44610 Federal Register / Vol. 68, No. 146 / Wednesday, July 30, 2003 / Rules and Regulations 

(a) Within six months after the effective 

date of this AD, replace APU fuel nozzles, P/

N WE3830486–2, with new design fuel 

nozzles, P/N WE3830513–1. Information on 

fuel nozzle replacement can be found in 

Honeywell International Inc. alert service 

bulletin (ASB) RE220–49–A7714, dated 

November 4, 2002. 

(b) Reidentify the APU as follows: 

(1) Change the P/N from WE3800770–2 to 

WE3800770–3 on the identification plate, by 

removing the –2 and vibropeening or hand 

stamping a –3 in its place. 

(2) Vibropeen or hand stamp the letter ‘‘C’’

after the serial number to show conversion. 

(3) Vibropeen or hand stamp ‘‘Change 

Number 3’’ on the identification plate 

adjacent to the MOD RECORD. 

(c) Start the APU and perform a visual fuel 

leak check after one minute of operation. 

(d) After the effective date of this AD, do 

not install fuel nozzles P/N WE3830486–2 

into any APU P/N WE3800770–3. 

Alternative Methods of Compliance 

(e) An alternative method of compliance or 

adjustment of the compliance time that 

provides an acceptable level of safety may be 

used if approved by the Manager, Los 

Angeles Aircraft Certification Office 

(LAACO). Operators must submit their 

requests through an appropriate FAA 

Principal Maintenance Inspector, who may 

add comments and then send it to the 

Manager, LAACO.

Note 2: Information concerning the 

existence of approved alternative methods of 

compliance with this airworthiness directive, 

if any, may be obtained from the LAACO.

Special Flight Permits 

(f) Special flight permits may be issued in 

accordance with §§ 21.197 and 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199) to operate the airplane to a 

location where the requirements of this AD 

can be done. 

Effective Date 

(g) This amendment becomes effective on 

September 3, 2003.

Issued in Burlington, Massachusetts, on 

July 24, 2003. 

Francis A. Favara, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service.

[FR Doc. 03–19309 Filed 7–29–03; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NE–03–AD; Amendment 

39–13249; AD 2003–15–06] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc RB211 Trent 800 Series Turbofan 

Engines

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) that 

applies to Rolls-Royce plc (RR) RB211 

Trent 875–17, Trent 877–17, Trent 884–

17, Trent 892–17, Trent 892B–17, and 

Trent 895–17 turbofan engines with 

high pressure (HP) compressor rotor rear 

stage 5 and 6 discs and cone shafts, part 

numbers (P/Ns) FK25230 and FK27899 

installed. This amendment requires 

removal from service of these HP 

compressor rotor rear stage 5 and 6 discs 

and cone shafts, before reaching newly 

reduced life limits. This amendment is 

prompted by three reports of crack 

indications in the stage 5 and stage 6 

blade loading slots, found during engine 

overhaul. We are issuing this AD to 

prevent stage 5 and 6 disc crack 

initiation and propagation leading to 

uncontained disc failure and damage to 

the airplane.

DATES: Effective September 3, 2003.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Rolls Royce plc, P.O. Box 31, 

DERBY, DE24 8BJ, UK, telephone: 44 (0) 

1332 242424; fax: 44 (0) 1332 249936. 

This information may be examined, by 

appointment, at the Federal Aviation 

Administration (FAA), New England 

Region, Office of the Regional Counsel, 

12 New England Executive Park, 

Burlington, MA; or at the Office of the 

Federal Register, 800 North Capitol 

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

James Lawrence, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803–5299, telephone (781) 238–7176; 

fax (781) 238–7199.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an AD that is applicable to RR 

RB211 Trent 875–17, Trent 877–17, 

Trent 884–17, Trent 892–17, Trent 

892B–17, and Trent 895–17 turbofan 

engines with HP compressor rotor rear 

stage 5 and 6 discs and cone shafts, part 

numbers (P/Ns) FK25230 and FK27899 

installed was published in the Federal 

Register on March 11, 2003. That action 

proposed to require removal from 

service of these HP compressor rotor 

rear stage 5 and 6 discs and cone shafts, 

before reaching newly reduced life 

limits. Information on the reduced life 

limits of these HP compressor rotors 

may be found in RR mandatory service 

bulletin (MSB) RB.211–72–E082, 

Revision 2, dated November 22, 2002. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

comments received. 

Request To Include a Reference to RR 

Service Information 

One commenter requests that a 

reference to RR MSB RB.211–72–E082, 

Revision 2, dated November 22, 2002, 

be included in the final rule. The 

commenter believes that the reference to 

the MSB is necessary for clarification 

and for traceability to the AD if future 

revisions to the MSB are issued. 

The FAA agrees. The MSB reference 

is included in the Supplementary 

Information paragraph and in 

Compliance paragraph (a). 

Request To Withdraw Unnecessary AD 

One commenter states that the new 

life limit specified in the AD has already 

been included in the RB211 Trent Time 

Limits Manual (Chapter 5); therefore, 

the AD is unnecessary. 

The FAA does not agree. Although the 

new life limits have been included in 

the RB211 Time Limits Manual, the 

reduced life limits are not enforceable 

unless mandated by an AD. 

Accordingly, the FAA will not change 

the AD based on this comment. 

After careful review of the available 

data, including the comments noted 

above, the FAA has determined that air 

safety and the public interest the 

adoption of the rule with the change 

described previously. The FAA has 

determined that this change will neither 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Regulatory Analysis 

This final rule does not have 

federalism implications, as defined in 

Executive Order 13132, because it 

would 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 

Federal Register / Vol. 68, No. 146 / Wednesday, July 30, 2003 / Rules and Regulations 44611

various levels of government. 

Accordingly, the FAA has not consulted 

with state authorities prior to 

publication of this final rule. 

For the reasons discussed above, I 

certify that this action: (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. A final evaluation has 

been prepared for this action and it is 

contained in the Rules Docket. A copy 

of it may be obtained by contacting the 

Rules Docket at the location provided 

under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety.

Adoption of the Amendment

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. Section 39.13 is amended by adding 

a new airworthiness directive to read as 

follows:

2003–15–06 Rolls-Royce plc: Amendment 

39–13249. Docket No. 2003–NE–03–AD.

Applicability 

This airworthiness directive (AD) applies 

to Rolls-Royce plc (RR) RB211 Trent 875–17, 

Trent 877–17, Trent 884–17, Trent 892–17, 

Trent 892B–17, and Trent 895–17 turbofan 

engines with high pressure (HP) compressor 

rotor rear stage 5 and 6 discs and cone shafts, 

part numbers (P/Ns) FK25230 and FK27899 

installed. These engines are installed on, but 

not limited to Boeing 777 airplanes.

Note 1: This AD applies to each engine 

identified in the preceding applicability 

provision, regardless of whether it has been 

modified, altered, or repaired in the area 

subject to the requirements of this AD. For 

engines that have been modified, altered, or 

repaired so that the performance of the 

requirements of this AD is affected, the 

owner/operator must request approval for an 

alternative method of compliance in 

accordance with paragraph (c) of this AD. 

The request should include an assessment of 

the effect of the modification, alteration, or 

repair on the unsafe condition addressed by 

this AD; and, if the unsafe condition has not 

been eliminated, the request should include 

specific proposed actions to address it.

Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified unless the 

actions have already been accomplished. 

To prevent stage 5 and 6 disc crack 

initiation and propagation leading to 

uncontained disc failure and damage to the 

airplane, do the following: 

(a) Remove HP compressor rotor rear stage 

5 and 6 discs and cone shafts, from service 

at or before accumulating 7,500 cycles-sincenew (CSN). Information on the reduced life 

limits may be found in RR mandatory service 

bulletin RB.211–72–E082, Revision 2, dated 

November 22, 2002. 

(b) After the effective date of this AD, do 

not install any HP compressor rotor rear stage 

5 and 6 discs and cone shaft, listed in this 

AD, that exceed 7,500 CSN. 

Alternative Methods of Compliance 

(c) An alternative method of compliance or 

adjustment of the compliance time that 

provides an acceptable level of safety may be 

used if approved by the Manager, Engine 

Certification Office (ECO). Operators must 

submit their request through an appropriate 

FAA Principal Maintenance Inspector, who 

may add comments and then send it to the 

Manager, ECO.

Note 2: Information concerning the 

existence of approved alternative methods of 

compliance with this airworthiness directive, 

if any, may be obtained from the ECO.

Special Flight Permits 

(d) Special flight permits may be issued in 

accordance with §§ 21.197 and 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199) to operate the airplane to a 

location where the requirements of this AD 

can be done.

Note 3: The subject of this AD is addressed 

in CAA airworthiness directive 002–08–2002, 

dated November 22, 2002.

Effective Date 

(e) This amendment becomes effective on 

September 3, 2003.

Issued in Burlington, Massachusetts, on 

July 23, 2003. 

Francis A. Favara, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service.

[FR Doc. 03–19306 Filed 7–29–03; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 95 

[Docket No. 30380; Amdt. No. 443] 

IFR Altitudes; Miscellaneous 

Amendments

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts 

miscellaneous amendments to the 

required IFR (instrument flight rules) 

altitudes and changeover points for 

certain Federal airways, jet routes, or 

direct routes for which a minimum or 

maximum en route authorized IFR 

altitude is prescribed. This regulatory 

action is needed because of changes 

occurring in the National Airspace 

System. These changes are designed to 

provide for the safe and efficient use of 

the navigable airspace under instrument 

conditions in the affected areas.

EFFECTIVE DATE: 0901 UTC, September 4, 

2003.

FOR FURTHER INFORMATION CONTACT:

Donald P. Pate, Flight Procedure 

Standards Branch (AMCAFS–420), 

Flight Technologies and Programs 

Division, Flight Standards Service, 

Federal Aviation Administration, Mike 

Monroney Aeronautical Center, 6500 

South MacArthur Blvd. Oklahoma City, 

OK. 73169 (Mail Address: PO Box 25082 

Oklahoma City, OK. 73125) telephone: 

(405) 954–4164.

SUPPLEMENTARY INFORMATION: This 

amendment to part 95 of the Federal 

Aviation Regulations (14 CFR part 95) 

amends, suspends, or revokes IFR 

altitudes governing the operation of all 

aircraft in flight over a specified route 

or any portion of that route, as well as 

the changeover points (COPs) for 

Federal airways, jet routes, or direct 

routes as prescribed in part 95. 

The Rule 

The specified IFR altitudes, when 

used in conjunction with the prescribed 

changeover points for those routes, 

ensure navigation aid coverage that is 

adequate for safe flight operations and 

free of frequency interference. The 

reasons and circumstances that create 

the need for this amendment involve 

matters of flight safety and operational 

efficiency in the National Airspace 

System, are related to published 

aeronautical charts that are essential to 

the user, and provide for the safe and 

efficient use of the navigable airspace. 

In addition, those various reasons or