AC 29-2C, Chg 2 4/25/06 AC 29.602 § 29.602 CRITICAL PARTS .
a. Explanation.
(1) Critical parts requirements apply to structural components, rotor drive systems, rotors, and mechanical control systems.
(2) The objective of identifying critical parts is to ensure that critical parts are controlled during design, manufacture, and throughout their service life so that the risk of failure in service is minimized by ensuring that the critical parts maintain the critical characteristics on which certification is based.
(3) Definitions with respect to § 29.602:
(i) The use of the word “could” in paragraph 29.602(a) of the rule means that this failure assessment should consider the effect of flight regime (i.e., forward flight, hover, etc.). The operational environment need not be considered.
(ii) With respect to this rule, the term “catastrophic” means the inability to conduct an autorotation to a safe landing, without exceptional piloting skills, assuming a suitable landing surface is available.
(iii) The use of the word “and” in paragraph 29.602(a) of the rule means the part must have both a catastrophic failure mode together with one or more critical characteristics.
(iv) With respect to this rule, the term “part” means one piece, or two or more pieces permanently joined together.
(v) With respect to this rule, the term “critical characteristic” means any dimension, tolerance, finish, material, or any manufacturing or inspection process, or other feature which cannot tolerate variation from type design requirements and, if nonconforming, would cause failure of the critical part.
(4) Many rotorcraft manufacturers already have procedures in place within their companies for handling “critical parts.” These plans may be required by their dealings with other customers, frequently military (e.g., US DoD, UK MoD, Italian MoD).
Although these plans may have slightly different definitions of “critical parts” which have sometimes been called “Flight Safety Parts,” “Critical Parts,” “Vital Parts,” or “Identifiable Parts,” they have in the past been accepted as meeting the intent of this requirement and providing the expected level of safety. It is acceptable for these plans to use alternative names and terminology provided they meet the intent of this requirement.
b. Procedures. The rotorcraft manufacturer should establish a Critical Parts Plan that identifies and controls the critical characteristics. The policies and procedures which constitute that plan should be such as to ensure that-- Page D - 2
(1) All critical parts of the rotorcraft are identified by means of an appropriate failure assessment and a Critical Parts List is established.
(2) Documentation draws the attention of the personnel involved in the design, manufacture, maintenance, inspection, and overhaul of a critical part to the special nature of the part and details the relevant special instructions. For example all drawings, work sheets, inspection documents, etc., could be prominently annotated with the words "Critical Part" or equivalent and the Instructions for Continued Airworthiness and Overhaul Manuals (if applicable) should clearly identify critical parts and include the needed maintenance and overhaul instructions. The documentation should:
(i) Contain comprehensive instructions for the maintenance, inspection and overhaul of critical parts and emphasize the importance of these special procedures;
(ii) Indicate to operators and overhaulers that unauthorized repairs or modifications to critical parts may have hazardous consequences;
(iii) Emphasize the need for careful handling and protection against damage or corrosion during maintenance, overhaul, storage, and transportation and accurate recording and control of service life (if applicable);
(iv) Require notification of the manufacturer of any unusual wear or deterioration of critical parts and the return of affected parts for investigation when appropriate;
(3) Procedures should be established for identifying and controlling critical characteristics.
(4) To the extent needed for control of critical characteristics, procedures and processes for manufacturing critical parts (including test articles) are defined (for example material source, forging procedures, machining operations and sequence, inspection techniques, and acceptance and rejection criteria). Procedures for changing these manufacturing procedures should also be established.
(5) Any changes to the manufacturing procedures, to the design of a critical part, to the approved operating environment, or to the design loading spectrum are evaluated to establish the effects, if any, on the fatigue evaluation of the part.
(6) Materials review procedures for critical parts (i.e., procedures for determining the disposition of parts having manufacturing errors or material flaws) are in accordance with paragraphs (4) and (5) above.
(7) Critical parts are identified as required, and relevant records relating to the identification are maintained such that it is possible to establish the manufacturing history of the individual parts or batches of parts.
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AC 29-2C, Chg 4 5/1/2014
(8) The critical characteristics of critical parts produced in whole or in part by suppliers are maintained.
AC 29.603. § 29.603 (Amendment 29-17) MATERIALS.
a. Explanation. The rule requires that the suitability and durability of materials, the failure of which could adversely affect safety, must be determined by three-fold considerations:
(1) Considerations based on experience or tests.
(2) Meeting approved specifications.
(3) Taking into account environmental conditions such as temperature and humidity.
b. Procedures.
(1) Experience may be used to show a material’s resistance to wear and deterioration from environmental effects (environmental effects include both natural environmental effects such as exposure to sunlight, water, salt spray, etc., and installation environmental effects such as exposure to fuel, hydraulic fluids, deicing fluids, etc.). Installation environmental e ffects should consider both direct exposure contact and expected migration of potentially deleterious fluids and compounds.
Testing for environmental effects may use either coupon testing, full-scale testing, or a combination. A combination of te sting and experience may also be used.
(i) MIL-HDBK’s-5, -17, and -23 include consideration of some environmental effects and contain reference to additional methods of testing for environmental effects.
(ii) The use of AC 20-107A, Composite Aircraft Structure, is recommended for environmental and damage tolerance considerations of advanced composite materials. (Also see sections 29.573 and AC 29 MG 8 of this AC.)
(iii) The effects of excessive wear and delamination of elastomeric and self-lubricated bearings used in critical load carrying applications in relation to redistribution of loading should be considered.
(2) Where possible, materials that meet widely accepted specifications such as AISI, SAE, MIL, or AMS and alloys which have favorable experience or tests should be used. Where company-developed materials are used, approved specifications are required to ensure the developed properties are duplicated in each lot of material.
Documented specification usage is necessary to maintain quality assurance of materials.
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(3) Section 29.613 concerns strength properties and design values. (See paragraph AC 29.613.)
AC 29.605. § 29.605 (Amendment 29-17) FABRICATION METHODS.
a. Explanation. The basic requirement of this rule is that the methods of fabrication must produce sound structure and produce it consistently.
(1) A process specification is required for fabrication processes requiring close control.
(2) A test program is explicitly required for each new aircraft fabrication method.
b. Procedures.
(1) The approved specifications required by this rule may either be established government/industry specifications such as MIL, AISI, ASTM, or SAE, or the specifications may be company-developed proprietary specifications. Sufficient data should be provided to the FAA/AUTHORITY aircraft engineering offices to show that the desired features are provided by the process specification. In addition, sufficient process controls, inspections, and tests should be coordinated with FAA/AUTHORITY manufacturing inspection personnel to ensure that continued quality of the process is provided.
(2) In addition to the examples given by the rule; i.e., gluing, spot welding, and heat treating process, specifications should also be prepared for types of welding other than spot welding, for platings of metals, for protective finishes (other than decorative), for sealing, and for unique fabrication methods such as those used for composite materials.
(3) The required test programs should consider static strength effects, fatigue strength effects, and environmental effects as appropriate to the processes.
(4) During the fabrication of advanced composite materials, the effects of fabrication anomalies (i.e., disbonds, voids, porosity) should be considered. Special nondestruct testing inspection techniques and procedures should be developed to cover fabrication with allowable anomalies and permitted repair procedures. (See also paragraph AC 29 MG 8.)
AC 29.607. § 29.607 (Amendment 29-5) FASTENERS.
a. Explanation. Section 29.607 of Amendment 29-5 requires dual locking removable fasteners in critical locations. A nonfriction locking device is specifically required in any bolt subject to rotation, as stated in the rules.
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b. Procedures. Advisory Circular 20-71, Dual Locking Devices or Fasteners, December 8, 1970, contains information, procedures, and means of complying with § 29.607 of Amendment 29-5.
AC 29.609. § 29.609 PROTECTION OF STRUCTURE.
a. Explanation. The structure should be suitably protected as specified in the rule to maintain its design strength. Ventilation and drainage provisions must be provided as specified in the rule. Overboard drains should be furnished for corrosive or waste liquids. Drains for flammable fluids are specified in other rules such as §§ 29.999 and
29.1187.
b. Procedures.
(1) The structure may be preserved, painted, or treated with chemical films to protect it from strength deterioration. An approved process specification should be used for these types of treatments.
(2) Parts may be plated or chemically treated, such as anodized, for protection.
An evaluation and substantiation may be required to assure the structure or parts are not adversely affected during, or as a result of, the plating or treatment process.
(§ 29.605 concerns approval of process specifications and fabrication methods.)
(3) Plating or material surface hardness or composition changes may require fatigue substantiation to assure the fatigue strength is not altered or is otherwise properly assessed. An approved process specification should be used for these types of treatments.
(4) To prevent water accumulation, drain holes should be placed at possible dams such as bulkheads, and at low points in the fuselage and in the stabilizing surfaces.
(5) Control tubes and tubes used as primary mount structures (i.e., transmission support structure and engine mount structure) should be designed to prevent entry and collection of corrosive fluids or vapor, including water.
(i) A closed insert in each tube end may be used.
(ii) A s ealant applied around the tube ends and around each rivet head may be used.
(6) Overboar d drains should discharge clear of the entire rotorcraft. Dyed water discharged in flight, may be used to assure fluids are properly drained.
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(7) Welded tubes should be flushed and sealed after welding in accordance with an approved process specification.
(8) Refer to AC 43-4, “Corrosion Control for Aircraft,“ for further procedures.
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AC 29-2C, Chg 4 5/1/2014 AC 29.610. § 29.610 (Amendment 29-53) LIGHTNING AND STATIC ELECTRICITY PROTECTION.
a. Background. During the initial devel opment and promulgation of airworthiness standards, rotorcraft operated primarily in a VFR and non-icing environment. A prudent pilot avoided thunderstorms where the possibility of encountering severe weather and a lightning strike was much greater. Now, many rotorcraft are authorized to fly under IFR and into known icing conditions. Because many rotorcraft now use the same advanced technologies in structures and systems as fixed-wing aircraft, a specific rule on lightning protection of rotorcraft was adopted in Amendment 29-24. Am endment 29-40 revised the title of § 29.610 to include protection from static electricity, and a new § 29.610(d) was added specifying requirements for electrical bonding and protection against lightning and static electricity. Amendment 29-53 removed the system lightning protection requirements for electrical and electronic equipment in § 29.610(d)(4) because those requirements were implemented in the new § 29.1316.
b. Explanation.
(1) The regulation requires protection of rotorcraft from the catastrophic effects of lightning. This means that lightning must not prevent the continued safe flight and landing of the rotorcraft.
(2) Rotorcraft structural components, propulsion system, gearboxes, and mechanical and hydraulic control systems should be designed to ensure lightning will not prevent continued safe flight and landing of the rotorcraft (i.e., damage due to lightning currents that flow through any of the components must not result in catastrophic failure).
c. Procedures.
(1) Certification Plan. A formal written certification plan is an acceptable means to ensure demonstration of regulatory compliance. This plan is also useful to identify and define an acceptable resolution to the critical issues early in the certification process. These are the usual steps to follow when utilizing a certification plan:
(i) Prepare a certification plan that describes the analytical procedures and qualification tests to be utilized to demonstrate lightning and static electricity protection effectiveness. Test proposals should describe the rotorcraft and system to be utilized, test drawing(s) as required, the method of installation that simulates the production installation, the lightning zone(s) applicable, the lightning simulation method(s), test voltage or current waveforms to be used, diagnostic methods, and the appropriate schedules and location(s) of proposed test(s).
(ii) Obtain FAA/AUTHORITY concurrence that the certification plan is adequate.
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(iii) Obtain FAA/AUTHORITY detail part conformity of the test articles and installation conformity of applicable portions of the test setup. Obtain FAA/AUTHORITY approval of the test proposal. A comprehensive test proposal may be used.
(iv) Schedule FAA/AUTHORITY witnessing of the test or tests proposed.
(v) Submit a test report describing all results and obtain FAA/AUTHORITY approval of each report prepared.
(2) Lightning Environment and Zones. AC 20-155 refers to SAE documents ARP5412 (or EUROCAE ED-84) and ARP5414 (or EUROCAE ED-91), which provide acceptable definitions for the rotorcraft lightning environment and for rotorcraft lightning attachment zones.
(3) Testing. Tests may be required to check the adequacy of the lightning and electrostatic charge protection. Refer to SAE ARP5416 (or EUROCAE ED-105) for acceptable test methods to show that the lightning protection is effective and to SAE ARP5672 for acceptable test methods to show rotorcraft electrostatic charge control.
(4) Aircraft Lightning Protection Design Features. The Aircraft Lightning Protection Handbook (DOT/FAA/CT-89/22) provides information on aircraft lightning protection design. The following are examples where lightning protection should be considered.
(i) Rotors and Control Systems.
(A) It should be established that an adequate bonding path exists between the rotors and the airframe, such that a lightning strike to a rotor will not result in damage to or seizure of gearbox or swashplate bearings, control jacks, etc.
(B) Each hinge and bearing of rotor blades and control surfaces should either:
(1) be capable of withstanding lightning without damage or seizure leading to loss of function, or
(2) be provided with at least one bonding conductor, as flexible and short as possible and installed so that there is no danger of the conductor jamming the hinge or bearing following a lightning strike.
(ii) External Non-Metallic Parts.
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AC 29-2C, Chg 4 5/1/2014 (A) Where non-metallic parts are fitted externally to the rotorcraft (e.g., rotors, radomes, composite skin panels) and may be subjected to lightning, they should be protected. The protection should consider disruption of the materials because of:
(1) rapid expansion of gases within them (e.g., water vapor),
(2) rapid build-up of pressure in voids or in the enclosure provided by the parts resulting in mechanical disruption of the parts themselves or of the structure enclosed by them, and
(3) fire caused by the ignition of the materials themselves or of the materials contained within the enclosures.
(B) Materials used for external non-metallic parts should have low water absorption characteristics, should not occlude gases, and should be of high dielectric strength in order to encourage surface flashover rather than puncture.
(C) Rotors and other external parts of nonmetallic construction should be provided with effective lightning conductors that are capable of safely carrying lightning current, unless it can be shown that damage due to lightning will not endanger the rotorcraft or its occupants. Bonding straps and leads are not required for small gaps between metallic structure and diverters in non-conducting panels in order to comply with the lightning protection criteria. However, an el ectrical bonding path may be required to achieve static electricity protection.
(5) Protection Against the Effects Static Electricity.
(i) General. Rotorcraft structure, rotor systems, and equipment should be electrically bonded together to minimize the accumulation and discharge of electrostatic charge, which could result in electrical shock, ignition of flammable vapors, or interference with essential equipment such as radio communications and navigational aids.
(ii) Intermittent Contact. The design should prevent random intermittent contact between metallic or metallized parts such that unwanted radio interference or degradation of the components due to sparking will not occur.
(iii) Rotors and other external parts of nonmetallic construction should be provided with effective electrical conductors that are capable of safely conducting electrostatic charge.
(iv) High Pressure Refueling and Fuel Transfer. Where prov ision is made for high pressure refueling or high rates of fuel transfer, it should be established, by test, or by consultation with the appropriate fuel manufacturers, that dangerously high voltages Page D - 10
will not be induced within the fuel system. If compliance with this requirement involves any restriction on the types of fuel to be used or on the use of additives, an appropriate operating limitation should be established under § 29.1501(a). The critical refueling rates are related to the rotorcraft refueling installations, and the designer should seek the advice of fuel suppliers on this problem.
(A) With standard refueling equipment and standard aircraft turbine fuels, voltages high enough to cause sparking may be induced between the surface of the fuel and metal parts of the tank at refueling rates above approximately 250 gal/min. These induced voltages may be increased by the presence of additives and contaminants
(e.g., anti-corrosion inhibitors, lubricating oil, free water) and by splashing or spraying of the fuel in the tank.
(B) The static charge can be reduced as follows:
(1) by means taken in the refueling equipment such as increasing the diameter of refueling lines and designing filters to give the minimum of electrostatic charging, or
(2) by changing the electrical properties of the fuel by the use of antistatic additives and thus reducing the accumulation of static charge in the tank to a negligible amount.
(6) Fuel Systems. Requirements for lightning protection for fuel systems are in § 29.954. AC 20-53B provides guidance on compliance with § 29.954. Section 29.954 of this AC addresses the protection required for systems.
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AC 29-2C, Chg 4 5/1/2014 AC 29.611. § 29.611 INSPECTION PROVISIONS.
a. Explanation. The rotorcraft must have access panels, or openings, that will allow for proper maintenance and/or adjustment of the rotorcraft systems.
(1) The rule states: There must be means to allow close examination of each part that requires recurring inspection, adjustment for proper alignment and functioning, or lubrication.
(2) “Structural” or load-carrying access panels may be used to comply with the rule. Structural panels should have stencils or permanent labels (§ 29.1541(a)(2)) stating the panels must be installed prior to ground or flight operation.
(3) Holes or “nonstructural” access panels should be used whenever possible.
b. Procedures.
(1) The determination of compliance can be accomplished in conjunction with the following activities:
(i) Reviewing type design drawings.
(ii) Conformity inspections accomplished during certification testing.
(iii) Be evaluated during the control system proof and operation tests (§§ 29.681 and 29.683).
(iv) During type inspection tests and functioning and reliability testing.
(2) Equipment requiring frequent inspections (at less than 25-hour intervals), lubrication, or adjustments should be accessible through “nonstructural” doors. Areas or items requiring daily attention should be accessible through “nonstructural” doors since properly rated maintenance personnel are required to “open and close,” or reinstall structural panels and special design features, such as multiple pins and latches, are generally necessary for structural doors.
(3) If the rotorcraft is subject to an FAA Maintenance Review Board Approval Program, further review of the rotorcraft inspection provisions will be obtained.
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AC 29.613. § 29.613 (Amendment 29-17) MATERIAL STRENGTH PROPERTIES AND DESIGN VALUES.
a. Explanation. The rule requires the use of materials that have a known minimum strength value. The structur e must not be understrength and must be designed to minimize fatigue failure.
(1) Material design values in certain specified documents may be used. The FAA/AUTHORITY may approve other material design values thus allowing the applicant greater flexibility in selection of materials by proving their strength properties and design values as stated in § 29.613(d).
(2) Other materials that may be new or are not included in the specified documents may be tested and design values established as provided by § 29.613(a) and (d).
(3) Section 29.613(d) requires the selection of materials that will retain design values and properties in the type of service environment and for the length of service time intended for the structure.
(4) Section 29.613(c) is an objective rule concerning minimizing fatigue failures.
Paragraph AC 29.571, § 29.571, concerns quantitative fatigue substantiation requirements.
b. Procedures.
(1) The properties and design values in the documents noted in the rule may be used.
(2) MIL-HDBK-5, Metallic Materials and Elements for Flight Vehicle Structure, Chapter 9, contains procedures for establishing design values of additional materials.
Uniform means of presenting the data is also contained in this chapter.
(3) Design values and properties must include effects of the service environment and service time. An example is exposure at elevated temperatures on the ultimate tensile strength of 7079-T6 aluminum alloys as found in figure 3.7.4.1.1(c) of MIL-HDBK-5C.
(4) The probability of disastrous fatigue failures must be minimized. This may be accomplished by using design features usually identified as fail-safe features, such as the following. (See paragraph AC 29.571 fo r the fatigue requirement information.)
(i) Selection of materials and stress levels that provide a controlled slow rate of crack propagation combined with high residual strength after initiation of cracks (lightly loaded structures).
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