57736 Federal Register / Vol. 70, No. 191 / Tuesday, October 4, 2005 / Rules and Regulations 

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 the regulation: 

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. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2005–20–10 Airbus: Amendment 39–14304. 

Docket No. FAA–2005–22563; 

Directorate Identifier 2004–NM–177–AD. 

Effective Date 

(a) This AD becomes effective October 19, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Airbus Model 

A330–243, –341, –342, and –343 airplanes, 

certificated in any category. 

Unsafe Condition 

(d) This AD results from reports of damage 

to the engine blades of the first stage of the 

intermediate pressure compressor due to ice 

accumulation. We are issuing this AD to 

prevent engine damage due to ice 

accumulation, which could result in an 

engine shutdown and cause the flightcrew to 

divert to the nearest available airport. 

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. 

AFM Revision 

(f) Within 10 days after the effective date 

of this AD, revise the Normal Procedures 

section of the Airbus A330 Airplane Flight 

Manual (AFM) by inserting a copy of Airbus 

Temporary Revision (TR) 4.03.00/24, dated 

April 2, 2004, into the AFM. 

(g) When the information in Airbus TR 

4.03.00/24, dated April 2, 2004, is included 

in the general revisions of the AFM, the 

general revisions may be inserted in the 

AFM, and this TR may be removed. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(i) French airworthiness directive F–2004–

081, dated June 9, 2004, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(j) You must use Airbus Temporary 

Revision 4.03.00/24, dated April 2, 2004, to 

the Airbus A330 Airplane Flight Manual to 

perform the actions that are required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference of this document 

in accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. Contact Airbus, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France, for a copy of this service information. 

You may review copies at the Docket 

Management Facility, U.S. Department of 

Transportation, 400 Seventh Street SW., 

room PL–401, Nassif Building, Washington, 

DC; on the Internet at http://dms.dot.gov; or 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at the NARA, 

call (202) 741–6030, or go to http:// 

www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on 

September 20, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19436 Filed 10–3–05; 8:45 am] 

BILLING CODE 4910–13–U 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22562; Directorate 

Identifier 2004–NM–60–AD; Amendment 39–

14303; AD 2005–20–09] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited Model 

ATP Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

BAE Systems (Operations) Limited 

Model ATP airplanes. This AD requires 

doing an inspection of each bolt 

attaching the aft isolators to both engine 

subframes and replacing bolts if 

necessary. This AD results from reports 

of failures of the bolts attaching the aft 

isolators to the engine subframe. We are 

issuing this AD to prevent failure of the 

bolts attaching the aft isolators to the 

engine subframe, which may result in 

an engine separating from the airplane. 

DATES: This AD becomes effective 

October 19, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 19, 2005. 

We must receive comments on this 

AD by December 5, 2005. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

Federal Register / Vol. 70, No. 191 / Tuesday, October 4, 2005 / Rules and Regulations 57737 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street SW., Nassif Building, 

room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact British Aerospace Regional 

Aircraft American Support, 13850 

Mclearen Road, Herndon, Virginia 

20171, for service information identified 

in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1175; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The Civil Aviation Authority (CAA), 

which is the airworthiness authority for 

the United Kingdom, notified us that an 

unsafe condition may exist on certain 

BAE Systems (Operations) Limited 

Model ATP airplanes. The CAA advises 

that in-service failures of the bolts 

attaching the aft isolators to the engine 

subframe have been reported. Testing 

has demonstrated that reduced torque 

loading has an adverse effect on the 

fatigue life of the bolts attaching the aft 

isolators to the engine subframe. Failure 

of all bolts in the bolt group will affect 

the ability of the engine subframe to 

control the effects of resonance and 

whirl flutter. This condition, if not 

corrected, could result in an engine 

separating from an airplane. 

Relevant Service Information 

BAE Systems (Operations) Limited 

has issued Service Bulletin ATP–54–20, 

dated July 29, 2003. The service bulletin 

describes procedures for performing a 

visual inspection for missing or failed 

bolts that attach aft isolator brackets to 

both engine subframes, replacing all 

four bolts on an engine subframe if any 

bolt is missing or failed on that engine 

subframe, and reporting results. The 

replacement includes doing a torque 

check of each bolt, checking the 

dimensions of the bolt holes, and 

contacting the manufacturer if the holes 

are not within tolerance. The service 

bulletin also notes that quick engine 

change unit subframes should be 

inspected prior to installation. 

The CAA mandated the service 

information and issued British 

airworthiness directive G–2004–0001, 

dated January 22, 2004, to ensure the 

continued airworthiness of these 

airplanes in the United Kingdom. 

FAA’s Determination and Requirements 

of This AD 

This airplane model is manufactured 

in the United Kingdom and is type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Pursuant to this bilateral 

airworthiness agreement, the CAA has 

kept the FAA informed of the situation 

described above. We have examined the 

CAA’s findings, evaluated all pertinent 

information, and determined that we 

need to issue an AD for products of this 

type design that are certificated for 

operation in the United States. 

Therefore, we are issuing this AD to 

prevent failure of the bolts attaching the 

aft isolators to the engine subframe, 

which may result in an engine 

separating from the airplane. This AD 

requires accomplishing the actions 

specified in the service information 

described previously, except as 

discussed under ‘‘Differences Among 

the AD, the Service Bulletin, and the 

British Airworthiness Directive.’’

Differences Among the AD, the Service 

Bulletin, and the British Airworthiness 

Directive 

The service bulletin specifies to 

contact the manufacturer for 

instructions if holes are not within 

tolerance, but this AD would require 

repairing those conditions using a 

method that we or the CAA (or its 

delegated agent) approve. In light of the 

type of repair that would be required to 

address the unsafe condition, and 

consistent with existing bilateral 

airworthiness agreements, we have 

determined that, for this AD, a repair we 

or the CAA approve would be 

acceptable for compliance with this AD. 

The service bulletin refers only to a 

‘‘visual inspection.’’ We have 

determined that the procedures in the 

service bulletin should be described as 

a ‘‘detailed inspection.’’ Note 1 has been 

included in this AD to define this type 

of inspection. 

Interim Action 

We consider this AD interim action. If 

final action is later identified, we may 

consider further rulemaking then. 

Costs of Compliance 

None of the airplanes affected by this 

action are on the U.S. Register. All 

airplanes affected by this AD are 

currently operated by non-U.S. 

operators under foreign registry; 

therefore, they are not directly affected 

by this AD action. However, we 

consider this AD necessary to ensure 

that the unsafe condition is addressed if 

any affected airplane is imported and 

placed on the U.S. Register in the future. 

The following table provides the 

estimated costs to comply with this AD 

for any affected airplane that might be 

imported and placed on the U.S. 

Register in the future. 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Parts cost Cost per airplane 

Inspection, per inspection cycle ............................................... 1 $65 None ........... $65, per inspection cycle. 

FAA’s Determination of the Effective 

Date 

No airplane affected by this AD is 

currently on the U.S. Register. 

Therefore, providing notice and 

opportunity for public comment is 

unnecessary before this AD is issued, 

and this AD may be made effective in 

less than 30 days after it is published in 

the Federal Register. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

relevant written data, views, or 

arguments regarding this AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2005–22562; Directorate Identifier 

2004–NM–60–AD’’ at the beginning of 

your comments. We specifically invite 

57738 Federal Register / Vol. 70, No. 191 / Tuesday, October 4, 2005 / Rules and Regulations 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD that might suggest a 

need to modify it. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of that web site, anyone 

can find and read the comments in any 

of our dockets, including the name of 

the individual who sent the comment 

(or signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78), or you may visit 

http://dms.dot.gov. 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

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 the regulation: 

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. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2005–20–09 BAE Systems (Operations) 

Limited (Formerly British Aerospace 

Regional Aircraft): Amendment 39–

14303. Docket No. FAA–2005–22562; 

Directorate Identifier 2004–NM–60–AD. 

Effective Date 

(a) This AD becomes effective October 19, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to BAE Systems 

(Operations) Limited Model ATP airplanes, 

certificated in any category; on which 

modification 35256A (BAE Systems 

(Operations) Limited Service Bulletin ATP–

54–10) has been accomplished. 

Unsafe Condition 

(d) This AD results from reports of failures 

of the bolts attaching the aft isolators to the 

engine subframe. We are issuing this AD to 

prevent failure of the bolts attaching the aft 

isolators to the engine subframe, which may 

result in an engine separating from 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. 

Inspection and Replacement 

(f) At the later of the times specified in 

paragraphs (f)(1) and (f)(2) of this AD: Do a 

detailed inspection for missing or failed bolts 

that attach aft isolator brackets to both engine 

subframes in accordance with the 

Accomplishment Instructions of BAE 

Systems (Operations) Limited Service 

Bulletin ATP–54–20, dated July 29, 2003. 

Repeat the inspection thereafter at intervals 

not to exceed 2,000 flight cycles. 

(1) Within 2,000 flight cycles after the last 

torque check of the bolts attaching the aft 

isolator brackets to both engine subframes 

done in accordance with BAE Systems 

(Operations) Limited Service Bulletin ATP–

54–20. 

(2) Within 300 flight cycles after the 

effective date of this AD. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

(g) If any bolt is missing or failed on any 

engine subframe during the inspection 

required by paragraph (f) of this AD: Before 

further flight, replace all bolts on that engine 

subframe in accordance with the 

Accomplishment Instructions of BAE 

Systems (Operations) Limited Service 

Bulletin ATP–54–20, dated July 29, 2003. If 

any bolt holes on any engine subframe are 

not within the tolerance specified in the 

service bulletin: Before further flight, repair 

according to a method approved by either the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

Civil Aviation Authority (CAA) (or its 

delegated agent). 

Parts Installation 

(h) As of the effective date of this AD, no 

person may install a quick engine change 

unit subframe on any airplane, unless the 

subframe has been inspected in accordance 

with paragraph (f) of this AD. 

No Reporting Requirement 

(i) Although the service bulletin referenced 

in this AD specifies to submit certain 

information to the manufacturer, this AD 

does not include that requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

Federal Register / Vol. 70, No. 191 / Tuesday, October 4, 2005 / Rules and Regulations 57739 

(2) Before using any AMOC approved in 

accordance with 14 CFR 39.19 on any 

airplane to which the AMOC applies, notify 

the appropriate principal inspector in the 

FAA Flight Standards Certificate Holding 

District Office. 

Related Information 

(k) British airworthiness directive G–2004–

0001, dated January 22, 2004, also addresses 

the subject of this AD. 

Material Incorporated by Reference 

(l) You must use BAE Systems (Operations) 

Limited Service Bulletin ATP–54–20, dated 

July 29, 2003, to perform the actions that are 

required by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approved the incorporation by 

reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact British Aerospace Regional Aircraft 

American Support, 13850 Mclearen Road, 

Herndon, Virginia 20171, for a copy of this 

service information. You may review copies 

at the Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street, SW., room PL–401, Nassif Building, 

Washington, DC; on the Internet at http:// 

dms.dot.gov; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the NARA, call (202) 741–6030, 

or go to http://www.archives.gov/federal_

register/code_of_federal_regulations/ibr_

locations.html. 

Issued in Renton, Washington, on 

September 20, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19437 Filed 10–3–05; 8:45 am] 

BILLING CODE 4910–13–U 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2001–NE–12–AD; Amendment 

39–14319; AD 2005–20–23] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc RB211 Trent 875, 877, 884, 884B, 

892, 892B, and 895 Series Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

Rolls-Royce plc (RR) RB211 Trent 875, 

877, 884, 892, 892B, and 895 series 

turbofan engines. That AD currently 

requires repetitive application of dry 

film lubricant (DFL) to low pressure 

compressor (LPC) fan blade roots. This 

AD requires the same actions but at 

more frequent intervals than the existing 

AD. This AD also adds the Trent 884B 

engine to the list of engine models 

affected, adds a fan blade part number 

(P/N) to the affected list of fan blades, 

and relaxes the initial DFL repetitive 

application compliance time for certain 

fan blades that have never been 

removed from the disk. This AD results 

from discovering DFL in worse 

condition than anticipated on fan blades 

fitted to disks previously run for a 

significant period. This AD also results 

from the need to update the list of 

engine models affected, and to update 

the list of fan blade part numbers 

affected. We are issuing this AD to 

prevent LPC fan blade loss, which could 

result in an uncontained engine failure 

and possible aircraft damage. 

DATES: This AD becomes effective 

November 8, 2005. 

ADDRESSES: You may examine the AD 

docket at the FAA, New England 

Region, Office of the Regional Counsel, 

12 New England Executive Park, 

Burlington, MA. You may examine the 

service information at the FAA, New 

England Region, Office of the Regional 

Counsel, 12 New England Executive 

Park, Burlington, MA. 

FOR FURTHER INFORMATION CONTACT: 

Christopher Spinney, Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine and Propeller Directorate, 

12 New England Executive Park, 

Burlington, MA 01803–5299; telephone: 

(781) 238–7175, fax: (781) 238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR Part 39 with 

a proposed airworthiness directive (AD). 

The proposed AD applies to RR RB211 

Trent 875, 877, 884, 892, 892B, and 895 

series turbofan engines with LPC fan 

blade P/Ns: FK 30838, FK30840, 

FK30842, FW12960, FW12961, 

FW12962, FW13175, FW18548, or 

FW23552. We published the proposed 

AD in the Federal Register on February 

18, 2005 (70 FR 8303). That action 

proposed to require repetitive 

application of DFL to LPC fan blade 

roots at more frequent intervals than the 

existing AD. That action also proposed 

to add the Trent 884B engine to the 

applicability, to add a fan blade P/N to 

the affected list of fan blades, and to 

relax the initial DFL repetitive 

application compliance time for certain 

fan blades that have never been 

removed from the disk. 

Examining the AD Docket 

You may examine the AD Docket 

(including any comments and service 

information), by appointment, between 

8 a.m. and 4:30 p.m., Monday through 

Friday, except Federal holidays. See 

ADDRESSES for the location. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We received 

one comment on the proposal and it was 

favorable. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed. 

Costs of Compliance 

There are approximately 388 RR 

RB211 Trent 875, 877, 884, 884B, 892, 

892B, and 895 series turbofan engines of 

the affected design in the worldwide 

fleet. We estimate that 106 engines 

installed on airplanes of U.S. registry 

will be affected by this AD. We also 

estimate that it will take approximately 

six work hours per engine to perform 

the DFL application, and that the 

average labor rate is $65 per work hour. 

Based on these figures, we estimate the 

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

perform one repetitive application of 

DFL to the affected engines to be 

$41,340. 

Special Flight Permits Paragraph 

Removed 

Paragraph (d) of the current AD, AD 

2002–10–15, contains a paragraph 

pertaining to special flight permits. 

Even though this final rule does not 

contain a similar paragraph, we have 

made no changes with regard to the use 

of special flight permits to operate the 

airplane to a repair facility to do the 

work required by this AD. In July 2002, 

we published a new Part 39 that 

contains a general authority regarding 

special flight permits and airworthiness 

directives; see Docket No. FAA–2004–

8460, Amendment 39–9474 (69 FR 

47998, July 22, 2002). Thus, when we 

now supersede ADs we will not include 

a specific paragraph on special flight 

permits unless we want to limit the use 

of that general authority granted in 

section 39.23. 

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,