Results
93-24-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T93-24-51 that was sent previously to all known U.S. owners and operators of all Airbus Model A310 and A300-600 series airplanes by individual telegrams. This AD requires repetitive operational tests of feel and limitation computers (FLC) 1 and 2. This amendment is prompted by a report that the pitch control on a Model A300-600 series airplane operated with stiffness. The actions specified by this AD are intended to prevent stiff operation of the pitch control and undetected loss of rudder travel limitation function.
2008-07-01: The FAA is superseding an existing airworthiness directive (AD) for certain Turbomeca Arriel 1B, 1D, 1D1, and 1S1 turboshaft engines. That AD currently requires initial and repetitive position checks of the gas generator 2nd stage turbine blades on all Turbomeca Arriel 1B, 1D, 1D1, and 1S1 turboshaft engines. That AD also currently requires initial and repetitive replacements of 2nd stage turbines on 1B, 1D, and 1D1 engines only. This AD requires adding a 3,000 hour life limit to Arriel 1B 2nd stage turbine blades. This AD results from reports of failures of second stage turbine blades. We are issuing this AD to prevent failures of the 2nd stage turbine blades, which could result in uncommanded in-flight engine shutdown, and subsequent forced autorotation landing or accident. DATES: This AD becomes effective April 30, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of April 30, 2008.The Director of the Federal Register previously approved the incorporation by reference of Turbomeca Mandatory Alert Service Bulletins A292 72 0809, Update 1, dated October 4, 2005; and A292 72 0810, dated March 24, 2004; as of February 28, 2006 (71 FR 3754, January 24, 2006).
78-12-08: 78-12-08 AVCO LYCOMING: Amendment 39-3239. Applies to O-320-H series engines Serial Numbers L-101-76 through L-3829-76, L-3831-76, L-3843-76 through L-3859-76, L-3864-76, L-3866-76, L-3871-76, L-3902-76 through L-3907-76 and all O-320-H series engines overhauled (Remanufactured by Lycoming) before March 24, 1978. Compliance required within the next 10 hours in service, unless already accomplished. a. To prevent oil pump failures, remove, inspect and alter the oil pump body and replace the oil pump driving impeller with driving impeller P/N LW-15998 and the oil pump driven impeller with driven impeller P/N LW-15999 in accordance with AVCO Lycoming Service Bulletin No. 423 dated March 24, 1978, or FAA approved equivalent. b. Equivalent method of compliance must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective June 20, 1978.
2020-11-06: The FAA is adopting a new airworthiness directive (AD) for Pilatus Aircraft Ltd. Model PC-6, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/ B2-H4, PC-6/C-H2, PC-6/C1-H2, PC-6-H1, and PC-6-H2 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 flap actuator taper pins that were not swaged during the manufacturing process. The FAA is issuing this AD to require actions to address the unsafe condition on these products.
92-27-05: 92-27-05 PIPER AIRCRAFT CORPORATION: Amendment 39-8438. Docket No. 91- CE-14-AD. \n\n\tApplicability: PA-31 Series airplanes (all models and serial numbers), certificated in any category. \n\n\tCompliance: Required the next time the aileron cables are disconnected for any reason, but no later than 12 calendar months after the effective date of this AD, unless already accomplished. \n\n\tTo prevent improper connection of the aileron control systems, which could result in loss of lateral control of the airplane, accomplish the following: \n\n\t(a)\tUsing red enamel paint, color code the aileron balance cable and the bellcrank lug of both aileron control systems in accordance with Figure 1 of this AD. \n\n\t(b)\tSpecial 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. \n\n\t(c)\tAn 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. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. \n\n\t(d)\tAll persons affected by this directive may examine any information that is applicable to this AD at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. \n\n\t(e)\tThis amendment becomes effective on January 29, 1993. \n\n\n\t\t\t\tFIGURE 1 AD 92-27-05\n\t\tVIEW LOOKING THRU TOP WING SKIN (LEFT WING)\n\t\t\t\t RIGHT WING OPPOSITE
76-24-05: 76-24-05 ROLLS-ROYCE (1971) LIMITED: Amendment 39-2781. Applies to Rolls-Royce Bristol Viper Mk 601-22 engines installed, or being held for installation on Hawker Siddeley/Beechcraft Hawker Model DH/BH-125 series airplanes, certificated in all categories. Compliance is required within the next 150 hours time in service after the effective date of this AD, unless already accomplished. To prevent possible turbine disc damage, replace the inner exhaust turbine cone assembly in accordance with the "Accomplishment Instructions" of Rolls-Royce Alert Service Bulletin No. 72-A69, dated May 1976, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, APO New York, N.Y. 09667. This amendment becomes effective December 14, 1976.
92-02-14: 92-02-14 AIRBUS INDUSTRIE: Amendment 39-8150. Docket 91-NM-255-AD. Applicability: Model A320 series airplanes through manufacturer's serial number 175, inclusive, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the overwing emergency escape slides to deploy, accomplish the following: (a) Within 50 hours time-in-service after the effective date of this AD, perform an inspection of the flexible control cables on the right-hand and left-hand overwing emergency escape slides to ensure that the flexible control assembly on each overwing escape slide is correctly installed, in accordance with Airbus Industrie All Operator Telex (AOT) 25-02, dated May 16, 1991. (1) If each flexible control assembly is correctly installed, no further action is required. (2) If a flexible control assembly is incorrectly installed, prior to further flight, reconnect the assembly, in accordance with the AOT.(b) An 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, Standardization Branch, ANM-113, 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, Standardization Branch, ANM-113. (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) The inspections and reconnections of the flexible control assemblies and release cable assemblies required by this AD shall be done in accordance with Airbus Industrie All Operator Telex 25-02, dated May 16, 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. Copies may be inspected at the FAA, Transport Airplane Directorate, Standardization Branch, ANM-113, 1601 Lind Avenue S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. (e) This amendment (39-8150, AD 92-02-14) becomes effective on March 2, 1992.
77-07-09: 77-07-09 AVIONS MARCEL DASSAULT/BREGUET AVIATION (AMD/BA): Amendment 39-2867. Applies to Falcon 10 airplanes, certificated in all categories, equipped with Grumman tailpipe, P/N F10A5B10003-7, installed without back-up ring, P/N F10A5B10606-11. Compliance is required as indicated, unless already accomplished. To prevent the possible loss of the tailpipe, accomplish the following: (a) For tailpipes having more than 750 hours time in service on the effective date of this AD, comply with paragraph (c) of this AD within 90 days or 150 hours time in service after the effective date of this AD, whichever occurs first. (b) For tailpipes having 750 hours or less time in service on the effective date of this AD, comply with paragraph (c) of this AD prior to the accumulation of 900 hours total time in service. (c) Replace tailpipe, P/N F10A5B10003-7, with a new part of the same part number, or with a serviceable part of improved design, P/N F10A5RDB20217-3, and in either case install with back-up ring P/N F10A5B10606-11. (Falcon 10 Service Bulletin No. 0129, dated December 21, 1976, covers this subject.) This amendment becomes effective April 18, 1977.
96-26-03: This amendment supersedes an existing airworthiness directive (AD), applicable to all Fokker Model F28 Mark 0070 and 0100 series airplanes, that currently requires a revision to the Airplane Flight Manual (AFM) that will enable the flightcrew to determine if the thrust reversers are properly stowed and locked prior to take-off. In addition, the existing AD requires a revision to the maintenance program to incorporate instructions to perform checks of the thrust reverser system and correct thrust reverser malfunctions. That AD was prompted by results of a review, which indicated that a potential latent failure of the secondary lock actuator switch 1 of the thrust reverser system in the open position may occur, in addition to the potential failure of the secondary lock relay 1 in the energized position. This new AD adds a requirement to accomplish new modifications that will serve as terminating actions for the revisions to the AFM and maintenance program, and new repetitivechecks of the thrust reverser system. The actions specified in this AD are intended to ensure protection against inadvertent deployment of the thrust reversers during flight.
76-07-05: 76-07-05 BOEING: Amendment 39-2569. Applies to all Boeing Model 727 series airplanes, certificated in all categories, which are equipped with Boeing P/N 65-18949-1 nose landing gear release mechanism torsion shafts not affected by AD 73-26-06. Compliance required as indicated. \n\tTo prevent failure of the nose landing gear release mechanism torsion shaft and a resulting possible gear-up landing, accomplish the following: \n\tA.\tWithin the next 750 landings after the effective date of this AD, unless accomplished within the last 750 landings, and thereafter at intervals not to exceed 1,500 landings for shafts inspected in accordance with the ultrasonic inspection procedures or 2,400 landings for shafts inspected in accordance with the magnetic particle inspection procedures, inspect the P/N 65- 18949-1 shafts, reworked and nonreworked, which have accumulated 8,000 or more total landings since reworked or new, respectively, on or after the effective date of this AD, per paragraph Bbelow until the shaft is replaced per paragraph C. \n\tB.\tInspect the torsion shaft bearing surface in accordance with the ultrasonic or magnetic particle inspection procedures specified in paragraph III of Boeing Service Bulletin No. 727-32-238, or later FAA approved revisions, or inspect in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. Shafts found cracked must be replaced prior to further flight, per paragraph C or with either one of the following: \n\t\t1.\tA nonreworked P/N 65-18949-1 shaft which has accumulated less than 8,000 landings. (Upon accumulation of 8,000 landings the inspection requirements of paragraph A above apply); or \n\t\t2.\tAn uncracked shaft, P/N 65-18949-1, which has been reworked once in accordance with Boeing Service Bulletin No. 727-32-203, Revision 3, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. These shafts are subject to the inspection provisions of paragraph A upon accumulation of 8,000 landings after initial rework. Additional rework will not thereafter exempt the shaft from the inspection requirements. \n\tC.\tInstallation of a new improved shaft, P/N 65-86496-1, and associated parts in accordance with Boeing Service Bulletin Nos. 727-32-205, or 727-32-223, or later FAA approved revisions, or an equivalent installation approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, constitutes terminating action of this AD. \n\tD.\tFor the purpose of this AD, when conclusive records are not available to show the number of landings accumulated by a particular shaft, the number of landings may be computed by dividing the airplane time in service since the shaft was installed in the airplane by the operator's fleet average time per flight for his Model 727 airplanes. \n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made apart hereof pursuant to 5 U.S.C. 552(a)(1). \n\tAll persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. The documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98124. The documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington.\n \n\tThis amendment becomes effective May 11, 1976.
90-02-11: 90-02-11 PIPER: Amendment 39-6455. Applicability: Models PA-42, PA-42-720, and PA-42-720R (all serial numbers) 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 preclude premature deterioration of the engine which could result in possible engine failure, accomplish the following: (a) Insert a copy of this AD in the Pilots Operating Handbook and FAA Approved Airplane Flight Manual (POH/AFM) for the applicable airplane and operate in accordance with the revised limitation: (1) For the Model PA-42 POH/AFM, revise the POH/AFM as follows: Insert Revision 8 of LK 1213 into the POH/AFM. (2) For the Models PA-42-720 and PA-42-720R, revise the POH/AFM as follows: (i) For the Model PA-42-720, insert Revision 7 of LK 1394 or VB 1314 into the POH/AFM. (ii) For the Model PA-42-720R, insert Revision 6 of LK 1485 into the POH/AFM. (b) The following annotation of the applicable pages of the POH/AFM may be accomplished in lieu of complying with paragraph (a). Locate the paragraph entitled "Fuel Specifications" or "Fuel" in the Limitations Section of the POH/AFM. In the first sentence of this paragraph, block out with permanent black ink the words "hot section inspections." Place 1/6 inch wide white self-adhesive correction tape over these blocked out words and type the following words "engine overhaul periods" on the correction tape. (c) The requirements of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by this person. The person accomplishing these actions must make the appropriate airplane maintenance record entry as prescribed by FAR 43.9 and FAR 91.173. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) An alternate method of compliance or adjustment of the compliance time which provides an equivalent level of safety, may be approved by the Manager, Atlanta Certification Office, Federal Aviation Administration, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. NOTE: The request should be forwarded through an FAA Maintenance Inspector, who will may add comments and send it to the Manager, Atlanta Aircraft Certification Office. All persons affected by this directive may obtain copies of the documents referred to herein upon request to the Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 32960, or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6455, AD 90-02-11) becomes effective on February 8, 1990.
2008-13-02: 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: Cracks have been found in the propeller blades and propeller hubs, for which ongoing controlling actions issued by the propeller TC [type certificate] holder (McCauley Propeller Systems) have been mandated by FAA Airworthiness Directive (AD) action. Current FAA ADs related to this subject are 2003-17-10 (which superseded AD 2003-15-01), 2004-23-16, 2005-24-08 and 2006-15-13. Cracking of the blade or hub can ultimately lead to blade release with potentially catastrophic consequences. * * * * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
90-01-03: 90-01-03 HONEYWELL, INC., SPERRY COMMERCIAL FLIGHT SYSTEMS GROUP, BUSINESS AND COMMUTER AVIATION SYSTEMS DIVISION (Sperry Corporation): Amendment 39-6442. Docket No. 89-NM-98-AD. Applicability: Honeywell AH-600 Attitude and Heading Reference System (AHRS) Strapdown Attitude and Heading Reference Unit (AHRU), part numbers 7003360-931, -932, -933, -934, -935, and -936, with serial numbers 0100 through 0277. Compliance: Required as indicated, unless previously accomplished. NOTE: These systems are known to be installed in, but not limited to, de Havilland Model DHC-8, British Aerospace Model BAe 125-800, Cessna Model 650, and Aerospatiale Model ATR42-300 series airplanes. To eliminate the possibility of the primary attitude and heading displays on both sides of the instrument panel failing simultaneously, accomplish the following: A. Within 10 days after January 9, 1989 (the effective date of Amendment 39-6093), inspect airplanes with Honeywell AH-600 AHRSinstalled to determine the part number, serial number, and Mod Level of the strapdown AHRU installed in the pilot's (Number 1) AHRS. Prior to further flight after inspection, remove all AHRU part numbers 7003360-931, -932, -933, -934, -935, and -936 with serial numbers 0100 through 0277, without Mod Level "F", from service in the pilot's (Number 1) AHRS. Install the same part number with Mod Level "F" incorporated, or modify the AHRU in accordance with Honeywell Inc., Service Bulletin 7003360-34-32, dated August 2, 1988. NOTE: Serial numbers of the strapdown AHRU are eight digit numbers; the first four are date code and the last four are the individual unit identifier. Serial numbers referred to in this AD are the last four numbers of the serial number. B. Within 60 calendar days after the effective date of this amendment, inspect airplanes with Honeywell AH-600 AHRS installed to determine the part number, serial number, and Mod Level of the strapdown AHRU installed in copilot's (Number 2) AHRS and the auxiliary (Number 3) AHRS. Within 45 days after the inspection, remove all AHRU part numbers 7003360-931, -932, -933, -934, -935, and -936, with serial numbers 0100 through 0277, without Mod Level "F", from service in the copilot's (Number 2) AHRS and the auxiliary (Number 3) AHRS. Install the same part number with Mod Level "F" incorporated, or modify the AHRU in accordance with Honeywell, Inc., Service Bulletin 7003360-34-32, dated August 2, 1988. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager, Los Angeles Aircraft Certification Office. D. Special 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Honeywell Inc., Sperry Commercial Flight Systems Group, Business and Commuter Aviation Systems Division, 5353 West Bell Road, Glendale, Arizona 85308. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. This AD supersedes AD 88-26-05, Amendment 39-6093. This amendment (39-6442, AD 90-01-03) becomes effective on February 5, 1990.
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.
2008-12-13: 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 aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: ENAC Italy AD 2004-376 was issued in response to two separate reports of cracks found in the Firewall-to-Engine mounting attachments. Detachment of the engine mounts from the structure is the possible consequence. Although the actual cause has not been finally determined, some repairs have been approved to address and correct the unsafe condition. This new AD, which supersedes ENAC Italy AD 2004-376, retains the initial inspection requirement, adds repetitive inspections and clarifies the conditions under which aircraft that have been repaired by an approved method can be allowed to return to service. We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-10-05: The FAA is adopting a new airworthiness directive (AD) for certain Rockwell Collins, Inc. (Rockwell Collins) flight management systems (FMS) installed on airplanes. This AD was prompted by reports of the flight management computer (FMC) software issuing incorrect turn commands when the altitude climb field is edited or the temperature compensation is activated on the FMS control display unit. This AD requires disabling the automatic temperature compensation feature of the FMS through the configuration strapping units (CSU) and revising the airplane flight manual (AFM) Limitations section. The FAA is issuing this AD to address the unsafe condition on these products.