Federal Register / Vol. 73, No. 185 / Tuesday, September 23, 2008 / Proposed Rules 54755 

this AD, except for the inspections specified 

in paragraph (r) of this AD. 

Post-Modification Inspection and Repair 

(r) Within 20,000 flight cycles after the 

modification required by paragraph (p) or (q) 

of this AD, as applicable, inspect the BS 2598 

bulkhead for cracks, and repair any crack 

before further flight, in accordance with a 

method approved by the Manager, Seattle 

ACO. 

Open Hole HFEC Inspection(s) and 

Terminating Repair 

(s) For airplanes on which the terminating 

modification required by paragraph (l) or (q) 

of this AD has not been done: Do an initial 

open hole HFEC inspection to detect cracks 

in the bulkhead splice fitting, frame support 

fitting, and forward and aft inner chords on 

the left and right sides of the BS 2598 

bulkhead, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2427, Revision 4, 

dated March 6, 2008. Do the initial 

inspection at the applicable time specified in 

Table 1 or 3 of paragraph 1.E., ‘‘Compliance,’’ 

of 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. 

(1) If no crack is detected, repeat the open 

hole HFEC inspection thereafter at intervals 

not to exceed 1,500 flight cycles. 

(2) If any crack is detected, before further 

flight, repair it in accordance with the service 

bulletin; except, where the service bulletin 

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 (w) of 

this AD. Accomplishment of the aft inner 

chord repair in accordance with the 

applicable SRM specified in the 

Accomplishment Instructions of the service 

bulletin ends the repetitive open hole HFEC 

inspections required by paragraphs (h) and 

(s)(1) of this AD for that side of the bulkhead 

only. 

Interim Modification 

(t) For Group 1 airplanes, as identified in 

Boeing Alert Service Bulletin 747–53A2427, 

Revision 4, dated March 6, 2008, on which 

the terminating modification required by 

paragraph (l) or (q) of this AD has not been 

done: Before the accumulation of 12,000 total 

flight cycles, or within 1,500 flight cycles 

after the effective date of this AD, whichever 

occurs later, install the interim modification 

for the aft inner chords, in accordance with 

the Accomplishment Instructions of the 

service bulletin. Accomplishment of the 

interim modification ends the repetitive open 

hole and surface HFEC inspections required 

by paragraphs (h) and (s)(1) of this AD. 

Post-Interim Modification/Repair Repetitive 

Surface and Open Hole HFEC Inspections 

(u) For airplanes on which the interim 

modification required by paragraph (t) of this 

AD has been done or the repair of any 

cracked aft inner chord has been done in 

accordance with the SRM specified in the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2427, Revision 4, 

dated March 6, 2008, as required by 

paragraph (i) or (s)(2) of this AD; and on 

which the terminating modification required 

by paragraph (l) or (q) of this AD has not been 

done: At the applicable times specified in 

Table 1, 2, or 3 of paragraph 1.E., 

‘‘Compliance,’’ of the service bulletin, do a 

surface HFEC inspection to detect cracks on 

the forward side (unmodified area) of the 

bulkhead and open hole and surface HFEC 

inspections to detect cracks in the modified 

or repaired area, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2427, Revision 4, 

dated March 6, 2008. Repeat the open hole 

and surface HFEC inspections thereafter at 

intervals not to exceed 1,500 flight cycles, 

until the modification required by paragraph 

(q) of this AD is done, as applicable; except, 

for airplanes on which the repair of any 

cracked aft inner chord has been done on 

only one side of the bulkhead in accordance 

with the applicable SRM as required by 

paragraph (i) or (s)(2) of this AD, the 

repetitive open hole and surface HFEC 

inspections required by paragraph (h) and 

(s)(1) of this AD must continue to be done for 

the other side of the bulkhead. 

Repair of Any Cracked Inner Chord, Splice 

Fitting, or Frame Support Fitting 

(v) If any crack is detected during any open 

hole or surface HFEC inspection required by 

paragraph (u) of this AD, before further flight, 

repair any cracked inner chord, splice fitting, 

or frame support fitting, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2427, 

Revision 4, dated March 6, 2008; except, 

where the service bulletin 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 (w) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(w)(1) The Manager, Seattle ACO, FAA, 

ATTN: Ivan Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle ACO, 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. 

(4) AMOCs approved previously in 

accordance with AD 2006–05–06 are 

approved as AMOCs for the corresponding 

provisions of this AD. 

Issued in Renton, Washington, on 

September 11, 2008. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–22215 Filed 9–22–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1006; Directorate 

Identifier 2008–NM–110–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100, 747–100B, 747–200B, 

747–200C, 747–200F, 747–300, 747SR, 

and 747SP 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 747–100, 747–100B, 747– 

200B, 747–200C, 747–200F, 747–300, 

747SR, and 747SP series airplanes. The 

existing AD currently requires an 

inspection to determine if acceptable 

external skin doublers are installed at 

the stringer 6 (S–6) lap splices, between 

station (STA) 340 and STA 400. For 

airplanes without the acceptable 

external skin doublers, the existing AD 

requires repetitive related investigative 

actions and corrective actions if 

necessary. The existing AD also 

provides an optional terminating 

modification for the repetitive related 

investigative actions. This proposed AD 

would mandate the optional terminating 

modification. This proposed AD results 

from a report of cracked fastener holes 

at the right S–6 lap splice between STA 

340 and STA 380. We are proposing this 

AD to prevent cracking in the fuselage 

skin, which could result in rapid 

decompression and loss of structural 

integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 7, 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. 


jlentini on PROD1PC65 with PROPOSALS
54756 Federal Register / Vol. 73, No. 185 / Tuesday, September 23, 2008 / Proposed Rules 

• 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. 

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–2008–1006; Directorate Identifier 

2008–NM–110–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 May 13, 2008, we issued AD 

2008–10–15, amendment 39–15522 

(73 FR 29042, May 20, 2008), for certain 

Boeing Model 747–100, 747–100B, 747– 

200B, 747–200C, 747–200F, 747–300, 

747SR, and 747SP series airplanes. That 

AD requires an inspection to determine 

if acceptable external skin doublers are 

installed at the stringer 6 (S–6) lap 

splices, between station (STA) 340 and 

STA 400. For airplanes without the 

acceptable external skin doublers, that 

AD requires repetitive related 

investigative actions and corrective 

actions if necessary. That AD also 

provides an optional terminating 

modification for the repetitive related 

investigative actions. That AD resulted 

from a report of cracked fastener holes 

at the right S–6 lap splice between STA 

340 and STA 380. We issued that AD to 

detect and correct cracking in the 

fuselage skin, which could result in 

rapid decompression and loss of the 

airplane. 

Actions Since Existing AD Was Issued 

The preamble to AD 2008–10–15 

specifies that we consider the 

requirements ‘‘interim action’’ and that 

we were considering requiring the 

modification (installation of acceptable 

external skin doublers), which would 

terminate the repetitive related 

investigative actions. We now have 

determined that further rulemaking is 

indeed necessary, and this proposed AD 

follows from that determination. 

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 2008– 

10–15 and would retain the 

requirements of the existing AD. This 

proposed AD would also mandate the 

terminating action that was optional in 

AD 2008–10–15. 

Costs of Compliance 

There are about 501 airplanes of the 

affected design in the worldwide fleet. 

This proposed AD would affect about 

174 airplanes of U.S. registry. 

The inspection for acceptable external 

skin doublers that is required by AD 

2008–10–15 and retained in this 

proposed AD takes about 2 work hours 

per airplane, at an average labor rate of 

$80 per work hour. Based on these 

figures, the estimated cost of the 

inspection for U.S. operators is $27,840, 

or $160 per airplane. 

The cost for the proposed terminating 

action depends upon the results of the 

inspections. Therefore, we cannot 

calculate those costs because we do not 

know what doubler conditions operators 

will find. 

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: 


jlentini on PROD1PC65 with PROPOSALS
Federal Register / Vol. 73, No. 185 / Tuesday, September 23, 2008 / Proposed Rules 54757 

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 removing amendment 39–15522 (73 

FR 29042, May 20, 2008) and adding the 

following new airworthiness directive 

(AD): 

Boeing: Docket No. FAA–2008–1006; 

Directorate Identifier 2008–NM–110–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by November 7, 2008. 

Affected ADs 

(b) This AD supersedes AD 2008–10–15. 

Applicability 

(c) This AD applies to Boeing Model 747– 

100, 747–100B, 747–200B, 747–200C, 747– 

200F, 747–300, 747SR, and 747SP series 

airplanes, certificated in any category; as 

identified in Boeing Alert Service Bulletin 

747–53A2748, dated May 9, 2008. 

Unsafe Condition 

(d) This AD results from a report of cracked 

fastener holes at the right stringer 6 (S–6) lap 

splice between station (STA) 340 and STA 

380. We are issuing this AD to prevent 

cracking in the fuselage skin, which could 

result in rapid decompression and loss of 

structural integrity 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. 

Requirements of AD 2008–10–15 

Service Bulletin Reference Paragraph 

(f) The term ‘‘alert service bulletin,’’ as 

used in this AD, means the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2748, dated May 9, 2008. 

Inspection for Acceptable External Skin 

Doublers 

(g) For airplanes identified as Group 1, 

Configuration 2, in Boeing Alert Service 

Bulletin 747–53A2748, dated May 9, 2008: At 

the latest of the times specified in paragraphs 

(g)(1), (g)(2), and (g)(3) of this AD, do an 

external general visual inspection to 

determine if acceptable external skin 

doublers are installed at the left- and rightside S–6 lap splices, in accordance with Part 

1 of the alert service bulletin. 

(1) Prior to the accumulation of 10,000 

total flight cycles. 

(2) Within 8,000 flight cycles after a 

modification was done in accordance with 

Boeing Service Bulletin 747–53–2253. 

(3) Within 15 days or 100 flight cycles after 

May 20, 2008 (the effective date of AD 2008– 

10–15), whichever occurs first. 

Acceptable External Skin Doublers Found at 

Both Sides 

(h) If, during the inspection required by 

paragraph (g) of this AD, acceptable external 

skin doublers in accordance with the alert 

service bulletin are found installed at both 

the left- and right-side S–6 lap splices, no 

further work is required by this AD. 

Acceptable External Skin Doublers Not 

Found—Repetitive Related Investigative 

Actions and Corrective Actions 

(i) If, during the inspection required by 

paragraph (g) of this AD, acceptable external 

skin doublers in accordance with alert 

service bulletin are not found installed at 

either the left- or right-side S–6 lap splice: 

Before further flight, do all applicable related 

investigative and corrective actions by doing 

all actions specified in Part 2 of the alert 

service bulletin. Repeat the applicable related 

investigative actions thereafter at intervals 

not to exceed 300 flight cycles until the 

modification specified in paragraph (j) of this 

AD is done. 

New Requirement of This AD 

Terminating Modification 

(j) If, during the inspection required by 

paragraph (g) of this AD, acceptable external 

skin doublers as specified in the alert service 

bulletin are not found installed at either the 

left- or right-side S–6 lap splice: Within 3,000 

flight cycles after doing the initial related 

investigative actions in paragraph (i) of this 

AD, or within 300 flight cycles after the 

effective date of this AD, whichever occurs 

later, install acceptable external skin 

doublers at both the left- and right-side S–6 

lap splices, as applicable. The installation of 

the acceptable skin doublers is required on 

the side of the airplane that does not have the 

doublers already. The installation includes 

doing an open-hole high-frequency eddy 

current (HFEC) inspection of the skin for 

cracking, and trimming out cracking as 

applicable. Do all actions in accordance with 

the alert service bulletin. Doing this 

installation terminates the repetitive related 

investigative actions required by paragraph 

(i) of this AD. 

Note 1: The alert service bulletin refers to 

Boeing Service Bulletins 747–53–2253, 

Revision 3, dated March 24, 1994; and 747– 

53–2272, Revision 18, dated May 16, 2002; as 

additional sources of service information for 

accomplishment of the modification 

(installation of acceptable external skin 

doublers). 

Note 2: AD 90–06–06, amendment 39– 

6490, requires, among other actions, a 

modification as specified in Boeing Service 

Bulletin 747–53–2253, dated December 14, 

1984. 

Note 3: AD 90–23–14, amendment 39– 

6801, requires inspections as specified in 

Boeing Service Bulletin 747–53–2253, 

Revision 2, dated March 29, 1990. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, ATTN: Ivan 

Li, Aerospace Engineer, Airframe Branch, 

ANM–120S, FAA, Seattle ACO, 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. 

(4) AMOCs approved previously in 

accordance with AD 2008–10–15 are 

approved as AMOCs for the corresponding 

provisions of this AD. 

Issued in Renton, Washington, on 

September 12, 2008. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–22211 Filed 9–22–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 165 

[Docket No. USCG–2008–0070] 

RIN 1625–AA87 

Security Zone; Port of Mayaguez, 

Puerto Rico 

AGENCY: Coast Guard, DHS. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The Coast Guard proposes to 

establish moving and fixed security 

zones around cruise ships entering, 

departing, mooring or anchoring at the 

Port of Mayaguez, Puerto Rico. This 

proposed regulation is necessary to 

protect cruise ships operating in this 

port. All vessels, with the exception of 

servicing pilot boat and assisting tug 

boats, would be prohibited from 

entering the security zones without the 

express permission of the Captain of the 

Port San Juan or a designated 

representative. 

DATES: Comments and related material 

must reach the Coast Guard on or before 

November 24, 2008. 


jlentini on PROD1PC65 with PROPOSALS