This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

2605 

Vol. 76, No. 10 

Friday, January 14, 2011 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0821; Directorate 

Identifier 2010–NE–30–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc RB211–Trent 800 Series Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

In January 2009 a Trent 895 powered 

Boeing 777–200 aircraft experienced release 

of a low pressure (LP) compressor blade 

which failed due to fatigue cracking in the 

root section of the blade. The released blade 

(undercut root standard) had received a part 

life processing to apply a compression layer 

to the blade root (Service Bulletin SB 72– 

D672—Introduction of Laser Shock Peening 

(LSP)) and also a part life upgrade to the 

retention feature lubrication system. 

Investigation has revealed that the 

effectiveness of this upgraded blade root 

lubrication coating system may be reduced 

dependant on the extent of previous running 

with the earlier standard, leading to 

increased blade root stress levels. In the 

specific case of the released blade, a review 

of its in-service modification history has 

shown that it operated for a relatively high 

number of flight cycles prior to the 

compression layer processing and the new 

retention feature lubrication system. A 

review of the Engine Health Monitoring data 

has also identified it operated at high N1 

speeds compared to the Trent 800 fleet 

average N1 speeds. The combination of these 

factors has resulted in increased fatigue life 

usage which is considered to have led to 

crack initiation and propagation prior to 

reaching the blades declared life limit. A 

review of all in-service undercut/LSP 

standard Trent 800 LP compressor blades has 

identified specific blades that carry a similar 

increased susceptibility to cracking. 

This AD is issued to mitigate the risk of 

possible multiple fan blades failure affecting 

those blades identified as described above 

which could lead to high energy non 

contained debris from the engine. 

We are proposing this AD to prevent LP 

compressor blades from failing due to 

blade root cracks, which could lead to 

uncontained engine failure and damage 

to the airplane. 

DATES: We must receive comments on 

this proposed AD by February 28, 2011. 

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: Docket Management Facility, 

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. 

Contact Rolls-Royce plc, P.O. Box 31, 

DERBY, DE24 8BJ, UK; telephone 44 (0) 

1332 242424; fax 44 (0) 1332 249936, for 

the service information identified in this 

proposed AD. 

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 proposed 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: 

Alan Strom, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: alan.strom@faa.gov; telephone 

(781) 238–7143; fax (781) 238–7199. 

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–2010–0821; Directorate Identifier 

2010–NE–30–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 with FAA 

personnel concerning this proposed 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). 

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 2010–0097, 

dated May 26, 2010 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

In January 2009 a Trent 895 powered 

Boeing 777–200 aircraft experienced release 

of a low pressure (LP) compressor blade 

which failed due to fatigue cracking in the 

root section of the blade. The released blade 

(undercut root standard) had received a part 

life processing to apply a compression layer 

to the blade root (Service Bulletin SB 72– 

D672—Introduction of Laser Shock Peening 

(LSP)) and also a part life upgrade to the 

retention feature lubrication system. 

Investigation has revealed that the 

effectiveness of this upgraded blade root 

lubrication coating system may be reduced 

dependant on the extent of previous running 

with the earlier standard, leading to 

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2606 Federal Register / Vol. 76, No. 10 / Friday, January 14, 2011 / Proposed Rules 

increased blade root stress levels. In the 

specific case of the released blade, a review 

of its in-service modification history has 

shown that it operated for a relatively high 

number of flight cycles prior to the 

compression layer processing and the new 

retention feature lubrication system. A 

review of the Engine Health Monitoring data 

has also identified it operated at high N1 

speeds compared to the Trent 800 fleet 

average N1 speeds. The combination of these 

factors has resulted in increased fatigue life 

usage which is considered to have led to 

crack initiation and propagation prior to 

reaching the blades declared life limit. A 

review of all in-service undercut/LSP 

standard Trent 800 LP compressor blades has 

identified specific blades that carry a similar 

increased susceptibility to cracking. 

This AD is issued to mitigate the risk of 

possible multiple fan blades failure affecting 

those blades identified as described above 

which could lead to high energy non 

contained debris from the engine. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Rolls-Royce plc has issued Alert 

Service Bulletin No. RB.211–72–AG244, 

Revision 1, dated January 26, 2010. 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 Proposed AD 

This product has been approved by 

the aviation authority of the United 

Kingdom, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the United 

Kingdom, they have notified us of the 

unsafe condition described in the MCAI 

and service information referenced 

above. We are proposing 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. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 20 engines installed on 

airplanes of U.S. registry. We also 

estimate that it would take about 18 

work-hours per engine to perform the 

inspections in one year’s time. The 

average labor rate is $85 per work-hour. 

We estimate that one LP compressor 

blade per year would need replacement, 

at a cost of about $82,000. Based on 

these figures, we estimate the annual 

cost of the proposed AD on U.S. 

operators to be $112,600. Our cost 

estimate is exclusive of possible 

warranty coverage. 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 proposed regulation: 

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 proposed 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

Rolls-Royce plc: Docket No. FAA–2010– 

0821; Directorate Identifier 2010–NE– 

30–AD. 

Comments Due Date 

(a) We must receive comments by February 

28, 2011. 

Affected Airworthiness Directives (ADs) 

(b) None. 

Applicability 

(c) This AD applies to Rolls-Royce plc (RR) 

RB211–Trent 875–17, RB211–Trent 877–17, 

RB211–Trent 884–17, RB211–Trent 884B–17, 

RB211–Trent 892–17, RB211–Trent 892B–17, 

and RB211–Trent 895–17 turbofan engines. 

Reason 

(d) This AD results from mandatory 

continuing airworthiness information (MCAI) 

issued by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. We are 

issuing this AD to prevent low-pressure (LP) 

compressor blades from failing due to blade 

root cracks, which could lead to uncontained 

engine failure and damage to the airplane. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) Using the corresponding compliance 

threshold in Table 1 of this AD, perform an 

initial ultrasonic inspection (UI) of the 

affected LP compressor blades identified by 

serial number (S/N) in Appendices 3A 

through 3F of RR Alert Service Bulletin 

(ASB) No. RB.211–72–AG244, Revision 1, 

dated January 26, 2010. 

TABLE 1—INITIAL INSPECTION THRESHOLDS

Appendix number of RR ASB No. RB.211– 

72–AG244, Revision 1, that identifies affected LP compressor blades by 

S/N 

Initial inspection threshold 

3A ................................................................... 120 flight cycles after the effective date of this AD. 

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Federal Register / Vol. 76, No. 10 / Friday, January 14, 2011 / Proposed Rules 2607 

TABLE 1—INITIAL INSPECTION THRESHOLDS—Continued 

Appendix number of RR ASB No. RB.211– 

72–AG244, Revision 1, that identifies affected LP compressor blades by 

S/N 

Initial inspection threshold 

3B ................................................................... Blades shown in RR ASB No. RB.211–72–AG244, Revision 1 as fitted to engine serial number 

(ESN) 51039—802 flight cycles after the effective date of this AD. 

ESNs 51146, 51177, 51145, and 51149—380 flight cycles after the effective date of this AD. 

3C ................................................................... Blades shown in RR ASB No. RB.211–72–AG244, Revision 1 as fitted to ESNs 51001, 51137 

and blade S/N RGG16694—1,680 flight cycles after the effective date of this AD. 

ESN 51145, 51149, 51150 and 51204—796 flight cycles after the effective date of this AD. 

ESN 51160—1,160 flight cycles after the effective date of this AD. 

3D ................................................................... Blades shown in RR ASB No. ASB RB.211–72–AG244, Revision 1 as fitted to ESN 51193 and 

blade S/N RGG20216—1,212 flight cycles after the effective date of this AD. 

ESN 51200—1,237 flight cycles after the effective date of this AD. 

ESN 51280—1,551 flight cycles after the effective date of this AD. 

3E ................................................................... Blades shown in RR ASB No. RB.211–72–AG244, Revision 1 as fitted to ESN 51004, ‘‘na’’ and 

blade S/Ns RGG12590, RGG14081, and RGG15419—3,433 flight cycles after the effective 

date of this AD. 

ESN 51156—1,627 flight cycles after the effective date of this AD. 

3F ................................................................... Blades shown in RR ASB No. RB.211–72–AG244, Revision 1 as fitted to ESN 51175, 51194, 

51201, 51205, and 51228—2,042 flight cycles after the effective date of this AD. 

ESN 51264—4,309 flight cycles after the effective date of this AD. 

ESN 51443—2,636 flight cycles after the effective date of this AD. 

Blade S/N RGG15698—2,638 flight cycles after the effective date of this AD. 

(2) Thereafter, perform repetitive UIs of the 

affected LP compressor blades within every 

100 flight cycles. 

(3) Use paragraph 3 of Accomplishment 

Instructions of RR ASB No. RB.211–72– 

AG244, Revision 1, dated January 26, 2010, 

and Appendix 1 of that ASB to perform the 

UIs. 

(4) Remove blades from service before 

further flight that fail the inspection criteria 

in Appendix 1 of RR ASB No. RB.211–72– 

AG244, Revision 1, dated January 26, 2010. 

(5) After the effective date of this AD, do 

not install any affected LP compressor blade 

unless it has passed the initial and repetitive 

UIs required by this AD. 

FAA AD Differences 

(f) This AD differs from MCAI European 

Aviation safety Agency (EASA) AD 2010– 

0097, dated May 26, 2010. The EASA AD 

uses calendar dates for initial inspection 

thresholds. This AD uses flight cycles. 

Alternative Methods of Compliance 

(g) The Manager, Engine Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(h) Refer to EASA AD 2010–0097, dated 

May 26, 2010, and RR Alert SB No. RB.211– 

72–AG244, Revision 1, dated January 26, 

2010, for related information. Contact RollsRoyce plc, P.O. Box 31, DERBY, DE24 8BJ, 

UK; telephone 44 (0) 1332 242424; fax 44 (0) 

1332 249936, for a copy of this service 

information. 

(i) Contact Alan Strom, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: alan.strom@faa.gov; telephone 

(781) 238–7143; fax (781) 238–7199. 

Issued in Burlington, Massachusetts, on 

January 10, 2011. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–775 Filed 1–13–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1301; Directorate 

Identifier 2010–SW–008–AD] 

RIN 2120–AA64 

Airworthiness Directives; MD 

Helicopters, Inc. (MDHI) Model MD900 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes 

superseding an existing airworthiness 

directive (AD) for MDHI Model MD900 

helicopters. That AD currently requires 

turning on both Vertical Stabilizer 

Control System (VSCS) switches and 

turning off the autopilot (AP/SAS) 

switch; pulling certain AP/SAS circuit 

breakers; installing a placard near the 

AP/SAS master switch; installing an 

airspeed limitation placard on the 

instrument panel; and making changes 

to the Rotorcraft Flight Manual (RFM). 

This action would retain those 

requirements and would provide an 

option of replacing each affected tube 

adapter with a newly-designed tube 

adapter, which would provide 

terminating action for the unsafe 

condition. This proposal is prompted by 

the manufacturer introducing an 

improved, newly-designed tube adapter. 

The actions specified by this AD are 

intended to prevent loss of yaw control 

and subsequent loss of control of the 

helicopter. 

DATES: Comments must be received on 

or before March 15, 2011. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD: 

• 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 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

You may get the service information 

identified in this proposed AD from MD 

Helicopters, Inc., Attn: Customer 

Support Division, 4555 E. McDowell 

Rd., Mail Stop M615, Mesa, AZ 85215– 

9734, telephone 1–800–388–3378, fax 

480–346–6813, or at http:// 

www.mdhelicopters.com. 

You may examine the comments to 

this proposed AD in the AD docket on 

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