(a) Except as provided in paragraph (b) of this section, prior to each helicopter air ambulance operation, each pilot in command, or other flight crewmember designated by the certificate holder, must ensure that all medical personnel have been briefed on the following--
(1) Passenger briefing requirements in Sec. 135.117(a) and (b); and
(2) Physiological aspects of flight;
(3) Patient loading and unloading;
(4) Safety in and around the helicopter;
(5) In-flight emergency procedures;
(6) Emergency landing procedures;
(7) Emergency evacuation procedures;
(8) Efficient and safe communications with the pilot; and
(9) Operational differences between day and night operations, if appropriate.
(b) The briefing required in paragraphs (a)(2) through (9) of this section may be omitted if all medical personnel on board have satisfactorily completed the certificate holder's FAA-approved medical personnel training program within the preceding 24 calendar months. Each training program must include a minimum of 4 hours of ground training, and 4 hours of training in and around an air ambulance helicopter, on the topics set forth in paragraph (a)(2) through (9) of this section.
(c) Each certificate holder must maintain a record for each person trained under this section that--
(1) Contains the individual's name, the most recent training completion date, and a description, copy, or reference to training materials used to meet the training requirement.
(2) Is maintained for 24 calendar months following the individual's completion of training. [Doc. No. FAA-2010-0982, 79 FR 9975, Feb. 2, 2014; Amdt. 135-129A, 79 FR 41126, July 15, 2014]
Sec. Appendix A to Part 135--Additional Airworthiness Standards for 10
or More Passenger Airplanes
Applicability
1. Applicability. This appendix prescribes the additional airworthiness standards required by Sec. 135.169.
2. References. Unless otherwise provided, references in this appendix to specific sections of part 23 of the Federal Aviation Regulations (FAR part 23) are to those sections of part 23 in effect on March 30, 1967.
Flight Requirements
3. General. Compliance must be shown with the applicable requirements of subpart B of FAR part 23, as supplemented or modified in Sec. Sec. 4 through 10.
Performance
(a) Unless otherwise prescribed in this appendix, compliance with each applicable performance requirement in sections 4 through 7 must be shown for ambient atmospheric conditions and still air.
(b) The performance must correspond to the propulsive thrust available under the particular ambient atmospheric conditions and the particular flight condition. The available propulsive thrust must correspond to engine power or thrust, not exceeding the approved power or thrust less--
(1) Installation losses; and
(2) The power or equivalent thrust absorbed by the accessories and services appropriate to the particular ambient atmospheric conditions and the particular flight condition.
(c) Unless otherwise prescribed in this appendix, the applicant must select the take-off, en route, and landing configurations for the airplane.
(d) The airplane configuration may vary with weight, altitude, and temperature, to the extent they are compatible with the operating procedures required by paragraph (e) of this section.
(e) Unless otherwise prescribed in this appendix, in determining the critical engine inoperative takeoff performance, the accelerate-stop distance, takeoff distance, changes in the airplane's configuration, speed, power, and thrust must be made under procedures established by the applicant for operation in service.
(f) Procedures for the execution of balked landings must be established by the applicant and included in the Airplane Flight Manual.
(g) The procedures established under paragraphs (e) and (f) of this section must--
(1) Be able to be consistently executed in service by a crew of average skill;
(2) Use methods or devices that are safe and reliable; and
(3) Include allowance for any time delays, in the execution of the procedures, that may reasonably be expected in service.
(a) General. Takeoff speeds, the accelerate-stop distance, the takeoff distance, and the one-engine-inoperative takeoff flight path data (described in paragraphs (b), (c), (d), and (f) of this section), must be determined for--
(1) Each weight, altitude, and ambient temperature within the operational limits selected by the applicant;
(2) The selected configuration for takeoff;
(3) The center of gravity in the most unfavorable position;
(4) The operating engine within approved operating limitations; and
(5) Takeoff data based on smooth, dry, hard-surface runway.
(b) Takeoff speeds. (1) The decision speed V1 is the calibrated airspeed on the ground at which, as a result of engine failure or other reasons, the pilot is assumed to have made a decision to continue or discontinue the takeoff. The speed V1 must be selected by the applicant but may not be less than--
(1) The decision speed V1 is the calibrated airspeed on the ground at which, as a result of engine failure or other reasons, the pilot is assumed to have made a decision to continue or discontinue the takeoff. The speed V1 must be selected by the applicant but may not be less than--
(i) 1.10VS1;
(ii) 1.10VMC;
(iii) A speed that allows acceleration to V1 and stop under paragraph (c) of this section; or
(iv) A speed at which the airplane can be rotated for takeoff and shown to be adequate to safely continue the takeoff, using normal piloting skill, when the critical engine is suddenly made inoperative.
(2) The initial climb out speed V2, in terms of calibrated airspeed, must be selected by the applicant so as to allow the gradient of climb required in section 6(b)(2), but it must not be less than V1 or less than 1.2VS1.
(3) Other essential take off speeds necessary for safe operation of the airplane.
(c) Accelerate-stop distance. (1) The accelerate-stop distance is the sum of the distances necessary to--
(1) The accelerate-stop distance is the sum of the distances necessary to--
(i) Accelerate the airplane from a standing start to V1; and
(ii) Come to a full stop from the point at which V1 is reached assuming that in the case of engine failure, failure of the critical engine is recognized by the pilot at the speed V1.
(2) Means other than wheel brakes may be used to determine the accelerate-stop distance if that means is available with the critical engine inoperative and--
(i) Is safe and reliable;
(ii) Is used so that consistent results can be expected under normal operating conditions; and
(iii) Is such that exceptional skill is not required to control the airplane.
(d) All engines operating takeoff distance. The all engine operating takeoff distance is the horizontal distance required to takeoff and climb to a height of 50 feet above the takeoff surface under the procedures in FAR 23.51(a).
(e) One-engine-inoperative takeoff. Determine the weight for each altitude and temperature within the operational limits established for the airplane, at which the airplane has the capability, after failure of the critical engine at V1 determined under paragraph (b) of this section, to take off and climb at not less than V2, to a height 1,000 feet above the takeoff surface and attain the speed and configuration at which compliance is shown with the en route one-engine-inoperative gradient of climb specified in section 6(c).
(f) One-engine-inoperative takeoff flight path data. The one-engine-inoperative takeoff flight path data consist of takeoff flight paths extending from a standing start to a point in the takeoff at which the airplane reaches a height 1,000 feet above the takeoff surface under paragraph (e) of this section.
(a) Landing climb: All-engines-operating. The maximum weight must be determined with the airplane in the landing configuration, for each altitude, and ambient temperature within the operational limits established for the airplane, with the most unfavorable center of gravity, and out-of-ground effect in free air, at which the steady gradient of climb will not be less than 3.3 percent, with:
(1) The engines at the power that is available 8 seconds after initiation of movement of the power or thrust controls from the minimum flight idle to the takeoff position.
(2) A climb speed not greater than the approach speed established under section 7 and not less than the greater of 1.05VMC or 1.10VS1.
(b) Takeoff climb: one-engine-inoperative. The maximum weight at which the airplane meets the minimum climb performance specified in paragraphs (1) and (2) of this paragraph must be determined for each altitude and ambient temperature within the operational limits established for the airplane, out of ground effect in free air, with the airplane in the takeoff configuration, with the most unfavorable center of gravity, the critical engine inoperative, the remaining engines at the maximum takeoff power or thrust, and the propeller of the inoperative engine windmilling with the propeller controls in the normal position except that, if an approved automatic feathering system is installed, the propellers may be in the feathered position:
(1) Takeoff: landing gear extended. The minimum steady gradient of climb must be measurably positive at the speed V1.
(2) Takeoff: landing gear retracted. The minimum steady gradient of climb may not be less than 2 percent at speed V2. For airplanes with fixed landing gear this requirement must be met with the landing gear extended.
(c) En route climb: one-engine-inoperative. The maximum weight must be determined for each altitude and ambient temperature within the operational limits established for the airplane, at which the steady gradient of climb is not less 1.2 percent at an altitude 1,000 feet above the takeoff surface, with the airplane in the en route configuration, the critical engine inoperative, the remaining engine at the maximum continuous power or thrust, and the most unfavorable center of gravity.
(a) The landing field length described in paragraph (b) of this section must be determined for standard atmosphere at each weight and altitude within the operational limits established by the applicant.
(b) The landing field length is equal to the landing distance determined under FAR 23.75(a) divided by a factor of 0.6 for the destination airport and 0.7 for the alternate airport. Instead of the gliding approach specified in FAR 23.75(a)(1), the landing may be preceded by a steady approach down to the 50-foot height at a gradient of descent not greater than 5.2 percent (3[deg]) at a calibrated airspeed not less than 1.3VS1.
Trim
(a) Lateral and directional trim. The airplane must maintain lateral and directional trim in level flight at a speed of VH or VMO/MMO, whichever is lower, with landing gear and wing flaps retracted.
(b) Longitudinal trim. The airplane must maintain longitudinal trim during the following conditions, except that it need not maintain trim at a speed greater than VMO/MMO:
(1) In the approach conditions specified in FAR 23.161(c) (3) through (5), except that instead of the speeds specified in those paragraphs, trim must be maintained with a stick force of not more than 10 pounds down to a speed used in showing compliance with section 7 or 1.4VS1 whichever is lower.
(2) In level flight at any speed from VH or VMO/MMO, whichever is lower, to either Vx or 1.4VS1, with the landing gear and wing flaps retracted.
Stability
(a) In showing compliance with FAR 23.175(b) and with paragraph (b) of this section, the airspeed must return to within 7\1/2\ percent of the trim speed.
(b) Cruise stability. The stick force curve must have a stable slope for a speed range of 50 knots from the trim speed except that the speeds need not exceed VFC/MFC or be less than 1.4VS1. This speed range will be considered to begin at the outer extremes of the friction band and the stick force may not exceed 50 pounds with--
(1) Landing gear retracted;
(2) Wing flaps retracted;
(3) The maximum cruising power as selected by the applicant as an operating limitation for turbine engines or 75 percent of maximum continuous power for reciprocating engines except that the power need not exceed that required at VMO/MMO;
(4) Maximum takeoff weight; and
(5) The airplane trimmed for level flight with the power specified in paragraph (3) of this paragraph.
VFC/MFC may not be less than a speed midway between VMO/MMO and VDF/MDF, except that, for altitudes where Mach number is the limiting factor, MFC need not exceed the Mach number at which effective speed warning occurs.
(c) Climb stability (turbopropeller powered airplanes only). In showing compliance with FAR 23.175(a), an applicant must, instead of the power specified in FAR 23.175(a)(4), use the maximum power or thrust selected by the applicant as an operating limitation for use during climb at the best rate of climb speed, except that the speed need not be less than 1.4VS1.
Stalls
10. Stall warning. If artificial stall warning is required to comply with FAR 23.207, the warning device must give clearly distinguishable indications under expected conditions of flight. The use of a visual warning device that requires the attention of the crew within the cockpit is not acceptable by itself.
Control Systems
11. Electric trim tabs. The airplane must meet FAR 23.677 and in addition it must be shown that the airplane is safely controllable and that a pilot can perform all the maneuvers and operations necessary to effect a safe landing following any probable electric trim tab runaway which might be reasonably expected in service allowing for appropriate time delay after pilot recognition of the runaway. This demonstration must be conducted at the critical airplane weights and center of gravity positions.
Instruments: Installation
12. Arrangement and visibility. Each instrument must meet FAR 23.1321 and in addition:
(a) Each flight, navigation, and powerplant instrument for use by any pilot must be plainly visible to the pilot from the pilot's station with the minimum practicable deviation from the pilot's normal position and line of vision when the pilot is looking forward along the flight path.
(b) The flight instruments required by FAR 23.1303 and by the applicable operating rules must be grouped on the instrument panel and centered as nearly as practicable about the vertical plane of each pilot's forward vision. In addition--
(1) The instrument that most effectively indicates the attitude must be in the panel in the top center position;
(2) The instrument that most effectively indicates the airspeed must be on the panel directly to the left of the instrument in the top center position;
(3) The instrument that most effectively indicates altitude must be adjacent to and directly to the right of the instrument in the top center position; and
(4) The instrument that most effectively indicates direction of flight must be adjacent to and directly below the instrument in the top center position.
13. Airspeed indicating system. Each airspeed indicating system must meet FAR 23.1323 and in addition:
(a) Airspeed indicating instruments must be of an approved type and must be calibrated to indicate true airspeed at sea level in the standard atmosphere with a minimum practicable instrument calibration error when the corresponding pitot and static pressures are supplied to the instruments.
(b) The airspeed indicating system must be calibrated to determine the system error, i.e., the relation between IAS and CAS, in flight and during the accelerate-takeoff ground run. The ground run calibration must be obtained between 0.8 of the minimum value of V1 and 1.2 times the maximum value of V1, considering the approved ranges of altitude and weight. The ground run calibration is determined assuming an engine failure at the minimum value of V1.
(c) The airspeed error of the installation excluding the instrument calibration error, must not exceed 3 percent or 5 knots whichever is greater, throughout the speed range from VMO to 1.3VS1 with flaps retracted and from 1.3VSO to VFE with flaps in the landing position.
(d) Information showing the relationship between IAS and CAS must be shown in the Airplane Flight manual.
14. Static air vent system. The static air vent system must meet FAR 23.1325. The altimeter system calibration must be determined and shown in the Airplane Flight Manual.
Operating Limitations and Information
15. Maximum operating limit speed VMO/MMO. Instead of establishing operating limitations based on VNE and VNO, the applicant must establish a maximum operating limit speed VMO/MMO as follows:
(a) The maximum operating limit speed must not exceed the design cruising speed VC and must be sufficiently below VD/MD or VDF/MDF to make it highly improbable that the latter speeds will be inadvertently exceeded in flight.
(b) The speed VMO must not exceed 0.8VD/MD or 0.8VDF/MDF unless flight demonstrations involving upsets as specified by the Administrator indicates a lower speed margin will not result in speeds exceeding VD/MD or VDF. Atmospheric variations, horizontal gusts, system and equipment errors, and airframe production variations are taken into account.
16. Minimum flight crew. In addition to meeting FAR 23.1523, the applicant must establish the minimum number and type of qualified flight crew personnel sufficient for safe operation of the airplane considering--
(a) Each kind of operation for which the applicant desires approval;
(b) The workload on each crewmember considering the following:
(1) Flight path control.
(2) Collision avoidance.
(3) Navigation.
(4) Communications.
(5) Operation and monitoring of all essential aircraft systems.
(6) Command decisions; and
(c) The accessibility and ease of operation of necessary controls by the appropriate crewmember during all normal and emergency operations when at the crewmember flight station.
17. Airspeed indicator. The airspeed indicator must meet FAR 23.1545 except that, the airspeed notations and markings in terms of VNO and VNH must be replaced by the VMO/MMO notations. The airspeed indicator markings must be easily read and understood by the pilot. A placard adjacent to the airspeed indicator is an acceptable means of showing compliance with FAR 23.1545(c).
Airplane Flight Manual
18. General. The Airplane Flight Manual must be prepared under FARs 23.1583 and 23.1587, and in addition the operating limitations and performance information in sections 19 and 20 must be included.
19. Operating limitations. The Airplane Flight Manual must include the following limitations--
(a) Airspeed limitations. (1) The maximum operating limit speed VMO/MMO and a statement that this speed limit may not be deliberately exceeded in any regime of flight (climb, cruise, or descent) unless a higher speed is authorized for flight test or pilot training;
(1) The maximum operating limit speed VMO/MMO and a statement that this speed limit may not be deliberately exceeded in any regime of flight (climb, cruise, or descent) unless a higher speed is authorized for flight test or pilot training;
(2) If an airspeed limitation is based upon compressibility effects, a statement to this effect and information as to any symptoms, the probable behavior of the airplane, and the recommended recovery procedures; and
(3) The airspeed limits, shown in terms of VMO/MMO instead of VNO and VNE.
(b) Takeoff weight limitations. The maximum takeoff weight for each airport elevation ambient temperature and available takeoff runway length within the range selected by the applicant may not exceed the weight at which--
(1) The all-engine-operating takeoff distance determined under section 5(b) or the accelerate-stop distance determined under section 5(c), whichever is greater, is equal to the available runway length;
(2) The airplane complies with the one-engine-inoperative takeoff requirements specified in section 5(e); and
(3) The airplane complies with the one-engine-inoperative takeoff and en route climb requirements specified in sections 6 (b) and (c).
(c) Landing weight limitations. The maximum landing weight for each airport elevation (standard temperature) and available landing runway length, within the range selected by the applicant. This weight may not exceed the weight at which the landing field length determined under section 7(b) is equal to the available runway length. In showing compliance with this operating limitation, it is acceptable to assume that the landing weight at the destination will be equal to the takeoff weight reduced by the normal consumption of fuel and oil en route.
20. Performance information. The Airplane Flight Manual must contain the performance information determined under the performance requirements of this appendix. The information must include the following:
(a) Sufficient information so that the takeoff weight limits specified in section 19(b) can be determined for all temperatures and altitudes within the operation limitations selected by the applicant.
(b) The conditions under which the performance information was obtained, including the airspeed at the 50-foot height used to determine landing distances.
(c) The performance information (determined by extrapolation and computed for the range of weights between the maximum landing and takeoff weights) for--
(1) Climb in the landing configuration; and
(2) Landing distance.
(d) Procedure established under section 4 related to the limitations and information required by this section in the form of guidance material including any relevant limitations or information.
(e) An explanation of significant or unusual flight or ground handling characteristics of the airplane.
(f) Airspeeds, as indicated airspeeds, corresponding to those determined for takeoff under section 5(b).
21. Maximum operating altitudes. The maximum operating altitude to which operation is allowed, as limited by flight, structural, powerplant, functional, or equipment characteristics, must be specified in the Airplane Flight Manual.
22. Stowage provision for airplane flight manual. Provision must be made for stowing the Airplane Flight Manual in a suitable fixed container which is readily accessible to the pilot.
23. Operating procedures. Procedures for restarting turbine engines in flight (including the effects of altitude) must be set forth in the Airplane Flight Manual.
Airframe Requirements
Flight Loads
(a) Each turbopropeller engine mount and its supporting structure must be designed for the torque effects of:
(1) The conditions in FAR 23.361(a).
(2) The limit engine torque corresponding to takeoff power and propeller speed multiplied by a factor accounting for propeller control system malfunction, including quick feathering action, simultaneously with 1g level flight loads. In the absence of a ration- al analysis, a factor of 1.6 must be used.
(b) The limit torque is obtained by multiplying the mean torque by a factor of 1.25.
25. Turbine engine gyroscopic loads. Each turbopropeller engine mount and its supporting structure must be designed for the gyroscopic loads that result, with the engines at maximum continuous r.p.m., under either--
(a) The conditions in FARs 23.351 and 23.423; or
(b) All possible combinations of the following:
(1) A yaw velocity of 2.5 radians per second.
(2) A pitch velocity of 1.0 radians per second.
(3) A normal load factor of 2.5.
(4) Maximum continuous thrust.
(a) Turbopropeller powered airplanes must be designed for the unsymmet- rical loads resulting from the failure of the critical engine including the following conditions in combination with a single malfunction of the propeller drag limiting system, considering the probable pilot corrective action on the flight controls:
(1) At speeds between Vmo and VD, the loads resulting from power failure because of fuel flow interruption are considered to be limit loads.
(2) At speeds between Vmo and Vc, the loads resulting from the disconnection of the engine compressor from the turbine or from loss of the turbine blades are considered to be ultimate loads.
(3) The time history of the thrust decay and drag buildup occurring as a result of the prescribed engine failures must be substantiated by test or other data applicable to the particular engine-propeller combination.
(4) The timing and magnitude of the probable pilot corrective action must be conserv- atively estimated, considering the characteristics of the particular engine-propeller-airplane combination.
(b) Pilot corrective action may be assumed to be initiated at the time maximum yawing velocity is reached, but not earlier than 2 seconds after the engine failure. The magnitude of the corrective action may be based on the control forces in FAR 23.397 except that lower forces may be assumed where it is shown by analysis or test that these forces can control the yaw and roll resulting from the prescribed engine failure conditions.
Ground Loads
27. Dual wheel landing gear units. Each dual wheel landing gear unit and its supporting structure must be shown to comply with the following:
(a) Pivoting. The airplane must be assumed to pivot about one side of the main gear with the brakes on that side locked. The limit vertical load factor must be 1.0 and the coefficient of friction 0.8. This condition need apply only to the main gear and its supporting structure.
(b) Unequal tire inflation. A 60-40 percent distribution of the loads established under FAR 23.471 through FAR 23.483 must be applied to the dual wheels.
(c) Flat tire. (1) Sixty percent of the loads in FAR 23.471 through FAR 23.483 must be applied to either wheel in a unit.
(1) Sixty percent of the loads in FAR 23.471 through FAR 23.483 must be applied to either wheel in a unit.
(2) Sixty percent of the limit drag and side loads and 100 percent of the limit vertical load established under FARs 23.493 and 23.485 must be applied to either wheel in a unit except that the vertical load need not exceed the maximum vertical load in paragraph (c)(1) of this section.
Fatigue Evaluation
28. Fatigue evaluation of wing and associated structure. Unless it is shown that the structure, operating stress levels, materials and expected use are comparable from a fatigue standpoint to a similar design which has had substantial satisfactory service experience, the strength, detail design, and the fabrication of those parts of the wing, wing carrythrough, and attaching structure whose failure would be catastrophic must be evaluated under either--
(a) A fatigue strength investigation in which the structure is shown by analysis, tests, or both to be able to withstand the repeated loads of variable magnitude expected in service; or
(b) A fail-safe strength investigation in which it is shown by analysis, tests, or both that catastrophic failure of the structure is not probable after fatigue, or obvious partial failure, of a principal structural element, and that the remaining structure is able to withstand a static ultimate load factor of 75 percent of the critical limit load factor at VC. These loads must be multiplied by a factor of 1.15 unless the dynamic effects of failure under static load are otherwise considered.
Design and Construction
29. Flutter. For multiengine turbopropeller powered airplanes, a dynamic evaluation must be made and must include--
(a) The significant elastic, inertia, and aerodynamic forces associated with the rotations and displacements of the plane of the propeller; and
(b) Engine-propeller-nacelle stiffness and damping variations appropriate to the particular configuration.
Landing Gear
30. Flap operated landing gear warning device. Airplanes having retractable landing gear and wing flaps must be equipped with a warning device that functions continuously when the wing flaps are extended to a flap position that activates the warning device to give adequate warning before landing, using normal landing procedures, if the landing gear is not fully extended and locked. There may not be a manual shut off for this warning device. The flap position sensing unit may be installed at any suitable location. The system for this device may use any part of the system (including the aural warning device) provided for other landing gear warning devices.
Personnel and Cargo Accommodations
31. Cargo and baggage compartments. Cargo and baggage compartments must be designed to meet FAR 23.787 (a) and (b), and in addition means must be provided to protect passengers from injury by the contents of any cargo or baggage compartment when the ultimate forward inertia force is 9g.
32. Doors and exits. The airplane must meet FAR 23.783 and FAR 23.807 (a)(3), (b), and (c), and in addition:
(a) There must be a means to lock and safeguard each external door and exit against opening in flight either inadvertently by persons, or as a result of mechanical failure. Each external door must be operable from both the inside and the outside.
(b) There must be means for direct visual inspection of the locking mechanism by crewmembers to determine whether external doors and exits, for which the initial opening movement is outward, are fully locked. In addition, there must be a visual means to signal to crewmembers when normally used external doors are closed and fully locked.
(c) The passenger entrance door must qualify as a floor level emergency exit. Each additional required emergency exit except floor level exits must be located over the wing or must be provided with acceptable means to assist the occupants in descending to the ground. In addition to the passenger entrance door:
(1) For a total seating capacity of 15 or less, an emergency exit as defined in FAR 23.807(b) is required on each side of the cabin.
(2) For a total seating capacity of 16 through 23, three emergency exits as defined in FAR 23.807(b) are required with one on the same side as the door and two on the side opposite the door.
(d) An evacuation demonstration must be conducted utilizing the maximum number of occupants for which certification is desired. It must be conducted under simulated night conditions utilizing only the emergency exits on the most critical side of the aircraft. The participants must be representative of average airline passengers with no previous practice or rehearsal for the demonstration. Evacuation must be completed within 90 seconds.
(e) Each emergency exit must be marked with the word ``Exit'' by a sign which has white letters 1 inch high on a red background 2 inches high, be self-illuminated or independently internally electrically illuminated, and have a minimum luminescence (brightness) of at least 160 microlamberts. The colors may be reversed if the passenger compartment illumination is essentially the same.
(f) Access to window type emergency exits must not be obstructed by seats or seat backs.
(g) The width of the main passenger aisle at any point between seats must equal or exceed the values in the following table: ------------------------------------------------------------------------
Minimum main passenger aisle width
-------------------------------------
Total seating capacity Less than 25 25 inches and
inches from floor more from floor------------------------------------------------------------------------10 through 23..................... 9 inches......... 15 inches.------------------------------------------------------------------------
Miscellaneous
33. Lightning strike protection. Parts that are electrically insulated from the basic airframe must be connected to it through lightning arrestors unless a lightning strike on the insulated part--
(a) Is improbable because of shielding by other parts; or
(b) Is not hazardous.
34. Ice protection. If certification with ice protection provisions is desired, compliance with the following must be shown:
(a) The recommended procedures for the use of the ice protection equipment must be set forth in the Airplane Flight Manual.
(b) An analysis must be performed to establish, on the basis of the airplane's operational needs, the adequacy of the ice protection system for the various components of the airplane. In addition, tests of the ice protection system must be conducted to demonstrate that the airplane is capable of operating safely in continuous maximum and intermittent maximum icing conditions as described in appendix C of part 25 of this chapter.
(c) Compliance with all or portions of this section may be accomplished by reference, where applicable because of similarity of the designs, to analysis and tests performed by the applicant for a type certificated model.
35. Maintenance information. The applicant must make available to the owner at the time of delivery of the airplane the information the applicant considers essential for the proper maintenance of the airplane. That information must include the following:
(a) Description of systems, including electrical, hydraulic, and fuel controls.
(b) Lubrication instructions setting forth the frequency and the lubricants and fluids which are to be used in the various systems.
(c) Pressures and electrical loads applicable to the various systems.
(d) Tolerances and adjustments necessary for proper functioning.
(e) Methods of leveling, raising, and towing.
(f) Methods of balancing control surfaces.
(g) Identification of primary and secondary structures.
(h) Frequency and extent of inspections necessary to the proper operation of the airplane.
(i) Special repair methods applicable to the airplane.
(j) Special inspection techniques, such as X-ray, ultrasonic, and magnetic particle inspection.
(k) List of special tools.
Propulsion
General
36. Vibration characteristics. For turbopropeller powered airplanes, the engine installation must not result in vibration characteristics of the engine exceeding those established during the type certification of the engine.
37. In flight restarting of engine. If the engine on turbopropeller powered airplanes cannot be restarted at the maximum cruise altitude, a determination must be made of the altitude below which restarts can be consistently accomplished. Restart information must be provided in the Airplane Flight Manual.
(a) For turbopropeller powered airplanes. The engine installation must comply with the following:
(1) Engine isolation. The powerplants must be arranged and isolated from each other to allow operation, in at least one configuration, so that the failure or malfunction of any engine, or of any system that can affect the engine, will not--
(i) Prevent the continued safe operation of the remaining engines; or
(ii) Require immediate action by any crewmember for continued safe operation.
(2) Control of engine rotation. There must be a means to individually stop and restart the rotation of any engine in flight except that engine rotation need not be stopped if continued rotation could not jeopardize the safety of the airplane. Each component of the stopping and restarting system on the engine side of the firewall, and that might be exposed to fire, must be at least fire resistant. If hydraulic propeller feathering systems are used for this purpose, the feathering lines must be at least fire resistant under the operating conditions that may be expected to exist during feathering.
(3) Engine speed and gas temperature control devices. The powerplant systems associated with engine control devices, systems, and instrumentation must provide reasonable assurance that those engine operating limitations that adversely affect turbine rotor structural integrity will not be exceeded in service.
(b) For reciprocating engine powered airplanes. To provide engine isolation, the powerplants must be arranged and isolated from each other to allow operation, in at least one configuration, so that the failure or malfunction of any engine, or of any system that can affect that engine, will not--
(1) Prevent the continued safe operation of the remaining engines; or
(2) Require immediate action by any crewmember for continued safe operation.
(a) Turbopropeller reversing systems intended for ground operation must be designed so that no single failure or malfunction of the system will result in unwanted reverse thrust under any expected operating condition. Failure of structural elements need not be considered if the probability of this kind of failure is extremely remote.
(b) Turbopropeller reversing systems intended for in flight use must be designed so that no unsafe condition will result during normal operation of the system, or from any failure (or reasonably likely combination of failures) of the reversing system, under any anticipated condition of operation of the airplane. Failure of structural elements need not be considered if the probability of this kind of failure is extremely remote.
(c) Compliance with this section may be shown by failure analysis, testing, or both for propeller systems that allow propeller blades to move from the flight low-pitch position to a position that is substantially less than that at the normal flight low-pitch stop position. The analysis may include or be supported by the analysis made to show compliance with the type certification of the propeller and associated installation components. Credit will be given for pertinent analysis and testing completed by the engine and propeller manufacturers.
40. Turbopropeller drag-limiting systems. Turbopropeller drag-limiting systems must be designed so that no single failure or malfunction of any of the systems during normal or emergency operation results in propeller drag in excess of that for which the airplane was designed. Failure of structural elements of the drag-limiting systems need not be considered if the probability of this kind of failure is extremely remote.
41. Turbine engine powerplant operating characteristics. For turbopropeller powered airplanes, the turbine engine powerplant operating characteristics must be investigated in flight to determine that no adverse characteristics (such as stall, surge, or flameout) are present to a hazardous degree, during normal and emergency operation within the range of operating limitations of the airplane and of the engine.
(a) For turbopropeller powered airplanes--
(1) The fuel system must provide for continuous supply of fuel to the engines for normal operation without interruption due to depletion of fuel in any tank other than the main tank; and
(2) The fuel flow rate for turbopropeller engine fuel pump systems must not be less than 125 percent of the fuel flow required to develop the standard sea level atmospheric conditions takeoff power selected and included as an operating limitation in the Airplane Flight Manual.
(b) For reciprocating engine powered airplanes, it is acceptable for the fuel flow rate for each pump system (main and reserve supply) to be 125 percent of the takeoff fuel consumption of the engine.
Fuel System Components
43. Fuel pumps. For turbopropeller powered airplanes, a reliable and independent power source must be provided for each pump used with turbine engines which do not have provisions for mechanically driving the main pumps. It must be demonstrated that the pump installations provide a reliability and durability equivalent to that in FAR 23.991(a).
44. Fuel strainer or filter. For turbopropeller powered airplanes, the following apply:
(a) There must be a fuel strainer or filter between the tank outlet and the fuel metering device of the engine. In addition, the fuel strainer or filter must be--
(1) Between the tank outlet and the engine-driven positive displacement pump inlet, if there is an engine-driven positive displacement pump;
(2) Accessible for drainage and cleaning and, for the strainer screen, easily removable; and
(3) Mounted so that its weight is not supported by the connecting lines or by the inlet or outlet connections of the strainer or filter itself.
(b) Unless there are means in the fuel system to prevent the accumulation of ice on the filter, there must be means to automatically maintain the fuel-flow if ice-clogging of the filter occurs; and
(c) The fuel strainer or filter must be of adequate capacity (for operating limitations established to ensure proper service) and of appropriate mesh to insure proper engine operation, with the fuel contaminated to a degree (for particle size and density) that can be reasonably expected in service. The degree of fuel filtering may not be less than that established for the engine type certification.
45. Lightning strike protection. Protection must be provided against the ignition of flammable vapors in the fuel vent system due to lightning strikes.
Cooling
(a) Turbopropeller powered airplanes must be shown to comply with FAR 23.1041 during takeoff, climb, en route, and landing stages of flight that correspond to the applicable performance requirements. The cooling tests must be conducted with the airplane in the configuration, and operating under the conditions that are critical relative to cooling during each stage of flight. For the cooling tests a temperature is ``stabilized'' when its rate of change is less than 2 [deg]F. per minute.
(b) Temperatures must be stabilized under the conditions from which entry is made into each stage of flight being investigated unless the entry condition is not one during which component and engine fluid temperatures would stabilize, in which case, operation through the full entry condition must be conducted before entry into the stage of flight being investigated to allow temperatures to reach their natural levels at the time of entry. The takeoff cooling test must be preceded by a period during which the powerplant component and engine fluid temperatures are stabilized with the engines at ground idle.
(c) Cooling tests for each stage of flight must be continued until--
(1) The component and engine fluid temperatures stabilize;
(2) The stage of flight is completed; or
(3) An operating limitation is reached.
Induction System
47. Air induction. For turbopropeller powered airplanes--
(a) There must be means to prevent hazardous quantities of fuel leakage or overflow from drains, vents, or other components of flammable fluid systems from entering the engine intake systems; and
(b) The air inlet ducts must be located or protected so as to minimize the ingestion of foreign matter during takeoff, landing, and taxiing.
48. Induction system icing protection. For turbopropeller powered airplanes, each turbine engine must be able to operate throughout its flight power range without adverse effect on engine operation or serious loss of power or thrust, under the icing conditions specified in appendix C of part 25 of this chapter. In addition, there must be means to indicate to appropriate flight crewmembers the functioning of the powerplant ice protection system.
49. Turbine engine bleed air systems. Turbine engine bleed air systems of turbopropeller powered airplanes must be investigated to determine--
(a) That no hazard to the airplane will result if a duct rupture occurs. This condition must consider that a failure of the duct can occur anywhere between the engine port and the airplane bleed service; and
(b) That, if the bleed air system is used for direct cabin pressurization, it is not possible for hazardous contamination of the cabin air system to occur in event of lubrication system failure.
Exhaust System
50. Exhaust system drains. Turbopropeller engine exhaust systems having low spots or pockets must incorporate drains at those locations. These drains must discharge clear of the airplane in normal and ground attitudes to prevent the accumulation of fuel after the failure of an attempted engine start.
Powerplant Controls and Accessories
51. Engine controls. If throttles or power levers for turbopropeller powered airplanes are such that any position of these controls will reduce the fuel flow to the engine(s) below that necessary for satisfactory and safe idle operation of the engine while the airplane is in flight, a means must be provided to prevent inadvertent movement of the control into this position. The means provided must incorporate a positive lock or stop at this idle position and must require a separate and distinct operation by the crew to displace the control from the normal engine operating range.
52. Reverse thrust controls. For turbopropeller powered airplanes, the propeller reverse thrust controls must have a means to prevent their inadvertent operation. The means must have a positive lock or stop at the idle position and must require a separate and distinct operation by the crew to displace the control from the flight regime.
53. Engine ignition systems. Each turbopropeller airplane ignition system must be considered an essential electrical load.
54. Powerplant accessories. The powerplant accessories must meet FAR 23.1163, and if the continued rotation of any accessory remotely driven by the engine is hazardous when malfunctioning occurs, there must be means to prevent rotation without interfering with the continued operation of the engine.
Powerplant Fire Protection
55. Fire detector system. For turbopropeller powered airplanes, the following apply:
(a) There must be a means that ensures prompt detection of fire in the engine compartment. An overtemperature switch in each engine cooling air exit is an acceptable method of meeting this requirement.
(b) Each fire detector must be constructed and installed to withstand the vibration, inertia, and other loads to which it may be subjected in operation.
(c) No fire detector may be affected by any oil, water, other fluids, or fumes that might be present.
(d) There must be means to allow the flight crew to check, in flight, the functioning of each fire detector electric circuit.
(e) Wiring and other components of each fire detector system in a fire zone must be at least fire resistant.
56. Fire protection, cowling and nacelle skin. For reciprocating engine powered airplanes, the engine cowling must be designed and constructed so that no fire originating in the engine compartment can enter either through openings or by burn through, any other region where it would create additional hazards.
57. Flammable fluid fire protection. If flammable fluids or vapors might be liberated by the leakage of fluid systems in areas other than engine compartments, there must be means to--
(a) Prevent the ignition of those fluids or vapors by any other equipment; or
(b) Control any fire resulting from that ignition.
Equipment
(a) The following are required for turbopropeller airplanes:
(1) The instruments required by FAR 23.1305 (a) (1) through (4), (b) (2) and (4).
(2) A gas temperature indicator for each engine.
(3) Free air temperature indicator.
(4) A fuel flowmeter indicator for each engine.
(5) Oil pressure warning means for each engine.
(6) A torque indicator or adequate means for indicating power output for each engine.
(7) Fire warning indicator for each engine.
(8) A means to indicate when the propeller blade angle is below the low-pitch position corresponding to idle operation in flight.
(9) A means to indicate the functioning of the ice protection system for each engine.
(b) For turbopropeller powered airplanes, the turbopropeller blade position indicator must begin indicating when the blade has moved below the flight low-pitch position.
(c) The following instruments are required for reciprocating engine powered airplanes:
(1) The instruments required by FAR 23.1305.
(2) A cylinder head temperature indicator for each engine.
(3) A manifold pressure indicator for each engine.
Systems and Equipments
General
59. Function and installation. The systems and equipment of the airplane must meet FAR 23.1301, and the following:
(a) Each item of additional installed equipment must--
(1) Be of a kind and design appropriate to its intended function;
(2) Be labeled as to its identification, function, or operating limitations, or any applicable combination of these factors, unless misuse or inadvertent actuation cannot create a hazard;
(3) Be installed according to limitations specified for that equipment; and
(4) Function properly when installed.
(b) Systems and installations must be designed to safeguard against hazards to the aircraft in the event of their malfunction or failure.
(c) Where an installation, the functioning of which is necessary in showing compliance with the applicable requirements, requires a power supply, that installation must be considered an essential load on the power supply, and the power sources and the distribution system must be capable of supplying the following power loads in probable operation combinations and for probable durations:
(1) All essential loads after failure of any prime mover, power converter, or energy storage device.
(2) All essential loads after failure of any one engine on two-engine airplanes.
(3) In determining the probable operating combinations and durations of essential loads for the power failure conditions described in paragraphs (1) and (2) of this paragraph, it is permissible to assume that the power loads are reduced in accordance with a monitoring procedure which is consistent with safety in the types of operations authorized.
60. Ventilation. The ventilation system of the airplane must meet FAR 23.831, and in addition, for pressurized aircraft, the ventilating air in flight crew and passenger compartments must be free of harmful or hazardous concentrations of gases and vapors in normal operation and in the event of reasonably probable failures or malfunctioning of the ventilating, heating, pressurization, or other systems, and equipment. If accumulation of hazardous quantities of smoke in the cockpit area is reasonably probable, smoke evacuation must be readily accomplished.
Electrical Systems and Equipment
61. General. The electrical systems and equipment of the airplane must meet FAR 23.1351, and the following:
(a) Electrical system capacity. The required generating capacity, and number and kinds of power sources must--
(1) Be determined by an electrical load analysis; and
(2) Meet FAR 23.1301.
(b) Generating system. The generating system includes electrical power sources, main power busses, transmission cables, and associated control, regulation and protective devices. It must be designed so that--
(1) The system voltage and frequency (as applicable) at the terminals of all essential load equipment can be maintained within the limits for which the equipment is designed, during any probable operating conditions;
(2) System transients due to switching, fault clearing, or other causes do not make essential loads inoperative, and do not cause a smoke or fire hazard;
(3) There are means, accessible in flight to appropriate crewmembers, for the individual and collective disconnection of the electrical power sources from the system; and
(4) There are means to indicate to appropriate crewmembers the generating system quantities essential for the safe operation of the system, including the voltage and current supplied by each generator.
62. Electrical equipment and installation. Electrical equipment, controls, and wiring must be installed so that operation of any one unit or system of units will not adversely affect the simultaneous operation of any other electrical unit or system essential to the safe operation.
(a) For the purpose of complying with this section, the distribution system includes the distribution busses, their associated feeders, and each control and protective device.
(b) Each system must be designed so that essential load circuits can be supplied in the event of reasonably probable faults or open circuits, including faults in heavy current carrying cables.
(c) If two independent sources of electrical power for particular equipment or systems are required under this appendix, their electrical energy supply must be ensured by means such as duplicate electrical equipment, throwover switching, or multichannel or loop circuits separately routed.
64. Circuit protective devices. The circuit protective devices for the electrical circuits of the airplane must meet FAR 23.1357, and in addition circuits for loads which are essential to safe operation must have individual and exclusive circuit protection.
Sec. Appendix B to Part 135--Airplane Flight Recorder Specifications ----------------------------------------------------------------------------------------------------------------
Installed system
\1\ minimum Sampling interval Resolution \4\
Parameters Range accuracy (to (per second) read out
recovered data)----------------------------------------------------------------------------------------------------------------Relative time (from recorded on 25 hr minimum..... 0.125% per
hour.Indicated airspeed.............. Vso to VD (KIAS).. 5% or 1
0 kts., whichever
is greater.
Resolution 2 kts.
below 175 KIAS.Altitude........................ -1,000 ft. to max 100 to 7
00 ft. (see Table
1, TSO C51-a).Magnetic heading................ 360[deg].......... 5[deg].Vertical acceleration........... -3g to +6g........ 0.2g in where peaks, ref.
addition to 0 recorded).
.3g maximum datum.Longitudinal acceleration....... 1.0g. eq>1.5% max.
range excluding
datum error of
5%.Pitch attitude.................. 100% of usable.... 2[deg].Roll attitude................... 60[deg] or eq>2[deg].
100% of usable
range, whichever
is greater.Stabilizer trim position........ Full range........ 3% unless
higher uniquely
required.
OrPitch control position.......... Full range........ 3% unless
higher uniquely
required.
Engine Power, Each Engine
Fan or N1 speed or EPR or Maximum range..... 5%.
aircraft certification.
OrProp. speed and torque (sample .................. .................. 1 (prop speed), 1
once/sec as close together as (torque).
practicable).Altitude rate \2\ (need depends 8,000 fpm. eq>10%. 12,000
Resolution 250
fpm below 12,000
ft. indicated.Angle of attack \2\ (need -20[deg] to 2[deg].
usable range.Radio transmitter keying On/off............ .................. 1.................
(discrete).TE flaps (discrete or analog)... Each discrete .................. 1.................
position (U, D, T/
O, AAP).
Or.............
Analog 0-100% 3[deg].LE flaps (discrete or analog)... Each discrete .................. 1.................
position (U, D, T/
O, AAP).
Or.............
Analog 0-100% 3[deg].Thrust reverser, each engine Stowed or full .................. 1.................
(Discrete). reverse.Spoiler/speedbrake (discrete)... Stowed or out..... .................. 1.................Autopilot engaged (discrete).... Engaged or .................. 1.................
disengaged.----------------------------------------------------------------------------------------------------------------\1\ When data sources are aircraft instruments (except altimeters) of acceptable quality to fly the aircraft the
recording system excluding these sensors (but including all other characteristics of the recording system)
shall contribute no more than half of the values in this column.\2\ If data from the altitude encoding altimeter (100 ft. resolution) is used, then either one of these
parameters should also be recorded. If however, altitude is recorded at a minimum resolution of 25 feet, then
these two parameters can be omitted.\3\ Per cent of full range.\4\ This column applies to aircraft manufacturing after October 11, 1991. [Doc. No. 25530, 53 FR 26152, July 11, 1988; 53 FR 30906, Aug. 16, 1988, as amended by Amdt. 135-69, 62 FR 38397, July 17, 1997]
Sec. Appendix C to Part 135--Helicopter Flight Recorder Specifications ----------------------------------------------------------------------------------------------------------------
Installed system
\1\ minimum Sampling interval Resolution \3\
Parameters Range accuracy (to (per second) read out
recovered data)----------------------------------------------------------------------------------------------------------------Relative time (from recorded on 25 hr minimum..... 0.125% per
hour.Indicated airspeed.............. Vm in to VD (KIAS) 5% or 1
with installed 0 kts., whichever
pilot-static is greater.
system).Altitude........................ -1,000 ft. to 100 to 7
00 ft. (see Table
1, TSO C51-a).Magnetic heading................ 360[deg].......... 5[deg].Vertical acceleration........... -3g to +6g........ 0.2g in where peaks, ref.
addition to 0 recorded).
.3g maximum datum.Longitudinal acceleration....... 1.0g. eq>1.5% max.
range excluding
datum error of
5%.Pitch attitude.................. 100% of usable 2[deg].Roll attitude................... 60[deg] or eq>2[deg].
100% of usable
range, whichever
is greater.Altitude rate................... 8,000 fpm. eq>10% Resolution 12,000.
250 fpm below
12,000 ft.
indicated.
Engine Power, Each Engine
Main rotor speed................ Maximum range..... 5%.Free or power turbine........... Maximum range..... +5%............... 1................. 1% \2\
Engine torque................... Maximum range..... 5%.
Flight Control--Hydraulic
Pressure
Primary (discrete).............. High/low.......... .................. 1.................Secondary--if applicable High/low.......... .................. 1.................
(discrete).Radio transmitter keying On/off............ .................. 1.................
(discrete).Autopilot engaged (discrete).... Engaged or .................. 1.................
disengaged.SAS status--engaged (discrete).. Engaged/disengaged .................. 1.................SAS fault status (discrete)..... Fault/OK.......... .................. 1.................
Flight Controls
Collective \4\.................. Full range........ 3%.Pedal Position \4\.............. Full range........ 3%.Lat. Cyclic \4\................. Full range........ 3%.Long. Cyclic \4\................ Full range........ 3%.Controllable Stabilator Position Full range........ 3%.----------------------------------------------------------------------------------------------------------------\1\ When data sources are aircraft instruments (except altimeters) of acceptable quality to fly the aircraft the
recording system excluding these sensors (but including all other characteristics of the recording system)
shall contribute no more than half of the values in this column.\2\ Per cent of full range.\3\ This column applies to aircraft manufactured after October 11, 1991.\4\ For all aircraft manufactured on or after December 6, 2010, the sampling interval per second is 4. [Doc. No. 25530, 53 FR 26152, July 11, 1988; 53 FR 30906, Aug. 16, 1988, as amended by Amdt. 135-69, 62 FR 38397, July 17, 1997; Amdt. 135-113, 73 FR 12570, Mar. 7, 2008; 73 FR 15281, Mar. 21, 2008; Amdt. 135-121, 75 FR 17047, Apr. 5, 2010]
Sec. Appendix D to Part 135--Airplane Flight Recorder Specification ----------------------------------------------------------------------------------------------------------------
Accuracy sensor
Parameters Range input to DFDR Sampling interval resolution \4\
readout (per second) read out----------------------------------------------------------------------------------------------------------------Time (GMT or Frame Counter) 24 Hrs............ 0.125% Per seconds).
frame). Hour.Altitude........................ -1,000 ft to max 100 to 7
aircraft. 00 ft (See Table
1, TSO-C51a).Airspeed........................ 50 KIAS to Vso, 5%, 3
%.Heading......................... 360[deg].......... 2[deg].Normal Acceleration (Vertical).. -3g to +6g........ 1% of max
range excluding
datum error of
5%.Pitch Attitude.................. 75[deg]. eq>2[deg].Roll Attitude................... 180[deg]. eq>2[deg].Radio Transmitter Keying........ On-Off (Discrete). .................. 1................. ..................Thrust/Power on Each Engine..... Full range forward 2%.Trailing Edge Flap or Cockpit Full range or each 3[deg] or as
pilot's indicator.Leading Edge Flap on or Cockpit Full range or each 3[deg] or as
pilot's indicator.Thrust Reverser Position........ Stowed, in .................. 1 (per 4 seconds ..................
transit, and per engine).
reverse
(discretion).Ground Spoiler Position/Speed Full range or each 2% unless
higher accuracy
uniquely required.Marker Beacon Passage........... Discrete.......... .................. 1................. ..................Autopilot Engagement............ Discrete.......... .................. 1................. ..................Longitudinal Acceleration....... 1g. eq>1.5% max range
excluding datum
error of 5
%.Pilot Input And/or Surface Full range........ 2[deg] unless
(Pitch, Roll, Yaw) \3\. higher accuracy
uniquely required.Lateral Acceleration............ 1g. eq>1.5% max range
excluding datum
error of 5
%.Pitch Trim Position............. Full range........ 3% unless
higher accuracy
uniquely required.Glideslope Deviation............ 400 Microamps. eq>3%.
Localizer Deviation............. 400 Microamps. eq>3%.AFCS Mode And Engagement Status. Discrete.......... .................. 1................. ..................Radio Altitude.................. -20 ft to 2,500 ft 2 Ft or 3
% whichever is
greater below 500
ft and 5
% above 500 ft.Master Warning.................. Discrete.......... .................. 1................. ..................Main Gear Squat Switch Status... Discrete.......... .................. 1................. ..................Angle of Attack (if recorded As installed...... As installed...... 2................. 0.3% \2\.
directly).Outside Air Temperature or Total -50 [deg]C to +90 2[deg] c.Hydraulics, Each System Low Discrete.......... .................. 0.5............... or 0.5% \2\.
Pressure.Groundspeed..................... As installed...... Most accurate 1................. 0.2% \2\.
systems installed
(IMS equipped
aircraft only).----------------------------------------------------------------------------------------------------------------
If additional recording capacity is available, recording of the following parameters is recommended. The
parameters are listed in order of significance:----------------------------------------------------------------------------------------------------------------Drift Angle..................... When available. As As installed...... 4................. ..................
installed.Wind Speed and Direction........ When available. As As installed...... 4................. ..................
installed.Latitude and Longitude.......... When available. As As installed...... 4................. ..................
installed.Brake pressure/Brake pedal As installed...... As installed...... 1................. ..................
position.Additional engine parameters:
EPR......................... As installed...... As installed...... 1 (per engine).... ..................
N \1\....................... As installed...... As installed...... 1 (per engine).... ..................
N \2\....................... As installed...... As installed...... 1 (per engine).... ..................EGT............................. As installed...... As installed...... 1 (per engine).... ..................Throttle Lever Position......... As installed...... As installed...... 1 (per engine).... ..................Fuel Flow....................... As installed...... As installed...... 1 (per engine).... ..................TCAS:
TA.......................... As installed...... As installed...... 1................. ..................
RA.......................... As installed...... As installed...... 1................. ..................
Sensitivity level (as As installed...... As installed...... 2................. ..................
selected by crew).GPWS (ground proximity warning Discrete.......... .................. 1................. ..................
system).Landing gear or gear selector Discrete.......... .................. 0.25 (1 per 4 ..................
position. seconds).DME 1 and 2 Distance............ 0-200 NM;......... As installed...... 0.25.............. 1mi.Nav 1 and 2 Frequency Selection. Full range........ As installed...... 0.25..............----------------------------------------------------------------------------------------------------------------\1\ When altitude rate is recorded. Altitude rate must have sufficient resolution and sampling to permit the
derivation of altitude to 5 feet.\2\ Per cent of full range.\3\ For airplanes that can demonstrate the capability of deriving either the control input on control movement
(one from the other) for all modes of operation and flight regimes, the ``or'' applies. For airplanes with non-
mechanical control systems (fly-by-wire) the ``and'' applies. In airplanes with split surfaces, suitable
combination of inputs is acceptable in lieu of recording each surface separately.\4\ This column applies to aircraft manufactured after October 11, 1991. [Doc. No. 25530, 53 FR 26153, July 11, 1988; 53 FR 30906, Aug. 16, 1988]
Sec. Appendix E to Part 135--Helicopter Flight Recorder Specifications ----------------------------------------------------------------------------------------------------------------
Accuracy sensor
Parameters Range input to DFDR Sampling interval Resolution \2\
readout (per second) read out----------------------------------------------------------------------------------------------------------------Time (GMT)...................... 24 Hrs............ 0.125% Per seconds).
Hour.Altitude........................ -1,000 ft to max 100 to 7
aircraft. 00 ft (See Table
1, TSO-C51a).Airspeed........................ As the installed 3%.Heading......................... 360[deg].......... 2[deg].
Normal Acceleration (Vertical).. -3g to +6g........ 1% of max
range excluding
datum error of
5%.Pitch Attitude.................. 75[deg]. eq>2[deg].Roll Attitude................... 180[deg]. eq>2[deg].Radio Transmitter Keying........ On-Off (Discrete). .................. 1................. 0.25 secPower in Each Engine: Free Power 0-130% (power 2%. (per engine). \1\
Full range
(Torque).Main Rotor Speed................ 0-130%............ 2%.Altitude Rate................... 6,000 ft/min.Pilot Input--Primary Controls Full range........ 3%.
Cyclic, Lateral Cyclic, Pedal)
\3\.Flight Control Hydraulic Discrete, each .................. 1................. ..................
Pressure Low. circuit.Flight Control Hydraulic Discrete.......... .................. 1................. ..................
Pressure Selector Switch
Position, 1st and 2nd stage.AFCS Mode and Engagement Status. Discrete (5 bits .................. 1................. ..................
necessary).Stability Augmentation System Discrete.......... .................. 1................. ..................
Engage.SAS Fault Status................ Discrete.......... .................. 0.25.............. ..................Main Gearbox Temperature Low.... As installed...... As installed...... 0.25.............. 0.5% \1\Main Gearbox Temperature High... As installed...... As installed...... 0.5............... 0.5% \1\Controllable Stabilator Position Full Range........ 3%.Longitudinal Acceleration....... 1g. eq>1.5% max range
excluding datum
error of 5
%.Lateral Acceleration............ 1g. eq>1.5% max range
excluding datum
of 5%.Master Warning.................. Discrete.......... .................. 1................. ..................Nav 1 and 2 Frequency Selection. Full range........ As installed...... 0.25.............. ..................Outside Air Temperature......... -50 [deg]C to +90 2[deg] c.----------------------------------------------------------------------------------------------------------------\1\ Per cent of full range.\2\ This column applies to aircraft manufactured after October 11, 1991.\3\ For all aircraft manufactured on or after December 6, 2010, the sampling interval per second is 4. [Doc. No. 25530, 53 FR 26154, July 11, 1988; 53 FR 30906, Aug. 16, 1988; Amdt. 135-113, 73 FR 12571, Mar. 7, 2008; 73 FR 15281, Mar. 21, 2008; Amdt. 135-121, 75 FR 17047, Apr. 5, 2010]
Sec. Appendix F to Part 135--Airplane Flight Recorder Specification
The recorded values must meet the designated range, resolution and accuracy requirements during static and dynamic conditions. Dynamic condition means
the parameter is experiencing change at the maximum rate attainable, including the maximum rate of reversal. All data recorded must be correlated in
time to within one second.--------------------------------------------------------------------------------------------------------------------------------------------------------
Accuracy (sensor Seconds per sampling
Parameters Range input) interval Resolution Remarks--------------------------------------------------------------------------------------------------------------------------------------------------------1. Time or Relative Time Counts \1\ 24 Hrs, 0 to 4095..... 0.125% Per Hour. when available.
Counter increments
each 4 seconds of
system operation.2. Pressure Altitude............... -1000 ft to max 100 to . obtained from the
of aircraft. +5000 ft. minus700 air data computer
ft (see table, TSO when practicable.
C124a or TSO C51a).3. Indicated airspeed or Calibrated 50 KIAS or minimum 5% and 3%. air data computer
to 1.2 V.D. when practicable.4. Heading (Primary flight crew 0-360[deg] and 2[deg]. heading can be
``mag''. selected as the
primary heading
reference, a
discrete indicating
selection must be
recorded.
5. Normal Acceleration (Vertical) -3g to +6g............ 1% of max range
excluding datum error
of 5%.6. Pitch Attitude.................. 75%. eq>2[deg]. airplanes operated 0.25 is recommended.
under Sec.
135.152(j).7. Roll Attitude \2\............... 180[deg]. eq>2[deg]. airplanes operated 0.5 is recommended.
under Sec.
135.152(j).8. Manual Radio Transmitter Keying On-Off (Discrete)..... ...................... 1.................... ..................... Preferably each crew
or CVR/DFDR synchronization None.................. member but one
reference. discrete acceptable
for all transmission
provided the CVR/FDR
system complies with
TSO C124a CVR
synchronization
requirements
(paragraph 4.2.1 ED-
55).9. Thrust/Power on each engine-- Full Range Forward.... 2%. (e.g. EPR, N1 or
Torque, NP) as
appropriate to the
particular engine
being recorded to
determine power in
forward and reverse
thrust, including
potential overspeed
condition.10. Autopilot Engagement........... Discrete ``on'' or ...................... 1.................... .....................
``off''.11. Longitudinal Acceleration...... 1g. eq>1.5% max. range
excluding datum error
of 5%.12a. Pitch control(s) position Full Range............ 2[deg] unless airplanes operated have a flight
higher accuracy under Sec. control breakaway
uniquely required. 135.152(j). capability that
allows either pilot
to operate the
controls
independently,
record both control
inputs. The control
inputs may be
sampled alternately
once per second to
produce the sampling
interval of 0.5 or
0.25, as applicable.12b. Pitch control(s) position (fly- Full Range............ 2[deg] unless airplanes operated
higher accuracy under Sec.
uniquely required. 135.152(j).13a. Lateral control position(s) Full Range............ 2[deg] unless airplanes operated have a flight
higher accuracy under Sec. control breakaway
uniquely required. 135.152(j). capability that
allows either pilot
to operate the
controls
independently,
record both control
inputs. The control
inputs may be
sampled alternately
once per second to
produce the sampling
interval of 0.5 or
0.25, as applicable.13b. Lateral control position(s) Full Range............ 2[deg] unless airplanes operated
higher accuracy under Sec.
uniquely required. 135.152(j).
14a. Yaw control position(s) Full Range............ 2[deg] unless have a flight
higher accuracy control breakaway
uniquely required. capability that
allows either pilot
to operate the
controls
independently,
record both control
inputs. The control
inputs may be
sampled alternately
once per second to
produce the sampling
of 0.5 or 0.25, as
applicable.14b. Yaw control position(s) (fly- Full Range............ 2[deg] unless
higher accuracy
uniquely required.15. Pitch control surface(s) Full Range............ 2[deg] unless airplanes operated with multiple or
higher accuracy under Sec. split surfaces, a
uniquely required. 135.152(j).. suitable combination
of inputs is
acceptable in lieu
of recording each
surface separately.
The control surfaces
may be sampled
alternately to
produce the sampling
interval of 0.5 or
0.25, as applicable.16. Lateral control surface(s) Full Range............ 2[deg] unless airplanes operated combination of
higher accuracy under Sec. surface position
uniquely required. 135.152(j). sensors is
acceptable in lieu
of recording each
surface separately.
The control surfaces
may be sampled
alternately to
produce the sampling
interval of 0.5 or
0.25, as applicable.17. Yaw control surface(s) position Full Range............ 2[deg] unless multiple or split
higher accuracy surfaces, a suitable
uniquely required. combination of
surface position
sensors is
acceptable in lieu
of recording each
surface separately.
The control surfaces
may be sampled
alternately to
produce the sampling
interval of 0.5.18. Lateral Acceleration........... 1g. eq>1.5% max. range
excluding datum error
of 5%.19. Pitch Trim Surface Position.... Full Range............ 3[deg] Unless
Higher Accuracy
Uniquely Required.20. Trailing Edge Flap or Cockpit Full Range or Each 3[deg] or as cockpit control may
Pilot's Indicator. each be sampled
alternately at 4
second intervals, to
give a data point
every 2 seconds.21. Leading Edge Flap or Cockpit Full Range or Each 3[deg] or as of flap position and
Pilot's Indicator and cockpit control may
sufficient to each be sampled at 4
determine each second intervals, so
discrete position. as to give a data
point to every 2
seconds.22. Each Thrust reverser Position Stowed, In Transit, ...................... 1 (per engine........ ..................... Turbo-jet--2
(or equivalent for propeller and reverse discretes enable the
airplane). (Discrete). 3 states to be
determined
Turbo-prop--1
discrete
23. Ground Spoiler Position or Full Range or Each 2[deg] Unless airplanes operated
Higher Accuracy under Sec.
Uniquely Required. 135.152(j).24. Outside Air Temperature or -50 [deg]C to +90 2 [deg]C.25. Autopilot/Autothrottle/AFCS A suitable combination ...................... 1.................... ..................... Discretes should show
Mode and Engagement Status. of discretes. which systems are
engaged and which
primary modes are
controlling the
flight path and
speed of the
aircraft.26. Radio Altitude \14\............ -20 ft to 2,500 ft.... 2 ft or 3% radio altimeter
Whichever is Greater should be recorded,
Below 500 ft and but arranged so that
5% Above 500 ft. recorded each
second.27. Localizer Deviation, MLS 400 Microamps or minus3% 3 operations. Each
available sensor recommended.. system should be
range as installed recorded but
62[deg]. least one is
recorded each
second. It is not
necessary to record
ILS and MLS at the
same time, only the
approach aid in use
need be recorded.28. Glideslope Deviation, MLS 400 Microamps or minus3% 3 operations. Each
Deviation. available sensor recommended. system should be
range as installed. recorded but
0.9 to + 30[deg]...... arranged so that at
least one is
recorded each
second. It is not
necessary to record
ILS and MLS at the
same time, only the
approach aid in use
need be recorded.29. Marker Beacon Passage.......... Discrete ``on'' or ...................... 1.................... ..................... A single discrete is
``off''. acceptable for all
markers.30. Master Warning................. Discrete.............. ...................... 1.................... ..................... Record the master
warning and record
each ``red'' warning
that cannot be
determined from
other parameters or
from the cockpit
voice recorder.31. Air/ground sensor (primary Discrete ``air'' or ...................... 1 (0.25 recommended.)
airplane system reference nose or ``ground''.
main gear).32. Angle of Attack (If measured As installed.......... As installed.......... 2 or 0.5 for 0.3% of full range... If left and right
directly). airplanes operated sensors are
under Sec. available, each may
135.152(j). be recorded at 4 or
1 second intervals,
as appropriate, so
as to give a data
point at 2 seconds
or 0.5 second, as
required.33. Hydraulic Pressure Low, Each Discrete or available 5%.
or ``normal''.34. Groundspeed.................... As installed.......... Most Accurate Systems 1.................... 0.2% of full range. .....................
Installed.35. GPWS (ground proximity warning Discrete ``warning'' ...................... 1.................... ..................... A suitable
system). or ``off''. combination of
discretes unless
recorder capacity is
limited in which
case a single
discrete for all
modes is acceptable.
36. Landing Gear Position or Discrete.............. ...................... 4.................... ..................... A suitable
Landing gear cockpit control combination of
selection. discretes should be
recorded.37. Drift Angle \15\............... As installed.......... As installed.......... 4.................... 0.1[deg]38. Wind Speed and Direction....... As installed.......... As installed.......... 4 1 knot, and 1.0[deg]. .....................39. Latitude and Longitude......... As installed.......... As installed.......... 4.................... 0.002[deg], or as Provided by the
installed. Primary Navigation
System Reference.
Where capacity
permits latitude/
longitude resolution
should be
0.0002[deg].40. Stick shaker and pusher Discrete(s) ``on'' or ...................... 1.................... ..................... A suitable
activation. ``off''. combination of
discretes to
determine
activation.41. Windshear Detection............ Discrete ``warning'' ...................... 1.
or ``off''.42. Throttle/power lever position Full Range............ 2%. non-mechanically
linked cockpit
engine controls.43. Additional Engine Parameters... As installed.......... As installed.......... Each engine each 2% of full range..... Where capacity
second. permits, the
preferred priority
is indicated
vibration level, N2,
EGT, Fuel Flow, Fuel
Cut-off lever
position and N3,
unless engine
manufacturer
recommends
otherwise.44. Traffic Alert and Collision Discretes............. As installed.......... 1.................... ..................... A suitable
Avoidance System (TCAS). combination of
discretes should be
recorded to
determine the status
of--Combined
Control, Vertical
Control, Up
Advisory, and down
advisory. (ref.
ARINC Characteristic
735 Attachment 6E,
TCAS VERTICAL RA
DATA OUTPUT WORD.)45. DME 1 and 2 Distance........... 0-200 NM;............. As installed.......... 4.................... 1 NM................. 1 mile.46. Nav 1 and 2 Selected Frequency. Full range............ As installed.......... 4.................... ..................... Sufficient to
determine selected
frequency.47. Selected barometric setting.... Full Range............ 5%.48. Selected altitude.............. Full Range............ 5%.49. Selected speed................. Full Range............ 5%.50. Selected Mach.................. Full Range............ 5%.51. Selected vertical speed........ Full Range............ 5%.52. Selected heading............... Full Range............ 5%.53. Selected flight path........... Full Range............ 5%.54. Selected decision height....... Full Range............ 5%.55. EFIS display format............ Discrete(s)........... ...................... 4.................... ..................... Discretes should show
the display system
status (e.g., off,
normal, fail,
composite, sector,
plan, nav aids,
weather radar,
range, copy.
56. Multi-function/Engine Alerts Discrete(s)........... ...................... 4.................... ..................... Discretes should show
Display format. the display system
status (e.g., off,
normal, fail, and
the identity of
display pages for
emergency
procedures, need not
be recorded.57. Thrust comand \17\............. Full Range............ 2%.58. Thrust target.................. Full Range............ 2%.59. Fuel quantity in CG trim tank.. Full Range............ 5%.60. Primary Navigation System Discrete GPS, INS, VOR/ ...................... 4.................... ..................... A suitable
Reference. DME, MLS, Loran C, combination of
Omega, Localizer discretes to
Glidescope. determine the
Primary Navigation
System reference.61. Ice Detection.................. Discrete ``ice'' or ...................... 4.
``no ice''.62. Engine warning each engine Discrete.............. ...................... 1.
vibration.63. Engine warning each engine over Discrete.............. ...................... 1.
temp..64. Engine warning each engine oil Discrete.............. ...................... 1.
pressure low.65. Engine warning each engine over Discrete.............. ...................... 1.
speed.66. Yaw Trim Surface Position...... Full Range............ 3% Unless Higher
Accuracy Uniquely
Required.67. Roll Trim Surface Position..... Full Range............ 3% Unless Higher
Accuracy Uniquely
Required.68. Brake Pressure (left and right) As installed.......... 5%. effort applied by
pilots or by
autobrakes.69. Brake Pedal Application (left Discrete or Analog 5% (Analog). applied by pilots.
``off''.70. Yaw or sideslip angle.......... Full Range............ 5%.71. Engine bleed valve position.... Discrete ``open'' or ...................... 4.
``closed''.72. De-icing or anti-icing system Discrete ``on'' or ...................... 4.
selection. ``off''.73. Computed center of gravity..... Full Range............ 5%.74. AC electrical bus status....... Discrete ``power'' or ...................... 4.................... ..................... Each bus.
``off''.75. DC electrical bus status....... Discrete ``power'' or ...................... 4.................... ..................... Each bus.
``off''.76. APU bleed valve position....... Discrete ``open'' or ...................... 4.
``closed''.77. Hydraulic Pressure (each Full range............ 5%.78. Loss of cabin pressure......... Discrete ``loss'' or ...................... 1.
``normal''.
79. Computer failure (critical Discrete ``fail'' or ...................... 4.
flight and engine control systems). ``normal''.80. Heads-up display (when an Discrete(s) ``on'' or ...................... 4.
information source is installed). ``off''.81. Para-visual display (when an Discrete(s) ``on'' or ...................... 1.
information source is installed). ``off''.82. Cockpit trim control input Full Range............ 5%. means for control
inputs are not
available, cockpit
display trim
positions should be
recorded.83. Cockpit trim control input Full Range............ 5%. means for control
inputs are not
available, cockpit
display trim
position should be
recorded.84. Cockpit trim control input Full Range............ 5%. means for control
input are not
available, cockpit
display trim
positions should be
recorded.85. Trailing edge flap and cockpit Full Range............ 5%. and cockpit flap
control position may
each be sampled
alternately at 4
second intervals to
provide a sample
each 0.5 second.86. Leading edge flap and cockpit Full Range or Discrete 5%.87. Ground spoiler position and Full Range or Discrete 5%.88. All cockpit flight control Full Range Control 5[deg]. flight control
control column, rudder pedal) \18\. thn-eq>70 lbs. systems, where
Control column 85 surface position is
lbs. Rudder pedal a function of the
165 lbs. control input device
only, it is not
necessary to record
this parameter. For
airplanes that have
a flight control
breakaway capability
that allows either
pilot to operate the
control
independently,
record both control
force inputs. The
control force inputs
may be sampled
alternately once per
2 seconds to produce
the sampling
interval of 1.--------------------------------------------------------------------------------------------------------------------------------------------------------\1\ For A300 B2/B4 airplanes, resolution = 6 seconds.\2\ For A330/A340 series airplanes, resolution = 0.703[deg].\3\ For A318/A319/A320/A321 series airplanes, resolution = 0.275% (0.088[deg]0.064[deg]). For A330/A340 series airplanes, resolution = 2.20%
(0.703[deg]0.064[deg]).\4\ For A318/A319/A320/A321 series airplanes, resolution = 0.22% (0.088[deg]0.080[deg]). For A330/A340 series airplanes, resolution = 1.76%
(0.703[deg]0.080[deg]).\5\ For A330/A340 series airplanes, resolution = 1.18% (0.703[deg]0.120[deg]).\6\ For A330/A340 series airplanes, resolution = 0.783% (0.352[deg]0.090[deg]).
\7\ For A330/A340 series airplanes, aileron resolution = 0.704% (0.352[deg]0.100[deg]). For A330/A340 series airplanes, spoiler resolution =
1.406% (0.703[deg]0.100[deg]).\8\ For A330/A340 series airplanes, resolution = 0.30% (0.176[deg]0.12[deg]). For A330/A340 series airplanes, seconds per sampling interval =
1.\9\ For B-717 series airplanes, resolution = .005g. For Dassault F900C/F900EX airplanes, resolution = .007g.\10\ For A330/A340 series airplanes, resolution = 1.05% (0.250[deg]0.120[deg]).\11\ For A330/A340 series airplanes, resolution = 1.05% (0.250[deg]0.120[deg]). For A300 B2/B4 series airplanes, resolution = 0.92%
(0.230[deg]0.125[deg]).\12\ For A330/A340 series airplanes, spoiler resolution = 1.406% (0.703[deg]0.100[deg]).\13\ For A330/A340 series airplanes, resolution = 0.5 [deg]C.\14\ For Dassault F900C/F900EX airplanes, Radio Altitude resolution = 1.25 ft.\15\ For A330/A340 series airplanes, resolution = 0.352 degrees.\16\ For A318/A319/A320/A321 series airplanes, resolution = 4.32%. For A330/A340 series airplanes, resolution is 3.27% of full range for throttle lever
angle (TLA); for reverse thrust, reverse throttle lever angle (RLA) resolution is nonlinear over the active reverse thrust range, which is 51.54
degrees to 96.14 degrees. The resolved element is 2.8 degrees uniformly over the entire active reverse thrust range, or 2.9% of the full range value
of 96.14 degrees.\17\ For A318/A319/A320/A321 series airplanes, with IAE engines, resolution = 2.58%.\18\ For all aircraft manufactured on or after December 6, 2010, the seconds per sampling interval is 0.125. Each input must be recorded at this rate.
Alternately sampling inputs (interleaving) to meet this sampling interval is prohibited. [Doc. No. 28109, 62 FR 38398, July 17, 1997; 62 FR 48135, Sept. 12, 1997; Amdt. 135-85, 67 FR 54323, Aug. 21, 2002; Amdt. 135-89, 68 FR 42939, July 18, 2003; 68 FR 50069, Aug. 20, 2003; Amdt. 135-113, 73 FR 12570, Mar. 7, 2008; Amdt. 135-121, 75 FR 17047, Apr. 5, 2010; Amdt. 135-120, 75 FR 7357, Feb. 19, 2010]
Sec. Appendix G to Part 135--Extended Operations (ETOPS)
G135.1 Definitions.
G135.1.1 Adequate Airport means an airport that an airplane operator may list with approval from the FAA because that airport meets the landing limitations of Sec. 135.385 or is a military airport that is active and operational.
G135.1.2 ETOPS Alternate Airport means an adequate airport that is designated in a dispatch or flight release for use in the event of a diversion during ETOPS. This definition applies to flight planning and does not in any way limit the authority of the pilot in command during flight.
G135.1.3 ETOPS Entry Point means the first point on the route of an ETOPS flight, determined using a one-engine inoperative cruise speed under standard conditions in still air, that is more than 180 minutes from an adequate airport.
G135.1.4 ETOPS Qualified Person means a person, performing maintenance for the certificate holder, who has satisfactorily completed the certificate holder's ETOPS training program.
G135.2 Requirements.
G135.2.1 General. After August 13, 2008, no certificate holder may operate an airplane, other than an all-cargo airplane with more than two engines, outside the continental United States more than 180 minutes flying time (at the one-engine-inoperative cruise speed under standard conditions in still air) from an airport described in Sec. 135.364 unless--
(a) The certificate holder receives ETOPS approval from the FAA;
(b) The operation is conducted in a multi-engine transport category turbine-powered airplane;
(c) The operation is planned to be no more than 240 minutes flying time (at the one engine inoperative cruise speed under standard conditions in still air) from an airport described in Sec. 135.364; and
(d) The certificate holder meets the requirements of this appendix.
G135.2.2 Required certificate holder experience prior to conducting ETOPS.
Before applying for ETOPS approval, the certificate holder must have at least 12 months experience conducting international operations (excluding Canada and Mexico) with multi-engine transport category turbine-engine powered airplanes. The certificate holder may consider the following experience as international operations:
(a) Operations to or from the State of Hawaii.
(b) For certificate holders granted approval to operate under part 135 or part 121 before February 15, 2007, up to 6 months of domestic operating experience and operations in Canada and Mexico in multi-engine transport category turbojet-powered airplanes may be credited as part of the required 12 months of international experience required by paragraph G135.2.2(a) of this appendix.
(c) ETOPS experience with other aircraft types to the extent authorized by the FAA.
G135.2.3 Airplane requirements. No certificate holder may conduct ETOPS in an airplane that was manufactured after February 17, 2015 unless the airplane meets the standards of Sec. 25.1535.
G135.2.4 Crew information requirements. The certificate holder must ensure that flight crews have in-flight access to current weather and operational information needed to comply with Sec. 135.83, Sec. 135.225, and Sec. 135.229. This includes information on all ETOPS Alternate Airports, all destination alternates, and the destination airport proposed for each ETOPS flight.
G135.2.5 Operational Requirements.
(a) No person may allow a flight to continue beyond its ETOPS Entry Point unless--
(1) The weather conditions at each ETOPS Alternate Airport are forecast to be at or above the operating minima in the certificate holder's operations specifications for that airport when it might be used (from the earliest to the latest possible landing time), and
(3) All ETOPS Alternate Airports within the authorized ETOPS maximum diversion time are reviewed for any changes in conditions that have occurred since dispatch.
(b) In the event that an operator cannot comply with paragraph G135.2.5(a)(1) of this appendix for a specific airport, another ETOPS Alternate Airport must be substituted within the maximum ETOPS diversion time that could be authorized for that flight with weather conditions at or above operating minima.
(c) Pilots must plan and conduct ETOPS under instrument flight rules.
(d) Time-Limited Systems.
(1) Except as provided in paragraph G135.2.5(d)(3) of this appendix, the time required to fly the distance to each ETOPS Alternate Airport (at the all-engines-operating cruise speed, corrected for wind and temperature) may not exceed the time specified in the Airplane Flight Manual for the airplane's most limiting fire suppression system time required by regulation for any cargo or baggage compartments (if installed), minus 15 minutes.
(2) Except as provided in G135.2.5(d)(3) of this appendix, the time required to fly the distance to each ETOPS Alternate Airport (at the approved one-engine-inoperative cruise speed, corrected for wind and temperature) may not exceed the time specified in the Airplane Flight Manual for the airplane's most time limited system time (other than the airplane's most limiting fire suppression system time required by regulation for any cargo or baggage compartments), minus 15 minutes.
(3) A certificate holder operating an airplane without the Airplane Flight Manual information needed to comply with paragraphs G135.2.5(d)(1) and (d)(2) of this appendix, may continue ETOPS with that airplane until February 17, 2015.
G135.2.6 Communications Requirements.
(a) No person may conduct an ETOPS flight unless the following communications equipment, appropriate to the route to be flown, is installed and operational:
(1) Two independent communication transmitters, at least one of which allows voice communication.
(2) Two independent communication receivers, at least one of which allows voice communication.
(3) Two headsets, or one headset and one speaker.
(b) In areas where voice communication facilities are not available, or are of such poor quality that voice communication is not possible, communication using an alternative system must be substituted.
G135.2.7 Fuel Requirements. No person may dispatch or release for flight an ETOPS flight unless, considering wind and other weather conditions expected, it has the fuel otherwise required by this part and enough fuel to satisfy each of the following requirements:
(a) Fuel to fly to an ETOPS Alternate Airport. (1) Fuel to account for rapid decompression and engine failure. The airplane must carry the greater of the following amounts of fuel:
(1) Fuel to account for rapid decompression and engine failure. The airplane must carry the greater of the following amounts of fuel:
(i) Fuel sufficient to fly to an ETOPS Alternate Airport assuming a rapid decompression at the most critical point followed by descent to a safe altitude in compliance with the oxygen supply requirements of Sec. 135.157;
(ii) Fuel sufficient to fly to an ETOPS Alternate Airport (at the one-engine-inoperative cruise speed under standard conditions in still air) assuming a rapid decompression and a simultaneous engine failure at the most critical point followed by descent to a safe altitude in compliance with the oxygen requirements of Sec. 135.157; or
(iii) Fuel sufficient to fly to an ETOPS Alternate Airport (at the one-engine-inoperative cruise speed under standard conditions in still air) assuming an engine failure at the most critical point followed by descent to the one engine inoperative cruise altitude.
(2) Fuel to account for errors in wind forecasting. In calculating the amount of fuel required by paragraph G135.2.7(a)(1) of this appendix, the certificate holder must increase the actual forecast wind speed by 5% (resulting in an increase in headwind or a decrease in tailwind) to account for any potential errors in wind forecasting. If a certificate holder is not using the actual forecast wind based on a wind model accepted by the FAA, the airplane must carry additional fuel equal to 5% of the fuel required by paragraph G135.2.7(a) of this appendix, as reserve fuel to allow for errors in wind data.
(3) Fuel to account for icing. In calculating the amount of fuel required by paragraph G135.2.7(a)(1) of this appendix, (after completing the wind calculation in G135.2.7(a)(2) of this appendix), the certificate holder must ensure that the airplane carries the greater of the following amounts of fuel in anticipation of possible icing during the diversion:
(i) Fuel that would be burned as a result of airframe icing during 10 percent of the time icing is forecast (including the fuel used by engine and wing anti-ice during this period).
(ii) Fuel that would be used for engine anti-ice, and if appropriate wing anti-ice, for the entire time during which icing is forecast.
(4) Fuel to account for engine deterioration. In calculating the amount of fuel required by paragraph G135.2.7(a)(1) of this appendix (after completing the wind calculation in paragraph G135.2.7(a)(2) of this appendix), the certificate holder must ensure the airplane also carries fuel equal to 5% of the fuel specified above, to account for deterioration in cruise fuel burn performance unless the certificate holder has a program to monitor airplane in-service deterioration to cruise fuel burn performance.
(b) Fuel to account for holding, approach, and landing. In addition to the fuel required by paragraph G135.2.7 (a) of this appendix, the airplane must carry fuel sufficient to hold at 1500 feet above field elevation for 15 minutes upon reaching the ETOPS Alternate Airport and then conduct an instrument approach and land.
(c) Fuel to account for APU use. If an APU is a required power source, the certificate holder must account for its fuel consumption during the appropriate phases of flight.
G135.2.8 Maintenance Program Requirements. In order to conduct an ETOPS flight under Sec. 135.364, each certificate holder must develop and comply with the ETOPS maintenance program as authorized in the certificate holder's operations specifications for each two-engine airplane-engine combination used in ETOPS. This provision does not apply to operations using an airplane with more than two engines. The certificate holder must develop this ETOPS maintenance program to supplement the maintenance program currently approved for the operator. This ETOPS maintenance program must include the following elements:
(a) ETOPS maintenance document. The certificate holder must have an ETOPS maintenance document for use by each person involved in ETOPS. The document must--
(1) List each ETOPS Significant System,
(2) Refer to or include all of the ETOPS maintenance elements in this section,
(3) Refer to or include all supportive programs and procedures,
(4) Refer to or include all duties and responsibilities, and
(5) Clearly state where referenced material is located in the certificate holder's document system.
(b) ETOPS pre-departure service check. The certificate holder must develop a pre-departure check tailored to their specific operation.
(1) The certificate holder must complete a pre-departure service check immediately before each ETOPS flight.
(2) At a minimum, this check must:
(i) Verify the condition of all ETOPS Significant Systems;
(ii) Verify the overall status of the airplane by reviewing applicable maintenance records; and
(iii) Include an interior and exterior inspection to include a determination of engine and APU oil levels and consumption rates.
(3) An appropriately trained maintenance person, who is ETOPS qualified must accomplish and certify by signature ETOPS specific tasks. Before an ETOPS flight may commence, an ETOPS pre-departure service check (PDSC) Signatory Person, who has been authorized by the certificate holder, must certify by signature, that the ETOPS PDSC has been completed.
(4) For the purposes of this paragraph (b) only, the following definitions apply:
(i) ETOPS qualified person: A person is ETOPS qualified when that person satisfactorily completes the operator's ETOPS training program and is authorized by the certificate holder.
(ii) ETOPS PDSC Signatory Person: A person is an ETOPS PDSC Signatory Person when that person is ETOPS Qualified and that person:
(A) When certifying the completion of the ETOPS PDSC in the United States:
(1) Works for an operator authorized to engage in part 135 or 121 operation or works for a part 145 repair station; and
(2) Holds a U.S. Mechanic's Certificate with airframe and powerplant ratings.
(B) When certifying the completion of the ETOPS PDSC outside of the U.S. holds a certificate in accordance with Sec. 43.17(c)(1) of this chapter; or
(C) When certifying the completion of the ETOPS PDSC outside the U.S. holds the certificates needed or has the requisite experience or training to return aircraft to service on behalf of an ETOPS maintenance entity.
(iii) ETOPS maintenance entity: An entity authorized to perform ETOPS maintenance and complete ETOPS pre-departure service checks and that entity is:
(A) Certificated to engage in part 135 or 121 operations;
(B) Repair station certificated under part 145 of this title; or
(C) Entity authorized pursuant to Sec. 43.17(c)(2) of this chapter.
(c) Limitations on dual maintenance. (1) Except as specified in paragraph G135.2.8(c)(2) of this appendix, the certificate holder may not perform scheduled or unscheduled dual maintenance during the same maintenance visit on the same or a substantially similar ETOPS Significant System listed in the ETOPS maintenance document, if the improper maintenance could result in the failure of an ETOPS Significant System.
(1) Except as specified in paragraph G135.2.8(c)(2) of this appendix, the certificate holder may not perform scheduled or unscheduled dual maintenance during the same maintenance visit on the same or a substantially similar ETOPS Significant System listed in the ETOPS maintenance document, if the improper maintenance could result in the failure of an ETOPS Significant System.
(2) In the event dual maintenance as defined in paragraph G135.2.8(c)(1) of this appendix cannot be avoided, the certificate holder may perform maintenance provided:
(i) The maintenance action on each affected ETOPS Significant System is performed by a different technician, or
(ii) The maintenance action on each affected ETOPS Significant System is performed by the same technician under the direct supervision of a second qualified individual; and
(iii) For either paragraph G135.2.8(c)(2)(i) or (ii) of this appendix, a qualified individual conducts a ground verification test and any in-flight verification test required under the program developed pursuant to paragraph G135.2.8(d) of this appendix.
(d) Verification program. The certificate holder must develop a program for the resolution of discrepancies that will ensure the effectiveness of maintenance actions taken on ETOPS Significant Systems. The verification program must identify potential problems and verify satisfactory corrective action. The verification program must include ground verification and in-flight verification policy and procedures. The certificate holder must establish procedures to clearly indicate who is going to initiate the verification action and what action is necessary. The verification action may be performed on an ETOPS revenue flight provided the verification action is documented as satisfactorily completed upon reaching the ETOPS entry point.
(e) Task identification. The certificate holder must identify all ETOPS-specific tasks. An ETOPS qualified person must accomplish and certify by signature that the ETOPS-specific task has been completed.
(f) Centralized maintenance control procedures. The certificate holder must develop procedures for centralized maintenance control for ETOPS.
(g) ETOPS parts control program. The certificate holder must develop an ETOPS parts control program to ensure the proper identification of parts used to maintain the configuration of airplanes used in ETOPS.
(h) Enhanced Continuing Analysis and Surveillance System (E-CASS) program. A certificate holder's existing CASS must be enhanced to include all elements of the ETOPS maintenance program. In addition to the reporting requirements of Sec. 135.415 and Sec. 135.417, the program includes reporting procedures, in the form specified in Sec. 135.415(e), for the following significant events detrimental to ETOPS within 96 hours of the occurrence to the certificate holding district office (CHDO):
(1) IFSDs, except planned IFSDs performed for flight training.
(2) Diversions and turnbacks for failures, malfunctions, or defects associated with any airplane or engine system.
(3) Uncommanded power or thrust changes or surges.
(4) Inability to control the engine or obtain desired power or thrust.
(5) Inadvertent fuel loss or unavailability, or uncorrectable fuel imbalance in flight.
(6) Failures, malfunctions or defects associated with ETOPS Significant Systems.
(7) Any event that would jeopardize the safe flight and landing of the airplane on an ETOPS flight.
(i) Propulsion system monitoring. The certificate holder, in coordination with the CHDO, must--
(1) Establish criteria as to what action is to be taken when adverse trends in propulsion system conditions are detected, and
(2) Investigate common cause effects or systemic errors and submit the findings to the CHDO within 30 days.
(j) Engine condition monitoring. (1) The certificate holder must establish an engine-condition monitoring program to detect deterioration at an early stage and to allow for corrective action before safe operation is affected.
(1) The certificate holder must establish an engine-condition monitoring program to detect deterioration at an early stage and to allow for corrective action before safe operation is affected.
(2) This program must describe the parameters to be monitored, the method of data collection, the method of analyzing data, and the process for taking corrective action.
(3) The program must ensure that engine limit margins are maintained so that a prolonged engine-inoperative diversion may be conducted at approved power levels and in all expected environmental conditions without exceeding approved engine limits. This includes approved limits for items such as rotor speeds and exhaust gas temperatures.
(k) Oil consumption monitoring. The certificate holder must develop an engine oil consumption monitoring program to ensure that there is enough oil to complete each ETOPS flight. APU oil consumption must be included if an APU is required for ETOPS. The operator's consumption limit may not exceed the manufacturer's recommendation. Monitoring must be continuous and include oil added at each ETOPS departure point. The program must compare the amount of oil added at each ETOPS departure point with the running average consumption to identify sudden increases.
(l) APU in-flight start program. If an APU is required for ETOPS, but is not required to run during the ETOPS portion of the flight, the certificate holder must have a program acceptable to the FAA for cold soak in-flight start and run reliability.
(m) Maintenance training. For each airplane-engine combination, the certificate holder must develop a maintenance training program to ensure that it provides training adequate to support ETOPS. It must include ETOPS specific training for all persons involved in ETOPS maintenance that focuses on the special nature of ETOPS. This training must be in addition to the operator's maintenance training program used to qualify individuals for specific airplanes and engines.
(n) Configuration, maintenance, and procedures (CMP) document. The certificate holder must use a system to ensure compliance with the minimum requirements set forth in the current version of the CMP document for each airplane-engine combination that has a CMP.
(o) Reporting. The certificate holder must report quarterly to the CHDO and the airplane and engine manufacturer for each airplane authorized for ETOPS. The report must provide the operating hours and cycles for each airplane.
G135.2.9 Delayed compliance date for all airplanes. A certificate holder need not comply with this appendix for any airplane until August 13, 2008. [Doc. No. FAA-2002-6717, 72 FR 1885, Jan. 16, 2007, as amended by Amdt. 135-108, 72 FR 7348, Feb. 15, 2007; 72 FR 26542, May 10, 2007; Amdt. 135-112, 73 FR 8798, Feb. 15, 2008; Amdt. 135-115, 73 FR 33882, June 16, 2008]