Results
83-05-07: 83-05-07 PARTENAVIA COSTRUZIONI AERONAUTICHE S.p.A.: Amendment 39-4583. Applies to Models P68 and P68B (Serial Nos. 1 through 182, excluding Serial Nos. 74, 89, 133, 142, 155, 163, and 171) airplanes certificated in any category. COMPLIANCE: Required as indicated, unless already accomplished. To prevent possible failure of the engine oil cooler left-hand elbow fittings and oil cooler hoses, within the next 50 hours time-in-service on airplanes having 500 or more hours time-in-service on the effective date of this AD or prior to 550 hours time-in-service on airplanes having less than 500 hours time-in-service on the effective date of this AD, accomplish the following: (a) Replace the engine oil cooler left-hand elbow fitting in accordance with steps one through nine of the INSTRUCTIONS FOR REPLACEMENT section of Partenavia Costruzioni Aeronautiche S.p.A. SB No. 45, R.A.I. approved July 9, 1979. (b) Visually inspect the oil cooler hoses for chafing or damage, andprior to further flight, replace any unairworthy hoses. (c) The airplane may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent method of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, Federal Aviation Administration, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on March 17, 1983.
2016-11-16: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes equipped with Rolls-Royce Model RB211-Trent 800 engines. This AD was prompted by reports of thrust reverser (T/R) events related to thermal damage of the T/R inner wall. Depending on the airplane configuration, this AD requires a records review and applicable repetitive inspections, replacements, and installations of the T/R inner wall; and related investigative and corrective actions if necessary. This AD also requires installation of serviceable T/R halves, which would terminate the repetitive actions. This AD also requires revising the inspection or maintenance program by incorporating new airworthiness limitations. We are issuing this AD to detect and correct a degraded T/R inner wall panel. A degraded T/R inner wall panel could lead to failure of the T/R and adjacent components and their consequent separation from the airplane, which could result in arejected takeoff (RTO) and cause asymmetric thrust and consequent loss of control of the airplane during reverse thrust operation. If a T/R inner wall overheats, separated components could cause structural damage to the airplane, damage to other airplanes, or possible injury to people on the ground.
83-06-07: 83-06-07 WYTWORNIA SPRZETU KOMUNIKACYJNEGO, PZL-MIELEC: Amendment 39-4594. Applies to Model PZL M18 (all Serial Numbers through 1Z007-25) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent loss of primary flight control about the yaw axis, accomplish the following: a) Before the first flight of each day, visually check the rudder skin for cracks along the trailing edge. This check may be performed by the pilot. 1) If no cracks are found the airplane may be placed in service. 2) If cracks are found prior to further flight conduct the inspections of paragraph b). b) Within 25 hours time-in-service after the effective date of this Airworthiness Directive (AD) and at 50 hours time-in-service intervals thereafter, using a 5-power magnifying glass inspect the rudder on both sides in the upper hinge area and along the trailing edge. 1) If no cracks are detected, return the aircraft to service. 2) If cracks are detected, remove the rudder and accomplish repairs as prescribed in paragraph III of Bulletin R/028/81. c) The intervals between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane. d) Aircraft may be flown in accordance with FAR 21.197 to a location where this Airworthiness Directive (AD) can be accomplished. e) An equivalent method of compliance with this AD if used must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on April 4, 1983.
62-14-03: 62-14-03 HUGHES: Amdt. 455 Part 507 Federal Register June 21, 1962. Applies to Model 269A helicopter Serial Numbers 0011 to 0059 Inclusive. Compliance required as indicated. (a) To prevent failure of the tail rotor blade, within the next 10 hours' time in service after the effective date of this AD, and each day thereafter, conduct a visual inspection of the tip of the Hughes P/N 269A6124 tail rotor blade for separation of the rib and the blade skin. This will appear as a crack in the bond line between the blade tip rib and the blade skin. (b) If no separation is detected, the tail rotor blades may continue to be used in service for the remainder of their service life subject to the inspection specified in paragraph (a). (c) If separation is detected, remove the tail rotor assembly and replace prior to further flight with an assembly incorporating tail rotor blades P/N 269A6124 Change E or later. After installation of P/N 269A6124 Change E or later, the normal inspection procedures may be followed. (Hughes Tool Company, Aircraft Division, Hughes-O-Gram to operators dated May 2, 1962, covers the same subject.) This directive effective June 26, 1962.
2016-11-05: We are superseding Airworthiness Directive (AD) 99-16-01 for certain Airbus 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). AD 99-16-01 required repetitive inspections of certain bolt holes where parts of the main landing gear (MLG) are attached to the wing rear spar, and repair if necessary. Since we issued AD 99-16-01, we have determined that the risk of cracking in the wing rear spar is higher than initially determined. This new AD adds airplanes to the applicability, reduces the compliance times and repetitive intervals for the inspections, and changes the inspection procedures. This AD was prompted by a determination that the risk of cracking in the wing rear spar is higher than initially determined. We are issuing this AD to detect and correct cracking of the rear spar of the wing, which could result in reduced structural integrity of the airplane.
2010-16-10: 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: A potential fleet wide problem has been identified regarding the interchanging of wing links on all BAe 146 & AVRO 146-RJ aircraft during scheduled maintenance. Some operators erroneously believed that these parts were interchangeable. The effects of changing winglinks has resulted in either a shorter or longer wing link being fitted, which introduces local stresses in the wing top and bottom surfaces local to rib 2, wing links and wing link fitting attachment and the fuselage local to Frames 26 and 29. This condition, if not corrected, could result in a reduction of structural integrity of the fuselage/wing attachment with possible catastrophic consequences. * * * * * The unsafe condition could result in loss of a wing or controllability of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
80-26-03: 80-26-03 DEHAVILLAND: Amendment 39-3993. Applies to all DeHavilland DHC-4 and DHC-4A aircraft equipped with Pratt & Whitney Aircraft Twin Wasp D-5 and R-2000-7M2 engines incorporating left-hand magneto drive arrangement. Compliance required within the next 1400 hours in service after the effective date of this AD unless already accomplished. To preclude failure of the left hand magneto drive mechanism, incorporate the right-hand magneto drive and associated parts as described in Pratt & Whitney Aircraft Service Bulletin No. 1756 dated September 13, 1963, or approved equivalent instructions and parts. The Twin Wasp D-5 and R-2000-7M2 engines so modified must be redesignated as noted in Section C of the Pratt & Whitney Aircraft Service Bulletin No. 1756, or an approved equivalent instruction. All equipment instructions and parts must be approved by the Chief, Engineering & Manufacturing Branch, FAA Eastern Region. (Pratt & Whitney Aircraft Service Bulletin No. 1756 pertains to this subject.) This amendment is effective December 19, 1980.
83-24-10 R1: 83-24-10 R1 BRITISH AEROSPACE: Amendment 39-4780 as amended by Amendment 39- 5053. Applies to Model BAC 1-11 200 and 400 series airplanes, certificated in all categories. Compliance is required as indicated unless already accomplished. To detect cracking and corrosion and to prevent structural failure of the fuselage pressure vessel with the resultant cabin depressurization, accomplish the following: A. Within the next 12 months after the effective date of this AD, unless accomplished within the last 2 years, and thereafter at intervals not to exceed 3 years from the last inspection, visually inspect for corrosion and cracks the interior of the lower fuselage skin between stations 416-456 and stringers 32(LH) and 32(RH) and the interior of the lower fuselage skin between stations 630-690 and stringers 32(LH) and 32(RH), and ensure that drain paths in these areas are unobstructed, in accordance with paragraphs 2.1.1 and 2.1.2 of British Aerospace Alert Service Bulletin 53-A-PM5632, dated August 18, 1978. B. On airplanes having long range fuel tanks or water injection tanks installed, accomplish the instructions of paragraph 2.1.3 of the service bulletin. C. If cracks or corrosion are found during any inspection required by this AD, before further flight, rework or repair in accordance with Structural Repair Manual, Chapters 53-01-0 or 53-02-0 as appropriate, and continue the repetitive inspections at the intervals specified in paragraph A. of this AD. D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. Amendment 39-4780 became effective January 15, 1984. This Amendment 39-5053 becomes effective June 4, 1985.
2016-11-11: We are adopting a new airworthiness directive (AD) for EVEKTOR, spol. s.r.o. Models L 13 SEH VIVAT and L 13 SDM VIVAT gliders (type certificate previously held by AEROTECHNIK s.r.o.). This AD results from mandatory continuing airworthiness information (MCAI) issued 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 lack of distinct color marking of the elevator drive. We are issuing this AD to require actions to address the unsafe condition on these products.
83-15-04: 83-15-04 PARTENAVIA COSTRUZIONI AERONAUTICHE S.p.A.: Amendment 39- 4695. Applies to Models P68, P68B, P68C, P68C-TC and P68 Observer (all serial numbers (S/N) up to S/N 289, excluding S/Ns 234, 256, 259, 269, and 288) airplanes certificated in any category. Compliance: Required within 50 hours time-in-service from the effective date of this AD, unless already accomplished. To preclude loosening of the stabilator support brackets, accomplish the following: a) Check and correct, if necessary, the torque of the AN4-6A bolts which attach the horizontal stabilator torque tube support brackets to the fuselage frame (ref. Parts Catalog P68B, Figure No. 5.2, Item No. 33; or Parts Catalog P68C, Figure No. 5.3, Item No. 36). NOTE: The correct torque value for these bolts is 0.9 to 0.950 Kpm; 78 to 83 in. lbs. b) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. c) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. Partenavia Service Bulletin No. 57 dated March 7, 1983, covers the subject matter of this AD. This amendment becomes effective on August 4, 1983.