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.

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# Rules and Regulations Federal Register 

### 11089

Vol. 78, No. 32

Friday, February 15, 2013

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 25**

**[Docket No. FAA–2012–1236; Special Conditions No. 25–477–SC]** 

**Special Conditions: Bombardier Aerospace, Model BD–500–1A10 and**  **BD–500–1A11 Airplanes; Sidestick Controllers** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final special conditions.

**SUMMARY :**  These special conditions are issued for the Bombardier Aerospace Model BD–500–1A10 and BD–500– 1A11 airplanes. These airplanes will have a novel or unusual design feature, specifically sidestick controllers designed to be operated with only one hand. 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 :**  Effective Date: March 18, 2013.

**FOR FURTHER INFORMATION CONTACT :**  Todd Martin, FAA, Airframe and Cabin Safety Branch, ANM–115, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone 425–227–1178; facsimile
425–227–1232.

**SUPPLEMENTARY INFORMATION :**  Background

On December 10, 2009, Bombardier Aerospace applied for a type certificate for their new Model BD–500–1A10 and BD–500–1A11 airplanes. The Model BD–500–1A10 and BD–500–1A11 airplanes are swept-wing monoplanes with pressurized cabins, and they share an identical supplier base and significant common design elements. The fuselages are aluminum alloy material, blended double-bubble fuselages, sized for nominal five-abreast seating. Each airplane’s powerplant includes two under-wing Pratt and Whitney PW1524G ultra-high bypass, geared turbofan engines. The flight controls are fly-by-wire flight with two passive/uncoupled sidesticks. Avionics include five landscape primary cockpit displays. The dimension of the aircraft encompasses a wingspan of 115 feet; height of 37.75 feet; and length of 114.75 feet for the Model BD–500–1A10 and length of 127 feet for the Model BD– 500–1A11. Passenger capacity is designated as 110 for the Model BD– 500–1A10 and 125 for the Model BD– 500–1A11. Maximum takeoff weight is 131,000 pounds for the Model BD–500– 1A10 and 144,000 pounds for the Model BD–500–1A11. Maximum takeoff thrust is 21,000 pounds for the Model BD– 500–1A10 and 23,300 pounds for the Model BD–500–1A11. The range is 5,463 kilometres for both model airplanes. The maximum operating altitude is 41,000 feet for both model airplanes.

Bombardier Model BD–500–1A10 and BD–500–1A11 airplanes will be equipped with a sidestick controller instead of a conventional control column and wheel. This kind of controller is designed for only one-hand operation.

The requirement of Title 14, Code of Federal Regulations (14 CFR) 25.397(c), which defines limit pilot forces and torques for conventional wheel or stick controls, is not adequate for a sidestick controller. A special condition is necessary to specify the appropriate loading conditions for this kind of controller. Type Certification Basis

Under the provisions of 14 CFR 21.17, Bombardier Aerospace must show that the Model BD–500–1A10 and BD–500– 1A11 airplanes meet the applicable provisions of part 25, as amended by Amendments 25–1 through 25–129 thereto.

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 Bombardier Aerospace Model BD–500–1A10 and BD–500–1A11 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 or similar novel or unusual design feature, the special conditions would also apply to the other model under § 21.101.

In addition to the applicable airworthiness regulations and special conditions, the Bombardier Aerospace Model BD–500–1A10 and BD–500– 1A11 airplanes 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 14 CFR 11.19, in accordance with § 11.38, and they become part of the type-certification basis under § 21.17(a)(2). Novel or Unusual Design Features

The Bombardier Aerospace Model BD–500–1A10 and BD–500–1A11 airplanes will incorporate the following novel or unusual design feature: A sidestick controller instead of a conventional control column and wheel. This kind of controller is designed for one-hand operation.

Discussion

The Bombardier Aerospace Model BD–500–1A10 and BD–500–1A11 airplanes are equipped with a sidestick controller instead of a conventional wheel or control stick. This kind of controller is designed to be operated using only one hand. The requirement of 14 CFR 25.397(c), which defines limit pilot forces and torques for conventional wheel or stick controls, is not adequate for a sidestick controller, because pilot forces are applied to sidestick controllers with only the wrist, not arms. A special condition is necessary to specify the appropriate loading conditions for a sidestick controller. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to


### 11090 Federal Register / Vol. 78, No. 32 / Friday, February 15, 2013 / Rules and Regulations

that established by the existing airworthiness standards.

Discussion of Comments

Notice of proposed special conditions No. 25–12–14–SC for the Bombardier Aerospace Model BD–500–1A10 and BD–500–1A11 airplanes was published in the Federal Register on November 20, 2012 (77 FR 69568). No comments were received, and the special conditions are adopted as proposed. Applicability

As discussed above, these special conditions are applicable to the Bombardier Aerospace Model BD–500– 1A10 and BD–500–1A11 airplanes. Should Bombardier Aerospace 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 on Bombardier Aerospace Model BD–500– 1A10 and BD–500–1A11 airplanes. 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 Model BD–500– 1A10 and BD–500–1A11 airplanes by Bombardier Aerospace:

Limit Pilot Forces for Sidestick Control

In lieu of the pilot forces specified in § 25.397(c), for the Bombardier Model BD–500–1A10 and BD–500–1A11 airplanes equipped with sidestick controls designed for forces to be applied by one wrist and not arms, the limit pilot forces are as follows:

1. For all components between and including the handle and its control stops.

Pitch Roll

Nose up 200 pounds

force (Lbf) Nose Left 100 Lbf

Nose down 200 Lbf Nose Right 100 Lbf

2. For all other components of the sidestick control assembly, excluding the internal components of the electrical sensor assemblies, to avoid damage as a result of an in-flight jam.

Pitch Roll

Nose up 125 lbf Nose Left 50 lbf Nose down 125 lbf Nose Right 50 lbf

Issued in Renton, Washington, on February 12, 2013. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013–03590 Filed 2–14–13; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Parts 117, 119, and 121**

**[Docket No. FAA–2009–1093; Amdt. Nos. 117–1, 119–16, 121–357]** 

**RIN 2120–AJ58**

**Flightcrew Member Duty and Rest Requirements; Technical Correction** 

**AGENCY :**  Federal Aviation Administration, DOT.

**ACTION :**  Final rule; technical correction.

**SUMMARY :**  The FAA is correcting the effective date of a final rule correction for flightcrew member duty and rest requirements published on February 6, 2013, that required technical corrections in the codified text of the final flightcrew member duty and rest rule. The correct effective date of the rule should read January 4, 2014.

**DATES :**  Effective date: The effective date of a final rule correction published in the Federal Register of February 6, 2013 (78 FR 8361), is corrected from January 14, 2014, to January 4, 2014.

**FOR FURTHER INFORMATION CONTACT :**  For technical questions concerning this action, contact Dale E. Roberts, AFS– 200, Flight Standards Service, Air Transportation Division Federal Aviation Administration, 800 Independence Avenue SW., Washington, DC 20591; telephone (202) 267–5749; email dale.e.roberts@faa.gov.

For legal questions concerning this action, contact Robert Frenzel, AGC– 220, Office of Chief Counsel, Regulations Division, Federal Aviation Administration, 800 Independence Avenue SW., Washington, DC 20591; telephone (202) 267–3073; email: robert.frenzel@faa.gov.

**SUPPLEMENTARY INFORMATION :**  Background On January 4, 2012, the FAA published a final rule entitled ‘‘Flightcrew Member Duty and Rest Requirements’’ (77 FR 330). In that rule, the FAA created a new part, part 117, which replaced the then-existing flight, duty, and rest regulations for part 121 passenger operations. As part of this rulemaking, the FAA also applied the new part 117 to certain part 91 operations, and it permitted all-cargo operations operating under part 121 to voluntarily opt into the part 117 flight, duty, and rest regulations.

Subsequent to publication, the FAA discovered several issues requiring a technical correction in the regulatory text of the rule and published a final rule, technical correction on February 6, 2013 (78 FR 8361). The FAA realized that the effective date in this rule was inadvertently changed from January 4, 2014, to January 14, 2014.

This technical correction changes the effective date to January 4, 2014.

Issued in Washington, DC, on February 11,
2013. Mark W. Bury, Acting Assistant Chief Counsel for International Law, Legislation, and Regulations.
[FR Doc. 2013–03559 Filed 2–14–13; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF COMMERCE**

**International Trade Administration**

**19 CFR Part 360**

**[Docket No.: 121016549–2549–01]**

**RIN 0625–AA93**

**Steel Import Monitoring and Analysis System** 

**AGENCY :**  Import Administration, International Trade Administration, Department of Commerce.

**ACTION :**  Final rule.

**SUMMARY :**  The Department of Commerce (the Department) publishes this action to make final a rule to extend the Steel Import Monitoring and Analysis (SIMA) system until March 21, 2017. The purpose of the SIMA system is to provide the public statistical data on steel imports entering the United States seven weeks earlier than it would otherwise be available to the public. Aggregate data collected from the licenses are made available to the public on a weekly basis following review by the Department.