# ~DEING

February7, 2014

M-ABOH-14-00022

U.S. Department ofTransportation Docket Operations, M-30 1200NewJersey Avenue S.E. 

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Room W12-140, West Bldg. Ground Floor Washington, DC 20590-0001 The Boeing Company P.O. Box3707 Seattle, WA98124-2207



### Subject:

Model: Petition for Exemption from Title 14, Code ofFederal Regulations (14 CFR) Part 25 Regulations, for Model 767-300 Boeing Converted Freighter (BCF) 767-300BCF FAA ProjectNo.: 

## NIA EASA ProjectNo.: 

## NIA EASALevel: 

## NIA

This letter is to submit:
(X) Petition for Exemption



### This letter is being sent for:
(X) Regulatory Review/ Approval

The Boeing Company respectfully submits the enclosed Petition for Exemption from the applicable Title 14 Code ofFederal Regulations Part 25 for the Boeing Model 767-300BCF airplane as related to the proposed installation ofan oven. '

Please contact Ted Scoville at 425-717-3895 ifyou have further questions.

The information being forwarded to theFAA by or with this correspondence is for the exclusive purpose ofsupport ofapplications for oramendments to Type Certificates, is considered proprietary to The Boeing Company and/or its suppliers, and is provided on a confidential basis.

The data provided should be returned to Boeing immediately following use by the FAA, including any copies thereof which the FAA may be required to make in the course of its review. Boeing does not authorize the FAA to retain any portion of the materials being supplied.

# rti-BDEIND

_/ Page 2 U.S. Department ofTransportation M-ABOH-14-00022

Sincerely,

T. A. Scoville Manager, Puget Sound Regulatory Administration Technical Services, Commercial Airplanes M/C 7A-WP, (425) 717-3895 FAX: (425) 965-8280

Enclosures:

cc 

### Name

Mr.A.Lam

Ms. M. Gordon (a) Petition for Exemption (b) SpecificationApproval Letter



### Enclosures Share Comments Point No 

### X FAA Program Mgr., TS & OOP Models (LAACO)
No 

### X FAATADEnclosure (a) to M-ABOH-14-00022 Page 1 of 12



### , A. Name andAddress of thePetitioner

Doug Lane, Director, Regulatory Administration The Boeing Company PO Box 3707

. Seattle, Washington, 98124



### B. Section of the Code of FederalRegulations (CFRs) thatareAffected

As provided for in §11.61 (b), per §11.81, Boeing hereby petitions for exemption for the following CFR Title 14 Part 25 regulations associated with the installation ofJAMCO oven, Part Number A233-1, on model767-300 Boeing Converted Freighter (BCF), VS721 (SIN 32972). All regulations listed below are per the model certification basis as defined by Type Certification Data Sheet A1NM.

Regulation Requirement 

### 14CFR (a) Strengthrequirements are specified in terms oflimit loads (the 25.301(a)(b)(c) maximum loads to be expected in service) and ultimate loads Loads (limit loads multiplied by prescribed factors ofsafety). Unless otherwise provided, prescribed loads are limit loads. (b) Unless otherwise provided, the specified air, ground, and
water loads must be placed in equilibrium with inertia forces, considering each item ofmass in the airplane. These loads must be distributed to conservatively approximate or closely represent actual conditions. Methods used to determine load intensities and distribution mustbe validated by flight load measurement unless the methods used for determining those loading conditions are shown to be reliable. (c) Ifdeflections under load would significantly change the distribution ofexternal or internal loads, this redistribution must be taken into account. 14 CFR 25.303 Unless otherwise specified, a factor ofsafety of 1.5 mustbe Factor ofsafety applied to the prescribed limit load which are considered external loads on the structure. When a loading condition is prescribed in
terms ofultimate loads, a factor ofsafety need not be applied unless otherwise specified. 14CFR (a) The structure mustbe able to support limit loads without any 25.305(a)(b)(c)(e)(f) 

### detrimental permanent deformation. At any load up to limit loads Strength and the deformation may not interfere with safe operation. deformation. (b) The structure must be able to support ultimate loads without failure for at least 3 seconds. However, whenproofofstrength is shown by dynamic tests simulating actual load conditions, the 3- second limit does not apply. Static tests conducted to ultimate load must include the ultimate deflections and ultimate deformation induced by the loading. When analytical methods are used to14 CFR25.307(a)(d) Proofofstructure.

14CFR 25.561(a)(b)(c) General. Enclosure (a) to M-ABOH-14-00022 Page 2 of 12

show compliance with the ultimate load strength requirements, it
must be shown that-- (1) The effects ofdeformation are not significant; (2) The deformations involved are fully accounted for in the analysis; or (3) The methods and assumptions used are sufficientto coverthe effects ofthese deformations. (c) Where structural flexibility is suchthat any rate ofload application likely to occur inthe operating conditions might produce transient stresses appreciably higherthan those corresponding to static loads, the effects ofthis rate ofapplication
mustbe considered. (e) The airplane must be designed to withstand any vibration and buffetingthatmight occur in any likely operating condition up to V0/M0 , including stall and probable inadvertent excursions beyond the boundaries ofthe buffet onset envelope. This must be shown by analysis, flight tests, or othertests found necessary by the Administrator. (f) Unless shownto be extremely improbable, the airplane mustbe designed to withstand any forced structural vibration resulting from any failure, malfunction or adverse condition in the flight control system. These must be considered limit loads and mustbe investigated at airspeeds up to Vc/Mc. (a) Compliance with the strength and deformation requirements of this subpartmust be shown for each critical loading condition. Structural analysis may be used only ifthe structure conforms to those for which experience has shown this method to be reliable. The Administratormay require ultimate load tests in cases where limit load tests maybe inadequate. (d) When static or dynamic tests are used to showcompliance with the requirements ofSec. 25.305(b) for flight structures, appropriate material correction factors mustbe applied to the test

.results, unless the structure, orpartthereof, beingtested has features such that a number ofelements contribute to the total strength ofthe structure and the failure ofone element results in the redistribution ofthe load through 'alternate load paths.

(a)The airplane, although it may be damaged in emergency landing conditions on land orwater, mustbe designed as prescribed in this sectionto protect each occupantunderthose conditions. (b) The structure mustbe designed to give each occupant every reasonable chance ofescaping serious injury in a minor crash landing when-- (1) Properuse is made ofseats, belts, and all other safety design provisions;14 CFR 25.601 General

14 CFR 25.603(a)(b)(c) Materials

14 CFR25.605(a)(b) Fabrication methods

14CFR 25.607(a)(b)(c) Fasteners Enclosure (a) to M-ABOH-14-00022 Page 3 of 12

(2) The wheels are retracted (where applicable); and (3) The occupant experiences the following ultimate inertia forces relative to the surrounding structure: (i) Upward, 3.0g. (ii) Forward, 9.0g. (iii) Sideward, 3.0g on the airframe; and 4.0g on the seats and their attachments. (iv) Downward, 6.0g. (v) Rearward, 1.5g. (c) Forequipment, cargo in the passenger compartments and any other large masses, the following apply: (1) Except as provided in paragraph (c)(2) ofthis section, these items must be positioned so that ifthey break loose, they will be unlikely to: (i) Cause direct injury to occupants; (ii) Penetrate fuel tanks or lines or cause fire or explosion hazard by damage to adjacent systems; or (iii) Nullify any ofthe escape facilities provided for use after an emergency landing. (2) The supporting structure must be designed to restrain, under all loads up to those specified in paragraph (b)(3) ofthis section, each item ofmass that could injure an occupant ifit came loose in

a minor crash landing. The airplane may not have design features ordetails that experience**ha~** shown to be hazardous or unreliable. The suitability ofeach questionable design detail and part must be established by tests. The suitability and durability ofmaterials used for parts, the failure ofwhich could adversely affect safety, must-- (a) Be established on the basis ofexperience ortests; (b) Conform to approved specifications (such as industry or military specifications, orTechnical Standard Orders)that ensure theirhaving the strength and otherproperties assumed in the design data; and · (c) Take into accountthe effects ofenvironmental conditions, such as temperature and humidity, expected in service.

, (a) The methods offabrication used mustproduce a consistently

sound structure. Ifa fabrication process (such as gluing, spot welding, orheattreating) requires close control to reach this objective, theprocess mustbeperformed under an approved process specification. (b) Each new aircraft fabrication method must be substantiated by

a test program. (a) Each removable bolt, screw, nut, pin, or other removable fastener must incorporate two separate locking devices if-- (1) Its loss could preclude continued flight and landing within the

### I4 CFR 25.609(a)(b) Protection ofstructure

I4 CFR 25.6I I Accessibility prOVISIOnS

14CFR 25 .613(a)(b)(c)(e)(f) 

### Material strength properties and material design values Enclosure (a) to M-ABOH-14-00022 Page 4 of 12


### design limitations ofthe airplane using normal pilot skill and strength; or (2) Its Joss could result in reduction in pitch, yaw, orroll control capability orresponse belowthatrequired by Subpart B ofthis chapter. (b) The fasteners specified in paragraph (a) ofthis section and their locking devices may not be adversely affected by the environmental conditions associated with the particular installation. (c) No self-locking nut may be used on any bolt subjectto rotation in operation unless a nonfriction locking device is used in addition
to the self-locking device. Each part ofthe structure must-- (a) Be suitably protected against deterioration or loss ofstrength in service due to any cause, including-- (I) Weathering; (2) Corrosion; and (3) Abrasion; and (b) Haveprovisions for ventilation and drainage where necessary for protection. Means must be provided to allow inspection (including inspection ofprincipal structural elements and control systems), replacement ofparts normally requiring replacement, adjustment, and lubrication as necessary for continued airworthiness. The inspection means for each item must bepracticable for the inspection interval for the item. Nondestructive inspection aids may be used to inspect structural elements where it is impracticable to provide means for direct visual inspection ifit is shown that the inspection is effective and the inspection procedures are specified in the maintenance manual required by Sec. 25.1529. (a) Material strength properties must be based on enough tests of material meeting approved specifications to establish design values on a statistical basis. (b) Material design values must be chosen to minimize the probability ofstructural failures due to material variability. Except

as provided in paragraphs (e) and (f) 

### ofthis section, compliance
must be shown by selecting material design values which assure material strength with the following probability: (1) 

### Where applied loads are eventually distributed through a single member within an assembly, the failure ofwhich would result in loss ofstructural integrity ofthe component, 99 percent probability with 95 percent confidence. (2) Forredundant structure, in which the failure ofindividual elements would result in applied loads being safely distributed to other load carrying members, 90 percent probability with 95

### 14CFR 25.619(a)(b)(c) Special factors

14CFR 25.621 (a)(b)(c)(d) Casting factors percent confidence. Enclosure (a) to M-ABOH-14-00022 Page 5 of 12



### (c) The effects ofenvironmental conditions, such as temperature and moisture, on material design values used in an essential component or structure must be considered where these effects are significant within the airplane operating envelope. (e) Greater material design values may be used ifa "premium selection" ofthe material is made in which a specimen ofeach individual item is tested before use to determine thatthe actual strength properties ofthatparticular item will equal orexceed those used in design. (f) 

### Othermaterial design values may be used ifapproved by the Adm'inistrator. The factor ofsafetyprescribed in Sec. 25.303 must be multiplied by the highestpertinent special factor ofsafety prescribed in Sees. 25.621 through 25.625 for each part ofthe structure whose strength is-- (a) Uncertain; (b) Likely to deteriorate in service before normal replacement; or (c) Subjectto appreciable variability because ofuncertainties in manufacturing processes or inspection methods. (a) 

### General. The factors, tests, and inspections specified in paragraphs (b) through (d) ofthis section must be applied in addition to those necessary to establish foundry quality control. The inspections must meet approved specifications. Paragraphs (c) and (d) ofthis section apply to any structural castings except castings that are pressure tested as parts ofhydraulic orother fluid systems and do not support structural loads. (b) 

### Bearingstressesandsurfaces. The casting factors specified in paragraphs (c) and (d) ofthis section-- (I)Need not exceed I.25 with respect to bearing stresses regardless ofthe method ofinspection used; and (2) Need notbe used with respect to the bearing surfaces ofa part whose bearing factor is larger than the applicable casting factor. (c) 

### Critical castings. For each casting whose failure would preclude continued safe flight and landing ofthe airplane or result in serious injury to occupants, the following apply: (1) 

### Each critical casting must-- (i) Have a casting factor ofnot less than I.25; and (ii) Receive I00percent inspection by visual, radiographic, and magneticparticle orpenetrant inspection methods or approved equivalent nondestructive inspection methods. (2) Foreach critical casting with a casting factor Jess than 1.50, three sample castings must be static tested and shown to meet-- (i) The strength requirements ofSec. 25.305 at an ultimate load corresponding to a casting factor of 1.25; and (ii)

### The deformation requirements ofSec. 25.305 at a load of 1.15

### 14 CFR25.623(a)(b) Bearing factors.

14 CFR 25.625(a)(b)(c) Fitting factors Enclosure (a) to M-ABOH-14-00022 Page 6 of 12



### times the limit load. (3) Examples ofthese castings are structural attachment fittings, parts offlight control systems, control surface hinges and balance weight attachments, seat, berth, safety belt, and fuel and oil tank supports and attachments, and cabin pressure valves. (d) 

### Noncritical castings. For each casting otherthan those specified in paragraph (c) ofthis section, the following apply: (1) 

### Except as provided in subparagraphs (2) and (3) ofthis paragraph, the casting factors and corresponding inspections must meet the**follo~ing** 

### table: 

### Casting 

# I

. .. Inspection factor

# ~~~~-~:-~ore**-~100** percent visual.

..

·Lessthan 2.0 100 percentvisual, and magnetic particle or but more penetrant or equivalent ·.than 1.5 nondestructive inspec!ion methods.

1.25 through 100 percentvisual, magnetic particle orpenetrant, 1.50--- and radiographic, or approved equivalent nondestructive inspection methods.

(2) Thepercentage ofcastings inspected by nonvisual methods may be reduced below that specified in subparagraph (1) ofthis paragraph when an approved quality control procedure is established. (3) For castingsprocured to a Specification that guarantees the mechanical properties ofthe material in the casting and provides for demonstration ofthese properties by test ofcoupons cut from the castings on a sampling basis-- (i) A casting factor of 1.0 may be used; and (ii) The castings must be inspected as provided in subparagraph (1) ofthis paragraph for casting factors of"1.25 through 1.50" and tested under paragraph (c)(2) ofthis section. (a) Except as provided in paragraph (b) ofthis section, each part that has clearance (free fit), and that is subjectto pounding or vibration, must have a bearing factor large enough to provide for the effects ofnormal relative motion. (b) No bearing factor need be used for a part for which any larger special factor is prescribed. For each fitting (a part or terminal used tojoin one structural memberto another), the following apply: (a) For each fitting whose strength is notproven by limit and ultimate load tests in which actual stress conditions are simulated14 CFR25.787(a)(b) Stowage compartments

14 CFR25.789(a) Retention ofitems of

mass in passenger and

crew compartments and galleys

14 CFR 25.853(a) Compartment interiors Enc,losure (a) to M-ABOH-14-00022 Page 7 of 12

in the fitting and surrounding structures, a fitting factor ofat least 1.15 must be applied to each part of-- (I) The fitting; (2) The means ofattachment; and (3) The bearing on thejoined members. (b) No fitting factor need be used-- (1) Forjoints made under approved practices and based on comprehensive test data (such as continuousjoints in metal plating, weldedjoints, and scarf joints in wood); or (2) With respect to any bearing surface for which a larger special factor is used. (c) For each integral fitting, thepart must be treated as a fitting up to thepoint at which the section properties become typical ofthe member. (a) Each compartment for the stowage ofcargo, baggage, carryon articles, and equipment (such as life rafts), and any other stowage compartmentmust be designed for its placarded maximum weight ofcontents and for the critical load distribution
at the appropriate maximum load factors corresponding to the specified flight and ground load conditions, and to the emergency

. landing conditions ofSec. 25.561(b), exceptthatthe forces speCified in the emergency landing conditions need not be applied
to compartments located below, orforward, ofall occupants in the airplane. 

### Ifthe airplane has a passenger seating configuration, excluding pilots seats, ofI0 seats or more, each stowage compartment in the passenger cabin, except for underseat and· overhead compartments for passenger convenience, mustbe completely enclosed. (b) There must be a means to preventthe contents in the compartments from becoming a hazard by shifting, underthe loads specified in paragraph (a) ofthis section. For stowage compartments in the passenger and crew cabin, ifthe means used is a latched door, the design musttake into consideration the wear and deterioration expected in service. (a) Means must be provided to prevent each item ofmass (that is part ofthe airplane type design) in a passenger or**c~ew** compartment or galley from becoming a hazard by shifting under the appropriate maximum load factors corresponding to the specified flight and ground load conditions, and to the emergency landing conditions ofSec. 25.561(b). For each compartment occupied by the crew orpassengers, the following apply: (a) Materials (inchiding finishes ordecorative surfaces applied to the materials) must meetthe applicable test criteriaprescribed in partI ofappendixF ofthis part, orother approved equivalent methods, regardless ofthe passengercapacity ofthe airplane.

### 14 CFR25.869(a)(4) Fire protection: systems

14 CFR 25.1301(a)(b)(c)(d) Function and installation

14 CFR 25.1309 (a)(b)(d)(g) Equipment, systems, and installations



# . (a) Electrical system components: Enclosure (a) to M-ABOH-14-00022 Page 8 of 12



### (4) Insulation on electrical wire andelectrical cable installed in any area ofthe airplane mustbe self-extinguishing when tested in accordance with the applicable portions ofPartI, Appendix F of this part. Each item ofinstalled equipment must-- (a) Be ofakind and design appropriate to its intended function; (b) Be labeled as to its identification, function, or operating limitations, orany applicable combination ofthese factors; (c) Be installed according to limitations specified for that equipment; and (d) Function properly.when installed. (a) The equipment, systems, and installations whose functioning isrequired bythis subchapter, mustbe designed to ensure thatthey perform their intended functions under any foreseeable operating condition. (b) The airplane systems and associated components, considered separately and in relation to other systems, must be designed so that-- (1) The occurrence ofany failure condition which wouldprevent the continued safe flight and landing ofthe airplane is extremely improbable, and (2) The occurrence ofany other failure condition which would reduce the capability ofthe airplane orthe ability ofthe crew to cope with adverse operating conditions is improbable. (d) Compliance with the requirements ofparagraph (b) ofthis section mustbe shown by analysis, and where necessary, by appropriate ground, flight, or simulatortests. The analysis must consider-- (1) Possible modes offailure, including malfunctions and damage from external sources. (2) The probability ofmultiple failures and undetected failures. (3) The resulting effects on the airplane and occupants, considering the stage offlight and operating conditions, and (4) The crew warning cues, corrective action required, and the capability ofdetecting faults. (g) In showing compliance withparagraphs (a) and (b) ofthis section with regard to the electrical system and equipment design and installation,ccritical environmental conditions must be considered. For electrical generation, distribution, and utilization equipment required by or used in complying with this chapter, except equipmentcovered by Technical Standard Orders containing environmental testprocedures, the ability to provide continuous, safe service underforeseeable environmental conditions may be shown by environmental tests, design analysis,

orreference to previous comparable service experience on other

### 14 CFR25.1351(a)(l) General

14 CFR 25.1353(a)(b)(d) Electrical equipment and installations

14 CFR 25.1357(a)(c) Circuitprotective devices

14 CFR25.1541(a)(b) General

14 CFR25.1557(a) Miscellaneous markings and placards aircraft. Enclosure (a) to M-ABOH-14-00022 Page 9 of 12



### (a) Electricalsystem capacity. The required generating capacity, and number and kinds ofpower sources must-- (1) Be determined by an electrical load analysis;

(a) Electrical equipment, controls, and wiring must be installed so that operations ofany one unit or system ofunits will not adversely affect the simultaneous operation ofany other electrical unit or system essential to the safe operation. Any electrical interference likely to be present in the airplane mustnot result in hazardous effects upon the airplane or its systems except under extremely remote conditions. (b) Cables must be grouped, routed, and spaced so that damage to essential circuits will be minimized ifthere are faults in heavy current-carrying cables. (d) Electrical cables and cable installations must be designed and installed as follows: (1) The electrical cables used mustbe compatible withthe circuit protection devices required by Sec. 25.1357 ofthis part, such that

a fire or smoke hazard cannotbe created undertemporary or continuous fault conditions.



# . (2) Means ofpermanent identification must be provided for electrical cables, connectors and terminals. (3) Electrical cables must be installed suchthatthe risk of mechanical damage and/or damage caused by fluids, vapors, or
sources ofheat, is minimized. (a) Automatic protective devices mustbe used to minimize· distress to the electrical system and hazard to the airplane in the
event ofwiring faults or serious malfunction ofthe system or connected equipment. (c) Each resettable circuitprotective device must be designed so that, when an overload or circuit fault exists, it will open the circuit irrespective ofthe position ofthe operating control. (a) The airplane must contain-- (1) The specified markings and placards; and (2) Any additional information, instrument markings, and placards required for the safe operation ifthere are unusual design, operating, orhandling characteristics. (b) Each marking and placard prescribed in paragraph (a) ofthis**section-~** 

### (1) Must be displayed in a conspicuous place; and (2) May notbe easily erased, disfigured, or obscured. (a) Baggage andcargo compartmentsandballast location. Each baggage and cargo compartment, and each ballast location must have a placard stating any limitations on contents, including weight, that are necessary under the loading requirements.Enclosure (a) to M-ABOH-14-00022 Page 10 of 12



### However, underseat compartments designed for the storage of carry-on articles weighing not more than 20 pounds need not have

a loading limitation placard.



### C. 

## The Extentof Relief BeingSought

Regulations Requirement Why relief is necessary 14 CFR Part 25 Provide applicable JAMCO oven part numberA233-1 has been sections: requirements for the previously installed on new 767-300ER and 767- 25.301 (a)(b)(c) component level 300F airplanes produced by Boeing and delivered 25.303 certification ofJAMCO to All Nippon Airlines (ANA). Since the oven itself 25.305(a)(b)(c)(e)(f) oven, part number was not FAA-approved, exceptions were included 25.307(a)(d) A233-1. on the Export Certificates ofAirworthiness for those 25.561 (a)(b)(c) airplanes per 14 CFR 21.329, citing Japan Civil 25.601 Aviation Bureau (JCAB) Specification Approval 25.603(a)(b)(c) Letters which include the oven part number and the 25.605(a)(b) FAA regulations for which the JCAB indicates 25.607(a)(b)(c) approval. 25.609(a)(b) 25.611 Boeing has been requested by our customer, to 25.613(a)(b)(c)(e)(f) install the same oven on VS721 as part ofthe 25.619(a)(b)(c) Boeing Converted Freighter modification project 25.621 (a)(b)(c)(d) currently in work. Enclosure (b) is a copy ofthe 25.623(a)(b) JCAB Spec Approval Letter (KOKU-KU-KI-114) 25.625(a)(b)(c) that Boeing has received to support installation of 25.787(a)(b) the A233-1 oven on the VS721 BCF modification. 25.789(a) 25.853(a) 25.869(a)(4) 25.1301 (a)(b)(c)(d) 25.1309(a)(b)(d)(g) 25.1351 (a)(1) 25.1353(a)(b)(d) 25.1357(a)(c) 25.1541 (a)(b) 25.1557(a)



## D. Description of theIssue

Boeing initially proposed to the FAA the use of FCAA waivers for FCAA accepted 14 CFR Part 25 regulations resulting from Boeing modifications offoreign registered airplanes. The FAA responded, via letter 1OOB-13-57 (dated March 26, 2013), that the OMT did not concur with Boeing's proposal because 14 CFR Part 21.329 is not intended to apply to type design changes on an aircraft that has been previously exported, and that the proposed change, which is regulated by 14 CFR Part 21.97, under subpart D, is not covered by section 21.329 for obtaining exception or deviation approval of a modification project from an FCAA. ·

The FAA further stated that Boeing may petition for an exemption requesting relieffrom the requirements ofa current regulation in a major change to type design project, or for a rulemaking to amend section 21.329 to extend the exception or deviation to a major change to type design.Enclosure (a) to M-ABOH-14-00022 Page 11 of 12

Since 14 CFR Part 21.329 only applies to production airplanes in regard to waiver applicability, and is not intended to apply to approval of changes to type design of previously exported airplanes, Boeing is seeking relief from the 14 CFR Part 25 requirements identified in Table C above, to allow installation ofthe JAMCO oven (part numberA233-1) on VS721 (SIN 32972). As noted in Enclosure (b), the oven has been granted Specification Approval by the JCAB to the regulations listed above and has been installed on new Boeing production aircraft. Therefore, Boeing is requesting an exemption to the listed 14 CFR Part 25 regulations.



### E. Statement of PublicInterest

Granting this exemption would benefit the public by helping to maintain international commercial trade of goods and services. It would allow Boeing to provide post-production services equivalent to those provided for production aircraft, and result in operational commonality among our customer's fleet. Denial ofthis petition would not be in the public's interest, and would reduce the operational capability ofthe affected aircraft, requiring our customers to operate a mixed fleet, and could cause Boeing to lose customers in the aircraft modification market, resulting in reduced potential US Gross Domestic Product.



### F. Statement of NoAdverseEffecton Safety

The oven to be installed on VS721 (S/N 32972) has been previously installed on new 767-300ER and 767-300F model airplanes delivered to ANA. There have been no safety issues with the installation ofthese ovens on the airplane. Granting this exemption would allow Boeing to install the same part as delivered on ANA's productions airplanes, providing ANA functional commonality among its fleet.


### G. Requestto Waive Publication andComment

Based on the limited scope ofthis proposed exemption (one airplane}, Boeing respectfully requests that the public comment period be deemed not required forthis exemption.



### H. 

### Conclusion

Boeing Commercial Airplanes requests exemption from the listed 14 CFR Part 25 regulations for the certification ofJAMCO oven A233-1 to be installed on Boeing 767-300BCF model airplane, VS721 (S/N 32972}.



### I. 

### Privileges of this Exemption Outside the UnitedStates

Per§ 11.81 (h), Boeing requests that the privileges ofthis Exemption be extended outside ofthe United States. This extension of privileges is necessary for operations based within foreign countries having bilateral agreements with the United States accepting FAA 14 CFR Part 25 as their airworthiness standard for transport category aircraft.



### Summary to bePublishedin the FederalRegister

PETITIONER: Boeing Commercial AirplanesEnclosure (a) to M-ABOH-14-00022 Page 12 of 12

SECTION OF 14 CFR AFFECTED: 14 CFR Part 25 regulations per the model certification basis

as defined by Type Certification Data Sheet A1NM provided below:

25.301 (a)(b)(c) 25.605(a)(b) 25.623(a)(b) 25.1309(a).(b)(d)(g) 25.303 25.607(a){b)(c) 25.625(a)(b)(c) 25.1351 (a)(1) 25.305(a)(b){c)(e)(f) 25.609(a){b) 25.787(a)(b) 25.1353(a)(b)(d) 25.307(a)(d) 25.611 25.789(a) 25.1357(a)(c) 25.561 (a)(b)(c) 25.613(a)(b)(c)(e)(f) 25.853(a) 25.1541(a)(b) 25.601 25.619(a)(b)(c) 25.869(a)(4) 25.1557(a) 25.603(a)(b)(c) 25.621 (a)(b)(c)(d) 25.1301 (a)(b)(c)(d)

DESCRIPTION OF RELIEF SOUGHT: To permit the installation ofan A233-1 JAMCO oven that has been installed on previously-delivered production airplanes when the FCAA has provided acceptance ofthe oven via letterto the FAA, for the modification of a foreign registered 767-300ER to a Boeing Converted Freighter configuration. Allowance will permit Boeing to install an FCAA accepted oven on a 767-300ER airplane during modification to a Boeing Converted Freighter configuration.

# Civil )f.viation(Bureau Enclosure (b) to M-ABOH-14-00022 Page 1o£3

9dinistry 

## Of £atuf, Irifrastnu:ture, tfransport}f.tuftfourism 2-1-3, Kasumigaseki, Chiyoda·ku,

KOKU-KU-KI-114

Mr. Ross Landes Manager, ANM-1OOS DepartmentofTranspotiation FederalAviationAdministration SeattleAircraft Certification Office 1601 LindAvenue SW Renton, WA 98057-3356 USA

DearMt: Landes, TOKYO 100·8918,JAPAN

Aug 7, 2013

An All Nippon Airways' (ANA) Boeing 767-300 airplane (Registration Number JA603A, Block Number VS721) is now under the Boeing convetted freighter modification work at SASCO Modification Center, Singapore. This modificationwill be approved thi:ough Boeing Service Bulletins (SBs) bythe FAA.

This letter notifies you that certain equipment furnished by ANA, which is to be installed on the airplanes, hasbeen granted SpecificationApprovals by the JCAB as shown in AttachmentI. The compliance list with the applicable FAR requirements for the equipment is shown inAttachmentII, which hasbeen determined inthecourse ofSpecificationApproval. Status ofamendment of the FAR requirements in Attachment II corresponds to that ofthe certificationbasisofB767·300F (FAAType Certificate Data SheetNo. AlNM).

It would be highly appreciated if you take into account of our approval when you approve SBs for B767·300BCF modification.

Thank you for your consideration in advance. Ifyou need any further information, please contactus.
Sincerely,

# r::~JM<Wlk

YasuhiroYamada Chief AirworthinessEnginee1· Airworthiness Division

C. C. Mr. Takeo Kikuchi Director, Engineering All NipponAirways Co., LTD.

Attachment I 

### n BFE List perEach Mamifacturer FAR ComplianceListKOKU-KU-KI-114 Enclosure (b) toM-ABOH-14-00022 Page 2 of3

Attachment#I

EquipmentList perEach Manufacturer

MANUFACTURER: JAMCO CORPORATION

PARTS NAME

Oven PART NUMBER

A233-1 DRAWING NUMBER

A233 S.A. NUMBER

394KOKU-KU-KI-114

Applicable JAMCO FAR Requirements A233-1 Oven Subpart C 1§25.301 

### 0 Structure !§25.303 

### 0 1§25.305 

### 0 1§25.307 

### 0 1&25.561 

### 0 SubpartD [§25.601 

### 0 Design and [§25.603 

### 0 Construction

1§25.605 

### 0 1&25.607 

### 0 1&25.609 

### 0 [§25.611 

### 0 1§25.613 

### 0 1&25.619 

### 0

1&25.621 

### 0· ,&25.623 

### 0 1&25.625 

### 0
_.:;:;, [§25.785 

### 0 [§25.787 

### 0 1&25.789 

### 0 1&25.853 

### 0 [§25.869 

### 0 SubpartF [§25.1301 

### 0 Equipment 1&25.1309 

### 0 1§25.1351 

### 0 1&25.1353 

### 0**~** 1&25.1355 

### 0 1&25.1357 

### 0**~** 1&25.1363 

### 0 Subpart G 1&25.1541 

### 0 Operating Limitations §25.1557 

### 0
and Information Appendix F to Part 25 

### 0

Note; 

### "0" denotes applicable, thru Amendment 25-117



## FAR Compliance List Endosure (b) to M-ABOH-14-00022 Page 3 o£3
Attachment#2



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