21234 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 

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 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 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): 

2016–08–07 Rolls-Royce plc: Amendment 

39–18483; Docket No. FAA–2015–4076; 

Directorate Identifier 2015–NE–30–AD. 

(a) Effective Date 

This AD becomes effective May 16, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Rolls-Royce plc RB211– 

22B–02, RB211–22B (MOD 72–8700), RB211– 

524B–02, RB211–524B–B–02, RB211–524B2– 

19, RB211–524B2–B–19, RB211–524B3–02, 

RB211–524B4–02, RB211–524B4–D–02, 

RB211–524C2–19, RB211–524C2–B–19, 

RB211–524D4–19, RB211–524D4–B–19, 

RB211–524D4X–19, RB211–524D4X–B–19, 

RB211–524D4–39, RB211–524D4–B–39, 

RB211–524G2–19, RB211–524G3–19, 

RB211–524–G2–T–19, RB211–524G3–T–19, 

RB211–524H–36, RB211–524H2–19, RB211– 

524H–T–36, and RB211–524H2–T–19 

turbofan engines, all serial numbers, with 

low-pressure turbine (LPT) support roller 

bearing, part number (P/N) LK30313 or P/N 

UL29651, installed. 

(d) Reason 

This AD was prompted by a report of a 

breach of the turbine casing and release of 

engine debris through a hole in the engine 

nacelle. We are issuing this AD to prevent 

failure of the LPT support roller bearing, loss 

of radial position following LPT blade 

failure, uncontained part release, damage to 

the engine, and damage to the airplane. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. At the next shop visit or within 24 

months after the effective date of this AD, 

whichever occurs first, remove from service 

LPT support roller bearing, P/N LK30313 or 

P/N UL29651, and replace with a part 

eligible for installation. 

(f) Installation Prohibition 

After the effective date of this AD, do not 

install an LPT support roller bearing, P/N 

LK30313 or P/N UL29651, onto any engine. 

(g) Definition 

For the purpose of this AD, a ‘‘shop visit’’ 

is defined as induction of an engine into the 

shop for maintenance involving the 

separation of pairs of major mating engine 

flanges, except that the separation of engine 

flanges solely for the purposes of 

transportation without subsequent engine 

maintenance does not constitute an engine 

shop visit. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. You may email your 

request to: ANE-AD-AMOC@faa.gov. 

(i) Related Information 

(1) For more information about this AD, 

contact Brian Kierstead, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7772; fax: 781–238–7199; email: 

brian.kierstead@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2015–0187, dated 

September 9, 2015, for more information. 

You may examine the MCAI in the AD 

docket on the Internet at http:// 

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2015–4076. 

(j) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

April 4, 2016. 

Colleen M. D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–08092 Filed 4–8–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4112; Directorate 

Identifier 2014–SW–043–AD; Amendment 

39–18471; AD 2016–07–26] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (previously Eurocopter 

France) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2010–23– 

02 for Eurocopter France (now Airbus 

Helicopters) Model SA–365N, SA– 

365N1, AS–365N2, and AS 365 N3 

helicopters. AD 2010–23–02 required 

amending the Limitations section of the 

Rotorcraft Flight Manual (RFM) to limit 

the never-exceed velocity (VNE) to 150 

Knots Indicated Air Speed (KIAS) and 

to add a 1,500 ft/minute rate of descent 

(R/D) limitation beyond 140 KIAS. 

Since we issued AD 2010–23–02, a 

design change designated as 

modification (MOD) 0755B28 improved 

the dynamic behavior of the horizontal 

stabilizer such that AD actions are not 

required. This new AD retains the 

requirements of AD 2010–23–01 and 

revises the applicability to exclude 

helicopters with MOD 0755B28. We are 

issuing this AD to exclude certain 

helicopters from the applicability and 

restrict the VNE on other helicopters to 

prevent failure of the horizontal 

stabilizer and subsequent loss of control 

of the helicopter. 

DATES: This AD is effective May 16, 

2016. 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 21235 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Helicopters, Inc., 2701 N. Forum 

Drive, Grand Prairie, TX 75052; 

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

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

www.airbushelicopters.com/techpub. 

You may view this referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy., Room 6N–321, 

Fort Worth, Texas 76177. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov in Docket No. 

FAA–2015–4112; or in person at the 

Docket Management Facility 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, the 

economic evaluation, any comments 

received, and other information. The 

address for the Docket Office (phone: 

800–647–5527) is 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 FURTHER INFORMATION CONTACT: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 10101 

Hillwood Pkwy., Fort Worth, Texas 

76177; telephone (817) 222–5110; email 

robert.grant@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to remove AD 2010–23–02, 

Amendment 39–16491 (75 FR 68169, 

November 5, 2010) and add a new AD. 

AD 2010–23–02 applied to Eurocopter 

France (now Airbus Helicopters) Model 

SA 365N, SA–365N1, AS 365N2, and 

AS 365 N3 helicopters. AD 2010–23–02 

required amending the Limitations 

section of the RFM to limit the VNE to 

150 KIAS and to add a 1,500 ft/minute 

R/D limitation beyond 140 KIAS and 

installing one or more placards on the 

cockpit instrument panel in full view of 

the pilot and copilot. AD 2010–23–01 

was prompted by AD No. 2008–0204R1, 

Revision 1, dated May 21, 2014, issued 

by EASA, which is the Technical Agent 

for the Member States of the European 

Union. EASA advises that Airbus 

Helicopters developed MOD 07 55B28 

to improve the dynamic behavior of the 

horizontal stabilizer and thus reduce the 

vibration levels during high speed 

descent. EASA issued AD No. 2008– 

0204R1 to retain the requirements of its 

previous AD but to exclude helicopters 

with MOD 07 55B28 from the 

applicability. 

The NPRM published in the Federal 

Register on October 19, 2015 (80 FR 

63145). The NPRM proposed to retain 

the requirements to amend the 

Limitations section of the RFM and 

install one or more placards on the 

cockpit instrument panel. The NPRM 

also proposed to revise the applicability 

to exclude helicopters with MOD 

0755B28 installed. The proposed 

requirements were intended to exclude 

certain helicopters from the 

applicability and restrict the VNE on 

other helicopters to prevent failure of 

the horizontal stabilizer and subsequent 

loss of control of the helicopter. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (80 FR 63145, October 19, 2015). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of France and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, EASA, its 

technical representative, has notified us 

of the unsafe condition described in its 

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 the same 

type designs and that air safety and the 

public interest require adopting the AD 

requirements as proposed. 

Related Service Information 

Eurocopter has issued an Emergency 

Alert Service Bulletin (EASB) with three 

numbers (01.00.60, 01.00.16, and 01.28), 

Revision 1, dated December 2, 2008. 

EASB No. 01.00.60 applies to U.S. typecertificated Model SA–365N, SA– 

365N1, AS–365N2, and AS 365 N3 

helicopters and also to military Model 

AS365F, Fs, Fi, and K helicopters that 

are not type certificated in the United 

States. EASB 01.00.16 applies to 

military Model AS565AA, MA, MB, SA, 

SB, and UB helicopters that are not type 

certificated in the United States. EASB 

01.28 applies to the Model SA–366G1 

helicopter. The EASB specifies bonding 

one or more locally-produced labels to 

the instrument panel stating that the 

VNE is limited to 150 KIAS and the R/ 

D must not exceed 1,500 ft/min beyond 

140 KIAS. Eurocopter states in the 

EASB that it is working on an enhanced 

definition that will be proposed as soon 

as possible. EASA classified this EASB 

as mandatory and issued AD No. 2008– 

0204–E, dated December 4, 2008, and 

revised with Revision 1, dated May 21, 

2014, to ensure the continued 

airworthiness of these helicopters. 

Airbus Helicopters has issued Service 

Bulletin (SB) No. AS365–55.00.06, 

Revision 0, dated November 14, 2014, 

which Airbus Helicopters identifies as 

MOD 0755B28. The SB specifies 

repairing the stabilizer for suppression 

of the flutter phenomenon. 

Costs of Compliance 

We estimate that this AD will affect 

33 helicopters of U.S. Registry. We 

estimate that operators may incur the 

following costs in order to comply with 

this AD. Labor costs are estimated at $85 

per work-hour. We estimate about l

⁄2

work-hour per helicopter to make copies 

to include in the RFM and to make and 

install the placards. The parts costs are 

minimal. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators will be $1,403 for the fleet. 

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 have 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 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 


jstallworth on DSK7TPTVN1PROD with RULES
21236 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 

(3) Will not affect intrastate aviation 

in Alaska to the extent that a regulatory; 

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 

removing Airworthiness Directive (AD) 

2010–23–02, Amendment 39–16491 (75 

FR 68169, November 5, 2010), and 

adding the following new AD: 

2016–07–26 Airbus Helicopters (previously 

Eurocopter France): Amendment 39– 

18471; Docket No. FAA–2015–4112; 

Directorate Identifier 2014–SW–043–AD. 

(a) Applicability 

This AD applies to Model SA–365N, SA– 

365N1, AS–365N2, and AS 365 N3 

helicopters, with a horizontal stabilizer, part 

number 365A13–3030–1901, –1902, –1903, 

–1904, –1905, –1906, –1908, –1909; 365A13– 

3036–00, –0001, –0002, –0003; or 365A13– 

3038–00, installed, except those with 

modification 0755B28 installed, certificated 

in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

vibration during descent at high speed. This 

condition could result in failure of the 

horizontal stabilizer and subsequent loss of 

control of the helicopter. 

(c) Affected ADs 

This AD replaces AD 2010–23–02, 

Amendment 39–16491 (75 FR 68169, 

November 5, 2010). 

(d) Effective Date 

This AD becomes effective May 16, 2016. 

(e) 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. 

(f) Required Actions 

Before further flight: 

(1) Revise the airspeed operating limitation 

in the Limitations section of the Rotorcraft 

Flight Manual (RFM) by making pen and ink 

changes or by inserting a copy of this AD into 

the RFM stating: ‘‘The never-exceed speed 

(VNE) is limited to 150 knots indicated 

airspeed (KIAS)’’ and ‘‘The rate-of-descent 

(R/D) must not exceed 1,500 ft/min when the 

airspeed is beyond 140 KIAS.’’ 

(2) Install one or more self-adhesive 

placards, with 6 millimeter red letters on 

white background, on the cockpit instrument 

panel in full view of the pilot and co-pilot 

to read as follows: ‘‘VNE LIMITED TO 150 

KIAS’’ and ‘‘R/D MUST NOT EXCEED 1,500 

ft/min when airspeed is beyond 140 KIAS’’ 

(g) 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, Rotorcraft Directorate, FAA, 10101 

Hillwood Pkwy., Fort Worth, Texas 76177; 

telephone (817) 222–5110; email 9-asw-ftwamoc-requests@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) Eurocopter Emergency Alert Service 

Bulletin (EASB) No. 01.00.60, 01.00.16, and 

01.28, Revision 1, dated December 2, 2008, 

and Airbus Helicopters Service Bulletin No. 

AS365–55.00.06, Revision 0, dated November 

14, 2014, which are not incorporated by 

reference, contain additional information 

about the subject of this final rule. For 

service information identified in this final 

rule, contact Airbus Helicopters, Inc., 2701 

N. Forum Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232–0323; 

fax (972) 641–3775; or at http:// 

www.airbushelicopters.com/techpub. You 

may review a copy of the service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2008–0204R1, dated May 21, 2014. You 

may view the EASA AD on the Internet at 

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

FAA–2015–4112. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code 5310: Horizontal Stabilizer Structure. 

Issued in Fort Worth, Texas, on March 31, 

2016. 

James A. Grigg, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–07981 Filed 4–8–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA-2014-0775; Directorate 

Identifier 2014–NM–046–AD; Amendment 

39–18467; AD 2016–07–22] 

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 all 

Airbus Model A300 B4–600, B4–600R, 

and F4–600R series airplanes, Model 

A300 C4–605R Variant F airplanes 

(collectively called Model A300–600 

series airplanes), and Model A310 series 

airplanes. This AD was prompted by 

reports of insufficient clearance for the 

electrical wiring bundles in the leading 

and trailing edges of the right-hand (RH) 

and left-hand (LH) wings. This AD 

requires modifying the electrical routing 

installation at the RH and LH wings. We 

are issuing this AD to prevent 

insufficient clearance of electrical 

wiring bundles located in the leading 

and trailing edges of the RH and LH 

wings, which could lead to chafing 

damage and arcing, possibly resulting in 

an on-board fire. 

DATES: This AD becomes effective May 

16, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of May 16, 2016. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0775; 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. 

For service information identified in 

this final rule, contact Airbus SAS, 

Airworthiness Office—EAW, 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. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 


jstallworth on DSK7TPTVN1PROD with RULES