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87-08-08 R3:
90-15-12 R1: This amendment revises an existing airworthiness directive (AD), applicable to Boeing Model 727 series airplanes modified by the installation of Pratt and Whitney JT8D-217C or -219 engines in accordance with Valsan STC SA4363NM, that currently requires repetitive inspections of the through-bolt nut for proper torque and for certain other conditions of the through-bolt and nut, and replacement, if necessary. That AD also requires the installation of anti-rotation plates, which constitutes terminating action for the repetitive inspections. This amendment changes the responsible office for approval of an alternative method of compliance. This amendment is prompted by the transfer of the supplemental type certificate. The actions specified in this AD are intended to prevent the nut coming off the through-bolt allowing the through-bolt to migrate out of the engine mount flange and cone bolt and possible separation of the engine.
76-06-05: 76-06-05 BRITTEN NORMAN LTD: Amendment 39-2555. Applies to BN-2A and BN-2A Mark III airplanes certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent inadvertent release of the pilots' seats in the seat tracks, accomplish the following: (a) Within the next 50 hours' time in service after the effective date of this AD, inspect the pilots' seats locking mechanism (Alar P/N NB-99-H-007, or Jetseats P/N JS114) for damage and for short pawls, in accordance with paragraph Nos. 1, 2, 3, and 4 of the section titled "Inspection" of Britten Norman Ltd. Service Bulletin No. BN-2/SB.71, dated June 12, 1974, or an FAA-approved equivalent. (b) If seats with damaged locking parts are found, before further flight, remove damaged parts and install serviceable parts of the same part numbers, or FAA-approved equivalents. (c) If seats with short pawls are found, before further flight, lock the seats in place in accordance with paragraph 5a. of the section titled "Inspection" of Britten Norman Ltd. Service Bulletin No. BN-2/SB.71, dated June 12, 1974, or an FAA-approved equivalent, until compliance with paragraph (d) of this AD is accomplished. (d) Within the next 100 hours' time in service after the effective date of this AD, modify seats with short pawls in accordance with paragraph 5b. of section titled "Inspection" of Britten Norman Ltd. Service Bulletin No. BN-2/SB.71, dated June 12, 1974, or an FAA-approved equivalent. This amendment becomes effective on April 19, 1976.
2020-11-02: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, and EC225LP helicopters. This AD requires revising the Rotorcraft Flight Manual (RFM) for your helicopter and either installing placards or removing the hoist arm. This AD was prompted by a failure of a right- hand (RH) side lateral sliding plug door (sliding door) to jettison. The actions of this AD are intended to address an unsafe condition on these products.
88-25-08: 88-25-08 PIPER: Amendment 39-6087. Applies to Model PA-46-310P (all serial numbers) airplanes certificated in any category. Compliance: Required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent possible catastrophic engine failure accomplish the following: (a) Modify the engine cooling system in accordance with Piper Service Bulletin 892, dated August 24, 1988. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent means of compliance with this AD, if used, must be approved by the Manager, Atlanta Aircraft Certification Office, ACE-115A, Federal Aviation Administration, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. This amendment (39-6087, AD 88-25-08) becomes effective on January 3, 1989.
83-23-03: 83-23-03 BEECH: Amendment 39-4769. Applies to Model 77 (serial numbers WA-1 through WA-312) airplanes, certificated in any category. Compliance: Required within the next 25 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent loss of rudder control or flutter of the rudder, accomplish the following: a) Install the balance weight attach bracket reinforcements provided in Beech Kit 77-4006-1S as identified in Beech Service Instructions No. 1256. b) Airplanes may be flown in accordance with FAR 21.197 to a location where the AD may be accomplished. c) An equivalent means of compliance with this AD may be used, if approved, by the Manager, Wichita Aircraft Certification Office, Room 238, Terminal Building 2299, Mid- Continent Airport, Wichita, Kansas 67209; telephone (316) 269-7000. This amendment becomes effective on November 22, 1983.
2008-12-14: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Analyses of in-service reports revealed that in case of failure of the wings' anti-ice valve, indications of untimely anti-icing with the wings' anti-ice selector on "OFF'' or of insufficient anti-icing with the wings' anti-ice selector on "AUTO'' might not be properly displayed to the flight crew. It may result, on ground, in potential structural damages due to a leading edge overheat, or in-flight, in an insufficient anti-ice power. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
88-13-01: 88-13-01 MITSUBISHI: Amendment 39-5951. Applies to Model MU-2B, MU-2B-10, - 15, -20, -25, -26, -26A, -30, -35, -36, -36A, -40, and -60 (all serial numbers, with or without the SA suffix) airplanes certificated in any category, equipped with Bendix M-4C or M-4D autopilots and/or Bendix electric pitch trim systems. NOTE 1: The serial number of airplanes manufactured in the United States by Mitsubishi (MAI) under TC A10SW are suffixed by "SA." The serial numbers of airplanes manufactured in Japan by Mitsubishi Heavy Industries, Inc. (MHI) under TC A2PC have no suffix. Compliance: Required within the next 200 flight hours or five (5) calendar months, whichever occurs first, unless already accomplished. To minimize the possibility of confusion in autopilot/manual electric pitch trim disconnect/interrupt switch location, accomplish the following: (a) Modify the control yoke in the affected model and serial numbered airplanes as follows: (1) For MU-2B-30 and -35 model airplanes manufactured under TC A2PC equipped with a Japanese Civil Airworthiness Board (JCAB) approved Bendix M-4C autopilot, in accordance with MHI Service Bulletin (S/B) No. 206 dated October 13, 1987, or (2) For all other MU-2B model airplanes equipped with an FAA approved installation of the Bendix M-4C or M-4D autopilots, in accordance with MHI S/B No. 066/22- 006, dated December 18, 1987. (b) For MU-2B-35 and -36 model airplanes with Bendix autopilots installed in accordance with STC SA1693SW and MU-2B-35, -36A, and -60 model airplanes with Bendix M-4D autopilots installed in accordance with approved MAI data, accomplish the following: (1) Insert additional placard data in the LIMITATION section of the Airplane Flight Manual Supplement (AFMS) as follows: "COUPLED AUTOPILOT APPROACHES BELOW 125 KCAS OR 300 FEET AGL NOT PERMITTED." (2) Fabricate and install a permanent red colored placard in full view of the pilot using white colored letters of a minimum of 0.10 inches in height which state: "COUPLED AUTOPILOT APPROACHES BELOW 125 KCAS OR 300 FEET AGL NOT PERMITTED." (c) Insertion of a copy of this AD in the LIMITATIONS section of the AFMS satisfies the requirements of paragraph (b)(1) of this AD. (d) Prior to returning the aircraft to service, accomplish a visual configuration check and system functional ground test, and record successful completion in the appropriate airplane maintenance record as prescribed by FAR 91.173, as follows: (1) Visually verify that: (i) The disconnect/interrupt switch is red in color and located on the outboard horn of the control wheel; and, (ii) The disconnect/interrupt switch is properly labeled as shown in Figure 7 of the MHI S/B No. 206 for A2PC airplanes or as shown in Figure 8 or Figure 9, (as appropriate for the control wheel configuration) of MHI S/B No. 066/22-006 for A10SW airplanes, as applicable; and, (iii) The autopilot circuit breaker is properly labeled. (2) If a manual electric pitch trim system is installed with or without an autopilot system, engage the system and press the trim button to cause the manual pitch trim wheel to rotate, then verify that after each of the following operations is performed the manual pitch trim wheel stops moving when: (i) The disconnect/interrupt switch is depressed; (ii) The Master Electric Power switch is positioned to "OFF;" (iii) The Radio Master switch is positioned to "OFF" (if installed and so configured), (iv) The electric trim circuit breaker is pulled. (On some MU-2B airplanes without an electric trim circuit breaker, the autopilot circuit breaker/switch is used to disconnect the system in lieu of the electric trim circuit breaker.) NOTE 2: It is very important to verify that the manual pitch trim wheel stops moving after each of the above operations. (3) If an autopilot system is installed, with or without a manual electric trim system, engage the system and then verify: (i) That the autopilot system canbe overpowered by pushing or pulling on the control yoke; and, (ii) That, while overpowering the autopilot, the manual pitch trim wheel stops moving when each of the following operations is performed: (A) The disconnect/interrupt switch is depressed; (B) The autopilot master switch is positioned to "OFF" (On some MU-2B airplanes not equipped with an autopilot master switch beside the controller, the radio master switch must be used to disconnect the system in lieu of the autopilot master switch); (C) The autopilot circuit breaker is pulled. NOTE 3: It is very important that the manual pitch trim wheel stops moving after each of these operations. (e) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (f) An equivalent method of compliance with this AD may be used on the MHI airplanes, if approved by the Manager, Western Aircraft Certification Office, ANM-170W, FAA, P.O. Box 92007, Worldway Postal Center, Los Angeles, California 90009-2003; and on the MAI airplanes, if approved by the Manager, Wichita Aircraft Certification Office, ACE-115W, FAA, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Beech Aircraft Corporation (Licensee to Mitsubishi), P.O. Box 85, Wichita, Kansas 67201; Telephone (316) 681-7279; or may examine the documents referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment, 39-5951, becomes effective on July 11, 1988.
92-08-05: 92-08-05 BOEING: Amendment 39-8216. Docket No. 91-NM-249-AD.\n\n\tApplicability: Model 767 series airplanes listed in Boeing Service Bulletin 767-25-0160, dated July 18, 1991; and airplane having variable number VF093; certificated in any category.\n\n\tCompliance: Required within 60 days after the effective date of this AD, unless previously accomplished.\n\n\tTo prevent the galley from coming loose during an emergency landing, accomplish the following:\n\n\t(a)\t Replace the aft galley tie rods in accordance with Boeing Service Bulletin 767-25-0160, dated July 18, 1991; or Revision 1, dated February 13, 1992.\n\n\t(b)\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO.\n\n\t(c)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.\n\n\t(d)\tThe modification shall be done in accordance with Boeing Service Bulletin 767-25-0160, dated July 18, 1991; or Revision 1, dated February 13, 1992; which include the following list of effective pages:\n\nService Bulletin\tPage Number\tRevision Level\tDate\n\n767-25-0160\t1-9\tOriginal\tJuly 18, 1991\nOriginal\n\n767-25-0160\t1, 3, 4, 5\t1\tFebruary 13, 1992 \nRevision 1\n\t2, 6, 7, 8, 9\tOriginal\tJuly 18, 1991\n\nThis 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at theOffice of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC.\n\n\t(e)\tThis amendment becomes effective on June 23, 1992.
2020-09-12: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-400 series airplanes. This AD was prompted by a report that certain elevator power control unit (PCU) arm fittings have nonconforming fillet radii. This AD requires an inspection for affected elevator PCU assemblies, inspections of affected elevator PCU arm fittings for nonconforming fillet radii and cracks, replacement if necessary, and re- identification of the affected elevator PCU assemblies. The FAA is issuing this AD to address the unsafe condition on these products.