Federal Register / Vol. 77, No. 132 / Tuesday, July 10, 2012 / Rules and Regulations 40479 

relaxation will result in blending the Cat 

III operational and system performance 

distinctions, and appears to ignore the 

potential reduction in safety’’ These 

individuals also commented that 

‘‘* * * fail-passive systems and flight 

crews trained to the fail-passive 

minimums and procedures will be 

permitted to fly to fail-operational 

minimums.’’ 

In response to Boeing’s comment, the 

FAA notes that the removal of the 

Category IIIa, IIIb, and IIIc definitions 

will not affect current FAA category III 

aircraft certifications or operator 

authorizations and will not require 

changes to other FAA regulations. 

Category III standards used in the 

United States will be completely 

unaffected by the removal of the 

Category IIIa, IIIb, and IIIc definitions. 

The Category III operational concepts 

represented by the Category IIIa, IIIb, 

and IIIc definitions are used to develop 

the certification and authorization 

criteria and these criteria are then 

applied directly to individual aircraft 

certifications and operator 

authorizations. Thus, the certification of 

Category III aircraft systems under 

Advisory Circular (AC) 120–28D no 

longer directly refers to the Category 

IIIa, b, and c definitions contained in 14 

CFR 1.1, but uses the airworthiness 

criteria in the AC and the certification 

statements refer to those criteria as well. 

Likewise, Operations Specification 

(OpSpec) C060, the operational 

authorization for Category III operators, 

no longer specifically uses the Category 

IIIa, IIIb, and IIIc definitions, but rather 

ties authorized weather minima to the 

certification level of aircraft, as 

specified in the AC. 

In response to the individual 

comments, the FAA notes that AC 120– 

28D uses the ICAO Category IIIa, IIIb, 

and IIIc definitions in its development 

of Category III operational concepts. 

Category IIIa, IIIb, and IIIc definitions 

will continue to be used unless changed 

in the normal ICAO process. In its 

second comment, ICAO stated that this 

rulemaking would have no impact on 

the recognition of any CAT III a, b, or 

c operational approval for international 

operators or United States-issued 

operational approvals which conform to 

Annex 6—Operation of Aircraft and 

therefore has no objection to the change. 

Thus, operational authorizations for all 

operators and aircraft certification 

through AC 120–28D and OpSpec C060 

rely only upon the ICAO Category IIIa, 

IIIb, and IIIc definitions and will be 

completely unaffected by removing the 

definitions of Category IIIa, IIIb, and IIIc 

in the CFR. Additionally, the use of Fail 

Passive or Fail Operational Category III 

minima is not bound by the Category III 

definition. Category III minima are 

controlled completely by the 

operational authorization, OpSpec 

C060, under criteria contained in AC 

120–28D. Since, as explained above, the 

AC criteria will be unaffected by 

removal of the sub-definitions, CAT III 

minima authorized through the OpSpec 

will be unchanged. 

Conclusion 

After consideration of the comments 

submitted in response to the direct final 

rule, the FAA has determined that no 

further rulemaking action is necessary. 

Therefore, Amendment 1–67 remains in 

effect. 

How To Obtain Additional Information 

A. Rulemaking Documents 

An electronic copy of a rulemaking 

document my be obtained by using the 

Internet— 

1. Search the Federal eRulemaking 

Portal (http://www.regulations.gov); 

2. Visit the FAA’s Regulations and 

Policies Web page at http:// 

www.faa.gov/regulations_policies/ or 

3. Access the Government Printing 

Office’s Web page at http://www.

gpoaccess.gov/fr/index.html. 

Copies may also be obtained by 

sending a request (identified by notice, 

amendment, or docket number of this 

rulemaking) to the Federal Aviation 

Administration, Office of Rulemaking, 

ARM–1, 800 Independence Avenue 

SW., Washington, DC 20591, or by 

calling (202) 267–9680. 

B. Comments Submitted to the Docket 

Comments received may be viewed by 

going to http://www.regulations.gov and 

following the online instructions to 

search the docket number for this 

action. Anyone is able to search the 

electronic form of all comments 

received into any of the FAA’s dockets 

by the name of the individual 

submitting the comment (or signing the 

comment, if submitted on behalf of an 

association, business, labor union, etc.). 

C. Small Business Regulatory 

Enforcement Fairness Act 

The Small Business Regulatory 

Enforcement Fairness Act (SBREFA) of 

1996 requires FAA to comply with 

small entity requests for information or 

advice about compliance with statutes 

and regulations within its jurisdiction. 

A small entity with questions regarding 

this document, may contact its local 

FAA official, or the person listed under 

the FOR FURTHER INFORMATION CONTACT

heading at the beginning of the 

preamble. To find out more about 

SBREFA on the Internet, visit http://

www.faa.gov/regulations_policies/

rulemaking/sbre_act/. 

Issued in Washington, DC, on June 11, 

2012. 

John M. Allen, 

Director, Flight Standards Service. 

[FR Doc. 2012–16846 Filed 7–9–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0961; Directorate 

Identifier 2011–NE–22–AD; Amendment 39– 

17120; AD 2012–14–06] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Corporation Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Rolls-Royce Corporation (RRC) 250– 

C20, –C20B, and –C20R/2 turboshaft 

engines. This AD was prompted by 

seven cases reported of released turbine 

blades and shrouds, which led to loss of 

power and engine in-flight shutdowns 

(IFSDs). This AD requires a one-time 

visual inspection and fluorescent 

penetrant inspection (FPI) on certain 

3rd and 4th stage turbine wheels for 

cracks in the turbine blades. We are 

issuing this AD to prevent failure of 3rd 

or 4th stage turbine wheel blades which 

could cause engine failure and damage 

to the airplane. 

DATES: This AD is effective August 14, 

2012. 

ADDRESSES: For service information 

identified in this AD, contact RollsRoyce Corporation Customer Support, 

P.O. Box 420, Indianapolis, IN 46206– 

0420; phone: 888–255–4766 or 317– 

230–2720; fax: 317–230–3381, email: 

helicoptercustsupp@rolls-royce.com, 

and Web site: www.rolls-royce.com. You 

may review copies of the referenced 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 


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40480 Federal Register / Vol. 77, No. 132 / Tuesday, July 10, 2012 / Rules and Regulations 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: John 

Tallarovic, Aerospace Engineer, Chicago 

Aircraft Certification Office, FAA, 2300 

E. Devon Ave., Des Plaines, IL 60018; 

phone: 847–294–8180; fax: 847–294– 

7834; email: john.m.tallarovic@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 published in the Federal 

Register on December 20, 2011 (76 FR 

78863). That NPRM proposed to require 

a one-time visual inspection and FPI on 

certain 3rd and 4th stage turbine wheels 

for cracks in the turbine blades. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Proposed AD Applicability Clarity 

One commenter said that the 

proposed AD applicability is unclear. 

The commenter stated that the RRC 

Commercial Engine Bulletins (CEBs) 

referenced in the proposed AD apply to 

specific model 250 engines in MD 

Helicopter, Inc. aircraft only. However, 

the proposed AD appears to cover the 

subject part number (P/N) wheels in 

three engine models in all applications. 

Also, the subject P/N wheels can be 

installed in many engine models in 

addition to the 250–C20, C20B, and 

C20R/2 engines called out in the 

proposed AD. The original issue with 

the wheels cracking was tied to specific 

power turbine speed ranges as 

manifested in specific aircraft 

applications. As the proposed AD is 

written, there are airframe applications 

where one model of installed engine 

would be subject to the AD and another 

model being only slightly different and 

identical in the power turbine section 

concerned, would not be subject to the 

AD. 

We do not agree. The proposed AD is 

only applicable to the model 250–C20, 

C20B, and C20R/2 turboshaft engines on 

all installations. The affected turbine 

wheels, P/N 23065818 and P/N 

23055944, can be installed on other 

model 250 engines. However, the 

proposed AD is only applicable to the 

model 250–C20, C20B, and C20R/2 

turboshaft engines. While RRC Alert 

CEB–A–1407, Revision 1, dated 

February 7, 2011 and CEB–A–72–4098, 

Revision 1, dated February 7, 2011 

(combined in one document) is directed 

at engines installed on MD Helicopters 

Inc. aircraft, the proposed AD is 

applicable to all installations of model 

250–C20, C20B, and C20R/2 turboshaft 

engines. The service bulletins do not 

establish the applicability for the 

proposed AD. The service bulletins are 

referenced as related information only. 

We did not change the AD. 

Overhaul Period 

One commenter pointed out that 

paragraph (e)(1) of the proposed AD 

stated to remove the turbine wheels at 

the next 1,750 hour overhaul. The 

overhaul period in these engines is 

3,500 hours, not 1,750 hours. 

We agree. We changed paragraph 

(e)(1) to state to remove the 3rd stage 

turbine wheel, P/N 23065818, and the 

4th stage turbine wheel, P/N 23055944, 

before accumulating 1,750-hours since 

last inspection. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

Costs of Compliance 

We estimate that this AD will affect 

500 RRC C250–C20, –C20B, and 

–C20R/2 turboshaft engines installed on 

aircraft of U.S. registry. We also estimate 

that it will take about 5 hours to perform 

a one-time visual inspection and FPI of 

the 3rd stage turbine wheel and the 4th 

stage turbine wheel for each engine. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

total cost of the AD to U.S. operators to 

be $212,500. 

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 

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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, 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 

■ 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 airworthiness 

directive (AD): 

2012–14–06 Rolls-Royce Corporation 

(Formerly Allison Engine Company and 

Allison Gas Turbine Division of General 

Motors): Amendment 39–17120; Docket 

No. FAA–2011–0961; Directorate 

Identifier 2011–NE–22–AD. 

(a) Effective Date 

This AD is effective August 14, 2012. 

(b) Affected ADs 

None. 


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Federal Register / Vol. 77, No. 132 / Tuesday, July 10, 2012 / Rules and Regulations 40481 

(c) Applicability 

This AD applies only to Rolls-Royce 

Corporation 250–C20, –C20B, and –C20R/2 

turboshaft engines with 3rd stage turbine 

wheel, part number (P/N) 23065818, and 4th 

stage turbine wheel, P/N 23055944. 

(d) Unsafe Condition 

This AD was prompted by seven cases 

reported of released turbine blades and 

shrouds, which led to loss of power and 

engine in-flight shutdowns. We are issuing 

this AD to prevent failure of 3rd or 4th stage 

turbine wheel blades which could cause 

engine failure and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Remove the 3rd stage turbine wheel, 

P/N 23065818, and the 4th stage turbine 

wheel, P/N 23055944, within 1,750-hours 

since last inspection. 

(2) Perform a one-time visual inspection 

and a fluorescent penetrant inspection on the 

3rd and 4th stage turbine wheels for cracks 

at the trailing edge of the turbine blades near 

the fillet at the rim. 

(3) If any cracks in the trailing edge near 

the rim are detected, do not return the wheel 

to service. 

(f) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Chicago Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Use the procedures 

found in 14 CFR 39.19 to make your request. 

(g) Related Information 

(1) For more information about this AD, 

contact John Tallarovic, Aerospace Engineer, 

Chicago Aircraft Certification Office, FAA, 

2300 E. Devon Ave., Des Plaines, IL 60018; 

phone: 847–294–8180; fax: 847–294–7834; 

email: john.m.tallarovic@faa.gov. 

(2) Rolls-Royce Corporation Alert 

Commercial Engine Bulletin No. CEB–A– 

1407, Revision 1, dated February 7, 2011 and 

CEB–A–72–4098, Revision 1, dated February 

7, 2011 (combined in one document) pertain 

to the subject of this AD. 

(3) For service information identified in 

this AD, contact Rolls-Royce Corporation 

Customer Support, P.O. Box 420, 

Indianapolis, IN 46206–0420; phone: 

888–255–4766 or 317–230–2720; fax: 317– 

230–3381; email: helicoptercustsupp@rollsroyce.com, and Web site: www.rollsroyce.com. 

(4) You may review copies of the 

referenced service information at the FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803. For information on the availability of 

this material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

June 25, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–16797 Filed 7–9–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0991; Directorate 

Identifier 2010–NM–134–AD; Amendment 

39–17110; AD 2012–13–08] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain The Boeing Company Model 

747–100, 747–100B, 747–200B, 747– 

200C, 747–200F, 747–400F, 747SR, and 

747SP series airplanes, without a 

stretched upper deck or stretched upper 

deck modification. That AD currently 

requires repetitive inspections for cracks 

of each affected tension tie and of the 

surrounding structure, and related 

investigative and corrective actions if 

necessary. This new AD requires, for 

certain airplanes, modifying the tension 

tie structure or tension tie and frame 

structure at certain stations; and a postmodification inspection of the modified 

area and post-modification repetitive 

inspections of the unmodified area, and 

repair if necessary. Doing the 

modification would terminate the 

repetitive inspection requirements in 

the existing AD. This AD reduces the 

compliance time and adds inspections 

for certain airplanes. This AD was 

prompted by reports that certain 

airplanes have tension ties that are 

susceptible to widespread fatigue 

damage. This AD also results from 

reports of cracks on the forward and aft 

tension tie channels at station (STA) 740 

and STA 760, and a determination that 

initial inspection intervals need to be 

reduced. We are issuing this AD to 

prevent tension ties from becoming 

severed or disconnected from the 

frames, which could lead to rapid inflight decompression. 

DATES: This AD is effective August 14, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of August 14, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of February 16, 2006 (71 FR 

1947, January 12, 2006). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility 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 address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6428; fax: (425) 917–6590; email: 

nathan.p.weigand@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2006–01–07, 

Amendment 39–14446 (71 FR 1947, 

January 12, 2006). That AD applies to 

the specified products. The NPRM 

published in the Federal Register on 

September 22, 2011 (76 FR 58722). That 

NPRM proposed to continue to require 

repetitive inspections for cracks of each 

affected tension tie and of the 

surrounding structure, and related 

investigative and corrective actions if 

necessary. For certain airplanes, that 

NPRM proposed to require modifying 

the tension tie structure or tension tie 

and frame structure at certain stations; 

and a post-modification inspection of 

the modified area and post-modification 

repetitive inspections of the unmodified 

area, and repair if necessary. Doing the 

modification would terminate the 

repetitive inspection requirements in 

the existing AD. That NPRM also 

proposed to reduce the compliance time 


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