[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:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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: <a href="/cdn-cgi/l/email-protection#07636872606b6674297374726d6e4761666629606871"><span class="__cf_email__" data-cfemail="d7b3b8a2b0bbb6a4f9a3a4a2bdbe97b1b6b6f9b0b8a1">[email protected]</span></a>.

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:
    <bullet> Dual hydraulic failure resulting in a free outboard (OB) 
aileron, free inboard (IB) elevator, and free OB elevator;
    <bullet> Dual electrical system failure resulting in both OB 
ailerons free;
    <bullet> System failures resulting in a free OB aileron;
    <bullet> System failures resulting in a free IB elevator; and
    <bullet> 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.
    <bullet> Boeing Alert Service Bulletin 747-27A2506, February 3, 
2014.
    <bullet> 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:''
    <bullet> Item Numbers 27-CMR-10, ``Lubricate inboard elevator hinge 
bearings.''
    <bullet> 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
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------

    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: <a href="/cdn-cgi/l/email-protection#efd6c2aea1a2c2bc8a8e9b9b838ac2aeaca0c2aea2a0acc2bd8a9e9a8a9c9b9caf898e8ec1888099"><span class="__cf_email__" data-cfemail="360f1b77787b1b65535742425a531b7775791b777b79751b64534743534542457650575718515940">[email 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 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: <a href="/cdn-cgi/l/email-protection#32565d47555e53411c464147585b725453531c555d44"><span class="__cf_email__" data-cfemail="70141f05171c11035e0403051a19301611115e171f06">[email 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 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


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