Results
64-08-02: 64-08-02 LOCKHEED: Amdt. 711 Part 507 Federal Register April 8, 1964. Applies to All Model 1649A Series Aircraft. Compliance required as indicated. (a) Within 350 hours' time in service after the effective date of this AD, unless already accomplished, and within each 5,500 hours' time in service thereafter following the initial inspection, inspect for cracks in the right and left hand wing upper milled skin panel (second plank aft of the front spar) in the area aft of the Nos. 2 and 3 nacelles between W.S. 175 and W.S. 283.5 at the forward and aftmost risers adjacent to the skin lap joints using the ultrasonic shear wave inspection technique described in Lockheed Letter FS/267105-L or an FAA approved equivalent. (b) Within 1,400 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 1,050 hours' time in service, visually inspect for cracks in the right and left hand wing upper milled skin panel (second plank aft of the frontspar) in the area aft of the Nos. 2 and 3 nacelles between W.S. 175 and W.S. 283.5 at the forward and aft-most risers adjacent to skin lap joints. (c) Any cracks found during the inspections specified in (a) and (b) shall be repaired in accordance with Lockheed Report 11885 (Structural Repair Manual), Figure 2-10 or an FAA approved equivalent before further flight, except that the aircraft may be ferried in accordance with the provisions of Section 1.76 of CAR Part 1 to a base where the repairs are to be accomplished. (d) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Western 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 increase for such operator. (Lockheed Letter FS/267105-L dated August 30, 1963, covers this same subject.) This directive effective May 11, 1964.
2020-20-05: The FAA is superseding Airworthiness Directive (AD) 2018-25-02 and AD 2019-23-01, which applied to certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, -233, -251N, -252N, and -271N airplanes; and Model A321 series airplanes. Those ADs require revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive maintenance requirements and/or airworthiness limitations. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary and models need to be added to the applicability. The FAA is issuing this AD to address the unsafe condition on these products.
2003-21-11: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211-524 series turbofan engines. This AD requires replacing the dedicated generator rotor assembly, the adaptor casing on the high speed gearbox (HSGB), and bearings with new design parts on certain engines. This AD is prompted by several reports of dedicated generator rotor assembly bearing failures. We are issuing this AD to prevent possible uncommanded engine acceleration with no reaction to throttle movement, which could result in uncontrollable asymmetric engine thrust levels during takeoff or climb.
88-21-07 R1: 88-21-07 R1 PIPER: Amendment 39-6042 as revised by Amendment 39-6272. Applicability: Model PA-23, PA-23-160, PA-23-250, PA-23-235 and PA-E23-250 (all serial numbers) airplanes certificated in any category, except Model PA-23-250 airplanes, serial numbers 27-7654001 through 27-8154030. Compliance: Required within the next 60 calendar days after the effective date of this AD and at intervals not to exceed 12 calendar months thereafter, unless already accomplished per the unrevised version of this AD. To reduce the possibility of precipitation and/or wash water from entering the fuel filler compartment and leaking into the fuel cell resulting in engine failure, accomplish the following: (a) Inspect the fuel vent/drain lines, the thermos type fuel cell caps, and the fuel filler compartment covers on both main fuel cell systems and, if installed, both auxiliary fuel cell systems in accordance with the instructions in Piper Service Bulletin (SB) No. 340, dated May 24, 1971. (b) If any defects are found, correct them before further flight. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Atlanta Aircraft Certification Office, ACE-115A, Federal Aviation Administration, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. This AD revises AD 88-21-07, Amendment 39-6042, which became effective on November 6, 1988. This amendment (39-6272, AD 88-21-07 R1) becomes effective on August 22, 1989.
2020-21-04: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A300 F4-600R series airplanes. This AD was prompted by a report of damaged main deck cargo crossbeams on the right-hand side, between certain frame locations. This AD requires repetitive detailed inspections of the affected main deck cargo crossbeams for any damage, and depending on findings, accomplishment of applicable corrective actions, 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.
98-16-17 R1: This amendment rescinds Airworthiness Directive (AD) 98-16-17 R1, which is applicable to all Cessna Model 750 Citation X series airplanes. That AD requires repetitive in-flight functional tests to verify proper operation of the secondary horizontal stabilizer pitch trim system, and repair if necessary. The requirements of that AD were intended to detect and correct contamination and damage in the system actuator, which could result in simultaneous failure of both primary and secondary pitch trim systems, and consequent reduced controllability of the airplane. Since the issuance of that AD, an improved part has been developed, which, if installed, would terminate the repetitive tests; that improved part has been installed on all affected airplanes or is being installed in production. Therefore, the identified unsafe condition no longer exists.
86-19-15 R1: 86-19-15 R1 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-5470. Applies to Aerospatiale Model AS 350 and AS 355 series helicopters, certificated in any category. Compliance is required as indicted unless already accomplished. To prevent failure of the main rotor head sleeves, accomplish the following: (a) For AS 350B and AS 350D helicopters, accomplish the following: (1) Within the next 100 hours' time in service after the effective date of this AD, replace, with serviceable parts, those main rotor head sleeves (Part Numbers (P/N) 350A31.1831.00, .01, .04, .05, .06, and .07) which have 3,900 or more hours' time in service. (2) For those main rotor head sleeves having less than 3,900 hours' time in service on the effective date of this AD, replace with serviceable parts before 4,000 hours' time in service. (b) For AS 355 series helicopters, accomplish the following: (1) Within the next 100 hours' time in service after the effective date of this AD, replace, with serviceable parts, those main rotor head sleeves (P/N's 350A31.1831.04, .05, .06, and .07) which have 1,400 or more hours' time in service. (2) For those main rotor head sleeves having less than 1,400 hours' time in service after the effective date of this AD, replace with serviceable parts before 1,500 hours' time in service. (c) In the event of sudden or repeated occurrence of a severe tracking defect, accomplish the following before the next flight: (1) Remove blades and visually check to determine if outboard sleeve bushes are separated; and (2) If bush separation is found, remove and replace sleeves. (d) An alternate method of compliance with this AD, which provides an equivalent level of safety, may be used when approved by the Manager, Aircraft Certification Division, Federal Aviation Administration, P.O. Box 1689, Fort Worth, Texas 76101, or by the Manager, Aircraft Certification Office, AEU-100, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (e) In accordance with FAR sections 21.197 and 21.199, flight is permitted to a base where the maintenance required by this AD may be accomplished. NOTE: Aerospatiale Telex Services 01.13 and 01.16 and French AD's 86-35-28(B) and 86-57-44(B) pertain to this subject. This amendment becomes effective December 18, 1986, as to all persons except those persons to whom it was made immediately effective by priority letter AD 86-19-15 issued September 24, 1986, which contained this amendment.
2020-21-05: The FAA is superseding Airworthiness Directive (AD) 2017-25- 16, which applied to all Airbus SAS Model A330-200 Freighter, A330-200, A330-300, A340-200, A340-300, A340-500, and A340-600 series airplanes. AD 2017-25-16 required repetitive inspections of certain fuel pumps for cavitation erosion, corrective action if necessary, and revision of the minimum equipment list (MEL). This AD continues to require those actions, and also requires expanding the inspection area, adding certain maintenance actions, and expanding the applicability, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by reports of a fuel pump showing cavitation erosion that exposed the fuel pump power supply wires, and by new findings that suggest the need to expand the inspection area and the applicability. The FAA is issuing this AD to address the unsafe condition on these products.
86-18-10: 86-18-10 PIPER AIRCRAFT CORPORATION: Amendment 39-5446. Applies to Model PA-42-1000 (S/N's 42-5527002 through 42-5527033) airplanes certificated in any category. Compliance: Required within the next 10 hours time in service after receipt of this AD, unless already accomplished. To prevent loss of power and wing damage accomplish the following: (a) Fabricate a checking device from 3/8 inch O.D. polyethylene plastic tubing, 48 inches in length with a wall thickness of approximately 0.060 inches. NOTE 1: Polyethylene tubing is used in plumbing and air conditioning installations and may be found in hardware stores. Other types of plastic tubing may not work due to friction buildup. (b) Chamfer the end of the tube which will be inserted into the vent lines. Mark the tube at a point 40 inches from the chamfered end. (c) Remove the vent well covers located on top of the left and the right wing tip tanks. (d) Insert the checking device into each wingtip tank vent line up to the 40 inch mark. (e) If the checking device can be inserted to the 40 inch mark, the vent line is clear. Reinstall the vent well covers. No further action is required. (f) If the checking device cannot be inserted to the 40 inch mark, prior to further flight: (1) Drain the fuel from the airplane on the affected side(s). (2) Remove the forward outboard access cover from the bottom of the left and/or right wing(s) as required. (3) Visually inspect the affected tip tank vent lines for blockage or deformation. (4) Remove the fuel cap on the affected tip tank(s), depress the antisiphon flapper valve and using a light and mirror, visually inspect the upper portion of the wing tip tanks fuel vent line for blockage or deformation. (5) Replace any lines found blocked or deformed. (6) Reinstall the wing access plates with the sealant specified in the airplane maintenance instructions. (7) Fuel the airplane and check for leaks. NOTE 2: Piper Telex Service Bulletin No. 846, dated August 26, 1986, applies to the subject of this AD. (g) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (h) Within five (5) days of accomplishing this AD, report, in writing, all defects found during accomplishment of this AD to the Manager, Atlanta Aircraft Certification Office, 1075 Inner Loop Road, College Park, GA 30337. (Reporting approved by the Offices of Management and Budget under OMB No. 2120-0056.) (i) An alternate method of compliance which provides an equivalent level of safety, may be approved by the Manager, Atlanta Aircraft Certification Office. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 32960; or FAA, Office of Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. Thisamendment becomes effective on October 27, 1986, to all persons except those to whom it has already been made effective by priority letter from the FAA dated September 4, 1986, and is identified as AD 86-18-10.
2020-21-03: The FAA is superseding Airworthiness Directive (AD) 2015-14- 01, which applied to certain Bombardier, Inc., Model DHC-8-400 series airplanes. AD 2015-14-01 required a detailed inspection for loose bolts on the aft translating door crank assembly, and removal and reinstallation of the bolts. This AD retains the inspections of AD 2015-14-01 and adds airplanes to the applicability. For all airplanes, this AD also requires a modification of the door crank handle, which will terminate the inspection requirements. This AD was prompted by reports of loose bolts that are intended to secure the translating door crank assembly to the outside handle shaft, and of sealant missing from these bolts on another translating door. The FAA is issuing this AD to address the unsafe condition on these products.