Results
2014-15-06: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100B SUD, 747-200B, 747-300, 747-400, and 747-400D series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the upper deck tension ties are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections for cracking in the upper deck tension ties, and related investigative and corrective actions if necessary; tension tie replacement; and post-replacement repetitive inspections for cracking in the upper deck tension ties, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct fatigue cracking of the upper deck tension ties. Severed or disconnected tension ties at multiple locations could result in rapid decompression and loss of structural integrity of the airplane.
46-24-02: 46-24-02 DOUGLAS: (Was Mandatory Note 3 of AD-762-7.) Applies to C-54 Series Aircraft. \n\n\tTo be accomplished not later than next periodic inspection. \n\n\tRevise the magneto wires forward of the firewall in accordance with Douglas Service Bulletin No. C-54-283 dated March 19, 1946. This is necessary to prevent burning of the magneto ground wire conduit which will cause the magneto to short out.
99-27-11: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11 200 and 400 series airplanes, that requires replacing the thrust reverser control unit selector valve with a new or modified valve and inspecting for proper rigging of the thrust reverser cable drums and thrust reverser control unit selector valve detent, and corrective actions, if necessary. This amendment also requires revising the Airplane Flight Manual to provide the flight crew with procedures to address uncontrolled operation of the thrust reverser system. 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 provide the flight crew with procedures in the event of uncommanded deployment of the thrust reverser, and to prevent uncommanded deployment of the thrust reverser in flight or on the ground, which could result in reduced controllability of the airplane.
99-27-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Rolls-Royce Limited Dart series turboprop engines. This amendment requires a one-time visual inspection of the interior of the switch to determine the type of low torque switch, and removal from service of unapproved Klixon low torque switches and replacement with serviceable parts. This amendment is prompted by the discovery of unapproved low torque switches in fleet operation. The actions specified by this AD are intended to prevent possible low torque switch failure, which could result in failure of a propeller to auto-feather following an engine power loss, resulting in possible loss of control of the airplane due to high asymmetric drag.
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.)
2014-13-17: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; Airbus 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. This AD was prompted by reports of failures of the right inner tank fuel pump. This AD requires repetitive functional tests of the circuit breakers for the fuel pump power supply, and replacement of certain circuit breakers. We are issuing this AD to detect and correct failure of the circuit breakers for the fuel pump power supply, which could result in a fuel pump overheating, leading to a fuel tank explosion.
99-25-13 C1: This document corrects two typographical errors that appeared in airworthiness directive (AD) 99-25-13 that applies to all Boeing Model 777-200 and -300 series airplanes. That AD currently requires revising the Limitations Section of the Airplane Flight Manual to prohibit the dispatch of certain airplanes under certain conditions. That AD also requires repetitive inspections to ensure correct operation of the backup generators; and, for certain airplanes, a one-time inspection to detect damage of the engine external gearbox; and corrective actions, if necessary. This document corrects incorrect paragraph references. This correction is necessary to ensure that operators accomplish the appropriate requirements of the AD.
99-26-06: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney JT8D-200 series turbofan engines, that requires initial and repetitive fluorescent magnetic particle inspections or fluorescent penetrant inspections of the combustion chamber outer case (CCOC) for cracks, and, if necessary, replacement with serviceable parts. Also, this AD requires a one-time boss material verification, and, if necessary, replacement with serviceable parts. Finally, this AD requires replacement of CCOCs with welded-on bosses with improved, one-piece CCOCs. Installation of the one-piece CCOC constitutes terminating action to the inspection requirements of this AD. This amendment is prompted by a report of an uncontained engine failure caused by fatigue cracks originating at the weld joining the drain boss to the CCOC. The actions specified by this AD are intended to prevent CCOC cracks, which could result in an uncontained engine failure and damage to the airplane.
92-16-14: 92-16-14 BEECH: Amendment 39-8323. Docket No. 92-NM-95-AD. Applicability: Model 400A series airplanes having serial numbers RK-1 through RK-28, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent fire and potential explosion of the fuselage fuel tanks, accomplish the following: (a) Within 14 days after the effective date of this AD, conduct a one-time visual inspection of the flame arrestor filter, Beech part number 45A48235-3, to determine whether it is manufactured of aluminum honeycomb (silver-colored) or phenolic honeycomb (brown-colored) material, in accordance with Beech Service Bulletin 2445, dated June 1992. (1) If the filter is made of aluminum honeycomb material, no further action is required. (2) If the filter is made of phenolic honeycomb material, prior to further flight, replace the currently installed flame arrestor filter with one having Beech part number 45A48235-5, or with Beech part number 45A48235-3 that has been confirmed to be made of aluminum. (b) As of the effective date of this AD, no flame arrestor filter, Beech P/N 45A48235-3, constructed of phenolic honeycomb material shall be installed on any airplane. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Wichita Aircraft Certification Office (ACO), FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (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 inspection shall be done in accordance with Beech Service Bulletin 2445, dated June 1992. (NOTE: The issue date of this Beech Service Bulletin 2445 is indicated only on page 1 of 4; no other page is dated.) This 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 Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 North Capitol Street NW., 7th Floor, Suite 700, Washington, DC. (f) This amendment becomes effective on September 1, 1992.
90-21-18: 90-21-18 GULFSTREAM: Amendment 39-6762. Docket No. 90-NM-87-AD. Applicability: Model G-IV series airplanes, Serial Numbers 1000 through 1130, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent in-flight failure of avionics equipment due to water intrusion, accomplish the following: A. Within 25 hours time-in-service or within 30 days after the effective date of this AD, whichever occurs later, install additional sealant on the upper portion of the radome and fuselage mating structure, and inspect the integrity of the rubber radome seal and aerodynamic seal, in accordance with Gulfstream Aerospace Aircraft Service Change (ASC) 183, dated March 15, 1990. 1. If defects are found in the rubber radome seal, replace prior to further flight, in accordance with ASC 183. 2. If defects are found in the aerodynamic seal, repair prior to further flight, in accordance with ASC 183. B. 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, Atlanta Aircraft Certification Office (ACO), ACE-115A, FAA, Central Region. NOTE: The request should be submitted directly to the Manager, Atlanta ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Atlanta ACO. C. 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 documents from the manufacturer may obtain copies upon request to Gulfstream Aerospace Corporation, P.O. Box 2206, M/S D-10, Savannah, Georgia 31402-9980. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton,Washington, or at the FAA, Central Region, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia. This amendment (39-6762, AD 90-21-18) becomes effective on November 14, 1990.
2014-14-03: We are superseding Airworthiness Directive (AD) 2014-07-01, for certain The Boeing Company Model 747 airplanes. AD 2014-07-01 required repetitive inspections for cracking in certain bulkhead structure; inspections of certain fasteners and support frame modifications on certain airplanes; related investigative and corrective actions, if necessary; and an interim modification that would terminate certain repetitive inspections. This AD clarifies certain paragraph references and revises a compliance time. This AD was prompted by a determination that certain paragraph references are in error. We are issuing this AD to detect and correct fatigue cracking of the BS 2598 bulkhead structure, which could adversely affect the structural integrity of the bulkhead and the horizontal stabilizer support structure, and result in loss of controllability of the airplane.
99-26-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 and 767 series airplanes, that requires replacement of the existing deactivation pin, pin bushing, and insert flange on each thrust reverser half, with new, improved components. This amendment is prompted by reports of partial deployment of deactivated thrust reversers during landing. The actions specified by this AD are intended to prevent failure of the thrust reverser deactivation pins, which could result in deployment of the thrust reverser in flight and consequent reduced controllability of the airplane.
82-03-08: 82-03-08 AIRBUS INDUSTRIE: Amendment 39-4307. Applies to Model A300 series airplanes, certificated in all categories, with main landing gear hinge arms, P/N C65-381-2, which have accumulated more than 2,500 takeoff/landing cycles and which have not been modified in accordance with Airbus Industrie Service Bulletin No. A300-32-118, dated August 21, 1979. Compliance required as indicated, unless already accomplished. To prevent failure of the main landing gear hinge arms, accomplish the following: (a) Within the next 8 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 12 hours time in service from the last inspection, but at least once each operating day, visually inspect the main landing gear hinge arms, P/N C65-381-2, for cracks in accordance with Airbus Industrie All Operators Telex AOT 32/80/105/SC1/0644/EM/AK/ME, dated March 21, 1980, and AOT 32/80/107/SC1/0795/EM/AK/ME, dated April 8, 1980, or FAA approved equivalents. Report defects found to the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.) NOTES: 1. Compliance times specified in Airbus Industrie All Operators Telex AOT 32/80/105/SC1/0644/EM/AK/ME, dated March 21, 1980, and AOT 32/80/107/SC1/0795/EM/AK/ME, dated April 8, 1980, are not applicable to this AD. 2. Pay particular attention to - (a) the inner edge of the hinge arm fork and the inner upper and lower edge between the LH and RH attachment lugs. (b) the hinge arm between the fork webs and cylindrical lugs or MLG actuator attachments. (c) the surrounding area of the cylindrical attachment lugs. (b) If the inspection required by paragraph (a) of this AD reveals cracks in a hinge arm, prior to further flight, replace the affected hinge arm with a serviceable hinge arm, P/N C65- 381-2 or P/N C65-381-4, in accordance with Airbus Industrie Service Bulletin No. A300-32-118. Repetitive inspections may be discontinued upon installation of P/N C65-381-4 hinge arms. (c) Prior to February 15, 1982, unless already accomplished, perform the visual and ultrasonic inspections, rework, and modification specified in Airbus Industrie Service Bulletin No. A300-32-287, dated May 19, 1980, or an FAA-approved equivalent. Repetitive inspections are required as follows: (1) If the depth of the corrosion pitting on the hinge arm does not exceed 0.008 inches, within sixty (60) days from accomplishment of the inspection required by Airbus Industrie Service Bulletin No. A300-32-287, dated May 19, 1980, or an FAA-approved equivalent, and thereafter at intervals not to exceed 120 days, ultrasonically inspect the hinge arm in accordance with Airbus Industrie Service Bulletin No. A300-32-288, dated May 19, 1980, or an FAA-approved equivalent. (2) If the depth of the corrosion pitting onthe hinge arm exceeds 0.008 inches, within thirty (30) days from accomplishment of the inspection required by Airbus Industrie Service Bulletin No. A300-32-287, dated May 19, 1980, or an FAA-approved equivalent, and thereafter at intervals not to exceed thirty (30) days, ultrasonically inspect the hinge arms in accordance with Airbus Industrie Service Bulletin No. A300-32-288, dated May 19, 1980, or an FAA-approved equivalent. (d) Cracked hinge arms must be replaced prior to further flight. (e) Accomplishment of paragraph (c) of this AD terminates the visual inspection requirements of paragraph (a). (f) Airplanes may be ferried in accordance with FAR Sections 21.197 and 21.199 to a place where the inspections and or repairs can be made in order to comply with this AD. (g) Upon request of an operator and submission of substantiating data, the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium,may upon recommendation of the cognizant FAA aviation safety inspector, adjust the inspection intervals. (h) If an equivalent means of compliance is used in complying with this AD, that equivalent must be approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. All persons affected by this directive who have not already received the referenced documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, B.P. 33, 31700 Blagnac, France. These documents may be examined at FAA Headquarters, Room 916, 800 Independence Avenue, SW., Washington, D.C. 20591. This amendment amends telegraphic AD T80EU16, as amended by telegraphic AD T80EU16A. This amendment becomes effective February 15, 1982.
99-26-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-7 series airplanes, that requires a one-time visual inspection to detect corrosion on the upper half of the lower longerons on the inboard nacelles; and corrective actions, if necessary. This AD also requires modification of the upper and lower longeron halves. 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 corrosion in the upper halves of the left and right hand lower longerons on the inboard nacelles, which could result in a landing gear failure.
80-13-07: 80-13-07 GOVERNMENT AIRCRAFT FACTORIES (GAF): Amendment 39-3806. Applies to Models N22B (Serial Nos. N22B-5 and up) and N24A (Serial Nos. N24A-42 and up). Compliance required as indicated. To prevent possible control obstruction when aileron is applied at the extreme aft stick position, accomplish the following: (a) Before the first flight of each day, until inspected per paragraph (b) of this AD, check the longitudinal and lateral controls for freedom of movement in the aft stick position by application of full left and right aileron. This check may be performed by the pilot-in-command and shall be recorded in the appropriate aircraft records in accordance with FAR 91.173. If interference is detected, accomplish paragraph (b) before further flight except that the aircraft may be flown in accordance with FAR 21.197 and FAR 21.199 to a base where the repair can be performed. (b) Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, inspect the gimbal support structure tie rod attachment plates and take corrective action as necessary to ensure that a minimum clearance of 0.125 inches exists between the end of the control wheel attachment bolt and the attachment plates in accordance with Part B of GAF Alert Service Bulletin ANMD-27-14 dated December 3, 1979, or an FAA approved equivalent. (c) The equivalent means of compliance specified in this AD must be approved by the Chief, Engineering and Manufacturing District Office, FAA, Pacific-Asia Region, Honolulu, Hawaii. NOTE: All persons affected by this directive who have not already received the applicable service bulletin from the manufacturer, may obtain copies upon request to the Government Aircraft Factories, 226 Lorimer Street, Port Melbourne, 3207 Vic., Australia. This document may be examined at the FAA, Engineering and Manufacturing District Office, 300 Ala Moana Blvd., Room 7321, Honolulu, Hawaii 96850, or Rules Docket, Room916, FAA, 800 Independence Ave., S.W., Washington, D.C. 20591. This amendment becomes effective July 6, 1980.
2001-23-15: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires repetitive detailed visual inspections to find discrepancies of the installation of the midspar fuse pins of the inboard and outboard struts, and follow-on actions, if necessary. That AD also provides for an optional terminating modification for the repetitive inspections. This amendment continues to require repetitive detailed visual inspections to find discrepancies of the installation of the midspar fuse pins of the inboard and outboard struts, and follow-on actions, if necessary. This amendment mandates accomplishment of the previously optional terminating modification. The actions specified by this AD are intended to find and fix discrepancies of the installation of the midspar fuse pins, which could result in loss of the secondary retention capability of the fuse pins, migration of the fuse pins, and consequent loss of the strut and engine from the airplane. This action is intended to address the identified unsafe condition.