Federal Register / Vol. 75, No. 212 / Wednesday, November 3, 2010 / Rules and Regulations 67613 

TABLE 3—AFFECTED TAY 650–15 ENGINES BY SERIAL NUMBER (ADDED

NEW IN THIS AD)—Continued 

Engine serial No. 

17694 

17698 

17707 

17716 

17718 

17719 

17731 

17756 

17757 

Reason 

(d) This AD revision results from: 

(1) The need to correct the applicability 

paragraph of AD 2010–17–12; and 

(2) From mandatory continuing 

airworthiness information (MCAI) issued by 

an aviation authority of another country to 

identify and correct an unsafe condition on 

an aviation product. The MCAI states: 

(3) Strip results from some of the engines 

listed in the applicability section of this AD 

revealed excessively corroded low-pressure 

turbine disks stage 2 and stage 3. The 

corrosion is considered to be caused by the 

environment in which these engines are 

operated. Following a life assessment based 

on the strip findings it is concluded that 

inspections for corrosion attack are required. 

The action specified by this European 

Aviation Safety Agency (EASA) AD 2008– 

0122 was intended to avoid a failure of a lowpressure turbine disk stage 2 or stage 3 due 

to potential corrosion problems which could 

result in uncontained engine failure and 

damage to the airplane. It has been later 

realized that the same unsafe condition could 

potentially occur on more serial numbers for 

the Tay 650–15 engines and on the Tay 651– 

54 engines. This AD, superseding EASA AD 

2008–0122, retaining its requirements, is 

therefore issued to expand the Applicability 

in adding further engine serial numbers for 

the Tay 650–15 engines and in adding the 

Tay 651–54 engines. 

We are issuing this AD to detect corrosion 

that could cause the stage 2 or stage 3 disk 

of the LP turbine to fail, uncontained engine 

failure, and damage to the airplane. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) Prior to accumulating 11,700 flight 

cycles (FC) since new of disk life, and 

thereafter at intervals not exceeding 11,700 

FC of disk life, inspect the LP turbine disks 

stage 2 and stage 3 for corrosion using RRD 

Alert Service Bulletin (ASB) No. TAY–72– 

A1524, Revision 3, dated March 24, 2010. 

(2) For engines with disk life that already 

exceed 11,700 FC on the effective date of this 

AD, perform the inspection within 90 days 

after the effective date of this AD. 

(3) When, during any of the inspections as 

required by paragraphs (e)(1) and (e)(2) of 

this AD, corrosion is found, replace the 

affected parts. RRD TAY 650 Engine 

Manual—E–TAY–3RR, Tasks 72–52–23–200– 

000 and 72–52–24–200–000, and RRD TAY 

651 Engine Manual—E–TAY–5RR, Tasks 

72–52–23–200–000 and 72–52–24–200–000, 

contain guidance on performing the 

inspection for corrosion and rejection 

criteria. 

Previous Credit 

(f) Initial inspections done before the 

effective date of this AD on LP turbine disks 

stage 2 and stage 3 listed in Table 1 and 

Table 2 of this AD using RRD ASB No. TAY– 

72–A1524, Revision 1, dated September 1, 

2006, or Revision 2, dated June 13, 2008, 

comply with the initial inspection 

requirements specified in this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(g) The Manager, Engine Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(h) Refer to EASA AD 2010–060R1, dated 

April 14, 2010, for related information. 

Contact Rolls-Royce Deutschland Ltd & Co 

KG, Eschenweg 11, Dahlwitz, 15827 

Blankenfelde-Mahlow, Germany; phone: 011 

49 (0) 33–7086–1883; fax: 011 49 (0) 33– 

7086–3276, for a copy of the service 

information referenced in this AD. 

(i) Contact Mark Riley, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: mark.riley@faa.gov; phone: 

(781) 238–7758; fax (781) 238–7199, for more 

information about this AD. 

Material Incorporated by Reference 

(j) You must use Rolls-Royce Deutschland 

Ltd & Co KG Alert Service Bulletin No. TAY– 

72–A1524, Revision 3, dated March 24, 2010, 

to do the inspections required by this AD. 

(1) The Director of the Federal Register 

previously approved the incorporation by 

reference of RRD Alert Service Bulletin No. 

TAY–72–A1524, Revision 3, dated March 24, 

2010, listed in the AD as of September 27, 

2010 (75 FR 51651, August 23, 2010). 

(2) For service information identified in 

this AD, contact Rolls-Royce Deutschland Ltd 

& Co KG, Eschenweg 11, Dahlwitz, 15827 

Blankenfelde-Mahlow, Germany; phone: 011 

49 (0) 33–7086–1883; fax: 011 49 (0) 33– 

7086–3276. 

(3) You may review copies at the FAA, 

New England Region, 12 New England 

Executive Park, Burlington, MA; or at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

(202) 741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

October 22, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–27486 Filed 11–2–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22690; Directorate 

Identifier 2005–NE–35–AD; Amendment 39– 

16495; AD 2010–23–06] 

RIN 2120–AA64 

Airworthiness Directives; McCauley 

Propeller Systems Five-Blade Propeller 

Assemblies 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. That AD 

currently requires removing certain 

propeller hubs from service at new, 

reduced life limits and eddy current 

inspections (ECIs) of the propeller hub. 

This new AD requires removing certain 

propeller hubs from service before they 

exceed 6,000 hours time-since-new 

(TSN). This AD was prompted by a 

report of a crack in a propeller hub. We 

are issuing this AD to prevent cracked 

propeller hubs, which could cause 

failure of the propeller hub, blade 

separation, and loss of control of the 

airplane. 

DATES: This AD is effective December 8, 

2010. 

ADDRESSES: 

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: Jeff 

Janusz, Aerospace Engineer, Wichita 

Aircraft Certification Office, FAA, Small 

Airplane Directorate, 1801 Airport 

Road, Room 100, Wichita, KS 67209, 

telephone: (316) 946–4148; fax: (316) 

946–4107; e-mail: jeff.janusz@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 


emcdonald on DSK2BSOYB1PROD with RULES
67614 Federal Register / Vol. 75, No. 212 / Wednesday, November 3, 2010 / Rules and Regulations 

part 39 to supersede airworthiness 

directive (AD) 2005–24–08, Amendment 

39–14388. (70 FR 71756, November 30, 

2005). That AD applies to the specified 

products. That NPRM published in the 

Federal Register on June 17, 2010 (75 

FR 34390). That NPRM proposed to 

require: 

• Removing from service the hub of any 

propeller assembly, P/N B5JFR36C1101/ 

114GCA–0, C5JFR36C1102/L114GCA–0, 

B5JFR36C1103/114HCA–0, or 

C5JFR36C1104/L114HCA–0, if the hub 

exceeds 6,000 hours TSN on the effective 

date of this AD, within 250 hours time-inservice (TIS) after the effective date of this 

AD. 

• Removing from service the hub of any 

propeller assembly, P/N B5JFR36C1101/ 

114GCA–0, C5JFR36C1102/L114GCA–0, 

B5JFR36C1103/114HCA–0, or 

C5JFR36C1104/L114HCA–0, if the hub has 

fewer than 6,000 hours TSN, not later than 

6,000 hours TSN. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed—except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Costs of Compliance 

We estimate that this AD affects 30 

engines installed on airplanes of U.S. 

registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Remove the propeller hub from service ......... 42 work-hours × $85 per hour = $3,570 ........ $6,000 $9,570 $287,100 

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 have 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 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, 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 

removing airworthiness directive (AD) 

2005–24–08, Amendment 39–14388. (70 

FR 71756, November 30, 2005), and 

adding the following new AD: 

2010–23–06 McCauley Propeller Systems: 

Amendment 39–16495; Docket No. 

FAA–2005–22690; Directorate Identifier 

2005–NE–35–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective December 8, 2010. 

Affected ADs 

(b) This AD supersedes AD 2005–24–08, 

Amendment 39–14388. 

Applicability 

(c) This AD applies to McCauley Propeller 

Systems propeller assemblies, part numbers 

(P/Ns) B5JFR36C1101/114GCA–0, 

C5JFR36C1102/L114GCA–0, B5JFR36C1103/ 

114HCA–0, and C5JFR36C1104/L114HCA–0. 

These propeller assemblies are installed on 

BAE Systems (Operations) Limited Jetstream 

Model 4100 series airplanes. 

Unsafe Condition 

(d) This AD results from a report of a 

cracked propeller hub. We are issuing this 

AD to prevent cracked propeller hubs, which 

could cause failure of the propeller hub, 

blade separation, and loss of control of the 

airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

Propeller Hub Reduced Life Limits 

(f) For any propeller assembly, P/N 

B5JFR36C1101/114GCA–0, C5JFR36C1102/ 

L114GCA–0, B5JFR36C1103/114HCA–0, or 

C5JFR36C1104/L114HCA–0, with a hub that 

exceeds 6,000 hours time-since-new (TSN) 

on the effective date of this AD, remove the 

propeller hub from service within 250 hours 

time-in-service after the effective date of this 

AD. 

(g) For any propeller assembly, P/N 

B5JFR36C1101/114GCA–0, C5JFR36C1102/ 

L114GCA–0, B5JFR36C1103/114HCA–0, or 

C5JFR36C1104/L114HCA–0, with a hub with 

fewer than 6,000 hours TSN, remove the 

propeller hub from service not later than 

6,000 hours TSN. 

Prohibition of Hubs Exceeding Life Limit 

(h) After the effective date of this AD, don’t 

install any hub removed from any propeller 

assembly that was removed by paragraphs (f) 

or (g) of this AD into any propeller assembly. 


emcdonald on DSK2BSOYB1PROD with RULES
Federal Register / Vol. 75, No. 212 / Wednesday, November 3, 2010 / Rules and Regulations 67615 

1The Commission last amended Appendix D4 

(comparability ranges for instantaneous gas water 

heaters) on August 29, 2007 (72 FR 49948). The 

correct capacity descriptor for instantaneous water 

heaters is maximum flow rate measured in gallons 

per minute, not ‘‘first hour rating’’ as the current 

Rule indicates. 

Alternative Methods of Compliance 

(i) The Manager, Wichita Aircraft 

Certification Office, has the authority to 

approve alternative methods of compliance 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Related Information 

(j) Contact Jeff Janusz, Aerospace Engineer, 

Wichita Aircraft Certification Office, FAA, 

Small Airplane Directorate, 1801 Airport 

Road, Room 100, Wichita, KS 67209, 

telephone: (316) 946–4148; fax: (316) 946– 

4107, for more information about this AD. 

Material Incorporated by Reference 

(k) None. 

Issued in Burlington, Massachusetts, on 

October 25, 2010. 

Karen M. Grant, 

Acting Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–27608 Filed 11–2–10; 8:45 am] 

BILLING CODE 4910–13–P 

FEDERAL TRADE COMMISSION 

16 CFR Part 305 

[RIN 3084–AB03] 

Appliance Labeling Rule 

AGENCY: Federal Trade Commission. 

ACTION: Correcting amendments. 

SUMMARY: The Federal Trade 

Commission (‘‘Commission’’) is issuing 

technical corrections to the Appliance 

Labeling Rule (16 CFR Part 305). This 

document republishes the text of 

§ 305.20(f) concerning catalog 

requirements not published in the CFR 

and corrects text in Appendix D4 

concerning labels for instantaneous 

water heaters. 

DATES: Effective Date: July 19, 2011. 

FOR FURTHER INFORMATION CONTACT: 

Hampton Newsome, Attorney, Division 

of Enforcement, Bureau of Consumer 

Protection, Federal Trade Commission, 

Washington, DC 20580 (202–326–2889). 

SUPPLEMENTARY INFORMATION: The 

Commission is republishing § 305.20(f) 

of the Appliance Labeling Rule (16 CFR 

Part 305) which appeared in the Federal 

Register on October 23, 2008 (73 FR 

63066, 63068), but was inadvertently 

not printed in the Code of Federal 

Regulations. In addition, the 

Commission is correcting text in 

Appendix D4 to the change the phrase 

‘‘First Hour Rating’’ to ‘‘Capacity 

(maximum flow rate); gallons per 

minute (gpm).’’ 1

List of Subjects in 16 CFR Part 305 

Advertising, Energy conservation, 

Household appliances, Labeling, 

Reporting and recordkeeping 

requirements. 

■ For the reasons discussed above, the 

Commission amends part 305 of title 16, 

Code of Federal Regulations, as follows: 

PART 305—RULE CONCERNING 

DISCLOSURES REGARDING ENERGY 

CONSUMPTION AND WATER USE OF 

CERTAIN HOME APPLIANCES AND 

OTHER PRODUCTS REQUIRED 

UNDER THE ENERGY POLICY AND 

CONSERVATION ACT (‘‘APPLIANCE 

LABELING RULE’’) 

■ 1. The authority citation for Part 305 

continues to read as follows: 

Authority: 42 U.S.C. 6294. 

■ 2. In § 305.20, paragraph (f) is added 

to read as follows: 

305.20 Paper catalogs and Web sites. 

* * * * * 

(f) Any manufacturer, distributor, 

retailer, or private labeler who 

advertises a covered product that is a 

ceiling fan in a catalog, from which it 

may be purchased, shall disclose clearly 

and conspicuously in such catalog, on 

each page that lists the covered product, 

all the information concerning the 

product required by § 305.13(a)(1). 

■ 3. Appendix D4 is revised to read as 

follows: 

APPENDIX D4 TO PART 305—WATER 

HEATERS—INSTANTANEOUS—GAS 

RANGE INFORMATION

Capacity Range of estimated annual operating costs 

(dollars/year) 

Capacity (maximum flow rate); gallons per minute (gpm) Natural gas ($/year) Propane ($/year) 

LOW HIGH LOW HIGH 

Under 1.00 ....................................................................... 285 285 479 479 

1.00 to 2.00 ...................................................................... 280 285 456 471 

2.01 to 3.00 ...................................................................... 174 268 346 445 

Over 3.00 ......................................................................... 199 290 301 486 

* No data submitted. 

By direction of the Commission. 

Donald S. Clark, 

Secretary. 

[FR Doc. 2010–27692 Filed 11–2–10; 8:45 am] 

BILLING CODE 6750–01–P 


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