Federal Register / Vol. 81, No. 86 / Wednesday, May 4, 2016 / Rules and Regulations 26675 

717–55A0012, dated June 12, 2015, except as 

required by paragraph (i)(2) of this AD. Do all 

applicable related investigative and 

corrective actions before further flight. 

Repeat the applicable inspection thereafter at 

the intervals specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 717–55A0012, dated June 12, 2015. 

(1) Do detailed inspections for any loose 

and missing fasteners of the vertical stabilizer 

leading edge as specified in ‘‘Part 4’’ of 

Boeing Alert Service Bulletin 717–55A0012, 

dated June 12, 2015. 

(2) Do eddy current testing high frequency 

(ETHF) and radiographic testing (RT) 

inspections for any crack of the vertical 

stabilizer spar cap as specified in ‘‘Part 2’’ of 

Boeing Alert Service Bulletin 717–55A0012, 

dated June 12, 2015; or do ETHF inspections 

for any crack of the vertical stabilizer spar 

cap as specified in ‘‘Part 3’’ of Boeing Alert 

Service Bulletin 717–55A0012, dated June 

12, 2015. 

(i) Exceptions to the Service Information 

(1) Where Boeing Alert Service Bulletin 

717–55A0012, dated June 12, 2015 specifies 

a compliance time ‘‘after the original issue 

date of this service bulletin,’’ this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) If any crack is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 717–55A0012, dated 

June 12, 2015, specifies to contact Boeing for 

appropriate action: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

initial inspection specified in paragraph (g) 

of this AD, if that inspection was performed 

before the effective date of this AD using 

Boeing MOM–MOM–14–0437–01B(R1), 

dated July 3, 2014, which is not incorporated 

by reference in this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 

paragraph (l) of this AD. Information may be 

emailed to: 9-ANM-LAACO-AMOCRequests@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, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(l) Related Information 

For more information about this AD, 

contact Eric Schrieber, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles ACO, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5348; fax: 562–627–5210; email: 

Eric.Schrieber@faa.gov. 

(m) 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) Boeing Alert Service Bulletin 717– 

55A0012, dated June 12, 2015. 

(ii) Reserved. 

(3) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, 3855 Lakewood 

Boulevard, MC D800–0019, Long Beach, CA 

90846–0001; telephone: 206–544–5000, 

extension 2; fax: 206–766–5683; Internet: 

https://www.myboeingfleet.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(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 Renton, Washington, on April 20, 

2016. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–10160 Filed 5–3–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–7490; Directorate 

Identifier 2015–NE–40–AD; Amendment 39– 

18500; AD 2016–09–02] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Turbomeca S.A. Astazou XIV B and H 

turboshaft engines. This AD requires a 

one-time inspection of the front surface 

of the 3rd stage turbine for a groove. 

This AD was prompted by a report of a 

crack on the 3rd stage turbine wheel. 

We are issuing this AD to prevent cracks 

in the 3rd stage turbine wheel, failure of 

the engine, in-flight shutdown, and loss 

of control of the helicopter. 

DATES: This AD becomes effective June 

8, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 8, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Turbomeca S.A., 40220 Tarnos, France; 

phone: 33 (0)5 59 74 40 00; fax: 33 (0)5 

59 74 45 15. You may view this service 

information at the FAA, Engine & 

Propeller Directorate, 1200 District 

Avenue, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

It is also available on the Internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2015– 

7490. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

7490; 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 mandatory 

continuing airworthiness information 

(MCAI), the regulatory 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: 

Wego Wang, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7134; fax: 781–238–7199; 

email: wego.wang@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 


asabaliauskas on DSK3SPTVN1PROD with RULES
26676 Federal Register / Vol. 81, No. 86 / Wednesday, May 4, 2016 / Rules and Regulations 

NPRM was published in the Federal 

Register on February 2, 2016 (81 FR 

5395). The NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During the overhaul of an ASTAZOU XIV 

engine, a crack was detected on the front face 

of the third stage turbine wheel between two 

balancing lugs. The cause of the crack is 

probably linked to a geometric singularity, 

likely caused by the transformation operation 

aimed at introducing expansion slots 

between the blades during embodiment of 

Turbomeca mod AB 173. Although there is 

only one known case of this type of crack, 

and although it was detected, the possibility 

exists that additional parts have the same 

geometric singularity. 

This condition, if not detected and 

corrected, may lead to failure of a turbine 

blade and its associated piece of rim, 

possibly resulting in an uncommanded inflight shut-down and/or release of high 

energy debris. 

You may obtain further information 

by examining the MCAI in the AD 

docket on the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

7490. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (81 

FR 5395, February 2, 2016). 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Related Service Information Under 1 

CFR Part 51 

Turbomeca S.A. has issued Service 

Bulletin (SB) No. 283 72 0811, Version 

A, dated August 25, 2015. The SB 

describes procedures for inspection of 

the 3rd stage turbine wheel. This service 

information is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 9 

engines installed on helicopters of U.S. 

registry. We also estimate that it will 

take about 5 hours per engine to comply 

with this AD. The average labor rate is 

$85 per hour. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $3,825. 

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 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): 

2016–09–02 Turbomeca S.A.: Amendment 

39–18500; Docket No. FAA–2015–7490; 

Directorate Identifier 2015–NE–40–AD. 

(a) Effective Date 

This AD becomes effective June 8, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Astazou XIV B and 

XIV H turboshaft engines with 3rd stage 

turbine wheel, part number (P/N) 0 265 25 

700 0 or P/N 0 265 25 706 0, installed, if the 

engine incorporates Turbomeca modification 

AB–173 or AB–208. 

(d) Reason 

This AD was prompted by a report of a 

crack on the 3rd stage turbine wheel. We are 

issuing this AD to prevent cracks in the 3rd 

stage turbine wheel, failure of the engine, inflight shutdown, and loss of control of the 

helicopter. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) At the next piece part exposure of the 

3rd stage turbine wheel or within 1,000 

engine hours after the effective date of this 

AD whichever comes first, perform a onetime inspection for a groove on the front 

surface of the 3rd stage turbine wheel. Use 

Accomplishment Instructions, paragraph 

4.4.2, of Turbomeca S.A. Service Bulletin 

(SB) No. 283 72 0811, Version A, dated 

August 25, 2015 to perform the inspection. 

(2) If the 3rd stage turbine wheel passes 

inspection required by paragraph (e)(1) of 

this AD, no further action is required. 

(3) If the 3rd stage turbine wheel fails 

inspection required by paragraph (e)(1) of 

this AD, remove the part and replace with a 

part eligible for installation. 

(f) Installation Prohibition 

After the effective date of this AD, do not 

install any 3rd stage turbine wheel, P/N 0 265 

25 700 0 or P/N 0 265 25 706 0, unless it was 

inspected per the Accomplishment 

Instructions, paragraph 4.4.2, of Turbomeca 

S.A. SB No. 283 72 0811, Version A, dated 

August 25, 2015. 

(g) 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. 

(h) Related Information 

(1) For more information about this AD, 

contact Wego Wang, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7134; fax: 781–238–7199; email: 

wego.wang@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2015–0223, dated 

November 16, 2015, for more information. 

You may examine the MCAI in the AD 


asabaliauskas on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 81, No. 86 / Wednesday, May 4, 2016 / Rules and Regulations 26677 

docket on the Internet at http:// 

www.regulations.gov/ 

#!documentDetail;D=FAA-2015-7490-0001. 

(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) Turbomeca S.A. Service Bulletin No. 

283 72 0811, Version A, dated August 25, 

2015. 

(ii) Reserved. 

(3) For Turbomeca S.A. service information 

identified in this AD, contact Turbomeca 

S.A., 40220 Tarnos, France; phone: 33 (0)5 59 

74 40 00; fax: 33 (0)5 59 74 45 15. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 1200 

District Avenue, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

(5) You may 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/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

April 21, 2016. 

Colleen M. D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–10279 Filed 5–3–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–5811; Directorate 

Identifier 2014–NM–158–AD; Amendment 

39–18489; AD 2016–08–13] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2004–19– 

11 for certain Airbus Model A320 series 

airplanes. AD 2004–19–11 required 

modification of the inner rear spar web 

of the wing, cold expansion of the 

attachment holes of the forward pintle 

fitting and the actuating cylinder 

anchorage of the main landing gear 

(MLG), repetitive ultrasonic inspections 

for cracking of the rear spar of the wing, 

and corrective action if necessary. AD 

2004–19–11 also provided optional 

terminating action for the repetitive 

inspections. This new AD retains the 

requirements of AD 2004–19–11, and 

requires the previously optional 

terminating action. This AD was 

prompted by a determination that the 

previously optional terminating action 

is necessary to address the unsafe 

condition. We are issuing this AD to 

prevent fatigue cracking of the inner 

rear spar, which may lead to reduced 

structural integrity of the wing and the 

MLG. 

DATES: This AD becomes effective June 

8, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 8, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 5, 2004 (69 FR 58828, 

October 1, 2004). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of June 30, 2000 (65 FR 

34069, May 26, 2000). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 14, 1994 (59 FR 1903, 

January 13, 1994). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of June 11, 1993 (58 FR 

27923, May 12, 1993). 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus, Airworthiness Office—EIAS, 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 

FAA, call 425–227–1221. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

5811. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

5811; 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 regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is 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 FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

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 supersede AD 2004–19–11, 

Amendment 39–13805 (69 FR 58828, 

October 1, 2004) (‘‘AD 2004–19–11’’). 

AD 2004–19–11 applied to certain 

Airbus Model 320 series airplanes. The 

NPRM published in the Federal 

Register on November 27, 2015 (80 FR 

74058) (‘‘the NPRM’’). The NPRM was 

prompted by a determination that the 

previously optional terminating action 

is necessary to address the unsafe 

condition. The NPRM proposed to 

retain the requirements of AD 2004–19– 

11, and requires the previously optional 

terminating action. We are issuing this 

AD to prevent fatigue cracking of the 

inner rear spar, which may lead to 

reduced structural integrity of the wing 

and the MLG. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0169, dated July 17, 

2014, corrected July 22, 2014 (referred 

to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition on certain Airbus Model 320 

series airplanes. The MCAI states: 

During centre fuselage certification full 

scale fatigue test, cracks were found on the 

inner rear spar at holes position 52 on the 

right hand wing due to fatigue aspects. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

To prevent such cracks, Airbus developed 

modifications, which were introduced in 

production and in service through several 

Airbus Service Bulletins (SB). 

DGAC France issued * * * [an earlier AD], 

which was subsequently superseded by 

[DGAC] AD 2001–249 [which corresponds 

with FAA AD 2004–19–11, Amendment 39– 

13805 (69 FR 58828, October 1, 2004)], to 

require modification of the rear spar on some 


asabaliauskas on DSK3SPTVN1PROD with RULES