Final Special Conditions: AmSafe Aviation; Inflatable Restraints Installation; Approved Model List of Normal and Utility Category Airplanes, and Agricultural Airplanes Certificated in the Normal/Utility/Restricted Category, 66163-66171 [E8-26663]

Download as PDF Federal Register / Vol. 73, No. 217 / Friday, November 7, 2008 / Rules and Regulations Rules does not affect the collections of information outlined in the Interim Rule nor does it affect the estimated burden set forth in the Interim Rule. List of Subjects in 12 CFR Part 370 Banks, Banking, Bank deposit insurance, Holding companies, National banks, Reporting and recordkeeping requirements, Savings associations. ■ For the reasons stated above, The Board of Directors of the Federal Deposit Insurance Corporation amends 12 CFR part 370 as follows: PART 370—TEMPORARY LIQUIDITY GUARANTEE PROGRAM 1. The authority citation for part 370 continues to read as follows: ■ Authority: 12 U.S.C. 1813(l), 1813(m), 1817(i), 1818, 1819(a) (Tenth); 1820(f), 1821(a); 1821(c); 1821(d); 1823(c)(4). § 370.2 [Amended] 2. Amend § 370.2 as follows: A. In paragraph (f), remove ‘‘November 12’’ and replace it with ‘‘December 5’’. ■ B. In paragraph (g), remove ‘‘November 12’’ and replace it with ‘‘December 5’’ and remove ‘‘November 13’’ wherever it appears and replace it with ‘‘December 6’’. ■ ■ § 370.3 [Amended] 3. Amend § 370.3 as follows: In paragraphs (b) and (f), remove ‘‘November 12’’ wherever it appears and replace it with ‘‘December 5’’. ■ ■ § 370.5 [Amended] 4. Amend § 370.5 as follows: A. In paragraphs (a), (c), (f), and (j), remove ‘‘November 12’’ wherever it appears and replace it with ‘‘December 5’’. ■ B. In paragraph (h), remove ‘‘December 1’’ and replace it with ‘‘December 19’’. ■ 5. Amend § 370.6 by revising paragraphs (a), (b)(1), (b)(2), and (c) to read as follows: ■ ■ pwalker on PROD1PC71 with RULES § 370.6 Assessments under the Debt Guarantee Program. (a) Waiver of assessment for certain initial periods. No eligible entity shall pay any assessment associated with the debt guarantee program for the period from October 14, 2008 through November 12, 2008. An eligible entity that opts out of the program on or before December 5, 2008 will not pay any assessment under the program. (b) * * * (1) Any eligible entity that does not opt out of the Debt Guarantee Program on or before December 5, 2008, as VerDate Aug<31>2005 16:21 Nov 06, 2008 Jkt 217001 provided in § 370.5, and that issues any guaranteed debt during the period from October 14, 2008 through December 5, 2008 which is still outstanding on December 5, 2008, shall notify the FDIC of that issuance via the FDIC’s ebusiness Web site FDICconnect on or before December 19, 2008, and the eligible entity’s Chief Financial Officer or equivalent shall certify that the issuances outstanding at each point of time did not exceed the guaranteed amount limit as set forth in § 370.3. (2) Any eligible entity that does not opt out of the program and that issues guaranteed debt after December 5, 2008, shall notify the FDIC of that issuance via the FDIC’s e-business Web site FDICconnect within the time period specified by the FDIC. The eligible entity’s Chief Financial Officer or equivalent shall certify that the issuance of guaranteed debt does not exceed the guarantee limit as set forth in § 370.3. * * * * * (c) Initiation of assessments. Assessments, calculated in accordance with paragraph (d) of this section, will accrue, with respect to each eligible entity that does not opt out of the debt guarantee program on or before December 5, 2008. (1) Beginning on November 13, 2008, on all senior unsecured debt, other than overnight debt instruments, issued by it on or after October 14, 2008 that is still outstanding on November 13, 2008; (2) Beginning on November 13, 2008, on all senior unsecured debt, other than overnight debt instruments, issued by it on or after November 13, 2008 and before December 6, 2008; and (3) Beginning on December 6, 2008, on all senior unsecured debt issued by it on or after December 6, 2008. ■ 6. Amend § 370.7 by revising paragraphs (a) and (b) to read as follows: § 370.7 Assessments under the Transaction Account Guarantee Program. (a) Waiver of assessment for certain initial periods. No eligible entity shall pay any assessment associated with the transaction account guarantee program for the period from October 14, 2008, through November 12, 2008. An eligible entity that opts out of the program on or before December 5, 2008 will not pay any assessment under the program (b) Initiation of assessments. Beginning on November 13, 2008 each eligible entity that does not opt out of the transaction account guarantee program on or before December 5, 2008 will be required to pay the FDIC assessments on all deposit amounts in noninterest-bearing transaction accounts PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 66163 calculated in accordance with paragraph (c) of this section. * * * * * Federal Deposit Insurance Corporation. Robert E. Feldman, Executive Secretary. [FR Doc. E8–26569 Filed 11–4–08; 4:15 pm] BILLING CODE 6714–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 23 [Docket No. CE285, Special Conditions No. 23–225A–SC] Final Special Conditions: AmSafe Aviation; Inflatable Restraints Installation; Approved Model List of Normal and Utility Category Airplanes, and Agricultural Airplanes Certificated in the Normal/Utility/Restricted Category Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions; request for comments. AGENCY: SUMMARY: These special conditions are issued for AmSafe Aviation to amend the list of approved models. These airplanes, as modified by AmSafe Aviation, will have novel and unusual design features associated with the lap belt or shoulder harness portion of the safety belt, which contains an integrated airbag device. The applicable airworthiness regulations do not contain adequate and 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 airworthiness standards. The effective date of these amended special conditions is October 31, 2008. Comments must be received on or before December 8, 2008. ADDRESSES: Mail two copies of your comments on these amended special conditions to: Federal Aviation Administration (FAA), Regional Counsel, ACE–7, Attention: Rules Docket, Docket No. CE285, 901 Locust, Room 506, Kansas City, Missouri 64106, or you may deliver two copies to the Regional Counsel at the above address. Mark your comments: Docket No. CE285. You may inspect comments in the Rules Docket weekdays, except Federal holidays, between 7:30 a.m. and 4 p.m. DATES: E:\FR\FM\07NOR1.SGM 07NOR1 66164 Federal Register / Vol. 73, No. 217 / Friday, November 7, 2008 / Rules and Regulations Mr. Bob Stegeman, Federal Aviation Administration, Small Airplane Directorate, Aircraft Certification Service, ACE–111, 901 Locust, Kansas City, Missouri, 816–329–4140, fax 816– 329–4090, e-mail Robert.Stegeman@faa.gov. FOR FURTHER INFORMATION CONTACT: 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 amended special conditions effective upon issuance. SUPPLEMENTARY INFORMATION: Comments Invited We invite interested persons to participate in the making of these special conditions by submitting such written data, views, or arguments as they may desire. Identify the regulatory docket or notice number and submit the comments in duplicate to the address specified above. All comments received on or before the closing date for comments will be considered by the Administrator. The special conditions may be changed in light of the comments received. All comments received will be available in the Rules Docket for examination by interested persons, both before and after the closing date for comments. A report summarizing each substantive public contact with FAA personnel concerning this rulemaking will be filed in the docket. Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this notice must include a self-addressed, stamped postcard on which the following statement is made: ‘‘Comments to CE285.’’ The postcard will be date stamped and returned to the commenter. pwalker on PROD1PC71 with RULES Background On June 18, 2008, AmSafe Aviation, 1043 North 47th Avenue, Phoenix, AZ 85043, applied to add several more models to an existing supplemental type certificate. The AML STC allows for the installation of inflatable restraints in airplane models included herein that were certificated prior to the dynamic seat rule specified in 14 CFR part 23, § 23.562. AmSafe Aviation has previously applied for and obtained an Approved VerDate Aug<31>2005 16:21 Nov 06, 2008 Jkt 217001 Model List (AML) Supplemental Type Certificate (STC) for the installation of Inflatable Two-, Three-, Four- or FivePoint Restraint Safety Belts with an Integrated Airbag Device in airplanes certificated in the Part 23 Normal/ Utility and Restricted-Agricultural categories. This special condition includes additional normal and utility category aircraft. The inflatable restraint system is either a two-, three-, four-, or five-point safety belt restraint system consisting of a shoulder harness and a lap belt with an inflatable airbag attached to either the lap belt or the shoulder harness. The inflatable portion of the restraint system will rely on sensors to electronically activate the inflator for deployment. The inflatable restraint system will be made available on the pilot, co-pilot, and passenger seats of these airplanes. If an emergency landing occurs, the airbag will inflate and provide a protective cushion between the occupant’s head and structure within the airplane. This will reduce the potential for head and torso injury. The inflatable restraint behaves in a manner that is similar to an automotive airbag. However, in this case, the airbag is integrated into the lap or shoulder belt. While airbags and inflatable restraints are standard in the automotive industry, the use of an inflatable restraint system is novel for aircraft operations. The FAA has determined that this project will be accomplished on the basis of not lowering the current level of safety of the airplanes’ original certification basis. The FAA has two primary safety concerns with the installation of airbags or inflatable restraints: • That they perform properly under foreseeable operating conditions; and • That they do not perform in a manner or at such times as to impede the pilot’s ability to maintain control of the airplane or constitute a hazard to the airplane or occupants. The latter point has the potential to be the more rigorous of the requirements. An unexpected deployment while conducting the takeoff or landing phases of flight may result in an unsafe condition. The unexpected deployment may either startle the pilot, or it may generate a force sufficient to cause a sudden movement of the control yoke. Either action could result in a loss of control of the airplane, the consequences of which are magnified due to the low operating altitudes during these phases of flight. This consideration is of special concern for aircraft designated for agricultural use because these aircraft spend a majority PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 of their flight time at low altitudes. The FAA has considered this when establishing these amended special conditions. The inflatable restraint system relies on sensors to electronically activate the inflator for deployment. These sensors could be susceptible to inadvertent activation, causing deployment in a potentially unsafe manner. The consequences of an inadvertent deployment must be considered in establishing the reliability of the system. AmSafe Aviation must show that the effects of an inadvertent deployment in flight are not a hazard to the airplane or that an inadvertent deployment is extremely improbable. In addition, general aviation and agricultural aircraft are susceptible to a large amount of cumulative wear and tear on a restraint system. It is likely that the potential for inadvertent deployment increases as a result of this cumulative damage. Therefore, the impact of wear and tear on inadvertent deployment must be considered. Due to the effects of this cumulative damage, a life limit must be established for the appropriate system components in the restraint system design. There are additional factors to be considered to minimize the chances of inadvertent deployment. General aviation airplanes are exposed to a unique operating environment, since the same airplane may be used by both experienced and student pilots. The effect of this environment on inadvertent deployment must be understood. Therefore, qualification testing of the firing hardware/software must consider the following: • The airplane vibration levels appropriate for general aviation and agricultural airplanes; and • The inertial loads that result from typical flight/ground maneuvers, gusts, hard landings and flight maneuvering unique to both general aviation and agricultural aircraft operations. Any tendency for the firing mechanism to activate as a result of these loads or acceleration levels is unacceptable. Other influences on inadvertent deployment include high intensity electromagnetic fields (HIRF) and lightning. Since the sensors that trigger deployment are electronic, they must be protected from the effects of these threats. To comply with HIRF and lightning requirements, the AmSafe Aviation inflatable restraint system is considered a critical system, since its inadvertent deployment could have a hazardous effect on the airplane. Given the level of safety of the retrofitted airplane occupant restraints, E:\FR\FM\07NOR1.SGM 07NOR1 Federal Register / Vol. 73, No. 217 / Friday, November 7, 2008 / Rules and Regulations the inflatable restraint system must show that it will offer an equivalent level of protection in the event of an emergency landing. If a deployment occurs, the restraint must still be at least as strong as a Technical Standard Order approved belt and shoulder harnesses. There is no requirement for the inflatable portion of the restraint to offer protection during multiple impacts. The inflatable restraint system must deploy and provide protection for each occupant during crash conditions as specified in the original certification basis. Therefore, the test emergency landing loads identified in the original certification basis of the airplane must be used to satisfy this requirement. It must be shown that the inflatable restraint will deploy and provide protection under crash conditions as specified in the original certification basis. Compliance will be demonstrated using the test condition specified in the original certification basis. It must be shown that the crash sensor will trigger when exposed to a rapidly applied deceleration, like an actual crash event. Therefore, the test crash pulses identified in § 23.562 must be used to satisfy this requirement, although the peak ‘‘G’’ may be reduced to a level meeting the original certification requirements of the aircraft. Testing to these pulses will demonstrate that the crash sensor will trigger when exposed to a rapidly applied deceleration, like an actual crash event. It is possible a wide range of occupants will use the inflatable restraint. Thus, the protection offered by this restraint should be effective for occupants that range from the fifth percentile female to the ninety-fifth percentile male. In support of this operational capability, there must be a means to verify the integrity of this system before each flight. As an option, AmSafe Aviation can establish inspection intervals where they have demonstrated the system to be reliable between these intervals. An inflatable restraint may be ‘‘armed’’ even though no occupant is using the seat. While there will be means to verify the integrity of the system before flight, it is also prudent to require that unoccupied seats with active restraints not constitute a hazard to any occupant. This will protect any individual performing maintenance inside the cockpit while the aircraft is on the ground. The restraint must also provide suitable visual warnings that would alert rescue personnel to the presence of an inflatable restraint system. In addition, the design must prevent the inflatable seatbelt from being incorrectly buckled and/or installed such that the airbag would not properly deploy. As an alternative, AmSafe Aviation may show that such deployment is not hazardous to the occupant and will still provide the required protection. The cabins of the various model airplanes identified in these special conditions are confined areas, and the FAA is concerned that noxious gases may accumulate if an airbag deploys. When deployment does occur, either by design or inadvertently, there must not be a release of hazardous quantities of gas or particulate matter into the cockpit. An inflatable restraint should not increase the risk already associated with fire. Therefore, the inflatable restraint should be protected from the effects of fire, so that an additional hazard is not created by, for example, a rupture of the inflator. Finally, the airbag is likely to have a large volume displacement, and it may impede the egress of an occupant. Since the bag deflates to absorb energy, it is likely that the inflatable restraint would be deflated at the time an occupant would attempt egress. However, it is appropriate to specify a time interval after which the inflatable restraint may not impede rapid egress. Ten seconds 66165 has been chosen as reasonable time. This time limit will offer a level of protection throughout the impact event. Special conditions for the installation of AAIR systems on other certificated airplanes have been issued and no substantive public comments were received. Since the same special conditions were issued multiple times for different model airplanes with no substantive public comments, the FAA began issuing direct final special conditions with an invitation for public comment. This was done to eliminate the waiting period for public comments and to allow AmSafe Aviation to proceed with the project. These previous special conditions were typically issued for a single model airplane or for variants of a model from a single airplane manufacturer, and required dynamic testing of each AAIR system installation for showing compliance. Since AmSafe Aviation has previously demonstrated by dynamic testing, and has the supporting data, that the Electronics Module Assembly (EMA) and inflator assembly will function as intended in a simulated dynamic emergency landing, it is not necessary to repeat the test for each airplane model shown in these amended special conditions. Type Certification Basis Under the provisions of 14 CFR part 21, § 21.101, AmSafe Aviation must show that affected airplane models, as changed, continue to meet the applicable provisions of the regulations incorporated by reference in the Type Certificate Numbers listed below or the applicable regulations in effect on the date of application for the change. The regulations incorporated by reference in the type certificate data sheet are commonly referred to as the original ‘‘type certification basis’’ and can be found in the Type Certificate Data Sheets for the numbers listed below. The following models are covered by this amended special condition: LIST OF ALL AIRPLANE MODELS AND APPLICABLE TCDS Model 1 Aerostar ........................... pwalker on PROD1PC71 with RULES Make PA–60–600 (Aerostar 600) ....................... PA–60–601 (Aerostar 601) ....................... PA–60–601P (Aerostar 601P) .................. PA–60–602P (Aerostar 602P) .................. PA–60–700P (Aerostar 700P) .................. 10A ............................................................ 402 ............................................................ 1 All American .................... 1 American Champion (Champion). VerDate Aug<31>2005 16:21 Nov 06, 2008 Jkt 217001 PO 00000 Frm 00023 TCDS Certification basis Aerostar Aircraft Corporation. A17WE, Revision 22 ...... 14 CFR PART 23. All American Aircraft, Inc American Champion Aircraft Corp. A–792 ............................. A3CE, Revision 5 .......... CAR 3. CAR 3. TC holder Fmt 4700 Sfmt 4700 E:\FR\FM\07NOR1.SGM 07NOR1 66166 Federal Register / Vol. 73, No. 217 / Friday, November 7, 2008 / Rules and Regulations LIST OF ALL AIRPLANE MODELS AND APPLICABLE TCDS—Continued Make 1 American Champion (Bellanca) (Champion) (Aeronca). 1 American Champion (Bellanca) (Trytek) (Aeronca). 1 American Champion (Bellanca) (Trytek) (Aeronca). 1 VARGA (Morrisey) .......... 1 Bellanca .......................... TC holder TCDS 7AC, 7ACA, 7EC, 7GCB, S7AC, S7EC, 7GCBA (L–16A), 7BCM, 7ECA, 7GCBC (L–16B), 7CCM, 7FC, 7HC, S7CCM, 7GC, 7JC, 7DC, 7GCA, 7KC, S7DC, 7GCAA, 7KCAB. 11AC, S11AC, 11BC, S11BC ................... American Champion Aircraft Corp. A–759, Revision 67 ....... CAR 4a. American Champion Aircraft Corp. A–761, Revision 17 ....... CAR 4a. 11CC, S11CC ........................................... American Champion Aircraft Corporation. A–796, Revision 14 ....... CAR 3. 2150, 2150A, 2180 ................................... 14–13, 14–13–2, 14–13–3, 14–13–3W .... Augustair, Inc. ................ Bellanca Aircraft Corporation. Bellanca Aircraft Corporation. Cessna Aircraft Company. Cessna Aircraft Company. Cessna Aircraft Company. 4A19, Revision 9 ........... A–773, Revision 10 ....... CAR 3. CAR 4a. TC716 ............................ CAR 4a. A–768, Revision 34 ....... CAR 4a. 5A2, Revision 21 ........... CAR 3. 3A19, Revision 44 ......... CAR 3. Cessna Aircraft Company. Cessna Aircraft Company. A–799, Revision 54 ....... CAR 3. 3A12, Revision 73 ......... CAR 3. Cessna Aircraft Company. 3A17, Revision 45 ......... CAR 3. Cessna Aircraft pany. Cessna Aircraft pany. Cessna Aircraft pany. Cessna Aircraft pany. Com- A13CE, Revision 24 ...... Com- A20CE, Revision 21 ...... Com- 5A6, Revision 66 ........... 14 CFR PART 23. 14 CFR PART 23. CAR 3. Com- 3A13, Revision 64 ......... CAR 3. Com- 3A24, Revision 37 ......... CAR 3. Com- A9CE, Revision 27 ........ Com- A–790, Revision 36 ....... 14 CFR PART 23. CAR 3. Com- A4CE, Revision 43 ........ CAR 3. Cessna Aircraft Company. Cessna Aircraft Company. A37CE, Revision 12 ...... 3A21, Revision 46 ......... 14 CFR PART 23. CAR 3. Cessna Aircraft Company. 3A10, Revision 62 ......... CAR 3. 1 Bellanca .......................... 14–9, 14–9L .............................................. 1 Cessna ............................ 120, 140 .................................................... 1 Cessna ............................ 140A .......................................................... 1 Cessna ............................ 150, 150J, 150A, 150K, 150B, A150K, 150C, 150L, 150D, A150L, 150E, 150M, 150F, A150M, 150G, 152, 150H, A152. 170, 170A, 170B ....................................... 1 Cessna ............................ 1 Cessna ............................ 1 Cessna ............................ 172, 172I, 172A, 172K, 172B, 172L, 172C, 172M, 172D, 172N, 172E, 172P, 172F (USAF T–41A), 172Q, 172G, 172H, (USAF T–41A). 175, 175A, 175B, 175C, P172D, R172E (USAF T–41B) (USAF T–41C and D), R172F (USAF T–41D), R172G (USAF T–41C or D), R172H (USAF T–41D), R172J, R172K, 172RG. 177, 177A, 177B ....................................... Cessna ............................... 177RG ....................................................... Cessna ............................... 180, 180E, 180A, 180F, 180B, 180G, 180C, 180H, 180D, 180J, 180E, 180K. 182, 182K, 182A, 182L, 182B, 182M, 182C, 182N, 182D, 182P, 182E, 182Q, 182F, 182R, 182G, R182, 182H, T182, 182J, TR182. 185, A185E, 185A, A185F, 185B, 185C, 185D, 185E. 188, 188A, 188B, A188, A188A, A188B, T188C. 190 (LC–126A,B,C), 195, 195A, 195B ..... 1 Cessna ............................ 1 Cessna ............................ 1 Cessna ............................ Cessna AgWagon .............. 1 Cessna ............................ 1 Cessna ............................ 1 Cessna ............................ pwalker on PROD1PC71 with RULES 1 Cessna ............................ 1 Cessna ............................ VerDate Aug<31>2005 Certification basis Model 206, U206B, TP206D, P206, U206C, TP206E, P206A, U206D, TU206A, P206B, U206E, TU206B, P206C, U206F, TU206C, P206D, U206G, TU206D, P206E, TP206A, TU206E, U206, TP206B, TU206F, U206A, TP206C, TU206G. 208, 208A, 208B ....................................... 210, 210K, 210A, T210K, 210B, 210L, 210C, T210L, 210D, 210M, 210E, T210M, 210F, 210N, T210F, P210N, 210G, T210N, T210G, 210R, 210H, P210R, T210H, T210R, 210J, 210–5 (205), T210J, 210–5A (205A). 310, 310J, 310A(USAF U–3A),310J–1, 310B, E310J, 310C, 310K, 310D, 310L, 310E(USAF U–3B), 310N, 310F, 310P, 310G, T310P, 310H, 310Q, E310H, T310Q, 310I, 310R, T310R. 17:28 Nov 06, 2008 Jkt 217001 PO 00000 Frm 00024 Fmt 4700 Cessna Aircraft pany. Cessna Aircraft pany. Cessna Aircraft pany. Cessna Aircraft pany. Sfmt 4700 E:\FR\FM\07NOR1.SGM 07NOR1 Federal Register / Vol. 73, No. 217 / Friday, November 7, 2008 / Rules and Regulations 66167 LIST OF ALL AIRPLANE MODELS AND APPLICABLE TCDS—Continued Make Model 1 Cessna ............................ 1 Cessna ............................ 320, 320F, 320–1, 335, 320A, 340, 320B, 340A, 320C, 320D, 320E. 321 (Navy OE–2) ...................................... 1 Cessna ............................ 336 ............................................................ 1 Cessna ............................ 1 Cessna ............................ 337A (USAF 02B), T337E, 337B, 337F, M337B (USAF 02A), T337F, T337B, 337G, 337C, T337G, T337C, 337H, 337D, P337H, T337D, T337H, T337H– SP. 401, 401A, 401B, 402, 402A, 402B, 402C, 411, 411A, 414, 414A, 421, 421A, 421B, 421C, 425. 404, 406 .................................................... 1 Cessna ............................ 441 ............................................................ 1 Commander Aircraft ........ Diamond ............................. Model 112, Model 114, Model 112TC, Model 112B, Model 112TCA, Model 114A, Model 114B, Model 114TC. DA20–A1, DA20–C1 ................................. 1 Great Lakes .................... 2T–1A, 2T–1A–1, 2T–1A–2 ...................... 1 Helio (Taylorcraft) ............ 15A, 20 ..................................................... 1 Learjet ............................. 1 Lockheed ......................... 23 .............................................................. 402–2 ........................................................ 1 Land-Air (TEMCO) (Luscombe). 1 Maule .............................. 11A, 11E ................................................... 1 Cessna ............................ 1 Mooney ........................... 1 Interceptor (Aero Commander) (Meyers). 1 Beech .............................. 1 Beech .............................. 1 Beech .............................. pwalker on PROD1PC71 with RULES 1 Beech .............................. 1 Beech .............................. VerDate Aug<31>2005 TC holder Bee Dee M–4, M–5–180C, MXT–7–160, M–4–180V, M–4 M–5–200, MX–7– 180A, M–4C, M–5–210C, MXT–7– 180A, M–4S, M–5–210TC, MX–7– 180B, M–4T, M–5–220C, M–7–235B, M–4–180C, M–5–235C, M–7–235A, M–4–180S, M–6–180, M–7–235C, M– 4–180T, M–6–235, MX–7–180C, M–4– 210, M–7–235, M–7–260, M–4–210C, MX–7–235, MT–7–260, M–4–210S, MX–7–180, M–7–260C, M–4–210T, MX–7–420, M–7–420AC, M–4–220, MXT–7–180, MX–7–160C, M–4–220C, MT–7–235, MX–7–180AC, M–4–220S, M–8–235, M–7–420A, M–4–220T, MX– 7–160, MT–7–420. M20, M20A, M20B, M20C, M20D, M20E, M20F, M20G, M20J, M20K (Up to S/N 25–2000), M20L. 200, 200A, 200B, 200C, 200D, 400 ......... 35–33, J35, 35–A33, K35, 35–B33, M35, 35–C33, N35, 35–C33A, P35, E33, S35, E33A, V35, E33C, V35A, F33, V35B, F33A, 36, F33C, A36, G33, A36TC, H35, B36TC, G36. 45 (YT–34), A45 (T–34A, B–45), D45 (T– 34B). 19A, B23, B19, C23, M19A, A24, 23, A24R, A23, B24R, A23A, C24R, A23– 19, A23–24. 3N, 3NM, 3TM, JRB–6, D18C, D18S, E18S, E18S–9700, G18S, H18, C– 45G, TC–45G, C–45H, TC–45H, TC– 45J or UC–45J (SNB–5), RC–45J (SNB–5P). 35, A35, E35, B35, F35, C35, G35, D35, 35R. 16:21 Nov 06, 2008 Jkt 217001 PO 00000 Frm 00025 Fmt 4700 Cessna Aircraft pany. Cessna Aircraft pany. Cessna Aircraft pany. Cessna Aircraft pany. TCDS Certification basis Com- 3A25, Revision 25 ......... CAR 3. Com- 3A11, Revision 6 ........... CAR 3. Com- A2CE, Revision 7 .......... CAR 3. Com- A6CE, Revision 40 ........ CAR 3/14 CFR PART 23. Cessna Aircraft Company. A7CE, Revision 46 ........ CAR 3. Cessna Aircraft Company. Cessna Aircraft Company. Commander Aircraft Company. A25CE, Revision 11 ...... 14 CFR PART 23. 14 CFR PART 23. 14 CFR PART 23. Diamond Aircraft Industries, Inc.. Great Lakes Aircraft Company, LLC. TA4CH, Revision 14 ...... Helio Aircraft Corporation. Learjet Inc ...................... Lockheed Aircraft International. Luscombe Aircraft Corporation. Maule Aerospace Technology, Inc. 3A3, Revision 7 ............. 14 CFR PART 23. Aeronautical Bulletin No. 7–A. CAR 4a. A5CE, Revision 10 ........ 2A11, Revision 4 ........... CAR 3. CAR 3. A–804, Revision 14 ....... CAR 3. 3A23, Revision 30 ......... CAR 3. Mooney Airplane Company, Inc. 2A3, Revision 47 ........... CAR 3. Prop-Jets, Inc ................. 3A18, Revision 16 ......... CAR 3. Raytheon Aircraft Company. 3A15, Revision 90 ......... CAR 3. Raytheon Aircraft Company. Raytheon Aircraft Company. 5A3, Revision 25 ........... CAR 03. A1CE, Revision 34 ........ CAR 3. Raytheon Aircraft Company. A–765 ............................. Revision 74 CAR 03. Raytheon Aircraft Company. A–777, Revision 57 ....... CAR 03. Sfmt 4700 A28CE, Revision 12 ...... A12SO, Revision 21 ...... A18EA, Revision 10 ....... E:\FR\FM\07NOR1.SGM 07NOR1 66168 Federal Register / Vol. 73, No. 217 / Friday, November 7, 2008 / Rules and Regulations LIST OF ALL AIRPLANE MODELS AND APPLICABLE TCDS—Continued TCDS Certification basis Raytheon Aircraft Company. A24CE, Revision 91 ...... 14 CFR PART 23. Raytheon Aircraft Company. 3A16, Revision 81 ......... CAR 3. Raytheon Aircraft Company. Raytheon Aircraft Company. Reims Aviation S.A ........ A12CE, Revision 23 ...... 14 CFR PART 23. 14 CFR PART 23. CAR 10/CAR 3. SOCATA-GROUPE AEROSPATIALE. Sky International Inc. (Aviat Aircraft, Inc.). Taylorcraft Aviation, LLC A51EU, Revision 14 ...... 1A9, Revision 19 ........... 14 CFR PART 23. 14 CFR PART 23. CAR 3. Taylorcraft Aviation, LLC A–696, Revision 22 ....... CAR 04. Taylorcraft, Inc ............... A–699, Revision 5 ......... CAR 4a. The Don Luscombe Aviation History Foundation, Inc. Sierra Hotel Aero, Inc .... A–694, Revision 23 ....... CAR 4a. A–782, Revision 51 ....... CAR 3. Piper Aircraft Inc ............ Piper Aircraft Inc ............ ATC 660, Revision 0 ..... A–691, Revision 33 ....... Not listed. CAR 4a. FS 2003 Corporation ..... A–780, Revision 13 ....... CAR 3. PA–14 ....................................................... FS 2002 Corporation ..... A–797, Revision 11 ....... CAR 3. PA–15 ....................................................... PA–16, PA–16S ........................................ PA–17 ....................................................... PA–18, PA–18S, PA–18A, PA–18S ‘‘125’’, PA–18AS ‘‘125’’, PA–18A ‘‘135’’, PA–18S ‘‘135’’, PA–18AS ‘‘135’’, PA–18 ‘‘150’’, PA–18A ‘‘150’’, PA–18S ‘‘150’’, PA–18AS ‘‘150’’, PA– 19S. PA–20, PA–20–115, PA–20–135, PA– 20S, PA–20S–115, PA–20S–135. Piper Aircraft Inc ............ Piper Aircraft Inc ............ Piper Aircraft Inc ............ The New Piper Aircraft, Inc. A–800, Revision 11 ....... 1A1, Revision 13 ........... A–805, Revision 12 ....... 1A2, Revision 37 ........... CAR CAR CAR CAR Piper Aircraft Inc ............ 1A4, Revision 24 ........... CAR 3. Make Model 1 Raytheon ......................... 1 Beech .............................. 200, A100–1 (U–21J), 200C, A200 (C– 12A), 200CT, A200 (C–12C), 200T, A200C (UC–12B), B200, A200CT (C– 12D), B200C, A200CT (FWC–12D), B200CT, A200CT (C–12F), B200T, A200CT (RC–12D), 300, A200CT (RC– 12G), 300LW, A200CT (RC–12H), B300, A200CT (RC–12K), B300C, A200CT (RC–12P), 1900, A200CT (RC–12Q), 1900C, B200C (C–12F), 1900D, B200C (UC–12M), B200C (C– 12R), B200C (UC–12F), 1900C (C– 12J). B95A, D55, D95A, D55A, E95, E55, 95– 55, E55A, 95–A55, 56TC, 95–B55, A56TC, 95–B55A, 58, 95–B55B (T– 42A), 58A, 95–C55, 95, 95–C55A, B95, G58. 60, A60, B60 ............................................. 1 Beech .............................. 58P, 58PA, 58TC, 58TCA ........................ 1 Cessna ............................ CESSNA F172D ....................................... CESSNA F172E ....................................... CESSNA F172F ........................................ CESSNA F172G ....................................... CESSNA F172H ....................................... CESSNA F172K ....................................... CESSNA F172L ........................................ CESSNA F172M ....................................... CESSNA F172N ....................................... CESSNA F172P ....................................... TB 9, TB 10, TB 20, TB 21, TB 200 ........ 1 Beech .............................. 1 Socata ............................. 1 Pitts ................................. 1 Taylorcraft ....................... 1 Taylorcraft ....................... 1 Taylorcraft ....................... 1 Luscombe ........................ Sierra Hotel Aero, Inc. (Navion). Piper ................................... Piper ................................... pwalker on PROD1PC71 with RULES FS 2003 Corporation (Piper). FS 2002 Corporation (Piper). Piper ................................... Piper ................................... Piper ................................... 2 Piper ................................ Piper ................................... VerDate Aug<31>2005 TC holder S–1S, S–1T, S–2, S–2A, S–2S, S–2B, S–2C. 19, F19, F21, F21A, F21B, F22, F22A, F22B, F22C. BC, BCS12–D, BCS, BC12–D1, BC–65, BCS12-D1, BCS–65, BC12D–85, BC12–65 (Army L–2H), BCS12D–85, BCS12–65, BC12D–4–85, BC12-D, BCS12D–4–85. (Army L–2G) BF, BFS, BF–60,BFS–60, BF–65, BFS–65,(Army L–2K) BF 12– 65, BFS–65. 8, 8D, 8A, 8E, 8B, 8F, 8C, T–8F .............. Navion (L–17A), Navion A (L–17B) (L– 17C),Navion B, Navion D, Navion E, Navion F, Navion G, Navion H. J–3 ............................................................ J3C–40, J3C–50, J3C–50S, J3C–65, J3C–65S, PA–11, PA–11S. PA–12, PA–12S ........................................ 16:21 Nov 06, 2008 Jkt 217001 PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 A23CE, Revision 14 ...... A4EU, Revision 11 ........ A8SO, Revision 21 ........ E:\FR\FM\07NOR1.SGM 07NOR1 3. 3. 3. 3. Federal Register / Vol. 73, No. 217 / Friday, November 7, 2008 / Rules and Regulations 66169 LIST OF ALL AIRPLANE MODELS AND APPLICABLE TCDS—Continued Certification basis Make Model TC holder TCDS Piper ................................... PA–22, PA–22–108, PA–22–135, PA– 22–150, PA–22–160, PA–22S–135, PA–22S–150, PA–22S–160. PA–23, PA–23–160, PA–23–235, PA– 23–250. PA–24, PA–24–250,PA–24–260, PA–24– 400. PA–28–140, PA–28–151, PA–28–150, PA–28–161, PA–28–160, PA–28–181, PA–28–180, PA–28R–201, PA–28– 235, PA–28R–201T, PA–28S–160, PA–28–236, PA–28S–180, PA–28RT– 201, PA–28R–180, PA–28RT–201T, PA–28R–200, PA–28–201T. PA–30, PA–39, PA–40 ............................. Piper Aircraft Inc ............ 1A6, Revision 34 ........... CAR 3. Piper Aircraft Inc ............ 1A10, Revision 51 ......... CAR 3. Piper Aircraft Inc ............ 1A15, Revision 34 ......... CAR 3. The New Piper Aircraft, Inc. 2A13, Revision 47 ......... CAR 3. The New Piper Aircraft, Inc. The New Piper Aircraft, Inc. A1EA, Revision 16 ......... CAR 3. A3SO, Revision 29 ........ CAR 3. The New Inc. The New Inc. The New Inc. The New Inc. Piper Aircraft, A7SO, Revision 16 ........ Piper Aircraft, A8EA, Revision 22 ......... 14 CFR PART 23. CAR 3. Piper Aircraft, A9SO, Revision 9 .......... Piper Aircraft, A10SO, Revision 12 ...... Piper ................................... Piper ................................... 1 Piper ................................ 1 Piper ................................ 1 Piper ................................ 1 Piper ................................ 1 Piper ................................ PA–32–260, PA–32R–301 (SP), PA–32– 300, PA–32R–301 (HP),PA–32S–300, PA–32R–301T, PA–32R–300, PA–32– 301, PA–32RT–300, PA–32–301T, PA– 32RT–300T, PA–32–301FT, PA–32– 301XTC. PA–34–200, PA–34–200T, PA–34–220T 1 Piper ................................ PA–31P, PA–31T, PA–31T1, PA–31T2, PA–31T3, PA–31P–350. PA–36–285, PA–36–300, PA–36–375 ..... 1 Piper ................................ PA–36–285, PA–36–300, PA–36–375 ..... Piper ................................... PA–38–112 ............................................... 1 Piper ................................ PA–44–180, PA–44–180T ........................ 1 Piper ................................ PA–31, PA–31–300, PA–31–325, PA– 31–350. PA–42, PA–42–720, PA–42–1000 ........... 14 CFR PART 23. 14 CFR PART 21/14 CFR PART 23. 14 CFR PART 23. 14 CFR PART 23. CAR 3. A18SO, Revision 4 ........ PA–46–310P, PA–46–350P, PA–46– 500TP. PA–46R–350T .......................................... The New Piper Aircraft, Inc. The New Piper Aircraft, Inc. The New Piper Aircraft, Inc. The New Piper Aircraft, Inc. The New Piper Aircraft, Inc. Piper Aircraft, Inc ........... 1 Tiger Aircraft LLC (American General). 1 Tiger Aircraft .................... AA–1, AA–1A, AA–1B, AA–1C ................. Tiger Aircraft LLC .......... A11EA, Revision 10 ....... AA–5, AA–5A, AA–5B, AG–5B ................. Tiger Aircraft LLC .......... A16EA, Revision 13 ....... 1 Twin Commander ............ 500, 500–A, 500–B, 500–U, 520, 560, 560–A, 560–E, 500–S. 560–F, 681, 680, 690, 680E, 685, 680F, 690A, 720, 690B, 680FL, 690C, 680FL(P), 690D, 680T, 695, 680V, 695A, 680W, 695B. 108, 108–1, 108–2, 108–3, 108–5 ........... Twin Commander Aircraft Corporation. Twin Commander Aircraft Corporation. 6A1, Revision 45 ........... 14 CFR 23. 14 CFR 23. 14 CFR 23. 14 CFR 23. 14 CFR 23. CAR 3. 2A4, Revision 46 ........... CAR 3. Univair Aircraft Corporation. Univair Aircraft Corporation. A–767, Revision 27 ....... CAR 3. A–787, Revision 33 ....... CAR 3. Univair Aircraft Corporation. A–718, Revision 29 ....... CAR 4a. 1 Piper ................................ 1 Piper ................................ Piper ................................... 1 Twin Commander ............ 1 Univair (Stinson) .............. 1 Univair ............................. pwalker on PROD1PC71 with RULES 1 Univair (Mooney) ............. (ERCO) 415–D ......................................... (ERCO) E (ERCO) G (Forney) F–1 (Forney) F–1A (Alon) A–2 (Alon) A2–A (Mooney) M10 (ERCO) 415–C, (ERCO) 415–CD ............ A19SO, Revision 9 ........ A20SO, Revision 10 ...... A23SO, Revision 17 ...... A25SO, Revision 14 ...... A25SO, Revision 16 ...... The following aircraft are certified in the restricted category: VerDate Aug<31>2005 16:21 Nov 06, 2008 Jkt 217001 PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 E:\FR\FM\07NOR1.SGM 07NOR1 PART PART PART PART PART 66170 Federal Register / Vol. 73, No. 217 / Friday, November 7, 2008 / Rules and Regulations LIST OF ALL AIRPLANE MODELS AND APPLICABLE TCDS Make Model TC holder TCDS Certification basis Air Tractor .......................... AT–250, AT–300, AT–301, AT–302, AT– 400, AT–400A. AT–401, AT–401A, AT–401B, AT–402, AT–402A, AT–402B, AT–501, AT–502, AT–502A, AT–502B, AT–503, AT– 503A. AT–802A, AT–802, AT–602 ..................... Air Tractor, Inc ............... A9SW, Revision 12 ........ Air Tractor, Inc ............... A17SW, Revision 10 ...... 14 CFR PART 23. 14 CFR PART 23. Air Tractor, Inc ............... A19SW, Revision 4 ........ Allied Ag Cat Productions, Inc. 1A16, Revision 24 ......... Gippsland Aeronautics ....... G–164, G–164A, G–164B, G–164B with 73″, G–164B–15T, G–164B–34T, G– 164B–20T, G–164C, G–164D, G–164D with 73″ wing gap. GA200 ....................................................... A00001LA, Revision 1 ... 2 Piper ................................ PA–18A, PA–18A ‘‘135’’, PA–18A ‘‘150’’ LAVIA S.A. (Piper) ............. PA–25, PA–25–235, PA–25–260 ............. Thrush Aircraft, Inc. (Snow, Rockwell, Ayres). Thrush Aircraft, Inc. (Snow, Rockwell, Ayres). Thrush Aircraft, Inc. (Snow, Rockwell, Ayres). S–2B, S–2C, 600–S2C ............................. Gippsland Aeronautics Pty. Ltd.. The New Piper Aircraft, Inc. Latino Americana De ´ Aviacion (LAVIA) S.A. Thrush Aircraft, Inc ........ Air Tractor .......................... Air Tractor .......................... Allied Ag Cat ...................... Weatherly ........................... 3 Ximango .......................... 600 S–2D, S–2R, S2R–T34, S2R–T15, S2R–T11, S2R–R3S, S2R–R1340. 600 S2D, S2R–R1340, S2R–G10, S–2R, S2R–R1820, S2R–G5, S2R–T34, S2R–T65, S2R–G1, S2R–T15, S2RHG–T65, S2RHG–T34, S2R–R3S, S2R–T45, S2R–T660, S2R–T11, S2R– G6. 620, 620TP, 620A, 620B, 620B–TG ........ AMT–100, AMT–200, AMT–300, AMT– 200S. 14 CFR PART 23. CAR 8. AR–7, Revision 11 ......... 14 CFR PART 23. CAR 8. 2A10, Revision 24 ......... CAR 8. 2A7, Revision 16 ........... CAR 8. Thrush Aircraft, Inc ........ A3SW, Revision 18 ........ CAR 3. Thrush Aircraft, Inc ........ A4SW, Revision 28 ........ CAR 8. Weatherly Aircraft Company. Aeromot-Industria Mecanico Metalugica Ltd. A26WE, Revision 7 ........ 14 CFR PART 23. 14 CFR PART 23. TG00004AT, Revision 4 pwalker on PROD1PC71 with RULES Aircraft identified with a 1 have special conditions for AmSafe Aviation Inflatable Restraints published under Special Conditions 23–182–SC. Piper PA–18A, PA–18A ‘‘135’’ and PA–18A ‘‘150’’ (identified with a 2) are type certificated in Normal/Utility Category on TCDS 1A2 and in Restricted Category on TCDS AR–7. The same aircraft may be operated under either TCDS in accordance with the restrictions listed on TCDS AR– 7. Ximango (identified with a 3) is certificated in the Utility Category. For all the models listed above, the certification basis also includes all exemptions, if any; equivalent level of safety findings, if any; and the other special conditions. If the Administrator finds that the applicable airworthiness regulations (i.e., part 23 as amended) do not contain adequate or appropriate safety standards for the AmSafe Aviation, inflatable restraint as installed on these models because of a novel or unusual design feature, special conditions are prescribed under the provisions of § 21.16. Special conditions, as appropriate, as defined in § 11.19, are issued in accordance with § 11.38, and become part of the type certification basis in accordance with § 21.101. Special conditions are initially applicable to the model for which they are issued. Should the applicant apply for a supplemental type certificate to modify any other model included on the same type certificate to incorporate the same novel or unusual design feature, VerDate Aug<31>2005 16:21 Nov 06, 2008 Jkt 217001 the special conditions would also apply to that model under the provisions of § 21.101. Novel or Unusual Design Features The various airplane models will incorporate the following novel or unusual design feature: The AmSafe Aviation Inflatable Two-, Three-, Four-, or Five-Point Restraint Safety Belt with an Integrated Airbag Device. The purpose of the airbag is to reduce the potential for injury in the event of an accident. In a severe impact, an airbag will deploy from the restraint, in a manner similar to an automotive airbag. The airbag will deploy between the head of the occupant and airplane interior structure. This will, therefore, provide some protection to the head of the occupant. The restraint will rely on sensors to electronically activate the inflator for deployment. The Code of Federal Regulations state performance criteria for seats and restraints in an objective manner. However, none of these criteria are PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 adequate to address the specific issues raised concerning inflatable restraints. Therefore, the FAA has determined that, in addition to the requirements of part 21 and part 23, special conditions are needed to address the installation of this inflatable restraint. Accordingly, these amended special conditions are adopted for the various airplane models equipped with the AmSafe Aviation, two-, three-, four, or five-point inflatable restraint. Other conditions may be developed, as needed, based on further FAA review and discussions with the manufacturer and civil aviation authorities. Applicability As discussed above, these amended special conditions are applicable to the Approved Model List (AML) above. Should AmSafe Aviation apply at a later date for a supplemental type certificate to modify any other model included on the type certificates listed above to incorporate the same novel or unusual E:\FR\FM\07NOR1.SGM 07NOR1 Federal Register / Vol. 73, No. 217 / Friday, November 7, 2008 / Rules and Regulations design feature, the special conditions would apply to that model as well. Conclusion This action affects only certain novel or unusual design features on the previously identified airplane models. It is not a rule of general applicability, and it affects only the applicant who applied to the FAA for approval of these features on the airplane. 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 these airplane models, as modified by AmSafe Aviation, is imminent, the FAA finds that good cause exists to make these amended special conditions effective upon issuance. List of Subjects in 14 CFR Part 23 Aircraft, Aviation safety, Signs and symbols. Citation The authority citation for these amended special conditions is as follows: ■ pwalker on PROD1PC71 with RULES Authority: 49 U.S.C. 106(g), 40113 and 44701; 14 CFR 21.16 and 21.101; and 14 CFR 11.38 and 11.19. The Amended Special Conditions The FAA has determined that this project will be accomplished on the basis of not lowering the current level of safety of the occupant restraint system for the airplane models listed in these special conditions. Accordingly, the FAA is issuing the following amended special conditions as part of the type certification basis for these models, as modified by AmSafe, Aviation. Inflatable Two-, Three-, Four-, or FivePoint Restraint Safety Belt with an Integrated Airbag Device Installed in an Airplane Model. 1a. It must be shown that the inflatable restraint will provide restraint protection under the emergency landing conditions specified in the original certification basis of the airplane. Compliance will be demonstrated using the static test conditions specified in the original certification basis for each airplane. 1b. It must be shown that the crash sensor will trigger when exposed to a rapidly applied deceleration, like an actual emergency landing event. Therefore, compliance may be demonstrated using the deceleration pulse specified in § 23.562, which may be modified as follows: I. The peak longitudinal deceleration may be reduced; however, the onset rate of the VerDate Aug<31>2005 16:21 Nov 06, 2008 Jkt 217001 deceleration must be equal to or greater than the emergency landing pulse identified in § 23.562. II. The peak longitudinal deceleration must be above the deployment threshold of the sensor, and equal or greater than the forward static design longitudinal load factor required by the original certification basis of the airplane. 2. The inflatable restraint must provide adequate protection for each occupant. In addition, unoccupied seats that have an active restraint must not constitute a hazard to any occupant. 3. The design must prevent the inflatable restraint from being incorrectly buckled and/or incorrectly installed such that the airbag would not properly deploy. Alternatively, it must be shown that such deployment is not hazardous to the occupant and will provide the required protection. 4. It must be shown that the inflatable restraint system is not susceptible to inadvertent deployment as a result of wear and tear or the inertial loads resulting from in-flight or ground maneuvers (including gusts and hard landings) that are likely to be experienced in service. 5. It must be extremely improbable for an inadvertent deployment of the restraint system to occur, or an inadvertent deployment must not impede the pilot’s ability to maintain control of the airplane or cause an unsafe condition (or hazard to the airplane). In addition, a deployed inflatable restraint must be at least as strong as a Technical Standard Order (C22g or C114) restraint. 6. It must be shown that deployment of the inflatable restraint system is not hazardous to the occupant or will not result in injuries that could impede rapid egress. This assessment should include occupants whose restraints are loosely fastened. 7. It must be shown that an inadvertent deployment that could cause injury to a sitting person is improbable. In addition, the restraint must also provide suitable visual warnings that would alert rescue personnel to the presence of an inflatable restraint system. 8. It must be shown that the inflatable restraint will not impede rapid egress of the occupants 10 seconds after its deployment. 9. For the purposes of complying with HIRF and lightning requirements, the inflatable restraint system is considered a critical system since its deployment could have a hazardous effect on the airplane. 10. It must be shown that the inflatable restraints will not release hazardous quantities of gas or particulate matter into the cabin. PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 66171 11. The inflatable restraint system installation must be protected from the effects of fire such that no hazard to occupants will result. 12. There must be a means to verify the integrity of the inflatable restraint activation system before each flight or it must be demonstrated to reliably operate between inspection intervals. 13. A life limit must be established for appropriate system components. 14. Qualification testing of the internal firing mechanism must be performed at vibration levels appropriate for a general aviation airplane. Issued in Kansas City, Missouri on October 31, 2008. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–26663 Filed 11–6–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HOMELAND SECURITY U.S. Customs and Border Protection 19 CFR Part 102 [CBP Dec. 08–42] Technical Corrections Relating to the Rules of Origin for Goods Imported Under the NAFTA and for Textile and Apparel Products Correction In rule document E8–25734 beginning on page 64518 in the issue of Thursday, October 30, 2008, make the following correction: §102.21 [Corrected] On page 64539, in §102.21, in the table, in the first column, in the firstentry, ‘‘6209.20.1000....’’should read ‘‘6209.20.1000–’’. [FR Doc. Z8–25734 Filed 11–6–08; 8:45 am] BILLING CODE 1505–01–D DEPARTMENT OF LABOR Mine Safety and Health Administration 30 CFR Parts 56, 57, and 71 RIN 1219–AB24 Asbestos Exposure Limit Mine Safety and Health Administration, Labor. ACTION: Final rule, technical amendment. AGENCY: E:\FR\FM\07NOR1.SGM 07NOR1

Agencies

[Federal Register Volume 73, Number 217 (Friday, November 7, 2008)]
[Rules and Regulations]
[Pages 66163-66171]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-26663]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. CE285, Special Conditions No. 23-225A-SC]

Final Special Conditions: AmSafe Aviation; Inflatable Restraints
Installation; Approved Model List of Normal and Utility Category
Airplanes, and Agricultural Airplanes Certificated in the Normal/
Utility/Restricted Category

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions; request for comments.

-----------------------------------------------------------------------

SUMMARY: These special conditions are issued for AmSafe Aviation to
amend the list of approved models. These airplanes, as modified by
AmSafe Aviation, will have novel and unusual design features associated
with the lap belt or shoulder harness portion of the safety belt, which
contains an integrated airbag device. The applicable airworthiness
regulations do not contain adequate and 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
airworthiness standards.

DATES: The effective date of these amended special conditions is
October 31, 2008. Comments must be received on or before December 8,
2008.

ADDRESSES: Mail two copies of your comments on these amended special
conditions to: Federal Aviation Administration (FAA), Regional Counsel,
ACE-7, Attention: Rules Docket, Docket No. CE285, 901 Locust, Room 506,
Kansas City, Missouri 64106, or you may deliver two copies to the
Regional Counsel at the above address. Mark your comments: Docket No.
CE285. You may inspect comments in the Rules Docket weekdays, except
Federal holidays, between 7:30 a.m. and 4 p.m.

[[Page 66164]]

FOR FURTHER INFORMATION CONTACT: Mr. Bob Stegeman, Federal Aviation
Administration, Small Airplane Directorate, Aircraft Certification
Service, ACE-111, 901 Locust, Kansas City, Missouri, 816-329-4140, fax
816-329-4090, e-mail Robert.Stegeman@faa.gov.

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 amended special conditions effective upon issuance.

Comments Invited

We invite interested persons to participate in the making of these
special conditions by submitting such written data, views, or arguments
as they may desire. Identify the regulatory docket or notice number and
submit the comments in duplicate to the address specified above. All
comments received on or before the closing date for comments will be
considered by the Administrator. The special conditions may be changed
in light of the comments received. All comments received will be
available in the Rules Docket for examination by interested persons,
both before and after the closing date for comments. A report
summarizing each substantive public contact with FAA personnel
concerning this rulemaking will be filed in the docket. Commenters
wishing the FAA to acknowledge receipt of their comments submitted in
response to this notice must include a self-addressed, stamped postcard
on which the following statement is made: ``Comments to CE285.'' The
postcard will be date stamped and returned to the commenter.

Background

On June 18, 2008, AmSafe Aviation, 1043 North 47th Avenue, Phoenix,
AZ 85043, applied to add several more models to an existing
supplemental type certificate. The AML STC allows for the installation
of inflatable restraints in airplane models included herein that were
certificated prior to the dynamic seat rule specified in 14 CFR part
23, Sec. 23.562.
AmSafe Aviation has previously applied for and obtained an Approved
Model List (AML) Supplemental Type Certificate (STC) for the
installation of Inflatable Two-, Three-, Four- or Five-Point Restraint
Safety Belts with an Integrated Airbag Device in airplanes certificated
in the Part 23 Normal/Utility and Restricted-Agricultural categories.
This special condition includes additional normal and utility
category aircraft.
The inflatable restraint system is either a two-, three-, four-, or
five-point safety belt restraint system consisting of a shoulder
harness and a lap belt with an inflatable airbag attached to either the
lap belt or the shoulder harness. The inflatable portion of the
restraint system will rely on sensors to electronically activate the
inflator for deployment. The inflatable restraint system will be made
available on the pilot, co-pilot, and passenger seats of these
airplanes.
If an emergency landing occurs, the airbag will inflate and provide
a protective cushion between the occupant's head and structure within
the airplane. This will reduce the potential for head and torso injury.
The inflatable restraint behaves in a manner that is similar to an
automotive airbag. However, in this case, the airbag is integrated into
the lap or shoulder belt. While airbags and inflatable restraints are
standard in the automotive industry, the use of an inflatable restraint
system is novel for aircraft operations.
The FAA has determined that this project will be accomplished on
the basis of not lowering the current level of safety of the airplanes'
original certification basis. The FAA has two primary safety concerns
with the installation of airbags or inflatable restraints:
That they perform properly under foreseeable operating
conditions; and
That they do not perform in a manner or at such times as
to impede the pilot's ability to maintain control of the airplane or
constitute a hazard to the airplane or occupants.
The latter point has the potential to be the more rigorous of the
requirements. An unexpected deployment while conducting the takeoff or
landing phases of flight may result in an unsafe condition. The
unexpected deployment may either startle the pilot, or it may generate
a force sufficient to cause a sudden movement of the control yoke.
Either action could result in a loss of control of the airplane, the
consequences of which are magnified due to the low operating altitudes
during these phases of flight. This consideration is of special concern
for aircraft designated for agricultural use because these aircraft
spend a majority of their flight time at low altitudes. The FAA has
considered this when establishing these amended special conditions.
The inflatable restraint system relies on sensors to electronically
activate the inflator for deployment. These sensors could be
susceptible to inadvertent activation, causing deployment in a
potentially unsafe manner. The consequences of an inadvertent
deployment must be considered in establishing the reliability of the
system. AmSafe Aviation must show that the effects of an inadvertent
deployment in flight are not a hazard to the airplane or that an
inadvertent deployment is extremely improbable.
In addition, general aviation and agricultural aircraft are
susceptible to a large amount of cumulative wear and tear on a
restraint system. It is likely that the potential for inadvertent
deployment increases as a result of this cumulative damage. Therefore,
the impact of wear and tear on inadvertent deployment must be
considered. Due to the effects of this cumulative damage, a life limit
must be established for the appropriate system components in the
restraint system design.
There are additional factors to be considered to minimize the
chances of inadvertent deployment. General aviation airplanes are
exposed to a unique operating environment, since the same airplane may
be used by both experienced and student pilots. The effect of this
environment on inadvertent deployment must be understood. Therefore,
qualification testing of the firing hardware/software must consider the
following:
The airplane vibration levels appropriate for general
aviation and agricultural airplanes; and
The inertial loads that result from typical flight/ground
maneuvers, gusts, hard landings and flight maneuvering unique to both
general aviation and agricultural aircraft operations.
Any tendency for the firing mechanism to activate as a result of
these loads or acceleration levels is unacceptable.
Other influences on inadvertent deployment include high intensity
electromagnetic fields (HIRF) and lightning. Since the sensors that
trigger deployment are electronic, they must be protected from the
effects of these threats. To comply with HIRF and lightning
requirements, the AmSafe Aviation inflatable restraint system is
considered a critical system, since its inadvertent deployment could
have a hazardous effect on the airplane.
Given the level of safety of the retrofitted airplane occupant
restraints,

[[Page 66165]]

the inflatable restraint system must show that it will offer an
equivalent level of protection in the event of an emergency landing. If
a deployment occurs, the restraint must still be at least as strong as
a Technical Standard Order approved belt and shoulder harnesses. There
is no requirement for the inflatable portion of the restraint to offer
protection during multiple impacts.
The inflatable restraint system must deploy and provide protection
for each occupant during crash conditions as specified in the original
certification basis. Therefore, the test emergency landing loads
identified in the original certification basis of the airplane must be
used to satisfy this requirement. It must be shown that the inflatable
restraint will deploy and provide protection under crash conditions as
specified in the original certification basis. Compliance will be
demonstrated using the test condition specified in the original
certification basis. It must be shown that the crash sensor will
trigger when exposed to a rapidly applied deceleration, like an actual
crash event. Therefore, the test crash pulses identified in Sec.
23.562 must be used to satisfy this requirement, although the peak
``G'' may be reduced to a level meeting the original certification
requirements of the aircraft. Testing to these pulses will demonstrate
that the crash sensor will trigger when exposed to a rapidly applied
deceleration, like an actual crash event.
It is possible a wide range of occupants will use the inflatable
restraint. Thus, the protection offered by this restraint should be
effective for occupants that range from the fifth percentile female to
the ninety-fifth percentile male.
In support of this operational capability, there must be a means to
verify the integrity of this system before each flight. As an option,
AmSafe Aviation can establish inspection intervals where they have
demonstrated the system to be reliable between these intervals.
An inflatable restraint may be ``armed'' even though no occupant is
using the seat. While there will be means to verify the integrity of
the system before flight, it is also prudent to require that unoccupied
seats with active restraints not constitute a hazard to any occupant.
This will protect any individual performing maintenance inside the
cockpit while the aircraft is on the ground. The restraint must also
provide suitable visual warnings that would alert rescue personnel to
the presence of an inflatable restraint system.
In addition, the design must prevent the inflatable seatbelt from
being incorrectly buckled and/or installed such that the airbag would
not properly deploy. As an alternative, AmSafe Aviation may show that
such deployment is not hazardous to the occupant and will still provide
the required protection.
The cabins of the various model airplanes identified in these
special conditions are confined areas, and the FAA is concerned that
noxious gases may accumulate if an airbag deploys. When deployment does
occur, either by design or inadvertently, there must not be a release
of hazardous quantities of gas or particulate matter into the cockpit.
An inflatable restraint should not increase the risk already
associated with fire. Therefore, the inflatable restraint should be
protected from the effects of fire, so that an additional hazard is not
created by, for example, a rupture of the inflator.
Finally, the airbag is likely to have a large volume displacement,
and it may impede the egress of an occupant. Since the bag deflates to
absorb energy, it is likely that the inflatable restraint would be
deflated at the time an occupant would attempt egress. However, it is
appropriate to specify a time interval after which the inflatable
restraint may not impede rapid egress. Ten seconds has been chosen as
reasonable time. This time limit will offer a level of protection
throughout the impact event.
Special conditions for the installation of AAIR systems on other
certificated airplanes have been issued and no substantive public
comments were received. Since the same special conditions were issued
multiple times for different model airplanes with no substantive public
comments, the FAA began issuing direct final special conditions with an
invitation for public comment. This was done to eliminate the waiting
period for public comments and to allow AmSafe Aviation to proceed with
the project.
These previous special conditions were typically issued for a
single model airplane or for variants of a model from a single airplane
manufacturer, and required dynamic testing of each AAIR system
installation for showing compliance. Since AmSafe Aviation has
previously demonstrated by dynamic testing, and has the supporting
data, that the Electronics Module Assembly (EMA) and inflator assembly
will function as intended in a simulated dynamic emergency landing, it
is not necessary to repeat the test for each airplane model shown in
these amended special conditions.

Type Certification Basis

Under the provisions of 14 CFR part 21, Sec. 21.101, AmSafe
Aviation must show that affected airplane models, as changed, continue
to meet the applicable provisions of the regulations incorporated by
reference in the Type Certificate Numbers listed below or the
applicable regulations in effect on the date of application for the
change. The regulations incorporated by reference in the type
certificate data sheet are commonly referred to as the original ``type
certification basis'' and can be found in the Type Certificate Data
Sheets for the numbers listed below. The following models are covered
by this amended special condition:

[[Page 66166]]

1 American Champion (Bellanca) 7AC, 7ACA, 7EC, 7GCB, S7AC, S7EC, American Champion A-759, Revision 67...... CAR 4a.
(Champion) (Aeronca). 7GCBA (L-16A), 7BCM, 7ECA, 7GCBC (L- Aircraft Corp.
16B), 7CCM, 7FC, 7HC, S7CCM, 7GC,
7JC, 7DC, 7GCA, 7KC, S7DC, 7GCAA,
7KCAB.
1 American Champion (Bellanca) 11AC, S11AC, 11BC, S11BC............. American Champion A-761, Revision 17...... CAR 4a.
(Trytek) (Aeronca). Aircraft Corp.
1 American Champion (Bellanca) 11CC, S11CC.......................... American Champion A-796, Revision 14...... CAR 3.
(Trytek) (Aeronca). Aircraft Corporation.
1 VARGA (Morrisey)................. 2150, 2150A, 2180.................... Augustair, Inc.......... 4A19, Revision 9........ CAR 3.
1 Bellanca......................... 14-13, 14-13-2, 14-13-3, 14-13-3W.... Bellanca Aircraft A-773, Revision 10...... CAR 4a.
Corporation.
1 Bellanca......................... 14-9, 14-9L.......................... Bellanca Aircraft TC716................... CAR 4a.
Corporation.
1 Cessna........................... 120, 140............................. Cessna Aircraft Company. A-768, Revision 34...... CAR 4a.
1 Cessna........................... 140A................................. Cessna Aircraft Company. 5A2, Revision 21........ CAR 3.
1 Cessna........................... 150, 150J, 150A, 150K, 150B, A150K, Cessna Aircraft Company. 3A19, Revision 44....... CAR 3.
150C, 150L, 150D, A150L, 150E, 150M,
150F, A150M, 150G, 152, 150H, A152.
1 Cessna........................... 170, 170A, 170B...................... Cessna Aircraft Company. A-799, Revision 54...... CAR 3.
1 Cessna........................... 172, 172I, 172A, 172K, 172B, 172L, Cessna Aircraft Company. 3A12, Revision 73....... CAR 3.
172C, 172M, 172D, 172N, 172E, 172P,
172F (USAF T-41A), 172Q, 172G, 172H,
(USAF T-41A).
1 Cessna........................... 175, 175A, 175B, 175C, P172D, R172E Cessna Aircraft Company. 3A17, Revision 45....... CAR 3.
(USAF T-41B) (USAF T-41C and D),
R172F (USAF T-41D), R172G (USAF T-
41C or D), R172H (USAF T-41D),
R172J, R172K, 172RG.
1 Cessna........................... 177, 177A, 177B...................... Cessna Aircraft Company. A13CE, Revision 24...... 14 CFR PART 23.
Cessna............................. 177RG................................ Cessna Aircraft Company. A20CE, Revision 21...... 14 CFR PART 23.
Cessna............................. 180, 180E, 180A, 180F, 180B, 180G, Cessna Aircraft Company. 5A6, Revision 66........ CAR 3.
180C, 180H, 180D, 180J, 180E, 180K.
1 Cessna........................... 182, 182K, 182A, 182L, 182B, 182M, Cessna Aircraft Company. 3A13, Revision 64....... CAR 3.
182C, 182N, 182D, 182P, 182E, 182Q,
182F, 182R, 182G, R182, 182H, T182,
182J, TR182.
1 Cessna........................... 185, A185E, 185A, A185F, 185B, 185C, Cessna Aircraft Company. 3A24, Revision 37....... CAR 3.
185D, 185E.
Cessna AgWagon..................... 188, 188A, 188B, A188, A188A, A188B, Cessna Aircraft Company. A9CE, Revision 27....... 14 CFR PART 23.
T188C.
1 Cessna........................... 190 (LC-126A,B,C), 195, 195A, 195B... Cessna Aircraft Company. A-790, Revision 36...... CAR 3.
1 Cessna........................... 206, U206B, TP206D, P206, U206C, Cessna Aircraft Company. A4CE, Revision 43....... CAR 3.
TP206E, P206A, U206D, TU206A, P206B,
U206E, TU206B, P206C, U206F, TU206C,
P206D, U206G, TU206D, P206E, TP206A,
TU206E, U206, TP206B, TU206F, U206A,
TP206C, TU206G.
1 Cessna........................... 208, 208A, 208B...................... Cessna Aircraft Company. A37CE, Revision 12...... 14 CFR PART 23.
1 Cessna........................... 210, 210K, 210A, T210K, 210B, 210L, Cessna Aircraft Company. 3A21, Revision 46....... CAR 3.
210C, T210L, 210D, 210M, 210E,
T210M, 210F, 210N, T210F, P210N,
210G, T210N, T210G, 210R, 210H,
P210R, T210H, T210R, 210J, 210-5
(205), T210J, 210-5A (205A).
1 Cessna........................... 310, 310J, 310A(USAF U-3A),310J-1, Cessna Aircraft Company. 3A10, Revision 62....... CAR 3.
310B, E310J, 310C, 310K, 310D, 310L,
310E(USAF U-3B), 310N, 310F, 310P,
310G, T310P, 310H, 310Q, E310H,
T310Q, 310I, 310R, T310R.

[[Page 66167]]

1 Cessna........................... 320, 320F, 320-1, 335, 320A, 340, Cessna Aircraft Company. 3A25, Revision 25....... CAR 3.
320B, 340A, 320C, 320D, 320E.
1 Cessna........................... 321 (Navy OE-2)...................... Cessna Aircraft Company. 3A11, Revision 6........ CAR 3.
1 Cessna........................... 336.................................. Cessna Aircraft Company. A2CE, Revision 7........ CAR 3.
1 Cessna........................... 337A (USAF 02B), T337E, 337B, 337F, Cessna Aircraft Company. A6CE, Revision 40....... CAR 3/14 CFR PART 23.
M337B (USAF 02A), T337F, T337B,
337G, 337C, T337G, T337C, 337H,
337D, P337H, T337D, T337H, T337H-SP.
1 Cessna........................... 401, 401A, 401B, 402, 402A, 402B, Cessna Aircraft Company. A7CE, Revision 46....... CAR 3.
402C, 411, 411A, 414, 414A, 421,
421A, 421B, 421C, 425.
1 Cessna........................... 404, 406............................. Cessna Aircraft Company. A25CE, Revision 11...... 14 CFR PART 23.
1 Cessna........................... 441.................................. Cessna Aircraft Company. A28CE, Revision 12...... 14 CFR PART 23.
1 Commander Aircraft............... Model 112, Model 114, Model 112TC, Commander Aircraft A12SO, Revision 21...... 14 CFR PART 23.
Model 112B, Model 112TCA, Model Company.
114A, Model 114B, Model 114TC.
Diamond............................ DA20-A1, DA20-C1..................... Diamond Aircraft TA4CH, Revision 14...... 14 CFR PART 23.
Industries, Inc..
1 Great Lakes...................... 2T-1A, 2T-1A-1, 2T-1A-2.............. Great Lakes Aircraft A18EA, Revision 10...... Aeronautical Bulletin
Company, LLC. No. 7-A.
1 Helio (Taylorcraft).............. 15A, 20.............................. Helio Aircraft 3A3, Revision 7......... CAR 4a.
Corporation.
1 Learjet.......................... 23................................... Learjet Inc............. A5CE, Revision 10....... CAR 3.
1 Lockheed......................... 402-2................................ Lockheed Aircraft 2A11, Revision 4........ CAR 3.
International.
1 Land-Air (TEMCO) (Luscombe)...... 11A, 11E............................. Luscombe Aircraft A-804, Revision 14...... CAR 3.
Corporation.
1 Maule............................ Bee Dee M-4, M-5-180C, MXT-7-160, M-4- Maule Aerospace 3A23, Revision 30....... CAR 3.
180V, M-4 M-5-200, MX-7-180A, M-4C, Technology, Inc.
M-5-210C, MXT-7-180A, M-4S, M-5-
210TC, MX-7-180B, M-4T, M-5-220C, M-
7-235B, M-4-180C, M-5-235C, M-7-
235A, M-4-180S, M-6-180, M-7-235C, M-
4-180T, M-6-235, MX-7-180C, M-4-210,
M-7-235, M-7-260, M-4-210C, MX-7-
235, MT-7-260, M-4-210S, MX-7-180, M-
7-260C, M-4-210T, MX-7-420, M-7-
420AC, M-4-220, MXT-7-180, MX-7-
160C, M-4-220C, MT-7-235, MX-7-
180AC, M-4-220S, M-8-235, M-7-420A,
M-4-220T, MX-7-160, MT-7-420.
1 Mooney........................... M20, M20A, M20B, M20C, M20D, M20E, Mooney Airplane Company, 2A3, Revision 47........ CAR 3.
M20F, M20G, M20J, M20K (Up to S/N 25- Inc.
2000), M20L.
1 Interceptor (Aero Commander) 200, 200A, 200B, 200C, 200D, 400..... Prop-Jets, Inc.......... 3A18, Revision 16....... CAR 3.
(Meyers).
1 Beech............................ 35-33, J35, 35-A33, K35, 35-B33, M35, Raytheon Aircraft 3A15, Revision 90....... CAR 3.
35-C33, N35, 35-C33A, P35, E33, S35, Company.
E33A, V35, E33C, V35A, F33, V35B,
F33A, 36, F33C, A36, G33, A36TC,
H35, B36TC, G36.
1 Beech............................ 45 (YT-34), A45 (T-34A, B-45), D45 (T- Raytheon Aircraft 5A3, Revision 25........ CAR 03.
34B). Company.
1 Beech............................ 19A, B23, B19, C23, M19A, A24, 23, Raytheon Aircraft A1CE, Revision 34....... CAR 3.
A24R, A23, B24R, A23A, C24R, A23-19, Company.
A23-24.
1 Beech............................ 3N, 3NM, 3TM, JRB-6, D18C, D18S, Raytheon Aircraft A-765................... Revision 74 CAR 03.
E18S, E18S-9700, G18S, H18, C-45G, Company.
TC-45G, C-45H, TC-45H, TC-45J or UC-
45J (SNB-5), RC-45J (SNB-5P).
1 Beech............................ 35, A35, E35, B35, F35, C35, G35, Raytheon Aircraft A-777, Revision 57...... CAR 03.
D35, 35R. Company.

[[Page 66168]]

1 Raytheon......................... 200, A100-1 (U-21J), 200C, A200 (C- Raytheon Aircraft A24CE, Revision 91...... 14 CFR PART 23.
12A), 200CT, A200 (C-12C), 200T, Company.
A200C (UC-12B), B200, A200CT (C-
12D), B200C, A200CT (FWC-12D),
B200CT, A200CT (C-12F), B200T,
A200CT (RC-12D), 300, A200CT (RC-
12G), 300LW, A200CT (RC-12H), B300,
A200CT (RC-12K), B300C, A200CT (RC-
12P), 1900, A200CT (RC-12Q), 1900C,
B200C (C-12F), 1900D, B200C (UC-
12M), B200C (C-12R), B200C (UC-12F),
1900C (C-12J).
1 Beech............................ B95A, D55, D95A, D55A, E95, E55, 95- Raytheon Aircraft 3A16, Revision 81....... CAR 3.
55, E55A, 95-A55, 56TC, 95-B55, Company.
A56TC, 95-B55A, 58, 95-B55B (T-42A),
58A, 95-C55, 95, 95-C55A, B95, G58.
1 Beech............................ 60, A60, B60......................... Raytheon Aircraft A12CE, Revision 23...... 14 CFR PART 23.
Company.
1 Beech............................ 58P, 58PA, 58TC, 58TCA............... Raytheon Aircraft A23CE, Revision 14...... 14 CFR PART 23.
Company.
1 Cessna........................... CESSNA F172D......................... Reims Aviation S.A...... A4EU, Revision 11....... CAR 10/CAR 3.
CESSNA F172E.........................
CESSNA F172F.........................
CESSNA F172G.........................
CESSNA F172H.........................
CESSNA F172K.........................
CESSNA F172L.........................
CESSNA F172M.........................
CESSNA F172N.........................
CESSNA F172P.........................
1 Socata........................... TB 9, TB 10, TB 20, TB 21, TB 200.... SOCATA-GROUPE A51EU, Revision 14...... 14 CFR PART 23.
AEROSPATIALE.
1 Pitts............................ S-1S, S-1T, S-2, S-2A, S-2S, S-2B, S- Sky International Inc. A8SO, Revision 21....... 14 CFR PART 23.
2C. (Aviat Aircraft, Inc.).
1 Taylorcraft...................... 19, F19, F21, F21A, F21B, F22, F22A, Taylorcraft Aviation, 1A9, Revision 19........ CAR 3.
F22B, F22C. LLC.
1 Taylorcraft...................... BC, BCS12-D, BCS, BC12-D1, BC-65, Taylorcraft Aviation, A-696, Revision 22...... CAR 04.
BCS12-D1, BCS-65, BC12D-85, BC12-65 LLC.
(Army L-2H), BCS12D-85, BCS12-65,
BC12D-4-85, BC12-D, BCS12D-4-85.
1 Taylorcraft...................... (Army L-2G) BF, BFS, BF-60,BFS-60, BF- Taylorcraft, Inc........ A-699, Revision 5....... CAR 4a.
65, BFS-65,(Army L-2K) BF 12-65, BFS-
65.
1 Luscombe......................... 8, 8D, 8A, 8E, 8B, 8F, 8C, T-8F...... The Don Luscombe A-694, Revision 23...... CAR 4a.
Aviation History
Foundation, Inc.
Sierra Hotel Aero, Inc. (Navion)... Navion (L-17A), Navion A (L-17B) (L- Sierra Hotel Aero, Inc.. A-782, Revision 51...... CAR 3.
17C),Navion B, Navion D, Navion E,
Navion F, Navion G, Navion H.
Piper.............................. J-3.................................. Piper Aircraft Inc...... ATC 660, Revision 0..... Not listed.
Piper.............................. J3C-40, J3C-50, J3C-50S, J3C-65, J3C- Piper Aircraft Inc...... A-691, Revision 33...... CAR 4a.
65S, PA-11, PA-11S.
FS 2003 Corporation (Piper)........ PA-12, PA-12S........................ FS 2003 Corporation..... A-780, Revision 13...... CAR 3.
FS 2002 Corporation (Piper)........ PA-14................................ FS 2002 Corporation..... A-797, Revision 11...... CAR 3.
Piper.............................. PA-15................................ Piper Aircraft Inc...... A-800, Revision 11...... CAR 3.
Piper.............................. PA-16, PA-16S........................ Piper Aircraft Inc...... 1A1, Revision 13........ CAR 3.
Piper.............................. PA-17................................ Piper Aircraft Inc...... A-805, Revision 12...... CAR 3.
2 Piper............................ PA-18, PA-18S, PA-18A, PA-18S The New Piper Aircraft, 1A2, Revision 37........ CAR 3.
``125'', PA-18AS ``125'', PA-18A Inc.
``135'', PA-18S ``135'', PA-18AS
``135'', PA-18 ``150'', PA-18A
``150'', PA-18S ``150'', PA-18AS
``150'', PA-19S.
Piper.............................. PA-20, PA-20-115, PA-20-135, PA-20S, Piper Aircraft Inc...... 1A4, Revision 24........ CAR 3.
PA-20S-115, PA-20S-135.

[[Page 66169]]

Piper.............................. PA-22, PA-22-108, PA-22-135, PA-22- Piper Aircraft Inc...... 1A6, Revision 34........ CAR 3.
150, PA-22-160, PA-22S-135, PA-22S-
150, PA-22S-160.
Piper.............................. PA-23, PA-23-160, PA-23-235, PA-23- Piper Aircraft Inc...... 1A10, Revision 51....... CAR 3.
250.
Piper.............................. PA-24, PA-24-250,PA-24-260, PA-24-400 Piper Aircraft Inc...... 1A15, Revision 34....... CAR 3.
1 Piper............................ PA-28-140, PA-28-151, PA-28-150, PA- The New Piper Aircraft, 2A13, Revision 47....... CAR 3.
28-161, PA-28-160, PA-28-181, PA-28- Inc.
180, PA-28R-201, PA-28-235, PA-28R-
201T, PA-28S-160, PA-28-236, PA-28S-
180, PA-28RT-201, PA-28R-180, PA-
28RT-201T, PA-28R-200, PA-28-201T.
1 Piper............................ PA-30, PA-39, PA-40.................. The New Piper Aircraft, A1EA, Revision 16....... CAR 3.
Inc.
1 Piper............................ PA-32-260, PA-32R-301 (SP), PA-32- The New Piper Aircraft, A3SO, Revision 29....... CAR 3.
300, PA-32R-301 (HP),PA-32S-300, PA- Inc.
32R-301T, PA-32R-300, PA-32-301, PA-
32RT-300, PA-32-301T, PA-32RT-300T,
PA-32-301FT, PA-32-301XTC.
1 Piper............................ PA-34-200, PA-34-200T, PA-34-220T.... The New Piper Aircraft, A7SO, Revision 16....... 14 CFR PART 23.
Inc.
1 Piper............................ PA-31P, PA-31T, PA-31T1, PA-31T2, PA- The New Piper Aircraft, A8EA, Revision 22....... CAR 3.
31T3, PA-31P-350. Inc.
1 Piper............................ PA-36-285, PA-36-300, PA-36-375...... The New Piper Aircraft, A9SO, Revision 9........ 14 CFR PART 23.
Inc.
1 Piper............................ PA-36-285, PA-36-300, PA-36-375...... The New Piper Aircraft, A10SO, Revision 12...... 14 CFR PART 21/14 CFR
Inc. PART 23.
Piper.............................. PA-38-112............................ The New Piper Aircraft, A18SO, Revision 4....... 14 CFR PART 23.
Inc.
1 Piper............................ PA-44-180, PA-44-180T................ The New Piper Aircraft, A19SO, Revision 9....... 14 CFR PART 23.
Inc.
1 Piper............................ PA-31, PA-31-300, PA-31-325, PA-31- The New Piper Aircraft, A20SO, Revision 10...... CAR 3.
350. Inc.
1 Piper............................ PA-42, PA-42-720, PA-42-1000......... The New Piper Aircraft, A23SO, Revision 17...... 14 CFR PART 23.
Inc.
1 Piper............................ PA-46-310P, PA-46-350P, PA-46-500TP.. The New Piper Aircraft, A25SO, Revision 14...... 14 CFR PART 23.
Inc.
Piper.............................. PA-46R-350T.......................... Piper Aircraft, Inc..... A25SO, Revision 16...... 14 CFR PART 23.
1 Tiger Aircraft LLC (American AA-1, AA-1A, AA-1B, AA-1C............ Tiger Aircraft LLC...... A11EA, Revision 10...... 14 CFR PART 23.
General).
1 Tiger Aircraft................... AA-5, AA-5A, AA-5B, AG-5B............ Tiger Aircraft LLC...... A16EA, Revision 13...... 14 CFR PART 23.
1 Twin Commander................... 500, 500-A, 500-B, 500-U, 520, 560, Twin Commander Aircraft 6A1, Revision 45........ CAR 3.
560-A, 560-E, 500-S. Corporation.
1 Twin Commander................... 560-F, 681, 680, 690, 680E, 685, Twin Commander Aircraft 2A4, Revision 46........ CAR 3.
680F, 690A, 720, 690B, 680FL, 690C, Corporation.
680FL(P), 690D, 680T, 695, 680V,
695A, 680W, 695B.
1 Univair (Stinson)................ 108, 108-1, 108-2, 108-3, 108-5...... Univair Aircraft A-767, Revision 27...... CAR 3.
Corporation.
1 Univair.......................... (ERCO) 415-D......................... Univair Aircraft A-787, Revision 33...... CAR 3.
(ERCO) E............................. Corporation.
(ERCO) G
(Forney) F-1
(Forney) F-1A
(Alon) A-2
(Alon) A2-A
(Mooney) M10
1 Univair (Mooney)................. (ERCO) 415-C, (ERCO) 415-CD.......... Univair Aircraft A-718, Revision 29...... CAR 4a.
Corporation.
--------------------------------------------------------------------------------------------------------------------------------------------------------

The following aircraft are certified in the restricted category:

[[Page 66170]]

List of All Airplane Models and Applicable TCDS
--------------------------------------------------------------------------------------------------------------------------------------------------------
Make Model TC holder TCDS Certification basis
--------------------------------------------------------------------------------------------------------------------------------------------------------
Air Tractor........................ AT-250, AT-300, AT-301, AT-302, AT- Air Tractor, Inc........ A9SW, Revision 12....... 14 CFR PART 23.
400, AT-400A.
Air Tractor........................ AT-401, AT-401A, AT-401B, AT-402, AT- Air Tractor, Inc........ A17SW, Revision 10...... 14 CFR PART 23.
402A, AT-402B, AT-501, AT-502, AT-
502A, AT-502B, AT-503, AT-503A.
Air Tractor........................ AT-802A, AT-802, AT-602.............. Air Tractor, Inc........ A19SW, Revision 4....... 14 CFR PART 23.
Allied Ag Cat...................... G-164, G-164A, G-164B, G-164B with Allied Ag Cat 1A16, Revision 24....... CAR 8.
73'', G-164B-15T, G-164B-34T, G-164B- Productions, Inc.
20T, G-164C, G-164D, G-164D with
73'' wing gap.
Gippsland Aeronautics.............. GA200................................ Gippsland Aeronautics A00001LA, Revision 1.... 14 CFR PART 23.
Pty. Ltd..
2 Piper............................ PA-18A, PA-18A ``135'', PA-18A The New Piper Aircraft, AR-7, Revision 11....... CAR 8.
``150''. Inc.
LAVIA S.A. (Piper)................. PA-25, PA-25-235, PA-25-260.......... Latino Americana De 2A10, Revision 24....... CAR 8.
Aviaci[oacute]n (LAVIA)
S.A.
Thrush Aircraft, Inc. (Snow, S-2B, S-2C, 600-S2C.................. Thrush Aircraft, Inc.... 2A7, Revision 16........ CAR 8.
Rockwell, Ayres).
Thrush Aircraft, Inc. (Snow, 600 S-2D, S-2R, S2R-T34, S2R-T15, S2R- Thrush Aircraft, Inc.... A3SW, Revision 18....... CAR 3.
Rockwell, Ayres). T11, S2R-R3S, S2R-R1340.
Thrush Aircraft, Inc. (Snow, 600 S2D, S2R-R1340, S2R-G10, S-2R, Thrush Aircraft, Inc.... A4SW, Revision 28....... CAR 8.
Rockwell, Ayres). S2R-R1820, S2R-G5, S2R-T34, S2R-T65,
S2R-G1, S2R-T15, S2RHG-T65, S2RHG-
T34, S2R-R3S, S2R-T45, S2R-T660, S2R-
T11, S2R-G6.
Weatherly.......................... 620, 620TP, 620A, 620B, 620B-TG...... Weatherly Aircraft A26WE, Revision 7....... 14 CFR PART 23.
Company.
3 Ximango.......................... AMT-100, AMT-200, AMT-300, AMT-200S.. Aeromot-Industria TG00004AT, Revision 4... 14 CFR PART 23.
Mecanico Metalugica Ltd.
--------------------------------------------------------------------------------------------------------------------------------------------------------
Aircraft identified with a 1 have special conditions for AmSafe Aviation Inflatable Restraints published under Special Conditions 23-182-SC.
Piper PA-18A, PA-18A ``135'' and PA-18A ``150'' (identified with a 2) are type certificated in Normal/Utility Category on TCDS 1A2 and in Restricted
Category on TCDS AR-7. The same aircraft may be operated under either TCDS in accordance with the restrictions listed on TCDS AR-7.
Ximango (identified with a 3) is certificated in the Utility Category.

For all the models listed above, the certification basis also
includes all exemptions, if any; equivalent level of safety findings,
if any; and the other special conditions.
If the Administrator finds that the applicable airworthiness
regulations (i.e., part 23 as amended) do not contain adequate or
appropriate safety standards for the AmSafe Aviation, inflatable
restraint as installed on these models because of a novel or unusual
design feature, special conditions are prescribed under the provisions
of Sec. 21.16.
Special conditions, as appropriate, as defined in Sec. 11.19, are
issued in accordance with Sec. 11.38, and become part of the type
certification basis in accordance with Sec. 21.101.
Special conditions are initially applicable to the model for which
they are issued. Should the applicant apply for a supplemental type
certificate to modify any other model included on the same type
certificate to incorporate the same novel or unusual design feature,
the special conditions would also apply to that model under the
provisions of Sec. 21.101.

Novel or Unusual Design Features

The various airplane models will incorporate the following novel or
unusual design feature:
The AmSafe Aviation Inflatable Two-, Three-, Four-, or Five-Point
Restraint Safety Belt with an Integrated Airbag Device.
The purpose of the airbag is to reduce the potential for injury in
the event of an accident. In a severe impact, an airbag will deploy
from the restraint, in a manner similar to an automotive airbag. The
airbag will deploy between the head of the occupant and airplane
interior structure. This will, therefore, provide some protection to
the head of the occupant. The restraint will rely on sensors to
electronically activate the inflator for deployment.
The Code of Federal Regulations state performance criteria for
seats and restraints in an objective manner. However, none of these
criteria are adequate to address the specific issues raised concerning
inflatable restraints. Therefore, the FAA has determined that, in
addition to the requirements of part 21 and part 23, special conditions
are needed to address the installation of this inflatable restraint.
Accordingly, these amended special conditions are adopted for the
various airplane models equipped with the AmSafe Aviation, two-, three-
, four, or five-point inflatable restraint. Other conditions may be
developed, as needed, based on further FAA review and discussions with
the manufacturer and civil aviation authorities.

Applicability

As discussed above, these amended special conditions are applicable
to the Approved Model List (AML) above. Should AmSafe Aviation apply at
a later date for a supplemental type certificate to modify any other
model included on the type certificates listed above to incorporate the
same novel or unusual

[[Page 66171]]

design feature, the special conditions would apply to that model as
well.

Conclusion

This action affects only certain novel or unusual design features
on the previously identified airplane models. It is not a rule of
general applicability, and it affects only the applicant who applied to
the FAA for approval of these features on the airplane.
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 these airplane
models, as modified by AmSafe Aviation, is imminent, the FAA finds that
good cause exists to make these amended special conditions effective
upon issuance.

List of Subjects in 14 CFR Part 23

Aircraft, Aviation safety, Signs and symbols.

Citation

0
The authority citation for these amended special conditions is as
follows:

Authority: 49 U.S.C. 106(g), 40113 and 44701; 14 CFR 21.16 and
21.101; and 14 CFR 11.38 and 11.19.

The Amended Special Conditions

The FAA has determined that this project will be accomplished on
the basis of not lowering the current level of safety of the occupant
restraint system for the airplane models listed in these special
conditions. Accordingly, the FAA is issuing the following amended
special conditions as part of the type certification basis for these
models, as modified by AmSafe, Aviation.
Inflatable Two-, Three-, Four-, or Five-Point Restraint Safety Belt
with an Integrated Airbag Device Installed in an Airplane Model.
1a. It must be shown that the inflatable restraint will provide
restraint protection under the emergency landing conditions specified
in the original certification basis of the airplane. Compliance will be
demonstrated using the static test conditions specified in the original
certification basis for each airplane.
1b. It must be shown that the crash sensor will trigger when
exposed to a rapidly applied deceleration, like an actual emergency
landing event. Therefore, compliance may be demonstrated using the
deceleration pulse specified in Sec. 23.562, which may be modified as
follows:

I. The peak longitudinal deceleration may be reduced; however,
the onset rate of the deceleration must be equal to or greater than
the emergency landing pulse identified in Sec. 23.562.
II. The peak longitudinal deceleration must be above the
deployment threshold of the sensor, and equal or greater than the
forward static design longitudinal load factor required by the
original certification basis of the airplane.

2. The inflatable restraint must provide adequate protection for
each occupant. In addition, unoccupied seats that have an active
restraint must not constitute a hazard to any occupant.
3. The design must prevent the inflatable restraint from being
incorrectly buckled and/or incorrectly installed such that the airbag
would not properly deploy. Alternatively, it must be shown that such
deployment is not hazardous to the occupant and will provide the
required protection.
4. It must be shown that the inflatable restraint system is not
susceptible to inadvertent deployment as a result of wear and tear or
the inertial loads resulting from in-flight or ground maneuvers
(including gusts and hard landings) that are likely to be experienced
in service.
5. It must be extremely improbable for an inadvertent deployment of
the restraint system to occur, or an inadvertent deployment must not
impede the pilot's ability to maintain control of the airplane or cause
an unsafe condition (or hazard to the airplane). In addition, a
deployed inflatable restraint must be at least as strong as a Technical
Standard Order (C22g or C114) restraint.
6. It must be shown that deployment of the inflatable restraint
system is not hazardous to the occupant or will not result in injuries
that could impede rapid egress. This assessment should include
occupants whose restraints are loosely fastened.
7. It must be shown that an inadvertent deployment that could cause
injury to a sitting person is improbable. In addition, the restraint
must also provide suitable visual warnings that would alert rescue
personnel to the presence of an inflatable restraint system.
8. It must be shown that the inflatable restraint will not impede
rapid egress of the occupants 10 seconds after its deployment.
9. For the purposes of complying with HIRF and lightning
requirements, the inflatable restraint system is considered a critical
system since its deployment could have a hazardous effect on the
airplane.
10. It must be shown that the inflatable restraints will not
release hazardous quantities of gas or particulate matter into the
cabin.
11. The inflatable restraint system installation must be protected
from the effects of fire such that no hazard to occupants will result.
12. There must be a means to verify the integrity of the inflatable
restraint activation system before each flight or it must be
demonstrated to reliably operate between inspection intervals.
13. A life limit must be established for appropriate system
components.
14. Qualification testing of the internal firing mechanism must be
performed at vibration levels appropriate for a general aviation
airplane.

Issued in Kansas City, Missouri on October 31, 2008.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-26663 Filed 11-6-08; 8:45 am]
BILLING CODE 4910-13-P

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