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 M
I
)
.
•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 M
I
)
.
•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 M
I
)
.
•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 M
I
)
.
•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
Summary of Contents for 35A
Page 26: ...1 8 Center of Gravity Envelope Figure 1 3 FAA APPROVED 4 30 76 REISSUED 2 25 81 ...
Page 47: ...1 24 111 111 INTENTIONAlLY LEFf BlANK FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 12 ...
Page 115: ...2 58 INTENTIONALLY LEFT BLANK FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 12 ...
Page 117: ...2 60 INTENTIONALLY LEFT BlANK FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 12 ...
Page 158: ...INTENIlONAlLY LEFT BlANK FAA APPROVED 4 30 76 REISSUED 2 25 81 CHANGE 12 3 13 ...