716 Federal Register / Vol. 82, No. 2 / Wednesday, January 4, 2017 / Rules and Regulations 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Service Bulletin A300–53–6176, 

dated May 20, 2015. 

(ii) Airbus Service Bulletin A300–53–6177, 

dated May 20, 2015. 

(3) For service information identified in 

this AD, 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. 

(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 

December 6, 2016. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–30117 Filed 1–3–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–0733; Directorate 

Identifier 2015–SW–040–AD; Amendment 

39–18762; AD 2016–26–04] 

RIN 2120–AA64 

Airworthiness Directives; Robinson 

Helicopter Company Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Robinson Helicopter Company 

(Robinson) Model R44, R44 II, and R66 

helicopters. This AD requires inspecting 

the main rotor blade (MRB). This AD 

was prompted by a determination that 

some MRBs may have reduced blade 

thickness due to blending out corrosion. 

The actions are intended to prevent the 

unsafe condition on these products. 

DATES: This AD is effective February 8, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of February 8, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Robinson Helicopter Company, 2901 

Airport Drive, Torrance, CA 90505; 

telephone (310) 539–0508; fax (310) 

539–5198; or at http:// 

www.robinsonheli.com. You may review 

a copy of the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy, Room 6N–321, 

Fort Worth, TX 76177. It is also 

available on the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

0733. 

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–2016– 

0733; 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 incorporated-byreference 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: Eric 

Schrieber, Aviation Safety Engineer, Los 

Angeles Aircraft Certification Office, 

Transport Airplane Directorate, FAA, 

3960 Paramount Blvd., Lakewood, 

California 90712; telephone (562) 627– 

5348; email eric.schrieber@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 27, 2016, at 81 FR 33609, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 by 

adding an AD that would apply to 

Robinson Model R44 and R44 II 

helicopters with an MRB part number 

(P/N) C016–7, Revision N/C, A through 

Z, and AA through AE; and Model R66 

helicopters with an MRB P/N F016–2, 

Revision A through E. The NPRM 

proposed to require a one-time visual 

inspection of the MRB for a crack, 

corrosion, dent, nick, and scratch and 

either altering the MRB or removing it 

from service. 

The NPRM was prompted by a report 

of a fatigue crack on a Model R44 II 

helicopter at the MRB trailing edge that 

had grown to reach the blade spar. The 

FAA subsequently determined that 

some MRBs may have reduced blade 

fatigue resistance due to repair by 

blending out corrosion in the area of the 

crack site radius. The proposed 

requirements were intended to prevent 

an MRB fatigue crack, which could lead 

to MRB failure and subsequent loss of 

helicopter control. 

Comments 

After our NPRM (81 FR 33609, May 

27, 2016) was published, we received a 

comment from one commenter. 

Request 

Robinson requested we change the 

applicability of the AD for part number 

(P/N) C016–7 from ‘‘Revision N/C, A 

through Z, and AA through AE’’ to 

‘‘Revision AA through AE.’’ Robinson 

stated that P/N C016–7 did not exist 

until Revision AA and suggested that 

some technicians may wrongfully apply 

the proposed AD to P/N C016–5 

Revisions W thru Z. 

We agree and have revised the AD 

accordingly. 

FAA’s Determination 

We have reviewed the relevant 

information, considered the comment 

received, and determined that an unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs and that air safety and the 

public interest require adopting the AD 

requirements as proposed with the 

change previously described. This 

change is consistent with the intent of 

the proposals in the NPRM (81 FR 

33609, May 27, 2016) and will not 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Robinson R44 Service 

Bulletin SB–89, dated March 30, 2015 

(SB–89), for Model R44 and R44 II 

helicopters and Robinson R66 Service 

Bulletin SB–13, dated March 30, 2015 

(SB–13), for Model R66 helicopters. SB– 

89 and SB–13 provide a one-time 

procedure to inspect each MRB for 

cracks, corrosion, and damage that may 

indicate a crack. If there is a crack, 

corrosion, or any damage, SB–89 and 

SB–13 specify removing the MRB from 

service and contacting Robinson. 

Otherwise, SB–89 and SB–13 describe 

procedures to smooth the transition at 

the chord increase of each MRB to 

reduce the stress concentration. 

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. 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 82, No. 2 / Wednesday, January 4, 2017 / Rules and Regulations 717 

Differences Between This AD and the 

Service Information 

This AD requires compliance within 

the next 100 hours time-in-service (TIS) 

or at the next annual inspection, 

whichever occurs first. The service 

information recommends compliance 

within 15 hours TIS or by May 31, 2015, 

whichever occurs first, for the R44 and 

R44 II helicopters and 10 hours TIS or 

by May 31, 2015, whichever occurs first, 

for the R66 helicopters. 

Costs of Compliance 

We estimate that this AD affects 2,236 

helicopters of U.S. Registry and that 

labor costs average $85 per work hour. 

Based on these estimates, we expect the 

following costs: 

• The visual inspection requires 1 

work hour. No parts are needed, so the 

cost per helicopter totals $85. The cost 

for the U.S. fleet totals $190,060. 

• Altering each MRB, if necessary, 

requires 2 work hours and $65 for parts. 

We estimate a total cost of $235 per 

helicopter and $525,460 for the U.S. 

fleet. 

• Replacing an MRB, if necessary, 

requires 3 work hours. Parts cost 

$19,900 for the Model R44 and R44 II 

and $20,900 for the R66 helicopter for 

a total cost of $20,155 and $21,155, 

respectively, per MRB. 

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 

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 adding 

the following new airworthiness 

directive (AD): 

2016–26–04 Robinson Helicopter Company: 

Amendment 39–18762; Docket No. 

FAA–2016–0733; Directorate Identifier 

2015–SW–040–AD. 

(a) Applicability 

This AD applies to Robinson Helicopter 

Company (Robinson) Model R44 and R44 II 

helicopters with a main rotor blade (MRB) 

part number (P/N) C016–7, Revision AA 

through AE installed; and Model R66 

helicopters with a MRB P/N F016–2, 

Revision A through E, installed; certificated 

in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

fatigue crack on an MRB. This condition 

could result in failure of an MRB and loss of 

helicopter control. 

(c) Effective Date 

This AD becomes effective February 8, 

2017. 

(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 

Within 100 hours time-in-service or at the 

next annual inspection, whichever occurs 

first: 

(1) Clean each MRB in the area depicted in 

Figure 1 of Robinson R44 Service Bulletin 

SB–89, dated March 30, 2015 (SB–89), or 

Robinson R66 Service Bulletin SB–13, dated 

March 30, 2015 (SB–13), as applicable to 

your model helicopter. 

(2) Using 10X or higher power 

magnification and a light, visually inspect 

the upper and lower MRB surfaces and 

trailing edge as depicted in Figure 1 of SB– 

89 or SB–13, whichever applies to your 

helicopter, for a crack, a nick, a scratch, a 

dent, or corrosion. If there is a crack, a nick, 

a scratch, a dent, or any corrosion, repair the 

MRB to an airworthy configuration if the 

damage is within the maximum repair 

damage limits or remove the MRB from 

service. 

(3) Alter the MRB in accordance with 

Compliance Procedure, paragraphs 4 through 

19, of SB–89 or SB–13, as applicable to your 

model helicopter. Equivalent tubing may be 

used for R7769–1 and R7769–6 tubes. Power 

tools may not be used for this procedure. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

Eric Schrieber, Aviation Safety Engineer, Los 

Angeles Aircraft Certification Office, 

Transport Airplane Directorate, FAA, 3960 

Paramount Blvd., Lakewood, California 

90712; telephone (562) 627–5348; email 9- 

ANM-LAACO-AMOC-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. 

(g) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6210, Main Rotor Blades. 

(h) 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) Robinson R44 Service Bulletin SB–89, 

dated March 30, 2015. 

(ii) Robinson R66 Service Bulletin SB–13, 

dated March 30, 2015. 

(3) For Robinson Helicopter Company 

service information identified in this AD, 

contact Robinson Helicopter Company, 2901 

Airport Drive, Torrance, CA 90505; telephone 

(310) 539–0508; fax (310) 539–5198; or at 

http://www.robinsonheli.com. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy, 


jstallworth on DSK7TPTVN1PROD with RULES
718 Federal Register / Vol. 82, No. 2 / Wednesday, January 4, 2017 / Rules and Regulations 

Room 6N–321, Fort Worth, TX 76177. 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 December 

15, 2016. 

Stephen Barbini, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–30832 Filed 1–3–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–9109; Directorate 

Identifier 2016–NM–011–AD; Amendment 

39–18761; AD 2016–26–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Defense and Space S.A. (Formerly 

Known as Construcciones 

Aeronauticas, S.A.) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2013–23– 

02 for all Airbus Defense and Space S.A. 

Model CN–235, CN–235–100, CN–235– 

200, CN–235–300, and C–295 airplanes. 

AD 2013–23–02 required an inspection 

of the feeder cables of certain fuel 

booster pumps for damage (including, 

but not limited to, signs of electrical 

arcing and fuel leaks), and replacement 

if necessary. This new AD retains those 

requirements and also requires 

modification of the electrical 

installation of the fuel booster pumps. 

This AD was prompted by a report of an 

in-flight problem with the fuel transfer 

system. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective February 8, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 8, 2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of December 2, 2013 (78 FR 

68688, November 15, 2013). 

ADDRESSES: For service information 

identified in this final rule, contact 

EADS CASA (Airbus Defense and 

Space), Services/Engineering Support, 

Avenida de Arago ́n 404, 28022 Madrid, 

Spain; telephone: +34 91 585 55 84; fax: 

+34 91 585 31 27; email: 

MTA.TechnicalService@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–2016– 

9109. 

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–2016– 

9109; 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: 

Shahram Daneshmandi, Aerospace 

Engineer, International Branch, ANM– 

116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; telephone: 425–227– 

1112; fax: 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2013–23–02, 

Amendment 39–17657 (78 FR 68688, 

November 15, 2013) (‘‘AD 2013–23– 

02’’). AD 2013–23–02 applied to all 

Airbus Defense and Space S.A. Model 

CN–235, CN–235–100, CN–235–200, 

CN–235–300, and C–295 airplanes. The 

NPRM published in the Federal 

Register on September 19, 2016 (81 FR 

64080). The NPRM was prompted by a 

report of an in-flight problem with the 

fuel transfer system. The NPRM 

proposed to continue to require an 

inspection of the feeder cables of certain 

fuel booster pumps for damage 

(including, but not limited to, signs of 

electrical arcing and fuel leaks), and 

replacement if necessary. The NPRM 

also proposed to require modification of 

the electrical installation of the fuel 

booster pumps. We are issuing this AD 

to prevent damage to certain fuel 

booster pumps, which could create an 

ignition source in the fuel tank vapor 

space, and result in a fuel tank 

explosion and consequent loss of the 

airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2016–0014, 

dated January 14, 2016 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus Defense and Space S.A. 

Model CN–235, CN–235–100, CN–235– 

200, CN–235–300, and C–295 airplanes. 

The MCAI states: 

An occurrence with a CN–235 aeroplane 

was reported, involving an in-flight problem 

with the fuel transfer system. The results of 

the subsequent investigation revealed 

damage on the fuel booster pump electrical 

feeding cable and some burn marks on the 

pump body and plate (fairing) at the external 

side of the fuel tank; confirmed electrical 

arcing between the wire and pump body; and 

revealed fuel leakage onto the affected wire. 

This condition, if not detected and 

corrected, could create an ignition source in 

the fuel tank vapour space, possibly resulting 

in a fuel tank explosion and loss of the 

aeroplane. 

To address this potential unsafe condition, 

EADS CASA (Airbus Military) issued All 

Operators Letter (AOL) 235–025 and AOL 

295–025, providing inspection instructions 

for the affected fuel booster pumps, Part 

Number (P/N) 1C12–34 and P/N 1C12–46. 

Consequently, EASA issued AD 2013–0186 

[which corresponds to FAA AD 2013–23–02] 

to require a one-time [detailed visual] 

inspection of the affected fuel booster pumps 

to detect damage and, depending on findings, 

replacement of the fuel booster pump. That 

[EASA] AD also required reporting of all 

findings to EADS CASA for evaluation. 

Since that [EASA] AD was issued, Airbus 

Defence and Space (D&S) developed [a] 

modification of the fuel boost pump 

electrical installation, available for in-service 

application through Airbus D&S Service 

Bulletin (SB) 235–28–0023. That 

modification involves improved protection of 

the output of affected fuel pump harness 

avoiding undesired electrical contacts and 

preventing potential arcing between the 

affected harness and metallic parts of the fuel 

boost cover. 

For the reasons described above this 

[EASA] AD partially retains the requirements 

of EASA AD 2013–0186, which is 

superseded, and requires modification of the 

fuel pump electrical installation. 

You may examine the MCAI in the 

AD docket on the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

9109. 


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