
[Federal Register Volume 81, Number 91 (Wednesday, May 11, 2016)]
[Proposed Rules]
[Pages 29206-29209]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-10915]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6428; Directorate Identifier 2015-NM-119-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 certain wing side-of-body stringer 
fittings have been installed with faying surface mismatch beyond the 
allowed machining tolerance. This proposed AD would require inspection 
of certain stringer fittings for faying surface mismatch common to the 
side-of-body rib chord, replacement if necessary, and replacement of 
the clearance fit fasteners common to the side-of-body fittings and 
upper side-of-body rib chord with tapered sleeve bolts. We are 
proposing this AD to prevent an unacceptable reduction of the fatigue 
life in the upper side-of-body rib chord. Associated fatigue cracks can 
reduce the structural capability to a point where it cannot sustain 
limit load, which could adversely affect the structural integrity of 
the airplane.

DATES: We must receive comments on this proposed AD by June 27, 2016.

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: 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-2016-6428.

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-
6428; 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: Allen Rauschendorfer, Aerospace 
Engineer, Airframe Branch, ANM-120S,

[[Page 29207]]

FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., 
Renton, WA 98057-3356; phone: 425-917-6487; fax: 425-917-6590; email: 
allen.rauschendorfer@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-2016-6428; 
Directorate Identifier 2015-NM-119-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

    We have received reports indicating that certain wing side-of-body 
stringer fittings have been installed with faying surface mismatch 
beyond the allowed machining tolerance. The fittings are assembled to 
the mating side-of-body rib chord. The faying surface mismatch produces 
a gouge in the mating surface which reduces the fatigue life, and could 
grow into a widespread fatigue condition on the upper side-of-body rib 
chord. We are proposing this AD to prevent an unacceptable reduction of 
the fatigue life in the upper side-of-body rib chord. Associated 
fatigue cracks can reduce the structural capability to a point where it 
cannot sustain limit load, which could adversely affect the structural 
integrity of the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin B787-81205-SB570018-00, 
Issue 001, dated July 1, 2015. The service information describes 
procedures for inspection of the left and right hand side stringer 1 
fittings for faying surface mismatch common to the side-of-body rib 
chord. If faying surface mismatch is found, instructions are also given 
to replace the stringer 1 fitting, and removal and replacement of the 
clearance fit fasteners common to the side-of-body fittings and upper 
side-of-body rib chord with tapered sleeve bolts from stringer 5 to 
stringer 11. 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, except as described in 
``Differences Between this Proposed AD and the Service Information.''

Differences Between This Proposed AD and the Service Information

    Boeing Alert Service Bulletin B787-81205-SB570018-00, Issue 001, 
dated July 1, 2015, specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 5 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
-----------------------------------------------------------------------------------------------------------------------------------------
Modification and inspection...................  144 work-hours x $85 per hour =               $100,079         $112,319         $561,595
                                                 $12,240.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary corrective 
action for fretting damage or cutter mismatch 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 corrective 
actions:

                                               On-condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                 Action                                Labor cost                  Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair for fretting damage or cutter      9 work-hours x $85 per hour = $765..              $0             $765
 mismatch.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the crack repair specified in this proposed AD.

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

[[Page 29208]]

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-2016-6428; Directorate Identifier 
2015-NM-119-AD.

(a) Comments Due Date

    We must receive comments by June 27, 2016.

(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-SB570018-00, Issue 001, dated July 1, 2015.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports indicating that certain wing 
side-of-body stringer fittings have been installed with faying 
surface mismatch beyond the allowed machining tolerance. We are 
issuing this AD to prevent an unacceptable reduction of the fatigue 
life in the upper side-of-body rib chord. Associated fatigue cracks 
can reduce the structural capability to a point where it cannot 
sustain limit load, which could adversely affect the structural 
integrity of the airplane.

(f) Compliance

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

(g) Inspection

    Before the accumulation of 18,000 total flight cycles, or within 
13 years after the effective date of this AD, whichever occurs 
first, do the inspections specified in paragraphs (g)(1), (g)(2), 
and (g)(3) of this AD, and all applicable corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin B787-81205-SB570018-00, Issue 001, dated July 1, 
2015, except as required by paragraph (i) of this AD. Do all 
applicable corrective actions before further flight.
    (1) Do a detailed inspection for fretting damage of the faying 
surface of the aluminum T-chord.
    (2) Do an eddy current inspection for cracking of the fastener 
holes.
    (3) Do a detailed inspection for a machine mismatch condition of 
the stringer 1 fitting faying surface.

(h) Modifications

    Concurrently with accomplishment of the requirements of 
paragraph (g) of this AD: Modify the stringer fitting fasteners, and 
do an eddy current inspection for cracking of the fastener holes, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin B787-81205-SB570018-00, Issue 001, dated July 1, 
2015. If any crack is found, before further flight, repair using a 
method approved in accordance with the procedures specified in 
paragraph (j) of this AD.

(i) Exception to Service Information Specifications

    Where Boeing Alert Service Bulletin B787-81205-SB570018-00, 
Issue 001, dated July 1, 2015, specifies to contact Boeing for 
repair of cracking: Before further flight, repair the cracking using 
a method approved in accordance with the procedures specified in 
paragraph (j) of this AD.

(j) 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 (k)(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) Except as required by paragraph (i) of this AD: For service 
information that contains steps that are labeled as Required for 
Compliance (RC), the provisions of paragraphs (j)(4)(i) and 
(j)(4)(ii) 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.

(k) Related Information

    (1) For more information about this AD, contact Allen 
Rauschendorfer, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, 
Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., 
Renton, WA 98057-3356; phone: 425-917-6487; fax: 425-917-6590; 
email: allen.rauschendorfer@faa.gov.
    (2) For service information identified in this AD, 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.


[[Page 29209]]


    Issued in Renton, Washington, on May 3, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-10915 Filed 5-10-16; 8:45 am]
 BILLING CODE 4910-13-P


