82 FR 21681 - Special Conditions: Textron Aviation Inc. Model 700 Airplane; Design Roll Maneuver Condition
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 89 (May 10, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 89 (May 10, 2017)
| Page Range | 21681-21683 | |
| FR Document | 2017-09440 |
[Federal Register Volume 82, Number 89 (Wednesday, May 10, 2017)] [Rules and Regulations] [Pages 21681-21683] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-09440] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 25 [Docket No. FAA-2017-0215; Special Conditions No. 25-669-SC] Special Conditions: Textron Aviation Inc. Model 700 Airplane; Design Roll Maneuver Condition AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions; request for comments. ----------------------------------------------------------------------- SUMMARY: These special conditions are issued for the Textron Aviation Inc. (Textron) Model 700 airplane. This airplane will have a novel or unusual design feature when compared to the state of technology envisioned in the airworthiness standards for transport-category airplanes. This design feature is an electronic flight-control system that provides control through pilot inputs to the flight computer. 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: This action is effective on Textron on May 10, 2017. We must receive your comments by June 26, 2017. ADDRESSES: Send comments identified by docket number FAA-2017-0215 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 or 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://www.regulations.gov/, including any personal information the commenter provides. Using the search [[Page 21682]] 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) 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 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: Greg Schneider, FAA, Airframe and Cabin Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW., Renton, Washington 98057- 3356; telephone 425-227-2116; facsimile 425-227-1320. SUPPLEMENTARY INFORMATION: The FAA has determined that notice of, and opportunity for prior public comment on, these special conditions is impracticable because these procedures would significantly delay issuance of the design approval and thus delivery of the affected airplane. In addition, 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 it unnecessary to delay the effective date and finds tthat good cause exists for making these special conditions effective upon publication in the Federal Register. 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 will consider all comments we receive by the closing date for comments. We may change these special conditions based on the comments we receive. Background On November 20, 2014, Textron applied for a type certificate for their new Model 700 airplane. The Model 700 airplane is low-wing, pressurized, turbofan-powered executive jet airplane with seating for two crewmembers and up to 12 passengers. This airplane will have two Honeywell AS907-2-1S turbofan engines and a maximum takeoff weight of 38,514 pounds. Type Certification Basis Under the provisions of Title 14, Code of Federal Regulations (14 CFR) 21.17, Textron must show that the Model 700 airplane meets the applicable provisions of part 25, as amended by Amendments 25-1 through 25-139, 25-141, and 25-143. If the Administrator finds that the applicable airworthiness regulations (i.e., 14 CFR part 25) do not contain adequate or appropriate safety standards for the Textron Model 700 airplane 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 novel or unusual design feature, these special conditions would also apply to the other model under Sec. 21.101. In addition to the applicable airworthiness regulations and special conditions, the Model 700 airplane 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. 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 Model 700 airplane will incorporate the following novel or unusual design feature: An electronic flight-control system that provides control through pilot inputs to the flight computer. Discussion The roll control system uses both ailerons and flight spoilers. The aileron control system is a fully mechanical system, and the flight spoilers are fly-by-wire. Section 25.349 specifies roll maneuver load conditions that are based on aileron deflection, rather than control- wheel deflection. By specifying the load conditions in terms of aileron deflection, the current requirement does not address electronic flight controls that cause nonlinearities and other loads caused by spoilers. Since this type of system affects flight loads, and therefore the structural capability of the airplane, special conditions are necessary to address these effects. These special conditions differ from current requirements in that they require the actuation of the cockpit roll control, as opposed to the aileron itself, to perform the roll maneuver. Also, these special conditions require an additional load condition at V A , in which the cockpit roll control is returned to neutral following the initial roll input. These special conditions differ from similar special conditions applied to previous similar technologies. These special conditions are limited to the roll axis only, whereas previous special conditions also included the pitch and yaw axes. Special conditions are no longer necessary for the pitch or yaw axes because Amendment 25-91 takes into account the effects of an electronic flight-control system in those axes (Sec. 25.331 for pitch and Sec. 25.351 for yaw). 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. Applicability As discussed above, these special conditions are applicable to the Textron Model 700 airplane. Should Textron apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, these special conditions would apply to that model as well. Conclusion This action affects only one novel or unusual design feature on one model of airplane. It is not a rule of general applicability. The substance of these special conditions has been subjected to the notice and comment period in several prior instances 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, because a delay would significantly affect the certification of the airplane, the FAA has determined that prior public notice and comment are unnecessary and impracticable, and good cause exists for adopting these special conditions upon publication in the Federal Register. The FAA is requesting comments to allow interested persons to submit views that [[Page 21683]] may not have been submitted in response to the prior opportunities for comment described above. List of Subjects in 14 CFR Part 25 Aircraft, Aviation safety, Reporting and recordkeeping requirements. The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. The Special Conditions 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 Textron Aviation Inc. Model 700 airplanes. In lieu of compliance with Sec. 25.349(a), the following conditions, speeds, and cockpit roll control motions (except as the motions may be limited by pilot effort) must be considered in combination with an airplane load factor of zero and of two-thirds of the positive maneuvering factor used in design. In determining the resulting control-surface deflections, the torsional flexibility of the wing must be considered in accordance with Sec. 25.301(b): 1. Conditions corresponding to steady rolling velocities must be investigated. In addition, conditions corresponding to maximum angular acceleration must be investigated for airplanes with engines or other weight concentrations outboard of the fuselage. For the angular- acceleration conditions, zero rolling velocity may be assumed in the absence of a rational time history investigation of the maneuver. 2. At VA , sudden movement of the cockpit roll control up to the limit is applied. The position of the cockpit roll control must be maintained until a steady roll rate is achieved, and then must be returned suddenly to the neutral position. 3. At VC , the cockpit roll control must be moved suddenly and maintained so as to achieve a roll rate not less than that obtained in paragraph 2. 4. At VD , the cockpit roll control must be moved suddenly and maintained so as to achieve a roll rate not less than one third of that obtained in paragraph 2. Issued in Renton, Washington, on April 24, 2017. Michael Kaszycki, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-09440 Filed 5-9-17; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 82, No. 89 / Wednesday, May 10, 2017 / Rules and Regulations 21681
electrical power sources inoperative, as requirements of these special DEPARTMENT OF TRANSPORTATION
prescribed by paragraphs 1.a. and 1.b., conditions, and if reaching a suitable
below. For purposes of these special runway for landing is beyond the Federal Aviation Administration
conditions, normal sources of electrical capacity of the battery systems, then the
power generation do not include any APU must be able to be started under 14 CFR Part 25
alternate power sources such as the any foreseeable flight condition prior to [Docket No. FAA–2017–0215; Special
battery, ram air turbine, or independent the depletion of the battery or the Conditions No. 25–669–SC]
power systems such as the flight control restoration of normal electrical power,
permanent magnet generating system. In whichever occurs first. Flight test must Special Conditions: Textron Aviation
showing capability for continued safe demonstrate this capability at the most Inc. Model 700 Airplane; Design Roll
flight and landing, the applicant must Maneuver Condition
critical condition.
account for systems capability, effects
on crew workload and operating a. The applicant must show that the AGENCY: Federal Aviation
conditions, and the physiological needs APU will provide adequate electrical Administration (FAA), DOT.
of the flightcrew and passengers for the power for continued safe flight and ACTION: Final special conditions; request
longest diversion time for which the landing. for comments.
applicant is seeking approval. b. The operating limitations section of
a. In showing compliance with this SUMMARY: These special conditions are
the airplane flight manual (AFM) must issued for the Textron Aviation Inc.
requirement, the applicant must account incorporate non-normal procedures that
for common-cause failures, cascading (Textron) Model 700 airplane. This
direct the pilot to take appropriate airplane will have a novel or unusual
failures, and zonal physical threats.
b. The applicant may consider the actions to activate the APU after loss of design feature when compared to the
ability to restore operation of portions of normal engine-driven generated state of technology envisioned in the
the electrical power generation and electrical power. airworthiness standards for transport-
distribution system if it can be shown 5. As part of showing compliance category airplanes. This design feature
that unrecoverable loss of those portions with these special conditions, the tests is an electronic flight-control system
of the system is extremely improbable. to demonstrate loss of all normal that provides control through pilot
The design must provide an alternative electrical power must also take into inputs to the flight computer. The
source of electrical power for the time account the following: applicable airworthiness regulations do
required to restore the minimum not contain adequate or appropriate
a. The assumption that the failure safety standards for this design feature.
electrical power generation capability
condition occurs during night These special conditions contain the
required for safe flight and landing. The
instrument meteorological conditions additional safety standards that the
applicant may exclude unrecoverable
loss of all engines when showing (IMC) at the most critical phase of the Administrator considers necessary to
compliance with this requirement. flight, relative to the worst possible establish a level of safety equivalent to
2. Regardless of any electrical electrical power distribution and that established by the existing
generation and distribution system equipment-loads-demand condition. airworthiness standards.
recovery capability shown under b. After the un-restorable loss of DATES: This action is effective on
paragraph 1 of these special conditions, normal engine generator power, the Textron on May 10, 2017. We must
sufficient electrical system capability airplane engine restart capability is receive your comments by June 26,
must be provided to: provided and operations continued in 2017.
a. Allow time to descend, with all IMC.
engines inoperative, at the speed that ADDRESSES: Send comments identified
provides the best glide distance, from c. The airplane is demonstrated to be by docket number FAA–2017–0215
the maximum operating altitude to the capable of continued safe flight and using any of the following methods:
top of the engine restart envelope, and landing. The length of time must be • Federal eRegulations Portal: Go to
b. Subsequently allow multiple start computed based on the maximum http://www.regulations.gov/ and follow
attempts of the engines and auxiliary diversion time capability for which the the online instructions for sending your
power unit (APU). The design must airplane is being certified. The applicant comments electronically.
provide this capability in addition to the must account for airspeed reductions • Mail: Send comments to Docket
electrical capability required by existing resulting from the associated failure or Operations, M–30, U.S. Department of
part 25 requirements related to failures. Transportation (DOT), 1200 New Jersey
operation with all engines inoperative. Avenue SE., Room W12–140, West
d. The airplane must provide Building Ground Floor, Washington, DC
3. The airplane emergency electrical
adequate indication of loss of normal 20590–0001.
power system must be designed to
supply:
electrical power to direct the pilot to the • Hand Delivery or Courier: Take
a. Electrical power required for non-normal procedures, and the comments to Docket Operations in
immediate safety, which must continue operating limitations section of the AFM Room W12–140 of the West Building
to operate without the need for crew must incorporate non-normal Ground Floor at 1200 New Jersey
action following the loss of the normal procedures that will direct the pilot to Avenue SE., Washington, DC, between 9
electrical power, for a duration take appropriate actions. a.m. and 5 p.m., Monday through
sufficient to allow reconfiguration to Issued in Renton, Washington, on May 2, Friday, except Federal holidays.
jstallworth on DSK7TPTVN1PROD with RULES
provide a non-time-limited source of 2017. • Fax: Fax comments to Docket
electrical power. Operations at 202–493–2251.
Michael Kaszycki,
b. Electrical power required for Privacy: The FAA will post all
continued safe flight and landing for the Assistant Manager, Transport Airplane comments it receives, without change,
Directorate, Aircraft Certification Service. to http://www.regulations.gov/,
maximum diversion time.
4. If the applicant uses APU-generated [FR Doc. 2017–09441 Filed 5–9–17; 8:45 am] including any personal information the
electrical power to satisfy the BILLING CODE 4910–13–P commenter provides. Using the search
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![Federal Register / Vol. 82, No. 89 / Wednesday, May 10, 2017 / Rules and Regulations 21683
may not have been submitted in DEPARTMENT OF TRANSPORTATION information. The street address for the
response to the prior opportunities for Docket Operations Office (phone: 800–
comment described above. Federal Aviation Administration 647–5527) is U.S. Department of
Transportation, Docket Operations
List of Subjects in 14 CFR Part 25 14 CFR Part 39 Office, M–30, West Building Ground
Aircraft, Aviation safety, Reporting [Docket No. FAA–2016–6436; Directorate Floor, Room W12–140, 1200 New Jersey
and recordkeeping requirements. Identifier 2015–SW–037–AD; Amendment Avenue SE., Washington, DC 20590.
39–18869; AD 2017–09–07]
The authority citation for these FOR FURTHER INFORMATION CONTACT:
special conditions is as follows: RIN 2120–AA64 George Schwab, Aviation Safety
Authority: 49 U.S.C. 106(g), 40113, 44701,
Engineer, Safety Management Group,
Airworthiness Directives; Airbus Rotorcraft Directorate, FAA, 10101
44702, 44704.
Helicopters Deutschland GmbH Hillwood Pkwy., Fort Worth, TX 76177;
The Special Conditions Helicopters telephone (817) 222–5110; email
AGENCY: Federal Aviation george.schwab@faa.gov.
Accordingly, pursuant to the
authority delegated to me by the Administration (FAA), DOT. SUPPLEMENTARY INFORMATION:
Administrator, the following special ACTION: Final rule.
conditions are issued as part of the type Discussion
certification basis for Textron Aviation SUMMARY: We are adopting a new
airworthiness directive (AD) for Airbus On December 7, 2016, at 81 FR 88143,
Inc. Model 700 airplanes. the Federal Register published our
Helicopters Deutschland GmbH (Airbus
In lieu of compliance with § 25.349(a), Helicopters) Model MBB–BK117 C–2 notice of proposed rulemaking (NPRM),
the following conditions, speeds, and helicopters. This AD requires inspecting which proposed to amend 14 CFR part
cockpit roll control motions (except as the pilot collective wiring harness and 39 by adding an AD that would apply
the motions may be limited by pilot was prompted by a report that the heat- to Airbus Helicopters MBB–BK 117 C–
effort) must be considered in shrinkable sleeve prevented the twist 2 helicopters, serial numbers 9004
combination with an airplane load grip on the collective from being fully through 9708. The NPRM proposed to
factor of zero and of two-thirds of the engaged during a flight test. The actions require visually inspecting the pilot
positive maneuvering factor used in of this AD are intended to prevent an collective wiring harness for proper
design. In determining the resulting unsafe condition on these products. installation of the heat-shrinkable and
control-surface deflections, the torsional transparent sleeves. The proposed
flexibility of the wing must be DATES: This AD is effective June 14,
requirements were intended to detect an
considered in accordance with 2017.
incorrectly installed heat-shrinkable
§ 25.301(b): The Director of the Federal Register
sleeve on the collective lever wiring
approved the incorporation by reference
1. Conditions corresponding to steady harness, which if not corrected, could
of a certain document listed in this AD
rolling velocities must be investigated. result in chafing of the wiring and
as of June 14, 2017.
In addition, conditions corresponding to subsequent failure of the hoist cable
ADDRESSES: For service information cutter or emergency landing gear
maximum angular acceleration must be
identified in this final rule, contact flotation systems.
investigated for airplanes with engines
Airbus Helicopters, 2701 N. Forum
or other weight concentrations outboard The NPRM was prompted by AD No.
Drive, Grand Prairie, TX 75052;
of the fuselage. For the angular- 2015–0144, dated July 21, 2015, issued
telephone (972) 641–0000 or (800) 232–
acceleration conditions, zero rolling by EASA, which is the Technical Agent
0323; fax (972) 641–3775; or at https://
velocity may be assumed in the absence for the Member States of the European
www.airbushelicopters.com/techpub/
of a rational time history investigation Union, to correct an unsafe condition
FO/scripts/myFO_login.php. You may
of the maneuver. for Airbus Helicopters Model MBB–
review the referenced service
2. At VA, sudden movement of the information at the FAA, Office of the BK117 C–2 helicopters, up to serial
cockpit roll control up to the limit is Regional Counsel, Southwest Region, number 9708. EASA advises that,
applied. The position of the cockpit roll 10101 Hillwood Pkwy., Room 6N–321, during a flight test, the pilot could not
control must be maintained until a Fort Worth, TX 76177. It is also fully engage a twist grip on a Model
steady roll rate is achieved, and then available on the Internet at http:// MBB–BK117 C–2 helicopter. According
must be returned suddenly to the www.regulations.gov by searching for to EASA, further investigation found a
neutral position. and locating Docket No. FAA–2016– transparent sleeve on the collective
6436. lever wiring harness damaged because
3. At VC, the cockpit roll control must
of incorrect installation of the heat-
be moved suddenly and maintained so Examining the AD Docket shrinkable sleeve. This condition, if not
as to achieve a roll rate not less than
You may examine the AD docket on detected and corrected, could result in
that obtained in paragraph 2.
the Internet at http:// chafing of the harness, leading to the
4. At VD, the cockpit roll control must malfunction of the affected systems,
www.regulations.gov by searching for
be moved suddenly and maintained so EASA advises. EASA consequently
and locating Docket No. FAA–2016–
as to achieve a roll rate not less than one requires a one-time inspection of the
6436; or in person at the Docket
third of that obtained in paragraph 2. heat-shrinkable and transparent sleeves
Operations Office between 9 a.m. and 5
jstallworth on DSK7TPTVN1PROD with RULES
Issued in Renton, Washington, on April 24, p.m., Monday through Friday, except installed on the collective lever wiring
2017. Federal holidays. The AD docket harness.
Michael Kaszycki, contains this AD, the European Aviation Comments
Assistant Manager, Transport Airplane Safety Agency (EASA) AD, any
Directorate, Aircraft Certification Service. incorporated-by-reference service We gave the public the opportunity to
[FR Doc. 2017–09440 Filed 5–9–17; 8:45 am] information, the economic evaluation, participate in developing this AD, but
BILLING CODE 4910–13–P any comments received, and other we received no comments on the NPRM.
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Document Created: 2017-05-10 00:00:53
Document Modified: 2017-05-10 00:00:53
| 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 | This action is effective on Textron on May 10, 2017. We must receive your comments by June 26, 2017. | |
| Contact | Greg Schneider, FAA, Airframe and Cabin Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW., Renton, Washington 98057- 3356; telephone 425-227-2116; facsimile 425-227-1320. | |
| FR Citation | 82 FR 21681 | |
| CFR Associated | Aircraft; Aviation Safety and Reporting and Recordkeeping Requirements |
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