1332 Federal Register / Vol. 70, No. 5 / Friday, January 7, 2005 / Rules and Regulations 

Nassif Building, Room PL–401, Washington, 

DC 20590–001 or on the Internet at http://

dms.dot.gov. The docket number is FAA–

2004–19221.

Issued in Kansas City, Missouri, on 

December 28, 2004. 

David A. Downey, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 05–185 Filed 1–6–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–18597; Directorate 

Identifier 2004–CE–21–AD; Amendment 39–

13934; AD 2005–01–10] 

RIN 2120–AA64 

Airworthiness Directives; The New 

Piper Aircraft, Inc. Models PA–23–235, 

PA–23–250, and PA–E23–250 Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) that 

supersedes Airworthiness Directive 

(AD) 74–06–01, which applies to certain 

The New Piper Aircraft, Inc. (Piper) 

Models PA–23–235, PA–23–250, and 

PA–E23–250 airplanes equipped with 

Garrett Aviation Services (Garrett) 

(formerly AiResearch) 

turbosuperchargers installed under 

supplemental type certificate (STC) 

SA852WE, SA909WE, or SA978WE; or 

installed under Piper Aircraft Drawing 

Number 32016. AD 74–06–01 currently 

requires you to replace 

turbosupercharger oil tanks, install fire 

shrouds, seal all openings in the fire 

shrouds, and add drainage provisions in 

the oil tank fairings for airplane serial 

numbers 27–1 through 27–2504; and 

add drainage provisions in the air 

scoops on serial numbers 27–2505 and 

higher. This AD requires you to replace 

the oil reservoir and related hoses with 

a fireproof oil tank and fire-shielded 

hoses. This AD results from a report of 

a fatal accident related to the breakdown 

of the turbocharger oil reservoir 

following a fire in the engine nacelle. 

We are issuing this AD to prevent 

turbosupercharger oil reservoirs with 

inadequate fire resistance from failing 

when exposed to flame or exhaust gases. 

This failure could lead to an in-flight 

fire within the nacelle area penetrating 

the firewall and subsequent failure of 

the wing spar.

DATES: This AD becomes effective on 

February 22, 2005. 

As of February 22, 2005, the Director 

of the Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulation.

ADDRESSES: You may get the service 

information identified in this AD from:

—For any installation under 

supplemental type certificate (STC) 

SA852WE, SA909WE, or SA978WE:

The Nordam Group, Nacelle/Thrust 

Reverser Division, 6911 N. Whirlpool 

Drive, Tulsa, OK 74117; telephone: 

(918) 878–4000; facsimile: (918) 878–

4808; and 

—For any installation under Piper 

Aircraft Drawing Number 32016: The 

New Piper Aircraft, Inc., 2926 Piper 

Drive, Vero Beach, Florida, 32960; 

and The Nordam Group, Nacelle/

Thrust Reverser Division, 6911 N. 

Whirlpool Drive, Tulsa, OK 74117; 

telephone: (918) 878–4000; facsimile: 

(918) 878–4808.

To review this service information, go 

to the National Archives and Records 

Administration (NARA). For 

information on the availability of this 

material at NARA, go to: http://

www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html or call (202) 741–

6030. 

To view the AD docket, go to the 

Docket Management Facility; U.S. 

Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

001 or on the Internet at http://

dms.dot.gov. The docket number is 

FAA–2004–18597.

FOR FURTHER INFORMATION CONTACT:

Roger Pesuit, Aerospace Engineer, FAA, 

Los Angeles Aircraft Certification 

Office, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; telephone: 

(562) 627–5251; facsimile: (562) 627–

5210.

SUPPLEMENTARY INFORMATION: 

Discussion 

What events have caused this AD?

The need to minimize fire hazards in 

the engine compartment on The New 

Piper Aircraft, Inc. (Piper) Models PA–

23–235, PA–23–250, and PA–E23–250 

airplanes equipped with AiResearch 

turbosuperchargers installed under 

supplemental type certificate (STC) 

SA852WE, SA909WE, or SA978WE; or 

installed under Piper Aircraft Drawing 

32016 caused FAA to issue AD 74–06–

01, Amendment 39–1977. AD 74–06–01 

currently requires the following on any 

Piper Models PA–23–235, PA–23–250, 

and PA–E23–250 airplanes equipped 

with AiResearch turbosuperchargers 

installed under STC SA852WE, 

SA909WE, or SA978WE; or installed 

under Piper Aircraft Drawing Number 

32016:

—Replacing the existing 

turbosupercharger oil tanks; 

—installing fire shrouds; 

—sealing all openings in the fire 

shrouds; 

—(for airplane serial numbers 27–1 

through 27–2504) adding drainage 

provisions in the oil tank fairings; and 

—(for airplane serial numbers 27–2505 

and higher) adding drainage 

provisions in the air scoops.

What has happened since AD 74–06–

01 to initiate this action? The FAA has 

received a report of a fatal accident 

related to the breakdown of the 

turbosupercharger oil reservoir. A Piper 

Model PA 23–250 airplane equipped 

with the STC turbocharger installation 

was involved in a fatal accident. The 

accident investigation revealed a 

breakdown of the turbosupercharger oil 

reservoir. Examination of the aircraft 

wreckage revealed evidence of an inflight fire where the turbosupercharger 

oil reservoir was burned to include the 

rear firewall portion of the reservoir 

allowing fire to move aft, softening the 

wing spar. 

What is the potential impact if FAA 

took no action? Failure of the 

turbosupercharger oil reservoir when 

exposed to flame or exhaust gases could 

lead to an in-flight fire and failure of the 

wing spar. 

Has FAA taken any action to this 

point? We issued a proposal to amend 

part 39 of the Federal Aviation 

Regulations (14 CFR part 39) to include 

an AD that would apply to certain Piper 

Models PA–23–235, PA–23–250, and 

PA–E23–250 airplanes equipped with 

Garrett Aviation Services (Garrett) 

(formerly AiResearch) 

turbosuperchargers installed under STC 

SA852WE, SA909WE, or SA978WE; or 

installed under Piper Aircraft Drawing 

Number 32016. This proposal was 

published in the Federal Register as a 

notice of proposed rulemaking (NPRM) 

on September 22, 2004 (69 FR 56733). 

The NPRM proposed to supersede AD 

74–06–01, which applies to certain 

Piper Models PA–23–235, PA–23–250, 

and PA–E23–250 airplanes equipped 

with Garrett Aviation Services (Garrett) 

(formerly AiResearch) 

turbosuperchargers installed under STC 

SA852WE, SA909WE, or SA978WE; or 

installed under Piper Aircraft Drawing 

Number 32016. AD 74–06–01 currently 

requires you to replace 

turbosupercharger oil tanks, install fire 

shrouds, seal all openings in the fire 

shrouds, and add drainage provisions in 

Federal Register / Vol. 70, No. 5 / Friday, January 7, 2005 / Rules and Regulations 1333

the oil tank fairings for airplane serial 

numbers 27–1 through 27–2504; and the 

NPRM proposed to require you to add 

drainage provisions in the air scoops on 

serial numbers 27–2505 and higher. 

Comments 

Was the public invited to comment?

We provided the public the opportunity 

to participate in developing this AD. 

The following presents the comment 

received on the proposal and FAA’s 

response to the comment: 

Comment Issue: Require Installation of 

FAA-Approved Parts Manufacturer 

Approval (PMA) Parts 

What is the commenter’s concern?

The commenter recommends that FAA 

revise the AD to require installation of 

FAA-approved PMA parts. Further, the 

commenter writes that the proposed AD 

requires replacement of parts installed 

under an STC. The parts proposed to be 

installed have not been approved under 

14 CFR 21.303(a). Therefore, the 

commenter states that the parts are not 

eligible for installation. 

What is FAA’s response to the 

concern? The FAA concurs that the AD 

should require the installation of PMA 

parts. However, incorporating the 

service bulletin, either standard parts or 

PMA parts are required. Therefore, we 

do not feel that a rewrite of the AD is 

necessary. Note that the first two sets of 

parts shipped omitted the PMA 

identification. The recipients of these 

were notified and arrangements made to 

exchange these parts for those having 

appropriate PMA identification. All 

subsequent shipments contain the 

required PMA identification. 

We are not changing the final rule AD 

action based on these comments. 

Conclusion 

What is FAA’s final determination on 

this issue? We have carefully reviewed 

the available data and determined that 

air safety and the public interest require 

adopting the AD as proposed except for 

the changes discussed above and minor 

editorial corrections. We have 

determined that these changes and 

minor corrections:

—Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

—do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Docket Information 

Where can I go to view the docket 

information? You may view the AD 

docket that contains information 

relating to this subject in person at the 

DMS Docket Offices between 9 a.m. and 

5 p.m. (eastern standard time), Monday 

through Friday, except Federal holidays. 

The Docket Office (telephone 1–800–

647–5227) is located on the plaza level 

of the Department of Transportation 

NASSIF Building at the street address 

stated in ADDRESSES. You may also view 

the AD docket on the Internet at

http://dms.dot.gov.

Changes to 14 CFR Part 39—Effect on 

the AD 

How does the revision to 14 CFR part 

39 affect this AD? On July 10, 2002, the 

FAA published a new version of 14 CFR 

part 39 (67 FR 47997, July 22, 2002), 

which governs the FAA’s AD system. 

This regulation now includes material 

that relates to altered products, special 

flight permits, and alternative methods 

of compliance. This material previously 

was included in each individual AD. 

Since this material is included in 14 

CFR part 39, we will not include it in 

future AD actions. 

Costs of Compliance 

How many airplanes does this AD 

impact? We estimate that this AD affects 

250 airplanes in the U.S. registry. 

What is the cost impact of this AD on 

owners/operators of the affected 

airplanes? We estimate the following 

costs to do the modification:

Labor cost Parts cost Total cost per 

airplane 

Total cost on 

U.S. operators 

14 workhours × $65 per hour = $910 .......................................................................................... $2,500 $3,410 $852,500 

Authority for This Rulemaking 

What authority does FAA have for 

issuing this rulemaking action? 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 AD. 

Regulatory Findings 

Will this AD impact various entities?

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. 

Will this AD involve a significant rule 

or regulatory action? For the reasons 

discussed above, I certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under 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 summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary by sending a request to us 

at the address listed under ADDRESSES.

Include ‘‘Docket No. FAA–2004–18597; 

Directorate Identifier 2004–CE–21–AD’’

in your request.

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 Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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.

1334 Federal Register / Vol. 70, No. 5 / Friday, January 7, 2005 / Rules and Regulations 

§ 39.13 [Amended]

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

74–06–01, Amendment 39–1977, and by 

adding a new AD to read as follows:

2005–01–10 The New Piper Aircraft, Inc.:

Amendment 39–13934; Docket No. 

FAA–2004–18597; Directorate Identifier 

2004–CE–21–AD. 

When Does This AD Become Effective? 

(a) This AD becomes effective on February 

22, 2005. 

What Other ADs Are Affected by This 

Action? 

(b) This AD supersedes AD 74–06–01. 

What Airplanes Are Affected by This AD? 

(c) This AD affects Models PA–23–235, 

PA–23–250, and PA–E23–250 airplanes, all 

serial numbers, that are 

(1) certificated in any category; and 

(2) equipped with Garrett Aviation 

Services (Garrett) (formerly AiResearch) 

turbosuperchargers installed under 

supplemental type certificate (STC) 

SA852WE, SA909WE, or SA978WE; or 

installed under The New Piper, Inc. (Piper) 

Aircraft Drawing Number 32016.

Note: Piper manufactured the majority of 

affected airplanes with the turbocharger 

system. The turbocharger system installed 

under Piper Aircraft Drawing Number 32016 

(STC SA909WE) was a factory option on the 

Piper Model PA–23–250 or PA–E23–250 with 

serial numbers 27–2505 through 27–3943.

What is the Unsafe Condition Presented in 

This AD? 

(d) This AD is the result of a report of a 

fatal accident related to the breakdown of the 

turbocharger oil reservoir following a fire in 

the engine nacelle. The actions specified in 

this AD are intended to prevent 

turbosupercharger oil reservoirs with 

inadequate fire resistance from failing when 

exposed to flame or exhaust gases. This 

failure could lead to an in-flight fire within 

the nacelle area penetrating the firewall and 

subsequent failure of the wing spar. 

What Must I do to Address This Problem? 

(e) To address this problem, you must do 

the following:

Actions Compliance Procedures 

(1) For any turbosupercharger installation 

under supplemental type certificate (STC) 

SA852WE, SA909WE, or SA978WE:

Within the next 100 hours time-in-service (TIS) 

after February 22, 2005 (the effective date 

of this AD), unless already done.

Follow the procedures in Garrett Aviation 

Service Bulletin No. 1002143, Revision A, 

dated June 18, 2004. 

(i) Replace any oil reservoir (part number (P/

N) 286–P23–028–81 or 286–P23–028–111, 

or FAA-approved equivalent P/N) with a 

fireproof oil tank (P/N 10ND79200–1 or 

10ND79200–3, or FAA-approved equivalent 

P/N); and 

(ii) Replace the installed oil reservoir hoses 

with fire-shielded hoses. 

(2) For any turbosupercharger installation 

under Piper Aircraft Drawing Number 32016:

Within the next 100 hours TIS after February 

22, 2005 (the effective date of this AD), unless already done.

Follow the procedures in The New Piper Aircraft, Inc. Vendor Service Publication No. 

166, dated August 20, 2004 and the procedures in Garrett Aviation Service Bulletin 

No. 1002143, Revision A, dated June 18, 

2004. 

(i) Replace any oil reservoir (P/N 286–P23–

028–81 or 286–P23–028–111, or FAA-approved equivalent P/N) with a fireproof oil 

tank (P/N 10ND79200–1 or 10ND79200–3, 

or FAA-approved equivalent P/N); and 

(ii) Replace the installed oil reservoir hoses 

with fire-shielded hoses. 

(3) For any turbosupercharger installation 

under STC SA852WE, SA909WE, or 

SA978WE; or Piper Aircraft Drawing Number 

32016: Do not install any oil reservoir (P/N 

286–P23–028–81 or 286–P23–028–111, or 

FAA-approved equivalent P/N). Do not install 

any oil reservoir hose that is not fire-shielded.

As of February 22, 2005 (the effective date of 

this AD).

Not Applicable. 

May I Request an Alternative Method of 

Compliance? 

(f) You may request a different method of 

compliance or a different compliance time 

for this AD by following the procedures in 14 

CFR 39.19. Unless FAA authorizes otherwise, 

send your request to your principal 

inspector. The principal inspector may add 

comments and will send your request to the 

Manager, Los Angeles Aircraft Certification 

Office (ACO), FAA. For information on any 

already approved alternative methods of 

compliance, contact Roger Pesuit, Aerospace 

Engineer, FAA, Los Angeles ACO, 3960 

Paramount Boulevard, Lakewood, CA 90712–

4137; telephone: (562) 627–5251; facsimile: 

(562) 627–5210. 

Does This AD Incorporate Any Material by 

Reference? 

(g) You must do the actions required by 

this AD following the instructions in The 

New Piper Aircraft, Inc. Vendor Service 

Publication No. 166, dated August 20, 2004, 

and the procedures in Garrett Aviation 

Service Bulletin No. 1002143, Revision A, 

dated June 18, 2004. The Director of the 

Federal Register approved the incorporation 

by reference of these service bulletins in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. To get a copy of this service 

information, contact: (for any installation 

under STC SA852WE, SA909WE, or 

SA978WE) The Nordam Group Nacelle/

Thrust Reverser Systems Division, 6911 N. 

Whirlpool Drive, Tulsa, OK 74117 telephone: 

(918) 878–4000; facsimile: (918) 878–4808; 

and (for any installation under Piper Aircraft 

Drawing Number 32016) The New Piper 

Aircraft, Inc., 2926 Piper Drive, Vero Beach, 

Florida, 32960; and The Nordam Group 

Nacelle/Thrust Reverser Systems Division 

6911 N. Whirlpool Drive, Tulsa, OK 74117 

telephone: (918) 878–4000; facsimile: (918) 

878–4808. To review copies of this service 

information, go to the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, go to: http://

www.archives.gov/ federal_register/ 

code_of_federal_ regulations/

ibr_locations.html or call (202) 741–6030. To 

view the AD docket, go to the Docket 

Management Facility; U.S. Department of 

Transportation, 400 Seventh Street, SW., 

Nassif Building, Room PL–401, Washington, 

DC 20590–001 or on the Internet at http://

Federal Register / Vol. 70, No. 5 / Friday, January 7, 2005 / Rules and Regulations 1335

dms.dot.gov. The docket number is FAA–

2004–18597.

Issued in Kansas City, Missouri, on 

December 28, 2004. 

David A. Downey, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 05–184 Filed 1–6–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–19560; Directorate 

Identifier 2004–NM–121–AD; Amendment 

39–13930; AD 2005–01–06] 

RIN 2120–AA64

Airworthiness Directives; Airbus Model 

A310 Series Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Airbus Model A310 series airplanes. 

This AD requires modifying the wire 

routing of electrical harness 636VB in 

the right-hand wing. This AD is 

prompted by the manufacturer’s 

analysis for compliance with Special 

Federal Aviation Regulation No. 88, 

which has shown that wiring 2M of the 

115V anti-collision white strobe lights 

and wiring 2S of the fuel quantity 

indication system (FQIS) should be 

rerouted into separate conduits. We are 

issuing this AD to prevent chafing 

damage to wiring 2M and 2S, which 

could result in a short circuit and 

consequently introduce an electrical 

current into the wiring of the FQIS and 

create an ignition source in the fuel 

tank.

DATES: This AD becomes effective 

February 11, 2005. 

The incorporation by reference of a 

certain publication listed in the AD is 

approved by the Director of the Federal 

Register as of February 11, 2005.

ADDRESSES: For service information 

identified in this AD, contact Airbus, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France. You can 

examine this information 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.

You can examine the contents of this 

AD docket on the Internet at http://

dms.dot.gov, or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW., room PL–401, on the plaza level of 

the Nassif Building, Washington, DC. 

This docket number is FAA–2004–

19560; the directorate identifier for this 

docket is 2004–NM–121–AD.

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

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

fax (425) 227–1149. 

Examining the Docket 

The AD docket contains the proposed 

AD, comments, and any final 

disposition. You can 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.

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

an AD for all Airbus Model A310 series 

airplanes. That action, published in the 

Federal Register on November 9, 2004 

(69 FR 64871), proposed to require 

modifying the wire routing of electrical 

harness 636VB in the right-hand wing. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. No comments 

have been submitted on the proposed 

AD or on the determination of the cost 

to the public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed. 

Costs of Compliance 

This AD will affect about 51 airplanes 

of U.S. registry. The required actions 

will take about 34 work hours per 

airplane, at an average labor rate of $65 

per work hour. Required parts will cost 

about $356 per airplane. Based on these 

figures, the estimated cost of the AD for 

U.S. operators is $130,866 or $2,566 per 

airplane. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action.

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD. 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.