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93-07-15: 93-07-15 BOEING AND MCDONNELL DOUGLAS: Amendment 39-8547. Docket No. 92- NM-67-AD. Supersedes AD 91-10-02, Amendment 39-6986. \n\n\tApplicability: Boeing Models 707, 727, 737, 747, and 757 series airplanes and McDonnell Douglas Models DC-8, DC-9, and DC-10 series airplanes; equipped with a main deck Class B cargo compartment, as defined by Federal Aviation Regulations (FAR) 25.857(b) or its predecessors, with a volume exceeding 200 cubic feet; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo minimize the hazard associated with a main deck Class B cargo compartment fire, accomplish the following: \n\n\t(a)\tWithin one year after May 3, 1990 (the effective date of Amendment 39-6557, AD 89-18-12 R1), or prior to carrying cargo in a Class B cargo compartment, whichever occurs later, accomplish the following in accordance with the appropriate technical data approved by the Manager, Seattle Aircraft Certification Office (for affected Boeing series airplanes), FAA, Transport Airplane Directorate; or the Manager, Los Angeles Aircraft Certification Office (for affected McDonnell Douglas series airplanes), FAA, Transport Airplane Directorate: \n\n\t\t(1)\tRevise the Limitations Section of the FAA-approved Airplane Flight \t\t\tManual (AFM) to include the following: "FOR EACH FLIGHT IN \t\t\t\tWHICH CARGO IS TRANSPORTED IN THE CLASS B CARGO \t\t\t\tCOMPARTMENT: Prior to flight, a flight deck crewmember must \t\t\t\tmake a visual inspection throughout the Class B cargo compartment \t\t\tto verify access to cargo and the general fire security of the \t\t\t\tcompartment after the cargo door is closed and secured." \n\n\tNOTE 1: This visual inspection is in no manner intended to relieve the pilot of his/her responsibility to ensure safe operation of the airplane, as required by FAR 91.3. \n\n\t\t(2)\tIncorporate the following systems and equipment: \n\n\t\t\t(i)\tProvide a minimum of 48 lbs. Halon 1211 fire extinguishant, or its equivalent, in portable fire extinguisher bottles readily available for use in the cargo compartment. At least two bottles must be a minimum of 16 lb. capacity. \n\n\t\t\t(ii)\tProvide at least two Underwriters Laboratories (UL)2A (2-1/2 gallon) rated water portable fire extinguishers, or its equivalent, adjacent to the cargo compartment entrance for use in the compartment. \n\n\t\t\t(iii)\tProvide a means for two-way communication between the flight deck and the interior of the cargo compartment. \n\n\t\t\t(iv)\tInstall placards in conspicuous place(s) within the cargo compartment clearly defining the cargo loading envelope and limitations that provide sufficient access of sufficient width for firefighting along the entire length of at least two sides of a loaded pallet or container. Amend the appropriate Weight and Balance and loading instructions by description and diagrams to include this information. \n\n\t\t(3)\tIncorporate the following systems and equipment: \n\n\t\t\t(i)\tProvide appropriate protective garmentsstored adjacent to the cargo compartment entrance. \n\n\t\t\t(ii)\tProvide a minimum of 30 minutes of protective breathing. This equipment must meet the requirements of Technical Standard Order (TSO) C-116, Action Notice 8150.2A, or equivalent, and be stored adjacent to the cargo compartment entrance. \n\n\t(b)\tWithin 42 months after the effective date of this AD, or prior to carrying cargo in a Class B cargo compartment, whichever occurs later, accomplish the requirements of either paragraph (b)(1), (b)(2), (b)(3), or (b)(4) of this AD: \n\n\t\t(1)\tOPTION 1: Modify the Class B cargo compartment to comply with the requirements for a Class C cargo compartment, as defined in FAR 25.855 (Amdt. 25-60), 25.857(c), and 25.858 (Amdt. 25-54). \n\n\t\t(2)\tOPTION 2: Modify all main deck Class B cargo compartments to require the following placard installed in conspicuous locations approved by the Manager, Seattle Aircraft Certification Office, FAA, Transport Airplane Directorate (for affected Boeing series airplanes), or the Manager, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate (for affected McDonnell Douglas series airplanes), throughout the compartment: "Cargo carried in this compartment must be loaded in an approved flame penetration-resistant container meeting the requirements of FAR 25.857(c) with ceiling and sidewall liners and floor panels that meet the requirements of FAR 25, Appendix F, Part III, (Amdt. 25-60)." \n\n\t\t(3)\tOPTION 3: In addition to the requirements of paragraph (a)(2) of this AD, accomplish the following in accordance with technical data approved by the Manager, Seattle Aircraft Certification Office (for affected Boeing series airplanes), or the Manager, Los Angeles Aircraft Certification Office (for affected McDonnell Douglas series airplanes): \n\n\t\t\t(i)\tCarriage of all cargo in Class B cargo compartments must meet the requirements of either paragraph (b)(3)(i)(A) or (b)(3)(i)(B) of this AD: \n\n\t\t\t\t(A)\tCover cargo with fire containment covers. \n\n\t\t\t\t(B)\tCarry cargo in fire containment containers. \n\n\t\t\t(ii)\tProvide a smoke or fire detection system in the Class B cargo compartment that meets the requirements of FAR 25.858 (Amdt. 25-54) and also provides an aural and visual warning to the crewmembers in the passenger compartment. \n\n\t\t\t(iii)\tProvide a barrier between the Class B cargo compartment and the passenger compartment to prevent the penetration of smoke or flames from the cargo compartment into the passenger compartment. The barrier must extend from the cargo compartment floor to the upper crown area of the fuselage, and from the right sidewall to the left sidewall of the cargo compartment, completely isolating the cargo compartment from the passenger compartment. The barrier and associated seals/interfaces must meet the requirements of FAR 25, Appendix F, Part III (Amdt. 25-60). \n\n\t\t\t(iv)\tProvide illumination of the Class B cargo compartment as specified in paragraphs (b)(3)(iv)(A) and(b)(3)(iv)(B) of this AD: \n\n\t\t\t\t(A)\tGeneral area illumination of the cargo with an average illumination of 0.1 foot-candle measured at 40-inch intervals both at one-half the pallet or container height, and at the full pallet or container height, or as approved by the FAA. \n\n\t\t\t\t(B)\tIllumination of the longitudinal access pathways, required by paragraph (a)(2)(iv) of this AD, with an average illumination of .05 foot-candle when measured at 40-inch intervals along a line that is within 2 inches of and parallel to the floor centered on the pathway, or illumination under visibility conditions likely to occur in the cargo compartment in the event of a fire. \n\n\t\t\t(v)\tEstablish FAA-approved procedures and training as specified in paragraphs (b)(3)(v)(A) and (b)(3)(v)(B) of this AD: \n\n\t\t\t\t(A)\tUse and maintenance of items required by paragraph \t\t\t\t\t(b)(3)(i). \n\n\t\t\t\t(B)\tResponding to alarms, and monitoring and controlling \t\t\t\t\tClass B cargo compartment fires. \n\n\t\t\t(vi)\tProvide a viewport into the Class B cargo compartment from the passenger compartment. The viewport must be located such that a crewmember can readily identify the overall smoke conditions in the compartment prior to entering it. \n\n\t\t\t(vii)\tDemonstrate the following features and functions, specified in paragraphs (b)(3)(vii)(A), (b)(3)(vii)(B), and (b)(3)(vii)(C) of this AD: \n\n\t\t\t\t(A)\tSmoke or Fire Detection System, required by paragraph (b)(3)(ii) of this AD, by flight test. \n\n\t\t\t\t(B)\tPrevention of smoke penetration into occupied compartments (refer to FAR 25.857(b)(2) and 25.855(e)(2)), by flight test. \n\n\t\t\t\t(C)\tCargo accessibility, as specified in paragraph \t\t\t\t\t\t(a)(2)(iv) of this AD. \n\n\t\t\t(viii) \tProvide the following systems and equipment: \n\n\t\t\t\t(A)\tProvide appropriate protective garments for two persons stored in the passenger compartment, adjacent to the Class B cargo compartment entrance. \n\t\t\t\t(B)\tProvide a minimum of 120 minutes of protective breathing for one person, and an additional 30 minutes of protective breathing for an additional person. This equipment must meet the requirements of Technical Standard Order (TSO) C-116, Action Notice 8150.2A, or equivalent, and at least 30 minutes of the total protective breathing must be stored adjacent to the Class B cargo compartment entrance. All protective breathing equipment must be located outside the cargo compartment. \n\n\t\t\t(ix)\tRevise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the following:\n\n\t\t\t\t "FOR EACH FLIGHT IN WHICH CARGO IS \t\t\t\t\t\tTRANSPORTED IN THE CLASS B CARGO \t\t\t\t\t\tCOMPARTMENT:\n\t\t\t\t Prior to flight, a \tcrewmember who is assigned firefighting \t\t\t\tresponsibility for the flight must make a visual inspection \t\t\t\t\tthroughout the Class B cargo compartment for familiarization, \t\t\t\tafter the cargo door is closed and secured." \n\n\tNOTE 2: This visual inspection is in no manner intended to relieve the pilot of his/her responsibility to ensure safe operationof the airplane, as required by FAR 91.3. \n\n\t\t(4)\tOPTION 4: In addition to the requirements of paragraph (a)(2) of this AD, accomplish the following in accordance with technical data approved by the Manager, Seattle Aircraft Certification Office (for affected Boeing series airplanes), or the Manager, Los Angeles Aircraft Certification Office (for affected McDonnell Douglas series airplanes): \n\n\t\t\t(i)\tProvide a cargo compartment fire extinguishing system in the Class B cargo compartment that provides an initial fire extinguishant concentration of at least 5 percent of the empty compartment volume of Halon 1301 or equivalent, and a fire suppression extinguishant concentration of at least 3 percent of the empty compartment volume of Halon 1301 or equivalent, for a period of time not less than 90 minutes. \n\n\t\t\t(ii)\tProvide a smoke or fire detection system in the Class B cargo compartment that meets the requirements of FAR 25.858 (Amdt. 25-54) and also provides an aural and visual warning to the crewmembers in the passenger compartment. \n\n\t\t\t(iii)\tProvide a means from the flight deck to shut off ventilation system inflow to the Class B cargo compartment. \n\n\t\t\t(iv)\tProvide a barrier between the Class B cargo compartment and the passenger compartment to prevent the penetration of smoke or flames from the cargo compartment into the passenger compartment. The barrier must extend from the cargo compartment floor to the upper crown area of the fuselage, and from the right sidewall to the left sidewall of the cargo compartment, completely isolating the cargo compartment from the passenger compartment. The barrier and associated seals/interfaces must meet the requirements of FAR 25, Appendix F, Part III (Amdt. 25-60). \n\n\t\t\t(v)\tProvide appropriate protection of the cockpit voice and flight data recorders, and all systems or components required for safe flight and landing of the airplane, unless it can be demonstrated that these systems are not susceptible to damagein the event of a fire in the Class B cargo compartment. \n\n\t\t\t(vi)\tProvide illumination of the Class B cargo compartment as specified in paragraphs (b)(4)(vi)(A) and (b)(4)(vi)(B) of this AD: \n\n\t\t\t\t(A)\tGeneral area illumination of the cargo with an average illumination of 0.1 foot-candle measured at 40-inch intervals both at one-half the pallet or container height, and at the full pallet or container height, or as approved by the FAA. \n\n\t\t\t\t(B)\tIllumination of the longitudinal access pathways, required by paragraph (a)(2)(iv) of this AD, with an average illumination of .05 foot-candle when measured at 40-inch intervals along a line that is within 2 inches of and parallel to the floor centered on the pathway, or illumination under visibility conditions likely to occur in the cargo compartment in the event of a fire, as approved by the FAA. \n\n\t\t\t(vii)\tEstablish FAA-approved procedures and training for responding to alarms, and monitoring and controlling cargo compartment fires.(viii) \tProvide a viewport into the Class B cargo compartment from the passenger compartment. The viewport must be located such that a crewmember can readily identify the overall smoke conditions in the compartment prior to entering it.\n \n\t\t\t(ix)\tDemonstrate the following features and functions: \n\n\t\t\t\t(A)\tFire extinguishant concentration, required by paragraph (b)(4)(i) of this AD, by flight test. \n\n\t\t\t\t(B)\tSmoke or fire detection system, required by paragraph (b)(4)(ii) of this AD, by flight test. \n\n\t\t\t\t(C)\tPrevention of smoke penetration into occupied compartments (refer to FAR 25.857(b)2 and 25.855(e)2), demonstrated by flight test. \n\n\t\t\t\t(D)\tCargo accessibility, as specified in paragraph (a)(2)(iv) of this AD. \n\t\t\t(x)\tProvide the following systems and equipment: \n\n\t\t\t\t(A)\tProvide appropriate protective garments for two persons stored in the passenger compartment, adjacent to the Class B cargo compartment entrance. \n\t\t\t\t(B)\tProvide a minimum of 120 minutes of protective breathing for one person, and an additional 30 minutes of protective breathing for an additional person. This equipment must meet the requirements of Technical Standard Order (TSO) C-116, Action Notice 8150.2A, or equivalent, and at least 30 minutes of the total protective breathing must be stored adjacent to the Class B cargo compartment entrance. All protective breathing equipment must be located outside the cargo compartment. \n\n\t\t\t(xi)\tRevise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the following statement: \n\n\t\t\t\t"FOR EACH FLIGHT IN WHICH CARGO IS TRANSPORTED \t\t\t\tIN THE CLASS B CARGO COMPARTMENT: \n\t\t\t\tPrior to flight, a crewmember who is assigned firefighting \n\t\t\t\tresponsibility for the flight must make a visual inspection \n\t\t\t\tthroughout the Class B cargo compartment for familiarization, \t\t\t\tafter the cargo door is closed and secured." \n\n\tNOTE 3: This visual inspection is in no manner intended to relieve the pilot ofhis/her responsibility to ensure safe operation of the airplane, as required by FAR 91.3. \n\n\t(c)\tCompliance with paragraph (b)(1) or (b)(2) of this AD constitutes terminating action for the requirements of paragraph (a) of this AD. Compliance with paragraph (b)(3) or (b)(4) of this AD constitutes terminating action for the requirements of paragraphs (a)(1) and (a)(3) of this AD. \n\n\t(d)\tAn alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate (for affected Boeing series airplanes); or the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate (for affected McDonnell Douglas series airplanes). Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, of the Seattle ACO, orthe Manager of the Los Angeles ACO, as appropriate. \n\n\tNOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO or the Los Angeles ACO. \n\n\tNOTE 5: Alternative methods of compliance previously granted for Amendment 39- 6557, AD 89-18-12 R1; or Amendment 39-6986, AD 91-10-02; continue to be considered as acceptable alternative methods of compliance with this amendment. \n\n\t(e)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. \n\n\tThis AD supersedes AD 91-10-02, Amendment 39-6986, which superseded AD 89-18- 12 R1, Amendment 39-6557. \n\n\t(f)\tThis amendment becomes effective on May 2, 1993.
96-18-05: This amendment supersedes an existing priority letter airworthiness directive (AD), applicable to Bell Helicopter Textron, A Division of Textron Canada Ltd. (BHTC) Model 206L, 206L-1, and 206L-3 helicopters, that currently requires a visual inspection of the tailboom skin in the areas around the nutplates and in the areas of the tailboom drive shaft cover retention clips for cracks and corrosion using a 10-power or higher magnifying glass. This amendment requires the same actions as the existing AD, but corrects a part number that was incorrectly stated in that AD. This amendment is prompted by a recent accident and several reports of fatigue cracks in the tailboom skin in the areas around the nutplates for the tail rotor fairing and in the areas of the tail rotor drive shaft cover retention clips. The actions specified by this AD are intended to prevent failure of the tailboom and subsequent loss of control of the helicopter.
95-15-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Aerospatiale Model ATR42 series airplanes. This action requires replacement of the currently installed side brace pins of the main landing gear (MLG) with new pins. This amendment is prompted by a report of a ruptured pin on an in-service airplane. The actions specified in this AD are intended to prevent failure of the side brace pins and the subsequent collapse of the MLG.
76-09-01: 76-09-01 BEECH: Amendment 39-2589. Applies to Models 65, A65 and A65-8200 (Serial Numbers L-1, L-2, L-3, LF-7, LF-8 and LC-1 thru LC-335), Model 70 (Serial Numbers LB-1 thru LB-35), and Models 65-80, 65-A80, 65-A80-8800 and 65-B80 (Serial Numbers LD-1 thru LD-494) airplanes. Compliance: Required as indicated, unless already accomplished. To provide instruction on the operation of the emergency exit door, within the next 100 hours' time in service after the effective date of this AD, accomplish the following: A) On all airplanes, below the existing emergency exit operating instructions placard, install P/N 50-535033-7 decal or an equivalent pressure sensitive decal which reads: "DO NOT OPEN IN FLIGHT" B) On all airplanes, except Model 65-B80, add Airplane Flight Manual Supplement P/N 1313300 dated March 28, 1975, or later date, to the existing FAA-approved flight manual. C) On Model 65-B80 airplanes, examine the FAA-approved flight manual to verifythat it is P/N 50-590211-1A3, revised May 30, 1975, and if not, install same in the airplane. This amendment becomes effective April 30, 1976.
92-25-04: 92-25-04 BOEING: Amendment 39-8419. Docket No. 92-NM-108-AD.\n \n\tApplicability: Model 737 series airplanes, as listed in Boeing Alert Service Bulletin 737- 35A1037, dated February 13, 1992, and Boeing Alert Service Bulletin 737-35A1038, dated March 19, 1992; and Model 757 series airplanes, as listed in Boeing Alert Service Bulletin 757- 35A0010, dated February 13, 1992; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent maintenance test stop plungers from interfering with proper deployment of oxygen masks, accomplish the following: \n\n\t(a)\tFor Model 737 series airplanes: Within 900 flight hours or 6 months after the effective date of this AD, whichever occurs later, accomplish the requirements of paragraphs (a)(1) and (a)(2) of this AD. \n\n\t\t(1)\tModify the test stop plungers in the oxygen box assemblies in the lavatories in accordance with Boeing Alert Service Bulletin 737-35A1037, dated February 13, 1992.(i)\tAs an alternative action, operators may accomplish the modification of the test stop with the oxygen box assembly removed from the airplane. \n\n\t\t\t(ii)\tIn lieu of the method for reidentification of the test stop prescribed in the service bulletin, operators may use an alternative method of reidentification if it is approved by the cognizant FAA Principal Maintenance Inspector (PMI). \n\n\t\t(2)\tModify the oxygen box assemblies in modular lavatory "A" in accordance with Boeing Alert Service Bulletin 737-35A1038, dated March 19, 1992. \n\n\t(b)\tFor Model 757 series airplanes: Within 900 flight hours or 6 months after the effective date of this AD, whichever occurs later, modify the test stop plungers in the oxygen box assemblies in the lavatories and at doors 1 and 4 flight attendant seats in accordance with Boeing Alert Service Bulletin 757-35A0010, dated February 13, 1992. \n\n\t\t(1)\tAs an alternative action, operators may accomplish the modification of the test stop with the oxygen box assembly removed from the airplane. \n\n\t\t(2)\tIn lieu of the method for reidentification of the test stop prescribed in the service bulletin, operators may use an alternative method of reidentification if it is approved by the cognizant FAA Principal Maintenance Inspector (PMI). \n\n\t(c)\tAn alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. \n\n\t(d)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. \n\n\t(e)\tThe modifications shall be done in accordance with Boeing Alert Service Bulletin 737-35A1037, dated February 13, 1992; Boeing Alert Service Bulletin 737-35A1038, dated March 19, 1992; or Boeing Alert Service Bulletin 757-35A0010, dated February 13, 1992; as applicable. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. \n\n\t(f)\tThis amendment becomes effective on December 23, 1992.
77-08-03: 77-08-03 GRUMMAN AMERICAN AVIATION CORPORATION: Amendment 39- 2873. Applies to Model AA-5A, serials AA5A-0001 through AA5A-0340 and Model AA-5B, serials AA5B-0001 through AA5B-0451 airplanes equipped with an alternate static source system. Compliance required prior to further flight under Instrument Flight Rules (IFR) or night flight, or within the next 25 hours day Visual Flight Rules (VFR) time in service after the effective date of this AD or the next scheduled inspection, whichever comes first, unless already accomplished. To prevent faulty altitude, airspeed, and vertical speed indications from being presented to the pilot, accomplish the following: Disassemble, clean, lubricate, and reassemble the alternate static source valve, Gerdes part number A-1390, and leak test the static system in accordance with the following procedure: 1. Remove static source valve knob and jamb nut. 2. Note static line routing and remove lines from valve body. 3. Remove attach screws and valve assembly from aircraft. 4. Disassemble valve by removing hex bushing from forward end of valve and pushing valve shaft thru valve body. 5. Wipe and save all grease from valve shaft with a clean lint-free cloth. 6. Clean inside valve body with a lint-free cloth. 7. Blow compressed air thru fittings into valve body to clear ports. 8. Reclean inside of valve body. 9. Lubricate O-rings only with a very thin film of grease removed in Step 5. Keep rest of shaft dry. 10. Reassemble valve, mark serial number plate with a red dot, reinstall in instrument panel and reconnect lines to their respective ports. 11. Conduct a static system leak test according to the procedure in Grumman American Service Bulletin No. 160, dated March 21, 1977, or FAA Advisory Circular AC 43- 203A (Ref. FAR 23.1325). Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. This amendment becomes effective April 19, 1977.
95-15-11: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Jetstream Model 4101 airplanes. This action requires a visual inspection of the passenger seat belt assemblies to determine if certain seat belt shackles are installed, and replacement of those shackles with improved ones. This amendment is prompted by reports indicating that certain passenger seat belt shackles have failed. The actions specified in this AD are intended to prevent reduced effectiveness of the passenger safety restraint system during take-off and landing or in an emergency situation, due to failure of the passenger seat belt shackles.
90-25-17: 90-25-17 SOCATA GROUPE AEROSPATIALE: Amendment 39-6807. Docket No. 90-CE-45-AD. Applicability: Models TB9, TB10, TB20, and TB21 airplanes (all serial numbers), certificated in any category. Compliance: Required within the next 25 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent possible uncontrolled release of flammable fluids into the engine compartment and engine malfunction because of loss of oil, accomplish the following: (a) Visually inspect the mounting bases of the oil cooler inlet and outlet elbows and the sponsons located near the outlet fittings for cracks or distortions. (1) If no cracks or distortions are found, return the airplane to service. (2) If cracks or distortions are found, prior to further flight remove the damaged cooler and install a new engine oil cooler as specified below in accordance with SOCATA Groupe AEROSPATIALE TB Aircraft Mandatory Service Bulletin No. 50/1, undated:Model Oil Cooler Part Number TB9-TB10 Z00.12258.64 TB20 Z00.12258.513 TB21 Z00.12258.518 (b) Airplanes may be flown in accordance with FAR 21.197 and 21.199 to a location where the AD can be accomplished. (c) An alternate method of compliance or adjustment to the compliance time that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, 15 Rue de la Loi, B-1040, Brussels, Belgium. NOTE 1: 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 Staff. NOTE 2: All persons affected by this directive may obtain copies of the document referred to herein upon request to SOCATA Groupe AEROSPATIALE, Socata Product Support, Aeroport Tarbes-Ossun-Lourdes, B P 930, 65009 Tarbes Cedex, France; Telephone 62.41.74.26; Facsimile62.41.74.32; or the Product Support Manager, U.S.; AEROSPATIALE, 2701 Forum Drive, Grand Prairie, Texas 75053; Telephone (214) 641-3614; Facsimile (214) 641-3527; or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-6807, AD 90-25-17) becomes effective on January 3, 1991.
90-14-07: 90-14-07 MCDONNELL DOUGLAS: Amendment 39-6647. Docket No. 90-NM-104-AD. \n\n\tApplicability: Models DC-9-81, -82, -83, and -87 series airplanes, and Model MD-88 airplanes, delivered between December 30, 1989, and May 8, 1990, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent the loss of elevator control, accomplish the following: \n\n\tA.\tWithin 30 days after the effective date of this AD, conduct a visual inspection to determine the date on the elevator control tab identification tag (P/N 5910413-507/-508). The identification tag is located on the inboard side of the second hinge cutout from the inboard end of the control tab. \n\n\tNOTE: Do not use the date on the P/N 5910413-407/-408 tag, which is similar. \n\n\t\t1.\tConfirm that the elevator control tab assembly has not been changed from that which was delivered on the airplane; \n\n\t\t2.\tIf the elevator control tab assembly has been changed since the delivery of the airplane, the identification tag date of the original tab must be ascertained by inspection of the original part. \n\n\t\t3.\tIf the date on the identification tag is between December 30, 1989, and May 8, 1990, accomplish the following: \n\n\t\t\ta.\tRemove access opening door no. 3523A, left-hand, and 3624A, right-hand. (Reference Maintenance Manual 6-23-00, Figure 2.) \n\n\t\t\tb.\tCheck the elevator control tab fitting in the clevis area using Webster pliers, or equivalent per Douglas Process Specification (DPS) 1.05. Non-heat treated (soft) parts will exhibit a reading of less than 10 on the Webster pliers. Properly heat treated parts will have a reading of 10 or greater on Webster pliers, which is equivalent to Rockwell "B" 78-87, Rockwell "E" 103-107, or Brinell 126-147. \n\n\tNOTE: Remove all paint and primer locally before using Webster pliers. An invalid reading will be obtained if any paint remains in the indentation area. \n\n\tNOTE: Do not use conductivity readings as a methodof acceptance. \n\n\tB.\tIf the fittings are properly heat treated, no further action is required. \n\n\tC.\tIf the fittings have a Webster pliers reading of less than 10, before further flight, remove the fittings and replace them with fittings exhibiting a Webster pliers reading of 10 or greater. \n\n\tD.\tIf only one fitting per airplane is found to be soft, special 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\tE.\tAny elevator control tab fitting, P/N 5937825-1/-2, that fails the hardness test specified in paragraph A.3.b., above, shall not be subsequently installed on any airplane, unless the fitting is heat treated to meet the requirements in paragraph A.3.b. \n\n\tF.\tReplacement of the elevator control tab fittings with those exhibiting a Webster pliers reading of 10 or greater, constitutes an acceptable alternate means of compliance with the requirements of this AD. \n\n\tG.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, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Los Angeles ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Los Angeles ACO. \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: Business Unit Manager of Publications, C1-HCO (54-60). This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 3229 EastSpring Street, Long Beach, California. \n\n\tThis amendment (39-6647, AD 90-14-07) becomes effective on July 23, 1990.
93-01-22: 93-01-22 FOKKER: Amendment 39-8476. Docket 92-NM-177-AD. Applicability: Model F28 Mark 0100 series airplanes; serial numbers 11244 through 11365, inclusive, and 11367; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To ensure that the cabin attendants seated in the forward and aft cabin attendant seats can reach their oxygen masks in emergency situations, accomplish the following: (a) Within 6 months after the effective date of this AD, modify the oxygen drop-out panels of the forward and aft cabin attendant positions, in accordance with Fokker 100 Service Bulletin SBF100-35- 003, dated March 23, 1992. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The modification shall be done in accordance with Fokker 100 Service Bulletin SBF100- 35-003, dated March 23, 1992. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 NorthCapitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on March 10, 1993.