82 FR 32618 - Special Conditions: Pilatus Aircraft Ltd., PC-24, Autothrust System

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 82, Issue 135 (July 17, 2017)

Page Range		32618-32620
FR Document		2017-14938

These special conditions are issued for the Pilatus Aircraft Ltd. PC-24 airplane. This airplane will have a novel or unusual design feature associated with installation of an autothrust system. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.

Federal Register, Volume 82 Issue 135 (Monday, July 17, 2017)

[Federal Register Volume 82, Number 135 (Monday, July 17, 2017)]
[Rules and Regulations]
[Pages 32618-32620]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2017-14938]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. FAA-2017-0703; Special Conditions No. 23-283-SC]


Special Conditions: Pilatus Aircraft Ltd., PC-24, Autothrust 
System

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions; request for comments.

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SUMMARY: These special conditions are issued for the Pilatus Aircraft 
Ltd. PC-24 airplane. This airplane will have a novel or unusual design 
feature associated with installation of an autothrust system. The 
applicable airworthiness regulations do not contain adequate or 
appropriate safety standards for this design feature. These special 
conditions contain the additional safety standards that the 
Administrator considers necessary to establish a level of safety 
equivalent to that established by the existing airworthiness standards.

DATES: These special conditions are effective July 17, 2017, and are 
applicable July 6, 2017.

ADDRESSES: Send comments identified by docket number FAA-2017-0703 
using any of the following methods:
    [squ] Federal eRegulations Portal: Go to http://www.regulations.gov 
and follow the online instructions for sending your comments 
electronically.
    [squ] 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.
    [squ] 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.
    [squ] 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, ACE-111, Federal Aviation 
Administration, Small Airplane Directorate, Aircraft Certification 
Service, 901 Locust Street, Kansas City, MO 64106; telephone (816) 329-
3239; facsimile (816) 329-4090.

SUPPLEMENTARY INFORMATION: The FAA has determined, in accordance with 5 
U.S.C. 553(b)(3)(B) and 553(d)(3), that notice and opportunity for 
prior public comment hereon are unnecessary because the substance of 
these special conditions has been subject to the public comment process 
in several prior instances with no substantive comments received. The 
FAA therefore finds that good cause exists for making these special 
conditions effective upon issuance.

------------------------------------------------------------------------
       Special condition No.\2\              Company/airplane model
------------------------------------------------------------------------
23-264-SC.............................  Honda Aircraft Company/Model HA-
                                         420.
23-272-SC.............................  Cirrus Design Corporation/Model
                                         SF50.
23-281-SC.............................  Innovative Solutions and Support
                                         Inc./Pilatus Aircraft Ltd., PC-
                                         12 Models.
------------------------------------------------------------------------

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.
---------------------------------------------------------------------------

    \2\ See http://rgl.faa.gov/ to review the listed special 
conditions.
---------------------------------------------------------------------------

    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 July 9, 2012, Pilatus Aircraft Ltd. applied for a type 
certificate for their new PC-24 airplane. The PC-24 is an aluminum 
pressurized low-wing business jet with a T-tail configuration and 
retractable undercarriage designed to meet the commuter category 
requirements of part 23. Two Williams International FJ44-4A turbofan 
engines rated at 3,400 pounds (lbs.) of take-off thrust, situated in 
nacelles on each side of the rear fuselage power the PC-24. The PC-24 
will have a Maximum Take-off Weight (MTOW) of 17,200 pounds (7,802 
kilograms). It has a maximum seating capacity of up to ten passengers 
and one or two pilots. The airplane will be certificated for day and 
night Visual Flight Rules, Instrument Flight Rules and flight into 
known icing.
    The PC-24 is equipped with an autothrust system--also referred to 
as an autothrottle system. The autothrust system is useable in all 
phases of flight from takeoff to decision height on approach. The 
system includes speed and thrust modes along with monitors to prevent 
the system from exceeding engine or airspeed limits. A servo provides 
throttle movement, which is part of each throttle quadrant assembly. 
The servo(s) can be overridden by pilot force or disconnected using the 
autothrottle quick disconnect switch on either thrust control lever, 
the autopilot quick disconnect switch on the yoke, or the autothrottle 
control switch on the flight guidance panel.

Type Certification Basis

    Under the provisions of 14 CFR 21.17, Pilatus Aircraft Ltd. must 
show the PC-24 meets the applicable provisions of part 23, as amended 
by amendments 23-1 through 23-62 thereto.
    If the Administrator finds the applicable airworthiness regulations 
(i.e., 14 CFR part 23) do not contain adequate or appropriate safety 
standards for the PC-24 because of a novel or unusual design feature, 
special conditions are prescribed under the provisions of Sec.  21.16.
    In addition to the applicable airworthiness regulations and special 
conditions, the PC-24 must comply with the fuel vent and exhaust 
emission

[[Page 32619]]

requirements of 14 CFR part 34, the noise certification requirements of 
14 CFR part 36, and the FAA must issue a finding of regulatory adequacy 
pursuant to section 611 of Public Law 92-574, the ``Noise Control Act 
of 1972.''
    The FAA issues special conditions, as defined in Sec.  11.19, under 
Sec.  11.38 and they become part of the type certification basis under 
Sec.  21.17(a)(2).
    Special conditions are initially applicable to the model for which 
they are issued. Should the type certificate for that model be amended 
later to include any other model that incorporates the same novel or 
unusual design feature, the FAA would apply these special conditions to 
the other models under Sec.  21.101.

Novel or Unusual Design Features

    The PC-24 will incorporate the following novel or unusual design 
features:

Autothrust System

Discussion

    As discussed in the ``Background'' section, the PC-24 will 
incorporate an autothrust system, which is considered 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 the relevant portions 14 CFR 25.1329 (automatic pilot systems) 
applicable to the autothrust system--along with FAA experience with 
similar autothrust systems. This additional requirement mitigates the 
concerns associated with installation of the autothrust system.

Applicability

    As discussed above, these special conditions are applicable to the 
PC-24. Should Pilatus Aircraft Ltd. apply at a later date for a change 
to the type certificate to include another model on the same type 
certificate incorporating 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 one model of airplanes. It is not a rule of general applicability 
and it affects only the applicant who applied to the FAA for approval 
of these features on the airplane.
    The substance of these special conditions has been subjected to the 
notice and comments period in several prior instances--identified 
above--and has been derived without substantive change from those 
previously issued. It is unlikely that prior public comment would 
result in a significant change from the substance contained herein. 
Therefore, notice and opportunity for prior public comments hereon are 
unnecessary and the FAA finds good cause, in accordance with 5 U.S.C. 
553(b)(3)(B) and 553(d)(3), making these special conditions effective 
upon issuance. The FAA is requesting comments to allow interested 
persons to submit views that may not have been submitted in response to 
the prior opportunities for comment described above.

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 and 44701; 14 CFR 
21.16 and 21.17; and 14 CFR 11.38 and 11.19.

The Special Conditions

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the following special conditions are issued as part of 
the type certification basis for Pilatus Aircraft Ltd. PC-24 airplanes.
    1. Autothrust System.
    For autothrust systems, 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 auto thrust 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 period of 
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. 
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.
    (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

[[Page 32620]]

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 July 6, 2017.
Kelly Broadway,
Acting Manager, Small Airplane Directorate Aircraft Certification 
Service.
[FR Doc. 2017-14938 Filed 7-14-17; 8:45 am]
BILLING CODE 4910-13-P

Federal Register / Vol. 82, No. 135 / Monday, July 17, 2017 / Rules and Regulations 32619

requirements of 14 CFR part 34, the change from those previously issued. It guidance system may not result in a
noise certification requirements of 14 is unlikely that prior public comment transient any greater than a significant
CFR part 36, and the FAA must issue a would result in a significant change transient, as defined in paragraph (l)(2)
finding of regulatory adequacy pursuant from the substance contained herein. of this special condition.
to section 611 of Public Law 92–574, the Therefore, notice and opportunity for (f) The function and direction of
‘‘Noise Control Act of 1972.’’ prior public comments hereon are motion of each command reference
The FAA issues special conditions, as unnecessary and the FAA finds good control, such as heading select or
defined in § 11.19, under § 11.38 and cause, in accordance with 5 U.S.C. vertical speed, must be plainly
they become part of the type 553(b)(3)(B) and 553(d)(3), making these indicated on—or adjacent to—each
certification basis under § 21.17(a)(2). special conditions effective upon control if necessary to prevent
Special conditions are initially issuance. The FAA is requesting inappropriate use or confusion.
applicable to the model for which they comments to allow interested persons to (g) Under any condition of flight
are issued. Should the type certificate submit views that may not have been appropriate to its use, the flight
for that model be amended later to submitted in response to the prior guidance system may not produce
include any other model that opportunities for comment described hazardous loads on the airplane, nor
incorporates the same novel or unusual above. create hazardous deviations in the flight
design feature, the FAA would apply path. This applies to both fault-free
these special conditions to the other List of Subjects in 14 CFR Part 23 operation and in the event of a
models under § 21.101. Aircraft, Aviation safety, Signs and malfunction and assumes that the pilot
symbols. begins corrective action within a
Novel or Unusual Design Features reasonable period of time.
The PC–24 will incorporate the Citation (h) When the flight guidance system
following novel or unusual design The authority citation for these is in use, a means must be provided to
features: special conditions is as follows: avoid excursions beyond an acceptable
Autothrust System Authority: 49 U.S.C. 106(f), 106(g), 40113 margin from the speed range of the
and 44701; 14 CFR 21.16 and 21.17; and 14 normal flight envelope. If the airplane
Discussion experiences an excursion outside this
CFR 11.38 and 11.19.
As discussed in the ‘‘Background’’ range, a means must be provided to
section, the PC–24 will incorporate an The Special Conditions prevent the flight guidance system from
autothrust system, which is considered ■ Accordingly, pursuant to the authority providing guidance or control to an
a novel design for this type of airplane. delegated to me by the Administrator, unsafe speed.
The applicable airworthiness the following special conditions are (i) The flight guidance system
regulations do not contain adequate or issued as part of the type certification functions, controls, indications, and
appropriate safety standards for this basis for Pilatus Aircraft Ltd. PC–24 alerts must be designed to minimize
design feature. Mandating additional airplanes. flightcrew errors and confusion
requirements—developed in part by 1. Autothrust System. concerning the behavior and operation
adapting the relevant portions 14 CFR For autothrust systems, in addition to of the flight guidance system. Means
25.1329 (automatic pilot systems) the requirements of §§ 23.143, 23.1309, must be provided to indicate the current
applicable to the autothrust system— and 23.1329 the following apply: mode of operation, including any armed
along with FAA experience with similar (a) Quick disengagement controls for modes, transitions, and reversions.
autothrust systems. This additional the autothrust function must be Selector switch position is not an
requirement mitigates the concerns provided for each pilot. The autothrust acceptable means of indication. The
associated with installation of the quick disengagement controls must be controls and indications must be
autothrust system. located on the thrust control levers. grouped and presented in a logical and
Quick disengagement controls must be consistent manner. The indications
Applicability readily accessible to each pilot while must be visible to each pilot under all
As discussed above, these special operating the thrust control levers. expected lighting conditions.
conditions are applicable to the PC–24. (b) The effects of a failure of the (j) Following disengagement of the
Should Pilatus Aircraft Ltd. apply at a system to disengage the autothrust autothrust function, a caution—visual
later date for a change to the type function when manually commanded by and auditory—must be provided to each
certificate to include another model on the pilot must be assessed in accordance pilot.
the same type certificate incorporating with the requirements of § 23.1309. (k) During autothrust operation, it
the same novel or unusual design (c) Engagement or switching of the must be possible for the flightcrew to
feature, the FAA would apply these flight guidance system, a mode or a move the thrust levers without requiring
special conditions to that model as well. sensor may not cause the auto thrust excessive force. The autothrust may not
system to affect a transient response that create a potential hazard when the
Conclusion alters the airplane’s flight path any flightcrew applies an override force to
This action affects only certain novel greater than a minor transient, as the thrust levers.
or unusual design features on one model defined in paragraph (l)(1) of this (l) For purposes of this section, a
of airplanes. It is not a rule of general special condition. transient is a disturbance in the control
applicability and it affects only the (d) Under normal conditions, the or flight path of the airplane that is not
applicant who applied to the FAA for disengagement of any automatic control consistent with response to flightcrew
jstallworth on DSK7TPTVN1PROD with RULES

approval of these features on the function of a flight guidance system may inputs or environmental conditions.
airplane. not cause a transient response of the (1) A minor transient would not
The substance of these special airplane’s flight path any greater than a significantly reduce safety margins and
conditions has been subjected to the minor transient. would involve flightcrew actions that
notice and comments period in several (e) Under rare normal and non-normal are well within their capabilities. A
prior instances—identified above—and conditions, disengagement of any minor transient may involve a slight
has been derived without substantive automatic control function of a flight increase in flightcrew workload or some

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32620 Federal Register / Vol. 82, No. 135 / Monday, July 17, 2017 / Rules and Regulations

physical discomfort to passengers or The Director of the Federal Register SUPPLEMENTARY INFORMATION:
cabin crew. approved the incorporation by reference
Discussion
(2) A significant transient may lead to of a certain publication listed in this AD
a significant reduction in safety as of August 1, 2017. Transport Canada Civil Aviation
margins, an increase in flightcrew We must receive comments on this (TCCA), which is the aviation authority
workload, discomfort to the flightcrew, AD by August 31, 2017. for Canada, has issued Canadian AD
or physical distress to the passengers or ADDRESSES: You may send comments, CF–2017–12, dated March 10, 2017
cabin crew, possibly including non-fatal using the procedures found in 14 CFR (referred to after this as the Mandatory
injuries. Significant transients do not 11.43 and 11.45, by any of the following Continuing Airworthiness Information,
require—in order to remain within or methods: or ‘‘the MCAI’’), to correct an unsafe
recover to the normal flight envelope— • Federal eRulemaking Portal: Go to condition for certain Bombardier, Inc.
any of the following: http://www.regulations.gov. Follow the Model BD–100–1A10 airplanes. The
(i) Exceptional piloting skill, instructions for submitting comments. MCAI states:
alertness, or strength. • Fax: 202–493–2251. During production, it was observed that
(ii) Forces applied by the pilot which • Mail: U.S. Department of some fasteners joining the machined rear
are greater than those specified in Transportation, Docket Operations, M– spar center fitting were installed with a gap
§ 23.143(c). between the fastener head and the structure,
30, West Building Ground Floor, Room
(iii) Accelerations or attitudes in the and others were installed tilted. Improperly
W12–140, 1200 New Jersey Avenue SE., installed fasteners could cause a premature
airplane that might result in further Washington, DC 20590. failure of the fitting fasteners and cracking
hazard to secured or non-secured • Hand Delivery: U.S. Department of within the fitting or frame, resulting in the
occupants. Transportation, Docket Operations, M– loss of structural integrity of the wing to
Issued in Kansas City, Missouri, on July 6, 30, West Building Ground Floor, Room fuselage attachment.
2017. W12–140, 1200 New Jersey Avenue SE., This [Canadian] AD mandates the removal
Washington, DC, between 9 a.m. and 5 of all fasteners at the rear spar frame lower
Kelly Broadway,
flange splice, inspection and rework [and
Acting Manager, Small Airplane Directorate p.m., Monday through Friday, except repair] of the holes, and fastener replacement
Aircraft Certification Service. Federal holidays. with self-aligning fasteners and self-aligning
[FR Doc. 2017–14938 Filed 7–14–17; 8:45 am] For service information identified in collars.
BILLING CODE 4910–13–P
this final rule, contact Bombardier, Inc.,
The inspections include a general
400 Côte-Vertu Road West, Dorval,
visual inspection of the fasteners for
Québec H4S 1Y9, Canada; telephone:
damage (i.e., missing, broken, or
DEPARTMENT OF TRANSPORTATION 514–855–5000; fax: 514–855–7401;
deformed), and an eddy current
email: thd.crj@aero.bombardier.com;
Federal Aviation Administration inspection of the fastener holes for
Internet: http://www.bombardier.com.
damage. Rework includes deburring and
You may view this referenced service
14 CFR Part 39 chamfering the holes.
information at the FAA, Transport
You may examine the MCAI on the
Airplane Directorate, 1601 Lind Avenue
[Docket No. FAA–2017–0696; Directorate Internet at http://www.regulations.gov
Identifier 2017–NM–070–AD; Amendment SW., Renton, WA. For information on
by searching for and locating Docket No.
39–18960; AD 2017–14–16] the availability of this material at the
FAA–2017–0696.
FAA, call 425–227–1221. It is also
RIN 2120–AA64 available on the Internet at http:// Related Service Information Under 1
www.regulations.gov by searching for CFR Part 51
Airworthiness Directives; Bombardier,
Inc., Airplanes and locating Docket No. FAA–2017– Bombardier, Inc., has issued Service
0696. Bulletin 100–53–32, dated February 16,
AGENCY: Federal Aviation 2017. The service information describes
Examining the AD Docket
Administration (FAA), DOT. procedures for removing and replacing
ACTION: Final rule; request for You may examine the AD docket on the fasteners attaching the machined
comments. the Internet at http:// center fitting to the rear spar frame
www.regulations.gov by searching for lower flange splice. The service
SUMMARY: We are adopting a new and locating Docket No. FAA–2017– information also describes procedures
airworthiness directive (AD) for certain 0696; or in person at the Docket for inspecting the fasteners and fastener
Bombardier, Inc., Model BD–100–1A10 Operations office between 9 a.m. and 5 holes and reworking the fastener holes.
airplanes. This AD requires removing p.m., Monday through Friday, except This service information is reasonably
the fasteners attaching the machined Federal holidays. The AD docket available because the interested parties
center fitting to the rear spar frame contains this AD, the regulatory have access to it through their normal
lower flange splice, inspecting the evaluation, any comments received, and course of business or by the means
fasteners and fastener holes for damage, other information. The street address for identified in the ADDRESSES section.
reworking and repairing the fastener the Docket Operations office (telephone
holes, as applicable, and replacing the 800–647–5527) is in the ADDRESSES FAA’s Determination and Requirements
fasteners. This AD was prompted by a section. Comments will be available in of This AD
report indicating that certain fasteners the AD docket shortly after receipt. This product has been approved by
attaching the machined rear spar center FOR FURTHER INFORMATION CONTACT: Aziz the aviation authority of another
jstallworth on DSK7TPTVN1PROD with RULES

fitting to the frame were installed with Ahmed, Airframe Engineer, Airframe country, and is approved for operation
a gap between the fastener head and the and Mechanical Systems Branch, ANE– in the United States. Pursuant to our
structure, or were installed tilted. We 171, FAA, New York Aircraft bilateral agreement with the State of
are issuing this AD to address the unsafe Certification Office (ACO), 1600 Stewart Design Authority, we have been notified
condition on these products. Avenue, Suite 410, Westbury, NY of the unsafe condition described in the
DATES: This AD becomes effective 11590; telephone: 516–228–7329; fax: MCAI and service information
August 1, 2017. 516–794–5531. referenced above. We are issuing this

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Document Created: 2017-07-15 03:46:01
Document Modified: 2017-07-15 03:46:01

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		Rules and Regulations
Action		Final special conditions; request for comments.
Dates		These special conditions are effective July 17, 2017, and are applicable July 6, 2017.
Contact		Jeff Pretz, ACE-111, Federal Aviation Administration, Small Airplane Directorate, Aircraft Certification Service, 901 Locust Street, Kansas City, MO 64106; telephone (816) 329- 3239; facsimile (816) 329-4090.
FR Citation		82 FR 32618
CFR Associated		Aircraft; Aviation Safety and Signs and Symbols

82 FR 32618 - Special Conditions: Pilatus Aircraft Ltd., PC-24, Autothrust System

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 82, Issue 135 (July 17, 2017)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration