39520 Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations 

Airframe and Mechanical Systems Section, 

FAA, New York ACO Branch, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7318; fax 516–794–5531. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (k)(3) and (k)(4) of this AD. 

(k) 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) Bombardier Service Bulletin 605–35– 

003, Revision 02, dated April 18, 2016. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; Widebody Customer Response 

Center North America toll-free telephone 1– 

866–538–1247 or direct-dial telephone 1– 

514–855–2999; fax 514–855–7401; email 

ac.yul@aero.bombardier.com; Internet http:// 

www.bombardier.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 

4, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–17086 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–2017–0520; Product 

Identifier 2016–NM–143–AD; Amendment 

39–18995; AD 2017–17–05] 

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 certain 

Airbus Model A300 series airplanes; 

and Model A300 B4–600, B4–600R, and 

F4–600R series airplanes, and Model 

A300 C4–605R Variant F airplanes 

(collectively called Model A300–600 

series airplanes). This AD was prompted 

by reports of cracks initiating at the 

upper radius of a certain frame and a 

determination that the current 

inspection procedure is not reliable in 

detecting certain cracking of the forward 

fitting of the frame. This AD requires 

repetitive inspections to detect cracking 

of the upper radius of the forward fitting 

of a certain frame, and related 

investigative actions and corrective 

actions if necessary. 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 

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.airwortheas@airbus.com; Internet: http://

www.airbus.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– 

0520. 

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– 

0520; 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: 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. 

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 certain Airbus Model A300 

series airplanes; and Model A300 B4– 

600, B4–600R, and F4–600R series 

airplanes, and Model A300 C4–605R 

Variant F airplanes (collectively called 

Model A300–600 series airplanes). The 

NPRM published in the Federal 

Register on May 31, 2017 (82 FR 24903) 

(‘‘the NPRM’’). The NPRM was 

prompted by reports of cracks initiating 

at the upper radius of frame (FR) 47 and 

a determination that the current 

inspection procedure is not reliable in 

detecting certain cracking of the forward 

fitting of FR 47. The NPRM proposed to 

require repetitive inspections to detect 

cracking of the upper radius of the 

forward fitting of FR 47, and related 

investigative actions and corrective 

actions if necessary. We are issuing this 

AD to detect and correct fatigue 

cracking of the FR 47 forward fitting 

upper radius on the left-hand and righthand sides of the fuselage, which could 

propagate and result in reduced 

structural integrity 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 2016–0150, 

dated July 25, 2016 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

on all. The MCAI states: 

During scheduled maintenance inspections 

on the fuselage, cracks initiating at the upper 

radius of frame (FR) 47 have been reported 

on several aeroplanes. Similar damage was 

also discovered on the A300 fatigue test 

fuselage. 

This condition, if not detected and 

corrected, could reduce the structural 

integrity of the fuselage. 

Prompted by these findings, Airbus issued 

Service Bulletin (SB) A300–53–0246, SB 

A300–53–6029 and SB A300–53–9014 to 

provide inspection instructions and, 

consequently, DGAC France issued AD F– 

2006–016 to require repetitive inspections 

and corrective action. 

Since that [French] AD was issued, further 

investigation led to the conclusion that the 

current ultrasonic inspection performed in 

accordance with Airbus SB A300–53–0246 

Revision 06, or SB A300–53–6029 Revision 

08, or SB A300–53–9014 Revision 01, as 

applicable, was not reliable to detect deep 

crack going downward. 

Consequently, to ensure the crack depth is 

correctly measured whatever the crack 

direction, Airbus developed a new 

nondestructive testing method [eddy current] 


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Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations 39521 

for this special detailed inspection (SDI) and 

revised the affected SBs accordingly. 

For the reasons described above, this 

[EASA] AD retains the requirements of DGAC 

France AD F–2006–016, which is 

superseded, but requires the accomplishment 

of repetitive SDI to replace the previously 

required ultrasonic inspections [and related 

investigative and corrective actions if 

necessary]. 

Related investigative actions include an 

ultrasonic inspection for cracking on the 

forward face of the forward fitting and 

a detailed inspection for cracking of the 

aft fitting around the fasteners. 

Corrective actions include crack repairs, 

and modification of the sealing fittings 

and sealing shims. This AD requires 

reporting of the inspection results to 

Airbus. 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–2017– 

0520. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Airbus Service 

Bulletin A300–53–0246, Revision 08, 

including Appendix 1, dated April 13, 

2016 (for Model A300 series airplanes); 

and Airbus Service Bulletin A300–53– 

6029, Revision 12, including Appendix 

1, dated April 13, 2016 (for Model 

A300–600 series airplanes). The service 

information describes procedures for 

doing an SDI for cracking of the FR 47 

forward fitting upper radius on the lefthand and right-hand sides of the 

fuselage, and related investigative and 

corrective actions. 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 will affect 

132 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection ............ 19 work-hours × $85 per hour = 

$1,615.

$0 $1,615 per inspection cycle ......... $213,180 per inspection cycle. 

Reporting ............. 1 work-hour × $85 per hour = $85 $0 $85 per inspection cycle .............. $11,220 per inspection cycle. 

We estimate the following costs to do 

any necessary related investigative and 

corrective actions that would be 

required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these repairs: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Related investigative and Corrective actions ............... 21 work-hours × $85 per hour = $1,785 ...................... $1,835 $3,620 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to 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 control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is 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. 

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. 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to transport category 

airplanes to the Director of the System 

Oversight Division. 


sradovich on DSK3GMQ082PROD with RULES
39522 Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations 

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 that 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; 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): 

2017–17–05 Airbus: Amendment 39–18995; 

Docket No. FAA–2017–0520; Product 

Identifier 2016–NM–143–AD. 

(a) Effective Date 

This AD is effective September 25, 2017. 

(b) Affected ADs 

This AD affects AD 2007–26–14, 

Amendment 39–15316 (73 FR 2803, January 

16, 2008) (‘‘AD 2007–26–14’’). 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1) through (c)(5) 

of this AD, certificated in any category, 

except airplanes that have been repaired as 

specified in Airbus Service Bulletin A300– 

53–0370; or Airbus Service Bulletin A300– 

53–6144, as applicable. 

(1) Model A300 B2–1A, B2–1C, B2K–3C, 

B2–203, B4–2C, B4–103, and B4–203 

airplanes. 

(2) Model A300 B4–601, B4–603, B4–620, 

and B4–622 airplanes. 

(3) Model A300 B4–605R and B4–622R 

airplanes. 

(4) Model A300 F4–605R and F4–622R 

airplanes. 

(5) Model A300 C4–605R Variant F 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by reports of cracks 

initiating at the upper radius of frame (FR) 

47 and a determination that the current 

inspection procedure is not reliable in 

detecting certain cracking of the forward 

fitting of FR 47. We are issuing this AD to 

detect and correct fatigue cracking of the FR 

47 forward fitting upper radius on the lefthand and right-hand sides of the fuselage, 

which could propagate and result in reduced 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

Except as required by paragraph (h) of this 

AD: Before exceeding 10,000 flight cycles 

since first flight of the airplane or within 30 

days after the effective date of this AD, 

whichever occurs later, do a special detailed 

inspection (SDI) for cracking of the FR 47 

forward fitting upper radius on the left-hand 

and right-hand sides of the fuselage, in 

accordance with the Accomplishment 

Instructions of the applicable Airbus service 

information specified in paragraphs (g)(1) 

and (g)(2) of this AD. Repeat the inspection 

thereafter at intervals not to exceed 4,150 

flight cycles, except as required by paragraph 

(j) of this AD. 

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

Revision 08, including Appendix 1, dated 

April 13, 2016. 

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

Revision 12, including Appendix 1, dated 

April 13, 2016. 

(h) Initial Inspection for Airplanes 

Previously Inspected 

For airplanes previously inspected as 

specified in the applicable Airbus service 

information specified in paragraphs (h)(1) 

through (h)(6) of this AD and on which no 

cracking was found: Within 4,150 flight 

cycles after the most recent inspection, do 

the inspection for cracking of the FR 47 

forward fitting upper radius required by 

paragraph (g) of this AD. 

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

Revision 06, dated October 19, 2005. 

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

Revision 07, dated September 9, 2008. 

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

Revision 08, dated October 19, 2005. 

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

Revision 09, dated September 9, 2008. 

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

Revision 10, dated July 9, 2009. 

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

Revision 11, dated September 28, 2009. 

(i) Inspections for Airplanes With Abnormal 

Load Events 

For airplanes on which any crack was 

found during any inspection done as 

specified in Airbus Service Bulletin A300– 

53–0246 or Airbus Service Bulletin A300– 

53–6029, as applicable, and on which any 

abnormal load event, such as hard landing or 

flight in excessive turbulence, occurred 

within 3 months before the effective date of 

this AD or occurs on or after the effective 

date of this AD: Within 3 months after each 

event, accomplish an SDI for cracking of the 

FR 47 forward fitting upper radius, left-hand 

and right-hand sides of the fuselage, in 

accordance with the applicable 

Accomplishment Instructions of the Airbus 

service information specified in paragraphs 

(g)(1) or (g)(2) of this AD. If, during this 3- 

month period, another abnormal load event 

occurs, and if no SDI has yet been 

accomplished, before further flight after the 

second event, obtain corrective action 

instructions from the Manager, International 

Section, Transport Standards Branch, FAA; 

or the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA), and 

accomplish those instructions accordingly. 

(j) Corrective Actions for Airplanes With 

Cracks 

If, during any SDI as required by paragraph 

(g), (h), or (i) of this AD, any crack is found: 

Before further flight, do the applicable 

related investigative and corrective actions, 

in accordance with the Accomplishment 

Instructions of the applicable Airbus service 

information specified in paragraph (g)(1) or 

(g)(2) of this AD, and obtain additional 

corrective action instructions from the 

Manager, International Section, Transport 

Standards Branch, FAA; or EASA; or 

Airbus’s EASA DOA, and accomplish those 

instructions accordingly before further flight. 

(k) Reporting 

Submit a report of the findings (both 

positive and negative) of each SDI inspection 

required by paragraphs (g), (h), and (i) of this 

AD to Airbus Service Bulletin Reporting 

Online Application on Airbus World (https:// 

w3.airbus.com/), at the applicable time 

specified in paragraph (k)(1) or (k)(2) of this 

AD. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(l) Terminating Action for AD 2007–26–14 

Accomplishing any inspection required by 

paragraph (g) or (h) of this AD terminates all 

requirements of AD 2007–26–14 for the 

inspected airplane. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards Branch, FAA, 

has the authority to approve AMOCs for this 


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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 


sradovich on DSK3GMQ082PROD with RULES