30752 Federal Register / Vol. 73, No. 104 / Thursday, May 29, 2008 / Rules and Regulations 

TABLE 2.—DRAWINGS INCLUDED IN FOKKER SERVICE BULLETIN SBF100–22–050—Continued 

Fokker drawing Sheet Issue Date 

W41504 ..................................................................... 011 J ............................................................................... April 25, 2006. 

W41504 ..................................................................... 012 L ............................................................................... April 25, 2006. 

W41504 ..................................................................... 013 L ............................................................................... April 25, 2006. 

W46140 ..................................................................... 27 AR ............................................................................ March 5, 2002. 

W46140 ..................................................................... 28 AR ............................................................................ March 8, 2002. 

W46143 ..................................................................... 02 K ............................................................................... February 26, 2002. 

W46143 ..................................................................... 03 K ............................................................................... March 7, 2002. 

W46144 ..................................................................... 06 R ............................................................................... March 4, 2002. 

W46144 ..................................................................... 07 S ............................................................................... March 7, 2002. 

W46912 ..................................................................... 01 D ............................................................................... March 12, 2002. 

W46930 ..................................................................... 01 Original ..................................................................... March 14, 2002. 

W46930 ..................................................................... 02 E ............................................................................... March 14, 2002. 

W46932 ..................................................................... 01 D ............................................................................... March 13, 2002. 

W59140 ..................................................................... 177 GC ............................................................................ February 8, 2006. 

W59140 ..................................................................... 178 GB ............................................................................ February 6, 2006. 

W59140 ..................................................................... 221 GB ............................................................................ February 6, 2006. 

(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 Fokker Services B.V., 

Technical Services Dept., P.O. Box 231, 2150 

AE Nieuw-Vennep, the Netherlands. 

(3) You may review copies at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or 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 Renton, Washington, on May 14, 

2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–11501 Filed 5–28–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0544; Directorate 

Identifier 2008–NM–099–AD; Amendment 

39–15535; AD 2008–10–51] 

RIN 2120–AA64 

Airworthiness Directives; Dornier 

Model 328–100 and –300 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: This document publishes in 

the Federal Register an amendment 

adopting airworthiness directive (AD) 

2008–10–51 that was sent previously to 

all known U.S. owners and operators of 

all Dornier Model 328–100 and –300 

airplanes by individual notices. This AD 

requires detailed visual and eddy 

current inspections of both the left-hand 

and right-hand lower wing panel of the 

rear trailing edge (inboard and outboard 

of flap lever arm 1 (rib 3 and rib 5)) for 

cracks, and repair if necessary. This AD 

is prompted by cracks found in the 

lower wing panel of the rear trailing 

edge (inboard and outboard of flap lever 

arm 1 (rib 5)) during a routine 

inspection on a Model 328–100 

airplane. Subsequent inspection of the 

other Model 328–100 airplanes in the 

same fleet revealed several more 

airplanes with cracks at the same 

location. We are issuing this AD to 

prevent structural failure of the affected 

wing panel, possible separation of the 

wing from the airplane, and consequent 

loss of control of the airplane. 

DATES: This AD becomes effective June 

3, 2008 to all persons except those 

persons to whom it was made 

immediately effective by emergency AD 

2008–10–51, issued May 8, 2008, which 

contained the requirements of this 

amendment. 

The incorporation by reference of 

certain publications listed in the AD is 

approved by the Director of the Federal 

Register as of June 3, 2008. 

We must receive comments on this 

AD by July 28, 2008. 

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 328 Support Services 

GmbH, P.O. Box 1252, D–82231 

Wessling, Federal Republic of Germany. 

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 (telephone 800–647–

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Mike Borfitz, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2677; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: On May 8, 

2008, we issued emergency AD 2008–

10–51, which applies to all Dornier 

Model 328–100 and –300 airplanes. 

Background 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, notified the FAA that an 

unsafe condition may exist on all 

Dornier Model 328–100 and –300 

airplanes. The EASA advises that, 

during a routine inspection, cracks were 

found in the lower wing panel of the 


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Federal Register / Vol. 73, No. 104 / Thursday, May 29, 2008 / Rules and Regulations 30753 

rear trailing edge (inboard and outboard 

of flap lever arm 1 (rib 5)) on a Model 

328–100 airplane. Subsequent 

inspection of the other Model 328–100 

airplanes in the same fleet revealed 

several more airplanes with cracks at 

the same location. The cause of the 

cracking is unknown. This condition, if 

not corrected, could result in structural 

failure of the affected wing panel, 

possible separation of the wing from the 

airplane, and consequent loss of control 

of the airplane. 

Relevant Service Information 

328 Support Services GmbH has 

issued Dornier Alert Service Bulletins 

ASB–328J–57–015 (for Model 328–300 

airplanes), and ASB–328–57–037 (for 

Model 328–100 airplanes), both 

Revision 1, both dated May 8, 2008. The 

service bulletins describe procedures for 

detailed visual and eddy current 

inspections of both the left-hand (LH) 

and right-hand (RH) lower wing panel of 

the rear trailing edge (inboard and 

outboard of flap lever arm 1 (rib 3 and 

rib 5)) for cracks. The EASA mandated 

the service bulletins and issued EASA 

emergency airworthiness directive 

2008–0087–E, dated May 8, 2008, to 

ensure the continued airworthiness of 

these airplanes in Europe. 

FAA’s Determination and Requirements 

of This AD 

These airplane models are 

manufactured in Europe and are type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Pursuant to this bilateral 

airworthiness agreement, the EASA has 

kept the FAA informed of the situation 

described above. We have examined the 

EASA’s findings, evaluated all pertinent 

information, and determined that we 

need to issue an AD for products of this 

type design that are certificated for 

operation in the United States. 

Since the unsafe condition described 

is likely to exist or develop on other 

airplanes of the same type design, we 

issued emergency AD 2008–10–51 to 

prevent structural failure of the affected 

wing panel, possible separation of the 

wing from the airplane, and consequent 

loss of control of the airplane. The AD 

requires accomplishing the actions 

specified in the service information 

previously described, except as 

described in ‘‘Differences Between This 

AD and Service Information.’’ This AD 

also requires you to report the 

inspection results to 328 Support 

Services GmbH. 

We found that immediate corrective 

action was required; therefore, notice 

and opportunity for prior public 

comment thereon were impracticable 

and contrary to the public interest, and 

good cause existed to make the AD 

effective immediately by individual 

notices issued on May 8, 2008, to all 

known U.S. owners and operators of all 

Dornier Model 328–100 and –300 

airplanes. These conditions still exist, 

and the AD is hereby published in the 

Federal Register as an amendment to 

section 39.13 of the Federal Aviation 

Regulations (14 CFR 39.13) to make it 

effective to all persons. 

Differences Between This AD and 

Service Information 

The service bulletins specify to 

contact the manufacturer for 

instructions on how to repair cracks, but 

this AD requires repairing the cracks 

using a method approved by the FAA or 

the EASA (or its delegated agent). In 

light of the type of repair that is 

required to address the unsafe 

condition, and consistent with existing 

bilateral airworthiness agreements, we 

have determined that, for this AD, a 

repair approved by the FAA or the 

EASA (or its delegated agent) is 

acceptable for compliance with this AD. 

Unlike the procedures described in 

the service bulletins that specify a onetime eddy current inspection, this AD 

requires the eddy current inspection to 

be repeated at intervals not to exceed 

400 flight hours. Doing the eddy current 

inspections terminates the detailed 

visual inspections required by this AD. 

We have determined that, because of the 

safety implications and consequences 

associated with the cracking, the eddy 

current inspection of the affected area 

must be repeated. This difference has 

been coordinated with the EASA. 

Interim Action 

This AD requires that operators report 

the results of the inspections to 328 

Support Services GmbH. Because the 

cause of the cracking is not known, 

these required inspection reports will 

help determine the extent of the 

cracking in the affected fleet. Based on 

the results of these reports, we may 

determine that further corrective action 

is warranted. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA–

2008–0544; Directorate Identifier 2008–

NM–099–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 have 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. 

The FAA has determined that this 

regulation is an emergency regulation 

that must be issued immediately to 

correct an unsafe condition in aircraft, 

and that it is not a ‘‘significant 

regulatory action’’ under Executive 

Order 12866. It has been determined 

further that this action involves an 

emergency regulation under DOT 

Regulatory Policies and Procedures (44 

FR 11034, February 26, 1979). If this 

emergency regulation is later deemed 

significant under DOT Regulatory 

Policies and Procedures, we will 

prepare a final regulatory evaluation 


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30754 Federal Register / Vol. 73, No. 104 / Thursday, May 29, 2008 / Rules and Regulations 

and place it in the AD Docket. See the 

ADDRESSES section for a location to 

examine the regulatory evaluation, if 

filed. 

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): 

2008–10–51 328 Support Services GmbH 

(Formerly Avcraft Aerospace GmbH): 

Amendment 39–15535. Docket No. 

FAA–2008–0544; Directorate Identifier 

2008–NM–099–AD. 

Effective Date 

(a) This AD becomes effective June 3, 2008, 

to all persons except those persons to whom 

it was made immediately effective by 

emergency AD 2008–10–51, issued on May 8, 

2008, which contained the requirements of 

this amendment. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies all Dornier Model 328–

100 and –300 airplanes, certificated in any 

category. 

Unsafe Condition 

(d) This AD results from a report indicating 

that, during a routine inspection, cracks were 

found in the lower wing panel of the rear 

trailing edge (inboard and outboard of flap 

lever arm 1 (rib 5)) on a Model 328–100 

airplane. Subsequent inspection of the other 

Model 328–100 airplanes in the same fleet 

revealed several more airplanes with cracks 

at the same location. We are issuing this AD 

to prevent structural failure of the affected 

wing panel, possible separation of the wing 

from the airplane, and consequent loss of 

control of the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Repetitive Detailed Visual Inspections for 

Cracks 

(f) Within 10 flight cycles, or 10 flight 

hours, or 7 days, whichever occurs first, after 

the effective date of this AD: Accomplish a 

detailed visual inspection of both the lefthand (LH) and right-hand (RH) lower wing 

panel inboard and outboard of flap lever arm 

1 (rib 5) for cracks, in accordance with the 

Accomplishment Instructions of Dornier 

Alert Service Bulletin ASB–328J–57–015, or 

ASB–328–57–037, both Revision 1, both 

dated May 8, 2008, as applicable. If no crack 

is detected, repeat the detailed visual 

inspection thereafter at intervals not to 

exceed 50 flight hours until the eddy current 

inspection required by paragraph (g) of this 

AD is accomplished. If any crack is detected, 

before further flight, do an eddy current 

inspection in accordance with paragraph (g) 

of this AD. 

Repetitive Eddy Current Inspections for 

Cracks 

(g) Within 400 flight hours or 3 months 

after the effective date of this AD, whichever 

occurs first: Accomplish an eddy current 

inspection of both the LH and RH lower wing 

panel in the vicinity of rib 3 and inboard and 

outboard of flap lever arm 1 (rib 5) for cracks, 

in accordance with the Accomplishment 

Instructions of Dornier Alert Service Bulletin 

ASB–328J–57–015, or ASB–328–57–037, 

both Revision 1, both dated May 8, 2008, as 

applicable. Repeat the eddy current 

inspection thereafter at intervals not to 

exceed 400 flight hours. Accomplishment of 

the eddy current inspection terminates the 

detailed visual inspection required by 

paragraph (f) of this AD. 

Repair 

(h) If any crack is detected during any 

inspection required by this AD: Before 

further flight, repair the crack using a method 

approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (or its delegated 

agent). 

Credit for Previously Accomplished Actions 

(i) Accomplishment of the actions required 

by paragraph (f) or (g) of this AD before the 

effective date of this AD in accordance with 

Dornier Alert Service Bulletin ASB–328J–57–

015 or ASB–328–57–037, both dated May 5, 

2008, as applicable, is considered acceptable 

for compliance with the corresponding initial 

inspection requirements specified in 

paragraph (f) or (g) of this AD. 

Report 

(j) At the applicable time specified in 

paragraph (j)(1) or (j)(2) of this AD: Send 328 

Support Services GmbH a report of findings 

(both positive and negative) found during 

each inspection required by paragraphs (f) 

and (g) of this AD. The report must include 

the inspection results, a description of any 

cracks found, the airplane serial number, and 

the number of landings and flight hours on 

the airplane. Send the report to 328 Support 

Services GmbH, Global Support Center, P.O. 

Box 1252, D–82231 Wessling, Federal 

Republic of Germany; Telephone +49 8153 

88111 6666; fax 49 8153 88111 6565; E-mail: 

gsc.op@328support.de. 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 contained in this AD 

and has assigned OMB Control Number 

2120–0056. 

(1) For any inspection done after the 

effective date of this AD: Within 3 days after 

the inspection. 

(2) For any inspection done before the 

effective date of this AD: Within 3 days after 

the effective date of this AD. 

Special Flight Permits 

(k) Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the requirements of this AD 

can be done if the following conditions are 

met: 

(1) The initial inspection required by 

paragraph (f) of this AD must be 

accomplished. 

(2) If a crack indication exceeds 12.5 mm 

(0.49 inch), the Manager, International 

Branch, ANM–116, concurs with issuance of 

the special flight permits. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

Related Information 

(m) European Aviation Safety Agency 

emergency airworthiness directive 2008–

0087–E, dated May 8, 2008, also addresses 

the subject of this AD. 

Material Incorporated by Reference 

(n) You must use Dornier Alert Service 

Bulletin ASB–328J–57–015, Revision 1, dated 

May 8, 2008; or Dornier Alert Service 

Bulletin ASB–328–57–037, Revision 1, dated 

May 8, 2008; as applicable; to perform the 

actions that are required by this AD, unless 

the AD specifies otherwise. (Only the oddnumbered pages of the documents contain 

the document revision level and issue date; 

the even-numbered pages do not contain this 

information.) The Director of the Federal 

Register approved the incorporation by 

reference of these documents in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. To 

get copies of the service information, contact 

328 Support Services GmbH, P.O. Box 1252, 

D–82231 Wessling, Germany. You may 

review copies at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; or 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/ibr-locations.html. 


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Federal Register / Vol. 73, No. 104 / Thursday, May 29, 2008 / Rules and Regulations 30755 

Issued in Renton, Washington, on May 14, 

2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–11468 Filed 5–28–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28598; Directorate 

Identifier 2007–NM–036–AD; Amendment 

39–15529; AD 2008–11–07] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 757 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Boeing Model 757 airplanes. This AD 

requires installation of an automatic 

shutoff system for the center tank fuel 

boost pumps, and installation of a 

placard in the airplane flight deck if 

necessary. This AD also requires 

revisions to the Limitations and Normal 

Procedures sections of the airplane 

flight manual to advise the flightcrew of 

certain operating restrictions for 

airplanes equipped with an automated 

center tank fuel pump shutoff control. 

This AD also requires a revision to the 

Airworthiness Limitations (AWLs) 

section of the Instructions for Continued 

Airworthiness to incorporate AWLs No. 

28–AWL–20 and No. 28–AWL–26. This 

AD also requires replacement of the fuel 

control panel assembly with a modified 

part, installation of two secondary 

pump control relays for the center tank 

fuel pumps, other specified actions, and 

concurrent modification of the fuel 

control panel assembly. This AD results 

from fuel system reviews conducted by 

the manufacturer. We are issuing this 

AD to prevent center tank fuel pump 

operation with continuous low pressure, 

which could lead to friction sparks or 

overheating in the fuel pump inlet that 

could create a potential ignition source 

inside the center fuel tank; these 

conditions, in combination with 

flammable fuel vapors, could result in a 

center fuel tank explosion and 

consequent loss of the airplane. 

DATES: This AD is effective July 3, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 3, 2008. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 

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 address for the 

Docket Office (telephone 800–647–5527) 

is the Document 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: Judy 

Coyle, Aerospace Engineer, Propulsion 

Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6497; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to all 

Boeing Model 757–200, –200CB, 

–200PF, and –300 series airplanes. That 

NPRM was published in the Federal 

Register on July 9, 2007 (72 FR 37132). 

That NPRM proposed to require 

installation of an automatic shutoff 

system for the center tank fuel boost 

pumps, and installation of a placard in 

the airplane flight deck if necessary. 

That NPRM also proposed to require 

revisions to the Limitations and Normal 

Procedures sections of the airplane 

flight manual to advise the flightcrew of 

certain operating restrictions for 

airplanes equipped with an automated 

center tank fuel pump shutoff control. 

That NPRM also proposed to require a 

revision to the Airworthiness 

Limitations (AWLs) section of the 

Instructions for Continued 

Airworthiness (ICA) to incorporate 

AWLs No. 28–AWL–20 and No. 28–

AWL–26. That NPRM also proposed to 

require replacement of the fuel control 

panel assembly with a modified part, 

installation of two secondary pump 

control relays for the center tank fuel 

pumps, other specified actions, and 

concurrent modification of the fuel 

control panel assembly. 

Actions Since NPRM Was Issued 

On April 29, 2008, we issued AD 

2008–10–11, amendment 39–15517, that 

applies to all Model 757 airplanes. AD 

2008–10–11, among other actions, 

requires revising the AWLs section of 

the ICA by incorporating AWLs No. 28–

AWL–01 through No. 28–AWL–24 of 

Section 9 of the Boeing 757 

Maintenance Planning Document (MPD) 

Document D622N001–9, Revision 

March 2008. AD 2008–10–11 also 

provides the optional action of 

incorporating AWL No. 28–AWL–26. 

This AD, however, requires the 

incorporation of AWLs No. 28–AWL–20 

and No. 28–AWL–26 in accordance with 

paragraphs (j) and (m) of this AD, 

respectively. Therefore, we have added 

a new paragraph (q) to this AD 

specifying that incorporating AWLs No. 

28–AWL–20 and No. 28–AWL–26 into 

the AWLs section of the ICA in 

accordance with paragraph (g)(3) of AD 

2008–10–11 terminates the 

corresponding actions required by this 

AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received from 

the four commenters. 

Request To Revise the Unsafe Condition 

Boeing requests that we clarify the 

unsafe condition in the summary and in 

paragraph (d) of the NPRM. Boeing 

states that the unsafe condition exists 

when continuous low pressure is 

indicated during pump operation with 

no fuel available to cover the pump 

inlet, and that it does not exist when 

there is fuel available to cover the pump 

inlet during pump operation. Boeing 

suggests using the following statement: 

We are issuing this AD to prevent center 

tank fuel pump operation with continuous 

low pressure (with no fuel passing through 

the pump), which could lead to friction 

sparks or overheating in the fuel pump inlet 

that could create a potential ignition source 

inside the center fuel tank. These conditions, 

in combination with flammable fuel vapors, 

could result in a center fuel tank explosion 

and consequent loss of the airplane. 

We agree that the unsafe condition is 

present only when there is no fuel 

available to cover the pump inlet. When 

fuel is not covering the pump inlet, the 

‘‘continuous low pressure’’ indication 

will be present. Therefore, we have not 

added the phrase ‘‘with no fuel passing 

through the pump’’ to this AD in this 

regard, since the continuous low 

pressure indication is integral to 

describing the unsafe condition. We 

have, however, revised the summary 

and paragraph (d) of this AD by 


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