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85-16-02: 85-16-02 McDONNELL DOUGLAS: Amendment 39-5108. Applies to McDonnell Douglas Model DC-10 series airplanes, certificated in any category, which are listed in McDonnell Douglas Alert Service Bulletin A24-131, dated July 17, 1985. Compliance required within 15 days after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent hydraulic line damage and/or arcing of the electrical wiring installation associated with the lower galley hot entree cart, accomplish the following: \n\n\tA.\tInspect the lower galley electrically heated hot entree cart wiring and conduit installation in accordance with Douglas Alert Service Bulletin A24-131, dated July 17, 1985, or later FAA approved revision, Accomplishment Instructions A and B. Install or replace parts as necessary. \n\n\tB.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis amendment becomes effective August 19, 1985.
2003-11-14: This amendment adopts a new airworthiness directive (AD) that applies to certain The New Piper Aircraft, Inc. (Piper) Models PA-34- 200T, PA-34-220T, PA-44-180, and PA-44-180T airplanes that have a model 91E92-1 or model 91E93-1 combustion heater fuel pump installed. This AD requires you to accomplish a one-time inspection of the combustion heater fuel pumps for fuel leakage. If leakage is found, repair or replace the fuel pump. This AD is the result of recent reports of fuel leakage. The actions specified by this AD are intended to correct quality control problems with the heater fuel pump, which could result in failure of the heater fuel pump. Such failure could lead to fire or explosion in the cockpit.
86-15-03: 86-15-03 MITSUBISHI HEAVY INDUSTRIES, LTD.: Amendment 39-5354. Applies to Model MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, MU-2B-25, MU-2B-26 (Serial Numbers (S/N) 008 through 347 except S/Ns 313 and 321); MU-2B-30, MU-2B-35, MU-2B-36 (S/Ns 501 through 696 except S/Ns 652 and 661) airplanes with U.S. Type Certificate No. A2PC, with certain nose landing gear strut assemblies installed, certificated in any category. (This AD does not apply to MU-2B series airplanes having serial numbers with "SA" suffix.) Compliance: Required as indicated, unless already accomplished. To preclude failure of the nose landing gear (NLG) strut assembly with part numbers and serial numbers listed in MHI MU-2 Service Bulletin (S/B) 181 Revision B, dated April 8, 1985 (hereafter referred to as S/B 181) installed, accomplish the following: (a) For those airplanes with NLG strut assemblies having 4000 or more hours time- in-service (TIS) on the effective date of this AD, within the next 200 hours TIS, and thereafter at intervals not to exceed 200 hours TIS from the last inspection, inspect for cracks using magnetic flux inspection method or fluorescent penetrant inspection method in accordance with "INSTRUCTIONS," Part I of S/B No. 181. (b) For those airplanes with NLG strut assemblies having less than 4,000 hours TIS on the effective date of this AD; (1) For the outer cylinder assembly, within the next 200 hours TIS and thereafter at intervals not to exceed 200 hours TIS from the last inspection, inspect for cracks using magnetic flux inspection method or fluorescent penetrant inspection method in accordance with "INSTRUCTIONS," Part I, of S/B No. 181. (2) For the trunnion and the axle assembly, prior to achieving 4,200 hours total TIS and thereafter at intervals not to exceed 200 hours TIS from the last inspection, inspect for cracks using magnetic flux inspection method or fluorescent penetrant inspection method in accordance with "INSTRUCTIONS," Part I of S/B No. 181.(c) If cracks are found during any inspection required by paragraph (a) or (b) of this AD, prior to further flight, replace the cracked parts with serviceable parts marked "SP" in accordance with "INSTRUCTIONS," Part II of S/B No. 181. (d) Installation of the outer cylinder assembly, axle assembly or trunnion marked "SP" is terminating action for the repetitive inspection for that particular part. When all affected parts are replaced in accordance with Part II, permanently identify the NLG strut assembly with "SB 181" in vicinity of the NLG assembly part number. (e) Special flight permits may be issued in accordance with FAR Section 21.197 to ferry aircraft to a maintenance base in order to accomplish this AD. (f) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Western Aircraft Certification Office, ANM-170W, Northwest Mountain Region, FAA, Post Office Box 92007, Worldway Postal Center, Los Angeles, California 90009-2007. Allpersons affected by this AD may obtain copies of the documents referred to herein upon request to Mitsubishi Heavy Industries, Ltd., 10, Oye-Cho, Minato-ku, Nagoya, Japan, or Beech Aircraft Corporation (Licensee for Mitsubishi), 9709 East Central, Post Office Box 85, Wichita, Kansas 67201, or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment supersedes Amendment 39-3892 (45 FR 54729) as amended by Amendment 39-3956 (45 FR 70227), AD 80-18-12 R1. This amendment becomes effective August 13, 1986.
2020-12-11: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A319-111, -112, -113, -114, -115, -151N, and -153N airplanes; Model A320-251N, -252N, -253N, -271N, -272N, and -273N airplanes; and Model A321-251N, -251NX, -252N, -252NX, -253N, \n\n((Page 41178)) \n\n-253NX, -271N, -271NX, -272N, and -272NX airplanes. This AD was prompted by a report of a non-stabilized approach followed by an automatic go-around, which led to an airplane pitch-up attitude and resulted in an auto-pilot disconnection. This AD requires revising the airplane flight manual (AFM) and applicable corresponding operational procedures to limit the use of speed brakes in certain airplane configurations and informing all flight crews, thereafter, to operate the airplane with limitations accordingly, 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.
99-24-05: This amendment supersedes an existing emergency priority letter airworthiness directive (AD), applicable to ECD Model BO-105CB-5 and BO-105-CBS-5 helicopters, that currently requires, before further flight, creating a component log card or equivalent record and determining the calendar age and number of flights on each tension-torsion (TT) strap. This amendment requires the same actions as the emergency priority letter AD and additionally clarifies the compliance time requirements specified in the emergency priority letter AD. This amendment is prompted by an accident in which a main rotor blade (blade) separated from an ECD Model MBB-BK 117 helicopter due to fatigue failure of a TT strap. The same part number TT strap is also used on the ECD Model BO-105 helicopter. The actions specified by this AD are intended to prevent failure of a TT strap, loss of a blade, and subsequent loss of control of the helicopter.
87-03-01: 87-03-01 SHORT BROTHERS, PLC: Amendment 39-5510. Applies to Model SD3-30 airplanes listed in Short Brothers, PLC, Service Bulletin SD330-28-33, Revision 1, dated January 1, 1986, certificated in any category. To prevent fuel leaks into the passenger cabin, accomplish the following, unless previously accomplished: 1. Within 9 months after the effective date of this AD, modify the fuel containment system in accordance with Short Brothers, PLC, Service Bulletin SD330-28-33, Revision 1, dated January 1, 1986. 2. 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, Northwest Mountain Region. 3. 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 the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Short Brothers, PLC, 2011 Crystal Drive, Suite 713, Arlington, Virginia, 22202-3702. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective February 12, 1987.
2006-07-07: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A300-600 series airplanes. This AD requires modifying nine bolt holes in the vertical flange to prevent cracking before the inspection threshold of AD 98-18-02. This AD results from reports of cracking in the vertical web of the center spar sealing angles of the wing earlier than the inspection interval specified in the existing AD. We are issuing this AD to prevent crack formation in the sealing angles; such cracks could rupture the sealing angle and lead to subsequent crack formation in the bottom skin of the wing, and resultant reduced structural integrity of the center spar section of the wing.
99-23-17: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model AS 332C, L, and L1 helicopters, that requires a one-time inspection of the length of the main gearbox epicyclic module upper casing bearing attachment bolts (attachment bolts), and if they exceed a certain length, replacing the epicyclic module to preclude a potential interference between the attachment bolts and the 2nd stage planet gear cage web. This amendment is prompted by a report of interference between the attachment bolts and the second stage planet gear cage web of the epicyclic module in the main gearbox. The actions specified by this AD are intended to prevent failure of the second stage planet gear of the main gearbox, loss of main rotor drive and subsequent loss of control of the helicopter.
99-23-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model Hawker 1000 series airplanes, that requires a visual inspection of the PS wire bundle, shielded wires going to fuel probe `G,' and any other wire or wire bundle for chafing in the forward wing spar and forward ventral tank area; and corrective actions, if necessary. This amendment is prompted by reports indicating that, due to improper routing of a wire bundle, the wire bundle chafed against the forward ventral tank transfer/crossfeed valve, which caused an electrical short and resulted in failure of the landing light. The actions specified by this AD are intended to prevent a short circuit due to wire chafing, which can cause a fire in the ventral fuel tank area.
2006-08-13: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney Canada (PWC) PW535A turboshaft engines with serial numbers (SNs) lower than DC0241, and with hydromechanical fuel control (HFC) part number (P/N) 819735-4, 819735-5, or 819735-6 installed. This AD requires inspection and verification of the proper adjustment of the ratio unit setscrew adjustment of installed HFC units. This AD results from incidents of PW535A turboshaft engines experiencing lack of response to the power lever input during attempted engine acceleration, due to an incorrect adjustment of the HFC ratio unit setscrew. We are issuing this AD to prevent lack of engine response to power lever input, which could cause a single or dual engine in-flight shutdown event.