402 

14 CFR Ch. I (1–1–19 Edition) 

Pt. 60, App. C 

T

ABLE

C3D—F

UNCTIONS AND

S

UBJECTIVE

T

ESTS

—Continued 

QPS requirements 

Information 

Entry No. 

Motion system (and special 

aerodynamic model) effects 

Simulator level 

Notes 

B C D 

1 ...............

Runway rumble, oleo deflection, ground 

speed, uneven runway, runway and taxi-
way centerline light characteristics: 

Procedure: After the helicopter has been pre- 

set to the takeoff position and then released, 
taxi at various speeds with a smooth runway 
and note the general characteristics of the 
simulated runway rumble effects of oleo de-
flections. Repeat the maneuver with a run-
way roughness of 50%, then with maximum 
roughness. Note the associated motion vi-
brations affected by ground speed and run-
way roughness 

X 

X 

X  If time permits, different gross weights can 

also be selected as this may also affect the 
associated vibrations depending on heli-
copter type. The associated motion effects 
for the above tests should also include an 
assessment of the effects of rolling over 
centerline lights, surface discontinuities of 
uneven runways, and various taxiway char-
acteristics. 

2 ...............

Friction Drag from Skid-type Landing Gear: 

Procedure: Perform a running takeoff or a run-

ning landing and note an increase in a fuse-
lage vibration (as opposed to rotor vibration) 
due to the friction of dragging the skid along 
the surface. This vibration will lessen as the 
ground speed decreases 

X X 

3. ..............

Rotor Out-of-Track and/or Out-of-Balance 

condition: 

Procedure: Select the malfunction or condition 

from the IOS. Start the engine(s) normally 
and check for an abnormal vibration for an 
Out-of-Track condition and check for an ab-
normal vibration for an Out-of-Balance con-
dition 

X 

X 

X 

Does not require becoming airborne. The ab-

normal vibration for Out-of-Track and Out-of- 
Balance conditions should be recognized in 
the frequency range of the inverse of the 
period for each; i.e., 1/P for vertical vibra-
tion, and 1/P for lateral vibration. 

4. ..............

Bumps associated with the landing gear: 

Procedure: Perform a normal take-off paying 

special attention to the bumps that could be 
perceptible due to maximum oleo extension 
after lift-off 

X 

X 

X  When the landing gear is extended or re-

tracted, motion bumps can be felt when the 
gear locks into position. 

5. ..............

Buffet during extension and retraction of 

landing gear: 

Procedure: Operate the landing gear. Check 

that the motion cues of the buffet experi-
enced represent the actual helicopter 

X X X 

6. ..............

Failure of Dynamic Vibration Absorber or 

similar system as appropriate for the hel-
icopter (e.g., droop stop or static stop): 

Procedure: May be accomplished any time the 

rotor is engaged. Select the appropriate fail-
ure at the IOS, note an appropriate increase 
in vibration and check that the vibration in-
tensity and frequency increases with an in-
crease in RPM and an increase in collective 
application 

X X X 

7. ..............

Tail Rotor Drive Failure: 

Procedure: With the engine(s) running and the 

rotor engaged—select the malfunction and 
note the immediate increase of medium fre-
quency vibration 

X 

X 

X  The tail rotor operates in the medium fre-

quency range, normally estimated by multi-
plying the tail rotor gear box ratio by the 
main rotor RPM. The failure can be recog-
nized by an increase in the vibrations in this 
frequency range. 

8. ..............

Touchdown cues for main and nose gear: 

Procedure: Conduct several normal ap-

proaches with various rates of descent. 
Check that the motion cues for the touch-
down bumps for each descent rate are rep-
resentative of the actual helicopter 

X X X 

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