Issued: 15-SEP-1981 | To: FAA | A-81-104 |
INCORPORATE THE FOLLOWING INFORMATION INTO THE DC-9-80 AIRCRAFT FLIGHT MANUAL UNDER THE ABNORMAL HYDRAULICS-OUT LANDING SECTION AND THE NORMAL LANDINGS ON WET/SLIPPERY RUNWAYS SECTION (Closed - Acceptable Alternate Action) |
Issued: 15-SEP-1981 | To: FAA | A-81-105 |
INCORPORATE THE FOLLOWING INFORMATION INTO THE DC-9-80 TRAINING MANUALS AND TRAINING PROGRAMS UNDER THE FLIGHT CONTROL AND LANDING SECTIONS (Closed - Acceptable Action) |
Issued: 15-SEP-1981 | To: FAA | A-81-106 |
REQUIRE THAT DC-9-80 LANDING-APPROVED SIMULATORS INCORPORATE ACTUAL AIRCRAFT CHARACTERISTICS INCLUDING THE DECREASE IN VERTICAL STABILIZER AND RUDDER CONTROL EFFECTIVENESS AS A FUNCTION OF ENGINE REVERSE THRUST LEVELS. THE FLIGHT TEST DATA USED SHOULD BE TAKEN FROM MCDONNELL DOUGLAS REPORT MDC-J9005. FIGURE 14, YAWING ACCELERATION DUE TO MAXIMUM RUDDER, POWER ON, AND FIGURE 15, YAWING ACCELERATION DUE TO MAXIMUM RUDDER, MANUAL, SHOULD BE USED FOR SYMMETRIC REVERSER CONFIGURATIONS FOR THRUST VALUES FROM FORWARD IDLE TO 1.3 EPR REVERSE. DATA SIMILAR TO THAT IN FIGURE 71, EFFECT OF REVERSE THRUST ON DIRECTIONAL CONTROL, SHOULD BE DERIVED AND USED FOR ALL SPEEDS AND SYMMETRIC REVERSE THRUST SETTINGS. CONTROL EFFECTIVENESS FROM A SYMMETRIC 1.3 EPR TO A SYMMETRIC 1.6 EPR SHOULD DECREASE TO ZERO. FOR ASYMMETRIC REVERSE THRUST CONDITIONS, THE DATA IN FIGURE 20, CONTROLLABILITY WITH ASYMMETRIC REVERSE THRUST, SHOULD BE USED. (Closed - Unacceptable Action) |
Issued: 15-SEP-1981 | To: FAA | A-81-107 |
INCORPORATE THE FOLLOWING INFORMATION IN THE DC-9 SERIES -10 THROGH -50 AIRCRAFT FLIGHT MANUALS UNDER THE ABNORMAL HYDRAULICS-OUT LANDING SECTION AND THE NORMAL LANDINGS ON WET/SLIPPERY RUNWAYS SECTION (Closed - Acceptable Action) |
Issued: 15-SEP-1981 | To: FAA | A-81-108 |
INCORPORATE THE FOLLOWING INFORMATION IN THE DC-9 SERIES -10 THROUGH -50 TRAINING MANUALS AND PROGRAMS UNDER THE FLIGHT CONTROL AND LANDING SECTIONS (Closed - Acceptable Action) |
Issued: 15-SEP-1981 | To: FAA | A-81-109 |
REQUIRE THAT DC-9 SERIES -10 THROUGH -50 LANDING-APPROVED SIMULATORS INCORPORATE ACTUAL AIRCAFT CHARACTERISTICS INCLUDING THE DECREASE IN VERTICAL STABILIZER AND RUDDER CONTROL EFFECTIVENESS AS A FUNCTION OF ENGINE REVERSE THRUST LEVELS. THE FLIGHT TEST DATA TO BE USED SHOULD BE TAKEN FROM MCDONNELL DOUGLAS CORPORATION REPORT MDC-J9005. DATA SIMILAR TO THAT IN FIGURE 71, EFFECT OF REVERSE THRUST ON DIRECTIONAL CONTROL, SHOULD BE DERIVED AND USED FOR ALL SPEEDS AND SYMMETRIC REVERSE THRUST SETTINGS. (Closed - Unacceptable Action) |
Issued: 15-SEP-1981 | To: FAA | A-81-110 |
CONDUCT AN ENGINEERING EVALUATION OF THE DC-9 SERIES -10 THROUGH -50 BRAKE HYDRAULIC ACCUMULATORS AND ANTISKID SYSTEMS TO DETERMINE IF THE BRAKE ANTISKID SYSTEMS CAN BE LEFT ON DURING HYDRAULICS-OUT LANDINGS. REVISE WHERE APPLICABLE THE HYDRAULICS-OUT LANDING PROCEDURES FOR THE DC-9 SERIES -10 THROUGH -50 AIRPLANES TO CORRESPOND WITH THOSE DEVELOPED FOR THE DC-9-80 WITHIN THE CAPABILITIES OF THE RESPECTIVE BRAKE HYDRAULIC ACCUMULATORS AND ANTISKID SYSTEMS. (Closed - Acceptable Action) |
Issued: 15-SEP-1981 | To: FAA | A-81-111 |
EXAMINE ALL AIRCRAFT MODELS WITH AFT POD-MOUNTED ENGINE/THRUST REVERSERS TO DETERMINE IF VERTICAL STABLIZER AND RUDDER EFFECTIVENESS IS LOST OR REDUCED WHEN REVERSE THRUST IS USED DURING LANDING ROLLOUT. IF THIS ADVERSE CHARACTERISTIC OCCURS, REVISE LANDING PROCEDURES, APPROPRIATE MANUALS, AND TRAINING MATERIALS AS NECESSARY TO ASSURE THAT MAXIMUM DIRECTIONAL CONTROL IS MAINTAINED DURING THE LANDING ROLLOUT. (Closed - Acceptable Action) |
Issued: 15-SEP-1981 | To: FAA | A-81-112 |
REVISE CERTIFICATION REQUIREMENTS FOR THOSE AIRCRAFT FOR WHICH SAFE FLIGHT AND LANDING FOLLOWING A PARTIAL OR TOTAL HYDRAULIC SYSTEM FAILURE MUST BE DEMONSTRATED TO (Closed - Unacceptable Action) |
Issued: 15-SEP-1981 | To: FAA | A-81-122 |
ENSURE THAT PHASE I, II, AND III SIMULATOR REQUIREMENTS FOR OTHER MODEL AIRCRAFT AS DEFINED IN 14 CFR 121, APPENDIX H, SPECIFICALLY INCLUDE THE REPRESENTATIVE DEGRADATION OF DIRECTIONAL CONTROL ASSOCIATED WITH THE EFFECT OF REVERSE THRUST ON THE AERODYNAMIC CONTROL SURFACES IF THE SIMULATED AIRCRAFT HAS SUCH CHARACTERISTICS FOR NORMAL AND ABNORMAL CONFIGURATIONS OR SYSTEMS CONDITION, AND REVISE ADVISORY CIRCULAR 121-14C ACCORDINGLY. (Closed - Unacceptable Action) |
Issued: 15-SEP-1981 | To: FAA | A-81-123 |
ENSURE THAT AIR CARRIER TRAINING AND PROFICIENCY CHECK PROGRAMS REQUIRED BY 14 CFR 121 INCLUDE A DEMONSTRATION OF DIRECTIONAL CONTROL CHARACTERISTICS DURING LANDING ROLLOUT WHEN CONDUCTED IN ACCORDANCE WITH THE TRAINING AND CHECKING PERMITTED USING A PHASE I, II, OR III SIMULATOR AS PROVIDED FOR IN 14 CFR 121, APPENDIX H. (Closed - Acceptable Action) |