Results
2012-13-11: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (ECD) Model MBB-BK 117 (all versions) and BO-105LS A-3 helicopters. This AD requires inspecting the tail rotor pitch link spherical bearing for proper swaging. This AD is prompted by a report of a tail rotor pitch link with a spherical bearing that had migrated out of the bearing bore. The actions specified by this AD are intended to prevent failure of the tail rotor pitch link and subsequent loss of control of the helicopter.
75-24-13: 75-24-13 MCCAULEY PROPELLERS: Amendment 39-2435. Applies to the two- bladed constant speed and full feathering Model D2AF34C52/ 80GF-0 and D2AF34C52A/80GF- 0 series propellers having hub serial numbers 63000 through 659999, installed on but not limited to Cessna 310I type aircraft. Compliance required as indicated, unless already accomplished. To prevent hub failures, accomplish the following: A. Propellers with 1500 or more total hours in service as of the effective date of this Airworthiness Directive must be inspected and modified in accordance with Paragraph (D) within the next 100 hours in service after the effective date of this AD. B. Propellers with less than 1500 hours in service as of the effective date of this Airworthiness Directive must be inspected and modified in accordance with Paragraph (D) prior to the accumulation of 1600 hours in service. C. Propellers whose total hours in service are unknown will be assumed to have 1500 hours minimum and thus fall within the requirements for inspection and modification in accordance with Paragraph (A). D. Remove propeller from the aircraft, disassemble, inspect components and replace the hub in accordance with McCauley Service Manual No. 710930 and Bulletin No. 111 dated August 11, 1975, or later Federal Aviation Administration approved revisions, or an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, Great Lakes Region. The manufacturer's specifications and procedures identified in this Directive are incorporated herein and made part hereof pursuant to 5 U.S.C. 522(a)(1). All persons affected by this Directive who have not already received these documents from the manufacturer, may obtain copies upon request to McCauley Accessory Division, Cessna Aircraft Corporation, Box 7, Roosevelt Station, Dayton, Ohio 45417. These documents may also be examined at the Great Lakes Regional Office, 2300 East Devon Avenue, Des Plaines, Illinois 60018, and at FAA Headquarters, 800 Independence Avenue S.W., Washington, D.C. A historical file on this Airworthiness Directive which includes incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C. and at the Great Lakes Region. This amendment becomes effective November 26, 1975.
2012-14-13: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318-112 and -121 airplanes; Model A319-111, -112, -115, - 132, and -133 airplanes; Model A320-214, -232, and -233 airplanes; and Model A321-211, -212, -213, and -231 airplanes. This AD was prompted by reports of some fuselage nuts found cracked. This AD requires an inspection to determine if certain fuselage nuts are installed, a detailed inspection for cracking of fuselage nuts having a certain part number, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct fuselage nuts found cracked, which could result in reduced structural integrity of the airplane.
2018-05-03: We are adopting a new airworthiness directive (AD) for certain Safran Helicopter Engines, S.A., Arrius 2F turboshaft engines. This AD requires inspection and replacement of the magnetic heads installed on oil system electrical magnetic plugs. This AD was prompted by reports from the manufacturer of a batch of non-conforming magnetic heads installed on electrical magnetic plugs. We are issuing this AD to address the unsafe condition on these products.
2012-14-15: We are adopting a new airworthiness directive (AD) for certain aircraft equipped with Honeywell International, Inc. Model KGS200 Mercury\2\ wide area augmentation system (WAAS) global navigation satellite sensor units (GNSSU). This AD requires you cease all localizer performance (LP), localizer performance with vertical guidance (LPV), and satellite based augmentation system (SBAS) lateral navigation/vertical navigation (LNAV/VNAV) approaches until a software problem is corrected. This AD was prompted by a report and follow-up investigation of a software problem that occurred during flight test trials of SBAS-capable aircraft using a similar Honeywell global positioning system (GPS) sensor and the same software as the Model KGS200 Mercury\2\ GNSSU. A software problem occurred that could result in misleading information during LP, LPV, or SBAS LNAV/VNAV approaches. We are issuing this AD to correct the unsafe condition on these products.
2003-08-16: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 airplanes, that requires a one-time inspection for chafing of the RDB wire bundle against the No. 2 automatic direction finder (ADF) receiver located at the aft end of the forward right radio rack; repair or replacement, if necessary; and modification of the wire bundle. The actions specified by this AD are intended to prevent chafing of the RDB wire bundle against the No. 2 ADF receiver, which could result in electrical arcing and consequent smoke and/or fire in the cockpit. This action is intended to address the identified unsafe condition.
47-34-02: 47-34-02 BEECH: (Was Mandatory Note 3 of AD-770-1 and Mandatory Note 4 of AD- 765-1.) Applies to D18S, D18C and D18C-T Airplanes Which Do Not Have Drain Provisions at Bulkhead No. 15. Compliance required prior to December 1, 1947. To provide additional drainage, to prevent freezing of trapped moisture in the tail cone which could jam the elevator control system, a 3/4-inch diameter hole should be drilled near the front of the tail cone outer section on the centerline of the lower surface. A suitable marine grommet should be installed to provide for negative pressures. Also a 1/2-inch diameter hole should be drilled on each side of the jack pad through the lower part of bulkhead No. 15. (Beech Service Bulletin D18-46 covers this same subject.)
2021-18-15: The FAA is adopting a new airworthiness directive (AD) for certain PZL Swidnik S.A. Model PZL W-3A helicopters. This AD was prompted by a report that displaced teeth were detected on the moveable assemblies of a main rotor (MR) blade droop stop. This AD requires removing from service the moveable assemblies from each affected MR blade droop stop and prohibits installation of an affected MR blade droop stop and moveable assemblies of affected MR blade droop stops. The FAA is issuing this AD to address the unsafe condition on these products.
2012-13-10: We are adopting a new airworthiness directive (AD) for the PZL Swidnik S.A. (PZL) Model PZL W-3A helicopter with a certain generator air outlet collector (collector) installed. This AD requires modifying the generator air outlet collector attachments (collector attachments). This AD is prompted by an incident where cyclic control stick movement was restricted due to rotation of a loose collector, resulting in locking of the longitudinal control system hydraulic actuator fork end. These actions are intended to prevent rotation of the collector, which could lead to restricted cyclic control stick movement, and subsequent loss of control of the helicopter.
99-06-02: This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft, Inc. (Fairchild) SA226 and SA227 series airplanes. This AD requires repetitively inspecting the wing spar center web cutout on both wings for cracks between Wing Station (WS) 8 and WS 17.5, and immediately repairing any area found cracked. This repair will eliminate the need for the repetitive inspections on that particular wing spar. This AD is the result of reports of cracks in the wing spar center web cutout caused by fatigue due to airplane maneuvering and wind gusts. The actions specified by this AD are intended to detect and correct fatigue cracking of the wing spar center web cutout area, which could result in structural failure of the wing spar to the point of failure with consequent loss of control of the airplane.
2003-08-12: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) series airplanes. This action requires a detailed inspection to detect cracks of the vane brackets of the inboard flap actuator beam, and follow-on repetitive detailed inspections or corrective actions, as applicable. This action also provides for two optional terminating actions for the detailed inspection(s). This action is necessary to detect and correct gaps between the flap vane bracket and the adjacent lower skin and between the flap vane bracket and vane actuator beam of the wing flap systems, and premature cracking of the flap vane brackets, which could result in failure of the flap vane bracket(s) when the flaps are extended and the flap vane is aerodynamically loaded. Loss or warping of the flap vane in flight could decrease the lift on one side of the airplane, which could lead to reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
67-32-01: 67-32-01 BRITISH AIRCRAFT CORP: Amendment 39-573. Applies to BAC 1-11 Airplanes Model/Type 212AR, 401AK, 410AQ, which have a center fuel tank fitted with Thompson Ramo fuel pumps P/N 248800/4, P/N 248800/5 or pumps manufactured under license by Plessey which include additional part number 570/1/21221/004. Amendment 39-522 (32 F.R. 17515), AD 67-32-1, is amended. Compliance required as indicated. To prevent fuel pump movement and consequent fuel leakage, accomplish the following: (a) Within the next 200 hours' time in service after the effective date of this AD, unless already accomplished, inspect the center tank fuel pump installation in accordance with BAC 1-11 Alert Service Bulletin 28-A-PM 2701, Issue 2, or later ARB-approved issue, or FAA- approved equivalent. (b) If leaks are found when conducting the inspection required by paragraph (a), before further flight stop the leaks by repositioning the fuel booster pump and, if necessary, replacing the seals between the pump and canister. (c) Within the next 1,000 hours' time in service after the effective date of this AD, modify the center tank fuel booster pumps in accordance with British Aircraft Corporation Service Bulletin No. 28-PM 2701 or later ARB-approved issue, or an equivalent approved by the Chief, Aircraft Certification Staff, European Region. This amendment becomes effective May 2, 1968.
2012-13-12: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model G-IV, GIV-X, GV, and GV-SP airplanes. This AD requires measuring to determine paint thickness on the flight control surfaces and corrective actions if necessary, and revising the Airplane Flight Manual (AFM). This AD was prompted by reports of failure to inspect or document the paint thickness on flight controls (ailerons, rudder, elevator), potentially having a negative impact on the flutter characteristics of the airplane. We are issuing this AD to detect and correct paint thickness on flight controls, which could result in loss of control of the airplane due to flutter.
99-06-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400, -400D, and -400F series airplanes, that requires modification of the P212 and P213 panels of the cabin pressure control system. For certain airplanes, this amendment also requires modification of the P5, P6, and P7 panels, and the W4701, W4703, and W4908 wire bundles, as applicable. This amendment is prompted by a report of in-flight loss of cabin pressurization control due to a single failure of the auxiliary power unit (APU) battery. The actions specified by this AD are intended to prevent loss of control of the cabin pressurization system, which could result in rapid depressurization of the airplane. Such rapid depressurization could result in deleterious physiological effects on the passengers and crew; and airplane diversions, which represent an increased risk to the airplane, passengers, and crew.
2012-13-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, -300ER, and 777F series airplanes. This AD was prompted by a report indicating that a fire originated near the first officer's area, which caused extensive damage to the flight deck. This AD requires replacing the low-pressure oxygen hoses with non-conductive low-pressure oxygen hoses in the flight compartment. We are issuing this AD to prevent electrical current from passing through the low-pressure oxygen hose internal anti-collapse spring, which can cause the low-pressure oxygen hose to melt or burn, and a consequent oxygen-fed fire in the flight compartment.
55-15-02: 55-15-02 CONVAIR: Applies to All 240 and 340 Series Aircraft Equipped with Hamilton Standard Propellers. Compliance required by first scheduled engine change after November 1, 1955, but not later than November 1, 1956. To increase the fire resistance integrity of the propeller feathering system against damage by a powerplant fire, all flexible hose components of propeller feathering lines forward of the firewall in zone 2 must be replaced with lines and fittings which will meet current fire resistance requirements. Convair Service AirGram No. 123 dated October 8, 1954, covers this subject. The following hose assemblies may also be considered acceptable for this application: (a) Aeroquip 680-10S hose assemblies with Aeroquip 304 protective sleeves over end fittings (Aeroquip assembly P/N 304000). (b) Resistoflex-SSFR-3800-10 hose assemblies. (c) Aeroquip 309009 hose assemblies.
2018-04-12: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, -500 series airplanes. This AD was prompted by a report of wire damage on a fuel boost pump power cable, and a separate report of a fuel tank explosion on a similarly equipped airplane. This AD requires the installation of new shielded wire bundles and convoluted liners within fuel tank conduits, and revision of the maintenance or inspection program, as applicable, to incorporate certain airworthiness limitations (AWLs). We are issuing this AD to address the unsafe condition on these products.
2012-14-06: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Corporation (RRC) 250-C20, -C20B, and -C20R/2 turboshaft engines. This AD was prompted by seven cases reported of released turbine blades and shrouds, which led to loss of power and engine in- flight shutdowns (IFSDs). This AD requires a one-time visual inspection and fluorescent penetrant inspection (FPI) on certain 3rd and 4th stage turbine wheels for cracks in the turbine blades. We are issuing this AD to prevent failure of 3rd or 4th stage turbine wheel blades which could cause engine failure and damage to the airplane.
2003-08-11: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 747-100, -200B, -200F, -200C, -100B, -300, -100B SUD, -400, -400D, and -400F series airplanes; and Model 747SR series airplanes. This action requires repetitive inspections to detect discrepancies of the actuator attach fittings of the inboard and outboard flaps, and follow-on and corrective actions as necessary. This action is necessary to detect and correct cracking and other damage of the actuator attach fittings of the trailing edge flaps, which could result in abnormal operation or retraction of a trailing edge flap, and possible loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
96-17-14: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 series airplanes, that currently requires repetitive visual inspections to detect cracks in the forward intermediate section skin at frame 30A where it joins stringer 30, and repair, if necessary. This amendment adds a requirement for eddy current inspection(s) to detect cracks of the outer skin of the fuselage; accomplishment of this inspection terminates the repetitive visual inspections. This amendment also requires repair of any cracked area and modification of the structure at certain frames. This amendment is prompted by in-service experience which has identified fatigue cracks in this area. The actions specified by this AD are intended to prevent fatigue cracking, which could result in rapid decompression of the airplane.
2018-04-11: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. Model AB139 and Model AW139 helicopters. This AD requires inspecting the thickness of the tail gearbox (TGB) central housing (housing). This AD was prompted by reports that the housing thickness does not conform to its type design. The actions of this AD are intended to detect and correct an unsafe condition on these products.
99-05-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that requires revising the maintenance program to require verification that a certain shipping container and shipping sleeve assembly were used in shipping the ram air turbine (RAT) deployment actuator. This amendment also requires inspection of the identification plate on the RAT deployment actuator to determine the actuator serial numbers or a records check to determine such information; and repair or replacement of certain RAT deployment actuators, if necessary. This amendment is prompted by reports of certain RAT actuators that failed to deploy upon command due to interference in the actuator locking mechanism caused by damage incurred during shipping of the actuators. Failure of the RAT to deploy, specifically during a dual engine failure, would result in loss of hydraulic power and would adversely affect the continued safe flight and landing of the airplane.
99-05-12: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-100, -200, -300, -400, and -500 series airplanes. This action requires removal of the float switch and wiring and inspection of the float switch wiring in the center fuel tank to detect discrepancies, and either reinstallation of existing float switch and wiring, or replacement of the float switch and wiring with a new float switch and wiring. This action also requires installation of Teflon sleeving over the wiring of the float switch. In lieu of the above mentioned requirements, this AD requires deactivation of the float switch, accomplishment of specific fueling procedures, and installation of Caution signs. This amendment is prompted by a report indicating that chafing of the direct current (DC) powered float switch wiring insulation in the center fuel tank has occurred on several airplanes. The actions specified in this AD are intended to detect and correct suchchafing and the resultant arcing from the wiring to the in-tank conduit, which could present an ignition source inside the fuel tank and consequent fire/explosion.
99-05-08: This amendment adopts a new airworthiness directive (AD) that is applicable to McDonnell Douglas Helicopter Systems (MDHS) Model MD-900 helicopters. This action requires establishing or reducing certain life limits, applying serial numbers (S/N's), determining hours time-in-service (TIS), and creating component history cards or equivalent records for various parts. This amendment is prompted by analysis that indicates a need for establishing or reducing life limits to avoid fatigue failure of certain parts. The actions specified by this AD are intended to apply appropriate life limits to various parts.
93-01-26: 93-01-26 DE HAVILLAND, INC.: Amendment 39-8480. Docket 92-NM-99-AD. Supersedes AD 91-19-04, Amendment 39-8031 which superseded AD 91-12-51, Amendment 39-7076. Applicability: Model DHC-8-300 series airplanes; serial numbers 202, 210, 216, 221, 224, 230, 232, 234, 236, 238, 240, 242, 244, 246, 248, 250, 252, 254, 256, 257, 259, 261, 262, 264, 266, 267, 269, 271, 272, 274, 276, 278, 279, 281, 283, 284, 286, 288, and 307; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the accumulation of fuel vapors in the dry bay area, presenting a potential risk of an in-flight explosion in the event of a lightning strike, accomplish the following: (a) For those airplanes listed in de Havilland Alert Service Bulletin S.B. A8-28-16, dated May 30, 1991, accomplish the following: (1) Within 24 hours after August 26, 1991 (the effective date of AD 91-12- 51, Amendment 39-7076), and thereafter at intervals not to exceed 300 hours time-in-service or 30 days, whichever occurs first, perform an external visual inspection of the wing dry bay drains for blockage in accordance with the service bulletin. If drain blockage is found, prior to further flight, repair in accordance with paragraph B.1. of the Accomplishment Instructions of the service bulletin. (2) Within 24 hours after August 26, 1991, and thereafter at daily intervals, perform an external visual inspection of the wing dry bay drains to detect evidence of fuel leaks in accordance with the service bulletin. (3) Within 7 days after August 26, 1991, unless accomplished within the previous 14 days; or prior to further flight if evidence of fuel leaks is detected at the wing dry bay drains as a result of the inspection required by paragraph (a)(2) of this AD; perform an internal visual inspection of the wing dry bay in accordance with the service bulletin. (i) If no leakage is found as a result of the inspection required by paragraph (a)(3) of this AD, repeat the internal visual inspection of the wing dry bay required by paragraph (a)(3) of this AD at intervals not to exceed 14 days. (ii) If the leakage is within the limits specified in the service bulletin, within 14 days, perform the local re-sealing repair procedure described in paragraph C.7. of the Accomplishment Instructions of the service bulletin. The airplane may be returned to service within this 14-day period, subject to the following conditions: (A) Perform the internal visual inspection of the wing dry bay required by paragraph (a)(3) of this AD at intervals not to exceed 7 days to ensure that the leakage remains within the specified limit; and (B) Prior to further flight, incorporate the following into the Limitations Section of the Airplane Flight Manual (AFM), which may be accomplished by including a copy of this airworthiness directive in the AFM: "Flight is prohibited in areas where lightning or thunderstorms are observed or reported within 5 nautical miles of the flight path, or when the existing weather conditions may reasonably be expected to result in a lightning strike." (iii) If leakage exceeds the limit specified in the service bulletin, prior to further flight, repair in accordance with paragraph C.7. of the Accomplishment Instructions of the service bulletin. (iv) Application of a fuel vapor barrier coating in accordance with paragraph D. of the Accomplishment Instructions of the service bulletin constitutes terminating action only for the repetitive internal visual inspections required by paragraph (a)(3)(i) of this AD. (b) For those airplanes listed in de Havilland Alert Service Bulletin S.B. A8-28-16, Revision 'B', dated June 24, 1991, that are not subject to paragraph (a) of this AD, accomplish the following: (1) Within 24 hours after September 26, 1991 (the effective date of AD 91- 19-04, Amendment 39-8031), and thereafter at intervals not to exceed 300hours time-in-service or 30 days, whichever occurs first, perform an external visual inspection of the wing dry bay drains for blockage in accordance with the service bulletin. If drain blockage is found, prior to further flight, repair in accordance with paragraph B.1. of the Accomplishment Instructions of the service bulletin. (2) Within 24 hours after September 26, 1991, and thereafter at daily intervals, perform an external visual inspection of the wing dry bay drains to detect evidence of fuel leaks in accordance with the service bulletin. (3) Within 7 days after September 26, 1991, unless accomplished within the previous 14 days; or prior to further flight if evidence of fuel leaks is detected at the wing dry bay drains as a result of the inspection required by paragraph (b)(2) of this AD; perform an internal visual inspection of the wing dry bay in accordance with the service bulletin. (i) If no leakage is found as a result of the inspection required by paragraph (b)(3) of this AD, repeat the internal visual inspection of the wing dry bay required by paragraph (b)(3) of this AD at intervals not to exceed 14 days. (ii) If the leakage is within the limits specified in the service bulletin, within 14 days, perform the local re-sealing repair procedure described in paragraph C.7. of the Accomplishment Instructions of the service bulletin. The airplane may be returned to service within this 14-day period, subject to the following conditions: (A) Perform the internal visual inspection of the wing dry bay required by paragraph (b)(3) of this AD at intervals not to exceed 7 days to ensure that the leakage remains within the specified limit; and (B) Prior to further flight, incorporate the following into the Limitations Section of the Airplane Flight Manual (AFM), which may be accomplished by including a copy of this airworthiness directive in the AFM: "Flight is prohibited in areas where lightning or thunderstorms are observed or reported within 5 nautical miles of the flight path, or when the existing weather conditions may reasonably be expected to result in a lightning strike." (iii) If leakage exceeds the limit specified in the service bulletin, prior to further flight, repair in accordance with paragraph C.7. of the Accomplishment Instructions of the service bulletin. (iv) Application of a fuel vapor barrier coating in accordance with paragraph D. of the Accomplishment Instructions of the service bulletin constitutes terminating action only for the repetitive internal visual inspections required by paragraph (b)(3)(i) of this AD. (c) For airplane serial numbers 279, 281, 283, 284, 286, 288, and 307, accomplish the following in accordance with de Havilland Alert Service Bulletin S.B. A8-28-16, Revision 'C', dated January 31, 1992: (1) Within 7 days after the effective date of this AD, and thereafter at intervals not to exceed 300 hours time-in-service or 30 days, whichever occurs first, perform an external visual inspection of the wing dry bay drains for blockage in accordance with the service bulletin. If drain blockage is found, prior to further flight, repair in accordance with paragraph B.1. of the Accomplishment Instructions of the service bulletin. (2) Within 7 days after the effective date of this AD, and thereafter at daily intervals, perform an external visual inspection of the wing dry bay drains to detect evidence of fuel leaks in accordance with the service bulletin. (3) Within 7 days after the effective date of this AD, unless accomplished within the previous 14 days; or prior to further flight if evidence of fuel leaks is detected at the wing dry bay drains as a result of the inspection required by paragraph (c)(2) of this AD; perform an internal visual inspection of the wing dry bay in accordance with the service bulletin. (i) If no leakage is found as a result of the inspection required by paragraph (c)(3) of this AD, repeat the internal visual inspection of the wing dry bay required by paragraph (c)(3) of this AD at intervals not to exceed 14 days. (ii) If the leakage is within the limits specified in the service bulletin, within 14 days, perform the local re-sealing repair procedure described in paragraph C.7. of the Accomplishment Instructions of the service bulletin. The airplane may be returned to service within this 14-day period, subject to the following conditions: (A) Perform the internal visual inspection of the wing dry bay required by paragraph (c)(3) of this AD at intervals not to exceed 7 days to ensure that the leakage remains within the specified limit; and (B) Prior to further flight, incorporate the following into the Limitations Section of the Airplane Flight Manual (AFM), which may be accomplished by including a copy of this airworthiness directive in the AFM: "Flight is prohibited in areas where lightning or thunderstorms are observed or reported within 5 nautical miles of the flight path, or when the existing weather conditions may reasonably be expected to result in a lightning strike." (iii) If leakage exceeds the limit specified in the service bulletin, prior to further flight, repair in accordance with paragraph C.7. of the Accomplishment Instructions of the service bulletin. (iv) Application of a fuel vapor barrier coating in accordance with paragraph D. of the Accomplishment Instructions of the service bulletin constitutes terminating action only for the repetitive internal visual inspections required by paragraph (c)(3)(i) of this AD. (d) Within 6 months after the effective date of this AD, accomplish Modification No. 8/1776 in accordance with de Havilland Service Bulletin S.B. 8-57-20, Revision A, dated January 31, 1992. Accomplishment of this modification constitutes terminating action for the requirements of this AD. (e) 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, New York Aircraft Certification Office (ACO), ANE-170, FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (f) 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. (g) Certain inspections, repairs, and modification shall be done in accordance with de Havilland Alert Service Bulletin S.B. A8-28-16, dated May 30, 1991; de Havilland Alert Service Bulletin S.B. A8-28-16, Revision 'C', dated January 31, 1992; and de Havilland Service Bulletin S.B. 8-57-20, Revision 'A', dated January 31, 1992; as indicated. 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. Certain other inspections, repairs, and modifications shall be done in accordance with de Havilland Alert Service Bulletin S.B. A8-28-16, Revision 'B', dated June 24, 1991. Incorporation by reference of de Havilland Alert Service Bulletin S.B. A8-28-16, Revision 'B', dated June 24, 1991, was approved previously by the Director of the Federal Register as of September 26, 1991 (56 FR 46228, September 11, 1991). Copies may be obtained from de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington,DC. (h) This amendment becomes effective on March 10, 1993.