DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[4910-13-P] 

[Docket No. FAA-2012-1327; Directorate Identifier 2012-NE-47-AD; Amendment 

39-17478; AD 2013-12-01] 

RIN 2120-AA64 

Airworthiness Directives; Rolls-Royce pic Turbofan Engines 

AGENCY: Federal Aviation Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new airworthiness directive (AD) for all Rolls-Royce 

pic (RR) model RB211 Trent 768-60, 772-60, and 772B-60 turbofan engines. This AD 

was prompted by low-pressure (LP) compressor blade partial airfoil release events. This 

AD requires a one-time ultrasonic inspection of LP compressor blades that had 

accumulated more than 2,500 flight cycles (FC) since new. We are issuing this AD to 

prevent LP compressor blade airfoil separations, engine damage, and damage to the 

airplane. 

DATES: This AD becomes effective [INSERT DATE 35 DAYS AFTER DATE OF 

PUBLICATION IN THE FEDERAL REGISTER]. The Director ofthe Federal Register 

approved the incorporation by reference of certain publications listed in this AD as of 

[INSERT DATE 35 DAYS AFTER DATE OF PUBLICATION IN THE FEDERAL 

REGISTER]. 
ADDRESSES: The Docket Operations office is located at Docket Management Facility, 

U.S. Department of Transportation, 1200 New Jersey Avenue SE., West Building Ground 

Floor, Room W12-140, Washington, DC 20590-0001. 

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 provided in the ADDRESSES 

section. Comments will be available in the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; phone: 781-238-7754; fax: 781-238-7199; email: 

robert. green@faa. gov. 

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 January 31 , 2013 (78 FR 6749). That NPRM proposed to require 

a one-time ultrasonic C-scan inspection of LP compressor blades that have accumulated 

more than 2,500 FC since new. The European Aviation Safety Agency (EASA) 

subsequently superseded EASA AD 2012-0247, dated November 20, 2012, by issuing 

EASA AD 2013-0060, dated March 11 , 2013, to include are-inspection requirement for 

certain LP compressor blades that were not inspected correctly. 

The new mandatory continuing airworthiness information (MCAI) states: 

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Comments 

Low-Pressure (LP) compressor partial aerofoil blade 

release events have occurred in service on RR Trent 700 

engines. While primary containment of the released 

sections has been achieved in each case, some of the 

releases did exhibit secondary effects that are considered to 

present a potential hazard. Previously, expeditious actions 

by RR have mitigated the risks presented by these effects, 

by removal from service of batches of LP compressor 

blades. However, some causal factors still exist that are not 

fully understood. 

This condition, if not detected and corrected, could lead to 

LP compressor blade release with possible consequent loss 

of the engine nose cowl, under cowl fires and forward 

projection of secondary debris, possibly resulting in 

damage to the aeroplane and/or injury to persons on the 

ground. 

To mitigate the risk of further partial fan blade release 

events, RR issued Non-Modification Service Bulletin 

(NMSB) RB.211-72-G872, providing instructions for an 

ultrasonic inspection of the affected LP compressor blades 

to detect subsurface anomalies in the aerofoil and, 

depending on findings, replacement of LP compressor 

blades. 

To address this potential unsafe condition, EASA issued 

AD 2012-0247 to require a one-time inspection of the 

affected LP compressor blades. 

Since that AD was issued, a population of LP compressor 

blades have been identified as incorrectly inspected and 

therefore require re-inspection. Consequently, RR issued 

NMSB RB.211-72-H311 to provide the instructions for this 

re-inspection. 

For the reason described above, this AD retains the 

requirements ofEASA AD 2012-0247, which is 

superseded, and adds, for the affected group of LP 

compressor blades, a one-time re-inspection. 

We gave the public the opportunity to participate in developing this AD. We 

considered the comments received. 

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Request to Change Summary 

RR requested that we change the Summary to state that the AD would require a 

one-time ultrasonic inspection ofLP compressor blades (without being specific to Cscan). The reason for this request is that RR issued Revision 2 to NMSB RB.211-72-

G872, dated March 8, 2013, which added phased array as an alternative ultrasonic 

technique to C-scan. 

We agree. We changed the AD Summary to state: "This AD requires a one-time 

ultrasonic inspection of LP compressor blades that had ... " 

Request to Change Discussion 

RR requested that we change the Discussion to note that EASA AD 2012-0247, 

dated November 20, 2012, was superseded by EASA AD 2013-0060, dated March 11 , 

2013, which includes are-inspection requirement for certain LP compressor blades that 

were not inspected correctly. 

We agree. We referenced EASA AD 2013-0060, dated March 11 , 2013 in the 

Discussion and Related Information paragraphs of this AD. 

Request to Change Relevant Service Information 

RR requested that the Relevant Service Information paragraph be changed 

because they issued NMSB RB.211-72-G872, Revision 2, dated March 8, 2013. This 

NMSB adds phased array ultrasonic inspection as an on-wing or in-shop alternative to the 

C-scan inspection technique. Also, because certain LP compressor blades were not 

inspected correctly in accordance with RR NMSB RB.211-72-G872, Revision 1, dated 

July 2, 2012, RR issued NMSB RB.211-72-H311 , dated March 8, 2013, to require reinspection of blades identified by serial number (SIN). The accomplishment instructions 

and compliance period for NMSB RB.211-72-H311 , dated March 8, 2013, are identical 

to those ofNMSB RB.211-72-G872, Revision 2, dated March 8, 2013. Blades inspected 

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to NMSB RB.211-72-H311, dated March 8, 2013, do not then need inspection to NMSB 

RB.211-72-G872, Revision 2, dated March 8, 2013 . 

We partially agree. We agree that RR updated its service information. We do not 

agree that the Relevant Service Information paragraph be changed, because that 

paragraph only exists in the proposed AD (78 FR 6749, January 31 , 2013). We did not 

change the AD. 

Request to Change AD Requirements Statement 

RR requested that we replace the requirements statement, of inspections specific 

to C-scan, with a statement requiring a one-time ultrasonic inspection of LP compressor 

blades (without being specific to C-scan). 

We agree. We changed the AD Summary to state that the AD requires a one-time 

ultrasonic inspection of LP compressor blades that had accumulated more than 2,500 FC 

smce new. 

Request to Change Compliance Time 

RR requested that the compliance time be changed from within 500 FC, to within 

500 FC or 10 months, whichever is earlier. RR stated that this change is necessary to 

ensure compliance within a reasonable period of time. 

We agree that a calendar end date is appropriate for AD management, and for that 

purpose, we agree 10 months is appropriate. We changed the AD to include the 10-month 

compliance end date. 

Request to Change Actions and Compliance 

RR requested that paragraph (e) of the AD be changed to reflect the revised 

inspection methods issued in RR NMSB RB.211-72-G872, Revision 2, dated March 8, 

2013, to include are-inspection requirement for certain blades provided by NMSB 

RB.211-72-H311 , dated March 8, 2013, and to eliminate the requirement to remove the 

LP compressor blades. RR stated that these changes were needed because the revised 

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inspections in their service information adds phased array ultrasonic inspection and onwing inspection instructions. RR NMSB RB.211-72-H311 introduces are-inspection 

requirement for blades that were previously inspected incorrectly. The on-wing phased 

array ultrasonic inspection added by NMSB RB.211-72-G872, Revision 2, dated March 

8, 2013, and included in NMSB RB.211-72-H311 , does not require removal ofthe blades 

from the engine for inspection. 

We agree. We changed paragraph (e) of this AD to state the following: 

For engines with LP compressor blades that have 2,500 FC or more since new or 

since last inspection using RR NMSB RB.211-72-G702, dated May 23,2011, perform an 

ultrasonic inspection of each compressor blade within 500 FC or within 10 months after 

the effective date ofthis AD, whichever is sooner. Use paragraphs 3.C through 3.H ofRR 

NMSB RB.211-72-G872, Revision 2, dated March 8, 2013, to do the inspection. You 

may do the on-wing phased array ultrasonic inspection added by NMSB RB.211-72-

G872, and included in NMSB RB.211-72-H311 , without removing the blades from the 

engine for the inspection. 

We added a Credit for Previous Actions paragraph (g) of this AD, which states 

that you may take credit for the ultrasonic C-scan inspection of each LP compressor blade 

if you performed the inspection before the effective date of this AD using RR NMSB 

RB.211-72-G872, dated April3, 2012, or Revision 1, dated July 2, 2012. 

Request to Change Actions and Compliance 

RR requested that the Actions and Compliance paragraph be changed from " ... do 

not install on an engine any LP compressor blade ... " to " ... do not install on an engine 

any replacement blade ... ". RR stated that the purpose of this change was to avoid 

confusion in the case that the blades are removed for routine maintenance such as relubrication ofthe blade root. 

We partially agree. We agree that blades removed for routine on-wing 

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maintenance such as the re-lubrication of the blade roots should not be subject to the 

installation prohibition ifthey are within the compliance period interval. We do not agree 

with the use of the word "replacement" as it is ambiguous. We changed the Installation 

Prohibition paragraph (f) of this AD to read: "After the effective date ofthis AD, do not 

install, on any engine, any LP compressor blade that has 2,500 FC or more since new or 

since last inspection using RR NMSB RB.211-72-G702, dated May 23 , 2011 , unless the 

LP compressor blade has passed the ultrasonic inspection required in paragraphs (e)( 1) or 

(e)(2) of this AD. LP compressor blades that are removed for routine on-wing 

maintenance such as blade root re-lubrication that will subsequently be reassembled into 

the engine are not subject to this Installation Prohibition." 

Conclusion 

We reviewed the available data, including the comments received, and determined 

that air safety and the public interest require adopting the AD with the changes described 

previously. We determined that these changes will not increase the economic burden on 

any operator or increase the scope of the AD. 

Costs of Compliance 

We estimate that this AD will affect 56 engines installed on airplanes of U.S. 

registry. We also estimate that it will take about 38 hours per engine to comply with this 

AD. The average labor rate is $85 per hour. Based on these figures, we estimate the cost 

of the AD on U.S. operators to be $180,880. 

Authority for This Rulemaking 

Title 49 ofthe 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 ofthe Agency's 

authority. 

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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), 

(3) Will not affect intrastate aviation in Alaska to the extent that it justifies 

making a regulatory distinction, 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 

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. 

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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: 

2013-12-01 Rolls-Royce pic: Amendment 39-17478; Docket No. FAA-2012-1327; 

Directorate Identifier 2012-NE-47-AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes effective [INSERT DATE 35 DAYS 

AFTER DATE OF PUBLICATION IN THE FEDERAL REGISTER]. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Rolls-Royce pic (RR) model RB211 Trent 768-60, 772-60, 

and 772B-60 turbofan engines. 

(d) Reason 

This AD was prompted by low-pressure (LP) compressor blade partial airfoil 

release events. We are issuing this AD to prevent LP compressor blade airfoil 

separations, engine damage, and damage to the airplane. 

(e) Actions and Compliance 

Unless already done, do the following actions. 

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(1) Inspection of LP Compressor Blade On-Wing or In-Shop 

(i) For engines with LP compressor blades that have 2,500 flight cycles (FC) or 

more since new or since last inspection using RR Non-Mandatory Service Bulletin 

(NMSB) RB.211-72-G702, dated May 23 , 2011 , perform an ultrasonic inspection of each 

LP compressor blade within 500 FC or within 10 months after the effective date of this 

AD, whichever is sooner. 

(ii) Use paragraphs 3.C through 3.H ofthe Accomplishment Instructions ofRR 

NMSB RB.211-72-G872, Revision 2, dated March 8, 2013, to do the inspection. 

(iii) You may do the on-wing phased array ultrasonic inspection added by NMSB 

RB.211-72-G872, Revision 2, dated March 8, 2013, and included in NMSB RB.211-72-

H311, without removing the blades from the engine for the inspection. 

(2) Re-Inspection of LP Compressor Blade Identified by Serial Number (SIN) 

(i) For engines with LP compressor blades installed and identified by SIN in 

Appendix 1 ofRR NMSB RB.211-72-H311 , dated March 8, 2013, and that have, on the 

effective date of this AD, accumulated 2,500 FC since new or since last inspection using 

RR NMSB RB.211-72-G702, dated May 23 , 2011 , perform an ultrasonic inspection of 

each LP compressor blade. 

(ii) The inspection, either on-wing or in-shop, must be performed within 500 FC 

or 10 months, whichever is sooner, after the effective date of this AD. 

(iii) Use paragraphs 3.C through 3.H ofthe Accomplishment Instructions ofRR 

NMSB RB.211-72-H311 , dated March 8, 2013, to do the inspection. 

(f) Installation Prohibition 

(1) After the effective date of this AD, do not install, on any engine, any LP 

compressor blade that has 2,500 FC or more since new or since last inspection using RR 

NMSB RB.211-72-G702, dated May 23 , 2011 , unless the LP compressor blade has 

passed the ultrasonic inspection required in paragraphs (e)(1) or (e)(2) ofthis AD. 

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(2) LP compressor blades that are removed for routine on-wing maintenance such 

as blade root re-lubrication that will subsequently be reassembled into the engine are not 

subject to this Installation Prohibition. 

(g) Credit for Previous Actions 

You may take credit for the ultrasonic C-scan inspection of each compressor 

blade if you performed the inspection before the effective date of this AD using RR 

NMSB RB.211-72-G872, dated April3, 2012, or Revision 1, dated July 2, 2012. 

(h) Alternative Methods of Compliance (AMOCs) 

The Manager, Engine Certification Office, FAA, may approve AMOCs for this 

AD. Use the procedures found in 14 CFR 3 9.19 to make your request. 

(i) Related Information 

(1) For more information about this AD, contact Robert Green, Aerospace 

Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 01803; phone: 781-238-7754; fax: 781-238-

7199; email: robert.green@faa.gov. 

(2) European Aviation Safety Agency AD 2013-0060, dated March 11 , 2013, 

pertains to the subject ofthis AD. 

(j) 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 the AD specifies otherwise. 

(i) Rolls-Royce plc Non-Modification Service Bulletin RB.211-72-H311 , dated 

March 8, 2013 . 

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(ii) Rolls-Royce plc Non-Modification Service Bulletin RB.211-72-G872, 

Revision 2, dated March 8, 2013. 

(3) For Rolls-Royce pic service information identified in this AD, contact RollsRoyce pic, P.O. Box 31 , Derby DE24 8BJ, UK; phone: 44 (0) 1332 242424; 

fax: 44 (0) 1332 249936. 

( 4) You may view this service information at 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. 

(5) You may view this service information 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 Burlington, Massachusetts, on June 5, 2013 . 

Colleen M. D' Alessandro, 

Assistant Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

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