2.
Cockpit doors jettison and cabin doors open prior to entering water.
3.
Cyclic -Position in direction of roll.
4.
Exit when main rotor has stopped.
9.29 FLIGHT CONTROL/MAIN-ROTOR SYSTEM MALFUNCTIONS.
a. Failure of components within the .ight control sys-tem may be indicated through varying degrees of feedback, binding, resistance, or sloppiness. These conditions should not be mistaken for malfunction of the AFCS.
TM 1-1520-253-10
b. Failure of a main rotor component may be indicated by the sudden onset or steady increase in main rotor vibra-tion or unusual noise. Severe changes in lift characteristics and/or balance condition can occur due to blade strikes, skin separation, shift or loss of balance weights or other material. Malfunctions may result in severe main rotor .ap-ping. The severity of vibrations may be minimized by re-ducing airspeed.
If the main rotor system malfunctions:
Danger exists that the main rotor system could collapse or separate from the air-craft after landing. Exit when main rotor has stopped.
1.
LAND AS SOON AS POSSIBLE.
2. EMER ENG(S) SHUTDOWN after landing.
9.29.1 SAS Failure With No Failure Advisory Indi-cation. Erratic electrical input to a SAS actuator can re-sult in moderate rotor tip path oscillations that are often accompanied with pounding sounds or 9knocking9 which may be felt in the cyclic or pedal controls. No SAS mal-function, however, can physically drive the pilots’ .ight controls. Failure of SAS 2 is usually but not necessarily followed by a failure/advisory indication. Failure of a SAS 1 component will not be accompanied by a failure/advisory indication as SAS 1 does not contain diagnostic capabili-ties.
If the helicopter experiences erratic motion of the rotor tip path without failure/advisory indication:
1. SAS 1 switch -Off.
If condition persists:
2. SAS 1 switch -ON.
3.
SAS 2 switch -Off.
If malfunction still persists:
4. SAS 1 and FPS switches -Off.
9.29.2 SAS 2 Failure Advisory Light On.
POWER ON RESET switches -Simulta-neously press and then release.
9.29.3 SAS OFF Caution Legend On.
FPS switch -Off.
9.29.4 FLT PATH STAB Caution Legend On. An FPS malfunction will be detected by the SAS/FPS com-puter, which will disengage FPS function in the applicable axis and light the FLT PATH STAB caution legend and corresponding FAILURE ADVISORY light.
1. POWER ON RESET switches -Simulta-neously press and then release.
If failure returns, control affected axis manually.
If the airspeed fault advisory light is illu-minated, continued .ight above 70 KIAS with the stabilator in the AUTO MODE is unsafe since a loss of the airspeed signal from the remaining airspeed sensor would result in the stabilator slewing full-down.
If the airspeed fault light remains illuminated on the AFCS panel:
NOTE
Use of the cyclic mounted stabilator slew-up switch should be announced to the crew to minimize cockpit confusion.
2.
Manually slew stabilator -Adjust to 0° if above 40 KIAS. The preferred method of manually slewing the stabilator up is to use the cyclic mounted stabilator slew-up switch.
3.
LAND AS SOON AS PRACTICABLE.
9.29.5 Pitch, Roll or Yaw/Trim Hardover.
a. A pitch FPS/trim hardover will cause a change in pitch attitude and a corresponding longitudinal cyclic movement of about 1/2 inch. This condition will be de-tected by the SAS/FPS computer which will disengage FPS and trim functions in the pitch axis and light the FLT PATH STAB and TRIM FAIL caution legends.
Change 3 9-19
TM 1-1520-253-10
b.
A roll FPS/trim hardover will be characterized by a 1/2 inch lateral stick displacement, resulting in a corre-sponding roll rate and a constant heading sideslip condi-tion, caused by the yaw FPS attempting to maintain head-ing. The SAS/FPS computer will detect the hardover condition and disengage lateral trim and illuminate the FLT PATH STAB and TRIM FAIL caution legends.
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