Results
2004-26-06: This amendment adopts a new airworthiness directive (AD), that is applicable to certain Boeing Model 767-300 and 767-300F series airplanes equipped with General Electric or Pratt & Whitney engines. This AD requires reworking the wing-to-strut diagonal braces and the aft pitch load fittings of the wings, and reinstalling the diagonal braces with new fuse pins and associated hardware. This action is necessary to prevent undetected loss of the diagonal brace fuse pins of the wings and consequent increased loads in other wing-to-strut joints, which could result in separation of the struts and engines from the wings. This action is intended to address the identified unsafe condition.
2023-11-09: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model GVII-G500 and GVII-G600 airplanes. This AD was prompted by reports of two landing incidents in which the alpha limiter engaged in the landing flare in unstable air, resulting in high rate of descent landings and damage to the airplanes. This AD requires updating the flight control computer (FCC) software. The FAA is issuing this AD to address the unsafe condition on these products.
97-03-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas DC-9 series airplanes, that currently requires repetitive visual inspections to detect corrosion and cracking of the fuselage upper skin and frames in the area of the loop antenna assemblies of the automatic direction finder (ADF), and repair, if necessary. This amendment adds a requirement to perform a visual and an eddy current inspection of the fuselage forward upper skin under the antennas, followed by the reinstallation of the ADF antennas using an improved procedure. This amendment is prompted by the development of a modification of the ADF antenna installation that constitutes terminating action for the required repetitive visual inspections. The actions specified by this AD are intended to prevent rapid decompression of the fuselage, significant structural damage, and subsequent reduced structural integrity of the airplane, due to problems associated with corrosion and fatigue cracking in the subject area.
2005-01-03: The FAA is adopting a new airworthiness directive (AD) for certain Boeing airplanes listed above. This AD requires repetitive detailed inspections of the midspar web of the inboard and/or outboard struts for cracking, disbonding, or buckling; repetitive detailed inspections of the midspar stiffeners for any crack or fracture; related investigative actions; and corrective actions, if necessary. This AD is prompted by reports of cracking in the midspar web. We are issuing this AD to detect and correct cracking in the midspar assembly, which could result in the loss of the midspar assembly load path, and could, combined with the loss of the nacelle station 180 bulkhead load path, lead to the separation of the engine from the airplane.
61-16-02: 61-16-02 ARMSTRONG-WHITWORTH: Amdt. 315, Part 507 Federal Register August 3, 1961. Applies to the following Model AW-65O Argosy Series 101 aircraft only: Serial Numbers 6655, 6656, 6657, 6659, and 6660. Compliance required as indicated. Because of service defects found on the elevators, rudders, fins and flaps, the following is required: (a) Prior to every flight, visually inspect the following areas for loose rivets, cracks and damaged skin: (1) Top and bottom surface of both elevators including horn balances. (2) Inboard and outboard sides of left and right fins. (3) Entire surface of left and right rudders including tabs. (4) Undersurface of inboard flaps. (b) If loose rivets or damaged skin is found an FAA approved repair must be accomplished prior to further flight. (c) If cracks are found, the following action must be taken: (1) If cracks between adjacent rivets or cracks at least one inch long are found, the internal structure in that location must be inspected. If no internal damage is found, an FAA approved repair must be made to the skin prior to the next flight. If any internal damage is found the component must either be replaced or an FAA approved repair incorporated prior to next flight. (2) If cracks less than one inch long and less than twelve inches apart are found, they must be repaired prior to the next flight. Cracks less than one inch long which are twelve inches or more apart must either be stopped by drilling or repaired prior to next flight. (d) The special inspections in (a), (b), and (c) are no longer required when AWA modifications 650/686, 650/687, 650/688, 650/689, and 650/690 are all incorporated. This supersedes AD 61-05-01. This directive effective August 3, 1961.
2023-09-09: The FAA is adopting a new airworthiness directive (AD) for turbocharged, reciprocating engine-powered airplanes and helicopters and turbocharged, reciprocating engines with a certain v-band coupling installed. This AD was prompted by multiple failures of spot-welded, multi-segment v-band couplings at the tailpipe to the turbocharger exhaust housing flange (also referred to as ''spot-welded, multi- segment exhaust tailpipe v-band coupling''). This AD establishes a life limit for the spot-welded, multi-segment exhaust tailpipe v-band coupling and requires repetitively inspecting the spot-welded, multi- segment exhaust tailpipe v-band coupling. The FAA is issuing this AD to address the unsafe condition on these products.
2014-12-52: We are superseding emergency airworthiness directive (AD) 2014-12-52 for all Honeywell International Inc. TFE731-4, -4R, -5AR, - 5BR, -5R, -20R, -20AR, -20BR, -40, -40AR, -40R, -40BR, -50R, and -60 turbofan engines. Emergency AD 2014-12-52 was sent previously to all known U.S. owners and operators of these engines. AD 2014-12-52 required, before further flight, a review of the engine logbook maintenance records to determine if any affected engines are installed. AD 2014-12-52 also prohibited operation of an airplane with two or more affected engines that have 2nd stage low-pressure turbine (LPT2) blades with less than 250 operating hours since new. This AD retains the requirements of AD 2014-12-52 and clarifies the intent of the mandatory requirements. This AD was prompted by reports of LPT2 blade separations. We are issuing this AD to prevent LPT2 blade failure, multiple engine in-flight shutdowns, and damage to the airplane.
97-03-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 and 737 series airplanes, that requires replacing the fuel cap assembly with a new assembly on the inlet fitting at the inside top of the Boeing-designed auxiliary fuel tank(s). This amendment also requires installing certain new placards once the replacement action is accomplished. This amendment is prompted by reports that the fuel cap assembly, due to its design, became loose and allowed fuel to enter the deactivated auxiliary fuel tanks on in-service airplanes. The actions specified by this AD are intended to prevent unwanted fuel transferring to the deactivated auxiliary fuel tanks, due to the problems associated with a loose fuel cap assembly.
88-13-07: 88-13-07 SHORT BROTHERS, PLC: Amendment 39-5950. Applies to Model SD3-30 series airplanes; serial numbers SH3002 through SH3096, inclusive; certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent pitot tubes from becoming inoperative due to icing, which could result in erroneous airspeed and altitude indication, accomplish the following: A. Within the next 180 days after the effective date of this AD, replace pitot tubes having the code letter "Z" adjacent to the serial number with one containing a code letter other than "Z", in accordance with accomplishment instructions in Service Bulletin SD3-34-26, Revision 1, dated September 1, 1985. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Seattle Aircraft Certification Office. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the requirements required by this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Short Brothers, PLC, Service Representative, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3702. This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment, 39-5950, becomes effective July 11, 1988.
2004-26-08: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-215-6B11 (CL215T variant) and CL-215-6B11 (CL415 variant) series airplanes. This AD requires replacing the mounting pad studs of the auxiliary feather pump with new, longer studs, and installing a pressure relief valve. This AD is prompted by a few incidents of external oil leaks from the oil pump of the power control unit due to a malfunction of the pressure regulating valve. We are issuing this AD to prevent fracturing of the pump body, which could result in loss of engine oil, and consequent inability to maintain engine oil pressure and to feather the propeller.