Federal Register / Vol. 72, No. 72 / Monday, April 16, 2007 / Rules and Regulations 18861 

submitted by July 31. A waiver request 

must include a minimum amount of 

data in order for DOE to make a decision 

about granting the waiver. 

The DOE document Alternative 

Compliance: Preparing and Submitting 

a Waiver Request and Other 

Documentation Requirements, 10 CFR 

Part 490 Subpart I, helps requesting 

covered fleets by illustrating the data 

and information requirements as well as 

DOE’s implementation of the waiver 

provision. 

The guidelines include information 

for covered fleets regarding timing of 

waiver requests and responses by DOE, 

waiver documentation and submission 

requirements, annual reporting of 

petroleum reductions, use of credits and 

rollover of excess petroleum reduction, 

enforcement authority, record retention 

and appeals. 

Issued in Washington, DC, on April 9, 

2007. 

Alexander A. Karsner, 

Assistant Secretary, Energy Efficiency and 

Renewable Energy. 

[FR Doc. E7–7133 Filed 4–13–07; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 25 

[Docket No. NM374: Special Conditions No. 

25–351–SC] 

Special Conditions: Dassault Aviation, 

Model Falcon 7X; Design Roll 

Maneuvering Conditions 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final special conditions; request 

for comments. 

SUMMARY: These special conditions are 

issued for the Dassault Aviation Falcon 

7X airplane. This airplane will have a 

novel or unusual design feature 

associated with an electronic fly-by-wire 

flight control system. 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: The effective date of these 

special conditions is April 4, 2007. We 

must receive your comments by May 16, 

2007. 

ADDRESSES: You must mail two copies 

of your comments to: Federal Aviation 

Administration, Transport Airplane 

Directorate, Attn: Rules Docket (ANM–

113), Docket No. NM374, 1601 Lind 

Avenue, SW., Renton, Washington, 

98057–3356. You may deliver two 

copies to the Transport Airplane 

Directorate at the above address. You 

must mark your comments: Docket No. 

NM374. You can inspect comments in 

the Rules Docket weekdays, except 

Federal holidays, between 7:30 a.m. and 

4 p.m. 

FOR FURTHER INFORMATION CONTACT: Rich 

Yarges, FAA, Airframe/Cabin Safety 

Branch, ANM–115, Transport Airplane 

Directorate, Aircraft Certification 

Service, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; 

telephone (425) 227–2143; facsimile 

(425) 227–1232. 

SUPPLEMENTARY INFORMATION: The FAA 

has determined that notice and 

opportunity for prior public comment 

hereon are impracticable because these 

procedures would significantly delay 

issuance of the approval design and 

thus delivery of the affected aircraft. 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 that 

good cause exists for making these 

special conditions effective upon 

issuance. 

Comments Invited 

We invite interested people to take 

part in this rulemaking by sending 

written comments, data, or views. The 

most helpful comments reference a 

specific portion of the special 

conditions, explain the reason for any 

recommended change, and include 

supporting data. We ask that you send 

us two copies of written comments. 

We will file in the docket all 

comments we receive as well as a report 

summarizing each substantive public 

contact with FAA personnel about these 

special conditions. You can inspect the 

docket before and after the comment 

closing date. If you wish to review the 

docket in person, go to the address in 

the ADDRESSES section of this preamble 

between 7:30 a.m. and 4 p.m., Monday 

through Friday, except Federal holidays. 

We will consider all comments we 

receive by the closing date for 

comments. We will consider comments 

filed late if it is possible to do so 

without incurring expense or delay. We 

may change these special conditions 

based on the comments we receive. 

If you want us to let you know we 

received your comments on these 

special conditions, send us a preaddressed, stamped postcard on which 

the docket number appears. We will 

stamp the date on the postcard and mail 

it back to you. 

Background 

On June 4, 2002, Dassault Aviation, 9 

rond Point des Champs Elysees, 75008, 

Paris, France, applied for a type 

certificate for its new Model Falcon 7X. 

The Dassault Aviation Falcon 7X is a 19 

passenger transport category airplane, 

powered by three aft mounted Pratt & 

Whitney PW307A high bypass ratio 

turbofan engines. The airplane is 

operated using a fly-by-wire electronic 

flight control system. This flight control 

system does not provide a mechanical 

link between the airplane flight control 

surface and the pilot’s cockpit control 

device as there is on more conventional 

airplanes. This will be the first 

application of such a system in an 

airplane primarily intended for private 

or corporate use. However, several 

models of airplanes certificated under 

part 25 have incorporated fly-by-wire 

electronic flight control systems. 

Type Certification Basis 

Under the provisions of 14 CFR 21.17, 

Dassault Aviation must show that the 

Model Falcon 7X meets the applicable 

provisions of Part 14 CFR part 25, as 

amended by Amendment 25–1 through 

25–107. 

If the Administrator finds that the 

applicable airworthiness regulations do 

not contain adequate or appropriate 

safety standards for the Model Falcon 

7X because of a novel or unusual design 

feature, special conditions are 

prescribed under the provisions of 

§ 21.16. 

In addition to the applicable 

airworthiness regulations and special 

conditions, the Dassault Model Falcon 

7X must comply with the fuel vent and 

exhaust emission requirements of 14 

CFR part 34 and the noise certification 

requirements of 14 CFR part 36, and the 

FAA must issue a finding of regulatory 

adequacy under § 611 of Public Law 92–

574, the ‘‘Noise Control Act of 1972.’’

The FAA issues special conditions, as 

defined in § 11.19, under § 11.38, and 

they become part of the type 

certification basis under § 21.17(a)(2). 

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, the special conditions 

would also apply to the other model. 

Novel or Unusual Design Features 

The Falcon 7X is equipped with an 

electronic flight control system. In this 


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18862 Federal Register / Vol. 72, No. 72 / Monday, April 16, 2007 / Rules and Regulations 

system, there is not a direct mechanical 

link between the airplane flight control 

surface and the pilot’s cockpit control 

device as there is on more conventional 

airplanes. Instead, a flight control 

computer commands the airplane flight 

control surfaces, based on input 

received from the cockpit control 

device. The pilot input is modified by 

the flight control computer—based on 

the current airplane flight parameters—

before the command is given to the 

flight control surface. 

Discussion 

The formulation of airplane design 

load conditions in 14 CFR part 25 is 

based on the assumption that the 

airplane is equipped with a control 

system in which there is a direct 

mechanical linkage between the pilot’s 

cockpit control and the control surface. 

Thus, for roll maneuvers, the regulation 

specifies a displacement for the aileron 

itself and does not envision any 

modification of the pilot’s control input. 

Since such a system will affect the 

airplane flight loads and thus the 

structural strength of the airplane, 

special conditions appropriate for this 

type of control system are needed. 

In particular, the special condition 

adjusts the design roll maneuver 

requirements specified in § 25.349(a), so 

that they take into account the effect of 

the Falcon 7X’s electronic flight control 

computer on the control surface 

deflection. The special condition 

requires that the roll maneuver be 

performed by deflection of the cockpit 

roll control, as opposed to specifying a 

deflection of the aileron itself as the 

current regulation does. The deflection 

of the control surface would then be 

determined from the cockpit input, 

based on the computer’s flight control 

laws and the current airplane flight 

parameters. 

Applicability 

As discussed above, these special 

conditions are applicable to the Dassault 

Aviation Model Falcon 7X. Should 

Dassault Aviation apply at a later date 

for a change to the type certificate to 

include another model incorporating the 

same novel or unusual design feature, 

the special conditions would apply to 

that model as well. 

Conclusion 

This action affects only certain novel 

or unusual design features of the 

Dassault Aviation Model Falcon 7X 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 

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, which is 

imminent, the FAA has determined that 

prior public notice and comment are 

unnecessary and impracticable and that 

good cause exists for adopting these 

special conditions upon issuance. The 

FAA is requesting comments to allow 

interested persons to submit views that 

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 Dassault Aviation Model 

Falcon 7X airplanes. 

Design Roll Maneuvering Conditions 

In lieu of compliance with 14 CFR 

25.349(a), the following special 

conditions apply: 

Maneuvering: 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 the twothirds of limit positive maneuvering 

load factor. In determining the resulting 

control surface deflections, the torsional 

flexibility of the wing must be 

considered in accordance with 14 CFR 

25.301(b): 

(1) Conditions corresponding to 

maximum steady rolling velocities and 

conditions corresponding to maximum 

angular accelerations must be 

investigated. 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, movement of the cockpit 

roll control up to the limit is assumed. 

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 subparagraph (2) of this paragraph. 

(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 sub-paragraph (2) of this paragraph. 

Issued in Renton, Washington, on April 4, 

2007. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 07–1809 Filed 4–13–07; 8:45 am] 

BILLING CODE 4910–13–M 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27824; Directorate 

Identifier 2003–NE–12–AD; Amendment 39–

15026; AD 2006–11–05R1] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc RB211 Series Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is revising an 

existing airworthiness directive (AD) for 

Rolls-Royce plc (RR) RB211–22B series, 

RB211–524B, –524C2, –524D4, –524G2, 

–524G3, and –524H series, and RB211–

535C and –535E series turbofan engines 

with high pressure compressor (HPC) 

stage 3 disc assemblies, part numbers 

(P/Ns) LK46210, LK58278, LK67634, 

LK76036, UL11706, UL15358, UL22577, 

UL22578, and UL24738 installed. That 

AD currently requires removing from 

service certain disc assemblies before 

they reach their full published life if not 

modified with anticorrosion protection. 

This AD requires the same actions but 

relaxes the removal compliance time for 

certain disc assemblies that have a 

record of detailed inspection. This AD 

results from the FAA allowing certain 

affected disc assemblies that entered 

into service before 1990 that have a 

record of detailed inspections, to remain 

in service for a longer period than the 

previous AD allowed. We are issuing 

this AD to relax the compliance time for 

certain disc assemblies and track the 

disc life based on a detailed inspection 

rather than by its entry into service date, 

while continuing to prevent corrosioninduced uncontained disc assembly 

failure, resulting in damage to the 

airplane. 


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