56854 Federal Register / Vol. 71, No. 188 / Thursday, September 28, 2006 / Rules and Regulations 

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): 

2006–20–01 Airbus: Amendment 39–14770. 

Docket No. FAA–2006–25421; 

Directorate Identifier 2006–NM–074–AD. 

Effective Date 

(a) This AD becomes effective November 2, 

2006. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Airbus Model 

A310 airplanes, certificated in any category. 

Unsafe Condition 

(d) This AD results from several incidents 

of pitch oscillations with high vertical loads 

that occurred during turbulence at high 

altitudes. We are issuing this AD to prevent 

pitch oscillations during turbulence, which 

could result in 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. 

Revision of Airplane Flight Manual (AFM) 

(f) Within 10 days after the effective date 

of this AD, revise the Limitations section of 

the Airbus A310 AFM to include the 

information in Airbus A310 Temporary 

Revision (TR) 2.03.00/21, dated April 11, 

2005. This may be done by inserting a copy 

of the TR into the AFM. When the 

information in the TR has been included in 

the general revisions of the AFM, those 

general revisions may be inserted into the 

AFM, provided the relevant information in 

the general revisions is identical to that in 

the TR. 

Alternative Methods of Compliance 

(AMOCs) 

(g)(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 

(h) French airworthiness directive F–2005–

114, dated July 6, 2005, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(i) You must use Airbus A310 Temporary 

Revision 2.03.00/21, dated April 11, 2005, to 

the Airbus A310 Airplane Flight Manual, 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 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 

September 14, 2006. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 06–8228 Filed 9–27–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–24990; Directorate 

Identifier 2006–NM–013–AD; Amendment 

39–14772; AD 2006–20–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A319, A320, and A321 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 

Airbus Model A319, A320, and A321 

airplanes. This AD requires an 

inspection to determine if the stiff part 

of the girt and girt bar position of the 

forward left-hand and right-hand 

passenger doors is incorrect, and repair 

if necessary. This AD results from cases 

of girt bar disengagement from the floor 

fitting during deployment tests of slide 

rafts at the forward passenger doors. We 

are issuing this AD to prevent 

disengagement of the telescopic girt bar 

from the airplane when the door is 

opened in emergency situations, which 

could result in the inability to open the 

passenger door and to use the escape 

slide/raft at that door during an 

emergency evacuation of the airplane. 

DATES: This AD becomes effective 

November 2, 2006. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 2, 2006. 

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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2125; 

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 notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to certain Airbus Model A319, 

A320, and A321 airplanes. That NPRM 

was published in the Federal Register 

on June 12, 2006 (71 FR 33661). That 

NPRM proposed to require an 

inspection to determine if the stiff part 

of the girt and girt bar position of the 

forward left-hand and right-hand 

passenger doors is incorrect, and repair 

if necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Support for the NPRM 

Airbus agrees with the NPRM. 

Request To Withdraw the NPRM 

The Air Transport Association (ATA), 

on behalf of its member, US Airways, 

requests that we clarify the impact of 

AD 2005–23–05 on the NPRM. (On 

October 25, 2005, we issued AD 2005–

23–05, amendment 39–14363 (70 FR 

69063, November 14, 2005), for certain 

Airbus Model A319–100, A320–200, 

and A321–100 and –200 series 


jlentini on PROD1PC65 with RULES
Federal Register / Vol. 71, No. 188 / Thursday, September 28, 2006 / Rules and Regulations 56855 

airplanes. AD 2005–23–05 requires 

modification of the telescopic girt bar of 

the escape slide/raft assembly, and 

follow-on actions. AD 2005–23–05 also 

requires a new modification of the 

telescopic girt bar and the installation of 

placards on the modified girt bars, 

which terminate the repetitive 

functional tests. We issued AD 2005–

23–05 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.) US Airways 

states that the intent of the NPRM has 

already been accomplished with AD 

2005–23–05. US Airways asserts that 

AD 2005–23–05 requires replacement of 

the telescopic girt bar on affected slide 

rafts, and that during replacement of the 

girt bar, the girt is reinstalled using the 

same instructions referenced in the 

NPRM. US Airways points out that the 

compliance time of AD 2005–23–05 is 

August 19, 2007. Therefore, US Airways 

requests that we either withdraw the 

NPRM or grant AD 2005–23–05 as an 

alternative method of compliance 

(AMOC) to the NPRM. 

We do not agree to withdraw this AD, 

since the applicability of AD 2005–23–

05 and this AD do not exactly match. 

Also, this AD mandates a shorter 

compliance time than AD 2005–23–05. 

However, we do agree to provide credit 

for accomplishing the actions in 

paragraph (g) of AD 2005–23–05. 

Paragraph (g) of AD 2005–23–05 

references Airbus Service Bulletin 

A320–52–1112, Revision 05, dated June 

25, 2004, as the appropriate source of 

service information for modifying the 

telescopic girt bar. We have reviewed 

Airbus Service Bulletin A320–52–1112, 

Revision 05, and have determined that 

accomplishing the actions in that 

service bulletin is acceptable for 

accomplishing the actions specified in 

paragraph (f) of this AD. Therefore, we 

have added a new paragraph (h) to this 

AD allowing credit for accomplishment 

of paragraph (g) of AD 2005–23–05. We 

have reidentified the subsequent 

paragraphs accordingly. 

Change to the Cost of Compliance 

We have reduced our estimate for the 

number of affected airplanes of U.S. 

registry. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

the changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

This AD affects about 200 airplanes of 

U.S. registry. The actions in this AD 

take about 1 work hour per airplane, at 

an average labor rate of $80 per work 

hour. Based on these figures, the 

estimated cost of the AD for U.S. 

operators is $16,000, or $80 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): 

2006–20–03 Airbus: Amendment 39–14772. 

Docket No. FAA–2006–24990; 

Directorate Identifier 2006–NM–013–AD. 

Effective Date 

(a) This AD becomes effective November 2, 

2006. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A319, 

A320, and A321 airplanes, certificated in any 

category; on which Airbus Modification 

20233, 25902, or 24365 (installation of slide 

raft) has been done in production; excluding 

those airplanes having manufacturer’s serial 

numbers 1794, 2155, 2195, 2204, 2231, 2239, 

2244, 2246, 2247, 2252, 2254, 2255, 2257, 

2259, 2261, 2263, 2267, 2273, 2274, 2275, 

2278, 2280, 2282, 2284, 2286, 2288, 2297, 

2301, 2307, 2310, 2314, 2327, 2369, and 

subsequent. 

Unsafe Condition 

(d) This AD results from cases of girt bar 

disengagement from the floor fitting during 

deployment tests of slide rafts at the forward 

passenger doors. We are issuing this AD to 

prevent disengagement of the telescopic girt 

bar from the airplane when the door is 

opened in emergency situations, which could 

result in the inability to open the passenger 

door and to use the escape slide/raft at that 

door during an emergency evacuation 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. 

Inspection and Repair 

(f) Within 200 days after the effective date 

of this AD, do a general visual inspection to 

determine if the stiff part of the girt and girt 

bar position of the forward left-hand and 

right-hand passenger doors is incorrect, in 

accordance with the Accomplishment 


jlentini on PROD1PC65 with RULES
56856 Federal Register / Vol. 71, No. 188 / Thursday, September 28, 2006 / Rules and Regulations 

Instructions of Airbus Service Bulletin A320–

25–1394, Revision 01, dated December 12, 

2005. If the stiff part of the girt or the girt bar 

position is incorrect, before further flight, 

repair in accordance with the service 

bulletin. 

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’

(g) Inspecting and repairing if necessary 

before the effective date of this AD in 

accordance with Airbus Service Bulletin 

A320–25–1394, dated July 23, 2004, is 

acceptable for compliance with the 

requirements of paragraph (f) of this AD. 

Credit for AD 2005–23–05, Amendment 39–

14363 

(h) Accomplishing the actions required by 

paragraph (g) of AD 2005–23–05 is acceptable 

for compliance with the corresponding 

requirements of paragraph (f) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(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 

(j) French airworthiness directive F–2005–

172, issued December 21, 2005, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(k) You must use Airbus Service Bulletin 

A320–25–1394, Revision 01, dated December 

12, 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 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 

September 14, 2006. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 06–8229 Filed 9–27–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–24867; Directorate 

Identifier 2006–NM–064–AD; Amendment 

39–14773; AD 2006–20–04] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model DHC–8–102, –103, and –106 

Airplanes, and Model DHC–8–200 and 

DHC–8–300 Series 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 

Bombardier Model DHC–8–102, –103, 

and –106 airplanes, and Model DHC–8–

200 and DHC–8–300 series airplanes. 

This AD requires performing a one-time 

general visual inspection for nonconforming chain links of chain 

assemblies of the elevator trim system 

and gust lock system, and corrective 

actions if necessary. This AD also 

requires temporary revisions to the 

airplane flight manuals of the affected 

airplanes, which describe procedures 

for elevator trim checks. This AD results 

from reports of several failures of the 

elevator trim chain, due to hydrogen 

embrittlement. We are issuing this AD 

to prevent breakage of the elevator trim 

chain, which would prevent the actual 

position of the elevator trim tab from 

being annunciated to the flightcrew. 

Attempting to adjust the trim tab from 

the full nose up or full nose down 

position with a broken trim chain could 

result in misleading information relative 

to takeoff trim settings and consequent 

loss of control on takeoff. 

DATES: This AD becomes effective 

November 2, 2006. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of November 2, 2006. 

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 Bombardier, Inc., Bombardier 

Regional Aircraft Division, 123 Garratt 

Boulevard, Downsview, Ontario M3K 

1Y5, Canada, for service information 

identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Ezra 

Sasson, Aerospace Engineer, Systems 

and Flight Test Branch, ANE–172, FAA, 

New York Aircraft Certification Office, 

1600 Stewart Avenue, suite 410, 

Westbury, New York 11590; telephone 

(516) 228–7320; fax (516) 794–5531. 

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 notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to certain Bombardier Model 

DHC–8–102, –103, and –106 airplanes, 

and Model DHC–8–200 and DHC–8–300 

series airplanes. That NPRM was 

published in the Federal Register on 

May 25, 2006 (71 FR 30070). That 

NPRM proposed to require performing a 

one-time inspection for non-conforming 

chain links of chain assemblies of the 

elevator trim system and gust lock 

system, and corrective actions if 

necessary. That NPRM also proposed to 

require temporary revisions to the 

airplane flight manuals of the affected 

airplanes, which describe procedures 

for elevator trim checks. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the single comment 

received. 

Request To Revise Costs of Compliance 

One commenter, Horizon Air, 

requests that we adjust the costs of 

compliance in the NPRM. Horizon Air 

asserts that, rather than the 5 work 

hours specified in the NPRM to 

accomplish the inspection on each 

airplane, the figure specified by 

Bombardier of 15 work hours to 


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