Results
2002-14-24: This amendment adopts a new airworthiness directive (AD), applicable to certain Cessna Model 650 airplanes, that requires a one-time inspection of the side brace mechanism assemblies of the left and right main landing gears (MLG) to detect any incorrect part number, and corrective actions if necessary. This action is necessary to prevent inadvertent disengagement of the locking mechanism of the side brace mechanism assembly, which could lead to collapse of the respective MLG, and result in a gear-up landing and possible injury to passengers and crew. This action is intended to address the identified unsafe condition.
80-09-11: 80-09-11\tTELEDYNE CONTINENTAL MOTORS: Amendment 39-3763. Applies to Model GTSIO-520 series engines overhauled by AAR Western Skyways, Inc. \n\tTo prevent the possible separation of the starter torsional damper from the starter gear shaft and subsequent damage to critical components in the engine nacelle, accomplish the following: \n\ta.\tPrior to next flight: \n\t\t1.\tRemove engine cowling to the extent that the rear of the engine, where the starter and/or starter adapter are installed, can be seen. \n\t\t2.\tInspect the locking device at the outboard end of the starter gear shaft, which secures the torsional damper (see Figure I) for proper installation of all required parts. There must be a snap ring (TCM P/N 502171), a nut lock key (TCM P/N 632980), a compression spring (TCM P/N 628311) and a Marsden slotted hex nut (TCM P/N 632979) installed. \n\t\t3.\tIf all of the parts (in 2. above) are installed correctly, no further action is required. \n\tb.\tIf all the parts (in a.2. above) are not installed or are of the incorrect part, accomplish the following: \n\t\t1.\tPrior to the next flight and within every 25 hours engine operating time thereafter until all correct parts are installed, check the torque on the existing hexagon nut on the starter gear shaft to 180-220 foot pounds. For installations incorporating a compressor sheave for air conditioner drive, the hex nut must be checked for a torque of 195-235 foot pounds. \n\t\t2.\tWithin 100 hours engine operating time after the effective date of this AD, install all correct parts in accordance with TCM overhaul manual instructions. \n\tParts may be obtained from Teledyne Continental Motors, P.O. Box 90, Mobile, Alabama 36601, telephone (A/C 205) 438-3411, or AAR Western Skyways, Inc., Troutdale, Oregon, telephone (A/C 503) 665- 1181 or any other Teledyne Continental Motors distributor. \n\n\t\nc.\tAircraft may be flown in accordance with FAR 21.197 to a base where the repairs required by this AD can be accomplished. \n\tAn equivalentmethod of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, P.O. Box 20636, Atlanta, Georgia 30320. \n\tThis amendment is effective upon publication in the Federal Register as to all persons except those persons to whom it was made immediately effective by priority mail, issued April 3, 1980, which contained this amendment.
92-08-01: 92-08-01 BOEING: Amendment 39-8212. Docket No. 91-NM-228-AD.\n\n\tApplicability: Model 757 series airplanes, equipped with Pratt and Whitney PW2000 series engines; as listed in Boeing Alert Service Bulletin 757-28A0028, dated October 3, 1991; certificated in any category.\n\n\tCompliance: Required within 270 days after the effective date of this AD, unless previously accomplished.\n\n\tTo ensure that in-flight engine restart capability is available, accomplish the following:\n\n\t(a)\tRemove and replace the left and right engine fuel shutoff valves in accordance with Boeing Alert Service Bulletin 757-28A0028 dated October 3, 1991.\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 the airplane to a location where the requirements of this AD can be accomplished.\n\n\t(d)\tThe replacement shall be done in accordance with Boeing Alert Service Bulletin 757-28A0028 dated October 3, 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington, 98124. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC.\n\n\t(e)\tThis amendment becomes effective on May 19, 1992.
89-22-13: 89-22-13 BOEING: Amendment 39-6362. Docket No. 89-NM-103-AD \n\tApplicability: Model 757 series airplanes equipped with Pratt and Whitney engines, listed in Boeing Service Bulletin 757-76-0006, dated March 16, 1989, certificated in any category. \n\n\tCompliance: Required within the next 12 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent the elevator control cables binding on the engine throttle control cable fairleads, accomplish the following: \n\n\t\tA.\tRemove two engine throttle control cable fairleads in accordance with Boeing Service Bulletin 757-76-0006, dated March 16, 1989. \n\n\t\tB.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur orcomment, and then send it to the Manager, Seattle Aircraft Office. \n\n\t\tC.\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\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6362, AD 89-22-13) becomes effective on November 20, 1989.
2007-11-18R1: The FAA is revising an existing airworthiness directive (AD) for General Electric Company (GE) CF6-50C series turbofan engines. That AD currently requires reworking certain forward fan stator cases and installing a fan module secondary containment shield. This AD requires the same actions but eliminates a certain service bulletin from the compliance method. This AD results from a review that shows that only one of the service bulletins referenced in the original AD is applicable as a compliance method. We are issuing this AD revision to eliminate a certain service bulletin from the compliance method and to prevent uncontained fan blade failures, which can result in separation of airplane hydraulic lines, damage to critical airplane systems, and possible loss of airplane control.
46-39-05: 46-39-05 DOUGLAS: (Was Mandatory Note 6 of AD-762-7.) Applies Only to C-54B and Other C-54 Series Airplanes Having the C-54B Fuel System. \n\n\tTo be accomplished not later than December 1, 1946. \n\n\tThe main fuel line supporting brackets at wing Stations 357, 378, and 399 are subject to vibration failure and are to be replaced with redesigned brackets. In addition, the United Carr clips at wing Station 378 are to be replaced by Adel clips. \n\n\t(Douglas Service Bulletin No. DC-4-5 covers this same subject.)
91-21-07: 91-21-07 MCDONNELL DOUGLAS: Amendment 39-8054. Docket No. 91-NM-104-AD. Supersedes AD 90-26-53 and AD 91-01-51. \n\n\tApplicability: Model DC-9 and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (Military) airplanes; equipped with Primary Longitudinal Trim Relays (up and down), Leech (P/N) 9207-8333, -8333-1, -8968, -10101, -10296, and -10166; certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo eliminate overheating of primary longitudinal trim relays and the possibility of fire in the forward cargo compartment, accomplish the following: \n\n\t(a)\tFor Model DC-9 series airplanes (other than Model DC-9-80 series airplanes), and C-9 (military) airplanes: Within 17 days after February 27, 1991 (the effective date of Amendment 39-6894, AD 90-26-53; and Amendment 39-6894, AD 91-01-51), or prior to the accumulation of 8,000 flight hours on the subject relays, whichever occurs later, remove the relay cover and inspect theprimary longitudinal trim relays for evidence of contact degradation, arcing, carbon build-up, or other evidence of abnormal wear on the contacts; and perform a functional check of the system in accordance with McDonnell Douglas Alert Service Bulletin A27-316, dated December 22, 1990, or January 4, 1991. \n\n\t(b)\tFor Model DC-9-80 series airplanes and Model MD-88 airplanes: Within 30 days after February 27, 1991, or prior to the accumulation of 16,000 flight hours on the subject relays, whichever occurs later, remove the relay cover and inspect the primary longitudinal trim relays for evidence of contact degradation, arcing, carbon build-up, or other evidence of abnormal wear on the contacts; and perform a functional check of the system in accordance with McDonnell Douglas Alert Service Bulletin A27-316, dated December 22, 1990, or January 4, 1991. \n\n\t(c)\tIf damage is found during the inspections or functional tests required by paragraphs (a) and (b) of this AD, prior to further flight, remove and replace the relays in accordance with McDonnell Douglas Alert Service Bulletin A27-316, dated December 22, 1990, or January 4, 1991. \n\n\t(d)\tFor Model DC-9 series airplanes (other than Model DC-9-80 series airplanes) and C-9 (Military) airplanes: Within 90 days after the effective date of this AD or prior to the accumulation of 8,000 flight hours on the subject relays, whichever occurs later; and thereafter at intervals not to exceed 8,000 flight hours; remove and replace the primary longitudinal trim relays with new approved parts in accordance with McDonnell Douglas DC-9 Maintenance Manual, Chapter 27-40-4. This replacement constitutes terminating action for the inspection and functional test required by paragraph (a) of this AD. \n\n\t(e)\tFor Model DC-9-80 series airplanes and Model MD-88 airplanes: Within 90 days after the effective date of this AD, or prior to the accumulation of 16,000 flight hours on the subject relays, whichever occurs later; and thereafterat intervals not to exceed 16,000 flight hours; remove and replace the primary longitudinal trim relays with new approved parts in accordance with McDonnell Douglas MD-80 Maintenance Manual, Chapter 27-40-4. This replacement constitutes terminating action for the inspection and functional test required by paragraph (b) of this AD. \n\n\t(f)\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, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles ACO. \n\n\t(g)\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(h)\tThe inspection and replacement requirements shall be done inaccordance with McDonnell Douglas Alert Service Bulletin A27-316, dated December 22, 1990, or January 4, 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 McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846. Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. \n\n\tAirworthiness Directive 91-21-07 supersedes AD 90-26-53, Amendment 39-6894; and AD 91-01-51, Amendment 39-6893. \n\n\tThis amendment (39-8054, AD 91-21-07) becomes effective on November 19, 1991.
2009-15-02: 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: In-service experience has shown that a fracture of the gerotor pump of the A320 RAT [ram air turbine] may occur. This may lead to the non-operation of the RAT in case of an in-flight deployment. The Non-Deployment or Non-Pressurization of the RAT, associated with a double engine failure or a total loss of normal electrical power generation constitutes an unsafe condition. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
69-25-01: 69-25-01\tBOEING: Amdt. 39-882. Applies to Model 727, 727C and 727-200 series airplanes. \n\tCompliance required within the next 2500 hours time in service after the effective date of this AD, unless already accomplished. \n\tTo prevent malfunction of the generator control circuit caused by induced electrical interference, accomplish the following or an equivalent modification procedure and parts installation approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\tWithin 2500 hours time in service after the effective date of this AD, unless already accomplished, modify the generator control panels in accordance with Section II, Boeing Service Bulletin No. 24-47, dated March 3, 1969, or later FAA approved revisions. \n\tThis amendment becomes effective January 3, 1970.
2009-14-06: The FAA is superseding an existing airworthiness directive (AD), which applies to all Boeing Model 777 airplanes. That AD currently requires, for the drive mechanism of the horizontal stabilizer, repetitive detailed inspections for discrepancies, repetitive lubrication of the ballnut and ballscrew, repetitive measurements of the freeplay between the ballnut and the ballscrew, and corrective action if necessary. This new AD revises the compliance times of the existing AD. This AD results from a report of extensive corrosion of a ballscrew in the drive mechanism of the horizontal stabilizer on a Boeing Model 757 airplane, which is similar in design to the ballscrew on Model 777 airplanes. We are issuing this AD to prevent an undetected failure of the primary load path for the ballscrew in the drive mechanism of the horizontal stabilizer and subsequent wear and failure of the secondary load path, which could lead to loss of control of the horizontal stabilizer and consequent lossof control of the airplane.