Results
2004-14-11: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that currently requires repetitive inspections for discrepancies of the upper and lower areas of the backup struts in the left and right nacelles; and corrective actions, if necessary. This amendment requires repetitive inspections for cracks in the lower areas of the backup struts, and corrective actions if necessary. This action also requires the eventual replacement of the backup struts with new, improved struts, which terminates the repetitive inspections. The actions specified by this AD are intended to prevent failure of the backup struts in the left and right nacelles due to fatigue cracking, which could result in loss of fail-safe redundancy in the design of the nacelle in terms of load capability, and consequent separation of the engine from the airplane and subsequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
82-18-04: 82-18-04 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 4441. Applies to Model SA 330F, SA 330G, and AS 330J helicopters certificated in all categories and equipped with any dash number of main gearbox (MGB), Part Number (P/N) 330A32.2000, 330A32.3000, 330A32.4000, or 330A32.6000, which has not incorporated Aerospatiale modification No. AMS 330A07.52.171, or for which the Spectrometric Oil Analysis Procedure (SOAP) is not included in the routine maintenance of the MGB. Compliance is required as indicated unless already accomplished. To prevent possible bearing failure within the MGB due to fretting in the main bevel gear wheel-to-shaft junction, accomplish the following: (a) In accordance with the instructions in paragraphs 1.C(1) and 1.C(2) of Aerospatiale SA 330 PUMA Service Bulletin No. 05.64, dated April 28, 1982, or an FAA approved equivalent, gain access and inspect the bolted junction of the main bevel gear wheel and its shaft inside the MGB for evidence of fretting. Compliance with this inspection is required within the following time periods: (1) For an overhauled MGB: (i) Within the next 50 hours' time in service after the effective date of this AD, if the MGB has accumulated 200 hours' or more since overhaul on the effective date of this AD, or (ii) Before reaching 250 hours' time in service since the last overhaul, if the MGB has accumulated less than 200 hours' time in service since the overhaul on the effective date of this AD. (2) For an MGB which has not been overhauled: (i) Within the next 100 hours' time in service after the effective date of this AD, if the MGB has accumulated 1,100 hours' or more time in service on the effective date of this AD, or (ii) Before reaching 1,200 hours' time in service, if the MGB has accumulated less than 1,100 hours' time in service on the effective date of this AD. (b) When no evidence of fretting is found during the inspection required byparagraph (a) of this AD, the MGB may be returned to service in accordance with paragraph 1.C(4) of Aerospatiale SA 330 PUMA Service Bulletin No. 05.64 or FAA approved equivalent. (c) When evidence of fretting is found during the inspection required by paragraph (a) of this AD, before further flight and in accordance with the instructions given in paragraph 1.C(3)(b) of Aerospatiale SA 330 PUMA Service Bulletin No. 05.64 or an FAA approved equivalent, inspect each of the 18 nuts on the bolts joining the main bevel gear wheel to its shaft for rotation/slippage. Dispose of findings as follows: (1) When nut rotation/slippage is found, remove the MGB from service before further flight. (2) When no nut rotation/slippage is found, the MGB may be returned to service with repetitive nut inspections not to exceed 400 hours' time in service since the last inspection. (d) A special flight permit may be issued, in accordance with FAR 21.197 and 21.199, to operate the helicopter to a base where the requirements of paragraph (c) of this AD may be accomplished. (e) Equivalent means of compliance must be approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. This amendment becomes effective September 7, 1982.
2022-01-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 series airplanes; Airbus SAS Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Airbus SAS Model A310 series airplanes. This AD was prompted by reports of incorrect installation of the fire shut-off valves (FSOV) actuator, which was found to rotate around its pivot axis. This AD requires a one-time detailed inspection of the FSOV actuator for rotation around its pivot axis, and replacement if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2004-13-26: This amendment adopts a new airworthiness directive (AD) for Kaman Aerospace Corporation (Kaman) Model K-1200 helicopters. This action requires certain initial and repetitive visual inspections of the main rotor blade (blade) grips for a crack. If a crack is found, this AD requires replacing the blade grip before further flight. This amendment is prompted by an accident involving the loss of all blades because of a crack in a blade grip on the upper surface around the bolthole. The actions specified in this AD are intended to prevent failure of a blade grip, loss of a blade, and subsequent loss of control of the helicopter.
2022-03-03: The FAA is superseding Airworthiness Directive (AD) 2021-22-20 which applied to certain Austro Engine GmbH E4 and E4P model diesel piston engines. AD 2021-22-20 required, for engines with an affected cylinder head, inspection of the high pressure pump (HPP) driving gear and, depending on the results of the inspection, replacement of the HPP driving gear with a part eligible for installation. AD 2021-22-20 also required, for engines with an affected HPP driving gear, replacement of the HPP driving gear before further flight or within a certain number of flight hours, depending on the engine configuration and number of affected engines installed. This AD requires, for engines equipped with a certain cylinder head and HPP driving gear combination, removal, inspection, and replacement of the HPP driving gear before further flight and, depending on the inspection findings, replacement of the HPP shaft, cylinder head, camshaft gear, or inlet/outlet camshaft bushing. This AD also requires, for engines with an affected HPP driving gear, replacement of the HPP driving gear before further flight or within a certain number of flight hours, depending on the engine configuration and number of affected engines installed. This AD was prompted by reports of failure of the HPP driving gear and a subsequent determination that a batch of HPP driving gears may have been damaged during assembly. This AD was also prompted by an investigation which found that certain cylinder heads installed in combination with certain HPP driving gear on the same engine may cause damage to the HPP driving gear. The FAA is issuing this AD to address the unsafe condition on these products.
96-14-06: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 777-200 series airplanes. This action requires repetitive inspections for broken lockwires on the bearing retainer nut of the pivot fittings of the horizontal stabilizer. This AD also requires eventual modification of the bearing nut retention means, which, when accomplished, terminates the repetitive inspections. This amendment is prompted by reports of broken lockwires on the bearing retainer nut of the pivot fittings of the horizontal stabilizer due to inadequate torquing of the nut. The actions specified in this AD are intended to prevent failure of the lockwires, which could result in loosening of the retainer nut for the pivot bearing of the horizontal stabilizer, and subsequent migration of the pivot bearing. This condition, if not corrected, could result in reduced controllability of the airplane.
99-03-05: This amendment adopts a new airworthiness directive (AD) that is applicable to Textron Lycoming Model O-540-F1B5 reciprocating engines. This action requires the removal and replacement of the crankshaft gear retaining bolts. This amendment is prompted by 2 reported failures of the crankshaft gear retaining bolts. The actions specified in this AD are intended to prevent failure of the crankshaft gear retaining bolts, which can result in engine failure and subsequent autorotation and forced landing.
2003-13-15 R1: This amendment revises an existing airworthiness directive (AD), for the specified Schweizer Aircraft Corporation (Schweizer) model helicopters, that currently requires inspecting the lugs on certain aft cluster fittings and each aluminum end fitting on certain tailboom struts. Modifying or replacing each strut assembly within a specified time period and serializing certain strut assemblies are also required. Additionally, a one-time inspection and repair, if necessary, of certain additional cluster fittings, and replacement and modification of certain cluster fittings within 150 hours time-in- service (TIS) or 6 months, whichever occurs first, is required. This amendment requires the same actions as the existing AD, but revises the Applicability section of the AD. This amendment is prompted by the discovery of an error in the Applicability section of the existing AD. The actions specified by this AD are intended to prevent failure of a tailboom support strut or a cluster fitting, which could cause rotation of a tailboom into the main rotor blades, and subsequent loss of control of the helicopter. \n\nDATES: Effective August 10, 2004.\n\n\tThe incorporation by reference of certain publications listed in the regulations was approved previously by the Director of the Federal Register as of August 12, 2003 (68 FR 40478, July 8, 2003).
2012-18-14: We are adopting a new airworthiness directive (AD) for certain serial numbers of Pratt & Whitney Canada (P&WC) PW901A auxiliary power units (APUs) approved under Technical Standard Order TSO-C77A and installed on, but not limited to, Boeing 747-400 series airplanes. This AD requires modifications of the rear gas generator case, exhaust duct support, and turbine exhaust duct flanges. This AD was prompted by several events of high-pressure turbine blade fracture leading to separation of the rear gas generator case and release of high energy debris. We are issuing this AD to prevent separation of the rear gas generator case and release of high energy debris, which could result in injury and damage to the airplane.
2011-18-10: We are superseding an existing airworthiness directive (AD) for the products listed above. The existing AD currently requires reviewing the airplane maintenance records to determine whether an engine has been removed from the airplane since the airplane was manufactured. For airplanes on which an engine has been removed, the existing AD also requires an inspection of the aft engine mount to determine if the center link assembly is correctly installed, and follow-on actions if necessary. This new AD expands the applicability to include airplanes on which the engine has not been previously removed, and Model 737-900ER airplanes. This AD was prompted by reports indicating that operators found that the center link assembly for the aft engine mount was reversed on several airplanes that had not had an engine removed since delivery. We are issuing this AD to prevent increased structural loads on the aft engine mount, which could result in failure of the aft engine mount and consequent separation of the engine from the airplane.