Federal Register / Vol. 74, No. 182 / Tuesday, September 22, 2009 / Rules and Regulations 48143 

TABLE 1—ENGINE MODELS AFFECTED

O–470–G, K, L, R, S, M, U 

IO–470–C, D, E, F, H, L, M, N, S, U, V, VO 

TSIO–470–B, C, D 

IO–520–A, B, BA, BB, C, CB, D, E, F, J, K, 

L, M, MB 

TSIO–520–AF, B, BB, C, CE, D, DB, E, EB, 

G, H, J, JB, K, KB, L, LB, M, N, NB, P, R, 

T, UB, VB, WB 

IO–550–A, B, C, D, E, F, L 

IOF–550–B, C, D, E, F, L 

(d) These engines are installed on, but not 

limited to, Alexandria Aircraft LLC (formerly 

Bellanca) model 300 Super Viking; Beech 

Bonanza 33, 35 and 36 series, Beech Baron 

56 and 58 series, Cessna 180, 182, 188, 205, 

206, 207, 210, 303, 310, 320, 402, and 414 

model series; Aero Commander 200 and 500; 

certain Rockwell (formerly Meyers) 

Windecker Eagle 200, and Navion airplanes. 

Unsafe Condition 

(e) This AD results from reports of 35 EQ3 

cylinders found cracked. We are issuing this 

AD to prevent loss of engine power due to 

cracks in the cylinder head, possible engine 

failure, and fire in the engine compartment. 

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. 

Identification and Initial Visual Inspection 

(g) Within 20 flight hours after the effective 

date of this AD, identify EQ3 cylinders using 

Step 1 of TCM MSB No. MSB09–1B, dated 

July 14, 2009. 

(1) Within 20 flight hours after the effective 

date of this AD, for EQ3 cylinders with 400 

or more hours total time of operation on the 

effective date of this AD, perform an initial 

visual inspection of the cylinder for cracks 

using Step 2, paragraph B, of TCM MSB No. 

MSB09–1B, dated July 14, 2009. 

(2) For EQ3 cylinders with fewer than 400 

hours total time of operation on the effective 

date of this AD, perform an initial visual 

inspection of the cylinder for cracks before 

reaching 400 hours total time of operation, 

using Step 2, paragraph B, of TCM MSB No. 

MSB09–1B, dated July 14, 2009. 

(3) Remove from service before flight, any 

cylinders found cracked. 

Repetitive Visual Inspections 

(h) Repeat the visual inspections required 

by this AD every 50 hours of operation. Use 

Step 2, paragraph B, of TCM MSB No. 

MSB09–1B, dated July 14, 2009, to perform 

the inspection. 

(i) Remove from service before flight, any 

cylinders found cracked. 

Removal of All EQ3 Cylinders From Service 

(j) Within 1,300 hours total time of 

operation after the effective date of this AD, 

remove all EQ3 cylinders from service. 

EQ3 Cylinder Installation Prohibition 

(k) After the effective date of this AD, do 

not install any EQ3 cylinder onto any engine, 

or any EQ3 cylinder-equipped engine, onto 

any aircraft. 

Previous Credit 

(l) Initial visual inspections done before 

the effective date of this AD per TCM MSB 

No. MSB09–1A, dated March 11, 2009, 

comply with the initial inspection 

requirements specified in this AD. 

Alternative Methods of Compliance 

(m) The Manager, Atlanta Aircraft 

Certification Office, has the authority to 

approve alternative methods of compliance 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Special Flight Permits 

(n) Under 14 CFR 39.23, we are limiting 

the special flight permits for this AD to 

engines that have no evidence of fuel or 

combustion staining in the cylinder crack 

location, and for a total special flight time of 

5 hours. 

Related Information 

(o) Contact Anthony Holton, Engineer, 

Propulsion, Atlanta Aircraft Certification 

Office, FAA, Small Airplane Directorate, 

1701 Columbia Avenue, College Park, 

Georgia 30337; e-mail 

anthony.holton@faa.gov; telephone: (404) 

474–5567; fax: (404) 474–5606, for more 

information about this AD. 

Material Incorporated by Reference 

(p) You must use Teledyne Continental 

Motors Mandatory Service Bulletin No. 

MSB09–1B, dated July 14, 2009, to perform 

the actions required by this AD. The Director 

of the Federal Register approved the 

incorporation by reference of this service 

bulletin in accordance with 5 U.S.C. 552(a) 

and 1 CFR part 51. Contact Teledyne 

Continental Motors, Inc., PO Box 90, Mobile, 

AL 36601; telephone (251) 438–3411, or go 

to: http://tcmlink.com/servicebulletins.cfm, 

for a copy of this service information. You 

may review copies at the FAA, New England 

Region, 12 New England Executive Park, 

Burlington, MA; 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 Burlington, Massachusetts, on 

September 8, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–22287 Filed 9–21–09; 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; Amendment 

39–16011; AD 2009–18–15] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300, A310, and A300–600 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Airbus Model 

A300 and A310 series airplanes. That 

AD currently requires replacement of 

the nose landing gear drag strut upper 

attachment pin. This new AD requires 

revising the Airworthiness Limitations 

section (ALS) 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 also expands the applicability. This 

AD results from revisions to the ALS of 

the 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. 

DATES: This AD becomes effective 

October 27, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 27, 2009. 

ADDRESSES: For service information 

identified in this 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; email: account.airworth-eas@airbus.com; 

Internet http://www.airbus.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 


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Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

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: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 87–16–06, amendment 

39–5692 (52 FR 28241, July 29, 1987). 

The existing AD applies to certain 

Airbus Model A300 and A310 series 

airplanes. That NPRM was published in 

the Federal Register on April 1, 2009 

(74 FR 14751). That NPRM proposed to 

continue to require replacement of the 

nose landing gear drag strut upper 

attachment pin. That NPRM also 

proposed to require revising the 

Airworthiness Limitations section (ALS) 

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. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been received on the NPRM. 

Request To Add Grace Period 

TradeWinds Airlines requests that we 

add a ‘‘grace period’’ to the life limit 

placed on the nose landing gear (NLG) 

shock absorber bottom, part number 

(P/N) C62037–1, listed in Table 1 of the 

NPRM, as referenced in paragraph 

(h)(1)(i) of the NPRM. TradeWinds 

explains that this component was not 

listed in Chapter 5 of the Airbus A300 

Airplane Maintenance Manual (AMM) 

and had no corresponding FAA AD 

issued against it. Therefore, for U.S. 

operators, there was never a 

requirement to track the life limit. 

TradeWinds suggests a grace period of 

the next NLG overhaul or restoration be 

added so this internal component can be 

replaced without unscheduled removal 

from the airplane. 

We do not agree that it is necessary 

to add a grace period based on the 

operator’s next overhaul or restoration. 

Maintenance schedules vary among 

operators; there is no assurance that the 

overhaul or restoration would occur 

within the maximum interval of time 

allowable for the affected airplanes to 

operate safely. However, under the 

provisions of paragraph (l) of this AD, 

we will consider requests for 

adjustments to the compliance time if 

data are submitted to substantiate that 

such an adjustment would provide an 

acceptable level of safety. We have not 

changed the AD in this regard. 

Request To Clarify Purpose of Service 

Information Letter (SIL) 

TradeWinds Airlines requests that we 

clarify the purpose of Airbus Service 

Information Letter (SIL) 32–118, 

Revision 02, dated October 24, 2007, as 

referenced in paragraph (j) of the NPRM. 

TradeWinds requests a note or some 

clarification to describe the use or 

application of the SIL as it pertains to 

the AD. 

We agree with the request to clarify 

the purpose of the SIL. We have added 

Note 2 to the AD to include the 

following information from page 1 of the 

SIL: 

Note 2: Airbus Service Information Letter 

32–118, Revision 02, dated October 24, 2007, 

provides operators with guidance on the 

means to assign a conservative calculated life 

to parts whose history of accumulated 

landings is partial or unknown; and to select 

the limitations applicable to parts whose 

history of application details (aircraft type, 

aircraft model, weight variant, etc.) is partial 

or unknown. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

that have been 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 

The following table provides the 

estimated costs for U.S. operators to 

comply with this 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 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 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 


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Federal Register / Vol. 74, No. 182 / Tuesday, September 22, 2009 / Rules and Regulations 48145 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–5692 (52 

FR 28241, July 29, 1987) and by adding 

the following new airworthiness 

directive (AD): 

2009–18–15 Airbus: Amendment 39–16011. 

Docket No. FAA–2009–0292; Directorate 

Identifier 2008–NM–011–AD. 

Effective Date 

(a) This AD becomes effective October 27, 

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. 

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 applicable 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 05, ‘‘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 No. (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. 


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Note 2: Airbus Service Information Letter 

32–118, Revision 02, dated October 24, 2007, 

provides operators with guidance on the 

means to assign a conservative calculated life 

to parts whose history of accumulated 

landings is partial or unknown; and to select 

the limitations applicable to parts whose 

history of application details (aircraft type, 

aircraft model, weight variant, etc.) is partial 

or unknown. 

BILLING CODE 4910–13–P 


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BILLING CODE 4910–13–C 

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, 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. 

Material Incorporated by Reference 

(n) You must use the service information 

contained in Table 2 of this AD to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

TABLE 2—MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Section 05–10–00 of Chapter 05, ‘‘Service Life Limits and Maintenance Checks,’’ of the Airbus A300 Aircraft Maintenance Manual.28 ............. February 27, 1998. 

Airbus A300 Airworthiness Limitations Section, ALS Part 1, ‘‘Safe Life Airworthiness Limitations Items’’ ...... Original .... September 6, 2007. 

Airbus A300–600 Airworthiness Limitations Section, ALS Part 1, ‘‘Safe Life Airworthiness Limitations 

Items’’.

Original .... December 21, 2006. 

Airbus A310 Airworthiness Limitations Section, ALS Part 1, ‘‘Safe Life Airworthiness Limitation Items’’ ........ Original .... December 21, 2006. 

Airbus Service Bulletin A300–32–374 ............................................................................................................... 1 ............... July 15, 1986. 

Airbus Service Bulletin A310–32–2023 ............................................................................................................. 2 .............. November 14, 1986. 

Airbus Service Bulletin A300–32–374, 

Revision 1, dated July 15, 1986, has the 

following effective pages: 

Page No. 

Revision 

level 

shown on 

page 

Date shown on 

page 

1, 3–8, 11 1 .............. July 15, 1986. 

2 ............. Original ... April 16, 1986. 

(Airbus Service Bulletin A300–32–374, 

Revision 1, dated July 15, 1986 does not 

contain pages 9 and 10.) 

Airbus Service Bulletin A310–32–2023, 

Revision 2, dated November 14, 1986, has the 

following effective pages: 

Page No. 

Revision 

level 

shown on 

page 

Date shown on 

page 

1, 5–9 ..... 2 .............. November 14, 1986 

2, 4 ......... 1 .............. July 15, 1986 

3 ............. Original ... April 16, 1986 

Chapter 05 of Airbus A300 Aircraft 

Maintenance Manual has the following 

effective pages: 


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LIST OF EFFECTIVE PAGES

Page title/description Page No.(s) Revision No. Date shown on 

page(s) 

AMM Title Page .................................................................... None shown .......................... None shown * ........................ February 27, 1998. 

Chapter 05 Record of Revisions .......................................... 1–2 ........................................ 28 .......................................... February 27, 1998. 

Chapter 05 Effective Pages .................................................. 1–4 ........................................ None shown * ........................ February 27, 1998. 

Chapter 05 Table of Contents .............................................. 1–4 ........................................ None shown * ........................ February 27, 1998. 

Section 05–10–00 ................................................................. 1 ............................................ None shown * ........................ February 27, 1998. 

* The revision number is indicated only in the Record of Revisions section of Chapter 05. 

(The List of Effective Pages (LOEP) for 

Chapter 05 of the Airbus A300 Aircraft 

Maintenance Manual contains the following 

errors: Transmittal Letter page, page 4 of the 

LOEP and Table of Contents sections, page 2 

of Subsection 05–00–01, page 1 of Subsection 

05–11–11, and Subsection 05–10–00, are not 

listed in the LOEP; and the LOEP also does 

not specify a date for the Record of Revisions 

page. In addition, the LOEP identifies three 

pages for Subsection 05–11–00, 

Configuration 5; however, only one page 

exists. The LOEP identifies three pages for 

Subsection 05–11–00, Configuration 9; 

however, those pages do not exist.) 

(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—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.airwortheas@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. 

Issued in Renton, Washington, on August 

24, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–21033 Filed 9–21–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE TREASURY 

Internal Revenue Service 

26 CFR Part 1 

[TD 9452] 

RIN 1545–BB28 

Application of Separate Limitations to 

Dividends From Noncontrolled Section 

902 Corporations; Correction 

AGENCY: Internal Revenue Service (IRS), 

Treasury. 

ACTION: Correcting amendment. 

SUMMARY: This document contains 

corrections to final regulations (TD 

9452) that were published in the 

Federal Register on Thursday, June 11, 

2009, regarding the application of 

separate foreign tax credit limitations to 

dividends received from noncontrolled 

section 902 corporations. 

DATES: This correction is effective on 

September 22, 2009 and is applicable in 

taxable years ending on or after April 

20, 2009. 

FOR FURTHER INFORMATION CONTACT: 

Richard Chewning, (202) 622–3850 (not 

a toll-free number). 

SUPPLEMENTARY INFORMATION: 

Background 

The final regulations that are the 

subject of this document are under 

section 964 of the Internal Revenue 

Code. 

Need for Correction 

As published on Thursday, June 11, 

2009 (74 FR 27886), the final regulations 

(TD 9452) contain errors that may prove 

to be misleading and are in need of 

clarification. 

List of Subjects in 26 CFR Part 1 

Income taxes, Reporting and 

recordkeeping requirements. 

Correction of Publication 

■ Accordingly, 26 CFR part 1 is 

corrected by making the following 

correcting amendments: 

PART 1—INCOME TAXES 

■ Paragraph 1. The authority citation 

for part 1 continues to read in part as 

follows: 

Authority: 26 U.S.C. 7805 * * * 

■ Par. 2. Section 1.964–1 is amended by 

revising the last sentence of paragraph 

(c)(2) and paragraph (c)(4)(i)(D) to read 

as follows: 

§ 1.964–1 Determination of the earnings 

and profits of a foreign corporation. 

* * * * * 

(c) * * * 

(2) * * * See also §§ 1.985–5, 1.985– 

6, and 1.985–7 relating to adjustments to 

earnings and profits of a QBU required 

when the QBU changes its functional 

currency or begins to use the dollar 

approximate separate transactions 

method of accounting. 

(4) * * * 

(i) * * * 

(D) Whether the domestic shareholder 

received the written notice required by 

paragraph (c)(3)(iii) of this section. 

* * * * * 

LaNita VanDyke, 

Chief, Publications and Regulations Branch, 

Legal Processing Division, Associate Chief 

Counsel, (Procedure and Administration). 

[FR Doc. E9–22694 Filed 9–21–09; 8:45 am] 

BILLING CODE 4830–01–P 

DEPARTMENT OF DEFENSE 

Department of the Army, Corps of 

Engineers 

33 CFR Part 334 

United States Navy Restricted Area, 

SUPSHIP Bath Detachment Mobile, 

Mobile, AL 

AGENCY: U.S. Army Corps of Engineers, 

Department of Defense. 

ACTION: Final rule. 

SUMMARY: The U.S. Army Corps of 

Engineers (Corps) is adding regulations 

to establish a restricted area around the 

AUSTAL, USA shipbuilding facility 

located in Mobile, Alabama, because of 


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