Results
2001-03-02: This amendment adopts a new airworthiness directive (AD) that is applicable to Pratt & Whitney Canada (PWC) models PW306A and PW306B turbofan engines. This amendment requires removing compressor rotor 2nd, 3rd, and 4th stage drum assemblies and impellers from service before exceeding new, lower cyclic life limits. This amendment is prompted by the results of test analyses that indicate certain compressor rotor 2nd, 3rd, and 4th stage drum assemblies and impellers do not have full published life. The actions specified in this AD are intended to prevent premature cracking of compressor rotor 2nd, 3rd, and 4th stage drum assemblies and impellers which could result in an uncontained engine failure and damage to the airplane.
2000-25-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2000-25-51 that was sent previously to all known U.S. owners and operators of Rolls-Royce Deutschland GmbH (formerly BMW Rolls-Royce GmbH) model BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 turbofan engines. This action requires that certain high pressure turbine (HPT) stage 1 disks, part numbers (P/N's) BRH20009, BRH20010, BRH12167, BRH12168, BRH12466, and BRH12467; and stage 2 disks, P/N's BRH19349 and BRH19350, be removed before exceeding the new reduced cyclic limit, and replaced with a serviceable disk. This amendment is prompted by a reduction of the life limit for several high pressure turbine (HPT) stage 1 and stage 2 disks. The actions specified in this AD are intended to prevent an uncontained failure of the HPT stage 1 or stage 2 disk due to exceeded life-cycle limits.
75-16-02: 75-16-02 PIPER: Amendment 39-2270. Applies to Models PA-31P, Serial Nos. 31P-1 through 31P-7530019 and PA-31T, Serial Nos. 31T-400002 through 31T-7520022 certificated in all categories except aircraft incorporating Piper Kit No. 76-923, Rudder and Nose Gear Steering Cable Replacement or equivalent. To prevent possible hazards in flight associated with restricted rudder travel due to rudder nose gear steering cable entwinement, accomplish the following: 1. Within the next fifty hours in service from the effective date of this AD, replace the existing rudder nose gear steering cable installation in accordance with the instructions and parts contained in Piper Kit No. 760-923, Rudder and Nose Gear Steering Cable Replacement or equivalent. 2. Equivalent replacement must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (Piper Service Bulletin No. 446 refers to this subject.) This supersedes Amendment, AD 72-26-2. This amendment is effective July 29, 1975.
2007-09-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2007-09-51, sent previously to all known U.S. owners and operators of the specified MD Helicopters, Inc. (MDHI), model helicopters by individual letters. This AD requires, before further flight, removing each affected tail rotor blade assembly and inspecting the bore of the tail rotor blade root fitting. If the blade assembly does not have a smooth radius, the AD requires replacing it. The AD also requires identifying each airworthy tail rotor blade assembly with the applicable helicopter model. This amendment is prompted by a report of an accident after the loss of a tail rotor blade. The actions specified by this AD are intended to prevent the failure of a tail rotor blade and subsequent loss of control of the helicopter.
2004-15-14: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319-131, -132, and -133; A320-231, -232, and -233; and A321-131 and -231 series airplanes. This AD requires revising the airplane flight manual (AFM) to advise the flightcrew of procedures associated with the intermittent interruption of the electrical power. Under certain conditions, this AD also requires inspecting for signs of arcing and performing any necessary corrective actions. This AD also provides for optional terminating action for the requirements of the AD. This AD is prompted by reports of fretting and consequent arcing of the electrical harness of the integrated drive generator (IDG) at the pin-to-socket connector at the firewall. We are issuing this AD to prevent transient loss of certain systems and consequent reduced ability of the flightcrew to cope with adverse flight conditions.
2001-02-03: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 206A, B, L, L1, and L3 helicopters. This AD requires inspecting the collective lever assembly (assembly) for a raised forging boss, inspecting the assembly for adequate clearance between the collective lever and the swashplate outer ring (outer ring), and modifying any assembly with a raised forging boss and inadequate clearance before further flight. Modifying any assembly that has a raised forging boss and adequate clearance would be required before further flight after January 31, 2001. This AD is prompted by the discovery that a raised forging boss could result in control system interference. The actions specified by this AD are intended to prevent interference between the collective lever and the outer ring, damage to flight controls, and subsequent loss of control of the helicopter.
2018-04-02: We are adopting a new airworthiness directive (AD) for Viking Air Limited Models DHC-6-1, DHC-6-100, DHC-6-200, DHC-6-300, and DHC-6- 400 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and address an unsafe condition on an aviation product. The MCAI describes the unsafe condition as aileron cable wear; fouling at the wing root rib, fuselage skin, and wing root rib fairlead; and/or fraying of the cable from the root rib fairlead. We are issuing this AD to require actions to address the unsafe condition on these products.
75-12-06: 75-12-06 PIPER: Amendment 39-2227. Applies to Piper Models PA-24, PA-24-250, PA-24-260 and PA-24-400 certificated in all categories. Compliance required as indicated. 1. Affects the fin forward spar to fuselage attachment assembly where the channel P/N 20749-0 and the straps P/N 20749-5 and -6 are riveted together. (a) Within the next 25 hours' time in service, unless already accomplished within the last 75 hours' time in service: (i) Inspect the channel P/N 20749-0 and the two straps P/N 20749-5 and -6 in the area of the channel bend relief holes for cracks using a dye penetrant method or an approved equivalent inspection. (ii) Polish the rough edges of the bend relief holes. (b) Within 100 hours' time in service after the inspection specified in "a" above, visually inspect the channel and straps in the area of the channel relief holes for cracks using a magnifying glass of at least 5 power or an approved equivalent inspection. (c) The inspection specified in "b" above shall be repeated at intervals not to exceed 100 hours' time in service from the last inspection. 2. Repair cracked parts with an FAA approved repair or replace parts with an unused part of the same number or an approved equivalent part prior to further flight. 3. 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 interval specified in this AD. Equivalent inspections and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective June 5, 1975.
2007-12-16: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as some stringer reinforcements (F900DX) and some rivets (F900DX/F2000EX) missing from the skin panels on each side of the fuselage between frames 9 and 10 on certain Falcon 900DX and Falcon 2000EX EASy aircraft; this situation affects the structural integrity of the fuselage. We are issuing this AD to require actions to correct the unsafe condition on these products.
2019-14-02: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737 series airplanes. This AD was prompted by a \n\n\nreport that structural fatigue cracks can develop in certain aluminum pressure module check valves prior to the design limit. This AD requires an inspection to determine the part numbers of the four hydraulic systems A and B pressure module check valves and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2001-02-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2001-02-51 that was sent previously to all known U.S. owners and operators of EMBRAER Model EMB-145 and EMB-135 series airplanes by individual notices. This AD requires revising the FAA-approved airplane flight manual and installing placards to alert the flight crew to the maximum speed for airplane retrimming after takeoff and during the climb phase. This action is prompted by issuance of mandatory continuing airworthiness information by a foreign airworthiness authority. The actions specified by this AD are intended to prevent high pitch control forces, which could result in possible loss of control of the airplane.
2019-13-04: The FAA is adopting a new airworthiness directive (AD) for certain ATR-GIE Avions de Transport R(eacute)gional Model ATR72 airplanes. This AD was prompted by a determination that new or more restrictive maintenance instructions and airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive maintenance instructions and airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
75-06-04: 75-06-04 PIPER: Amendment 39-2121. Applies to Model PA-31-350, Serial Nos. 31- 5001 through 31-7405495 certificated in all categories. Compliance required within the next ten hours in service from the effective date of this AD unless previously accomplished, as indicated. 1. Inspect the forward rudder control cable installation as follows: a. Remove the left pilot's seat and associated floor panels. b. Inspect the left- and right-hand forward rudder control cables P/N 41947-03 for proper routing between the pulleys and cable guard pins. c. Remove the forward rudder cable guard pins and inspect the pins for evidence of contact with the control cable. d. If a forward rudder control cable is not properly routed or the cable guard pins show evidence of contact with the control cable, the control cable must be replaced with an acceptable part of the same part number, before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where repairs can be made. (Piper Service Bulletin No. 379A refers to this subject.) This amendment is effective March 13, 1975, and was effective for all recipients of the airmail dispatch of February 12, 1975, upon receipt.
2000-23-52: This document publishes in the Federal Register an amendment adopting superseding Airworthiness Directive (AD) 2000-23-52, which was sent previously to all known U.S. owners and operators of Sikorsky Aircraft Corporation (Sikorsky) Model S-76A, S-76B, and S-76C helicopters by individual letters. This AD requires, before further flight, performing a fluorescent penetrant inspection of the main rotor shaft assembly (shaft). Also required are recurring fluorescent penetrant inspections and visual inspections for any crack. If any crack is found, the shaft must be replaced with an airworthy shaft before further flight. This amendment is prompted by the discovery of two in-service cracked shafts, one with 477 hours time-in-service (TIS) and one with 313 hours TIS. A third shaft, that had been rejected from the manufacturing process for other reasons, was also discovered to have a crack. The actions specified by this AD are intended to prevent failure of the shaft and subsequent loss of control of the helicopter.
2007-12-23: This amendment adopts a new airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HS, 369HM, 500N, and OH-6A helicopters that requires inspecting each landing gear fairing support assembly (support assembly), replacing or reworking certain forward and aft landing gear assemblies, and creating an access hole to facilitate inspections and a recurring inspection. A terminating action for the requirements of this AD is also provided. This amendment is prompted by five reports of landing gear strut (strut) failures. The actions specified by this AD are intended to detect a crack that could result in the failure of a strut and subsequent loss of control of the helicopter during landing.
2007-12-19: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as explosion risks. Chafing of the fuel pump cables could result in short circuits leading to fuel pump failure, intermittent operation, arcing, and possible fuel tank explosion. We are issuing this AD to require actions to correct the unsafe condition on these products.
74-26-07: 74-26-07 PIPER: Amendment 39-2047. Applies to Model PA-28-180 airplanes serial numbers 28-7305001 through 28-7505079 certificated in all categories. Compliance required as indicated. To detect an incorrect placard accomplish the following: a. Before further flight, unless already accomplished, check the airplane Operating Limitations Placard to insure that it indicates that spins are not approved for normal and utility category operation. If placard correctly indicates that spins are not approved, no further action is necessary. b. If the incorrect placard is installed, cut out appropriate temporary Operating Limitations Placard from Piper Service Bulletin No. 436 or an FAA approved equivalent and attach over existing placard before further flight. c. If a temporary placard is necessary, install permanent placard Piper Part No. 76206-00 (m.p.h.) or 76298-00 (knots) or an FAA approved equivalent within 100 hours time in service from the effective date of this AD. The action required by paragraphs (a) and (b) may be performed by the pilot. Note: For the requirements regarding the listing of compliance and method of compliance with this AD in the airplanes permanent maintenance record, see FAR 91.173. This amendment becomes effective December 21, 1974.
2018-03-16: We are superseding Airworthiness Directive (AD) 2017-10-11 for Stemme AG Model Stemme S10-VT gliders (type certificate previously held by Stemme GmbH & Co. KG). This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and address an unsafe condition on an aviation product. The MCAI describes the unsafe condition as certain propeller front transmission gear wheels having insufficient material strength because of improper heat treatment during manufacturing. We are issuing this AD to require actions to address the unsafe condition on these products and to add Stemme AG Model Stemme S 12 gliders to the Applicability section.
2001-02-12: This amendment adopts a new airworthiness directive (AD) that is applicable to CFMI model CFM56-7B turbofan engines. This action requires a one-time on-wing torque inspection, and torque if needed, of all the PS3 pressure line fittings to insure proper torque. This amendment is prompted by service events which resulted in two in-flight shutdowns (IFSD's) and an aborted takeoff due to the disconnection of one of the PS3 line fittings. The actions specified in this AD are intended to prevent air leakage from incorrectly torqued fittings of the PS3 line, which could result in engine power loss.
74-26-10: 74-26-10 PIPER AIRCRAFT: Amendment 39-2053. Applies to Magneto Switch Guard Installation on Piper PA-31 and PA-31-300 S/N 31-2 to 31-7300969 incl; PA-31-350 S/N 31- 5001 to 31-7305091 incl; and PA-31P S/N 31P-1 to 31P-7300161 incl. To prevent inadvertently or accidentally shutting down an engine, perform the following: 1. Within the next 100 hours time in service, after the effective date of this Airworthiness Directive, install a protective guard over the magneto switches in accordance with Piper Service Letter No. 675, dated September 17, 1973. 2. Equivalent installations must be approved by the Chief, Engineering and Manufacturing Branch, Eastern Region, Jamaica, New York. 3. 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 time specified in this A.D. This amendment is effective December 26, 1974.
74-21-02: 74-21-02 PIPER: Amendment 39-1981. Applies to Piper PA-36-285 airplanes serial numbers 36-7360001 through 36-7460025 certificated in all categories. Compliance required within the next 50 hours time in service after the effective date of this AD, unless already accomplished. To provide a more reliable stall warning system, accomplish the lift detector relocation and modification per Piper Service Bulletin No. 418 or equivalent approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. This amendment becomes effective October 4, 1974.
74-19-01: 74-19-01 PIPER: Amendment 39-1952. Applies to Piper PA-28-235 airplanes, serial numbers 28-7410001 through 28-7410090, PA-32-260 airplanes serial numbers 32-7400001 through 32-7400047, PA-32-300 airplanes 32-7440001 through 32-7440147, and PA-34-200 airplanes serial numbers 34-7450001 through 34-7450205 certificated in all categories. Compliance required within the next ten hours time in service after the effective date of this AD, unless already accomplished. To detect improperly formed lightening holes in the outer wing spars, accomplish the following: (a) PA-28-235 and PA-32 series airplanes (1) Remove the inspection plate on bottom of wing which is located adjacent to the aileron bellcrank. (2) Inspect both sides of left and right spar around the first lightening hole outboard of the fish mouth of the main spar splice for evidence of a die stamping mark approximately six by six inches square surrounding the lightening hole area. (3) Inspect the lightening hole flange radius for cracks. (b) PA-34 series airplanes (1) Remove the inspection plate on bottom of wing which is located adjacent to the aileron bellcrank and aft of the outboard fuel tank. (2) Inspect as in paragraph (a)(2) around first and second lightening holes outboard of the fish mouth at the main spar splice. (3) Inspect the lightening flange radii for cracks. (c) If square die stamping mark is evident on the aft side of spar only and there are no cracks in the lightening hole flange radii, no further action is required. (d) If square die stamping mark is evident on forward side of spar and/or if there are cracks in the lightening hole flange, replace the outboard spar with a serviceable spar of the same part number or repair in a method approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. (e) Report positive findings from paragraph (d) to Chief, Engineering and Manufacturing Branch, FAA SouthernRegion within 10 days of inspection. (Reporting approved by the Bureau of the Budget under BOB No. 04-R0174.) This amendment becomes effective September 7, 1974.
74-18-06: 74-18-06 PIPER: Amendment 39-1932. Applies to PA-28-235 airplanes Serial numbers 28-7310001 to 28-7310064 inclusive and 28-7410001 to 28-7410039 inclusive certificated in all categories. Compliance required within the next 50 hours' time in service after the effective date of this AD, unless already accomplished. To detect and replace erroneous fuel quantity placards, accomplish the following: 1. Inspect the fuel quantity placards located on both aircraft wing (inboard main) fuel tanks and replace each placard that does not state "Usable fuel capacity 24 gallons", with Placard Piper Part Number 69669-64V or an equivalent placard approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. 2. Inspect the fuel selector placard (in the aircraft cabin) and replace the placard if it does not state "24 gallons" at both the left main and the right main positions with Placard Piper Part Number 69672-00V or an equivalent placard approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. Piper Service Letter No. 720 pertains to this same subject. This amendment becomes effective August 28, 1974.
2007-12-20: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as electrical arcing due to chafing between a bonding cable and electrical wires in the 120 VU (volt unit) electrical harness, causing the loss of some instruments and loss of one hydraulic circuit pressure (i.e., loss of pressure of one hydraulic circuit). We are issuing this AD to require actions to correct the unsafe condition on these products.
2001-02-05: This amendment supersedes an existing airworthiness directive (AD), applicable to Model CL-604 variant of Bombardier Model Canadair CL-600-2B16 series airplanes modified in accordance with certain Supplemental Type Certificates, that currently requires that the fuel service panel maintenance light on the fuel service panel be disconnected. This amendment requires modification of the wiring of the fuel port flood light (which is the name given to the fuel service panel maintenance light in the service bulletin that describes the wiring modification). This amendment is prompted by a report indicating that an electrical spark was noted when the fuel cap chain contacted the fuel port flood light housing of the fuel service panel. The actions specified by this AD are intended to prevent electrical sparks from a grounded object from coming into contact with the fuel port flood light housing of the fuel service panel, which could result in a fuel fire due to the proximity of thefuel service panel to the fuel port.