[Federal Register Volume 84, Number 153 (Thursday, August 8, 2019)]
[Proposed Rules]
[Pages 38889-38892]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-16841]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0603; Product Identifier 2019-NM-087-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: The FAA proposes to adopt a new airworthiness directive (AD)
for certain The Boeing Company Model 777-300ER and 777F series
airplanes. This proposed AD was prompted by an evaluation by the design
approval holder (DAH) indicating that the fuselage stringers, stringer
splices, and skin splice straps are subject to widespread fatigue
damage (WFD). This proposed AD would require repetitive detailed
inspections of certain stringer splices and skin splice straps for any
cracks, repetitive high frequency eddy current (HFEC) inspections of
certain stringers and stringer splices for any cracks, and applicable
on-condition actions. The agency is proposing this AD to address the
unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by September
23, 2019.
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.
[[Page 38890]]
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 90740-5600;
telephone 562-797-1717; internet https://www.myboeingfleet.com. You may
view this referenced service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For information
on the availability of this material at the FAA, call 206-231-3195. It
is also available on the internet at http://www.regulations.gov by
searching for and locating Docket No. FAA-2019-0603.
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-2019-
0603; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this NPRM, the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations is listed above.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Eric Lin, Aerospace Engineer, Airframe
Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA
98198; phone and fax: 206-231-3523; email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites 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-2019-0603;
Product Identifier 2019-NM-087-AD'' at the beginning of your comments.
The agency specifically invites comments on the overall regulatory,
economic, environmental, and energy aspects of this NPRM. The FAA will
consider all comments received by the closing date and may amend this
NPRM because of those comments.
The FAA will post all comments, without change, to http://www.regulations.gov, including any personal information you provide.
The agency will also post a report summarizing each substantive verbal
contact received about this proposed AD.
Discussion
Fatigue damage can occur locally, in small areas or structural
design details, or globally, in widespread areas. Multiple-site damage
is widespread damage that occurs in a large structural element such as
a single rivet line of a lap splice joining two large skin panels.
Widespread damage can also occur in multiple elements such as adjacent
frames or stringers. Multiple-site damage and multiple-element damage
cracks are typically too small initially to be reliably detected with
normal inspection methods. Without intervention, these cracks will
grow, and eventually compromise the structural integrity of the
airplane. This condition is known as WFD. It is associated with general
degradation of large areas of structure with similar structural details
and stress levels. As an airplane ages, WFD will likely occur, and will
certainly occur if the airplane is operated long enough without any
intervention.
The FAA's WFD final rule (75 FR 69746, November 15, 2010) became
effective on January 14, 2011. The WFD rule requires certain actions to
prevent structural failure due to WFD throughout the operational life
of certain transport category airplanes that had already been
certificated by the FAA at the time of that rule's enactment, and all
transport-category airplanes to be certificated afterward. The rule
requires that DAHs establish a limit of validity (LOV) of the
engineering data that support the airplanes' structural maintenance
program. Operators affected by the WFD rule may not fly an airplane
beyond its LOV, unless the FAA approves an extended LOV.
The WFD rule does not require identifying and developing
maintenance actions if the DAHs can show that such actions are not
necessary to prevent WFD before the airplane reaches its LOV. Many
LOVs, however, depend on accomplishment of future maintenance actions.
As stated in the WFD rule, any maintenance actions necessary to reach
the LOV will be mandated by airworthiness directives through separate
rulemaking actions.
In the context of WFD, this action is necessary to enable DAHs to
propose LOVs that allow operators the longest operational lives for
their airplanes, and still ensure that WFD will not occur. This
approach allows for an implementation strategy that provides
flexibility to DAHs in determining the timing of service information
development (with FAA approval), while providing operators with
certainty regarding the LOV applicable to their airplanes.
The FAA has received a report indicating that aluminum chips and
conical burr foreign object debris (FOD), were found on in-production
model 777-300ER and 777F airplanes in the interfaces beneath stringer
splices at station (STA) 825+210, STA 655, and STA 1434+189, and the
circumferential splices at STA 1832. FOD has been found in splices that
were built using an automated drilling and fastener installation
process. This automated process is not always sufficient to close gaps
that can occur as a result of the manufacturing build sequence and
geometry. This process has also resulted in hole defects at these
stations. A product acceptance plan has been inadequate in finding
holes that were out of tolerance. FOD and hole defects can reduce the
fatigue performance of the splices, and the existing Maintenance
Planning Data (MPD) inspections do not provide adequate crack detection
for the reduced fatigue thresholds. This could lead to undetected
cracking.
This condition, if not addressed, could result in undetected
fatigue cracks, which could adversely affect the structural integrity
of the airplane.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Boeing Alert Requirements Bulletin 777-53A0091 RB,
dated April 8, 2019. The service information describes procedures for
repetitive detailed inspections of certain stringer splices and skin
splice straps for any cracks, repetitive HFEC inspections of certain
stringers and stringer splices for any cracks, and applicable on-
condition actions. On-condition actions include repair.
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
The FAA is proposing this AD because the agency 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 accomplishment of the actions
identified in Boeing Alert Requirements Bulletin 777-53A0091 RB, dated
April 8, 2019, described previously, except for any differences
identified as exceptions
[[Page 38891]]
in the regulatory text of this proposed AD.
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-2019-0603.
Explanation of Requirements Bulletin
The FAA worked in conjunction with industry, under the
Airworthiness Directive Implementation Aviation Rulemaking Committee
(AD ARC), to enhance the AD system. One enhancement is a process for
annotating which steps in the service information are ``required for
compliance'' (RC) with an AD. Boeing has implemented this RC concept
into Boeing service bulletins.
In an effort to further improve the quality of ADs and AD-related
Boeing service information, a joint process improvement initiative was
worked between the FAA and Boeing. The initiative resulted in the
development of a new process in which the service information more
clearly identifies the actions needed to address the unsafe condition
in the ``Accomplishment Instructions.'' The new process results in a
Boeing Requirements Bulletin, which contains only the actions needed to
address the unsafe condition (i.e., only the RC actions).
Costs of Compliance
The FAA estimates that this proposed AD affects 12 airplanes of
U.S. registry. The agency estimates the following costs to comply with
this proposed AD:
Estimated Costs for Required Actions
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Detailed and HFEC Inspections.... Up to 79 work-hours $0 Up to $6,715 per Up to $80,580 per
x $85 per hour = inspection cycle. inspection cycle.
Up to $6,715 per
inspection cycle.
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The FAA has have received no definitive data that would enable us
to provide cost estimates for the on-condition actions specified in
this proposed AD.
According to the manufacturer, some or all of the costs of this
proposed AD may be covered under warranty, thereby reducing the cost
impact on affected individuals. The FAA does not control warranty
coverage for affected individuals. As a result, the agency has included
all known costs in its 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.
The FAA is 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.
This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes and associated appliances to the
Director of the System Oversight Division.
Regulatory Findings
The FAA 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) Will not affect intrastate aviation in Alaska, and
(3) 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-2019-0603; Product Identifier
2019-NM-087-AD.
(a) Comments Due Date
The FAA must receive comments by September 23, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 777-300ER and 777F
series airplanes, certificated in any category, as identified in
Boeing Alert Requirements Bulletin 777-53A0091 RB, dated April 8,
2019.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by the design approval
holder (DAH) indicating that the fuselage stringers, stringer
splices, and skin splice straps are subject to widespread fatigue
damage (WFD). The FAA is issuing this AD to address undetected
fatigue cracks, which could adversely affect the structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
[[Page 38892]]
(g) Required Actions
Except as specified by paragraph (h) of this AD: At the
applicable times specified in the ``Compliance'' paragraph of Boeing
Alert Requirements Bulletin 777-53A0091 RB, dated April 8, 2019, do
all applicable actions identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Requirements Bulletin
777-53A0091 RB, dated April 8, 2019.
Note 1 to paragraph (g): Guidance for accomplishing the actions
required by this AD can be found in Boeing Alert Service Bulletin
777-53A0091, dated April 8, 2019, which is referred to in Boeing
Alert Requirements Bulletin 777-53A0091 RB, dated April 8, 2019.
(h) Exceptions to Service Information Specifications
(1) For purposes of determining compliance with the requirements
of this AD: Where Boeing Alert Requirements Bulletin 777-53A0091 RB,
dated April 8, 2019, uses the phrase ``the original issue date of
Requirements Bulletin 777-53A0091 RB'' or ``the original issue date
of this service bulletin,'' this AD requires using ``the effective
date of this AD,'' except where Boeing Alert Requirements Bulletin
777-53A0091 RB, dated April 8, 2019, uses the phrase ``the original
issue date of this service bulletin'' in a note or flag note.
(2) Where Boeing Alert Requirements Bulletin 777-53A0091 RB,
dated April 8, 2019, specifies contacting Boeing for repair
instructions: This AD requires doing the repair before further
flight using a method approved in accordance with the procedures
specified in paragraph (i) of this AD.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle ACO Branch, 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 certification office, send it to the attention of the
person identified in paragraph (j)(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, modification, or alteration required by this AD
if it is approved by The Boeing Company Organization Designation
Authorization (ODA) that has been authorized by the Manager, Seattle
ACO Branch, FAA, 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.
(j) Related Information
(1) For more information about this AD, contact Eric Lin,
Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200
South 216th St., Des Moines, WA 98198; phone and fax: 206-231-3523;
email: [email protected].
(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-
5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this referenced service
information at the FAA, Transport Standards Branch, 2200 South 216th
St., Des Moines, WA. For information on the availability of this
material at the FAA, call 206-231-3195.
Issued in Des Moines, Washington, on July 26, 2019.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-16841 Filed 8-7-19; 8:45 am]
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