Results
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.
2020-09-11: The FAA is superseding Airworthiness directive (AD) 2017-06-06 and AD 2019-12-10, which applied to all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. Those ADs required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive airworthiness limitations; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
85-21-51: This action publishes in the Federal Register and makes effective as to all persons an amendment adopting a new airworthiness directive (AD) which was previously made effective to all known U.S. owners and operators of certain Boeing Model 767-200 airplanes by individual telegrams. The AD requires inspection and replacement, if necessary, of self-locking nuts located in certain critical areas of the airplanes. This action was prompted by the discovery that two elevator actuator rod end bolt retaining nuts on one recently delivered Model 767 airplane did not have their intended self-locking feature. Such a nut could back off its mating bolt and result in a disconnection of the affected joint. Multiple disconnections of elevator to actuator joints could result in partial or complete loss of airplane control. These nuts have other critical applications on the Model 767 airplane, which are also addressed in the AD.
2005-10-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A310 series airplanes. This AD requires measuring the clearance between the compensator and the guide assembly of probe no. 1 on the outboard fuel tanks, and performing corrective actions if necessary. This AD is prompted by the results of fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent interference between the compensator and the guide assembly of probe no. 1, which could create an ignition source that could result in a fire or explosion.
76-07-01: 76-07-01 FAIRCHILD AIRCRAFT: Amendment 39-2562. Applies to Models F-27 series and FH-227 series aircraft. Compliance required as indicated: To detect loose studs which may create a hazard, accomplish the following: (a) Within the next 200 hours time in service after the effective date of this AD, unless already accomplished within the last 1000 hours in service, inspect, clean and torque studs on terminal board assembly P/N 27-746011-11 to 100 inch-lbs. (b) Within the next 1800 hours replace the existing terminal block assembly with an MS 27212 terminal block assembly unless already accomplished. Fairchild Service Bulletin Nos. FH-227-24-11 and F-27-24-15, dated March 1, 1976, covers the replacement of the terminal block. (c) Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the compliance times specified in this AD if the request contains substantiating data to justify the increase for that operator. Fairchild Service Letter Nos. F-27-646 and FH-227-24-17, dated January 26, 1976, pertain to this subject. This amendment is effective April 2, 1976.
79-20-05: 79-20-05 BELL: Amendment 39-3572 as amended by Amendment 39-3626 is further amended by Amendment 39-3662. Applies to Models 204B, 205A-1, and 212 helicopters, certificated in all categories equipped with main rotor hub assembly, P/N 204-012-101 and yoke assembly, P/N 204-011-102 (Airworthiness Docket No. 79-ASW-25). For main rotor yokes having 500 hours or more total time in service on the effective date of this AD, compliance required prior to December 1, 1979, unless already accomplished, and thereafter at intervals not to exceed 2400 hours from the last inspection. For main rotor yokes having less than 500 hours' total time in service on the effective date of this AD, compliance required prior to attaining 1000 hours' total time in service and thereafter at intervals not to exceed 2400 hours' from the last inspection. To detect and preclude corrosion and possible cracks in the main rotor yoke, accomplish the following: (a) Remove the yoke assembly from the mainrotor hub assembly. (b) Conduct the following inspections: (1) Inspect yoke for corrosion pits, scratches, and damage in the pillow block bushing hole, in each spindle radius, and yoke web section by using a five power or higher magnifying glass. (2) Inspect the yoke for cracks using a magnetic particle inspection method. Note: Special attention should be directed to the center section web, spindles, radius, and pillow block bushing holes. (c) Remove corrosion pits, repair, refinish, and seal the yoke as prescribed by Model 212 Component Repair and Overhaul, Revision 4, Chapter 65 or Revision 12, Model 204B Maintenance and Overhaul Manual, or Revision 1, Model 205A-1 Component Repair and Overhaul Manual. (d) Replace yokes having a crack or that exceed repair limits specified in the appropriate model maintenance or repair and overhaul manual with a serviceable yoke before further flight. The serviceable yoke must have been refinished and sealed as prescribed byModel 212 Component Repair and Overhaul, Revision 4, Chapter 65, or Revision 12, Model 204B Maintenance and Overhaul Manual, or Revision 1, Model 205A-1 Component Repair and Overhaul Manual. (e) Equivalent means of compliance with this AD may be approved by the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region. (f) The helicopter may be flown in accordance with FAR 21.197 to a base where inspections and repairs can be performed. (g) Upon request of the operator, an FAA maintenance inspector subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Southwest Region, may adjust the repetitive inspection intervals specified in this AD if the request contains data justifying the increase. Amendment 39-3572 became effective October 31, 1979. Amendment 39-3626 became effective December 1, 1979. This Amendment 39-3662 becomes effective January 18, 1980.
91-03-15: 91-03-15 MOONEY AIRCRAFT CORPORATION: Amendment 39-6870; Docket No. 90-CE-74-AD. Applicability: Model M20M airplanes (serial numbers (S/N 27-0001 through 27-0071, S/N 27-0073, S/N 27-0075, and S/N 27-0076), 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 the discharge of high temperature exhaust gases inside the engine compartment that could result in the airplane cabin catching fire, accomplish the following: (a) Replace the tailpipe coupling (P/N MVT69183-275, LW-12093-8, 4571-275, 4574-275, or 4391 AF) with an improved tailpipe coupling (P/N 55677-340M or 40D21162-340M) in accordance with the instructions in Mooney Aircraft Corporation Special Letter 90-06, dated November 1, 1990. (b) 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. (c) An alternate method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, FAA, Southwest Region, Airplane Certification Office, Fort Worth, Texas 76193-0150. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Fort Worth Airplane Certification Office. (d) All persons affected by this directive may obtain copies of the document referred to herein upon request to Mooney Aircraft Corporation, P.O. Box 72, Kerrville, Texas 78029-0072; Telephone (512) 896-6000; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-6870, AD 91-03-15) becomes effective on February 19, 1991.
78-07-09: 78-07-09 BOEING: Amendment 39-3177. Applies to Model 747 series airplanes listed in Boeing Service Bulletin 747-25-2306 certificated in all categories. Compliance required as indicated. To assure proper operation of the depressurization vent modification required by AD 75-15-05, on or before June 30, 1978, unless already accomplished, inspect and rework the cargo compartment lining in accordance with Boeing Service Bulletin 747-25-2418, dated December 27, 1977, or later FAA approved revision, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region.\n \tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part 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.These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective May 10, 1978.
2008-06-21: We are adopting a new airworthiness directive (AD) for all McDonnell Douglas airplane models identified above. This AD requires revising the FAA-approved maintenance program, or the Airworthiness Limitations (AWLs) section of the Instructions for Continued Airworthiness, as applicable, to incorporate new AWLs for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. For certain airplanes, this AD also requires the initial accomplishment of a certain repetitive AWL inspection to phase in that inspection, and repair if necessary. This AD results from a design review of the fuel tank systems. We are issuing this AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
93-25-07: 93-25-07 BEECH AIRCRAFT CORPORATION: Amendment 39-8773. Docket No. 93-CE-38-AD. Applicability: The model and serial number airplanes presented below, certificated in any category, that do not have all the fuselage stringers Nos. 5 through 11 modified on both the right and left hand sides in accordance with either (1) Beech Service Bulletin (SB) 2472, Revision 1, dated September 1993; (2) Chapter 51-10 or 53-10, as applicable, of the maintenance manual; or (3) the instructions to Priester Aviation Service Supplemental Type Certificate (STC) SA63CH: Models Serial Numbers 200, A200, B200, and A100-1 BB-2 through BB-1462, BC-1 through BC-75, and BD-1 through BD-30 200C, A200C, and B200C BL-1 through BL-138, BJ-1 through BJ-66, BU-1 through BU-12, and BV-1through BV-12 200CT, A200CT, B200CT BN-1 through BN-4, BP-1 through BP-71, FC-1, FC-2, FC-3, FE-1 through FE-31, FG-1, FG-2, and GR-1 through GR-19 200T and B200T BT-1 through BT-38 300 FA-1 through FA-228 300 (FAA) FF-1 through FF-19 B300 FL-1 through FL-103 B300C FM-1 through FM-8 and FN-1 Compliance: Required upon the accumulation of 3,000 hours time-in-service (TIS) or within the next 100 hours TIS after the effective date of this AD, whichever occurs later, unless already accomplished, and thereafter as indicated. To prevent structural damage to the fuselage caused by cracked stringers in the rear pressure bulkhead area, accomplish the following: (a) Inspect fuselage stringers Numbers (Nos.) 5 through 11 on both the left and right hand sides for cracks in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Beech SB No. 2472, Revision 1, dated September 1993. (1) If no cracks are found, reinspect at intervals that correspond with the following: Stringers Modified in Accordance With One of the Three Modifications Referenced in the Applicability Section of this AD Inspection Interval No Stringers Modified 600 hours TIS on all stringers Nos. 8, 9, and 10 (one side) with Internal Modification 1,200 hours TIS on unmodified stringers Nos. 8, 9, and 10 (one side) with External Modification 600 hours TIS on unmodified stringers Nos. 5 through 11 AD no longer applies (2) If cracks are found, modify all cracked fuselage stringers at any time up to the time specified in the chart presented in paragraph (a)(3) of this AD. Accomplish this modification in accordance with the instructions in one of the three modifications specified in the Applicability section of this AD, and reinspect at intervals presented in the chart in paragraph (a)(1) of this AD. (3) The following chart specifies the required compliance time where cracked stringers must be modified: No. of Stringers Cracked on Any One Side of Fuselage When Modification Must be Accomplished (Hours TIS) 1 to 3 150 4 30 5 or more Prior to further flight (b) The modifications specified in the Applicability section of this AD may be accomplished at any time as terminating action for the inspection requirement of this AD provided that all fuselage stringers Nos. 5 through 11 are modified. (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, Wichita Aircraft Certification Office (ACO), FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and send it to the Manager, Wichita ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (e) The inspections and modification required by this AD shall be done in accordance with Beech Service Bulletin 2472, Revision 1, dated September 1993. 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 Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. 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 (39-8773) becomes effective on February 15, 1994.