Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations 59229 

date from ‘‘19’’ to be ‘‘20’’ every place 

it is mentioned. 

Dated: September 16, 2005. 

Russell T. Davis, 

Administrator, Rural Housing Service. 

[FR Doc. 05–20357 Filed 10–11–05; 8:45 am] 

BILLING CODE 3410–XV–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22626; Directorate 

Identifier 2002–NM–295–AD; Amendment 

39–14332; AD 2005–20–35] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A320–111 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Airbus Model 

A320–111 airplanes. The existing AD 

currently requires repetitive inspections 

for cracking in the front and rear faces 

and at the crown fittings of the upper 

stringers of the center wing box and 

applicable repairs. This new AD 

requires continuing the repetitive 

inspections at revised thresholds and 

intervals, and applicable repairs. This 

AD results from a manufacturer survey 

of airplanes affected by the existing 

inspection program that led to the 

consequent revision of the thresholds 

and intervals of the repetitive 

inspections. We are issuing this AD to 

detect and correct fatigue cracking of the 

upper stringers of the center wing box, 

which could lead to loss of structural 

integrity of the wing. 

DATES: Effective October 27, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 27, 2005. 

We must receive comments on this 

AD by December 12, 2005. 

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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2125; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On October 13, 1993, the FAA issued 

AD 93–16–10, amendment 39–8667 (58 

FR 47825, September 13, 1993). That 

AD applies to certain Airbus Model 

A320 airplanes. That AD requires 

repetitive inspections for cracking in the 

front and rear faces and at the crown 

fittings of the upper stringers of the 

center wing box and applicable repairs, 

if necessary. We issued that AD to 

detect fatigue cracking in the upper 

stringer, which could lead to loss of 

structural integrity. 

Actions Since Existing AD Was Issued 

Since we issued AD 93–16–10, Airbus 

conducted a survey of the upper 

stringers of the center wing boxes of 

airplanes affected by the existing 

inspection program. The results of the 

survey demonstrated that it was 

necessary to decrease the thresholds and 

intervals of the repetitive inspections, 

due to an adjustment of the A320 family 

reference fatigue mission. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–57–1030, Revision 03, dated 

August 28, 2002. The service bulletin 

describes procedures for performing 

repetitive inspections—at thresholds 

and intervals which have been revised 

from those specified in Service Bulletin 

A320–57–1030, dated August 12, 1991, 

which is the service information 

referenced in AD 93–16–10—for 

cracking in the front and rear faces and 

at the crown fittings of the upper 

stringers of the center wing box between 

frame (FR) 36 and FR42. The Direction 

Ge ́ne ́rale de l’Aviation Civile (DGAC), 

which is the airworthiness authority for 

France, mandated the service 

information and issued French 

airworthiness directive 2002–341(B), 

dated June 26, 2002, to ensure the 

continued airworthiness of these 

airplanes in France. 

FAA’s Determination and Requirements 

of This AD 

This airplane model is manufactured 

in France and is 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 

supersede AD 93–16–10. This new AD 

continues to require repetitive 

inspections with revised inspection 

thresholds and intervals, applicable 

repairs; as specified in the service 

information described previously, 

except as discussed under ‘‘Differences 

Between the AD and Service 

Information.’’

Differences Between the AD and 

Service Information 

Where the service bulletin describes 

procedures to contact the manufacturer 

for repair methods, this AD requires 

operators to use a repair method that we 

or the DGAC (or its delegated agent) 

approve. 

Clarification of Inspection Terminology 

In this AD, the ‘‘detailed visual 

inspection’’ specified in the service 

bulletin is referred to as a ‘‘detailed 

inspection.’’ We have included the 

definition for a detailed inspection in 

Note 1 of this AD. 

Explanation of Change to Applicability 

We have revised the applicability of 

the existing AD to identify model 

designations as published in the most 

recent type certificate data sheet for the 

affected models. 

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 

59230 Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations 

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 inspection 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, 

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 the address listed under 

the ADDRESSES section. Include ‘‘Docket 

No. FAA–2005–22626; Directorate 

Identifier 2002–NM–295–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 removing amendment 39–8667 (58 

FR 47825, September 13, 1993) and by 

adding the following new airworthiness 

directive (AD): 

2005–20–35 Airbus: Amendment 39–14332. 

Docket No. FAA–2005–22626; 

Directorate Identifier 2002–NM–295–AD. 

Effective Date 

(a) This AD becomes effective October 27, 

2005. 

Affected ADs 

(b) This AD supersedes AD 93–16–10. 

Applicability 

(c) This AD applies to Airbus Model A320–

111 airplanes, certificated in any category, 

having manufacturer serial number 002 

through 021 inclusive. 

Unsafe Condition 

(d) This AD results from a manufacturer 

survey of airplanes affected by the inspection 

program required by AD 93–16–10 and the 

consequent revision of the thresholds and 

intervals of the repetitive inspections. We are 

issuing this AD to detect and correct fatigue 

cracking of the upper stringers of the center 

wing box, which could lead to loss of 

structural integrity of the wing. 

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. 

Initial Inspection 

(f) Prior to the accumulation of 6,500 total 

flight cycles or within 50 flight cycles after 

the effective date of this AD, whichever 

occurs later, except as provided by paragraph 

(g) of this AD, perform a detailed inspection 

for cracking in the front and rear faces and 

at the crown fittings of the upper stringers of 

the center wing box between frame (FR) 36 

and FR42, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1030, Revision 03, 

dated August 28, 2002. 

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.’’

(1) If no crack is found, repeat the 

inspection thereafter at intervals not to 

Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations 59231 

exceed 5,500 flight cycles, in accordance 

with the service bulletin. 

(2) If any crack is found, prior to further 

flight, repair in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the Direction Ge ́ne ́rale 

de l’Aviation Civile (DGAC) or its delegated 

agent. 

Previous Initial Inspection 

(g) Airplanes that received an initial 

inspection prior to the effective date of this 

AD using any service information specified 

in paragraph (h) of this AD must receive the 

next inspection within 2,000 flight cycles 

after the effective date of this AD or 7,500 

flight cycles since the last inspection, 

whichever occurs first; in accordance with 

paragraph (f) of this AD. 

Previous Revisions of Service Bulletins 

(h) Actions accomplished before the 

effective date of this AD in accordance with 

Airbus Service Bulletin A320–57–1030, 

dated August 12, 1991; Revision 1, dated 

September 16, 1996; or Revision 02, dated 

February 20, 1998; are considered acceptable 

for compliance with the corresponding 

actions specified in paragraph (f) of this AD, 

except as provided by paragraph (g) of this 

AD. 

No Reporting Requirement 

(i) Although Airbus Service Bulletin A320–

57–1030, Revision 03, dated August 28, 2002, 

describes procedures for reporting inspection 

findings to Airbus, this AD does not require 

such a report. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(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 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. 

(3) AMOCs approved previously according 

to AD 93–16–10 are not approved as AMOCs 

for this AD. 

Related Information 

(k) French airworthiness directive 2002–

341(B), dated June 26, 2002, also addresses 

the subject of this AD. 

Material Incorporated by Reference 

(l) You must use Airbus Service Bulletin 

A320–57–1030, Revision 03, dated August 

28, 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 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 28, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–20069 Filed 10–11–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22625; Directorate 

Identifier 2003–NM–213–AD; Amendment 

39–14331; AD 2005–20–34] 

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 certain 

British Aerospace Model HS 748 

airplanes. This AD requires relocating 

the battery earth posts located on the 

nose landing gear (NLG) pintle webs. 

This AD results from an accident in 

which the nose landing leg, together 

with the pintle webs, detached from the 

airplane. As a result, the battery earth 

return cables were severed from their 

earth posts. We are issuing this AD to 

prevent loss of safety critical services 

including fuel shut-off and nacelle fire 

extinguishing services. 

DATES: This AD becomes effective 

October 27, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 27, 2005. 

We must receive comments on this 

AD by December 12, 2005. 

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 British Aerospace Regional 

Aircraft American Support, 13850 

Mclearen Road, Herndon, Virginia 

20171, for service information identified 

in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1175; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The Civil Aviation Authority (CAA), 

which is the airworthiness authority for 

the United Kingdom, notified us that an 

unsafe condition may exist on certain 

British Aerospace Model HS 748 

airplanes. The CAA advises that, in an 

accident involving a Model HS 748 

airplane, the nose landing leg, together 

with the pintle webs, detached from the 

airplane. As a result, the battery earth 

return cables were severed from their 

earth posts. This condition, if not 

corrected, could result in the loss of 

safety critical services including fuel 

shut-off and nacelle fire extinguishing 

services. 

Relevant Service Information 

BAE Systems (Operations) Limited 

has issued Service Bulletin HS748–24–

131, Revision 1, dated June 16, 2003. 

The service bulletin describes 

procedures for relocating the battery 

earth posts. The tasks comprise: 

• Assembling a new earth post 

mounting plate; 

• Fitting the mounting plate on the 

side beams of the nose landing gear 

(NLG) below the cockpit floor; 

• Testing the bonding on the new 

earth post plate installation; 

• Rerouting the battery earth return 

cables; 

• Connecting the cables to the earth 

posts at their new location; and 

• Connecting the aircraft batteries. 

Accomplishing the actions specified 

in the service information is intended to 

adequately address the unsafe 

condition. The CAA mandated the 

service information and issued British