[4910-13-P] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-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 Admini stration (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, ifnecessary, replacement of affected bolts and, if any bolt is found broken, inspection ofthe 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 ofpublication 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 ofproposed 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 Fed eral 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, ifnot 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 2visit on the effective date ofthe 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 ofthe proposed rule. Paragraph ( e)(2) ofthe 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 ofthis 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 ofthis 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

3that 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 ofU

.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 ofthe United States Code specifies the FAA ' s authority to issue rules on aviation safety

. Subtitle I, section I06, describes the authority ofthe FAA Administrator.

" Subtitle VII: Aviation Programs ," describes in more detail the scope ofthe 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 ofthat 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 4the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels ofgovernment. 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 ofthe Regulatory Flexibility Act. We prepared a regulatory evaluation ofthe 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. re gul ati ons .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 of fice (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:

5PART 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. FAA-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 ofpublication 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 ofthe last shop visit before November 15 , 2007 : (1) Ifengine cycles accumulated since the last engine shop visit are 4,400 cycles

or more on the effective date ofthis 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 ofthis 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) Ifyou identify any broken bolt, brown bolt, or bolt with a rough oxidized surface, replace all bolts ofthe 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 ofthis 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 ifnecessary, and the

7LPT stage 2 disc and HPT stage 1 disc have been inspected ifnecessary, as specified in paragraph (e) ofthis AD. 

### (g) Definition For the purpose ofthis AD , a shop visit is when the engine is inducted into the shop for any maintenance involving the separation ofpairs ofmajor mating engine flanges (lettered flanges). However, the separation ofengine flanges solely for the purposes oftransporting 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



### 8England Executive Park, Burlington, MA. For information on the availability ofthis 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.

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