Federal Register / Vol. 79, No. 46 / Monday, March 10, 2014 / Rules and Regulations 13199 

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 February 

20, 2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–04589 Filed 3–7–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0109; Directorate 

Identifier 2013–SW–049–AD; Amendment 

39–17772; AD 2014–04–13] 

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. This AD requires 

inspecting the tail rotor (T/R) blade for 

a crack, corrosion, nick, scratch, dent, or 

other damage and replacing or repairing 

the blade, depending on the damage. 

This AD is prompted by reports of T/R 

blade failures caused by fatigue cracking 

that originated from surface damage. 

These actions are intended to prevent 

failure of the T/R blade and subsequent 

loss of control of the helicopter. 

DATES: This AD becomes effective 

March 25, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of March 25, 2014. 

We must receive comments on this 

AD by May 9, 2014. 

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 European 

Aviation Safety Agency (EASA) AD, any 

incorporated by reference service 

information, 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 service information identified in 

this AD, contact Agusta Westland, 

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 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: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

robert.grant@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 

On April 22, 2008, we issued AD 

2008–10–03, Amendment 39–15509 (73 

FR 24858, May 6, 2008) for Bell 

Helicopter Textron Helicopters (Bell) 

Model 204B, 205A, 205A–1, 205B, 210, 

212, 412, 412CF, and 412EP helicopters. 

AD 2008–10–03 required certain checks 

and inspections of each T/R blade at 

specified intervals and repairing or 

replacing, as applicable, any 

unairworthy T/R blade. AD 2008–10–03 

was prompted by eight reports of fatigue 

cracking of T/R blades installed on Bell 

Model 212 and 412 helicopters (three 

failures on Bell Model 212 and five 

failures on Bell Model 412) with a T/R 

blade, part number (P/N) 212–010–750– 

009, –105, and –107. Three of the Model 

412 failures occurred during flight. 

After we issued AD 2008–10–03, an 

accident attributed to a T/R failure 

occurred. Because of this accident, we 

determined that a second, more detailed 

inspection was necessary to allow for an 

earlier detection of a crack or other 

damage. As a result, on July 11, 2013, 

we issued AD 2013–15–02, Amendment 

39–17518 (78 FR 45845, July 30, 2013), 

which superseded AD 2008–10–03. 

These actions were intended to prevent 

failure of the T/R blade and subsequent 

loss of helicopter control. 

Although similar failures have not 

been reported on Agusta helicopters, T/ 

R blade P/N 212–010–750 may be 

installed on Agusta Model AB205A1, 

AB212, AB412, and AB412 EP 

helicopters. As a result, EASA, which is 

the Technical Agent for the Member 

States of the European Union, issued 

AD No. 2013–0185, dated August 14, 

2013, to correct an unsafe condition for 

Agusta Model AB205A1, AB212, 

AB412, and AB412 EP helicopters. 

EASA advised that Bell reported some 

failures in T/R blade P/N 212–010–750 

(all dash numbers), which originated 

from a fatigue crack derived from 

surface damages. EASA consequently 

requires detailed visual inspections of 

the T/R blade surface for nicks, dents, 

scratches, corrosion or cracks. EASA 

also requires repair or replacement of 

the T/R blade, depending on the 

outcome of those inspections. 

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 


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13200 Federal Register / Vol. 79, No. 46 / Monday, March 10, 2014 / Rules and Regulations 

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 that 

the unsafe condition exists and is likely 

to exist or develop on other helicopters 

of these same type designs. 

Related Service Information 

AgustaWestland, formerly Agusta 

S.p.A., issued Bollettino Tecnico No. 

412–136, dated August 13, 2013 (BT), 

for Model AB412 and Model AB412 EP 

helicopters. The BT calls for visually 

inspecting the T/R blade surface for a 

crack, corrosion, a nick, a scratch, a 

dent, or other damage using a 3X 

magnifying glass every 25 hours time-inservice (TIS) or 30 days, whichever 

occurs first. The BT also calls for a 

recurring detailed visual inspection of 

the blade surface with a 10X magnifying 

glass between stations 20.00 to 35.00 

from the T/R blade’s leading edge to the 

trailing edge. If paint blistering, peeling, 

flaking, bubbling, or cracking exists, the 

BT calls for removing the paint and 

inspecting the affected area with a 10X 

magnifying glass. If a nick, scratch or 

dent exists, the BT calls for a visual 

inspection for a crack with a 10X 

magnifying glass and measuring any 

damage. If skin damages exceed 

maintenance manual limits or if a crack 

exists, the BT calls for removing the 

blade from service. 

AD Requirements 

This AD requires within 25 hours TIS 

or 30 days, whichever occurs first, and 

thereafter at intervals not to exceed 25 

hours TIS or 30 days, whichever occurs 

first: 

• Cleaning each T/R blade by hand 

and, using a 3X or higher power 

magnifying glass and a light, visually 

inspecting the T/R blade skins, leading 

edge spar, doublers, grip plates, and 

trailing edge on both sides of each blade 

for a crack, corrosion, a nick, scratch, 

dent, or other damage. This inspection 

requires you to pay particular attention 

to the area located between blade station 

20.00 to 35.00 and to the inboard T/R 

blade butt area near the attachment of 

the external balance weight and screws. 

• Using a 10X or higher magnifying 

glass and a light, visually inspecting 

both sides of each blade for a crack or 

other damage between blade station 

20.00 to 35.00. 

• If blistering, peeling, flaking, 

bubbling, or cracked paint is detected 

anywhere on the blade, removing the 

paint and then visually inspecting the 

affected area for any corrosion or a crack 

using a 10X or higher magnifying glass 

and a light. 

• If a nick, scratch, or dent is found 

anywhere on the blade, visually 

inspecting for a crack using a 10X or 

higher power magnifying glass and a 

light. 

• Before further flight, removing from 

service any T/R blade that has a crack 

or that has corrosion, a nick, a scratch, 

a dent, or other damage that exceeds any 

of the maximum repair limits. 

• Before further flight, repairing or 

removing from service any T/R blade 

that has any corrosion, nick, scratch, 

dent or other damage that is within the 

maximum repair limits. 

Differences Between This AD and the 

EASA AD 

The EASA AD applies to Agusta 

Model AB205A1 and AB212 

helicopters. This AD does not because 

these helicopters have no FAA type 

certificate. This AD requires paying 

particular attention to both sides of each 

T/R blade in the area located 16 to 32 

inches from the T/R blade tip when 

conducting the inspection using a 3X or 

higher power magnifying glass and a 

light. The EASA AD makes no such 

requirement. 

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 no helicopters on the U.S. 

registry and that good cause exists for 

making this amendment effective in less 

than 30 days. 

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: 

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): 

2014–04–13 Agusta S.p.A. Helicopters: 

Amendment 39–17772; Docket No. 

FAA–2014–0109; Directorate Identifier 

2013–SW–049–AD. 

(a) Applicability 

This AD applies to Agusta S.p.A. (Agusta) 

Model AB412 and AB412 EP helicopters with 

a tail rotor blade (T/R) blade, part number 


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Federal Register / Vol. 79, No. 46 / Monday, March 10, 2014 / Rules and Regulations 13201 

(P/N) 212–010–750 (all dash numbers), 

installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

fatigue cracking of a T/R blade, which could 

lead to failure of the T/R blade and 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective March 25, 2014. 

(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 25 hours time-in-service (TIS) or 

30 days, whichever occurs first, and 

thereafter at intervals not to exceed 25 hours 

TIS or 30 days, whichever occurs first: 

(i) Clean each T/R blade by hand using a 

mild soap and cheesecloth on both sides of 

the blade in a spanwise direction and dry 

thoroughly. 

(ii) Using a 3X or higher power magnifying 

glass and a light, visually inspect the T/R 

blade skin, leading edge spar, doublers, grip 

plates, and trailing edge on both sides of each 

blade for a crack, corrosion (which may be 

indicated by blistering, peeling, flaking, 

bubbling, or cracked paint), a nick, a scratch, 

a dent, or other damage. Pay particular 

attention to both sides of each T/R blade in 

the area located 16 to 32 inches from the T/ 

R blade tip (blade station 20.00 to 35.00; the 

T/R blade tip is located at blade station 51) 

as depicted by the shaded area in Figure 2 

of AgustaWestland Bollettino Tecnico No. 

412–136, dated August 13, 2013 (BT). Also, 

pay particular attention to the inboard T/R 

blade butt area near the attachment of the 

external balance weight and screws and to 

any T/R blade surface that was snagged by 

cheesecloth, as this may be an indication of 

a crack or paint chip that could lead to 

corrosion. 

(iii) Using a 10X or higher power 

magnifying glass and a light, visually inspect 

both sides of each T/R blade for a crack, 

corrosion (which may be indicated by 

blistering, peeling, flaking, bubbling, or 

cracked paint), a nick, a scratch, a dent or 

other damage between blade station 20.00 to 

35.00 as depicted by the shaded area in 

Figure 2 of the BT. 

(iv) If there is any blistering, peeling, 

flaking, bubbling, or cracked paint on a T/R 

blade, remove the paint from the affected 

area by sanding in a spanwise direction first 

with abrasive cloth or paper 240-grit or finer 

and then with abrasive cloth or paper 400- 

grit or finer. After paint removal, wipe area 

with a clean cloth dampened with alcohol 

and dry thoroughly and then visually inspect 

the affected area for any corrosion or a crack 

using a 10X or higher power magnifying glass 

and a light. If any corrosion is found, 

measure the depth of the damage. 

(v) If there is a nick, scratch, or dent on the 

T/R blade, visually inspect for a crack using 

a 10X or higher power magnifying glass and 

a light. Measure the depth of the damage. 

(2) Before further flight, remove from 

service any T/R blade that has a crack, 

corrosion, a nick, a scratch, a dent, or other 

damage that exceeds any of the maximum 

repair damage limits. 

(3) Before further flight, repair or remove 

from service any T/R blade that has 

corrosion, a nick, a scratch, a dent or other 

damage that is within the maximum repair 

damage limits. 

(4) Do not install on any helicopter T/R 

blade P/N 212–010–750 (all dash numbers) 

unless it has been inspected in accordance 

with the requirements of this AD. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, FAA, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; telephone (817) 222– 

5110; email robert.grant@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 

The subject of this AD is addressed in the 

European Aviation Safety Agency (EASA) 

AD. No. 2013–0185, dated August 14, 2013. 

You may view the EASA AD on the Internet 

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

FAA–2014–0109. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6410, tail rotor blades. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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. 

412–136, dated August 13, 2013. 

(ii) Reserved. 

(3) 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. 

(4) 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. 

(5) 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 February 

20, 2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–04274 Filed 3–7–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0554; Directorate 

Identifier 2012–SW–009–AD; Amendment 

39–17774; AD 2014–05–01] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Eurocopter Deutschland GmbH 

(Eurocopter) Model EC135P1, EC135P2, 

EC135P2+, EC135T1, EC135T2, and 

EC135T2+ helicopters. This AD requires 

analyzing the main gearbox (MGB) oil 

for indications of metal chips or pieces, 

reviewing the MGB log or equivalent 

record, and inspecting certain teeth in 

the MGB after two chip indications. 

This AD was prompted by a partial 

tooth rupture found in an MGB that was 

returned to the manufacturer for repairs. 

The actions of this AD are intended to 

detect wear in the MGB that could lead 

to a gear tooth rupture, failure of the 

MGB, loss of power to the main rotor, 

and subsequent loss of control of the 

helicopter. 

DATES: This AD is effective April 14, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of April 14, 2014. 

ADDRESSES: For service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http://

www.eurocopter.com/techpub. 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. 


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