[Federal Register Volume 81, Number 37 (Thursday, February 25, 2016)]
[Proposed Rules]
[Pages 9370-9374]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-03690]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-3702; Directorate Identifier 2015-NM-103-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2013-24-
12, which applies to all The Boeing Company Model 747-8 and 747-8F 
airplanes. AD 2013-24-12 currently requires repetitive ultrasonic or 
dye penetrant inspections for cracking of the barrel nuts and bolts on 
each forward engine mount, and related investigative and corrective 
actions if necessary. Since we issued AD 2013-24-12, we have determined 
that it is necessary to mandate the installation of new barrel nuts or 
new inspections to adequately address the unsafe condition. This 
proposed AD would retain the requirements of AD 2013-24-12 and add 
requirements to install new barrel nuts at the forward engine mounts; 
or identify the part number of the barrel nuts, inspect affected barrel 
nuts for gaps of the strut bulkhead and forward engine mount, and do 
related investigative and corrective actions if necessary. This 
proposed AD would also remove airplanes from the applicability. We are 
proposing this AD to detect and correct cracked barrel nuts on a 
forward engine mount, which could result in reduced load capacity of 
the forward engine mount, separation of an engine under power from the 
airplane, and consequent loss of control of the airplane.

DATES: We must receive comments on this proposed AD by April 11, 2016.

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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, 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 https://www.myboeingfleet.com. 
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. It 
is also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2016-3702.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
3702; 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

[[Page 9371]]

(phone: 800-647-5527) is in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6428; fax: 425-917-6590; email: [email protected].

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-2016-3702; 
Directorate Identifier 2015-NM-103-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

    On November 19, 2013, we issued AD 2013-24-12, Amendment 39-17686 
(78 FR 71989, December 2, 2013) (``AD 2013-24-12''), for all The Boeing 
Company Model 747-8 and 747-8F airplanes. AD 2013-24-12 requires 
repetitive ultrasonic or dye penetrant inspections for cracking of the 
barrel nuts and bolts, as applicable, on each forward engine mount, and 
related investigative and corrective actions if necessary. AD 2013-24-
12 resulted from a report of cracked barrel nuts found on a forward 
engine mount. We issued AD 2013-24-12 to detect and correct cracked 
barrel nuts on a forward engine mount, which could result in reduced 
load capacity of the forward engine mount, separation of an engine 
under power from the airplane, and consequent loss of control of the 
airplane.

Actions Since AD 2013-24-12 Was Issued

    The preamble to AD 2013-24-12 explains that we considered the 
requirements ``interim action'' and were considering further 
rulemaking. We now have determined that further rulemaking is indeed 
necessary, and this proposed AD follows from that determination.

Related Service Information Under 1 CFR Part 51

    We reviewed the following service information:
     Boeing Service Bulletin 747-71A2329, Revision 1, dated May 
28, 2015. The service information describes procedures for inspecting 
for cracked bolts and barrel nuts on the forward engine mounts, 
replacing cracked bolts and barrel nuts, and sending the inspection 
results and cracked parts to Boeing.
     Boeing Special Attention Service Bulletin 747-71-2332, 
Revision 1, dated May 28, 2015. The service information describes 
procedures for installing new barrel nuts, inspecting the barrel nuts 
at the forward engine mount to determine the part number (P/N), 
inspecting for gaps of the strut bulkhead and forward engine mount, and 
doing applicable related investigative and corrective actions.
     747-8/-8F Airworthiness Limitation (AWL), Document Number 
D011U721-02-01, dated September 2015, which includes a limitation for 
Structurally Significant Item (SSI) 54-50-003c, which describes 
procedures for structural inspections.
    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.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain all requirements of AD 2013-24-12. 
This proposed AD would also require accomplishing the actions specified 
in Boeing Special Attention Service Bulletin 747-71-2332, Revision 1, 
dated May 28, 2015, described previously, except as discussed under 
``Differences Between Proposed AD and Service Information.'' For 
information on the procedures and compliance times, see this service 
information at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2016-3702.
    The phrase ``related investigative actions'' is used in this 
proposed AD. ``Related investigative actions'' are follow-on actions 
that (1) are related to the primary action, and (2) further investigate 
the nature of any condition found. Related investigative actions in an 
AD could include, for example, inspections.
    The phrase ``corrective actions'' is used in this proposed AD. 
``Corrective actions'' are actions that correct or address any 
condition found. Corrective actions in an AD could include, for 
example, repairs.

Differences Between Proposed AD and Service Information

    Boeing Special Attention Service Bulletin 747-71-2332, Revision 1, 
dated May 28, 2015, 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:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 7 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost    Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspections (retained actions      Up to 24 work-hours            $0  Up to $2,040 per      Up to $14,280 per
 from AD 2013-24-12).               x $85 per hour =                   inspection cycle.     inspection cycle.
                                    $2,040 per
                                    inspection cycle.
Installation (new proposed         17 work-hours x $85         6,384  $7,829..............  Up to $54,803.
 action).                           per hour = $1,445.

[[Page 9372]]

 
Inspections (new proposed          4 work-hours x $85              0  $340................  Up to $2,380.
 alternative actions).              per hour = $340.
Maintenance program revision (new  1 work-hour x $85               0  $85.................  $595.
 proposed requirement).             per hour = $85.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the bootstrap installation specified in this 
proposed AD. We estimate the following costs to do other necessary 
related investigative and corrective actions that would be required 
based on the results of the proposed inspection. We have no way of 
determining the number of aircraft that might need these actions:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                      Cost per
                     Action                                   Labor cost               Parts cost      product
----------------------------------------------------------------------------------------------------------------
Ultrasonic inspection...........................  5 work-hours x $85 per hour = $425           $0          $425
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this proposed 
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 costs in our cost 
estimate.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid Office of Management and Budget 
(OMB) control number. The control number for the collection of 
information required by this AD is 2120-0056. The paperwork cost 
associated with this AD has been detailed in the Costs of Compliance 
section of this document and includes time for reviewing instructions, 
as well as completing and reviewing the collection of information. 
Therefore, all reporting associated with this AD is mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing the 
burden should be directed to the FAA at 800 Independence Ave. SW., 
Washington, DC 20591. ATTN: Information Collection Clearance Officer, 
AES-200.

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 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 that the 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

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 removing Airworthiness Directive (AD) 
2013-24-12, Amendment 39-17686 (78 FR 71989, December 2, 2013), and 
adding the following new AD:

The Boeing Company: Docket No. FAA-2016-3702; Directorate Identifier 
2015-NM-103-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by April 11, 
2016.

(b) Affected ADs

    This AD replaces AD 2013-24-12, Amendment 39-17686 (78 FR 71989, 
December 2, 2013).

(c) Applicability

    This AD applies to The Boeing Company Model 747-8F and 747-8 
airplanes, certificated in any category, as identified in Boeing 
Service Bulletin 747-71A2329, Revision 1, dated May 28, 2015.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Powerplant.

[[Page 9373]]

(e) Unsafe Condition

    This AD was prompted by a report of cracked barrel nuts found on 
a forward engine mount, and by the determination that additional 
actions are necessary to address the unsafe condition. We are 
issuing this AD to detect and correct cracked barrel nuts on a 
forward engine mount, which could result in reduced load capacity of 
the forward engine mount, separation of an engine under power from 
the airplane, and consequent loss of control of the airplane.

(f) Compliance

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

(g) Retained Repetitive Inspections and Corrective Actions, With 
Revised Service Information

    This paragraph restates the actions required by paragraph (g) of 
AD 2013-24-12, Amendment 39-17686 (78 FR 71989, December 2, 2013) 
(``AD 2013-24-12''), with revised service information: Except as 
required by paragraph (h)(1) of this AD, at the time specified in 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-71A2329, dated September 27, 2013: Do the inspection specified 
in paragraph (g)(1) or (g)(2) of this AD, and do all applicable 
related investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
71A2329, dated September 27, 2013; or Boeing Service Bulletin 747-
71A2329, Revision 1, dated May 28, 2015. Do all applicable related 
investigative and corrective actions before further flight. Repeat 
the inspection thereafter at the times specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-71A2329, dated 
September 27, 2013. As of the effective date of this AD, use only 
Boeing Service Bulletin 747-71A2329, Revision 1, dated May 28, 2015.
    (1) Ultrasonic inspection for cracking of the barrel nuts on 
each forward engine mount, except as required by paragraph (h)(2) of 
this AD.
    (2) Dye penetrant inspection for cracking of the bolts and 
barrel nuts. Whenever a dye penetrant inspection is done, all the 
bolts and barrel nuts on that engine mount must be removed and 
replaced with new or serviceable parts.

(h) Retained Exceptions to Service Information Specifications, With 
Revised Service Information References

    (1) Where Boeing Alert Service Bulletin 747-71A2329, dated 
September 27, 2013; or Boeing Service Bulletin 747-71A2329, Revision 
1, dated May 28, 2015; specify a compliance time ``after the 
original issue date of this service bulletin,'' this AD requires 
compliance within the specified compliance time after December 17, 
2013 (the effective date of AD 2013-24-12).
    (2) Where Appendix B of Boeing Alert Service Bulletin 747-
71A2329, dated September 27, 2013, and Appendix B of Boeing Service 
Bulletin 747-71A2329, Revision 1, dated May 28, 2015, state that 
alternate instruments and transducers can be used, this AD requires 
that only equivalent instruments and transducers can be used.
    (3) Where Appendix A of Boeing Alert Service Bulletin 747-
71A2329, dated September 27, 2013, and Appendix A of Boeing Service 
Bulletin 747-71A2329, Revision 1, dated May 28, 2015, state to 
record flight hours and flight cycles, record the flight hours and 
flight cycles on the airplane and the flight hours and flight cycles 
for each engine since change or removal.

(i) Retained Reporting and Sending Parts, With Revised Service 
Information

    After any inspection required by paragraph (g) of this AD: 
Submit a report of the inspection results (both positive and 
negative), and return all cracked bolts and barrel nuts, at the 
applicable time specified in paragraph (i)(1) or (i)(2) of this AD. 
The report must include the information requested in Appendix A of 
Boeing Alert Service Bulletin 747-71A2329, dated September 27, 2013, 
or Appendix A of Boeing Service Bulletin 747-71A2329, Revision 1, 
dated May 28, 2015, except as required by paragraph (h)(3) of this 
AD. Both the report and all cracked bolts and barrel nuts must be 
sent to the address specified in Appendix A of Boeing Alert Service 
Bulletin 747-71A2329, dated September 27, 2013, or Appendix A of 
Boeing Service Bulletin 747-71A2329, Revision 1, dated May 28, 2015.
    (1) For airplanes on which an ultrasonic inspection was done and 
no cracking was found, do the required actions at the time specified 
in paragraph (i)(1)(i) or (i)(1)(ii) of this AD, as applicable.
    (i) If the inspection was done on or after December 17, 2013 
(the effective date of AD 2013-24-12): Submit the report within 10 
days after the inspection.
    (ii) If the inspection was done before December 17, 2013 (the 
effective date of AD 2013-24-12): Submit the report within 10 days 
after December 17, 2013 (the effective date of AD 2013-24-12).
    (2) For airplanes on which a dye penetrant inspection was done, 
do the required actions at the time specified in paragraph (i)(2)(i) 
or (i)(2)(ii) of this AD, as applicable.
    (i) If the inspection was done on or after December 17, 2013 
(the effective date of AD 2013-24-12): Submit the report and return 
all cracked bolts and barrel nuts within 10 days after replacing the 
bolts and barrel nuts with new or serviceable bolts and barrel nuts 
in accordance with Part 2 of the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-71A2329, dated September 27, 2013; 
or Boeing Service Bulletin 747-71A2329, Revision 1, dated May 28, 
2015.
    (ii) If the inspection was done before December 17, 2013 (the 
effective date of AD 2013-24-12): Submit the report and return all 
cracked bolts and barrel nuts within 10 days after December 17, 2013 
(the effective date of AD 2013-24-12).

(j) Retained Paperwork Reduction Act Burden Statement, With No Changes

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty 
for failure to comply with a collection of information subject to 
the requirements of the Paperwork Reduction Act unless that 
collection of information displays a current valid Office of 
Management and Budget (OMB) Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(k) New Installation or Inspections

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Special Attention Service Bulletin 747-71-
2332, Revision 1, dated May 28, 2015, except as required by 
paragraph (o)(1) of this AD: Do the actions specified in paragraph 
(k)(1) or (k)(2) of this AD, in accordance with the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 747-71-
2332, Revision 1, dated May 28, 2015, except as required by 
paragraph (o)(2) of this AD.
    (1) Install new barrel nuts using the bootstrap installation 
method identified in Part 1 of the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 747-71-2332, Revision 1, 
dated May 28, 2015.
    (2) Do a general visual inspection to determine the part number 
(P/N) of the barrel nuts at the forward engine mount. If any barrel 
nut P/N SL4081C14SP1 is installed, before further flight, do a 
general visual inspection for gaps of the strut bulkhead and forward 
engine mount to determine if the nut-by-but method identified in 
Part 4 of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 747-71-2332, Revision 1, dated May 28, 
2015, can be used, and do all applicable related investigative and 
corrective actions. Do all applicable related investigative and 
corrective actions before further flight, including the nut-by-nut 
replacement identified in Part 4 of the Accomplishment Instructions 
of Boeing Special Attention Service Bulletin 747-71-2332, Revision 
1, dated May 28, 2015. If the nut-by-nut replacement identified in 
Part 4 of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 747-71-2332, Revision 1, dated May 28, 
2015 cannot be accomplished, install new nuts, in accordance with 
paragraph (k)(1) of this AD.

(l) Maintenance Program Revision

    Within 30 days after accomplishment of the actions required by 
paragraph (k) of this AD, or within 30 days after the effective date 
of this AD, whichever occurs later: Revise the maintenance or 
inspection program, as applicable, to incorporate the 747-8/-8F 
Airworthiness Limitation (AWL), Document Number D011U721-02-01, 
Structurally Significant Item (SSI) 54-50-003c.

[[Page 9374]]

(m) Terminating Action

    Accomplishment of the actions required by paragraphs (k) and (l) 
of this AD terminate the requirements of paragraphs (g) and (i) of 
this AD.

(n) Parts Installation Prohibition

    As of the effective date of this AD, no person may install or 
reinstall any barrel nut P/N SL4081C14SP1 at the forward engine 
mount assembly on any airplane, and only P/N SL4750NA may be 
installed.

(o) New Exceptions to Service Information Specifications

    (1) Where Boeing Special Attention Service Bulletin 747-71-2332, 
Revision 1, dated May 28, 2015, 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 Special Attention Service Bulletin 747-71-2332, 
Revision 1, dated May 28, 2015, specifies to contact Boeing for 
appropriate action: Before further flight, repair using a method 
approved in accordance with the procedures specified in paragraph 
(r) of this AD.

(p) No Alternative Actions or Intervals

    After the maintenance or inspection program has been revised as 
required by paragraph (l) of this AD, no alternative actions (e.g., 
inspections) or intervals may be used unless the actions or 
intervals are approved as an alternative method of compliance (AMOC) 
in accordance with the procedures specified in paragraph (r) of this 
AD.

(q) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraph (k) of this AD, if those actions were performed before the 
effective date of this AD using Boeing Special Attention Service 
Bulletin 747-71-2332, dated May 30, 2014, which is not incorporated 
by reference in this AD.

(r) 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 (s)(1) of this AD. 
Information may be emailed to: [email protected].
    (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 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) AMOCs approved for AD 2013-24-12 are approved as AMOCs for 
the corresponding provisions of this AD.
    (5) Except as required by paragraph (o)(2) of this AD: For 
service information that contains steps that are labeled as Required 
for Compliance (RC), the provisions of paragraphs (r)(5)(i) and 
(r)(5)(ii) of this AD 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.

(s) Related Information

    (1) For more information about this AD, contact Nathan Weigand, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; 
fax: 425-917-6590; email: [email protected].
    (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 https://www.myboeingfleet.com. 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.

    Issued in Renton, Washington, on February 15, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-03690 Filed 2-24-16; 8:45 am]
 BILLING CODE 4910-13-P