Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Proposed Rules 54671 

(A) Within 750 flight cycles since the last 

surface HFEC inspection required by 

paragraph (g) of this AD. 

(B) Within 250 flight cycles after the 

effective date of this AD. 

Optional Repair/Modification 

(h) For airplanes on which the inspection 

required by paragraph (g) of this AD is done 

per Part 1 of the Work Instructions of Boeing 

Alert Service Bulletin 747–53A2439, dated 

July 5, 2001, or Revision 1, dated March 10, 

2005; and on which no cracking is found: 

Accomplishment of the actions specified in 

either paragraph (h)(1) or (h)(2) of this AD 

extends the threshold for the initiation of the 

repetitive inspections required by paragraph 

(g)(2) of this AD. For airplanes on which the 

inspection required by paragraph (g) of this 

AD is done per Part 2 of the Work 

Instructions of Boeing Alert Service Bulletin 

747–53A2439, dated July 5, 2001, or Revision 

1, dated March 10, 2005; and on which no 

cracking is found: Accomplishment of the 

actions specified in paragraph (h)(1) of this 

AD extends the threshold for the initiation of 

the repetitive inspections required by 

paragraph (g)(2) of this AD. 

(1) Do the applicable repair per Part 3 of 

the Work Instructions of the service bulletin. 

At the applicable time specified in Table 1 

of Part 3 of the Work Instructions of the 

service bulletin, do the applicable inspection 

of the repaired area per Part 1 of the Work 

Instructions of the service bulletin. Repeat 

the inspection thereafter within the 

applicable interval per Figure 1 of the service 

bulletin. As of the effective date of this AD, 

the actions must be done per Parts 1, 3, and 

6 of the Work Instructions of Boeing Alert 

Service Bulletin 747–53A2439, Revision 1, 

dated March 10, 2005, as applicable, and 

repeat the applicable inspection thereafter at 

intervals not to exceed 3,000 flight cycles. 

(2) Do the modification of the attachment 

hole of the floor panel per Figure 5 of the 

service bulletin. Within 10,000 flight cycles 

after accomplishment of the modification, do 

the inspection of the modified area per Part 

1 of the Work Instructions of the service 

bulletin. Repeat the inspection thereafter 

within the applicable interval per Figure 1 of 

the service bulletin. As of the effective date 

of this AD, the actions must be done per 

Figure 5 and Part 1 of the Work Instructions 

of Boeing Alert Service Bulletin 747–

53A2439, Revision 1, dated March 10, 2005, 

and repeat the inspection thereafter at 

intervals not to exceed 3,000 flight cycles. 

Determining the Number of Flight Cycles for 

Compliance Time 

(i) For the purposes of calculating the 

compliance threshold and repetitive intervals 

for actions required by paragraphs (f), (g), or 

(h) of this AD: As of the effective date of this 

AD, all flight cycles, including the number of 

flight cycles in which cabin differential 

pressure is at 2.0 pounds per square inch 

(psi) or less, must be counted when 

determining the number of flight cycles that 

have occurred on the airplane. 

No Reporting Requirement 

(j) Although the service bulletin referenced 

in this AD specifies to submit certain 

information to the manufacturer, this AD 

does not include that requirement. 

Alternative Methods of Compliance (AMOCs) 

(k)(1) The Manager, Seattle Aircraft 

Certification Office (SACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(2) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Delegation Option Authorization 

Organization who has been authorized by the 

Manager, Seattle ACO, to make those 

findings. For a repair method to be approved, 

the repair must meet the certification basis of 

the airplane, and the approval must 

specifically refer to this AD. 

(3) AMOCs approved previously according 

to AD 2004–03–11 are approved as AMOCs 

for the corresponding provisions of 

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

Issued in Renton, Washington, on 

September 7, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–18403 Filed 9–15–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22427; Directorate 

Identifier 2004–NM–263–AD] 

RIN 2120–AA64 

Airworthiness Directives; British 

Aerospace Model BAC 1–11 200 and 

400 Series 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 all 

British Aerospace Model BAC 1–11 200 

and 400 series airplanes. This proposed 

AD would require revising the airplane 

flight manual (AFM) to contain 

applicable AFM amendments, which 

advise the flightcrew of information 

pertaining to safely operating the fuel 

system. The proposed AD would also 

require revising the FAA-approved 

maintenance program to include certain 

repetitive maintenance tasks intended to 

improve the safety of the fuel system. 

This proposed AD results from fuel 

system reviews conducted by the 

manufacturer. We are proposing this AD 

to prevent potential ignition sources 

inside the fuel system, which, in 

combination with flammable fuel 

vapors, could result in a fuel tank 

explosion and consequent loss of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by October 17, 2005. 

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 British Aerospace, Service 

Support, Airbus Limited, P.O. Box 77, 

Bristol BS99 7AR, England, for service 

information identified in this proposed 

AD. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1175; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Include the 

docket number ‘‘Docket No. FAA–2005–

22427; Directorate Identifier 2004–NM–

263–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 our docket 

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 

54672 Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Proposed Rules 

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 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 

recent 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’’ (67 FR 23085, 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 another 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. 

The Joint Aviation Authorities (JAA) 

has issued a regulation that is similar to 

SFAR 88. (The JAA is an associated 

body of the European Civil Aviation 

Conference (ECAC) representing the 

civil aviation regulatory authorities of a 

number of European States who have 

agreed to co-operate in developing and 

implementing common safety regulatory 

standards and procedures.) Under this 

regulation, the JAA stated that all 

members of the ECAC that hold type 

certificates for transport category 

airplanes are required to conduct a 

design review against explosion risks. 

We have determined that the actions 

identified in this proposed 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. 

The Civil Aviation Authority (CAA), 

which is the airworthiness authority for 

the United Kingdom, notified us that an 

unsafe condition may exist on all British 

Aerospace Model BAC 1–11 200 and 

400 series airplanes. The CAA advises 

that specific changes to operating 

procedures are necessary to ensure that 

the flightcrew is aware of appropriate 

procedures for addressing tripped 

circuit breakers or dry fuel tanks. 

Failure to follow appropriate procedures 

could introduce a possible ignition 

source into the fuel system. The CAA 

also advises that changes to the 

maintenance program are needed to 

prevent the possibility of ignition 

sources inside the fuel system. An 

ignition source inside the fuel system, 

in combination with flammable fuel 

vapors, could result in a fuel tank 

explosion and consequent loss of the 

airplane. 

Relevant Service Information 

The manufacturer has issued Airbus 

UK BAC One-Eleven Alert Service 

Bulletin 28–A–PM6057, Issue 1, dated 

May 10, 2004. The service bulletin 

describes procedures for revising the 

airplane flight manual (AFM) to contain 

applicable AFM amendments, which 

advise the flightcrew of information 

pertaining to the safety of the fuel 

system. Among other items, the AFM 

amendments advise the flightcrew of the 

following: 

• Normal procedures for checking the 

proper operation of fuel system 

elements. 

• Limitations on resetting tripped 

circuit breakers for electrical circuits for 

the fuel system, or restarting a fuel boost 

pump or transfer pump after a failure 

indication. 

• Procedures for removing power 

from affected components in the event 

of an indication of an electrical fault in 

the fuel system. 

• Procedures for operating the fuel 

pumps in a low-fuel or dry condition. 

The service bulletin also contains 

procedures for revising the FAAapproved maintenance program to 

include certain maintenance tasks 

intended to improve the safety of the 

fuel system. Among other items, the 

maintenance tasks include: 

• Visually inspecting the outlets of 

the fuel drain system for fuel leakage, 

and locating and correcting any leak. 

• Performing a functional test of the 

temperature indicating system of the 

cold air unit, or performing an integrity 

test of the ducting of the air 

conditioning bay. 

• Inspecting the drain pipes, drip 

trays, drip shields, and connectors of 

the fuel drain system for damage or 

corrosion, and for minimum clearance 

between drain pipes and adjacent 

structure. 

• Inspecting the fuel system drains 

for correct positioning and freedom 

from obstruction. 

• Pressure testing the wiring conduits 

for the booster pump in the wing tanks 

and for the transfer pump in the center 

tank. 

• Inspecting the cables, components, 

and ducting of the wing leading edge for 

secure mounting and connection, and 

for discrepancies including chafing, 

damage, corrosion, evidence of leakage, 

and obstruction, as applicable. 

• For certain airplanes, inspecting the 

anti-ice ducts of the wing leading edge 

for damage between ribs 4 and 5. 

• Inspecting the ducting in the air 

conditioning bay for secure duct 

connections. 

Table 1 of the service bulletin refers 

to specific chapters of the airplane 

maintenance manual (AMM) for 

applicable procedures for performing 

most of these inspections and tests. 

However, the service bulletin refers to 

British Aerospace Alert Service Bulletin 

30–A–PM5149, dated May 30, 1973; as 

the applicable source of service 

information for inspecting the anti-ice 

ducts of the wing leading edge for 

damage between ribs 4 and 5. British 

Aerospace Alert Service Bulletin 30–A–

Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Proposed Rules 54673 

PM5149 describes a visual or 

radiographic inspection for damage of 

the anti-ice ducts, and corrective 

actions, consisting of repairing or 

replacing the duct, if necessary. 

Table 1 specifies normal repetitive 

intervals ranging from 100 hours to 4800 

hours, depending on the task. For 

airplanes subject to a ‘‘corporate 

schedule,’’ Table 1 specifies repetitive 

intervals ranging from every month to 

every 4 years, depending on the task. 

Accomplishing the actions specified 

in the service information is intended to 

adequately address the unsafe 

condition. The CAA mandated the 

service information and issued British 

airworthiness directive G–2004–0012, 

dated June 21, 2004, to ensure the 

continued airworthiness of these 

airplanes in the United Kingdom. 

FAA’s Determination and Requirements 

of the Proposed AD 

These airplane models are 

manufactured in the United Kingdom 

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 CAA has 

kept the FAA informed of the situation 

described above. We have examined the 

CAA’s findings, evaluated all pertinent 

information, and determined that we 

need to issue an AD for airplanes of this 

type design that are certificated for 

operation in the United States. 

Therefore, we are proposing this AD, 

which would require accomplishing the 

actions specified in the service 

information described previously, 

except as discussed under ‘‘Clarification 

of Proposed AD and Maintenance 

Manual Temporary Revisions.’’

Differences Between the Proposed AD 

and British Airworthiness Directive 

British airworthiness directive G–

2004–0012 mandates changes to the 

master minimum equipment list 

(MMEL). This (FAA) AD will not 

mandate those MMEL changes because 

the limits imposed by the FAAapproved MMEL meet or exceed those 

mandated by the British airworthiness 

directive. We have coordinated this 

issue with the CAA. 

Clarification of Proposed AD and 

Maintenance Manual Temporary 

Revisions (TRs) 

In addition to the AFM amendments 

described previously, Table 2 of British 

Aerospace Alert Service Bulletin 28–A–

PM6057 also lists numerous TRs to the 

airplane maintenance manual. We have 

determined that these TRs were 

included in the service bulletin to 

provide operators with a summary of all 

measures taken to address current 

practices for fuel system safety. These 

TRs were not intended to address any 

identified unsafe condition. Therefore, 

this proposed AD would not require any 

action relative to these TRs. We have 

coordinated this issue with the CAA 

and our decision not to mandate the TRs 

to the maintenance manual is consistent 

with the CAA’s action in British 

airworthiness directive G–2004–0012. 

Clarification of Terminology 

Where Table 1 of British Aerospace 

Alert Service Bulletin 28–A–PM6057 

specifies a repetitive interval in 

‘‘hours,’’ for the purposes of this AD, 

this means ‘‘flight hours.’’

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD. 

ESTIMATED COSTS

Action Work 

hours 

Average 

labor rate 

per hour 

Cost per 

airplane 

Number of 

U.S.-registered airplanes Fleet 

cost 

AFM Revision ....................................................................................................... 1 $65 $65 11 $715 

Maintenance Program Revision ........................................................................... 1 65 65 11 715 

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. 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 

54674 Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Proposed Rules 

by adding the following new 

airworthiness directive (AD): 

British Aerospace Airbus Limited: Docket 

No. FAA–2005–22427; Directorate 

Identifier 2004–NM–263–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by October 17, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all British Aerospace 

Model BAC 1–11 200 and 400 series 

airplanes, certificated in any category. 

Unsafe Condition 

(d) This AD results from fuel system 

reviews conducted by the manufacturer. We 

are issuing this AD to ensure that the 

flightcrew and maintenance personnel are 

advised of procedures pertaining to the safety 

of the fuel system. These procedures are 

needed to prevent potential ignition sources 

inside the fuel system, which, in 

combination with flammable fuel vapors, 

could result in a fuel tank explosion 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. 

Airplane Flight Manual and Maintenance 

Program Revisions 

(f) Within 3 months after the effective date 

of this AD, do the actions specified in 

paragraphs (f)(1) and (f)(2) of this AD to 

improve the safety of the fuel system, in 

accordance with the Accomplishment 

Instructions of Airbus UK BAC One-Eleven 

Alert Service Bulletin 28–A–PM6057, Issue 

1, dated May 10, 2004. 

(1) Revise the airplane flight manual to 

include the applicable amendments advising 

the flightcrew of appropriate procedures to 

check for proper operation of the fuel system, 

and to address tripped circuit breakers, 

failure of a fuel pump in flight, and 

operations in a low-fuel situation, as 

specified in Table 2 (under Section 4.11) of 

the service bulletin. 

Note 1: The actions required by paragraph 

(f)(1) of this AD may be done by inserting a 

copy of the applicable advance amendment 

bulletins (AABs) specified in Table 2 of 

Airbus UK BAC One-Eleven Alert Service 

Bulletin 28–A–PM6057, Issue 1, dated May 

10, 2004, into the AFM. When information 

identical to that in the applicable AABs has 

been included in the general revisions of the 

AFM, the AABs no longer need to be inserted 

into the AFM. 

(2) Revise the FAA-approved maintenance 

program to include all repetitive 

maintenance tasks specified in Table 1 

(under Section 4.10.2.) of the service bulletin. 

Then, thereafter, comply with the 

requirements of these maintenance tasks at 

the interval specified in Table 1 of the service 

bulletin; except for airplanes that operate 

fewer than a total of 1,250 flight hours per 

year, accomplish the requirements of these 

maintenance tasks at the earlier of the times 

specified in columns 2 and 3 of Table 1 of 

the service bulletin. Where Table 1 of the 

service bulletin specifies a repetitive interval 

in ‘‘hours,’’ for the purposes of this AD, this 

means ‘‘flight hours.’’ Any applicable 

corrective actions must be done before 

further flight. 

Note 2: After revising the maintenance 

program to include the required periodic 

maintenance tasks according to paragraph 

(f)(2) of this AD, operators do not need to 

make a maintenance log entry to show 

compliance with this AD every time those 

maintenance tasks are accomplished 

thereafter. 

Alternative Methods of Compliance 

(AMOCs) 

(g) 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. 

Related Information 

(h) British airworthiness directive G–2004–

0012, dated June 21, 2004, also addresses the 

subject of this AD. 

Issued in Renton, Washington, on 

September 7, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–18402 Filed 9–15–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22425; Directorate 

Identifier 2005–NM–066–AD] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Model DC–8–33, DC–8–51, 

DC–8–53, DC–8–55, DC–8F–54, DC–8F–

55, DC–8–63, DC–8–62F, DC–8–63F, 

DC–8–71, DC–8–73, DC–8–71F, DC–8–

72F, and DC–8–73F 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 transport category airplanes, 

identified above. This proposed AD 

would require repetitive inspections for 

cracks of the doorjamb corners of the 

main cargo door, and repair if necessary. 

This proposed AD also provides an 

optional preventive modification that 

extends certain repetitive intervals. This 

proposed AD results from reports of 

cracks in the fuselage skin at the corners 

of the doorjamb for the main cabin cargo 

door. We are proposing this AD to 

detect and correct fatigue cracks in the 

fuselage skin, which could result in 

rapid decompression of the airplane. 

DATES: We must receive comments on 

this proposed AD by October 31, 2005. 

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, Long Beach Division, 3855 

Lakewood Boulevard, Long Beach, 

California 90846, Attention: Data and 

Service Management, Dept. C1–L5A 

(D800–0024), for the service information 

identified in this proposed AD. 

FOR FURTHER INFORMATION CONTACT: Jon 

Mowery, Aerospace Engineer, Airframe 

Branch, ANM–120L, FAA, Los Angeles 

Aircraft Certification Office, 3960 

Paramount Boulevard, Lakewood, 

California 90712–4137; telephone (562) 

627–5322; fax (562) 627–5210. 

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–2005–22425; Directorate 

Identifier 2005–NM–066–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