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[Federal Register Volume 81, Number 227 (Friday, November 25, 2016)]
[Rules and Regulations]
[Pages 85118-85121]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-28059]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5041; Directorate Identifier 2015-NM-102-AD; 
Amendment 39-18719; AD 2016-24-02]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 747-8 and 747-8F series airplanes. This AD was 
prompted by a report that static strength analysis has shown that the 
aluminum transmission aft bearing plate assemblies have inadequate 
structural strength for one or more of the required load cases. This AD 
requires removing aluminum transmission aft bearing plate assemblies 
from the flap track and installing titanium transmission aft bearing 
plate assemblies to the flap track. We are issuing this AD to address 
the unsafe condition on these products.

[[Page 85119]]

DATES: This AD is effective December 30, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 30, 
2016.

ADDRESSES: For service information identified in this final rule, 
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-
5041.

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-
5041; 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 AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6432; fax: 425-917-6590; email: bill.ashforth@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain The Boeing Company 
Model 747-8 and 747-8F series airplanes. The NPRM published in the 
Federal Register on April 5, 2016 (81 FR 19514) (``the NPRM''). The 
NPRM was prompted by a report that static strength analysis has shown 
that the aluminum transmission aft bearing plate assemblies have 
inadequate structural strength for one or more of the required load 
cases, including cases for drive system jam, flap skew, and structural 
damage tolerance. Inadequate structural strength can result in damage 
to the transmission aft bearing plate assemblies. The NPRM proposed to 
require removing aluminum transmission aft bearing plate assemblies 
from the flap track and installing titanium transmission aft bearing 
plate assemblies to the flap track. We are issuing this AD to prevent 
inadequate structural strength of transmission aft bearing plate 
assemblies. This condition could result in damaged transmission aft 
bearing plate assemblies, which could result in incorrect operation and 
departure of the flap from the airplane and consequent loss of 
controllability of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Request To Use the Latest Service Information

    Boeing requested that we revise the NPRM to refer to Boeing Alert 
Service Bulletin 747-57A2348, Revision 1, dated February 26, 2016. 
Boeing stated that Boeing Alert Service Bulletin 747-57A2348, dated 
June 12, 2015, erroneously included three airplanes, line numbers 1435, 
1506, and 1509, which were delivered with the terminating action 
already incorporated. Boeing stated that the airplane effectivity in 
paragraph 1.A.1. of Boeing Alert Service Bulletin 747-57A2348, Revision 
1, dated February 26, 2016, is listed correctly; however, airplane line 
numbers 1435, 1506, and 1509 were still erroneously included in the 
table that lists the airplane groups by line numbers. Boeing noted that 
Boeing Alert Service Bulletin 747-57A2348, Revision 1, dated February 
26, 2016, also contains corrections to the access requirements, part 
quantities, and part numbers.
    We agree with the commenter's request for the reasons provided. We 
have updated this final rule accordingly. Since the table in paragraph 
1.A.1. of Boeing Alert Service Bulletin 747-57A2348, Revision 1, dated 
February 26, 2016, is not accurate, we have also revised paragraph (c) 
of this AD to state that the AD is applicable to Model 747-8 and 747-8F 
series airplanes, except for line numbers 1435, 1506, and 1509, which 
were delivered with the terminating action already incorporated. We 
have also added a new paragraph (h) to this AD, which provides credit 
for actions completed before the effective date of this AD using Boeing 
Alert Service Bulletin 747-57A2348, dated June 12, 2015. We have 
redesignated subsequent paragraphs accordingly.

Request To Revise the Costs of Compliance

    Boeing requested that we update the Costs of Compliance section of 
the NPRM with the latest information in Boeing Alert Service Bulletin 
747-57A2348, Revision 1, dated February 26, 2016. Boeing stated that 
the work hours and parts costs have been updated with the new service 
information.
    We agree with the commenter's request for the reason provided. We 
have updated this final rule accordingly.

Request for Credit for Previous Actions

    Boeing requested that we add a statement to the NPRM to indicate 
that no further work is required on airplanes that have completed the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2348, dated June 12, 2015. Boeing stated that Boeing Alert Service 
Bulletin 747-57A2348, Revision 1, dated February 26, 2016, has no 
effect on airplanes that have incorporated Boeing Alert Service 
Bulletin 747-57A2348, dated June 12, 2015.
    We agree with the commenter's request for the reason provided. As 
stated previously, we have revised this AD to provide credit for 
actions completed before the effective date of this AD using Boeing 
Alert Service Bulletin 747-57A2348, dated June 12, 2015.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 747-57A2348, Revision 1, 
dated February 26, 2016. The service information describes procedures 
for removing the aluminum transmission aft bearing plate assembly from 
the flap

[[Page 85120]]

track and installing a new titanium transmission aft bearing plate 
assembly to the flap track. 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.

Costs of Compliance

    We estimate that this AD affects 11 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                             Cost per      Cost on U.S.
                 Action                                             Labor cost                              Parts cost        product        operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Replacement............................  136 work-hours x $85 per hour = $11,560........................         $43,787         $55,347        $608,817
--------------------------------------------------------------------------------------------------------------------------------------------------------

    According to the manufacturer, all of the costs of this 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

    This AD will not have federalism implications under Executive Order 
13132. This AD will 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under 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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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):

2016-24-02 The Boeing Company: Amendment 39-18719; Docket No. FAA-
2016-5041; Directorate Identifier 2015-NM-102-AD.

(a) Effective Date

    This AD is effective December 30, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 747-8 and 747-8F 
series airplanes, certificated in any category, as identified in 
Boeing Alert Service Bulletin 747-57A2348, Revision 1, dated 
February 26, 2016; except for line numbers 1435, 1506, and 1509, 
which were delivered with the terminating action already 
incorporated and are not affected by this AD.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by a report that static strength analysis 
has shown that the aluminum transmission aft bearing plate 
assemblies have inadequate structural strength for one or more of 
the required load cases, including cases for drive system jam, flap 
skew, and structural damage tolerance. Inadequate structural 
strength can result in damage to the transmission aft bearing plate 
assemblies. We are issuing this AD to prevent inadequate structural 
strength of transmission aft bearing plate assemblies. This 
condition could result in damaged transmission aft bearing plate 
assemblies, which could result in incorrect operation and departure 
of the flap from the airplane and consequent loss of controllability 
of the airplane.

(f) Compliance

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

(g) Replacement

    Within 48 months after the effective date of this AD: Remove 
aluminum transmission aft bearing plate assemblies from the flap 
track and install new titanium transmission aft bearing plate 
assemblies to the flap track, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-57A2348, Revision 
1, dated February 26, 2016.

(h) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Boeing Alert Service Bulletin 747-
57A2348, dated June 12, 2015.

(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: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (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

[[Page 85121]]

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) 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. If a step or substep is labeled ``RC Exempt,'' then the 
RC requirement is removed from that step or substep. 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 Bill Ashforth, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6432; 
fax: 425-917-6590; email: bill.ashforth@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (k)(3) and (k)(4) of this AD.

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Alert Service Bulletin 747-57A2348, Revision 1, dated 
February 26, 2016.
    (ii) Reserved.
    (3) For Boeing 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.
    (4) 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on November 10, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-28059 Filed 11-23-16; 8:45 am]
 BILLING CODE 4910-13-P
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