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90-22-08: 90-22-08 AIRBUS INDUSTRIE: Amendment 39-6781. Docket No. 90-NM-199-AD. Applicability: All Model A320-231 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect cracks in the rear engine mount barrel nuts, and to prevent reduced structural integrity of the rear engine support structure, accomplish the following: A. Within 25 hours time-in-service after the effective date of this AD, and thereafter at intervals not to exceed 700 hours time-in-service, perform a visual inspection of the rear engine mount barrel nuts, in accordance with Airbus Industrie Operator Information Telex (AOT) ST/999.0085/90, dated April 3, 1990. If a nut is cracked, replace with a new nut, prior to further flight, in accordance with the Operator Information Telex. Following replacement of the nut, continue the visual inspections at intervals not to exceed 700 hours time-in-service in accordance with the AOT. NOTE: This Airbus Industrie telex references International Aero Engines (IAE) Service Bulletin No. V2500-NAC-71-0071, Revision 3, dated March 30, 1990, for additional information. B. On each day that flying occurs, perform a torque check of the rear engine mount bolts in accordance with Airbus Industrie Operator Information Telex (AOT) ST/999.0087/90, dated April 4, 1990. Any bolt which does not meet the appropriate torque limits specified in the AOT must be retorqued prior to further flight. NOTE: This Airbus Industrie telex references IAE Service Bulletin No. V2500-NAC-71- 0071, Revision 3, dated March 30, 1990, for additional information. C. 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. D. 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 information from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6781, AD 90-22-08) becomes effective on November 5, 1990.
99-21-21: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310-300 and A300-600R series airplanes, that requires installation of a new cover assembly, associated new drain and vent pipework, and a new electrical harness on the trimmable horizontal stabilizer for the fuel tank water scavenge motive pump. 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 fuel leakage from the seal of the water scavenge pumps, which, if not corrected, could result in leakage of fuel into fuselage areas not designed for fuel, and consequent potential for fuel to be in contact with a fuel ignition source.
2023-03-06: The FAA is adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by the determination that radio altimeters cannot be relied upon to perform their intended function if they experience interference from wireless broadband operations in the 3.7-3.98 GHz frequency band (5G C-Band), and a recent determination that this interference can result in unavailable or misleading radio altimeter information, adversely affecting the performance of the automatic flight control system (AFCS) and resulting in increased flightcrew workload during takeoff, approach, and landing below 400 feet above ground level (AGL). This AD requires revising the existing airplane flight manual (AFM) with new limitations to mitigate identified hazards due to 5G C-Band interference as identified by Notices to Air Missions (NOTAMs). The FAA is issuing this AD to address the unsafe condition on these products.
T83-25-51 R1: T83-25-51 R1 BOEING VERTOL COMPANY: Amendment 39-4828 and Telegram issued June 11, 1984. Applies to Boeing Vertol Model 234 series helicopters certificated in all categories. Compliance is required as indicated. To prevent possible hazards in flight associated with cracking of the main rotor head horizontal hinge pins, accomplish the following: (a) Within the next 25 hours time in service from the effective date of this AD or before the accumulation of 1,600 hours time in service, whichever comes later, retire main rotor head horizontal hinge pins P/N's 114R2196-2, 114R2197-1, and 114R2197-5 and replace with serviceable parts. (b) An equivalent method of compliance with this AD may be used when approved by the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York 11581. (c) In accordance with FAR 21.197 flight is permitted to a base where the requirements of this AD may be accomplished. (d) Within the next 50 hours time in service from the effective date of this AD revision or before the accumulation of 300 hours time in service, whichever comes later, retire main rotor head horizontal hinge pins that have serial numbers other than A-356 thru A-367, A- 380 thru A-403, A-440 and subsequent, and YZ-135 and subsequent, and replace with serviceable parts. Amendment 39-4828 became effective March 26, 1984, as to all persons except those persons to whom it was made immediately effective by telegraphic AD No. T83-25-51 issued December 9, 1983, which contained the amendment. This telegraphic revision becomes effective upon receipt.
68-11-02: 68-11-02 LOCKHEED: Amdt. 39-701. Applies to Lockheed Model 188A and 188C Series airplanes. Compliance required as indicated. To detect fatigue cracks in the upper planks at the fillet attachment holes, accomplish the following: (a) Within the next 400 hours' time in service after the effective date of this AD, unless already accomplished within the last 1000 hours' time in service, and thereafter at intervals not to exceed 1400 hours' time in service from the last inspection, inspect visually the upper wing planks in the vicinity of the fillet attachment holes on both sides of the four nacelles in accordance with Paragraphs (2)(B) of Lockheed Service Bulletin No. 88/SB-649A dated June 14, 1968, (or later FAA approved revision), or by a method approved by the Chief, Aircraft Engineering Division, FAA Western Region, and if cracks are found, repair before further flight in accordance with Section (2)(C) or (2)(D) of Lockheed Service Bulletin No. 88/SB-649A dated June 14,1968, (or later FAA approved revision,) or by a method approved by the Chief, Aircraft Engineering Division, FAA Western Region. (b) The repetitive inspection required by (a) may be discontinued in the respective affected areas upon completion of the repairs described in Section 2.C. of Lockheed Service Bulletin No. 88/SB-649A, dated June 14, 1968, (or later FAA approved revision), or upon completion of the appropriate preventive repair installation described in Section I.C.I. or preventive reinforcement of Section I.C.II. of Lockheed Service Bulletin No. 88/SB-665, dated November 11, 1968, (or later FAA approved revision). (c) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, 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 that operator. This Directive effective July 5, 1968. Revised August 20, 1968. Revised October 26, 1968. Revised January 4, 1969.
2002-01-24: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81, -82, -83, and -87 series airplanes, and Model MD-88 airplanes, that requires replacing the dust seals of the passenger service unit (PSU) panels of the overhead stowage compartment with new dust seals. The AD provides two options to accomplish this. Operators can either replace the seals all at once or remove the seals and repetitively clean and inspect the area to defer the installation for an interim period. The actions specified by this AD are intended to ensure replacement of dust seals of the lower PSU panel that may contribute to the spread of a fire when ignition occurs from electrical arcing of a failed light holder assembly, which could cause damage to adjacent structure and smoke emitting from the PSU panel into the passenger cabin. This action is intended to address the identified unsafe condition.
2017-20-02: We are superseding Airworthiness Directive (AD) 2017-13-05, which applied to all Airbus Model A330-200, A330-300, A340-200, A340- 300, A340-500, and A340-600 series airplanes. AD 2017-13-05 required an inspection, corrective actions if necessary, lubrication of the ball- nut, modification of the trimmable horizontal stabilizer actuator (THSA), and additional work for previously modified airplanes. For certain airplanes, AD 2017-13-05 required installation of an electronic harness, terminating actions, and a ball-screw assembly inspection. This AD clarifies the formatting of a figure in the published version of AD 2017-13-05. This AD was prompted by reports indicating that affected parties misinterpreted the intent of a figure as formatted in the published version of AD 2017-13-05, which could result in a negative effect on compliance. We are issuing this AD to address the unsafe condition on these products.
2002-01-21: This amendment adopts a new airworthiness directive (AD), applicable to certain BAE Systems (Operations) Limited Model BAe 146 series airplanes and Avro 146-RJ series airplanes, that requires replacement of the standby generator with a new, improved standby generator. This amendment is prompted by mandatory continuing airworthiness information from a foreign airworthiness authority. This action is necessary to prevent loss of the standby generator, which, in the event of an emergency involving the principal generator, could result in the loss of electrical power to the airplane. This action is intended to address the identified unsafe condition.
2002-01-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires replacement of the trigger spring of the slide bar on each of the passenger doors with a new, stronger trigger spring. This action is necessary to prevent corrosion of the trigger spring on the slide bar of the passenger doors, which could result in incorrect locking of the slide bar and, during deployment of the escape slide, lead to a delay in evacuating passengers in an emergency. This action is intended to address the identified unsafe condition.
76-10-10: 76-10-10 BEECH: Amendment 39-2617. Applies to Models 65-88 (Serial Numbers LP-1 thru LP-47 except LP-27 and LP-29), 65-90, 65-A90, B90 and C90 (Serial Numbers LJ-1 thru LJ-676), E90 (Serial Numbers LW-1 thru LW-163), 100 and A100 (Serial Numbers B-1 thru B- 225) and 200 (Serial Numbers BB-2 thru BB-111) airplanes. Compliance: Required as indicated, unless already accomplished. To preclude opening of the cabin door in flight, accomplish the following: I. Within 50 hours' time in service after the effective date of this AD, and within each 50 hours' time in service thereafter, check the cabin door for proper operation and rigging in accordance with the applicable Beech Shop/Maintenance Manual. When all the items specified in Paragraph II have been complied with the requirements of this paragraph (I) are no longer applicable. II. Within 50 hours' time in service after September 15, 1976, perform the following: A. On Models 65-88 (Serial Numbers LP-1 thru LP-47 except LP-27 and LP-29) and 65-90, 65-A90, B90 (Serial Numbers LJ-1 thru LJ-351) airplanes, modify the cabin door installation in accordance with Beechcraft Service Instructions 0043-104 or 0016-105, Rev. I, or later approved revisions, as applicable. B. On Models 65-88 (Serial Numbers LP-1 thru LP-47 except LP-27 and LP-29), 65-90, 65-A90, B90 and C90 (Serial Numbers LJ-1 thru LJ-676), E90 (Serial Numbers LW-1 thru LW-163), 100 and A100 (Serial Numbers B-1 thru B-225), and 200 (Serial Numbers BB-2 thru BB-111) airplanes, perform the following in accordance with Beechcraft Service Instruction 0818-016 or later approved revisions: 1. Install Beech P/N 101-430124-1 and if fixed step door Beech P/N 101-430124-3 or -5 decals on the existing cabin door instruction plate and operate the cabin door accordingly. 2. Check cabin door latching mechanism and warning system for proper operation and rigging and rerig, if required, as instructed in the appropriate Beech Shop/Maintenance Manual. C. On the airplane models and serial numbers listed below add the indicated part number FAA-approved Airplane Flight Manual Supplement/Revision to the existing airplane pilot's operating manual or FAA-approved airplane flight manual: MODELS Beech Part Number (P/N) of FAA-Approved Airplane Flight Manual Supplement Revision dated November 14, 1975 or Subsequent 1) 65-88, 65-90, 65-A90, B90 and C90 (S/N LJ-502 thru LJ-624) and 100 (S/N B-2 thru B-89 and B-93) 1) P/N 131344 2) C90 (S/N LJ-625 thru LJ-676) 2) P/N 90-590010-53A6 3) E90 (S/N LW-1 thru LW-163) 3) P/N 90-590012-3A6 4) A100 (S/N B-1, B90 thru B-92, B-94 thru B-225) 4) P/N 100-590032-1A6 5) 200 (S/N BB-2 thru BB-111) 5) P/N 101-590010-3A4 III. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective May 28, 1976.