Results
2015-16-05: We are adopting a new airworthiness directive (AD) for British Aerospace Regional Aircraft Jetstream Series 3101 and Jetsream Model 3201 airplanes. 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 missing countersunk washers under the head of the main landing gear trunnion cap tension bolts that could cause fatigue in the bolt shanks. We are issuing this AD to require actions to address the unsafe condition on these products.
2015-16-06: We are adopting a new airworthiness directive (AD) for British Aerospace Regional Aircraft Model Jetstream Model 3201 airplanes. 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 the in-service special detailed inspection technique required for the Jetstream 3200's life extension program was delayed; consequently, the in-service special detailed inspection technique is not formally part of the life extension program and may therefore not be accomplished as intended. We are issuing this AD to require actions to address the unsafe condition on these products.
2000-12-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes, that requires repetitive inspections to check the play of the eye-end of the piston rod of the elevator servo-controls, and follow-on corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct excessive play of the eye-end of the piston rod of the elevator servo-controls, which could result in failure of the elevator servo-control.
2000-12-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that currently requires an initial inspection of fastener holes on certain outer frames of the fuselage to detect fatigue cracking, and modification of the area by cold expanding the holes and installing oversized fasteners. This amendment requires revising the applicability to include additional airplanes; a high frequency eddy current inspection to detect fatigue cracking in the frames and frame feet at fuselage frames FR37 through FR41; and follow-on actions. This amendment also provides for an optional terminating action for the follow-on repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fatigue cracking of the fuselage frames and frame feet, and consequent reduced structural integrity of the fuselage.
2000-12-03: This amendment adopts a new airworthiness directive (AD) for Eurocopter France Model AS332L2 helicopters. This AD requires inspecting for interference between the transmission flexible mounting plate (plate) and the forward and aft shims (shims), replacing shims and repairing the plate if interference is found, and inspecting the plate for a broken plate slat (slat) and repairing the plate if a broken slat is found or replacing the plate if slat damage beyond repair limits is found. This AD is prompted by the discovery that several helicopters were manufactured with shims that did not have cutouts to permit relative motion between the plate slats and the shims without interference. The actions specified by this AD are intended to prevent cracking of the plate slats, increased helicopter vibration, loss of transmission mounting integrity, and subsequent loss of control of the helicopter.
2015-16-03: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211-524B-02, RB211-524B2-19, RB211-524B3-02, RB211-524B4-02, RB211-524B4-D-02, RB211-524C2-19, RB211-524D4-19, RB211-524D4-39, and RB211-524D4X-19 turbofan engines. This AD requires removing affected high-pressure turbine (HPT) blades. This AD was prompted by several failures of affected HPT blades. We are issuing this AD to prevent failure of the HPT blade, which could lead to failure of one or more engines, loss of thrust control, and damage to the airplane.
2015-15-14: We are adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model ATP airplanes. This AD requires a one-time inspection for solder deposited on the frangible plug of certain engine and auxiliary power unit (APU) fire extinguishers. This AD was prompted by reports of a fire extinguisher that failed to discharge due to solder deposited on the frangible plug of the fire extinguisher. We are issuing this AD to detect and correct solder deposited on the frangible plug of the fire extinguisher, which could result in failure of the fire extinguisher to discharge, and consequent inability to put out a fire in an engine or in the APU.
2000-11-12: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company CF6-45/50 series turbofan engines. This AD requires initial and repetitive inspections for cracks in the stage 14 high pressure compressor (HPC) disk lock slots, and removal from service of certain disks, at the first piece-part level or HPC rotor disassembly level exposure, after 6,000 cycles since new (CSN). This amendment is prompted by reports of stage 14 HPC disk lock slot cracks discovered during shop fluorescent penetrant inspections. The actions specified by this AD are intended to prevent stage 14 HPC disk failure, which could result in an uncontained engine failure and damage to the aircraft.
85-06-01: 85-06-01 ROLLS-ROYCE LIMITED: Amendment 39-5013. Applies to Rolls-Royce Limited Dart engine series 525, 526, 527, 528, 529, 530, 531, 532, 535, 551, and all variants of these series which do not feature Rolls-Royce Modifications 1425, 1618, 1719, or 1723. Compliance required as indicated unless already accomplished. To prevent excessive wear in flame tube liners and suspension pins which may lead to flame breakout from the combustion chamber and to overheating and failure of the high pressure turbine disk rim, accomplish the following: 1. For engines which do not have Modification 1736, Part 2 incorporated accomplish the following: (a) Inspect flame tube liners and suspension pins for wear at the primary and repetitive intervals in accordance with mandatory Rolls-Royce Dart SB No. Da72-485, dated July 2, 1984. Replace the affected parts, if wear is outside the "acceptable" limits given in paragraphs 4D(3) and 4D(4) of SB Da72-485, prior to further flight.(b) Incorporate Modification 1736, Part 2, in accordance with Rolls-Royce SB No. Da72-423, Part 2, Revision 16, dated July 13, 1984, at the next flame tube overhaul. 2. For engines which have incorporated Modification 1736, Part 2, inspect flame tube liners and suspension pins for wear at the initial and standard intervals in accordance with Rolls-Royce Dart SB Da72-470, Revision 1, dated March 30, 1984. Replace the affected parts, if wear is outside the "acceptable" limits given in paragraphs 4D(3) and 4D(4) of SB 72-470, prior to further flight. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulation (FARs) 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Manager, Dart Service, Rolls-Royce Limited, East Kilbride, Glasgow, G74 4PY Scotland. These documents also may be examined at the Office of the Regional Counsel, FAA, New England Region, Rules Docket No. 84-ANE-16, 12 New England Executive Park, Burlington, Massachusetts 01803, weekdays, except federal holidays, between the hours of 8:00 a.m. and 4:30 p.m. This AD supersedes AD 77-18-02, Amendment 39-3027, and AD 78-01-07, Amendment 39-3109, which became effective on September 28, 1977, and January 12, 1978, respectively. This amendment becomes effective on April 3, 1985.
81-14-08: 81-14-08 FOKKER B.V.: Amendment 39-4156. Applies to Model F27 airplanes, all series, certificated in all categories as indicated below. Unless already accomplished, accomplish the following within the time specified in each paragraph below after the effective date of this AD. A. Applies to airplanes S/N 10479, 10492, 10499, 10500, 10502, 10529, 10534, 10536 through 10557, 10559, 10561 through 10585. To prevent inadvertent unlocking of the Ipeco seats, inspect and modify the bolt and tracklock stop block in accordance with the Accomplishment Instructions of Fokker F27 Service Bulletin No. 25-47 dated January 1, 1979, or later FAA approved revisions. Perform this inspection within the next 100 hours time in service and every 50 hours thereafter until the bolt and tracklock stop block have been modified. The bolt and tracklock stop block are to be modified within the next 500 hours time in service. B. Applies to airplanes S/N 10572 and below equipped with a large cargo door identified by Fokker F27 Service Bulletin No. 52-60. To ensure the functional and structural integrity of the cargo door latch mechanism, within the next 100 hours time in service, inspect the latch mechanism and rework, as necessary, in accordance with the Accomplishment Instructions of Fokker F27 Service Bulletin No. 52-60 dated May 1, 1979, or later FAA approved revisions. C. Applies to airplanes S/N 10547 and below, 10558 and 10560. To prevent failure of the right elevator center hinge fitting, within 100 hours and every 100 hours thereafter until replaced, inspect for cracks in accordance with the F27 Structural Integrity Program, item 55-50- 01, Revision 1. Within the next 500 hours time in service, replace hinge fittings in accordance with the Accomplishment Instructions of Fokker F27 Service Bulletin No. 55-52, dated May 1, 1979, or later FAA approved revisions. D. Applies to airplane S/N 10102 through 10462 incorporating Fokker F27 Service Bulletin No.52-47, 10464 through 10468, 10470 through 10477, 10484, 10486, 10498, 10501, 10503 through 10506, 10508, 10511 through 10515, 10519, 10521 through 10525, 10527, 10528, 10530 through 10535, 10539, 10545, 10550, 10551, 10552, 10554, 10557 through 10560, 10562, 10563, 10566, 10567, 10569, 10572, 10573, 10574, 10576, 10579, 10581, 10585 through 10589 and 10591. To ensure the operation of the main passenger door during an emergency evacuation, within the next 100 hours time in service after the effective date of this AD, modify the emergency release mechanism of the main passenger door in accordance with the Accomplishment Instructions of Fokker F27 Service Bulletin No. 52-61, dated January 2, 1980. E. Applies to all Fokker F27 airplanes having accumulated more than 7,000 landings. To ensure main landing gear system operation, prior to 7,500 landings or within 500 landings after the effective date of this AD, whichever comes later, replace main gear actuating ram retaining ring P/NACM18254 with a serviceable retaining ring having less than 7,500 landings in accordance with the F27 Structural Integrity Program under item 32-30-01, Revision 1, subitem d or in accordance with the Accomplishment Instructions of Fokker F27 Service Bulletin No. 32-136, dated February 18, 1980, or later FAA approved revisions. (Note: Established life limits are not to be exceeded.) F. Applies to airplane S/N 10505 to 10547 inclusive and 10550. To ensure proper function of the pitot static system, within the next 100 hours time in service, modify the pitot static system in accordance with the Fokker F27 Service Bulletin No. 34-41, dated March 13, 1978, or later FAA approved revisions. G. Applies to airplane S/N 10299 to 10547 inclusive. To prevent damage to the cable loom, within the next 200 hours time in service, inspect and modify as necessary the cable loom in accordance with Fokker F27 Service Bulletin No. 30-34 dated April 17, 1978, or later FAA approved revisions.H. Applies to airplane S/N 10526, 10527, 10529, 10543, 10547, 10533, 10555, 10556, 10563, 10564, 10565, 10570, 10582 and 10583. To ensure airplane battery power to the main DC tie bus, within 100 hours time in service, inspect and modify as necessary the battery wiring to the battery reverse current circuit breakers in accordance with the Fokker F27 Special Instructions No. 76 dated November 20, 1978, or later FAA approved revisions. 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. Alternate means of compliance or other actions which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to5 U.S.C. 552(a)(1). This amendment becomes effective August 10, 1981.