Results
2000-22-17: This amendment adopts a new airworthiness directive (AD) that applies to all SOCATA - Groupe AEROSPATIALE (Socata) Models MS 880B, MS 885, MS 892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS 894E, Rallye 100S, Rallye 150T, Rallye 150ST, Rallye 235C, and Rallye 235E airplanes. This AD requires you to repetitively inspect, and, if necessary, replace elevator clevis and rudder governor control clevis that are too thin. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified in this AD are intended to correct rudder and elevator control clevis that are too thin because of abnormal wear, with consequent failure of the rudder and elevator clevis. Such failure could lead to loss of directional or pitch control.
2008-14-02: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. Model AB 139 and AW 139 helicopters. This AD results from mandatory continuing airworthiness information (MCAI) issued by the European Aviation Safety Agency (EASA), the Technical Agent for Italy, with which we have a bilateral agreement, which indicates that the Agusta AB 139's and AW 139's Fuselage Frame 5700 middle section is prone to fatigue damage. The actions are intended to detect cracks in the fuselage frame structure and to prevent structural failure in this area.
50-08-01: 50-08-01 SIKORSKY: Applies to All Model S-51 Helicopters. Compliance required at each 25-hour inspection. Inspect the upper longerons, Drawing S-520879, of the S-10-20-3003 tail cone mounting assembly for cracks in the area adjacent to the generator support plate and clamps, and in all the welds on the longerons adjacent to the clamps. If cracks are found, the defective member should be reinforced or replaced prior to continuing flight. (Sikorsky Service Information Circular No. 38, Revision A, dated January 4, 1950, covers this same subject.) This supersedes AD 48-11-03.
88-10-03: 88-10-03 MCDONNELL DOUGLAS: Amendment 39-5906. Applies to McDonnell Douglas Model DC-10 and KC-10 series airplanes, as listed in McDonnell Douglas Service Bulletin A24-140, dated March 24, 1988, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo prevent fire and smoke resulting from chafing of the DC Ground Service Bus power feeder cable against the forward right cabin entrance door push-pull cable, accomplish the following: \n\n\tA.\tWithin 30 days after the effective date of this airworthiness directive (AD), inspect the DC power feeder cable for evidence of chafing and inspect for minimum clearance between the DC power feeder cable and the forward right cabin entrance door push-pull cable, in accordance with the Accomplishment Instructions of McDonnell Douglas Service Bulletin A24-140, dated March 24, 1988. \n\n\t\t1.\tIf the clearance is less than the minimum allowable, modify the installation in accordance with the service bulletin. \n\n\t\t2.\tIf there is evidence of chafing on the DC power feeder cable, repair the power cable in accordance with the service bulletin. \n\n\tB.\tAlternate means of compliance or adjustment of the compliance time, which provide an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \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). This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis Amendment becomes effective May 20, 1988.
2008-14-08: We are adopting a new airworthiness directive (AD) for all Boeing Model 747 airplanes listed above. This AD requires repetitive inspections for broken or missing fasteners in the single-row hinge fasteners of the forward and aft cargo doors, and related investigative/corrective actions. This AD results from reports of broken and missing fasteners in the hinges of the forward and aft cargo doors in both the body hinge segments and the door hinge segments. We are issuing this AD to detect and correct broken or missing fasteners in the hinge segments with a single fastener row, which could lead to opening of the cargo door during flight and result in rapid decompression of the airplane.
88-24-04 R1: 88-24-04 R1 MCDONNELL DOUGLAS: Amendment 39-6066 as revised by Amendment 39-6510. Docket No. 89-NM-199-AD. \n\n\tApplicability: McDonnell Douglas Model DC-9, C-9 (Military), and DC-9-80 (MD-80) series airplanes, and Model MD-88 airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent fire in the aft accessory compartment, accomplish the following: \n\n\tA.\tWithin 30 days or 300 flight hours time-in-service after December 2, 1988 (the effective date of AD 88-24-04, Amendment 39-6066), whichever occurs first, or upon the accumulation of 3,000 flight hours time-in-service since new, whichever occurs later, accomplish the following: \n\n\t\t1.\tCheck for evidence of fuel on the APU exhaust ducting and in the surrounding area in the aft accessory compartment, including the insulation blankets. Remove any fuel before the next APU start attempt. \n\n\t\t2.\tInstall a placard on or above the center instrument panel in a location that allows it to be in full view of both pilot and co-pilot, and on the aircraft logbook, stating the following: "DO NOT ATTEMPT TO RESTART APU AFTER A FALSE START UNTIL CHECK OF AFT ACCESSORY COMPARTMENT FOR FUEL IS ACCOMPLISHED." \n\n\t\t3.\tAdd the following 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: "DO NOT ATTEMPT TO RESTART APU AFTER A FALSE START UNTIL CHECK OF AFT ACCESSORY COMPARTMENT FOR FUEL IS ACCOMPLISHED." \n\n\tB.\tWithin 36 months from the effective date of this amendment, inspect, modify, and repair the APU exhaust duct assembly in accordance with procedures described in Figures 3, 4, and 5 of McDonnell Douglas DC-9 Service Bulletin A49-40, Revision 1, dated May 16, 1989. Once the actions required by this paragraph are accomplished, the placard and AFM change required by paragraph A., above, may be removed. \n\n\tC.\tWithin 36 months from the effective date of this amendment, trim the ends of the APU forward lower frame and modify the aft pressure bulkhead insulation blanket, in accordance with procedures described in McDonnell Douglas DC-9 Service Bulletin 53-229, dated July 6, 1989. \n\n\tD.\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 will either concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office. \n\n\tE.\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 uponrequest to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Group Leader, DC-9/MD-80, Technical Publications, C1-HCP (54-60). These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. \n\n\tThis AD revises AD 88-24-04, Amendment 39-6066. \n\n\tThis amendment (39-6510, AD 88-24-04 R1) becomes effective on March 19, 1990.
2008-13-20: We are adopting a new airworthiness directive (AD) for certain Boeing Model 757 airplanes equipped with Rolls Royce RB211-535E engines. This AD requires repetitive inspections for signs of damage of the aft hinge fittings and attachment bolts of the thrust reversers, and related investigative and corrective actions if necessary. This AD results from reports of several incidents of bolt failure at the aft hinge fittings of the thrust reversers due to, among other things, high operational loads. We are issuing this AD to prevent failure of the attachment bolts and consequent separation of a thrust reverser from the airplane during flight, which could result in structural damage to the airplane.
87-26-04: 87-26-04 BRITISH AEROSPACE (BAe): Amendment 39-5804. Applies to Model BAe- 146 series airplanes listed in BAe Service Bulletin 24-30-00757A, Revision 1, dated September 5, 1986, certificated in any category. Compliance is required within 6 months after the effective date of this AD, unless previously accomplished. To prevent battery depletion and subsequent loss of Essential DC and Emergency DC busbars accomplish the following: A. Modify the DC power distribution in accordance with British Aerospace BAe-146 Aircraft Modification Service Bulletin 24-30-00757A, Revision 1, dated September 5, 1986. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197and 21.199 to operate airplanes to a base for the accomplishment of the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to British Aerospace, Inc., Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective February 1, 1988.
2008-13-11: 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: \n\n\tService experience indicates that as aircraft become older, they are more likely to exhibit indications of corrosion. \n\nAdditionally, the FAA has reviewed the service experience and finds this action to be necessary based upon that service experience. We are issuing this AD to require actions to correct the unsafe condition on these products.
82-06-08: 82-06-08 SIKORSKY AIRCRAFT DIVISION: Amendment 39-4348. Applies to Model S-76A helicopters, prior to S/N 760207, certificated in all categories. Compliance is required within the next 50 hours' time in service after the effective date of the AD unless already accomplished. To prevent possible loss of both DC generators due to loss of ground, modify DC junction box ground circuits in accordance with Sikorsky Alert Service Bulletin 76-24-7, dated February 3, 1982, or an equivalent means of compliance approved by the Chief, Boston Aircraft Certification Branch, Aircraft Certification Division, New England Region, Federal Aviation Administration. This amendment becomes effective March 22, 1982.
2008-12-11: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. Model A109E, A109S, and A119 helicopters. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority to identify and correct an unsafe condition on an aviation product. The European Aviation Safety Agency (EASA), the technical agent for Italy, with which we have a bilateral agreement, states in the MCAI: During a ground test of the emergency door release system, the Pilot doors failed to disengage. Investigation determined that the reason of this malfunction is interference between the lower hinge and the fuselage structure. This condition, if not corrected, creates the risk of non-disengagement of the Pilot- and/or Co-pilot doors during an emergency, inhibiting the evacuation of the aircraft, possibly resulting in injuries to the occupants. This AD requires actions that are intended to address the unsafe condition caused by interference between thepilot or co-pilot door lower hinge and the fuselage structure.
89-10-05: 89-10-05 BRITISH AEROSPACE: Amendment 39-6212. Applicability: Model BAe 125-800 series airplanes, Serial Numbers 8091 to 8147, certificated in any category. Compliance: Required within 7 days after the effective date of this AD, unless previously accomplished. To prevent loss of electrical power and eliminate a potential fire hazard, due to chafed cable looms, accomplish the following: A. Perform a one-time inspection of the electrical cable looms above panel DA-E for cable chafing and adequate clearance from adjacent equipment, in accordance with British Aerospace Service Bulletin 24-270, dated March 20, 1989. If any cable is chafed or if clearance is insufficient, prior to further flight, repair in accordance with the service bulletin. B. 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region.NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may concur or comment, and then send it to the Manager, Standardization Branch, ANM-113. C. 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 the requirements of this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. This information 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. This amendment (39-6212, AD 89-10-05) becomes effective on May 26, 1989.
2000-23-31: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9-82 (MD-82) and DC-9-83 (MD-83) series airplanes, and Model MD-88 airplanes. This action requires deactivating the left and right lower sidewall lights located in the passenger compartment. This action is necessary to prevent arcing and heat damage of the Luminator fluorescent lamp holders located outboard of the Passenger Service Unit panel, which could result in smoke and fire in the passenger compartment. This action is intended to address the identified unsafe condition.\n\n\tThe incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of December 13, 2000.\n\n\tComments for inclusion in the Rules Docket must be received on or before January 29, 2001.
2008-12-01: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Model 525 airplanes. This AD requires you to inspect for missing firewall sealant between the aft firewall assembly and seal assembly; and, if you find that firewall sealant is missing, seal with firewall sealant between the aft firewall assembly and seal assembly. This AD results from a report that firewall sealant may not have been applied between the aft firewall assembly and seal assembly during manufacture of certain Model 525 airplanes. We are issuing this AD to detect and correct missing firewall sealant between the aft firewall assembly and seal assembly, which could result in failure of the fire extinguishing system to prevent the spread of fire through the firewall gap. This failure could lead to an uncontrolled fire.
82-01-01: 82-01-01 CANADAIR: Amendment 39-4288. Applies to Model CL-600 airplanes with serial number 1002 to 1050 inclusive. To prevent asymmetric spoiler deployment, accomplish the following within ten days after the effective date of this AD, unless already accomplished: 1. Visually inspect and adjust, if necessary, the left and right controlex cables (parts numbers 600-91305-5 and 600-91305-7) for compliance with the revised rigging procedure specified in Canadair Alert Service Bulletin A600-0024, Revision 1, dated November 6, 1981, or in a manner approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 2. Airplanes may be flown in accordance with FAR 21.197 to a maintenance base for accomplishment of the inspection 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). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the addresses listed above. These documents may also be examined at FAA Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment becomes effective January 4, 1982.
2008-11-20: We are adopting a new airworthiness directive (AD) for the products listed above that will supersede an existing AD. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: AD 2007-0315-E was issued to address a possible fuel leakage in the gear compartment in front of the engine and mandated inspections and replacement of fuel plastic-made connectors by connectors made of metal. Since its publication, another fuel leakage has been reported on a S10-VT which had implemented the STEMME Service Bulletin (SB) A31-10-082 as required by AD 2007-0315-E. It has been determined that the fuel leak may have been caused by the deformation that the originally installed clamps created on the fuel hoses and thus preventing the new clamps from being sufficiently pinched to perform a correct tightening.This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective June 23, 2008. On June 23, 2008, the Director of the Federal Register approved the incorporation by reference of STEMME F & D Service Bulletin A31-10-083, Am-Index: 01.a, dated February 26, 2008, listed in this AD. As of February 20, 2008 (73 FR 5733, January 31, 2008), the Director of the Federal Register approved the incorporation by reference of STEMME F & D Service Bulletin A31-10-082, AM.-Index: 01.a, dated November 30, 2007, listed in this AD. We must receive comments on this AD by July 2, 2008.
2008-11-18: We are adopting a new airworthiness directive (AD) for certain Cirrus Design Corporation (CDC) Model SR20 airplanes. This AD requires you to perform an inspection and replacement as necessary of the heat exchanger. This AD results from the discovery of engine exhaust fumes in the cabin of CDC Model SR20 airplanes. We are issuing this AD to detect and correct leaks in the exhaust system, which could result in exhaust gases leaking into the cabin heating system. This condition could lead to carbon monoxide in the cabin and incapacitation of the pilot.
86-12-01 L: 86-12-01 BELL HELICOPTER TEXTRON, INC.: Letter issued June 6, 1986. Applies to all Bell Model 214ST helicopters, certificated in all categories. Compliance is required prior to further flight after receipt of this AD, unless previously accomplished. To prevent loss of main rotor collective control, visually inspect locking plate, Part Number (P/N) 214-010-232-101, in accordance with Part I of Bell Helicopter, Textron, Inc., Alert Service Bulletin (ASB) 214ST-86-36, dated May 23, 1986. If the locking plate is defective, check the torque of the lower collective hub nut, Part Number 214-010-407-001, in accordance with Part IV of ASB 214ST-86-36. At the next "A" check, inspect the locking plate in accordance with Part II of ASB 214ST-86-36. At each subsequent "A" check, inspect the locking plate in accordance with Part III of ASB 214ST-86-36. At the next "B" check and each subsequent "B" check, check the torque of the lower collective hub nut, P/N 214-010-407-1, in accordance with Part IV of ASB 214ST-86-36. An alternate method of compliance or adjustment of the compliance time, which provides an equivalent level of safety, may be approved by the Manager, Helicopter Certification Branch, Aircraft Certification Division, FAA, Southwest Region. This airworthiness directive becomes effective upon receipt.
2008-11-09: We are adopting a new airworthiness directive (AD) for all Boeing Model 727 airplanes. This AD requires repetitive inspections for any cracking of or damage to the left side and right side flight deck No. 2, No. 4, and No. 5 windows, as necessary, and corrective actions if necessary. This AD results from reports of in-flight departure and separation of the flight deck windows. We are issuing this AD to detect and correct cracking in the vinyl interlayer or damage to the structural inner glass panes of the flight deck No. 2, No. 4, and No. 5 windows, which could result in loss of a window and rapid loss of cabin pressure. Loss of cabin pressure could cause crew communication difficulties or crew incapacitation.
2007-14-05: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A310 and A300-600 series airplanes. This AD requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness by incorporating new and revised certification maintenance requirements. This AD results from the manufacturer determining that additional and revised certification maintenance requirements are necessary in order to ensure continued operational safety of the affected airplanes. We are issuing this AD to prevent safety-significant latent failures that would, in combination with one or more other specific failures or events, result in a hazardous or catastrophic failure condition of avionics, hydraulic systems, fire detection systems, fuel systems, or other critical systems.
73-12-08: 73-12-08 GENERAL DYNAMICS: Amdt. 39-1659. Applies to Models 22 and 22M airplanes. Compliance, as indicated, required on all airplanes with 28,000 hours or more of total time in service, unless already accomplished. To prevent failures of the flap track support structure accomplish the following: a. Within the next 50 landings after the effective date of this A.D., unless already accomplished within the last 275 landings, and thereafter at intervals not to exceed 325 landings from the last inspection, (1) Visually inspect the right and left inboard flap at wing station 180.504 for cracks in the flap track support rails 22-17463-57, -58, -59, -60, in the fitting 22-18994-1, -3 or -5 and in the track supporting structure general vicinity. (2) If cracks are found in any fitting, it must be replaced before further flight. If cracks are found in the rails or supporting structure other than fittings, parts must be replaced or repaired, before further flight, in amanner approved by the Chief, Aircraft Engineering Division, FAA Western Region. Airplanes with minor cracks in fittings, rails or support structure may be flown per FAR 21.197 to a base where replacement or repair of parts can be accomplished. b. When parts are replaced or repaired per (a)(2) above, the repetitive inspections of (a) above, are no longer required for that part until it accumulates another 28000 hours' time in service from the last inspection. For the purpose of complying with this A.D., subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplanes hours' time in service by the operator's fleet average time from takeoff to landing for the airplane type. This amendment becomes effective June 12, 1973.
2008-10-12: We are adopting a new airworthiness directive (AD) to supersede AD 2007-13-17, which applies to certain Air Tractor, Inc. (Air Tractor) Models AT-602, AT-802, and AT-802A airplanes. AD 2007-13- 17 currently requires you to repetitively inspect the engine mount for any cracks, repair or replace any cracked engine mount, and report any cracks found to the FAA. Since we issued AD 2007-13-17, Air Tractor has learned of a Model AT-502B with a crack located where the lower engine mount tube is welded to the engine mount ring. In addition, Air Tractor has developed gussets that, when installed according to their service letter, terminate the repetitive inspection requirement. Consequently, this AD would retain the inspection actions of AD 2007-13-17 for Model AT-602, AT-802, and AT-802A airplanes, including the compliance times and effective dates; establish new inspection actions for the AT-400 and AT-500 series airplanes; incorporate a mandatory terminating action for all airplanes; and terminate the reporting requirement of AD 2007- 13-17. We are issuing this AD to detect and correct cracks in the engine mount, which could result in failure of the engine mount. Such failure could lead to separation of the engine from the airplane. DATES: This AD becomes effective on June 12, 2008. On June 12, 2008, the Director of the Federal Register approved the incorporation by reference of Snow Engineering Co. Service Letter 253, Rev. C, dated April 17, 2008; Snow Engineering Co. Service Letter 253, Rev. B, dated November 30, 2007; and Snow Engineering Co. Service Letter 253 Rev. A, dated October 16, 2007, as listed in this AD. As of August 10, 2007 (72 FR 36863, July 6, 2007), the Director of the Federal Register approved the incorporation by reference of Snow Engineering Co. Service Letter 253, revised January 22, 2007, as listed in this AD.
2007-14-06: 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 was detected by the STC holder that in earlier installations of the ACASII system there were no isolation diodes installed in the Heading and Attitude Valid lines. The absence of an isolation diode in the valid lines can prevent the valid flag to come up even if a gyro fault exists. The problem has only been detected for Heading Valid lines but could equally affect the Attitude Valid lines. With installation of the ACASII, the heading and attitude valid lines have to be connected to the TPU67A. On valid state, the signals are +28VDC. On invalid, the signals are open. This condition of direct connection (without an isolation diode installed) of the valid lines to the TPU67A, if not corrected, could cause the TPU67A to feed current into the open stated valid lines. This prevents the flag to appear even if the gyro is invalid, providing the flight crew with erroneous navigation information. We are issuing this AD to require actions to correct the unsafe condition on these products.
87-10-08: 87-10-08 CASA: Amendment 39-5622. Applies to CASA Model C-212 series airplanes, serial numbers as listed in CASA Service Bulletin 212-52-16, dated October 23, 1985, certificated in any category. Compliance is required within 9 months after the effective date of this AD. To prevent inadvertent opening of the crew door, accomplish the following, unless previously accomplished: A. Install a protective cover over the crew door internal handle in accordance with CASA Service Bulletin 212-52-16, dated October 23, 1985. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. 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 the modification required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Construcciones Aeronauticas S.A., Getafe, Madrid, Spain. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment 39-5622 becomes effective June 19, 1987.
2008-10-09: We are adopting a new airworthiness directive (AD) for all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires revising the FAA-approved maintenance program to incorporate new airworthiness limitations (AWLs) for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. This AD also requires the initial inspection of a certain repetitive AWL inspection to phase in that inspection, and repair if necessary. This AD results from a design review of the fuel tank system. We are issuing this AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.