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2019-14-08: The FAA is superseding Airworthiness Directive (AD) 2016-07- 22, which applied to all Airbus SAS Model A300 B4-600, B4-600R, and F4- 600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. AD 2016-07-22 required modifying the electrical routing installation at the right-hand (RH) and left-hand (LH) wings to achieve a minimum distance between wiring bundles and surrounding structures. This new AD retains the requirements of AD 2016-07-22 and, for certain airplanes, adds a requirement to further modify the electrical installations in both wings, as specified in a European Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by reports of missing installation information for certain airplanes. The FAA is issuing this AD to address the unsafe condition on these products.
94-04-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Industrie Models A300, A310, and A300-600 series airplanes. This action requires repetitive deployment tests of the ram air turbine (RAT) and checks of the adjustment of the locking rod. This amendment is prompted by reports of failure of the RAT to rotate when necessary, due to maladjustment of the locking rod. The actions specified in this AD are intended to ensure the availability of the RAT in case of need.
90-18-03: 90-18-03 McDONNELL DOUGLAS: Amendment 39-6701. Docket No. 89-NM-197-AD.\n\n\tApplicability: Model DC-9 and C-9 (Military) series airplanes, including Model DC-9-80 series and Model MD-88 airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent structural failure, accomplish the following: \n\n\tA.\tWithin the threshold for inspections specified in the service bulletins listed in Table 2.1 or Table 2.2, as applicable, of "DC-9/MD-80 Aging Aircraft Service Action Requirements Document," McDonnell Douglas Report No. MDC-K1572, Revision A, dated June 1, 1990 (hereinafter referred to as "The Document"), or within one repetitive inspection period specified in those service bulletins after the effective date of this AD, whichever is later, inspect for cracks in accordance with those service bulletins. Repeat these inspections at intervals specified in the service bulletins listed in Table 2.1 or Table 2.2, as applicable, of The Document.\n\n\t\t1.\tIf cracks are found during any inspection, prior to further flight, either accomplish the terminating modification in accordance with paragraph B. of this AD, or repair in accordance with data approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.\n\n\tNOTE: Detection of discrepancies other than cracking necessitates appropriate corrective action in accordance with the provisions of Part 43 of the Federal Aviation Regulations (FAR).\n\n\t\t2.\tModification in accordance with paragraph B. of this AD terminates the individual inspection requirements of the applicable service bulletin.\n\n\tB.\tPrior to reaching the incorporation thresholds listed in Table 2.1 or Table 2.2, as applicable, of The Document, or within 4 years after the effective date of this AD, whichever occurs later, accomplish the structural modifications specified in the service bulletins listed in Table 2.1 or Table 2.2, as applicable, of The Document.\n\n\tNOTE: The modifications required by this paragraph do not terminate the inspection requirements of any other AD unless that AD specifies that any such modification constitutes terminating action for those specified inspection requirements. \n\n\tC.\tAn 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. \n\n\tNOTE: 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. \n\n\tD.\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\tThe inspections and modifications shall be done in accordance with the "DC-9/MD-80 Aging Aircraft Service Action Requirements Document," McDonnell Douglas Report No. MDC-K1572, Revision A, dated June 1, 1990, which incorporates the following list of affected pages:\n\n\nPage Number\nRevision\nDate\ni\nA\nJune 1, 1990\nii\nOriginal\t\nSeptember 12, 1989\niii - v\t\nA\nJune 1, 1990\n1 - 36\nA\nJune 1, 1990\n\t\t\t\n\tThis incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Business Unit Manager of Publications, C1-HCO (54-60). Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue, S.W., Renton, Washington; at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 1100 L Street, N.W., Room 8301, Washington, D.C. \n\n\tThis amendment (39-6701, AD 90-18-03) becomes effective on September 24, 1990.
84-03-52 R1: 84-03-52 R1 McDONNELL DOUGLAS: Amendment 39-4869. Applies to McDonnell Douglas Model DC-9 and Military C-9 series airplanes, certificated in all categories. Compliance required as indicated, unless previously accomplished. \n\n\tTo prevent degradation of available roll control, possible loss of an engine at critical flight regime, and/or loss of normal MLG retraction/extension capability, accomplish the following, unless previously accomplished: \n\n\tA.\tWithin five (5) calendar days after the effective date of this AD: \n\n\t\t1.\tOpen left and right inboard MLG doors and install doorkeepers. (See Maintenance Manual, Chapter 32-00, paragraph entitled "General Maintenance Practice.") \n\n\t\t2.\tLocate an area convenient to the secondary latch, P/N 9953874, or bracket, P/N 2919899-1, to install safety wire. Secure lateral control mixer shield assembly to adjacent structure (mixer assembly, P/N 5924667) with .032-inch or .040-inch inconel or stainless steel safety wire and verify the safety wiring installation. \n\n\t\t3.\tWhenever the lateral control mixer shield has been opened, the shield shall, upon closing, be properly secured and safety wired with .032-inch or .040-inch inconel or stainless steel safety wire. The installation of the safety wire shall be verified by a representative of the operator and recorded in the aircraft records prior to further flight. \n\n\t\t4.\tRemove doorkeepers and close left and right MLG doors. \n\n\tB.\tAlternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: Removal of the mixer shields in accordance with McDonnell Douglas Service Bulletin 27-247, dated February 16, 1984, or later revision approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region, is an approved alternate means of compliance for the DC-9-10 through -80 and Military C-9 series airplanes.All 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 June 4, 1984, and was effective earlier to those recipients of telegraphic AD T84-03-52 dated January 27, 1984.
89-14-02: 89-14-02 McDONNELL DOUGLAS: Amendment 39-6245. \n\n\tApplicability: Model DC-8, DC-9 and C-9 (Military) series airplanes, including Model DC-9-80 series airplanes and Model MD-88 airplanes. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent failure of the rudder pedal bracket assembly, which could result in the loss of rudder and braking control at either the captain's or first officer's positions, accomplish the following: \n\n\tA.\tPrior to the accumulation of 40,000 landings or within 30 days after the effective date of this AD, whichever occurs later, perform either a visual or dye penetrant inspection for cracks of the captain's and first officer's rudder pedal bracket, part numbers (P/N) 5616067 and 5616068, respectively, in accordance with McDonnell Douglas Alert Service Bulletins A27-273 (for Model DC-8 series) or A27-307 (for Model DC-9 and DC-9-80 series and Model MD-88), as applicable, both dated May 16, 1989. \n\n\tNOTE: McDonnell Douglas Alert Service Bulletins A27-273 (DC-8) and A27-307, both dated May 16, 1989, are hereinafter referred to as ASB A27-273 and ASB A27-307, respectively. \n\n\t\t1.\tIf an initial visual inspection is accomplished, and no cracks are found, perform a dye penetrant inspection of the rudder pedal bracket assembly within 180 days after the visual inspection, and thereafter accomplish dye penetrant inspections at intervals not to exceed 12 months or 2,500 landings, whichever occurs earlier. \n\n\t\t2.\tIf an initial dye penetrant inspection is accomplished, and no cracks are found, accomplish repetitive dye penetrant inspections at intervals not to exceed 12 months or 2,500 landings, whichever occurs earlier. \n\n\tB.\tIf cracks are detected, prior to further flight, remove and replace the rudder pedal bracket assembly in accordance with ASB A27-273 or A27-307, as applicable. Prior to the accumulation of 40,000 landings after replacement with the new part, resume the repetitive inspections in accordance with paragraph A., above. \n\n\tC.\tAn 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. \n\n\tNOTE: 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. \n\n\tD.\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 initial inspection requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publications, C1-LOO (54-60). These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. \n\n\tThis amendment (39-6245, AD 89-14-02) becomes effective on July 5, 1989.
81-21-01: 81-21-01 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4227. Applies to Model SA315B helicopters, equipped with Eastern Rotorcraft Corporation (ERC) cargo hook assemblies, P/N 17112-4, Serial Numbers 1 through 103, in accordance with Supplemental Type Certificate (STC) SH1735SW, certificated in all categories (Airworthiness Docket No. 81-ASW-33). Compliance required as indicated. To prevent possible failure of the ERC cargo hook support legs, P/N 12579-1, due to fatigue cracks, accomplish the following, unless already accomplished, within the next 100 hours' time in service after the effective date of this AD: a. For suspension assemblies, P/N 17112-4, which have accumulated 1,000 lifts or calendar months of service, whichever occurs first, accomplish a magnetic particle inspection of the lugs, P/N 12579-1, in accordance with Aerospatiale Helicopter Corporation Service Bulletin No. SB315-05, dated March 11, 1981, or an FAA-approved equivalent.b. If one lug is found to have cracks, remove and replace all four lugs in accordance with Aerospatiale Helicopter Corporation Service Bulletin No. SB315-04, dated January 20, 1981, or an FAA-approved equivalent. c. If no lugs are cracked, reinstall and accomplish magnetic particle inspections at intervals of 1,000 lifts or 12 calendar months, whichever occurs first, as required by paragraph a. of this AD. d. The inspections required by paragraph a. of this AD are not required after compliance with Aerospatiale Helicopter Corporation Service Bulletin No. SB315-04. e. The helicopter may be flown in accordance with FAR 21.197 to a base where inspections can be performed. f. For the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of lifts may be determined by multiplying each helicopter's hours' time in service by the operator's fleet average lifts per hour for the helicopter type. This amendment becomes effective November 4, 1981.
2019-14-03: The FAA is superseding Airworthiness Directive (AD) 2016-07- 12, which applied to certain Airbus SAS Model A318, A319, A320, and A321 series airplanes. AD 2016-07-12 required repetitive inspections for damage and cracking of the aft fixed fairing (AFF) of the pylons, and repair if necessary. This AD retains the requirements of AD 2016- 07-12 and requires additional repetitive inspections at the upper spar at a certain rib area and corrective actions if necessary, as specified in an European Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by reports of cracking of the AFF of the pylons due to fatigue damage of the structure and reports of cracks on a certain rib of a modified AFF of the pylons. The FAA is issuing this AD to address the unsafe condition on these products.
94-24-02: This amendment supersedes an existing airwothiness directive (AD), applicable to certain Canadair Model CL-600-2B19 series airplanes, that currently requires a revision to the FAA- approved Airplane Flight Manual (AFM) to restrict altitude and airspeed operations of the airplane under certain conditions of hydraulic system failure. This amendment requires the removal of all elevator flutter dampers and requires a revision to the AFM that advises the flight crew of the need to perform daily checks to verify proper operation of the elevator control system. This amendment is prompted by reports that the installation of the stronger shear pins may jam or restrict movement of the elevator. The actions specified in this AD are intended to prevent failure of the lugs and/or pins, which may increase the likelihood of jamming or restricting movement of the elevator and the resultant adverse affect on the controllability of the airplane.
92-04-06: 92-04-06 AIRBUS INDUSTRIE: Amendment 39-8177. Docket 91-NM-263-AD. Applicability: Model A320 Series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent excessive backlash at the elevator, which could lead to reduced controllability of the airplane, accomplish the following: (a) Within 30 days after the effective date of this AD, measure the deflection at each elevator trailing edge in accordance with paragraph 2.B.(1) of Airbus Service Bulletin A320-27- 1043, dated October 7, 1991. (1) If the measured elevator deflection is less than or equal to 4 mm, (0.16 inch), with zero play, repeat the elevator deflection inspections, in accordance with the following schedule: (i) If the procedures in paragraphs 2.B.(2), 2.B.(3), 2.B.(4), and 2.B.(5) in the Service Bulletin have been accomplished, repeat the inspection at intervals not to exceed 12,000 hours time in-service. (ii) If the procedures in paragraphs 2.B.(2), 2.B.(3), 2.B.(4), and 2.B.(5) in the Service Bulletin have not been accomplished, repeat the inspection at intervals not to exceed 350 hours time in-service. (2) If the measured elevator deflection is greater than 4 mm (0.16 inch), and less than or equal to 10 mm (0.40 inch), repeat the elevator deflection inspections, in accordance with the following schedule: (i) If the procedures in paragraphs 2.B.(2), 2.B.(3), 2.B.(4), and 2.B.(5) in the Service Bulletin have been accomplished, repeat the inspection at intervals not to exceed 3,000 hours time in-service. (ii) If the procedures in paragraphs 2.B.(2), 2.B.(3), 2.B.(4), and 2.B.(5) in the Service Bulletin have not been accomplished, repeat the inspection at intervals not to exceed 7 calendar days. (3) If the measured elevator deflection is greater than 10 mm (0.40 inch), and less than or equal to 15 mm (0.60 inch), accomplish the following: (i) If the procedures in paragraphs 2.B.(2), 2.B.(3), 2.B.(4), and 2.B.(5) in the Service Bulletin have not been accomplished, repeat the elevator deflection inspections daily. Within 50 additional hours time in-service, accomplish the procedures of paragraphs 2.B.(2), 2.B.(3), 2.B.(4), and 2.B.(5) in the Service Bulletin. Prior to further flight, replace worn parts in accordance with the Service Bulletin. (ii) If the procedures in paragraphs 2.B.(2), 2.B.(3), 2.B.(4), and 2.B.(5) in the Service Bulletin have been accomplished, prior to further flight, replace worn parts, in accordance with the Service Bulletin. (4) If the measured elevator deflection is greater than 15 mm (0.60 inch), prior to further flight, replace worn parts and accomplish the procedures of paragraphs 2.B.(2), 2.B.(3), 2.B.(4), and 2.B.(5), in the Service Bulletin. (b) If worn or out-of-tolerance components of the elevator servo controls and attachments are replaced in accordance with Airbus Industrie Service Bulletin A320-27-1043, paragraphs 2.B.(2), 2.B(3), 2.B.(4), and 2.B.(5), after such replacement, repeat the elevator deflection inspections at intervals specified in paragraph (a) of this AD. (c) An alternative method 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. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it 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 the airplane to a location where the requirements of this AD can be accomplished. (e) The inspections and replacements required by this AD shall be done in accordance with Airbus Service Bulletin A320-27-1043, dated October 7, 1991. This incorporation by reference was approved by the Director of the Federal Registerin accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. (f) This amendment (39-8177, AD 92-04-06) becomes effective on March 6, 1992.
2019-16-06: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A320-251N and A320-271N airplanes. This AD was prompted by analysis and laboratory testing of the behavior of the flight control laws, which identified reduced efficiency of the angle of attack (AoA) protection that may result in excessive pitch attitude in certain configurations in combination with specific maneuvers commanded by the flight crew. This AD requires revising the existing airplane flight manual (AFM) to incorporate operational limitations, 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.