Airworthiness Directives; The Boeing Company Airplanes, 57155-57158 [2022-19960]
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Federal Register / Vol. 87, No. 180 / Monday, September 19, 2022 / Proposed Rules
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Would not affect intrastate
aviation in Alaska, and
(3) Would 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:
■
Airbus SAS: Docket No. FAA–2022–1166;
Project Identifier MCAI–2022–00407–T.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by November 3,
2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus SAS
airplanes identified in paragraphs (c)(1)
through (7) of this AD, certificated in any
category.
(1) Model A330–201, –202, –203, –223,
–243 airplanes.
(2) Model A330–223F and –243F airplanes.
(3) Model A330–301, –302, –303, –321,
–322, –323, –341, –342, and –343 airplanes.
(4) Model A330–841 airplanes.
(5) Model A330–941 airplanes.
(6) Model A340–211, –212, and –213
airplanes.
(7) Model A340–311, –312, and –313
airplanes.
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(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing gear.
(e) Unsafe Condition
This AD was prompted by a determination
that certain landing gear parts have been
manufactured with improper material or
using a deviating manufacturing processes.
The FAA is issuing this AD to address
possible nose landing gear (NLG) or main
landing gear (MLG) structural fatigue failure
and subsequent collapse, which could result
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57155
in damage to the airplane and injury to
occupants.
changes to procedures or tests identified as
RC require approval of an AMOC.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(j) Related Information
(1) For EASA AD 2022–0049, contact
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221 8999
000; email ADs@easa.europa.eu; internet
easa.europa.eu. You may find this EASA AD
on the EASA website at ad.easa.europa.eu.
You may view this material at the FAA,
Airworthiness Products Section, Operational
Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195. This material may be found
in the AD docket at regulations.gov by
searching for and locating Docket No. FAA–
2022–1166.
(2) For more information about this AD,
contact Vladimir Ulyanov, Aerospace
Engineer, Large Aircraft Section, FAA,
International Validation Branch, 2200 South
216th St., Des Moines, WA 98198; telephone
206–231–3229; email vladimir.ulyanov@
faa.gov.
(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, European Union Aviation
Safety Agency (EASA) AD 2022–0049, dated
March 21, 2022 (EASA AD 2022–0049).
(h) Exceptions to EASA AD 2022–0049
(1) Where the affected part and serviceable
part definitions in EASA AD 2022–0049 refer
to ‘‘the SB,’’ replace the text ‘‘the SB’’ with
‘‘Airbus Service Bulletin A330–32–3302,
dated January 18, 2022; or Airbus Service
Bulletin A340–4321, dated January 18, 2022;
as applicable.’’
(2) Where EASA AD 2022–0049 refers to its
effective date, this AD requires using the
effective date of this AD.
(3) The ‘‘Remarks’’ section of EASA AD
2022–0049 does not apply to this AD.
(i) Additional AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Large Aircraft
Section, International Validation 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 responsible Flight
Standards Office, as appropriate. If sending
information directly to the Large Aircraft
Section, International Validation Branch,
send it to the attention of the person
identified in paragraph (j)(2) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the responsible
Flight Standards Office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, Large Aircraft Section,
International Validation Branch, FAA; or
EASA; or Airbus SAS’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(3) Required for Compliance (RC): Except
as required by paragraph (i)(2) of this AD, if
any service information contains procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
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 procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
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Issued on September 13, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2022–20089 Filed 9–16–22; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2022–1054; Project
Identifier AD–2022–00278–T]
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
supersede Airworthiness Directive (AD)
2017–18–05, which applies to all The
Boeing Company Model 747–100, 747–
100B, 747–100B SUD, 747–200B, 747–
200C, 747–200F, 747–300, 747–400,
747–400D, 747–400F, 747SR, and 747SP
series airplanes. AD 2017–18–05
requires repetitive replacement or
inspection of certain fuse pins, and
applicable on-condition actions. Since
the FAA issued AD 2017–18–05, it has
been determined that adding repetitive
ultrasonic testing (UT) inspections of
the fuse pin of the wing landing gear
beam end fitting for any cracking and
the option for repetitive replacement of
certain corrosion-resistant (stainless)
steel (CRES) fuse pins and steel alloy
fuse pins is necessary to address the
SUMMARY:
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Federal Register / Vol. 87, No. 180 / Monday, September 19, 2022 / Proposed Rules
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unsafe condition. This proposed AD
would continue to require the actions in
AD 2017–18–05 and would also require
repetitive replacement of certain fuse
pins at the wing landing gear beam end
fitting, and repetitive inspections of the
fuse pin for any cracking and applicable
on-condition actions. This proposed AD
would also revise the applicability by
adding airplanes. 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 November 3,
2022.
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
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
90740–5600; telephone 562–797–1717;
internet www.myboeingfleet.com. You
may view this service information at the
FAA, Airworthiness Products Section,
Operational Safety 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 at
www.regulations.gov by searching for
and locating Docket No. FAA–2022–
1054.
Examining the AD Docket
You may examine the AD docket at
www.regulations.gov by searching for
and locating Docket No. FAA–2022–
1054; 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, any
comments received, and other
information. The street address for
Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT:
Stefanie Roesli, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–
231–3964; email: Stefanie.N.Roesli@
faa.gov.
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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 ADDRESSES. Include ‘‘Docket No.
FAA–2022–1054; Project Identifier AD–
2022–00278–T’’ at the beginning of your
comments. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
supporting data. The FAA will consider
all comments received by the closing
date and may amend the proposal
because of those comments.
Except for Confidential Business
Information (CBI) as described in the
following paragraph, and other
information as described in 14 CFR
11.35, the FAA will post all comments
received, without change, to
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.
Confidential Business Information
CBI is commercial or financial
information that is both customarily and
actually treated as private by its owner.
Under the Freedom of Information Act
(FOIA) (5 U.S.C. 552), CBI is exempt
from public disclosure. If your
comments responsive to this NPRM
contain commercial or financial
information that is customarily treated
as private, that you actually treat as
private, and that is relevant or
responsive to this NPRM, it is important
that you clearly designate the submitted
comments as CBI. Please mark each
page of your submission containing CBI
as ‘‘PROPIN.’’ The FAA will treat such
marked submissions as confidential
under the FOIA, and they will not be
placed in the public docket of this
NPRM. Submissions containing CBI
should be sent to Stefanie Roesli,
Aerospace Engineer, Airframe Section,
FAA, Seattle ACO Branch, 2200 South
216th St., Des Moines, WA 98198;
phone and fax: 206–231–3964; email:
Stefanie.N.Roesli@faa.gov. Any
commentary that the FAA receives that
is not specifically designated as CBI will
be placed in the public docket for this
rulemaking.
Background
The FAA issued AD 2017–18–05;
Amendment 39–19014 (82 FR 41331,
August 31, 2017) (AD 2017–18–05), for
all The Boeing Company Model 747–
100, 747–100B, 747–100B SUD, 747–
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200B, 747–200C, 747–200F, 747–300,
747–400, 747–400D, 747–400F, 747SR,
and 747SP airplanes. AD 2017–18–05
was prompted by a report of damage
found at the lower trailing edge panels
of the left wing and a broken fuse pin
of the landing gear beam end fitting. AD
2017–18–05 requires repetitive
replacement or inspection of certain
fuse pins, and applicable on-condition
actions. The agency issued AD 2017–
18–05 to detect and correct cracking in
the fuse pin of the wing landing gear
beam end fitting. A broken fuse pin will
not support the wing landing gear beam,
causing damage to the surrounding
structure, including flight control cables
and hydraulic systems, which could
result in loss of controllability of the
airplane.
Actions Since AD 2017–18–05 Was
Issued
Since the FAA issued AD 2017–18–
05, it has been determined that adding
repetitive UT inspections of the fuse pin
of the wing landing gear beam end
fitting for any cracking and the option
for repetitive replacement of certain
CRES fuse pins and steel alloy fuse pins
is necessary to address the unsafe
condition.
In addition, Model 747–8F and 747–
8 series airplanes have been added to
the applicability. Analysis showed that
Model 747–8F and 747–8 series
airplanes have a similar fuse pin in the
same location as on Model 747–400
series airplanes, and these fuse pins are
susceptible to fatigue cracks on the
inner and outer surfaces.
FAA’s Determination
The FAA is issuing this NPRM after
determining that the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design.
Related Service Information Under
1 CFR Part 51
The FAA reviewed Boeing Alert
Service Bulletin 747–57A2360, Revision
1, dated February 9, 2022. This service
information specifies procedures for
optional repetitive replacement of
certain steel alloy fuse pins or CRES
fuse pins with new or serviceable fuse
pins, at the wing landing gear beam end
fitting; and repetitive magnetic particle
inspections, or repetitive surface high
frequency eddy current (HFEC) and UT
testing inspections, of the fuse pin of the
wing landing gear beam end fitting for
any cracking and corrosion and
applicable on-condition actions. Oncondition actions includes replacing
with steel alloy or CRES fuse pins, and
doing magnetic particle, surface HFEC,
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Federal Register / Vol. 87, No. 180 / Monday, September 19, 2022 / Proposed Rules
and UT testing inspections, and
replacing cracked fuse pins.
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.
Proposed AD Requirements in This
NPRM
Although this proposed AD does not
explicitly restate the requirements of AD
2017–18–05, this proposed AD would
retain all of the requirements of AD
2017–18–05. Those requirements are
referenced in the service information
identified previously, which, in turn, is
referenced in paragraph (g) of this
proposed AD. This proposed AD would
add airplanes to the applicability. This
proposed AD would also require
accomplishment of the actions
identified as ‘‘RC’’ (required for
compliance) in the Accomplishment
Instructions of Boeing Alert Service
Bulletin 747–57A2360, Revision 1,
dated February 9, 2022, described
previously.
57157
For information on the procedures
and compliance times, see this service
information at www.regulations.gov by
searching for and locating Docket No.
FAA–2022–1054.
Costs of Compliance
The FAA estimates that this AD, if
adopted as proposed, would affect 207
airplanes of U.S. registry. The FAA
estimates the following costs to comply
with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Fuse pin replacement 1 (retained actions from AD
2017–18–05).
Magnetic particle inspection 1
(retained actions from AD
2017–18–05).
Surface inspection 1 (retained
actions from AD 2017–18–
05).
CRES fuse pin replacement 1
(new proposed action).
Steel alloy fuse pin replacement1 (new proposed action).
Surface HFEC and UT inspections1 (new proposed
action).
1
Parts cost
Up to 46 work–hours × $85
per hour = $3,910 per replacement cycle.
Up to 48 work–hours × $85
per hour = $4,080 per inspection cycle.
Up to 10 work–hours × $85
per hour = $850 per inspection cycle.
Up to 46 work–hours × $85
per hour = $3,910 per replacement cycle.
Up to 46 work–hours × $85
per hour = $3,910 per replacement cycle.
Up to 11 work–hours × $85
per hour = $935 per inspection cycle.
Cost per product
Cost on U.S. operators
Up to $15,150 ..
Up to $19,060 per replacement cycle.
Up to $3,945,420 per replacement cycle.
$0 .....................
Up to $4,080 per inspection
cycle.
Up to $844,560 per inspection cycle.
$0 .....................
Up to $850 per inspection
cycle.
Up to $175,950 per inspection cycle.
$9,007 ..............
Up to $12,917 per replacement cycle.
Up to $2,673,819 per replacement cycle.
$9,693 ..............
Up to $13,603 per replacement cycle.
Up to $2,815,821 per replacement cycle.
$0 .....................
Up to $935 per inspection
cycle.
Up to $193,545 per inspection cycle.
Operators may choose which action they want to use.
The FAA estimates the following
costs to do any necessary replacements
and inspections that would be required
based on the results of the proposed
inspections. The FAA has no way of
determining the number of aircraft that
might need these replacements and
inspections:
ON-CONDITION COSTS
Action
Labor cost
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CRES fuse pin replacement .........................................
Steel alloy fuse pin replacement ..................................
Magnetic particle inspection .........................................
Surface HFEC and UT inspections ..............................
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
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16:37 Sep 16, 2022
Jkt 256001
46
46
48
11
work-hours
work-hours
work-hours
work-hours
×
×
×
×
$85
$85
$85
$85
per
per
per
per
hour
hour
hour
hour
=
=
=
=
Parts cost
$3,910 ......................
$3,910 ......................
$4,080 ......................
$935 .........................
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
The FAA has 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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$9,007
9,693
0
0
Cost per
product
$12,917
13,603
4,080
935
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Would not affect intrastate
aviation in Alaska, and
(3) Would not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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Federal Register / Vol. 87, No. 180 / Monday, September 19, 2022 / Proposed Rules
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:
a. Removing Airworthiness Directive
(AD) 2017–18–05; Amendment 39–
19014 (82 FR 41331, August 31, 2017),
and
■ b. Adding the following new AD:
■
■
The Boeing Company: Docket No. FAA–
2022–1054; Project Identifier AD–2022–
00278–T.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) action by
November 3, 2022.
(b) Affected ADs
This AD replaces AD 2017–18–05;
Amendment 39–19014 (82 FR 41331, August
31, 2017) (AD 2017–18–05).
(c) Applicability
This AD applies to all The Boeing
Company Model 747–100, 747–100B, 747–
100B SUD, 747–200B, 747–200C, 747–200F,
747–300, 747–400, 747–400D, 747–400F,
747SR, 747SP, 747–8F, and 747–8 series
airplanes, certificated in any category.
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(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by a report of
damage found at the lower trailing edge
panels of the left wing and a broken fuse pin
of the landing gear beam end fitting, and the
determination that repetitive ultrasonic
testing inspections of the fuse pin for any
cracking and optional repetitive replacement
of certain CRES and steel alloy fuse pins is
necessary to address the unsafe condition.
The FAA is issuing this AD to detect and
correct cracking in the fuse pin of the wing
landing gear beam end fitting. A broken fuse
pin will not support the wing landing gear
beam, causing damage to the surrounding
structure, including flight control cables and
hydraulic systems, which could result in loss
of controllability of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Required Actions
Except as specified by paragraph (h) of this
AD: At the applicable times specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–57A2360,
Revision 1, dated February 9, 2022, do all
applicable actions identified as ‘‘RC’’
(required for compliance) in, and in
accordance with, the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–57A2360, Revision 1, dated February 9,
2022.
(h) Exceptions to Service Information
Specifications
(1) Where the Compliance Time columns
of the tables in the ‘‘Compliance’’ paragraph
of Boeing Alert Service Bulletin 747–
57A2360, Revision 1, dated February 9, 2022,
use the phrase ‘‘the original issue date of this
service bulletin,’’ this AD requires using the
date of October 5, 2017 (the effective date of
AD 2017–18–05).
(2) Where the Compliance Time columns
of the tables in the ‘‘Compliance’’ paragraph
of Boeing Alert Service Bulletin 747–
57A2360, Revision 1, dated February 9, 2022,
use the phrase ‘‘the Revision 1 date of this
service bulletin,’’ this AD requires using ‘‘the
effective date 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 responsible Flight
Standards 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-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 responsible Flight Standards 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.
(4) Except as specified by paragraph (h) of
this AD: For service information that
contains steps that are labeled as Required
for Compliance (RC), the provisions of
paragraphs (i)(4)(i) and (ii) of this AD apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
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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 Stefanie Roesli, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch,
2200 South 216th St., Des Moines, WA
98198; phone and fax: 206–231–3964; email:
Stefanie.N.Roesli@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 90740–5600;
telephone 562–797–1717; internet
www.myboeingfleet.com. You may view this
referenced service information at the FAA,
Airworthiness Products Section, Operational
Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195.
Issued on August 12, 2022.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2022–19960 Filed 9–16–22; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2022–1117; Airspace
Docket No. 20–AGL–31]
RIN 2120–AA66
Proposed Establishment of Class E
Airspace; Delphi, IN
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
This action proposes to
establish Class E airspace at Delphi, IN.
The FAA is proposing this action to
support new public instrument
procedures.
SUMMARY:
Comments must be received on
or before November 3, 2022.
ADDRESSES: Send comments on this
proposal to the U.S. Department of
Transportation, Docket Operations,
West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590; telephone (202)
366–9826, or (800) 647–5527. You must
identify FAA Docket No. FAA–2022–
1117/Airspace Docket No. 20–AGL–31
at the beginning of your comments. You
DATES:
E:\FR\FM\19SEP1.SGM
19SEP1
]]>Agencies
[Federal Register Volume 87, Number 180 (Monday, September 19, 2022)]
[Proposed Rules]
[Pages 57155-57158]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-19960]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2022-1054; Project Identifier AD-2022-00278-T]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2017-18-05, which applies to all The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SR, and 747SP series airplanes. AD 2017-18-05
requires repetitive replacement or inspection of certain fuse pins, and
applicable on-condition actions. Since the FAA issued AD 2017-18-05, it
has been determined that adding repetitive ultrasonic testing (UT)
inspections of the fuse pin of the wing landing gear beam end fitting
for any cracking and the option for repetitive replacement of certain
corrosion-resistant (stainless) steel (CRES) fuse pins and steel alloy
fuse pins is necessary to address the
[[Page 57156]]
unsafe condition. This proposed AD would continue to require the
actions in AD 2017-18-05 and would also require repetitive replacement
of certain fuse pins at the wing landing gear beam end fitting, and
repetitive inspections of the fuse pin for any cracking and applicable
on-condition actions. This proposed AD would also revise the
applicability by adding airplanes. 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 November 3,
2022.
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 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 90740-5600;
telephone 562-797-1717; internet www.myboeingfleet.com. You may view
this service information at the FAA, Airworthiness Products Section,
Operational Safety 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 at www.regulations.gov by searching for
and locating Docket No. FAA-2022-1054.
Examining the AD Docket
You may examine the AD docket at www.regulations.gov by searching
for and locating Docket No. FAA-2022-1054; 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, any comments
received, and other information. The street address for Docket
Operations is listed above.
FOR FURTHER INFORMATION CONTACT: Stefanie Roesli, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206-231-3964; email:
Stefan[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 ADDRESSES. Include ``Docket No. FAA-2022-1054; Project Identifier
AD-2022-00278-T'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
the proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
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.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to
Stefanie Roesli, Aerospace Engineer, Airframe Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206-
231-3964; email: [email protected]. Any commentary that the FAA
receives that is not specifically designated as CBI will be placed in
the public docket for this rulemaking.
Background
The FAA issued AD 2017-18-05; Amendment 39-19014 (82 FR 41331,
August 31, 2017) (AD 2017-18-05), for all The Boeing Company Model 747-
100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300,
747-400, 747-400D, 747-400F, 747SR, and 747SP airplanes. AD 2017-18-05
was prompted by a report of damage found at the lower trailing edge
panels of the left wing and a broken fuse pin of the landing gear beam
end fitting. AD 2017-18-05 requires repetitive replacement or
inspection of certain fuse pins, and applicable on-condition actions.
The agency issued AD 2017-18-05 to detect and correct cracking in the
fuse pin of the wing landing gear beam end fitting. A broken fuse pin
will not support the wing landing gear beam, causing damage to the
surrounding structure, including flight control cables and hydraulic
systems, which could result in loss of controllability of the airplane.
Actions Since AD 2017-18-05 Was Issued
Since the FAA issued AD 2017-18-05, it has been determined that
adding repetitive UT inspections of the fuse pin of the wing landing
gear beam end fitting for any cracking and the option for repetitive
replacement of certain CRES fuse pins and steel alloy fuse pins is
necessary to address the unsafe condition.
In addition, Model 747-8F and 747-8 series airplanes have been
added to the applicability. Analysis showed that Model 747-8F and 747-8
series airplanes have a similar fuse pin in the same location as on
Model 747-400 series airplanes, and these fuse pins are susceptible to
fatigue cracks on the inner and outer surfaces.
FAA's Determination
The FAA is issuing this NPRM after determining that the unsafe
condition described previously is likely to exist or develop on other
products of the same type design.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Boeing Alert Service Bulletin 747-57A2360,
Revision 1, dated February 9, 2022. This service information specifies
procedures for optional repetitive replacement of certain steel alloy
fuse pins or CRES fuse pins with new or serviceable fuse pins, at the
wing landing gear beam end fitting; and repetitive magnetic particle
inspections, or repetitive surface high frequency eddy current (HFEC)
and UT testing inspections, of the fuse pin of the wing landing gear
beam end fitting for any cracking and corrosion and applicable on-
condition actions. On-condition actions includes replacing with steel
alloy or CRES fuse pins, and doing magnetic particle, surface HFEC,
[[Page 57157]]
and UT testing inspections, and replacing cracked fuse pins.
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.
Proposed AD Requirements in This NPRM
Although this proposed AD does not explicitly restate the
requirements of AD 2017-18-05, this proposed AD would retain all of the
requirements of AD 2017-18-05. Those requirements are referenced in the
service information identified previously, which, in turn, is
referenced in paragraph (g) of this proposed AD. This proposed AD would
add airplanes to the applicability. This proposed AD would also require
accomplishment of the actions identified as ``RC'' (required for
compliance) in the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-57A2360, Revision 1, dated February 9, 2022, described
previously.
For information on the procedures and compliance times, see this
service information at www.regulations.gov by searching for and
locating Docket No. FAA-2022-1054.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 207 airplanes of U.S. registry. The FAA estimates the following
costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Fuse pin replacement \1\ Up to 46 work- Up to $15,150......... Up to $19,060 per Up to $3,945,420
(retained actions from AD 2017- hours x $85 per replacement per replacement
18-05). hour = $3,910 cycle. cycle.
per replacement
cycle.
Magnetic particle inspection Up to 48 work- $0.................... Up to $4,080 per Up to $844,560
\1\ (retained actions from AD hours x $85 per inspection cycle. per inspection
2017-18-05). hour = $4,080 cycle.
per inspection
cycle.
Surface inspection \1\ Up to 10 work- $0.................... Up to $850 per Up to $175,950
(retained actions from AD 2017- hours x $85 per inspection cycle. per inspection
18-05). hour = $850 per cycle.
inspection cycle.
CRES fuse pin replacement \1\ Up to 46 work- $9,007................ Up to $12,917 per Up to $2,673,819
(new proposed action). hours x $85 per replacement per replacement
hour = $3,910 cycle. cycle.
per replacement
cycle.
Steel alloy fuse pin Up to 46 work- $9,693................ Up to $13,603 per Up to $2,815,821
replacement\1\ (new proposed hours x $85 per replacement per replacement
action). hour = $3,910 cycle. cycle.
per replacement
cycle.
Surface HFEC and UT Up to 11 work- $0.................... Up to $935 per Up to $193,545
inspections\1\ (new proposed hours x $85 per inspection cycle. per inspection
action). hour = $935 per cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
\1\ Operators may choose which action they want to use.
The FAA estimates the following costs to do any necessary
replacements and inspections that would be required based on the
results of the proposed inspections. The FAA has no way of determining
the number of aircraft that might need these replacements and
inspections:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
CRES fuse pin replacement..................... 46 work-hours x $85 per hour = $9,007 $12,917
$3,910.
Steel alloy fuse pin replacement.............. 46 work-hours x $85 per hour = 9,693 13,603
$3,910.
Magnetic particle inspection.................. 48 work-hours x $85 per hour = 0 4,080
$4,080.
Surface HFEC and UT inspections............... 11 work-hours x $85 per hour = 0 935
$935.
----------------------------------------------------------------------------------------------------------------
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.
Regulatory Findings
The FAA has 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 that the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
[[Page 57158]]
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:
0
a. Removing Airworthiness Directive (AD) 2017-18-05; Amendment 39-19014
(82 FR 41331, August 31, 2017), and
0
b. Adding the following new AD:
The Boeing Company: Docket No. FAA-2022-1054; Project Identifier AD-
2022-00278-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) action by November 3, 2022.
(b) Affected ADs
This AD replaces AD 2017-18-05; Amendment 39-19014 (82 FR 41331,
August 31, 2017) (AD 2017-18-05).
(c) Applicability
This AD applies to all The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SR, 747SP, 747-8F, and 747-8 series
airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by a report of damage found at the lower
trailing edge panels of the left wing and a broken fuse pin of the
landing gear beam end fitting, and the determination that repetitive
ultrasonic testing inspections of the fuse pin for any cracking and
optional repetitive replacement of certain CRES and steel alloy fuse
pins is necessary to address the unsafe condition. The FAA is
issuing this AD to detect and correct cracking in the fuse pin of
the wing landing gear beam end fitting. A broken fuse pin will not
support the wing landing gear beam, causing damage to the
surrounding structure, including flight control cables and hydraulic
systems, which could result in loss of controllability 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 paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 747-57A2360, Revision 1, dated
February 9, 2022, do all applicable actions identified as ``RC''
(required for compliance) in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2360, Revision 1, dated February 9, 2022.
(h) Exceptions to Service Information Specifications
(1) Where the Compliance Time columns of the tables in the
``Compliance'' paragraph of Boeing Alert Service Bulletin 747-
57A2360, Revision 1, dated February 9, 2022, use the phrase ``the
original issue date of this service bulletin,'' this AD requires
using the date of October 5, 2017 (the effective date of AD 2017-18-
05).
(2) Where the Compliance Time columns of the tables in the
``Compliance'' paragraph of Boeing Alert Service Bulletin 747-
57A2360, Revision 1, dated February 9, 2022, use the phrase ``the
Revision 1 date of this service bulletin,'' this AD requires using
``the effective date 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 responsible Flight Standards 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 responsible Flight Standards 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.
(4) Except as specified by paragraph (h) of this AD: For service
information that contains steps that are labeled as Required for
Compliance (RC), the provisions of paragraphs (i)(4)(i) and (ii) of
this AD apply.
(i) The steps labeled as RC, including substeps under an RC step
and any figures identified in an RC step, must be done to comply
with the AD. If a step or substep is labeled ``RC Exempt,'' then the
RC requirement is removed from that step or substep. An AMOC is
required for any deviations to RC steps, including substeps and
identified figures.
(ii) Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection
program without obtaining approval of an AMOC, provided the RC
steps, including substeps and identified figures, can still be done
as specified, and the airplane can be put back in an airworthy
condition.
(j) Related Information
(1) For more information about this AD, contact Stefanie Roesli,
Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200
South 216th St., Des Moines, WA 98198; phone and fax: 206-231-3964;
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 www.myboeingfleet.com. You
may view this referenced service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 2200
South 216th St., Des Moines, WA. For information on the availability
of this material at the FAA, call 206-231-3195.
Issued on August 12, 2022.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2022-19960 Filed 9-16-22; 8:45 am]
BILLING CODE 4910-13-P
