[Federal Register Volume 80, Number 238 (Friday, December 11, 2015)]
[Proposed Rules]
[Pages 76878-76881]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-31218]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-6548; Directorate Identifier 2015-NM-114-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 adopt a new airworthiness directive (AD) for
certain The Boeing Company Model 787-8 and 787-9 airplanes equipped
with General Electric engines. This proposed AD was prompted by reports
of cracking in barrel nuts on a forward engine mount of Model 747-8
airplanes, which shares a similar design to the forward engine mount of
Model 787-8 and 787-9 airplanes. This proposed AD would require, for
certain airplanes, replacement of the four barrel nuts of the forward
engine mount on each engine. For certain other airplanes, this proposed
AD would require an inspection to determine if any forward
[[Page 76879]]
engine mount barrel nut having a certain part number is installed, and
related investigative and corrective actions if necessary. We are
proposing this AD to detect and correct cracking of the forward engine
mount barrel nuts; such cracking could result in reduced load capacity
of the forward engine mount and could result in separation of an engine
from the airplane, and consequent loss of control of the airplane.
DATES: We must receive comments on this proposed AD by January 25,
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 proposed 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
6548.
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-2015-
6548; 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 (phone: 800-647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Allen Rauschendorfer, Aerospace
Engineer, Airframe Branch, ANM-120S, Seattle Aircraft Certification
Office, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-
917-6487; 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 proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2015-6548;
Directorate Identifier 2015-NM-114-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We received a report indicating that during the replacement of the
No. 2 engine on a Model 747-8 airplane, an operator conducted a non-
destructive test (NDT) inspection of the barrel nuts on the forward
engine mount and found cracks on two of the four barrel nuts. The same
operator also discovered one cracked barrel nut on the No. 1 engine of
the same Model 747-8 airplane. Boeing did an NDT inspection on the
barrel nuts of the No. 2 engine of a Model 747-8 flight test airplane
and discovered two barrel nuts with cracks. Since these initial
findings, two additional barrel nuts were found cracked on two
additional Model 747-8 airplanes.
The barrel nuts are located at the forward end of the strut box and
are used to fasten the forward engine mount to the strut. A barrel nut
with a crack on one side is still able to carry ultimate load. A crack
on both sides of a barrel nut will cause complete failure of the barrel
nut. Complete failure of two or more barrel nuts on the same forward
engine mount reduces the load capacity of the forward engine mount and
could result in separation of an engine from the airplane, and
consequent loss of control of the airplane.
Model 787-8 and 787-9 airplanes with General Electric engines have
a similar forward engine mount bolt and barrel nut configuration to
that on Model 747-8 series airplanes. Therefore, Model 787-8 and 787-9
airplanes are subject to the same unsafe condition revealed on Model
747-8 series airplanes. We issued AD 2013-24-12, Amendment 39-17686 (78
FR 71989, December 2, 2013), to address this unsafe condition on Model
747-8 series airplanes.
Relevant Service Information Under 1 CFR Part 51
We reviewed Boeing Service Bulletin B787-81205-SB710026-00, Issue
001, dated June 10, 2015. The service information describes procedures
for replacing the forward engine mount barrel nuts with new, improved
barrel nuts; doing an inspection to determine if barrel nuts having a
certain part number are installed on the forward engine mount; and
doing related investigative and corrective actions. 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 of this NPRM.
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 require accomplishing the actions specified
in the service information described previously, except as discussed
under ``Differences Between this Proposed AD and the Service
Information.'' For information on the procedures and compliance times,
see this service information at http://www.regulations.gov by searching
for Docket No. FAA-2015-6548.
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 actions, 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.
[[Page 76880]]
Differences Between This Proposed AD and the Service Information
The service 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.
Explanation of ``RC'' Steps in Service Information
The FAA worked in conjunction with industry, under the
Airworthiness Directive Implementation Aviation Rulemaking Committee
(ARC), to enhance the AD system. One enhancement was a new process for
annotating which steps in the service information are required for
compliance with an AD. Differentiating these steps from other tasks in
the service information is expected to improve an owner's/operator's
understanding of crucial AD requirements and help provide consistent
judgment in AD compliance. The steps identified as Required for
Compliance (RC) in any service information identified previously have a
direct effect on detecting, preventing, resolving, or eliminating an
identified unsafe condition.
For service information that contains steps that are labeled as RC,
the following provisions apply: (1) 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, and an AMOC is required for any
deviations to RC steps, including substeps and identified figures; and
(2) 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.
Costs of Compliance
We estimate that this proposed AD affects 36 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
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Cost per
Action Labor cost Parts cost product Cost on U.S. operators
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Replacement (2 engines)...... 29 work-hours x $1,988 per $6,441 $64,410 (10 airplanes).
$85 per hour = engine x 2
$2,465 for 2 engines =
engines. $3,976.
Inspection for part number 1 work-hour x $0.............. 85 $2,210 (26 airplanes).
using maintenance records (2 $85 per hour =
engines). $85 for 2
engines.
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We estimate the following costs to do any related investigative
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
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Cost per
Action Labor cost Parts cost product
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Inspection (2 engines)....................... 9 work-hours x $85 per hour = $0 $765
$765 for 2 engines.
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We have received no definitive data that would enable us to provide
cost estimates for the on-condition corrective actions specified in
this proposed AD.
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.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
[[Page 76881]]
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 adding the following new airworthiness
directive (AD):
No. FAA-2015-6548; Directorate Identifier 2015-NM-114-AD.
(a) Comments Due Date
We must receive comments by January 25, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 787-8 and 787-9
airplanes, certificated in any category, equipped with General
Electric GEnx-1B engines, as identified in Boeing Service Bulletin
B787-81205-SB710026-00, Issue 001, dated June 10, 2015.
(d) Subject
Air Transport Association (ATA) of America Code 71, Powerplant.
(e) Unsafe Condition
This AD was prompted by reports of cracking in barrel nuts on a
forward engine mount of Model 747-8 airplanes, which shares a
similar design to the forward engine mount of Model 787-8 and 787-9
airplanes. We are issuing this AD to detect and correct cracking of
the forward engine mount barrel nuts; such cracking could result in
reduced load capacity of the forward engine mount, and could result
in separation of an engine 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) Replacement Barrel Nuts
For Group 1 airplanes as identified in Boeing Service Bulletin
B787-81205-SB710026-00, Issue 001, dated June 10, 2015: Except as
provided by paragraph (i)(1) of this AD, at the time specified in
paragraph 5., ``Compliance,'' of Boeing Service Bulletin B787-81205-
SB710026-00, Issue 001, dated June 10, 2015, replace the existing
forward engine mount barrel nuts on each engine, in accordance with
the Accomplishment Instructions of Boeing Service Bulletin B787-
81205-SB710026-00, Issue 001, dated June 10, 2015.
(h) Part Number Inspection for Installed Barrel Nuts
For Group 2 airplanes as identified in Boeing Service Bulletin
B787-81205-SB710026-00, Issue 001, dated June 10, 2015: Except as
provided by paragraph (i)(1) of this AD, at the time specified in
paragraph 5. ``Compliance,'' of Boeing Service Bulletin B787-81205-
SB710026-00, Issue 001, dated June 10, 2015, review the aircraft
maintenance records to determine if the airplane engine has been
removed, installed, or replaced, in accordance with the
Accomplishment Instructions of Boeing Service Bulletin B787-81205-
SB710026-00, Issue 001, dated June 10, 2015. If the maintenance
records indicate that a barrel nut having part number SL4081C14SP1
is installed, or if the part number of an installed barrel nut
cannot be determined, before further flight, do the related
investigative and applicable corrective actions, in accordance with
the Accomplishment Instructions of Boeing Service Bulletin B787-
81205-SB710026-00, Issue 001, dated June 10, 2015.
(i) Exception to Service information
(1) Where Boeing Service Bulletin B787-81205-SB710026-00, Issue
001, dated June 10, 2015, specifies a compliance time ``after the
Issue 001 date on this service bulletin,'' this AD requires
compliance within the specified compliance time after the effective
date of this AD.
(2) Where Boeing Service Bulletin B787-81205-SB710026-00, Issue
001, dated June 10, 2015, specifies to contact Boeing for repair
instructions: Before further flight, repair using a method approved
in accordance with the procedures specified in paragraph (j) of this
AD.
(j) 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 (k)(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) Except as required by paragraph (i)(2) of this AD: For
service information that contains steps that are labeled as Required
for Compliance (RC), the provisions of paragraphs (j)(4)(i) and
(j)(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.
(k) Related Information
(1) For more information about this AD, contact Allen
Rauschendorfer, Aerospace Engineer, Airframe Branch, ANM-120S,
Seattle Aircraft Certification Office, FAA, 1601 Lind Avenue SW.,
Renton, WA 98057-3356; phone: 425-917-6487; 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 December 4, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-31218 Filed 12-10-15; 8:45 am]
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