Results
2011-06-03: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires measuring the electrical bond resistance between the motor operated valve (MOV) actuators and airplane structure for the main, center, auxiliary, and horizontal stabilizer fuel tanks, as applicable, and corrective action if necessary; revising the maintenance program to incorporate airworthiness limitation (AWL) No. 28-AWL-21 or AWL No. 28-AWL-27, as applicable; and replacing production-installed laminate phenolic spacers with metallic spacers between the fuel jettison MOV and the airplane structure, as applicable. This AD was prompted by fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent electrical current from flowing through an MOV actuator into a fuel tank, which could create a potential ignition source inside the fuel tank. This condition, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss ofthe airplane.
2011-07-01: We are superseding an existing airworthiness directive (AD) for General Electric Company (GE) CF6-45 and CF6-50 series turbofan engines. That AD currently requires replacing certain forward and aft centerbodies of the long fixed core exhaust nozzle (LFCEN) assembly. This AD adds certain new forward and aft centerbody part numbers (P/Ns) to the list requiring replacement. This AD was prompted by the discovery of more LFCEN forward and aft centerbody P/Ns that require replacement. We are issuing this AD to prevent the forward and aft centerbody of the LFCEN assembly from separating from the engine, causing damage to the engine, and damage to the airplane.
70-04-03: 70-04-03\tBOEING: Amdt. 39-941 as amended by Amendment 39-1020. Applies to Model 737 series airplanes. \n\n\tCompliance required as indicated unless already accomplished. \n\n\tTo prevent possible damage to airplane structure, systems and components due to failure of the APU bleed air duct or failure of the APU fire extinguisher bottle to discharge safely, or from exposure to an overheat condition following ground operation of the pneumatic system with bleed air from the APU or external ground service, accomplish the following: \n\n\t(a)\tWithin 25 hours time in service after the effective date of this directive, \n\n\t\t(1)\tInstall a placard in full view of the pilot to read: "Discharge APU fire extinguisher bottle whenever left bleed air overheat light illuminates", or "Discharge APU fire extinguisher bottle whenever left bleed air wing-body overheat light illuminates." \n\n\t\t(2)\tInstall a placard in the cockpit in full view of the pilot and install an external placard adjacent to thepneumatic ground service connection to read: "Monitor cockpit bleed air overheat system during all operations of the pneumatic system", or "Monitor cockpit bleed air wing-body overheat system during all operations of the pneumatic system." \n\n\t(b)\tIn lieu of the placard installations required by para. (a)(2), the cockpit bleed air wing- body overheat system and master caution light must be checked prior to further flight for an overheat condition following ground operation of the pneumatic system with bleed air from the APU or external pneumatic ground service. If an overheat condition exists, the source of the overheat condition must be established. Inspect the airplane structure, systems and components for overheat damage and repair if necessary. \n\n\t(c)\tWithin 50 hours time in service after the effective date of this AD, unless already accomplished within the last 500 hours time in service prior to the effective date of this AD, and thereafter at intervals not to exceed 500 hours time in service, inspect the APU bleed air duct, part number 69/37931-3, -4, or -6 for cracks and replace cracked ducts in accordance with Boeing Alert Service Bulletin 36/1003 dated 17 January 1970 or later FAA approved revision, or method approved by the Chief, Aircraft Engineering Division, FAA Western Region.\n \n\t(d)\tIn lieu of the placards and procedures required in paragraphs (a) and (b), remove APU fire extinguisher container, Part Number 806000-21 and install Part Number 806000-31 container in accordance with Boeing Service Bulletin 26-1011, dated June 9, 1970, or later FAA approved revision or an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region.\n \n\tNOTE: Do not insert operational procedure specified in revision 1, dated 19 January 1970, to step E of Boeing S.B. 36/1003." \n\n\tAmendment 39-941 effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated 31 January 1970. \n\n\tThis Amendment (39-1020) becomes effective July 9, 1970.
71-11-03: 71-11-03 FAIRCHILD-HILLER: Amdt. 39-1209. Applies to Fairchild Hiller FH 1100 and Model 1100 type helicopters certificated in all categories with short stabilizers, P/N 24 62001, or extended Stabilizers, P/N 24 62001 31. 1. A. Before the next flight, install the following placard in the cockpit in full view of the pilot. "VNE NOT TO EXCEED 80 MPH IAS" B. Remove placard "VNE NOT TO EXCEED 80 MPH IAS" on helicopters with stabilizers modified in accordance with 2 below. 2. Within the next 100 hours' time in service after receipt of this message, unless already accomplished, modify stabilizers, P/N 24 62001 and P/N 24 62001 31, in accordance with Section Two of Fairchild Hiller Service Bulletin FH 1100 62 6 dated 18 March 1971 or later approved revision or an equivalent modification approved by Chief, Engineering and Manufacturing Branch, Eastern Region. This amendment is effective May 19, 1971 and was effective for all recipients of the airmail letter of March 9, 1971 and amending airmail letter of March 25, 1971 upon receipt.
2011-03-06: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters. This AD requires replacing the aluminum tail rotor (T/R) blade pitch control shaft with a steel T/R blade pitch control shaft. This AD is prompted by an incident involving a Eurocopter Model AS-365N2 helicopter on which there was a loss of control of the T/R due to a broken shaft. The actions specified by this AD are intended to prevent failure of the T/R blade pitch control shaft, loss of T/R control, and subsequent loss of control of the helicopter.
75-04-10: 75-04-10 LOCKHEED: Amendment 39-2090. Applies to L-1011-385-1 airplanes certificated in all categories. Compliance required within 10 calendar days after the effective date of this AD, unless already accomplished. To prevent heater blanket overheat conditions and possible fires caused by a malfunctioning cargo sump drain heater, Electrofilm P/N 111202-101 (LAC Control No. 672726- 101), accomplish (a) or (b) below: (a) Disconnect the C-1, C-2, and C-3 cargo compartment drain heaters per Lockheed Alert Service Bulletin 093-30-A032, dated January 23, 1975, or later FAA-approved revisions, or; (b) Equivalent deactivation modifications approved by the Chief, Aircraft Engineering Division, FAA Western Region. (c) An airplane may be flown to a base for the performance of the work required by this AD per FAR's 21.197 and 21.199. (d) The C-1, C-2 and C-3 cargo compartment drain heaters may be reactivated in accordance with modifications or instructions approved by theChief, Aircraft Engineering Division, FAA Western Region. The approved data must reference this AD, and the FAA-approval date. This amendment becomes effective February 19, 1975.
2011-05-02: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires repetitively inspecting the elevator control tabs for discrepancies and, if any discrepancies are found, taking necessary corrective actions to bring all discrepancies within acceptable tolerances. This AD also requires reporting certain inspection results to the FAA. This AD was prompted by an evaluation of revisions to the manufacturer's maintenance manual that adds new repetitive inspections of the elevator control tabs. To require compliance with these inspections for U.S. owners and operators we are mandating the inspections through the rulemaking process. We are issuing this AD to add new repetitive inspections of the elevator control tabs. If these inspections are not done, excessive free-play in the elevator control tabs could develop. This condition could lead to loss of tab control linkage and severe elevator flutter. Such elevator flutter could lead to possible loss ofcontrol.
75-09-06: 75-09-06 CESSNA: Amendment 39-2176. Applies to A185 series (Serial Numbers 18502008 through 18502650) airplanes and A188 series (Serial Numbers 18800833 through 18801374). Compliance: Required as indicated, unless already accomplished. To preclude the collapse of the existing flexible engine induction air duct, within the next 50 hours' time in service after the effective date of this AD, accomplish the following: Replace the flexible engine induction air duct with a new flexible engine induction air duct (P/N 1650044-1); duct adapter (P/N 1652021-10); and drain line (P/N 0700147-82)(A185 only), in accordance with Cessna Service Letter SE75-5, dated February 7, 1975, or later approved revisions, or any alternate means of compliance approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective May 5, 1975.
2011-04-04: We are superseding an existing airworthiness directive (AD) for Pratt & Whitney (PW) JT8D-209, -217, -217A, -217C, and -219 turbofan engines. That AD currently requires revisions to the engine manufacturer's time limits section (TLS) to include enhanced inspection of selected critical life-limited parts at each piece-part opportunity. This new AD modifies the TLS of the manufacturer's engine manual and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements. This AD was prompted by PW developing, and the FAA approving, improved inspection procedures for the critical life-limited parts. The mandatory inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. We are issuing this AD to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
75-20-05: 75-20-05 BOEING: Amendment 39-2371 as amended by Amendment 39-2426 is further amended by Amendment 39-2446. Applies to all Boeing Model 747 series airplanes certificated in all categories. Compliance required as indicated unless already accomplished. \n\tTo prevent fore flap separations, accomplish the following:\n \tA.\tWithin the next 100 flights after the effective date of this AD, unless accomplished within the last 200 flights, and at intervals thereafter not to exceed 350 flights: \n\t\t1.\tInspect all fore flap track, airload rollers for freedom of movement, and inspect upper and lower surfaces of the tracks and rollers for evidence of sliding. Inspect and lubricate rollers in accordance with procedures described in Boeing Service Bulletin 747-57-2107 dated November 3, 1972, or later FAA approved revisions, or the Boeing 747 Maintenance Manual. Replace any seized rollers before further flight unless, upon inspection: \n\t\t\t(a)\tThe fittings attaching the fore flap to the sequencecarriage are found free of cracks. \n\t\t\t(b)\tThe exposed surfaces of the fore flap tracks are found free of galling. \n\t\t\t(c)\tThe flap is found free of any evidence of binding or racking. \n\tIf (a) - (c) are accomplished the airplane may continue in service for a maximum of 10 flights before the seized rollers are replaced, provided the fore flap tracks are lubricated prior to each flight. \n\t\t2.\tInspect the attach (sequence) fittings of the inboard trailing edge fore flap (P/N 65B39025-1 and -2 opposite, or 65B39025-3 or 65B02015-1 and -2 opposite inboard fitting) for cracks in accordance with Boeing Service Bulletins 747-57-2119, Revision 2, dated June 20, 1975, and 747-57- 2088, Revision 2, dated June 30, 1975, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. Replace any cracked fittings before further flight if any crack exceeds the limits listed in Boeing Service Bulletin Nos. 747-57-2088 or 747-57-2119. \n\t\t3.\tInspect the outboard fore flap inboard carriage frame for cracks in accordance with Boeing Service Bulletin 747-57-2126, Revision 2, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. Parts found cracked which are within the limits of Figure 1, Part III of Boeing Service Bulletin 747-57-2126, may be repaired in accordance therewith and reinspected at intervals not to exceed 40 landings. If cracks exceed the limits given in Boeing Service Bulletin 747-57-2126, replace the fitting before further flight. \n\tB.\tUnless already accomplished, with the next 350 flights after the effective date of this AD: \n\tRemove the existing steel bolts attaching the fore flap carriage stop to the flap tracks on the outboard flaps and install new bolts with sealant in accordance with Boeing Service Bulletin 747-57- 2128, Revision 1, dated April 25, 1975, or later FAA approved revisions. \n\tC.\t1.\tReplace the three forward inboard fore flap airload rollers with new or overhauled rollers on or before December 31, 1976. The replacement rollers are to be lubricated with MIL-G-23827 grease, or an equivalent grease approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, which does not contain molybdenum disulfide (MoS2) as an additive. Airplanes delivered with the redesigned rollers which have been lubricated at an interval not greater than that allowed by this AD, need not have these bearings replaced. \n\t\t2.\tReplace all inboard trailing edge fore flap attach fittings on or before December 31, 1976, in accordance with Boeing Service Bulletin No. 747-57-2119, Revision 2, and Boeing Service Bulletin No. 747-57-2088, Revision 2, or later FAA approved revisions, or replace fittings in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tD.\tUpon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, may adjust the repetitive 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 adjustment period. Fleet average flight time may be used to calculate the number of flights. \n\tE.\tUnless already accomplished, on or before the next airload roller scheduled inspection, cut inspection holes in the mid flaps in accordance with Boeing Service Bulletin No. 747-57-2138. \n\tF.\tReplacement of the remaining inboard fore flap airload rollers and all outboard fore flap airload rollers with new or overhauled rollers lubricated with MIL-G-23827 or equivalent constitutes terminating action for the inspections required by paragraph A1. Replacement of both the inboard and outboard fore flap attach fittings constitutes terminating action for the inspections required by paragraphs A2 and A3. \n\tThe 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). \n\tAll persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Boeing Commercial Airplane Company, P. O. Box 3707, Seattle, Washington 98124. The documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tAmendment 39-2371 became effective October 24, 1975. \n\tAmendment 39-2426 becomes effective December 12, 1975.\n\tThis amendment 39-2446 becomes effective December 12, 1975.