Federal Register / Vol. 76, No. 30 / Monday, February 14, 2011 / Proposed Rules 8321

Authority: 49 U.S.C. 106(g), 40113, 44701, DEPARTMENT OF TRANSPORTATION Comments Invited 44702, 44704. We invite interested people to take Federal Aviation Administration The Proposed Special Conditions part in this rulemaking by sending written comments, data, or views. The 14 CFR Part 33 Accordingly, the Federal Aviation most helpful comments reference a Administration (FAA) proposes the [Docket No. NE130; Notice No. 33–10–01– specific portion of the special following special conditions as part of SC] conditions, explain the reason for any the type certification basis for the GVI recommended change, and include airplanes. Special Conditions: Pratt and Whitney supporting data. We ask that you send Canada Model PW210S Turboshaft us two copies of written comments. In lieu of compliance with § 25.349(a), Engine Gulfstream must comply with the We will file in the docket all following special conditions. AGENCY: Federal Aviation comments we receive, as well as a Administration (FAA), DOT. report summarizing each substantive The following conditions, speeds, and public contact with FAA personnel cockpit roll control motions (except as ACTION: Notice of proposed special conditions. about these special conditions. You can the motions may be limited by pilot inspect the docket before and after the effort) must be considered in SUMMARY: This action proposes special comment closing date. If you wish to combination with an airplane load conditions for the Pratt and Whitney review the docket in person, go to the factor of zero and of two-thirds of the Canada (PWC) model PW210S address in the ADDRESSES section of this positive maneuvering factor used in turboshaft engine. This engine model preamble between 9 am. and 5 p.m., design. In determining the resulting will have a novel or unusual design Monday through Friday, except Federal control surface deflections, the torsional feature associated with engine operation holidays. flexibility of the wing must be in auxiliary power unit (APU) mode. We will consider all comments we considered in accordance with The applicable airworthiness receive by the closing date for § 25.301(b): regulations do not contain adequate or comments. We will consider comments filed late if it is possible to do so 1. Conditions corresponding to steady appropriate safety standards for this without incurring expense or delay. We rolling velocities must be investigated. design feature. These proposed special may change these special conditions In addition, conditions corresponding to conditions contain the added safety standards that the Administrator based on the comments we receive. maximum angular acceleration must be considers necessary to establish a level If you want us to let you know we investigated for airplanes with engines of safety equivalent to that established received your comments on this or other weight concentrations outboard by the existing airworthiness standards. proposal, send us a pre-addressed, of the fuselage. For the angular DATES: stamped postcard on which the docket acceleration conditions, zero rolling We must receive your comments by March 16, 2011. number appears. We will stamp the date velocity may be assumed in the absence on the postcard and mail it back to you. of a rational time history investigation ADDRESSES: You must mail two copies of the maneuver. of your comments to: Federal Aviation Background Administration, Engine and Propeller On December 5, 2005, PWC applied 2. At VA, sudden movement of the Directorate, Attn: Marc Bouthillier, cockpit roll control up to the limit is for a type certificate for the model Rules Docket (ANE–111), Docket No. PW210S turboshaft engine. The engine assumed. The position of the cockpit NE130, 12 New England Executive Park, roll control must be maintained until a is a free turbine turboshaft designed for Burlington, Massachusetts 01803–5299. a transport category helicopter. This steady roll rate is achieved and then You may deliver two copies to the engine incorporates a two stage must be returned suddenly to the Engine and Propeller Directorate at the compressor driven by a single stage neutral position. above address. You must mark your turbine and a two stage free power comments: Docket No. NE130. You can 3. At VC, the cockpit roll control must turbine driving a two stage reduction be moved suddenly and maintained so inspect comments in the Rules Docket gearbox and main output shaft. The as to achieve a roll rate not less than weekdays, except Federal holidays, control system includes a dual channel that obtained in paragraph 2. between 7:30 am. and 4 p.m. digital electronic control. The engine FOR FURTHER INFORMATION CONTACT: For 4. At V , the cockpit roll control must will incorporate a novel or unusual D technical questions concerning this be moved suddenly and maintained so design feature associated with engine proposed rule contact Marc Bouthillier, operation in auxiliary power unit (APU) as to achieve a roll rate not less than one ANE–111, Engine and Propeller third of that obtained in paragraph 2. mode. The helicopter will incorporate a Directorate, Aircraft Certification main rotor brake what will allow the Issued in Renton, Washington, on February Service, 12 New England Executive engine main output shaft and power 3, 2011. Park, Burlington, Massachusetts 01803– turbine to be brought to a stop and to Ali Bahrami, 5299, telephone (781) 238–7120; remain stationary, while the gas Manager, Transport Airplane Directorate, facsimile (781) 238–7199; e-mail generator portion of the engine Aircraft Certification Service. [email protected]. For legal continues to operate as an APU while questions concerning this proposed rule [FR Doc. 2011–3216 Filed 2–11–11; 8:45 am] on the ground. contact Vincent Bennett, ANE–7 Engine BILLING CODE 4910–13–P The applicable airworthiness and Propeller Directorate, Aircraft standards do not contain adequate or Certification Service, 12 New England appropriate airworthiness standards to Executive Park, Burlington, address this design feature. Massachusetts 01803–5299; telephone These special conditions contain the (781) 238–7044; facsimile (781) 238– additional airworthiness standards 7055; e-mail [email protected]. necessary to establish a level of safety SUPPLEMENTARY INFORMATION: equivalent to the level that would result

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from compliance with the applicable Also, the type certification engine rotor speed, torque, temperature, standards of airworthiness in effect on considerations for function and air bleed and power extraction as the date of application. reliability are common between these specified by the applicant. two engine types in this regard, making (b) Dynamic braking: A total of 400 Type Certification Basis requirements similar to current § 33.96 application-release cycles of simulated Under the provisions of 14 CFR 21.17, generally applicable to turboshaft brake engagements must be made in a PWC must show that the model PW210S engine types. Future rulemaking may manner which clearly demonstrates the turboshaft engine meets the provisions occur to expand the applicability of complete engine’s ability to function of the applicable regulations in effect on § 33.96 to include turboshaft type without adverse affect under the the date of application. The application engines. maximum conditions of engine date is December 5, 2005, which acceleration and deceleration rate, rotor Applicability corresponds to 14 CFR part 33 speed, torque and temperature as Amendment 20. However, PWC has As discussed above, these special specified by the applicant. The engine elected to demonstrate compliance to conditions are applicable to PWC model output shaft must be stopped prior to later amendments of part 33 for this PW210S turboshaft engines. If Pratt and brake-release. model. Therefore, the certification basis Whitney Canada applies later for a (c) One hundred engine starts and for the PW210S model turboshaft engine change to the type certificate to include stops with the output shaft locked in a will be part 33, effective February 1, another related model incorporating the manner simulating rotor brake 1965, as amended by Amendments 33– same novel or unusual design feature, engagement. 1 through 33–24. these special conditions would apply to (d) The tests required by paragraphs If the Administrator finds that the that model as well. (a), (b) and (c) of this section must be applicable airworthiness regulations in performed on the same engine, but this Conclusion part 33, as amended, do not contain engine need not be the same engine adequate or appropriate safety standards This action affects only certain novel used for the tests required by § 33.87 of for the PWC model PW210S turboshaft or unusual design features on one model 14 CFR part 33. engine, because of a novel or unusual of engine. It is not a rule of general (e) The tests required by paragraphs design feature, special conditions are applicability, and it affects only the (a), (b) and (c) of this section must be prescribed under the provisions of applicant who applied to the FAA for followed by engine disassembly to the § 21.16. approval of these features on the engine. extent necessary to show that each The FAA issues special conditions, as List of Subjects in 14 CFR Part 33 engine part conforms to the type design defined by 14 CFR 11.19, in accordance and is eligible for incorporation into an with 14 CFR 11.38, which become part Air transportation, Aircraft, Aviation engine for continued operation in of the type certification basis in safety, Safety. accordance with information submitted accordance with § 21.17(b)(2). The authority citation for these in compliance with § 33.4, Instructions Special conditions are initially special conditions is as follows: for Continued Airworthiness. applicable to the model for which they Authority: 49 U.S.C. 106(g), 40113, 44701– (f) Brake engagement and release: The are issued. Should the type certificate 44702, 44704. effects on the engine of braking and for that model be amended later to releasing the output shaft, including The Proposed Special Conditions include another related model that partial or sudden events while the incorporates the same or similar novel Accordingly, the Federal Aviation engine is running, must be determined. Administration (FAA) proposes the or unusual design feature, or should any Issued in Burlington, Massachusetts, on other model already included on the following special conditions as part of January 30, 2011. the type certification basis for Pratt and same type certificate be modified to Peter A. White, incorporate the same or similar novel or Whitney Canada (PWC) model PW210S turboshaft engines. Acting Manager, Engine and Propeller unusual design feature, the special Directorate, Aircraft Certification Service. conditions would also apply to the other 1. PART 1 DEFINITION. Unless [FR Doc. 2011–3068 Filed 2–11–11; 8:45 am] model. otherwise approved by the Administrator and documented in the BILLING CODE 4910–13–M Novel or Unusual Design Features appropriate manuals and certification The Pratt and Whitney Canada (PWC) documents, the following definition DEPARTMENT OF TRANSPORTATION model PW210S turboshaft engine will applies to this special condition: incorporate a novel or unusual design ‘‘Auxiliary Power Unit Mode’’ Engine Federal Aviation Administration feature associated with engine operation operation with the main output shaft in auxiliary power unit (APU) mode. and power turbine locked and 14 CFR Part 71 Special conditions for APU mode are stationary, while the gas generator proposed to address the novel and portion of the engine continues to [Docket No. FAA–2010–1264; Airspace unusual design feature. The special operate, for the purpose of supplying Docket No. 10–AWP–23] conditions are discussed below. the rotorcraft with electric/hydraulic/ Proposed Amendment of Class D and pneumatic power (as applicable) while Discussion Class E Airspace; Livermore, CA on the ground. The proposed special conditions are 2. PART 33 REQUIREMENTS: AGENCY: Federal Aviation similar to those requirements that (a) Ground locking: A total of 45 Administration (FAA), DOT. currently exist in 14 CFR part 33, hours with the engine output shaft ACTION: Notice of proposed rulemaking § 33.96 Engine Tests in Auxiliary Power locked to simulate rotor brake (NPRM). Unit (APU) Mode. However the current engagement, in a manner which clearly rule only applies to turboprop type demonstrates the complete engine’s SUMMARY: This action proposes to engines, therefore special conditions are ability to function without adverse amend Class E airspace at Livermore, needed to apply appropriate affect while operating in the APU mode CA, to accommodate aircraft using new requirements to turboshaft type engines. under the maximum conditions of Instrument Landing System (ILS)

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