Special Conditions: Airbus Model A330-841 and A330-941 (A330neo) Airplanes; Electronic Flight-Control System; Lateral-Directional and Longitudinal Stability, and Low-Energy Awareness, 466-468 [2017-28453]

Download as PDF 466 Federal Register / Vol. 83, No. 3 / Thursday, January 4, 2018 / Rules and Regulations battery charge state if the battery’s function is required for safe operation of the airplane. Note: A battery system consists of the battery and any protective, monitoring, and alerting circuitry or hardware inside or outside of the battery. It also includes vents (where necessary) and packaging. For the purpose of these special conditions, a ‘‘battery’’ and ‘‘battery system’’ are referred to as a battery. Issued in Renton, Washington, on December 28, 2017. Suzanne Masterson, Acting Manager, Transport Standards Branch, Policy and Innovation Division, Aircraft Certification Service. [FR Doc. 2017–28454 Filed 1–3–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 25 [Docket No. FAA–2017–0483; Special Conditions No. 25–708–SC] Special Conditions: Airbus Model A330–841 and A330–941 (A330neo) Airplanes; Electronic Flight-Control System; Lateral-Directional and Longitudinal Stability, and Low-Energy Awareness Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions; request for comments. AGENCY: These special conditions are issued for the Airbus Model A330–841 and A330–941 (A330neo) airplanes. These airplanes 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 low-energy awareness and directional stability with respect to electronic flight-control systems (EFCS). 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 Airbus on January 4, 2018. Send your comments by February 20, 2018. ADDRESSES: Send comments identified by docket number FAA–2017–0483 using any of the following methods: • Federal eRegulations Portal: Go to http://www.regulations.gov/and follow rmajette on DSKBCKNHB2PROD with RULES SUMMARY: VerDate Sep<11>2014 14:53 Jan 03, 2018 Jkt 244001 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 function of the docket website, 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: Paul Giesman, FAA, Airplane and Flight Crew Interface, AIR–671, Transport Standards Branch, Policy and Innovation Division, Aircraft Certification Service, 1601 Lind Avenue SW, Renton, Washington 98057–3356; telephone 425–227–2790; facsimile 425–227–1320. SUPPLEMENTARY INFORMATION: The substance of these special conditions has been published in the Federal Register for public comment in several prior instances with no substantive comments received. The FAA therefore finds it unnecessary to delay the effective date and finds it unnecessary to delay the effective date and finds that 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 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 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 January 20, 2015, Airbus applied for an amendment to Type Certificate No. A46NM to include the new Model A330–841 (A330–800neo) and A330– 941 (A330–900neo) airplanes, collectively marketed as Model A330neo airplanes. These airplanes, which are derivatives of the Model A330–200 and A330–300 airplanes currently approved under Type Certificate No. A46NM, are wide-body, jet-engine airplanes with a maximum takeoff weight of 533,519 pounds and a passenger capacity of 257 (A330–841); and a maximum takeoff weight of 535,503 pounds and a passenger capacity of 287 (A330–941). Type Certification Basis Under the provisions of title 14, Code of Federal Regulations (14 CFR) 21.101, Airbus must show that the Model A330neo airplanes meet the applicable provisions of the regulations listed in Type Certificate No. A46NM, or the applicable regulations in effect on the date of application for the change, except for earlier amendments as agreed upon by the FAA. If the Administrator finds that the applicable airworthiness regulations (i.e., 14 CFR part 25) do not contain adequate or appropriate safety standards for Model A330neo airplanes because of a novel or unusual design feature, special conditions are prescribed under the provisions of § 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, or should any other model already included on the same type certificate be modified to incorporate the same novel or unusual design feature, these special conditions would also apply to the other model under § 21.101. In addition to the applicable airworthiness regulations and special conditions, the Airbus Model A330neo airplanes must comply with the fuelvent and exhaust-emission requirements of 14 CFR part 34 and the noise- E:\FR\FM\04JAR1.SGM 04JAR1 Federal Register / Vol. 83, No. 3 / Thursday, January 4, 2018 / Rules and Regulations certification requirements of 14 CFR part 36. The FAA issues special conditions, as defined in 14 CFR 11.19, in accordance with § 11.38, and they become part of the type certification basis under § 21.101. rmajette on DSKBCKNHB2PROD with RULES Novel or Unusual Design Features The Airbus Model A330neo airplanes will incorporate the following novel or unusual design features: Low-energy awareness and directional stability functions of the EFCS, which are not sufficiently addressed in Special Conditions (SC) No. 25–ANM–77, ‘‘Airbus Industrie Model A330 Series Airplanes,’’ Discussion section item 11, Flight Characteristics. Discussion An initial review of the Model A330 and A340 airplanes’ SC 25–ANM–77, Discussion section item 11, and subsequent certifications of the Model A340–500/600, A380, and A350 airplanes, revealed that SC 25–ANM–77, item 11, does not address low-energy awareness, nor does it provide similar detail as to the demonstration of directional stability, as has become the standard in later special conditions for Airbus airplanes. These special conditions, for the Model A330–841 and –941 airplanes, replace the current item 11b and c in SC 25–ANM–77. In addition, these special conditions, in conjunction with the application of part 25, subpart B, at Amendment 25–108 for 1 g stall speeds; and § 25.177(a) and (b) at Amendment 25–135; are intended to parallel the requirements provided in type certifications of Model A340–500 and –600, A380, and A350 airplanes. In the absence of positive lateral stability, the curve of lateral controlsurface deflections against sideslip angle should be in a conventional sense and reasonably in harmony with rudder deflection during steady-heading sideslip maneuvers. Because conventional relationships between stick forces and control-surface displacements do not apply to the loadfactor-command flight-control system on the Model A330–841 and –941 airplanes, longitudinal stability characteristics should be evaluated by assessing the airplane handling qualities during simulator and flight-test maneuvers appropriate to operation of the airplane. This may be accomplished by using the Handling Qualities Rating Method presented in Advisory Circular 25–7C, ‘‘Flight Test Guide for Certification of Transport Category Airplanes,’’ Appendix 5, or an acceptable alternative method proposed VerDate Sep<11>2014 14:53 Jan 03, 2018 Jkt 244001 by the Airbus. Important considerations are as follows: 1. Adequate speed control without excessive pilot workload, 2. Acceptable high- and low-speed protection, and 3. Provision for adequate cues to the pilot of significant speed excursions beyond VMO/MMO, and low-speedawareness flight conditions. The airplane should provide adequate awareness cues to the pilot of a lowenergy (low-speed/low-thrust/lowheight) state to ensure that the airplane retains sufficient energy to recover when flight-control laws provide neutral longitudinal stability significantly below the normal operating speeds. This may be accomplished as follows: 1. Adequate low-speed/low-thrust cues at low altitude may be provided by a strong positive-static-stability force gradient (1 pound per 6 knots applied through the sidestick), or, 2. The low-energy awareness may be provided by an appropriate warning with the following characteristics: a. It should be unique, unambiguous, and unmistakable. b. It should be active at appropriate altitudes and in appropriate configurations (i.e., at low altitude, in the approach and landing configurations). c. It should be sufficiently timely to allow recovery to a stabilized flight condition inside the normal flight envelope while maintaining the desired flight path, and without entering the flight controls angle-of-attack protection mode. d. It should not be triggered during normal operation, including operation in moderate turbulence for recommended maneuvers at recommended speeds. e. The system should not allow the pilot to cancel the warning, or the lowenergy awareness function, other than by achieving a higher energy state. f. The various warnings should have an adequate hierarchy of alert so that the pilot is not confused and led to take inappropriate recovery action if multiple warnings occur at the same time. 3. Global energy awareness and nonnuisance of low-energy cues should be evaluated by simulator and flight tests in the whole take-off and landing altitude range for which certification is requested. This would include all relevant combinations of weight, centerof-gravity position, configuration, airbrakes position, and available thrust, including reduced and derated take-off thrust operations and engine-failure cases. A sufficient number of tests should be conducted, allowing the level PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 467 of energy awareness and the effects of energy-management errors to be assessed. 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 Airbus Model A330–841 and A330–941 (A330neo) airplanes. Should Airbus 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 certain novel or unusual design features on one model series of airplane. It is not a rule of general applicability. 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 Airbus Model A330–841 and A330–941 (A330neo) airplanes. In lieu of the requirements of §§ 25.171, 25.173, 25.175, and 25.177(c), the following special conditions apply: 1. The airplane must be shown to have suitable static lateral, directional, and longitudinal stability in any condition normally encountered in service, including the effects of atmospheric disturbance. The showing of suitable static lateral, directional, and longitudinal stability must be based on the airplane handling qualities, including pilot workload and pilot compensation, for specific test procedures during the flight-test evaluations. 2. The airplane must provide to the pilot adequate awareness of a lowenergy (low-speed/low-thrust/lowheight) state when fitted with flightcontrol laws presenting neutral longitudinal stability significantly below the normal operating speeds. ‘‘Adequate awareness’’ means that warning information must be provided ■ E:\FR\FM\04JAR1.SGM 04JAR1 468 Federal Register / Vol. 83, No. 3 / Thursday, January 4, 2018 / Rules and Regulations to alert the flightcrew of unsafe operating conditions, and to enable them to take appropriate corrective action. 3. In straight, steady sideslips over the range of sideslip angles appropriate to the operation of the airplane, but not less than those obtained with one-half of the available rudder-control movement (but not exceeding a rudder-control force of 180 pounds), rudder-control movements and forces must be substantially proportional to the angle of sideslip in a stable sense; and the factor of proportionality must lie between limits found necessary for safe operation. This requirement must be met for the configurations and speeds specified in § 25.177(a). Issued in Renton, Washington, on December 28, 2017. Suzanne Masterson, Acting Manager, Transport Standards Branch, Policy and Innovation Division, Aircraft Certification Service. [FR Doc. 2017–28453 Filed 1–3–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF ENERGY Federal Energy Regulatory Commission 18 CFR Part 381 [Docket No. RM18–3–000] Annual Update of Filing Fees Federal Energy Regulatory Commission, DOE. AGENCY: Final rule; annual update of Commission filing fees. ACTION: In accordance with the Commission regulations, the Commission issues this update of its filing fees. This notice provides the yearly update using data in the Commission’s Financial System to calculate the new fees. The purpose of updating is to adjust the fees on the basis of the Commission’s costs for Fiscal Year 2017. DATES: Effective Date: February 5, 2018. FOR FURTHER INFORMATION CONTACT: VuHang Nguyen, Office of the Executive Director, Federal Energy Regulatory Commission, 888 First Street NE, Room 42–65, Washington, DC 20426, 202– 502–8892. SUPPLEMENTARY INFORMATION: Document Availability: In addition to publishing the full text of this document in the Federal Register, the Commission provides all interested persons an opportunity to view and/or print the contents of this document via the internet through FERC’s Home Page (http://www.ferc.gov) and in FERC’s Public Reference Room during normal business hours (8:30 a.m. to 5:00 p.m. Eastern time) at 888 First Street NE, Room 2A, Washington, DC 20426. From FERC’s website on the internet, this information is available in the eLibrary. The full text of this document is available on eLibrary in PDF and Microsoft Word format for viewing, printing, and/or downloading. To access this document in eLibrary, type the docket number excluding the last three SUMMARY: digits of this document in the docket number field and follow other directions on the search page. User assistance is available for eLibrary and other aspects of FERC’s website during normal business hours. For assistance, contact FERC Online Support at FERCOnlineSupport@ ferc.gov or toll free at (866) 208–3676, or for TTY, contact (202) 502–8659. Annual Update of Filing Fees (Issued December 28, 2017) The Federal Energy Regulatory Commission (Commission) is issuing this notice to update filing fees that the Commission assesses for specific services and benefits provided to identifiable beneficiaries. Pursuant to 18 CFR 381.104, the Commission is establishing updated fees on the basis of the Commission’s Fiscal Year 2017 costs. The adjusted fees announced in this notice are effective February 5, 2018. The Commission has determined, with the concurrence of the Administrator of the Office of Information and Regulatory Affairs of the Office of Management and Budget, that this final rule is not a major rule within the meaning of section 251 of Subtitle E of Small Business Regulatory Enforcement Fairness Act, 5 U.S.C. 804(2). The Commission is submitting this final rule to both houses of the United States Congress and to the Comptroller General of the United States. The new fee schedule is as follows: Fees Applicable to the Natural Gas Policy Act 1. Petitions for rate approval pursuant to 18 CFR 284.123(b)(2). (18 CFR 381.403) ........................................................................ $13,500 Fees Applicable to General Activities 1. Petition for issuance of a declaratory order (except under Part I of the Federal Power Act). (18 CFR 381.302(a)) .................... 2. Review of a Department of Energy remedial order: Amount in controversy $0–9,999. (18 CFR 381.303(b)) ............................................................................................................................................ $10,000–29,999. (18 CFR 381.303(b)) ................................................................................................................................. $30,000 or more. (18 CFR 381.303(a)) ................................................................................................................................ 3. Review of a Department of Energy denial of adjustment: Amount in controversy $0–9,999. (18 CFR 381.304(b)) ............................................................................................................................................ $10,000–29,999. (18 CFR 381.304(b)) ................................................................................................................................. $30,000 or more. (18 CFR 381.304(a)) ................................................................................................................................ 4. Written legal interpretations by the Office of General Counsel. (18 CFR 381.305(a)) .................................................................. 27,130 100 600 39,610 100 600 20,770 7,780 rmajette on DSKBCKNHB2PROD with RULES Fees Applicable to Natural Gas Pipelines 1. Pipeline certificate applications pursuant to 18 CFR 284.224. (18 CFR 381.207(b)) .................................................................... * 1,000 Fees Applicable to Cogenerators and Small Power Producers 1. Certification of qualifying status as a small power production facility. (18 CFR 381.505(a)) ......................................................... 2. Certification of qualifying status as a cogeneration facility. (18 CFR 381.505(a)) ......................................................................... * This fee has not been changed. VerDate Sep<11>2014 14:53 Jan 03, 2018 Jkt 244001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\04JAR1.SGM 04JAR1 23,330 26,410

Agencies

[Federal Register Volume 83, Number 3 (Thursday, January 4, 2018)]
[Rules and Regulations]
[Pages 466-468]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-28453]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 25

[Docket No. FAA-2017-0483; Special Conditions No. 25-708-SC]


Special Conditions: Airbus Model A330-841 and A330-941 (A330neo) 
Airplanes; Electronic Flight-Control System; Lateral-Directional and 
Longitudinal Stability, and Low-Energy Awareness

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions; request for comments.

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

SUMMARY: These special conditions are issued for the Airbus Model A330-
841 and A330-941 (A330neo) airplanes. These airplanes 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 low-energy awareness and directional 
stability with respect to electronic flight-control systems (EFCS). 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 Airbus on January 4, 2018. Send your 
comments by February 20, 2018.

ADDRESSES: Send comments identified by docket number FAA-2017-0483 
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 function of the 
docket website, 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: Paul Giesman, FAA, Airplane and Flight 
Crew Interface, AIR-671, Transport Standards Branch, Policy and 
Innovation Division, Aircraft Certification Service, 1601 Lind Avenue 
SW, Renton, Washington 98057-3356; telephone 425-227-2790; facsimile 
425-227-1320.

SUPPLEMENTARY INFORMATION: The substance of these special conditions 
has been published in the Federal Register for public comment in 
several prior instances with no substantive comments received. The FAA 
therefore finds it unnecessary to delay the effective date and finds it 
unnecessary to delay the effective date and finds that 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 January 20, 2015, Airbus applied for an amendment to Type 
Certificate No. A46NM to include the new Model A330-841 (A330-800neo) 
and A330-941 (A330-900neo) airplanes, collectively marketed as Model 
A330neo airplanes. These airplanes, which are derivatives of the Model 
A330-200 and A330-300 airplanes currently approved under Type 
Certificate No. A46NM, are wide-body, jet-engine airplanes with a 
maximum takeoff weight of 533,519 pounds and a passenger capacity of 
257 (A330-841); and a maximum takeoff weight of 535,503 pounds and a 
passenger capacity of 287 (A330-941).

Type Certification Basis

    Under the provisions of title 14, Code of Federal Regulations (14 
CFR) 21.101, Airbus must show that the Model A330neo airplanes meet the 
applicable provisions of the regulations listed in Type Certificate No. 
A46NM, or the applicable regulations in effect on the date of 
application for the change, except for earlier amendments as agreed 
upon by the FAA.
    If the Administrator finds that the applicable airworthiness 
regulations (i.e., 14 CFR part 25) do not contain adequate or 
appropriate safety standards for Model A330neo airplanes 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, or should any other model already included on 
the same type certificate be modified to incorporate 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 Airbus Model A330neo airplanes must comply with the 
fuel-vent and exhaust-emission requirements of 14 CFR part 34 and the 
noise-

[[Page 467]]

certification requirements of 14 CFR part 36.
    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.

Novel or Unusual Design Features

    The Airbus Model A330neo airplanes will incorporate the following 
novel or unusual design features:
    Low-energy awareness and directional stability functions of the 
EFCS, which are not sufficiently addressed in Special Conditions (SC) 
No. 25-ANM-77, ``Airbus Industrie Model A330 Series Airplanes,'' 
Discussion section item 11, Flight Characteristics.

Discussion

    An initial review of the Model A330 and A340 airplanes' SC 25-ANM-
77, Discussion section item 11, and subsequent certifications of the 
Model A340-500/600, A380, and A350 airplanes, revealed that SC 25-ANM-
77, item 11, does not address low-energy awareness, nor does it provide 
similar detail as to the demonstration of directional stability, as has 
become the standard in later special conditions for Airbus airplanes.
    These special conditions, for the Model A330-841 and -941 
airplanes, replace the current item 11b and c in SC 25-ANM-77. In 
addition, these special conditions, in conjunction with the application 
of part 25, subpart B, at Amendment 25-108 for 1 g stall speeds; and 
Sec.  25.177(a) and (b) at Amendment 25-135; are intended to parallel 
the requirements provided in type certifications of Model A340-500 and 
-600, A380, and A350 airplanes.
    In the absence of positive lateral stability, the curve of lateral 
control-surface deflections against sideslip angle should be in a 
conventional sense and reasonably in harmony with rudder deflection 
during steady-heading sideslip maneuvers.
    Because conventional relationships between stick forces and 
control-surface displacements do not apply to the load-factor-command 
flight-control system on the Model A330-841 and -941 airplanes, 
longitudinal stability characteristics should be evaluated by assessing 
the airplane handling qualities during simulator and flight-test 
maneuvers appropriate to operation of the airplane. This may be 
accomplished by using the Handling Qualities Rating Method presented in 
Advisory Circular 25-7C, ``Flight Test Guide for Certification of 
Transport Category Airplanes,'' Appendix 5, or an acceptable 
alternative method proposed by the Airbus. Important considerations are 
as follows:
    1. Adequate speed control without excessive pilot workload,
    2. Acceptable high- and low-speed protection, and
    3. Provision for adequate cues to the pilot of significant speed 
excursions beyond VMO/MMO, and low-speed-
awareness flight conditions.
    The airplane should provide adequate awareness cues to the pilot of 
a low-energy (low-speed/low-thrust/low-height) state to ensure that the 
airplane retains sufficient energy to recover when flight-control laws 
provide neutral longitudinal stability significantly below the normal 
operating speeds. This may be accomplished as follows:
    1. Adequate low-speed/low-thrust cues at low altitude may be 
provided by a strong positive-static-stability force gradient (1 pound 
per 6 knots applied through the sidestick), or,
    2. The low-energy awareness may be provided by an appropriate 
warning with the following characteristics:
    a. It should be unique, unambiguous, and unmistakable.
    b. It should be active at appropriate altitudes and in appropriate 
configurations (i.e., at low altitude, in the approach and landing 
configurations).
    c. It should be sufficiently timely to allow recovery to a 
stabilized flight condition inside the normal flight envelope while 
maintaining the desired flight path, and without entering the flight 
controls angle-of-attack protection mode.
    d. It should not be triggered during normal operation, including 
operation in moderate turbulence for recommended maneuvers at 
recommended speeds.
    e. The system should not allow the pilot to cancel the warning, or 
the low-energy awareness function, other than by achieving a higher 
energy state.
    f. The various warnings should have an adequate hierarchy of alert 
so that the pilot is not confused and led to take inappropriate 
recovery action if multiple warnings occur at the same time.
    3. Global energy awareness and non-nuisance of low-energy cues 
should be evaluated by simulator and flight tests in the whole take-off 
and landing altitude range for which certification is requested. This 
would include all relevant combinations of weight, center-of-gravity 
position, configuration, airbrakes position, and available thrust, 
including reduced and derated take-off thrust operations and engine-
failure cases. A sufficient number of tests should be conducted, 
allowing the level of energy awareness and the effects of energy-
management errors to be assessed.
    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 
Airbus Model A330-841 and A330-941 (A330neo) airplanes. Should Airbus 
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 certain novel or unusual design features 
on one model series of airplane. It is not a rule of general 
applicability.

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

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 Airbus Model A330-841 and A330-941 
(A330neo) airplanes.
    In lieu of the requirements of Sec. Sec.  25.171, 25.173, 25.175, 
and 25.177(c), the following special conditions apply:
    1. The airplane must be shown to have suitable static lateral, 
directional, and longitudinal stability in any condition normally 
encountered in service, including the effects of atmospheric 
disturbance. The showing of suitable static lateral, directional, and 
longitudinal stability must be based on the airplane handling 
qualities, including pilot workload and pilot compensation, for 
specific test procedures during the flight-test evaluations.
    2. The airplane must provide to the pilot adequate awareness of a 
low-energy (low-speed/low-thrust/low-height) state when fitted with 
flight-control laws presenting neutral longitudinal stability 
significantly below the normal operating speeds. ``Adequate awareness'' 
means that warning information must be provided

[[Page 468]]

to alert the flightcrew of unsafe operating conditions, and to enable 
them to take appropriate corrective action.
    3. In straight, steady sideslips over the range of sideslip angles 
appropriate to the operation of the airplane, but not less than those 
obtained with one-half of the available rudder-control movement (but 
not exceeding a rudder-control force of 180 pounds), rudder-control 
movements and forces must be substantially proportional to the angle of 
sideslip in a stable sense; and the factor of proportionality must lie 
between limits found necessary for safe operation. This requirement 
must be met for the configurations and speeds specified in Sec.  
25.177(a).

    Issued in Renton, Washington, on December 28, 2017.
Suzanne Masterson,
Acting Manager, Transport Standards Branch, Policy and Innovation 
Division, Aircraft Certification Service.
[FR Doc. 2017-28453 Filed 1-3-18; 8:45 am]
 BILLING CODE 4910-13-P