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81-23-05: 81-23-05 PIPER AIRCRAFT CORPORATION: Amendment 39-4333. Applies to Piper Aircraft Models PA-28-151 (S/N 28-7415001 through 28-7715314), and PA-28-161 (S/N 28-7716001 through 28-8216066) airplanes certificated in any category. COMPLIANCE: Required prior to further flight and as indicated in the body of this AD. To prevent possible inflight fire, accomplish the following: A) On Piper Models PA-28-151 (S/N 28-7415001 through 28-7715314) and PA-28-161 (S/H 28-7716001 through 28-7916210) airplanes: (1) Remove the rear seat base and check for any broken springs or evidence of electrical contact between the seat springs and the battery. Check the battery box and cover for any evidence of damage, especially wear of the battery box cover caused by contact with the seat springs. If the seat spring or the battery box cover is damaged, repair or replace with serviceable items. If not, reinstall the battery box cover and ensure that all fasteners lock and that the cover is secure. (2) Install the seat base, ensuring that the saddle clamps at the rear of the seat, left and right, are engaged. When the seat base is lowered into position, the forward edge of the seat legs must be at least 0.80 inch aft of the forward vertical face of the wing spar box. (3) Install a placard in clear view of the pilot stating "DO NOT USE REAR SEAT FOR PASSENGERS OR CARGO" and operate the airplane in accordance with this limitation. The placard may be made from any convenient durable material with contrasting color letters at least 1/4 inch high. (4) The requirements of paragraphs A)(1), (2) and (3) may be complied with by a person authorized to perform preventive maintenance in accordance with Federal Aviation Regulation 43.3(h), except that repair or replacement must be accomplished by appropriately rated persons. (5) The placard required by paragraph A) (3) may be removed after the rear seat has been modified in accordance with the instructions contained in Piper Aircraft Corporation Service Kit No. 764, 303V, SEAT AFT BOTTOM MODIFICATION, dated October 29, 1981, and Piper Service Bulletin 631B, dated October 29, 1981. B) On Piper Models PA-28-161 (S/N 28-7916211 through 28-8216066) airplanes: (1) Remove the rear seat base and check for any broken springs or evidence of electrical contact between the seat springs and the battery. Check the battery box and cover for any evidence of damage, especially wear of the battery box cover caused by contact with the seat springs. If the seat spring or the battery box cover is damaged, repair or replace with serviceable items. If not, reinstall the battery box cover and ensure that all fasteners lock and that the cover is secure. (2) Install the seat base, ensuring that the saddle clamps at the rear of the seat, left and right, are engaged. Ensure that the forward legs on the rear seat base are aft of the reference line established by the placard (Piper P/N 35669-194) on top of the spar box, reference Piper Service Bulletin 631B dated October 29, 1981. (3) Before each flight, check that the rear seat base is properly positioned as indicated by the placard. (4) The requirements of paragraphs B)(1), (2) and (3) may be complied with by a person authorized to perform preventive maintenance in accordance with Federal Aviation Regulation 43.3(h), except that repair or replacement must be accomplished by appropriately rated persons. (5) Within the next 50 hours time-in-service after the effective date of this AD, modify the rear seat base in accordance with the instructions contained in Piper Aircraft Corporation Service Kit No. 764 3O3V, SEAT AFT BOTTOM MODIFICATION, dated October 29, 1981, and Piper Service Bulletin 631B, dated October 29, 1981. The repeat preflight checks of paragraph B)(3) may be discontinued after this modification. C) An equivalent method of compliance may be approved by Chief, Engineering and Manufacturing Branch, FAA, Southern Region, P.O. Box 20636, Atlanta, Georgia 30320. This amendment becomes effective on March 8, 1982, to all persons except those to whom it has already been made effective by priority letter from the FAA dated November 3, 1981, and is identified as AD 81-23-05.
81-04-05 R1: 81-04-05 R1 PIPER: Amendment 39-4040 as amended by amendment 39-4312. Applies to the following Piper PA-23 Series airplanes certificated in all categories: PA-23 S/N 23-1 thru 23-2046 PA-23-235 S/N 27-505 thru 27-622 PA-23-250 S/N 27-1 thru 27-504 PA-23-250 (6 place) S/N 27-2000 thru 27-8054059 (a) To prevent malfunctioning of the flaps comply with the following: (1) For all referenced airplanes except PA-23-250s (6 place) above S/N 27- 7405300, inspect the flap-spar hinge attachment areas for cracks and repair if necessary in accordance with the instructions paragraph of Piper Service Letter No. 853 dated June 8, 1979, or equivalent as follows: (i) Airplanes with more than 2000 hours in service but not exceeding 3000 hours, inspect and repair if necessary within the next 100 hours in service and thereafter at intervals not to exceed 100 hours in service since the last inspection. (ii) Airplanes with more than 3000 hours in service, inspect and repair if necessary, within the next 50 hours in service, unless already inspected within the last 50 hours in service, and thereafter at intervals not to exceed 100 hours in service since the last inspection. (2) When the flaps are replaced by the appropriate flaps in accordance with the part numbers in the Materials Required section in Piper Service Letter No. 853 dated June 8, 1979, or equivalent, further compliance with (a) is not required. (b) To prevent malfunctioning of the flap control system, comply with the following: (1) For all referenced airplanes, inspect the flap control system for cracks and repair if necessary in accordance with steps 1 through 13 under "instructions" in Piper Service Bulletin No. 671 dated October 20, 1980 or equivalent, and alter in accordance with step 9, as follows: (i) Airplanes with more than 1000 hours in service but not exceeding 2000 hours, comply with (b)(1) within the next 100 hours in service, unless already accomplished. (ii) Airplanes with more than 2000 hours in service, comply with (b)(1) within the next 50 hours in service, unless already accomplished. (2) After the bellcrank, Piper Number 16423-00, is reassembled in accordance with 4e in Service Bulletin 671, conduct a visual inspection of the bellcrank for cracks at intervals not to exceed 100 hours in service after the initial inspection of step 4. If cracks are found replace with new bellcrank Piper P/N 16423-06, or equivalent, before further flight. Upon installation of bellcrank Piper P/N 16423-06, or equivalent, the repetitive inspections are no longer required. Equivalent inspections, parts and alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Upon submittal 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. Amendment 39-4040 was effective February 12, 1981. This amendment 39-4312 is effective February 11, 1982.
2023-12-05: The FAA is superseding Airworthiness Directive (AD) 2022-03- 05, which applied to all The Boeing Company Model 747-8F and 747-8 series airplanes and Model 777 airplanes. AD 2022-03-05 required revising the limitations section of the existing airplane flight manual (AFM) to incorporate limitations prohibiting dispatching or releasing to airports, and approaches or landings on runways, when in the presence of interference from wireless broadband operations in the 3.7- 3.98 GHz frequency band (5G C-Band) as identified by Notices to Air Missions (NOTAMs). Since the FAA issued AD 2022-03-05, the FAA determined that additional limitations are needed due to the continued deployment of new 5G C-Band stations whose signals are expected to cover most of the contiguous United States at transmission frequencies between 3.7-3.98 GHz. This AD requires revising the limitations section of the existing AFM to incorporate limitations prohibiting dispatching or releasing to airports, and approaches or landings on runways, due to the presence of 5G C-Band interference. The FAA is issuing this AD to address the unsafe condition on these products.
81-23-07: 81-23-07 PIPER: Amendment 39-4252. Applies to Model PA-38-112 Serial Nos. 38-78A0001 thru 38-78A0678 certificated in all categories except aircraft incorporating engine mount assembly Piper Part Number 77651-02. To prevent possible nose-gear failure associated with weakening of the engine-mount, accomplish the following unless previously accomplished: a. On aircraft modified in accordance with Piper S/B 617 dated October 12, 1978, or equivalent, with less than 950 hours in service since incorporation of the modification, inspect and replace, if required, the engine mount within the next 50 hours in service after the effective date of this AD, in accordance with Piper S/B 617B dated January 13, 1981, Instructions Paragraph 3 or equivalent. Repeat inspection at intervals not to exceed 50 hours until 1000 hours in service from modification or until replacement of the engine mount with engine mount assembly Piper Part Number 77651-02. Replacement engine mount P/N 77651-02must be installed prior to the accumulation of 1000 hours in service on modified engine mount. b. On aircraft modified in accordance with Piper S/B 617 dated October 12, 1978, or equivalent, with 950 or more hours in service since the modification, within the next 50 hours in service after the effective date of this AD, replace the engine mount with engine mount assembly Piper Part No. 77651-02. c. On aircraft which have not been modified in accordance with Piper S/B 617, dated October 12, 1978, within the next 50 hours in service after the effective date of this AD, replace the engine mount with engine mount assembly Piper Part No. 77651-02. d. Alternative inspections and alterations which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. e. Upon submission of substantiating data through an FAA Maintenance Inspector, the compliance times specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment supersedes AD 79-01-07. This amendment is effective November 16, 1981.
2002-09-12: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Beech Model C90 airplanes. This AD requires you to inspect the left-hand (LH) and right-hand (RH) nacelle and spar assembly for the existence of rivets, and requires you to install rivets if they do not exist or are the wrong size or type. This AD is the result of Raytheon identifying several instances where rivets were either missing or were the wrong size or type on these airplanes. The actions specified by this AD are intended to correct the installation of rivets in the LH and RH nacelle and spar assembly. These rivets must be present and have the correct dimension in order to prevent reduced structural integrity, which could result in structural failure and possible loss of control of the airplane.
2023-12-12: The FAA is superseding Airworthiness Directive (AD) 2022-04- 05, which applied to all The Boeing Company Model 757 and 767 airplanes. AD 2022-04-05 required revising the limitations and operating procedures sections of the existing airplane flight manual (AFM) to incorporate specific operating procedures for landing distance calculations, instrument landing system (ILS) approaches, non-precision approaches, speedbrake deployment, and go-around and missed approaches, when in the presence of interference from wireless broadband operations in the 3.7-3.98 GHz frequency band (5G C-Band) as identified by Notices to Air Missions (NOTAMs). Since the FAA issued AD 2022-04-05, the FAA determined that additional limitations are needed due to the continued deployment of new 5G C-Band base stations whose signals are expected to cover most of the contiguous United States at transmission frequencies between 3.7-3.98 GHz. This AD requires revising the limitations and operating procedures sections of the existing AFM to incorporate specific operating procedures for landing distance calculations, ILS approaches, non-precision approaches, speedbrake deployment, and go- around and missed approaches, due to the presence of 5G C-Band interference. The FAA is issuing this AD to address the unsafe condition on these products.
80-25-07 R1: 80-25-07 R1 STEWART-WARNER CORPORATION: Amendment 39-4028 as amended by Amendment 39-4220. Applies to the following Stewart-Warner oil cooler models: \n\n\nSTEWART WARNER\nMODEL NOS.\nBEGINNING\nSERIAL NOS.\nENDING \nSERIAL NOS. \n8406J\n12558\n16212 \n8406L\n1496\n1763 \n8432K\n514\n541 \n8432L\n631\n964 \n10568C\n1105\n1141 \n10578B\n2212\n2316 \n10599A\n7369\n9013 \n10610A\n1815\n1956 \n10614A\n732\n947 \n10622A\n333\n394 \n10634D\n105\n907 \n8446C\n372\n629 \n8437C\n422\n472 \n10641B\n101\n162 \n8493B\n1269\n1603\n\n\tNOTE: The affected oil coolers were manufactured between July 1, 1979, and November 1, 1980. Oil coolers of the above model and serial numbers that have a date ink stamped next to the nameplate have been inspected by Stewart-Warner and found satisfactory for continued use. \n\n\tThese oil coolers may be installed on, but not limited to, the following aircraft: \n\n\tBellanca Models: 7ECA, 7GCAA, 7GCBC, 7KCAB, 8GCBC, and 8KCAB. \n\n\tCessna Models (including Reims Aviation): 152, A152, F152, FA152, 172I, 172K, 172L, 172M, 172N, 172P, 172RG, F172L, F172M, F172P, 177, 177A, 177B, 177RG, F177RG, R182, FR182, TR182, T182, A188B, T188C, 210N, T210N, and P210N. \n\n\tPiper Model: PA-38-112. \n\n\tMooney Models: M20C, M20E, M20F, M20G, and M20J. \n\n\tGreat Lakes Models: 2T-1A-1 and 2T-1A-2. \n\n\tBeech Models: 269 Series. \n\n\tCompliance is required prior to further flight after the effective date of this AD, unless already accomplished. To prevent the loss of engine oil, accomplish the following: \n\n\t1.\tIf the oil cooler has accumulated 10 hours or less total time in service since new, prior to further flight, replace with an airworthy oil cooler not of the above serial numbers or with an airworthy oil cooler of the above serial numbers that have a date ink stamped next to the oil cooler name plate. \n\n\t\tNOTE: Removed oil coolers may be returned to: Stewart-Warner Corp., Attn: Mr. Ben Gillen, 1514 Drover Street, Indianapolis, Indiana 46221. \n\n\t2.\tIf the oil cooler has accumulated more than 10 hours time in service since new, visually inspect the cooler for oil leakage prior to further flight. \n\n\t\tNOTE: Removal of the engine cowling is not required if it can be positively determined from inspection of areas adjacent to the oil cooler that the oil cooler is not leaking. \n\n\t\tA.\tIf oil leakage is evident, prior to further flight, replace with an airworthy oil cooler not of the above serial numbers or with an airworthy oil cooler of the above serial numbers that have a date ink stamped next to the oil cooler name plate. \n\n\t\tB.\tIf oil leakage is not detected: \n\n\t\t\ti.\tFabricate and install the following placard on the aircraft instrument panel in plain view of the crew, using letters 1/8-inch high minimum: \n\n\t\t\t"Visually check oil cooler for leakage prior to each flight. If leakage is detected, refer to AD Number 80-25-07." \n\n\t\tNOTE: The owner or operator may make and install this placard and conduct the preflight check.This check does not require a logbook entry. The inspection procedures identified in the note following paragraph 2 also apply to this preflight check. \n\n\t\t\tii.\tIf the oil cooler is replaced with an airworthy oil cooler not of the above serial numbers or with an airworthy oil cooler of the above serial numbers that have a date ink stamped next to the oil cooler name plate, the placard can be removed. \n\n\t3.\tAny equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018, telephone (312) 694-7357. \n\n\tAmendment 39-4028 became effective January 29, 1981, as to all persons except those to whom it was made immediately effective by the priority mail letter dated December 5, 1980, which contained this amendment. \n\n\tThis amendment 39-4220 becomes effective September 24, 1981.
2002-09-10: This amendment adopts a new airworthiness directive (AD), that is applicable to CFE Company Model CFE738-1-1B turbofan engines. This amendment requires replacing the high pressure turbine (HPT) stage 1 aft cooling plate and HPT stage 2 disk at or before they reach new reduced life cycle limits. This amendment is prompted by analysis of the existing life cycle limits by the engine manufacturer. The actions specified by this AD are intended to prevent failure of the HPT stage 1 aft cooling plate and HPT stage 2 disk, which could result in an uncontained engine failure and damage to the airplane.
81-16-10: 81-16-10 PIPER AIRCRAFT CORPORATION: Amendment 39-4210. Applies to the following Piper models of aircraft certificated in all categories: PA-44-180 Seminole, S/N 44- 7995001 through 44-8195016; PA-44-180T Turbo Seminole, S/N 44-8107001 through 44- 8107044. Compliance is required as indicated upon receipt of this directive, unless already accomplished. NOTE: An airmail letter was mailed to owners and operators on August 3. To prevent possible damage to the outboard leading edge skin, as well as an aileron out- of-balance condition which could lead to aeroelastic instability, accomplish the following: (a) Before further flight, visually check for cracks at the aileron outboard leading edge balance weight attachment screws. (1) If cracks are found, comply with paragraph (d). (2) If no cracks are found, make log book entry that visual check was made. NOTE: The visual check only may be accomplished by the pilot. (b) At intervals not to exceed25 hours until 100 hours time in service from the effective date of this AD accomplish the following: (1) Inspect, using a 10-power magnifying glass, the left and right aileron outboard leading edge skin for cracks near the balance weight attachment screws. (2) If the skin is cracked near any balance weight attachment screw, comply with paragraph (d) of this AD before further flight. (3) If there are no cracks, make appropriate log book entry of each inspection. (c) Within 100 hours time in service from the effective date of this AD comply with paragraph (d). (d) Reinforce the ailerons outboard leading edge skins by installing Piper's aileron rework kit, Piper Part No. 764 148V in accordance with instructions included with the kit, and make appropriate log book entry. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. Airplanes on which cracks arefound may be flown in accordance with FAR 21.197 and 21.199 to a base where the aileron rework kit can be installed, provided the airplane is not flown in excess of 130 MPH indicated speed. Piper Service Bulletin No. 725A pertains to this subject. This amendment becomes effective September 17, 1981, and was effective upon receipt of the airmail letter mailed August 3 to owners and operators.
2023-11-04: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a report that a design deficiency was discovered which could allow a no-back pawl to be incorrectly installed in a horizontal stabilizer trim actuator (HSTA). This AD requires a check for part number and serial numbers of the HSTA, and if necessary, inspection of the no-back pawl installation, and corrective action. The FAA is issuing this AD to address the unsafe condition on these products.
2002-09-07: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and MD-88 airplanes. This AD requires an inspection of the electrical power feeder cables in the aft cargo compartment sidewall for chafing and/or preloading, and corrective actions, if necessary. This action is necessary to prevent possible arcing of the electrical power cables in the aft cargo compartment sidewall and consequent damage to equipment and the adjacent structure, which could result in smoke and/or fire in the cargo compartment. This action is intended to address the identified unsafe condition.
2002-08-17: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, and DC-10-30F (KC10A and KDC-10) airplanes. This action requires revising the airplane flight manual to advise the flightcrew of necessary procedures if certain thrust reverser indicator lights illuminate or are inoperative, and locking out any affected thrust reverser under certain conditions. This action also provides for returning a thrust reverser to service after it has been locked out. This action is necessary to prevent an uncommanded in-flight deployment of a thrust reverser, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2002-09-01: This amendment adopts a new airworthiness directive (AD), that is applicable to Pratt & Whitney (PW) PW4090, PW4090-3, PW4074D, PW4077D, PW4090D, and PW4098 turbofan engines with 15th stage high pressure compressor (HPC) disks having certain part numbers (P/N's). This amendment requires initial and repetitive borescope inspections of 15th stage HPC disks for cracks in the knife edges, eddy current inspections (ECI's) of blade loading slots if required, and removal of cracked disks. In addition, this amendment requires the removal from service of these P/N disks, at a new lower cyclic life limit. This amendment is prompted by two reports of 15th stage HPC disks with cracks in the outer rim front rail of the blade loading slots, and in the front forward and middle knife edges. The actions specified by this AD are intended to prevent 15th stage HPC disk failures from cracks, which could result in an uncontained engine failure.
2023-11-05: The FAA is superseding Airworthiness Directive (AD) 2021-10- 28, which applied to all Pilatus Aircraft Ltd. (Pilatus) Model PC-24 airplanes. AD 2021-10-28 required incorporating new revisions to the airworthiness limitations section (ALS) of the existing airplane maintenance manual (AMM) or Instructions for Continued Airworthiness (ICA) to incorporate new or more restrictive airworthiness limitations. Since the FAA issued AD 2021-10-28, the FAA determined that new or more restrictive airworthiness limitations are necessary. This AD requires revising the ALS of the existing AMM or ICA for your airplane, 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.
2002-09-02: This amendment adopts a new airworthiness directive (AD), that is applicable to Rolls-Royce plc. (RR) Tay model 650-15 and 651-54 turbofan engines. This amendment requires revisions to the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA) in the Time Limits Section of the Engine Manual for Rolls-Royce plc. Tay model 650-15 and 651-54 series turbofan engines to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
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.
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.