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2001-08-24: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 737 series airplanes. This action requires revising the Airplane Flight Manual to prohibit extended dry operation of the center tank fuel pumps (with no fuel passing through the pumps). This action is necessary to prevent ignition of fuel vapors due to the generation of sparks and a potential ignition source inside the center tank caused by metal-to-metal contact during dry fuel pump operation, which could result in a fire or explosion of the fuel tank. This action is intended to address the identified unsafe condition.
82-03-09: 82-03-09 SHORT BROTHERS LIMITED: Amendment 39-4308. Applies to Model SD3-30 series airplanes, serial numbers SH3001 through SH3024 inclusive, certificated in all categories. Compliance required prior to the accumulation of 12,000 landings, or 300 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 3,000 landings. To prevent fatigue failures of the stub wing spar and stub wing bolted joints, accomplish the following: (a) Inspect the bolt holes in the stub wing spars for cracks using the eddy current method described in Short Brothers "Non-destructive Test Specification," NDTI RD 1, dated October 1979, and in accordance with "ACCOMPLISHMENT INSTRUCTIONS," paragraph 2, of Short Brothers Limited Service Bulletin SD3-53-34, Revision 2, dated December 12, 1979, or an FAA-approved equivalent, and for airplane serial numbers SH3008 through SH3013 inclusive, replace the laminated aluminum shims in the stub wing boltedjoints with single thickness shims in accordance with Short Brothers Limited Service Bulletin SD3-53-21, Revision 1, dated September 5, 1979, or an FAA-approved equivalent. (b) If as a result of the inspection in paragraph (a) of this AD, no cracks are found, reassemble the stub wing in accordance with "ACCOMPLISHMENT INSTRUCTIONS," paragraphs 2A.15 and 2A.11(b) for the front spar frame, and paragraphs 2A.15 and 2A.12(b) for the rear spar frame, of Short Brothers Limited Service Bulletin SD3-53-34, Revision 2, dated December 12, 1979, or an FAA-approved equivalent. (c) If as a result of the inspection required in paragraph (a) of this AD, cracks are found - (1) Before further flight, except as provided in paragraph (f) of this AD, install Short Brothers Limited SD3-30 Modifications 5514, 5600 and 5790, in accordance with Short Brothers Limited Service Bulletin SD3-53-39, Revision 1, dated January 14, 1980, or an FAA-approved equivalent; and (2) Repair any bolt holes in which cracks are found and fit oversize bolts in accordance with paragraph 2A.11 for the front spar frame, and paragraph 2A.12 for the rear spar frame, of Short Brothers Limited Service Bulletin SD3-53-34, Revision 2, dated December 12, 1979, or an FAA-approved equivalent; and (3) Reassemble the stub wing in accordance with "ACCOMPLISHMENT INSTRUCTIONS," paragraphs 2A, and 29 through 47, of Short Brothers Limited Service Bulletin SD3-53-39, Revision 1, dated January 14, 1980, or an FAA-approved equivalent. (d) If cracks in the stub wing spar bolt holes cannot be removed by the procedure specified in paragraph (c)(2) of this AD, report those findings to the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Office, AEU-100, FAA, c/o American Embassy, Brussels, Belgium. (Reporting approved by the Office of Management and Budget under OMB No. 04- R0174). Additional repair procedures must be approved by that office prior to returning aircraft to service. (e) Upon incorporation of Short Brothers Limited Service Bulletin SD3-53-39, Revision 1, dated January 14, 1980, the repetitive inspection required by this AD may be discontinued. (f) In accordance with FAR Sections 21.197 and 21.199, the airplane may be flown to a base where the inspections, modifications, and repairs required by this AD may be accomplished. (g) If an equivalent means of compliance is used in complying with any paragraph of this AD, that equivalent means must be approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. (h) Upon submission of substantiating data, through an FAA Aviation Safety Inspector, the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, Brussels, Belgium, may adjust the inspection intervals. (i) For the purpose of this AD, when conclusive records are not available to show the total number of landings accumulated by a particular part (or assembly), the number of landings may be computed by dividing the airplane time-in-service since the part (or assembly) was installed in the airplane by the operator's fleet average time per flight for his Model SD3-30 series airplanes. All persons affected by this directive who have not already received the referenced documents from the manufacturer may obtain copies upon request to Short Brothers Limited, P.O. Box 241, Airport Road, Belfast, BT 9DZ, Northern Ireland, Attention: Product Support Manager. These documents may be examined at FAA Headquarters, Room 916, 800 Independence Avenue, SW., Washington, D.C. 20591. This amendment becomes effective March 1, 1982.
88-25-02: 88-25-02 PIPER (AEROSTAR): Amendment 39-6080. Applies to Models PA-60-601 equipped with an automatic waste gate controller per Retrofit Option 106 (S/N 61-0001-004 through 61-0334-111), PA-60-601 (S/N 61-0342-112 through 61-0880-8162157), PA-60-601P (S/N 61P-0157-001 through 61P-0860-8163455), PA-60-602P (S/N 62P-0750-8165001, and 62P-0861-8165002 through 60-8365010), PA-60-700P (S/N 60-8423001 through 60-8423025) 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 reduce the possibility of damage to the oil supply hoses which, if not corrected, could result in an in-flight fire, oil starvation and/or engine failure, accomplish the following: (a) For all the above applicable airplanes except Model PA-60-700P (S/N 60- 8423001 through 60-8423025) airplanes, replace and modify the engine fluid-carrying hoses and associated hardware in accordance withthe instructions contained in Piper Service Bulletin (SB) No. 761, dated April 18, 1983, and Piper SB No. 815, dated January 3, 1986. (b) For Model PA-60-700P Aerostars (S/N 60-8423001 through 60- 8423025) airplanes replace and modify the engine fluid-carrying hoses and associated hardware in accordance with the instructions contained in Piper SB No. 815, dated January 3, 1986. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Atlanta Aircraft Certification Office, ACE-115A, Federal Aviation Administration, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 32960; or may examine these documents at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment, 39-6080, becomes effective on December 26, 1988.
86-17-03: 86-17-03 SOCATA: Amendment 39-5392. Applies to Model TB20 (Serial Numbers up to and including No. 479) airplanes certificated in any category. Compliance: Required within 100 hours time-in-service after the effective date of this AD, unless already accomplished. To assure the integrity of the trim control system, accomplish the following: (a) Replace the attachment of the elevator tab control to the elevator tab levers in accordance with Operation II of the Description paragraph of SOCATA Service Bulletin (S/B) No. 24, dated January 1985, as follows: (1) Remove and discard the bolt, washers, spacer, nut and pin attaching the elevator trim tab rod eye-end-fitting to the trim tab levers. (Ref. Detail A of the figure in SOCATA Service Bulletin No. 24) (2) Measure the rod length in order to reposition the eye-end-fitting. (3) Remove the eye-end-fitting. (4) Bore the eye-end-fitting at dia. 10 mm (.3937 inches + .0009, - .0000). (5) Bore the two tab levers at dia. 6 mm (.2363 inches + .0007, - .0000). (6) Grease the new bolt of dia. 6 mm (nominal 0.24 in.). (7) Install the eye-end-fitting at the rod length measured using a new lock plate (Z00.5544.1.10.000). (8) Install the dia. 6 mm bolt, the spacer and washers according to Detail A of the figure shown in SOCATA S/B No. 24. (9) Tighten the castellated nut (apply a tightening torque of 0.42 m.daN-37 inch.Pound), if necessary loosen to the lower notch. (10) Install pin and grease. (11) Bore the tab levers according to Detail B of the figure shown in SOCATA S/B No. 24 to 5 mm (.1969 inches + .0003, -.0000) diameter. (12) Grease the bolt. (13) Install the spacer, the dia. 5 mm (nominal 0.20 in.) bolt, the washer and nut according to Detail B of the figure in SOCATA S/B No. 24. (14) Tighten the nut (apply a tightening torque of 0.25 m.daN - 23 inch.Pound). (15) Check the tab deflection angles (SOCATA TB20 Maintenance Manual Section V.5). (b) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (c) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to SOCATA Groupe Aerospatiale, B. P. 38, 65001 Tarbes, France; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on September 22, 1986.
91-11-14: 91-11-14 PARTENAVIA COSTRUZIONI AERONAUTICHE: Amendment 39-6992. Docket No. 91-CE-39-AD. Applicability: Models P68C-TC airplanes (all serial numbers (S/N)), P68-OTC airplanes (S/N 344-01-OTC and 340-02-OTC), and P68C and P68 Observer airplanes (S/N 268 to 381), certificated in any category. Compliance: Within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent fuel leakage into the airplane cabin that could result in ignition and explosion of the airplane, accomplish the following: (a) For Models P68C-TC and P68-OTC, remove the fuel and Janitrol system lines in accordance with the instructions in Partenavia Service Instruction No. 39, dated February 14, 1991. (1) Install the applicable service kit in accordance with the instructions in Partenavia Instruction No. 39. (2) Replace the light alloy line of the Janitrol system (part number (P/N) 7.6131-2) with P/N 7.6131C-2 on the applicable Model P68C-TC airplanes in accordance with the instructions in Partenavia Service Instruction No. 39. (b) For Models P68C and P68 Observer, remove the fuel and Janitrol system lines in accordance with the instructions in Partenavia Service Instruction No. 40, dated February 14, 1991. (1) Install the applicable service kit in accordance with the instructions in Partenavia Instruction No. 40. (2) Replace the light alloy line of the Janitrol system (part number (P/N) 7.6131-2) with P/N 7.6131C-2 on the applicable Model P68C airplanes in accordance with the instructions in Partenavia Service Instruction No. 40. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Office, Europe, Africa, Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. (e) The replacements and modifications required by this AD shall be done in accordance with Partenavia Service Instruction No. 39 or Partenavia Service Instruction No. 40, both dated February 14, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. Section 552(a) and 1 CFR Part 51. Copies may be obtained from Partenavia Costruzioni Aeronautiche, S.p.A., Via G. Pascoli N. 7, 80026 Casoria (NA), Italy. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC. This amendment (39-6992, AD 91-11-14) becomes effective on June 14, 1991.
2001-08-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-200 and -300 series airplanes, that currently requires a one-time inspection to detect cracks of the lower frames and reinforcing angles of the main deck cargo door where the door latch fittings attach between certain fuselage stations and water lines, and replacement of any cracked part with a new part having the same part number. That AD was prompted by reports that, during the inspections required by the existing AD, cracks were found in the reinforcing angles of the main deck cargo door frame. This amendment requires, among other actions, an inspection to detect cracks of the lower frames and reinforcing angles of the main deck cargo door; replacement of any lower frame or reinforcing angle of the main deck cargo door when it has reached its maximum life limit. The actions specified by this AD are intended to detect and correct cracking of the lower portion of themain deck cargo door frames, which could result in sudden depressurization, loss or opening of the main deck cargo door during flight, and loss of control of the airplane.
71-24-04: 71-24-04 CESSNA: Amdt. 39-1340. Applies to following airplanes: MODELS SERIAL NUMBERS AFFECTED 177 661, 17700001 and 17700003 thru 17701164 206 206-0001 thru 206-0275 U206 U206-0276 thru U206-0437 P206 P206-0002 thru P206-0160 U206A U206-0438 thru U206-0656 P206A P206-0161 thru P206-0306 TU206A U206-0487 thru U206-0656 P206B P206-0307 thru P206-0419 TU206B U206-0657 thru U206-0914 TP206A P206-191 thru P206-0306 TP206B P206-0307 thru P206-0419 U206B U206-0657 thru U206-0914 P206C, TP206C P206-0420 thru P206-0519 U206C, TU206C U206-0915 thru U206-1234 210D 21058221 thru 21058510 210E 21058511 thru 21058715 T210F T210-0001 thru T210-0197 210F 21058716 thru 21058818 T210G T210-0198 thru T210-0307 210G 21058819 thru 21058936 T210H T210-0307 thru T210-0392 210H 21058937 thru 21059062 336 633, 636, 336-001 thru 336-0195 337 337-0002 thru 337-0239 337A 337-0240 thru 337-0525 (except 337-0306 and 337-0470) 337B 337-0001, 337-0470, 337-0526 thru 337-0755 T337B 337-0001, 337-0526 thru 337-0755 (except 337-0569) 337C, T337C 337-0756 thru 337-0978 Compliance: Required as indicated, unless already accomplished. To detect leakage of flammable fluids from flexible hose assemblies in the engine compartment within 100 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 100 hours' time in service, accomplish the following: A. Visually, or by any other method approved by FAA, inspect fuel lines as follows: 1. Pressurize the fuel lines with boost pump operating in high position. When accomplishing this test, the mixture control should be in the idle cutoff position. 2. With fuel lines pressurized, examine all flexible hose exteriors in the engine compartment for evidence of fuel stains, wetness, or leakage. 3. After pressure testing fuel hoses, allow sufficient time for excess fuel to drain overboard from the engine manifold before attempting an engine start. B. Visually, or by any other method approved by the FAA, inspect oil lines for evidence of wetness or leakage. C. If, as a result of the inspections required by Paragraphs A or B, fuel and/or oil stain, wetness or leaking is found, replace with a serviceable hose assembly. D. Inspections required by Paragraphs A and B will no longer be required when hose assemblies are replaced with assemblies having a Cessna dated metal tag attached. TSO-C53a Type C approved hose assemblies are also acceptable for this replacement. (See Note 1) NOTE 1: This does not preclude continued inspections of this area as required by FAR 91. NOTE: Cessna Service Letter SE71-7, Supplement No. 1 dated November 3, 1971, covers this subject. The above airplanes use Aeroquip 601 series or Stratoflex 156 series hose assemblies available under Cessna P/N S1236-x-xxxx. The hose assemblies are identified by a steel braided exterior. This amendment becomes effective November 23, 1971.
93-08-14: 93-08-14 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-8562. Docket Number 93-SW-01-AD. Applicability: Model 222, 222B, and 222U helicopters, equipped with main rotor flapping bearings (bearings), part number (P/N) 222-310-114-003, -105, -107 and -109, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the bearings, loss of a main rotor blade, and subsequent loss of control of the helicopter, accomplish the following: (a) Within the next 10 hours' time-in-service after the effective date of this AD, and thereafter at intervals not to exceed 10 hours' time-in-service from the last inspection, visually inspect the bearings for cracks in accordance with paragraph 1 of the Accomplishment Instructions of the applicable BHTI Alert Service Bulletin Nos. 222U-92-33 or 222-92-60, both dated December 16, 1992. (b) If a crack is found in the bearings, replace the affected bearings with an airworthy part before further flight. (c) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Rotorcraft Standards Staff, FAA, Rotorcraft Directorate. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Standards Staff. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished. (e) The inspection and any necessary replacement shall be done in accordance with the applicable BHTI Alert Service Bulletin Nos. 222U-92-33 or 222-92-60, both dated December 16, 1992. This incorporation byreference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 2601 Meacham Boulevard, room 663, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on April 6, 1994.
90-03-19 R1: 90-03-19 R1 FAIRCHILD AIRCRAFT CORPORATION (formerly Swearingen Aviation Corporation): Amendment 39-6499 as revised by 39-6672. Docket No. 89-CE-24-AD. Applicability: Models SA226-T (Serial Numbers (S/N) T201 through T275, and T277 through T291), SA226-T(B), (S/N T(B)276 and T(B)292 through T(B)417), SA226-AT (S/N AT001 through AT074), SA226-TC (S/N TC201 through TC419), SA227-TT (S/N TT421 through TT541), SA227-AT (S/N AT423 through AT695), SA227-AC (S/N AC406, AC415, AC416, AC420 through AC705, and AC707 through AC733) airplanes certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished per AD 90-03-19. To prevent an inadvertent deenergized battery bus relay, which could result in unrecoverable loss of the airplane's electrical power, accomplish the following: (a) Modify the electrical system using the following procedures, or the procedures contained in Fairchild Service Bulletins SA226-24-032 and SA227-24-013, both dated August 7, 1989, as applicable: (1) Remove the access cover of the "J-Box", EP11. (2) Locate Battery Bus Relay K40 and remove diode from across X1 and X2 terminals. (3) Reinstall access cover. (4) Using the Battery Switches, verify that battery voltage is present on the LH Essential, RH Essential, and Nonessential busses. NOTE 1: Fairchild Service Bulletins SA226-24-032 and SA227-24-013 both dated August 7, 1989, pertain to the subject of this AD. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An alternate method or adjustment of the compliance time, which provides an equivalent level of safety, may be approved by the Manager, Airplane Certification Office, Federal Aviation Administration, Fort Worth, Texas 76193-0150. NOTE 2: The request should be forwarded through an FAA Maintenance Inspector, who may add commentsand then send it to the Manager, Airplane Certification Office, Fort Worth, Texas. All persons affected by this directive may obtain copies of the documents referred to herein upon request to the Fairchild Aircraft Corporation, P.O. Box 790490, San Antonio, Texas 78279-0490, or may examine these documents at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This AD revises AD 90-03-19, Amendment 39-6499. This amendment (39-6672, AD 90-03-19 R1) becomes effective on August 15, 1990.
2016-12-04: We are adopting a new airworthiness directive (AD) for all Airbus Model A318 series airplanes; A319 series airplanes; A320-211, - 212, -214, -231, -232, and -233 airplanes; and A321 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain structural repair manual (SRM) inspection requirements for the fuselage skin repairs are insufficient to detect cracks. This AD requires an inspection to determine whether any fuselage external skin (doubler) repairs have been accomplished, an inspection for cracking of certain repaired external fuselage skin areas in the fuselage, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin, which could result in reduced structural integrity of the airplane.