Federal Register / Vol. 74, No. 61 / Wednesday, April 1, 2009 / Proposed Rules 14751 

TABLE—ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Parts Cost 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Replacement ............................................ 25 $80 $60,670 $62,670 249 $15,604,830 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 proposed 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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

Boeing: Docket No. FAA–2009–0293; 

Directorate Identifier 2008–NM–221–AD. 

Comments Due Date 

(a) We must receive comments by May 18, 

2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 747– 

100, –100B, –100B SUD, –200B, –200C, 

–200F, –300, –400, –400D, –400F, and 747SR 

series airplanes, certificated in any category; 

as identified in Boeing Special Attention 

Service Bulletin 747–27–2422, dated October 

30, 2008. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight controls. 

Unsafe Condition 

(e) This AD results from reports of the 

inboard trailing edge (TE) flaps blowing back 

due to the failure of a transmission carbon 

disk no-back brake. The no-back brake did 

not hold the flaps in the commanded 

position. The Federal Aviation 

Administration is issuing this AD to prevent 

a decrease of the aerodynamic controllability 

of the airplane, which could adversely affect 

the airplane’s continued safe flight and 

landing. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Corrective Action 

(g) Within 5 years after the effective date 

of this AD, replace the trailing edge flap 

transmission no-back brakes with skewed 

roller no-back brakes at the trailing edge flap 

transmission, positions 4 and 5, in 

accordance with Boeing Special Attention 

Service Bulletin 747–27–2422, dated October 

30, 2008. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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: 

Douglas Tsuji, Aerospace Engineer, Systems 

and Equipment Branch, ANM–130S, FAA, 

Seattle Aircraft Certification Office, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6487; fax 

(425) 917–6590. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. 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. 

Issued in Renton, Washington, on March 

18, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–7273 Filed 3–31–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0292; Directorate 

Identifier 2008–NM–011–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300, A310, and A300–600 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to certain 

Airbus Model A300 and A310 series 

airplanes. The existing AD currently 

requires replacement of the nose 

landing gear drag strut upper 

attachment pin. This proposed AD 

would require revising the 

Airworthiness Limitations section (ALS) 

14752 Federal Register / Vol. 74, No. 61 / Wednesday, April 1, 2009 / Proposed Rules 

of the Instructions for Continued 

Airworthiness (ICA) to require 

additional life limits and/or 

replacements for certain main landing 

gear and nose landing gear components, 

and would also expand the 

applicability. This proposed AD results 

from revisions to the ALS of the ICA to 

include new or more restrictive life 

limits and/or replacements. We are 

proposing this AD to ensure the 

continued structural integrity of these 

airplanes. 

DATES: We must receive comments on 

this proposed AD by May 1, 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 

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

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS— 

EAW (Airworthiness Office), 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; e-mail: 

account.airworth-eas@airbus.com; 

Internet: http://www.airbus.com. You 

may review copies of the referenced 

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. 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket 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: Tom 

Stafford, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1622; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2009–0292; Directorate Identifier 

2008–NM–011–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

Discussion 

On July 21, 1987, we issued AD 87– 

16–06, amendment 39–5692 (52 FR 

28241, July 29, 1987), for certain Airbus 

Model A300 and A310 series airplanes. 

That AD requires replacement of the 

nose landing gear drag strut upper 

attachment pin. That AD resulted from 

reports of pins which were found to be 

improperly manufactured. We issued 

that AD to prevent failure of the pin and 

collapse of the nose landing gear. 

Actions Since Existing AD Was Issued 

Since we issued AD 87–16–06, the 

manufacturer has revised the 

Airworthiness Limitations Section 

(ALS) of the Instructions for Continued 

Airworthiness (ICA) to include new or 

more restrictive life limits and 

replacements for the main landing gear 

and the nose landing gear. These new 

limits affect the replacement of the 

upper attachment pin for the nose 

landing gear drag strut that was the 

subject of AD 87–16–06. 

In addition, European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2007–0293, dated November 29, 2007, 

which is parallel to this proposed AD, 

includes Model A300–600 series 

airplanes. Those airplane models were 

not included in AD 87–16–06. 

Relevant Service Information 

Airbus has issued the following 

revisions to the ALS of the ICA. These 

documents provide each mandatory 

replacement time, structural inspection 

interval, and related structural 

inspection procedures or other 

procedures (e.g., modifications). 

• For Model A300 Series Airplanes: 

‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Subpart 1–3: Demonstrated fatigue lives’’ of 

Part 1, ‘‘Safe Life Airworthiness 

Limitation Items,’’ dated September 6, 

2007. 

• For Model A300–600 Series 

Airplanes: ‘‘Sub-part 1–2: Life Limits,’’ 

and ‘‘Sub-part 1–3: Demonstrated 

fatigue lives’’ of Part 1, ‘‘Safe Life 

Airworthiness Limitation Items,’’ dated 

December 21, 2006. 

• For Model A310 Series Airplanes: 

‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Subpart 1–3: Demonstrated fatigue lives’’ of 

Part 1, ‘‘Safe Life Airworthiness 

Limitation Items,’’ dated December 21, 

2006. 

Airbus has also issued Section 05–10– 

00, Revision 28, dated February 27, 

1998, of Chapter 5, ‘‘Service Life Limits 

and Maintenance Checks,’’ of the A300 

Aircraft Maintenance Manual. Section 

05–10–00 includes life limit values for 

the nose and main landing gears. This 

document is an alternate source for the 

life limits defined in Part 1, ‘‘Safe Life 

Airworthiness Limitation Items,’’ dated 

September 6, 2007, of the ALS, for 

Model A300 series airplanes. 

Airbus has also issued Service 

Information Letter (SIL) 32–118, 

Revision 02, dated October 24, 2007. 

This SIL gives instructions for 

calculating the life limit of main or nose 

landing gear parts where the history of 

accumulated landings is partial or 

unknown, or where the history of 

application details (airplane type, 

model, weight variant, etc.) is partial or 

unknown. 

Accomplishing the actions specified 

in the service information is intended to 

adequately address the unsafe 

condition. EASA mandated the service 

information and issued Airworthiness 

Directive 2007–0292, dated November 

29, 2007, to ensure the continued 

airworthiness of these airplanes in the 

European Union. 

Other Relevant Rulemaking 

On January 11, 1984, we issued AD 

84–02–04 (49 FR 2746, January 23, 

1984), for certain Airbus Model A300 B2 

and B4 series airplanes. That AD 

requires inspection of main landing gear 

hinge arms for corrosion and cracks, and 

repair or modifications if needed. That 

AD also requires replacement of the 

main landing gear shock absorber 

sliding rod attachment fitting. That AD 

resulted from corrosion and cracks 

found on these components. We issued 

that AD to prevent landing gear failure. 

The actions specified in paragraph (h) 

of this proposed AD would satisfy the 

Federal Register / Vol. 74, No. 61 / Wednesday, April 1, 2009 / Proposed Rules 14753 

requirements of paragraph A. of AD 84– 

02–04. There are no actions in this 

proposed AD that would satisfy the 

requirements of paragraphs B. and C. of 

AD 84–02–04. 

FAA’s Determination and Requirements 

of the Proposed 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 proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

This proposed AD would supersede 

AD 87–16–06 and would retain the 

requirements of that existing AD. This 

proposed AD would also add airplanes 

to the applicability and require revising 

the ALS of the ICA to incorporate 

additional life limits and/or structural 

inspections for certain main landing 

gear and nose landing gear components. 

Change to Existing AD 

This proposed AD would retain the 

requirements of AD 87–16–06. Since AD 

87–16–06 was issued, the AD format has 

been revised. As a result, the 

corresponding paragraph identifiers 

have changed in this proposed AD, and 

paragraph (g) of this proposed AD 

corresponds to paragraph A. of AD 87– 

16–06. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD. 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Parts Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Replacement (required by AD 87–16–06) 7 $80 $3,300 $3,860 94 $362,840 

Revision (new proposed action) .............. 1 80 0 80 238 19,040 

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 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 proposed 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 proposed 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–5692 (52 

FR 28241, July 29, 1987) and adding the 

following new airworthiness directive 

(AD): 

Airbus: Docket No. FAA–2009–0292; 

Directorate Identifier 2008–NM–011–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by May 1, 2009. 

Affected ADs 

(b) This AD supersedes AD 87–16–06. 

Applicability 

(c) This AD applies to all Airbus Model 

A300, A310, and A300–600 series airplanes, 

certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 32: Landing Gear. 

Unsafe Condition 

(e) This AD results from revisions to the 

Airworthiness Limitations section (ALS) of 

the Instructions for Continued Airworthiness 

(ICA) to include new or more restrictive life 

limits and/or replacements. We are issuing 

this AD to ensure the continued structural 

integrity of these airplanes. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new replacements. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these replacements, 

the operator may not be able to accomplish 

the replacements described in the revisions. 

In this situation, to comply with 14 CFR 

91.403(c), the operator must request approval 

for an alternative method of compliance 

according to paragraph (l) of this AD. The 

request should include a description of 

changes to the required replacements that 

will ensure the continued operational safety 

of the airplane. 

14754 Federal Register / Vol. 74, No. 61 / Wednesday, April 1, 2009 / Proposed Rules 

Restatement of the Requirements of AD 87– 

16–06 

(g) For Model A300 and A310 Series 

Airplanes: Prior to the accumulation of 

16,000 landings, or within the next 2,000 

landings after September 3, 1987 (the 

effective date of AD 87–16–06), whichever 

occurs later, replace the nose landing gear 

drag strut upper attachment pin in 

accordance with Airbus Service Bulletin 

A300–32–374, Revision 1, dated July 15, 

1986 (applicable to Model A300 airplanes); 

or A310–32–2023, Revision 2, dated 

November 14, 1986 (applicable to Model 

A310 airplanes). 

New Requirements of This AD 

ALS Revision 

(h) For Model A300, A310, and A300–600 

Series Airplanes: Within 3 months after the 

effective date of this AD, revise the ALS of 

the ICA to incorporate the applicable 

document listed in paragraph (h)(1), (h)(2), or 

(h)(3) of this AD. Accomplishing the actions 

specified in the applicable document satisfies 

the requirements of paragraph A. of AD 84– 

02–04, amendment 39–4795. 

(1) For Model A300 Series Airplanes: 

Incorporate the document listed in paragraph 

(h)(1)(i) or (h)(1)(ii) of this AD. 

(i) Section 05–10–00, Revision 28, dated 

February 27, 1998, of Chapter 5, ‘‘Service Life 

Limits and Maintenance Checks,’’ of the 

Airbus A300 Aircraft Maintenance Manual, 

except that the parts listed in Table 1 of this 

AD are subject to the life limits defined in 

the document listed in paragraph (h)(1)(ii) of 

this AD. 

(ii) ‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Subpart 1–3: Demonstrated fatigue lives’’ of Part 

1, ‘‘Safe Life Airworthiness Limitation 

Items,’’ dated September 6, 2007, of the 

Airbus A300 ALS. 

TABLE 1—PARTS SUBJECT TO THE LIFE LIMITS SPECIFIED IN THE DOCUMENT IDENTIFIED IN PARAGRAPH (H)(1)(II) OF THIS

AD 

Part Number (P/N) Part name 

P/N C61643–2, P/N C61643–4, P/N C61643–5 ...................................... Main landing gear (MLG) shock absorber end fitting. 

P/N A32210001205xx ............................................................................... Nose landing gear (NLG) pintle pin. 

P/N C62037–1 .......................................................................................... NLG shock absorber bottom. 

P/N 196–0328–501 ................................................................................... Cross beam (Pratt & Whitney forward engine mount). 

(2) For Model A310 Series Airplanes: 

Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and 

‘‘Sub-part 1–3: Demonstrated fatigue lives’’ of 

Part 1, ‘‘Safe Life Airworthiness Limitation 

Items,’’ dated December 21, 2006, of the 

Airbus A310 ALS. 

(3) For Model A300–600 Series Airplanes: 

Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and 

‘‘Sub-part 1–3: Demonstrated fatigue lives’’ of 

Part 1, ‘‘Safe Life Airworthiness Limitation 

Items,’’ dated December 21, 2006, of the 

Airbus A300–600 ALS. 

Initial Compliance Times and Repetitive 

Inspections 

(i) Do the replacement at the applicable 

time specified in paragraph (i)(1) or (i)(2) of 

this AD, except as provided by paragraph (j) 

of this AD. The replacement must be done 

thereafter within the interval specified in the 

applicable document identified in paragraph 

(h)(1), (h)(2), or (h)(3) of this AD. 

(1) For any life limitation/task that has 

been complied with before the effective date 

of this AD in accordance with the applicable 

document listed in paragraph (h)(1), (h)(2), or 

(h)(3) of this AD, or in accordance with 

paragraph (g) of this AD, use the last 

accomplishment of each limitation/task as a 

starting point for accomplishing each 

corresponding limitation/task required by 

this AD. 

(2) For any life limitation/task that has not 

been complied with before the effective date 

of this AD in accordance with the applicable 

document listed in paragraphs (h)(1), (h)(2), 

and (h)(3) of this AD, or in accordance with 

paragraph (g) of this AD, the initial 

compliance time starts from the date of initial 

entry into service as defined in the applicable 

document. 

Special Compliance Times 

(j) For any airplane on which the history 

of accumulated landings is partial or 

unknown, or where the history of application 

details (airplane type, model, weight variant, 

etc.) is partial or unknown, with or without 

using the information in Airbus Service 

Information Letter 32–118, Revision 02, 

dated October 24, 2007: Parts listed in Figure 

1 of this AD must be replaced at the 

associated compliance time. The replacement 

must be done thereafter at the interval 

specified in the applicable document(s) 

specified in paragraphs (h)(1), (h)(2), and 

(h)(3) of this AD. 

BILLING CODE 4910–13–P 

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Federal Register / Vol. 74, No. 61 / Wednesday, April 1, 2009 / Proposed Rules 14759 

Alternative Intervals or Limits 

(k) Except as provided by paragraph (l) of 

this AD, after accomplishing the actions 

specified in paragraphs (h), (i), and (j) of this 

AD, no alternative replacements, replacement 

intervals, or limitations may be used. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(1) The Manager, Manager, ANM–116, 

International Branch, 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: Tom Stafford, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1622; fax (425) 227–1149. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. 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. 

Related Information 

(m) European Aviation Safety Agency 

(EASA) Airworthiness Directive 2007–0293, 

dated November 29, 2007, also addresses the 

subject of this AD. 

Issued in Renton, Washington, on March 

12, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–7267 Filed 3–31–09; 8:45 am] 

BILLING CODE 4910–13–C 

ENVIRONMENTAL PROTECTION 

AGENCY 

40 CFR Part 52 

[EPA–R06–OAR–2008–0509; FRL–8788–7] 

Approval and Promulgation of 

Implementation Plans; New Mexico; 

Albuquerque/Bernalillo County 

AGENCY: Environmental Protection 

Agency (EPA). 

ACTION: Proposed rule. 

SUMMARY: EPA is proposing to approve 

a revision to the New Mexico 

Albuquerque/Bernalillo County State 

Implementation Plan (SIP). This 

revision replaces Regulation 8, Airborne 

Particulate Matter, with NMAC 

20.11.20, Fugitive Dust Control. This 

rulemaking action is being taken under 

section 110 of the Clean Air Act (CAA). 

DATES: Written comments must be 

received on or before May 1, 2009. 

ADDRESSES: Comments may be mailed to 

Mr. Guy Donaldson, Chief, Air Planning 

Section (6PD–L), Environmental 

Protection Agency, 1445 Ross Avenue, 

Suite 1200, Dallas, Texas 75202–2733. 

Comments may also be submitted 

electronically or through hand delivery/ 

courier by following the detailed 

instructions in the ADDRESSES section of 

the direct final rule located in the rules 

section of this Federal Register. 

FOR FURTHER INFORMATION CONTACT: Joe 

Kordzi, Air Planning Section (6PD–L), 

Environmental Protection Agency, 

Region 6, 1445 Ross Avenue, Suite 700, 

Dallas, Texas 75202–2733, telephone 

(214) 665–7186; fax number 214–665– 

7263; e-mail address 

kordzi.joe@epa.gov. 

SUPPLEMENTARY INFORMATION: In the 

final rules section of this Federal 

Register, EPA is approving the State’s 

SIP submittal as a direct final rule 

without prior proposal because the 

Agency views this as a noncontroversial 

submittal and anticipates no adverse 

comments. A detailed rationale for the 

approval is set forth in the direct final 

rule. If no adverse comments are 

received in response to this action rule, 

no further activity is contemplated. If 

EPA receives adverse comments, the 

direct final rule will be withdrawn and 

all public comments received will be 

addressed in a subsequent final rule 

based on this proposed rule. EPA will 

not institute a second comment period. 

Any parties interested in commenting 

on this action should do so at this time. 

Please note that if EPA receives adverse 

comment on an amendment, paragraph, 

or section of this rule and if that 

provision may be severed from the 

remainder of the rule, EPA may adopt 

as final those provisions of the rule that 

are not the subject of an adverse 

comment. 

For additional information, see the 

direct final rule which is located in the 

rules section of this Federal Register. 

Dated: March 16, 2009. 

Lawrence E. Starfield, 

Acting Regional Administrator, Region 6. 

[FR Doc. E9–7297 Filed 3–31–09; 8:45 am] 

BILLING CODE 6560–50–P 


EP01AP09.008</GPH>