Results
2009-24-14: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: It has been found the possibility of elevator mass balance fasteners becoming slack under certain conditions. The loose of at least two fasteners may lead to an unbalance condition, which may induce flutter on airplane elevators. We are issuing this AD to require actions to correct the unsafe condition on these products.
2009-17-02: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During refueling, the ground crew detected smoke from the refuel/defuel panel illuminated placard 160VU. * * * * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2009-17-03: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: The airbrake upper crossbeam on an airplane failed in-flight. The crossbeam failure caused damage to the rudder control system, resulting in loss of rudder control. Loss of rudder control will cause handling difficulties particularly during take-off, approach, and landing phases in cross winds. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
92-08-11: 92-08-11 BOEING: Amendment 39-8222. Docket No. 91-NM-212-AD.\n\n\tApplicability: Model 737-300, 737-400, and 737-500 series airplanes, and Model 757-200 series airplanes; equipped with TransAero P/N 91465 series single flight attendant seats identified in TransAero Service Bulletin No. 192, Revision C, dated August 12, 1991, certificated in any category. \n \n\tCompliance: Required as indicated, unless accomplished previously.\n\n\tTo prevent failure of the seat pans and possible injury to flight attendants, accomplish the following:\n\n\t(a)\tWithin 60 days after the effective date of this AD, inspect the front edge of the affected seat pans for areas of abnormal flexibility in accordance with paragraph C. of TransAero Service Bulletin No. 192, Revision C., dated August 12, 1991.\n\n\t\t(1)\tIf no damage is detected, repeat the inspection at intervals not to exceed 375 flight hours.\n\n\t\t(2)\tIf damage is detected, prior to further flight, accomplish either subparagraph (a)(2)(i) or (a)(2)(ii):\n\n\t\t\t(i)\tInstall a placard stating that the damaged seat is not to be occupied; or\n\n\t\t\t(ii)\tReplace the seat pan with a serviceable seat pan of the same part number, and continue to inspect thereafter at intervals not to exceed 375 flight hours in accordance with paragraph (a) of this AD.\n\n\t(b)\tWithin 18 months after the effective date of this AD, modify all single flight attendant seat pans in accordance with TransAero Service Bulletin No. 192, Revision C, dated August 12, 1991.\n\n\t(c)\tThe inspections required by paragraph (a) of this AD may be terminated upon accomplishing the modification described in TransAero Service Bulletin 192, Revision C, dated August 12, 1991.\n\n\t(d)\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate.\n\n\tNOTE: The request should be forwarded through anFAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO.\n\n\t(e)\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\t(f)\tThe inspection and modification shall be done in accordance with TransAero Service Bulletin No. 192, Revision C, dated August 12, 1991, which contains the following list of effective pages:\n\n\tPage number\tRevision level\tDate\n\n\tCover\tC\tAugust 12, 1991\n\n\tSheets i, ii,\tC\t(Not dated)\n\tand iii\n\n\tiv\t(None)\t(Not dated)\n\n\t1 - 24\t(None)\t(Not dated)\n\nThis 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 TransAero Industries, Inc., 502 North Oak Street, Inglewood, California 90302-2942. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC.\n\n\t(g)\tThis amendment becomes effective on May 29, 1992.
91-11-10: 91-11-10 MCDONNELL DOUGLAS: Amendment 39-7008. Docket No. 90-NM-249-AD. \n\n\tApplicability: Model DC-9-15F, -32F, -33F, and -34F series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent loss of control following the opening of the main deck cargo door, accomplish the following: \n\n\tA.\tWithin 30 days after the effective date of this AD, add the following procedure to the FAA-approved Airplane Flight Manual (AFM) Emergency Procedures. This may be accomplished by inserting a copy of this AD in the AFM. \n\nCARGO DOOR OPENS DURING FLIGHT \n\nMAIN CARGO DOOR OPENS AFTER TAKEOFF: \n\n\n\nSeries 15F\t\nSeries 32F, 33F, 34F \n\n\n\nDirectional Control.........................\nMaintain\nMaintain\n Landing Gear.................................\nUp\t\nUp \nFlaps..................................................\nTakeoff\t\n--- \nFlaps/Slats.......................................\n ---\t\nTakeoff\n Land as soon aspractical. \n\n\n\t \n\tNOTE: The airplane yaw to the right may require almost full left rudder and aileron inputs to correct. Left turns may be more controllable than right turns. Return to the runway should be accomplished with coordinated turns using very little bank (less than 20 degrees), and with speed appropriate to the flap/slat position. Loss of communication may result if the cargo door strikes the upper VHF antenna (try another radio). Do not change configuration until lined up for straight-in landing. \n\n\nMAIN CARGO DOOR OPENS DURING CLIMB, CRUISE, DESCENT, OR APPROACH: \n\n\nDirectional control:\nMaintain \t\nMaintain \t\n\n\nRapid decompression/emergency descent: \n\n\nAccomplish\n(if required)\nAccomplish \n(if required) \n\n\tNOTE: Do not exceed recommended structural damage airspeed during descent. \n\tAfter level-off, slow to minimum maneuvering speed. \n\tLand as soon as practical. Accomplish "on final approach" items. \n\nMAIN CARGO DOOR OPENS ON FINAL APPROACH: \n\n\nLanding Gear\nDown\nDown\nFlaps\n30°\n --- \nFlaps/Slats\n---\n25°/Ext \nIAS\nEstablish*\nEstablish* \n\n \t*Reduce to normal approach speed using normal wind additives. \n\n\tNOTE: There may be indicated airspeed and altitude variations due to disturbed airflow across the static ports. \n\n\tB.\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Operations Inspector who may concur or comment then send it to the Manager, Los Angeles 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 information from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Business Unit Manager, Technical Publications, C1-HCW (34-60). This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington, or the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. \n\n\tThis amendment (39-7008, AD 91-11-10) becomes effective on July 1, 1991.
88-24-06: 88-24-06 McDONNELL DOUGLAS: Amendment 39-6067. Applies to McDonnell Douglas Model DC-9-10 through -80 series, Model MD-88, and C-9 (Military) series airplanes, Fuselage Numbers 2 through 1510, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo preclude separation of the forward passenger or aft service door assist handle, accomplish the following: \n\n\tA.\tWithin 45 days after the effective date of this AD, inspect the forward entry and aft service doors assist handles and attachment hardware to ascertain if the proper assist handle retaining parts are installed and if the self-locking plate nuts retain appropriate locking torque, in accordance with the Accomplishment Instructions of McDonnell Douglas Alert Service Bulletin A25-302, dated September 21, 1988. If any part is found to be improperly installed, replace prior to further flight, in accordance with the Service Bulletin. \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, Los Angeles 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, Los Angeles 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 information from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846; Attention: Director of Publications, C1-L00 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. \n\n\tThis amendment, 39-6067, becomes effective December 2, 1988.
2009-24-12: The FAA is adopting a new airworthiness directive (AD) for Honeywell International Inc. LTS101 series turboshaft and LTP101 series turboprop engines with certain gas generator turbine discs installed. This AD requires reducing the life limits for certain gas generator turbine discs. This AD results from an error in a change to the engineering drawing for the gas generator turbine disc from which Honeywell manufactured 260 discs. We are issuing this AD to prevent rupture of the gas generator turbine disc, which could result in uncontained engine failure and damage to the aircraft.
85-01-07: 85-01-07 BOEING: Amendment 39-4983. Applies to Model 737 series airplanes certificated in all categories listed in Boeing Service Bulletin 737-57-1087, Revision 4, dated November 18, 1983. Unless previously accomplished, prior to the accumulation of 10,000 landings or within 180 days or 2500 flight cycles after the effective date of this AD, whichever occurs later, accomplish the following to detect cracking which may lead to failure of the body buttock line (BBL) 70.85 rib upper chord: \n\n\tA.\tVisually inspect the BBL 70.85 rib upper chord for cracks in accordance with Table I of the Flight Safety Addendum of Boeing Service Bulletin 737-57-1087, Revision 4, or later FAA approved revisions. Repeat the inspections at intervals not to exceed 5000 landings. \n\n\tB.\tVisually inspect the BBL 70.85 rib upper chord repair angles installed in accordance with Boeing Service Bulletin 737-57-1087, Revision 2, or earlier FAA approved revisions, for cracks in accordance with Table I of the Flight Safety Addendum of Boeing Service Bulletin 737- 57-1087, Revision 4 or later FAA approved revisions. Repeat the inspection at intervals not to exceed 5000 landings. \n\n\tC.\tIf cracks are detected, prior to further flight replace or repair cracked parts in accordance with Table I of the "Accomplishment Instructions" in Boeing Service Bulletin 737- 57-1087, Revision 4, or later FAA approved revisions; and continue the repetitive inspections of paragraph A., above, at intervals not to exceed 5000 landings. \n\n\tD.\tParts repaired in accordance with the "stop drilling" interim action (a) in Table I of the "Accomplishment Instructions" of Boeing Service Bulletin 737-57-1087, Revision 4, must be reinspected at intervals not to exceed 1500 landings and must be repaired in accordance with Part III or IV of Boeing Service Bulletin 737-57-1087, Revision 4, or later FAA approved revisions, within two years of the accomplishment of the interim repair. \n\n\tE.\tThe requirements of this AD areterminated if the Preventative Modification Part III or the Special Modification Part IV of the Accomplishment Instructions in Boeing Service Bulletin 737-57-1087, Revision 3, or later FAA approved revisions, is incorporated. \n\n\tF.\tAirplanes may be ferried to a maintenance base for repairs or replacement of parts in accordance with FAR 21.197 and 21.199 with prior approval of the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tG.\tFor the purpose of this AD, and when approved by an FAA Maintenance Inspector, the number of landings may be computed by dividing each airplane's time in service by the operator's fleet average time from takeoff to landing for the aircraft type. \n\n\tH.\tAlternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, Seattle, Washington. \n\n\tI.\tUpon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of an operator, if the request contains substantiating data to justify the adjustment period. \n\n\tAll persons affected by this directive who have not already received these 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 also be examined at FAA, Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective February 25, 1985.
89-11-01: 89-11-01 BOEING: Amendment 39-6208. \n\tApplicability: Model 737-300 series airplanes not equipped with Electronic Flight Instrument System (EFIS), certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo preclude the possibility of loss of the primary attitude display to both pilots during Instrument Meteorological Conditions (IMC) or during extended range flight, accomplish the following: \n\n\tA.\tWithin 10 days after the effective date of this AD, inspect the Inertial Reference Units (IRU) installed to determine the part number and modification status. \n\n\t\t1.\tIf both are part number S242T101-103 and neither have Mod 6 implemented, add the following restriction to the Limitations Section of the FAA-approved Airplane Flight Manual (AFM). This may be accomplished by inserting a copy of this AD in the AFM: \n\n\t\t\ta.\t"Instrument approach conditions are restricted to a 1000 foot ceiling and 3 miles visibility." \n\n\t\t\tb.\t"No Extended Range Operations (ETOPS)." \n\n\t\t2.\tIf one IRU is part number S242T101-103 without Mod 6 implemented, and the other IRU either has Mod 6 or is an approved part number other than S242T101-103, add the following restriction to the Limitations Section of the FAA-approved Airplane Flight Manual (AFM). This may be accomplished by inserting a copy of this AD in the AFM: \n\n\t\t\ta.\t"Instrument approach minimums are restricted to a 200 foot Decision Height (DH) and 1800 Runway Visual Range (RVR), (Category I)." \n\n\t\t\tb.\t"No Extended Range Operations (ETOPS)." \n\n\t\t3.\tInstall a placard on the control cabin center instrument panel clearly defining the appropriate limitation applicable to each airplane, as required by paragraphs A.1. and A.2., above. A placard restricting ETOPS is not required if ETOPS has not been approved for the airplane. Placard wording and location shall be approved by an FAA Principal Operations Inspector (POI). \n\n\tB.\tThe limitations on each airplane, as requiredby paragraph A., above, shall remain in effect until both IRU's, P/N S242T101-103, have been modified in accordance with Honeywell Service Bulletin HG1050AD-34-04, dated December 1, 1987, or Honeywell Service Bulletin HG1050AD-34-03, Revision A, dated February 15, 1989, or have been replaced by IRU P/N S242T101-105. \n\n\tC.\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) or Principal Operations Inspector (POI), as appropriate, who will either concur or comment, and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base to comply with the requirements of this AD. \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 Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6208, AD 89-11-01) becomes effective on May 22, 1989.
90-26-09: 90-26-09 BOEING: Amendment 39-6835. Docket No. 90-NM-42-AD. \n\n\tApplicability: Model 727 series airplanes, listed in Boeing Service Bulletin 727-53- 0084, Revision 4, dated August 2, 1990, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent loss of cabin pressurization due to delamination, cracking, and/or corrosion of fuselage skin circumferential joints, accomplish the following: \n\n\tA.\tWithin the next 15 months after the effective date of this AD, accomplish an external visual inspection in accordance with Part II.A. of the Accomplishment Instructions of Boeing Service Bulletin 727-53-0084, Revision 4, dated August 2, 1990, and a low frequency eddy current (LFEC) inspection in accordance with Part II.B. in the Accomplishment Instructions of the service bulletin. \n\n\t\t1.\tIf no corrosion is detected: \n\n\t\t\ta.\tRepeat the external visual inspection at intervals not to exceed 15 months; and \n\n\t\t\tb.\tRepeat theLFEC inspection at intervals not to exceed 30 months; and \n\n\t\t\tc.\tWithin 48 months after the effective date of this AD, conduct an internal close visual inspection in accordance with Part II.C. in the Accomplishment Instructions of the service bulletin. Repeat this inspection at intervals not to exceed 48 months. \n\n\t\t2.\tIf corrosion is detected, repair prior to further flight, in accordance with Part III of the Accomplishment Instructions of the service bulletin. \n\n\tB.\tWithin the next 3,000 landings or 30 months after the effective date of this AD, whichever occurs first, accomplish a high frequency eddy current (HFEC) inspection in accordance with Part II.D. of the Accomplishment Instructions of Boeing Service Bulletin 727- 53-0084, Revision 4, dated August 2, 1990. \n\n\t\t1.\tIf no cracking is detected, repeat the inspection at intervals not to exceed 4,000 landings or 48 months, whichever occurs first. \n\n\t\t2.\tIf cracking is detected, repair before further flight, in accordance with Part III in the Accomplishment Instructions of the service bulletin. \n\n\tC.\tIf the sealant has deteriorated but no cracking or corrosion is detected as a result of the inspections required by paragraphs A. and B. of this AD, reseal in accordance with Figure 5 or 6, as applicable, of Boeing Service Bulletin 727-53-0084, Revision 4, dated August 2, 1990. \n\n\tD.\tModification in accordance with Part III in the Accomplishment Instructions of Boeing Service Bulletin 727-53-0084, Revision 4, dated August 2, 1990, constitutes terminating action for the inspections required by this AD for the area modified. \n\n\tE.\tModification in accordance with Part IV in the Accomplishment Instructions of Boeing Service Bulletin 727-53-0084, Revision 4, dated August 2, 1990, constitutes terminating action for the inspections required by paragraph B. of this AD. \n\n\tF.\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\tG.\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 Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. \n\n\tThis amendment (39-6835, AD 90-26-09) becomes effective on January 22, 1991.