Airworthiness Directives; The Boeing Company Airplanes, 30958-30961 [2019-13672]
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30958
Federal Register / Vol. 84, No. 125 / Friday, June 28, 2019 / Proposed Rules
valve (OBV). The FAA is issuing this AD to
prevent failure of the OBV. The unsafe
condition, if not addressed, could result in
engine fire and damage to the airplane.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) For CF34–8C1, CF34–8C5, CF34–
8C5A1, and CF34–8C5B1 model turbofan
engines with serial numbers (S/Ns): 965101
through 965670 inclusive; 194101 through
194999 inclusive; and 195101 through
195653 inclusive:
(i) Perform an inspection of the OBV bleed
air manifold link rod assemblies and the OBV
fuel fittings within 500 flight hours after
November 30, 2017 (effective date of AD
2017–23–06), or before next flight after the
effective date of this AD, whichever occurs
later.
(ii) Within 880 flight hours since the
previous inspection, 500 flight hours from
the effective date of this AD, or 6,880 flight
hours since new, whichever occurs later,
inspect the OBV bleed air manifold link rod
assemblies, the OBV fuel fittings, and the
OBV fuel tubes.
(iii) Thereafter, perform additional repeat
inspections of the OBV bleed air manifold
link rod assemblies, the OBV fuel fittings,
and the OBV fuel tubes within every 880
flight hours since the previous inspection.
(iv) Use the Accomplishment Instructions,
Paragraph 3.B., of GE CF34–8C–AL S/B 75–
0020, R04, dated May 10, 2019 (‘‘the SB’’), to
perform the inspections in paragraphs
(g)(1)(i) through (iii) of this AD and, per the
criteria for the results of inspections in
Paragraph 3.B. of the SB, do the following:
(A) Replace any OBV or fuel tube that is
leaking and tighten or replace any loose OBV
fuel tube clamps with a part eligible for
installation before further flight.
(B) Replace any worn OBV link rod
assembly hardware within 50 flight cycles
after the inspection required by paragraphs
(g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of this AD. The
engine can be returned to service each day
for up to the 50 flight cycles if the OBV
fittings are inspected each day for fuel leaks
and looseness and, if they do not require
removal based on the criteria in Table 1,
‘‘OBV Inspection,’’ of GE SB CF34–8C–AL S/
B 75–0020, R04, dated May 10, 2019.
(2) For CF34–8C5B1 model turbofan
engines with S/Ns not listed in paragraph
(g)(1) of this AD and for all CF34–8C5A2 and
CF34–8C5A3 model turbofan engines,
perform the following:
(i) For engines with 6,000 flight hours or
more since new on the effective date of this
AD, perform an initial inspection of the OBV
bleed air manifold link rod assemblies, OBV
fuel fittings, and OBV fuel tubes within 880
flight hours after the effective date of this AD.
(ii) For engines with less than 6,000 flights
hours since new on the effective date of this
AD, perform an initial inspection of the OBV
bleed air manifold link rod assemblies, OBV
fuel fittings, and OBV fuel tubes within 880
flight hours time in service or 6,880 flight
hours since new, whichever occurs later.
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(iii) Thereafter, repeat the inspection of the
OBV bleed air manifold link rod assemblies,
OBV fuel fittings, and OBV fuel tubes within
880 flight hours since the last inspection.
(iv) Use the Accomplishment Instructions,
Paragraph 3.B., of GE CF34–8C–AL S/B 75–
0020, R04, dated May 10, 2019, to perform
the inspections in paragraphs (g)(2)(i)
through (iii) of this AD.
(v) Replace any parts according to the
criteria in paragraph (g)(1)(iv) of this AD after
the inspection required by paragraphs
(g)(2)(i), (g)(2)(ii), or (g)(2)(iii) of this AD.
(3) For all affected engines, the reporting
instructions in GE SB CF34–8C–AL S/B 75–
0020, R04, dated May 10, 2019, are not
required by this AD.
(h) Credit for Previous Actions
(1) For engines identified in paragraph
(g)(1) of this AD, you may take credit for the
inspection of the OBV bleed air manifold link
rod assemblies and the OBV fuel fittings
required by paragraph (g)(1)(i) of this AD if
you performed this inspection before
November 30, 2017 (the effective date of AD
2017–23–06) using GE SB CF34–8C SB 75–
0019, Revision 01, dated October 24, 2017, or
R00, dated August 4, 2017;
(2) For all affected engines, you may take
credit for the inspection of the OBV bleed air
manifold link rod assemblies and the OBV
fuel fittings required by paragraph (g)(1)(i) or
(g)(2)(i) of this AD if you performed this
inspection before the effective date of this AD
using GE SB CF34–8C SB 75–0020, Revision
03, dated December 14, 2018.
(3) You are still required to perform the
repeat inspections and any replacements, as
needed, required by paragraphs (g)(1)(ii)
through (g)(1)(iv) of this AD.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, ECO 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) of this AD. You
may email your request to: ANE-AD-AMOC@
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.
(j) Related Information
(1) For more information about this AD,
contact Michael Richardson-Bach, Aerospace
Engineer, ECO Branch, FAA, 1200 District
Avenue, Burlington, MA, 01803; phone: 781–
238–7747; fax: 781–238–7199; email:
michael.richardson-bach@faa.gov.
(2) For service information identified in
this AD, contact General Electric Company,
GE-Aviation, Room 285, 1 Neumann Way,
Cincinnati, OH 45215, phone: 513–552–3272;
fax: 513–552–3329; email: geae.aoc@ge.com.
You may view this service information at the
FAA, Engine and Propeller Standards
Branch, 1200 District Avenue, Burlington,
PO 00000
Frm 00003
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MA. For information on the availability of
this material at the FAA, call 781–238–7125.
Issued in Burlington, Massachusetts, on
June 24, 2019.
Robert J. Ganley,
Manager, Engine and Propeller Standards
Branch, Aircraft Certification Service.
[FR Doc. 2019–13761 Filed 6–27–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0438; Product
Identifier 2019–NM–033–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for all
The Boeing Company Model 757
airplanes. This proposed AD was
prompted by a report that during a
maintenance check an operator
discovered cracking in the station 1460
frame web and inner chord between
certain stringers. This proposed AD
would require an inspection of the
fuselage frames for any existing repair,
repetitive surface high frequency eddy
current (HFEC) inspections of the
fuselage frames with a cargo liner
support channel for any cracking, and
applicable on-condition actions. The
FAA is proposing this AD to address the
unsafe condition on these products.
DATES: The FAA must receive comments
on this proposed AD by August 12,
2019.
SUMMARY:
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
https://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
ADDRESSES:
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Federal Register / Vol. 84, No. 125 / Friday, June 28, 2019 / Proposed Rules
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FAA’s Determination
Discussion
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0438; 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:
Peter Jarzomb, Aerospace Engineer,
Airframe Section, FAA, Los Angeles
ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5234; fax: 562–627–
5210; email: peter.jarzomb@faa.gov.
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–2019–0438; Product
Identifier 2019–NM–033–AD’’ at the
beginning of your comments. The FAA
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 https://
www.regulations.gov, including any
personal information you provide. The
course of business or by the means
identified in the ADDRESSES section.
FAA will also post a report
summarizing each substantive verbal
contact the agency receives about this
proposed AD.
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 https://www.regulations.gov by
searching for and locating Docket No.
FAA–2019–0438.
The FAA has received a report
indicating that an operator found
cracking of the aft cargo compartment
frames in the station 1460 frame web
and inner chord between stringers S–26
and S–27 near an existing repair. The
crack initiated at the fastener hole
common to the cargo liner support
channel, and was found near an existing
structural repair manual (SRM) repair.
Primer was discovered in the crack,
indicating that the crack already existed
at the time the SRM repair was
installed. The crack was discovered at
82,227 total flight hours and 37,450 total
flight cycles, and was the result of
fatigue caused by cyclic pressurization
of the fuselage and flight loads. This
condition, if not addressed, could allow
cracks to propagate until they cause a
severed frame, which could result in
additional undetected cracking in
adjacent fuselage frames, and could
ultimately result in reduced structural
integrity of the aft cargo frames and
consequent rapid decompression of the
airplane.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Boeing Alert
Requirements Bulletin 757–53A0113
RB, dated February 22, 2019. The
service information describes
procedures for a general visual
inspection of the fuselage frames with a
cargo liner support channel for any
existing repair, repetitive surface HFEC
inspections of the fuselage frames with
a cargo liner support channel for any
cracking, and applicable on-condition
actions. On-condition actions include a
general visual inspection of the fuselage
frames adjacent to the frame with a
severed inner chord for any existing
repair, a detailed inspection and a
surface HFEC inspection of the fuselage
frames adjacent to a frame with a
severed inner chord for any cracking,
and repair.
This service information is reasonably
available because the interested parties
have access to it through their normal
The FAA is proposing this AD
because the FAA 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 757–53A0113 RB, dated
February 22, 2019, described
previously, except for any differences
identified as exceptions in the
regulatory text of this proposed AD.
For information on the procedures
and compliance times, see this service
information at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0438.
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 544 airplanes of U.S. registry.
The FAA estimates the following costs
to comply with this proposed AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
General visual inspection.
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Labor cost
Parts cost
37 work-hours × $85 per hour = $3,145 ............
16:43 Jun 27, 2019
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Cost per product
$0
$3,145 ..........................
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Cost on U.S. operators
$1,710,880.
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Federal Register / Vol. 84, No. 125 / Friday, June 28, 2019 / Proposed Rules
ESTIMATED COSTS FOR REQUIRED ACTIONS—Continued
Action
Labor cost
Repetitive surface HFEC
inspections.
Up to 37 work-hours × $85 per hour = Up to
$3,145 per inspection cycle.
The FAA estimates the following
costs to do any necessary on-condition
Parts cost
Cost per product
0
Up to $3,145 per inspection cycle.
inspections that would be required. The
FAA has no way of determining the
Cost on U.S. operators
Up to $1,710,880 per
inspection cycle.
number of aircraft that might need these
on-condition inspections:
ESTIMATED COSTS OF ON-CONDITION ACTIONS
Labor cost
Parts cost
Up to 20 work-hour × $85 per hour = Up to $1,700 per inspection cycle ...................
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The FAA has received no definitive
data that would enable us to provide
cost estimates for the on-condition
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.
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
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$0
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
The Boeing Company: Docket No. FAA–
2019–0438; Product Identifier 2019–
NM–033–AD.
(a) Comments Due Date
The FAA must receive comments by
August 12, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing
Company Model 757–200, –200PF, –200CB,
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Cost per product
Up to $1,700 per inspection cycle.
and –300 series airplanes, certificated in any
category.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report that
during a maintenance check an operator
discovered cracking of the aft cargo
compartment frames in the station 1460
frame web and inner chord between certain
stringers. The FAA is issuing this AD to
address cracking at the frame web and inner
chord; such cracks could propagate until they
cause a severed frame, which could result in
additional undetected cracking in adjacent
fuselage frames, and could ultimately result
in reduced structural integrity of the aft cargo
frames and consequent rapid decompression
of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(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 757–53A0113 RB,
dated February 22, 2019, do all applicable
actions identified in, and in accordance with,
the Accomplishment Instructions of Boeing
Alert Requirements Bulletin 757–53A0113
RB, dated February 22, 2019.
Note 1 to paragraph (g): Guidance for
accomplishing the actions required by this
AD can be found in Boeing Alert Service
Bulletin 757–53A0113, dated February 22,
2019, which is referred to in Boeing Alert
Requirements Bulletin 757–53A0113 RB,
dated February 22, 2019.
(h) Exceptions to Service Information
Specifications
(1) For purposes of determining
compliance with the requirements of this AD:
Where Boeing Alert Requirements Bulletin
757–53A0113 RB, dated February 22, 2019,
uses the phrase ‘‘the original issue date of
Requirements Bulletin 757–53A0113 RB,’’
this AD requires using ‘‘the effective date of
this AD,’’ except where Boeing Alert
Requirements Bulletin 757–53A0113 RB,
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Federal Register / Vol. 84, No. 125 / Friday, June 28, 2019 / Proposed Rules
dated February 22, 2019, uses the phrase ‘‘the
original issue date of Requirements Bulletin
757–53A0113 RB’’ in a note or flag note.
(2) Where Boeing Alert Requirements
Bulletin 757–53A0113 RB, dated February
22, 2019, specifies contacting Boeing for
repair instructions or for alternative
inspections: This AD requires doing the
repair, or doing the alternative inspections
and applicable on-condition actions 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)
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(1) The Manager, Los Angeles 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: 9ANM-LAACO-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 Company
Organization Designation Authorization
(ODA) that has been authorized by the
Manager, Los Angeles 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.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 91
[Docket No.: FAA–2019–0451; Notice No.
19–08]
RIN 2120–AL30
Special Flight Authorizations for
Supersonic Aircraft
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
Current regulations prohibit
overland supersonic civil flights in the
United States, but include a procedure
to request authorization for these flights
for the purposes of test and
development of new aircraft. The
criteria for such authorizations were
developed in the 1970s and placed in an
appendix to the operating regulations.
With renewed interest in supersonic
aircraft development, the FAA is
proposing to modernize the procedure
for requesting these special flight
authorizations.
DATES: Send comments on or before
August 27, 2019.
ADDRESSES: Send comments identified
by docket number FAA–2019–0451
using any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov and follow
the online instructions for sending your
comments electronically.
• Mail: Send comments to Docket
Operations, M–30; U.S. Department of
(j) Related Information
Transportation (DOT), 1200 New Jersey
(1) For more information about this AD,
Avenue SE, Room W12–140, West
contact Peter Jarzomb, Aerospace Engineer,
Building Ground Floor, Washington, DC
Airframe Section, FAA, Los Angeles ACO
20590–0001.
Branch, 3960 Paramount Boulevard,
• Hand Delivery or Courier: Take
Lakewood, CA 90712–4137; phone: 562–627–
comments to Docket Operations in
5234; fax: 562–627–5210; email:
peter.jarzomb@faa.gov.
Room W12–140 of the West Building
(2) For service information identified in
Ground Floor at 1200 New Jersey
this AD, contact Boeing Commercial
Avenue SE, Washington, DC, between 9
Airplanes, Attention: Contractual & Data
a.m. and 5 p.m., Monday through
Services (C&DS), 2600 Westminster Blvd.,
Friday, except Federal holidays.
MC 110–SK57, Seal Beach, CA 90740–5600;
• Fax: Fax comments to Docket
telephone 562–797–1717; internet https://
Operations at 202–493–2251.
www.myboeingfleet.com. You may view this
Privacy: In accordance with 5 U.S.C.
referenced service information at the FAA,
553(c), DOT solicits comments from the
Transport Standards Branch, 2200 South
public to better inform its rulemaking
216th St., Des Moines, WA. For information
process. DOT posts these comments,
on the availability of this material at the
without edit, including any personal
FAA, call 206–231–3195.
information the commenter provides, to
Issued in Des Moines, Washington, on June https://www.regulations.gov, as
12, 2019.
described in the system of records
Michael Kaszycki,
notice (DOT/ALL–14 FDMS), which can
Acting Director, System Oversight Division,
be reviewed at https://www.dot.gov/
Aircraft Certification Service.
privacy.
[FR Doc. 2019–13672 Filed 6–27–19; 8:45 am]
Docket: Background documents or
comments received may be read at
BILLING CODE 4910–13–P
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SUMMARY:
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30961
https://www.regulations.gov at any time.
Follow the online instructions for
accessing the docket or go to the Docket
Operations in Room W12–140 of the
West Building Ground Floor at 1200
New Jersey Avenue SE, Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
FOR FURTHER INFORMATION CONTACT:
Mehmet Marsan, Office of Environment
and Energy, AEE–100, Federal Aviation
Administration, 800 Independence
Avenue SW, Washington, DC 20591;
telephone (202) 267–7703; email
mehmet.marsan@faa.gov.
SUPPLEMENTARY INFORMATION:
I. Executive Summary
Civil aircraft may not operate in the
United States in excess of Mach 1
except in accordance with an
authorization issued by the FAA.
Currently, the application requirements
for an authorization are found in
appendix B to 14 CFR part 91,
Authorizations to exceed Mach 1
(§ 91.817). The FAA is proposing to
streamline the application procedure for
these special flight authorizations by
clarifying the information that needs to
be submitted and specifying the contact
office within the FAA. This proposed
rule sets forth those application criteria
in a more user-friendly format.
In this proposed rule, the FAA has
identified three areas to improve
provisions that are currently appendix
B. The first designates to which office in
the agency applicants should send
applications and direct questions. The
second gathers the scattered application
requirements into a list, and presents
them in current regulatory format. As
part of this effort, the FAA is correcting
the language to be consistent throughout
the new section. Third, the agency is
proposing the addition of a new reason
for flight testing to accommodate future
noise certification actions.
This proposal removes the application
criteria and procedure from an appendix
and places it in regulatory text 1 in
accordance with current regulatory
format. This modernization of the
authorization process for certain civil
supersonic flights is intended to
simplify and clarify the process for
applicants interested in the
authorization process.
Finally, while not proposed as a
change, the FAA is requesting comment
on whether a regulatory provision that
has yet to be used should be removed.
1 The material in appendix B was originally
proposed as part of § 91.55 (now § 91.817) but was
moved to an appendix at the suggestion of a
commenter.
E:\FR\FM\28JNP1.SGM
28JNP1
]]>Agencies
[Federal Register Volume 84, Number 125 (Friday, June 28, 2019)]
[Proposed Rules]
[Pages 30958-30961]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-13672]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0438; Product Identifier 2019-NM-033-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 all The Boeing Company Model 757 airplanes. This proposed AD was
prompted by a report that during a maintenance check an operator
discovered cracking in the station 1460 frame web and inner chord
between certain stringers. This proposed AD would require an inspection
of the fuselage frames for any existing repair, repetitive surface high
frequency eddy current (HFEC) inspections of the fuselage frames with a
cargo liner support channel for any cracking, and applicable on-
condition actions. The FAA is proposing this AD to address the unsafe
condition on these products.
DATES: The FAA must receive comments on this proposed AD by August 12,
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 https://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
[[Page 30959]]
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 https://www.regulations.gov by searching
for and locating Docket No. FAA-2019-0438.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0438; 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: Peter Jarzomb, Aerospace Engineer,
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5234; fax: 562-627-
5210; 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-2019-0438;
Product Identifier 2019-NM-033-AD'' at the beginning of your comments.
The FAA 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 https://www.regulations.gov, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact the agency receives about this proposed AD.
Discussion
The FAA has received a report indicating that an operator found
cracking of the aft cargo compartment frames in the station 1460 frame
web and inner chord between stringers S-26 and S-27 near an existing
repair. The crack initiated at the fastener hole common to the cargo
liner support channel, and was found near an existing structural repair
manual (SRM) repair. Primer was discovered in the crack, indicating
that the crack already existed at the time the SRM repair was
installed. The crack was discovered at 82,227 total flight hours and
37,450 total flight cycles, and was the result of fatigue caused by
cyclic pressurization of the fuselage and flight loads. This condition,
if not addressed, could allow cracks to propagate until they cause a
severed frame, which could result in additional undetected cracking in
adjacent fuselage frames, and could ultimately result in reduced
structural integrity of the aft cargo frames and consequent rapid
decompression of the airplane.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Boeing Alert Requirements Bulletin 757-53A0113 RB,
dated February 22, 2019. The service information describes procedures
for a general visual inspection of the fuselage frames with a cargo
liner support channel for any existing repair, repetitive surface HFEC
inspections of the fuselage frames with a cargo liner support channel
for any cracking, and applicable on-condition actions. On-condition
actions include a general visual inspection of the fuselage frames
adjacent to the frame with a severed inner chord for any existing
repair, a detailed inspection and a surface HFEC inspection of the
fuselage frames adjacent to a frame with a severed inner chord for any
cracking, and 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 FAA 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 757-53A0113 RB, dated
February 22, 2019, described previously, except for any differences
identified as exceptions in the regulatory text of this proposed AD.
For information on the procedures and compliance times, see this
service information at https://www.regulations.gov by searching for and
locating Docket No. FAA-2019-0438.
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 544 airplanes of
U.S. registry. The FAA estimates the following costs to comply with
this proposed AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
General visual inspection...... 37 work-hours x $85 per $0 $3,145............ $1,710,880.
hour = $3,145.
[[Page 30960]]
Repetitive surface HFEC Up to 37 work-hours x 0 Up to $3,145 per Up to $1,710,880
inspections. $85 per hour = Up to inspection cycle. per inspection
$3,145 per inspection cycle.
cycle.
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any necessary on-
condition inspections that would be required. The FAA has no way of
determining the number of aircraft that might need these on-condition
inspections:
Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
Labor cost Parts cost Cost per product
------------------------------------------------------------------------
Up to 20 work-hour x $85 per hour $0 Up to $1,700 per
= Up to $1,700 per inspection inspection cycle.
cycle.
------------------------------------------------------------------------
The FAA has received no definitive data that would enable us to
provide cost estimates for the on-condition 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.
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-2019-0438; Product Identifier
2019-NM-033-AD.
(a) Comments Due Date
The FAA must receive comments by August 12, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing Company Model 757-200, -200PF,
-200CB, and -300 series airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report that during a maintenance check
an operator discovered cracking of the aft cargo compartment frames
in the station 1460 frame web and inner chord between certain
stringers. The FAA is issuing this AD to address cracking at the
frame web and inner chord; such cracks could propagate until they
cause a severed frame, which could result in additional undetected
cracking in adjacent fuselage frames, and could ultimately result in
reduced structural integrity of the aft cargo frames and consequent
rapid decompression of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(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 757-53A0113 RB, dated February 22, 2019,
do all applicable actions identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Requirements Bulletin
757-53A0113 RB, dated February 22, 2019.
Note 1 to paragraph (g): Guidance for accomplishing the actions
required by this AD can be found in Boeing Alert Service Bulletin
757-53A0113, dated February 22, 2019, which is referred to in Boeing
Alert Requirements Bulletin 757-53A0113 RB, dated February 22, 2019.
(h) Exceptions to Service Information Specifications
(1) For purposes of determining compliance with the requirements
of this AD: Where Boeing Alert Requirements Bulletin 757-53A0113 RB,
dated February 22, 2019, uses the phrase ``the original issue date
of Requirements Bulletin 757-53A0113 RB,'' this AD requires using
``the effective date of this AD,'' except where Boeing Alert
Requirements Bulletin 757-53A0113 RB,
[[Page 30961]]
dated February 22, 2019, uses the phrase ``the original issue date
of Requirements Bulletin 757-53A0113 RB'' in a note or flag note.
(2) Where Boeing Alert Requirements Bulletin 757-53A0113 RB,
dated February 22, 2019, specifies contacting Boeing for repair
instructions or for alternative inspections: This AD requires doing
the repair, or doing the alternative inspections and applicable on-
condition actions 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, Los Angeles 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, Los
Angeles 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 Peter Jarzomb,
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5234; fax: 562-627-5210; 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 June 12, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-13672 Filed 6-27-19; 8:45 am]
BILLING CODE 4910-13-P
