Pt. 91, App. A

14 CFR Ch. I (1-1-19 Edition)

altitude for the use of the autopilot, instrument and equipment failure warning systems, instrument failure, and other procedures, instructions, and limitations that
may be found necessary by the Administrator.

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2. Required Instruments and Equipment
The instruments and equipment listed in
this section must be installed in each aircraft operated in a Category II operation.
This section does not require duplication of
instruments and equipment required by
Section 91.205 or any other provisions of this chapter.
(a) Group I. (1) Two localizer and glide
slope receiving systems. Each system must
provide a basic ILS display and each side of
the instrument panel must have a basic ILS
display. However, a single localizer antenna
and a single glide slope antenna may be used.
(2) A communications system that does not
affect the operation of at least one of the
ILS systems.
(3) A marker beacon receiver that provides
distinctive aural and visual indications of
the outer and the middle markers.
(4) Two gyroscopic pitch and bank indicating systems.
(5) Two gyroscopic direction indicating
systems.
(6) Two airspeed indicators.
(7) Two sensitive altimeters adjustable for
barometric pressure, each having a placarded
correction for altimeter scale error and for
the wheel height of the aircraft. After June
26, 1979, two sensitive altimeters adjustable
for barometric pressure, having markings at
20-foot intervals and each having a placarded
correction for altimeter scale error and for
the wheel height of the aircraft.
(8) Two vertical speed indicators.
(9) A flight control guidance system that
consists of either an automatic approach
coupler or a flight director system. A flight
director system must display computed information as steering command in relation
to an ILS localizer and, on the same instrument, either computed information as pitch
command in relation to an ILS glide slope or
basic ILS glide slope information. An automatic approach coupler must provide at
least automatic steering in relation to an
ILS localizer. The flight control guidance
system may be operated from one of the receiving systems required by subparagraph (1)
of this paragraph.
(10) For Category II operations with decision heights below 150 feet either a marker
beacon receiver providing aural and visual
indications of the inner marker or a radio altimeter.
(b) Group II. (1) Warning systems for immediate detection by the pilot of system faults
in items (1), (4), (5), and (9) of Group I and, if
installed for use in Category III operations,
the radio altimeter and autothrottle system.

(2) Dual controls.
(3) An externally vented static pressure
system with an alternate static pressure
source.
(4) A windshield wiper or equivalent means
of providing adequate cockpit visibility for a
safe visual transition by either pilot to
touchdown and rollout.
(5) A heat source for each airspeed system
pitot tube installed or an equivalent means
of preventing malfunctioning due to icing of
the pitot system.
3. Instruments and Equipment Approval
(a) General. The instruments and equipment required by section 2 of this appendix
must be approved as provided in this section
before being used in Category II operations.
Before presenting an aircraft for approval of
the instruments and equipment, it must be
shown that since the beginning of the 12th
calendar month before the date of submission - 
(1) The ILS localizer and glide slope equipment were bench checked according to the
manufacturer-s instructions and found to
meet those standards specified in RTCA
Paper 23-63/DO-117 dated March 14, 1963,
 - Standard Adjustment Criteria for Airborne
Localizer and Glide Slope Receivers, -  which
may be obtained from the RTCA Secretariat,
1425 K St., NW., Washington, DC 20005.
(2) The altimeters and the static pressure
systems were tested and inspected in accordance with appendix E to part 43 of this chapter; and
(3) All other instruments and items of
equipment specified in section 2(a) of this appendix that are listed in the proposed maintenance program were bench checked and
found to meet the manufacturer-s specifications.
(b) Flight control guidance system. All components of the flight control guidance system must be approved as installed by the
evaluation program specified in paragraph
(e) of this section if they have not been approved for Category III operations under applicable type or supplemental type certification procedures. In addition, subsequent
changes to make, model, or design of the
components must be approved under this
paragraph. Related systems or devices, such
as the autothrottle and computed missed approach guidance system, must be approved in
the same manner if they are to be used for
Category II operations.
(c) Radio altimeter. A radio altimeter must
meet the performance criteria of this paragraph for original approval and after each
subsequent alteration.
(1) It must display to the flight crew clearly and positively the wheel height of the
main landing gear above the terrain.
(2) It must display wheel height above the
terrain to an accuracy of plus or minus 5 feet

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