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Rules and Regulations Federal Register Vol. 78, No. 95

Thursday, May 16, 2013

This section of the FEDERAL REGISTER Room W12–140 of the West Building conditions, explain the reason for any contains regulatory documents having general Ground Floor at 1200 New Jersey recommended change, and include applicability and legal effect, most of which Avenue SE., Washington, DC, between 8 supporting data. We ask that you send are keyed to and codified in the Code of a.m., and 5 p.m., Monday through us two copies of written comments. Federal Regulations, which is published under Friday, except Federal holidays. We will file in the docket all 50 titles pursuant to 44 U.S.C. 1510. b Fax: Fax comments to Docket comments we receive, as well as a The Code of Federal Regulations is sold by Operations at 202–493–2251. report summarizing each substantive the Superintendent of Documents. Prices of Privacy: The FAA will post all public contact with FAA personnel new books are listed in the first FEDERAL comments it receives, without change, concerning these special conditions. REGISTER issue of each week. to http://regulations.gov, including any You can inspect the docket before and personal information the commenter after the comment closing date. If you provides. Using the search function of wish to review the docket in person, go DEPARTMENT OF TRANSPORTATION the docket Web site, anyone can find to the address in the ADDRESSES section and read the electronic form of all of this preamble between 7:30 a.m. and Federal Aviation Administration comments received into any FAA 4:00 p.m., Monday through Friday, docket, including the name of the except Federal holidays. 14 CFR Part 23 individual sending the comment (or We will consider all comments we [Docket No. FAA–2013–0413; Special signing the comment for an association, receive on or before the closing date for Conditions No. 23–259–SC] business, labor union, etc.). DOT’s comments. We will consider comments complete Privacy Act Statement can be filed late if it is possible to do so Special Conditions: Cessna Aircraft found in the Federal Register published without incurring expense or delay. We Company, Model J182T; Diesel Cycle on April 11, 2000 (65 FR 19477–19478), may change these special conditions Engine Installation as well as at http://DocketsInfo.dot.gov. based on the comments we receive. Docket: Background documents or AGENCY: Federal Aviation Background Administration (FAA), DOT. comments received may be read at http://www.regulations.gov at any time. On April 2, 2012, Cessna applied for ACTION: Final special conditions; request Follow the online instructions for for comments. an amendment to Type Certificate No. accessing the docket or go to the Docket 3A13 to include the new Model J182T SUMMARY: These special conditions are Operations in Room W12–140 of the with the Societe de Motorisation issued for the Cessna Aircraft Company West Building Ground Floor at 1200 Aeronautiques (SMA) Engines, Inc. (Cessna) Model J182T airplane. This New Jersey Avenue SE., Washington, SR305–230E–C1 which is a four-stroke, airplane will have a novel or unusual DC, between 9 a.m., and 5 p.m., Monday air cooled, diesel cycle engine that uses design feature(s) associated with the through Friday, except Federal holidays. turbine (jet) fuel. The Model No. J182T, installation of an aircraft diesel engine FOR FURTHER INFORMATION CONTACT: Mr. which is a derivative of the T182 (ADE). The applicable airworthiness Peter Rouse, Federal Aviation currently approved under Type regulations do not contain adequate or Administration, Small Airplane Certificate No. 3A13, is an aluminum, appropriate safety standards for this Directorate, Aircraft Certification four place, single engine airplane with design feature. These special conditions Service, 901 Locust, Room 301, Kansas a cantilever high wing, with the SMA contain the additional safety standards City, MO 64106; telephone (816) 329– SR305–230E–C1 diesel cycle engine and that the Administrator considers 4135; facsimile (816) 329–4090. associated systems installed. necessary to establish a level of safety SUPPLEMENTARY INFORMATION: The FAA In anticipation of the reintroduction equivalent to that established by the has determined that notice and of diesel engine technology into the existing airworthiness standards. opportunity for prior public comment small airplane fleet, the FAA issued DATES: The effective date of these hereon are impracticable because these Policy Statement PS–ACE100–2002–004 special conditions is May 8, 2013. We procedures would significantly delay on May 15, 2004, which identified areas must receive your comments by June 17, issuance of the approval design and of technological concern. Refer to this 2013. thus delivery of the affected aircraft. In policy for a detailed summary of the ADDRESSES: Send comments identified addition, the substance of these special FAA’s development of diesel engine by docket number [FAA–2013–0413] conditions has been subject to the requirements. using any of the following methods: public comment process in several prior The general areas of concern b Federal eRegulations Portal: Go to instances with no substantive comments involving the application of a diesel http://www.regulations.gov and follow received. The FAA therefore finds that cycle engine are: the online instructions for sending your good cause exists for making these • The power characteristics of the comments electronically. special conditions effective upon engine, b Mail: Send comments to Docket issuance. • the use of turbine fuel in an Operations, M–30, U.S. Department of airplane class that is typically powered Transportation (DOT), 1200 New Jersey Comments Invited by gasoline fueled engines, Avenue SE., Room W12–140, West We invite interested people to take • the vibration characteristics, both Building Ground Floor, Washington, part in this rulemaking by sending normal and with an inoperative DC, 20590–0001. written comments, data, or views. The cylinder, b Hand Delivery or Courier: Take most helpful comments reference a • anticipated use of an electronic comments to Docket Operations in specific portion of the special engine control system,

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• the appropriate limitations and incorporate the same novel or unusual the fuel flow requirements of § 23.955(c) indications for a diesel cycle engine, design feature, the special conditions are modified to be reflective of the and would also apply to the other model. diesel engine operating characteristics. • the failure modes of a diesel cycle Section 23.961 will be complied with Novel or Unusual Design Features engine. using the turbine fuel requirements. A historical record review of diesel The J182T will incorporate the These requirements will be engine use in aircraft and part 23 following novel or unusual design substantiated by flight-testing as identified these concerns. The review features: described in Advisory Circular (AC) 23– identified specific regulatory areas The Installation of an ADE 8B, Flight Test Guide for Certification of requiring evaluation for applicability to Part 23 Airplanes. diesel engine installations. These Discussion This special condition specifically concerns are not considered universally Several major concerns were requires testing to show compliance to applicable to all types of possible diesel identified in developing FAA policy. § 23.961 and adds the possibility of engines and diesel engine installations. These include installing the diesel testing non-aviation diesel fuels. However, after reviewing the Cessna engine and noting its vibration levels To ensure fuel system compatibility installation, the SMA engine type, the under both normal operating conditions and reduce the possibility of misfueling, SMA engine requirements, and Policy and when one cylinder is inoperative. and discounting the first clause of Statement PS–ACE100–2002–004, the The concerns also include § 23.973(f) referring to turbine engines, FAA proposes engine installation and accommodating turbine fuels in airplane the applicant will comply with fuel system special conditions. The systems that have generally evolved § 23.973(f). SMA engine has a Full Authority Digital based on gasoline requirements, Due to the use of turbine fuel, the Engine Control (FADEC), which also anticipated use of a FADEC to control applicant will comply with requires special conditions. The FADEC the engine, and appropriate limitations § 23.977(a)(2), and § 23.977(a)(1) will special conditions will be issued in a and indications for a diesel engine not apply. ‘‘Turbine engines’’ will be separate notice. powered airplane. The general concerns interpreted to mean ‘‘aircraft diesel engine’’ for this requirement. An Type Certification Basis associated with the aircraft diesel engine installation are as follows: additional requirement to consider the Under the provisions of § 21.101, possibility of fuel freezing was imposed. Cessna must show that the J182T meets Installation and Vibration Requirements Due to the use of turbine fuel, the the applicable provisions of the Fuel and Fuel System Related applicant will comply with regulations incorporated by reference in Requirements § 23.1305(c)(8). Type Certificate No. 3A13 or the Due to the use of turbine fuel, the Limitations and Indications applicable regulations in effect on the applicant must comply with date of application for the change to the Installation and Vibration § 23.1557(c)(1)(ii). Section model T182T. The regulations Requirements: These special conditions 23.1557(c)(1)(ii) will not apply. incorporated by reference in the type include requirements similar to the ‘‘Turbine engine’’ is interpreted to mean certificate are commonly referred to as requirements of § 23.901(d)(1) for ‘‘aircraft diesel engine’’ for this the ‘‘original type certification basis.’’ In turbine engines. In addition to the requirement. addition, the J182T certification basis requirements of § 23.901 applied to includes special conditions and reciprocating engines, the applicant will Limitations and Indications equivalent levels of safety. be required to construct and arrange Section 23.1305 will apply, except If the Administrator finds that the each diesel engine installation to result that the critical engine parameters for applicable airworthiness regulations in vibration characteristics that do not this installation that will be displayed (i.e., 14 CFR part 23) do not contain exceed those established during the type include: adequate or appropriate safety standards certification of the engine. These (1) Power setting, in percentage, and for the J182T because of a novel or vibration levels must not exceed (2) Fuel temperature. unusual design feature, special vibration characteristics that a Due to the use of turbine fuel, the conditions are prescribed under the previously certificated airframe requirements for § 23.1521(d), as provisions of § 21.16. structure has been approved for, unless applicable to fuel designation for In addition to the applicable such vibration characteristics are shown turbine engines, as well as compliance airworthiness regulations and special to have no effect on safety or continued to § 23.1557(c)(1)(ii) will be in lieu of conditions, the J182T must comply with airworthiness. The engine installation § 23.1557(c)(1)(i). the fuel vent and exhaust emission must be shown to be free of whirl mode requirements of 14 CFR part 34 and the flutter and also any one cylinder Applicability noise certification requirements of 14 inoperative flutter effects. The engine As discussed above, these special CFR part 36. limit torque design requirements as conditions are applicable to the Model The FAA issues special conditions, as specified in § 23.361 are also modified. J182T. Should Cessna apply at a later defined in § 11.19, under § 11.38 and An additional requirement to consider date for a change to the type certificate they become part of the type vibration levels and/or effects of an to include another model incorporating certification basis under § 21.101. inoperative cylinder was imposed. Also, the same novel or unusual design Special conditions are initially a requirement to evaluate the engine feature, the special conditions would applicable to the model for which they design for the possibility of, or effect of, apply to that model as well. are issued. Should the type certificate liberating high-energy engine fragments, for that model be amended later to in the event of a catastrophic engine Conclusion include any other model that failure, requirements was added. This action affects only certain novel incorporates the same novel or unusual Fuel and Fuel System Related or unusual design features on one model design feature, or should any other Requirements: Due to the use of turbine of airplane. It is not a rule of general model already included on the same fuel, this airplane must comply with the applicability and affects only the type certificate be modified to requirements in § 23.951(c). In addition, applicant who applied to the FAA for

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approval of these features on the in § 23.361(c)(3) will result in limit 5. Powerplant—Fuel System—Fuel airplane. torques on the mount that are equivalent Flow (Compliance with § 23.955 The substance of these special to or less than those imposed by a requirements): conditions has been subjected to the conventional gasoline reciprocating In place of § 23.955(c), the engine fuel notice and comment period in several engine. system must provide at least 100 prior instances and has been derived 2. Flutter—(Compliance with § 23.629 percent of the fuel flow required by the without substantive change from those (e)(1) and (e)(2) requirements): engine, or the fuel flow required to previously issued. It is unlikely that The flutter evaluation of the airplane prevent engine damage, if that flow is prior public comment would result in a done in accordance with § 23.629 must greater than 100 percent. The fuel flow significant change from the substance include — rate must be available to the engine contained herein. Therefore, because a (a) Whirl mode degree of freedom under each intended operating delay would significantly affect the which takes into account the stability of condition and maneuver. The certification of the airplane, which is the plane of rotation of the propeller conditions may be simulated in a imminent, the FAA has determined that and significant elastic, inertial, and suitable mockup. This flow must be prior public notice and comment are aerodynamic forces, and shown in the most adverse fuel feed unnecessary and impracticable, and (b) Propeller, engine, engine mount condition with respect to altitudes, good cause exists for adopting these and airplane structure stiffness and attitudes, and any other condition that special conditions upon issuance. The damping variations appropriate to the is expected in operation. FAA is requesting comments to allow particular configuration, and 6. Powerplant—Fuel System—Fuel (c) The flutter investigation will interested persons to submit views that system hot weather operation include showing the airplane is free may not have been submitted in (Compliance with § 23.961 from flutter with one cylinder response to the prior opportunities for requirements): inoperative. comment described above. In place of compliance with § 23.961, 3. Powerplant—Installation the applicant must comply with the List of Subjects in 14 CFR Part 23 (Provisions similar to § 23.901(d)(1) for following: turbine engines): Aircraft, Aviation safety, Signs and a. Each fuel system must be free from Considering the vibration symbols. vapor lock when using fuel at its critical characteristics of diesel engines, the temperature, with respect to vapor applicant must comply with the Citation formation, when operating the airplane The authority citation for these following: a. Each diesel engine installation must in all critical operating and special conditions is as follows: be constructed and arranged to result in environmental conditions for which Authority: 49 U.S.C. 106(g), 40113, and vibration characteristics that— approval is requested. For turbine fuel, 44701; 14 CFR 21.16 and 21.101; and 14 CFR (1) Do not exceed those established or for aircraft equipped with diesel 11.38 and 11.19. during the type certification of the cycle engines that use turbine or diesel engine; and type fuels, the initial temperature must The Special Conditions ° ¥ ° ° (2) Do not exceed vibration be 110 F, 0 , +5 or the maximum Accordingly, pursuant to the characteristics that a previously outside air temperature for which authority delegated to me by the certificated airframe structure has been approval is requested, whichever is Administrator, the following special approved for— more critical. conditions are issued as part of the type (i) Unless such vibration b. The fuel system must be in an certification basis for Cessna Model characteristics are shown to have no operational configuration that will yield J182T airplanes. effect on safety or continued the most adverse, that is, conservative 1. Engine torque (Provisions similar to airworthiness, or results. § 23.361(b)(1) and (c)(3)): (ii) Unless mitigated to an acceptable c. To comply with this requirement, a. For diesel engine installations, the level by utilization of isolators, dampers the applicant must use the turbine fuel engine mounts and supporting structure clutches, and similar provisions, so that requirements and must substantiate must be designed to withstand the unacceptable vibration levels are not these by flight-testing, as described in following: imposed on the previously certificated Advisory Circular AC 23–8C, Flight Test (1) A limit engine torque load structure. Guide for Certification of Part 23 imposed by sudden engine stoppage due 4. Powerplant—Fuel System—Fuel Airplanes. to malfunction or structural failure. system with water saturated fuel 7. Powerplant—Fuel system—Fuel (2) The effects of sudden engine (Compliance with § 23.951(c) tank filler connection (Compliance with stoppage may alternatively be mitigated requirements): § 23.973(f) requirements): to an acceptable level by utilization of Considering the fuel types used by In place of compliance with isolators, dampers clutches, and similar diesel engines, the applicant must § 23.973(e), the applicant must comply provisions, so unacceptable load levels comply with the following: with the following: are not imposed on the previously a. Each fuel system for a diesel engine For airplanes that operate on turbine certificated structure. must be capable of sustained operation or diesel type fuels, the inside diameter b. The limit engine torque to be throughout its flow and pressure range of the fuel filler opening must be no considered under § 23.361(a) must be with fuel initially saturated with water smaller than 2.95 inches. obtained by multiplying the mean at 80° F and having 0.75cc of free water 8. Powerplant—Fuel system—Fuel torque by a factor of four for diesel cycle per gallon added and cooled to the most tank outlet (Compliance with engines. critical condition for icing likely to be § 23.977(a)(2) requirements): (1) If a factor of less than four is used, encountered in operation. In place of compliance with it must be shown that the limit torque b. Methods of compliance that are § 23.977(a)(1), the applicant will comply imposed on the engine mount is acceptable for turbine engine fuel with the following: consistent with the provisions of systems requirements of § 23.951(c) are There must be a fuel strainer for the § 23.361(c). In other words, it must be also considered acceptable for this fuel tank outlet or for the booster pump. shown that the use of the factors listed requirement. This strainer must, for diesel engine

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powered airplanes, prevent the passage applicable, etc.). This is in addition to (a) Vibration levels imposed on the of any object that could restrict fuel flow the existing requirements specified by airframe must be less than or equivalent or damage any fuel system component. § 23.1521(b) and (c). If any of those to those of the gasoline engine; or 9. Equipment—General—Powerplant limits can be exceeded, there must be (b) Any vibration level higher than Instruments (Compliance with § 23.1305 continuous indication to the flight crew that imposed on the airframe by the and § 91.205 requirements): of the status of that parameter with replaced gasoline engine must be In place of compliance with appropriate limitation markings. considered in the modification and the § 23.1305, the applicant will comply Instead of compliance with effects on the technical areas covered by with the following: § 23.1521(d), the applicant must comply the following paragraphs must be Below are required powerplant with the following: investigated: instruments: The minimum fuel designation (for 14 CFR part 23, §§ 23.251; 23.613; (a) A fuel quantity indicator for each diesel engines) must be established so it 23.627; 23.629 (or CAR 3.159, as fuel tank, installed in accordance with is not less than required for the applicable to various models); 23.572; § 23.1337(b). operation of the engine within the 23.573; 23.574 and 23.901. (b) An oil pressure indicator. limitations in paragraphs (b) and (c) of Vibration levels imposed on the (c) An oil temperature indicator. § 23.1521. airframe can be mitigated to an (d) An oil quantity measuring device 11. Markings and Placards— acceptable level by utilization of for each oil tank which meets the Miscellaneous markings and placards— isolators, damper clutches, and similar requirements of § 23.1337(d). Fuel, and oil, filler openings provisions so that unacceptable (e) A tachometer indicating propeller (Compliance with § 23.1557(c)(1)(ii) vibration levels are not imposed on the speed. requirements): previously certificated structure. (f) An indicating means for the fuel Instead of compliance with 14. Powerplant Installation—One strainer or filter required by § 23.997 to § 23.1557(c)(1)(i), the applicant must cylinder inoperative: indicate the occurrence of Tests or analysis, or a combination of comply with the following: contamination of the strainer or filter methods, must show that the airframe Fuel filler openings must be marked before it reaches the capacity can withstand the shaking or vibratory at or near the filler cover with— established in accordance with forces imposed by the engine if a For diesel engine-powered § 23.997(d). cylinder becomes inoperative. Diesel airplanes— Alternately, no indicator is required if engines of conventional design typically (a) The words ‘‘Jet Fuel’’; and the engine can operate normally for a have extremely high levels of vibration (b) The permissible fuel designations, specified period with the fuel strainer when a cylinder becomes inoperative. or references to the Airplane Flight exposed to the maximum fuel Data must be provided to the airframe Manual (AFM) for permissible fuel contamination as specified in MIL– installer/modifier so either appropriate designations. 5007D. Additionally, provisions for design considerations or operating (c) A warning placard or note that replacing the fuel filter at this specified procedures, or both, can be developed to states the following or similar: period (or a shorter period) are included prevent airframe and propeller damage. in the maintenance schedule for the ‘‘Warning—this airplane is equipped 15. Powerplant Installation—High engine installation. with an aircraft diesel engine; service Energy Engine Fragments: (g) Power setting either in percentage with approved fuels only.’’ It may be possible for diesel engine power, or through the use of manifold The colors of this warning placard cylinders (or portions thereof) to fail pressure. should be black and white. and physically separate from the engine (h) Fuel temperature indicator. 12. Powerplant—Fuel system—Fuel- at high velocity (due to the high internal (i) Fuel flow indicator (engine fuel Freezing: pressures). This failure mode will be consumption). If the fuel in the tanks cannot be considered possible in engine designs If percentage power is used in place shown to flow suitably under all with removable cylinders or other non- of manifold pressure, compliance to possible temperature conditions, then integral block designs. The following is § 91.205 will be accomplished with the fuel temperature limitations are required: following: required. These limitations will be (a) It must be shown that the engine The diesel engine has no manifold considered as part of the essential construction type (massive or integral pressure gauge as required by § 91.205, operating parameters for the aircraft. block with non-removable cylinders) is in its place, the engine instrumentation Limitations will be determined as inherently resistant to liberating high as installed is to be approved as follows: energy fragments in the event of a equivalent. The Type Certification Data (a) The takeoff temperature limitation catastrophic engine failure; or Sheet (TCDS) is to be modified to show must be determined by testing or (b) It must be shown by the design of power indication will be accepted to be analysis to define the minimum fuel the engine, that engine cylinders, other equivalent to the manifold pressure cold-soaked temperature that the engine components or portions thereof indication. airplane can operate on. (fragments) cannot be shed or blown off 10. Operating Limitations and (b) The minimum operating of the engine in the event of a Information—Powerplant limitations— temperature limitation must be catastrophic engine failure; or Fuel grade or designation (Compliance determined by testing to define the (c) It must be shown that all possible with § 23.1521 requirements): minimum acceptable operating liberated engine parts or components do All engine parameters that have limits temperature after takeoff (with not have adequate energy to penetrate specified by the engine manufacturer for minimum takeoff temperature engine cowlings; or takeoff or continuous operation must be established in (1) above). (d) Assuming infinite fragment investigated to ensure they remain 13. Powerplant Installation— energy, and analyzing the trajectory of within those limits throughout the Vibration levels: the probable fragments and components, expected flight and ground envelopes Vibration levels throughout the any hazard due to liberated engine parts (e.g. maximum and minimum fuel engine operating range must be or components will be minimized and temperatures, ambient temperatures, as evaluated and: the possibility of crew injury is

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eliminated. Minimization must be Operations, M–30, West Building default growing larger and larger with considered during initial design and not Ground Floor, Room W12–140, 1200 each inspection. presented as an analysis after design New Jersey Avenue SE., Washington, We have determined that the current completion. DC 20590. 5-year repetitive ‘‘cutout’’ inspections Issued in Kansas City, Missouri, on May 8, For service information identified in will eventually weaken the wing 2013. this AD, contact Slingsby Advanced structure and could result in an unsafe Earl Lawrence, Composites Ltd., Ings Lane, condition. We concur with the change to the annual endoscope inspection. Manager, Small Airplane Directorate, Aircraft Kirkbymoorside, North Yorkshire, Certification Service. England YO62 6EZ; telephone: Comments [FR Doc. 2013–11731 Filed 5–15–13; 8:45 am] +44(0)1751 432474; Internet: None. You may review copies of the referenced We gave the public the opportunity to BILLING CODE 4910–13–P service information at the FAA, Small participate in developing this AD. We Airplane Directorate, 901 Locust, have considered the comments received. John Wells, Michael Hoke, Chad Croix DEPARTMENT OF TRANSPORTATION Kansas City, Missouri 64106. For information on the availability of this Wille, and one anonymous commenter Federal Aviation Administration material at the FAA, call (816) 329– support the NPRM (78 FR 14467, March 4148. 6, 2013). 14 CFR Part 39 FOR FURTHER INFORMATION CONTACT: Jim Conclusion [Docket No. FAA–2013–0220; Directorate Rutherford, Aerospace Engineer, FAA, We reviewed the relevant data, Identifier 2013–CE–002–AD; Amendment Small Airplane Directorate, 901 Locust, considered the comments received, and 39–17451; AD 2013–09–09] Room 301, Kansas City, Missouri 64106; determined that air safety and the RIN 2120–AA64 telephone: (816) 329–4165; fax: (816) public interest require adopting the AD 329–4090; email: as proposed except for minor editorial Airworthiness Directives; Slingsby [email protected]. changes. We have determined that these Sailplanes Ltd. Sailplanes SUPPLEMENTARY INFORMATION: minor changes: • Are consistent with the intent that AGENCY: Federal Aviation Discussion was proposed in the NPRM (78 FR Administration (FAA), Department of 14467, March 6, 2013) for correcting the Transportation (DOT). We issued a notice of proposed unsafe condition; and ACTION: Final rule. rulemaking (NPRM) to amend 14 CFR • part 39 to include an AD that would Do not add any additional burden SUMMARY: We are superseding an apply to the specified products. That upon the public than was already existing airworthiness directive (AD) for NPRM was published in the Federal proposed in the NPRM (78 FR 14467, all Slingsby Sailplanes Ltd. Models Dart Register on March 6, 2013 (78 FR March 6, 2013). T.51, Dart T.51/17, and Dart T.51/17R 14467), and proposed to supersede AD Costs of Compliance sailplanes equipped with aluminum 98–22–15, Amendment 39–10863 (63 We estimate that this AD will affect alloy spar booms. This AD results from FR 58624, November 2, 1998). 10 products of U.S. registry. We also mandatory continuing airworthiness Since we issued AD 98–22–15, information (MCAI) issued by an estimate that it will take about 40 work- Amendment 39–10863 (63 FR 58624, hours per product to comply with the aviation authority of another country to November 2, 1998), Slingsby Aviation identify and correct an unsafe condition initial inspection requirement retained Ltd. has revised the related service from AD 98–22–15, Amendment 39– on an aviation product. The MCAI information to remove the 5-year describes the unsafe condition as an 10863 (63 FR 58624, November 2, 1998) repetitive ‘‘cutout’’ inspection and to in this AD. The average labor rate is $85 incident of glue joint failure on a add a repetitive annual inspection using starboard wing caused by water entering per work-hour. an endoscope. The endoscope Based on these figures, we estimate the area of the airbrake box that resulted inspection method would be done using the cost of the initial inspection in delamination and corrosion in the existing drain holes in the lower wing required in this AD on U.S. operators to area of the aluminum alloy spar booms skin. be $34,000, or $3,400 per product. and the wing attach fittings. We are Using revised service information is We also estimate that it will take issuing this AD to require actions to mandatory within the United Kingdom about 2 work-hours per product to address the unsafe condition on these airworthiness system. It is not necessary comply with the new repetitive products. for the Civil Aviation Authority (CAA), inspection requirement in this AD. The DATES: This AD is effective June 20, which is the aviation authority for the average labor rate is $85 per work-hour. 2013. United Kingdom, to issue an AD to Based on these figures, we estimate The Director of the Federal Register mandate the use of new service the cost of the new repetitive inspection approved the incorporation by reference information. required in this AD on U.S. operators to of a certain publication listed in the AD AD action is the only way the FAA be $1,700, or $170 per product. as of June 20, 2013. can mandate the use of new service We have no way of determining the The Director of the Federal Register information; however, owners/operators number of repetitive inspections an approved the incorporation by reference may request approval from the FAA to owner/operator will incur over the life of a certain other publication listed in use an alternative method of compliance of the sailplane or the number of this AD as of December 14, 1998 (63 FR (AMOC). sailplanes that will need repairs. 58624, November 2, 1998). Several U.S. operators have ADDRESSES: You may examine the AD complained that the repetitive 5-year Authority for This Rulemaking docket on the Internet at http:// ‘‘cutout’’ inspection in the wooden wing Title 49 of the United States Code www.regulations.gov or in person at the skin, currently required by AD 98–22– specifies the FAA’s authority to issue Docket Management Facility, U.S. 15, Amendment 39–10863 (63 FR rules on aviation safety. Subtitle I, Department of Transportation, Docket 58624, November 2, 1998), was by section 106, describes the authority of

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