Source: https://www.federalregister.gov/documents/2014/12/18/2014-29594/special-conditions-sikorsky-aircraft-corporation-sikorsky-model-s-76d-helicopter-search-and-rescue
Timestamp: 2017-08-20 15:50:47
Document Index: 648255025

Matched Legal Cases: ['art 29', 'art 29', 'art 29', 'art 29', 'art 29', 'art 36', 'art 29', '§\u200921', '§\u200921', 'art 29', '§\u200929', 'art 29', '§\u200929', 'art 133']

Federal Register :: Special Conditions: Sikorsky Aircraft Corporation (Sikorsky) Model S-76D Helicopter, Search and Rescue (SAR) Automatic Flight Control System (AFCS) Installation
A Rule by the Federal Aviation Administration on 12/18/2014
This action is effective on Sikorsky Aircraft Corporation Model S-76D on December 9, 2014.
75423-75428 (6 pages)
Docket No.FAA-2011-1026
FAA-2011-1026
https://www.federalregister.gov/d/2014-29594 https://www.federalregister.gov/d/2014-29594
We must receive your comments by February 17, 2015.
Send comments identified by docket number FAA-2014-1026 using any of the following methods:
Mitchell Soth, FAA, Rotorcraft Directorate, Regulations and Policy Group, ASW-111, Rotorcraft Directorate, Aircraft Certification Service, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5104; email mitch.soth@faa.gov.
On January 13, 2014, Sikorsky Aircraft Corporation applied for a change to Type Certificate (TC) No. H1NE to install an optional SAR AFCS in the Model S-76D helicopter. The S-76D is a transport category helicopter certificated to Category A and Category B requirements, and instrument flight certificated under the requirements of Appendix B to 14 CFR part 29, Amendment 29-52.
Flight operations conducted over water at night may have an extremely limited visual horizon with little visual reference to the surface even when conducted under Visual Meteorological Conditions. Consequently, the certification requirements for SAR modes are considered equivalent to operating under Instrument Meteorological Conditions, and therefore must meet the criteria in Appendix B to 14 CFR part 29. While this Appendix prescribes airworthiness criteria for instrument flight, it does not consider operations below instrument flight minimum speed (VMINI), whereas the SAR modes allow for coupled operations at low speed, all-azimuth flight to zero airspeed (hover).
Since SAR operations have traditionally been a public use mission, the use of SAR modes in civil operations requires special airworthiness standards (special conditions) to maintain a level of safety consistent with Category B and Instrument Flight Rule (IFR) certification. In this regard, 14 CFR part 29 lacks adequate airworthiness standards for AFCS SAR mode certification to include flight characteristics, performance, and installed equipment and systems. These special conditions do not require guaranteed departure from a hover following an engine failure. Therefore, designs that apply these special conditions are prohibited from conducting external load operations requiring one engine inoperative hover capability. In addition, these special conditions do not address the 14 CFR 29.865 requirements for the carriage of human external cargo.
Under the provisions of 14 CFR 21.101, Sikorsky must show that the S-76D model helicopter, as changed, continues to meet either the applicable provisions of the regulations incorporated by reference in TC No. Start Printed Page 75425H1NE or the applicable regulations in effect on the date of application for the change, depending on the significance of the change as defined by 14 CFR 21.101. The regulations incorporated by reference in the TC are commonly referred to as the “original type certification basis.” The regulations incorporated by reference in H1NE are as follows:
(a) 14 CFR 29.391, 29.561(b)(c), 29.625, 29.671, 29.785, 29.967, 29.973 at amendment 29-0.
(b) 14 CFR 29.927 at 29-3.
(c) 14 CFR 29.307 at amendment 29-4 (all but main rotor and tail blades).
(d) 14 CFR 29.787, 29.865 at amendment 29-12 (does not meet the 29-43 requirements for Human External Cargo).
(e) 14 CFR 29.908 at amendment 29-13.
(f) 14 CFR 29.1309 at amendment 29-14 (all but new avionics, AFCS, and Electrical Power Generation and Distribution System).
(g) 14 CFR 29.571 at amendment 29-20 (all but main and tail rotor blades only).
(h) 14 CFR 29.1 at amendment 29-21.
(i) 14 CFR 29.923(c)-(o), 29.963, 29.975 at amendment 29-26.
(j) 14 CFR 29.561(c) at amendment 29-29 (for engine installation only).
(k) 14 CFR 29.923(a)(b1)(b3) at amendment 29-34.
(l) 14 CFR part 29 through Amendment 29-52 as follows: 29.2, 29.21, 29.25, 29.27, 29.29, 29.31, 29.33, 29.45, 29.49, 29.51, 29.53, 29.55, 29.59, 29.60, 29.61, 29.62, 29.63, 29.64, 29.65, 29.67, 29.71, 29.73, 29.75, 29.77, 29.79, 29.81, 29.83, 29.85, 29.87, 29.141, 29.143, 29.151, 29.161, 29.171, 29.173, 29.175, 29.177, 29.181, 29.231, 29.235, 29.239, 29.241, 29.251, 29.301, 29.303, 29.305, 29.307 (main and tail rotor blades only), 29.309, 29.321, 29.337, 29.339, 29.341, 29.351, 29.361, 29.395, 29.397, 29.399, 29.401, 29.403, 49.411, 29.413, 29.471, 29.473, 29.475, 29.477, 29.479, 29.481, 29.483, 29.485, 29.493, 29.547, 29.549, 29.551, 29.561(a)(d), 29.563, 29.571 (main and tail rotor blades only), 29.601, 29.602, 29.603, 29.605, 29.607, 29.609, 29.610, 29.611, 29.613, 29.619, 29.621, 29.623, 29.629, 29.653, 29.659, 29.661, 29.663, 29.672, 29.673, 29.674, 29.675, 29.681, 29.683, 29.685, 29.687, 29.691, 29.695, 29.723, 29.725, 29.727, 29.729, 29.731, 29.733, 29.735, 29.771, 29.773, 29.775, 29.777, 29.779, 29.783, 29.801, 29.803, 29.805, 29.807, 29.809, 29.811, 29.812(a)(c)(d)(e)(f), 29.813(c)(2), 29.831, 29.851, 29.853, 29.855, 29.861, 29.863, 29.871, 29.873, 29.877, 29.901, 29.903, 29.907, 29.917, 29.921, 29.931, 29.939, 29.951, 29.953, 29.954, 29.955, 29.959, 29.961, 29.965, 29.969, 29.971, 29.977, 29.993, 29.995, 29.997, 29.999, 29.1011, 29.1013, 29.1015, 29.1017, 29.1019, 29.1021, 29.1023, 29.1027, 29.1041, 29.1043, 29.1045, 29.1047, 29.1049, 29.1091, 29.1093, 29.1103, 29.1121, 29.1123, 29.1141, 29.1143, 29.1145, 29.1151, 29.1163, 29.1165, 29.1181, 29.1183, 29.1185, 29.1187, 29.1189, 29.1191, 29.1193, 29.1194, 29.1195, 29.1197, 29.1199, 29.1201, 29.1203, 29.1301, 19.1303, 29.1305, 29.1307, 29.1309 (new avionics, AFCS, and Electrical Power Generation and Distribution System only), 29.1317, 29.1321, 29.1322, 29.1323, 29.1325, 29.1327, 29.1329, 29.1331, 29.1333, 29.1335, 29.1337, 29.1351, 29.1353, 29.1355, 29.1357, 29.1359, 29.1363, 29.1381, 29.1383, 29.1385, 29.1387, 29.1389, 29.1391, 29.1393, 29.1395, 29.1397, 29.1401. 29.1411, 29.1413, 29.1415, 29.1431, 29.1435, 29.1457, 29.1459, 29.1461, 29.1501, 29.1503, 29.1505, 29.1509, 29.1517, 29.1519, 29.1521, 29.1523, 29.1525, 29.1527, 29.1529, 29.1541, 29.1543, 29.1545, 29.1547, 29.1549, 29.1551, 29.1553, 29.1555, 29.1557, 29.1559, 29.1561, 29.1565, 29.1581, 29.1583, 29.1585, 29.1587, 29.1589, A29.1, A29.2, A29.3, A29.4, B29.1, B29.2, B29.3, B29.4, B29.5, B29.6, B29.7, B29.8, B29.9, C29.1, E29.1.
(m) 14 CFR part 29 Not Adopted: 29.427, 29.497, 29.501, 29.505, 59.511, 29.519, 29.521, 29.562, 29.631, 29.679, 29.737, 29.751, 29.753, 29.755, 29.757, 29.812(b), 29.815, 29.833, 29.859, 29.935, 29.952, 29.957, 29.979, 29.991, 29.1001, 29.1025, 29.1101, 29.1105, 29.1107, 29.1109, 29.1125, 29.1142, 29.1147, 29.1157, 29.1159, 29.1399, 29.1419, 29.1433, 29.1439, 29.1522, D29.1.
(m) 14 CFR part 36 through Amendment 36-28 as follows: 36.801, 36.803, 36.805, H36.1-H36.305.
(n) Special Conditions No. 29-004-SC (Docket No. SW004), dated June 17, 1998.
(o) Equivalent Level of Safety Findings:
(1) Number TD1509BO-R-S-1 for 14 CFR 29.1401(d) at amendment 29-11; Anticollision light system installed in accordance with Sikorsky Drawing 33776-92603.
(2) Number AT01847BO-R-P-1 for 14 CFR 29.1305 at amendment 29-40 and 14 CFR 29.1549 at amendment 29-34; Use of a Power Limit Indicator (PLI) as the primary means for indicating/setting power.
(p) Ditching: If emergency floatation gear, P/N 33776-92709, is installed, then compliance has also been shown to Amendment 29-52 of 29.563, 29.801(b), (c), (d) and (e) and 29.807(b) and (d). For overwater operations, compliance with the operating rules and 29.1411, 29.1415, and 26.1561 must be shown.
If the Administrator finds that the applicable airworthiness regulations (i.e., 14 CFR part 29) do not contain adequate or appropriate safety standards for the Sikorsky Model S-76D because of a novel or unusual design feature, special conditions are prescribed under § 21.16.
The Sikorsky Model S-76D will incorporate the following novel or unusual design features.
The SAR system is composed of a navigation computer with SAR modes, an AFCS that provides coupled SAR functions, hoist operator control, a hover speed reference system, and two radio altimeters. The AFSC coupled SAR functions include:
The SAR system only entails navigation, flight control, and coupled AFCS operation of the helicopter. The system does not include additional equipment that may be required for over Start Printed Page 75426water flight or external loads to meet other operational requirements.
These special conditions apply to the Sikorsky Model S-76D helicopter. Should Sikorsky apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, the special conditions would apply to that model as well under the provisions of § 21.101(d).
This action affects only certain novel or unusual design features on one model (i.e., S-76D) of helicopter. It is not a rule of general applicability.
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 Sikorsky Aircraft Corporation Model S-76D helicopters when the optional Search and Rescue (SAR) Automatic Flight Control System (AFCS) is installed.
In addition to the 14 CFR part 29 certification requirements for helicopter instrument flight (Appendix B), the following additional requirements must be met for certification of the SAR AFCS:
(4) A means to prevent unintended flight below a safe minimum height. Pilot-commanded descent below the safe minimum height is acceptable provided the alerting requirements in paragraph (b)(7)(i) of these Special Conditions alert the pilot of this descent below safe minimum height.
(6) A system that monitors for flight guidance deviations and failures and contains an alerting function that provides the flight crew with enough information to take appropriate corrective action.
(7) An alerting system that provides visual or aural alerts, or both, to the flight crew under any of the following conditions:
(10) A functional hazard assessment and a system safety assessment must address the failure conditions associated with SAR operations.
(ii) The assessments must consider all the systems required for SAR operations, including the AFCS, all associated AFCS sensors (for example, radio altimeter), and primary flight displays. Electrical and electronic Start Printed Page 75427systems with SAR catastrophic failure conditions (for example, AFCS) must comply with the § 29.1317(a)(4) HIRF requirements.
(i) Sea State: Wave height of 2.5 meters (8.2 feet), considering both short and long swells. This is in addition to the Sea State demonstrated in reference to the airframe's ditching capability.
(ii) Wind: 25 knots headwind, 17 knots for all other azimuths.
(3) The minimum use height (MUH) for the SAR modes must be no more than the maximum loss of height following any single failure or any combination of failures not shown to be extremely improbable, plus an additional margin of 15 feet above the surface. MUH is the minimum height at which any SAR AFCS mode may be engaged.
(1) The basic aircraft must meet all of the 14 CFR part 29 airworthiness criteria for helicopter instrument flight (Appendix B).
(A) Any oscillation must be damped and any aperiodic response must not double in amplitude in less than 10 seconds. This requirement must also be met with degraded upper modes of the AFCS. An “upper mode” is a mode that utilizes a fully coupled autopilot to provide an operational SAR profile.
(4) With any of the upper modes of the AFCS engaged, the pilot must be able to manually recover the aircraft and transition to the normal (Appendix B) IFR flight profile envelope without exceptional skill, alertness, or strength.
The following performance information must be provided in the Rotorcraft Flight Manual Supplement (RFMS). OEI performance information and emergency procedures, providing the maximum weight that will provide a safe landing (or ditching) or the ability to fly away following failure of the critical engine in a hover. The maximum weight must be presented as a function of the hover height for the temperature and pressure altitude range requested for certification. The effects of wind must be reflected in the hover performance information. These OEI performance requirements do not replace performance requirements that may be needed to comply with the airworthiness or operational standards (§ 29.865 or 14 CFR part 133) for external loads or human external cargo.
(A) Minimum crew requirements. No fewer than 2 pilots, except for approved external load operations that will also require a hoist operator.
(B) Maximum SAR weight as determined by the lower of the SAR Mode performance requirement of paragraph (c)(4) of these Special Conditions or the aircraft performance information provided by paragraph (e) of these Special Conditions.
(C) Maximum demonstrated sea state conditions for ditching compliance.
(D) Engagement criteria for each of the SAR modes to include MUH, as determined in paragraph (c)(3) of these Special Conditions.
(E) The prohibition of external load operations requiring OEI hover capability.
(ii) Normal and emergency procedures for operation of the SAR system (including operation of the hoist operator control), with AFCS failure modes, AFCS degraded modes, and engine failures.
(D) Information and/or advisory information concerning operations in a heavy salt spray environment, including any airframe or power effects as a result of salt encrustation.
(5) All AFCS malfunctions must include evaluation at the low-speed and high-power flight conditions typical of SAR operations. Additionally, AFCS hard-over, slow-over, and oscillatory malfunctions, particularly in yaw, require evaluation. AFCS malfunction testing must include a single or a combination of failures (such as erroneous data from and loss of the radio altimeter, attitude, heading, and Start Printed Page 75428altitude sensors) that are not shown to be extremely improbable.
(7) The flight demonstration must also evaluate OEI procedures from hover while hoisting an external load.
Issued in Fort Worth, Texas, on December 9, 2014.
[FR Doc. 2014-29594 Filed 12-17-14; 8:45 am]