21166 Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Proposed Rules 

TABLE 1.—EXCEPTIONS TO APPLICABILITY

Airplane model Configuration Airbus modifications installed in production 

A330, A340–200, –300 ...................................... With Modification 40161 (optional Type A door 

3).

50806, 50807, 55071, and 55072. 

A330, A340–200, –300 ...................................... Without Modification 40161 (Type 1 door 3) ... 50806 and 55071. 

A340–500 ........................................................... ........................................................................... Either 50806, 50807, and 55071, or 50806 

and 55071. 

A340–600 ........................................................... ........................................................................... 50806, 50808, 55071, and 55073. 

TABLE 2.—EXCEPTIONS TO APPLICABILITY

Airplane model Airbus Service Bulletins installed in service 

A330 ............................................ A330–25–3173, Revision 01, dated August 2, 2006; and A330–25–3301, dated March 24, 2006. 

A340–200, –300 .......................... A340–25–4191, Revision 01, dated August 2, 2006; and A340–25–4273, dated March 24, 2006. 

A340–500, –600 .......................... A340–25–5004, Revision 01, dated August 2, 2006; and A340–25–5110, dated March 24, 2006. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) states that 

several operators have reported nonautomatic deployment of slide rafts during 

ground operational testing. In all cases, the 

slide raft released correctly from the door but 

did not inflate automatically. Pulling the 

manual backup handle correctly inflated the 

slide raft. Investigation conducted by the 

slide raft manufacturer showed that nonautomatic deployments have two potential 

root causes: Non-opening of the lacing; and 

stiffness and stiction (static friction) on the 

painted inflatable material. This situation, if 

not corrected, could delay the evacuation of 

passengers in case of an emergency. A new 

design solution has been developed to ensure 

the automatic slide raft deployment, which 

consists of: continuous ‘‘speed lacing’’ cord 

and new soft covers with rounded grommets 

(this modification ensures that the lacing 

opens); and a new shorter firing cable, a new 

anchor block for the slide raft packboard and 

a new folding procedure (this modification 

ensures automatic deployment regardless of 

the inflatable paint condition). Both 

modifications together ensure the automatic 

deployment function. The MCAI requires 

accomplishment of the set of modifications. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) For slide raft P/Ns 7A1508–003/–005/ 

–007/–023/–025/–027/–029/–115; P/Ns 

7A1539–003/–004/–005/–006/–007/–008/ 

–023/–024/–025/–026/–027/–028/–029/–030/ 

–115/ –116; P/Ns 7A1510–003/–004/–005/–

006/–007/–008/–023/–024/–025/–026/–027/ 

–028/–029/ –030/–115/–116; and P/Ns 

4A3934–1/–2/–001/–002: No later than 36 

months after the effective date of this AD, 

modify the slide raft in accordance with the 

instructions given in Airbus Service Bulletin 

A330–25–3173, A340–25–4191, or A340–25–

5004, all Revision 01, all dated August 2, 

2006; as applicable; and modify the slide raft 

assembly of each door in accordance with the 

instructions given in Airbus Service Bulletin 

A330–25–3301, A340–25–4273, or A340–25–

5110, all dated March 24, 2006; as applicable. 

(2) For slide raft P/Ns 7A1508–033/–035/ 

–037/–119/–121; P/Ns 7A1539–033/–034/ 

–035/–036/–037/ 

–038/–119/–120/–121/–122; P/Ns 7A1510–

033/–034/–035/–036/–037/–038/ –119/–120/ 

–121/–122; and P/Ns 4A3934–5/–6/–7/–8: No 

later than 36 months after the effective date 

of this AD, modify the slide raft assembly of 

each door in accordance with the 

instructions given in Airbus Service Bulletin 

A330–25–3301, A340–25–4273, or A340–25–

5110, all dated March 24, 2006; as applicable. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(f) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, ATTN: Tim Backman, 

Aerospace Engineer, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Before using any AMOC approved 

in accordance with § 39.19 on any airplane 

to which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

(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, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(g) Refer to MCAI EASA Airworthiness 

Directive 2006–0354, dated November 28, 

2006; and the Airbus Service Bulletins 

specified in Table 3 of this AD for related 

information. 

TABLE 3.—AIRBUS SERVICE BULLETINS

Service Bulletin 

Revision 

level 

Date 

A330–25–3173 01 ........ August 2, 2006. 

A340–25–4191 01 ........ August 2, 2006. 

A340–25–5004 01 ........ August 2, 2006. 

A330–25–3301 Original March 24, 2006. 

A340–25–4273 Original March 24, 2006. 

A340–25–5110 Original March 24, 2006. 

Issued in Renton, Washington, on April 23, 

2007. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–8172 Filed 4–27–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28035; Directorate 

Identifier 2006–NM–293–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 767 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Boeing Model 767 airplanes. 

This proposed AD would require sealing 

certain fasteners and stiffeners in the 

fuel tank, and changing certain wire 

bundle clamp configurations on the fuel 


jlentini on PROD1PC65 with PROPOSAL
Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Proposed Rules 21167 

tank walls. This proposed AD results 

from fuel system reviews conducted by 

the manufacturer. We are proposing this 

AD to prevent possible ignition sources 

in the auxiliary fuel tank, main fuel 

tanks, and surge tanks caused by a 

wiring short or lightning strike, which 

could result in fuel tank explosions and 

consequent loss of the airplane. 

DATES: We must receive comments on 

this proposed AD by June 14, 2007. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

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

through Friday, except Federal holidays. 

Contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for the service 

information identified in this proposed 

AD. 

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: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include the docket 

number ‘‘FAA–2007–28035; Directorate 

Identifier 2006–NM–293–AD’’ at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. We will consider all 

comments received by the closing date 

and may amend the proposed AD in 

light of those comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 

Using the search function of that web 

site, anyone can find and read the 

comments in any of our dockets, 

including the name of the individual 

who sent the comment (or signed the 

comment on behalf of an association, 

business, labor union, etc.). You may 

review DOT’s complete Privacy Act 

Statement in the Federal Register 

published on April 11, 2000 (65 FR 

19477–78), or you may visit http:// 

dms.dot.gov. 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

Discussion 

The FAA has examined the 

underlying safety issues involved in fuel 

tank explosions on several large 

transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 

systems. As a result of those findings, 

we issued a regulation titled ‘‘Transport 

Airplane Fuel Tank System Design 

Review, Flammability Reduction and 

Maintenance and Inspection 

Requirements’’ (66 FR 23086, May 7, 

2001). In addition to new airworthiness 

standards for transport airplanes and 

new maintenance requirements, this 

rule included Special Federal Aviation 

Regulation No. 88 (‘‘SFAR 88,’’

Amendment 21–78, and subsequent 

Amendments 21–82 and 21–83). 

Among other actions, SFAR 88 

requires certain type design (i.e., type 

certificate (TC) and supplemental type 

certificate (STC)) holders to substantiate 

that their fuel tank systems can prevent 

ignition sources in the fuel tanks. This 

requirement applies to type design 

holders for large turbine-powered 

transport airplanes and for subsequent 

modifications to those airplanes. It 

requires them to perform design reviews 

and to develop design changes and 

maintenance procedures if their designs 

do not meet the new fuel tank safety 

standards. As explained in the preamble 

to the rule, we intended to adopt 

airworthiness directives to mandate any 

changes found necessary to address 

unsafe conditions identified as a result 

of these reviews. 

In evaluating these design reviews, we 

have established four criteria intended 

to define the unsafe conditions 

associated with fuel tank systems that 

require corrective actions. The 

percentage of operating time during 

which fuel tanks are exposed to 

flammable conditions is one of these 

criteria. The other three criteria address 

the failure types under evaluation: 

single failures, single failures in 

combination with a latent condition(s), 

and in-service failure experience. For all 

four criteria, the evaluations included 

consideration of previous actions taken 

that may mitigate the need for further 

action. 

We have determined that the actions 

identified in this AD are necessary to 

reduce the potential of ignition sources 

inside fuel tanks, which, in combination 

with flammable fuel vapors, could result 

in fuel tank explosions and consequent 

loss of the airplane. 

A safety assessment by Boeing 

identified a certain fastener type in the 

fuel tank walls that has an insufficient 

bond to the structure. These fasteners 

can be a path for electrical energy to 

enter the fuel tank if a wiring short 

occurs in a wire bundle installed along 

the fuel tank boundary structure, or if 

lightning strikes a wing surface. If 

energy from a wiring short or lightning 

strike goes through these fasteners, 

arcing can occur at the ends of the 

fasteners in the fuel tank. The ends of 

the fasteners in the fuel tank do not 

have sufficient electrical insulation to 

contain the energy from the arcs. This 

condition, if not corrected, could result 

in a potential ignition source inside a 

fuel tank. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 767–57A0100, dated 

August 21, 2006. The service bulletin 

describes procedures for sealing the 

ends of the fasteners on the brackets that 

hold the vortex generators, and, for 

certain airplanes, sealing the ends of 

fasteners on certain stiffeners on the rear 

spar. 

We have also reviewed Boeing Alert 

Service Bulletin 767–57A0102, dated 

October 25, 2006. The service bulletin 

describes procedures for changing the 

wire bundle clamp configurations at 

specified locations on the fuel tank 

walls, and sealing the fasteners and 

certain stiffeners at specified locations 

in the fuel tank. 

Accomplishing the actions specified 

in the service information is intended to 

adequately address the unsafe 

condition. 


jlentini on PROD1PC65 with PROPOSAL
21168 Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Proposed Rules 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to exist or 

develop on other airplanes of this same 

type design. For this reason, we are 

proposing this AD, which would require 

accomplishing the actions specified in 

the service information described 

previously. 

Costs of Compliance 

There are about 925 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD. There 

are no U.S.-registered airplanes in 

Group 3 of Service Bulletin 767–

57A0102. The average labor rate is $80 

per work hour. 

ESTIMATED COSTS

Service bulletin Group Work hours Parts Cost per 

airplane 

Number of 

U.S.- 

registered 

airplanes 

Fleet cost 

767–57A0100 ................................................................... 1 6 (1) $480 341 $163,680 

2 114 (1) 9,120 21 191,520 

767–57A0102 ................................................................... 1 246 $1,632 21,312 341 7,267,392 

2 874 1,304 71,224 21 1,495,704 

3 24 338 2,258 0 0 

(1) Minimal. 

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 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

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 proposed AD and placed it in the 

AD docket. See the ADDRESSES section 

for a location to examine the regulatory 

evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

Boeing: Docket No. FAA–2007–28035; 

Directorate Identifier 2006–NM–293–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by June 14, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model 767–200, 

–300, –300F, and –400ER series airplanes; 

certificated in any category; as identified in 

Boeing Alert Service Bulletin 767–57A0100, 

dated August 21, 2006; and Boeing Alert 

Service Bulletin 767–57A0102, dated October 

25, 2006. 

Unsafe Condition 

(d) This AD results from fuel system 

reviews conducted by the manufacturer. We 

are issuing this AD to prevent possible 

ignition sources in the auxiliary fuel tank, 

main fuel tanks, and surge tanks caused by 

a wiring short or lightning strike, which 

could result in fuel tank explosions and 

consequent loss 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. 

Fastener Sealant Application 

(f) For airplanes identified in Boeing Alert 

Service Bulletin 767–57A0100, dated August 

21, 2006: Within 60 months after the effective 

date of this AD, seal the ends of the fasteners 

on the brackets that hold the vortex 

generators, and seal the ends of the fasteners 

on certain stiffeners on the rear spar, as 

applicable. Do the actions in accordance with 

the Accomplishment Instructions of the 

service bulletin. 

Wire Bundle Sleeve and Clamp Installation 

and Fastener Sealant Application 

(g) For airplanes identified in Boeing Alert 

Service Bulletin 767–57A0102, dated October 

25, 2006: Within 60 months after the effective 

date of this AD, change the wire bundle 

clamp configurations at specified locations 

on the fuel tank walls, and seal the fasteners 

and certain stiffeners at specified locations 

on the fuel tank. Do the actions in accordance 

with the Accomplishment Instructions of the 

service bulletin. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 


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Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Proposed Rules 21169 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Issued in Renton, Washington, on April 17, 

2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–8175 Filed 4–27–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–24978; Directorate 

Identifier 2006–NM–108–AD] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Model 717–200 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: The FAA is revising an earlier 

proposed airworthiness directive (AD) 

for certain McDonnell Douglas Model 

717–200 airplanes. The original NPRM 

would have required modifying the fuel 

boost pump container of the center tank. 

The original NPRM resulted from fuel 

system reviews conducted by the 

manufacturer. This action revises the 

original NPRM by adding airplanes to 

the applicability. We are proposing this 

supplemental NPRM to prevent 

exposing the fuel pump container vapor 

area to electrical arcing during a fuel 

pump motor case or connector burn 

through, which could result in a fuel 

tank explosion. 

DATES: We must receive comments on 

this supplemental NPRM by May 25, 

2007. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

supplemental NPRM. 

• DOT Docket web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

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

through Friday, except Federal holidays. 

Contact Boeing Commercial 

Airplanes, Long Beach Division, 3855 

Lakewood Boulevard, Long Beach, 

California 90846, Attention: Data and 

Service Management, Dept. C1 L5A 

(D800–0024), for service information 

identified in this proposed AD. 

FOR FURTHER INFORMATION CONTACT: 

William Bond, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, 

Los Angeles Aircraft Certification 

Office, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

telephone (562) 627–5253; fax (562) 

627–5210. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this supplemental NPRM. 

Send your comments to an address 

listed in the ADDRESSES section. Include 

the docket number ‘‘Docket No. FAA 

2006–24978; Directorate Identifier 

2006–NM–108–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this supplemental NPRM. We 

will consider all comments received by 

the closing date and may amend this 

supplemental NPRM in light of those 

comments. 

We will post all comments submitted, 

without change, to http://dms.dot.gov, 

including any personal information you 

provide. We will also post a report 

summarizing each substantive verbal 

contact with FAA personnel concerning 

this supplemental NPRM. Using the 

search function of that web site, anyone 

can find and read the comments in any 

of our dockets, including the name of 

the individual who sent the comment 

(or signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78), or you may visit 

http://dms.dot.gov. 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level in the Nassif Building at the DOT 

street address stated in ADDRESSES. 

Comments will be available in the AD 

docket shortly after the Docket 

Management System receives them. 

Discussion 

We proposed to amend 14 CFR part 

39 with a notice of proposed rulemaking 

(NPRM) for an AD (the ‘‘original 

NPRM’’) for certain McDonnell Douglas 

Model 717–200 airplanes. The original 

NPRM was published in the Federal 

Register on June 8, 2006 (71 FR 33262). 

The original NPRM proposed to require 

modifying the fuel boost pump 

container of the center tank. 

Comments 

We have considered the following 

comments on the original NPRM. 

Support for the NPRM 

AirTran Airways supports the 

proposed actions specified in the 

NPRM. 

Request To Refer to Latest Revision of 

Service Bulletin 

AirTran Airways and Boeing request 

that we reference Boeing Service 

Bulletin 717–28–0013, Revision 1, dated 

April 7, 2006, in the NPRM (we referred 

to Boeing Service Bulletin 717–28–0013, 

dated July 28, 2004, as the appropriate 

source of service information for doing 

the actions specified in the NPRM). 

AirTran Airways also requests that we 

give credit for actions done in 

accordance with the original issue. 

Boeing commented that there was 

additional work required by Revision 1, 

but in a subsequent comment Boeing 

states that this was in error and that no 

additional work was needed. Boeing 

also notes that Revision 2 of the service 

bulletin is being drafted. 

We agree to revise this AD to refer to 

the latest revision of the service bulletin 

as the appropriate source of service 

information. We have reviewed Boeing 

Service Bulletin 717–28–0013, Revision 

1, dated April 7, 2006; and Boeing 

Service Bulletin 717–28–0013, Revision 

2, dated September 13, 2006. The 

service bulletins contain essentially the 

same actions as described in the original 

issue of the service bulletin. 

However, Revision 1 of the service 

bulletin adds new airplanes to the 

effectivity (fuselages number 5136 

through 5146), clarifies the 

configuration table, and clarifies the 

installation of the hat and cover 

assembles. Revision 2 of the service 

bulletin revises the parts pricing and 

clarifies the notes in the figures. We 

have revised this AD to refer to Revision 

2 of the service bulletin. 


jlentini on PROD1PC65 with PROPOSAL