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80-22-13: 80-22-13 PIPER: Amendment 39-3960. Applies to model PA-38-112 airplanes, Serial Nos. 38-78A0001 thru 38-80A0099, 38-80A0113, 38-80A0120 and 38-80A0123 thru 38-80A0165, certificated in all categories. To avoid possible hazards in flight associated with a crack in the rudder upper hinge P/N 77610-02, accomplish the following: a. Within the next five hours in service unless previously accomplished and thereafter at intervals not to exceed 50 hours in service from the last inspection, remove the rudder upper hinge pin and carefully displace the rudder from the fin aft to expose the surfaces of the rudder upper hinge P/N 77610-02. The rudder upper hinge consists of two brackets, P/N 77610-02. Inspect all the hinge surfaces in the area of the hinge pin hole to the forward edge of the hinge for cracks using a dye check inspection method or an equivalent. Upper hinge bolt is to be installed with a torque of 50 to 70 in. lb.; do not exceed the maximum value. b. If a cracked fitting is found, before further flight, replace with a part of the same part number or an equivalent, which have been inspected in accordance with (a). c. Within the next 100 hours in service replace brackets, P/N 77610-02, with two steel rudder upper hinge brackets, Piper P/N 77610-03 or equivalent in accordance with the instruction section of Piper Service Bulletin No. 686 dated May 23, 1980, or equivalent. Upon compliance with this paragraph, the inspections required in paragraph (a) may be discontinued. d. The steel upper rudder hinge P/N 77610-03 or equivalent must be replaced within 5000 hours time in service. e. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the compliance times specified in this AD. f. Equivalent parts, instructions and inspections must be approved by the Chief, Engineering and Manufacturing Branch, FAA,Eastern Region. g. Report findings of cracked parts to the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, within five days of the inspection: include the time on the part, and aircraft serial No. (Reporting approved by the Office of Management and Budget under OMB No. O4-R0174.) This supersedes AD Number 80-11-02 issued by letter dated May 16, 1980. This amendment is effective October 31, 1980.
2002-08-18: This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-135 and -145 series airplanes. This action requires repetitive inspections (tests) of the actuator clutches of the primary and backup pitch trim systems of the horizontal stabilizer for proper pitch trim indications, and replacement of the actuator, if necessary. This action is necessary to prevent loss of pitch trim command during the takeoff and climb phase of flight due to improper set point of the actuator clutches, which could result in high pitch control forces and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2002-08-21: This amendment supersedes an existing airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135ER and "135LR series airplanes, and Model EMB-145, -145ER, -145MR, and -145LR series airplanes, that currently requires a one-time inspection to determine if the bonding jumpers that connect the horizontal stabilizer to the vertical stabilizer are properly installed, a one-time inspection to determine if the supports that connect the bonding jumpers to the horizontal stabilizer are deformed, and corrective actions if necessary. This amendment requires new repetitive inspections to detect discrepancies of both vertical-to-horizontal stabilizer bonding jumpers and the connecting support structure; and corrective action, if necessary. This amendment also revises the applicability to include additional airplanes. The actions specified in this AD are intended to prevent damaged or severed bonding jumpers, which, in the event of a lightning strike, could result in severed elevator control cables and consequent reduced elevator control capability and reduced controllability of the airplane. This AD is intended to address the identified unsafe condition.
2002-08-20: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 737-600, -700, -700C, and 800 series airplanes. This action requires inspecting the airplane following any suspected limit cycle oscillation (LCO) of the elevator tab; and revising the airplane flight manual (AFM) to limit airspeeds under certain conditions and to provide the flight crew with information regarding elevator tab LCO. This action also requires repetitive cleaning of the elevator tab and a one-time cleaning of the elevator balance bays. This action provides for the option to repetitively clean the elevator tab and balance bays following every deicing/anti-icing of the horizontal stabilizer, which would temporarily allow airspeeds exceeding those limited by the AFM revision. For certain airplanes, this action requires trimming the elevator balance panel seals, which will terminate the optional repetitive cleaning procedures for the balance bays. This action is necessary to prevent the accumulation of fluid or residue in the balance bays and foreign substances on the external surfaces of the elevator tab, which can lead to limit cycle oscillation, severe vibration, flutter, and loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
2002-08-52: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2002-08-52, that was sent previously to all known U.S. owners and operators of all Boeing Model 737-600, -700, and -700C series airplanes by individual notices. This AD requires revising the Airplane Flight Manual (AFM) to prohibit operating the airplane at speeds in excess of 300 knots indicated airspeed (KIAS) with speedbrakes extended. This AD also provides for optional terminating action for the AFM revision. This action is prompted by a report indicating that severe vibration of the horizontal stabilizer occurred on a Boeing Model 737-700 series airplane. The actions specified by this AD are intended to prevent severe vibration of the elevator and elevator tab assembly following deployment of the speedbrakes, which, if not corrected, could result in severe damage to the horizontal stabilizer, followed by possible loss of controllability of the airplane.
80-17-06: 80-17-06 PIPER AIRCRAFT CORPORATION: Amendment 39-3874. Applies to Model PA-31 and PA-31-325 airplanes, Serial Numbers 31-7401201 through 31-8012072; and PA-31-350 airplanes, Serial Numbers 31-7405401 through 31-8052162 certificated in all categories. Compliance is required as indicated unless already accomplished. To prevent the possible use of incorrect airspeed information during normal and emergency operations and to insure accessibility to emergency landing gear extension placards and operating equipment, accomplish the following within the next 50 hours time in service after the effective date of this AD: (a) Check for the following placards on these airplanes to insure they are correct and accessible: (1) Piper PA-31 Serial Numbers 31-7401201 through 31-8012072. On top right side of instrument panel: THIS AIRCRAFT MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS. NO ACROBATIC MANEUVERS (INCLUDING SPINS) APPROVED. For Serial Numbers 31-7401201 through 31-7612110 FOR TYPES OF OPERATION SEE AIRPLANE FLIGHT MANUAL For Serial Numbers 31-7712001 through 31-8012072 FOR TYPES OF OPERATION SEE PILOT'S OPERATING HANDBOOK On top left side of instrument panel: For Serial Numbers 31-7401201 through 31-7612110 MINIMUM CONTROL SPEED 85 MPH MAXIMUM SPEED LANDING GEAR OPERATION 150 MPH DESIGN MANEUVERING SPEED 183 MPH SEE AIRPLANE FLIGHT MANUAL FOR ADDITIONAL SPEEDS For Serial Numbers 31-7712001 through 31-7712103 MINIMUM CONTROL SPEED 76 KIAS MAXIMUM SPEED LANDING GEAR OPERATION 129 KIAS DESIGN MANEUVERING SPEED 159 KIAS SEE PILOT'S OPERATING HANDBOOK FOR ADDITIONAL SPEEDS For Serial Numbers 31-7812001 through 31-8012072 MINIMUM CONTROL SPEED 76 KIAS MAXIMUM 5P. LG - RET. 129 KIAS EXTEND 156 KIAS DESIGN MANEUVERING SPEED 159 KIAS SEE PILOT'S OPERATING HANDBOOK FOR ADDITIONAL SPEEDS On floor between pilot and copilot seats, check the following two placards for accessibility: EMERGENCY GEAR EXTENSION REMOVE COVER EXTENSION INSTRUCTIONS ON REVERSE SIDE On underside of emergency gear extension door: EMERGENCY GEAR EXTENSION 1. PLACE GEAR SELECTOR IN DOWN POSITION. 2. PULL EMERGENCY PUMP HANDLE OUT AS FAR AS POSSIBLE. 3. PUMP HANDLE UP AND DOWN UNTIL ALL 3 GREEN LIGHTS COME ON. CONTINUE PUMPING UNTIL PRESSURE BUILDS UP AND SELECTOR HANDLE RETURNS TO NEUTRAL. (2) Piper PA-31-325, Serial Numbers 31-7512001 through 31-8012072. On top right side of instrument panel: THIS AIRCRAFT MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS. NO ACROBATIC MANEUVERS (INCLUDING SPINS) APPROVED. For Serial Numbers 31-7512001 through 31-7612110 FOR TYPES OF OPERATION SEE AIRPLANE FLIGHT MANUAL For Serial Numbers 31-7712001 and UP FOR TYPES OF OPERATION SEE PILOT'S OPERATING HANDBOOK On left side, center of pilot's panel: For Serial Numbers 31-7512001 through 31-7612110 MINIMUM CONTROL SPEED 85 MPH MAXIMUM SPEED LANDING GEAR OPERATION 150 MPH DESIGN MANEUVERING SPEED 183 MPH SEE AIRPLANE FLIGHT MANUAL FOR ADDITIONAL SPEEDS For Serial Numbers 31-7712001 through 31-7712103 MINIMUM CONTROL SPEED 71 KIAS MAXIMUM SPEED LANDING GEAR OPERATION 127 KIAS DESIGN MANEUVERING SPEED 155 KIAS SEE PILOT'S OPERATING HANDBOOK FOR ADDITIONAL SPEEDS For Serial Numbers 31-7812001 through 31-8012072 MINIMUM CONTROL SPEED 71 KIAS MAXIMUM 5P. LG - RET. 127 KIAS EXTEND 152 KIAS DESIGN MANEUVERING SPEED 155 KIAS SEE PILOT'S OPERATING HANDBOOK FOR ADDITIONAL SPEEDS On floor between pilot and copilot seats, check the following two placards for accessibility: EMERGENCY GEAR EXTENSION REMOVE COVER EXTENSION INSTRUCTIONS ON REVERSE SIDE On underside of emergency gear extensiondoor: EMERGENCY GEAR EXTENSION 1. PLACE GEAR SELECTOR HANDLE IN DOWN POSITION. 2. PULL EMERGENCY PUMP HANDLE OUT AS FAR AS POSSIBLE. 3. PUMP HANDLE UP AND DOWN UNTIL ALL 3 GREEN LIGHTS COME ON. CONTINUE PUMPING UNTIL PRESSURE BUILDS UP AND SELECTOR HANDLE RETURNS TO NEUTRAL. On pedestal adjacent engine controls (when air conditioning is installed): AIR CONDITIONING OFF FOR SINGLE ENGINE OPERATION Above airspeed indicator: For Serial Numbers 31-7512001 through 31-7612110 ABOVE 12,000 FEET REDUCE VNE SPEED 3 MPH PER 1,000 FEET For Serial Numbers 31-7712001 through 31-8012072 ABOVE 12,000 FEET REDUCE VNE SPEED 2.6 KTS PER 1,000 FEET Adjacent to airspeed indicator: For Serial Numbers 31-7512001 through 31-7612110 ABOVE 21,000 FEET REDUCE VNO SPEED 3 MPH PER 1,000 FEET For Serial Numbers 31-7712001 through 31-8012072 ABOVE 21,000 FEET REDUCE VNO SPEED 2.6 KTS PER 1,000 FEET (3) Piper PA-31-350, Serial Numbers 31-7405401 through 31-8052162. On top right side of instrument panel: THIS AIRCRAFT MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS. NO ACROBATIC MANEUVERS (INCLUDING SPINS) APPROVED. For Serial Numbers 31-7405401 through 31-7652176 FOR TYPES OF OPERATION SEE AIRPLANE FLIGHT MANUAL For Serial Numbers 31-7752001 and UP FOR TYPES OF OPERATION SEE PILOT'S OPERATING HANDBOOK On top left side of instrument panel: For Serial Numbers 31-7405401 through 31-7652176 MINIMUM CONTROL SPEED 90 MPH MAXIMUM SPEED LANDING GEAR OPERATION 150 MPH DESIGN MANEUVERING SPEED 186 MPH SEE AIRPLANE FLIGHT MANUAL FOR ADDITIONAL SPEEDS For Serial Numbers 31-7752001 through 31-7752201 MINIMUM CONTROL SPEED 76 KIAS MAXIMUM SPEED LANDING GEAR OPERATION 128 KIAS DESIGN MANEUVERING SPEED 160 KIAS SEE PILOT'S OPERATING HANDBOOK FOR ADDITIONAL SPEEDSFor Serial Numbers 31-7852001 through 31-8052162 MINIMUM CONTROL SPEED 76 KIAS MAXIMUM SP. LG - RET. 128 KIAS EXTEND 153 KIAS DESIGN MANEUVERING SPEED 160 KIAS SEE PILOT'S OPERATING HANDBOOK FOR ADDITIONAL SPEEDS On floor between pilot and copilot seats, check the following two placards for accessibility: EMERGENCY GEAR EXTENSION REMOVE COVER EXTENSION INSTRUCTIONS ON REVERSE SIDE On underside of emergency.gear extension door: EMERGENCY GEAR EXTENSION 1. PLACE GEAR SELECTOR HANDLE IN DOWN POSITION. 2. PULL EMERGENCY PUMP HANDLE OUT AS FAR AS POSSIBLE. 3. PUMP HANDLE UP AND DOWN UNTIL ALL 3 GREEN LIGHTS COME ON.CONTINUE PUMPING UNTIL PRESSURE BUILDS UP AND SELECTOR HANDLE RETURNS TO NEUTRAL On pedestal adjacent engine controls (when air conditioning is installed): AIR CONDITIONING OFF FOR SINGLE ENGINE OPERATION (b) If aircraft is equipped with floor runners to protect carpeting, an opening must be cut in the runner to match opening in carpet in order to provide access to Emergency Gear Extension Cover. (c) Replace incorrect or missing placards with correct placards. NOTE: Placards may be obtained from Piper Aircraft Corporation, Lakeland Division 3000 Medula Road, Lakeland, Florida 33803, telephone (813) 646-2911. (d) When (a) through (c) above are accomplished, make an appropriate maintenance record entry. These actions may be accomplished by a pilot as provided in FAR 43.3(h). An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. NOTE: Piper Service Bulletin 688 pertains to this subject. This amendment becomes effective August 13, 1980.
2023-10-08: The FAA is superseding Airworthiness Directive (AD) 2022-25- 16, which applied to all ATR--GIE Avions de Transport R[eacute]gional Model ATR42-200, -300, and -320 airplanes. AD 2022-25-16 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require certain actions in AD 2022-25-16 and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2002-08-13: This amendment adopts a new airworthiness directive (AD) that is applicable to all Airbus Model A319, A320, and A321 series airplanes. This action requires identification of the part number and serial number of the parking brake operated valve (PBOV); and, if necessary, inspection of the PBOV, including a functional check of the PBOV, and follow-on and corrective actions. This action also provides for optional terminating action for the requirements of this AD. This action is necessary to prevent loss of the yellow hydraulic system, which provides all the hydraulics for certain spoilers; elements of the hydraulics for flaps, stabilizer, pitch and yaw feel systems, pitch and yaw autopilot, and yaw damper; and elevator, rudder, and aileron. This action is intended to address the identified unsafe condition.
80-14-08: 80-14-08 PIPER: Amendment 39-3829. Applies to Model PA-31T, Serial Numbers 31T-7400002 thru 31T-7620057 and PA-31T-7720001 thru 31T-7920004 certificated in all categories. Compliance required within 25 hours in service after the effective date of this AD unless already accomplished. In order to prevent undesirable high altitude (above 20,000 feet) Longitudinal Dynamic Stability (Phugoid) Characteristics, accomplish the following: a. Incorporate the applicable Airplane Flight Manual/Pilot's Operating Handbook Revision as listed below into the FAA-Delegation Option Authority approved Airplane Flight Manual/Pilot's Operating Handbook in accordance with Piper Instruction, Code 31T-6 dated February 5, 1979, or Piper Instruction Code PFL-31T-790228 dated August 17, 1979. Airplane Serial Number: 31T-7400002 thru 31T-7620057. AFM/POH Rev. and Part No.: Rev. 11-761 560 (AFM). REM Rev. No.: 790228. Date: 2/28/79. Airplane Serial Number: 31T-7720001 thru 31T-7920004. AFM/POH Rev. and Part No.: Rev. 5-761 625 (POH). AEM Rev. No.: 781006. Date: 10/6/78. b. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the inspection intervals specified in this AD. c. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a) (1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Piper Aircraft Corporation, 820 E. Bald Eagle Street, Lock Haven, Pennsylvania 17745. These documents may also be examined at the Eastern Region, Federal Aviation Administration, Federal Building, JFK International Airport, Jamaica, New York 11430, and at FAA headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on thisAD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Eastern Region. This amendment becomes effective July 7, 1980.
80-14-15: 80-14-15 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-3833. Applies to Model AS-350 series helicopters with flange, P/N 350A371201-20 installed, certificated in all categories. To prevent the failure of flange P/N 350A371201-20, accomplish the following: (a) Within the next five hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 25 hours time in service from the last inspection until a steel flange P/N 350A371207-20 is installed, inspect the flange P/N 350A371201-20 for cracks using the dye penetrant method as follows: (1) Remove the vibration damper in accordance with Aerospatiale Maintenance Work Card 65.12.403, dated February 1979, or an FAA-approved equivalent. Do not remove flange. (2) Clean the flange P/N 350A371201-20 with soapy water and a non-metallic brush. (3) Apply the dye penetrant to the flange blending radius to the cylindrical section, being careful to protect the adjacent areas against splashing. (b) If, during an inspection required by paragraph (a) or (d) of this AD, no cracking is found, reinstall the vibration damper in accordance with Aerospatiale Maintenance Work Card 65.12.403, dated February 1979, or an FAA-approved equivalent, return the assembly to service, and continue to inspect in accordance with paragraph (a) or (d) of this AD, as appropriate. (c) If, during an inspection required by paragraph (a) or (d) this AD, cracking is found, before further flight - (1) Replace the flange in accordance with Aerospatiale Maintenance Work Card 65.12.401, dated June 1977, or an FAA-approved equivalent, with a crack-free new or serviceable used flange of the same part number and accomplish the repetitive inspection required by paragraph (d) of this AD. (Before installation of a used flange, inspect it in accordance with the method specified in paragraph (a) of this AD to ensure that it is crack-free); or (2) Install a steelflange, P/N 350A371207-20 (also identified as modification AMS 6063). (d) Within the next 25 hours time in service after flange replacement in accordance with paragraph (c)(1) of this AD, and thereafter at intervals not to exceed 25 hours time in service from the last inspection, inspect flange P/N 350A371201-20 in accordance with the method specified in paragraph (a) of this AD. (e) Upon installation of a steel flange P/N 350A371207-20, inspections required by paragraphs (a) and (d) of this AD may be discontinued. (f) For purposes of this AD, an FAA-approved equivalent must be approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office. NOTE: SNIAS (Aerospatiale) Mandatory Service Bulletin 05-03, dated May 10, 1979, pertains to this same subject. This amendment becomes effective July 3, 1980, as to all persons except those persons to whom it was made immediately effective by the telegram issued April 23, 1979, which contained this amendment.