70090 Federal Register / Vol. 75, No. 221 / Wednesday, November 17, 2010 / Rules and Regulations 

performance needed to restore the land 

to the applicable FSA, NRCS, Forest 

Service, or State forestry standard. 

§§ 701.213 through 701.225 [Reserved] 

§ 701.226 Maximum financial assistance. 

(a) In addition to other restrictions 

that may be applied by FSA, an EFRP 

participant will not receive more than 

75 percent of the lesser of the 

participant’s total actual cost or of the 

total allowable costs, as determined by 

this subpart, to perform the practice. 

(b) A person, as defined in part 1400 

of this title, is limited to a maximum 

cost-share of $500,000 per person or 

legal entity, per disaster. 

(c) The Deputy Administrator may 

waive the provisions of this section on 

a case by case basis to address 

unusually large losses. Such relief is 

solely at the discretion of the Deputy 

Administrator, and the failure to 

provide such relief is not subject to 

administrative review or appeal under 

parts 11 or 780 of this title. 

Signed in Washington, DC, November 9, 

2010. 

Jonathan W. Coppess, 

Administrator, Farm Service Agency. 

[FR Doc. 2010–28946 Filed 11–16–10; 8:45 am] 

BILLING CODE 3410–05–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 25 

[Docket No. NM435; Special Conditions No. 

25–413–SC] 

Special Conditions: Bombardier Inc. 

Model CL–600–2E25 Airplane, 

Operation Without Normal Electrical 

Power 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final special conditions; request 

for comments. 

SUMMARY: These special conditions are 

issued for the Bombardier Inc. Model 

CL–600–2E25 airplane. This airplane 

will have a novel or unusual design 

feature associated with a command-bywire (CBW) rudder-control system, 

which requires a source of continuous 

electrical power to operate the control 

system. The current 14 CFR part 

25.1351(d), ‘‘Operation without normal 

electrical power,’’ requires safe 

operation in VFR conditions for at least 

five minutes with inoperative normal 

electrical power. 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 November 5, 2010. 

We must receive your comments by 

January 3, 2011. 

ADDRESSES: You must mail two copies 

of your comments to: Federal Aviation 

Administration, Transport Airplane 

Directorate, Attn: Rules Docket (ANM– 

113), Docket No. NM435, 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. 

NM435 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: 

Steve Slotte, ANM–111, Transport 

Airplane Directorate, Aircraft 

Certification Service, 1601 Lind 

Avenue, SW., Renton, Washington, 

98057–3356; telephone (425) 227–2315; 

facsimile (425) 227–1149. 

SUPPLEMENTARY INFORMATION: The FAA 

has determined that notice of, and 

opportunity for prior public comment 

on, these special conditions are 

impracticable because these procedures 

would significantly delay issuance of 

the design approval 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 

concerning 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 on or before 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 acknowledge receipt 

of your comments on these special 

conditions, include with your 

comments a self-addressed, stamped 

postcard on which you have written the 

docket number. We will stamp the date 

on the postcard and mail it back to you. 

Background 

On February 28, 2007, Bombardier 

Inc. applied for an amendment to Type 

Certificate No. A21EA, through 

Transport Canada, to include the new 

Model CL–600–2E25 airplane. The CL– 

600–2E25, which is a derivative of the 

CL–600–2D24 currently approved under 

Type Certificate No. A21EA, is to be 

certified for a maximum occupancy of 

110 people, including 5 crewmembers. 

The CL–600–2E25 has increased gross 

weight, extended wing tip, and 

increased fuselage length to 

accommodate the additional passengers 

as compared to the CL–600–2D24. 

The CL–600–2E25 will have a CBW 

rudder-control system that will affect 

the performance of the airplane. This 

system requires a continuous source of 

electrical power to maintain an operable 

control system. 

Type Certification Basis 

Under the provisions of Title 14, Code 

of Federal Regulations (14 CFR) 21.101, 

Bombardier Inc. must show that the 

Model CL–600–2E25 airplane meets the 

applicable provisions of 14 CFR part 25, 

as amended by Amendments 25–1 

through 25–119, except for earlier 

amendments as agreed upon by the 

FAA. These regulations will be 

incorporated into Type Certificate No. 

A21EA after type-certification approval 

of the Model CL–600–2E25. The 

regulations incorporated by reference in 

the type certificate are commonly 

referred to as the ‘‘original typecertification basis.’’ The regulations 

incorporated by reference in Type 

Certificate No. A21EA are as follows: 

The original type-certification basis 

for the Model CL–600–2D24 (CRJ 900), 

shown on TCDS A21EA, Revision 25, 

and reprinted below. 

Model CL–600–2D15/CL–600–2D24 

Part 25, including Amendments 25–1 

through 25–86, Amendments 25–88 

through Amendments 25–90, and 


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Federal Register / Vol. 75, No. 221 / Wednesday, November 17, 2010 / Rules and Regulations 70091 

Amendments 25–92 through 25–98 with 

the following exceptions: 

• Section 25.783(f) at Amendment 

25–23 shall replace § 25.783(f) at 

Amendment 25–88 for the Aft Cargo 

Compartment and Main Avionics Bay 

Doors only (common doors with CL– 

600–2C10 (CRJ–700); 

• Section 25.807(d)(6) at Amendment 

25–72 shall replace § 25.807(h) at 

Amendment 25–94; 

• Sections 25.365, 25.831(a), and 

25.1447(c) at Amendment 25–87. Part 

25, Amendment 25–91, is not included 

in the type-certification basis. 

Additional FAA Requirements for 

Model CL–600–2D15/CL–600–2D24 

1. 14 CFR part 36, effective September 

10, 1990, and including all amendments 

effective on the date of type 

certification. 

2. 14 CFR part 34, effective September 

10, 1990, and including all amendments 

effective on the date of type 

certification. 

3. Special Conditions: 

(a) High Intensity Radiated Fields, No. 

25–ANM–109, dated October 31, 1995. 

(b) Go-Around Performance Credit for 

Use of Automatic Power Reserve (APR), 

No. 25–167–SC, dated October 24, 2000 

(same as CL–600–2C10). 

(c) Sudden Engine Stoppage, No. 25– 

217–SC, dated October 04, 2002. 

(d) Passenger Seats With Nontraditional, Large, Non-metallic Panels, 

No. 25–384–SC, dated August 12, 2009. 

4. Exemptions: Exemption No. 7447, 

hydraulic-systems testing per 14 CFR 

25.1435(b)(1). 

Equivalent safety has been established 

for the following requirements: 

CL–600–2D15/CL–600–2D24 

1. Section 25.103 and others, Reduced 

Minimum Operating Speed Factors. 

2. Section 25.811(d)(2), Main Door 

Exit Marking Sign. 

3. Section 25.813(c)(2)(i), Emergency 

Exit Access. 

4. Section 25.904, Performance Credit 

for Use of APR During Reduced Thrust 

Takeoff. 

5. Section 25.933(a)(1)(ii), Thrust 

Reverser System. 

6. Section 25, appendix I, § 25.5(b)(4), 

Lack of On/Off Switch for Automatic 

Takeoff Thrust Control System 

(ATTCS). 

7. Section 25.841(b)(6), High Altitude 

Takeoff and Landing Operations 

documented in Transport Airplane 

Directorate ELOS Memo AT2587NY–T, 

dated January 31, 2007. 

In addition, the certification basis 

includes other regulations, special 

conditions, and exemptions that are not 

relevant to these special conditions. 

Type Certificate No. A21EA will be 

updated to include a complete 

description of the certification basis for 

this airplane model. 

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 CL–600–2E25 because of a novel 

or unusual design feature, special 

conditions are prescribed under the 

provisions of 14 CFR 21.16. 

In addition to the applicable 

airworthiness regulations and special 

conditions, the CL–600–2E25 must 

comply with the fuel-vent and exhaustemission requirements of 14 CFR part 

34, and the noise-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 

14 CFR 21.101. 

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 or similar novel 

or unusual design feature, or should any 

other model already included on the 

same type certificate be modified to 

incorporate the same or similar novel or 

unusual design feature, the special 

conditions would also apply to the other 

model under § 21.101. 

Novel or Unusual Design Features 

The Bombardier Model CL–600–2E25 

airplane will incorporate the following 

novel or unusual design features: 

The CL–600–2E25 airplane will have 

a CBW rudder-control system that 

requires a continuous source of 

electrical power to maintain operability 

of the control system. 

Discussion 

The current 14 CFR 25.1351(d), 

‘‘Operation without normal electrical 

power,’’ requires safe operation in VFR 

conditions for at least five minutes with 

inoperative normal power. This rule 

was premised on a traditional design 

utilizing mechanical control cables for 

flight control while the crew took time 

to sort out the electrical failure, start 

engine(s) if necessary, and re-establish 

some of the electrical-power-generation 

capability. 

To maintain the same level of safety 

associated with traditional designs, the 

Bombardier CL–600–2E25 design must 

not be time limited in its operation, 

including being without the normal 

source of engine- or Auxiliary Power 

Unit (APU)-generated electrical power. 

Service experience on other airplane 

models with similar electrical-power 

systems has shown that the loss of all 

electrical power, which is generated by 

the airplane’s engine generators or APU, 

is not extremely improbable. Thus, it 

must be demonstrated that the airplane 

can continue through safe flight and 

landing (including steering and braking 

on ground for airplanes using steer/ 

brake-by-wire) with the use of its 

emergency electrical-power systems. 

These emergency electrical-power 

systems must be able to power loads 

that are essential for continued safe 

flight and landing. 

Applicability 

As discussed above, these special 

conditions are applicable to the Model 

CL–600–2E25. Should Bombardier Inc. 

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 

of airplane. It is not a rule of general 

applicability. 

Under standard practice, the effective 

date of final special conditions would 

be 30 days after the date of publication 

in the Federal Register; however, as the 

certification date for the Model CL–600– 

2E25 airplane is imminent, the FAA 

finds that good cause exists to make 

these special conditions effective upon 

issuance. 

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 typecertification basis for Bombardier Model 

CL–600–2E25 airplanes modified 

according to DCA 0145–000–00020– 

2008/FAA (latest revision approved by 

the FAA). 

To ensure that the total loss of 

electrical power is extremely 

improbable, and because the loss of all 

electrical power may be catastrophic to 

airplanes utilizing an Electronic Flight 

Control System, the following Special 

Condition is issued in lieu of 

§ 25.1351(d): 


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70092 Federal Register / Vol. 75, No. 221 / Wednesday, November 17, 2010 / Rules and Regulations 

It must be demonstrated by test, or 

combination of test and analysis, that the 

airplane can continue safe flight and landing 

with inoperative normal engine- and APUgenerated electrical power (for example, 

without electrical power from any source, 

except for the battery and any other standby 

electrical sources). The airplane operation 

should be considered at the critical phase of 

flight and include the ability to restart the 

engines and maintain flight for the maximum 

diversion time capability being certified. 

Issued in Renton, Washington on 

November 5, 2010. 

Jeffrey Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–28998 Filed 11–16–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 25 

[Docket No. NM434; Notice No. 25–412–SC] 

Special Conditions: Bombardier Inc. 

Model CL–600–2E25 Airplane, 

Interaction of Systems and Structures 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final special conditions; request 

for comments. 

SUMMARY: These special conditions are 

issued for the Bombardier Inc. Model 

CL–600–2E25 airplane. This airplane 

will have a novel or unusual design 

feature associated with the ruddertraveler limiting system controlling the 

command-by-wire (CBW) rudder. This 

system can serve to alleviate loads in 

the airframe but, in a failure state, can 

create loads in the airframe. 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 November 5, 2010. 

We must receive your comments by 

January 3, 2011. 

ADDRESSES: You must mail two copies 

of your comments to: Federal Aviation 

Administration, Transport Airplane 

Directorate, Attn: Rules Docket (ANM– 

113), Docket No. NM434, 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. 

NM434. 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: 

Todd Martin, FAA, ANM–115, 

Transport Airplane Directorate, Aircraft 

Certification Service, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–1178; 

facsimile (425) 227–1149. 

SUPPLEMENTARY INFORMATION: The FAA 

has determined that notice of, and 

opportunity for prior public comment 

on, these special conditions are 

impracticable because these procedures 

would significantly delay issuance of 

the design approval 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 

concerning 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 on or before 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 acknowledge receipt 

of your comments on these special 

conditions, include with your 

comments a self-addressed, stamped 

postcard on which you have written the 

docket number. We will stamp the date 

on the postcard and mail it back to you. 

Background 

On February 28, 2007, Bombardier 

Inc. applied for an amendment to Type 

Certificate No. A21EA, through 

Transport Canada, to include the new 

Model CL–600–2E25 airplane. The CL– 

600–2E25, which is a derivative of the 

CL–600–2D24 currently approved under 

Type Certificate No. A21EA, is to be 

certified for a maximum occupancy of 

110 people, including 5 crewmembers. 

The CL–600–2E25 has increased gross 

weight, extended wing tip, and 

increased fuselage length to 

accommodate the additional passengers 

as compared to the CL–600–2D24. 

The CL–600–2E25 will have a CBW 

rudder-control system that will affect 

the structural performance of the 

airplane. The airplane will use CBW 

Rudder Electronic Control Unit (ECU) 

software as a replacement for the 

Rudder Travel Limiter to limit rudder 

commands. The CBW Rudder ECU 

controls the rudder, trim, and yaw 

damping as well. This system can serve 

to alleviate loads in the airframe but, in 

a failure state, can create loads in the 

airframe. The current rules do not 

adequately account for the effects of this 

system and its failures on structural 

performance. The special conditions 

defined herein provide the criteria to be 

used in assessing the effects of this 

system on structures. 

Type Certification Basis 

Under the provisions of § 21.101, 

Bombardier Inc. must show that the 

Model CL–600–2E25 airplane meets the 

applicable provisions of Title 14, Code 

of Federal Regulations (14 CFR) part 25, 

as amended by Amendments 25–1 

through 25–119, except for earlier 

amendments as agreed upon by the 

FAA. These regulations will be 

incorporated into Type Certificate No. 

A21EA after type-certification approval 

of the Model CL–600–2E25. The 

regulations incorporated by reference in 

the type certificate are commonly 

referred to as the ‘‘original typecertification basis.’’ The regulations 

incorporated by reference in Type 

Certificate No. A21EA are as follows: 

The original type-certification basis 

for the Model CL–600–2D24 (CRJ 900), 

shown on TCDS A21EA, Revision 25, 

and reprinted below. 

Model CL–600–2D15/CL–600–2D24 

Part 25, including Amendments 25–1 

through 25–86, Amendments 25–88 

through Amendments 25–90, and 

Amendments 25–92 through 25–98 with 

the following exceptions: 

• Section 25.783(f) at Amendment 

25–23 shall replace § 25.783(f) at 

Amendment 25–88 for the Aft Cargo 

Compartment and Main Avionics Bay 

Doors only (common doors with CL– 

600–2C10 (CRJ–700); 


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