Learjet 35A - Page 184

FAA APPROVED 4-30-76 3-39
REISSUED 2-25-81, CHANGE 13
PITCH AXIS MALFUNCTION (CONT)
4. STALL WARNING Switches — OFF.
5. PITCH TRIM Switch (pedestal) — OFF.
6. AUTOPILOT Switch — OFF.
7. Control Wheel Master Switch (MSW) — Release.
8. Yaw Damper (PRI or SEC) — Engage.
If flight conditions permit, isolate malfunction as follows:
9. Pitch Trim System: PITCH TRIM Switch (pedestal) — Operate to
PRI then SEC to isolate malfunctioning trim system.
•If malfunction recurs in PRI pitch trim:
a. PITCH TRIM Switch (pedestal) — SEC.
b. NOSE DN-NOSE UP Switch (pedestal) — Operate to retrim
aircraft as required.
c. PITCH TRIM Circuit Breaker (pilot’s ess bus) — Pull.
Mach trim will be inoperative. If autopilot is not en-
gaged, Do not exceed M
MO (0.74 MI).
•If malfunction recurs in SEC pitch trim:
a. PITCH TRIM Switch (pedestal) — PRI.
b. Control Wheel Trim Switch — Operate to retrim aircraft as
required.
c. SEC PITCH TRIM Circuit Breaker (copilot’s ess bus) — Pull.
Autopilot trim will be inoperative. If Mach trim has been
disabled also, Do not exceed M
MO (0.74 MI).
•If malfunction does not recur:
a. PITCH TRIM Switch (pedestal) — PRI or SEC as desired.
b. Maintain aircraft trim with selected trim system.
Probable cause of malfunction was autopilot (if autopilot
was engaged). Do not engage autopilot.
•If neither PRI nor SEC pitch trim can be restored, refer to
JAMMED STABILIZER LANDING, Section IV.
NOTE
NOTE
NOTE
, CHANGE
13
FAA APPROVED 4-30-76 3-39
REISSUED 2-25-81, CHANGE 13
PITCH AXIS MALFUNCTION (CONT)
4. STALL WARNING Switches — OFF.
5. PITCH TRIM Switch (pedestal) — OFF.
6. AUTOPILOT Switch — OFF.
7. Control Wheel Master Switch (MSW) — Release.
8. Yaw Damper (PRI or SEC) — Engage.
If flight conditions permit, isolate malfunction as follows:
9. Pitch Trim System: PITCH TRIM Switch (pedestal) — Operate to
PRI then SEC to isolate malfunctioning trim system.
•If malfunction recurs in PRI pitch trim:
a. PITCH TRIM Switch (pedestal) — SEC.
b. NOSE DN-NOSE UP Switch (pedestal) — Operate to retrim
aircraft as required.
c. PITCH TRIM Circuit Breaker (pilot’s ess bus) — Pull.
Mach trim will be inoperative. If autopilot is not en-
gaged, Do not exceed M
MO (0.74 MI).
•If malfunction recurs in SEC pitch trim:
a. PITCH TRIM Switch (pedestal) — PRI.
b. Control Wheel Trim Switch — Operate to retrim aircraft as
required.
c. SEC PITCH TRIM Circuit Breaker (copilot’s ess bus) — Pull.
Autopilot trim will be inoperative. If Mach trim has been
disabled also, Do not exceed M
MO (0.74 MI).
•If malfunction does not recur:
a. PITCH TRIM Switch (pedestal) — PRI or SEC as desired.
b. Maintain aircraft trim with selected trim system.
Probable cause of malfunction was autopilot (if autopilot
was engaged). Do not engage autopilot.
•If neither PRI nor SEC pitch trim can be restored, refer to
JAMMED STABILIZER LANDING, Section IV.
NOTE
NOTE
NOTE
, CHANGE
13
llilill Rlanual
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