[Federal Register Volume 79, Number 242 (Wednesday, December 17, 2014)]
[Proposed Rules]
[Pages 75100-75103]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-29484]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0926; Directorate Identifier 2014-NM-085-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 747-8 and 747-8F airplanes. This
proposed AD was prompted by an analysis, which determined that in a
limited flight envelope with specific conditions, divergent flutter
could occur during a high g-load maneuver in combination with certain
system failures. This proposed AD would require replacing the lateral
control electronic (LCE)
[[Page 75101]]
modules, replacing the inboard elevator power control packages (PCPs),
installing new external compensators for the PCPs, and revising the
maintenance or inspection program. We are proposing this AD to prevent
certain system failures from resulting in divergent flutter, and
subsequent loss of continued safe flight and landing.
DATES: We must receive comments on this proposed AD by February 2,
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.
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-2014-
0926; 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: Douglas Tsuji, Senior Aerospace
Engineer, Systems and Equipment Branch, ANM-130S, Seattle Aircraft
Certification Office, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356;
phone: 425-917-6546; 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-2014-0926;
Directorate Identifier 2014-NM-085-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
It was determined by analysis that, within a limited speed/Mach/
altitude envelope and with specific payload and fuel conditions,
divergent flutter could occur on Model 747-8 and 747-8F airplanes with
0% tail fuel during a high g-load maneuver (>1.6 g) in combination with
any of the following system failures:
Dual hydraulic failure resulting in a free outboard (OB)
aileron, free inboard (IB) elevator, and free OB elevator;
Dual electrical system failure resulting in both OB
ailerons free;
System failures resulting in a free OB aileron;
System failures resulting in a free IB elevator; and
Latent excessive IB elevator freeplay.
We are proposing this AD to prevent certain system failures from
resulting in divergent flutter, and subsequent loss of continued safe
flight and landing.
Relevant Service Information
We reviewed the following 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-2014-0926.
Boeing Alert Service Bulletin 747-27A2506, February 3,
2014.
Boeing Alert Service Bulletin 747-27A2513, Revision 1,
dated July 18, 2014.
We have also reviewed Boeing 747-8/8F Certification Maintenance
Requirements (CMRs) Document D011U721-02-03, Revision December 2013,
which contains the following tasks in Section G., ``CMR Tasks:''
Item Numbers 27-CMR-10, ``Lubricate inboard elevator hinge
bearings.''
Item Number 27-CMR-11, ``Functional check of inboard
elevator hinge bearing and power control unit rod end bearing
freeplay.''
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 identified previously.
Explanation of Applicability, Compliance Time, and Repetitive Intervals
The applicability in paragraph (c) and the compliance times and
repetitive intervals in paragraph (i) of this proposed AD are based on
airplane utilization. Model 747-8 airplanes referred to as Boeing
Business Jets (BBJs) are designated as low utilization airplanes and
are maintained under a Boeing Manufacturer's Recommended Program (MRP).
The Boeing MRP is limited to airplanes operated less than 1,200 flight
hours per calendar year. Therefore, this proposed AD has different
implementation task intervals and repetitive intervals for these low
utilization airplanes due to unique operations.
Explanation of ``RC'' Steps in Service Information
The FAA worked in conjunction with industry, under the
Airworthiness Directives Implementation Aviation Rulemaking Committee,
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 actions specified in the service
information described previously include steps that are labeled as RC
(required for compliance) because these steps have a direct effect on
detecting, preventing, resolving, or eliminating an identified unsafe
condition.
[[Page 75102]]
As noted in the specified service information, steps labeled as RC
must be done to comply with the proposed AD. However, steps that are
not labeled as RC are recommended. Those steps that are not labeled as
RC may be deviated from, done as part of other actions, or done using
accepted methods different from those identified in the service
information without obtaining approval of an alternative method of
compliance (AMOC), provided the steps labeled as RC can be done and the
airplane can be put back in a serviceable condition. Any substitutions
or changes to steps labeled as RC will require approval of an AMOC.
Costs of Compliance
We estimate that this proposed AD affects 8 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 of LCEs................... 4 work-hours x $85 per $0 $340 $2,720
hour = $340.
Replacement of IB elevator PCPs and 57 work-hours x $85 per 44,894 49,739 397,912
installation of external IB elevator hour = $4,845.
compensators.
Revision to maintenance or inspection 1 work-hour x $85 per 0 85 680
program. hour = $85.
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According to the manufacturer, all 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.
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-2014-0926; Directorate Identifier
2014-NM-085-AD.
(a) Comments Due Date
We must receive comments by February 2, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company airplanes, certificated in
any category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of
this AD.
(1) Model 747-8 and 747-8F series airplanes, as identified in
Boeing Alert Service Bulletin 747-27A2506, dated February 3, 2014.
(2) Model 747-8 and 747-8F series airplanes, as identified in
Boeing Alert Service Bulletin 747-27A2513, Revision 1, dated July
18, 2014.
(3) Model 747-8 series airplanes that are operated less than
1,200 flight hours per calendar year.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
Controls.
(e) Unsafe Condition
This AD was prompted by an analysis, which determined that in a
limited flight envelope with specific conditions, divergent flutter
could occur during a high g-load maneuver in combination with
certain system failures. We are issuing this AD to prevent certain
system failures from resulting in divergent flutter, and subsequent
loss of continued safe flight and landing.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Replacement of Lateral Control Electronic (LCE) Modules
For airplanes identified in paragraph (c)(1) of this AD: Within
12 months after the effective date of this AD, replace the LCE
modules with new LCE modules having revised software, and do an
operational test of the LCE modules, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
27A2506, dated February 3, 2014. If the operational test fails,
before further flight, do corrective actions and repeat the
operational test and applicable corrective actions until the
operational test passes.
(h) Replacement of Inboard Elevator Power Control Packages and
Installation of External Inboard Elevator Compensators
For airplanes identified in paragraph (c)(2) of this AD: Within
60 months after the effective date of this AD, replace both
[[Page 75103]]
inboard elevator power control packages (PCPs) with new PCPs that
have the internal compensators removed, install two larger external
compensators for each PCP, and do an operational test of each
inboard elevator PCP, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-27A2513, Revision
1, dated July 18, 2014. If the operational test fails, before
further flight, do corrective actions and repeat the operational
test and applicable corrective actions until the operational test
passes.
(i) Revision to the Maintenance or Inspection Program
For all airplanes: Within 90 days after the effective date of
this AD, revise the maintenance or inspection program, as
applicable, to incorporate Item Numbers 27-CMR-10, ``Lubricate
inboard elevator hinge bearings,'' and 27-CMR-11, ``Functional check
of inboard elevator hinge bearing and power control unit rod end
bearing freeplay,'' of Section G., ``CMR Tasks,'' of the 747-8/8F
Certification Maintenance Requirements (CMRs) Document D011U721-02-
03, Revision December 2013. The initial compliance times and
repetitive intervals for the lubrication and functional check are
specified in paragraphs (i)(1) and (i)(2) of this AD.
(1) For airplanes identified in paragraphs (c)(1) and (c)(2) of
this AD that are not identified in paragraph (c)(3) of this AD:
(i) The initial compliance time for the lubrication of the
inboard elevator hinge bearings is within 18 months after the most
recent lubrication. The repetitive lubrication intervals are
specified in Item Number 27-CMR-10, ``Lubricate inboard elevator
hinge bearings,'' of Section G., ``CMR Tasks,'' of the 747-8/8F
Certification Maintenance Requirements (CMRs) Document D011U721-02-
03, Revision December 2013.
(ii) The initial compliance time for the functional check of the
inboard elevator hinge bearing and power control unit rod end
bearing freeplay is within 12 months after the effective date of
this AD. The repetitive functional check intervals are specified in
Item Number 27-CMR-11, ``Functional check of inboard elevator hinge
bearing and power control unit rod end bearing freeplay,'' of
Section G., CMR Tasks, of the 747-8/8F Certification Maintenance
Requirements, D011U721-02-03, December 2013.
(2) For airplanes identified in paragraph (c)(3) of this AD:
(i) The initial compliance time for the lubrication of the
inboard elevator hinge bearings is within 24 months after the most
recent lubrication. Repeat the lubrication thereafter at intervals
not to exceed 24 months.
(ii) The initial compliance time for the functional check of the
inboard elevator hinge bearing and power control unit rod end
bearing freeplay is within 36 months after the effective date of
this AD. Repeat the functional check thereafter at intervals not to
exceed 36 months.
(j) Parts Installation Prohibition
As of the effective date of this AD, no person may install an
LCE having part number (P/N) CA49253-001 or CA49253-002, or an
inboard elevator PCP having P/N 327400-1009, on any airplane.
(k) Credit for Actions Accomplished Previously
This paragraph provides credit for the actions required by
paragraph (h) of this AD if those actions were performed before the
effective date of this AD using Boeing Alert Service Bulletin 747-
27A2513, dated February 4, 2014, which is not incorporated by
reference in this AD.
(l) 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 (m)(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) If the service information contains steps that are labeled
as RC (Required for Compliance), those steps must be done to comply
with this AD; any steps that are not labeled as RC are recommended.
Those steps that are not labeled as RC may be deviated from, done as
part of other actions, or done using accepted methods different from
those identified in the specified service information without
obtaining approval of an AMOC, provided the steps labeled as RC can
be done and the airplane can be put back in a serviceable condition.
Any substitutions or changes to steps labeled as RC require approval
of an AMOC.
(m) Related Information
(1) For more information about this AD, contact Doug Tsuji,
Senior Aerospace Engineer, Systems and Equipment Branch, ANM-130S,
Seattle Aircraft Certification Office, FAA, 1601 Lind Avenue SW.,
Renton, WA 98057-3356; phone: 425-917-6546; 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 10, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-29484 Filed 12-16-14; 8:45 am]
BILLING CODE 4910-13-P