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93-23-13: 93-23-13 PIPER AIRCRAFT CORPORATION: Amendment 39-8749. Docket No. 93-CE- 32-AD. Supersedes AD 93-02-13, Amendment 39-8496 which superseded AD 92-26-02, Amendment 39-8429 and AD 80-20-04, Amendment 39-3925. Applicability: Model PA31, PA31-300, and PA31-325 airplanes (serial numbers 31-2 through 31-8012089), and Model PA31-350 airplanes (serial numbers 31-5001 through 31-8052199), certificated in any category. Compliance: Required initially within the next 50 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished (compliance with AD 80-20-04, Amendment 39-3925, AD 92-26-02, Amendment 39-8429, or AD 93-02-13, Amendment 39- 8496), and thereafter as indicated. To prevent improper sealing of the baffle seals to the engine cowling, which could result in high engine operating temperatures, accomplish the following: (a) Visually inspect the engine baffle seals for proper positioning by using a light and looking in air inlets andaccess doors to ensure that forward seals and lower aft seals are all facing forward and not blown back. (b) If baffle seals are improperly positioned (blown back), prior to further flight, accomplish one of the following: (1) Install thicker baffle seals in accordance the instructions to Piper Kit 764 093, dated November 10, 1980; or NOTE 1: Piper Kit 764 093 includes the entire baffle assembly consisting of both baffles and baffle seals. Replacing the baffle seals included in this kit is the only requirement of paragraph (b)(1) or (c)(2) of this AD. (2) Install baffles of one of the following materials in accordance with Figure 1 of this AD: (i) Brown Aircraft Supply Engine Baffle Material, part number (P/N) BA71646-1 and BA71646-2, temperature range -40 to 300 degrees Fahrenheit. (ii) Brown Aircraft Supply, Fiber Reinforced High Temperature Silicone Engine Baffle Material (red), P/N T-95182, temperature range -65 to 550 degrees Fahrenheit; and(iii) Brown Aircraft Supply, Engine Baffle Material, P/N T-8071, temperature range -40 to 300 degrees Fahrenheit. FIGURE 1 BROWN AIRCRAFT SUPPLY BAFFLE SEAL INSTALLATION PROCEDURES 1. Inspect the existing baffle seals through the front of the cowl to ensure existing seals are of sufficient length to provide at least 1-inch of contact with upper and lower cowls when properly positioned. Mark areas that need lengthening, and note the minimum length needed to meet requirements. 2. Remove the cowls in accordance with the applicable maintenance manual. Remove rivets, wire, and screws, as applicable, that secure baffle seals (fabric) to the engine baffles (metal). Retain any metal strips that are used to secure seals to the engine baffles. 3. Remove existing baffle seals and lay against Brown Aircraft Supply baffle seal material. 4. Cut new seals around the layout, ensuring that seals are lengthened as noted in procedure 1. 5. Reattach new seals to the engine baffles with the original screws, rivets, and wires, as applicable, or new hardware of the same part number. NOTE: The front upper cowl baffle seal is most critical, especially at the inboard and outboard corners. If the old material can be removed intact, and the curve can be transferred to the new flat material, then it may not be necessary to slit the material where it curves from vertical to horizontal contact with the cowl. If the curve requires a slit in the material at the corner, then it is recommended that the slit be tied with ty-raps or safety wire to ensure contact with the cowl around the radius. (c) If baffle seals are properly positioned (not blown back), within the next 50 hours TIS, accomplish one of the following: (1) Reinspect the engine baffle seals as specified in paragraph (a) of this AD, and continue to reinspect thereafter at intervals not to exceed 50 hours TIS; or (2) Install thicker baffle seals as specified in either paragraph (b)(1) or (b)(2) of this AD. This installation terminates the inspection requirements of this AD. (d) The inspections required by this AD may be performed by the owner/operator holding at least a private pilot certificate as authorized by FAR 43.7, and must be entered into the aircraft records showing compliance with this AD in accordance with FAR 43.11. (e) 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. (f) 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 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. (g) The installation (using Piper Aircraft Corporation parts) required by this AD shall be done in accordance with Piper Kit 764 093, dated November 11, 1980. 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, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment (39-8749) supersedes AD 93-02-13, Amendment 39-8496 which superseded AD 92-26-02, Amendment 39-8429 and AD 80-20-04, Amendment 39-3925. (i) This amendment becomes effective on January 21, 1994.
94-01-05: This amendment adopts a new airworthiness directive (AD) that applies to certain Allied Signal Aerospace Company, Air Transport Avionics (Allied Signal) Traffic Alert and Collision Avoidance System (TCAS) II processors that are installed on aircraft. This action requires replacing the existing TCAS II processor with a new processor that incorporates updated computer logic. The development of candidate enhancements to TCAS II logic that improves its utility and increases its overall operational acceptance prompted the proposed action. The actions specified by this AD are intended to prevent collisions or near misses caused by incompatibility between the TCAS II processors and the current air traffic control system.
93-06-02: 93-06-02 PIPER AIRCRAFT CORPORATION: Amendment 39-8527. Docket No. 92- CE-48-AD. Applicability: Models PA-23-150, PA-23-160, PA-23-235, and PA-23-250 airplanes (all serial numbers) that have Met-Co-Aire 48-gallon fuel tip tanks installed in accordance with Supplemental Type Certificate SA1480WE, certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. NOTE 1: The compliance time referenced in this AD takes precedence over that referenced in Met-Co-Aire (MCA) Service Bulletin No. 23-001, dated July 1992. To prevent fuel leakage and possible fire, which could result in passenger injury, accomplish the following: (a) Replace any existing Parker "Push-Lok" flexible fuel hose, MCA part number (P/N) 11059-4 or Parker-Hannifin P/N 801-6/250PSI, with a Stratoflex hose, MCA P/N 11059-10 or Parker-Hannifin P/N 130001-6S-0154, in accordance with the instructionsin Met-Co-Aire Service Bulletin No. 23-001, dated July 1992. (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, Los Angeles Aircraft Certification Office, FAA, 3229 E. Spring Street, Long Beach, California 90806-2425. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles 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 Los Angeles Aircraft Certification Office. (d) The replacement required by this AD shall be done in accordance with Met-Co-Aire Service Bulletin No. 23-001, datedJuly 1992. 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 Met-Co-Aire, P.O. Box 2216, Fullerton, California 92633. 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. (f) This amendment becomes effective on May 12, 1993.
2002-10-08: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-80E1 series turbofan engines installed on Airbus Industrie A330 series airplanes. This action requires initial and repetitive thrust reverser inspections and checks, and allows extended threshold and repetitive inspection intervals for certain inspections if an optional double p-seal configuration is installed. This amendment is prompted by reports of service-induced hardware deterioration that reduces the overall thrust reverser system protection against inadvertent deployment, which can result in loss of control of the airplane. The actions specified in this AD are intended to prevent inadvertent in-flight thrust reverser deployment, which can result in loss of control of the airplane.
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.