Results
2017-26-05: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Models G-1159A (GIII), G-IV, and GIV-X airplanes. This AD was prompted by a report that certain flap tracks were manufactured with the upper flange thickness less than design minimum. This AD requires replacing any defective flap track. We are issuing this AD to address the unsafe condition on these products.
2000-24-03: This amendment supersedes an existing airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to provide the flightcrew with additional information regarding procedures to ensure complete pressurization of the hydraulic lines for the flaps. This amendment requires revising the existing AFM revision to include a flap system test to be performed prior to the first flight of the day. This amendment also requires, for certain airplanes, modification of the flap actuators of the flight controls. The actions specified by this AD are intended to prevent an uncommanded retraction of the flaps during takeoff, which could result in an aborted takeoff and consequent potential for runway overrun.
86-25-07: 86-25-07 ROLLADEN-SCHNEIDER FLUGZEUGBAU GmbH: Amendment 39-5487. Applies to Model LS-6, all serial numbers. Compliance is required prior to further flight, after the effective date of this AD, unless already accomplished. To prevent possible damage of the control stick, accomplish the following: a) Remove Bezel from airspeed indicator and mask out the red arc with tape that would not interfere with airspeed indictor needle and readability of the instrument. b) Replace Bezel to airspeed indicator and mark a red radial line on the face of the Bezel 0.05" wide, 0.30" long at 200 km/h (108 kts) establishing a new maximum airspeed limit. c) Install a placard on the instrument panel in clear view of the pilot which states: "Maximum Airspeed (IAS): 200 km/h (108 kts)." d) On existing placard mask out with tape the yellow arc limitations 108 - 146 kts, and the following red arc airspeed indicator markings: Vne 6500 Ft 146 kts Vne 6501-9800 Ft 139kts Vne 9801-19700 Ft 118 kts e) Flight manual pages 2.2, Limitations; page 2.3, Airspeed Indicator Markings; page 2.7, Placards, are obsolete. f) Attach a copy of this Airworthiness Directive to the Flight Manual. NOTE: Rolladen-Schneider Technical Bulletin No. 6009 dated July 7, 1986, applies to this AD. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium 09667-1011; telephone 513.38.30 Ext 2710, or the Manager, New York Aircraft Certification Office, Aircraft Certification Division, FAA, New England Region, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581, telephone (516) 791-6220. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations 21.197 and 21.199 to a base where the AD can be accomplished. This amendmentbecomes effective December 30, 1986.
2000-24-15: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires a one-time detailed visual inspection to detect discrepancies of all electrical wiring installations in various areas of the airplane; and corrective actions, if necessary. This amendment is necessary to prevent electrical arcing and/or heat damaged wires due to improper wire installations during manufacture and/or maintenance of the airplane, and consequent fire and smoke in various areas of the airplane. This amendment is intended to address the identified unsafe condition.
98-14-08: 98-14-08 ROBINSON HELICOPTER COMPANY: Docket No. 98-SW-30-AD. Applicability: Model R22 helicopters, with forward flexplate, part number (P/N) A947-1 A through D, or P/N A193-1, installed, certificated in any category. NOTE 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (b) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by thisAD. In no case does the presence of any modification, alteration, or repair remove any helicopter from the applicability of this AD. Compliance: Required within 25 hours time-in-service (TIS) or 15 calendar days, whichever occurs first, unless accomplished previously. To prevent failure of the flexplate, which could result in failure of the main rotor drive system and subsequent loss of control of the helicopter, accomplish the following: (a) Remove the flexplate and replace it with an airworthy flexplate, P/N A947-1 E or F, in accordance with the following: (1) With the clutch disengaged, support the forward end of the clutch shaft, P/N A166-1, and remove the forward flexplate, P/N A947-1 or A193-1, and the intermediate flexplate, P/N A947-2 or P/N A193-2. Record any shim locations for reinstallation. (2) Install a zero TIS forward flexplate, P/N A947-1 E or F, and any shims that were noted. Use washers, P/N AN960-516 or AN960-516L, under the nut so that 2-4threads are exposed. Torque the fasteners. (3) Inspect the sheave alignment. (4) Inspect the clutch shaft, P/N A166-1, angle. (5) Reinstall the intermediate flexplate and shim. NOTE 2: Robinson R22 Maintenance Manual, Sections 1.320, 7.230, 7.240, and 7.330 pertain to paragraphs (a)(2), (a)(3), (a)(4), and (a)(5) of this AD, respectively. NOTE 3: Robinson Helicopter Company R22 Service Bulletin SB-75, dated November 22, 1994, pertains to the subject of this AD. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Los Angeles Aircraft Certification Office, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office. NOTE 4: Information concerning the existence of approved alternative methods of compliance with thisAD, if any, may be obtained from the Los Angeles Aircraft Certification Office. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the helicopter to a location where the requirements of this AD can be accomplished. (d) Priority Letter AD 98-14-08, issued June 25, 1998, becomes effective upon receipt.
97-13-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires loosening certain nuts on the horizontal stabilizer control unit (HSCU) to reduce stress on bolts; a one-time inspection of certain bolts on the HSCU to detect cracking, and replacement, if necessary; application of corrosion protection to these bolts; and reassembly and reidentification of the modified HSCU. This amendment is prompted by reports indicating that stress corrosion, resulting from overtightening of nuts on these bolts, has caused some of these bolts to crack and fail. The actions specified by this AD are intended to prevent failure of these bolts because of stress corrosion cracking which, if not corrected, could lead to loss of control of the horizontal stabilizer and reduced controllability of the airplane.
2007-07-13: 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: Avionics and electrical wire harnesses are routed behind the Primary Flight Displays (PFD) tray at the rear of the instrument panel. In some cases, the wire harness has been found to be chafing on the PFD tray. That could result in electrical arcing and shorting and subsequent loss of systems essential for safe flight. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2000-24-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires inspections to detect cracking of the frame web, doubler, and inner chord of the forward edge frame of main entry door number 1, and various follow-on actions. This amendment is prompted by reports of cracking in the frame web, doubler, inner chord, and strap of the forward edge frame of main entry door number 1. The actions specified by this AD are intended to prevent cracks in the frame web and doubler of the forward edge frame of main entry door number 1, which could result in inability of the edge frame to react door stop loads, and consequent rapid depressurization of the airplane.
2017-26-04: We are superseding Airworthiness Directive (AD) 2009-25-07 for Airbus Helicopters Model EC120B helicopters. AD 2009-25-07 required amending the rotorcraft flight manual supplement (RFMS) and pre-flight checking the emergency flotation gear before each flight over water. Since we issued AD 2009-25-07, Airbus Helicopters developed a terminating action and identified an additional part- [[Page 60293]] numbered emergency floatation gear part with the unsafe condition. This new AD retains the requirements of AD 2009-25-07, expands the applicability, and adds a terminating action for the repetitive inspections. The actions of this AD are intended to correct an unsafe condition on these helicopters.
87-02-04: 87-02-04 BRITISH AEROSPACE: Amendment 39-5497. Applies to Models HP 137 Mk.1 (all serial numbers), Jetstream Series 200 (all serial numbers), and Jetstream Model 3101 airplanes (serial numbers 601 to 606) equipped with Main Landing Gear Type Numbers 1863 and 1864 (all suffixes), certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To prevent the development of hazardous cracks in the main landing gear pintle housing, accomplish the following: (a) Within 300 landings and every 1200 landings thereafter: Conduct an eddy current inspection in accordance with Section 2 "Accomplishment Instructions", Part A "Non- destructive Testing" of British Aerospace (BAe) Mandatory Service Bulletin (MSB) No. 32-A- JA851226 dated December 19, 1985, Section 2 "Accomplishment Instructions" of BAe Air Weapons Division (AWD) Service Bulletin (S/B) No. 32-19 dated December 19, 1985. If cracks are found, before further flight, carry out repairs in accordance with AWD S/B No. 32-19. (b) At intervals of 300 landings after the initial inspection, required by paragraph (a) of this AD, conduct a visual inspection in accordance with Section 2 "Accomplishment Instructions," Part B, "Visual Inspections" of AWD S/B No. 32-19. If indications of cracks are discovered, conduct an eddy current inspection in accordance with paragraph (a) of this AD. If cracks are found, before further flight, carry out repairs in accordance with AWD S/B No. 32-19. (c) Within 300 landings after a heavy or abnormal landing, conduct an eddy current inspection in accordance with paragraph (a) of this AD. (d) If the actual number of landings is unknown for the purpose of complying with this AD, one landing may be substituted for each one-half hour of flight unless the operator substantiates a different flight hours to landings ratio. This substantiation must be submitted to, and approved by, the Manager, Aircraft Certification Staff, address below. (e) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (f) The intervals between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishment of these inspections concurrent with other scheduled maintenance on the airplane. (g) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, B-1000 Brussels, Belgium. All persons affected by this directive may obtain copies of the documents referred to herein upon request to British Aerospace, Engineering Department, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041; Telephone (703) 435-9100; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on January 30, 1987.