Fabrication of Aircraft parts by Maintenance Personnel

©

Advisory

U.S. Department of Transportation Federal Aviation

Circular

Administration Subject: Fabrication of Aircraft Parts by Date: 06/07/11 AC No: 43-18 Maintenance Personnel Initiated by: AFS-300 Change: 2 1. PURPOSE. This advisory circular (AC) has been revised to update AC 43-18, Fabrication of Aircraft Parts by Maintenance Personnel, dated February 29, 2008.

2. PRINCIPLE CHANGES. This change updates information regarding the fabrication quality control system (FQCS), AC references, and all references related to Title 14 of the Code of Federal Regulations (14 CFR) part 21.

PAGE CONTROL CHART Remove Pages Dated Insert Pages Dated 1 1 06/07/11 02/29/08 4 thru 11 02/29/08 4thrull 06/07/11 Appendix 1 02/29/08 Appendix 1 06/07/11 ORIGINAL Signed by /s/ John McGraw for John M. Allen Director, Flight Standards Service

©

Advisory

U.S. Department of Transportation Federal Aviation

Circular

Administration Subject: Fabrication of Aircraft Parts by Date: 2/29/08 AC No: 43-18 Maintenance Personnel Initiated by: AFS-300 Change: 1 1. PURPOSE. This advisory circular (AC) has been revised to update AC 43-18, Fabrication of Aircraft Parts by Maintenance Personnel, dated March 24,2006.

2. PRINCIPLE CHANGES. This change updates guidance, including all references related to Title 14 of the Code of Federal Regulations (14 CFR).

PAGE CONTROL CHART Remove Pages Insert Pages Dated Dated 1 thru 11 03/24/06 I t h r u l l 2/29/08 ORIGINAL SIGNED BY John M. Allen for James J. Ballough Director, Flight Standards Service

® Advisory

U.S. Department of Transportation

Federal Aviation Circular

Administration Subject: Fabrication of Aircraft Parts by Date: 06/07/11 AC No: 43-18 ! Maintenance Personnel _ | | | | d t t o d b y ; A F S 3 0 ( ) C h a n g e ; 2 1. PURPOSE. This advisory circular (AC) ensures that parts fabricated during maintenance and alteration have an equivalent level of safety as those parts produced under the original design holder's production certificate. This AC provides one means of complying with the requirements of Title 14 of the Code of Federal Regulations (14 CFR) parts 21 and 43 for the design and fabrication of parts by persons performing maintenance and alterations using methods, techniques, and practices acceptable to the Administrator. As required by regulations, such parts fabrication and their implementation must be accomplished "in such a manner...that the condition of the aircraft, airframe, aircraft engine, propeller, or appliance worked on will be at least equal to its original or properly altered condition." This AC is not mandatory and does not constitute a regulation. It outlines one method (but not the only method) of compliance with the rules. A person may elect to follow an alternative method, provided the Federal Aviation Administration (FAA) finds the alternative method to be an acceptable means of complying with the applicable requirements of 14 CFR.

2. RELATED 14 CFR PARTS.

a. Part 1, Definitions and Abbreviations.

b. Part 21, Certification Procedures for Products and Parts.

c. Part 23, Airworthiness Standards: Normal, Utility, Acrobatic, and Commuter Category Airplanes.

d. Part 25, Airworthiness Standards: Transport Category Airplanes.

e. Part 27, Airworthiness Standards: Normal Category Rotorcraft.

f. Part 29, Airworthiness Standards: Transport Category Rotorcraft.

g. Part 31, Airworthiness Standards: Manned Free Balloons.

h. Part 33, Airworthiness Standards: Aircraft Engines.

AC 43-18 3/24/06 i. Part 35, Airworthiness Standards: Propellers.

j . Part 39, Airworthiness Directives.

k. Part 43, Maintenance, Preventive Maintenance, Rebuilding, and Alteration.

1. Part 45, Identification and Registration Marking.

m. Part 65, Certification: Airmen Other than Flight Crewmembers.

n. Part 91, General Operating and Flight Rules, o. Part 145, Repair Stations.

p. Part 183, Representatives of the Administrator.

3. DEFINITIONS. The following definitions apply for this AC: a. Acceptable Data. Data is acceptable to the Administrator when used within the context of maintenance, a minor repair, or an alteration if the data substantiates that the product has been returned to its original or properly altered condition. Acceptable data may establish that the fabricated part complies with applicable airworthiness standards (i.e., regulations). When acceptable data is used to substantiate that the article meets the regulatory requirements and will be returned to its original or properly altered condition, it can be considered acceptable to the Administrator.

b. Airworthy. The term "airworthy" is defined in 14 CFR part 3. § 3.5(a): a clear understanding of its meaning is essential in making an airworthiness determination. Furthermore, the definition of airworthy applies to type-certificated products (aircraft, aircraft engine, or propeller), and parts thereof. Title 49 of the United States Code (49 U.S.C.) § 44704(c) and 14 CFR part 21, § 21.183(a), (b), and (c) state that the two conditions that must be met for issuance of an airworthiness certificate are: (1) The product must conform to its type certificate (TC). A product conforms to its TC when its configuration and the components installed are as described in the drawings, specifications, and other data that are part of the TC, which includes any Supplemental Type Certificates (STC), Airworthiness Directives (AD), and field-approved alterations incorporated into the product; and (2) The aircraft (product) must be in a condition for safe operation.

NOTE: If one or more of these conditions are not satisfied, the product would not be considered airworthy.

c. Approved Data. Data that has been approved by the FAA and that is used to perform maintenance and alterations on products under part 43. Approved data must be used when performing major repairs and alterations. The FAA approves the data in conjunction with the issuance of a TC, STC, Technical Standard Order Authorization (TSOA), or Parts Page 2 Par 2 2/29/08 AC 43-18 CHG1 Manufacturer Approval (PMA). Other forms of approved data include ADs, letters of engineering design approval issued by an FAA Aircraft Certification Office (ACO), maintenance instructions approved by an FAA Designated Engineering Representative (DER), and FAA-approved Structural Repair Manuals (SRM).

NOTE: While technical and other forms of data are approved under the field approval process as declared on FAA Form 337, such approved data may not be sufficiently detailed to allow for fabrication of parts that are intended for use in multiple applications.

d. Certificate Holder. Any person certificated by the FAA and authorized to perform maintenance, preventive maintenance, rebuilding, and alterations as provided in part 43, § 43.3.

Within the context of this AC, if a certificate holder intends to fabricate a part for maintaining a product he/she may do so only under the provisions (privileges) of his/her certificate.

e. Certificate Management ACO. The ACO responsible for issuing and overseeing the original design or technical approval under TC, STC, TSOA, or PMA of the product or article on which the fabricated part will be installed. The certificate management ACO is also responsible for managing continued airworthiness of a product for as long as it is in service.

t Critical. A term of significance applied to a part or to a function performed by a part. A critical part performs a function of such significance (critical function) to the aircraft on which it is installed that, if it failed, the airworthiness of the aircraft would be degraded to an extent that would preclude continued safe flight or landing.

g. Consumed. A fabricated part is considered consumed in a repair when it is installed into the next higher assembly component part, or within a product by the fabricator, while undergoing maintenance or an alteration.

h. Design. Consists of all drawings and specifications, which may be summarized on a master drawing list. These are necessary to show the configuration of the part(s) and all information on dimensions, tolerances, materials, processes, and procedures necessary to define all characteristics of the part(s), as well as, the Airworthiness Limitations Section (ALS) of the instructions for continued airworthiness (ICA).

i. Fabrication. An act in which a part/subpart is made (fabricated) and consumed by the fabricator on the product, or part thereof, in the course of performing maintenance or alterations in accordance with approved or acceptable data, depending on the category (CAT) classification of the part being fabricated and the applicable regulations. In addition, a maintenance record entry must be made with a description of work performed, date of completion, name of person who performed the work, and a satisfactory signature and FAA certificate number.

j . Flight Standards District Office (FSDO). The FAA FSDO that has the responsibility for certificate management over the certificate holder that is undertaking the fabrication of the part or part thereof.

Par 3 Page 3 AC43-18CHG2 06/07/11 k. Part. For the purposes of this AC, is an article that could be produced under the provisions of 14 CFR part 21 and is eligible for installation on a certificated aircraft without further manufacturing processes.

NOTE: The definition of a part for the purposes of this AC would not include raw materials or repair segments being utilized for the repair or alteration of a part, (i.e., sheet metal stock, sealants, lubricants, raw forgings, or castings, billet material, etc.

1. Parts CATs. Parts are classified into one of three CATs, depending on their potential effect on safety. They are listed on a Category Parts List (CPL). Criteria exists for establishing and identifying part CATs, as discussed in paragraphs 6d(l) and 7b(l) through (3) of this AC.

The criteria details the level of FAA involvement necessary to approve the fabrication of such parts. It also specifies the level of technical data, quality control system, procedures development, and processes necessary to substantiate fabrication of such parts within each CAT.

m. Project ACO. The ACO is responsible for a project, which results in approving data submitted by the fabricator to FAA for fabricating the part. The project ACO may be required to coordinate with the certificate management ACO, depending upon the criticality classification and complexity of the part to be fabricated.

n. Production. An act in which a part is manufactured under part 21 to an approved design, or to an established industry standard or specification recognized by the United States.

o. Subcontractor. A person providing parts, materials, or related services (welding, plating, machining, etc.) to the certificate holder responsible for fabrication of the part. The subcontractor must be subject to control and surveillance by that certificate holder who is ultimately responsible for the airworthiness of the part and its fabrication processes.

4. RELATED READING MATERIAL (current editions).

a. FAA Orders. You may obtain the current editions of these orders from the FAA Web site at http://www.faa.gov/.

(1) Order 8110.42, Parts Manufacturer Approval Procedures.

(2) Order 8120.2, Production Approval and Certificate Management Procedures.

(3) Order 8120.11, Disposition of Scrap or Salvageable Aircraft Parts and Material.

(4) Order 8130.2, Airworthiness Certification of Aircraft and Related Products.

(5) Order 8900.1, Flight Standards Information Management System (FSIMS).

b. Advisory Circulars. You may obtain the current editions of these ACs from the FAA Web site at http://www.airweb.faa.gov/rgl.

(1) AC 20-62, Eligibility, Quality, and Identification of Aeronautical Replacement Parts.

(2) AC 21-29, Detecting and Reporting Suspected Unapproved Parts.

(3) AC 43-9, Maintenance Records.

Page 4 Par 3 06/07/11 AC43-18CHG2 (4) AC 43.9-1, Instructions for Completion of FAA Form 337 (OMB NO. 2120-0020), Major Repair and Alteration (Airframe, Powerplant, Propeller, or Appliance).

(5) AC 43.13-1, Acceptable Methods, Techniques, and Practices-Aircraft Inspection and Repair.

(6) AC 43.13-2, 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 91-82, Fatigue Management Programs for Airplanes with Demonstrated Risk of Catastrophic Failure Due to Fatigue.

(9) AC 120-77, Maintenance and Alteration Data.

5. BACKGROUND.

a. Authority to Fabricate Parts. 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 part 21 to produce parts for installation on type-certificated products or whether it is permissible to use the maintenance rules outlined in 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. Difference in Rules. 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 part 43, for maintenance or repair purposes, as those produced under the production rules under part 2 1 .

c. Conformance to Approved Design. 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 Par 4 Page 5 AC43-18CHG2 06/07/11 (2) A FQCS (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.

a. Important Considerations. 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 the pertinent airworthiness requirements of the product are satisfied. Parts design data

I may be approved under § 21.8(d) and fabricated under § 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 I alteration) must obtain a PMA (refer to § 21.9(a)).

b. Limitations. Parts fabrication must be performed within the privileges and limitations of the certificate holder's FAA authorization and ratings and in accordance with his/her established quality control system.

c. Subcontractor Limitations. 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. Required Documentation. Procedures for addressing the criteria recommended in paragraph 6d(l)(a), 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, Determining Part Category.

(a) For CAT 1 and CAT 2 Parts: 7. 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 Page 6 Par 5 06/07/11 AC43-18CHG2 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.

6. IC A/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 43.13-2B, Service Bulletins (SB), component maintenance manual (CMM), service history, or prior service experience, etc., in accordance with § 43.13(b).

NOTE: All fabrication repairs of parts must be accomplished in accordance with methods, techniques, and practices acceptable to the Administrator in accordance with § 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 I and requirements necessary to fabricate the part are identified and adhered to. The depth and detail of the FQCS depends on the complexity and CAT classification of the part being fabricated. The following are recommended elements that could be addressed in the FQCS: (a) Design data control. Procedures for controlling design data and subsequent changes to ensure that only current, correct, and approved or acceptable data is used.

(b) A list of the parts fabricated by nomenclature and part number.

(c) Document control. Procedures for controlling quality system documents and data and subsequent changes to ensure that only current, correct, and approved or acceptable documents and data are used.

(d) Subcontractor control. Procedures that: 1. Ensure that each subcontractor-fiirnished part conforms to its approved design; and 2. Require each subcontractor to report to the fabricator if a part has been released from that subcontractor and subsequently found not to conform to the applicable design data.

(e) Inspecting and testing. Procedures for inspections and tests used to ensure that each part conforms to its approved design.

Par 6 Page 7 AC43-18CHG2 06/07/11 (f) Inspection, measuring, and test equipment control. Procedures to ensure calibration and control of all inspection, measuring, and test equipment used in determining conformity of each part to its approved or acceptable design. Each calibration standard must be traceable to a standard acceptable to the FAA.

(g) Inspection and test status. Procedures for documenting the inspection and test status of parts supplied to the approved design.

(h) Nonconforming part control.

1. Procedures to ensure that only parts that conform to their approved or acceptable design are installed on a type-certificated product. These procedures must provide for the identification, documentation, evaluation, segregation, and disposition of nonconforming articles. Only authorized individuals may make disposition determinations.

2. Procedures to ensure that discarded articles are rendered unusable.

(i) Corrective and preventive actions. Procedures for implementing corrective and preventive actions to eliminate the causes of an actual or potential nonconformity to the approved design or noncompliance with the FQCS.

(j) Handling and storage. Procedures to prevent damage and deterioration of each part.

(k) Control of quality records. Procedures for identifying, storing, protecting, retrieving, and retaining fabrication quality records associated with the part must be retained in accordance with regulatory requirements.

(1) Internal audits. Procedures for planning, conducting, and documenting internal audits to ensure compliance with the FQCS. The procedures must include reporting results of internal audits to the person responsible for implementing corrective and preventive actions.

(m) In-service feedback. Procedures for receiving and processing feedback on in-service failures, malfunctions, and defects. These procedures must include a process to— 1. Address any in-service problem involving design changes; and 2. Determine if any changes to the ICAs are necessary.

(n) Quality escapes. Procedures for identifying, analyzing, and initiating appropriate corrective action for products or articles that have been released from the quality system and that do not conform to the applicable design data or quality system 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: Page 8 Par 6 06/07/11 AC43-18CHG2 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 5. The original manufacturer's part number if removed as a result of the fabrication.

(b) Critical parts must be marked in accordance with part 45, § 45.15. 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 § 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).

(5) Determine whether the existing ICA for the original part is sufficient to ensure the fabricated part continues to meet all airworthiness requirements.

(6) 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.

(7) 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.

(8) 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.

(9) 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 (AIR) 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.

Par 6 ' Page 9 AC43-18CHG2 06/07/11 (10) 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 § 21.9(a).

(11) Recordkeeping. Fabrication of a part in accordance with this AC is subject to the maintenance recordkeeping provisions of § 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 AD, current inspection status, and current status of life-limited parts. These maintenance records should be retained with the aircraft records.

(12) 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 CAT.

a. Criticality Level—CPL.

(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), in combination with other factors, to determine a part's criticality level. The CPL classifies parts into one of three CATs depending on their effect on safety. The CPL should be used as a guide in determining a part's 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 Page 10 Par 6 06/07/11 AC43-18CHG2 the design data. The list of data to be submitted to the ACO can be found in paragraph 6d(l)(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(l)(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.

(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 AIR unless the AFS 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 FQCS for compliance with paragraph 6d(l)(b).

NOTE: A summary of the certificate holder requirements for data based on the CAT of the part can be found in Appendix 1.

Par 7 Page 11 06/07/11 AC43-18CHG2 Appendix 1 APPENDIX 1. SUMMARY OF REQUIREMENTS FOR CERTIFICATE HOLDERS SEEKING TO FABRICATE PARTS PURSUANT TO 14 CFR PART 21 AND PART 43 Fabrication FQCS Required ACO Design DER FSDO Part Category Manual Data Approval Approval Review of Procedures Authority FQCS 1 Yes Yes Yes (Recommend Yes Certificating Approval Only) ACO through the Geographical ACO 2 Yes Yes Yes Yes Yes Geographic ACO 3 Yes Yes Only Acceptable Not Required Yes Data is Required for this Category ACO Intervention Only on Request by AFS 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.

Page 1 (and 2) 2/29/08 AC 43-18 CHG1 Appendix 2 APPENDIX 2. CATEGORY PARTS LIST The infonnation 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 fiiture 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.

Fuselage Structural Sa£jag£(23-i),(25-i) 23,25 23.25 Hydraulic Main Pump 23, Software Thrust (EEC) 23.25 Electrical Power System 23, 21, Alternator/Generator Drfce 25, (23-1), (25-2), (27-1), (23-1). (25-1) 27,29 27,29 Pressure Bulkheads (23-1). (29-1) System <23-2),(25-2) Man Accumulator AC Generator-Alternator (2S-1) (23-2) (25-2) Keel Beam (25-1) (25-2) Longeron/Stringer (25-2) Main Reservoir (25-2) AC Inverter (23-2) (25-2) Floor Beam (25-2) Phase Adapter (25-2) Auxiliary Pump (25-2) plates/Skms(25-2) AC Regulator (25-2) Fuselage to Wing Attach Fire Protection Fittings (25-1) Smoke Detection (25-2).

StabBizer to Fuselage Attach (27-2). (29-2) Fittings (25-1) Fire Detection (25-2), (27-2).

Gear to Fuselage attach (29-2) Fittings (25-1) Overheat Detection (25-2), Door Hinge (on Fuselage) (27-2), (29-2) (25-1) Extinguishing System Fuselage Panels (23-1), (25-1) (25-2), (27-2). (29-2) Fire Bottle-Fixed (25-2), (27-2), (29-2) Flight Central Surfaces Flight Control Structural 23, Flight Control Servo 25, Thrust Reveraers (23-1), Fuel System 23,25 23,25 23,25 Ailerons (23-1), (25-1) Actuators (25-2), (25-2) Boost Pumps (23-1), (25-2), 25, 27,29 Rudder (23-1), (25-1) Aileron Tabs (25-2) (27-1), (29-1) Auxiliary Power Units (23-1) Transfer Valves (23-1). 27.21 TE Flaps (23-1), (25-2) Flap Actuator (25-2) (25-2) jackscrew (23-1), (25-1) FADEC(23-1) LE Devices (25-2) Rudder Actuator FuetSOV (23-1),(26-1) BeBcranks (23-1), (25-1) Elevator (23-1), (26-1) (25-2) Digital Fuel Flow System Flight Control Cables (23-1), Spoilers (26-2) (23-2) (26-2) Stabilizer Actuator (25-1) (25-2) Fuel Dump (26-2) Fuel Hose (Single engine applications ONLY) (23-2) (27-2), (29-2) Fuel Quantity indicator (23-2) (25-2), £27-2), (29-2) Fuel Flow Indicating (27-2), (29-2) (23-2) Fuel Pressure Indicating (27-2), (29-2) (23-2) Fuel Pump (25-2), (27-1).

(29-1) Engine Lubrication System Oil Cooler (Single engine applications ONLY) (23-2) (27-2). (29-2) Page 1 AC 43-18 CHG1 2/29/08 Appendix 2 CATEGORY PARTS LIST structural « C F R * Wniotwal CFR . HydrauJIo PhwrnaHo, CFR ^ Propulsion 8ystflnv-. \t. CFR !

ARswnbiiaa Btnteqie .' Components .'.-.-r- if!"*' " Compontns^' PWl Engine Liquid Cooling System Radiators, Coolant Pumps.

Water Hoses and Head Gasket (Single engine applications ONLY) (23-2) (27-2), (29-2) Crew Oxyoen System (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 23,25 Control Valves (23-2), Brake System and 23,25 23,25 23,25 23,25 Empennage 8trMfftnn»» Eng'"t cwlinq ftyfrm Horizontal Stabilizers (23-1), (25-2) Assembly Components Elements Horizontal lnleta(23-1),(25-2) Shut Off Valves Brakes(23-1), (25-1) (25-1) Stabilizer Nacelles (23-1), (25-2) Spars/Ribs (23-2) (25*2) (23-2), (25-2) Anti-Skid Valves (23-2), Elevators (23-1). (25-1) Fairings (23-1). (25-2) Plates/Skins (23-2) (25-2) Rudder Power Control (25-2) Vertical stabilizers (23-1), Tab Structure (23-2) (25-2) Units (23-1), (25-2) Wheel Assemblies (23-1) (25-1) Attach Fitting (23-2) (25-2) Rudder Power Control (25-2) Rudder (23-1), (25-1) Empennage Structural Unit (Boeing 737) Tire Casing (25-2) Elements Elevator (25-1) Tire Tube (25-2) Spars/Ribs (23-2) (25-2) Antiskid Section (25-2) Plates/Skins (23-2) (25-2) Master Cylinder/Brake Valve Tab Structure (23-2) (25-2) (25-1) Attach Fitting Elevator Tab (23-2) (25-2) Empennage Structural Elflmnnts Vortical Stabilizer Spars/Rfos (23-2) (25-2) Plaies/Skms (23-2) (25-2) Attach Fitting (23-2) (25-2) Ventral Structure (23-2) (25-2) EmpWn^gtrMgTuiaj Elements Hortzontal Stabilizer Spars/Ribs (23-2) (25-2) Plates/Skins (23-2) (25-2) Tab Structure (23-2) £25-2) Attach Fitting (23-2) (25-2) NOTAR (High Speed 27 29 Wlno Structure f23-1V (26-1) Wlno Structure Structural Airborne Software^ 23, 23,25 23,25 Elements 25.33 FanU27-1U29-1) CffnlrvtirtEflHlprrmit Page 2 2/29/08 AC 43-18 CHG1 Appendix 2 CATEGORY PARTS LIST Sgg||graJ sassi Stniotural CFR * HydrwUo PnoumallQj CFR . - Propulsion System.:. •....

WJI, .-CFR, ^ SysisMiil " i f i W > ftSh ASMnitWoK * " pat "•- ofminls*' 'part • |>artv, • ^ . ^ n - S a ^ ^ ^ n ^ S • gait— ''Component*;. ' * part*? " * ' - " G p n w m r t i ' t - v . ' ' i\ir* *,-"». 1 ) , ( 2 " ) '^ll'lW.llL ' < l l AlOlSf Automat lr, pliant Control M ' . v i r r t . - i i:-. r, Syrems'Stabllltv .". jfcVTi?(23»t.' <- ; Spars (23-1), (25-1) (25-1). (33-1) Auomentatlon Systems Ribs/Bulkheads (23-2) (25-2) Flight Control Computers Software Levels B, or C (per Longeron/Stringers (25-2) RTCA/D017aB)(23-2) (27-1), (29-2) Center Wing Box (25-1) (25-2). (33-2) Servo/Linear Actuators Auxiffiary Structure (25-2) (27-1), (29-1) Wing Attach Fitting (26-1) Electrical Power Systems NAC/pylon Wing Fitting AC Generator (27-2), (29-2) (23-1), (25-1) AC Inverters (27-2), (29-2) Blended Winglet (26-2) Battery (27-2). (29-2) Starter Generator (27-2).

(29-2) Main Rotor 27,29 Main Rotor Control 27,29 Prooellere 35 Drive Systems 27,29 Hubs (27-1), (29-1) (Hubs (35-1), Blades (3fr-1) Masts (27-1), (29-1) Swasnpfetes (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-Dnves (27-1), (29-1) Counter Weights (35-1) Dnveshafts(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 613068(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 Bote (27-1). Actuator Supports (27-1), (29-1) (29-1) Elastomers Dampers (27-1), Control System (29-1) Tube6/BoN6/Plns(27-1), Bearings (27-1). (29-1) (29-1) Bushings (27-1), (29-1) Fuel Tank Structure Drive Beits (27-1), (29-1) 27, 30 Stall Warning (23-2). (25-2) 23,25 Nose Section (23-1), (25-1) 23,25 23, Radomes (23-2), (25-2) Fuel Ceil (23-1), (25-1), (27-1), 25, (29-1) 27 29 Nacelles/Pylons f23-1V (25-11 23,25 Nacelles/Pylons Structural 23,25 Gas Turbine Enalnes- 33 Anti-Ice System (23-2) 25,27, Doors Elements 27 29 Enalne Rotors Pltot/Statlc Anti-Ice (23-2) Fan Blades (33-1), (25-2) Passenger Crew Doors (25-1) Attachment Fittings (25-1), Emergency Exit Door (25-2) (27-1),(29-1) Disks (33-1), Blisks (33-1), Air Foil Anti Ice/Delce Landing Gear Doors (25-2) Bulkhead/Firewalls Impellers (33-1), Spools (23-2) (25-2), (27-2), (29-2) Cargo Baqgage Door (25-2) (Nac/PvBn) (23-2) (25-2), (Drum Rotors) (33-1), Window/Windshield & Doors Page 3 AC 43-18 CHG1 2/29/08 Appendix 2 CATEGORY PARTS LIST Longerons/Stringers Thermal Shields for cooling (23-2) (25-2) (Nac/Pylon) (25-2) of main rotors (33-1), Antenna/Radome Anti Ice Cooling Plates (33-1), Plates/Skins (Nac/Pyion) (25-2) (25-2) Main Rotor Rotating Spacers Intake Anti-lce/Deice (27-2), and Seals (33-1). Main Line Attach Frtbngs (Nac/Pyion) (23-2) (29-2) Engine Shahs (I e , low and (23-2) (25-1), (27-1), (29-1) high pressure rotor shafts, Engine Struts (23-1). (25-1), propeller shafts for turboprop (27-1), (29-1) applications and power Engine Mounts (23-1), (25-1), transmission shafts for Input (27-1), (29-1) to propeller and transmission Pylon Lilt/Link Assemblies gearPoxes) (33-1), Main Line (27-1), (29-1) Engine Bearings (33-2).

Rotating Compressor & Turbine Airfoils (33-2).

Spinners (33-2) Gas Turbine Engines fContl Main Engine Mounts (I e , redundant designa)(33-1), High Pressure Vessels (i a Casting subject to compressor dlscharge pressure & cornbuster PressureK33-1).

Containment Structures (33-1), Pnmary 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 Ccnlrols/Fufl 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) Flight Control Mechanisms LifOCompression Struts (23-1) Reciprocating Engines Airborne Software 21, 21 .13 21,25 (23-1). (25-1) Flying Wires £23-1) Crankshafts (33-1) System^ Software Level A 25, Floats (23-1), Skis (23-1) Connecting Rods Assembly (perRTCA/D0178B), 27,29 Tail Wheels (23-1) (23-1)(25-1), (27-1). (29-1) (33-1) Software Levels B, or C (per Connecting Rod Bearings RTCA/D0178B)(23-2) (33-1) (25-2), (27-2), (29-2) Pistons (33-1) Navigation System Wrist Pins (33-1) Wind Shear Detection Cylinders (33-1) Page 4 2/29/08 AC 43-18 CHGl Appendix 2 CATEGORY PARTS LIST Cylinder Heads (33-1) System (25-2) Engine Mounts (33-1) Ground Proximity System Crankcase (33-2) (23-2) (25-2) Crankshaft Bearings (33-2) Air Collision Avoidance Valve Train (valves, valve (TCAS) (23-2) (25-2) springs, pushrods, Air Speed Indicator (23-2) camshafts, rocker shaft (27-2), (29-2) assembly) (33-2) Altimeter (23-2) (27-2), Fuel Delivery Systems (29-2) (carburetors, Injectors, fuel Air Data Computer (23-2) pumps) (33-2), Valve (27-2), (29-2) Train/Accessory Drive Gears Attitude Gyro and Indication (33-2) (23-2) (27-2), (29-2) Electronic Engine Control Directional Gyro and (EEC)/Fuii Authority Digital indication (23-2) (27-2), Electronic Controls (33-2) (29-2) Pilot/Static System (23-2) (27-2), (29-2) LoealUerA/QK system (23-2) (27-2), (29-2) Glide Slops System (23-2) (27-2). (29-2) Balloon Fuel Systems .11 Tall Rotor and Controls Balloons .11 Balloon Burner Systems 31 27,29 Baskets (31-1) Burner Units (31-1) Fuel Manifolds (31-1) Hubs (27-1). (29-1) Yokes (27-1), (29-1) Envelopes (31-1) Trunnions (27-1). (29-1) Blades (27-1), (29-1) Blade spars (27-1), (29-1) Grips(27-1).(29-1) Pitch Change Links (27-1), (29-1) PrtchChange Bearings (27-1), (29-1) Output/Drive Shafts (27-1), (29-1)Gearsets (27-1), (29-1) strap Packs (27-1), (29-1) Pedal Linkages (27-1), (29-1) Bellcranks(27-1). Flapping & Lead/Lag Bearings (27-1), (29-1) 23,25 Main Landing Gear 23, Main Landing. Gear 23, 33 Fuselage (27-1), (29-1) 27,29 yy]nd,oY/WlndfihHd < t o T " f M r * E T O l T r f » ? W c System 27,29 Struts (23-1). (25-1), (27-1), 25, 25, Structures Tail Boom (27-1). (29-1) (29-1) Flight Compartment 27 29 Landing Gear Actuator 27,29 Engine Mounts (t e non- Tail Boom Struts (27-1), (29-1) Crosslubes (23-1), (25-1). Windows (23-1), (23-2) redundant designs) (33-1) Tall Boom Mount Fittings (23-1), (25-2), (27-1), (27-1). (29-1) (25-1) (29-1) High Pressure Vessels (27-1), (29-1) Drag Links (23-1). (25-2), Passenger Compartment Selector Valve (25-2) (Casings Subject to Vertical Stabilizers (27-1), (27-11,(29-1) Page 5 AC 43-18 CHGl 2/29/08 Appendix 2 CATEGORY PARTS LIST atructw Assambi (29-1) Fuse Pins (26-2) Landing Gear Door Compressor Discharge Windows (25-2) Attach Section (25-1) Horizontal Stabilizers (27-1) Actuator (25-2) Pressure & Combuster Door Windows ( - ' . ) ' • Extension and Retract System VHF Communication (29-1) Nose Landing Gear Pressure) (33-1) (25-2) Containment Structures (33-1) SjaleoL (27-2). (29-2) Elevator (27-1), (29-1) Components Landing Gear Door Retract Primary structures (that Elevator Horn (27-1), (29-1) Shimmy Damper Seclion (25-2) provide support and rigidity of Skin Assemblies (27-1), (29-1) (25-2) Landing Gear Position and the main engine backbone Bonded Panel Assemblies Steenng Unit (25-2) Warning (27-2) (29-2) and for attachment of engine (27-1),(29-1) Hose Landing Gear to airframe (33-1) Spars (27-1) (29-1) (23-1), (25-1) Strut/Axle (25-1) Attach Section (25-1) Stewing Links (23-1) (25-2) (27-1) (29-1) Page 6