Results
98-20-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires replacement of certain landing gear proximity sensor electrical units (PSEU) with improved units. 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 the failure of normal extension and retraction of the landing gear, which could result in collapse of the main landing gear upon landing.
98-20-09: This amendment supersedes an existing airworthiness directive (AD), applicable to all British Aerospace (Jetstream) Model 4101 airplanes, that currently requires repetitive functional testing of the main entrance door, cleaning and lubricating of the "speed" lock and "G" lock systems, and repair, if necessary. This amendment adds a requirement for replacement of the "G" lock rollers with new, improved "G" lock rollers. 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 inability of the main entrance door to open, which could delay or impede passengers from exiting the airplane, or rescue personnel from entering the airplane during an emergency.
58-25-01: 58-25-01 CONVAIR: Applies to All Model 240 Series Aircraft. Compliance required as indicated. During a recent inspection of a Convair 240 aircraft, six rivets out of the total of eight attaching P/N 3540311 to the left-hand elevator torque tube were found sheared. In order to assure airworthiness of the aircraft, the following action is to be taken. (NOTE: A previous Convair service bulletin, issued as a result of a number of reports of rivet failures in this area, recommends replacement of the original rivets with steel rivets. This replacement had not been accomplished in the case mentioned above.) 1. Compliance required as soon as possible but not later than the next 25 hours of operation and every 300 hours thereafter until modified in accordance with item 2. Inspect the 240-3540311 flange fitting attachment to the elevator torque tube, left and right side, for looseness and sheared rivets. If looseness or any sheared rivets are found, compliance with item 2 required prior to further flight. 2. Compliance required not later than the next major overhaul. Replace the eight AN 470-D8 rivets attaching the flange fitting P/N 240-3540311 to the torque tube, left and right side, with eight Q4311-C9-12 steel, drilled shank, rivets or equivalent. Eight close tolerance corrosion resistant steel bolts or four close tolerance corrosion resistant steel bolts and four oversized rivets are acceptable equivalents. (Convair Service Bulletin 240-384 dated October 25, 1950, covers this same subject.)
2012-05-02: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD was prompted by reports of heat damage to the inner wall of the thrust reversers, which could result in separation of adjacent components and consequent structural damage to the airplane, damage to other airplanes, and injury to people on the ground. This AD requires modifying the thrust reverser inner walls, inspecting for damage of the upper and lower inner wall insulation blankets, measuring the electrical conductivity on the aluminum upper compression pads 2 and 3 as applicable, inspecting for discrepancies of the inner wall of the thrust reverser, and corrective actions if necessary. This AD also requires, for certain airplanes, doing various concurrent actions (including replacing the inner wall blanket insulation, installing updated full-authority digital electronic control software, and modifying the thrust reverser inner wall and insulation blankets). We are issuing this AD to correct the unsafe condition on these products.
2012-06-13: We are adopting a new airworthiness directive (AD) for DG Flugzeugbau GmbH Models DG-500 Elan Orion, DG-500 Elan Trainer, DG-500/ 20 Elan, DG-500/22 Elan, DG-500M, and DG-500MB gliders. 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 damage to the bulkhead of the glider's center of gravity (CG) tow hook that, if not detected and corrected, may lead to failure of the fiberglass structure during a winch launch. We are issuing this AD to require actions to address the unsafe condition on these products.
2012-06-16: We are adopting a new airworthiness directive (AD) for Pilatus Aircraft Ltd. Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC- 6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2- H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 airplanes. 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 loose elevator and rudder hinge bolts caused by incorrect torquing and locking of the bolts, which could lead to in-flight failure of the elevator or rudder attachment. We are issuing this AD to require actions to address the unsafe condition on these products.
2012-06-11: We are adopting a new airworthiness directive (AD) for certain Airbus Model A321-131, -211, -212, and -231 airplanes. This AD requires a rotating probe inspection for cracking of the lower panel bore holes of the center wing box (CWB), and corrective actions if necessary. This AD was prompted by reports of incorrect installation of rib pads of the lower aft panel of the CWB due to poor clamping during drilling, and reports that metal chips trapped between panels and stiffeners could impact the fatigue life of CWB panels. We are issuing this AD to detect and correct cracking and damage in the bore holes of the rib pads of the lower forward and aft panels of the CWB which could result in reduced structural integrity of the wings.
75-24-08: 75-24-08 CANADAIR: Amendment 39-2431. Applies to all CL-44D4 and CL-44J airplanes, certificated in all categories, but not altered in accordance with Canadair Service Bulletin 44-478. Compliance required within the next 25 landings, unless already accomplished within the last 275 landings, and thereafter at subsequent intervals not to exceed 300 landings, after the effective date of this AD. To detect fretted, pitted or cracked main landing gear actuator attachment bolts, P/N SD300-55880, SD300-65779 or SD300-65779-12S, inspect and, if necessary, replace bolts in accordance with Canadair Service Information Circular 328-CL44D4, Issue 2 or an approved equivalent inspection and part replacement. Bolts found to be in good condition may be reinstalled provided: (a) they are of a type specified for replacement in the Canadair SIC 328-CL44D4 or are approved equivalent bolts; (b) they have not exceeded the life limits specified in Canadair SIC 328-CL44D4; and (c)they have not been reworked. Equivalent inspection or parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Upon request, with substantiating data submitted through an FAA maintenance inspector, the compliance time of this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective November 25, 1975.
2012-06-22: We are adopting a new airworthiness directive (AD) for all Airbus Model A340-500 and Model -600 series airplanes. This AD requires performing repetitive high frequency eddy current inspections of the external radius on upper horizontal cruciform fitting at frame (FR) 47 on the left- and right-hand sides for cracks, and repairing the cracks if necessary. This AD was prompted by reports that during fatigue testing, damages occurred in the external radius on the upper horizontal cruciform fitting at FR47 on the left- and right-hand sides. We are issuing this AD to detect and correct fatigue cracking, which could adversely affect the structural integrity of the airplane.
2012-06-18: We are adopting a new airworthiness directive (AD) for all Pratt & Whitney PW4050, PW4052, PW4056, PW4060, PW4060A, PW4060C, PW4062, PW4062A, PW4152, PW4156, PW4156A, PW4158, PW4160, PW4460, PW4462, and PW4650 turbofan engines, including models with any dash number suffix. This AD was prompted by reports of five engine in-flight shutdowns and seven unplanned engine removals. This AD requires inspections, cleaning, and engine modifications to address coking in the No. 4 bearing compartment and in the oil pressure and scavenge tubes. We are issuing this AD to prevent an engine fire, a fractured fan drive shaft, and damage to the airplane.
75-17-04: 75-17-04 LOCKHEED: Amendment 39-2300 as amended by Amendment 39-3185. Applies to all Model 382 series airplanes, serial numbers 3946 and 4101 through 4751, certificated in all categories. Compliance required within the next 325 hours' time in service on airplanes which have accumulated 10,000 or more flight hours and thereafter at each "C" check inspection. (a) To detect cracks in the main frames, inspect the frames in accordance with Lockheed Service Bulletin A382-189, or later FAA approved revision, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. (b) In the event a crack or cracks are found, before further flight, contact the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, P.O. Box 20636, Atlanta, Georgia 30320. (c) The inspection required by the A.D. may be discontinued on those airplanes which have been repaired in accordance with Lockheed Service Bulletin A382-189, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. Amendment 39-2300 became effective August 8, 1975. This Amendment 39-3185 becomes effective April 21, 1978.
2012-06-08: We are adopting a new airworthiness directive (AD) for certain Airbus Model A340-211, -212, -311, and -312 airplanes. This AD requires repetitive inspections for cracking at the fastener hole area just above stringer 28, of both left- and right-hand fuselage frame 39.1, and repair if necessary. This AD was prompted by a determination that certain airplanes were not included in a certain airworthiness limitation item (ALI) task (inspections for cracking of the fuselage frame 39.1) and that the inspections must be done to address the identified unsafe condition. We are issuing this AD to detect and correct cracking in the fuselage that could result in reduced structural integrity of the airplane.
68-17-06: 68-17-06 BEECH: Amendment 39-641. Applies to Models 23, A23 and A23A, Serial Numbers M-1 through M-1034; Model A23-19, Serial Numbers MB-1 through MB-264; Model A23-24, Serial Numbers MA-1 through MA-233. Compliance: Required as indicated. To prevent inadvertent engagement of parking brake, in flight, accomplish the following: (A) For Models 23, A23 and A23A, Serial Numbers M-555 through M-1034; Model A23-19, Serial Numbers MB-1 through MB-264; and Model A23-24, Serial Numbers MA-1 through MA-233 modify the master brake cylinders as set forth in (C) or (D). (B) For Models 23, A23 and A23A, Serial Numbers M-1 through M-554, inspect the left master brake cylinder. If brake cylinder Part No. 169-380006 is installed no further action is required. If brake cylinders Part No. VHR-625NL are installed modify as set forth in (C) or (D). (C) Remove the steel ball Part No. A134-9 from the parking brake check valve on both left and right master brake cylinders soas to disengage the parking brake and thereafter operationally check the brakes to assure proper operation; or, (D) Modify the left master brake cylinder in accordance with either Beech Class 1, Service Instruction 0092-220 and drill out the floor board beneath the left brake pedal in accordance with procedures set forth in the aforesaid Beech Service Instruction, or install the improved braking system provided by Beech Service Letter No. 67-12, Revision 1. (E) The foregoing modification must be accomplished prior to further flight except the airplane may be flown in accordance with Federal Aviation Regulation 21.197 to a base where the repair can be performed. This amendment becomes effective August 27, 1968.
75-06-07: 75-06-07 MCDONNELL DOUGLAS: Amendment 39-2126 as amended by Amendment 39-2605 is further amended by Amendment 39-3227. Applies to Douglas Model DC-10-10, -30, -30F, and -40 series airplanes, certificated in all categories, with factory serial numbers as indicated in Douglas Service Bulletin No. 52-132, Revision 1, dated February 21, 1975, or later FAA-approved revisions. \n\n\tTo insure proper functioning of forward passenger doors during emergency operation, accomplish the following: \n\n\t(a)\tCompliance required within the next 300 hours' time in service after the effective date of this AD, unless already accomplished. \n\n\t\t(1)\tInspect the forward passenger door (L & R) operating mechanisms for proper rigging, broken, damaged, or corroded cables, and adjust rigging or replace cables as required, in accordance with Douglas Service Bulletin No. 52-132, Revision 1, dated February 21, 1975, or later FAA-approved revisions. \n\n\t\t(2)\tAfter accomplishment of the inspection per paragraph (a)(1) above, check pneumatic operation of doors (L & R) from both the inside and outside of the aircraft. \n\n\t(b)\tCompliance required on airplanes with 5,000 hours' or more total time in service after the effective date of this AD, unless already accomplished per paragraph (a) above within the last 1500 hours' time in service, and thereafter at intervals not to exceed 2250 hours' time in service from the last inspection. \n\n\t\t(1)\tReinspect the forward passenger door (L & R) mechanism cables, and replace if required, in accordance with Douglas Service Bulletin No. 52-132, Revision 1, dated February 21, 1975, or later FAA-approved revisions. \n\n\t\t(2)\tIf cable(s) has been replaced, recheck pneumatic operation of applicable door(s) from both the inside and outside of the aircraft. \n\n\t\t(3)\tThe repetitive 2250-hour inspections required by paragraph (b) may be discontinued provided stainless steel cables and swivel clevises are installed in accordance with McDonnell Douglas Service Bulletin No. 52-152, dated February 3, 1976, or later FAA-approved revisions. \n\n\t(c)\tCompliance required within the next 5000 hours' time in service after accomplishment of the inspection per paragraph (a) above, and thereafter at intervals not to exceed 5000 hours' time in service from the last inspection. \n\n\t\t(1)\tReinspect the forward passenger door (L & R) mechanism rigging, and adjust if required, in accordance with Douglas Service Bulletin No. 52-132, Revision 1, dated February 21, 1975, or later FAA-approved revisions. \n\n\t\t(2)\tIf rigging has been adjusted, recheck pneumatic operation of applicable door(s) from both the inside and outside of the aircraft. \n\n\t\t(3)\tThe repetitive 5000-hour inspections required by paragraph (c) may be discontinued provided any one of the following combination of McDonnell Douglas Service Bulletins, or later FAA-approved revisions, has been accomplished: \n\n\t\t\t(i)\tS./B 52-118, Revision 1, dated February 14, 1975, (Installation of new cams on control mechanism), S/B 52-140, Revision 4, dated August 29, 1975, (Installation of return springs on reservoir actuator), S/B 52-146, Revision 1, dated November 21, 1975, (Installation of direct drive visible downlock), S/B 52-152, dated February 3, 1976, (Installation of stainless steel cables and swivel clevises); \n\n\t\t\t(ii)\tS/B 52-118, Revision 1, dated February 14, 1975, S/B 52-146, Revision 1, dated November 21, 1975, S/B 52-152, dated February 3, 1976, and S/B 52-154, Revision 1, dated March 1, 1976, (Installation of new reservoir control assembly) \n\n\t\t\t(iii)\tS/B 52-140, Revision 4, dated August 29, 1975, S/B 52-150, dated September 9, 1975, (Installation of combination up/downlock assembly). S/B 52-152, dated February 3, 1976; or \n\n\t\t\t(iv)\tS/B 52-150, dated September 9, 1975, S/B 52-152, dated February 3, 1976, and S/B 52-154, Revision 1, dated March 1, 1976. \n\n\t\t(4)\tThe repetitive 5000-hour inspection required by paragraph (c) may be replaced by satisfactory accomplishment, at 6000-hour intervals of both electrical and pneumatic door operational checks at applicable doors per Douglas Service Bulletin No. 52-132, Revision 1, dated February 21, 1975, or later FAA approved revisions, provided that all service bulletins except SB 52-152, required by any one of the combination of service bulletins in paragraph (c)(3) have been accomplished. \n\n\t(d)\tThe Chief, Aircraft Engineering Division, FAA Western Region, may approve equivalent inspections and modifications upon submittal of substantiating data. \n\n\t(e)\tAircraft may be flown to a base for accomplishment of the maintenance required by this AD per FAR's 21.197 and 21.199. \n\n\tAmendment 39-2126 became effective April 14, 1975. \n\n\tAmendment 39-2605 became effective May 17, 1976. \n\n\tThis amendment 39-3227 becomes effective July 6, 1978.
2012-06-04: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by reports of difficulties in opening the airstair door. This AD requires inspecting the structure and gearbox drain paths for blockages by sealant, and removing any blockages. We are issuing this AD to detect and correct drain paths blocked by sealant, resulting in an airstair door that is unable to be opened, which could hinder evacuation in the event of an emergency.
2012-06-01: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company Model 560XL airplanes. This AD was prompted by reports of jammed or stiff rudder control due to water freezing on the rudder bias cables and pulleys of the stinger. This AD requires modification of the drain installation of the tailcone stinger on the aft canted bulkhead, inspections for drain holes in the forward and aft frames, and modification of the drain holes. We are issuing this AD to prevent ice accumulation on the cables and pulleys of the stinger, which could result in jamming of the rudder and consequent reduced controllability of the airplane.
2012-05-03: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. This AD was prompted by a design review following a ground fire incident and reports of flammable fluid leaks from the wing leading edge area onto the engine exhaust area. This AD requires modifying the fluid drain path in the leading edge area of the wing. We are issuing this AD to prevent flammable fluid from leaking onto the engine exhaust nozzle, which could result in a fire.
76-26-04: 76-26-04 SCOTTISH AVIATION LIMITED: Amendment 39-2793. Applies to Model HP- 137 Mk. 1 Jetstream airplanes, certificated in all categories, except those airplanes which incorporate Scottish Aviation Limited Modification No. 5111. Compliance is required as indicated. To detect cracks in the outer end of each outer wing flap and to prevent possible flap separation from the airplane and possible loss of airplane control, accomplish the following: (a) For airplanes with 500 or more total landings on the effective date of this AD: (1) Comply with paragraph (c) of this AD, before further flight, (except that the airplane may be flown in accordance with FAR Sections 21.197 and 21.199 to a base where the work can be performed, provided that the flaps remain in the fully retracted position for the duration of the flight,) unless already accomplished within the last 50 landings and thereafter continue to comply with paragraph (c) of this AD at intervals not to exceed 50 landings. (2) Comply with paragraph (d) of this AD, within the next 50 landings and thereafter continue to comply with paragraph (d) at intervals not to exceed 500 landings. (b) For airplanes with less than 500 total landings on the effective date of this AD: (1) Comply with paragraph (c) of this AD before the accumulation of 500 landings and thereafter continue to comply with paragraph (c) at intervals not to exceed 50 landings. (2) Comply with paragraph (d) of this AD before the accumulation of 500 landings or within the next 50 landings after the effective date of this AD whichever occurs later, and thereafter continue to comply with paragraph (d) at intervals not to exceed 500 landings. (c) Visually inspect the outer end of each outer wing flap, Part No. 13760B-405 (left) and 13760B-406 (right), for cracks along the lower flange of the end rib and rib doubler using a magnifying glass with at least 5 power in accordance with the instructions contained in Paragraph 3, Part B of Scottish Aviation Limited Service Bulletin No. 9/5, issue 2, dated August 4, 1976, or an FAA-approved equivalent. (d) Inspect the outer end of each outer wing flap, Part No. 13760-B-405 (left) and 13760B-406 (right), for cracks along the lower flange of the end rib and rib doubler using the radiographic technique in accordance with the instructions contained in Paragraph 3, Part C of Scottish Aviation Limited Service Bulletin No. 9/5, issue 2, dated August 4, 1976, or an FAA- approved equivalent. (e) If, during the inspections required by paragraph (c) and (d) of this AD, cracks are found, replace the affected part with a serviceable part of the same part number. NOTE: A "serviceable part" is defined in Note 1, Parts (a) and (b) of Scottish Aviation Limited Service Bulletin, No. 9/5, issue 2, dated August 4, 1976. (f) Compliance with paragraphs (a)(1), (a)(2), (b)(1), and (b)(2) may be discontinued upon the incorporation of Scottish Aviation Limited Modification 5111. This amendment supersedes Amendment 39-2465, (40FR 58129), AD 75-26-16. This amendment becomes effective January 6, 1977.
2012-05-01: We are adopting a new airworthiness directive (AD) for the Eurocopter France (ECF) Model SA-365C, SA-365C1, SA-365C2, SA-365N, SA- 365N1, AS-365N2, AS 365 N3, and SA-366G1 helicopters. This AD was prompted by some reports of deterioration and two reports of failure of Starflex star arm ends. The actions are intended to modify the main rotor frequency adapters to reduce the temperature in the area, to prevent failure of the star arm end, severe vibration, and subsequent loss of control of the helicopter.
2012-05-05: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-215-1A10, CL-215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 Variant) airplanes. This AD was prompted by reports of cracked or broken support bracket assemblies of the emergency water dump pulley. This AD requires inspecting the bracket assembly of the emergency water dump pulley to determine if certain rivets are installed; replacing rivets and installing new stiffeners on the bracket assembly, if necessary; inspecting the stiffeners for the bracket assembly for cracks, deformation, or corrosion, and replacement if necessary; and re-installing the bracket assembly with radius packers. We are issuing this AD to detect and correct failure of the support bracket assembly of the emergency water dump pulley, and in combination with other system failures, such as an engine failure during take off or a pitch control system jam, may result in loss of controllability of the airplane.
95-23-04: This amendment adopts a new airworthiness directive (AD) that is applicable to all British Aerospace Model BAC 1-11 400 series airplanes. This action requires an inspection of the rod ends of the lift dumper to detect drill holes; a dye penetrant inspection to detect any cracking of drilled holes; and replacement of the rod end with an undrilled rod end, if necessary. This amendment is prompted by a report that, during a routine examination of the operating mechanism of the lift dumper, two cracked aft rod ends were found. Investigation revealed that holes had been drilled in the rod ends for grease nipples during manufacturing, and that cracking had developed at the holes. The actions specified in this AD are intended to prevent asymmetric deployment and subsequent lateral control problems due to cracking of either pair of aft rod ends of the operating mechanism of the lift dumper.
2012-04-10: We are adopting a new airworthiness directive (AD) for all Burl A. Rogers (type certificate previously held by William Brad Mitchell and Aeronca, Inc.) Models 15AC and S15AC airplanes. This AD was prompted by reports of intergranular exfoliation and corrosion of the upper and/or lower wing main spar cap angles found on the affected airplanes. This AD requires repetitive inspections of the upper and lower main wing spar cap angles for cracks and/or corrosion and installing inspection access panels. This AD also requires replacing the wing spar cap angles if moderate or severe corrosion is found and applying corrosion inhibitor. We are issuing this AD to correct the unsafe condition on these products.
97-04-18: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, that requires repetitive x-ray inspections to detect cracks in stringers 4 through 7 of the lower skin of the wings, and modification or repair, if necessary. This amendment also requires modification of the stringers of the lower skin of the wings, which terminates the repetitive inspections. This amendment is prompted by reports of fatigue cracking found in stringers 4 through 7 of the lower skin of the wings. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the wings.
2012-04-13: We are superseding an existing airworthiness directive (AD) for all RR model RB211-524G2-T-19, -524G3-T-19, -524H-T-36, and -524H2- T-19; and RB211-Trent 553-61, 553A2-61, 556-61, 556A2-61, 556B-61 556B2-61, 560-61, 560A2-61; RB211-Trent 768-60, 772-60, 772B-60; and RB211-Trent 875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17, and 895- 17 turbofan engines that have a high-pressure (HP) compressor stage 1 to 4 rotor disc with a part number (P/N) listed in Table 1 of the AD. That AD currently requires repetitive inspections of the axial dovetail slots, and follow-on corrective action depending on findings. Since we issued that AD, we determined that the definition of shop visit is too restrictive in the existing AD. This continues to require those repetitive inspections and follow-on corrective actions. This new AD changes the definition of a shop visit to be less restrictive. This AD was prompted by our determination that the definition of ``shop visit'' in the existing AD is too restrictive, in that it would require operators to inspect more often than required to ensure safety. We are issuing this AD to detect cracks in the HP compressor stage 1 and 2 disc posts, which could result in failure of the disc post and HP compressor blades, release of uncontained engine debris, and damage to the airplane.
91-24-05: 91-24-05 MCDONNELL DOUGLAS: Amendment 39-8091. Docket No. 91-NM-30-AD. Supersedes AD 90-15-02, Amendment 39-6651. \n\n\tApplicability: All Model DC-9 and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) airplanes, certified in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent the lap belt connector or buckle from jamming the passenger entrance door hinge, accomplish the following: \n\n\t(a)\tFor airplanes listed in McDonnell Douglas DC-9 Alert Service Bulletin A25-311, dated January 31, 1990: Within six months after August 14, 1990 (the effective date of AD 90-15-02, Amendment 39-6651), modify the forward cabin attendant dual seat, outboard position, lap belt restraint system, in accordance with the Accomplishment Instructions, Paragraph 2, of McDonnell Douglas DC-9 Alert Service Bulletin A25-311, dated January 31, 1990. \n\n\t(b)\tFor airplanes not listed in McDonnell Douglas DC-9 Alert Service Bulletin A25-311, dated January 31, 1990, and having dual forward cabin attendant seats incorporating a restraint system with lap belts independent of the shoulder harness: Within six months after the effective date of this AD, inspect the outboard attendant seat lap belt to determine if the connector or buckle is capable of reaching and interfering with the lower hinge of the passenger entrance door and obstructing the opening of the door. \n\n\t\t(1)\tIf opening of the passenger door entrance is obstructed, prior to further flight, modify the installation so that a shorter lap belt half is utilized, in a manner approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\t\t(2)\tIf opening of the passenger entrance door is not obstructed, no further action is necessary. \n\n\t(c)\tAn alternate 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: This result should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles ACO. \n\n\tNOTE: Any previously-approved alternative method of compliance with AD 90-15-02 is considered to be an approved alternative method of compliance with this AD. \n\n\tNOTE: The procedures described in McDonnell Douglas DC-9 Alert Service Bulletin A25-321, dated August 8, 1991, are considered an approved alternative method of compliance with paragraph (b) of this AD. \n\n\t(d)\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(e)\tThe modification requirements of paragraph (a) of this AD shall be done in accordance with McDonnell Douglas DC-9 Alert Service Bulletin A25-311, dated January 31, 1990. 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 McDonnell Douglas Corporation, Post Office Box 1771, Long Beach, California 90801; Attn: Business Unit Manager, Technical Publications & Technical Administrative Support, C1-L5B (54-60). Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. \n\n\tAirworthiness Directive 91-24-05 supersedes AD 90-15-02, Amendment 39-6651. \n\n\tThis amendment (39-8091, AD 91-24-05) becomes effective on January 7, 1992.