Results
2010-21-14: 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: Due to a manufacturing error, some rivets, required by drawings, were not installed in the joints between two ceiling beams and the rear pressurized bulkhead. If left uncorrected, long term fatigue stress could locally weaken the structure, compromising the fuselage structural integrity. We are issuing this AD to require actions to correct the unsafe condition on these products.
2001-01-03: This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace HP137 Mk1, Jetstream series 200, and Jetstream Models 3101 and 3201 airplanes. This AD requires you to remove the nose landing gear steering actuator and install one that incorporates a modified piston rod. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent failure of the nose landing gear steering actuator because of problems with the current design piston rod. Continued operation with the current design piston rod could result in loss of nose wheel steering and possible loss of control of the airplane during takeoff, landing, and taxi operations.
93-01-20: 93-01-20 BEECH AIRCRAFT CORPORATION: Amendment 39-8474. Docket No. 92-CE-42-AD. Supersedes AD 89-22-12, Amendment 39-6351. Applicability: Model 300 airplanes (serial numbers FA-2 through FA-211 and FF-1 through FF-19), certificated in any category. Compliance: Required as indicated, unless already accomplished (compliance with superseded AD 89-22-12). To prevent separation of an aft cowling door, which could result in occupant injury if decompression or structural damage occurs, accomplish the following: (a) Within the next 25 hours time-in-service (TIS) after the effective date of this AD, inspect the upper aft cowling access door latches for proper tension and total engagement of the adjusting bolts and striker plates in accordance with Part I of the ACCOMPLISHMENT INSTRUCTIONS section of Beech Service Bulletin (SB) No. 2329, dated August 1989, revised February 1991. (1) If improper tension is found, prior to further flight, adjust the cowling door latch in accordance with Beechcraft Super King Air 300 Maintenance Manual, Chapter 71-10. (2) If the adjusting bolts and striker plates do not totally engage, prior to further flight, modify the cowling door in accordance with Beechcraft Safety Communique No. 300-75. (b) Within the next 50 hours TIS after the effective date of this AD, accomplish one of the following: (1) Modify the cowlings to provide upper aft cowling access door retention in accordance with Part II of the ACCOMPLISHMENT INSTRUCTIONS section of Beech SB No. 2329, dated August 1989, revised February 1991; or (2) Install cowling door latch replacement Kit No. 101-9052-1 S in accordance with Part III of the ACCOMPLISHMENT INSTRUCTIONS section of Beech SB No. 2329, dated August 1989, revised February 1991. (c) If the requirements of paragraphs (a), (a)(1), (a)(2), and (b)(1) were previously accomplished (compliance with superseded AD 89-22-12) in accordance with Beech SB No. 2329, dated August1989, then no further action is required by this AD. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and send it to the Manager, Wichita Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office. (f) The inspection and modification or installation required by this AD shall be done in accordance with Beech Service Bulletin No. 2329, dated August 1989,revised February 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the 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. (g) This amendment (39-8474) supersedes AD 89-22-12, Amendment 39-6351. (h) This amendment becomes effective on March 10, 1993.
82-08-07: 82-08-07 BRITISH AEROSPACE: Amendment 39-4367. Applies to British Aerospace Models HS/DH-125 airplanes series 1A, 3A, and variants that have not been modified in accordance with modification 25/5640, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent hydraulic pressure loss in the wing flap system and wing flap movement away from the selected position: 1. Within the next 100 landings or prior to accumulating 8000 landings, whichever occurs later, after the effective date of this AD and at each 8000 landing interval thereafter, replace wing flap actuator P/N AIR45566 or AIR45568 in accordance with the "Accomplishment Instructions" of British Aerospace Service Bulletin SB.27-125 dated March 19, 1979. Note: Operators who can substantiate the number of landings on the flap jack assembly may use this in lieu of using the number of landings on the airplane for compliance with the AD. 2. Special flight permits may beissued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. 3. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. The 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). This amendment becomes effective April 26, 1982.
2016-07-13: We are adopting a new airworthiness directive (AD) for certain GE Aviation Czech s.r.o. M601E-11 turboprop engines. This AD requires inspection of the engine power turbine (PT) disk and, if found damaged, its replacement with a part eligible for installation. This AD was prompted by discovery of damage to certain engine PT disks during engine shop visits. We are issuing this AD to prevent failure of the engine PT disk, which could result in release of high-energy debris, damage to the engine, and reduced control of the airplane.
2001-01-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2, A300 B4, A300 B4-600, A300 B4-600R, A300 F4-600R, and A310 series airplanes, that requires modification of the escape slides. The actions specified by this AD are intended to prevent deflation of the escape slide after deployment, which could result in a delay during an emergency evacuation. This action is intended to address the identified unsafe condition.
85-23-51 R1: 85-23-51 R1 BOEING VERTOL COMPANY: Amendment 39-5253. Applies to Boeing Vertol Model 234 series helicopters certificated in any category. Compliance is required as indicated unless already accomplished. To prevent possible hazards in flight associated with a cracked main rotor head vertical hinge pin, accomplish the following: (a) Prior to further flight, conduct a visual inspection of the forward and aft main rotor head vertical hinge pins, P/N 114R2172-1, internal surface with a light assisted bore-scope for cracks. (b) After the initial inspection of paragraph (a), repeat the inspection prior to the first flight of each day. (c) Within the next 150 hours time in service from March 31, 1986, conduct an eddy current inspection of the internal surfaces of the forward and aft main rotor head vertical hinge pins, P/N 114R2172-1, in accordance with the instructions contained in Boeing Vertol Document D210-12089-1 titled "Eddy Current Inspection Requirements for Detection of Cracks in P/N 114R2172, Vertical Hinge Pins." Upon accomplishment of this paragraph, the daily bore-scope inspection of paragraph (b) may be eliminated. (d) Within the next 500 hours time in service from March 31, 1986, remove from the helicopter the main rotor head vertical hinge pins and conduct a magnetic particle inspection in accordance with Boeing Airplane Company document BAC 5424 titled "Magnetic Particle Inspection" Class B. (e) Remove from service vertical hinge pins found cracked and replace with a serviceable part prior to further flight. (f) Any alternate method of compliance with the AD which provides an equivalent level of safety may be used when approved by the Manager, New York Aircraft Certification Office, Federal Aviation Administration, 181 South Franklin Avenue, Valley Stream, New York 11581. The 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). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Boeing Vertol Company, Boeing Center, P.O. Box 1858, Philadelphia, Pennsylvania 19142. These documents may also be examined at the Office of the Regional Counsel, FAA Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106. This amendment becomes effective March 31, 1986, as to all persons except those to whom it was made immediately effective by telegraphic AD T85-23-51 issued November 20, 1985, which contained part of this amendment.
91-26-03: 91-26-03 AIRBUS INDUSTRIE: Amendment 39-8114. Docket No. 91-NM-129-AD. Applicability: Model A300, A310, and A300-600 series airplanes equipped with BF Goodrich emergency evacuation slides and/or slide rafts, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent non-deployment of the emergency evacuation slides and/or slide rafts during an emergency evacuation, accomplish the following: (a) Within 120 days after the effective date of this AD, accomplish the following in accordance with Airbus Service Bulletins A300-25-434 (for Model A300 series airplanes), A300- 25-6028 (for Model A300-600 series airplanes), and A310-25-2054 (for Model A310 series airplanes), all dated October 22, 1990, as applicable: NOTE: These service bulletins reference BF Goodrich Service Bulletin 25-230, dated July 20, 1990, for additional instructions. (1) Perform a visual inspection of release pin lanyard assemblies forrelease pins in the early configuration, unauthorized modifications, and incorrect installation and operation. Prior to further flight, replace release pin lanyards in the early configuration, unauthorized modifications, or incorrectly installed or damaged release pin lanyards, if found. (2) Perform a visual inspection of lanyard cables for evidence of fraying. If frayed lanyards are found, replace the lanyards prior to further flight. (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 airplanes to a base in order to comply with the requirements of this AD. (d) The inspections and replacements required by this AD shall be done in accordance with Airbus Service Bulletins A300-25-434 (for Model A300 series airplanes), A300- 25-6028 (for Model A300-600 series airplanes), and A310-25-2054 (for Model A310 series airplanes), all dated October 22, 1990. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 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 (39-8114, AD 91-26-03) becomes effective on January 27, 1992.
2016-07-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757 airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer. This AD requires modifying the fuel quantity indication system (FQIS) wiring to prevent development of an ignition source inside the center fuel tank. We are issuing this AD to prevent ignition sources inside the center fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
56-03-03: 56-03-03 NAVION: Applies to All Models. Compliance required as indicated. Cracks starting at the wing centerline attaching bolt hole in the wing rear spar junction fittings (P/N 145-14070) at wing Station O have been found on a number of Navion aircraft. To correct this, it will be necessary to inspect all Navions for this condition as soon as practicable but not later than May 1, 1956. Access to these fitting may be gained through the main wheel wells. If no cracks are found, 3/16-inch thick 1010 steel (or equivalent) end plates, properly radiused for a snug fit, should be installed in each fitting prior to the next 50 hours of flight time. If cracks are found, they should be stop-drilled with a No. 60 (0.040 drill and the end plates as described above should be installed prior to the next flight. No further inspections will be necessary upon installation of these end plates. (Ryan Navion Service Bulletin No. 23 dated December 5, 1955, covers this same subject.)