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pilot intends to use to go from one to the other. IT IS THE
RESPONSIBILITY OF THE PILOT TO RESOLVE THESE
DISCONTINUITIES AND EDIT THE FLIGHT PLAN TO ELIMINATE
ANY *NO LINK*s. The pilot may manually eliminate the *NO LINK*
using FPL editing techniques, or go "Direct To" another waypoint
after the *NO LINK* in order to maintain a continuous flight plan
sequence.
NEXT LEG INVALID Message
If a GAP or *NO LINK* exists in the flight plan and is not edited out
by the pilot, the message "NEXT LEG INVALID" will occur whenever
the GAP or *NO LINK* sequences into the NX position (i.e., it
becomes the next waypoint after the current TO waypoint). If it is
not eliminated, the FMS will continue to fly on last heading (0° roll
steering command) upon passing the TO waypoint and will issue the
message CURRENT LEG EXTENDED.
Section V
Operations
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Change 1
Duplication of Waypoints in the Flight Plan
Sometimes a SID or STAR procedure may duplicate existing
waypoints when linked into a flight plan. For instance, if the flight
plan were generated on J-45 from STL to Atlanta KATL, the
waypoints LAJUG, Nashville (BNA) and Atlanta (ATL) would be
inserted automatically at the end. The flight plan would read:
5 ....
6 LAJUG
7 BNA
8 ATL
9 KATL
When the ROME 6 Arrival with Nashville transition is linked into the
flight plan between the last waypoint and the destination airport,
BNA and ATL will be repeated, since they are part of the STAR. A
NO LINK will be inserted between ATL and BNA since they don't
logically link. The flight plan would now read:
6 LAJUG ↑
7 BNA Original flight plan
8 ATL ↓
9 *NO LINK*
10 BNA ↑
11 DRAKK
12 NEUTO These are the
13 RMG ROME 6
14 ERLIN Arrival waypoints
15 DALAS
16 ATL ↓
17 KATL
Section V
Operations
2423sv602 5-79
Change 1
The redundant waypoints and NO LINK (Items 7, 8 and 9) must be
edited out of the flight plan before reaching BNA or else the aircraft
will sequence directly from BNA to ATL instead of navigating the
ROME 6 Arrival. The cursor should be placed over Item 7 BNA and
the number "10" entered and ENTER key pressed. This procedure
will then "close up" the flight plan which will now read correctly as
follows:
6 LAJUG
7 BNA
8 DRAKK
9 NEUTO
10 RMG
11 ERLIN
12 DALAS
13 ATL
14 KATL
ANY TIME A SID, STAR OR APPROACH IS LINKED INTO THE
FLIGHT PLAN, THE PILOT SHOULD REVIEW THE RESULTING
FLIGHT PLAN TO VERIFY THAT IT IS CONTINUOUS WITH NO
GAPS OR DUPLICATED WAYPOINTS, AND THAT IT
CONFORMS TO THE INTENDED PATH OF FLIGHT.
Section V
Operations
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Change 1
Approaches - General
The following section describes the aspects of operation of the FMS,
which are common to all approach operations, without regard to the
type of navigation sensor upon which the approach guidance is
predicated.
Later portions of this section provide details specific to certain
approach types, e.g., ILS, VOR or GPS approaches, as well as
certain exceptions to the general comments made here.
NOTE: All approach modes must use QNH altitude and not QFE.
Each altitude type is defined as follows:
QNH - Used in all FMS approach modes. This is the
altitude above sea level based on local station pressure
(i.e. MSL altitude).
QFE - Do Not Use. This is the height above airport
elevation (or runway threshold elevation) based on local
station pressure.
The FMS is approved for a variety of approaches. The approach
capabilities of a specific installation depends on the installed sensor
suite and the interfaced aircraft flight guidance system. The
approved approaches can include the following:
ILS (FMS defined ILS guided)
LOC
LOC-BC
VOR
VOR-DME
TACAN
RNAV
GPS Overlay NDB)
GPS (Stand-alone approaches)
VFR
The configuration module contains the list of approach types that are
permitted for the specific installation. Approaches, which are not on
the configuration list, can not be selected.
Section V
Operations
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Change 1
HSI Course Deviation Indicator
The discussion below describes the scale sensitivities for analog
instruments. The Operator’s Manual or Technical Manual for the
EFIS equipment should be consulted to determine the display
sensitivity for these instruments.
Enroute Mode:
EFIS Display: 5.0 nm F.S.
CDU Display: XTK (E)
NAV TO Leg = Missed Appr:
　
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