Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations 421 

237, both dated August 25, 2009; for related 

information. 

Material Incorporated by Reference 

(l) You must use 328 Support Services 

Service Bulletin SB–328–27–488, dated 

August 25, 2009; or 328 Support Services 

Service Bulletin SB–328J–27–237, dated 

August 25, 2009; as applicable, to do the 

actions required by this AD, unless the AD 

specifies otherwise. (The document date is 

only referenced on the odd-numbered pages 

of these documents.) 

(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 328 Support Services GmbH, 

Global Support Center, P.O. Box 1252, D– 

82231 Wessling, Federal Republic of 

Germany; telephone +49 8153 88111 6666; 

fax +49 8153 88111 6565; e-mail 

gsc.op@328support.de; Internet http:// 

www.328support.de. 

(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. 

(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 

December 17, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–32982 Filed 1–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0854; Directorate 

Identifier 2009–NM–261–AD; Amendment 

39–16559; AD 2011–01–06] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) 

that applies to 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 High Time Equipment (HTE) 

reviews conducted within the scope of the 

A310 aircraft Design Service Goal (DSG) 

extension work, Airbus discovered that the 

splined couplings and the sliding bearings of 

the flap transmission system could be 

affected by corrosion and wear, especially 

when their protective components such as 

wiper rings and rubber gaiters could become 

defective. 

This condition, if not detected and 

corrected, could degrade the functional 

integrity of the flap transmission system. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

February 9, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 9, 2011. 

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 September 23, 2010 (75 FR 

57880), and proposed to supersede AD 

2007–02–22, Amendment 39–14909 (72 

FR 3708, January 26, 2007). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states: 

During High Time Equipment (HTE) 

reviews conducted within the scope of the 

A310 aircraft Design Service Goal (DSG) 

extension work, Airbus discovered that the 

splined couplings and the sliding bearings of 

the flap transmission system could be 

affected by corrosion and wear, especially 

when their protective components such as 

wiper rings and rubber gaiters could become 

defective. 

This condition, if not detected and 

corrected, could degrade the functional 

integrity of the flap transmission system. 

For the reason described above, this AD 

requires repetitive inspections of the flap 

transmission system and associated 

components [for any missing, damaged, or 

incorrectly installed rubber gaiter, wiper 

rings and straps], and corrective action(s), 

depending on findings. [The corrective action 

is replacing missing, damaged, or incorrectly 

installed components.] 

This [EASA] AD has been revised to 

correct the compliance time of 400 flight 

cycles in paragraph (3) into 400 flight hours. 

In addition, paragraph (4) has been 

introduced to clarify that the corrective 

actions do not end the requirement to 

continue the repetitive inspections, and some 

editorial changes for reasons of 

standardization. These do not affect the 

requirements of this AD as originally 

intended. 

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 comment received. 

Request To Clarify Compliance Times 

in Paragraphs (h)(1) and (h)(2) of the 

NPRM 

FedEx (FedEx) requested that we 

clarify the compliance times in 

paragraphs (h)(1) and (h)(2) of the 

NPRM. FedEx stated that paragraph 

(h)(1) establishes the deadline for 

replacing defective components found 

before the effective date of the AD, and 

pointed out that paragraph (h)(2) should 

establish the deadline for replacing the 

defective components found after the 

effective date of the AD. 

We agree with the commenter. We 

removed ‘‘not’’ from paragraph (h)(2) of 

this final rule so that it now establishes 

the deadline for replacing the defective 

components after the effective date of 

the AD. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We determined that this change 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 

WReier-Aviles on DSKGBLS3C1PROD with RULES

422 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations 

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 affects about 

46 products of U.S. registry. 

The actions that are required by AD 

2007–02–22 and retained in this AD 

take about 3 work-hours per product, at 

an average labor rate of $85 per workhour. Based on these figures, the 

estimated cost of the currently required 

actions is $255 per product. 

We estimate that it will take about 3 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Based on these figures, we 

estimate the cost of this AD to the U.S. 

operators to be $11,730, or $255 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 

removing Amendment 39–14909 (72 FR 

3708, January 26, 2007) and adding the 

following new AD: 

2011–01–06 Airbus: Amendment 39–16559. 

Docket No. FAA–2010–0854; Directorate 

Identifier 2009–NM–261–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective February 9, 2011. 

Affected ADs 

(b) This AD supersedes AD 2007–02–22, 

Amendment 39–14909. 

Applicability 

(c) This AD applies to all Airbus Model 

A310–203, –204, –221, –222, –304, –322, 

–324, and –325 airplanes; certificated in any 

category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During High Time Equipment (HTE) 

reviews conducted within the scope of the 

A310 aircraft Design Service Goal (DSG) 

extension work, Airbus discovered that the 

splined couplings and the sliding bearings of 

the flap transmission system could be 

affected by corrosion and wear, especially 

when their protective components such as 

wiper rings and rubber gaiters could become 

defective. 

This condition, if not detected and 

corrected, could degrade the functional 

integrity of the flap transmission system. 

* * * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2007– 

02–22, With Revised Service Information 

and Reduced Compliance Time for 

Corrective Action 

Initial and Repetitive Inspections 

(g) Within 2,500 flight cycles after March 

2, 2007 (the effective date of AD 2007–02– 

22): Do a detailed inspection for any missing, 

damaged, or incorrectly installed wiper rings 

in the splined couplings of the flap 

transmission shafts; and a detailed inspection 

for any missing, damaged, or incorrectly 

installed rubber gaiters and straps on the 

sliding bearing/plunging joints of the flap 

transmission; in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–27–2099, dated 

February 17, 2006; or Airbus Mandatory 

Service Bulletin A310–27–2099, Revision 01, 

dated March 21, 2008. Repeat the inspections 

thereafter at intervals not to exceed 2,500 

flight cycles. After the effective date of this 

AD, use only Airbus Mandatory Service 

Bulletin A310–27–2099, Revision 01, dated 

March 21, 2008. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’ 

Corrective Actions 

(h) If any damaged, missing or incorrectly 

installed wiper rings, rubber gaiters, or straps 

are found during any inspection required by 

paragraph (g) of this AD: At the applicable 

time in paragraph (h)(1) or (h)(2) of this AD, 

replace the applicable component with a 

serviceable component in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A310–27–2099, dated 

February 17, 2006; or Airbus Mandatory 

Service Bulletin A310–27–2099, Revision 01, 

dated March 21, 2008. After the effective date 

of this AD, use only Airbus Mandatory 

WReier-Aviles on DSKGBLS3C1PROD with RULES

Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations 423 

Service Bulletin A310–27–2099, Revision 01, 

dated March 21, 2008. 

(1) For airplanes on which the inspection 

required by paragraph (g) of this AD has been 

done before the effective date of this AD: 

Within 400 flight cycles after accomplishing 

the inspection. 

(2) For airplanes on which the inspection 

required by paragraph (g) of this AD has been 

done on or after the effective date of this AD: 

Within 400 flight hours after accomplishing 

the inspection required by paragraph (g) of 

this AD. 

New Requirements of This AD 

Actions 

(i) Accomplishment of the actions required 

by paragraph (h) do not terminate the 

repetitive inspections required by paragraph 

(g) 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 

(j) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, Transport Airplane Directorate, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. Send information to ATTN: 

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. AMOCs 

approved previously in accordance with AD 

2007–02–22, Amendment 39–14909, are 

approved as AMOCs for the corresponding 

provisions of paragraphs (g) and (h) of 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 FAAapproved 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: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(k) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2006– 

0111R1, dated August 26, 2009; and Airbus 

Mandatory Service Bulletin A310–27–2099, 

Revision 01, dated March 21, 2008; for 

related information. 

Material Incorporated by Reference 

(l) You must use Airbus Mandatory Service 

Bulletin A310–27–2099, Revision 01, dated 

March 21, 2008, 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 

Airbus Mandatory Service Bulletin A310–27– 

2099, Revision 01, dated March 21, 2008, 

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. 

(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 

December 17, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–32987 Filed 1–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0701; Directorate 

Identifier 2010–NM–017–AD; Amendment 

39–16561; AD 2011–01–08] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Model F.28 Mark 0100 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) 

that applies to 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: 

Two reports have been received where, 

during inspection of the vertical stabilizer of 

F28 Mark 0100 aeroplanes, one of the bolts 

that connect the horizontal stabilizer control 

unit actuator with the dog-links was found 

broken (one on the nut side & one on the 

head side). In both occasions, the bolt shaft 

was still present in the connection and 

therefore the horizontal stabilizer function 

was not affected. If a single dog-link 

connection fails, the complete stabilizer load 

is taken up by the remaining dog-link 

connection. * * * 

To address and correct this unsafe 

condition EASA [European Aviation Safety 

Agency] issued AD 2007–0287 

[corresponding FAA AD 2008–22–14] that 

required a one-time inspection of the affected 

bolts, * * * and replacement of failed bolts 

with serviceable parts. EASA AD 2007–0287 

also required the installation of a tie wrap 

through the lower bolts of the horizontal 

stabilizer control unit, to keep the bolt in 

place in the event of a bolt head failure. 

Recent examination revealed that the bolts 

failed due to stress corrosion, attributed to 

excessive bolt torque. Investigation of the 

recently failed bolts showed that the 

modification as required by AD 2007–0287 is 

not adequate. 

* * * * * 

Loss of horizontal stabilizer function 

could result in partial 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 

February 9, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 9, 2011. 

WReier-Aviles on DSKGBLS3C1PROD with RULES