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“With the Fowler/Bowers Holematic
Mark II gage, all anyone using the
instrument has to do is insert the probe
into the bore, squeeze the trigger, and
get the reading quickly.”
The pistol-grip gage has a resolution
of 0.00005 in and a large, easy-toread
LCD swivel display as well as two
pre-set memories. Heads above 0.5-in
diameter are fitted with tungsten-carbide
measuring anvils. Special anvils are
used for threads, splines, and slots.
As part of its efforts to improve
inspection efficiency, Schweizer is
moving into use of coordinate measuring
machines and has upgraded its
tooling with the addition of highaccuracy
Sumitomo drills, according to
Rick Kent, Schweizer Production
Manager. He said the company
recently has added a portable articulating
arm to measure airframes.
Kent said gage calibration is carried
out at least every six months.
Patrick Ponticel
A Fowler/Bowers
pistol-grip bore
gage is used to
check a Schweizer
Aircraft Corp.
helicopter idler
pulley.
Airbus Automatics
FMGS The Flight Management, Guidance and Envelope System (1.22.10 p1) is pilot interactive (honest) and contains the following units: 2 FMGC,
3 MCDU, 1 FCU and 1 FM source set. There are 2 other crew interfaces, the thrust levers and the EFIs.
FMGC The Flight management Guidance and Envelope Computer has 4 main parts:
1. The FM part controlling navigation, flight planning, performance, NavRad, and display driving.
2. The FG part controlling AP command, FD command and Auto-thrust command.
3. The FE part controlling speed envelope, monitoring FG/FE parameters, windshear and aft cg detection and computation of GW and CG
info.
4. The FIDS part providing maintenance data functions and interface with the CMC.
Each FMGC has its own database containing 2 fields; one unmodifiable core of performance and navigation data and one pilot created
navigation data, which may include 20 waypoints, 20 navaids, 10 runways and 5 routes. The main database is updated every 28 days.
The FMGC is the basic means for navaid tuning: normally navaids being auto-tuned by the FMGC (each FMGC controlling its onside
receivers), however pilots can manually tune navaids through the MCDU for visual display.
MCDU The MCDU is the long term interface between the FMGC and the pilot and allows:
1. Definition of an overall Flt Plan. 2. Display, selection and modification of flight management info.
3. Selection of specific FM functions. 4. Peripheral data display, inc ACARS.
5. Back-up navigation.
Pilot entries and modifiable data are displayed in large font.
FCU The FCU is the short term interface between the FMGC and the pilot and allows:
1. Engagement of the AP and A/THR.
2. Selection of the required guidance modes.
3. Selection and display of manual guidance targets.
FM source set This selector allows switching of the FMGC data to the offside MCDU and EFIs display in case of one FM failure. MCDU 3 is not able
to operate as Back Up Nav even when it replaces MCDU 1 or 2. The BUN mode is only accessible on the MCDU MENU page if the FM source is set
to NORM position
FD Roll, pitch and yaw bars are only in view at the same time during align. Below 30ft during TO or landing when a localiser is available, the
vertical bar is replaced by a yaw bar index. The FDs are auto-engaged at FMGC power up on the ground or in flight. On the ground, 1FD2 is
displayed on PFD, no FD bars in view and FCU windows are dashed: directions are displayed when a mode is active. If 1 FMGC is not valid, the
remaining FD is displayed on both PFDs. FDs are occulted when aircraft pitch or roll limits are reached or when ROLL OUT mode is engaged. FD
bars flash for 10 secs when ALT* mode is lost after 250ft change to FCU altitude or when in APPR mode FD reverts to VS. FD bars flash
permanently when reception of glideslope data is lost above 100ft RA. The roll FD bar flash for 10secs when FD reverts to HDG mode in APPR or 1
AP/FD is engaged while both AP/FD were previously off. The roll bars flash permanently when reception of the localiser data is lost above 15ft RA.
AutoFlight
Modes There are four possible modes of operation: 1: normal/dual mode, 2: degraded/independent mode, 3: degraded/single mode
and 4: degraded/back-up navigation mode:
1. DUAL Both FMGCs are synchronised, achieve their own computations and exchange data through a crosstalk bus. One FMGC is autoselected
as master. 3 MCDUs are supplied; #1 and #2 act with each FMGC, #3 acts as a spare and monitors ACMS, CMS, etc. Both
MCDUs act independently but entries can be made from either and are auto-transmitted to the other and applied to both FMGCs.
2. INDEPENDENT If a mismatch occurs, the system auto-degrades and cannot be corrected by resynchronisation. Each FMGC works
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