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 

Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Proposed Rules 54675 

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 

We have received reports of cracks in 

the fuselage skin at the corners of the 

doorjamb for the main cabin cargo door 

on McDonnell Douglas Model DC–8–

71F airplanes. Cracks were found on 

airplanes that had accumulated 14,600 

landings. The manufacturer’s 

investigation showed that the cracks 

resulted from fatigue stress. Fatigue 

cracks, if not corrected, could progress 

and result in rapid decompression of the 

airplane. 

Other Relevant Rulemaking 

On January 11, 1993, we issued AD 

93–01–15, amendment 39–8469 (58 FR 

5576, January 22, 1993). We issued that 

AD to ensure the continuing structural 

integrity of McDonnell Douglas Model 

DC–8 airplanes. That AD requires 

revising the FAA-approved maintenance 

inspection program, which provides for 

inspection of the Principal Structural 

Elements (PSEs) identified in 

McDonnell Douglas Report No. L26–

011, ‘‘DC–8 Supplemental Inspection 

Document (SID).’’ That AD also requires 

reporting results of inspections to 

McDonnell Douglas, and repairing any 

cracked structure detected during the 

inspections. 

Relevant Service Information 

We have reviewed Boeing Service 

Bulletin DC8–53–079, Revision 01, 

dated June 26, 2002. The service 

bulletin describes procedures for 

repetitive inspections for cracks of the 

doorjamb corners of the main cargo 

door. The inspections include 

radiographic, high frequency eddy 

current (HFEC), and visual (optically 

aided) inspections. Each inspection type 

is repeated in combination (e.g., 

radiographic and HFEC together) at 

varying intervals that range from 4,937 

landings to 11,325 landings depending 

on the type of inspection. These 

intervals are described in Table 1 of 

paragraph 1.E. ‘‘Compliance’’ of the 

service bulletin. 

If any crack is found that is 2.50 

inches in length or less, the service 

bulletin describes procedures for 

repairing the fuselage skin and 

installing an external doubler. If any 

crack is found that is greater than 2.50 

inches in length, the service bulletin 

specifies contacting the manufacturer 

for repair instructions and for reporting 

certain information. The service bulletin 

also gives procedures for a preventive 

modification of installing an external 

doubler at the corner of the main cabin 

cargo doorjamb. 

After any modification or repair, the 

service bulletin specifies that operators 

should inspect again for cracks of the 

modified or repaired doorjamb corner 

within 17,000 landings after doing the 

modification or repair, and then repeat 

the inspection at intervals not to exceed 

4,400 landings. 

Accomplishing the actions specified 

in the service information is intended to 

adequately address the unsafe 

condition. 

The inspection program in Revision 

01 of the service bulletin is an 

alternative method of compliance 

(AMOC) for the requirements of 

paragraphs (a) and (b) of AD 93–01–15 

for the specified areas of PSE 53.08.044. 

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, except as discussed under 

‘‘Differences Between the Proposed AD 

and the Service Bulletin.’’

Differences Between the Proposed AD 

and the Service Bulletin 

The service bulletin specifies to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions in 

one of the following ways: 

• Using a method that we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by an 

Authorized Representative for the 

Boeing Commercial Airplanes 

Delegation Option Authorization (DOA) 

Organization whom we have authorized 

to make those findings. 

Operators should note that, although 

the Accomplishment Instructions of the 

service bulletin describe procedures for 

submitting certain information to the 

manufacturer, this AD would not 

require that action. 

Clarification of Inspection Language 

In this proposed AD, the ‘‘visual 

(optically aided)’’ inspection specified 

in the Boeing service bulletin is referred 

to as a ‘‘detailed inspection.’’ We have 

included the definition for a detailed 

inspection in a note in the proposed AD. 

Costs of Compliance 

There are about 225 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. 

ESTIMATED COSTS

Action Work 

hours 

Average labor 

rate per hour Parts Cost per airplane Number of U.S.-registered airplanes Fleet cost 

Inspection, per inspection cycle.20 $65 None ......................... $1,300, per inspection cycle.166 ........................... $215,800, per inspection cycle. 

Optional preventive 

modification (per 

corner).

80 65 $26,881 to $30,913 

(per corner, depending on airplane configuration).

$32,081 to $36,113 .. Up to 166 ................. Up to between 

$5,325,446 and 

$5,994,758 (for 

one corner). 

54676 Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Proposed Rules 

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): 

McDonnell Douglas: Docket No. FAA–2005–

22425; Directorate Identifier 2005–NM–

066–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by October 31, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to 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, 

certificated in any category; as identified in 

Boeing Service Bulletin DC8–53–079, 

Revision 01, dated June 26, 2002. 

Unsafe Condition 

(d) This AD results from reports of cracks 

in the fuselage skin at the corners of the 

doorjamb for the main cabin cargo door. We 

are issuing this AD to detect and correct 

fatigue cracks in the fuselage skin, which 

could result in rapid decompression 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. 

Inspections 

(f) At the applicable time in paragraph 

(f)(1) or (f)(2) of this AD: Do detailed, high 

frequency eddy current, and radiographic 

inspections, as applicable, for cracks of the 

doorjamb corners of the main cargo door in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin DC8–

53–079, Revision 01, dated June 26, 2002. 

Except as provided by paragraph (g) and (h) 

of this AD, repeat the inspections thereafter 

at intervals not to exceed the applicable 

intervals specified in Table 1 of Paragraph 

1.E. ‘‘Compliance’’ of the service bulletin. 

(1) For airplanes that have been converted 

from passenger to cargo under Amended 

Type Certificate Data Sheet 4A25, Notes 25 

and 26, and McDonnell Douglas 

Supplemental Type Certificates SA3749WE 

and SA3403WE: Within 15,000 flight cycles 

after the conversion; or within 12 months 

after the effective date of this AD; whichever 

occurs later. 

(2) For airplanes that have not been 

converted from passenger to cargo: Before the 

accumulation of 15,000 total flight cycles, or 

within 3,000 flight cycles after the effective 

date of this AD, whichever occurs later. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Corrective Actions and New Repetitive 

Intervals 

(g) If any crack is found during any 

inspection required by this AD, before further 

flight: Do the applicable action in paragraph 

(g)(1) or (g)(2) of this AD in accordance with 

the Accomplishment Instructions of Boeing 

Service Bulletin DC8–53–079, Revision 01, 

dated June 26, 2002. 

(1) For any corner where all cracks are 2.50 

inches or less in length, install an external 

doubler in accordance with the service 

bulletin: Before the accumulation of 17,000 

flight cycles after the installation, do the next 

inspection of that corner as specified in 

paragraph (f) of this AD. Repeat the 

inspections in paragraph (f) of this AD for 

that corner thereafter at intervals not to 

exceed 4,400 flight cycles. 

(2) For any corner where any crack is 

greater than 2.50 inches in length, repair the 

crack using a method approved in 

accordance with paragraph (k) of this AD. 

Optional Preventive Modification 

(h) Installing an external doubler on a 

corner in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin DC8–53–079, Revision 01, 

dated June 26, 2002, terminates the repetitive 

inspection intervals of paragraph (f) of this 

AD for that corner. Before the accumulation 

of 17,000 flight cycles after the installation: 

Do the next inspection of that corner, as 

specified in paragraph (f) of this AD. Repeat 

the inspections in paragraph (f) of this AD for 

that corner thereafter at intervals not to 

exceed 4,400 flight cycles. 

No Reporting Required 

(i) Although the service bulletin referenced 

in this AD specifies to submit certain 

information to the manufacturer, this AD 

does not include that requirement. 

Actions Accomplished in Accordance With 

Previous Issue of Service Bulletin 

(j) Actions accomplished before the 

effective date of this AD in accordance with 

Boeing Service Bulletin DC8–53–079, dated 

January 31, 2001, are acceptable for 

compliance with the corresponding action in 

this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Los Angeles 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. 

(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 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Proposed Rules 54677 

the certification basis of the airplane and 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

(3) Inspections required by this AD of 

specified areas of Principal Structural 

Element (PSE) 53.08.044 are acceptable for 

compliance with the applicable requirements 

of paragraphs (a) and (b) of AD 93–01–15, 

amendment 39–8469 (58 FR 5576, January 

22, 1993). The remaining areas of the affected 

PSEs must be inspected and repaired as 

applicable, in accordance with AD 93–01–15. 

Issued in Renton, Washington, on 

September 7, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–18401 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–2005–22426; Directorate 

Identifier 2005–NM–105–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–300, 

747–400, 747–400D, and 747SR 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 

Boeing Model 747–100, 747–100B, 747–

100B SUD, 747–200B, 747–200C, 747–

300, 747–400, 747–400D, and 747SR 

series airplanes. This proposed AD 

would require a one-time inspection to 

determine whether any steel doubler 

(small or large) is installed at the lower 

forward and upper aft corners of the 

fuselage cutout at main entry doors 

(MEDs) number 3. Depending on the 

results of this inspection, this proposed 

AD also would require repetitive 

inspections for cracks of the skin, 

bearstrap, and small steel doubler (if 

installed) at the applicable corner or 

corners of the fuselage cutouts, and 

related investigative/corrective actions 

if necessary. This proposed AD also 

would provide the optional terminating 

action for the repetitive inspections of 

installing a large steel doubler at the 

affected corners. This proposed AD is 

prompted by reports of cracks in the 

skin and bearstrap at the upper aft 

corner and at the lower forward corner 

of the fuselage cutout at MEDs number 

3. We are proposing this AD to detect 

and correct cracks in the skin, bearstrap, 

and small steel doubler (if installed), 

which could propagate and 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. 

• By 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. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 

You can examine the contents of this 

AD docket on the Internet at http:// 

dms.dot.gov, or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW., room PL–401, on the plaza level of 

the Nassif Building, Washington, DC. 

This docket number is FAA–2005–

22426; the directorate identifier for this 

docket is 2005–NM–105–AD. 

FOR FURTHER INFORMATION CONTACT: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 917–6437; 

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 under 

ADDRESSES. Include ‘‘Docket No. FAA–

2005–22426; Directorate Identifier 

2005–NM–105–AD’’ in the subject line 

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 

submitted 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 

website, 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 can 

review DOT’s complete Privacy Act 

Statement in the Federal Register 

published on April 11, 2000 (65 FR 

19477–78), or you can visit http:// 

dms.dot.gov. 

Examining the Docket 

You can 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 (DMS) receives 

them. 

Discussion 

We have received a report indicating 

that seven operators of the affected 

airplanes have found cracks in the skin 

and bearstrap at the upper aft corner of 

the fuselage cutout at main entry doors 

(MEDs) number 3. These cracks, which 

were between 0.6 inch and 2.5 inches in 

length, were found on airplanes that had 

accumulated between 12,140 and 23,927 

flight cycles. We have received other 

reports indicating that some operators 

also found cracks in the skin and 

bearstrap at the lower forward corner of 

the fuselage cutout at MEDs number 3. 

These cracks were between 0.5 inch and 

4.0 inches in length, and were found on 

airplanes that had accumulated between 

11,986 and 23,083 flight cycles. Cracks 

in the skin, bearstrap, and small steel 

doubler, if not detected and corrected, 

could propagate and result in rapid 

decompression of the airplane. 

Other Relevant Rulemaking 

On December 8, 1992, we issued AD 

92–27–04, amendment 39–8437 (57 FR 

59801, December 16, 1992) for certain 

Boeing Model 747 series airplanes. [A 

correction of that AD was published in 

the Federal Register on February 17, 

1993 (58 FR 8693)]. We issued that AD 

to prevent the structural degradation of