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

73801 

Vol. 79, No. 239 

Friday, December 12, 2014 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0256; Directorate 

Identifier 2007–SW–01–AD; Amendment 39– 

18046; AD 2008–14–02 R1] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. (Agusta) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are revising Airworthiness 

Directive (AD) 2008–14–02 for Agusta 

Model AB139 and AW139 helicopters. 

AD 2008–14–02 required inspecting the 

fuselage frame to detect fatigue cracks 

which could lead to structural failure 

and subsequent loss of control of the 

helicopter. Since we issued AD 2008– 

14–02, Agusta developed a frame 

reinforcement modification, which 

supports extending the interval for 

inspecting the fuselage frame for a 

fatigue crack. This new AD requires 

inspecting the fuselage frame for a crack 

and reduces the applicability from AD 

2008–14–02 to exclude helicopters with 

the frame reinforcement modification. 

The actions of this AD are intended to 

detect a fatigue crack that could result 

in failure of the fuselage frame and 

subsequent loss of control of the 

helicopter. 

DATES: This AD is effective January 16, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of August 14, 2008 (73 FR 39572, July 

10, 2008). 

ADDRESSES: For service information 

identified in this AD, contact 

AgustaWestland, Product Support 

Engineering, Via del Gregge, 100, 21015 

Lonate Pozzolo (VA) Italy, ATTN: 

Maurizio D’Angelo; telephone 39–0331– 

664757; fax 39–0331–664680; or at 

http://www.agustawestland.com/ 

technical-bulletins. 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. 

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 European 

Aviation Safety Agency (EASA) AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to revise AD 2008–14–02, 

Amendment 39–15597 (73 FR 39572, 

July 10, 2008) (AD 2008–14–02), for 

Agusta Model AB 139 and AW 139 

helicopters. The NPRM published in the 

Federal Register on July 8, 2013 (78 FR 

40640). The NPRM proposed to retain 

all requirements of AD 2008–14–02 but 

remove from the applicability section 

any helicopter modified by installing 

structural reinforcement skins in 

accordance with Agusta Bollettino 

Tecnico No. 139–089, dated February 

19, 2010 (BT 139–089). The NPRM 

proposed to continue to require initially 

inspecting the fuselage frame 5700 

middle section within 10 hours time-inservice (TIS), or upon accumulating 100 

hours TIS since new, whichever occurs 

later, for a crack. The NPRM also 

proposed to continue to require 

repeating this inspection at intervals not 

exceeding 100 hours TIS, and, if there 

is a crack, before further flight, repairing 

the crack in accordance with FAAapproved procedures. 

The NPRM was prompted by AD No. 

2006–0357R1, dated April 22, 2010, 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union, to correct an unsafe 

condition for Agusta Model AB 139 and 

AW 139 helicopters. EASA advised that 

tests have shown that the Agusta AB/ 

AW 139’s fuselage frame 5700 middle 

section is prone to fatigue damage. 

EASA issued AD No. 2006–0357R1 to 

revise EASA AD No. 2006–0357, dated 

November 29, 2006, by removing Agusta 

Model AB139 and AW139 helicopters 

modified with the structural reinforced 

frames from the applicability 

requirements of the fatigue crack 

inspection. 

Comments 

After our NPRM (78 FR 40640, July 8, 

2013), was published, we received a 

comment from one commenter. 

Request 

One commenter requested that the 

Applicability section include an 

exception for Agusta Model AB139 and 

AW139 helicopters with Main Cabin 

serial numbers (S/Ns) ‘‘TA1721 and 

subsequent,’’ and ‘‘PZL219 and 

subsequent.’’ The commenter proposed 

this change because the specified 

helicopters have left-hand (LH) frame 

station 5700 part number (P/N) 

3P5338A13354 and right-hand (RH) 

frame station 5700 P/N 3P5338A13454 

installed. 

We disagree that such a change is 

necessary. Paragraph (a) of the AD states 

that it does not apply to helicopters 

with LH frame station 5700, P/N 

3P5338A13354, and RH frame station 

5700, P/N 3P5338A13454, installed. 

Thus, helicopters with the specified 

main cabin S/Ns are already excepted 

from the applicability of this AD. 

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 


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73802 Federal Register / Vol. 79, No. 239 / Friday, December 12, 2014 / Rules and Regulations 

because we evaluated all information 

provided by EASA, reviewed the 

relevant information, considered the 

comment received, and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed, except we have correctly 

stated the design holder’s name as 

Agusta S.p.A. instead of 

AgustaWestland S.p.A. as specified by 

the current FAA type certificate. This 

change is consistent with the intent of 

the proposals in the NPRM (78 FR 

40640, July 8, 2013) and will not 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Differences Between This AD and the 

EASA AD 

The EASA AD requires contacting the 

type certificate (TC) holder for further 

instructions if damage or a crack is 

found; this AD requires repairing the 

crack, before further flight, with FAAapproved procedures with no 

requirement to contact the TC holder. 

The EASA AD also excludes helicopters 

with S/Ns 31002, 31003, 31004, and 

31007; whereas, this AD does not. 

Related Service Information 

Agusta issued Bollettino Tecnico No. 

139–018, Revision B, dated October 18, 

2006, which specifies inspection 

procedures for the middle section frame 

5700 for all Model AB139 and AW139 

helicopters except S/Ns 31002, 31003, 

31004, and 31007. Subsequently, Agusta 

issued BT 139–089, which describes 

procedures for installing carbon fiber 

structural reinforcement skins at frame 

station 5700 for two part-numbered 

fuselage frames and for one frame 

station 3900 fuselage frame. Once the 

fuselage frames have been modified in 

accordance with BT 139–089, the 

inspection interval of Mandatory 

Inspection Task MI53–12 may be 

extended. 

Costs of Compliance 

We estimate this AD affects 33 

helicopters of U.S. Registry. We estimate 

that operators may incur the following 

costs in order to comply with this AD. 

It will take about 1 work-hour to comply 

with the initial and each subsequent 

inspection required by this AD. The 

average labor rate is $85 per work-hour 

so the approximate cost for each 

inspection is $85 per helicopter or 

$2,805 for the U.S.-registered fleet. We 

estimate the cost to repair the fuselage 

middle frame section to be about 

$10,000. 

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 

helicopters identified in this rulemaking 

action. 

Regulatory Findings 

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); 

(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. 

We prepared an economic 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 

removing Airworthiness Directive (AD) 

2008–14–02, Amendment 39–15597 (73 

FR 39572, July 10, 2008), and adding the 

following new AD: 

2008–14–02 R1 Agusta S.p.A. (Agusta) 

Helicopters: Amendment 39–18046; 

Docket No. FAA–2008–0256; Directorate 

Identifier 2007–SW–01–AD. 

(a) Applicability 

This AD applies to Agusta Model AB139 

and AW139 helicopters, except helicopters 

with reinforcement skin part number (P/N) 

3G5306P08512 installed on left hand (LH) 

frame station 5700 P/N 3P5338A13352 and 

right hand (RH) frame station 5700 P/N 

3P5338A13452; or with reinforcement skin 

P/N 3G5306P08513 installed on LH frame 

station 5700 P/N 3P5338A13353 and RH 

frame station 5700 P/N 3P5338A13453; or 

with LH frame station 5700 P/N 

3P5338A13354 and RH frame station 5700 

P/N 3P5338A13454, installed; certificated in 

any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

fatigue crack in the fuselage frame 5700 

middle section. This condition could result 

in structural failure of the frame and 

subsequent loss of control of the helicopter. 

(c) Affected ADs 

This AD revises AD 2008–14–02, 

Amendment 39–15597 (73 FR 39572, July 10, 

2008). 

(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) Within 10 hours time-in-service (TIS), 

or upon accumulating 100 hours TIS since 

new, whichever occurs later, inspect the 

fuselage frame 5700 middle section for a 

crack in accordance with the Compliance 

Instructions, paragraphs 1. through 4., of 

Agusta Bollettino Tecnico No. 139–018, 

Revision B, dated October 18, 2006. 

(2) Thereafter, at intervals not exceeding 

100 hours TIS, repeat the inspection as 

required by paragraph (e)(1) of this AD. 

(3) If there is a crack, before further flight, 

repair the crack in accordance with an FAAapproved procedure. 

(f) Effective Date 

This AD becomes effective January 16, 

2015. 

(g) 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 


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Federal Register / Vol. 79, No. 239 / Friday, December 12, 2014 / Rules and Regulations 73803 

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. 

(h) Additional Information 

(1) Agusta Bollettino Tecnico No. 139–089, 

dated February 19, 2010, which is not 

incorporated by reference, contains 

additional information about the subject of 

this AD. For this service information, contact 

AgustaWestland, Product Support 

Engineering, Via del Gregge, 100, 21015 

Lonate Pozzolo (VA) Italy, ATTN: Maurizio 

D’Angelo; telephone 39–0331–664757; fax 

39–0331–664680; or at http:// 

www.agustawestland.com/technicalbulletins. You may review a copy of the 

service information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2006–0357R1, dated April 22, 2010. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov in Docket No. 

FAA–2008–0256. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5311, Fuselage, Main Frame. 

(j) 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 August 14, 2008 (73 FR 

39572, July 10, 2008). 

(i) Agusta Bollettino Tecnico No. 139–018, 

Revision B, dated October 18, 2006. 

(ii) Reserved. 

(4) For Agusta service information 

identified in this AD, contact 

AgustaWestland, Product Support 

Engineering, Via del Gregge, 100, 21015 

Lonate Pozzolo (VA) Italy, ATTN: Maurizio 

D’Angelo; telephone 39–0331–664757; fax 

39–0331–664680; or at http:// 

www.agustawestland.com/technicalbulletins. 

(5) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(6) You may view this 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/ibrlocations.html. 

Issued in Fort Worth, Texas, on November 

24, 2014. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–28913 Filed 12–11–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0717; Directorate 

Identifier 2014–CE–026–AD; Amendment 

39–18045; AD 2014–25–04] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Limited Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

airworthiness directive (AD) 2013–11– 

08 for Pilatus Aircraft Limited 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 a need 

to incorporate new revisions into the 

aircraft maintenance manual or in the 

limitations document of the FAAapproved maintenance program. We are 

issuing this AD to require actions to 

address the unsafe condition on these 

products. 

DATES: This AD is effective January 16, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of January 16, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0717; or in person at the Docket 

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; email: fodermatt@pilatusaircraft.com. You may view this 

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 add an AD that would apply 

to Pilatus Aircraft Limited 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. 

That NPRM was published in the 

Federal Register on September 18, 2014 

(79 FR 56023), and proposed to 

supersede AD 2013–11–08, Amendment 

39–17468 (78 FR 37701; June 24, 2013). 

The NPRM proposed to correct an 

unsafe condition for the specified 

products and was based on mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country. The MCAI 

states that: 

The maintenance instructions and 

airworthiness limitations applicable to the 

Structure and Components of PC–6 

aeroplanes are specified in the Aircraft 

Maintenance Manual (AMM) under Chapter 

4 or in the Airworthiness Limitations 

Document (ALS), depending on aeroplane 

model. 

The instructions contained in the ALS 

document have been identified as mandatory 

actions for continued airworthiness and 

failure to comply with these instructions and 

limitations could potentially lead to an 

unsafe condition. 

Pilatus Aircraft Ltd. (Pilatus) recently 

issued PC–6 AMM, Chapter 04–00–00, 

Document Number 01975 issue 19 for PC–6 

B2–H2 and PC–6 B2–H4 aeroplanes and PC– 

6 ALS, Document Number 02334 issue 4 for 

all other PC–6 aeroplane models to 

incorporate new life limits for the Fire 

Extinguisher. 

For the reason described above, this AD 

retains the requirements of EASA AD 2012– 

0268, which is superseded, and requires 


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