86-14-01 -- To prevent loss of attitude/heading reference information 14/07/1986 Amendment 39-5340. Applies to Sperry Corporation AHZ-600 Attitude Heading Reference System (AHRS), known to be installed in, but not limited to, DeHavilland Model DHC-8, British Aerospace Model BAe 125-800, Cessna Model 650, and Aerospatiale Model ATR-42 series airplanes, certificated in any category. Modify the Sperry Corporation AH-600 Strapdown Attitude and Heading Reference Unit (AHRU) by incorporating modifications in accordance with the following Sperry Service Bulletins or later revisions approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region: 21-1985-175, dated April 7, 1986 (Modification T); 21-1985-186, dated April 7, 1986 (Modifications S & V); 21-1985-187, dated April 7, 1986 (Modification U); 21-1986-19, dated April 22, 1986 (Modification Z); 21-1986-20, dated April 22, 1986 (Modification AA); and 21-1986-29, dated April 22, 1986 (Modification AB). N/A by Mod 87-06-02 -- To reduce the possibility of AHRS attitude and heading computations being contaminated, which can result in frozen attitude and heading displays on both instrument panels, accomplish the following 13/03/1987 Applicable to the following models of Sperry Electronics Flight Instrument Systems (EFIS) Symbol Generators, which have not been modified to Mod Level S or subsequent: MODEL SPERRY PART NUMBER SG-810 7004544-901 SG-811 7004544-811 SG-610 7004544-902 A. Prior to fiirther flight, install a placard adjacent to the first pilot's electronic attitude direction indicator (EADI), in full view of the pilot, stating "FLIGHT INTO KNOWN IMC PROHIBITED." B. Modification of the Sperry EFIS Symbol Generator models listed above to Mod Level S or subsequent, or installation of the following Sperry EFIS Symbol Generator models, constitutes terminating action of the operational and placard requirements of paragraph A., above: MODEL SPERRY PART NUMBERS MOD LEVEL (OR SUBSEQUENT) SG-811 7004544-211 V SG-811 7004544-311 AD SG-811 7004544-411 U SG-611 7004544-611 S B. Modification of the Sperry EFIS Symbol Generator models listed above to Mod Level S or subsequent, or installation of the following Sperry EFIS Symbol Generator models, constitutes terminating action of the operational and placard requirements of paragraph A., above: MODEL SPERRY PART NUMBERS MOD LEVEL (OR SUBSEQUENT) SG-811 7004544-211 V SG-811 7004544-311 AD SG-811 7004544-411 U SG-611 7004544-611 S N/A by Part Number 1 of 11 11/8/2017
90-01-03 -- Honeywell Attitude & heading system 05/02/1990 Honeywell AH-600 Attitude and Heading Reference System (AHRS) Strapdown Attitude and Heading Reference Unit (AHRU), part numbers 7003360-931, - 932, -933, -934, -935, and -936, with serial numbers 0100 through 0277. Within 10 days after January 9, 1989 (the effective date of Amendment 39-6093), inspect airplanes with Honeywell AH-600 AHRS installed to determine the part number, serial number, and Mod Level of the strapdown AHRU installed in the pilot s (Number 1) AHRS. Prior to further flight after inspection, remove all AHRU part numbers 7003360-931, -932, -933, -934, -935, and -936 with serial numbers 0100 through 0277, without Mod Level F", from service in the pilot's (Number 1) AHRS. Install the same part number with Mod Level "F" incorporated, or modify the AHRU in accordance with Honeywell Inc., Service Bulletin 7003360-34-32, dated August 2, 1988. Within 60 calendar days after the effective date of this amendment, inspect airplanes with Honeywell AH-600 AHRS installed to determine the part number, serial number, and Mod Level of the strapdown AHRU installed in copilot's (Number 2) AHRS and the auxiliary (Number 3) AHRS. Within 45 days after the inspection, remove all AHRU part numbers 7003360-931, -932, - 933, -934, -935, and -936, with serial numbers 0100 through 0277, without Mod Level "F", from service in the copilot's (Number 2) AHRS and the auxiliaiy (Number 3) AHRS. Install the same part number with Mod Level "F" incorporated, or modify the AHRU in accordance with Honeywell, Inc., Service Bulletin 7003360-34-32, dated August 2, 1988. N/A by Part Number 90-06-13 -- Honeywell vertical gyro 30/03/1990 Within 60 days after the effective date of this AD, inspect the Model VG-14A vertical gyros to determine the serial number. 1. If the vertical gyros have serial numbers listed in Table 1 of Honeywell Alert Service Bulletin 21-1989-191, Revision 1, dated November 20, 1989, and have the letter "D" marked out on the modification status plate, no further action is Honeywell Model VG-14A vertical gyro, required, and the airplane may be returned to part number 7000622-901, with serial service. numbers listed in Honeywell Alert 2. If the vertical gyros have serial numbers listed Service Bulletin 21-1989-191, Revision 1, in Table 1 of Honeywell Alert Service Bulletin 21- dated November 20, 1989 1989-191, Revision 1, dated November 20, 1989, and do not have the letter "D" marked out on the modification status plate, prior to further flight, remove the gyro, replace the liquid levels, test, and verify operation, in accordance with the procedures specified in paragraph 2., Accomplishment Instructions, of the service bulletin. N/A, NO Vertical Gyro installed in aircraft. AHRS and STBY Gyro only 2 of 11 11/8/2017
93-04-02 Rockwell transponders 26/03/1993 TDR-94D Mode S transponders, P/N CPN Within the next 10 calendar days after the 622-9210-002, installed on, but not effective date of this AD, fabricate a placard with limited to the following, certificated in the following words in letters at least 0.10-inch any category: Aerospatiale ATR-42 and in height and install this placard within the pilot's ATR-72 series airplanes Saab 340A and clear view on the instrument panel: "OPERATION 340B airplanes Short Model SD3-60 OF TCAS II IN ANY MODE OTHER THAN THE "TA airplanes de Havilland DHC-7 and DHC-8 ONLY" MODE IS PROHIBITED." series airplanes British Aerospace ATP (b) Within the next 6 calendar months after the airplanes Gulfstream G-ll, G-lll, and G-IV effective date of this AD, modify the software of series airplanes Dassault Mystere-Falcon the Mode S transponders in accordance with the 50, Mystere-Falcon 200, and Mystere- Accomplishment Instructions section of Collins Falcon 900 airplanes Canadair Challenger Service Bulletin TDR-94/94D-34-6, Revision 2, CL-601 airplanes British Aerospace HS dated September 21, 1992. The placard required 125-700A airplanes by paragraph (a) of this AD is no longer required Beechcraft 300 series airplanes after this modification is incorporated. N/A due to Part Number. Parts Number 622-9210-007 installed on aircraft. 94-01-06 -- Rockwell TCAS 04/02/1994 Traffic Alert and Collision Avoidance System II processors that are installed on, but not limited to the following airplanes (all serial numbers), certificated in any category: General Aviation Airplanes: Astra Model 1125 airplanes; BAC Model 1-11 airplanes; British Aerospace Model 125-800 airplanes; Beech Models C90A, B200, 300, 350, and 400A airplanes; Canadair Models CL-600, CL-600-2B16, CL-601, CL- 601-1 A, and CL-601-3A airplanes; Learjet Models 31, 55, and 60 airplanes; Falcon Models 20, 50,200, and 900 airplanes Gulfstream Models G2 and G3 airplanes; British Aerospace Models HS- 125-700 airplanes; and Sabreliner Model 60 airplanes. Air Transport Airplanes: Aerospatiale Models ATR-42 and ATR-72 airplanes; Airbus Industries Models A300B2, A-300B, and A-320 airplanes; British Aerospace Models ATP and 146 airplanes; Boeing Models 707, 727, 737, 747, 757, and 767 airplanes; British Aerospace/Aerospatiale Model Concorde SST airplanes; de Havilland DHC-7 and DHC-8 series airplanes; McDonnell Douglas Models DC-8, DC-9, and DC-10, MD-80, and MD-11 airplanes; Ilyushin Model IL-86 airplanes; Lockheed Model L-1011 airplanes; SAAB Models SF340A and SF340B airplanes; and Shorts Models SD3-60-300 airplanes. Prior to December 31, 1994, unless already accomplished. To prevent collisions or near misses caused by incompatibility between the traffic alert and collision avoidance system (TCAS) II processors and the current air traffic control system, accomplish the following: (a) Incorporate "Change 6.04A Enhanced" by accomplishing either (1) or (2) below, as applicable: (1) Remove any TCAS II processor with a part number (P/N) suffix listed in the "Existing P/N Suffix" column of the table below, and install a corresponding TCAS II processor with a P/N listed in the "New P/N Suffix" column of the table below: Existing P/N Suffix New P/N Suffix -001,-002,-011, -020-012, or -612-102,- 111, or-112-120 -014-320 NOTE 1: Collins SB No. 16, TTR-920-34-16, dated December 9, 1993, specifies procedures for incorporating the referenced New P/N suffixes. (2) Change the part number of the TCAS II unit on board the aircraft by reprogramming the software with a data loader in order to obtain the New P/N Suffix as specified in the following table: Existing P/N Suffix New P/N Suffix -012-020 -112-120 -014-320 NOTE 2: Units with P/N suffix of -001, -002, -011, - 102, -111, and -612 cannot be reprogrammed on board the aircraft. N/A by STC ST00844WI-D installing TCAS II change 7. 3 of 11 11/8/2017
94-21-06 -- 96-25-12 -- Lap Belt Assemblies and Restraint Systems Prevent compressor wheel rupture 11/25/1994 13/01/1997 Lap belt assemblies and restraint systems, as listed in Pacific Scientific SB 1108435-25-01, and Pacific Scientific SB 1108460-25-01; as installed on aircraft and rotorcraft Sundstrand Aerospace SB No. SB-T-62T- 49-120, Revision 2, dated November 5, 1996 Sundstrand Aerospace SB No. SB-T- 62T-49-120, Revision 1, dated September 9, 1996 Sundstrand Aerospace SB No. SB-T-62T-49-120, dated July 22, 1996 Within 90 days after the effective date of this AD, remove the applicable lap belt assemblies and restraint systems, and replace them with new design assemblies in accordance with Pacific Scientific SB 1108435-25-01, or Pacific Scientific SB 1108460-25-01, as applicable. Remove from service compressor wheels in accordance with the procedures described in the Accomplishment Instructions of Sundstrand Aerospace Service Bulletin (SB) No. SB-T-62T-49-120, Revision 2, dated November 5, 1996, Revision 1, dated September 9, 1996, or Original, dated July 22, 1996, and the drawdown schedule described in Table 2 of Revision 2 only, dated November 5, 1996, and replace with serviceable parts. (b) This AD establishes a new life limit of 6,000 cycles for existing uninstalled compressor wheels, identified as Sundstrand P/Ns 162690-1, 165111-1, and 167200-1. Pacific Scientific SB 1108435-25-01 or Pacific Scientific SB 1108460-25-01 Accomplishment Instructions of Sundstrand Aerospace Service Bulletin (SB) No. SB-T-62T-49-120, Revision 2, dated November 5, 1996, Revision 1, dated September 9, 1996, or Original, dated July 22, 1996 N/A due Pacific Scientific not installed on aircraft. N/A due to Part Number of Compressor Wheel 97-04-15 -- Fire extinguisher bottle cartridge 07/03/1997 Within 30 days after the effective date of this Fire extinguisher bottle cartridges AD, accomplish the following: (squibs) having part numbers (P/N) (1) Pull the applicable circuit breakers and 13083-10 and -25; as installed in, but not disconnect the electrical connector from any limited to, the following airplane models, Pacific Scientific Company, HTL/Kin-Tech certificated in any category: Division, fire extinguisher bottle cartridge (squib) de Havilland Model DHC-7 series having P/N 13083-10 or 13083-25. CAUTION: airplanes; Prior to removing the electrical connector from de Havilland Model DHC-8-100 and -300 the fire extinguisher bottle cartridge, ensure that series airplanes; the technician is grounded properly. Cartridges General Dynamics Convair Model 340, are electrostatic discharge (ESD) sensitive. 440, and C-131 (military) series airplanes (2) Perform a one-time visual inspection of the modified in accordance with electrical receptacle of the cartridge and its Supplemental Certificate SA41100; mating connector to detect the presence of Lockheed Model 382 series airplanes; aluminum foil in the area of the pins of the and cartridge and the connector. The aluminum foil Sabreliner Model NA-265-60, -65, and - may have the appearance of solder. Remove any 75A series airplanes. aluminum foil that is present. Complied with Ex Factory by Tyrolean records. 4 of 11 11/8/2017
2001-15- 17 -- Prevent such erroneous altitude interpretations 20/08/2001 This AD applies to CTL-92 transponder control panel part numbers 622-6523- 204, 622-6523- 205, 622-6523-206, 622- (1) Modify the altitude encoder inputs of the CTL- 6523-207, and 622-6523-208 (serial 92 transponder control panels. Within the next numbers as specified in Rockwell Collins 10 hours time-in- service (TIS) after August 20, Service Bulletin 33 (CTL-92-34-33), dated 2001 (the effective date of this AD). Modify in April 2001), that are installed in aircraft. accordance with the Accomplishment These CTL-92 transponder control panels Instructions section of Rockwell Collins Service are installed in, but not limited to, the Bulletin 33 (CTL-92-34-33), dated April5, 2001. following aircraft that are certificated in (2) Do not install, on any aircraft, an affected CTLany category: 92 transponder control panel that has not been (1) Aerospatiale ATR42 and ATR72 series modified as required by paragraph (d)(1) of this airplanes; AD. As of August 20, 2001 (the effective date of (2) Saab Aircraft Models 340B and this AD). Modify in accordance with the SF340A airplanes; Accomplishment Instructions section of Rockwell (3) Embraer EMB-120 series airplanes; Collins Service Bulletin 33 (CTL-92-34-33), dated (4) dehavilland DHC-8 series airplanes; April5, 2001. and (5) Raytheon Models C90A, B200, 350, and 1900D airplanes. Part Number 622-6523-205 installed. 12781 is N/A by S/B CTL-92-34-33 2002-06- 06 -- Prevent erroneous altitude resolutions 03/05/2002 This AD applies to TDR-94 Mode S transponders (Collins part number (CPN) 622-9352-004) and TDR-94D Mode S transponders (CPN 622-9210- 004) that derive altitude information from a Gillham (gray code) encoded pressure altitude source and are installed on, but not limited to, the following airplanes that are certificated in any category: (1) Aerospatiale ATR42 series airplanes; (2) dehavilland DHC-7 and DHC-8 series airplanes; and (3) Short Brothers Models SD3-60 and SD3-60 SHERPA airplanes. Determine whether the altitude information from any TDR-94 Mode S transponder (CPN 622-9352-004) or TDR-94D Mode S transponder (CPN 622-9120-004) is derived from a digital air data source or a Gillham (gray code) encoded source. Accomplish the modification in accordance with Rockwell Collins Service Bulletin No. 17 (TDR- 94/94D- 34-17), dated February 8,1999, Service Bulletin 17, Revision No. 1, dated May 15, 2000, or Service Bulletin 20 (TDR- 94/94D-34-20), Revision No. 1, dated May 2, 2001. Collins Product Information Letter No. 71, dated January 1999, references Service Bulletin 17, dated February 8,1999. N/A by Part Number. Part Number 622-9210-007 2009-21- 03 To prevent overfueling of the APU during the start sequence 11/20/09 Hamilton Sundstrand Power Systems T- 62T-46C12 auxiliary power units (APUs) At the next FADEC removal, but no later than 18 months after the effective date of this AD, upgrade the software in the APU FADEC from software version 02.01.000 to version 03.00.000, and change the FADEC part number (P/N) from 4503069E to 4503069F. (g) Use paragraphs 3. A through 3.F.(2) of the Accomplishment Instructions of Hamilton Sundstrand Power Systems Service Bulletin No. 4503067-49-12, Revision 2, dated March 9,2009, to do the software upgrade and the FADEC P/N change N/A by Model Number. APU APS500/T-62-T-40C7B/167301-101A installed on aircraft 5 of 11 11/8/2017
2011-01- 09 -- Protective Breathing Equipment (PBE) 9/2/11 B/E Aerospace protective breathing equipment (PBE) units having part number (P/N) 119003-11. These PBE units may be installed on (or carried or stowed on board), various transport category airplanes, certificated in any category. Within 120 days after the effective date of this AD, inspect to determine the serial number of the PBE units installed in the aircraft, in accordance with the Accomplishment Instructions of B/E Aerospace Service Bulletin 119003-35-5. (1) For any PBE that has a serial number from 003-50730M to 003-51329M inclusive: Before further flight, replace the PBE with a serviceable PBE, except as provided by paragraph (g)(2) of this AD. (2) For any PBE that has a label showing that it has been restored in accordance with B/E Aerospace Service Bulletin 119003-35-6: The replacement has been done, and no further action is required by paragraph (g) of this AD. (3) For any PBE not having a serial number from 003-50730M to 003-51329M inclusive: No further action is required by paragraph (g) of this AD. B/E Aerospace Service Bulletin 119003-35-6 B/E Aerospace PBE not installed in Aircraft. ESSEX PB&R CORPORATION PBE Installed. Part Number MR10049N. 6 of 11 11/8/2017
2011-21- 08 -- Sicma Aero Seat 88xx, 89xx, 90xx, 91xx, 92xx, 93xx, 95xx, and 96xx series passenger seat assemblies 11/23/11 (f) Unless already done, do the following actions. (1) At the later of the compliance times specified in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD, do a general visual inspection of the backrest links having P/Ns 90-000200-104-1 and 90-000200- 104-2, in accordance with Part One of Sicma Aero Seat Service Bulletin 90-25-013, Issue 4, dated March 19, 2004, including Annex 1, Issue 2, dated March 19, 2004: This AD applies to Sicma Aero Seat 88xx, (i) Before 6,000 flight hours on the backrest link 89xx, 90xx, 91xx, 92xx, 93xx, 95xx, and since new. 96xx series passenger seat assemblies (ii) Within 900 flight hours or 5 months after the identified in Annex 1, Issue 2, dated effective date of this AD, whichever occurs March 19, 2004, of Sicma Aero later. Seat Service Bulletin 90-25-013, Issue 4, (2) If, during the inspection required by dated March 19, 2004, that have paragraph (f)(1) of this AD, cracking is found backrest links having part numbers between the side of the backrest link and the (P/Ns) 90-000200-104-1 and 90-000200- lock-out pin hole but the cracking does not pass 104-2; and that are installed on, but not this lock-out pin hole (refer to Figure 2 of Sicma limited to, Aero Seat Service Bulletin 90-25-013, Issue 4, the airplanes identified in table 1 of this dated March 19,2004, including Annex 1, Issue 2, AD, certificated in any category. This AD dated March 19, 2004): Within 600 flight hours does not apply to Sicma Aero Seat series or 3 months after doing the inspection, 9140, 9166, 9173, 9174, 9184, 9188, whichever occurs first, replace both backrest 9196, 91B7, 91B8, 91C0, 91C2, 91C4, links of the affected seat with new, improved 91C5, 9301, and 9501 passenger seat backrest links having P/Ns 90-100200-104-1 and assemblies. 90-100200-104-2, in accordance with Part Two of Sicma Aero Seat Service Bulletin 90-25-013, Issue 4, dated March 19, 2004, including Annex 1, Issue 2, dated March 19, 2004. (3) If, during the inspection required by paragraph (f)(1) of this AD, cracking is found that passes beyond the lock-out pin hole (refer to Figure 2 of Sicma Aero Seat Service Bulletin 90-25-013, Issue 4, dated March 19, 2004, including Sicma Aero Seat Service Bulletin 90-25-013, Issue 4, dated March 19, 2004 N/A TO EQUIPMENT NOT INSTALLED 7 of 11 11/8/2017
2011-23- 06 -- Air Transport Association (ATA) of America Code 25: Equipment/Furnishing s. 11/21/11 (c) This AD applies to Sicma Aero Seat Model 9401, 9402, 9404, 9505, 9406, 9407, 9408, and 9409 series passenger seat assemblies, all part numbers, except front row and aft facing seats, and those modified to ''Amendment B'' standard. These passenger seat assemblies are installed on, but not limited to, ATR-GIE Avions de Transport Régional Model ATR42-200, -300, -320, and -500 airplanes and Model ATR72-101, -201, -102, -202, -211, -212, and - 212A airplanes. Note 1: This AD applies to Sicma Aero Seat passenger seat assemblies as installed on any airplane, (g) Within 6 months after the effective date of this AD, perform a detailed inspection for cracking of the central and lateral spreaders of the affected seats, in accordance with paragraph 2/A1., ''Checking procedures of lateral and central spreaders,'' of the Accomplishment Instructions of Sicma Aero Seat Service Bulletin 94-25-013, Issue 4, dated February 12, 2008. (1) If no cracking is found on any central spreader, repeat the detailed inspection thereafter at intervals not to exceed 550 flight hours until the replacement specified in paragraph (h) of this AD is done. (2) If no cracking or only cracks that are shorter than 8 millimeters (mm) (0.315 inch) are found on any lateral spreader, repeat the detailed inspection thereafter at intervals not to exceed 550 flight hours until the replacement specified in paragraph (h) of this AD is done. (3) If all cracks found on any central spreader are shorter than 8 mm (0.315 inch), before further flight, repair the affected spreader, in accordance with paragraphs 2/A through C2. of the Accomplishment Instructions of Sicma Aero Seat Service Bulletin 94-25-011, Revision 3, dated June 30, 2008. Within 550 flight hours after doing the repair, do the detailed inspection specified in paragraph (g) of this AD, and repeat the inspection thereafter at intervals not to exceed 550 flight hours until the replacement specified in paragraph (h) of this AD is done. (4) If one or more cracks are found that are 8 mm (0.315 inch) or longer on any lateral or central spreader, before further flight, replace the affected spreader, in accordance with Sicma Aero Seat Service Bulletin 94-25-012, Revision 1, dated June 26, 2008. S/S N/A N/A N/A N/A N/A N/A N/A N/A N/A N/A by P/N installed. This AD is superseded by AD 2012-08-07 ######## -- Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 3/13/12 This AD applies to Aviation Communication & Surveillance Systems (ACSS) traffic alert and collision avoidance system (TCAS) units with part numbers identified in ACSS Technical Newsletter 8008359, Revision B, dated August 3, 2011, as installed on but not limited to various transport and small airplanes, certificated in any category. Note 1 to paragraph (c) of this AD: Table 1 of this AD also provides a crossreferenced list of part numbers with associated service bulletins to help operators identify affected parts. Within 36 months after the effective date of this AD, upgrade software for the ACSS TCAS, in accordance with the Accomplishment Instructions of the applicable ACSS publication identified in table 1 of this AD. Note 2 to paragraph (g) of this AD: ACSS Service Bulletin 8008233-001 (ATA Service Bulletin 9000000-34-6016), Revision 03, dated June 30, 2011, contains three part numbers (P/Ns 9000000-10007, -20007, and -55007) that were never produced. Within 36 months after the effective date of this AD, upgrade software for the ACSS TCAS, in accordance with the Accomplishment Instructions of the applicable ACSS publication identified in table 1 of this AD. N/A by P/N installed 8 of 11 11/8/2017
######## -- Air Transport Association (ATA) of America Code 25: Equipment/Furnishing s. 5/9/12 (1) This AD applies to Sicma Aero Seat Model 9401, 9402, 9404, 9405, 9406, 9407, 9408, and 9409 series passenger seat assemblies, all part numbers, except front row and aft facing seats, and those modified to ''Amendment B'' standard. These passenger seat assemblies are installed on, but not limited to, ATR GIE Avions de Transport Régional Model ATR42-200, -300, -320, and -500 airplanes and Model ATR72-101, -201, -102, -202, -211, -212, and - 212A airplanes. (2) This AD applies to Sicma Aero Seat passenger seat assemblies as installed on any airplane, This paragraphs restates the actions required by paragraph (g) of AD 2011-23-06, Amendment 39-16857 (76 FR 68304, November 4, 2011). For Sicma Aero Seat Model 9401, 9402, 9404, 9406, 9407, 9408, and 9409 series passenger seat assemblies: Within 6 months after November 21, 2011 (the effective date of AD 2011-23-06), perform a detailed inspection for cracking of the central and lateral spreaders of the affected seats, in accordance with paragraph 2/A1., ''Checking procedures of lateral and central spreaders,'' of the Accomplishment Instructions of Sicma Aero Seat Service Bulletin 94-25-013, Issue 4, dated February 12, 2008. (1) If no cracking is found on any central spreader, repeat the detailed inspection thereafter at intervals not to exceed 550 flight hours until the replacement specified in paragraph (i) of this AD is done. (2) If no cracking or only cracks that are shorter than 8 millimeters (mm) (0.315 inch) are found on any lateral spreader, repeat the detailed inspection thereafter at intervals not to exceed 550 flight hours until the replacement specified in paragraph (i) of this AD is done. (3) If all cracks found on any central spreader are shorter than 8 mm (0.315 inch), before further flight, repair the affected spreader, in accordance with paragraphs 2/A through C2. of the Accomplishment Instructions of Sicma Aero Seat Service Bulletin 94-25-011, Revision 3, dated June 30, 2008. Within 550 flight hours after doing the repair, do the detailed inspection specified in paragraph (g) of this AD, and repeat the inspection thereafter at intervals not to exceed Sicma Aero Seat Service Bulletin 94-25-012, Revision 1, dated June 26, 2008. N/A by P/N installed. This AD supersedes AD 2011-23-06 9 of 11 11/8/2017
######## -- 34, Navigation. 6/16/15 This AD applies to Zodiac Aerotechnics (formerly Intertechnique Aircraft Systems) flightcrew oxygen mask regulators, all part number (P/N) MA10, MC10, MC20, MF10, MF20, MLC20, MLD20, MRA005, MRA022, and MRA023 series; certificated in any category; installed on, but not limited to, airplanes manufactured by Airbus, ATR, BAE Systems ( Certificate previously held by British Aerospace), Boeing, Bombardier ( Certificate previously held by Canadair, De Havilland Canada), Cessna, Dassault, EADS CASA, EMBRAER, Gulfstream, Hawker Beechcraft ( Certificate previously held by Raytheon, Beech), Israel Aircraft Industries (IAI), McDonnell Douglas, Piaggio, Pilatus, Piper, and SOCATA. Except as provided by paragraph (i) of this AD: Within 24 months after the effective date of this AD, inspect the inflatable harness fitted to each flightcrew oxygen mask regulator to determine if the inflatable harness is installed with a part number and a batch number identified in Appendix I of Zodiac Aerospace Service Bulletin MXH-35-240, Revision 7, dated September 1, 2011 (for all 11 airplanes other than Bombardier airplanes); or Appendix I of Zodiac Aerospace Service Bulletin MXH-35-241, Revision 3, dated June 23, 2011 (for Bombardier airplanes). Note 1 to paragraph (g) of this AD: Referring only to Appendix II of Zodiac Aerospace Service Bulletin MXH-35-240, Revision 7, dated September 1, 2011; or Appendix II of Zodiac Aerospace Service Bulletin MXH-35-241, Revision 3, dated June 23, 2011; to identify a specific oxygen mask regulator is insufficient to demonstrate that the inflatable harness fitted to that oxygen mask regulator is not listed in Appendix I of Zodiac Aerospace Service Bulletin MXH-35-240, Revision 7, dated September 1, 2011; or Appendix I of Zodiac Aerospace Service Bulletin MXH-35-241, Revision 3, dated June 23, 2011. Within 24 months after the effective date of this AD, replace the inflatable harness with a new or re-identified harness, in accordance with the Accomplishment Instructions of Zodiac Aerospace Service Bulletin MXH-35-240, Revision 7, dated September 1, 2011 (for all airplanes other than Bombardier airplanes); or Zodiac Aerospace Service Bulletin MXH-35-241, Revision 3, dated June 23, 2011 (for Bombardier airplanes). N/A by P/N installed 10 of 11 11/8/2017
######## -- Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 35; Oxygen. 7/15/16 This AD applies to B/E Aerospace Protective Breathing Equipment (PBE), part number (P/N) 119003-11, that is installed on airplanes. (g) Inspection Within 3 months after July 15, 2016 (the effective date of this AD), while still in the stowage box, physically inspect the PBE pouch to determine if it has an intact vacuum seal. Do this inspection following paragraph III.A.1. of the Accomplishment Instructions in B/E Aerospace Service Bulletin No. 119003-35-011, Rev. 000, dated February 4, 2015. (h) Replacement (1) If a PBE pouch is found that does not have an intact vacuum seal during the inspection required in paragraph (g) of this AD: Before further flight or following existing minimum equipment list (MEL) procedures, replace the PBE with a PBE, P/N 119003-21, following paragraphs III.C., III.D.(4), III.D.(6), and III.D.(7) of the Accomplishment Instructions in B/E Aerospace Service Bulletin No. 119003-35- 009, Rev. 001, dated April 12, 2016, or replace it with another FAAapproved serviceable PBE. (2) If a PBE pouch is found during the inspection required in paragraph (g) of this AD where the vacuum seal is intact: Within 18 months after July 15, 2016 (the effective date of this AD), remove PBE, P/N 119003-11, and replace the PBE with PBE, P/N 119003-21, following paragraphs III.C., III.D.(4), III.D.(6), and III.D.(7) of the Accomplishment Instructions in B/E Aerospace Service Bulletin No. 119003-35-009, Rev. 001, dated April 12, 2016, or replace it with another FAAapproved serviceable PBE. (h) Replacement (1) If a PBE pouch is found that does not have an intact vacuum seal during the inspection required in paragraph (g) of this AD: Before further flight or following existing minimum equipment list (MEL) procedures, replace the PBE with a PBE, P/N 119003-21, following paragraphs III.C., III.D.(4), III.D.(6), and III.D.(7) of the Accomplishment Instructions in B/E Aerospace Service Bulletin No. 119003-35- 009, Rev. 001, dated April 12, 2016, or replace it with another FAAapproved serviceable PBE. (2) If a PBE pouch is found during the inspection required in paragraph (g) of this AD where the vacuum seal is intact:within 18 months after July 15, 2016 (the effective date of this AD), remove PBE, P/N 119003-11, and replace the PBE with PBE, P/N 119003-21, following paragraphs III.C., III.D.(4), III.D.(6), and III.D.(7) of the Accomplishment Instructions in B/E Aerospace Service Bulletin No. 119003-35- 009, Rev. 001, dated April 12, 2016, or replace it with another FAAapproved serviceable PBE. N/A by P/N installed 11 of 11 11/8/2017