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88-11-08: 88-11-08 BRUCE INDUSTRIES, INC.: Amendment 39-5932. Applies to all ballasts, Part Number 05241-1, as installed on, but not limited to, aircraft modified in accordance with Supplemental Type Certificate (STC) Numbers SA1081NW, SA1315NM, SA1952NM, SA3144NM, and SA4042WE; and Civil Aviation Authority Airworthiness Approval Note No. 17027, Issue 2. Compliance required as indicated. NOTE: HITCO Alert Service Bulletin A9000203-33-20-01, dated May 2, 1988, lists specific aircraft modified in accordance with the referenced STC's; however, these ballasts may also be installed on other aircraft. To prevent fire caused by shorted and sparking ballast, accomplish the following, unless already accomplished: A. Within 30 days after the effective date of this airworthiness directive (AD), install a fuse assembly for each affected ballast in accordance with the accomplishment instructions of Bruce Industries, Inc., Alert Service Bulletin A05241-33-20-01, dated May 2, 1988.NOTE: HITCO Alert Service Bulletin A9000203-33-20-01, dated May 2, 1988, is considered an approved equivalent modification. 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, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Los Angeles Aircraft Certification Office. 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 information from the manufacturer may obtain copies upon request to Bruce Industries, Inc., P.O. Box 1700, Dayton, Nevada 89403, Attention: Contracts Department; or (for airplanes with HITCO cabin interiors) HITCO, 1600 West 135th Street, Gardena, California 90249, Attention: Contracts Department. This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. This Amendment 39-5932 becomes effective June 10, 1988.
84-11-05: 84-11-05 BRITISH AEROSPACE: Amendment 39-4888. Applies to British Aerospace (BAe) HP.137 Jetstream Mk. 1, Jetstream Series 200, and Jetstream Model 3101 airplanes (all serial numbers through 619, except serial number 615), certificated in any category. Compliance: Required prior to further flight, unless already accomplished. To reduce the possibility of a malfunction causing the flaps to move to the lift dump position in flight, accomplish the following: a) For the HP.137 Jetstream Mk.1 and Jetstream Series 200 airplanes: 1) Fabricate and install in full view of the pilot, a temporary placard using letters of minimum .10 inch in height which states: "PRIOR TO EACH FLIGHT, COMPLETE THE FLAP OPERATIONAL CHECKS IN THE INSERT TO SECTION 4 OF THE AFM. MAXIMUM FLAP EXTENSION SPEED - 140 KNOTS IAS" 2) Temporarily blank out the flap extension speeds on the Limitations Placard and operate the airplane in accordance with these limitations. 3) Add the following information to Section 4 of the Airplane Flight Manual (AFM): i) Upon completion of "After Start Checks" accomplish Flaps Operational Check as follows: With POWER levers just forward of the GROUND IDLE range, check T.O. and DOWN positions. Retard the POWER levers to GROUND IDLE and check that the flaps extend to the DUMP position. Move POWER levers just forward of GROUND IDLE and check flaps return to DOWN position. Select FLAPS UP and check the flaps return to the UP position. Ensure that the position of flap selector switch corresponds with the indication on the flap position indicator. ii) If the flaps do not move to the correct position, remove the airplane from service and contact BAe (see note for address). 4) Add the following information to Section 3 of the AFM: i) Should the flaps fail to retract after takeoff, re-select the T.O. position. ii) Should the flaps fail to extend on selection, re-select to the UP position.iii) Should the flaps run to DOWN when selected to T.O. for approach, select the achieved position. iv) Do not use the Emergency Hydraulic System to lower the flaps when a malfunction has been identified. v) Depending on circumstances, either carry out a landing with flaps UP or with the flaps partially deflected, using the LANDING WITH FLAPS UP procedures detailed in Section 3 of the Flight Manual, or if the flaps are fully extended to the normal landing position, carry out a normal landing using normal procedures. LIFT DUMP should be available on touch-down. vi) If a malfunction has been identified, remove the airplane from service and contact BAe (see note for address). b) For Jetstream Model 3101 airplanes: 1) Fabricate and install in full view of the pilot, a temporary placard using letters of minimum .10 inch in height which states: "PRIOR TO EACH FLIGHT, COMPLETE THE FLAP OPERATIONAL CHECKS IN THE INSERT TO SECTION 4 OF THE AFM. MAXIMUM FLAP EXTENSION SPEED - 149 KNOTS IAS" 2) Temporarily blank out the flap extension speeds on the Limitations Placard and operate the airplane in accordance with these limitations. 3) Add the following information to Section 4 of the AFM: i) Upon completion of "After Start Checks" accomplish Flaps Operational Check as follows: Ensure each time by reference to the Wing Flaps Position Indicator, that the achieved position corresponds to the Selected position. Check that Lift Dump is only achieved with flaps selected to 50 degrees and Power Levers to Ground Idle. ii) If the flaps do not move to the correct position, remove the airplane from service and contact BAe (see note for address). 4) Add the following information to Section 3 of the AFM: i) Should the flaps fail to retract after takeoff, re-select previously selected position. ii) Should the flaps fail to extend on selection, re-select to the UP position. iii) Should the flaps run to 50 degrees when selected to 10 degrees or 20 degrees for approach, select the achieved position. iv) Do not use the Emergency Hydraulic System to lower the flaps when a malfunction has been identified. v) Depending on circumstances, either carry out a landing with flaps UP or with the flaps partially deflected, using the LANDING WITH FLAPS UP procedures detailed in Section 3 of the Flight Manual, or if the flaps are fully extended to the normal landing position, carry out a normal landing using normal procedures. LIFT DUMP should be available on touch-down. vi) If a malfunction has been identified, remove the airplane from service and contact BAe (see note for address). c) Insertion of a copy of this AD in front of the sections specified in paragraphs a)3), a)4), b)3), and b)4) above satisfies the requirements of these paragraphs. d) The requirements of paragraph c) of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by him. The person accomplishing these actions must make the appropriate aircraft maintenance record entry as prescribed by FAR 91.173. e) Remove the temporary placards, AFM inserts and operational placard changes required elsewhere in this AD when BAe Modification JM5236 is accomplished. f) An equivalent means of compliance with this AD may be used, if approved, by Manager, Aircraft Certification Office, AEU-100, Europe, Africa & Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. NOTE: Repair and parts information may be obtained from British Aerospace (BAe), Engineering Department, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041; telephone (703) 435-9100. This amendment becomes effective on July 17, 1984, to all persons except those to whom it has already been made effective by priority letter from the FAA dated June 6, 1984, and is identified asAD 84-11-05.
2001-17-23: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100, -200, and -300 series airplanes, that requires a one-time detailed visual inspection to detect damage of the ladder plates and access cover areas of the upper surface of the wings; repair, if necessary; and installation of new O-ring seals. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent damage of the upper wing ladder plates, which could result in displacement of the adjacent channel seals and consequent reduced lightning strike protection of the fuel tanks.
76-16-07: 76-16-07 CESSNA AVIATION: Amendment 39-2694. Applies to Cessna models 401 and 402 series airplanes and model 414 airplanes certificated in all categories, which have been modified in accordance with either Supplemental Type Certificate SA2424WE or SA117NW, incorporating Allison turboprop engines. Compliance required as indicated. To prevent and detect possible failures of the engine attachment tangs, of engine mount PN5002, accomplish the following: (a) Within 10 hours' time in service after the effective date this AD, unless already accomplished, loosen the engine attach bolts and compress the rubber mounts. Use steel shims to reduce the gap between the forward tang and AN970 washer (with the bushing and washers compressed against the aft tang) to no greater than 0.005 inches and retorque the bolts to 160-190 inch pounds. (b) Within 10 hours' time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed the time limits indicated below, visually inspect, with a glass of at least 8-power, the forward and aft tangs of all three engine attachment points on the engine support truss for cracks: TIME IN SERVICE ON ENGINE MOUNT TIME IN SERVICE BEFORE NEXT INSPECTION 0 to 1,000 hrs. 500 hrs. 1,000 to 2,000 hrs. 200 hrs. 2,000 and above 10 hrs. Example: Engine mount with 100 hours time in service on effective date of this AD. Inspections required at or before 110, 610, 1110, 1310, 1510, 1710, 1910, 2110, 2120, 2130, etc., hours. (c) If any crack is detected as a result of any of the inspections conducted in accordance with paragraph (b), before further flight the engine mount, P/N 5002, must be replaced with an uncracked engine mount of the same part number or an engine mount approved by the Chief, Aircraft Engineering Division, FAA Western Region. (d) The modification and repetitive inspections required by paragraphs (a) and (b) may be discontinued on engine mounts modified in accordance with American Jet Industries Service Bulletin 400-1 dated June 7, 1976, or later FAA-approved revision. (e) Equivalent inspections or modifications may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. (f) Special flight permits may be issued per FAR 21.197 and FAR 21.199 to authorize flight to perform the modification required by paragraph (a), the initial inspection required by paragraph (b), and the modification specified in paragraph (d). This supersedes amendment 39-2597 (41 F.R. 18647), AD 76-09-08. This amendment becomes effective August 20, 1976.
93-10-03: 93-10-03 AIRBUS INDUSTRIE: Amendment 39-8581. Docket 92-NM-224-AD. Applicability: Model A320 series airplanes, as listed in Airbus Industrie Service Bulletin A320-28-1040, Revision 1, dated April 3, 1992; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the occurrence of electrical arcing between the fuel probes and the center and inner wing fuel tanks, accomplish the following: (a) For airplanes on which Modification 22647 has not been accomplished: Within 9 months after the effective date of this AD, remove fuel probes 35QT, 36QT, 37QT, 38QT, and 39QT; install a nylon plate on each attachment bracket in the center fuel tank, Modification 22647; reinstall the fuel probes; and perform a functional check; in accordance with Airbus Industrie Service Bulletin A320-28-1040, Revision 1, dated April 3, 1992; or Revision 3, dated January 15, 1993. (b) For airplanes on which Modification 22855 has not been accomplished: Within 9 months after the effective date of this AD, remove fuel probes 21QT1, 21QT2, 22QT1, 22QT2, 23QT1, 23QT2, 25QT1, 25QT2, 26QT1, 26QT2, 27QT1, 27QT2, 29QT1, 29QT2, 31QT1, and 31QT2; install new support bracket assemblies on fuel probes 1 and 2 in the inner fuel tanks of the left- and right-hand wings, Modification 22855; reinstall fuel probes; and perform a functional check; in accordance with Airbus Industrie Service Bulletin A320-28-1040, Revision 1, dated April 3, 1992; or Revision 3, dated January 15, 1993. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, 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, ANM-113. NOTE: Information concerning theexistence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The removal, modification, reinstallation and functional check shall be done in accordance with the following Airbus Industrie service bulletins, which contain the specified effective pages, as applicable: Service Bulletin Referenced and Date Revision Level Page Number Date Shown on Page Shown on Page A320-28-1040, Revision 1, April 3, 1992 1-5, 7, 9 12-13, 27-29 6, 8, 10-11 14-26 1 (Original) April 3, 1992 January 31, 1992 A320-28-1040, Revision 3, January 15, 1993 1-4, 7, 9-23 26-38 5-6, 8 24-25 3 (Original) January 15, 1993 January 31, 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 Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 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, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on July 1, 1993.
92-19-09 R1: 92-19-09 R1 SHORT BROTHERS, PLC: Amendment 39-8716. Docket 93-NM-61-AD. Revises AD 92-19-09, Amendment 39-8367, which superseded AD 84-07-06 R1, Amendment 39-6036. Applicability: All Model SD3-30 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. NOTE 1: Paragraphs (a), (b), (c), and (f) of this AD restate the requirements of those paragraphs as they appeared in AD 92-19-09, Amendment 39-8367; the requirements of those paragraphs entail specific one-time actions. As allowed by the phrase, "unless accomplished previously," if the requirements of those paragraphs have been accomplished previously, this AD does not require that they be repeated. NOTE 2: Paragraphs (d) and (e) of this AD restate the requirements for repetitive inspections contained in the same paragraphs of AD 92-19-09, Amendment 39-8367. The first inspection required by this AD must be performed within the specified repetitive inspection interval after the last inspection performed in accordance with paragraphs (d) and (e) of AD 92-19-09. To prevent reduced structural capability of the wing, accomplish the following: (a) Within 180 days after November 3, 1988 (the effective date of AD 84-07-06 R1, Amendment 39-6036), install a new closing panel in the aft baggage compartment in accordance with Shorts Service Bulletin SD3-25-30, dated January 8, 1982. (b) Within 180 days after November 3, 1988, inspect to detect fuel leakage and seal the fuselage crown in accordance with Shorts Service Bulletins SD3-53-01, Revision 2, dated January 19, 1977; SD3-53-18, dated November 25, 1977; and SD3-53-41, dated May 21, 1980. (c) Within 600 hours time-in-service after November 3, 1988, or prior to the accumulation of 4,800 total hours time-in-service, whichever occurs later, inspect to detect cracking and modify the wing drag links in accordance with Shorts Service Bulletin SD3-53-48, Revision 1, dated January 5, 1983. Replace damaged parts prior to further flight, in accordance with the service bulletin. (d) Within 90 days after November 3, 1988, inspect to detect corrosion or wear in the horizontal stabilizer (tailplane)-to-fuselage fittings, pins, and bushings in accordance with Shorts Service Bulletin SD3-55-16, Revision 3, dated November 1987. For airplanes that have accumulated less than 4,800 total hours time-in-service and are less than 2 years old as of November 3, 1988, accomplishment of this inspection may be deferred until the affected airplane reaches 4,800 total hours time-in-service or 2 years of age, whichever occurs first. Replace any worn or corroded parts prior to further flight, in accordance with the service bulletin. (1) If no pin has been replaced with a new pin, and if there is no corrosion found on any attachment fitting, repeat this inspection thereafter at intervals not to exceed 1,200 flight hours or within 6 months following the immediately preceding inspection, whichever occurs first. (2) If all the pins on one side have been replaced with new pins, repeat the inspection on that side within the next 4,800 flight hours or 2 years following replacement of the pins, whichever occurs first. Repeat this inspection thereafter at intervals not to exceed 2,400 flight hours or 1 year following the immediately preceding inspection, whichever occurs first. (e) For airplanes having serial numbers SH3002 through SH3090, inclusive: Within 300 hours time-in-service after November 3, 1988, or prior to the accumulation of 4,800 total hours time- in-service, whichever occurs later, inspect to detect cracked or broken rib/skin attachment cleats at left wing station 160 in accordance with Part A (Inspection) of paragraph 2.A. of the Accomplishment Instructions in Shorts Service Bulletin SD3-57-10, Revision 1, dated October 11, 1982; or Revision 2, dated January 4, 1993. Repeat this inspection within 2,400 hours time-in-service following the immediately preceding inspection, or within 300 hours time-in-service after November 17, 1992 (the effective date of AD 92-19-09, Amendment 39-8367), whichever occurs later. (1) If no crack is found, repeat this inspection of each bay thereafter at intervals not to exceed 2,400 hours time-in-service. (2) If any crack is found, prior to further flight, repair in accordance with Part B (Repair - Rear Bay) and/or Part C (Repair - Forward Bay) of paragraph 2.A. of the Accomplishment Instructions in the service bulletin; and repeat the inspection of the repaired bay thereafter at intervals not to exceed 9,600 hours time-in-service. (f) Within 180 days after November 3, 1988, modify the power control circuit in accordance with Shorts Service Bulletin SD3-76-01, dated September 8, 1981. (g) 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, ANM-113. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (h) 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. (i) The actions shall be done in accordance with Shorts Service Bulletin SD3-25-30, dated January 8, 1982; Shorts Service Bulletin SD3-53-01, Revision 2, dated January 19, 1977; Shorts Service Bulletin SD3-53-18, dated November 25, 1977; Shorts Service Bulletin SD3-53-41, dated May 21, 1980; Shorts Service Bulletin SD3-53-48, Revision 1, dated January 5, 1983; Short Service Bulletin SD3-55-16, Revision 3, dated November 1987; Shorts Service Bulletin SD3-76-01, dated September 8, 1981; Shorts Service Bulletin SD3-57-10, Revision 1, dated October 11, 1982; and Shorts Service Bulletin SD3-57-10, Revision 2, dated January 4, 1993. Revision 2 of Shorts Service Bulletin SD3-57-10 contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1, 3-13 1 October 11, 1982 2 2 January 4, 1993 This incorporation by reference of Shorts Service Bulletin SD3-57-10, Revision 2, dated January 4, 1993, is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. The incorporation by reference of the remainder of the service documents listed above was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51 as of November 17, 1992 (57 FR 46772, October 13, 1992). Copies may be obtained from Short Brothers, PLC, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3719. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (j) This amendment becomes effective on November 26, 1993.
2017-02-05: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of skin cracking found at the corners of the aft entry and aft galley doorways. This AD requires repetitive inspections for cracking of the fuselage \n\n((Page 9493)) \n\nskin assembly and the bear strap at the corners of the aft entry and aft galley doorways, and repair if necessary, which terminates the repetitive inspections of the repaired areas. We are issuing this AD to address the unsafe condition on these products.
2017-02-06: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. Models PA-31T, PA-31T1, PA-31T2, PA-31T3, and PA- 31P-350 airplanes. This AD requires repetitive detailed visual inspections of the wiring below the main circuit breaker panel for proper clearance and evidence of damage and rerouting or replacing wires and/or parts as necessary. This AD was prompted by a fatal accident where evidence of thermal damage in this area was found. We are issuing this AD to correct the unsafe condition on these products.
2001-17-22: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 and MD-10 series airplanes, that requires an inspection of the one phase remote control circuit breakers (RCCB) in the main avionics compartment and center accessory compartment to determine their part numbers and serial numbers, and replacement of RCCB's with certain RCCB's, if necessary. This action is necessary to ensure that defective braze joints of certain latch assemblies of the RCCB are not installed on the airplane. Defective braze joints could fail and prevent the RCCB from tripping during an overload condition, which could result in a fire and smoke in certain wire bundles that are routed to and from the main avionics compartment or center accessory compartment. This action is intended to address the identified unsafe condition.
92-18-10: 92-18-10 BRITISH AEROSPACE: Amendment 39-8354. Docket 92-NM-34-AD. Applicability: Model ATP series airplanes; serial numbers 2001 through 2045, inclusive; which have been modified in accordance with Pratt and Whitney Service Bulletin PW100-72-21097, dated November 8, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent severe structural damage to the airplane due to an internal engine fire within the intercompressor case, accomplish the following: (a) Within 90 days after modification in accordance with Pratt and Whitney Service Bulletin PW100-72-21097, dated November 8, 1991, or within 90 days after the effective date of this AD, whichever occurs later: (1) Install an intercompressor case (ICC) fire detector system, in accordance with British Aerospace Service Bulletin ATP-26-5-35225A, dated October 30, 1991. (2) Revise Section 0.25.0 of the FAA-approved Airplane Flight Manual (AFM) to include the following statement. This may be accomplished by inserting a copy of this AD in the AFM. "Modification No. Description 35225A Introduction of ICC Fire Detector at the Intercompressor Case." (3) Revise the FAA-approved AFM to include operating information pertaining to the ICC fire detection systems. This may be accomplished by inserting a copy of Temporary Revision No. T/24, Issue 1, dated February 17, 1992, into the AFM. (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, ANM-113. 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 installation and revision of the AFM shall be done in accordance with Temporary Revision No. T/24, Issue 1, dated February 17, 1992; and British Aerospace Service Bulletin ATP-26-5-35225A, dated October 30, 1991, which contains the following list of effective pages: Page Number Revision Level Date 1-7, 9, 11, 13, 15, 17, 19, 21, 23, 25, 27, 29, 31, 33, 35, 37, 39, 41, 43 Original October 30, 1991 8, 10, 12, 14, 16, 18, 20, 22, 24, 26, 28, 30, 32, 34, 36, 38, 40, 42 (These pages are not used) 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, DC 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., Suite 700, Washington, DC. (e) This amendment becomes effective on October 13, 1992.