This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents.

Rules and Regulations Federal Register

36723 

Vol. 83, No. 147 

Tuesday, July 31, 2018 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 25 

[Docket No. FAA–2018–0201; Special 

Conditions No. 25–717A–SC] 

Special Conditions: Bombardier Inc., 

Model BD–700–2A12 and BD–700– 

2A13 Series Airplanes, Flight Envelope 

Protection: Pitch and Roll Limiting 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Amended final special 

conditions; request for comments. 

SUMMARY: These amended special 

conditions are issued for the 

Bombardier Inc. (Bombardier), Model 

BD–700–2A12 and BD–700–2A13 series 

airplanes. These amended special 

conditions change paragraphs 2 and 3 of 

the special conditions section based on 

information from Bombardier that 

makes changes to the novel or unusual 

design feature of this airplane. This 

airplane will have a novel or unusual 

design feature when compared to the 

state of technology envisioned in the 

applicable airworthiness standards for 

transport category airplanes. This design 

feature is the fly-by-wire electronic 

flight-control system (EFCS) that will 

limit pitch and roll functions to prevent 

the airplane from attaining certain pitch 

attitudes and roll angles. 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 

Bombardier Inc. on July 31, 2018. Send 

comments on or before September 14, 

2018. 

ADDRESSES: Send comments identified 

by docket number FAA–2018–0201 

using any of the following methods: 

b Federal eRegulations Portal: Go to 

http://www.regulations.gov/ and follow 

the online instructions for sending your 

comments electronically. 

b 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. 

b 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. 

b 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: 

Joe Jacobsen, FAA, Airplane and Flight 

Crew Interface Section, AIR–671, 

Transport Standards Branch, Policy and 

Innovation Division, Aircraft 

Certification Service, 2200 South 216th 

Street, Des Moines, Washington 98198; 

telephone 206–231–3158; email 

Joe.Jacobsen@faa.gov. 

SUPPLEMENTARY INFORMATION: The FAA 

has determined that notice of, and 

opportunity for prior public comment 

on, these amended special conditions is 

impracticable because these procedures 

would significantly delay issuance of 

the design approval and thus delivery of 

the affected airplane. Additionally, 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. Therefore, the FAA 

has determined that prior public notice 

and comment are impracticable and 

unnecessary, and finds that, for the 

same reasons, good cause exists for 

adopting these special conditions 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 May 30, 2012, Bombardier applied 

for an amendment to Type Certificate 

No. T00003NY to include the new 

Models BD–700–2A12 and BD–700– 

2A13 series airplanes. The BD–700– 

2A12 and BD–700–2A13 series 

airplanes, are derivatives of the BD–700 

currently approved under Type 

Certificate No. T00003NY, and are 

business jets with a maximum certified 

passenger capacity of 19. The maximum 

takeoff weight of Model BD–700–2A12 

airplane is 106,250 lbs. and 104,800 lbs. 

for the Model BD–700–2A13 airplane. 

Type Certification Basis 

Under the provisions of title 14, Code 

of Federal Regulations (14 CFR) 21.101, 

Bombardier must show that the Model 

BD–700–2A12 and BD–700–2A13 series 

airplanes meet the applicable provisions 

of the regulations listed in Type 

Certificate No. T00003NY 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 the Model BD–700–2A12 and BD– 

700–2A13 series airplanes because of a 

novel or unusual design feature, special 

conditions are prescribed under the 

provisions of § 21.16. 


daltland on DSKBBV9HB2PROD with RULES
36724 Federal Register / Vol. 83, No. 147 / Tuesday, July 31, 2018 / Rules and Regulations 

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 Bombardier Model BD– 

700–2A12 and BD–700–2A13 series 

airplanes must comply with the fuelvent and exhaust-emission requirements 

of 14 CFR part 34, and the noisecertification 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 Model BD–700–2A12 and BD– 

700–2A13 series airplanes will 

incorporate the following novel or 

unusual design features: 

Fly-by-wire EFCS that will limit pitch 

and roll functions to prevent the 

airplane from attaining certain pitch 

attitudes and roll angles greater than 

plus or minus 65 degrees, and introduce 

positive spiral stability introduced for 

roll angles greater than 30 degrees at 

speeds below VMO/MMO. This system 

generates the actual surface commands 

that provide for stability augmentation 

and flight control for all three airplane 

axes (longitudinal, lateral, and 

directional). 

Discussion 

Part 25 of title 14 of the CFR does not 

specifically relate to flight 

characteristics associated with fixed 

attitude limits. Bombardier proposes to 

implement on the airplanes pitch and 

roll attitude-limiting functions via the 

EFCS normal mode. This will prevent 

the airplane from attaining certain pitch 

attitudes and roll angles greater than 

plus or minus 65 degrees. In addition, 

positive spiral stability, introduced for 

roll angles greater than 30 degrees at 

speeds below VMO/MMO, and spiral 

stability characteristics, must not 

require excessive pilot strength to 

achieve bank angles up to the bankangle limit. 

Bombardier requested this 

amendment, in order to be performancebased rather than prescriptive and to 

more closely follow the language 

developed in the Aviation Rulemaking 

Advisory Committee (ARAC) Flight Test 

Harmonization Working Group 

(FTHWG). The FAA concurs with this 

request. 

The basic envelope protection 

requirement, historically applied, is to 

not unduly limit the maneuver 

capability of the airplane, or interfere 

with its ability to perform maneuvers 

required for normal and emergency 

operations. Since the design details 

used to meet this requirement vary from 

airplane to airplane, this amendment 

recognizes and adopts that philosophy 

for this specific design implementation. 

The substance of the special conditions 

is unchanged, in that, for this specific 

design, the design details support the 

objective of not unduly limiting the 

maneuver capability, while also 

protecting the airplane from adverse 

attitudes. 

These special conditions are in 

addition to the requirements of § 25.143. 

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 Model 

BD–700–2A12 and BD–700–2A13 series 

airplanes. Should Bombardier 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 airplanes. It is not a rule of 

general applicability. 

List of Subjects in 14 CFR Part 25 

Aircraft, Aviation safety, Reporting 

and recordkeeping requirements. 

Authority Citation 

The authority citation for these 

special conditions is as follows: 

Authority: 49 U.S.C. 106(f), 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 Bombardier Model BD–700– 

2A12 and BD–700–2A13 series 

airplanes: 

In addition to § 25.143, the following 

requirements apply to the electronic 

flight-control system (EFCS) pitch- and 

roll-limiting functions: 

1. The pitch-limiting function must 

not impede normal maneuvering for 

pitch angles up to the maximum 

required for normal maneuvering, 

including a normal, all-enginesoperating takeoff, plus a suitable margin 

to allow for satisfactory speed control. 

2. The pitch- and roll-limiting 

functions must not restrict or prevent 

attaining pitch attitudes necessary for 

emergency maneuvering, or roll angles 

up to 65 degrees. Spiral stability, which 

is introduced above 30 degrees of roll 

angle, must not require excessive pilot 

strength to achieve these roll angles. 

Other protections, which further limit 

the roll capability under certain extreme 

angle-of-attack, attitude, or high-speed 

conditions, are acceptable, as long as the 

airplane is able to perform coordinated 

turns as per § 25.143(h). A roll attitude 

limit of approximately 45 degrees at 

high angle-of-attack conditions is 

acceptable. 

3. A reduced roll attitude limit is 

acceptable at extreme nose down pitch 

attitudes and beyond the overspeed 

warning to provide protection against 

high-speed combined pitch and roll 

upsets. The airplane should be able to 

perform operational turns at these 

speeds. A roll attitude limit of 

approximately 30 degrees at Vdf/Mdf is 

considered acceptable. 

Issued in Des Moines, Washington. 

Victor Wicklund, 

Manager, Transport Standards Branch, Policy 

and Innovation Division, Aircraft 

Certification Service. 

[FR Doc. 2018–16360 Filed 7–30–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0630; Product 

Identifier 2018–NE–25–AD; Amendment 39– 

19347; AD 2018–16–07] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

General Electric Company (GE) GEnx– 

1B54, –1B58, –1B64, –1B67, –1B70, 

–1B54/P1, –1B58/P1, –1B64/P1, –1B67/ 


daltland on DSKBBV9HB2PROD with RULES