STC ST00157MC

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate FAA Form 8110-2 (5/14) Page 2 of 16

This certificate may be transf erred or made available to third persons by licensing agreements in accordance with 14 CFR 21.47. Possession of this Supplemental Ty pe Certif icate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or propeller.

INSTRUCTIONS: The transf er endorsement below may be used to notif y the appropriate FAA Aircraf t Certif ication Of f ice of the transf er of this Supplemental T ype Certificate. T he FAA will reissue the certificate in the name of the transferee and forward it to him.

To (Name and address of transferee)

From (Name and address of grantor) The Boeing Com pany 6001 South Air Depot Blvd Oklahom a City, OK 73135

ST00157MC

FAA Form 8110-2 (5/14) United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST00157MC Page 3 of 16

This certificate may be transf erred or made available to third persons by licensing agreements in accordance with 14 CFR 21.47. Possession of this Supplemental Ty pe Certif icate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or propeller.

Limitations and Conditions (Continued from Page 1):

3. Ins tallation of this STC m odification (ex cluding Optional WARP kits) must be accomplished at a Boeing site operating under the PC700 Production Certificate. This STC mus t be ins talled in its entirety prior to installation of WARPs.

4. If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that perm ission. The installer m ust determ ine whether this design change is com patible with previously approved modifications.

5. This approval should not be incorporated in any aircraft of this specific m odel on which other approved m odifications are incorporated, unless it is determ ined that the interrelationship between this change and any of those previously incorporated approved m odifications will not introduce any adverse effect upon the airworthiness of the airplane.

6. A finding of com pliance with Stage 4 noise standards requirem ents of 14 CFR Part 36 at am endm ent 36-31, effective Novem ber 3, 2017, was m ade by the FAA on October 21, 2020.

7. These airplanes are certified only for use by a m ilitary organization and are not eligible for a U.S. airworthi ness certificate. An FAA Form 8130-31, STATEMENT OF CONFORMITY – MILITARY AIRCRAFT, will be issued for each delivered aircraft.

8. Aerial refueling operations are prohibited and are not FAA approved for civil or m ilitary operation. Aerial refueling operational procedures, crew training, receiver aircraft qualifications, military flight manuals, and approval to operate the KC-46 as an aerial refueling platform are to be obtained through issuance of the corresponding USAF KC-46 military type certificate and other associated military publications.

9. The 25.1309 System Safety Analysis has identified operational hazards when conducting aerial refueling operations (the act of passing fuel from one aircraft to another in mid-flight) in the Military Operating Environment.

These hazards are associated with potential system failures and malfunctions which could be ex perienced during operation of tanker/receiver aircraft in close prox imity, and represent conditions which are not com patible with the intent or applicability of CFR Title 14 Section 25.1309 in the civil environm ent. These hazards are retained in the KC-46 STC FAA System Safety Analysis to docum ent the operational hazards, but are ex cluded from com pliance findings to 25.1309 since they are not applicable. These items are listed in Boeing document D842-902030-3 (USAF) or D842-902040-1 (Japan) System Safety Hazard Analysis, and have been coordinated with the USAF Technical Airworthiness Authority to develop acceptable ris k mitigations for military aerial refueling operational approval under the USAF m ilitary type certificate.

10. Installation of Optional WARP Kits on aircraft line numbers 1102, 1107, 1111 through 1200 and 1205 may be accom plished only after or concurrent with Boeing SB767-28-0151 to ensure required markers are installed. All other aircraft have required markers installed in production.

FAA Form 8110-2 (5/14) Page 4 of 16 United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST00157MC

This certificate may be transf erred or made available to third persons by licensing agreements in accordance with 14 CFR 21.47. Possession of this Supplemental Ty pe Certif icate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or propeller.

Certification Basis (Continued from Page 1):

Airw orthiness Standards

1. Based on 14 CFR 21.115 and 21.101, and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for the Model 767-2C is as follows :

a. For Components and Areas Not Affected by the Change, the original certification basis for the Boeing Model 767-2C shown on the Type Certificate Data Sheet (TCDS) A1NM, Revisi on

37.

b. For Components and Areas Affected by the Change, 14 CFR part 25 effective Fe b ruary 1, 1965, including Amendments 25-1 through 25-138, with the following ex ceptions:

14 CFR Section Amendment Applicable Area

25.21 72 Entire airplane

25.103 108 Entire airplane

25.105 92 Entire airplane

25.107 108 Entire airplane

25.111 115 Entire airplane

25.119 108 Entire airplane

25.121 108 Entire airplane

25.123 0 Entire airplane

25.125 108 Entire airplane

25.143 108 Entire airplane

25.207 108 Entire airplane

25.237 108 Entire airplane

25.253(c) 84 Entire airplane (See Note 1)

25.519(b)(2)

N/A* Airplane Prim ary Jacking Points

* See “Additional Design Requirem ents and Conditions” for inform ation on required design features and conditions.

FAA Form 8110-2 (5/14) Page 5 of 16 United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST00157MC

This certificate may be transf erred or made available to third persons by licensing agreements in accordance with 14 CFR 21.47. Possession of this Supplemental Ty pe Certif icate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or propeller.

Certification Basis (Continued from Page 1):

25.571(a) and (b) [except

(b)(3), (b)(4), (b)(5), and

86* Airplane Structures (ex cept for the Aerial Refueling Boom , Centerline Drogue, and Wing Aerial Refueling Pod/Pylon assem blies) (See Note 2)

* See “Additional Design Requirem ents and Conditions” for inform ation on required design features and conditions.

25.603

38 Em pennage:

• Fin and Rudder (ex cept wire brackets/installation on rear spar and fix ed trailing edge panels between Rudder Station

230.97 and 305.87)

• Horizontal Stabilizer Elevators and Fix ed Trailing Edge

25.603 38 Engine Nacelle:

• Engine Nacelle Fan Cowl Panel

25.603

38 Engine Pylon:

• Pylon Forward, Underwing, and Nacelle Fairings and all related fairing support structure

25.613

0 Fuselage:

• Nose Landing G ear Doors and support structure

25.613

0 Em pennage:

• Fin and Rudder (ex cept wire brackets/installation on rear spar and fixe d trailing edge panels between Rudder Sta.

230.97 and 305.87)

• Horizontal Stabilizer Elevators and Fixed TE

25.613 0 Engine Nacelle:

• Engine Nacelle Fan Cowl Panel

25.613

0 Engine Pylon:

• Pylon Forward, Underwing, and Nacelle Fairings and all related fairing support structure

FAA Form 8110-2 (5/14) Page 6 of 16 United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST00157MC

This certificate may be transf erred or made available to third persons by licensing agreements in accordance with 14 CFR 21.47. Possession of this Supplemental Ty pe Certif icate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or propeller.

Certification Basis (Continued from Page 1):

25.613

0 Flight Control System s:

• Prim ary Flight Control hydraulic equipm ent (ex cept Elevator Feel Computer and Elevator Feel Shift Module)

25.613

0 Landing G ear System s:

• Landing G ear Actuation System (ex cept for gear ex tension/retraction command, alternate ex tend cable load lim iter, and flight deck indication)

• Brake Control System (ex cept for right brake control cable and antiskid light and brake tem perature indication)

• Nose Wheel Steering System

25.615

23 Fuselage:

• Nose Landing G ear Doors and support structure

25.615

23 Em pennage:

• Fin and Rudder (ex cept wire brackets/installation on rear spar and fixe d trailing edge panels between Rudder Sta.

230.97 and 305.87)

• Horizontal Stabilizer Elevators and Fixed TE

25.615 23 Engine Nacelle:

• Engine Nacelle Fan Cowl Panel

25.615

23 Engine Pylon:

• Pylon Forward, Underwing, and Nacelle Fairings and all related fairing support structure

25.615

23 Flight Control System s:

• Prim ary Flight Control hydraulic equipm ent (ex cept Elevator Feel Computer and Elevator Feel Shift Module)

FAA Form 8110-2 (5/14) Page 7 of 16 United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST00157MC

This certificate may be transf erred or made available to third persons by licensing agreements in accordance with 14 CFR 21.47. Possession of this Supplemental Ty pe Certif icate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or propeller.

Certification Basis (Continued from Page 1):

25.615

23 Landing G ear System s:

• Landing G ear Actuation System (ex cept for gear ex tension/retraction command, alternate ex tend cable load lim iter, and flight deck indication)

• Brake Control System (ex cept for right brake control cable and antiskid light and brake temperature indication)

• Nose Wheel Steering System

25.735

23 Landing G ear Systems:

• Brake Control System (ex cept for right brake control cable and antiskid light and brake temperature indication)

25.735(a), (f)(1), (f)(2), and (g) 92 Landing G ear System s: • Tires, Wheels, and Brakes

25.735(h)(1), and (h)(2) 92 Landing G ear System s:

• Tires, Wheels, and Brakes

25.773(b)(2) 23 Flight Crew Operations:

• Pilot Com partm ent Vie w

25.773

121 Environm ental Control System s:

• Ice and Rain Protection Systems (Window Heat System only) (See Note 3)

25.777

0 Landing G ear System s:

• Brake Control System (ex cept for right brake control cable and antiskid light and brake temperature indication)

25.783(c)(2)

NA* Fuselage Doors:

• Fwd Entry and Service Doors (See Note 4)

* See “Additional Design Requirem ents and Conditions” for inform ation on required design features and conditions.

FAA Form 8110-2 (5/14) Page 8 of 16 United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST00157MC

This certificate may be transf erred or made available to third persons by licensing agreements in accordance with 14 CFR 21.47. Possession of this Supplemental Ty pe Certif icate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or propeller.

Certification Basis (Continued from Page 1):

25.783

23 Fuselage:

• Wing-to-Body Fairing Access Door Assy – ADP, Aft Fairing (See Note 5)

• Wing-to-Body Fairing Access Door Assy – Hydraulic Res ervoir Fill, Aft Fairing (See Note 5)

• Wing-to-Body Fairing Access Door Assy – Pressure Bottle, Aft Fairing (See Note 5)

• Wing-to-Body Fairing Panel Assy – Pressure Relief Door, Aft Fairing (See Note 5)

• Wing-to-Body Fairing Door Assy – RAT, Aft Fairing (See Note 5)

• Wing-to-Body Fairing Underwing Fairing Access Panels/Doors (See Note 5)

25.783

23 Fuselage Doors:

• Fwd Access Door

• EE Access Door

• Lower Fwd Small Cargo Door

• Lower Aft Small Cargo Door

• Aft Entry Door

• Aft Service Door

• Overwing Ex it Doors

25.783

23 Fuselage Doors:

• Electrical Subsystem s Door Control and Indication

25.783

23 Flight Deck Windows:

• Flight Deck No. 2 Openable Window (See Note 5)

25.795(c)(2) 106 Entire airplane (See Note 6)

25.809(a)

34 Escape Systems:

• Flight Deck Window Egress V iewing Means

• Overwing Ex it and Aft Ex it Windows V iewing Means

FAA Form 8110-2 (5/14) Page 9 of 16 United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST00157MC

This certificate may be transf erred or made available to third persons by licensing agreements in accordance with 14 CFR 21.47. Possession of this Supplemental Ty pe Certif icate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or propeller.

Certification Basis (Continued from Page 1):

25.863

23 Landing G ear Sy s tems:

• Landing G ear Actuation System (ex cept for gear ex tension/retraction command, alternate ex tend cable load lim iter, and flight deck indication)

• Brake Control System (ex cept for right brake control cable and antiskid light and brake temperature indication)

25.869

N/A Landing G ear System s:

• Landing G ear Actuation System (ex cept for gear ex tension/retraction command, alternate ex tend cable load lim iter, and flight deck indication)

• Brake Control System (ex cept for right brake control cable and antiskid light and brake temperature indication)

25.1021 0 Engine System s:

Engine Oil System (drainage hardware)

25.1091(e) N/A Engine System s:

Engine Inlet Probe

25.1093(b) 38 Engine System s:

Engine Operability

25.1163(a) 0 Engine System s:

Engine Air Turbine Starter Oil System

25.1183 57 Engine System s:

Engine Air/V ent System (hardware)

25.1301 0 Entire airplane

25.1302 N/A Entire airplane

25.1309 41 Entire airplane

25.1310 N/A Entire airplane

25.1316

NA* Avionics:

• Thrust Managem ent Com puter

* See “Additional Design Requirem ents and Conditions” for inform ation on required design features and conditions.

FAA Form 8110-2 (5/14) Page 10 of 16 United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST00157MC

This certificate may be transf erred or made available to third persons by licensing agreements in accordance with 14 CFR 21.47. Possession of this Supplemental Ty pe Certif icate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or propeller.

Certification Basis (Continued from Page 1):

25.1316

N/A Flight Control Sy s tems:

• Control System Electronics Unit Spoiler Control Module

25.1316 N/A Flight Control System s:

• High Lift System

25.1316

N/A Landing G ear System s:

• Brake Control System (ex cept for right brake control cable and antiskid light and brake temperature indication)

25.1316

N/A* Environm ental Control System s:

• Ice and Rain Protection Systems (Window Heat System only)

* See “Additional Design Requirem ents and Conditions” for inform ation on required design features and conditions.

25.1317

N/A* Avionics:

• Thrust Managem ent Com puter

* See “Additional Design Requirem ents and Conditions” for inform ation on required design features and conditions.

25.1317

N/A* Engine System s:

• Engine Control System

* See “Additional Design Requirem ents and Conditions” for inform ation on required design features and conditions.

25.1317

N/A Flight Control System s:

• Control System Electronics Unit

• Spoiler Control Module

25.1317 N/A Flight Control System s:

• High Lift System

FAA Form 8110-2 (5/14) Page 11 of 16 United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST00157MC

This certificate may be transf erred or made available to third persons by licensing agreements in accordance with 14 CFR 21.47. Possession of this Supplemental Ty pe Certif icate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or propeller.

Certification Basis (Continued from Page 1):

25.1317

N/A Landing G ear System s:

• Brake Control System (ex cept for right brake control cable and antiskid light and brake temperature indication)

25.1317

N/A* Environm ental Control System s:

• Ice and Rain Protection Systems (Window Heat System only)

* See “Additional Design Requirem ents and Conditions” for inform ation on required design features and conditions.

25.1353

42 Landing G ear System s:

• Landing G ear Actuation System (ex cept for gear ex tension/retraction command, alternate ex tend cable load lim iter, and flight deck indication)

• Brake Control System (ex cept for right brake control cable and antiskid light and brake temperature indication)

25.1360

N/A Landing G ear System s:

• Landing G ear Actuation System (ex cept for gear ex tension/retraction command, alternate ex tend cable load lim iter, and flight deck indication)

• Brake Control System (ex cept for right brake control cable and antiskid light and brake temperature indication)

25.1419 23 Entire airplane (See Note 7)

25.1431

0 Landing G ear System s:

• Brake Control System (ex cept for right brake control cable and antiskid light and brake temperature indication)

25.1435

41 Flight Control System s:

• Prim ary Flight Control hydraulic equipm ent (ex cept Elevator Feel Com puter, Horizontal Stabilizer Trim Actuator, and Elevator Feel Shift Module)

FAA Form 8110-2 (5/14) Page 12 of 16 United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST00157MC

This certificate may be transf erred or made available to third persons by licensing agreements in accordance with 14 CFR 21.47. Possession of this Supplemental Ty pe Certif icate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or propeller.

Certification Basis (Continued from Page 1):

25.1435 41 Flight Control System s:

• High Lift System

25.1435

41 Landing G ear Systems:

• Landing G ear Actuation System (ex cept for gear ex tension/retraction command, alternate ex tend cable load lim iter, and flight deck indication)

• Brake Control System (ex cept for right brake control cable and antiskid light and brake tem perature indication)

• Nose Wheel Steering System

25.1435

72 Flight Control Systems:

• Elevator Control System Feel Com puter

• Elevator Control System Feel Shift Module

• Horizontal Stabilizer Trim Actuator

NOTES Note 1: The flight in icing requirem ents of § 25.253(c) did not ex ist at Am endm ent 25-84.

Note 2: The certification requirements for § 25.571(a) and (b) are Amendment 25-86. The certification requirements for § 25.571(b)(1), (b)(2), (b)(3), (b)(4), (b)(5) and (b)(6) are Amendment 25-132.

Note 3: The certification requirements for § 25.773 are Amendment 25-136, except for § 25.773(b)(2) for which the certification requirement is Amendment 25-23.

Note 4: The certification requirem ent for Fwd Entry and Service Doors is § 25.783 Am endm ent 25-114, except that the self-latching requirement of § 25.783(c)(2) does not apply; the self-latching requirem ent of subparagraph (c)(2) did not ex ist prior to Am endm ent

25-114.

Note 5: The certification requirements of § 25.783 are not applicable to this area at Amendment 25-23.

Note 6: Com pliance is not required (for the entire airplane) for the following regulations:

§ 25.795(c)(2), (c)(2)(i), and (c)(2)(ii) Amendment 25-127.

Note 7: Com pliance with the ice protection requirem ents of § 25.1419 at Am endm ent 25-23 includes com pliance with Part 25 Appendix C at Am endm ent 25-0.

2. Sp ecial Cond itions: None.

3. Equivalent Safety Findings:

TAD ELOS Memo No Appl i cabl e Part 25 Sectio n Subject ST00279MC-T-A-3 § 25.629(b)(d) Aeroelastic stability requirements

FAA Form 8110-2 (5/14) Page 13 of 16 United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST00157MC

This certificate may be transf erred or made available to third persons by licensing agreements in accordance with 14 CFR 21.47. Possession of this Supplemental Ty pe Certif icate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or propeller.

Certification Basis (Continued from Page 1):

4. Exemptions:

Exemption Number Applicable Part 25 Section Title Date Issued 12733 25.979 (d) and (e) Pressure Fueling System September 2, 2015 13477 25.345(c) Deploym ent of Flaps or Other High Lift Devices for Enroute Conditions October 30, 2015 15762 25.341(a) Discrete G ust and Turbulence Design Loads and Criteria March 25, 2016 17794 25.1322(c)(2) Warning, Caution, and Advi sor y Lights April 10, 2018 Note: Time-Lim ited Ex em ption No. 17794 ex pires December 31, 2019. Compliance with Boeing Service Bulletin (SB) KC46-31-0001 revision A dated May 24, 2019 or later FAA Approved revision eliminates the applicability of the time-limited ex emption. All aircraft not identified within this SB are delivered fully com pliant.

17890 25.901(c), 25.979(b)(c),

25.1309(b), and 25.1322(a)(1) Potential ARMS Fuel Tank Onload Overpressure Protection June 29, 2018 Note: Time-Lim ited Ex em ption No. 17890 ex pires June 30, 2019. Com pliance with Boeing Service Bulletin (SB) KC46-31-0001 revision A dated May 24, 2019 or later FAA Approved revision eliminates the applicability of the time-limited ex em ption. All aircraft not identified within this SB are delivered fully com pliant.

18586 25.1461 WARP RAT Blade Out July 14, 2020 Certification Maintenance Requirements (CMRs):

See FAA-approved Certification Maintenance Requirements for the Model KC-46A STC, Boeing docum ent number D011T030-09.

5. Additional Design Requirements and Conditions: The following design details or inform ation m ust be m aintained to ensure that an unsafe design condition is not present.

14 CFR 25.519(b)(2) – Jacking and tie-down provisions The following design features m ust be incorporated in the type design (reference § 25.519, Am endm ent N/A).

In lieu of the following, you m ay show com pliance to § 25.519, Am endm ent 25-81:

1. The prim ary jacking points on the body and wing m ust be designed for the following ultim ate conditions with the max imum jacking loads prescribed in the Maintenance Manual:

a. V ertical 2.5 factor

b. V ertical 2.0 factor and side 0.50 factor (acting singularly)

c. V ertical 2.0 factor and longitudinal 0.50 factor (acting s ingularly)

FAA Form 8110-2 (5/14) Page 14 of 16 United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST00157MC

This certificate may be transf erred or made available to third persons by licensing agreements in accordance with 14 CFR 21.47. Possession of this Supplemental Ty pe Certif icate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or propeller.

Certification Basis (Continued from Page 1):

14 CFR 25.571(a) and (b) [excluding (b)(1) through (b)(6)] – Damage-tolerance and fatigue evaluation of structure, 767-2C Airplane Structures The following design features m ust be incorporated in the type design (reference § 25.571(a) and (b), Am endm ent 25-86). In lieu of incorporating the following design features, you m ay show com pliance to §

25.571(a) and (b), Amendment 25-96:

1. For the 767-2C structure, an evaluation of the ex isting damage tolerance analysis (DTA) maintenance actions must be performed to determine if any changes are required due to changes in loads, geometry, material, etc. New or changed maintenance actions for the Model KC-46A STC m ust be included in Section 9 (Airworthiness Lim itations Section) of the Boeing Maintenance Planning Docum ent (MPD) D011T030-02 in accordance with § 25.571(a)(3) at Amendment 25 86.

2. The above evaluation m ust include loading m agnitudes and loading spectra which are developed in accordance with § 25.571 at Amendment 25-96. This evaluation includes usage of the 1.15 factor for pressure acting alone in accordance with § 25.571(b)(5) at Amendment 25-96.

3. Maintenance instructions m ust be based on in-service data and fatigue testing to ensure freedom from widespread fatigue damage.

14 CFR 25.783(c)(2) – Doors. Forward Entry and Service Doors The following design features m ust be incorporated in the type design. In lieu of com plying with the following design features, you m ay show com pliance to § 25.783(c)(2), Am endm ent 25-114:

1. These doors m ust rem ain open to the ex tent necessary to prevent pressurization or safely close (but not latch) as pressurization takes place.

14 CFR 25.1316 – Sy s tem Lightning Protection.

The following design features m ust be incorporated in the type design (reference § 25.1316, Am endm ent N/A) .

In lieu of the following, you m ay show com pliance to § 25.1316, Am endm ent 25 134:

1. Thrust Managem ent Com puter (TMC). The following design features are required to minimize ex posure of the TMC to coupled lightning transients:

a. TMC wiring routed to the Electronic Engine Control (inside the pressure vess el) m ust incorporate enhanced shielding, i.e., have a single, braided shield, grounded at every break.

b. TMC wiring routed to the Electronic Engine Control (outside the pressure vessel) m ust incorporate enhanced shielding, i.e., have a second layer of shielding (typically overbraid) applied to it, and the m ajority of this shielding m ust be term inated peripherally at pressure hull, at outboard equipm ent, and all disconnects between the outboard equipm ent and pressure hull.

2. Window Heat System . The following design features are required to m inim ize ex posure of the Window Heat System to coupled lightning transients:

a. The power and sensor wiring between the Window Heat Control Unit and the No. 1 flight deck window m ust be s hielded.

14 CFR 25.1317 High-intensity Radiated Fields (HIRF) Protection.

The following design features m ust be incorporated in the type design (reference § 25.1317, Am endm ent N/A) .

In lieu of the following, you m ay show com pliance to § 25.1317, Am endm ent 25-122:

FAA Form 8110-2 (5/14) Page 15 of 16 United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST00157MC

This certificate may be transf erred or made available to third persons by licensing agreements in accordance with 14 CFR 21.47. Possession of this Supplemental Ty pe Certif icate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or propeller.

Certification Basis (Continued from Page 1):

1. Electronic Engine Control System (EECS). The following design features are required to minimize ex posure of the EECS to internal HIRF fields .

a. The EECS m ust com ply with Special Condition 25-ANM-18, dated April 29, 1988.

b. All on-engine EECS wiring m ust incorporate enhanced shielding, i.e., have a second layer of shielding (typically overbraid) applied to it, and the m ajority of this shielding m ust be term inated peripherally, rather than with m ulti-inch long jum per wires .

c. RF shielding of the EECS is required as part of the engine nacelle type design as follows:

i. The fan cowl shall have a ply of BMS 8-336 ex panded alum inum foil or equivalent on the outer mold line (OML) surfaces.

ii. The fan cowl and its access doors shall have a ply of BMS8-289 alum inum foil or equivalent on their inner m old line (IML) which shall be in electrical physical contact with the adjacent nacelle com ponents when closed.

iii. An alum inum foil layer m ust be incorporated on the forward strut fairing panels .

2. Thrust Managem ent Com puter (TMC). The following design features are required to m inim ize ex posure of the TMC to internal HIRF fields :

a. TMC wiring routed to the Electronic Engine Control (inside the pressure vess el) m ust incorporate enhanced shielding, i.e. have a single, braided shield, grounded at every break.

b. TMC wiring routed to the Electronic Engine Control (outside the pressure vessel) m ust incorporate enhanced shielding, i.e., have a second layer of shielding (typically overbraid) applied to it, and the m ajority of this shielding m ust be term inated peripherally at pressure hull, at outboard equipment, and all disconnects between the outboard equipm ent and pressure hull.

3. Window Heat System . The following design features are required to m inim ize ex posure of the Window Heat System to internal HIRF fields :

a. The power and sensor wiring between the Window Heat Control Unit and the No. 1 flight deck window m ust be s hielded.

6. Op tional Design Requirements:

14 CFR 25.1535 – ETOPS approval.

7. 14 CFR p art 26: effective December 10, 2007, including Amendments 26-1 through 26-6. Bas ed on 14 CFR

21.101(g), applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 am endm ents, the holder of this STC m ust dem onstrate com pliance with the applicable sections.

As of the issuance date of this STC, compliance has been found for the following regulations:

§ 26.11 at Amendment 26-0 §§ 26.47 and 26.49 at Amendment 26-1 §§ 26.33 and 26.39 at Amendment 26-3 §§ 26.43, 26.45 at Amendment 26-4 § 26.21 at Amendment 26-6

FAA Form 8110-2 (5/14) Page 16 of 16 United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST00157MC

This certificate may be transf erred or made available to third persons by licensing agreements in accordance with 14 CFR 21.47. Possession of this Supplemental Ty pe Certif icate (STC) document by persons other than the STC holder does not constitute rights to the design data nor to alter an aircraft, aircraft engine, or propeller.

Certification Basis (Continued from Page 1):

Environmental Standards for the Changed Product

1. Noise Standards per 14 CFR Part 36: The “No Acoustical Change” provisions of § 21.93(b). Not applicable. This m odification has been determ ined to be a no acoustic change by analysis approved by the FAA in accordance with 14 CFR 21.93(b).

2. Fuel Venting and Exhaust Emissions Standards per 14 CFR Part 34: This m odification has been determ ined to be a no em issions change by design review in accordance with 14 CFR 21.93(c) by the FAA.

- END -