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2010-18-08: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: During testing, it was discovered that when the outflow valve (OFV) manual mode connector is not connected, the manual mode motor and altitude limitation are not properly tested. Consequently, a disconnect of the OFV manual mode and/or a related wiring failure could potentially result in a dormant loss of several CPC [cabin pressure control] backup/safety functions, including OFV manual control, altitude limitation, emergency depressurization and smoke clearance. * * * * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective October 7, 2010. The Directorof the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 7, 2010. On May 29, 2009 (74 FR 22646, May 14, 2009), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD.
76-07-09: 76-07-09 COLLINS: Amendment 39-2570. Applies to Collins Model 332C-10 Radio Magnetic Indicator (part numbers and serial numbers listed below) installed on various aircraft makes and models equipped with 24 V electrical systems: Collins Part No. Serial No. 622-0555-001 729 and below 622-0555-002 963 and below 622-0555-003 3593 and below, 3595 thru 3600, 3602 thru 3611, 3613 thru 3628 622-0555-004 3693 and below, 3695 thru 3706 622-0555-005 3252 and below 622-0555-006 4156 and below 622-0555-007 3208 and below, 3210 thru 3231, 3233 thru 3239 622-0555-008 2805 and below Compliance: Required as indicated, unless already accomplished. To preclude possible erroneous VOR bearing information presentation, with no flag warning, when 26 VAC input power is lost, accomplish the following: A) Within 50 hours" time in service in service after the effective date of this AD, determine if the 332C-10 Radio Magnetic Indicator(s) is (are) installed, and if so, whether modified in accordance with Collins 332C-10 Radio Magnetic Indicator (622-0555-XXX) Service Bulletin No. 6, dated February 16, 1976, or later approved revision. On those units not modified in accordance with Service Bulletin No. 6, prior to further flight, install a placard on glass face of the magnetic indicator which reads: "USE ADF MODE ONLY" and operate the unit in accordance with this limitation. NOTE: Indicators which have been modified in accordance with Service Bulletin No. 6 will have the No. 6 removed from the modification plate attached to the unit. B) On or before January 1, 1977, modify the 332C-10 indicators(s) in accordance with Collins 332C-10 Radio Magnetic Indicator (622-0555-XXX) Service Bulletin No. 6, dated February 16, 1976, or later approved revisions. C) When Paragraph B has been accomplished, compliance with Paragraph A is no longer required. D) Any alternate method of compliance with this AD must be approvedby the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective April 19, 1976.
76-10-12: 76-10-12 BEECH: Amendment 39-2620. Applies to Beech Aircraft Corporation B200, R201, R202, R203, and 214 Series wood blade propellers having Beech Aircraft Corporation manufactured B200, R201, R203, 214 or 272 Series blades installed. (These propellers were installed originally on Beech Models 35, A35, B35, C35, D35, E35, 35R, 45 (Military YT-34), and 50 (Military L-23A) airplanes, but may be installed on other airplanes.) Compliance: Required as indicated, unless already accomplished. To prevent failure of wood blades in these propellers, accomplish the following: A) Within the next 100 hours' time in service or one year, whichever comes first, after the effective date of this AD, and thereafter at intervals not to exceed 300 hours' time in service or five years, whichever comes first, from the last inspection, visually inspect the blades as follows: 1. Carefully remove the plastic coating to expose the shank of the blade for a minimum distance of 4 1/2" outboard of the ferrule. 2. Using a 10-power glass, visually inspect the blade surface for cracks and separation as shown on the reproduction of a deteriorated blade in Figure 1. 3. If no deterioration is found, reinstall the plastic film over the exposed area in accordance with Univair Process (P-200) or an FAA-approved equivalent procedure. 4. If the blade shows any sign of deterioration prior to further flight, remove it from service and replace it with an eligible airworthy blade. 5. Only an approved propeller repair station is authorized to accomplish the inspection required in this paragraph. B) Within the next 100 hours' time in service or one year, whichever comes first, after the effective date of this AD and at each annual inspection thereafter, visually inspect the blade leading edge and tips as follows: 1. Using a 10-power magnifying glass examine the tipping area for cracks in the plastic coating coming from under the tipping. 2. Check for looseness of the tip and leading edge sheathing by holding the blade securely and gripping the sheathing by hand and attempting to flex the tipping while visually observing for relative motion between the piece to which force is applied and adjacent sheathing and blade. 3. If any of the above conditions are noted, prior to further flight, replace the blade with an eligible airworthy blade. NOTE 1: (Beech Aircraft Corporation no longer manufactures Beech Models 214, B200, R201, R202 and R203 propellers; however, propellers and replacement blades as hereinafter listed may be installed on the indicated airplane models.) REPLACEMENT UNIVAIR WOOD BLADES Univair Blade Model Beech Propeller Assembly Model FA203-218 or FA203-219 R200-100/R201-217-88 and R203-218-88 FA200-244 or FA200-245 B200-105/B200-220-88 and B200-100/B200-220-88 and B200-100-B200-244-88 and B200-100/B200-234-88 and B200-100/B200-264-88 See Propeller Specification P-875 for further information. REPLACEMENT METAL BLADE PROPELLER ASSEMBLIES Eligible Propeller Assemblies Aircraft Models Beech 215-109/215-207-88 35, A35, B35, C35, D35, E35, 35R Beech 215-109/215-213-84 or Beech 215-107/215-213-84 A35, B35, C35, D35, E35, F35, G35 Beech 215-107/215-207-88 35, A35, B35, C35, D35, E35, 35R Hartzell HC12X20-7(B,C or D) or Hartzell HCD2X20-7/8433-0 35, A35, B35, C35, D35, E35, 35R Beech 215-102/272-234-98 Model 50 See Aircraft Type Certificate Data Sheet and/or Propeller Specifications for approval of specific airplane propeller engine combinations. This amendment becomes effective June 2, 1976.
77-15-08: 77-15-08 AVIONS MARCEL DASSAULT-BREGUET AVIATION (AMD-BA): Amendment 39-2981. Applies to Model Falcon 10 airplanes, certificated in all categories, incorporating SICMA AERO-SEAT pilot seat, P/N 376-2, or copilot seat, P/N 376-3. Compliance is required within the next 100 hours time in service after the effective date of this AD unless already accomplished. To prevent possible unwanted movement of a pilot or copilot seat when operating in turbulence or when performing high-g maneuvers, for SICMA AERO-SEAT pilot seats, P/N 376-2, and copilot seats, P/N 376-3, modify the seat rails and reidentify the seats in accordance with SICMA AERO-SEAT Service Bulletin 376/F10/BS01, dated June 5, 1975, including Revision "A", dated July 1975, or an FAA-approved equivalent. (AMD-BA Service Bulletin No. F10/0093 (ATA No. F10/25/007), dated July 18, 1975, pertains to this subject.) This amendment becomes effective August 22, 1977.
82-19-04: 82-19-04 BRITISH AEROSPACE (formerly Hawker Siddeley): Amendment 39-4462. Applies to H.S. 748 Series 2A airplanes certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent loss of an emergency overwing exit panel during flight, accomplish the following within thirty days after the effective date of this AD: 1. Remove the word "CLOSED" and the associated indicator line from the exterior of the overwing emergency exit panels. 2. Inspect each overwing emergency exit panel for free movement of the handle and lock operating mechanism in accordance with paragraphs 2A(1), (2), (3), and (4) of the H.S. Service Bulletin A52-82, dated May 31, 1979, Accomplishment Instructions. 3. Check the fit of each overwing emergency exit panel in the fuselage aperture in accordance with Chapter 52-20-1 of the H.S. 748 Maintenance Manual or an FAA approved equivalent procedure. 4. Reestablish the indicator marking on the cam lever in accordance with paragraph 2A(4) of the service bulletin if the inspections and checks required in paragraph 2 of this AD show the indicator markings on the cam lever and the lever stop do not coincide. 5. Alternate means of compliance with this AD which provide an equivalent level of safety may be used when approved by the Manager, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 6. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). This amendment becomes effective September 28, 1982.
93-23-11: 93-23-11 MCDONNELL DOUGLAS: Amendment 39-8747. Docket 93-NM-51-AD. \n\n\tApplicability: All Model DC-9-10, -20, -30, -40, and -50 series airplanes; Model DC-9-81, -82, -83, and -87 series airplanes; Model MD-88 airplanes; and C-9 (military) airplanes; equipped with nose wheel assembly part number 9550267-6 or 9550267-7; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent reduced structural integrity of the nose wheel assembly, resulting from installation of a suspected unapproved part, accomplish the following: \n\n\t(a)\tWithin 60 days after the effective date of this AD, accomplish either paragraph (a)(1) or (a)(2) of this AD. \n\n\t\t(1)\tPerform a one-time visual inspection of nose wheel assemblies, part numbers 9550267-6 and 9550267-7, to ensure that these assemblies are identified correctly in accordance with Section II, Accomplishment Instructions, of Aircraft Braking Systems Corporation Service Letter MD81-SL-3, MD82-SL-3, MD83-SL-4, MD87-SL-3, MD88-SL-4, MD90-SL-1, DC9-10-SL-12, DC9-30-SL-16, DC9-40-SL-16, DC9-50-SL-8 (included in one document), dated February 10, 1993. \n\n\t\t\t(i)\tIf any nose wheel assembly is not identified correctly, prior to further flight, replace that assembly with an FAA-approved assembly in accordance with the applicable Aircraft Maintenance Manual. \n\n\t\t\t(ii)\tIf each nose wheel assembly is identified correctly, no further action is required by this paragraph. \n\n\t\t(2)\tDetermine if the nose wheel assemblies, part numbers 9550267-6 and 9550267-7, have ever been in the possession of Aviation Wheel and Brake, Miami, Florida. This determination may be accomplished by performing a search of maintenance or other records. \n\n\t\t\t(i)\tIf it is not possible to make such a determination, or if the results of that determination indicate that any nose wheel assembly has been in the possession of Aviation Wheel and Brake, accomplish the inspection required by paragraph (a)(1) of this AD. \n\n\t\t\t(ii)\tIf it is determined that a nose wheel assembly has never been in the possession of Aviation Wheel and Brake, no further action is required by this paragraph with respect to that nose wheel assembly. \n\n\t(b)\tAs of the effective date of this AD, no person shall install a nose wheel assembly, part number 9550267-6 or 9550267-7, on any airplane unless, prior to installation, that nose wheel assembly has been inspected in accordance with the requirements of paragraph (a)(1) of this AD and has been found to be identified correctly; or unless, prior to installation, it has been determined that the nose wheel assembly has never been in the possession of Aviation Wheel and Brake in accordance with the requirements of paragraph (a)(2) of this AD. \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, Los Angeles 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, Los Angeles ACO. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles 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 inspection shall be done in accordance with Aircraft Braking Systems Corporation Service Letter MD81-SL-3, MD82-SL-3, MD83-SL-4, MD87-SL-3, MD88-SL-4, MD90-SL-1, DC9-10-SL-12, DC9-30-SL-16, DC9-40-SL-16, DC9-50-SL-8 (included in one document), dated February 10, 1993. 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 Aircraft Braking Systems Corporation, 1204 Massillon Road, Akron, Ohio 44306-4186. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; 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 January 5, 1994.
93-21-10: 93-21-10 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-8724. Docket Number 91-ASW-18. Applicability: Model 214B and 214B-1 helicopters, serial numbers (S/N's) 28001 through 28070, equipped with main rotor yoke assembly (assembly), part number (P/N) 214-010-105-001, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the assembly, loss of the main rotor, and subsequent loss of control of the helicopter, accomplish the following: (a) For assemblies that have 3,700 hours' or less time-in-service on the effective date of this airworthiness directive (AD), replace the assembly on or before reaching 3,750 hours' time-in-service. For assemblies that have more than 3,700 hours' time-in-service on the effective date of this AD, replace the assembly within the next 50 hours' time-in-service. (b) Within 50 hours' time-in-service after the effective date of this AD, install new airspeed versusaltitude decals, P/N 214-075-256-105 for BHTI Model 214B-1 and P/N 214-075-256-107 for Model 214B helicopters. (c) Within 50 hours' time-in-service after the effective date of this AD and thereafter at intervals of 1,200 hours' time-in-service, inspect the yoke for straightness in accordance with the applicable maintenance manual. NOTE: BHTI Alert Service Bulletin No. 214-87-37, Revision A, dated September 10, 1987, pertains to this AD. (d) 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 Certification Office, FAA, Rotorcraft Directorate, Fort Worth, Texas 76193-0170. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Certification Office. (e) 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. (f) This amendment becomes effective on January 18, 1994.
91-25-01: 91-25-01 ISRAEL AIRCRAFT INDUSTRIES (IAI), LTD.: Amendment 39-8102. Docket No. 91- NM-219-AD. Applicability: All Model 1125 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent uncontrolled pitch trim movement, accomplish the following: (a) Within 3 days after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the following. This may be done by inserting a copy of this AD in the AFM. "BEFORE TAXIING Horizontal stabilizer trim - CHECK OVERRD & EMERG; EMERG ARM pushbutton - DISENGAGE, CHECK NORMAL (buzzer) NOTE When checking override system, observe trim indicator; electrical limit switches are inoperative. CAUTION Do not use emergency trim in place of normal or override trim systems. Use of emergency trim is limited to elevator control failure (Section II, page II-28) and horizontal stabilizertrim failure (Section III, page III-9)." NOTE: Inserting Astra (Model 1125) AFM Temporary Revision No. 3, dated June 9, 1991, in the Limitations section of the AFM, or inserting an AFM revision containing this information, is considered an acceptable alternative method of compliance with this paragraph. (b) Within 3 days after the effective date of this AD, revise the Normal Procedures Section of the FAA-approved AFM to include the following. This may be done by inserting a copy of this AD in the AFM. "BEFORE TAXIING Horizontal stabilizer trim - CHECK OVERRD & EMERG; EMERG ARM pushbutton - DISENGAGE, CHECK NORMAL (buzzer) NOTE When checking override system, observe trim indicator; electrical limit switches are inoperative. CAUTION Do not use emergency trim in place of normal or override trim systems. Use of emergency trim is limited to elevator control failure (Section II, page II-28) and horizontal stabilizer trim failure (Section III, page III-9)." NOTE: Inserting Astra (Model 1125) AFM Temporary Revision No. 3, dated June 9, 1991, in the Procedures Section of the AFM, or inserting an AFM revision containing this information, is considered an acceptable alternative method of compliance with this paragraph. (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, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Operations Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. (d) 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. (e) This amendment (39-8102, AD 91-25-01) becomes effective on December 10, 1991.
93-02-09: 93-02-09 SAAB-SCANIA: Amendment 39-8492. Docket 92-NM-121-AD. Applicability: Model SAAB SF340A series airplanes, serial numbers 004 through 159, inclusive; and Model SAAB 340B series airplanes, serial numbers 160 through 339, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent damage/disbonding of the fuselage skin due to overheat, and subsequent reduced structural capability, accomplish the following: (a) Within 3 months after the effective date of this AD, relocate the sensor loops of the bleed air leak detection system, in accordance with SAAB-SCANIA Service Bulletin SAAB 340-36-006, dated August 6, 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 relocation shall be done in accordance with SAAB-SCANIA Service Bulletin SAAB 340-36-006, dated August 6, 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 SAAB-SCANIA AB, SAAB Aircraft Product Support, S-581 88, Link ping, Sweden. 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. (e) This amendment becomes effective on March 26, 1993.
76-21-01: 76-21-01 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-2745. Applies to Lockheed Model L-1011-385 series airplanes certificated in all categories having C-1A cargo door installed. Compliance required within the next 300 hours' time in service after the effective date of this AD, unless already accomplished. To prevent the latch pins on the latch fittings of the C-1A cargo door surround structure from being incorrectly installed during maintenance replacement, which could result in a possible in-flight loss of the C-1A cargo door, accomplish the following: a. Install latch pin guard assemblies and related components, reidentify the latch fitting assemblies and check proximity sensors adjustment as necessary, on the C-1A cargo door surround structure, in accordance with Lockheed-California Company Service Bulletin 093-52-083 dated May 25, 1976, or later FAA-approved revision or equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region.b. Airplanes may be flown in accordance with FAR 21.197 to a base where the modification can be performed. This amendment becomes effective November 20, 1976.