[Federal Register Volume 83, Number 97 (Friday, May 18, 2018)]
[Proposed Rules]
[Pages 23240-23242]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-10585]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
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 

  Federal Register / Vol. 83, No. 97 / Friday, May 18, 2018 / Proposed 
Rules  

[[Page 23240]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0440; Product Identifier 2016-SW-077-AD]
RIN 2120-AA64


Airworthiness Directives; Scotts-Bell 47 Inc. (Type Certificate 
Previously Held by Bell Helicopter Textron Inc.)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
Scotts-Bell 47 Inc. (Scotts-Bell) Model 47, 47B, 47B3, 47D, 47D1, 47E, 
47G, 47G-2, 47G-2A, 47G-2A-1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-
3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A, 47H-1, 47J, 47J-2, 47J-2A, and 47K 
helicopters. This proposed AD would require repetitively inspecting and 
adjusting the throttle linkage. This proposed AD is prompted by reports 
of the throttle linkage separating from the engine carburetor shaft, 
which could result in loss of throttle control. The actions in this 
proposed AD are intended to correct an unsafe condition on these 
products.

DATES: We must receive comments on this proposed AD by July 17, 2018.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address 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-2018-
0440; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this proposed AD, the economic evaluation, any comments received, and 
other information. The street address for Docket Operations (telephone 
800-647-5527) is in the ADDRESSES section. Comments will be available 
in the AD docket shortly after receipt.
    For service information identified in this proposed rule, contact 
Scott's-Bell 47, Inc., 100 Minnesota Ave, Le Sueur, MN 56058; telephone 
(507) 665-0035; email [email protected]. 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.

FOR FURTHER INFORMATION CONTACT: Shawn Malekpour, Aviation Safety 
Engineer, Chicago ACO Branch, Compliance & Airworthiness Division, FAA, 
2300 East Devon Ave., Des Plaines, Illinois 60018; telephone (847) 294-
7834; email [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to participate in this rulemaking by submitting 
written comments, data, or views. We also invite comments relating to 
the economic, environmental, energy, or federalism impacts that might 
result from adopting the proposals in this document. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. To 
ensure the docket does not contain duplicate comments, commenters 
should send only one copy of written comments, or if comments are filed 
electronically, commenters should submit only one time.
    We will file in the docket all comments that we receive, as well as 
a report summarizing each substantive public contact with FAA personnel 
concerning this proposed rulemaking. Before acting on this proposal, we 
will consider all comments we receive on or before the closing date for 
comments. We will consider comments filed after the comment period has 
closed if it is possible to do so without incurring expense or delay. 
We may change this proposal in light of the comments we receive.

Discussion

    We propose to adopt a new AD for Scotts-Bell Model 47, 47B, 47B3, 
47D, 47D1, 47E, 47G, 47G-2, 47G-2A, 47G-2A-1, 47G-3, 47G-3B, 47G-3B-1, 
47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A, 47H-1, 47J, 47J-2, 
47J-2A, and 47K helicopters with a Marvel Schebler Model MA-3, MA-3A, 
MA3-PA, MA-3SPA, MA4-SPA, MA4-5, MA4-5AA, MA-5, MA-5AA, MA-6AA, or HA-6 
carburetor installed. This proposed AD would require an initial 
inspection and repetitive daily check of the throttle linkage-
carburetor attachment for broken or missing safety wire and for 
fracturing of the anti-sabotage lacquer. This proposed AD would also 
require adjusting and securing the throttle linkage within 100 hours 
time-in-service.
    This proposed AD is prompted by several reports of the throttle 
linkage separating from the engine carburetor shaft, which resulted in 
loss of throttle control. An investigation determined that missing or 
improperly installed safety wire may fail to prevent an excessively 
worn splined carburetor shaft from separating from the throttle 
linkage. The investigation further determined that the unusual routing 
of the safety wire in this design along with a lack of clarity in the 
maintenance instructions may have contributed to nine other incidents. 
To address this unsafe condition, Scotts-Bell has developed an 
inspection to determine whether the safety wire is correctly applied 
and has revised the maintenance instructions with updated procedures 
for safety wire installation.
    While our data indicates Model 47, 47B, 47B3, 47D, 47E, and 47K 
helicopters are not likely to have the affected carburetors installed, 
we have included those models in this proposed AD to ensure we fully 
address the unsafe condition.

FAA's Determination

    We are proposing this AD because we evaluated all known relevant

[[Page 23241]]

information and determined that an unsafe condition exists and is 
likely to exist or develop on other products of these same type 
designs.

Related Service Information Under 1 CFR Part 51

    We reviewed Scott's-Bell 47, Inc. Alert Service Bulletin 47-15-27 
R1, dated November 1, 2016 (ASB), for Model 47, 47B, 47B3, 47D, 47D1, 
47E, 47G, 47G-2, 47G-2A, 47G-2A-1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 
47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A, 47H-1, 47J, 47J-2, 47J-2A, and 
47K helicopters. The ASB specifies, prior to the next flight, 
inspecting the engine throttle linkage and carburetor shaft to 
determine if the safety wire is correctly applied. The ASB also 
specifies adjusting and securing the throttle linkage at the next 100-
hour or annual inspection, but no later than 90 days after release of 
the ASB, and then any time the throttle linkage connection is 
disassembled.
    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.

Other Related Service Information

    We also reviewed Scott's-Bell 47, Inc. Model 47D-1, 47G, & 47G-2 
Maintenance and Overhaul Instructions Temporary Revision (M&O TR) 47-
16-2, Models 47G-2A & 47G-2A-1 M&O TR 47-16-3, Model 47G-3 M&O TR 47-
16-3, Models 47G-3B & 47G-3B-1 M&O TR 47-16-3, Model 47G-3B-2 M&O TR 
47-16-3, Model 47G-3B-2A M&O TR 47-16-3, Models 47G-4 & 47G-4A M&O TR 
47-16-3, Model 47G-5 M&O TR 47-16-3, Model 47G-5A M&O TR 47-16-3, Model 
47H-1 M&O TR 47-16-2, Model 47J M&O TR 47-16-2, and Models 47J-2 & 47J-
2A M&O TR 47-16-3, each dated November 1, 2016. Each M&O TR describes 
procedures for inspecting and safety wiring the throttle control 
linkage.
    Scott's Bell did not issue temporary revisions to the M&O 
procedures for Model 47, 47B, 47B3, 47D, 47E, and 47K helicopters, as 
there are limited manufacturing and maintenance records available for 
these models, and as it is unlikely these models have an affected model 
carburetor installed.

Proposed AD Requirements

    This proposed AD would require the following:
     Before further flight, inspecting the throttle linkage 
connection at the engine carburetor for condition, security, and to 
determine if the safety wire is in place and captures the throttle 
linkage and the carburetor stop arm.
     Before the first flight of each day, visually checking the 
throttle-linkage to carburetor attachment for installed safety wire and 
for intact anti-sabotage lacquer. An owner/operator (pilot) may perform 
the visual check required by paragraph (e)(2)(i) of the proposed AD and 
must enter compliance with that paragraph into the helicopter 
maintenance records in accordance with 14 CFR 43.9(a)(1) through (4) 
and 91.417(a)(2)(v). A pilot may perform this check because it involves 
only a visual check of the throttle-linkage to carburetor attachment 
and can be performed equally well by a pilot or a mechanic. This check 
is an exception to our standard maintenance regulations.
     Within 100 hours time-in-service or at the next annual or 
100-hour inspection, whichever occurs first, and thereafter at each 
annual or 100-hour inspection, whichever occurs first, adjusting, 
safety wiring, and applying anti-sabotage lacquer to the throttle 
linkage. For Model 47, 47B, 47B3, 47D, 47E, and 47K helicopters, 
adjusting and safety wiring the throttle linkage would be required to 
be done by using a method approved by the Manager, Chicago ACO Branch. 
For all other helicopters, these actions would be accomplished as 
specified in the applicable M&O TR.

Costs of Compliance

    We estimate that this proposed AD would affect 698 helicopters of 
U.S. Registry.
    We estimate that operators may incur the following costs in order 
to comply with this proposed AD. Conducting a pre-flight check of the 
throttle linkage connection by the pilot would require about 5 minutes, 
therefore the cost per helicopter would be minimal. At an average labor 
rate of $85, inspecting the engine throttle linkage would require about 
0.5 work-hour, for a cost of $43 per helicopter and $30,014 for the 
U.S. fleet. Adjusting and securing the throttle linkage would require 
about 3 work-hours and required parts would be $12 for a cost of $267 
per helicopter and $186,366 for the U.S. fleet per occurrence.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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, I certify this proposed regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska to the extent that 
it justifies making a regulatory distinction; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared an economic evaluation of the estimated costs to comply 
with this proposed 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):


[[Page 23242]]


Scotts-Bell 47 Inc. (Type Certificate Previously Held by Bell 
Helicopter Textron Inc.): Docket No. FAA-2018-0440; Product 
Identifier 2016-SW-077-AD.

(a) Applicability

    This AD applies to Scotts-Bell 47 Inc. (Scotts-Bell) Model 47, 
47B, 47B3, 47D, 47D1, 47E, 47G, 47G-2, 47G-2A, 47G-2A-1, 47G-3, 47G-
3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A, 
47H-1, 47J, 47J-2, 47J-2A, and 47K helicopters, certificated in any 
category, with a Marvel Schebler Model MA-3, MA-3A, MA3-PA, MA-3SPA, 
MA4-SPA, MA4-5, MA4-5AA, MA-5, MA-5AA, MA-6AA, or HA-6 carburetor 
installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as separation of the 
throttle linkage from an engine carburetor shaft. This condition 
could result in loss of throttle control and subsequent forced 
landing of the helicopter.

(c) Comments Due Date

    We must receive comments by July 17, 2018.

(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

    (1) Before further flight, inspect the throttle linkage 
connection at the engine carburetor for security: Determine whether 
the throttle linkage is securely attached to the serrated shaft of 
the carburetor, inspect the throttle linkage clamp screw for broken 
or missing safety wire, and determine whether safety wire captures 
the throttle linkage and carburetor stop arm.
    (i) If there is any looseness, axial movement, or movement 
between the serrated shaft and the throttle linkage; if a throttle 
linkage clamp screw is loose; if any safety wire is broken or 
missing; or if safety wire does not capture the throttle linkage and 
carburetor stop arm, before further flight, adjust and secure the 
throttle linkage as required by paragraph (e)(3)(i) and (e)(3)(ii) 
of this AD.
    (ii) If there is no looseness, axial movement, or movement 
between the serrated shaft and the throttle linkage; no throttle 
linkage clamp screws are loose; no safety wire is broken or missing; 
and safety wire captures the throttle linkage and carburetor stop 
arm, before further flight, apply anti-sabotage lacquer (Torque-Seal 
or equivalent) between the throttle arm and the serrated shaft and 
between the self-locking nut and the throttle arm.
    (2) Before the first flight of each day:
    (i) Check the throttle linkage-carburetor attachment for broken 
or missing safety wire and for missing or fractured anti-sabotage 
lacquer. The actions required by this paragraph may be performed by 
the owner/operator (pilot) holding at least a private pilot 
certificate, and must be entered into the aircraft records showing 
compliance with this AD in accordance with 14 CFR 43.9 (a)(1) 
through (4) and 14 CFR 91.417(a)(2)(v). The record must be 
maintained as required by 14 CFR 91.417, 121.380, or 135.439.
    (ii) If the safety wire is missing or broken or if the anti-
sabotage lacquer is missing or fractured, before further flight, 
adjust and secure the throttle linkage as described in paragraph 
(e)(3)(i) and (e)(3)(ii) of this AD.
    (3) Within 100 hours time-in-service or at the next annual or 
100-hour inspection, whichever occurs first, and thereafter at each 
annual or 100-hour inspection, whichever occurs first:
    (i) Adjust and secure the throttle linkage as specified in 
Appendix 1 of the Scotts-Bell Maintenance and Overhaul Instructions 
Temporary Revision that is applicable to your helicopter, as listed 
in Table 1 of Scotts-Bell Alert Service Bulletin 47-15-27 R1, dated 
November 1, 2016.
    (ii) For Model 47, 47B, 47B3, 47D, 47E, and 47K helicopters, 
adjust and secure the throttle linkage using a method approved by 
the Manager, Chicago ACO Branch. For a repair method to be approved 
as required by this AD, the Manager's approval letter must 
specifically refer to this AD.

 (f) Special Flight Permits

    Special flight permits are prohibited.

(g) Alternative Methods of Compliance

    (1) The Manager, Chicago ACO Branch, FAA, may approve AMOCs for 
this AD. Send your proposal to: Shawn Malekpour, Aviation Safety 
Engineer, Chicago ACO Branch, Compliance & Airworthiness Division, 
FAA, 2300 East Devon Ave., Des Plaines, Illinois 60018; telephone 
(847) 294-7834; email [email protected].
    (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) Additional Information

    For service information identified in this AD, contact Scott's-
Bell 47, Inc., 100 Minnesota Ave., Le Sueur, MN 56058; telephone 
(507) 665-0035; email [email protected]. You may review a copy 
of this referenced service information at the FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-
321, Fort Worth, TX 76177.

 (i) Subject

    Joint Aircraft Service Component (JASC) Code: 7322 Engine 
Controls.

    Issued in Fort Worth, Texas, on May 9, 2018.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2018-10585 Filed 5-17-18; 8:45 am]
 BILLING CODE 4910-13-P


