[4910-13-P] 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA-2012-1031; Directorate Identifier 2012-NE-31-AD; Amendment 

39-17391; AD 2013-05-19] 

RIN 2120-AA64 

Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Turbofan 

Engines 

AGENCY: Federal Aviation Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new airworthiness directive (AD) for certain RollsRoyce Deutschland Ltd & Co KG (RRD) Tay 611-8 turbofan engines. This AD requires 

inspection and replacement, if necessary, of affected bolts. This AD was prompted by a 

quality review determination that bolts with reduced material properties may have been 

installed in some engines. We are issuing this AD to prevent uncontained turbine disc 

fracture and damage to the airplane. 

DATES: This AD becomes effective [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 ofTransportation, 1200 New Jersey Avenue SE., West Building Ground 

Floor, Room Wl2-140, Washington, DC 20590-0001. 
FOR FURTHER INFORMATION CONTACT: Frederick Zink, Aerospace Engineer, 

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

Executive Park, Burlington, MA 01803 ; email: frederick.zink@faa.gov; telephone: 781-

238-7779; 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 13, 2012 (77 FR 67582). That NPRM proposed to 

correct an unsafe condition for the specified products. The Mandatory Continuing 

Airworthiness Information states: 

Comments 

The results of a recent quality review of low pressure turbine 

(LPT) stage 1 static air seal and high pressure turbine (HPT) stage 

1 air seal support bolts identified that, before installation, those 

bolts may have not been inspected. As a consequence, bolts with 

reduced material properties may have been installed in some 

engmes. 

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

of a bolt, potentially causing turbine disc fracture and release of 

high-energy debris, possibly resulting in damage to the aeroplane 

and/or injury to the occupants. 

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

received no comments on the NPRM (77 FR 67582, November 13 , 2012). However, we 

changed paragraph (e) of this AD by removing the reporting requirement because that 

requirement is not necessary to correct the unsafe condition. 

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Conclusion 

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

interest require adopting the AD as proposed (77 FR 67582, November 13, 2012). 

Costs of Compliance 

Based on the service information, we estimate that this AD affects about 20 

engines of U.S. registry. We also estimate that it will take about 4 hours per product to 

comply with this AD. The average labor rate is $85 per hour. Required parts will cost 

about $1 ,848 per engine. Based on these figures, we estimate the cost of the AD on U.S. 

operators to be $4 3, 7 60. 

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. 

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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 

AD and placed it in the AD docket. 

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. 

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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. 1 06(g), 40113 , 44701. 

§ 39.13 [Amended] 

2. The FAA amends§ 39.13 by adding the following new AD: 

2013-05-19 Rolls-Royce Deutschland Ltd & Co KG: Amendment 39-17391; Docket 

No. FAA-2012-1 031; Directorate Identifier 2012-NE-31-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 Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 611-8 

turbofan engines, serial numbers 16245, 16256, 16417, 16418, 16584, 16585, 16639, 

16640, 16701 , 16702, 16813, 16814, 16853, 16854, 16879, 16880, 16898, 16905, 16906, 

16911 , 16923, 16935, and 16936, with a date of the last shop visit before December 8, 

2006. 

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(d) Reason 

This AD was prompted by a recent quality review determination that bolts with 

reduced material properties may have been installed in some engines. We are issuing this 

AD to prevent uncontained turbine disc fracture and damage to the airplane. 

(e) Actions and Compliance 

Unless already done, for engines with a date of the last shop visit before 

December 8, 2006, do the following actions: 

(1) If engine cycles accumulated since the last engine shop visit is 5,400 cycles or 

more on the effective date of this AD, inspect the bolts installed in the low-pressure 

turbine (LPT) stage I static seal and high-pressure turbine (HPT) stage 1 air seal support 

within 100 engine cycles-in-service after the effective date of this AD. 

(2) If engine cycles accumulated since the last engine shop visit is fewer than 

5,400 cycles on the effective date of this AD, inspect the bolts installed in the LPT stage 

1 static seal and HPT stage 1 air seal support before accumulating 5,500 engine cycles 

since the last engine shop visit. 

(3) If you find any broken bolt, brown bolt, or bolt with a rough oxidized surface, 

then replace all bolts of the inspected engine flange with new bolts before further flight. 

(f) Installation Prohibition 

After the effective date of this AD, do not install any HPT module and/or LPT 

module into any engine, or any engine onto an airplane, unless the bolts have been 

inspected and replaced if necessary, as specified in paragraph (e) of this AD. 

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(g) Alternative Methods of Compliance (AMOCs) 

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

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

(h) 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 2012-0163, dated August 28, 

2012, and RRD Alert Service Bulletin T A Y -72-A 1696, Revision 1, dated June 11, 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; phone: 49 0 33-7086-1200 (direct 1016); fax: 49 0 33-7086-1212. You may 

view this service information at the FAA, Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA. For information on the availability ofthis 

material at the FAA, call 781-238-7125. 

(i) Material Incorporated by Reference 

None. 

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Issued in Burlington, Massachusetts, on March 7, 2013 . 

Colleen M. D' Alessandro, 

Assistant Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

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