70362 Federal Register / Vol. 77, No. 227 / Monday, November 26, 2012 / Rules and Regulations 

76137, telephone (817) 222–5110, email 

rao.edupuganti@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2011–0143, dated July 26, 2011. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6700: Tail Rotor Drive System. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the following service information 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Eurocopter Alert Service Bulletin (ASB) 

No. SA315–65.48, Revision 0, dated March 

23, 2011. 

(ii) Eurocopter ASB No. ALOUETTE–65– 

149, Revision 0, dated March 23, 2011. 

(3) For Eurocopter service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052, telephone 

(972) 641–0000 or (800) 232–0323, fax (972) 

641–3775, or at http://www.eurocopter.com/ 

techpub. 

(4) You may view this service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. 

(5) You may also view this service 

information 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/

cfr/ibr-locations.html. 

Issued in Fort Worth, Texas, on November 

5, 2012. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–28033 Filed 11–23–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0794; Directorate 

Identifier 2009–NM–035–AD; Amendment 

39–17239; AD 2012–22–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 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, 747SR, and 747SP 

series airplanes. This AD was prompted 

by reports of cracks in the main entry 

door number 1 upper main sill outer 

chord, along the bend radius of the 

chord on several airplanes. This AD 

requires a general visual inspection to 

identify any existing structural repair 

manual (SRM) repairs of the upper main 

sill outer chord of the left and right side 

main entry door number 1, repetitive 

detailed inspections for cracks in the 

upper main sill of the door(s); and 

related investigative and corrective 

actions, if necessary. This AD also 

requires repetitive inspections for 

airplanes on which a certain repair is 

done, and corrective actions if 

necessary, and reduces certain 

compliance times. We are issuing this 

AD to detect and correct cracks in the 

main entry door number 1 upper main 

sill outer chord, along the bend radius 

of the chord, which could result in loss 

of structural integrity of the airplane. 

DATES: This AD is effective December 

31, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of December 31, 2012. 

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; 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: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 

98057–3356; phone: (425) 917–6437; 

fax: (425) 917–6590; email: ivan.li@faa.

gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to include an 

airworthiness directive (AD) that would 

apply to the specified products. That 

supplemental NPRM published in the 

Federal Register on December 29, 2011 

(76 FR 81879). The original NPRM (74 

FR 49351, September 28, 2009) 

proposed to require a general visual 

inspection to identify any existing SRM 

repairs of the upper main sill outer 

chord of the left and right side main 

entry door number 1, as applicable; 

repetitive detailed inspections for cracks 

in the upper main sill of the door(s); and 

related investigative and corrective 

actions, if necessary. The original NPRM 

also proposed to require repetitive 

inspections for airplanes on which a 

certain repair is done, and corrective 

actions if necessary The supplemental 

NPRM proposed to revise the original 

NPRM by reducing certain compliance 

times. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (76 FR 81879, 

December 29, 2011) and the FAA’s 

response to each comment. 

Request To Repair Crack by Using SRM 

Boeing requested that we revise 

paragraph (k) of the supplemental 

NPRM (76 FR 81879, December 29, 

2011) to allow, for repair of any crack 

found during any inspection specified 

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in paragraph (g) or (h) of the 

supplemental NPRM, using ‘‘the FAA 

approved Boeing 747–400 SRM 53–10– 

15, Fig 201 Repair 1-‘‘MED #1 Upper 

Main Sill web’’ or a method approved 

in accordance with the procedures 

specified in paragraph (s) of this AD.’’ 

Boeing explained that the Boeing 747– 

400 SRM provides an FAA-approved 

repair, and that allowing its use for 

repairs would reduce the resource 

requirements of providing alternative 

method of compliance (AMOC) 

approvals. 

We agree to include the SRM 

reference requested by Boeing for Model 

747–400 series airplanes. We have 

revised paragraph (k) of this final rule 

accordingly. 

Request To Revise Inspection 

Compliance 

Boeing requested that we revise 

paragraph (l) of the supplemental NPRM 

(76 FR 81879, December 29, 2011) to 

explain that the specified inspection is 

repeated only until the outer chord 

repair is installed (as specified in Part 

3 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747– 

53A2785, Revision 1, dated July 15, 

2010). Boeing explained that paragraphs 

(g) and (h) of the supplemental NPRM 

allow termination of repetitive 

inspections if that repair has been 

accomplished. Boeing reasoned that 

paragraph (l) of the supplemental NPRM 

implies that inspections are ongoing. 

We agree with the commenter’s 

request for the reasons stated by Boeing. 

We have revised paragraph (l) of this 

final rule accordingly. 

Request To Include Certain Paragraphs 

as Acceptable for Repair Requirements 

of AD 2010–01–01, Amendment 39– 

16157 (75 FR 1533, January 12, 2010) 

All Nippon Airways (ANA) requested 

that we revise paragraph (o) of the 

supplemental NPRM (76 FR 81879, 

December 29, 2011) to reference 

paragraphs (j) and (k) of the 

supplemental NPRM as acceptable for 

compliance with AD 2010–01–01, 

Amendment 39–16157 (75 FR 1533, 

January 12, 2010). ANA explained that, 

otherwise, operators would have to 

obtain an AMOC for the requirements of 

AD 2010–01–01 when they repair the 

subject area per paragraph (j) or (k) of 

the supplemental NPRM. 

We agree that accomplishment of the 

repairs required by paragraphs (j) and 

(k) of this AD are acceptable for 

compliance with the repair 

requirements of paragraph (h) of AD 

2010–01–01, Amendment 39–16157 (75 

FR 1533, January 12, 2010). In addition, 

we have determined that 

accomplishment of the repairs required 

by paragraphs (j) and (k) of this AD are 

acceptable for compliance with 

paragraph (l) of AD 2009–18–07, 

Amendment 39–16003 (74 FR 43629, 

August 27, 2009). We have revised 

paragraph (o) of this final rule 

accordingly. 

Explanation of Additional Changes 

Made to This AD 

We have revised the heading and 

wording for paragraph (r) of this AD to 

provide appropriate credit for previous 

accomplishment of certain actions. This 

change does not affect the intent of that 

paragraph. 

We have re-identified Note 1 to 

paragraph (o) of the supplemental 

NPRM (76 FR 81879, December 29, 

2011) as paragraph (o)(2) in this final 

rule. 

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— 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the supplemental 

NPRM (76 FR 81879, December 29, 

2011) for correcting the unsafe 

condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the supplemental NPRM 

(76 FR 81879, December 29, 2011). 

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 

We estimate that this AD affects 165 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Work hours Parts cost Cost per product 

Number of 

U.S.-registered 

airplanes 

Cost on U.S. operators 

Inspection (Groups 1, 3, 

5–6 airplanes).

6 work-hours × $85 per 

hour = $510.

$0 $510 per inspection cycle 86 $43,860 per inspection 

cycle. 

Inspection (Groups 2, 4, 

7 airplanes).

3 work-hours × $85 per 

hour = $255.

$0 $255 per inspection cycle 79 $20,145 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 AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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70364 Federal Register / Vol. 77, No. 227 / Monday, November 26, 2012 / Rules and Regulations 

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

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. 

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 airworthiness 

directive (AD): 

2012–22–03 The Boeing Company: 

Amendment 39–17239; Docket No. 

FAA–2009–0794; Directorate Identifier 

2009–NM–035–AD. 

(a) Effective Date 

This AD is effective December 31, 2012. 

(b) Affected ADs 

AD 2009–18–07, Amendment 39–16003 

(74 FR 43629, August 27, 2009); and AD 

2010–01–01, Amendment 39–16157 (75 FR 

1533, January 12, 2010); affect this AD. 

(c) Applicability 

This AD applies to all 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, 

747SR, and 747SP series airplanes, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53: Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

in the main entry door number 1 upper main 

sill outer chord, along the bend radius of the 

chord on several airplanes. We are issuing 

this AD to detect and correct such cracks, 

which could result in loss of structural 

integrity of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Inspection for Groups 1 Through 4 

Airplanes 

For Groups 1 through 4 airplanes, as 

identified in Boeing Alert Service Bulletin 

747–53A2785, Revision 1, dated July 15, 

2010: At the applicable time specified in 

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

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010, except as 

provided by paragraphs (p) and (q) of this 

AD, do a one-time general visual inspection 

to identify any existing structural repair 

manual (SRM) repairs of the upper main sill 

outer chord of the left and right main entry 

door 1, as applicable. Remove any existing 

SRM outer chord repair that is found, before 

further flight, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2785, Revision 1, 

dated July 15, 2010. In addition, after doing 

the one-time general visual inspection to 

identify any existing SRM repairs of the 

upper main sill outer chord of the left and 

right main entry door 1, before further flight, 

do a detailed inspection for cracks of the 

main upper sill outer chord, web, and frame 

attachment angles (or clips) of the left and 

right main entry door 1, as applicable. Do all 

actions in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2785, Revision 1, 

dated July 15, 2010. If no crack and no 

existing SRM outer chord repair is found 

during any inspection required by this 

paragraph, at the applicable time specified in 

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

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010, except as 

provided by paragraphs (p) and (q) of this 

AD, repeat thereafter the detailed inspection 

for cracks, at intervals specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2785, Revision 1, dated July 

15, 2010, until the outer chord repair 

specified in Part 3 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2785, Revision 1, dated July 15, 

2010, is installed. 

(h) Inspection for Groups 5 Through 7 

Airplanes 

For Groups 5 through 7 airplanes, as 

identified in Boeing Alert Service Bulletin 

747–53A2785, Revision 1, dated July 15, 

2010: At the applicable time specified in 

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

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010, except as 

provided by paragraphs (p) and (q) of this 

AD, do a detailed inspection for cracks of the 

main upper sill outer chord, web, and frame 

attachment angles (or clips) of the left and 

right main entry door 1, as applicable, in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2785, Revision 1, 

dated July 15, 2010. If no crack is found 

during any inspection required by this 

paragraph, at the applicable time specified in 

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

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010, except as 

provided by paragraphs (p) and (q) of this 

AD, repeat thereafter the detailed inspection 

for cracks, at intervals specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2785, Revision 1, dated July 

15, 2010, until the outer chord repair 

specified in Part 3 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2785, Revision 1, dated July 15, 

2010, is installed. 

(i) Repair for Groups 1 Through 4 Airplanes 

For Groups 1 through 4 airplanes, as 

identified in Boeing Alert Service Bulletin 

747–53A2785, Revision 1, dated July 15, 

2010: If an existing SRM outer chord repair 

is found and removed during the inspection 

required by paragraph (g) of this AD, before 

further flight, install a new outer chord repair 

in accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2785, Revision 1, 

dated July 15, 2010. 

(j) Repair of Outer Chord Crack or Cracked 

Frame Attachment Angles (or Clips) 

If any outer chord crack or cracked frame 

attachment angles (or clips) are found during 

any inspection required by paragraph (g) or 

(h) of this AD, before further flight, repair, in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2785, Revision 1, 

dated July 15, 2010. 

(k) Repair of Upper Main Sill Web Crack 

If any upper main sill web crack is found 

during any inspection required by paragraph 

(g) or (h) of this AD, before further flight, 

repair the crack using a method approved in 

accordance with the procedures specified in 

paragraph (s) of this AD. For Boeing Model 

747–400 series airplanes only, the repair may 

also be done in accordance with Figure 201, 

of Repair 1, ‘‘Main Entry Door Number 1 

Upper Main Sill Web Crack Repair from STA 

440 to STA 480,’’ of Subject 53–10–15, 

‘‘Fuselage Door Surround Structure-Section 

41,’’ of Chapter 53, ‘‘Fuselage,’’ of Boeing 

747–400 Structural Repair Manual, Revision 

83, dated June 20, 2012. 

(l) Inspection 

If any upper main sill web or frame 

attachment angles (or clips) have been 

repaired as specified in PART 3—REPAIR of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010, and the outer 

chord repair specified in PART 3—REPAIR of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010, has not been 

installed, at the applicable time specified in 

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

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010, except as 

provided by paragraphs (p) and (q) of this 

AD, do a detailed inspection for cracks as 

specified in paragraph (g) or (h) of this AD, 

as applicable, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2785, Revision 1, 

dated July 15, 2010. Repeat the inspections 

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

applicable, thereafter at intervals specified in 

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

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010, until the 

outer chord repair specified in Part 3 of the 

Accomplishment Instructions of Boeing Alert 

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Service Bulletin 747–53A2785, Revision 1, 

dated July 15, 2010, is installed. 

(m) Post-Repair Inspection 

For airplanes having the outer chord repair 

installed as specified in PART 3—REPAIR of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010: At the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2785, Revision 1, dated July 

15, 2010, except as provided by paragraphs 

(p) and (q) of this AD, do a detailed 

inspection for cracks of the left and right 

main entry door 1 upper sill, as applicable, 

with the outer chord repair installed, in 

accordance with PART 5—AFTER-REPAIR 

INSPECTION of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2785, Revision 1, dated July 15, 

2010. Repeat the inspection for cracks 

thereafter at the applicable intervals specified 

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

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010. 

(n) Repair of Any Crack Found From PostRepair Inspection 

Repair any crack found during any 

inspection required by paragraph (m) of this 

AD, before further flight, using a method 

approved in accordance with the procedures 

specified in paragraph (s) of this AD. 

(o) Credit for Inspections Required by AD 

2009–18–07, Amendment 39–16003 (74 FR 

43629, August 27, 2009), or AD 2010–01–01, 

Amendment 39–16157 (75 FR 1533, January 

12, 2010), and AMOC for the Repairs 

Required by Those ADs 

(1) Accomplishing the main entry door 1 

cutout detailed inspection required by AD 

2009–18–07, Amendment 39–16003 (74 FR 

43629, August 27, 2009); or AD 2010–01–01, 

Amendment 39–16157 (75 FR 1533, January 

12, 2010); as applicable; before the effective 

date of this AD is acceptable for compliance 

with the detailed inspection requirements of 

paragraphs (g), (h), (l), and (m) of this AD 

only. The one-time general visual inspection 

of paragraph (g) of this AD is still required. 

For the repaired area only, accomplishment 

of the applicable repair required by 

paragraphs (j) and (k) of this AD is acceptable 

for compliance with paragraph (l) of AD 

2009–18–07, and paragraph (h) of AD 2010– 

01–01. 

(2) For all applicable airplanes that have 

accumulated 22,000 total flight cycles or 

more as of October 1, 2009 (the effective date 

of AD 2009–18–07, Amendment 39–16003 

(74 FR 43629, August 27, 2009)), AD 2009– 

18–07 requires accomplishing the main entry 

door 1 cutout detailed inspection in 

accordance with Boeing Alert Service 

Bulletin 747–53A2349, Revision 3, dated 

October 2, 2008 (which is incorporated by 

reference in AD 2009–18–07). For all 

applicable airplanes (except Model 747–400 

series airplanes modified to the Model 747– 

400 large cargo freighter (LCF) configuration) 

that have accumulated 22,000 total flight 

cycles or more as of February 16, 2010 (the 

effective date of AD 2010–01–01, 

Amendment 39–16157 (75 FR 1533, January 

12, 2010)), AD 2010–01–01 requires 

accomplishing the main entry door 1 cutout 

detailed inspection in accordance with 

Boeing Alert Service Bulletin 747–53A2500, 

Revision 1, dated September 25, 2008 (which 

is incorporated by reference in AD 2010–01– 

01). For Model 747–400 series airplanes 

modified to the Model 747–400 LCF 

configuration and having accumulated 

15,000 total flight cycles or more as of 

February 16, 2010 (the effective date of AD 

2010–01–01), AD 2010–01–01 requires 

accomplishing the inspections in accordance 

with Boeing Alert Service Bulletin 747– 

53A2500, Revision 1, dated September 25, 

2008 (which is incorporated by reference in 

AD 2010–01–01). 

(p) Exception to the Service Information 

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

Boeing Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010, specifies a 

compliance time ‘‘after the original issue date 

of this service bulletin,’’ or ‘‘after the date on 

Revision 1 of this service bulletin,’’ this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(q) Exception to Compliance Time 

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

Boeing Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010, specifies a 

compliance time of ‘‘within’’ a specified 

‘‘total flight-cycles,’’ this AD requires 

compliance ‘‘before the accumulation’’ of the 

specified total flight cycles. 

(r) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g), (h), (i), (j), 

(k), (l), (m), and (n) of this AD, if those 

actions were performed before the effective 

date of this AD using Boeing Alert Service 

Bulletin 747–53A2785, dated February 12, 

2009, which is not incorporated by reference 

in 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. 

(t) Related Information 

(1) For more information about this AD, 

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; email: ivan.li@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, Washington 98124–2207; telephone 

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

5680; Internet https:// 

www.myboeingfleet.com 

(u) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the following service information 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 747– 

53A2785, Revision 1, dated July 15, 2010. 

(ii) Figure 201, of Repair 1, ‘‘Main Entry 

Door Number 1 Upper Main Sill Web Crack 

Repair from STA 440 to STA 480,’’ of Subject 

53–10–15, ‘‘Fuselage Door Surround 

Structure-Section 41,’’ of Chapter 53, 

‘‘Fuselage,’’ of Boeing 747–400 Structural 

Repair Manual, Revision 83, dated June 20, 

2012. 

(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; 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/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on October 

19, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–26666 Filed 11–23–12; 8:45 am] 

BILLING CODE 4910–13–P 

mstockstill on DSK4VPTVN1PROD with RULES