TM  1-1520-240-10            9-1-25 9-1-59.  NO.1 and NO. 2 RECT OFF Cautions. When both transformer-rectifiers (TR) fail, all equipment on the No. 1 and No. 2 DC buses will be disabled. Equip- ment which will be lost includes all fuel boost pumps, both AFCS, accompanied by abrupt attitude change, and both torque indicators. ⁷¹²   Normal Engine beep trim is also disabled, therefore changes in power settings should be minimized. The only source of DC power is the battery. CAUTION If both transformer rectifiers have failed, the main tank boost pumps will be inoperative. If flight  is  conducted  above  6,000  feet  PA,  a descent below 6,000 feet PA must be initiated as soon as possible to avoid a dual engine flameout.  If  applicable,  airspeed  should  be reduced  to  100  KIAS  or Vne,  whichever is slower. LCT and DASH actuators will remain programmed  at  the  airspeed  at  which  the transformer rectifiers failed. ⁷¹²   All normal engine beep trim functions will be inopera- tive.  The  control  of  engine  RPM  will  be accomplished via the EMER ENG TRIM 1 and 2 switches. If both transformer rectifiers fail, perform the following: 1.   Land as soon as possible. 2. ⁷¹²EMER ENG Trim — ADJUST. If unable to land, proceed as follows: 1.   Airspeed — below 100 KIAS. 2.   Altitude — below 6,000 feet PA. 3.   AFCS — OFF. 4.   PDPs — Check circuit breakers in. 5.   DC  Crosstie  circuit  breakers  on  both  NO.  1 and NO. 2 PDPs — Pull out. 6.   DC  Equipment  —  OFF  or  pull  out  circuit breakers  on  essential,  switched  battery  and hot battery buses. 7.   Land as soon as possible. 9-1-60.  BATT SYS MAL Caution. 1.   BATT CHGR circuit breaker — Out, then in. If the BATT SYS MAL caution remains on: 2.   BATT switch — OFF. 9-1-61.  Hydraulic System. WARNING The power transfer pumps were designed for ground checkout of the flight control system and  have  the  capacity  to  pressurize  the system  for  gentle  maneuvers  only.  Rapid control inputs must be avoided to preclude upper boost actuator stalling (binding) and/ or  jam  button  extensions.  Use  the  power transfer pumps in flight is restricted to these emergency conditions only. 9-1-62.  NO. 1 or NO. 2 HYD FLT CONTR Caution. Fluid loss is evident: Land as soon as possible. Fluid loss is not evident: 1.   PWR XFER 1 or 2 switch (affected system) — ON. F 2.   MAINTENANCE PANEL — Monitor. 3.   Land as soon as possible. High fluid temperature is evident. Land as soon as possible. 9-1-63.  NO. 1 and NO. 2 HYD FLT CONTR Caution. If both hydraulic systems fail, flight controls cannot be moved. In addition, the No. 1 and No. 2 AFCS-OFF cau- tion will illuminate. 1.   PWR XFER 1 and 2 switches — ON. 2.   Land as soon as possible. 9-1-64.  UTIL HYD SYS Caution. Depending upon the nature and location of the system failure, it may not be possible to operate the following items of equipment: APU, engine starters, ramp and car- go door, wheel brakes, swivel locks, power steering, car- go hook, PTUs and winch. Should a failure occur in any of these subsystems: APU — Start. If pressure is restored: 1.   Land as soon as practicable. 2.   MAINTENANCE PANEL — Monitor. If pressure is not restored: 1.   APU — Off. 2.   Land as soon as possible.