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2020-05-27: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by a report that cracking was discovered in a channel within a structural support member for the rudder quadrant, rudder feel unit assembly, and environmental control system due to fatigue. This AD requires repetitive inspections of the rudder quadrant box assembly for any cracking, and modification of the rudder quadrant box assembly. The FAA issuing this AD to address the unsafe condition on these products.
79-22-02: 79-22-02 PIPER AIRCRAFT CORPORATION: Amendment 39-3595. Applies to Model PA-28-161, serial numbers 28-7816024 through 28-7916475; Model PA-28-181, serial numbers 28-7890023 through 28-7990493, Model PA-28-201T, serial numbers 28-7921001 through 28-7921068; Model PA-28R-201, serial numbers 28R-7737135 through 28R-7837317; Model PA-28RT-201, serial numbers 28R-7918001 through 28R-7918172; Model PA-28R-201T, serial numbers 28R-7703309 through 28R-7803373; Model PA-28RT-201T, serial numbers 28R-7931001 through 28R-7931222; Model PA-28-235, serial numbers 28-7710079 through 28-7710089; and Model PA-28-236, serial numbers 28-7911001 through 28-7911204 airplanes certificated in all categories. Compliance required within the next 50 hours' time in service after the effective date of this AD unless already accomplished. To prevent possible fuel leakage and potential fire hazard, accomplish the following: a. De-fuel the aircraft in accordance with the Piper Service or Maintenance Manual, for the appropriate model aircraft. b. Remove the right hand and left hand fuel tanks in accordance with the Piper Service or Maintenance Manual for the appropriate model aircraft. c. Modify the fuel tank vent system in accordance with the instructions listed in the "Fuel Tank Vent Modification and Vent Hose Replacement" Kit, Piper part number 763 934V. d. Reinstall the fuel tanks in accordance with instruction in the appropriate Piper Service or Maintenance Manual. CAUTION Do not allow lines or hoses to rotate during installation and tightening when attaching the fuel lines to the tank fittings to prevent fuel flow obstruction due to hose twisting. e. Refuel the aircraft and check for leaks and fuel quantity gauge function. f. Make an appropriate maintenance record entry. g. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region.NOTE: Piper Service Bulletin 646 pertains to this subject. This amendment is effective October 26, 1979.
86-25-04: 86-25-04 FAIRCHILD AIRCRAFT CORPORATION: Amendment 39-5485. Applies to Model SA 227 (all serial numbers) airplanes certificated in any category. Compliance: Required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent engine flameout when in or departing an icing environment, accomplish the following: (a) Revise the airplane Pilot's Operating Handbook and Airplane Flight Manual (POH/AFM) by inserting Appendix 1 of this AD in the "LIMITATIONS" section of the POH/AFM. Appendix 1 procedures supersede any other POH/AFM procedures which may be contradictory. NOTE: Automatic-relite ignition is a system which automatically energizes engine ignition without pilot action when engine RPM or torque decays below a specified level, and de-energizes engine ignition when RPM or torque exceeds the specified level. It is not synonymous with CONTINUOUS IGNITION. (b) The requirements of paragraph (a)of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by him. The person accomplishing these actions must make the appropriate aircraft maintenance record entry as prescribed by FAR 91.173. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent method of compliance with this AD, if used, must be approved by contacting the Manager, Airplane Certification Branch, ASW-150, Rotorcraft Certification Directorate, P.O. Box 1689, Fort Worth, Texas 76101; Telephone (817) 877-5150. All persons affected by this directive may obtain copies of the document referred to herein upon request to GTEC, P.O. Box 5217, Phoenix, Arizona 85010; Telephone (602) 231-1000; or Fairchild Aircraft Corporation, P.O. Box 32486, San Antonio, Texas 78284; Telephone (512) 824-9421. This amendment becomes effective on December 15, 1986. APPENDIX 1 Supplement to the POH/AFM Fairchild Models SA 227-TT, SA 227-AT and SA 227-AC Airplanes The IGNITION MODE switches shall be selected to OVERRIDE or, for those aircraft which have the auto-relite system installed, CONTINUOUS or AUTO during all operations in actual or potential icing conditions described herein: (1) During takeoff and climb out in actual or potential icing conditions. (2) When ice is visible on, or shedding from propeller(s), spinner(s), or leading edge(s). (3) Before selecting ANTI-ICE, when ice has accumulated. (4) Immediately, any time engine flameout occurs as a possible result of ice ingestion. (5) During approach and landing while in or shortly following flight in actual or potential icing conditions. *Note: If icing conditions are entered in flight without the engine anti-icing system having been selected, switch one ENGINE system to an ENGINE HEAT position. If the engine runs satisfactorily, switch the second ENGINE system to an ENGINE HEAT position and check that the second engine continues to run satisfactorily. For the purpose of this supplement, the following definition applies: "Potential icing conditions in precipitation or visible moisture meteorological conditions: (1) Begin when the OAT is plus 5 degrees C (plus 41 degrees F) or colder, and (2) End when the OAT is plus 10 degrees C (plus 50 degrees F) or warmer." The procedures and conditions described in this appendix supersede any other POH/AFM procedures and conditions which may be contradictory.
80-19-05: 80-19-05 BOEING: Amendment 39-3906. Applies to all Model 747 series airplanes, unless already accomplished: \n\n\tWithin the next 24 months from the effective date of this AD, modify the leading edge flap systems in accordance with Boeing Service Bulletin No. 747-27-2204, dated April 25, 1980, or a later FAA-approved service bulletin, or in a manner approved by the Chief, Engineering and Manufacturing Branch, Northwest Region.\n \n\tThe 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 Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at FAA, Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective October 9,1980.
77-12-06: 77-12-06 HARTZELL PROPELLERS: Amendment 39-2922 as amended by Amendment 39-3018 is further amended by Amendment 39-3097. Applies to the Model ( )HC-( )( )Y( ) compact series constant speed or feathering propellers with Hartzell manufactured "Y" shank blades, used on but not limited to Aero Commander 200B and 200D, Aerostar 600, Beech 24, 35, 36, 45, 55, 56TC, 58, 60, and 95, Bellanca 14 and 17 series, Britten Norman BN-2, BN-2A, and BN-2A-6, Cessna 182 and 188, Embraer EMB-200A, Maule M5, Mooney M20 and M22, Piper PA-23, PA-24, PA-28, PA-30, PA-31, PA-32, PA-34, PA-36, and PA-39, Pitts S-1T and S-2A, Siai Marchetti S-208, and Rockwell 112, 114, 200, 500, and 685 series aircraft. NOTE: Parentheses preceding or following hub or blade model designations are used herein to accommodate variations of those models. A parenthesis can indicate either the presence or absence of additional letters or numbers. Compliance required as indicated for both initial and repetitive procedures unless already accomplished. To detect blade shank cracks and prevent possible blade failure, accomplish the following: GENERAL Propellers with all blades serial D47534 or above, or with all blades identified with the letters "PR" or "R" ink-stamped on the camber side and "SP" and "RD" metal stamped on the blade butt, or with all blades model F7666A-( )P are considered to be in compliance with the initial inspection and rework requirements only of this AD where specified by reference to Hartzell Bulletin 118A dated February 15, 1977. (a) Models ( )HC-( )( )Y( ) Compact Series "Y" Shank Propellers. (1) All propellers not specified in paragraph (b), (c), or (d) of this AD, remove, inspect and rework or replace if necessary in accordance with Hartzell Bulletin 118A dated February 15, 1977, or later FAA approved revision(s) prior to accumulating those time intervals (hours or years, whichever occurs first) since new or last complete overhaul specified in HartzellService Letter 61B (Overhaul Periods for Hartzell Propellers) dated September 10, 1976, or later FAA approved revision(s). If such time intervals have been exceeded or are unknown, compliance is required within the next 500 hours after June 24, 1977, or prior to June 24, 1979, whichever occurs first. Reinspect and, if necessary, rework in accordance with Hartzell Bulletin 118A at intervals specified in Hartzell Service Letter 61B, or later FAA approved revision(s). (2) Propellers subjected to momentary overspeed greater than 10 percent above rated r.p.m. or continuous overspeed totaling one hour or more at greater than 5 percent above rated r.p.m.; remove, inspect and rework, or replace if necessary in accordance with Hartzell Bulletin 118A before further flight. (3) Propellers subjected to ground or object strike; remove, inspect and rework, or replace if necessary in accordance with Hartzell Bulletin 118A before further flight. (b) Propeller Model HC-E2YR-2( )()/( )C8475-( ) Propeller Models HC-E2YR-2( )( )/( )C8475-( ) installed on Piper PA-31 series aircraft; remove, inspect and rework, or replace if necessary in accordance with Hartzell Bulletin 118A within the next 50 hours in service after June 24, 1977. Reinspect and, if necessary, rework in accordance with Hartzell Bulletin 118A at intervals specified in Hartzell Service Letter 61B, or later FAA approved revision(s). (c) Propeller Models ( )HC-C2YK-( )( )( )/( )( )7666A-( ) Installed on Undampered Lycoming O-360 or IO-360 Series Only. NOTE: Models carrying "-G" hub suffix designation are excluded from this paragraph and covered by paragraph (a). (1) Propellers which have not been inspected and reworked as specified by AD 75-07-05, installed on, but not limited to Pitts S-2A, Piper PA28-180 (STC SA2213WE), PA28R-180, PA28R-200, and Mooney M20( ) series aircraft; remove, inspect and rework or replace if necessary in accordance with Hartzell Bulletin 118A withinthe next 100 hours after June 24, 1977, or by June 24, 1978, whichever occurs first. Reinspect and, if necessary, rework in accordance with Hartzell Bulletin 118A at intervals specified in Hartzell Service Letter 61B, or later FAA approved revision(s). (2) (i) As of June 24, 1977, propellers with less than 500 hours time in service since last inspection and rework in accordance with AD 75-07-05, remove, inspect, and rework, or replace if necessary in accordance with Hartzell Bulletin 118A or later FAA approved revision(s) prior to the accumulation of 600 hours time in service since last compliance with AD 75-07-05 or by June 24, 1979, whichever occurs first. (ii) As of June 24, 1977, propellers with 500 or more hours in service, or whose time in service is unknown since last inspection and rework in accordance with AD 75-07-05, remove, inspect, and rework, or replace if necessary in accordance with Hartzell Bulletin 118A or later FAA approved revision(s) within the next100 hours or by June 24, 1978, whichever occurs first. (iii) Reinspect and if necessary rework propellers cited under preceding paragraphs (c)(2)(i) and (c)(2)(ii) in accordance with Hartzell Service Letter 61B, or later FAA approved revision(s). (3) Propellers installed on aircraft with (undampered) 200 h.p. Lycoming IO-360 series engines, including but not limited to Mooney M20E and F and Piper PA-28R-200 type normal category aircraft and Pitts S-1T and S-2A acrobatic aircraft, accomplish the following within the next 100 hours time in service after June 24, 1977: (i) Remove the present propeller vibration placard, if installed, and on the instrument panel near the engine tachometer affix a new placard and revise the tachometer markings as follows: (A) Placard for normal category aircraft: "Avoid continuous operation: Between 2000 and 2350 r.p.m. Above 2600 r.p.m. in full throttle level flight." (B) Placard for utility and acrobatic aircraft:"Avoid continuous operation: Between 2000 and 2350 r.p.m. Above 2600 r.p.m. in acrobatic and full throttle level flight." (C) Remark the engine tachometer face or bezel with a red arc for each restricted engine speed range, i.e., between 2000 and 2350 r.p.m. and between 2600 and 2700 r.p.m. (red line). (ii) Upon compliance with paragraph (c)(1) or (c)(2) above, the restrictions against operation above 2600 r.p.m. in full throttle level flight only may be removed and the placards and tachometer markings revised as follows: (A) Placard for normal category aircraft: "Avoid continuous operation: Between 2000 and 2350 r.p.m." (B) Placard for utility and acrobatic aircraft: "Avoid continuous operation: Between 2000 and 2350 r.p.m. Above 2600 r.p.m. in acrobatic flight." (C) Tachometer marking for normal category aircraft: Red arc between 2000 and 2350 r.p.m. (D) Tachometer marking for utility and acrobatic aircraft: No change; same as (i)(C)above. (d) Propeller Models ( )HC-C2YK-( )( )/( )( )8475( )-( ) or ( )( )8477( )-( ). (1) Propellers installed on, but not limited to Piper PA-32-260, PA-32-300 and Siai Marchetti 208, which have not been inspected and reworked as specified in AD 74-15-02, accomplish the following within the next 50 hours in service after June 24, 1977: (i) Remove propeller from aircraft, modify pitch change mechanism and replace blades with equivalent model blades prefixed with letter "F" in accordance with Hartzell Service Letter 69 revised November 30, 1971 and Bulletin 101D dated December 19, 1974, or later FAA approved revision(s). (ii) Inspect and repair or replace if necessary, in accordance with Hartzell Bulletin 118A. Reinspect and, if necessary rework in accordance with Hartzell Bulletin 118A at intervals specified in Service Letter 61B, or later FAA approved revision(s). (2) (i) Propeller Models ( )HC-C2YK( )( )( )/F( )8475( )-( ) or F()8477()-() used on but not limited to Aero Commander 200B and 200D, Mooney M22, Britten-Norman BN-2, BN-2A, and BN-2A-6, Bellanca 17-31, Embraer EMB-200A, Piper PA-32-260 and PA-32-300 and Siai Marchetti S-208 series aircraft with less than 1000 hours total time in service as of June 24, 1977, remove, inspect and rework or replace if necessary in accordance with Hartzell Bulletin 118A or later FAA approved revision(s) prior to the accumulation of 1300 hours or by June 24, 1978, whichever occurs first. (2) (ii) Propeller Models ( )HC-C2YK( )( )( )/F( )8475( )-( ) or F( )8477( )-( ) with 1000 or more hours total time in service, or whose time in service is unknown as of June 24, 1977, remove, inspect and rework, or replace if necessary in accordance with Hartzell Bulletin 118A or later FAA approved revision(s) within the next 300 hours after June 24, 1977, or by June 24, 1978, whichever occurs first. (2) (iii) Reinspect and if necessary rework propellers under preceding paragraphs (d)(2)(i) and (d)(2)(ii) in accordance with Hartzell Service Letter 61B, or later FAA approved revision(s) Upon request of the operator, a FAA Maintenance Inspector, subject to approval of the Chief, Engineering and Manufacturing Branch, Great Lakes Region, may adjust the repetitive inspection intervals specified in this AD if the request contains satisfactory substantiating data to justify the adjustment for that operator. The manufacturer's specifications and procedures identified in this directive are incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by the directive who have not already received these documents from the manufacturer, may obtain copies upon request to Hartzell Propeller, Inc., 350 Washington Avenue, Piqua, Ohio 45356. These documents may also be examined at the Great Lakes Regional Office, 2300 East Devon Avenue, Des Plaines, Illinois 60018, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591.A historical file on this airworthiness directive which includes incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and the Great Lakes Region. This supersedes Amendment 39-1049 (35 F.R. 12325), AD 70-16-03, as amended by Amendment 39-1341; Amendment 39-1637 (38 F.R. 12325), AD 73-10-03; Amendment 39-1896 (39 F.R. 25644), AD 74-15-02; and Amendment 39-2136 (49 F.R. 12772), AD 75-07-05, as amended by Amendment 39-2216. Amendment 39-2922 became effective June 24, 1977. Amendment 39-3018 became effective August 26, 1977. This amendment 39-3097 becomes effective December 21, 1977, and was effective for all recipients of the airmail letter dated November 10, 1977, upon receipt thereof.
79-20-10: 79-20-10 PIPER: Amendment 39-3579. Applies to the following Piper Model airplanes: PA-24 Serial Nos. 24-1 and up PA-24-250 Serial Nos. 24-1 and up PA-24-260 Serial Nos. 24-3642, 24-4000 and up PA-24-400 Serial Nos. 26-1 and up PA-30 Serial Nos. 30-1 and up PA-39 Serial Nos. 39-1 and up, certificated in all categories except airplanes incorporating Piper Kit Part No. 763 893: (a) Within the next 50 hours in service, after the effective date of this AD, unless already accomplished within the past 50 hours in service and at intervals not to exceed 100 hours in service thereafter, inspect in accordance with paragraph "Instructions" in Service Letter No. 850 dated April 18, 1979, Parts 1, 2, 3, 4a, b and c or equivalent inspection. (b) Upon incorporation of Piper Kit No. 763 893 or equivalent, compliance with this AD may be terminated. (c) Equivalent parts and inspections and alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (d) Upon submittal of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the inspection intervals specified in this AD. This supersedes AD 74-10-03. This amendment is effective October 4, 1979.
79-11-06: 79-11-06 PIPER: Amendment 39-3481 as amended by Amendment 39-3545. Applies to all PA-23 series aircraft, certificated in all categories, which have landing gear selector lever, P/N 752303, installed. To prevent possible failure of the landing gear selector lever, Piper Part No. 752303 accomplish the following: a. Within the next 50 hours in service after the effective date of this AD, unless already accomplished, inspect the landing gear selector lever in accordance with Instructions Section in Piper S/B No. 635 steps (1) through (4) or equivalent inspection. b. If cracks are found, replace the landing gear selector lever with lever Piper P/N 761213 or equivalent before further flight. c. If no cracks are found, repeat the inspection in (a) at intervals not to exceed 100 hours in service. The requirements of this AD may be cancelled upon installation of landing gear selector lever Piper P/N 761213 or equivalent. d. Equivalent inspections and replacementsmust be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. e. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, Eastern Region, may adjust the inspection intervals specified in this AD. Amendment 39-3481 was effective June 5, 1979. This Amendment 39-3545 is effective August 29, 1979.
88-12-10: 88-12-10 GARRETT ENGINE DIVISION, ALLIED-SIGNAL INCORPORATED (FORMERLY GARRETT TURBINE ENGINE COMPANY, FORMERLY AIRESEARCH MANUFACTURING COMPANY OF ARIZONA): Amendment 39-5910. Applies to model TPE331-10, -10R, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, and -11U turboprop engines equipped with second stage turbine rotors, part numbers 3102106-1, -6, and -8, installed in aircraft certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent an uncontained engine failure, accomplish the following: (a) Remove from service the second stage turbine rotor per the schedule below in accordance with the accomplishment instructions of Garrett Alert SB TPE331-A72-0571, dated March 31, 1988: Second Stage Turbine Rotor Cycles Since New (CSN) Removal Schedule 0 to 4,400 Prior to 4,800 cycles since new CSN. 4,401 to 5,000 Within 400 cycles after the effective date of this AD or 5,200 CSN, whichever occurs first. 5,001 to 5,900 Within 200 cycles after the effective date of this AD or 6,000 CSN, whichever occurs first. 5,901 to 6,800 Within 100 cycles after the effective date of this AD or 6,800 CSN, whichever occurs first. (b) Remove from service prior to January 1, 1989, all second stage turbine rotors with 4,800 or more cycles since new CSN, regardless of the schedule provided in paragraph (a) above. NOTE: Garrett SB TPE331-72-0180 Revision 12, dated March 31, 1988, which defines critical component service life limits includes the required life limit and states the cycle definitions. (c) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (d) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Los Angeles Aircraft Certification Office, Federal Aviation Administration, Northwest Mountain Region, 4344 Donald Douglas Drive, Long Beach,California 90808. (e) Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Los Angeles Aircraft Certification Office, Northwest Mountain Region, may adjust the compliance schedule specified in this AD. Garrett SB, TPE331-A72-0571, dated March 31, 1988, identified and described in this document, is 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 the manufacturer's SB may obtain copies upon request to Garrett General Aviation Services Division, Distribution Center, 2340 East University, Phoenix, Arizona 85034. This document may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket Number 88-ANE-18, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment, 39-5910, becomes effective June 6, 1988.
76-17-08: 76-17-08 ENSTROM: Amendment 39-2700 as amended by Amendment 39-3043. Applies to Models F-28, F-28A, and 280 helicopters certificated in all categories, except for those helicopters which have the following main rotor shaft gear box serial numbers. 032FS 07-012-74PS 39-002-13PS 041PS 08-001-72S 44-011-76PS 067PS 10-002-72PS 44-019-76PS 070PS 19-024-74PS 53-003-73PS 091 34-029-75PS To detect tool marks, surface irregularities, and cracks which may develop into failure of the Main Rotor Shaft (Enstrom Part Number 28-13104) accomplish the following: A. Before further flight visually inspect the main rotor shaft in the area of the radius beneath the rotor hub shoulder, using an eight power or greater magnifying glass and report to the Enstrom Helicopter Corporation, Menominee County Airport, P.O. Box 277, Menominee, Michigan, Phone 906-863-9971, any evidence of circumferentially disposed tool marks or surface irregularities. B. Before further flight, unless previously accomplished within the last 20 hours time in service or one month, and every 20 hours or one month thereafter, whichever occurs first, inspect the main rotor shaft for cracks in the area of the radius beneath the rotor hub shoulder using a 3-step dye-penetrant method. The inspections are to be performed by maintenance personnel familiar with the dye-penetrant inspection method. C. Within 10 hours time in service or 15 days, whichever occurs first after each dye- penetrant inspection, visually check the main rotor shaft for cracks in the area of the radius beneath the rotor hub shoulder using an eight power or greater magnifying glass. D. Before further flight remove from service any main rotor shaft found to contain cracks or other evidence of damage and replace with an airworthy shaft of the same part number or later FAA approved part number. E. Immediately check in accordance with Paragraph B above any helicopter which develops unusual once-per-rotor-revolution vibration. Such vibrations serve as warning of imminent failure. F. Within the next 200 hours time in service or six months after the effective date of this amendment, whichever occurs first, remove main rotor shaft from service or return gearbox and shaft to Enstrom Helicopter Corporation for modification in accordance with Enstrom Service Directed Bulletin No. 0036. G. Repetitive inspections of paragraphs B and C above may be discontinued after main rotor shaft modification in accordance with Enstrom Service Directed Bulletin No. 0036. 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 Enstrom Helicopter Corporation, Menominee County Airport, P.O. Box 277, Menominee, Michigan 49858.These documents may also be examined at the FAA Great Lakes Region, Engineering and Manufacturing Branch, AGL-210, 2300 East Devon Avenue, Des Plaines, Illinois. A historical file on this AD which includes the incorporated material in full is also maintained at that office. Amendment 39-2700 superseded Amendment 39-2472 (40 F.R. 59197), AD 75-26-19. Amendment 39-2700 became effective September 1, 1976 and was effective immediately for all recipients of the airmail letters dated August 6, 1976 which contained this amendment. This amendment 39-3043 becomes effective October 4, 1977.
98-12-33: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires repetitive inspections to detect fatigue cracking on the connecting angle between frame 56 and the right-hand frame support at stringer 38; and replacement of the connecting angle, if necessary. This amendment also provides for an optional terminating action for the repetitive inspections. 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 detect and correct fatigue cracking on the connecting angle, which could result in reduced structural integrity of the airplane.