4902 Federal Register / Vol. 68, No. 21 / Friday, January 31, 2003 / Rules and Regulations 

disconnect panel. Do this inspection 

according to the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

DC9–24A190, Revision 01, excluding 

Evaluation Form, dated November 21, 2001. 

(1) If no evidence of contamination of 

electrical connectors is found, and a 

dripshield is installed, no further action is 

required by this AD. 

(2) If any evidence of contamination of any 

electrical connector is found: Before further 

flight, remove each affected connector, and 

install a new or serviceable connector 

according to the service bulletin.

(3) If no dripshield is installed over the 

disconnect panel: Before further flight, install 

a dripshield according to the service bulletin. 

Previously Accomplished Inspections and 

Corrective Actions 

(b) Inspections and corrective actions 

accomplished before the effective date of this 

AD in accordance with Boeing Alert Service 

Bulletin DC9–24A190, dated July 31, 2001, 

are considered acceptable for compliance 

with the corresponding action specified in 

this AD. 

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, Los 

Angeles Aircraft Certification Office (ACO), 

FAA. Operators shall submit their requests 

through an appropriate FAA Principal 

Maintenance Inspector, who may add 

comments and then send it to the Manager, 

Los Angeles ACO.

Note 2: Information concerning the 

existence of approved alternative methods of 

compliance with this AD, if any, may be 

obtained from the Los Angeles ACO.

Special Flight Permits 

(d) Special flight permits may be issued in 

accordance with sections 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 accomplished. 

Incorporation by Reference 

(e) Unless otherwise specified by this AD, 

the actions shall be done in accordance with 

Boeing Alert Service Bulletin DC9–24A190, 

Revision 01, excluding Evaluation Form, 

dated November 21, 2001. 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 Boeing Commercial Aircraft 

Group, Long Beach Division, 3855 Lakewood 

Boulevard, Long Beach, California 90846, 

Attention: Data and Service Management, 

Dept. C1-L5A (D800–0024). Copies may be 

inspected at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; or at the FAA, Los Angeles 

Aircraft Certification Office, 3960 Paramount 

Boulevard, Lakewood, California; or at the 

Office of the Federal Register, 800 North 

Capitol Street, NW., suite 700, Washington, 

DC. 

Effective Date 

(f) This amendment becomes effective on 

March 7, 2003.

Issued in Renton, Washington, on January 

22, 2003. 

Vi L. Lipski, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 03–1954 Filed 1–30–03; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–48–AD; Amendment 

39–13034; AD 2003–03–10] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited Model 

BAe 146 and Avro 146-RJ Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to all BAE Systems 

(Operations) Limited Model BAe 146 

and Avro 146–RJ series airplanes, that 

requires replacement of the existing 

‘‘Low Temp’’ terminal blocks ‘‘G’’ with 

new, fireproof ceramic terminal blocks 

‘‘G’’ in engine zones 412, 422, 432, and 

442. This action is necessary to prevent 

failure of the engine fire detection and 

suppression systems to operate properly 

in the event of a fire due to failure of 

non-fireproof terminal blocks, which 

could result in an undetected and 

uncontrollable fire in an engine. This 

action is intended to address the 

identified unsafe condition.

DATES: Effective March 7, 2003. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of March 7, 

2003.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from British Aerospace Regional 

Aircraft American Support, 13850 

Mclearen Road, Herndon, Virginia 

20171. 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 Office of the 

Federal Register, 800 North Capitol 

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

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: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an airworthiness directive (AD) 

that is applicable to all BAE Systems 

(Operations) Limited Model BAe 146 

and Avro 146-RJ series airplanes was 

published in the Federal Register on 

May 15, 2002 (67 FR 34633). That action 

proposed to require replacement of the 

existing ‘‘Low Temp’’ terminal blocks 

‘‘G’’ with new, fireproof ceramic 

terminal blocks ‘‘G’’ in engine zones 

412, 422, 432, and 442. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

comment received. 

Request To Extend the Compliance 

Time 

One commenter requests that the FAA 

extend the compliance time for the 

replacement in the proposed AD from 

21 months to July 31, 2004, (the 

equivalent of an additional 12 months). 

The commenter states that the request is 

based upon limited parts availability 

and feedback from large fleet operators. 

The commenter also states that the Civil 

Aviation Authority for the United 

Kingdom has approved the extension of 

the compliance time for airplanes 

operating in the United Kingdom. 

The FAA concurs with the 

commenter’s request. We have verified 

that the lead time for obtaining the 

required modification parts will exceed 

the proposed compliance time of 21 

months. In light of this situation, we 

will extend the compliance time from 

21 months to 31 months after the 

effective date of this AD. We have 

determined that such an extension will 

accommodate the time necessary for 

affected operators to order and obtain 

the replacement parts, without 

adversely affecting safety. We have 

revised paragraph (a) of this AD 

accordingly. 

Explanation of New Relevant Service 

Information 

Since issuance of the proposed AD, 

the manufacturer has issued BAE 

Systems (Operations) Limited Service 

Bulletin SB.71–077–01693A, Revision 1, 

dated March 28, 2002; and Revision 2, 

dated May 28, 2002. The proposed rule

Federal Register / Vol. 68, No. 21 / Friday, January 31, 2003 / Rules and Regulations 4903

referenced the original issue of this 

service bulletin, dated October 10, 2001, 

as the appropriate source of service 

information for the proposed 

replacement. We find that the 

procedures described in Revision 1 and 

Revision 2 of the service bulletin are 

essentially the same as those in the 

original issue. Therefore, we have 

revised paragraph (a) of the final rule to 

reference Revision 2 of the service 

bulletin as the appropriate source of 

service information. We have also 

included a new paragraph (b) to this 

final rule (and re-lettered subsequent 

paragraphs accordingly) to give credit 

for replacements accomplished before 

the effective date of this AD per the 

original issue or Revision 1 of the 

service bulletin. 

Conclusion 

After careful review of the available 

data, including the comment noted 

above, we have determined that air 

safety and the public interest require the 

adoption of the rule with the changes 

described previously. We have 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Cost Impact 

We estimate that 55 Model BAe 146 

and Avro 146-RJ series airplanes of U.S. 

registry will be affected by this AD, that 

it will take approximately 4 work hours 

per airplane (1 hour per engine, 4 

engines per airplane) to accomplish the 

required actions, and that the average 

labor rate is $60 per work hour. The cost 

for required parts will be negligible. 

Based on these figures, the cost impact 

of the AD on U.S. operators is estimated 

to be $13,200, or $240 per airplane. 

The cost impact figure discussed 

above is 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 

adding the following new airworthiness 

directive:

2003–03–10 BAE Systems (Operations) 

Limited: Amendment 39–13034. Docket 

2002–NM–48–AD.

Applicability: All Model BAE 146 and 

Avro 146–RJ series airplanes, certificated in 

any category.

Note 1: This AD applies to each airplane 

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 

airplanes 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: Required as indicated, unless 

accomplished previously. 

To prevent failure of the engine fire 

detection and suppression systems to operate 

properly in the event of a fire, which could 

result in an undetected and uncontrollable 

fire in an engine, accomplish the following: 

Replacement 

(a) Within 31 months after the effective 

date of this AD, replace the existing ‘‘Low 

Temp’’ terminal blocks ‘‘G’’ with new, 

fireproof ceramic terminal blocks ‘‘G,’’ part 

number S3409–872, in engine zones 412, 

422, 432, and 442; per BAE Systems 

(Operations) Limited Service Bulletin SB.71–

077–01693A, Revision 2, dated May 28, 2002. 

(b) Replacements accomplished prior to the 

effective date of this AD per BAE Systems 

(Operations) Limited Service Bulletin SB.71–

077–01693A, dated October 10, 2001; or 

Revision 1, dated March 28, 2002; are 

acceptable for compliance with the 

requirements of paragraph (a) of this AD. 

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, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate. Operators 

shall submit their requests through an 

appropriate FAA Principal Maintenance 

Inspector, who may add comments and then 

send it to the Manager, International Branch, 

ANM–116.

Note 2: Information concerning the 

existence of approved alternative methods of 

compliance with this AD, if any, may be 

obtained from the International Branch, 

ANM–116.

Special Flight Permits 

(d) Special flight permits may be issued in 

accordance with sections 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 accomplished. 

Incorporation by Reference 

(e) Unless otherwise specified in this AD, 

the replacement shall be done per BAE 

Systems (Operations) Limited Service 

Bulletin SB.71–077–01693A, Revision 2 

dated May 28, 2002. 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 British Aerospace Regional 

Aircraft American Support, 13850 Mclearen 

Road, Herndon, Virginia 20171. Copies may 

be inspected 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.

Note 3: The subject of this AD is addressed 

in British airworthiness directive 005–10–

2001.

Effective Date 

(f) This amendment becomes effective on 

March 7, 2003.

4904 Federal Register / Vol. 68, No. 21 / Friday, January 31, 2003 / Rules and Regulations 

Issued in Renton, Washington, on January 

22, 2003. 

Vi L. Lipski, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 03–1955 Filed 1–30–03; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2001–NE–06–AD; Amendment 

39–13036; AD 2003–03–12] 

RIN 2120–AA64

Airworthiness Directives; Turbomeca 

S.A. Arriel 1 A2, 1 C, 1 C1, 1 C2, 1 D, 

1 D1, 1 E2, 1 K, 1 K1, 1 S, 1 S1 and 

Arriel 2 B, 2 B1, 2 C, 2 C1, 2 S1 Series 

Turboshaft Engines

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), that is 

applicable to Turbomeca S.A. Arriel 1 

A2, 1 C, 1 C1, 1 C2, 1 D, 1 D1, 1 E2, 

1 K, 1 K1, 1 S, 1 S1 and Arriel 2 B, 2 

B1, 2 C, 2 C1, 2 S1 series turboshaft 

engines. This amendment requires the 

insertion of a sleeve in the attachment 

boss of the compressor bleed valve, and 

bonding the sleeve in the bleed-valve 

mounting pad. This amendment is 

prompted by several cases of contained 

centrifugal compressor impeller blade 

ruptures that occurred in service. The 

actions specified by this AD are 

intended to prevent acoustic excitation 

of the centrifugal compressor impeller 

blades resulting in contained 

compressor impeller blade ruptures and 

power loss that could lead to an 

uncommanded in-flight shutdown.

DATES: Effective March 7, 2003. The 

incorporation by reference of certain 

publications listed in the regulations is 

approved by the Director of the Federal 

Register as of March 7, 2003.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Turbomeca S.A, 64511 Bordes 

Cedex, France; telephone 33 05 59 64 40 

00; fax 33 05 59 64 60 80. 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:

Antonio Cancelliere, Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine and Propeller Directorate, 

12 New England Executive Park, 

Burlington, MA 01803–5299; telephone 

(781) 238–7751; 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 

Turbomeca S.A. Arriel 1 D, 1 D1, 1 S, 

1 S1, and ¥2B series turboshaft engines 

was published in the Federal Register

on September 6, 2001 (66 FR 46562). 

That proposal was revised by a 

supplemental notice of proposed 

rulemaking (SNPRM) to amend part 39 

of the Federal Aviation Regulations (14 

CFR part 39) to include an AD that 

expanded the applicability to 

Turbomeca S.A. Arriel 1 A2, 1 C, 1 C1, 

1 C2, 1 D, 1 D1, 1 E2, 1 K, 1 K1, 1 S, 

1 S1 and Arriel 2 B, 2 B1, 2 C, 2 C1, 

2 S1 series turboshaft engines. That 

SNPRM was published in the Federal 

Register on September 20, 2002 (67 FR 

59217). That action proposed to require 

the insertion of a sleeve in the 

attachment boss of the compressor bleed 

valve, and bonding the sleeve in the 

bleed-valve mounting pad, in 

accordance with Turbomeca S.A. 

Mandatory Service Bulletin (MSB) No. 

292 72 2054, dated September 20, 1999; 

MSB No. 292 72 0261, dated September 

20, 1999; MSB No. 292 72 2070, Update 

No. 1, dated October 5, 2001; and MSB 

No. 292 72 0275, Update No. 1, dated 

October 2, 2001. Since the publication 

of the SNPRM, MSB No. 292 72 0275 

has been reissued as Update No. 2, 

dated April 15, 2002. This MSB expands 

the engine model applicability of this 

AD by referencing MSB No. 292 72 

0261, dated September 20, 1999, and 

Service Bulletin (SB) No. 292 72 0262, 

dated September 28, 1999. Accordingly, 

a new paragraph (b) has been added to 

reflect the updated MSB. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. No 

comments were received on the 

proposal or the FAA’s determination of 

the cost to the public. The FAA has 

determined that air safety and the 

public interest require the adoption of 

the rule as proposed. 

Economic Analysis 

There are approximately 1,406 

Turbomeca S.A. Arriel 1 and Arriel 2 

model turboshaft engines of the affected 

design in the worldwide fleet. The FAA 

estimates that 476 engines installed on 

helicopters of U.S. registry will be 

affected by this AD, that it will take 

approximately 1.0 work hour per engine 

to perform the required actions, and that 

the average labor rate is $60 per work 

hour. Required parts will cost 

approximately $430 per engine. Based 

on these figures, the total cost of the AD 

to U.S. operators is estimated to be 

$233,240. 

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 

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, 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 

adding a new airworthiness directive to 

read as follows:

2003–03–12 Turbomeca S.A.: Amendment 

39–13036. Docket No. 2001–NE–06–AD.

Applicability: This airworthiness directive 

(AD) is applicable to Turbomeca S.A. Arriel