This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

24712 

Vol. 74, No. 99 

Tuesday, May 26, 2009 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0477; Directorate 

Identifier 2008–NM–191–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100, –100B, –100B SUD, 

–200B, and –300 Series Airplanes; and 

Model 747SP and 747SR Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to certain 

Boeing Model 747 series airplanes. The 

existing AD currently requires repetitive 

inspections to detect cracks in various 

areas of the fuselage internal structure, 

and related investigative/corrective 

actions if necessary. This proposed AD 

would require additional repetitive 

inspections for cracking of certain 

fuselage structure, and related 

investigative/corrective actions if 

necessary. This proposed AD results 

from fatigue tests and analysis by 

Boeing that identified areas of the 

fuselage where fatigue cracks can occur. 

We are proposing this AD to prevent the 

loss of the structural integrity of the 

fuselage, which could result in rapid 

depressurization of the airplane. 

DATES: We must receive comments on 

this proposed AD by July 10, 2009. 

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 proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1, fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221 or 425–227–1152. 

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 proposed 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: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2009–0477; Directorate Identifier 

2008–NM–191–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

Discussion 

On September 26, 2005, we issued AD 

2005–20–30, amendment 39–14327 (70 

FR 59252, October 12, 2005), for certain 

Boeing Model 747 series airplanes. That 

AD requires repetitive inspections to 

detect cracks in various areas of the 

fuselage internal structure, and related 

investigative/corrective actions if 

necessary. That AD resulted from 

fatigue tests and analysis by Boeing that 

identified areas of the fuselage where 

fatigue cracks can occur. We issued that 

AD to prevent the loss of the structural 

integrity of the fuselage, which could 

result in rapid depressurization of the 

airplane. 

Actions Since Existing AD Was Issued 

Since we issued AD 2005–20–30, 

Boeing has conducted an additional 

analysis that shows that Section 41 

fuselage frames in the areas attached to 

the upper deck floor beams are also 

prone to fatigue cracking. Cracking of 

the frames was found on the fatigue test 

airplane at about 40,000 total pressure 

cycles. As a result, we have determined 

that additional inspections are 

necessary, as specified in the service 

information described below. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 747–53A2349, Revision 

3, dated October 2, 2008 (‘‘the service 

bulletin’’). In AD 2005–20–30, we 

referred to Boeing Alert Service Bulletin 

747–53A2349, Revision 1, dated 

October 12, 2000; and Boeing Service 

Bulletin 747–53A2349, Revision 2, 

dated April 3, 2003; as the appropriate 

sources of service information for doing 

the actions required by that AD. 

Revision 3 of the service bulletin retains 

the procedures from Revision 2, revises 

some airplane groups, and adds the 

repetitive inspections listed in the table 

titled ‘‘New Service Bulletin 

Procedures.’’ 

Federal Register / Vol. 74, No. 99 / Tuesday, May 26, 2009 / Proposed Rules 24713 

NEW SERVICE BULLETIN PROCEDURES

Revision 3 of the service bulletin adds procedures for repetitive detailed inspections for cracking of these areas 

specified in the service bulletin— 

For airplanes identified as 

these groups in Revision 3 

of the service bulletin— 

Additional inspections in Area 1: Fuselage frames at body stations 260–520 in areas where the upper deck floor 

beams are attached (Figure 11 of the Accomplishments Instructions of the service bulletin).

1 through 7 inclusive. 

Additional inspections in Area 6: Fuselage frames at body stations 400–500 in areas above the Main Entry Door 1 

cutouts, from the upper chord of the upper deck floor beams to Stringer 8 (Figure 12 of the Accomplishment Instructions of the service bulletin).

6 and 7. 

The service bulletin specifies that the 

compliance time for the inspections of 

additional areas is before 22,000 total 

flight cycles or within 1,000 flight 

cycles after the date on the service 

bulletin, whichever occurs later. The 

service bulletin also specifies repeating 

the inspections at intervals not to 

exceed 3,000 flight cycles. The service 

bulletin specifies to repair any crack or 

to contact Boeing for repair instructions. 

Accomplishing the actions specified 

in the service information is intended to 

adequately address the unsafe 

condition. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to develop on 

other airplanes of the same type design. 

For this reason, we are proposing this 

AD, which would supersede AD 2005– 

20–30 and would retain the 

requirements of the existing AD. This 

proposed AD would also require 

accomplishing the additional actions 

specified in Boeing Alert Service 

Bulletin 747–53A2349, Revision 3, 

dated October 2, 2008, described 

previously. 

Change to Existing AD 

This proposed AD would retain all 

requirements of AD 2005–20–30. Since 

AD 2005–20–30 was issued, the AD 

format has been revised, and certain 

paragraphs have been rearranged. As a 

result, the corresponding paragraph 

identifiers have changed in this 

proposed AD, as listed in the following 

table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

2005–20–30 

Corresponding 

requirement in this 

proposed AD 

paragraph (f) ............. paragraph (g). 

paragraph (g) ............ paragraph (h). 

paragraph (h) ............ paragraph (i). 

paragraph (i) ............. paragraph (j). 

paragraph (j) ............. paragraph (k). 

paragraph (k) ............ paragraph (l). 

Costs of Compliance 

There are about 209 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. The 

average labor rate is $80 per work hour. 

ESTIMATED COSTS

Action Work 

hours 

Cost per 

airplane, per 

inspection 

cycle 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspections (required by AD 2005–20–30) .............................................................. 130 $10,400 69 $717,600 

Additional inspections in Area 1 (new proposed action) ......................................... 6 480 69 33,120 

Additional inspections in Area 6 (new proposed action) ......................................... 1 80 69 5,520 

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, Incorporation by reference, 

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: 

24714 Federal Register / Vol. 74, No. 99 / Tuesday, May 26, 2009 / Proposed Rules 

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 

removing amendment 39–14327 (70 FR 

59252, October 12, 2005) and adding the 

following new AD: 

Boeing: Docket No. FAA–2009–0477; 

Directorate Identifier 2008-NM–191-AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by July 10, 2009. 

Affected ADs 

(b) This AD supersedes AD 2005–20–30. 

Applicability 

(c) This AD applies to Boeing Model 747– 

100, 747–100B, 747–100B SUD, 747–200B, 

747–300, 747SP, and 747SR series airplanes; 

certificated in any category; identified in 

Boeing Service Bulletin 747–53A2349, 

Revision 3, dated October 2, 2008. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from fatigue tests and 

analysis by Boeing that identified areas of the 

fuselage where fatigue cracks can occur. We 

are issuing this AD to prevent the loss of the 

structural integrity of the fuselage, which 

could result in rapid depressurization of the 

airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2002– 

10–10 

(Excluding Upper Deck Floor Beams) 

Repetitive Inspections 

(g) Prior to the accumulation of 22,000 total 

flight cycles, or within 1,000 flight cycles 

after June 11, 1993 (the effective date of AD 

93–08–12, amendment 39–8559, which was 

superseded by AD 2002–10–10), whichever 

occurs later, unless accomplished previously 

within the last 2,000 flight cycles; and 

thereafter at intervals not to exceed 3,000 

flight cycles: Perform an internal detailed 

inspection to detect cracks in the areas of the 

fuselage internal structure specified in 

paragraphs (g)(1) through (g)(6) of this AD; in 

accordance with Boeing Service Bulletin 

747–53–2349, dated June 27, 1991; Boeing 

Alert Service Bulletin 747–53A2349, 

Revision 1, dated October 12, 2000; Boeing 

Service Bulletin 747–53A2349, Revision 2, 

dated April 3, 2003; or Boeing Alert Service 

Bulletin 747–53A2349, Revision 3, dated 

October 2, 2008. After the effective date of 

this AD, only Revision 3 of Boeing Alert 

Service Bulletin 747–53A2349 may be used. 

Continue doing the inspections until the 

inspections required by paragraph (j) of this 

AD are done. 

(1) Section 42 upper lobe frames. 

(2) Section 46 lower lobe frames. 

(3) Section 42 lower lobe frames. 

(4) Main entry door cutouts. 

(5) Section 41 body station 260, 340, and 

400 bulkheads. 

(6) Main entry doors. 

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.’’ 

(h) Prior to the accumulation of 25,000 

total flight cycles, or within 1,000 flight 

cycles after June 11, 1993, whichever is later, 

unless already done within the last 2,000 

flight cycles; and thereafter at intervals not to 

exceed 3,000 flight cycles: Do an internal 

detailed inspection to detect cracks in the 

Section 46 upper lobe frames, in accordance 

with Boeing Service Bulletin 747–53–2349, 

dated June 27, 1991; Boeing Alert Service 

Bulletin 747–53A2349, Revision 1, dated 

October 12, 2000; Boeing Service Bulletin 

747–53A2349, Revision 2, dated April 3, 

2003; or Boeing Alert Service Bulletin 747– 

53A2349, Revision 3, dated October 2, 2008. 

After the effective date of this AD, only 

Revision 3 of Boeing Alert Service Bulletin 

747–53A2349 may be used. 

Repair of Cracks Detected During Paragraph 

(g) or (h) Inspections 

(i) Before further flight, repair any cracks 

detected during the inspections done per 

paragraph (g) or (h) of this AD by doing the 

actions specified in paragraph (i)(1) or (i)(2) 

of this AD, as applicable. 

(1) Repair in accordance with a method 

approved by the Manager, Seattle Aircraft 

Certification Office (ACO), FAA; or using a 

method approved in accordance with 

paragraph (p) of this AD. 

(2) Repair in accordance with Boeing 

Service Bulletin 747–53A2349, Revision 2, 

dated April 3, 2003; or Boeing Alert Service 

Bulletin 747–53A2349, Revision 3, dated 

October 2, 2008. After the effective date of 

this AD, only Revision 3 of Boeing Alert 

Service Bulletin 747–53A2349 may be used. 

Where either revision of the service bulletin 

specifies to contact Boeing for repair 

instructions, repair in accordance with a 

method approved by the Manager, Seattle 

ACO; or using a method approved in 

accordance with paragraph (p) of this AD. 

Restatement of Requirements of AD 2005– 

20–30 

Repetitive Inspections 

(j) Do an internal detailed inspection to 

detect cracking in the areas of the fuselage 

internal structure specified in paragraphs 

(j)(1), (j)(2), and (j)(3) of this AD, and internal 

and external detailed inspections of the areas 

specified in paragraphs (j)(4), (j)(5), (j)(6), and 

(j)(7) of this AD. Do the inspections in 

accordance with Boeing Service Bulletin 

747–53A2349, Revision 2, dated April 3, 

2003; or Boeing Alert Service Bulletin 747– 

53A2349, Revision 3, dated October 2, 2008. 

After the effective date of this AD, only 

Revision 3 of Boeing Alert Service Bulletin 

747–53A2349 may be used. Do the 

inspections at the applicable time specified 

in paragraph (k) of this AD. Accomplishment 

of these inspections terminates the 

requirements of paragraph (g) of this AD. 

(1) Section 42 upper lobe frames. 

(2) Section 46 lower lobe frames. 

(3) Section 42 lower lobe frames. 

(4) Main entry door cutouts. 

(5) Nose wheel well bulkheads, sidewall 

panels, and Station (STA) 360 and 380 floor 

beams. These areas include Section 41 body 

station 260, 340, and 400 bulkheads. 

(6) Main entry doors. 

(7) Main electronics bay access door 

cutout. 

(k) Do the inspections required by 

paragraph (j) of this AD at the applicable time 

specified in paragraph (k)(1), (k)(2), or (k)(3) 

of this AD. Repeat the inspections thereafter 

at intervals not to exceed 3,000 flight cycles. 

(1) For airplanes on which the inspections 

required by paragraphs (g)(1), (g)(2), (g)(3), 

(g)(4), and (g)(6) of this AD have been done 

before November 16, 2005 (the effective date 

of AD 2005–20–30), but the inspections 

required by paragraphs (j)(5) and (j)(7) of this 

AD have not been done: Within 3,000 flight 

cycles since accomplishment of the most 

recent inspection required by paragraphs 

(g)(1), (g)(2), (g)(3), (g)(4), and (g)(6) of this 

AD, except that the inspections specified in 

paragraphs (j)(5) and (j)(7) of this AD may be 

done within 3,000 flight cycles since 

accomplishment of the most recent 

inspection required by paragraphs (g)(1), 

(g)(2), (g)(3), (g)(4), and (g)(6) of this AD, or 

within 1,000 flight cycles after November 16, 

2005, whichever is later. 

(2) For airplanes on which the inspections 

required by paragraphs (j)(5) and (j)(7) have 

been done before November 16, 2005: Within 

3,000 flight cycles since accomplishment of 

the most recent inspection required by 

paragraphs (j)(5) and (j)(7) of this AD, or 

within 1,000 flight cycles after November 16, 

2005, whichever is later. 

(3) For airplanes on which the inspections 

required by paragraph (g) of this AD have not 

been done before November 16, 2005: Prior 

to the accumulation of 22,000 total flight 

cycles, or within 1,000 flight cycles after 

November 16, 2005, whichever is later. 

Repair of Cracks Detected During Paragraph 

(j) Inspection 

(l) Before further flight, repair any cracking 

found during any inspection required by 

paragraph (j) of this AD in accordance with 

Boeing Service Bulletin 747–53A2349, 

Revision 2, dated April 3, 2003; or Boeing 

Alert Service Bulletin 747–53A2349, 

Revision 3, dated October 2, 2008. After the 

effective date of this AD, only Revision 3 of 

Boeing Alert Service Bulletin 747–53A2349 

may be used. Where any revision of the 

service bulletin specifies to contact Boeing 

for repair instructions, repair in accordance 

Federal Register / Vol. 74, No. 99 / Tuesday, May 26, 2009 / Proposed Rules 24715 

with a method approved by the Manager, 

Seattle ACO; or using a method approved in 

accordance with paragraph (p) of this AD. 

New Requirements of This AD 

Inspections and Repair 

(m) Do initial and repetitive detailed 

inspections for cracking in the areas specified 

in Table 1 of this AD using applicable 

internal and external detailed inspection 

methods; and repair all cracks, by doing all 

the applicable actions in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2349, Revision 3, 

dated October 2, 2008, except as required by 

paragraph (n) of this AD. Do the initial and 

repetitive inspections at the times specified 

in paragraph 1.E., ‘‘Compliance,’’ of the 

service bulletin, except as required by 

paragraph (o) of this AD. Repair all cracks 

before further flight after detection. 

TABLE 1—ADDITIONAL INSPECTIONS

Inspect the addition portion of area 1 and area 6 as specified in Boeing Alert Service Bulletin 747–53A2349, Revision 3, dated October 2, 2008 (‘‘the service bulletin’’)— 

For airplanes identified as 

these groups in the service 

bulletin— 

In Area 1: Fuselage frames at body stations 260–520 in areas where the upper deck floor beams are attached 

(Figure 11 of the Accomplishments Instructions of the service bulletin).

1 through 7 inclusive. 

In Area 6: Fuselage frames at body stations 400–500 in areas above the Main Entry Door 1 cutouts, from the 

upper chord of the upper deck floor beams to Stringer 8 (Figure 12 of the Accomplishment Instructions of the 

service bulletin).

6 and 7. 

Exceptions to Certain Procedures 

(n) If any crack is found during any 

inspection required by paragraph (m) of this 

AD, and Boeing Alert Service Bulletin 747– 

53A2349, Revision 3, dated October 2, 2008, 

specifies to contact Boeing for appropriate 

action: Before further flight, repair the crack 

using a method approved in accordance with 

the procedures specified in paragraph (p) of 

this AD. 

(o) Where Boeing Alert Service Bulletin 

747–53A2349, Revision 3, dated October 2, 

2008, specifies a compliance time after the 

date on Boeing Alert Service Bulletin 747– 

53A2349, Revision 3, dated October 2, 2008, 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(p)(1) The Manager, Seattle ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. Send information to Attn: Ivan Li, 

Aerospace Engineer, Airframe Branch, ANM– 

120S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6437; fax (425) 917–6590. Or, e-mail 

information to 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(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 principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(3) AMOCs approved previously in 

accordance with AD 2005–20–30 are 

approved as AMOCs with the corresponding 

provisions of this AD. 

(4) 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, 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. 

Issued in Renton, Washington, on May 15, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–12111 Filed 5–22–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0476; Directorate 

Identifier 2008–NM–188–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 707 Airplanes, and Model 720 

and 720B Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to certain 

Boeing Model 707 airplanes, and Model 

720 and 720B series airplanes. The 

existing AD currently requires repetitive 

detailed inspections to detect cracks and 

corrosion on any existing repairs and at 

certain body stations (STA) of the 

visible surfaces of the wing to body 

terminal fittings including the web, 

flanges, and ribs; and applicable related 

investigative and corrective actions. 

This proposed AD would retain the 

requirements of the existing AD and 

would require repetitive ultrasonic 

inspections to detect any stress 

corrosion cracks within the outboard 

flange of the left and right body terminal 

fittings at STA 820, and related 

investigative and corrective actions if 

necessary. This proposed AD would 

also provide for an optional terminating 

action for the repetitive inspections. 

This proposed AD also adds two 

airplanes to the applicability. This 

proposed AD results from reports of 

cracks found in the wing to body 

terminal fittings during routine 

inspections. We are proposing this AD 

to detect and correct cracks and 

corrosion in the body terminal fittings 

above and below the floor, which could 

cause loss of support for the wing and 

could adversely affect the structural 

integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by July 10, 2009. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; e-mail,