Federal Register / Vol. 70, No. 223 / Monday, November 21, 2005 / Rules and Regulations 70035 

email_subscription/ and allows FSIS 

customers to sign up for subscription 

options across eight categories. Options 

range from recalls to export information 

to regulations, directives and notices. 

Customers can add or delete 

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List of Subjects in 9 CFR Part 327 

Imported Products. 

■ For the reasons set out in the 

preamble, FSIS is amending 9 CFR part 

327 as follows: 

PART 327—IMPORTED PRODUCTS 

■ 1. The authority citation for part 327 

continues to read as follows: 

Authority: 21 U.S.C. 601–695; 7 CFR 2.18, 

2.53. 

§ 327.2 [Amended] 

■ 2. Section 327.2 is amended by adding 

Chile in alphabetical order to the list of 

countries in paragraph (b). 

Done at Washington, DC, on: October, 11, 

2005. 

Barbara J. Masters, 

Administrator. 

[FR Doc. 05–22980 Filed 11–18–05; 8:45 am] 

BILLING CODE 3410–DM–P 

FARM CREDIT ADMINISTRATION 

12 CFR Part 627 

RIN 3052–AC26 

Title IV Conservators, Receivers, and 

Voluntary Liquidations; Receivership 

Repudiation Authorities; Effective Date 

AGENCY: Farm Credit Administration. 

ACTION: Notice of effective date. 

SUMMARY: The Farm Credit 

Administration (FCA) published a final 

rule under part 627 on September 22, 

2005 (70 FR 55513). This final rule gives 

certainty to Farm Credit System 

institutions regarding how the Farm 

Credit System Insurance Corporation 

will treat qualifying participations and 

securitizations if the institution is 

subsequently placed in conservatorship 

or receivership. In accordance with 12 

U.S.C. 2252, the effective date of the 

final rule is 30 days from the date of 

publication in the Federal Register 

during which either or both Houses of 

Congress are in session. Based on the 

records of the sessions of Congress, the 

effective date of the regulations is 

November 14, 2005. 

DATES: The regulation amending 12 CFR 

part 627, published on September 22, 

2005 (70 FR 55513) is effective 

November 14, 2005. 

FOR FURTHER INFORMATION CONTACT: 

Robert E. Donnelly, Senior Accountant, 

Office of Policy and Analysis, Farm 

Credit Administration, McLean, VA 

22102–5090, (703) 883–4498, TTY (703) 

883–4434; or Rebecca S. Orlich, Senior 

Attorney, Office of General Counsel, 

Farm Credit Administration, McLean, 

VA 22102–5090, (703) 883–4020, TTY 

(703) 883–4020. 

(12 U.S.C. 2252(a)(9) and (10)) 

Dated: November 15, 2005. 

Jeanette C. Brinkley, 

Secretary, Farm Credit Administration Board. 

[FR Doc. 05–23001 Filed 11–18–05; 8:45 am] 

BILLING CODE 6705–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–23005; Directorate 

Identifier 2003–NM–110–AD; Amendment 

39–14379; AD 2005–23–21] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 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 A340–200 and A340–300 

series airplanes. This AD requires 

repetitive inspections for cracking of the 

junction between the thrust reverser 

forward frame and the 12 o’clock and 6 

o’clock beams; the thrust reverser 

common fittings; and the thrust reverser 

J-ring structure at the 12 o’clock and 6 

o’clock positions; and related 

investigative and corrective actions. 

This AD results from fatigue and 

damage tolerance testing of the engine 

thrust reversers which revealed fatigue 

cracking of the junction between the 

thrust reverser forward frame and the 12 

o’clock beam, and of the thrust reverser 

J-ring structure. We are issuing this AD 

to detect and correct such fatigue 

cracking, which could result in rupture 

of the J-ring, forward frame, or common 

fittings; loss of the thrust reverser 

system; or inadvertent deployment of a 

thrust reverser in flight and consequent 

reduced controllability of the airplane. 

DATES: This AD becomes effective 

December 6, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of December 6, 2005. 

We must receive comments on this 

AD by January 20, 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; 

or Rohr Inc., 850 Lagoon Drive, Chula 

Vista, California 91912; for service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

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 A340–200 and 

A340–300 series airplanes. The DGAC 

advises that fatigue and damage 

tolerance testing of the engine thrust 

reversers revealed cracking of the 

junction between the thrust reverser 

forward frame and the 12 o’clock beam. 

The cracking of the junction was found 

after the accumulation of approximately 

20,000 total flight cycles. In addition to 

the fatigue cracking that was found 

during fatigue tests, fatigue cracking of 

the J-ring was also found on in-service 

airplanes that had accumulated fewer 

than 6,666 total flight cycles. These 

conditions, if not corrected, could result 

in rupture of the J-ring, forward frame, 

or common fittings; loss of the thrust 

reverser system; or inadvertent 

deployment of a thrust reverser in flight 

70036 Federal Register / Vol. 70, No. 223 / Monday, November 21, 2005 / Rules and Regulations 

and consequent reduced controllability 

of the airplane. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A340–78–4028, including Appendix 01, 

Revision 01, dated October 23, 2003. 

The service bulletin describes 

procedures for repetitive inspections for 

cracking of the junction between the 

thrust reverser forward frame and the 12 

o’clock and 6 o’clock beams and the 

thrust reverser common fittings, and 

related investigative and corrective 

actions. 

The Airbus Service Bulletin refers to 

Rohr Service Bulletin RA34078–71, 

Revision 1, dated February 7, 2003, as 

an appropriate source of service 

information for accomplishing the eddy 

current inspections for cracking. The 

related investigative and corrective 

actions include performing eddy current 

inspections for missing fasteners, 

installing missing fasteners, replacing 

the thrust reverser with a new thrust 

reverser if any cracking is found or 

missing fasteners cannot be replaced, 

and contacting the manufacturer to 

report any damage. 

The DGAC mandated the Airbus 

service information and issued French 

airworthiness directives 2003–108(B), 

dated March 19, 2003; and F–2004–020, 

dated February 4, 2004, to ensure the 

continued airworthiness of these 

airplanes in France. 

The parts manufacturer has also 

issued the following service bulletins: 

Service bulletin Revision 

level Date Including 

CFM International CFM56–5C Alert Service Bulletin 78–A0072.2 January 27, 2004 ........... Rohr Alert Service Bulletin RA340A78–72, Revision 2, dated January 27, 2004 

CFM International CFM56–5C Alert Service Bulletin 78–A0073.1 January 27, 2004 ........... Rohr Alert Service Bulletin RA340A78–73, Revision 1, dated January 27, 2004 

Service Bulletin 78–A0072 describes 

procedures for repetitive eddy current 

inspections for cracking of the J-ring 

structure at the 12 o’clock and 6 o’clock 

positions, and corrective action if 

necessary. The corrective action 

procedures specify replacing the thrust 

reverser with a new thrust reverser. 

Service Bulletin 78–A0073 describes 

procedures for modifying the J-ring and 

replacing the 12 o’clock fitting 

(including inspecting machined parts 

for cracks and contacting the 

manufacturer if necessary.) 

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 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Pursuant to this bilateral 

airworthiness agreement, the DGAC has 

kept the FAA informed of the situation 

described above. We have examined the 

DGAC’s findings, evaluated all pertinent 

information, and determined that we 

need to issue an AD for products of this 

type design that are certificated for 

operation in the United States. 

Therefore, we are issuing this AD to 

detect and correct fatigue cracking of the 

J-ring and on the junction between the 

forward frame and the 12 o’clock beam, 

which could result in rupture of the Jring, forward frame, or common fittings, 

inadvertent deployment of a thrust 

reverser in flight and consequent 

reduced controllability of the airplane. 

This AD requires accomplishing the 

actions specified in the service 

information described previously, 

except as discussed under ‘‘Differences 

Among This AD, Service Bulletins, and 

French Airworthiness Directives.’’

Differences Among This AD, Service 

Bulletins, and French Airworthiness 

Directives 

French airworthiness directive 2003–

108(B) specifies certain compliance 

thresholds for the inspection of the 

thrust reversers since new. For certain 

airplanes, this AD would require you to 

perform the inspections at those 

thresholds or within 6 months after the 

effective date of the AD, whichever is 

latest. We have included a 6-month 

grace period to ensure that any airplane 

that is close to or has passed the 

threshold is not grounded as of the 

effective date of the AD. 

If any cracking is found on machined 

parts during the inspections specified in 

CFM International CFM56–5C Alert 

Service Bulletin 78–A0073, and the 

service bulletin specifies contacting 

Airbus or CFM for repair, this AD 

requires repairing those conditions 

using a method that we approve. 

If damage is found on any common 

fitting during the inspections specified 

in Airbus Service Bulletin A340–78–

4028, and the service bulletin specifies 

contacting Airbus for repair, this AD 

requires repairing those conditions 

using a method that we approve. 

Although Airbus Service Bulletin 

A340–78–4028 and CFM International 

CFM56–5C Alert Service Bulletin 78–

A0072, specify reporting the 

replacement of any thrust reverser to 

Airbus or CFM, this AD does not 

include that requirement. 

Clarification of Inspection Terminology 

The French airworthiness directives 

specify a ‘‘visual inspection’’ and an 

‘‘inspection’’ for cracking of the J-ring 

structure at the junction between the 

forward frame and the 12 o’clock and 6 

o’clock beams of the engine thrust 

reversers. We refer to these inspections 

as ‘‘detailed inspections.’’ We have 

included the definition for a detailed 

inspection in a note in the AD. (This 

terminology is consistent with the 

terminology used in the service 

information.) 

Clarification of Optional Replacement 

If a crack is detected at the 12 o’clock 

fitting, the French airworthiness 

directive F–2004–020 includes 

replacing the thrust reverser as one 

option for the corrective action. 

Costs of Compliance 

None of the airplanes affected by this 

action are on the U.S. Register. All 

airplanes affected by this AD are 

currently operated by non-U.S. 

operators under foreign registry; 

therefore, they are not directly affected 

by this AD action. However, we 

consider this AD necessary to ensure 

that the unsafe condition is addressed if 

any affected airplane is imported and 

placed on the U.S. Register in the future. 

If an affected airplane is imported and 

placed on the U.S. Register in the future, 

the required actions would take about 2 

work hours per airplane, at an average 

labor rate of $65 per work hour. Based 

on these figures, the estimated cost of 

the AD would be $130 per airplane, per 

inspection cycle. 

FAA’s Determination of the Effective 

Date 

No airplane affected by this AD is 

currently on the U.S. Register. 

Therefore, providing notice and 

opportunity for public comment is 

unnecessary before this AD is issued, 

Federal Register / Vol. 70, No. 223 / Monday, November 21, 2005 / Rules and Regulations 70037 

and this AD may be made effective in 

less than 30 days after it is published in 

the Federal Register. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

relevant written data, views, or 

arguments regarding this AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2005–23005; Directorate Identifier 

2003–NM–110–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD that might suggest a 

need to modify it. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of that web site, anyone 

can find and read the comments in any 

of our dockets, including the name of 

the individual who sent the comment 

(or signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78), or you may visit 

http://dms.dot.gov. 

Examining the Docket 

You may examine the 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 DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

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 the regulation: 

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. 

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): 

2005–23–21 Airbus: Amendment 39–14379. 

Docket No. FAA–2005–23005; 

Directorate Identifier 2003–NM–110–AD. 

Effective Date 

(a) This AD becomes effective December 6, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Airbus Model 

A340–211, –212, and –213 and A340–311, 

–312, and –313 airplanes, certificated in any 

category. 

Unsafe Condition 

(d) This AD results from fatigue and 

damage tolerance testing of the engine thrust 

reversers which revealed fatigue cracking of 

the junction between the thrust reverser 

forward frame and the 12 o’clock beam, and 

of the thrust reverser J-ring structure. We are 

issuing this AD to detect and correct such 

fatigue cracking, which could result in 

rupture of the J-ring, forward frame, or 

common fittings; loss of the thrust reverser 

system; or inadvertent deployment of a thrust 

reverser in 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. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Repetitive Inspections/Investigative and 

Corrective Actions 

(f) Accomplish detailed and eddy current 

inspections for cracking of the junction 

between the thrust reverser forward frame 

and the 12 o’clock and 6 o’clock beams, and 

the thrust reverser common fittings, and 

related investigative and corrective actions, 

by doing all the actions in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A340–78–4028, Revision 01, 

dated October 23, 2003. Except, if damage is 

found on the common fittings, repair the 

damage using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA. Do the 

inspections at the later of the times specified 

in paragraphs (f)(1) and (f)(2) of this AD. Do 

any related investigative and corrective 

actions before further flight in accordance 

with the service bulletin. Repeat the 

inspections thereafter at intervals not to 

exceed 4,500 flight cycles on the thrust 

reverser. 

(1) For thrust reversers that have 

accumulated fewer than 4,500 total flight 

cycles since new as of the effective date of 

this AD: Before the accumulation of 4,500 

total flight cycles on the thrust reverser since 

new, or within 2,166 flight cycles after the 

effective date of this AD, whichever is later. 

(2) For thrust reversers that have 

accumulated 4,500 or more total flight cycles 

since new as of the effective date of this AD: 

Before the accumulation of 6,666 total flight 

70038 Federal Register / Vol. 70, No. 223 / Monday, November 21, 2005 / Rules and Regulations 

cycles on the thrust reverser since new or 

within 6 months after the effective date of 

this AD, whichever is later. 

Note 2: Airbus Service Bulletin A340–78–

4028, Revision 01, dated October 23, 2003, 

references Rohr Service Bulletin RA34078–

71, Revision 1, dated February 7, 2003, as an 

additional source of service information for 

accomplishing the applicable actions in 

paragraph (f) of this AD. 

(g) At the later of the times specified in 

paragraphs (g)(1) and (g)(2) of this AD: 

Accomplish an eddy current inspection for 

cracking of the J-ring structure at the 12 

o’clock and 6 o’clock positions by doing all 

the applicable actions in accordance with 

CFM International CFM56–5C Alert Service 

Bulletin 78–A0072, Revision 2, dated January 

27, 2004, including Rohr Alert Service 

Bulletin RA340A78–72, Revision 2, dated 

January 27, 2004. If no cracking is found: 

Repeat the inspection thereafter at intervals 

not to exceed 800 flight hours or 175 flight 

cycles on the thrust reverser, whichever is 

first. 

(1) Before the accumulation of 3,000 total 

flight cycles on any thrust reverser since 

new. 

(2) Within 800 flight hours or 175 flight 

cycles after the effective date of this AD, 

whichever is first. 

(h) If any cracking is found at the 12 

o’clock position, before further flight, do the 

actions required by either paragraph (h)(1) or 

(h)(2) of this AD. 

(1) Replace the thrust reverser by doing all 

the applicable actions in accordance with 

CFM International CFM56–5C Alert Service 

Bulletin 78–A0072, Revision 2, dated January 

27, 2004, including Rohr Alert Service 

Bulletin RA340A78–72, Revision 2, dated 

January 27, 2004. 

(2) Modify the J-ring and replace the 12 

o’clock fitting by doing all the applicable 

actions in accordance with CFM 

International CFM56–5C Alert Service 

Bulletin 78–A0073, Revision 1, dated January 

27, 2004, including Rohr Alert Service 

Bulletin RA340A78–73, Revision 1, dated 

January 27, 2004. Except, if any cracking is 

found on machined parts, repair the damage 

using a method approved by the Manager, 

International Branch, ANM–116. Repeat the 

inspection of the 6 o’clock position only at 

the time specified in paragraph (g) of this AD. 

(i) If cracking is found at the 6 o’clock 

position: Before further flight, replace the 

thrust reverser by doing all the applicable 

actions in accordance with CFM 

International CFM56–5C Alert Service 

Bulletin 78–A0072, Revision 2, dated January 

27, 2004, including Rohr Alert Service 

Bulletin RA340A78–72, Revision 2, dated 

January 27, 2004. 

No Reporting Required 

(j) Although Airbus Service Bulletin A340–

78–4028, Revision 01, dated October 23, 

2003; and CFM International CFM56–5C 

Alert Service Bulletin 78–A0072, Revision 2, 

dated January 27, 2004, specify reporting the 

replacement of any thrust reverser to Airbus 

or CFM, this AD does not include that 

requirement. 

Alternative Methods of Compliance 

(AMOCs) 

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

ANM–116, 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 

(l) French airworthiness directives 2003–

108(B), dated March 19, 2003; and F–2004–

020, dated February 4, 2004, also address the 

subject of this AD. 

Material Incorporated by Reference 

(m) You must use Airbus Service Bulletin 

A340–78–4028, Revision 01, excluding 

Appendix 01, dated October 23, 2003; CFM 

International CFM56–5C Alert Service 

Bulletin 78–A0072, Revision 2, dated January 

27, 2004, including Rohr Alert Service 

Bulletin RA340A78–72, Revision 2, dated 

January 27, 2004; and CFM International 

CFM56–5C Alert Service Bulletin 78–A0073, 

Revision 1, dated January 27, 2004, including 

Rohr Alert Service Bulletin RA340A78–73, 

Revision 1, dated January 27, 2004; as 

applicable; 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 these documents 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; or 

Rohr Inc., 850 Lagoon Drive, Chula Vista, 

California 91912, 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 

November 9, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–22789 Filed 11–18–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–23006; Directorate 

Identifier 2002–NM–51–AD; Amendment 39–

14380; AD 2005–23–22] 

RIN 2120–AA64 

Airworthiness Directives; British 

Aerospace Model HS 748 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 

British Aerospace Model HS 748 

airplanes. This AD requires repetitive 

inspections for fatigue cracking, 

corrosion, and other related 

discrepancies of the rear pressure 

bulkhead and associated areas, and the 

fin attachment fittings, particularly the 

fin link beam; and related investigative 

and corrective actions. This AD results 

from a structural integrity audit of the 

airplane that showed the importance of 

inspecting for fatigue cracking and 

corrosion of these areas. We are issuing 

this AD to detect and correct cracking, 

corrosion, and other related 

discrepancies of the rear pressure 

bulkhead and associated areas, and the 

fin attachment fittings, particularly the 

fin link beam, which could result in 

damage to the airplane structure or 

injury to airplane occupants. 

DATES: This AD becomes effective 

December 6, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 6, 2005. 

We must receive comments on this 

AD by January 20, 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,