Results
96-12-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 series airplanes, that requires measurements of the thickness of the inner skin of the longitudinal lap joint from the inside of the fuselage at certain stringers. This amendment also requires inspections to detect stress corrosion cracking in the subject area, and repair, if necessary. This amendment is prompted by reports of stress corrosion cracking found in the skin at the longitudinal lap joint at certain stringers of the fuselage, which was caused by the increased stress level in the subject area when it was reworked beyond certain limits. The actions specified by this AD are intended to prevent such stress corrosion cracking which, if not detected and corrected in a timely manner, could result in rapid depressurization of the airplane.
2004-22-03: The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model EMB-135 and -145 series airplanes. This AD requires measuring the fillet radius dimension of the trunnion fitting webs of the wings; and reworking the fillet radius of the trunnion fitting web in order to increase the radius, doing related investigative actions, and doing applicable corrective action, if necessary. This AD is prompted by a report indicating that trunnion fittings of the wings have been manufactured with a web fillet radius smaller than the minimum required by the design data, which may induce the occurrence of fatigue cracks at the root of the trunnion fillet radius and adjacent structures (e.g., spar and ribs). We are issuing this AD to detect and correct fatigue cracking of the wing trunnion fittings or adjacent structure, which could result in failure of the main landing gear, consequent damage to surrounding structure, and possible loss of control of the airplane during landing.
99-27-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 series airplanes. This action requires repetitive inspections of the connections between certain ribs and stringers of the wing skins to detect loose or missing rivets or gaps, and corrective actions, if necessary. This action also requires eventual modification of the rib-stringer connection, which terminates the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent fatigue cracking in the skin and stringers, which could result in reduced structural integrity of the wings.
2022-20-04: The FAA is superseding airworthiness directive (AD) 2021-26- 08, which applied to certain Bell Textron Canada Limited Model 206, 206A, 206A-1, 206B, 206B-1, 206L, 206L-1, 206L-3, and 206L-4 helicopters. AD 2021-26-08 required removing certain nuts from service; installing newly designed nuts; applying a specific torque, and a torque stripe to each newly installed nut; after the installation of each newly designed nut, inspecting the torque; and depending on the inspection results, either applying a torque stripe, or performing further inspections and removing certain parts from service. AD 2021- 26-08 also prohibited installing any affected nut on any tail rotor drive shaft (TRDS) disc pack (Thomas) coupling. Since the FAA issued AD 2021-26-08, the FAA determined certain torque values and part numbers (P/Ns) need to be revised. This AD was prompted by reports of cracked or missing nuts installed on the TRDS Thomas couplings and the need to revise certain torque values and P/Ns in AD 2021-26-08. This AD requires removing certain nuts from service; installing newly designed nuts; applying torque and a torque stripe; and additional corrective actions if necessary. This AD also prohibits installing any affected nut on any TRDS Thomas coupling, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
95-25-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Beech Model 400, 400A, and 400T (military T-1A) airplanes, that requires modification of the standby instrument lighting system. This amendment is prompted by a report that, due to the design of the standby instrument lighting system, the lighting for the standby instruments dimmed to an unacceptable level when the main electrical power was turned off. The actions specified by this AD are intended to ensure that the standby instrument lighting system adequately illuminates the standby instrument, if normal electrical power is lost or is turned off as a result of fire or smoke in the cockpit.
99-27-02: This amendment adopts a new airworthiness directive (AD) that applies to all Cessna Aircraft Company (Cessna) 170, 172, 175, and 177 series airplanes. This AD requires replacing certain fuel selector valve cams or fuel selector valves that Cessna shipped from December 6, 1998, through May 10, 1999, and prevents the future installation of these fuel selector valve cams or fuel selector valves. This AD allows the pilot to check the logbooks to determine whether one of these fuel selector valve cams or fuel selector valves is installed. This AD results from reports from Cessna that fuel selector valve cams and fuel selector valves were manufactured with control shafts that will not allow both tanks to supply fuel to the engine in certain situations. The actions specified by this AD are intended to prevent an inadequate supply of fuel from reaching the engine because of a fuel selector valve cam or fuel selector valve. This could result in an emergency landing or loss of control of the airplane.
90-17-11: 90-17-11 BRITISH AEROSPACE: Amendment 39-6699. Docket No. 90-NM-78-AD. Applicability: Model HS. 125-700A and BAe 125-800A series airplanes, as listed in British Aerospace Service Bulletin 24-263-9486A, Revision 1, dated January 27, 1988, certificated in any category. Compliance: Required within 30 days after the effective date of this AD, unless previously accomplished. To ensure crewmembers will pull the correct circuit breakers to electrical/electronic equipment that may be the source of fire or smoke in the cockpit, accomplish the following. A. Install circuit breaker identification labels in panel DA-A, in accordance with British Aerospace Service Bulletin 24-263-9486A, Revision 1, dated January 27, 1988. 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM- 113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. 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 British Aerospace PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue, S.W., Renton, Washington. This amendment (39-6699, AD 90-17-11) becomes effective on September 17, 1990.
2022-22-08: The FAA is adopting a new airworthiness directive (AD) for Bell Textron Canada Limited (type certificate previously held by Bell Helicopter Textron Canada Limited) Model 206L, 206L-1, 206L-3, and 206L-4 helicopters with a certain part-numbered main rotor (M/R) blade installed under Supplemental Type Certificate (STC) SR02684LA. This AD was prompted by delamination of M/R blades. This AD requires a repetitive inspection for delamination, and depending on the results, removing the M/R blade from service and reporting certain information. The FAA is issuing this AD to address the unsafe condition on these products.
96-12-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires replacement of the flexible cables of the power and condition controls of the engines with new flexible cables. This amendment also requires installation of protective tape on the outside case of these flexible cables, and reidentification of the cables. This amendment is prompted by reports of stiff operation of the power and condition controls of the engines due to heat damage to and moisture contamination of the flexible cable. The actions specified by this AD are intended to prevent heat damage and moisture contamination to the flexible cable, which could result in stiff operation of the power and condition controls and subsequent reduced engine control.
99-25-11: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAe 146 series airplanes and certain British Aerospace Model Avro 146-RJ series airplanes, that requires repetitive eddy current inspections to detect fatigue cracking along the face of the retraction attachment boss in the nose landing gear sidewall; and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil aviation authority. The actions specified by this AD are intended to detect and correct fatigue cracking along the face of the retraction attachment boss in the nose landing gear sidewall, which could result in premature extension of the nose landing gear or depressurization of the airplane.
2004-22-12: This amendment adopts a new airworthiness directive (AD) for MD Helicopters, Inc. Model 600N helicopters that requires replacing the fuselage Station 75 control support bracket assembly (control support bracket), reducing the life limit, and revising the Limitations section of the applicable maintenance manual to state the reduced life limits on certain serial-numbered helicopters. This amendment is prompted by information received from the manufacturer indicating that the fatigue life of the control support bracket is shorter than the original analysis indicated. The actions specified by this AD are intended to prevent failure of the control support bracket and subsequent loss of control of the helicopter.
2022-21-51: The FAA is adopting a new airworthiness directive (AD) for all Viking Air Limited (type certificate previously held by Bombardier Inc. and de Havilland, Inc.) Model DHC-3 airplanes. This AD was prompted by multiple recent reports of cracks in the left-hand elevator auxiliary spar. This AD requires repetitive detailed visual inspections of the entire left-hand elevator auxiliary spar for cracks, corrosion, and previous repairs, and depending on the findings, replacement of the left-hand elevator auxiliary spar. This AD also requires sending the inspection results to the FAA. The FAA previously sent an emergency AD to all known U.S. owners and operators of these airplanes and is now issuing this AD to address the unsafe condition on these products.
91-13-08: 91-13-08 ISRAEL AIRCRAFT INDUSTRIES (IAI): Amendment 39-7039. Docket No. 91-NM-32- AD. Applicability: Models 1121, 1121A, 1121B, 1123, 1124, and 1124A series airplanes, certificated in any category. Compliance: Required within 60 days after the effective date of this AD, unless previously accomplished. To prevent the inability to extend the nose landing gear for landing, accomplish the following: A. Remove the existing towing instruction placard and install a new placard in accordance with the applicable service bulletin, as follows: Airplane Models Service Bulletin 1121, 1121A, 1121B 1121-11-015, dated November 26, 1990 1123 1123-11-031, dated November 26, 1990 1124 and 1124A 1124-11-103, dated November 26, 1990 B. 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. 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 Astra Jet Corporation, Technical Publications, 77 McCullough Drive, Suite 11, New Castle, Delaware 19720. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-7039, AD 91-13-08) becomes effective on July 22, 1991.
72-14-01: 72-14-01 DOWTY ROTOL, LTD: Amdt. 39-1473. Applies to Dowty Rotol Propeller Types (c)R130/4-20-4/12E, (c)R186/4-30-4/16, (c)R187/4-30-4/18, (c)R193/4-30-4/50, (c)R184/4-30-4/50, (c)R259/4-40-4.5/17, (c)R148/4-20-4/21E, (c)R175/4-30-4/13E, (c)R179/4- 20-4/33, (c)R257/4-30-4/60, (c)R245/4-40-4.5/13, and (c)R209/4-40-4.5/2. These propellers are installed on, but not necessarily limited to, BAC Viscount Models 744, 745D, and 810; Armstrong Whitworth Model Argosy AW.650 Series 101; Fairchild and Fokker Models F27 and F227; Handley Page Model Herald; and Grumman Model Gulfstream G-159 airplanes. Compliance is required as indicated unless already accomplished. To prevent failure of a propeller blade due to the disengagement of the blade bearing retaining bolts resulting from excessive wear on the teeth of the locking segments, accomplish the following: Within the next 5,000 hours' time in service or at the next propeller overhaul, after the effective date of this AD, whichever occurs sooner, incorporate Dowty Rotol Modification No. (c) VP.2676 (Rev. 1) in accordance with Dowty Rotol Limited Service Bulletin No. 61-714, Revision 3, dated July 26, 1971, or an FAA-approved equivalent. This amendment becomes effective 22 July, 1972.
91-16-01: 91-16-01 MITSUBISHI HEAVY INDUSTRIES (MHI), LTD. [formerly Nihon Aeroplane Manufacturing Company (NMAC)]: Amendment 39-7091. Docket No. 91-NM-118-AD. Supersedes AD 91-06-04. Applicability: Model YS-11, YS-11A-200, YS-11A-300, YS-11A-500, and YS-11A-600 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent uncontrolled nose down pitch of the airplane on landing approach during icing conditions, accomplish the following: (a) Within 30 days after March 19, 1991 (the effective date of Amendment 39-6922, AD 91- 06-04), accomplish the following: (1) Revise the Operating Limitations Section of the FAA-approved Airplane Flight Manual (AFM) for the Model YS-11/-11A by adding a subparagraph B. to paragraph 1.10.5, WING DE- ICER SYSTEM, to read as follows: This may be accomplished by inserting a copy of this AD in the AFM. "B. Do not extend flaps greater than 20 degrees in the presence of known icing conditions or in visible moisture below plus 5 degrees centigrade (plus 41 degrees Fahrenheit) outside air temperature (OAT)." (2) Add a placard as near as possible to the flap handle to read as follows: "Flaps limited to 20 degrees in known icing conditions." (b) Within 30 days after the effective date of this amendment, accomplish the following: (1) Insert the following MHI Transmittal Letters in the Normal Operating Procedures Section of the AFM, as applicable: (i) For Model YS-11 airplanes: NMAC YS-11 Flight Manual Publication No. YS-FM-001, Transmittal Letter E32, dated October 2, 1990; (ii) For Model YS-11A-200 and -300 series airplanes: NMAC YS-11A- 200/300 Flight Manual Publication No. YS-FM-002, Transmittal Letter No. E2027, dated October 2, 1990; (iii) For Model YS-11A-500 series airplanes: NMAC YS-11A-500 Flight Manual Publication No. YS-FM-005, Transmittal Letter No. E5021, dated October 2, 1990; (iv) For ModelYS-11A-600 series airplanes: NMAC YS-11A-600 Flight Manual Publication No. YS-FM-006, Transmittal Letter No. E6021, dated October 2, 1990. (2) In the Normal Operating Procedures Section of the AFM, just after the MHI Transmittal Letter required by paragraph (b)(1) of this AD, revise subparagraph "(2) Flaps" of paragraph 3.1.10.1, APPROACH AND LANDING IN ICING CONDITIONS OR IN VISIBLE MOISTURE BELOW plus 5 DEGREES C (plus 41 DEGREES F) OAT, to read as follows: This may be accomplished by inserting a copy of this AD in the AFM. "(2) Flaps.............................................Set Position NOTE: Do not extend flaps greater than 20 degrees. CAUTION: IF UNUSUAL PITCHING OR YOKE MOVEMENT OCCURS WHILE EXTENDING THE FLAPS, IMMEDIATELY RETRACT THE FLAPS UNTIL THE PITCHING OR YOKE MOVEMENT STOPS." (c) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office (ACO), 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, Los Angeles ACO. NOTE: Previous FAA approval granted for an alternative method of compliance with AD 91-06- 04 constitutes FAA approval as an alternative method of compliance with this AD. (d) 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. (e) The AFM revision requirements shall be accomplished, in part, by incorporating the following documents into the AFM: NMAC YS-11 Flight Manual Publication No. YS-FM-001, Transmittal Letter E32; NMAC YS-11A-200/300 Flight Manual Publication No. YS-FM-002, Transmittal Letter No. E2027; NMAC YS-11A-500 Flight Manual Publication No. YS-FM-005, Transmittal Letter No. E5021; NMAC YS-11A-600 Flight Manual Publication No. YS-FM-006, Transmittal Letter No. E6021; all of which are dated October 2, 1990. These documents contain the following list of effective pages: Publication Number/ Transmittal Letter Number Section Code Symbol Page Number Publication No. YS-FM-001 Transmittal Letter E32, dated October 2, 1990 Transmittal Sheet L.E.P. Log of Revision (1) 3 T/L E32 (none) (none) (none) (none) (none) 1/1 i ii-10 i 25 25a Publication No. YS-FM-002 Transmittal Letter E2027 dated October 2, 1990 Transmittal Sheet L.E.P. Log of Revision (1) 3 T/L E2027 E101 E101 E100 E100 E100 1/1 i ii-8 i 21 22 Publication No. YS-FM-005 Transmittal Letter E5021 dated October 2, 1990 Transmittal Sheet L.E.P. Log of Revision (1) 3 T/L E5021 E500 E156 E100 E100 E100 1/1 i ii-5 i 21 22 Publication No. YS-FM-006 Transmittal Letter E6021 dated October 2, 1990 Transmittal Sheet L.E.P. Log of Revision (1) 3 T/LE6021 E600 E156 E100 E100 E100 1/1 i ii-5 i 21 22 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 Nagoya Aircraft Works, Mitsubishi Heavy Industries, Ltd., 10 Oye-cho, Minato-Ku, Nagoya 455, Japan, Attention: Manager, YS-11 Group, Service Department. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. Airworthiness Directive 91-16-01 supersedes AD 91-06-04, Amendment 39-6922. This amendment (39-7091, AD 91-16-01) becomes effective on August 22, 1991.
2022-21-16: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace LP Model Gulfstream G150 airplanes. This AD was prompted by reports that wing flap fairing debonding and corrosion were discovered at certain areas of the lower skin on both wings. This AD requires an inspection for corrosion in certain areas of the wing skin fairings, additional inspections if necessary, resealing the fairings with new fillet seal, and applicable corrective actions, as specified in a Civil Aviation Authority of Israel (CAAI) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2004-22-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400, -400D, and -400F series airplanes, equipped with GE or P&W series engines. This amendment requires modifications and functional tests of the wiring of the wire integration unit and the air supply control test unit (ASCTU) of the engine bleed air distribution system. The actions specified by this AD are intended to prevent inadvertent commanded shutdown of the engine bleed air distribution systems due to an erroneous ASCTU command. This type of shutdown could cause depressurization of the airplane and subsequent ice build-up on the engine inlets during descent, which could result in ingestion of ice into the engine(s) and consequent loss of thrust on one or more engines. This action is intended to address the identified unsafe condition.
72-19-02: 72-19-02 PITTS AVIATION ENTERPRISES, INC: Amdt. 39-1518. Applies to the Pitts Model S-2A Series Airplanes, S/N 2001 through 2025. Compliance required within the next 10 hours time in service after the effective date of this AD, unless already accomplished. To prevent structural damage because of excessive in-flight vibration of the aileron interconnect tubes, accomplish the following: (a) Remove streamline aileron interconnect tubes, P/N 2-5216-1. NOTE: Make certain the length between the AN3 bolt centers for the upper and lower aileron attachments of the interconnect tube are not changed during removal. (b) Install round aileron interconnect tubes, P/N 2-5216-11. When installing the replacement tubes, make certain to adjust the length of the lower threaded end to the same overall length between AN3 bolt centers as the tubes originally installed on your airplane. Make certain that the correct number of AN960-10 (1/16 or 1/32 inch thick) washers are installed so that the bearing inner races are clamped-up snugly without bending the fork ends of the tubes. Pitts Service Bulletin No. 5, including Supplement No. 1, pertains to this same subject. This amendment becomes effective September 15, 1972.
2004-22-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 and -300 series airplanes, that requires inspection of the metal oxide varistor (MOV) modules and transient absorption zener (TAZ) diodes to determine if those parts are outside of tolerance limits, and replacement of MOV modules and TAZ diodes with new parts, if necessary. This action is necessary to prevent the failure of critical ice protection systems following a lightning strike, which could result in reduced controllability and degraded performance of the airplane in the event of an encounter with icing conditions. This action is intended to address the identified unsafe condition.
2022-22-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by a report that the path for the grounding wire of the engine fire shut off valve (FSOV) is routed through the wing trailing edge, which is not the shortest path available. This AD requires modifying the wiring between the inboard fixed leading edge in the wing and in the forward cargo compartment on the left- and right-hand sides, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2013-15-04: We are adopting a new airworthiness directive (AD) for certain Hartzell Propeller, Inc. propeller models HC-(1,D)2(X,V,MV)20-7, HC- (1,D)2(X,V,MV)20-8, and HC-(1,D)3(X,V,MV)20-8. This AD was prompted by failures of the propeller hydraulic bladder diaphragm and resulting engine oil leak. This AD requires replacement of the propeller hydraulic bladder diaphragm. We are issuing this AD to prevent propeller hydraulic bladder diaphragm rupture, loss of engine oil, damage to the engine, and loss of the airplane.
97-02-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model BAe ATP airplanes, that requires repetitive inspections to detect damage of the antenna mounting reinforcing plates and surrounding fuselage skin. If any damage is detected, the AD requires replacement of the reinforcing plate with a new reinforcing plate and/or repair of the surrounding fuselage skin, which would terminate the repetitive inspection requirements. This amendment is prompted by reports of corrosion found at the antenna reinforcing plates, which was caused by the ingress of water at the plates. The actions specified by this AD are intended to prevent such corrosion, which could result in reduced structural integrity of the fuselage pressure vessel.
99-26-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires repetitive general visual inspections of the power feeder cables, terminal strip, fuseholder, and fuses of the galley load control unit (GLCU) within the No. 3 bay electrical power center to detect damage; and corrective actions, if necessary. This amendment is prompted by an incident of no power to the aft galleys and two incidents of sparking sounds coming from the G3 galley due to damage of the No. 3 and 4 wire assembly terminal lugs and overheating of the power feeder cables on the G3 GLCU. The actions specified in this AD are intended to prevent such damage due to the accumulated effects over time from overheating of the power feeder cables on the G3 GLCU, which could result in smoke and fire in the G3 galley.
2004-22-05: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 737-300, -400, and -500 series airplanes. This AD requires inspecting for discrepancies of the fuselage skin under the dorsal fin assembly, and repairing if necessary. This AD is prompted by a report of an 18-inch crack found in the fuselage skin area under the blade seals of the nose cap of the dorsal fin due to previous wear damage. We are issuing this AD to find and fix discrepancies of the fuselage skin, which could result in fatigue cracking due to cabin pressurization, and consequent rapid in-flight decompression of the airplane fuselage.
92-15-12: 92-15-12 AEROSPATIALE: Amendment 39-8306. Docket No. 92-NM-31-AD. Applicability: Model ATR42-300 and -320 series airplanes on which Modification 1694 (Aerospatiale Service Bulletin ATR42-32-0021) has been accomplished and on which Modification 2063 (Aerospatiale Service Bulletin ATR42-32-0028) has not been accomplished, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent a gear-up landing, accomplish the following: (a) Within 6 months after the effective date of this AD, modify the nose landing gear (NLG) retraction control logic, and perform a functional test of the landing gear retraction manual override control, in accordance with Aerospatiale Service Bulletin ATR42-32-0028, Revision 3, dated February 12, 1991. (b) 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, Standardization Branch, ANM-113, FAA, Transport 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, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (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) The modification and functional test shall be done in accordance with Aerospatiale Service Bulletin ATR42-32-0028, Revision 3, dated February 12, 1991, which includes the following list of effective pages: Page Number Revision Level Date 1-2, 11, 13-21 3 February 12, 1991 3-10, 12 1 February 23, 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (e) This amendment becomes effective on September 8, 1992.