This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

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REGISTER issue of each week.

Rules and Regulations Federal Register

19059 

Vol. 77, No. 62 

Friday, March 30, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0297; Directorate 

Identifier 2011–NM–093–AD; Amendment 

39–17003; AD 2012–06–22] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

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 all 

Airbus Model A340–500 and Model 

–600 series airplanes. This AD requires 

performing repetitive high frequency 

eddy current inspections of the external 

radius on upper horizontal cruciform 

fitting at frame (FR) 47 on the left- and 

right-hand sides for cracks, and 

repairing the cracks if necessary. This 

AD was prompted by reports that during 

fatigue testing, damages occurred in the 

external radius on the upper horizontal 

cruciform fitting at FR47 on the left- and 

right-hand sides. We are issuing this AD 

to detect and correct fatigue cracking, 

which could adversely affect the 

structural integrity of the airplane. 

DATES: This AD becomes effective April 

16, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of the service information listed in the 

AD as of April 16, 2012. 

We must receive comments on this 

AD by May 14, 2012. 

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 

W12–140, 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 (telephone 

(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 2011–0075, 

dated April 29, 2011 (referred to after 

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

condition for the specified products. 

The MCAI states: 

During the A340–600 EF2 fatigue test, 

damages occurred in external radius on 

upper horizontal cruciform in rear corner at 

FR47 respectively on Right-Hand-(RH) side 

and on Left-Hand-(LH) side. These damages 

were detected after tear down inspections 

using High Frequency Eddy Current method. 

This condition, if not corrected, could 

impair the structural integrity of the 

aeroplane. 

For the reasons described above, this 

[EASA] AD requires to perform repetitive 

Special Detailed Inspections for early 

detection of cracks on upper horizontal 

cruciform fitting at FR47 on LH and RH 

sides, and the accomplishment of corrective 

actions [repair], as applicable. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A340–57–5029, including 

Appendices 01 and 02, dated February 

25, 2011. 

For the initial inspection, the 

compliance time ranges between 4,450 

total flight cycles or 35,600 total flight 

hours and 9,750 total flight cycles or 

63,600 total flight hours, whichever 

occurs first, depending on airplane 

configuration. For the repetitive 

intervals, the compliance time ranges 

between 2,350 flight cycles or 19,000 

flight hours, whichever occurs first; and 

6,050 flight cycles or 46,200 flight 

hours, whichever occurs first, 

depending on airplane configuration. 

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 

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. 

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 


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19060 Federal Register / Vol. 77, No. 62 / Friday, March 30, 2012 / Rules and Regulations 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2012–0297; 

Directorate Identifier 2011–NM–093– 

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 the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. 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: 

2012–06–22 Airbus: Amendment 39– 

17003. Docket No. FAA–2012–0297; 

Directorate Identifier 2011–NM–093–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective April 16, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A340– 

541 and –642 airplanes, certificated in any 

category, all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57: Wings. 

(e) Reason 

This AD was prompted by reports that 

during fatigue testing, damages occurred in 

the external radius on the upper horizontal 

cruciform fitting at frame (FR) 47 on the leftand right-hand sides. We are issuing this AD 

to detect and correct fatigue cracking, which 

could adversely affect the structural integrity 

of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Inspection 

Before the accumulation of the applicable 

threshold specified in paragraph 1.E. 

Compliance, Table 2, of Airbus Mandatory 

Service Bulletin A340–57–5029, including 

Appendices 01 and 02, dated February 25, 

2011, or within 90 days after the effective 

date of this AD, whichever occurs later: Do 

a high frequency eddy current inspection of 

the external radius on upper horizontal 

cruciform fitting at FR47 on the left- and 

right-hand sides for cracks, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A340–57– 

5029, including Appendices 01 and 02, dated 

February 25, 2011. Where the ‘‘Threshold’’ 

column of Table 2, specified in paragraph 

1.E., ‘‘Compliance,’’ of Airbus Mandatory 

Service Bulletin A340–57–5029, including 

Appendices 01 and 02, dated February 25, 

2011, specifies the compliance time as ‘‘FC’’ 

and ‘‘FH,’’ this AD requires the compliance 

times as ‘‘total flight cycles’’ and ‘‘total flight 

hours.’’ The thresholds for airplane postmodification number 56558S19405 must be 

counted from the airplane’s first flight and 

not from the accomplishment of Airbus 

Service Bulletin A340–57–5010. 

(h) Repetitive Inspections 

Repeat the inspection required by 

paragraph (g) of this AD at intervals not to 

exceed the times specified in the ‘‘Repetitive 

Interval’’ column of Table 2, specified in 

paragraph 1.E. Compliance, of Airbus 

Mandatory Service Bulletin A340–57–5029, 

including Appendices 01 and 02, dated 

February 25, 2011. Where the ‘‘Repetitive 

Interval’’ column of Table 2, specified in 

paragraph 1.E. Compliance, of Airbus 

Mandatory Service Bulletin A340–57–5029, 

including Appendices 01 and 02, dated 

February 25, 2011, specifies the compliance 

times as ‘‘FC’’ and ‘‘FH,’’ this AD requires the 

compliance times as ‘‘flight cycles’’ and 

‘‘flight hours.’’ 

(i) Corrective Action 

If any crack is found during the initial or 

repetitive inspections required by paragraphs 

(g) and (h) of this AD: Before further flight, 

contact the Manager, International Branch, 

ANM–116, FAA; or the European Aviation 

Safety Agency (EASA) (or its delegated 

agent); for repair instructions and do the 

repair. 

(j) Reporting Requirement 

Submit a report of the findings (both 

positive and negative) of the inspections 

required by paragraphs (g) and (h) of this AD, 

in accordance with the Inspection Report of 

Airbus Mandatory Service Bulletin A340–57– 

5029, Appendix 01, dated February 25, 2011, 

at the applicable time specified in paragraph 

(j)(1) or (j)(2) of this AD. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 90 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 90 days after the effective date of this 

AD. 

(k) Credit for Previous Actions 

This paragraph provides credit for 

inspections required by paragraph (g) of this 

AD, if those inspections were performed 

before the effective date of this AD using 

Airbus A340–500/–600 Nondestructive 

Testing Manual Task 57–18–07, Revision 35, 

dated April 1, 2011. As of the effective date 

of this AD, inspections must be repeated in 

accordance with the requirements of 

paragraph (h) of this AD. 


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Federal Register / Vol. 77, No. 62 / Friday, March 30, 2012 / Rules and Regulations 19061 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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 emailed 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 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: 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. 

(4) Special Flight Permits: Special flight 

permits, as described in Section 21.197 and 

Section 21.199 of the Federal Aviation 

Regulations (14 CFR 21.197 and 21.199), are 

not allowed. 

(m) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2011–0075, dated 

April 29, 2011; and Airbus Mandatory 

Service Bulletin A340–57–5029, including 

Appendices 01 and 02, dated February 25, 

2011; for related information. 

(n) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) of the 

following service information under 5 U.S.C. 

552(a) and 1 CFR part 51: 

(i) Airbus Mandatory Service Bulletin 

A340–57–5029, including Appendices 01 

and 02, dated February 25, 2011. 

(2) For Airbus 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; email 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 an NARA facility, 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 

19, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–7374 Filed 3–29–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0018; Directorate 

Identifier 2011–CE–042–AD; Amendment 

39–16997; AD 2012–06–16] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Pilatus 

Aircraft Ltd. Models PC–6, PC–6–H1, 

PC–6–H2, PC–6/350, PC–6/350–H1, PC– 

6/350–H2, PC–6/A, PC–6/A–H1, PC–6/ 

A–H2, PC–6/B–H2, PC–6/B1–H2, PC–6/ 

B2–H2, PC–6/B2–H4, PC–6/C–H2, and 

PC–6/C1–H2 airplanes. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as loose elevator and rudder 

hinge bolts caused by incorrect torquing 

and locking of the bolts, which could 

lead to in-flight failure of the elevator or 

rudder attachment. We are issuing this 

AD to require actions to address the 

unsafe condition on these products. 

DATES: This AD is effective May 4, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of May 4, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

For service information identified in 

this AD, contact PILATUS AIRCRAFT 

LTD., Customer Liaison Manager, CH– 

6371 STANS, Switzerland; telephone: 

+41 (0) 41 619 65 80; fax: +41 (0) 41 619 

65 76; Internet: http://www.pilatusaircraft.com. You may review copies of 

the referenced service information at the 

FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. 

For information on the availability of 

this material at the FAA, call (816) 329– 

4148. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4059; fax: (816) 329–4090; email: 

doug.rudolph@faa.gov. 

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 January 17, 2012 (77 FR 

2238). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

A case of loss of elevator and rudder hinge 

bolts on a PC–6 aeroplane has been reported. 

The results of the investigations indicate 

that the elevator and rudder hinge bolt loss 

are suspected to have been caused by an 

incorrect torque and locking of the bolts. 

This condition, if not detected and 

corrected, could lead to in-flight failure of the 

elevator or rudder attachment, possibly 

resulting in loss of control of the aeroplane. 

For the reasons described above, this AD 

requires the installation of a new locking 

screw and the modification of the installation 

of the hinge bolt. 


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