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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.
80-14-03: 80-14-03 PIPER AIRCRAFT CORPORATION: Amendment 39-3810. Applies to the following airplanes certificated in all categories equipped with Bendix, King or Narco transmitters with factory installed control wheel push-to-talk switches. \n\n\nModels Affected\nSerial Numbers Affected \nPA-28-161 Warrior II\n28-7816001 through 28-8016289 \nPA-28-181 Archer II\n28-7890001 through 28-8090266 \nPA-28-201T Turbo Dakota\n28-7921001 through 28-7921091 \nPA-28-236 Dakota\n28-7911001 through 28-8011096\nPA-28R-201 Arrow III\n28R-7837001 through 28R-7837317 \nPA-28RT-201 Arrow IV\n28R-7918001 through 28R-8018049 \nPA-28R-201T Turbo Arrow III\n28R-7803001 through 28R-7803373 \nPA-28RT-201T Turbo Arrow IV\n28R-7931001 through 28R-8031074 \nPA-32-260 Six\n32-7800001 through 32-7800008\nPA-32-300 Six 300\n32-7840001 through 32-7940290 \nPA-32-301 Saratoga\n32-8006001 through 32-8006015 \nPA-32-301T Turbo Saratoga\n32-8024001 through 32-8024007 \nPA-32R-300 Lance\n32-7880001 through 32-7880068 \nPA-32RT-300 Lance II\n32R-7885001 through 32R-7985105\nPA-32RT-300T Turbo Lance II\n32R-7787001, 32R-7887002 through 32R-7987126 \nPA-32R-301 Saratoga SP\n32R-8013001 through 32R-8013071 \nPA-32R-301T Turbo Saratoga SP\n32R-802900 1 through 32R-8029068 \nPA-34-200T Seneca II\n34-7870001 through 34-8070150 \nPA-44-180 Seminole\n44-7995001 through 44-8095020 \n\n\tCompliance is required as indicated unless already accomplished to prevent disruption of radio communication. \n\n\t(a)\tWithin the next 10 hours time in service after the effective date of this AD, comply with the following: \n\n\t\t(1)\tLocate the audio adapter connector in the main radio harness behind the radio stack. This is the interconnect for individual radios in the audio selector panel. \n\t\n\t\t(2)\tLocate the muting relay plug in this connector. It is a three (3) pin plug containing wires ASP-1, ASP-2, and ASP-3 and is positioned at one end of the adapter connector. \n\n\t\t(3)\tDisconnect the muting relay plug and attach securely to the harness in accordance with Advisory Circular AC43.13-1A. \n\n\t\t(4)\tConduct complete operational check of all radios. \n\n\t\t(5)\tMake a maintenance record entry. \n\n\t(b)\tWithin the next 100 hours time in service after the effective date of this AD, comply with the following: \n\n\t\t(1)\tOn PA-32-260, PA-32-3O0, PA-32-301, PA-32-301T, PA-32R-300, PA- 32RT-300, PA-32RT-300T, PA-32R-301, PA-32R-301T and PA-34-200T model aircraft gain access by removing four (4) screws from the speaker grille ring. On all other affected models, gain access by lowering the overhead dome panel. \n\n\t\t(2)\tRemove the 22 mfd capacitor, part number 454-045, soldered to the muting relay, noting polarity, and install diode as shown in figure 1. Diode is not required on Bendix avionics systems. \n\n\t\t(3)\tReconnect the muting relay plug and conduct radio check for proper operation. \n\n\t\t(4)\tMake a maintenance record entry. \n\n\tPiper Service Bulletin No. 681 applies to the same subject. \n\n\tAny equivalent method of compliance with this Airworthiness Directive may be approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. \n\n\tThis amendment becomes effective July 1, 1980.
80-13-10: 80-13-10 DEHAVILLAND: Amendment 39-3812. Applies to DeHavilland Model DHC- 6 airplanes fitted with main landing gear legs which have not been inspected in accordance with DeHavilland Modification No. 6/1660. To prevent possible failure of the main landing gear legs at the Y-joint weld, accomplish the following: (a) Within the next 10 hours in service, unless accomplished within the last 590 hours in service, inspect the weld juncture at the Y-joint of the main landing gear legs for cracks using dye penetrant or X-Ray inspection methods. If dye penetrant inspection is used, all paint must be removed from the Y-joint weld junction area, and the area must be reprotected after completion of the inspection. If X-Ray inspection is used, paint removal is not required. An acceptable X-Ray method calls for a Phillips 300 KVA constant potential unit or equivalent with exposure of 250 KV and 10 milliamps (MA) for 2.5 minutes. The film to focal spot distance is to be 48 inches with a focal spot size of 4 mm square. Use Kodak Type AA film or equivalent sandwiched between .010 inch thick lead screens in flexible cassettes. The leg material is HY-TUF to AMS 6418B specifications. (b) If no cracks are found, repeat the inspection in Paragraph (a) at intervals not to exceed 600 hours in service or six months, whichever occurs first, until the "D" inspection or equivalent, per DeHavilland Maintenance Manual PSM 1-6-2, is accomplished by 6000 hours in service. (c) Within the next 50 hours in service, unless accomplished within the last 2350 hours in service, inspect the inside of the leg assembly around the crevice location at the Y-joint in accordance with the method noted in Paragraph (e)(1) of this directive for the presence of corrosion and integrity of the internal finish coat. If no corrosion or failure of the inner coat is found, repeat the inspection at intervals not to exceed 2400 hours in service or one year, whichever occurs first, until the "D"inspection, or equivalent, of the leg is accomplished. (d) When complying with Paragraphs (a), (b), or (c) of this directive, (1) If cracks are found, repair in accordance with a method approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region or replace before next flight with a part satisfactorily inspected in accordance with Paragraphs (a) and (c) of this directive. (2) If irregularities are found in the internal finish coat integrity, or if internal corrosion is detected, repair in accordance with DeHavilland Overhaul Manual PSM 1-6- 6, Chapter 32-10-11, revised December 15, 1978, or equivalent, before next flight. (e) For inspection and repair of the main landing gear leg: (1) For an internal inspection, a borescope requiring removal of the leg assembly may be used. X-Ray inspection, or equivalent, which does not require removal of the leg assembly, also may be used. X-Ray inspection is to be accomplished in accordance with Paragraph (a) of this directive. (2) Remove and install the main landing gear leg in accordance with procedures specified in DeHavilland Maintenance Manual PSM 1-6-2 Part 2 or PSM 1-63-2 Chapter 32-00-00, or an equivalent. (3) For local removal of the leg finish and details of a "D" inspection of the leg, comply with Maintenance Manual PSM 1-6-2 Temporary Revision No. 85 or PSM 1-63-2 Chapter 32-10-11, Temporary Revision No. 32-8 dated December 15, 1978, or an equivalent. (4) Disassemble the leg, clean and remove internal and external protective treatment in accordance with Overhaul Manual PSM 1-6-6 Chapter 32-10-11, revised December 15, 1978, or an equivalent. (f) After accomplishment of the "D" inspection, or equivalent, no further action is required for compliance with this AD. (g) 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. (h) Equivalent inspection procedures and repairs may be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (i) The aircraft may be flown in accordance with FAR 21.197 to a base where the inspection or repairs can be performed. This amendment is effective July 1, 1980.
80-15-05: 80-15-05 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 3845. Applies to Model AS 350 series and Model SA 365C series helicopters with spherical thrust bearing rear block P/N 704A-33-633-27 or P/N 704A-33-633-30 installed, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent the failure of the spherical thrust bearing rear block, accomplish the following: (a) Within the next five hours time in service after the effective date of this AD, unless already accomplished, inspect the spherical thrust bearing rear block, P/N 704A-33-633-27 or P/N 704A-33-633-30 (hereinafter referred to as the block) to determine the serial number of the block and, if appropriate, comply with paragraph (b) of this AD. (b) If as a result of the inspection required by paragraph (a) of this AD, the block is found to have a serial number other than one listed in paragraph 1A, "Effectivity", of Aerospatiale Service Bulletin AS350 No. 01-03, dated July 4, 1979, or an FAA-approved equivalent, or Aerospatiale Service Bulletin SA 365 No. 01-04, dated July 4, 1979, or an FAA- approved equivalent, as appropriate (hereinafter referred to as the applicable service bulletin), return the block to service. (c) If as a result of the inspection required by paragraph (a) the block is found to have a serial number listed in paragraph 1A, "Effectivity", of the applicable service bulletin, before further flight - (1) Remove the block from service; (2) Return the block to the factory in accordance with paragraph 1C(2) of the applicable service bulletin; and (3) Replace the block with a serviceable block of the same part number which has a serial number not listed in paragraph 1A of the applicable service bulletin, or a serviceable block of the same part number which has a serial number listed in paragraph 1A, but which is also marked as noted in paragraph 1C(2) of the applicable service bulletin.(d) Before installation of blocks held as spares, inspect them and - (1) Return to the factory those blocks which have serial numbers listed in paragraph 1A of the applicable service bulletin in accordance with paragraph 1C(2) of the applicable service bulletin; and (2) Retain as serviceable those blocks which have serial numbers listed in paragraph 1A of the applicable service bulletin but are also marked as noted in paragraph 1C(2) of the applicable service bulletin. (e) For purposes of complying with this AD, an FAA-approved equivalent must be approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. This amendment supersedes telegraphic AD T79EU-9, issued August 14, 1979. This amendment becomes effective July 14, 1980.