17082 Federal Register / Vol. 78, No. 54 / Wednesday, March 20, 2013 / Rules and Regulations 

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 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Rolls-Royce 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 April 

24, 2013. 

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: 

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: 

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. 

Comments 

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) of this 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 

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) of the 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 low-pressure 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 that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

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 of the 

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 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 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); 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. 


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Federal Register / Vol. 78, No. 54 / Wednesday, March 20, 2013 / Rules and Regulations 17083 

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. 

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 adding 

the following new AD: 

2013–05–20 Rolls-Royce Deutschland Ltd & 

Co KG (formerly Rolls-Royce 

Deutschland GmbH, formerly RollsRoyce plc): Amendment 39–17392; 

Docket No. FAA–2012–1006; Directorate 

Identifier 2012–NE–28–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective April 24, 2013. 

(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. 

(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 

low-pressure 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 

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 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. 

[FR Doc. 2013–06174 Filed 3–19–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2012–0121; Airspace 

Docket No. 12–AAL–2] 

Amendment of Class E Airspace; 

Scammon Bay, AK 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action modifies Class E 

airspace at Scammon Bay Airport, 

Scammon Bay, AK. Controlled airspace 

is necessary to accommodate aircraft 

using a new Area Navigation (RNAV) 

Global Positioning System (GPS) 

standard instrument approach 

procedures at Scammon Bay Airport. 

This action enhances the safety and 

management of aircraft operations at the 

airport. 

DATES: Effective date, 0901 UTC, June 

27, 2013. The Director of the Federal 

Register approves this incorporation by 

reference action under 1 CFR part 51, 

subject to the annual revision of FAA 

Order 7400.9 and publication of 

conforming amendments. 

FOR FURTHER INFORMATION CONTACT: 

Richard Roberts, Federal Aviation 

Administration, Operations Support 

Group, Western Service Center, 1601 

Lind Avenue SW., Renton, WA, 98057; 

telephone (425) 203–4517. 

SUPPLEMENTARY INFORMATION: 

History 

On May 9, 2012, the FAA published 

in the Federal Register a notice of 

proposed rulemaking to modify 

controlled airspace at Scammon Bay, 

AK (77 FR 27146). Interested parties 

were invited to participate in this 

rulemaking effort by submitting written 

comments on the proposal to the FAA. 

No comments were received. 

Class E airspace designations are 

published in paragraph 6005, of FAA 

Order 7400.9W dated August 8, 2012, 

and effective September 15, 2012, which 

is incorporated by reference in 14 CFR 

71.1. The Class E airspace designations 


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