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, 

57740 Federal Register / Vol. 70, No. 191 / Tuesday, October 4, 2005 / Rules and Regulations 

‘‘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); 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 summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary by sending a request to us 

at the address listed under ADDRESSES. 

Include ‘‘AD Docket No. 2001–NE–12–

AD’’ in your request. 

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 Federal Aviation Administration 

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 Amendment 39–12761 (67 FR 

36803, May 28, 2002) and by adding a 

new airworthiness directive, 

Amendment 39–14319, to read as 

follows: 

2005–20–23 Rolls-Royce plc: Amendment 

39–14319. Docket No. 2001–NE–12–AD. 

Effective Date 

(a) This AD becomes effective November 8, 

2005. 

Affected ADs 

(b) This AD supersedes AD 2002–10–15. 

Applicability 

(c) This AD applies to Rolls-Royce plc (RR) 

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

and 895 series turbofan engines with low 

pressure compressor (LPC) fan blade part 

numbers (P/Ns): FK 30838, FK30840, 

FK30842, FW12960, FW12961, FW12962, 

FW13175, FW18548, or FW23552. These 

engines are installed on, but not limited to, 

Boeing 777 series airplanes. 

Unsafe Condition 

(d) This AD results from the discovery of 

dry film lubricant (DFL) condition appearing 

worse 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. The actions specified in this AD are 

intended to prevent LPC fan blade loss, 

which could result in an uncontained engine 

failure and possible aircraft damage. 

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. 

(f) Apply an approved DFL to LPC fan 

blade roots as follows: 

(1) For LPC fan blades P/Ns FW13175, 

FW12960, FW12961, FW12962, FW18548, 

and FW23552 that have never been removed 

from the disk, apply DFL at the first removal 

from the disk or before 1,200 cycles-inservice (CIS), whichever occurs first. 

(2) For LPC fan blades P/Ns FW13175, 

FW12960, FW12961, FW12962, FW18548, 

and FW23552 that have been removed from 

the disk since entering service, apply DFL 

before accumulating 600 cycles-since-new 

(CSN) or before accumulating 600 cyclessince-last DFL application, or within 200 CIS 

from the effective date of this AD, whichever 

occurs later. 

(3) For LPC fan blades P/Ns FK30842, 

FK30840, and FK300838, apply DFL before 

accumulating 600 CSN or before 

accumulating 600 cycles-since-last DFL 

application, or within 100 CIS after July 2, 

2002 (effective date of superseded AD 2002–

10–15), whichever occurs first. 

(4) Thereafter, reapply DFL to LPC fan 

blade roots within 600 cycles-since-last DFL 

application. 

(5) Information on applying DFL to fan 

blade roots can be found in RR Alert Service 

Bulletin No. RB.211–72–AD347, Revision 6, 

dated April 22, 2004, or Revision 7, dated 

August 2, 2005. 

Alternative Methods of Compliance 

(g) The Manager, Engine 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 

(h) Civil Aviation Authority Airworthiness 

Directive G–2004–0008, dated April 29, 2004, 

also addresses the subject of this AD. 

Issued in Burlington, Massachusetts, on 

September 27, 2005. 

Francis A. Favara, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–19845 Filed 10–3–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–20917; Directorate 

Identifier 2004–NM–85–AD; Amendment 39–

14312; AD 2005–20–18] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100, –200B, –200F, –200C, 

–100B, –300, –100B SUD, –400, –400D, 

and –400F Series Airplanes; and Model 

747SR Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding two 

existing airworthiness directives (AD), 

which apply to certain Boeing transport 

category airplanes. One AD currently 

requires doing certain inspections to 

detect cracks and corrosion around the 

lower bearing of the actuator attach 

fittings of the inboard and outboard 

flaps; repairing if necessary; and either 

overhauling the fittings or replacing 

them, which ends certain repetitive 

inspections. The other AD currently 

requires certain other inspections to 

detect discrepancies of the actuator 

attach fittings of the flaps, and followon and corrective actions if necessary, 

which ends the repetitive inspections of 

the first AD. For certain airplanes, this 

AD requires new inspections for 

discrepancies of the actuator attach 

fittings of the flaps, and follow-on and 

corrective actions if necessary, which 

ends the repetitive inspections of both 

existing ADs. For all airplanes, this AD 

requires repetitive overhaul/ 

replacements of the actuator attach 

fittings of both the inboard and outboard 

flaps. This AD results from reports of 

cracks of the actuator attach fittings of 

the trailing edge flaps. We are issuing 

this AD to prevent cracking and other 

damage of the actuator attach fittings of 

the trailing edge flaps, which could 

result in abnormal operation or