68174 Federal Register / Vol. 75, No. 214 / Friday, November 5, 2010 / Rules and Regulations 

Issued in Kansas City, Missouri, on 

October 21, 2010. 

Christina L. Marsh, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–27456 Filed 11–4–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1041; Directorate 

Identifier 2010–NM–198–AD; Amendment 

39–16493; AD 2010–23–04] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model DHC–8–400 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Several reports have been received of 

cracked nacelle attachment fittings. The 

preliminary investigation determined the 

cause to be stress corrosion. Stress corrosion 

cracking could compromise the structural 

integrity of the nacelle attachment fitting and 

could adversely affect the safe landing of the 

aeroplane. 

Failure of the fitting could result in 

collapse of the landing gear. This AD 

requires actions that are intended to 

address the unsafe condition described 

in the MCAI. 

DATES: This AD becomes effective 

November 22, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 22, 2010. 

We must receive comments on this 

AD by December 20, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–40, 1200 New Jersey 

Avenue, SE., Washington, DC, between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office 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. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Craig Yates, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7355; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2010–30R1, 

dated September 21, 2010 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Several reports have been received of 

cracked nacelle attachment fittings. The 

preliminary investigation determined the 

cause to be stress corrosion. Stress corrosion 

cracking could compromise the structural 

integrity of the nacelle attachment fitting and 

could adversely affect the safe landing of the 

aeroplane. 

This [Canadian] directive, as an interim, 

mandates a detailed visual inspection [for 

cracking] and conductivity check of each of 

the four (4) nacelle attachment fittings. 

Revision 1 of this [Canadian] directive is 

issued to update the aircraft serial number 

(S/N) applicability based on the latest crack 

findings and also to revise the acceptable 

conductivity values in Part I.A. In addition, 

Part II. has been added to provide 

instructions for newly affected aircraft and 

aircraft that have replaced nacelle attachment 

fittings. 

Failure of the fitting could result in 

collapse of the landing gear. Required 

actions include repetitive detailed 

inspections and replacement of the 

fittings, depending on inspection 

findings. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Bombardier has issued Service 

Bulletin 84–54–14, Revision J, dated 

September 17, 2010. For certain 

airplanes, this service bulletin describes 

procedures for a conductivity inspection 

and a repetitive detailed inspection for 

cracking of the nacelle attachment 

fittings. If the inspections find cracking, 

this service bulletin specifies 

replacement of the fitting, or if the 

inspection finds certain conductivity 

results, a daily repetitive detailed 

inspection until replacement of the 

fitting is accomplished. For certain 

other airplanes, this service bulletin 

describes repetitive detailed inspections 

for cracking of the nacelle attachment 

fittings and replacement of the fitting if 

any cracking is found. For all airplanes, 

this service bulletin specifies that 

replacement of the fitting extends the 

compliance time for the first repetitive 

detailed inspection on that fitting. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between the AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a Note within the AD. 

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Federal Register / Vol. 75, No. 214 / Friday, November 5, 2010 / Rules and Regulations 68175 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because there is a possibility that 

stress corrosion cracking of the fitting, if 

undetected, could adversely affect safe 

landing. Therefore, we determined that 

notice and opportunity for public 

comment before issuing this AD are 

impracticable and that good cause exists 

for making this amendment effective in 

fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2010–1041; 

Directorate Identifier 2010–NM–198– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

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 

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 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); and 

3. 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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 AD: 

2010–23–04 Bombardier, Inc.: Amendment 

39–16493. Docket No. FAA–2010–1041; 

Directorate Identifier 2010–NM–198–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 22, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier, Inc. 

Model DHC–8–400, –401, and –402 

airplanes, certificated in any category, serial 

numbers 4001 and subsequent. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 54: Nacelles/Pylons. 

Reason 

(e) The mandatory continued airworthiness 

information (MCAI) states: 

Several reports have been received of 

cracked nacelle attachment fittings. The 

preliminary investigation determined the 

cause to be stress corrosion. Stress corrosion 

cracking could compromise the structural 

integrity of the nacelle attachment fitting and 

could adversely affect the safe landing of the 

aeroplane. 

Failure of the fitting could result in collapse 

of the landing gear. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

Inspection and Conductivity Inspection of 

the Nacelle Attachment Fitting Assembly, 

Part Number 85414663, for Certain 

Airplanes 

(g) For airplanes having serial numbers 

4001 through 4304 inclusive, 4314, and 4315: 

Within 100 flight hours after the effective 

date of this AD, do a detailed inspection for 

cracking, and a conductivity inspection on 

each of the 4 nacelle attachment fittings, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–54–14, Revision J, dated September 17, 

2010. Repeat the detailed inspection at 

intervals not to exceed 300 flight hours, 

except as provided by paragraph (j) of this 

AD. 

(1) If any nacelle attachment fitting is 

found cracked, before further flight, replace 

the fitting with a new fitting in accordance 

with paragraph (3) of Part A of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–54–14, Revision J, dated 

September 17, 2010. 

(2) If the conductivity of any test points on 

any fitting is found to be greater than 45.0 

percent International Annealed Copper 

Standard (IACS) or if the conductivity of any 

test points on any fitting is found to be less 

than 38.0 percent IACS, do the actions 

required by paragraphs (g)(2)(i) and (g)(2)(ii) 

of this AD. 

(i) Within 24 hours after accomplishing the 

conductivity inspection specified in 

paragraph (g) of this AD, do a detailed 

inspection of the nacelle attachment fitting 

for cracking, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–54–14, Revision J, dated 

September 17, 2010, and repeat thereafter at 

intervals not to exceed 24 hours. If cracking 

is found, before further flight, replace the 

fitting with a new fitting in accordance with 

the requirements of paragraph (g)(2)(ii) of this 

AD. Replacement of the fitting terminates the 

daily detailed inspection requirements of this 

paragraph. 

(ii) Except as required by paragraph 

(g)(2)(i) of this AD: Within 300 flight hours 

after accomplishing the conductivity 

inspection specified in paragraph (g) of this 

AD, replace the fitting with a new fitting in 

accordance with paragraph (3) of Part A of 

the Accomplishment Instructions of 

Bombardier Service Bulletin 84–54–14, 

Revision J, dated September 17, 2010. 

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68176 Federal Register / Vol. 75, No. 214 / Friday, November 5, 2010 / Rules and Regulations 

Inspection Reports 

(h) Submit a report of the findings (both 

positive and negative) of the conductivity 

inspection required by paragraph (g) of this 

AD to Bombardier, at the applicable time 

specified in paragraph (h)(1) or (h)(2) of this 

AD, in accordance with Bombardier Service 

Bulletin 84–54–14, Revision J, dated 

September 17, 2010. The report must include 

the inspection results, a description of any 

discrepancies found, the airplane serial 

number, and the number of flight cycles and 

flight hours on the airplane. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 14 days after the inspection. 

(2) If the inspection was accomplished 

prior to the effective date of this AD: Submit 

the report within 14 days after the effective 

date of this AD. 

Inspection of the Nacelle Attachment Fitting 

Assembly, Part Number 85414663, for 

Certain Other Airplanes 

(i) For airplanes having serial numbers 

4305 through 4313 inclusive, and 4316 and 

subsequent: Within 1,200 flight hours after 

the effective date of this AD, do a detailed 

inspection for cracking on each of the 4 

nacelle attachment fittings, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 84–54–14, 

Revision J, dated September 17, 2010. If any 

nacelle attachment fitting is found cracked, 

before further flight, replace the fitting with 

a new fitting in accordance with paragraph 

(3) of Part A of the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–54–14, Revision J, dated September 17, 

2010. Thereafter, repeat the detailed 

inspection at intervals not to exceed 300 

flight hours, except as provided by paragraph 

(j) of this AD. 

Initial Inspection Compliance Time for New 

Fittings 

(j) For any fitting that is replaced in 

accordance with paragraph (3) of Part A of 

the Accomplishment Instructions of 

Bombardier Service Bulletin 84–54–14, 

Revision J, dated September 17, 2010, as 

specified in paragraph (g) or (i) of this AD: 

Within 1,200 flight hours after replacing the 

fitting, do a detailed inspection of that 

replaced fitting as specified in paragraph (g) 

or (i) of this AD, and repeat the detailed 

inspection thereafter at intervals not to 

exceed 300 flight hours. 

Credit for Replacing the Fitting Using 

Previous Service Information 

(k) Accomplishing the replacement of the 

nacelle fittings in accordance with any 

Bombardier service bulletin identified in 

Table 1 of this AD before the effective date 

of this AD is also acceptable for compliance 

with the fitting replacements specified in 

paragraphs (g) and (i) of this AD. 

TABLE 1—ACCEPTABLE SERVICE INFORMATION

Bombardier Service Bulletin— Revision— Dated— 

84–54–14 ..................................................................................................................................... Original ...................... April 16, 2010. 

84–54–14 ..................................................................................................................................... A ................................ April 22, 2010. 

84–54–14 ..................................................................................................................................... B ................................ June 11, 2010. 

84–54–14 ..................................................................................................................................... C ................................ June 30, 2010. 

84–54–14 ..................................................................................................................................... D ................................ July 5, 2010. 

84–54–14 ..................................................................................................................................... E ................................ August 19, 2010. 

84–54–14 ..................................................................................................................................... F ................................ August 20, 2010. 

84–54–14 ..................................................................................................................................... G ................................ September 9, 2010. 

84–54–14 ..................................................................................................................................... H ................................ September 10, 2010. 

Credit for Inspections Accomplished in 

Accordance With Previous Service 

Information 

(l) Accomplishment of the inspections 

required by paragraphs (g) and (i) of this AD 

before the effective date of this AD in 

accordance with any Bombardier service 

bulletin identified in Table 1 of this AD is 

acceptable for compliance with the 

corresponding actions required by 

paragraphs (g) and (i) of this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

Although the MCAI does not state a 

requirement for submitting inspection 

reports, this AD requires inspection reports 

to be submitted to the manufacturer so the 

manufacturer can gather information on the 

extent of the problem and develop corrective 

actions. Based on the results of these reports, 

we might determine that further rulemaking 

is warranted. This difference has been 

coordinated with TCCA. 

Other FAA AD Provisions 

(m) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, ANE–170, New York 

Aircraft Certification Office (ACO), FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. Send information to Attn: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone 516–228–7300; fax 516– 

794–5531. Before using any approved AMOC 

on any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(n) Refer to MCAI Canadian Airworthiness 

Directive CF–2010–30R1, dated September 

21, 2010; and Bombardier Service Bulletin 

84–54–14, Revision J, dated September 17, 

2010; for related information. 

Material Incorporated by Reference 

(o) You must use Bombardier Service 

Bulletin 84–54–14, Revision J, dated 

September 17, 2010, to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., Q–Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

e-mail thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

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Federal Register / Vol. 75, No. 214 / Friday, November 5, 2010 / Rules and Regulations 68177 

Issued in Renton, Washington, on October 

18, 2010. 

Michael J. Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–27611 Filed 11–4–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1040; Directorate 

Identifier 2010–NM–207–AD; Amendment 

39–16492; AD 2010–23–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 757 and 767 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD requires 

repetitive testing for correct functioning 

of the engine indication and crew 

alerting system (EICAS) to ensure that it 

receives both the LOW FUEL and FUEL 

CONFIG discrete signals from the fuel 

quantity processor unit, and alerts the 

flightcrew of a low fuel situation, and if 

the test fails, troubleshooting to find 

wire faults and damaged equipment, 

and corrective actions if necessary. This 

AD was prompted by a report that the 

EICAS failed to alert the flightcrew of an 

improper fuel system configuration 

during flight. Later in that flight, the 

EICAS failed to alert the flightcrew that 

the fuel in the left- and right-hand main 

tanks was depleted below the minimum 

of 2,200 pounds. We are issuing this AD 

to detect and correct a single latent 

failure of the FUEL CONFIG discrete 

signal, which disables both the FUEL 

CONFIG and LOW FUEL messages. 

Such failure, combined with a 

flightcrew error in configuring the fuel 

system, could lead to depletion of the 

fuel in the main tanks and possible 

flame out of both engines. A dual engine 

flame out could result in inaccessibility 

of the remaining fuel in the center tank 

due to loss of electrical power to the 

pumps, consequent unrecoverable dual 

engine shutdown, and forced landing of 

the airplane. 

DATES: This AD is effective November 

22, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of November 22, 2010. 

We must receive comments on this 

AD by December 20, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590, 

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

through Friday, except Federal holidays. 

For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; 

telephone 206–544–5000, extension 1, 

fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

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; 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 Office (phone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Tak 

Kobayashi, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6499; fax (425) 917–6590; 

e-mail: takahisa.kobayashi@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received a report from an operator 

of a Model 757–200 series airplane that 

the engine indication and crew alerting 

system (EICAS) failed to alert the 

flightcrew of an improper fuel system 

configuration during flight. Later in that 

flight, the EICAS failed to alert the 

flightcrew that the fuel in the left- and 

right-hand main tanks was depleted 

below the minimum of 2,200 pounds. 

The EICAS receives both the LOW FUEL 

and FUEL CONFIG discrete signals from 

the fuel quantity processor unit to 

display certain messages to alert the 

flightcrew. When the center fuel tank 

pump switches are off with more than 

200 pounds of fuel in the center tank the 

EICAS should display the FUEL 

CONFIG advisory message. When the 

fuel in either main tank is below 2,200 

pounds, the EICAS should display the 

LOW FUEL caution message. The EICAS 

design allows a single latent failure of 

the FUEL CONFIG discrete signal, 

which disables both the FUEL CONFIG 

and LOW FUEL messages. Such failure, 

combined with a flightcrew error in 

configuring the fuel system, could lead 

to depletion of the fuel in the main 

tanks and possible flame out of both 

engines. A dual engine flame out could 

result in inaccessibility of the remaining 

fuel in the center tank due to loss of 

electrical power to the pumps, 

consequent unrecoverable dual engine 

shutdown, and forced landing of the 

airplane. 

The fuel quantity indicating system 

(FQIS), EICAS, and large format display 

system (LFDS) installed on Model 757– 

200 series airplanes are similar to the 

systems installed on Model 767 

airplanes. Therefore, Model 767 

airplanes are also subject to the 

identified unsafe condition and are 

included in the applicability of this AD. 

Relevant Service Information 

We reviewed Boeing Special 

Attention Service Bulletins 757–28– 

0121, dated August 18, 2010; and 767– 

28–0106, dated August 25, 2010. The 

service information describes 

procedures for repetitive testing for 

correct functioning of the EICAS, and if 

the test fails, troubleshooting to find 

wire faults, bent connector pins, or 

damaged equipment. Boeing Special 

Attention Service Bulletin 757–28– 

0121, dated August 18, 2010, also 

specifies procedures for corrective 

actions if any wire fault or damaged 

equipment (including bent connector 

pins) is found. The corrective actions 

include repairing or replacing affected 

wires and damaged equipment 

(including bent connector pins). 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of these same 

type designs. 

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