42952 Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations 

(2) The controllability and 

maneuverability requirements of this 

part are met within a practical 

operational flight envelope (for 

example, speed, altitude, normal 

acceleration, and airplane configuration) 

that is described in the Airplane Flight 

Manual (AFM); and 

(3) The trim, stability, and stall 

characteristics are not impaired below a 

level needed to permit continued safe 

flight and landing. 

(B) In place of 14 CFR part 23, 

§ 23.677 Trim systems requirement, 

comply with the following: 

SC 23.677 Load Alleviation Active 

Control Surface 

(a) Proper precautions must be taken 

to prevent inadvertent, improper, or 

abrupt Tamarack Active Control Surface 

(TACS) operation. 

(b) The load alleviation system must 

be designed so that, when any one 

connecting or transmitting element in 

the primary flight control system fails, 

adequate longitudinal control for safe 

flight and landing is available. 

(c) The load alleviation system must 

be irreversible unless the TACS is 

properly balanced and has no unsafe 

flutter characteristics. The system must 

have adequate rigidity and reliability in 

the portion of the system from the tab 

to the attachment of the irreversible unit 

to the airplane structure. 

(d) It must be demonstrated that the 

airplane is safely controllable and that 

the pilot can perform all maneuvers and 

operations necessary to effect a safe 

landing following any probable powered 

system runaway that reasonably might 

be expected in service, allowing for 

appropriate time delay after pilot 

recognition of the system runaway. The 

demonstration must be conducted at 

critical airplane weights and center of 

gravity positions. 

(C) In place of 14 CFR part 23, 

§ 23.683 Operation tests requirement, 

comply with the following: 

SC 23.683 Operation tests 

(a) It must be shown by operation 

tests that, when the load alleviation 

system is active and operational and 

loaded as prescribed in paragraph (b) of 

this section, the system is free from— 

(1) Jamming; 

(2) Excessive friction; and 

(3) Excessive deflection. 

(b) The prescribed test loads are, for 

the entire system, loads corresponding 

to the limit airloads on the appropriate 

surface. 

(D) In place of 14 CFR part 23, 

§ 23.685 Control system details 

requirement, comply with the following: 

SC 23.685 Control System Details 

(a) Each detail of the Tamarack Active 

Control Surface (TACS) must be 

designed and installed to prevent 

jamming, chafing, and interference from 

cargo, passengers, loose objects, or the 

freezing of moisture. 

(b) There must be means in the 

cockpit to prevent the entry of foreign 

objects into places where they would 

jam any one connecting or transmitting 

element of the system. 

(c) Each element of the load 

alleviation system must have design 

features, or must be distinctively and 

permanently marked, to minimize the 

possibility of incorrect assembly that 

could result in malfunctioning of the 

control system. 

(E) In place of 14 CFR part 23, 

§ 23.697 Wing flap controls 

requirement, comply with the following: 

SC 23.697 Load Alleviation System 

Controls 

(a) The Tamarack Active Control 

Surface (TACS) must be designed so 

that, when the surface has been placed 

in any position, it will not move from 

that position unless the control is 

adjusted or is moved by the automatic 

operation of a load alleviation system. 

(b) The rate of movement of the TACS 

in response to the automatic device 

must give satisfactory flight and 

performance characteristics under 

steady or changing conditions of 

airspeed, engine power, and attitude. 

(F) In place of 14 CFR part 23, 

§ 23.701 Flap interconnection 

requirement, comply with the following: 

SC 23.701 Load Alleviation System 

Interconnection 

(a) The load alleviation system and 

related movable surfaces as a system 

must— 

(1) Be synchronized by a mechanical 

interconnection between the movable 

surfaces; or by an approved equivalent 

means; or 

(2) Be designed so that the occurrence 

of any failure of the system that would 

result in an unsafe flight characteristic 

of the airplane is extremely improbable; 

or 

(b) The airplane must be shown to 

have safe flight characteristics with any 

combination of extreme positions of 

individual movable surfaces. 

Issued in Kansas City, Missouri, on July 13, 

2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–17864 Filed 7–20–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0329; Directorate 

Identifier 2011–NM–139–AD; Amendment 

39–17127; AD 2012–14–13] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A318–112 and –121 

airplanes; Model A319–111, –112, –115, 

–132, and –133 airplanes; Model A320– 

214, –232, and –233 airplanes; and 

Model A321–211, –212, –213, and –231 

airplanes. This AD was prompted by 

reports of some fuselage nuts found 

cracked. This AD requires an inspection 

to determine if certain fuselage nuts are 

installed, a detailed inspection for 

cracking of fuselage nuts having a 

certain part number, and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

detect and correct fuselage nuts found 

cracked, which could result in reduced 

structural integrity of the airplane. 

DATES: This AD becomes effective 

August 27, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 27, 2012. 

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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1405; 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 April 2, 2012 (77 FR 19567). 

That NPRM proposed to correct an 

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Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations 42953 

unsafe condition for the specified 

products. The MCAI states: 

During structural part assembly in Airbus 

production line, some nuts Part Number (P/ 

N) ASNA2531–4 were found cracked. 

Investigations were performed to determine 

the batches of the affected nuts and had 

revealed that these nuts have been installed 

in production on the fuselage of aeroplanes 

listed in the applicability section of this 

[EASA] AD. 

Static, fatigue and corrosion tests were 

performed, which demonstrated that no 

immediate maintenance action is necessary. 

However, a large number of these nuts are 

fitted on primary structural elements, which 

could have long-term consequences. 

This condition, if not corrected, could 

impair the structural integrity of the affected 

aeroplanes. 

For the reasons described above, this 

[EASA] AD requires [an inspection to 

determine if certain fuselage nuts are 

installed,] a detailed inspection [for cracking] 

of the affected nuts, associated corrective 

actions, [general visual inspection for 

scratching of the hole if necessary] 

depending on findings, and replacement of 

the affected P/N ASNA2531–4 nuts with new 

ones, having the same P/N. 

* * * * * 

Required actions include related 

investigative and corrective actions if 

necessary. Related investigative actions 

include a general visual inspection for 

scratching of the hole. Corrective 

actions include replacing the fastener 

and installing a new fuselage nut. 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 

received no comments on the NPRM (77 

FR 19567, April 2, 2012) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD will affect 

152 products of U.S. registry. We also 

estimate that it will take about 15 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

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

be $193,800, or $1,275 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 10 work-hours and require parts 

costing $362, for a cost of $1,212 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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. 

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 (77 FR 19567, April 

2, 2012), 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: 

2012–14–13 Airbus: Amendment 39–17127. 

Docket No. FAA–2012–0329; Directorate 

Identifier 2011–NM–139–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective August 27, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A318– 

112 and –121 airplanes; Model A319–111, 

–112, –115, –132, and –133 airplanes; Model 

A320–214, –232, and –233 airplanes; and 

Model A321–211, –212, –213, and –231 

airplanes; certificated in any category; 

manufacturer serial numbers 3339, 3340, 

3350, 3355, 3360, 3367, 3369, 3372, 3380, 

3382, 3385, 3387, 3388, 3390, 3393, 3395, 

3397 through 3508 inclusive, 3510 through 

3519 inclusive, 3522, 3523, 3525, 3527, 3529, 

3530, 3537, 3539, 3542, 3544, 3546, 3548, 

3552, and 3555. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53: Fuselage. 

(e) Reason 

This AD was prompted by reports of 

fuselage nuts found cracked. We are issuing 

this AD to detect and correct fuselage nuts 

found cracked, which could result in reduced 

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 and Replacement 

Within 72 months since first flight of the 

airplane or within 90 days after the effective 

date of this AD, whichever occurs later, do 

an inspection for nuts having part number (P/ 

N) ASNA2531–4 located in the fuselage. If a 

nut having P/N ASNA2531–4 is found, before 

further flight, do a detailed inspection for 

cracking of the nut, and all applicable related 

investigative and corrective actions, in 

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42954 Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1218, Revision 01, including Appendices 

01 and 02, dated June 17, 2010. If any 

cracking is found, before further flight, repair 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1218, Revision 01, including Appendices 

01 and 02, dated June 17, 2010. 

(h) Reporting 

Submit a report of the findings of the 

inspection required by paragraph (g) of this 

AD to Airbus in accordance with Appendix 

01 of Airbus Service Bulletin A320–53–1218, 

Revision 01, including Appendices 01 and 

02, dated June 17, 2010, at the applicable 

time specified in paragraph (h)(1) or (h)(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. 

(i) Credit for Previous Actions 

This paragraph provides credit for 

inspections and replacements required by 

paragraph (g) of this AD, if those actions were 

performed before the effective date of this AD 

using Airbus Service Bulletin A320–53–1218, 

including Appendices 01 and 02, dated 

February 8, 2010. 

(j) 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–227–1405; 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. 

(k) Related Information 

Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2011– 

0120R1, dated July 13, 2011; and Airbus 

Service Bulletin A320–53–1218, Revision 01, 

including Appendices 01 and 02, dated June 

17, 2010; for related information. 

(l) Material Incorporated by Reference 

(1) 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. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) Airbus Service Bulletin A320–53–1218, 

Revision 01, including Appendices 01 and 

02, dated June 17, 2010. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; Internet 

http://www.airbus.com. 

(4) 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. 

(5) 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 July 5, 

2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–17389 Filed 7–20–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0730; Directorate 

Identifier 2012–SW–048–AD; Amendment 

39–17124; AD 2012–14–10] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Vertol (Type Certificate Currently Held 

by Columbia Helicopters, Inc. (CHI)) 

and Kawasaki Heavy Industries, 

Limited Helicopters (Kawasaki) 

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 CHI 

Model 107–II and Kawasaki Model 

KV107–II and KV107–IIA helicopters. 

This AD requires, before further flight, 

replacing certain upper collective pitch 

control yoke bolts. This AD is prompted 

by three failures of the affected bolts. 

These actions are intended to prevent 

failure of an upper collective pitch 

control yoke bolt (bolt), excessive 

vibration, migration of the shafts, and 

subsequent loss of control of the 

helicopter. 

DATES: This AD becomes effective 

August 7, 2012. 

We must receive comments on this 

AD by September 21, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

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

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address 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 economic 

evaluation, any comments received, and 

other information. The street address for 

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