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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.
81-02-10: 81-02-10 BELL: Amendment 39-4025. Applies to Models 214B and 214B-1 helicopters, serial numbers up to and including S/N 28049. Compliance is required as indicated unless already accomplished. To prevent a clutch failure which will result in the loss of engine power to the main rotor, accomplish the following: (a) The freewheeling clutch assembly, P/N 214-040-021-001, must be removed from service and P/N 214-040-021-103 clutch assembly installed according to the following schedule; (1) P/N 214-040-021-001 clutch assemblies with 290 or more hours' time in service on the effective date of this AD must be removed from service within the next 10 hours' time in service. (2) P/N 214-040-021-001 clutch assemblies with less than 290 hours' time in service on the effective date of this AD must be removed from service prior to attaining 300 hours' time in service. (3) P/N 214-040-021-001 clutch assemblies with unknown time in service must be removed within the next ten hours' time in service. NOTE: BHT Alert Service Bulletin No. 214-80-13, dated August 22, 1980, pertains to this subject. (b) Special flight permits may be issued in accordance with FAR 21.197 and FAR 21.199 to fly aircraft to a base where this AD can be accomplished. (c) Any alternate equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. This AD supersedes AD 80-07-11 (Amdt. 39-3726, 45 FR 20778). The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a 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 Bell Helicopter Textron, Product Support Department, Post Office Box 482, Fort Worth, Texas 73101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at the FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at their headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. This amendment becomes effective January 26, 1981.
89-14-03: 89-14-03 LOCKHEED AERONAUTICAL SYSTEMS COMPANY: Amendment 39-6243. Applicability: Lockheed Model L-188A and L-188C series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent airplane control difficulties due to flap asymmetry, accomplish the following: A. Within 90 days after the effective date of this AD, inspect the flap universal joints to determine if they are splined without a stop. NOTE: Flap universal joints that are splined without a stop are easily detected by the lack of a screw and washer that holds the pins in place. If they do not have a stop, accomplish the following: 1. Remove from service any flap universal joints that are splined without a stop and install universal joints that are splined with a stop; or 2. Cut a circumferential groove in the splines of the torque tube shafts on each side of the universal joints (1 inch from the end of the shaft) and installa snap ring, in a manner approved by the Manager, Los Angeles Aircraft Certification Office, Northwest Mountain Region. The snap ring is to eliminate the possibility of spline disengagement. The snap ring should completely encircle the shaft; or 3. Modify each universal joint by drilling a hole and installing a 1/8-inch diameter steel pin through each side (two per joint). Locate the pin from .7 to .8-inch from each end, and locate so as to intersect the spline centerline. Peen both pin ends. This modification must be accomplished in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office, Northwest Mountain Region. NOTE: Local spotfacing may be necessary on pins located at maximum dimension. B. Within 90 days after the effective date of this AD and thereafter at intervals not to exceed one year, verify proper torque tube-to-universal joint engagement of .375-inch, as specified in Detail E of the L-188 Maintenance Manual, Section 27-6-8, Figure 201; and verify that the distance between the edges of the torque tube shoulders at BL55 is 5.5 to 5.87 inches (universal joints with internal stop), or 6.0 to 6.6 inches for universal joints reworked with added stop pins. C. Within 90 days after the effective date of this AD and thereafter at intervals not to exceed one year, inspect the wing flap asymmetry shutoff valves, P/N 668225-1, to ascertain whether the valves hang up or respond slowly (greater than 1 second). 1. If the valves hang up or respond slowly, prior to further flight, install a functioning serviceable valve of the same part number (P/N 668225-1) and repeat the inspections at intervals not to exceed one year. 2. Installation of modified valve, P/N 668225-101, or a new valve P/N 668225-101, in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office, Northwest Mountain Region, constitutes terminating action for the repetitive inspections of the wingflap asymmetry shutoff valves required by paragraph C. and C.1., above. D. Within 90 days after the effective date of this AD, rewire the flap asymmetry annunciator light in the cockpit to trigger the annunciator, in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office, Northwest Mountain Region, so that the light in the cockpit will illuminate when the asymmetry detector is tripped and not be dependent on the shutoff valve. E. 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, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office. F. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a base to accomplish the actions required by 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 Lockheed Aeronautical Systems Company, P.O. Box 551, Burbank, California 91520, Attn: L-188 Commercial Support Contracts, Dept. 63-11, Unit 33. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or 3229 East Spring Street, Long Beach, California. This amendment (39-6243, AD 89-14-03) becomes effective on July 24, 1989.
2017-19-22: We are superseding Airworthiness Directive (AD) 2014-07-09 for British Aerospace Regional Aircraft Jetstream Series 3101 and Jetstream Model 3201 airplanes. 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 both the need for newly added inspections for corrosion, which includes the door hinges/supporting structure and attachment bolts for the main spar joint and engine support, and inadequate existing instructions for inspection for corrosion for several areas including the rudder hinge location on the vertical stabilizer. We are issuing this AD to require actions to address the unsafe condition on these products.