Section 1
Federal Aviation Administration, DOT § 43.10 appendix B, by the person performing § 43.9 Content, form, and disposition of maintenance, preventive mainte- the work.
nance, rebuilding, and alteration [Amdt. 43–23, 47 FR 41085, Sept. 16, 1982, as records (except inspections per- amended by Amdt. 43–37, 66 FR 21066, Apr. 27, formed in accordance with part 91, 2001; Amdt. 43–39, 69 FR 44863, July 27, 2004] part 125, § 135.411(a)(1), and § 135.419 of this chapter).
§ 43.10 Disposition of life-limited air- (a) Maintenance record entries. Except craft parts.
as provided in paragraphs (b) and (c) of (a) Definitions used in this section. For this section, each person who main- the purposes of this section the fol- tains, performs preventive mainte- lowing definitions apply.
nance, rebuilds, or alters an aircraft, Life-limited part means any part for airframe, aircraft engine, propeller, ap- which a mandatory replacement limit pliance, or component part shall make is specified in the type design, the In- an entry in the maintenance record of structions for Continued Airworthi- that equipment containing the fol- ness, or the maintenance manual.
lowing information: Life status means the accumulated (1) A description (or reference to data cycles, hours, or any other mandatory acceptable to the Administrator) of replacement limit of a life-limited work performed.
part.
(2) The date of completion of the (b) Temporary removal of parts from work performed.
type-certificated products. When a life- (3) The name of the person per- limited part is temporarily removed forming the work if other than the per- and reinstalled for the purpose of per- son specified in paragraph (a)(4) of this forming maintenance, no disposition section.
under paragraph (c) of this section is (4) If the work performed on the air- required if— craft, airframe, aircraft engine, pro- (1) The life status of the part has not peller, appliance, or component part changed; has been performed satisfactorily, the (2) The removal and reinstallation is signature, certificate number, and kind performed on the same serial numbered of certificate held by the person ap- product; and proving the work. The signature con- (3) That product does not accumulate stitutes the approval for return to time in service while the part is re- service only for the work performed.
moved.
(b) Each holder of an air carrier oper- (c) Disposition of parts removed from ating certificate or an operating cer- type-certificated products. Except as pro- tificate issued under Part 121 or 135, vided in paragraph (b) of this section, that is required by its approved oper- after April 15, 2002 each person who re- ations specifications to provide for a moves a life-limited part from a type- continuous airworthiness maintenance certificated product must ensure that program, shall make a record of the the part is controlled using one of the maintenance, preventive maintenance, methods in this paragraph. The method rebuilding, and alteration, on aircraft, must deter the installation of the part airframes, aircraft engines, propellers, after it has reached its life limit. Ac- appliances, or component parts which ceptable methods include: it operates in accordance with the ap- (1) Record keeping system. The part plicable provisions of Part 121 or 135 of may be controlled using a record keep- this chapter, as appropriate.
ing system that substantiates the part (c) This section does not apply to per- number, serial number, and current life sons performing inspections in accord- status of the part. Each time the part ance with Part 91, 125, § 135.411(a)(1), or is removed from a type certificated § 135.419 of this chapter.
product, the record must be updated (d) In addition to the entry required with the current life status. This sys- by paragraph (a) of this section, major tem may include electronic, paper, or repairs and major alterations shall be other means of record keeping.
entered on a form, and the form dis- (2) Tag or record attached to part. A posed of, in the manner prescribed in tag or other record may be attached to 14 CFR Ch. I (1–1–25 Edition) § 43.11 the part. The tag or record must in- mutilated before it is sold or trans- clude the part number, serial number, ferred.
and current life status of the part.
[Doc. No. FAA–2000–8017, 67 FR 2110, Jan. 15, Each time the part is removed from a 2002, as amended by Amdt. 43–38A, 79 FR type certificated product, either a new 67055, Nov. 12, 2014] tag or record must be created, or the § 43.11 Content, form, and disposition existing tag or record must be updated of records for inspections con- with the current life status.
ducted under parts 91 and 125 and (3) Non-permanent marking. The part §§ 135.411(a)(1) and 135.419 of this may be legibly marked using a non- chapter.
permanent method showing its current (a) Maintenance record entries. The life status. The life status must be up- person approving or disapproving for dated each time the part is removed return to service an aircraft, airframe, from a type certificated product, or if aircraft engine, propeller, appliance, or the mark is removed, another method component part after any inspection in this section may be used. The mark performed in accordance with part 91, must be accomplished in accordance 125, § 135.411(a)(1), or § 135.419 shall with the instructions under § 45.16 of make an entry in the maintenance this chapter in order to maintain the record of that equipment containing integrity of the part.
the following information: (4) Permanent marking. The part may (1) The type of inspection and a brief be legibly marked using a permanent description of the extent of the inspec- method showing its current life status.
tion.
The life status must be updated each (2) The date of the inspection and air- time the part is removed from a type craft total time in service.
certificated product. Unless the part is (3) The signature, the certificate permanently removed from use on type number, and kind of certificate held by certificated products, this permanent the person approving or disapproving mark must be accomplished in accord- for return to service the aircraft, air- ance with the instructions under § 45.16 frame, aircraft engine, propeller, appli- of this chapter in order to maintain the ance, component part, or portions integrity of the part.
thereof.
(5) Segregation. The part may be seg- (4) Except for progressive inspec- regated using methods that deter its tions, if the aircraft is found to be air- installation on a type-certificated worthy and approved for return to product. These methods must include, service, the following or a similarly at least— worded statement—‘‘I certify that this (i) Maintaining a record of the part aircraft has been inspected in accord- number, serial number, and current life ance with (insert type) inspection and status, and was determined to be in airworthy con- (ii) Ensuring the part is physically dition.’’ stored separately from parts that are (5) Except for progressive inspec- currently eligible for installation.
tions, if the aircraft is not approved for (6) Mutilation. The part may be muti- return to service because of needed lated to deter its installation in a type maintenance, noncompliance with ap- certificated product. The mutilation plicable specifications, airworthiness must render the part beyond repair and directives, or other approved data, the incapable of being reworked to appear following or a similarly worded state- to be airworthy.
ment—‘‘I certify that this aircraft has (7) Other methods. Any other method been inspected in accordance with (in- approved or accepted by the FAA.
sert type) inspection and a list of dis- (d) Transfer of life-limited parts. Each crepancies and unairworthy items person who removes a life-limited part dated (date) has been provided for the from a type certificated product and aircraft owner or operator.’’ later sells or otherwise transfers that (6) For progressive inspections, the part must transfer with the part the following or a similarly worded state- mark, tag, or other record used to com- ment—‘‘I certify that in accordance ply with this section, unless the part is with a progressive inspection program, Federal Aviation Administration, DOT § 43.13 a routine inspection of (identify wheth- (2) Any reproduction, for fraudulent er aircraft or components) and a de- purpose, of any record or report under this part; or tailed inspection of (identify compo- (3) Any alteration, for fraudulent nents) were performed and the (aircraft purpose, of any record or report under or components) are (approved or dis- this part.
approved) for return to service.’’ If dis- (b) The commission by any person of approved, the entry will further state an act prohibited under paragraph (a) ‘‘and a list of discrepancies and unair- of this section is a basis for suspending worthy items dated (date) has been or revoking the applicable airman, op- provided to the aircraft owner or oper- erator, or production certificate, Tech- ator.’’ nical Standard Order Authorization, (7) If an inspection is conducted FAA-Parts Manufacturer Approval, or under an inspection program provided Product and Process Specification for in part 91, 125, or § 135.411(a)(1), the issued by the Administrator and held entry must identify the inspection pro- by that person.
gram, that part of the inspection pro- [Amdt. 43–19, 43 FR 22639, May 25, 1978, as gram accomplished, and contain a amended by Amdt. 43–23, 47 FR 41085, Sept.
statement that the inspection was per- 16, 1982] formed in accordance with the inspec- tions and procedures for that par- § 43.13 Performance rules (general).
ticular program.
(a) Each person performing mainte- (b) Listing of discrepancies and plac- nance, alteration, or preventive main- ards. If the person performing any in- tenance on an aircraft, engine, pro- spection required by part 91 or 125 or peller, or appliance shall use the meth- § 135.411(a)(1) of this chapter finds that ods, techniques, and practices pre- the aircraft is unairworthy or does not scribed in the current manufacturer’s meet the applicable type certificate maintenance manual or Instructions data, airworthiness directives, or other for Continued Airworthiness prepared approved data upon which its air- by its manufacturer, or other methods, worthiness depends, that persons must techniques, and practices acceptable to the Administrator, except as noted in give the owner or lessee a signed and § 43.16. He shall use the tools, equip- dated list of those discrepancies. For ment, and test apparatus necessary to those items permitted to be inoper- assure completion of the work in ac- ative under § 91.213(d)(2) of this chapter, cordance with accepted industry prac- that person shall place a placard, that tices. If special equipment or test appa- meets the aircraft’s airworthiness cer- ratus is recommended by the manufac- tification regulations, on each inoper- turer involved, he must use that equip- ative instrument and the cockpit con- ment or apparatus or its equivalent ac- trol of each item of inoperative equip- ceptable to the Administrator.
ment, marking it ‘‘Inoperative,’’ and (b) Each person maintaining or alter- shall add the items to the signed and ing, or performing preventive mainte- dated list of discrepancies given to the nance, shall do that work in such a owner or lessee.
manner and use materials of such a [Amdt. 43–23, 47 FR 41085, Sept. 16, 1982, as quality, that the condition of the air- amended by Amdt. 43–30, 53 FR 50195, Dec. 13, craft, airframe, aircraft engine, pro- 1988; Amdt. 43–36, 61 FR 19501, May 1, 1996; 71 peller, or appliance worked on will be FR 44188, Aug. 4, 2006] at least equal to its original or prop- erly altered condition (with regard to § 43.12 Maintenance records: Falsifica- aerodynamic function, structural tion, reproduction, or alteration.
strength, resistance to vibration and (a) No person may make or cause to deterioration, and other qualities af- be made: fecting airworthiness).
(1) Any fraudulent or intentionally (c) Special provisions for holders of air false entry in any record or report that carrier operating certificates and oper- is required to be made, kept, or used to ating certificates issued under the provi- show compliance with any requirement sions of Part 121 or 135 and Part 129 oper- under this part; ators holding operations specifications.
14 CFR Ch. I (1–1–25 Edition) § 43.15 Unless otherwise notified by the ad- source. This checklist must include the ministrator, the methods, techniques, scope and detail of the items contained and practices contained in the mainte- in appendix D to this part and para- nance manual or the maintenance part graph (b) of this section.
of the manual of the holder of an air (2) Each person approving a recipro- carrier operating certificate or an op- cating-engine-powered aircraft for re- erating certificate under Part 121 or 135 turn to service after an annual or 100- and Part 129 operators holding oper- hour inspection shall, before that ap- ations specifications (that is required proval, run the aircraft engine or en- by its operating specifications to pro- gines to determine satisfactory per- vide a continuous airworthiness main- formance in accordance with the manu- tenance and inspection program) con- facturer’s recommendations of— stitute acceptable means of compliance (i) Power output (static and idle with this section. r.p.m.); (ii) Magnetos; [Doc. No. 1993, 29 FR 5451, Apr. 23, 1964, as (iii) Fuel and oil pressure; and amended by Amdt. 43–20, 45 FR 60182, Sept.
(iv) Cylinder and oil temperature.
11, 1980; Amdt. 43–23, 47 FR 41085, Sept. 16, (3) Each person approving a turbine- 1982; Amdt. 43–28, 52 FR 20028, June 16, 1987; Amdt. 43–37, 66 FR 21066, Apr. 27, 2001] engine-powered aircraft for return to service after an annual, 100-hour, or § 43.15 Additional performance rules progressive inspection shall, before for inspections.
that approval, run the aircraft engine (a) General. Each person performing or engines to determine satisfactory an inspection required by part 91, 125, performance in accordance with the or 135 of this chapter, shall— manufacturer’s recommendations.
(1) Perform the inspection so as to (d) Progressive inspection. (1) Each per- determine whether the aircraft, or por- son performing a progressive inspec- tion(s) thereof under inspection, meets tion shall, at the start of a progressive all applicable airworthiness require- inspection system, inspect the aircraft ments; and completely. After this initial inspec- (2) If the inspection is one provided tion, routine and detailed inspections for in part 125, 135, or § 91.409(e) of this must be conducted as prescribed in the chapter, perform the inspection in ac- progressive inspection schedule. Rou- cordance with the instructions and pro- tine inspections consist of visual exam- cedures set forth in the inspection pro- ination or check of the appliances, the gram for the aircraft being inspected. aircraft, and its components and sys- (b) Rotorcraft. Each person per- tems, insofar as practicable without forming an inspection required by Part disassembly. Detailed inspections con- 91 on a rotorcraft shall inspect the fol- sist of a thorough examination of the lowing systems in accordance with the appliances, the aircraft, and its compo- maintenance manual or Instructions nents and systems, with such dis- for Continued Airworthiness of the assembly as is necessary. For the pur- manufacturer concerned: poses of this subparagraph, the over- (1) The drive shafts or similar sys- haul of a component or system is con- tems. sidered to be a detailed inspection.
(2) The main rotor transmission gear (2) If the aircraft is away from the box for obvious defects. station where inspections are normally (3) The main rotor and center section conducted, an appropriately rated me- (or the equivalent area). chanic, a certificated repair station, or (4) The auxiliary rotor on heli- the manufacturer of the aircraft may copters. perform inspections in accordance with (c) Annual and 100-hour inspections. (1) the procedures and using the forms of Each person performing an annual or the person who would otherwise per- 100-hour inspection shall use a check- form the inspection.
list while performing the inspection.
[Doc. No. 1993, 29 FR 5451, Apr. 23, 1964, as The checklist may be of the person’s amended by Amdt. 43–23, 47 FR 41086, Sept.
own design, one provided by the manu- 16, 1982; Amdt. 43–25, 51 FR 40702, Nov. 7, 1986; facturer of the equipment being in- Amdt. 43–31, 54 FR 34330, Aug. 18, 1989; 71 FR spected or one obtained from another 44188, Aug. 4, 2006]
Section 2
Federal Aviation Administration, DOT § 43.17
requirements of paragraph (d) of this § 43.16 Airworthiness limitations.
section and approve the affected prod- Each person performing an inspec- ucts for return to service in accordance tion or other maintenance specified in with the requirements of paragraph (e) an Airworthiness Limitations section of this section.
of a manufacturer’s maintenance man- (d) Performance requirements. A person ual or Instructions for Continued Air- authorized in paragraph (c) of this sec- worthiness shall perform the inspec- tion may perform maintenance (includ- tion or other maintenance in accord- ing any inspection required by Sec.
ance with that section, or in accord- 91.409 of this chapter, except an annual ance with operations specifications ap- inspection), preventive maintenance, proved by the Administrator under and alterations, provided— part 121 or 135, or an inspection pro- gram approved under § 91.409(e). (1) The person performing the work is authorized by Transport Canada Civil [71 FR 44188, Aug. 4, 2006] Aviation to perform the same type of work with respect to Canadian aero- § 43.17 Maintenance, preventive main- tenance, and alterations performed nautical products; on U.S. aeronautical products by (2) The maintenance, preventive certain Canadian persons.
maintenance, or alteration is per- (a) Definitions. For purposes of this formed in accordance with a Bilateral section: Aviation Safety Agreement between Aeronautical product means any civil the United States and Canada and asso- aircraft or airframe, aircraft engine, ciated Maintenance Implementation propeller, appliance, component, or Procedures that provide a level of safe- part to be installed thereon.
ty equivalent to that provided by the Canadian aeronautical product means provisions of this chapter; any aeronautical product under air- (3) The maintenance, preventive worthiness regulation by Transport maintenance, or alteration is per- Canada Civil Aviation.
formed such that the affected product U.S. aeronautical product means any complies with the applicable require- aeronautical product under airworthi- ments of part 36 of this chapter; and ness regulation by the FAA.
(4) The maintenance, preventive (b) Applicability. This section does not maintenance, or alteration is recorded apply to any U.S. aeronautical prod- in accordance with a Bilateral Aviation ucts maintained or altered under any Safety Agreement between the United bilateral agreement made between States and Canada and associated Canada and any country other than the Maintenance Implementation Proce- United States.
dures that provide a level of safety (c) Authorized persons. (1) A person equivalent to that provided by the pro- holding a valid Transport Canada Civil visions of this chapter.
Aviation Maintenance Engineer license (e) Approval requirements. (1) To re- and appropriate ratings may, with re- turn an affected product to service, a spect to a U.S.-registered aircraft lo- person authorized in paragraph (c) of cated in Canada, perform maintenance, this section must approve (certify) preventive maintenance, and alter- maintenance, preventive maintenance, ations in accordance with the require- and alterations performed under this ments of paragraph (d) of this section section, except that an Aircraft Main- and approve the affected aircraft for tenance Engineer may not approve a return to service in accordance with major repair or major alteration.
the requirements of paragraph (e) of this section. (2) An AMO whose system of quality (2) A Transport Canada Civil Avia- control for the maintenance, preven- tion Approved Maintenance Organiza- tive maintenance, alteration, and in- tion (AMO) holding appropriate ratings spection of aeronautical products has may, with respect to a U.S.-registered been approved by Transport Canada aircraft or other U.S. aeronautical Civil Aviation, or an authorized em- products located in Canada, perform ployee performing work for such an maintenance, preventive maintenance, AMO, may approve (certify) a major re- and alterations in accordance with the pair or major alteration performed
14 CFR Ch. I (1–1–25 Edition) Pt. 43, App. A
(iii) Installation of an accessory which is under this section if the work was per- not approved for the engine.
formed in accordance with technical (iv) Removal of accessories that are listed data approved by the FAA.
as required equipment on the aircraft or en- (f) No person may operate in air com- gine specification.
merce an aircraft, airframe, aircraft (v) Installation of structural parts other engine, propeller, or appliance on than the type of parts approved for the in- which maintenance, preventive main- stallation.
tenance, or alteration has been per- (vi) Conversions of any sort for the purpose of using fuel of a rating or grade other than formed under this section unless it has that listed in the engine specifications.
been approved for return to service by (3) Propeller major alterations. The following a person authorized in this section.
alterations of a propeller when not author- [Amdt. 43–33, 56 FR 57571, Nov. 12, 1991, as ized in the propeller specifications issued by amended by Amdt. 43–40, 71 FR 40877, July 14, the FAA are propeller major alterations: 2005] (i) Changes in blade design.
(ii) Changes in hub design.
A PPENDIX A TO P ART 43—M AJOR A LTER - (iii) Changes in the governor or control de- ATIONS, M AJOR R EPAIRS , AND P RE - sign.
(iv) Installation of a propeller governor or VENTIVE M AINTENANCE feathering system.
(a) Major alterations —(1) Airframe major al- (v) Installation of propeller de-icing sys- terations. Alterations of the following parts tem.
and alterations of the following types, when (vi) Installation of parts not approved for not listed in the aircraft specifications the propeller.
issued by the FAA, are airframe major alter- (4) Appliance major alterations. Alterations ations: of the basic design not made in accordance (i) Wings. with recommendations of the appliance man- (ii) Tail surfaces. ufacturer or in accordance with an FAA Air- (iii) Fuselage. worthiness Directive are appliance major al- (iv) Engine mounts.
terations. In addition, changes in the basic (v) Control system.
design of radio communication and naviga- (vi) Landing gear.
tion equipment approved under type certifi- (vii) Hull or floats.
cation or a Technical Standard Order that (viii) Elements of an airframe including have an effect on frequency stability, noise spars, ribs, fittings, shock absorbers, brac- level, sensitivity, selectivity, distortion, ing, cowling, fairings, and balance weights.
spurious radiation, AVC characteristics, or (ix) Hydraulic and electrical actuating sys- ability to meet environmental test condi- tem of components.
tions and other changes that have an effect (x) Rotor blades.
on the performance of the equipment are (xi) Changes to the empty weight or empty also major alterations.
balance which result in an increase in the (b) Major repairs —(1) Airframe major repairs.
maximum certificated weight or center of Repairs to the following parts of an airframe gravity limits of the aircraft.
and repairs of the following types, involving (xii) Changes to the basic design of the the strengthening, reinforcing, splicing, and fuel, oil, cooling, heating, cabin pressuriza- manufacturing of primary structural mem- tion, electrical, hydraulic, de-icing, or ex- bers or their replacement, when replacement haust systems.
is by fabrication such as riveting or welding, (xiii) Changes to the wing or to fixed or are airframe major repairs.
movable control surfaces which affect flutter (i) Box beams.
and vibration characteristics.
(ii) Monocoque or semimonocoque wings or (2) Powerplant major alterations. The fol- control surfaces.
lowing alterations of a powerplant when not (iii) Wing stringers or chord members.
listed in the engine specifications issued by (iv) Spars.
the FAA, are powerplant major alterations.
(v) Spar flanges.
(i) Conversion of an aircraft engine from (vi) Members of truss-type beams.
one approved model to another, involving (vii) Thin sheet webs of beams.
any changes in compression ratio, propeller (viii) Keel and chine members of boat hulls reduction gear, impeller gear ratios or the or floats.
substitution of major engine parts which re- (ix) Corrugated sheet compression mem- quires extensive rework and testing of the bers which act as flange material of wings or engine.
tail surfaces.
(ii) Changes to the engine by replacing air- (x) Wing main ribs and compression mem- craft engine structural parts with parts not bers.
supplied by the original manufacturer or (xi) Wing or tail surface brace struts.
parts not specifically approved by the Ad- (xii) Engine mounts.
ministrator. (xiii) Fuselage longerons.
Federal Aviation Administration, DOT Pt. 43, App. A
(xiv) Members of the side truss, horizontal (xiii) Repairs to deep dents, cuts, scars, truss, or bulkheads. nicks, etc., and straightening of aluminum (xv) Main seat support braces and brack- blades.
ets. (xiv) The repair or replacement of internal elements of blades.
(xvi) Landing gear brace struts.
(4) Appliance major repairs. Repairs of the (xvii) Axles.
following types to appliances are appliance (xviii) Wheels.
major repairs: (xix) Skis, and ski pedestals.
(i) Calibration and repair of instruments.
(xx) Parts of the control system such as (ii) Calibration of radio equipment.
control columns, pedals, shafts, brackets, or (iii) Rewinding the field coil of an elec- horns.
trical accessory.
(xxi) Repairs involving the substitution of (iv) Complete disassembly of complex hy- material.
draulic power valves.
(xxii) The repair of damaged areas in metal (v) Overhaul of pressure type carburetors, or plywood stressed covering exceeding six and pressure type fuel, oil and hydraulic inches in any direction.
pumps.
(xxiii) The repair of portions of skin sheets (c) Preventive maintenance. Preventive by making additional seams.
maintenance is limited to the following (xxiv) The splicing of skin sheets.
work, provided it does not involve complex (xxv) The repair of three or more adjacent assembly operations: wing or control surface ribs or the leading (1) Removal, installation, and repair of edge of wings and control surfaces, between landing gear tires.
such adjacent ribs.
(2) Replacing elastic shock absorber cords (xxvi) Repair of fabric covering involving on landing gear.
an area greater than that required to repair (3) Servicing landing gear shock struts by two adjacent ribs. adding oil, air, or both.
(xxvii) Replacement of fabric on fabric cov- (4) Servicing landing gear wheel bearings, ered parts such as wings, fuselages, stabi- such as cleaning and greasing.
(5) Replacing defective safety wiring or lizers, and control surfaces.
cotter keys.
(xxviii) Repairing, including rebottoming, (6) Lubrication not requiring disassembly of removable or integral fuel tanks and oil other than removal of nonstructural items tanks.
such as cover plates, cowlings, and fairings.
(2) Powerplant major repairs. Repairs of the (7) Making simple fabric patches not re- following parts of an engine and repairs of quiring rib stitching or the removal of struc- the following types, are powerplant major re- tural parts or control surfaces. In the case of pairs: balloons, the making of small fabric repairs (i) Separation or disassembly of a crank- to envelopes (as defined in, and in accord- case or crankshaft of a reciprocating engine ance with, the balloon manufacturers’ in- equipped with an integral supercharger.
structions) not requiring load tape repair or (ii) Separation or disassembly of a crank- replacement.
case or crankshaft of a reciprocating engine (8) Replenishing hydraulic fluid in the hy- equipped with other than spur-type propeller draulic reservoir.
reduction gearing.
(9) Refinishing decorative coating of fuse- (iii) Special repairs to structural engine lage, balloon baskets, wings tail group sur- parts by welding, plating, metalizing, or faces (excluding balanced control surfaces), other methods.
fairings, cowlings, landing gear, cabin, or (3) Propeller major repairs. Repairs of the cockpit interior when removal or dis- following types to a propeller are propeller assembly of any primary structure or oper- major repairs: ating system is not required.
(i) Any repairs to, or straightening of steel (10) Applying preservative or protective blades.
material to components where no dis- (ii) Repairing or machining of steel hubs.
assembly of any primary structure or oper- (iii) Shortening of blades.
ating system is involved and where such (iv) Retipping of wood propellers.
coating is not prohibited or is not contrary (v) Replacement of outer laminations on to good practices.
fixed pitch wood propellers.
(11) Repairing upholstery and decorative (vi) Repairing elongated bolt holes in the furnishings of the cabin, cockpit, or balloon hub of fixed pitch wood propellers.
basket interior when the repairing does not (vii) Inlay work on wood blades.
require disassembly of any primary struc- (viii) Repairs to composition blades.
ture or operating system or interfere with an (ix) Replacement of tip fabric.
operating system or affect the primary (x) Replacement of plastic covering.
structure of the aircraft.
(xi) Repair of propeller governors. (12) Making small simple repairs to fair- (xii) Overhaul of controllable pitch propel- ings, nonstructural cover plates, cowlings, lers. and small patches and reinforcements not
14 CFR Ch. I (1–1–25 Edition) Pt. 43, App. B
changing the contour so as to interfere with that primary category aircraft that has a proper air flow. special training program approved under (13) Replacing side windows where that § 21.24 of this subchapter; or (2) issued by an- work does not interfere with the structure or other entity that has a course approved by any operating system such as controls, elec- the Administrator; and trical equipment, etc.
(ii) The inspections and maintenance tasks (14) Replacing safety belts.
are performed in accordance with instruc- (15) Replacing seats or seat parts with re- tions contained by the special inspection and placement parts approved for the aircraft, preventive maintenance program approved not involving disassembly of any primary as part of the aircraft’s type design or sup- structure or operating system.
plemental type design.
(16) Trouble shooting and repairing broken (31) Removing and replacing self-con- circuits in landing light wiring circuits.
tained, front instrument panel-mounted (17) Replacing bulbs, reflectors, and lenses navigation and communication devices that of position and landing lights.
employ tray-mounted connectors that con- (18) Replacing wheels and skis where no nect the unit when the unit is installed into weight and balance computation is involved.
the instrument panel, (excluding automatic (19) Replacing any cowling not requiring flight control systems, transponders, and removal of the propeller or disconnection of microwave frequency distance measuring flight controls.
equipment (DME)). The approved unit must (20) Replacing or cleaning spark plugs and be designed to be readily and repeatedly re- setting of spark plug gap clearance.
moved and replaced, and pertinent instruc- (21) Replacing any hose connection except tions must be provided. Prior to the unit’s hydraulic connections.
intended use, and operational check must be (22) Replacing prefabricated fuel lines.
performed in accordance with the applicable (23) Cleaning or replacing fuel and oil sections of part 91 of this chapter.
strainers or filter elements.
(24) Replacing and servicing batteries.
(Secs. 313, 601 through 610, and 1102, Federal (25) Cleaning of balloon burner pilot and Aviation Act of 1958 as amended (49 U.S.C.
main nozzles in accordance with the balloon 1354, 1421 through 1430 and 1502); (49 U.S.C.
manufacturer’s instructions.
106(g) (Revised Pub. L. 97–449, Jan. 21, 1983); (26) Replacement or adjustment of non- and 14 CFR 11.45) structural standard fasteners incidental to [Doc. No. 1993, 29 FR 5451, Apr. 23, 1964, as operations.
amended by Amdt. 43–14, 37 FR 14291, June (27) The interchange of balloon baskets and 19, 1972; Amdt. 43–23, 47 FR 41086, Sept. 16, burners on envelopes when the basket or 1982; Amdt. 43–24, 49 FR 44602, Nov. 7, 1984; burner is designated as interchangeable in Amdt. 43–25, 51 FR 40703, Nov. 7, 1986; Amdt.
the balloon type certificate data and the bas- 43–27, 52 FR 17277, May 6, 1987; Amdt. 43–34, 57 kets and burners are specifically designed for FR 41369, Sept. 9, 1992; Amdt. 43–36, 61 FR quick removal and installation.
19501, May 1, 1996; Amdt. 43–45, 77 FR 71096, (28) The installations of anti-misfueling de- Nov. 29, 2012; Docket No. FAA–2021–0237, vices to reduce the diameter of fuel tank Amdt. No. 43–52, 87 FR 31414, May 24, 2022] filler openings provided the specific device has been made a part of the aircraft type A PPENDIX B TO P ART 43—R ECORDING OF certificiate data by the aircraft manufac- M AJOR R EPAIRS AND M AJOR A LTER- turer, the aircraft manufacturer has pro- ATIONS vided FAA-approved instructions for instal- lation of the specific device, and installation (a) Except as provided in paragraphs (b), does not involve the disassembly of the ex- (c), and (d) of this appendix, each person per- isting tank filler opening.
forming a major repair or major alteration (29) Removing, checking, and replacing shall— magnetic chip detectors.
(1) Execute FAA Form 337 at least in dupli- (30) The inspection and maintenance tasks cate; prescribed and specifically identified as pre- (2) Give a signed copy of that form to the ventive maintenance in a primary category aircraft owner; and aircraft type certificate or supplemental type certificate holder’s approved special in- (3) Forward a copy of that form to the FAA spection and preventive maintenance pro- Aircraft Registration Branch in Oklahoma gram when accomplished on a primary cat- City, Oklahoma, within 48 hours after the egory aircraft provided: aircraft, airframe, aircraft engine, propeller, (i) They are performed by the holder of at or appliance is approved for return to serv- least a private pilot certificate issued under ice.
part 61 of this chapter who is the registered (b) For major repairs made in accordance owner (including co-owners) of the affected with a manual or specifications acceptable aircraft and who holds a certificate of com- to the Administrator, a certificated repair petency for the affected aircraft (1) issued by station may, in place of the requirements of the holder of the production certificate for paragraph (a)—
Federal Aviation Administration, DOT Pt. 43, App. D
(1) Use the customer’s work order upon 73125, within 48 hours after the work is in- which the repair is recorded; spected.
(2) Give the aircraft owner a signed copy of (Secs. 101, 610, 72 Stat. 737, 780, 49 U.S.C. 1301, the work order and retain a duplicate copy 1430) for at least two years from the date of ap- proval for return to service of the aircraft, [Doc. No. 1993, 29 FR 5451, Apr. 23, 1964, as airframe, aircraft engine, propeller, or appli- amended by Amdt. 43–10, 33 FR 15989, Oct. 31, ance; 1968; Amdt. 43–29, 52 FR 34101, Sept. 9, 1987; (3) Give the aircraft owner a maintenance Amdt. 43–31, 54 FR 34330, Aug. 18, 1989; 71 FR release signed by an authorized representa- 58495, Oct. 4, 2006; Amdt. 43–41, 72 FR 53680, tive of the repair station and incorporating Sept. 20, 2007; Doc. No. FAA–2018–0119, Amdt.
the following information: 43–50, 83 FR 9170, Mar. 5, 2018] (i) Identity of the aircraft, airframe, air- A PPENDIX C TO P ART 43 [R ESERVED ] craft engine, propeller or appliance.
(ii) If an aircraft, the make, model, serial A PPENDIX D TO P ART 43—S COPE AND D E- number, nationality and registration marks, and location of the repaired area. TAIL OF ITEMS ( AS A PPLICABLE TO (iii) If an airframe, aircraft engine, pro- THE P ARTICULAR A IRCRAFT) T O B E peller, or appliance, give the manufacturer’s I NCLUDED IN A NNUAL AND 100-H OUR name, name of the part, model, and serial I NSPECTIONS numbers (if any); and (4) Include the following or a similarly (a) Each person performing an annual or worded statement— 100-hour inspection shall, before that inspec- ‘‘The aircraft, airframe, aircraft engine, tion, remove or open all necessary inspection propeller, or appliance identified above was plates, access doors, fairing, and cowling. He repaired and inspected in accordance with shall thoroughly clean the aircraft and air- current Regulations of the Federal Aviation craft engine.
Agency and is approved for return to service.
(b) Each person performing an annual or Pertinent details of the repair are on file 100-hour inspection shall inspect (where ap- at this repair station under Order No. ___ , plicable) the following components of the fu- selage and hull group: Date lllllllllllllllllllll (1) Fabric and skin—for deterioration, dis- Signed llllllllllllllllllll tortion, other evidence of failure, and defec- For signature of authorized representative) tive or insecure attachment of fittings.
(2) Systems and components—for improper Repair station name) (Certificate No.)
installation, apparent defects, and unsatis- ____________ .’’ factory operation.
(Address) (3) Envelope, gas bags, ballast tanks, and (c) Except as provided in paragraph (d) of related parts—for poor condition.
this appendix, for a major repair or major al- (c) Each person performing an annual or teration made by a person authorized in 100-hour inspection shall inspect (where ap- § 43.17, the person who performs the major re- plicable) the following components of the pair or major alteration and the person au- cabin and cockpit group: thorized by § 43.17 to approve that work shall (1) Generally—for uncleanliness and loose execute an FAA Form 337 at least in dupli- equipment that might foul the controls.
cate. A completed copy of that form shall (2) Seats and safety belts—for poor condi- be— tion and apparent defects.
(1) Given to the aircraft owner; and (3) Windows and windshields—for deterio- (2) Forwarded to the Federal Aviation Ad- ration and breakage.
ministration, Aircraft Registration Branch, (4) Instruments—for poor condition, Post Office Box 25504, Oklahoma City, OK mounting, marking, and (where practicable) 73125, within 48 hours after the work is in- improper operation.
spected. (5) Flight and engine controls—for im- (d) For extended-range fuel tanks installed proper installation and improper operation.
within the passenger compartment or a bag- (6) Batteries—for improper installation and gage compartment, the person who performs improper charge.
the work and the person authorized to ap- (7) All systems—for improper installation, prove the work by § 43.7 shall execute an FAA poor general condition, apparent and obvious Form 337 in at least triplicate. A completed defects, and insecurity of attachment.
copy of that form shall be— (d) Each person performing an annual or (1) Placed on board the aircraft as specified 100-hour inspection shall inspect (where ap- in § 91.417 of this chapter; plicable) components of the engine and na- (2) Given to the aircraft owner; and celle group as follows: (3) Forwarded to the Federal Aviation Ad- (1) Engine section—for visual evidence of ministration, Aircraft Registration Branch, , excessive oil, fuel, or hydraulic leaks, and Post Office Box 25724, Oklahoma City, OK sources of such leaks.
14 CFR Ch. I (1–1–25 Edition) Pt. 43, App. E
(2) Studs and nuts—for improper torquing (1) Propeller assembly—for cracks, nicks, and obvious defects. binds, and oil leakage.
(3) Internal engine—for cylinder compres- (2) Bolts—for improper torquing and lack sion and for metal particles or foreign mat- of safetying.
ter on screens and sump drain plugs. If there (3) Anti-icing devices—for improper oper- is weak cylinder compression, for improper ations and obvious defects.
internal condition and improper internal tol- (4) Control mechanisms—for improper op- erances.
eration, insecure mounting, and restricted (4) Engine mount—for cracks, looseness of travel.
mounting, and looseness of engine to mount.
(i) Each person performing an annual or (5) Flexible vibration dampeners—for poor 100-hour inspection shall inspect (where ap- condition and deterioration.
plicable) the following components of the (6) Engine controls—for defects, improper radio group: travel, and improper safetying.
(1) Radio and electronic equipment—for (7) Lines, hoses, and clamps—for leaks, im- improper installation and insecure mount- proper condition and looseness.
ing.
(8) Exhaust stacks—for cracks, defects, and (2) Wiring and conduits—for improper rout- improper attachment.
ing, insecure mounting, and obvious defects.
(9) Accessories—for apparent defects in se- (3) Bonding and shielding—for improper in- curity of mounting.
stallation and poor condition.
(10) All systems—for improper installation, (4) Antenna including trailing antenna—for poor general condition, defects, and insecure poor condition, insecure mounting, and im- attachment.
proper operation.
(11) Cowling—for cracks, and defects.
(j) Each person performing an annual or (e) Each person performing an annual or 100-hour inspection shall inspect (where ap- 100-hour inspection shall inspect (where ap- plicable) each installed miscellaneous item plicable) the following components of the that is not otherwise covered by this listing landing gear group: for improper installation and improper oper- (1) All units—for poor condition and inse- ation.
curity of attachment.
(2) Shock absorbing devices—for improper A PPENDIX E TO P ART 43—A LTIMETER oleo fluid level.
S YSTEM T EST AND INSPECTION (3) Linkages, trusses, and members—for undue or excessive wear fatigue, and distor- Each person performing the altimeter sys- tion.
tem tests and inspections required by § 91.411 (4) Retracting and locking mechanism—for of this chapter must comply with the fol- improper operation.
lowing: (5) Hydraulic lines—for leakage.
(a) Static pressure system: (6) Electrical system—for chafing and im- (1) Ensure freedom from entrapped mois- proper operation of switches.
ture and restrictions.
(7) Wheels—for cracks, defects, and condi- (2) Perform a proof test to demonstrate the tion of bearings.
integrity of the static pressure system in a (8) Tires—for wear and cuts.
manner acceptable to the Administrator. For (9) Brakes—for improper adjustment.
airplanes certificated under part 25 of this (10) Floats and skis—for insecure attach- chapter, determine that leakage is within ment and obvious or apparent defects.
the tolerances established by § 25.1325.
(f) Each person performing an annual or (3) Determine that the static port heater, 100-hour inspection shall inspect (where ap- if installed, is operative.
plicable) all components of the wing and cen- (4) Ensure that no alterations or deforma- ter section assembly for poor general condi- tions of the airframe surface have been made tion, fabric or skin deterioration, distortion, that would affect the relationship between evidence of failure, and insecurity of attach- air pressure in the static pressure system ment.
and true ambient static air pressure for any (g) Each person performing an annual or flight condition.
100-hour inspection shall inspect (where ap- (b) Altimeter: plicable) all components and systems that make up the complete empennage assembly (1) Test by an appropriately rated repair for poor general condition, fabric or skin de- facility in accordance with the following terioration, distortion, evidence of failure, subparagraphs. Unless otherwise specified, insecure attachment, improper component each test for performance may be conducted installation, and improper component oper- with the instrument subjected to vibration.
ation. When tests are conducted with the tempera- (h) Each person performing an annual or ture substantially different from ambient 100-hour inspection shall inspect (where ap- temperature of approximately 25 degrees C., plicable) the following components of the allowance shall be made for the variation propeller group: from the specified condition.
Federal Aviation Administration, DOT Pt. 43, App. E
(i) Scale error. With the barometric pres- (v) Case leak. The leakage of the altimeter sure scale at 29.92 inches of mercury, the al- case, when the pressure within it cor- timeter shall be subjected successively to responds to an altitude of 18,000 feet, shall pressures corresponding to the altitude spec- not change the altimeter reading by more ified in Table I up to the maximum normally than the tolerance shown in Table II during expected operating altitude of the airplane an interval of 1 minute.
in which the altimeter is to be installed. The (vi) Barometric scale error. At constant at- reduction in pressure shall be made at a rate mospheric pressure, the barometric pressure not in excess of 20,000 feet per minute to scale shall be set at each of the pressures within approximately 2,000 feet of the test (falling within its range of adjustment) that point. The test point shall be approached at are listed in Table IV, and shall cause the a rate compatible with the test equipment.
pointer to indicate the equivalent altitude The altimeter shall be kept at the pressure difference shown in Table IV with a toler- corresponding to each test point for at least ance of 25 feet.
1 minute, but not more than 10 minutes, be- (2) Altimeters which are the air data com- fore a reading is taken. The error at all test puter type with associated computing sys- points must not exceed the tolerances speci- tems, or which incorporate air data correc- fied in Table I.
tion internally, may be tested in a manner (ii) Hysteresis. The hysteresis test shall and to specifications developed by the manu- begin not more than 15 minutes after the al- facturer which are acceptable to the Admin- timeter’s initial exposure to the pressure istrator.
corresponding to the upper limit of the scale (c) Automatic Pressure Altitude Reporting error test prescribed in subparagraph (i); and Equipment and ATC Transponder System In- while the altimeter is at this pressure, the tegration Test. The test must be conducted hysteresis test shall commence. Pressure by an appropriately rated person under the shall be increased at a rate simulating a de- conditions specified in paragraph (a). Meas- scent in altitude at the rate of 5,000 to 20,000 ure the automatic pressure altitude at the feet per minute until within 3,000 feet of the output of the installed ATC transponder first test point (50 percent of maximum alti- when interrogated on Mode C at a sufficient tude). The test point shall then be ap- number of test points to ensure that the alti- proached at a rate of approximately 3,000 tude reporting equipment, altimeters, and feet per minute. The altimeter shall be kept ATC transponders perform their intended at this pressure for at least 5 minutes, but functions as installed in the aircraft. The not more than 15 minutes, before the test difference between the automatic reporting reading is taken. After the reading has been output and the altitude displayed at the al- taken, the pressure shall be increased fur- timeter shall not exceed 125 feet.
ther, in the same manner as before, until the (d) Records: Comply with the provisions of pressure corresponding to the second test § 43.9 of this chapter as to content, form, and point (40 percent of maximum altitude) is disposition of the records. The person per- reached. The altimeter shall be kept at this forming the altimeter tests shall record on pressure for at least 1 minute, but not more the altimeter the date and maximum alti- than 10 minutes, before the test reading is tude to which the altimeter has been tested taken. After the reading has been taken, the and the persons approving the airplane for pressure shall be increased further, in the return to service shall enter that data in the same manner as before, until atmospheric airplane log or other permanent record.
pressure is reached. The reading of the al- timeter at either of the two test points shall T ABLE I not differ by more than the tolerance speci- fied in Table II from the reading of the al- Equivalent timeter for the corresponding altitude re- pressure Tolerance Altitude (inches of ± (feet) corded during the scale error test prescribed mercury) in paragraph (b)(i).
(iii) After effect. Not more than 5 minutes ¥ 1,000 .......................................... 31.018 20 after the completion of the hysteresis test 0 ..................................................... 29.921 20 500 ................................................. 29.385 20 prescribed in paragraph (b)(ii), the reading of 1,000 .............................................. 28.856 20 the altimeter (corrected for any change in 1,500 .............................................. 28.335 25 atmospheric pressure) shall not differ from 2,000 .............................................. 27.821 30 the original atmospheric pressure reading by 3,000 .............................................. 26.817 30 more than the tolerance specified in Table 4,000 .............................................. 25.842 35 II. 6,000 .............................................. 23.978 40 8,000 .............................................. 22.225 60 (iv) Friction. The altimeter shall be sub- 10,000 ............................................ 20.577 80 jected to a steady rate of decrease of pres- 12,000 ............................................ 19.029 90 sure approximating 750 feet per minute. At 14,000 ............................................ 17.577 100 each altitude listed in Table III, the change 16,000 ............................................ 16.216 110 in reading of the pointers after vibration 18,000 ............................................ 14.942 120 shall not exceed the corresponding tolerance 20,000 ............................................ 13.750 130 listed in Table III. 22,000 ............................................ 12.636 140
14 CFR Ch. I (1–1–25 Edition) Pt. 43, App. F
T ABLE I—Continued A PPENDIX F TO P ART 43—ATC T RANSPONDER T ESTS AND I NSPECTIONS Equivalent pressure Tolerance Altitude The ATC transponder tests required by (inches of ± (feet) § 91.413 of this chapter may be conducted mercury) using a bench check or portable test equip- 25,000 ............................................ 11.104 155 ment and must meet the requirements pre- 30,000 ............................................ 8.885 180 scribed in paragraphs (a) through (j) of this 35,000 ............................................ 7.041 205 appendix. If portable test equipment with ap- 40,000 ............................................ 5.538 230 propriate coupling to the aircraft antenna 45,000 ............................................ 4.355 255 system is used, operate the test equipment 50,000 ............................................ 3.425 280 for ATCRBS transponders at a nominal rate of 235 interrogations per second to avoid pos- T ABLE II—T EST T OLERANCES sible ATCRBS interference. Operate the test equipment at a nominal rate of 50 Mode S in- Tolerance Test terrogations per second for Mode S. An addi- (feet) tional 3 dB loss is allowed to compensate for Case Leak Test ............................................... ± 100 antenna coupling errors during receiver sen- Hysteresis Test: sitivity measurements conducted in accord- First Test Point (50 percent of maximum ance with paragraph (c)(1) when using port- able test equipment.
Second Test Point (40 percent of max- (a) Radio Reply Frequency: (1) For all classes of ATCRBS tran- sponders, interrogate the transponder and verify that the reply frequency is 1090 ± 3 T ABLE III—F RICTION Megahertz (MHz).
(2) For classes 1B, 2B, and 3B Mode S tran- Tolerance Altitude (feet) sponders, interrogate the transponder and (feet) verify that the reply frequency is 1090 ± 3 1,000 .................................................................... ± 70 MHz.
(3) For classes 1B, 2B, and 3B Mode S tran- sponders that incorporate the optional 1090 ± 1 MHz reply frequency, interrogate the transponder and verify that the reply fre- 20,000 .................................................................. 100 quency is correct.
(4) For classes 1A, 2A, 3A, and 4 Mode S transponders, interrogate the transponder and verify that the reply frequency is 1090 ± 1 MHz.
(b) Suppression: When Classes 1B and 2B ATCRBS Transponders, or Classes 1B, 2B, T ABLE IV—P RESSURE -A LTITUDE D IFFERENCE and 3B Mode S transponders are interrogated Mode 3/A at an interrogation rate between Altitude dif- 230 and 1,000 interrogations per second; or Pressure (inches of Hg) ference when Classes 1A and 2A ATCRBS Tran- (feet) sponders, or Classes 1B, 2A, 3A, and 4 Mode S 28.10 .................................................................... ¥ 1,727 transponders are interrogated at a rate be- 28.50 .................................................................... ¥ 1,340 tween 230 and 1,200 Mode 3/A interrogations 29.00 .................................................................... ¥ 863 per second: 29.50 .................................................................... ¥ 392 (1) Verify that the transponder does not re- spond to more than 1 percent of ATCRBS in- 30.50 .................................................................... + 531 30.90 .................................................................... + 893 terrogations when the amplitude of P pulse 30.99 .................................................................... + 974 is equal to the P pulse.
(2) Verify that the transponder replies to at least 90 percent of ATCRBS interrogations (Secs. 313, 314, and 601 through 610 of the Fed- when the amplitude of the P 2 pulse is 9 dB eral Aviation Act of 1958 (49 U.S.C. 1354, 1355, less than the P 1 pulse. If the test is con- and 1421 through 1430) and sec. 6(c), Dept. of ducted with a radiated test signal, the inter- Transportation Act (49 U.S.C. 1655(c))) rogation rate shall be 235 ± 5 interrogations [Amdt. 43–2, 30 FR 8262, June 29, 1965, as per second unless a higher rate has been ap- amended by Amdt. 43–7, 32 FR 7587, May 24, proved for the test equipment used at that 1967; Amdt. 43–19, 43 FR 22639, May 25, 1978; location.
Amdt. 43–23, 47 FR 41086, Sept. 16, 1982; Amdt.
(c) Receiver Sensitivity: 43–31, 54 FR 34330, Aug. 18, 1989; Doc. No.
(1) Verify that for any class of ATCRBS FAA–2015–1621, Amdt. 43–49, 81 FR 96700, Dec.
Transponder, the receiver minimum trig- 30, 2016] gering level (MTL) of the system is ¥ 73 ± 4
Federal Aviation Administration, DOT Pt. 45
dbm, or that for any class of Mode S trans- equipped, use the communication formats ponder the receiver MTL for Mode S format UF = 20, 21, and 24.
(P6 type) interrogations is ¥ 74 ± 3 dbm by use (h) Mode S All-Call Interrogations: Inter- of a test set either: rogate the Mode S transponder with the (i) Connected to the antenna end of the Mode S-only all-call format UF = 11 and transmission line; verify that the correct address and capa- (ii) Connected to the antenna terminal of bility are reported in the replies (downlink the transponder with a correction for trans- format DF = 11).
mission line loss; or (i) ATCRBS-Only All-Call Interrogation: (iii) Utilized radiated signal. Interrogate the Mode S transponder with the (2) Verify that the difference in Mode 3/A ATCRBS-only all-call interrogation (0.8 and Mode C receiver sensitivity does not ex- microsecond P pulse) and verify that no ceed 1 db for either any class of ATCRBS reply is generated.
transponder or any class of Mode S trans- (j) Squitter: Verify that the Mode S trans- ponder. ponder generates a correct acquisition (d) Radio Frequency (RF) Peak Output squitter approximately once per second.
Power: (k) Records: Comply with the provisions of (1) Verify that the transponder RF output § 43.9 of this chapter as to content, form, and power is within specifications for the class of disposition of the records.
transponder. Use the same conditions as de- [Amdt. 43–26, 52 FR 3390, Feb. 3, 1987; 52 FR scribed in (c)(1)(i), (ii), and (iii) above.
6651, Mar. 4, 1987, as amended by Amdt. 43–31, (i) For Class 1A and 2A ATCRBS tran- 54 FR 34330, Aug. 18, 1989; Amdt. 43–53, 88 FR sponders, verify that the minimum RF peak 71476, Oct. 17, 2023] output power is at least 21.0 dbw (125 watts).
(ii) For Class 1B and 2B ATCRBS Tran-
sponders, verify that the minimum RF peak PART 45—IDENTIFICATION AND
output power is at least 18.5 dbw (70 watts).
REGISTRATION MARKING
(iii) For Class 1A, 2A, 3A, and 4 and those Class 1B, 2B, and 3B Mode S transponders Subpart A—General that include the optional high RF peak out- put power, verify that the minimum RF peak Sec.
output power is at least 21.0 dbw (125 watts).
45.1 Applicability.
(iv) For Classes 1B, 2B, and 3B Mode S transponders, verify that the minimum RF Subpart B—Marking of Products and peak output power is at least 18.5 dbw (70 Articles watts).
(v) For any class of ATCRBS or any class 45.10 Marking.
of Mode S transponders, verify that the max- 45.11 Marking of products.
imum RF peak output power does not exceed 45.13 Identification data.
27.0 dbw (500 watts).
45.15 Marking requirements for PMA arti- cles, TSO articles, and Critical parts.
N OTE : The tests in (e) through (j) apply 45.16 Marking of life-limited parts.
only to Mode S transponders.
(e) Mode S Diversity Transmission Channel Subpart C—Nationality and Registration Isolation: For any class of Mode S trans- Marks ponder that incorporates diversity operation, verify that the RF peak output power trans- 45.21 General.
mitted from the selected antenna exceeds 45.22 Exhibition, antique, and other air- the power transmitted from the nonselected craft: Special rules.
antenna by at least 20 db.
45.23 Display of marks; general.
(f) Mode S Address: Interrogate the Mode S 45.25 Location of marks on fixed-wing air- transponder and verify that it replies only to craft.
its assigned address. Use the correct address 45.27 Location of marks; nonfixed-wing air- and at least two incorrect addresses. The in- craft.
terrogations should be made at a nominal 45.29 Size of marks.
rate of 50 interrogations per second.
45.31 Marking of export aircraft.
(g) Mode S Formats: Interrogate the Mode 45.33 Sale of aircraft; removal of marks.
S transponder with uplink formats (UF) for which it is equipped and verify that the re- A UTHORITY : 49 U.S.C. 106(f), 106(g), 40103, plies are made in the correct format. Use the 40113–40114, 44101–44105, 44107–44111, 44504, surveillance formats UF = 4 and 5. Verify 44701, 44708–44709, 44711–44713, 44725, 45302– that the altitude reported in the replies to 45303, 46104, 46304, 46306, 47122.
UF = 4 are the same as that reported in a S OURCE : Docket No. 2047, 29 FR 3223, Mar.
valid ATCRBS Mode C reply. Verify that the 11, 1964, unless otherwise noted.
identity reported in the replies to UF = 5 are the same as that reported in a valid ATCRBS E DITORIAL N OTE : Nomenclature changes to Mode 3/A reply. If the transponder is so part 45 appear at 74 FR 53394, Oct. 16, 2009.