50716 Federal Register / Vol. 73, No. 168 / Thursday, August 28, 2008 / Rules and Regulations 

Terminating Action for AWLs Revision 

(j) Incorporating AWL No. 28–AWL–07 

into the AWLs section of the ICA in 

accordance with paragraph (g)(3) of AD 

2008–10–10, amendment 39–15516, 

terminates the action required by paragraph 

(g) of this AD. 

AMOCs 

(k)(1) The Manager, Seattle Aircraft 

Certification Office, FAA, ATTN: Georgios 

Roussos, Aerospace Engineer, Systems and 

Equipment Branch, ANM–130S, 1601 Lind 

Avenue SW., Renton, Washington 98057–

3356; telephone (425) 917–6482; 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 

(l) You must use Boeing Alert Service 

Bulletin 737–28A1221, Revision 1, dated 

November 9, 2007; and Airworthiness 

Limitation 28–AWL–07 of Section 9 of the 

Boeing 737–600/700/800/900 Maintenance 

Planning Data (MPD) Document, D626A001–

CMR, Revision March 2007 R2; 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 

12, 2008. 

Michael J Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–19367 Filed 8–27–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0148; Directorate 

Identifier 2007–NM–299–AD; Amendment 

39–15655; AD 2008–17–17] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Boeing Model 747 airplanes. This AD 

requires a one-time inspection of certain 

fuselage skins at section 41 to find any 

external doublers that cover the 

inspection areas and to identify the 

external doublers that end on a stringer 

and those that do not, and related 

investigative and corrective actions if 

necessary. This AD results from reports 

of cracks found at fastener locations in 

the fuselage skins at section 41. We are 

issuing this AD to detect and correct 

fuselage skin cracks at fastener locations 

along the skin-to-stringer attachments, 

which could join together and become 

large and consequently result in rapid 

decompression of the cabin. 

DATES: This AD is effective October 2, 

2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 2, 2008. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 

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 address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to all 

Boeing Model 747 airplanes. That 

NPRM was published in the Federal 

Register on February 8, 2008 (73 FR 

7486). That NPRM proposed to require 

a one-time inspection of certain fuselage 

skins at section 41 to find any external 

doublers that cover the inspection areas 

and to identify the external doublers 

that end on a stringer and those that do 

not, and related investigative and 

corrective actions if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received from 

the two commenters. 

Support for the NPRM 

Boeing concurs with the contents of 

the NPRM. 

Request to Either Delay Issuance of the 

AD or Extend the Compliance Time 

Japan Airlines (JAL) requests that we 

delay issuance of the AD until Boeing 

has published a revision to Boeing Alert 

Service Bulletin 747–53A2704, dated 

October 4, 2007, to extend the 

compliance time from 16,000 total flight 

cycles to 25,000 total flight cycles for 

accomplishing the general visual 

inspection for external doublers in 

Areas 2 and 3. If we cannot delay 

issuance of the AD, then JAL requests 

that we revise the compliance time 

accordingly in this AD. JAL states that 

Boeing has advised that only the 

inspection of Area 1 must be done 

before 16,000 total flight cycles, and that 

Areas 2 and 3 should be inspected 

together with the high frequency eddy 

current inspection of the skin-to-stringer 

attachments before 25,000 total flight 

cycles. JAL asserts that Boeing will 

revise the compliance time in the next 

revision to the service bulletin. 

We do not agree to delay issuance of 

this AD, or to revise the compliance 

time for inspecting for external doublers 

in Areas 2 and 3. We have coordinated 

with Boeing, and Boeing has no plans, 

at this time, to revise the service 

bulletin. Boeing also has confirmed that 

the inspection of Areas 1, 2, and 3 was 

left at 16,000 total flight cycles for 

simplicity of the compliance table in the 

service bulletin. Therefore, we agree 

that, for Groups 1 through 5 airplanes, 

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Federal Register / Vol. 73, No. 168 / Thursday, August 28, 2008 / Rules and Regulations 50717 

the general visual inspection for 

external doublers in Areas 2 and 3 may 

be done before 25,000 total flight cycles, 

or within 2,000 flight cycles after the 

effective date of this AD, whichever 

occurs later. However, due to the unique 

nature of JAL’s request, it would be best 

to address it using the alternative 

methods of compliance (AMOC) 

process, rather than revising this AD. 

We will consider requests for 

adjustments to the compliance time, 

under the provisions of paragraph (h) of 

this AD, if data are submitted to 

substantiate that such an adjustment 

would provide an acceptable level of 

safety. We have not changed the AD in 

this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 165 

airplanes of U.S. registry. We also 

estimate that it takes up to 64 workhours per product to comply with this 

AD. The average labor rate is $80 per 

work-hour. Based on these figures, we 

estimate the cost of this AD to the U.S. 

operators to be $844,800 or $5,120 per 

product. 

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, 

(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: 

2008–17–17 Boeing: Amendment 39–15655. 

Docket No. FAA–2008–0148; Directorate 

Identifier 2007–NM–299–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective October 2, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Boeing Model 

747–100, 747–100B, 747–100B SUD, 747–

200B, 747–200C, 747–200F, 747–300, 747–

400, 747–400D, 747–400F, 747SR, and 747SP 

series airplanes, certificated in any category. 

Unsafe Condition 

(d) This AD results from reports of cracks 

found at fastener locations in the fuselage 

skins at section 41. We are issuing this AD 

to detect and correct fuselage skin cracks at 

fastener locations along the skin-to-stringer 

attachments, which could join together and 

become large and consequently result in 

rapid decompression of the cabin. 

Compliance 

(e) Comply with this AD within the 

compliance times specified, unless already 

done. 

Repetitive Inspections and Related 

Investigative/Corrective Actions 

(f) At the applicable compliance times 

specified in Tables 1 and 2 of paragraph 1.E. 

of Boeing Alert Service Bulletin 747–

53A2704, dated October 4, 2007: Do a general 

visual inspection of the fuselage skins at 

section 41 to find any external doublers that 

cover the inspection area and to identify the 

external doublers that end on a stringer in the 

inspection area and those that do not, and do 

all the related investigative and corrective 

actions as applicable, by accomplishing all of 

the applicable actions specified in the 

Accomplishment Instructions of the service 

bulletin, except as provided by paragraph (g) 

of this AD. Repeat the related investigative 

actions thereafter at the interval specified in 

Tables 1 and 2 of the service bulletin, as 

applicable. 

Exceptions to the Service Bulletin 

(g) Where Tables 1 and 2 of paragraph 1.E. 

of Boeing Alert Service Bulletin 747–

53A2704, dated October 4, 2007, specify 

counting the compliance time from ‘‘ * * * 

after the date on this service bulletin,’’ this 

AD requires counting the compliance time 

from the effective date of this AD. Where 

Figure 19 of the service bulletin specifies 

doing a ‘‘detailed visual inspection’’ for any 

crack at fastener holes common to the 

stringer, this AD requires doing a detailed 

inspection. In Figure 3 of the service bulletin, 

also inspect the areas at stringer 5 (S–5) and 

S–5A between station (STA) 340 and STA 

360 (similar to Figure 8 for the right side). In 

Figure 15 of the service bulletin, also inspect 

the area at S–14A between STA 200 and STA 

220 (similar to Figure 17 for the right side). 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, ATTN: Ivan 

Li, Aerospace Engineer, Airframe Branch, 

ANM–120S, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6437; 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 747–53A2704, dated October 4, 

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50718 Federal Register / Vol. 73, No. 168 / Thursday, August 28, 2008 / Rules and Regulations 

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 

8, 2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–19378 Filed 8–27–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27339; Directorate 

Identifier 2006–NM–280–AD; Amendment 

39–15654; AD 2008–17–16] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Model DC–10–10 and DC–10–

10F Airplanes, Model DC–10–15 

Airplanes, Model DC–10–30 and DC–

10–30F (KC–10A and KDC–10) 

Airplanes, Model DC–10–40 and DC–

10–40F Airplanes, Model MD–10–10F 

and MD–10–30F Airplanes, and Model 

MD–11 and MD–11F Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

transport category airplanes identified 

above. This AD requires modifying the 

fuel boost pumps. This AD results from 

a fuel boost pump found with blown 

thermal fuses and a fractured thrust 

washer. We are issuing this AD to 

prevent failure of the fuel boost pumps, 

which could lead to the potential of 

ignition sources inside fuel tanks. This 

condition, in combination with 

flammable fuel vapors, could result in 

fuel tank explosions and consequent 

loss of the airplane. 

DATES: This AD becomes effective 

October 2, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 2, 2008. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Long Beach 

Division, 3855 Lakewood Boulevard, 

Long Beach, California 90846, 

Attention: Data and Service 

Management, Dept. C1–L5A (D800–

0024). 

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 address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Samuel Lee, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, 

Los Angeles Aircraft Certification 

Office, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

telephone (562) 627–5262; fax (562) 

627–5210. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a supplemental 

notice of proposed rulemaking (NPRM) 

to amend 14 CFR part 39 to include an 

AD that would apply to certain 

McDonnell Douglas Model DC–10–10 

and DC–10–10F airplanes, Model DC–

10–15 airplanes, Model DC–10–30 and 

DC–10–30F (KC–10A and KDC–10) 

airplanes, Model DC–10–40 and DC–10–

40F airplanes, Model MD–10–10F and 

MD–10–30F airplanes, and Model MD–

11 and MD–11F airplanes. That 

supplemental NPRM was published in 

the Federal Register on March 7, 2008 

(73 FR 12301). That supplemental 

NPRM proposed to require modifying 

the fuel boost pumps. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Support for the Supplemental NPRM 

FedEx agrees with the technical 

aspects of the supplemental NPRM. 

Request to Allow Use of Parts 

Manufacture Approval (PMA) Parts 

Wencor West requests that we revise 

the supplemental NPRM to allow the 

use of PMA part numbers (P/Ns) 60–

84744WE, 60–06561WE, 60–01317WE, 

and 60–02927WE as acceptable means 

of compliance for the replacement of 

Hydro-Aire fuel boost pumps having 

P/Ns 60–84744, 60–06561, 60–01317, 

and 60–02927, respectively. Wencor 

West states that these PMA parts were 

developed through the test and 

computation method governed by 

section 21.303 (‘‘Replacement and 

modification parts’’) of the Federal 

Aviation Regulations (14 CFR 21.303) 

and FAA Order 8110–42B. Wencor West 

also states that the FAA found the PMA 

parts to be equal to and interchangeable 

with the Hydro-Aire parts. In addition, 

Wencor West requests that we clarify 

that certain other PMA parts, which 

may be used when doing further 

maintenance or overhaul of the pump, 

continue to be approved as equivalents 

to the original equipment manufacturer 

parts. 

We disagree with revising this AD. 

Boeing conducted safety assessments of 

the fuel tank systems approved by the 

Los Angeles Aircraft Certification Office 

(ACO). As a result, we issued AD 2008–

06–21, amendment 39–15433 (73 FR 

14673, March 19, 2008), to require 

revising the FAA-approved maintenance 

program to incorporate new 

Airworthiness Limitations for the fuel 

tank systems to satisfy the requirements 

of Special Federal Aviation Regulation 

No. 88. That AD, in part, addressed 

maintenance of the fuel boost pumps. 

Any deviation from the safety 

assessment conducted by Boeing, 

including the use of PMA parts on the 

fuel boost pumps, must be approved by 

the Manager, Los Angeles ACO. 

Consequently, all previously approved 

PMA parts must be re-evaluated to 

determine whether an equivalent level 

of safety for each part meets the 

approved safety assessment. Therefore, 

engineering design approval of the PMA 

parts manufactured by Wencor West 

must be approved as an alternative 

method of compliance (AMOC) under 

the provisions of paragraph (h) of this 

AD. We will consider requests for 

approval of an AMOC if sufficient data 

are submitted to substantiate that the 

design change would provide an 

acceptable level of safety. We have not 

changed the AD in this regard. 

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