Federal Register / Vol. 77, No. 237 / Monday, December 10, 2012 / Rules and Regulations 73265 

Oversight Committee, the division also 

oversees and coordinates FHFA 

activities that involve certain data 

analysis, and analysis affecting housing 

finance and financial markets. 

(4) Division of Federal Home Loan 

Bank Regulation. The division supports 

and implements the responsibilities of 

the Deputy Director described in 

paragraph (d) of this section, including 

overseeing and directing all Bank 

supervisory activities, developing 

examination findings, preparing reports 

of examination, and preparing the 

sections of the annual report to Congress 

that describe the condition and 

performance of the Banks. The division 

monitors and assesses the financial 

condition and performance of the Banks 

and the OF and monitors and assesses 

their compliance with regulations, the 

amount of risk they assume, and the 

quality of their risk management 

through annual on-site examinations, 

periodic visits, and ongoing off-site 

monitoring and analysis. 

(5) Office of Inspector General. The 

office is headed by a presidentially 

appointed and Senate-confirmed 

Inspector General who serves under the 

general supervision of the Director. The 

office carries out activities and 

responsibilities established in the 

Inspector General Act of 1978. 

(6) Office of General Counsel. The 

office advises and supports the Director 

and FHFA staff on legal matters related 

to the functions, activities, and 

operations of FHFA and the regulated 

entities; it supports supervision 

functions, development and 

promulgation of regulations and orders, 

and enforcement actions. The office 

manages the Freedom of Information, 

Privacy Act and ethics programs. The 

Designated Agency Ethics Official 

advises, counsels, and trains FHFA 

employees on ethical standards and 

conflicts of interest, and manages the 

agency’s financial disclosure program. 

(7) Office of the Ombudsman. The 

office is responsible for considering 

complaints and appeals from the 

regulated entities, the OF and any 

person that has a business relationship 

with a regulated entity or the OF 

concerning any matter relating to 

FHFA’s regulation and supervision of 

that entity or the OF. 

(8) Office of Minority and Women 

Inclusion. The office is responsible for 

all matters of FHFA relating to diversity 

in management, employment, and 

business activities, and for supervising 

the diversity requirements applicable to 

the regulated entities and the OF. 

(f) Other Offices and Departments. 

The Director may from time to time 

establish other Offices and Divisions of 

the agency as the Director deems 

necessary or appropriate to carry out 

FHFA’s mission, such as an Office of 

Conservatorship Operations during such 

period as regulated entities are under 

FHFA’s conservatorship; an Office of 

Strategic Initiatives to manage such 

strategic initiatives as the Director may 

identify; and a Division of Supervision 

Policy and Support to facilitate 

consistent supervision and examination 

policies across all regulated entities. 

The Director may also establish other 

Offices and positions as the Director 

deems necessary and appropriate to 

support the operations of a federal 

agency, such as a Chief Operating 

Officer, a Chief Financial Officer, an 

Office of Information Technology, and 

such other offices, departments, and 

positions as are necessary and 

appropriate or may be required by 

statute. 

(g) Additional information. Current 

information on the organization of 

FHFA may be obtained by mail from the 

Office of Congressional Affairs and 

Communications, 400 Seventh Street, 

SW., Washington, DC 20024. Such 

information, as well as other FHFA 

information, also may be obtained 

electronically by accessing FHFA’s Web 

site located at www.FHFA.gov. 

§ 1200.3 Official logo and seal. 

This section describes and displays 

the logo adopted by the Director as the 

official symbol representing FHFA. It is 

displayed on correspondence, selected 

documents, and signage. The logo serves 

as the official seal to certify and 

authenticate official documents of the 

agency. 

(a) Description. The logo is a disc 

consisting of three polygons each drawn 

in a manner resembling a silhouette of 

a pitched roof house and with 

distinctive eaves under its roof. Each 

polygon is placed one in front of the 

other, two of which are diminished in 

size from the polygon behind it. Placed 

in the center of the smallest polygon is 

the acronym for the organization, 

‘‘FHFA.’’ The polygons are encircled by 

a designation scroll having an outer and 

inner border of plain heavy lines and 

containing the words ‘‘FEDERAL 

HOUSING FINANCE AGENCY’’ in 

capital letters with serifs, with two 

mullets on the extreme left and right of 

the scroll. 

(b) Display. FHFA’s official logo and 

seal appears below: 

Chapter XVII—Office of Federal Housing 

Enterprise Oversight, Department of 

Housing and Urban Development 

PART 1700—[REMOVED] 

■ 3. Remove part 1700. 

Dated: December 3, 2012. 

Edward J. DeMarco, 

Acting Director, Federal Housing Finance 

Agency. 

[FR Doc. 2012–29695 Filed 12–7–12; 8:45 am] 

BILLING CODE 8070–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1243; Directorate 

Identifier 2007–SW–03–AD; Amendment 39– 

17267; AD 2012–23–11] 

RIN 2120–AA64 

Airworthiness Directives; Erickson AirCrane Incorporated Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Erickson Air-Crane Incorporated 

(Erickson) Model S–64F helicopters. 

This AD requires inspecting for cracking 

or working rivets in each left and right 

splice fitting (transition fitting), the 

pylon bulkhead assembly-canted 

(bulkhead assembly), and the pylon 

steel strap (strap). This AD was 

prompted by several reports of cracking 

in the transition fittings, the bulkhead 

assembly, and the pylon. The actions 

specified by this AD are intended to 

detect cracking in the rotary rudder 

boom or pylon due to fatigue, and to 

prevent failure from static overload and 

subsequent loss of control of the 

helicopter. 

DATES: This AD is effective January 14, 

2013. 


srobinson on DSK4SPTVN1PROD with ER10DE12.004</GPH>
73266 Federal Register / Vol. 77, No. 237 / Monday, December 10, 2012 / Rules and Regulations 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of January 14, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Erickson 

Air-Crane Incorporated, ATTN: Chris 

Erickson/Compliance Officer, 3100 

Willow Springs Rd., P.O. Box 3247, 

Central Point, OR 97502; telephone 

(541) 664–5544; fax (541) 664–2312; 

email cerickson@ericksonaircrane.com. 

You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

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, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Michael Kohner, Aviation Safety 

Engineer, Rotorcraft Certification Office, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5170; email 

7-avs-asw-170@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On November 26, 2008, at 73 FR 

71952, the Federal Register published 

our notice of proposed rulemaking 

(NPRM), which proposed to amend 14 

CFR part 39 to include an AD that 

would apply to Erickson Model S–64F 

helicopters with a transition fitting, part 

number (P/N) 6420–66341–101, –102, 

–103, or –104; bulkhead assembly, P/N 

6420–66340–041, –043, or –044; or a 

strap, P/N 6420–66301–119 or –127, 

installed. That NPRM proposed to 

require inspecting for cracking or 

working rivets in each transition fitting, 

the bulkhead assembly, the strap, and 

the attaching rotary rudder boom and 

pylon structure, and repairing or 

replacing any cracked or damaged part 

with an airworthy part. The NPRM also 

proposed to require, for any part where 

you could not visually determine that a 

crack does not exist, inspecting using a 

10-power or higher magnifying glass. If 

you could not determine that a crack 

does not exist in the part after 

inspecting it with a 10-power or higher 

magnifying glass, the NPRM proposed to 

require performing a fluorescent particle 

inspection (FPI) of any part other than 

a strap, and performing a magnetic 

particle inspection (MPI) of any strap. 

The NPRM also proposed to require 

replacing any loose or working rivet. 

The proposed requirements were 

intended to detect cracking in the rotary 

rudder boom or pylon due to fatigue, 

and to prevent failure from static 

overload and subsequent loss of control 

of the helicopter. 

Comments 

After our NPRM (73 FR 71952, 

November 26, 2008) was published, we 

received comments from one 

commenter. 

Request 

A commenter from Erickson AirCrane asked that we delete the bulkhead 

assembly, P/N 6420–66340–041, from 

the applicability and compliance 

section of the NPRM (73 FR 71952, 

November 26, 2008) since that P/N is 

not used on Erickson Model S–64F 

helicopters. We agree and have revised 

this AD accordingly. 

The commenter also asked that we 

delete the words ‘‘other than a strap’’ 

from the requirement to perform an FPI 

on a part other than a strap if you 

cannot determine that a crack does not 

exist, and delete the entire requirement 

to perform an MPI of the strap if you 

cannot determine that a crack does not 

exist. The commenter states that an MPI 

cannot be performed on the strap when 

it is installed on a helicopter; instead an 

FPI of the strap would need to be 

performed with the other parts. We 

partially agree. We agree that an MPI 

cannot be performed on the strap while 

it is installed on the helicopter because 

the strap is attached to the aluminum 

pylon section. An MPI for the strap was 

initially proposed in the NPRM (73 FR 

71952, November 26, 2008) because this 

would be the type of inspection 

normally used for a steel part. Instead of 

changing the MPI on the strap to an FPI 

as requested, after further review, we 

determined that deleting this 

inspection, as well as the magnifying 

glass inspection and certain FPIs that 

were proposed in the NPRM, will not 

impact the overall level of safety. These 

inspections were included in the event 

a visual inspection was insufficient to 

determine whether a crack exists. If any 

additional inspections are necessary to 

determine if a crack exists, a qualified 

individual performing the inspection 

must make this determination. 

FAA’s Determination 

We have reviewed the relevant 

information, considered the comments 

received, and determined that an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design and that air safety and the 

public interest require adopting the AD 

requirements as proposed with the 

changes described previously and minor 

editorial changes. We have also revised 

the estimated costs of complying with 

this AD to reflect an average labor rate 

of $85 per work-hour instead of $80 per 

work-hour. These changes are consistent 

with the intent of the proposals in the 

NPRM (73 FR 71952, November 26, 

2008) and will not increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Related Service Information 

We have reviewed Erickson Service 

Bulletin (SB) No. 64B20–6, Revision A, 

dated December 12, 2007, which 

describes procedures for inspecting the 

transition fittings, the bulkhead 

assembly, the strap, and the attaching 

rotary rudder boom and pylon structure 

for cracking or working rivets. We have 

also reviewed Erickson SB No. 64F 

General-3, Revision C, dated December 

12, 2007, which summarizes a listing of 

a portion of the Model S–64F helicopter 

components, their part numbers, and 

the corresponding SBs to use when 

performing the structural inspections. 

Costs of Compliance 

We estimate that this AD will affect 7 

helicopters of U.S. Registry. We estimate 

that operators may incur the following 

costs in order to comply with this AD. 

It will take about 0.75 work-hour to 

visually inspect the transition fittings, 

skin panels, the bulkhead assembly, 

strap, and pylon exterior in the strap 

area; we estimate 30 of these visual 

inspections per year. It will take about 

0.50 work-hour to visually inspect the 

pylon interior in the strap area; we 

estimate 4 of these visual inspections 

per year. It will take about 0.75 workhour to visually and fluorescent 

penetrant inspect the skin panels at the 

transition fitting; we estimate 

performing these inspections 1 time per 

year. It will take about 40 work-hours to 

repair a pylon structural assembly. The 

average labor rate is $85 per work-hour 

and the cost for required parts to repair 

a pylon structural assembly is 

approximately $50,000. Based on these 

figures, we estimate the annual cost of 

the inspections will be $2,146 per 

helicopter and $15,024 for the fleet on 


srobinson on DSK4SPTVN1PROD with 
Federal Register / Vol. 77, No. 237 / Monday, December 10, 2012 / Rules and Regulations 73267 

U.S. operators. The estimated cost to 

repair a pylon structural assembly, 

including the cost for replacement parts 

and labor, is $53,400. 

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 to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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): 

2012–23–11 Erickson Air-Crane 

Incorporated: Amendment 39–17267; 

Docket No. FAA–2008–1243; Directorate 

Identifier 2007–SW–03–AD. 

(a) Applicability 

This AD applies to Erickson Air-Crane 

Incorporated (Erickson) Model S–64F 

helicopters with a left or right splice fitting 

(transition fitting), part number (P/N) 6420– 

66341–101, –102, –103, or –104; pylon 

bulkhead assembly-canted (bulkhead 

assembly), P/N 6420–66340–043 or –044; or 

a pylon steel strap (strap), P/N 6420–66301– 

119 or –127, installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

cracking in the rotary rudder boom or pylon 

due to fatigue, failure from static overload, 

and subsequent loss of control of the 

helicopter. 

(c) Effective Date 

This AD becomes effective January 14, 

2013. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) Within 20 hours time-in-service (TIS), 

and thereafter at intervals not to exceed 20 

hours (TIS): 

(i) Visually inspect each transition fitting, 

P/N 6420–66341–101, –102, –103, or –104, 

for a crack or working rivets on the inboard 

face of the rotary rudder boom and pylon, 

paying particular attention to the fastener 

attachment holes, as depicted in Figure 1, 

Detail A, of the Accomplishment Instructions 

in Erickson Air-Crane Incorporated Service 

Bulletin No. 64B20–6, Revision A, dated 

December 12, 2007 (SB). 

(ii) Visually inspect the outboard face of 

each rotary rudder boom and pylon skin 

panel (skin panel) that attaches to the 

transition fittings for a crack or working 

rivets in the transition fitting attachment 

areas, paying particular attention to the 

fastener attachment holes, as shown in Figure 

1, Detail B, of the Accomplishment 

Instructions in the SB. 

(iii) Visually inspect the forward and aft 

sides of each bulkhead assembly, P/N 6420– 

66340–043 or –044, for a crack. Pay 

particular attention to the circled areas 

shown in Figure 2 of the Accomplishment 

Instructions in the SB. 

(iv) Visually inspect the upper 12 inches of 

each strap, P/N 6420–66301–119 or –127, for 

a crack or for working rivets as shown in 

Figure 3 of the Accomplishment Instructions 

in the SB. 

(v) Visually inspect the pylon for a crack 

or working rivets on each side of the upper 

12 inches of the strap, and also 6 inches 

above the end of the strap as shown in Figure 

3 of the Accomplishment Instructions in the 

SB. 

(2) For any pylon with a strap installed, 

within 155 hours TIS, and thereafter at 

intervals not to exceed 155 hours TIS, 

remove the inspection access covers, P/N 

6420–66304–109 and P/N 6420–66303–125, 

on the forward and aft sides of the pylon and 

visually inspect the left-hand cap angle 

(longeron), P/N 6420–66304–136, and the 

interior area of the pylon adjacent to the 

upper 12 inches of the strap, as well as 6 

inches above the end of the strap, for a crack 

or working rivets, as shown in Figure 3 of the 

Accomplishment Instructions in the SB. 

(3) At each transition fitting replacement, 

which is required at intervals not to exceed 

8,300 hours TIS: 

(i) With each transition fitting removed, 

visually inspect both sides of each skin panel 

for a crack in the areas to which the 

transition fitting attaches, paying particular 

attention to the fastener attachment holes, as 

depicted in Details A and B, Figure 1, of the 

Accomplishment Instructions in the SB. 

(ii) Perform a fluorescent penetrant 

inspection of each skin panel for a crack in 

the areas around the fastener holes where the 

transition fittings attach to the rotary rudder 

boom and pylon. 

(4) If there is a crack, before further flight, 

replace any cracked part with an airworthy 

part, or repair the cracked part if the damage 

is within the maximum repair damage limits. 

Note to paragraph (e)(4) of this AD: The 

maximum repair damage limitations are 

stated in the applicable Component and 

Repair Overhaul Manual. 

(5) If any loose or working rivets are found, 

before further flight, remove the rivets and 

visually inspect the fastener holes and 

surrounding area for a crack or any other 

damage. Replace any part that is cracked 

with an airworthy part; replace any damaged 

part with damage exceeding the maximum 

repair damage limits with an airworthy part; 

or repair any damaged part that is within the 

maximum repair damage limits. Also, replace 

any loose or working rivets. 

(f) Special Flight Permits 

Special flight permits may be issued in 

accordance with 14 CFR 21.197 and 21.199 

to operate the helicopter to a location where 

the inspection requirements of this AD can 

be accomplished. No special flight permits 

will be issued to accomplish replacements or 

repairs, or if a crack is suspected. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to: Michael Kohner, 

Aviation Safety Engineer, Rotorcraft 

Certification Office, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5170; 

email 7-avs-asw-170@faa.gov. 


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73268 Federal Register / Vol. 77, No. 237 / Monday, December 10, 2012 / Rules and Regulations 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Additional Information 

Erickson Air-Crane Service Bulletin No. 

64F General-3, Revision C, dated December 

12, 2007, which is not incorporated by 

reference, contains additional information 

about the subject of this AD. For this service 

information, contact Erickson Air-Crane 

Incorporated, ATTN: Chris Erickson/ 

Compliance Officer, 3100 Willow Springs 

Rd., P.O. Box 3247, Central Point, OR 97502; 

telephone (541) 664–5544; fax (541) 664– 

2312; email cerickson@ericksonaircrane.com. 

You may also review this service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5302, Rotorcraft Tail Boom. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Erickson Air-Crane Incorporated Service 

Bulletin No. 64B20–6, Revision A, dated 

December 12, 2007. 

(ii) Reserved. 

(3) For Erickson Air-Crane Incorporated 

service information identified in this AD, 

contact Erickson Air-Crane Incorporated, 

ATTN: Chris Erickson/Compliance Officer, 

3100 Willow Springs Rd., P.O. Box 3247, 

Central Point, OR 97502; telephone (541) 

664–5544; fax (541) 664–2312; email 

cerickson@ericksonaircrane.com. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(5) You may view this service information 

that is incorporated by reference 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 Fort Worth, Texas, on November 

13, 2012. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–28434 Filed 12–7–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1117; Directorate 

Identifier 2012–NE–25–AD; Amendment 39– 

17275; AD 2012–24–05] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Rolls-Royce plc (RR) RB211-Trent 900 

series turbofan engines. This AD 

requires inspection of the low pressure 

turbine (LPT) bearing housing end cover 

assembly in certain engines and, if 

necessary, its replacement. This AD was 

prompted by a Trent 900 engine 

experiencing a high intermediate 

pressure vibration fault, along with 

other fluctuating engine parameters, 

while in flight. We are issuing this AD 

to prevent fracture of the oil transfer 

tube, which could result in uncontained 

failure of the engine and damage to the 

airplane. 

DATES: This AD becomes effective 

December 26, 2012. 

We must receive comments on this 

AD by January 24, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of December 26, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

For service information identified in 

this AD, contact Rolls-Royce plc, 

Corporate Communications, P.O. Box 

31, Derby, England, DE248BJ; phone: 

011–44–1332–242424; fax: 011–44– 

1332–245418 or email from http:// 

www.rolls-royce.com/contact/ 

civil_team.jsp, or download the 

publication from https:// 

www.aeromanager.com. You may view 

this 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. 

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 the same as the Mail 

address provided in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Alan Strom, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7143; fax: 781–238– 

7199; email: alan.strom@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive AD No. 2012– 

0145, dated August 6, 2012 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

During a revenue service flight, a Trent 900 

engine experienced a high Intermediate 

Pressure (IP/N2) vibration fault along with 

several other fluctuating engine parameters, 

including Low Pressure (LP/N1) faults. The 

flight crew decided to throttle back the 

engine to idle and performed an air turn 

back. The other engines continued to operate 

normally and an uneventful landing was 

made. 

The results of an initial investigation 

revealed that the LP system was seized. 

Removal of the Low Pressure Turbine (LPT) 

bearing housing end cover revealed that the 

oil transfer tube assembly had fractured 

because the spherical seat between the oil 

transfer tube and the end cover was missing 

(not installed). 

This non-conformity caused the fracture of 

the oil transfer tube, leading to reduced oil 

flow and subsequent damage to the LP and 

IP bearings. Rolls-Royce has identified that 

other Trent 900 engines could potentially be 

affected. 

The in-service event engine was 

assembled at the factory by RR. After the 

in-service event, RR inspected all LPT 

bearing housing end cover assemblies 


srobinson on DSK4SPTVN1PROD with