Results
2001-08-14 R1: The FAA is revising an existing airworthiness directive (AD) for Turbomeca S.A. Arrius Models 2B, 2B1, and 2F turboshaft engines. That AD currently requires replacing the right injector half manifold, left injector half manifold, and privilege injector pipe. This AD requires the same actions, but relaxes the compliance time for the repetitive replacements on Arrius 2F engines. This AD results from Turbomeca relaxing the repetitive replacement interval for Arrius 2F engine fuel nozzles based on review of returned fuel nozzles to Turbomeca. We are issuing this AD to prevent engine flameout during rapid deceleration, or the inability to maintain the 2.5 minutes one engine inoperative (OEI) rating, and to prevent air path cracks due to blockage of the fuel injection manifolds.
99-07-06: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767 series airplanes. This action requires repetitive inspections to detect cracking or damage of the forward and aft lugs of the diagonal brace of the nacelle strut, and follow-on actions, if necessary. This action also provides optional terminating action for the repetitive inspections. This amendment is prompted by a report that a fractured diagonal brace lug was found during a routine maintenance inspection. The actions specified in this AD are intended to detect and correct cracking of the diagonal brace of the nacelle strut, which could result in failure of the diagonal brace, and consequent fatigue failure of a strut secondary load path and separation of the engine and strut.
99-04-15: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-04-15 that was sent previously to all known U.S. owners and operators of Porsche PFM3200N01, N02, and N03 reciprocating engines by individual letters. This AD requires replacement of valve springs prior to further flight on PFM3200N01, N02, and N03 engines. This amendment is prompted by reports of six cases of undetected fatigue failures of valve springs, with one valve spring failure causing an in-flight engine failure that ended in an emergency landing. The actions specified by this AD are intended to prevent an in-flight engine shutdown due to undetected fatigue failures of valve springs.
88-12-06: 88-12-06 BOEING: Amendment 39-5936. Applies to Model 767 series airplanes, listed in Boeing Service Bulletin 767-53-0025, dated June 4, 1987, certificated in any category. \n\n\tCompliance required within 12 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent structural failure of the vertical fin in the event of a failure of the aft pressure bulkhead, accomplish the following: \n\n\tA.\tInstall seal plates over the electrical wiring and hydraulic tubing cutouts on the fin-to-body skin in accordance with Boeing Service Bulletin 767-53-0025, dated June 4, 1987. \n\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, FAA, Northwest Mountain Region.\n \n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Seattle Aircraft Certification Office. \n\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\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment, 39-5936, becomes effective July 1, 1988.
2006-02-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A330-200 and -300 series airplanes, Model A340-200 and - 300 series airplanes, and Model A340-541 and A340-642 airplanes. This AD requires revising the airplane flight manual by incorporating new procedures to follow in the event of a fuel leak. This AD results from a determination that, once a fuel leak is detected, fuel management procedures are a critical factor in limiting the consequences of the leak. We are issuing this AD to ensure that the flightcrew, in the event of a fuel leak, is advised of appropriate procedures to follow, such as isolating the fuel tanks, stopping any fuel transfers, and landing as soon as possible. Failure to follow these procedures could result in excessive fuel loss that could cause the engines to shut down during flight.
2019-03-20: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a determination that new and more restrictive maintenance requirements and airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new and more restrictive maintenance requirements and airworthiness limitations for airplane structures and systems. We are issuing this AD to address the unsafe condition on these products.
2002-26-05: This amendment supersedes Airworthiness Directive (AD) 2002-11-03, which applies to certain Air Tractor, Inc. (Air Tractor) Models AT-502, AT-502A, AT-502B, and AT-503A airplanes. AD 2002-11-03 lowered the safe life for the wing lower spar cap and further reduced the safe life for airplanes that incorporate or have incorporated Marburger Enterprises, Inc. winglets. AD 2002-11-03 also currently requires you to eddy-current inspect the wing lower spar cap immediately prior to the replacement/modification to detect and correct any crack in a bolthole before it extends to the modified center section of the wing and report the results of this inspection to the Federal Aviation Administration (FAA). Field inspections on the affected airplanes have revealed wings with cracks below the currently established safe life. This AD would further reduce the safe life of the Models AT502, AT-502B, and AT-503A airplanes and would add airplanes recently manufactured to the Applicability of theAD. The actions specified by this AD are intended to prevent fatigue cracks from occurring in the wing lower spar cap before the established safe life is reached. Fatigue cracks in the wing lower spar cap, if not detected and corrected, could result in the wing separating from the airplane during flight.
99-07-07: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France (Eurocopter) Model SA 330J helicopters. This action requires the visual inspection and, if any crack is found, replacement of the affected main rotor head sleeve. This amendment is prompted by the discovery of a crack through the thickness of a lower lug of a blade sleeve. The actions specified by the proposed AD are intended to prevent failure of a main rotor head sleeve that could result in the loss of a main rotor blade and subsequent loss of control of the helicopter.
2009-18-04: We are adopting a new airworthiness directive (AD) for certain Air Tractor, Inc. Models AT-802 and AT-802A airplanes. This AD requires installing a rudder-aileron interconnect cable system shield kit and securing any items stowed in the baggage compartment, using tie downs and/or a cargo net until the cable shield kit is installed. We are issuing this AD to prevent jamming of the rudder-aileron interconnect cables by unsecured items in the baggage compartment, which could result in failure of the rudder-aileron interconnect cable system. This failure could lead to loss of control.
2006-01-07: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747-400F, 747SR, and 747SP series airplanes, without a stretched upper deck or stretched upper deck modification. This AD requires detailed and high-frequency eddy current inspections for cracks of each affected tension tie and of the surrounding structure, and related investigative and corrective actions if necessary. This AD results from a report of a crack in the tension tie at the body station 820 frame connection, and cracks found on the Boeing 747SR fatigue-test airplane in both the tension ties and frames at the tension tie to frame connections at body stations 800, 820, and 840. We are issuing this AD to find and fix cracks in the tension ties, which could lead to cracks in the skin and body frame and result in rapid in-flight depressurization of the airplane.
99-07-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive inspections to detect cracks in the edge frame web and doubler of the number 1 main entry door cutout; and repair, if necessary. This AD also provides for optional terminating action for the repetitive inspections. This amendment is prompted by reports indicating that fatigue cracks were found in the edge frame web and doubler at the door stop number 1 of the number 1 main entry door cutout. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in rapid decompression of the airplane.
63-21-05: 63-21-05 NAVION and TWIN NAVION: Amdt. 624 Part 507 Federal Register October 2, 1963. Applies to All Navion Serial Numbers NAV-4-2 and up, and all Twin Navion Aircraft, Temco D-16, Temco D-16A, Dauby, Riley, and Camair 480. Compliance required within the next 50 hours' time in service after the effective date of this directive. Service experience indicates that the unsafe condition in the main and nose gear retraction links which prompted the issuance of AD's 61-12-04 and 62-14-04 cannot in all cases be detected by the inspection as required in those AD's. Therefore, the following must be accomplished: (a) Replace the main gear retraction links with revised assembly Navion P/N 143- 33165-20, Temco P/N 57001-9 or FAA approved equivalent having the longer lap welded center section that completely covers the turned down part of the end fitting. (b) Replace the nose gear retraction link with revised assembly Navion P/N 145- 34106-20, Camair P/N 1-6031 or FAA approved equivalent having the longer lap welded center section that completely covers the turned down part of the end fitting. (c) Approval of equivalent parts shall be obtained from an FAA Regional Engineering and Manufacturing Branch or Aircraft Engineering Division, as appropriate. This supersedes AD's 61-12-04 and 62-14-04. This directive effective November 1, 1963. Revised August 25, 1965.
83-09-02: 83-09-02 MITSUBISHI HEAVY INDUSTRIES, LTD: Amendment 39-4647. Applies to Models MU-2B-25 and -26 (serial numbers 239 through 328; except serial numbers 313, 321, and airplanes having a serial number with the suffix "SA") and Models MU-2B-30, -35, and -36 (serial numbers 501, 504, and 548 through 673; except serial numbers 652, 661 and airplanes having a serial number with the suffix "SA") airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent fuel or fuel vapors from entering the wing tip strobe light assemblies, accomplish the following: (a) Within the next 100 hours time-in-service after the effective date of this AD and thereafter at intervals not to exceed 100 hours time-in-service from the last inspection, inspect the strobe light conduit tubes in the wing tip fuel tanks as detailed in MU-2 Service Bulletin No. 174C dated October 2, 1981 (hereafter referred to as the SB), Item 1 - Inspection for Leakage. Ifleaks are found, prior to further flight, modify the tip tank conduit tube in accordance with Item 2 - Rework Procedure of the SB. (b) On or before September 1, 1983, modify the tip tank conduit tubes in accordance with Item 2 - Rework Procedure of the SB. (c) When Item 2 - Rework Procedure of the SB is accomplished, the repetitive inspection required by paragraph (a) is no longer required. (d) The intervals between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane. (e) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (f) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Field Office, ANM-170H, Federal Aviation Administration, P.O. Box 50246, Honolulu, Hawaii 96850. This AD supersedes AD 77-13-12, Amendment 39-2937. This amendment becomes effective on May 17, 1983.
2006-01-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2006-01-51 that was sent previously by individual notices to all known U.S. owners and operators of Frakes Aviation (Gulfstream American) Model G-73 (Mallard) series airplanes and Model G-73 airplanes that have been converted to have turbine engines. This AD requires an inspection to detect repairs, cracking, or corrosion of the wings from wing station (WS) 77L to WS 77R, front spar to rear (main) spar; removal of repairs, if found; removal of sealant from the interior of the wet bays; and repair of any crack or corrosion. This AD results from a report indicating that the right wing of a Frakes Aviation (Gulfstream American) Model G-73 (Mallard) airplane separated from the fuselage on takeoff, which resulted in the airplane impacting the water near Miami Beach, Florida. We are issuing this AD to prevent structural failure of the wing and loss of control of the airplane.
2019-18-05: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Model DHC-8-400 series airplanes. This AD was prompted by reports of the nose landing gear (NLG) locking in a partially extended position due to loose bushings on the lock link of the NLG locking mechanism. This AD requires repetitive inspections of the bushings and the lower lock link of the NLG for discrepancies, and corrective actions if necessary. This AD also requires replacement of the lower lock link of the NLG, which terminates the repetitive inspections. The FAA is issuing this AD to address the unsafe condition on these products.
99-02-15: This action confirms the effective date of Airworthiness Directive (AD) 99-02-15, which applies to certain Avions Pierre Robin Model R2160 airplanes. AD 99-02-15 requires repetitively inspecting the engine bearer for cracks, and replacing the engine bearer with a reinforced part either immediately or at a certain time period depending on whether cracks are found during the inspections. Replacing the engine bearer with a reinforced part terminates the repetitive inspection requirement. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified in this AD are intended to detect and correct cracks in the engine bearer, which could result in the engine separating from the airplane.
79-18-09: 79-18-09 LOCKHEED CALIFORNIA: Amendment 39-3536. Applies to Lockheed L- 1011-385 series airplanes certificated in all categories. Compliance required within the next 400 hours' time in service from the effective date of this AD, unless already accomplished. To prevent local structural damage and insure security of the No. 2 engine generator feeder cables, accomplish the following: (a) Inspect the No. 2 engine generator feeder cables in the aft body area between Fuselage Station 2011 and Fuselage Station 2053 above Waterline 350 for looseness and slack, surface abrasions, discoloration of outer surface and close proximity to structure without clamps or other protective supports. Inspect feeder cable support clamps for lack of clamp cushions and bent or dislodged mount brackets or clamps. These inspections are to be made in accordance with Part 2 of Lockheed Service Bulletin 093-24-086, dated August 2, 1979. (b) If any of the above discrepant conditions is found toexist, prior to further flight perform corrective action in accordance with Part 2 of Lockheed Service Bulletin 093-24-086, dated August 2, 1979. (c) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD. This amendment becomes effective August 29, 1979.
2006-01-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus airplanes, listed above. This AD requires installing two-stage relays in the electronics rack (90VU), and performing related corrective and investigative actions. This AD results from reports of inadvertent rudder trim activation when the autopilot is on. We are issuing this AD to prevent inadvertent trim activation when the autopilot is on and the slats are extended, which could result in rudder activation when the autopilot is turned off.
2019-18-07: The FAA is superseding Airworthiness Directive (AD) 2015-17- 14, which applied to all Airbus SAS Model A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes, and Model A321- 111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2015- 17-14 required repetitive rototest inspections of the open tack holes and rivet holes at the cargo floor support fittings of the fuselage, including doing all applicable related investigative actions, and repair if necessary. This AD continues to require the actions of AD 2015-17-14, adds actions for certain airplanes, and reduces the compliance times for certain airplanes, as specified in an European Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also reduces the applicability. This AD was prompted by further analysis and widespread fatigue damage (WFD) evaluations which identified the need to reduce the initial compliance times and repetitive intervals for the inspections for certain airplanes, and to add work for certain airplanes. The FAA is issuing this AD to address the unsafe condition on these products.
99-06-13: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires inspection(s) to detect fatigue cracking of the shock strut cylinder of the main landing gear (MLG), and replacement of any cracked shock strut cylinder with a serviceable part. That AD also provides for installation of brake line hydraulic restrictors on the MLG brake systems, which, if accomplished, terminates the repetitive inspections. This amendment requires that the subject inspection be accomplished repetitively following installation of brake line hydraulic restrictors. This amendment is prompted by an additional report of fatigue cracking and subsequent fracturing of the shock strut cylinder of the MLG. The actions specified by this AD are intended to prevent collapse of the MLG due to fracturing of the shock strut cylinder.
83-11-03: 83-11-03 PACIFIC SCIENTIFIC COMPANY, KIN-TECH DIVISION: Amendment 39-4662. Applies to Pacific Scientific flight attendant restraint system rotary buckle assemblies, Part Numbers 1107261-01, -05 and -09, manufactured prior to 1982. Compliance required within 180 days from the effective date of this AD, unless previously accomplished. To prevent the entrapment of occupants caused by the inability to release the restraint system assembly, accomplish the following: a. Inspect flight attendant restraint systems to determine if Pacific Scientific rotary buckle as identified in Figure 1 of Pacific Scientific Service Bulletin 1107261-25-01 is installed. b. If installed, determine if the old lower cover 1107270-01 or the new cover assembly 1107525-01 is installed. The cover is not identified with a part number; however, with the old cover only the two (2) attachment screw heads will be seen. The new cover assembly also has two (2) rivet upsets on the outside of the cover assembly and, in addition, the lap belt and/or inertia reel nameplate should be identified with the letter "M" after the assembly part number. c. If the new cover assembly 1107525-01 is installed, no further action is required per this AD. d. If the old cover 1107270-01 is installed, replace the old cover with the new 1107525-01 cover assembly and stamp or mark a suffix letter "M" next to part number on each lap belt and on inertia reel nameplate. NOTE: Pacific Scientific Service Bulletin 1107261-25-01, Revision 1, dated June 1, 1982, pertains to this subject. e. Alternate inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Manager, Western Aircraft Certification Field Office, FAA, Northwest Mountain Region. This amendment becomes effective July 18, 1983.
2006-01-08: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model Avro 146-RJ airplanes. This AD requires reviewing the airplane's maintenance records to determine if certain tasks of the BAE Systems (Operations) Limited BAe146/Avro RJ Maintenance Planning Document issued May 15, 2004, have been accomplished. This AD also requires doing repetitive detailed inspections of the external fuselage skin adjacent to the longeron at rib 0 from frame 29 to frame 31, and repairing any damage. This AD results from issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. We are issuing this AD to detect and correct cracking of the fuselage skin, which could result in structural failure of the fuselage.
62-21-04: 62-21-04 LOCKHEED: Amdt. 489 Part 507 Federal Register October 3, 1962. Applies to All Model 1649A Aircraft. Compliance required as indicated. As a result of chordwise cracks on the wing lower milled skin at wing Station 590, the following shall be accomplished: (a) Within the next 400 hours' time in service after the effective date of this AD, unless already accomplished within the past 600 hours' time in service, and at periods thereafter not exceeding 1,000 hours' time in service following that initial inspection, inspect from wing Station 580 through wing Station 600, the external lower surface of the aft skin panels, P/N 472066, for any evidence of cracks emanating from the aft edge of the panel through the rear beam attachment holes. Inspection shall be by close visual or dye penetrant means. (b) Any cracks shall be repaired prior to further flight in accordance with Lockheed 1649 Service Bulletin No. 73, Section 1, "Modification Data," and Lockheed Drawing SED61- 9004, or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. (c) The periodic inspections may be discontinued following repair per (b) or when an uncracked skin panel has been reinforced in accordance with Lockheed 1649 Service Bulletin No. 73. (d) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. (Lockheed Field Service Letter FS/240893L, dated April 14, 1960, and Lockheed 1649 Service Bulletin No. 73 cover this same subject.) This directive effective November 2, 1962.
99-06-01: This amendment supersedes Airworthiness Directive (AD) 81-15-04 R1, which currently requires repetitively inspecting for cracks at the elevator outboard hinge attachment on the horizontal stabilizer rear spar on certain The New Piper Aircraft, Inc. (Piper) Models PA-31, PA-31-300, PA-31-325, PA-31-350, and PA-31P-350 airplanes, and if cracks are found, incorporating a spar and hinge bracket assembly kit. This AD requires repetitively inspecting the horizontal rear spar in the area of the outboard hinge attachment and the outboard hinge attach bracket for cracks. When cracks are found or at a certain accumulation of time-in-service (TIS), this AD also requires modifying the horizontal stabilizer spar by incorporating an improved stabilizer spar and hinge bracket assembly kit that will terminate the repetitive inspections. This AD is prompted by several field reports of cracks found during routine inspections on airplanes already in compliance with AD 81-15-04 R1. The actions specified by this AD are intended to prevent failure of the horizontal stabilizer rear spar caused by cracks at the elevator outboard hinge attachment, which could result in loss of control of the airplane.
88-18-03: 88-18-03 GARRETT ENGINE DIVISION, ALLIED-SIGNAL, INC. (formerly Garrett Turbine Engine Company, GTEC): Amendment 39-6248. Final copy of priority letter AD issued August 30, 1988. Applicability: Garrett TFE731-3 turbofan engine models installed in airplane models as follows: GARRETT MODEL NO. AIRPLANE MODEL TFE731-3-1C FALCON 50 TFE731-3-1E 731 JETSTAR TFE731-3-1F JETSTAR II TFE731-3-1G WESTWIND 1124 TFE731-3-1H BAe HS125-SERIES TFE731-3-1J CASA 101 TFE731-3-1K JETSTAR II (SPRINGFIELD) TFE731-3A-2B LEARJET 55 TFE731-3A-2B1 LEARJET 55 TFE731-3A-200G WESTWIND 1125 TFE731-3AR-2B LEARJET 55 TFE731-3AR-2B1 LEARJET 55 TFE731-3AR-200G WESTWIND 1125 TFE731-3R-1D SABERLINER 65/65A TFE731-3R-1G WESTWIND 1124 TFE731-3R-1H BAe HS125-SERIES Compliance: Required as indicated, unless already accomplished. To prevent uncontained engine failures, accomplish the following within 25 cycles in service, after the effective date of this AD. (a) Review the engine maintenance records on the above listed engine models to determine if part number 3072316-2 or -3, or 3073110-1 or -2, high pressure turbine rotor (HPTR) disc with one of the following serial numbers is installed. Spare discs must also be checked for applicable part number and serial number. 1-18040-9514 6-12112-960 4-12112-167 6-12112-1938 4-12112-1536 7-12112-875 4-12112-1564 8-12112-199 6-12112-938 9-12112-3862 6-12112-954 9-12112-3878 (b) Inspect and remove from service, if necessary, suspect serial number disc installed in engines in accordance with the accomplishment instructions of Garrett Alert Service Bulletin TFE731-A72-3376, dated August 19, 1988, and replace with serviceable HPTR disc. (c) Inspection of the disc is required per paragraph (b) above, before further flight operation, if a suspect serial number disc is located in a spare engine or as a spare part. (d) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (e) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, Aircraft Certification Service, Federal Aviation Administration, 3229 East Spring Street, Long Beach, California 90806- 2425, may approve an equivalent means of compliance or an adjustment of the compliance schedule which provides an equivalent level of safety. The HPTR disc inspection shall be done in accordance with Garrett SB TFE731-A72-3376, dated August 19, 1988. 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 Garrett General Aviation Services Division, Distribution Center, 2340 East University, Phoenix, Arizona 85034; telephone (602) 225-2548. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the Office of the Federal Register, 1100 L Street, Room 8301, Washington, DC 20591. This amendment (39-6248) becomes effective on July 21, 1989, as to all persons except those persons to whom it was made immediately effective by Priority Letter AD 88-18-03 issued August 30, 1988, which contained this amendment.