AD 2015-26-07

[Federal Register Volume 80, Number 251 (Thursday, December 31, 2015)]
[Rules and Regulations]
[Pages 81738-81742]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2015-32596]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0683; Directorate Identifier 2014-NM-196-AD; 
Amendment 39-18355; AD 2015-26-07]
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 767-200, -300, and -300F series airplanes. This AD 
was prompted by a finding that certain barrel nuts installed at the 
vertical fin may be subject to stress corrosion and cracking. This AD 
requires either repetitive inspections of vertical fin barrel nuts for 
corrosion or a magnetic check to identify certain barrel nuts, and 
corrective actions if necessary. We are issuing this AD to detect and 
correct corroded and loose barrel nuts that attach the vertical fin to 
body section 48; this condition could result in reduced structural 
integrity of the vertical fin attachment joint, loss of the vertical 
fin, and consequent loss of controllability of the airplane.

DATES: This AD is effective February 4, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of February 4, 
2016.

ADDRESSES: For service information identified in this final rule, 
contact Boeing Commercial Airplanes, Attention: Data & Services 
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 
206-544-5000, extension 1; fax 206-766-5680; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2015-
0683; 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 Docket 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: Wayne Lockett, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6447; fax: 425-917-6590; email: <a href="/cdn-cgi/l/email-protection#3b4c5a42555e15575458505e4f4f7b5d5a5a155c544d"><span class="__cf_email__" data-cfemail="9aedfbe3f4ffb4f6f5f9f1ffeeeedafcfbfbb4fdf5ec">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all The Boeing Company 
Model 767-200, -300, and -300F series airplanes. The NPRM published in 
the Federal Register on April 10, 2015 (80 FR 19248). The NPRM was 
prompted by a finding that certain barrel nuts installed at the 
vertical fin may be subject to stress corrosion and cracking. The NPRM 
proposed to require either

[[Page 81739]]

repetitive inspections of vertical fin barrel nuts for corrosion or a 
magnetic check to identify certain barrel nuts, and corrective actions 
if necessary. We are issuing this AD to detect and correct corroded and 
loose barrel nuts that attach the vertical fin to body section 48; this 
condition could result in reduced structural integrity of the vertical 
fin attachment joint, loss of the vertical fin, and consequent loss of 
controllability of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (80 
FR 19248, April 10, 2015) and the FAA's response to each comment.

Request To Revise Applicability

    Boeing and Air New Zealand requested that additional clarification 
be added to paragraph (c) of the proposed AD (80 FR 19248, April 10, 
2015). Boeing stated that this addition will add clarity because there 
is an existing AD (AD 2003-10-11, Amendment 39-13156 (68 FR 28703, May 
27, 2003)) of a similar subject that covers only Boeing Model 767 
airplanes, line numbers 1 through 574 inclusive. Boeing requested we 
clarify that Boeing Alert Service Bulletin 767-53A0261, dated August 
12, 2014, addresses only Boeing Model 767 airplanes with line numbers 
575 through 681 inclusive. Air New Zealand asked whether the NPRM would 
supersede AD 2003-10-11.
    We agree to provide clarification. Only Model 767 airplanes with 
line numbers 575 through 681 inclusive are affected by this AD. Some 
proposed requirements overlap with the requirements of AD 2003-10-11, 
Amendment 39-13156 (68 FR 28703, May 27, 2003). We have therefore 
revised the applicability of this AD to specify airplanes identified in 
Boeing Alert Service Bulletin 767-53A0261, dated August 12, 2014, which 
limits the applicability to line numbers 575 through 681 inclusive.

Request To Add Clarification About the Previous Replacement of 
Discovered H-11 Barrel Nuts With Inconel Alternatives

    Boeing stated that operators may have already replaced discovered 
H-11 barrel nuts with Inconel alternatives. Boeing requested that we 
revise the NPRM (80 FR 19248, April 10, 2015) to specify the 
``Compliance Time Exceptions'' noted in paragraph 1.E., ``Compliance,'' 
of Boeing Alert Service Bulletin 767-53A0261, dated August 12, 2014. 
Those ``exceptions'' would specify that no further action is required 
at the vertical stabilizer attachment point, provided the following 
conditions are met:
    <bullet> The vertical stabilizer attachment barrel nut has been 
inspected;
    <bullet> No H-11 steel barrel nut was found during the inspection; 
and
    <bullet> Any replacement barrel nut is either a drawing 
configuration barrel nut made from an alternative material to H-11 
steel; or a barrel nut made from alternative material to H-11 steel 
approved by the FAA or by a Boeing Company Authorized Representative.
    We do not agree with the request because paragraph (g) of this AD 
already makes reference to paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 767-53A0261, dated August 12, 2014, which lists 
the compliance time exceptions. We have not changed this AD regarding 
this issue.

Request To Clarify Terminating Action for Repetitive Inspections and 
Replacement

    United Parcel Service (UPS) requested that we provide terminating 
action similar to that provided in paragraph (i) of AD 2013-18-02, 
Amendment 39-17575 (78 FR 57049, September 17, 2013).
    We agree with the commenter's request. The NPRM (80 FR 19248, April 
10, 2015) is not clear whether the repetitive inspections are 
terminated by replacement with an Inconel barrel nut or by a finding of 
no H-11 steel barrel nut installed. Replacing a barrel nut at an 
attachment point location with a new Inconel barrel nut in accordance 
with Part 5 of Boeing Alert Service Bulletin 767-53A0261, dated August 
12, 2014, terminates the inspections and replacement required by 
paragraph (g) of this AD for that attachment point location only. In 
addition, if no H-11 steel barrel nut is found installed at an 
attachment point location, the repetitive inspections and replacement 
required by paragraph (g) of this AD are terminated for that attachment 
location only. We have added a new paragraph (h) to this AD to clarify 
the terminating action and redesignated the subsequent paragraphs 
accordingly.

Request For Clarification of Barrel Nuts To Be Replaced

    UPS requested that we provide clarification of paragraph 
(g)(1)(ii)(B) of the proposed AD (80 FR 19248, April 10, 2015). UPS 
stated that its interpretation of paragraph (g)(1)(ii)(B) of the 
proposed AD is that replacement of only H-11 steel barrel nuts is 
required, although it appears that all barrel nuts are to be replaced, 
even if the installed barrel nuts are Inconel or other approved barrel 
nuts.
    We agree that clarification is necessary. Operators are required to 
do all actions specified in either paragraph (g)(1) or (g)(2) of this 
AD. Paragraph (g)(1) of this AD is only an internal and external 
detailed inspection of the barrel nuts and does not provide a method 
for determination of the material of the barrel nuts. Paragraph (g)(2) 
of this AD provides the method to determine if the material of the 
barrel nuts is H-11 steel.
    Therefore, if operators have chosen to do the internal and external 
inspections along with the torque check specified in paragraph (g)(1) 
of this AD, and have not chosen to do the magnetic check specified in 
paragraph (g)(2) of this AD, then they have not determined the material 
of the barrel nuts. For airplanes on which the material of the barrel 
nuts has not been determined, the requirement is to replace all barrel 
nuts, as required by paragraph (g)(1)(ii)(B) of this AD.
    Operators choosing to do the magnetic check specified in paragraph 
(g)(2) of this AD would have determined the material of the barrel 
nuts, and may replace only H-11 steel barrel nuts, as required by 
paragraph (g)(2)(i)(B)(2) of this AD.
    Operators are not permitted to mix actions from paragraphs (g)(1) 
and (g)(2) of this AD. Operators may, however, submit requests for 
approval of an alternative method of compliance (AMOC) to the 
requirements of paragraph (g) of this AD along with justification of an 
equivalent level of safety. We have not changed this AD regarding this 
issue.

Request For Clarification of Compliance Time

    UPS requested that we provide an exception to the initial 
inspection thresholds of the ``last Torque Check Inspection'' specified 
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
767-53A0261, dated August 12, 2014. The specified compliance time is 
the later of 24 months after issuance of the service information or 36 
months after the last torque check inspection specified in Task 53-734-
00, ``Internal, Special Detailed, Vertical Stabilizer Attach Bolt, of 
Section 2, ``Structural Maintenance Requirements,'' of the Boeing Model 
767 Maintenance Planning Document. The commenter understands that the 
most recent accomplishment of Task 53-734-00 must be done prior to the 
effective date of this AD. The commenter added that if the initial 
inspection required by paragraph (g)(1) or (g)(2) of the proposed AD 
(80 FR 19248, April 10, 2015) is

[[Page 81740]]

done from the most recent accomplishment of Task 53-734-00 and that 
accomplishment occurs after the effective date of this AD, the time 
limits given in paragraphs (g)(1)(ii)(B) and (g)(2)(i)(B)(2) of this 
proposed AD may be exceeded (i.e., will have already passed).
    We agree with the commenter's request and rationale regarding 
providing an exception to the specified initial inspection threshold. 
We have redesignated paragraph (h) of the proposed AD (80 FR 19248, 
April 10, 2015) as paragraph (i)(1) of this AD and added new paragraph 
(i)(2) to this AD to provide a compliance time exception to address the 
issue described by the commenter. If the most recent accomplishment of 
Task 53-734-00 occurs after the effective date of this AD, then 
operators still have to comply with the requirements of paragraph 
(g)(1) or (g)(2) of this AD.

Request For Clarification of Effect of Winglets on Accomplishment of 
the Proposed Actions

    Aviation Partners Boeing stated that accomplishing the supplemental 
type certificate (STC) ST01920SE (<a href="http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027F43B9A7486E86257B1D006591EE">http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027F43B9A7486E86257B1D006591EE</a>) does not affect the actions specified 
in the NPRM (80 FR 19248, April 10, 2015).
    We agree with the commenter's statement. We have redesignated 
paragraph (c) of the proposed AD (80 FR 19248, April 10, 2015) as 
paragraph (c)(1) of this AD, and added new paragraph (c)(2) to this AD 
to state that installation of STC ST01920SE (<a href="http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027F43B9A7486E86257B1D006591EE">http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027F43B9A7486E86257B1D006591EE</a>) does not affect the ability to 
accomplish the actions required by this AD. Therefore, for airplanes on 
which STC ST01920SE (<a href="http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027F43B9A7486E86257B1D006591EE">http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027F43B9A7486E86257B1D006591EE</a>) is installed, a ``change in product'' 
AMOC approval request is not necessary to comply with the requirements 
of 14 CFR 39.17.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
    <bullet> [Agr]re consistent with the intent that was proposed in 
the NPRM (80 FR 19248, April 10, 2015) for correcting the unsafe 
condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 19248, April 10, 2015).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Boeing has issued Alert Service Bulletin 767-53A0261, dated August 
12, 2014. The service information describes procedures for repetitive 
internal and external detailed inspections of the barrel nut holes and 
sealant for cracked/damaged sealant, corrosion, or a cracked/broken 
barrel nut, and replacement of the barrel nut with a new Inconel barrel 
nut if necessary. The service information also describes procedures for 
repetitive torque checks on each affected vertical fin attachment bolt, 
or, alternatively, a magnetic check to identify H-11 steel barrel nuts, 
and replacement with a new Inconel barrel nut if necessary.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 38 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on  U.S.
             Action                    Labor cost         Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Option 1: Detailed inspections    4 work-hours x $85            (\1\)   Up to $482,661 per   Up to $18,341,118.
 and torque check.                 per hour = $340                       inspection cycle.
                                   per inspection
                                   cycle.
Option 2: Magnetic check........  4 work-hours x $85               $0   $340...............  $12,920.
                                   per hour = $340.
----------------------------------------------------------------------------------------------------------------
\1\ For the torque check, operators may choose to rent a special tool, with rental costs up to $482,321.

    We estimate that replacing any barrel nut would take 1 work-hour, 
at an average labor rate of $85 per work-hour. We have received no 
definitive data that would enable us to provide cost estimates for the 
cost of replacement parts. We have no way of determining the number of 
aircraft that might need these replacements.
    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all available costs in our 
cost estimate.

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 81741]]

    (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):

2015-26-07 The Boeing Company: Amendment 39-18355; Docket No. FAA-
2015-0683; Directorate Identifier 2014-NM-196-AD.

(a) Effective Date

    This AD is effective February 4, 2016.

(b) Affected ADs

    None.

(c) Applicability

    (1) This AD applies to The Boeing Company Model 767-200, -300, -
300F series airplanes, certificated in any category, as identified 
in Boeing Alert Service Bulletin 767-53A0261, dated August 12, 2014.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01920SE (<a href="http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027F43B9A7486E86257B1D006591EE">http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027F43B9A7486E86257B1D006591EE</a>) does not affect the 
ability to accomplish the actions required by this AD. Therefore, 
for airplanes on which STC ST01920SE (<a href="http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027F43B9A7486E86257B1D006591EE">http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027F43B9A7486E86257B1D006591EE</a>) is installed, a ``change in 
product'' alternative method of compliance (AMOC) approval request 
is not necessary to comply with the requirements of 14 CFR 39.17.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a finding that certain barrel nuts 
installed at the vertical fin may be subject to stress corrosion and 
cracking. We are issuing this AD to detect and correct corroded and 
loose barrel nuts that attach the vertical fin to body section 48; 
this condition could result in reduced structural integrity of the 
vertical fin attachment joint, loss of the vertical fin, and 
consequent loss of controllability of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Inspection

    For airplanes identified in Boeing Alert Service Bulletin 767-
53A0261, dated August 12, 2014: Do the actions specified in 
paragraph (g)(1) or (g)(2) of this AD, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 767-
53A0261, dated August 12, 2014. Signs of corrosion include, but are 
not limited to, sealant cracks, sealant bulging, powder residue, and 
cracked barrel nuts.
    (1) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 767-53A0261, dated 
August 12, 2014, except as provided by paragraph (i) of this AD: Do 
internal and external detailed inspections of the barrel nuts and 
sealant for signs of corrosion, and do a torque check of the 
vertical stabilizer attachment bolts for loose barrel nuts.
    (i) If corrosion or any loose barrel nut is found at any 
attachment point location, before further flight, replace the barrel 
nut with a new Inconel barrel nut.
    (ii) If no corrosion or loose barrel nut is found at any 
attachment point location, do the actions specified in paragraphs 
(g)(1)(ii)(A) and (g)(1)(ii)(B) of this AD.
    (A) Repeat the inspections and torque check thereafter at 
intervals not to exceed 18 months until the replacement specified in 
paragraph (g)(1)(ii)(B) of this AD is done at that attachment point 
location.
    (B) Within 36 months after the effective date of this AD, 
replace all barrel nuts with new Inconel barrel nuts.
    (2) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 767-53A0261, dated 
August 12, 2014, except as provided by paragraph (i) of this AD: Do 
a magnetic check to identify H-11 steel barrel nuts.
    (i) If any H-11 steel barrel nut is found at any attachment 
point location, before further flight, do an internal and external 
detailed inspection of the barrel nut holes and sealant for signs of 
corrosion, and do a torque check of the vertical stabilizer 
attachment bolts for loose barrel nuts.
    (A) If corrosion or any loose barrel nut is found, before 
further flight, replace the barrel nut with a new Inconel barrel 
nut.
    (B) If no corrosion or loose barrel nut is found, do the actions 
specified in paragraphs (g)(2)(i)(B)(1) and (g)(2)(i)(B)(2) of this 
AD.
    (1) Repeat the inspections and torque check thereafter at 
intervals not to exceed 18 months until the replacement specified in 
paragraph (g)(2)(i)(B)(2) of this AD is done at that attachment 
point location.
    (2) Within 36 months after the effective date of this AD, 
replace all H-11 steel barrel nuts with new Inconel barrel nuts.
    (ii) If no H-11 steel barrel nut is found at all attachment 
point locations, no further work is required by this paragraph.

(h) Terminating Action for Repetitive Inspections and Replacement

    (1) Replacing a barrel nut at an attachment point location with 
a new Inconel barrel nut, in accordance with Part 5 of Boeing Alert 
Service Bulletin 767-53A0261, dated August 12, 2014, terminates the 
inspections and replacement required by paragraph (g) of this AD for 
that attachment point location only.
    (2) If no H-11 steel barrel nut is found installed at an 
attachment point location, the repetitive inspections and 
replacement required by paragraph (g) of this AD are terminated for 
that attachment location only.

(i) Exception to Service Information Specifications

    (1) Where Boeing Alert Service Bulletin 767-53A0261, dated 
August 12, 2014, specifies a compliance time ``after the Original 
Issue date of this Service Bulletin,'' this AD requires compliance 
within the specified compliance time after the effective date of 
this AD.
    (2) Where Boeing Alert Service Bulletin 767-53A0261, dated 
August 12, 2014, specifies a compliance time after the ``last Torque 
Check Inspection'' in accordance with Task 53-734-00, ``Internal, 
Special Detailed, Vertical Stabilizer Attach Bolt, of Section 2, 
Structural Maintenance Requirements,'' of the Boeing Model 767 
Maintenance Planning Document, that compliance time only applies if 
the most recent accomplishment of Task 53-734-00 occurred on or 
before the effective date of this AD.

(j) Parts Installation Prohibition

    As of the effective date of this AD, no person may install an H-
11 steel barrel nut on the vertical stabilizer of any airplane.

(k) 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 paragraph (l)(1) of this AD. 
Information may be emailed to: <a href="/cdn-cgi/l/email-protection#41786c000f0c6c12242035352d246c00020e6c000c0e026c1324303424323532012720206f262e37"><span class="__cf_email__" data-cfemail="dde4f09c9390f08eb8bca9a9b1b8f09c9e92f09c90929ef08fb8aca8b8aea9ae9dbbbcbcf3bab2ab">[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, modification, or alteration 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

[[Page 81742]]

ACO, to make those findings. To be approved, the repair method, 
modification deviation, or alteration deviation must meet the 
certification basis of the airplane, and the approval must 
specifically refer to this AD.
    (4) For service information that contains steps that are labeled 
as Required for Compliance (RC), the provisions of paragraphs 
(k)(4)(i) and (k)(4)(ii) apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. An AMOC is required for any deviations to RC steps, 
including substeps and identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(l) Related Information

    (1) For more information about this AD, contact Wayne Lockett, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6447; fax: 425-917-6590; email: 
<a href="/cdn-cgi/l/email-protection#8afdebf3e4efa4e6e5e9e1effefecaecebeba4ede5fc"><span class="__cf_email__" data-cfemail="a9dec8d0c7cc87c5c6cac2ccdddde9cfc8c887cec6df">[email&#160;protected]</span></a>.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. You may view this referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Alert Service Bulletin 767-53A0261, dated August 12, 
2014.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
    (4) You may view this service information at FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this 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/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on December 9, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-32596 Filed 12-30-15; 8:45 am]
 BILLING CODE 4910-13-P