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2017-14-11: We are superseding Airworthiness Directive (AD) 2007-13-08, for certain Airbus Model A318, A319, A320, and A321 series airplanes. AD 2007-13-08 required repetitive inspections of the auxiliary power unit (APU) starter motor, APU inlet plenum, and APU air intake for discrepancies; repetitive cleaning of the APU air intake; and applicable corrective actions. This AD expands the applicability of AD 2007-13-08, and includes an optional terminating installation for the repetitive actions. This AD was prompted by a determination that the unsafe condition could occur on additional airplanes. We are issuing this AD to address the unsafe condition on these products.
60-11-03: 60-11-03 LOCKHEED: Amdt. 159 Part 507 Federal Register May 24, 1960. Applies to All 188 Series Aircraft. Compliance required as indicated. Due to loose attachments and cracked quick engine change upper cowl panel longerons the following inspections are required. Prior to dispatch from a terminal where inspection facilities are available, unless already accomplished within the last 300 hours' time in service, and thereafter at every 300 hours' time in service, inspect the top cowl panel upper longerons and the attachments at the rear fittings for cracks or loose attachments. (a) Replace loose attachments in the longeron fittings. Acceptable replacements are: (1) One-sixty-fourths-inch diameter oversize Hi-Lok (P/N HL 56-6 pin, P/N HL 64-6-5 pin, P/N HL 85-6 collar). (2) Thirteen-sixty-fourths-inch diameter NAS type close tolerance screw, minimum heat treat 160,000 p.s.i. Ream to oversize hole limits of 0.212-0.2192-inch diameter. (3) Seven-thirty-seconds-inch diameter NAS type close tolerance screws; minimum heat treat 160,000 p.s.i.; minimum edge distance, 1 1/2 diameters. Ream to oversize hole limits of 0.2181-0.2192-inch diameter. (4) It is satisfactory to mix Huck bolts and Hi-Lok fasteners, but it is not acceptable to mix NAS type screws with Huck bolts or Hi-Lok fasteners. (b) Cracked longerons must be replaced or an FAA approved repair incorporated before next flight. The preceding inspections may be discontinued after the incorporation of the modifications contained in Lockheed Service Bulletin 88/SB-500. (Lockheed Alert Service Bulletin No. 467 covers this same subject.) This airworthiness directive sent by telegram to all operators of 188 aircraft on April 29, 1960. Revised September 29, 1960. Revised May 13, 1961.
2017-14-05: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model SA330J helicopters. This AD requires replacing certain hydraulic pumps and is prompted by reports of broken screws that attach the cover of the hydraulic pump. The actions of this AD are intended to prevent an unsafe condition on these products.
2017-13-12: We are adopting a new airworthiness directive (AD) for all Airbus Model A318 and A319 series airplanes; Model A320-211, -212, - 214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, - 211, -212, -213, -231, and -232 airplanes. This AD was prompted by an evaluation by the design approval holder (DAH), which indicates that the main landing gear (MLG) does not comply with certification specifications, which could result in a locking failure of the MLG side stay. This AD requires modification or replacement of certain MLG side stay assemblies. We are issuing this AD to address the unsafe condition on these products.
80-12-51 R2: 80-12-51 R2 PRATT & WHITNEY AIRCRAFT: Amendment 39-3809. Applies to all Pratt & Whitney Aircraft JT3D series turbofan engines. Compliance required as indicated. To prevent possible first stage fan blade failures resulting from low cycle fatigue, perform inspections in accordance with the schedule below: 1. Within 50 cycles after May 27, 1980, unless already accomplished, and every 200 cycles thereafter, perform a visual inspection of the critical area of the fan blade convex airfoil surface, in accordance with Pratt & Whitney Aircraft All Operator Telegram Nos. JT3D/72-00/PSE.WJM.0-5-26-1 and JT3D/72-00/PSE.WJM.0-5- 30-1. Remove from service any blade having a visual indication, crack, lap, or blend in the critical area. Any questionable visual indication may be dye penetrant inspected for verification. If the dye check is positive, remove from service. If there is no positive dye check indication, repeat within the next 50 cycles and every 50 cycles thereafter.2. Within 200 cycles after the effective date of this amendment, unless already accomplished, and every 2,200 cycles thereafter, perform an ultrasonic inspection of the fan blade in accordance with the provisions of Pratt & Whitney Alert Service Bulletin No. 5136, dated May 30, 1980, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. If any crack indications are found, the blade must be removed from service prior to further flight. 3. Once the ultrasonic inspections of Paragraph 2 have been initiated, the visual inspections per Paragraph 1 may be discontinued. Upon request of the operator, an equivalent method of compliance with the requirements of this AD may be approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, New England Region, may adjustthe inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. 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 Pratt & Whitney Aircraft, Division of United Technologies Corporation, 400 Main Street, East Hartford, Connecticut 06108. These documents may also be examined at the FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts, an at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at its Headquarters in Washington, D.C., and the New England Region. This amendment amends TAD No. T 80NE-26 issued May 28, 1980, as amended by TAD No. T 80-12-51 effective June 2, 1980. This Amendment 39-3809 becomes effective July 1, 1980.
2024-13-06: The FAA is adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a determination that certain left-hand (LH) and right-hand (RH) pylon bleed air leak detectors (BALDs) might be defective, due to incorrect manufacturing processes and incomplete acceptance test procedures. This AD requires a one-time operational check of affected parts and, depending on findings, accomplishment of applicable corrective action, and limits the installation of affected parts under certain conditions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
79-08-01 R1: 79-08-01 R1 GATES LEAR JET: Amendment 39-3447 as amended by Amendment 39- 4361. Applies to Models 35, 35A, 36 and 36A airplanes equipped with Aeronca thrust reversers. COMPLIANCE: Required as indicated unless already accomplished. To preclude inadvertent thrust reverser deployment and possible loss of aircraft control, prior to next flight accomplish the following: A) Insert in the Aeronca Thrust Reverser Supplement to the Airplane Flight Manual the FAA-approved temporary changes shown herein as Figures I, II and III or the FAA-approved Flight Manual Supplement changes (temporary or permanent) supplied by the manufacturer and containing the same information as the above figures. B) Operate the airplane in accordance with instructions in the Flight Manual Supplement changes specified in Paragraph A) of this Airworthiness Directive. C) Airplanes may make one flight to the location where the changes to the Aeronca Thrust Reverser Supplement to the Airplane Flight Manual specified in this Airworthiness Directive are available, providing the Exterior Inspection in Figure II and Limitations in Figure I are complied with. D) The installation of Gates Learjet Thrust Reverser Blocker Door Position Indication System, per Gates Learjet Corporation Modification Kit No. AMK 81-6, constitutes terminating action for the requirements of paragraphs A), B), and C) of this AD. E) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Amendment 39-3447 became effective on April 19, 1979, to all persons except those to whom it had already been made effective by an airmail letter from the FAA dated March 1, 1979. This Amendment 39-4361 becomes effective April 19, 1982. FIGURE I TEMPORARY CHANGE, SUPPLEMENT FOR AERONCA THRUST REVERSERS Aircraft Affected: All Gates Lear Jet Model 35, 36, 35A, 36A Aircraft equipped with Aeronca Thrust Reversers. Description of Change: Add Limitations to Section I of the Aeronca Thrust Reverser AFM Supplement. Filing Instructions: Insert this page adjacent to page 2 of 23 in your Thrust Reverser Supplement and retain until further notice. Amend Section I - Limitations by adding the following limitations: Section I - LIMITATIONS (Cont) 7. Thrust Reversers must not be operated prior to takeoff. 8. Thrust Reversers must not be used to control taxi speed, except after landing. 9. Thrust Reversers must not be used for touch and go landings. 10. After Thrust Reversers have been deployed, a visual check of proper door stowing must be made prior to takeoff. 11. Operational Procedures in this Thrust Reverser Supplement are mandatory. FIGURE II TEMPORARY CHANGE, SUPPLEMENT FOR AERONCA THRUST REVERSERS Aircraft Affected: All Gates Lear Jet Model 35, 36, 35A, 36A Aircraft equipped with Aeronca Thrust Reversers. Description of Change: Add Thrust ReverserOperational Changes. Filing Instructions: Insert this page adjacent to page 2 of 23 in your Thrust Reverser Supplement and retain until further notice. Add the following EXTERIOR INSPECTION to Section II - NORMAL PROCEDURES EXTERIOR INSPECTION (Power-Off) A. Inspect both thrust reversers as follows: 1. Check that thrust reverser upper and lower blocker doors are completely stowed. Change BEFORE TAKEOFF to read as follows: CAUTION: Do not operationally check thrust reversers before takeoff. 1. Thrust Reverser Circuit Breaker - In. 2. Thrust Reverser Position Indicator Lights - Extinguished. 3. Deleted. NOTE: This Temporary Change deletes Thrust Reverser Operational Check, Before Takeoff. FIGURE III TEMPORARY CHANGE, SUPPLEMENT FOR AERONCA THRUST REVERSERS Aircraft Affected: All Gates Lear Jet Model 35, 36, 35A, 36A Aircraft with Aeronca Thrust Reversers. Description of Change: Add Postflight Operational Check. Filing Instructions: Insert this page adjacent to page 4 of 23 in your Thrust Reverser Supplement and retain until further notice. Add the following POSTFLIGHT Operational Check after NORMAL PROCEDURES - After Landing: POSTFLIGHT A. Operationally check Thrust Reverser as follows: CAUTION: It is recommended that the aircraft be headed into the wind during static thrust reverser ground operational check. Keep thrust reverser deployed time to a minimum to prevent possible engine reingestion of exhaust gases. a NORM-EMER STOW Switch - NORM, EMER STOW light extinguished. b Thrust Levers - IDLE. c Thrust Reverser Levers - Pull to deploy lever stop position. UNLOCK lights will come on and then go off when DEPLOY lights come on. Check that the throttle lock releases when the DEPLOY lights illuminate. d NORM-EMER STOW Switch - EMER STOW, EMER STOW light illuminated. DEPLOY lights will go off when UNLOCK lights go on. UNLOCK lights will go off when system is stowed. eThrust Reverser Levers - Push to stow position. f NORM-EMER STOW Switch - NORM, EMER-STOW lights extinguished. g Thrust Reverser Levers - Pull to deploy position. Check for proper light sequence. h Thrust Reverser Levers - Push to stow position. Check for proper light sequence.
2017-13-14: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-300ER series airplanes. This AD was prompted by a report that certain galley tripod mount assemblies were not connected to the tie rods in the overhead support structure. This AD requires an inspection of certain galleys for the presence of the hardware that connects the tripod mount assembly to the tie rods in the overhead support structure, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
80-02-18: 80-02-18 MCDONNELL DOUGLAS: Amendment 39-3677. Applies to McDonnell Douglas DC-10-10, -10F, -30, -30F, and -40 airplanes certificated in all categories utilizing the following passenger evacuation systems manufactured by the PICO Division of Sargent Industries: (Subsequent production serial numbers are not affected.) \n\t\n\nPART NUMBER\nSERIAL NUMBER \n5LS230100-( )\nA0001-A0091 \n5LD230300-( )\nB0001-B0093 \n5LD230500-( )\nC0001-C0086 \n5LD230600-( )\nD0001-D0081\n5LD260100-( )\n E0001-E0087 \n5WD230100-( )\nAA001-AA420 \n5WD230500-( )\t\nCC001-CC169 \n5WD230600-( )\t\nDD001-DD178 \n5WD260100-( )\nEE001-EE792 \n\t\t\n\tCompliance required within the next eighteen calendar months after the effective date of this AD, unless already accomplished. \n\n\tTo prevent failure of the Sargent Industries, PICO Division emergency evacuation system due to inflation hose end fitting failure accomplish the following: \n\n\t(a)\tVisually inspect the passenger evacuation system inflation hoses in accordance with PICO Service Bulletin No. DC-10-25-78, Revision 2, dated December 5, 1979, to determine which hoses have end fittings configured as shown in Figure 2 of the PICO Service Bulletin. \n\n\t(b)\tInflation hose assemblies with end fittings configured as shown in Figure 2 of the PICO Service Bulletin, must be modified in accordance with Subpart 2, "Accomplishment Instructions," of PICO Service Bulletin No. DC-10-25-78 Revision 2, dated December 5, 1979, or each replaced with an approved production hose assembly part number (P/N) 720111-101 in accordance with appropriate maintenance manual procedures. \n\n\t(c)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD. \n\n\t(d)\tAlternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective March 3, 1980.
64-12-05: 64-12-05 LOCKHEED: Amdt. 744 Part 507 Federal Register June 9, 1964. Applies to All Models 188A and 188C Aircraft. Compliance required as indicated. As a result of failures of the landing gear cam follower P/N NAS 562-3-7A and of worn and bent landing gear lever detent plate P/N 827127-3 or -5, accomplish the following unless already accomplished: (a) Correct Lockheed Service Information Letter 84 dated May 6, 1964, by changing in item 6 (A) the word "pilot's" to "co-pilot's" and by changing item 6 (F) to read "Perform steps 6 (A), (B) and (D) on pilot's landing gear control lever". (b) Within the next 40 hours' time in service after the effective date of this AD and at periods not to exceed 4,000 hours' time in service from the last inspection, accomplish the following: (1) Accomplish items 1 through 8 of the section entitled "Description" of Lockheed Service Information Letter No. 84 dated May 6, 1964, as corrected. (2) If during accomplishment of item 6(B) of Service Information Letter 84, the force required to unseat cam follower is less than 5 pounds, before further flight replace the control lever handle return spring with a new return spring. (3) If during accomplishment of items 6(A), (C), (D), (E), and (F) of Service Information Letter 84, the cam follower is unseated from the detent, before further flight replace the cam follower P/N NAS 562-3-7A, with a new cam follower P/N NAS 562-3-7A and inspect the landing gear lever detent plate, P/N 827127-3 or -5, for deformation and for wear or cracks in the detents. If the landing gear lever detent plate exhibits wear beyond the wear limits recommended by the manufacturer or exhibits deformation or cracks, replace the detent plate, P/N 827127-3 or -5, with a new detent plate P/N 827127-3 or -5. The detent plates P/N 827127-3 or - 5 are interchangeable. (4) If any parts are replaced in accordance with (b) (1) and (b)(3), before further flight rig the system in accordance with the Electra Maintenance Manual, Section 32-1-0 and reaccomplish items 1 through 8 of the section entitled "Description" of Lockheed Service Information Letter No. 84 dated May 6, 1964. This directive effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated May 22, 1964. Revised September 28, 1965.
2021-20-16: The FAA is superseding Airworthiness Directive (AD) 2021-04- 15, which applied to all Airbus Helicopters Model AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters; and certain Model AS350B3 helicopters. AD 2021-04-15 required repetitive visual inspections of the right-hand side of the vertical fin spar for discrepancies (cracking), and corrective action if necessary. This AD retains the requirements of AD 2021-04-15, and requires repetitive cleaning and repetitive detailed inspections for cracking of the vertical fin spar and vertical fin upper attachments, and corrective action if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also expands the applicability to include additional Model AS350B3 helicopters. This AD was prompted by a report that, during an unscheduled post-flight inspection of the tail cone area, a crack was found in the spar of the upper part of the vertical fin and fractures were found in the two front attachment screws. The FAA is issuing this AD to address the unsafe condition on these products.
83-18-51 R2: 83-18-51 R2 BOEING VERTOL COMPANY: Amendment 39-4862. Applies to Boeing Vertol Model 234 series helicopters certificated in all categories. Compliance is required as indicated. To prevent possible hazards in flight associated with cracking of the main rotor head pitch shafts, accomplish the following: (a) Unless already accomplished, prior to further flight on helicopters equipped with main rotor head pitch shafts Part Numbers (P/N) 114R2088-7, -14, -15, -16, conduct an eddy current inspection of the pitch shaft in accordance with the Accomplishment Instructions (Part 2) of Boeing Vertol Service Bulletin No. 234-64-1006, Revision 2, dated August 25, 1983, or (Part 3) of Service Bulletin No. 234-64-1006 dated January 16, 1984. (b) After the initial inspection of paragraph (a), repeat the inspection of paragraph (a) at intervals not to exceed 15 hours time in service. (c) Remove from service pitch shafts having a crack and replace with a serviceable part prior to further flight. (d) An equivalent method of compliance with this AD may be used when approved by the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York 11581. (e) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Manager, New York Aircraft Certification Office, FAA, New England Region, may adjust the compliance times specified in this AD. (f) Within the next 25 hours time in service from the effective date of this AD or prior to the accumulation of 550 hours time in service, whichever occurs later, remove from service at main rotor head pitch shafts P/N's 114R2088-14 and -16 and replace with serviceable parts. (g) Within the next 25 hours time in service from the effective date of this AD or prior to the accumulation of 700 hours time in service, whichever occurs later, remove from service forward main rotor head pitch shafts P/N's 114R2088-7 and -15 and replace with serviceable parts. This amendment becomes effective May 31, 1984, as to all persons except those persons to whom it was made immediately effective by telegraphic AD's No. T83-18-51, issued September 2, 1983, and No. T83-18-51R1, issued October 28, 1983, which contained parts of this amendment.
2003-17-03: This document supersedes Airworthiness Directive (AD) 2003-03- 14, which applies to all PIAGGIO AERO INDUSTRIES S.p.A. (PIAGGIO) Model P-180 airplanes. AD 2003-03-14 currently requires you to inspect and determine whether any firewall shutoff or crossfeed valve with a serial number in a certain range is installed and requires you to replace or modify any valve that has a serial number within this range. The modification consisted of reworked valves that were re-identified with an "A" at the end of the serial number. AD 2003-03-14 allows the pilot to check the logbook and does not require the inspection and replacement requirement if the check shows that one of these valves is definitely not installed. Since AD 2003-03-14 became effective, the Federal Aviation Administration (FAA) has found that the valve manufacturer was not correctly incorporating the modification on reworked valves. Consequently, the installation of modified fuel valves installed per AD 2003-03-14 could allow the unsafe condition to remain on the affected airplanes. This AD would require you to replace any firewall shutoff or crossfeed valve with a serial number in a certain range even if it has been modified per AD 2003-03-14. The actions specified by this AD are intended to prevent a faulty firewall shutoff or crossfeed valve from developing cracks and leaking fuel. This could result in an engine fire.
2017-13-13: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of frame web cracking at certain locations. This AD requires repetitive inspections in certain locations of the frame web, and corrective action if necessary. We are issuing this AD to address the unsafe condition on these products.
2017-13-09: We are superseding Airworthiness Directive (AD) 2014-16-02, which applied to certain Bombardier, Inc., Model CL-600-1A11 (CL-600) airplanes. AD 2014-16-02 required revising the airplane flight manual to prohibit thrust reverser operation, doing repetitive detailed inspections of both engine thrust reversers for cracks, and modifying the thrust reversers if necessary. The modification is also an interim (optional) terminating action for the repetitive inspections. This new AD adds a new terminating modification of the thrust reversers, which includes new inspections and repair, if necessary. This AD was prompted by a determination that it is necessary to add a requirement to repair or modify the thrust reversers, which would terminate the requirements of AD 2014-16-02. We are issuing this AD to address the unsafe condition on these products.
63-10-04: 63-10-04 MCCAULEY: Amdt. 556 Part 507 Federal Register May 9, 1963. Applies to McCauley Full Feathering and Constant Speed Propeller Model 2AF36C39 Equipped With Model 78BF Blades and Those Modified to Model 78BFM, but Excluding the Following: Original Model 78BFM Blades, Those Blades Having Serial Numbers with a "Y" Suffix, and Those Blades or Blade Assemblies Which Are Metal Stamped With Identification "P xxxx-3993" Along With a 5 Digit Serial Number Without a Suffix. (Example: P1062-3933, S/N 27236.) (NOTE: These propellers may be found on Beech Models 95-55 and 95-A55 aircraft.) Compliance required as indicated. Because of cranking in the blade threaded shank, accomplish the following: (a) Propellers with blade having accumulated the maximum time in service as listed in Table I of McCauley Service Bulletin No. 53 dated March 4, 1963, before the effective date of this AD, must be replaced prior to the accumulation of 25 hours' time in service after the effective date of this AD. (b) Propellers with blades having accumulated less than the maximum time in service as listed in Table I of McCauley Service Bulletin No. 53 dated March 4, 1963, on the effective date of this AD, must be replaced prior to the accumulation of 25 hours' time after the maximum time listed in Table I of McCauley Service Bulletin No. 53 dated March 4, 1963. (c) Propellers with affected blades that are continued in service regardless of the number of hours service, shall not be operated continuously between 2,250 and 2,400 r.p.m. Aircraft with affected blades installed shall be so placarded within 5 hours' time in service after the effective date of this AD. The placard may be removed when the blades are replaced. (d) Identification of propeller blade serial numbers shall be determined in accordance with McCauley Service Bulletin No. 53 dated March 4, 1963. (e) Replacement of blades shall be made in accordance with instructions in McCauley Service Bulletin No. 53 dated March 4, 1963. (f) Revise the FAA approved Flight Manual to incorporate operating limitations covering the new propeller installed. An AFM Supplement containing this material may be obtained from the airplane or propeller manufacturer. (McCauley Service Bulletin No. 53 dated March 4, 1963, including supplemental revisions, and Service Manual 601101 cover this subject.) This directive effective May 20, 1963.
2017-13-06: We are adopting a new airworthiness directive (AD) for all DG Flugzeugbau GmbH Models DG-400, DG-500M, DG-500MB, DG-800A, and DG-800B 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 a manufacturing defect in certain textile fabric covered fuel hoses, which could cause the fuel hose to fail. We are issuing this AD to require actions to address the unsafe condition on these products.
2017-12-13: We are adopting a new airworthiness directive (AD) for certain Airbus Model A320-212, -214, -232, and -233 airplanes. This AD was prompted by a report of a crack found during an inspection of the pocket radius of the fuselage frame. This AD requires repetitive low frequency eddy current inspections or repetitive high frequency eddy current inspections of this area, and repair if necessary. The repair terminates the repetitive inspections. We are issuing this AD to address the unsafe condition on these products.
62-21-03: 62-21-03 HUGHES: Amdt. 485 Part 507 Federal Register September 20, 1962. Applies to All Model 269A Helicopters Except Those Operated Under CAR Part 8 With Limitations Which Prohibit Flight Over Densely Populated Areas, in Congested Airlanes, or in the Vicinity of Busy Airports. Compliance required as indicated. Prior to further flight, unless already accomplished, incorporate modification in accordance with Hughes Service Bulletin No. 2A7 or equivalent approved by FAA Western Region. This directive effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegrams dated August 17, 1962, and August 31, 1962.
2003-17-10: The FAA is superseding an existing airworthiness directive (AD) for McCauley Systems, Inc. propellers that are installed on, but not limited to, BAE Systems (Operations) Limited Jetstream Model 4101 airplanes. That AD currently requires a one-time fluorescent penetrant inspection (FPI) of propeller blade retention areas for cracks. This AD requires initial and repetitive FPI or Ultrasonic Inspection (UT) of propeller blade retention areas for cracks, replacement of high time propeller blades, and a one-time inspection of propeller hubs. This AD is prompted by four reports of significant cracks found in propeller blade shanks since the issuance of AD 2003-15-01. We are issuing this AD to prevent propeller blade failure or hub failure due to cracking, which could result in failure of the propeller and loss of control of the airplane.
2017-12-14: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757-200 and -200PF series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain areas of the frame webs are subject to widespread fatigue damage (WFD). This AD requires inspections of the frame webs for any crack of any open coordinating holes, tooling holes, and insulation blanket attachment holes; repair if necessary; and modification of the frame webs at all open hole locations, which would terminate the repetitive inspections. We are issuing this AD to address the unsafe condition on these products.
2017-12-12: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 757-200, -200PF, and -200CB series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain fuselage circumferential splice plates are subject to widespread fatigue damage (WFD). This AD requires repetitive low frequency eddy current (LFEC) inspections for cracks of certain circumferential splice plates, and repairs if necessary. We are issuing this AD to address the unsafe condition on these products.
62-21-02: 62-21-02 GENERAL DYNAMICS/CONVAIR: Amdt. 487 Part 507 Federal Register September 25, 1962. Applies to All Models 22 and 22M Series Aircraft. Compliance required within the next 350 hours' time in service after the effective date of this AD, unless already accomplished. With the rudder pedals adjusted to the full forward position and the rudder fully deflected, mechanical interference can make it impossible to apply brakes on the side with the deflected rudder. To correct this interference problem, P/N's 22-41202-1 LH and 22-41202-2 RH located at fuselage Station 192 shall be reworked in accordance with General Dynamics/Convair Service Bulletin A27-53 for the Model 22 and A27-22 for the Model 22M or in accordance with an FAA engineering approved equivalent modification. (General Dynamics/Convair Alert Service Bulletin A27-53 for the Model 22 and A27-22 for the Model 22M cover this same subject.) This directive effective October 25, 1962.
79-21-02: 79-21-02 AVIONS MARCEL DASSAULT (A.M.D.): Amendment 39-3587. Applies to all models of the Fan Jet Falcon series airplanes, Serial Numbers 1 through 376, 378 through 380, 382, and 385 through 388, certificated in all categories. Compliance required as specified in the body of this AD, unless already accomplished. To prevent inadvertent opening of the passenger door due to incomplete manual engagement in closing, worn components, or poor adjustment of the latching mechanism, accomplish the following: (a) For aircraft serial numbers 371 and 386, comply only with paragraph (e) of this AD. All other aircraft must comply with paragraphs (b) through (g) of this AD. (b) Within the next 50 hours in service after the effective date of this AD, unless already accomplished, inspect the passenger door outer control handle and its catch for evidence of wear or inadequate mating of the engaging surfaces in accordance with Avions Marcel Dassault (A.M.D.) Service Bulletin (SB)No. 604 dated May 17, 1978, with Revision 1 dated June 8, 1978, or equivalent approved by the Chief, Aircraft Certification Staff, FAA, AEU-100, Europe, Africa, and Middle East Region. (c) If during any inspection required by this AD, inadequate mating of the door outer control handle and its catch is found, before further flight, except that the airplane may be flown in accordance with FAR 21.197 and 21.199 to a base where repairs can be made, modify the door outer control handle assembly and its catch and install new steel lock bolts in accordance with AMD - SB No. 615, dated May 17, 1978, or an equivalent approved by Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, or if wear is localized on the door outer handle, replace it with a door outer handle of the same part number in accordance with the Falcon 20 service manuals referenced in paragraph "J" of AMD-SB No. 615 or equivalent approved by Chief, Aircraft Certification Staff, AEU-100, FAA, Europe, Africa, and Middle East Region. (d) If during any inspection required by this AD, inadequate mating of the door outer control handle and its catch is found or if a new door outer control handle has been installed in accordance with paragraph (c) of this AD, inspect the door outer control handle and its catch in accordance with the method specified in paragraph (b) of this AD at intervals not to exceed 500 hours time in service from the last inspection until the door outer control handle assembly and its catch are modified and steel lock bolts are installed in accordance with AMD - SB No. 615, dated May 17, 1978, or equivalent approved by the Chief, Aircraft Certification Staff, AEU-100, FAA, Europe, Africa, and Middle East Region. (e) Within the next 500 hours time in service after the effective date of this AD, install passenger door closing instruction placards and symbols in accordance with the Accomplishment Instructions, paragraph 2.k. of AMD - SB No. 616, dated May 17, 1978 or FAA-approved equivalent. (f) Within the next 1000 hours time in service after the effective date of this AD, install a microswitch and associated electrical circuitry to the passenger door handle mechanism and accomplish associated modifications, in accordance with AMD - SB 616, dated May 17, 1978, or equivalent approved by the Chief, Aircraft Certification Staff, AEU-100, Federal Aviation Administration, Europe, Africa, and Middle East Region, c/o American Embassy, Brussels, Belgium. (g) Upon accomplishment of each modification specified in this AD, incorporate appropriate revisions to the Aircraft Parts, Maintenance and Repair Manuals, and Wiring Diagrams related to AMD service bulletins referenced in this AD. This amendment becomes effective November 12, 1979.
2017-12-15: We are adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD requires revising the airplane flight manual (AFM) to provide procedures to stabilize the airplane's airspeed and attitude. This AD was prompted by two in-service incidents of loss of all air data information in the flight deck. We are issuing this AD to address the unsafe condition on these products.