Federal Register / Vol. 75, No. 248 / Tuesday, December 28, 2010 / Rules and Regulations 81427 

(5) Revise the Operating Limitations 

section of the RFM by inserting a copy of this 

AD into the appropriate section of the RFM. 

(b) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Manager, Boston Aircraft 

Certification Office, FAA, Attn: Tony Pigott, 

Aviation Safety Engineer, 12 New England 

Executive Park, Burlington, MA 01803, 

telephone (781) 238–7158, fax (781) 238– 

7170. 

(c) The Joint Aircraft System/Component 

(JASC) Code is 3420: Navigation. 

(d) Installing the placards shall be done by 

following the specified portions of Sikorsky 

Alert Service Bulletin No. 76–34–11, dated 

May 17, 2010. The Director of the Federal 

Register approved this incorporation by 

reference in accordance with 5 U.S.C. 552(a) 

and 1 CFR part 51. Copies may be obtained 

from Sikorsky Aircraft Corporation, Attn: 

Manager, Commercial Technical Support, 

mailstop s581a, 6900 Main Street, Stratford, 

CT, telephone (203) 383–4866, e-mail address 

tsslibrary@sikorsky.com, or at http://www.

sikorsky.com. Copies may be inspected at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas, 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. 

(e) This amendment becomes effective on 

January 12, 2011. 

Issued in Fort Worth, Texas, on December 

13, 2010. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–31962 Filed 12–27–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0232; Directorate 

Identifier 2009–NM–032–AD; Amendment 

39–16549; AD 2010–26–10] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–200C, –200F, 

–400, –400D, and –400F Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Model 747– 

200C, –200F, –400, –400D, and –400F 

series airplanes. That AD currently 

requires repetitive inspections for cracks 

in the overlapping (upper) skin of the 

upper fastener row of the lap joints of 

the fuselage skin in sections 41, 42, and 

46; and related investigative and 

corrective actions, if necessary. This 

new AD expands the inspection area in 

the existing AD, and adds a 

modification of certain lap joints and 

certain post-repair inspections of the lap 

joints. Accomplishing the modification 

would end the repetitive inspections 

required by the existing AD for the 

length of lap joint that is modified. This 

AD results from a structural review of 

affected skin lap joints for widespread 

fatigue damage. We are issuing this AD 

to prevent fatigue cracking in certain lap 

joints, which could result in rapid 

depressurization of the airplane. 

DATES: This AD becomes effective 

February 1, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of February 1, 2011. 

On April 13, 2006 (71 FR 12122, 

March 9, 2006), the Director of the 

Federal Register approved the 

incorporation by reference of a certain 

other publication listed in the AD. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

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

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. 

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: 

Nicholas Han, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6449; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2006–05–09, 

Amendment 39–14506 (71 FR 12122, 

March 9, 2006). The existing AD applies 

to certain Model 747–200C, –200F, 

–400, –400D, and –400F series 

airplanes. That NPRM was published in 

the Federal Register on March 18, 2010 

(75 FR 13046). That NPRM proposed to 

continue to require repetitive 

inspections for cracks in the 

overlapping (upper) skin of the upper 

fastener row of the lap joints of the 

fuselage skin in Sections 41, 42, and 46; 

and related investigative and corrective 

actions, if necessary. That NPRM also 

proposed to expand the inspection area 

in the existing AD, and add a 

modification of certain lap joints and 

certain post-repair inspections of the lap 

joints. Accomplishing the modification 

would end the repetitive inspections 

required by the existing AD. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been received on the NPRM. 

Request To Revise Certain Language in 

Paragraph (k) of the NPRM 

Boeing asked that we revise the 

language in paragraph (k) of the NPRM 

to indicate that additional actions are 

required in the area of the modification 

for operation beyond 15,000 total flight 

cycles after doing the proposed 

modification. Boeing stated that 

Revision 2 of Boeing Alert Service 

Bulletin 747–53A2499 is currently in 

work at the Boeing Company, and that 

Revision 2 recommends accomplishing 

additional actions after doing the 

modification. 

Since this comment was submitted, 

we have received and reviewed Boeing 

Service Bulletin 747–53A2499, Revision 

2, dated August 12, 2010. Boeing Alert 

Service Bulletin 747–53A2499, dated 

August 11, 2005; and Revision 1, dated 

October 30, 2008; were referred to in the 

NPRM as the appropriate source of 

service information for accomplishing 

the actions. No more work is necessary 

for airplanes on which Boeing Alert 

Service Bulletin 747–53A2499, Revision 

1, dated October 30, 2008, was used for 

doing the required actions. Revision 2 of 

this service bulletin moves certain 

airplanes from Group 1 to Groups 15 

and 16, adds post-modification actions, 

and contains editorial changes. 

We have revised paragraphs (c), (g), 

(h), (i), (j), and (k) of this AD to refer to 


srobinson on DSKHWCL6B1PROD with RULES
81428 Federal Register / Vol. 75, No. 248 / Tuesday, December 28, 2010 / Rules and Regulations 

Boeing Service Bulletin 747–53A2499, 

Revision 2, dated August 12, 2010. In 

addition, we have removed Notes 1 and 

2 of this AD since that information is 

incorporated into Boeing Service 

Bulletin 747–53A2499, Revision 2, 

dated August 12, 2010. We have also 

added a new paragraph (n) to the AD to 

give credit for accomplishing the 

specified actions in accordance with 

Boeing Alert Service Bulletin 747– 

53A2499, Revision 1, dated October 30, 

2008. 

Although Boeing Service Bulletin 

747–53A2499, Revision 2, dated August 

12, 2010, includes post-modification 

actions, this AD will not mandate those 

actions. The threshold for the skin lap 

joint modification mandated by this AD 

is 30,000 total flight cycles. Adding 

15,000 flight cycles to the threshold 

would extend the compliance time for 

the recommended additional actions to 

45,000 total flight cycles. We have 

determined that it is highly unlikely 

that a Model 747 airplane will reach 

that number of total flight cycles. This 

determination also takes into 

consideration the proposed wide spread 

fatigue damage (WFD) operating rules 

imposing operating limits that could be 

significantly lower than 45,000 total 

flight cycles. 

In light of these factors, we have 

determined that this final rule must be 

issued without any further delay due to 

the severity of the unsafe condition 

addressed by this AD. Further 

rulemaking might be issued in the 

future to mandate the additional actions 

included in Boeing Service Bulletin 

747–53A2499, Revision 2, dated August 

12, 2010. We have not changed the AD 

in this regard. 

Request To Delay AD Pending New 

Service Information 

Japan Airlines (JAL) asked that we 

delay issuance until the manufacturer 

can release Revision 2 of Boeing Alert 

Service Bulletin 747–53A2499. JAL 

stated that Boeing has issued Service 

Bulletin Information Notices 747– 

53A2499 IN 01, dated April 2, 2009; and 

747–53A2499 IN 02, dated September 

10, 2009; to Boeing Alert Service 

Bulletin 747–53A2499, Revision 1, 

dated October 30, 2008, to notify 

operators of a typo and revised 

drawings. JAL noted that operators 

cannot accomplish a correct inspection 

and modification unless the information 

provided in Boeing Service Bulletin 

Information Notices 747–53A2499 IN 01 

and 747–53A2499 IN 02 is used. JAL 

added that including Revision 2 of this 

service bulletin would reduce 

unnecessary burden on both operators 

and the manufacturer. 

All Nippon Airways (ANA) also asked 

that the modification be done in 

accordance with Revision 2 of Boeing 

Alert Service Bulletin 747–53A2499 

instead of Boeing Alert Service Bulletin 

747–53A2499, Revision 1, dated 

October 30, 2008. ANA stated that it has 

already performed the terminating 

modification at stringer 6 using Boeing 

Alert Service Bulletin 747–53A2499, 

Revision 1, and had to request AMOCs 

during the modification because certain 

drawings in Boeing Alert Service 

Bulletin 747–53A2499, dated August 11, 

2005; and Revision 1, dated October 30, 

2008; were not specific to the 

modification. ANA added that this will 

reduce the AMOC requests to this 

proposed AD, in addition to reducing 

the maintenance burden. 

We partially agree with the 

commenters. We do not agree to delay 

this AD, due to the severity of the 

unsafe condition. However, as described 

previously, Boeing has issued Boeing 

Service Bulletin 747–53A2499, Revision 

2, dated August 12, 2010. Therefore, we 

have revised the requirements in this 

AD to allow the use of Boeing Service 

Bulletin 747–53A2499, Revision 2, 

dated August 12, 2010, for 

accomplishing the specified actions. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We also determined that these changes 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Costs of Compliance 

There are about 735 airplanes of the 

affected design in the worldwide fleet. 

This AD affects 96 airplanes of U.S. 

registry. 

The actions that are required by AD 

2006–05–09 and retained in this AD 

take about 541 work-hours per airplane, 

at an average labor rate of $85 per workhour. Based on these figures, the 

estimated cost of the currently required 

actions is $45,985 per airplane, per 

inspection cycle. 

The new Area 2 inspections take 

about 124 work-hours per airplane, at an 

average labor rate of $85 per work-hour. 

Based on these figures, the estimated 

cost of the new inspections specified in 

this AD for U.S. operators is $1,011,840, 

or $10,540 per airplane, per inspection 

cycle. 

The new modification takes about 

4,799 work hours per airplane, at an 

average labor rate of $85 per work-hour. 

Required parts cost per airplane will be 

minimal. Based on these figures, the 

estimated cost of the new modification 

specified in this AD for U.S. operators 

is $39,159,840, or $407,915 per airplane. 

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 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 


srobinson on DSKHWCL6B1PROD with RULES
Federal Register / Vol. 75, No. 248 / Tuesday, December 28, 2010 / Rules and Regulations 81429 

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 39–14506 (71 

FR 12122, March 9, 2006) and by adding 

the following new airworthiness 

directive (AD): 

2010–26–10 The Boeing Company: 

Amendment 39–16549. FAA–2010–0232; 

Directorate Identifier 2009–NM–032–AD. 

Effective Date 

(a) This AD becomes effective February 1, 

2011. 

Affected ADs 

(b) This AD supersedes AD 2006–05–09. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 747–200C, –200F, –400, 

–400D, and –400F series airplanes, 

certificated in any category; as identified in 

Boeing Service Bulletin 747–53A2499, 

Revision 2, dated August 12, 2010. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from a structural review 

of affected skin lap joints for widespread 

fatigue damage. The Federal Aviation 

Administration is issuing this AD to prevent 

fatigue cracking in certain lap joints, which 

could result in rapid depressurization of the 

airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2006– 

05–09, With Revised Service Information 

Initial Inspections and Related Investigative 

and Corrective Actions 

(g) For airplanes identified in Boeing Alert 

Service Bulletin 747–53A2499, dated August 

11, 2005: At the applicable time specified in 

Table 1 of this AD, do an external surface 

high frequency eddy current (HFEC), external 

low frequency eddy current (LFEC), and 

internal LFEC inspection, as applicable, for 

cracks in the overlapping (upper) skin of the 

upper fastener row of the lap joints of the 

fuselage skin in sections 41, 42, and 46, and 

any applicable related investigative and 

corrective actions by doing all of the actions 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2499, dated August 11, 2005; 

Revision 1, dated October 30, 2008; or Boeing 

Service Bulletin 747–53A2499, Revision 2, 

dated August 12, 2010. Do any applicable 

related investigative and corrective actions 

before further flight. As of the effective date 

of this AD, only Boeing Service Bulletin 747– 

53A2499, Revision 2, dated August 12, 2010, 

may be used. 

TABLE 1—INITIAL COMPLIANCE TIME

For airplanes on which Structural Significant Items (SSIs) 

F–25G, F–25H, and F–25I— Inspect— 

(1) Have not been inspected in accordance with paragraph (i) of AD 2004–07–22 R1, Amendment 39– 

15326, using the HFEC method.

Before the accumulation of 22,000 total flight cycles, or within 1,000 flight cycles 

after April 13, 2006 (the effective date of AD 2006–05–09), whichever occurs later. 

(2) Have been inspected in accordance with paragraph 

(i) of AD 2004–07–22 R1, using the HFEC method.

Within 3,000 flight cycles after the most recent supplemental structural inspection 

document (SSID) inspection of each applicable structural significant item (as given 

in Boeing Document D6–35022, ‘‘SSID for Model 747 Airplanes,’’ Revision G, 

dated December 2000), or within 1,000 flight cycles after April 13, 2006, whichever 

occurs later. 

Repetitive Inspections 

(h) Repeat the applicable inspections 

required by paragraph (g) of this AD 

thereafter at intervals not to exceed those 

specified in paragraph 1.E., ‘‘Compliance,’’ 

(including the note) of Boeing Alert Service 

Bulletin 747–53A2499, dated August 11, 

2005; Revision 1, dated October 30, 2008; or 

Boeing Service Bulletin 747–53A2499, 

Revision 2, dated August 12, 2010. As of the 

effective date of this AD, only Boeing Service 

Bulletin 747–53A2499, Revision 2, dated 

August 12, 2010, may be used. 

New Requirements of This AD 

Repetitive Inspections/Investigative and 

Corrective Actions 

(i) For all airplanes: Do an external HFEC 

inspection of the lap joints in Sections 41, 42, 

and 46 for cracks, by doing all the actions, 

including all applicable related investigative 

and corrective actions, specified in the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2499, Revision 2, 

dated August 12, 2010. Do the inspection at 

the applicable time specified in paragraph 

1.E. of Boeing Service Bulletin 747–53A2499, 

Revision 2, dated August 12, 2010; except as 

required by paragraph (m) of this AD. Do all 

applicable related investigative and 

corrective actions before further flight. 

Repeat the inspection thereafter at the times 

specified in paragraph 1.E. of Boeing Service 

Bulletin 747–53A2499, Revision 2, dated 

August 12, 2010. Accomplishment of the 

inspections required by this paragraph 

terminates the inspections required by 

paragraphs (g) and (h) of this AD. 

(j) For areas on which a lap joint repair was 

installed and the repair doubler is greater 

than or equal to 40 inches long: Do initial 

and repetitive internal HFEC inspections for 

cracks by doing all the actions, including all 

applicable corrective actions, specified in the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2499, Revision 2, 

dated August 12, 2010, except as required by 

paragraph (l) of this AD. Do the inspections 

and corrective actions at the times specified 

in paragraph 1.E. of Boeing Service Bulletin 

747–53A2499, Revision 2, dated August 12, 

2010, except as required by paragraph (m) of 

this AD. 

Terminating Action 

(k) Modify the applicable lap joints in 

Sections 41 and 42 by doing all the 

applicable actions specified in the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2499, Revision 2, 

dated August 12, 2010, at the time specified 

in paragraph 1.E. of Boeing Service Bulletin 

747–53A2499, Revision 2, dated August 12, 

2010; except as required by paragraphs (l) 

and (m) of this AD. Accomplishing this 

modification terminates the repetitive 

inspections of the skin lap joints in Sections 

41 and 42 required by paragraphs (i) and (j) 

of this AD for the length of lap joint that is 

modified. 

Exceptions to Service Bulletin Procedures 

(l) Where Boeing Service Bulletin 747– 

53A2499, Revision 2, dated August 12, 2010, 

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 (o) of 

this AD. 

(m) Where Boeing Service Bulletin 747– 

53A2499, Revision 2, dated August 12, 2010, 

specifies a compliance time after the date of 

that service bulletin, this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

Credit for Actions Done Using Previous 

Service Information 

(n) Actions done before the effective date 

of this AD in accordance with Boeing Alert 

Service Bulletin 747–53A2499, Revision 1, 

dated October 30, 2008, are acceptable for 

compliance with the corresponding 

requirements of this AD. 


srobinson on DSKHWCL6B1PROD with RULES
81430 Federal Register / Vol. 75, No. 248 / Tuesday, December 28, 2010 / Rules and Regulations 

Alternative Methods of Compliance 

(AMOCs) 

(o)(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. Send information to Attn: 

Nicholas Han, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle ACO, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6449; fax 

(425) 917–6590. Information may be e-mailed 

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

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(3) 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) or other 

person 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 2006–05–09 are 

approved as alternative methods of 

compliance with the corresponding 

requirements of this AD. 

Material Incorporated by Reference 

(p) You must use Boeing Alert Service 

Bulletin 747–53A2499, dated August 11, 

2005; or Boeing Service Bulletin 747– 

53A2499, Revision 2, dated August 12, 2010; 

as applicable; 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 

Boeing Service Bulletin 747–53A2499, 

Revision 2, dated August 12, 2010, under 5 

U.S.C. 552(a) and 1 CFR part 51. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of Boeing Alert Service Bulletin 

747–53A2499, dated August 11, 2005, on 

April 13, 2006 (71 FR 12122, March 9, 2006). 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

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

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.com. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(5) You may also review copies of the 

service information that is incorporated by 

reference 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 

December 13, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–31992 Filed 12–27–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0674; Directorate 

Identifier 2010–NM–012–AD; Amendment 

39–16546; AD 2010–26–07] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD requires 

repetitive inspections for cracking in the 

body skin around the aft corners of the 

nose wheel well; for certain airplanes, 

repetitive inspections for cracking in the 

skin splice plate at the aft corners of the 

nose wheel well; and related 

investigative and corrective actions if 

necessary. This AD also requires 

repetitive post-modification inspections 

for cracking in the body skin and the 

skin splice plate; for certain airplanes, 

an inspection for steel cross-shaped 

doublers on the larger aluminum 

doublers; and corrective action if 

necessary. This AD also requires 

repetitive surface high frequency eddy 

current (HFEC) inspections of a certain 

bulkhead outer chord, skin splice plate, 

and outer chord radius filler for 

cracking; repetitive detailed inspections 

for cracking of the bulkhead frame web 

and body skin; and corrective actions if 

necessary. This AD provides for 

optional terminating action for certain 

repetitive inspections. This AD was 

prompted by reports of cracking of the 

fuselage skin and adjacent internal skin 

splice plate at the left and right nose 

wheel well aft corners, and the outer 

chord of the body station (BS) 400 

bulkhead. We are issuing this AD to 

detect and correct cracking of the 

fuselage skin or splice plate, which, 

together with cracking of the bulkhead 

outer chord, could result in large skin 

cracks and subsequent in-flight rapid 

decompression of the airplane. 

DATES: This AD is effective February 1, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of February 1, 2011. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

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

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

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 (phone: 800–647–5527) is 

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: 

Steven Fox, Senior Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6425; fax (425) 917–6590; email: steven.fox@faa.gov. 

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 the 

specified products. That NPRM 

published in the Federal Register on 

July 8, 2010 (75 FR 39189). That NPRM 

proposed to require repetitive 

inspections for cracking in the body 

skin around the aft corners of the nose 

wheel well; for certain airplanes, 

repetitive inspections for cracking in the 

skin splice plate at the aft corners of the 

nose wheel well; and related 

investigative and corrective actions if 


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