29112 Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations 

consulting with employing agencies and 

determining that this would give 

agencies sufficient time to modify their 

personnel and payroll systems to 

provide for immediate agency 

contributions. That is, in order to 

efficiently administer the Thrift Savings 

Plan and to carry out his responsibilities 

as Executive Director, he determined it 

necessary to give employing agencies 

sufficient time to modify their computer 

systems to carry out the requirements of 

this regulation and the law that was 

passed by the House less than eighteen 

hours after it was passed by the Senate. 

This flexibility will also benefit those 

participants whose employing agencies 

are capable of implementing sooner. 

That is, their employing agencies may 

begin making contributions on behalf of 

these employees as soon as practicable. 

Providing implementing flexibility is 

consistent with the grant of authority 

given to the Executive Director by the 

Thrift Savings Plan Enhancement Act of 

2009. Section 102 of the Act provides 

for ‘‘Automatic Enrollments and 

Immediate Employing Agency 

Contributions.’’ Immediate Employing 

Agency Contributions was meant as an 

enhancement to automatic enrollment. 

For example, it envisions a 3 percent 

default contribution rate in order to 

provide participants with a dollar for 

dollar match on their contributions. It 

specifies that the default contribution 

rate may not exceed 5 percent, which 

would provide participants with the 

greatest matching contributions allowed 

by law. Section 102 gives the Executive 

Director the authority to promulgate 

regulations pertaining to automatic 

enrollment. The Executive Director 

relies on this authority as well as the 

authorities specified above in 

promulgating this regulation. 

Regulatory Flexibility Act 

I certify that these regulations will not 

have a significant economic impact on 

a substantial number of small entities. 

They will affect only employees of the 

Federal government and members of the 

uniformed services. 

Paperwork Reduction Act 

I certify that these regulations do not 

require additional reporting under the 

criteria of the Paperwork Reduction Act. 

Unfunded Mandates Reform Act of 

1995 

Pursuant to the Unfunded Mandates 

Reform Act of 1995, 2 U.S.C. 602, 632, 

653, 1501–1571, the effects of this 

regulation on State, local, and Tribal 

governments and the private sector have 

been assessed. This regulation will not 

compel the expenditure in any one year 

of $100 million or more by State, local, 

and Tribal governments, in the 

aggregate, or by the private sector. 

Therefore, a statement under section 

1532 is not required. 

Submission to Congress and the 

General Accounting Office 

Pursuant to 5 U.S.C. 810(a)(1)(A), the 

Agency submitted a report containing 

this rule and other required information 

to the U.S. Senate, the U.S. House of 

Representatives, and the Comptroller 

General of the United States before 

publication of this rule in the Federal 

Register. This rule is not a major rule as 

defined at 5 U.S.C. 814(2). 

List of Subjects in 5 CFR Part 1600 

Government employees, Pensions, 

Retirement. 

Gregory T. Long, 

Executive Director, Federal Retirement Thrift 

Investment Board. 

■ For the reasons stated in the preamble, 

the Federal Retirement Thrift 

Investment Board amends part 1600 of 

title 5 of the Code of Federal 

Regulations as follows: 

PART 1600—EMPLOYEE 

CONTRIBUTION ELECTIONS AND 

CONTRIBUTION ALLOCATIONS 

■ 1. The authority citation for part 1600 

is revised to read as follows: 

Authority: 5 U.S.C. 8351, 8432(a), 8432(b), 

8432(c), 8432(j), 8474(b)(5) and (c)(1), Thrift 

Savings Plan Enhancement Act of 2009, 

section 102. 

■ 2. Revise § 1600.13 to read as follows: 

§ 1600.13 Timing of agency contributions. 

An employee appointed or 

reappointed to a position covered by 

FERS is immediately eligible to receive 

agency contributions. In order to enable 

agencies to modify their personnel and 

payroll systems, agencies must 

implement this regulation as soon as 

practicable, but in no case later than the 

first full pay period in August 2009. 

Effective with the first full pay period of 

August 2009, all eligible employees 

must receive immediate agency 

contributions. 

[FR Doc. E9–14478 Filed 6–18–09; 8:45 am] 

BILLING CODE 6760–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1082; Directorate 

Identifier 2007–NM–337–AD; Amendment 

39–15925; AD 2009–12–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 Airplanes; Model A300 B4–601, 

B4–603, B4–620, B4–622, B4–605R, 

B4–622R, F4–605R, F4–622R, and C4– 

605R Variant F Airplanes (Collectively 

Called A300–600 Series Airplanes); 

and Model A310 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 the airplanes identified 

above. That AD currently requires 

revising the FAA-approved maintenance 

program to include a new airplane 

maintenance manual task that specifies 

a detailed inspection after each ram air 

turbine (RAT) retraction. That existing 

AD also currently requires, for certain 

airplanes, a one-time inspection to 

detect breaks in the bottom flange fitting 

of the RAT and corrective actions, if 

necessary; for certain airplanes, an 

adjustment of the ejection jack; and, for 

certain other airplanes, replacement of 

the aluminum part with an improved 

steel part. This AD also continues to 

require certain actions for additional 

airplanes and revising the FAAapproved maintenance program to 

include procedures for replacing the 

RAT swivel coupling fork fitting with a 

new steel part only. This AD results 

from a report that an additional swivel 

coupling of the RAT yoke fitting was 

found cracked during the 

accomplishment of the requirements of 

the existing AD. We are issuing this AD 

to prevent misrigging of the ejection jack 

of the RAT and to ensure removal of any 

RAT yoke fitting made from aluminum 

material. Such conditions could result 

in a broken or cracked swivel coupling 

and consequent failure of the RAT yoke 

fitting, which could result in the loss of 

RAT function and possible loss of 

critical flight control systems in the 

event of certain emergency situations. 

DATES: This AD becomes effective July 

24, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of July 24, 2009. 


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Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations 29113 

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; 

e-mail account.airwortheas@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 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2007–03–09, amendment 

39–14920 (72 FR 5157, February 5, 

2007). The existing AD applies to all 

Model A300 airplanes; Model A300 B4– 

601, B4–603, B4–620, B4–622, B4–605R, 

B4–622R, F4–605R, F4–622R, and C4– 

605R Variant F airplanes; and Model 

A310 airplanes. That NPRM was 

published in the Federal Register on 

October 10, 2008 (73 FR 60203). That 

NPRM proposed to continue to require 

revising the FAA-approved maintenance 

program to include a new airplane 

maintenance manual task that specifies 

a detailed inspection after each ram air 

turbine (RAT) retraction and, for certain 

airplanes, to continue to require 

replacing the aluminum yoke fitting of 

the swivel coupling of the RAT with a 

new steel yoke fitting. That NPRM also 

proposed to require replacing the RAT 

swivel coupling fork fitting for 

additional airplanes and revising the 

FAA-approved maintenance program to 

include procedures for replacing the 

RAT swivel coupling fork fitting with a 

new steel part only. 

Actions Since NPRM Was Issued 

The NPRM cited Airbus Mandatory 

Service Bulletin A300–57–0244, dated 

March 4, 2005, as the appropriate source 

of service information for procedures to 

replace the RAT swivel coupling fork 

fitting with a new steel fitting. Airbus 

has since revised that service bulletin. 

Revision 01, dated September 3, 2007, 

of that service bulletin includes revised 

installation procedures. The procedures 

in Revision 02, dated November 19, 

2007, of that service bulletin are 

essentially the same as those in Revision 

01, dated September 3, 2007. 

We have revised paragraphs (f) and 

(h) of this AD to refer to Revision 02 of 

Airbus Mandatory Service Bulletin 

A300–57–0244. We have also added a 

new paragraph (k) to this AD to give 

credit for actions done in accordance 

with Revision 01 of Airbus Mandatory 

Service Bulletin A300–57–0244. 

We have also revised paragraph (f) to 

refer to Airbus Mandatory Service 

Bulletins A310–57–2086, Revision 01, 

dated September 3, 2007; and A300–57– 

6099, Revision 01, dated September 3, 

2007. We referred to the original issue 

of Airbus Mandatory Service Bulletin 

A310–57–2086, dated March 1, 2005; 

and Airbus Mandatory Service Bulletin 

A300–57–6099, dated February 23, 

2005; for the replacement in paragraph 

(f) of the NPRM. The replacement 

procedures specified in Revision 01 of 

these service bulletins are identical to 

those in the original issue of these 

service bulletins. 

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 Revise the Applicability 

Airbus requests that modification 

19578 be removed from Table 1 in the 

NPRM because this modification applies 

to the A300F4–608ST model only. This 

model is not included on any U.S.-type 

certificate and is not referenced in 

paragraph (c) of the NPRM. 

We agree. Airbus Model A300F4– 

608ST is not included on any U.S.-type 

certificate; therefore, we have removed 

the reference to the modification for this 

model from Table 1 of this AD. 

Request for Revising Requirements 

The Air Transport Association (ATA), 

on behalf of its member American 

Airlines (AA), requests that paragraph 

(g) of the NPRM be revised to coincide 

with the requirements of paragraph (k) 

of the NPRM. AA finds that paragraphs 

(g) and (k) of the NPRM require similar 

actions. 

AA states that paragraph (g) of the 

NPRM would require changes to the 

FAA-approved maintenance program; 

specifically, changes to select AMM 

chapters are required, with a mandate to 

replace broken yoke fittings with new 

steel or aluminum parts. AA states that 

these AMM chapters are cited by both 

page block and date. AA states that 

paragraph (k) of the NPRM would 

similarly require changes to the 

maintenance program, and also would 

mandate changes to AMM sections; 

however, in paragraph (k) of the NPRM, 

specific revision dates of the AMM 

sections in question are not discussed. 

AA states that furthermore, paragraph 

(k) of the NPRM would require that a 

broken yoke be replaced with only a 

new steel part; paragraph (g) of the 

NPRM would authorize the use of an 

aluminum part. AA states that the 

requirements of paragraph (k) of the 

NPRM include the updated requirement 

to use only the steel yoke as a 

replacement. AA also states that 

paragraph (k) of the NPRM, unlike 

paragraph (g) of the NPRM, does not cite 

specific revision dates, allowing 

operators necessary latitude for 

incorporating future AMM revisions. 

We find that clarification is necessary. 

Paragraph (g) of this final rule restates 

the requirements from superseded AD 

2007–03–09, and paragraph (l) of this 

final rule (referred to as paragraph (k) in 

the NPRM) provides the new 

requirements. Performing the actions in 

paragraph (l) of this AD terminates the 

requirements of paragraph (g) of this 

AD. However, the requirements of 

paragraph (g) of this AD must be 

retained to ensure that applicable 

requirements of this AD are done. 

Paragraph (g) of this final rule states that 

the actions must be accomplished in 

accordance with the service 

information; therefore that service 

information contains specific revision 

numbers and dates. Paragraph (k) 

provides additional information; 

therefore, that information does not 

contain specific dates. 

We have clarified paragraphs (g) and 

(l) of this AD to specify the actions are 

to be done in accordance with a method 

approved by the FAA or Direction 

Ge ́ne ́rale de l’Aviation Civile (DGAC) or 

European Aviation Safety Agency 

(EASA). Also, we have added Notes 2 

and 4 of this final rule to specify where 

the information pertaining to the 

replacement and inspection procedures 

can be found. 


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29114 Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations 

Request for Alternative Replacement 

Procedures 

The ATA, on behalf of its member 

AA, requests that the yoke replacement 

not be limited to the accomplishment 

procedures contained in Airbus 

Mandatory Service Bulletin A300–57– 

6099. AA requests that alternative 

replacement procedures be incorporated 

into the final rule. 

We disagree. We find that the 

procedures included Airbus Mandatory 

Service Bulletin A300–57–6099 provide 

an adequate level of safety. However, we 

have no evidence that any alternative 

procedures not included in that service 

bulletin would provide an adequate 

level of safety. An operator may apply 

for approval of an alternative method of 

compliance (AMOC) in accordance with 

the procedures outlined in paragraph 

(m) of this AD. We have not changed the 

final rule regarding this issue. 

Explanation of Changes to Paragraphs 

(g) and (l) of This AD and Additions of 

Note 2 and Note 4 in This AD 

We have revised paragraphs (g) and (l) 

of this AD and have added Note 2 and 

Note 4 to this AD to clarify the 

requirements of those paragraphs. The 

revised paragraphs (g) and (l) specify the 

actions are to be done in accordance 

with a method approved by the FAA. 

However, we have added Notes 2 and 4 

to specify where information pertaining 

to the replacement and inspection 

procedures can be found. We have also 

moved Note 1 to the applicability 

section. 

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 

changes described previously. We have 

determined that these changes 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 ...................... 14 $80 $470 .................................... $1,590 205 $325,950 

Revision of FAA-approved 

maintenance program.

1 80 None .................................... 80 205 16,400 

In consideration of the compliance 

time and effective date for 

accomplishing the replacement and 

revision of the FAA-approved 

maintenance program required by AD 

2007–03–09 (retained in paragraphs (f) 

and (g) of this AD), we assume that 

operators of the affected airplanes have 

already initiated the required actions. 

The AD adds no new costs associated 

with those airplanes. 

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 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 39–14920 (72 

FR 5157, February 5, 2007) and by 

adding the following new airworthiness 

directive (AD): 

2009–12–02 Airbus: Amendment 39–15925. 

Docket No. FAA–2008–1082; Directorate 

Identifier 2007–NM–337–AD. 

Effective Date 

(a) This AD becomes effective July 24, 

2009. 

Affected ADs 

(b) This AD supersedes AD 2007–03–09. 

Applicability 

(c) This AD applies to all Model A300 

airplanes; Model A300 B4–601, B4–603, B4– 

620, B4–622, B4–605R, B4–622R, F4–605R, 

F4–622R, and C4–605R Variant F airplanes; 

and Model A310 airplanes, certificated in 

any category. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. 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 inspections, the 

operator may not be able to accomplish the 


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Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations 29115 

inspections 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 (m) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued damage tolerance of the affected 

structure. The FAA has provided guidance 

for this determination in Advisory Circular 

(AC) 25–1529–1. 

Unsafe Condition 

(d) This AD results from a report that an 

additional swivel coupling of the ram air 

turbine (RAT) yoke fitting was found cracked 

while accomplishing the requirements of the 

existing AD. We are issuing this AD to 

prevent misrigging of the ejection jack of the 

RAT and to ensure removal of any RAT yoke 

fitting made from aluminum material. Such 

conditions could result in a broken or 

cracked swivel coupling and consequent 

failure of the RAT yoke fitting, which could 

result in the loss of RAT function and 

possible loss of critical flight control systems 

in the event of certain emergency situations. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Certain Requirements of AD 2007–03–09 

Replacement 

(f) For Model A300 airplanes, Model 

A300–600 series airplanes, and Model A310 

airplanes equipped with Dowty Rotol RATs, 

except airplanes on which Airbus 

Modification 12986 has been done: Within 12 

months after March 12, 2007 (the effective 

date of AD 2007–03–09), replace the RAT 

swivel coupling fork fitting with a new steel 

fitting, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–0244, dated March 

4, 2005, or Airbus Mandatory Service 

Bulletin A300–57–0244, Revision 02, dated 

November 19, 2007 (for Model A300 

airplanes); Airbus Service Bulletin A300–57– 

6099, dated February 23, 2005, or Airbus 

Mandatory Service Bulletin A300–57–6099, 

Revision 01, dated September 3, 2007 (for 

Model A300–600 series airplanes); or Airbus 

Service Bulletin A310–57–2086, dated March 

1, 2005, or Airbus Mandatory Service 

Bulletin A310–57–2086, Revision 01, dated 

September 3, 2007 (for Model A310 

airplanes); except as provided by paragraph 

(h) of this AD. 

Revisions of FAA-Approved Maintenance 

Program 

(g) For all airplanes: Within 3 months after 

March 12, 2007, incorporate information into 

the FAA-approved maintenance program to 

specify an inspection for breaks of the bottom 

flange of the RAT swivel coupling yoke 

fitting after each RAT retraction; and 

replacement of the RAT swivel coupling yoke 

fitting with a new aluminum or steel part as 

applicable; in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the Direction Ge ́ne ́rale 

de l’Aviation Civile (or its delegated agent); 

or the European Aviation Safety Agency (or 

its delegated agent). Thereafter, except as 

provided by paragraphs (l) and (m) of this 

AD, no alternative inspection intervals may 

be approved for the bottom flange of the RAT 

swivel coupling yoke fitting. 

Note 2: Guidance on the inspection and 

replacement procedures specified in 

paragraph (g) of this AD can be found in 

these documents as applicable: 

• Airbus A300–600 Aircraft Maintenance 

Manual (AMM), Chapter 29–25–00, Page 

Block 301, dated June 1, 2005. 

• Airbus A310 AMM, Chapter 29–25–00, 

Page Block 301, dated June 1, 2005. 

• Airbus A300 AMM Chapter 29–25–00, 

Page Block 301, dated March 1, 2006. 

Note 3: After revising the maintenance 

program to include the required periodic 

inspections according to paragraph (g) or (l) 

of this AD, operators do not need to make a 

maintenance log entry to show compliance 

with this AD every time those inspections are 

accomplished thereafter. 

New Requirements of This AD 

Revised Service Bulletins 

(h) As of the effective date of this AD, use 

only the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A310–57– 

2086, Revision 01, dated September 3, 2007 

(for Model A310 series airplanes); Airbus 

Mandatory Service Bulletin A300–57–6099, 

Revision 01, dated September 3, 2007 (for 

Model A300–600 series airplanes); or Airbus 

Mandatory Service Bulletin A300–57–0244, 

Revision 02, dated November 19, 2007 (for 

Model A300 airplanes), to do the 

replacement required by paragraph (f) of this 

AD. 

Replacement 

(i) For airplanes identified in Table 1 of 

this AD: Before 102 months since first flight, 

or within 12 months after the effective date 

of this AD, whichever occurs later, replace 

the aluminum yoke fitting of the swivel 

coupling of the RAT with a new steel yoke 

fitting, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–57–2086, 

Revision 01, dated September 3, 2007 (for 

Model A310 series airplanes); or Airbus 

Mandatory Service Bulletin A300–57–6099, 

Revision 01, dated September 3, 2007 (for 

Model A300–600 series airplanes). 

TABLE 1—AIRPLANES AFFECTED BY THE REQUIREMENTS OF PARAGRAPH (I) OF THIS AD 

Model— Except for those airplanes on which— Or on which— 

(1) A310 series airplanes equipped with Hamilton Sundstrand RAT.Airbus Modification 12986 has been done in 

production.

Airbus Service Bulletin A310-57-2086, dated 

March 1, 2005; or Airbus Mandatory Service Bulletin A310-57-2086, Revision 01, 

dated September 3, 2007; has been done 

in service. 

(2) A300–600 series airplanes equipped with 

Hamilton Sundstrand RAT.

Airbus Modification 12986 has been done in 

production.

Airbus Service Bulletin A300-57-6099, dated 

February 23, 2005; or Airbus Mandatory 

Service Bulletin A300-57-6099, Revision 01, 

dated September 3, 2007; has been done 

in service. 

Credit for Actions Performed According to 

Previous Service Bulletins 

(j) Replacements done before the effective 

date of this AD in accordance with Airbus 

Service Bulletin A310–57–2086, dated March 

1, 2005 (for Model A310 series airplanes); or 

Airbus Service Bulletin A300–57–6099, 

dated February 23, 2005 (for Model A300– 

600 series airplanes); are acceptable for 

compliance with the requirements of 

paragraph (i) of this AD. 

(k) Replacements done before the effective 

date of this AD in accordance with Airbus 

Service Bulletin A300–57–0244, Revision 01, 

dated September 3, 2007 (for Model A300 

airplanes), are acceptable for compliance 

with the requirements of paragraph (f) of this 

AD for the affected airplanes. 

Revision of FAA-Approved Maintenance 

Program 

(l) For all airplanes: Within 3 months after 

the effective date of this AD, incorporate 

information into the FAA-approved 

maintenance program to specify an 

inspection for breaks of the bottom flange of 

the RAT swivel coupling yoke fitting after 

each RAT retraction; and replacement of the 

RAT swivel coupling yoke fitting with a new 

steel part; in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or European Aviation 

Safety Agency (or its delegated agent). 

Thereafter, except as provided by paragraph 

(m) of this AD, no alternative inspection 

intervals may be approved for the bottom 

flange of the RAT swivel coupling yoke 

fitting. Accomplishing this incorporation 


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29116 Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations 

terminates the requirements of paragraph (g) 

of this AD. 

Note 4: Guidance on the inspection and 

replacement procedures specified in 

paragraph (l) of this AD can be found in these 

documents as applicable: 

• Airbus A300–600 AMM, Chapter 29–25– 

00, Page Block 301. 

• Airbus A310 AMM, Chapter 29–25–00, 

Page Block 301. 

• Airbus A300 AMM Chapter 29–25–00, 

Page Block 301. 

Alternative Methods of Compliance 

(AMOCs) 

(m) The Manager, International Branch, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Vladimir Ulyanov, Aerospace 

Engineer, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–1138; fax 

(425) 227–1149. Before using any approved 

AMOC on any airplane to which the AMOC 

applies, notify your principal maintenance 

inspector (PMI) or principal avionics 

inspector (PAI), as appropriate, or lacking a 

principal inspector, your local Flight 

Standards District Office. The AMOC 

approval letter must specifically reference 

this AD. 

Related Information 

(n) European Aviation Safety Agency 

(EASA) airworthiness directive 2007–0273, 

dated October 23, 2007, and French 

airworthiness directive F–2005–089, dated 

June 8, 2005, also address the subject of this 

AD. 

Material Incorporated by Reference 

(o) You must use the service information 

contained in Table 2 of this AD to do the 

actions required by this AD, as applicable, 

unless the AD specifies otherwise. 

TABLE 2—MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Airbus Mandatory Service Bulletin A300–57–0244 ................................................................................... 02 November 19, 2007. 

Airbus Mandatory Service Bulletin A300–57–6099 ................................................................................... 01 September 3, 2007. 

Airbus Mandatory Service Bulletin A310–57–2086 ................................................................................... 01 September 3, 2007. 

(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 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 May 20, 

2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–13146 Filed 6–18–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0261 Directorate 

Identifier 2009–CE–017–AD; Amendment 

39–15943; AD 2009–13–04] 

RIN 2120–AA64 

Airworthiness Directives; Dornier 

Luftfahrt GmbH Models Dornier 228– 

100, Dornier 228–101, Dornier 228–200, 

Dornier 228–201, Dornier 228–202, and 

Dornier 228–212 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued 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: 

Excessive wear on a guide pin of a power 

lever has been detected during inspections. 

The total loss of the pin could cause loss of 

the flight idle stop and lead to inadvertent 

activation of the beta mode in flight. The 

inadvertent activation of beta mode in flight 

can result in loss of control of the airplane. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective July 

24, 2009. 

On July 24, 2009, the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Greg 

Davison, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4130; fax: (816) 

329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (NPRM) to amend 

14 CFR part 39 to include an AD that 

would apply to the specified products. 

That NPRM was published in the 

Federal Register on April 23, 2009 (74 

FR 18477). That NPRM proposed to 

correct an unsafe condition for the 

specified products. The MCAI states: 

Excessive wear on a guide pin of a power 

lever has been detected during inspections. 

The total loss of the pin could cause loss of 

the flight idle stop and lead to inadvertent 

activation of the beta mode in flight. The 

inadvertent activation of beta mode in flight 

can result in loss of control of the airplane. 

For the reasons described above, this new 

EASA Airworthiness Directive (AD) 

introduces a repetitive detailed inspection of 

the guide pins of the power and condition 

levers and requires the replacement of the 

pins that exceed the allowable wear-limits. 


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