56958 Federal Register / Vol. 73, No. 191 / Wednesday, October 1, 2008 / Rules and Regulations 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2008–17–13 Boeing: Amendment 39–15651. 

Docket No. FAA–2008–0149; Directorate 

Identifier 2007–NM–319–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective November 5, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 737– 

100, –200, –200C, –300, –400, and –500 

series airplanes, certificated in any category; 

as identified in Boeing Alert Service Bulletin 

737–38A1054, dated August 23, 2007. 

Unsafe Condition 

(d) This AD results from a report of a 

separated hose assembly for the passenger 

water system. We are issuing this AD to 

prevent a water leak into the flight deck 

ceiling, which could result in an electrical 

short and possible loss of several functions 

essential to safe flight. 

Compliance 

(e) Comply with this AD within the 

compliance times specified, unless already 

done. 

Replacement 

(f) Within 60 months after the effective 

date of this AD, replace the existing straightto-90-degree hose assembly for the Lavatory 

‘‘A’’ water supply with a new straight hose 

assembly and a separate 90-degree elbow 

fitting, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–38A1054, dated August 

23, 2007. 

Parts Installation 

(g) As of the effective date of this AD, any 

hose assembly part having a part number 

identified in Table 1 of this AD must not be 

used in any location that is subject to the 

requirements of this AD. However, those 

parts may be used in other locations if not 

otherwise prohibited. 

TABLE 1—SPARE PARTS PROHIBITED FOR THIS AD 

Airplane group identified in Boeing Alert 

Service Bulletin 737–38A1054, 

dated August 23, 2007 

Existing part number(s) 

1 and 2 ..................................................................................................... 10–61998–430, AS4471–08–0401, or AS4471–08–0404. 

3 ................................................................................................................ 10–61998–25 or 10–60871–125. 

4 ................................................................................................................ 10–61998–31 or 10–60871–139. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Seattle Aircraft 

Certification Office, FAA, ATTN: Marcia 

Smith, Aerospace Engineer, Cabin Safety and 

Environmental Systems Branch, ANM–150S, 

1601 Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6484; fax 

(425) 917–6590; has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

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

FSDO. 

Material Incorporated by Reference 

(i) You must use Boeing Alert Service 

Bulletin 737–38A1054, dated August 23, 

2007, to do the actions required by this AD, 

unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207. 

(3) You may review copies of the service 

information incorporated by reference at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington; or at 

the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on August 

6, 2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–22649 Filed 9–30–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0947; Directorate 

Identifier 2008–NM–154–AD; Amendment 

39–15670; AD 2008–19–03] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–300, –400, and –500 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 737–300, –400, and –500 

series airplanes. This AD requires 

repetitive external detailed inspections 

or non-destructive inspections to detect 

cracks in the fuselage skin along the 

chem-mill steps at stringers S–1 and S– 

2R, between station (STA) 400 and STA 

460, and repair if necessary. This AD 

results from reports of cracks in the 

fuselage skin common to stringer S–1 

and between STA 400 and STA 460. We 

are issuing this AD to detect and correct 

fatigue cracking of the fuselage skin 

panels at the chem-mill steps, which 

could result in sudden fracture and 

failure of the fuselage skin panels, and 

consequent rapid decompression of the 

airplane. 

DATES: This AD is effective October 16, 

2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 16, 2008. 

We must receive comments on this 

AD by December 1, 2008. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

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

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

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

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207. 


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Federal Register / Vol. 73, No. 191 / Wednesday, October 1, 2008 / Rules and Regulations 56959 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6447; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received three reports of cracks in 

the fuselage skin common to stringer S– 

1 and between station (STA) 400 and 

STA 460. In all three cases, there were 

cracks in adjacent 10-inch tear strap 

bays. In one case, there were cracks in 

four adjacent 10-inch tear strap bays. 

The cracks measured between 4.0 and 

10.5 inches long. The airplanes had 

accumulated between 42,038 and 57,523 

total flight cycles. Analysis indicates 

that the cracks were caused by fatigue 

due to high tension stresses and local 

bending at the edge of the chem-mill 

pockets of the bonded fuselage skin. 

Airplanes with 20-inch tear strap bays 

are also susceptible to cracks at this 

location. Fatigue cracking of the 

fuselage skin panels at the chem-mill 

steps, if not detected and corrected, 

could result in sudden fracture and 

failure of the fuselage skin panels, and 

consequent rapid decompression of the 

airplane. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 737–53A1293, dated August 13, 

2008. The service bulletin describes 

procedures for repetitive external 

detailed inspections or non-destructive 

inspections (NDI) to detect cracks in the 

fuselage skin along the chem-mill steps 

at stringers S–1 and S–2R between STA 

400 and STA 460, and contacting 

Boeing for repair instructions. The NDI 

inspections that can be used are 

medium frequency eddy current, 

magneto optical imaging, or c-scan. For 

the initial inspection, the service 

bulletin specifies a compliance time of 

before 35,000 total flight cycles, or 

within 500 flight cycles after the date on 

the service bulletin, whichever occurs 

later. For the repetitive inspections, the 

service bulletin specifies repeat 

intervals ranging between 1,200 and 

4,500 flight cycles, depending on the 

airplane configuration and the type of 

inspection previously done. 

FAA’s Determination and Requirements 

of This AD 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the(se) 

same type design(s). This AD requires 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Difference Between the AD and the 

Service Information.’’ 

Difference Between the AD and the 

Service Information 

Boeing Alert Service Bulletin 737– 

53A1293, dated August 13, 2008, 

specifies contacting the manufacturer 

for instructions on how to repair a 

certain condition, but this AD requires 

repairing that condition 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 

Organization whom we have authorized 

to make those findings. 

Interim Action 

We consider this AD interim action. If 

final action is later identified, we might 

consider further rulemaking then. 

FAA’s Justification and Determination 

of the Effective Date 

We are issuing this AD to detect and 

correct fatigue cracking of the fuselage 

skin panels at the chem-mill steps, 

which could result in sudden fracture 

and failure of the fuselage skin panels, 

and consequent rapid decompression of 

the airplane. Because of our requirement 

to promote safe flight of civil aircraft 

and thus, the critical need to assure the 

structural integrity of the fuselage and 

the short compliance time involved 

with this action, this AD must be issued 

immediately. 

Because an unsafe condition exists 

that requires the immediate adoption of 

this AD, we find that notice and 

opportunity for prior public comment 

hereon are impracticable and that good 

cause exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2008–0947; Directorate Identifier 2008– 

NM–154–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this AD. We will consider all 

comments received by the closing date 

and may amend this AD because of 

those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 


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56960 Federal Register / Vol. 73, No. 191 / Wednesday, October 1, 2008 / Rules and Regulations 

(2) Is not a ‘‘significant rule’’ under 

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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2008–19–03 Boeing: Amendment 39–15670. 

Docket No. FAA–2008–0947; Directorate 

Identifier 2008–NM–154–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective October 16, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 737– 

300, –400, and –500 series airplanes, 

certificated in any category; as identified in 

Boeing Alert Service Bulletin 737–53A1293, 

dated August 13, 2008. 

Unsafe Condition 

(d) This AD results from reports of cracks 

in the fuselage skin common to stringer 

S–1 and between station (STA) 400 and STA 

460. We are issuing this AD to detect and 

correct fatigue cracking of the fuselage skin 

panels at the chem-mill steps, which could 

result in sudden fracture and failure of the 

fuselage skin panels, and consequent rapid 

decompression of the airplane. 

Compliance 

(e) Comply with this AD within the 

compliance times specified, unless already 

done. 

Repetitive Inspections 

(f) At the applicable times specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 737–53A1293, dated 

August 13, 2008 (hereafter ‘‘the service 

bulletin’’); except where the service bulletin 

specifies a compliance time after the date on 

the service bulletin, this AD requires 

compliance within the specified compliance 

time after the effective date of this AD: Do 

repetitive external detailed inspections or 

non-destructive inspections (NDI) to detect 

cracks in the fuselage skin along the chemmill steps at stringers S–1 and S–2R, between 

STA 400 and STA 460, by accomplishing the 

applicable inspections specified in the 

Accomplishment Instructions of the service 

bulletin. 

Repair 

(g) If any crack is found during any 

inspection required by paragraph (f) of this 

AD, before further flight, repair the cracked 

fuselage skin using a method approved in 

accordance with the procedures specified in 

paragraph (h) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, ATTN: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6447; fax (425) 917–6590; has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

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

FSDO. 

(3) 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. 

Material Incorporated by Reference 

(i) You must use Boeing Alert Service 

Bulletin 737–53A1293, dated August 13, 

2008, to do the actions required by this AD, 

unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207. 

(3) You may review copies of the service 

information incorporated by reference at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington; or at 

the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal_register/code_of_

federal_regulations/ibr_locations.html. 

Issued in Renton, Washington, on 

September 11, 2008. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–22755 Filed 9–30–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–29227; Directorate 

Identifier 2007–NM–100–AD; Amendment 

39–15664; AD 2008–18–07] 

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), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 747–100, 747–100B, 747– 

100B SUD, 747–200B, 747–200C, 747– 

300, 747–400, 747–400D, and 747SR 

series airplanes. For certain airplanes, 

this AD requires a material type 

inspection to determine if the lower 

forward corner reveal of the number 3 

main entry doors (MEDs) is a casting. If 

the reveals are castings, this AD requires 

repetitive inspections of the reveals for 

cracking, and corrective action if 

necessary. If the reveals are not castings, 

this AD requires a detailed inspection of 

the reveals for a sharp edge and 

repetitive inspections of the reveals for 

cracking, and corrective action if 

necessary. For certain other airplanes, 

this AD requires only a detailed 

inspection of the reveals for a sharp 

edge and repetitive inspections of the 

reveals for cracking, and corrective 

action if necessary. For certain other 

airplanes, this AD requires repetitive 

inspections of the reveals for cracking 

only, and corrective action if necessary. 

This AD also allows a certain 

replacement as an optional action for 

the material type inspection for certain 

airplanes. This AD results from reports 

of cracking and/or a sharp edge in the 

lower forward corner reveal of the 

number 3 MEDs. We are issuing this AD 

to detect and correct fatigue cracking of 

the lower forward corner reveal of the 

number 3 MEDs, which could lead to 

the door escape slide departing the 

airplane when the door is opened and 

the slide is deployed, and consequent 


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