Document ID: FAA-2009-0794-0005
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2011-12-29T05:00Z

[Federal Register Volume 76, Number 250 (Thursday, December 29, 2011)]
[Proposed Rules]
[Pages 81879-81883]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-33376]

 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 76, No. 250 / Thursday, December 29, 2011 / 
Proposed Rules  

[[Page 81879]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0794; Directorate Identifier 2009-NM-035-AD]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

-----------------------------------------------------------------------

SUMMARY: We are revising an earlier proposed 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. The original NPRM proposed a general 
visual inspection to identify any existing structural repair manual 
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 repetitive inspections for airplanes on 
which a certain repair is done, and corrective actions if necessary. 
The original NPRM 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 action revises the original NPRM by 
reducing certain compliance times. We are proposing this supplemental 
NPRM 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. Since these 
actions impose an additional burden over that proposed in the original 
NPRM, we are reopening the comment period to allow the public the 
chance to comment on these proposed changes.

DATES: We must receive comments on this supplemental NPRM by February 
13, 2012.

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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this proposed 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; email 
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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone (800) 647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe 
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue SW., Renton, Washington 98057-3356; phone: (425) 917-6437; fax: 
(425) 917-6590; email: ivan.li@faa.gov.

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-2009-0794; 
Directorate Identifier 2009-NM-035-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

    We issued a notice of proposed rulemaking (NPRM) (the ``original 
NPRM'') to amend 14 CFR part 39 to include an airworthiness directive 
(AD) that would apply 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. That original 
NPRM was published in the Federal Register on September 28, 2009 (74 FR 
49351). That original NPRM proposed to require 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, 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.

[[Page 81880]]

Actions Since Previous NPRM Was Issued

    Since we issued the original NPRM (74 FR 49351, September 28, 
2009), Boeing has issued Boeing Alert Service Bulletin 747-53A2785, 
Revision 1, dated July 15, 2010. Among other things, Boeing Alert 
Service Bulletin 747-53A2785, Revision 1, dated July 15, 2010, makes 
certain grouping changes for the affected airplanes, and also describes 
procedures for reducing the compliance threshold and repetitive 
interval for inspections of Model 747-400 series airplanes modified to 
the large cargo freighter (LCF) configuration.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received from the commenters.

Request To Change Compliance Times for Certain Airplanes

    Boeing requested that we revise paragraphs (g), (h)(1), and (i) of 
the original NPRM (74 FR 49351, September 28, 2009) to reduce the 
compliance times and repetitive inspection interval for certain Model 
747-400 series airplanes modified to the LCF configuration. Boeing 
explained that those airplanes operate at higher stress levels, and 
that cracks may initiate sooner and grow faster. Boeing suggested using 
the compliance times in paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-53A2785, Revision 1, dated July 15, 2010, instead 
of the compliance times listed in paragraph 1.E. ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2785, dated February 12, 2009, 
which was referred to in the original NPRM.
    We agree to revise this supplemental NPRM as requested by the 
commenter. The original NPRM (74 FR 49351, September 28, 2009) referred 
to Boeing Alert Service Bulletin 747-53A2785, dated February 12, 2009, 
as the appropriate source of service information. We have reviewed 
Boeing Alert Service Bulletin 747-53A2785, Revision 1, dated July 15, 
2010. Among other things, this service information makes certain 
grouping changes for the affected airplanes. This service information 
also describes procedures for reducing the compliance threshold and 
repetitive interval for inspections of Model 747-400 series airplanes 
modified to the LCF configuration. This service information specifies 
that the reduced compliance threshold for those airplanes is 10,000 
total flight cycles or within 1,500 flight cycles after the date of 
Boeing Alert Service Bulletin 747-53A2785, Revision 1, dated July 15, 
2010 (whichever occurs later). The revised repetitive interval for 
those airplanes is 3,000 flight cycles.
    In addition, Boeing Alert Service Bulletin 747-53A2785, Revision 1, 
dated July 15, 2010, specifies a compliance threshold for certain Model 
747-400, -400D, and -400F series airplanes (i.e., Groups 6 and 7 
airplanes) of 12,000 total flight cycles or within 1,500 flight cycles 
after the date of Boeing Alert Service Bulletin 747-53A2785, dated 
February 12, 2009, (whichever occurs later). The repetitive interval 
for those airplanes is 6,000 flight cycles.
    In light of this revised service information, we have revised this 
supplemental NPRM to refer to Boeing Alert Service Bulletin 747-
53A2785, Revision 1, dated July 15, 2010. In addition, we have 
reformatted this supplemental NPRM to specify certain required actions 
by airplane group.
    We have also added paragraph (r) to this supplemental NPRM to give 
credit for accomplishing the inspections and repairs before the 
effective date of this AD, as specified in Boeing Alert Service 
Bulletin 747-53A2785, dated February 12, 2009.

Request To Refer to Service Information Instead of the Drawing

    Boeing requested that we revise paragraph (h) of the original NPRM 
(September 28, 2009 (74 FR 49351)) to refer to ``the service bulletin 
repair drawing reference'' instead of ``drawing 691U0145.'' Boeing 
explained that they were in the process of revising Boeing Alert 
Service Bulletin 747-53A2785 to change Drawing 691U0145 into an 
orderable kit, which means that the repair drawing number will change.
    We agree with the commenter's request to remove references to a 
particular drawing since the number will change. Based on Boeing's 
comment, we have revised this supplemental NPRM to refer to Boeing 
Alert Service Bulletin 747-53A2785, Revision 1, dated July 15, 2010, 
for the outer chord repair.

Requests To Add Acceptable Method of Compliance Information

    Boeing requested that paragraph (j) of the original NPRM (September 
28, 2009 (74 FR 49351)) (i.e., paragraph (o) of this supplemental NPRM) 
be revised to add that accomplishment of the inspections required by AD 
2009-18-07, Amendment 39-16003 (74 FR 43629, August 27, 2009); or AD 
2006-05-02, Amendment 39-14499 (71 FR 10605, March 2, 2006) (as 
superseded by AD 2010-01-01, Amendment 39-16157 (75 FR 1533, January 
12, 2010)); as applicable; is acceptable for compliance with the 
inspection requirements of paragraphs (h) and (i) of the original NPRM.
    Boeing explained that Boeing Alert Service Bulletin 747-53A2785, 
dated February 12, 2009, states that when the inspections ``per the 
fatigue test ADs 2009-18-07, Amendment 39-16003 (74 FR 43629, August 
27, 2009) or 2006-05-02, Amendment 39-14499 (71 FR 10605, March 2, 
2006)'' are accomplished, the inspections per the original NPRM 
(September 28, 2009 (74 FR 49351)) and Boeing Alert Service Bulletin 
747-53A2785, dated February 12, 2009, are satisfied. Therefore, 
accomplishment of the inspections required by AD 2009-18-07 or 2006-05-
02 (as superseded by AD 2010-01-01, Amendment 39-16157 (75 FR 1533, 
January 12, 2010)) is acceptable for compliance with the inspection 
requirements of paragraphs (g), (h), and (i) of the original NPRM. 
Boeing reasoned that the information should be included in paragraph 
(j) of the original NPRM.
    Boeing also requested that we revise paragraph (j) of the original 
NPRM (September 28, 2009 (74 FR 49351)) to replace the reference to AD 
2005-20-30, Amendment 39-14327 (70 FR 59252, October 12, 2005), with a 
reference to AD 2009-18-07, Amendment 39-16003 (74 FR 43629, August 27, 
2009). Boeing explained that AD 2005-20-30 has been superseded by AD 
2009-18-07.
    All Nippon Airways (ANA) also requested that paragraph (j) of the 
original NPRM (September 28, 2009 (74 FR 49351)) be revised to refer to 
both paragraphs (g) and (h) of the original NPRM to clarify AMOC 
requirements. ANA explained that paragraph (j) of the original NPRM 
specifies that accomplishing the inspections required by AD 2005-20-30, 
Amendment 39-14327 (70 FR 59252, October 12, 2005) (which was 
superseded by AD 2009-18-07, Amendment 39-16003 (74 FR 43629, August 
27, 2009)); or AD 2006-05-02, Amendment 39-14499 (71 FR 10605, March 2, 
2006) (which was superseded by AD 2010-01-01, Amendment 39-16157 (75 FR 
1533, January 12, 2010)); is an acceptable method of compliance for the 
inspections required by paragraph (g) of the original NPRM. ANA 
reasoned further, that paragraph (g) of the original NPRM refers only 
to the initial inspection, and paragraph (h) of the original NPRM 
refers to the repetitive inspection.
    We agree that accomplishing the detailed inspections required by AD 
2009-18-07, Amendment 39-16003 (74

[[Page 81881]]

FR 43629, August 27, 2009); or AD 2010-01-01, Amendment 39-16157 (75 FR 
1533, January 12, 2010); as applicable; is acceptable for compliance 
with the detailed inspection requirements of paragraphs (g), (h), and 
(i) of this supplemental NPRM. Therefore, in paragraph (o) of this 
supplemental NPRM (which corresponds to paragraph (j) of the original 
NPRM (74 FR 49351, September 28, 2009)), we have referred to paragraphs 
(g), (h), (l), and (m), since the actions specified by paragraph (o) of 
this supplemental NPRM are acceptable for compliance with those 
paragraphs.
    We also agree to revise paragraph (o) of this supplemental NPRM to 
reference to current 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). In addition, we have referenced the current ADs in 
paragraph (b) of this supplemental NPRM, since those ADs are affected 
by this supplemental NPRM.

Request To Include Latest Revision of Service Information

    Boeing requested that we revise paragraph (j) of the original NPRM 
(September 28, 2009 (74 FR 49351)) (i.e., paragraph (o) of this 
supplemental NPRM), to refer to Boeing Alert Service Bulletin 747-
53A2349, Revision 3, dated October 2, 2008, instead of Revision 2, 
dated April 3, 2003, of that service bulletin.
    We agree that this supplemental NPRM should refer to the latest 
service information. We have revised paragraph (o) of this supplemental 
NPRM to refer to Boeing Alert Service Bulletin 747-53A2349, Revision 3, 
dated October 2, 2008.

Request To Revise Boeing Delegated Option Authorization (DOA) to Boeing 
Organization Designation Authorization (ODA)

    Boeing requested that we revise any occurrence of the phrase 
``Boeing DOA'' in the original NPRM (September 28, 2009 (74 FR 49351)) 
to ``Boeing ODA'' in this supplemental NPRM. Boeing explained that 
Boeing Commercial Airplanes has changed from ``DOA'' to ``ODA.''
    We agree to revise ``Boeing DOA'' to ``Boeing ODA'' in this 
supplemental NPRM. Boeing Commercial Airplanes has received an ODA, 
which replaces their previous designation as a DOA holder. We have 
revised paragraph (s) of this supplemental NPRM to delegate the 
authority to approve an AMOC for any repair required by this AD to the 
Boeing Commercial ODA.

Clarification of ``PART 3--REPAIR''

    The installation of a new outer chord repair specified in Section 
``PART 3--REPAIR'' of Boeing Alert Service Bulletin 747-53A2785, 
Revision 1, dated July 15, 2010, includes replacing any existing SRM 
outer chord repair with a new repair, repairing cracked outer chords, 
replacing cracked frame attach angles or clips, and contacting Boeing 
for repair instructions and doing the repair for main upper sill web 
cracks.

Clarification of Service Bulletin

    The ``detailed inspection of the upper main sill web and frame 
attachment angles (or clips) for crack(s)'' in the second column, sixth 
row down, on page 26 of Boeing Alert Service Bulletin 747-53A2785, 
Revision 1, dated July 15, 2010, is not in the Accomplishment 
Instructions of that document. PART 3--REPAIR of the Accomplishment 
Instructions in Boeing Alert Service Bulletin 747-53A2785, Revision 1, 
dated July 15, 2010, is correct; there is no detailed inspection 
necessary as part of the repair. We note that a detailed inspection of 
the upper main sill (including the sill web and frame attachment angles 
(or clips) for cracks) is already required in PART 2--INSPECTION of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2785, Revision 1, dated July 15, 2010.

FAA's Determination

    We are proposing this supplemental NPRM because we evaluated all 
pertinent information and determined an unsafe condition exists and is 
likely to exist or develop on other products of these same type 
designs. Certain changes described above expand the scope of the 
original NPRM (September 28, 2009 (74 FR 49351)). As a result, we have 
determined that it is necessary to reopen the comment period to provide 
additional opportunity for the public to comment on this supplemental 
NPRM.

Proposed Requirements of the Supplemental NPRM

    This supplemental NPRM would require accomplishing the actions 
specified in the service information described previously, except as 
discussed under ``Differences Between the Supplemental NPRM and the 
Service Information.''

Differences Between the Supplemental NPRM and the Service Information

    Boeing Alert Service Bulletin 747-53A2785, Revision 1, dated July 
15, 2010, 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 ODA whom we have authorized to make 
those findings.

Explanation of Change to Costs of Compliance

    Since issuance of the original NPRM (September 28, 2009 (74 FR 
49351)), we have increased the labor rate used in the Costs of 
Compliance from $80 per work-hour to $85 per work-hour. The Costs of 
Compliance information, below, reflects this increase in the specified 
labor rate.

Costs of Compliance

    We estimate that this proposed AD affects 165 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

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

[[Page 81882]]

     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.

Regulatory Findings

    We 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 this 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.

Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

The Boeing Company: Docket No. FAA-2009-0794; Directorate Identifier 
2009-NM-035-AD.

(a) Comments Due Date

    We must receive comments by February 13, 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 Group 1 Through 4 Airplanes

    For Group 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 Group 5 Through 7 Airplanes

    For Group 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 paragraph (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 Group 1 Through 4 Airplanes

    For Group 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) is found during any inspection required by paragraph (g) or 
(h) of this AD, before further flight, repair, in

[[Page 81883]]

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.

(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.

(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)

    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.

    Note 1:  For all applicable airplanes that have accumulated 
22,000 total flight cycles or more after 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. For all applicable airplanes (except 747-400 series airplanes 
modified to the 747-400 large cargo freighter (LCF) configuration) 
that have accumulated 22,000 total flight cycles or more after 
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. 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, AD 2010-01-01 requires accomplishing the inspections in 
accordance with Boeing Alert Service Bulletin 747-53A2500, Revision 
1, dated September 25, 2008.

(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 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 Actions Accomplished in Accordance With Previous Service 
Information

    Doing the inspections and repairs, in accordance with Boeing 
Alert Service Bulletin 747-53A2785, dated February 12, 2009, before 
the effective date of this AD, is acceptable for compliance with the 
corresponding inspections and repairs required by paragraphs (g), 
(h), (i), (j), (k), (l), (m), and (n) 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-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; email 
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.

    Issued in Renton, Washington, on December 22, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-33376 Filed 12-28-11; 8:45 am]
BILLING CODE 4910-13-P