Document ID: FAA-2009-0794-0010
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2012-11-26T05:00Z

[Federal Register Volume 77, Number 227 (Monday, November 26, 2012)]
[Rules and Regulations]
[Pages 70362-70365]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-26666]

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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.

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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

[[Page 70363]]

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:
     [Agr]re 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
----------------------------------------------------------------------------------------------------------------
                                                                                 Number of U.S.-
            Action                Work hours      Parts cost        Cost per       registered      Cost on U.S.
                                                                    product         airplanes       operators
----------------------------------------------------------------------------------------------------------------
Inspection (Groups 1, 3, 5-6   6 work-hours x               $0  $510 per                     86  $43,860 per
 airplanes).                    $85 per hour =                   inspection                       inspection
                                $510.                            cycle.                           cycle.
Inspection (Groups 2, 4, 7     3 work-hours x               $0  $255 per                     79  $20,145 per
 airplanes).                    $85 per hour =                   inspection                       inspection
                                $255.                            cycle.                           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,

[[Page 70364]]

    (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

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  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

[[Page 70365]]

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 Post-Repair 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-ANM-Seattle-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