
[Federal Register Volume 81, Number 228 (Monday, November 28, 2016)]
[Proposed Rules]
[Pages 85448-85450]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-27308]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 81, No. 228 / Monday, November 28, 2016 / 
Proposed Rules  

[[Page 85448]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9307; Directorate Identifier 2016-NM-076-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 787-9 airplanes. This proposed AD was 
prompted by a determination that a certain bolt used on the outboard 
clevis of the ram air turbine (RAT) forward support fitting might not 
be long enough to allow for proper installation of the RAT. This 
proposed AD would require inspection of the forward support fitting of 
the RAT and replacement if cracking is found, and installation of a 
longer shoulder bolt. We are proposing this AD to address the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by January 12, 
2017.

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 NPRM, contact Boeing 
Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740; telephone 
562-797-1717; 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-2016-9307.

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-
9307; 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: Kelly McGuckin, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6490; fax: 425-917-6590; email: 
kelly.mcguckin@faa.gov.

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-2016-9307; 
Directorate Identifier 2016-NM-076-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

    During production, a determination was made that the shoulder bolt 
used on the outboard clevis of the RAT forward support fitting might 
not be long enough to allow for proper installation of the RAT; 
therefore, the clevis of the joint could be clamped together, resulting 
in reduced fatigue life and possible fracture of the clevis. The RAT 
system supplies an emergency source of hydraulic power to operate the 
minimum flight controls necessary for flight, and an emergency source 
of electrical power in the case of a dual non-restartable engine loss. 
Fracture of the clevis of the forward support fitting of the RAT could 
result in the RAT departing the airplane during a dual non-restartable 
engine loss, and consequent loss of control of the airplane. The RAT 
departing the airplane could also result in injury to maintenance crews 
during periodic RAT ground tests.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin B787-81205-SB290031-00, 
Issue 001, dated March 25, 2016. The service information describes 
procedures for inspecting for cracking of the clevis of the forward 
support fitting of the RAT, installing a longer shoulder bolt, and 
replacing the forward support fitting with a new fitting if any 
cracking is found. 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.

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. For information on the

[[Page 85449]]

procedures and compliance times, see this service information at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9307.

Costs of Compliance

    We estimate that this proposed AD affects 2 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
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection/shoulder bolt             3 work-hours x $85 per hour = $255..............................            $152             $407             $814
 replacement.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements of 
the forward support fitting 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 replacements:

                                                                   On-Condition Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                                             Cost per
                    Action                                                    Labor cost                                   Parts cost        product
--------------------------------------------------------------------------------------------------------------------------------------------------------
Forward support fitting replacement...........  15 work-hours x $85 per hour = $1,275.................................         $28,309          $29,584
--------------------------------------------------------------------------------------------------------------------------------------------------------

    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.

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-2016-9307; Directorate Identifier 
2016-NM-076-AD.

(a) Comments Due Date

    We must receive comments by January 12, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 787-9 airplanes, 
certificated in any category, as identified in Boeing Alert Service 
Bulletin B787-81205-SB290031-00, Issue 001, dated March 25, 2016.

(d) Subject

    Air Transport Association (ATA) of America Code 29; Hydraulic 
power.

(e) Unsafe Condition

    This AD was prompted by a determination that the shoulder bolt 
used on the outboard clevis of the ram air turbine (RAT) might not 
be long enough to allow for proper installation of the RAT; 
therefore, the clevis of the joint could be clamped together, 
resulting in reduced fatigue life and possible fracture of the 
clevis. We are issuing this AD to prevent fracture of the clevis of 
the forward support fitting of the RAT, which could result in the 
RAT departing the airplane during a dual non-restartable engine 
loss, and consequent loss of control of the airplane, or injury to 
maintenance crews during periodic RAT ground tests.

(f) Compliance

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

(g) Inspection, Replacement of Shoulder Bolt, and Replacement of RAT 
Forward Support Fitting if Necessary

    Within 12,000 flight hours or 24 months after the effective date 
of this AD, whichever occurs first: Do a high frequency eddy current 
inspection for cracking of the clevis of the forward support fitting 
of the RAT, and install a longer shoulder bolt, in accordance

[[Page 85450]]

with the Accomplishment Instructions of Boeing Alert Service 
Bulletin B787-81205-SB290031-00, Issue 001, dated March 25, 2016. If 
any cracking is found, before further flight, replace the RAT 
forward support fitting with a new fitting, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin B787-
81205-SB290031-00, Issue 001, dated March 25, 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 the service information specified in 
paragraphs (h)(1), (h)(2), (h)(3), or (h)(4) of this AD.
    (1) Boeing Message TBC-ANA-15-0272-01B, dated September 22, 
2015.
    (2) Boeing Message TBC-ANZ-15-0016-06B, dated October 14, 2015.
    (3) Boeing Message TBC-CAL-15-0089-01B, dated September 22, 
2015.
    (4) Boeing Message TBC-VAA-15-0089-01B dated September 22, 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 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. 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 Kelly McGuckin, 
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, 
Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 
425-917-6490; fax: 425-917-6590; email: kelly.mcguckin@faa.gov.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Contractual & Data Services 
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740; 
telephone 562-797-1717; 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 November 2, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-27308 Filed 11-25-16; 8:45 am]
 BILLING CODE 4910-13-P


