2364 Federal Register / Vol. 83, No. 11 / Wednesday, January 17, 2018 / Rules and Regulations 

Region, 10101 Hillwood Pkwy., Room 6N– 

321, Fort Worth, TX 76177. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6210, Main Rotor Blades. 

Issued in Fort Worth, Texas, on January 9, 

2018. 

James A. Grigg, 

Acting Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

Appendix 1 to AD 2018–02–07 

Please report the following by mail to the 

Los Angeles ACO Branch, Compliance and 

Airworthiness Division, FAA, 3960 

Paramount Blvd., Lakewood, California 

90712; attn. Galib Abumeri; or by email to 

galib.abumeri@faa.gov. 

(1) Date of inspection: 

(2) Aircraft N-number: 

(3) M/R blade serial number: 

(4) M/R blade hours of time-in-service: 

(5) Location of each crack: 

(6) Dimension of each crack: 

(7) Primary operating location of the M/R 

blade: 

[FR Doc. 2018–00658 Filed 1–16–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–1249; Product 

Identifier 2013–NM–104–AD; Amendment 

39–19156; AD 2018–02–03] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Fokker Services B.V. Model F28 Mark 

0070 and Mark 0100 series airplanes. 

This AD requires contacting the FAA to 

obtain instructions for addressing the 

unsafe condition on these products, and 

doing the actions specified in those 

instructions. This AD was prompted by 

an erroneous radio altimeter reading, 

which caused certain systems to 

respond in a way that led to loss of 

speed. We are issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD becomes effective 

February 15, 2018. 

We must receive comments on this 

AD by March 5, 2018. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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– 

1249; 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, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone: 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

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. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2013–0112, 

dated May 28, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Fokker Services B.V. Model F28 

Mark 0070 and Mark 0100 series 

airplanes. The MCAI states: 

Following an accident*** [of an] 

aeroplane on final approach, the 

investigating body determined that an 

important contributing factor to the accident 

was an erroneous reading of -7 to -8 feet from 

the left Radio Altimeter (RA). The responses 

of the autothrottle and autopilot systems to 

this erroneous RA system reading led to 

speed loss and, in combination with 

operational factors, caused the aeroplane to 

hit the ground before reaching the runway. 

Fokker Services conducted an evaluation 

of the effects of un-flagged erroneous low RA 

system indications in response to the 

recommendations in the investigator’s report. 

The result of the evaluation was a new 

‘‘ERRONEOUS RADIO ALTIMETER 

INDICATION’’ abnormal procedure in the 

Airplane Flight Manual (AFM). This new 

procedure includes pulling the circuit 

breaker of a failed RA system, and in support 

of this, new yellow identification collars to 

the RA circuit breakers are to be introduced 

to improve instantaneous recognition, both 

visual and tactile, in low illumination and 

under increased workload conditions. 

In order to prevent an unsafe condition, 

similar to the one that contributed to the 

accident described above, this [EASA] AD 

requires incorporation of the new abnormal 

procedure in the AFM and installation of the 

new yellow RA circuit breaker identification 

collars. 

You may examine the MCAI on the 

internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2017–1249. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI. We are issuing this AD because 

we evaluated all pertinent information 

and determined the unsafe condition 

exists and is likely to exist or develop 

on other products of the same type 

design. 

FAA’s Determination of the Effective 

Date 

Since there are currently no domestic 

operators of this product, we find good 

cause that notice and opportunity for 

prior public comment are unnecessary. 

In addition, for the reason(s) stated 

above, we find that good cause exists for 

making this amendment effective in less 

than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2017–1249; 

Product Identifier 2013–NM–104–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD based on those 

comments. 


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Federal Register / Vol. 83, No. 11 / Wednesday, January 17, 2018 / Rules and Regulations 2365 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

Currently, there are no affected U.S.- 

registered airplanes. This AD requires 

contacting the FAA to obtain 

instructions for addressing the unsafe 

condition, and doing the actions 

specified in those instructions. Based on 

the actions specified in the MCAI AD, 

we are providing the following cost 

estimates for an affected airplane that is 

placed on the U.S. Register in the future: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Modification ...................................... 1 work-hour × $85 per hour = $85 ............................................................ $9 $94 

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. 

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): 

2018–02–03 Fokker Services B.V.: 

Amendment 39–19156; Docket No. 

FAA–2017–1249; Product Identifier 

2013–NM–104–AD. 

(a) Effective Date 

This AD becomes effective February 1, 

2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Fokker Services B.V. 

Model F28 Mark 0070 and Mark 0100 series 

airplanes, certificated in any category, all 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 34, Navigation. 

(e) Reason 

This AD was prompted by an erroneous 

radio altimeter (RA) reading, which caused 

certain systems to respond in a way that led 

to loss of speed. We are issuing this AD to 

ensure the flight crew has procedures for 

detecting erroneous RA readings. Erroneous 

RA readings could cause the autothrottle and 

autopilot systems to respond by causing a 

loss of speed, which, in combination with 

operational factors, could cause an airplane 

to hit the ground before reaching the runway. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Action(s) 

Within 30 days after the effective date of 

this AD, request instructions from the 

Manager, International Section, Transport 

Standards Branch, FAA, to address the 

unsafe condition specified in paragraph (e) of 

this AD; and accomplish the action(s) at the 

times specified in, and in accordance with, 

those instructions. Guidance can be found in 

Mandatory Continuing Airworthiness 

Information (MCAI) European Aviation 

Safety Agency (EASA) AD 2013–0112, dated 

May 28, 2013. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, International Section, 

Transport Standards Branch, 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 International Section, send it to the 

attention of the person identified in 

paragraph (i)(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. 

(i) Related Information 

(1) Refer to MCAI EASA AD 2013–0112, 

dated May 28, 2013, for related information. 

You may examine the MCAI on the internet 

at http://www.regulations.gov by searching 

for and locating Docket No. FAA–2017–1249. 


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2366 Federal Register / Vol. 83, No. 11 / Wednesday, January 17, 2018 / Rules and Regulations 

(2) For more information about this AD, 

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. 

(j) Material Incorporated by Reference 

None. 

Issued in Renton, Washington, on January 

5, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–00656 Filed 1–16–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0141; Product 

Identifier 2016–SW–067–AD; Amendment 

39–19154; AD 2018–02–01] 

RIN 2120–AA64 

Airworthiness Directives; The Enstrom 

Helicopter Corporation Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2015–08– 

51 for the Enstrom Helicopter 

Corporation (Enstrom) Model F–28A, 

280, F–28C, F–28C–2, F–28C–2R, 280C, 

F–28F, F–28F–R, 280F, 280FX, and 480 

helicopters. AD 2015–08–51 required an 

inspection of the main rotor spindle 

(spindle) and reporting the inspection 

results to the FAA. This new AD was 

prompted by additional reports of 

cracked spindles and requires 

establishing a life limit and a recurring 

inspection. The actions of this AD are 

intended to prevent the unsafe 

condition on these products. 

DATES: This AD is effective February 21, 

2018. 

ADDRESSES: For service information 

identified in this final rule, contact 

Enstrom Helicopter Corporation, 2209 

22nd Street, Menominee, MI; telephone 

(906) 863–1200; fax (906) 863–6821; or 

at www.enstromhelicopter.com. You 

may view this referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy., Room 6N–321, 

Fort Worth, TX 76177. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at http://

www.regulations.gov in Docket No. 

FAA–2017–0141; 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 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: 

Manzoor Javed, Senior Aerospace 

Engineer, Chicago ACO Branch, 

Compliance and Airworthiness 

Division, FAA, 2300 East Devon Ave., 

Des Plaines, IL 60018; telephone (847) 

294–8112; email manzoor.javed@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to remove AD 2015–08–51, 

Amendment 39–18160 (80 FR 28172, 

May 18, 2015) (AD 2015–08–51) and 

add a new AD. AD 2015–08–51 applied 

to Enstrom Model F–28A, 280, F–28C, 

F–28C–2, F–28C–2R, 280C, F–28F, F– 

28F–R, 280F, 280FX, and 480 

helicopters with a spindle part number 

(P/N) 28–14282–11 or 28–14282–13 

installed. AD 2015–08–51 required 

conducting a one-time magnetic particle 

inspection (MPI) of the spindle for 

cracks and reporting the inspection 

results to the FAA. AD 2015–08–51 was 

prompted by a fatal accident and reports 

of spindles with cracks. AD 2015–08–51 

was issued as an interim action and was 

intended to detect a crack in a spindle 

and prevent loss of a main rotor blade 

and subsequent loss of control of the 

helicopter. 

The NPRM published in the Federal 

Register on March 2, 2017 (82 FR 

12308). The NPRM was prompted by 

additional reports of cracked spindles. 

Based on review of in-service data and 

a fatigue analysis, the FAA determined 

a life limit and recurring MPIs are 

necessary to reduce the risk of a crack 

developing in a spindle. We also 

determined the reporting requirement in 

AD 2015–08–51 is no longer necessary. 

Accordingly, the NPRM proposed to 

require an MPI of the spindle every 500 

hours time-in-service (TIS) until the 

spindle reaches its new life limit of 

1,500 hours TIS. 

Since the NPRM was issued, the 

FAA’s Aircraft Certification Service has 

changed its organizational structure. 

The new structure replaces product 

directorates with functional divisions. 

We have revised some of the office titles 

and nomenclature throughout this Final 

rule to reflect the new organizational 

changes. Additional information about 

the new structure can be found in the 

Notice published on July 25, 2017 (82 

FR 34564). 

Comments 

After our NPRM was published, we 

received comments from 50 

commenters. 

A. Support for the NPRM 

One commenter supported the 500- 

hour repetitive inspection proposed by 

the NPRM. 

B. Comments Regarding the FAA’s 

Justification of the Unsafe Condition 

Many commenters, including 

Enstrom, disagreed with the FAA’s 

determination that an unsafe condition 

exists and requested the FAA provide 

more information about the additional 

cracks that prompted this AD. 

Request: A few commenters noted the 

entire fleet has been inspected in 

accordance with AD 2015–08–51 and no 

additional cracks were found. Other 

commenters stated no additional cracks 

have been found in the area of a spindle 

where a failure could cause a 

catastrophic accident. A few 

commenters, including Enstrom, stated 

no additional cracking has been 

reported in the same location as that of 

the accident spindle. 

Other commenters requested the FAA 

provide information about the number 

of additional reported cracks and 

whether there is any correlation 

between cracks and manufacturing dates 

or suppliers. Enstrom stated the cracked 

spindles discovered after the accident 

were manufactured between 1975 to 

1980 by two specific suppliers. 

FAA Response: We agree to provide 

information about the cracks that 

prompted this AD. Contrary to the 

public comments stating there were no 

additional cracks found by the 

inspections required by AD 2015–08– 

51, those inspection results revealed 34 

cracked spindle assemblies. The 

commenters are correct that the 

additional cracking was not in the same 

location as that of the accident spindle. 

The location of the additional 34 

spindle cracks was at the hole for the 

cotter pin securing the lamiflex bearing 

nut. However, we disagree that the 

additional cracks were not in an area 

where a failure could cause a 

catastrophic accident. A spindle 

assembly is a primary structural element 

and a critical part. Flight with any 

known crack is prohibited in primary 


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