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82-19-04: 82-19-04 BRITISH AEROSPACE (formerly Hawker Siddeley): Amendment 39-4462. Applies to H.S. 748 Series 2A airplanes certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent loss of an emergency overwing exit panel during flight, accomplish the following within thirty days after the effective date of this AD: 1. Remove the word "CLOSED" and the associated indicator line from the exterior of the overwing emergency exit panels. 2. Inspect each overwing emergency exit panel for free movement of the handle and lock operating mechanism in accordance with paragraphs 2A(1), (2), (3), and (4) of the H.S. Service Bulletin A52-82, dated May 31, 1979, Accomplishment Instructions. 3. Check the fit of each overwing emergency exit panel in the fuselage aperture in accordance with Chapter 52-20-1 of the H.S. 748 Maintenance Manual or an FAA approved equivalent procedure. 4. Reestablish the indicator marking on the cam lever in accordance with paragraph 2A(4) of the service bulletin if the inspections and checks required in paragraph 2 of this AD show the indicator markings on the cam lever and the lever stop do not coincide. 5. Alternate means of compliance with this AD which provide an equivalent level of safety may be used when approved by the Manager, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 6. 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 and/or modifications required by this AD. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). This amendment becomes effective September 28, 1982.
93-23-11: 93-23-11 MCDONNELL DOUGLAS: Amendment 39-8747. Docket 93-NM-51-AD. \n\n\tApplicability: All Model DC-9-10, -20, -30, -40, and -50 series airplanes; Model DC-9-81, -82, -83, and -87 series airplanes; Model MD-88 airplanes; and C-9 (military) airplanes; equipped with nose wheel assembly part number 9550267-6 or 9550267-7; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent reduced structural integrity of the nose wheel assembly, resulting from installation of a suspected unapproved part, accomplish the following: \n\n\t(a)\tWithin 60 days after the effective date of this AD, accomplish either paragraph (a)(1) or (a)(2) of this AD. \n\n\t\t(1)\tPerform a one-time visual inspection of nose wheel assemblies, part numbers 9550267-6 and 9550267-7, to ensure that these assemblies are identified correctly in accordance with Section II, Accomplishment Instructions, of Aircraft Braking Systems Corporation Service Letter MD81-SL-3, MD82-SL-3, MD83-SL-4, MD87-SL-3, MD88-SL-4, MD90-SL-1, DC9-10-SL-12, DC9-30-SL-16, DC9-40-SL-16, DC9-50-SL-8 (included in one document), dated February 10, 1993. \n\n\t\t\t(i)\tIf any nose wheel assembly is not identified correctly, prior to further flight, replace that assembly with an FAA-approved assembly in accordance with the applicable Aircraft Maintenance Manual. \n\n\t\t\t(ii)\tIf each nose wheel assembly is identified correctly, no further action is required by this paragraph. \n\n\t\t(2)\tDetermine if the nose wheel assemblies, part numbers 9550267-6 and 9550267-7, have ever been in the possession of Aviation Wheel and Brake, Miami, Florida. This determination may be accomplished by performing a search of maintenance or other records. \n\n\t\t\t(i)\tIf it is not possible to make such a determination, or if the results of that determination indicate that any nose wheel assembly has been in the possession of Aviation Wheel and Brake, accomplish the inspection required by paragraph (a)(1) of this AD. \n\n\t\t\t(ii)\tIf it is determined that a nose wheel assembly has never been in the possession of Aviation Wheel and Brake, no further action is required by this paragraph with respect to that nose wheel assembly. \n\n\t(b)\tAs of the effective date of this AD, no person shall install a nose wheel assembly, part number 9550267-6 or 9550267-7, on any airplane unless, prior to installation, that nose wheel assembly has been inspected in accordance with the requirements of paragraph (a)(1) of this AD and has been found to be identified correctly; or unless, prior to installation, it has been determined that the nose wheel assembly has never been in the possession of Aviation Wheel and Brake in accordance with the requirements of paragraph (a)(2) of this AD. \n\n\t(c)\tAn 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, Los Angeles Aircraft Certification Office (ACO), 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, Los Angeles ACO. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. \n\n\t(d)\tSpecial 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. \n\n\t(e)\tThe inspection shall be done in accordance with Aircraft Braking Systems Corporation Service Letter MD81-SL-3, MD82-SL-3, MD83-SL-4, MD87-SL-3, MD88-SL-4, MD90-SL-1, DC9-10-SL-12, DC9-30-SL-16, DC9-40-SL-16, DC9-50-SL-8 (included in one document), dated February 10, 1993. 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 Aircraft Braking Systems Corporation, 1204 Massillon Road, Akron, Ohio 44306-4186. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. \n\n\t(f)\tThis amendment becomes effective on January 5, 1994.
93-21-10: 93-21-10 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-8724. Docket Number 91-ASW-18. Applicability: Model 214B and 214B-1 helicopters, serial numbers (S/N's) 28001 through 28070, equipped with main rotor yoke assembly (assembly), part number (P/N) 214-010-105-001, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the assembly, loss of the main rotor, and subsequent loss of control of the helicopter, accomplish the following: (a) For assemblies that have 3,700 hours' or less time-in-service on the effective date of this airworthiness directive (AD), replace the assembly on or before reaching 3,750 hours' time-in-service. For assemblies that have more than 3,700 hours' time-in-service on the effective date of this AD, replace the assembly within the next 50 hours' time-in-service. (b) Within 50 hours' time-in-service after the effective date of this AD, install new airspeed versusaltitude decals, P/N 214-075-256-105 for BHTI Model 214B-1 and P/N 214-075-256-107 for Model 214B helicopters. (c) Within 50 hours' time-in-service after the effective date of this AD and thereafter at intervals of 1,200 hours' time-in-service, inspect the yoke for straightness in accordance with the applicable maintenance manual. NOTE: BHTI Alert Service Bulletin No. 214-87-37, Revision A, dated September 10, 1987, pertains to this AD. (d) 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, Rotorcraft Certification Office, FAA, Rotorcraft Directorate, Fort Worth, Texas 76193-0170. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Certification Office. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished. (f) This amendment becomes effective on January 18, 1994.
91-25-01: 91-25-01 ISRAEL AIRCRAFT INDUSTRIES (IAI), LTD.: Amendment 39-8102. Docket No. 91- NM-219-AD. Applicability: All Model 1125 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent uncontrolled pitch trim movement, accomplish the following: (a) Within 3 days after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the following. This may be done by inserting a copy of this AD in the AFM. "BEFORE TAXIING Horizontal stabilizer trim - CHECK OVERRD & EMERG; EMERG ARM pushbutton - DISENGAGE, CHECK NORMAL (buzzer) NOTE When checking override system, observe trim indicator; electrical limit switches are inoperative. CAUTION Do not use emergency trim in place of normal or override trim systems. Use of emergency trim is limited to elevator control failure (Section II, page II-28) and horizontal stabilizertrim failure (Section III, page III-9)." NOTE: Inserting Astra (Model 1125) AFM Temporary Revision No. 3, dated June 9, 1991, in the Limitations section of the AFM, or inserting an AFM revision containing this information, is considered an acceptable alternative method of compliance with this paragraph. (b) Within 3 days after the effective date of this AD, revise the Normal Procedures Section of the FAA-approved AFM to include the following. This may be done by inserting a copy of this AD in the AFM. "BEFORE TAXIING Horizontal stabilizer trim - CHECK OVERRD & EMERG; EMERG ARM pushbutton - DISENGAGE, CHECK NORMAL (buzzer) NOTE When checking override system, observe trim indicator; electrical limit switches are inoperative. CAUTION Do not use emergency trim in place of normal or override trim systems. Use of emergency trim is limited to elevator control failure (Section II, page II-28) and horizontal stabilizer trim failure (Section III, page III-9)." NOTE: Inserting Astra (Model 1125) AFM Temporary Revision No. 3, dated June 9, 1991, in the Procedures Section of the AFM, or inserting an AFM revision containing this information, is considered an acceptable alternative method of compliance with this paragraph. (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, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Operations Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. (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) This amendment (39-8102, AD 91-25-01) becomes effective on December 10, 1991.
93-02-09: 93-02-09 SAAB-SCANIA: Amendment 39-8492. Docket 92-NM-121-AD. Applicability: Model SAAB SF340A series airplanes, serial numbers 004 through 159, inclusive; and Model SAAB 340B series airplanes, serial numbers 160 through 339, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent damage/disbonding of the fuselage skin due to overheat, and subsequent reduced structural capability, accomplish the following: (a) Within 3 months after the effective date of this AD, relocate the sensor loops of the bleed air leak detection system, in accordance with SAAB-SCANIA Service Bulletin SAAB 340-36-006, dated August 6, 1992. (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, ANM-113. (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 relocation shall be done in accordance with SAAB-SCANIA Service Bulletin SAAB 340-36-006, dated August 6, 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 SAAB-SCANIA AB, SAAB Aircraft Product Support, S-581 88, Link ping, Sweden. 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 March 26, 1993.
76-21-01: 76-21-01 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-2745. Applies to Lockheed Model L-1011-385 series airplanes certificated in all categories having C-1A cargo door installed. Compliance required within the next 300 hours' time in service after the effective date of this AD, unless already accomplished. To prevent the latch pins on the latch fittings of the C-1A cargo door surround structure from being incorrectly installed during maintenance replacement, which could result in a possible in-flight loss of the C-1A cargo door, accomplish the following: a. Install latch pin guard assemblies and related components, reidentify the latch fitting assemblies and check proximity sensors adjustment as necessary, on the C-1A cargo door surround structure, in accordance with Lockheed-California Company Service Bulletin 093-52-083 dated May 25, 1976, or later FAA-approved revision or equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region.b. Airplanes may be flown in accordance with FAR 21.197 to a base where the modification can be performed. This amendment becomes effective November 20, 1976.
92-20-02: 92-20-02 FOKKER: Amendment 39-8376. Docket No. 92-NM-70-AD. Applicability: Model F28 Mark 0100 series airplanes; serial numbers 11290, 11296, 11298, 11299, 11301, 11306, 11308, 11310, and 11313; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent structural damage to the wing, empennage, or an engine, caused by loss of the radome during flight or ground operations, accomplish the following: (a) Within 6 months after the effective date of the AD, replace the currently installed blind bolts that attach the latch brackets to the radome with new bolts, in accordance with Fokker Service Bulletin SBF100-53-067, dated July 1, 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 anappropriate 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 replacement shall be done in accordance with Fokker Service Bulletin SBF100-53- 067, dated July 1, 1991. 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on December 14, 1992.
78-12-01 R1: 78-12-01 R1 SHORT BROTHERS LIMITED: Amendment 39-3229 as amended by Amendment 39-3858. Applies to Model SD3-30 Airplanes Serial Numbers SH 3003 through SH 3007 and SH 3009 through SH 3015, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent fuel system purge valve leakage and associated fuel leakage or fuel vapors entering the cabin accomplish the following: (a) Within the next 30 hours time in service after the effective date of this AD, remove purge valves, Part Number 3706190, and replace them with modified purge valves, Part Number 3706235, in accordance with Shorts Service Bulletin SD3-28-08, Revision No. 1, dated February 15, 1979. (b) If fuel leakage or vapors are detected in the cabin prior to compliance with paragraph (a) of this AD but after the effective date of this AD, comply with paragraph (a) before further flight. (c) Equivalent methods of compliance with paragraph (a) of this AD may beapproved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium, if the request is submitted through an FAA Maintenance Inspector and contains substantiating data to justify the method of compliance for that operator. Amendment 39-3229 became effective June 22, 1978. This Amendment 39-3858 becomes effective August 11, 1980.
77-16-07: 77-16-07 MESSERSCHMITT-BOLKOW-BLOHM (MBB). Amendment 39-3001. Applies to Model BO-105A and BO-105C helicopters which incorporate main rotor gearbox oil pumps, P/N's 7631 955 112 or 7631 955 115, having Serial Numbers up to and including 229. Compliance is required as indicated, unless already accomplished. To prevent excessive wear of the sun gear in the planet gear carrier of the main rotor gearbox, accomplish the following: (a) Within the next 100 hours time in service after the effective date of this AD, modify the main rotor gearbox oil pump as follows: (1) For pumps, P/N 7631 955 115, install a stronger compression spring in accordance with MBB Service Bulletin No. 10-16, dated July 28, 1975, or an FAA-approved equivalent. (2) For pumps, P/N 7631 955 112, replace the pump plunger in accordance with MBB Service Bulletin No. 10-20, dated May 25, 1976, or an FAA-approved equivalent and install a stronger compression spring in accordance with MBB Service Bulletin No. 10-16, dated July 28, 1975, or an FAA-approved equivalent. (b) Within the next 10 hours time in service after the effective date of this AD and thereafter at intervals not to exceed 10 hours time in service since the last inspection, inspect the main rotor gearbox magnetic chip detector plug for the presence of metallic particles. If metallic particles are found, comply with the relevant instructions specified in section 10-1-2 of the MBB BO-105 Maintenance and Overhaul Manual, or an FAA-approved equivalent. (c) An equivalent means of compliance with the requirements in paragraph (b) of the AD, including the initial compliance time and the repetitive inspection interval, may be used in lieu thereof when approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Region, Federal Aviation Administration, c/o American Embassy, Brussels, Belgium, Tel. 513.38.30. This amendment becomes effective September 6, 1977.
90-02-08: 90-02-08 BOEING: Amendment 39-6470. Docket No. 89-NM-149-AD. \n\n\tApplicability: All Model 727 series airplanes certificated in any category. \n\n\tCompliance: Required within the next 3,000 landings after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent nose and main landing gear failure to extend properly due to a disconnect of the landing gear control selector valve actuator arm, accomplish the following: \n\n\tA. Modify the selector valve actuator arm and splined shaft, in accordance with Figure 1, of Boeing Service Bulletin 727-32-0372, dated May 11, 1989, or Revision 2, dated December 14, 1989. \n\n\tB. 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tC. 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 Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6470, AD 90-02-08) becomes effective on February 12, 1990.