Federal Register / Vol. 70, No. 218 / Monday, November 14, 2005 / Rules and Regulations 69061 

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 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): 

2005–23–06 Learjet: Amendment 39–14364. 

Docket No. FAA–2005–20947; 

Directorate Identifier 2004–NM–245–AD. 

Effective Date 

(a) This AD becomes effective December 

19, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Learjet Model 23, 24, 

24A, 24B, 24B–A, 24D, 24D–A, 24E, 24F, 25, 

25A, 25B, 25C, 25D, and 25F airplanes; 

certificated in any category; modified by 

Supplemental Type Certificate SA1731SW, 

SA1669SW, or SA1670SW; equipped with 

Nordam (formerly Dee Howard Company) 

thrust reverser accumulators having part 

number (P/N) 25–0570–127–1, –3, –7, –13, or 

–17. 

Unsafe Condition 

(d) This AD was prompted by reports of the 

failure of two thrust reverser accumulators. 

We are issuing this AD to prevent failure of 

the thrust reverser accumulators, due to 

fatigue cracking on the female threads, which 

could result in the loss of hydraulic power 

and damage to the surrounding airplane 

structure. 

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. 

Remove Thrust Reverser Accumulator 

(f) Within 60 days after the effective date 

of this AD, remove the thrust reverser 

accumulator, and make the thrust reverser 

hydraulic system and the thrust reversers 

inoperable, by doing all of the actions 

specified in the Accomplishment 

Instructions of The Nordam Group Alert 

Service Bulletin A3000 78–21, dated 

November 25, 2002. Where there are 

differences between the Master Minimum 

Equipment List and the AD, the AD prevails. 

Although the service bulletin referenced in 

this AD specifies to submit certain 

information to the manufacturer, this AD 

does not include that requirement. 

Parts Installation 

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

person may install a thrust reverser 

accumulator having P/N 25–0570–127–1, –3, 

–7, –13, or –17 on any airplane. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Special Certification 

Office, Rotorcraft 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 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. 

Material Incorporated by Reference 

(i) You must use The Nordam Group Alert 

Service Bulletin A3000 78–21, dated 

November 25, 2002, 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 The Nordam Group, Nacelle/Thrust 

Reverser Systems Division, 6911 North 

Whirlpool Drive, Tulsa, Oklahoma 74117, 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/cfr/ibrlocations.html. 

Issued in Renton, Washington on October 

28, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–22215 Filed 11–10–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22255; Directorate 

Identifier 2005–NM–106–AD; Amendment 

39–14362; AD 2005–23–04] 

RIN 2120–AA64 

Airworthiness Directives; Saab Model 

SAAB 2000 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Saab Model SAAB 2000 airplanes. This 

AD requires modifying the manual 

feather-and-unfeather system for the 

propellers to make the design of the 

system more robust. This AD results 

from reports of in-flight engine 

shutdown caused by uncommanded 

operation of the feather pump of the 

propeller. We are issuing this AD to 

prevent uncommanded feathering of the 

propeller, which could result in the 

shutdown of an engine during flight and 

consequent reduced controllability of 

the airplane. 

DATES: This AD becomes effective 

December 19, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 19, 2005. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, room PL–401, 

Washington, DC. 

Contact Saab Aircraft AB, SAAB 

Aircraft Product Support, S–581.88, 

Linko ̈ping, Sweden, for service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Mike Borfitz, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 227–2677; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

69062 Federal Register / Vol. 70, No. 218 / Monday, November 14, 2005 / Rules and Regulations 

Examining the Docket 

You may examine the airworthiness 

directive (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 street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to certain Saab Model SAAB 2000 

airplanes. That NPRM was published in 

the Federal Register on September 1, 

2005 (70 FR 52041). That NPRM 

proposed to require modifying the 

manual feather-and-unfeather system for 

the propellers to make the design of the 

system more robust. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We received no 

comments on the NPRM or on the 

determination of the cost to the public. 

Clarification of Alternative Method of 

Compliance (AMOC) Paragraph 

We have revised this action to clarify 

the appropriate procedure for notifying 

the principal inspector before using any 

approved AMOC on any airplane to 

which the AMOC applies. 

Conclusion 

We have carefully reviewed the 

available data, and determined that air 

safety and the public interest require 

adopting the AD with the change 

described previously. We have 

determined that this change will neither 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Costs of Compliance 

This AD will affect about 3 airplanes 

of U.S. registry. The actions will take 

about 50 work hours per airplane, at an 

average labor rate of $65 per work hour. 

Required parts will cost about $13,571 

per airplane. Based on these figures, the 

estimated cost of the AD for U.S. 

operators is $50,463, or $16,821 per 

airplane. 

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 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 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): 

2005–23–04 Saab Aircraft AB: Amendment 

39–14362. Docket No. FAA–2005–22255; 

Directorate Identifier 2005–NM–106–AD. 

Effective Date 

(a) This AD becomes effective December 

19, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model SAAB 2000 

airplanes, certificated in any category, serial 

numbers –004 through –063 inclusive. 

Unsafe Condition 

(d) This AD results from reports of in-flight 

engine shutdown caused by uncommanded 

operation of the feather pump of the 

propeller. We are issuing this AD to prevent 

uncommanded feathering of the propeller, 

which could result in the shutdown of an 

engine during flight and consequent reduced 

controllability of 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. 

Modification 

(f) Within 12 months after the effective 

date of this AD, modify the manual featherand-unfeather system of the propellers by 

doing all actions specified in the 

Accomplishment Instructions of Saab Service 

Bulletin 2000–61–006, Revision 01, dated 

February 17, 2005. 

Actions Accomplished Previously 

(g) A modification accomplished before the 

effective date of this AD in accordance with 

Saab Service Bulletin 2000–61–006, dated 

December 20, 2004, is acceptable for 

compliance with paragraph (f) of this AD. 

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) Swedish airworthiness directive 1–198, 

dated February 14, 2005, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(j) You must use Saab Service Bulletin 

2000–61–006, Revision 01, dated February 

17, 2005, 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 Saab Aircraft AB, SAAB Aircraft 

Federal Register / Vol. 70, No. 218 / Monday, November 14, 2005 / Rules and Regulations 69063 

Product Support, S–581.88, Linko ̈ping, 

Sweden, 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 October 

27, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–22218 Filed 11–10–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19863; Directorate 

Identifier 2003–NM–29–AD; Amendment 39–

14363; AD 2005–23–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A319–100, A320–200, and A321–100 

and –200 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Airbus Model 

A319–100, A320–200, and A321–100 

and –200 series airplanes. That AD 

currently requires modification of the 

telescopic girt bar of the escape slide/ 

raft assembly, and follow-on actions. 

This new AD requires a new 

modification of the telescopic girt bar 

and the installation of placards on the 

modified girt bars, which terminates the 

repetitive functional tests required by 

the existing AD. This AD results from 

development of a new, improved 

modification. We are issuing this AD to 

prevent failure of the escape slide/raft to 

deploy correctly, which could result in 

the slide being unusable during an 

emergency evacuation and consequent 

injury to passengers or airplane 

crewmembers. 

DATES: This AD becomes effective 

December 19, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 19, 2005. 

On August 31, 2001 (66 FR 42939, 

August 16, 2001), the Director of the 

Federal Register approved the 

incorporation by reference of Airbus 

Industrie All Operators Telex A320–

52A1111, Revision 01, dated July 23, 

2001, including Airbus Industrie 

Technical Disposition 959.1492/01, 

Issue C, dated July 17, 2001. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, room PL–401, 

Washington, DC. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2141; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (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 street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a supplemental 

notice of proposed rulemaking (NPRM) 

to amend 14 CFR part 39 to include an 

AD that supersedes AD 2001–16–14, 

amendment 39–12383 (66 FR 42939, 

August 16, 2001). The existing AD 

applies to certain Airbus Model A319, 

A320, and A321 series airplanes. That 

supplemental NPRM was published in 

the Federal Register on July 21, 2005 

(70 FR 42005). That supplemental 

NPRM proposed to mandate the 

installation of placards on the modified 

girt bars, which terminates the repetitive 

functional tests required by the existing 

AD. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the additional comment that 

has been received on the supplemental 

NPRM. The commenter supports the 

supplemental NPRM. 

Clarification of Alternative Method of 

Compliance (AMOC) Paragraph 

We have changed this AD to clarify 

the appropriate procedure for notifying 

the principal inspector before using any 

approved AMOC on any airplane to 

which the AMOC applies. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

that has been received, and determined 

that air safety and the public interest 

require adopting the AD as proposed. 

Costs of Compliance 

This AD will affect about 517 

airplanes of U.S. registry. 

The modification that is required by 

AD 2001–16–14 and retained in this AD 

takes about 7 work hours per airplane, 

at an average labor rate of $65 per work 

hour. The cost of required parts is 

negligible. Based on these figures, the 

estimated cost of the currently required 

modification for U.S. operators is 

$235,235, or $455 per airplane. 

The functional test that is required by 

AD 2001–16–14 and retained in this AD 

takes about 1 work hour per airplane, at 

an average labor rate of $65 per work 

hour. Based on these figures, the cost 

impact of the currently required 

functional test for U.S. operators is 

$33,605, or $65 per airplane, per test 

cycle. 

For airplanes that have not been 

modified in accordance with AD 2001–

16–14: The new modification (including 

the new placard installation) takes about 

17 work hours per airplane, at an 

average labor rate of $65 per work hour. 

Required parts cost about $5,130 per 

airplane. Based on these figures, the 

estimated cost of the new modification 

specified in this AD is $6,235 per 

airplane. 

For airplanes that have been modified 

in accordance with AD 2001–16–14: 

The new modification (including the 

new placard installation) takes about 21 

work hours per airplane, at an average 

labor rate of $65 per work hour. 

Required parts cost about $5,130 per 

airplane. Based on these figures, the 

estimated cost of the new modification 

specified in this AD is $6,495 per 

airplane. 

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.