Federal Register / Vol. 79, No. 190 / Wednesday, October 1, 2014 / Rules and Regulations 59093 

6.B.(1)(c), and the requirement to return 

module M01 in paragraph 6.B.(2)(b)2 of 

Turbomeca S.A. MSB No. 292 72 2849, 

Version B, dated November 25, 2013, are not 

required by this AD. 

(2) For all affected Turbomeca S.A. 

engines, during each engine shop visit after 

the effective date of this AD, perform a 

vibration check of the AGB 41/23-tooth bevel 

gear meshing. Guidance on performing the 

vibration check during an engine shop visit 

can be found in the service information listed 

in paragraph (i)(3) in the Related Information 

section. 

(3) If the AGB does not pass the vibration 

check required by paragraphs (e)(1) or (e)(2) 

of this AD, replace the AGB with a part 

eligible for installation. 

(f) Credit for Previous Action 

If you performed a vibration check of the 

AGB before the effective date of this AD 

using Turbomeca S.A. MSB No. 292 72 0839, 

Version A, dated September 9, 2013; or MSB 

No. 292 72 2849, Version A, dated September 

9, 2013, or during an engine shop visit per 

paragraph (e)(2) of this AD, you met the 

initial inspection requirement of paragraph 

(e)(1) of this AD. 

(g) Definition 

For the purpose of this AD, an ‘‘engine 

shop visit’’ is the induction of an engine into 

the shop for maintenance involving the 

separation of pairs of major mating engine 

flanges. The separation of engine flanges 

solely for the purpose of transportation 

without subsequent engine maintenance does 

not constitute an engine shop visit. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs to this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(i) Related Information 

(1) For more information about this AD, 

contact Mark Riley, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7758; fax: 781–238–7199; 

email: mark.riley@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2014–0036, dated 

February 11, 2014, for related information. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/#!docketDetail;D=FAA2014-0164. 

(3) Turbomeca Engine Test Bed Acceptance 

Test Specifications CCT No. 0292009400, 

Version T; CCT No. 0292019400, Version R; 

CCT No. 0292019690, Version I; CCT No. 

029201530, Version K; CCT No. 0292019610, 

Version K; CCT No. 0292029450, Version J; 

CCT No. 0292029490, Version I; CCT No. 

0292029440, Version I; CCT No. 0292029480, 

Version K; CCT No. 0292029520, Version H; 

CCT No. 0292029410, Version L; CCT No. 

0292029530, Version H; or Turbomeca ID No. 

383952; or Turbomeca RTD No. X 292 65 327 

2, which are not incorporated by reference in 

this AD, can be obtained from Turbomeca 

S.A., using the contact information in 

paragraph (j)(3) of this AD. This service 

information provides guidance on performing 

the vibration check during an engine shop 

visit. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Turbomeca S.A. Mandatory Service 

Bulletin (MSB) No. 292 72 0839, Version B, 

dated November 25, 2013. 

(ii) Turbomeca S.A. MSB No. 292 72 2849, 

Version B, dated November 25, 2013. 

(iii) Turbomeca S.A. Arriel 1 Technical 

Instruction (TI) No. 292 72 0839, Version E, 

dated February 20, 2014. 

(iv) Turbomeca S.A. Arriel 1 TI No. 292 72 

0840, Version A, dated November 29, 2013. 

(v) Turbomeca S.A. Arriel 2 TI No. 292 72 

2849, Version E, dated February 20, 2014. 

(vi) Turbomeca S.A. Arriel 2 TI No. 292 72 

2850, Version A, dated November 29, 2013. 

(3) For Turbomeca S.A. service information 

identified in this AD, contact Turbomeca, 

S.A., 40220 Tarnos, France; phone: 33 (0)5 59 

74 40 00; telex: 570 042; fax: 33 (0)5 59 74 

45 15. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 12 

New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

(5) You may view this service information 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

September 15, 2014. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–23353 Filed 9–30–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0424; Directorate 

Identifier 2014–NM–003–AD; Amendment 

39–17976; AD 2014–20–03] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model BD–700–1A10 

and BD–700–1A11 airplanes. This AD 

was prompted by reports of an 

incorrectly assembled check tee fitting 

used in fire extinguishing (FIREEX) 

distribution lines. This AD requires 

inspecting to determine the part number 

and for all affected check tee fittings 

measuring for correct depth, and 

replacing if necessary. We are issuing 

this AD to detect and correct faulty 

check tee fittings, which will reduce fire 

extinguishing protection. 

DATES: This AD becomes effective 

November 5, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 5, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0424 or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For service information identified in 

this AD, contact Bombardier, Inc., 400 

Coˆte-Vertu Road West, Dorval, Que ́bec 

H4S 1Y9, Canada; telephone 514–855– 

5000; fax 514–855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

FOR FURTHER INFORMATION CONTACT: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7318; fax 

516–794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Bombardier, Inc. Model 

BD–700–1A10 and BD–700–1A11 

airplanes. The NPRM published in the 

Federal Register on July 1, 2014 (79 FR 

37246). 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2013–41, 

dated December 30, 2013 (referred to 


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59094 Federal Register / Vol. 79, No. 190 / Wednesday, October 1, 2014 / Rules and Regulations 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

on certain Bombardier, Inc. Model BD– 

700–1A10 and BD–700–1A11 airplanes. 

The MCAI states: 

A check tee fitting used in the aeroplane 

fire extinguishing (FIREEX) distribution 

lines, was discovered by another airframe 

manufacturer as being incorrectly assembled. 

A properly assembled check tee fitting 

normally contains one check ball, however 

the affected fitting contained two check balls. 

The FIREEX manufacturer advised 

Bombardier that this condition may be 

present on aeroplane models BD–700–1A10 

and BD–700–1A11. 

Testing has verified that incorrect 

installation of the additional check ball in the 

fitting reduces the flow rate of the 

extinguishing agent. There are three check 

tee fittings installed on the BD–700–1A10 

and BD–700–1A11 aeroplanes, one for each 

engine and one for the auxiliary power unit. 

Faulty fittings will reduce fire extinguishing 

protection at the affected locations. 

Bombardier has issued several Alert 

Service Bulletins (ASBs) to identify, inspect 

and replace if required, all affected fittings. 

This [Canadian] AD mandates incorporation 

of the applicable Bombardier ASBs to rectify 

this problem. 

You may examine the MCAI in the 

AD docket on the Internet at http:// 

www.regulations.gov/#!documentDetail;

D=FAA-2014-0424-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 37246, July 1, 2014) or on the 

determination of the cost to the public. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. 

We have become aware that some 

operators have misunderstood or 

misinterpreted the Airworthy Product 

paragraph to allow the owner/operator 

to use messages provided by the 

manufacturer as approval of deviations 

during the accomplishment of an ADmandated action. The Airworthy 

Product paragraph does not approve 

messages or other information provided 

by the manufacturer for deviations to 

the requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed the 

paragraph and retitled it ‘‘Contacting the 

Manufacturer.’’ This paragraph now 

clarifies that for any requirement in this 

AD to obtain corrective actions from a 

manufacturer, the actions must be 

accomplished using a method approved 

by the FAA, TCCA, or Bombardier, 

Inc.’s TCCA Design Approval 

Organization (DAO). 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DAO, the approval must include 

the DAO-authorized signature. The DAO 

signature indicates that the data and 

information contained in the document 

are TCCA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DAO-authorized signature approval are 

not TCCA-approved, unless TCCA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

We also have decided not to include 

a generic reference to either the 

‘‘delegated agent’’ or ‘‘design approval 

holder (DAH) with State of Design 

Authority design organization 

approval,’’ but instead we have 

provided the specific delegation 

approval granted by the State of Design 

Authority for the DAH. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

37246, July 1, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 37246, 

July 1, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 57 

airplanes of U.S. registry. 

We also estimate that it would take 

about 1 work-hour per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work hour. Required parts would 

cost about $0 per product. Based on 

these figures, we estimate the cost of 

this AD on U.S. operators to be $4,845, 

or $85 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 1 work-hour, for a cost of $85 per 

tee fitting. We have no way of 

determining the number of aircraft that 

might need this action. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 


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Federal Register / Vol. 79, No. 190 / Wednesday, October 1, 2014 / Rules and Regulations 59095 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0424; or in 

person at the Docket Management 

Facility between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The AD docket contains this 

AD, the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2014–20–03 Bombardier, Inc.: Amendment 

39–17976. Docket No. FAA–2014–0424; 

Directorate Identifier 2014–NM–003–AD. 

(a) Effective Date 

This AD becomes effective November 5, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

BD–700–1A10 and BD–700–1A11 airplanes, 

certificated in any category, serial numbers 

9002 through 9500 inclusive, and 9998. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 26, Fire Protection. 

(e) Reason 

This AD was prompted by reports of an 

incorrectly assembled check tee fitting used 

in fire extinguishing (FIREEX) distribution 

lines. We are issuing this AD to detect and 

correct faulty check tee fittings, which will 

reduce fire extinguishing protection. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Part Number Identification 

Within 100 flight hours or 180 days, 

whichever occurs first after the effective date 

of this AD, inspect to determine the part 

number (P/N) of the FIREEX check tee fitting, 

in accordance with the Accomplishment 

Instructions of the applicable service bulletin 

identified in paragraph (g)(1), (g)(2), (g)(3), or 

(g)(4) of this AD. 

(1) Bombardier Alert Service Bulletin 

A700–1A11–26–003, dated April 18, 2013 

(for Model BD–700–1A11 (BD–700) airplanes 

having S/Ns 9127 through 9383 inclusive; 

9389 through 9400 inclusive, 9404 through 

9431 inclusive, and 9998). 

(2) Bombardier Alert Service Bulletin 

A700–26–010, dated April 18, 2013 (for 

Model BD–700–1A10 (BD–700) airplanes 

having S/Ns 9002 through 9312 inclusive, 

9314 through 9380 inclusive, and 9384 

through 9429 inclusive). 

(3) Bombardier Alert Service Bulletin 

A700–26–5002, dated April 18, 2013 (for 

Model BD–700–1A11 (BD–700) airplanes 

having S/Ns 9386, 9401, and 9445 through 

9498 inclusive). 

(4) Bombardier Alert Service Bulletin 

A700–26–6002, dated April 18, 2013 (for 

Model BD–700–1A10 (BD–700) airplanes 

having S/Ns 9313, 9381, and 9432 through 

9500 inclusive). 

(h) Measurement and Replacement 

If any inspection specified in paragraph (g) 

of this AD reveals any check tee fitting 

having P/N 446651 and S/N 062 through 070 

inclusive, 117 through 133 inclusive, 3728 

through 3731 inclusive, 3733 through 3760 

inclusive, or 3762 through 3776 inclusive: 

Within 100 flight hours or 180 days, 

whichever occurs first after the effective date 

of this AD, measure the depth of the inlet 

fitting of the check tee, in accordance with 

the Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraph (g)(1), (g)(2), (g)(3), or (g)(4) of this 

AD. If the check tee depth is less than 1.70 

inches (4.32 cm), before further flight, replace 

the check tee in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraph (g)(1), (g)(2), (g)(3), or (g)(4) of this 

AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; fax 516–794–5531. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, New York ACO, ANE–170, 

Engine and Propeller Directorate, FAA; or 

Transport Canada Civil Aviation (TCCA); or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–41, dated 

December 30, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0424-0002. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Bombardier Alert Service Bulletin 

A700–1A11–26–003, dated April 18, 2013. 

(ii) Bombardier Alert Service Bulletin 

A700–26–010, dated April 18, 2013. 

(iii) Bombardier Alert Service Bulletin 

A700–26–5002, dated April 18, 2013. 

(iv) Bombardier Alert Service Bulletin 

A700–26–6002, dated April 18, 2013. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 


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59096 Federal Register / Vol. 79, No. 190 / Wednesday, October 1, 2014 / Rules and Regulations 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 19, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–22978 Filed 9–30–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0792; Directorate 

Identifier 2013–NM–118–AD; Amendment 

39–17979; AD 2014–20–06] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 737–600, –700, 

–700C, –800, –900, and –900ER series 

airplanes, and Model 777 airplanes. 

This AD was prompted by testing 

reports on certain Honeywell phase 3 

display units (DUs). These DUs 

exhibited susceptibility to radio 

frequency emissions in WiFi frequency 

bands at radiated power levels below 

the levels that the displays are required 

to tolerate for certification of WiFi 

system installations. The phase 3 DUs 

provide primary flight information 

including airspeed, altitude, pitch and 

roll attitude, heading, and navigation 

information to the flightcrew. This AD 

requires replacing the existing phase 3 

DUs with phase 1, phase 2, or phase 3A 

DUs, and for certain replacement DUs, 

installing new DU database software. 

We are issuing this AD to prevent loss 

of flight-critical information displayed 

to the flightcrew during a critical phase 

of flight, such as an approach or takeoff, 

which could result in loss of airplane 

control at an altitude insufficient for 

recovery, or controlled flight into 

terrain. 

DATES: This AD is effective November 5, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 5, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2013– 

0792; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Jeffrey W. Palmer, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, Seattle Aircraft Certification 

Office, FAA, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425– 

917–6472; fax: 425–917–6590; email: 

jeffrey.w.palmer@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all The Boeing Company Model 

737–600, –700, –700C, –800, –900, and 

–900ER series airplanes, and Model 777 

airplanes. The NPRM published in the 

Federal Register on September 24, 2013 

(78 FR 58487). The NPRM was 

prompted by testing reports on certain 

Honeywell phase 3 DUs. These DUs 

exhibited susceptibility to radio 

frequency emissions in WiFi frequency 

bands at radiated power levels below 

the levels that the displays are required 

to tolerate for certification of WiFi 

system installations. The phase 3 DUs 

provide primary flight information 

including airspeed, altitude, pitch and 

roll attitude, heading, and navigation 

information to the flightcrew. The 

NPRM proposed to require replacing the 

existing phase 3 DUs with new phase 

3A DUs and installing new DU database 

software. We are issuing this AD to 

prevent loss of flight-critical 

information displayed to the flightcrew 

during a critical phase of flight, such as 

an approach or takeoff, which could 

result in loss of airplane control at an 

altitude insufficient for recovery, or 

controlled flight into terrain. 

Clarification of Cause of Unsafe 

Condition 

The cause of the unsafe condition 

stated in the Discussion section of this 

AD is a known susceptibility of the 

Phase 3 DUs to RF transmissions inside 

and outside of the airplane. This 

susceptibility has been verified to exist 

in a range of RF spectrum (mobile 

satellite communications, cell phones, 

air surveillance and weather radar, and 

other systems), and is not limited to 

WiFi transmissions. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 58487, 

September 24, 2013), and the FAA’s 

response to each comment. 

Request To Change Applicability 

Three commenters requested that we 

revise the applicability. A4A requested 

that we change the applicability to 

address only airplanes that have phase 

3 DUs installed. Mr. Philipp Schmid 

requested that the applicability only 

address airplanes that have a WiFi 

system installed in the cabin. All 

Nippon Airways (ANA) requested that 

we revise applicability paragraph (c) of 

the proposed AD (78 FR 58487, 

September 24, 2013) to refer to the 

airplanes identified in Boeing Special 

Attention Service Bulletin 737–31– 

1471, dated November 29, 2012; and 

Boeing Special Attention Service 

Bulletin 777–31–0187, dated November 

29, 2012. 

A4A stated that the FAA is making 

the NPRM (78 FR 58487, September 24, 

2013) applicable to all Model 737 NG 

and Model 777 series airplanes, 

regardless of the operator’s intent to 

install a Wi-Fi system. A4A expressed 

that in paragraph (e) of the proposed 

AD, the FAA acknowledges that the 

unsafe condition is directly related to 

electromagnetic interference (EMI) 

characteristics exhibited at specific 

frequency ranges related to Wi-Fi 

transmission. A4A stated that the phase 

3 DUs have passed all applicable 

certification testing required for 

approval and use on transport category 

airplanes, including the DO–160 

environmental standards. A4A asserted 


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