Federal Register / Vol. 75, No. 29 / Friday, February 12, 2010 / Rules and Regulations 6849 

Signed this 4th day of February, 2010, in 

Washington, DC. 

Dave White, 

Chief, Natural Resources Conservation 

Service. 

[FR Doc. 2010–2814 Filed 2–11–10; 8:45 am] 

BILLING CODE 3410–16–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0613; Directorate 

Identifier 2009–NM–013–AD; Amendment 

39–16195; AD 2010–04–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310–221, –222, –322, –324, and –325 

Airplanes, and Model A300 B4–620, 

B4–622, B4–622R, and F4–622R 

Airplanes, Equipped With Pratt & 

Whitney PW4000 or JT9D–7R4 Series 

Engines 

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) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

During the year 2000, life extension 

exercise programs were launched for Airbus 

A310 and A300–600 aircraft. Certification of 

Extended Service Goal (ESG) is based on 

analysis, except for fan cowl and thrust 

reverser (T/R) latches, which are always 

certified by tests. 

* * * testing of the T/R door centre latch 

has shown that this does not meet the 

requirements for ESG. 

* * * * * 

The unsafe condition is possible failure 

of the T/R latch and detachment of the 

T/R from the airplane, which could 

result in structural damage and 

consequent reduced controllability of 

the airplane. We are issuing this AD to 

require actions to correct the unsafe 

condition on these products. 

DATES: This AD becomes effective 

March 19, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of March 19, 2010. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a 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 July 16, 2009 (74 FR 34516). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

During the year 2000, life extension 

exercise programs were launched for Airbus 

A310 and A300–600 aircraft. Certification of 

Extended Service Goal (ESG) is based on 

analysis, except for fan cowl and thrust 

reverser (T/R) latches, which are always 

certified by tests. 

Currently, the Airworthiness Limitation 

Item (ALI) task 54–50–28 for engine pylon T/ 

R hinges requires inspection every 1,200 

Flight Cycles (FC). An analysis performed by 

Airbus shows that forward and aft T/R door 

latches have been demonstrated successful 

for ESG, with inspection task every 1,200 FC. 

However, testing of the T/R door centre latch 

has shown that this does not meet the 

requirements for ESG. 

For the reason described above, this EASA 

AD requires the replacement of the T/R 

centre latches with serialized latches on LH 

[left hand] and RH [right hand] engines and 

repetitive [detailed] inspections [for cracking] 

of the serialized latches. In addition, this AD 

introduces a life limit of 18,000 FC for the 

serialized centre latches. 

The unsafe condition is possible failure 

of the T/R latch and detachment of the 

T/R from the airplane, which could 

result in structural damage and 

consequent reduced controllability of 

the airplane. The corrective action 

includes replacing the T/R latch if any 

surface crack is found during any 

inspection. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Support for the NPRM 

FedEx Express has no objections or 

comments on the content or technical 

details of the NPRM. 

Request To Reduce Applicability 

Airbus asks that Model A300 F4–605R 

airplanes be removed from the 

applicability specified in the NPRM. 

Airbus states that these airplanes are 

equipped with General Electric CF6– 

80C2A5 or CF6–80C2A5F engines. 

We agree with Airbus for the reasons 

provided. The actions required by this 

AD are not applicable to Model A300 

F4–605R airplanes and the MCAI does 

not refer to this model; therefore, we 

have removed that model from the 

applicability of this AD. 

Request To Add a Note 

Airbus also recommends that we 

include a note after paragraph (f)(2) of 

the NPRM that specifies that 

accomplishing ALI Task 54–50–28, 

which pertains to a detailed inspection 

of the engine cowl hinge fittings LH/RH, 

can be done when complying with the 

inspections required by paragraph (f)(2) 

of the AD. 

We agree with the recommendation 

from Airbus. While not mandatory, 

performing the specified ALI task at the 

same time as the inspection required by 

paragraph (f)(2) of this AD would be of 

benefit to operators and would help to 

maintain an acceptable level of safety on 

the airplanes. We have added a new 

Note 1 to this AD (and renumbered 

subsequent notes) to include this 

recommendation. 

Explanation of Clarification Made to 

the Service Bulletin References 

In paragraph (f)(2) of the NPRM, we 

refer to Airbus Mandatory Service 

Bulletins A300–78–6029 and A310–78– 

2030, both including Appendix 1, both 

dated October 3, 2008, as the 

appropriate sources of service 

information for doing the inspection. 

However, the Accomplishment 

Instructions of those service bulletins do 

not contain procedures for doing the 

inspection, and the Pratt & Whitney 

service bulletins that contain the 

inspection procedures are referred to 

only in the Reason section of the Airbus 

service bulletins. Therefore, for 

clarification, we have referenced Pratt & 

Whitney Service Bulletins PW4NAC 78– 

113 and PW7R4 78–182, both dated 

August 15, 2005; in paragraph (f)(2) of 

this AD as the appropriate sources of 

service information for doing the 

inspection. 

Explanation of Clarification Made to 

the NPRM 

We have clarified the inspection 

requirement contained in the NPRM. 

Whereas the NPRM specifies an 

‘‘inspection,’’ we have revised this AD to 


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6850 Federal Register / Vol. 75, No. 29 / Friday, February 12, 2010 / Rules and Regulations 

clarify that our intent is to require a 

detailed inspection. 

Conclusion 

We 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 determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a Note within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

47 products of U.S. registry. We also 

estimate that it will take about 30 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $80 per work-hour. 

Required parts will cost about $6,442 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$415,574, or $8,842 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2010–04–02 Airbus: Amendment 39–16195. 

Docket No. FAA–2009–0613; Directorate 

Identifier 2009–NM–013–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective March 19, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A310– 

221, –222, –322, –324, and –325 airplanes, 

and Model A300 B4–620, B4–622, B4–622R, 

and F4–622R airplanes, all serial numbers; 

certificated in any category; equipped with 

Pratt & Whitney PW4000 or JT9D–7R4 series 

engines. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 78: Engine exhaust. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During the year 2000, life extension 

exercise programs were launched for Airbus 

A310 and A300–600 aircraft. Certification of 

Extended Service Goal (ESG) is based on 

analysis, except for fan cowl and thrust 

reverser (T/R) latches, which are always 

certified by tests. 

Currently, the Airworthiness Limitation 

Item (ALI) task 54–50–28 for engine pylon 

T/R hinges requires inspection every 1,200 

Flight Cycles (FC). An analysis performed by 

Airbus shows that forward and aft T/R door 

latches have been demonstrated successful 

for ESG, with inspection task every 1,200 FC. 

However, testing of the T/R door centre latch 

has shown that this does not meet the 

requirements for ESG. 

For the reason described above, this EASA 

AD requires the replacement of the T/R 

centre latches with serialized latches on LH 

[left hand] and RH [right hand] engines and 

repetitive [detailed] inspections [for cracking] 

of the serialized latches. In addition, this AD 

introduces a life limit of 18,000 FC for the 

serialized centre latches. 

The unsafe condition is possible failure of 

the T/R latch and detachment of the T/R from 

the airplane, which could result in structural 

damage and consequent reduced 

controllability of the airplane. The corrective 

action includes replacing the T/R latch if any 

surface crack is found during any inspection. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Before the accumulation of 30,000 total 

flight cycles since first flight of the airplane, 

or within 1,200 flight cycles after the 

effective date of this AD, whichever occurs 

later: Replace the non-serialized T/R center 

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

sides, having part number (P/N) 221D0029– 

11 and P/N 221D0029–13, with a serialized 

T/R center latch having P/N 221D0029–15 in 


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Federal Register / Vol. 75, No. 29 / Friday, February 12, 2010 / Rules and Regulations 6851 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A300–78–6029 (for Model A300 B4– 

620, B4–622, B4–622R, and F4–622R 

airplanes) or A310–78–2030 (for Model 

A310–221, –222, –322, –324, and –325 

airplanes), both including Appendix 1, both 

dated October 3, 2008. 

(2) Within 1,200 flight cycles after 

accomplishing the replacement required by 

paragraph (f)(1) of this AD: Perform a 

detailed inspection for surface cracking of the 

T/R center serialized latches having P/N 

221D0029–15, in accordance with the 

Accomplishment Instructions of Pratt 

&Whitney Service Bulletins PW4NAC 78–113 

(for airplanes equipped Pratt & Whitney 

PW4000 series engines) and PW7R4 78–182 

(for airplanes equipped JT9D–7R4 series 

engines), both dated August 15, 2005; as 

applicable. If any crack is found, before 

further flight, replace the serialized T/R 

center latch with a new serialized T/R center 

latch in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–78–6029 

or A310–78–2030, both including Appendix 

1, both dated October 3, 2008; as applicable. 

Repeat the inspection thereafter at intervals 

not to exceed 1,200 flight cycles. 

Note 1: Concurrent accomplishment of the 

inspections required by paragraph (f)(2) of 

this AD, with the inspections for engine 

pylon T/R hinges specified by ALI Task 54– 

50–28, is recommended. 

(3) Before the accumulation of 18,000 total 

flight cycles since accomplishing the most 

recent replacement required by paragraph 

(f)(1) or (f)(2) of this AD: Replace the 

serialized T/R center latch having P/N 

221D0029–15 with a new serialized T/R 

center latch having P/N 221D0029–15 in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A300–78–6029 (for Model A300 B4– 

620, B4–622, B4–622R, and F4–622R) or 

A310–78–2030 (for Model A310–221, –222, 

–322, –324, and –325 airplanes), both 

including Appendix 1, both dated October 3, 

2008. Replacement of the center latches does 

not constitute terminating action for the 

repetitive inspections required by paragraph 

(f)(2) of this AD. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2125; 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. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

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

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2008– 

0226, dated December 19, 2008; and the 

service information contained in Table 1 of 

this AD; for related information. 

TABLE 1—RELATED SERVICE INFORMATION

Document Date 

Airbus Mandatory Service Bulletin A300–78–6029, including Appendix 1 ................................................................................. October 3, 2008. 

Airbus Mandatory Service Bulletin A310–78–2030, including Appendix 1 ................................................................................. October 3, 2008. 

Pratt & Whitney Service Bulletin PW4NAC 78–113 ................................................................................................................... August 15, 2005. 

Pratt & Whitney Service Bulletin PW7R4 78–182 ...................................................................................................................... August 15, 2005. 

Material Incorporated by Reference 

(i) 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 Date 

Airbus Mandatory Service Bulletin A300–78–6029, including Appendix 1 ................................................................................. October 3, 2008. 

Airbus Mandatory Service Bulletin A310–78–2030, including Appendix 1 ................................................................................. October 3, 2008. 

Pratt & Whitney Service Bulletin PW4NAC 78–113 ................................................................................................................... August 15, 2005. 

Pratt & Whitney Service Bulletin PW7R4 78–182 ...................................................................................................................... August 15, 2005. 

(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 January 

28, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–2601 Filed 2–11–10; 8:45 am] 

BILLING CODE 4910–13–P 


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