Federal Register / Vol. 74, No. 138 / Tuesday, July 21, 2009 / Rules and Regulations 35785 

TABLE 1—INCORPORATION BY REFERENCE

Honeywell International Inc. Service Bulletin No. Page Revision Date 

T53–0144, Total Pages: 10 .................................................................................................... ALL ....................... 4 March 31, 2008. 

T53–0144, Appendix, Total Pages: 13 .................................................................................. ALL ....................... C January 25, 2008. 

Issued in Burlington, Massachusetts, on 

July 14, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–17146 Filed 7–20–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0645; Directorate 

Identifier 2009–NM–034–AD; Amendment 

39–15973; AD 2009–15–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–301, –321, –322, –341, and –342 

Series Airplanes, and Airbus Model 

A340–211, –212, –213, –311, –312, and 

–313 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

During accomplishment of A330–300 

Airworthiness Limitation Item (ALI) task 

57.11.04–01–02 of a fastener hole between 

stringer 38 and 39 at FR40 rear fitting web, 

a crack was found on an adjacent hole at 

vertical post Y1959 lower attachment on both 

sides. 

Other crack findings on this adjacent hole 

have been reported on A330–300 and A340– 

200/–300 aircraft as a result of sampling 

inspections. 

If not corrected, crack propagation could 

result in loss of the fuselage structural 

integrity. 

* * * * * 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective 

August 5, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of August 5, 2009. 

We must receive comments on this 

AD by August 20, 2009. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2009–0001, 

dated January 8, 2009 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

During accomplishment of A330–300 

Airworthiness Limitation Item (ALI) task 

57.11.04–01–02 of a fastener hole between 

stringer 38 and 39 at FR40 rear fitting web, 

a crack was found on an adjacent hole at 

vertical post Y1959 lower attachment on both 

sides. 

Other crack findings on this adjacent hole 

have been reported on A330–300 and A340– 

200/–300 aircraft as a result of sampling 

inspections. 

If not corrected, crack propagation could 

result in loss of the fuselage structural 

integrity. 

In order to fulfil[l] the certification 

requirements and following a fatigue analysis 

based on reported findings, a repetitive High 

Frequency Eddy Current (HFEC) Rototest 

inspection on the affected adjacent holes on 

both left hand (LH) and right hand (RH) sides 

between stringer 38 and 39 at FR40 rear 

fitting web is required by this AD and, in 

case of crack finding, the associated 

corrective actions have to be applied. 

The associated corrective actions are 

oversizing the holes and performing an 

additional rototest inspection for 

cracking. If the cracking is within 

certain limits, the corrective action is to 

install oversize fasteners. If the cracking 

exceeds certain limits defined in the 

service bulletin, the corrective action is 

contacting Airbus for repair instructions 

and doing the repair. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A330–57–3107, including 

Appendices 01 and 02, dated October 7, 

2008; and Mandatory Service Bulletin 

A340–57–4117, including Appendices 

01 and 02, dated October 7, 2008. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 


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35786 Federal Register / Vol. 74, No. 138 / Tuesday, July 21, 2009 / Rules and Regulations 

There are no products of this type 

currently registered in the United States. 

However, this rule is necessary to 

ensure that the described unsafe 

condition is addressed if any of these 

products are placed on the U.S. Register 

in the future. 

Differences Between the AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a Note within the AD. 

FAA’s Determination of the Effective 

Date 

Since there are currently no domestic 

operators of this product, notice and 

opportunity for public comment before 

issuing this AD are unnecessary. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2009–0645; 

Directorate Identifier 2009–NM–034– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

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 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 this AD: 

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. 

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 FAA amends § 39.13 by adding 

the following new AD: 

2009–15–10 Airbus: Amendment 39–15973. 

Docket No. FAA–2009–0645; Directorate 

Identifier 2009–NM–034–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 5, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the airplanes 

certificated in any category, identified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) Airbus Model A330–301, –321, –322, 

–341, and –342 series airplanes, all serial 

numbers, except those on which Airbus 

Modification 44360 has been embodied in 

production. 

(2) Airbus Model A340–211, –212, –213, 

–311, –312, and –313 series airplanes, all 

serial numbers, except those on which 

Airbus Modification 44360 has been 

embodied in production. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Reason 

(e) The mandatory continued airworthiness 

information (MCAI) states: 

During accomplishment of A330–300 

Airworthiness Limitation Item (ALI) task 

57.11.04–01–02 of a fastener hole between 

stringer 38 and 39 at FR40 rear fitting web, 

a crack was found on an adjacent hole at 

vertical post Y1959 lower attachment on both 

sides. 

Other crack findings on this adjacent hole 

have been reported on A330–300 and A340– 

200/–300 aircraft as a result of sampling 

inspections. 

If not corrected, crack propagation could 

result in loss of the fuselage structural 

integrity. 

In order to fulfil[l] the certification 

requirements and following a fatigue analysis 

based on reported findings, a repetitive High 

Frequency Eddy Current (HFEC) Rototest 

inspection on the affected adjacent holes on 

both left hand (LH) and right hand (RH) sides 

between stringer 38 and 39 at (frame) FR40 

rear fitting web is required by this AD and, 

in case of crack finding, the associated 

corrective actions have to be applied. 

* * * * * 

The associated corrective actions are 

oversizing the holes and performing an 

additional rototest inspection for cracking. If 

the cracking is within certain limits, the 

corrective action is to install oversize 

fasteners. If the cracking exceeds certain 

limits defined in the service bulletin, the 

corrective action is contacting Airbus for 

repair instructions and doing the repair. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within the applicable time as specified 

in Table 1 of this AD, or within 90 days after 

the effective date of this AD, whichever 

occurs later: Perform a HFEC inspection by 

rototest for cracking of two holes on the left 

and right sides of the fuselage structure FR40 

rear fitting, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–57–3107, 


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Federal Register / Vol. 74, No. 138 / Tuesday, July 21, 2009 / Rules and Regulations 35787 

dated October 7, 2008; or Airbus Mandatory 

Service Bulletin A340–57–4117, dated 

October 7, 2008; as applicable. Do the 

associated corrective actions, before further 

flight, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–57–3107, 

dated October 7, 2008; or Airbus Mandatory 

Service Bulletin A340–57–4117, dated 

October 7, 2008; as applicable. 

TABLE 1—COMPLIANCE TIMES

Model Threshold from the first flight 

(whichever occurs first) 

A330–300 series airplanes .................................................................................................. 17,700 total flight cycles or 53,100 total flight hours. 

A340–200 series airplanes with modification 41652S11888 .............................................. 11,900 total flight cycles or 80,700 total flight hours. 

A340–300 series airplanes with modification 41652S11888 .............................................. 11,900 total flight cycles or 80,700 total flight hours. 

A340–200 series airplanes without modification 41652S11888 ......................................... 14,500 total flight cycles or 98,200 total flight hours. 

A340–300 series airplanes without modification 41652S11888 ......................................... 12,700 total flight cycles or 85,900 total flight hours. 

(2) Repeat the inspection required by 

paragraph (f)(1) of this AD within the 

applicable intervals as specified in Table 2 of 

this AD, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–57–3107, 

dated October 7, 2008; or Airbus Mandatory 

Service Bulletin A340–57–4117, dated 

October 7, 2008; as applicable. 

TABLE 2—REPETITIVE INSPECTION INTERVALS

Model Intervals (not to exceed) 

A330–300 series airplanes ........................................................................................................... 12,800 flight cycles or 38,500 flight hours, whichever occurs first. 

A340–200 series airplanes with modification 41652S11888 ....................................................... 8,600 flight cycles or 58,500 flight hours, whichever occurs first. 

A340–300 series airplanes with modification 41652S11888 ....................................................... 8,600 flight cycles or 58,500 flight hours, whichever occurs first. 

A340–200 series airplanes without modification 41652S11888 .................................................. 10,500 flight cycles or 71,200 flight hours, whichever occurs first. 

A340–300 series airplanes without modification 41652S11888 .................................................. 9,200 flight cycles or 62,300 flight hours, whichever occurs first. 

(3) Where Airbus Mandatory Service 

Bulletin A330–57–3107, dated October 7, 

2008; and Airbus Mandatory Service Bulletin 

A340–57–4117, dated October 7, 2008; 

recommend contacting Airbus for 

appropriate action: Before further flight, 

contact Airbus for repair instructions and do 

the repair. 

(4) Accomplishment of the inspections 

required by paragraph (f)(1) of this AD before 

the effective date of this AD in accordance 

with the instructions of Airbus Technical 

Disposition LR5710D07014394, Issue B, 

dated September 24, 2008, is acceptable for 

compliance with the requirements of 

paragraph (f)(1) of this AD. However, 

inspections must be repeated thereafter in 

accordance with the requirements of 

paragraph (f)(2) of this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Vladimir 

Ulyanov, Aerospace Engineer, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

The AMOC approval letter must specifically 

reference this AD. 

(2) Airworthy Product: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer or other source, 

use these actions if they are FAA-approved. 

Corrective actions are considered FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2009– 

0001, dated January 8, 2009; Airbus 

Mandatory Service Bulletin A330–57–3107, 

dated October 7, 2008; and Airbus Mandatory 

Service Bulletin A340–57–4117, dated 

October 7, 2008; for related information. 

Material Incorporated by Reference 

(i) You must use Airbus Mandatory Service 

Bulletin A330–57–3107, including 

Appendices 01 and 02, dated October 7, 

2008; or Airbus Mandatory Service Bulletin 

A340–57–4117, including Appendices 01 

and 02, dated October 7, 2008, as applicable, 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80, e-mail 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 


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35788 Federal Register / Vol. 74, No. 138 / Tuesday, July 21, 2009 / Rules and Regulations 

Issued in Renton, Washington, on July 2, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–16924 Filed 7–20–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0645; Directorate 

Identifier 2007–NM–358–AD; Amendment 

39–15969; AD 2009–15–06] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 707 Airplanes and Model 720 

and 720B 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 all 

Boeing Model 707 airplanes and Model 

720 and 720B series airplanes. This AD 

requires performing an operational test 

of the engine fuel suction feed of the 

fuel system, and other related testing 

and corrective actions if necessary. This 

AD results from a report of in-service 

occurrences of loss of fuel system 

suction feed capability, followed by 

total loss of pressure of the fuel feed 

system. We are issuing this AD to detect 

and correct failure of the engine fuel 

suction feed capability of the fuel 

system, which could result in multiengine flameout, inability to restart the 

engines, and consequent forced landing 

of the airplane. 

DATES: This AD becomes effective 

August 25, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of August 25, 2009. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1, fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Sue 

Lucier, Aerospace Engineer, Propulsion 

Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6438; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a supplemental 

notice of proposed rulemaking (NPRM) 

to amend 14 CFR part 39 to include an 

AD that would apply to all Boeing 

Model 707 airplanes and Model 720 and 

720B series airplanes. That 

supplemental NPRM was published in 

the Federal Register on December 10, 

2008 (73 FR 75007). That supplemental 

NPRM proposed to require performing 

an operational test of the engine fuel 

suction feed of the fuel system, and 

other related testing and corrective 

actions if necessary. 

Explanation of Revised Service 

Information 

Boeing has published Revision 1 of 

Boeing 707 Service Bulletin A3527, 

dated August 6, 2008. In the 

supplemental NPRM, we referred to the 

original issue of Boeing Alert 707 

Service Bulletin A3527, dated 

November 7, 2007, as the appropriate 

source of service information for 

accomplishing the proposed actions. 

The procedures in Revision 1 of this 

service bulletin are essentially the same 

as those in the original issue of this 

service bulletin. Revision 1 of this 

service bulletin clarifies certain work 

instructions and specifies that no 

further work is necessary for airplanes 

on which the actions in the original 

issue were performed. Therefore, we 

have revised this AD to refer to Revision 

1 of this service bulletin as the 

appropriate source of service 

information. We have also added a new 

paragraph (g) to this AD that specifies 

that actions done before the effective 

date of this AD in accordance with the 

original issue of this service bulletin are 

acceptable for compliance with the 

requirements of this AD. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment received. 

Boeing concurs with the content of the 

supplemental NPRM. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

received, and determined that air safety 

and the public interest require adopting 

the AD with the change described 

previously. We have determined that 

this change will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

We estimate that this AD affects 21 

airplanes of U.S. registry. We also 

estimate that it takes 1 work-hour per 

product, per test, to comply with this 

AD. The average labor rate is $80 per 

work-hour. Based on these figures, we 

estimate the cost of this AD to the U.S. 

operators to be $1,680, or $80 per 

product, per test. 

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; 


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