55812 Federal Register / Vol. 68, No. 188 / Monday, September 29, 2003 / Rules and Regulations 

–524G3–T, –524H, –524H–T, –524H2, 

and ‘‘524H2–T Series, and Models 

RB211 Trent 768–60, 772–60, and 772B–

60 Turbofan Engines’’ is corrected to 

read ‘‘Airworthiness Directives; RollsRoyce plc RB211–524G2, –524G2–T, 

–524G3, –524G3–T, –524H, –524H–T, 

–524H2, and ‘‘524H2–T Series Turbofan 

Engines’’.

■ 2. In the second column of page 42242, 

the first sentence of the Summary, ‘‘The 

FAA is adopting a new airworthiness 

directive (AD) for Rolls-Royce plc (RR) 

RB211–524G2, –524G2–T, –524G3, 

–524G3–T, –524H, –524H–T, –524H2, 

and –524H2–T series, and models RB211 

Trent 768–60, 772–60, and 772B–60 

turbofan engines with high pressure 

compressor (HPC) rotor stage 1 through 

stage 6 drums, part numbers (P/Ns) 

FK25502 and FW20195 installed.’’ is 

corrected to read ‘‘The FAA is adopting 

a new airworthiness directive (AD) for 

Rolls-Royce plc (RR) RB211–524G2, 

–524G2–T, –524G3, –524G3–T, –524H, 

–524H–T, –524H2, and –524H2–T series 

turbofan engines with high pressure 

compressor (HPC) rotor stage 1 through 

stage 6 drums, part numbers (P/Ns) 

FK25502 and FW20195 installed.’’

■ 3. In the third column of page 42242, 

the first sentence of the Supplementary 

Information, ‘‘The Civil Aviation 

Authority (CAA), which is the 

airworthiness authority for the U.K., 

recently notified the FAA that an unsafe 

condition may exist on RR RB211–

524G2, –524G2–T, –524G3, –524G3–T, 

–524H, –524H–T, –524H2, and –524H2–

T series, and models RB211 Trent 768–

60, –772–60, and 772B–60 turbofan 

engines with HPC stage 1 through stage 

6 drums, P/Ns FK25502 and FW20195 

installed.’’ is corrected to read ‘‘The Civil 

Aviation Authority (CAA), which is the 

airworthiness authority for the U.K., 

recently notified the FAA that an unsafe 

condition may exist on RR RB211–

524G2, –524G2–T, –524G3, –524G3–T, 

–524H, –524H–T, –524H2, and 524H2–T 

series turbofan engines with HPC stage 1 

through stage 6 drums, P/Ns FK25502 

and FW20195 installed.’’

■ 4. In the first column of page 42243, 

the second sentence under FAA’s 

Determination and Requirements of This 

AD ‘‘Since an unsafe condition has been 

identified that is likely to exist or 

develop on other Rolls-Royce plc 

RB211–524G2, –524G2–T, –524G3, 

–524G3–T, –524H, –524H–T, –524H2, 

and –524H2–T series, and models RB211 

Trent 768–60, 772–60, and 772B–60 

turbofan engines of this same type 

design’’ is corrected to read ‘‘Since an 

unsafe condition has been identified that 

is likely to exist or develop on other 

Rolls-Royce plc RB211–524G2, –524G2–

T, –524G3, –524G3–T, –524H, –524H–T, 

–524H2, and ‘‘524H2–T series turbofan 

engines of this same type design,’’

§ 39.13 [Corrected]

■ 5. On page 42243, in the third column, 

the first sentence in paragraph (c) is 

corrected to read as follows: 

(c) This AD applies to Rolls-Royce plc 

RB211–524G2, –524G2–T, –524G3, 

–524G3–T, –524H, –524H–T, –524H2, 

and –524H2–T series turbofan engines 

with high pressure compressor (HPC) 

rotor stage 1 through stage 6 drums, part 

numbers (P/Ns) FK25502 and FW20195 

installed. * * *

Issued in Burlington, MA, on September 

19, 2003. 

Francis A. Favara, 

Assistant Manager, Engine and Propeller 

Directorate, , Aircraft Certification Service.

[FR Doc. 03–24374 Filed 9–26–03; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2000–NM–408–AD; Amendment 

39–13314; AD 2003–19–11] 

RIN 2120–AA64 

Airworthiness Directives; Learjet 

Model 60 Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to certain Learjet Model 60 

airplanes, that currently requires 

inspection to detect bends in or damage 

to the fuel crossflow tube; inspection to 

determine clearance between the fuel 

crossflow tube and the flight control 

cables; and replacement or repair of the 

tube, if necessary. This amendment 

requires a review of airplane 

maintenance records or an inspection to 

determine if a fuel crossflow tube 

having a certain part number is 

installed; and follow-on/corrective 

actions, as applicable. This amendment 

also expands the applicability of the 

existing AD to include additional 

airplanes. The actions specified by this 

AD are intended to prevent chafing and 

consequent failure of the fuel crossflow 

tube due to inadequate clearance 

between the tube and the flight control 

cables, which could result in loss of fuel 

from one fuel tank during normal 

operating conditions or loss of fuel from 

both main fuel tanks during fuel crossfeeding operations. This action is 

intended to address the identified 

unsafe condition.

DATES: Effective November 3, 2003. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of November 

3, 2003.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Learjet, Inc., One Learjet Way, 

Wichita, Kansas 67209–2942. This 

information may be examined at the 

Federal Aviation Administration (FAA), 

Transport Airplane Directorate, Rules 

Docket, 1601 Lind Avenue, SW., 

Renton, Washington; or at the FAA, 

Wichita Aircraft Certification Office, 

1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas; or 

at the Office of the Federal Register, 800 

North Capitol Street, NW., suite 700, 

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Jeffrey Janusz, Aerospace Engineer, 

Systems and Propulsion Branch, ACE–

116W, FAA, Wichita Aircraft 

Certification Office, 1801 Airport Road, 

Room 100, Mid-Continent Airport, 

Wichita, Kansas 67209; telephone (316) 

946–4148; fax (316) 946–4407.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) 

by superseding AD 95–14–09, 

amendment 39–9303 (60 FR 36984, July 

19, 1995), which is applicable to certain 

Learjet Model 60 airplanes, was 

published in the Federal Register on 

June 18, 2003 (68 FR 36502). That action 

proposed to require inspection to detect 

bends in or damage to the fuel crossflow 

tube; inspection to determine clearance 

between the fuel crossflow tube and the 

flight control cables; and replacement or 

repair of the tube, if necessary. That 

action also proposed to require a review 

of airplane maintenance records or an 

inspection to determine if a fuel 

crossflow tube having a certain part 

number is installed; and follow-on/

corrective actions, as applicable. That 

action also proposed to expand the 

applicability of the existing AD to 

include additional airplanes. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. No 

comments were submitted in response 

to the proposal or the FAA’s 

determination of the cost to the public.

Federal Register / Vol. 68, No. 188 / Monday, September 29, 2003 / Rules and Regulations 55813

Explanation of Change to Proposed 

Rule 

In paragraph (a) of the proposed rule, 

we inadvertently specified an incorrect 

part number. We have revised this AD 

to specify the correct part number. 

Conclusion 

After careful review of the available 

data, including the comments noted 

above, the FAA has determined that air 

safety and the public interest require the 

adoption of the rule with the changes 

previously described. The FAA has 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Change to Labor Rate Estimate 

We have reviewed the figures we have 

used over the past several years to 

calculate AD costs to operators. To 

account for various inflationary costs in 

the airline industry, we find it necessary 

to increase the labor rate used in these 

calculations from $60 per work hour to 

$65 per work hour. The cost impact 

information, below, reflects this 

increase in the specified hourly labor 

rate. 

Cost Impact 

There are approximately 145 

airplanes of the affected design in the 

worldwide fleet. The FAA estimates that 

109 airplanes of U.S. registry will be 

affected by this AD. 

It will take approximately 2 work 

hours per airplane to accomplish the 

review of airplane maintenance records/

inspection required in this AD action, at 

an average labor rate of $65 per work 

hour. Based on these figures, the cost 

impact of the requirements of this AD 

on U.S. operators is estimated to be 

$14,170, or $130 per airplane. 

The cost impact figures discussed 

above are based on assumptions that no 

operator has yet accomplished any of 

the requirements of this AD action, and 

that no operator would accomplish 

those actions in the future if this AD 

were not adopted. The cost impact 

figures discussed in AD rulemaking 

actions represent only the time 

necessary to perform the specific actions 

actually required by the AD. These 

figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

Regulatory Impact 

The regulations adopted herein 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. Therefore, it is 

determined that this final rule does not 

have federalism implications under 

Executive Order 13132. 

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 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 from the Rules 

Docket at the location provided under 

the caption ‘‘ADDRESSES.’’

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

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 

removing amendment 39–9303 (60 FR 

36984, July 19, 1995), and by adding a 

new airworthiness directive (AD), 

amendment 39–13314, to read as 

follows:

2003–19–11 Learjet: Amendment 39–13314. 

Docket 2000–NM–408–AD. Supersedes 

AD 95–14–09, Amendment 39–9303.

Applicability: Model 60 airplanes, serial 

numbers 60–001 through 60–145 inclusive, 

certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent chafing and consequent failure 

of the fuel crossflow tube due to inadequate 

clearance between the tube and the flight 

control cables, which could result in loss of 

fuel from one fuel tank during normal 

operating conditions or loss of fuel from both 

main fuel tanks during fuel cross-feeding 

operations, accomplish the following: 

Part Identification 

(a) Within 25 flight hours after the effective 

date of this AD, inspect the fuel crossflow 

tube to determine whether part number (P/

N) 6026020–005 is installed. Instead of 

inspecting the tube, a review of airplane 

maintenance records is acceptable if the P/N 

of the tube can be positively determined from 

that review. 

Clearance Measurement and Corrective 

Action 

(b) For all airplanes: If P/N 6026020–005 is 

found installed during the review or 

inspection required by paragraph (a) of this 

AD, before further flight, measure the 

clearance between the fuel crossflow tube 

and the flight control cables to determine if 

it is at least 0.35 inch, per paragraph 2.B.(8) 

of the Accomplishment Instructions of 

Bombardier Alert Service Bulletin A60–28–3, 

Revision 2, dated October 26, 1998. 

(1) If the clearance is 0.35 inch or more, no 

further action is required by this paragraph. 

(2) If the clearance is less than 0.35 inch, 

before further flight, repair per a method 

approved by the Manager, Wichita Aircraft 

Certification Office (ACO), FAA. 

Part Replacement, Measurement, and Repair 

(c) For airplanes having serial numbers 60–

001 through 60–055: If P/N 6026020–005 is 

not found installed during the review or 

inspection required by paragraph (a) of this 

AD, within 90 days after accomplishing the 

review or inspection, replace the existing fuel 

crossflow tube with a new fuel crossflow 

tube having P/N 6026020–005, and measure 

the clearance between the newly installed 

fuel crossflow tube and the flight control 

cables, per paragraph 2.A. of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 60–28–4, Revision 2, dated 

August 22, 2001. 

(1) If the clearance is 0.35 inch or more, no 

further action is required by this paragraph. 

(2) If the clearance is less than 0.35 inch, 

before further flight, repair per a method 

approved by the Manager, Wichita ACO, 

FAA. 

(d) For airplanes having serial numbers 60–

056 through 60–145: If P/N 6026020–005 is 

not found installed during the review or 

inspection required by paragraph (a) of this 

AD, within 90 days after accomplishing the 

review or inspection, replace the existing fuel 

crossflow tube with a new fuel crossflow 

tube having P/N 6026020–005, and measure 

the clearance between the newly installed 

fuel crossflow tube and the flight control 

cables to determine if the clearance is at least 

0.35 inch, per paragraph 2.B. of the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin A60–28–3, Revision 2, 

dated October 26, 1998. 

(1) If the clearance is 0.35 inch or more, no 

further action is required by this paragraph. 

(2) If the clearance is less than 0.35 inch, 

before further flight, repair per a method 

approved by the Manager, Wichita ACO, 

FAA.

Note 1: Bombardier Alert Service Bulletin 

A60–28–3, Revision 2, Figure 1, Detail D, 

incorrectly identifies the fuel crossflow tube 

to be installed as P/N 6026020–001. The 

manufacturer is aware of this error and plans 

to correct the part number in the next 

revision of the alert service bulletin.

55814 Federal Register / Vol. 68, No. 188 / Monday, September 29, 2003 / Rules and Regulations 

Part Installation 

(e) As of the effective date of this AD, only 

fuel crossflow tubes having P/N 6026020–005 

shall be installed on any airplane. 

Alternative Methods of Compliance 

(f) In accordance with 14 CFR 39.19, the 

Manager, Wichita ACO, FAA, is authorized 

to approve alternative methods of 

compliance (AMOCs) for this AD. 

Incorporation by Reference 

(g) Unless otherwise specified by this AD, 

the actions shall be done in accordance with 

Bombardier Alert Service Bulletin A60–28–3, 

Revision 2, dated October 26, 1998; and 

Bombardier Service Bulletin 60–28–4, 

Revision 2, dated August 22, 2001; as 

applicable. This incorporation by reference 

was approved by the Director of the Federal 

Register in accordance with 5 U.S.C. 552(a) 

and 1 CFR part 51. Copies may be obtained 

from Learjet, Inc., One Learjet Way, Wichita, 

Kansas 67209–2942. Copies may be inspected 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue, SW., Renton, 

Washington; or at the FAA, Wichita Aircraft 

Certification Office, 1801 Airport Road, 

Room 100, Mid-Continent Airport, Wichita, 

Kansas; or at the Office of the Federal 

Register, 800 North Capitol Street, NW., suite 

700, Washington, DC. 

Effective Date 

(h) This amendment becomes effective on 

November 3, 2003.

Issued in Renton, Washington, on 

September 16, 2003. 

Ali Bahrami, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 03–24074 Filed 9–26–03; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–206–AD; Amendment 

39–13319; AD 2003–20–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

(Collectively Called A300–600) Series 

Airplanes, and Airbus Model A310 

Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to certain Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

(collectively called A300–600) series 

airplanes, and Airbus Model A310 

series airplanes, that currently requires 

replacement of Honeywell inertial 

reference units (IRU) with new or 

modified Honeywell IRUs. For certain 

airplanes, that existing AD also requires 

replacement of Litton IRUs, mode 

selector units (MSU), and an inertial 

sensor display unit (ISDU) with new 

Honeywell IRUs, MSUs, and a new 

ISDU. This amendment removes the 

requirement to replace the Litton IRUs, 

MSUs, and ISDU with Honeywell IRUs, 

MSUs, and ISDU. This amendment also 

allows the use of certain Honeywell 

IRUs as spare parts until the final 

compliance date of this AD. The actions 

specified in this AD are intended to 

prevent loss of positioning data and a 

display of incorrect attitude data, which 

could compromise the ability of the 

flightcrew to maintain the safe flight 

and landing of the airplane. This action 

is intended to address the identified 

unsafe condition.

DATES: Effective September 29, 2003. 

The incorporation by reference of 

certain publications listed in the 

regulations was approved previously by 

the Director of the Federal Register as of 

September 22, 2003 (68 FR 49340, 

August 18, 2003). 

Comments for inclusion in the Rules 

Docket must be received on or before 

October 29, 2003.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, ANM–114, 

Attention: Rules Docket No. 2003-NM–

206-AD, 1601 Lind Avenue, SW., 

Renton, Washington 98055–4056. 

Comments may be inspected at this 

location between 9 a.m. and 3 p.m., 

Monday through Friday, except Federal 

holidays. Comments may be submitted 

via fax to (425) 227–1232. Comments 

may also be sent via the Internet using 

the following address: 9-anmiarcomment@faa.gov. Comments sent 

via fax or the Internet must contain 

‘‘Docket No. 2003–NM–206–AD’’ in the 

subject line and need not be submitted 

in triplicate. Comments sent via the 

Internet as attached electronic files must 

be formatted in Microsoft Word 97 or 

2000 or ASCII text. 

The service information referenced in 

this AD may be obtained from Airbus 

Industrie, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France. 

This information may be examined at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., 

Renton, Washington; or at the Office of 

the Federal Register, 800 North Capitol 

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

FOR FURTHER INFORMATION CONTACT:

Anthony Jopling, Program Manager, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2190; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: On August 

6, 2003, the FAA issued AD 2003–16–

15, amendment 39–13268 (68 FR 49340, 

August 18, 2003), applicable to certain 

Airbus Model A300 B4–600, B4–600R, 

and F4–600R (collectively called A300–

600) series airplanes, and Airbus Model 

A310 series airplanes. That AD requires 

replacement of Honeywell inertial 

reference units (IRU) with new or 

modified Honeywell IRUs. For certain 

airplanes, that AD also requires 

replacement of Litton IRUs, mode 

selector units (MSU), and an inertial 

sensor display unit (ISDU) with new 

Honeywell IRUs, MSUs, and a new 

ISDU. That action was prompted by 

notification from the Direction 

Gee ́nee ́rale de l’Aviation Civile (DGAC), 

which is the airworthiness authority for 

France, that an operator reported loss of 

positioning data and the display of 

incorrect attitude data shortly after takeoff because the airplane was moved on 

the ground before the IRU alignment 

procedure had been completed. The 

actions required by that AD are 

intended to prevent loss of positioning 

data and a display of incorrect attitude 

data. 

Related Rulemaking 

It should be noted that the FAA 

previously issued AD 2001–13–24, 

amendment 39–12306 (66 FR 35532, 

July 6, 2001), applicable to certain 

Airbus Model A300–600 and A310 

series airplanes. The DGAC notified the 

FAA that an unsafe condition may exist 

on certain Airbus Model A310 series 

airplanes and certain Airbus Model 

A300–600 series airplanes with certain 

Honeywell IRUs. The DGAC advised 

that an operator reported the loss of 

positioning data and the display of 

incorrect attitude data shortly after takeoff, because the aircraft had been moved 

on the ground before the end of the IRU 

alignment procedure. This condition, if 

not corrected, could result in the loss of 

positioning data and a display of 

incorrect attitude data, which could 

compromise the ability of the flightcrew 

to maintain the safe flight and landing 

of the airplane. AD 2001–13–24 requires 

revisions to the Normal Procedures 

section of the airplane flight manual to 

prohibit movement of the airplane 

during IRU alignment and to provide 

instructions to the flightcrew to check 

the navigational display system to 

ensure correct display of all primary 

attitude and heading information prior