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91-06-16: 91-06-16 BRITISH AEROSPACE: Amendment 39-6935. Docket No. 90-NM-257-AD. Applicability: Model BAC 1-11 200 and 400 series airplanes, as listed in British Aerospace Service Bulletin 52-PM-5970, dated August 16, 1990, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural integrity of the rear pressure bulkhead door, accomplish the following: A. Prior to the accumulation of 55,000 landings or within 15 months after the effective date of this AD, whichever occurs later, install horizontal members, various angle bracket assemblies, throat strips, cleats, furnishing bracket assemblies, furnishing angles, stiffeners, and a detachable door panel, in accordance with British Aerospace Service Bulletin 52-PM-5970, dated August 16, 1990. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6935, AD 91-06-16) becomes effective on April 18, 1991.
2020-26-18: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A330-243, -343, and -941 airplanes. This AD was prompted by a report that during an inspection of the wing/fuselage fillet interface, evidence of black stains and white oxidation was found on several areas of the fillet fairing adjustable rods due to surface corrosion. This AD requires replacing each affected fillet fairing adjustable rod with a serviceable part, 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.
2004-01-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 series airplanes (Regional Jet Series 100 & 440), that requires a one-time inspection of the dust covers for the flight data recorder (FDR) and cockpit voice recorder (CVR) equipment for the presence of markings that indicate the presence of a chemical-resistant coating, and corrective actions if necessary. The actions specified by this AD are intended to prevent peeling of the paint and markings from the dust covers for FDR and CVR equipment due to hydraulic mist from the actuators, which could result in the inability to identify FDR and CVR equipment in the event of an accident-recovery mission. The lack of data from FDR and CVR equipment could hamper discovery of the unsafe condition that caused an accident or an incident and prevent the FAA from developing and mandating actions to prevent additional accidents or incidents caused by that same unsafe condition. This action is intended to address the identified unsafe condition.
78-12-04: 78-12-04 PRATT & WHITNEY AIRCRAFT: Amendment 39-3234. Applies to all Pratt & Whitney Aircraft of Canada, Limited PT6A-38 engines prior to Serial Number PCE-79179, PT6A-41 engines prior to Serial Number PCE-80718, PT6A-45A engines prior to Serial Number PCE-84108 and Pratt & Whitney Aircraft PT6A-38 engines prior to Serial Number P-79179 with Part Number 3019268 or 3027054 No. 2 bearing pressure oil transfer tube assemblies. Compliance required within the next 50 hours in service, after the effective date of this AD, unless already accomplished. To preclude oil leakage from the No. 2 bearing pressure oil transfer tube assembly replace the Part Number 3019268 and 3027054 tube assemblies with Part Number 3030150 tube assembly in accordance with Paragraph 2, accomplishment instructions in Pratt & Whitney Aircraft of Canada, Limited Service Bulletin No. 3099 or approved equivalent parts. Aircraft may be flown to a base for performance of maintenance required by this ADper FAR 21.197 or FAR 21.199. All equivalent parts must be approved by the Chief, Engineering and Manufacturing Branch of the Eastern Region of the FAA. This amendment is effective June 19, 1978.
95-04-09: This amendment adopts a new airworthiness directive (AD) that applies to Pilatus Britten-Norman BN2A, BN2B, and BN2T Islander and BN2A Mk III Trislander series airplanes that are equipped with a nose wheel steering disconnect system with either a Modification NB/M/503 or Modification NB/M/733 nose undercarriage unit. This action requires repetitively inspecting the nose wheel steering drive ring for cracks, and replacing any cracked drive ring. A report of the rudder pedals jamming in the central position during takeoff on one of the affected airplanes prompted this action. The actions specified by this AD are intended to prevent failure of the nose wheel steering system because of a cracked drive ring, which, if not detected and corrected, could result in the inability to move the rudder pedals.
2020-26-21: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by a report that during the assembly of a certain section of the fuselage, the gaps found on self-aligning nuts for eight fasteners were out of tolerance. This AD requires a rotating probe test of all fastener holes located in the affected area for any discrepancies, an eddy current inspection of the surrounding flange for any discrepancies, a detailed inspection of certain frames for any discrepancies, and corrective actions if necessary, 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.
77-17-11: 77-17-11 BOEING: Amendment 39-3025 as amended by amendment 39-3392. Applies to all B-17F & G airplanes certified in all categories. Compliance required within the next 25 hours' time-in-service or within 6 months after the effective date of this AD, whichever comes first, unless already accomplished within the last 25 hours time in service or 6 months, and thereafter at intervals not to exceed 50 hours time in service or 12 months, whichever comes first, (from the last inspection). To detect cracking in the rear spar lower cap center section, P/N 75-3425-2 or 85-3425-2, accomplish the following: 1. Remove the 3 most inboard bolts from the 14 bolt pattern attaching the rear spar center section lower chord P/N 75-3425-2 or 85-3425-2 to the terminal plates, left and right hand sides. These bolts are approximately 40 to 42 inches from the airplane centerline. Using eddy current inspection procedures or boroscope methods in conjunction with dye penetrants, inspect the rear spar lower chord center section for cracks around the bolt holes in both the forward and aft walls of the tube. 2. If cracks are found, replace the spar cap with a serviceable part of the same part number, or repair in accordance with Army T.O. No. 01-20E or other methods approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. 3. After repairs per (2) have been accomplished, reinspect in accordance with (1) at intervals not to exceed 150 hours time-in-service or every 12 months, whichever comes first. 4. The bolt holes described in paragraph (1) above may be reamed .063 inch oversize for a close tolerance oversize bolt, provided no cracks are detected when the chords are inspected in accordance with paragraph (1) above using the eddy current inspection methods. Any holes reworked with the oversize bolts must be reinspected in accordance with (1) above within 1500 flight hours after such rework. Upon accumulation of 1500 flight hours on the reworked holes, the repeat inspection interval reverts to the interval specified in (3) above. 5. Any new replacement beam chords must be inspected within 2500 flight hours after installation and thereafter at intervals specified in paragraph (3) above. Amendment 39-3025 became effective September 6, 1977. This amendment 39-3392 becomes effective January 23, 1979.
97-24-02 R1: This amendment revises an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-1A11 (CL-600), CL- 600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) series airplanes, that currently requires repetitive inspections to find cracks of a certain bulkhead web of the fuselage at certain locations, and repair if necessary. The actions specified by that AD are intended to prevent cracking in the pressure bulkhead at frame station (FS) 409.00, which could result in uncontrolled depressurization of the airplane and/or reduced structural integrity of the fuselage. This amendment provides an optional terminating modification for certain airplanes. This action is intended to address the identified unsafe condition.
95-04-11: This amendment supersedes an existing airworthiness directive (AD), applicable to Textron Lycoming ALF502R series turbofan engines, that currently requires the establishment of a reduced stress rupture retirement life limit for certain third stage turbine disks. This amendment establishes a new increased stress rupture retirement life limit for certain third stage turbine disks used in conjunction with third stage turbine nozzles that have improved cooling effectiveness, expands the applicability by adding the ALF502L series engines, and establishes other new reduced stress rupture retirement life limits. This amendment is prompted by the introduction of an improved design third stage turbine nozzle, and a new reduced stress rupture retirement life limit for certain third stage turbine disks on the ALF502L series engines. The actions specified by this AD are intended to prevent a total loss of engine power, inflight engine shutdown, and possible damage to the aircraft.
2004-01-07: This amendment adopts a new airworthiness directive (AD), applicable to certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ series airplanes. This AD requires one-time inspections of the inner webs and flanges at frames 15, 18, 41, and 43 for evidence of corrosion or cracking; and corrective actions if necessary. This action is necessary to detect and correct corrosion and cracking of the inner webs and flanges at frames 15, 18, 41, and 43, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.