Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations 39523 

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 International Section, send it 

to the attention of the person identified in 

paragraph (n)(2) of this AD. Information may 

be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Section, 

Transport Standards Branch, FAA; or EASA; 

or Airbus’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2016–0150, dated July 25, 2016, for related 

information. This MCAI may be found in the 

AD docket on the Internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2017–0520. 

(2) For more information about this AD, 

contact Dan Rodina, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; telephone: 425– 

227–2125; fax: 425–227–1149. 

(o) 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 this AD specifies otherwise. 

(i) Airbus Service Bulletin A300–53–0246, 

Revision 08, including Appendix 1, dated 

April 13, 2016. 

(ii) Airbus Service Bulletin A300–53–6029, 

Revision 12, including Appendix 1, dated 

April 13, 2016. 

(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 Standards Branch, 

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 August 

8, 2017. 

Dionne Palermo, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–17203 Filed 8–18–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0270; Product 

Identifier 2016–SW–032–AD; Amendment 

39–18993; AD 2017–17–03] 

RIN 2120–AA64 

Airworthiness Directives; MD 

Helicopters, Inc., Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2014–16– 

01 for MD Helicopters, Inc. (MDHI), 

Model MD900 helicopters. AD 2014– 

16–01 required an eddy current 

inspection of the main rotor upper hub 

assembly (upper hub) for a crack. This 

AD requires additional inspections and 

replacing the fillet seal. This AD was 

prompted by three additional reports of 

upper hub cracks. The actions of this 

AD are intended to prevent an unsafe 

condition on these products. 

DATES: This AD is effective September 

25, 2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 25, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact MD 

Helicopters, Inc., Attn: Customer 

Support Division, 4555 E. McDowell 

Rd., Mail Stop M615, Mesa, AZ 85215– 

9734; telephone 1–800–388–3378; fax 

480–346–6813; or at http://

www.mdhelicopters.com. You may 

review 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–2017– 

0270. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov in Docket No. 

FAA–2017–0270; 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, any 

incorporated-by-reference information, 

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: Eric 

Schrieber, Aviation Safety Engineer, Los 

Angeles ACO Branch, Compliance and 

Airworthiness Division, FAA, 3960 

Paramount Blvd., Lakewood, California 

90712; telephone (562) 627–5348; email 

eric.schrieber@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to remove AD 2014–16–01, 

Amendment 39–17925 (79 FR 45322, 

August 5, 2014) and add a new AD. AD 

2014–16–01 applied to MDHI Model 

MD900 helicopters, serial numbers 900– 

00008 through 900–00140, with an 

upper hub part number (P/N) 

900R2101006–105, –107, –109, or –111 

installed. AD 2014–16–01 required eddy 

current inspecting the upper hub and 

replacing it if there is a crack. The 

NPRM published in the Federal 

Register on April 3, 2017 (82 FR 16138). 

The NPRM was prompted by reports 

of three additional cracks found in the 

MD900 fleet. These cracks were not 

discovered by the one-time eddy current 

inspection required by AD 2014–16–01, 

but were found during regular 

maintenance of the upper hub. The 

NPRM proposed to require for MDHI 


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MD900 helicopters with an upper hub, 

regardless of helicopter serial number, 

repetitive visual inspections of the fillet 

seal and the areas around the flexbeam 

boltholes for a crack and repetitive 

visual inspections of the lead leg shims 

and bushings for corrosion around the 

flexbeam boltholes. The NPRM also 

proposed repetitive ultrasonic eddycurrent inspections of the areas adjacent 

to the flexbeam boltholes for a crack. If 

during any inspection there is corrosion 

or a crack, the NPRM proposed 

replacing the upper hub before further 

flight. Finally, after each inspection, the 

NPRM proposed installing a fillet seal to 

the bushing and upper hub interface. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM. 

FAA’s Determination 

We have reviewed the relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

the same type design and that air safety 

and the public interest require adopting 

the AD requirements as proposed. 

Related Service Information Under 1 

CFR Part 51 

MDHI has issued Service Bulletin 

SB900–125, dated February 19, 2016, 

which describes procedures for 

repetitive visual and eddy current 

inspections of the upper hub upper and 

lower flexbeam bolthole areas and for 

applying a fillet seal on the interface of 

the bushing and the flex beam retention 

bolt hole. 

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. 

Differences Between This AD and the 

Service Information 

The service information applies to 

upper hubs with 1,000 or more hours 

TIS. This AD applies to all upper hubs 

regardless of hours TIS. The service 

information applies to upper hub P/N 

900R2101006–107 and –109; this AD 

also applies to upper hub P/N 

900R2101006–105 and –111. 

Costs of Compliance 

We estimate that this AD affects 23 

helicopters of U.S. Registry. At an 

average labor rate of $85 per hour, we 

estimate that operators may incur the 

following costs in order to comply with 

this AD. 

Inspecting the fillet seal around the 

flexbeam boltholes (100 hour TIS 

inspection) requires about 1 work-hour, 

for a cost per helicopter of $85 and a 

cost of $1,955 for the fleet, per 

inspection cycle. Inspecting the 

flexbeam area and lead leg shims and 

bushings (annual inspection) requires 

about 2 work-hours, for a cost per 

helicopter of $170 and a cost of $3,910 

for the fleet, per inspection cycle. Eddy 

current inspecting (1,000 hour TIS 

inspection) the upper hub requires 

about 2 work-hours, for a cost per 

helicopter of $170 and a cost of $3,910 

for the fleet. 

If required, replacing the upper hub 

requires about 11 work-hours, and 

required parts would cost about 

$15,998, for a cost per helicopter of 

$16,933. If required, replacing a missing 

or damaged fillet seal requires about .5 

work-hour, and required parts cost 

would be minimal, for a cost per 

helicopter of $43. 

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), 

(3) Will not affect intrastate aviation 

in Alaska to the extent that a regulatory 

distinction is required, 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) 

2014–16–01, Amendment 39–17925 (79 

FR 45322, August 5, 2014), and adding 

the following new AD: 

2017–17–03 MD Helicopters, Inc. (MDHI): 

Amendment 39–18993; Docket No. 

FAA–2017–0270; Product Identifier 

2016–SW–032–AD. 

(a) Applicability 

This AD applies to Model MD900 

helicopters with main rotor upper hub 

assembly (upper hub) part number 

900R2101006–105, –107, –109, or –111 

installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

cracked upper hub. This condition could 

result in failure of the upper hub and 

subsequent loss of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2014–16–01, 

Amendment 39–17925 (79 FR 45322, August 

5, 2014). 

(d) Effective Date 

This AD becomes effective September 25, 

2017. 

(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 

(1) Within 100 hours time-in-service (TIS), 

and thereafter at intervals not to exceed 100 

hours TIS: 

(i) Inspect the fillet seal around each 

flexbeam bolthole to determine whether it 

adheres properly to the hub or bushing or is 

missing. Indications of an improperly 


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Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations 39525 

adhered seal include lifting, bubbling, 

peeling away, drying out, or cracking. If the 

fillet seal is not properly adhered or is 

missing, before further flight, replace the 

fillet seal with sealant C232 or equivalent by 

following the Accomplishment Instructions, 

paragraphs 2.D.(2) through 2.D.(5) and Figure 

1, of MD Helicopters Service Bulletin SB900– 

125, dated February 19, 2016 (SB900–125). 

(ii) Using a light and a 10X or higher power 

magnifying glass, inspect the area outside of 

the fillet seal around each flexbeam bolthole 

on the top of the upper hub assembly for a 

crack. If there is a crack, before further flight, 

replace the upper hub assembly. 

(2) Within 12 months, and thereafter at 

intervals not to exceed 12 months: 

(i) Remove the paint and primer from the 

area around each flexbeam bolthole on top of 

the upper hub. Remove the fillet seal from 

the mating surface of each bushing and the 

top of the upper hub. 

(ii) Using a light and a 10X or higher power 

magnifying glass, inspect the area around 

each flexbeam bolthole for a crack. If there 

is a crack, before further flight, replace the 

upper hub assembly. 

(iii) Inspect each lead leg shim and bushing 

for corrosion around the flexbeam boltholes 

on the bottom of the upper hub in the 

flexbeam pockets. If there is corrosion, before 

further flight: 

(A) Remove the lead leg shim from the 

flexbeam pocket and clean the area adjacent 

to the flexbeam bolthole to remove any 

corrosion within maximum repair damage 

limits. If the corrosion exceeds maximum 

repair damage limits, replace the upper hub 

assembly. 

(B) Using a light and a 10X or higher power 

magnifying glass, inspect the area around the 

flexbeam bolthole for a crack. If there is a 

crack, before further flight, replace the upper 

hub assembly. 

(iv) Replace the fillet seal as described in 

paragraph (f)(1)(i) of this AD. 

(3) Within 1,000 hours TIS, and thereafter 

at intervals not to exceed 1,000 hours TIS: 

(i) Eddy current inspect the areas adjacent 

to each flexbeam bolthole, top and bottom, 

for a crack. This eddy current inspection 

must be performed by a Level II or higher 

technician with the American Society for 

Nondestructive Testing ASNT–TC–1A, 

European Committee for Standardization 

CEN EN 4179, Military Standard MIL–STD– 

410, National Aerospace Standard NAS410, 

or equivalent certification who has 

performed an eddy current inspection within 

the last 12 months. If there is a crack, before 

further flight, replace the upper hub 

assembly. 

(ii) Replace the fillet seal as described in 

paragraph (f)(1)(i) of this AD. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles ACO Branch, 

FAA, may approve AMOCs for this AD. Send 

your proposal to: Eric Schrieber, Aviation 

Safety Engineer, Los Angeles ACO Branch, 

Compliance and Airworthiness Division, 

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. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6220, Main Rotor Head. 

(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) MD Helicopters Service Bulletin SB900– 

125, dated February 19, 2016. 

(ii) Reserved. 

(3) For MD Helicopters service information 

identified in this AD, contact MD 

Helicopters, Inc., Attn: Customer Support 

Division, 4555 E. McDowell Rd., Mail Stop 

M615, Mesa, AZ 85215–9734; telephone 1– 

800–388–3378; fax 480–346–6813; or at 

http://www.mdhelicopters.com. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy, 

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 August 7, 

2017. 

Scott A. Horn, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2017–17085 Filed 8–18–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0130; Product 

Identifier 2016–NM–058–AD; Amendment 

39–18986; AD 2017–16–09] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Dassault Aviation Model MYSTERE– 

FALCON 50 airplanes and FALCON 

2000 airplanes. This AD was prompted 

by a report indicating that during 

ground maintenance, a Model FALCON 

2000 airplane experienced a loss of 

hydraulic pressure affecting both 

hydraulic systems due to damage to 

both brake hoses on the main landing 

gear (MLG). This AD requires an 

inspection for certain brake hoses, 

installation of protective wraps or 

installation of certain brake hoses, and 

replacement of certain brake hoses. We 

are issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective September 

25, 2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 25, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Dassault Falcon Jet Corporation, 

Teterboro Airport, P.O. Box 2000, South 

Hackensack, NJ 07606; telephone: 201– 

440–6700; Internet: http://

www.dassaultfalcon.com. You may 

view this referenced service information 

at the FAA, Transport Standards 

Branch, 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–2017–0130. 

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–2017– 

0130; 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 street 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: Tom 

Rodriguez, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: 425–227–1137; fax: 425– 

227–1149. 


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