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96-10-01 R1: This amendment revises Airworthiness Directive (AD) 96-10-01, which currently requires a complete landing light support replacement on certain The New Piper Aircraft, Inc. (Piper) Models PA-28-140, PA-28-150, PA-28-160, and PA-28-180 airplanes. Some of the serial numbers for these airplanes were incorrectly referenced in the Applicability section of AD 96-10-01. This AD maintains the requirements of AD 96-10-01, and corrects the serial numbers referenced in the Applicability section. The actions specified by this AD are intended to prevent the landing light retainer support seal from being ingested by the updraft carburetor, which could result in rough engine operation or possible engine failure and loss of control of the airplane. The incorporation by reference of Piper Service Bulletin No. 975, dated November 2, 1994, as listed in the regulations, was previously approved by the Director of the Federal Register as of June 10, 1996 (61 FR 19813, May 3, 1996).
2022-11-03: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by an indication that both elevator actuators of the PRIMary flight control computers (PRIMs) were considered faulty due to incorrect instructions with a new PRIM standard. This AD requires revising the existing airplane flight manual (AFM), and revising the operator's existing FAA-approved minimum equipment list (MEL) by incorporating certain master minimum equipment list (MMEL) provisions, to include limitations and procedures to mitigate the risk of elevator failure during flare, as specified in a European Union Aviation Safety Agency (EASA) Emergency AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2004-21-08 R1: We are revising an existing airworthiness directive (AD) for all Cessna Aircraft Company (Cessna) Models 190, 195 (L-126A,B,C), 195A, and 195B airplanes that are equipped with certain inboard aileron hinge brackets. That AD currently requires you to repetitively inspect the affected inboard aileron hinge brackets for cracks or corrosion and replace them if cracks or corrosion is found. Replacement with aluminum brackets would terminate the need for the repetitive inspections. This new AD retains the actions of AD 2004-21-08 while requiring future compliance following a revised service bulletin that clarifies the casting numbers and part numbers to be inspected. This AD was prompted by reports of confusion between the casting number on the aileron hinge bracket and the part number (P/N) called out in the AD. We are issuing this AD to correct the unsafe condition on these products.
97-01-01 R1: This amendment revises Airworthiness Directive (AD) 97-01-01, which currently requires repetitively inspecting the main gear sidebrace studs for cracks on The New Piper Aircraft, Inc. (Piper) Models PA-24, PA-28R, PA-30, PA-32R, PA-34, and PA-39 series airplanes, and replacing any main gear sidebrace stud found cracked. The Federal Aviation Administration (FAA) has approved certain alternative methods of compliance (AMOC) for AD 97-01-01, and has determined that these AMOC's should be incorporated into the AD. This AD will retain all the actions of AD 97-01-01, and will incorporate certain AMOC's as a way of accomplishing the actions specified in AD 97-01-01. The actions specified by this AD are intended to prevent a main landing gear collapse caused by main gear sidebrace stud cracks, which could result in loss of control of the airplane during landing operations.
2013-08-12: We are superseding an existing airworthiness directive (AD) for The Boeing Company Model 787-8 airplanes. That AD currently requires modification of the battery system, or other actions. This AD requires installing main and auxiliary power unit (APU) battery enclosures and environmental control system (ECS) ducts; and replacing the main battery, APU battery, and their respective battery chargers. This AD also requires revising the maintenance program to include an airworthiness limitation. This AD also revises the applicability by removing airplanes on which these changes have been incorporated in production prior to delivery. This AD was prompted by recent incidents involving lithium ion battery failures that resulted in release of flammable electrolytes, heat damage, and smoke on two Model 787-8 airplanes. We are issuing this AD to minimize the occurrence of battery cell failures and propagation of such failures to other cells and to contain any flammable electrolytes, heat,and smoke released \n\n((Page 24674)) \n\nduring a battery thermal event in order to prevent damage to critical systems and structures and the potential for fire in the electronics equipment bays.
78-24-01 R1: 78-24-01 R1 ROLLS-ROYCE LIMITED: Amendment 39-3345 as amended by Amendment 39-4641. Applies to Rolls-Royce DART engines and all variants of those engines listed below which have Rolls-Royce DART Modification 1525 incorporated (covered in Rolls-Royce DART Service Bulletin Da 72-351), as installed on, but not necessarily limited to the airplanes listed below. DART Engine Airplane 506, 510, 525, 530 Vickers Viscount Model 744, 745D, 810 511, 514, 528, 532 Fairchild F-27 & FH-227 series and Fokker F-27 series 526 Armstrong Whitworth AW-650 series 1 527 Handley Page Herald Type 300 529 Grumman G-159 and Fairchild F-27 and FH-227 series 532 Hawker Siddeley 748 series 2 542 General Dynamics Model 240 with STC No. SA1054WE installed (or Model 600), General Dynamics Model 340/440 with STC No. SA1096WE installed (or Model 640), and Nihon YS-11 and YS-11A series. Compliance is required as indicated, unless already accomplished. 1. Compliance for all affected DART engines except the Mk. 530 is based on an effective date of December 11, 1978. 2. Compliance for the DART Mk. 530 engines is based on an effective date of May 12, 1983. To prevent restricted movement of the engine power lever or the high pressure fuel shut-off valve control lever caused by control box mounting bolt failure, accomplish the following: (a) Within the next 100 hours engine time in service or one month after the effective date of this AD, whichever occurs first, inspect the engine control box mounting bolts for integrity as specified in paragraph 5 of Rolls-Royce Service Bulletin Da 76-A17, Revision 1, dated April 4, 1978 (hereinafter referred to as the service bulletin) or an FAA-approved equivalent. (b) If, during an inspection required by this AD, a bolt head is found to be detached or missing, before further flight replace both mounting bolts either - (1) With new bolts of the same part number in accordance with paragraph 6 of the Service Bulletin or an FAA-approved equivalent and continue to inspect the bolts in accordance with paragraph (a) of this AD at intervals not to exceed 400 hours engine time in service or 4 months, whichever occurs first; or (2) Install control box mounting bolts, in accordance with Rolls-Royce Service Bulletin Da 76-16, dated April 18, 1978, or an FAA-approved equivalent. (c) If a detached or missing bolt head is not found during the inspection required by paragraph (a) of this AD, continue to inspect the bolts in accordance with that paragraph at intervals not to exceed 400 hours engine time in service or 4 months, whichever occurs first. (d) The inspections required by paragraphs (b)(1) and (c) of this AD may be discontinued upon the installation of control box mounting bolts in accordance with Rolls-Royce Service Bulletin Da 76-16, dated April 18, 1978, or an FAA-approved equivalent. (e) Upon request of an operator, the Manager, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium, may adjust the inspection interval specified in paragraphs (b) and (c) of this AD provided that such requests are made through an FAA maintenance inspector and the request contains substantiating data to justify the request for that operator. Amendment 39-3345 became effective December 11, 1978. This Amendment 39-4641 becomes effective May 12, 1983.
2013-08-10: We are adopting a new airworthiness directive (AD) for certain Tracor (Convair) Model 340 and 440 airplanes and certain Military Model C-131B, C-131D, C-131E, and C131F/R4Y-1 airplanes. This AD requires repetitive inspections of the lower skin of the wings for cracking around the inboard side of the wing station (WS) 6 and 7 access panel doubler fingers and between stringers 5 and 11; repetitive inspections of the lower skin of the wings for cracking around stringers 6, 8, and 10, and around the WS 6 and WS 7 access panel doubler fingers; and repair if necessary. This AD was prompted by a report of a crack found on the lower skin of the right-hand wing between WS 5 and WS 6. We are issuing this AD to detect and correct fatigue cracking of the lower skin of the wings, which could result in reduced structural integrity of the wings.
48-14-03: 48-14-03 BEECH: Applies to Models AT-11 and C18S. Compliance required by next periodic inspection but not later than July 1, 1948. Inspect the lower member of the center section main wing spar in the landing gear nacelle area for evidence of wear caused by chafing of the cabin heater control housing. To prevent chafing either use clamps to support housing or cover control housing with 20-inch length of synthetic rubber hose.
98-22-13: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, and -40 series airplanes; and certain C-9 (military) series airplanes. This amendment requires modifying the piping of the potable water system. This amendment is prompted by reports of ice forming on the control cables in the wheel well of the left main landing gear due to the freezing and rupturing of undrained potable water pipes. The actions specified by this AD are intended to prevent such ice formation, which could render the slat, aileron, and spoiler flight controls inoperative, and consequently could result in reduced controllability of the airplane.
90-15-10: 90-15-10 LOCKHEED AERONAUTICAL SYSTEMS COMPANY: Amendment 39-6662. Docket No. 90-NM-115-AD. Applicability: Model L-1011 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent structural failure of the aft and mid fuselage eight-inch diameter duct compensators, accomplish the following: A. Within the next 300 flight hours after the effective date of this AD, verify that the part numbers of the aft and mid fuselage 8-inch diameter bleed air duct compensators coincide with the part numbers listed in Table I of the Accomplishment Instructions, Lockheed Service Bulletin 093-36-064, dated May 29, 1990. 1. If the part numbers coincide with the part numbers listed in Table I, no further actions are required. 2. If any compensator is found without coinciding part numbers, prior to further flight, conduct a thorough visual inspection of the fillet weld on the barrel assembly for cracks.a. If there is no evidence of cracking in the weld area, the compensator may remain in service and the visual inspection must be performed at intervals not to exceed 150 flight hours. b. If there is evidence of cracking during any inspection, prior to further flight, replace the compensator with one having a part number listed in Table I. B. Replacement of any aft or mid fuselage 8-inch diameter bleed air duct compensator with one having a part number listed in Table I of the Accomplishment Instructions of Lockheed Service Bulletin 093-36-064, dated May 29, 1990, constitutes terminating action for the repetitive inspections required by paragraph A.2., above, for that compensator. 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, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Los Angeles ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Los Angeles ACO. 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 Lockheed Aeronautical Systems Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Order Administration, Dept 65-33, U-33, B-1. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. This amendment (39-6662, AD 90-15-10) becomes effective July 31, 1990.