(5) AC 43.13-1B, Acceptable Methods, Techniques, and Practices - Aircraft Inspection and Repair.
(6) AC 43.13-2A, Acceptable Methods, Techniques, and Practices - Aircraft Alterations.
(7) AC 43-210, Standardized Procedures for Requesting Field Approval of Data, Major Alterations, and Repairs.
(8) AC 91-60, The Continued Airworthiness of Older Airplanes.
(9) AC 120-77, Maintenance and Alteration Data.
5. BACKGROUND.
a. Maintenance personnel have raised questions and concerns regarding their authority to fabricate aircraft parts during the course of performing maintenance and alterations on a product or part thereof. Typically, such questions center around whether a person needs an approval under 14 CFR part 21 to produce parts for installation on type-certificated products or whether it is permissible to use the maintenance rules outlined in 14 CFR part 43 to fabricate parts for consumption during maintenance or alteration. Previous questions were evaluated against regulatory criteria and answered on a case-by-case basis.
b. It is important to emphasize that design and production rules differ from maintenance and alteration rules. Therefore, it is crucial that the FAA organization responsible for each of these different activities is appropriately involved when acquiring approvals. For example, FSDO inspectors have the necessary knowledge on requirements for maintaining a product, whereas Manufacturing Inspection District Office (MIDO) inspectors possess the expertise and familiarity with the requirements for manufacturing parts and their use of specific materials and processes. Compliance with both the maintenance and manufacturing requirements is the only way a certificate holder can ensure that a fabricated part is airworthy. This AC provides guidance for establishing a system that ensures the same level of safety for parts fabricated under 14 CFR part 43, for maintenance or repair purposes, as those produced under the production rules under 14 CFR part 21.
c. Any person who engages in the design, production, operation, maintenance, or alteration of a civil aviation product is responsible for ensuring that the part/product conforms to its approved design and is in condition for safe operation. Therefore, an appropriately rated certificate holder that fabricates a part in the course of performing maintenance or alterations must possess:
(1) Approved design data or data acceptable to the Administrator that is determined by the CAT classification for the part being fabricated; and
(2) A fabrication quality control system (FQCS) to ensure each fabricated part conforms to its design data and is in a condition for safe operation.
6. FABRICATION UNDER 14 CFR PARTS 21 AND 43.
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a. Many elements affect the nature of the processes and extent of the requirements needed to fabricate parts during the course of performing maintenance and/or an alteration. This includes such elements as: the criticality (application) of the part being fabricated, any processes required for fabrication, sufficiency of design data, equipment necessary for fabrication of the part, and the extent of FAA involvement in data approval to ensure airworthiness requirements are satisfied. Parts design data may be approved under 14 CFR part 21, § 21.305(d) and fabricated under 14 CFR, part 43, § 43.13(a) and (b), providing the fabricator installs the part onto or within the product or part thereof while it is undergoing repair or alteration.
NOTE: A certificate holder that desires to sell his/her fabricated parts separately (i.e., outside the course of performing maintenance or an alteration) must obtain a PMA (refer to 14 CFR part 21, § 21.303(a)).
b. Parts fabrication must be performed within the privileges and limitations of the certificate holder's FAA authorization and ratings, and IAW his/her established quality control system.
c. When a subcontractor is used in the fabrication process, the certificate holder under whose surveillance the fabrication occurs must control the design, manufacture, and quality of the part. The work performed by the subcontractor must be documented to support a determination of conformance to the purchase order requirements and substantiated by a maintenance record. The documentation must describe any special processes. Subcontractors must be subject to control and audit by the certificate holder fabricating the part for return to service.
d. Procedures for addressing the criteria recommended in paragraph 6d(1) through (7) below must be documented and recorded in a manual or similar type of document, easily understood, and readily available to the person(s) fabricating the part(s).
(1) Required Data. This data must include the following, dependent on the CAT of the part as defined in paragraph 7.
(a) For CAT 1 and CAT 2 Parts:
1. Drawings and specifications necessary to show the configuration of the fabricated part.
2. Information on materials, dimensions, and processes (including special manufacturing processes) necessary to define the structural strength or other critical characteristics of the fabricated part.
3. Inspection and test procedures.
4. Substantiating data (test reports, analysis, computations, and assessments) necessary to show that the design data used to fabricate the part for a repair or alteration meets the applicable airworthiness standards and that no detrimental consequences will result in degradation to the next higher-level subassembly or assembly, or to the product.
5. Airworthiness limitations, as applicable.
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6. Instructions for continued airworthiness (ICA)/maintenance instructions if the application for design approval is sought for a product or article in which the fabricated part is eligible for installation, was filed on or after January 28, 1981.
7. Fabricated part marking.
(b) For CAT 3 Parts: Data adequate to substantiate that the fabricated part as consumed within the repair or during the alteration returns the product to its original or properly altered condition, e.g., AC 43.13-2A, Service Bulletins, component maintenance manual (CMM), service history, or prior service experience, etc., IAW 14 CFR part 43, § 43.13(b).
NOTE: All fabrication repairs of parts must be accomplished IAW methods, techniques, and practices acceptable to the Administrator IAW 14 CFR part 43, § 43.13(a).
(2) FQCS. In order to substantiate and demonstrate that a part being fabricated during the course of performing maintenance conforms to the approved design data and is in condition for safe operation, quality control system procedures should be established for ensuring all processes and requirements necessary to fabricate the product or part thereof are identified and adhered to.
The depth and detail of the fabrication quality control system depends on the complexity and CAT classification of the part being fabricated. The following are recommended elements that could be addressed in the fabricator’s quality control system:
(a) Materials and services used in the fabrication process should be properly identified and inspected to ensure that they conform to the applicable design data, including their physical and chemical properties, and other characteristics affecting airworthiness.
(b) A list of the parts fabricated by nomenclature and part number.
(c) Name and location of any fabrication subcontractor(s) involved must be included in the quality control system, or recorded and maintained separately, and must be made available to the FAA upon request. The methods used to qualify subcontractors and to control the design and quality of the finished part should also be addressed within the quality control system.
(d) Materials used in such fabrication that may be subject to damage or deterioration
(e.g., composite material, shelf life-limited, sealants, etc.,) must be suitably stored, documented, and adequately protected.
(e) Processes affecting the quality and safety of the finished product must be accomplished IAW acceptable specifications by trained and qualified personnel.
(f) Fabrication methods used, including any special fabrication processes, must be adequately controlled and contain instructions such as acceptable methods, techniques, and practices for performing the work, and be documented as established by the quality control system.
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(g) Specifications used must have definitive and verifiable standards for evaluating airworthiness, including in-process inspections, as appropriate, and a final inspection before the part's release for use in a repair or alteration.
(h) All part fabrication and inspection data must be current and readily available to fabrication inspection personnel and FAA inspectors.
(i) Changes to design data must be evaluated by the certificate holder before being incorporated into the finished part IAW the requirements outlined in Appendix 1.
(j) Rejected materials must be segregated and identified in such a manner as to preclude further use.
(k) Fabrication and inspection records associated with the part must be retained IAW regulatory requirements.
(3) Part Marking. Except as noted below, fabricated parts must be clearly identified with an additional permanent and legible marking.
(a) The marking must include the following:
1. The name, trademark, or symbol of the FAA certificate holder (fabricator) under whose control the fabrication occurred;
2. A unique part number that clearly distinguishes the fabricated part; and
3. The original manufacturer’s part number if removed as a result of the fabrication.
(b) Critical parts must be marked IAW 14 CFR part 45, § 45.14. This part marking provides traceability for subsequent operators and maintenance providers to the source of the fabricated part.
NOTE: In cases where it is impractical to mark the fabricated part without compromising the airworthiness (integrity) of the part, the marking information should be included in the maintenance records for the part or part thereof.
(4) ICA. Under 14 CFR part 21, § 21.50, design approval holders are required to develop and distribute information essential to continued airworthiness of their parts and/or products.
Typically, these instructions are included in maintenance and overhaul manuals to describe the methods, techniques, and practices for performing inspections, maintenance, preventive maintenance, and alterations to ensure that the affected products are maintained in an airworthy condition. Certain sections of the ICA, and any changes to those sections, (e.g., airworthiness limitations, wiring diagrams, or SRM revisions) require FAA approval. When parts are fabricated during the course of performing maintenance, the fabricator must address the following ICA requirements that may be applicable to the fabricated part(s).
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(a) Determine whether the existing ICA for the original part is sufficient to ensure the fabricated part continues to meet all airworthiness requirements.
(b) In cases where the original part manufacturer’s ICA has been determined to be inadequate, the fabricator must develop its own ICA to ensure continued airworthiness of the fabricated or affected part.
(c) When it is necessary to develop a new ICA, current inspection criteria essential to the airworthiness of the part(s) must be maintained and kept current.
(d) When the certificate holder develops its own ICA, it must be provided with the part and made available to any other person requesting the ICA for maintaining the fabricated parts.
(e) Revision control for the ICA must be maintained to ensure it remains applicable.
This is particularly important when changes are made to the original product and the ICAs were changed to accommodate installation of a fabricated part.
NOTE: Each Aircraft Certification Service Directorate has an established Aircraft Evaluation Group (AEG) that is part of Flight Standards Service (AFS) and is directly responsible for the operational and maintenance aspects of the certification process.
(5) Fabrication of Multiple Parts. A quantity of identical parts bearing the same part number may be fabricated at the same time, providing they will be consumed in later repairs by the certificate holder that fabricated those parts. Controls should be in place to prevent separate sales of these specific parts (i.e., sales to other persons independent of the repair). If a certificate holder desires to sell its fabricated part(s) separately, it must obtain a PMA. The fabrication of multiple parts is not to be used as a means to circumvent the requirements of 14 CFR part 21, § 21.303(a).
(6) Recordkeeping. Fabrication of a part IAW this AC is subject to the maintenance recordkeeping provisions of 14 CFR part 43, § 43.9. A recordkeeping system should be established for documenting fabricated parts containing sufficient information to determine the airworthiness status of the part. Information contained in the maintenance record entry could include a description of work performed, date of work completion, person approving return to service, current status of any Airworthiness Directives (AD), current inspection status, and current status of life-limited parts. These maintenance records should be retained with the aircraft records.
(7) Destruction of Replaced Material. Material replaced by the fabricated part should be mutilated/destroyed beyond any possibility of repair or reassembly and should not be retained for future use.
7. DETERMINING PART CATEGORY.
a. Criticality Level — Category Parts List (CPL).
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(1) For the purposes of this AC, the FAA recommends use of the CPL (a copy of the CPL can be found in Appendix 2 of this AC), in combination with other factors, to determine a part’s criticality level. The CPL classifies parts into one of three categories depending on their effect on safety. The CPL should be used as a guide in determining a parts criticality. It’s important to understand that not all component parts have been addressed on this list, and therefore, specific questions concerning parts not addressed can be evaluated by contacting the certificate holding ACO.
(2) When used in the context of this AC, this CPL is a means to determine the criticality category of the part and the level of AIR involvement needed in the design data approval process for certificate holders fabricating parts.
NOTE: No part, or fabricated part thereof, that is the subject of an AD can be installed on an aircraft without complying with the AD or obtaining an alternative method of compliance (AMOC) approval from the responsible ACO.
b. Part Categories.
(1) CAT 1 Part. A fabricated part, the failure of which could prevent continued safe flight and landing; resulting consequences could reduce safety margins, degrade performance, or cause loss of capability to conduct certain flight operations.
(a) Design Issues. A CAT 1 part is a part intended to be consumed within a major repair or major alteration. The certificating ACO, through the geographic ACO, must approve the design data. The list of data to be submitted to the ACO can be found in paragraph 6d(1)(a).
The ACO will make the determination of necessary data for development and submittal based on each circumstance. In the case of a CAT 1 part, a DER may only “recommend approval” of the design data.
(b) Fabrication Issues. The certificate holder is responsible for ensuring all aspects of the FQCS are addressed and satisfied. The guidelines provided in paragraph 6d(2) should be used to develop the FQCS for compliance.
(2) CAT 2 Part. A fabricated part, the failure of which would not prevent continued safe flight and landing, but would reduce the capability of the aircraft or the ability of the flightcrew to cope with adverse operating conditions or subsequent failures.
(a) Design Issues. A CAT 2 part is a part intended to be consumed within a major repair or major alteration. Design data is required to be approved by the geographic ACO or appropriately authorized DER. The list of required data to be submitted to the ACO or the DER for approval can be found in paragraph 6d(1)(a).
(b) Fabrication Issues. The certificate holder is responsible for ensuring all aspects of the FQCS are addressed and satisfied. The guidelines provided in paragraph 6d(2) should be used to develop the FQCS for compliance.
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(3) CAT 3 Part. A fabricated part, the failure of which would have no effect on the continued safe flight and landing of the aircraft.
(a) Design Issues. The fabrication of a CAT 3 part will generally require only acceptable data. Fabrication of this type of part will typically result in no involvement by Aircraft Certification Service (AIR) unless the Flight Standards Service aviation safety inspector (ASI) requests assistance.
(b) Fabrication Issues. The certificate holder is responsible for ensuring all aspects of the FQCS are addressed and satisfied. The guidelines provided in Appendix 1 should be used to develop the fabrication quality control system for compliance with paragraph 6d(1)(b).
NOTE: A summary of the certificate holder requirements for data based on the CAT of the part can be found in Appendix 1.
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Appendix 1 Page 1 (and 2) APPENDIX 1. SUMMARY OF REQUIREMENTS FOR CERTIFICATE HOLDERS SEEKING TO FABRICATE PARTS PURSUANT TO TITLE 14 OF THE FEDERAL CODE OF REGULATIONS (14 CFR) PART 21 AND PART 43
Fabrication Part Category FQCS Required Manual Procedures ACO Design Data Approval DER Approval Authority FSDO Review of FQCS 1 Yes Yes Yes Certificating ACO through the Geographical ACO (Recommend Approval Only) Yes 2 Yes Yes Yes Geographic ACO Yes Yes 3 Yes Yes Only Acceptable Data is Required for this Category, ACO Intervention Only on Request by AFS Yes, but not Required Yes Fabrication part categories used in this AC were derived from FAA Order 8120.2, Production Approval and Certificate Management Procedures.
Category 1 Part: A fabricated part, the failure of which could prevent continued safe flight and landing; resulting consequences could reduce safety margins, degrade performance, or cause loss of capability to conduct certain flight operations.
Category 2 Part: A fabricated part, the failure of which would not prevent continued safe flight and landing, but would reduce the capability of the aircraft or the ability of the crew to cope with adverse operating conditions or subsequent failures.
Category 3 Part: A fabricated part the failure of which would have no effect on the continued safe flight and landing of the aircraft.
Appendix 2 P age 1 APPENDIX 2. CATEGORY PARTS LIST Note: The information contained in this Appendix should be used as a guideline in determining a parts criticality. It is not all inclusive and specific questions concerning parts not addressed can be evaluated by contacting the certificate holding ACO.
The CPL has not been reviewed for update since July 1, 2004 and is not scheduled for any future update. Current FAA Safety Management System initiatives could render the CPL obsolete at which time it will be eliminated. The CPL posted on the Internet is for information only and if used for other purposes than what is stated above it is solely at the user's risk.
Structural Assemblies CFR part Structural Elements CFR part Hydraulic Pneumatic Components CFR part Propulsion System Components CFR part Systems and Equipment CFR part Fuselage (23-1), (25-1) 23, 25 Fuselage Structural Elements Pressure Bulkheads (23-1), (25-1) Keel Beam (25- 1) Longeron/Stringer (25-2) Floor Beam (25-2) Plates/Skins (25-2) Fuselage to Wing Attach Fitti ngs (25-1) Stabilizer to Fuselage Attach Fitti ngs (25-1) Gear to Fuselage attach Fitti ngs (25-1) Door Hinge (on Fuselage) ( 25-1) Fuselage Panels (23-1), (25-1) 23, 25 Hydraulic Main Pump (23-
1), (25-2), (27-1), (29-1) Main Accumulator (25-2) Main Reservoir (25-2) Auxiliary Pump (25-2) 23, 25, 27, 29 Softwar e Thrust (EEC) ( 23-
1), (25-1) 23, 25 Electrical Power System Alternator/Generator Drive Syste m (25-2) AC Gener ator-Alter nator (25-2) AC Inverter (25-2) Phase Adapter (25-2) AC Regulator (25 -2) Fire Protection Smoke Detection (25-2), (27-2), (29-
2) Fire Detection (25-2), (27-2), (29-2) Overheat Detection (25-2), (27-2), (29-2) Extinguishing Syste m (25-2), (27-2), (29-2) Fire Bottle-Fixed (25-2), (27-2), (29-2) 25, 27, 29 Flight Contr ol Surfaces Ailerons (23-1), (25-1) Rudder (23-1), (25-1) TE Flaps (23-1), (25-2) LE Devices (25-2) Elevator (23-1), (25-1) Spoilers (25-2) 23, 25 Flight Contr ol Structural Elements Ailer on Tabs ( 25-2) Jackscrew ( 23-1) , (25-1) Bellcr anks (23-1), (25-1) Flight Control Cables (23-1), (25-1) 23, 25 Flight Control Servo Actuators (25-2), (27-1), (29-1) Flap Actuator (25-
2) Rudder Actu ator (25-
2) Stabi lizer Actuator (25-2) 25, 27, 29 Thrust Reversers (23-1), (25-2) Auxiliary Power Units (23-1) FADEC (23-1) 23, 25 Fuel System Boost Pumps (23-1), (25-2), Transfer Valves (23-
1), (25-2) Fuel S.O.V. (23-1), (25-1) Digital Fuel Flow System (25-2) Fuel Du mp (25-2) Fuel Hose ( Single engine appl ications ONLY) (23-2) (27-2), (29-2) Fuel Quantity Indicator (25-2), (27-2), (29-2) Fuel Flow Indicating (27-2), (29-2) Fuel Pressu re Indicating (27-2), (29-2) Fuel Pump (25-2), (27-1), (29-1) Oil Coo ler (Single engine applicatio ns ONLY) ( 23-2) (27-2), (29-2) Crew Oxygen Sy stem 23, 25, 27, 29
Appendix 2
CATEGORY PARTS LIST Structural Assemb lies CFR part Structural Elements CFR part Hydraulic Pneumatic Components CFR part Propulsion System Components CFR part Systems and Equipment CFR part (27-2), (29-2) Indicating System Warning, Caution, and Advisory Lights (27-2), (29-2), Main Rotor Indicating System (27-2), (29-2) Engine Power (27-2), (29-2) Engine Temperature (27-2), (29-
2)
Empennage Structural Elements Horizontal Empennage Horizontal Stabilizers (23-1), (25-
1) Elevators (23-1), (25-1) Vertical Stabilizers (23-1), (25-1) Rudder (23-1), (25-1) 23, 25 Stabilizer Spars/Ribs (25-2) Plate s/Skins (25-
2) Tab Structure (25-2) Attach Fitting (25-2) Empennage Structural Elements Elevator Spars/Ribs (25-2) Plates/Skins (25-2) Tab Structure (25-2) Attach Fitting Elevator Tab (25-2) Empennage Structural Elements Vertical Stabilizer Spars/Ribs (25-2) Plates /Skins (25-2) Att ach Fitting (25-2) Ventral Structu re (25-2) Empennage Structural Elements Horizontal Stabilizer Spars/Ribs (25-2) Plates/Skins (25-2) Tab Structure (25-2) Attach Fitting (25-
2) 25 Control Valves (23-2), (25-2) Shut Off Valves (23-2), (25-2) Rudder Power Control Units (23-
1), (25-2) Rudder Power Control Unit (Boeing 737) (25-1) 23, 25 Engine Cowling Systems Inlets(23-1), (25-2) Nacelles (23-1), (25-2) Fairings (23-1), (25-2) 23, 25 Brake System and Assembly Components Brakes(23-1), (25-1) Anti-Skid Valves (23-2), (25-2) Wheel Assemblies (23-1) (25-2) Tire Casing (25-2) Tire Tube (25-2) Anti Skid Section (25-2) Master Cylinder/Brake Valve (25-1) 23, 25 NOTAR (High Speed Fan) (27-
1), (29-1) Automatic Flight Control Wing Structure (23-1), (25-1) 23, 25 Wing Structure Structural Elements Panels (23-1), (25-2) Wing Webs (23-1), (25-2) Spars (23-
1), (25-1) Ribs/Bulkheads (25-
2) Longeron/Stringers (25-2) Center Wing Box (25-1) Auxilliary Structure (25-2) Wing Attach Fitting (25-1) NAC/Pylon Wing Fitting ( 23-
1), (25-1) 23, 25 Airborne Software Controlled Equipment Software Level A (per RTCA/DO 178B), (23-1) (25-1), (33-1) Software Levels B, or C (per RTCA/DO 178B) (23-2) (25-
2), (33-2) 23, 25, 33 Systems/Stability Aug mentation Systems Flight Control Computers (27-
1), (29-2) Servo/Linear Actuators (27-1), (29-1) Electrical Power Systems AC Generator (27-2), (29-2) AC Inverters (27-2), (29-2) 27, 29
Appendix 2 P age 3
CATEGORY PARTS LIST Structural CFR Structural CFR Hydraulic Pneumatic CFR Propulsion System CFR Systems and CFR Assemblies part Elements part Components part Components part Equipment part Blended Winglet (25-2) Battery (27-2), (29-2) Starter Generator (27-2), (29-2) Main Rotor 27, 29 Main Rotor Control 27, 29 Propellers 35 Drive Systems 27, 29 Hubs (27-1), (29-1) Swashplates (27-1), (29-1) (Hubs (35-1), Blades (35-1) Masts (27-1), (29-1) Trunnions (27-1), (29-1) Swashplate Drives (27-1), Blade Retention Devices Gear Boxes (27-1), Yokes (27-1), (29-1) (29-1) (35-1) (29-1) Spindles (27-1), (29-1) Anti-Drives (27-1), (29-1) Counter Weights (35-1) Driveshafts (27-1), Grips (27-1), (29-1) Anti- Links (27-1), (29-1) Pitch Control Systems (29-1) Pitch Horns (27-1), (29-1) Pitch Change Links (27-1), Including PCU (35-1) Bearings (27-1), (29-1) Drag Braces (27-1), (29-1) (29-1) Governors (35-1) Hanger Bearings (27-1), Blades (27-1), (29-1) Drive Links (27-1), (29-1) Actuators (35-1) (29-1) Blade Spars (27-1), (29-1) Drive-Levers (27-1), (29-1) PCU Mechanisms (35-1) Clutches (27-1), (29-1) Damper Hubs (27-1), (29-1) Gimbal Stabilizer Bars (27-1), Propeller Electronic Controls Couplings (27-1), (29-1) Retention Pins/Straps/Bolts (29-1) (35-1), and Transmissions (27-1), (29-1) Mixing Levers (27-1), (29-1) Propeller Valve Modules Cases (27-1), (29-1) Tension-Torsion Straps (27-1), Collective Sleeves (27-1), (35-1) Gears (27-1), (29-1) (29-1) (29-1) Clutches (27-1), (29-1) Strap Packs (27-1), (29-1) Cyclic & Collective Control Oil Pumps (27-1), (29-1) Pillow Blocks (27-1, (29-1) Sticks (27-1), (29-1) Bearings (27-1), (29-1) Droop Restraint Bolts (27-1), Actuator Supports (27-1), (29-1) (29-1) Elastomeric Dampers (27-1), Control System (29-1) Tubes/Bolts/Pins (27-1), Bearings (27-1), (29-1) (29-1) Bushings (27-1), (29-1) Nose Section (23-1), (25-1) 23, 25 Fuel Tank Structure 23, Drive Belts (27-1), (29-1) 27, 29 Stall Warning (23-2), (25-2) 23, 25 Radomes (23-2), (25-2) Fuel Cell (23-1), (25-1), (27-1), 25, (29-1) 27, 29 Nacelles/Pylons (23-1), (25-1) 23, 25 Nacelles/Pylons Structural 23, 25 Gas Turbine Engines- 33 Anti-Ice System 25, Doors Elements 27, 29 Engine Rotors Pitot/Static Anti-Ice (25-2) 27, 29 Passenger Crew Doors (25-1) Attachment Fittings (25-1), Fan Blades (33-1), Air Foil Anti Ice/Deice Emergency Exit Door (25-2) (27-1), (29-1) Disks (33-1), Blisks (33-1), (25-2), (27-2), (29-2) Landing Gear Doors (25-2) Bulkhead/Firewalls Impellers (33-1), Spools Window/Windshield & Doors Cargo Baggage Door (25-2) (Nac/Pylon) (25-2), (Drum Rotors) (33-1), (25-2) Longerons/Stringers Thermal Shields for cooling Antenna/Radome Anti Ice (Nac/Pylon) (25-2) of main rotors (33-1), (25-2) Plates/Skins (Nac/Pylon) Cooling Plates (33-1), Intake Anti-Ice/Deice (27-2), (25-2) Main Rotor Rotating Spacers (29-2) Attach Fittings (Nac/Pylon) and Seals (33-1), Main Line (25-1), (27-1), (29-1) Engine Shafts (i.e., low and Engine Struts (23-1), (25-1), high pressure rotor shafts, (27-1), (29-1) propeller shafts for turboprop Engine Mounts (23-1), (25-1), applications and power (27-1), (29-1) transmission shafts for input Pylon Lift/Link Assemblies to propeller and transmission (27-1), (29-1) gearboxes) (33-1), Main Line
Appendix 2
CATEGORY PARTS LIST Structural Ass emblies CFR part Structural Elements CFR part Hydraulic Pneumatic Components CFR part Propulsion System Components CFR part Systems and Equipment CFR part Gas Turbine Engines (Con't) Engine Bearings (33-2), Rotating Compressor & Turbine Air foils (33-2), Spinner s (33-2), Main Engine Mounts (i.e., redundant designs)(33-1), High Pressure Vessels (i.e. Casting subject to compressor discharge pressure & combuster Pressure) (33-1), Containment Structures (33-1), Primary Structures (i.e. structures that provide support and rigidity of the main engine backbone and for attachment of engine to airframe) (33-1), Main Engine Mounts (i.e., redundant designs) (33-2), Electronic Engine Controls/Full Authority Digital Electronic Controls (33-2), Gas Path (Static & Variable Nozzle Guide Vanes) (33-
2), Control System Actuators (33-
2), Combustion Liners (33-2), Fuel Nozzles (33-2) 33 Airborne SoftwareFlight Control Mechanisms (23-1), (25-1) 23, 25 Lift/Compression Struts (23-1) Flying Wires (23-1) Floats (23-1), Skis (23-1) Tail Wh eels (23 -1) 23 Reciprocating Engines Crankshafts (33-1) Connectin g Rods Assembly (33-1) Pis tons (33-1) Wrist Pins (33-1) Cylinders (33-1) Cylind er Heads (33-1) Engine Mounts (33-1 ) Crankcase ( 33-2) Crankshaft Bearings (33-2) Valve Train (valves, valve springs, pushrods, camshafts, rocker shaft assembly) (33-2) Fuel Delivery Systems (carburetors, injectors, fuel pumps) (33-2), Valve Train/Accessory Drive Gears (33-
2) 33 Systems Software Level A (per RTCA/DO 178B ), (23-1) (25-1), (27-1), (29-1) Software Levels B, or C (per RTCA/DO 178B ) (23-2) (25-2), (27-2), (29-2) Navigation System Wind Shear Detection System (25-2) Ground Pr oximity System (25-2) Air Collision Avoidan ce (TCAS) (25-2) Air Speed Indicator (27- 2), (29-2) Altimeter (27-2), (29-2) Air Data Computer (27-2), (29-2) Attitud e Gyro and I ndication (27-2), (29-
2) Directional Gyro and 23, 25, 27, 29