57732 Federal Register / Vol. 70, No. 191 / Tuesday, October 4, 2005 / Rules and Regulations 

strength components from the table are 

to be demonstrated. 

Frequency 

Field strength 

(volts per meter) 

Peak Average 

10 kHz–100 kHz ........... 50 50 

100 kHz–500 kHz ......... 50 50 

500 kHz–2 MHz ............ 50 50 

2 MHz–30 MHz ............. 100 100 

30 MHz–70 MHz ........... 50 50 

70 MHz–100 MHz ......... 50 50 

100 MHz–200 MHz ....... 100 100 

200 MHz–400 MHz ....... 100 100 

400 MHz–700 MHz ....... 700 50 

700 MHz–1 GHz ........... 700 100 

1 GHz–2 GHz ............... 2000 200 

2 GHz–4 GHz ............... 3000 200 

4 GHz–6 GHz ............... 3000 200 

6 GHz–8 GHz ............... 1000 200 

8 GHz–12 GHz ............. 3000 300 

12 GHz–18 GHz ........... 2000 200 

18 GHz–40 GHz ........... 600 200 

The field strengths are expressed in terms 

of peak of the root-mean-square (rms) over 

the complete modulation period. 

The threat levels identified above are 

the result of an FAA review of existing 

studies on the subject of HIRF, in light 

of the ongoing work of the 

Electromagnetic Effects Harmonization 

Working Group of the Aviation 

Rulemaking Advisory Committee. 

Applicability 

As discussed above, these special 

conditions are applicable to DassaultAviation Mystere-Falcon 50 airplanes 

modified by Premier Air Center. Should 

Premier Air Center apply at a later date 

for a STC to modify any other model 

included on Type Certificate No. A46EU 

to incorporate the same or similar novel 

or unusual design feature, these special 

conditions would apply to that model as 

well under the provisions of § 21.101. 

Conclusion 

This action affects only certain novel 

or unusual design features on DassaultAviation Mystere-Falcon 50 airplanes 

modified by Premier Air Center. It is not 

a rule of general applicability and 

affects only the applicant who applied 

to the FAA for approval of these features 

on the airplane. 

The substance of these special 

conditions has been subjected to the 

notice and comment procedure in 

several prior instances and has been 

derived without substantive change 

from those previously issued. Because a 

delay would significantly affect the 

certification of the airplane, which is 

imminent, the FAA has determined that 

prior public notice and comment are 

unnecessary and impracticable, and 

good cause exists for adopting these 

special conditions upon issuance. The 

FAA is requesting comments to allow 

interested persons to submit views that 

may not have been submitted in 

response to the prior opportunities for 

comment described above. 

List of Subjects in 14 CFR Part 25 

Aircraft, Aviation safety, Reporting 

and recordkeeping requirements. 

The authority citation for these 

special conditions is as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701, 

44702, 44704. 

The Special Conditions 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the following special 

conditions are issued as part of the 

supplemental type certification basis for 

the Dassault-Aviation Mystere-Falcon 

50 airplanes modified by Premier Air 

Center. 

1. Protection from Unwanted Effects 

of HIRF. Each electrical and electronic 

system that performs critical functions 

must be designed and installed to 

ensure that the operation and 

operational capability of these systems 

to perform critical functions are not 

adversely affected when the airplane is 

exposed to high-intensity radiated 

fields. 

2. For the purpose of these special 

conditions, the following definition 

applies: Critical Functions: Functions 

whose failure would contribute to or 

cause a failure condition that would 

prevent the continued safe flight and 

landing of the airplane. 

Issued in Renton, Washington. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19860 Filed 10–3–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22539; Directorate 

Identifier 2004–NM–08–AD; Amendment 39–

14300; AD 2005–20–07] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for certain 

Airbus Model A330–300 series 

airplanes. This AD requires reinforcing 

the structure of the center fuselage by 

installing external stiffeners (butt straps) 

at frame (FR) 53.3 on the fuselage skin 

between left-hand and right-hand 

stringer 13, and related investigative 

actions. This AD results from a report 

that, during fatigue tests of the fuselage, 

cracks initiated and grew at the 

circumferential joint of FR53.3. We are 

issuing this AD to prevent fatigue 

cracking of the fuselage, which could 

result in reduced structural integrity of 

the fuselage. 

DATES: Effective October 19, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 19, 2005. 

We must receive comments on this 

AD by December 5, 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: Tim 

Backman, Aerospace Engineer, ANM–

116, International Branch, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

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

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Although this is a final rule that was 

not preceded by notice and an 

opportunity for public comment, we 

invite you to submit any relevant 

written data, views, or arguments 

regarding this AD. Include ‘‘Docket No. 

FAA–2005–22539; Directorate Identifier 

2004–NM–08–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

Federal Register / Vol. 70, No. 191 / Tuesday, October 4, 2005 / Rules and Regulations 57733 

aspects of the AD. We will consider all 

comments received by the closing date 

and may amend the AD in light of those 

comments. 

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. 

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 certain Airbus Model A330–300 

series airplanes. The DGAC advises that, 

during fatigue tests of the fuselage, 

cracks initiated and grew at the 

circumferential joint of frame (FR) 53.3. 

This condition, if not corrected, could 

result in reduced structural integrity of 

the fuselage. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A330–53–3127, including Appendix 01, 

Revision 01, dated November 21, 2003. 

The service bulletin describes 

procedures for reinforcing the structure 

of the center fuselage by installing 

external doublers (butt straps) at FR53.3 

on the fuselage skin between left- and 

right-hand stringer 13. The installation 

of the three butt straps includes 

removing fasteners and doing the 

related investigative action of 

rototesting the holes where the fasteners 

were removed. If a crack is found during 

a rototest, the service bulletin specifies 

contacting Airbus for repair 

instructions. If no crack is found, the 

installation includes counter-drilling 

the fastener holes in the butt straps, 

cold-expanding the matching holes in 

the fuselage, reaming and deburring the 

holes, shimming, and applying sealant 

around the butt straps. Accomplishing 

the actions specified in the service 

information is intended to adequately 

address the unsafe condition. The 

DGAC mandated the service information 

and issued French airworthiness 

directive F–2003–415, dated November 

12, 2003, 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 

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 

prevent fatigue cracking of the fuselage, 

which could result in reduced structural 

integrity of the fuselage. This AD 

requires accomplishing the actions 

specified in the service information 

described previously. 

Difference Between the Proposed AD 

and the French Airworthiness Directive 

The applicability of French 

airworthiness directive F–2003–415, 

dated November 12, 2003, excludes 

airplanes on which Airbus Service 

Bulletin A330–53–3127, Revision 01, 

has been accomplished in service. 

However, we have not excluded those 

airplanes in the applicability of this 

proposed AD; rather, this proposed AD 

includes a requirement to accomplish 

the actions specified in that service 

bulletin. This requirement would ensure 

that the actions specified in the service 

bulletin and required by this proposed 

AD are accomplished on all affected 

airplanes. Operators must continue to 

operate the airplane in the configuration 

required by this proposed AD unless an 

alternative method of compliance is 

approved. 

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. 

The following table provides the 

estimated costs to comply with this AD 

for any affected airplane that might be 

imported and placed on the U.S. 

Register in the future. 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Parts cost Cost per airplane 

Installation ........................................................................................................ 172 $65 $8,920 $20,100 

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. 

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 

57734 Federal Register / Vol. 70, No. 191 / Tuesday, October 4, 2005 / Rules and Regulations 

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): 

2005–20–07 Airbus: Amendment 39–14300. 

Docket No. FAA–2005–22539; 

Directorate Identifier 2004–NM–08–AD. 

Effective Date 

(a) This AD becomes effective October 19, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model A330–301, 

–321, –322, –323, –341, –342, and –343 series 

airplanes, certificated in any category, except 

those on which Airbus Modification 41652 

has been accomplished in production. 

Unsafe Condition 

(d) This AD results from a report that, 

during fatigue tests of the fuselage, cracks 

initiated and grew at the circumferential joint 

of frame (FR) 53.3. We are issuing this AD 

to prevent fatigue cracking of the fuselage, 

which could result in reduced structural 

integrity of the fuselage. 

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. 

Installation 

(f) At the later of the times in paragraphs 

(f)(1) and (f)(2) of this AD: Install the butt 

straps at FR53.3 on the fuselage skin between 

left- and right-hand stringer 13, and do all 

related investigative and corrective actions 

before further flight. Except as provided by 

paragraph (g) of this AD, do all actions in 

accordance with Airbus Service Bulletin 

A330–53–3127, Revision 01, dated November 

21, 2003. 

(1) Before the accumulation of 14,700 total 

flight cycles or 51,400 total flight hours, 

whichever occurs earlier. 

(2) Within 6 months after the effective date 

of this AD. 

Contact the FAA/Direction Ge ́ne ́rale de 

l’Aviation Civile (DGAC) for Certain Repair 

Instructions 

(g) If any crack is detected during the 

related investigative actions (rototest) 

required by paragraph (f) of this AD: Before 

further flight, repair the crack according to a 

method approved by either the Manager, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate; or the DGAC 

(or its delegated agent). 

Alternative Methods of Compliance 

(AMOCs) 

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

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(i) French airworthiness directive F–2003–

415, dated November 12, 2003, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(j) You must use Airbus Service Bulletin 

A330–53–3127, Revision 01, dated November 

21, 2003, 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 20, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19333 Filed 10–3–05; 8:45 am] 

BILLING CODE 4910–13–U 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22563; Directorate 

Identifier 2004–NM–177–AD; Amendment 

39–14304; AD 2005–20–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–243, –341, –342, and –343 

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 A330–243, –341, –342, 

and –343 airplanes. This AD requires 

revising the airplane flight manual to 

provide the flightcrew with new, ground 

ice-shedding procedures during long 

taxi periods in certain icing conditions. 

This AD results from reports of engine 

damage to the blades of the first stage of 

the intermediate pressure compressor 

due to ice accumulation. We are issuing 

this AD to prevent engine damage due 

to ice accumulation, which could result 

in an engine shutdown and cause the 

flightcrew to divert to the nearest 

available airport. 

DATES: This AD becomes effective 

October 19, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 19, 2005.