80 FR 50808 - Special Conditions: Cirrus Aircraft Corporation, SF50; Auto Throttle.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 162 (August 21, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 162 (August 21, 2015)
| Page Range | 50808-50810 | |
| FR Document | 2015-20756 |
[Federal Register Volume 80, Number 162 (Friday, August 21, 2015)] [Proposed Rules] [Pages 50808-50810] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-20756] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 23 [Docket No. FAA-2015-3464; Notice No. 23-15-04-SC] Special Conditions: Cirrus Aircraft Corporation, SF50; Auto Throttle. AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed special conditions. ----------------------------------------------------------------------- SUMMARY: This action proposes special conditions for the Cirrus Aircraft Corporation Model SF50 airplane. This airplane will have a novel or unusual design feature(s) associated with installation of an Auto Throttle System. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These proposed 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: Send your comments on or before October 5, 2015. ADDRESSES: Send comments identified by docket number FAA-2015-3464 using any of the following methods: [ssquf] Federal eRegulations Portal: Go to http://www.regulations.gov and follow the online instructions for sending your comments electronically. [ssquf] 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. [ssquf] 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. [ssquf] 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, FAA, Regulations and Policy Branch, ACE-111, Small Airplane Directorate, Aircraft Certification Service, 901 Locust; Kansas City, Missouri 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 September 9, 2008, Cirrus Aircraft Corporation applied for a type certificate for their new Model SF50. On December 11, 2012 Cirrus elected to adjust the certification basis of the SF50 to include 14 CFR part 23 through amendment 62. The SF50 is a low-wing, 7-seat (5 adults and 2 children), pressurized, retractable gear, carbon composite airplane with one turbofan engine mounted partially in the upper aft fuselage. It is constructed largely of carbon and fiberglass composite materials. Like other Cirrus products, the SF50 includes a ballistically deployed airframe parachute. The SF50 has a maximum operating altitude of 28,000 feet and the maximum takeoff weight will be at or below 6,000 pounds with a range at economy cruise of roughly 1,000 nautical miles. [[Page 50809]] Current part 23 airworthiness regulations do not contain appropriate safety standards for an Auto Throttle System (ATS) installation; therefore, special conditions are required to establish an acceptable level of safety. Part 25 regulations contain appropriate safety standards for these systems, making the intent for this project to apply the language in Sec. 25.1329 for the auto throttle, while substituting Sec. 23.1309 and Sec. 23.143 in place of the similar part 25 regulations referenced in Sec. 25.1329. In addition, malfunction of the ATS to perform its intended function shall be evaluated per the Loss of Thrust Control (LOTC) criteria established under part 33 for electronic engine controls. An analysis must show that no single failure or malfunction or probable combinations of failures of the ATS will permit the LOTC probability to exceed those established under part 33 for an electronic engine control. Type Certification Basis Under the provisions of 14 CFR 21.17, Cirrus must show that the Model SF50 meets the applicable provisions of part 23, as amended by amendments 23-1 through 23-62 thereto. If the Administrator finds that the applicable airworthiness regulations (i.e., 14 CFR part 23) do not contain adequate or appropriate safety standards for the SF50 because of a novel or unusual design feature, special conditions are prescribed under the provisions of Sec. 21.16. 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 or similar novel or unusual design feature, the special conditions would also apply to the other model under Sec. 21.101. In addition to the applicable airworthiness regulations and special conditions, the SF50 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 and the FAA must issue a finding of regulatory adequacy under Sec. 611 of Public Law 92-574, the Noise Control Act of 1972. 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. 21.17(a)(2). Novel or Unusual Design Features The SF50 will incorporate the following novel or unusual design features: An ATS as part of the automatic flight control system. The ATS utilizes a Garmin ``smart'' autopilot servo with a physical connection to the throttle quadrant control linkage. The auto throttle may be controlled by the pilot with an optional auto throttle control panel adjacent to the throttle lever. The auto throttle also provides an envelope protection function which does not require installation of the optional control panel. Discussion Part 23 currently does not sufficiently address auto throttle (also referred to as auto thrust) technology and safety concerns. Therefore, special conditions must be developed and applied to this project to ensure an acceptable level of safety has been obtained. For approval to use the ATS during flight, the SF50 must demonstrate compliance to the intent of the requirements of Sec. 25.1329, applying the appropriate part 23 references to Sec. 23.1309 (to include performing a functional hazard assessment or system safety assessment to determine the applicable Software and Airborne Electronic Hardware assurance levels, and compliance to DO-178C & DO-254, as required) and Sec. 23.143. In addition, a malfunction of the ATS to perform its intended function is an LOTC event, and may result in a total loss of thrust control, transients, or uncommanded thrust changes. The classification of the failure condition for an LOTC event on a Class II single-engine aircraft is hazardous for aircraft that stall at or below 61 knots. From publication AC 23.1309-1E, based upon failure probability values shown in Figure 2, an LOTC event would have to meet a probability of failure value not to exceed 1X10-6. In-service data for LOTC in single-engine turbine aircraft shows LOTC events exceed this probability; therefore, part 33 requirements for engine control probabilities will be accepted for the part 23 LOTC requirement. The probabilities of failure for an LOTC event on a turbine engine shall not exceed the following (see AC33.28-1 and ANE-1993-33.28TLD-R1 for further guidance): 1. Average Events per Million Hours: 10 (1X10-05 per hour). 2. Maximum Events per Million Hours: 100 (1X10-04 per hour). Note: The maximum events per flight hour are intended for Time Limited Dispatch (TLD) operation where the risk exposure is mitigated by limiting the time in which the aircraft is operated in the degraded condition. Applicability As discussed above, these special conditions are applicable to the Model SF50. Should Cirrus apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, the special conditions would apply 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. List of Subjects in 14 CFR Part 23 Aircraft, Aviation safety, Signs and symbols. Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. The Proposed Special Conditions Accordingly, the Federal Aviation Administration (FAA) proposes the following special conditions as part of the type certification basis for Cirrus Aircraft Corporation Model SF50 airplanes. 1. Certification of auto throttle system under part 23. (a) Quick disengagement controls for the auto thrust functions must be provided for each pilot. The auto thrust 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 auto thrust functions 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 section. (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 section. (f) The function and direction of motion of each command reference [[Page 50810]] 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 flight crew 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 auto thrust function, a caution (visual and auditory) must be provided to each pilot. (k) During auto thrust operation, it must be possible for the flight crew to move the thrust levers without requiring excessive force. The auto thrust may not create a potential hazard when the flight crew 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 flight crew inputs or environmental conditions. (1) A minor transient would not significantly reduce safety margins and would involve flight crew actions that are well within their capabilities. A minor transient may involve a slight increase in flight crew 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 flight crew workload, discomfort to the flight crew, 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. Cirrus must also demonstrate, through tests and analysis, that no single failure or malfunction or probable combinations of failures of the auto thrust system components results in the probability for LOTC, or un-commanded thrust changes and transients that result in an LOTC event, to exceed the following: 1. Average Events per Million Hours: 10 (1X10-05 per hour) 2. Maximum Events per Million Hours: 100 (1X10-04 per hour) Note: The term ``probable'' in the context of ``probable combination of failures'' does not have the same meaning as used for a safety assessment process. The term ``probable'' in ``probable combination of failures'' means ``foreseeable,'' or those failure conditions anticipated to occur one or more times during the operational life of each airplane. Issued in Kansas City, Missouri, on August 13, 2015. Earl Lawrence, Manger, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-20756 Filed 8-20-15; 8:45 am] BILLING CODE 4910-13-P
![50808 Federal Register / Vol. 80, No. 162 / Friday, August 21, 2015 / Proposed Rules
§ 1238.3 Annual stress test. Dated: August 13, 2015. and read the electronic form of all
(a) * * * Melvin L. Watt, comments received into any FAA
Director, Federal Housing Finance Agency. docket, including the name of the
(1) Shall complete an annual stress individual sending the comment (or
[FR Doc. 2015–20613 Filed 8–20–15; 8:45 am]
test of itself based on its data as of signing the comment for an association,
BILLING CODE 8070–01–P
December 31 of the preceding calendar business, labor union, etc.). DOT’s
year; complete Privacy Act Statement can be
* * * * * found in the Federal Register published
DEPARTMENT OF TRANSPORTATION
on April 11, 2000 (65 FR 19477–19478),
(b) Scenarios provided by FHFA. In
Federal Aviation Administration as well as at http://DocketsInfo.dot.gov.
conducting its annual stress tests under Docket: Background documents or
this section, each regulated entity must comments received may be read at
use scenarios provided by FHFA, which 14 CFR Part 23
http://www.regulations.gov at any time.
shall be generally consistent with and [Docket No. FAA–2015–3464; Notice No. 23– Follow the online instructions for
comparable to those established by the 15–04–SC] accessing the docket or go to the Docket
FRB, that reflect a minimum of three Operations in Room W12–140 of the
sets of economic and financial Special Conditions: Cirrus Aircraft West Building Ground Floor at 1200
conditions, including a baseline, Corporation, SF50; Auto Throttle. New Jersey Avenue SE., Washington,
adverse, and severely adverse scenario. DC, between 9 a.m., and 5 p.m., Monday
AGENCY: Federal Aviation
Not later than 30 days after the FRB through Friday, except Federal holidays.
Administration (FAA), DOT.
publishes its scenarios, FHFA will issue FOR FURTHER INFORMATION CONTACT: Jeff
ACTION: Notice of proposed special
to all regulated entities a description of Pretz, FAA, Regulations and Policy
the baseline, adverse, and severely conditions.
Branch, ACE–111, Small Airplane
adverse scenarios that each regulated SUMMARY: This action proposes special Directorate, Aircraft Certification
entity shall use to conduct its annual conditions for the Cirrus Aircraft Service, 901 Locust; Kansas City,
stress tests under this part. Corporation Model SF50 airplane. This Missouri 64106; telephone (816) 329–
* * * * * airplane will have a novel or unusual 3239; facsimile (816) 329–4090.
■ 3. Amend § 1238.5 by revising design feature(s) associated with SUPPLEMENTARY INFORMATION:
paragraph (a) to read as follows: installation of an Auto Throttle System.
The applicable airworthiness Comments Invited
§ 1238.5 Required report to FHFA and the regulations do not contain adequate or We invite interested people to take
FRB of stress test results and related appropriate safety standards for this part in this rulemaking by sending
information. design feature. These proposed special written comments, data, or views. The
conditions contain the additional safety most helpful comments reference a
(a) Report required for stress tests. On
standards that the Administrator specific portion of the special
or before May 20 of each year, the
considers necessary to establish a level conditions, explain the reason for any
Enterprises must report the results of
of safety equivalent to that established recommended change, and include
the stress tests required under § 1238.3
by the existing airworthiness standards. supporting data. We ask that you send
to FHFA, and to the FRB, in accordance us two copies of written comments.
with paragraph (b) of this section; and DATES: Send your comments on or
We will consider all comments we
on or before August 31 of each year, the before October 5, 2015.
receive on or before the closing date for
Banks must report the results of the ADDRESSES: Send comments identified comments. We will consider comments
stress tests required under § 1238.3 to by docket number FAA–2015–3464 filed late if it is possible to do so
FHFA, and to the FRB, in accordance using any of the following methods: without incurring expense or delay. We
with paragraph (b) of this section; D Federal eRegulations Portal: Go to may change these special conditions
* * * * * http://www.regulations.gov and follow based on the comments we receive.
the online instructions for sending your
■ 4. Amend § 1238.7 by revising Background
comments electronically.
paragraph (a) to read as follows: D Mail: Send comments to Docket On September 9, 2008, Cirrus Aircraft
§ 1238.7 Publication of results by Operations, M–30, U.S. Department of Corporation applied for a type
regulated entities. Transportation (DOT), 1200 New Jersey certificate for their new Model SF50. On
Avenue SE., Room W12–140, West December 11, 2012 Cirrus elected to
(a) Public disclosure of results Building Ground Floor, Washington, DC adjust the certification basis of the SF50
required for stress tests of regulated 20590–0001. to include 14 CFR part 23 through
entities. The Enterprises must disclose D Hand Delivery of Courier: Take amendment 62. The SF50 is a low-wing,
publicly a summary of the stress test comments to Docket Operations in 7-seat (5 adults and 2 children),
results for the severely adverse scenario Room W12–140 of the West Building pressurized, retractable gear, carbon
not earlier than August 1 and not later Ground Floor at 1200 New Jersey composite airplane with one turbofan
than August 15 of each year. Each Bank Avenue SE., Washington, DC, between 9 engine mounted partially in the upper
must disclose publicly a summary of the a.m., and 5 p.m., Monday through aft fuselage. It is constructed largely of
stress test results for the severely Friday, except Federal holidays. carbon and fiberglass composite
rmajette on DSK7SPTVN1PROD with PROPOSALS
adverse scenario not earlier than D Fax: Fax comments to Docket materials. Like other Cirrus products,
November 15 and not later than Operations at 202–493–2251. the SF50 includes a ballistically
November 30 of each year. The Privacy: The FAA will post all deployed airframe parachute. The SF50
summary may be published on the comments it receives, without change, has a maximum operating altitude of
regulated entity’s Web site or in any to http://regulations.gov, including any 28,000 feet and the maximum takeoff
other form that is reasonably accessible personal information the commenter weight will be at or below 6,000 pounds
to the public; provides. Using the search function of with a range at economy cruise of
* * * * * the docket Web site, anyone can find roughly 1,000 nautical miles.
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![50810 Federal Register / Vol. 80, No. 162 / Friday, August 21, 2015 / Proposed Rules
control, such as heading select or or physical distress to the passengers or prompted by a report of significant fuel
vertical speed, must be plainly cabin crew, possibly including non-fatal leakage at the middle position of the left
indicated on, or adjacent to, each injuries. Significant transients do not outboard slat. This proposed AD would
control if necessary to prevent require, in order to remain within or require modifying the assembly of the
inappropriate use or confusion. recover to the normal flight envelope, slat extension mechanical stop. We are
(g) Under any condition of flight any of the following: proposing this AD to prevent failure of
appropriate to its use, the flight i. Exceptional piloting skill, alertness, the assembly of the slat extension
guidance system may not produce or strength. mechanical stop, which if not corrected,
hazardous loads on the airplane, nor ii. Forces applied by the pilot which could lead to a significant fuel leak and
create hazardous deviations in the flight are greater than those specified in result in an uncontained fire.
path. This applies to both fault-free § 23.143(c). DATES: We must receive comments on
operation and in the event of a iii. Accelerations or attitudes in the this proposed AD by October 5, 2015.
malfunction, and assumes that the pilot airplane that might result in further ADDRESSES: You may send comments,
begins corrective action within a hazard to secured or non-secured using the procedures found in 14 CFR
reasonable period of time. occupants. 11.43 and 11.45, by any of the following
(h) When the flight guidance system Cirrus must also demonstrate, through methods:
is in use, a means must be provided to tests and analysis, that no single failure • Federal eRulemaking Portal: Go to
avoid excursions beyond an acceptable or malfunction or probable http://www.regulations.gov. Follow the
margin from the speed range of the combinations of failures of the auto instructions for submitting comments.
normal flight envelope. If the airplane thrust system components results in the • Fax: 202–493–2251.
experiences an excursion outside this probability for LOTC, or un-commanded • Mail: U.S. Department of
range, a means must be provided to thrust changes and transients that result Transportation, Docket Operations, M–
prevent the flight guidance system from in an LOTC event, to exceed the 30, West Building Ground Floor, Room
providing guidance or control to an following: W12–140, 1200 New Jersey Avenue SE.,
unsafe speed. 1. Average Events per Million Hours: Washington, DC 20590.
(i) The flight guidance system 10 (1X10¥05 per hour) • Hand Delivery: U.S. Department of
functions, controls, indications, and 2. Maximum Events per Million Transportation, Docket Operations, M–
alerts must be designed to minimize Hours: 100 (1X10¥04 per hour) 30, West Building Ground Floor, Room
flight crew errors and confusion W12–140, 1200 New Jersey Avenue SE.,
concerning the behavior and operation Note: The term ‘‘probable’’ in the context Washington, DC, between 9 a.m. and 5
of the flight guidance system. Means of ‘‘probable combination of failures’’ does
not have the same meaning as used for a
p.m., Monday through Friday, except
must be provided to indicate the current safety assessment process. The term Federal holidays.
mode of operation, including any armed ‘‘probable’’ in ‘‘probable combination of For service information identified in
modes, transitions, and reversions. failures’’ means ‘‘foreseeable,’’ or those this proposed AD, contact Dassault
Selector switch position is not an failure conditions anticipated to occur one or Falcon Jet, P.O. Box 2000, South
acceptable means of indication. The more times during the operational life of each Hackensack, NJ 07606; telephone 201–
controls and indications must be airplane. 440–6700; Internet http://
grouped and presented in a logical and www.dassaultfalcon.com. You may
consistent manner. The indications Issued in Kansas City, Missouri, on August view this referenced service information
13, 2015.
must be visible to each pilot under all at the FAA, Transport Airplane
expected lighting conditions. Earl Lawrence, Directorate, 1601 Lind Avenue SW.,
(j) Following disengagement of the Manger, Small Airplane Directorate, Aircraft Renton, WA. For information on the
auto thrust function, a caution (visual Certification Service. availability of this material at the FAA,
and auditory) must be provided to each [FR Doc. 2015–20756 Filed 8–20–15; 8:45 am] call 425–227–1221.
pilot. BILLING CODE 4910–13–P
Examining the AD Docket
(k) During auto thrust operation, it
must be possible for the flight crew to You may examine the AD docket on
move the thrust levers without requiring DEPARTMENT OF TRANSPORTATION the Internet at http://
excessive force. The auto thrust may not www.regulations.gov by searching for
create a potential hazard when the flight Federal Aviation Administration and locating Docket No. FAA–2015–
crew applies an override force to the 3144; or in person at the Docket
thrust levers. 14 CFR Part 39 Management Facility between 9 a.m.
(l) For purposes of this section, a [Docket No. FAA–2015–3144; Directorate and 5 p.m., Monday through Friday,
transient is a disturbance in the control Identifier 2014–NM–110–AD] except Federal holidays. The AD docket
or flight path of the airplane that is not contains this proposed AD, the
RIN 2120–AA64 regulatory evaluation, any comments
consistent with response to flight crew
inputs or environmental conditions. received, and other information. The
Airworthiness Directives; Dassault
(1) A minor transient would not street address for the Docket Operations
Aviation
significantly reduce safety margins and office (telephone 800–647–5527) is in
would involve flight crew actions that AGENCY: Federal Aviation the ADDRESSES section. Comments will
are well within their capabilities. A Administration (FAA), DOT. be available in the AD docket shortly
rmajette on DSK7SPTVN1PROD with PROPOSALS
minor transient may involve a slight ACTION: Notice of proposed rulemaking after receipt.
increase in flight crew workload or (NPRM). FOR FURTHER INFORMATION CONTACT: Tom
some physical discomfort to passengers Rodriguez, Aerospace Engineer,
or cabin crew. SUMMARY: We propose to adopt a new International Branch, ANM–116,
(2) A significant transient may lead to airworthiness directive (AD) for certain Transport Airplane Directorate, FAA,
a significant reduction in safety Dassault Aviation Model FALCON 1601 Lind Avenue SW., Renton, WA
margins, an increase in flight crew 900EX airplanes and FALCON 2000EX 98057–3356; telephone 425–227–1137;
workload, discomfort to the flight crew, airplanes. This proposed AD was fax 425–227–1149.
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Document Created: 2018-02-23 11:01:00
Document Modified: 2018-02-23 11:01:00
| 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 comments on or before October 5, 2015. | |
| Contact | Jeff Pretz, FAA, Regulations and Policy Branch, ACE-111, Small Airplane Directorate, Aircraft Certification Service, 901 Locust; Kansas City, Missouri 64106; telephone (816) 329-3239; facsimile (816) 329-4090. | |
| FR Citation | 80 FR 50808 | |
| CFR Associated | Aircraft; Aviation Safety and Signs and Symbols |
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