This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

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REGISTER issue of each week.

Rules and Regulations Federal Register

13483 

Vol. 77, No. 45 

Wednesday, March 7, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0562; Directorate 

Identifier 2009–NE–29–AD; Amendment 39– 

16969; AD 2012–04–13] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc (RR) Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

all RR model RB211–524G2–T–19, 

–524G3–T–19, –524H–T–36, and 

–524H2–T–19; and RB211–Trent 553– 

61, 553A2–61, 556–61, 556A2–61, 

556B–61 556B2–61, 560–61, 560A2–61; 

RB211–Trent 768–60, 772–60, 772B–60; 

and RB211–Trent 875–17, 877–17, 884– 

17, 884B–17, 892–17, 892B–17, and 

895–17 turbofan engines that have a 

high-pressure (HP) compressor stage 1 

to 4 rotor disc with a part number 

(P/N) listed in Table 1 of the AD. That 

AD currently requires repetitive 

inspections of the axial dovetail slots, 

and follow-on corrective action 

depending on findings. Since we issued 

that AD, we determined that the 

definition of shop visit is too restrictive 

in the existing AD. This continues to 

require those repetitive inspections and 

follow-on corrective actions. This new 

AD changes the definition of a shop 

visit to be less restrictive. This AD was 

prompted by our determination that the 

definition of ‘‘shop visit’’ in the existing 

AD is too restrictive, in that it would 

require operators to inspect more often 

than required to ensure safety. We are 

issuing this AD to detect cracks in the 

HP compressor stage 1 and 2 disc posts, 

which could result in failure of the disc 

post and HP compressor blades, release 

of uncontained engine debris, and 

damage to the airplane. 

DATES: This AD is effective April 11, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of April 11, 2012. 

ADDRESSES: For service information 

identified in this AD, contact RollsRoyce plc, Corporate Communications, 

P.O. Box 31, Derby, England, DE248BJ; 

phone: 011–44–1332–242424; fax: 011– 

44–1332–245418 or email from http:// 

www.rolls-royce.com/contact/ 

civil_team.jsp, or download the 

publication from https:// 

www.aeromanager.com. You may 

review 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Alan Strom, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7143; fax: 781–238– 

7199; email: alan.strom@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2011–09–07, 

Amendment 39–16669 (76 FR 24793, 

May 3, 2011). That AD applies to the 

specified products. The NPRM 

published in the Federal Register on 

October 20, 2011 (76 FR 65136). That 

NPRM proposed to continue to require 

initial and repetitive fluorescent 

penetrant inspections of the HP 

compressor stage 1 to 4 rotor discs at the 

first shop visit after accumulating 1,000 

cycles-since-new on the stage 1 to 4 

rotor discs or at the next shop visit after 

the effective date of that AD, which ever 

occurs later. That NPRM also proposed 

to continue to require repetitive 

inspections at every shop visit. That 

NPRM also proposed to change the 

definition of a shop visit to be less 

restrictive. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Support for the NPRM 

Two commenters, the Boeing 

Company and American Airlines, 

support the intent of the NPRM (76 FR 

65136, October 20, 2011). 

Request To Change From a Supersedure 

to a Revision 

One commenter, American Airlines, 

requested that we change the proposed 

AD (76 FR 65136, October 20, 2011) 

from being an AD supersedure to being 

an AD revision of the existing AD 2011– 

09–07 (76 FR 24793, May 3, 2011), or, 

have Rolls-Royce plc revise Alert 

Service Bulletin (ASB) No. RB.211–72– 

AF964 to remove the reference to AD 

2011–09–07, so that we can reference 

that latest ASB revision in the AD. The 

commenter stated that the ASB revision 

should be issued before the AD is 

issued, and referenced in the AD, to 

avoid the burden of needing global 

Alternative Methods of Compliances 

written. 

We do not agree. The reference to the 

previous AD (76 FR 24793, May 3, 2011) 

in ASB No. RB.211–72–AF964 is not the 

section of the ASB incorporated by 

reference by this AD. We can not delay 

publishing an AD to wait for an 

administrative change to a service 

bulletin. Administrative updates to 

service bulletins are made for a variety 

of reasons. These revisions are easily 

handled by the alternative method of 

compliance process described in 

paragraph (i) of this AD. We did not 

change the AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 


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13484 Federal Register / Vol. 77, No. 45 / Wednesday, March 7, 2012 / Rules and Regulations 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD will affect about 

371 products of U.S. registry. We also 

estimate that it will take about 20 workhours per product to comply with this 

AD. The average labor rate is $85 per 

work-hour. No parts will be required per 

product. Based on these figures, we 

estimate the cost of the AD on U.S. 

operators to be $630,700. 

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 have 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 

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. 

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 

removing airworthiness directive (AD) 

2011–09–07, Amendment 39–16669 (76 

FR 24793, May 3, 2011), and adding the 

following new AD: 

2012–04–13 Rolls-Royce plc: Amendment 

39–16969; Docket No. FAA–2010–0562; 

Directorate Identifier 2009–NE–29–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective April 11, 2012. 

(b) Affected ADs 

This AD supersedes AD 2011–09–07, 

Amendment 39–16669 (76 FR 24793, May 3, 

2011). 

(c) Applicability 

This AD applies to Rolls-Royce plc (RR) 

model RB211–524G2–T–19, –524G3–T–19, 

–524H–T–36, and –524H2–T–19; and RB211– 

Trent 553–61, 553A2–61, 556–61, 556A2–61, 

556B–61 556B2–61, 560–61, 560A2–61; 

RB211–Trent 768–60, 772–60, 772B–60; and 

RB211–Trent 875–17, 877–17, 884–17, 884B– 

17, 892–17, 892B–17, and 895–17 turbofan 

engines that have a high-pressure (HP) 

compressor stage 1 to 4 rotor disc with a part 

number (P/N) listed in Table 1 of this AD. 

TABLE 1—AFFECTED HP COMPRESSOR STAGE 1 TO 4 ROTOR DISC P/NS BY ENGINE MODEL

Engine model HP compressor stage 1 to 4 rotor disc P/N 

(1) RB211–524G2–T–19, –524G3–T–19, –524H–T–36, and –524H2– 

T–19.

FW20195, FK25502, or FW23711. 

(2) RB211 Trent 553–61, 553A2–61, 556–61, 556A2–61, 556B–61, 

556B2–61, 560–61, and 560A2–61.

FK30524. 

(3) RB211 Trent 768–60, 772–60, and 772B–60 .................................... FK22745, FK24031, FK26185, FK23313, FK25502, FK32129, 

FW20195, FW20196, FW20197, FW20638, or FW23711. 

(4) RB211 Trent 875–17, 877–17, 884–17, 884B–17, 892–17, 892B– 

17, and 895–17.

FK24009, FK26167, FK32580, FW11590, or FW61622. 

(d) Unsafe Condition 

This AD was prompted by our 

determination that the definition of ‘‘shop 

visit’’ in the existing AD is too restrictive, in 

that it would require operators to inspect 

more often than required to ensure safety. We 

are issuing this AD to detect cracks in the HP 

compressor stage 1 and 2 disc posts, which 

could result in failure of the disc post and 

HP compressor blades, release of 

uncontained engine debris, and damage to 

the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) Cleaning and Inspection 

(1) Clean and perform a fluorescent 

penetrant inspection of the HP compressor 

stage 1 to 4 rotor discs at the first shop visit 

after accumulating 1,000 cycles since new on 

the stage 1 to 4 rotor discs or at the next shop 

visit after the effective date of this AD, which 

ever occurs later. 

(2) Use paragraph 3.A through 3.E.(11) of 

the Accomplishment Instructions of RollsRoyce Alert Service Bulletin (ASB) No. 

RB.211–72–AF964, Revision 2, dated June 8, 

2011, to do the inspections. 

(3) Thereafter at every engine shop visit, 

perform the inspection specified by 

paragraph (f) of this AD. 

(g) Definition 

For the purpose of this AD, an ‘‘engine 

shop visit’’ is whenever all compressor 

blades are removed from the HP compressor 

drum. 

(h) Credit for Previous Action 

A cleaning and inspection performed 

before the effective date of this AD using 

Rolls-Royce ASB No. RB.211–72–AF964, 

Revision 1, dated June 6, 2008, or Revision 

2, dated June 8, 2011, satisfies a cleaning and 

inspection cycle required by this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA may approve AMOCs for this AD. Use 


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Federal Register / Vol. 77, No. 45 / Wednesday, March 7, 2012 / Rules and Regulations 13485 

the procedures found in 14 CFR 39.19 to 

make your request. 

(j) Related Information 

(1) For more information about this AD, 

contact Alan Strom, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7143; fax: 781–238–7199; 

email: alan.strom@faa.gov. 

(2) See European Aviation Safety Agency 

Airworthiness Directive 2009–0073R1, dated 

April 8, 2009, for related information. 

(k) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 5 

U.S.C. 552(a) and 1 CFR part 51 of the 

following service information on the date 

specified: 

(i) Rolls-Royce Alert Service Bulletin No. 

RB.211–72–AF964, Revision 2, dated June 8, 

2011 approved for IBR April 11, 2012. 

(ii) Rolls-Royce ASB No. RB.211–72– 

AF964, Revision 1, dated June 6, 2008 

approved for IBR June 7, 2011 (76 FR 24793, 

May 3, 2011). 

(2) For service information identified in 

this AD, contact Rolls-Royce plc, Corporate 

Communications, P.O. Box 31, Derby, 

England, DE248BJ; phone: 011–44–1332– 

242424; fax: 011–44–1332–245418 or email 

from http://www.rolls-royce.com/contact/ 

civil_team.jsp, or download the publication 

from https://www.aeromanager.com. 

(3) You may review copies of the 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. 

(4) 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 NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/ 

cfr/ibr_locations.html. 

Issued in Burlington, Massachusetts, on 

February 23, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–5370 Filed 3–6–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0959; Directorate 

Identifier 2011–NE–25–AD; Amendment 39– 

16970; AD 2012–04–14] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for RB211– 

Trent 800 series turbofan engines. This 

AD requires inspecting the front 

combustion liner head section for 

cracking, and if found cracked, 

removing the front combustion liner 

head section from service at the next 

shop visit. This AD was prompted by 

mandatory continuing airworthiness 

information (MCAI) issued by an 

aviation authority of another country to 

identify and correct an unsafe condition 

on an aviation product. Specifically, 

routine inspections revealed cracking on 

the head sections of two RB211–Trent 

800 front combustion liners. We are 

issuing this AD to prevent uncontained 

engine failure and damage to the 

airplane. 

DATES: This AD becomes effective April 

11, 2012. The Director of the Federal 

Register approved the incorporation by 

reference of certain publications listed 

in this AD as of April 11, 2012. 

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. 

FOR FURTHER INFORMATION CONTACT: 

Alan Strom, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

email: alan.strom@faa.gov; phone: 781– 

238–7143; fax: 781–238–7199. 

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 November 25, 2011 (76 FR 

72650). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Routine inspections have revealed cracking 

on the head sections of two Trent 800 front 

combustion liners. 

This condition, if not detected and 

corrected, could lead to hot gas breakout with 

subsequent downstream component release 

potentially leading to uncontained high 

energy debris, possibly resulting in damage 

to the aeroplane or injury to persons on the 

ground. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Reference the Latest Service 

Information 

American Airlines, The Boeing 

Company, and Rolls-Royce plc, 

requested that we reference the latest 

service information, which is Alert 

Service Bulletin (ASB) No. RB.211–72– 

AG456, Revision 1, dated November 4, 

2011. 

We agree. We changed the AD to 

reference Revision 1 of the ASB. 

Request To Add Previous Credit 

Paragraph 

American Airlines, The Boeing 

Company, and Rolls-Royce plc, 

requested that we add a Previous Credit 

paragraph to list the original ASB to 

give credit to operators who have 

performed the initial and repetitive 

inspections before the effective date of 

the AD. 

We agree. We added Credit for 

Previous Action paragraph (i) to the AD. 

Request To Borescope-Inspect the 04 

Module When Removed 

Rolls-Royce plc requested that we add 

wording to the AD that states that the 04 

module may be borescope-inspected 

when it is removed from the engine but 

is not being stripped. This would give 

the operator the opportunity to restart 

the 2,000-cycle on-wing life before the 

next inspection, or if cracked, would 

give the operator the opportunity to 

replace the front combustion liner head 

section. 

We agree. We changed the AD to 

allow as an alternate procedure, an inshop borescope inspection. 

Request To Eliminate Unnecessary 

Borescope Inspection 

Rolls-Royce plc pointed out that the 

proposed AD requires the front 

combustion liner head section to be 

borescope inspected even if it is being 

stripped. Visual and fluorescent 

penetrant inspections would be done as 

part of the maintenance manual 

activities after stripping, and the 

borescope inspection would be 

unnecessary. 


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