55684 Federal Register / Vol. 77, No. 176 / Tuesday, September 11, 2012 / Rules and Regulations 

information identified in paragraphs (o)(1), 

(o)(2), and (o)(3) of this AD, as applicable. 

(1) Figure 20, ‘‘Electrical Conductivity 

Measurement for Aluminum,’’ of Subject 51– 

00–00, ‘‘Structures-General,’’ of Part 6—Eddy 

Current, of the Boeing 707/720 

Nondestructive Test Manual, Document D6– 

48023, Revision 118, dated July 15, 2011. 

(2) Subject 55–10–07, ‘‘Horizontal 

Stabilizer,’’ of Part 6—Eddy Current, of the 

Boeing 707/720 Nondestructive Test Manual, 

Document D6–48023, Revision 118, dated 

July 15, 2011. 

(3) Subject 51–01–00, ‘‘Orientation and 

Preparation for Testing’’ of Part 1—General, 

of the Boeing 707/720 Nondestructive Test 

Manual, Document D6–48023, Revision 118, 

dated July 15, 2011. 

(p) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install any horizontal stabilizer 

assembly with any chord segment having a 

part number other than that identified in 

paragraph 2.C.2. of Boeing 707 Alert Service 

Bulletin A3515, dated December 19, 2007, on 

any airplane. 

(q) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(r) Related Information 

For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425–917– 

6577; fax: 425–917–6590; email: 

berhane.alazar@faa.gov. 

(s) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on October 16, 2012. 

(i) Boeing 707 Alert Service Bulletin 

A3515, dated December 19, 2007. 

(ii) Boeing 707 Alert Service Bulletin 

A3516, dated April 4, 2008. 

(iii) Subject 51–00–00, ‘‘Structures— 

General,’’ Figure 20, ‘‘Electrical Conductivity 

Measurement for Aluminum,’’ of Part 6— 

Eddy Current, of the Boeing 707/720 

Nondestructive Test Manual, Document D6– 

48023, Revision 118, dated July 15, 2011. The 

revision level of this document is identified 

in only the manual revision Transmittal 

Sheet. 

(iv) Subject 55–10–07, ‘‘Horizontal 

Stabilizer,’’ of Part 6—Eddy Current, of the 

Boeing 707/720 Nondestructive Test Manual, 

Document D6–48023, Revision 118, dated 

July 15, 2011. The revision level of this 

document is identified in only the manual 

revision Transmittal Sheet. 

(v) Subject 51–01–00, ‘‘Orientation and 

Preparation for Testing’’ of Part 1—General, 

of the Boeing 707/720 Nondestructive Test 

Manual, Document D6–48023, Revision 118, 

dated July 15, 2011. The revision level of this 

document is identified in only the manual 

revision Transmittal Sheet. 

(4) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; Internet https:// 

www.myboeingfleet.com. 

(5) 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. 

(6) 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/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on August 

24, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–21533 Filed 9–10–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0927; Directorate 

Identifier 2012–SW–052–AD; Amendment 

39–17178; AD 2012–18–02] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. Helicopters 

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 Agusta 

S.p.A. (Agusta) Model AB412 and 

AB412 EP helicopters with certain hoist 

hook assemblies (hook) installed. This 

AD requires inspecting the hook for 

correct assembly of the nut and body. 

This AD is prompted by a report that a 

hook separated from the cable of a 

helicopter. These actions are intended 

to prevent detachment of the hook from 

the helicopter and subsequent loss of an 

external load, possibly resulting in 

personal injury. 

DATES: This AD becomes effective 

September 26, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of September 26, 2012. 

We must receive comments on this 

AD by November 13, 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, any comments 

received, and other information. The 


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Federal Register / Vol. 77, No. 176 / Tuesday, September 11, 2012 / Rules and Regulations 55685 

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 service information identified in 

this AD, contact Agusta Westland, 

Customer Support & Services, Via per 

Tornavento 15, 21019 Somma Lombardo 

(VA) Italy, ATTN: Giovanni Cecchelli; 

telephone 39–0331–711133; fax 39 0331 

711180; or at http://www.agusta

westland.com/technical-bullettins. You 

may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: 

Sharon Miles, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222 5110; email 

sharon.y.miles@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, we invite you to participate in 

this rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit them only one time. We will file 

in the docket all comments that we 

receive, as well as a report summarizing 

each substantive public contact with 

FAA personnel concerning this 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD No. 2012– 

0086–E, dated May 18, 2012 (EASA AD 

2012–0086–E), to correct an unsafe 

condition for Agusta Model AB412 and 

AB412EP helicopters. EASA advises of 

a report where a hoist hook separated 

from an AB412 helicopter. EASA states 

the initial investigation revealed that the 

nut and housing hook were not properly 

assembled. According to EASA, this 

condition could lead to separation of the 

hook and detachment of an external 

load from the hoist, resulting in 

personal injury or damage to property 

on the ground. For these reasons, EASA 

issued EASA AD 2012–0086–E to 

require inspecting the hook before the 

next flight, and after every subsequent 

reassembly of the hook. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Italy and are 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Italy, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs. 

Related Service Information 

We reviewed AgustaWestland 

Bollettino Tecnico (BT) No. 412–132, 

dated May 2, 2012, and BT No. 412–133, 

dated May 17, 2012, which describe 

procedures for inspecting the nut and 

housing hook to determine whether the 

two locking screws are inserted into the 

slot of the housing. Both BTs also 

describe procedures for assembling the 

hook if the nut and body are not 

properly aligned. 

AD Requirements 

This AD requires, before further flight, 

and after any reassembly of the hook: 

• Inspecting the nut and housing 

hook to determine whether the two 

locking screws are inserted into the slot 

of the housing. 

• Correcting the assembly, before 

further flight, if the locking screws are 

not properly inserted in the slots of the 

housing. 

Costs of Compliance 

There are no costs of compliance with 

this AD because there are no helicopters 

with this type certificate on the U.S. 

Registry. 

FAA’s Justification and Determination 

of the Effective Date 

There are no helicopters with this 

type certificate on the U.S. Registry. 

Therefore, we believe it is unlikely that 

we will receive any adverse comments 

or useful information about this AD 

from U.S. Operators. 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we determined that notice and 

opportunity for public comment before 

issuing this AD are unnecessary because 

there are none of these products on the 

U.S. Registry. 

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, 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); 

3. Will not affect intrastate aviation in 

Alaska to the extent that it justifies 

making a regulatory distinction; 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. 

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: 


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55686 Federal Register / Vol. 77, No. 176 / Tuesday, September 11, 2012 / Rules and Regulations 

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 airworthiness 

directive (AD): 

2012–18–02 AGUSTA S.P.A.: Amendment 

39–17178; Docket No. FAA–2012–0927; 

Directorate Identifier 2012–SW–052–AD. 

(a) Applicability 

(1) This AD applies to Model AB412 and 

AB412EP helicopters with: 

(i) Hoist part-number (P/N) 412–8800–01– 

202 (Breeze Eastern P/N BL–20200–402) or 

P/N 412–8800–01–412 (Breeze Eastern P/N 

BL–20200–412), with a hook assembly (hook) 

P/N HK–118–2 installed; or 

(ii) Hoist P/N BL–20200–75 (Breeze 

Eastern) or P/N BL–20200–95 (Breeze 

Eastern), with a hook P/N BL–5740–8 

installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

the hook body locking screws not properly 

inserted into the slot on the housing, which 

could result in detachment of the hook and 

subsequent loss of an external load or person 

from the helicopter hoist. 

(c) Effective Date 

This AD becomes effective September 26, 

2012. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) For hook, P/N HK–118–2, before further 

flight, and thereafter after every disassembly 

and reassembly of the hook, inspect the hook 

for correct assembly of the nut and housing 

hook by doing the following. 

(i) Using a .5 millimeter (mm) thickness 

feeler gauge, position the feeler gauge on the 

handwheel as shown in Figure 2 of 

AgustaWestland Bollettino Tecnico (BT) No. 

412–132, dated May 2, 2012 (BT 412–132). 

(ii) If feeler gauge cannot be inserted, the 

nut and housing are correctly assembled. 

(iii) If feeler gauge can be inserted, as 

shown in Figure 3 of BT 412–132, reassemble 

the hook by following the Accomplishment 

Instructions, paragraphs 5 through 20, and 

figures 4 and 5, of BT 412–132. 

(2) For hook, P/N BL–5740–8, before 

further flight, and thereafter after every 

disassembly and reassembly of the hook, 

inspect the hook for correct assembly of the 

nut and body by doing the following. 

(i) Pull down the rubber bumper to expose 

the body and setscrews. 

(ii) Determine if the two setscrews are 

inserted in the two slots as shown in Figure 

2 of AgustaWestland BT No. 412–133, dated 

May 17, 2012 (BT 412–133). 

(iii) If the setscrews are inserted in the 

slots, the nut and body are correctly 

assembled. Return the rubber bumper to its 

proper position. 

(iv) If the two setscrews are not inserted in 

the slots, as shown in Figure 3 of BT 412– 

133, reassemble the hook by following the 

Accomplishment Instructions, paragraphs 5 

through 20, and figures 4 and 5, of BT 412– 

133. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Sharon Miles, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222 5110; email 

sharon.y.miles@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

(1) The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2012–0086–E, dated May 18, 2012. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2550: External Load Handling 

Equipment. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) AgustaWestland Bollettino Tecnico No. 

412–132, dated May 2, 2012. 

(ii) AgustaWestland Bollettino Tecnico No. 

412–133, dated May 17, 2012. 

(3) For AgustaWestland service 

information identified in this AD, contact 

AgustaWestland, Customer Support & 

Services, Via Per Tornavento 15, 21019 

Somma Lombardo (VA) Italy, ATTN: 

Giovanni Cecchelli; telephone 39–0331– 

711133; fax 39 0331 711180; or at http:// 

www.agustawestland.com/technicalbullettins. 

(4) You may view this service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. 

(5) You may also view this service 

information 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 Fort Worth, Texas, on August 28, 

2012. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–21722 Filed 9–10–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0946; Directorate 

Identifier 2012–CE–037–AD; Amendment 

39–17187; AD 2012–18–10] 

RIN 2120–AA64 

Airworthiness Directives; GA200 (Pty) 

Ltd Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for comments 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for GA200 

(Pty) Ltd Models GA200 and GA200C 

airplanes. This AD results from 

mandatory continuing airworthiness 

information (MCAI) issued by the 

aviation authority of another country to 

identify and correct an unsafe condition 

on an aviation product. The MCAI 

describes the unsafe condition as failure 

of the strut bolt through the main spar. 

We are issuing this AD to require 

actions to address the unsafe condition 

on these products. 

DATES: This AD is effective September 

14, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of September 14, 2012. 

We must receive comments on this 

AD by October 26, 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 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, contact GippsAero, P.O. Box 


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