Results
76-06-01: 76-06-01 SIKORSKY AIRCRAFT: Amendment 39-2541. Applies to S-61L, S-61N, S- 61NM, S-61R, S-62A, S-64A, S-64E, S-64F helicopters certified in all categories, including Military CH-3C, HH-3C, CH-3E, HH-3E, CH-54B helicopters certificated in all categories and equipped with: 1. Model 66WAP200 hydraulic pumps, Serial Numbers 1080 through 1086, 2013, 2015, 2228, 2298, 2670, 2889, and all Serial Numbers with "DO-" prefix, except FAA approved New York Air Brake Company Serial Numbers DO-1 through DO-83. 2. Model 66WAN200 hydraulic pumps, Serial Numbers DO-2110, DO-2117, DO- 2163, DO-2165, DO-2222, DO-2227. Compliance required as indicated. To detect flaking chrome plating from the pistons of Model 66WAP200 hydraulic pump, Serial Numbers 1080 through 1086, 2013, 2015, 2228, 2298, 2670, 2889, and all Serial Numbers with "DO-" prefix, except FAA approved New York Air Brake Company Serial Numbers DO-1 through DO-83; and Model 66WAN200 hydraulic pump, Serial Numbers DO-2110, DO-2117, DO-2163, DO-2165, DO-2222, DO-2227, accomplish the following: a. Before the first flight each day, inspect the filter and filter bowl on the primary, auxiliary, and utility hydraulic manifold for the presence of chrome plating flakes, in accordance with the applicable Maintenance Manual instructions. If flakes are found, remove all pumps, with serial numbers noted above, and replace with FAA approved pumps before further flight. Immediately after replacement of the pump, flush and inspect the hydraulic system in accordance with the applicable Maintenance Manual instructions. NOTE: For the requirements regarding the listing of compliance with this AD in the helicopter's permanent maintenance record, see FAR 91.173. b. Within the next 180 calendar days after the effective date of this AD, replace all pumps, with serial numbers noted above, with FAA approved New York Air Brake Company pumps. c. Advise the FAA, Chief, Engineering and Manufacturing Branch, New EnglandRegion, 12 New England Executive Park, Burlington, Massachusetts 01803, of the serial numbers of unapproved pumps found, the registration and serial number of the helicopter on which they are installed, and the serial nubmers of the replacement pumps. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.) d. After complying with Paragraph (b) of this AD, the inspection required by Paragraph (a) may be discontinued. This amendment becomes effective March 24, 1976.
2014-14-05: We are adopting a new airworthiness directive (AD) for certain Airbus Model A320-111, -211, -212, and -231 airplanes. This AD was prompted by reports of broken struts of the center wing box (CWB). This AD requires a detailed inspection of the CWB struts for cracking, and repair if necessary. We are issuing this AD to detect and correct cracked or broken struts, which could result in strut failure and consequent reduced structural integrity of the airplane.
2010-16-11: We are adopting a new airworthiness directive (AD) for certain Model MD-90-30 airplanes. This AD requires inspecting for corrosion of the retract cylinder support fitting for the main landing gear (MLG) and the mating bore for the support fitting in the MLG trunnion fitting, performing corrective actions if necessary, and replacing cadmium-plated retract cylinder support bushings and bearings. This AD results from reports of the retract cylinder support fitting for the MLG failing during gear extension and subsequently damaging the hydraulic system. We are issuing this AD to prevent corrosion and damage that could compromise the integrity of the retract cylinder support fitting for the MLG, which could adversely affect the airplane's safe landing.
2008-17-06: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Bombardier Model DHC-8-400 series airplanes. The existing AD currently requires revising the Limitations section of the airplane flight manual (AFM) to include procedures for pulling the "HYD PWR XFER'' circuit breaker in the event of the loss of all hydraulic fluid in the No. 1 or No. 2 hydraulic system. This AD requires a revision to the AFM to include additional procedures for ensuring that the "PTU CNTRL'' switch is Normal, the "PTU CNTRL ON'' advisory light is out, and the "HYD PWR XFER'' circuit breaker is pulled in the event of the illumination of the "2 HYD ISO VALVE'' caution light. This AD resulted from low No. 2 hydraulic pressure in-flight, which caused the power transfer unit to overspeed, and the fluid flow within the No. 1 hydraulic system to increase. We are issuing this AD to prevent possible loss of both the No. 1 and No. 2 hydraulic systems, resulting in the potential loss of several functions essential for safe flight and landing of the airplane. DATES: This AD becomes effective September 2, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of September 2, 2008. On July 10, 2007 (72 FR 30968, June 5, 2007), the Director of the Federal Register approved the incorporation by reference of certain other publications. We must receive any comments on this AD by September 15, 2008.
99-26-18: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace (Jetstream) Model 4101 airplanes, that requires repetitive inspections to detect loose or migrated levers of the elevator cable tension regulators, and replacement of the regulator assembly with a new assembly, if necessary. 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 detect and correct loose or migrated regulator levers of the elevator cable tension regulators, which could result in reduced controllability of the airplane.
2014-15-03: We are adopting a new airworthiness directive (AD) for certain serial number Pratt & Whitney Canada Corporation (P&WC) model PW150A turboprop engines. This AD requires rerouting of the igniter cables and installation of new support brackets. This AD was prompted by reports of damage to a high-pressure fuel line, which could result in a high- pressure fuel leak into the engine nacelle. We are issuing this AD to prevent high-pressure fuel leaks, which could cause engine fire and damage to the engine and the airplane.
90-15-07: 90-15-07 SHORT BROTHERS, PLC: Amendment 39-6661. Docket No. 90-NM-137-AD. Applicability: Model SD3-60 series airplanes, equipped with AAR Oklahoma, Inc., freon air conditioning system, installed in accordance with Supplemental Type Certificate (STC) SA3749SW, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent an electrical fire and subsequent loss of essential equipment and/or flight instruments, accomplish the following: A. Within 10 days after the effective date of this AD, inspect electrical panels 1C, 2C, 2D, and 6D to verify that all wiring and terminals are installed in accordance with Advisory Circular (AC) 43.13-1A. If there is evidence of arcing or burnt wires, prior to further flight, replace any defective wires and terminals. B. Within 10 days after the effective date of this AD, accomplish either sub-paragraph 1. or 2., below: 1. Modify the air conditioning system wiring installation and install a new placard on the co-pilot's audio panel, in accordance with AAR Oklahoma, Inc., Service Information Letter 5-90-1, dated June 7, 1990; and revise the Airplane Flight Manual (Document No. 18R008, Freon Air Conditioner Flight Manual Supplement) by incorporating Revision A, dated June 7, 1990; or 2. Deactivate the air conditioning system as follows: a. In Panel 1C, remove wire HH1A-2P (2 gauge wire) connected to the left- hand general service bus; cap and stow this wire. b. In Panel 2C, remove wire HH101A-2P (2 gauge wire) connected to the right-hand general service bus; cap and stow this wire. c. Locate the ground service circuit breakers located in panel 2D or 6D; pull the two 20 amp and the two 2 amp circuit breakers; and install a suitable collar around each circuit breaker shaft to prevent them from being reset. 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, Airplane Certification Office, ASW-150, FAA, Southwest Region. NOTE: The request should be submitted directly to the Manager, Airplane Certification Office, ASW-150, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Airplane Certification Office, ASW-150. D. Special flight permits may be issued in accordance with FAR Sections 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 AAR Oklahoma, Inc., 6611 S. Meridian Avenue, P.O. Box 59100, Oklahoma City, Oklahoma 73159. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the FAA, Southwest Region, Airplane Certification Office, 4400 Blue Mound Road, Fort Worth, Texas. This amendment (39-6661, AD 90-15-07) becomes effective on July 31, 1990.
99-24-04 C1: This document corrects information in an existing airworthiness directive (AD) that applies to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes. That AD currently requires a one-time visual inspection to determine whether self-aligning nuts are installed at certain locations of the aft pressure bulkhead tee; and corrective actions, if necessary. This document corrects a typographical error in a service bulletin reference. This correction is necessary to ensure that the appropriate service information is used to accomplish the AD. \n\n\tThe incorporation by reference of certain publications listed in the regulations was approved previously by the Director of the Federal Register as of December 27, 1999. (64 FR 63187, November 19, 1999).
47-49-01: 47-49-01 LOCKHEED: (Was Mandatory Note 34 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2088. Compliance required prior to December 31, 1947. Relocate the rudder trim tab cockpit control unit to comply with provisions of CAR 4b.322 regarding plane and sense of motion of control. (LAC Service Instruction 49/SI-18 covers this same subject.)
47-10-04: 47-10-04 LOCKHEED: (Was Mandatory Note 4 of AD-763-3.) Applies Only to Model 49 Serial Numbers 2021, 2022, 2026, 2027, 2028, 2034, and 2035. Compliance required prior to March 15, 1947. Add 12 grounding jumpers between the engine autosyn transmitters and their support brackets. (LAC Service Bulletin 049/SB-20 covers this same subject.)