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92-18-08: 92-18-08 BENDIX/KING: Amendment 39-8352. Docket No. 92-CE-07-AD. Applicability: KAP 150/KFC 150 Flight Control Systems installed on Piper Models PA-46-310P and PA-46-350P airplanes, certificated in any category. Compliance: Required within the next 90 calendar days after the effective date of this AD, unless already accomplished. To prevent moisture from entering the electronic circuit board through the pitch servo, which could possibly lead to undesired movement of the elevator, accomplish the following: (a) Install a pitch servo cover kit, part number 050-03007-0000, in accordance with the instructions in Bendix/King Installation Bulletin No. 312, dated March 19, 1990. NOTE 1: Installation of the yaw servo cover kit, part number 050-03006-0000, which is referenced in Bendix/King Installation Bulletin No. 312, is not required by this AD action. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished. (c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office. (d) The installation required by this AD shall be done in accordance with Bendix/King Installation Bulletin No. 312, dated March 19, 1990. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Bendix/King, Product Support Department, 400 N. Rogers Road, Olathe, Kansas 66062-0212. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. (e) This amendment becomes effective on October 2, 1992.
92-15-15: 92-15-15 PIPER AIRCRAFT CORPORATION: Amendment 39-8309. Docket No. 91-CE-97-AD. Applicability: Model PA-36-300 airplanes (serial numbers 36-7760001 through 36-8160023) and Model PA-36-375 airplanes (serial numbers 36-7802001 through 36-8302025), certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent separation of the engine from the airplane because of cracks at the engine mount attach points, accomplish the following: (a) Within the next 100 hours time-in-service (TIS) after the effective date of this AD, inspect the welds and areas adjacent to the welds at each engine mount attach point for cracks in accordance with the "INSTRUCTIONS: Inspection" section of Piper Service Bulletin (SB) No. 828, dated April 7, 1986. (1) If cracks are found, prior to further flight, install gusset attachments in accordance with the "INSTRUCTIONS: Repair" section of Piper SB No. 828, dated April 7, 1986. (2) If cracks are not found, reinstall the forward side panels and reinspect at intervals not to exceed 100 hours TIS. NOTE 1: The compliance times referenced in this AD take precedence over those cited in the referenced service information. (b) The installation described in paragraph (a)(1) of this AD may be accomplished at any time as terminating action for the repetitive inspections required by this AD. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. (e) The inspections and possible installation required by this AD shall be done in accordance with Piper Service Bulletin No. 828, dated April 7, 1986. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 32960. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC. (f) This amendment becomes effective on August 24, 1992.
92-15-14: 92-15-14 PIPER AIRCRAFT CORPORATION: Amendment 39-8308. Docket No. 91-CE-98-AD. Applicability: Model PA-46-310P airplanes (serial numbers (S/N) 46-8408001 through 46-8608067 and S/N 4608001 through 4608140) and Model PA-46-350P airplanes (S/N 4622001 through 4622118), certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent failure of the air-driven attitude gyro and autopilot systems caused by an undetected low vacuum, accomplish the following: (a) Install vacuum gauge markings in accordance with the INSTRUCTIONS section in Part II of Piper Service Bulletin No. 947A, dated October 29, 1991. (b) Incorporate whichever of the following reports that is applicable into the limitations section of the Airplane Flight Manual, and operate the airplane accordingly: Model Report PA-46-310P REPORT: VB-1200, page 2-4, Issued: January 11, 1984, Revised: October 14, 1991 PA-46-310P REPORT: VB-1300, page 2-4, Issued: July 1, 1986, Revised: October 14, 1991 PA-46-350P REPORT: VB-1332, page 2-4, Issued: June 15,1988, Revised: October 14, 1991 (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. (e) The installation required by this AD shall be done in accordance with Piper Service Bulletin No. 947A, dated October 29, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 32960. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC. (f) This amendment becomes effective on August 22, 1992.
92-13-05: 92-13-05 PIPER AIRCRAFT CORPORATION: Amendment 39-8275. Docket No. 91-CE-99-AD. Applicability: Model PA-34-200 airplanes (serial numbers 34-7250001 through 34- 7450220) and Model PA-34-200T airplanes (serial numbers 34-7570001 through 34-8170092), certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent loss of control of the airplane during landing operations because of the inability to fully extend the nose landing gear, accomplish the following: (a) Inspect the nose gear centering spring assembly and determine whether a clevis-head bolt or hex-head bolt is installed. (b) If a part number (P/N) 400-910 clevis-head bolt is installed, ensure that it is correctly installed in accordance with paragraph 2 of the INSTRUCTIONS section of and Sketch "A" in Piper Service Bulletin (SB) No. 893, dated October 11, 1988. (1) If the bolt is correctly installed, incorporate placard P/N 582-943 in accordance with paragraph 6(C) of the INSTRUCTIONS section of Piper SB No. 893, dated October 11, 1988. (2) If the bolt is incorrectly installed, disassemble and reinstall in accordance with paragraphs 3 through 6 of the INSTRUCTIONS section of Piper SB No. 893, dated October 11, 1988, and incorporate placard P/N 582-943 in accordance with paragraph 6(C) of the INSTRUCTIONS section of Piper SB No. 893, dated October 11, 1988. (c) If a hex-head bolt or a clevis-head bolt that is not P/N 400-910 is installed, replace with a P/N 400-910 clevis-head bolt in accordance with paragraphs 3 through 6 of the INSTRUCTIONS section of Piper SB No. 893, dated October 11, 1988, and incorporate placard P/N 582-943 in accordance with paragraph 6(C) of the INSTRUCTIONS section of Piper SB No. 893, dated October 11, 1988. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. (f) The inspection, installations, and replacements required by this AD shall be done in accordance with Piper Service Bulletin No. 893, dated October 11, 1988. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained fromthe Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 32960. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC. (g) This amendment becomes effective on August 21, 1992.
92-13-04: 92-13-04 PIPER AIRCRAFT CORPORATION: Amendment 39-8274. Docket No. 91-CE-95-AD. Supersedes AD 90-23-18, Amendment 39-6782. Applicability: Models PA-23-150 and PA-23-160 airplanes (serial numbers 23-1 through 23-2046) that have not been modified by the installation of a dual fuel drain kit, part number 765- 363, in accordance with the instructions in Part II of Piper Service Bulletin No. 827A, dated November 4, 1988, certificated in any category. Compliance: Required within the next 180 calendar days after the effective date of this AD, unless already accomplished. To prevent rough engine operation or complete power interruption caused by water contamination in the fuel, accomplish the following: (a) Incorporate paragraphs 1 through 5 of the Aircraft Systems Operating Instructions that are contained in Part I of Piper Service Bulletin (SB) No. 827A, dated November 4, 1988, into the Owner Handbook and Pilots Operating Manual. NOTE 1: Paragraphs 6 and 7of the Handling and Servicing instructions that are contained in Part I of Piper SB No. 827A, dated November 4, 1988, are covered by AD 88-21-07 R1. NOTE 2: If more than one tablespoon of water is found in the fuel during preflight draining procedures, then it is recommended that fuel draining procedures be repeated after the wings are rocked or the airplane has been put in a nose-down attitude. If water continues to be found, drainage and inspection of the fuel tanks is recommended. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. (d) The procedures required by this AD shall be done in accordance with Piper Service Bulletin No. 827A, dated November 4, 1988. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Piper Aircraft Corporation, Customer Services, 2926 Piper Drive, Vero Beach, Florida 32960. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, D.C. (e) This amendment supersedes AD 90-23-18, Amendment 39-6782. (f)This amendment becomes effective on August 21, 1992.
92-13-07: 92-13-07 PIPER AIRCRAFT CORPORATION: Amendment 39-8277. Docket No. 91-CE-101-AD. Applicability: Model PA-46-310P airplanes (serial numbers (S/N) 46-8408001 through 46-8608067 and S/N 4608001 through 4608140) and Model PA-46-350P airplanes (S/N 4622001 through 4622109), certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent structural deterioration because of loose empennage rivets, accomplish the following: (a) Replace the empennage countersunk rivets indicated in Piper Service Bulletin (SB) No. 944, dated October 5, 1990, with universal head rivets of a larger diameter in accordance with the INSTRUCTIONS section of Piper SB No. 944. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. (d) The replacements required by this AD shall be done in accordance with Piper Service Bulletin No. 944, dated October 5, 1990. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 32960. Copies may be inspected at the FAA, CentralRegion, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC. (e) This amendment becomes effective on August 21, 1992.
92-13-06: 92-13-06 PIPER AIRCRAFT CORPORATION: Amendment 39-8276. Docket No. 91-CE-89-AD. Applicability: The following model airplanes, certificated in any category: Models Serial Numbers PA-46-310P 46-8408001 through 46-8608067 and 4608001 through 4608140 PA-46-350P 4622001 through 4622117 Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent sudden pitch change related to a jammed trim tab, which could result in loss of control of the airplane, accomplish the following: (a) Visually inspect the elevator trim cable guide tube for severance. Severance is defined as any cut, break, or division of the elevator trim cable guide tube (generally performed to gain access to the trim cable turnbuckles). (b) If severance is found, prior to further flight, splice the elevator trim cable guide tube and install an external sleeve in accordance with the instructions in Elevator Trim Cable Guide Tube Splice Kit, Piper Part Number 766-272. NOTE 1: Revised maintenance procedures on gaining access to the trim cable turnbuckles may be obtained from the manufacturer at the address specified in paragraph (e) of this AD. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained fromthe Atlanta Aircraft Certification Office. (e) The possible modification required by this AD shall be done in accordance with Elevator Trim Cable Guide Tube Splice Kit, Piper Part Number 766-272, which is referenced in Piper Service Bulletin No. 953, dated October 29, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 32960. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC. (f) This amendment becomes effective on August 21, 1992.
92-08-04: 92-08-04 PIPER AIRCRAFT CORPORATION: Amendment 39-8215. Docket No. 91-CE-71-AD. Supersedes AD 90-17-04, Amendment 39-6674. Applicability: Model PA34-200 airplanes (serial numbers (S/N) 34-7250001 through 34-7450220), Model PA34-200T airplanes (S/N 34-7570001 through 34-8170092), and Model PA34-220T airplanes (S/N 34-8133001 through 34-8533012), certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent failure of the torque tube fitting and possible loss of rudder control, accomplish the following: (a) Within the next 50 hours time-in-service (TIS) after September 14, 1990 (the effective date of AD 90-17-04, Amendment 39-6674), inspect to determine whether the rudder torque tube fitting is steel or aluminum. (1) If steel, inspect for proper attachment, and check the bolt torque in accordance with the criteria and instructions in Piper Service Bulletin (SB) No. 899, dated February 10, 1989. If fitting is improperly attached and bolt torque is incorrect, prior to further flight, properly attach fitting and torque to proper criteria as specified in and in accordance with the instructions in Piper SB No. 899, dated February 10, 1989. (2) If aluminum, prior to further flight, replace with steel fitting in accordance with the instructions in Piper SB No. 899, dated February 10, 1989. (b) If the steel fitting required by paragraph (a)(2) of this AD has been ordered but is not available, prior to further flight, accomplish the following: (1) Visually inspect the aluminum fitting for corrosion. If any evidence of corrosion is found, remove and treat the corroded area in accordance with AC 43-13.1A. (2) Dye penetrant inspect the aluminum fitting for cracks. If found cracked, replace with an aluminum fitting found to be free from cracks and corrosion. (3) Visually inspect the aluminum fitting for proper attachment, cracks, and corrosion at intervals not to exceed 50hours TIS. (i) If fitting is found improperly attached or hardware is found loose, properly attach fitting in accordance with the instructions in Piper SB No. 899, dated February 10, 1989. (ii) If any evidence of corrosion is found, remove and treat the corroded area in accordance with AC 43-13.1A. (iii) If found cracked, replace with aluminum fitting found to be free from cracks and corrosion in accordance with the installation instructions in Piper SB No. 899, dated February 10, 1989. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. (e) The checks and installations required by this AD shall be done in accordance with Piper Service Bulletin No. 899, dated February 10, 1989. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Piper Aircraft Corporation, Customer Services, 2926 Piper Drive, Vero Beach, Florida 32960. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC. (f) This amendment (39-8215) supersedes AD 90-17-04, Amendment 39-6674. (g) This amendment (39-8215) becomes effective on May 15, 1992.
2023-12-18: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-8 and -8F series airplanes. This AD was prompted by reports of cracking in stringers and splice fittings located at stringer splices at multiple body stations. This AD requires an inspection of each free flange of the stringers at the stringer splice for the presence of radius fillers at fastener locations, an inspection for cracking of the stringers and stringer splice fittings at certain stringer splice locations, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2023-12-17: The FAA is superseding Airworthiness Directive (AD) 2022-19-03 which applied to Pilatus Aircraft Ltd. (Pilatus) Model PC-12, PC-12/45, PC-12/47, and PC-12/47E airplanes. AD 2022-19-03 required incorporating new revisions to the airworthiness limitation section (ALS) of the existing airplane maintenance manual (AMM) or Instructions for Continued Airworthiness (ICA) to establish a 5-year life limit for certain main landing gear (MLG) actuator bottom attachment bolts and new life limits for the rudder bellcrank. Since the FAA issued AD 2022- 19-03, the FAA determined that new or more restrictive tasks and 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.