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under FAR Section 21.29 exported from countries other than the country manufacture (e.g., third party country) is FAR Sections
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. Special Federal Aviation Regulation (SFAR) No.27 effective February 1, 1974, including Amendments 27-1 through
27-5.
c. Part 36 of the FAR effective December 1, 1969, including Amendments 36-1 through 36-12.
d. 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.
(2) June 9, 1989:
- Computerized Airplane Flight Manual
e. 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.
f. The following paragraphs of the FAR have been complied with through equivalent safety demonstrations:
- 25.783(e) for cargo doors
- 25.783(f) for passenger doors and bulk cargo door
- 25.813(c) for emergency exit access
- 25.811(e)(3) Type III emergency exit marking.
g. 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.
A28NM Page 13 of 22
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 26.959. (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
defined in FAR Part 25.959. This "unusable" fuel is included in System Fuel as indicated in paragraph d. above, and need not be
accounted for separately.
f. System oil is the weight of all remaining in the engine, constant speed drive, lines, and tanks after subtracting the oil in the
tanks which is above the standpipe (zero gauge) levels. The engine oil capacities shown elsewhere in this data sheet include only
the usable oil for which the tanks must be placarded.
Note 2:
The aircraft must be operated in accordance with the DGAC-approved FAA Airplane Flight Manual. ("DGAC-approved" is
　
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