 or 

lower installed: Within 10 days after April 9, 

2010 (the effective date of AD 2010–07–04), 

revise the Limitations section of the AFM to 

include the following statement. This may be 

done by inserting a copy of this AD in the 

AFM. Doing the actions required by 

paragraph (i) of this AD terminates the 

requirements of this paragraph. 

Dispatch with the message ‘RECIRC SMK 

DET FAIL’ displayed on the ground is 

prohibited unless troubleshooting action 

confirms the message has not been triggered 

due to a failure of an AMS controller card. 

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

a statement identical to that in paragraph (g) 

of this AD has been included in the general 

revisions of the AFM, the general revisions 

may be inserted into the AFM, and the copy 

of this AD may be removed from the AFM. 

(h) Retained AFM Revision for All Airplanes 

This paragraph restates the requirements of 

paragraph (g) of AD 2010–18–01, 

Amendment 39–16414 (75 FR 52238, August 

25, 2010). For all airplanes: Within 14 days 

after September 9, 2010 (the effective date of 

AD 2010–18–01), revise the Limitations 

section of the applicable AFM to include the 

information in EMBRAER Operational 

Bulletin 170–001/09, Revision 1, dated 

February 10, 2010, as specified in the 

operational bulletin. This operational 

bulletin introduces limitations for the use of 

APU bleed. Doing the actions required by 

paragraph (i) of this AD terminates the 

requirements of this paragraph. 

Note 2 to paragraph (h) of this AD: This 

may be done by inserting a copy of 

EMBRAER Operational Bulletin 170–001/09, 

Revision 1, dated February 10, 2010, into the 

AFM. When this operational bulletin has 

been included in general revisions of the 

AFM, the general revisions may be inserted 

in the AFM, provided the relevant 

information in the general revision is 

identical to that in the operational bulletin, 

and the operational bulletin can be removed. 

(i) New Requirement of This AD: Load 

Software or Replace AMS Controller Module 

Within 3,300 flight hours after the effective 

date of this AD: Replace existing Hamilton 

Sundstrand AMS controller processor 

modules (slots 18 and 25) P/N 1001050–1– 

YYY, 1001050–2–YYY, 1001050–3–YYY, or 

1001050–4–YYY, with a new or serviceable 

AMS controller processor module containing 

software version Black Label—11, or later 

approved version of the software, in 

accordance with the Accomplishment 

Instructions of Embraer Service Bulletin 170– 

21–0049, dated November 29, 2010 (for 

Model ERJ 170 airplanes); Embraer Service 

Bulletin 190–21–0035, dated November 29, 

2010 (for Model ERJ 190 airplanes); or 

Embraer Service Bulletin 190LIN–21–0016, 

dated February 23, 2011 (for Model ERJ 190– 

100 ECJ airplanes). 

(j) Definition 

For the purposes of this AD, ‘‘laterapproved version of the software,’’ is defined 

as software having design approval holder 

(DAH) design changes that have been 

approved after the publication of Embraer 

Service Bulletin 170–21–0049, dated 

November 29, 2010 (for Model ERJ 170 

airplanes); Embraer Service Bulletin 190–21– 

0035, dated November 29, 2010 (for Model 

ERJ 190 airplanes); and Embraer Service 

Bulletin 190LIN–21–0016, dated February 23, 

2011 (for Model ERJ 190–100 ECJ airplanes). 

(k) New Requirement of This AD: Revise 

Limitations Section of AFM 

After doing the actions required by 

paragraph (i) of this AD, before further flight, 

revise the Limitations section of the 

applicable AFM by removing the limitation 

required by paragraph (g) of this AD and the 

revision required by paragraph (h) of this AD. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: 

Cindy Ashforth, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–227–2768; 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 or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(m) Related Information 

Refer to MCAI Brazilian ADs 2011–05–01 

and AD 2011–05–02, both dated May 9, 2011, 

and the service information specified in 

paragraphs (m)(1), (m)(2), (m)(3) and (m)(4) of 

this AD, for related information. 

(1) EMBRAER Operational Bulletin 170– 

001/09, Revision 1, dated February 10, 2010. 

(2) Embraer Service Bulletin 170–21–0049, 

dated November 29, 2010. 

(3) Embraer Service Bulletin 190–21–0035, 

dated November 29, 2010. 

(4) Embraer Service Bulletin 190LIN–21– 

0016, dated February 23, 2011. 

(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 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 160 / Friday, August 17, 2012 / Rules and Regulations 49705 

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 the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on September 21, 2012. 

(i) Embraer Service Bulletin 170–21–0049, 

dated November 29, 2010. 

(ii) Embraer Service Bulletin 190–21–0035, 

dated November 29, 2010. 

(iii) Embraer Service Bulletin 190LIN–21– 

0016, dated February 23, 2011. 

(4) The following service information was 

approved for IBR on September 9, 2010 (75 

FR 52238, August 25, 2010). 

(i) EMBRAER Operational Bulletin 170– 

001/09, Revision 1, dated February 10, 2010. 

(ii) Reserved. 

(5) 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. 

(6) You may review copies of the 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. 

(7) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on July 31, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–19396 Filed 8–16–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0659; Directorate 

Identifier 2011–SW–061–AD; Amendment 

39–17101; AD 2012–12–21] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments; correction. 

SUMMARY: The FAA is correcting an 

airworthiness directive (AD) that was 

published in the Federal Register. That 

AD applies to Eurocopter Deutschland 

GmbH Model MBB–BK 117 C–2 

helicopters. A page reference of the 

rotorcraft flight manual in the Required 

Actions section, paragraph (e)(1)(i), is 

incorrect. This document corrects that 

error. In all other respects, the original 

document remains the same. 

DATES: This correction is effective 

August 17, 2012. The effective date for 

AD 2012–12–21 remains July 10, 2012. 

The last date for submitting comments 

to the final rule; request for comments 

remains August 24, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov; 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, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

George Schwab, Aviation Safety 

Engineer, FAA, Rotorcraft Directorate, 

Safety Management Group, 2601 

Meacham Blvd., Fort Worth, TX 76137, 

telephone (817) 222–5110, email: 

george.schwab@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Airworthiness Directive 2012–12–21, 

Amendment 39–17101 (77 FR 37777, 

June 25, 2012), currently includes the 

following paragraph (e)(1)(i) in the 

Required Actions section: 

‘‘(i) ‘‘Emergency and Malfunction 

Procedures’’: pages 3–3 and 3–4, and’’ 

As published, the reference to page 3– 

4 is incorrect. The correct reference is to 

page 3–3a. 

No other part of the preamble or 

regulatory information has been 

changed; therefore, only the changed 

portion of the final rule is being 

published in the Federal Register. 

Correction of Regulatory Text 

§ 39.13 [Corrected] 

In the Federal Register of June 25, 

2012, on page 37779 in the second 

column, paragraph (e)(1)(i) of AD 2012– 

12–21 is corrected to read as follows: 

* * * * * 

(i) ‘‘Emergency and Malfunction 

Procedures’’: pages 3–3 and 3–3a, and 

* * * * * 

Issued in Fort Worth, Texas, on August 9, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–20177 Filed 8–16–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0291; Directorate 

Identifier 2011–NM–168–AD; Amendment 

39–17158; AD 2012–16–11] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A318–112 and –121 

airplanes; Model A319–111, –112, –115, 

–132, and –133 airplanes; Model A320– 

214, –232, and –233 airplanes; and 

Model A321–211, –212, –213, and –231 

airplanes. This AD was prompted by 

reports that some nuts installed on the 

wing, including on primary structural 

elements, were found cracked. This AD 

requires inspecting to determine if 

certain nuts are installed or cracked, 

and replacing the affected nuts if 

necessary. We are issuing this AD to 

detect and correct missing and cracked 

nuts, which could result in the 

structural integrity of the airplane wings 

being impaired. 

DATES: This AD becomes effective 

September 21, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 21, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1405; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 


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