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 

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 § 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 noiseVerDate Sep<11>2014 14:53 Jan 03, 2018 Jkt 244001 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 E:\FR\FM\04JAR1.SGM 04JAR1

rmajette on DSKBCKNHB2PROD with RULES
Federal Register / Vol. 83, No. 3 / Thursday, January 4, 2018 / Rules and Regulations 467 

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. 

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 

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 

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 


rmajette on DSKBCKNHB2PROD with RULES
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 

AGENCY: Federal Energy Regulatory 

Commission, DOE. 

ACTION: Final rule; annual update of 

Commission filing fees. 

SUMMARY: 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 

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)) .................... 27,130 

2. Review of a Department of Energy remedial order: 

Amount in controversy 

$0–9,999. (18 CFR 381.303(b)) ............................................................................................................................................ 100 

$10,000–29,999. (18 CFR 381.303(b)) ................................................................................................................................. 600 

$30,000 or more. (18 CFR 381.303(a)) ................................................................................................................................ 39,610 

3. Review of a Department of Energy denial of adjustment: 

Amount in controversy 

$0–9,999. (18 CFR 381.304(b)) ............................................................................................................................................ 100 

$10,000–29,999. (18 CFR 381.304(b)) ................................................................................................................................. 600 

$30,000 or more. (18 CFR 381.304(a)) ................................................................................................................................ 20,770 

4. Written legal interpretations by the Office of General Counsel. (18 CFR 381.305(a)) .................................................................. 7,780 

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)) ......................................................... 23,330 

2. Certification of qualifying status as a cogeneration facility. (18 CFR 381.505(a)) ......................................................................... 26,410 

* This fee has not been changed. 


rmajette on DSKBCKNHB2PROD with RULES