82 FR 17943 - Special Conditions: Pilatus Aircraft Limited Models PC-12, PC-12/45, PC-12/47; Autothrust System

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 82, Issue 71 (April 14, 2017)

Page Range		17943-17945
FR Document		2017-07382

This action proposes a special condition for the Pilatus Aircraft Limited PC-12, PC-12/45, and PC-12/47 airplanes. These airplanes, as modified by Innovative Solutions & Support, Inc., will have a novel or unusual design feature associated with the use of an autothrust system. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. This proposed special condition contains the additional safety standards the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.

Federal Register, Volume 82 Issue 71 (Friday, April 14, 2017)

[Federal Register Volume 82, Number 71 (Friday, April 14, 2017)]
[Proposed Rules]
[Pages 17943-17945]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2017-07382]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

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.

========================================================================


Federal Register / Vol. 82, No. 71 / Friday, April 14, 2017 / 
Proposed Rules

[[Page 17943]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. FAA-2017-0290; Notice No. 23-17-01-SC]


Special Conditions: Pilatus Aircraft Limited Models PC-12, PC-12/
45, PC-12/47; Autothrust System

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed special conditions.

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

SUMMARY: This action proposes a special condition for the Pilatus 
Aircraft Limited PC-12, PC-12/45, and PC-12/47 airplanes. These 
airplanes, as modified by Innovative Solutions & Support, Inc., will 
have a novel or unusual design feature associated with the use of an 
autothrust system. The applicable airworthiness regulations do not 
contain adequate or appropriate safety standards for this design 
feature. This proposed special condition contains the additional safety 
standards the Administrator considers necessary to establish a level of 
safety equivalent to that established by the existing airworthiness 
standards.

DATES: Send your comment on or before May 15, 2017.

ADDRESSES: Send comments identified by docket number FAA-2017-0290 
using any of the following methods:
     Federal eRegulations Portal: Go to http://www.regulations.gov and follow the online instructions for sending your 
comments electronically.
     Mail: Send comments to Docket Operations, M-30, U.S. 
Department of Transportation (DOT), 1200 New Jersey Avenue SE., Room 
W12-140, West Building Ground Floor, Washington, DC 20590-0001.
     Hand Delivery of Courier: Take comments to Docket 
Operations in Room W12-140 of the West Building Ground Floor at 1200 
New Jersey Avenue SE., Washington, DC, between 9 a.m., and 5 p.m., 
Monday through Friday, except Federal holidays.
     Fax: Fax comments to Docket Operations at 202-493-2251.
    Privacy: The FAA will post all comments it receives, without 
change, to http://regulations.gov, including any personal information 
the commenter provides. Using the search function of the docket Web 
site, anyone can find and read the electronic form of all comments 
received into any FAA docket, including the name of the individual 
sending the comment (or signing the comment for an association, 
business, labor union, etc.). DOT's complete Privacy Act Statement can 
be found in the Federal Register published on April 11, 2000 (65 FR 
19477-19478), as well as at http://DocketsInfo.dot.gov.
    Docket: Background documents or comments received may be read at 
http://www.regulations.gov at any time. Follow the online instructions 
for accessing the docket or go to the Docket Operations in Room W12-140 
of the West Building Ground Floor at 1200 New Jersey Avenue SE., 
Washington, DC, between 9 a.m., and 5 p.m., Monday through Friday, 
except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Jeff Pretz, Federal Aviation 
Administration, Small Airplane Directorate, Aircraft Certification 
Service, 901 Locust, Room 301, Kansas City, MO 64106; telephone (816) 
329-3239; facsimile (816) 329-4090.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite interested people to take part in this rulemaking by 
sending written comments, data, or views. The most helpful comments 
reference a specific portion of the special conditions, explain the 
reason for any recommended change, and include supporting data. We ask 
that you send us two copies of written comments.
    We will consider all comments we receive on or before the closing 
date for comments. We will consider comments filed late if it is 
possible to do so without incurring expense or delay. We may change 
these special conditions based on the comments we receive.

Background

    On April 4, 2016, Innovative Solutions & Support applied for a 
supplemental type certificate for installation of an autothrust system 
in the PC-12, PC-12/45, and PC-12/47 airplanes. The autothrust system 
is capable of setting forward thrust based on operation in either a 
pilot selectable torque or airspeed mode. Operation is limited to use 
only when above 400 feet AGL after takeoff, and requires disengagement 
at decision height (DH) or minimum decision altitude (MDA) on approach. 
The PC-12, PC-12/45, and PC-12/47 airplanes are nine-passenger two-
crew, single-engine turbo-propeller airplanes with a 30,000-foot 
service ceiling and a maximum takeoff weight of 9,039 to 10,450 
pounds--depending on airplane model. These airplanes are powered by a 
single Pratt & Whitney PT6A-67 engine.
    The Innovative Solutions & Support, Inc., modification installs an 
autothrust system in the PC-12, PC-12/45, and PC-12/47 airplanes to 
reduce pilot workload. The autothrust system is useable in all phases 
of flight from 400 feet AGL after takeoff down to the decision height 
on approach. The system includes a torque and airspeed mode along with 
monitors to prevent the system from exceeding critical engine or 
airspeed limits. A stepper motor provides throttle movement by acting 
through a linear actuator, which acts as a link between the stepper 
motor and throttle. The pilot can override the linear actuator by 
moving the throttle, which automatically disengages the autothrust 
system upon disagreement in the expected throttle position versus the 
actual position.

Type Certification Basis

    Under the provisions of 14 CFR 21.101, Innovative Solutions & 
Support must show that the PC-12, PC-12/45, and PC-12/47 airplanes, as 
changed, continues to meet the applicable provisions of the regulations 
incorporated by reference in Type Certificate No. A78EU. The 
regulations incorporated by reference in the type certificate are 
commonly referred to as the ``original type certification basis.'' The 
regulations incorporated by reference in A78EU are as follows: 14 CFR 
part 23, amendments 23-1 through 23-42.\2\
---------------------------------------------------------------------------

    \2\ See Type Certification Data Sheet A78EU, revision 25, 
``Certification Basis'' section for the PC-12, PC-12/45, and PC-12/
47 full certification basis (http://rgl.faa.gov/).
---------------------------------------------------------------------------

    If the Administrator finds the applicable airworthiness regulations

[[Page 17944]]

(i.e., 14 CFR part 23) do not contain adequate or appropriate safety 
standards for the PC-12, PC-12/45, and PC-12/47 airplanes because of a 
novel or unusual design feature(s), special conditions are prescribed 
under the provisions of Sec.  21.16.
    The FAA issues special conditions, as defined in 14 CFR 11.19, in 
accordance with Sec.  11.38 and they become part of the type 
certification basis under Sec.  21.101. Special conditions are 
initially applicable to the model for which they are issued. Should the 
applicant apply for a supplemental type certificate to modify any other 
model included on the same type certificate to incorporate the same 
novel or unusual design feature, the FAA would apply these special 
conditions to the other model under Sec.  21.101.
    In addition to the applicable airworthiness regulations and special 
conditions, the PC-12, PC-12/45, and PC-12/47 airplanes must comply 
with the fuel vent and exhaust emission requirements of 14 CFR part 34 
and the noise certification requirements of 14 CFR part 36.

Novel or Unusual Design Features

    The PC-12, PC-12/45, and PC-12/47 airplanes will incorporate the 
following novel or unusual design features: Autothrust system.

Discussion

    As discussed in the summary section, this modification makes use of 
an autothrust system, which is a novel design for this type of 
airplane. The applicable airworthiness regulations do not contain 
adequate or appropriate safety standards for this design feature. 
Mandating additional requirements--developed in part--by adapting 
relevant portions of 14 CFR 25.1329, Flight guidance systems--
applicable to autothrust systems--along with FAA experience with 
similar autothrust systems, mitigates the concerns associated with 
installation of the proposed autothrust system.
    The FAA has previously issued this proposed special condition to 
part 23 turbojet airplanes, but not for turbo-propeller airplanes. The 
PC-12, PC-12/45, and PC-12/47 airplanes are unique with respect to 
other turbo-propeller designs in that the basic design does not include 
a separate propeller control lever. Future use of these special 
conditions on other turbo-propeller designs will require evaluation of 
the engine and propeller control system to determine their 
appropriateness.

Applicability

    As discussed above, these special conditions are applicable to the 
PC-12, PC-12/45, and PC-12/47 airplanes. Should Innovative Solutions & 
Support, Ltd. apply at a later date for a supplemental type certificate 
to modify any other model included on Type Certificate No. A78EU to 
incorporate the same novel or unusual design feature, the FAA would 
apply these special conditions to that model as well.

Conclusion

    This action affects only certain novel or unusual design features 
on PC-12, PC-12/45, and PC-12/47 airplanes. It is not a rule of general 
applicability and affects only the applicant who applied to the FAA for 
approval of these features on the airplane.

List of Subjects in 14 CFR Part 23

    Aircraft, Aviation safety, Signs and symbols.

Citation

    The authority citation for these special conditions is as follows:

    Authority: 49 U.S.C. 106(f), 106(g), 40113, 44701-44702, 44704.

The Proposed Special Conditions

    Accordingly, the Federal Aviation Administration (FAA) proposes the 
following special condition as part of the type certification basis for 
Pilatus Aircraft Ltd., PC-12, PC-12/45, and PC-12/47 airplane models 
modified by Innovative Solutions & Support, Inc.

1. Autothrust System

    In addition to the requirements of Sec. Sec.  23.143, 23.1309, and 
23.1329, the following apply:
    (a) Quick disengagement controls for the autothrust function must 
be provided for each pilot. The autothrust quick disengagement controls 
must be located on the thrust control levers. Quick disengagement 
controls must be readily accessible to each pilot while operating the 
thrust control levers.
    (b) The effects of a failure of the system to disengage the 
autothrust function when manually commanded by the pilot must be 
assessed in accordance with the requirements of Sec.  23.1309.
    (c) Engagement or switching of the flight guidance system, a mode, 
or a sensor may not cause the autothrust system to affect a transient 
response that alters the airplane's flight path any greater than a 
minor transient, as defined in paragraph (l)(1) of this special 
condition.
    (d) Under normal conditions, the disengagement of any automatic 
control function of a flight guidance system may not cause a transient 
response of the airplane's flight path any greater than a minor 
transient.
    (e) Under rare normal and non-normal conditions, disengagement of 
any automatic control function of a flight guidance system may not 
result in a transient any greater than a significant transient, as 
defined in paragraph (l)(2) of this special condition.
    (f) The function and direction of motion of each command reference 
control, such as heading select or vertical speed, must be plainly 
indicated on--or adjacent to--each control if necessary to prevent 
inappropriate use or confusion.
    (g) Under any condition of flight appropriate to its use, the 
flight guidance system may not produce hazardous loads on the airplane, 
nor create hazardous deviations in the flight path. This applies to 
both fault-free operation and in the event of a malfunction, and 
assumes that the pilot begins corrective action within a reasonable 
time.
    (h) When the flight guidance system is in use, a means must be 
provided to avoid excursions beyond an acceptable margin from the speed 
range of the normal flight envelope. If the airplane experiences an 
excursion outside this range, a means must be provided to prevent the 
flight guidance system from providing guidance or control to an unsafe 
speed.
    (i) The flight guidance system functions, controls, indications, 
and alerts must be designed to minimize flightcrew errors and confusion 
concerning the behavior and operation of the flight guidance system. A 
means must be provided to indicate the current mode of operation, 
including any armed modes, transitions, and reversions. Selector switch 
position is not an acceptable means of indication. The controls and 
indications must be grouped and presented in a logical and consistent 
manner. The indications must be visible to each pilot under all 
expected lighting conditions.
    (j) Following disengagement of the autothrust function, a caution 
(visual and auditory) must be provided to each pilot.
    (k) During autothrust operation, it must be possible for the 
flightcrew to move the thrust levers without requiring excessive force. 
The autothrust may not create a potential hazard when the flightcrew 
applies an override force to the thrust levers.
    (l) For purposes of this section, a transient is a disturbance in 
the control or flight path of the airplane that is not consistent with 
response to flightcrew inputs or environmental conditions.

[[Page 17945]]

    (1) A minor transient would not significantly reduce safety margins 
and would involve flightcrew actions that are well within their 
capabilities. A minor transient may involve a slight increase in 
flightcrew workload or some physical discomfort to passengers or cabin 
crew.
    (2) A significant transient may lead to a significant reduction in 
safety margins, an increase in flightcrew workload, discomfort to the 
flightcrew, or physical distress to the passengers or cabin crew, 
possibly including non-fatal injuries. Significant transients do not 
require--in order to remain within or recover to the normal flight 
envelope--any of the following:
    (i) Exceptional piloting skill, alertness, or strength.
    (ii) Forces applied by the pilot which are greater than those 
specified in Sec.  23.143(c).
    (iii) Accelerations or attitudes in the airplane that might result 
in further hazard to secured or non-secured occupants.

    Issued in Kansas City, Missouri on April 4, 2017.
Pat Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-07382 Filed 4-13-17; 8:45 am]
BILLING CODE 4910-13-P

17944 Federal Register / Vol. 82, No. 71 / Friday, April 14, 2017 / Proposed Rules

(i.e., 14 CFR part 23) do not contain Applicability not cause a transient response of the
adequate or appropriate safety standards As discussed above, these special airplane’s flight path any greater than a
for the PC–12, PC–12/45, and PC–12/47 conditions are applicable to the PC–12, minor transient.
airplanes because of a novel or unusual PC–12/45, and PC–12/47 airplanes. (e) Under rare normal and non-normal
design feature(s), special conditions are Should Innovative Solutions & Support, conditions, disengagement of any
prescribed under the provisions of Ltd. apply at a later date for a automatic control function of a flight
§ 21.16. supplemental type certificate to modify guidance system may not result in a
transient any greater than a significant
The FAA issues special conditions, as any other model included on Type
transient, as defined in paragraph (l)(2)
defined in 14 CFR 11.19, in accordance Certificate No. A78EU to incorporate the
of this special condition.
with § 11.38 and they become part of the same novel or unusual design feature, (f) The function and direction of
type certification basis under § 21.101. the FAA would apply these special motion of each command reference
Special conditions are initially conditions to that model as well. control, such as heading select or
applicable to the model for which they Conclusion vertical speed, must be plainly
are issued. Should the applicant apply indicated on—or adjacent to—each
for a supplemental type certificate to This action affects only certain novel
or unusual design features on PC–12, control if necessary to prevent
modify any other model included on the inappropriate use or confusion.
same type certificate to incorporate the PC–12/45, and PC–12/47 airplanes. It is
(g) Under any condition of flight
same novel or unusual design feature, not a rule of general applicability and
appropriate to its use, the flight
affects only the applicant who applied
the FAA would apply these special guidance system may not produce
to the FAA for approval of these features
conditions to the other model under hazardous loads on the airplane, nor
on the airplane.
§ 21.101. create hazardous deviations in the flight
In addition to the applicable List of Subjects in 14 CFR Part 23 path. This applies to both fault-free
airworthiness regulations and special Aircraft, Aviation safety, Signs and operation and in the event of a
conditions, the PC–12, PC–12/45, and symbols. malfunction, and assumes that the pilot
PC–12/47 airplanes must comply with begins corrective action within a
Citation reasonable time.
the fuel vent and exhaust emission
requirements of 14 CFR part 34 and the The authority citation for these (h) When the flight guidance system
noise certification requirements of 14 special conditions is as follows: is in use, a means must be provided to
avoid excursions beyond an acceptable
CFR part 36. Authority: 49 U.S.C. 106(f), 106(g), 40113,
44701–44702, 44704. margin from the speed range of the
Novel or Unusual Design Features normal flight envelope. If the airplane
The Proposed Special Conditions experiences an excursion outside this
The PC–12, PC–12/45, and PC–12/47 Accordingly, the Federal Aviation range, a means must be provided to
airplanes will incorporate the following Administration (FAA) proposes the prevent the flight guidance system from
novel or unusual design features: following special condition as part of providing guidance or control to an
Autothrust system. the type certification basis for Pilatus unsafe speed.
Aircraft Ltd., PC–12, PC–12/45, and PC– (i) The flight guidance system
Discussion
12/47 airplane models modified by functions, controls, indications, and
As discussed in the summary section, Innovative Solutions & Support, Inc. alerts must be designed to minimize
this modification makes use of an flightcrew errors and confusion
autothrust system, which is a novel 1. Autothrust System concerning the behavior and operation
design for this type of airplane. The In addition to the requirements of of the flight guidance system. A means
applicable airworthiness regulations do §§ 23.143, 23.1309, and 23.1329, the must be provided to indicate the current
not contain adequate or appropriate following apply: mode of operation, including any armed
safety standards for this design feature. (a) Quick disengagement controls for modes, transitions, and reversions.
Mandating additional requirements— the autothrust function must be Selector switch position is not an
developed in part—by adapting relevant provided for each pilot. The autothrust acceptable means of indication. The
portions of 14 CFR 25.1329, Flight quick disengagement controls must be controls and indications must be
guidance systems—applicable to located on the thrust control levers. grouped and presented in a logical and
autothrust systems—along with FAA Quick disengagement controls must be consistent manner. The indications
experience with similar autothrust readily accessible to each pilot while must be visible to each pilot under all
systems, mitigates the concerns operating the thrust control levers. expected lighting conditions.
associated with installation of the (b) The effects of a failure of the (j) Following disengagement of the
proposed autothrust system. system to disengage the autothrust autothrust function, a caution (visual
function when manually commanded by and auditory) must be provided to each
The FAA has previously issued this the pilot must be assessed in accordance pilot.
proposed special condition to part 23 with the requirements of § 23.1309. (k) During autothrust operation, it
turbojet airplanes, but not for turbo- (c) Engagement or switching of the must be possible for the flightcrew to
propeller airplanes. The PC–12, PC–12/ flight guidance system, a mode, or a move the thrust levers without requiring
45, and PC–12/47 airplanes are unique sensor may not cause the autothrust excessive force. The autothrust may not
jstallworth on DSK7TPTVN1PROD with PROPOSALS

with respect to other turbo-propeller system to affect a transient response that create a potential hazard when the
designs in that the basic design does not alters the airplane’s flight path any flightcrew applies an override force to
include a separate propeller control greater than a minor transient, as the thrust levers.
lever. Future use of these special defined in paragraph (l)(1) of this (l) For purposes of this section, a
conditions on other turbo-propeller special condition. transient is a disturbance in the control
designs will require evaluation of the (d) Under normal conditions, the or flight path of the airplane that is not
engine and propeller control system to disengagement of any automatic control consistent with response to flightcrew
determine their appropriateness. function of a flight guidance system may inputs or environmental conditions.

VerDate Sep<11>2014 13:41 Apr 13, 2017 Jkt 241001 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 E:\FR\FM\14APP1.SGM 14APP1

Federal Register / Vol. 82, No. 71 / Friday, April 14, 2017 / Proposed Rules 17945

(1) A minor transient would not 11.43 and 11.45, by any of the following We will post all comments we
significantly reduce safety margins and methods: receive, without change, to http://
would involve flightcrew actions that • Federal eRulemaking Portal: Go to www.regulations.gov, including any
are well within their capabilities. A http://www.regulations.gov. Follow the personal information you provide. We
minor transient may involve a slight instructions for submitting comments. will also post a report summarizing each
increase in flightcrew workload or some • Fax: 202–493–2251. substantive verbal contact we receive
physical discomfort to passengers or • Mail: U.S. Department of about this NPRM.
cabin crew. Transportation, Docket Operations, M–
30, West Building Ground Floor, Room Discussion
(2) A significant transient may lead to
a significant reduction in safety W12–140, 1200 New Jersey Avenue SE., We learned that GE has determined,
margins, an increase in flightcrew Washington, DC 20590. based on analysis, that the stresses in
workload, discomfort to the flightcrew, • Hand Delivery: Deliver to Mail the pinholes in the affected fan blade
or physical distress to the passengers or address above between 9 a.m. and 5 could result in crack initiation at
cabin crew, possibly including non-fatal p.m., Monday through Friday, except pinhole surfaces beyond 19,000, 19,500,
injuries. Significant transients do not Federal holidays. or 25,000 cyles-since-new (CSN),
For service information identified in depending on the engine model on
require—in order to remain within or
this NPRM, contact General Electric which the blade is installed. GE,
recover to the normal flight envelope—
Company, GE-Aviation, Room 285, 1 therefore, has initiated a program of
any of the following:
(i) Exceptional piloting skill, Neumann Way, Cincinnati, OH 45215, initial and repetitive eddy current
alertness, or strength. phone: 513–552–3272; fax: 513–552– inspections (ECIs) and removal of this
(ii) Forces applied by the pilot which 3329; email: geae.aoc@ge.com. You may fan blade before it reaches 41,000 CSN.
are greater than those specified in view this service information at the GE also provided an option to repair the
§ 23.143(c). FAA, Engine & Propeller Directorate, blade which allows for an additional
(iii) Accelerations or attitudes in the 1200 District Avenue, Burlington, MA. 28,000 cycles before it must be removed.
airplane that might result in further For information on the availability of This condition, if not corrected, could
hazard to secured or non-secured this material at the FAA, call 781–238– result in failure of the fan blade,
occupants. 7125. uncontained blade release, damage to
Issued in Kansas City, Missouri on April 4, Examining the AD Docket the engine, and damage to the airplane.
2017. You may examine the AD docket on Related Service Information Under 1
Pat Mullen, the Internet at http:// CFR Part 51
Acting Manager, Small Airplane Directorate, www.regulations.gov by searching for
We reviewed GE Alert Service
Aircraft Certification Service. and locating Docket No. FAA–2017–
Bulletins (ASBs) CF34–8C SB 72–A0137
[FR Doc. 2017–07382 Filed 4–13–17; 8:45 am] 0164; or in person at the Docket
R05, dated June 15, 2016; and CF34–8E
BILLING CODE 4910–13–P Management Facility between 9 a.m.
SB 72–A0060 R05, dated June 15, 2016.
and 5 p.m., Monday through Friday,
These ASBs provide the procedures
except Federal holidays. The AD docket
necessary for calculating the adjusted
DEPARTMENT OF TRANSPORTATION contains this proposed AD, the
CSN for the initial inspection. This
regulatory evaluation, any comments
Federal Aviation Administration service information is reasonably
received, and other information. The
available because the interested parties
street address for the Docket Office
14 CFR Part 39 have access to it through their normal
(phone: 800–647–5527) is in the
course of business or by the means
[Docket No. FAA–2017–0164; Directorate ADDRESSES section. Comments will be
identified in the ADDRESSES section.
Identifier 2017–NE–06–AD] available in the AD docket shortly after
receipt. Other Related Service Information
RIN 2120–AA64
FOR FURTHER INFORMATION CONTACT: We reviewed GE ASB CF34–8E SB
Airworthiness Directives; General Martin Adler, Aerospace Engineer, 72–A0115 R03, issued on December 9,
Electric Company Turbofan Engines Engine Certification Office, FAA, Engine 2016, and GE ASB CF34–8C SB 72–
& Propeller Directorate, 1200 District A0225 R03, issued on December 9,
AGENCY: Federal Aviation Avenue, Burlington, MA 01803; phone: 2016. The ASB’s describe procedures for
Administration (FAA), DOT. 781–238–7157; fax: 781–238–7199; repairing fan blade, part number (P/N)
ACTION: Notice of proposed rulemaking email: martin.adler@faa.gov. 4114T15P02, to P/N 4114T31G01 with
(NPRM). SUPPLEMENTARY INFORMATION: the installation of a bushing in the
SUMMARY: We propose to adopt a new Comments Invited pinholes.
airworthiness directive (AD) for certain We invite you to send any written FAA’s Determination
General Electric Company (GE) CF34–8 relevant data, views, or arguments about We are proposing this AD because we
model turbofan engines. This proposed this NPRM. Send your comments to an evaluated all the relevant information
AD was prompted by analysis that address listed under the ADDRESSES and determined the unsafe condition
resulted in the reduction of the life of section. Include ‘‘Docket No. FAA– described previously is likely to exist or
the affected fan blades. This proposed 2017–0164; Directorate Identifier 2017– develop in other products of the same
jstallworth on DSK7TPTVN1PROD with PROPOSALS

AD would require inspections of the NE–06–AD’’ at the beginning of your type design.
affected fan blades until their removal. comments. We specifically invite
We are proposing this AD to correct the comments on the overall regulatory, Proposed AD Requirements
unsafe condition on these products. economic, environmental, and energy This proposed AD would require
DATES: We must receive comments on aspects of this NPRM. We will consider initial and repetitive ECIs of the affected
this proposed AD by May 30, 2017. all comments received by the closing fan blade. This proposed AD would also
ADDRESSES: You may send comments, date and may amend this NPRM require removal or repair of the affected
using the procedures found in 14 CFR because of those comments. fan blade at a reduced life. A fan blade

VerDate Sep<11>2014 13:41 Apr 13, 2017 Jkt 241001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 E:\FR\FM\14APP1.SGM 14APP1

Document Created: 2017-04-14 00:56:23
Document Modified: 2017-04-14 00:56:23

Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Proposed Rules
Action		Notice of proposed special conditions.
Dates		Send your comment on or before May 15, 2017.
Contact		Jeff Pretz, Federal Aviation Administration, Small Airplane Directorate, Aircraft Certification Service, 901 Locust, Room 301, Kansas City, MO 64106; telephone (816) 329-3239; facsimile (816) 329-4090.
FR Citation		82 FR 17943
CFR Associated		Aircraft; Aviation Safety and Signs and Symbols

82 FR 17943 - Special Conditions: Pilatus Aircraft Limited Models PC-12, PC-12/45, PC-12/47; Autothrust System

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 82, Issue 71 (April 14, 2017)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration