12550 Federal Register / Vol. 72, No. 51 / Friday, March 16, 2007 / Rules and Regulations 

discovery of propeller control cables with a 

defective crimping. Two cable ends were 

found uncrimped at the factory after an 

engine run-up test, and one cable end was 

also found uncrimped on the first 100-hour 

time-in-service aircraft maintenance check. If 

not corrected, an incorrect crimping of the 

propeller control lever cable could generate 

a decrease of the propeller revolutions per 

minute which could result in loss of power. 

Actions and Compliance 

(e) Unless already done, within the next 50 

hours time-in-service (TIS) after April 20, 

2007 (the effective of this AD), inspect for the 

batch number identification and replace 

defective control cables as necessary in 

accordance with the paragraph B. of the 

‘‘ACCOMPLISHMENT INSTRUCTIONS’’ of 

EADS SOCATA TBM Aircraft Mandatory 

Alert Service Bulletin SB 70–123, dated 

October 2004. 

FAA AD Differences 

Note: This AD differs from the MCAI, the 

French Direction ge ́ne ́rale de l’ aviation civile 

(DGAC) AD No. F–2004–175, dated 

November 10, 2004, as follows: 

(1) The requirement of paragraph 3.1 of 

DGAC AD No. F–2004–175, dated November 

10, 2004, was based on the urgency in 

November 2004. However, in 2007, this 

action is not necessary. 

(2) For the requirement of paragraph 3.2 of 

DGAC AD No. F–2004–175, dated November 

10, 2004, the FAA has determined the 

seriousness of the condition does not warrant 

a compliance time of 25 hours TIS; we 

require instead a compliance time of 50 

hours TIS. 

Other FAA AD Provisions 

(f) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Staff, 

FAA, ATTN: Albert J. Mercado, Aerospace 

Safety Engineer, FAA, Small Airplane 

Directorate, 901 Locust, Room 301, Kansas 

City, Missouri 64106; telephone: (816) 329–

4119; fax: (816) 329–4090, has the authority 

to approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Before using any approved AMOC on any 

airplane to which the AMOC applies, notify 

your appropriate principal inspector (PI) in 

the FAA Flight Standards District Office 

(FSDO), or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(g) Refer to Direction Ge ́ne ́rale de l’

Aviation Civile Airworthiness Directive No. 

F–2004–175, dated November 10, 2004 (the 

MCAI); and EADS SOCATA TBM Aircraft 

Mandatory Alert Service Bulletin SB 70–123, 

dated October 2004, for related information. 

Material Incorporated by Reference 

(h) You must use EADS SOCATA TBM 

Aircraft Mandatory Alert Service Bulletin SB 

70–123, dated October 2004, to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact EADS SOCATA, Direction 

des Services, 65921 Tarbes Cedex 9, France; 

telephone: 33 (0)5 62.41.73.00; fax: 33 (0)5 

62.41.76.54; or SOCATA AIRCRAFT, INC., 

North Perry Airport, 7501 Airport Road, 

Pembroke Pines, Florida 33023; telephone: 

(954) 893–1400; fax (954) 964–4141. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Room 506, Kansas City, 

Missouri 64106; or at the National Archives 

and Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/ 

cfr/ibr-locations.html. 

Issued in Kansas City, Missouri, on March 

9, 2007. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–4736 Filed 3–15–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22036; Directorate 

Identifier 2005–NM–009–AD; Amendment 

39–14994; AD 2007–06–13] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

Series Airplanes, and Model C4–605R 

Variant F Airplanes (Collectively Called 

A300–600 Series Airplanes); and Model 

A310 Airplanes; Equipped With 

General Electric CF6–80A3 or CF6–

80C2 Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus airplane models, as specified 

above. This AD requires installing 

electro-pneumatic locking bar devices 

(TRAS lock systems) in the engine 

nacelles, installing a dedicated and 

shielded electrical circuit that is 

segregated from the existing thrust 

reverser control system, and performing 

related investigative/corrective actions 

if necessary. This AD results from the 

manufacturer’s reassessment of the 

thrust reverser systems in the Airbus 

airplane models specified above, which 

showed that the thrust reverser could 

inadvertently deploy in flight under 

certain conditions. We are issuing this 

AD to prevent inadvertent deployment 

of thrust reversers in flight, which could 

result in reduced controllability of the 

airplane. 

DATES: This AD becomes effective April 

20, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of April 20, 2007. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2797; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (AD) docket on the Internet at 

http://dms.dot.gov or in person at the 

Docket Management Facility office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to certain Airbus Model A300 B2 

and B4 series airplanes; Model A300 

B4–600, B4–600R, and F4–600R series 

airplanes, and Model C4–605R Variant F 

airplanes (collectively called A300–600 

series airplanes); and Model A310 series 

airplanes; equipped with General 


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Electric (GE) CF6–80A3 or CF6–80C2 

engines. That NPRM was published in 

the Federal Register on August 8, 2005 

(70 FR 45595). That NPRM proposed to 

require installing electro-pneumatic 

locking bar devices (TRAS lock systems) 

in the engine nacelles, installing a 

dedicated and shielded electrical circuit 

that is segregated from the existing 

thrust reverser control system, and 

performing related investigative/ 

corrective actions if necessary. 

Since the Issuance of the NPRM 

We have received copies of the 

following Airbus service bulletins: 

• Airbus Service Bulletin A300–78–

6024, Revision 01, dated April 22, 2005. 

Revision 01 describes essentially the 

same procedures specified in the 

original issue of the service bulletin, 

dated October 7, 2003 (referenced in the 

NPRM as one appropriate source of 

service information). Revision 01 also 

adds technical notes referring to certain 

Middle River Aircraft Systems (MRAS) 

proprietary data 491B1200200, 

491B1200201, 491B1200202, and 

491B1200203, Revision B, dated 

September 9, 2003, which provide 

instructions to install the electropneumatic locking bar devices in the 

nacelles on GE Model CF6–80C2 

engines with a full authority digital 

engine control (FADEC) thrust reverser 

system, as additional sources of service 

information. 

• Airbus Service Bulletin A300–78–

6025, Revision 01, dated April 22, 2005. 

Revision 01 describes essentially the 

same procedures specified in the 

original issue of the service bulletin, 

dated October 7, 2003 (referenced in the 

NPRM as one appropriate source of 

service information). Revision 01 also 

adds technical notes referring to certain 

MRAS proprietary data 491B1200202 

and 491B1200203, both Revision B, both 

dated September 9, 2003, as additional 

sources of service information. The 

proprietary data provide instructions to 

install the electro-pneumatic locking bar 

devices in the nacelles on GE Model 

CF6–80C2 engines with a power 

management control (PMC) thrust 

reverser system. 

• Airbus Service Bulletin A310–78–

2023, Revision 01; and Airbus Service 

Bulletin A310–78–2025, Revision 01; 

both dated April 22, 2005. These service 

bulletins were issued to advise 

operators of the issuance of technical 

notes referenced in MRAS proprietary 

data 603A1000, 603A1001, 603A2000, 

603A2001, and 603A2100. The 

proprietary data provides instructions to 

install the electro-pneumatic locking bar 

devices, as additional sources of service 

information. (Airbus Service Bulletin 

A310–78–2023, dated October 7, 2003; 

and Airbus Service Bulletin A310–78–

2025, dated July 23, 2004; were 

referenced as appropriate sources of 

service information in the NPRM.) 

• Airbus Service Bulletin A310–78–

2022, Revision 02, including 

Appendices 01 and 02, dated July 18, 

2006. (The original version of this 

service bulletin, dated January 7, 2003, 

was referenced as an appropriate source 

of service information in the NPRM.) 

Revision 02 updates certain figures 

referenced in the original version of the 

service bulletin. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Request To Withdraw the NPRM 

One commenter, American Airlines, 

states that it appears inconsistent to 

invest a significant amount of money for 

additional protection by installing 

electro-pneumatic locking bar devices 

(TRAS lock system). The commenter 

points out that the FAA has previously 

extended the inspection interval of 

current mandated inspections in 

another existing AD that also addresses 

inadvertent thrust reverser deployment. 

We infer that American Airlines is 

questioning the cost benefit of the 

additional protection that the AD 

provides, and would like us to 

withdraw the NPRM. We acknowledge 

that, although we have extended the 

inspection intervals due to positive 

results of past inspections, the 

possibility still exists that a directional 

pilot valve (DPV) leak may occur. This 

type of leak is a hidden failure that 

cannot be detected at the system level, 

and could result in inadvertent thrust 

reverser deployment. We have 

determined that installation of electropneumatic locking bar devices will 

ensure an adequate measure of 

protection for the system. No change is 

necessary to the AD in this regard. 

Requests To Revise the Applicability 

Two commenters, Tradewinds 

Airlines and GE Transportation, request 

that the applicability stated in the 

NPRM be revised by removing Airbus 

Model A300 B2 and B4 series airplanes. 

One commenter points out that those 

models are not specified in the French 

airworthiness directive, and that there 

are no service bulletins specified in the 

NPRM that are applicable to those 

models. 

We agree with the commenters. We 

acknowledge that the Model A300 B2 

and B4 series airplanes are not equipped 

with the affected engines and were 

inadvertently included in the NPRM. 

The applicability of this AD is revised 

to remove those airplane models. 

Another commenter, Airbus, requests 

that the associated modification 

numbers for the corresponding service 

bulletins be added to the applicability of 

the NPRM. Airbus suggests that adding 

the associated modification numbers 

will make it easier for operators to 

comply with the AD and will help 

operators to avoid having to request 

alternative methods of compliance. 

We partially agree with the 

commenter’s request in this case. The 

applicability of French airworthiness 

directive F–2004–165 excludes 

airplanes on which Airbus Service 

Bulletins A310–78–2024; A310–78–

2025; A310–78–2022; A310–78–2023, 

A300–78–6022, Revision 1; A300–78–

6025; A300–78–6021 original issue or 

Revision 01; and A300–78–6024; have 

been accomplished in-service, as well as 

certain modifications accomplished 

during production. We agree that 

revising the applicability of the final 

rule is necessary to exclude airplanes on 

which certain modifications have been 

accomplished during production. 

However, as is our standard practice, we 

have not excluded those airplanes that 

have accomplished certain 

modifications in service in the 

applicability of this final rule. Rather, 

this final rule includes requirements to 

accomplish the actions specified in the 

service bulletins that clearly identify the 

airplanes that the service bulletins 

affect. The requirements of the specified 

service bulletins will ensure that the 

actions required by this final rule are 

accomplished on all affected airplanes. 

Operators must continue to operate the 

airplane in the configuration required 

by this final rule unless an alternative 

method of compliance is approved. We 

have, however, added a new Note 1 and 

Table 2 to this final rule that provide a 

list of corresponding modifications with 

the applicable service bulletins for ease 

of reference for the operators. We have 

re-identified subsequent notes and 

tables accordingly. 

Requests To Revise the ‘‘Costs of 

Compliance’’ Section 

Several commenters, including theAir 

Transport Association (ATA), on behalf 

of one of its members, American 

Airlines, and FedEx and GE 

Transportation, request that the 

estimated costs of complying with the 

NPRM be revised to add additional 

work hours. American Airlines states 

that the NPRM would require 

concurrent accomplishment of four 

service bulletins that are not specified 


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in the NPRM. American Airlines 

estimates it will take 600 work hours 

and $283,042 for parts per each of its 

airplanes, rather than the costs 

estimated in the applicable service 

bulletins in the NPRM for various 

airplane models. FedEx explains that 

the cost estimates in the NPRM are not 

realistic because additional 

modification requirements are necessary 

that are described in MRAS and 

Goodrich/Rohr technical documents. 

One commenter, GE Transportation, 

also points out that certain cost 

information is available in certain 

service information that is not referred 

to in the NPRM. 

We acknowledge that certain 

estimated costs were not included in the 

NPRM. We have obtained the additional 

service information from MRAS, but it 

does not contain estimated cost 

information. We also have requested 

further information from one of the 

commenters, GE Transportation, which 

has provided some new cost 

information figures to us. We have 

revised the estimated costs of the AD by 

including the estimated costs of 

accomplishing the MRAS service 

bulletins. We have coordinated those 

estimated costs with Airbus. 

Request To Clarify ‘‘Relevant Service 

Information’’ Section 

GE Transportation suggests certain 

revised wording regarding the work 

tasks described in the service bulletins 

specified in the ‘‘Relevant Service 

Information’’ section of the NPRM. 

We consider that the descriptions of 

the work tasks in the NPRM adequately 

describe those tasks. Since that section 

of the preamble in the NPRM does not 

reappear in the final rule, no change to 

the AD is necessary. 

Request To Consider the Possibility of 

No Deployment 

American Airlines requests that we 

consider the possibility that an increase 

in risk of no deployment on landing 

may occur with the modification 

installed. American Airlines states that 

the modification could affect reliable 

operations in those airports restricted by 

short runway lengths when employing 

the Minimum Equipment List 

provisions. 

We acknowledge the commenter’s 

concern. In its reassessment of thrust 

reverser reliability, the manufacturer 

considered the possibility of thrust 

reverser non-deployment on landing 

with the third line of defense (TLOD) 

system installed. The reassessment 

showed that the thrust reverser without 

the TLOD could inadvertently deploy in 

flight under certain conditions, which 

could lead to decreased aircraft 

controllability. We have determined that 

the basic two-line-of-defense 

architecture does not adequately 

address the system’s vulnerability to 

damage and long-term maintainability. 

Therefore, the modification is necessary 

to prevent the identified unsafe 

condition. In addition, we have not seen 

an increase in occurrences of thrust 

reverser nondeployments on landing for 

aircraft that have a TLOD or other thrust 

reverser third lock-type system 

installed. No change to the AD is 

necessary regarding this issue. 

Request To Use Latest Service Bulletin 

Revisions 

Several commenters, including the 

ATA, on behalf of one of its members, 

American Airlines, and FedEx, note that 

new revisions of certain service 

bulletins have been issued since the 

issuance of the NPRM. The commenters 

are requesting that we mandate the new 

revisions, which contain test procedures 

that will take less time for the operators 

to accomplish. 

We agree with the commenters. We 

have received certain newer revisions of 

the service bulletins (described 

previously) from the manufacturer and 

have specified those revisions in Table 

3 of the AD. Additionally, we received 

new revisions of the service bulletins 

specified in Table 2 of the AD from the 

manufacturer. We have revised Table 2 

of the AD accordingly. 

Explanation of Change to Applicability 

We have revised the applicability of 

the AD to identify model designations 

as published in the most recent type 

certificate data sheet for the affected 

models. 

Clarification of Alternative Method of 

Compliance (AMOC) Paragraph 

We have revised this action to clarify 

the appropriate procedure for notifying 

the principal inspector before using any 

approved AMOC on any airplane to 

which the AMOC applies. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

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 significantly 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Costs of Compliance 

This AD affects about 101 airplanes of 

U.S. registry. (The total number of 

airplanes in the following table totals 

more than 101 airplanes because most of 

the airplanes are required to accomplish 

two of the specified service bulletins.) 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD at an average labor 

rate per hour of $80. 

ESTIMATED COSTS FOR MODIFICATIONS (LISTED BY APPLICABLE SERVICE BULLETIN) 

Airbus service bulletins (SB) Work 

hours Parts Cost per airplane 

Number of 

airplanes Cost per SB 

A300–78–6021, Revision 02 ............................................................................... 257 $19,652 $40,212 36 $1,447,632 

A300–78–6024, Revision 01 ............................................................................... 206 223,649 240,129 36 8,644,644 

A300–78–6022, Revision 02 ............................................................................... 289 19,220 42,340 34 1,439,560 

A300–78–6025, Revision 01 ............................................................................... 206 223,649 240,129 34 8,164,386 

A310–78–2024, Revision 01 ............................................................................... 262 19,119 40,079 31 1,242,449 

A310–78–2025, Revision 01 ............................................................................... 206 194,487 210,967 31 6,539,977 

None of the airplanes required to 

accomplish the following service 

bulletins are currently on the U.S. 

Register. The airplanes affected by the 

following service bulletins are currently 

operated by non-U.S. operators under 

foreign registry; therefore, they are not 

directly affected by this AD action. 

However, we consider it necessary to 

include these airplanes to ensure that 

the unsafe condition is addressed if any 

affected airplane is imported and placed 

on the U.S. Register in the future. The 

estimated costs apply to any affected 


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airplane should it be imported and 

placed on the U.S. Register in the future. 

ESTIMATED COSTS FOR MODIFICATIONS FOR CERTAIN OTHER AIRPLANES

Airbus service bulletin (SB) Work 

hours Parts Cost per airplane 

A310–78–2022 ......................................................................................................................................................... 275 19,652 41,652 

A310–78–2023 ......................................................................................................................................................... 206 $223,649 $240,129 

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 adding the following new 

airworthiness directive (AD): 

2007–06–13 Airbus: Amendment 39–14994. 

Docket No. FAA–2005–22036; Directorate 

Identifier 2005–NM–009–AD. 

Effective Date 

(a) This AD becomes effective April 

20, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus series 

airplanes, certificated in any category, 

as identified in the service bulletins 

listed in Table 1 of this AD; except for 

those airplanes on which the following 

applicable modifications have been 

incorporated in production: Airbus 

Modification 12348, 12349, 12350, 

12514, and 12511. 

TABLE 1.—APPLICABILITY

Airplane models General Electric engine model Airbus service bulletin and 

revision Date 

A300 B4–605R and F4–605R airplanes ................................. CF6–80C2 .............................. A300–78–6024, Revision 01 April 22, 2005. 

A300 B4–605R and F4–605R airplanes ................................. CF6–80C2 .............................. A300–78–6021, Revision 02 June 8, 2005. 

A300 B4–601, B4–603, B4–605R, and C4–605R Variant F 

airplanes.

CF6–80C2 .............................. A300–78–6025, Revision 01 April 22, 2005. 

A300 B4–601, B4–603, B4–605R, and C4–605R Variant F 

airplanes.

CF6–80C2 .............................. A300–78–6022, Revision 02 June 8, 2005. 

A310 airplanes ......................................................................... CF6–80C2 .............................. A310–78–2023, Revision 01 April 22, 2005. 

A310 airplanes ......................................................................... CF6–80C2 .............................. A310–78–2022, Revision 02 July 18, 2006. 

A310 airplanes ......................................................................... CF6–80A3 .............................. A310–78–2024, Revision 01 June 13, 2005. 

A310 airplanes ......................................................................... CF6–80A3 .............................. A310–78–2025, Revision 01 April 22, 2005. 

Note 1: We have provided a list of 

corresponding modifications with the 

applicable Airbus service bulletins in Table 

2 of this AD for ease of reference for the 

operators. 

TABLE 2.—CORRESPONDING

MODIFICATIONS

Airbus service bulletin Modifications 

A310–78–2022 and 

A300–78–6022.

12348, 12350, 12351, 

and 12514. 

TABLE 2.—CORRESPONDING

MODIFICATIONS—Continued 

Airbus service bulletin Modifications 

A310–78–2023 and 

A300–78–6025.

12512. 


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TABLE 2.—CORRESPONDING

MODIFICATIONS—Continued 

Airbus service bulletin Modifications 

A310–78–2024 .......... 12552 and 12553. 

A310–78–2025 .......... 12564. 

A300–78–6021 .......... 12348, 12349, 12350, 

and 12514. 

A300–78–6024 .......... 12511. 

Unsafe Condition 

(d) This AD results from the 

manufacturer’s reassessment of the 

thrust reverser systems in the Airbus 

airplane models specified in Table 1 of 

this AD, which showed that the thrust 

reverser could deploy in flight under 

certain conditions. We are issuing this 

AD to prevent inadvertent deployment 

of thrust reversers in flight, which could 

result in reduced controllability of the 

airplane. 

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. 

Installing TRAS Lock Systems and 

Accomplishing Modifications 

(f) For airplanes identified in the 

service bulletins specified in Table 3 of 

this AD: Within 36 months after the 

effective date of this AD, install the 

electro-pneumatic locking bar devices 

(TRAS Lock Systems) in the thrust 

reverser system of the nacelles, in 

accordance with the Accomplishment 

Instructions of the applicable service 

bulletin. 

TABLE 3.—INSTALLING TRAS LOCK SYSTEMS

Airplane models General electric engine model Airbus service bulletin and 

revision Date 

A300 B4–605R and F4–605R airplanes ................................. CF6–80C2 .............................. A300–78–6024, Revision 01 April 22, 2005. 

A300 B4–601, B4–603, B4–605R, and C4–605R Variant F 

airplanes.

CF6–80C2 .............................. A300–78–6025, Revision 01 April 22, 2005. 

A310 airplanes ......................................................................... CF6–80C2 .............................. A310–78–2023, Revision 01 April 22, 2005. 

A310 airplanes ......................................................................... CF6–80A3 .............................. A310–78–2025, Revision 01 April 22, 2005. 

Note 2: Airbus Service Bulletin A310–78–

2025, Revision 01, dated April 22, 2005, 

references draft Goodrich Service Bulletin 

71–065 as an additional source of service 

information. After the issuance of Airbus 

Service Bulletin A310–78–2025, the 

Goodrich service bulletin was reissued as 

Rohr Service Bulletin CF6–80A3–NAC–71–

065, dated April 28, 2005. 

(g) For airplanes identified in the 

service bulletins specified in Table 4 of 

this AD: Prior to or concurrent with the 

accomplishment of the applicable 

service bulletin specified in paragraph 

(f) of this AD, accomplish all the 

modifications and actions related to an 

independent third line of defense on the 

thrust reversers, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin specified in 

Table 4 of this AD. 

TABLE 4.—PRIOR OR CONCURRENT ACCOMPLISHMENT

Airplane models Airplanes equipped with General Electric engine model 

Airbus service bulletin and 

revision Date 

A300 B4–605R and F4–605R airplanes ................................. CF6–80C2 (with full authority 

digital engine control 

(FADEC)).

A300–78–6021, Revision 02, 

including Appendices 01 

and 02.

June 8, 2005. 

A300 B4–601, B4–603, B4–605R, and C4–605R Variant F 

airplanes.

CF6–80C2 (without FADEC) A300–78–6022, Revision 02, 

including Appendices 01 

and 02.

June 8, 2005. 

A310 airplanes ......................................................................... CF6–80C2 (without FADEC) A310–78–2022 Revision 02, 

including Appendices 01 

and 02.

June 18, 2006. 

A310 airplanes ......................................................................... CF6–80A3 .............................. A310–78–2024 Revision 01, 

including Appendices 01 

and 02.

June 13, 2005. 

Actions Accomplished According to 

Previous Issues of Service Bulletins 

(h) Actions accomplished in 

accordance with the following service 

bulletins are acceptable for compliance 

with the requirements of this AD, as 

applicable, if done before the effective 

date of this AD: 

TABLE 5.—SERVICE BULLETINS ACCOMPLISHED PREVIOUSLY

Airbus service bulletin Revision level Date 

A300–78–6021 ........................................................................ Original ................................................................................... April 8, 2003. 

A300–78–6021 ........................................................................ 01 ............................................................................................ October 7, 2003. 

A300–78–6022 ........................................................................ 01 ............................................................................................ January 7, 2003. 

A300–78–6024 ........................................................................ Original ................................................................................... October 7, 2003. 

A300–78–6025 ........................................................................ Original ................................................................................... October 7, 2003. 

A310–78–2022 ........................................................................ Original ................................................................................... January 7, 2003. 

A310–78–2022 ........................................................................ 01 ............................................................................................ June 8, 2005. 


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TABLE 5.—SERVICE BULLETINS ACCOMPLISHED PREVIOUSLY—Continued 

Airbus service bulletin Revision level Date 

A310–78–2023 ........................................................................ Original ................................................................................... October 7, 2003. 

A310–78–2024 ........................................................................ Original ................................................................................... October 15, 2003. 

A310–78–2025 ........................................................................ Original ................................................................................... July 23, 2004. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if 

requested in accordance with the 

procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved 

in accordance with 14 CFR 39.19 on any 

airplane to which the AMOC applies, 

notify the appropriate principal 

inspector in the FAA Flight Standards 

Certificate Holding District Office. 

Related Information 

(j) French airworthiness directive F–

2004–165, dated October 13, 2004, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(k) You must use the applicable 

Airbus service bulletins specified in 

Table 6 of this AD to perform the 

actions that are required by this AD, 

unless the AD specifies otherwise. The 

Director of the Federal Register 

approved the incorporation by reference 

of these documents in accordance with 

5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for a copy of this service information. 

You may review copies at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington; 

or at the National Archives and Records 

Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, 

or go to: http://www.archives.gov/ 

federal-register/cfr/ibr-locations.html. 

TABLE 6.—MATERIAL INCORPORATED BY REFERENCE

Airbus service bulletin Revision level Date 

A300–78–6021, including Appendices 01 and 02 .................. 02 ............................................................................................ June 8, 2005. 

A300–78–6022, including Appendices 01 and 02 .................. 02 ............................................................................................ June 8, 2005. 

A300–78–6024 ........................................................................ 01 ............................................................................................ April 22, 2005. 

A300–78–6025 ........................................................................ 01 ............................................................................................ April 22, 2005. 

A310–78–2022, including Appendices 01 and 02 .................. 02 ............................................................................................ July 18, 2006. 

A310–78–2023 ........................................................................ 01 ............................................................................................ April 22, 2005. 

A310–78–2024, including Appendices 01 and 02 .................. 01 ............................................................................................ June 13, 2005. 

A310–78–2025 ........................................................................ 01 ............................................................................................ April 22, 2005. 

Issued in Renton, Washington, on March 5, 

2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–4734 Filed 3–15–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26324; Directorate 

Identifier 2006–NM–214–AD; Amendment 

39–14993; AD 2007–06–12] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330 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 

A330–300 airplanes. That AD currently 

requires reinforcement of the structure 

of the center fuselage by installing 

external stiffeners (butt straps) at frame 

(FR) 53.3 on the fuselage skin between 

left-hand (LH) and right-hand (RH) 

stringer (STR) 13, and related 

investigative and corrective actions. 

This new AD requires additional 

reinforcement of the structure of the 

center fuselage by installing external 

stiffeners (butt straps) at frame FR53.3 

on the fuselage skin between LH and RH 

STR13, and related investigative and 

other specified actions. This AD also 

adds airplanes to the applicability. This 

AD results from cracking found at the 

circumferential joint of FR53.3. We are 

issuing this AD to prevent fatigue 

cracking of the fuselage, which could 

result in reduced structural integrity of 

the fuselage. 

DATES: This AD becomes effective April 

20, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of April 20, 2007. 

On October 19, 2005 (70 FR 57732, 

October 4, 2005), the Director of the 

Federal Register approved the 

incorporation by reference of Airbus 

Service Bulletin A330–53–3127, 

Revision 01, dated November 21, 2003. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2797; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (AD) docket on the Internet at 

http://dms.dot.gov or in person at the 

Docket Management Facility office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Management Facility office 

(telephone (800) 647–5227) is located on 


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