PART 43--MAINTENANCE, PREVENTIVE MAINTENANCE, REBUILDING, AND ALTERATION
Sec.
43.1 Applicability.
43.2 Records of overhaul and rebuilding.
43.3 Persons authorized to perform maintenance, preventive maintenance,
rebuilding, and alterations.
43.5 Approval for return to service after maintenance, preventive
maintenance, rebuilding, or alteration.
43.7 Persons authorized to approve aircraft, airframes, aircraft engines,
propellers, appliances, or component parts for return to service after
maintenance, preventive maintenance, rebuilding, or alteration.
43.9 Content, form, and disposition of maintenance, preventive maintenance,
rebuilding, and alteration records (except inspections performed in
accordance with Part 91, Part 123, Part 125, Sec. 135.411(a)(1), and Sec.
135.419 of this chapter).
43.11 Content, form, and disposition of records for inspections conducted
under Parts 91 and 125 and Secs. 135.411(a)(1) and 135.419 of this
chapter.
43.12 Maintenance records: Falsification, reproduction, or alteration.
43.13 Performance rules (general).
43.15 Additional performance rules for inspections.
43.16 Airworthiness Limitations.
43.17 Maintenance, preventive maintenance, and alterations performed on
U.S. aeronautical products by certain Canadian persons.
Appendix A--Major Alterations, Major Repairs, and Preventive Maintenance
Appendix B--Recording of Major Repairs and Major Alterations
Appendix C--[Reserved]
Appendix D--Scope and Detail of Items (as Applicable to the Particular
Aircraft) to be Included in Annual and 100-Hour Inspections
Appendix E--Altimeter System Test and Inspection
Appendix F--ATC Transponder Tests and Inspections
Editorial Note: For miscellaneous technical amendments to this Part 43, see
Amdt. 43-3, 31 FR 3336, Mar. 3, 1966, and Amdt. 43-6, 31 FR 9211, July 6,
1966.
Special Federal Aviation Regulation No. 27 [Removed. Amdt. No. 43-32, 55
FR 32861, Aug. 10, 1990. Corrected at 55 FR 35139, Aug. 28, 1990]
EDITORIAL NOTE: For the convenience of the user, the removed text is set
out below.
Special Federal Aviation Regulation No. 27--Fuel Venting and Exhaust Emission
Requirements for Turbine Engine Powered Airplanes
EDITORIAL NOTE: For the text of SFAR No. 27, see Part 11 of this chapter.
SUMMARY: This final rule codifies as new part 34 all of the applicable
aircraft engine fuel venting and exhaust emission requirements of Special
Federal Aviation Regulation (SFAR) 27-5, and the test procedures specified
under the regulations implementing the Clean Air Act. This rule consolidates
all of the requirements and test procedures into this part, and inserts into
other affected parts the requirements to comply with new part 34. New part 34
does not alter any of the requirements specified under SFAR 27-5 or the
regulations implementing the Clean Air Act.
(a) Except as provided in paragraph (b) of this section, this part
prescribes rules governing the maintenance, preventive maintenance,
rebuilding, and alteration of any--
(1) Aircraft having a U.S. airworthiness certificate;
(2) Foreign-registered civil aircraft used in common carriage or carriage
of mail under the provisions of Part 121, 127, or 135 of this chapter; and
(3) Airframe, aircraft engines, propellers, appliances, and component parts
of such aircraft.
(b) This part does not apply to any aircraft for which an experimental
airworthiness certificate has been issued, unless a different kind of
airworthiness certificate had previously been issued for that aircraft.
[Doc. No. 1993, 29 FR 5451, Apr. 23, 1964, as amended by Amdt. 43-23, 47 FR
41084, Sept. 16, 1982]
Sec. 43.2 Records of overhaul and rebuilding.
(a) No person may describe in any required maintenance entry or form an
aircraft, airframe, aircraft engine, propeller, appliance, or component part
as being overhauled unless--
(1) Using methods, techniques, and practices acceptable to the
Administrator, it has been disassembled, cleaned, inspected, repaired as
necessary, and reassembled; and
(2) It has been tested in accordance with approved standards and technical
data, or in accordance with current standards and technical data accepteble
to the Administrator, which have been developed and documented by the holder
of the type certificate, supplemental type certificate, or a material, part,
process, or applicance approval under Sec. 21.305 of this chapter.
(b) No person may describe in any required maintenace entry or form an
aircraft, airframe, aircraft engine, propeller, appliance, or component part
as being rebuilt unless it has been disassembled, cleaned, inspected,
repaired as necessary, reassembled, and tested to the same tolerances and
limits as a new item, using either new parts or used parts that either
conform to new part tolerances and limits or to approved oversized or
undersized dimensions.
[Amdt. 43-23, 47 FR 41084, Sept. 16, 1982]
Sec. 43.3 Persons authorized to perform maintenance, preventive maintenance,
rebuilding, and alterations.
(a) Except as provided in this section and Sec. 43.17, no person may
maintain, rebuild, alter, or perform preventive maintenance on an aircraft,
airframe, aircraft engine, propeller, appliance, or component part to which
this part applies. Those items, the performance of which is a major
alteration, a major repair, or preventive maintenance, are listed in Appendix
A.
(b) The holder of a mechanic certificate may perform maintenance,
preventive maintenance, and alterations as provided in Part 65 of this
chapter.
(c) The holder of a repairman certificate may perform maintenance and
preventive maintenance as provided in Part 65 of this chapter.
(d) A person working under the supervision of a holder of a mechanic or
repairman certificate may perform the maintenance, preventive maintenance,
and alterations that his supervisor is authorized to perform, if the
supervisor personally observes the work being done to the extent necessary to
ensure that it is being done properly and if the supervisor is readily
available, in person, for consultation. However, this paragraph does not
authorize the performance of any inspection required by Part 91 or Part 125
of this chapter or any inspection performed after a major repair or
alteration.
(e) The holder of a repair station certificate may perform maintenance,
preventive maintenance, and alterations as provided in Part 145 of this
chapter.
(f) The holder of an air carrier operating certificate or an operating
certificate issued under Part 121, 127, or 135, may perform maintenance,
preventive maintenance, and alterations as provided in Part 121, 127, or 135.
(g) The holder of a pilot certificate issued under Part 61 may perform
preventive maintenance on any aircraft owned or operated by that pilot which
is not used under Part 121, 127, 129, or 135.
(h) Notwithstanding the provisions of paragraph (g) of this section, the
Administrator may approve a certificate holder under Part 135 of this
chapter, operating rotorcraft in a remote area, to allow a pilot to perform
specific preventive maintenance items provided--
(1) The items of preventive maintenance are a result of a known or
suspected mechanical difficulty or malfunction that occurred en route to or
in a remote area;
(2) The pilot has satisfactorily completed an approved training program and
is authorized in writing by the certificate holder for each item of
preventive maintenance that the pilot is authorized to perform;
(3) There is no certificated mechanic available to perform preventive
maintenance;
(4) The certificate holder has procedures to evaluate the accomplishment of
a preventive maintenance item that requires a decision concerning the
airworthiness of the rotorcraft; and
(5) The items of preventive maintenance authorized by this section are
those listed in paragraph (c) of Appendix A of this part.
(i) A manufacturer may--
(1) Rebuild or alter any aircraft, aircraft engine, propeller, or appliance
manufactured by him under a type or production certificate;
(2) Rebuild or alter any appliance or part of aircraft, aircraft engines,
propellers, or appliances manufactured by him under a Technical Standard
Order Authorization, an FAA-Parts Manufacturer Approval, or Product and
Process Specification issued by the Administrator; and
(3) Perform any inspection required by Part 91 or Part 125 of this chapter
on aircraft it manufacturers, while currently operating under a production
certificate or under a currently approved production inspection system for
such aircraft.
Sec. 43.5 Approval for return to service after maintenance, preventive
maintenance, rebuilding, or alteration.
No person may approve for return to service any aircraft, airframe,
aircraft engine, propeller, or appliance, that has undergone maintenance,
preventive maintenance, rebuilding, or alteration unless--
(a) The maintenance record entry required by Sec. 43.9 or Sec. 43.11, as
appropriate, has been made;
(b) The repair or alteration form authorized by or furnished by the
Administrator has been executed in a manner prescribed by the Administrator;
and
(c) If a repair or an alteration results in any change in the aircraft
operating limitations or flight data contained in the approved aircraft
flight manual, those operating limitations or flight data are appropriately
revised and set forth as prescribed in Sec. 91.9 of this chapter.
[Docket No. 1993, 29 FR 5451, Apr. 23, 1964, as amended by Amdt. 43-23, 47 FR
41084, Sept. 16, 1982; Amdt. 43-31, 54 FR 34330, Aug. 18, 1989]
Effective Date Note: At 54 FR 34330, Aug. 18, 1989, Sec. 43.5(c) was
amended by changing the cross reference "Sec. 91.31" to "Sec. 91.9",
effective August 18, 1990.
Sec. 43.7 Persons authorized to approve aircraft, airframes, aircraft
engines, propellers, appliances, or component parts for return to service
after maintenance, preventive maintenance, rebuilding, or alteration.
(a) Except as provided in this section and Sec. 43.17, no person, other
than the Administrator, may approve an aircraft, airframe, aircraft engine,
propeller, appliance, or component part for return to service after it has
undergone maintenance, preventive maintenance, rebuilding, or alteration.
(b) The holder of a mechanic certificate or an inspection authorization may
approve an aircraft, airframe, aircraft engine, propeller, appliance, or
component part for return to service as provided in Part 65 of this chapter.
(c) The holder of a repair station certificate may approve an aircraft,
airframe, aircraft engine, propeller, appliance, or component part for return
to service as provided in Part 145 of this chapter.
(d) A manufacturer may approve for return to service any aircraft,
airframe, aircraft engine, propeller, appliance, or component part which that
manufacturer has worked on under Sec. 43.3(h). However, except for minor
alterations, the work must have been done in accordance with technical data
approved by the Administrator.
(e) The holder of an air carrier operating certificate or an operating
certificate issued under Part 121, 127, or 135, may approve an aircraft,
airframe, aircraft engine, propeller, appliance, or component part for return
to service as provided in Part 121, 127, or 135 of this chapter, as
applicable.
(f) A person holding at least a private pilot certificate may approve an
aircraft for return to service after performing preventive maintenance under
the provisions of Sec. 43.3(g).
[Amdt. 43-23, 47 FR 41084, Sept. 16, 1982]
Sec. 43.9 Content, form, and disposition of maintenance, preventive
maintenance, rebuilding, and alteration records (except inspections
performed in accordance with Part 91, Part 123, Part 125, Sec.
135.411(a)(1), and Sec. 135.419 of this chapter).
(a) Maintenance record entries. Except as provided in paragraphs (b) and
(c) of this section, each person who maintains, performs preventive
maintenance, rebuilds, or alters an aircraft, airframe, aircraft engine,
propeller, appliance, or component part shall make an entry in the
maintenance record of that equipment containing the following information:
(1) A description (or reference to data acceptable to the Administrator) of
work performed.
(2) The date of completion of the work performed.
(3) The name of the person performing the work if other than the person
specified in paragraph (a)(4) of this section.
(4) If the work performed on the aircraft, airframe, aircraft engine,
propeller, appliance, or component part has been performed satisfactorily,
the signature, certificate number, and kind of certificate held by the person
approving the work. The signature constitutes the approval for return to
service only for the work performed.
In addition to the entry required by this paragraph, major repairs and major
alterations shall be entered on a form, and the form disposed of, in the
manner prescribed in Appendix B, by the person performing the work.
(b) Each holder of an air carrier operating certificate or an operating
certificate issued under Part 121, 127, or 135, that is required by its
approved operations specifications to provide for a continuous airworthiness
maintenance program, shall make a record of the maintenance, preventive
maintenance, rebuilding, and alteration, on aircraft, airframes, aircraft
engines, propellers, appliances, or component parts which it operates in
accordance with the applicable provisions of Part 121, 127, or 135 of this
chapter, as appropriate.
(c) This section does not apply to persons performing inspections in
accordance with Part 91, 123, 125, Sec. 135.411(a)(1), or Sec. 135.419 of
this chapter.
[Amdt. 43-23, 47 FR 41085, Sept. 16, 1982]
Sec. 43.11 Content, form, and disposition of records for inspections
conducted under Parts 91 and 125 and Secs. 135.411(a)(1) and 135.419 of
this chapter.
(a) Maintenance record entries. The person approving or disapproving for
return to service an aircraft, airframe, aircraft engine, propeller,
appliance, or component part after any inspection performed in accordance
with Part 91, 123, 125, Sec. 135.411(a)(1), or Sec. 135.419 shall make an
entry in the maintenance record of that equipment containing the following
information:
(1) The type of inspection and a brief description of the extent of the
inspection.
(2) The date of the inspection and aircraft total time in service.
(3) The signature, the certificate number, and kind of certificate held by
the person approving or disapproving for return to service the aircraft,
airframe, aircraft engine, propeller, appliance, component part, or portions
thereof.
(4) Except for progressive inspections, if the aircraft is found to be
airworthy and approved for return to service, the following or a similarly
worded statement--"I certify that this aircraft has been inspected in
accordance with (insert type) inspection and was determined to be in
airworthy condition."
(5) Except for progressive inspections, if the aircraft is not approved for
return to service because of needed maintenance, noncompliance with
applicable specifications, airworthiness directives, or other approved data,
the following or a similarly worded statement--"I certify that this aircraft
has been inspected in accordance with (insert type) inspection and a list of
discrepancies and unairworthy items dated (date) has been provided for the
aircraft owner or operator."
(6) For progressive inspections, the following or a similarly worded
statement--"I certify that in accordance with a progressive inspection
program, a routine inspection of (identify whether aircraft or components)
and a detailed inspection of (identify components) were performed and the
(aircraft or components) are (approved or disapproved) for return to
service." If disapproved, the entry will further state "and a list of
discrepancies and unairworthy items dated (date) has been provided to the
aircraft owner or operator."
(7) If an inspection is conducted under an inspection program provided for
in Part 91, 123, 125, or Sec. 135.411(a)(1), the entry must identify the
inspection program, that part of the inspection program accomplished, and
contain a statement that the inspection was performed in accordance with the
inspections and procedures for that particular program.
(b) Listing of discrepancies and placards. If the person performing any
inspection required by Part 91 or 125 or Sec. 135.411(a)(1) of this chapter
finds that the aircraft is unairworthy or does not meet the applicable type
certificate data, airworthiness directives, or other approved data upon which
its airworthiness depends, that persons must give the owner or lessee a
signed and dated list of those discrepancies. For those items permitted to be
inoperative under Sec. 91.30(d)(2), that person shall place a placard, that
meets the aircraft's airworthiness certification regulations, on each
inoperative instrument and the cockpit control of each item of inoperative
equipment, marking it "Inoperative," and shall add the items to the signed
and dated list of discrepancies given to the owner or lessee.
[Amdt. 43-23, 47 FR 41085, Sept. 16, 1982, as amended by Amdt. 43-30, 53 FR
50195, Dec. 13, 1988]
Sec. 43.12 Maintenance records: Falsification, reproduction, or alteration.
(a) No person may make or cause to be made:
(1) Any fraudulent or intentionally false entry in any record or report
that is required to be made, kept, or used to show compliance with any
requirement under this part;
(2) Any reproduction, for fraudulent purpose, of any record or report under
this part; or
(3) Any alteration, for fraudulent purpose, of any record or report under
this part.
(b) The commission by any person of an act prohibited under paragraph (a)
of this section is a basis for suspending or revoking the applicable airman,
operator, or production certificate, Technical Standard Order Authorization,
FAA-Parts Manufacturer Approval, or Product and Process Specification issued
by the Administrator and held by that person.
[Amdt. 43-19, 43 FR 22639, May 25, 1978, as amended by Amdt. 43-23, 47 FR
41085, Sept. 16, 1982]
Sec. 43.13 Performance rules (general).
(a) Each person performing maintenance, alteration, or preventive
maintenance on an aircraft, engine, propeller, or appliance shall use the
methods, techniques, and practices prescribed in the current manufacturer's
maintenance manual or Instructions for Continued Airworthiness prepared by
its manufacturer, or other methods, techniques, and practices acceptable to
the Administrator, except as noted in Sec. 43.16. He shall use the tools,
equipment, and test apparatus necessary to assure completion of the work in
accordance with accepted industry practices. If special equipment or test
apparatus is recommended by the manufacturer involved, he must use that
equipment or apparatus or its equivalent acceptable to the Administrator.
(b) Each person maintaining or altering, or performing preventive
maintenance, shall do that work in such a manner and use materials of such a
quality, 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 (with regard to aerodynamic function, structural
strength, resistance to vibration and deterioration, and other qualities
affecting airworthiness).
(c) Special provisions for holders of air carrier operating certificates
and operating certificates issued under the provisions of Part 121, 127, or
135 and Part 129 operators holding operations specifications. Unless
otherwise notified by the administrator, the methods, techniques, and
practices contained in the maintenance manual or the maintenance part of the
manual of the holder of an air carrier operating certificate or an operating
certificate under Part 121, 127, or 135 and Part 129 operators holding
operations specifications (that is required by its operating specifications
to provide a continuous airworthiness maintenance and inspection program)
constitute acceptable means of compliance with this section.
Sec. 43.15 Additional performance rules for inspections.
(a) General. Each person performing an inspection required by Part 91, 123,
125, or 135 of this chapter, shall--
(1) Perform the inspection so as to determine whether the aircraft, or
portion(s) thereof under inspection, meets all applicable airworthiness
requirements; and
(2) If the inspection is one provided for in Part 123, 125, 135, or Sec.
91.409(e) of this chapter, perform the inspection in accordance with the
instructions and procedures set forth in the inspection program for the
aircraft being inspected.
(b) Rotorcraft. Each person performing an inspection required by Part 91 on
a rotorcraft shall inspect the following systems in accordance with the
maintenance manual or Instructions for Continued Airworthiness of the
manufacturer concerned:
(1) The drive shafts or similar systems.
(2) The main rotor transmission gear box for obvious defects.
(3) The main rotor and center section (or the equivalent area).
(4) The auxiliary rotor on helicopters.
(c) Annual and 100-hour inspections. (1) Each person performing an annual
or 100-hour inspection shall use a checklist while performing the inspection.
The checklist may be of the person's own design, one provided by the
manufacturer of the equipment being inspected or one obtained from another
source. This checklist must include the scope and detail of the items
contained in Appendix D to this part and paragraph (b) of this section.
(2) Each person approving a reciprocating-engine-powered aircraft for
return to service after an annual or 100-hour inspection shall, before that
approval, run the aircraft engine or engines to determine satisfactory
performance in accordance with the manufacturer's recommendations of--
(i) Power output (static and idle r.p.m.);
(ii) Magnetos;
(iii) Fuel and oil pressure; and
(iv) Cylinder and oil temperature.
(3) Each person approving a turbine-engine-powered aircraft for return to
service after an annual, 100-hour, or progressive inspection shall, before
that approval, run the aircraft engine or engines to determine satisfactory
performance in accordance with the manufacturer's recommendations.
(d) Progressive inspection. (1) Each person performing a progressive
inspection shall, at the start of a progressive inspection system, inspect
the aircraft completely. After this initial inspection, routine and detailed
inspections must be conducted as prescribed in the progressive inspection
schedule. Routine inspections consist of visual examination or check of the
appliances, the aircraft, and its components and systems, insofar as
practicable without disassembly. Detailed inspections consist of a thorough
examination of the appliances, the aircraft, and its components and systems,
with such disassembly as is necessary. For the purposes of this subparagraph,
the overhaul of a component or system is considered to be a detailed
inspection.
(2) If the aircraft is away from the station where inspections are normally
conducted, an appropriately rated mechanic, a certificated repair station, or
the manufacturer of the aircraft may perform inspections in accordance with
the procedures and using the forms of the person who would otherwise perform
the inspection.
Effective Date Note: At 54 FR 34330, August 18, 1989, Sec. 43.15(a)(2) was
amended by changing the cross reference "Sec. 91.169(e)" to "Sec. 91.409(e)",
effective August 18, 1990.
Sec. 43.16 Airworthiness Limitations.
Each person performing an inspection or other maintenance specified in an
Airworthiness Limitations section of a manufacturer's maintenance manual or
Instructions for Continued Airworthiness shall perform the inspection or
other maintenance in accordance with that section, or in accordance with
operations specifications approved by the Administrator under Parts 121, 123,
127, or 135, or an inspection program approved under Sec. 91.409(e).
[Amdt. 43-20, 45 FR 60183, Sept. 11, 1980, as amended by Amdt. 43-23, 47 FR
41086, Sept. 16, 1982; Amdt. 43-31, 54 FR 34330, Aug. 18, 1989]
Effective Date Note: At 54 FR 34330, Aug. 18, 1989, Sec. 43.16 was amended
by changing the cross reference "Sec. 91.169(e)" to "Sec. 91.409(e)",
effective August 18, 1990.
Sec. 43.17 Maintenance, preventive maintenance, and alterations performed on
U.S. aeronautical products by certain Canadian persons.
(a) Definitions. For purposes of this section:
Aeronautical product means any civil aircraft or airframe, aircraft engine,
propeller, appliance, component, or part to be installed thereon.
Canadian aeronautical product means any civil aircraft or airframe,
aircraft engine, propeller, or appliance under airworthiness regulation by
the Canadian Department of Transport, or component or part to be installed
thereon.
U.S. aeronautical product means any civil aircraft or airframe, aircraft
engine, propeller, or appliance under airworthiness regulation by the FAA, or
component or part to be installed thereon.
(b) Applicability. This section does not apply to any U.S. aeronautical
products maintained or altered under any bilateral agreement made between
Canada and any country other than the United States.
(c) Authorized persons. (1) A person holding a valid Canadian Department of
Transport license (Aircraft Maintenance Engineer) and appropriate ratings
may, with respect to a U.S.-registered aircraft located in Canada, perform
maintenance, preventive maintenance, and alterations in accordance with the
requirements of paragraph (d) of this section and approve the affected
aircraft for return to service in accordance with the requirements of
paragraph (e) of this section.
(2) A company (Approved Maintenance Organization) (AMO) whose system of
quality control for the maintenance, alteration, and inspection of
aeronautical products has been approved by the Canadian Department of
Transport, or a person who is an authorized employee performing work for such
a company may, with respect to a U.S.-registered aircraft located in Canada
or other U.S. aeronautical products transported to Canada from the United
States, perform maintenance, preventive maintenance, and alterations in
accordance with the requirements of paragraph (d) of this section and approve
the affected products for return to service in accordance with the
requirements of paragraph (e) of this section.
(d) Performance requirements. A person authorized in paragraph (c) of this
section may perform maintenance (including any inspection required by Sec.
91.409 of this chapter, except an annual inspection), preventive maintenance,
and alterations, provided:
(1) The person performing the work is authorized by the Canadian Department
of Transport to perform the same type of work with respect to Canadian
aeronautical products;
(2) The work is performed in accordance with Secs. 43.13, 43.15, and 43.16
of this chapter, as applicable;
(3) The work is performed such that the affected product complies with the
applicable requirements of part 36 of this chapter; and
(4) The work is recorded in accordance with Secs. 43.2(a), 43.9, and 43.11
of this chapter, as applicable.
(e) Approval requirements. (1) To return an affected product to service, a
person authorized in paragraph (c) of this section must approve (certify)
maintenance, preventive maintenance, and alterations performed under this
section, except that an Aircraft Maintenance Engineer may not approve a major
repair or major alteration.
(2) An AMO whose system of quality control for the maintenance, preventive
maintenance, alteration, and inspection of aeronautical products has been
approved by the Canadian Department of Transport, or an authorized employee
performing work for such an AMO, may approve (certify) a major repair or
major alteration performed under this section if the work was performed in
accordance with technical data approved by the Administrator.
(f) No person may operate in air commerce an aircraft, airframe, aircraft
engine, propeller, or appliance on which maintenance, preventive maintenance,
or alteration has been performed under this section unless it has been
approved for return to service by a person authorized in this section.
SUMMARY: This amendment provides for the acceptance by the FAA of
maintenance, preventive maintenance, and alterations accomplished on U.S.
civil aeronautical products and components in Canada. The amendment
implements the airworthiness maintenance provisions contained in the
U.S./Canada Bilateral Airworthiness Agreement (U.S./CBAA) and the Schedule of
Implementation Procedures between the United States and Canada. The amendment
provides for acceptance by the FAA of maintenance, preventive maintenance,
and alterations performed on aircraft engines, propellers, appliances,
materials, parts, and other components which are transported from the United
States to Canada and which are for installation on U.S.-registered aircraft.
Appendix A--Major Alterations, Major Repairs, and Preventive Maintenance
(a) Major alterations--(1) Airframe major alterations. Alterations of the
following parts and alterations of the following types, when not listed in
the aircraft specifications issued by the FAA, are airframe major
alterations:
(i) Wings.
(ii) Tail surfaces.
(iii) Fuselage.
(iv) Engine mounts.
(v) Control system.
(vi) Landing gear.
(vii) Hull or floats.
(viii) Elements of an airframe including spars, ribs, fittings, shock
absorbers, bracing, cowling, fairings, and balance weights.
(ix) Hydraulic and electrical actuating system of components.
(x) Rotor blades.
(xi) Changes to the empty weight or empty balance which result in an
increase in the maximum certificated weight or center of gravity limits of
the aircraft.
(xii) Changes to the basic design of the fuel, oil, cooling, heating, cabin
pressurization, electrical, hydraulic, de-icing, or exhaust systems.
(xiii) Changes to the wing or to fixed or movable control surfaces which
affect flutter and vibration characteristics.
(2) Powerplant major alterations. The following alterations of a powerplant
when not listed in the engine specifications issued by the FAA, are
powerplant major alterations.
(i) Conversion of an aircraft engine from one approved model to another,
involving any changes in compression ratio, propeller reduction gear,
impeller gear ratios or the substitution of major engine parts which requires
extensive rework and testing of the engine.
(ii) Changes to the engine by replacing aircraft engine structural parts
with parts not supplied by the original manufacturer or parts not
specifically approved by the Administrator.
(iii) Installation of an accessory which is not approved for the engine.
(iv) Removal of accessories that are listed as required equipment on the
aircraft or engine specification.
(v) Installation of structural parts other than the type of parts approved
for the installation.
(vi) Conversions of any sort for the purpose of using fuel of a rating or
grade other than that listed in the engine specifications.
(3) Propeller major alterations. The following alterations of a propeller
when not authorized in the propeller specifications issued by the FAA are
propeller major alterations:
(i) Changes in blade design.
(ii) Changes in hub design.
(iii) Changes in the governor or control design.
(iv) Installation of a propeller governor or feathering system.
(v) Installation of propeller de-icing system.
(vi) Installation of parts not approved for the propeller.
(4) Appliance major alterations. Alterations of the basic design not made
in accordance with recommendations of the appliance manufacturer or in
accordance with an FAA Airworthiness Directive are appliance major
alterations. In addition, changes in the basic design of radio communication
and navigation equipment approved under type certification or a Technical
Standard Order that have an effect on frequency stability, noise level,
sensitivity, selectivity, distortion, spurious radiation, AVC
characteristics, or ability to meet environmental test conditions and other
changes that have an effect on the performance of the equipment are also
major alterations.
(b) Major repairs--(1) Airframe major repairs. Repairs to the following
parts of an airframe and repairs of the following types, involving the
strengthening, reinforcing, splicing, and manufacturing of primary structural
members or their replacement, when replacement is by fabrication such as
riveting or welding, are airframe major repairs.
(i) Box beams.
(ii) Monocoque or semimonocoque wings or control surfaces.
(iii) Wing stringers or chord members.
(iv) Spars.
(v) Spar flanges.
(vi) Members of truss-type beams.
(vii) Thin sheet webs of beams.
(viii) Keel and chine members of boat hulls or floats.
(ix) Corrugated sheet compression members which act as flange material of
wings or tail surfaces.
(x) Wing main ribs and compression members.
(xi) Wing or tail surface brace struts.
(xii) Engine mounts.
(xiii) Fuselage longerons.
(xiv) Members of the side truss, horizontal truss, or bulkheads.
(xv) Main seat support braces and brackets.
(xvi) Landing gear brace struts.
(xvii) Axles.
(xviii) Wheels.
(xix) Skis, and ski pedestals.
(xx) Parts of the control system such as control columns, pedals, shafts,
brackets, or horns.
(xxi) Repairs involving the substitution of material.
(xxii) The repair of damaged areas in metal or plywood stressed covering
exceeding six inches in any direction.
(xxiii) The repair of portions of skin sheets by making additional seams.
(xxiv) The splicing of skin sheets.
(xxv) The repair of three or more adjacent wing or control surface ribs or
the leading edge of wings and control surfaces, between such adjacent ribs.
(xxvi) Repair of fabric covering involving an area greater than that
required to repair two adjacent ribs.
(xxvii) Replacement of fabric on fabric covered parts such as wings,
fuselages, stabilizers, and control surfaces.
(xxviii) Repairing, including rebottoming, of removable or integral fuel
tanks and oil tanks.
(2) Powerplant major repairs. Repairs of the following parts of an engine
and repairs of the following types, are powerplant major repairs:
(i) Separation or disassembly of a crankcase or crankshaft of a
reciprocating engine equipped with an integral supercharger.
(ii) Separation or disassembly of a crankcase or crankshaft of a
reciprocating engine equipped with other than spur-type propeller reduction
gearing.
(iii) Special repairs to structural engine parts by welding, plating,
metalizing, or other methods.
(3) Propeller major repairs. Repairs of the following types to a propeller
are propeller major repairs:
(i) Any repairs to, or straightening of steel blades.
(ii) Repairing or machining of steel hubs.
(iii) Shortening of blades.
(iv) Retipping of wood propellers.
(v) Replacement of outer laminations on fixed pitch wood propellers.
(vi) Repairing elongated bolt holes in the hub of fixed pitch wood
propellers.
(vii) Inlay work on wood blades.
(viii) Repairs to composition blades.
(ix) Replacement of tip fabric.
(x) Replacement of plastic covering.
(xi) Repair of propeller governors.
(xii) Overhaul of controllable pitch propellers.
(xiii) Repairs to deep dents, cuts, scars, nicks, etc., and straightening
of aluminum blades.
(xiv) The repair or replacement of internal elements of blades.
(4) Appliance major repairs. Repairs of the following types to appliances
are appliance major repairs:
(i) Calibration and repair of instruments.
(ii) Calibration of radio equipment.
(iii) Rewinding the field coil of an electrical accessory.
(iv) Complete disassembly of complex hydraulic power valves.
(v) Overhaul of pressure type carburetors, and pressure type fuel, oil and
hydraulic pumps.
(c) Preventive maintenance. Preventive maintenance is limited to the
following work, provided it does not involve complex assembly operations:
(1) Removal, installation, and repair of landing gear tires.
(2) Replacing elastic shock absorber cords on landing gear.
(3) Servicing landing gear shock struts by adding oil, air, or both.
(4) Servicing landing gear wheel bearings, such as cleaning and greasing.
(5) Replacing defective safety wiring or cotter keys.
(6) Lubrication not requiring disassembly other than removal of
nonstructural items such as cover plates, cowlings, and fairings.
(7) Making simple fabric patches not requiring rib stitching or the removal
of structural parts or control surfaces. In the case of balloons, the making
of small fabric repairs to envelopes (as defined in, and in accordance with,
the balloon manufacturers' instructions) not requiring load tape repair or
replacement.
(8) Replenishing hydraulic fluid in the hydraulic reservoir.
(9) Refinishing decorative coating of fuselage, balloon baskets, wings tail
group surfaces (excluding balanced control surfaces), fairings, cowlings,
landing gear, cabin, or cockpit interior when removal or disassembly of any
primary structure or operating system is not required.
(10) Applying preservative or protective material to components where no
disassembly of any primary structure or operating system is involved and
where such coating is not prohibited or is not contrary to good practices.
(11) Repairing upholstery and decorative furnishings of the cabin, cockpit,
or balloon basket interior when the repairing does not require disassembly of
any primary structure or operating system or interfere with an operating
system or affect the primary structure of the aircraft.
(12) Making small simple repairs to fairings, nonstructural cover plates,
cowlings, and small patches and reinforcements not changing the contour so as
to interfere with proper air flow.
(13) Replacing side windows where that work does not interfere with the
structure or any operating system such as controls, electrical equipment,
etc.
(14) Replacing safety belts.
(15) Replacing seats or seat parts with replacement parts approved for the
aircraft, not involving disassembly of any primary structure or operating
system.
(16) Trouble shooting and repairing broken circuits in landing light wiring
circuits.
(17) Replacing bulbs, reflectors, and lenses of position and landing
lights.
(18) Replacing wheels and skis where no weight and balance computation is
involved.
(19) Replacing any cowling not requiring removal of the propeller or
disconnection of flight controls.
(20) Replacing or cleaning spark plugs and setting of spark plug gap
clearance.
(21) Replacing any hose connection except hydraulic connections.
(22) Replacing prefabricated fuel lines.
(23) Cleaning or replacing fuel and oil strainers or filter elements.
(24) Replacing and servicing batteries.
(25) Cleaning of balloon burner pilot and main nozzles in accordance with
the balloon manufacturer's instructions.
(26) Replacement or adjustment of nonstructural standard fasteners
incidental to operations.
(27) The interchange of balloon baskets and burners on envelopes when the
basket or burner is designated as interchangeable in the balloon type
certificate data and the baskets and burners are specifically designed for
quick removal and installation.
(28) The installations of anti-misfueling devices to reduce the diameter of
fuel tank filler openings provided the specific device has been made a part
of the aircraft type certificiate data by the aircraft manufacturer, the
aircraft manufacturer has provided FAA-approved instructions for installation
of the specific device, and installation does not involve the disassembly of
the existing tank filler opening.
(29) Removing, checking, and replacing magnetic chip detectors.
(30) The inspection and maintenance tasks prescribed and specifically
identified as preventive maintenance in a primary category aircraft type
certificate or supplemental type certificate holder's approved special
inspection and preventive maintenance program when accomplished on a primary
category aircraft provided:
(i) They are performed by the holder of at least a private pilot
certificate issued under part 61 who is the registered owner (including co-
owners) of the affected aircraft and who holds a certificate of competency
for the affected aircraft (1) issued by a school approved under Sec.
147.21(f) of this chapter; (2) issued by the holder of the production
certificate for that primary category aircraft that has a special training
program approved under Sec. 21.24 of this subchapter; or (3) issued by
another entity that has a course approved by the Administrator; and
(ii) The inspections and maintenance tasks are performed in accordance with
instructions contained by the special inspection and preventive maintenance
program approved as part of the aircraft's type design or supplemental type
design.
(Secs. 313, 601 through 610, and 1102, Federal Aviation Act of 1958 as
amended (49 U.S.C. 1354, 1421 through 1430 and 1502); (49 U.S.C. 106(g)
(Revised Pub. L. 97-449, Jan. 21, 1983); and 14 CFR 11.45)
SUMMARY: This final rule establishes a new primary category of aircraft, and
new simplified procedures for type, production, and airworthiness
certification, and associated maintenance procedures. Aircraft in this
category are of simple design intended exclusively for pleasure and personal
use. Primary category aircraft (airplanes, gliders, rotorcraft, manned free
balloons, etc.) may be unpowered or powered by a single, naturally aspirated
engine, with a 61-knot or less stall speed limitation for airplanes and a 6-
pound per square foot main rotor disc loading limitation for rotorcraft.
Primary category aircraft may have a maximum certificated weight of no more
than 2,700 pounds, maximum seating capacity of four, and unpressurized
cabins. Although these aircraft may be available for rental and flight
instruction under certain conditions, the carrying of persons or property for
hire is prohibited. This final rule also adds a new section addressing the
falsification of documents submitted as part of certification for products
and parts.
Appendix B--Recording of Major Repairs and Major Alterations
(a) Except as provided in paragraphs (b), (c), and (d) of this appendix,
each person performing a major repair or major alteration shall--
(1) Execute FAA Form 337 at least in duplicate;
(2) Give a signed copy of that form to the aircraft owner; and
(3) Forward a copy of that form to the local Flight Standards District
Office within 48 hours after the aircraft, airframe, aircraft engine,
propeller, or appliance is approved for return to service.
(b) For major repairs made in accordance with a manual or specifications
acceptable to the Administrator, a certificated repair station may, in place
of the requirements of paragraph (a)--
(1) Use the customer's work order upon which the repair is recorded;
(2) Give the aircraft owner a signed copy of the work order and retain a
duplicate copy for at least two years from the date of approval for return to
service of the aircraft, airframe, aircraft engine, propeller, or appliance;
(3) Give the aircraft owner a maintenance release signed by an authorized
representative of the repair station and incorporating the following
information:
(i) Identity of the aircraft, airframe, aircraft engine, propeller or
appliance.
(ii) If an aircraft, the make, model, serial number, nationality and
registration marks, and location of the repaired area.
(iii) If an airframe, aircraft engine, propeller, or appliance, give the
manufacturer's name, name of the part, model, and serial numbers (if any);
and
(4) Include the following or a similarly worded statement--
"The aircraft, airframe, aircraft engine, propeller, or appliance
identified above was repaired and inspected in accordance with current
Regulations of the Federal Aviation Agency and is approved for return to
service.
Pertinent details of the repair are on file at this repair station under
Order No. ------,
Date-------------------------------------------------------------------------
Signed-----------------------------------------------------------------------
(For signature of authorized representative)
-----------------------------------------------------------------------------
(Repair station name) (Certificate No.)
------------------------."
(Address)
(c) For a major repair or major alteration made by a person authorized in
Sec. 43.17, the person who performs the major repair or major alteration and
the person authorized by Sec. 43.17 to approve that work shall execute a FAA
Form 337 at least in duplicate. A completed copy of that form shall be--
(1) Given to the aircraft owner; and
(2) Forwarded to the Federal Aviation Administration, Aircraft Registration
Branch, Post Office Box 25082, Oklahoma City, Okla. 73125, within 48 hours
after the work is inspected.
(d) For extended-range fuel tanks installed within the passenger
compartment or a baggage compartment, the person who performs the work and
the person authorized to approve the work by Sec. 43.7 of this part shall
execute an FAA Form 337 in at least triplicate. One (1) copy of the FAA Form
337 shall be placed on board the aircraft as specified in Sec. 91.417 of this
chapter. The remaining forms shall be distributed as required by paragraph
(a) (2) and (3) or (c) (1) and (2) of this paragraph as appropriate.
Effective Date Note: At 54 FR 34330, Aug. 18, 1989, Appendix B, Part 43 was
amended by changing the cross reference "91.173" to "91.417" in paragraph
(d), effective August 18, 1990.
Appendix C--[Reserved]
Appendix D--Scope and Detail of Items (as Applicable to the Particular
Aircraft) To Be Included in Annual and 100-Hour Inspections
(a) Each person performing an annual or 100-hour inspection shall, before
that inspection, remove or open all necessary inspection plates, access
doors, fairing, and cowling. He shall thoroughly clean the aircraft and
aircraft engine.
(b) Each person performing an annual or 100-hour inspection shall inspect
(where applicable) the following components of the fuselage and hull group:
(1) Fabric and skin--for deterioration, distortion, other evidence of
failure, and defective or insecure attachment of fittings.
(2) Systems and components--for improper installation, apparent defects,
and unsatisfactory operation.
(3) Envelope, gas bags, ballast tanks, and related parts--for poor
condition.
(c) Each person performing an annual or 100-hour inspection shall inspect
(where applicable) the following components of the cabin and cockpit group:
(1) Generally--for uncleanliness and loose equipment that might foul the
controls.
(2) Seats and safety belts--for poor condition and apparent defects.
(3) Windows and windshields--for deterioration and breakage.
(4) Instruments--for poor condition, mounting, marking, and (where
practicable) improper operation.
(5) Flight and engine controls--for improper installation and improper
operation.
(6) Batteries--for improper installation and improper charge.
(7) All systems--for improper installation, poor general condition,
apparent and obvious defects, and insecurity of attachment.
(d) Each person performing an annual or 100-hour inspection shall inspect
(where applicable) components of the engine and nacelle group as follows:
(1) Engine section--for visual evidence of excessive oil, fuel, or
hydraulic leaks, and sources of such leaks.
(2) Studs and nuts--for improper torquing and obvious defects.
(3) Internal engine--for cylinder compression and for metal particles or
foreign matter on screens and sump drain plugs. If there is weak cylinder
compression, for improper internal condition and improper internal
tolerances.
(4) Engine mount--for cracks, looseness of mounting, and looseness of
engine to mount.
(5) Flexible vibration dampeners--for poor condition and deterioration.
(6) Engine controls--for defects, improper travel, and improper safetying.
(7) Lines, hoses, and clamps--for leaks, improper condition and looseness.
(8) Exhaust stacks--for cracks, defects, and improper attachment.
(9) Accessories--for apparent defects in security of mounting.
(10) All systems--for improper installation, poor general condition,
defects, and insecure attachment.
(11) Cowling--for cracks, and defects.
(e) Each person performing an annual or 100-hour inspection shall inspect
(where applicable) the following components of the landing gear group:
(1) All units--for poor condition and insecurity of attachment.
(2) Shock absorbing devices--for improper oleo fluid level.
(3) Linkages, trusses, and members--for undue or excessive wear fatigue,
and distortion.
(4) Retracting and locking mechanism--for improper operation.
(5) Hydraulic lines--for leakage.
(6) Electrical system--for chafing and improper operation of switches.
(7) Wheels--for cracks, defects, and condition of bearings.
(8) Tires--for wear and cuts.
(9) Brakes--for improper adjustment.
(10) Floats and skis--for insecure attachment and obvious or apparent
defects.
(f) Each person performing an annual or 100-hour inspection shall inspect
(where applicable) all components of the wing and center section assembly for
poor general condition, fabric or skin deterioration, distortion, evidence of
failure, and insecurity of attachment.
(g) Each person performing an annual or 100-hour inspection shall inspect
(where applicable) all components and systems that make up the complete
empennage assembly for poor general condition, fabric or skin deterioration,
distortion, evidence of failure, insecure attachment, improper component
installation, and improper component operation.
(h) Each person performing an annual or 100-hour inspection shall inspect
(where applicable) the following components of the propeller group:
(1) Propeller assembly--for cracks, nicks, binds, and oil leakage.
(2) Bolts--for improper torquing and lack of safetying.
(3) Anti-icing devices--for improper operations and obvious defects.
(4) Control mechanisms--for improper operation, insecure mounting, and
restricted travel.
(i) Each person performing an annual or 100-hour inspection shall inspect
(where applicable) the following components of the radio group:
(1) Radio and electronic equipment--for improper installation and insecure
mounting.
(2) Wiring and conduits--for improper routing, insecure mounting, and
obvious defects.
(3) Bonding and shielding--for improper installation and poor condition.
(4) Antenna including trailing antenna--for poor condition, insecure
mounting, and improper operation.
(j) Each person performing an annual or 100-hour inspection shall inspect
(where applicable) each installed miscellaneous item that is not otherwise
covered by this listing for improper installation and improper operation.
Appendix E--Altimeter System Test and Inspection
Each person performing the altimeter system tests and inspections required
by Sec. 91.411 shall comply with the following:
(a) Static pressure system:
(1) Ensure freedom from entrapped moisture and restrictions.
(2) Determine that leakage is within the tolerances established in Sec.
23.1325 or Sec. 25.1325, whichever is applicable.
(3) Determine that the static port heater, if installed, is operative.
(4) Ensure that no alterations or deformations of the airframe surface have
been made that would affect the relationship between air pressure in the
static pressure system and true ambient static air pressure for any flight
condition.
(b) Altimeter:
(1) Test by an appropriately rated repair facility in accordance with the
following subparagraphs. Unless otherwise specified, each test for
performance may be conducted with the instrument subjected to vibration. When
tests are conducted with the temperature substantially different from ambient
temperature of approximately 25 degrees C., allowance shall be made for the
variation from the specified condition.
(i) Scale error. With the barometric pressure scale at 29.92 inches of
mercury, the altimeter shall be subjected successively to pressures
corresponding to the altitude specified in Table I up to the maximum normally
expected operating altitude of the airplane in which the altimeter is to be
installed. The reduction in pressure shall be made at a rate not in excess of
20,000 feet per minute to within approximately 2,000 feet of the test point.
The test point shall be approached at a rate compatible with the test
equipment. The altimeter shall be kept at the pressure corresponding to each
test point for at least 1 minute, but not more than 10 minutes, before a
reading is taken. The error at all test points must not exceed the tolerances
specified in Table I.
(ii) Hysteresis. The hysteresis test shall begin not more than 15 minutes
after the altimeter's initial exposure to the pressure corresponding to the
upper limit of the scale error test prescribed in subparagraph (i); and while
the altimeter is at this pressure, the hysteresis test shall commence.
Pressure shall be increased at a rate simulating a descent in altitude at the
rate of 5,000 to 20,000 feet per minute until within 3,000 feet of the first
test point (50 percent of maximum altitude). The test point shall then be
approached at a rate of approximately 3,000 feet per minute. The altimeter
shall be kept at this pressure for at least 5 minutes, but not more than 15
minutes, before the test reading is taken. After the reading has been taken,
the pressure shall be increased further, in the same manner as before, until
the pressure corresponding to the second test point (40 percent of maximum
altitude) is reached. The altimeter shall be kept at this pressure for at
least 1 minute, but not more than 10 minutes, before the test reading is
taken. After the reading has been taken, the pressure shall be increased
further, in the same manner as before, until atmospheric pressure is reached.
The reading of the altimeter at either of the two test points shall not
differ by more than the tolerance specified in Table II from the reading of
the altimeter for the corresponding altitude recorded during the scale error
test prescribed in paragraph (b)(i).
(iii) After effect. Not more than 5 minutes after the completion of the
hysteresis test prescribed in paragraph (b)(ii), the reading of the altimeter
(corrected for any change in atmospheric pressure) shall not differ from the
original atmospheric pressure reading by more than the tolerance specified in
Table II.
(iv) Friction. The altimeter shall be subjected to a steady rate of
decrease of pressure approximating 750 feet per minute. At each altitude
listed in Table III, the change in reading of the pointers after vibration
shall not exceed the corresponding tolerance listed in Table III.
(v) Case leak. The leakage of the altimeter case, when the pressure within
it corresponds to an altitude of 18,000 feet, shall not change the altimeter
reading by more than the tolerance shown in Table II during an interval of 1
minute.
(vi) Barometric scale error. At constant atmospheric pressure, the
barometric pressure scale shall be set at each of the pressures (falling
within its range of adjustment) that are listed in Table IV, and shall cause
the pointer to indicate the equivalent altitude difference shown in Table IV
with a tolerance of 25 feet.
(2) Altimeters which are the air data computer type with associated
computing systems, or which incorporate air data correction internally, may
be tested in a manner and to specifications developed by the manufacturer
which are acceptable to the Administrator.
(c) Automatic Pressure Altitude Reporting Equipment and ATC Transponder
System Integration Test. The test must be conducted by an appropriately rated
person under the conditions specified in paragraph (a). Measure the automatic
pressure altitude at the output of the installed ATC transponder when
interrogated on Mode C at a sufficient number of test points to ensure that
the altitude reporting equipment, altimeters, and ATC transponders perform
their intended functions as installed in the aircraft. The difference between
the automatic reporting output and the altitude displayed at the altimeter
shall not exceed 125 feet.
(d) Records: Comply with the provisions of Sec. 43.9 of this chapter as to
content, form, and disposition of the records. The person performing the
altimeter tests shall record on the altimeter the date and maximum altitude
to which the altimeter has been tested and the persons approving the airplane
for return to service shall enter that data in the airplane log or other
permanent record.
Table I
Equivalent
pressure
(inches of Tolerance
Altitude mercury) +/-(feet)
Case Leak Test +/-100
Hysteresis Test:
First Test Point (50 percent of maximum altitude) 75
Second Test Point (40 percent of maximum altitude) 75
After Effect Test 30
(Secs. 313, 314, and 601 through 610 of the Federal Aviation Act of 1958 (49
U.S.C. 1354, 1355, and 1421 through 1430) and sec. 6(c), Dept. of
Transportation Act (49 U.S.C. 1655(c)))
[Amdt. 43-2, 30 FR 8262, June 29, 1965, as amended by Amdt. 43-7, 32 FR 7587,
May 24, 1967; Amdt. 43-19, 43 FR 22639, May 25, 1978; Amdt. 43-23, 47 FR
41086, Sept. 16, 1982; Amdt. 43-31, 54 FR 34330, Aug. 18, 1989]
Effective Date Note: At 54 FR 34330, Aug. 18, 1989, Appendix E, Part 43 was
amended by changing the cross reference "Sec. 91.173" to "Sec. 91.411" in the
introductory paragraph, effective August 18, 1990.
Appendix F--ATC Transponder Tests and Inspections
The ATC transponder tests required by Sec. 91.413 of this chapter may be
conducted using a bench check or portable test equipment and must meet the
requirements prescribed in paragraphs (a) through (j) of this appendix. If
portable test equipment with appropriate coupling to the aircraft antenna
system is used, operate the test equipment for ATCRBS transponders at a
nominal rate of 235 interrogations per second to avoid possible ATCRBS
interference. Operate the test equipment at a nominal rate of 50 Mode S
interrogations per second for Mode S. An additional 3 dB loss is allowed to
compensate for antenna coupling errors during receiver sensitivity
measurements conducted in accordance with paragraph (c)(1) when using
portable test equipment.
(a) Radio Reply Frequency:
(1) For all classes of ATCRBS transponders, interrogate the transponder and
verify that the reply frequency is 1090+/-3 Megahertz (MHz).
(2) For classes 1B, 2B, and 3B Mode S transponders, interrogate the
transponder and verify that the reply frequency is 1090+/-3 MHz.
(3) For classes 1B, 2B, and 3B Mode S transponders that incorporate the
optional 1090+/-1 MHz reply frequency, interrogate the transponder and verify
that the reply frequency 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, and 3B Mode S transponders are interrogated Mode 3/A at an interrogation
rate between 230 and 1,000 interrogations per second; or when Classes 1A and
2A ATCRBS Transponders, or Classes 1B, 2A, 3A, and 4 Mode S transponders are
interrogated at a rate between 230 and 1,200 Mode 3/A interrogations per
second:
(1) Verify that the transponder does not respond to more than 1 percent of
ATCRBS interrogations when the amplitude of P2 pulse is equal to the P1
pulse.
(2) Verify that the transponder replies to at least 90 percent of ATCRBS
interrogations when the amplitude of the P2 pulse is 9 dB less than the P1
pulse. If the test is conducted with a radiated test signal, the
interrogation rate shall be 235+/-5 interrogations per second unless a higher
rate has been approved for the test equipment used at that location.
(c) Receiver Sensitivity:
(1) Verify that for any class of ATCRBS Transponder, the receiver minimum
triggering level (MTL) of the system is -73+/-4 dbm, or that for any class of
Mode S transponder the receiver MTL for Mode S format (P6 type)
interrogations is -74+/-3 dbm by use of a test set either:
(i) Connected to the antenna end of the transmission line;
(ii) Connected to the antenna terminal of the transponder with a correction
for transmission line loss; or
(iii) Utilized radiated signal.
(2) Verify that the difference in Mode 3/A and Mode C receiver sensitivity
does not exceed 1 db for either any class of ATCRBS transponder or any class
of Mode S transponder.
(d) Radio Frequency (RF) Peak Output Power:
(1) Verify that the transponder RF output power is within specifications
for the class of transponder. Use the same conditions as described in (c)(1)
(i), (ii), and (iii) above.
(i) For Class 1A and 2A ATCRBS transponders, verify that the minimum RF
peak output power is at least 21.0 dbw (125 watts).
(ii) For Class 1B and 2B ATCRBS Transponders, verify that the minimum RF
peak output power is at least 18.5 dbw (70 watts).
(iii) For Class 1A, 2A, 3A, and 4 and those Class 1B, 2B, and 3B Mode S
transponders that include the optional high RF peak output power, verify that
the minimum RF peak output power is at least 21.0 dbw (125 watts).
(iv) For Classes 1B, 2B, and 3B Mode S transponders, verify that the
minimum RF peak output power is at least 18.5 dbw (70 watts).
(v) For any class of ATCRBS or any class of Mode S transponders, verify
that the maximum RF peak output power does not exceed 27.0 dbw (500 watts).
Note: The tests in (e) through (j) apply only to Mode S transponders.
(e) Mode S Diversity Transmission Channel Isolation: For any class of Mode
S transponder that incorporates diversity operation, verify that the RF peak
output power transmitted from the selected antenna exceeds the power
transmitted from the nonselected antenna by at least 20 db.
(f) Mode S Address: Interrogate the Mode S transponder and verify that it
replies only to its assigned address. Use the correct address and at least
two incorrect addresses. The interrogations should be made at a nominal rate
of 50 interrogations per second.
(g) Mode S Formats: Interrogate the Mode S transponder with uplink formats
(UF) for which it is equipped and verify that the replies are made in the
correct format. Use the surveillance formats UF=4 and 5. Verify that the
altitude reported in the replies to UF=4 are the same as that reported in a
valid ATCRBS Mode C reply. Verify that the identity reported in the replies
to UF=5 are the same as that reported in a valid ATCRBS Mode 3/A reply. If
the transponder is so equipped, use the communication formats UF=20, 21, and
24.
(h) Mode S All-Call Interrogations: Interrogate the Mode S transponder with
the Mode S-only all-call format UF=11, and the ATCRBS/Mode S all-call formats
(1.6 microsecond P4 pulse) and verify that the correct address and capability
are reported in the replies (downlink format DF=11).
(i) ATCRBS-Only All-Call Interrogation: Interrogate the Mode S transponder
with the ATCRBS-only all-call interrogation (0.8 microsecond P4 pulse) and
verify that no reply is generated.
(j) Squitter: Verify that the Mode S transponder generates a correct
squitter approximately once per second.
(k) Records: Comply with the provisions of Sec. 43.9 of this chapter as to
content, form, and disposition of the records.
[Amdt. 43-26, 52 FR 3390, Feb. 3, 1987; 52 FR 6651, Mar. 4, 1987, as amended
by Amdt. 43-31, 54 FR 34330, Aug. 18, 1989]
Effective Date Note: At 54 FR 34330, Aug. 18, 1989, Appendix F, Part 43 was
amended by changing the cross reference "Sec. 91.172" to "Sec. 91.413" in the
introductory paragraph, effective August 18, 1990.
