[4910-13-P] 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. F AA-2012-1006; Directorate Identifier 2012-NE-28-AD; Amendment 

39-17392; AD 2013-05-20] 

RIN 2120-AA64 

Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Turbojet 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) Spey 511-8 turbojet engines. This AD requires 

inspection and, if necessary, replacement of affected bolts and, if any bolt is found 

broken, inspection of the adjacent disc(s) for damage. 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. 

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 W12-140, 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 ; phone: 781-238-7779; fax: 781-238-7199; email: 

frederick.zink@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 November 7, 2012 (77 FR 66769). 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) support assembly, high pressure turbine (HPT) bearing 

support assembly and HPT air seal sleeve bolts identified that, 

before installation, those bolts are not subjected to a complete 

quality inspection. As a consequence, bolts with reduced material 

properties may have been installed in some engines. 

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 66769, November 7, 2012). 

However, we made editorial changes to paragraph (e) ofthis AD for clarification 

purposes. Paragraphs (e)( 1) and ( e )(2) were re-written to clearly define the drawdown for 

engines that have accumulated more then 4,500 engine cycles since the last engine shop 

2 
visit on the effective date of the AD. If an engine had greater than 4,500 cycles since the 

last engine shop visit, paragraph (e)(1) ofthe NPRM (77 FR 66769, November 7, 2012) 

could be interpreted to mean that the actions were required before further flight. This is 

not the intent of the proposed rule. Paragraph ( e )(2) of the NPRM specified that an 

inspection within 100 engine cycles was required for engines with greater than 4,400 

cycles since last shop visit, but we determined that this could be confusing. We therefore 

changed paragraphs ( e )(1) and ( e )(2) in the final rule to: 

( 1) If engine cycles accumulated since the last engine shop visit are 4,400 cycles 

or more on the effective date of this AD, visually inspect the bolts installed in the lowpressure turbine (LPT) support assembly, high-pressure turbine (HPT) bearing support 

assembly, and HPT air seal sleeve within 100 engine cycles-in-service. 

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

4,400 cycles on the effective date of this AD, visually inspect the bolts installed in the 

LPT support assembly, HPT bearing support assembly, and HPT air seal sleeve before 

accumulating 4,500 engine cycles since the last shop visit. 

Paragraph (e) was also modified to clarify that the type of inspection required is a 

visual inspection. The NPRM only stated to " inspect." 

Paragraph (e) was also modified by removing the reporting requirement, because 

that requirement is not necessary to correct the unsafe condition. 

Conclusion 

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

interest require adopting the AD with the changes described previously. We determined 

3 
that these changes will not increase the economic burden on any operator or increase the 

scope ofthe AD. 

Costs of Compliance 

We estimate that this AD affects about six engines installed on airplanes of U.S. 

registry. We also estimate that it will take about 2 hours per engine to comply with this 

AD. The average labor rate is $85 per hour. Required parts will cost about $860 per 

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

$6,180. 

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 I 06, 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 AD will not have federalism implications under 

Executive Order 13132. This AD will not have a substantial direct effect on the States, on 

4 
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); 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 

AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on the Internet at http://www.regul ations.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. 

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: 

5 
PART 39 -AIRWORTHINESS DIRECTIVES 

I. 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: 

2013-05-20 Rolls-Royce Deutschland Ltd & Co KG (formerly Rolls-Royce 

Deutschland GmbH, formerly Rolls-Royce pic): Amendment 39-17392; Docket No. 

F AA-20 12-1 006; Directorate Identifier 20 12-NE-28-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) Spey 511-8 

turbojet engines, serial numbers 8847, 8853, 8879, 8989, 8994, and 9817, with a date of 

the last shop visit before November 15, 2007. 

(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. 

6 
(e) Actions and Compliance 

Unless already done, do the following actions for engines with a date of the last 

shop visit before November 15, 2007: 

(1) If engine cycles accumulated since the last engine shop visit are 4,400 cycles 

or more on the effective date of this AD, visually inspect the bolts installed in the lowpressure turbine (LPT) support assembly, high-pressure turbine (HPT) bearing support 

assembly, and HPT air seal sleeve within 100 engine cycles-in-service. 

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

4,400 cycles on the effective date of this AD, visually inspect the bolts installed in the 

LPT support assembly, HPT bearing support assembly, and HPT air seal sleeve before 

accumulating 4,500 engine cycles since the last shop visit. 

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

surface, replace all bolts of the inspected engine flange with new bolts before further 

flight. 

( 4) If you find any broken bolt in the LPT support assembly, visually inspect the 

LPT stage 2 disc for damage before further flight. 

( 5) If you find any broken bolt in the HPT shaft air seal sleeve, visually inspect 

the HPT stage 1 disc for damage before further flight. 

(f) Installation Prohibition 

After the effective date of this AD, do not install any LPT support assembly, HPT 

bearing support assembly, or HPT air seal sleeve into any engine, or any engine onto an 

airplane, unless the affected bolts have been inspected and replaced if necessary, and the 

7 
LPT stage 2 disc and HPT stage 1 disc have been inspected if necessary, as specified in 

paragraph (e) of this AD. 

(g) Definition 

For the purpose of this AD, a shop visit is when the engine is inducted into the 

shop for any maintenance involving the separation of pairs of major mating engine 

flanges (lettered flanges). However, the separation of engine flanges solely for the 

purposes of transporting the engine without subsequent engine maintenance is not an 

engine shop visit. 

(h) 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. 

(i) 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 2012-0158, dated August 22, 

2012, and RRD Alert Service Bulletin Sp72-A1068, 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 

8 
England Executive Park, Burlington, MA. For information on the availability of this 

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

(j) Material Incorporated by Reference 

None. 

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

Colleen M. D' Alessandro, 

Assistant Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

9