TCDS R00024BO

I I I I I I I I I I I I I I I I DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION R00024BO Revision 28 Sikorsky Aircraft Model S-92A October 4, 2021 TYPE CERTIFICATE DATA SHEET NO. R00024BO This data sheet, which is part of Type Certificat e (TC) Number R00024BO, prescribes conditions and limitations under which the product for which the Ty pe Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. TYPE CERTIFICATE (TC) HOLDER: Sikor sky Aircraft Corporation 6900 Main Street Stratford, CT 06615-9129 MODEL NUMBER S-92A (Transport Helicopter, Category A, Approved 17 December 2002; Transport Helicopter, Category B, Approved May 7, 2004) ENGINES 2 General Electric Company Model GE CT7-8 (TC E8NE) or 2 General Electric Company Model GE CT7-8A (TC E8NE) or 2 General Electric Company Model GE CT7-8A6 (TC E8NE) FUELS JET A, JET B, JET A-1, JP-4, JP-5, JP-8, PRC No. 3, TS-1, RT For all operations below –20°C (-4°F) ambient temperature, all fuel used must contain MIL-D-27686 or equivalent anti-icing additive. ENGINE AND TRANSMISSIONS APPROVED OILS See Rotorcraft Flight Manual for list of approved oils. HYDRAULIC FLUID MIL-PRF-87257 is authorized for use at all approved ambient temperatures. MIL-PRF-83282 may only be used at ambient temperatures above -32°C (- 25°F). DEICING FLUID Kilfrost DF PLUS (88) ENGINE AND TRANSMISSION LIMITS Page 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 Rev 28 3 3 24 27 27 27 27 27 25 24 26 24 27 28 Page 2 of 15 R00024BO CT7-8 Engine DUAL ENGINE LIMITS Rating Time Q (%) T4.5 (°C) Ng (%) Np (%) Rated SHP @ SLS Rated Np (%) Max continuous 100 920 99.9 106 2043 105 86 (1) when airspeed is greater than 100 KIAS 30 Min (2) 30 min 100 957 101.5 106 2336 105 Takeoff 5 min 100 986 102.9 106 2520 105 Transient 12 sec 987 103.2 116 10 sec 120 (3) SINGLE ENGINE LIMITS Rating Time Q (%) T4.5 (°C) Ng (%) Np (%) Rated SHP @ SLS Rated Np (%) Max continuous 120 920 99.9 106 2043 105 OEI 30 min 120 979 102.4 106 2498 100 OEI 2 min 120 990 102.9 106 2520 100 OEI 30 sec 135 1010 103.7 106 2600 100 Transient 5 sec 156(3) Max starting peak 1000  Shaded box with bold number denotes a FADEC controlled limiter value.  Q (%) values are gearbox limits.  (1) 86% Q is not a gearbox limit. Its purpose is to limit flight control loads at high speed thereby preserving dynamic component replacement times.  (2) Rating applies to hovering flight only.  (3) Associated with “torque ramp up” due to abnormal rotor droop at FADEC controlled dual or OEI limit.  100% Q corresponds to a combined power input from both engines to the MGB of 4,170 shp at a rotor speed of 105% (258 rpm). Power turbine speed (Np) of 105% corresponds to 21,945 rpm.  Maximum continuous dual engine torque may exceed 100% on one engine to a maximum of 110% provided that the torque on the other engine is proportionally less than 100% and the sum of the individual torque values does not exceed 200%.  Np overspeed trip is at 120%.  Ng overspeed trip is at 108.5%  When flying at altitudes greater than 8,000 feet at outside air temperatures lower that –20 degrees C, it is possible to reach the corrected Ng speed limit of the engine. When this occurs, the engine will not produce more power. The only indication that the pilot will see when reaching this limit is that further increase in collective will commensurately droop Nr. Page 3 of 15 R00024BO CT7-8A Engine DUAL ENGINE LIMITS Rating Time Q (%) T4.5 (°C) Ng (%) Np (%) Rated SHP @ SLS Rated Np (%) Max continuous 100 935 99.9 106 2043 105 86 (1) when airspeed is greater than 100 KIAS 30 Min (2) 30 min 100 988 101.5 106 2336 105 Takeoff 5 min 100 995 102.9 106 2520 105 Transient 12 sec 1003 103.2 116 10 sec 120 (3) SINGLE ENGINE LIMITS Rating Time Q (%) T4.5 (°C) Ng (%) Np (%) Rated SHP @ SLS Rated Np (%) Max continuous 120 988 102.4 106 2498 105 OEI 2 min 120 1006 102.9 106 2520 100 OEI 30 sec 141 1049 103.7 106 2740 100 Transient 5 sec 156(3) Max starting peak 1000  Shaded box with bold number denotes a FADEC controlled limiter value.  Q (%) values are gearbox limits.  (1) 86% Q is not a gearbox limit. Its purpose is to limit flight control loads at high speed thereby preserving dynamic component replacement times.  (2) Rating applies to hovering flight only.  (3) Associated with “torque ramp up” due to abnormal rotor droop at FADEC controlled dual or OEI limit.  100% Q corresponds to a combined power input from both engines to the MGB of 4,170 shp at a rotor speed of 105% (258 rpm). Power turbine speed (Np) of 105% corresponds to 21,945 rpm.  Maximum continuous dual engine torque may exceed 100% on one engine to a maximum of 110% provided that the torque on t he other engine is proportionally less than 100% and the sum of the individual torque values does not exceed 200%.  Np overspeed trip is at 120%.  Ng overspeed trip is at 108.5%  When flying at altitudes greater than 8,000 feet at outside air temperatures lower that –20 degrees C, it is possible to reach the corrected Ng speed limit of the engine. When this occurs, the engine will not produce more power. The only indication that the pilot will see when reaching this limit is that further increase in collective will commensurately droop Nr. Page 4 of 15 R00024BO CT7-8A6 Engine DUAL ENGINE LIMITS Rating Time Q(%) T4.5(ºC) Ng(%) Np(%) Rated SHP @ SLS Rated Np(%) Max continuous 100 946 100.6 106 2329 105 86 (1) when airspeed is greater than 100 KIAS ** 30 Min (2) 30 min 100 996 102.9 106 2637 105 Takeoff 5 min 100 1008 102.9 106 2695 105 Transient 12 sec 1009 103.2 116 10 sec 120 (3) SINGLE ENGINE LIMITS Rating Time Q(%) T4.5(ºC) Ng(%) Np(%) Rated SHP @ SLS Rated Np(%) Max continuous 120 996 102.9 106 2637 105 OEI 2 min 120 1013 102.9 106 2684 100 OEI 30 sec 141 1097 103.7 106 2845 100 Transient 5 sec 156(3) Max starting peak 1000  Shaded box with bold font denotes a FADEC controlled limiter value.  Q (%) values are gearbox limits.  100% Q corresponds to a combined power input from both engines to the MGB of 4,170 SHP, at a rotor speed of 105% (258 RPM). Power turbine speed (NP) of 105% corresponds to 21,945 RPM.  Maximum continuous dual engine torque may exceed 100% on one engine to a maximum of 110% provided that the torque on the other engine is proportionally less than 100% and the sum of the individual torque values does not exceed 200%.  Np overspeed trip is at 120%. Ng overspeed trip is at 108.5%.  When flying at altitudes greater than 8,500 ft at outside air temperatures lower than −30°C, it is possible to reach the corrected Ng speed limit of the engines. When this occurs, the engine will not produce more power. The only indication that the pilot will see when reaching this limit is that any further increase in collective will commensurately droop Nr.  Engine will be shut down by ground idle protection if TGT is above 980°c, power control lever (PCL) is at idle, weight on wheels, and engine start cycle is completed. Notes: 1. Greater than 100 KIAS & below a density altitude of 6,000 ft Hd, the torque limit is reduced to 86% Q. greater than 100 KIAS & above 6,000 ft Hd, the torque limit is further reduced by 2% Q per 1,000 ft Hd. This is not a gearbox limit. Its purpose is to limit flight control loads at high speed to preserve dynamic component replacement times. This limit is not FADEC controlled. 2. Associated with torque ramp up due to abnormal rotor droop at FADEC controlled dual engine or OEI limit. 3. Rating applies to hovering flight only. 4. PCL must be at idle for limiter to function. Page 5 of 15 R00024BO ROTOR SPEED LIMITS DRIVE SYSTEM LIMITS POWER OFF Maximum 110% Nr Minimum 95% Nr POWER ON Maximum 110% Nr Minimum 95% Nr Dual Engine Torque (%) No Ins pect Req’d Serviceabilit y Check Remove/Replace MGB 0% to 100% Continuous 101% to 120% < 10 sec ≥ 10 sec 121% to 140% < 10 sec ≥ 10 sec greater than 140% Any occurrence Single Engine Torque (%) No Ins pect Req’d Serviceabilit y Check Remove/Replace MGB 0% to 120% Continuous 121% to 140% < 30 sec ≥ 30 sec 141% to 156% < 5 sec ≥ 5 sec greater than 156% Any occurrence AIRSPEED LIMITS Vne (never exceed) Power On 165 KIAS. See Rotorcraft Flight Manual for variations of Vne with gross weight and density altitude. Vle/Vlo (gear extended/gear operating) 165 KIAS/165 KIAS. Vne with floats “armed” 80 KIAS. Vne Power Off 120 KIAS. Vne Hoist Extended 120 KIAS. Vne Upper Sliding Door Open 120 KIAS. Vne External Cargo 120 KIAS. Heavy External Lift 'iii' "C C ::J 0 E:: .E Cl 'qj s: 30000 25000 20000 15000 340.0 - 1 I I Weight and Center of Gravity Envelope Maximum Gross Weight 26,500 Pounds i I -,J ' I 3&0.3: I I : I 134r , 7 I : I I I I I I I I I I I I --1 ---, t--- ·t--- :--- -1-- -t- 1--t- --1----- ----1-----t----1"--- 1--- ·t-- ·t--- -1- ,- -- : 1--~ 2a,3ob - 1- ,-'--------------------------------------- •·-. --·- 2s,3oo ! I f I 1 I ! J60~ I ~- -t- -t- -~ ;• J 26f, ou;-__,-,.._,;.._;...~ ........ -..;.-.;..-.;... ............ - ..... - ..... - .... - ~: -I --; 26fsoo: : I 00111,.......;.! ~ +-'~-!--'--+--!--~-~--'--+-+-~--!,--l!----i ! _ _ P.-_ -;--=>,: 00 ,­ ' ' ' ' r· , r r- -·--1 r- - , r- r- r· r· T ,. --, I I I I I I I I I I I I : I I I I :--;-~~ .. LE __ I I I I 345.0 350.0 355.0 Aircraft Stat ion (inches) Heavy External Lift Limit Light External Lift Limit Aircraft Without External Load 360.0 365.0 Page 6 of 15 R00024BO CENTER OF GRAVITY (CG) LIMITS iii "O C: :::, 0 Q. ... ~ Cl ·a; 3: 30000 25000 20000 Weight and Center of Gravity Envelope Maximum Gross Weight 27,700 Pounds : 347!.7 36L_, 360.~ 2a,300 : I i -----;i I ' -- r--------------------. 1--?8, 390 ' ' 2~.100--: : : : : : 360.8: 21_,100 I ' I ' ' ' ' ' ' I ' I ·--- : -~--- r ~t:~~r-'.-----. -;~~--~-----:-----------r----r-r--r ----- --r--1--------r ·- '. 2s.soo ------' ---- '-----'-----' ____ _t_ ____ '- ·- '-----' ---- , _____ j ___________ , ---- , _____ , _____ 1 __________ '----- , __________ _L ___ ------'-----' ----------· ' ' : ' : : __ ! !--'. _i__: : __ : __ ) -i ___ j__ : ~~-- : 346,8 : : : : : : : : : : : : ' ' ' ' ~45.~ : : : i : : : i : : : : : : : : ! I : : : : I : : : : : : : : : ' I I I I ---:- 2p,8s'.o : ....... ' I : I : ' ' ' ' ' : : ·e - :--7-- j - - ~ - - ! - - ! - - ! --:---:---- -1-- ! - - l -- ~ ----- :-- :.::i : : : I : : : : I : : : I : (.!) u : 1 : I : : : : I : : : I : I I I I ' ' ' ' 1 t t 1 ] ' ' ' LL ' I ' I ' ' I : I : : ' I I ----➔- - ..... .E -- ~----- ::::; , ; --+- :17,~00 : : : : : : : : : : --,- 17,300 ---r\ -----;- : , -;----;-----~----:·----.-----------;----;-----·-----,------- -;--: - -- :--T -- -1 -- T -·- - - 341.8 - +---+ -- :----i-----j-16,f-oo.: _____ ;-----·-T : ___ :-----j----+------ --i- --+----·----:-360.8- +--+ --- 15000 340.0 i , , , , 351:_7 i , i , i , 345.0 350.0 355.0 360.0 365.0 Aircraft Station (inches) Heavy External Lift Limit Light External Lift Limit Aircraft Without External Load Page 7 of 15 R00024BO CENTER OF GRAVITY (CG) LIMITS (CONTINUED) 10 S-92 Lateral CG Limits I ,+3.53 -3.53 I I ~8,300 -----t- r---~,!------t-----➔-----1 I I I I I ------,-------r------,- -----r------ I I I I ------~-------L----~~W ··----L------I I I I 2~,500 1 I ------~-------L----- ------L-------1 I 1 I I ------◄ --- ~~eoo ~ ~---+--------• • I I I I I I ------;-------~------ -------~------ I I ------,-------r----- 1 I ------ 1 _______ 1 ----. . 100,000 lbin. I I --~-------L------1 I I I I I ------~-------~-- ---~-------~------ I I I I I I ------➔-------~-- ---➔-------~------ • I I I • I I I I I -----,-------r------ 1 I I I ------,-------,------ 1 I I 15!200 - I I I ------ ,------ t , ------ ,-------, ------ : +6 17 : : ,-------r------,------- I I 21000--~----- U-----L------~-------1 I I I I I 2SOOE>--~------ -------L-------~-------1 I I -4.00 2-&900 ---- ···----~------ ◄···----1 I I I I I I I I I 24000- ~~------~ ------~------~-------.0 , - 1 I I I +-t 1 I I I 23000"§[------~-------i------~------- ·; , I I 22000 -3 ~------~- _____ I------·------- I I I I 21-000--~------~-- ----L------~-------1 I I I I I I I I 20000--~------~--- ---~------~------- I I I I I I I I 49000 --~------ ◄---- --~------➔------- I I 1 I I I I I 48000--~------~----- I I I I I 47000 --~------~------ I------~------- 1 --1 ------ .-------1 1------ :------- 1 I I I I I -6.17 I 8 6 4 2 LH 0 Buttline in. -2 -4 -6 -8 -10 RH Heavy External Lift Limit Light External Lift Limit Aircraft Without External Load Page 8 of 15 R00024BO LATERAL CG LIMITS: MAXIMUM GROSS WEIGHT 26,500 POUNDS 10 5-92 Latera l CG Limits : +3.61 : +3r53 -3 73 ;3 61 I I - - - - - - ~ - - - - - - - ~ 2~,~o - - - : - - - - -: - - - - - - - 28000- -:- - - - - - _! - - - - - - -:- - - - - - - + ------- I I 27,700 ---,- ,,_ ___ .,... ____ +-----,--- - I I I I I I I I I I I •••••• J ••••••• L •••••• J •••••• L •••••• · 27000··~····· J ••••••• L •••••• ~ ••••••• I I I ______ J _______ L ___ _ ______ L _____ _ I I I I I I I I I ······~·····26;000---------------1 I I I ------~-------r------ 1 I I I I I ------,-------r----- I I I I I I ------,-------r---- ·,·······r······ 100,000 lb1n. I I I I I I -- .-------. ------ I I ______ J _______ L __ ___ 3 _______ L _____ _ I I I I I I I I I I I I ------◄-------~- ----~-------~------ I I I I -------i-------t- -----➔ -------t-------1 I 1 I I I I I I I I I -------,------- ------~-------r------ I I I I 16,200 ······,······ ~r······,·······r······ : +6_17 : : I I I I I I I · 20000 • · ~ · · · · · · ,-4 iio · · · · ~ · · · · · · 1 · · · · · · · I I__J I I I I I I 26000---- ........................ . I I I - 24000 - , ~------~ ------~------~------- .C 1 I I I - 1 I I I ..,_, I I I I · 23000if ······~ ······r······T······· 'aj 1 I I I · 22000~ ~······+· ·····~······+······· I I I I I I I · 21000 · ·:· • • • • • • ~ • • ----. ------ 1------- I I I I · 20000··~······~··· ___ L ______ i ______ _ I I I I I I I I I I •r9000·· ... ······•···· --~------4-------I I -raooe--~------~------~------~------- ' I I I I I I I I J I I • r rOOO ••r••••••;•••••• r••••••T••••••• I I I · HlOOO··r······,······· ~······+······· : : -4.17 : I I 8 6 4 2 LH 0 Buttl ine in. -2 -4 -6 -8 -10 RH Heavy External Lift Limit Light Externa l Lift Limit Aircraft Without External Load Page 9 of 15 R00024BO LATERAL CG LIMITS (CONTINUED): MAXIMUM GROSS WEIGHT 27,700 POUNDS EMPTY WEIGHT C.G. RANGE None DATUM 341.2 inches forward of the main rotor centroid LEVELING MEANS Leveling plate at STA 238.3, BL 40 RH, and plumbline from top of RH forward doorframe. MAXIMUM WEIGHT 26,500 pounds 27,700 pounds with Gross Weight Expansion Option (see Note 16) 28,300 pounds with external load. Heavy External Lift MAXIMUM EXTERNAL LOAD 8000 pounds. Heavy External Lift Page 10of 15 R00024BO ALTITUDE LIMITS Takeoff and landing 11,000 feet density altitude Enroute 15,000 feet density altitude 10,000 feet pressure altitude in icing conditions See Note 11 AMBIENT TEMPERATURE LIMITS -40°C to ISA+35°C (see Note 9) MINIMUM FLIGHT CREW 2 pilots (See Note 8) 3 (2 pilots, 1 cabin crew) Combination Passenger and Cargo NUMBER OF SEATS 2 Crew 1 Observer 19 Passenger maximum (See Notes 6, 8 and 14) Combination Passenger and Cargo Interior Option 3 Crew 9 Passenger maximum MAXIMUM BAGGAGE 1000 pounds Combination Passenger and Cargo Interior Option 0 pounds MAXIMUM CARGO Combination Passenger and Cargo Interior Option (See Note 15) 92276-54000-011 kit installed 1650 lb at 200 lb./sq. ft., Sta 281 to 462 1100 lb at 200 lb./sq. ft., Sta 340 to 462 550 lb at 200 lb./sq. ft., Sta 397 to 462 92276-54000-012 kit installed 5000 lb at 200 lb./sq. ft., Sta 281 to 462 3100 lb at 200 lb./sq. ft., Sta 340 to 462 1200 lb at 200 lb./sq. ft., Sta 397 to 462 FUEL CAPACITY 764 gals (pressure refuel) 713 gals. (gravity refuel) 4.8 gals. unusable at Station 362.5 (See Notes 1 and 7) OIL CAPACITY See General Electric Installation Manual SEI-866 ROTOR BLADE CONTROL MOVEMENTS For rigging information refer to Maintenance Manual Page 11of 15 R00024BO MANUFACTURER’S SERIAL NUMBERS Sikorsky Aircraft Corporation under Production Certificate CERTIFICATION BASIS Number 105: 920006 through 920114, 920116 through 920126, 920128, 920130, 920133, 920137, 920143 and subsequent are eligible. Keystone Helicopter Corporation for Production under Type Certificate Only. 920115 is eligible Keystone Helicopter Corporation under Production Certificate Number 121NE: 920127*, 920129*, 920131, 920132, 920134 through 920136, 920138 through 920142 are eligible. *920127 and 920129 originally designated as eligible for production by Keystone Helicopter Corporation under Type Certificate Only and redesignated upon addition of S-92A to Production Certificate Number 121 NE. Type Certificate No. R00024BO 14 CFR Part 29 Amendments 29-1 to 29-47, inclusive 14 CFR Part 36 Amendment 24 Equivalent Safety Findings: Number TC0309BO-R/F-1 14 CFR Part 29.173 Static longitudinal stability 14 CFR Part 29.175 Demonstration of static longitudinal stability. Number TC0309BO-R/F-4 14 CFR Part 29.177 Static directional stability. Number TC0309BO-R/P-1 14 CFR Part 29.1305(a)(24) Power Plant Instruments. Number TC0309BO-R/P-5 14 CFR Part 29.1 181(a)(4) Designated Fire Zones; Regions Included. Special Conditions: No. 29-011-SC for Dual-Engine 30 Minute Power No. 29-008-SC for High Intensity Radiated Frequency Noise Control Act of 1972 Compliance with the following optional requirements has been established: Ditching provisions FAR 29.563 including 29.801 and 29.807(d) and excluding 29.1411, 29.1415, and 29.1561 when emergency flotation system is installed. For extended over-water operations, compliance with the operating rules and FAR 29.1411, 29.1415, and 29.1561 must be shown. Page 12of 15 R00024BO Anticollision light system installed in accordance with Sikorsky Drawing 33792-52871 Basis of certification is the same as the S-92A plus the following Equivalent Safety Findings: Number AT1610BO-R-S-1 14 CFR Part 29.1401(d) Anticollision light system Passenger Configuration with Side Facing Executive Seats: Basis of certification is the same as the S-92A plus the following Equivalent Safety Findings: Number AT01655BO-R-C-2, Number AT00407MC-R-C-1, and Number AT00407MC-R-C-2 14 CFR Part 29.809(a) Emergency exit arrangement 14 CFR Part 29.813(c)(2) Emergency exit access Special Conditions: None Combination Passenger and Cargo Configuration: Basis of certification is the same as the S-92A plus the following Equivalent Safety Findings: Number TD1454BO-R-S-1 14 CFR 29.855(a)(1), (d) Cargo and baggage compartments Number TD1454BO-R-C-1 14 CFR 29.809(a) Emergency exit arrangement 14 CFR 29.813(c)(2) Emergency exit access Special Conditions: None Search and Rescue (SAR) Automatic Flight Control System (AFCS) Installation: Basis of certification is the same as the S-92A plus the following Equivalent Safety Findings: None Special Conditions: No. 29-023-SC for Installation of a Search and Rescue (SAR) Automatic Flight Control System (AFCS) If CVR/FDR defined by 33792-54647 is installed, then compliance has also been shown to Amendment 29-52 of 14 CFR 29.1457 and 29.1459. Page 13of 15 R00024BO PRODUCTION BASIS Sikorsky Aircraft Corporation Production Certificate Number 105 Keystone Helicopter Corporation, Production Certificate Number 121 NE, under licensing agreement with Sikorsky Aircraft Corporation. In the event of an application for a standard airworthiness certificate or, if an applicant intends to produce a new aircraft under 14 CFR § 21.183(d), and the applicant is manufacturing, building, or assembling to another person’s type certificate, t he applicant must provide written evidence of permission from the type certificate holder. Conduct of such activity without written evidence of permission may be a violation of 49 U.S.C. § 44704(a)(3). EQUIPMENT The basic required equipment as prescribed in the applicable Airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following item(s) of equipment is (are) required: Rotorcraft Flight Manual as shown in FAA Approved Sikorsky document SA S92A-FMCD-000. This document specifies the applicable flight manual number for each aircraft. The applicable flight manual number is determined by the aircraft configuration. SA S92A-FMCD-000 will be revised as required to add additional rotorcraft flight manual numbers, new revisions, and new aircraft as appropriate. - NOTES - NOTE 1 Current weight and balance report, including list of equipment included in certified empty weight, and loading instructions, when necessary, must be provided for each rotorcraft at the time of original certification. The certificated empty weight and corresponding C.G. locations must include un-drainable oil and unusable fuel. See Rotorcraft Flight Manual loading section for variations of fuel weight and moment- arm with variations of fuel and fuel quantity. NOTE 2 The rotorcraft must be operated in accordance with the appropriate FAA-approved Rotorcraft Flight Manual as required under “EQUIPMENT”. All placards required in the FAA-approved Rotorcraft Flight Manual must be installed in the rotorcraft. The following placard must be displayed in front of and in clear view of the pilots: “THIS HELICOPTER MUST BE OPERATED IN ACCORDANCE WITH THE OPERATING LIMITATIONS SPECIFIED IN THE FAA APPROVED ROTORCRAFT FLIGHT MANUAL.” All placards listed in the approved flight manual must be installed in the specified locations. NOTE 3 Information essential to the proper main tenance of the rotorcraft is contained in the Sikorsky S-92A Maintenance Manual, SA S92A-AMM-000 and in the Airworthiness Limitations and Inspection Requirements Manual, SA S92A-AWL-000. The Airworthiness Limitations and Inspection Requirements for gross weights above 26,500 pounds are Page 14of 15 R00024BO contained in document number SIC920010 (see Note 16). The values of retirement (service) life are contained in Chapter 4 of the Airworthiness Limitations and Inspection Requirements Manual in documents SA S92A-AWL-000 and SIC920010 (if applicable). The values of retirement (service) life cannot be changed without FAA Engineering approval. Manuals SA S92A-AMM-000 and SA S92A-AWL-000 are provided with each helicopter. Manual SIC920010 is provided with helicopters with the 27,700 lb. Gross Weight Expansion option. NOTE 4 The term “Unlimited Life” is defined as 30 ,000 flight hours for the Model S-92A rotorcraft. Operation of individual aircraft beyond 30,000 flight hours is contingent upon a Life Extension Program approved by FAA Engineering NOTE 5 The model S-92A rotorcraft employs electronic engine controls that are recognized to be more susceptible to Electromagnetic Interference (EMI) than manual (non-electronic) controls used on other rotorcraft. EMI may be the result of radiated or conducted interference. For this reason, modifications that add or change systems that have the potential for EMI, must either be qualified to an FAA acceptable standard or tested at the time of installation for interference to the engine controls. This type of testing must employ the particular engine control’s diagnostic techniques and external diagnostic techniques. This testing must be accomplished in accordance with an FAA Engineering approved alternate test plan. NOTE 6 Seating arrangements for 19 passengers maximum have been approved by the FAA. With these seating arrangements, seats located along the aisle way shall not have armrests installed on the aisle way side of any aisle seat unless the aisle way seat armrest incorporates an armrest hold down feature. Installation of the Observer Seat and/or Passenger Seat located on the forward starboard bulkhead is prohibited with the installation of the Lower Search/Rescue Door. Occupancy of the Passenger Seat located on the forward starboard bulkhead is prohibited if Observer Seat is installed. Carriage of passengers is prohibited with the installation of the Lower Search/Rescue Door. These seating arrangements are shown in the Loading Information section of the FAA-approved Rotorcraft Flight Manual. Additional optional seating arrangements or related passenger provisions may be approved in accordance with the Type Certificate Basis. NOTE 7 See the appropriate FAA approved Rotorcraft Flight Manual for fuel capacities of aircraft defined by SER-92020578 Revision -, or later approved revision.