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contains regulatory documents having general

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are keyed to and codified in the Code of

Federal Regulations, which is published under

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Rules and Regulations Federal Register

2195 

Vol. 78, No. 7 

Thursday, January 10, 2013 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1202; Directorate 

Identifier 2012–NE–38–AD; Amendment 39– 

17309; AD 2012–26–14] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Rolls-Royce Deutschland Ltd & Co KG 

BR700–715A1–30, BR700–715B1–30, 

and BR700–715C1–30 turbofan engines. 

This AD requires a one-time removal 

from service of the high-pressure (HP) 

compressor stages 1 to 6 rotor disc 

assembly before exceeding certain 

thresholds. This AD was prompted by a 

report of silver chloride-induced stress 

corrosion cracking of the HP compressor 

stages 1 to 6 rotor disc assembly, 

identified during overhaul. We are 

issuing this AD to prevent failure of the 

HP compressor stages 1 to 6 rotor disc 

assembly, which could result in 

uncontained failure of the engine and 

damage to the airplane. 

DATES: This AD becomes effective 

January 10, 2013. 

We must receive comments on this 

AD by February 25, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: 202–493–2251. 

For service information identified in 

this AD, contact Rolls-Royce 

Deutschland Ltd & Co KG, Eschenweg 

11, Dahlewitz, 15827 BlankenfeldeMahlow, Germany; telephone: 49 0 33– 

7086–1883; fax: 49 0 33–7086–3276. 

You may view copies of the referenced 

service information at the FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803. 

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; 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 (phone: 

800–647–5527) is the same as the Mail 

address provided in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7779; fax: 781–238– 

7199; email: frederick.zink@faa.gov. 

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 2012–0230, 

dated October 30, 2012 (referred to 

hereinafter as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Silver chloride-induced stress corrosion 

cracking was identified during overhaul of a 

BR700–715 engine, on the High Pressure 

Compressor (HPC) stages 1 to 6 rotor disc 

assembly. Subsequent evaluation concluded 

that the affected part life limitation values 

declared in the engine Time Limits Manual 

cannot be supported for high cyclic life HPC 

discs. 

This condition, if not corrected, could lead 

to uncontained HPC disc failure, possibly 

resulting in damage to, and/or reduced 

control of the aeroplane. 

You may obtain further information by 

examining the MCAI in the AD docket. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of Germany, and 

is approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Germany, they have 

notified us of the unsafe condition 

described in the MCAI referenced 

above. We are issuing this AD because 

we evaluated all information provided 

by EASA and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. This AD requires a onetime removal from service of the HP 

compressor stages 1 to 6 rotor disc 

assembly before exceeding certain 

thresholds. 

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 of the short compliance 

times for HP compressor stages 1 to 6 

rotor disc assemblies that are at or over 

the removal thresholds. 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–2012–1202; 

Directorate Identifier 2012–NE–38–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 


wreier-aviles on DSK5TPTVN1PROD with 
2196 Federal Register / Vol. 78, No. 7 / Thursday, January 10, 2013 / Rules and Regulations 

received by the closing date and may 

amend this AD because of 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 with FAA 

personnel concerning this AD. Using the 

search function of the Web site, anyone 

can find and read the comments in any 

of our dockets, including, if provided, 

the name of the individual who sent the 

comment (or signed the comment on 

behalf of an association, business, labor 

union, etc.). You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

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 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); and 

3. 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. 

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 AD: 

2012–26–14 Rolls-Royce Deutschland Ltd & 

Co KG (Formerly Rolls-Royce 

Deutschland GmbH, formerly BMW 

Rolls-Royce GmbH): Amendment 39– 

17309; Docket No. FAA–2012–1202; 

Directorate Identifier 2012–NE–38–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective January 10, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Rolls-Royce 

Deutschland Ltd & Co KG BR700–715A1–30, 

BR700–715B1–30, and BR700–715C1–30 

turbofan engines. 

(d) Reason 

This AD was prompted by a report of silver 

chloride-induced stress corrosion cracking of 

the high-pressure (HP) compressor stages 1 to 

6 rotor disc assembly, identified during 

overhaul. We are issuing this AD to prevent 

failure of the HP compressor stages 1 to 6 

rotor disc assembly, which could result in 

uncontained failure of the engine and 

damage to the airplane. 

(e) Actions and Compliance 

Unless already done, do the following 

actions. 

(1) BR700–715A1–30 Turbofan Engines 

Operated Under the Hawaiian Flight 

Mission Only 

For BR700–715A1–30 turbofan engines 

operated under the Hawaiian Flight Mission 

only, do the following: 

(1) If the HP compressor stages 1 to 6 rotor 

disc assembly has accumulated 15,700 flight 

cycles since new or fewer on the effective 

date of this AD, remove the rotor disc 

assembly from service before exceeding 

16,000 flight cycles since new (CSN). 

(2) If the HP compressor stages 1 to 6 rotor 

disc assembly has accumulated more than 

15,700 flight CSN on the effective date of this 

AD, remove the rotor disc assembly from 

service within 300 flight cycles. 

(2) BR700–715A1–30, BR700–715B1–30, and 

BR700–715C1–30 Turbofan Engines (All 

Flight Missions Except the Hawaiian Flight 

Mission) 

For BR700–715A1–30, BR700–715B1–30, 

and BR700–715C1–30 turbofan engines (all 

flight missions except the Hawaiian Flight 

Mission), do the following: 

(1) If the HP compressor stages 1 to 6 rotor 

disc assembly has accumulated 13,700 flight 

CSN or fewer on the effective date of this AD, 

remove the rotor disc assembly from service 

before exceeding 14,000 flight CSN. 

(2) If the HP compressor stages 1 to 6 rotor 

disc assembly has accumulated more than 

13,700 flight cycles since new on the 

effective date of this AD, remove the rotor 

disc assembly from service within 300 flight 

cycles. 

(f) Terminating Action 

Performing the one-time removal from 

service of the stages 1 to 6 rotor disc 

assembly, as specified in this AD, is 

terminating action to this AD. 

(g) Definition 

For the purpose of this AD, flight cycles is 

the total flight CSN on the HP compressor 

stages 1 to 6 rotor disc assembly, without any 

pro-rated calculations applied for different 

flight missions. Guidance on calculating total 

flight cycles can be found in Rolls-Royce 

Deutschland Ltd & Co KG Notice to Operators 

BR715 engines NTO: No. 184, dated October 

25, 2012. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(i) Related Information 

(1) For more information about this AD, 

contact Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7779; fax: 781–238–7199; 

email: frederick.zink@faa.gov. 

(2) Refer to European Aviation Safety 

Agency AD 2012–0230, dated October 30, 

2012, and Rolls-Royce Deutschland Ltd & Co 

KG Alert Service Bulletin No. SB–BR700–72– 

A900401, dated October 25, 2012, for related 

information. 

(3) For service information identified in 

this AD, contact Rolls-Royce Deutschland Ltd 

& Co KG, Eschenweg 11, Dahlewitz, 15827 

Blankenfelde-Mahlow, Germany; telephone: 

49 0 33–7086–1883; fax: 49 0 33–7086–3276. 

You may view copies of the referenced 

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. 


wreier-aviles on DSK5TPTVN1PROD with 
Federal Register / Vol. 78, No. 7 / Thursday, January 10, 2013 / Rules and Regulations 2197 

Issued in Burlington, Massachusetts, on 

December 27, 2012. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–31588 Filed 1–9–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1350; Directorate 

Identifier 2012–NE–40–AD; Amendment 39– 

17313; AD 2012–27–01] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Rolls-Royce Deutschland Ltd & Co KG 

(RRD) Model Tay 620–15 turbofan 

engines. This AD requires a one-time 

inspection of the low-pressure 

compressor (LPC) fan blades and if 

erosion is found their replacement 

before further flight. This AD was 

prompted by evidence of excessive 

leading edge erosion of the LPC fan 

blades on certain Tay 620–15 engines. 

We are issuing this AD to prevent 

failure of the LPC fan blade, which 

could result in uncontained engine 

failure and damage to the airplane. 

DATES: This AD becomes effective 

January 25, 2013. 

We must receive comments on this 

AD by February 25, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: 202–493–2251. 

For service information identified in 

this AD, contact Rolls-Royce 

Deutschland Ltd & Co KG, Eschenweg 

11, Dahlewitz, 15827 BlankenfeldeMahlow, Germany; phone: 49 0 33– 

7086–1883; fax: 49 0 33–7086–3276. 

You may view this service information 

at the FAA, Engine & Propeller 

Directorate, 12 New England Executive 

Park, Burlington, MA 01803. 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; 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 (phone: 

800–647–5527) is the same as the Mail 

address provided in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7779; fax: 781–238– 

7199; email: frederick.zink@faa.gov. 

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 

Emergency Airworthiness Directive 

2012–0234, dated November 6, 2012 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

The Low Pressure Compressor (LPC) (fan) 

blades of certain Tay 620/15/20 and Tay 620– 

15 engines show evidence of excessive 

leading edge erosion. Excessive material 

removal during the maintenance reduces the 

LPC (fan) blade chordal width and 

potentially changes the balance of the fan 

blade. Reduced chordal width can affect LPC 

(fan) blade performance and in combination 

with other circumstances could lead to a fan 

blade root failure and fan blade separation. 

This condition, if not detected and corrected, 

could lead to the LPC (fan) blade failure, 

potentially causing release of high-energy 

debris, possibly resulting in damage to the 

aeroplane and/or injury to the occupants. 

We are issuing this AD to prevent 

failure of the LPC fan blade, which 

could result in uncontained engine 

failure and damage to the airplane. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

RRD has issued Alert NonModification Service Bulletin TAY–72– 

A1777, dated October 26, 2012. 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 

Germany and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the European 

Community, EASA has notified us of 

the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all 

information provided by EASA and 

determined the unsafe condition exists 

and is likely to exist or develop on other 

products of the same type design. This 

AD requires a one-time inspection of the 

LPC fan blades and if erosion is found 

their replacement before further flight. 

FAA’s Determination of the Effective 

Date 

No domestic operators use this 

product. Therefore, we find that notice 

and opportunity for prior public 

comment are unnecessary 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–2012–1350; 

Directorate Identifier 2012–NE–40–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 because of 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 with FAA 

personnel concerning this AD. Using the 

search function of the Web site, anyone 

can find and read the comments in any 

of our dockets, including, if provided, 

the name of the individual who sent the 

comment (or signed the comment on 

behalf of an association, business, labor 

union, etc.). You may review the DOT’s 

complete Privacy Act Statement in the 


wreier-aviles on DSK5TPTVN1PROD with