74722 Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification 

For Embraer S.A. Model ERJ 190 airplanes 

identified in Embraer Service Bulletin 190– 

21–0041, Revision 02, dated July 30, 2013, 

within 3 months after the effective date of 

this AD, replace the Hamilton Sundstrand air 

management system (AMS) controller 

operation program of the AMS controller 

processor boards, as specified in paragraph 

(g)(1) or (g)(2) of this AD. 

(1) Replace with a new, improved program, 

in accordance with the Accomplishment 

Instructions of Embraer Service Bulletin 190– 

21–0041, Revision 02, dated July 30, 2013. 

(2) Replace with a version of the Hamilton 

Sundstrand AMS controller operation 

program approved after August 31, 2012, 

using a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; Ageˆncia Nacional 

de Aviac ̧a ̃o Civil (ANAC); or ANAC’s 

authorized Designee. 

(h) Valve Replacement 

For Embraer S.A. Model ERJ 190 airplanes 

identified in Embraer Service Bulletin 190– 

21–0041, Revision 02, dated July 30, 2013, 

within 3 months after the effective date of 

this AD, and after accomplishment of the 

actions required by paragraph (g) of this AD: 

Replace the check valve and associated seals 

of the left-hand and right-hand engine bleed 

system with a check valve identified in 

paragraph (i) of this AD, and new seals, in 

accordance with the Accomplishment 

Instructions of Embraer Service Bulletin 190– 

36–0023, Revision 03, dated September 24, 

2014. 

(i) Allowed Valves 

When complying with paragraph (h) of this 

AD, the low-stage bleed check valves having 

P/N 1001447–6, and associated seals, are 

replaced with new ones (zero-hour). Lowstage bleed check valves having P/N 

1001447–6 that can be demonstrated with 

logged hours only on ERJ–170 aircraft and/ 

or on ERJ–190 aircraft equipped with the 

AMS Controller Operational Program version 

Black Label 13, or a later version, can be used 

instead of new ones (zero-hour). 

(j) Parts Installation Limitation 

(1) For Model ERJ 170–100 STD, –100 LR, 

–100SU, –100SE, –200 STD, –200 LR, and 

–200 SU airplanes: No person may install on 

any airplane a low-stage bleed check valve 

having P/N 1001447–6 that was installed on 

any Model ERJ 190–100 STD, –100 LR, –100 

IGW, –200 STD, –200 LR, or –200 IGW 

airplane, any serial number except 190– 

00587, 190–00589, and 190–00593 and 

subsequent, prior to accomplishment of 

paragraph (g) of this AD. 

(2) For Model ERJ 190–100 STD, –100 LR, 

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

airplanes: No person may install on any 

airplane on which the actions of paragraph 

(g) of this AD have been done, a low-stage 

bleed check valve having P/N 1001447–6 that 

was previously installed on any Model ERJ 

190–100 STD, –100 LR, –100 IGW, –200 STD, 

–200 LR, or –200 IGW airplane, any serial 

number except 190–00587, 190–00589, 190– 

00593 and subsequent, prior to 

accomplishment of paragraph (g) of this AD. 

(k) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using the service 

information identified in paragraph (k)(1)(i) 

or (k)(1)(ii) of this AD. This service 

information is not incorporated by reference 

in this AD. 

(i) Embraer Service Bulletin 190–21–0041, 

dated September 27, 2012. 

(ii) Embraer Service Bulletin 190–21–0041, 

Revision 01, dated December 20, 2012. 

(2) This paragraph provides credit for 

actions required by paragraph (h) of this AD, 

if those actions were performed before the 

effective date of this AD using the service 

information identified in paragraph (k)(2)(i), 

(k)(2)(ii), or (k)(2)(iii) of this AD. This service 

information is not incorporated by reference 

in this AD. 

(i) Embraer Service Bulletin 190–36–0023, 

dated July 22, 2013. 

(ii) Embraer Service Bulletin 190–36–0023, 

Revision 01, dated September 3, 2013. 

(iii) Embraer Service Bulletin 190–36– 

0023, Revision 02, dated April 30, 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: 

Ana Martinez Hueto, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1622; 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) 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 2015–02–02, dated 

March 6, 2015, 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 Docket No. FAA– 

2015–6542. 

(2) 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. 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 

November 20, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–30224 Filed 11–27–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1014; Directorate 

Identifier 2015–NE–14–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Proposed rule; withdrawal. 

SUMMARY: The FAA is withdrawing a 

notice of proposed rulemaking (NPRM). 

The NPRM proposed a new 

airworthiness directive (AD) that had 

applied to all Rolls-Royce Deutschland 

Ltd & Co KG (RRD) Tay 650–15 and Tay 

651–54 turbofan engines. The proposed 

action would have required reducing 

the cyclic life limits for certain highpressure turbine (HPT) disks. 

Accordingly, we withdraw the proposed 

rule. 

DATES: The proposed rule published in 

the Federal Register on June 8, 2015 (80 

FR 32315, June 8, 2015) is withdrawn as 

of November 30, 2015. 

FOR FURTHER INFORMATION CONTACT: 

Philip Haberlen, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7770; fax: 781–238– 

7199; email: philip.haberlen@faa.gov. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 


jstallworth on DSK7TPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules 74723 

a proposed AD (80 FR 32315, June 8, 

2015). The proposed AD had applied to 

Rolls-Royce Deutschland Ltd & Co KG 

(RRD) Tay 650–15 and Tay 651–54 

turbofan engines. The NPRM proposed 

to reduce the cyclic life limits for 

certain HPT disks. The proposed action 

was prompted by an analysis that 

showed the need to reduce the cyclic 

life limits for certain HPT disks. The 

proposed actions intended to prevent 

failure of the HPT disk, which could 

result in uncontained disk release, 

damage to the engine, and damage to the 

airplane. 

Since we issued the NPRM (80 FR 

32315, June 8, 2015), additional 

information became available after the 

public comment period closed on 

August 7, 2015. 

Upon further consideration, we 

hereby withdraw the proposed rule 

because we will propose to supersede 

AD 2006–18–14 (71 FR 52988, 

September 8, 2006). 

Withdrawal of the NPRM (80 FR 

32315, June 8, 2015) constitutes only 

such action, and does not preclude the 

agency from issuing another notice in 

the future, nor does it commit the 

agency to any course of action in the 

future. 

Since this action only withdraws a 

notice of proposed rulemaking, it is 

neither a proposed nor a final rule. 

Therefore, Executive Order 12866, the 

Regulatory Flexibility Act, or DOT 

Regulatory Policies and Procedures (44 

FR 11034, February 26, 1979) do not 

cover this withdrawal. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Withdrawal 

Accordingly, the notice of proposed 

rulemaking, Docket No. FAA–2015– 

1014; Directorate Identifier 2015–NE– 

14–AD, published in the Federal 

Register on June 8, 2015 (80 FR 32315), 

is withdrawn. 

Issued in Burlington, Massachusetts, on 

November 20, 2015. 

Colleen M. D’Alessandro, 

Directorate Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–30010 Filed 11–27–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–6539; Directorate 

Identifier 2015–NM–036–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 A318–111 and –112 

airplanes; Model A319–111, –112, –113, 

–114, and –115 airplanes; Model A320– 

211, –212, and –214 airplanes; and 

Model A321–111, –112, –211, –212, and 

–213 airplanes. This proposed AD was 

prompted by an evaluation by the 

design approval holder (DAH) 

indicating that the forward engine 

mounts are subject to widespread 

fatigue damage (WFD). This proposed 

AD would require repetitive detailed 

inspections of the right and left forward 

engine mounts, and corrective action if 

necessary. These inspections are 

required by AD 2015–05–02. This 

proposed AD would reduce the 

compliance times for those inspections. 

We are proposing this AD to detect and 

correct fatigue cracking in the forward 

engine mounts, which could result in 

reduced structural integrity of the 

airplane and could lead to in-flight loss 

of an engine, possibly resulting in 

reduced controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by January 14, 2016. 

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 proposed AD, contact Airbus, 

Airworthiness Office—EIAS, 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–2015– 

6539; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–6539; Directorate Identifier 

2015–NM–036–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 

Structural fatigue damage is 

progressive. It begins as minute cracks, 

and those cracks grow under the action 

of repeated stresses. This can happen 

because of normal operational 

conditions and design attributes, or 


jstallworth on DSK7TPTVN1PROD with PROPOSALS