[Federal Register Volume 80, Number 142 (Friday, July 24, 2015)]
[Proposed Rules]
[Pages 43972-43974]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-18151]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-2959; Directorate Identifier 2015-NM-008-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 airplanes. This proposed AD was
prompted by reports indicating that the ram air turbine (RAT) assembly
may fail to operate if deployed at low airspeeds. This proposed AD
would require replacing either the RAT pump and control module assembly
or the entire RAT assembly. We are proposing this AD to prevent failure
of the RAT assembly to operate at low air speeds. The volume fuse on
the RAT assembly may be activated in-flight before the RAT is deployed.
This may lead to improper pump hydraulic pressure offloading when the
RAT is needed. Failure of the RAT to operate in an all engine out event
would result in loss of control of the airplane.
DATES: We must receive comments on this proposed AD by September 8,
2015.
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-
2959.
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-
2959; 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: Sean J. Schauer, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6479; 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-2015-2959;
Directorate Identifier 2015-NM-008-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
An engineering review by Boeing's RAT supplier discovered that the
RAT assembly may fail to operate if deployed at low airspeeds. A
hydraulic fuse in the RAT control module is intended to remain open to
enable RAT spin-up at low air speeds by off-loading the RAT hydraulic
pump. After the RAT is spinning, the fuse sets and the pump
[[Page 43973]]
output supplies power to the center hydraulic system. The supplier
found that the fuse may prematurely set as a result of nominal leakage
through the hydraulic pump and/or check valve, preventing the RAT from
spinning up when deployed below 160 knots. This has been attributed to
a design defect in the fuse. A RAT in service will spin up if deployed
above 160 knots and remain operational as the airplane decelerates
through the minimum RAT design speed of 130 knots. The premature
setting of the RAT fuse can prevent the RAT from spinning up and
providing emergency hydraulic power when deployed below 160 knots. In
an all engine out event, an inoperative RAT would result in loss of
control of the airplane.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin B787-81205-SB290015-00,
Issue 002, dated November 25, 2014. The service information describes
procedures for replacing either the RAT pump and control module
assembly or the RAT assembly including an installation test and
corrective actions 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 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. Refer to this service
information for details on the procedures and compliance times.
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.
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 RC (required for
compliance) 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
Required for Compliance (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 12 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Replacement....................... 7 work-hours x $85 N/A................. $595 $7,140
per hour = $595.
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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 43974]]
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):
The Boeing Company: Docket No. FAA-2015-2959; Directorate Identifier
2015-NM-008-AD.
(a) Comments Due Date
We must receive comments by September 8, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 787-8 airplanes,
certificated in any category, as identified in Boeing Alert Service
Bulletin B787-81205-SB290015-00, Issue 002, dated November 25, 2014.
(d) Subject
Air Transport Association (ATA) of America Code 29, Hydraulic
Power.
(e) Unsafe Condition
This AD was prompted by reports indicating that the ram air
turbine (RAT) assembly may fail to operate if deployed at low
airspeeds. We are issuing this AD to prevent failure of the RAT
assembly to operate at low air speeds. The volume fuse on the RAT
assembly may be activated in-flight before the RAT is deployed. This
may lead to improper pump hydraulic pressure offloading when the RAT
is needed. Failure of the RAT to operate in an all engine out event
would result in loss of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Replacement
Within 36 months after the effective date of this AD, replace
the RAT pump and control module assembly or the RAT assembly,
including an installation test and applicable corrective actions, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin B787-81205-SB290015-00, Issue 002, dated November
25, 2014. Do all applicable corrective actions before further
flight.
(h) Credit for Previous Actions
This paragraph provides credit for actions required by paragraph
(g) of this AD, if those actions were performed before the effective
date of this AD using Boeing Alert Service Bulletin B787-81205-
SB290015-00, Issue 001, dated September 4, 2014, which is not
incorporated by reference in this AD.
(i) 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 (j)(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 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) For service information that contains steps that are labeled
as Required for Compliance (RC), the provisions of paragraphs
(i)(4)(i) and (i)(4)(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.
(j) Related Information
(1) For more information about this AD, contact Sean J. Schauer,
Aerospace Engineer, Systems and Equipment Branch, ANM 130S, FAA,
Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW.,
Renton, WA 98057-3356; phone: 425-917-6479; 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 July 16, 2015.
Suzanne Masterson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-18151 Filed 7-23-15; 8:45 am]
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