20496 Federal Register / Vol. 76, No. 71 / Wednesday, April 13, 2011 / Rules and Regulations 

Revision 1, dated September 15, 2010; for 

related information. 

Material Incorporated by Reference 

(p) You must use Fokker Service Bulletin 

SBF50–28–028, Revision 1, dated September 

15, 2010; and Fokker Service Bulletin 

SBF50–28–031, Revision 1, dated September 

15, 2010; as applicable; 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 Fokker Services B.V., 

Technical Services Dept., P.O. Box 231, 2150 

AE Nieuw-Vennep, the Netherlands; phone: 

+31 (0)252–627–350; fax: +31 (0)252–627– 

211; e-mail: 

technicalservices.fokkerservices@stork.com; 

Internet: http://www.myfokkerfleet.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 March 

22, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–7743 Filed 4–12–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0263; Directorate 

Identifier 2010–NM–105–AD; Amendment 

39–16653; AD 2011–08–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A340–541 and –642 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

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: 

An operator has reported cracks on the aft 

hinge FWD [forward] fittings of the NLG 

[nose landing gear] aft doors (Right Hand 

(RH) side or Left Hand (LH) side). The cracks 

extended by approximately 15 millimetres 

from the upper hole to the edge of the 

fittings. 

* * * Cracks on the NLG aft door fittings, 

if not corrected, could lead to the loss in 

flight of the door, possibly resulting in injury 

to persons on the ground or aeroplane 

damages. 

* * * * * 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective April 

28, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of April 28, 2011. 

We must receive comments on this 

AD by May 31, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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 this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (phone: 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

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 European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0028, 

dated February 23, 2010 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

An operator has reported cracks on the aft 

hinge FWD [forward] fittings of the NLG 

[nose landing gear] aft doors (Right Hand 

(RH) side or Left Hand (LH) side). The crack 

extended by approximately 15 millimetres 

from the upper hole to the edge of the 

fittings. 

Investigation has revealed that these cracks 

have initiated due to fatigue loads and 

propagated under bending load. Cracks on 

the NLG aft door fittings, if not corrected, 

could lead to the loss in flight of the door, 

possibly resulting in injury to persons on the 

ground or aeroplane damages. 

Consequently, in order to maintain the 

structural integrity of the NLG aft door aft 

hinge attachment fittings, this AD requires 

repetitive [detailed] inspections [for cracking] 

of the area and fittings replacement in case 

of finding [including repetitive high 

frequency eddy current inspections or 

fluorescent penetrant inspections for 

cracking of the area for certain findings until 

the replacement is done]. 

Required actions also include, for 

airplanes on which the forward fitting of 

the NLG aft door aft hinge is replaced, 

repetitive detailed inspections for 

cracking of the replaced fitting; and if 

any cracking is found, replacement of 

both forward and aft fittings by new 

fittings on the aft hinge of the affected 

NLG aft door. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A340–52–5016, including 

Appendices 01 and 02, Revision 02, 

dated August 25, 2010. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 


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Federal Register / Vol. 76, No. 71 / Wednesday, April 13, 2011 / Rules and Regulations 20497 

develop on other products of the same 

type design. 

There are no products of this type 

currently registered in the United States. 

However, this rule is necessary to 

ensure that the described unsafe 

condition is addressed if any of these 

products are placed on the U.S. Register 

in the future. 

Differences Between the 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 FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

FAA’s Determination of the Effective 

Date 

Since there are currently no domestic 

operators of this product, notice and 

opportunity for public comment before 

issuing this AD are unnecessary. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2011–0263; 

Directorate Identifier 2010–NM–105– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

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 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. 

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: 

2011–08–03 Airbus: Amendment 39–16653. 

Docket No. FAA–2011–0263; Directorate 

Identifier 2010–NM–105–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective April 28, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A340– 

541 and –642 airplanes; certificated in any 

category; all serial numbers. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 52: Doors. 

Reason 

(e) The mandatory continued airworthiness 

information (MCAI) states: 

An operator has reported cracks on the aft 

hinge FWD [forward] fittings of the NLG 

[nose landing gear] aft doors (Right Hand 

(RH) side or Left Hand (LH) side). The cracks 

extended by approximately 15 millimetres 

from the upper hole to the edge of the 

fittings. 

* * * Cracks on the NLG aft door fittings, 

if not corrected, could lead to the loss in 

flight of the door, possibly resulting in injury 

to persons on the ground or aeroplane 

damages. 

* * * * * 

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. 

Inspection 

(g) At the applicable time specified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD: 

Perform a detailed inspection of the aft hinge 

forward attachment fittings of the right and 

left NLG aft doors, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A340–52–5016, 

Revision 02, dated August 25, 2010. 

(1) For airplanes having accumulated less 

than 1,000 total flight cycles as of the 

effective date of this AD: Prior to the 

accumulation of 1,000 total flight cycles or 

within 100 flight cycles after the effective 

date of this AD, whichever occurs later. 

(2) For airplanes having accumulated 1,000 

or more total flight cycles, but less than 2,500 

total flight cycles as of the effective date of 

this AD: Within 100 flight cycles after the 

effective date of this AD. 

(3) For airplanes having accumulated 2,500 

or more total flight cycles as of the effective 

date of this AD: Within 50 flight cycles after 

the effective date of this AD. 

Repetitive Inspection 

(h) If no cracking is found during the 

inspection required by paragraph (g) of this 

AD, repeat the detailed inspection specified 

in paragraph (g) of this AD thereafter at 

intervals not to exceed 500 flight cycles. 

(i) If any cracking is found during any 

inspection required by paragraph (g) or (h) of 

this AD, before further flight, perform a high 

frequency eddy current (HFEC) inspection for 

cracking of the forward and aft attachment 

fittings of the aft hinge on the affected aft 


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20498 Federal Register / Vol. 76, No. 71 / Wednesday, April 13, 2011 / Rules and Regulations 

NLG door, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A340–52–5016, 

Revision 02, dated August 25, 2010. 

Repair 

(j) If an additional crack finding is made 

during any HFEC inspection required by 

paragraph (i) of this AD, before further flight, 

replace both forward and aft fittings with 

new fittings on the aft hinge of the affected 

NLG aft door, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A340–52–5016, 

Revision 02, dated August 25, 2010. 

(k) If no additional crack finding is made 

during any HFEC inspection required by 

paragraph (i) of this AD: Repeat the HFEC 

inspection specified in paragraph (i) of this 

AD thereafter at intervals not to exceed 10 

flight cycles; or perform a fluorescent 

penetrant inspection for cracking thereafter at 

intervals not to exceed 3 flight cycles, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A340–52–5016, Revision 02, dated 

August 25, 2010, until the replacement 

required by paragraph (k)(1) or (k)(2) of this 

AD is done. 

(1) If an additional crack is found during 

any inspection required by paragraph (k) of 

this AD, before further flight, replace both 

forward and aft fittings with new fittings on 

the aft hinge of the affected NLG aft door, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A340–52–5016, Revision 02, dated 

August 25, 2010. 

(2) If no additional crack finding is made 

during any HFEC inspection required by 

paragraph (i) of this AD, or repetitive HFEC 

inspection or fluorescent penetrant 

inspection required by paragraph (k) of this 

AD: Within 20 flight cycles after finding a 

crack during the most recent inspection 

required by paragraph (g) or (h) of this AD, 

replace both forward and aft fittings with 

new fittings on the aft hinge of the affected 

NLG aft door, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A340–52–5016, 

Revision 02, dated August 25, 2010. 

(l) For airplanes on which the forward 

fitting of the aft hinge of the NLG aft door is 

replaced in accordance with paragraph (j) or 

(k) of this AD: Prior to the accumulation of 

1,000 flight cycles on the forward fitting, 

perform the detailed inspection required in 

paragraph (g) of this AD, and thereafter the 

applicable repetitive inspection required in 

paragraph (h) of this AD, and apply the 

applicable actions required in paragraphs (i), 

(j), and (k) of this AD. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(m) Inspections accomplished before the 

effective date of this AD according to Airbus 

Mandatory Service Bulletin A340–52–5016, 

dated February 1, 2010; or Airbus Mandatory 

Service Bulletin A340–52–5016, Revision 01, 

dated March 30, 2010; are considered 

acceptable for compliance with the 

corresponding action specified in this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: The 

MCAI does not specify corrective action if 

cracking is found during a fluorescent 

penetrant inspection. This AD specifies 

replacing both forward and aft fittings with 

new fittings on the aft hinge of the affected 

nose landing gear aft door, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A340–52– 

5016, Revision 02, dated August 25, 2010. 

Other FAA AD Provisions 

(n) 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. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it 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. Information may be e-mailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding 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 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. 

Related Information 

(o) Refer to MCAI EASA Airworthiness 

Directive 2010–0028, dated February 23, 

2010; and Airbus Mandatory Service Bulletin 

A340–52–5016, Revision 02, dated August 

25, 2010; for related information. 

Material Incorporated by Reference 

(p) You must use Airbus Mandatory 

Service Bulletin A340–52–5016, excluding 

Appendix 01 and including Appendix 02, 

Revision 02, dated August 25, 2010, 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 Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone: +33 

5 61 93 36 96; fax: +33 5 61 93 45 80; e-mail: 

airworthiness.A330-A340@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 March 

25, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–8278 Filed 4–12–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0703; Directorate 

Identifier 2009–NM–093–AD; Amendment 

39–16654; AD 2011–08–04] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model CL–600–2C10 (Regional Jet 

Series 700, 701 & 702) Airplanes, 

Model CL–600–2D15 (Regional Jet 

Series 705) Airplanes, and Model CL– 

600–2D24 (Regional Jet Series 900) 

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) 

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: 

There have been four reports of loose or 

detached main landing gear torque link apex 

pin locking plate and the locking plate 

retainer bolt. This condition could result in 

torque link apex pin disengagement, heavy 

vibration during landing, damage to main 

landing gear components and subsequent 

main landing gear collapse. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 


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