Source: https://www.federalregister.gov/documents/2006/06/14/E6-9226/special-conditions-amsafe-inc-approved-model-list-installation-of-amsafe-inflatable-restraints-in
Timestamp: 2017-11-23 06:19:24
Document Index: 499380576

Matched Legal Cases: ['art 23', '§\u200923', '§\u200923', '§\u200923', 'art 21', '§\u200921', 'art 23', 'art 23', 'art 23', 'art 23', 'art 23', 'art 23', 'art 23', 'art 23', 'art 23', 'art 23', 'art 23', 'art 23', 'art 23', 'art 23', 'art 21', 'art 23', 'art 23', 'art 23', 'art 23', 'art 23', 'art 23', 'art 23', 'art 23', '§\u200921', '§\u200911', '§\u200911', '§\u200921', '§\u200921', '§\u200921']

Federal Register :: Special Conditions: AmSafe, Inc.; Approved Model List; Installation of AmSafe Inflatable Restraints in Normal and Utility Category Non-23.562 Certified Airplanes
Special Conditions: AmSafe, Inc.; Approved Model List; Installation of AmSafe Inflatable Restraints in Normal and Utility Category Non-23.562 Certified Airplanes
71 FR 34237
34237-34243 (7 pages)
Special Conditions No. 23-182-SC
E6-9226
https://www.federalregister.gov/d/E6-9226 https://www.federalregister.gov/d/E6-9226
These special conditions are issued for the installation of an AmSafe, Inc., Inflatable Two-, Three-, Four- or Five-Point Restraint Safety Belt with an Integrated Airbag Device on various airplane models. These airplanes, as modified by AmSafe, Inc., will have a novel or unusual design feature(s) 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 or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
Effective Date: The effective date of these special conditions is June 6, 2006.
Mr. Mark James, Federal Aviation Administration, Aircraft Certification Service, Small Airplane Directorate, ACE-111, 901 Locust, Room 301, Kansas City, Missouri 64106; 816-329-4137, fax 816-329-4090 e-mail mark.james@faa.gov.
On August 19, 2005, AmSafe, Inc., Aviation Inflatable Restraints (AAIR) Division, 1043 North 47th Avenue, Phoenix, AZ 85043, applied for a supplemental type certificate for the installation of an inflatable restraint in various airplane models certificated before the dynamic structural requirements as specified in 14 CFR, part 23, § 23.562, took effect.
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, Inc., 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 aircraft are susceptible to a large amount of cumulative wear and tear on a restraint system. It is likely that the potential for inadvertent Start Printed Page 34238deployment 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.
Given the level of safety of the retrofitted airplane occupant restraints, the inflatable restraint system must show that it will offer an equivalent level of protection in the event of an emergency landing. In the event of a deployment, the restraint must still be at least as strong as a Technical Standard Order approved belt and shoulder harness. There is no requirement for the inflatable portion of the restraint to offer protection during multiple impacts, where more than one impact would require protection.
The inflatable restraint system must deploy and provide protection for each occupant during emergency landing conditions as specified in the original certification basis. The seats of the various airplane models were certificated prior to the dynamic structural requirements of § 23.562. Therefore, the emergency landing loads conditions identified in the original certification basis of the airplane must be used to satisfy this requirement. Compliance will be demonstrated using the test condition specified in the original certification basis. It must also 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.
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 in the event of airbag deployment. 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.
Special conditions for the installation of AAIR systems on other Non-23.562 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 so AmSafe, Inc., could proceed with the project, since no comments were expected.
These previous special conditions were 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. The AML Supplemental Type Certificate sought by AmSafe, Inc., has numerous airplane models and manufacturers. Since AmSafe, Inc., has previously demonstrated by dynamic testing, and has the supporting data, that the Electronics Module Assembly (EMA) and the 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 special conditions.
This is a departure from the method of showing compliance used in the prior special conditions. Testing is required to show compliance, but it is not necessary to repeat the testing for each airplane installation. Existing test data Start Printed Page 34239is adequate for showing compliance for other airplanes where the AAIR equipment is identical and the installation is nearly identical. Since this is a substantial change in the philosophy of showing compliance, it was prudent to give the public time to comment on these special conditions. We published a notice of proposed special conditions No. 23-06-02-SC on April 20, 2006 (71FR 20368). The comment period closed on May 22, 2006.
Under the provisions of 14 CFR part 21, § 21.101, AmSafe, Inc., must show that the 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 are commonly referred to as the “original type certification basis” and can be found in the Type Certificate Numbers listed below. The following models are covered by this special condition:
Aerostar 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) Aerostar Aircraft Corporation A17WE Revision 22 14 CFR Part 23.
All American 10A All American Aircraft, Inc A-792 CAR 3.
American Champion (Champion) 402 American Champion Aircraft Corp A3CE Revision 5 CAR 3.
American Champion (Bellanca) (Champion) (Aeronca) 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 American Champion Aircraft Corp A-759 Revision 67 CAR 4a.
American Champion (Bellanca) (Trytek) (Aeronca) 11AC, S11AC, 11BC, S11BC American Champion Aircraft Corp A-761 Revision 17 CAR 4a.
American Champion (Bellanca) (Trytek) (Aeronca) 11CC, S11CC American Champion Aircraft Corporation A-796 Revision 14 CAR 3.
Varga (Morrisey) 2150, 2150A, 2180 Augustair, Inc 4A19 Revision 9 CAR 3.
Bellanca 14-13, 14-13-2, 14-13-3, 14-13-3W Bellanca Aircraft Corporation A-773 Revision 10 CAR 4a.
Bellanca 14-9, 14-9L Bellanca Aircraft Corporation TC716 CAR 4a.
Cessna 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 Cessna Aircraft Company 3A10 Revision 62 CAR 3.
Cessna 321 (Navy OE-2) Cessna Aircraft Company 3A11 Revision 6 CAR 3.
Cessna 172, 172I, 172A, 172K, 172B, 172L, 172C, 172M, 172D, 172N, 172E, 172P, 172F (USAF T-41A), 172Q, 172G, 172H, (USAF T-41A) Cessna Aircraft Company 3A12 Revision 73 CAR 3.
Cessna 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 Cessna Aircraft Company 3A17 Revision 45 CAR 3.
Cessna 182, 182K, 182A, 182L, 182B, 182M, 182C, 182N, 182D, 182P, 182E, 182Q, 182F, 182R, 182G, R182, 182H, T182, 182J, TR182 Cessna Aircraft Company 3A13 Revision 64 CAR 3.
Cessna 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) Cessna Aircraft Company 3A21 Revision 46 CAR 3.
Cessna 185, A185E, 185A, A185F, 185B, 185C, 185D, 185E Cessna Aircraft Company 3A24 Revision 37 CAR 3.
Cessna 320, 320F, 320-1, 335, 320A, 340, 320B, 340A, 320C, 320D, 320E Cessna Aircraft Company 3A25 Revision 25 CAR 3.
Cessna 140A Cessna Aircraft Company 5A2 Revision 21 CAR 3.
Cessna 180, 180E, 180A, 180F, 180B, 180G, 180C, 180H, 180D, 180J, 180E, 180K Cessna Aircraft Company 5A6 Revision 66 CAR 3
Start Printed Page 34240
Cessna 336 Cessna Aircraft Company A2CE Revision 7 CAR 3.
Cessna 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 Cessna Aircraft Company A4CE Revision 43 CAR 3.
Cessna 337A (USAF 02B), T337E, 337B, 337F, M337B (USAF 02A), T337F, T337B, 337G, 337C, T337G, T337C, 337H, 337D, P337H, T337D, T337H, T337H-SP Cessna Aircraft Company A6CE Revision 40 CAR 3/14 CFR Part 23.
Cessna 401, 411A, 401A, 414, 401B, 414A, 402, 421, 402A, 421A, 402B, 421B, 402C, 421C, 411, 425 Cessna Aircraft Company A7CE Revision 46 CAR 3.
Cessna 190 (LC-126A,B,C), 195, 195A, 195B Cessna Aircraft Company A-790 Revision 36 CAR 3.
Cessna 170, 170A, 170B Cessna Aircraft Company A-799 Revision 54 CAR 3.
Cessna 150, 150J, 150A, 150K, 150B, A150K, 150C, 150L, 150D, A150L, 150E, 150M, 150F, A150M, 150G, 152, 150H, A152 Cessna Aircraft Company 3A19 Revision 44 CAR 3.
Cessna 177, 177A, 177B Cessna Aircraft Company A13CE Revision 24 14 CFR Part 23.
Cessna 404, 406 Cessna Aircraft Company A25CE Revision 11 14 CFR Part 23.
Cessna 208, 208A, 208B Cessna Aircraft Company A37CE Revision 12 14 CFR Part 23.
Cessna 441 Cessna Aircraft Company A28CE Revision 12 14 CFR Part 23.
Cessna 120, 140 Cessna Aircraft Company A-768 Revision 34 CAR 4a.
Commander Aircraft Model 112, Model 114, Model 112TC, Model 112B, Model 112TCA, Model 114A, Model 114B, Model 114TC Commander Aircraft Company A12SO Revision 21 14 CFR Part 23.
Great Lakes 2T-1A, 2T-1A-1, 2T-1A-2 Great Lakes Aircraft Company, LLC A18EA Revision 10 Aeronautical Bulletin No. 7-A.
Helio (Taylorcraft) 15A, 20 Helio Aircraft Corporation 3A3 Revision 7 CAR 4a.
Learjet 23 Learjet Inc A5CE Revision 10 CAR 3.
Lockheed 402-2 Lockheed Aircraft International 2A11 Revision 4 CAR 3.
Land-Air (Temco) (Luscombe) 11A, 11E Luscombe Aircraft Corporation A-804 Revision 14 CAR 3.
Maule 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 Maule Aerospace Technology, Inc 3A23 Revision 30 CAR 3.
Mooney M20, M20A, M20B, M20C, M20D, M20E, M20F, M20G, M20J, M20K (Up to S/N 25-2000), M20L Mooney Airplane Company, Inc 2A3 Revision 47 CAR 3.
Interceptor (Aero Commander) (Meyers) 200, 200A, 200B, 200C, 200D, 400 Prop-Jets, Inc 3A18 Revision 16 CAR 3.
Beech 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 Raytheon Aircraft Company 3A15 Revision 90 CAR 3.
Beech 45 (YT-34), A45 (T-34A, B-45), D45 (T-34B) Raytheon Aircraft Company 5A3 Revision 25 CAR 03.
Beech 19A, B23, B19, C23, M19A, A24, 23, A24R, A23, B24R, A23A, C24R, A23-19, A23-24 Raytheon Aircraft Company A1CE Revision 34 CAR 3.
Beech 3N, E18S-9700, 3NM, G18S, 3TM, H18, JRB-6, C-45G, TC-45G, D18C, C-45H, TC-45H, D18S, TC-45J or E18S, UC-45J (SNB-5) RC-45J (SNB-5P) Raytheon Aircraft Company A-765 Revision 74 CAR 03.
Beech 35, A35, E35, B35, F35, C35, G35, D35, 35R Raytheon Aircraft Company A-777 Revision 57 CAR 03.
Raytheon 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) Raytheon Aircraft Company A24CE Revision 91 14 CFR Part 23.
Beech 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 Raytheon Aircraft Company 3A16 Revision 81 CAR 3.
Beech 60, A60, B60 Raytheon Aircraft Company A12CE Revision 23 14 CFR Part 23.
Beech 58P, 58PA, 58TC, 58TCA Raytheon Aircraft Company A23CE Revision 14 14 CFR Part 23.
Cessna Cessna F172D Cessna F172E Cessna F172F Cessna F172G Cessna F172H Cessna F172K Cessna F172L Cessna F172M Cessna F172N Cessna F172P Reims Aviation S.A A4EU Revision 11 CAR 10/CAR 3.
Socata TB 9, TB 10, TB 20, TB 21, TB 200 Socata—Groupe Aerospatiale A51EU Revision 14 14 CFR Part 23.
Pitts S-1S, S-1T, S-2, S-2A, S-2S, S-2B, S-2C Sky International Inc. (Aviat Aircraft, Inc.) A8SO Revision 21 14 CFR Part 23.
Taylorcraft 19, F19, F21, F21A, F21B, F22, F22A, F22B, F22C Taylorcraft Aviation, LLC 1A9 Revision 19 CAR 3.
Taylorcraft 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 Taylorcraft Aviation, LLC A-696 Revision 22 CAR 04
Taylorcraft (Army L-2G) BF, BFS, BF-60, BFS-60, BF-65, BFS-65, (Army L-2K) BF 12-65, BFS-65 Taylorcraft, Inc A-699 Revision 5 CAR 4a
Luscombe 8, 8D, 8A, 8E, 8B, 8F, 8C, T-8F The Don Luscombe Aviation History Foundation, Inc A-694 Revision 23 CAR 4a
Piper 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 The New Piper Aircraft, Inc 2A13 Revision 47 CAR 3.
Piper PA-30, PA-39, PA-40 The New Piper Aircraft, Inc A1EA Revision 16 CAR 3.
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 The New Piper Aircraft, Inc A3SO Revision 29 CAR 3.
Piper PA-34-200, PA-34-200T, PA-34-220T The New Piper Aircraft, Inc A7SO Revision 16 14 CFR Part 23.
Piper PA-31P, PA-31T, PA-31T1, PA-31T2, PA-31T3, PA-31P-350 The New Piper Aircraft, Inc A8EA Revision 22 CAR 3.
Piper PA-36-285, PA-36-300, PA-36-375 The New Piper Aircraft, Inc A9SO Revision 9 14 CFR Part 23.
Piper PA-36-285, PA-36-300, PA-36-375 The New Piper Aircraft, Inc A10SO Revision 12 14 CFR Part 21/14 CFR Part 23.
Piper PA-38-112 The New Piper Aircraft, Inc A18SO Revision 4 14 CFR Part 23.
Piper PA-44-180, PA-44-180T The New Piper Aircraft, Inc A19SO Revision 9 14 CFR Part 23.
Piper PA-31, PA-31-300, PA-31-325, PA-31-350 The New Piper Aircraft, Inc A20SO Revision 10 CAR 3.
Piper PA-42, PA-42-720, PA-42-1000 The New Piper Aircraft, Inc A23SO Revision 17 14 CFR Part 23
Piper PA-46-310P, PA-46-350P, PA-46-500TP The New Piper Aircraft, Inc A25SO Revision 14 14 CFR Part 23.
Tiger Aircraft LLC (American General) AA-1, AA-1A, AA-1B, AA-1C Tiger Aircraft LLC A11EA Revision 10 14 CFR Part 23.
Tiger Aircraft AA-5, AA-5A, AA-5B, AG-5B Tiger Aircraft LLC A16EA Revision 13 14 CFR Part 23.
Twin Commander 500, 500-A, 500-B, 500-U, 520, 560, 560-A, 560-E, 500-S Twin Commander Aircraft Corporation 6A1 Revision 45 CAR 3.
Twin Commander 560-F, 681, 680, 690, 680E, 685, 680F, 690A, 720, 690B, 680FL, 690C, 680FL(P), 690D, 680T, 695, 680V, 695A, 680W, 695B Twin Commander Aircraft Corporation 2A4 Revision 46 CAR 3.
Univair (Stinson) 108, 108-1, 108-2, 108-3, 108-5 Univair Aircraft Corporation A-767 Revision 27 CAR 3.
Univair (ERCO) 415-D (ERCO) E (ERCO) G (Forney) F-1 (Forney) F-1A (Alon) A-2 (Alon) A2-A (Mooney) M10 Univair Aircraft Corporation A-787 Revision 33 CAR 3.
Univair (Mooney) (ERCO) 415-C, (ERCO) 415-CD Univair Aircraft Corporation A-718 Revision 29 CAR 4a.
If the Administrator finds that the applicable airworthiness regulations (i.e., CAR 3 or part 23, as amended) do not contain adequate or appropriate safety standards for the AmSafe, Inc., 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, the special conditions would also apply to that model under the provisions of § 21.101.
Accordingly, these special conditions are adopted for the various airplane models equipped with the AmSafe, Inc., 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.
A notice of proposed special conditions No. 23-06-02-SC for the various airplane models was published on April 20, 2006 (71FR 20368). No comments were received, and the special conditions are adopted as proposed.
As discussed above, these special conditions are applicable to the various airplane models previously shown. Should AmSafe, Inc., apply at a later date for a supplemental type certificate to modify any other model included on the Type Certificates shown above, to incorporate the same novel or unusual design feature, the special conditions would apply to that model as well under the provisions of § 21.101(a)(1).
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 some of the airplanes listed is imminent, the FAA finds that good cause exists to make Start Printed Page 34243these special conditions effective upon issuance.
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 these airplanes.
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, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for the airplane models listed in these special conditions, modified by AmSafe, Incorporated. Inflatable Two-, Three-, Four-, or Five-Point Restraint Safety Belt with an Integrated Airbag Device installed in an airplane model.
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 paragraph 23.562, which may be modified as follows:
Issued in Kansas City, Missouri, on June 6, 2006.
[FR Doc. E6-9226 Filed 6-13-06; 8:45 am]