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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 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
considered equivalent to "FAA-approved".)
Note 3:
Life limitations are provided in the A319/A320/A321 Maintenance Planning Document, Section 9 “Airworthiness
Limitation Section”, Sub-Sections 9-1-2 and 9-1-3 - Approved by DGAC.
Note 4:
The A321 basic definition for U.S. import certification is contained in the following documents:
- 00E000A0010/C11 for A321-111 model
- 00E000A0011/C11 for A321-112 model
- 00E000A0012/C11 for A321-131 model
- AI/EA-S 413.3365/96 (supplement) for A321-111/112/131 models
- AI/EA-S 413.0401/97 for A321-211 model
- AI/EA-S 413.0399/97 for A321-231 model.
Note 5:
Maintenance criteria to comply with certification requirements for systems are given in Airbus Document AI/ST4/955.061/89
“Certification Maintenance Requirements (FAA version)” (CMR).
Maintenance criteria to comply with certification requirements for structure are given in Airbus Document AI/SEM4/
95A.0252/96 “Airworthiness Limitation Items”.
Note 6:
Door 2 and/or Door 3 may be derated to Type III.
Note 7:
If modifications 24173 and 22853 are embodied on models with IAE engines, the aircraft is qualified for Cat II precision
approach. This does not constitute operational approval.
A28NM Page 20 of 22
Note 8:
If modification 24064 is embodied on models with CFM engines, the aircraft is qualified for Cat III precision approach. This
does not constitute operational approval.
Note 9:
If modification 24066 is embodied on models with IAE engines, the aircraft is qualified for Cat III precision approach. This does
not constitute operational approval.
Note 10:
If modification 25199 is embodied on models with CFM engines, the aircraft is qualified for Cat III B precision approach. This
does not constitute operational approval.
Note 11:
If modification 25200 is embodied on models with IAE engines, the aircraft is qualified for Cat III B precision approach. This
does not constitute operational approval.
Note 12:
If FWC Standard D2 and FAC standard BAM 0510 are fitted on A321 aircraft, VFE speed in configuration 2 is increased from
205kts to 215kts (as identified by speed limitation placard installed by modification 24641).
Note 13:
Modifications 25302 (for IAE engine) and 25303 (for CFM engine) are part of the FAA Type Design, and shall be implemented
on any A321 aircraft entered on the U.S. register, before the individual U.S. standard Certificate of Airworthiness be issued.
Note 14:
If modification 25800 is embodied on models with CFM56-5B engines, the engine performance is improved. The engine
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