[Docket No. FAA-2015-0095; Directorate Identifier 2015-NE-01-AD; Amendment 

39-18228; AD 2015-16-03) 

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 certain RollsRoyce pic (RR) RB21 1-524B-02, RB211-524B2-19, RB211-524B3-02, RB211 -524B4-

02, RB2 11-524B4-D-02, RB21 1-524C2-1 9, RB211-524D4-1 9, RB211 -524D4-39, and 

RB211-524D4X-19 turbofan engines. This AD requires removing affected high-pressure 

turbine (HPT) blades. This AD was prompted by several failures of affected HPT blades. 

We are issuing this AD to prevent failure of the HPT blade, which could lead to failure of 

one or more engines, loss of thrust control, and damage to the airplane. 

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

PUBLICATION IN THE FEDERAL REGISTER). 

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-2015-0095; or in person at the Docket 

Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Katheryn Malatek, Aerospace 

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

England Executive Park, Burlington, MA 01803; phone: 781-238-7747; fax: 781-238-

7199; email: katheryn.malatek@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by 

adding an AD that would apply to the specified products. The NPRM was published in 

the Federal Register on April29, 2015 (80 FR 23741). The NPRM proposed to correct 

an unsafe condition for the specified products. The MCAI states: 

There were a number of pre-MOD/SB 72-7730 High Pressure 

Turbine (HPT) blade failures, with some occurring within a 

relatively short time. Engineering analysis carried out by RR on 

those occurrences indicates that certain pre-MOD/SB 72-7730 

blades, Part Number (PIN) UL32958 and PIN UL21691 (hereafter 

referred to as 'affected HPT blade'), with an accumulated life of 

6500 flight hours (FH) since new or more, have an increased risk 

of in-service failure. 

This condition, if not corrected, could lead to HPT blade failure, 

release of debris and consequent (partial or complete) loss of 

engine power, possibly resulting in reduced control of the 

aeroplane. 

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We reviewed the available data and determined that air safety and the public 

interest require adopting this AD as proposed. 

Costs of Compliance 

We estimate that this AD affects 6 engines installed on airplanes of U.S. registry. 

We also estimate that it will take about 4 hours per engine to comply with this AD. The 

average labor rate is $85 per hour. Pro-rated cost of required parts is about $250,000 per 

engine. Based on these figures, we estimate the cost of this AD on U.S. operators to be 

$1,502,040. 

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 

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Executive Order 13 1 32. 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. 

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 

l. The authority citation for part 39 continues to read as follows: 

Authority: 49 U.S.C. 1 06(g), 40113, 44701. 

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Directorate Identifier 20 15-NE-0 l-AD. 

(a) Effective Date 

This 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 plc (RR) RB211-524B-02, RB211 -524B2-19, 

RB211-524B3-02, RB211-524B4-02, RB211-524B4-D-02, RB211-524C2-19, RB211-

524D4-19, RB211 -524D4-39, and RB211-524D4X-19 turbofan engines with highpressure turbine (HPT) blades, part numbers (PINs) UL32958 and UL21691, installed. 

(d) Reason 

This AD was prompted by several failures of affected HPT blades. We are issuing 

this AD to prevent failure of the HPT blade, which could lead to failure of one or more 

engines, loss of thrust control, and damage to the airplane. 

(e) Actions and Compliance 

Comply with this AD within the compliance times specified, unless already done. 

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

AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email 

your request to: ANE-AD-AMOC@faa.gov. 

(g) Related Information 

(1) For more information about this AD, contact Katheryn Malatek, Aerospace 

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

England Executive Park, Burlington, MA 01803; phone: 781-238-7747; fax: 781-238-

7199; email: katheryn.malatek@faa.gov. 

(2) Refer to MCAI European Aviation Safety Agency AD 2014-0250, dated 

November 19,2014, for more information. You may examine the MCAI in the AD 

docket on the Internet at http://www.regulations.gov by searching for and locating it in 

Docket No. FAA-2015-0095. 

(h) Material Incorporated by Reference 

None. 

[ssued in Burlington, Massachusetts, on July 30, 2015. 

Ann C. Mollica, Acting Assistant Directorate Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

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