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90-14-07: 90-14-07 MCDONNELL DOUGLAS: Amendment 39-6647. Docket No. 90-NM-104-AD. \n\n\tApplicability: Models DC-9-81, -82, -83, and -87 series airplanes, and Model MD-88 airplanes, delivered between December 30, 1989, and May 8, 1990, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent the loss of elevator control, accomplish the following: \n\n\tA.\tWithin 30 days after the effective date of this AD, conduct a visual inspection to determine the date on the elevator control tab identification tag (P/N 5910413-507/-508). The identification tag is located on the inboard side of the second hinge cutout from the inboard end of the control tab. \n\n\tNOTE: Do not use the date on the P/N 5910413-407/-408 tag, which is similar. \n\n\t\t1.\tConfirm that the elevator control tab assembly has not been changed from that which was delivered on the airplane; \n\n\t\t2.\tIf the elevator control tab assembly has been changed since the delivery of the airplane, the identification tag date of the original tab must be ascertained by inspection of the original part. \n\n\t\t3.\tIf the date on the identification tag is between December 30, 1989, and May 8, 1990, accomplish the following: \n\n\t\t\ta.\tRemove access opening door no. 3523A, left-hand, and 3624A, right-hand. (Reference Maintenance Manual 6-23-00, Figure 2.) \n\n\t\t\tb.\tCheck the elevator control tab fitting in the clevis area using Webster pliers, or equivalent per Douglas Process Specification (DPS) 1.05. Non-heat treated (soft) parts will exhibit a reading of less than 10 on the Webster pliers. Properly heat treated parts will have a reading of 10 or greater on Webster pliers, which is equivalent to Rockwell "B" 78-87, Rockwell "E" 103-107, or Brinell 126-147. \n\n\tNOTE: Remove all paint and primer locally before using Webster pliers. An invalid reading will be obtained if any paint remains in the indentation area. \n\n\tNOTE: Do not use conductivity readings as a methodof acceptance. \n\n\tB.\tIf the fittings are properly heat treated, no further action is required. \n\n\tC.\tIf the fittings have a Webster pliers reading of less than 10, before further flight, remove the fittings and replace them with fittings exhibiting a Webster pliers reading of 10 or greater. \n\n\tD.\tIf only one fitting per airplane is found to be soft, 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. \n\n\tE.\tAny elevator control tab fitting, P/N 5937825-1/-2, that fails the hardness test specified in paragraph A.3.b., above, shall not be subsequently installed on any airplane, unless the fitting is heat treated to meet the requirements in paragraph A.3.b. \n\n\tF.\tReplacement of the elevator control tab fittings with those exhibiting a Webster pliers reading of 10 or greater, constitutes an acceptable alternate means of compliance with the requirements of this AD. \n\n\tG.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 (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Los Angeles ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Los Angeles ACO. \n\n\tAll persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Business Unit Manager of Publications, C1-HCO (54-60). This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 3229 EastSpring Street, Long Beach, California. \n\n\tThis amendment (39-6647, AD 90-14-07) becomes effective on July 23, 1990.
93-01-22: 93-01-22 FOKKER: Amendment 39-8476. Docket 92-NM-177-AD. Applicability: Model F28 Mark 0100 series airplanes; serial numbers 11244 through 11365, inclusive, and 11367; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To ensure that the cabin attendants seated in the forward and aft cabin attendant seats can reach their oxygen masks in emergency situations, accomplish the following: (a) Within 6 months after the effective date of this AD, modify the oxygen drop-out panels of the forward and aft cabin attendant positions, in accordance with Fokker 100 Service Bulletin SBF100-35- 003, dated March 23, 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 modification shall be done in accordance with Fokker 100 Service Bulletin SBF100- 35-003, dated March 23, 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 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, 800 NorthCapitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on March 10, 1993.
93-09-01: 93-09-01 BOEING: Amendment 39-8568. Docket 92-NM-209-AD. \n\n\tApplicability: Model 747-400 series airplanes, passenger and combi configurations, line positions 696 through 906, inclusive; Model 757 series airplanes, line numbers 1 through 488, inclusive; and Model 767 series airplanes, line numbers 1 through 421, inclusive; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent an improper electrical connection of the fire extinguishing system due to a damaged discharge cartridge or electrical connector on the fire extinguisher bottle, accomplish the following: \n\n\t(a)\tWithin 120 days after the effective date of this AD, conduct a detailed visual inspection to detect damage to the discharge cartridges and the electrical connectors on each fire extinguisher bottle installed in auxiliary power unit (APU), cargo compartment, and engine fire extinguishing systems, in accordance with Boeing Alert Service Bulletin 747-26A2210, dated October 29, 1992 (for Model 747-400 series airplanes); Boeing Alert Service Bulletin 757-26A0032, dated October 22, 1992, as amended by Notice of Status Change 757-26A0032 NSC 2, dated February 4, 1993 (for Model 757 series airplanes); or Boeing Alert Service Bulletin 767-26A0089, dated October 22, 1992 (for Model 767 series airplanes); as applicable. The operational tests of the discharge cartridges specified in the Accomplishment Instructions of the applicable service bulletin are not required to be performed prior to accomplishing the detailed visual inspection required by this paragraph. Since an operational test of the fire extinguishing system can be successfully completed even if there is a damaged pin or connector, this inspection must be performed by visually examining the discharge cartridge and the electrical connector. \n\n\t(b)\tIf any damage is detected during the inspection required by paragraph (a) of this AD, prior to further flight, replace the damaged item with a serviceable part and perform an operational test of the bottle discharge cartridge circuit in accordance with Boeing Alert Service Bulletin 747-26A2210, dated October 29, 1992 (for Model 747-400 series airplanes); Boeing Alert Service Bulletin 757-26A0032, dated October 22, 1992, as amended by Notice of Status Change 757-26A0032 NSC 2, dated February 4, 1993 (for Model 757 series airplanes); or Boeing Alert Service Bulletin 767-26A0089, dated October 22, 1992 (for Model 767 series airplanes); as applicable. Any discrepancy detected as a result of the operational test must be corrected prior to further flight. \n\n\t(c)\tThe cross-wiring end-to-end functional tests required by AD 89-03-51, Amendment 39-6213, do not have to be accomplished following performance of the inspection required by paragraph (a) of this AD, if the inspection is accomplished one discharge cartridge at a time. \n\n\t(d)\tAs of the effective date of this AD, no person shall install a fire extinguisher bottleon any airplane unless the discharge cartridge and electrical connector have been inspected in accordance with this AD. \n\n\t(e)\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, Seattle 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, Seattle ACO. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. \n\n\t(f)\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(g)\tThe inspection and replacement shall be done in accordance with Boeing Alert Service Bulletin 747-26A2210, dated October 29, 1992 (for Model 747-400 series airplanes); Boeing Alert Service Bulletin 757-26A0032, dated October 22, 1992, and Notice of Status Change 757-26A0032 NSC 2, dated February 4, 1993 (for Model 757 series airplanes); or Boeing Alert Service Bulletin 767-26A0089, dated October 22, 1992 (for Model 767 series airplanes); as applicable. 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 Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. 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. \n\n\t(h)\tThis amendment becomes effective on June 9, 1993.
77-01-07: 77-01-07 PRATT & WHITNEY AIRCRAFT: Amendment 39-2807. Applies to all Pratt & Whitney Aircraft JT9D-3A, -7, -7H, -7A, -7AH, -7F and -20 turbofan engines containing fifth stage turbine hubs, P/N 704705, 714905, 718905, 719205, and 726805. Compliance required as indicated. To prevent cracking and possible failure of fifth stage turbine hubs, the cyclic life limits on these parts have been reduced below the figures currently approved. Unless already accomplished, remove from service fifth stage turbine hubs prior to reaching the revised life limit listed below or within the next 25 cycles in service after the effective date of this AD, whichever is later. Hub Part Number Previous Life Limit (Cycles) Revised Life Limit (Cycles) 704705 15,000 7,000 714905 15,000 6,000 718905 8,000 5,000 719205 8,000 5,000 726805 8,000 5,000 Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering & Manufacturing Branch, New England Region, may adjust the 25 cycle compliance interval to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. (NOTE: Pratt & Whitney Alert Service Bulletin No. 4671 pertains to this subject.) This amendment becomes effective upon publication in the Federal Register.
66-03-02: 66-03-02 HUGHES: Amdt. 39-181, Part 39, Federal Register January 14, 1966. Applies to Models 269A, 269A-1, and 269B Helicopters. Compliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished. To eliminate a possible navigational hazard, accomplish the following: (a) On helicopters with the 12-volt electrical system, remove the existing tail position light bulb and replace it with General Electric No. 1777 bulb or FAA-approved equivalent. (b) On helicopters with the 24-volt electrical system, remove the existing bulb and replace it with a Grimes No. 1683 bulb or FAA-approved equivalent. (Hughes Service Notices Nos. 2A-54 (269A), 2A-1-21 (269A-1 and (2B-22), (269B) dated October 28, 1965, pertain to this same modification.) This directive effective January 14, 1966.
90-18-05: 90-18-05 BOEING: Amendment 39-6713. Docket No. 89-NM-280-AD. \n\n\tApplicability: Model 767 series airplanes, line numbers 002 through 299, certificated in any category. \n\n\tCompliance: Required within the next 18 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent structural failure of the vertical stabilizer from overpressurization in the event of a rupture of the fuselage under the dorsal fin, accomplish the following: \n\n\tA.\tInstall a cover plate and a panel assembly over the lightening and access holes in the vertical stabilizer forward closure rib, in accordance with Boeing Alert Service Bulletin 767- 55A0007, dated June 22, 1989. \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 (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \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 Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW, 5th Floor, Renton, Washington, or Seattle Aircraft Certification Office, 1601 Lind Avenue SW, 2nd Floor, Renton, Washington. \n\n\tThis amendment (39-6713, AD 90-18-05) becomes effective on October 9, 1990.
78-11-09: 78-11-09 SHORT BROTHERS LIMITED: Amendment 39-3217. Applies to Model SD3-30 airplanes, S/Ns 3003 through 3010, certificated in all categories. Compliance required prior to accumulating 5000 landings or within 100 landings after the effective date of this AD, whichever occurs later, unless already accomplished. To prevent failure of the main landing gear swivel assembly, remove the swivel sub- assembly, P/N 17684-1, -3, -7, -9, or -9A, the flange collar, P/N SD3-40-0023, and associated fasteners and replace with a swivel sub-assembly, P/N 17684-13, flanged collar, P/N SD3-40- 0040xB, and new fasteners all in accordance with paragraph 2, "Accomplishment Instructions", of Short Brothers Limited Mandatory Service Bulletin SD3-32-03, Revision 3, dated March 3, 1978, or an FAA-approved equivalent, and paragraph 10, "Accomplishment Instructions" of Menasco Manufacturing Service Bulletin 32-8, Revision 1, dated January 24, 1978, or an FAA- approved equivalent. This amendmentbecomes effective June 6, 1978.
97-03-13: 97-03-13 CASA: Amendment 39-9918. Docket 96-NM-89-AD. Applicability: All Model C-212 series airplanes, certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent the settings for therudder pedals from restricting the flight crew in its ability to move the rudder to its maximum certified deflection, which could result in insufficient deflection and consequent reduction in controllability of the airplane, accomplish the following: (a) As of the effective date of this AD, prior to each flight, adjust the left and right rudder pedal setting mechanisms in accordance with CASA Flight Operation Instructions COM 212-245, Revision 1, dated November 16, 1993, until the modification required by paragraph (b) of this AD has been accomplished. (b) Within 6 months after the effective date of this AD, modify the left and right rudder pedal assemblies by installing stops and other parts, in accordance with CASA Service Bulletin SB-212-27-47, Revision 1, dated April 13, 1994. Accomplishment of this modification constitutes terminating action for the repetitive adjustments required by paragraph (a) of this AD. (c) For CASA Model C-212 series airplanes listed in CASA Service Bulletin SB-212-27-47, Revision 1, dated April 13, 1994: Within 6 months after the effective date of this AD, replace the attachment rails for the pilot and co-pilot seats in accordance with CASA Service Bulletin SB-212-27-47, Revision 1, dated April 13, 1994. (d) 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 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The actions shall be done in accordance with CASA Flight Operation Instructions COM 212-245, Revision 1, dated November 16, 1993; and CASA Service Bulletin SB-212-27-47, Revision 1, dated April 13, 1994, which contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1-5, 8, 14-17, 19-23, 26, 34, 35 1 April 13, 1994 6, 7, 9-13, 18, 24, 25, 27-33 Original September 14, 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 Construcciones Aeronauticas, S.A., Getafe, Madrid, Spain. 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. (g) This amendment becomes effective on March 14, 1997.
96-10-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires inspections of the handrail assembly at the main entrance door to detect loose or missing rivets, abnormal movement between the handrail pivot-tube and the spigot that attaches to the bearing assembly, and cracks on the handrail pivot-tube. It also requires repair or replacement of the assembly, if necessary, and provides for two optional terminating actions. This amendment is prompted by a report indicating that fatigue cracks and loose rivets were found on the handrail assembly of the main passenger entrance door on an in-service airplane. The actions specified by this AD are intended to prevent these conditions, which can lead to the failure of the door handrail assembly; such failure could allow the door to fall free and subsequently cause injury to people on the airplane or on the ground.
94-25-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires installation of additional venting between the flight deck and the passenger compartment. This amendment is prompted by results of an engineering analysis that revealed there was insufficient venting in the forward stowage and wardrobe assembly. The actions specified by this AD are intended to prevent injury to the crew resulting from structural failure of the bulkhead between the flight deck and the passenger compartment in the event of windshield failure and subsequent rapid decompression.