Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations 12077 

(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 and placed it in the AD Docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.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 the 

NPRM, the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Office (telephone (800) 647–

5227) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

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: 

2007–06–04 EADS SOCATA: Amendment 

39–14985; Docket No. FAA–2006–26231; 

Directorate Identifier 2006–CE–61–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective April 19, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model TBM 700 

airplanes, serial numbers 1 through 268, and 

270 through 327, certificated in any category. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) states 

reports of two fatigue failures of flap carriage 

rollpins that occurred on in-service airplanes. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) Within the next 100 hours time-inservice (TIS) after April 19, 2007 (the 

effective date of this AD), inspect all flap 

inboard carriage rollpins for proper torque 

values and correct as necessary before further 

flight. 

(2) Repeat these inspections thereafter at 

intervals not to exceed 100 hours TIS and 

correct as necessary before further flight after 

the inspection in which a correction is 

necessary. 

(3) Accomplish these actions according to 

the instructions given in EADS SOCATA 

TBM Aircraft Mandatory Service Bulletin SB 

70–122, Amendment 1, dated March 2006, or 

EADS SOCATA TBM Aircraft Mandatory 

Service Bulletin SB 70–122, Amendment 2, 

dated January 2007, and the applicable 

maintenance manual. 

(4) If both flap inboard carriages have been 

replaced following EADS SOCATA TBM 

Aircraft Mandatory Service Bulletin SB 70–

138, dated March 2006, no further action is 

required. Make an entry in the logbook to 

show compliance with this AD. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(f) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Staff, 

FAA, Small Airplane Directorate, ATTN: 

Albert J. Mercado, Aerospace Engineer, 901 

Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4119; fax: (816) 

329–4090, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

(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 FAA-approved 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 

(44 U.S.C. 3501 et seq.), 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 Direction ge ́ne ́rale de 

l’aviation civile AD No. F–2005–017, Issue 

date: January 19, 2005, for related 

information. 

Material Incorporated by Reference 

(i) You must use EADS SOCATA TBM 

Aircraft Mandatory Service Bulletin SB 70–

122, Amendment 1, dated March 2006, or 

EADS SOCATA TBM Aircraft Mandatory 

Service Bulletin SB 70–122, Amendment 2, 

dated January 2007, 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 EADS SOCATA, Direction 

des Services, 65921 Tarbes Cedex 9, France; 

telephone: 33 (0)5 62 41 73 00; fax: 33 (0)5 

62 41 76 54; or SOCATA AIRCRAFT, INC., 

North Perry Airport, 7501 South Airport Rd., 

Pembroke Pines, FL 33023; telephone: (954) 

893–1400; fax: (954) 964–4141. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Room 506, Kansas City, 

Missouri 64106; or 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/ 

cfr/ibr-locations.html. 

Issued in Kansas City, Missouri, on March 

6, 2007. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E7–4383 Filed 3–14–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27360; Directorate 

Identifier 2007–NM–026–AD; Amendment 

39–14986; AD 2007–06–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318, A319, A320 and A321 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: 

* * * * * 

* * * updates [to the airplane maintenance 

manual (AMM), engine service manual 

(ESM), and quick engine change kit 

instruction manual (QECKIM)] have 

inadvertently introduced torque value errors 

for the bolts that attach the forward engine 

mount to the engine. * * * 

* * * * * 


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12078 Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations 

Application of the incorrect torque to 

the forward engine mount bolts during 

maintenance could result in failure of 

the forward engine mount and possible 

separation of the engine from the 

airplane and damage to the wing or loss 

of control of the airplane. This AD 

requires actions that are intended to 

address the unsafe condition described 

in the MCAI. 

DATES: This AD becomes effective 

March 30, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications, listed in the AD, 

as of March 30, 2007. 

We must receive comments on this 

AD by April 16, 2007. 

ADDRESSES: You may send comments by 

any of the following methods: 

• DOT Docket Web Site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Fax: (202) 493–2251. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• 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. 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.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 street address for the 

Docket Office (telephone (800) 647–

5227) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2141; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. This streamlined 

process will allow us to adopt MCAI 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

follow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act, and Federal Register 

requirements. We also continue to meet 

our technical decision-making 

responsibilities to identify and correct 

unsafe conditions on U.S.-certificated 

products. 

This AD references the MCAI and 

related service information that we 

considered in forming the engineering 

basis to correct the unsafe condition. 

The AD contains text copied from the 

MCAI and for this reason might not 

follow our plain language principles. 

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 2007–0036R1, 

dated February 27, 2007 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

From May 2006, the forward engine mount 

removal and installation procedures (AMM, 

ESM, QECKIM) have been updated to add 

removal and installation of the support 

assemblies. 

These updates have inadvertently 

introduced torque value errors for the bolts 

that attach the forward engine mount to the 

engine. This condition, if not corrected, may 

have the following consequences: 

—rupture of bolts and failure of the support 

assembly due to overtorqued bolts; 

—reduced safe life of the secondary thrust 

load path due to low torque on monoball 

housing bolts. 

Application of the incorrect torque to 

the forward engine mount bolts during 

maintenance could result in failure of 

the forward engine mount and possible 

separation of the engine from the 

airplane and damage to the wing or loss 

of control of the airplane. The MCAI 

requires inspection, replacement, and 

re-torque of the affected bolts and 

adjustment of the torque values. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued All Operators Telex 

A320–71A1042, Revision 01, dated 

February 12, 2007. Goodrich has issued 

All Operators Letter CFM56–074, 

Revision 1, dated February 1, 2007. 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. 

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 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because application of the incorrect 

torque to the engine mount primary and 

secondary load path bolts during 

maintenance could result in failure of 

the forward engine mount and possible 

separation of the engine from the 

airplane and damage to the wing or loss 

of control of the airplane. Therefore, we 

determined that notice and opportunity 

for public comment before issuing this 

AD are impracticable and that good 

cause exists for making this amendment 

effective in fewer than 30 days. 

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–2007–27360; 

Directorate Identifier 2007–NM–026–

AD’’ at the beginning of your comments. 


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Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations 12079 

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:// 

dms.dot.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: 

2007–06–05 Airbus: Amendment 39–14986. 

Docket No. FAA–2007–27360; 

Directorate Identifier 2007–NM–026–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective March 30, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A318–

111 and –112; A319–111, –112, –113, –114, 

and –115; A320–111, –211, –212, and –214; 

and A321–111, –112, –211, –212, and –213 

airplanes; certificated in any category; all 

serial numbers, which have CFM 

International CFM56–5A or CFM56–5B series 

engines installed. 

Subject 

(d) Powerplant. 

Reason 

(e) The mandatory continued airworthiness 

information (MCAI) states: 

From May 2006, the forward engine mount 

removal and installation procedures (airplane 

maintenance manual (AMM), engine service 

manual (ESM), quick engine change kit 

instruction manual (QECKIM)) have been 

updated to add removal and installation of 

the support assemblies. 

These updates have inadvertently 

introduced torque value errors for the bolts 

that attach the forward engine mount to the 

engine. This condition, if not corrected, may 

have the following consequences: 

—rupture of bolts and failure of the support 

assembly due to overtorqued bolts; 

—reduced safe life of the secondary thrust 

load path due to low torque on monoball 

housing bolts. 

Application of the incorrect torque to the 

forward engine mount bolts during 

maintenance could result in failure of the 

forward engine mount and possible 

separation of the engine from the airplane 

and damage to the wing or loss of control of 

the airplane. The MCAI requires inspection, 

replacement, and re-torque of the affected 

bolts and adjustment of the torque values. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) As of the effective date of this AD: 

(i) Any maintenance on the engine mounts 

must be performed in accordance with 

correct instructions as identified in the 

Airbus All Operators Telex (AOT) A320–

71A1042, Revision 01, dated February 12, 

2007; or Goodrich All Operators Letter (AOL) 

CFM56–074, Revision 1, dated February 1, 

2007; and 

(ii) Any forward engine mount support 

assemblies fitted on an engine which is used 

as replacement must be fitted in accordance 

with correct instructions as identified in 

Airbus AOT A320–71A1042, Revision 01, 

dated February 12, 2007; or Goodrich AOL 

CFM56–074, Revision 1, dated February 1, 

2007. 

(2) For aircraft on which any forward 

engine mount support assembly has been 

installed or maintained since May 2006 using 

erroneous torque values given in the 

maintenance data identified in paragraph 1. 

of the Airbus AOT A320–71A1042, Revision 

01, dated February 12, 2007, or where the use 

of correct torque values cannot be 

established: Within 20 days after the effective 

date of this AD, accomplish the actions in 

paragraphs (f)(2)(i), (f)(2)(ii), (f)(2)(iii), and 

(f)(2)(iv) of this AD, as applicable, in 

accordance with the instructions of Airbus 

AOT A320–71A1042, Revision 01, dated 

February 12, 2007. Aircraft on which no 

engine removal has been performed since 

aircraft delivery are not affected by this 

paragraph. The alternative procedure given 

in paragraph 4.2.3 of the AOT is acceptable, 

provided that the nominal torque values 

specified in paragraphs 4.2.1 and 4.2.2 are 

restored within 120 flight cycles after 

accomplishing paragraph 4.2.3 of the AOT. 

(i) Remove and inspect the following 

forward engine mount bolts: 77710–5H6 

(AMM item 90) and NAS2815C15H (AMM 

item 85). 

(ii) If any bolts, 77710–5H6 (AMM item 

90), are found broken during the above 

inspection, before further flight, replace the 

affected forward engine mount support 

assembly (AMM item 75). 

(iii) Replace bolts, 77710–5H6 (AMM item 

90) and NAS2815C15H (AMM item 85), with 

new items and torque them to the correct 

value. 

(iv) Re-torque 77458–7H21 bolts (AMM 

item 95) and NAS2816C7H (AMM item 50) 

to the correct value. 

(3) Actions done before the effective date 

of this AD in accordance with Airbus AOT 

A320–71A1042, dated February 5, 2007, are 

acceptable for compliance with the 

corresponding provisions of paragraph (f)(2) 

of this AD. 

(4) Within 7 days after the inspection, 

report all findings to Airbus Customer 

Services, Engineering and Technical Support, 

Attention: Mr. J-P Pourtau SEE11; telephone 

+33 (0) 5 62 11 04 48; fax +33 (0) 5 61 93 

36 14. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 


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12080 Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations 

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, 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: Tim Dulin, 

Aerospace Engineer, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2141; fax (425) 227–1149. 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. 

(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 FAA-approved 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 (EASA) Airworthiness 

Directive 2007–0036R1, dated February 27, 

2007; Airbus All Operators Telex A320–

71A1042, Revision 01, dated February 12, 

2007; and Goodrich All Operators Letter 

CFM56–074, Revision 1, dated February 1, 

2007, for related information. 

Material Incorporated by Reference 

(i) You must use Airbus All Operators 

Telex A320–71A1042, Revision 01, dated 

February 12, 2007; or Goodrich All Operators 

Letter CFM56–074, Revision 1, dated 

February 1, 2007; 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, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France. 

(3) You may review copies at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on March 7, 

2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–4535 Filed 3–14–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2006–26396; Airspace 

Docket No. 06–AAL–40] 

Revision of Class E Airspace; Red 

Dog, AK 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action revises Class E 

airspace at Red Dog, AK. Two new Area 

Navigation (RNAV) Required Navigation 

Performance (RNP) Special Instrument 

Approach Procedures (SIAPs) and an 

RNAV RNP Special Departure 

Procedure (DP) are being developed for 

the Red Dog Airport. This rule results in 

the revision of Class E airspace upward 

from 700 feet (ft.) and 1,200 ft. above the 

surface near the Red Dog Airport, Red 

Dog, AK. 

DATES: Effective Dates: 0901 UTC, May 

10, 2007, the Director of the Federal 

Register approves this incorporation by 

reference action under title 1, Code of 

Federal Regulations, part 51, subject to 

the annual revision of FAA Order 

7400.9 and publication of conforming 

amendments. 

FOR FURTHER INFORMATION CONTACT: Gary 

Rolf, AAL–538G, Federal Aviation 

Administration, 222 West 7th Avenue, 

Box 14, Anchorage, AK 99513–7587; 

telephone number (907) 271–5898; fax: 

(907) 271–2850; e-mail: 

gary.ctr.rolf@faa.gov. Internet address: 

http://www.alaska.faa.gov/at. 

SUPPLEMENTARY INFORMATION: 

History 

On Monday, December 18, 2006, the 

FAA proposed to amend part 71 of the 

Federal Aviation Regulations (14 CFR 

part 71) to revise Class E airspace 

upward from 700 ft. and 1,200 ft. above 

the surface at Red Dog, AK (71 FR 

75686). The action was proposed in 

order to create Class E airspace 

sufficient in size to contain aircraft 

while executing two new SIAPs, and 

one new DP for the Red Dog Airport. 

The new Special approaches are (1) The 

RNAV RNP Runway (RWY) 05, and (2) 

the RNAV RNP RWY 20. The Special DP 

is the IHOPO ONE RNAV RNP 

Departure. Class E controlled airspace 

extending upward from 700 ft. and 

1,200 ft. above the surface in the Red 

Dog Airport area is revised by this 

action. 

Interested parties were invited to 

participate in this proposed rulemaking 

by submitting written comments on the 

proposal to the FAA. No comments have 

been received, thus the rule is adopted 

as proposed. 

The area will be depicted on 

aeronautical charts for pilot reference. 

The coordinates for this airspace docket 

are based on North American Datum 83. 

The Class E airspace areas designated as 

700/1,200 ft. transition areas are 

published in paragraph 6005 of FAA 

Order 7400.9P, Airspace Designations 

and Reporting Points, dated September 

1, 2006, and effective September 15, 

2006, which is incorporated by 

reference in 14 CFR 71.1. The Class E 

airspace designation listed in this 

document will be published 

subsequently in the Order. 

The Rule 

This amendment to 14 CFR part 71 

revises Class E airspace at the Red Dog 

Airport, Alaska. This Class E airspace is 

revised to accommodate aircraft 

executing two new Special SIAPs, and 

one new Special DP, and will be 

depicted on aeronautical charts for pilot 

reference. The intended effect of this 

rule is to provide adequate controlled 

airspace for Instrument Flight Rule (IFR) 

operations at the Red Dog airport, Red 

Dog, Alaska. 

The FAA has determined that this 

regulation only involves an established 

body of technical regulations for which 

frequent and routine amendments are 

necessary to keep them operationally 

current. It, therefore—(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) 

does not warrant preparation of a 

regulatory evaluation as the anticipated 

impact is so minimal. Since this a 

routine matter that will only affect air 

traffic procedures and air navigation, it 

is certified that this rule will not have 

a significant economic impact on a 

substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

The FAA’s authority to issue rules 

regarding aviation safety is found in 

Title 49 of the United States Code. 

Subtitle 1, Section 106 describes the 

authority of the FAA Administrator. 

Subtitle VII, Aviation Programs, 


rmajette on PROD1PC67 with RULES