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21.183(d) or 21.185(b). Notwithstanding that FAR section 21.183(d) and 25.185(b) do not specifically address or require
certification by the foreign civil airworthiness authority of the country of manufacture, such certification is the only practical
way for an applicant to show, and the Federal Aviation Administration (FAA) to find conformity to the FAA-approved type
design and condition for safe operation. Additional guidance is contained in FAA advisory Circular 21-23, Airworthiness
Certification of Civil Aircraft, Engines, Propellers, and Related Products Imported into the United States.
Certification Basis:
a. Part 25 of the FAR effective February 1, 1965, including Amendments 25-1 through 25-56 thereto.
b.1 Plus the following sections of Part 25 as amended by amendments 25-1 through:
-25-58 (Section 25.812(e))
-25-63 (Section 25.25 (a)(3))
-25-67 (Section 25.807 (c)(7))
(Applied per FAA derivative aircraft policy – reference FAA order 8110.4A)
b.2 Airbus elected to comply with the following sections of Part FAR 25 through Amendment 86:
25.305(d), 25.321(c)/(d), 25.331(a)/(d), 25.333(a)/(c),25.335(d), 25.341,
25.343 (b)(1)(ii), 25.345(a)/(c), 25.349(b), 25.351(b),25.371, 25.373(a),
25.391(e), 25.427, 25.445(a), 25.571(b)(2)/(b)(3), 25.1517.
b.3 Airbus elected to comply with portions of FAR 25.562, Amendment 64, for the passenger seats only. FAR
paragraphs 25.562(c)(5), (c)(6) do not apply.
c. Part 34 of the FAR effective Sept. 10, 1990, including amendment 34-1.
d. Part 36 of the FAR effective December 1, 1965, including amendments 36-1 through 36-20 thereto.
e. FAA Special Conditions issued for the A320 in accordance with Section 21.16 of the FAR and published in the
Federal Register as follows:
(1) January 27, 1989:
- Electronic Flight Controls
- Active Controls
- Engine Controls and Monitoring
- Protection from Lightning and Unwanted Effects of Radio Frequency
- (RF) Energy
- Flight Characteristics
- Flight Envelope Protection
- Side Stick Controllers
- Flight Recorder
A28NM Page 6 of 22
(2) June 9, 1989:
- Computerized AFM
f. For precision approach and landing, the applicable technical requirements are complemented by AC 120-29 and
AC 120-28c.
For the automatic flight control system, the applicable technical requirements are complemented by AC 20-57A for
automatic landing and by AC 25.1329-1A for cruise.
Use of JAR AWO where applicable to the requirements above, is acceptable.
g. The following paragraphs of the FAR have been complied with through equivalent safety demonstrations:
- 25.101, 25.105, 25.109, 25.113, 25.115, 25.735, for rejected takeoff and landing performance
- 25.783(f) for passenger doors
- 25.807(c) for maximum passenger capacity
- 25.813(a) emergency exit access for a single 13 inch aisle
- 25.933(a), 25.1309(b) for thrust reversing system
- 25.811(e)(3) Type III emergency exit marking.
h. Optional Requirements elected:
- 25.801 for ditching
- 25.1419 for icing
Note 1 - Weight and Balance
a. Current weight and balance report including list of equipment, entitled "Aircraft Inspection Report" included in certificated
empty weight, and loading instructions, must be in each aircraft at the time of original certification and at all times thereafter,
except in the case of operators having an approved weight control system. Airbus report, " Weight and Balance Manual,"
contains loading information for each airplane and interior arrangement configuration as delivered. This report contains, or
refers to, information relative to location of all passengers and crew member seats, location and capacity of all cargo and baggage
compartments, buffets, storage spaces and coat rooms, location and capacity of lounges, lavatories, and the required placards in
the passenger compartment.
b. The airplane must be loaded so that the CG is within specified limits at all times, considering fuel loading usage, gear
retraction and movement of crew and passengers from their assigned positions.
c. The weights of system fuel and oil, as defined below, and hydraulic fluid, all of which must be included in the airplane empty
weight, are listed for each airplane in the Weight and Balance Manual specified in paragraph a. above.
d. System fuel is the weight of all fuel required to fill a lines and tanks up to zero-fuel point on the fuel gauges in the most
critical flight attitude, including the unusable tank fuel as defined by FAR part 25.959. (The usable fuel in the crossfeed
manifold lines, manifolds, and engine that is not part of the system fuel must be included in the total usable fuel to obtain correct
weight and CG for take-off.)
e. The unusable fuel is that amount of fuel in the tanks which is unavailable to the engines under critical flight conditions as
　
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