Federal Register / Vol. 78, No. 44 / Wednesday, March 6, 2013 / Proposed Rules 14469 

determine whether an affected sailplane is 

equipped with aluminum alloy spar booms. 

(2) If any corrosion or delamination 

damage is found during the inspection 

required by paragraph (f)(1) of this AD, before 

further flight, contact the manufacturer at the 

address specified in paragraph (i) of this AD 

to obtain an FAA-approved repair scheme 

and incorporate the repair. 

(g) New Actions and Compliance 

(1) Within 5 years after the last inspection 

required by AD 98–22–15, Amendment 39– 

10863 (63 FR 58624, November 2, 1998) and 

repetitively thereafter at intervals not to 

exceed 12 months, using an endoscope, 

inspect the aluminum alloy spar booms and 

the wing attach fittings for delamination or 

corrosion damage following paragraph 11. of 

the ACTION section of Slingsby Aviation 

Ltd. Technical Instruction T.I. No. 109/T51, 

Issue 3, dated August 21, 2000. 

(2) If any corrosion or delamination 

damage is found during any inspection 

required by paragraph (g)(1) of this AD, 

before further flight, contact the 

manufacturer at the address specified in 

paragraph (i) of this AD to obtain an FAAapproved repair scheme and incorporate the 

repair. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

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: Jim Rutherford, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 329– 

4090; email: jim.rutherford@faa.gov. Before 

using any approved AMOC on any sailplane 

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. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, a federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(i) Related Information 

Refer to Civil Aviation Authority (CAA) 

AD British AD 005–09–97, dated October 3, 

1997; Slingsby Aviation Ltd. Technical 

Instruction T.I. No. 109/T51, Issue No. 2, 

dated October 7, 1997; and Slingsby Aviation 

Ltd. Technical Instruction T.I. No. 109/T51, 

Issue 3, dated August 21, 2000, for related 

information. For service information related 

to this AD, contact Slingsby Advanced 

Composites Ltd., Ings Lane, Kirkbymoorside, 

North Yorkshire, England YO62 6EZ ; 

telephone: +44(0)1751 432474; Internet: 

none. You may review copies of the 

referenced service information at the FAA, 

Small Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For information 

on the availability of this material at the 

FAA, call (816) 329–4148. 

Issued in Kansas City, Missouri, on 

February 27, 2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–05229 Filed 3–5–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0097; Directorate 

Identifier 2011–NM–243–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–200F, 747–300, 747–400, 747– 

400D, 747–400F, and 747SR series 

airplanes. The existing AD currently 

requires repetitive inspections to find 

cracking of the web, strap, inner chords, 

inner chord angle of the forward edge 

frame of the number 5 main entry door 

cutouts, the frame segment between 

stringers 16 and 31, and repair if 

necessary; and repetitive inspections for 

cracking of repairs. Since we issued that 

AD, we have received multiple reports 

of cracking outside of the previous 

fuselage inspection areas and a report of 

a crack that initiated at the aft edge of 

the inner chord rather than initiating at 

a fastener location, which was the 

previous cracking location. This 

proposed AD would expand the 

previous fuselage areas that are 

inspected for cracking. We are 

proposing this AD to detect and correct 

such cracks, which could cause damage 

to the adjacent body structure and could 

result in depressurization of the 

airplane in flight. 

DATES: We must receive comments on 

this proposed AD by April 22, 2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above 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, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https:// 

www.myboeingfleet.com. You may 

review copies of the service information 

at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

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 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6428; 

fax: 425–917–6590; email: 

Nathan.P.Weigand@faa.gov. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
14470 Federal Register / Vol. 78, No. 44 / Wednesday, March 6, 2013 / Proposed Rules 

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–2013–0097; Directorate Identifier 

2011–NM–243–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 15, 2010, we issued AD 

2010–20–08, Amendment 39–16442 (75 

FR 61337, October 5, 2010), for certain 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747–400, 747–400D, 747– 

400F, and 747SR series airplanes. That 

AD requires repetitive inspections to 

find cracking of the web, strap, inner 

chords, inner chord angle of the forward 

edge frame of the number 5 main entry 

door cutouts, the frame segment 

between stringers 16 and 31, and repair 

if necessary; and repetitive inspections 

for cracking of repairs. That AD resulted 

from additional reports of cracks that 

have been found in the strap and inner 

chord of the forward edge frame of the 

number 5 main entry door cutouts, 

between stringers 16 and 23. We issued 

that AD to detect and correct such 

cracks, which could cause damage to 

the adjacent body structure and could 

result in depressurization of the 

airplane in flight. 

Actions Since Existing AD (75 FR 

61337, October 5, 2010) Was Issued 

Since we issued AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, 

October 5, 2010), we have received 

multiple reports of cracking outside of 

the previous fuselage inspection areas 

and a report of a crack that initiated at 

the aft edge of the inner chord rather 

than initiating at a fastener location, 

which was the previous cracking 

location. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 747–53A2450, Revision 7, 

dated November 2, 2011. For 

information on the procedures and 

compliance times, see this service 

information at http:// 

www.regulations.gov by searching for 

Docket No. FAA–2013–0097. 

FAA’s Determination 

We are proposing 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 same 

type design. 

Proposed AD Requirements 

This proposed AD would retain all 

requirements of AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, 

October 5, 2010). This proposed AD 

would also expand the previous 

fuselage areas that are inspected for 

cracking. 

The phrase ‘‘related investigative 

actions’’ might be used in this proposed 

AD. ‘‘Related investigative actions’’ are 

follow-on actions that: (1) Are related to 

the primary actions, and (2) are actions 

that further investigate the nature of any 

condition found. Related investigative 

actions in an AD could include, for 

example, inspections. 

In addition, the phrase ‘‘corrective 

actions’’ might be used in this proposed 

AD. ‘‘Corrective actions’’ are actions 

that correct or address any condition 

found. Corrective actions in an AD 

could include, for example, repairs. 

Difference Between the Proposed AD 

and Relevant Service Information 

Boeing Alert Service Bulletin 747– 

53A2450, Revision 7, dated November 

2, 2011, specifies to contact the 

manufacturer for instructions on how to 

repair certain conditions, but this 

proposed AD would require repairing 

those conditions in one of the following 

ways: 

• Using a method that we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by an 

Authorized Representative for the 

Boeing Commercial Airplanes 

Delegation Option Authorization 

Organization whom we have authorized 

to make those findings. 

Costs of Compliance 

We estimate that this proposed AD 

affects 151 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspections [retained actions from AD 

2010-20–08, Amendment 39–16442 (75 

FR 61337, October 5, 

2010)].

Up to 44 work-hours × $85 per hour = $3,740 

per inspection cycle.

$0 Up to $3,740 per inspection cycle.Up to $564,740 per inspection cycle. 

Inspections [new proposed action].Up to 121 work-hours × $85 per hour = 

$10,285 per inspection cycle.

0 Up to $10,285 per inspection cycle.Up to $1,553,035 per 

inspection cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed 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. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 44 / Wednesday, March 6, 2013 / Proposed Rules 14471 

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), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) 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. 

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: 

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 airworthiness directive (AD) 

2010–20–08, Amendment 39–16442 (75 

FR 61337, October 5, 2010), and adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2013–0097; Directorate Identifier 2011– 

NM–243–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by April 22, 2013. 

(b) Affected ADs 

This AD supersedes AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, October 

5, 2010). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, 747–100B, 747–100B SUD, 

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

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

series airplanes, certificated in any category, 

having line numbers 1 through 1419 

inclusive; except for Model 747–400 series 

airplanes that have been modified into the 

Model 747–400 large cargo freighter 

configuration. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by multiple reports 

of cracking outside of the previous inspection 

areas and a report of a crack that initiated at 

the aft edge of the inner chord rather than 

initiating at a fastener location. We are 

issuing this AD to detect and correct such 

cracks, which could cause damage to the 

adjacent body structure and could result in 

a rapid depressurization of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Repetitive Inspections for 

Frame Segment Between Stringers 23 and 31 

(No Terminating Action) 

This paragraph restates the requirements of 

paragraph (g) of AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, October 

5, 2010). For airplanes having line numbers 

1 through 1304 inclusive: Inspect the 

airplane for cracks between stringers 23 and 

31 per Boeing Alert Service Bulletin 747– 

53A2450, Revision 2, including Appendix A, 

dated January 4, 2001; or Boeing Alert 

Service Bulletin 747–53A2450, Revision 5, 

dated January 29, 2009; at the later of the 

applicable times specified in paragraph (h) or 

(i) of this AD, per table 1 to paragraphs (g) 

and (h) of this AD, as follows. Where there 

are differences between the AD and Boeing 

Alert Service Bulletin 747–53A2450, 

Revision 2, including Appendix A, dated 

January 4, 2001; or Boeing Alert Service 

Bulletin 747–53A2450, Revision 5, dated 

January 29, 2009: the AD prevails. 

TABLE 1 TO PARAGRAPHS (G) AND (H) OF THIS AD—INSPECTION REQUIREMENTS

Type of inspection Area to inspect 

(1) Detailed Visual ........... Strap inner chords forward and aft of the web, and exposed web adjacent to the inner chords on station 2231 frame 

from stringers 23 through 31 per Figure 5 or Figure 6 of the service bulletins specified in paragraph (g) or (h) of 

this AD, as applicable. 

(2) Surface High Frequency Eddy Current 

(HFEC).

Station 2231 inner chord angles at lower main sill interface per Figure 5 or Figure 6 of the service bulletins specified 

in paragraph (g) or (h) of this AD, as applicable. 

(3) Open Hole HFEC ....... Station 2231 frame fastener locations per Figures 4 and 7, and either Figure 5 or 6 of the service bulletins specified 

in paragraph (g) or (h) of this AD, as applicable. 

(4) Surface HFEC ............ Around fastener locations on station 2231 inner chords from stringers 23 through 31 per Figure 5 or Figure 6 of the 

service bulletins specified in paragraph (g) or (h) of this AD, as applicable. 

(5) Low Frequency Eddy 

Current (LFEC).

Station 2231 frame strap in areas covered by the reveal per Figure 5 or Figure 6 of the service bulletins specified in 

paragraph (g) or (h) of this AD, as applicable. 

Note 1 to paragraph (g) of this AD: There 

is no terminating action currently available 

for the inspections required by paragraph (g) 

of this AD. 

(h) Retained Compliance Times 

This paragraph restates the requirements of 

paragraph (h) of AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, October 

5, 2010). Do the inspections specified in 

paragraph (g) of this AD at the applicable 

times specified in paragraph (h)(1) or (h)(2) 

of this AD. Repeat the inspections at intervals 

not to exceed 3,000 flight cycles until the 

inspections required by paragraph (m) or (o) 

of this AD are done. Where there are 

differences between the AD and Boeing Alert 

Service Bulletin 747–53A2450, Revision 2, 

including Appendix A, dated January 4, 

2001; or Boeing Alert Service Bulletin 747– 

53A2450, Revision 5, dated January 29, 2009: 

the AD prevails. 

(1) Do the inspections per table 1 to 

paragraphs (g) and (h) of this AD at the 

applicable time specified in the logic diagram 

in Figure 1 of Boeing Alert Service Bulletin 

747–53A2450, Revision 2, including 

Appendix A, dated January 4, 2001. Where 

the compliance time in the logic diagram 

specifies a compliance time beginning ‘‘from 

receipt of this service bulletin,’’ this AD 

requires that the compliance time begin 

‘‘after September 12, 2001 (the effective date 

of AD 2001–16–02, Amendment 39–12370 

(66 FR 41440, August 8, 2001)).’’ 

(2) After November 9, 2010 (the effective 

date of AD 2010–20–08, Amendment 39– 

16442 (75 FR 61337, October 5, 2010)), do the 

inspections per table 1 to paragraphs (g) and 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
14472 Federal Register / Vol. 78, No. 44 / Wednesday, March 6, 2013 / Proposed Rules 

(h) of this AD at the applicable compliance 

time specified in paragraph 1.E., 

‘‘Compliance’’ of Boeing Alert Service 

Bulletin 747–53A2450, Revision 5, dated 

January 29, 2009. Where the compliance time 

in Boeing Alert Service Bulletin 747– 

53A2450, Revision 2, including Appendix A, 

dated January 4, 2001, specifies a compliance 

time beginning ‘‘after the date on Revision 2 

of this service bulletin,’’ this AD requires that 

the compliance time begin ‘‘after September 

12, 2001 (the effective date of AD 2001–16– 

02, Amendment 39–12370 (66 FR 41440, 

August 8, 2001)).’’ 

(i) Retained Repetitive Inspections for Frame 

Segment Between Stringers 23 and 31 

This paragraph restates the requirements of 

paragraph (i) of AD 2010–20–08, Amendment 

39–16442 (75 FR 61337, October 5, 2010). 

Within 3,000 flight cycles after 

accomplishment of the inspections specified 

in Figure 1 of Boeing Alert Service Bulletin 

747–53A2450, dated May 4, 2000; or Boeing 

Alert Service Bulletin 747–53A2450, 

Revision 1, dated July 6, 2000; repeat the 

inspections specified in paragraph (g) of this 

AD at intervals not to exceed 3,000 flight 

cycles until the inspections required by 

paragraph (m) or (o) of this AD are done. 

Where there are differences between the AD 

and Boeing Alert Service Bulletin 747– 

53A2450, Revision 2, dated January 4, 2001; 

or Boeing Alert Service Bulletin 747– 

53A2450, Revision 5, dated January 29, 2009: 

the AD prevails. 

(j) Retained Additional Repetitive 

Inspections (for Frame Segment Between 

Stringers 16 and 23) 

This paragraph restates the requirements of 

paragraph (j) of AD 2010–20–08, Amendment 

39–16442 (75 FR 61337, October 5, 2010). 

(1) For all airplanes: Before the 

accumulation of 16,000 total flight cycles, or 

within 1,500 flight cycles after November 9, 

2010 (the effective date of AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, October 

5, 2010)), whichever occurs later, do a 

detailed inspection, an open hole HFEC 

inspection, a surface HFEC inspection, and a 

subsurface LFEC inspection for cracking of 

the forward edge frame of the number 5 main 

entry door cutouts, at station 2231, between 

stringers 16 and 23; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2450, Revision 5, 

dated January 29, 2009. Repeat the 

inspections thereafter at intervals not to 

exceed 3,000 flight cycles. 

(2) The part number of the nut for fastener 

code ‘‘K’’ in Figure 7 of Boeing Alert Service 

Bulletin 747–53A2450, Revision 5, dated 

January 29, 2009, should be 

‘‘BACN10JC3CD,’’ instead of 

‘‘BACB30JC3CD.’’ In addition, the part 

number of the optional nut for this fastener 

code should be ‘‘BACN10YR3CD,’’ instead of 

‘‘BACN10YR4CD’’ in Boeing Alert Service 

Bulletin 747–53A2450, Revision 5, dated 

January 29, 2009. 

(k) Retained Repetitive Inspections for Line 

Numbers 1305 and On (for Frame Segment 

Between Stringers 23 and 31) 

This paragraph restates the requirements of 

paragraph (k) of AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, October 

5, 2010). For airplanes having line numbers 

1305 and on: Before the accumulation of 

16,000 total flight cycles, or within 1,500 

flight cycles after November 9, 2010 (the 

effective date of AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, October 

5, 2010)), whichever occurs later, do a 

detailed inspection, an open hole HFEC 

inspection, a surface HFEC inspection, and a 

subsurface LFEC inspection for cracking of 

the forward edge frame of the number 5 main 

entry door cutouts, at station 2231, between 

stringers 23 and 31; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2450, Revision 5, 

dated January 29, 2009. Repeat the 

inspections thereafter at intervals not to 

exceed 3,000 flight cycles. 

(l) Retained Corrective Action for 

Paragraphs (g), (j), and (k) of This AD 

This paragraph restates the requirements of 

paragraph (l) of AD 2010–20–08, Amendment 

39–16442 (75 FR 61337, October 5, 2010). If 

any crack is found during any inspection 

required by paragraph (g), (j), or (k) of this 

AD, before further flight, repair the crack in 

accordance with a method approved by the 

Manager, Seattle Aircraft Certification Office 

(ACO), FAA, in accordance with data 

meeting the type certification basis of the 

airplane approved by the Boeing Commercial 

Airplanes Organization Designation 

Authorization (ODA) that has been 

authorized by the Manager, Seattle ACO, to 

make those findings; or in accordance with 

Boeing Alert Service Bulletin 747–53A2450, 

Revision 5, dated January 29, 2009; as 

applicable. For a repair method to be 

approved by the Manager, Seattle ACO, as 

required by this paragraph, the approval 

letter must specifically reference this AD. As 

of November 9, 2010 (the effective date of AD 

2010–20–08), repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (s) of this AD. 

(m) Retained Post-Repair Inspections 

This paragraph restates the requirements of 

paragraph (m) of AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, October 

5, 2010). Except as required by paragraph (n) 

of this AD, for airplanes on which the 

forward edge frame of the number 5 main 

entry door cutouts, at station 2231, between 

stringers 16 and 31, is repaired as specified 

in Boeing Alert Service Bulletin 747– 

53A2450: Within 3,000 flight cycles after 

doing the repair or within 1,500 flight cycles 

after November 9, 2010 (the effective date of 

AD 2010–20–08), whichever occurs later, do 

the detailed, LFEC, and HFEC inspections of 

the repaired area for cracks, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2450, 

Revision 5, dated January 29, 2009. If no 

cracking is found, repeat the inspections 

thereafter at intervals not to exceed 3,000 

flight cycles. If any crack is found: Before 

further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (s) of this AD. Doing 

the inspections specified in paragraph (m) of 

this AD terminates the repetitive inspections 

required by paragraphs (g), (h), (i), (j), and (k) 

of this AD for the repaired area. 

(n) Retained Post-Repair Inspection 

Restriction 

This paragraph restates the requirements of 

paragraph (n) of AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, October 

5, 2010). For any frame that is repaired in 

accordance with a method other than the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2450, Revision 5, 

dated January 29, 2009: Do the inspection in 

accordance with a method approved in 

accordance with the procedures specified in 

paragraph (s) of this AD. 

(o) New Repetitive Inspections With 

Expanded Inspection Area 

Before the accumulation of 16,000 total 

flight cycles, or within 3,000 flight cycles 

after the effective date of this AD, whichever 

occurs later, do the inspections required by 

paragraphs (o)(1) through (o)(5) of this AD, 

except as specified in paragraph (p) of this 

AD. Do all actions required by this paragraph 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2450, Revision 7, dated November 2, 

2011. Repeat the inspections thereafter at the 

applicable times specified in Paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2450, Revision 7, dated 

November 2, 2011. Accomplishment of the 

initial inspections required by this paragraph 

terminates the requirements of paragraphs (g) 

through (k) of this AD. 

(1) Do a detailed inspection for cracking on 

the frame strap, inner chords forward and aft 

of the web, and exposed web adjacent to the 

inner chords from stringer 15 to 31. 

(2) Do an HFEC inspection of the station 

2231 frame fastener locations for cracking 

from stringer 16 to 31, including locations 

common to the upper main sill strap and 

stringer clip at stringer 16. 

(3) Do an HFEC inspection for cracking of 

the frame inner chords around the fastener 

heads from stringer 15 to 31. 

(4) Do an HFEC inspection for cracking of 

the aft edge of the aft inner chord, of the 

forward edge of the forward inner chord, and 

of the forward and aft edges of the frame 

strap from stringer 15 to 31. 

(5) Do an LFEC inspection for cracking of 

the station 2231 frame strap from stringer 16 

to 31 in areas covered by the reveal. 

(p) New Post-Repair Inspection for Repaired 

Areas 

For airplanes on which the post-repair 

inspections are being done as specified in 

paragraph (m) of this AD: For the repaired 

area only, continue the inspections as 

specified in paragraph (m) of this AD in lieu 

of the inspections specified in paragraph (o) 

of this AD. 

(q) New Corrective Action 

If any cracking is found during any 

inspection required by paragraph (o), (p), or 

(r) of this AD: Before further flight, repair the 

cracking using a method approved in 

accordance with the procedures specified in 

paragraph (s) of this AD. 

(r) New Post-Repair Repetitive Inspections 

and Corrective Action 

For any airplane repaired as specified in 

paragraph (q) of this AD: Within 3,000 flight 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 44 / Wednesday, March 6, 2013 / Proposed Rules 14473 

cycles after doing the repair, do detailed, 

LFEC, and HFEC inspections of the repaired 

area for cracking, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2450, Revision 7, 

dated November 2, 2011. If no cracking is 

found, repeat the inspections thereafter at 

intervals not to exceed 3,000 flight cycles. If 

any cracking is found: Before further flight, 

do the actions specified in paragraph (q) of 

this AD. 

(s) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(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 the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that 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 2010–20–08, 

Amendment 39–16442 (75 FR 61337, October 

5, 2010), are approved as AMOCs for the 

corresponding provisions of paragraphs (g) 

through (m) of this AD. 

(5) AMOCs approved previously in 

accordance with AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, October 

5, 2010), that have post-repair inspections, 

are approved as AMOCs for the 

corresponding provisions of paragraph (o) of 

this AD for the repaired area only. 

(t) Related Information 

(1) For more information about this AD, 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6428; fax: 425–917–6590; 

email: Nathan.P.Weigand@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

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, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on February 

25, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–05178 Filed 3–5–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2012–1334; Airspace 

Docket No. 12–ASO–18] 

Proposed Establishment of Class E 

Airspace; Sanibel, FL 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

establish Class E Airspace at Sanibel, 

FL, to accommodate a new Area 

Navigation (RNAV) Global Positioning 

System (GPS) special Standard 

Instrument Approach Procedure (SIAP) 

serving Sanibel Island Heliport. This 

action would enhance the safety and 

airspace management of Instrument 

Flight Rules (IFR) operations within the 

National Airspace System. 

DATES: Comments must be received on 

or before April 22, 2013. 

ADDRESSES: Send comments on this rule 

to: U.S. Department of Transportation, 

Docket Operations, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey, SE., Washington, DC 

20590–0001; Telephone: 1–800–647– 

5527; Fax: 202–493–2251. You must 

identify the Docket Number FAA–2012– 

1334; Airspace Docket No. 12–ASO–18, 

at the beginning of your comments. You 

may also submit and review received 

comments through the Internet at 

http://www.regulations.gov. 

FOR FURTHER INFORMATION CONTACT: John 

Fornito, Operations Support Group, 

Eastern Service Center, Federal Aviation 

Administration, P.O. Box 20636, 

Atlanta, Georgia 30320; telephone (404) 

305–6364. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested persons are invited to 

comment on this rule by submitting 

such written data, views, or arguments, 

as they may desire. Comments that 

provide the factual basis supporting the 

views and suggestions presented are 

particularly helpful in developing 

reasoned regulatory decisions on the 

proposal. Comments are specifically 

invited on the overall regulatory, 

aeronautical, economic, environmental, 

and energy-related aspects of the 

proposal. 

Communications should identify both 

docket numbers (FAA Docket No. FAA– 

2012–1334; Airspace Docket No. 12– 

ASO–18) and be submitted in triplicate 

to the Docket Management System (see 

ADDRESSES section for address and 

phone number). You may also submit 

comments through the Internet at 

http://www.regulations.gov. 

Persons wishing the FAA to 

acknowledge receipt of their comments 

on this action must submit with those 

comments a self-addressed stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket No. FAA–2012–1334; Airspace 

Docket No. 12–ASO–18.’’ The postcard 

will be date/time stamped and returned 

to the commenter. 

All communications received before 

the specified closing date for comments 

will be considered before taking action 

on the proposed rule. The proposal 

contained in this notice may be changed 

in light of the comments received. A 

report summarizing each substantive 

public contact with FAA personnel 

concerned with this rulemaking will be 

filed in the docket. 

Availability of NPRMs 

An electronic copy of this document 

may be downloaded from and 

comments submitted through http:// 

www.regulations.gov. Recently 

published rulemaking documents can 

also be accessed through the FAA’s Web 

page at http://www.faa.gov/ 

airports_airtraffic/air_traffic/ 

publications/airspace_amendments/. 

You may review the public docket 

containing the proposal, any comments 

received and any final disposition in 

person in the Dockets Office (see the 

ADDRESSES section for address and 

phone number) between 9:00 a.m. and 

5:00 p.m., Monday through Friday, 

except Federal holidays. An informal 

docket may also be examined during 

normal business hours at the office of 

the Eastern Service Center, Federal 

Aviation Administration, Room 350, 

1701 Columbia Avenue, College Park, 

Georgia 30337. 

Persons interested in being placed on 

a mailing list for future NPRM’s should 

contact the FAA’s Office of Rulemaking, 

(202) 267–9677, to request a copy of 

Advisory circular No. 11–2A, Notice of 

Proposed Rulemaking distribution 

System, which describes the application 

procedure. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS