AD 2011-14-02

[Federal Register Volume 76, Number 197 (Wednesday, October 12, 2011)]
[Rules and Regulations]
[Pages 63172-63177]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2011-25618]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0033; Directorate Identifier 2009-NM-099-AD; 
Amendment 39-16737; AD 2011-14-02]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Model 767 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) that applies to all Model 767 airplanes. The existing AD currently 
requires repetitive detailed and high frequency eddy current (HFEC) 
inspections of the station (STA) 1809.5 bulkhead for cracking, and 
corrective actions if necessary. This AD expands the inspection area to 
include the vertical inner chord at STA 1809.5. This AD results from 
reported fatigue cracking in the vertical inner chord and the forward 
outer chord while doing the detailed inspection of the horizontal inner 
chord at STA 1809.5. We are issuing this AD to detect and correct 
fatigue cracking in the bulkhead structure at STA 1809.5 and the 
vertical inner chord at STA 1809.5, which could result in failure of 
the bulkhead structure for carrying the flight loads of the horizontal 
stabilizer, and consequent loss of controllability of the airplane.

DATES: This AD becomes effective November 16, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of November 16, 
2011.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; phone: 206-
544-5000, extension 1; fax: 206-766-5680; e-mail: <a href="/cdn-cgi/l/email-protection#5b363e7539343e3834361b39343e32353c75383436"><span class="__cf_email__" data-cfemail="7c1119521e13191f13113c1e131915121b521f1311">[email&#160;protected]</span></a>; 
Internet: <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a>; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Document Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Berhane Alazar, Airframe Branch, ANM-
120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, 
SW., Renton, Washington 98057-3356; phone: 425-917-6577; fax: 425-917-
6590; e-mail: <a href="/cdn-cgi/l/email-protection#81c3e4f3e9e0efe4afc0ede0fbe0f3c1e7e0e0afe6eef7"><span class="__cf_email__" data-cfemail="662403140e07080348270a071c07142600070748010910">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2006-24-04, Amendment 
39-14833 (71 FR 68432, November 27, 2006). The existing AD applies to 
all Model 767 airplanes. That NPRM was published in the Federal 
Register on February 8, 2010 (75 FR 6154). That NPRM proposed to 
continue to require repetitive detailed and HFEC inspections of the STA 
1809.5 bulkhead for cracking, and corrective actions if necessary. That 
NPRM also proposed to expand the inspection area to include the 
vertical inner chord at STA 1809.5.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
received on the NPRM (75 FR 6154, February 8, 2010).

Support for the NPRM

    Continental Airlines (CAL) stated that it supports the intent of 
the NPRM (75 FR 6154, February 8, 2010).

Request To Revise Paragraph (k)(1) of the NPRM

    Boeing requested that we revise the compliance time in paragraph 
(k)(1) of the NPRM (75 FR 6154, February 8, 2010) to state ``whichever 
occurs later'' rather than ``whichever occurs first.'' Boeing stated 
that a similar AD, AD 2006-24-04 (71 FR 68432, November 27, 2006) (the 
AD being superseded), provides a choice of the later of two compliance 
times. Boeing stated that changing the compliance time language in 
paragraph (k)(1) of the NPRM would make this AD consistent with AD 
2006-24-04.
    We agree with the request for the reasons provided by the 
commenter, and we have revised paragraph (k)(1) of this final rule 
accordingly.

Request To Add Model 767-300BCF and 767-200SF Structural Repair Manuals 
(SRMs) To Clarify Terminating Action

    Boeing requested that we specify Model 767-300BCF and Model 767-
200SF SRMs in paragraphs (i) and (m) of the NPRM (75 FR 6154, February 
8, 2010) to clarify the terminating action for converted Model 767-200 
and -300 series airplanes. Boeing stated that some Model 767-300 
airplanes have been converted to Model 767-300BCF airplanes, and some 
Model 767-200 airplanes have been converted to Model 767-200SF 
airplanes. Boeing stated that the Model 767-200SF and Model 767-

[[Page 63173]]

300BCF SRMs differ from the Model 767-200 and Model 767-300 SRMs.
    We partially agree with the request. The Model 767-300BCF is unique 
and has its own SRM documents. We have added the Model 767-300BCF SRMs 
to paragraphs (i) and (j) of this final rule and table 1 of this final 
rule (table 1 follows paragraph (l) of this final rule; paragraph (l) 
of this final rule was referred to as paragraph (m) in the NPRM (75 FR 
6154, February 8, 2010)).
    However, the Boeing Model 767-200SF SRM does not include Subject 
53-80-08, which is the subject referenced in paragraphs (i) and (l) of 
this AD; therefore, we have not changed the AD in regard to this model. 
The Model 767-200SF is unique and has its own SRM documents. After that 
material is developed, we will consider requests for approval of an 
alternative method of compliance (AMOC) under the provisions of 
paragraph (n) of this final rule.

Request To Clarify and Revise Paragraph (h) of the NPRM

    CAL requested that we clarify the AMOC requirements of paragraph 
(h) of the NPRM (75 FR 6154, February 8, 2010). CAL asserted that 
paragraph 3.B. of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 767-53A0131, Revision 1, dated March 12, 2009, allows 
repair of the vertical inner chord in accordance with Repair 11 of 
Subject 53-80-08; therefore, the vertical inner chord needs to be added 
to paragraph (h) of the NPRM as an exclusion to the AMOC requirements.
    We agree with commenter's request for the reasons provided. We have 
revised paragraph (h) of this AD to add the reference to the vertical 
inner chord, as requested by CAL.
    CAL also stated that for repairs or replacements of stringers and 
non-principal structural elements (PSE) parts (e.g., attach brackets, 
support clips, etc.), an AMOC should not be necessary. For instance, 
Parts 3 and 4 of Boeing Alert Service Bulletin 767-53A0131, Revision 1, 
dated March 12, 2009, specify the detailed inspection of the structure 
surrounding the forward outer chord of the STA 1809.5 bulkhead, and the 
corresponding figures illustrate the inspection area, which encloses 
the stringers and attach fittings. As written, CAL stated that 
paragraph (h) of the NPRM (75 FR 6154, February 8, 2010) will prevent 
operators from making stringer repairs/replacements using ``SRM 53-00-
03'' without first obtaining an AMOC. CAL stated further that replacing 
cracked clips and brackets using certain ``Boeing drawings'' should not 
require an AMOC.
    CAL also requested that we revise paragraph (h) of the NPRM (75 FR 
6154, February 8, 2010) to read as follows: ``If any cracking is found 
in the skin or the STA 1809.5 bulkhead's principal structural elements 
(PSE) other than the forward outer chord, horizontal inner chord, and 
vertical inner chord during any inspection required by paragraph (g) or 
(k) of this AD, and Boeing Service Bulletin 767-53A0131, dated March 
30, 2006; or Boeing Alert Service Bulletin 767-53A0131, Revision 1, 
dated March 12, 2009; specifies to contact Boeing for appropriate 
action: Before further flight, repair the cracking using a method 
approved in accordance with the procedures specified in paragraph (n) 
of this AD. When replacing cracked parts per the Boeing drawings or 
repairing stringers per 767 SRM 53-00-03, approval in accordance with 
the procedures specified in paragraph (n) of this AD is not required.''
    We partially agree with the request to revise paragraph (h) of this 
final rule. In order for a method of compliance other than the 
method(s) provided by the AD to be used, that method must be approved 
under the provisions of paragraph (n) of this AD. It is crucial that 
the FAA and Boeing are aware of all repairs made to PSEs or surrounding 
structure, and that damage tolerance be performed on each repair to 
establish its effect on the fatigue life of the affected structure.
    In addition, we have determined that repairing/replacing the 
stringers in accordance with the SRM referenced by the commenter is an 
acceptable method of compliance for those specific requirements of 
paragraph (h) of this AD. We have revised paragraph (h) of this AD 
accordingly.
    However, we disagree with including references to ``Boeing 
drawings'' for replacing cracked clips and brackets. We must cite 
specific service information (with dates and revision levels) in our 
ADs and would need to have the applicable drawings submitted for review 
prior to including those drawings in an AD. Each operator may be using 
different Boeing drawings as reference for replacing cracked clips and 
brackets. In addition, we do not consider it appropriate to include 
various provisions in an AD applicable only to certain airplanes or to 
a single operator's unique use of an affected airplane. Individual 
operators may request approval of an AMOC, provided sufficient data are 
submitted to substantiate such a request.

Request To Clarify the Requirements of Paragraph (l) of the NPRM

    ABX requested clarification as to why paragraph (l) of the NPRM (75 
FR 6154, February 8, 2010) is included. ABX stated that the NPRM 
specifies the limits in each applicable paragraph, and that the NPRM 
does not refer to paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 767-53A0131, Revision 1, dated March 12, 2009. ABX 
stated that the inclusion of paragraph (l) of the NPRM leads one to 
believe that somewhere in the NPRM other limits are hidden.
    We agree to provide clarification. We have determined that 
paragraph (l) of the NPRM (75 FR 6154, February 8, 2010) was included 
unnecessarily because the NPRM did not refer to paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 767-53A0131, Revision 
1, dated March 12, 2009. Therefore, we have removed that paragraph and 
other references to it from this final rule.

Request To Revise Note 1 of the NPRM

    ABX requested that we revise Note 1 of the NPRM (75 FR 6154, 
February 8, 2010) from ``Guidance on modifying a vertical inner chord * 
* *'' to ``Approved methods on modifying a vertical inner chord * * *'' 
ABX stated that Table 1 of the NPRM lists service information that 
provides guidance on modifying a vertical inner chord. ABX noted that 
this service information does not appear to be approved by the Manager 
of the Seattle Aircraft Certification Office (ACO). ABX stated that it 
believes that this service information should be approved for 
terminating action for the condition of no cracking found during the 
most recent detailed and HFEC inspections. ABX noted that the 
modification, with the removal of the damaged area, is approved as a 
terminating action when the cracks are found. ABX stated that it 
believes that the modification should also be approved when no cracks 
are found.
    We partially agree. We agree that accomplishing the terminating 
modification specified in Boeing Alert Service Bulletin 767-53A0131, 
Revision 1, dated March 12, 2009, terminates the applicable inspections 
for airplanes on which cracking is found and those on which cracking is 
not found. We have removed Note 1 of the NPRM (75 FR 6154, February 8, 
2010) from the final rule and, instead, have revised paragraph (l) of 
the final rule to incorporate the information in Note 1 to specify that 
the optional terminating modification may also be done in

[[Page 63174]]

accordance with the applicable Boeing 767 SRM. In addition, paragraph 
(m) of this final rule specifies that if any cracking is found during 
any modification done in accordance with paragraph (l) of this AD, and 
the applicable Boeing 767 SRM specifies to contact Boeing for 
appropriate action, the cracking must be repaired in accordance with a 
method approved by the Manager of the Seattle Aircraft Certification 
Office. We also note that the SRM is an FAA-approved document.

Explanation of Additional Changes to This AD

    We have added a new table 1 to this final rule to provide the 
applicable, current SRMs; we have re-identified subsequent tables 
accordingly.
    We have changed paragraphs (i) and (l) of this final rule to 
specify specific steps of the applicable SRM identified in table 1 of 
this AD. We have also reformatted paragraphs (i) and (l) of this final 
rule to differentiate the methods of compliance, and added new Note 1 
and Note 2 to this final rule to explain the reformatting changes.
    We have revised the references to the SRM in the following 
locations to accurately identify Subject 53-80-08, Fuselage Bulkheads--
Section 48: Paragraphs (i)(2)(i) through (i)(2)(v), (i)(3), (i)(4)(i) 
through (i)(4)(v), (i)(5), (j), and (l)(1) of this AD.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been received, and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We have determined that these changes will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Explanation of Change to Costs of Compliance

    Since issuance of the NPRM (75 FR 6154, February 8, 2010), 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 hourly labor rate.

Costs of Compliance

    There are about 975 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                    Number of
                                         Work     Average                                                             U.S.-
                Action                   hours   labor rate            Parts                Cost per airplane       registered         Fleet cost
                                                  per hour                                                          airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Repetitive inspections of STA 1809.5        12          $85  None.....................  $1,020 per inspection              354  $361,080 per inspection
 (required by AD 2006-24-04 (71 FR                                                       cycle.                                  cycle.
 68432, November 27, 2006)).
Inspection of inner chord (new action)       2           85  None.....................  $170 per inspection cycle          354  $60,180 per inspection
                                                                                                                                 cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing Amendment 39-14833 (71 FR 68432, November 27, 2006) and by 
adding the following new airworthiness directive (AD):

2011-14-02 The Boeing Company: Amendment 39-16737. Docket No. FAA-
2010-0033; Directorate Identifier 2009-NM-099-AD.

Effective Date

    (a) This AD becomes effective November 16, 2011.

Affected ADs

    (b) This AD supersedes AD 2006-24-04, Amendment 39-14833, (71 FR 
68432, November 27, 2006).

Applicability

    (c) This AD applies to all The Boeing Company Model 767-200, -
300, -300F, and -400ER series airplanes, certificated in any 
category.

[[Page 63175]]

Subject

    (d) Air Transport Association (ATA) of America Code 53: 
Fuselage.

Unsafe Condition

    (e) This AD results from reported fatigue cracking in the 
vertical inner chord and the forward outer chord while doing the 
detailed inspection of the horizontal inner chord at STA 1809.5. The 
Federal Aviation Administration is issuing this AD to detect and 
correct fatigue cracking in the bulkhead structure at STA 1809.5 and 
the vertical inner chord at STA 1809.5, which could result in 
failure of the bulkhead structure for carrying the flight loads of 
the horizontal stabilizer, and consequent loss of controllability of 
the airplane.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of Requirements of AD 2006-24-04 (71 FR 68432, November 27, 
2006), With Updated Service Information

Repetitive Inspections and Corrective Actions

    (g) Before the accumulation of 15,000 total flight cycles, or 
within 3,000 flight cycles after January 2, 2007 (the effective date 
of AD 2006-24-04 (71 FR 68432, November 27, 2006)), whichever is 
later: Do the detailed and high frequency eddy current (HFEC) 
inspections for cracking as specified in Parts 1, 2, 3, and 4 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 767-
53A0131, dated March 30, 2006; or Revision 1, dated March 12, 2009; 
and do all corrective actions before further flight; by 
accomplishing all the actions specified in the Accomplishment 
Instructions of Boeing Alert Service Bulletin 767-53A0131, dated 
March 30, 2006; or Revision 1, dated March 12, 2009; except as 
provided by paragraph (h) of this AD. After the effective date of 
this AD, use only Boeing Alert Service Bulletin 767-53A0131, 
Revision 1, dated March 12, 2009. Repeat the inspections thereafter 
at intervals not to exceed 6,000 flight cycles. Accomplishing the 
corrective action for the inspections specified in Part 1, 2, 3, or 
4, as applicable, of Boeing Alert Service Bulletin 767-53A0131, 
dated March 30, 2006; or Revision 1, dated March 12, 2009; as 
applicable; terminates the repetitive inspections for that area 
only.

Exceptions to Service Bulletin

    (h) If any cracking is found in the skin or in any structure 
other than the forward outer chord, horizontal inner chord, or 
vertical inner chord during any inspection required by paragraph (g) 
or (k) of this AD, and Boeing Alert Service Bulletin 767-53A0131, 
dated March 30, 2006; or Revision 1, dated March 12, 2009; specifies 
to contact Boeing for appropriate action: Before further flight, 
repair the cracking using a method approved in accordance with the 
procedures specified in paragraph (n) of this AD; except that 
repairing or replacing stringers in accordance with Subject 53-00-
03--Fuselage Stringers, of the applicable SRM identified in table 1 
of this AD is an acceptable method of compliance for those specific 
actions required by this AD.

Optional Terminating Action for the Repetitive Inspections Required by 
Paragraph (g) of This AD

    (i) For airplanes on which no cracking is found during the most 
recent detailed and HFEC inspections for a specified area as 
required by paragraph (g) of this AD: Paragraphs (i)(1) through 
(i)(5) of this AD provide optional terminating action for the 
repetitive inspections required by paragraph (g) of this AD for the 
specified area only.
    (1) Modification of a specified area in accordance with a method 
approved by the Manager, Seattle Aircraft Certification Office 
(ACO), FAA, terminates the repetitive inspections required by 
paragraph (g) of this AD for that area only.
    (2) Modification of a forward outer chord in accordance with the 
procedures specified in paragraphs (i)(2)(i) through (i)(2)(v) of 
this AD, as applicable, terminates the repetitive inspections 
required by paragraph (g) of this AD for that area only.
    (i) For Model 767-200 series airplanes: Steps 4.A through 4.C 
and Steps 4.G through 4.P of Repair 9, dated April 15, 2006, of 
Subject 53-80-08, Fuselage Bulkheads--Section 48, of the Boeing 767-
200 Structural Repair Manual (SRM), Document D634T201.
    (ii) For Model 767-300 series airplanes: Steps 4.A through 4.C 
and Steps 4.G through 4.P of Repair 9, dated April 15, 2006, of 
Subject 53-80-08, Fuselage Bulkheads--Section 48, of the Boeing 767-
300 SRM, Document D634T210.
    (iii) For Model 767-300F series airplanes: Steps 4.A through 4.C 
and Steps 4.G through 4.P of Repair 9, dated April 15, 2006, of 
Subject 53-80-08, Fuselage Bulkheads--Section 48, of the Boeing 767-
300F SRM, Document D634T215.
    (iv) For Model 767-300BCF series airplanes: Steps 4.A through 
4.C and Steps 4.G through 4.P of Repair 9, dated April 15, 2006, of 
Subject 53-80-08, Fuselage Bulkheads--Section 48, of the Boeing 767-
300BCF SRM, D634T235.
    (v) For Model 767-400 series airplanes: Steps 4.A through 4.C 
and Steps 4.G through 4.P of Repair 9, dated April 15, 2006, of 
Subject 53-80-08, Fuselage Bulkheads--Section 48, of the Boeing 767-
400 SRM, Document D634T225.
    (3) Modification of a forward outer chord in accordance with 
Steps 4.A through 4.C and 4.G through 4.P of Repair 9 of Subject 53-
80-08, Fuselage Bulkheads--Section 48, of the applicable SRM 
identified in table 1 of this AD also terminates the repetitive 
inspections required by paragraph (g) of this AD for that area.
    (4) Modification of a horizontal inner chord in accordance with 
the procedures specified in paragraphs (i)(4)(i) through (i)(4)(v) 
of this AD, as applicable, terminates the repetitive inspections 
required by paragraph (g) of this AD for that area.
    (i) For Model 767-200 series airplanes: Steps 4.A, 4.B, and 4.F 
through 4.P of Repair 10, dated April 15, 2006, of Subject 53-80-08, 
Fuselage Bulkheads--Section 48, of the Boeing 767-200 SRM, Document 
D634T201.
    (ii) For Model 767-300 series airplanes: Steps 4.A, 4.B, and 4.F 
through 4.P of Repair 10, dated April 15, 2006, of Subject 53-80-08, 
Fuselage Bulkheads--Section 48, of the Boeing 767-300 SRM, Document 
D634T210.
    (iii) For Model 767-300F series airplanes: Steps 4.A, 4.B, and 
4.F through 4.P of Repair 10, dated April 15, 2006, of Subject 53-
80-08, Fuselage Bulkheads--Section 48, of the Boeing 767-300F SRM, 
Document D634T215.
    (iv) For Model 767-300BCF series airplanes: Steps 4.A, 4.B, and 
4.F through 4.P of Repair 10, dated April 15, 2006, of Subject 53-
80-08, Fuselage Bulkheads--Section 48, of the Boeing 767-300BCF SRM, 
Document D634T235.
    (v) For Model 767-400 series airplanes: Steps 4.A, 4.B, and 4.F 
through 4.P of Repair 10, dated April 15, 2006, of Subject 53-80-08, 
Fuselage Bulkheads--Section 48, of the Boeing 767-400 SRM, Document 
D634T225.
    (5) Modification of a horizontal inner chord in accordance with 
Steps 4.A, 4.B, and 4.F through 4.P of Repair 10 of Subject 53-80-
08, Fuselage Bulkheads--Section 48, of the applicable SRM identified 
in Table 1 of this AD also terminates the repetitive inspections 
required by paragraph (g) of this AD for that area.

                          Table 1--Revised SRMs
------------------------------------------------------------------------
             SRM                Revision               Date
------------------------------------------------------------------------
Boeing 767-200 SRM, Document         105  December 15, 2010.
 D634T201.
Boeing 767-300 SRM, Document          85  December 15, 2010.
 D634T210.
Boeing 767-300F SRM, Document         49  December 15, 2010.
 D634T215.
Boeing 767-300BCF SRM,                 9  December 15, 2010.
 Document D634T235.
Boeing 767-400 SRM, Document          32  December 15, 2010.
 D634T225.
------------------------------------------------------------------------



[[Page 63176]]

    Note 1: We have reformatted paragraph (i) of this AD to 
differentiate the methods of compliance specified in that paragraph.

Credit for Previously Accomplished Repairs

    (j) Repair of a forward outer chord done before January 2, 2007, 
in accordance with Repair 9, dated April 15, 2006, of Subject 53-80-
08, Fuselage Bulkheads--Section 48, of the Boeing 767-200 SRM, 
Document D634T201; Boeing 767-300 SRM, Document D634T210; Boeing 
767-300F SRM, Document D634T215; Boeing 767-300BCF SRM, D634T235; or 
Boeing 767-400 SRM, Document D634T225; as applicable; is acceptable 
for compliance with the requirements of paragraph (g) of this AD for 
that area only. Repair of a horizontal inner chord before January 2, 
2007, in accordance with Repair 10, dated April 15, 2006, of Subject 
53-80-08, Fuselage Bulkheads--Section 48, of the Boeing 767-200 SRM, 
Document D634T201; Boeing 767-300 SRM, Document D634T210; Boeing 
767-300F SRM, Document D634T215; Boeing 767-300BCF SRM, Document 
D634T235; or Boeing 767-400 SRM, Document D634T225; as applicable; 
is acceptable for compliance with the terminating requirements of 
paragraph (g) of this AD for that area only.

New Requirements of This AD

Inspections

    (k) At the later of the times specified in paragraphs (k)(1) and 
(k)(2) of this AD: Do the detailed and HFEC inspections for cracking 
as specified in Parts 5 and 6 of the Accomplishment Instructions of 
Boeing Alert Service Bulletin 767-53A0131, Revision 1, dated March 
12, 2009; and do all applicable corrective actions by accomplishing 
all the actions specified in the Accomplishment Instructions of 
Boeing Alert Service Bulletin 767-53A0131, Revision 1, dated March 
12, 2009; except as provided by paragraph (h) of this AD. Do all 
applicable corrective actions before further flight. Repeat the 
inspections thereafter at intervals not to exceed 6,000 flight 
cycles. Accomplishing the corrective action for the inspections 
specified in Part 5 or 6 of the Accomplishment Instructions of 
Boeing Alert Service Bulletin 767-53A0131, Revision 1, dated March 
12, 2009, as applicable, terminates the repetitive inspections for 
that area only.
    (1) Before the accumulation of 15,000 total flight cycles or 
within 6,000 flight cycles after the inspection required by 
paragraph (g) of this AD, whichever occurs later.
    (2) Within 30 days after the effective date of this AD.

Optional Terminating Action for the Repetitive Inspections Required by 
Paragraph (k) of This AD

    (l) For airplanes on which no cracking is found during the most 
recent detailed and HFEC inspections for a specified area, as 
required by paragraph (k) of this AD: Paragraphs (l)(1) and (l)(2) 
of this AD provide optional terminating action for the repetitive 
inspections required by paragraph (k) of this AD for that area only. 
After the effective date of this AD, only the applicable SRM 
identified in table 1 of this AD or a method approved by the 
Manager, Seattle ACO, may be used.
    (1) Modify the specified area in accordance with Steps 4.A 
through 4.C and 4.G through 4.Q of Repair 11 of Subject 53-80-08, 
Fuselage Bulkheads--Section 48, of the applicable SRM identified in 
table 1 or table 2 of this AD, except as provided by paragraph (m) 
of this AD.
    (2) Modify the specified area in accordance with a method 
approved by the Manager, Seattle ACO.

                         Table 2--Previous SRMs
------------------------------------------------------------------------
           Steps--                   Dated--                Of--
------------------------------------------------------------------------
4.A through 4.C and 4.G       August 15, 2008.....  Boeing 767-200 SRM,
 through 4.Q of Repair 11 of                         Document D634T201.
 Subject 53-80-08.
4.A through 4.C and 4.G       August 15, 2008.....  Boeing 767-300 SRM,
 through 4.Q of Repair 11 of                         Document D634T210.
 Subject 53-80-08.
4.A through 4.C and 4.G       August 15, 2008.....  Boeing 767-300F SRM,
 through 4.Q of Repair 11 of                         Document D634T215.
 Subject 53-80-08.
4.A through 4.C and 4.G       August 15, 2008.....  Boeing 767-300BCF
 through 4.Q of Repair 11 of                         SRM, Document
 Subject 53-80-08.                                   D634T235.
4.A through 4.C and 4.G       August 15, 2008.....  Boeing 767-400 SRM,
 through 4.Q of Repair 11 of                         Document D634T225.
 Subject 53-80-08.
------------------------------------------------------------------------


    Note 2: We have reformatted paragraph (l) of this AD to 
differentiate the methods of compliance specified in that paragraph.

Exception to SRM Modification Specified in Paragraph (l) of This AD

    (m) If, during accomplishment of any modification in accordance 
with paragraph (l) of this AD, any cracking is found and the 
applicable SRM referenced in paragraph (l) of this AD specifies to 
contact Boeing for appropriate action: Before further flight, repair 
the cracking in accordance with a method approved by the Manager, 
Seattle ACO. 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.

Alternative Methods of Compliance (AMOCs)

    (n)(1) The Manager, Seattle ACO, 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. Or, e-mail information to <a href="/cdn-cgi/l/email-protection#635a4e222d2e4e30060217170f064e22202c4e222e2c204e3106121606101710230502024d040c15"><span class="__cf_email__" data-cfemail="61584c202f2c4c32040015150d044c20222e4c202c2e224c3304101404121512210700004f060e17">[email&#160;protected]</span></a>.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Seattle ACO, to make 
those findings. For a repair method to be approved, the repair must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.
    (4) AMOCs approved previously in accordance with AD 2006-24-04 
(71 FR 68432, November 27, 2006) are approved as AMOCs for the 
corresponding provisions of this AD.

Material Incorporated by Reference

    (o) You must use the service information specified in paragraph 
(o)(1) of this AD to do the actions required by this AD, unless the 
AD specifies otherwise. If you accomplish the optional actions 
specified by this AD, you must use the service information specified 
in paragraph (o)(2) of this AD to perform those actions, unless the 
AD specifies otherwise. The Director of the Federal Register 
approved the incorporation by reference (IBR) under 5 U.S.C. 552(a) 
and 1 CFR part 51 of the following service information on November 
16, 2011:
    (1) Boeing Alert Service Bulletin 767-53A0131, Revision 1, dated 
March 12, 2009.
    (2) Subject 53-00-03, Fuselage Stringers, of Chapter 53, 
Fuselage; or Subject 53-80-08, Fuselage Bulkheads--Section 48, 
Repair 9--Station 1809.5 Bulkhead--Forward Outer Chord Repair 
Between S-4 to S-8, Repair 10--Station 1809.5 Bulkhead--Horizontal 
Inner Chord Repair at Approximately WL 257 and BL 28, or Repair 11--
Station 1809.5 Bulkhead--Vertical Inner Chord Repair at 
Approximately WL 256 and BL 30, as applicable, of Chapter 53, 
Fuselage; as applicable; of the applicable Structural Repair Manual 
(SRM) specified in paragraphs (o)(2)(i) through (o)(2)(v) of this 
AD.
    (i) Boeing 767-200 SRM, Document D634T201, Revision 105, dated 
December 15, 2010. Only the transmittal letter, dated

[[Page 63177]]

December 15, 2010, of this document contains the revision level of 
the document.
    (ii) Boeing 767-300 SRM, Document D634T210, Revision 85, dated 
December 15, 2010. Only page 1 of the transmittal letter, dated 
December 15, 2010, of this document contains the revision level of 
the document.
    (iii) Boeing 767-300F SRM, Document D634T215, Revision 49, dated 
December 15, 2010. Only page 1 of the transmittal letter, dated 
December 15, 2010, of this document contains the revision level of 
the document.
    (iv) Boeing 767-300BCF SRM, Document D634T235, Revision 9, dated 
December 15, 2010. Only page 1 of the transmittal letter, dated 
December 15, 2010, of this document contains the revision level of 
the document.
    (v) Boeing 767-400 SRM, Document D634T225, Revision 32, dated 
December 15, 2010. Only page 1 of the transmittal letter, dated 
December 15, 2010, of this document contains the revision level of 
the document.
    (3) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 
206-544-5000, extension 1; fax 206-766-5680; e-mail 
<a href="/cdn-cgi/l/email-protection#cca1a9e2aea3a9afa3a18caea3a9a5a2abe2afa3a1"><span class="__cf_email__" data-cfemail="e68b83c884898385898ba68489838f8881c885898b">[email&#160;protected]</span></a>; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
    (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: <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>.

    Issued in Renton, Washington, on September 23, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-25618 Filed 10-11-11; 8:45 am]
BILLING CODE 4910-13-P