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2018-03-20: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-300 series airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. This AD was prompted by a report indicating that a pipe of the fire extinguishing system in the forward cargo compartment was too long, and therefore could be installed only under stress, which applies pressure to the pipe clamp. We are issuing this AD to address the unsafe condition on these products.
78-17-02 R3: 78-17-02 R3 PRATT & WHITNEY AIRCRAFT: Amendment 39-3281 as amended by Amendment 39-4334 and 39-4407 is further amended by Amendment 39-4818. Applies to Pratt & Whitney Aircraft models JT8D-9, - 9A, -11, -15, -15A, -17, -17A, -17R, and -17AR turbofan engines. Compliance is required as indicated, unless already accomplished. To detect cracks in compressor front hubs, P/Ns 594301, 791801, 640601, 743301, 750101, and 749801, except those excluded by serial number in Pratt & Whitney Aircraft Alert Service Bulletin No. 4841, Revision 6, dated July 15, 1983, which could result in fracture of the retention lugs and release of first stage fan blades, accomplish the following: (A) Inspect front compressor front hubs for cracks in the blade slots in accordance with Pratt & Whitney Aircraft Alert Service Bulletin No. 4841, Revision 6, dated July 15, 1983, or equivalent means approved by the Manager, Engine Certification Branch, New England Region, and in accordance with limits specified in Paragraphs (B) and (C) of this AD. Remove cracked compressor front hubs prior to further flight. (B) Hubs not previously inspected shall be inspected within 1,000 cycles from the effective date of this AD or before reaching the initial inspection limits specified in Column I of Paragraph (D), whichever occurs later, except do not exceed 13,000 total cycles. Repeat inspections at intervals listed in Column II, or Column III, Paragraph (D), thereafter. (C) Hubs which have been previously inspected shall be reinspected within 1,000 cycles after the effective date of this AD or before reaching the initial inspection limit specified in Column I, Paragraph (D), or before reaching the repetitive inspection limits specified in Column II or Column III of Paragraph (D), whichever comes later. Repeat inspections at intervals listed in Column II or Column III, Paragraph (D), thereafter. (D) Model Column I, initial inspection limit (cycles) Column II, Eddy current repetitive inspection limit (cycles) Column III, on-wing ultrasonic repetitive repetitive inspection limit (cycles) JT8D-9, -9A 13,000 6,000 2,000 JT8D-11 10,500 6,000 2,000 JT8D-15, -15A 9,500 5,000 1,500 JT8D-17, -17A 8,500 5,000 1,500 JT8D-17R, -17AR 8,000 5,000 1,500 NOTE: If the initial inspection or repetitive inspection is in paragraph (D) apply. If, however, the initial inspection or repetitive inspection is achieved by an eddy current inspection on an uninstalled engine, the Column II inspection limits of paragraph (D) would apply. (E) Upon request of the operator, an FAA maintenance inspector, subject to the approval of the Manager, Engine Certification Branch, FAA, New England Region, may adjust the inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. (F) For hubs that have been installed in more than one engine model, the inspection schedule for the engine model with the highest thrust rating in which it has operated is applicable. The manufacturer's Alert Service Bulletin identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a). All persons affected by this directive who have not already received the service bulletin from the manufacturer may obtain copies upon request to Pratt & Whitney Aircraft, Commercial Products Division, 400 Main Street, East Hartford, Connecticut 06108. The service bulletin may also be examined at Federal Aviation Administration, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, Massachusetts 01803. Amendment 39-3281 became effective September 20, 1978. Amendment 39-4334 became effective March 4, 1982. Amendment 39-4407 became effective June 28, 1982. This Amendment 39-4818 becomes effective March 30, 1984.
66-18-04: 66-18-04 PIPER: Amdt. 39-266 Part 39 Federal Register July 26, 1966. Applies to Model PA-24-260 and PA-30 Airplanes, Serial Numbers 24-4247, 24-4300 through 24-4443, 24- 4445 through 24-4448, 24-4450 through 24-4452, 24-4454 through 24-4456, 24-4461, 24-4465, 24-4467, 24-4474, 24-4475, 30-853, 30-902 through 30-1087, 30-1089 through 30-1093, 30- 1095, 30-1096, 30-1098 through 30-1106, 30-1109, 30-1112, 30-1113, 30-1117, 30-1120, 30- 1127, and 30-1129 through 30-1137. Compliance required within the next 10 hours' time in service after the effective date of this AD, unless already accomplished. To prevent inadvertent unlatching of the baggage door, accomplish the following: (a) Inspect the baggage door latch to ensure that the latch extends through the latch striker plate 1/4 inch +0, -1/16 inch, measured from the top of the striker plate. (b) If the latch does not extend 1/4 inch +0, -1/16 inch through the latch striker plate, before further flight accomplish the following, or an FAA-approved equivalent: Replace the present latch striker plate retaining screws with AN 526-1032R14 screws and insert AN 960-10 washers between the door jamb and the latch striker plate, to obtain the 1/4 inch +0, -1/16 inch dimension. However, if more than three washers would be required, rework the door jamb to obtain the 1/4 inch +0, -1/16 inch dimension in an FAA-approved manner. (Piper Service Letter No. 478, dated June 13, 1966, pertains to this subject). This directive effective August 10, 1966.
2003-02-05: This amendment adopts a new airworthiness directive (AD) for certain Eurocopter France (Eurocopter) model helicopters. This action requires measuring the diameter of the sliding door roller (roller) and the dimensions of the front end opening of the sliding door middle rail (rail) to determine if excessive wear exists, and if necessary, installing a placard prohibiting the operation of the sliding door during flight. This amendment is prompted by an incident in which a roller came out of the middle rail during a door-opening operation in flight. The actions specified in this AD are intended to prevent the roller from coming out of the middle rail when opening the door, which could lead to the sliding door separating from the helicopter during flight, damage to critical flight components, and subsequent loss of control of the helicopter.
90-17-01: 90-17-01 ROBINSON HELICOPTER COMPANY (RHC): Amendment 39-6687. Docket No. 89-ASW-58.\n\n\tApplicability: All Model R22 series helicopters, certified in any category, equipped with carburetor air box latches. \n\n\tCompliance: Required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. \n\n\tTo prevent carburetor air box latches from coming loose in flight, which could result in power loss in critical maneuvers close to the ground, accomplish the following: \n\n\t(a)\tRemove the three carburetor air box latches and replace with four bolts in accordance with the following: \n\n\t\t(1)\tOpen the air box and remove the filter element. \n\n\t\t(2)\tRemove the air box from the helicopter. \n\n\t\t(3)\tDrill out the four rivets in the cover holding 0.25 inch diameter spacers and enlarge the holes to 0.191 inch diameter. Discard the spacers. \n\n\t\t(4)\tClose the cover, and using the holes in the cover as guides, drill four matching holes through the upper box in line with the holes in the cover. \n\n\t\t(5)\tOpen the air box and drill out all the rivets holding the latches to the cover. Discard the latches and angles. Clean the drilling chips from the box. \n\n\t\t(6)\tReinstall the air box to the helicopter. \n\n\t\t(7)\tInstall the filter element and secure the cover using four AN3-35A bolts, AN960-10L washers, AN970-3 washers, and NAS679A3 nuts. \n\n\tNOTE: Refer to Figure 1 for accomplishing the instructions required by paragraph (a). \n\n\t(b)\tAn alternate method of compliance or adjustment of the compliance time, which provides an equivalent level of safety, may be used if approved by the Manager, Los Angeles Aircraft Certification Office, ANM-100L, FAA, Northwest Mountain Region, 3229 E. Spring Street, Long Beach, California 90806-2425. \n\n\tNOTE: Robinson Helicopter Company Service Bulletin Number 61, dated July 28, 1989, pertains to this AD. \n\n\tThis amendment (39-6687, AD 90-17-01) becomes effective on September 10, 1990. \n\nSB 61
97-13-07: This amendment adopts a new airworthiness directive (AD) that is applicable to Hamilton Standard 54H60 series propellers. This action requires removing from service affected propeller blades, and returning those blades to the manufacturer or an approved facility for inspection, rework, and return to service. This amendment is prompted by reports of a propeller blade manufacturing defect. The actions specified in this AD are intended to prevent propeller blade fracture due to the manufacturing defect, which could result in propeller blade separation and loss of control of the aircraft.
2011-16-02: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires revising the airplane flight manual (AFM) to advise the flightcrew to use certain procedures during descent in certain icing conditions. This AD was prompted by reports of several in-flight engine flameouts, including multiple dual engine flameout events and one total power loss event, in ice-crystal icing conditions. We are issuing this AD to ensure that the flightcrew has the proper procedures to follow in certain icing conditions. These certain icing conditions could cause a multiple engine flameout during flight with the potential inability to restart the engines, and consequent forced landing of the airplane.
2018-03-04: We are adopting a new airworthiness directive (AD) for Rosemount Aerospace Model 851AK pitot probes that were repaired by CSI Aerospace, Inc. between January 2013 and July 2014 that are installed on airplanes. This AD was prompted by a report that certain pitot probes are indicating the wrong airspeed during flight. This AD requires inspecting the airplane to determine the number of affected pitot probes installed and replacing the affected pitot probes. We are issuing this AD to address the unsafe condition on these products.
2003-02-06: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada Limited (Bell) Model 407 helicopters. This action requires visually inspecting certain tailboom gearbox support castings (castings) for cracks and replacing the tailboom assembly if a crack is found. This amendment is prompted by an incident in which a crack was discovered on the casting that holds the tail rotor gearbox and vertical fin. The actions specified in this AD are intended to detect a crack in the casting and prevent failure of the casting, loss of the vertical fin and tail rotor, and subsequent loss of control of the helicopter.
49-41-01: 49-41-01 LOCKHEED: Applies to All Models 649, 749 and 749A Aircraft Equipped With Curtiss Model C632S-A Propellers and Wright Model 749C18BD-1 Engines. Compliance required on items 1, 2 and 3 by October 11, 1949. In order to reduce the possibility of subjecting propellers to excessive stresses and to detect hub cracks which may have been caused by such stresses, the following steps are to be taken: 1. Change present 2,100-2,375 r.p.m. restriction to 2,050-2,375. Placard airplane or mark tachometer with green radial line for single point operation at 2,025 r.p.m. Other restrictions listed in AD 48-26-01 still apply. 2. Limit gross weight to 102,000 pounds maximum. 3. On hubs having more than 1,500 hours total service time, visually inspect for cracks the rear outboard portions of the hub barrels. Inspection is to be continued at intervals as close to 10 hours as practical but not exceeding 20 hours maximum. It is strongly recommended that whenever the necessary equipment is available, magnetic inspections be made at the same intervals in accordance with Curtiss Instruction entitled "Field Magnetic Inspection of C6832S-A Hubs." Remove from service any hub showing a crack. To facilitate these inspections, the propeller power unit is covered or sealed to prevent the entrance of water in the unit. As an alternate to the removal of the spinner, these inspections may be conducted through three 5-inch diameter holes located in the side of the spinner in accordance with instructions issued by Curtiss. 4. All C632S-A hubs (P/N 116366) with over 2,000 hours total time shall be retired from service as soon as possible and not later than November 30, 1949. 5. Items 1 and 2 also apply when the C-632S-B hub (P/N 129914) is used to replace the C632S-A hub (P/N 116366).