Results
2021-14-09: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by a design review that identified rib 0 of the center wing box (CWB) as an area where a single failure of a clamshell type refuel/defuel line coupling could lead to the accumulation of dangerous levels of electrostatic charges within the fuel tank. This AD requires replacing the clamshell type refuel/defuel line coupling in the CWB at rib 0 with a threaded type fuel coupling, and installing an additional support bracket and clamp in the CWB at rib 0, as specified in a Transport Canada Civil Aviation (TCCA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2021-14-20: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737 airplanes. This AD was prompted by reports of latent failures of the cabin altitude pressure switches. This AD requires repetitive functional tests of the pressure switches, and on- condition actions, including replacement, if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2004-07-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 series airplanes, that currently requires replacing the transformer ballast assembly in the pilot's console with a new, improved ballast assembly. This amendment expands the applicability of the existing AD to include additional airplanes and provides an optional method for accomplishing the requirements of the existing AD. The actions specified by this AD are intended to prevent overheating of the ballast transformers due to aging fluorescent tubes that cause a higher power demand on the ballast transformers, which could result in smoke in the cockpit. This action is intended to address the identified unsafe condition. \n\nDATES: Effective May 5, 2004. \n\n\tThe incorporation by reference of a certain publication, as listed in the regulations, is approved by the Director of the Federal Register as of May 5, 2004. \n\n\tThe incorporation by reference of a certain other publication, as listed in the regulations, was approved previously by the Director of the Federal Register as of February 8, 2002 (67 FR 497, January 4, 2002).
96-13-07: This amendment supersedes an existing airworthiness directive (AD), applicable to all Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, that currently requires supplemental structural inspections to detect fatigue cracks, and repair or replacement, as necessary, to ensure the continued airworthiness of these airplanes. This amendment adds and revises certain significant structural items for which inspection and repair or replacement is necessary. This amendment is prompted by a structural re-evaluation conducted by the manufacturer, which identified additional structural elements where fatigue damage is likely to occur. The actions specified by this AD are intended to prevent reduced structural integrity of these airplanes.
95-25-07: This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft SA226 series airplanes that are equipped with a part number 27-55001-229 actuator assembly. This action requires replacing the main landing gear door actuator tang and associated hardware with parts of improved design. Reports of the main landing gear doors hanging up and locking the landing gear links on the affected airplanes prompted this action. The actions specified by this AD are intended to prevent the inability to extend the main landing gear because of the main landing gear door actuation roller contacting the lower edge of the tang and causing the linkage to lock over-center.
2004-07-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757-200 series airplanes, that currently requires modifications to the attachment installation of the forward lavatory. This amendment adds airplanes to the applicability of the existing AD. The actions specified by this AD are intended to prevent failure of the attachment installation of the forward lavatory during an emergency landing, which could result in injury to the crew and passengers. This action is intended to address the identified unsafe condition. \n\nDATES: Effective May 5, 2004. \n\n\tThe incorporation by reference of Boeing Special Attention Service Bulletin 757-25-0181, Revision 1, dated November 21, 2000, as listed in the regulations, is approved by the Director of the Federal Register as of May 5, 2004. \n\n\tThe incorporation by reference of Boeing Service Bulletin 757-25- 0181, dated June 26, 1997; and Boeing Alert Service Bulletin 757- 25A0187, dated September 18, 1997; as listed in the regulations, was approved previously by the Director of the Federal Register as of June 1, 1999 (64 FR 20146, April 26, 1999).
2011-13-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Bombardier Aerospace has completed a system safety review of the aeroplanes fuel system against fuel tank safety standards introduced in Chapter 525 of the Airworthiness Manual through Notice of Proposed Amendment (NPA) 2002-043 [which corresponds with the FAA's Special Federal Aviation Regulation (SFAR) 88]. The identified non- compliances were then assessed using Transport Canada Policy Letter No. 525-001, to determine if mandatory corrective action is required. The assessment showed that a number of modifications to the fuel system are required to mitigate unsafe conditions that could result in potential ignition source within the fuel system.We are issuing this AD to require actions to correct the unsafe condition on these products.
2021-13-13: The FAA is adopting a new airworthiness directive (AD) for all \n\n((Page 38210)) \n\nLeonardo S.p.a. Model AW189 helicopters. This AD was prompted by the identification of misleading information in the emergency procedure for the ''1(2) FUEL LOW'' caution message. This AD requires revising the existing Rotorcraft Flight Manual (RFM) for your helicopter. The FAA is issuing this AD to address the unsafe condition on these products.
91-10-06: 91-10-06 BRITISH AEROSPACE (BAe): Amendment 39-6987; Docket No. 90-CE-46-AD. Applicability: Beagle B121 Pup series 1, 2, and 3 (all serial numbers) airplanes, certificated in any category. Compliance: Required within the next 30 calendar days after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 60 calendar months. To avoid loss of control of the airplane, accomplish the following: (a) Replace the flight control column handgrips, part number BE-45-10283, in accordance with the instructions in BAe Mandatory Pup Service Bulletin (SB) B121/95, Revision 2, dated January 28, 1991. (b) Special 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. (c) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approvedby the Manager, Brussels Aircraft Certification Office, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. (d) The replacements required by this AD shall be done in accordance with British Aerospace Mandatory Pup SB B121/95, Revision 2, dated January 28, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. Section 552(a) and 1 CFR Part 51. Copies may be obtained from British Aerospace PLC, Manager Product Support, Commercial Aircraft Airlines Division, Prestwick Airport, Ayrshire, KA9 2RW Scotland; or British Aerospace, Inc., Librarian, Box 17414, Dulles International Airport, Washington, DC, 20041. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558,601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC. This amendment (39-6987, AD 91-10-06) becomes effective on May 22, 1991.
78-18-05: 78-18-05 PIPER AEROSTAR: Amendment 39-3295. Applies to Piper Aerostar Model 600, 601 and 601P airplanes certificated in all categories, serial numbers 150 through 520. \n\n\tCompliance required as indicated. To prevent reversed readings of left and right wing tank fuel quantity accomplish the following: \n\n\t(a)\tWithin 10 hours time in service after the effective date of this AD, unless already accomplished, with LH and RH wing tanks at least 50% depleted from tank capacity: \n\n\t\t1)\tRead and record fuel quantity indication for LH and RH wing fuel tanks. \n\n\t\t2)\tAdd 10 gallons of fuel to one wing tank only. \n\n\t\t3)\tRead and record fuel quantity for each wing tank. \n\n\t\t4)\tDetermine that the added fuel registers on the correct wing tank fuel quantity indicator selector position. \n\n\t\t5)\tIf the correct wing tank fuel quantity selector position registers the added fuel, the system is normal and no further action is required under this AD. \n\n\t(b)\tIf the appropriate wing tank fuel indicator position does not correctly register the added fuel the system may be improperly wired or the selector may be improperly indexed. In this event, prior to further flight: \n\n\t\tCorrect the fuel quantity indicating system malfunction. Refer to figure 1 for details of proper switch installation. \n\n\t(c)\tWithin 10 hours time in service after the effective date of this AD, on those airplanes with the fuel quantity indicating selector switch relabelled as an interim solution under (B)(2) of the original message of July 7, 1978, correct the fuel quantity indicating system as in (b) of this AD and revert to standard switch labelling. \n\n\t(d)\tSpecial flight permits may be issued in accordance with FARs 21.197 and 21.199 to operate aircraft to a base for accomplishment of the repair required by paragraph (b) of this AD. \n\n\t(e)\tEquivalent inspections and repairs may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective September 13, 1978.
2004-07-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 series airplanes, and C-9 (military) airplanes, that currently requires repetitive ultrasonic or magnetic particle inspections to detect cracking of the engine pylon aft upper spar straps (caps); and if necessary, replacement of the strap with a new strap, or modification of the engine pylon rear spar straps, which constitutes terminating action for the repetitive inspections. This amendment requires new, improved repetitive ultrasonic inspections, and corrective actions if necessary. This amendment also requires, among other items, a terminating action for the repetitive inspection requirements. The actions specified by this AD are intended to detect and correct fatigue cracking, which could result in major damage to the adjacent structure of the pylon aft upper spar cap, and consequent reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
2011-13-02: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During Landing Gear retraction/extension ground checks performed on the P2006T, a loose Seeger ring was found on the nose landing gear hydraulic actuator cap. The manufacturer has identified the root cause of this discrepancy in a design deficiency of the hydraulic actuator caps. This condition, if not corrected, could determine uncommanded and improper extension of the nose or main landing gear. We are issuing this AD to require actions to correct the unsafe condition on these products.
2021-13-08: The FAA is adopting a new airworthiness directive (AD) for all Safran Helicopter Engines, S.A. Arriel 2C and Arriel 2S1 model turboshaft engines. This AD was prompted by reports of error messages on the full authority digital engine control (FADEC) B digital engine control unit (DECU), caused by blistering of the varnish on the DECU circuit board. This AD requires the replacement of certain FADEC B DECUs. The FAA is issuing this AD to address the unsafe condition on these products.
98-04-24: This amendment adopts a new airworthiness directive (AD) that applies to Raytheon Aircraft Company Models E55, E55A, 58, 58A, 58P, 58PA, 58TC, 58TCA airplanes, and 60, 65-B80, 65-B90, 90, F90, 100, 300, and B300 series airplanes. This action requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD is prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icingconditions by providing more clearly defined procedures and limitations associated with such conditions
98-04-22: This amendment adopts a new airworthiness directive (AD) that applies to SOCATA - Groupe AEROSPATIALE, Model TBM 700 airplanes. This action requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD is prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
98-04-05: This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft Incorporated (Fairchild) Models SA226-TC, SA226-T, SA226-T(B), and SA226-AT airplanes. This action requires inspecting the center flap hinge and wing trailing edge ribs at the flap actuator attach brackets for cracks and if no cracks are found, installing a doubler on the rib, or replacing a cracked rib with a new rib assembly that is reinforced with a doubler. This action is the result of high local stress concentration, which led to fatigue cracking of the wing trailing edge ribs. The actions specified by this AD are intended to prevent asymmetrical flap deflection, which could force the airplane into an uncommanded roll with possible loss of control of the airplane.
93-01-16: 93-01-16 BEECH AIRCRAFT CORPORATION: Amendment 39-8470. Docket No. 92-CE-39-AD. Applicability: Model 1900C airplanes, serial numbers UC-1 through UC-174 and UD-1 through UD-6 (also referred to as Model C-12J), certificated in any category. Compliance: Required within the next 200 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent an airplane fire caused by fuel entering the electrically-heated stall warning vane housing, accomplish the following: (a) Inspect the pneumatic deice lines and the deice distributor valve for fuel leakage in accordance with Parts I and II of the ACCOMPLISHMENT INSTRUCTIONS section of Beech Service Bulletin (SB) No. 2430, dated March 1992. Prior to further flight, replace any fuel contaminated parts in accordance with Part II of the ACCOMPLISHMENT INSTRUCTIONS section of the referenced service information. (b) Modify the wet wing fuel barriers in accordance with Parts III and IV of the ACCOMPLISHMENT INSTRUCTIONS section of Beech SB No. 2430, dated March 1992. (c) 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. (d) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and send it to the Manager, Wichita Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office. (e) The inspection and modification required by this AD shall be done in accordance with Beech Service Bulletin No. 2430, datedMarch 1992. 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 the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on March 8, 1993.
91-21-04: 91-21-04 BRITISH AEROSPACE: Amendment 39-8051. Docket No. 91-NM-26-AD. Applicability: Model BAC 1-11 200 and 400 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent degradation in the structural capabilities of the pressure cabin on affected airplanes, accomplish the following: A. For airplanes operating at a maximum cabin differential pressure of 7.5 pounds per square inch (psi), as specified in British Aerospace Alert Service Bulletin 53-A-PM5991, Issue 1, dated September 5, 1990: At or prior to the accumulation of 33,000 landings or within 4,000 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 8,000 landings, accomplish the following: 1. Perform a dye penetrant inspection to detect cracks in the left and right machined attachment angles, Part Number AB27-7761/2, in accordance with paragraph 2.1.3 of the service bulletin. 2. Perform a visual inspection to detect cracks in the top flange of the longitudinal boom of the left and right outboard auxiliary beam, in accordance with paragraph 2.1.4 of the service bulletin. B. For airplanes operating at a cabin pressure in excess of 7.5 psi up to a maximum of 8.2 psi, as specified in British Aerospace Alert Service Bulletin 53-A-PM5991, Issue 1, dated September 5, 1990: At or prior to the accumulation of 22,000 landings or within 3,000 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 5,000 landings, accomplish the following: 1. Perform a dye penetrant inspection to detect cracks in the left and right machined attachment angles, Part Number AB27-7761/2, in accordance with paragraph 2.2.3 of the service bulletin. 2. Perform a visual inspection to detect cracks in the top flange of the longitudinal boom of the left and right outboard auxiliary beam, in accordance with paragraph 2.2.4 of the service bulletin. C. If defects are found during the inspections required by this AD, prior to further flight, either replace the cracked structure with serviceable parts of the same part number; or repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. Following repair or replacement, repeat the inspections required by paragraphs A. and B. of this AD at the specified intervals. D. All machined attachment angles having Part Number AB27-7761/2 must be replaced with a new part of the same part number prior to the accumulation of 85,000 landings since new and thereafter at intervals not to exceed 85,000 landings. E. 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. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. F. 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. G. The inspection, repair, and replacement requirements shall be done in accordance with British Aerospace Alert Service Bulletin 53-A-PM5991, Issue 1, dated September 5, 1990. 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. 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.This amendment (39-8051, AD 91-21-04) becomes effective on November 19, 1991.
2021-13-02: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-300ER series airplanes. This AD was prompted by a report that a production design change to certain insulation blankets inadvertently opened up leakage paths for halon and smoke to escape from the aft cargo compartment in the event of a fire. This AD requires installation of an insulation blanket assembly on top of existing insulation blankets in certain areas of the forward endwall in the aft cargo compartment. The FAA is issuing this AD to address the unsafe condition on these products.
2021-14-10: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400, 747-400D, and 747-400F series airplanes. This AD was prompted by reports of burned Boeing Material Specification (BMS) 8-39 urethane foam found in certain locations on the airplane; investigation revealed that the fire-retardant properties degrade with age. This AD requires inspecting the insulation blankets in certain areas of the forward cargo compartment for exposed BMS 8-39 urethane foam, not encapsulated by a protective fire resistant barrier, and for seal integrity, and replacing the BMS 8-39 urethane foam and seal if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
48-08-01: 48-08-01 BEECH: Applies to Model 35 Airplanes Having Serial Numbers Below D-1095 Except D-923, D-925, D-940, D-954, D975, D-983, D-1003, D-1006, D-1013, D-1025, D-1031, D-1038, D-1042, D-1048 Through D-1050, D-1052, D-1053, D-1056 Through D-1062, D-1064, D-1066 Through D-1068, D-1071, D-1072, D-1074, D-1075, D-1077 Through D-1081, D-1083, and D-1085 Through D-1093. Compliance required by November 1, 1948. To preclude possible engine malfunctioning as a result of starter gear chipping caused by improper engagement of the starter mechanism, accomplish the following: (1) Remove the starter assembly from the engine and replace the original starter pinion and clutch assembly with the new assembly, P/N DR1885537. Check the solenoid linkage adjustment to ascertain that the pinion and clutch assembly can move rearward to contact the starter adapter. If the linkage prevents full disengagement of the pinion, remove the toggle link pin and turn the plunger shaft outward untilfull retraction is obtained. Check to make sure that at least two threads are still engaged. Reinstall the starter assembly. (2) Install the new resistor coil, P/N DR 1885541, on the starter battery and ground power terminals. The coil must hang downward from the terminals. (3) Make all electrical connections as covered in Beech Starter Latching Relay Installation Instructions. (Continental Service Bulletin No. M47-19 dated August 31, 1947, and Beech Service Letter No. 10, Model 35, cover this same subject.)
98-03-16: This amendment adopts a new airworthiness directive (AD) that applies to The New Piper Aircraft Corporation (Piper) Model PA-38-112 airplanes. This action requires repetitively replacing the upper rudder hinge bracket. Reports of fatigue cracks occurring on the upper rudder hinge bracket, and the manufacture of a new upper rudder hinge bracket with a life limited improved design prompted this action. The actions specified by this AD are intended to prevent cracks in the upper rudder hinge bracket, which could result in separation of the rudder from the airplane and loss of control of the airplane.
2011-12-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: An inspection by the vendor revealed that a number of Rubber Bull Gears (RBG) in the Horizontal Stabilizer Trim Actuator (HSTA) of the CL-600-2C10, CL-600-2D15 and CL-600-2D24 aeroplanes were installed with a wheel material hardness out of specification. This non-conformity has a direct impact on the HSTA life limit. The teeth of these non-conformant RBGs could break and in extreme cases, could lead to uncontrolled HSTA movement without the ability to re-trim the aeroplane. If not corrected, this condition could result in a difficulty to control the pitch and subsequent loss of the aeroplane. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
98-04-09: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F28 Mark 0070 and Mark 0100 series airplanes, that requires a one-time visual inspection to detect cracking of the brake torque tube lever, and corrective action, if necessary. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the brake torque tube lever, which could result in a disconnection between the brake pedal and brake system, and consequent reduced directional controllability of the airplane during landing.
90-25-08: 90-25-08 BOEING: Amendment 39-6816. Docket No. 90-NM-107-AD. \n\tApplicability: Model 747 and 767 series airplanes, equipped with Class "C" lower lobe cargo compartments that do not have complete cargo compartment floors, certificated in any category. \n\tCompliance: Required within 30 months after the effective date of this AD, unless previously accomplished; except that, for airplanes that are subject to the requirements of Federal Aviation Regulation (FAR) 121.314, the modifications required by this AD shall not be accomplished prior to the accomplishment of the modifications required by FAR 121.314. \n\tTo prevent a cargo compartment fire from migrating up behind the cargo liner, accomplish the following: \n\tA.\tInstall a fire stop near the bottom of the sloping sidewall cargo compartment liner, in accordance with a method approved by the Manager, Seattle Aircraft Certification Office, FAA, Transport Airplane Directorate. Fire stop material must meet the requirements of FAR Part25, Appendix F, Part III. \n\tB.\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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \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\tThis amendment (39-6816, AD 90-25-08) becomes effective on January 2, 1991.