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. 

69064 Federal Register / Vol. 70, No. 218 / Monday, November 14, 2005 / Rules and Regulations 

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 removing amendment 39–12383 (66 

FR 42939, August 16, 2001) and by 

adding the following new airworthiness 

directive (AD): 

2005–23–05 Airbus: Amendment 39–14363. 

Docket No. FAA–2004–19863; 

Directorate Identifier 2003–NM–29–AD. 

Effective Date 

(a) This AD becomes effective December 

19, 2005. 

Affected ADs 

(b) This AD supersedes AD 2001–16–14. 

Applicability 

(c) This AD applies to Airbus Model A319–

111, –112, –113, –114, –115, –131, –132, and 

–133; A320–211, –212, –214, –231, –232, and 

–233; and A321–111, –112, –131, –211, and 

–231 airplanes; certificated in any category; 

equipped with telescopic girt bars of the 

escape slide/raft assembly installed per 

Airbus Modification 20234, or Airbus Service 

Bulletin A320–25–1055 or A320–25–1218 in 

service; except those airplanes with Airbus 

Modification 31708. 

Unsafe Condition 

(d) This AD was prompted by development 

of a new, improved modification of the 

telescopic girt bar of the escape slide/raft 

assembly. 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. 

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. 

Restatement of Requirements of AD 2001–

16–14 

Modification/Follow-On Actions 

(f) For airplanes listed in Airbus Industrie 

All Operators Telex (AOT) A320–52A1111, 

Revision 01, dated July 23, 2001: Within 

1,500 flight hours after August 31, 2001 (the 

effective date of AD 2001–16–14); except as 

provided by paragraph (h) of this AD, modify 

the telescopic girt bar of the escape slide/raft 

assembly installed on all passenger and crew 

doors and do a functional test to ensure the 

girt bar does not retract, per Airbus Industrie 

AOT A320–52A1111, Revision 01, dated July 

23, 2001. 

(1) If the girt bar retracts, before further 

flight, replace any discrepant parts and do 

another functional test to ensure the girt bar 

does not retract, per the AOT. Repeat the 

functional test thereafter at intervals not to 

exceed 18 months until paragraph (g) of this 

AD is accomplished. 

(2) If the girt bar does not retract, repeat the 

functional test thereafter at intervals not to 

exceed 18 months. 

Note 1: Modification and follow-on actions 

accomplished prior to the effective date of 

this AD per Airbus Industrie AOT A320–

52A1111, dated July 5, 2001, are considered 

acceptable for compliance with the 

applicable actions specified in this 

amendment. 

New Requirements of This AD 

Modification 

(g) Within 20 months after the effective 

date of this AD: Accomplish the actions 

specified in paragraphs (g)(1) and (g)(2) of 

this AD by doing all the applicable actions 

specified in the Accomplishment 

Instructions of Airbus Service Bulletin A320–

52–1112, Revision 05, dated June 25, 2004. 

Accomplishing these actions terminates the 

repetitive functional tests required by 

paragraph (f) of this AD. 

(1) Modify the telescopic girt bar of the 

escape slide/raft assembly. 

(2) Install a placard on each modified girt 

bar. 

(h) For airplanes on which the 

modification of the telescopic girt bar 

required by paragraph (g)(1) of this AD is 

accomplished within the compliance time 

specified in paragraph (f) of this AD, 

accomplishing the modification required by 

paragraph (f) is not required. 

Modifications Accomplished According to 

Previous Issues of Service Bulletin 

(i) Modification of the telescopic girt bar 

accomplished before the effective date of this 

AD in accordance with Airbus Service 

Bulletin A320–52–1112, dated January 16, 

2002; Revision 01, dated April 3, 2002; 

Revision 02, dated September 6, 2002; 

Revision 03, dated June 27, 2003; or Revision 

04, dated November 12, 2003; is considered 

acceptable for compliance with the 

modification of the telescopic girt bar 

required by paragraph (g)(1) of this AD. 

Parts Installation 

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

person may install on any airplane a 

telescopic girt bar of the escape slide/raft 

assembly unless it has been modified as 

required by paragraph (g) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve alternative 

methods of compliance (AMOCs) for this AD, 

if requested in accordance with the 

procedures found in 14 CFR 39.19. 

(2) AMOCs approved previously in 

accordance with AD 2001–16–14 are 

approved as AMOCs with paragraph (f) of 

this AD. 

(3) 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 

(l) French airworthiness directives 2002–

637(B) R1, dated April 16, 2003, and F–2005–

057, dated April 13, 2005, also address the 

subject of this AD. 

Material Incorporated by Reference 

(m) You must use Airbus Service Bulletin 

A320–52–1112, Revision 05, dated June 25, 

2004; and Airbus Industrie All Operators 

Telex A320–52A1111, Revision 01, dated 

July 23, 2001, including Airbus Industrie 

Federal Register / Vol. 70, No. 218 / Monday, November 14, 2005 / Rules and Regulations 69065 

Technical Disposition 959.1492/01, Issue C, 

dated July 17, 2001; as applicable; to perform 

the actions that are required by this AD, 

unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Airbus Service Bulletin A320–52–1112, 

Revision 05, dated June 25, 2004; in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) 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. 

(3) Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 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 

25, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–22217 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–2005–22881; Directorate 

Identifier 2005–NM–202–AD; Amendment 

39–14368; AD 2005–23–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200 and A330–300 Series 

Airplanes; and Model A340–200 and 

A340–300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Airbus Model A330–200 and A330–300 

series airplanes; and Model A340–200 

and A340–300 series airplanes. This AD 

requires an accelerated schedule of 

repetitive testing of the elevator servo 

control loops, and corrective actions if 

necessary. This AD results from reports 

of failed elevator servo controls due to 

broken guides. We are issuing this AD 

to ensure proper functioning of the 

elevator servo controls. Failure of the 

elevator servo controls during certain 

phases of takeoff could result in an 

unannounced loss of elevator control 

and consequent reduced controllability 

of the airplane. 

DATES: This AD becomes effective 

November 29, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of November 29, 2005. 

We must receive comments on this 

AD by January 13, 2006. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street SW., Nassif Building, 

Room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2797; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The Direction Ge ́ne ́rale de l’Aviation 

Civile (DGAC), which is the 

airworthiness authority for France, 

notified us that an unsafe condition may 

exist on all Airbus Model A330–200 and 

A330–300 series airplanes; and Model 

A340–200 and A340–300 series 

airplanes. The DGAC advises that it has 

received reports of elevator servo 

control removals resulting from the ‘‘F/ 

CTL ELEV SERVO FAULT’’ warning. 

During repair, some of these servo 

controls installed at the active position 

(2CS1) (Left Green) or (2CS2) (Right 

Green) were found with a broken guide. 

The broken guides resulted in the 

inability for the affected servo controls 

to change their operating mode, leading 

to ‘‘F/CTL ELEV SERVO FAULT’’

warnings. Results of the investigation 

revealed a fatigue rupture inside the 

servo control induced by successive 

pressure cycles and resulting in a 

progressive decrease of the tightening 

torque of the plug to be the root cause 

of the broken guides. 

Each elevator is equipped with two 

servo controls having three operating 

modes: active mode, damping mode, 

and centering mode. In normal 

operating conditions, each elevator is 

actuated by one servo control in active 

mode, while the other is in damping 

mode. The mode change from active to 

damping is achieved by a mode-selector 

spool valve installed inside each servo 

control. The position of this spool valve 

is commanded by a rod that slides 

through a guide. A broken guide could 

result in the inability for the affected 

servo control to change its operating 

mode. 

Failure of the elevator servo controls 

during certain phases of takeoff, if not 

corrected, could result in an 

unannounced loss of elevator control 

and consequent reduced controllability 

of the airplane. 

Relevant Service Information 

Airbus has issued All Operators Telex 

(AOT) A330–27A3138, Revision 01, 

dated October 3, 2005, for Model A330–

200 and –300 series airplanes; and AOT 

A340–27A4137, Revision 01, dated 

October 3, 2005, for Model A340–200 

and –300 series airplanes. The AOTs 

describe procedures for repetitive tests 

of the elevator servo-loops and 

corrective actions if the test fails. If the 

test fails, the AOTs specify performing 

the associated troubleshooting manual 

tasks and applicable corrective actions. 

The corrective actions include repairing 

wiring, replacing certain solenoid 

valves, replacing certain mode selector 

valve transducers, and replacing the 

elevator servo control, among other 

actions, depending on the fault message 

displayed. The AOTs also specify 

reporting failed tests and sending 

replaced servo controls to Airbus. 

The DGAC mandated the AOTs and 

issued French airworthiness directive 

UF–2005–171, dated October 3, 2005, to 

ensure the continued airworthiness of 

these airplanes in France. 

FAA’s Determination and Requirements 

of This AD 

These airplane models are 

manufactured in France and are type 

certificated for operation in the United 

States under the provisions of section